Copyright: V0.46.001-xxxx for ******************************
Citation: Copyright ® 1993-1999 Tag's Broadcasting Services


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Main index
The Satellite Encyclopedia

devoted to unmanned artificial Earth satellites

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 Alphabetical satellite index

This index does not contain future satellites or programs; use the launch schedule or the search tool to access those.

A

Abrixas

ACTS

Adeos 1

AEM 1

AEM 2

AEM 3

Program: Aeros

Aeros 1

Aeros 2

Afristar

Ajisai

Alexis

Program: Alouette

Alouette 1

Alouette 2

Amos 1

Program: AMPTE

AMPTE CCE

AMPTE IRM

AMPTE UKS

Program: AMS

AMSC 1

Program: Anik

Anik A1

Anik A2

Anik A3

Anik B1

Anik C1

Anik C2

Anik C3

Anik D1

Anik D2

Anik E1

Anik E2

Anna 1B

ANS

Apex

Apple

Program: Apstar

Apstar 1

Apstar 1A

Apstar 2

Apstar 2R

Program: Arabsat

Arabsat 1A

Arabsat 1B

Arabsat 1C

Arabsat 1D

Arabsat 1E

Arabsat 2A

Arabsat 2B

Arabsat 3A

Argos

Program: Ariel

Ariel 1

Ariel 2

Ariel 3

Ariel 4

Ariel 5

Ariel 6

Arsène

Aryabhata

Program: ASC

ASC 1

ASC 2

Program: Asiasat

Asiasat 1

Asiasat 2

Asiasat 3

Asiasat 3S

Astérix

Program: Astra

Astra 1A

Astra 1B

Astra 1C

Astra 1D

Astra 1E

Astra 1F

Astra 1G

Astra 1H

Astra 2A

Astrid 1

Astrid 2

Program: Astro

Astro A

Astro B

Astro C

Astro D

Astron

Program: ATS

ATS 1

ATS 3

ATS 5

ATS 6

Aura

Program: Auréole

Auréole 1

Auréole 2

Auréole 3

Program: Aurora

Aurora 1

Aurora 2

Program: Ayame

Ayame 1

Ayame 2

Azur

B

Badr A

Program: Bhaskara

Bhaskara 1

Bhaskara 2

Program: Bion

Bion 11

Program: Brasilsat

Brasilsat A1

Brasilsat A2

Brasilsat B1

Brasilsat B2

Bremsat

Program: Bsat

Bsat 1A

Bsat 1B

Program: BSB

BSB 1

BSB 2

C

Cakrawarta 1

Castor

Program: Cat

Cat 1

Cat 2

Cat 3

Cat 4

Program: Celestis

Celestis 1

Celestis 2

Cerise

Chandra

Chinastar 1

COBE

Program: Comstar

Comstar 1

Comstar 2

Comstar 3

Comstar 4

Coronas 1

Corsa B

Cos B

Program: Cosmos

Cosmos 0001

Cosmos 0100

Cosmos 0110

Cosmos 0122

Cosmos 0144

Cosmos 0169

Cosmos 0186

Cosmos 0188

Cosmos 0368

Cosmos 0444

Cosmos 0445

Cosmos 0446

Cosmos 0447

Cosmos 0448

Cosmos 0449

Cosmos 0450

Cosmos 0451

Cosmos 0500

Cosmos 0504

Cosmos 0505

Cosmos 0506

Cosmos 0507

Cosmos 0508

Cosmos 0509

Cosmos 0510

Cosmos 0511

Cosmos 0588

Cosmos 0589

Cosmos 0590

Cosmos 0591

Cosmos 0592

Cosmos 0593

Cosmos 0594

Cosmos 0595

Cosmos 0596

Cosmos 0597

Cosmos 0598

Cosmos 0599

Cosmos 0600

Cosmos 0605

Cosmos 0637

Cosmos 0641

Cosmos 0642

Cosmos 0643

Cosmos 0644

Cosmos 0645

Cosmos 0646

Cosmos 0647

Cosmos 0648

Cosmos 0677

Cosmos 0678

Cosmos 0679

Cosmos 0680

Cosmos 0681

Cosmos 0682

Cosmos 0683

Cosmos 0684

Cosmos 0711

Cosmos 0712

Cosmos 0713

Cosmos 0714

Cosmos 0715

Cosmos 0716

Cosmos 0717

Cosmos 0718

Cosmos 0732

Cosmos 0733

Cosmos 0734

Cosmos 0735

Cosmos 0736

Cosmos 0737

Cosmos 0738

Cosmos 0739

Cosmos 0775

Cosmos 0777

Cosmos 0782

Cosmos 0936

Cosmos 0954

Cosmos 1000

Cosmos 1094

Cosmos 1267

Cosmos 1366

Cosmos 1402

Cosmos 1443

Cosmos 1540

Cosmos 1546

Cosmos 1629

Cosmos 1700

Cosmos 1738

Cosmos 1849

Cosmos 1850

Cosmos 1851

Cosmos 1852

Cosmos 1853

Cosmos 1854

Cosmos 1855

Cosmos 1856

Cosmos 1857

Cosmos 1858

Cosmos 1859

Cosmos 1860

Cosmos 1861

Cosmos 1870

Cosmos 1887

Cosmos 1888

Cosmos 1894

Cosmos 1897

Cosmos 1923

Cosmos 1924

Cosmos 1925

Cosmos 1926

Cosmos 1927

Cosmos 1928

Cosmos 1929

Cosmos 1930

Cosmos 1931

Cosmos 1932

Cosmos 1933

Cosmos 1934

Cosmos 1935

Cosmos 1957

Cosmos 1958

Cosmos 1959

Cosmos 1960

Cosmos 1961

Cosmos 1962

Cosmos 1963

Cosmos 1964

Cosmos 1965

Cosmos 1966

Cosmos 1967

Cosmos 1968

Cosmos 1969

Cosmos 1970

Cosmos 1971

Cosmos 1972

Cosmos 1973

Cosmos 1974

Cosmos 1975

Cosmos 1976

Cosmos 1977

Cosmos 1978

Cosmos 1979

Cosmos 1980

Cosmos 1982

Cosmos 1983

Cosmos 1984

Cosmos 1985

Cosmos 1986

Cosmos 1987

Cosmos 1988

Cosmos 1989

Cosmos 1990

Cosmos 1991

Cosmos 1992

Cosmos 1993

Cosmos 1994

Cosmos 1995

Cosmos 1996

Cosmos 1997

Cosmos 1998

Cosmos 1999

Cosmos 2000

Cosmos 2001

Cosmos 2002

Cosmos 2003

Cosmos 2004

Cosmos 2005

Cosmos 2006

Cosmos 2007

Cosmos 2008

Cosmos 2009

Cosmos 2010

Cosmos 2011

Cosmos 2012

Cosmos 2013

Cosmos 2014

Cosmos 2015

Cosmos 2016

Cosmos 2017

Cosmos 2018

Cosmos 2019

Cosmos 2020

Cosmos 2021

Cosmos 2022

Cosmos 2023

Cosmos 2024

Cosmos 2025

Cosmos 2026

Cosmos 2027

Cosmos 2028

Cosmos 2029

Cosmos 2030

Cosmos 2031

Cosmos 2032

Cosmos 2033

Cosmos 2034

Cosmos 2035

Cosmos 2036

Cosmos 2037

Cosmos 2038

Cosmos 2039

Cosmos 2040

Cosmos 2041

Cosmos 2042

Cosmos 2043

Cosmos 2044

Cosmos 2045

Cosmos 2047

Cosmos 2048

Cosmos 2049

Cosmos 2050

Cosmos 2051

Cosmos 2052

Cosmos 2054

Cosmos 2055

Cosmos 2056

Cosmos 2057

Cosmos 2058

Cosmos 2059

Cosmos 2061

Cosmos 2062

Cosmos 2063

Cosmos 2064

Cosmos 2065

Cosmos 2066

Cosmos 2067

Cosmos 2068

Cosmos 2069

Cosmos 2070

Cosmos 2071

Cosmos 2072

Cosmos 2073

Cosmos 2074

Cosmos 2079

Cosmos 2080

Cosmos 2081

Cosmos 2085

Cosmos 2100

Cosmos 2107

Cosmos 2108

Cosmos 2109

Cosmos 2110

Cosmos 2111

Cosmos 2112

Cosmos 2123

Cosmos 2133

Cosmos 2139

Cosmos 2140

Cosmos 2141

Cosmos 2142

Cosmos 2172

Cosmos 2173

Cosmos 2177

Cosmos 2178

Cosmos 2179

Cosmos 2204

Cosmos 2205

Cosmos 2206

Cosmos 2209

Cosmos 2218

Cosmos 2219

Cosmos 2220

Cosmos 2221

Cosmos 2222

Cosmos 2223

Cosmos 2224

Cosmos 2230

Cosmos 2231

Cosmos 2232

Cosmos 2233

Cosmos 2234

Cosmos 2235

Cosmos 2236

Cosmos 2237

Cosmos 2238

Cosmos 2239

Cosmos 2240

Cosmos 2241

Cosmos 2242

Cosmos 2243

Cosmos 2244

Cosmos 2245

Cosmos 2246

Cosmos 2247

Cosmos 2248

Cosmos 2249

Cosmos 2250

Cosmos 2251

Cosmos 2252

Cosmos 2253

Cosmos 2254

Cosmos 2255

Cosmos 2256

Cosmos 2257

Cosmos 2258

Cosmos 2259

Cosmos 2260

Cosmos 2261

Cosmos 2262

Cosmos 2263

Cosmos 2264

Cosmos 2265

Cosmos 2266

Cosmos 2267

Cosmos 2268

Cosmos 2269

Cosmos 2270

Cosmos 2271

Cosmos 2272

Cosmos 2273

Cosmos 2274

Cosmos 2275

Cosmos 2276

Cosmos 2277

Cosmos 2278

Cosmos 2279

Cosmos 2280

Cosmos 2281

Cosmos 2282

Cosmos 2283

Cosmos 2284

Cosmos 2285

Cosmos 2286

Cosmos 2287

Cosmos 2288

Cosmos 2289

Cosmos 2290

Cosmos 2291

Cosmos 2292

Cosmos 2293

Cosmos 2294

Cosmos 2295

Cosmos 2296

Cosmos 2297

Cosmos 2298

Cosmos 2299

Cosmos 2300

Cosmos 2301

Cosmos 2302

Cosmos 2303

Cosmos 2304

Cosmos 2305

Cosmos 2306

Cosmos 2307

Cosmos 2308

Cosmos 2309

Cosmos 2310

Cosmos 2311

Cosmos 2312

Cosmos 2313

Cosmos 2314

Cosmos 2315

Cosmos 2316

Cosmos 2317

Cosmos 2318

Cosmos 2319

Cosmos 2320

Cosmos 2321

Cosmos 2322

Cosmos 2323

Cosmos 2324

Cosmos 2325

Cosmos 2326

Cosmos 2327

Cosmos 2328

Cosmos 2329

Cosmos 2330

Cosmos 2331

Cosmos 2332

Cosmos 2333

Cosmos 2334

Cosmos 2335

Cosmos 2336

Cosmos 2337

Cosmos 2338

Cosmos 2339

Cosmos 2340

Cosmos 2341

Cosmos 2342

Cosmos 2343

Cosmos 2344

Cosmos 2345

Cosmos 2346

Cosmos 2347

Cosmos 2348

Cosmos 2349

Cosmos 2350

Cosmos 2351

Cosmos 2352

Cosmos 2353

Cosmos 2354

Cosmos 2355

Cosmos 2356

Cosmos 2357

Cosmos 2358

Cosmos 2359

Cosmos 2360

Cosmos 2361

Cosmos 2362

Cosmos 2363

Cosmos 2364

Cosmos 2365

Coupon 1

Courier 1B

CTA

CTS

D

Program: Dash

Program: DBS

DBS 1

DBS 2

DBS 3

Delta

Demosat

Denpa

Program: DFS Kopernikus

DFS 1

DFS 2

DFS 3

Program: Diadème

Diadème 1

Diadème 2

Dial-Wika

Diapason

Program: Discoverer

Program: DMSP

DMSP B5D2-3

DMSP B5D2-7

DMSP B5D2-8

DMSP B5D2-9

Program: Dong Fang Hong

Dong Fang Hong 01

Dong Fang Hong 02

Dong Fang Hong 03

Dong Fang Hong 04

Dong Fang Hong 05

Dong Fang Hong 06

Dong Fang Hong 07

Dong Fang Hong 08

Dong Fang Hong 09

Dong Fang Hong 10

Dong Fang Hong 11

Dong Fang Hong 12

Dong Fang Hong 13

Dong Fang Hong 14

Dong Fang Hong 15

Dong Fang Hong 16

Dong Fang Hong 17

Dong Fang Hong 18

Dong Fang Hong 19

Dong Fang Hong 20

Dong Fang Hong 21

Dong Fang Hong 22

Dong Fang Hong 23

Dong Fang Hong 24

Dong Fang Hong 25

Dong Fang Hong 26

Dong Fang Hong 30

Dong Fang Hong 31

Dong Fang Hong 32

Dong Fang Hong 33

Dong Fang Hong 34

Dong Fang Hong 35

Dong Fang Hong 36

Dong Fang Hong 37

Dong Fang Hong 38

Dong Fang Hong 39

Dong Fang Hong 40

Dong Fang Hong 41

Dong Fang Hong 42

Dong Fang Hong 43

Dong Fang Hong 44

Dong Fang Hong 45

Dove

Program: DSCS

DSCS 2-01

DSCS 2-02

DSCS 2-03

DSCS 2-04

DSCS 2-05

DSCS 2-06

DSCS 2-07

DSCS 2-08

DSCS 2-11

DSCS 2-12

DSCS 2-13

DSCS 2-14

DSCS 2-15

DSCS 2-16

DSCS 3-01

DSCS 3-02

DSCS 3-03

DSCS 3-04

DSCS 3-05

DSCS 3-06

DSCS 3-07

DSCS 3-08

DSCS 3-09

DSCS 3-10

Program: DSP

DSP F12

DSP 3-1

DSP 3-2

DSP 3-3

DSP 3-4

DSP 3-5

DSP 3-6

DSP 3-7

Dynamics Explorer 1

Dynamics Explorer 2

E

Early Bird

Program: Echo

Echo 1

Echo 2

Program: Echostar

Echostar 1

Echostar 2

Echostar 3

Echostar 4

Program: Ekran

Ekran 01

Ekran 02

Ekran 03

Ekran 04

Ekran 05

Ekran 06

Ekran 07

Ekran 08

Ekran 09

Ekran 10

Ekran 11

Ekran 12

Ekran 13

Ekran 14

Ekran 15

Ekran 16

Ekran 17

Ekran 18

Ekran 19

Ekran 20

Electro 1

Program: Elektron

Elektron 1

Elektron 2

Elektron 3

Elektron 4

Eole

Program: Eorsat

Equator S

ERBS

Program: ERS

ERS 1

ERS 2

ESA-Geos 1

ESA-Geos 2

Program: Esro

Esro 1A

Esro 1B

Esro 2B

Esro 4

Program: Essa

Essa 1

Essa 2

Essa 3

Essa 4

Essa 5

Essa 6

Essa 7

Essa 8

Essa 9

Program: ETS

ETS 1

ETS 2

ETS 3

ETS 4

ETS 5

ETS 6

ETS 7

Eureca 1

Program: Eutelsat

Eutelsat 1F1

Eutelsat 1F2

Eutelsat 1F3

Eutelsat 1F4

Eutelsat 1F5

Eutelsat 2F1

Eutelsat 2F2

Eutelsat 2F3

Eutelsat 2F4

Eutelsat 2F5

Eutelsat 3F2

Eutelsat 3F3

EUVE

Program: Exos

Exos A

Exos B

Exos C

Exos D

Exosat

Program: Explorer

Explorer 01

Explorer 03

Explorer 04

Explorer 06

Explorer 07

Explorer 08

Explorer 09

Explorer 10

Explorer 11

Explorer 12

Explorer 13

Explorer 14

Explorer 15

Explorer 16

Explorer 17

Explorer 18

Explorer 19

Explorer 20

Explorer 21

Explorer 22

Explorer 23

Explorer 24

Explorer 25

Explorer 26

Explorer 27

Explorer 28

Explorer 29

Explorer 30

Explorer 31

Explorer 32

Explorer 33

Explorer 34

Explorer 36

Explorer 38

Explorer 39

Explorer 40

Explorer 41

Explorer 42

Explorer 43

Explorer 45

Explorer 46

Explorer 47

Explorer 48

Explorer 50

Explorer 51

Explorer 52

Explorer 53

Explorer 54

Explorer 55

EXPRESS (German)

Program: Express

Express 1

Express 2

Eyesat

F

Program: Faisat

Faisat 1

Faisat 2V

Falcon Gold

Program: Fasat

Fasat Alfa

Fasat Bravo

Firewheel

Program: Fleetsatcom

Fleetsatcom 1

Fleetsatcom 2

Fleetsatcom 3

Fleetsatcom 4

Fleetsatcom 5

Fleetsatcom 6

Fleetsatcom 7

Fleetsatcom 8

Forté

Program: Foton

Foton 09

Foton 10

Foton 11

FR 1

Freja

Program: Fuji

Fuji 1A

Fuji 1B

Fuji 2

Fuse

G

Program: Galaxy

Galaxy 1

Galaxy 1R

Galaxy 1R failure

Galaxy 2

Galaxy 3

Galaxy 3R

Galaxy 4

Galaxy 5

Galaxy 6

Galaxy 7

Galaxy 8i

Galaxy 9

Program: Gals

Gals 1

Gals 2

Gamma

Program: GE

GE 1

GE 2

GE 3

GE 5

Program: Geizer

Gemstar

Program: Geo-IK

Geo-IK 1

Geos 3

Geotail

GFO 1

GFZ 1

Program: GGSE

GGSE 1

GGSE 2

GGSE 3

GGSE 4

GGSE 5

Program: Globalstar

Globalstar 1

Globalstar 2

Globalstar 3

Globalstar 4

Globalstar 6

Globalstar 8

Globalstar 14

Globalstar 15

Globalstar 19

Globalstar 22

Globalstar 23

Globalstar 24

Globalstar 25

Globalstar 26

Globalstar 27

Globalstar 28

Globalstar 30

Globalstar 32

Globalstar 35

Globalstar 36

Globalstar 37

Globalstar 38

Globalstar 40

Globalstar 41

Globalstar 42

Globalstar 43

Globalstar 44

Globalstar 45

Globalstar 46

Globalstar 47

Globalstar 48

Globalstar 49

Globalstar 51

Globalstar 52

Globalstar 53

Globalstar 54

Program: Glonass

Program: GMS

GMS 1

GMS 2

GMS 3

GMS 4

GMS 5

Program: Goes

Goes 01

Goes 02

Goes 03

Goes 04

Goes 05

Goes 06

Goes 07

Goes 08

Goes 09

Goes 10

Program: Gonets

Gonets D1-1

Gonets D1-2

Gonets D1-3

Program: Gorizont

Gorizont 01

Gorizont 02

Gorizont 03

Gorizont 04

Gorizont 05

Gorizont 06

Gorizont 07

Gorizont 08

Gorizont 09

Gorizont 10

Gorizont 11

Gorizont 12

Gorizont 13

Gorizont 14

Gorizont 15

Gorizont 16

Gorizont 17

Gorizont 18

Gorizont 19

Gorizont 20

Gorizont 21

Gorizont 22

Gorizont 23

Gorizont 24

Gorizont 25

Gorizont 26

Gorizont 27

Gorizont 28

Gorizont 29

Gorizont 30

Gorizont 31

Gorizont 32

Program: GPS

GPS BI-01

GPS BI-02

GPS BI-03

GPS BI-04

GPS BI-05

GPS BI-06

GPS BI-07

GPS BI-08

GPS BI-09

GPS BI-10

GPS BI-11

GPS BII-01

GPS BII-02

GPS BII-03

GPS BII-04

GPS BII-05

GPS BII-06

GPS BII-07

GPS BII-08

GPS BIIA-10

GPS BIIA-11

GPS BIIA-12

GPS BIIA-13

GPS BIIA-14

GPS BIIA-15

GPS BIIA-16

GPS BIIA-17

GPS BIIA-18

GPS BIIA-19

GPS BIIA-20

GPS BIIA-21

GPS BIIA-22

GPS BIIA-23

GPS BIIA-24

GPS BIIA-25

GPS BIIA-26

GPS BIIA-27

GPS BIIA-28

GPS BIIR-01

GPS BIIR-02

Granat

GRO

Program: Gstar

Gstar 1

Gstar 2

Gstar 3

Gstar 4

H

Haruka

Healthsat

Program: Hélios

Hélios 1A

Program: Heoa

Heao 1

Heao 2

Heao 3

Program: Heos

Heos 1

Heos 2

HETE

Hipparcos

Program: Hispasat

Hispasat 1A

Hispasat 1B

Hotbird 1

Hotbird 2

Hotbird 3

Hotbird 4

Hotbird 5

HST

I

Program: IDSCP

Program: IMEWS

Informator

Injun 3

Program: Inmarsat

Inmarsat 2F1

Inmarsat 2F2

Inmarsat 2F3

Inmarsat 2F4

Inmarsat 3F1

Inmarsat 3F2

Inmarsat 3F3

Inmarsat 3F4

Program: Insat

Insat 1A

Insat 1B

Insat 1C

Insat 1D

Insat 2A

Insat 2B

Insat 2C

Insat 2D

Insat 2E

Intasat

Program: Intelsat

Intelsat 101

Intelsat 201

Intelsat 202

Intelsat 203

Intelsat 204

Intelsat 301

Intelsat 302

Intelsat 303

Intelsat 304

Intelsat 305

Intelsat 306

Intelsat 307

Intelsat 308

Intelsat 401

Intelsat 402

Intelsat 403

Intelsat 404

Intelsat 405

Intelsat 406

Intelsat 407

Intelsat 408

Intelsat 4A01

Intelsat 4A02

Intelsat 4A03

Intelsat 4A04

Intelsat 4A05

Intelsat 4A06

Intelsat 501

Intelsat 502

Intelsat 503

Intelsat 504

Intelsat 505

Intelsat 506

Intelsat 507

Intelsat 508

Intelsat 509

Intelsat 510

Intelsat 511

Intelsat 512

Intelsat 513

Intelsat 514

Intelsat 515

Intelsat 601

Intelsat 602

Intelsat 603

Intelsat 604

Intelsat 605

Intelsat 701

Intelsat 702

Intelsat 703

Intelsat 704

Intelsat 705

Intelsat 706

Intelsat 707

Intelsat 708

Intelsat 709

Intelsat 801

Intelsat 802

Intelsat 803

Intelsat 804

Intelsat 805

Intelsat 806

Intelsat K

Program: Intercosmos

Intercosmos 01

Intercosmos 18

Intercosmos 22

Program: Intersputnik

IRAS

Program: Iridium

Iridium 04

Iridium 05

Iridium 06

Iridium 07

Iridium 08

Iridium 09

Iridium 10

Iridium 11

Iridium 12

Iridium 13

Iridium 14

Iridium 14A

Iridium 16

Iridium 17

Iridium 18

Iridium 19

Iridium 20

Iridium 21

Iridium 21A

Iridium 22

Iridium 23

Iridium 24

Iridium 25

Iridium 26

Iridium 27

Iridium 28

Iridium 29

Iridium 30

Iridium 31

Iridium 32

Iridium 33

Iridium 34

Iridium 35

Iridium 36

Iridium 37

Iridium 38

Iridium 39

Iridium 40

Iridium 41

Iridium 42

Iridium 43

Iridium 44

Iridium 45

Iridium 46

Iridium 47

Iridium 48

Iridium 49

Iridium 50

Iridium 51

Iridium 52

Iridium 53

Iridium 54

Iridium 55

Iridium 56

Iridium 57

Iridium 58

Iridium 59

Iridium 60

Iridium 61

Iridium 62

Iridium 63

Iridium 64

Iridium 65

Iridium 66

Iridium 67

Iridium 68

Iridium 69

Iridium 70

Iridium 71

Iridium 72

Iridium 73

Iridium 74

Iridium 75

Iridium 76

Iridium 77

Iridium 78

Iridium 79

Iridium 80

Iridium 81

Iridium 82

Iridium 83

Iridium 84

Iridium 85

Iridium 86

Iridium 87

Iridium 88

Iridium 89

Program: IRS

IRS 1A

IRS 1B

IRS 1C

IRS 1D

IRS 1E

IRS P2

IRS P3

IRS P4

IRT

Program: ISEE

ISEE 1

ISEE 2

Program: Isis

Isis 1

Isis 2

ISO

Program: Italsat

Italsat 1

Italsat 2

Itamsat

Itos

IUE

J

Program: Jcsat

Jcsat 1

Jcsat 2

Jcsat 3

Jcsat 4

Jcsat 5

Jcsat 6

JERS 1

K

Program: KH

KH 1-2

KH 1-5

KH 4-01

KH 4A-03

KH 7-01

KH 9-01

KH 11-1

KH 11-2

KH 11-3

KH 11-6

KH 11-7

KH 11-8

KH 12-1

KH 12-2

KH 12-3

Program: Kitsat

Kitsat A

Kitsat B

Kitsat 3

Program: Koreasat

Koreasat 1

Koreasat 2

Kwangmyongsong 1

L

Program: Lacrosse

Lacrosse 1

Lacrosse 2

Lacrosse 3

Program: Lageos

Lageos 1

Lageos 2

Program: Landsat

Landsat 1

Landsat 2

Landsat 3

Landsat 4

Landsat 5

Landsat 6

Landsat 7

Program: LCS

LCS 1

LCS 4

LDEF

Program: Leasat

Leasat 1

Leasat 2

Leasat 3

Leasat 4

Leasat 5

Program: LES

LES 1

LES 2

LES 3

LES 4

LES 5

LES 6

LES 8

LES 9

Lewis

Program: Luch

Luch 0

Luch 1

Lusat

M

Program: Mabuhay

Mabuhay 1

Program: Magion

Magion 1

Magion 2

Magion 3

Magion 4

Magion 5

Maqsat B

Maqsat H

Maqsat 3

Program: Marecs

Marecs A

Marecs B1

Marecs B2

Program: Marisat

Marisat 1

Marisat 2

Marisat 3

Program: Measat

Measat 1

Measat 2

Megsat 0

Meteor (US)

Program: Meteor

Meteor 1-01

Meteor 1-02

Meteor 2-01

Meteor 2-21

Meteor 3-03

Meteor 3-05

Meteor 3-06

Program: Meteosat

Meteosat 1

Meteosat 2

Meteosat 3

Meteosat 4

Meteosat 5

Meteosat 6

Meteosat 7

Microlab 1

Program: Midas

Midas 02

Midas 03

Midas 04

Midas 05

Midas 06

Midas 07

Midas 08

Midas 09

Midas 10

Mightysat

Program: Milstar

Milstar 1-1

Milstar 1-2

Milstar 2-1

Program: Minisat

Minisat 01

Miranda

Program: Molniya

Molniya 1-01

Molniya 1-71

Molniya 1-72

Molniya 1-74

Molniya 1-85

Molniya 1-86

Molniya 1-87

Molniya 1-88

Molniya 1-89

Molniya 1-90

Molniya 1-91

Molniya 2-01

Molniya 3-01

Molniya 3-34

Molniya 3-35

Molniya 3-36

Molniya 3-37

Molniya 3-42

Molniya 3-44

Molniya 3-45

Molniya 3-46

Molniya 3-47

Molniya 3-48

Molniya 3-49

Molniya 3-50

Molniya 1-S

Program: Momo

Momo 1A

Momo 1B

Program: Morelos

Morelos 1

Morelos 2

Morelos 3

MSAT 1

Program: MSTI

MSTI 1

MSTI 2

MSTI 3

MSX

Mublcom

Musat

Myojo

N

Program: N Star

N Star A

N Star B

Program: Nadezhda

Nadezhda 1

Nadezhda 2

Nadezhda 3

Nadezhda 4

Nadezhda 5

Program: Nahuel

Nahuel 1A

Program: NATO

Nato 1

Nato 2

Nato 3A

Nato 3B

Nato 3C

Nato 3D

Nato 4A

Nato 4B

Nilesat 101

Program: Nimbus

Nimbus 1

Nimbus 2

Nimbus 3

Nimbus 3A

Nimbus 4

Nimbus 5

Nimbus 6

Nimbus 7

Nimiq

Program: NOAA

NOAA 01

NOAA 02

NOAA 03

NOAA 04

NOAA 05

NOAA 06

NOAA 07

NOAA 08

NOAA 09

NOAA 10

NOAA 11

NOAA 12

NOAA 13

NOAA 14

NOAA 15

NOAA B

Program: NOSS

NOSS 01

NOSS 02

NOSS 03

NOSS 04

NOSS 05

NOSS 06

NOSS 07

NOSS 08

NOSS 09

NOSS 12

NOSS 13

NOSS 14

NOSS 15

Program: Nova

Nova 1

Nova 2

Nova 3

Program: N Star

N Star A

O

Program: OAO

OAO 1

OAO 2

OAO 3

OAO B

Program: Ocean

Ocean O1-1

Ocean O1-2

Ocean O1-3

Ocean O1-4

Ocean O2-1

Program: Oderacs

Oderacs 1A

Oderacs 1B

Oderacs 1C

Oderacs 1D

Oderacs 1E

Oderacs 1F

Oderacs 2A

Oderacs 2B

Oderacs 2C

Oderacs 2D

Oderacs 2E

Oderacs 2F

Program: Offek

Offek 1

Offek 2

Offek 3

Offek 4

OFO

Program: OGO

OGO 1

OGO 2

OGO 3

OGO 4

OGO 5

OGO 6

Ohsumi

Olympus

Program: Optus

Optus A1

Optus A2

Optus A3

Optus B1

Optus B2

Optus B3

Program: Orbcomm

Orbcomm X

Orbcomm XP 1

Orbcomm FM 1

Orbcomm FM 2

Orbcomm FM 3

Orbcomm FM 4

Orbcomm FM 5

Orbcomm FM 6

Orbcomm FM 7

Orbcomm FM 8

Orbcomm FM 9

Orbcomm FM 10

Orbcomm FM 11

Orbcomm FM 12

Orbcomm FM 13

Orbcomm FM 14

Orbcomm FM 15

Orbcomm FM 16

Orbcomm FM 17

Orbcomm FM 18

Orbcomm FM 19

Orbcomm FM 20

Orbcomm FM 21

Orbcomm FM 22

Orbcomm FM 23

Orbcomm FM 24

Orbcomm FM 25

Orbcomm FM 26

Orbcomm FM 27

Orbcomm FM 28

Orbview 2

Program: Orion

Orion 1

Orion 3

Orsted

Program: Oscar

Oscar 01

Oscar 02

Oscar 03

Oscar 04

Oscar 05

Oscar 06

Oscar 07

Oscar 08

Oscar 09 failure

Oscar 10

Oscar 13

Program: OSO

OSO 1

OSO 2

OSO 3

OSO 4

OSO 5

OSO 6

OSO 7

OSO 8

Program: OTS

OTS 1

OTS 2

Program: OV

OV 1-02

OV 1-04

OV 1-05

OV 1-08

OV 1-09

OV 1-10

OV 1-13

OV 1-14

OV 1-19

OV 1-21

OV 2-1

OV 2-3

OV 2-5

OV 3-1

OV 3-2

OV 3-3

OV 3-4

OV 5-5

OV 5-6

OV 5-9

P

Pacsat

Pageos

Program: Palapa

Palapa A1

Palapa A2

Palapa B1

Palapa B2

Palapa B2P

Palapa B2R

Palapa B4

Palapa C1

Palapa C2

Palapa D1

Program: Panamsat

Panamsat 1

Panamsat 2

Panamsat 3

Panamsat 3R

Panamsat 4

Panamsat 5

Panamsat 6

Panamsat 6B

Panamsat 7

Panamsat 8

Pansat

Program: Pegasus

Pegasus 1

Pegasus 2

Pegasus 3

Pegsat

Péole

PMG

Polaire

Polar

Pollux

Posat

Program: Prognoz

Prognoz 01

Prognoz 02

Prognoz 03

Prognoz 04

Prognoz 05

Prognoz 06

Prognoz 07

Prognoz 08

Prognoz 09

Prognoz 10

Prognoz 11

Prognoz 12

Prospero

Program: Proton

Proton 1

Proton 2

Proton 3

Proton 4

Q

Quickscat

R

Radarsat

Radcal

Program: Raduga

Raduga 01

Raduga 02

Raduga 03

Raduga 04

Raduga 05

Raduga 06

Raduga 07

Raduga 08

Raduga 09

Raduga 1-1

Raduga 1-2

Raduga 1-3

Raduga 1-4

Raduga 10

Raduga 11

Raduga 12

Raduga 13

Raduga 14

Raduga 15

Raduga 16

Raduga 17

Raduga 18

Raduga 19

Raduga 20

Raduga 21

Raduga 22

Raduga 23

Raduga 24

Raduga 25

Raduga 26

Raduga 27

Raduga 28

Raduga 29

Raduga 30

Raduga 31

Raduga 32

Raduga 33

Program: Relay

Relay 1

Relay 2

Program: Resurs

Resurs F01

Resurs F02

Resurs F03

Resurs F04

Resurs F05

Resurs F06

Resurs F07

Resurs F08

Resurs F09

Resurs F10

Resurs F11

Resurs F12

Resurs F13

Resurs F14

Resurs F15

Resurs F16

Resurs F17

Resurs F18

Resurs F19

Resurs F20

Resurs F21

Resurs 500

Resurs O1-3

Resurs O1-4

REX 2

Rocsat 1

Program: Rohini

Rohini 1B

Rohini 2

Rohini 3

Program: Eorsat

Rosat

RS 15

Ryusei

S

S80T

SAC A

SAC B

Program: Safir

Safir 1

Safir 2

Program: Sakura

Sakura 1

Sakura 2A

Sakura 2B

Sakura 3A

Sakura 3B

Sampex

Program: San Marco

San Marco 1

San Marco 2

San Marco 3

San Marco 4

San Marco 5

Sara

Program: Sarsat

Program: Satcom

Satcom 1

Satcom 1R

Satcom 2

Satcom 2R

Satcom 3

Satcom 3R

Satcom 4

Satcom C1

Satcom C3

Satcom C4

Satcom K1

Satcom K2

SAX

Program: SBS

SBS 1

SBS 2

SBS 3

SBS 4

SBS 5

SBS 6

Program: SCD

SCD 1

SCD 2

SCD 2A

Score

Seasat

Program: Secor

Secor 01B

Secor 02

Secor 03

Secor 04

Secor 05

Secor 06

Secor 07

Secor 08

Secor 09

Secor 13

Seds 1

Seds 2

Sedsat

SFU

Shinsei

Sich 1

Signe 3

Program: Sinosat 1

Program: Sirio

Sirio 1

Sirio 2

Program: Sirius

Sirius 1

Sirius 2

Sirius 3

Program: Skynet

Skynet 1A

Skynet 1B

Skynet 2A

Skynet 2B

Skynet 4A

Skynet 4B

Skynet 4C

Skynet 4D

Skynet 4E

SME

SMM

Program: SMS

SMS 1

SMS 2

SNOE

Solar A

Program: Solidaridad

Solidaridad 1

Solidaridad 2

Program: Solrad

Solrad 01

Solrad 03

Solrad 06A

Solrad 06B

Solrad 07A

Solrad 07B

Solrad 09

Solrad 10

Solrad 11A

Solrad 11B

Solwind

Program: Spacenet

Spacenet 1

Spacenet 2

Spacenet 3

Spacenet 3R

Program: Spartan

Spartan 101

Spartan 201-1

Spartan 201-2

Spartan 201-3

Spartan 201-4

Spartan 201-5

Spartan 204

Spartan 206

Spartan 207

Program: Spas

Spas 1

Spas 2

Spas 3

Spas 4

Program: Spot

Spot 1

Spot 2

Spot 3

Spot 4

Program: Sputnik

Sputnik 01

Sputnik 02

Sputnik 03

Sputnik 04

Sputnik 05

Sputnik 06

Sputnik 07

Sputnik 09

Sputnik 10

Sputnik 40

Sputnik 41

Sputnik 99

Program: Sret

Sret 1

Sret 2

Program: Sross

Sross 1

Sross 2

Sross 3

Sross C2

Program: Stacksat

ST 1

Starlette

Starshine

Start 1

Program: Statsionar

Statsionar 01

Statsionar 02

Statsionar 03

Statsionar 04

Statsionar 05

Statsionar 06

Statsionar 07

Statsionar 08

Statsionar 09

Statsionar 10

Statsionar 11

Statsionar 12

Statsionar 13

Statsionar 14

Statsionar 15

Statsionar 16

Statsionar 17

Statsionar 19

Statsionar 20

Statsionar 21

Statsionar 22

Statsionar 24

Statsionar 25

Statsionar 26

Statsionar 27

Stella

Program: Step

Step 1

Step 2

Step 3

Step 4

Program: STRV

STRV 1A

STRV 1B

Sunsat

Surfsat 1

Program: Superbird

Superbird A1

Superbird A2

Superbird B

Superbird B1

Superbird C

Swas

Program: Symphonie

Symphonie 1

Symphonie 2

Program: Syncom

Syncom 1

Syncom 2

Syncom 3

T

Taiyo

Program: Tansei

Tansei 1

Tansei 2

Tansei 3

Tansei 4

TD 1A

Program: TDF

TDF 1

TDF 2

Program: TDRS

TDRS 1

TDRS 2

TDRS 3

TDRS 4

TDRS 5

TDRS 6

TDRS 7

Techsat 1

Techsat 2

TELE X

Program: Telecom

Telecom 1A

Telecom 1B

Telecom 1C

Telecom 2A

Telecom 2B

Telecom 2C

Telecom 2D

Program: Teledesic

Teledesic 1

Program: Telstar

Telstar 1

Telstar 2

Telstar 301

Telstar 302

Telstar 303

Telstar 401

Telstar 402

Telstar 402R

Telstar 5

Telstar 6

Temisat

Program: Tempo

Tempo 2

Terriers

Program: Thaicom

Thaicom 1

Thaicom 2

Thaicom 3

Program: Thor

Thor 1

Thor 2

Thor 3

Program: Tiros

Tiros 01

Tiros 02

Tiros 03

Tiros 04

Tiros 05

Tiros 06

Tiros 07

Tiros 08

Tiros 09

Tiros 10

Tiros N

TMSAT

TOMS

Topex Poseidon

Tournesol

Traac

Program: Transit

Transit 2A

Transit 4A

Transit 4B

Transit 5BN1

Transit 5BN2

TRMM

Program: Tsikada

Tsikada 1

TTS 1

TTS 2

Program: Tubsat

Tubsat A

Tubsat B

Tubsat C

Tubsat N

Tubsat N 1

Program: Turksat

Turksat 1A

Turksat 1B

Program: Tvsat

Tvsat 1

Tvsat 2

U

UARS

Program: UHF

UHF 1

UHF 2

UHF 3

UHF 4

UHF 5

UHF 6

UHF 7

UHF 8

UHF 9

Ume 1

Ume 2

Unamsat 1

Unamsat 2

Program: Uosat

Uosat 1

Uosat 2

Uosat 3

Uosat 4

Uosat 5

Uosat 12

UPMsat 1

Program: USA

V

Program: Vanguard

Vanguard 1

Vanguard 2

Vanguard 3

Program: Vela

Viking

Program: Vitasat

Program: Vortex

Vortex 1

Vortex 2

Vortex 3

Vortex 4

Vortex 5

Vortex 6

W

Webersat

Westpac

Program: Westar

Westar 1

Westar 2

Westar 3

Westar 4

Westar 5

Westar 6

Dial-Wika

Wind 1

Wire

Wresat

WSF 2

X

XTE

Y

YES

Program: Yuri

Yuri 1

Yuri 2A

Yuri 2B

Yuri 2X

Yuri 3A

Yuri 3B

Yuri 3H

Yuri 3N


Designation
 Designation Numbers

Introduction

Objects in space are tracked by the US Space Command. Each object is identified by 2 numbers called the Catalog Number (in the US Space Command database) and the International Launch number. You will find those 2 designators in the General section of each satellite sheet.

The Catalog Number is just an incremented number from the first object launched in space on. To search a satellite by its catalog number, use the search tool (keyword search) and enter "CATNR " followed by that number.

The International Launch Number is a code is composed of the year (2 first digits), by the number of the launch in the year (the 3 next digits) and 2 letters can be added to identify the objects resulting of a launch. Thus number 91026 means the 26th launch in 1991. To search for a launch by number, use the search tool (keyword search) and enter "LAUNR " followed by that number.

Last launches

1999

99044A	18 Aug	Cosmos 2365

99043D	17 Aug	Globalstar 54

99043C	17 Aug	Globalstar 53

99043B	17 Aug	Globalstar 27

99043A	17 Aug	Globalstar 24

99042A	12 Aug	Palapa D1

99041D	25 Jul	Globalstar 48

99041C	25 Jul	Globalstar 43

99041B	25 Jul	Globalstar 28

99041A	25 Jul	Globalstar 26

99040B	23 Jul	Chandra

99040A	23 Jul	STS 93

99039A	17 Jul	Ocean O2-1

99038A	16 Jul	Progress M-42

99037D	10 Jul	Globalstar 51

99037C	10 Jul	Globalstar 35

99037B	10 Jul	Globalstar 30

99037A	10 Jul	Globalstar 32

99036A	08 Jul	Molniya 3-50

99____	05 Jul	Raduga

99035A	24 Jun	Fuse

99034A	20 Jun	Quickscat

99033A	18 Jun	Astra 1H

99032B	11 Jun	Iridium 21A

99032A	11 Jun	Iridium 14A

99031D	10 Jun	Globalstar 47

99031C	10 Jun	Globalstar 25

99031B	10 Jun	Globalstar 49

99031A	10 Jun	Globalstar 52

99030B	05 Jun	Starshine

99030A	27 May	STS 96

99029C	26 May	IRS P4

99029B	26 May	Tubsat C

99029A	26 May	Kitsat 3

99028A	22 May	USA 144

99027A	20 May	Nimiq

99026B	18 May	Mublcom

99026A	18 May	Terriers

99025B	10 May	DFH 47

99025A	10 May	DFH 46

99024A	05 May	Orion 3

99023A	30 Apr	Milstar 2-1

99022B	28 Apr	Megsat 0

99022A	28 Apr	Abrixas

99____	27 Apr	Ikonos 1

99021A	21 Apr	Uosat 12

99020A	15 Apr	Landsat 7

99019D	15 Apr	Globalstar 19

99019C	15 Apr	Globalstar 44

99019B	15 Apr	Globalstar 42

99019A	15 Apr	Globalstar 45

99018A	12 Apr	Eutelsat 3F3

99017A	09 Apr	DSP 3-7

99016A	02 Apr	Insat 2E

99015C	16 Apr	Sputnik 99

99015A	02 Apr	Progress M-41

99014A	28 Mar	Demosat

99013A	21 Mar	Asiasat 3S

99012D	15 Mar	Globalstar 37

99012C	15 Mar	Globalstar 46

99012B	15 Mar	Globalstar 41

99012A	15 Mar	Globalstar 22

99011A	05 Mar	Wire

99010A	28 Feb	Raduga 1-4

99009B	26 Feb	Skynet 4E

99009A	26 Feb	Arabsat 3A

99008C	23 Feb	Sunsat

99008B	23 Feb	Orsted

99008A	23 Feb	Argos

99007A	20 Feb	Soyuz TM-29

99006A	16 Feb	Jcsat 6

99005A	15 Feb	Telstar 6

99004D	09 Feb	Globalstar 40

99004C	09 Feb	Globalstar 38

99004B	09 Feb	Globalstar 23

99004A	09 Feb	Globalstar 36

99003A	07 Feb	Stardust

99002A	27 Jan	Rocsat 1

99001A	03 Jan	Mars Polar Lander

1998

98077C	30 Dec	Cosmos 2364

98077B	30 Dec	Cosmos 2363

98077A	30 Dec	Cosmos 2362

98076A	24 Dec	Cosmos 2361

98075A	22 Dec	Panamsat 6B

98074B	19 Dec	Iridium 89

98074A	19 Dec	Iridium 88

98073A	11 Dec	Mars Climate Observer

98072B	10 Dec	Astrid 2

98072A	10 Dec	Nadezhda 5

98071A	06 Dec	Swas

98070A	06 Dec	Morelos 3

98069C	15 Dec	Mightysat

98069B	14 Dec	SAC A

98069A	04 Dec	STS 88

98068A	22 Nov	Bonum 1

98067A	20 Nov	Zarya

98062C	10 Nov	Sputnik 41

98066E	06 Nov	Iridium 83

98066D	06 Nov	Iridium 84

98066C	06 Nov	Iridium 85

98066B	06 Nov	Iridium 86

98066A	06 Nov	Iridium 87

98065A	04 Nov	Panamsat 8

98064C	29 Oct	Spartan 201-5

98064B	29 Oct	Pansat

98064A	29 Oct	STS 95

98063B	28 Oct	GE 5

98063A	28 Oct	Afristar

98062A	25 Oct	Progress M-40

98061B	24 Oct	Sedsat

98061A	24 Oct	Deep Space 1

98060A	23 Oct	SCD 2

98059A	21 Oct	Maqsat 3

98058A	20 Oct	UHF 9

98057A	09 Oct	Hotbird 5

98056B	05 Oct	Sirius 3

98056A	05 Oct	Eutelsat 3F2

98055A	03 Oct	Stex

98054A	28 Sep	Molniya 1-91

98053H	23 Sep	Orbcomm FM 28

98053G	23 Sep	Orbcomm FM 27

98053F	23 Sep	Orbcomm FM 26

98053E	23 Sep	Orbcomm FM 25

98053D	23 Sep	Orbcomm FM 24

98053C	23 Sep	Orbcomm FM 23

98053B	23 Sep	Orbcomm FM 22

98053A	23 Sep	Orbcomm FM 21

98052A	16 Sep	Panamsat 7

98___	09 Sep	Globalstar 5, 7, 9, 10, 11, 12, 13, 16, 17, 18, 20, 21

98051E	08 Sep	Iridium 77

98051D	08 Sep	Iridium 79

98051C	08 Sep	Iridium 80

98051B	08 Sep	Iridium 81

98051A	08 Sep	Iridium 82

98____	31 Aug	Kwangmyongsong 1

98050A	30 Aug	Astra 2A

98___	27 Aug	Galaxy 10

98049A	25 Aug	ST 1

98048B	19 Aug	Iridium 76

98048A	19 Aug	Iridium 78

98047A	13 Aug	Soyuz TM-28

98____	12 Aug	USA (Mercury 3)

98046H	02 Aug	Orbcomm FM 20

98046G	02 Aug	Orbcomm FM 19

98046F	02 Aug	Orbcomm FM 18

98046E	02 Aug	Orbcomm FM 17

98046D	02 Aug	Orbcomm FM 16

98046C	02 Aug	Orbcomm FM 15

98046B	02 Aug	Orbcomm FM 14

98046A	02 Aug	Orbcomm FM 13

98045A	28 Jul	Cosmos 2360

98044A	18 Jul	Sinosat 1

98043F	10 Jul	Safir 2

98043E	10 Jul	Westpac

98043D	10 Jul	Techsat 2

98043C	10 Jul	TMSAT

98043B	10 Jul	Fasat bravo

98043A	10 Jul	Resurs O1-4

98042B	07 Jul	Tubsat N1

98042A	07 Jul	Tubsat N

98041A	03 Jul	Nozomi (Planet B)

98040A	01 Jul	Molniya 3-49

98039A	25 Jun	Cosmos 2359

98038A	24 Jun	Cosmos 2358

98037A	18 Jun	Intelsat 805

98036F	15 Jun	Cosmos 2357

98036E	15 Jun	Cosmos 2356

98036D	15 Jun	Cosmos 2355

98036C	15 Jun	Cosmos 2354

98036B	15 Jun	Cosmos 2353

98036A	15 Jun	Cosmos 2352

98035A	11 Jun	Thor 3

98034A	02 Jun	STS 91

98033A	30 May	Chinastar 1

98032E	17 May	Iridium 75

98032D	17 May	Iridium 74

98032C	17 May	Iridium 73

98032B	17 May	Iridium 72

98032A	17 May	Iridium 70

98031A	14 May	Progress M-39

98030A	13 May	NOAA 15

98029A	09 May	USA 139

98028A	07 May	Echostar 4

98027A	07 May	Cosmos 2351

98026B	02 May	Iridium 71

98026A	02 May	Iridium 69

98025A	29 Apr	Cosmos 2350

98024B	28 Apr	Bsat 1B

98024A	28 Apr	Nilesat 101

98023D	24 Apr	Globalstar 15

98023C	24 Apr	Globalstar 14

98023B	24 Apr	Globalstar 8

98023A	24 Apr	Globalstar 6

98022A	17 Apr	STS 90

98021G	07 Apr	Iridium 68

98021F	07 Apr	Iridium 67

98021E	07 Apr	Iridium 66

98021D	07 Apr	Iridium 65

98021C	07 Apr	Iridium 64

98021B	07 Apr	Iridium 63

98021A	07 Apr	Iridium 62

98020A	02 Apr	Trace

98019E	30 Mar	Iridium 60

98019D	30 Mar	Iridium 59

98019C	30 Mar	Iridium 58

98019B	30 Mar	Iridium 57

98019A	30 Mar	Iridium 55

98018B	25 Mar	Iridium 61

98018A	25 Mar	Iridium 51

98017A	24 Mar	Spot 4

98016A	16 Mar	UHF 8

98015A	14 Mar	Progress M-38

98014A	28 Feb	Intelsat 806

98013A	27 Feb	Hotbird 4

98012B	26 Feb	Teledesic 1

98012A	26 Feb	SNOE

98011A	21 Feb	Comets

98010E	18 Feb	Iridium 54

98010D	18 Feb	Iridium 53

98010C	18 Feb	Iridium 52

98010B	18 Feb	Iridium 51

98010A	18 Feb	Iridium 50

98009A	17 Feb	Cosmos 2349

98008D	14 Feb	Globalstar 4

98008C	14 Feb	Globalstar 3

98008B	14 Feb	Globalstar 2

98008A	14 Feb	Globalstar 1

98007D	10 Feb	Celestis 2

98007C	10 Feb	Orbcomm FM 4

98007B	10 Feb	Orbcomm FM 3

98007A	10 Feb	GFO 1

98006B	04 Feb	Inmarsat 3F5

98006A	04 Feb	Brasilsat B3

98005A	29 Jan	USA 137

98004A	29 Jan	Soyuz TM-27

98003A	22 Jan	STS 89

98___	22 Jan	Offek 4

98002A	10 Jan	Skynet 4D

98001A	07 Jan	Lunar Prospector

1997

97086A	24 Dec	Asiasat 3

97085A	24 Dec	Early Bird

97084H	23 Dec	Orbcomm FM 12

97084G	23 Dec	Orbcomm FM 11

97084F	23 Dec	Orbcomm FM 10

97084E	23 Dec	Orbcomm FM 9

97084D	23 Dec	Orbcomm FM 8

97084C	23 Dec	Orbcomm FM 7

97084B	23 Dec	Orbcomm FM 6

97084A	23 Dec	Orbcomm FM 5

97083A	22 Dec	Intelsat 804

97082E	20 Dec	Iridium 49

97082D	20 Dec	Iridium 48

97082C	20 Dec	Iridium 47

97082B	20 Dec	Iridium 46

97082A	20 Dec	Iridium 45

97081A	20 Dec	Progress M-37

97080A	15 Dec	Cosmos 2348

97079A	09 Dec	Cosmos 2347

97078A	08 Dec	Galaxy 8i

97077B	08 Dec	Iridium 44

97077A	08 Dec	Iridium 42

97076A	02 Dec	Astra 1G

97075B	02 Dec	Equator S

97075A	02 Dec	Jcsat 5

97074B	27 Nov	ETS 7

97074A	27 Nov	TRMM

97073B	19 Nov	Spartan 201-4

97073A	19 Nov	STS 87

97072A	18 Nov	Resurs F21

97071B	12 Nov	Cakrawarta 1

97071A	12 Nov	Sirius 2

97070A	12 Nov	Coupon 1

97069E	09 Nov	Iridium 38

97069D	09 Nov	Iridium 39

97069C	09 Nov	Iridium 40

97069B	09 Nov	Iridium 41

97069A	09 Nov	Iridium 43

97068A	08 Nov	USA 136

97067A	05 Nov	GPS BIIA-28

97058C	03 Nov	Sputnik 40

97____	02 Nov	SCD 2A

97066C	30 Oct	YES

97066B	30 Oct	Maqsat B

97066A	30 Oct	Maqsat H

97065B	25 Oct	Falcon Gold

97065A	25 Oct	DSCS 3-10

97064A	24 Oct	Lacrosse 3

97063A	22 Oct	Step 4

97062A	16 Oct	Apstar 2R

97061A	15 Oct	Cassini & Huygens

97060A	09 Oct	Foton 11

97059A	05 Oct	Echostar 3

97058A	05 Oct	Progress M-36

97057A	29 Sep	IRS 1D

97056E	27 Sep	Iridium 34

97056D	27 Sep	Iridium 35

97056C	27 Sep	Iridium 36

97056B	27 Sep	Iridium 37

97056A	27 Sep	Iridium 19

97055A	26 Sep	STS 86

97054A	24 Sep	Molniya 1-90

97053A	23 Sep	Intelsat 803

97052B	23 Sep	Faisat 2V

97052A	23 Sep	Cosmos 2346

97051G	14 Sep	Iridium 31

97051F	14 Sep	Iridium 30

97051E	14 Sep	Iridium 28

97051D	14 Sep	Iridium 27

97051C	14 Sep	Iridium 33

97051B	14 Sep	Iridium 32

97051A	14 Sep	Iridium 29

97050A	04 Sep	GE 3

97049B	02 Sep	Meteosat 7

97049A	02 Sep	Hotbird 3

97048B	01 Sep	Dummy Iridium 2

97048A	01 Sep	Dummy Iridium 1

97047A	28 Aug	Forté

97046A	28 Aug	Panamsat 5

97045A	25 Aug	ACE

97044A	23 Aug	Lewis

97043E	21 Aug	Iridium 22

97043D	21 Aug	Iridium 23

97043C	21 Aug	Iridium 24

97043B	21 Aug	Iridium 25

97043A	21 Aug	Iridium 26

97042A	19 Aug	Mabuhay 1

97041A	14 Aug	Cosmos 2345

97040A	08 Aug	Panamsat 6

97039B	07 Aug	SPAS

97039A	07 Aug	STS 85

97038A	05 Aug	Soyuz TM-26

97037A	01 Aug	Orbview 2

97036A	28 Jul	Superbird C

97035A	23 Jul	GPS BIIR-02

97034E	09 Jul	Iridium 21

97034D	09 Jul	Iridium 20

97034C	09 Jul	Iridium 18

97034B	09 Jul	Iridium 17

97034A	09 Jul	Iridium 15

97033A	05 Jul	Progress M35

97032A	01 Jul	STS 94

97031A	25 Jun	Intelsat 802

97030G	18 Jun	iridium 11

97030F	18 Jun	iridium 16

97030E	18 Jun	iridium 13

97030D	18 Jun	iridium 09

97030C	18 Jun	iridium 10

97030B	18 Jun	iridium 12

97030A	18 Jun	iridium 14

97029A	10 Jun	DFH 45

97028A	06 Jun	Cosmos 2344

97027B	03 Jun	Insat 2D

97027A	03 Jun	Inmarsat 3F4

97026A	24 May	Telstar 5

97025A	20 May	Thor 2

97____	20 May	Cosmos (Zenit, was a Tselina 2)

97024A	15 May	Cosmos 2343

97023A	15 May	STS 84

97022A	14 May	Cosmos 2342

97021A	11 May	DFH 44

97020E	05 May	Iridium 04

97020D	05 May	Iridium 05

97020C	05 May	Iridium 06

97020B	05 May	Iridium 07

97020A	05 May	Iridium 08

97019A	25 Apr	Goes 10

97018B	21 Apr	Celestis 1

97018A	21 Apr	Minisat 01

97017A	17 Apr	Cosmos 2341

97016B	16 Apr	Bsat 1A

97016A	16 Apr	Thaicom 3

97015A	09 Apr	Cosmos 2340

97014A	06 Apr	Progress M34

97013A	04 Apr	STS 83

97012A	04 Apr	DMSP B5D2-9

97011A	08 Mar	Tempo 2

97010A	04 Mar	Zeya

97009A	01 Mar	Intelsat 801

97008A	23 Feb	DSP 3-6

97007A	17 Feb	Jcsat 4

97006F	14 Feb	Cosmos 2339

97006E	14 Feb	Cosmos 2338

97006D	14 Feb	Cosmos 2337

97006C	14 Feb	Gonets-D1 6

97006B	14 Feb	Gonets-D1 5

97006A	14 Feb	Gonets-D1 4

97005A	12 Feb	Haruka

97004A	11 Feb	STS 82

97003A	10 Feb	Soyuz TM-25

97002B	30 Jan	Nahuel 1A

97002A	30 Jan	GE 2

97____	17 Jan	GPS BIIR-01

97001A	12 Jan	STS 81

1996

96073A	24 Dec	Bion 11

96072A	20 Dec	USA 129

96071A	20 Dec	Cosmos 2336

96070A	17 Dec	Inmarsat 3F3

96069A	11 Dec	Cosmos 2335

96068A	04 Dec	Pathfinder

96067A	21 Nov	Hotbird 2

96066A	20 Nov	Progress M-33

96065C	22 Nov	WSF

96065B	20 Nov	Orfeus

96065A	19 Nov	STS 80

96064A	16 Nov	Mars 96

96063B	13 Nov	Measat 2

96063A	13 Nov	Arabsat 2B

96062A	07 Nov	MGS

96061A	04 Nov	HETE

96061A	04 Nov	SAC B

96060A	24 Oct	Molniya 3-48

96059A	20 Oct	Dong Fang Hong 43 (FSW 2-3)

96058A	26 Sep	Express 2

96057A	16 Sep	STS 79

96056A	12 Sep	GPS BIIA-27

96055A	11 Sep	Echostar 2

96054A	08 Sep	GE 1

96053A	06 Sep	Inmarsat 3F2

96052B	05 Sep	Unamsat 2

96052A	05 Sep	Cosmos 2334

96051A	04 Sep	Cosmos 2333

96050C	29 Aug	Magion 5

96050B	29 Aug	Prognoz 12

96050A	29 Aug	Musat

96049A	21 Aug	Fast

96048A	18 Aug	Dong Fang Hong 42 (Chinasat 7)

96047A	17 Aug	Soyuz TM-24

96046B	17 Aug	Fuji 2

96046A	17 Aug	Adeos 1

96045A	14 Aug	Molniya 1-89

96044B	08 Aug	Telecom 2D

96044A	08 Aug	Italsat 2

96043A	31 Jul	Progress M-32

96042A	25 Jul	UHF 7

96041A	16 Jul	GPS BIIA-26

96040B	09 Jul	Turksat 1C

96040A	09 Jul	Arabsat 2A

96039A	03 Jul	Apstar 1A

96038A	03 Jul	USA 125

96037A	02 Jul	TOMS

960___	20 Jun	Cosmos (Yantar, aboard Soyuz)

96036A	20 Jun	STS 78

96035A	15 Jun	Intelsat 709

960___	04 Jun	Cluster 1, 2, 3, 4

96034A	25 May	Gorizont 32

96033A	23 May	Galaxy 9

96032B	19 May	Spartan 207

96032A	19 May	STS 77

96031A	17 May	MSTI 3

96030B	16 May	Amos 1

96030A	16 May	Palapa C2

96____	14 May	Cosmos 2333 failure

96029A	12 May	NOSS 15

96028A	05 May	Progress M-31

96027A	30 Apr	SAX

96026A	24 Apr	USA 118

96025A	24 Apr	Cosmos 2332

96024A	24 Apr	MSX

96023A	23 Apr	Priroda

96022A	20 Apr	MSAT 1

96021A	08 Apr	Astra 1F

96020A	03 Apr	Inmarsat 3F1

96019A	28 Mar	GPS BIIA-25

96018A	22 Mar	STS 76

96017A	21 Mar	IRS P3

96016A	14 Mar	Cosmos 2331

96015A	14 Mar	Intelsat 707

96014A	09 Mar	REX 2

96013A	24 Feb	Polar

96012B	26 Feb	TTS 2

96012A	22 Feb	STS 75

96011A	21 Feb	Soyuz TM-23

96010A	19 Feb	Raduga 33

96009F	19 Feb	Cosmos 2330

96009E	19 Feb	Cosmos 2329

96009D	19 Feb	Cosmos 2328

96009C	19 Feb	Gonets D1-3

96009B	19 Feb	Gonets D1-2

96009A	19 Feb	Gonets D1-1

96008A	17 Feb	NEAR

96____	14 Feb	Intelsat 708

96007A	05 Feb	N Star B

96006A	01 Feb	Palapa C1

96005A	25 Jan	Gorizont 31

96004A	16 Jan	Cosmos 2327

96003A	14 Jan	Koreasat 2

96002B	12 Jan	Measat 1

96002A	12 Jan	Panamsat 3R

96001B	11 Jan	Spartan 206

96001A	11 Jan	STS 72

1995

95074A	30 Dec	XTE

95073A	28 Dec	Echostar 1

95072B	28 Dec	Skipper

95072A	28 Dec	IRS 1C

95071A	20 Dec	Cosmos 2326

95070A	18 Dec	Progress M-30

95069A	15 Dec	Galaxy 3R

95068C	14 Dec	Cosmos 2325

95068B	14 Dec	Cosmos 2324

95068A	14 Dec	Cosmos 2323

95067B	06 Dec	Insat 2C

95067A	06 Dec	Telecom 2C

95066A	05 Dec	KH 12-3

95065A	02 Dec	Soho

95064A	28 Nov	Asiasat 2

95063A	17 Nov	Gals 2

95062A	17 Nov	ISO

95061A	12 Nov	STS 74

95060A	06 Nov	Milstar 1-2

95059B	04 Nov	Surfsat 1

95059A	04 Nov	Radarsat

95058A	31 Oct	Cosmos 2322

95____	23 Oct	Meteor (US)

95057A	22 Oct	UHF 6

95056A	20 Oct	STS 73

95055A	19 Oct	Astra 1E

95054A	11 Oct	Luch 1

95053A	08 Oct	Progress M-29

95052A	06 Oct	Cosmos 2321

95051A	29 Sep	Cosmos 2320

95050A	26 Sep	Resurs F20

95049A	24 Sep	Telstar 402R

95048C	11 Sep	WSF 2

95048B	08 Sep	Spartan 201-3

95048A	07 Sep	STS 69

95047A	03 Sep	Soyuz TM-22

95046A	31 Aug	Fasat Alfa

95046A	31 Aug	Sich 1

95045A	30 Aug	Cosmos 2319

95044A	29 Aug	N Star A

95043A	29 Aug	Jcsat 3

95____	15 Aug	Gemstar

95042A	09 Aug	Molniya 3-47

95041A	05 Aug	Koreasat 1

95040A	03 Aug	Panamsat 4

95039F	02 Aug	Magion 4

95039A	02 Aug	Prognoz 11

95038A	31 Jul	DSCS 3-09

95037C	24 Jul	Cosmos 2318

95037C	24 Jul	Cosmos 2317

95037A	24 Jul	Cosmos 2316

95036A	20 Jul	Progress M-28

95035B	13 Jul	TDRS 7

95035A	13 Jul	STS 70

95034A	10 Jul	USA 112

95033C	07 Jul	UPMsat 1

95033B	07 Jul	Cerise

95033A	07 Jul	Hélios 1A

95032A	05 Jul	Cosmos 2315

95031A	28 Jun	Cosmos 2314

95030A	27 Jun	STS 71

95____	22 Jun	Step 3

95029A	10 Jun	DBS 3

95028A	08 Jun	Cosmos 2313

95027A	31 May	UHF 5

95026A	24 May	Cosmos 2312

95025A	23 May	Goes 09

95024A	20 May	Spektr

95023A	17 May	Intelsat 706

95022A	14 May	USA 110

95021A	21 Apr	ERS 2

86017JE	19 Apr	GFZ 1

95020A	09 Apr	Progress M-27

95019A	07 Apr	AMSC 1

95018A	05 Apr	Offek 3

95017C	03 Apr	Microlab 1

95017B	03 Apr	Orbcomm FM2

95017A	03 Apr	Orbcomm FM1

95016B	28 Mar	Hotbird 1

95016A	28 Mar	Brasilsat B2

95___	28 Mar	Techsat 1

95___	28 Mar	Unamsat 1

95___	28 Mar	EKA (Eksperimental'niy Kosmicheskiy Apparat)

95015A	24 Mar	DMSP B5D2-8

95014A	22 Mar	Cosmos 2311

95013A	22 Mar	Intelsat 705

95012A	22 Mar	Cosmos 2310

95011B	17 Mar	GMS 5

95011A	17 Mar	SFU

95010A	14 Mar	Soyuz TM-21

95009C	07 Mar	Cosmos 2309

95009B	07 Mar	Cosmos 2308

95009A	07 Mar	Cosmos 2307

95008A	02 Mar	Cosmos 2306

95007A	02 Mar	STS 67

95006A	16 Feb	Foton 10

95005A	15 Feb	Progress M-26

95004H	04 Feb	Oderacs 2F

95004G	04 Feb	Oderacs 2E

95004F	04 Feb	Oderacs 2D

95004E	04 Feb	Oderacs 2C

95004D	04 Feb	Oderacs 2B

95004C	04 Feb	Oderacs 2A

95004B	07 Feb	Spartan 204

95004A	03 Feb	STS 63

95003A	29 Jan	UHF 4

95002C	24 Jan	Faisat 1

95002B	24 Jan	Astrid 1

95002A	24 Jan	Tsikada 1

95____	15 Jan	EXPRESS (German) (no number assigned)

95001A	10 Jan	Intelsat 704

1994

94089A	30 Dec	NOAA 14

94088A	29 Dec	Cosmos 2305

94087A	28 Dec	Raduga 32

94086F	26 Dec	Cosmos 2304

94086E	26 Dec	Cosmos 2303

94086D	26 Dec	Cosmos 2302

94086C	26 Dec	Cosmos 2301

94086B	26 Dec	Cosmos 2300

94086A	26 Dec	Cosmos 2299

94085A	26 Dec	RS 15

94084A	22 Dec	DSP 3-5

94083A	20 Dec	Cosmos 2298

94082A	16 Dec	Luch 0

94081A	14 Dec	Molniya 1-88

94____	01 Dec	Panamsat 3

94080A	29 Nov	Dong Fang Hong 41

94079A	29 Nov	Orion 1

94078A	24 Nov	Geo-IK 1

94077A	24 Nov	Cosmos 2297

94076C	20 Nov	Cosmos 2296

94076B	20 Nov	Cosmos 2295

94076A	20 Nov	Cosmos 2294

94075A	11 Nov	Progress M-25

94074A	04 Nov	Resurs O1-3

94073B	04 Nov	Spas 4 (Crista)

94073A	03 Nov	STS 66

94072A	02 Nov	Cosmos 2293

94071A	01 Nov	Wind 1

94070A	01 Nov	Astra 1D

94069A	31 Oct	Electro 1

94068A	15 Oct	IRS P2

94067A	13 Oct	Express 1

94066A	11 Oct	Ocean O1-4

94065B	08 Oct	Thaicom 2

94065A	08 Oct	Solidaridad 2

94064A	06 Oct	Intelsat 703

94063A	03 Oct	Soyuz TM-20

94062A	30 Sep	STS 68

94061A	27 Sep	Cosmos 2292

94060A	21 Sep	Cosmos 2291

94059B	13 Sep	Spartan 201-2

94059A	09 Sep	STS 64

94058A	09 Sep	Telstar 402

94057A	29 Aug	DMSP B5D2-7

94056A	28 Aug	ETS 6

94055A	27 Aug	Optus B3

94054A	27 Aug	USA 105

94053A	26 Aug	Cosmos 2290

94052A	25 Aug	Progress M-24

94051A	23 Aug	Molniya 3-46

94050C	11 Aug	Cosmos 2289

94050B	11 Aug	Cosmos 2288

94050A	11 Aug	Cosmos 2287

94049B	11 Aug	Turksat 1B

94049A	11 Aug	Brasilsat B1

94048A	05 Aug	Cosmos 2286

94047A	03 Aug	DBS 2

94046A	03 Aug	Apex

94045A	02 Aug	Cosmos 2285

94044A	29 Jul	Cosmos 2284

94043A	21 Jul	Apstar 1

94042A	20 Jul	Cosmos 2283

94041A	14 Jul	Nadezhda 4

94040B	08 Jul	Yuri 3N

94040A	08 Jul	Panamsat 2

94039A	08 Jul	STS 65

94038A	06 Jul	Cosmos 2282

94037A	03 Jul	Dong Fang Hong 40

94036A	01 Jul	Soyuz TM-19

94____	27 Jun	Step 1

94035A	24 Jun	UHF 3

94034C	17 Jun	STRV 1B

94034B	17 Jun	STRV 1A

94034A	17 Jun	Intelsat 702

94033A	14 Jun	Foton 09

94032A	07 Jun	Cosmos 2281

94____	25 May	Cosmos

94031A	22 May	Progress M-23

94030A	20 May	Gorizont 30

94029A	19 May	Step 2

94028A	09 May	MSTI 2

94027A	04 May	Sross C2

94026A	03 May	USA 103

94025A	28 Apr	Cosmos 2280

94024A	26 Apr	Cosmos 2279

94023A	23 Apr	Cosmos 2278

94022A	13 Apr	Goes 08

94021C	11 Apr	Cosmos 2277

94021B	11 Apr	Cosmos 2276

94021A	11 Apr	Cosmos 2275

94020A	09 Apr	STS 59

94019A	22 Mar	Progress M-22

94018A	17 Mar	Cosmos 2274

94017B	13 Mar	USA 102

94017A	13 Mar	USA 101

94016B	10 Mar	Seds 2

94016A	10 Mar	GPS BIIA-24

94015A	04 Mar	STS 62

94014A	02 Mar	Coronas 1

94013A	19 Feb	Galaxy 1R

94012A	18 Feb	Raduga 31

94011F	12 Feb	Cosmos 2273

94011E	12 Feb	Cosmos 2272

94011D	12 Feb	Cosmos 2271

94011C	12 Feb	Cosmos 2270

94011B	12 Feb	Cosmos 2269

94011A	12 Feb	Cosmos 2268

94010B	08 Feb	Dong Fang Hong 39

94010A	08 Feb	Dong Fang Hong 38

94009A	07 Feb	Milstar 1-1

94008A	05 Feb	Raduga 1-3

94007B	03 Feb	Ryusei (OREX)

94007A	03 Feb	Myojo (VEP)

94006H	09 Feb	Bremsat

94006G	09 Feb	Oderacs 1F

94006F	09 Feb	Oderacs 1E

94006E	09 Feb	Oderacs 1D

94006D	09 Feb	Oderacs 1C

94006C	09 Feb	Oderacs 1B

94006B	09 Feb	Oderacs 1A

94006A	03 Feb	STS 60

94005A	28 Jan	Progress M-21

94004A	25 Jan	DSPSE (Clementine)

94003A	25 Jan	Meteor 3-06

94003B	25 Jan	Tubsat B

94____	24 Jan	Turksat 1A

94____	24 Jan	Eutelsat 2F5

94002A	20 Jan	Gals 1

94001A	08 Jan	Soyuz TM-18

1993

93079A	22 Dec	Molniya 1-87

93078B	18 Dec	Thaicom 1

93078A	18 Dec	DBS 1

93077A	16 Dec	Telstar 401

93076A	08 Dec	Nato 4B

93075A	02 Dec	STS 61

93074A	28 Nov	DSCS 3-08

93073B	20 Nov	Meteosat 6

93073A	20 Nov	Solidaridad 1

93072A	18 Nov	Gorizont 29

93071A	05 Nov	Cosmos 2267

93070A	02 Nov	Cosmos 2266

93069A	28 Oct	Gorizont 28

93068A	26 Oct	GPS BIIA-23

93067A	26 Oct	Cosmos 2265

93066A	22 Oct	Intelsat 701

93065A	18 Oct	STS 58

93064A	11 Oct	Progress M-20

93063A	08 Oct	Dong Fang Hong 37

93____	05 Oct	Landsat 6

93062A	30 Sep	Raduga 30

93061H	26 Sep	Kitsat B

93061G	26 Sep	Posat

93061E	26 Sep	Healthsat

93061D	26 Sep	Itamsat

93061C	26 Sep	Eyesat

93061B	26 Sep	Stella

93061A	26 Sep	Spot 3

93____	20 Sep	IRS 1E

93060A	17 Sep	Cosmos 2264

93059A	16 Sep	Cosmos 2263

93058C	13 Sep	Spas 3

93058B	12 Sep	ACTS

93058A	12 Sep	STS 51

93057A	07 Sep	Cosmos 2262

93056A	03 Sep	UHF 2

93055C	31 Aug	Temisat

93055A	31 Aug	Meteor 2-21

93054A	30 Aug	GPS BIIA-22

93053A	24 Aug	Resurs F19

93052A	10 Aug	Progress M-19

93051A	10 Aug	Cosmos 2261

93050A	09 Aug	NOAA 13

93049A	04 Aug	Molniya 3-45

93____	02 Aug	NOSS 14

93048B	22 Jul	Insat 2B

93048A	22 Jul	Hispasat 1B

93047A	22 Jul	Cosmos 2260

93046A	19 Jul	DSCS 3-07

93045A	14 Jul	Cosmos 2259

93044A	07 Jul	Cosmos 2258

93043A	01 Jul	Soyuz TM-17

93042B	26 Jun	PMG

93042A	26 Jun	GPS BIIA-21

93041A	25 Jun	Radcal

93040A	25 Jun	Resurs F18

93039A	25 Jun	Galaxy 4

93038F	20 Jun	Cosmos 2257

93038E	20 Jun	Cosmos 2256

93038D	20 Jun	Cosmos 2255

93038C	20 Jun	Cosmos 2254

93038B	20 Jun	Cosmos 2253

93038A	20 Jun	Cosmos 2252

93037A	21 Jun	STS 57

93036A	16 Jun	Cosmos 2251

93____	27 May	Gorizont #39

93035A	26 May	Molniya 1-86

93034A	22 May	Progress M-18

93033A	21 May	Resurs F17

93032A	13 May	GPS BIIA-20

93031B	12 May	Arsène

93031A	12 May	Astra 1C

93030F	11 May	Cosmos 2250

93030E	11 May	Cosmos 2249

93030D	11 May	Cosmos 2248

93030C	11 May	Cosmos 2247

93030B	11 May	Cosmos 2246

93030A	11 May	Cosmos 2245

93029A	28 Apr	Cosmos 2244

93028A	27 Apr	Cosmos 2243

93027A	26 Apr	STS 55

93026A	25 Apr	Alexis

93025A	21 Apr	Molniya 3-44

93024A	16 Apr	Cosmos 2242

93023B	11 Apr	Spartan 201-1

93023A	08 Apr	STS 56

93022A	06 Apr	Cosmos 2241

93021A	02 Apr	Cosmos 2240

93020A	01 Apr	Cosmos 2239

93019A	31 Mar	Progress M-17

93018A	30 Mar	Cosmos 2238

93017B	30 Mar	Seds 1

93017A	30 Mar	GPS BIIA-19

93016A	26 Mar	Cosmos 2237

93015A	25 Mar	UHF 1

93014A	25 Mar	Start 1

93013A	25 Mar	Raduga 29

93012A	21 Feb	Progress M-16

93011A	20 Feb	Astro D

93010C	17 Feb	Cosmos 2236

93010B	17 Feb	Cosmos 2235

93010A	17 Feb	Cosmos 2234

93009B	09 Feb	SCD 1

93009A	09 Feb	Orbcomm XP 1

93008A	09 Feb	Cosmos 2233

93007A	03 Feb	GPS BIIA-18

93006A	26 Jan	Cosmos 2232

93005A	24 Jan	Soyuz TM-16

93004A	19 Jan	Cosmos 2231

93003B	13 Jan	TDRS 6

93003A	13 Jan	STS 54

93002A	13 Jan	Molniya 1-85

93001A	12 Jan	Cosmos 2230

1992

92095A	29 Dec	Cosmos 2229 (bion 10)

92094A	25 Dec	Cosmos 2228

92093A	25 Dec	Cosmos 2227

92092A	22 Dec	Cosmos 2226

92091A	22 Dec	Cosmos 2225

92090A	21 Dec	Optus B2

92089A	18 Dec	GPS BIIA-17

92088A	17 Dec	Cosmos 2224

92087A	09 Dec	Cosmos 2223

92086B	02 Dec	USA 089

92086A	02 Dec	STS 53

92085A	02 Dec	Molniya 3-

92084A	01 Dec	Superbird A2

92083A	28 Nov	KH 12-2

92082A	27 Nov	Gorizont 27

92081A	25 Nov	Cosmos 2222

92080A	24 Nov	Cosmos 2221

92079A	23 Nov	GPS BIIA-16

92078A	21 Nov	MSTI 1

86017GX	20 Nov	Mak 2

92077A	20 Nov	Cosmos 2220

92076A	17 Nov	Cosmos 2219

92075A	15 Nov	Resurs 500

92074A	30 Oct	Ekran 20

92073A	29 Oct	Cosmos 2218

92072A	28 Oct	Galaxy 7

92071A	27 Oct	Progress M-15

92070C	31 Oct	CTA

92070B	23 Oct	Lageos 2

92070A	22 Oct	STS 52

92069A	21 Oct	Cosmos 2217

92068F	20 Oct	Cosmos 2216

92068E	20 Oct	Cosmos 2215

92068D	20 Oct	Cosmos 2214

92068C	20 Oct	Cosmos 2213

92068B	20 Oct	Cosmos 2212

92068A	20 Oct	Cosmos 2211

92067A	14 Oct	Molniya 3-42

92066A	12 Oct	DFS 3

92065A	08 Oct	Foton

92064B	06 Oct	Dong Fang Hong 36

92064A	06 Oct	Freja

92063A	25 Sep	Mars Observer

92062A	22 Sep	Cosmos 2210

92061A	12 Sep	STS 47

92060B	10 Sep	Satcom C3

92060A	10 Sep	Hispasat 1A

92059A	10 Sep	Cosmos 2209

92058A	09 Sep	GPS BIIA-15

92057A	31 Aug	Satcom C4

92____	22 Aug	Galaxy 1R failure

92056D	19 Aug	Pion 2

92056C	19 Aug	Pion 1

92056A	19 Aug	Resurs F16

92055A	15 Aug	Progress M-14

92054A	13 Aug	Optus B1

92053A	12 Aug	Cosmos 2208

92052C	10 Aug	S80T

92052B	10 Aug	Kitsat A

92052A	10 Aug	Topex Poseidon

92051A	09 Aug	Dong Fang Hong 35

92050A	06 Aug	Molniya 1-

92049B	31 Jul	Eureca 1

92049A	31 Jul	STS 46

92048A	30 Jul	Cosmos 2207

92047C	29 Jul	Cosmos 2206

92047B	29 Jul	Cosmos 2205

92047A	29 Jul	Cosmos 2204

92046A	27 Jul	Soyuz TM-15

92045A	24 Jul	Cosmos 2203

92044B	24 Jul	DUVE

92044A	24 Jul	Geotail

92043A	14 Jul	Gorizont 26

92042F	13 Jul	Cosmos 2202

92042E	13 Jul	Cosmos 2201

92042D	13 Jul	Cosmos 2200

92042C	13 Jul	Cosmos 2199

92042B	13 Jul	Cosmos 2198

92042A	13 Jul	Cosmos 2297

92041B	09 Jul	Eutelsat 2F4

92041A	09 Jul	Insat 2A

92040A	08 Jul	Cosmos 2196

92039A	07 Jul	GPS BIIA-14

92038A	03 Jul	Sampex

92037A	02 Jul	DSCS 3-06

92036A	01 Jul	Cosmos 2195

92035A	30 Jun	Progress M-13

92034A	25 Jun	STS 50

92033A	23 Jun	Resurs F15

92032A	09 Jun	Intelsat K

92031A	07 Jun	EUVE

92030H	02 Jun	Cosmos 2194

92030G	02 Jun	Cosmos 2193

92030F	02 Jun	Cosmos 2192

92030E	02 Jun	Cosmos 2191

92030D	02 Jun	Cosmos 2190

92030C	02 Jun	Cosmos 2189

92030B	02 Jun	Cosmos 2188

92030A	02 Jun	Cosmos 2187

92029A	28 May	Cosmos 2186

92028A	20 May	Sross 3

92027A	14 May	Palapa B4

92026A	07 May	STS 49

92025A	29 Apr	Cosmos 2185

92024A	29 Apr	Resurs F14

92023A	25 Apr	USA 081

92022A	19 Apr	Progress M-12

92021B	15 Apr	Inmarsat 2F4

92021A	15 Apr	Telecom 2B

92020A	15 Apr	Cosmos 2184

92019A	10 Apr	GPS BIIA-13

92018A	08 Apr	Cosmos 2183

92017A	02 Apr	Gorizont 25

92016A	01 Apr	Cosmos 2182

92015A	24 Apr	STS 45

92014A	17 Mar	Soyuz TM-14

92013A	14 Mar	Galaxy 5

92012A	09 Mar	Cosmos 2181

92011A	04 Mar	Molniya 1-

92010B	26 Feb	Arabsat 1C

92010A	26 Feb	Superbird B1

92009A	23 Feb	GPS BIIA-12

92008A	17 Feb	Cosmos 2180

92007A	11 Feb	JERS 1

92006A	10 Feb	DSCS 3-05

92____	05 Feb	Cosmos FTO

92005C	29 Jan	Cosmos 2179

92005B	29 Jan	Cosmos 2178

92005A	29 Jan	Cosmos 2177

92004A	25 Jan	Progress M-11

92003A	24 Jan	Cosmos 2176

92002A	22 Jan	STS 42

92001A	21 Jan	Cosmos 2175


 TSE

The Satellite Encyclopedia is copyrighted by Tag's Broadcasting Services, © all rights reserved, 1993-1999. Main author: Jean-Philippe Donnio

Section en français

Also to be read:

License Agreement - Order forms

Bibliography reference

Acknowledgment

Versions

Compatible software

Help: how to use this encyclopedia?

TSE in year 2000 compliant

Philosophy of this encyclopedia

This satellite encyclopedia is aimed to gather knowlegde into a single easy to use document. Contributions are welcome... You may even become a coauthor of TSE like Jean-Jacques Serra who manages the launch vehicle section! This encyclopedia is published every 3/4 months. Therefore this software is not a final version!

If you are any kind of satellite specialist, satellite operator or constructor, or a space organization we would be very glad to get in touch with you. If for some reason you feel we are not treating your organization's satellites correctly, understand we only work with data we have! Operators are encouraged to send their Technical User Guide and other technical documentations, including preliminary data when available.

If you are the author of a satellite related book or software, or if your organization publishes a magazine or newsletter related to space or satellite, see our special offer in the license agreement.

The fair play

This encyclopedia is shareware: you can use it on a trial basis during SEVEN days; after this delay you should either register or delete it. The shareware version is size-limited to fit on a 3.5" floppy. Thus numerous EIRP maps are not included so as Russian programs. That's why you get an error when clicking on those items.

If you use The Satellite Encyclopedia after 7 days of trial or for commercial purposes, you MUST register. The registered version includes:

the full help file with:

450 EIRP maps

the listing of satellites on the Clarke Belt

the calendar with the future launches and details about the related satellites

the Russian programs

all the pages and maps (broken links) not available in this version

TSE is like a magazine: the shareware version is like the copy of a magazine you read at the bookshop. Buying this copy is like registering a single issue of TSE. Registering TSE with the subscription option gives you 4 full issues (one year) which is similar to subscribing to the bookshop magazine. The latter also opens you access to the online edition! Turn to the license agreement for more details.

While every precaution has been taken in the compilation of this data, the publisher assumes no responsability for errors or omissions. Neither is any liability assumed for damages resulting from the use of the information contained herein. Please report any errors or omissions.

How to obtain the latest release?

1°/ By registering: see the license agreement

2°/ By downloading:

Internet: see the list of ftp sites at http://www.TBS-satellite.com/tse/  The primary ftp site for TSE is ftp://ftp.TBS-satellite.com/pub/tse/

Online support

Online support is available from the internet via our web server at http://www.TBS-satellite.com/tse/

The online version of TSE is located at http://www.TBS-satellite.com/tse/online/  Check it out for the latest updates of TSE!

You may also subscribe to our mailing lists by email or online. To join the public mailing list, send an email:

To: tag-tse-subscribe@TBS-internet.com

Subject: none

Body: none

Contact

TBS

Suite #214, BP 237, 14012 Caen cedex 1, France

tbs@TBS-satellite.com

Please mention the version of the encyclopedia you currently use.

Providing data

We need:

Your name or alias

Your address

The information with it's precise origin and date

The version of the encyclopedia you currently use

Please ensure that we receives press releases from your company by fax or email:

fax: +33-1-5301-3114

Email: press@TBS-satellite.com


 License Agreement

Order form without VAT

Order form with VAT

License Agreement

The use of The Satellite Encyclopedia is subject to the following terms and conditions.

The Satellite Encyclopedia is copyrighted material. It is protected by the French copyright laws. You may not make any changes or modifications to The Satellite Encyclopedia. You may not decompile, disassemble, or otherwise reverse-engineer the software in any way. No reproduction whatever the method (including internet mirroring).

You may use The Satellite Encyclopedia on a trial basis provided you do not violate the protection afforded the licensed software by the copyright laws, and you agree to the terms of the license agreement. You are entitled to evaluate the software freely for SEVEN days. If you use The Satellite Encyclopedia further on or for COMMERCIAL PURPOSES, you must purchase a license for its use. If you don't use it, delete it.

How much is a license:

See the order forms above. Registration provides you with a personal most updated version which includes:

the full help file with:

450 EIRP maps

the listing of satellites on the Clarke Belt

the calendar with the future launches and details about the related satellites

the Russian programs

all the pages and maps (broken links) not available in this version

Subscriptions (4 issues) are available. A WWW edition is also available, see the prices online.

Special offers:

If you are a firm that publishes an electronic or paper periodical related to satellite (in French or English) you may obtain a free registration and a 1 year update subscription against a free one-year subscription to your publication.

If you are the author of a book related to satellite (in French or English) you may obtain a free registration and a 1 year update subscription against a free copy of your book.

If you are the author of a shareware related to satellite (in French or English) you may obtain a free registration and a 1 year update subscription against a free license for your shareware.

Please note we reserve the right to refuse your application.

Title to the licensed software is not transferred to the end user. The end-user is granted an non exclusive license to use the software on one computer or computer workstation at any given time. Moreover he agrees to only copy the software for backup purpose. This also applies for the WWW edition.

Tag's Broadcasting Services may include the buyers' name and contact information in The Satellite Encyclopedia's promotional materials.

Limited Warranty

While every precaution has been taken in the compilation of this data, the publisher assumes no responsability for errors or omissions. Neither is any liability assumed for damages resulting from the use of the information contained herein.

We shall not be responsible for any problems or damage caused by the licensed software that may result from using the licensed software. This includes, but is not limited to, computer hardware, computer software, operating systems, and any computer or computing accessories. End user agrees not to hold us responsible for any problems arising from the use of the software.

We shall not in any case be liable for any special, incidental, consequential, indirect or other similar damages arising from any breach of these warranties even if we have been advised of the possibility of such damages.

In no case shall our liability exceed the license fees paid for the right to use the licensed software.

In the event of invalidity of any provision of this license, the parties agree that such invalidity shall not affect the validity of the remaining portions of this license.

The Satellite Encyclopedia's Distribution (Winhelp edition only)

The Winhelp edition of The Satellite Encyclopedia must be copied in an unmodified form and must contain all the files required for an automatic installation. No fee, charge or other compensation may be accepted or requested by anyone without our express written permission.

Public Domain disk vendors may not charge a fee for The Satellite Encyclopedia itself. However you may include The Satellite Encyclopedia on a diskette or CD-ROM for which you charge a nominal distribution fee. If it is included on a CD-ROM you must send us a free copy of this CD-ROM. The purchaser of said media must be informed in advance that the fee paid to acquire the media does not relieve said purchaser from paying the registration fee for The Satellite Encyclopedia if said purchaser uses The Satellite Encyclopedia.

Operators of electronic Bulletin Board Systems (sysops) may post The Satellite Encyclopedia for downloading by their users without written permission only as long as the above conditions are met. A fee may be charged for access to the BBS as long as no specific fee is charged for downloading The Satellite Encyclopedia files without first obtaining express written permission from ourselves to charge such a fee. This also goes for Internet and Compuserve; other online services must apply for authorization. As far as the French Minitel is concerned, operators are NOT allowed to offer downloading of The Satellite Encyclopedia.

The above constitutes the license agreement for The Satellite Encyclopedia winhelp edition. It supersedes any and all previous license agreements.


Order form
 Order form without VAT

V0.46.001

      Name: ______________________________________________________

 [Company]: ______________________________________________________

   Address: ______________________________________________________

      City: ____________________________ Postal Code: ____________

   Country: ____________________________ [State]: ________________

     Phone: ________________________ Fax: ________________________

     Email: ______________________________________________________

Current Winhelp issue: with floppies

at EUR 61 each.........................................___x  61   ______

Current Winhelp issue: ftp download (internet)

at EUR 40 each.........................................___x  40   ______

4 issues (1 year) Winhelp subscription: with floppies

at EUR 220 each........................................___x 220   ______

4 issues (1 year) Winhelp subscription: ftp download (internet)

at EUR 143 each........................................___x 143   ______

TOTAL EUR WITHOUT VAT..........................................   ______

EU VAT number (if applicable): ________________________________

PAYMENT

( ) Check (must be drawn on a French bank in EUR or FRF, payable to TBS)

( ) Credit card (Visa/MasterCard):

    Number: ________________________________

Expiration: __________

 Signature: __________________________________________________

      Date: ________________________________

SEND TO:

            TBS

            Suite #214, BP 237, 14012 CAEN cedex 1, France

            Fax: +33-1-5301-3114 (if you fax, please write in ALL CAPS)

            email: tbs@TBS-satellite.com


 Order form with VAT

V0.46.001

WARNING: this order form is only applicable if you are in France or in European Union

      Name: ______________________________________________________

 [Company]: ______________________________________________________

   Address: ______________________________________________________

      City: ____________________________ Postal Code: ____________

   Country: ____________________________ [State]: ________________

     Phone: ________________________ Fax: ________________________

     Email: ______________________________________________________

Current Winhelp issue: with floppies

at EUR 73.57 each.....................................___x 73.57  ______

Current Winhelp issue: ftp download (internet)

at EUR 48.24 each.....................................___x 48.24  ______

4 issues (1 year) Winhelp subscription: with floppies

at EUR 265.32 each....................................___x265.32  ______

4 issues (1 year) Winhelp subscription: ftp download (internet)

at EUR 172.46 each....................................___x172.46  ______

TOTAL EUR (including 20.6% VAT)................................   ______

PAYMENT

( ) Check (must be drawn on a French bank in EUR or FRF, payable to TBS)

( ) Credit card (Visa/MasterCard):

    Number: ________________________________

Expiration: __________

 Signature: __________________________________________________

      Date: ________________________________

SEND TO:

            TBS

            Suite #214, BP 237, 14012 CAEN cedex 1, France

            Fax: +33-1-5301-3114 (if you fax, please write in ALL CAPS)

            email: tbs@TBS-satellite.com


Bibliography
 References

Books

Atlas de géographie de l'Espace (Fr)

Sous la direction de F. Verger, avec Isabelle Sourbès, Raymond Ghirardi et Yvette Palazot

SIDES / RECLUS, 1992

ISBN 2-86861-080-3 / 2-86912-044-1

Encyclopédie Internationale des Sciences et des Techniques (Fr)

1972

L'escalade du Cosmos (Fr)

Patrick Maurel

Bordas, 1972

L'état des sciences et des techniques (Fr)

Sous la direction de Nicolas Witkowski

La découverte, 1991

ISBN 2-7071-2069-3

Fusées et Astronautique (Fr)

Camille Rougeron et Jean Bodet

Larousse, 1964

Les fusées et missiles d'aujourd'hui (Fr)

Bill Gunston, translated from The Illustrated Encyclopedia of the World's Rockets & Missiles

Elsevier, 1979

ISBN 2-8003-0351-4

Grand Atlas de l'Espace (Fr)

Universalis, 1988

ISBN 2-85229-910-0

Le Guide des Lanceurs Spatiaux (Fr)

Serguei Grichkov

Tessier & Ashpool Ltd, 1992

ISBN 2-9094-6700-7

History of Liquid Rocket Engines - Development in the United States (Eng)

Stephen E. Doyle

American Astronautical Society 1992

ISBN 0-87703-350-1

L'Homme, l'Air et l'Espace (Fr)

Charles Bollfis, Henry Beauboir, Camille Rougeron

Édition de l'illustration, 1965

Matra Marconi Space Earth Observation Directory (Eng)

1993/94 edition

Matra Marconi Space European Spacecraft Directory (Eng)

3rd edition, 1992

Matra Marconi Space World Spacecraft Directory (Eng)

1993/94 edition

Réception TV par satellites (Fr)

René Besson

Dunod, Paris, 1992

ISBN 2-10-001462-5

Rockets into Space (Eng)

Frank H. Winter

Harvard University Press, 1990

ISBN 0-674-77660-7

La science au présent (Fr)

Encyclopædia Universalis, 1992

ISBN 2-85229-501-6

Les systèmes de télécommunications par satellite (Fr)

G. Maral, M. Bousquet, J. Pares

Masson, Paris, 1982

ISBN 2-225-75284-2

Les trente premières années du CNES (Fr)

Claude Carlier and Marcel Gilli

La documentation française, 1994

ISBN 2-11-003206-5

L'univers satellite, Guide pratique de la réception satellite (Fr)

Edition 91/92

Media Presse Information (MPI), 1991

ISBN 2-9505754-0-4

The Illustrated Encyclopedia of the World's Rockets & Missiles (Eng)

Bill Gunston

Salamander Books Ltd, London, 1979

ISBN 0-517-26870-1

Word Radio TV Handbook (Eng)

1993 edition

Billboard Books

WRTH Satellite Broadcasting Guide 1994 (Eng)

Bart Kuperus

Billboard Books

ISBN 0-8230-5954-5

WRTH Satellite Broadcasting Guide 1995 (Eng)

Bart Kuperus

Billboard Books

ISBN 0-8230-5955-3

Paper periodicals

Air & Cosmos (Fr)

ISSN 1240-3113

Arianespace Newsletter (Eng)

ISSN 0984-8452

Infosat (Ger)

ISSN 0933-6907

Megahertz Magazine (Fr)

ISSN 0755-4419

Revue des Télécoms (Fr)

ISSN 0183-8636

Satellites Infos (Fr)

ISSN n/a

Satellites Times (Eng)

ISSN 1077-2278

Satellite TV Magazine (Fr)

ISSN 0985-1542

Sciences et Avenir (Fr)

ISSN n/a

TELE-satellit (Ger)

ISSN 0943-9137

Télé Satellite (Fr)

ISSN n/a

Electronic periodicals

Jonathan's Space Report (Eng)

By Jonathan McDowell <jmcdowell@cfa.harvard.edu>

MediaScan (Eng)

From Radio Sweden <wood@stab.sr.se>

Space news from Aviation Week & Space Technology (Eng)

By Henry Spencer <henry@zoo.toronto.edu>

Space News InNet (Fr)

By Jean Etienne <etiennj@interpac.be>

Satellite Journal International (Eng)

Contact: <71165.2032@compuserve.com>

South Scanner Satellite Services Chart (Eng)

By Robert Smathers <roberts@nmia.com>

Space Calendar (Eng)

By Ron Baalke <baalke@kelvin.jpl.nasa.gov>

SpaceNews (Eng)

By John A. Magliacane <kd2bd@amsat.org>

Spacewarn Bulletin (Eng)

From National Space Science Data Center <sardi@nssdc.gsfc.nasa.gov>

http://nssdc.gsfc.nasa.gov/spacewarn/spacewarn.html

SAT News Desk (Eng)

By Peter C. Klanowski <pck@lynet.de>

Plus thousands of web sites...


Acknowlegdment
 Acknowledgment

In this section we want to thank all those who collaborated to improve The Satellite Encyclopedia. Please also check the compatible software section.

Co-authors

Jean-Jacques Serra

Gunter Krebs

Special thanks

Curt Swinehart

Curt is our information center! When something is going on related to satellite somewhere in the world, he's back with the press releases. Curt also monitors activity on the Internet. He is a vital resource to TSE! You may contact him at cswineha@emerald.tufts.edu

Tele Satellite International

A bimonthly satellite magazine edited in Munich, Germany.  For further details about Tele Satellite International have a look at their web site: http://www.tele-satellite.com

Data providers - Thanks!

We used to have here a long list of contributors, but not very accurate, many names were missing. We want to thank every contributor. We will not publish such a list anymore.


 Versions

Version	Release date	Comments
0.46.001	29 Aug 1999	Normal update
0.45.001	31 May 1999	Normal update (25th edition)
0.44.001	28 Feb 1999	Normal update. Year 2000 compliance check
0.43.001	25 Nov 1998	Normal update plus numerous footprint maps addition (including G/T)
0.42.002	14 Oct 1998	minor web update
0.42.001	30 Aug 1998	Normal update + Intelsat and other telecom satellites revision
0.41.002	14 Jul 1998	minor web update
0.41.001	06 Jun 1998	normal update
0.40.002	May 1998	First and last edition of the World Satellite CD
0.40.001	28 Feb 1998	New launch vehicle sections, new future satellites/programs
0.39.001	27 Nov 1997	Normal update, more addresses
0.38.002	20 Oct 1997	minor update
0.38.001	28 Aug 1997	new addresses section, normal update
0.37.001	29 May 1997	global update, more future satellites (especially LEOs & Ka-band) more organization addresses
0.36.001	25 Jan 1997	New pricing scheme for both 2 editions: WWW and Winhelp Added WWW pointers to each satellite programs when available  New and updated launcher information  Now over 300 footprints (including preliminary data)
0.35.001	31 Aug 1996	Important footprint upgrade
0.34.001	10 Apr 1996	First release of TSE Winhelp with TSE Online (http://www.TBS-satellite.com/tse/online/)
0.33.001	15 Dec 1995	Extension of the launcher section and the launch calendar (including details on future satellites) Added numerous EIRP maps TSE can be called from WinOrbit 2.7 and upper (freeware tracking program)
0.32.001	1 Sep 1995	First in History section Numerous launch programs added especially Atlas Support mailing list available New EIRP maps
0.31.001	1 Jun 1995	New CDROM distribution policy (compilers must send me a free copy) No Minitel distribution allowed Added numerous EIRP maps Introduced the full International Designator number
0.30.001	1 Mar 1995	Included a calendar of future launches Included a list of spacecrafts on the Clarke Belt Maps were redrawn and North-American satellites were added STS flights coverage was improved Added order forms and credit card registration
0.22.001	1 Dec 1994	New license agreement, data update
0.21.001	20 Sep 1994	Fixes numerous typos due to translation
0.20.001	12 Sep 1994	Translation in English
0.10.001	1 Sep 1994	Thematic index for missions Last French version
0.09.001	1 Jul 1994	Integrity checking with NASA's catalog number Technical data for geostationary telecommunication satellites
0.08.001	1 Jun 1994	Introduction of NASA's catalog & launch number
0.07.001	13 Apr 1994	First STS missions
0.06.001	7 Feb 1994	Modification of the maps Bug correction
0.05.001	17 Jan 1994	License agreement, first public release


 Compatible software

The Satellite Encyclopedia winhelp edition is compatible with some windows based software. This enables you to call your favorite satellite reference from those fine products with a single keystrike! Here is a list of those products with a description:

Logsat

This is a shareware tracking program which offer numerous goodies to ease your everyday monitoring. It handles an elements database and cares about the updates. It provides a logbook and a callbook to hold your records. It also provides antenna and propagation utilities.

You can get the full information on Logsat from http://www.logsat.com or contact Logsat by mail: support@logsat.com

Satmaster

This is a satellite tool box gathering all you need to install a satellite dish and design a reception station (from personal dish to ground earth station). It can calculate link budgets (analog, digital, SCPC) so as all kind of look angles. Moreover giving parameters of your reception station it will tell you the diameter of the dish you need to get a signal. It is ready to use with a database of towns around the globe.

You can get more information from here: http://www.arrowe.co.uk/ (where a freeware version is available) or contact its author at djsteph@arrowe.co.uk

WinOrbit

This is a program for computing artificial Earth-satellite position and visibility, with the Amateur Radio Satellite operator in mind. Quite simple to use it can operate with several different calculation models. Moreover it is freeware!

You can find the full documentation of Winorbit at http://www.sat-net.com/winorbit/ so as download the software. You can contact its author at cgregory@uiuc.edu


 How to use this encyclopedia?

What's hypertext?

If you never used a help file before and want to know more about them, press F1

Hypertext is a set of electronic textual data that can be read different ways. Data is distributed in items that are not attached like cars of a train but marked with links which enable passage from one another when the user activates them. Links are attached to words or to images.

Using hypertext links

Hypertext is very useful to enable the reader to define its own way through data.

The hypertext sensitive zones are generally in green (it may change) and underlined. You can press CTRL+TAB to see all of them. To active one, just click.

For example, on a satellite sheet you may click for data on its country of origin, mission, launch vehicle, etc. You also can access the program it belongs to (if it exists of course) by clicking the upper left icon.

Organization of the encyclopedia

This encyclopedia is organized around a satellite "dictionary". Satellites are sorted alphabetically by name and gathered by space program when possible. Numerous other themes are available such as the countries of origin, the launch vehicles, missions, etc.

The encyclopedia is full of popup windows with technical data and maps.

Search of specific data

The easiest way to find something is to question the searching tool. If your search is unsuccessful either your keyword is unknown or your question wasn't understood: try to express it differently. You also can browse through indexes.

Satellite channels

You are looking for satellite channels/programs? Our WWW edition has external links to such information.

Year 2000 compliance

The Satellite Encyclopedia does not contain any programming, its just text with hypertext links and images. Therefore year 2000 does not interfere with it, only the software used to read the files (such as Netscape Navigator, Microsoft Winhelp or Microsoft Internet Explorer) might have y2k problems, but we do not provide them. Please refer the the software vendor directly to check y2k compliance.

Other links

Glossary of terms

Help on printing


TSE (français)
 TSE

The Satellite Encyclopedia est sous copyright de Tag's Broadcasting Services, © tous droits réservés, 1993-1999. Auteur principal: Jean-Philippe Donnio

Ce document fut nommé second meilleur shareware français 1995 catégorie Home and Hobby par Ziff Davis.

A lire également en français :

Licence d'utilisation - Bons de commande

TSE est compatible an 2000.

Philosophie de cette encyclopédie

Cette encyclopédie a pour but de rassembler de l'information dans un document simple d'emploi. Les contributions sont bien venues.... Vous pouvez même devenir un co-auteur de TSE comme Jean-Jacques Serra qui s'occupe de la section des lanceurs! Cette encyclopédie est publiée tous les 3/4 mois environ. Ce logiciel n'est donc pas une version finale.

Si vous êtes un spécialiste du satellite, un opérateur ou un constructeur satellite, une organisation spatiale, nous serons très heureux d'entrer en contact avec vous. Si pour une raison ou une autre vous pensez que vos satellites ne sont traités correctement, comprenez que nous ne travaillons qu'à partir d'information que nous possédons. Si vous voulez améliorer les choses, envoyez nous directement vos informations.

Si vous êtes l'auteur d'un livre ou logiciel en rapport avec les satellites ou si votre organisation publie un magazine ou lettre d'information en rapport avec l'Espace et le satellite, consultez notre offre spéciale dans la licence.

La règle du jeu

Ce logiciel est en libre essai, c'est un shareware : vous pouvez donc l'essayer gratuitement pendant SEPT jours, ensuite vous devez soit vous enregistrer soit l'effacer. La version shareware est limitée pour tenir sur une disquette 3,5". De ce fait de nombreuses cartes PIRE et le programme Cosmos ne sont pas inclus. C'est pourquoi vous verrez des erreurs en activant ces éléments.

Si vous utilisez The Satellite Encyclopedia après la période d'essai ou à des fins commerciales, vous DEVEZ vous enregistrer. La version enregistrée comprend:

Le fichier complet avec :

450 cartes PIRE

la liste des satellites sur l'orbite de Clarke

un calendrier des lancements futurs et des satellites concernés

les programmes Russes

toutes les pages et cartes (liens cassés) non disponibles dans cette version

TSE est comme un magazine: la version shareware est comparable à un magazine que vous lisez en kiosque. Achetez ce magazine est comme enregistrer votre version de TSE. Et si vous enregistrez TSE avec l'abonnement vous obtenez 4 numeros de TSE consécutifs... ce qui revient à s'abonner à un magazine traditionnel. Bref c'est pas sorcier ! Reportez vous à la licence pour tous les détails.

Bien que toutes les précautions aient été prises lors de la compilation de ces informations, l'éditeur n'est pas responsable des erreurs ou omissions. De même l'éditeur ne peut être tenu responsable de conséquences de l'utilisation des informations contenues dans cette encyclopédie. Merci de nous signaler toute erreur ou omission.

Comment vous procurer la dernière version disponible ?

1°/ En vous enregistrant : voir la licence.

2°/ En la téléchargeant :

Internet : la liste des sites ftp se trouve à http://www.TBS-satellite.com/tse/  Le site ftp primaire se trouve à ftp://ftp.TBS-satellite.com/pub/tse/

Support en ligne

Le site Internet de TSE est http://www.TBS-satellite.com/tse/

La version WWW de TSE se trouve a http://www.TBS-satellite.com/tse/online/

Nous avons mis en place un certain nombre de listes de diffusion. Pour vous abonner (gratuitement) a la liste publique envoyez un mail:

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Ce qui précède constitue la licence de The Satellite Encyclopedia. Elle annule et remplace toutes les versions antérieures.


 Jean-Jacques SERRA

Contact: JJ.Serra@wanadoo.fr

Jean-Jacques Serra is a 43 years old French citizen. He devotes most of his free time to astronautics since the age of 17. He is responsible of the launch vehicle section.

He lives in eastern part of the Pyrenees mountains, a region famous for its solar ovens. He carries out research on new materials especially those aimed to extrem temperatures.

Reading of articles and information sorting relative to rockets and satellites consume most of his hobby time. He also enjoys his natural environment.

J'ai 43 ans et je m'intéresse à l'astronautique et son histoire depuis l'age de 17 ans.

Je vis à l'est des Pyrénées, dans une région où se trouve la plus grande concentration de fours solaires. J'y fais de la recherche sur les matériaux nouveaux et plus particulièrement ceux qui sont exposés à des températures extrêmes.

La lecture d'articles, le classement d'informations sur les fusées et les satellites occupent une grande partie de mes loisirs. Pour le reste, je profite de mon environnement, la découverte de la montagne est un sujet inépuisable.


 Gunter Krebs

no presentation available

External resources

Email: gk@smoky.ikf.physik.uni-frankfurt.de

http://www.rz.uni-frankfurt.de/~gkrebs/space/space.html


Countries of origin
 States and Organizations

Statistics (as of mid-Aug 1999)

Country	Satellite	Probes (non Earth orbit)	Debris	Total (including non Earth orbit)
Argentina	6	0	0	6
Australia	7	0	2	9
Brazil	8	0	0	8
Canada	16	0	1	17
Chile	1	0	0	1
China	29	0	102	131
CIS	1334	35	2586	3955
Czechoslovakia	4	0	0	4
Denmark	1	0	0	1
Egypt	1	0	0	1
France	30	0	17	47
France / Germany	3	0	0	3
Germany	15	2	1	18
India	19	0	6	25
Indonesia	9	0	0	9
Israel	3	0	0	3
Italy	8	0	3	11
Japan	65	4	52	121
Korea (South)	5	0	0	5
Luxemburg	9	0	0	9
Malaysia	2	0	0	2
Mexico	6	0	0	6
Norway	2	0	0	2
Philippines	2	0	0	2
Portugal	1	0	0	1
Singapore / Taiwan	1	0	0	2
South Africa	1	0	0	1
Spain	5	0	0	5
Sweden	7	0	0	7
Taiwan	1	0	0	1
Thailand	4	0	0	4
Turkey	2	0	0	2
United Kingdom	17	0	1	18
United States	870	46	3077	3993
Arab States	6	0	0	6
Europe	24	2	227	253
International (Eutelsat, Inmarsat & Intelsat)	80	0	0	80
NATO	8	0	0	8
Total	2612	89	6075	8777


Countries of origin

Countries

Argentina Australia Brazil Bulgaria Canada CIS Chile China Czechoslovakia Denmark Egypt France Germany	India Indonesia Israel Italy Japan Korea (South) Luxemburg Malaysia Mexico Netherlands North Korea Norway Pakistan	Philippines Portugal Singapore South Africa Spain Sweden Taiwan Thailand Turkey Ukraine United Kingdom United States
Organizations

Arab States Europe (ESA)	International NATO


 Argentina

CONAE is the national agency

External resources

http://www.conae.gov.ar/

Satellite launched

1990

Lusat

1996

Musat

SAC B

1997

Nahuel 1A

1998

SAC A

Main program

Nahuel


 Australia

Australia owns an old launch site (Woomera) from which it's first satellite was launched. Has created a space comity on 21 Sep 1986.

Satellites launched

1967

Wresat

1970

Oscar 05

1985

Optus A1

Optus A2

1987

Optus A3

1992

Optus B1

1994

Optus B3

1998

Westpac

Main program

Optus


 Brazil

The national space research center INPE (Instituto Nacional de Pesquisas Espacias) was created on 3 Aug 1961. Brazil has a launch program: VLS.

External resources

http://www.inpe.br/

Satellites launched

1985

Brasilsat A1 (SBTS A1)

1986

Brasilsat A2 (SBTS A2)

1990

Dove

1993

SCD 1

1994

Brasilsat B1 (SBTS B1)

1995

Brasilsat B2 (SBTS B2)

1998

Brasilsat B3

SCD 2

Main program

Brasilsat

Launch program

VLS


 Bulgaria

Bulgaria launched a satellite with the help of the CIS. Member of Intersputnik.

Satellite launched

1981

Intercosmos 22


 Canada

The Canadian Space Agency was created on 1 Mar 1989.

Canada is an associate member of ESA since 1978. This means that Canada does not have the same rights and obligations as a full member. For instance, Canada is not participating in the Scientific Program or in the Technological Research Programme of ESA. Both these programs are part of the mandatory activities which are financed by the full members pro rata of their gross national product (GNP).

Canada was the first country to develop a national telecommunication system.

External resources

http://www.space.gc.ca/

Satellites launched

1962

Alouette 1

1965

Alouette 2

1969

Isis 1

1971

Isis 2

1972

Anik A1 (Telesat 1)

1973

Anik A2 (Telesat 2)

1975

Anik A3 (Telesat 3)

1976

CTS

1978

Anik B1 (Telesat 4)

1982

Anik D1 (Telesat 5)

Anik C3 (Telesat 6)

1983

Anik C2 (Telesat 7)

1984

Anik D2 (Telesat 8)

1985

Anik C1 (Telesat 9)

1991

Anik E2 (Telesat 10)

Anik E1 (Telesat 11)

1992

CTA

1995

Radarsat

1996

MSAT 1

1999

Nimiq

Main programs

Alouette

Anik

Isis


 Chile

Satellites launched

1995

Fasat Alfa

1998

Fasat Bravo


 China

In 1958 Mao tze-tung decided to launch a program named "mission 581" directed by Quian Xue-sen. The first Chinese rocket was launched in 1960 (so as the first missile). When the CIS stopped helping China the spatial program changed drastically. Two organizations were created (in Shangai and Beijin) that managed to launch their first satellite. Since 1986 China offers launch services to foreign firms.

Satellites launched

1970

Dong Fang Hong 01 (Mao 1)

1971

Dong Fang Hong 02 (Mao 2)

1975

Dong Fang Hong 03 (Mao 3)

Dong Fang Hong 04 (Mao 4)

Dong Fang Hong 05 (Mao 5)

1976

Dong Fang Hong 06 (Mao 6)

Dong Fang Hong 07 (Mao 7)

1978

Dong Fang Hong 08 (Mao 8)

1981

Dong Fang Hong 09

Dong Fang Hong 10

Dong Fang Hong 11

1982

Dong Fang Hong 12

1983

Dong Fang Hong 13

1984

Dong Fang Hong 14

Dong Fang Hong 15 (STTW 0)

Dong Fang Hong 16

1985

Dong Fang Hong 17

1986

Dong Fang Hong 18 (STTW 1)

Dong Fang Hong 19

1987

Dong Fang Hong 20

Dong Fang Hong 21

1988

Dong Fang Hong 22 (Chinasat 1)

Dong Fang Hong 23

Dong Fang Hong 24(Feng Yun 1-1)

Dong Fang Hong 25 (Chinasat 2)

1990

Asiasat 1

Dong Fang Hong 26 (Chinasat 3)

Dong Fang Hong 30(Feng Yun 1-2)

Dong Fang Hong 31 (Atmosphere 1)

Dong Fang Hong 32 (Atmosphere 2)

Dong Fang Hong 33

1991

Dong Fang Hong 34 (Chinasat 4)

1992

Dong Fang Hong 35

Dong Fang Hong 36

1993

Dong Fang Hong 37 (Jianbing 93)

1994

Apstar 1

Dong Fang Hong 38 (Shijian 4)

Dong Fang Hong 39 (Shijian 4-2)

Dong Fang Hong 40 (FSW 2)

Dong Fang Hong 41

1995

Asiasat 2

1996

Apstar 1A

Dong Fang Hong 42 (Chinasat 7)

Dong Fang Hong 43 (FSW 2-3)

1997

Apstar 2R

Asiasat 3

Dong Fang Hong 44 (Chinasat 6)

Dong Fang Hong 45 (FY 2B)

1998

Chinastar 1

1999

Asiasat 3S

Dong Fang Hong 46 (FY 1C)

Dong Fang Hong 47 (SJ 5)

Main programs

Apstar

Asiasat

Dong Fang Hong

Launchers

Chinese launch vehicles (Long March)


 CIS

For the moment, we name the Russian Federation and the Community of Independant States CIS. All launches by the former USSR are considered as Russian launches. Sorry for this simplification.

CIS has a very complex space organization that we can't simply summarize here.

External resources

http://arc.iki.rssi.ru/Welcome.html

Main programs

Bion

Cosmos

Ekran

Elektron

Eorsat

Express

Foton

Gals

Geizer

Geo-IK

Glonass

Gonets

Gorizont

Intercosmos

Luch

Meteor

Molniya

Nadezhda

Ocean

Parus

Prognoz

Proton

Raduga

Resurs

Rorsat

Sputnik

Statsionar

Strela

Tsikada

Launch programs

Cosmos B

Cosmos C

Cyclone

Proton

Rokot

Semiorka family (Molniya, Soyuz)

Start

Zenit


Czechoslovakia
 Czech Republic

Formerly called Czechoslovakia, before the country splitted.

Developed a scientific program with the CIS. Member of Intersputnik.

Satellites launched

Two of these satellites are not officially registered by the country

1978

Magion 1

1989

Magion 2

1991

Magion 3

1995

Magion 4

1996

Magion 5

Main program

Magion


 Denmark

Satellites launched

1999

Orsted


 Egypt

Satellites launched

1998

Nilesat 101


 France

The French space agency CNES (Centre National d'Etudes Spatiales) was created on 19 Dec 1961. France has been part of ESRO and ELDO. Now it is member of ESA.

External resources

http://www.cnes.fr/

Satellites launched

1965

Astérix (A1)

FR 1

1966

Diapason (D1A)

1967

Diadème 1 (D1C)

Diadème 2 (D1D)

1970

Mika

Péole

1971

Tournesol (D2A)

Eole

Auréole 1

1972

Sret 1

1973

Auréole 2

1974

Symphonie 1

1975

Starlette

Pollux (D5A)

Castor (D5B)

Sret 2

Symphonie 2

Aura (D2B)

1977

Signe 3

1981

Auréole 3

1984

Telecom 1A

1985

Telecom 1B

1986

Spot 1

1988

Telecom 1C

TDF 1

1990

Spot 2

TDF 2

1991

Sara

Telecom 2A

1992

Telecom 2B

S80T

1993

Arsène

Spot 3

Stella

1995

Helios 1A

Cerise

Telecom 2C

1996

Telecom 2D

1998

Spot 4

Main programs

Auréole

Helios

Spot

Sret

Symphonie

TDF

Telecom

Launch program

Diamant


 Germany

In the 30ies, a space organization (Verein für Raumschiffahrt, society for space travel) was created with members as famous as Wernher von Braun and H. Oberth. In 1931 they managed to launch a rocket with liquid ergols. During the second world war Germany developed the V2 missile. In 1962 Germany started cooperating with European countries when the COPERS was created.

Germany has been part of ESRO and ELDO. It is now member of ESA. Has created in July 1989 a federal space agency: DARA (Deutsche Agentur für RaumfahrtAngelegenheiten). Member of Intersputnik.

External resources

http://www.dlr.de/

Satellites launched

1969

Azur (GRS A)

1970

Dial-Wika

1972

Aeros 1 (GRS B)

1974

Aeros 2

Symphonie 1

1975

Symphonie 2

1983

Oscar 10

Spas 1

1984

AMPTE IRM

1987

Tvsat 1

1989

DFS 1

Tvsat 2

1990

Rosat

DFS 2

1991

Tubsat A

1992

DFS 3

1993

Orfeus-Spas

1994

Tubsat B

Crista-Spas

1995

GFZ 1

1997

Equator S

1998

Tubsat N

Tubsat N1

Safir 2

1999

Abrixas

Tubsat C

Main programs

Aeros

DFS Kopernikus

Safir

Symphonie

Tubsat

Tvsat


 India

Indian space agency is the ISRO (Indian Space Research Organisation) created in 1969. A Ministry of Space was created in 1972 and India has its own launch vehicles. ISRO has a commercial arm named Antrix.

Satellites launched

1975

Aryabhata

1979

Bhaskara 1

1980

Rohini 1B (RS E2)

1981

Rohini 2 (RS D1)

Apple

Bhaskara 2

1982

Insat 1A

1983

Rohini 3 (RS D2)

Insat 1B

1988

IRS 1A

Insat 1C

1990

Insat 1D

1991

IRS 1B

1992

Sross 3

Insat 2A

1993

Insat 2B

1994

Sross C2

IRS P2

1995

IRS 1C

Insat 2C

1996

IRS P3

1997

Insat 2D

IRS 1D

1999

Insat 2E

IRS P4

Main programs

Bhaskara

Insat

IRS

Rohini

Sross

Launch program

ISRO launch vehicles(SLV 3, ASLV, PSLV)


 Indonesia

Satellites launched

1976

Palapa A1

1977

Palapa A2

1983

Palapa B1

1987

Palapa B2P

1990

Palapa B2R

1992

Palapa B4

1996

Palapa C1

Palapa C2

1997

Cakrawarta 1

1999

Palapa D1 / Telkom 1

Main program

Palapa


 Israel

Israel has a space agency since 1983

Satellites launched

1988

Offek 1

1990

Offek 2

1995

Offek 3

1996

Amos 1

1998

Techsat 2

Main programs

Offek

Techsat

Launch program

Shavit


 Italy

Italy is part of ESA and has created a space agency on 8 Jun 1988: ASI (Agenzia Spaziale Italania). Italy owns a little launch site in the Indian ocean (San Marco and Santa Rita).

External resources

http://www.asi.it

Satellites launched

1964

San Marco 1

1967

San Marco 2

1971

San Marco 3

1974

San Marco 4

1977

Sirio 1

1988

San Marco 5

1991

Italsat 1

1993

Itamsat

Temisat

1996

TTS 2

SAX

Italsat 2

1999

Megsat 0

Main programs

Italsat

San Marco

Sirio


 Japan

Japan has an important space program conducted by NASDA (National Space Development Agency) and ISAS (Institute of Space and Aeronautical Science).

External resources

http://www.nasda.go.jp/

http://www.isas.ac.jp/

Satellites launched

1970

Ohsumi

1971

Tansei 1

Shinsei

1972

Denpa

1974

Tansei 2

1975

Taiyo

Kiku 1 (ETS 1)

1976

Ume 1 (ISS 1)

1977

Tansei 3

Kiku 2 (ETS 2)

Himawari 1 (GMS 1)

Sakura 1 (CS 1A)

1978

Kyokko (Exos A)

Ume 2 (ISS 2)

Yuri 1 (BSE)

Jikiken (Exos B)

1979

Ayame 1 (ECS 1)

Hakucho (Corsa B)

1980

Tansei 4

Ayame 2 (ECS 2)

1981

Kiku 3 (ETS 4)

Hinotori (Astro A)

Himawari 2 (GMS 2)

1982

Kiku 4 (ETS 3)

1983

Sakura 2A (CS 2A)

Tenma (Astro B)

Sakura 2B (CS 2B)

1984

Yuri 2A (BS 2A)

Ohzora (Exos C)

Himawari 3 (GMS 3)

1986

Yuri 2B (BS 2B)

Ajisai (EGP)

Fuji 1A (JAS 1A)

1987

Ginga (Astro C)

Momo 1A (MOS 1A)

ETS 5

1988

Sakura 3A (CS 3A)

Sakura 3B (CS 3B)

1989

Akebono (Exos D)

Jcsat 1

Superbird A1

Himawari 4 (GMS 4)

1990

Jcsat 2

Hiten (Muses A) & Hagoromo: lunar probes

Momo 1B (MOS 1B)

Debut

Fuji 1B (JAS 1B)

Yuri 3A (BS 3A)

1991

Yuri 3B (BS 3B)

Solar A (Yohkoh)

1992

JERS 1

Superbird B1

Geotail

Superbird A2

1993

Astro D

1994

Ryusei

Myojo

Yuri 3N

1995

SFU

GMS 5

Jcsat 3

N Star A

1996

Adeos 1 (Midori)

Fuji 2

1997

Haruka (Muses B)

Jcsat 4

Bsat 1A

Superbird C

ETS 7

Jcsat 5

1998

Kakehashi (Comets)

Bsat 1B

Nozomi (Planet B)

1999

Jcsat 6

Main programs

Astro

Ayame

ETS

Fuji

GMS

Jcsat

Momo

N Star

Sakura

Superbird

Tansei

Yuri

Launch programs

ISAS launch vehicles (Mu series)

NASDA launch vehicles (N and H series)


 Korea (South)

Satellites launched

1992

Kitsat A

1993

Kitsat B

1995

Koreasat 1

1996

Koreasat 2

1999

Kitsat 3

Main programs

Kitsat

Koreasat


 Luxemburg

Satellites launched

1988

Astra 1A

1991

Astra 1B

1993

Astra 1C

1994

Astra 1D

1995

Astra 1E

1996

Astra 1F

1997

Astra 1G

1998

Astra 2A

1999

Astra 1H

Main program

Astra


 Malaysia

Malaysia plans to launch a micro satellite in the middle of 1997 (on Ariane) and the second in 2000

Satellite launched

1996

Measat 1

Measat 2

Main program

Measat


 Mexico

Satellites launched

1985

Morelos 1

Morelos 2

1993

Solidaridad 1

1994

Solidaridad 2

1996

Unamsat 2

1998

Morelos 3

Main programs

Morelos

Solidaridad


 Netherlands

Member of ESA

External resources

http://www.sron.ruu.nl/

Satellites launched

1974

ANS

1983

IRAS

1996

SAX (considered as Italian)


 North Korea

Satellite launch failure

1998

Kwangmyongsong 1


 Norway

Member of ESA since 1987.

External resources

http://www.spacecentre.no/

Satellite launched

1997

Thor 2

1998

Thor 3

Satellite bought in orbit

1992

Thor 1


 Pakistan

The Pakistan Space and Upper Atmosphere Research Commission (SUPARCO) was founded in 1961.

Satellite launched

1990

Badr A


 Philippines

Satellite launched

1997

Mabuhay 1

Satellites bought in orbit

1996

Palapa B2P

1997

Gorizont 29


 Portugal

Satellite launched

1993

Posat


 Singapore

Satellite launched

1998

ST 1


 South Africa

Satellite launched

1999

Sunsat


 Spain

Spain is part of ESA.

External resources

http://www.inta.es

Satellites launched

1974

Intasat

1992

Hispasat 1A

1993

Hispasat 1B

1995

UPMsat 1

1997

Minisat 01

Main program

Hispasat

Minisat


 Sweden

Member of ESA

Satellites launched

1986

Viking

1989

Tele X

1992

Freja

1994

Sirius 1 (bought in orbit)

1995

Astrid 1

1997

Sirius 2

1998

Sirius 3

Astrid 2

Main programs

Sirius


 Taiwan

Satellite launched

1998

ST 1

1999

Rocsat 1

Main programs

Rocsat


 Thailand

Satellite launched

1993

Thaicom 1

1994

Thaicom 2

1997

Thaicom 3

1998

Tmsat

Main program

Thaicom


 Turkey

Satellites launched

1994

Turksat 1B

1996

Turksat 1C

Main program

Turksat


 Ukraine

Ukraine has a space agency: National Space Agency of Ukraine (NKAU)

Satellites launched

1995

Sich 1


 United Kingdom

Has created the BNSC (British National Space Center), a space agency in 1985. United Kingdom is member of ESA.

External resources

http://www.bnsc.gov.uk/

Satellites

1962

Ariel 1 (UK 1)

1964

Ariel 2 (UK 2)

1967

Ariel 3 (UK 3)

1969

Skynet 1A

1971

Skynet 1B

Prospero (X3)

Ariel 4 (UK 4)

1974

Skynet 2A

Miranda (X 4)

Ariel 5 (UK 5)

Skynet 2B

1979

Ariel 6 (UK 6)

1981

Uosat 1

1983

IRAS

1984

Uosat 2

AMPTE UKS

1988

Skynet 4B

1989

BSB 1

Skynet 4A

1990

Uosat 3

Uosat 4

BSB 2

Skynet 4C

1991

Uosat 5

1994

STRV 1A

STRV 1B

1998

Skynet 4D

1999

Skynet 4E

Uosat 12

Main programs

Ariel

BSB

Skynet

STRV

Uosat

Launch program

Black Arrow


 United States

The US space program can't be described here... it requires a whole book!

External resources

http://www.nasa.gov/

Main programs

AMS

ASC

ATS

Aurora

Comstar

Columbia

Dash

DBS

Discoverer

DMSP

DSCS

DSP

Echo

Echostar

Essa

Explorer

Fleetsatcom

Galaxy

GE

GGSE

Globalstar

Goes

GPS

Gstar

Heao

IDSCP

IMEWS

Iridium

KH

Lacrosse

Lageos

Landsat

LCS

Leasat

LES

Marisat

Midas

Milstar

MSTI

Nimbus

NOAA

NOSS

Nova

OAO

Oderacs

OGO

Orbcomm

Orion

OSO

OV

Panamsat

Pegasus

Relay

Satcom

Discoverer

SBS

Secor

SMS

Solrad

Spacenet

Spartan

Stacksat

Syncom

TDRS

Telstar

Tempo

Tiros

Transit

UHF

USA

Vanguard

Vortex

Westar

Launchn programs

Athena

Atlas

Conestoga

Delta

Pegasus

Scout

STS

Taurus

Thor

Titan

Vanguard


 Arab States

Satellites launched

1985

Arabsat 1A

Arabsat 1B

1992

Arabsat 1C

1993

Arabsat 1D (bought in orbit)

1995

Arabsat 1E (bought in orbit)

1996

Arabsat 2A

Arabsat 2B

1999

Arabsat 3A

Main program

Arabsat


 Europe

We use the name 'Europe' to simplify naming. In fact, it may stand for the ESA or the ESRO.

On 27 Feb 1961 the COPERS (COmmission Préparatoire Européenne pour la Recherche Spatiale) was created. In 1964 the ESRO (European Space Research Organization) was created to develop satellites. The ELDO (European Launcher Development Organisation) was in charge of the development of the Europa launcher. The Convention establishing this organisation came into force on 29 February 1964. This multiple structure merged into a single organization ESA (European Space Agency) on 31 May 1975.

Members of ESA: Austria, Belgium, Denmark, Finland, France, Germany, Ireland, Italy, Netherlands, Norway, Spain, Sweden, United Kingdom, and Switzerland. Canada is an associate member.

The convention says: the purpose of the agency shall be to provide for and to promote, for exclusively peaceful purposes, cooperation among European states in space research and technology and their space applications, with a view to their being used for scientific purposes and for operating space applications systems.

The agency is directed by a council composed of representatives of member states. The Director General is the chief executive of the agency and its legal representative. The ESA headquarters are in Paris.

The major establishments of ESA are: The European Space Research and Technology Center (ESTEC), Noordwijk, Netherlands; The European Space Operations Center (ESOC), Darmstadt, Germany; ESRIN, Fracasti, Italy.

Contact

ESA

8/10 rue Mario Nikis, 75738 Paris cedex 15, France

Tel: +33-1-4273-7560

External resources

http://www.esrin.esa.it/

Satellites launched

1968

Esro 2B (Iris)

Esro 1A (Aurorae)

Heos 1

1969

Esro 1B (Boreas)

1972

Heos 2

TD 1A

Esro 4

1975

Cos B

1977

ESA-Geos 1

ISEE 2

Meteosat 1

1978

OTS 2

ESA-Geos 2

1979

Cat 1

1981

Meteosat 2

Cat 3

Marecs A

Cat 4

1983

Exosat

Eutelsat 1F1

1984

Eutelsat 1F2

Marecs B2

1987

Eutelsat 1F4

1988

Meteosat 3

Eutelsat 1F5

1989

Meteosat 4

Olympus

Hipparcos

1990

Eutelsat 2F1

1991

Eutelsat 2F2

Meteosat 5

ERS 1

Eutelsat 2F3

1992

Eutelsat 2F4

Eureca 1

1993

Meteosat 6

1995

Hotbird 1

ERS 2

ISO

1996

Hotbird 2

1997

Hotbird 3

Meteosat 7

Maqsat H

Maqsat B

Yes

1998

Hotbird 4

Eutelsat 3F2

Hotbird 5

1999

Eutelsat 3F3

Main programs

Cat

Esro

ERS

Eutelsat

Heos

Marecs

Meteosat

OTS

Launchers

Ariane


 International

Here are the satellites developed by an international organization, either Intelsat or Inmarsat. Intersputnik isn't in here because the satellites are owned by the CIS... but this will change as soon as Intersputnik launches its first satellite.

Numerous other programs were developed by multi-national partners but are still considered nationally.

External resources

http://www.un.or.at/OOSA_Kiosk/index.html

Satellites launched

1965

Intelsat 101

1966

Intelsat 201

1967

Intelsat 202

Intelsat 203

Intelsat 204

1968

Intelsat 302

1969

Intelsat 303

Intelsat 304

1970

Intelsat 306

Intelsat 307

Intelsat 308

1971

Intelsat 402

Intelsat 403

1972

Intelsat 404

Intelsat 405

1973

Intelsat 407

1974

Intelsat 408

1975

Intelsat 401

Intelsat 4A01

1976

Intelsat 4A02

1977

Intelsat 4A04

1978

Intelsat 4A03

Intelsat 4A06

1980

Intelsat 502

1981

Intelsat 501

Intelsat 503

1982

Intelsat 504

Intelsat 505

1983

Intelsat 506

Intelsat 507

1984

Intelsat 508

Intelsat 509

1985

Intelsat 510

Intelsat 511

Intelsat 512

1988

Intelsat 513

1989

Intelsat 515

Intelsat 602

1990

Intelsat 603

Intelsat 604

Inmarsat 2F1

1991

Inmarsat 2F2

Intelsat 605

Intelsat 601

Inmarsat 2F3

1992

Inmarsat 2F4

Intelsat K

1993

Intelsat 701

1994

Intelsat 702

Intelsat 703

1995

Intelsat 704

Intelsat 705

Intelsat 706

1996

Intelsat 707

Inmarsat 3F1

Intelsat 709

Inmarsat 3F2

Inmarsat 3F3

1997

Intelsat 801

Inmarsat 3F4

Intelsat 802

Intelsat 803

Intelsat 804

1998

Inmarsat 3F5

Intelsat 806

Intelsat 805

Main programs

Inmarsat

Intelsat

ISEE

Sarsat


 NATO

Satellites launched

1970

Nato 1

1971

Nato 2

1976

Nato 3A

1977

Nato 3B

1978

Nato 3C

1984

Nato 3D

1991

Nato 4A

1993

Nato 4B

Main program

Nato


The Clarke Belt
 Geostationary Orbit

Introduction

This chart keeps track of the satellites on the Clarke Belt. The transponder loading of the telecommunication satellites listed here can be found at http://www.lyngsat.com

First column is the slot of the satellite above the Equator; negative values stand for degrees West and positive for degrees East. Second column is the inclination of the spacecraft in degrees i.e. the angle between the satellite's plan and the Equator's plan. The "Mis." column is for the satellite's main mission; M stands for Military, C for Communication and W for Weather. Furthermore MC stands for Military Communications, MW for Military Warning. The "Frequency bands" column relates the downlink bands in which the satellite can be active, blank means unknown. The "Comment" column contains internal information, such as the "#" sign which indicates this data is unconfirmed or the satellite is non-operational.

Slot	Inc.	Satellite	Mis.	Freq. bands	Comment
-177.0	3.14	Intelsat 513	C	C, Ku
-174.3	1.36	TDRS 5	C/M	S, C, Ku
-171.0	3.05	TDRS 7	M	S, C, Ku
-169	13.5	Goes 02	W	S	#wavering but alive
-144.0	3.69	Brasilsat A1	C	C
-139.0	0.05	Aurora 2	C	C
-137.0	0.09	Satcom C1	C	C
-135	0.27	Goes 10	W	VHF, L, S
-135.0	0.07	Satcom C4	C	C
-133.0	0.05	Galaxy 1R	C	C
-131.0	0.07	Satcom C3	C	C
-125.0	0.05	Galaxy 5	C	C
-123.0	0.05	Galaxy 9	C	C
-122.9	0.05	SBS 5	C	Ku
-120	5.24	Goes 07	W	VHF, L, S	#drifting west
-120.3	0.79	Morelos 2	C	C, Ku
-119.0	0.07	Echostar 1	C	Ku
-119.0	0.03	Echostar 2	C	Ku
-118.8	0.09	Tempo 2	C	Ku
-116.8	0.03	Morelos 3	C	C, Ku
-113.0	0.05	Solidaridad 2	C	L, C, Ku
-111.1	0.07	Anik E1	C	C, Ku
-110.0	0.09	Echostar 4	C	Ku
-109.2	0.05	Solidaridad 1	C	L, C, Ku
-107.3	0.09	Anik E2	C	C, Ku
-106.5	0.05	MSAT 1	C	L, Ku
-106.3	1.90	Anik C1	C	Ku
-105	14.5	ATS 3	C	VHF	#old
-105	6.36	Aurora 1	C	C	#old
-105.1	2.53	Gstar 1	C	Ku
-105.0	0.07	Gstar 4	C	Ku
-103.0	0.03	GE 1	C	C, Ku
-101.2	0.05	DBS 1	C	Ku
-101.0	0.05	ASC 2	C	C, Ku
-101.0	0.05	AMSC 1	C	L, Ku
-101.0	0.03	DBS 3	C	Ku
-100.8	0.03	DBS 2	C	Ku
-100.0	0.84	ACTS	C	Ka
-100	0.49	Goes 09	W	VHF, L, S	wavering
-99.0	0.07	Galaxy 6	C	C
-98.1	1.85	Inmarsat 2F2	C	L, C
-97.0	0.05	Telstar 5	C	C, Ku
-95.0	0.05	Galaxy 3R	C	C, Ku
-95.0	0.03	Galaxy 8i	C	Ku
-93.0	0.05	Telstar 6	C	C, Ku
-92.0	2.35	Brasilsat A2	C	C
-91.0	0.05	Nimiq	C	Ku
-91.0	0.07	Galaxy 7	C	C, Ku
-89.0	0.07	Telstar 402R	C	C, Ku
-87.0	0.05	GE 3	C	C, Ku
-85.0	0.05	GE 2	C	C, Ku
-84.0	0.05	Brasilsat B3	C	C, X
-83.0	0.04	Spacenet 3R	C	L, C, Ku
-81.0	1.84	Satcom K2	C	Ku
-79.0	0.05	GE 5	C	Ku
-77.0	4.88	SBS 4	C	Ku
-76.0	10.4	Comstar 4	C	C	#old
-75	0.12	Goes 08	W	VHF, L, S	wavering
-74.0	0.07	SBS 6	C	Ku
-72.0	0.05	Nahuel 1A	C	Ku
-70.0	0.05	Brasilsat B1	C	C, X
-65.0	0.05	Brasilsat B2	C	C, X
-63	7.87	HGS 1	C	C, Ku	#highly inclined
-61.5	0.05	Echostar 3	C	Ku
-58.0	0.05	Panamsat 5	C	C, Ku
-55.5	0.05	Intelsat 805	C	C, Ku
-54.0	0.09	Inmarsat 3F4	C	L, C
-53.0	0.05	Intelsat 706	C	C, Ku
-50.0	0.05	Intelsat 709	C	C, Ku
-49.0	10.4	TDRS 1	M	S, C, Ku
-47.0	0.40	TDRS 6	C/M	S, C, Ku
-45.0	0.07	Panamsat 1	C	C, Ku
-43.2	0.07	Panamsat 6	C	Ku
-43.2	0.03	Panamsat 6B	C	Ku
-43.0	0.07	Panamsat 3R	C	C, Ku
-41.0	2.27	TDRS 4	M	S, C, Ku
-40.5	0.05	Intelsat 806	C	C, Ku
-37.8	1.58	Intelsat 515	C	C, Ku
-37.5	0.07	Orion 1	C	Ku
-34.5	0.03	Intelsat 601	C	C, Ku
-34.0	3.90	Skynet 4A	M	UHF, X, EHF
-31.5	0.05	Intelsat 801	C	C, Ku
-30.0	0.05	Hispasat 1A	C	X, Ku
-30.0	0.05	Hispasat 1B	C	X, Ku
-29.5	4.94	Intelsat 511	C	C, Ku
-27.5	0.05	Intelsat 605	C	C, Ku
-26.0	8.23	Marecs B2	C	L, C
-24.5	0.03	Intelsat 603	C	C, Ku
-21.5	0.09	Intelsat K	C	Ku
-21.5	0.03	Intelsat 803	C	C, Ku
-20.4	1.51	Nato 4B	M	UHF, X
-19.3	5.90	Nato 3D	M	X	wavering
-18.0	0.03	Intelsat 705	C	C, Ku
-18.0	2.54	Nato 4A	M	UHF, X
-15.5	0.55	Inmarsat 3F2	C	L, C
-14.0	0.09	Express 1	C	C, Ku
-13.5	2.23	Cosmos 2291	MC	C	wavering
-12.6	0.89	Tvsat 2	C	Ku
-12.5	0.03	Eutelsat 2F2	C	Ku
-12.2	3.98	Eutelsat 1F5	C	Ku
-11		Cosmos 2345	M		#drifting East
-11.0	3.85	Gorizont 26	C	L, C, Ku	wavering
-9.0	0.82	Meteosat 6	W	VHF, L, S
-8.0	0.05	Telecom 2A	C/M	C, X, Ku
-7.0	0.05	Nilesat 101	C	Ku
-5.0	0.05	Telecom 2B	C/M	C, X, Ku
-5.0	0.05	Telecom 2D	C/M	C, X, Ku
-4.0	0.09	Amos 1	C	Ku
-1.0	2.37	Skynet 4C	M	UHF, X, EHF
-1.0	0.03	Intelsat 707	C	C, Ku
-0.8	0.05	Thor 1	C	Ku
-0.8	0.07	Thor 2	C	Ku
-0.7	0.08	Thor 3	C	Ku
0.3	0.38	Meteosat 7	W	VHF, L, S
1		Cosmos 2224	MW	S	#drifting West
3.0	0.03	Telecom 2C	C/M	C, X, Ku
4.8	0.10	Sirius 2	C	Ku
5.2	0.18	Sirius 1	C	Ku
7.0	0.05	Eutelsat 3F3	C	Ku
10.0	0.03	Eutelsat 2F4	C	Ku
12.0	3.34	Raduga 29	MC	C, X
13.0	0.09	Hotbird 1	C	Ku
13.0	0.09	Hotbird 2	C	Ku
13.0	0.07	Hotbird 3	C	Ku
13.0	0.07	Hotbird 4	C	Ku
13.0	0.05	Hotbird 5	C	Ku
13.2	1.92	Italsat 1	C	Ka
15		Skynet 4D	M	UHF, X, EHF	#drifting West
16.0	0.03	Eutelsat 3F2	C	Ku
16.4	0.09	Italsat 2	C	Ka
19.2	0.07	Astra 1A	C	Ku
19.2	0.07	Astra 1B	C	Ku
19.2	0.07	Astra 1C	C	Ku
19.2	0.07	Astra 1D	C	Ku
19.2	0.05	Astra 1E	C	Ku
19.2	0.05	Astra 1F	C	Ku
19.2	0.05	Astra 1G	C	Ku
19.2	0.05	Astra 1H	C	Ku	new
21.0	0.05	Afristar	C	L
23.5	0.07	DFS 3	C	Ku, Ka
24.5	1.87	Inmarsat 3F5	C	L, C
25.5	4.75	Eutelsat 1F4	C	Ku
26.0	0.07	Arabsat 2A	C	C, Ku
26.0	0.07	Arabsat 3A	C	Ku
27.8	0.05	Sirius 3	C	Ku
28.2	0.03	Astra 2A	C	Ku
28.5	0.07	DFS 2	C	Ku, Ka
31.0	0.05	Arabsat 2B	C	C, Ku
31.2	0.05	Turksat 1B	C	Ku
33.0	4.97	Intelsat 510	C	C, Ku
35.0	1.28	Raduga 1-4	MC	C, X
36.0	1.27	Gals 1	C	Ku
36.0	0.40	Gals 2	C	Ku
36.0	0.05	Eutelsat 2F3	C	Ku
36.3	0.03	Bonum 1	C	Ku
40.0	1.18	Gorizont 31	C	L, C, Ku
42.0	0.05	Turksat 1C	C	Ku
45.0	4.36	Raduga 28	MC	C, X	wavering
48.0	0.55	Eutelsat 2F1	C	Ku
49.0	2.67	Raduga 1-3	MC	C, X
50.0	3.63	Gorizont 27	C	C, Ku
52.2	3.49	Skynet 4E	M	UHF, X, EHF
53.0	0.96	Gorizont 32	C	C, Ku
55.0	0.07	Insat 2R	C	S, C
57.0	0.09	Intelsat 703	C	C, Ku
60.0	0.07	Intelsat 604	C	C, Ku
62.0	0.05	Intelsat 602	C	C, Ku
63.0	2.88	Meteosat 5	W	VHF, L, S
63.8	0.20	Inmarsat 3F1	C	L, C
64.0	0.05	Intelsat 804	C	C, Ku
65.0	0.85	Inmarsat 2F3	C	L, C
66.0	0.03	Intelsat 704	C	C, Ku
68.5	0.05	Panamsat 4	C	C, Ku
68.6	0.07	Panamsat 7	C	Ku
70.0	2.01	Raduga 32	MC	C, X
72.0	7.14	Intelsat 505	C	L, C, Ku
72		Electro 1	W	L	drifting East
72		Gorizont 20	C	L, C, Ku	#drifting West, dead?
72		Cosmos 2350	M		drifting East
72.5	12.7	Marisat 3	C	L, C	#old
74.0	1.74	Insat 2A	C/W	S, C
76		Insat 1D	C/W	S, C	drifting west
76.5	0.05	Apstar 2R	C	C, Ku
78.5	0.07	Thaicom 3	C	C, Ku
78.5	0.09	Thaicom 2	C	C, Ku
80.0	1.46	Cosmos 2319	MC	C
80.0	1.17	Express 2	C	C, Ku
83.0	0.07	Insat 2E	C/W	C
85.0	2.93	Raduga 30	MC	C, X	wavering
85.3	4.68	TDRS 3	M	S, C, Ku	wavering, drifting West
87.5	0.07	Chinastar 1	C	C, Ku
88.0	0.05	ST 1	C	C, Ku
90.0	2.89	Gorizont 28	C	L, C, Ku
91.5	0.05	Measat 1	C	C, Ku
93.5	0.09	Insat 2C	C	S, C, Ku
93.5	0.09	Insat 2B	C/W	S, C
99.0	3.60	Ekran 20	C	UHF
100.5	0.07	Asiasat 2	C	C, Ku
103.0	4.13	Gorizont 25	C	L, C, Ku
104.0	0.62	Dong Fang Hong 45	W
105.5	0.05	Asiasat 3S	C	C, Ku
107.7	0.09	Cakrawarta 1	C	L, S
108.0	0.09	Palapa B2R	C	C
108.0		Palapa D1	C	C	new
109.0	2.62	Inmarsat 2F4	C	L, C
110.0	0.09	Yuri 3N	C	Ku	wavering
110.0	0.07	Bsat 1A	C	Ku
110.0	0.05	Bsat 1B	C	Ku
110.5	0.05	Sinosat 1	C	C, Ku
110.9	3.28	Dong Fang Hong 25	C	C
113.0	0.07	Palapa C2	C	C, Ku
115.5	2.68	Spacenet 1	C	C, Ku
116.0	0.05	Koreasat 1	C	Ku
116.0	0.30	Koreasat 2	C	Ku
118.0	0.07	Palapa B4	C	C
120.0	0.09	Thaicom 1	C	C, Ku
120.0	4.05	GMS 4	W	UHF, L, S
122.0	0.33	Asiasat 1	C	C
124.0	0.07	Jcsat 6	C	C, Ku
125.0	0.11	Dong Fang Hong 44	C	C
127.0	0.07	Jcsat 4	C	C, Ku
128.0	0.05	Jcsat 3	C	C, Ku
130.0	2.85	Gorizont 29	C	C, Ku
132.0	0.05	N Star A	C	S, C, Ku, Ka
134.0	0.05	Apstar 1A	C	C
136.0	0.07	N Star B	C	S, C, Ku, Ka
138.0	0.07	Apstar 1	C	C
140.0	0.41	GMS 5	W	UHF, L, S
140.0	5.22	Gorizont 22	C	L, C, Ku
142.5	2.60	Gorizont 30	C	C, Ku
144.0	0.05	Superbird C	C	Ku
145.0	5.30	Gorizont 21	C	L, C, Ku
146.0	0.07	Mabuhay 1	C	C, Ku
148.0	0.03	Measat 2	C	C, Ku
150.0	0.05	Jcsat 5	C	C, Ku
150.5	0.40	Palapa C1	C	C, Ku
154.0	0.05	Jcsat 2	C	Ku
155.7	3.78	Leasat 5	M	P, X
156.0	0.07	Optus B3	C	L, Ku
158.0	0.05	Superbird A2	C	X, Ku, Ka
160.0	0.09	Optus B1	C	L, Ku
162.0	0.07	Superbird B1	C	X, Ku, Ka
164.0	2.39	Optus A3	C	Ku
164.0	4.66	Optus A2	C	Ku
166.0	0.03	Panamsat 8	C	C, Ku
169.0	0.05	Panamsat 2	C	C, Ku
174.0	0.05	Intelsat 802	C	C, Ku
177.0	0.03	Intelsat 702	C	C, Ku
178.0	0.69	Inmarsat 3F3	C	L, C
179.0	1.75	Inmarsat 2F1	C	L, C
180.0	0.05	Intelsat 701	C	C, Ku


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To be launched
 Launch Schedule

Sep 1999

06	Yamal 100 (2) (Proton)
10	Echostar 5 (Atlas 2AR AC-155)
10	MTsat (H2)
21	LMI 1 (Proton with block DM stage)
21	Telstar 7 (Ariane)
23	GPS BIIR-04 (Delta 2)
24	Globalstar (4) #4 (Soyuz)
24	Ikonos 2 (Athena 2)
30	UHF 10 (Atlas 2 AC136)
??	DBS 1R (Zenit Sea Launch)
??	Garuda 1 (Proton)
Oct 1999

03	DMSP 15 / 5D-F15 (Titan 2)
14	STS 103 (HST maintenance)
15	Jawsat (OSC Minotaur, derived from Minuteman) Asusat 1  Opal Falconsat Optical calibration sphere
??	CBERS 1 (Long March 4B) SACI 1 DFH
??	DSCS 3-11 (Atlas AC138)
??	Express A1 (Proton)
??	Globalstar (4) #5 (Soyuz)
??	ICO 4 (Delta 3)
??	Orion 2 (Ariane)
??	STS 99?
Nov 1999

03	Kompsat 1 (Taurus) Acrimsat
??	EOS AM (Atlas 2AS AC-141)
??	Galaxy 11 (Ariane)
??	Globalstar (4) #6 (Soyuz)
??	Globalstar (4) #7 (Delta)
??	Goes 11 (L) (Atlas AC137)
??	ICO 5 (Delta 3)
Dec 1999

06	TSX5 STRV 2 (Pegasus XL)
15	EO 1 (Delta 2 7320) SAC C
15	Orbview 3 (Pegasus)
??	Eros A (Start 1)
??	GE 1A (Proton)
??	Globalstar (4) #8 (Delta)
??	Helios 1B (Ariane) Clementine
??	ICO 2 (Atlas 2AS AC-156)
??	Iridium #13 (Delta 2)
??	Milstar 2-2 (titan 4B Centaur launch)
??	PASI 1 (Ariane)
??	XMM (Ariane 5) STRV 1C & 1D
1999?

??	Arirang 1 (Korean Air satellite, for remote sensing and telecommunication experiments) (Pegasus, Vandenberg)
??	Badr B (Zenit) Meteor
??	CBERS 2 (Long March 4)
??	Coupon 2 (Proton)
??	Cyberstar 1
??	DRS (ESA, Ariane)
??	Foton 12 (Soyuz) (scientific experiments, 6390 kg (608 kg payload), 16-day flight)
??	Gals R12
??	Gorizont 33 (Proton)
??	ICO 1 (Proton)
??	Indostar 2
??	Intersputnik 8
??	Iridium #12 (Delta 2)
??	Koreasat 3 (Ariane 42P V120)
??	Loralsat 101 (Ariane)
??	Lybid (1st Ukrainian communication sat.)
??	Measat 3
??	Odin (Start 1, http://www.ssc.se/ssd/ssat/odin.html, launch cost $5 million, 250 kg)
??	Okean O2-N1 (Zenit) (http://sputnik.infospace.ru/ocean_o/engl/ocean_1.htm) Mysat 1
??	Quick Bird (Cosmos C)
??	Saci 2 (VLS)
??	Sicral (Ariane 5)
??	Tempo 1 (Proton)
??	Voxsat
Jan 2000

16	Asiastar (Ariane 5) Insat 3B
23	Hete 2 (Pegasus XL)
??	Eutelsat 3 SESAT (Proton)
??	Eutelsat 3F4 (Ariane 5)
23	Hispasat 1C (Atlas AC158)
??	NOAA L (Titan 2)
??	Radiosat 1 (Proton)
??	STS 101 (ISS 2A2)
Feb 2000

24	STS 92 (ISS 3A)
??	Artemis (H2A202) Dash (Isas) LDR-P (ETS 8 piggyback experiment)
??	Astra 2B (Ariane)
??	Astro E (Mu 5)
??	Brasilsat B4 (Ariane 5)
??	Globalstar (4) #9 (Delta)
??	Image (Delta 7326)
??	Oicets (J1)
Mar 2000

23	STS 97 (ISS 4A)
??	Echostar 6 (Proton or Atlas)
??	GE 4 (Proton)
??	ICO 7 (Delta 3)
??	SBIRS Low (Delta 2 7420) (prime contactor TRW)
??	TDRS 8 (Atlas 2A AC139)
Apr 2000

??	AMRC 1 (Sea Launch)
??	Eurasiasat 1 (Ariane 5)
??	Galaxy 10R (Sea Launch?)
??	GE 7 (Ariane)
??	M2A (Proton)
??	Mightysat 2
May 2000

??	Chinasat 8 (Long March 3B)
??	Envisat (Ariane 5)
??	Galaxy 4R
??	ICO 10 (Delta 3)
??	Timed (Delta 2 7920) Jason 1
Jun 2000

??	Cluster 2 (Soyuz)
??	Gravity (Delta 2) Probe B
??	Insat 3A (Ariane)
??	Proba (PSLV)
Jul 2000

??	AMRC 2 (Sea Launch)
??	Anik F1 (Ariane 44L)
??	Caribstar (Ariane)
??	GE 2A
??	HESSI (Pegasus)
Aug 2000

??	L Star 1 (Ariane)
??	Nilesat 102 (Ariane)
??	VCL (Athena 1)
Sep 2000

??	Adeos 2 (H2?)
??	ICO 12 (Delta 3)
2000

mid	Catsat (microsatellite, STEDI 3, http://www.catsat.sr.unh.edu/)
mid	Europe*Star (Ariane)
mid	Europesat 1
mid	Thuraya 1 (Ariane 5)
Oct	Astra 2D (Ariane)
Oct	Eutelsat 3F1R
Oct	Intelsat 901 (Proton or Ariane)
Oct	MSG 1 (Ariane 5)
Nov	MAP (Delta 2 7420) (http://map.gsfc.nasa.gov/ non-earth orbit)
Dec	EOS PM-1 (Delta)
Dec	Triana (STS)
late	Asiasat 4 (Delta 3?)
late	Bsat 2A (Ariane)
late	Eutelsat Ressat
late	Fedsat
late	GE 2E
late	GE 8 (Ariane)
late	L Star 2 (Ariane 5)
late	Stentor (Ariane 5) (ESA telecommunication sat., 2 tons)
??	Agrani 1
??	Agrani 2
??	Amos 2
??	AMRC 1 & 2 (HS-702 platforms)
??	APMT (Long March 3B)
??	Apstar 3
??	CBERS 2 (LM 4) HY 1
??	Champ (Cosmos C) Mita Bird
??	Columbia AOR
??	Columbia POR
??	DRTS W (H2) MDS 1
??	Express K1 (Proton)
??	Faisat 1A + Tubsat 2 (Cosmos 3, Plesetsk)
??	FY 1D (LM 4)
??	GE 6
??	GPS BIIR-03 (Delta 2)
??	Gsat (GSLV)
??	Helmarsat (to be the first Greek satellite, aluminium-clad box of 40 cm square, probably a LEO telecom satellite)
??	ICO 3 (Proton)
??	Intelsat KTV (Ariane)
??	IRS P5 (PSLV)
??	Ladybug 1 (Ariane 5)
??	LMI 2 (Proton)
??	LMI 3 (Proton)
??	Loralsat 102 (Ariane)
??	Nemo (Rokot)
??	Nsat 110 (Ariane)
??	Orbview 4
??	Panamsat 1R (Ariane)
??	Panamsat 9 (Sea Launch)
??	Radiosat 2 (Proton)
??	Radiosat 3 (Proton)
??	Resource21
??	Skynet 4F (Ariane)
??	Starlite
??	Superbird 4 (Ariane)
??	Thuraya 2 (Sea Launch or Ariane 5 if the satellite weighs over 5 tons)
??	TRSSS
2001

early	Astra 1K (Ariane)
early	E-sat (3 launches with Rokot)
early	Globalstar (4) #7 (Soyuz)
early	Optus C1
Jan	Intelsat 902 (Ariane)
Feb	Telstar 9
Feb	Vinasat (Vietnam's first telecommunications satellite). Vietnam plans to launch a GEO telecom satellite with 15-20 years lifetime estimated to cost 250-300 million USD It would be operated by the Vietnam Post and Telecommunications (VNPT). bidders are: Hughes, LM, Loral, MMS, Alcatel and IAI (Amos HP platform)
Mar	TDRS 9 (Atlas 2A)
1Q	Geolite (Delta 2 792X)
Apr	Goes 12 (M) (Atlas)
Apr	Intelsat 903 (Ariane)
Apr	NOAA M (Titan 2)
May	Atlantic Bird 1
Jun	IMEX (Titan 4)
Jul	Glas (http://ltpwww.gsfc.nasa.gov/eib/Home.html)
Jul	Icesat (http://icesat.gsfc.nasa.gov/)
Jul	Intelsat 904 (Ariane)
Sep	Galex (Pegasus)
Sep	Integral (Proton)
Sep	Spot 5
4Q	SIRFT (Delta 2 7920H) (IR astronomy, NASA)
Nov	Radarsat 2
Dec	Grace (Cosmos or Rokot)
late	Garuda 2
??	Andesat 1
??	Apstar 5
??	Aries 1
??	Astra 2C (Proton)
??	Bion 12 (Soyuz)
??	Bsat 2B (Ariane)
??	Chunghua 3 (Republic of China -US) mission : global atmosphere monitoring network
??	E-sat
??	Euroskyway
??	Express A2, 14°W (Proton)
??	FSW 2 (LM 2D)
??	Galaxy 3C (Ariane 5 ?) (second of the Galaxy/panamsat's HS-702)
??	GE 9
??	GFO 2 (lockheed EELV)
??	Globalstar (4) #7 (Soyuz)
??	Indostar 3
??	Insat 3C (GSLV)
??	IRS P6 (PSLV)
??	Koreasat 4
??	Ladybug 2 (Ariane 5)
??	LMI 4 (Proton)
??	Measat 3
??	Panamsat 10
??	Project between Boeing and the Israel Aircraft Industries Ltd concerning a new network communication of 17 satellites. Cost estimated at $1 billion  The network would be installed by 2003.
??	Rascom
??	Ruslan
??	Skybridge project
??	Spaceway
??	Telstar 8 (Ariane)
??	Thaicom 4 (Ariane)
2002

early	Intelsat 905 (Ariane)
Feb	Alos (H2A)
Mar	EAST
Dec	EOS Chemistry 1
??	Alsat (algerian communication satellite; should also monitor desert and water resources)
??	Anik F2
??	Aster
??	Astrolink (Atlas 5)
??	Chunghua 2 (Taiwan) low-orbit remote-sensing satelliteChunghua No 3
??	Cryosat (ESA Living Planet, to measure quantity of ice on the poles)
??	DoD (Atlas 3B)
??	DRTS E (H2A)
??	ECCO
??	Echostar Ka-band
??	Ellipsat (Ariane 5)
??	ETS 8 (H2A)
??	Express 3 (Proton)
??	GE Star
??	IRIS (Mu 5) (http://koala.astro.isas.ac.jp/iris/iris_E.html)
??	IRS P7 (PSLV)
??	Kitsat 4
??	M-Star
??	Millennium
??	Morning Star
??	MSG 2 (Ariane 5)
??	Nahuel 2
??	Netsat 28
??	Orblink
??	Orion 7, 8 & 9
??	Panamsat 11
??	Rocsat 2
??	Spaceway (Delta 3?)
??	TSIM (built by OSC on a Microstar platform for the university of Colorado. Cost: $22.8 million.
??	Visionstar
??	Yamal 201 (Proton)
2003

Jan	Rosetta (ESA)
mid	Metop 1
late	NOAA N
??	Argentina & Brasil should build a 350 kg satellite for remote sensing purposes. The satellite might be called Satellite Information project for Food, Water and the Environment (SABIAAA)
??	Hope X (Japan)
??	Indostar 4
??	IRS 2A (PSLV)
??	Mabuhay 2
??	Picasso-Cena Cloudsat
??	Techsat 3
??	Yamal 301 (Proton)
2004

late	Andesat 2
??	Glast (http://www701.gsfc.nasa.gov/glast/glast.htm)
??	Smos (ESA Living Planet, 475 kg including 175 kg payload, interferometer, to measure the salt levels)
??	Spot 6
2005

??	Bimilsatcom
??	Goes N (Delta 3)
2006

??	MSG 3 (Ariane 5, unofficial)
2007

Jan	NPOESS
??	FIRST (ESA, http://sci.esa.int/first/) Planck (http://astro.estec.esa.nl/Planck/)
??	Ines (a navigation program proposed by Alcatel and CNES made of 70 little LEOs with 9 to 12 GEO satellites. to provide GNSS-2 signals)
??	Metop 2
??	Multistar (a navigation program proposed by Alenia Aerospazio. It would include about 20 satellites in MEO and 7 in GEO. They would also include a telecommunication payload. also a GNSS-2 program)
??	NGST (http://ngst.gsfc.nasa.gov/, http://ecf.hq.eso.org/ngst/ngst.html)
2008

early	NOAA N'
No date or late

??	Coupon 3
??	David
??	Elekon
??	Expressway
??	Gramsat
??	Lightsar
??	Marathon/Arkos
??	MDS 2
??	Paksat
??	Panamsat satellite (Ariane) (HS-601HP, 3600 kg, 48 ku transponders)
??	Sapphire (microsatellite) (http://aa.stanford.edu/~ssdl/projects/squirt1/)
??	Sich 2 (Cyclone 3 or Zenit 2)
??	SMEX lite (http://sunland.gsfc.nasa.gov/smex/smexlite/)
??	V-Stream
??	West


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 Glossary

ADC	Analog to Digital Conversion

Apogee	The orbital point were the satellite is furthest from the earth

Apogee Kick Motor (AKM)	A motor on board the satellite that enables the satellite to move from GTO to GEO

Bandwidth	Range on frequency the transponder can transmit, in MHz  Give a measure of capacity

BOL	Begin Of Life

BUD	Big Ugly Dish

Carrier to Noise ratio (C/N)	Ratio which express the quality of a signal (the higher the better)

Catalog number	The number that identifies a satellite, attributed by NASA. See CATNR

CDMA	Code Division Multiple Access.  Access method for several stations to go through a single transponder which uses spread spectrum modulations and orthogonal codes.

Clarke belt	The geostationary orbit, named after Arthur Clarke that first said that such an orbit should exist

COMINT	Communication Intelligence

CONUS	Continental United States (all states but Alaska and Hawaii)

Coverage	Zone where the satellite's signals can be received

DBS	Direct Broadcast Satellite

dBW	ratio of the power to one Watt in decibels (unit used to express EIRP values)

DC power	Total power produced by the solar panels or nuclear reactor

DCME	Digital Circuit Multiplication Equipment

DCP	Data Collection Platform

Downlink	The satellite to earth signal path

DTH	Direct To Home

EIRP	Effective Isotropic Radiated Power
Technical value that evaluates the strength of receive signals

ELINT	Electronic Intelligence

EOL	End Of Life

FDMA	Frequency Division Multiple Access  Access method to a transponder by multiple stations each using 1 unique frequency

Footprint	A map of EIRP values that express the signal strengths at a given location

Frequencies (GHz if not specified)

HF-band	1.8 - 30 MHz
VHF-band	50 - 146 MHz
P-band	0.230 - 1.000
UHF-band	0.430 - 1.300
L-band	1.530 - 2.700
FCC's digital radio	2.310 - 2.360
SHF-band	3 - 30
S-band	2.700 - 3.500
C-band	Downlink: 3.700 - 4.200 Uplink: 5.925 - 6.425 Standard US chart (horizontal) Standard US chart (vertical)
X-band	Downlink: 7.250 - 7.745 Uplink: 7.900 - 8.395
Ku-band (Europe)	Downlink: FSS: 10.700 - 11.700 DBS: 11.700 - 12.500 Telecom: 12.500 - 12.750 Uplink: FSS & Telecom: 14.000 - 14.800 DBS: 17.300 - 18.100
Ku-band (America)	Downlink: FSS: 11.700 - 12.200 DBS: 12.200 - 12.700 Uplink: FSS: 14.000 - 14.500 DBS: 17.300 - 17.800
Ka-band	has multiple acceptations... roughly: 18 - 31 GHz
EHF-band	30 - 300
V-band	36 - 51.4

http://www.ntia.doc.gov/osmhome/nebbia.html

GEO	Geostationary Earth Orbit

Geostationary orbit	The circular orbit at 35.780 km above the equator. Satellites slotted on this orbit always appear at the same position in the sky. In degrees towards East (E or positive) or West (W or negative) from the Greenwich meridian.

G/T	Unit of measurement for an antenna + LNA  Expressed from the gain and and noise temperature. The higher the better

GTO	Geostationary Transfer Orbit
Geostationary satellites are usually launched on a temporary orbit before being moved to GEO

Inclined Orbit	Term used for a GEO satellite that has turned off its North/South stabilization. From Earth, such a satellite seems to draw an 8 in the sky; part of the day it is above the Equator, and then below.

IOL	Inter-Orbit Link

Launch id	Launch number that identifies the flight, see LAUNR

LEO	Low Earth Orbit

LNA	Low Noise Amplifier

LHCP	Left Hand Circular Polarization

PAM	Payload Assist Module

Perigee	The orbital point were the satellite is closest from the earth

Polar orbit	Orbit that is perpendicular to the plan of the Equator

Polarization	Plane of vibration of the electrical field of a signal  Differerent polarizations enable better frequency re-use

Power	The transponder amplification power

RADINT	Radar Intelligence

RHCP	Right Hand Circular Polarization

SCPC	Single Channel Per Carrier
Access method for a large number of signals to go through a single transponder

SIGINT	Signal Intelligence

SSPA	Solid State Power Amplifier

TDMA	Time Division Multiple Access  Access system where each station has a time slot for using a unique carrier shared with others

THEO	Twelve Hours Excentric Orbit (Molniya-type orbit)

Transponder	The association of a receiver, frequency converter and transmiter devices in a satellite

TWTA	Traveling Wave Tube Amplifier

Uplink	The earth to satellite signal path


Printing
 Footprint maps

This section lists EIRP maps first, and then below G/T maps. At the bottom of the page you will find printing tips.

EIRP maps

A

Amos 1: Central Europe

Amos 1: Middle East

Anik E1: C-band

Anik E1: Ku-band

Anik E2: C-band

Anik E2: Ku-band

Anik F1: C-band

Anik F1: Ku-band

Apstar 1: C-band

Apstar 1A: C-band horizontal

Apstar 1A: C-band vertical

Apstar 2R: C-band

Apstar 2R: Ku-band

Arabsat 1C: S-band

Arabsat 1C: C-band

Arabsat 2A: C-band

Arabsat 2A: Ku-band

Arabsat 2B: C-band

Arabsat 2B: Ku-band

Arabsat 3A: Ku-band

ASC 2: C-band, 36 MHz

ASC 2: C-band, 72 MHz

ASC 2: Ku-band

Asiasat 1: North beam

Asiasat 1: South beam

Asiasat 2: C-band

Asiasat 2: Ku-band

Asiasat 3: C-band

Asiasat 3: Ku-band North Asia

Asiasat 3: Ku-band South Asia

Asiasat 3S: C-band

Asiasat 3S: Ku-band North Asia

Asiasat 3S: Ku-band South Asia

Astra 1A: Horizontal 1

Astra 1A: Horizontal 2

Astra 1A: Vertical 1

Astra 1A: Vertical 2

Astra 1B: Horizontal 1

Astra 1B: Horizontal 2

Astra 1B: Vertical 1

Astra 1B: Vertical 2

Astra 1C: Horizontal 1

Astra 1C: Horizontal 2

Astra 1C: Vertical 1

Astra 1C: Vertical 2

Astra 1D: Horizontal 1 (*)

Astra 1D: Horizontal 2 (*)

Astra 1D: Vertical 1 (*)

Astra 1D: Vertical 2 (*)

Astra 1E: Horizontal 1

Astra 1E: Horizontal 2

Astra 1E: Vertical 1

Astra 1E: Vertical 2

Astra 1F: Horizontal 1

Astra 1F: Horizontal 2

Astra 1F: Vertical 1

Astra 1F: Vertical 2

Astra 1G

Astra 1H

Astra 1K: mission 1 (replacement)

Astra 1K: mission 2 (extension)

Astra 2A: Northern

Astra 2A: Southern

Aurora 2

B

Bonum 1

Brasilsat B1

Brasilsat B2: National

Brasilsat B2: Regional

Brasilsat B2: Argentina

Brasilsat B2: National combined

Brasilsat B2: Regional combined

C

Chinastar 1: C-band

Chinastar 1: Ku-band

Columbia AOR

Columbia POR: C-band

Columbia POR: Ku-band

D

DBS 1 (*)

DBS 2

DBS 3

DFS Kopernikus 3

Dong Fang Hong 48: C-band

Dong Fang Hong 48: Ku-band 1

E

Eurasiasat 1: West beam

Eurasiasat 1: East beam

Eutelsat 1F4: spot beams

Eutelsat 1F4: eurobeam

Eutelsat 1F4: SMS beam

Eutelsat 2F1: Super beam

Eutelsat 2F1: Wide beam

Eutelsat 2F2: Super beam

Eutelsat 2F2: Wide beam

Eutelsat 2F3: Super beam

Eutelsat 2F3: Wide beam

Eutelsat 2F4: Super beam

Eutelsat 2F4: Wide beam

Eutelsat 3F1

Eutelsat 3F2

Eutelsat 3F3

Eutelsat 3F3: spot

Eutelsat 3F4

Eutelsat 3 SESAT

Express 1: C-band quasi-global A3 & A5

Express 1: C-band hemispheric A4

Express 1: C-band spot A2

Express 1: Ku-band spot A9

Express 2: C-band quasi-global A3

Express 2: C-band hemispheric A4

Express 2: Ku-band spot A9

G

Galaxy 1R: C-band Horizontal

Galaxy 1R: C-band Vertical

Galaxy 3R: C-band Horizontal

Galaxy 3R: C-band Vertical

Galaxy 4: C-band Horizontal

Galaxy 4: C-band Vertical

Galaxy 4: Ku-band Horizontal

Galaxy 4: Ku-band Vertical

Galaxy 4R: C-band

Galaxy 4R: Ku-band

Galaxy 5: C-band Horizontal

Galaxy 5: C-band Vertical

Galaxy 6: C-band Horizontal

Galaxy 6: C-band Vertical

Galaxy 7: C-band Horizontal

Galaxy 7: C-band Vertical

Galaxy 7: Ku-band Horizontal

Galaxy 7: Ku-band Vertical

Galaxy 9: C-band Horizontal

Galaxy 9: C-band Vertical

Galaxy 9: C-band Alaska extended

Galaxy 10R: C-band

Galaxy 10R: Ku-band

Galaxy 11: C-band

Galaxy 11: C-band

Galaxy 11: Ku-band, North America

Galaxy 11: Ku-band, Extended

Gals 1/2

GE 1: C-band

GE 1: Ku-band

GE 2: C-band

GE 2: Ku-band

GE 3: C-band

GE 3: Ku-band

GE 4: C-band

GE 4: Ku-band

GE 5: Ku-band

Gorizont 20: C-band global A6

Gorizont 20: C-band large hemispheric A4

Gorizont 20: C-band narrow hemispheric A8

Gorizont 21: C-band global A6

Gorizont 21: C-band large hemispheric A4

Gorizont 21: C-band narrow hemispheric A8

Gorizont 21: Ku-band spot A9

Gorizont 22: C-band global A6

Gorizont 22: C-band large hemispheric A4

Gorizont 22: C-band narrow hemispheric A8

Gorizont 22: C-band spot A3

Gorizont 22: Ku-band spot A9

Gorizont 25: C-band global A6

Gorizont 25: C-band large hemispheric A4

Gorizont 25: C-band narrow hemispheric A8

Gorizont 25: Ku-band spot A9

Gorizont 26: C-band global A6

Gorizont 26: C-band large hemispheric A4

Gorizont 26: C-band narrow hemispheric A8

Gorizont 26: Ku-band spot A9

Gorizont 27: C-band global A6

Gorizont 27: C-band large hemispheric A4

Gorizont 27: C-band narrow hemispheric A8

Gorizont 27: Ku-band spot A9

Gorizont 28: C-band global A6

Gorizont 28: C-band large hemispheric A4

Gorizont 28: C-band narrow hemispheric A8

Gorizont 28: C-band spot A3

Gorizont 28: Ku-band spot A9

Gorizont 29: C-band global A6

Gorizont 29: C-band large hemispheric A4

Gorizont 29: C-band narrow hemispheric A8

Gorizont 29: Ku-band spot A9

Gorizont 30: C-band global A6

Gorizont 30: C-band spot A3

Gorizont 30: C-band large hemispheric A4

Gorizont 30: C-band narrow hemispheric A8

Gorizont 30: Ku-band spot A9

Gorizont 31: C-band global A6

Gorizont 31: C-band large hemispheric A4

Gorizont 31: C-band narrow hemispheric A8

Gorizont 31: Ku-band spot A9

Gorizont 32: C-band global A6

Gorizont 32: C-band large hemispheric A4

Gorizont 32: C-band narrow hemispheric A8

Gorizont 32: C-band spot A3

Gorizont 32: Ku-band spot A9

Gstar 2

Gstar 4

H

Hispasat 1A: Direct TV

Hispasat 1A: Telecommunication to Europe

Hispasat 1A: Telecommunication to America

Hispasat 1B: Direct TV

Hispasat 1B: Telecommunication to Europe

Hispasat 1B: Telecommunication to America

Hispasat 1C: Iberia

Hispasat 1C: Europe

Hispasat 1C: America

Hotbird 1

Hotbird 2: superbeam

Hotbird 2: widebeam

Hotbird 3: superbeam

Hotbird 3: widebeam

Hotbird 4: superbeam

Hotbird 4: widebeam

Hotbird 5: superbeam

Hotbird 5: widebeam

I

Insat 1D: C-band

Insat 2A: C-band

Insat 2B: C-band

Insat 2C: C-band standard

Insat 2C: C-band extended

Insat 2E: C-band

Intelsat 505: C-band

Intelsat 505: Ku-band

Intelsat 506: C-band

Intelsat 506: Ku-band

Intelsat 510: C-band

Intelsat 510: Ku-band

Intelsat 511: C-band

Intelsat 511: Ku-band

Intelsat 513: C-band

Intelsat 513: Ku-band

Intelsat 515: C-band

Intelsat 601: C-band

Intelsat 601: Ku-band

Intelsat 602: C-band

Intelsat 602: Ku-band

Intelsat 603: C-band

Intelsat 603: Ku-band

Intelsat 604: C-band

Intelsat 604: Ku-band

Intelsat 605: C-band (*)

Intelsat 605: Ku-band spot East (*)

Intelsat 605: Ku-band spot West (*)

Intelsat K: Ku-band to America

Intelsat K: Ku-band to Europe

Intelsat 701: C-band

Intelsat 701: Ku-band

Intelsat 702: C-band

Intelsat 702: Ku-band

Intelsat 703: C-band

Intelsat 703: Ku-band

Intelsat 704: C-band

Intelsat 704: Ku-band

Intelsat 705: C-band

Intelsat 705: Ku-band

Intelsat 706: C-band

Intelsat 706: Ku-band

Intelsat 707: C-band

Intelsat 707: Ku-band

Intelsat 709: C-band

Intelsat 709: Ku-band

Intelsat 801: C-band

Intelsat 801: Ku-band

Intelsat 802: C-band

Intelsat 802: Ku-band

Intelsat 803: C-band

Intelsat 803: Ku-band

Intelsat 804: C-band

Intelsat 804: Ku-band

Intelsat 805: C- and Ku-band

Intelsat 806: C- and Ku-band

Intelsat KTV: S1 and F1 Ku beams

Intelsat KTV: S2 and F2 Ku beams

Italsat 1: National Ka-band

Italsat 1: Multibeam Ka-band

Italsat 2: National Ka-band

Italsat 2: Multibeam Ka-band

Italsat 2: EMS (L- and Ku-band)

J

Jcsat 1

Jcsat 2

Jcsat 3: C-band

Jcsat 3: Ku-band

K

Koreasat 1: Ku-band FSS

Koreasat 1: Ku-band DBS

Koreasat 2: Ku-band FSS

Koreasat 2: Ku-band DBS

Koreasat 3: Ku-band FSS

Koreasat 3: Ku-band DBS

L

L Star 1

L Star 2

LMI 1: C-band, broad (A) beam

LMI 1: C-band, narrow (B) beam

LMI 1: Ku-band, north (A1) beam

LMI 1: Ku-band, south (A2) beam

M

Mabuhay 1: C-band

Mabuhay 1: Ku-band

Measat 1: C-band

Measat 1: Ku-band

Measat 2: C-band

Measat 2: Ku-band

Morelos 2: C-band

Morelos 2: Ku-band

Morelos 3: C-band

Morelos 3: Ku-band, beam 1

Morelos 3: Ku-band, beam 2

N

Nahuel 1A: Argentina

Nahuel 1A: Brazil

Nahuel 1A: Large beam

Nilesat 101: Ku-band

O

Optus A2: National

Optus A2: Australian spots

Optus A3: National

Optus A3: Australian spots

Optus B1: National (*)

Optus B1: Australian spots (*)

Optus B1: High Performance (*)

Optus B3: National

Optus B3: Australian spots

Optus B3: High Performance

Orion 1: Broad beam to Europe

Orion 1: Spot beams to Europe

Orion 1: Broad beam to US

Orion 1: Spot beams to US

Orion 2: Ku-band

Orion 3: C-band

Orion 3: Ku-band

P

Palapa B2P

Palapa B2R

Palapa B4

Palapa C1: C-band: Asean & New Zealand beam

Palapa C1: C-band: Asean beam

Palapa C1: C-band: Asia beam

Palapa C1: Ku-band

Palapa C2: C-band: Asean & New Zealand beam

Palapa C2: C-band: Asean beam

Palapa C2: C-band: Asia beam

Palapa C2: Ku-band

Panamsat 1: C-band

Panamsat 1: Ku-band to Europe

Panamsat 1: Ku-band to US

Panamsat 1R: C-band America and Africa

Panamsat 1R: C-band global

Panamsat 1R: Ku-band horizontal

Panamsat 1R: Ku-band vertical

Panamsat 1R: Ku-band South America beam 2

Panamsat 2: C-band, Pacific Rim

Panamsat 2: C-band, Oceania

Panamsat 2: Ku-band

Panamsat 3R: C-band beam 1

Panamsat 3R: C-band beam 2

Panamsat 3R: Ku-band

Panamsat 4: C-band, Africa & Asia

Panamsat 4: C-band, Asia/Middle East horizontal

Panamsat 4: C-band, Asia/Middle East vertical

Panamsat 4: Ku-band

Panamsat 5: C-band

Panamsat 5: Ku-band, US

Panamsat 5: Ku-band, Mexico

Panamsat 6: Ku-band, Argentina

Panamsat 6: Ku-band, Brasil

Panamsat 6: Ku-band, NTSC

Panamsat 7: C-band

Panamsat 7: Ku-band, India, Europe/Middle East, South Africa

Panamsat 8: C-band

Panamsat 8: Ku-band, Northeast Asia, Australia

Panamsat 8: Ku-band, Southeast Asia

R

Raduga 1-1

Raduga 1-2

Raduga 1-3

Raduga 21

Raduga 22

Raduga 28

Raduga 29

Raduga 30

Raduga 32

S

Satcom C1

Satcom C3

Satcom C4

Satcom K1

Satcom K2

SBS 5

SBS 6: Horizontal

SBS 6: Vertical

Sinosat 1: C-band

Sinosat 1: Ku-band

Sirius 1

Sirius 2: Europe

Sirius 2: Northern and Central Europe

Sirius 2: Scandinavia

Sirius 3: Scandinavia

Solidaridad 2: C-band

Solidaridad 2: Ku-band

Spacenet 1: C-band

Spacenet 2: C-band

Spacenet 3R: C-band, 36 MHz transponders

Spacenet 3R: C-band, 72 MHz transponders

Spacenet 3R: Ku-band, East and West spots

ST 1: C-band

ST 1: Ku-band

Superbird A2: Ku-band

Superbird B1: Ku-band

Superbird C: Japan & Hawaii

Superbird C: North East Asia

Superbird C: South East Asia

T

TDF 1

TDF 2

TDRS 4: C-band

TDRS 5: C-band

TDRS 6: C-band

TELE X

Telecom 2A: C-band

Telecom 2A: Ku-band

Telecom 2B: C-band (*)

Telecom 2B: Ku-band (*)

Telecom 2C: C-band

Telecom 2C: Ku-band

Telecom 2D: C-band

Telecom 2D: Ku-band

Telstar 301

Telstar 302

Telstar 303

Telstar 402R: C-band

Telstar 402R: Ku-band

Telstar 5: C-band

Telstar 5: Ku-band

Telstar 6: C-band

Telstar 6: Ku-band

Telstar 7: C-band

Telstar 7: Ku-band

Thaicom 1: C-band

Thaicom 1: Ku-band

Thaicom 2: C-band

Thaicom 2: Ku-band

Thaicom 3: C-band, quasi global

Thaicom 3: C-band, zone

Thaicom 3: Ku-band

Thor 1

Thor 2

Thor 3

Turksat 1B: European & Turkish spots

Turksat 1C: Central Europe & Turkey

Turksat 1C: Central Asia & Turkey

Tvsat 2

* means this footprint is available as a preview in the WWW or the Winhelp edition

G/T maps

A

Arabsat 3A: Ku-band

Asiasat 1: North beam

Asiasat 1: South beam

Asiasat 2: C-band

Asiasat 3S: C-band

Asiasat 3S: Ku-band North Asia

Asiasat 3S: Ku-band South Asia

C

Chinastar 1: C-band

Chinastar 1: Ku-band

G

Galaxy 4R: C-band

Galaxy 4R: Ku-band

Galaxy 10R: C-band

Galaxy 10R: Ku-band

Galaxy 11: C-band

Galaxy 11: Ku-band, North America

Galaxy 11: Ku-band, Extended

M

Mabuhay 1: C-band

O

Orion 1: Broad beam to Europe

Orion 1: Spot beam to Europe

Orion 1: Broad beam to US

Orion 1: Spot beam to US

Orion 3: C-band

Orion 3: Ku-band, NEA and India

Orion 3: Ku-band, SEA

P

Panamsat 1: C-band, Central America

Panamsat 1: C-band, South America

Panamsat 1: Ku-band, Europe

Panamsat 1: Ku-band, US

Panamsat 1R: C-band America horizontal

Panamsat 1R: C-band America vertical

Panamsat 1R: C-band Europe/Africa

Panamsat 1R: C-band Global

Panamsat 1R: Ku-band US, Europe, South America horizontal

Panamsat 1R: Ku-band US, Europe, South America vertical

Panamsat 2: C-band horizontal

Panamsat 2: C-band vertical

Panamsat 2: Ku-band horizontal

Panamsat 2: Ku-band vertical

Panamsat 3R: C-band america horizontal

Panamsat 3R: C-band america vertical

Panamsat 3R: C-band africa

Panamsat 3R: Ku-band horizontal

Panamsat 3R: Ku-band vertical

Panamsat 4: C-band, Africa/Middle East vertical

Panamsat 4: C-band, Asia/Middle East horizontal

Panamsat 4: C-band, Asia vertical

Panamsat 4: Ku-band, horizontal

Panamsat 4: Ku-band, vertical

Panamsat 5: C-band horizontal

Panamsat 5: C-band vertical

Panamsat 5: Ku-band

Panamsat 7: C-band horizontal

Panamsat 7: C-band vertical

Panamsat 7: Ku-band

Panamsat 8: C-band

Panamsat 8: Ku-band

S

Sirius 2: Europe

Sirius 2: Northern and Central Europe

Superbird B1: Ku-band

Superbird C: Japan

Superbird C: North East Asia

Superbird C: South East Asia

T

TDRS 4: C-band

TDRS 5: C-band

TDRS 6: C-band

Telstar 402R: C-band horizontal

Telstar 402R: C-band vertical

Telstar 402R: Ku-band horizontal

Telstar 402R: Ku-band vertical

Printing maps

Winhelp is not a very good program for printing. To print a page, use the Print item of the File menu.

To print footprints, you should use the following index: clic on one footprint to display it, then use the File Print function and come back to this page with the Back button of the toolbar.

Beware: we have noted important variations of the printing quality with Winhelp. Grey colors are seldomly properly printed. Check the grey color configuration in the printer panel. If Winhelp doesn't provide good quality printing you should screen shot and print with an external tool (Paintbrush).


C-band US frequency chart (starting horizontal)
 C-band US frequency chart (starting horizontal) (GHz)

Horizontal Uplink	Horizontal Downlink	Channel	Vertical Downlink	Vertical Uplink
	3.720	1		5.945
5.965		2	3.740
	3.760	3		5.985
6.005		4	3.780
	3.800	5		6.025
6.045		6	3.820
	3.840	7		6.065
6.085		8	3.860
	3.880	9		6.105
6.125		10	3.900
	3.920	11		6.145
6.165		12	3.940
	3.960	13		6.185
6.205		14	3.980
	4.000	15		6.225
6.245		16	4.020
	4.040	17		6.265
6.285		18	4.060
	4.080	19		6.305
6.325		20	4.100
	4.120	21		6.345
6.365		22	4.140
	4.160	23		6.385
6.405		24	4.180


C-band US frequency chart (starting vertical)
 C-band US frequency chart (starting vertical) (GHz)

Horizontal Uplink	Horizontal Downlink	Channel	Vertical Downlink	Vertical Uplink
5.945		1	3.720
	3.740	2		5.965
5.985		3	3.760
	3.780	4		6.005
6.025		5	3.800
	3.820	6		6.045
6.065		7	3.840
	3.860	8		6.085
6.105		9	3.880
	3.900	10		6.125
6.145		11	3.920
	3.940	12		6.125
6.185		13	3.960
	3.980	14		6.205
6.225		15	4.000
	4.020	16		6.245
6.265		17	4.040
	4.060	18		6.285
6.305		19	4.080
	4.100	20		6.325
6.345		21	4.120
	4.140	22		6.365
6.385		23	4.160
	4.180	24		6.405


First in History
 First time in History

1957

04 Oct	First satellite, first Russian satellite, Russia becomes the 1st space power: Sputnik 01

03 Nov	First living creature in space: Sputnik 02

1958

01 Feb	First American satellite, America becomes the 2nd space power: Explorer 01

18 Dec	First telecommunication satellite: Score

1959

13 Oct	First meteorology payload: Explorer 07

1960

03 Nov	First NASA satellite: Explorer 08

1961

12 Apr	First man in space

1962

24 Feb	First phone communication & TV broadcast via satellite: Echo 1

26 Apr	First English satellite: Ariel 1

10 Jul	First active telecommunication satellite and first time a company launchs a satellite: Telstar 1

29 Sep	First Canadian satellite: Alouette 1

1963

16 Jun	First woman in space

1964

19 Aug	First geostationary satellite, first geostationary telecommunication satellite: Syncom 3

15 Dec	First Italian satellite: San Marco 1

1965

26 Nov	First French satellite, France becomes the 3rd space power: Astérix

1967

05 Nov	First geostationary meteorology payload: ATS 3

29 Nov	First Australian satellite: Wresat

1968

17 May	First European satellite: ESRO 2B

1969

21 Jul	First man on the moon

08 Nov	First German satellite: Azur

1970

11 Feb	First Japanese satellite, Japan becomes the 4th space power: Ohsumi

10 Mar	First launch from Kourou: Mika

24 Apr	First Chinese satellite, China becomes the 5th space power: Dong Fang Hong 01

1971

28 Oct	First English launched satellite, UK becomes the 6th space power: Prospero

1974

30 May	First direct broadcasting satellite: ATS 6

30 Aug	First Dutch satellite: ANS

15 Nov	First Spanish satellite: Intasat

19 Dec	First civilian satellite 3-axis stabilized: Symphonie 1

1975

19 May	First Indian satellite: Aryabhata

1976

08 Jul	First Indonesian satellite: Palapa A1

1978

24 Oct	First Czechoslovakian satellite: Magion 1

1980

18 Jul	First Indian launched satellite, India becomes the 7th space power: Rohini 1B

1981

12 Apr	First manned launch of the Shuttle: STS 01

07 Aug	First Bulgarian satellite: Intercosmos 22

1982

11 Nov	First satellite launched from the Shuttle: SBS 3

1984

06 Apr	First satellite repared in orbit by the shuttle: SMM

16 Nov	First time satellites were brought back from space: STS 19

1985

08 Feb	First Brazilian satellite: Brasilsat A1

17 Jun	First Mexican satellite: Morelos 1

1986

22 Feb	First Swedish satellite: Viking

1988

19 Sep	First Israeli satellite, Israel becomes the 8th space power: Offek 1

11 Dec	First Luxemburger satellite: Astra 1A

1990

22 Jan	First Argentine satellite: Lusat

07 Apr	First relaunched satellite: Asiasat 1

16 Jul	First Pakistanese satellite: Badr A

1992

10 Aug	First South Korean satellite: Kitsat A

1993

25 Sep	First Portuguese satellite: Posat

18 Dec	First Thai satellite: Thaicom 1

1994

10 Aug	First Turkish satellite: Turksat 1B

1995

31 Aug	First Ukrainian satellite: Sich 1

31 Aug	First Chilean satellite: Fasat Alfa

Sep	PanAmSat becomes the first private company ever to provide global satellite services.

1996

12 Jan	First Malaysian satellite: Measat 1

1997

20 May	First Norwegian satellite: Thor 2

19 Aug	First Philippine satellite: Mabuhay 1

1998

28 Apr	First Egyptian satellite: Nilesat 101

1999

23 Feb	First Danish satellite: Orsted

23 Feb	First South African satellite: Sunsat


 Abrixas

A Broadband Imaging X-Ratz All-sky Survey Satellite

General

Designation	25721 / 99022A
Launch date	28 Apr 1999
Country of origin	Germany
Mission	Astronomy: X-ray astronomy
Perigee/Apogee	600 km
Inclination	51°
Period
Launch vehicle	Cosmos C
Launch site	Kapustin Yar (reopened specially)

DARA satellite developped with the help of the GFZ Postdam, Max-Planck-Institute for extraterrestrial Physics Garching, and the astronomy and astrophysics institute of the Tubingen university. Mission cost: $25 million

End of life

Out of service	1 May 1999
Cause	the battery failed. Enough power might be obtained later to regain contact
Decay
External resources

http://wave.xray.mpe.mpg.de/abrixas

http://zarm9.zarm.uni-bremen.de/2forschung/raumfahrt/abrixas.html

Technical data

Specifications

Prime contractor	OHB System
Platform
Mass at launch	460 kg
Mass in orbit
Dimension	2.5 x 3 x 1.2 m
Solar array
Stabilization
DC power
Design lifetime

MPE/Garching and the Astrophysical Institute in Potsdam developed the scientific payload, a set of seven hard X-ray imaging telescopes with an X-ray CCD detector which will carry out an all-sky survey in the 1-10 keV band with 30 arcsecond resolution.


ACeS
 Program: ACeS

Asia Cellular Satellite system

Mobile telecommunication satellite project to be operated by ACeS Regional Services Co., Ltd.

ACeS is equally owned by Indonesia's PT Pasifik Satelit Nusantara (see M2A), the Philippines Long Distance Telephone Company (see Mabuhay) and Thailand's Jasmine International Overseas Company Ltd which is a subdiary of Jasmine International Public Company Ltd JASM.BK  The global cost is evaluated at $1 billion

The system will provide voice, facsimile, and pager services through new satellites to hand-held mobile and fixed terminals throughout Southeast Asia, India, and China. ACeS will allow a person to use the same Global System for Mobile communications (GSM) based number for both mobile and cellular telephones while traveling throughout Asia. A dual-mode satellite-cellular handset, capable of communicating directly with the satellite as well as connecting up with local terrestrial cellular and fixed networks, will be manufactured by Ericsson Corp. of Sweden.

The ACeS system is expected to be commercial from January 1999, later deferred to mid-1999

In Jan 1999, PSN announced that Lockheed Martin Global Telecommunications will become an equity partner in ACeS. LMGT gets 30% of the shares for $150 million. Jasmine share comes down to 10%.

External resources

http://goldsite.com/Profile/Jasmine/jas14.html

Technical data

Two satellites and all ground installation are to be build by LM Astro Space for $650 million

Overview

Orbit type	GEO
Orbit range	circular
Nb of satellites	1 + 1 backup
Nb of planes	1
Inclination	0°
Nb beams per satellite	12
Modulation	TDMA
Mobile frequencies	L-band
Satellite mass	4500 kg
Coverage
Operational date	1999

Weighs over 5 tons at launch


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Program: ACeS

Garuda 1

Garuda 2


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 Garuda 1

General

Designation
Launch date	1999
Country of origin
Mission	Telecommunications
Geostationary orbit	118°E
Launch vehicle	Proton
Launch site

11000 simultaneous telephone communications

launch cost: $70 million

Technical data

Specifications

Prime contractor	Lockheed Martin
Platform	A2100
Mass at launch	4400 kg
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime	12-15 years
L-band

Main transponders
Backup transponders
Power
Bandwidth
Coverage	covering 22 countries from Indonesia to North Asia
EIRP
Polarization

2 antennas each 12 m diameter (to be built by Harris Aerospace (US))


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 Garuda 2

General

Designation
Launch date
Country of origin
Mission	Telecommunications
Geostationary orbit	118°E
Launch vehicle	Proton
Launch site

Will serve first as a back-up to Garuda 1, and then allow the ACeS system to expand coverage to western and central Asia, Eastern Europe and parts of northern Africa.

Mostly identical to Garuda 1


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 Acrimsat

Active Cavity Radiometer Irradiance Monitor

General

Designation
Launch date	initially planned in 1999
Country of origin	United States
Mission	Solar observation
Operator	NASA
Perigee/Apogee
Inclination
Period
Launch vehicle	Taurus
Launch site

Uses the ACRIM instrument which has already flown twice on SMM and UARS. It was the first instrument to clearly demonstrate that the total radiant energy from the sun was not a constant.

External resources

http://acrim.jpl.nasa.gov/

http://eospso.gsfc.nasa.gov/eos_observ/1_2_95/p39.html

Technical data

Specifications

Prime contractor	OSC?
Platform
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime	5 years


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 ACTS

Advanced Communications Technology Satellite

General

Designation	22796 / 93058B
Launch date	12 Sep 1993
Country of origin	United States
Operator	NASA
Mission	Telecommunications
Geostationary orbit	100°W
Launch vehicle	STS 51

Experimental satellite intended to develop Ka-band mobile services to VSAT terminals from high-data rate personal and transportable terminals.

External resources

http://kronos.lerc.nasa.gov/acts/acts.html

http://sulu.lerc.nasa.gov/dglover/acts.html

Technical data

Specifications

Prime contractor	GE Astro Space
Platform	GE 4000 modified
Mass at launch	2545 kg
Mass in orbit	1555 kg
Dimensions	2.03 x 2.13 x 1.92 m
Stabilization	3-axis
DC power	BOL: 1770 W (batteries: 2 NiCd of 19 AH each) EOL: 1418 W (no payload operation during eclipse)
Design lifetime	4 years
Telemetry & Command	Ka-band with backup in C-band

Orbit control: Blowdown Hydrazine System with redundant thrusters and 4 tanks

Stationkeeping: +/- 0.05°

Ka-band

Main transponders	4
Backup transponders
Power	40 W (TWTA)
Bandwidth	900 MHz
Coverage	A beam-forming network of 45 horns gives a coverage of about 20% of CONUS providing 3 x 0.3° fixed beams There is a single 1.0° mechanically steered beam
EIRP max	spot beam: 60 dBW contiguous sectors: 59 dBW steerable: 53 dBW
Polarization


 Adeos 1

Advanced Earth Observing Satellite, also called Midori (means "green")

General

Designation	24277 / 96046A
Launch date	17 Aug 1996
Country of origin	Japan
Operator	NASDA
Mission	Remote sensing
Perigee/Apogee	800/830 km
Inclination	98.6°
Period	101 min
Cycle	41 days
Launch vehicle	H2 #4

To acquire global observation data corresponding to enviromental changes, such as global warming, depletion of the ozone layer, decrease of tropical rain forests, occurrence of unusual weather, etc. it will also help develop the platform bus interorbit data relay technologies necessary for next-generation Earth Observation Systems.

The satellite encountered several problems after launch: first a thruster problem which required to use the 20 N adjusters to reach final orbit; then on 24th September 1996 the satellite shutdown all nonessential systems. At the same time a scanning mirror used by the Interferomic Monitor for Greenhouse Gases became stuck on 20 September. Also, it was found that cosmic radiations affected the on-board computer. In late 1996 it was also found that the OCTS instrument has a mirror blocked.

Satelite cost: $474 million

External resources

http://jwocky.gsfc.nasa.gov/adeos/adeos.html

http://www.spacer.com/spacenet/text/adeos-e.html

http://mentor.eorc.nasda.go.jp/ADEOS/index.html

End of life

Out of service	30 Jun 1997
Cause	electrical failure caused by the solar array paddle break itself caused by improper maneuver
Technical data

Specifications

Prime contractor	Mitsubishi
Platform
Mass at launch	3500 kg
Mass in orbit
Dimension	4 x 4 x 5 m
Solar array	3 x 26 m
Stabilization	3-axis
DC power	4500 W
Design lifetime	3 years

Telemetry/data at: 2220, 8150, 8250, 8350 MHz  perhaps also 467.7 MHz?

Ka-band inter orbit links to Comets

Payloads

Ocean Color and Temperature Scanner (OCTS)

Advanced Visible and NearInfrared Radiometer (AVNIR)

NASA Scatterometer (NSCAT)

Total Ozone Mapping Spectrometer (TOMS)

Polarization and Directionality of the Earth's reflectances (POLDER)

Interferometric Monitor for Greenhouse Gases (IMG)

Improved Limb Atmospheric Spectrometer (ILAS)

Retroreflector in Space (RIS)


 Adeos 2

Advanced Earth Observing Satellite, also called Midori

General

Designation
Launch date	planned in mid 2000
Country of origin	Japan
Operator	NASDA
Mission	Remote sensing
Perigee/Apogee	800/830 km
Inclination	98.6°
Period	101 min
Cycle	41 days
Launch vehicle	H2?
External resources

http://mentor.eorc.nasda.go.jp/ADEOS/index.html

Technical data

Mass: 3.5 tons

Downlink: 465.9875 or 468.875 MHz (EIRP > 27.1 dBm)

Uplink: 401.65 MHz

Payloads

Global Imager (GLI)

Advanced Microwave Scanning Radiometer (AMSR)

Improved Limb Atmospheric Spectrometer (ILAS 2)

Polarization and Directionality of the Earth's reflectances (POLDER)


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 AEM 1

Application Explorer Satellite, also called HCMM (Heat Capacity Mapping Mission)

General

Designation	10818 / 78041A
Launch date	26 Apr 1978
Country of origin	United States
Mission	Scientific: Remote sensing (Earth thermal study)
Perigee/Apogee	560/641 km
Inclination	97.6°
Period	96.7 min
Launch vehicle	Scout #98
End of life

Decay	26 Apr 1978


 AEM 2

Application Explorer Satellite, also called SAGE (Stratospheric Aerosol and Gas Experiment)

General

Designation	11270 / 79013A
Launch date	18 Feb 1979
Country of origin	United States
Mission	Scientific: high atmosphere study
Perigee/Apogee	456/506 km
Inclination	55°
Period	94.2 min
Launch vehicle	Scout #99
End of life

Decay	11 Apr 1989


 AEM 3

Application Explorer Satellite, also called Magsat

General

Designation	11604 / 79094A
Launch date	30 Oct 1979
Country of origin	United States
Mission	Scientific: Earth magnetic field study
Perigee/Apogee	352/561 km
Inclination	96.8°
Period	93.7 min
Launch vehicle	Scout #101
End of life

Decay	11 Jun 1980


 Program: Aeros

German scientific program


Program: Aeros

Aeros 1

Aeros 2


 Aeros 1

Also called GRS B

General

Designation	06315 / 72100A
Launch date	16 Dec 1972
Country of origin	Germany
Mission	Scientific: ionosphere study
Perigee/Apogee	223/867 km
Inclination	96.9°
Period	95.6 min
Launch vehicle	Scout #83
Mass at launch	127 kg
End of life

Decay	22 Aug 1973


 Aeros 2

General

Designation	07371 / 74055A
Launch date	16 Jul 1974
Country of origin	Germany
Mission	Scientific: ionosphere study
Perigee/Apogee	224/869 km
Inclination	97.5°
Period	95.6 min
Launch vehicle	Scout #88
Mass at launch	127 kg
End of life

Decay	25 Sep 1975


 Afristar

Also called AfriBSS

General

Designation	25515 / 98063A
Launch date	28 Oct 1998
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	21°E
Launch vehicle	Ariane V113

In early Jan 1999 it was revealed that one of the 2 payload interface units is not working properly. This could reduce the expected lifetime of the satellite by preventing a backup TWTA to replace a failed primary TWTA.

Technical data

Specifications

L-band

Onboard signal processing. Equipped with Fokker-made solar arrays which might have a defect.

Freq: 2.21242 or 2.21415 GHz


 Program: Agrani

Also called ASC

Wireless satellite telecommunications system for India: 2 geostationary satellites operated by Afro-Asian Satellite Communications Ltd. ASC is backed by India's Essel Group

In March 1999 news from this project appears again. We learn Videsh Sanchar Nigam Ltd (VSNL), an Indian telecom operator, would invest in the project. It is also said Lockheed Martin is the manufacturer of the satellite (yes not Hugues as constructor).

Previous information included: Ordered from Hughes for $700 million; project worth $850 million Enhanced HS-601s with very large antennas, to provide direct links with handheld radios from Clarke orbit. One will cover Africa, the other central Asia from Moscow to Singapore. Gallium-arsenide solar cells and Hughes xenon-ion stationkeeping engines will be used. One satellite will serve mobile users in 54 countries in Asia, the Middle East and the Indian sub-continent. The other satellite will be focused on Africa. Launch dates are tentatively set for late 1997 and mid 1998. Both satellites will be modified HS-601 spacecraft

Overview

Orbit type	GEO
Orbit range	circular
Nb of satellites	1 + 1 backup
Nb of planes	1
Inclination	0°
Nb beams per satellite	300
Modulation	TDMA
Mobile frequencies	S-band
Satellite mass	4600 kg
Coverage	20E - 120E longitudes, 70N - 30N latitudes
Operational date	1999


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 Ajisai

Means "hydrangea", also called EGP

General

Designation	16908 / 86061A
Launch date	12 Aug 1986
Country of origin	Japan
Mission	Scientific: geodesy
Perigee/Apogee	1479/1497 km
Inclination	50°
Period	115.7 min
Launch vehicle	H1

Japanese satellite designed to provide an orbiting benchmark for geodynamical studies of the Earth. Laser retroflectors are mounted on the surface of the spherical satellite to return incident laser radiation to its point of origin.

Technical data

Specifications

Mass at launch	685 kg
Diameter	2.15 m
Stabilization	passive

It featured 1436 (120 sets) Corner-cube Reflectors and 318 Sunlight Reflection Mirrors

Mission: accurate measurement of the satellite's position with respect to Earth; readjustment of domestic triangulation net for accurate map-making; establishment of ocean geodetic net to position outlying islands.


 Alexis

Also called P89-1

General

Designation	22638 / 93026A
Launch date	23 Apr 1993
Country of origin	United States
Operator	LANL
Mission	Scientific: EUV astronomy
Perigee/Apogee	800 km
Inclination	70°
Period
Launch vehicle	Pegasus #4

Cost: $17 million

External resources

http://nis-www.lanl.gov/nis-projects/alexis/

When Alexis was launched, a bracket that had been damaged during ground testing broke loose, leaving one of the satellite's four solar panels dangling by only its electrical cabling and throwing off the carefully determined balance of the spin-stabilized spacecraft. When the Alexis team restored contact with the satellite more than two months after launch they discovered that not only did it have a serious wobble, but the spacecraft's magnetometer, which was intended to determine the satellite's orientation by sensing Earth's magnetic field lines, had broken when the solar paddle came loose. The Los Alamos science team and the manufacturers came up with a way to determine the satellite's orientation in May 1994. Since then it has been quite successful.

Alexis was designed to monitored the sky in three narrow energy bands between 0.06 and 0.1 keV; it also carried the Blackbeard experiment to study ionospheric effects on radio transmissions.

Technical data

Specifications

Prime contractor	Aero Astro Inc
Platform
Mass at launch	115 kg
Mass in orbit
Dimension	1 m high x 0.6 m diameter
Solar array
Stabilization	spin stabilized (2 rpm)
DC power	50 W
Design lifetime	1 year

S-band telemetry & data


 Alos

Advanced Land Observing Satellite

General

Designation
Launch date	initially planned in 2002
Country of origin	Japan
Operator	NASDA
Mission	Remote sensing
Perigee/Apogee
Inclination
Period
Cycle
Launch vehicle	H2A

Mass: 3900 kg

High resolution JERS

External resources

http://eos-p71b.hq.nasda.go.jp/alos/alos.html

Technical data

PRISM: Panchromatic Remote sensing Instrument for Stereo Mapping (2.5 m resolution)

AVNIR-2: Advanced Visible and Near Infrared Radiometer (10 m resolution)

PALSAR: Phased Array Lband Synthetic Aperture Radar (10 m resolution, L-band)

Onboard storage: MDR, 706 Gb


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 Program: Alouette

Canadian scientific program


Program: Alouette

Alouette 1

Alouette 2


 Alouette 1

General

Designation	00424 / 62049A
Launch date	29 Sep 1962
Country of origin	Canada
Mission	Scientific: ionosphere study
Perigee/Apogee	988/1021 km
Inclination	80.5°
Period	105.2 min
Launch vehicle	Thor Agena B
Launch site	Vandenberg
Mass at launch	145 kg
External resources

http://nssdc.gsfc.nasa.gov/cgi-bin/database/www-nmc?62-049A

Technical data

Frequency: 136 MHz


 Alouette 2

General

Designation	01804 / 65098A
Launch date	29 Nov 1965
Country of origin	Canada
Mission	Scientific: ionosphere study
Perigee/Apogee	499/2706 km
Inclination	79.8°
Period	118.3 min
Launch vehicle	Thor Agena B
Launch site	Vandenberg
Mass at launch	147 kg
External resources

http://nssdc.gsfc.nasa.gov/cgi-bin/database/www-nmc?65-098A


 Amazonico

Remote sensing satellite to be developped by Brazil and Malaysia. It should cost $37 million and be put into orbit in 1998

The satellite should cover the whole amazonian region to monitor the preservation of natural resources and facilitate weather forecasts.


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 Amos 1

Affordable Modular Optimised Satellite

General

Designation	23865 / 96030B
Launch date	16 May 1996
Country of origin	Israel
Operator	Spacecom
Mission	Telecommunications
Geostationary orbit	4°W
Launch vehicle	Ariane V86

Cost: $250 million. The Israeli government supports the program since 1991 with $15 million per year. Launch was insured for over $145 million  The satellite was operational on 1st July 1996

Technical data

EIRP coverage (dBW)

Central Europe

Middle East

Specifications

Prime contractor	Israel Aircraft Industries (IAI)
Platform	AMOS
Mass at launch	961 kg
Mass in orbit	580 kg
Dimensions	2.33 x 2.39 x 2.07 m
Solar array	10.55 m span
Stabilization	3-axis
DC power	BOL: 1231 W
Design lifetime	10 years
Ku-band (11/14 GHz)

Main transponders	7
Backup transponders	2
Power	34 W
Bandwidth	72 MHz
Coverage	Middle East: 3 transponders Central Europe: 4 transponders
EIRP max	54 dBW
G/T max	14 dB/K
SFD max	-74 dBW/m²
Polarization	Linear H/V
Frequencies	Uplink: 14.17 - 14.5 GHz Downlink: 11 - 11.45 GHz
Transponder frequency chart (GHz)

Transponder	Polarization	Downlink  Frequency	Uplink  Frequency
1	V	10.990	14.040
2	V	11.074	14.124
3	V	11.158	14.208
7	H	11.158	14.208
8	H	11.242	14.292
9	H	11.326	14.376
10	H	11.410	14.460
4	V	11.492	14.292
5	V	11.576	14.376
6	V	11.660	14.460
Horizontal transponders are to Central Europe, Vertical transponders are to the Middle East


Amos 1's Central Europe EIRP


Amos 1's Middle East EIRP


Amos 2
 Amos 2? CERS?

Also called Magyarsat or Maggarsat

General

Designation
Launch date	1998
Country of origin	Israel
Mission	Telecommunications
Geostationary orbit	4°W
Launch vehicle	Proton?
Launch site

4 transponders would be reserved to Hungary.

Hungarian Broadcasting Corp. (Nasdaq: HBCO) could bring 69% of the money, the remaining 31% would be shared 50/50 by Antenna Hungaria Rt. (state-owned) and IAI (also state-owned).

Cost: $150 million

In early 1998 the project is said to be abandonned.

Technical data

Ku-band (10.95 - 11.2 & 11.45 - 11.7 GHz)

Main transponders	16
Backup transponders
Power
Bandwidth	36 MHz
Coverage	at least Central Europe
EIRP max	50 dBW
Polarization


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 Program: AMPTE

Active Magnetospheric Particle Tracer Explorers

International scientific program; composed of 3 small satellites launched together in geostationary transfer orbit. CCE separated and fired its Star 13 rocket to move to a lower inclination orbit. The IRM satellite then fired its Hercules BE-3 motor to raise its apogee to more than 100 000 km. Finally the British UKS satellite separated from IRM (UKS didn't have propulsion of its own).

External resources

http://sd-www.jhuapl.edu/AMPTE/

http://nssdc.gsfc.nasa.gov/space/ampte.html


Program: AMPTE

AMPTE CCE

AMPTE IRM

AMPTE UKS


 AMPTE CCE

Charge Composition Explorer

General

Designation	15199 / 84088A
Launch date	16 Aug 1984
Country of origin	United States
Mission	Scientific: magnetophere study
Perigee/Apogee	1121/49671 km
Inclination	4.8°
Period	939.5 min
Launch vehicle	Thor Delta #175
End of life

Out of service	12 July 1989
Cause	failed
Technical data

Specifications

Prime contractor	Johns Hopkins APL
Platform
Mass at launch
Mass in orbit	242 kg
Dimension
Solar array	140 W
Stabilization	spin stabilized, 10 rpm
DC power
Design lifetime

S-band telemetry (2.5 W) and telecommand


 AMPTE IRM

Ion Release Module

General

Designation	15200 / 84088B
Launch date	16 Aug 1984
Country of origin	Germany
Mission	Scientific: magnetophere study
Perigee/Apogee	560/120000 km
Inclination	27°
Period	2653.4 min
Launch vehicle	Thor Delta #175
End of life

Out of service	14 Aug 1986
Cause
Decay	Nov 1987
Technical data

Specifications

Prime contractor	Max Planck MPE
Platform
Mass at launch
Mass in orbit	705 kg
Dimension
Solar array	60 W
Stabilization	spin stabilized, 15 rpm
DC power
Design lifetime

S-band telemetry and telecommand


 AMPTE UKS

United Kingdom Subsatellite

General

Designation	15201 / 84088C
Launch date	16 Aug 1984
Country of origin	United Kingdom
Mission	Scientific: magnetophere study
Perigee/Apogee	1002/113417 km
Inclination	26.9°
Period	2659.6 min
Launch vehicle	Thor Delta #175

The IRM satellite created 3 'artifical comets' by releasing lithium and barium into the magnetosphere.

End of life

Out of service	15 Jan 1985
Cause
Technical data

Specifications

Prime contractor
Platform
Mass at launch
Mass in orbit	77 kg
Dimension
Solar array
Stabilization	spin stabilized, 12 rpm
DC power
Design lifetime

S-band telemetry and telecommand


 Program: AMRC

US satellite program for broadcast of digital radio. A new firm called XM Satellite Radio Inc was created, it is owned by AMSC (majority voting power), Hughes (invested $50 million) and Alcatel.

Two satellites to be delivered in orbit in April and August 2000. An option for a 3rd satellite is included. To be located at 115°W and 85°W.

Alcatel Espace of France, will provide the 9500 W S-band (2332.5-2345 MHz band) Digital Audio Radio Service (DARS) payload.

Radio towers will have to be deployed in cities.

Contact

XM Satellite Radio Inc. (formerly AMRC)

1250 23rd Street, NW, Washington, DC 20037

Tel: 202-969-7100

Fax: 202-969-2050

http://www.xmradio.com/

Technical data

Specifications

Prime contractor	Hughes
Platform	HS-702
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime


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 Program: AMS

Advanced Meteorological Satellite

Military meteorological American program; see DMSP. 3 satellites launched.


 AMSC 1

American Mobile Satellite Corporation 1

General

Designation	23553 / 95019A
Launch date	7 Apr 1995
Country of origin	United States
Operator	AMSC
Mission	Telecommunications
Geostationary orbit	101°W
Launch vehicle	Atlas Centaur

Operated by AMSC. This satellite is a twin of MSAT 1. Both satellites were ordered at the same time (with separate contracts). Both operators will provide complementary mobile telephone, radio, data, and positioning service to land, aviation, and maritime users. Each operator also will provide the other with backup and restoration capacity.

While testing a transmission was sent to the satellite which caused certain components of the communication payload to overheat. The overheating damaged one of eight output hybrid matrix ports that serve the spotbeams covering the Eastern and Central United States. The other seven hybrid ports are operating in accordance with specifications. The remaining four spotbeams, covering the Mountain and Western portions of the United States, Alaska, Hawaii and the Caribbean, were not affected. Furthermore, adjustments in the operation of the satellite will be made to compensate for the power loss.

The satellite experienced in mid-1995, on separate occasions the shutdown of two solid state power amplifiers (SSPA) serving the Mountain, Central, Alaska/Hawaii and Caribbean spotbeams. These spotbeams were designed to be served by eight SSPAs with two spares. As a result of these unusual occurrences, AMSC is currently operating these spotbeams in a seven SSPA configuration which preserves one spare SSPA for such spot beams.

Was to be leased to African Continental Telecommunications Ltd (ACTEL) of Gibraltar through 2003. Cost: $182 million. The satellite should have moved over Africa in mid-1998. ACTEL has signed with Telesat for TT&C services (building 2 earth stations + modifying 2 others) and the procurement of a new satellite by 2002. The 2 new earth stations will be in Gibraltar and Southern Africa. The total investments of ACTEL is $835 million. ACTEL has a South African subsidiary Elcor Holdings Ltd.

The satellite never moved. The deal was probably cancelled.

Technical data

Specifications

Prime contractor	Hughes Hughes (bus) and SPAR Aerospace (payload)
Platform	HS-601
Mass at launch	2550 kg
Mass in orbit	1510 kg
Dimension	2.5 m x 3.5 m x 7.9 m
Solar array	20.96 m span
Stabilization	3-axis
DC power	BOL: 3600 W
Design lifetime	12 years

Springback antennas: 6.7 x 4.9 m x 20 kg (for launch the 2 antennas as rolled together into a 4.9 m high cone shape atop the satellite)

L-band (1545-1559/1646.5-1660.5 MHz)

Main transponders	16
Backup transponders	4
Power	38 W (SSPA)
Bandwidth
Coverage	North America (4 spot beams) Alaska and Hawaii (1 beam) Carribean (1 beam)
EIRP max	58 dBW

Total bandwith: 3200 x 5 KHz

Each beam transponder is equipped with eight surface acoustic wave filters covering the 29 MHz L-band allocation, allowing selection of filters to math traffic needs and to coordinate with other international users. Frequency reuse is incorporated between the North American east and west beams. The beams are combined into two L-band power pools, one covering the east and central beams, and the other covering the remaining service areas. Each power pool is generated by a hybrid matrix amplifier assembly.

Ku-band

Main transponders	1
Backup transponders	2
Power	100 W (TWTA)
Bandwidth
Coverage	CONUS, Carribean, Canada, Alaska and Hawaii
EIRP max	36 dBW
Polarization


 Program: Andesat

Simon Bolivar Andean Satellite System (Sistema Satelital Andino Simón Bolívar)

Satellite telecommunication program of the Andean countries (Bolivia, Colombia, Ecuador, Peru and Venezuela). The satellite system should be called Simon Bolivar. It should cost $520 million

For the moment (before a satellite is launched) the company should lease capacity from Satmex The group has the 67, 78.5, 106 and 109°W slots registered with the ITU, all in coordination phase. The first satellite should be launched in late 2001 in 78.5°W slot.

2 satellites are planned (first launch in late 2004), with footprints covering the entire American continent plus part of Western Europe. Alcatel should take a 70% participation. 56 transponders planned. They will be provided by Alcatel.

Contact

Andesat S.A. E.M.A.

Columbia

External resources

http://www.aseta.org.ec/simonb.htm


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 Program: Anik

In the Inuit dialect, Anik means "little brother". The name was choosen from a national contest to name the program in 1969.

Canadian system owned by Telesat Canada. Canada was the first country to start a domestic telecommunication system because of it's large territory and distributions of its inhabitants.

In 1998 the DBS satellite has its name selected from a contest: Nimiq.


Program: Anik

Anik A1

Anik A2

Anik A3

Anik B1

Anik C1

Anik C2

Anik C3

Anik D1

Anik D2

Anik E1

Anik E2

Anik F1


Anik A's specifications

Prime contractor
Platform
Mass at launch	560 kg
Mass in orbit	295 kg
Diameter	1.9 m
Height	3.54 m
Stabilization	spin-stabilized
DC power	250 W minimum (full 46-day eclipse capability)
Design lifetime	7 years


Anik A's C-band

Main transponders	12
Backup transponders
Power
Bandwidth	36 MHz
Coverage
EIRP max	33 dBW
Polarization


Anik B's specifications

Prime contractor
Platform
Mass at launch
Mass in orbit
Length
Width
Height
Stabilization
DC power
Design lifetime	7 years


Anik B's C-band

Main transponders	12
Backup transponders
Power
Bandwidth	36 MHz
Coverage
EIRP max	36 dBW
Polarization


Anik B's Ku-band

Main transponders	6
Backup transponders
Power
Bandwidth	72 MHz
Coverage
EIRP max	47 dBW
Polarization


Anik C's specifications

Prime contractor	Hughes
Platform	HS-376
Mass at launch	1160 kg
Mass in orbit	563 kg
Diameter	2.16 m
Height	6.6 m (2.84 m stowed)
Stabilization	Spin stabilized
DC power	BOL: 1135 W
Design lifetime	8 years


Anik C's Ku-band

Main transponders	16
Backup transponders	4
Power	15 W (TWTA)
Bandwidth	54 MHz
Coverage
EIRP max	48 dBW
Polarization	linear


Anik D's specifications

Prime contractor	Spar Aerospace with technology licensed from Hughes
Platform	HS-376
Mass at launch	1240 kg
Mass in orbit	633 kg
Diameter	2.16 m
Height	6.6 m (2.84 m stowed)
Stabilization	Spin stabilized
DC power	BOL: 1000 W
Design lifetime	10 years


Anik D's C-band

Main transponders	24
Backup transponders	6
Power	11.5 W (TWTA)
Bandwidth	36 MHz
Coverage
EIRP max	36 dBW
Polarization	linear


Anik E's specifications

Prime contractor	Spar Aerospace with GE Astro
Platform	GE 5000
Mass at launch	2923 kg
Mass in orbit	1781 kg
Length	2.84 m
Width	2.26 m
Height	2.18 m
Solar array	24.3 m span
Stabilization	3-axis
DC power	EOL: 3888 W
Design lifetime	13.5 years


Anik E's C-band

Main transponders	24
Backup transponders	6
Power	11.5 W (SSPA)
Bandwidth	36 MHz
Coverage
EIRP max	36 dBW
Polarization	linear


Anik E's Ku-band

Main transponders	16
Backup transponders	2
Power	50 W (TWTA)
Bandwidth	54 MHz
Coverage
EIRP max	51 dBW
Polarization	linear


Anik E's C-band EIRP


Anik E's Ku-band EIRP


Anik's Ku-band transponder frequency chart
 Anik's Ku-band transponder frequency chart (GHz)

Horizontal Uplink	Horizontal Downlink	Transponder	Vertical Downlink	Vertical Uplink	Beam
14.017		1	11.717		W, N, E, X
	11.730	17		14.030	E or N
14.043		2	11.743		W, N, E, X
	11.756	18		14.056	E or N
14.078		3	11.778		W, N, E, X
	11.791	19		14.091	E or N
14.104		4	11.804		W, N, E, X
	11.817	20		14.117	E or N
14.139		5	11.839		W, N, E, X
	11.852	21		14.152	E
14.165		6	11.865		W, N, E, X
	11.878	22		14.178	E
14.200		7	11.900		W, N, E, X
	11.913	23		14.213	E
14.226		8	11.926		W, N, E, X
	11.939	24		14.239	E
14.261		9	11.961		W
	11.974	25		14.274	E
14.287		10	11.987		W
	12.000	26		14.300	E
14.322		11	12.022		W
	12.035	27		14.335	E
14.348		12	12.048		W
	12.061	28		14.361	E
14.383		13	12.083		W
	12.096	29		14.396	E
14.409		14	12.109		W
	12.122	30		14.422	E
14.444		15	12.144		W
	12.157	31		14.457	E
14.470		16	12.170		W
	12.183	32		14.483	E

Beams: W: West, E: East, N: North, X: Extended corss-border beam


 Anik A1

Also called Telesat 1

General

Designation	06278 / 72090A
Launch date	10 Nov 1972
Country of origin	Canada
Mission	Telecommunications
Geostationary orbit	114°W or 104°W
Launch vehicle	Thor Delta #92

Linked 37 earth stations

End of life

Out of service	yes
Technical data

Specifications

C-band


 Anik A2

Also called Telesat 2

General

Designation	06437 / 73023A
Launch date	20 Apr 1973
Country of origin	Canada
Mission	Telecommunications
Geostationary orbit	109°W
Launch vehicle	Thor Delta #94
End of life

Out of service	yes
Technical data

Specifications

Ku-band


 Anik A3

Also called Telesat 3

General

Designation	07790 / 75038A
Launch date	7 May 1975
Country of origin	Canada
Mission	Telecommunications
Geostationary orbit	104°W or 115°W
Launch vehicle	Thor Delta #110
End of life

Out of service	yes
Technical data

Specifications

Ku-band


 Anik B1

Also called Telesat 4

General

Designation	11153 / 78116A
Launch date	16 Dec 1978
Country of origin	Canada
Mission	Telecommunications
Geostationary orbit	109°W
Launch vehicle	Thor Delta #147
Mass in orbit	473 kg
End of life

Out of service	yes
Technical data

Specifications

C-band

Ku-band


 Anik C1

Also called Telesat 9, Nahuel C1, Nahuel I1

General

Designation	15642 / 85028B
Launch date	13 Apr 1985
Country of origin	Canada
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	STS 23

Was sold to Paracomsat an Argentine operator (when? in 1994?). Telesat obtained a 10% interest in Paracomsat and is to maintain the satellite in orbit until end-1996. The satellite was bought back by Telesat in 1997. In 1999 it is announced the satellite services South America again.

Location

Begin	End	Position
L: 13 Apr 1985		107.5°W
	Mar 1993	109.2°W
Apr 1993	Apr 1997	72°W
May 1997	Apr 1998	118.6°W
Aug 1998		106.3°W, inclined
Technical data

Specifications

Ku-band

Ku-band transponder frequency chart


 Anik C2

Also called Telesat 7, Nahuel C2

General

Designation	14133 / 83059B
Launch date	18 Jun 1983
Country of origin	Canada
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	STS 07

Was sold to Paracomsat an Argentine operator (when? in 1994?). Telesat obtained a 10% interest in Paracomsat and is to maintain the satellite in orbit until end-1996

Location

Begin	End	Position
L: 18 Jun 1983		114.5°W?
	Apr 1993	109.1°W
Jun 1993	mid-June 1997	75.8°W, inclined
mid-Aug 1997	Dec 1997	114.9°W, inclined

Inclined since Aug 1993

End of life

Out of service	Jan 1998
Cause	deorbited
Technical data

Specifications

Ku-band

Ku-band transponder frequency chart


 Anik C3

Also called Telesat 5

General

Designation	13652 / 82110C
Launch date	12 Nov 1982
Country of origin	Canada
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	STS 05
Location

Begin	End	Position
L: 12 Nov 1982	mid-June 1997	114.9°W
End of life

Out of service	Jun 1997
Cause	deorbited
Technical data

Specifications

Ku-band

Ku-band transponder frequency chart


 Anik D1

Also called Telesat 6

General

Designation	13431 / 82082A
Launch date	26 Aug 1982
Country of origin	Canada
Mission	Telecommunications
Geostationary orbit	104.5°W
Launch vehicle	Thor Delta #164
End of life

Out of service	Feb 1995
Technical data

Specifications

C-band


 Anik D2

Also called Telesat 8 or Satcom 4R

General

Designation	15383 / 84113B
Launch date	9 Nov 1984
Country of origin	Canada
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	STS 19

Replaced Anik 1B in November 1986.

Was sold in September 1993 and became Arabsat 1D

Location

Begin	End	Position
L: 9 Nov 1984		113°W?
May 1992	May 1992	82°W (Satcom 4R)
?		110.5°W (Anik D2)
September 1993		20°E (Arabsat 1D)
End of life

Out of service	Mar 1995
Cause	Sent to the junk orbit
Technical data

Specifications

C-band


 Anik E1

Also called Telesat 11

General

Designation	21726 / 91067A
Launch date	26 Sep 1991
Country of origin	Canada
Mission	Telecommunications
Geostationary orbit	111°W
Launch vehicle	Ariane V46

On January 20th, 1994 at 12:50 local time, the satellite ran out of control and thus all transmissions were interrupted. Control was regained at 19:00 and at 20:15 all was back into order. Soon after, it was Anik E2's turn! Those technical hitch were caused by magnetic storms.

At 10:47 UT on March 26, 1996 Telesat lost both the C and Ku-bands on the satellite. This was caused by the disconnection of the South solar panel... After this, the satellite is limited to 9 C-band and 10 Ku-band transponders by lack of power.

Technical data

Specifications

C-band

Ku-band

C-band transponder frequency chart

Ku-band transponder frequency chart

EIRP coverage (dBW)

C-band

Ku-band


 Anik E2

Also called Telesat 10

General

Designation	21222 / 91026A
Launch date	5 Apr 1991
Country of origin	Canada
Mission	Telecommunications
Geostationary orbit	107.3°W
Launch vehicle	Ariane V43

After Anik E1's incident, this satellite run out of control January 20th, 1994 at 21:00 local time after a magnetic storm. It distroyed the on-board stabilization system. To face this problem, Telesat has built a system that calculates and orders the satellite's movements from an Earth station.

This satellite was already victim of technical problems after launch to position its antennas.

On 30 Jul 1999 the satellite experienced another failure. Signals nearly disappeared at approx 20:00 UT and lasted a few hours. The reported cause was a severe magnetic storm.

Technical data

Specifications

C-band

Ku-band

C-band transponder frequency chart

Ku-band transponder frequency chart

EIRP coverage (dBW)

C-band

Ku-band


 Anik F1

General

Designation
Launch date	early 2000
Country of origin	Canada
Mission	Telecommunications
Geostationary orbit	107.3°W
Launch vehicle	Ariane 44L

To be delivered in-orbit (15 May 2000)

Technical data

EIRP coverage (dBW)

C-band

Ku-band

Specifications

Prime contractor	Hughes
Platform	HS-702
Mass at launch	4600 kg
Mass in orbit
Dimension	3.6 m (height) x 3.2 x 2.0 m
Solar array	45.6 m
Stabilization
DC power	EOL: 15000 W
Design lifetime	15 years
C-band

Main transponders	36 (24 for North America, 12 for South)
Backup transponders
Power	40 W
Bandwidth	36 MHz
Coverage	North America South America
EIRP max
G/T max
Polarization	linear H/V
Frequencies	uplink: 5.925-6.425 GHz downlink: 3.7-4.2 GHz
Ku-band

Main transponders	48 (32 for North America, 16 for South America)
Backup transponders
Power	115 W
Bandwidth	27 MHz (4 54 MHz can be formed with all America coverage)
Coverage	North America South America
EIRP max
G/T max
Polarization	linear H/V
Frequencies	uplink: 13.75-14.5 GHz downlink: 11.45-12.2 GHz


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Anik F1's C-band EIRP coverage


Anik F1's Ku-band EIRP coverage


 Anna 1B

General

Designation	00446 / 62060A
Launch date	31 Oct 1962
Country of origin	United States
Mission	Scientific: Geodesy
Perigee/Apogee	1075/1181 km
Inclination	50.1°
Period	107.9 min
Launch vehicle	Thor Ablestar
Launch site	Cape Canaveral


 ANS

Astronomical Netherlands Satellite

General

Designation	07427 / 74070A
Launch date	30 Aug 1974
Country of origin	Netherlands
Mission	Scientific: UV and X-ray astronomy
Perigee/Apogee	268/2174 km
Inclination	98°
Period	99.1 min
Launch vehicle	Scout #89
Mass at launch	130 kg

First Dutch satellite

End of life

Decay	14 Jun 1977


 Apex

Advanced Photovoltaic and Electronic eXperiments, also called P90-6

General

Designation	23191 / 94046A
Launch date	3 Aug 1994
Country of origin	United States
Mission	Scientific: magnetosphere study
Perigee/Apogee	360/2534 km
Inclination	69.9°
Period	115 min
Launch vehicle	Pegasus #7
Mass at launch	260 kg

Carries a variety of advanced solar cell experiments for the US Air Force: Photovoltaic Array and Space Power Plus Diagnostics (PASP-Plus), Ferroelectric Experiment (FERRO), and Cosmic Ray Upset Experiment (CRUX) to check the impact of radiation in the Van Allen belt on the other two target instruments.

Technical data

Platform: Pegastar


APMT
 Program: APMT

Asia Pacific Mobile Telecommunications

Hughes signed a $640 million contract awarded by a consortium of Chinese and Singaporean companies to provide satellite and ground communications equipment. The system will allow callers across a wide range of Asia to use mobile phones in areas without cellular or fixed-line service. 12000 voice channels capacity per satellite. The cost per minute should be < $1. Terminals should include GPS receivers.

Should be operational in 2000, 2 satellites to be launched by Long March 3B from Xichang in Southwest China(maybe only 1 with the other one as ground spare)

APMT regroups four Chinese companies, as well as Singapore Technologies Telemedia and Singapore Telecom. The Chinese participants are CASC, China Unicom Satellite Telecommunication Co Ltd, Chinasat, and China Satellite Launch and Tracking Control General.

In Feb 1999 the US government decided not to grant the export license for the satellite for national security reasons (mainly because of the use of the shinese launch vehicle). APMT cancelled the contract in mid-Apr 1999.

Orbital location: 110°E

Technical data

Specifications

Prime contractor	Hughes
Platform	HS-GEM
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization
DC power	7000 W
Design lifetime	12 years
L-band

Main transponders
Backup transponders
Power
Bandwidth
Coverage	from Japan to Pakistan and from North China to Indonesia
EIRP max
G/T max
Polarization

will have a 12.25 m diameter antenna.

wil be able to carry 16000 calls simultaneously.


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 Apple

Ariane Passenger PayLoad Experiment

General

Designation	12545 / 81057B
Launch date	19 Jun 1981
Country of origin	India
Operator	ISRO
Mission	Telecommunications, experimental
Geostationary orbit	102°E
Launch vehicle	Ariane L03
Mass at launch	670 kg

Carried a C-band transponder

End of life

Out of service	19 Sep 1983


 Program: Apstar

Chinese telecommunication program operated by APT.


Program: Apstar

Apstar 1

Apstar 1A

Apstar 2

Apstar 2R

Apstar 3


Apstar 1's transponder frequency chart (GHz)

Horizontal Uplink	Horizontal Downlink	Transponder	Vertical Downlink	Vertical Uplink	Bandwidth
	3.660	1A		5.885	72
5.885		1B	3.660		72
	3.740	2A		5.965	72
5.985		2B	3.760		72
	3.800	3A		6.025	36
6.045		3B	3.820		36
	3.840	4A		6.065	36
6.085		4B	3.860		36
	3.880	5A		6.105	36
6.125		5B	3.900		36
	3.920	6A		6.145	36
6.125		6B	3.940		36
	3.960	7A		6.185	36
6.205		7B	3.980		36
	4.000	8A		6.225	36
6.245		8B	4.020		36
	4.040	9A		6.265	36
6.285		9B	4.060		36
	4.080	10A		6.305	36
6.325		10B	4.100		36
	4.120	11A		6.345	36
6.365		11B	4.140		36
	4.160	12A		6.385	36
6.405		12B	4.180		36


 Apstar 1

General

Designation	23185 / 94043A
Launch date	21 Jul 1994 at 10:55 UT
Country of origin	China
Mission	Telecommunications
Geostationary orbit	138°E
Launch vehicle	Long March 3

The satellite was to be slotted at 131°E but this was too close from Sakura 3A (132°E) and Gorizont 29 (130°E). After protests from in-orbit satellite operators a slot at 138°E was leased to Tonga (for about $15 million).

Technical data

EIRP coverage (dBW)

Specifications

Prime contractor	Hughes
Platform	HS-376
Mass at launch	1400 kg
Mass in orbit	650 kg
Dry mass	560 kg
Diameter	2.16 m
Height	3.1m, 6.8 m deployed
Stabilization	Spin stabilized
DC power	EOL: 1022 W
Design lifetime	10 years
C-band

Main transponders	24
Backup transponders	6
Power	15 W
Bandwidth	20 transponders of 36 MHz 4 transponders of 72 MHz
Coverage & EIRP max	South East Asia, up to 36 dBW
G/T max	2 dB/K
Polarization	linear H/V
Frequencies	Uplink: 5.850 - 6.425 GHz Downlink: 3.625 - 4.200 GHz

Telemetry: 4.198125 H & 4.199625 H GHz

Command: 5.928 H & 6.422 V GHz

Transponder frequency chart


Apstar 1's C-band EIRP


 Apstar 1A

General

Designation	23943 / 96039A
Launch date	3 Jul 1996
Country of origin	China
Mission	Telecommunications
Geostationary orbit	134°E
Launch vehicle	Long March 3 #39

The satellite was insured for $130 million

Technical data

EIRP coverage (dBW)

Vertical

Horizontal

Specifications

Prime contractor	Hughes
Platform	HS-376
Mass at launch	1400 kg
Dry mass	560 kg
Diameter	2.2 m
Height	3.1m, 7.5 m deployed
Solar array
Stabilization	spin stabilized
DC power
Design lifetime	10 years
C-band (and extended C-band)

Main transponders	24
Backup transponders	6
Power	16 W
Bandwidth	4 transponders of 72 MHz 20 transponders of 36 MHz
Coverage	ASEAN
EIRP max	35 dBW
G/T max	-4 dB/K
Polarization	linear H/V
Frequencies	Uplink: 5.850 - 6.425 GHz Downlink: 3.625 - 4.200 GHz

Telemetry: 4.198125 H & 4.199375 H GHz

Command: 5.928 H & 6.422 V GHz

Transponder frequency chart


Apstar 1A's C-band horizontal EIRP


Apstar 1A's C-band vertical EIRP


 Apstar 2

General

Launch date	25 Jan 1995 at 19:26 UT
Country of origin	China
Mission	Telecommunications
Geostationary orbit	should have been in 77°E slot
Launch vehicle	Long March 2E

Six people had been killed by falling debris from the explosion which also injured 27. The insurers payed $160 million

End of life

Out of service	25 Jan 1995
Cause	Exploded of the satellite shortly after launcher. Failure Review attributed the failure to wind shear interaction with the vehicles structure and the inability of the rather rudimentary control and guidance system of the Long March 2E to account for this.
Technical data

Specifications

Prime contractor	Hughes
Platform	HS-601
Stabilization	3-axis
C-band

Main transponders	26
Backup transponders
Power	52 W
Bandwidth
Coverage
EIRP max
Polarization
Ku-band

Main transponders	8
Backup transponders
Power	6 transponders at 50 W 2 transponders at 120 W
Bandwidth
Coverage
EIRP max
Polarization


 Apstar 2R

General

Designation	25010 / 97062A
Launch date	16 Oct 1997
Country of origin	China
Mission	Telecommunications
Geostationary orbit	76.5°E
Launch vehicle	Long March 3B #46

Was insured for $220 million

In Aug 1999 Loral Space & Communications Ltd leased (via Loral Asia Pacific Satellite Ltd.) the satellite (27 C-band and 13 Ku-band transponders) through its remaining lifetime. It will replace Orion 3. Contract worth $298.1 million. Under the agreement, Loral will also have the option to lease from APT replacement satellites after the Apstar IIR's useful life has ended.

Technical data

EIRP coverage (dBW)

C-band

Ku-band

Specifications

Prime contractor	Space Systems/Loral
Platform	FS-1300
Mass at launch	3700 kg
Dry mass	1415 kg
Dimension	3.10 x 8.60 x 5.50 m
Solar array
Stabilization	3-axis
DC power
Design lifetime	15 years
C-band

Main transponders	28
Backup transponders	8
Power	60 W (TWTA)
Bandwidth	1 transponder of 30 MHz 27 transponders of 36 MHz
Coverage	Asia, Australia and part of Africa
EIRP max	39 dBW
G/T max	-0.4 dB/K
Polarization	linear H/V
Frequencies	Uplink: 5.850 - 6.425 GHz Downlink: 3.625 - 4.200 GHz

Telemetry: 3.627 V & 4.199625 H GHz

Command: 5.8505 H & 6.4245 V GHz

Transponder frequency chart (GHz)

Horizontal Uplink	Horizontal Downlink	Transponder	Vertical Downlink	Vertical Uplink	Bandwidth
	3.643	1A		5.868	30
5.885		1B	3.660		36
	3.680	2A		5.905	36
5.925		2B	3.700		36
	3.720	3A		5.945	36
5.985		3B	3.740		36
	3.760	4A		5.985	36
6.005		4B	3.780		36
	3.800	5A		6.025	36
6.045		5B	3.820		36
	3.840	6A		6.065	36
6.085		6B	3.860		36
	3.880	7A		6.105	36
6.125		7B	3.900		36
	3.920	8A		6.145	36
6.125		8B	3.940		36
	3.960	9A		6.185	36
6.205		9B	3.980		36
	4.000	10A		6.225	36
6.245		10B	4.020		36
	4.040	11A		6.265	36
6.285		11B	4.060		36
	4.080	12A		6.305	36
6.325		12B	4.100		36
	4.120	13A		6.345	36
6.365		13B	4.140		36
	4.160	14A		6.385	36
6.405		14B	4.180		36
Ku-band

Main transponders	16
Backup transponders	8
Power	110 W (TWTA)
Bandwidth	15 transponders of 54 MHz 1 transponder of 36 MHz
Coverage	China
EIRP max	beam 1: 53 dBW beam 2: 56 dBW
G/T max	+7.4 dB/K
Polarization	linear H/V
Frequencies	Uplink: 14.0 - 14.5 GHz Downlink: 12.25 - 12.75 GHz

Beacons: 12.251 & 12.749 GHz

Transponder frequency chart (GHz)

Horizontal Uplink	Horizontal Downlink	Transponder	Vertical Downlink	Vertical Uplink	Beam
	12.272	1A		14.022	beam 1 or 2 (36 MHz)
14.0435		1B	12.2935		beam 2
	12.324	2A		14.074	beam 1
14.1045		2B	12.3545		beam 1
	12.385	3A		14.135	beam 1 or 2
14.1655		3B	12.4155		beam 2
	12.446	4A		14.196	beam 1
14.2265		4B	12.4765		beam 1
	12.507	5A		14.257	beam 1 or 2
14.2875		5B	12.5375		beam 2
	12.568	6A		14.318	beam 1
14.3485		6B	12.5985		beam 1
	12.629	7A		14.379	beam 1 or 2
14.4095		7B	12.6595		beam 2
	12.690	8A		14.440	beam 1
14.4705		8B	12.7205		beam 1


Apstar 2R's EIRP (C-band)

Warning: this map is for a 77°E location only


Apstar 2R's EIRP (Ku-band)

Warning: this map is for a 77°E location only


 Apstar 3

or Apstar 3D

General

Designation
Launch date	1999
Country of origin	China
Mission	Telecommunications
Geostationary orbit	62, 80 or 92°E
Launch vehicle

16 transponders


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 Program: Arabsat

Satellite program of the Arab States operated by Arabsat also known as Arabsat Satellite Communications Organization (ASCO)

In 1976 22 countries decided to build, launch and operate their own telecommunications geostationary satellites. At this time the Arabsat project was an innovation because even if Canada (Anik) and the United States (Comstar, Satcom and Westar) had their own satellites it was only for national communications. 3 satellites were ordered in 1981 to Aérospatiale and the Earth stations were build from 1983 on by Japanese companies.

The organization has started a process towards privatization in 1998.

Contact

Arabsat Operation Center

Tel: +966 1 404 2019

Fax: +966 1 403 3072


Program: Arabsat

Arabsat 1A

Arabsat 1B

Arabsat 1C

Arabsat 1D

Arabsat 1E

Arabsat 2A

Arabsat 2B

Arabsat 3A


Arabsat 1A, 1B & 1C's specifications

Prime contractor	Aerospatiale
Platform	Spacebus-100
Mass in orbit	700 kg
Payload mass	122.4 kg: 101.4 kg: transponders, 21 kg: antennas
Dimension	2.26 x 1.64 x 2.26 m
Solar array	20.7 m span
Stabilization	3-axis
DC power	EOL: 1400 W (equinox), 1300 W (solstice)
Payload power	990.5 W
Design lifetime	7 years


Arabsat 1A, 1B & 1C's S-band

Main transponders	1
Backup transponders
Power	2 x 50 W (TWTA)
Bandwidth	33 MHz
Coverage
EIRP max	41 dBW
Polarization	linear V


Arabsat 1A, 1B & 1C's C-band

Main transponders	25
Backup transponders
Power	8.5 W
Bandwidth	33 MHz
Coverage
EIRP max	31 dBW
Polarization	circular


Arabsat 2's specifications

Prime contractor	Aerospatiale
Platform	Spacebus-3000
Mass at launch	2415 kg
Mass in orbit	1570 kg
Payload mass	260 kg
Dimension	2.4 x 1.6 x 2.3 m
Stabilization	3-axis
DC power	EOL: 5000 W
Design lifetime	12 years


Arabsat 2's C-band

Main transponders	14 + 8
Backup transponders	6 + 4
Power	14 transponders of 15 W (SSPA) 8 transponders of 57.6 W (TWTA)
Bandwidth	Medium power: 12 x 36 MHz + 2 x 54 MHz High power: 8 x 36 MHz
Coverage	Arab States
EIRP max	Medium power transponders: 35 dBW High power transponders: 41 dBW
G/T max	-6 dB/K
Polarization	circular
Frequencies	Uplink: 5.925-6.425 GHz Downlink: 3.7-4.2 GHz


Arabsat 2's Ku-band

Main transponders	12
Backup transponders	5
Power	93 to 96 W (TWTA)
Bandwidth	8 transponders of 36 MHz 4 transponders of 30 MHz
Coverage	Arab States
EIRP max	47 dBW
G/T max	0 dB/K
Polarization	linear
Frequencies	Uplink: 13.750-14.000 GHz Downlink: 12.5-12.75 GHz


Arabsat 2's C-band transponder frequency chart (GHz)

RHCP  Uplink	RHCP Downlink	Channel	LHCP Downlink	LHCP  Uplink	Bandwidth (MHz)
	3.72025	1		5.94525	36
5.96575		2	3.74075		36
	3.76125	3		5.98625	36
6.00675		4	3.78175		36
	3.80225	5		6.02725	36
6.04775		6	382275		36
	3.84325	7		6.06825	36
6.08875		8	3.86375		36
	3.88425	9		6.10925	36
6.12975		10	3.90475		36
	3.92525	11		6.15025	36
6.17075		12	3.94575		36
	3.97825	13		6.20325	54
6.22375		14	3.99875		54
	4.04375	15		6.26875	36
6.28250		16	4.05750		36
	4.08475	17		6.30975	36
6.32350		18	4.09850		36
	4.12575	19		6.35075	36
6.36450		20	4.13950		36
	4.16675	21		6.39175	36
6.40550		22	4.18050		36


Arabsat 2's Ku-band transponder frequency chart (GHz)

Horizontal  Uplink	Horizontal  Downlink	Channel	Vertical  Downlink	Vertical  Uplink	Bandwidth (MHz)
	12.52100	1		13.76800	36
13.78300		2	12.53600		36
	12.56277	3		13.80977	36
13.82477		4	12.57777		36
	12.60453	5		13.85153	36
13.86653		6	12.61953		36
	12.64630	7		13.89330	36
13.90830		8	12.66130		36
	12.68506	9		13.93206	30
13.94706		10	12.70006		30
	12.72000	11		13.96700	30
13.98200		12	12.73500		30


Arabsat 2's C-band EIRP map

For the high power transponders, add 6 dBW


Arabsat 2's Ku-band EIRP map


 Arabsat 1A

General

Designation	15560 / 85015A
Launch date	8 Feb 1985
Country of origin	Arab States
Mission	Telecommunications
Geostationary orbit	19°E
Launch vehicle	Ariane V12
Mass at launch	1170 kg

In Sep 1991 the satellite started drifting East and was completly lost in Mar 1992.

End of life

Out of service	Mar 1992
Cause	Out of control
Technical data

Specifications

S-band

C-band


 Arabsat 1B

General

Designation	15825 / 85048C
Launch date	18 Jun 1985
Country of origin	Arab States
Mission	Telecommunications
Geostationary orbit	26°E
Launch vehicle	STS 25
Mass at launch	1270 kg

In Oct 1992 the satellite started drifting East and was completly lost in early 1993.

End of life

Out of service	early 1993
Cause	Out of control
Technical data

Specifications

S-band

C-band


 Arabsat 1C

General

Designation	21894 / 92010B
Launch date	26 Feb 1992
Country of origin	Arab States
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V49
Mass at launch	1360 kg

Was sold to Insat in late Nov 1997 for $40 million. At that time it is said to have still 5 lifetime years. Replaced the failed Insat 2D and was renamed Insat 2R.

Location

Begin	End	Position
L: 26 Feb 1992	Dec 1997	31°E
Jan 1998		55°E
Technical data

Specifications

S-band

C-band

Beacons: 3.7031 & 4.1999 GHz

EIRP coverage (dBW)

S-band

C-band


Arabsat 1C's S-band EIRP


Arabsat 1C's C-band EIRP


 Arabsat 1D

General

Old name	Anik D2
Country	Arab States
Mission	Telecommunications

Bought in September 1993. A year after it started to have stabilisation problems and to consume alot of propellant.

Location

Begin	End	Position
L: 8 Nov 1984	1993	110.5°W
Sep 1993	Dec 1994...	20°E
Feb 1995	Feb 1995	19°E
End of life

Out of service	Mar 1995
Cause	Sent to the junk orbit


 Arabsat 1E

Also called Arabsat 1DR

General

Old name	Telstar 301
Country	Arab States
Mission	Telecommunications

Leased in January 1995 to replace Arabsat 1D

Location

Begin	End	Position
L: 26 Aug 1982	1994	104.5°W
Jan 1995	Sep 1996	20°E, inclined


 Arabsat 2A

General

Designation	23948 / 96040A
Launch date	9 Jul 1996
Country of origin	Arab States
Mission	Telecommunications
Geostationary orbit	26°E
Launch vehicle	Ariane V89
Mass at launch	2617 kg

Allocations:

Ku-band - Saudi Arabia (3), Qatar, Kuwait, Syria and Jordan (1) - 4 free

C-band - 41dBW - Saudi Arabia (3), Oman (1) - free 4

C-band - 35 dBW - Egypt, Bahrain, Mauritius, Sudan, UAE (1) - 8 free

Technical data

Specifications

C-band

Ku-band

C-band transponder frequency chart

Ku-band transponder frequency chart

EIRP coverage (dBW)

C-band

Ku-band


 Arabsat 2B

General

Designation	24652 / 96063A
Launch date	13 Nov 1996
Country of origin	Arab States
Mission	Telecommunications
Geostationary orbit	30.5°E
Launch vehicle	Ariane V92

Arabsat 1C should then move to 20°E

Technical data

Specifications

C-band

Ku-band

C-band transponder frequency chart

Ku-band transponder frequency chart

EIRP coverage (dBW)

C-band

Ku-band


 Arabsat 3A

Also called Arabsat 2BSS1

General

Designation	25638 / 99009A
Launch date	26 Feb 1999
Country of origin	Arab States
Mission	Telecommunications
Geostationary orbit	26°E
Launch vehicle	Ariane V116

Satellite, launch and insurance is worth $200 million

tested from 23.7°E

Technical data

EIRP coverage (dBW)

Ku-band

G/T coverage (dB/K)

Ku-band

Specifications

Prime contractor	Aerospatiale
Platform	Spacebus-3000
Mass at launch	2708 kg
Mass in orbit	1646 kg
Dry mass	1200 kg
Dimension	3.83 x 3.35 x 2.26 m at launch
Solar array	29 m
Stabilization	3-axis
DC power	6400 W
Design lifetime	12 years

Telecommand: 17.302 V & 17.305 H GHz

Telemetry: 11.702 V & 11.705 H GHz

has a DASA S400 liquid apogee engine

Ku-band

Main transponders	20
Backup transponders	8
Power	(TWTA)
Bandwidth	34 MHz
Coverage
EIRP max	48.5 dBW
G/T max	0.2 dB/K
Polarization	linear H/V
Frequencies	Uplink: 17.3-18.1 GHz Downlink: 11.7-12.5 GHz
Transponder Frequency chart (GHz)

Horizontal  Uplink	Horizontal  Downlink	Channel	Vertical  Downlink	Vertical  Uplink
	11.72748	1		17.32748
17.34666		2	11.74666
	11.76584	3		17.36584
17.38502		4	11.78502
	11.80420	5		17.40420
17.42338		6	11.82338
	11.84256	7		17.44256
17.46174		8	11.86174
	11.88092	9		17.48092
17.50010		10	11.90010
	11.91928	11		17.51928
17.53848		12	11.93848
	11.95764	13		17.55764
17.57682		14	11.97682
	11.99600	15		17.5960
17.61518		16	12.01518
	12.03436	17		17.63436
17.65354		18	12.05354
	12.07272	19		17.67272
17.69190		20	12.09190


Arabsat 3A's Ku-band EIRP coverage


Arabsat 3A's Ku-band G/T coverage


 Argos

Advanced Research and Observation satellite, also called P91-1

General

Designation	25634 / 99008A
Launch date	23 Feb 1999
Country of origin	United States
Mission	Scientific
Perigee/Apogee	831/848 km
Inclination	98.7°
Period	102 min
Launch vehicle	Delta 2 #267

Will collect valuable data on the Earth's global environment performing technology demonstrations for military space programs.

Technical data

Specifications

Prime contractor	Boeing
Platform
Mass at launch	2700 kg
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime	3 years

9 experiments on-board. The most important one is HTSCE II (High Temperature Super Conducting Experiment II) which will test supraconductors. Another interesting experiment is the Electric propulsion Space Experiment (ESEX); it was tested during 141 seconds with a 27 kW electric arc (150 minutes of tests are planned). The experiment must demonstrate no interference with the other satellite payloads.

Transmissions: 2212.5 & 2262.5 MHz


 Program: Ariel

First English space program


Program: Ariel

Ariel 1

Ariel 2

Ariel 3

Ariel 4

Ariel 5

Ariel 6


 Ariel 1

General

Designation	00285 / 62015A
Launch date	26 Apr 1962
Country of origin	United Kingdom
Mission	Scientific: ionosphere study
Perigee/Apogee	398/1203 km
Inclination	53.8°
Period	100.8 min
Launch vehicle	Thor Delta #9

First UK satellite

End of life

Decay	24 May 1976


 Ariel 2

General

Designation	00771 / 64015A
Launch date	27 Mar 1964
Country of origin	United Kingdom
Mission	Scientific: ionosphere and high atmosphere study
Perigee/Apogee	287/1349 km
Inclination	51.7°
Period	101.3 min
Launch vehicle	Scout #25
End of life

Decay	18 Nov 1967


 Ariel 3

General

Designation	02773 / 67042A
Launch date	5 May 1967
Country of origin	United Kingdom
Mission	Scientific: ionosphere and high atmosphere study
Perigee/Apogee	499/604 km
Inclination	80.6°
Period	95.6 min
Launch vehicle	Scout #53

First satellite entirely build in the UK

End of life

Decay	14 Dec 1970


 Ariel 4

General

Designation	05675 / 71109A
Launch date	11 Dec 1971
Country of origin	United Kingdom
Mission	Scientific: ionosphere and high atmosphere study
Perigee/Apogee	476/592 km
Inclination	82°
Period	95.3 min
Launch vehicle	Scout #78
End of life

Decay	12 Dec 1978


 Ariel 5

General

Designation	07471 / 74077A
Launch date	15 Oct 1974
Country of origin	United Kingdom
Mission	Scientific: X-ray astronomy
Perigee/Apogee	504/549 km
Inclination	2.9°
Period	94.9 min
Launch vehicle	Scout #90
End of life

Decay	14 Mar 1980


 Ariel 6

General

Designation	11382 / 79047A
Launch date	2 Jun 1979
Country of origin	United Kingdom
Mission	Scientific: X-ray astronomy
Perigee/Apogee	472/383 km
Inclination	55°
Period	92.1 min
Launch vehicle	Scout #100
End of life

Decay	23 Sep 1990

Downlink: 137.56 MHz, Uplink: 148.25 MHz


 Aries 1

Australian Resource Information and Environment Satellite

General

Designation
Launch date	2001
Country of origin	Australia
Mission	Remote sensing
Perigee/Apogee	400-450 km
Inclination
Period	90 min
Launch vehicle
Launch site

Developed by government scientific research body CSIRO, the Australian Centre for Remote Sensing (ACRES) and Auspace, a unit of MMS.  Will be able to search for minerals as well as monitor environmental changes.

Preliminary costs: A$200 million

A follow-up satellite could come

External resources

http://www.syd.dem.csiro.au/research/MMTG/aries/

Technical data

Specifications

Prime contractor
Platform
Mass at launch	400 kg
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime	5 years

Its hyperspectral imaging spectrometer scanning the surface with up to 105 spectra bands covering the visible, near-infrared and shortwave infrared spectrum.

Its sideways looking system means it can examine any region once every six to seven days. By building up a continuous spectrum of the earth passing below, scientists will be able to differentiate between the

spectral signatures of various minerals in the rocks and soil even through moderate vegetation cover. In addition it will be able to differentiate various vegetation species and a range of environmental indicators.

While its standard target will be a patch of ground 30 x 30 m, sophisticated software will enable the satellite to discern the mineral content of much smaller areas


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 Arsène

Ariane Radio-astronome Satellite ENseignement Espace

General

Designation	22654 / 93031B
Launch date	12 May 1993
Country of origin	France
Mission	Telecommunications
Perigee/Apogee	17261/36793 km
Inclination	1.8°
Period	1012.7 min
Launch vehicle	Ariane V56
Mass at launch	154 kg

Built by Sup Aéro students with the help of RACE (Radio Amateur Club de l'Espace). Made from recovery material.

End of life

Out of service	October 1993
Cause	Failure
Technical data

Packet radio uplink	1200baud, BELL 202 (standard VHF packet radio) AFSK (FM) 435.0625 435.1125 435.1375 MHz
Packet radio downlink	1200baud, BELL 202 AFSK (FM) 145.975 MHz
S-Mode linear transponder:

CW telemetry beacon	2446.4700 MHz, 110lpm CW
S-mode uplink	435.0625 MHz +/- 8kHz
S-mode downlink	2446.5025 MHz +/- 8kHz

Has a SEP Mars apogee motor


 Artemis

Advanced Relay and Technology Mission

General

Designation
Launch date	initially planned in early 2000
Country of origin	Europe
Mission	Telecommunications
Geostationary orbit	21.5°E
Launch vehicle	H2A
Launch site

Artemis will test inter orbit links with SILEX (Semi-conductor Inter-satellite Link Experiment). Artemis will also provide data relay links at Ka-Band (23 to 27 GHz) and S-Band (2 GHz). It will also carry an advanced L-Band (1,61 GHz) payload providing communications to mobile users.

Artemis will be used as relay by Spot 4, Envisat, Oicets, etc.  It is planned to lease one of the L-band transponders.

A navigation terminal to guide civilian aircraft, boats and land vehicles will be placed on board. This modification will cost $8 million.

Oicets (Optical Inter-orbit Communications Engineering Test Satellite) is a planned satellite, 500 kg in LEO capable of S-band and laser data relay

The satellite was developed by a consortium headed by the Italian company Alenia Aerospazio. Italy has a 40 percent share, France 21.25 percent, Germany 12 percent, Spain 7.5 percent, Britain 6.7 percent and Belgium four percent.  In exchange for launching Artemis at no cost, Japan will be able to make use of 40 percent of its telecommunications capacity.

The satellite is worth approx. $940 million. ESA's most expensive satellite.

Four beams will cover Europe, North Africa, and Near East and will be able to handle up to 400 bi-directionnal links.

Technical data

Specifications

Prime contractor	Alenia Spazio
Platform
Mass at launch	3100 kg
Dry mass	1500 kg
Dimension
Solar array
Stabilization	3-axis
DC power	2750 W
Design lifetime	10 years

Has got liquid-propellant motors (1 of 410 N and 16 of 10 N thrust) and ion propulsion (15 mN and 18 mN). Tanks contain 1.5 t ergols and 40 kg Xenon.

SKDR (S/Ka band Data Relay)

Main transponders	Ka band (20/ 30 GHz) S band (2 GHz) and Ka band (23/26 GHz)
Backup transponders
Power
Bandwidth
Coverage
EIRP max
G/T max
Polarization
Frequencies	20/30 GHz 23-26 GHz (interorbit) 2 GHz (interorbit)

The antenna is 2.85 m diameter, aimed at Envisat

Silex uses optical frequencies; it will work with Spot 4 and Oicets

LLM

Main transponders	L-band (1.5/1.6 GHz):  Ku-band (12/14 GHz):
Power
Bandwidth	L-band: 4 MHz? Ku-band: 0.9 MHz?
Coverage	Europe
EIRP max

A navigation payload (25 kg) was also added. It is part of the EGNOS program (European Geostationnary Navigation Overlay Service). Two Inmarsat 3 satellites are also part of this program.


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 Aryabhata

Named after a ancient Indian mathematician (5th century AD)

General

Designation	07752 / 75033A
Launch date	19 May 1975
Country of origin	India
Mission	Scientific: ionosphere study
Perigee/Apogee	563/619 km
Inclination	50.7°
Period	92.6 min
Launch vehicle	Cosmos C
Launch site	Kapustin Yar
Mass at launch	360 kg

Studied astronomy sources and relations between Earth and Sun (X-ray astronomy, solar physics and aeronomy).

End of life

Out of service	After 4 days
Cause	Failure of the Indian-designed transformer
Decay	11 Feb 1992


 Program: ASC

American Satellite Company

Program from ASC and CONTEL (CONtinental TELephone company). The satellites are used for GATS (Global Access Telecommunications Services).


Program: ASC

ASC 1

ASC 2


ASC's specifications

Prime contractor	GE Astro Space
Platform	GE 3000
Mass at launch	1250 kg
Mass in orbit	665 kg
Dimension	1.63 x 1.32 x 0.99 m
Solar array	14.33 m span
Stabilization	3-axis
Design lifetime	10 years


ASC's C-band transponder frequency chart
 ASC's C-band transponder frequency chart (GHz)

Vertical Uplink	Vertical Downlink	Transponder	Channel	Horizontal Downlink	Horizontal Uplink
	3.720	1	1		5.945
5.965		13L	2	3.740
	3.760	2	3		5.985
6.005		13U	4	3.780
	3.800	3	5		6.025
6.045		14L	6	3.820
	3.840	4	7		6.065
6.085		14U	8	3.860
	3.880	5	9		6.105
6.125		15L	10	3.900
	3.920	6	11		6.145
6.125		15U	12	3.940
	3.960	7	13		6.185
6.205		16L	14	3.980
	4.000	8	15		6.225
6.245		16U	16	4.020
	4.040	9	17		6.265
6.285		17L	18	4.060
	4.080	10	19		6.305
6.325		17U	20	4.100
	4.120	11	21		6.345
6.365		18L	22	4.140
	4.160	12	23		6.385
6.405		18U	24	4.180


ASC's Ku-band transponder frequency chart (GHz)

Horizontal Downlink	Transponder	Vertical Uplink
11.740	19	14.040
11.820	20	14.120
11.900	21	14.200
11.980	22	14.280
12.060	23	14.360
12.140	24	14.440


 ASC 1

General

Designation	15994 / 85076C
Launch date	27 Aug 1985
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	128°W
Launch vehicle	STS 27
End of life

Out of service	Nov 1994?
Technical data

Specifications

C-band transponder frequency chart

Ku-band transponder frequency chart

C-band

Main transponders	18
Backup transponders
Power	36 MHz: 12 of 8.5 W (SSPA) 72 MHz: 6 of 16.2 W (TWTA)
Bandwidth	12 of 36 MHz 6 of 72 MHz
Coverage
EIRP max	34 dBW
Polarization	linear
Ku-band

Main transponders	6
Backup transponders
Power	16.2 W (TWTA)
Bandwidth	72 MHz
Coverage
EIRP max	42 dBW
Polarization	linear H


 ASC 2

Otherwise known as Spacenet 4

General

Designation	21227 / 91028A
Launch date	13 Apr 1991
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	101°W
Launch vehicle	Delta 2 #204

[early 1998] Would have technical malfunctions in the Ku-band

Technical data

EIRP coverage (dBW)

C-band, 36 MHz transponders

C-band, 72 MHz transponders

Ku-band

Specifications

C-band transponder frequency chart

Ku-band transponder frequency chart

C-band

Main transponders	18
Backup transponders
Power	36 MHz: 12 of 8.5 W (SSPA) 72 MHz: 6 of 16 W (TWTA)
Bandwidth	12 of 36 MHz 6 of 72 MHz
Coverage
EIRP max	37 dBW
Polarization	linear
Ku-band

Main transponders	6
Backup transponders
Power	6 of 16.2 W (TWTA) 2 of 30 W (TWTA)
Bandwidth	72 MHz
Coverage
EIRP max	46 dBW
Polarization	linear H


ASC 2's C-band 36 MHz EIRP


ASC 2's C-band 72 MHz EIRP


ASC 2's Ku-band EIRP

This map is for 16 W transponders, add 3 dBW for 30 W transponders


 Program: Asiasat

Telecommunication program operated by Asiasat


Program: Asiasat

Asiasat 1

Asiasat 2

Asiasat 3

Asiasat 3S

Asiasat 4

Asiasat G


 Asiasat 1

General

Designation	20558 / 90030A
Launch date	7 Apr 1990
Country of origin	China
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Long March 3

This satellite was Westar 6 that was brought back from Space by the Shuttle in 1984. It was bought for only $58 million

Location

Begin	End	Position
L: 7 Apr 1990	Jun 1999	105.5°E
Aug 1999		122°E
Technical data

EIRP coverage (dBW)

North beam

South beam

G/T coverage (dB/K)

North beam

South beam

Specifications

Prime contractor	Hughes
Platform	HS-376
Mass at launch	1244 kg
Mass in orbit	620 kg
Diameter	2.16 m
Height	6.6 m (2.84 m stowed)
Stabilization	Spin stabilized
DC power	BOL: 850 W
Design lifetime	9 years
C-band

Main transponders	24
Backup transponders	6
Power	8.5 W (TWTA)
Bandwidth	36 MHz
Coverage and EIRP max	North beam: 36 dBW South beam: 37 dBW
G/T max	3 dB/K
SFD	-81 to -90 dBW/m²
Polarization	linear H/V
Transponder frequency chart (GHz)

Horizontal  Uplink	Horizontal  Downlink	Transponder	Vertical  Downlink	Vertical  Uplink
	3.720	1H		5.945
5.965		1V	3.740
	3.760	2H		5.985
6.005		2B	3.780
	3.800	3H		6.025
6.045		3V	3.820
	3.840	4H		6.065
6.085		4V	3.860
	3.880	5H		6.105
6.125		5V	3.900
	3.920	6H		6.145
6.165		6V	3.940
	3.960	7H		6.185
6.205		7V	3.980
	4.000	8H		6.225
6.245		8V	4.020
	4.040	9H		6.265
6.285		9V	4.060
	4.080	10H		6.305
6.325		10V	4.100
	4.120	11H		6.345
6.365		11V	4.140
	4.160	12H		6.385
6.405		12V	4.180


Asiasat 1's North beam EIRP coverage


Asiasat 1's South beam EIRP coverage


Asiasat 1's North beam G/T coverage


Asiasat 1's South beam G/T coverage


 Asiasat 2

General

Designation	23723 / 95064A
Launch date	28 Nov 1995 at 11:30 UT
Country of origin	China
Mission	Telecommunications
Geostationary orbit	100.5°E
Launch vehicle	Long March 2E

Second stage orbit: 185 km x 309 km x 28° Then the Chinese perigee kick motor SPTM-17 (second flight) lifted Asiasat to 222 x 35039 km x 25.6° and the liquid apogee motor (a Leros-class dual mode liquid apogee engine built by Royal Ordnance plc, England) then circularized the orbit.

Cost: $200 million

Technical data

EIRP coverage (dBW)

C-band

Ku-band

G/T coverage (dB/K)

C-band

Specifications

Prime contractor	GE Astro Space
Platform	GE 7000
Mass at launch	3460 kg
Mass in orbit	1500 kg
Dimension	24 x 7 m deployed
Stabilization	3-axis
DC power	BOL: 7100 W
Design lifetime	13 years

The perigee engine was made in China and is being used for the first time.

C-band

Main transponders	24
Backup transponders	6
Power	55 W (TWTA)
Bandwidth	20 transponders at 36 MHz 4 transponders at 72 MHz
Coverage	Asia and Australia
EIRP max	39 dBW
G/T max	0 dB/K
SFD	-97 dBW/m²
Polarization	Linear H/V
Frequencies	Uplink: 5.845-6.425 GHz Downlink: 3.625-4.2 GHz
Transponder frequency chart (GHz)

Horizontal downlink	Transponder	Vertical downlink	Bandwidth (MHz)
3.640	1B		36
	1A	3.660	36
3.680	2B		36
	2A	3.700	36
3.720	3B		36
	3A	3.740	36
3.760	4B		36
	4A	3.780	36
3.800	5B		36
	5A	3.820	36
3.840	6B		36
	6A	3.860	36
3.880	7B		36
	7A	3.900	36
3.920	8B		36
	8A	3.940	36
3.960	9B		36
	9A	3.980	36
4.000	10B		36
	10A	4.020	36
4.060	11B		72
	11A	4.080	72
4.140	12B		72
	12A	4.160	36
Ku-band

Main transponders	9
Backup transponders	3
Power	115 W (TWTA)
Bandwidth	54 MHz
Coverage	China and nearby countries
EIRP max	52 dBW
G/T max	6 dB/K
SFD	-97 dBW/m²
Polarization	Linear
Frequencies	Uplink: 14.0-14.3 GHz Downlink: 12.2-12.5 GHz
Transponder frequency chart (GHz)

Horizontal downlink	Transponder	Vertical downlink
12.230	1
	2	12.245
12.290	3
	4	12.305
12.350	5
	6	12.365
12.410	7
	8	12.425
12.470	9


Asiasat 2's C-band EIRP coverage


Asiasat 2's Ku-band EIRP coverage


Asiasat 2's C-band G/T coverage


 Asiasat 3

Also called HGS 1 and PS 22

General

Designation	25126 / 97086A
Launch date	24 Dec 1997
Country of origin	China
Mission	Telecommunications
Geostationary orbit	should have gone to 105.5°E, see below
Launch vehicle	Proton #255

Was to be launched by Long March but this was cancelled after the Intelsat 708 crash.

Satellite cost approx $100 million. Was to go to 105.5°E.

The launcher failed to place the satellite in GEO; it was left in 365 x 35989 km x 51.6°. The satellite was believed to be lost and the insurances payed $250 million in compensation. The ownership of the spacecraft was transfered to HGS (the satellite was renamed HGS 1) to try a very special manoeuver. HGS will share profits of the satellite salvage with the consortium of 27 insurers.

A first manoeuver was carried out in May 1998 to reach the GEO orbit using the attraction of the moon. On this very special orbit the satellite flied-by the moon (in spin-stabilized mode with main antennas deployed). A second lunar flyby was then programmed to improve the orbit. This was the very first time a commercial satellite used this kind of manoeuver.

This operation consumed most of the 1700 kg of propellant. On June 19th, the satellite over 152 W with a 35963 km apogee and a 35681 km perigee at a 8.7 degree orbit.

HGS was formed 10 months ago as a subsidiary of Hughes Space and Communications. It provides domestic and international government and public-sector agencies at all levels with "one-stop shopping" access to commercially available satellite communications.

In Apr 1999 Hughes filled to request authorization to operate the satellite at 60°W in C-band (transp. 3B to 14A) and in Ku-band (5B to 8A). The satellite is then renamed PAS 22

Location

Begin	End	Position
L: 24 Dec 1997		bad orbit
Jul 1998	Nov 1998	158°W, inclined
May 1999		62°W, inclined
External resources

http://www.hughesglobal.com/

Technical data

EIRP coverage (dBW)

C-band

Ku-band North Asia

Ku-band South Asia

G/T coverage (dBW)

C-band

Ku-band North Asia

Ku-band South Asia

Specifications

Prime contractor	Hughes
Platform	HS-601HP
Mass at launch	3480 kg
Mass in orbit	2534 kg
Dry mass	1674 kg
Dimension	26.2 x 7.6 m deployed
Solar array
Stabilization	3-axis
DC power	9900 W
Design lifetime	15 years

Has a Marquardt R-4D-11-300 liquid propulsion. Is reported to have battery problems.

C-band

Main transponders	28
Backup transponders	6
Power	55 W (TWTA)
Bandwidth	36 MHz
Coverage	Asia, the Indian subcontinent, the Middle East and Australia
EIRP max	40 dBW
G/T max	-1 dB/K
SFD	-98 dBW/m² (at G/T = -1 dB/K)
Polarization	linear H/V
Transponder frequency chart (GHz)

Horizontal  uplink	Horizontal downlink	Transponder	Vertical downlink	Vertical  uplink
	3.640	1B		5.865
5.885		1A	3.660
	3.680	2B		5.905
5.925		2A	3.700
	3.720	3B		5.945
5.965		3A	3.740
	3.760	4B		5.985
6.005		4A	3.780
	3.800	5B		6.025
6.045		5A	3.820
	3.840	6B		6.065
6.085		6A	3.860
	3.880	7B		6.105
6.125		7A	3.900
	3.920	8B		6.145
6.165		8A	3.940
	3.960	9B		6.185
6.205		9A	3.980
	4.000	10B		6.225
6.245		10A	4.020
	4.060	11B		6.265
6.285		11A	4.080
	4.140	12B		6.305
6.325		12A	4.160
	4.120	13B		6.345
6.365		13A	4.140
	4.160	14B		6.385
6.405		14A	4.180
Ku-band

Main transponders	16
Backup transponders	4
Power	138 W (TWTA)
Bandwidth	54 MHz
Coverage	2 beams: 1 for China & 1 for India + 1 steerable beam
EIRP max	53 dBW
G/T max	6 dB/K
SFD	-100 dBW/m² (at G/T = 7 dB/K)
Polarization	linear H/V
Transponder frequency chart (GHz)

Horizontal uplink	Horizontal downlink	Transponder	Vertical downlink	Vertical uplink	beam
	12.280	1B		14.028	North
14.048		1A	12.300		North/South
	12.340	2B		14.088	North
14.108		2A	12.360		North/South
	12.400	3B		14.148	North
14.168		3A	12.420		North/South
	12.460	4B		14.208	North
14.228		4A	12.480		North/South
	12.520	5B		14.268	North
14.288		5A	12.540		North/South/Steerable
	12.580	6B		14.328	North
14.348		6A	12.600		North/South/Steerable
	12.640	7B		14.388	North
14.408		7A	12.660		North/South/Steerable
	12.700	8B		14.448	North
14.468		8A	12.720		North/South/Steerable


Asiasat 3S's C-band EIRP


Asiasat 3S's Ku-band North Asia EIRP


Asiasat 3S's Ku-band South Asia EIRP


Asiasat 3S's C-band G/T coverage


Asiasat 3S's Ku-band North Asia G/T coverage


Asiasat 3S's Ku-band South Asia G/T coverage


 Asiasat 3S

General

Designation	25657 / 99013A
Launch date	21 Mar 1999
Country of origin	China
Mission	Telecommunications
Geostationary orbit	105.5°E
Launch vehicle	Proton #265

Almost identical to Asiasat 3  Cost: $195 million

Tested at 98°E, went operational on 8 May 1999

A backup of this satellite was ordered to Hughes in Nov 1998. It is said to be identical to Asiasat 3S

Technical data

EIRP coverage (dBW)

C-band

Ku-band North Asia

Ku-band South Asia

G/T coverage (dBW)

C-band

Ku-band North Asia

Ku-band South Asia

Specifications

Prime contractor	Hughes
Platform	HS-601HP
Mass at launch	3480 kg
Mass in orbit	2500 kg
Dimension	26.2 x 7.6 m deployed
Solar array
Stabilization	3-axis
DC power	9900 W
Design lifetime	15 years
C-band

Main transponders	28
Backup transponders	6
Power	55 W (TWTA)
Bandwidth	36 MHz
Coverage	Asia, the Indian subcontinent, the Middle East and Australia
EIRP max	40 dBW
G/T max	-1 dB/K
SFD	-98 dBW/m² (at G/T = -1 dB/K)
Polarization	linear H/V

beacons: 4.1995 & 4.2005 GHz

Transponder frequency chart (GHz)

Horizontal  uplink	Horizontal downlink	Transponder	Vertical downlink	Vertical  uplink
	3.640	1B		5.865
5.885		1A	3.660
	3.680	2B		5.905
5.925		2A	3.700
	3.720	3B		5.945
5.965		3A	3.740
	3.760	4B		5.985
6.005		4A	3.780
	3.800	5B		6.025
6.045		5A	3.820
	3.840	6B		6.065
6.085		6A	3.860
	3.880	7B		6.105
6.125		7A	3.900
	3.920	8B		6.145
6.165		8A	3.940
	3.960	9B		6.185
6.205		9A	3.980
	4.000	10B		6.225
6.245		10A	4.020
	4.060	11B		6.265
6.285		11A	4.080
	4.140	12B		6.305
6.325		12A	4.160
	4.120	13B		6.345
6.365		13A	4.140
	4.160	14B		6.385
6.405		14A	4.180
Ku-band

Main transponders	16
Backup transponders	4
Power	138 W (TWTA)
Bandwidth	54 MHz
Coverage	2 beams: 1 for China & 1 for India + 1 steerable beam
EIRP max	53 dBW
G/T max	6 dB/K
SFD	-100 dBW/m² (at G/T = 7 dB/K)
Polarization	linear H/V
Transponder frequency chart (GHz)

Horizontal uplink	Horizontal downlink	Transponder	Vertical downlink	Vertical uplink	beam
	12.280	1B		14.028	North
14.048		1A	12.300		North/South
	12.340	2B		14.088	North
14.108		2A	12.360		North/South
	12.400	3B		14.148	North
14.168		3A	12.420		North/South
	12.460	4B		14.208	North
14.228		4A	12.480		North/South
	12.520	5B		14.268	North
14.288		5A	12.540		North/South/Steerable
	12.580	6B		14.328	North
14.348		6A	12.600		North/South/Steerable
	12.640	7B		14.388	North
14.408		7A	12.660		North/South/Steerable
	12.700	8B		14.448	North
14.468		8A	12.720		North/South/Steerable


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 Asiasat 4

General

Designation
Launch date	initially planned in 1999
Country of origin	China
Mission	Telecommunications
Geostationary orbit	122°E
Launch vehicle
Launch site

Was planned for late 1999, but will be delayed because of the Asian crisis.

Should remain a ground backup identical to Asiasat 3S. It could later be transformed in the actual Asiasat 4

Worth $100 million


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 Asiastar

Also called AsiaBSS

General

Designation
Launch date	initially planned in late-1998
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	105°E
Launch vehicle	Ariane
Technical data

Specifications

L-band


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 Program: Aster

Telecommunication program of Spectrum Astro Inc.

Should offer communication in V-band in 2002. Would be composed of 5 GEO satellites, each providing coverage through 48 spot beams, 8 regional beams and 2 steerable beams. The system uses inter satellite links.

Subject to FCC approval

Contact

http://www.spectrumastro.com/


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 Astérix

Also called A1

General

Designation	01778 / 65096A
Launch date	26 Nov 1965 at 14:47 UT
Country of origin	France
Mission	Scientific
Perigee/Apogee	527/1797 km
Inclination	64.3°
Period	107.5 min
Launch vehicle	Diamant #1
Mass at launch	42 kg

First launch of a French satellite by a French launcher; makes France the 3rd space power.

It's antenna was damaged during launch thus the technological capsule didn't provide any data. The only payload was a radio transmitter.

End of life

Out of service	26 Nov 1965
Cause	Never transmited


 Program: Astra

Direct Broadcasting System that covers western Europe. Operated by SES, a company founded in March 1985 by 11 shareholders. Based at the Betzdorff castle in Luxemburg.

The first hotbird position of the program was 19.2°E  Another position at 28.8°E will be started in 1997 with the Astra 2 generation.

Technical data

Analog Modulation

Bandwidth	26 MHz
Video excursion	16 MHz/v
Mono bandwidth	180 KHz
Mono de-emphasis	50 µs
Stereo bandwidth	130 KHz
Stereo de-emphasis	75 µs
Stereo expansion	Panda 1


Program: Astra

Astra 1A

Astra 1B

Astra 1C

Astra 1D

Astra 1E

Astra 1F

Astra 1G

Astra 1H

Astra 1K

Astra 2A

Astra 2B

Astra 2C

Astra 2D


 Astra 1A

General

Designation	19688 / 88109B
Launch date	11 Dec 1988
Country of origin	Luxemburg
Mission	Direct TV
Geostationary orbit	19.2°E
Launch vehicle	Ariane V27

TV programs started on 5 Feb 1989. In 1994 a few transponders were taken over by Astra 1C because of technical problems.

Astra 1A will probably be used for satellite news gathering duties from 1998 onwards (after Astra 1H is in position), being placed in an inclined orbit, and moved to either 24.3, 26, or 28.2 degrees East. ("What Satellite TV")

Technical data

EIRP coverage (dBW)

Horizontal polarization mode 1

Horizontal polarization mode 2

Vertical polarization mode 1

Vertical polarization mode 2

Specifications

Prime contractor	GE Astro Space
Platform	GE 4000
Mass at launch	1800 kg
Payload mass	230 kg: transponders: 184 kg, antennas: 46 kg
Dimension	2.9 x 1.6 x 1 m
Solar array	19.3 m span
Stabilization	3-axis
DC power	BOL: equinox: 2236 W, solstice: 2057 W
Payload power	1674.4 W
Design lifetime	10 years
Beacon	11.20300 GHz vertical 11.44650 GHz horizontal
Ku-band (11.2-11.45 GHz)

Main transponders	16
Backup transponders	6
Power	45 W
Bandwidth	26 MHz
Coverage	Europe
EIRP max	50 dBW
Polarization	linear
Uplink	14.25-14.5 GHz
Transponder frequency chart (GHz)

Horizontal Downlink	Beam	Channel	Vertical Downlink
11.21425	H1	1
	V2	2	11.22900
11.24375	H2	3
	V1	4	11.25850
11.27325	H1	5
	V2	6	11.28800
11.30275	H2	7
	V1	8	11.31750
11.33225	H1	9
	V2	10	11.34700
11.36175	H2	11
	V1	12	11.37650
11.39125	H1	13
	V2	14	11.40600
11.42075	H2	15
	V1	16	11.43550


Astra 1A's EIRP (H polarization mode 1)


Astra 1A's EIRP (H polarization mode 2)


Astra 1A's EIRP (V polarization mode 1)


Astra 1A's EIRP (V polarization mode 2)


 Astra 1B

General

Designation	21139 / 91015A
Launch date	2 Mar 1991
Country of origin	Luxemburg
Mission	Direct TV
Geostationary orbit	19.2°E
Launch vehicle	Ariane V42
Technical data

EIRP coverage (dBW)

Horizontal polarization mode 1

Horizontal polarization mode 2

Vertical polarization mode 1

Vertical polarization mode 2

Specifications

Prime contractor	GE Astro Space
Platform	GE 5000
Mass at launch	2580 kg
Mass in orbit	1562 kg
Payload mass	354 kg: transponders: 308 kg, antennas: 46 kg
Dimension	2.2 x 2.9 x 2.3 m
Solar array	21.5 m span
Stabilization	3-axis
DC power	BOL: equinox: 2790 W, solstice: 2567 W
Payload power	2136 W
Design lifetime	10 years
Beacon	11.45350 GHz vertical 11.69650 GHz horizontal
Ku-band (11.45-11.7 GHz)

Main transponders	16
Backup transponders	6
Power	60 W
Bandwidth	26 MHz
Coverage	Europe
EIRP max	52.5 dBW
Polarization	linear
Uplink	14.0-14.25 GHz
Transponder frequency chart (GHz)

Horizontal Downlink	Beam	Channel	Vertical Downlink
11.46425	H1	17
	V2	18	11.47900
11.49375	H2	19
	V1	20	11.50850
11.52325	H1	21
	V2	22	11.53800
11.55275	H2	23
	V1	24	11.56750
11.58225	H1	25
	V2	26	11.59700
11.61175	H2	27
	V1	28	11.62650
11.64125	H1	29
	V2	30	11.65600
11.67075	H2	31
	V1	32	11.68550


Astra 1B's EIRP (H polarization mode 1)


Astra 1B's EIRP (H polarization mode 2)


Astra 1B's EIRP (V polarization mode 1)


Astra 1B's EIRP (V polarization mode 2)


 Astra 1C

General

Designation	22653 / 93031A
Launch date	12 May 1993
Country of origin	Luxemburg
Mission	Direct TV
Geostationary orbit	19.2°E
Launch vehicle	Ariane V56

Tests were carried out in 14.5°E slot.

Technical data

EIRP coverage (dBW)

Horizontal polarization mode 1

Horizontal polarization mode 2

Vertical polarization mode 1

Vertical polarization mode 2

Specifications

Prime contractor	Hughes
Platform	HS-601
Mass at launch	2700 kg
Dimension	2.3 x 2.5 x 2.5 m
Stabilization	3-axis
DC power	BOL: 3500 W
Design lifetime	14 years
Beacon	11.44850 vertical 11.45100 horizontal
Ku-band (10.9-11.2 GHz)

Main transponders	18
Backup transponders	6
Power	63 W
Bandwidth	27 MHz
Coverage	Europe
EIRP max	52.5 dBW
Polarization	linear
Uplink	13.0-13.25 GHz

Backup for Astra 1A

Transponder frequency chart (GHz)

Horizontal Downlink	Beam	Channel	Vertical Downlink
10.96425	H1	33
	V2	34	10.97900
10.99375	H2	35
	V1	36	11.00850
11.02325	H1	37
	V2	38	11.03800
11.05275	H2	39
	V1	40	11.06750
11.08225	H1	41
	V2	42	11.09700
11.11175	H2	43
	V1	44	11.12650
11.14125	H1	45
	V2	46	11.15600
11.17075	H2	47
	V1	48	11.18550
10.92075	H2	63
	V1	64	10.93550


Astra 1C's EIRP (H polarization mode 1)


Astra 1C's EIRP (H polarization mode 2)


Astra 1C's EIRP (V polarization mode 1)


Astra 1C's EIRP (V polarization mode 2)


 Astra 1D

General

Designation	23331 / 94070A
Launch date	1 Nov 1994
Country of origin	Luxemburg
Mission	Direct TV
Geostationary orbit	see below
Launch vehicle	Ariane V69
Location

Begin	End	Position
L: 1 Nov 1994	Feb 1998	19.2°E
Mar 1998	Oct 1998	28.2°E
Nov 1998		19.2°E

To enable the move from 19.2°E to 28.2°E, all services of the satellite were moved to Astra 1E & Astra 1G.

Technical data

EIRP coverage (dBW)

Horizontal polarization mode 1

Horizontal polarization mode 2

Vertical polarization mode 1

Vertical polarization mode 2

Specifications

Prime contractor	Hughes
Platform	HS-601
Mass at launch	2924 kg
Dimension	2.3 x 2.5 x 2.5 m
Solar array	21 m span
Stabilization	3-axis
DC power	BOL: 3500 W
Design lifetime	13 years
Beacon	11.44750 vertical 11.45200 horizontal

Launched with the PVA (Perigee Velocity Augmentation) technic: initial parameters were 199.4/31123 km.

Ku-band (10.7-10.95 GHz)

Main transponders	14
Backup transponders	6?
Power	63 W
Bandwidth	26 MHz
Coverage	Europe
EIRP max	52 dBW
Polarization	linear
Uplink	12.75-13.0 GHz
Ku-band (11.7-12.1 GHz), Astra 1E backup

Main transponders	4
Backup transponders	18
Power	63 W
Bandwidth	33 MHz
Coverage	Europe
EIRP max	52 dBW
Polarization	linear
Uplink	17.3-17.7 GHz

+ Backup for Astra 1B & 1C

Transponder frequency chart (GHz)

Horizontal Downlink	Beam	Channel	Vertical Downlink
10.74125	H1	49
	V2	50	10.72900
10.74375	H2	51
	V1	52	10.75850
10.77325	H1	53
	V2	54	10.78800
10.80275	H2	55
	V1	56	10.81750
10.83225	H1	57
	V2	58	10.84700
10.86175	H2	59
	V1	60	10.87650
10.89125	H1	61
	V2	62	10.90600
10.92075	H2	63
	V1	64	10.93550
11.71950	H2	65
	V2	66	11.73900
11.75850	H1	67
	V1	68	11.77800


Astra 1D's EIRP (H polarization mode 1)


Astra 1D's EIRP (H polarization mode 2)


Astra 1D's EIRP (V polarization mode 1)


Astra 1D's EIRP (V polarization mode 2)


 Astra 1E

General

Designation	23686 / 95055A
Launch date	19 Oct 1995
Country of origin	Luxemburg
Mission	Direct TV
Geostationary orbit	19.2°E
Launch vehicle	Ariane V79

Cost (launch, satellite and insurance): $320 million

Technical data

EIRP coverage (dBW)

Horizontal polarization mode 1

Horizontal polarization mode 2

Vertical polarization mode 1

Vertical polarization mode 2

Specifications

Prime contractor	Hughes
Platform	HS-601
Mass at launch	3000 kg
Dimension	4.5 x 3.4 x 2.8 m
Solar array	26.2 m span
Stabilization	3-axis
DC power	BOL: 5500 W EOL: 4700 W
Design lifetime	14 years
Beacon	11.20200 GHz vertical 10.94850 GHz horizontal
Ku-band (11.7-12.1 GHz)

Main transponders	18
Backup transponders	6
Power	85 W
Bandwidth	33 MHz
Coverage	Europe
EIRP max	52 dBW
Polarization	linear
Uplink	17.3-17.7 GHz

+ backup for Astra 1B, 1C & 1D

Transponder frequency chart (GHz)

Horizontal Downlink	Beam	Channel	Vertical Downlink
11.71950	H1	65
	V2	66	11.73900
11.75850	H2	67
	V1	68	11.77800
11.79750	H1	69
	V2	70	11.81700
11.83650	H2	71
	V1	72	11.85600
11.87550	H1	73
	V2	74	11.89500
11.91450	H2	75
	V1	76	11.93400
11.95350	H1	77
	V2	78	11.97300
11.99250	H2	79
	V1	80	12.01200
12.03150	H1	81
	V2	82	12.05100


Astra 1E's EIRP (H polarization mode 1)


Astra 1E's EIRP (H polarization mode 2)


Astra 1E's EIRP (V polarization mode 1)


Astra 1E's EIRP (V polarization mode 2)


 Astra 1F

General

Designation	23842 / 96021A
Launch date	8 Apr 1996
Country of origin	Luxemburg
Mission	Direct TV
Geostationary orbit	19.2°E
Launch vehicle	Proton #241

Launch cost: $60 million

Technical data

EIRP coverage (dBW)

Horizontal polarization mode 1

Horizontal polarization mode 2

Vertical polarization mode 1

Vertical polarization mode 2

Specifications

Prime contractor	Hughes
Platform	HS-601
Mass at launch	3010 kg
Mass in orbit	1800 kg
Dimension	2.3 x 2.5 x 2.5 m
Solar array	26 m span
Stabilization	3-axis
DC power	BOL: 4700 W
Design lifetime	13 years
Beacon	11.20100 vertical 10.94650 horizontal
Ku-band (12.1-12.5 GHz)

Main transponders	20 or 22?
Backup transponders	8
Power	82 W
Bandwidth	33 MHz
Coverage	Europe
EIRP max	52 dBW
Polarization	linear
Uplink	17.7-18.1 GHz

+ backup for Astra 1A & 1E

Transponder frequency chart (GHz)

Horizontal Downlink	Beam	Channel	Vertical Downlink
12.07050	H2	83
	V1	84	12.09000
12.10950	H1	85
	V2	86	12.12900
12.14850	H2	87
	V1	88	12.16800
12.18750	H1	89
	V2	90	12.20700
12.22650	H2	91
	V1	92	12.24600
12.26550	H1	93
	V2	94	12.28500
12.30450	H2	95
	V1	96	12.32400
12.34350	H1	97
	V2	98	12.36300
12.38250	H2	99
	V1	100	12.40200
12.42150	H1	101
	V2	102	12.44100
12.46050	H2	103
	V1	104	12.48000


Astra 1F's EIRP (H polarization mode 1)


Astra 1F's EIRP (H polarization mode 2)


Astra 1F's EIRP (V polarization mode 1)


Astra 1F's EIRP (V polarization mode 2)


 Astra 1G

General

Designation	25071 / 97076A
Launch date	2 Dec 1997
Country of origin	Luxemburg
Mission	Direct TV
Geostationary orbit	19.2°E
Launch vehicle	Proton #254
Technical data

EIRP coverage (dBW)

Astra 1G

Specifications

Prime contractor	Hughes
Platform	HS-601HP
Mass at launch	3379 kg
Mass in orbit	2485 kg
Dimensions
Solar array	gallium arsenide
Stabilization	3-axis
DC power	8000 W
Design lifetime	15 years
Beacon

Uses a new aerial design consisting of 2 ultra lightweight reflectors using Hughes' proprietary Contured Surface Technonlogy. Instead of conventional chemical rocket motors, Astra 1G incorporates a Xenon ion-drive for high power and reduced launch weight. But for security both standard and Xenon propulsion was installed.

Ku-band (12.5-12.75 GHz)

Main transponders	16
Backup transponders
Power	98.5 W (TWTA)
Bandwidth	26 MHz
Coverage	Europe
EIRP max	52 dBW
Polarization
Uplink	?
Ku-band, backup for Astra 1E or 1F

Main transponders	18 for 1E or 22 for 1F
Backup transponders
Power	98.5 W (TWTA)
Bandwidth	33 MHz
Coverage	Europe
EIRP max	52 dBW
Polarization
Frequencies	downlink: 11.7-12.1 GHz for Astra 1E, 12.1-12.5 GHz for Astra 1F uplink: 17.3-18.1 GHz
Transponder frequency chart (GHz)

Horizontal Downlink	Beam	Channel	Vertical Downlink
12.515	H	105
	V	106	12.522
12.545	H	107
	V	108	12.552
12.574	H	109
	V	110	12.581
12.604	H	111
	V	112	12.610
12.633	H	113
	V	114	12.640
12.663	H	115
	V	116	12.670
12.692	H	117
	V	118	12.699
12.722	H	119
	V	120	12.728


Astra 1G's EIRP


 Astra 1H

General

Designation	25785 / 99032A
Launch date	18 Jun 1999
Country of origin	Luxemburg
Mission	Direct TV
Geostationary orbit	19.2°E
Launch vehicle	Proton #267

Tested at 22°E

Technical data

EIRP coverage (dBW)

Astra 1H

Specifications

Prime contractor	Hughes
Platform	HS-601HP
Mass at launch	3690 kg
Mass in orbit
Length
Width
Height
Solar array	gallium arsenide
Stabilization	3-axis
DC power	8000 W
Design lifetime	15 years

XIPS propulsion

Ku-band (backup for Astra 1E, 1F or 1G)

Main transponders	28 (30 for the first 5 years)
Backup transponders
Power	98.5 W (TWTA)
Bandwidth	26 MHz in FSS, 33 MHZ in BSS
Coverage
EIRP max	51 dBW
Polarization
Frequencies	downlink: 11.7-12.1 GHz for Astra 1E, 12.1-12.5 GHz for Astra 1F, 12.5-12.75 GHz for Astra 1G uplink ?
Ka-band

Main transponders	2
Backup transponders
Power
Bandwidth
Coverage
EIRP max
Polarization

Nortel will provide the ground systems and satellite terminals. The terminals will feature 60 to 120 cm antennas and transmit at speeds from 150 kbps to 2 Mbps.

8 active upload channels.


Astra 1H's EIRP


 Astra 1K

General

Designation
Launch date	late 2000
Country of origin	Luxemburg
Mission	Direct TV
Geostationary orbit	19.2°E
Launch vehicle	Ariane 5
Launch site

Astra's mega satellite to replace all Astra 1A to 1D. Will provide increased coverage in Eastern Europe and the CIS. It will also implement ARCS (Astra Return Channel System); this uses Ka-band to receive signals from satellite uplink systems on homes and businesses. The hardware needed on the client end is a simple as a 30 cm dish and a cheap transmitter.

Technical data

EIRP coverage (dBW)

Mission 1

Mission 2

Specifications

Prime contractor	Aerospatiale
Platform	Spacebus-3000B3S
Mass at launch	4450 kg
Mass in orbit
Dimensions
Solar array
Stabilization	3-axis
DC power	13000 W
Design lifetime	13 years

9 antenna reflectors. The Ka-band antenna is provided by Spar Aerospace, it will cover major European cities.

Ku-band

Main transponders	52 (46 after 5 years)
Backup transponders	7
Power	105 W (TWTA)
Bandwidth	26 MHz
Coverage & max EIRP	Mission 1: replacement & backup for Ku-low-band: 52 dBW Mission 2: Continental Europe & UK: 53.5 dBW
G/T max
Polarization
Ka-band

Main transponders	2
Backup transponders
Power	66 W (TWTA)
Bandwidth	500 MHz
Coverage	multiple spot beams (16 beams)
EIRP max	55 dBW
G/T max
Polarization


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Astra 1K's mission 1 EIRP


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Astra 1K's mission 2 EIRP


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 Astra 2A

General

Designation	25462 / 98050A
Launch date	30 Aug 1998 at 00:31 UT
Country of origin	Luxemburg
Mission	Direct TV
Geostationary orbit	28.2°E
Launch vehicle	Proton

Half of the capacity (14 transponders) has been booked by BskyB.

The launched was originally booked with Ariane but due to technical problems with the satellite's bipropellant apogee motor the Proton launcher is more suitable (direct GEO injection). The Ariane contract is not cancelled and will be used for another satellite.

Technical data

EIRP coverage (dBW)

Northern beam

Southern beam

Specifications

Prime contractor	Hughes
Platform	HS-601HP
Mass at launch	3300 kg
Mass in orbit
Dimension
Solar array
Stabilization	3-axis
DC power	7000 W
Design lifetime	15 years

For security both standard and Xenon propulsion (XIPS) was installed.

It has been tested at 27°E.

Ku-band (11.7-12.5 GHz)

Main transponders	28 (32 for the first 5 years)
Backup transponders
Power	100 W
Bandwidth	26 MHz in FSS, 33 MHz in BSS
Coverage
EIRP max	52 dBW
Polarization
Transponder frequency chart (GHz)

Horizontal Downlink	Beam	Channel	Vertical Downlink
11.720	S1	1
	S2	2	11.740
11.758	N1	3
	N2	4	11.778
11.798	S1	5
	S2	6	11.817
11.837	N1	7
	N2	8	11.856
11.876	S1	9
	S2	10	11.895
11.914	N1	11
	N2	12	11.934
11.954	S1	13
	S2	14	11.973
11.992	N1	15
	N2	16	12.012
12.032	S1	17
	S2	18	12.051
12.070	N1	19
	N2	20	12.090
12.110	S1	21
	S2	22	12.129
12.148	N1	23
	N2	24	12.168
12.188	S1	25
	S2	26	12.207
12.226	N1	27
	N2	28	12.246
12.266	S1	29
	S2	30	12.285
12.304	N1	31
	N2	32	12.324
12.344	S1	33
	S2	34	12.363
12.382	N1	35
	N2	36	12.402
12.422	S1	37
	S2	38	12.441
12.460	N1	39
	N2	40	12.480
N1 stands for North 1 or A, N2 stands for North 2 or B, S1 stands for South 1, etc.


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Astra 2A's Northern EIRP


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Astra 2A's Southern EIRP


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 Astra 2B

General

Designation
Launch date	late 1998
Country of origin	Luxemburg
Mission	Direct TV
Geostationary orbit	28.2°E
Launch vehicle	Ariane
Launch site
Technical data

Specifications

Prime contractor	Matra Marconi Space
Platform	Eurostar 2000 plus
Mass at launch	3300 kg
Mass in orbit
Dimension
Solar array
Stabilization	3-axis
DC power
Design lifetime	15 years
Ku-band (11.7-12.5 GHz)

Main transponders	28 (30 for the first 5 years)
Backup transponders
Power	108 W
Bandwidth	26 MHz in FSS, 33 MHz in BSS
Coverage
EIRP max	52 dBW
Polarization
Ku-band (12.5-12.75 GHz)

Main transponders	16
Backup transponders
Power
Bandwidth
Coverage	mobile beam
EIRP max
Polarization


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 Astra 2C

General

Designation
Launch date	planned in 2001
Country of origin	Luxemburg
Mission	Direct TV
Geostationary orbit	28.2°E
Launch vehicle	Proton
Technical data

Specifications

Prime contractor	Hughes
Platform	HS-601HP
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization	3-axis
DC power
Design lifetime	15 years

The satellite is compatible with the 19.2°E system (could serve there as backup)

Ku-band (10.7-11.2 GHz)

Main transponders	32
Backup transponders
Power
Bandwidth
Coverage
EIRP max
Polarization
Ku-band (11.7-12.2 GHz)

Main transponders	24
Backup transponders
Power
Bandwidth
Coverage
EIRP max
Polarization


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 Astra 2D

General

Designation
Launch date	planned in late 2000
Country of origin	Luxemburg
Mission	Direct TV
Geostationary orbit	28.2°E
Launch vehicle	Ariane
Technical data

Specifications

Prime contractor	Hughes
Platform	HS-376HP
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization	spin stabilized
DC power
Design lifetime	12 years
Ku-band (10.7-10.95 GHz)

Main transponders	16 (EOL: 15)
Backup transponders
Power
Bandwidth
Coverage	UK and Eire
EIRP max
Polarization


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 Astrid 1

General

Designation	23464 / 95002B
Launch date	24 Jan 1995 at 03:54 UT
Country of origin	Sweden
Operator	Swedish Space Corporation
Mission	Scientific: ionosphere and magnetosphere study
Perigee/Apogee	968/1023 km
Inclination	82.9°
Period	105 min
Launch vehicle	Cosmos 3M
Launch site	Plesetsk LC132

The satellite will initially be controlled from Swedish Space Corporation's ground station at ESRANGE in Kiruna in Northern Sweden. Thereafter control will be taken from Esrange, by the Swedish Institute of Space Physics in Kiruna.

The payload, which will emphasize studies of energetic neutral particles in the Earth's magnetosphere, includes PIPPI, the neutral particle imager; MIO, the miniature UV imaging system (with optical, UV continuum and Lyman alpha monitors) and EMIL, an electron spectrometer.

External resources

http://www.ssc.se/ssd/msat/astrid.html

End of life

Out of service	Mar 1995
Cause	short circuit
Decay
Technical data

Specifications

Prime contractor	Platform: Swedish Space Corporation's Science Systems Division in Solna Payload: Swedish Institute of Space Physics in Kiruna
Platform	Freja C
Mass at launch	28 kg
Mass in orbit
Length	0.45 m
Width	0.45 m
Height	0.4 m
Solar array	4 wings, silicon
Stabilization	spin stabilized
DC power	28 V +-4v
Design lifetime	3 months
UHF-band (400.55 MHz)

Main transponders	1
Backup transponders	0
Power	2 W
Bandwidth	50 kHz
Coverage	omnidirectional
EIRP max	-12-0 dB
Polarization	RHCP
Data flow	8 kbps
S-band (2208.629 MHz)

Main transponders	1
Backup transponders	0
Power	2 W
Bandwidth	890 kHz
Coverage	omnidirectional
EIRP max	-6- 2 dB
Polarization	RHCP
Data flow	128 kbps


 Astrid 2

General

Designation	25568 / 98072B
Launch date	10 Dec 1998
Country of origin	Sweden
Operator	Swedish Space Corporation
Mission	Scientific: ionosphere and magnetosphere study
Perigee/Apogee	977 / 1013 km
Inclination	82.9°
Period	105 min
Launch vehicle	Cosmos C

The satellites were named after Astrid Lindgren, world-famous Swedish writer for children, the author of numerous fairy tales.

External resources

http://www.ssc.se/ssd/msat/astrid2.html

Technical data

Specifications

Prime contractor
Platform
Mass at launch	27 kg
Payload mass	10 kg
Dimensions	1.10 m x 1.70 m x 0.30 m
Solar array	4 wings, silicon
Stabilization	spin stabilized
DC power	90 W
Design lifetime	2 years
Scientific payload

EMMA (Electrical and Magnetic field Monitoring of the Aurora)

LINDA (Langmuir INterferometer and Density experiment for Astrid-2)

MEDUSA (Miniaturized Electrostatic DUal-tophat Spherical Analyzer)

PIA (Photometers for Imaging the Aurora)

S-band (2208.1629 MHz)

Main transponders	1
Backup transponders
Power
Bandwidth
Coverage	omnidirectional
EIRP max
Data flow	128 kbps


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 Program: Astro

Astronomy Japanese program

External resources

http://www.astro.isas.ac.jp/


Program: Astro

Astro A

Astro B

Astro C

Astro D

Astro E


 Astro A

Also called Hinotori

General

Designation	12307 / 81017A
Launch date	21 Feb 1981
Country of origin	Japan
Mission	Scientific: Sun study
Perigee/Apogee	573/639 km
Inclination	31.3°
Period	96.7 min
Launch vehicle	Mu 3S1
Launch site	Kagoshima
Mass at launch	195 kg
End of life

Decay	11 Jul 1991


 Astro B

Also called Tenma

General

Designation	13829 / 83011A
Launch date	20 Feb 1983
Country of origin	Japan
Mission	Scientific: X-ray astronomy
Perigee/Apogee	431/438 km
Inclination	31.5°
Period	93.3 min
Launch vehicle	Mu 3S1
Launch site	Tanegashima
Mass at launch	220 kg
End of life

Decay	17 Dec 1988


 Astro C

Also called Ginga

General

Designation	17480 / 87012A
Launch date	5 Feb 1987
Country of origin	Japan
Mission	Scientific: X-ray astronomy
Perigee/Apogee	395/450 km
Inclination	31°
Period	93 min
Launch vehicle	Mu 3S 2
Launch site	Kagoshima
Mass at launch	420 kg
External resources

http://www.astro.isas.ac.jp/xray/mission/ginga/gingaE.html

End of life

Decay	1 Nov 1991


 Astro D

Also called Asuka or ASCA (Advanced Satellite for Cosmology and Astrophysics)

General

Designation	22521 / 93011A
Launch date	20 Feb 1993 at 02:00 UT
Country of origin	Japan
Operator	ISAS
Mission	Scientific: X-ray astronomy
Perigee/Apogee	538/645 km
Inclination	31.1°
Period	96.5 min
Launch vehicle	Mu 3S 2
Launch site	Kagoshima
Mass at launch	420 kg

First truly telescopic telecope in space and first Japanese X-ray imaging telescope (its previous X-ray satellites have carried x-ray detectors without focussing optics).

External resources

http://www.astro.isas.ac.jp/xray/mission/asca/ascaE.html

http://nssdca.gsfc.nasa.gov/asca/asca.html

Technical data

Specifications

Prime contractor	Nagoya's university and the Goddard Space Flight Center
Platform
Mass at launch	420 kg
Mass in orbit
Dimension	1.2 m diameter x 2.8 m long (4 m deployed)
Solar array
Stabilization
DC power	BOL: 600 W
Design lifetime	2 + 2 years

Is equipped with 4 focal mirrors of 3.5 m and CCD detectors. The sensitiveness should be 100 times greater than HEAO 2. It carries CCD detectors and an imaging proportional counter. The spacecraft is sensitive to the 0.5-12 keV energy range. The Asuka telescope has a 30 arcmin field of view and 2 arcmin spatial resolution.

Telemetry: 2256.22 MHz (playback: 262144 bps, via DSN)


 Astro E

initially planned to be launched in 1999 by Mu-5

External resources

http://www.astro.isas.ac.jp/xray/mission/astroe/astroeE.html

http://lheawww.gsfc.nasa.gov/docs/xray/astroe/astroe.html


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 Program: Astrolink

Astrolink is a Lockheed Martin telecommunication program, based on Ka-band. It was partially approved by FCC in May 1997 and got final approval in May 1999. LMGT owns 46% of the company, with Telespazio and TRW both 27%. $900 million were provided to start the company. Total cost of the program: $3.6 billion

9 GEO interconnected satellites are planned. Should be ready in 2003. 4 satellites have been ordered in 1999 for a start.

Lockheed proposes to offer services such as global Internet service, videoconferencing, distance learning, telemedicine, high-speed data networks and "bandwidth on demand."

External resources

http://www.astrolink.com

Technical data

2 satellites per slots at 97°W, 21.5°W, 38°E & 130°E

later 1 satellite at 175.25°E

User terminals: 65 to 120 cm in diameter

Fixed gateway terminals: 3 m

Satellite to regional gateway links: 155 mbps

Satellite to user links: from 16 kbps to 9.6 mbps (depending on user requirements and dish sizes: the larger the dish, the faster the data rate)

The standard low-cost terminal will enable transmission speeds from 16 kpbs to 384 kbps

Specifications

Prime contractor	Lockheed Martin
Platform	A2100
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime	15 years

TRW will provide the payload while Telespazio will setup the ground stations.

Ka-band

Main transponders	68
Backup transponders
Power
Bandwidth	64 x 125 MHz (user terminal) 4 x 250 MHz (gateway terminal)
Coverage	multiple spot beam
EIRP max
Polarization	linear H/V
Frequencies	Uplink: 28.35-28.6 and 29.25-29.5 GHz Downlink: 19.7-20.2 GHz

On-board processing

A Time Division Multiplexed (TDM)/Frequency Division Multiple Access (FDMA) scheme is to be used on the user terminal uplinks.  On user terminal downlinks, a 130 Mbps TDM signal will be transmitted in each beam from each satellite.


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 Asusat 1

General

Designation
Launch date	initially planned in mid 1998
Country of origin	United States
Mission
Perigee/Apogee
Inclination
Period
Launch vehicle	Taurus
Launch site	Vandenberg

Designed by Arizona State University

It is equipped with 2 digital cameras for tracking changes to Earth's coasts and forests. Has a HAM payload

External resources

http://www.eas.asu.edu/~nasasg/asusat/main_asusat.html

Technical data

Frequency chart (MHz)

Uplink: 145.990 MHz FM

Downlink: 436.700 MHz FM


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 Program: ATS

Application Technology Satellite

American multipurpose satellites designed to test new space instruments and demonstrate new satellite technologies.

External resources

http://www.met.fsu.edu/explores/Guide/Ats_Html/


Program: ATS

ATS 1

ATS 3

ATS 5

ATS 6


 ATS 1

General

Designation	02608 / 66110A
Launch date	7 Dec 1966
Country of origin	United States
Mission	Meteorology and communication experimentation
Geostationary orbit	149°W
Launch vehicle	Atlas Agena D

Transmitted the first high resolution photos of the Earth. It also relayed color television across the U.S. and was the first satellite to permit two-way VHF communication between ground and aircraft in flight.

End of life

Out of service	yes
Technical data

Transmits on 137.35 MHz (weak signal)


 ATS 3

General

Designation	03029 / 67111A
Launch date	5 Nov 1967
Country of origin	United States
Mission	Meteorology experimentation
Geostationary orbit	see below
Launch vehicle	Atlas Agena D
Launch site	Cape Canaveral

Carried advanced communications, meteorology, and navigation experiments. Provided the first color pictures of the Earth and proved the interest of maritime communications via satellite. Transmitted the first space communication between an Earth station and a plane on 21 Nov 1967 above the Atlantic.

Since 1980 the satellite transmit data to and from Antartica, especially the Internet.

Location

Begin	End	Position
L: 5 Nov 1967		47°W
Jun 1988	...	105°W
Oldest satellite still station keeping

Technical data

Transponder frequency chart (MHz)

Uplink	Channel	Downlink
149.175	1	135.555
149.195	2	135.575
149.220	3	135.600
149.245	4	135.625
149.265	5	135.645


 ATS 5

General

Designation	04068 / 69069A
Launch date	12 Aug 1969
Country of origin	United States
Mission	Telecommunications experimentation
Geostationary orbit
Launch vehicle
Launch site	Cape Canaveral

Provided data on auroran phenomenons and propagation in ionosphere.

End of life

Out of service	yes


 ATS 6

General

Designation	07318 / 74039A
Launch date	30 May 1974
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	95°W
Launch vehicle	Titan 3 #78
Mass at launch	930 kg

Numerous telecommunications experiments were carried out. With the satellite's 9 m antenna only small Earth antennas were needed. Scholar TV was provided to american children in the Rockies and Alaska. It was also used by SITE (Satellite Instructional Television Experiment) in 1975 to try and solve educational problems of India (half success). It also enabled communications between 2 unmanned spacecrafts.

External resources

http://sulu.lerc.nasa.gov/dglover/ats6.html

http://uss-enterprise.bu.edu/BUSPACE/ATS6/ats6.html

End of life

Out of service	30 Jun 1979


 Aura

Also called D2B

General

Designation	08332 / 75092A
Launch date	27 Sep 1975
Country of origin	France
Mission	Scientific: astronomy
Perigee/Apogee	476/697 km
Inclination	37.1°
Period	96.5 min
Launch vehicle	Diamant #12
Mass at launch	120 kg

Built by Matra.

End of life

Out of service	28 Dec 1976
Cause	Stopped transmitting
Decay	30 Sep 1982


 Program: Auréole

Also called Oreol

French scientific program


Program: Auréole

Auréole 1

Auréole 2

Auréole 3


 Auréole 1

General

Designation	05729 / 71119A
Launch date	27 Dec 1971
Country of origin	France
Mission	Scientific: ionosphere study
Perigee/Apogee	388/1954 km
Inclination	74°
Period	108.8 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Auréole 2

General

Designation	07003 / 73107A
Launch date	26 Dec 1973
Country of origin	France
Mission	Scientific: ionosphere study
Perigee/Apogee	387/1441 km
Inclination	74°
Period	103.3 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Auréole 3

General

Designation	12848 / 81093A
Launch date	21 Sep 1981
Country of origin	France
Mission	Scientific: ionosphere and magnetosphere study
Perigee/Apogee	394/1672 km
Inclination	82.5°
Period	105.8 min
Launch vehicle	Cyclone 3


 Program: Aurora

Telecommunication program operated by Alascom.

Aurora 2 is partly operated with GE Americom


Program: Aurora

Aurora 1

Aurora 2


Aurora's specifications

Prime contractor	GE Astro Space
Platform	GE 3000
Mass in orbit	760 kg
Dimension	1.63 x 1.32 x 0.99 m
Stabilization	3-axis
DC power	BOL: 1400 W
Design lifetime	1: 10 years 2: 12 years


Aurora_1
 Aurora 1

Also called Satcom 5

General

Designation	13631 / 82105A
Launch date	28 Oct 1982
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Thor Delta #165
Mass at launch	1084 kg
Location

Begin	End	Position
L: 28 Oct 1982		139°W
1992?		143°W
Feb 1995	...	105°W
Technical data

Specifications

C-band

Main transponders	24
Backup transponders	4
Power	8.5 W (SSPA)
Bandwidth	36 MHz
Coverage
EIRP max	34 dBW
Polarization	linear


 Aurora 2

Also called Satcom C5

General

Designation	21392 / 91037A
Launch date	29 May 1991
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	139°W
Launch vehicle	Delta 2 #205
Mass at launch	1338 kg
Technical data

EIRP coverage (dBW)

Specifications

C-band transponder frequency chart

C-band

Main transponders	24
Backup transponders	8
Power	11 W (SSPA)
Bandwidth	36 MHz
Coverage	Odd transponders to the United States Even transponders to Alaska and Canada
EIRP max	34 dBW
Polarization	linear


Aurora 2's EIRP map


 Program: Ayame

Means "iris", also called ECS (Experimental Communication Satellite)

Japanese telecommunication program


Program: Ayame

Ayame 1

Ayame 2


 Ayame 1

Also called ECS 1

General

Designation	11261 / 79009A
Launch date	6 Feb 1979
Country of origin	Japan
Mission	Telecommunications, experimental
Perigee/Apogee	29259/37424 km
Inclination	4.9°
Period	1313 min
Launch vehicle	N1
Mass at launch	130 kg
End of life

Out of service	Collided with the top stage


 Ayame 2

General

Designation	11715 / 80018A
Launch date	22 Feb 1980
Country of origin	Japan
Mission	Telecommunications, experimental
Perigee/Apogee	32785/36839 km
Inclination	1.4°
Period	1386.6 min
Launch vehicle	N1
Mass at launch	130 kg
End of life

Out of service	After launch?


 Azur

Also called GRS A

General

Designation	04221 / 69097A
Launch date	8 Nov 1969
Country of origin	Germany
Mission	Scientific: ionosphere study
Perigee/Apogee	373/2118 km
Inclination	102.7°
Period	110.4 min
Launch vehicle	Scout #67
Mass at launch	72 kg

Studies aurora borealis, Earth's radiation belt and charged particles from the Sun.


 Badr A

General

Designation	20685 / 90059A
Launch date	16 Jul 1990
Country of origin	Pakistan
Mission
Perigee/Apogee	208/988 km
Inclination	28.5°
Period	96.7 min
Launch vehicle	Long March 2
Launch site	Xichang

Experimental digital communications satellite

End of life

Out of service	21 Aug 1990
Cause	failure of onboard systems
Decay	8 Dec 1990
Technical data

Specifications

Prime contractor	SSTL
Platform
Mass at launch	52 kg
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime


 Badr B

General

Designation
Launch date	initially planned in 1998
Country of origin	Pakistan
Mission	Scientific:
Perigee/Apogee
Inclination
Period
Launch vehicle	Zenit
Launch site

Should weigh 70 kg. It will measure solar radiation and will collect information about Pakistan's natural resources.

has a CCD camera (250 m x 250 m resolution)

External resources

http://www.ssd.rl.ac.uk/news/cdrom/eo/badr.htm

Technical data

Specifications

Prime contractor	Suparco (Space and Upper Atmosphere Research Commission)
Platform
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime	2 years

Downlink in UHF-, VHF- and S-band.


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 Program: Bhaskara

Indian program named from a Indian mathematician and astronomer.


Program: Bhaskara

Bhaskara 1

Bhaskara 2


 Bhaskara 1

General

Designation	11392 / 79051A
Launch date	7 Jun 1979
Country of origin	India
Mission	Remote sensing
Perigee/Apogee	394/399 km
Inclination	50.7°
Period	92.5 min
Launch vehicle	Cosmos C
Launch site	Kapustin Yar
Mass at launch	444 kg

Carried two TV cameras, one in visible and the other in near-infrared band, and a 3-frequency passive microwave radiometer. The cameras malfunctioned.

End of life

Decay	17 Feb 1989


 Bhaskara 2

General

Designation	12968 / 81115A
Launch date	20 Nov 1981
Country of origin	India
Mission	Remote sensing
Perigee/Apogee	541/557 km
Inclination	50.6°
Period	92 min
Launch vehicle	Cosmos C
Launch site	Kapustin Yar
Mass at launch	436 kg

Carried two TV cameras, one in visible and the other in near-infrared band, and a 3-frequency passive microwave radiometer.

End of life

Decay	30 Nov 1991


 Program: Bimilsatcom

Was Trimilsatcom

Project for 1 military telecommunication satellite shared by France and Germany. In late 1998 the UK decided not to join.

After this is was decided France would built alone a satellite to be launched in 2003 and a German-French satellite in 2007. The French satellite might not have EHF payload.

The system would have 2 GEO satellites at 37°W and 67°E plus a ground backup.

The system would have replaced UK's Skynet and France's Syracuse's payload on Telecom.


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 Bonum 1

Also called Most 1

General

Designation	25546 / 98068A
Launch date	22 Nov 1998
Country of origin	Russia
Mission	Telecommunications
Geostationary orbit	36°E
Launch vehicle	Delta 2 #263

Bonum is a subsidiary of Media Most, a major private Russian media group. They already operate pay TV from Gals 1, Gals 2 and TDF 2.

The contract calls for in-orbit delivery together with the control center and training of the staff.

Contact

Media Most

16 Kazakova Street, Moscow 103064 Russia

Tel: +7-95-261-1342

Fax: +7-95-263-2753

Email: bonum1@dol.ru

Technical data

EIRP coverage (dBW)

Specifications

Prime contractor	Hughes
Platform	HS-376HP
Mass at launch	1450 kg
Dry mass	630 kg
Dimension
Solar array
Stabilization	spin stabilized
DC power	1500 W
Design lifetime	11 years
Ku-band

Main transponders	8
Backup transponders
Power	75 W
Bandwidth
Coverage	Western Russia
EIRP max
G/T max
Polarization	circular
Frequencies	uplink: 14.0-14.5 GHz downlink: 11.7-12.2 GHz


Bonum 1's EIRP coverage


 Program: Brasilsat

Also called SBTS (Sistema Brasileiro de Telecomunicacoes por Satellite)

Brasilian telecommunication system operated by Embratel.

Contract for Brasilsat As was worth $122.5 million for construction. Contract for Brasilsat Bs was worth $175.2 million for construction.


Program: Brasilsat

Brasilsat A1

Brasilsat A2

Brasilsat B1

Brasilsat B2

Brasilsat B3

Brasilsat B4


Brasilsat A's specifications

Prime contractor	Spar Aerospace
Platform	HS-376
Mass at launch	1140 kg
Mass in orbit	671 kg
Diameter	2.19 m
Height	7.09 m deployed
Stabilization	Spin stabilized
DC power	BOL: 982 W EOL: 799 W
Design lifetime	1: 9 years 2: 11 years


Brasilsat A's C-band

Main transponders	26
Backup transponders	6
Power	10 W (TWTA)
Bandwidth	36 MHz
Coverage	Brasil and neighboring countries
EIRP max	36 dBW
Polarization	linear


Brasilsat B's specifications

Prime contractor	Hughes
Platform	HS-376W
Mass at launch	1760 kg
Mass in orbit	1052 kg
Dry mass	850 kg
Diameter	3.64 m
Height	3.64 m, 8.38 m deployed
Stabilization	spin stabilized
DC power	BOL: 1650 W
Design lifetime	12 years
Apogee motor	Thiokol Star 30 (solid fuel)


Brasilsat B's X-band

Main transponders	1
Backup transponders
Power	40 W (TWTA)
Bandwidth
Coverage
EIRP max
Polarization


 Brasilsat A1

Also called SBTS A1

General

Designation	15561 / 85015B
Launch date	8 Feb 1985
Country of origin	Brasil
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V12
Location

Begin	End	Position
L: 8 Feb 1985		65°W
late-1994	mid-Jun 1996	63°W, inclined
mid-Jul 1996	Aug 1998	79°W, inclined
Jan 1999		144°W, inclined

Sold to HCI in October 1995. The antenna was re-aimed to North America. The control of the satellite was passed to Panamsat on 12 Nov 1997.

Technical data

Specifications

C-band

Transponder frequency chart


 Brasilsat A2

Also called SBTS A2

General

Designation	16650 / 86026B
Launch date	28 Mar 1986
Country of origin	Brasil
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V17
Location

Begin	End	Position
L: 28 Mar 1986		70°W
late-1994	Jun 1995	65°W
Aug 1995		92°W
Technical data

Specifications

C-band

Transponder Frequency Chart


 Brasilsat B1

Also called SBTS B1

General

Designation	23199 / 94049A
Launch date	10 Aug 1994
Country of origin	Brasil
Mission	Telecommunications
Geostationary orbit	70°W
Launch vehicle	Ariane V66

Cost: $140 million

Technical data

EIRP coverage (dBW)

Brasil: National

Brasil: Regional & Argentina

Specifications

X-band

C-band

Main transponders	28
Backup transponders
Power	15 W
Bandwidth	31 MHz
Coverage	Brasil
EIRP max	38 dBW
G/T max	-2.5 dB/K
Polarization	linear H/V

Beacon: 4.1985 - 4.1990 GHz horizontal

Transponder frequency chart (GHz)

Horizontal Uplink	Horizontal Downlink	Channel	Vertical Downlink	Vertical Uplink	Beam
	3.6415	1AE		5.8665
5.885		1BE	3.660
	3.680	2AE		5.905
5.925		2BE	3.700
	3.720	1A		5.945
5.965		1B	3.740
	3.760	2A		5.985
6.005		2B	3.780
	3.800	3A		6.025
6.045		3B	3.820
	3.840	4A		6.065
6.085		4B	3.860
	3.880	5A		6.105
6.125		5B	3.900
	3.920	6A		6.145
6.125		6B	3.940
	3.960	7A		6.185
6.205		7B	3.980
	4.000	8A		6.225
6.245		8B	4.020
	4.040	9A		6.265
6.285		9B	4.060
	4.080	10A		6.305
6.325		10B	4.100
	4.120	11A		6.345
6.365		11B	4.140
	4.160	12A		6.385
6.405		12B	4.180


Brasilsat B's C-band National EIRP


Brasilsat B's C-band Regional EIRP


 Brasilsat B2

Also called SBTS B2

General

Designation	23536 / 95016A
Launch date	28 Mar 1995
Country of origin	Brasil
Mission	Telecommunications
Geostationary orbit	65°W
Launch vehicle	Ariane V71

Cost: $125 million

Should move to 84°W

Technical data

Specifications

X-band

EIRP coverage (dBW)

Brasil: National

Brasil: Regional & Argentina

Brasil: National combined

Brasil: Regional combined

C-band

Main transponders	28
Backup transponders
Power	15 W
Bandwidth	31 MHz
Coverage	Brasil: National Brasil: Regional Argentina National combined Regional combined
EIRP max	38 dBW
G/T max	-2.5 dB/K
Polarization	linear H/V

Beacon: 4.1990 - 4.1995 GHz horizontal

Transponder frequency chart (GHz)

Horizontal Uplink	Horizontal Downlink	Channel	Vertical Downlink	Vertical Uplink	Beam
	3.6415	1AE		5.8665	National, Regional, Regional combined
5.885		1BE	3.660		National, Regional
	3.680	2AE		5.905	National, Regional
5.925		2BE	3.700		National, Regional
	3.720	1A		5.945	National, Argentina, National combined
5.965		1B	3.740		National
	3.760	2A		5.985	National, Argentina, National combined
6.005		2B	3.780		National
	3.800	3A		6.025	National, Argentina, National combined
6.045		3B	3.820		National
	3.840	4A		6.065	National, Argentina, National combined
6.085		4B	3.860		National
	3.880	5A		6.105	National, Argentina, National combined
6.125		5B	3.900		National
	3.920	6A		6.145	National, Argentina, National combined
6.125		6B	3.940		National
	3.960	7A		6.185	National, Argentina, National combined
6.205		7B	3.980		National
	4.000	8A		6.225	National, Argentina, National combined
6.245		8B	4.020		National
	4.040	9A		6.265	National, Argentina, National combined
6.285		9B	4.060		National
	4.080	10A		6.305	National, Argentina, National combined
6.325		10B	4.100		National
	4.120	11A		6.345	National, Argentina, National combined
6.365		11B	4.140		National
	4.160	12A		6.385	National, Argentina, National combined
6.405		12B	4.180		National


Brasilsat B2's National C-band EIRP


Brasilsat B2's Argentina & Regional C-band EIRP


Brasilsat B2's National combined C-band EIRP


Brasilsat B2's Regional combined C-band EIRP


 Brasilsat B3

Also called SBTS B3

General

Designation	25152 / 98006A
Launch date	4 Feb 1998
Country of origin	Brasil
Mission	Telecommunications
Geostationary orbit	65°W
Launch vehicle	Ariane V105
Location

Begin	End	Position
L: 4 Feb 1998	Apr 1998	65°W
late May 1998		84°W

Cost: $70 million agreement (without launch?) This is an amendment to the Brasilsat B contract with Hughes signed in 1990, which gave EMBRATEL options for additional spacecraft.

Technical data

Specifications

EIRP coverage (dBW)

Brasil: National

Brasil: Regional & Argentina

C-band

Main transponders	28
Backup transponders
Power	18 W
Bandwidth	31 MHz
Coverage	Brasil: National Brasil: Regional
EIRP max	38 dBW
G/T max	-2.5 dB/K
Polarization	linear H/V

No X-band payload: the C-band only spacecraft will provide nearly 20 percent higher signal power than the 2 Brasilsat B's. It will have one C-band beam for national service, and a second C-band regional beam that will focus higher power on the major urban areas.


 Brasilsat B4

Also called SBTS B4

General

Designation
Launch date	initially planned in 2000
Country of origin	Brasil
Mission	Telecommunications
Geostationary orbit	92°W
Launch vehicle	Ariane

C-band only

Will replace Brasilsat A2

Technical data

Specifications

Prime contractor	Hughes
Platform	HS-376W
Mass at launch	1750 kg
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime	12 years
C-band

Main transponders	28
Backup transponders
Power
Bandwidth
Coverage
EIRP max
G/T max
Polarization


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 Bremsat

General

Designation	22998 / 94006H
Launch date	3 Feb 1994
Country of origin	Germany
Operator	ZARM, University of Bremen
Mission	Scientific: high atmosphere study
Perigee/Apogee	344/363 km
Inclination	56.9°
Period	91.4 min
Launch vehicle	STS 60
Mass at launch	63 kg

Measured heat conductivity, micrometeorites, and the density of the upper atmosphere.

External resources

http://www.zarm.uni-bremen.de/2forschung/raumfahrt/bremsat.html

End of life

Decay	12 Feb 1995


 Program: Bsat

Also called BS 4, Broadcast Satellite 4

Japanese telecommunication program to replace the Yuri program. Bsat (Broadcasting Satellite System Corp.) is a consortium of major Japanese broadcasters including NHK and the WOWOW group and provides direct broadcast services throughout Japan.

Contact

Broadcasting Satellite System Corporation

Parkside-Yamamotokan 2F, 1-16-4, Tomigaya, Shibuya-ku

Tokyo 151 JAPAN

Tel: +81-3-5453-6521

Fax: +81-3-5453-6524


Program: Bsat

Bsat 1A

Bsat 1B

Bsat 2A


Bsat's specifications

Prime contractor	Hughes
Platform	HS-376
Mass at launch	1230 kg
Mass in orbit	708 kg
Dry mass	500 kg
Dimension	2.17 m diameter x 3.15 m stowed (7.82 m deployed)
Solar array
Stabilization	spin stabilized
DC power	BOL: 1064 W
Design lifetime	12 years

Commands are received at 17 GHz, telemetry in the 12 GHz band.


Bsat's Ku-band

Main transponders	4
Backup transponders	4
Power	106 W (TWTA)
Bandwidth	27 MHz
Coverage	Japan only
EIRP max
Polarization	circular
Frequencies	Uplink: 14.2-14.3 GHz Downlink: 11.9-12.0 GHz


 Bsat 1A

General

Designation	24769 / 97016B
Launch date	16 Apr 1997
Country of origin	Japan
Mission	Telecommunications
Geostationary orbit	110°E
Launch vehicle	Ariane V95

Estimated Cost: $150 million (satellite, launch and insurance)

Test position: 122°E

Technical data

Specifications

Ku-band


 Bsat 1B

General

Designation	25312 / 98024B
Launch date	28 Apr 1998
Country of origin	Japan
Mission	Telecommunications
Geostationary orbit	110°E
Launch vehicle	Ariane V108

Estimated Cost: $150 million (satellite, launch and insurance)

Tested from 122°E

Technical data

Specifications

Ku-band


 Bsat 2A

General

Designation
Launch date	fall 2000
Country of origin	Japan
Mission	Telecommunications
Geostationary orbit	110°E
Launch vehicle	Ariane

Bsat 2B is also included in the same contract. This contract (with OSC) includes satellites and launches (in-orbit delivery).

Technical data

Specifications

Prime contractor	OSC
Platform	Novastar
Mass at launch
Dry mass	550 kg
Dimension
Solar array
Stabilization	3-axis
DC power	2000 W
Design lifetime	12 years

Communication payload provided by SS/L

Ku-band transponders


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 Program: BSB

English direct TV program abandonned in 1992. The satellites were ordered by BSB which merged with Sky TV giving BSkyB.


Program: BSB

BSB 1

BSB 2


BSB's specifications

Prime contractor	Hughes
Platform	HS-376
Mass at launch	1250 kg
Mass in orbit	660 kg
Payload mass	100 kg: transponders: 90 kg, antennas: 10 kg
Diameter	2.16 m
Height	4.8 m
Stabilization	Spin stabilized
DC power	BOL: 1024 W
Design lifetime	10 years
Beacon	12.494 or 12.495 GHz

Equipped with steerable antennas


BSB's Ku-band

Main transponders	5
Backup transponders	1
Power	2 x 55 W (TWTA)
Bandwidth	27 MHz
Coverage
EIRP max	59 dBW
Polarization	circular R
Frequencies	Uplink: 17.3-17.6 GHz Downlink: 11.786-12.091 GHz


 BSB 1

Also called Marco Polo 1

General

Designation	20193 / 89067A
Launch date	27 Aug 1989
Country of origin	United Kingdom
Mission	Direct TV
Geostationary orbit	see below
Launch vehicle	Thor Delta #187

Stopped transmitting on 31 Dec 1992 and became Sirius 1 in 1994.

Location

Begin	End	Position
L: 27 Aug 1989
Nov 1991	Dec 1992	31°W
1994	...	Sirius 1
Technical data

Specifications

Ku-band


 BSB 2

Also called Marco Polo 2

General

Designation	20762 / 90074A
Launch date	18 Aug 1990
Country of origin	United Kingdom
Mission	Direct TV
Geostationary orbit	see below
Launch vehicle	Delta 2 #198

Was sold in September 1992 and became Thor 1.

Location

Begin	End	Position
L: 18 Aug 1990
	Aug 1992	31°W
Sep 1992	...	Thor 1
Technical data

Specifications

Ku-band


 Cakrawarta 1

On September 1997, the Indonesian President renamed the satellite.

It was previously called Indostar 1

General

Designation	25050 / 97071B
Launch date	12 Nov 1997
Country of origin	Indonesia
Operator	PT Media Citra Indostar
Mission	DBS
Geostationary orbit	107.7°E
Launch vehicle	Ariane V102

Up to 4 small satellites have been ordered: Indostar 2 at 115°E and Indostar 3 at 106°E  (or all four satellite colocated at 107.5 and 119°E) The full project (satellite, launch, ground station, etc) is worth $175 million

Originally designed for TV and DAB, the satellite was modified to provide only TV capacity in S-band (this band was selected to face high attenuation caused by the rain).

A power regulator failed resulting in only 80% of eclipse power available.

Technical data

Specifications

Prime contractor	CTA Inc (now OSC)
Platform	STARbus
Mass at launch	1385 kg
Mass in orbit	802 kg
Dry mass	643 kg
Dimension
Solar array
Stabilization	spin stabilized
DC power	3200 W
Design lifetime	10 years
S-band (2520-2670 GHz)

Main transponders	5
Backup transponders
Power	70 W
Bandwidth	27 MHz
Coverage	Indonesia
EIRP max	47 dBW
Polarization
Frequencies	2.520-2.670 GHz

Uplink is in X-band (this is the first commercial use of X-band)


 Castor

Also called D5B

General

Designation	07802 / 75039B
Launch date	17 May 1975
Country of origin	France
Mission	Scientific: geodesy
Perigee/Apogee	277/1275 km
Inclination	29.9°
Period	100.3 min
Launch vehicle	Diamant #11
Mass at launch	76 kg

Tested a high precision micro-acceleratometer named Cactus.

It is the counterpart of the first Castor that was lost with Pollux on 22 May 1973.

End of life

Decay	18 Feb 1979


 Caribstar

Also called CariBSS and Ameristar

General

Designation
Launch date	initially planned in mid-1999
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	120°W
Launch vehicle	Ariane
Technical data

Specifications

L-band


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 Program: Cat

European micro satellite program for experimentation


Program: Cat

Cat 1

Cat 2

Cat 3

Cat 4


 Cat 1

General

Designation	11645 / 79104A
Launch date	24 Dec 1979
Country of origin	Europe
Mission	Technology experimentation
Perigee/Apogee	125/14047 km
Inclination	17.8°
Period	259.1 min
Launch vehicle	Ariane L01
End of life

Decay	27 Nov 1989


 Cat 2

End of life

Out of service	23 May 1980
Cause	Launch failure of Ariane L02


 Cat 3

General

Designation	12546 / 81057C
Launch date	19 Jun 1981
Country of origin	Europe
Mission	Technology experimentation
Perigee/Apogee	227/29240 km
Inclination	10.6°
Period	508.8 min
Launch vehicle	Ariane L03
End of life

Out of service	96 hours after launch


 Cat 4

Also called Thésée

General

Designation	13011 / 81122B
Launch date	20 Dec 1981
Country of origin	Europe
Mission	Scientific
Perigee/Apogee	219/38645 km
Inclination	63.8°
Period	534.3 min
Launch vehicle	Ariane L04

Measures the Sun light

End of life

Out of service	9 Jan 1982
Cause	Stopped transmitting


 Program: CBERS

China/Brazil Earth Resources Satellite

Joint venture to launch 2 satellites for remote monitoring of the environment related to agriculture, oceanography and geology. The Brazilian government has suggested to China that another two 1400-kilogram satellites should be developed.

The two satellites will be assembled in China with parts manufactured in both countries and Brazil will invest 60 million dollars, covering 30% of the costs of the project. The two countries started manufacturing the two satellites in 1988 but the project was delayed by a budget shortfall on the Brazilian side (satellites were planned for 1994 & 1995). As of Apr 1999 the total prograom cost is estimated at $400 million.

The Brazilian Ministry of the Environment will use the two new satellites in the Amazon Integrated Program, created to develop the Amazon region based on sustained development policies.

2 follow-on satellites are also planned

External resources

http://www.dgi.inpe.br/html/eng/cbers.htm


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 CBERS 1

General

Designation
Launch date	initially planned in Oct 1997
Country of origin	Brazil
Mission	Remote sensing
Perigee/Apogee	heliosynchronous orbit, 778 km
Inclination
Period	repeat period: 20 days
Launch vehicle	Long March
Launch site
Technical data

Specifications

Prime contractor	CASC/INPE
Platform
Mass at launch	1400 kg
Mass in orbit
Dimension	1.8 x 1.9 m
Solar array	8.3 x 3.3 m
Stabilization	3-axis
DC power
Design lifetime
5-channel linear CCD detector (visible, IR, panchromatic)

Wavebands	0.59-0.89 µm 0.5-12.9 µm
Swath width	120 km
Resolution	Visible: 19 m IR: 80 m
Wide-field imager

Resolution	260 m
Swath width	900 km


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 Program: Celestis

US private program to launch ashes into space (space burial).

Contact

Tel: +1-800-6724811

External resources

http://www.celestis.com/


Program: Celestis

Celestis 1

Celestis 2


 Celestis 1

General

Designation	24780 / 97018B
Launch date	4 Apr 1997
Country of origin	United States
Mission	Burial
Perigee/Apogee	554 / 582 km
Inclination	151° (inclination record)
Period	96.1 min
Launch vehicle	Pegasus #17
Launch site	Canary Islands

Set of 24 capsules containing the ashes of 24 people


 Celestis 2

General

Designation	25160 / 98007D
Launch date	10 Feb 1998
Country of origin	United States
Mission	Burial
Perigee/Apogee	777 / 875 km
Inclination	108°
Period
Launch vehicle	Taurus #2

The Celestis Payload Attach Container (CPAC) was attached to Taurus' top stage.


 Cerise

General

Designation	23606 / 95033B
Launch date	7 Jul 1995
Country of origin	France
Mission	Military: ELINT
Perigee/Apogee	666/675 km
Inclination	98.2°
Period	98.2 min
Launch vehicle	Ariane V75

Operated by CNES and the DGA (Délégation Générale de l'Armement), ministry of defense. Cerise is to catalog terrestrial electromagnetic sources between 500 MHz and 20 GHz. Cost: $17.4 million.

It will be followed by Clementine to be launched in 1997 to catalog source between 20 MHz and 1 GHz. (should cost $18 million).

On 24th July 1996 the satellite was hit by a fragment of the Ariane which launched Spot 1 Part of the stabilization system was destroyed

Technical data

Specifications

Prime contractor	Alcatel Espace & Thomson CSF
Platform	UoSAT
Mass at launch	50 kg
Mass in orbit
Length
Width
Height
Stabilization	3-axis
DC power
Design lifetime	2.5 years


 Cesasat

This satellite was reportedly order by the Czech company Cesa as a small DBS satellite.

In June 1999 it was rumored to be bought or leased by Eutelsat and transformed for other purposes.

Project worth $160 million (in-orbit delivery + ground station at Pardubice)

Technical data

Specifications

Prime contractor	Alenia Aerospazio
Platform
Mass at launch	1850 kg
Mass in orbit
Dimension
Solar array
Stabilization	3-axis
DC power	3000 W
Design lifetime	12 years
Ku-band

Main transponders	18
Backup transponders	6
Power
Bandwidth	6 x 72 MHz 12 x 32 MHz
Coverage	central europe, from baltic countries to Greece, from Austria to Ukraine
EIRP max	50 dBW
G/T max
Polarization


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 Champ

Challenging Mini-Satellite Payload for Geophysical Research and Application

General

Designation
Launch date	initially planned in 1999
Country of origin	Germany
Mission	Scientific
Perigee/Apogee	500 km
Inclination
Period
Launch vehicle	Cosmos C
Launch site

6 instruments

External resources

http://www.gfz-potsdam.de/pb1/CHAMP/champ.htm

Technical data

Specifications

Prime contractor	GFZ Postdam
Platform
Mass at launch	300 kg
Payload mass	25 kg
Dimension
Solar array
Stabilization
DC power
Design lifetime


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 Chandra

Advanced X-ray Astrophysics Facility (AXAF), renamed Chandra X-ray Observatory, as the nickname of Subrahmanyan Chandrasekhar, a nobel price holder which studied evolution of stars.

General

Designation	25867 / 99040B
Launch date	23 Jul 1999
Country of origin	United States
Operator	NASA
Mission	Scientific: X-ray astronomy
Perigee/Apogee	10000/140000 km
Inclination	28.5°
Period	64 hours
Launch vehicle	STS 93 with IUS-27

Designed to observe X-rays from high energy regions of the universe, such as hot gas in the remnants of exploded stars.

The launch was delayed several time, including in Jan 1999 when TRW reported conductivity problems on multi-layered circuit boards.

External resources

http://xrtpub.harvard.edu/pub.html

http://asc.harvard.edu/

Technical data

Specifications

Prime contractor	TRW
Platform
Mass at launch	5200 kg
Mass in orbit
Dimension	15 m deployed
Solar array	9 m span
Stabilization
DC power
Design lifetime

10 m focal length telescope

ACIS: camera with 10 X-ray CCD imagers based on Astro D technology

HRC: camera similar to Rosat technology


 Chinastar 1

Also called Zhongwei 1

General

Designation	25354 / 98033A
Launch date	30 May 1998
Country of origin	China
Operator	COTS
Mission	Telecommunications
Geostationary orbit	87.5°E
Launch vehicle	Long March 3B
External resources

http://www.chinastar.com.cn/english/english.html

Technical data

EIRP coverage (dBW)

C-band

Ku-band

G/T coverage (dB/K)

C-band

Ku-band

Specifications

Prime contractor	Lockheed Martin
Platform	A2100
Mass at launch	2984 kg
Mass in orbit
Dry mass	1418 kg
Dimension	1.8 x 2.0 x 2.8 m
Solar array
Stabilization	3-axis
DC power	BOL: 8394 W EOL: 6797 W
Design lifetime	15 years
C-band

Main transponders	12 + 6
Backup transponders	6
Power	45 W
Bandwidth	12 x 36 MHz 6 x 72 MHz
Coverage
G/T max	1 dB/K
EIRP max	41 dBW
Polarization	linear H/V

Beacon frequency: 3.7005 GHz (V) and 4.1995 GHz (H)

C-band Transponder frequency chart (GHz)

Horizontal Uplink	Horizontal Downlink	Transponder	Vertical Downlink	Vertical Uplink
	3.720	1A		5.945
5.955		1B	3.740
	3.760	2A		5.985
6.005		2B	3.780
	3.800	3A		6.025
6.045		3B	3.820
	3.840	4A		6.065
6.085		4B	3.860
	3.880	5A		6.105
6.125		5B	3.900
	3.920	6A		6.145
6.165		6B	3.940
	3.980	7A		6.205
6.775		7B	4.000
	4.060	8A		6.285
6.805		8B	4.080
	4.140	9A		6.365
6.855		9B	4.160
Ku-band

Main transponders	16 + 4
Backup transponders	10
Power	85 W at 36 MHz  115 W at 72 MHz
Bandwidth	16 x 36 MHz 4 x 72 MHz
Coverage	China
G/T max	5 dB/K
EIRP max	52 dBW at 36 MHz 54 dBW at 72 MHz
Polarization	linear H/V

Beacon frequency: 12.2505 GHz (V) and 12.7495 GHz (H)

Ku-band Transponder frequency chart (GHz)

Horizontal Uplink	Horizontal Downlink	Transponder	Vertical Downlink	Vertical Uplink
	12.290	10A		14.038
14.058		10B	12.310
	12.370	11A		14.118
14.138		11B	12.390
	12.430	12A		14.178
14.198		12B	12.450
	12.470	13A		14.218
14.238		13B	12.490
	12.510	14A		14.258
14.278		14B	12.530
	12.550	15A		14.298
14.318		15B	12.570
	12.590	16A		14.338
14.358		16B	12.510
	12.630	17A		14.378
14.398		17B	12.550
	12.670	18A		14.418
14.438		18B	12.690
	12.710	19A		14.458
14.478		19B	12.730


Chinastar 1's C-band EIRP coverage


Chinastar 1's Ku-band EIRP coverage


Chinastar 1's C-band G/T coverage


Chinastar 1's Ku-band G/T coverage


 Cloudsat

General

Designation
Launch date	Mar 2003
Country of origin	United States
Operator	NASA (Langley)
Mission
Perigee/Apogee
Inclination
Period
Launch vehicle
Launch site

Part of the ESSP (Earth System Science Pathfinder) program. Should cost $135 million

CloudSat would use advanced cloud-profiling radar to provide information on the vertical structure of highly dynamic tropical cloud systems. This new radar would enable measurements of cloud properties for the first time on a global basis, revolutionizing our understanding of cloud-related issues.

With Colorado State University

Prime contractor: Ball Aerospace


 Program: Cluster

European scientific program. The 4 satellites composing it were lost on Ariane 5's maiden flight.

General

Designation	n/a
Launch date	4 Jun 1996
Country of origin	Europe
Mission	Scientific: Sun study
Launch vehicle	Ariane V88

The total cost was evaluated at 2.9 billion francs.

External resources

http://www.esoc.esa.de/external/mso/cluster.html

http://cdhf3.bnsc.rl.ac.uk:8080/cluster.html

Technical data

Specifications

Prime contractor	Dornier
Platform
Mass at launch	1200 kg
Payload mass	72 kg
Propellant mass	650 kg
Dry mass	550 kg
Diameter	2.9 m
Height	1.3 m
Solar array
Stabilization	spin stabilized (15 rpm)
DC power	EOL: 224 W (80 Ah silver cadmium batteries)
Payload power	47 W
Design lifetime	2 years
Telemetry	2-262 kbps

Tape recorder capacity: 1 gbit  The final orbit was to be 25000/140000 km

Frequencies

Cluster 1	2242.000 MHz
Cluster 2	2249.000 MHz
Cluster 3	2277.000 MHz
Cluster 4	2270.000 MHz
Payload

STAFF ( Spatio-Temporal Analysis of Field Fluctuations)

EFW (Electric Fields and Waves)

WHISPER (Waves of High frequency and Sounder for probing of density by Relaxation)

WBD (Wide Band Data)

DWP (Digital Wave Processor)

FGM (Fluxgate Magnetometer)

EDI (Electronic Drift Instrument)

CIS (Cluster Ion Spectrometry)

PEACE (Plasma Electron And Current Analyser)

RAPID (Research with Adaptive Particle Imaging Detectors)

ASPOC (Active Spacecraft Potential Control)


 Program: Cluster 2

Following the loss of the Cluster satellites with Ariane 501 a remplacement could be financed.

This replacement will be composed of the Phenix satellite made from spare instruments of the first set and 3 new satellites to be built by Dornier. The satellites will be launched by pairs aboard Soyouz rockets.

The program should be completed in mid-2000. It will cost about $265 million

External resources

http://sci.esa.int/cluster/


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 Cobe

COsmic Background Explorer

General

Designation	20322 / 89089A
Launch date	18 Nov 1989
Country of origin	United States
Mission	Scientific: astronomy
Perigee/Apogee	872/886 km
Inclination	99°
Period	102.5 min
Launch vehicle	Thor Delta #189

Studies the thermical radiation of the sky (gave its precise temperature: 2.735 K).

External resources

http://www.gsfc.nasa.gov/astro/cobe/cobe_home.html

http://spectrum.lbl.gov/www/cobe/cobe.html


 Program: Columbia

Program operated by Columbia Communications Corporation  This company already operates the commercial C-band on the first generation TDRS satellites.

Program of GEO telecommunication satellites to be launched in 2000

The FCC granted on 11 Jan 1999 the contruction and launch of a C-band satellite at 47°W and a C- & Ku-band satellite at 172°E


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Program: Columbia

Columbia AOR

Columbia POR

Columbia TDRS 4

Columbia TDRS 5

Columbia TDRS 6

Columbia 515


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 Columbia AOR

General

Designation
Launch date	2000
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	47°W
Launch vehicle
Launch site
Technical data

EIRP coverage (dBW)

Specifications

Prime contractor
Platform
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime
C-band

Main transponders	44
Backup transponders
Power
Bandwidth	32 x 54 MHz 12 x 92 MHz
Coverage & EIRP max	West Atlantic: 42 dBW East Atlantic: 44 dBW Steerable: 43 dBW
G/T max
Polarization
Frequencies	uplink: 5.925-6.725 GHz downlink: 3.4-42 GHz

Beam overlap with Columbia POR in Southern California


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Columbia AOR's EIRP


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 Columbia POR

General

Designation
Launch date	2000
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	172°E
Launch vehicle
Launch site
Technical data

EIRP coverage (dBW)

C-band

Ku-band

Specifications

Prime contractor
Platform
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime
C-band

Main transponders	36
Backup transponders
Power
Bandwidth	32 x 72 MHz 12 x 92 MHz
Coverage & EIRP max	Oceania: 45 dBW Asia: 45 dBW Steerable: 46 dBW
G/T max
Polarization
Ku-band

Main transponders	24
Backup transponders
Power
Bandwidth	72 MHz
Coverage & EIRP max	Western USA & Hawaii: 56 dBW Australasia: 54 dBW Philippines: 56 dBW South-East Asia: 57 dBW Indo-China: 56 dBW North-East Asia: 56 dBW Steerable: 58 dBW
G/T max
Polarization

Beam overlaps with Columbia AOR in Southern California


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Columbia POR's C-band EIRP


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Columbia POR's Ku-band EIRP


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 Comets

Communications and Broadcasting Engineering Test Satellite, also called Kakehashi (means bridge)

General

Designation	25175 / 98011A
Launch date	21 Feb 1998
Country of origin	Japan
Mission	Telecommunications
Geostationary orbit	n/a (121°E initially planned)
Launch vehicle	H2 #6

Was to demonstrate inter-orbit links and Ka-band transmissions and mobile K-band transmissions (onboard relay). Cost: $36 million

Early shutdown of the second stage left the satellite in low orbit (44 seconds out of the 192 seconds planned). The apogee motor should be used to higher the orbit and enable a few experiments on a 500/17700 km orbit)

In Jan 1999 communications and broadcasting experiments ended. The satellite was damaged by going through the Van Allen belt. It will now be used for signal attenuation measurements and radiation influence.

Technical data

Specifications

Prime contractor
Platform	derived from ETS 6
Mass at launch	3900 kg
Mass in orbit	2000 kg
Dimension	2 x 3 x 3 m
Solar array	15 m span
Stabilization	3-axis
DC power	EOL: 5300 W
Design lifetime	3 years

Is equipped with ETS 6's apogee motor. Has 4 Xenon thrusters

Suffered an electrical overcharge before launch.

Ka-band

Main transponders	5
Backup transponders	1
Power	200 W
Bandwidth
Coverage	Japan only
EIRP max
Polarization

+ S-band capacity

+ 1 transponder with uplink at 44 GHz, downlink at 476 GHz

Downlink: 22.696 GHz 20.165 GHz


 Program: Comstar

American telecommunication satellite program operated by Comsat. Capacity was leased to AT&T.


Program: Comstar

Comstar 1

Comstar 2

Comstar 3

Comstar 4


Comstar's specifications

Prime contractor	Hughes
Platform	HS-351 (same as Intelsat 4)
Mass at launch	1516 kg
Mass in orbit	911 kg
Dimension	2.5 m
Stabilization	Spin stabilized (56 rpm)
DC power	BOL: 570 W
Design lifetime	10 years

Equipped with two Ka-band beacons for propagation research (19 and 28.6 GHz).


Comstar's C-band

Main transponders	24
Backup transponders
Power	Horizontal: 5 W (TWTA) Vertical: 5.5 W (TWTA)
Bandwidth	36 MHz
Coverage	CONUS
EIRP max	33 dBW
Polarization	linear H/V


 Comstar 1

General

Designation	08838 / 76042A
Launch date	13 May 1976
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	128°W
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
End of life

Out of service	yes
Technical data

Specifications

C-band


 Comstar 2

General

Designation	09047 / 76073A
Launch date	22 Jul 1976
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	94°W
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
End of life

Out of service	yes
Technical data

Specifications

C-band


 Comstar 3

General

Designation	10975 / 78068A
Launch date	29 Jun 1978
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	87°W
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
End of life

Out of service	yes
Technical data

Specifications

C-band


 Comstar 4

General

Designation	12309 / 81018A
Launch date	21 Feb 1981
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	76°W, inclined
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral

Used for telephony and data transmission, especially to and from ships in U.S. coastal waters and the Caribbean region.

Technical data

Specifications

C-band


 Coronas 1

General

Designation	23019 / 94014A
Launch date	2 Mar 1994 at 03:24 UT
Country of origin	Russia-Ukrain
Mission	Scientific: ionosphere, magnetosphere and Sun study
Operator	RKA space agency (probably by the IKI science institute)
Perigee/Apogee	483/526 km
Inclination	82.5°
Period	94.7 min
Launch vehicle	Cyclone 3 #109

The payload was developed by the IZMIRAN institute (Institute of Terrestrial Magnetism in Moscow) and includes the Terek spectroheliometer, the RES-K solar x-ray spectrograph, the Helikon solar gamma ray detector, the SUVR-SP-C ultraviolet radiometer, the DIFOS optical photometer, and other instruments.

Built by NPO Yuzhnoe, platform: AUOS-SM


 Corsa B

Also called Hakucho

General

Designation	11272 / 79014A
Launch date	21 Feb 1979
Country of origin	Japan
Mission	Scientific: X-ray astronomy
Perigee/Apogee	543/566 km
Inclination	29.8°
Period	95.7 min
Launch vehicle	Mu 3C
Launch site	Kagoshima
Mass at launch	96 kg
External resources

http://heasarc.gsfc.nasa.gov/docs/heasarc/missions/hakucho.html

End of life

Decay	15 Apr 1985


 Cos B

COsmic ray Satellite

General

Designation	08062 / 75072A
Launch date	9 Aug 1975
Country of origin	Europe
Mission	Scientific: gamma-ray astronomy
Perigee/Apogee	442/99002 km
Inclination	90.3°
Period	2203.9 min
Launch vehicle	Thor Delta #113
Mass at launch	280 kg
External resources

http://www.esoc.esa.de/external/mso/cos.html

http://astro.estec.esa.nl/SA-general/Archives/Cosb/cosb.html

http://heasarc.gsfc.nasa.gov/docs/heasarc/missions/cosb.html

End of life

Out of service	25 Apr 1982


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 Coupon 1

General

Designation	25045 / 97070A
Launch date	12 Nov 1997
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	55°E
Launch vehicle	Proton #253

Operated by GIS: Global Information Systems and the Central Bank of Russia.  Was originally to be launched in Oct 1994.

The price of manufacture and launching of this satellite totalled 560 billion roubles.  The insurance is to pay $70 million for the failure

End of life

Out of service	mid-Mar 1998
Cause	the onboard frequency detector caused a computer failure. Other sources claim 2 stabilizers have failed
Technical data

Specifications

Prime contractor	Lavochkin (first commercial comsat made)
Platform	Prognox 2nd generation
Mass at launch	2300 kg
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime

Only 70% of the planned power is effectively operational.

Ku-band

Main transponders	16
Backup transponders
Power
Bandwidth	36 MHz
Coverage	Europe and Asia, several spots
EIRP max	50 dBW
Polarization	linear
Transponder frequency chart (GHz)

Horizontal Downlink	Transponder	Vertical Downlink
10.980
		10.980
11.060
		11.060
11.100
		11.100
11.180
		11.180
11.480
		11.480
11.560
		11.560
11.600
		11.600
11.680
		11.680


 Coupon 2

General

Designation
Launch date	mid-1999
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	55°E
Launch vehicle	Proton

Originally planned for launch in April 1995, slotted in 9.5°W

The atomic standard in the onboard synchronizing device will be discarded.  Its malfunctions were responsible for putting the first satellite out of order. The second satellite will have its productivity doubled as compared with the first satellite, and its service life in orbit will reach 12 years.

Kupon-M bus


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 Coupon 3

Launch initially planned in October 1995 slotted in 162°E


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 Courier 1B

General

Designation	00058 / 60013A
Launch date	4 Oct 1960
Country of origin	United States
Mission	Telecommunications: recording satellite
Perigee/Apogee	967/1214 km
Inclination	28.3°
Period	107.1 min
Launch vehicle	Thor Ablestar
Launch site	Cape Canaveral

Could record messages from Earth station and rebroadcast them.


 CTA

General

Designation	22214 / 92070C
Launch date	22 Oct 1992
Country of origin	Canada
Mission
Perigee/Apogee	164/243 km
Inclination	28.4°
Period	88.4 min
Launch vehicle	STS 52
End of life

Cause	Retrieved by the Shuttle
Decay	1 Nov 1992


 CTS

Also called Hermès

General

Designation	08585 / 76004A
Launch date	17 Jan 1976
Country of origin	Canada
Mission	Telecommunications
Geostationary orbit	116°W
Launch vehicle	Thor Delta #119
Mass at launch	674 kg, 347 kg in orbit

Used by the United States and Canada for TV transmission tests with small Earth stations. Also used for computer links.

External resources

http://sulu.lerc.nasa.gov/dglover/cts.html

End of life

Out of service	November 1979


 Program: Cyberstar

Telecommunication program operated by Loral The CyberStar network proposes to offer services such as video telephony and videoconferencing, medical and technical tele-imaging, high-speed data networks and "bandwidth on demand."  Program worth $1.6 billion

3 satellites operating in Ka-band to be located at: 28°E, 105.5°E, and 115°W. Cost: $1.6 billion

Telstar 5 is used for immediate services until a dedicated satellite can be launched. First satellite to be launched in 1999.

A strategic partnership was drawn with Alcatel's Skybridge

External resources

http://www.cyberstar.com/

Technical data

Specifications

Prime contractor	SS/L
Platform
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime
Ka-band

Main transponders
Backup transponders
Power
Bandwidth
Coverage	27 regional beams
EIRP max
Polarization	RHCP/LHCP
Frequencies	Uplink: 28.35-28.6 and 29.5-30.0 GHz Downlink: 19.7-20.2 GHz

on-board switching

Frequency Division Multiple (FDM)/Time Division Multiplexed (TDM) protocol for uplink and TDM for downlink.

Inter-satellite link at 60 GHz is planned


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 Program: Dash

American program for radars calibration


 David

German & Israeli technology satellite. El-Op (Israel) and OHB System (Germany) are the main partners. Should carry a 12 channel multispectral sensor for 5 m observations. Partially funded by the european community for possible applications in agriculture and ecology.

It should weigh 180 kg. First satellite based on the Prima platform (up to 50 kg payload)

David could be the basis a of future commercial system based on such satellites.


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 Program: DBS

American digital direct TV program operated by HCI.

Two companies provide TV packages: DirecTV, a subsidiary of GM Hughes Electronics, and USSB a division of Hubbard Broadcasting Inc. The receivers were (at the beginning solely) provided by Thomson Consumer Electronics (RCA trademark).

U.S. Satellite Broadcasting has voluntarily returned its authorisation for eight transponders at the 148 degrees West orbital location to the FCC. DirectTV has previously returned the slot located at 157°W.

In Dec 1998 Hughes announced the acquisition of USSB for approx $1.3 billion. The FCC approved this in Apr 1999.

In Apr 1999 Hughes completed the acquisition of Primestar's medium power DBS customers and system (including Tempo 1). A 24-month transition to DBS is planned. A second part of the transaction consist of the first Tempo satellite not yet launched and the 11 frequencies at 119°W; this is still pending FCC approval.

Contact

DirecTv

Tel: +1-818-569-7700

http://www.directv.com

HCI

USSB


Program: DBS

DBS 1

DBS 1R

DBS 2

DBS 3


DBS' specifications

Prime contractor	Hughes
Platform	HS-601S
Mass at launch	2930 kg
Mass in orbit	1700 kg
Dimension	2.27 x 2.27 x 2.27 m
Solar array	35.1 m span
Stabilization	3-axis
DC power	4500 W
Design lifetime	12 years

Transponders are optimized for digital TV: fixed gain and automatic level control.


DBS' Ku-band (12.2-12.7 GHz)

Main transponders	16
Backup transponders	8
Power	120 W (TWTA)
Bandwidth	24 MHz
Coverage	Continental US
EIRP max	52 dBW
Polarization	LHCP

The system can be configured as 8 transponders with 240 W power to provide 2.9 dBW more.

The DSS architecture can broadcast 40Mbits/sec per transponder in either of two error control modes. In High mode, 30Mbps is allocated to information and 10Mbps to error control. In Low mode, 23Mbps is allocated to information and 17Mbps is allocated to error control.


DBS' EIRP

Add 2.9 dBW for transponders with 240 W power.


 DBS 1

General

Designation	22930 / 93078A
Launch date	18 Dec 1993
Country of origin	United States
Mission	Direct TV
Geostationary orbit	101.2°W
Launch vehicle	Ariane V62

One or two control processor failed on-board.

Technical data

EIRP coverage (dBW)

Specifications

Ku-band

Uplink frequency: 17.3-18.8 GHz


 DBS 2

General

Designation	23192 / 94047A
Launch date	3 Aug 1994
Country of origin	United States
Mission	Direct TV
Geostationary orbit	100.8°W
Launch vehicle	Atlas Centaur

It carried a time capsule named SpaceArc containing messages from the vice-president of the U.S.A. (Al-Gore) and his predecessor. After its useful life span the spacecraft will be moved to a higher orbit so that only an explorer from a distant future generation may uncover the messages.

Technical data

EIRP coverage (dBW)

Specifications

Ku-band

Apogee motor: ARC490N (liquid fuel)


 DBS 3

General

Designation	23598 / 95029A
Launch date	10 Jun 1995
Country of origin	United States
Mission	Direct TV
Geostationary orbit	101°W
Launch vehicle	Ariane V74

Will be used for power enforcement

Technical data

EIRP coverage (dBW)

Specifications

Ku-band


 DBS 1R

Also called DTV 1R

General

Designation
Launch date	mid 1999
Country of origin	United States
Mission	Direct TV
Geostationary orbit	101°W
Launch vehicle	Zenit Sea Launch

DBS 1 would then move to 110°W

to be delivered in orbit

Technical data

Specifications

Prime contractor	Hughes
Platform	HS-601HP
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization
DC power	7500 W
Design lifetime
Ku-band

Main transponders	16
Backup transponders
Power
Bandwidth
Coverage
EIRP max
G/T max
Polarization


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 Debut

Also called Orizuru

General

Designation	20479 / 90013B
Launch date	8 Feb 1990
Country of origin	Japan
Mission
Perigee/Apogee	908/1742 km
Inclination	99°
Period	112.2 min
Launch vehicle	H1


 Delta Star

Also called USA 036

General

Designation	19911 / 89026A
Launch date	24 Mar 1989
Country of origin	United States
Mission	Military
Perigee/Apogee	307/312 km
Inclination	47.7°
Period	90.7 min
Launch vehicle	Thor Delta #184

Part of the Star War program. Payload: radar, laser and 7 optical sensors (IR).

End of life

Decay	23 Jun 1992


 Demosat

Sea Launch Demonstration Satellite

General

Designation	25661 / 99014A
Launch date	28 Mar 1999
Country of origin	United States
Mission	Experimental
Perigee/Apogee
Inclination
Period
Launch vehicle	Zenit #31 (first Sea Launch)
Launch site	Sea Launch Odyssey

During pre-launch preparations, the Odyssey (located at 154°W and 0°N) was partially submerged for added stability. The rocket, with payload, then was withdrawn from its hangar on the platform, lifted into a vertical position, fuelled with kerosene and liquid oxygen (LOX), and launched. The fuelling and launch was completely automated and co-ordinated from the Sea Launch Commander.

The first two stages of the Zenit are built by Yuhznoe in the Ukraine. The third stage is a Blok DM-SL, built by Energiya/Kaliningrad and based on the Blok DM series used for Proton upper stages. Its first burn placed it in a 180 x 735 km x 1.2 deg parking orbit 13 min after launch, followed by a second burn 47 min after launch to deliver DemoSat to a 638 x 36064 km x 1.2 deg geostationary transfer orbit. A third DM-SL burn is then expected to lower the orbit for a quick reentry.

The rocket has a specific guidance computer (not the standard Zenit one)

Technical data

Specifications

Prime contractor	Boeing Commercial Space
Platform	HS-702
Mass at launch	4500 kg
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime

Carries 130 sensors. Telemetry relayed in real time directly and by TDRS


 Denpa

Means "radio wave"

General

Designation	06152 / 72064A
Launch date	19 Aug 1972
Country of origin	Japan
Mission	Scientific: ionosphere study
Perigee/Apogee	238/6322 km
Inclination	31°
Period	157.4 min
Launch vehicle	Mu 4S
Launch site	Kagoshima
Mass at launch	75 kg
External resources

http://www.isas.ac.jp/info/sat/denpa-e.html

End of life

Decay	19 May 1980


 Program: DFS Kopernikus

Deutscher Fernmelde Satellit

German telecommunication program operated by DTAG


Program: DFS Kopernikus

DFS 1

DFS 2

DFS 3


DFS Kopernikus's specifications

Prime contractor	R-DFS consortium with ANT and MBB-ERNO
Platform	Spacebus-100
Mass at launch	1415 kg
Mass in orbit	850 kg
Payload mass	158 kg: transponders: 126 kg, antennas: 32 kg
Dimension	1.4 x 1.9 x 4.1 m
Solar array	15.4 m span
Stabilization	3-axis
DC power	BOL: 1990 W EOL: solstice: 1463 W, equinox: 1558 W
Payload power	896 W
Design lifetime	10 years
Capacity	1800 phone circuits and 200 data circuits


DFS Kopernikus's Ku-band

Main transponders	10
Backup transponders
Power	20 W (TWTA)
Bandwidth	3 transponders in 11 GHz: 90 MHz 7 transponders in 12 GHz: 44 MHz
Coverage	Germany
EIRP max	49 dBW
Polarization	linear
Uplink	14.0-14.25 GHz for 11 GHz downlink 14.25-14.5 GHz for 12 GHz downlink


DFS Kopernikus's Ka-band

Main transponders	1
Backup transponders
Power	20 W (TWTA)
Bandwidth	90 MHz
Coverage	Germany
EIRP max	48 dBW
Polarization
Uplink	29.5-29.6 GHz
Downlink	19.7-19.8 GHz


DFS Kopernikus's Transponder frequency chart (GHz)

Horizontal Downlink	Transponder	Vertical Downlink
11.475	A1
11.525	A2
	B1	11.550
	B2	11.600
11.625	C1
11.675	C2
	K1	12.524
12.559	K2
	K3	12.591
12.625	K4
	K5	12.658
12.692	K6
	K7	12.725


 DFS 1

General

Designation	20041 / 89041B
Launch date	5 Jun 1989
Country of origin	Germany
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V31
Location

Begin	End	Position
L: 5 Jun 1989
Jan 1991	Jan 1993	23.5°E
Jul 1993	Nov 1995	33.5°E

Ran out of control a few days in Nov 1995. Control was regained in early December but DFS 1 escaped again in mid-December 1995

End of life

Out of service	Nov 1995
Cause	satellite out of control
Technical data

Specifications

Ku-band

Ka-band

Transponder frequency chart

Beacon: 11.450 GHz vertical & 11.4535 GHz horizontal


 DFS 2

General

Designation	20706 / 90063B
Launch date	24 Jul 1990
Country of origin	Germany
Mission	Telecommunications
Geostationary orbit	28.5°E
Launch vehicle	Ariane V37
Technical data

Specifications

Ku-band

Ka-band

Transponder frequency chart

Beacon: 11.450 GHz vertical & 11.4535 GHz horizontal


 DFS 3

General

Designation	22175 / 92066A
Launch date	12 Oct 1992
Country of origin	Germany
Mission	Telecommunications
Geostationary orbit	23.5°E
Launch vehicle	Delta 2 #215
Technical data

EIRP coverage (dBW)

Specifications

Ku-band

Ka-band

Transponder frequency chart


DFS Kopernikus 3's EIRP


 Program: Diadème

French scientific program: geodesy studies using laser and doppler effect


Program: Diadème

Diadème 1

Diadème 2


 Diadème 1

Also called D1C

General

Designation	02674 / 67011A
Launch date	8 Feb 1967
Country of origin	France
Mission	Scientific: geodesy
Operator	CNES
Perigee/Apogee	545/1083 km
Inclination	39.9°
Period	101.2 min
Launch vehicle	Diamant #3
Mass at launch	20 kg

Built by matra, had a doppler beacon in 150 / 400 MHz and laser reflectors.

End of life

Out of service	2 Jan 1970
Cause	Stopped broadcasting


 Diadème 2

Also called D1D

General

Designation	02680 / 67014A
Launch date	15 Feb 1967
Country of origin	France
Mission	Scientific: geodesy
Operator	CNES
Perigee/Apogee	586/1731 km
Inclination	39.4°
Period	108.5 min
Launch vehicle	Diamant #4
Mass at launch	20 kg

Identical to Diadème 1

End of life

Out of service	16 Sep 1968 (stopped transmitting on 5 Apr 1967)


 Diapason

Also called D1A

General

Designation	02016 / 66013A
Launch date	17 Feb 1966
Country of origin	France
Mission	Scientific: geodesy
Operator	CNES
Perigee/Apogee	502/2484 km
Inclination	34.1°
Period	115.8 min
Launch vehicle	Diamant #2
Mass at launch	18.5 kg

Also used to test technology. built by Matra.

Had a doppler beacon in 150 / 400 MHz

End of life

Out of service	23 Jan 1972
Cause	Stopped transmitting


 Program: Discoverer

USAF program: 38 satellites launched between 28 Feb 1959 and 27 Feb 1962

It seems that all Discoverers beginning with number 14 are KH spysats. See Thor Agena listing for the launches.

A second version of this program started in 1998 by a call for proposals (the idea is a constellation of radar/spy satellites for worldwide coverage; with SAR in X-band, 770 km). The program is managed by Darpa, USAF and the NRO. The project winner should be designated in june 2000. 2 demonstrations satellites should then be launched. The full system should consist of 24 satellites costing each less than $100 million. The total cost of exploitation over 20 years is targeted at $6.5 billion. The first phase of the program will be carried out by Lockheed Martin, TRW and Spectrum Astro. Each contract is woth $10 million. Planned resolution: 10 m standard with max 30 cm. 25 second repetition. The satellite would relay via GEO satellites.


 Program: DMSP

Defense Meteorological Satellite Program

Military meteorology program operated by NOAA since may 1998 (previously the Air Force Space Command was in charge of the program). The technology was first tested by the AMS program. All DMSP satellites were built by RCA Astro Space, which is now Lockheed Martin Astro Space; based on the Tiros N bus.

On 1st June 1998 the control and maintenance of the satellites were transfered to NOAA in order to reduce costs.

5 DMSP B5D3 have been ordered

External resources

http://www.ngdc.noaa.gov/dmsp/dmsp.html

http://www.spacecom.af.mil/usspace/dmsp.htm

http://www.fas.org/spp/military/program/met/dmsp.htm


Program: DMSP

DMSP B5D1-1 (76091A)

DMSP B5D1-2 (77044A)

DMSP B5D1-3 (78042A)

DMSP B5D1-4 (79050A)

DMSP B5D2-3

DMSP B5D2-4 (88006A)

DMSP B5D2-5 (90105A)

DMSP B5D2-6 (91082A)

DMSP B5D2-7

DMSP B5D2-8

DMSP B5D2-9


DMSP B5D1's specifications

Prime contractor	MM Astro Space
Platform
Mass at launch	between 450 & 513 kg
Mass in orbit
Diameter	1.68 m
Height	6.4 m
Solar array
Stabilization
DC power
Design lifetime


DMSP B5D2's specifications

Prime contractor	LM Astro Space
Platform	based on the Tiros N bus
Mass at launch	750 kg?
Mass in orbit
Diameter	1.68 m
Height	6.4 m
Solar array
Stabilization
DC power
Design lifetime


 DMSP B5D2-3

Also called USA 026 or DMSP 19543

General

Designation	18123 / 87053A
Launch date	20 Jun 1987 at 02:34 UT
Country of origin	United States
Mission	Military: meteorology
Perigee/Apogee	828/848 km
Inclination	98.8°
Period	101.7 min
Launch vehicle	Atlas E59
Launch site	Vandenberg
Mass at launch	822 kg

Must detect tropical cyclones and evaluate the intensity of storms.

Technical data

Specifications


 DMSP B5D2-7

Also called USA 106 and DMSP 5D F12 or DMSP 23545

General

Designation	23233 / 94057A
Launch date	29 Aug 1994 at 17:38 UT
Country of origin	United States
Mission	Military: meteorology
Perigee/Apogee	840/860 km
Inclination	98.9°
Period	101.9 min
Launch vehicle	Atlas E20
Launch site	Vandenberg

It carries instruments to measure energetic particles in the magnetosphere and photometers to scan auroral displays.

Technical data

Specifications


 DMSP B5D2-8

Also called USA 109 and DMSP 5D F13 or DMSP 24547

General

Designation	23533 / 95015A
Launch date	24 Mar 1995 at 14:05 UT
Country of origin	United States
Mission	Military: meteorology
Perigee/Apogee	846/854 km
Inclination	98.8°
Period	101.9 min
Launch vehicle	Atlas E45
Launch site	Vandenberg SLC3

The satellite carries the OLS (Operational Linescan System) weather imager, and a set of microwave sounders and particle detectors.

The launch vehicle was the last Atlas E, a refurbished intercontinental ballistic missile which had been built in the early 1960s.

Technical data

Specifications


 DMSP B5D2-9

Also called USA 131 and DMSP 5D F14

General

Designation	24753 / 97012A
Launch date	4 Apr 1997
Country of origin	United States
Mission	Military: meteorology
Perigee/Apogee	850 km
Inclination	99°
Period	102 min
Launch vehicle	Titan 2 #18
Launch site	Vandenberg

Last of the B5D2 series

Technical data

Specifications


 Program: Dong Fang Hong

Means "The Orient is red", also called DFH or PRC

People's Republic of China program which contains numerous sub-programs. Very few details are available...

Among those subprograms the Zhongxing alias Chinasat telecommunication program


Program: Dong Fang Hong

DFH 01 DFH 02 DFH 03 DFH 04 DFH 05 DFH 06 DFH 07 DFH 08 DFH 09 DFH 10 DFH 11 DFH 12 DFH 13 DFH 14 DFH 15 DFH 16	DFH 17 DFH 18 DFH 19 DFH 20 DFH 21 DFH 22 DFH 23 DFH 24 DFH 25 DFH 26 DFH 30 DFH 31 DFH 32 DFH 33 DFH 34 DFH 35	DFH 36 DFH 37 DFH 38 DFH 39 DFH 40 DFH 41 DFH 42 DFH 43 DFH 44 DFH 45 DFH 46 DFH 47 DFH 48


Feng Yun 1 A&B's payload

VHRR (Very High Resolution Radiometer)

Wavebands	0.58-0.68 µm (visible) 0.725-1.1 µm (near IR) 0.48-0.53 µm (visible) 0.53-0.58 µm (visible) 10.5-12.5 µm (thermal IR)
Resolution	1.1 km (visible) 4 km (IR)
Swath width	3200 km

Equipped with 2 of those radiometers


STTW's specifications

Shiyan Tongbu Tongxin Weixing means experimental synchronous communications satellite. Could also be named DFH 1

Prime contractor	Chinese industry
Platform	STTW
Mass at launch	1024 kg
Mass in orbit	approx. 450 kg
Diameter	2.1 m
Solar array	cells mounted on cylindrical body
Stabilization	Spin stabilized
DC power
Design lifetime	4 years


STTW's C-band

Main transponders	2
Backup transponders
Power	10 W (TWTA)
Bandwidth	36 MHz
Coverage	China
EIRP max	32 dBW
Polarization	linear H


DFH 2's specifications

Prime contractor	Chinese industry
Platform	DFH 2
Mass at launch
Mass in orbit
Diameter
Solar array
Stabilization	Spin stabilized
DC power
Design lifetime	4 years?


DFH 2's C-band

Main transponders	4
Backup transponders
Power	10 W (TWTA)
Bandwidth	36 MHz
Coverage	China
EIRP max	32 dBW
Polarization	linear H


DFH 3's specifications

Prime contractor	CAST/DASA
Platform	DFH 3
Mass at launch	2230 kg
Mass in orbit	1100 kg
Dimension
Stabilization	3-axis
DC power
Design lifetime	8 years
Capacity	6 tv channels and 8000 phone calls per minute!


DFH 3's C-band

Main transponders	24
Backup transponders
Power	6 transponders of 20 W (TWTA) 18 transponders of 10 W (TWTA)
Bandwidth	36 MHz
Coverage	China
EIRP max	6 transponders: 38 dBW 18 transponders: 35 dBW
G/T max	-2 dB/K
Polarization	linear, standard C-band
Beacons	3.70980 V & 4.19202 H GHz


 Dong Fang Hong 01

Also called Mao 1

General

Designation	04382 / 70034A
Launch date	24 Apr 1970
Country of origin	China
Mission	Scientific
Perigee/Apogee	431/2163 km
Inclination	68.4°
Period	111.5 min
Launch vehicle	Long March 1
Mass at launch	173 kg

Frequencies: 20.008 MHz, 202 MHz, 2752 MHz and 5600 MHz


 Dong Fang Hong 02

Also called Mao 2 or SJ 1

General

Designation	05007 / 71018A
Launch date	3 Mar 1971
Country of origin	China
Mission	Scientific (Shijian)
Perigee/Apogee	265/1833 km
Inclination	69.8°
Period	106.1 min
Launch vehicle	Long March 1

Frequencies: 19.997 MHz, 20.008 MHz, 202 MHz, 2752 MHz and 5600 MHz


 Dong Fang Hong 03

Also called Mao 3 or JSSW 1

General

Designation	08053 / 75070A
Launch date	26 Jul 1975
Country of origin	China
Mission	Remote sensing (JSSW)
Perigee/Apogee	190/455 km
Inclination	69°
Period	90.9 min
Launch vehicle	FB 1
End of life

Decay	14 Sep 1975


 Dong Fang Hong 04

Also called Mao 4 or FSW 0-1

General

Designation	08452 / 75111A
Launch date	26 Nov 1975
Country of origin	China
Mission	Remote sensing (FSW)
Perigee/Apogee	173/483 km
Inclination	63°
Period	91.1 min
Launch vehicle	Long March 2C
End of life

Out of service	3 Dec 1975
Cause	Normal (photos recovery)
Decay	29 Dec 1975


 Dong Fang Hong 05

Also called Mao 5 or JSSW 2

General

Designation	08488 / 75119A
Launch date	16 Dec 1975
Country of origin	China
Mission	Remote sensing (JSSW)
Perigee/Apogee	186/387 km
Inclination	69°
Period	90.3 min
Launch vehicle	FB 1
End of life

Decay	27 Jan 1976


 Dong Fang Hong 06

Also called Mao 6 or JSSW 3

General

Designation	09394 / 76087A
Launch date	30 Aug 1976
Country of origin	China
Mission	Remote sensing (JSSW)
Perigee/Apogee	195/2145 km
Inclination	69.2°
Period	108.8 min
Launch vehicle	FB 1
End of life

Decay	25 Nov 1978


 Dong Fang Hong 07

Also called Mao 7 or FSW 0-2

General

Designation	09587 / 76117A
Launch date	7 Dec 1976
Country of origin	China
Mission	Remote sensing (FSW)
Perigee/Apogee	172/489 km
Inclination	59.4°
Period	91.1 min
Launch vehicle	Long March 2C
End of life

Decay	2 Jan 1977


 Dong Fang Hong 08

Also called Mao 8 or FSW 0-3

General

Designation	10611 / 78011A
Launch date	26 Jan 1978
Country of origin	China
Mission	Remote sensing (FSW)
Perigee/Apogee	186/507 km
Inclination	57°
Period	91.4 min
Launch vehicle	Long March 2C
End of life

Decay	7 Feb 1978


 Dong Fang Hong 09

Also called SJ 2

General

Designation	12842 / 81093A
Launch date	19 Sep 1981
Country of origin	China
Mission	Scientific: ionosphere study (Shijian)
Perigee/Apogee	232/1598 km
Inclination	59.5°
Period	103.3 min
Launch vehicle	FB 1
End of life

Decay	19 Sep 1981


 Dong Fang Hong 10

Also called SJ 3A

General

Designation	12843 / 81093B
Launch date	19 Sep 1981
Country of origin	China
Mission	(Shijian)
Perigee/Apogee	233/1615 km
Inclination	59.4°
Period	103.5 min
Launch vehicle	FB 1
End of life

Decay	6 Oct 1982


 Dong Fang Hong 11

Also called SJ 3B

General

Designation	12845 / 81093D
Launch date	19 Sep 1981
Country of origin	China
Mission	(Shijian)
Perigee/Apogee	232/1608 km
Inclination	59.4°
Period	103.4 min
Launch vehicle	FB 1
End of life

Decay	17 Aug 1982


 Dong Fang Hong 12

Also called FSW 0-4

General

Designation	13521 / 82090A
Launch date	9 Sep 1982
Country of origin	China
Mission	Remote sensing (FSW)
Perigee/Apogee	172/392 km
Inclination	63°
Period	90.2 min
Launch vehicle	Long March 2C
End of life

Decay	21 Sep 1982


 Dong Fang Hong 13

Also called FSW 0-5

General

Designation	14288 / 83086A
Launch date	19 Aug 1983
Country of origin	China
Mission	Remote sensing (FSW)
Perigee/Apogee	170/493 km
Inclination	63.3°
Period	91.2 min
Launch vehicle	Long March 2C
End of life

Decay	3 Sep 1983


 Dong Fang Hong 14

Also called STTW T1

General

Designation	14670 / 84008A
Launch date	29 Jan 1984
Country of origin	China
Mission	(STTW)
Geostationary orbit	n/a
Perigee/Apogee	484/6446 km
Inclination	36.1°
Period	162 min
Launch vehicle	Long March 3

Would not have provided entire China coverage

End of life

Out of service	29 Jan 1984
Cause	Launcher 3rd stage failed to ignite
Technical data

Specifications

C-band


 Dong Fang Hong 15

Also called STTW T2

General

Designation	14899 / 84035A
Launch date	8 Apr 1984
Country of origin	China
Mission	Telecommunications (STTW)
Geostationary orbit
Launch vehicle	Long March 3

Did not cover entire China. Operated by Chinasat

End of life

Out of service	yes
Technical data

Specifications

C-band


 Dong Fang Hong 16

Also called FSW 0-6

General

Designation	15279 / 84098A
Launch date	12 Sep 1984
Country of origin	China
Mission	Remote sensing (FSW)
Perigee/Apogee	172/398 km
Inclination	67.9°
Period	90.2 min
Launch vehicle	Long March 2C
End of life

Decay	29 Sep 1984


 Dong Fang Hong 17

Also called FSW 0-7

General

Designation	16177 / 85096A
Launch date	21 Oct 1985
Country of origin	China
Mission	Remote sensing (FSW)
Perigee/Apogee	171/393 km
Inclination	63°
Period	90.2 min
Launch vehicle	Long March 2C
End of life

Decay	7 Nov 1985


 Dong Fang Hong 18

Also called STTW 1

General

Designation	16526 / 86010A
Launch date	1 Feb 1986
Country of origin	China
Mission	Telecommunications (STTW)
Geostationary orbit	103°E
Launch vehicle	Long March 3

Operated by Chinasat This was a pre DFH 2 satellite, with full China coverage

End of life

Out of service	Apr 1995
Technical data

Specifications

C-band


 Dong Fang Hong 19

Also called FSW 0-8

General

Designation	17001 / 86076A
Launch date	6 Oct 1986
Country of origin	China
Mission	Remote sensing (FSW)
Perigee/Apogee	169/337 km
Inclination	57°
Period	89.6 min
Launch vehicle	Long March 2C
End of life

Decay	23 Oct 1986


 Dong Fang Hong 20

Also called FSW 0-9

General

Designation	18306 / 87067A
Launch date	5 Aug 1987
Country of origin	China
Mission	Remote sensing (FSW)
Perigee/Apogee	169/366 km
Inclination	63°
Period	89.9 min
Launch vehicle	Long March 2C
End of life

Decay	23 Aug 1987


 Dong Fang Hong 21

Also called FSW 1-1

General

Designation	18341 / 87075A
Launch date	8 Sep 1987
Country of origin	China
Mission	Remote sensing (FSW)
Perigee/Apogee	181/222 km
Inclination	63°
Period	88.5 min
Launch vehicle	Long March 2C
End of life

Decay	4 Oct 1987


 Dong Fang Hong 22

Also called STTW 2 or Chinasat 1

General

Designation	18922 / 88014A
Launch date	7 Mar 1988
Country of origin	China
Mission	Telecommunications
Geostationary orbit	87.5°E, inclined
Launch vehicle	Long March 3

Operated by Chinasat

End of life

Out of service	Dec 1997
Cause	deorbited
Technical data

Specifications

C-band


 Dong Fang Hong 23

Also called FSW 1-2

General

Designation	19368 / 88067A
Launch date	5 Aug 1988
Country of origin	China
Mission	Remote sensing (FSW)
Perigee/Apogee	204/311 km
Inclination	63°
Period	89.7 min
Launch vehicle	Long March 2C
End of life

Decay	13 Aug 1988


 Dong Fang Hong 24

Also called Feng Yun 1-1, means "wind and cloud"

General

Designation	19467 / 88080A
Launch date	6 Sep 1988 at 20:30 UT
Country of origin	China
Mission	Meteorology
Perigee/Apogee	832/937 km
Inclination	99.2°
Period	102.7 min
Launch vehicle	Long March 4

Mission: weather forecasting and environment monitoring; cloud, ice, snow and flood monitoring; sea color and surface temperature.

End of life

Cause	Failed after 39 days
Technical data

Payload

Specifications

Prime contractor	State Met Administration
Mass at launch	750 kg
Stabilization	3-axis
Design lifetime	6 months

Transmits on 137.8 MHz.


 Dong Fang Hong 25

Also called STTW 3 or Chinasat 2

General

Designation	19710 / 88111A
Launch date	22 Dec 1988
Country of origin	China
Mission	Telecommunications
Geostationary orbit	110.5°E, inclined
Launch vehicle	Long March 3

Operated by Chinasat

Technical data

Specifications

C-band


 Dong Fang Hong 26

Also called STTW 4 or Chinasat 3

General

Designation	20473 / 90011A
Launch date	4 Feb 1990
Country of origin	China
Mission	Telecommunications
Geostationary orbit	98°E, inclined
Launch vehicle	Long March 3

Operated by Chinasat

End of life

Out of service	Aug 1998
Cause	out of control
Technical data

Specifications

C-band


 Dong Fang Hong 30

Also called Feng Yun 1-2, means "wind and cloud"

General

Designation	20788 / 90081A
Launch date	3 Sep 1990
Country of origin	China
Mission	Meteorology
Perigee/Apogee	875/897 km
Inclination	98.8°
Period	102.7 min
Launch vehicle	Long March 4

Mission: weather forcasting and environment monitoring; cloud, ice, snow and flood monitoring; sea color and surface temperature.

External resources

http://www.cma.gov.cn/fy2/chnsmc.htm

Technical data

Payload

Specifications

Prime contractor	State Met Administration
Mass at launch	750 kg
Stabilization	3-axis
Design lifetime	1 year

APT-Downlink is approximately 36kHz wide FM-modulated, APT-FAX format.

APT downlink freq.	137.800MHz (currently not active)
HRPT downlink freq.	? (around 1700MHz?, active)
Beacon freq.	?


 Dong Fang Hong 31

Also called Atmosphere 1

General

Designation	20789 / 90081B
Launch date	3 Sep 1990
Country of origin	China
Mission	Scientific: high atmosphere study
Perigee/Apogee	789/811 km
Inclination	99°
Period	100.9 min
Launch vehicle	Long March 4
End of life

Decay	11 Mar 1991


 Dong Fang Hong 32

Also called Atmosphere 2

General

Designation	20790 / 90081C
Launch date	3 Sep 1990
Country of origin	China
Mission	Scientific: high atmosphere study
Perigee/Apogee	596/629 km
Inclination	99°
Period	97 min
Launch vehicle	Long March 4
End of life

Decay	24 Jul 1991


 Dong Fang Hong 33

Also called FSW 1-3

General

Designation	20838 / 90089A
Launch date	5 Oct 1990
Country of origin	China
Mission	Remote sensing (FSW)
Perigee/Apogee	209/312 km
Inclination	57°
Period	89.7 min
Launch vehicle	Long March 2C
End of life

Decay	23 Oct 1990


 Dong Fang Hong 34

Also called STTW 5 or Chinasat 4

General

Designation	21833 / 91088A
Launch date	28 Dec 1991
Country of origin	China
Mission	Telecommunications
Geostationary orbit	n/a
Launch vehicle	Long March 3
End of life

Out of service	28 Dec 1991
Cause	Did not reach GEO
Technical data

Specifications

C-band


 Dong Fang Hong 35

Also called FSW 2-1

General

Designation	22072 / 92051A
Launch date	9 Aug 1992
Country of origin	China
Mission	Remote sensing (FSW 2)
Perigee/Apogee	171/332 km
Inclination	63.1°
Period	89.5 min
Launch vehicle	Long March 2D
End of life

Decay	1 Sep 1992


 Dong Fang Hong 36

Also called FSW 1-4

General

Designation	22162 / 92064B
Launch date	6 Oct 1992
Country of origin	China
Mission	Remote sensing (FSW)
Perigee/Apogee	213/309 km
Inclination	63°
Period	89.7 min
Launch vehicle	Long March 2C
End of life

Decay	31 Oct 1992


 Dong Fang Hong 37

Also called Jianbing 93 or FSW 1-5

General

Designation	22859 / 93063A (or 22870 / 93063H)
Launch date	8 Oct 1993 at 08:00 UT
Country of origin	China
Mission	Remote sensing (FSW)
Perigee/Apogee	177/2629 km
Inclination	56.5°
Period	113.9 min
Launch vehicle	Long March 2C

Contained a Mao's medallion of 28 g made of 44 South-African diamants that should have been sold by auction at its return on earth by Zhonyu company.

The reentry vehicle fired its deorbit motor successfully but, alas, in the wrong direction; the capsule ended up in a 187 x 3016 km orbit, starting from a low 196 x 251 km orbit.

End of life

Decay	12 Mar 1996


 Dong Fang Hong 38

Also called Shijian 4 or SJ 4. Means "Practice 4"

General

Designation	22996 / 94010A
Launch date	8 Feb 1994
Country of origin	China
Mission	Scientific & Technology (Shijian)
Perigee/Apogee	221/34459 km
Inclination	28.41°
Period	605.89 min
Launch vehicle	Long March 3A

It carried six instruments for measuring particle fluxes and spacecraft electric potential.


 Dong Fang Hong 39

Also called DFH 3-0

General

Designation	23009 / 94010B
Launch date	8 Feb 1994
Country of origin	China
Mission	Simulated satellite
Perigee/Apogee	211/32578 km
Inclination	27.49°
Period	570.03 min
Launch vehicle	Long March 3A

Mockup of the new DFH 3 telecommunication series (see Dong Fang Hong 41)


 Dong Fang Hong 40

Also called FSW 2-2, Fanhui Shi Weixing

General

Designation	23145 / 94037A
Launch date	3 Jul 1994 at 08:00 UT
Country of origin	China
Mission	Remote sensing (FSW)
Perigee/Apogee	176/355 km
Inclination	62.9°
Period	89.6 min
Launch vehicle	Long March 2D
End of life

Decay	payload: 15 Jul 1994 service module: 13 Sep 1994


 Dong Fang Hong 41

Also called DFH 3-1

General

Designation	23415 / 94080A
Launch date	29 Nov 1994 at 17:02 UT
Country of origin	China
Mission	Telecommunications
Geostationary orbit	should have been in 125°E slot
Launch vehicle	Long March 3A

Operated by Chinasat  First satellite of the DFH 3 generation, built with a 20% German participation (Daimler Benz Aerospace/MBB)

End of life

Out of service	9 Jan 1995
Cause	fuel leak
Technical data

Specifications

C-band


 Dong Fang Hong 42

Also called Chinasat 7 (Zhongxing 7)

General

Designation	24282 / 96048A
Launch date	18 Aug 1996
Country of origin	China
Mission	Telecommunications
Geostationary orbit	n/a
Launch vehicle	Long March 3 #40

Insured for $128 million. Should have replaced Spacenet 1 (Chinasat 5)

Operated by Chinasat

End of life

Out of service	18 Aug 1996
Cause	The satellite was not delivered in the correct transfer orbit (20 km x 17227 km x 27.2°)
Technical data

Specifications

Prime contractor	Hughes
Platform	HS-376
Mass at launch
Mass in orbit	734 kg
Dimension	2.2 m diameter x 3.1 m stowed (7.5 m deployed)
Solar array
Stabilization
DC power	BOL: 1200 W
Design lifetime	10 years

The apogee motor onboard is a solid Star-30

C-band

Main transponders	24
Backup transponders	6
Power	16 W
Bandwidth	4 x 72 MHz 20 x 36 MHz
Coverage	China and the South China Sea area
EIRP max	37 dBW
Polarization


 Dong Fang Hong 43

Also called FSW 2-3, Fanhui Shi Weixing

General

Designation	24634 / 96059A
Launch date	20 Oct 1996
Country of origin	China
Mission	Remote sensing (FSW-2)
Perigee/Apogee	172/335 km
Inclination	63.0°
Period	89.5 min
Launch vehicle	Long March 2D
End of life

Decay	4 Nov 1996 & 3 Dec 1996


 Dong Fang Hong 44

Also called Chinasat 6 and DFH 3-2

General

Designation	24798 / 97021A
Launch date	11 May 1997
Country of origin	China
Mission	Telecommunications
Geostationary orbit	125°E
Launch vehicle	Long March 3A #42

Insured for $100 million

Operated by Chinasat  To replace Dong Fang Hong 41

Technical data

Specifications

C-band


 Dong Fang Hong 45

Also called Feng Yun 2B or Feng Yun 2-1R (some incorrectly name it 2A)

General

Designation	24834 / 97029A
Launch date	10 Jun 1997
Country of origin	China
Mission	Meteorology
Geostationary orbit	105°E
Launch vehicle	Long March 3

First Chinese GEO meteorology satellite. The 1R and B denomination stands for the replacement of the original satellite destroyed before even being installed on the Long March and launched, in 1994.

The satellite is equipped with a scanning radiometer, a cloud coverage information system and a data collection and transmission system.

End of life

Out of service	April 1998
Cause	failure of the S-band antenna mechanism
External resources

http://www.cma.gov.cn/fy2/chnsmc.htm

Technical data

Specifications

Prime contractor	Shanghai Aerospace Technology Research Institute
Platform
Mass at launch	1380 kg
Mass in orbit
Dimension	cylinder: 2.1 m x 1.6 m
Solar array
Stabilization	spin-stabilized (100 rpm)
DC power
Design lifetime	3 years

The satellite is said to be a copy of GMS 5

VISSR (Visible and IR Spin Scan Radiometer)

Wavebands	0.55-1.05 µm (visible) 6.2-7.6 µm (water vapour) 10.5-12.5 µm (IR)
Resolution	visible: 1.25 km IR& WV: 5 km
Image repeat frequency	1 hour

Downlink: 1687.5 MHz linear (PCM/BPSK, 660 kbps)


 Dong Fang Hong 46

Also called Feng Yun 1-3 or FengYun 1C or FY 1C, means "wind and cloud"

General

Designation	25730 / 99025A
Launch date	10 May 1999
Country of origin	China
Mission	Meteorology
Perigee/Apogee	849/898 km
Inclination	98.8°
Period	102.1 min
Launch vehicle	Long March 4B #54
Technical data

Payload

Specifications

Prime contractor	State Met Administration
Mass at launch	750 kg
Stabilization	3-axis
Design lifetime	6 months

Downlink: 180.008 & 480.020 MHz + 1.7005 & 1.7045 GHz


 Dong Fang Hong 47

Also called Shijian 5 or SJ 5. Means "Practice 5"

General

Designation	25731 / 99025B
Launch date	10 May 1999
Country of origin	China
Mission	Scientific & Technology (Shijian)
Perigee/Apogee	849/868 km
Inclination	98.9°
Period	102.1 min
Launch vehicle	Long March 4B #54


 Dong Fang Hong 48

Also called Chinasat 8

General

Designation
Launch date	initially planned in late 1998
Country of origin	China
Mission	Telecommunications
Geostationary orbit	115.5°E
Launch vehicle	Long March 3B
Launch site	Xichang

Contract calls for in-orbit delivery, worth $200 million  Operated by Chinasat

In Apr 1999 it is known that the exportation of the satellite is comprised by the US new export policy. it seems that all satellite exports to be launched on Long March are compromised.

Technical data

EIRP coverage (dBW)

C-band

Ku-band 1

Specifications

Prime contractor	Space Systems/Loral
Platform	FS-1300
Mass at launch	4657 kg
Mass in orbit
Dimension	2.7 x 2.2 x 2. 45 m
Solar array
Stabilization	3-axis
DC power	11000 W?
Design lifetime	15 years
C-band

Main transponders	36
Backup transponders
Power	37 W
Bandwidth	34 x 36 MHz 2 x 72 MHz
Coverage	China and neighboring countries (India, Thailand, part of Japan with 32 dBW)
EIRP max	40 dBW
G/T max	-1 dB/K
Polarization	linear
Frequencies	uplink: 5.845-6.650 GHz downlink: 3.400-4.200 GHz

Beacons: 3.630 V & 4.1985 H GHz

Ku-band 1

Main transponders	10
Backup transponders
Power	125 W
Bandwidth	36 MHz
Coverage	Full China (minimum 46 dBW)
EIRP max	50 dBW
G/T max	6 dB/K
Polarization	linear
Frequencies	uplink: 13.75-14.00 GHz downlink: 11.45-11.70 GHz

Beacon: 11.698 H GHz

Ku-band 1 transponder frequency chart (GHz)

Uplink  Horizontal	Downlink Horizontal	Transponder	Downlink  Vertical	Uplink  Vertical
	11.496	19A		13.776
13.796		19B	11.516
	11.536	20A		13.816
13.836		20B	11.556
	11.576	21A		13.856
13.876		21B	11.596
	11.616	22A		13.896
13.916		22B	11.636
	11.656	23A		13.936
13.956		23B	11.676
Ku-band 2

Main transponders	6
Backup transponders
Power	125 W
Bandwidth	72 MHz
Coverage	Partial China (extrem north-east not covered)
EIRP max	50 dBW
G/T max	6 dB/K
Polarization	linear
Frequencies	uplink: 14.00-14.50 GHz downlink: 12.25-12.75 GHz

Beacon: 12.254 V GHz

Ku-band 2 transponder frequency chart (GHz)

Uplink  Horizontal	Transponder	Downlink  Vertical
14.058	24A	12.310
14.138	25A	12.390
14.218	26A	12.470
14.298	27A	12.550
14.378	28A	12.630
14.458	29A	12.710


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Dong Fang Hong 48's C-band EIRP coverage


Dong Fang Hong 48's Ku-band 1 EIRP coverage


 Dove

Short for Digital Orbiting Voice Encoder. Also called Microsat 2 or DO-17 or Oscar 17

General

Designation	20440 / 90005E
Launch date	22 Jan 1990
Country of origin	Brazil
Mission	Telecommunications
Perigee/Apogee	781/797 km
Inclination	98.6°
Period	100.6 min
Launch vehicle	Ariane V35
Mass at launch	9 kg

Based on a Amsat-NA Microsat bus

External resources

http://www.amsat.org/amsat/sats/nk6k/msatmain.html

Technical data

Downlink	1200 bps Bell 202 AX.25, same as used in terrestrial Packet Radio, Synthesized Voice Beacon.
	145.825, 145.825 MHz
S-Band beacon	2401.221 MHz

Passive magnetic stabilization


DRTS
 Program: DRTS

Data Relay Test Satellite

Japanese program to relay signals via 2 GEO satellites. The program must test acquisition and tracking technology and high speed data relay (240 Mbps).

First launch planned in 2000 with H2 and second with H2A in 2002. The 2 satellites to be called DRTS E and W (East & West) should be deployed 100 deg apart on GEO. Should operate in S- and Ka-band


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Program: DRTS

DRTS W

DRTS E


 DRTS W

General

Designation
Launch date	mid-2000
Country of origin	Japan
Mission
Geostationary orbit	90°E
Launch vehicle	H2
Launch site
Technical data

Specifications

Prime contractor
Platform
Mass at launch	2650 kg
Mass in orbit	1400 kg
Dimension	2.2 x 2.4 x 2.2 m
Solar array	2.4 x 7.3 m
Stabilization	3-axis
DC power	EOL: 2100 W
Design lifetime	7 years

Should operate in S- and Ka-band for inter satellite links and in Ka-band with the ground stations

Inter satellite link antenna: 3.6 m diameter; feeder link antenna: 1.8 m diameter


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 DRTS E

General

Designation
Launch date	2002
Country of origin	Japan
Mission
Geostationary orbit	170°W
Launch vehicle	H2A
Launch site


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 Program: DSCS

Defense Satellite Communication System, also called USGCSS

American geostationary satellite program owned by the Defense Communications Agency and operated by the US Army Space Command. Designed to provide military telecommunications.

Contact

Operator: US Army Space Command

Command and control:

50th Space Wing

300 O'Malley Ave, Suite 24, Falcon AFB, CO 80912-3024, USA

External resources

http://www.spacecom.af.mil/usspace/dscs.htm

http://www.fas.org/spp/military/program/com/dscs_2.htm

http://www.fas.org/spp/military/program/com/dscs_3.htm

Technical data

First generation

See IDSCP

Second generation

Specifications

Satellites were launched by pairs to GEO

Third generation

Specifications

Payload

Those satellites also carry an AFSATCOM package for the dissemination of Emergency Action Message and Single Integrated Operations Plan directives. It's purpose is to send orders to the nuclear capable forces.

Fleet composed of 14 satellites. USAF asked LM [in mid-1995] for a cost estimate on upgrades to the remaining ground-spare DSCS-3s to extend their lives somewhat: improved thrusters, better solar cells, more efficient amplifiers in the high-power channels. The DSCS-3 production line shut down several years ago, and the USAF wants to postpone the start of development on DSCS-4.


Program: DSCS

DSCS 2-01	DSCS 2-02	DSCS 2-03
DSCS 2-04	DSCS 2-05	DSCS 2-06
DSCS 2-07	DSCS 2-08	DSCS 2-11
DSCS 2-12	DSCS 2-13	DSCS 2-14
DSCS 2-15	DSCS 2-16
DSCS 3-01	DSCS 3-02	DSCS 3-03
DSCS 3-04	DSCS 3-05	DSCS 3-06
DSCS 3-07	DSCS 3-08	DSCS 3-09
DSCS 3-10	DSCS 3-11


DSCS 2's specifications

Prime contractor	TRW
Platform
Mass at launch
Mass in orbit	612 kg
Dimensions	2.7 m (diameter) x 1.82 m (high)
Solar arrays
Stabilization	spin stabilized
DC power	BOL: 535 W EOL: 358 W
Design lifetime	5 years

Had 2 dish antennas


DSCS 3's specifications

Prime contractor	Lockheed martin (former GE Astro Space)
Platform
Mass at launch	2615 kg
Mass in orbit	1170 kg
Dimensions	2.07 m x 1.93 m x 1.96 m (L x W x D)
Solar arrays	11.4 m
Stabilization	3-axis
DC power	BOL: 1240 W EOL: 837 W three 35 AH NiCd batteries
Design lifetime	10 years
Telemetry	S- and X-band
Beacon	7600.0 & 7604.7 MHz

Features fixed (multiple-beam) antennas and a steerable high power antenna


DSCS 3's payload

X-band

Main transponders	6
Backup	two 40 W and two 10 W amplifiers
Power	channels 1 & 2: 40 W (TWTA) channels 3 to 6: 10 W (SSPA)
Coverage and EIRP max	2 Global beams: 29 dBW 2 Spot beams: 34 dBW Gimballed dish: 44 dBW
Transponder frequency chart (GHz)

Channel	Bandwidth (MHz)	Frequency
1	50	?
2	75	?
3	85	?
4	85	?
5	60	?
6	50	?

Frequencies are probably in 250 MHz, S-band and X-band range. In X-band, uplink in the 7.9-8.025 GHz, 8.025-8.400 GHz, downlink in 7.250-7.750 GHz


 DSCS 2-01

General

Designation	05587 / 71095A
Launch date	3 Nov 1971
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit	see below
Launch vehicle	Titan 3 #56
End of life

Out of service	yes
Technical data

Specifications


 DSCS 2-02

General

Designation	05588 / 71095B
Launch date	3 Nov 1971
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit
Launch vehicle	Titan 3 #56
End of life

Out of service	yes
Technical data

Specifications


 DSCS 2-03

General

Designation	06973 / 73100A
Launch date	13 Dec 1973
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit
Launch vehicle	Titan 3 #71
End of life

Out of service	yes
Technical data

Specifications


 DSCS 2-04

General

Designation	06974 / 73100B
Launch date	13 Dec 1973
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit
Launch vehicle	Titan 3 #71
End of life

Out of service	yes
Technical data

Specifications


 DSCS 2-05

General

Designation	07807 / 75040A
Launch date	20 May 1975
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit
Launch vehicle	Titan 3 #85
End of life

Out of service	20 May 1975
Cause	Launch failure
Decay	26 May 1975
Technical data

Specifications


 DSCS 2-06

General

Designation	07808 / 75040B
Launch date	20 May 1975
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit
Launch vehicle	Titan 3 #85
End of life

Out of service	20 May 1975
Cause	Launch failure
Decay	26 May 1975
Technical data

Specifications


 DSCS 2-07

General

Designation	10000 / 77034A
Launch date	12 May 1977
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit
Launch vehicle	Titan 3 #103
End of life

Out of service	yes
Technical data

Specifications


 DSCS 2-08

General

Designation	10001 / 77034B
Launch date	12 May 1977
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit
Launch vehicle	Titan 3 #103
End of life

Out of service	yes
Technical data

Specifications


 DSCS 2-11

General

Designation	11144 / 78113A
Launch date	14 Dec 1978
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit
Launch vehicle	Titan 3 #114
End of life

Out of service	yes
Technical data

Specifications


 DSCS 2-12

General

Designation	11145 / 78113B
Launch date	14 Dec 1978
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit
Launch vehicle	Titan 3 #114
End of life

Out of service	yes
Technical data

Specifications


 DSCS 2-13

Also called OPS 9443

General

Designation	11621 / 79098A
Launch date	21 Nov 1979
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit
Launch vehicle	Titan 3 #119
End of life

Out of service	yes
Technical data

Specifications


 DSCS 2-14

Also called OPS 9444

General

Designation	11622 / 79098B
Launch date	21 Nov 1979
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit	see below
Launch vehicle	Titan 3 #119
End of life

Out of service	yes
Technical data

Specifications

Downlinks in X-band


 DSCS 2-15

General

Designation	13636 / 82106A
Launch date	30 Oct 1982
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit	see below
Launch vehicle	Titan 3 #131
Location

Begin	End	Position
L: 30 Oct 1982		?
Mar 1995	Mar 1997	65°E, inclined
End of life

Out of service	Apr 1997
Cause	deorbited
Technical data

Specifications

Downlinks in X-band


 DSCS 2-16

Also called USA 043

General

Designation	20202 / 89069A
Launch date	4 Sep 1989
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit	n/a
Launch vehicle	Titan 3 #152
Launch site	Cape Canaveral
Technical data

Specifications

Downlinks in X-band


 DSCS 3-01

(code A1)

General

Designation	13637 / 82106B
Launch date	30 Oct 1982
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit	see below
Launch vehicle	Titan 3 #131
Location

Begin	End	Position
L: 30 Oct 1982		?
Mar 1995	Mar 1999	130°W, inclined
		orbit classified
Technical data

Specifications

Payload


 DSCS 3-02

Also called USA 011 (code B4)

General

Designation	16116 / 85092B
Launch date	3 Oct 1985
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit	n/a
Launch vehicle	STS 28 + IUS
Launch site	Cape Canaveral
Technical data

Specifications

Payload


 DSCS 3-03

Also called USA 012 (code B5)

General

Designation	16117 / 85092C
Launch date	3 Oct 1985
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit	n/a
Launch vehicle	STS 28 + IUS
Launch site	Cape Canaveral
Technical data

Specifications

Payload


 DSCS 3-04

Also called USA 044 (code A2)

General

Designation	20203 / 89069B
Launch date	4 Sep 1989
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit	n/a
Launch vehicle	Titan 3 #152
Technical data

Specifications

Payload


 DSCS 3-05

Also called USA 078 (code B14)

General

Designation	21873 / 92006A
Launch date	11 Feb 1992
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit	n/a
Launch vehicle	Atlas Centaur + IABS

First satellite of the 3B generation. This generation is equipped with reinforced plating to resist to the explosion of an atomic bomb.

Technical data

Specifications

Payload


 DSCS 3-06

Also called USA 082 (code B12)

General

Designation	22009 / 92037A
Launch date	2 Jul 1992
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit	n/a
Launch vehicle	Atlas Centaur + IABS
Technical data

Specifications

Payload


 DSCS 3-07

Also called USA 093 (code B9)

General

Designation	22719 / 93046A
Launch date	19 Jul 1993
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit	n/a
Launch vehicle	Atlas Centaur + IABS
Technical data

Specifications

Payload


 DSCS 3-08

Also called USA 097 (code B10)

General

Designation	22916 / 93074A
Launch date	28 Nov 1993
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit	n/a
Launch vehicle	Atlas Centaur + IABS
End of life

Out of service	28 Nov 1993
Cause	didn't reach GEO, failure of the IABS?
Technical data

Specifications

Payload


 DSCS 3-09

Also called USA 113 (code B7)

General

Designation	23628 / 95038A
Launch date	31 Jul 1995
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit	n/a
Launch vehicle	Atlas Centaur + IABS
Technical data

Specifications

Payload


 DSCS 3-10

Also called B13

General

Designation	25019 / 97065A
Launch date	25 Oct 1997
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit	n/a
Launch vehicle	Atlas Centaur #111 + IABS
Technical data

Specifications

Payload


 DSCS 3-11

Also called B8

General

Designation
Launch date	planned in 1999
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit	n/a
Launch vehicle	Atlas Centaur
Technical data

Specifications

Payload


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 Program: DSP

Defense Support Program

Military geostationary satellite program for early warning and detection of nuclear explosions.

The first generation of those satellites was IMEWS.

Contact

Operator: 21St Space Wing

Peterson AFB, CO

Command and Control: 50th Space Wing

300 O'Malley Ave, Suite 24, Falcon AFB, CO 80912-3024, USA

External resources

http://www.spacecom.af.mil/usspace/dsp.htm

http://www.fas.org/spp/military/program/warning/dsp.htm


Program: DSP

DSP F12

DSP 3-1

DSP 3-2

DSP 3-3

DSP 3-4

DSP 3-5

DSP 3-6

DSP 3-7


DSP 3 series

Prime contractor	TRW
Platform
Mass at launch	around 2200 kg
Mass in orbit
Dimension	6.7 m diameter x 10 m long (deployed)
Solar array
Stabilization	spin stabilized
DC power	1485 W
Design lifetime

Probably downlinks in S- and X-band. Has a wide field infrared telescope to provide real-time warning of missile launches (6000 infrared detectors)


 DSP F12

Also called USA 007

General

Designation	15453 / 84129A
Launch date	22 Dec 1984
Country of origin	United States
Mission	Military: early warning
Geostationary orbit	n/a
Launch vehicle	Titan 3 #142


 DSP 3-1

Also called USA 028 or DSP F13

General

Designation	18583 / 87097A
Launch date	29 Nov 1987
Country of origin	United States
Mission	Military: early warning
Geostationary orbit	n/a
Launch vehicle	Titan 3 #148
Technical data

Specifications


 DSP 3-2

Also called USA 039 or DSP F14

General

Designation	20066 / 89046A
Launch date	14 Jun 1989
Country of origin	United States
Mission	Military: early warning
Geostationary orbit	145°E (till Mar 1999 when the orbit was classified)
Launch vehicle	Titan 4
Launch site	Cape Canaveral
Technical data

Specifications


 DSP 3-3

Also called USA 065 or DSP F15

General

Designation	20929 / 90095A
Launch date	13 Nov 1990
Country of origin	United States
Mission	Military: early warning
Geostationary orbit	4°E (till Mar 1999 when the orbit was classified)
Launch vehicle	Titan 4
Technical data

Specifications


 DSP 3-4

Also called USA 075 or DSP F16

General

Designation	21805 / 91080B
Launch date	24 Nov 1991
Country of origin	United States
Mission	Military: early warning
Geostationary orbit	7°W (till Mar 1999 when the orbit was classified)
Launch vehicle	STS 44
Mass at launch	2350 kg

Cost: $275 million

Technical data

Specifications


 DSP 3-5

Also called USA 107 or DSP F17

General

Designation	23435 / 94084A
Launch date	22 Dec 1994 at 22:19 UT
Country of origin	United States
Mission	Military: early warning
Geostationary orbit	103°W (till Mar 1999 when the orbit was classified)
Launch vehicle	Titan 4
Technical data

Specifications


 DSP 3-6

Also called USA 130 or DSP F18

General

Designation	24737 / 97008A
Launch date	24 Feb 1997
Country of origin	United States
Mission	Military: early warning
Geostationary orbit	n/a
Launch vehicle	Titan 4B

worth $200 million

Technical data

Specifications


 DSP 3-7

Also called DSP F19 or USA 142

General

Designation	25669 / 99017A
Launch date	9 Apr 1999
Country of origin	United States
Mission	Military: early warning
Geostationary orbit	n/a
Launch vehicle	Titan 4B #26

reported cost of failure: $682 million

In late April controllers stated they have regained control over the satellite (not spinning anymore). Evaluation of potential use is under way.

End of life

Out of service	9 Apr 1999
Cause	The satellite was not delivered in the proper orbit. Reason unknown yet probably a failure of the IUS, built by Boeing.
Technical data

Specifications

mass: 2340 kg


 Early Bird

General

Designation	25121 / 97085A
Launch date	24 Dec 1997
Country of origin	United States
Mission	Remote Sensing
Perigee/Apogee	470 km, sun-synchronous
Inclination	97.3°
Period	revisit time: 2 to 5 days
Launch vehicle	Start 1
Launch site	Svobodny

US satellite operated by Earth Watch Inc. The cost of the system is approx. $200 million. Launch cost is said to be $7 million

Five days after launch the satellite went silent, with no communications. This was the consequence of an electrical problem. Insurers paid $29 million for the loss.

External resources

http://www.terraserver.com

Technical data

Specifications

Prime contractor	CTA Space Systems
Platform
Mass at launch	317 kg
Payload mass
Dimension
Solar array
Stabilization
DC power
Design lifetime	5 years

On-board data storage: 2 GByte

Gimbaled-mirror pointing system for ± 30° in-track and ± 28° side-to-side pointing capability

Panchromatic Sensor

Wavebands	445-650 nm
Swath width	280 km
Resolution	3 m, image size: 3 km x 3 km
Multispectral Sensor

Wavebands	Green: 490-600 nm Red: 615-670 nm Near IR: 790-875 nm
Swath width	280 km
Resolution	15 m, image size: 15 km x 15 km


 Program: ECCO

Equatorial Constellation COmmunications

LEO telecommunication system to be operated by Constellation Communications, Inc. ECCO is backed by Bell Atlantic, SpaceVest and Raytheon E-Systems. Brazil's Telebras which had expressed the will to join its ECO-8 project with ECCO has decided not to. The system is targeted for late-2002.

The system will have 12 satellites in equatorial orbit (including 1 spare) to provide telephony services to the 100 countries located in the tropical area. Further sets are satellites are planned. OSC should manufacture the first 12 satellites. Launch should be provided by Ariane.

Orbital will receive a contract, valued at approximately US$450 million, to serve as the space segment prime contractor for ECCO's initial equatorial satellite network, including both the construction and launch services for 12 low-orbit communications satellites. At the same time, Orbital will also become a major investor in the ECCO project, with the company providing up to US$150 million in equity capital and vendor financing.

Constellation Communications Inc. (CCI) is a Delaware company formed in 1991 with headquarters in Fairfax, Virginia/USA. In 1997, CCI established CCI International N.V. in the Netherlands Antilles to design, build and launch the ECCO satellite system.

A future set of 35 satellites is planned

Contact

Constellation Communications, Inc.

12500 Fair Lakes Circle, Suite 260, Fairfax, Virginia 22033, USA

Tel: +1-703- 227-7140

Fax: +1-703-818-8240

Email: cci@cciglobal.com

http://www.cciglobal.com/

Technical data

Constellation overview

Orbit type	MEO
Orbit range	2000 km, circular
Nb of satellites	12
Nb of planes	1 (equatorial)
Inclination	0°
Nb beams per satellite	24
Coverage	between 23° north and south
Modulation	CDMA
Mobile frequencies	Uplink: L-band (1610-1626.5 MHz) Downlink: S-band (2483.5-2500 MHz)
Satellite mass	280 kg
Operational date	2002 (planned)

lifetime: 5 to 7 years

satellite-gateway: C-band (uplink: 5091 - 5250 MHz; downlink: 6924 - 7075 MHz)


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 Dynamics Explorer 1

Also called DE A

General

Designation	12624 / 81070A
Launch date	3 Aug 1981
Country of origin	United States
Mission	Scientific: magnetosphere study
Perigee/Apogee	468/23322 km
Inclination	88.8°
Period	409.7 min
Launch vehicle	Thor Delta #155
External resources

http://leadbelly.lanl.gov/de/DE_home.html

http://nssdc.gsfc.nasa.gov/space/de.html


 Dynamics Explorer 2

Also called DE B

General

Designation	12625 / 81070B
Launch date	3 Aug 1981
Country of origin	United States
Mission	Scientific: magnetosphere and ionosphere study
Perigee/Apogee	304/1002 km
Inclination	90°
Period	97.8 min
Launch vehicle	Thor Delta #155
External resources

http://leadbelly.lanl.gov/de/DE_home.html

http://nssdc.gsfc.nasa.gov/space/de.html

End of life

Decay	19 Feb 1983


 Program: E-sat

LEO system program lead by Echostar and DBS Industries; aimed at collection of remote data. Authorized by FCC on 1st Apr 1998.

E-SAT's system will offer data communications services including data messaging services for the gas and electric utility industry, data messaging and retrieval in support of the direct-to-home broadcast-satellite service, messaging for environmental monitoring, and other services to users in the United States and around the world. System cost: $111 million

DBS Industries is reported in Aug 1999 to have acquired a controlling interest in E-sat (80.9%). The remaining 19.1% are held by Echostar who would be allowed to used 20% of the satellite capacity for its own interests.

Launch vehicle: Rokot launch cost: $47 million

6 satellites orbiting at 1260 km (2 planes of 3 satellites) planned for first quarter of 2001. Should use CDMA. Terminals would transmit only twice a day during 400 ms. Uplink: 148-148.905 MHz, Downlink: 137.0725-137.9725 MHz

External resources

http://www.dbsindustries.com/

Technical data

Specifications

Prime contractor	Alcatel or Uosat
Platform	Uosat
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime


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 EAST

Euro Arabian African Satellite Telecommunications

General

Designation
Launch date	initially planned in 2001, then in Mar 2002
Country of origin
Mission	Telecommunications
Geostationary orbit	32°E
Launch vehicle
Launch site

$1.07 billion project to provide mobile phone (with 1 in-orbit satellite, 1 in reserve, 1 control center). It will be compatible with GSM and DCS. The EAST company was formed by MMS and Digimed (a 100% subsidiary of Cyprus Telecommunications Authority).

It will provide mobile telephony services to all of Europe, the Mideast and parts of Africa. Fixed telephony should cost $0.3 per minute while mobile telephony would cost $0.6 per minute. Should be compatible with Aces

Technical data

Specifications

Prime contractor	Matra Marconi Space
Platform	Eurostar 3000
Mass at launch	5000 kg
Mass in orbit
Dimension
Solar array
Stabilization
DC power	11000 W
Design lifetime

15 m diameter antenna onboard

Will operate in L- and Ku-band


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 Program: Echo

American experimental telecommunication program

External resources

http://sulu.lerc.nasa.gov/dglover/echo.html


Program: Echo

Echo 1

Echo 2


 Echo 1

Also called Echo 1A because the first Echo had a launch failure

General

Designation	00049 / 60009A
Launch date	12 Aug 1960
Country of origin	United States
Mission	Telecommunications and geodesy
Perigee/Apogee	966/2157 km
Inclination	47.3°
Period	117.3 min
Launch vehicle	Thor Delta #2
Mass at launch	61 kg

Plastic 30.5 m ball covered of mylar aluminumed that reflected radioelectric signals.

It enabled the first satellite telephone link and the broadcast of a TV program from California to Massachussets on 24 Feb 1962.

End of life

Decay	24 May 1968


 Echo 2

General

Designation	00740 / 64004A
Launch date	25 Jan 1964
Country of origin	United States
Mission	Telecommunications and geodesy
Perigee/Apogee	1030/1315 km
Inclination	81.5°
Period	108.8 min
Launch vehicle	Thor Agena
Launch site	Vandenberg
Mass at launch	256 kg

Plastic 41 m ball covered 2 aluminum sheets with a mylar sheet in between.

End of life

Decay	7 Sep 1969


 Program: Echostar

American DBS program operated by EchoStar. The system broadcasts the DISH (Digital Sky Highway).

The FCC granted EchoStar an extension of its satellite construction permit, and granted EchoStar subsidiary DirectSat an extension until Aug. 15, 1999, for construction and launch of its satellites to be located at 119 degrees and 175 degrees west longitude.

Echostar controls frequency allocations at 61.5, 119, 148 and 175 degrees West longitude (90 transponders of DBS spectrum).  Echostar has the 121°W & 83°W slots reserved for non-DBS Ku-band and Ka-band. Echostar also bought the license and satellites for 110°W.

External resources

http://www.dishnetwork.com

Echostar should launch 2 Ka-band satellites after the May 1997 FCC approval (83 & 121°W). Each satellite would have 48 transponders, with narrow and wide spot beams. It would have on-board signal processing and on-board switching. Maximum EIRP: 63 dBW

Downlink: 19.7-20.2 GHz; Uplink: 29.5-30.0 GHz band


Program: Echostar

Echostar 1

Echostar 2

Echostar 3

Echostar 4

Echostar 5

Echostar 6


 Echostar 1

General

Designation	23754 / 95073A
Launch date	28 Dec 1995 at 11:50 UT
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	119.2°W
Launch vehicle	Long March 2E
Technical data

Specifications

Prime contractor	Lockheed Martin Astro Space
Platform	GE 7000
Mass at launch
Mass in orbit
Dimension	4.08 x 2.22 x 2.54 m?
Solar array	24.5 m span?
Stabilization	3-axis
DC power	BOL: 6400 W? EOL: 5000 W?
Design lifetime	12 or 15 years

Telemetry in the C-band

Ku-band

Main transponders	16
Backup transponders
Power	130 W
Bandwidth	24 MHz
Coverage & EIRP max	CONUS only: 53 dBW (US Virgin Island: 1.8 m dish)
Polarization	RHCP
Frequencies	uplink: 17.3-17.8 GHz downlink: 12.2-12.7 GHz


 Echostar 2

General

Designation	24313 / 96055A
Launch date	11 Sep 1996
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	118.8°W
Launch vehicle	Ariane V91

Launch opportunities had been reserved with Long March and Proton but finally after the numerous launch problems, Echostar choose Ariane for launch.

The total satellite, launch and insurance are estimated at $225 million The satellite entered service on 1st Nov 1996.

The channels used by this satellite were originally licensed to Directsat Corp. This entity was transfered from SSE Telecom to Echostar in Nov 1994. Directsat was licensed to provide 11 channels of eastern half-CONUS or full-CONUS DBS service on even-numbered channels 2-20, at orbital position 119° West and on channel 24 at orbital position 110°West, and 11 channels of western half-CONUS service on odd-numbered channels 1-21 at orbital position 175°West.

Technical data

Specifications

Prime contractor	LM Astro Space
Platform	GE 7000
Mass at launch	2800 kg
Mass in orbit
Dimension
Solar array
Stabilization	3-axis
DC power
Design lifetime	10 years
Ku-band

Main transponders	16
Backup transponders
Power	130 W
Bandwidth	24 MHz
Coverage & EIRP max	CONUS only: 53 dBW (US Virgin Island: 1.8 m dish)
Polarization	LHCP
Frequencies	uplink: 17.3-17.8 GHz downlink: 12.2-12.7 GHz


 Echostar 3

Also called DBSC 1

General

Designation	25004 / 97059A
Launch date	4 Oct 1997
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	61.5°W
Launch vehicle	Atlas 2AS #110

This satellite was originaly ordered by DBSC (Direct Broadcast Satellite Corporation) which merged with a subsidiary of Echostar in late 1995. The merger was approved by the FCC in August 1996.

Echostar is only authorized to operate 11 transponders from 61.5°W but was granted in Mar 1998 a special authorization to use the full frequency space at that location.

In May 1999, Dominion Video Satellite, Inc. leased 8 transponders from this satellite and Echostar subleased 6 transponders back to propose additional channels.

Technical data

Specifications

Prime contractor	LM Astro Space
Platform	Astro Space A2100AX
Mass at launch	3675 kg
Mass in orbit	1700 kg
Dry mass	1325 kg
Dimension
Solar array
Stabilization	3-axis
DC power
Design lifetime	13.5 years
Ku-band

Main transponders	32
Backup transponders
Power	120 W
Bandwidth	24 MHz
Coverage & EIRP max	Eastern part of CONUS: 53 dBW
Polarization	circular
Frequencies	uplink: 17.3-17.8 GHz downlink: 12.2-12.7 GHz

Was to operate in double power mode (16 transponders at 240 W) but this feature failed.

In Oct 1998 Echostar announced they had lost 4 TWTAs on this satellite, it is expected that more transponders could fail. There is a risk that such failures are not covered by insurance.


 Echostar 4

General

Designation	25331 / 98028A
Launch date	7 May 1998
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Proton #258
Location

Begin	End	Position
L: 7 May 1998	end of tests	127°W (mexican DBS slot)
end of tests	Jun 1999	148°W
mid Jul 1999		110°W

The satellite should have replaced Echostar 1 at 119°W which would then have moved to 148°W (where only 24 transponders have been granted to Echostar)  After launch, the satellite has experienced anomalies in connection with solar panel deployment (two of five panels on one solar array have not unfolded). Several transponders are not operational. As a result, Echostar 4 did not replace Echostar 1. In Jul 1999 furthen anomalies with the heating and fuel systems were reported.

The satellite was insured for $220 million. The FCC licence for 148°W costed $52 million. Echostar has filled for constructive total loss of the satellite.

In Jun 1999 the FCC approved a move request to 110°W to allow Echostar to start broadcasting from there. Earlier the FCC granted to transfer of the 110°W licence of MCI to Echostar. Echostar is allowed to use channels 1 - 31 (odd) and 2 - 26 (even). When Echostar 5 is launched, this satellite will return to 148°W.

Technical data

Specifications

Prime contractor	LM
Platform	A2100AX
Mass at launch	3700 kg
Mass in orbit
Dry mass	1325 kg
Dimension
Solar array
Stabilization	3-axis
DC power
Design lifetime	15 years

Has a Leros liquid apogee engine

Telemetry and command: 12.2005 GHz, 12.2025 GHz, 12.6985 GHz and 17.308 GHz, with a 300 kHz bandwidth

Ku-band

Main transponders	32
Backup transponders
Power	120 W
Bandwidth	24 MHz
Coverage & EIRP max	Western part of CONUS: 53 dBW: 53 dBW Alaska Hawaii
Polarization	circular
Frequencies	uplink: 17.3-17.8 GHz downlink: 12.2-12.7 GHz

Transponders can be dual-combined (16 x 240 W)


Echostar 5 & 6's specifications (previously Sky)

Prime contractor	Space Systems/Loral
Platform	FS-1300
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization
DC power	7500 W
Design lifetime	12 years


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Echostar 5 & 6's Ku-band (previously Sky)

Main transponders	32
Backup transponders
Power	110 W (125 W for Echostar 6)
Bandwidth
Coverage	United States, Hawaii, Alaska and Puerto Rico
EIRP max
Polarization

Transponders can by dual combined to provide double power.


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 Echostar 5

Also known as Sky 1

General

Designation
Launch date	initially planned in late 1997
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	110°W
Launch vehicle	Atlas 2AS
Launch site

Echostar 5 & 6 were originally known as Sky 1 & 2 or MCI 1 & 2. They were intended to start DBS programming at 110°W for the MCI-News corp. venture called American Sky Broadcasting (ASkyB). They got the slot with a $682.6 million bid. The program including satellites and launch delivered in orbit and uplink facilities was valued between $400 and $500. Each satellite was insured for $225 million.

In early 1999 the satellites (and launch, and uplink center, and license for construction and distribution of 500000 receivers) and the licence for 110°W was sold to Echostar. This also included 3 years of Fox rebroadcast. Echostar payed with approx 37% of its equity (this represents 8.5% of voting power). Contract worth $1.25 billion.

Technical data

Specifications

Ku-band


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 Echostar 6

Also called MCI 1

General

Designation
Launch date	initially planned in early 1998
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	110°W
Launch vehicle	Proton
Launch site
Technical data

Specifications

Ku-band


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 Program: Ellipsat

Mobile satellite phone project with 2 types of satellites. Has been licensed by the FCC

Overview

Name	Borealis	Concordia
Orbit type	HEO	MEO
Orbit range	520/7846 km, elliptic	8040 km, circular
Nb of satellites	10	6
Nb of planes	2	1
Inclination	116.5°	0°
Nb beams per satellite	61	61
Coverage	11980 km²	11980 km²
Modulation	CDMA	CDMA
Mobile frequencies	Uplink: 1610 - 1626.5 MHz Downlink: 2483.5 - 2500 MHz	Uplink: 1610 - 1626.5 MHz Downlink: 2483.5 - 2500 MHz
Satellite mass	690 kg	880 kg
Coverage	all longitudes, 70N - 20S latitudes	all longitudes, 70N - 20S latitudes
Operational date	1999 (planned)	1999 (planned)

satellites to gateways: 6875 - 7075 MHz

gateways to satellites: 15.45 - 15.65 GHz

To be operated by Mobile Communications Holdings Inc. Boeing invested $200 million in the project. Other investors include Lockheed Martin Global Telecommunications, the Harris Corporation, L-3 Communications and Israel Aircraft Industries.

Boeing is the system integrator for design, development, construction and deployment of Ellipso. The estimated contract value is over $1.4 billion. First satellite launch expected in 2001. System operational in 2002.

The satellites would be arrayed in five orbital planes in two sub-constellations. Three planes of five satellites each will be placed in inclined elliptical orbits for Northern Hemisphere coverage. A fourth plane of six satellites will be launched into circular equatorial orbits and another five satellites in elliptical equatorial orbit.

ITU has provided the international telephone codes 881 2 & 881 3. Ellipso has also got approval to use the share mobile code 901 07.

Arianespace has signed a MoU for 4 Ariane 5 launches and financing services. First launch in 2002. Those satellites will be placed on the concordia orbit.

A second network named Ellipso 2G is planned. It will have 26 non-geostationary satellites to operate in 2 GHz band. The project is subject to FCC approval. Planned for 2003

External resources

http://www.ellipso.com


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 Envisat

General

Designation
Launch date	initially planned in 1999
Country of origin	Europe
Mission	Remote sensing (to replace ERS)
Perigee/Apogee	~800 km
Inclination
Period
Launch vehicle	Ariane 5
Launch site

The cost is covered at 24.5% by France, 18.5% by the UK and 17.5 % by Germany. The total program (satellite, launch and exploitation) is over 11.8 billion francs

External resources

http://envisat.estec.esa.nl/

http://www.dfd.dlr.de/PROJECT/ENVISAT/Index/

Technical data

Specifications

Prime contractor	Dornier or MMS?
Platform
Mass at launch	8093 kg
Mass in orbit
Payload mass	2200 kg
Dimension	26 m x 10 m x 5 m
Solar array	(weighs 400 kg)
Stabilization
DC power	6500 W
Design lifetime

4 on-board recorders provide 30 Gbits storage. Inter orbit link in Ka-band will be possible with Artemis (another ESA satellite which could be launched in 1999 via H2)

10 scientific payloads

ASAR (radar imaging, 27 m resolution)

GOMOS (ozone layer study)

AATSR (radiometer)

MWR (microwave radiometer)

MERIS (visible and near IR imaging)

MIPAS (atmospheric probe)

SCIAMACHY (atmospheric cartography spectrometer)

RA-2 (radar altimeter)

DORIS (orbitography)

LRR (laser reflectors)

The French Scarab experiment was withdrawn


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 EO 1

Earth Orbiter 1

General

Designation
Launch date	initially planned in 1999
Country of origin	United States
Mission
Operator	NASA
Perigee/Apogee	705 km sun synchronous
Inclination	98.7°
Period
Launch vehicle	Taurus
Launch site

The first of three New Millennium Program Earth orbiting missions. EO 1 is an advanced land imaging mission that will demonstrate new instruments and spacecraft systems. EO 1 will validate technologies contributing to the reduction in cost of follow-on Landsat missions. The centerpiece of this mission is the Advanced Land Imager (ALI) instrument, which is one seventh the mass, power consumption and volume of the Landsat 7 imager.

It will match within one minute the Landsat 7 orbit and collect identical images for later comparison.

External resources

http://eo1.gsfc.nasa.gov/

Technical data

Specifications

Prime contractor	Swales Aerospace
Platform
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime	5 years
ALI (Advanced Land Imager)

The ALI instrument will feature ten-meter ground resolution in the panchromatic (black-and-white) band and 30-meter ground resolution in its other spectral bands, using a four-chip multispectral focal plane array that covers seven of the eight bands of the current Landsat.

AC (Atmospheric Corrector)

The instrument will provide the first space-based test of an Atmospheric Corrector for increasing the accuracy of surface reflectance estimates. The AC enables more precise predictive models to be constructed for remote sensing applications. It will provide significant improvements in generating accurate reflectance measurements for land imaging missions.

Hyperion

The Hyperion provides a science grade instrument with quality calibration based on heritage from the Lewis Hyperspectral Imaging Instrument. The Hyperion capabilities provide resolution of surface properties into hundreds of spectral bands versus the ten multispectral bands flown on traditional Landsat imaging missions. Through this large number of spectral bands, complex land eco-systems shall be imaged and accurately classified. The Hyperion provides a high-resolution hyperspectral imager and can image detailed spectral mapping across all 220 channels with high radiometric accuracy.


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 Eole

Known as CAS 1 (Cooperative Applications Satellite) at NASA

General

Designation	05435 / 71071A
Launch date	16 Aug 1971
Country of origin	France
Mission	Scientific: high atmosphere study
Perigee/Apogee	651/835 km
Inclination	50.2°
Period	99.7 min
Launch vehicle	Scout #75
Mass at launch	80 kg

Meteorological experimental satellite aimed to study wind in the southern hemisphere. Eole destroyed 89 out of 479 balloons it interrogated because of a human error. When all balloons had disappeared it was used to study oceans currents, iceberg movements, etc.

End of life

Out of service	July 1974


Eorsat
 Program: Eorsat

Electronic Ocean Reconnaissance Satellite

Russian program part of the Cosmos constellation. Those satellites are observation satellites designed to monitor activity of foreign navies.

The series started in 1974 and around 40 satellites had been launched in mid-1995. The system went operational in 1978.

First generation

Cosmos 0699	Cosmos 0777	Cosmos 0838	Cosmos 0868	Cosmos 0937	Cosmos 1094
Cosmos 1096	Cosmos 1167	Cosmos 1220	Cosmos 1260	Cosmos 1286	Cosmos 1306
Cosmos 1337	Cosmos 1355	Cosmos 1405	Cosmos 1461	Cosmos 1507	Cosmos 1567
Cosmos 1588	Cosmos 1625	Cosmos 1646	Cosmos 1682	Cosmos 1735	Cosmos 1737
Cosmos 1769	Cosmos 1890	Cosmos 1949	Cosmos 1979	Cosmos 2033	Cosmos 2046
Cosmos 2051	Cosmos 2060	Cosmos 2096	Cosmos 2103	Cosmos 2107	Cosmos 2122 (decayed)
Cosmos 2238	Cosmos 2244	Cosmos 2258 (decayed)	Cosmos 2264	Cosmos 2293	Cosmos 2313
Cosmos 2326	Cosmos 2335	Cosmos 2347
Second generation

Cosmos 1867 (800 km, 65°, Topaz)	Cosmos 1818 (800 km, 65°, Topaz)
Technical data

Specifications

Prime contractor	NPO Machinostroenie
Platform
Mass at launch
Mass in orbit
Length
Width
Height
Perigee/Apogee	400 km
Inclination	65°
Period	92 min
Stabilization
DC power
Design lifetime	1.5 years

It uses a low thrust engine to maintain its orbit.


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 Program: EOS

Earth Observing System

The Earth Observing System is a multi-mission program with the objective of acquiring the geophysical, chemical, and biological information necessary for intense study of planet Earth.  A scientific research effort is underway to ensure that the planning and execution of the mission fulfills its intended purpose. An EOS data and information system will build up over 10 years and then function for at least 20 years to allow accurate modeling of the processes that control the environment.

The Earth Observing System (EOS) program involves the operation of numerous instruments on multiple spacecraft placed in polar and mid-inclination orbits in support of multiple disciplines within the Earth science user community.  The EOS mission is composed of several series of flights beginning with the EOS AM-1 flight from the AM series in 1998.  The other EOS series include PM, LALT (Laser Altimetry), and CHEM (Chemistry) flights.  Each spacecraft with exception of LALT has a projected lifetime of 5 years with operational goal of 6 years.  The Canadian Space Agency (CSA), the European Space Agency (ESA) and the Ministry of International Trade Industry (MITI) of Japan are planning Earth observing missions that complement the National Aeronautics and Space Administration (NASA) program.   In addition, they are also supplying instruments on selected EOS flights.

External resources

http://eospso.gsfc.nasa.gov/


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Program: EOS

EOS AM

EOS PM-1

EOS Chemistry 1


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 EOS AM

Renamed Terra

General

Designation
Launch date	initially planned in 1998
Country of origin	United States
Mission	Scientific Remote sensing
Perigee/Apogee	705 km, sun-synchronous (descending node: 10:30)
Inclination	98.2°
Period	100 min
Launch vehicle	Atlas 2AS
Launch site

Terra simultaneously will study clouds, water vapor, small particles in the atmosphere called "aerosol" particles, trace gases, land surface and oceanic properties, as well as the interaction between them and their effect on the Earths energy budget and climate. Moreover, Terra will observe changes in the Earths radiation energy budget, together with measurements of changes in land/ocean surface and interactions with the atmosphere through exchanges of energy, carbon and water.

External resources

http://terra.nasa.gov/

http://eos-am.gsfc.nasa.gov/

Technical data

Specifications

Prime contractor	Lockheed Martin
Platform
Mass at launch	5200 kg
Mass in orbit
Paylaod mass	1100 kg
Dimension
Solar array
Stabilization	3-axis
DC power	7500 W
Design lifetime

The 45 m² solar array will use 36,480 advanced gallium arsenide germanium (GaAs/Ge) and weigh 73 kg

Operates at 2, 13 and 15 GHz

Acquisition via TDRS

Telemetry: 2287.5 MHz

Command: 2106.4 MHz

Data: 15003.4 MHz (upto 150 Mbps)

ASTER (Advanced Spaceborne Thermal Emission and Reflection Radiometer)

ASTER provides high-resolution images of the land surface, water, ice, and clouds using three separate sensor subsystems covering 14 multi-spectral bands from visible to thermal infrared. The significant resolution scales are 15m, 30m, and 90m in the visible, short-wave IR, and thermal fR, respectively.

CERES (Clouds and the Earths Radiant Energy System)

CERES measures Earth's radiation budget and atmospheric radiation from the top of the atmosphere using a broadband scanning radiometer with bolometers detectors.

MISR (Multi-Angle Imaging Spectroradiometer)

MISR measures top-of-atmosphere, cloud and surface angular reflectance functions, and measures surface BRDF, aerosol, and vegetation properties using four spectral bands in each of nine pushbroom imaging cameras oriented at different angles along-track. The detectors are CCDS, the filters are interference qw.

MODIS (Moderate-Resolution Imaging Spectroradiometer)

MODIS measures biological and physical processes on land and the ocean using a cross-track scanning multi-spectral radiometer with 36 spectral bands from visible to thermal infrared. Detector cooling is through a passive radiant cooler, and filters are interference type.

MOPITT (Measurements of Pollution In The Troposphere)

MOPITT measures carbon monoxide and methane in the troposphere using correlation spectroscopy with pressure modulated and length modulated gas cells. Detectors are cooled using a Stirling Cycle mechanical cooler.


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 EOS PM-1

General

Designation
Launch date	initially planned in 2000
Country of origin	United States
Mission	Scientific
Perigee/Apogee	705 km (sunsynchronous)
Inclination	98.2°
Period	100 min
Launch vehicle
Launch site

Contracted together with EOS Chemistry 1 for $398 million; an option on two more crafts could amount the total to $668 million

External resources

http://mtpe.gsfc.nasa.gov/eos-pm1/PM1PROJ1.htm

Technical data

Specifications

Prime contractor	TRW
Platform	AM1200 EOS commun spacecraft bus
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization	3-axis
DC power
Design lifetime	6 years

Acquisition via TDRS

Telemetry: 2287.5 MHz

Command: 2106.4 MHz

Data: 15003.4 MHz (upto 150 Mbps)


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 EOS Chemistry 1

General

Designation
Launch date	initially planned in 2002
Country of origin	United States
Mission	Scientific
Perigee/Apogee
Inclination
Period
Launch vehicle
Launch site

Contracted together with EOS PM-1 for $398 million; an option on two more crafts could amount the total to $668 million

Technical data

Specifications

Prime contractor	TRW
Platform	AM1200 EOS commun spacecraft bus
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime


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 Equator S

General

Designation	25068 / 97075B
Launch date	2 Dec 1997
Country of origin	Germany
Mission	Observation of magnetosphere
Perigee/Apogee	500 / 63700 km
Inclination	4°
Period
Launch vehicle	Ariane V103

The satellite is a small version (therefore Equator S) of an equatorial spacecraft originally planned by NASA for the International Solar-Terrestrial Physics program, but later abandonned.

Will be measuring the effects of the solar winds on our planet's magnetic and electrical fields.

Satellite cost: $12 million

NASA & ESA contribution

External resources

http://www.go-ariane.com/main/feat/feat_18.html

http://www-istp.gsfc.nasa.gov

Technical data

Specifications

Prime contractor	Max Plank Institute (Germany)
Platform
Mass at launch	230 kg
Mass in orbit
Dimension
Solar array
Stabilization	spin-stabilized (60 rpm)
DC power
Design lifetime

Carries 8 experiments. Has a GPS receiver. On-board data storage: 192 Mo


 ERBS

Earth Radiation Budget Satellite, also called SAGE 2

General

Designation	15354 / 84108B
Launch date	5 Oct 1984
Country of origin	United States
Mission	Scientific: high atmosphere study
Perigee/Apogee	582/593 km
Inclination	57°
Period	96.4 min
Launch vehicle	STS 17
Mass at launch	147 kg

Part of a NASA Earth Radiation Budget Experiment (ERBE) to measure radiation emitted by the Earth and the effect of a solar radiation incident on the Earth.

External resources

http://www.ngdc.noaa.gov/stp/SOLAR/IRRADIANCE/erbs.html

Technical data

Specifications

Prime contractor	Ball
Mass at launch	2300 kg
Length	1.6 m
Height	3.8 m
Solar array	7 m span
Stabilization	3-axis

A 180 degree yaw maneuver is performed approximately every 5 weeks to keep sun on the solar arrays.

Payload: 2 radiometers and SAGE 2 (Stratospheric Aerosol and Gas Experiment) to monitor vertical distribution of aerosols, ozone and carbone dioxide in the stratosphere.

Telemetry and data via TDRS (S-band).


 Program: Eros

Remote sensing satellite program operated by West Indian Space Ltd., a US-Israeli joint-venture. Partners include Core Software Technology (US), Israel Aircraft Industries IAI (state-owned by Israel) and El-Op Electro-Optic Industries (Israel). The company announced it would issue bonds via a private placement that would help finance the US$250 million they need to launch and operate their first three satellites.

First satellite planned in late 1999. WIS plans to launch the second satellite by September 2000 and the third about nine months later. Subsequently, two satellites will be launched each year, indefinitely depending on demand, with the first eight deployed by 2004. A total of 8 satellites are planned. 3 launches have been reserved on Start 1

First satellite: 1.8 m resolution, the following will have 82 cm resolution; 12.5 km swath width

IAI will be the prime contractor. No onboard recording, all the data must be downloaded in realtime by earth stations.


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Program: Eros

Eros A


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 Eros A

Also called Eros A+

General

Designation
Launch date	planned in late 1999
Country of origin	Israel
Mission	Remote sensing
Perigee/Apogee
Inclination
Period
Launch vehicle	Start 1
Launch site	Plesetsk
Technical data

Specifications

Prime contractor	IAI
Platform
Mass at launch	250 kg
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime

Resolution: 1.2 m

Swath width: 12.5 m


ERS
 Program: ERS

European Remote Sensing satellite

European remote sensing program designed to provide images of the Earth in the microwave spectrum. Primary objectives of the multi-mission payload are in oceanographic science: ocean current patterns, wind velocity, ice coverage, etc. The radar payload allows observations through cloud and darkness.


Program: ERS

ERS 1

ERS 2


 ERS 1

General

Designation	21574 / 91050A
Launch date	17 Jul 1991
Country of origin	Europe
Mission	Remote sensing
Perigee/Apogee	768/769 km
Inclination	98.5°
Period	100.2 min
Orbital cycle	3, 35 and 176 days
Launch vehicle	Ariane V44

ESA's first remote sensing satellite. Cost: $500 million

Since early 1994 the satellite transmits with the backup travelling wave tube because the primary one failed.

Technical data

Specifications

Prime contractor	Dornier
Platform	MMS Spot (Mark 1)
Mass at launch	2400 kg
Payload mass	1100 kg
Dry mass	2080 kg
Length	11.8 m
Solar array	11.7 x 2.4 m
SAR antenna	10 x 1 m
Radar altimeter	1.2 m (diameter)
Stabilization	3-axis
DC power	2500 W
Design lifetime	3 years
AMI (Active Microwave Instrument)

Frequency	5.3 GHz (C-band)
SAR resolution	26 m
SAR swath width	99 km
Scatterometer resolution	47 km
Scatterometer swath width	613 km (fore and aft) 809 km (mid)

Mission: payload all-weather high-resolution images of land and ocean, windspeed and direction, ice mapping, pollution monitoring.

RA (Radar Altimeter)

Frequency	13.8 GHz (Ku-band)
Accuracy (wave height)	+/- 0.5 m
Altitude accuracy	0.1 m

Mission: windspeed and sea surface elevation, ice sheet topography.

ATSR (Along-Track Scanning Radiometer)

Wavelengths	1.6, 3.7, 10.8 and 12.0 µm
Accuracy (sea surface temperature)	+/- 0.5 K

Mission: images of sea surface temperature, total water vapour content of atmosphere, cloud, aerosols, haze, land and ice surface emissivity.

Microwave Sounder

Frequency	23.8 and 36.5 GHz
Altitude accuracy	0.02 m
Telemetry/data	S-band

Also equipped with Laser Reflectometer (LR), Precise Range and Range-rate Equipment (PRARE) and Instrument Data Handling and Transmission (IDHT).


 ERS 2

General

Designation	23560 / 95021A
Launch date	21 Apr 1995
Country of origin	Europe
Mission	Remote sensing
Perigee/Apogee	783/786 km
Inclination	98.6°
Period	100.5 min
Launch vehicle	Ariane V72

Cost: FF3.1 billion including FF2 billion for the satellite. The launch was not insured

Technical data

Specifications

Prime contractor	Dornier
Platform	MMS Spot (Mark 1)
Mass at launch	2500 kg
Payload mass	1100 kg
Dry mass	2080 kg
Length	11.8 m
Solar array	11.7 x 2.4 m
SAR antenna	10 x 1 m
Radar altimeter	1.2 m (diameter)
Stabilization	3-axis
DC power	2500 W
Design lifetime	3 years
AMI (Active Microwave Instrument)

Frequency	5.3 GHz (C-band)
SAR resolution	26 m
SAR swath width	99 km
Scatterometer resolution	47 km
Scatterometer swath width	613 km (fore and aft) 809 km (mid)

Mission: payload all-weather high-resolution images of land and ocean, windspeed and direction, ice mapping, pollution monitoring.

RA (Radar Altimeter)

Frequency	13.8 GHz (Ku-band)
Accuracy (wave height)	+/- 0.5 m
Altitude accuracy	0.1 m

Mission: windspeed and sea surface elevation, ice sheet topography.

ATSR (Along-Track Scanning Radiometer)

Wavelengths	1.6, 3.7, 10.8 and 12.0 µm
Accuracy (sea surface temperature)	+/- 0.5 K

Mission: images of sea surface temperature, total water vapour content of atmosphere, cloud, aerosols, haze, land and ice surface emissivity.

Microwave Sounder

Frequency	23.8 and 36.5 GHz
Altitude accuracy	0.02 m
GOME (Global Ozone Monitoring Experiment)

Waveband	0.24-0.79 µm
Resolution	40 x 40 km max. (horizontal) 1 km (vertical)
Swath width	120-960 km

Mission: stratospheric and tropospheric ozone profiles, cloud distribution and surface spectral reflection.

Also equipped with Laser Reflectometer (LR), Precise Range and Range-rate Equipment (PRARE) and Instrument Data Handling and Transmission (IDHT). The on board tape recorder (6.5 gigabit) can store data from a full orbit.

The telemetry is sent in S-band. The scientific data and a replication of the telemetry is sent on 2 X-band transponders.


 ESA-Geos 1

General

Designation	09931 / 77029A
Launch date	20 Apr 1977
Country of origin	Europe
Mission	Scientific: magnetosphere study
Perigee/Apogee	2767/38389 km
Inclination	26.8°
Period	734.1 min
Launch vehicle	Thor Delta #130
External resources

http://www.esoc.esa.de/external/mso/geos.html


 ESA-Geos 2

General

Designation	10981 / 78071A
Launch date	14 Jul 1978
Country of origin	Europe
Mission	Scientific: magnetosphere study
Perigee/Apogee	36020/36061 km
Inclination	11.8°
Period	1449.1 min
Launch vehicle	Thor Delta #143
External resources

http://www.esoc.esa.de/external/mso/geos.html


 Program: Esro

European Science Research Organisation

First European scientific program

External resources

http://www.esoc.esa.de/external/mso/esro.html


Program: Esro

Esro 1A

Esro 1B

Esro 2B

Esro 4


 Esro 1A

Also called Aurorae

General

Designation	03459 / 68084A
Launch date	3 Oct 1968
Country of origin	Europe
Mission	Scientific: ionosphere study
Perigee/Apogee	258/1538 km
Inclination	93.8°
Period	103 min
Launch vehicle	Scout #65
Mass at launch	86 kg

Aimed to study auroras and involved phenomenons.

End of life

Decay	26 Jun 1970


 Esro 1B

Also called Boreas

General

Designation	04114 / 69083A
Launch date	1 Oct 1969
Country of origin	Europe
Mission	Scientific: ionosphere study
Perigee/Apogee	298/378 km
Inclination	85°
Period	91.3 min
Launch vehicle	Scout #66
Mass at launch	85 kg

Aimed to study auroras and involved phenomenons.

End of life

Decay	23 Nov 1969


 Esro 2B

Also called Iris

General

Designation	03233 / 68041A
Launch date	17 May 1968
Country of origin	Europe
Mission	Scientific: ionosphere study
Perigee/Apogee	334/1085 km
Inclination	97.2°
Period	99 min
Launch vehicle	Scout #62
Mass at launch	86 kg

Aimed to study cosmic rays, solar X-rays and the radiation belts around the Earth.

End of life

Decay	8 May 1971


 Esro 4

General

Designation	06285 / 72092A
Launch date	22 Nov 1972
Country of origin	Europe
Mission	Scientific: ionosphere study
Perigee/Apogee	245/1173 km
Inclination	91.1°
Period	99 min
Launch vehicle	Scout #82
Mass at launch	115 kg

Study of ionosphere, auroras and solar particles.

End of life

Decay	15 Apr 1974


 Program: Essa

Environmental Science Service Administration

American meteorology program. The satellites of this program are evolved Tiros with better surface resolution.

External resources

http://www.met.fsu.edu/explores/Guide/essaindex.html


Program: Essa

Essa 1

Essa 2

Essa 3

Essa 4

Essa 5

Essa 6

Essa 7

Essa 8

Essa 9


 Essa 1

General

Designation	01982 / 66008A
Launch date	3 Feb 1966
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	684/805 km
Inclination	97.8°
Period	99.7 min
Launch vehicle	Thor Delta #36
Mass at launch	138.6 kg


 Essa 2

General

Designation	02091 / 66016A
Launch date	28 Feb 1966
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	1352/1412 km
Inclination	101°
Period	113.4 min
Launch vehicle	Thor Delta #37


 Essa 3

Also called TOS A

General

Designation	02435 / 66087A
Launch date	2 Oct 1966
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	1383/1484 km
Inclination	101°
Period	114.5 min
Launch vehicle	Thor Delta #41


 Essa 4

Also called TOS B

General

Designation	02657 / 67006A
Launch date	26 Jan 1967
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	1323/1437 km
Inclination	102°
Period	113.4 min
Launch vehicle	Thor Delta #45


 Essa 5

Also called TOS C

General

Designation	02757 / 67036A
Launch date	20 Apr 1967
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	1352/1419 km
Inclination	101.9°
Period	113.5 min
Launch vehicle	Thor Delta #48


 Essa 6

Also called TOS D

General

Designation	03035 / 67114A
Launch date	10 Nov 1967
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	1406/1483 km
Inclination	102.2°
Period	114.8 min
Launch vehicle	Thor Delta #54


 Essa 7

Also called TOS E

General

Designation	03345 / 68069A
Launch date	16 Aug 1968
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	1429/1470 km
Inclination	101.5°
Period	114.9 min
Launch vehicle	Thor Delta #58


 Essa 8

Also called TOS F

General

Designation	03615 / 68114A
Launch date	15 Dec 1968
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	1411/1461 km
Inclination	101.8°
Period	114.6 min
Launch vehicle	Thor Delta #62


 Essa 9

Also called TOS G

General

Designation	03764 / 69016A
Launch date	26 Feb 1969
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	1423/1502 km
Inclination	101.4°
Period	115.2 min
Launch vehicle	Thor Delta #67


 Program: ETS

Engineering Test Satellite, also called Kiku which means "chrysanthemum"

Primary purpose of the Japanese ETS is to develop and prove bus technology. Operated by NASDA

External resources

http://www.goin.nasda.go.jp/GOIN/NASDA/act/ets.html


Program: ETS

ETS 1

ETS 2

ETS 3

ETS 4

ETS 5

ETS 6

ETS 7

ETS 8


 ETS 1

Also called Kiku 1

General

Designation	08197 / 75082A
Launch date	9 Sep 1975
Country of origin	Japan
Mission
Perigee/Apogee	976/1103 km
Inclination	47°
Period	106 min
Launch vehicle	N1
Mass at launch	82.5 kg


 ETS 2

Also called Kiku 2

General

Designation	09852 / 77014A
Launch date	23 Feb 1977
Country of origin	Japan
Mission	Telecommunications
Geostationary orbit
Launch vehicle	N1
End of life

Out of service	yes


 ETS 3

Also called Kiku 4

General

Designation	13492 / 82087A
Launch date	3 Sep 1982
Country of origin	Japan
Mission	Telecommunications, experimental
Perigee/Apogee	966/1226 km
Inclination	44.6°
Period	107.2 min
Launch vehicle	N1


 ETS 4

Also called Kiku 3

General

Designation	12295 / 81012A
Launch date	11 Feb 1981
Country of origin	Japan
Mission
Perigee/Apogee	240/20680 km
Inclination	28.2°
Period	362.4 min
Launch vehicle	N2


 ETS 5

Also called Kiku 5

General

Designation	18316 / 87070A
Launch date	27 Aug 1987
Country of origin	Japan
Mission	Telecommunications
Geostationary orbit	150°E, inclined
Launch vehicle	H1

First 3-axis stabilized Japanese satellite with a built in apogee kick motor. It also carried a experimental mobile communications payload.

End of life

Out of service	mid-Oct 1997
Cause	deorbited
Technical data

Specifications

Prime contractor	Mitsubishi Electric
Platform	Mitsubishi
Mass at launch	1081 kg
Mass in orbit	550 kg
Length	3 m
Width	2.8 m
Height	2 m
Stabilization	3-axis
Design lifetime	1.5 years
L-band

Transponders	2
Power	30 W
Bandwidth	10 MHz
Coverage	Northern Pacific including Philippines, Indonesia and Australia
EIRP max	23.2 dBW
Polarization
C-band

Transponders	1
Power	6 W
Bandwidth	20 MHz
Coverage	Northern Pacific (used for a link to NASDA)
EIRP max
Polarization


 ETS 6

Also called Kiku 6

General

Designation	23230 / 94056A
Launch date	28 Aug 1994 at 22:10 UT
Country of origin	Japan
Mission	Telecommunications, experimental
Geostationary orbit	was expected in 153.8°E slot
Launch vehicle	H2

Was designed to demonstrate amongst other things ion propulsion and liquid bi-propellant GEO orbit insertion. The payload would have supported mobile communications and inter satellite communication at radio and laser frequencies in preparation for Data Relay and Tracking Satellite systems.

In mid-1995 it was reported than successful intersatellite communication had taken place with UARS Later in early 1996 bidirectionel laser communications between JPL and the satellite were carried out.

End of life

Out of service	28 Aug 1994
Cause	Unable to reach GEO: a valve controlling the ergol input in the apogee kick motor (LAPS) was blocked
Technical data

Specifications

Prime contractor	Toshiba
Platform	Mitsubishi
Mass at launch	3800 kg
Mass in orbit	2000 kg
Dimension	3.0 x 2.0 x 2.8 m
Solar array	30 m span
Stabilization	3-axis
Design lifetime	2 years
S-band

Main transponders	1
Power	100 W
Bandwidth	20 MHz forward/10 MHz return
Coverage	5 spot beams
EIRP max	31.5 dBW
Polarization
C-band

Main transponders	4
Power	8 W
Bandwidth	35 MHz
Coverage
EIRP max	35 dBW
Polarization
Ka-band (20/30 GHz)

Main transponders	6
Power	10 W (TWTA)
Bandwidth	120 MHz forward/30 MHz return
Coverage
EIRP max	48 dBW
Polarization
O-band (38/43 GHz)

Main transponders	1
Power	10 W (TWTA)
Bandwidth
Coverage
EIRP max
Polarization


 ETS 7

Also called Kiku 7, the two units are called Orihime and Hikoboshi

General

Designation	25064 / 97074B
Launch date	27 Nov 1997
Country of origin	Japan
Mission	Experimental
Perigee/Apogee	550 km
Inclination	35°
Period
Launch vehicle	H2 #5

ETS 7 is composed of a chase satellite and a target satellite. Its objectives are to carry out experiments to confirm the basic technologies for rendezvous-docking and space robotics. It will enable future Japanese supply missions to dock reliably with the International Space Station.

Success in orbit will be reliant on an internal navigation system which contains three sensors. A GPS receiver will be used to compute the relative positions and speeds of the separated satellite units from 10 km out to the 600 meter final approach stage. The rendezvous laser radar (LR) will then take over, computing the target satellite's position and azimuth from 660 to 2 meters, whereupon the proximity sensor will make final attitude and positional adjustments. Of the three sensing systems, the LR and the proximity sensor represent cutting-edge technology.

Had solar pannel problems right after launch. This was solved quickly but an automatic shutdown occured on Nov 30.

Sub satellite

Target - Orihime

Designation: 25424 / 97074E

Transmits on 2.22 GHz

Technical data

Specifications

Prime contractor	Toshiba
Platform
Mass at launch	2950 kg (chaser: 2540 kg, target: 410 kg)
Mass in orbit
Dimension
Solar array
Stabilization	3-axis
DC power
Design lifetime	1.5 years

Will use Comets to demonstrate inter-orbit links.  Transmits on 2.27699 & 2.04425 GHz

The docking system was developed by Mitsubishi.


 ETS 8

Also called ETS N

General

Designation
Launch date	initially planned in 2002
Country of origin	Japan
Mission	Telecommunications, experimental
Geostationary orbit	146°E
Launch vehicle	H2A
External resources

http://yyy.tksc.nasda.go.jp/Home/Satellites/e/ets8_e.html

Technical data

Specifications

Prime contractor
Platform	Mitsubishi (same as ETS 6 & Comets)
Mass at launch	5000 kg
Mass in orbit	2800 kg
Payload mass	1100 kg
Dimension
Solar array
Stabilization	3-axis
DC power	7500 W (after 3 years)
Design lifetime	3 years (satellite bus: 10 years)

Will feature two S-band transponders for mobile phone, digital broadcast and a nagivation system.

The navigation system will have Rubidium atomic clock and a signal generator for S- and Ka-band.

Two Large-Scale Deployable Reflectors will reach 19X17 m once deployed (1 m diameter at lift-off).

The giant antenna will be tested on a piggyback mission on the first H2A launch in early 2000.


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 Program: Eurasiasat

Telecommunication program to be operated by Eurasiasat, a Monaco-based joint venture between Turk Telekom and Aerospatiale. This is a followon for the Turksat program.


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Program: Eurasiasat

Eurasiasat 1


 Eurasiasat 1

Also called Turksat 2A

General

Designation
Launch date	initially planned in late 1999
Country of origin	Turkey
Mission	Telecommunications
Geostationary orbit	42°E co-located
Launch vehicle	Ariane

Total cost: $260 million

Technical data

EIRP coverage (dBW)

West beam

East beam

Specifications

Prime contractor	Aerospatiale
Platform	Spacebus-3000B3
Mass at launch	3400 kg
Mass in orbit
Dimension	3.74 m high
Solar array	36.5 m span
Stabilization	3-axis
DC power	9000 W
Design lifetime	15 years
Ku-band

Main transponders	32
Backup transponders
Power	110 W
Bandwidth	33 MHz
Coverage	West: Western & Central Europe to Turkey East: Turkey to Afghanistan Spot1: fully mobile Spot2: fully mobile
EIRP max	52 dBW
G/T max
Polarization	linear H/V

Command: 14.184 V & 13.998 H GHz

Telemetry: 11.69940 V & 11.704 H GHz

Downlink transponder frequency chart (GHz)

Horizontal Downlink	Transponder	Vertical Downlink	Bandwidth (MHz)	Beam
	1	11.75748	33	West
11.74666	2		33	East
	3	11.76534	33	West
11.78502	4		33	East
	5	11.80420	33	West
11.82338	6		33	East
	7	11.84256	33	West
11.86174	8		33	East
	9	11.88092	33	West
11.90010	10		33	East
	11	11.91928	33	West
11.93846	12		33	East
	13	11.95764	33	West
11.97982	14		33	East
	15	11.99600	33	West
12.01518	16		33	East
	17	12.03436	33	West
12.05354	18		33	East
	19	12.07272	33	West
12.09190	20		33	East
12.13026	21	12.13026	33	West (V) or S1 (H)
12.13026	22	12.13026	33	East (H) or S2 (V)
12.52350	23	12.52350	36	S1 (H) or West (V)
	24	12.52350	36	S2
12.56500	25		36	S1
12.56500	26	12.56500	36	S2 (V) or East (H)
12.60650	27		36	S1
	28	12.60650	36	S1 or S2
12.64800	29		36	S1
	30	12.64800	36	S1 or S2
12.68950	31		36	S1
	32	12.68950	36	S1 or S2
12.73100	33		36	S1
	34	12.73100	36	S1 or S2
Uplink transponder frequency chart (GHz)

Horizontal  Uplink	Transponder	Vertical  Uplink	Bandwidth (MHz)	Beam
	1	17.32748	33	West
17.34666	2		33	East
	3	17.36534	33	West
17.38502	4		33	East
	5	17.40420	33	West
17.42338	6		33	East
	7	17.44256	33	West
17.46174	8		33	East
	9	17.48092	33	West
17.50010	10		33	East
	11	17.51928	33	West
17.53846	12		33	East
	13	17.55764	33	West
17.57982	14		33	East
	15	17.59600	33	West
17.61518	16		33	East
	17	17.63436	33	West
17.65354	18		33	East
	19	17.67272	33	West
17.69190	20		33	East
17.73026	21	17.73026	33	West (V) or S1 (H)
17.73026	22	17.73026	33	East (H) or S2 (V)
	23	13.77050	36	S1
13.77050	24		36	S2
	25	13.81200	36	S1
13.81200	26		36	S2
	27	13.85350	36	S1
13.85350	28		36	S1 or S2
	29	13.89500	36	S1
13.89500	30		36	S1 or S2
	31	13.93650	36	S1
13.93650	32		36	S1 or S2
	33	13.97800	36	S1
13.97800	34		36	S1 or S2


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Eurasiasat 1's West beam EIRP


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Eurasiasat 1's East beam EIRP


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 Eureca 1

EUropean REtrievable CArrier

General

Designation	22065 / 92049B
Launch date	31 Jul 1992
Country of origin	Europe
Mission	Scientific
Perigee/Apogee	484/509 km
Inclination	28.5°
Period	94.6 min
Launch vehicle	STS 46

Eureca was an ESA scientific satellite designed to be launched and retrieved by the Space Shuttle. It carried the first European inter-orbit communications (IOC) link to be conducted with Olympus.

End of life

Decay	Retrieved by STS 57 on 1 Jul 1993
External resources

http://www.esoc.esa.de/external/mso/eureca.html

Technical data

Specifications

Prime contractor	MBB
Mass at launch	4450 kg
Payload mass	1000 kg
Dimension	4.5 x 2.3 x 2.7 m
Solar array	18 m span
Stabilization	3-axis
DC power	5000 W
Payload

Telemetry and data	S-band Ka-band (experimental/IOC)
Rates	uplink: 2 kbps downlink: 256 kbps


 Program: Europe*Star

Telecommunication satellite program lead by Alcatel with Loral. Should use 3 German GEO slots (43, 45 & 47.5°E) to beam to southern Africa, Asia, Europe, India and the Middle East. Cost: $300 million

The first satellite should weigh 3600 kg and be launched (by Ariane) in mid-2000 and located at 45°E. The second satellite is expected in 2002 at the same location.

Europe*Star Limited (based in London) is owned by France's Alcatel, as majority shareholder, and Loral Space Communications of the U.S., with interest held by the Dr. Schulte-Hillen Group which initiated the project.

Technical data

Specifications

Prime contractor	SS/L
Platform
Mass at launch	4150 kg
Mass in orbit
Dimension
Solar array
Stabilization
DC power	9500 W
Design lifetime

Payload provided by Alcatel

Ku-band

Main transponders	30
Backup transponders
Power	140 W
Bandwidth
Coverage	multiple beams for Europe, Middle East, South Africa, India, and South East Asia
EIRP max
G/T max
Polarization


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 Europesat 1

General

Designation
Launch date	initially planned for July 2000
Country of origin	Europe
Mission	Telecommunications
Geostationary orbit	29°E
Launch vehicle
Launch site

Eutelsat will operate Europesat 1. It might not be built, Eutelsat 3F1R might do the job.

Technical data

Specifications

Prime contractor	MMS
Platform	Eurostar
Mass at launch	3000 kg
Mass in orbit
Dimension
Solar array
Stabilization
DC power	6000 W
Design lifetime	15 years
Ku-band

Main transponders	36 (only 24 transp are needed for the freq range...)
Backup transponders
Power	70 W
Bandwidth
Coverage
EIRP max
G/T max
Polarization

Will downlink in 11.20 - 11.70 GHz and 12.50 - 12.75 GHz


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 Program: Euroskyway

Telecommunication program proposed by the Italian firm Alenia Spazio. It would offer large bandwidth for multimedia applications in Europe. It would use Ka-band

The program would have 5 GEO satellites located at 5, 13, 22, 30 & 39°E. The two first should be launched in 2001. The system would cover Europe, the Middle East, Africa, and Western Asia. Each satellite would weigh 4500 kg with 9000 W power onboard and 15 years lifetime. Each satellite would use 700 MHz bandwidth providing 9 Gbps. Each satellite will provide 82,000 channels od 64 kbps.

Financing is still to be found...


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 Program: Eutelsat

EUropean TELecommunication SATellite, also called ECS (European Communication Satellite)

In 1979 the European Space Agency decided to build five ECS satellites whose management were given to the European organization Eutelsat. The Satellites were aimed to respond to the post and telecommunications needs and to transmit EBU's TV channels. To avoid frequencies attribution problems in C-band the satellites were designed to operate in Ku-band. The OTS program had provided test transmissions with small Earth stations using on board powerful transponders.

Eutelsat was officialy created in 1985. The initial mission was to complete the telephone networks without acting contrary to Intelsat laws. In fact, Eutelsat mainly makes profit with TV channels (65% of its profits).

Eutelsat should be privatized as a French company by 2 July 2001.

External resources

http://www.esoc.esa.de/external/mso/ecs.html


Program: Eutelsat

Eutelsat 1F1	Eutelsat 1F2	Eutelsat 1F3	Eutelsat 1F4
Eutelsat 1F5
Eutelsat 2F1	Eutelsat 2F2	Eutelsat 2F3	Eutelsat 2F4
Eutelsat 2F5
Hotbird 1	Hotbird 2	Hotbird 3	Hotbird 4
Hotbird 5
Eutelsat 3F1	Eutelsat 3F1R	Eutelsat 3F2	Eutelsat 3F3
Eutelsat 3 SESAT		TDF 2	Telecom 2A
Atlantic Bird 1	Europesat 1	Eutelsat Ressat


Eutelsat 1's transponder frequency chart (GHz)

Horizontal Uplink	Horizontal Downlink	Transponder	Vertical Downlink	Vertical Uplink	Beam
	10.991667	1		14.291667	Euro/West
	11.075000	2		14.375000	East
	11.158333	3		14.458333	Euro/West
	14.491667	4		14.041667	West
	11.575000	5		14.125000	East/Atlantic
	11.658333	6		14.208333	West
14.291667		7	10.991667		Euro/West
14.375000		8	11.075000		East
14.458333		9	11.158333		Euro/West
14.041667		10	11.491667		West
14.125000		11	11.575000		Atlantic
14.208333		12	11.658333		West
	12.541667	13		14.041667	SMS
14.041667		14	12.541667		SMS

No 12 GHz transponders on 1F1


Eutelsat 1's specifications

Prime contractor	British Aerospace
Platform	ECS
Mass at launch	F1: 1050 kg Others: 1185 kg
Mass in orbit	585 kg
Payload mass	117 kg
Length	1.9 m
Width	1.4 m
Height	2.3 m
Solar array	13.8 m span
Stabilization	3-axis
DC power	EOL: 1000 W
Payload power	638.5 W
Design lifetime	7 years

Apogee kick motor: Mage 2


Eutelsat 1's Ku-band

Main transponders	10 in 11 GHz + 2 in 12 GHz (none for F1)
Backup transponders	2
Power	20 W (TWTA)
Bandwidth	72 MHz
Coverage & EIRP max	Atlantic, West & East spotbeams: 46 dBW Eurobeam: 41 dBW SMS beam: 43.5 dBW (not on F1)
Polarization	linear

Only 9 transponders can be active simultaneously


Eutelsat 2's EIRP (super beam)


Eutelsat 2 F1, F2 & F3's EIRP (wide beam)


Eutelsat 2F4's EIRP (wide beam)


Eutelsat 2's transponder frequency chart

Uplink frequencies	14-14.5 GHz
Downlink frequencies	10.95-11.2 GHz, 11.45-11.7 GHz and 12.5-12.75 GHz

Eutelsat 2 satellites are re-configurable in space i.e. transponders can be switched onto super or wide beam and to 11 GHz or 12 GHz.


Eutelsat 2's specifications

Prime contractor	Aerospatiale
Platform	Spacebus-100B
Mass at launch	1870 kg
Mass in orbit	915 kg
Payload mass	207.9 kg: transponders: 167.9 kg, antennas: 40 kg
Dimension	2.8 x 2.2 x 2.5 m
Solar array	22.4 m span
Stabilization	3-axis
DC power	BOL: 3000 W EOL: 2890 W
Design lifetime	10 years
Payload power	2090 W
G/T	-3.5 to +2.5 dB/K


Eutelsat 2's Ku-band

Main transponders	16
Backup transponders	8
Power	50 W (TWTA)
Bandwidth	7 transponders of 72 MHz 9 transponders of 36 MHz
Coverage & EIRP max	super beam: 52 dBW wide beam: 47 dBW
Polarization	linear


 Eutelsat 1F1

Also called ECS 1

General

Designation	14128 / 83058A
Launch date	16 Jun 1983
Country of origin	Europe
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane L06
Location

Begin	End	Position
L: 16 Jun 1983	Oct 1983	10°E
12 Oct 1983	Oct 1988	13°E
Oct 1988	Nov 1991	16°E, inclined (Sep 1989)
Dec 1991	Feb 1992	17.5°E, inclined
late-1992	Jul 1993	25.5°E, inclined
Sep 1993	Feb 1996	48°E, inclined
Mar 1996	Nov 1996	36°E, inclined
End of life

Out of service	Dec 1996
Technical data

Specifications

Ku-band

Transponder frequency chart

Beacon: 11.451091 GHz

This satellite was not as efficient as other Eutelsat 1 series. It could only use 6 transponders during an eclipse.


 Eutelsat 1F2

General

Designation	15158 / 84081A
Launch date	4 Aug 1984
Country of origin	Europe
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V10
Location

Begin	End	Position
L: 4 Aug 1984	Sep 1990	7°E
late-1990	Feb 1992	4°E
late-1992	late-1992	2°E
Jun 1993	Dec 1993	1°E
End of life

Out of service	December 1993
Cause	End of life, moved to the junk orbit Broadcast 634,969 hours
Technical data

Specifications

Ku-band

Transponder frequency chart

Beacon: 11.45035 GHz


 Eutelsat 1F3

End of life

Out of service	13 Sep 1985
Cause	Ariane V15 explosion


 Eutelsat 1F4

General

Designation	18351 / 87078B
Launch date	16 Sep 1987
Country of origin	Europe
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V19

In inclined orbit since mid-May 1993. Transponders 1, 5, 7, 8, 9, 10, 11 and 12 have failed.

Location

Begin	End	Position
L: 16 Sep 1987	Oct 1988	10°E
25 Oct 1988	Oct 1990	13°E
16 Oct 1990	Oct 1992	7°E
Oct 1992	late-1992	36°E
May 1993		25.5°E, inclined
Technical data

Specifications

Ku-band

Transponder frequency chart

Beacon: 11.44965 GHz

EIRP coverage (dBW)

Spot beams

Eurobeam

SMS


Eutelsat 1F4's EIRP (Atlantic, East & West spots)


Eutelsat 1F4's EIRP (Eurobeam)


Eutelsat 1F4's EIRP (SMS beam)


 Eutelsat 1F5

General

Designation	19331 / 88063B
Launch date	21 Jul 1988
Country of origin	Europe
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V24

In inclined orbit since 1 Aug 1994. Transponders 3, 4, 6 and 8 have failed. First Eutelsat satellite to provide transatlantic connectivity.

Location

Begin	End	Position
L: 21 Jul 1988	Oct 1988	10°E, tests
14 Oct 1988	Apr 1991	10°E
15 Apr 1991	Dec 1998	21.5°E, inclined
Feb 1999		12.5°W, inclined
Technical data

Specifications

Ku-band

Transponder frequency chart

Beacon: 11.44895 GHz


 Eutelsat 2F1

General

Designation	20777 / 90079B
Launch date	30 Aug 1990
Country of origin	Europe
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V38

Operational since 24 Sep 1990.

Location

Begin	End	Position
L: 30 Aug 1990	Nov 1998	13°E
Dec 1998	Jan 1999	36°E (replaces TDF 2)
Feb 1999		48°E (went inclined)
Technical data

Specifications

Ku-band

Transponder frequency chart

Beacons: 11.451091 GHz and 12.541667 GHz

EIRP coverage (dBW)

Wide beam

Super beam

Transponder frequency chart (GHz)

Horizontal Downlink	Transponder	Vertical Downlink
10.971	20A
	25A	10.986
11.005	20B
	25B	11.016
	26A	11.049
11.055	21A
	26B	11.080
11.095	21B
	27A	11.133
11.146	22A
	27B	11.163
11.181	22B
11.554	32
	37	11.575
11.595	33
	38	11.615
11.638	34A
	39	11.658
11.675	34B
12.521	40
	45	12.542
12.563	41
	46	12.583
12.604	42
	47	12.625
12.645	43
	48	12.666
12.688	44A
	49	12.708
12.728	44B


 Eutelsat 2F2

General

Designation	21056 / 91003B
Launch date	15 Jan 1991
Country of origin	Europe
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V41

Test were conducted in 21.5°E slot, operational since 8 Mar 1991

Location

Begin	End	Position
L: 15 Jan 1991	14 Jun 1999	10°E
Aug 1999		12.5°W
Technical data

Specifications

Ku-band

Transponder frequency chart

Beacons: 11.451820 and 12.541667 GHz

EIRP coverage (dBW)

Wide beam

Super beam

Transponder frequency chart (GHz)

Horizontal Downlink	Transponder	Vertical Downlink
	25A	10.971
10.986	20A
	25B	11.005
11.016	20B
11.049	21A
	26A	11.055
11.080	21B
	26B	11.095
11.130	22A
	27A	11.146
11.164	22B
	27B	11.181
11.554	32
	37	11.575
11.595	33
	38	11.615
11.638	34A
	39	11.658
11.675	34B
12.521	40
	45	12.542
12.562	41
	46	12.583
12.604	42
	47	12.625
12.645	43
	48	12.666
12.688	44A
	49	12.708
12.728	44B


 Eutelsat 2F3

General

Designation	21803 / 91083A
Launch date	7 Dec 1991
Country of origin	Europe
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Atlas Centaur

Operational since 10 Jan 1992

Location

Begin	End	Position
L: 7 Dec 1991	Nov 1998	16°E
Jan 1999		36°E
Technical data

Specifications

Ku-band

Transponder frequency chart

Beacons: 11.452570 and 12.541667 GHz

Equipped with an S400 apogee engine

EIRP coverage (dBW)

Wide beam

Super beam

Transponder frequency chart (GHz)

Horizontal Downlink	Transponder	Vertical Downlink
	25A	10.971
10.986	20A
	25B	11.005
11.016	20B
11.049	21A
	26A	11.055
11.080	21B
	26B	11.095
11.130	22A
	27A	11.146
11.164	22B
	27B	11.181
11.554	32
	37	11.575
11.595	33
	38	11.615
11.638	34A
	39	11.658
11.675	34B
12.521	40
	45	12.542
12.562	41
	46	12.583
12.604	42
	47	12.625
12.645	43
	48	12.666
12.688	44A
	49	12.708
12.728	44B


 Eutelsat 2F4

General

Designation	22028 / 92041B
Launch date	9 Jul 1992
Country of origin	Europe
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V51
Location

Begin	End	Position
L: 9 Jul 1992	May 1999	7°E
14 Jun 1999		10°E

Operational since 18 Sep 1992. On 30 Mar 1999 the satellite had an outage from 03:25 UT to 08:53 UT. The satellite went into safe mode.

Technical data

Specifications

Ku-band

Transponder frequency chart

Beacons: 11.451091 and 12.541667 GHz

EIRP coverage (dBW)

Wide beam

Super beam

Transponder frequency chart (GHz)

Horizontal  Uplink	Horizontal  Downlink	Transponder	Vertical  Downlink	Vertical  Downlink
	10.971	20A		14.271
14.286		25A	10.986
	11.005	20B		14.305
14.316		25B	11.016
14.349		26A	11.049
	11.055	21A		14.355
14.380		26B	11.080
	11.095	21B		14.395
		27A	11.133
	11.146	22A
		27B	11.163
	11.181	22B
	11.554	32
		37	11.575
	11.595	33
		38	11.615
	11.638	34A
		39	11.658
	11.675	34B
	12.521	40
		45	12.542
	12.563	41
		46	12.583
	12.604	42
		47	12.625
	12.645	43
		48	12.666
	12.688	44A
		49	12.708
	12.728	44B

The uplink frequency seems to be downlink freq. + 3.3 GHz


 Eutelsat 2F5

End of life

Out of service	24 Jan 1994
Cause	Ariane V63 failure

Was aimed to serve the eastern members in slot 36°E.

Cost: $200 million


 Atlantic Bird 1

General

Designation
Launch date	Jun 2001
Country of origin	Europe
Mission	Telecommunications
Geostationary orbit	12.5°W
Launch vehicle

Part of the Eutelsat network

Technical data

Specifications

Prime contractor	Alenia Aerospazio
Platform
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime
Ku-band

Main transponders	20
Backup transponders
Power
Bandwidth
Coverage	north + south America Europe part of North Africa & Middle East
EIRP max
G/T max
Polarization


 Hotbird 1

Also called Eutelsat 2F6

General

Designation	23537 / 95016B
Launch date	28 Mar 1995
Country of origin	Europe
Mission	Telecommunications
Geostationary orbit	13°E
Launch vehicle	Ariane V71
Technical data

EIRP coverage (dBW)

Specifications

Beacon: 11.44961 GHz horizontal

Ku-band (11.2-11.55 GHz)

Main transponders	16
Backup transponders	8
Power	70 W (TWTA)
Bandwidth	36 MHz
Coverage and EIRP max	super wide beam: 49 dBW
Polarization	linear
Uplink	12.89-13.25 GHz
Transponder frequency chart (GHz)

Horizontal Downlink	Transponder	Vertical Downlink
11.221	1
	2	11.242
11.262	3
	4	11.283
11.304	5
	6	11.325
11.345	7
	8	11.366
11.387	9
	10	11.408
11.428	11
	12	11.449
11.471	13
	14	11.492
11.513	15
	16	11.534


Hotbird 1's EIRP


Hotbird 2, 3, 4 & 5's superbeam EIRP


Hotbird 2, 3, 4 & 5's widebeam EIRP


 Hotbird 2

General

Designation	24665 / 96067A
Launch date	21 Nov 1996
Country of origin	Europe
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Atlas Centaur #103

Worth $200 million

It seems that the satellite has a fuel tank leak, which has been detected by abnormal fuel consumption.

Location

Begin	End	Position
L: 21 Nov 1996	5 Dec 1996	29°E
16 Dec 1996		13°E
Technical data

EIRP coverage (dBW)

Superbeam

Widebeam

Specifications

Prime contractor	Matra Marconi Space
Platform	Eurostar 2000+
Mass at launch
Payload mass	268 kg: transponders: 192 kg, antennas: 76 kg
Dimension	2.5 x 1.7 x 2.6 m
Stabilization	3-axis
DC power	equinox: 5500 W, solstice: 4988 W
Payload power	4188 W
Design lifetime	12-15 years

Telemetry: 2264.818 MHz

Ku-band (11.45-11.7 GHz & 11.7-12.5 GHz)

Main transponders	20
Backup transponders	10
Power	110 W (TWTA)
Bandwidth	20 transponders of 33 MHz (12 GHz) 5 transponders of 36 MHz (11 GHz) 1 transponder of 72 MHz (11 GHz) 1 transponder of 72 MHz (12.5 GHz)
Coverage	super beam: Europe from West to East wide beam: from the Canary Islands to the republics South of Russia and Gulf countries Transponders switchable one by one on each zone
EIRP max	Superbeam: 53 dBW Widebeam: 50 dBW
Polarization	linear
Frequencies	Uplink: 13.8-14.0 GHz and 17.3-18.1 GHz

6 transponders in 12 GHz can be switched in 11 GHz and the 36 MHz transponders can be operated in half-transponder mode.

Transponder frequency chart (GHz)

Horizontal Downlink	Transponder	Vertical Downlink	Bandwidth
11.554410	32/D1		36 MHz
	37/D2	11.575160	36 MHz
11.595910	33/D3		36 MHz
	38/D4	11.616660	36 MHz
11.658333	34/D5		72 MHz
	39/D6	11.658160	36 MHz
	50/E1	11.727480	33 MHz
11.746660	51/E2		33 MHz
	52/E3	11.765840	33 MHz
11.785020	53/E4		33 MHz
	54/E5	11.804200	33 MHz
11.823380	55/E6		33 MHz
	56/E7	11.842560	33 MHz
11.861740	57E8		33 MHz
	58/E9	11.880920	33 MHz
11.900100	59/E10		33 MHz
	60/E11	11.919280	33 MHz
11.938460	61/E12		33 MHz
	62/E13	11.957640	33 MHz
11.976820	63/E14		33 MHz
	64/E15	11.996000	33 MHz
12.015180	65/E16		33 MHz
	66/E17	12.034360	33 MHz
12.053540	67/E18		33 MHz
	68/E19	12.072720	33 MHz
12.091900	69/E20		33 MHz


 Hotbird 3

General

Designation	24931 / 97049A
Launch date	2 Sep 1997
Country of origin	Europe
Mission	Telecommunications
Geostationary orbit	13°E
Launch vehicle	Ariane V99

Cost with launch and insurance: over $250 million

Tested at 29 deg East. Declared operational on 3 Oct 1997

Technical data

EIRP coverage (dBW)

Superbeam

Widebeam

Specifications

Prime contractor	Matra Marconi Space
Platform	Eurostar 2000+
Mass at launch	2915 kg
Mass in orbit	1715 kg
Dry mass	1280 kg
Dimension
Solar array
Stabilization	3-axis
DC power
Design lifetime	12 years

Marquardt R-4D apogee engine

Ku-band

Main transponders	20
Backup transponders
Power	110 W
Bandwidth	19 transponders of 33 MHz 1 transponder of 50 MHz
Coverage	Europe + mobile spot beam
EIRP max
Polarization	linear H/V
Transponder frequency chart (GHz)

Horizontal Downlink	Transponder	Vertical Downlink	Bandwidth (MHz)
	70	12.1108	33
12.13026	71		33
	72	12.14944	33
12.16862	73		33
	74	12.18780	33
12.20698	75		33
	76	12.22616	33
12.24534	77		33
	78	12.26452	33
12.28370	79		33
	80	12.30288	33
12.32206	81		33
	82	12.34124	33
12.36042	83		33
	84	12.37960	33
12.39878	85		33
	86	12.41796	33
12.43714	87		33
	88	12.46691	50
12.47550	89		33


 Hotbird 4

General

Designation	25237 / 98013A
Launch date	27 Feb 1998
Country of origin	Europe
Mission	Telecommunications
Geostationary orbit	13°E
Launch vehicle	Ariane V106

cost: $280 million

Tested at 29°East.

Technical data

EIRP coverage (dBW)

Superbeam

Widebeam

Specifications

Prime contractor	Matra Marconi Space
Platform	Eurostar 2000
Mass at launch	2885 kg
Mass in orbit	1770 kg
Dry mass	1310 kg
Dimension
Solar array
Stabilization	3-axis
DC power	6000 W
Design lifetime	12 - 15 years
Ku-band

Main transponders	20
Backup transponders
Power	135 W (TWTA)
Bandwidth	33, 36 & 50 MHz
Coverage
EIRP max
Polarization
Frequencies	Downlink: 10.7-10.95 GHz, 12.6-12.75 GHz

Has 3 main antennas and a 50 cm mobile spot.

Will have a Skyplex device onboard (DVB compatible). This module is developped by Alenia Aerospazio. It has a digital processor to enable on board multiplexing of DVB signals; this let several channels to be uplinked from differents places although downlinked in the same multiplex. Such a module will be used by the Euroskyway program. The system can combine 6 uplinks of 6 mbps each into a 36 mbps downlink stream.

Transponder frequency chart (GHz)

Horizontal Downlink	Transponder	Vertical Downlink	Bandwidth (MHz)
	110	10.719	33
10.727	111		36
	112	10.757	33
10.775	113		33
	114	10.796	33
10.815	115		33
	116	10.834	33
10.853	117		33
	118	10.873	33
10.892	119		33
	120	10.911	33
10.930	121		36
	122	10.949	33
12.616	95		33
	96	12.635	33
12.654	97		33
	98	12.673	33
12.692	99		50
	100	12.713	33
12.731	101		50


 Hotbird 5

General

Designation	25495 / 98057A
Launch date	9 Oct 1998
Country of origin	Europe
Mission	Telecommunications
Geostationary orbit	13°E
Launch vehicle	Atlas #117

tested at 2°E

ordered in February 1996; worth $226 million

In Jul 1999 it is announced that the satellite has solar array problems which cause a loss of approx 10% of output power. This is related to problems with Fokker solar arrays provided with the Eurostar 2000+ platform.

Technical data

EIRP coverage (dBW)

Superbeam

Widebeam

Specifications

Prime contractor	Matra Marconi Space
Platform	Eurostar 2000+
Mass at launch	2995 kg
Mass in orbit
Dimension
Solar array
Stabilization	3-axis
DC power	5500 W
Design lifetime	14 years

Equipped with Fokker-made solar arrays which might have a defect.

Ku-band

Main transponders	22
Backup transponders
Power	130 W
Bandwidth	12 x 33, 8 x 36 & 2 x 72 MHz
Coverage
EIRP max	superbeam: 53 dBW widebeam: 50 dBW
Polarization	linear H/V
Frequencies	Downlink: 10.95-11.2 (10 tps), 11.55-11.7 (7 tps) & 12.5-12.6 (5 tps) GHz

Has a 3 Skyplex unit (such a unit was also on Hotbird 4) capable of assembling upto 8 streams as small as 1350 kbps.

Transponder frequency chart (GHz)

Horizontal Downlink	Transponder	Vertical Downlink	Bandwidth (MHz)
10.971	123
	124	10.992
11.013	125
	126	11.034
11.054	127
	128	11.075
11.069	129
	130	11.117
11.158	131
	132	11.179
11.566	153
	154	11.585
11.604	155
	156	11.623
11.642	157
	158	11.662
11.681	159
	90	12.520
12.539	91
	92	12.558
12.577	93
	94	12.597


Eutelsat 3 F1 & F3's EIRP coverage


 Eutelsat 3F1

Also called Eutelsat W1

General

Designation	n/a
Launch date	not launched
Country of origin	Europe
Mission	Telecommunications
Geostationary orbit	10°E
Launch vehicle	Ariane
Launch site

In May 1998 a fire broke up in the factory where the satellite was being built. The cause for the fire was that one of the antennas, being tested at maximum power, was directly pointing towards a wall covered in carbon foam. Owing to the high RF power released (60 Watts) the foam quickly overheated and started burning. The satellite was covered with water and later declared a total loss.

End of life

Out of service	never launched, destroyed on earth
Technical data

EIRP coverage (dBW)

Specifications

Prime contractor	Aerospatiale (with DASA, Alenia & SS/L)
Platform	Spacebus-3000
Mass at launch	2950 kg
Mass in orbit	1810 kg
Dry mass	1375 kg
Dimension	4.6 x 2.5 x 1.8 m
Solar array	29 m span
Stabilization	3-axis
DC power	EOL: 5900 W
Design lifetime	12 years
Ku-band

Main transponders	24
Backup transponders
Power	90 W
Bandwidth	72 MHz (6 switchable to steerable beam 1, 6 to steerable beam 2)
Coverage	One fixed beam to cover the entire European continent and the Mediterranean Bassin 2 steerable beams
EIRP max	fixed: 47 dBW steerable: 52 dBW
Polarization	linear
Frequencies	uplink: 13.0-13.25 GHz & 13.75-14.5 GHz downlink: 10.95-11.7 GHz (18 transp.) & 12.5-12.75 GHz (6 transp.)

The steerables beams have got an elliptical footprint that can be rotated by up to +/- 90°


 Eutelsat 3F1R

Also called Eutelsat W1R

General

Designation
Launch date	initially planned in 3rd quarter 2000
Country of origin	Europe
Mission	Telecommunications
Geostationary orbit	28.5°E
Launch vehicle	Ariane
Launch site

Could be used elsewhere if Cesasat goes to 28.5°E

Technical data

Specifications

Prime contractor	Aerospatiale (with DASA, Alenia & SS/L)
Platform	Spacebus-3000
Mass at launch	2950 kg
Mass in orbit	1810 kg
Dry mass	1375 kg
Dimension	4.6 x 2.5 x 1.8 m
Solar array	29 m span
Stabilization	3-axis
DC power	EOL: 5900 W
Design lifetime	12 years
Ku-band

Main transponders	24
Backup transponders
Power	90 W
Bandwidth	72 MHz (6 switchable to steerable beam 1, 6 to steerable beam 2)
Coverage
EIRP max	fixed: 47 dBW steerable: 52 dBW
Polarization	linear
Frequencies	Would downlink in 11.20 - 11.70 GHz and 12.50 - 12.75 GHz (6 transp.)

The steerable beams have an elliptical footprint that can be rotated by up to +/- 90°


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 Eutelsat 3 SESAT

Sesat stands for Siberian Europe Satellites

General

Designation
Launch date	initially planned in Dec 1998
Country of origin	Europe
Mission	Telecommunications
Geostationary orbit	36°E
Launch vehicle	Proton

Cost: $169 million  The contract calls for a replacement satellite in case of failure

Technical data

EIRP coverage (dBW)

Specifications

Prime contractor	NPO-PM (payload: Alcatel Espace)
Platform	Siberian platform
Mass at launch	2600 kg
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime	10 years
Ku-band

Main transponders	18
Backup transponders
Power	90 W (TWTA)
Bandwidth
Coverage
EIRP max
Polarization
Frequencies	10.950-11.200 GHz (6 transp.) 11.450-11.700 GHz (6 transp.) 12.500-12.750 GHz (6 transp.)


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Eutelsat 3 SESAT's EIRP


 Eutelsat 3F2

Also called Eutelsat W2

General

Designation	25491 / 98056A
Launch date	5 Oct 1998
Country of origin	Europe
Mission	Telecommunications
Geostationary orbit	16°E
Launch vehicle	Ariane V111

tested at 2°E

Technical data

EIRP coverage (dBW)

Specifications

Prime contractor	Aerospatiale (with DASA, Alenia & SS/L)
Platform	Spacebus-3000
Mass at launch	2950 kg
Mass in orbit	1810 kg
Dry mass	1375 kg
Dimension	4.6 x 2.5 x 1.8 m
Solar array	29 m span
Stabilization	3-axis
DC power	EOL: 5900 W
Design lifetime	12 years
Ku-band

Main transponders	34 (max 24 active at one time)
Backup transponders
Power	90 W
Bandwidth	21 x 36 MHz (9 switchable to steerable beam) 13 x 72 MHz (1 switchable to steerable beam)
Coverage	One fixed beam to cover the entire European continent and the Mediterranean Bassin One steerable beam to cover the Reunion Island
EIRP max	fixed: 50 dBW steerable: 52 dBW
Polarization	linear
Frequencies	uplink: 13.0-13.25 GHz & 13.75-14.5 GHz downlink: 10.95-11.7 GHz & 12.5-12.75 GHz
Transponder frequency chart (GHz)

Horizontal Downlink	Transponder	Vertical Downlink	Bandwidth
10.992	B1
	B2	10.992
11.075	B3
	B4	11.075
11.158	B5
	B6	11.158
	C1	11.221
11.242	C2
	C3	11.262
11.283	C4
	C5	11.304
11.324	C6
	C7	11.345
11.366	C8
	C9	11.387
11.408	C10
	C11	11.428
11.449	C12
	D1	11.471
11.492	D2
	D3	11.513
11.534	D4
	D5	11.554
11.575	D6
	D7	11.596
11.617	D8		spot beam
	D9	11.658
11.658	D10		spot beam
12.542	F1
	F2	12.542
12.625	F3
	F4	12.625
12.708	F5
	F6	12.708


Eutelsat 3F2's EIRP coverage


 Eutelsat 3F3

Also called Eutelsat W3

General

Designation	25673 / 99018A
Launch date	12 Apr 1999
Country of origin	Europe
Mission	Telecommunications
Geostationary orbit	7°E
Launch vehicle	Atlas 2AS #120

tested from 2°E. Went operational on 16 May 1999

Technical data

EIRP coverage (dBW)

fixed

spot

Specifications

Prime contractor	Aerospatiale (with DASA, Alenia & SS/L)
Platform	Spacebus-3000B2
Mass at launch	3183 kg
Mass in orbit	1810 kg
Dry mass	1375 kg
Dimension	4.6 x 2.5 x 1.8 m
Solar array	29 m span
Stabilization	3-axis
DC power	EOL: 5900 W
Design lifetime	12 years

The Ku-band telemetry is defective.

Ku-band

Main transponders	34 (max 24 active at one time)
Backup transponders
Power	90 W
Bandwidth	21 x 36 MHz (9 switchable to steerable beam) 13 x 72 MHz (1 switchable to steerable beam)
Coverage	One fixed beam to cover the entire European continent and the Mediterranean Bassin One steerable beam to Turkey (Aegan)
EIRP max	fixed: 47 dBW steerable: 52 dBW
Polarization	linear
Frequencies	uplink: 13.0-13.25 GHz & 13.75-14.5 GHz downlink: 10.95-11.7 GHz & 12.5-12.75 GHz

Dxx transponders can be switched to steerable beam

Transponder frequency chart (GHz)

Horizontal  Uplink	Horizontal  Downlink	Transponder	Vertical  Downlink	Vertical  Uplink	Bandwidth
14.29167	10.99167	B1			72 MHz
		B2	10.99167	14.29167	72 MHz
14.37500	11.07500	B3			72 MHz
		B4	11.07500	14.37500	72 MHz
14.45833	11.15833	B5			72 MHz
		B6	11.15833	14.45833	72 MHz
		C1	11.22075		36 MHz
	11.24150	C2			36 MHz
		C3	11.26225		36 MHz
	11.28300	C4			36 MHz
		C5	11.30375		36 MHz
	11.32450	C6			36 MHz
		C7	11.34525		36 MHz
	11.36600	C8			36 MHz
		C9	11.38675		36 MHz
	11.40750	C10			36 MHz
		C11	11.42825		36 MHz
	11.44900	C12			36 MHz
		D1	11.47141		36 MHz
	11.49216	D2			36 MHz
		D3	11.51291		36 MHz
	11.53366	D4			36 MHz
		D5	11.55441		36 MHz
	11.57516	D6			36 MHz
		D9	11.59591		36 MHz
	11.61666	D8			36 MHz
		D7	11.65833		72 MHz
	11.65816	D10			36 MHz
	12.542	F1			72 MHz
		F2	12.542		72 MHz
	12.625	F3			72 MHz
		F4	12.625		72 MHz
	12.708	F5			72 MHz
		F6	12.708		72 MHz


Eutelsat 3F3's spot beam EIRP coverage


 Eutelsat 3F4

Also called Eutelsat W4

General

Designation
Launch date	initially planned in 1999
Country of origin	Europe
Mission	Telecommunications
Geostationary orbit	36°E
Launch vehicle
Launch site
Technical data

EIRP coverage (dBW)

Specifications

Prime contractor	Aerospatiale (with DASA, Alenia & SS/L)
Platform	Spacebus-3000
Mass at launch	2950 kg
Mass in orbit	1810 kg
Dry mass	1375 kg
Dimension	4.6 x 2.5 x 1.8 m
Solar array	29 m span
Stabilization	3-axis
DC power	EOL: 5900 W
Design lifetime	12 years
Ku-band

Main transponders	31
Backup transponders
Power	90 W?
Bandwidth	33 MHz
Coverage	Russian beam (19 transp.) African beam (6 transp.) Steerable beam (6 transp.)
EIRP max	Russian beam: 52 dBW African beam: 42.5 dBW steerable: 52 dBW
G/T max	Africa: 0 dB/K
Polarization	Russian beam: circular Other beams: linear
Frequencies	11.7 - 12.5 GHz


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Eutelsat 3 F4's EIRP coverage


 Eutelsat Ressat

General

Designation
Launch date	Dec 1999
Country of origin	Europe
Mission	Telecommunications
Perigee/Apogee
Inclination
Period
Launch vehicle
Mass at launch

Matra Marconi Space will be the prime contractor.

Ressat will be able to operate at 7, 10, 16 and 36°E for Eutelsat


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 EUVE

Extreme Ultra Violet Explorer

General

Designation	21987 / 92031A
Launch date	7 Jun 1992
Country of origin	United States
Mission	Scientific: Astronomy
Perigee/Apogee	503/527 km
Inclination	28.4°
Period	94.9 min
Launch vehicle	Delta 2 #210

EUVE has completed a survey of the entire celestial sphere in the extreme ultraviolet (UV) spectrum. Spectroscopic observations of individual targets are now made possible for guest observers.

External resources

http://www.cea.berkeley.edu/

http://mahler.brera.mi.astro.it/STRUMENTI/euve.html

Technical data

Based on the MultiMission Spacecraft bus.

Telemetry & command via TDRS.

Telemetry: 2287.5 MHz (realtime: 1/32 kbps, playback: upto 1024 kbps)

Command: 2106.4 MHz (1/0.125 kbps)


Exos
 Program: Exos

Japanese scientific program


Program: Exos

Exos A

Exos B

Exos C

Exos D


 Exos A

Also called Kyokko which means "aurora"

General

Designation	10664 / 78014A
Launch date	4 Feb 1978
Country of origin	Japan
Mission	Scientific: ionosphere study
Perigee/Apogee	634/3957 km
Inclination	65.4°
Period	134 min
Launch vehicle	Mu 3H
Launch site	Kagoshima
Mass at launch	103 kg
External resources

http://www.isas.ac.jp/info/sat/kyokko-e3.html


 Exos B

Also called Jikiken which means "magnetosphere"

General

Designation	11027 / 78087A
Launch date	16 Sep 1978
Country of origin	Japan
Mission	Scientific: magnetophere study
Perigee/Apogee	246/21151 km
Inclination	31.4°
Period	370.2 min
Launch vehicle	Mu 3H
Launch site	Kagoshima
Mass at launch	92 kg

Initial orbit: probably 230 km x 30558 km x 31° x 525 min

External resources

http://www.isas.ac.jp/info/sat/jikiken-e3.html


 Exos C

Also called Ohzora which means "sky"

General

Designation	14722 / 84015A
Launch date	14 Feb 1984
Country of origin	Japan
Mission	Scientific: high atmosphere study
Perigee/Apogee	247/331 km
Inclination	74.6°
Period	90.3 min
Launch vehicle	Mu 3S1
Launch site	Kagoshima
Mass at launch	210 kg
End of life

Decay	19 Jul 1989
External resources

http://www.isas.ac.jp/info/sat/ohzora-e3.html


 Exos D

Also called Akebono

General

Designation	19822 / 89016A
Launch date	21 Feb 1989
Country of origin	Japan
Mission	Scientific: magnetosphere and ionosphere study
Perigee/Apogee	264/8501 km
Inclination	75.1°
Period	185.2 min
Launch vehicle	Mu 3S 2
Launch site	Kagoshima
Mass at launch	300 kg
External resources

http://www.isas.ac.jp/info/sat/akebono-e3.html

Downlink: 400.45 MHz


 Exosat

General

Designation	14095 / 83051A
Launch date	26 May 1983
Country of origin	Europe
Mission	Scientific: astronomy
Perigee/Apogee	340/191878 km
Inclination	72.5°
Period	5442.1 min
Launch vehicle	Thor Delta #169
Mass at launch	510 kg

Astronomy satellite designed to map the position and characteristics of cosmic X-ray sources. The observatory performed some 2000 observations during its operational lifetime.

End of life

Out of service	9 Apr 1986
Decay	6 May 1986
External resources

http://www.esoc.esa.de/external/mso/exosat.html

http://astro.estec.esa.nl/SA-general/Archives/Exosat/exosat.html

Technical data

Specifications

Prime contractor	MBB
Platform
Mass at launch	500 kg
Payload mass	120 kg
Diameter	2.1 m
Height	1.35 m
Solar array	1.85 x 2 m
Stabilization	3-axis
DC power	EOL: 260 W
Design lifetime	2 years
Telemetry/data	S-band (6 W): 8 kbps
Low energy experiment: 2 grazing incidence (imaging) telescopes

Field of view	1°
Collecting area	90 cm²
Medium energy experiment: 8 proportional counters

Field of view	1.5°
Collecting area	1800 cm²
Gas scintillator spectrometer

Field of view	1.5°
Collecting area	200 cm²
X-ray energy rate	low energy 0.04-2 keV medium energy 1.5-50 keV spectrometer 2-80 keV


 Program: Explorer

American scientific program operated by the US Army.

Beginning of the program

Date	Launch date	Launch vehicle
1 Feb 1958	Explorer 01	Jupiter C
5 Mar 1958	Failure	Jupiter C
26 May 1958	Explorer 03	Jupiter C
26 Jul 1958	Explorer 04	Jupiter C
24 Aug 1958	Failure	Jupiter C
22 Oct 1958	Failure	Jupiter C
16 Jul 1959	Failure	Juno 2
14 Aug 1959	Failure	Juno 2
13 Oct 1959	Explorer 07	Juno 2
Sub programs

AD (Air Density)

ADE (Atmospheric Density Explorer)

AE (Atmosphere Explorer)

DME (Direct Measurement Explorer)

EPE (Energetic Particules Explorer)

GEOS (Geodetic Earth Orbiting Satellite)

IE (Ionosphere Explorer)

IMP (Interplanetary Monitoring Probes)


Program: Explorer

Explorer 01 Explorer 03 Explorer 04 Explorer 06 Explorer 07 Explorer 08 Explorer 09 Explorer 10 Explorer 11 Explorer 12 Explorer 13 Explorer 14 Explorer 15	Explorer 16 Explorer 17 Explorer 18 Explorer 19 Explorer 20 Explorer 21 Explorer 22 Explorer 23 Explorer 24 Explorer 25 Explorer 26 Explorer 27 Explorer 28	Explorer 29 Explorer 30 Explorer 31 Explorer 32 Explorer 33 Explorer 34 Explorer 36 Explorer 38 Explorer 39 Explorer 40 Explorer 41 Explorer 42 Explorer 43	Explorer 45 Explorer 46 Explorer 47 Explorer 48 Explorer 50 Explorer 51 Explorer 52 Explorer 53 Explorer 54 Explorer 55


 Explorer 01

General

Designation	00004 / 58001A
Launch date	1 Feb 1958
Country of origin	United States
Mission	Scientific: ionosphere study
Perigee/Apogee	347/1859 km
Inclination	33.2°
Period	107.2 min
Launch vehicle	Jupiter C (Juno 1 from the US Army, 18 t, 21 m tall, 4 stages)
Launch site	Cape Canaveral
Mass at launch	14.6 kg

Rocked realized by Wernher von Braun's team, a german engineer from Peenemünde. He had been working since 1953 at the Redstone Arsenal (Huntsville, Alabama) to design a balistic missile with the help of the Army Ballistic Missile Agency and the Jet Propulsion Laboratory.

First American satellite: height 1.2 m, diameter 20 cm. It was in fact the 4th stage of the rocket. Carrying 5 kg of instruments (batteries, radio transmitter, Geiger counter).

Has discovered Van Allen belts (radiations belts around the Earth) because the orbit was more excentric than expected.

External resources

http://milkman.cac.psu.edu/~cooper/TourOfDC/smithsonian/Air-and-Space/MilestonesofFlight/explor.html

End of life

Out of service	23 May 1958
Decay	31 Mar 1970 in Southern Pacific


 Explorer 03

General

Designation	00006 / 58003A
Launch date	26 Mar 1958
Country of origin	United States
Mission	Scientific: ionosphere study
Perigee/Apogee	186/2799 km
Inclination	33.4°
Period	115.7 min
Launch vehicle	Jupiter C
Launch site	Cape Canaveral
End of life

Decay	28 Jun 1958


 Explorer 04

General

Designation	00009 / 58005A
Launch date	26 Jul 1958
Country of origin	United States
Mission	Scientific: ionosphere study
Perigee/Apogee	257/1352 km
Inclination	50.2°
Period	100.9 min
Launch vehicle	Jupiter C
Launch site	Cape Canaveral
End of life

Decay	23 Oct 1959


 Explorer 06

Also called S 2

General

Designation	00015 / 59004A
Launch date	7 Aug 1959
Country of origin	United States
Mission	Scientific: magnetosphere study
Perigee/Apogee	245/42400 km
Inclination	47°
Period	765 min
Launch vehicle	Thor Able
Launch site	Cape Canaveral
End of life

Decay	30 Jun 1961


 Explorer 07

General

Designation	00022 / 59009A
Launch date	13 Oct 1959
Country of origin	United States
Mission	Scientific: high atmosphere study
Perigee/Apogee	524/855 km
Inclination	50.3°
Period	98.6 min
Launch vehicle	Juno 2
Launch site	Cape Canaveral
Mass at launch	45 kg


 Explorer 08

General

Designation	00060 / 60014A
Launch date	3 Nov 1960
Country of origin	United States
Mission	Scientific: ionosphere study
Perigee/Apogee	394/1331 km
Inclination	49.9°
Period	102.2 min
Launch vehicle
Launch site	Cape Canaveral
Mass at launch	45 kg

First NASA satellite


 Explorer 09

General

Designation	00081 / 61004A
Launch date	16 Feb 1961
Country of origin	United States
Mission	Scientific: high atmosphere study
Perigee/Apogee	757/2433 km
Inclination	38.8°
Period	118 min
Launch vehicle	Scout #4
End of life

Decay	9 Apr 1964


 Explorer 10

Also called P-14

General

Designation	00098 / 61010A
Launch date	25 Mar 1961
Country of origin	United States
Mission
Perigee/Apogee	221/181100 km
Inclination	33°
Period	5013.9 min
Launch vehicle	Thor Delta #4
End of life

Decay	30 Jun 1961


 Explorer 11

General

Designation	00107 / 61013A
Launch date	27 Apr 1961
Country of origin	United States
Mission	Scientific: gamma-ray astronomy
Perigee/Apogee	480/1458 km
Inclination	28.8°
Period	104.5 min
Launch vehicle
Launch site	Cape Canaveral
External resources

http://heasarc.gsfc.nasa.gov/Images/pretty_pictures_explorer11.html


 Explorer 12

Also called EPE A

General

Designation	00170 / 61020A
Launch date	16 Aug 1961
Country of origin	United States
Mission	Scientific: magnetosphere study
Perigee/Apogee	790/79920 km
Inclination	33.4°
Period	1587.3 min
Launch vehicle	Thor Delta #6
End of life

Decay	30 Sep 1963


 Explorer 13

Also called S 55A

General

Designation	00180 / 61022A
Launch date	25 Aug 1961
Country of origin	United States
Mission	Scientific: observation of meteorites
Perigee/Apogee	125/1164 km
Inclination	37.7°
Period	97.5 min
Launch vehicle	Scout #6
End of life

Decay	28 Aug 1961


 Explorer 14

Also called EPE B and S 3A

General

Designation	00432 / 62051A
Launch date	2 Oct 1962
Country of origin	United States
Mission	Scientific: magnetosphere study
Perigee/Apogee	915/96959 km
Inclination	33.6°
Period	2157.9 min
Launch vehicle	Thor Delta #13
End of life

Decay	1 Jul 1966


 Explorer 15

Also called EPE C and S 3B

General

Designation	00445 / 62059A
Launch date	27 Oct 1962
Country of origin	United States
Mission
Perigee/Apogee	306/17610 km
Inclination	17.9°
Period	314.7 min
Launch vehicle	Thor Delta #14
End of life

Decay	19 Dec 1978


 Explorer 16

Also called S 55

General

Designation	00506 / 62070A
Launch date	16 Dec 1962
Country of origin	United States
Mission	Scientific: observation of meteorites
Perigee/Apogee	744/1159 km
Inclination	52°
Period	104.1 min
Launch vehicle	Scout #14


 Explorer 17

Also called AE A

General

Designation	00564 / 63009A
Launch date	3 Apr 1963
Country of origin	United States
Mission	Scientific: high atmosphere study
Perigee/Apogee	254/891 km
Inclination	57.6°
Period	96.1 min
Launch vehicle	Thor Delta #17
End of life

Decay	24 Nov 1966


 Explorer 18

Interplanetary Monitoring Probe, also called IMP 01

General

Designation	00693 / 63046A
Launch date	27 Nov 1963
Country of origin	United States
Mission	Scientific: magnetosphere study
Perigee/Apogee	192/197616 km
Inclination	33.3°
Period	5666.2 min
Launch vehicle	Thor Delta #21
End of life

Decay	30 Dec 1965


 Explorer 19

Atmospheric Density Explorer, also called ADE A

General

Designation	00714 / 63053A
Launch date	19 Dec 1963
Country of origin	United States
Mission	Scientific: high atmosphere study
Perigee/Apogee	597/2391 km
Inclination	78.6°
Period	115.9 min
Launch vehicle	Scout #24

Sphere in aluminum (3.65 m diameter, 7 to 9 kg)

End of life

Decay	10 May 1981


 Explorer 20

Also called IE A

General

Designation	00870 / 64051A
Launch date	25 Aug 1964
Country of origin	United States
Mission	Scientific: ionosphere study
Perigee/Apogee	855/1001 km
Inclination	79.9°
Period	103.6 min
Launch vehicle	Scout #30


 Explorer 21

Interplanetary Monitoring Probe, also called IMP 02

General

Designation	00889 / 64060A
Launch date	4 Oct 1964
Country of origin	United States
Mission	Scientific: magnetosphere study
Perigee/Apogee	191/95590 km
Inclination	33.5°
Period	2097 min
Launch vehicle	Thor Delta #26
End of life

Decay	30 Jan 1966


 Explorer 22

Also called Beacon B

General

Designation	00899 / 64064A
Launch date	10 Oct 1964
Country of origin	United States
Mission	Scientific: Geodesy and ionosphere study
Perigee/Apogee	872/1053 km
Inclination	79.7°
Period	104.3 min
Launch vehicle	Scout #32


 Explorer 23

Also called S 55C

General

Designation	00924 / 64074A
Launch date	6 Nov 1964
Country of origin	United States
Mission	Scientific: observation of meteorites
Perigee/Apogee	463/980 km
Inclination	51.9°
Period	99.2 min
Launch vehicle	Scout #33
End of life

Decay	29 Jun 1983


 Explorer 24

Atmospheric Density Explorer, also called ADE B

General

Designation	00931 / 64076A
Launch date	21 Nov 1964
Country of origin	United States
Mission	Scientific: high atmosphere study
Perigee/Apogee	530/2498 km
Inclination	81.4°
Period	116.3 min
Launch vehicle	Scout #34

Sphere in aluminum (3.65 m diameter, 7 to 9 kg)

End of life

Decay	18 Oct 1968


 Explorer 25

Also called Injun 4

General

Designation	00932 / 64076B
Launch date	21 Nov 1964
Country of origin	United States
Mission	Scientific: ionosphere study
Perigee/Apogee	524/2349 km
Inclination	81.4°
Period	114.6 min
Launch vehicle	Scout #34


 Explorer 26

Also called EPE D

General

Designation	00963 / 64086A
Launch date	21 Dec 1964
Country of origin	United States
Mission	Scientific: ionosphere study
Perigee/Apogee	284/10043 km
Inclination	19.8°
Period	205.7 min
Launch vehicle	Thor Delta #27


 Explorer 27

Also called Beacon C

General

Designation	01328 / 65032A
Launch date	29 Apr 1965
Country of origin	United States
Mission	Scientific: Geodesy and ionosphere study
Perigee/Apogee	932/1309 km
Inclination	41.2°
Period	107.7 min
Launch vehicle	Scout #36


 Explorer 28

Interplanetary Monitoring Probe, also called IMP 03

General

Designation	01388 / 65042A
Launch date	29 May 1965
Country of origin	United States
Mission	Scientific: magnetosphere study
Perigee/Apogee	229/261206 km
Inclination	30.5°
Period	8419.7 min
Launch vehicle	Thor Delta #31
End of life

Decay	4 Jul 1968


 Explorer 29

Also called Geos 1

General

Designation	01726 / 65089A
Launch date	6 Nov 1965
Country of origin	United States
Mission	Scientific: geodesy
Perigee/Apogee	1114/2273 km
Inclination	59.4°
Period	120.3 min
Launch vehicle	Thor Delta #34
Mass at launch	175 kg


 Explorer 30

Also called IQSY

General

Designation	01738 / 65093A
Launch date	19 Nov 1965
Country of origin	United States
Mission
Perigee/Apogee	667/871 km
Inclination	59.7°
Period	100.2 min
Launch vehicle	Scout #38


 Explorer 31

Also called DME A or ISIS X

General

Designation	01806 / 65098B
Launch date	29 Nov 1965
Country of origin	United States
Mission	Scientific: ionosphere study
Perigee/Apogee	502/2857 km
Inclination	79.8°
Period	120 min
Launch vehicle	Thor Agena B
Launch site	Vandenberg


 Explorer 32

Also AE B

General

Designation	02183 / 66044A
Launch date	25 May 1966
Country of origin	United States
Mission	Scientific: high atmosphere study
Perigee/Apogee	282/2723 km
Inclination	64.6°
Period	116 min
Launch vehicle	Thor Delta #38
End of life

Decay	22 Feb 1985


 Explorer 33

Interplanetary Monitoring Probe, also called IMP 04

General

Designation	02258 / 66058A
Launch date	1 Jul 1966
Country of origin	United States
Mission
Perigee/Apogee	85228/481417 km
Inclination	40.9°
Period	25863.5 min
Launch vehicle	Thor Delta #39


 Explorer 34

Interplanetary Monitoring Probe, also called IMP 05

General

Designation	02817 / 67051A
Launch date	24 May 1967
Country of origin	United States
Mission
Perigee/Apogee	242/214379 km
Inclination	67.1°
Period	6358.2 min
Launch vehicle	Thor Delta #49
End of life

Decay	3 May 1969


 Explorer 36

Also called Geos 2

General

Designation	03093 / 68002A
Launch date	11 Jan 1968
Country of origin	United States
Mission	Scientific: geodesy
Perigee/Apogee	1079/1572 km
Inclination	105.8°
Period	112.2 min
Launch vehicle	Thor Delta #56


 Explorer 38

Also called RAE 1

General

Designation	03307 / 68055A
Launch date	4 Jul 1968
Country of origin	United States
Mission	Scientific: radio-astronomy
Perigee/Apogee	5835/5861 km
Inclination	120.9°
Period	224.3 min
Launch vehicle	Thor Delta #57


 Explorer 39

Atmospheric Density Explorer, also called ADE C

General

Designation	03337 / 68066A
Launch date	8 Aug 1968
Country of origin	United States
Mission	Scientific: high atmosphere study
Perigee/Apogee	670/2538 km
Inclination	80.7°
Period	118.3 min
Launch vehicle	Scout #63

Sphere in aluminum (3.65 m diameter, 7 to 9 kg)

End of life

Decay	22 Jun 1981


 Explorer 40

Also called Injun 5

General

Designation	03338 / 68066B
Launch date	8 Aug 1968
Country of origin	United States
Mission	Scientific: ionosphere study
Perigee/Apogee	677/2494 km
Inclination	80.7°
Period	117.9 min
Launch vehicle	Scout #63


 Explorer 41

Interplanetary Monitoring Probe, also called IMP 07

General

Designation	03990 / 69053A
Launch date	21 Jun 1969
Country of origin	United States
Mission	Scientific: magnetosphere study
Perigee/Apogee	80374/98159 km
Inclination	86°
Period	4906.3 min
Launch vehicle	Thor Delta #69
End of life

Decay	23 Dec 1972


 Explorer 42

Also called Uhuru or SAS 1

General

Designation	04797 / 70107A
Launch date	12 Dec 1970
Country of origin	United States
Mission	Scientific: X-ray astronomy
Perigee/Apogee	521/570 km
Inclination	3°
Period	95.5 min
Launch vehicle	Scout #71

Discovered 200 X sources and the first black hole

End of life

Decay	5 Apr 1979


 Explorer 43

Interplanetary Monitoring Probe, also called IMP 08

General

Designation	05043 / 71019A
Launch date	13 Mar 1971
Country of origin	United States
Mission	Scientific: magnetosphere study
Perigee/Apogee	1845/203130 km
Inclination	31.2°
Period	5957.9 min
Launch vehicle	Thor Delta #83
End of life

Decay	2 Oct 1974


 Explorer 45

Also called SSS 1

General

Designation	05598 / 71096A
Launch date	15 Nov 1971
Country of origin	United States
Mission
Perigee/Apogee	272/18149 km
Inclination	3.2°
Period	322.8 min
Launch vehicle	Scout #77
End of life

Decay	10 Jan 1992


 Explorer 46

Also called MTS

General

Designation	06142 / 72061A
Launch date	13 Aug 1972
Country of origin	United States
Mission	Scientific: observation of meteorites
Perigee/Apogee	492/811 km
Inclination	37.7°
Period	97.7 min
Launch vehicle	Scout #79
End of life

Decay	2 Nov 1979


 Explorer 47

Interplanetary Monitoring Probe, also called IMP 09

General

Designation	06197 / 72073A
Launch date	23 Sep 1972
Country of origin	United States
Mission	Scientific: magnetosphere study
Perigee/Apogee	201100/235600 km
Inclination	17.2°
Period	17670 min
Launch vehicle	Thor Delta #90


 Explorer 48

Also called SAS 2

General

Designation	06282 / 72091A
Launch date	15 Nov 1972
Country of origin	United States
Mission	Scientific: gamma-ray astronomy
Perigee/Apogee	526/526 km
Inclination	1°
Period	95.2 min
Launch vehicle	Scout #81
End of life

Decay	20 Aug 1976


 Explorer 50

Interplanetary Monitoring Probe, also called IMP 10

General

Designation	06893 / 73078A
Launch date	26 Oct 1973
Country of origin	United States
Mission	Scientific: magnetosphere study
Perigee/Apogee	141185/288857 km mid-1996: 189024/247267 km
Inclination	28.7°
Period	17279 min mid-1996: 17646 min
Launch vehicle	Thor Delta #97
Technical data

Telemetry: 137.98 & 136.8 MHz (32 kbps)

Command: 148.98 MHz


 Explorer 51

Also called AE C

General

Designation	06977 / 73101A
Launch date	16 Dec 1973
Country of origin	United States
Mission	Scientific: high atmosphere study
Perigee/Apogee	155/4306 km
Inclination	68.1°
Period	132.5 min
Launch vehicle	Thor Delta #99
End of life

Decay	12 Dec 1978


 Explorer 52

Also called Hawkeye

General

Designation	07325 / 74040A
Launch date	3 Jun 1974
Country of origin	United States
Mission
Perigee/Apogee	469/125569 km
Inclination	89°
Period	3032 min
Launch vehicle	Scout #87
End of life

Decay	30 Apr 1978


 Explorer 53

Also called SAS 3

General

Designation	07788 / 75037A
Launch date	7 May 1975
Country of origin	United States
Mission	Scientific: X-ray astronomy
Perigee/Apogee	498/507 km
Inclination	3°
Period	94.7 min
Launch vehicle	Scout #91
End of life

Decay	9 Apr 1979


 Explorer 54

Also called AE D

General

Designation	08353 / 75096A
Launch date	6 Oct 1975
Country of origin	United States
Mission	Scientific: high atmosphere study
Perigee/Apogee	151/3819 km
Inclination	90.1°
Period	126.8 min
Launch vehicle	Thor Delta #115
End of life

Decay	12 Mar 1976


 Explorer 55

Also called AE E

General

Designation	08440 / 75107A
Launch date	20 Nov 1975
Country of origin	United States
Mission	Scientific: high atmosphere study
Perigee/Apogee	154/3002 km
Inclination	19.7°
Period	117.7 min
Launch vehicle	Thor Delta #117
End of life

Decay	10 Jun 1981


 EXPRESS (German)

EXPeriment REentry Space System

General

Designation	none assigned
Launch date	15 Jan 1995 at 13:45 UT
Country of origin	Germany
Mission	Experimentation of materials
Perigee/Apogee	110/250 km
Inclination	33°
Period
Launch vehicle	Mu 3S 2
Launch site	Kagoshima
Mass at launch	765 kg

The payload used a Russian-built reentry vehicle and the launch was carried out by the Japanese ISAS space agency. It was due to land in the Australian desert after a five day flight, but the TVC (thrust vector control) on the second stage malfunctioned 103 seconds after launch, and the fourth stage and payload entered a 110 x 250 km x 33 deg orbit, instead of the intended 270 x 380 km one. This failure was probably due to second-stage attitude-control oscillations that exhausted attitude-control fuel. The reentry capsule decay in Ghana whereas the service module reentered over the Pacific on its second orbit of the Earth.

The reentry vehicle carried two CATEX materials processing ovens, and three German (CETEX, PYREX and RAFLEX) and one Japanese (RTEX) heat shield material reentry experiments.

End of life

Decay	15 Jan 1995


 Program: Express

Also called Glavstar

Russian telecommunication program replacing Gorizont. Satellite are owned by Informcosmos and operated by Intersputnik.

Only the 2 first satellites are completely Russian made. New series should start with:

- Express A: 1 satellite to be launched in 1999, 12 C-band and 5 Ku-band transponders, payload provided by Alcatel. 2 other satellites are planned

- Express K: 3 satellites launched in 1999 & beyond: K1 should be based on a Spacebus-3000B with 52 transponders (32 C-band & 20 Ku-band); K2 should be similar to Eutelsat 3 Sesat and K3 a satellite jointly designed by NPO PM & Aerospatiale. This association of manufacturers is known ad the Troika Consortium.

- Express 2000: 1 satellite, payload provided by Hughes, 24 transponders

The Express slots (reservation names, not satellites) are:

Express 01	37.5°W
Express 02	14°W
Express 03	11°W
Express 04	40°E
Express 05	53°E
Express 06	80°E
Express 07	90°E
Express 08	96.5°E
Express 09	103°E
Express 10	140°E
Express 11	145°E
Express 12	155°W
Express 13	99°E


Program: Express

Express 1

Express 2

Express A1


Express' specifications

Prime contractor	NPO PM
Platform	NPO Express (similar to GALS)
Mass at launch	2500 kg
Mass in orbit
Diameter	3.6 m
Height	6.1 m
Solar array	twin panels, 21 m span
Stabilization	3-axis
DC power	2000 W
Design lifetime	5 years

Equipped with an advanced Xenon ion engine that reduces the amount of propellant needed to fine-tune the initial orbit and perform station-keeping maneuvers (SPT 100 , 8 units per satellite (including redundances) produced by Fakel CIS).

Beacons: 11.400 GHz (power: 0.1 W; EIRP: 14.5 dBW) and 3.800 GHz (power: 0.2 W; EIRP: 9 dBW)


Express antenna's specifications

Antenna	Frequency band	Function / Gain max	Coverage	Beam width	Steerability (degrees)
					North/South	West/East
A1	C	TX / 19.0	global	17°x17°	none	none
A2	C	TX / 30.0	spot	5°x5°	7.3/5	5.5/5.5
A3	C	TX / 20.7	quasi global	15°x15°	none	none
A4	C	TX / 26.5	elliptical	5°x11°	7.3/7.3	none
A5	C	TX / 20.7	quasi global	15°x15°	none	none
A6	C	TX / 26.5	elliptical	5°x11°	7.3/7.3	none
A7	C	RX / 19.0	global	17x17°	none	none
A8	C	RX / 26.5	elliptical	5°x11°	7.3/7.3	none
A9	Ku	RX and TX / 30.0	spot	5°x5°	7.3/5	5.5/5.5

See also the transponder/antenna connection diagram


Express' C-band

Main transponders	10
Backup transponders
Power	9 transponders of 10.5 W (TWTA) 1 transponder (#6) of 65 W (TWTA)
Bandwidth	all transponders: 34 MHz transponder #6: 40 MHz
Coverage and EIRP max	transponder #6: global beam (A1): 35.6 dBW spot beam (A2): 46.1 dBW 2 quasi global beams (A3 & A5): 28.9 or 31 dBW 2 zone beams (A4 & A6): 34.7 dBW
Polarization	uplink: LHCP downlink: RHCP


Express' Ku-band

Main transponders	2
Backup transponders
Power	60 W (TWTA)
Bandwidth	34 MHz
Coverage and EIRP max	spot beam (A9): 39.2 dBW
Polarization	uplink: V downlink: H


Express' transponder frequency chart (GHz)

C-band

LHCP Uplink	Transponder	RHCP Downlink	Comments
6.000	6	3.675	global or spot beam, 40 MHz
6.050	7	3.725	quasi global or zone beam
6.100	8	3.775	quasi global or zone beam
6.150	9	3.825	quasi global or zone beam
6.200	10	3.875	quasi global or zone beam
6.250	11	3.925	quasi global or zone beam
6.300	14	3.975	zone or spot beam
6.350	15	4.025	quasi global or zone beam
6.400	16	4.075	zone or spot beam
6.450	17	4.125	quasi global or zone beam
Ku-band

Horizontal Downlink	Transponder	Vertical Uplink
11.525	12	14.325
11.675	20	14.425


Express' transponder/antenna connections


 Express 1

General

Designation	23319 / 94067A
Launch date	13 Oct 1994 at 16:19 UT
Country of origin	CIS
Operator	Intersputnik
Mission	Telecommunications
Geostationary orbit	Express-02, 14°W
Launch vehicle	Proton #227

Test carried out in 71°E slot

Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder Frequency Chart

EIRP coverage (dBW)

C-band, quasi-global (A3 & A5)

C-band, hemispheric (A4)

C-band, spot (A2)

Ku-band, spot (A9)


Express 1's C-band EIRP: quasi-global A3 & A5


Express 1's C-band EIRP: spot A2

Add 7.9 dBW for transponder #6


Express 1's C-band EIRP: hemispheric A4


Express 1's Ku-band EIRP: spot A9


 Express 2

General

Designation	24435 / 96058A
Launch date	26 Sep 1996
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Express-06, 80°E
Launch vehicle	Proton #244

GE American Communications Inc. announced it will launch a international video programming satellite service on this bird aimed at the Indian sub-continent. The news programming will be in English and Hindi. Also GE Americom has a long-term agreement for five C-band and two Ku-band transponders.

Had a failure on 7 May 1999. Service has restored within hours.

Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder Frequency Chart

EIRP coverage (dBW)

C-band, quasi-global (A3)

C-band, hemispheric (A4)

Ku-band, spot (A9)


Express 2's C-band EIRP: quasi-global A3 & A5


Express 2's C-band EIRP: hemispheric A4


Express 2's Ku-band EIRP: spot A9


 Express A1

General

Designation
Launch date	planned in late 1999
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Express-06, 80°E
Launch vehicle	Proton
Technical data

Specifications

Prime contractor	NPO PM
Platform
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime

Alcatel supplied the payload

C-band

Main transponders	12
Backup transponders
Power
Bandwidth
Coverage
EIRP max
G/T max
Polarization
Ku-band

Main transponders	5
Backup transponders
Power
Bandwidth
Coverage
EIRP max
G/T max
Polarization


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 Program: Expressway

Project lead by Hughes to setup a $4 billion system of 14 GEO satellites to provide very high speed data rates around the world. The satellites should operate in V- (over 35 GHz) and Ku-band and lasers. Onboard switching processors are planned.

Expressway will consist of 14 satellites in 10 orbital slots, including 2 each colocated at 99°W, 101°W and 103°W slots over U.S., one each at 63°W and 53°W to serve Latin America, 2 at 10°E for Europe/Africa, one each at 48°E and 68.5°E for Europe/Asia, and one at 113°E and another at 119°E for Asia-Pacific.

588,000 T-1 circuits could be supported by Expressway with about 42,000 active users per satellite. Users will communicate directly to satellites via 2.5-m earth stations.

Hughes paid $250,000 to file application with FCC. Hughes said service will start 52 months after it receives license.  Hughes asked for 500 MHz allocation in Ku-band (12.75-14.5 GHz uplink and 10.7-12.75 GHz downlink) and 600 MHz in V-band (47.2-50.2 GHz uplink and 39.5-42.5 GHz downlink).

The system should cost $3.9 billion


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 Eyesat

Also called AO-27 or Amrad or Oscar 27

General

Designation	22825 / 93061C
Launch date	25 Sep 1993
Country of origin	United States
Mission	Telecommunications
Operator	Interferometrics (USA)
Perigee/Apogee	790/803 km
Inclination	98.7°
Period	100.8 min
Launch vehicle	Ariane V59

Aimed for transmiting data of localization and surveillance of industrial equipments for Interferometris.

External resources

http://www.amsat.org/amsat/sats/n7hpr/ao27.html

Technical data

Specifications

Prime contractor	Associazione Radioamatori Italiani
Platform	Amsat-NA Microsat
Mass at launch	12.5 kg
Mass in orbit
Length	230 mm
Width	230 mm
Height	235 mm
Stabilization	magnetic
DC power
Design lifetime	5-7 years
Frequency chart (MHz)

Uplink: 145.85 MHz FM

Downlink: 436.792 MHz FM


 Falcon Gold

General

Designation	25020 / 97065B
Launch date	25 Oct 1997
Country of origin	United States
Mission	Scientific
Perigee/Apogee	222/35263 km
Inclination	26.4°
Period	621 min
Launch vehicle	Atlas Centaur #111 + IABS

Cadets and Faculty of the United States Air Force Academy, in cooperation with University of Colorado-Colorado Springs have designed this satellite. It was attached to the upper stage.

This mission, named Falcon Gold, will be responsible for sampling the Global Positioning System (GPS) signal from behind the GPS constellation and downlinking spectrum samples to ground stations for post processing.

External resources

http://www.uccs.edu/~dasipple/masters/falcon_gold/falcon_gold.html

End of life

Out of service	9 Nov 1997
Cause	batteries dead (normal termination)
Decay

Estimated lifetime: 3 weeks

Downlink: 400.475 MHz


 Program: Fasat

Fuerza Aerea de chile Satellite

First Chilean satellite program. Purpose: remote sensing and telecommunication experiments

4 satellites are planned in this program

External resources

http://www.ee.surrey.ac.uk/EE/CSER/UOSAT/fasat/mission.html


Program: Fasat

Fasat Alfa

Fasat Bravo


 Fasat Alfa

General

Designation	n/a / 95046A Failed to separate from Sich 1
Launch date	31 Aug 1995 at 06:50 UT
Country of origin	Chile
Operator	Chilean Air Force (FACH: Fuerza Aerea de Chile)
Mission	Remote sensing
Perigee/Apogee	intended: 1050 km, polar orbit
Inclination
Period
Launch vehicle	Cyclone 3 #114

First Chilean satellite

Investigation of the failure showed a British docking mechanism had been at fault.

The satellite carried five grams of Chilean soil on board. It was to transmit regular information on ultraviolet radiation and the ozone layer over the antarctic. It was also to image the Chilean territory and carry out educational experiments for children with informative bulletins. The other 3 experiments, which would have been regularly carried out by Fasat Alfa, would have ment working with other satellite complexes, for the transmission and storage of data and space navigation systems.

When FACH proposed the construction of the first Chilean satellite in 1993, negotiations were arranged with Mexican, U.S. and British specialists. Surrey Satellite Technology Limited (SSTL) offered the most tempting deal to the Chileans, offering joint construction of the probe, technology transfer, and postgraduate training for the FACH technicians. The satellite was built using parts built by the Chilean National Aeronautical Company (ENAER), a branch of FACH, along with space computer technology donated by the Lockheed Company of the United States for experimental purposes.

Technical data

Specifications

Prime contractor	SSTL
Platform	UOSAT
Mass at launch	50 kg
Mass in orbit
Dimension	70 x 36 x 36 cm
Solar array
Stabilization
DC power
Design lifetime	6 years

It has a six meters long stabilization beam with a weight in its tail which will unfold once in orbit.


 Fasat Bravo

General

Designation	25395 / 98043B
Launch date	10 Jul 1998
Country of origin	Chile
Operator	Chilean Air Force (FACH: Fuerza Aerea de Chile)
Mission	Scientific:
Perigee/Apogee	269 / 283 km
Inclination	114
Period	90 minutes
Launch vehicle	Zenit #29

approx cost of the satellite: $2 million

FASat-Bravo is designed to monitor the destruction of the ozone layer above Chile. The sophisticated satellite will also take images of the Earth's surface and will carry an educational communications experiment for universities and schools in Chile.

Technical data

Specifications

Prime contractor	SSTL
Platform	micronsat
Mass at launch	50 kg
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime


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 Program: Faisat

Little LEO satellite project from Final Analysis. It should provide global store and forward data communications.

The constellation of 26 satellites (plus 4 spares) will be operated by FACS (Final Analysis Communication Services). This system is called infosat. Each of the launches can host a secondary payload. It enables experiments to be flown without financial risk (payment after orbit achievement), 25 kg max. FCC authorized on 1st April 1998.

FAI plans to launch a constellation of 26 satellites 4 planes of six each at 66°, plus 2 birds in individual 83° orbits for polar coverage to build a complete low data rate LEO comsat system; Russian launchers will be used throughout (Cosmos). The network should be fully deployed in 2001.

Faisat-Coscon agreement

Alliance (Oct 1995) of Final Analysis & Polyot Enterprises for global mobile and fixed satellite communications. They intend to manufacture and launch small satellites into low earth orbit. The alliance also intends to market mobile and fixed satellite communications on a global basis with service providers to be selected. The alliance is named FAISAT(TM)-COSCON after the planned commercial satellites of the two companies.

Polyot will be the service provider in Russia and the CIS countries. Final Analysis will provide training in business development, marketing and sales to Polyot for their commercial services.

They will deliver advanced digital data services (non-voice) to include delivery of low-cost applications for SCADA, asset tracking and environmental monitoring, messaging and e-mail.

The first experimental satellite is due early 1996. The launching services will be provided by Polyot: 4 dedicated Cosmos rockets (26 satellites to be launched)

Contact

Polyot (Omsk, Russia)

Tel/Fax: +7-3812-579-201

Technical data

Uplink

148.0-149.9 MHz (shared) & 149.9-150.05 MHz with restrictions:

148-148.250 MHz: shared with Leo One, Orbcomm and E-sat

148.750-148.855 MHz: shared with Leo One, Orbcomm and E-sat

148.855-148.905 MHz: may be used if E-sat does not use it, and if so must be shared with Leo One and Orbcomm

148.905-148.955 MHz: may be used if S80-1 does not use it, and if so must be shared with Leo One and Orbcomm

148.955-148.810 MHz: shared with Leo One and Orbcomm

excluded: 149.585-149.635 MHz for exclusive use of Orbcomm until relocation in the 150-150.05 MHz

Downlink

137.0-138.0 MHz (shared) & 400.15-401.0 MHz (shared) with restrictions:

137.025-137.175 MHz & 137.825-138.00 MHz: used by NOAA, those bands can be used on a secondary basis with time-sharing with NOAA and E-sat

137.333-1.4125 MHz, 137.475-137.525 MHz, 137.595-137.645 MHz, and 137.753-137.787 MHz: used by NOAA, those channels must be time-shared with NOAA and E-sat

400.505-400.5517 MHz and 400.5983-400.645 MHz: time-shared with VITA's system


Program: Faisat

Faisat 1

Faisat 1A

Faisat 2V


 Faisat 1

General

Designation	23465 / 95002C
Launch date	24 Jan 1995 at 03:54 UT
Country of origin	United States
Mission	Experimental: communications
Perigee/Apogee	967/1021 km
Inclination	82.9°
Period	105 min
Launch vehicle	Cosmos 3C
Launch site	Plesetsk LC132
Mass at launch	115 kg

This is a prototype of the satellites to form the infosat network.

This bird was modified by FAI from an existing satellite bus whose mission was cancelled (probably a DARPA satellite). The satellite also carries a small thermal-control experiment for USAF Phillips Lab.


 Faisat 2V

Also called Vitasat 1R

General

Designation	24954 / 97052B
Launch date	23 Sep 1997
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	1000 km
Inclination	83°
Period	105 min
Launch vehicle	Cosmos 3M
Launch site	Plesetsk LC132

Should have been launched in April 1997 with Cosmos 2341 Launch cost approx. $100,000  Power problems have been reported when operating in eclipse.

Equipped with a VHF/UHF scanner to map the use of frequencies below 1 GHz.

It carries the VITA secondary payload. It enables the delivery back and forth of email through gateways around the world. The payload is based on a Loral RS 6000 Command ad Data Handling processor with 16 MB of storage. Uplink in the 148-149.9 MHz band, Downlink tunable in the 400-401 MHz band, nominal downlink: 400.55 MHz RHCP 1 active transponder (+ 1 spare) of 15 W

Technical data

Specifications

Prime contractor
Platform	piggyback bus (100 kg)
Mass at launch	114.5 kg
Mass in orbit
Dimension deployed	1.8 m diameter x 6.8 m length
Stabilization	gradient stabilized
DC power	75 W
Design lifetime	5 years

From earth mobile equipment: Uplink: 455-456 and 459-460 MHz, Downlink: 400.62 MHz and 400.55 MHz, GMSK modulation, with Forward Error Correction, 4800 and 9600 bps

Command: 148.7 MHz ?

Uplink to satellite: up to 19.2 kbps, Downlink from satellite: up to 128 kbps (256 kbps in the dedicated bus version). The satellite carries a frequency scanner to dynamically select free spectrum (1 MHz scan in 300 Hz segments every second)

Has an on-board GPS receiver. Data is handled by a RISC 6000 processor, 160 MB RAM


 Faisat 1A

General

Designation
Launch date	initially planned in 2000
Country of origin	United States
Mission	Experimental: communications
Perigee/Apogee	1000 km
Inclination	83°
Period
Launch vehicle	Cosmos 3C
Launch site	Plesetsk

RA Ascending Node: 90°


 FAST

Fast Auroral Snapshot Explorer, also called SMEX 2

General

Designation	24285 / 96049A
Launch date	21 Aug 1996
Country of origin	United States
Mission	Scientific: magnetosphere study
Perigee/Apogee	350/4200 km
Inclination	83°
Period	133 min
Launch vehicle	Pegasus #13

The spacecraft will probe the physical processes that produce auroras and add signifcantly to the understanding of our near-Earth space environment.

External resources

http://sunland.gsfc.nasa.gov/smex/fast/

http://plasma2.ssl.berkeley.edu/fast/

http://www510.gsfc.nasa.gov/smex/fastpg.htm

http://www-ssc.igpp.ucla.edu/fast/Welcome.html

Technical data

Specifications

Prime contractor
Platform
Mass at launch	191 kg
Payload mass	51 kg
Dimension	octogonal
Solar array
Stabilization	spin stabilized, 12 rpm
DC power	52 W
Design lifetime	1 year

Telemetry: 2215.0 MHz (realtime: 4 kbps, playback: 900/1500/2250 kbps)

Command: 2039.65 MHz (realtime: 2 kbps)

Instruments:

Electric Field Experiment: to provide data on plasma density and electron temperature

Magnetic Field Experiment: 2 magnetometers

Time-of-Flight Energy Angle Mass Spectrograph (TEAMS)

Electrostatic Analyzers (ESA): measurements from 3 eV to 30 KeV


 Fedsat

Australian research satellite to be launched in late 2000. It will carry experiments for navigation, magnetic field measurement, profiling the Earth's atmosphere, and various communication tests.

800 km orbit

Technical data

Specifications

Prime contractor	SIL (subsidiary of Spacedev, UK-based)
Platform
Mass at launch	58 kg
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime	3 years

The satellite will be operated and integrated by Cooperative Research Centre on Satellite Systems, a group comprising Australian universities, firms and government entities.


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 Firewheel

End of life

Out of service	23 May 1980
Cause	Explosed with Ariane L02

Was operated by Max Plank INST.


 Program: Fleetsatcom

American military geostationary telecommunications satellite program

Contact

Operator: Naval Space Command

Command & control: Air Force Space Command

External resources

http://www.fas.org/spp/military/program/com/fltsat.htm

Fleetsatcom 7 & 8 carry an experimental EHF package for terminal applications, probably close to the one on UHF and on Milstar. The terminal is know as AN/USC-38(V)


Fleetsatcom's specifications

Prime contractor	TRW
Platform
Mass at launch	2250 kg
Mass in orbit	1043 kg
Dimension	hexagonal: 2.43 m (diameter) x 1.27 m (high) With a 4.88 m diameter antenna
Solar array	13.2 m
Stabilization	3-axis
DC power	BOL: 2000 W
Design lifetime	5 years

Telemetry in 7.250-7.750 GHz. Would also have uplink in 7.9-8.025 GHz


Fleetsatcom's UHF-band (244-263 MHz)

Each satellite has 23 communications channels, 10 of which are used by the Navy for communications between its land forces, ships, and aircraft. The Air Force uses 12 of the channels as part of its satellite communications system for command and control of nuclear forces. One channel is reserved for U.S. national command authorities.


Program: Fleetsatcom

Fleetsatcom 1

Fleetsatcom 2

Fleetsatcom 3

Fleetsatcom 4

Fleetsatcom 5

Fleetsatcom 6

Fleetsatcom 7

Fleetsatcom 8


 Fleetsatcom 1

Also called OPS 6391

General

Designation	10669 / 78016A
Launch date	9 Feb 1978
Country of origin	United States
Mission	Military: telecommunications
Geostationary orbit	see below
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
Location

Begin	End	Position
L: 9 Feb 1978		100°W
Mar 1995	Dec 1996	15°W, inclined
Feb 1997	Mar 1999	72°E, inclined
		orbit classified
Technical data

Specifications

Payload


 Fleetsatcom 2

Also called OPS 6392

General

Designation	11353 / 79038A
Launch date	4 May 1979
Country of origin	United States
Mission	Military: telecommunications
Geostationary orbit	75°E
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
End of life

Out of service	yes
Technical data

Specifications

Payload


 Fleetsatcom 3

Also called OPS 6393

General

Designation	11669 / 80004A
Launch date	18 Jan 1980
Country of origin	United States
Mission	Military: telecommunications
Geostationary orbit	23°W, inclined
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
End of life

Out of service	Sep 1995
Technical data

Specifications

Payload


 Fleetsatcom 4

Also called OPS 6394

General

Designation	12046 / 80087A
Launch date	31 Oct 1980
Country of origin	United States
Mission	Military: telecommunications
Geostationary orbit	172°E, inclined (till Mar 1999 when the orbit was classified)
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
Technical data

Specifications

Payload


 Fleetsatcom 5

General

Designation	12635 / 81073A
Launch date	6 Aug 1981
Country of origin	United States
Mission	Military: telecommunications
Geostationary orbit	n/a
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
End of life

Out of service	Aug 1981
Cause	The satellite reached GTO, but imploding payload shroud damaged it
Technical data

Specifications

Payload


 Fleetsatcom 6

End of life

Out of service	26 Mar 1987
Cause	Launch failure (Atlas Centaur)
Technical data

Specifications

Payload


 Fleetsatcom 7

Also called USA 020

General

Designation	17181 / 86096A
Launch date	5 Dec 1986
Country of origin	United States
Mission	Military: telecommunications
Geostationary orbit	100°W, inclined (till Mar 1999 when the orbit was classified)
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
Technical data

Specifications

Payload

Has an additional EHF payload


 Fleetsatcom 8

Also called USA 046

General

Designation	20253 / 89077A
Launch date	25 Sep 1989
Country of origin	United States
Mission	Military: telecommunications
Geostationary orbit	23°W, inclined (till Mar 1999 when the orbit was classified)
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
Technical data

Specifications

Payload

Has an additional EHF payload


Forte
 Forté

Fast On-orbit Recording of Transient Events, also called P94-1

General

Designation	24920 / 97047A
Launch date	29 Aug 1997
Country of origin	United States
Mission	Scientific:
Perigee/Apogee	800 km
Inclination	70°
Period	101 min
Launch vehicle	Pegasus XL #17

Advanced radio frequency (RF) impulse detection and characterization experiment. Emphasis is on the measurement of electromagnetic pulses (EMP), primarily due to lightning, within a noise environment dominated by continuous wave (CW) carriers, such as TV and FM stations. Optical sensors will augment the RF system in characterizing lightning events. A principal goal is to develop a comprehensive understanding of the correlation between the optical flash and the very high frequency (VHF) emissions from lightning.

External resources

http://sst.lanl.gov/nis-projects/forte/

Technical data

Specifications

Prime contractor	Los Alamos National Laboratory & Sandia National Lab.
Platform
Mass at launch	212 kg
Mass in orbit
Dimension
Solar array
Stabilization	3-axis
DC power	55 W
Design lifetime	3 years

First US satellite entirely made of composite materials (the 41 kg structure was built by Composite Optics). It will feature a 10.7 m antenna

RF system: receiver covering 30-300 MHz and high speed digitizers

Optical system: coarse imager 10 x 10 km resolution

Beacon: 401.565 MHz


 FR 1

General

Designation	01814 / 65101A
Launch date	6 Dec 1965
Country of origin	France
Mission	Scientific: ionosphere study
Perigee/Apogee	696/707 km
Inclination	75.9°
Period	98.8 min
Launch vehicle	Scout #39
Mass at launch	62 kg
End of life

Out of service	28 Feb 1969
Cause	Stopped transmitting


 Freja

In the nordic mythology Freja is the goddess of Love and fecundity

General

Designation	22161 / 92064A
Launch date	6 Oct 1992
Country of origin	Sweden
Operator	Swedish Space Corporation
Mission	Scientific: magnetosphere study
Perigee/Apogee	586/1767 km
Inclination	63°
Period	108.9 min
Launch vehicle	Long March 2
Mass at launch	230 kg

Successor of Viking with instruments for research into the Earth's magnetosphere and the aurora. Carries magnetic particles detectors and magnetic field captors.

Cost: $150 million

External resources

http://www.ssc.se/ssd/ssat/freja.html

End of life

Out of service	16 Oct 1996
Cause	out of control
Technical data

Specifications

Prime contractor	Swedish Space Corp.
Mass at launch	265 kg
Diameter	2.2 m
Stabilization	Spin stabilized (10 rpm)
DC power	EOL: 130 W
Design lifetime	2 years
Payload

Boom length	15 m
Telemetry data rate	250-500 kbps (2 Mbps burst)
Transmitter power	2 W
Frequencies	400.55 MHz (1200 bps), 2208.163 MHz


 Program: Fuji

Means "glycine flower"

Japanese small telecommunications satellite program


Program: Fuji

Fuji 1A

Fuji 1B

Fuji 2


 Fuji 1A

Also called JAS 1A or FO-12 or Oscar 12

General

Designation	16909 / 86061B
Launch date	12 Aug 1986
Country of origin	Japan
Mission	Telecommunications
Perigee/Apogee	1479/1497 km
Inclination	50°
Period	115.7 min
Launch vehicle	H1
End of life

Out of service	fall 1989
Cause	power problems

Launched with Experimental Geodetic Payload - first multi-payload launch by NASDA.

Technical data

Specifications

Mass at launch	50 kg
Stabilization	passive magnetic
DC power	8.5 W (6 Ah NiCd battery)


 Fuji 1B

Also called JAS 1A or FO-20 or Oscar 20

General

Designation	20480 / 90013C
Launch date	7 Feb 1990
Country of origin	Japan
Mission	Telecommunications
Perigee/Apogee	908/1743 km
Inclination	99°
Period	112.2 min
Launch vehicle	H1
Mass at launch	50 kg

Only operates in analog mode after failures. The beacon has been delimited to sending a permanent carrier.

External resources

http://www.amsat.org/amsat/sats/n7hpr/fo20.html

Technical data

Packet Radio Mailbox and Digipeater, and a mode J analog transponder.

Mode JD uplink	1200bps Manchester coded (Biphase-L) FSK (FM) AX.25 145.850 145.870 145.890 145.910 MHz
Mode JD downlink	1200bps BPSK (SSB) AX.25 435.910 MHz
Mode JA uplink	145.900 - 146.000 MHz (SSB, CW)
Mode JA downlink	435.900 - 435.800 MHz (SSB, CW, inverting)
Mode JA Beacon	435.795 MHz


 Fuji 2

Also called JAS 2 or FO-29 or Oscar 29

General

Designation	24278 / 96046B
Launch date	17 August 1996
Country of origin	Japan
Mission	Telecommunications
Perigee/Apogee	797/1317 km
Inclination	98.6°
Period	106 min
Launch vehicle	H2 #4

Only operates in analog mode after a failure

External resources

http://www.jarl.or.jp/English/5_Fuji/ejasmenu.htm

Technical data

Specifications

Prime contractor
Platform
Mass at launch	50 kg
Mass in orbit
Dimension	0.44 x 0.47 m
Solar array
Stabilization
DC power
Design lifetime

Packet Radio Mailbox and Digipeater, and a mode J analog transponder.

Mode JD uplink	1200bps Manchester coded (Biphase-L) FSK (FM) AX.25 145.850 145.870 145.890 145.910 MHz
Mode JD downlink	1200bps BPSK (SSB) AX.25 435.910 MHz
Total transmitting power is 1W

Mode JA uplink	145.900 - 146.000 MHz (SSB, CW)
Mode JA downlink	435.800 - 435.900 MHz (SSB, CW, inverting)
Mode JA Beacon	435.795 MHz
Total transmitting power is 1W, of which beacon is 100 mW


 FUSE

Far Ultraviolet Spectroscopic Explorer

General

Designation	25791 / 99035A
Launch date	24 Jun 1999
Country of origin	United States
Mission	Scientific: Astronomy
Perigee/Apogee	800 km
Inclination	25°
Period
Launch vehicle	Delta 2 #271

FUSE will access the wavelength below 1180 Angstroms (the HST STIS cutoff) with high resolution astronomical spectroscopy in the far-ultraviolet spectral region.No long-term observatory since Copernicus (1972) has possessed this capability.

Total project cost: $171 million including $120 million for the satellite. Funded by NASA. French and Canadian space agency share observation time. French CNES paid 6 million EUR.

External resources

http://fuse.pha.jhu.edu/

Technical data

Specifications

Prime contractor	OSC
Platform
Mass at launch	1360 kg
Mass in orbit
Dimension	1.2 x 1.8 x 5.5 m
Solar array
Stabilization
DC power
Design lifetime	3 years

Carries a telescope with 4 mirrors. It explores in the 912 to 1187 angstrom range. The instrument is provided by the John Hopkins University.


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 Program: Galaxy

Telecommunication program, now operated by Panamsat. It was previously operated by HCI


Program: Galaxy

Galaxy 1

Galaxy 1R

Galaxy 1R failure

Galaxy 2

Galaxy 3

Galaxy 3C

Galaxy 3R

Galaxy 4

Galaxy 4R

Galaxy 5

Galaxy 6

Galaxy 7

Galaxy 8i

Galaxy 9

Galaxy 10

Galaxy 10R

Galaxy 11


Galaxy 1, 2, 3 & 6's specifications

Prime contractor	Hughes
Platform	HS-376
Mass at launch	1200 kg
Mass in orbit	709 kg
Diameter	2.16 m
Height	6.6 m (2.84 m stowed)
Stabilization	Spin stabilized
DC power	BOL: 990 W Eclipse: 2 nickel-cadmium batteries
Design lifetime	10 years


Galaxy 1, 2 & 3's C-band

Main transponders	24
Backup transponders	6
Power	9 W (TWTA)
Bandwidth	36 MHz
Coverage
EIRP max	34 dBW
Polarization	linear

Antenna: 1.8 m diameter with two reflecting surfaces. One surface is sensitive to V polarization and the other to H.


Galaxy 4, 7 & 3R's specifications

Prime contractor	Hughes
Platform	HS-601
Mass at launch	2950 kg
Mass in orbit	BOL: 1692 kg EOL: 1320 kg
Dimension	2.7 x 3.6 x 3.1 m
Solar array	24.7 m span
Stabilization	3-axis
DC power	BOL: 6000 W EOL: 4700 W
Design lifetime	15 years

2 antennas of 2.44 m x 1.83 m: C-band on the West side and Ku-band and on the East


Galaxy 4, 7 & 3R's C-band

Main transponders	24
Backup transponders	6
Power	16 W (SSPA)
Bandwidth	36 MHz
Coverage & EIRP max	CONUS: 42 dBW Alaska, Hawaii: 33 dBW
Polarization	linear

Strap-crossing: transponders 18 and 24 can be feed by the Ku-band transponders 17 and 23 respectively


Galaxy 4 & 7's Ku-band

Main transponders	24
Backup transponders	6
Power	50 W (TWTA)
Bandwidth	8 transponders of 54 MHz 16 transponders of 27 MHz
Coverage
EIRP max	45 dBW
Polarization	linear

Strap-crossing: transponders 17 and 23 can be feed by the C-band transponders 18 and 24 respectively


Galaxy 1R, 5 & 9's specifications

Prime contractor	Hughes
Platform	HS-376
Mass at launch
Mass in orbit	788 kg
Diameter	2.16 m
Height	7.53 m (3.11 m stowed)
Stabilization	Spin stabilized
DC power	BOL: 1163 W Eclipse: 2 super nickel-cadmium batteries
Design lifetime	10 years


Galaxy 1R, 5 & 9's C-band

Main transponders	24
Backup transponders	6
Power	16 W (TWTA)
Bandwidth	36 MHz
Coverage	CONUS, Alaska, Hawaii, Caribbean
EIRP max	38 dBW
Polarization	linear

Antenna: 1.8 m diameter with two reflecting surfaces. One surface is sensitive to V polarization and the other to H.


 Galaxy 1

General

Designation	14158 / 83065A
Launch date	28 Jun 1983
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	133°W
Launch vehicle	Thor Delta #170
End of life

Out of service	Apr 1994
Technical data

Specifications

C-band

C-band transponder frequency chart


 Galaxy 1R failure

General

Launch date	22 Aug 1992
Country of origin	United States
Mission	Telecommunications
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
End of life

Out of service	23 Aug 1992
Cause	Fail to orbit because the launcher's 3rd stage malfunctioned

Was an HS-376


 Galaxy 1R

General

Designation	23016 / 94013A
Launch date	19 Feb 1994
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	133°W
Launch vehicle	Delta 2 #225

The launch was aborted on 9 Feb 1994 during main engine ignition and the vehicle did not leave the pad.

Technical data

Specifications

C-band

C-band transponder frequency chart

EIRP coverage (dBW)

C-band Horizontal

C-band Vertical


Galaxy 1R's EIRP (C-band Horizontal)


Galaxy 1R's EIRP (C-band Vertical)


 Galaxy 2

General

Designation	14365 / 83098A
Launch date	22 Sep 1983
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	74°W
Launch vehicle	Thor Delta #173
End of life

Out of service	May 1994
Technical data

Specifications

C-band

C-band transponder frequency chart


 Galaxy 3

General

Designation	15308 / 84101A
Launch date	21 Sep 1984
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	93.5°W
Launch vehicle	Thor Delta #176
End of life

Out of service	Oct 1995
Cause	was deorbited
Technical data

Specifications

C-band

C-band transponder frequency chart


 Galaxy 3R

General

Designation	23741 / 95069A
Launch date	15 Dec 1995
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	95°W
Launch vehicle	Atlas 2A #97
Mass at launch	3380 kg

Cost: $150 million

Using a combination of digital compression and tightly focused spot beams, Galaxy 3R will used 24 Ku-band transponders to deliver as many as 144 channels of digital video and 60 channels of CD- quality audio via 24-inch (60 cm) dishes. The service was called Galaxy Latin America. In early 1998 the service was moved to Galaxy 8i.

A beam of the satellite was then moved to the US in order to extend the DirecTV programming.

Technical data

Specifications

C-band

C-band transponder frequency chart

Ku-band transponder frequency chart

EIRP coverage (dBW)

C-band Horizontal

C-band Vertical

Ku-band

Main transponders	24
Backup transponders	6
Power	63 W (TWTA)
Bandwidth	16 transponders of 27 MHz (horizontal) 8 transponders of 54 MHz (vertical)
Coverage	2 beams (12 transponders each): North America
EIRP max	49 dBW
Polarization	linear
Frequencies	Uplink: 14.0 - 14.500 GHz Downlink: 11.7-12.2 GHz

Downlink frequencies where switched from 11.450 - 11.750 GHz circular (with coverage to Latin America and Brazil on 2 beams) to 11.7-12.2 GHz linear (coverage to North America) sometime in Apr 1998 after Galaxy 8i went operational. It is unclear if the uplink frequencies also changed.

Strap-crossing: transponders 17 and 23 can be feed by the C-band transponders 18 and 24 respectively


Galaxy 3R's EIRP (C-band Horizontal)


Galaxy 3R's EIRP (C-band Vertical)


 Galaxy 3C

Was also called PAS 9, but this denomination was reused for another satellite

General

Designation
Launch date	4th quarter of 1999
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	95°W
Launch vehicle	Proton

Will replace Galaxy 3R

Technical data

Specifications

Prime contractor	Hughes
Platform	HS-702
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime
C-band

Main transponders	24
Backup transponders
Power
Bandwidth	36 MHz
Coverage
EIRP max
G/T max
Polarization
Ku-band

Main transponders	24
Backup transponders
Power
Bandwidth	16 x 27 MHz 8 x 54 MHz
Coverage
EIRP max
G/T max
Polarization


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 Galaxy 4

General

Designation	22694 / 93039A
Launch date	25 Jun 1993
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	99°W
Launch vehicle	Ariane V57

A fuel cell rupture occured (approx. 22:20 UT on 19 May 1998). The attitude control and backup failed. The satellite was declared a total loss on 20 May. Insurance is expected to pay $160 million.

The failure affected millions of pager accross the US. Galaxy 6 was preempted to replace the satellite.

End of life

Out of service	20 May 1998
Cause	failure
Technical data

Specifications

C-band

Ku-band

C-band transponder frequency chart

Ku-band transponder frequency chart

EIRP coverage (dBW)

C-band Horizontal

C-band Vertical

Ku-band Horizontal

Ku-band Vertical

Galaxy 4 also has a special footprint in Ku-band for Hawaii (44 dBW), Alaska (40 dBW) and Puerto Rico (44 dBW), but only for some vertical transponders.

Vertically polarized transponders are theoretically the only transponders that can be made into half transponders. Cross-strapping: C-band transponders 18 and 24 can cross-strap to Ku-band transponders 17 and 23.

Launched using the PVA (Perigee Velocity Augmentation) technic. The transfert orbit is 200/27975 km and then the apogee is upped to 35975 km with the satellite's kick motor and then gradually circularized.


Galaxy 4's EIRP (C-band Horizontal)


Galaxy 4's EIRP (C-band Vertical)


Galaxy 4's EIRP (Ku-band Horizontal)


Galaxy 4's EIRP (Ku-band Vertical)


 Galaxy 4R

General

Designation
Launch date	4th quarter of 1999
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	99°W
Launch vehicle

To replace Galaxy 6

Technical data

EIRP coverage (dBW)

C-band

Ku-band

G/T coverage (dB/K)

C-band

Ku-band

Specifications

Prime contractor	Hughes
Platform	HS-601HP
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization	3-axis
DC power
Design lifetime	15 years

Beacons: 4.198125 V and 4.199625 H GHz

ULPC: 12.195 V and 11.701 H GHz

C-band

Main transponders	24
Backup transponders	4
Power	40 W
Bandwidth	36 MHz
Coverage	North America
EIRP max	41 dBW
G/T max	0 dB/K
Polarization	linear H/V
SFD	-94 dBW/m² (at 0 G/T & 0 dB attenuation)
Frequencies	Uplink: 5.925 - 6.425 GHz Downlink: 3.700 - 4.200 GHz

C-band transponder frequency chart

Ku-band

Main transponders	24
Backup transponders	4
Power	108 W
Bandwidth	36 MHz
Coverage	North America
EIRP max	46 dBW
G/T max	1 dB/K
Polarization	linear H/V
SFD	-94 dBW/m² (at 0 G/T & 0 dB attenuation)
Frequencies	Uplink: 14.000 - 14.500 GHz Downlink: 11.700 - 12.200 GHz
Ku-band transponder frequency chart (GHz)

Horizontal Uplink	Horizontal Downlink	Transponder	Vertical Downlink	Vertical Uplink
	11.720	1		14.020
14.040		2	11.740
	11.760	3		14.060
14.080		4	11.780
	11.800	5		14.100
14.120		6	11.820
	11.840	7		14.140
14.160		8	11.860
	11.880	9		14.180
14.200		10	11.900
	11.920	11		14.220
14.240		12	11.940
	11.960	13		14.260
14.280		14	11.980
	12.000	15		14.300
14.320		16	12.020
	12.040	17		14.340
14.360		18	12.060
	12.080	19		14.380
14.400		20	12.100
	12.120	21		14.420
14.440		22	12.140
	12.160	23		14.460
14.480		24	12.180


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Galaxy 4R's G/T (C-band)


Galaxy 4R's EIRP (C-band)


Galaxy 4R's G/T (Ku-band)


Galaxy 4R's EIRP (Ku-band)


 Galaxy 5

General

Designation	21906 / 92013A
Launch date	14 Mar 1992
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	125°W
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
Technical data

Specifications

C-band

C-band transponder frequency chart

EIRP coverage (dBW)

C-band Horizontal

C-band Vertical


Galaxy 5's EIRP (C-band Horizontal)


Galaxy 5's EIRP (C-band Vertical)


 Galaxy 6

General

Designation	20873 / 90091B
Launch date	12 Oct 1990
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V39

This satellite is Westar 6S (Westar 6's backup satellite) modified. It should serve as backup for Galaxy 7 once Galaxy 11 is launched.

Location

Begin	End	Position
L: 12 Oct 1990		93°W
< Nov 1991	May 1992 >	99°W
< Oct 1993	early 1994	103°W
spring 1994	20 May 1998	74°W
late May 1998		99°W

Will move back to 74°W once Galaxy 4R will be launched.

Technical data

Specifications

EIRP coverage (dBW)

Horizontal

Vertical

C-band

Main transponders	24
Backup transponders	6
Power	10.2 W (TWTA)
Bandwidth	36 MHz
Coverage	CONUS, Alaska, Hawaii, Caribbean
EIRP max	39 dBW
Polarization	linear

C-band transponder frequency chart


Galaxy 6's EIRP (C-band Horizontal)


Galaxy 6's EIRP (C-band Vertical)


 Galaxy 7

General

Designation	22205 / 92072A
Launch date	28 Oct 1992
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	91°W
Launch vehicle	Ariane V54

The primary control processor failed.

Technical data

Specifications

C-band

Ku-band

C-band transponder frequency chart

Ku-band transponder frequency chart

EIRP coverage (dBW)

C-band Horizontal

C-band Vertical

Ku-band Horizontal

Ku-band Vertical

The spacecraft was launched using the PVA (Perigee Velocity Augmentation) technic. The transfert orbit was 200/27975 km and then the apogee was upped to 35975 km with the satellite's kick motor and then gradually circularized.

Vertically polarized transponders are theoretically the only transponders that can be made into half transponders. Cross-strapping: C-band transponders 18 and 24 can cross-strap to Ku-band transponders 17 and 23.


Galaxy Ku-band frequency chart
 Ku-band transponder frequency chart (GHz)

Horizontal Uplink	Horizontal Downlink	Transponder	Vertical Downlink	Vertical Uplink
14.020		1	11.720
	11.750	2		14.050
14.050		3	11.750
14.080		4	11.780
	11.810	5		14.110
14.110		6	11.810
14.140		7	11.840
	11.870	8		14.170
14.170		9	11.870
14.200		10	11.900
	11.930	11		14.230
14.230		12	11.930
14.260		13	11.960
	11.990	14		14.290
14.290		15	11.990
14.320		16	12.020
	12.050	17		14.350
14.350		18	12.050
14.380		19	12.080
	12.110	20		14.410
14.410		21	12.110
14.440		22	12.140
	12.170	23		14.470
14.470		24	12.170


Galaxy 7's EIRP (C-band Horizontal)


Galaxy 7's EIRP (C-band Vertical)


Galaxy 7's EIRP (Ku-band Horizontal)


Galaxy 7's EIRP (Ku-band Vertical)


 Galaxy 8i

i stands for International

General

Designation	25086 / 97078A
Launch date	8 Dec 1997
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	95°W
Launch vehicle	Atlas 2 #112

This satellite should replace Galaxy 3R but could remain colocated. It's antennas will cover a larger area than the Galaxy 3R satellite, especially over the Caribbean and Central America.

Tested from 79 deg W

Battery problems were reported.

Technical data

Specifications

Prime contractor	Hughes
Platform	HS-601HP
Mass at launch	3560 kg
Mass in orbit
Dimension
Solar array
Stabilization
DC power	5000 W or 9900 W
Design lifetime	15 years

Xenon propulsion (XIPS)

Ku-band

Main transponders	32
Backup transponders
Power	115 W
Bandwidth	24 MHz
Coverage	2 beams: Latin America and Brazil + Central South America
EIRP max
Polarization	Circular
Frequencies	Uplink: 13.750 - 14.000 GHz Downlink: 11.450 - 11.950 GHz

16 transponders will be dedicated to South America, mainly for Portuguese programming.


 Galaxy 9

General

Designation	23877 / 96033A
Launch date	24 May 1996
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	123°W
Launch vehicle	Delta 2 #236
Mass at launch	1397 kg

Should have moved to 127°W after Galaxy 10 launch.

43rd HS-376 launched

satellite worth $150 million

Technical data

Specifications

C-band

C-band transponder frequency chart

EIRP coverage (dBW)

C-band Horizontal

C-band Vertical

C-band Alaska extended


Galaxy 9's EIRP (C-band Horizontal)


Galaxy 9's EIRP (C-band Vertical)


Galaxy 9's EIRP (C-band Alaska)


 Galaxy 10

General

Designation	n/a
Launch date	27 Aug 1998
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	was to replace Galaxy 9 & SBS 5 at 123°W
Launch vehicle	Delta 3 #259
End of life

Out of service	27 Aug 1998
Cause	Launch failure
Technical data

Specifications

Prime contractor	Hughes
Platform	HS-601HP
Mass at launch	3876 kg
Mass in orbit
Dimension	5.9 m x 2.7 m x 3.6 m
Solar array	26 m
Stabilization	3-axis
DC power	BOL: 5800 W EOL: 5200 W
Design lifetime	12 years
C-band

Main transponders	24
Backup transponders	6
Power	20 W (SSPA)
Bandwidth	36 MHz
Coverage	conus, Hawaii, Alaska
EIRP max	40 dBW
Polarization	linear H/V
Ku-band

Main transponders	24
Backup transponders	6
Power	63 W (TWTA)
Bandwidth	36 MHz
Coverage	conus, Hawaii, Alaska
EIRP max	50 dBW
Polarization	linear H/V


 Galaxy 10R

General

Designation
Launch date	4th quarter of 1999
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	123°W
Launch vehicle
Technical data

EIRP coverage (dBW)

C-band

Ku-band

G/T coverage (dB/K)

C-band

Ku-band

Specifications

Prime contractor	Hughes
Platform	HS-601HP
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime	15 years

Beacons: 4.198125 V and 4.199625 H GHz

ULPC: 12.195 V and 11.701 H GHz

C-band

Main transponders	24
Backup transponders	4
Power	40 W
Bandwidth	36 MHz
Coverage	North America
EIRP max	41 dBW
G/T max	0 dB/K
Polarization	linear H/V
SFD	-93 dBW/m² (at 0 G/T & 0 dB attenuation)
Frequencies	Uplink: 5.925 - 6.425 GHz Downlink: 3.700 - 4.200 GHz

C-band transponder frequency chart

Ku-band

Main transponders	24
Backup transponders	4
Power	108 W
Bandwidth	36 MHz
Coverage	North America
EIRP max	47 dBW
G/T max	1 dB/K
Polarization	linear H/V
SFD	-93 dBW/m² (at 0 G/T & 0 dB attenuation)
Frequencies	Uplink: 14.000 - 14.500 GHz Downlink: 11.700 - 12.200 GHz
Ku-band transponder frequency chart (GHz)

Horizontal Uplink	Horizontal Downlink	Transponder	Vertical Downlink	Vertical Uplink
14.020		1	11.720
	11.740	2		14.040
14.060		3	11.760
	11.780	4		14.080
14.100		5	11.800
	11.820	6		14.120
14.140		7	11.840
	11.860	8		14.160
14.180		9	11.880
	11.900	10		14.200
14.220		11	11.920
	11.940	12		14.240
14.260		13	11.960
	11.980	14		14.280
14.300		15	12.000
	12.020	16		14.320
14.340		17	12.040
	12.060	18		14.360
14.380		19	12.080
	12.100	20		14.400
14.420		21	12.120
	12.140	22		14.440
14.460		23	12.160
	12.180	24		14.480


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Galaxy 10R's EIRP (C-band)


Galaxy 10R's EIRP (Ku-band)


Galaxy 10R's G/T (C-band)


Galaxy 10R's G/T (Ku-band)


 Galaxy 11

General

Designation
Launch date	initially planned in 1998 (4th quarter)
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Sea Launch
Launch site

PanAmsat modified Galaxy 11 to enable operations from several of the company's orbital slots covering the United States. To replace Galaxy 6 (99°W) in a first place and then Galaxy 7 (91°W)

Technical data

EIRP coverage (dBW)

C-band

Ku-band, North America

Ku-band, Extended (might not be accurate)

G/T coverage (dB/K)

C-band

Ku-band, North America

Ku-band, Extended (might not be accurate)

Specifications

Prime contractor	Hughes
Platform	HS-702
Mass at launch
Mass in orbit
Dimension
Solar array	11000 W (gallium arsenide solar cells)
Stabilization	3-axis
DC power
Design lifetime	15 years
Station keeping	Xenon Ion Propulsion System (XIPS)
C-band

Main transponders	24
Backup transponders	6
Power	20 W
Bandwidth	36 MHz
Coverage	North America and Hawaii
EIRP max	38 dBW (Hawaii: 32 dBW)
G/T max	+1 dB/K (Hawaii: -4 dB/K)
Polarization	linear H/V
SFD	at 0 G/T & 0 dB attenuation: -91.5 dBW/m² H and -91 dBW/m² V
Frequencies	Uplink: 5.925-6.425 GHz Downlink: 3.700-4.200 GHz

C-band transponder frequency chart

Ku-band (11.7-12.2 GHz)

Main transponders	24
Backup transponders	6
Power	75 W
Bandwidth	36 MHz
Coverage	CONUS
EIRP max	47 dBW
G/T max	3 dB/K
Polarization	linear H/V
SFD	at 0 G/T & 0 dB attenuation: -93.5 dBW/m² H & V
Frequencies	Uplink: 14.0-14.5 GHz Downlink: 11.7-12.2 GHz

TM beacons: 11.701 & 11.702 GHz in both polarities

ULPC beacons: 12.195 GHz H (North America) and 10.951 GHZ H & V (Conus and Brazil)

Transponder frequency chart (GHz)

Horizontal  Downlink	Horizontal  Uplink	Transponder	Vertical  Uplink	Vertical  Downlink
11.720		1	14.020
	14.040	2		11.740
11.760		3	14.060
	14.080	4		11.780
11.800		5	14.100
	14.120	6		11.820
11.840		7	14.140
	14.160	8		11.860
14.880		9	14.180
	14.200	10		11.900
11.920		11	14.220
	14.240	12		11.940
11.960		13	14.260
	14.280	14		11.980
12.000		15	14.300
	14.320	16		12.020
12.040		17	14.340
	14.360	18		12.060
12.080		19	14.380
	14.400	20		12.100
12.120		21	14.420
	14.440	22		12.140
12.160		23	14.460
	14.480	24		12.180
Ku-band (10.95-11.2 GHz) (called extended)

Main transponders	16
Backup transponders	4
Power	140 W
Bandwidth	27 MHz
Coverage	CONUS & Brasil
EIRP max	47 dBW North America 48 dBW Brasil
G/T max	2 dB/K North America 2 dB/K Brazil
Polarization	linear H/V
Frequencies	Uplink: 13.75-14.0 GHz (North Am), 14.00-14.25 GHz (Brazil) Downlink: 10.95-11.2 GHz

Beacons: 12.195 GHz H to North America and 10.951 GHz in both polarizations to Brasil

NOTE: recent Panamsat documentation does not cover the Extended payload. Details included here are from older documentation. It might no longer be accurate.

Downlink Transponder frequency chart (GHz)

Horizontal	Transponder	Vertical
10.964	1
	2	10.976
10.994	3
	4	11.006
11.024	5
	6	11.036
11.054	7
	8	11.066
11.084	9
	10	11.096
11.114	11
	12	11.126
11.144	13
	14	11.156
11.174	15
	16	11.186
Uplink Transponder frequency chart (GHz)

Horizontal  North Am	Horizontal  Brasil	Transponder	Vertical  North Am	Vertical  Brasil
13.764	14.014	1
		2	13.776	14.026
13.794	14.044	3
		4	13.806	14.056
13.824	14.074	5
		6	13.836	14.086
13.854	14.104	7
		8	13.866	14.116
13884	14.134	9
		10	13.896	14.146
13.914	14.164	11
		12	13.926	14.176
13.944	14.194	13
		14	13.956	14.206
13.974	14.224	15
		16	13.986	14.236

For each transponder, uplink is possible from only 1 of the North America or Brasil frequency.


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Galaxy 11's C-band EIRP coverage


Galaxy 11's Ku-band North America EIRP coverage


Galaxy 11's Ku-band Extended EIRP coverage


Galaxy 11's C-band G/T coverage

For Horizontal the signal is 1 to 2 dB/K is weaker.


Galaxy 11's Ku-band North America G/T coverage


Galaxy 11's Ku-band Extended G/T coverage


 Galex

Galaxy Evolution Explorer

General

Designation
Launch date	Sep 2001
Country of origin	United States
Mission	Scientific: part of SMEX
Perigee/Apogee	690 km
Inclination	28.5°
Period
Launch vehicle	Pegasus
Launch site	Cape Canaveral

Cost: $16.5 million

Galex is a Space Ultraviolet Small Explorer mission that will map the global history and probe the causes of star formation over the redshift range 0<z<2, 80% of the life of the Universe, the period over which galaxies have evolved dramatically, and the time that most stars, elements, and galaxy disks had their origins.

External resources

http://www.srl.caltech.edu/galex/

Technical data

Specifications

Prime contractor	OSC
Platform
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization	3-axis
DC power
Design lifetime	28 months

GALEX uses the space ultraviolet to simultaneously measure redshift (using metal lines and the Lyman break), extinction (using the UV spectral slope), and star formation rate (using the UV luminosity which is proportional to the instantaneous star formation rate). Slitless grism spectroscopy is highly efficient, providing 100,000 galaxy spectra in one year. The 50 cm telescope, operating from 1300-3000 Å, is simple, cost-effective, efficient, and exploits MCP detectors and optical coatings which are flight-proven and cutting-edge to attain the deep, broad-band imaging and spectroscopy required.

X- and S-band transponders


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 Program: Galileo

Also called GNSS-2 or Galileosat

European navigation program to be operational in 2008. Composed of satellites in MEO

The system should cost between 2.2 and 2.9 billion euro.

Before this system is operational, the EGNOS payload (European Geostationary Navigation Overlay Service) will be included in Artemis and 2 Inmarsats. It will send signals that will be used to enhance GPS measurements.


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 Program: Gals

Soviet direct TV-built satellites financed by The Land Group, a Chinese non-state sector company.

On the 2 first satellites, 2 transponders are said to have failed

Intersputnik has plans to operate Gals R12 satellites from 1997 on. (5 to 7 years lifetime, 12 Ku-band transponders (27 MHz), 2400 W.

Gals R16 satellites could also be launched in 1999. 16 transponders each for DBS services, those transponders would be manufactured by a Western supplier.

External resources

http://www.lnd.cn.net/TEXT/TEA4B1.HTM


Program: Gals

Gals 1

Gals 2


Gals' specifications

Prime contractor	Informcosmos
Platform	NPO Gals
Mass at launch	2500 kg
Mass in orbit
Diameter	2.5 m
Solar array	twin panels
Stabilization	3-axis
DC power	2400 W
Design lifetime	5 to 7 years

Xenon thrusters: SPT 100 , 8 units per satellite (including redundances) produced by Fakel CIS.


Gals' ku-band

Main transponders	3
Backup transponders
Power	150-300 W (TWTA)
Bandwidth	27 MHz
Coverage	2 spot beams (steerable): A: 2.5° x 1.25° (2 transponders) B: 1.2° x 0.9° (1 transponder)
EIRP max	57 dBW
Polarization	circular
Frequencies	uplink: 17404.2 - 17883.7 MHz downlink: 11804.2 - 12283.7 MHz

Receive antenna: spot: 2° x 2°


 Gals 1

General

Designation	22963 / 94002A
Launch date	20 Jan 1994
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Proton #219
Location

Begin	End	Position
L: 20 Jan 1994	mid-May 1996	71°E
June 1996		36°E

No service on this satellite in May 1999

Technical data

Specifications

Ku-band

EIRP coverage (dBW)

Transponder frequency chart (GHz)

Transponder	Polarization	Frequency
3	LHCP	11.766
2	LHCP	11.919


 Gals 2

General

Designation	23717 / 95063A
Launch date	17 Nov 1995 at 14:30 UT
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Proton #237

Land has leased the satellite for $9 million a year to Global DBS Company, whose shareholders include the Loral Corp, General Instruments Co and TCI Cable TV Co, all of the United States, and British General Telecommunications Ltd/Asian TV network.

Location

Begin	End	Position
L: 17 Nov 1995	mid-Jun 1996	71°E
Jul 1996		36°E
Technical data

Specifications

Ku-band

EIRP coverage (dBW)

Transponder frequency chart (GHz)

Transponder	Polarization	Frequency
3	LHCP	11.835
1	LHCP	12.166


Gals' EIRP coverage


 Program: GE

Telecommunication program operated by GE Americom.

Another project of GE Americom: a set of satellite for global services; operated from Gibraltar. Planned orbital locations include 3°E, 6.5°W, 10°W, 15°W and 23°W for Europe; 37.5°E, 47°E and 51°E for Africa; and 97°E, 100.7°E, 105.3°E and 108.2°E for Asia and the Pacific. The proposed satellites would be used mainly for video programming distribution, including direct-to-home, cable headend and other broadcast applications. The planned spacecraft design would accommodate both analog and digital video formats, as well as other uses including VSAT and data networks.


Program: GE

GE 1

GE 1A

GE 1E

GE 2

GE 2A

GE 2E

GE 3

GE 4

GE 5

GE 6

GE 7

GE 8

GE 9


GE's specifications

Prime contractor	Lockheed Martin Astro Space
Platform	A2100
Mass at launch	2750 kg
Mass in orbit	1600 kg
Dimension	1.83 x 1.85 x 2.64 m (22.2 m deployed)
Solar array
Stabilization	3-axis
DC power	BOL: 6000 W
Design lifetime	15 years

Beacon frequencies were intentionally not provided by GE Americom


GE's C-band

Main transponders	24
Backup transponders	8
Power	12 to 18 W (SSPA)
Bandwidth	36 MHz
Coverage
EIRP max	37 dBW
Polarization


GE's Ku-band

Main transponders	24
Backup transponders	12
Power	60 W (TWTA)
Bandwidth	36 MHz
Coverage
EIRP max	49 dBW
Polarization


GE's transponder frequency chart (GHz)

Horizontal Uplink	Horizontal Downlink	Transponder	Vertical Downlink	Vertical Uplink
	11.720	1		14.020
14.040		2	11.740
	11.600	3		14.060
14.080		4	11.780
	11.800	5		14.100
14.120		6	11.820
	11.840	7		14.140
14.160		8	11.860
	11.880	9		14.180
14.200		10	11.900
	11.920	11		14.220
14.240		12	11.940
	11.960	13		14.260
14.280		14	11.980
	12.000	15		14.300
14.320		16	12.020
	12.040	17		14.340
14.360		18	12.060
	12.080	19		14.380
14.400		20	12.100
	12.120	21		14.420
14.440		22	12.140
	12.160	23		14.460
14.480		24	12.180


 GE 1

General

Designation	24315 / 96054A
Launch date	8 Sep 1996
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	103°W
Launch vehicle	Atlas 2A (AC-123)

Gstar 1 replacement

Technical data

EIRP coverage (dBW)

C-band

Ku-band

Specifications

C-band

Ku-band

C-band transponder frequency chart

Ku-band transponder frequency chart


GE 1's C-band EIRP


GE 1's Ku-band EIRP


 GE 1A

General

Designation
Launch date	initially planned for 1999
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	97°E or 108°E
Launch vehicle	Proton

This is the first satellite of the LMGT and GE Americom.

Technical data

Specifications

Prime contractor	Lockheed Martin
Platform	A2100
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime
Ku-band

Main transponders	28
Backup transponders
Power
Bandwidth
Coverage	China beam (8 to 16 transp.) NE Asia & Philippines beam (8 to 16 transp.) India (8 to 8 transp.)
EIRP max
G/T max
Polarization


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 GE 2

General

Designation	24713 / 97002A
Launch date	30 Jan 1997
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	85°W
Launch vehicle	Ariane V93

Satcom K1 replacement. All the Ku-band transponders have been secured for 4 years (with an option up to 15 years) by Primestar

Technical data

EIRP coverage (dBW)

C-band

Ku-band

Specifications

C-band

Ku-band

C-band transponder frequency chart

Ku-band transponder frequency chart


GE 2's C-band EIRP


GE 2's Ku-band EIRP


 GE 2A

General

Designation
Launch date	initially planned for 2000
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	108.2°E
Launch vehicle
Technical data

Specifications

Prime contractor	Aerospatiale?
Platform
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime
Ku-band

Main transponders	36
Backup transponders
Power
Bandwidth
Coverage	Australia beam (8 to 16 transp.) South East Asia beam (8 to 16 transp.) India (4 to 8 transp.) Steerable (8 transp.)
EIRP max
G/T max
Polarization


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 GE 2E

General

Designation
Launch date	late 2000 could be delayed until 2002
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	to cover europe
Launch vehicle


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 GE 3

General

Designation	24936 / 97050A
Launch date	4 Sep 1997
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	87°W
Launch vehicle	Atlas Centaur #109

Spacenet 3R replacement. Tested at 83°W. Went operational on 1 Oct 1997

Worth $100 million  FCC has authorized GE Americom to change the satellite's location . New location would be 72°W.

On 12 Mar 1999 at 9:02 UT the satellite lost attitude control because of a gyroscope failure. The service was restored at 14:49 UT.

Technical data

EIRP coverage (dBW)

C-band

Ku-band

Specifications

C-band

Ku-band

C-band transponder frequency chart

Ku-band transponder frequency chart

Royal Ordnance Leros apogee engine


 GE 4

General

Designation
Launch date	3rd quarter 1999
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	101°W
Launch vehicle

should replace ASC 2

Technical data

EIRP coverage (dBW)

C-band

Ku-band

Specifications

C-band

Main transponders	24
Backup transponders	8
Power	20 W
Bandwidth	36 MHz
Coverage	Conus, Canada, Mexico, Caribbean
EIRP max	40 dBW
G/T max
Polarization	linear H/V
Beacons	3.7005 GHz H & 4.1995 GHZ V

C-band transponder frequency chart

Ku-band

Main transponders	28
Backup transponders	8
Power	110 W (TWTA)
Bandwidth	24 x 36 MHz 4 x 72 MHz
Coverage	US, Hawaii, Canada, Mexico Central-South America
EIRP max	51 dBW
G/T max
Polarization	linear H/V
Beacons	11.702 GHZ V & 12.198 GHz H

Ku-band transponders are individually switchable between North American and South American coverage

Ku-band Transponder frequency chart (GHz)

Horizontal Uplink	Horizontal Downlink	Transponder	Vertical Downlink	Vertical Uplink	Notes
13.875		25	11.575		54 MHz
	11.575	26		13.875	54 MHz
13.955		27	11.655		54 MHz
	11.655	28		13.955	54 MHz
14.020		1	11.720
	11.740	2		14.040
14.060		3	11.760
	11.780	4		14.080
14.100		5	11.800
	11.820	6		14.120
14.140		7	11.840
	11.860	8		14.160
14.180		9	11.880
	11.900	10		14.200
14.220		11	11.920
	11.940	12		14.240
14.260		13	11.960
	11.980	14		14.280
14.300		15	12.000
	12020	16		14.320
14.340		17	12.040
	12060	18		14.360
14.380		19	12.080
	12100	20		14.400
14.420		21	12.120
	12.140	22		14.440
14.460		23	12.160
	12.160	24		14.480


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GE 4's C-band EIRP


GE 4's Ku-band EIRP


 GE 5

General

Designation	25516 / 98063B
Launch date	28 Oct 1998
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	79°W
Launch vehicle	Ariane V113

First time a US operator buys the satellite & launch services from European-only companies. This is because the satellite was originaly Nahuel 1B, but was sold to GE Americom. The footprint coverage was modified to cover the CONUS.

Technical data

EIRP coverage (dBW)

Ku-band

Specifications

Prime contractor	Alcatel Space
Platform	Spacebus-2000
Mass at launch	1698 kg
Mass in orbit	1013 kg
Dry mass	769 kg
Dimension	1.5 x 1.6 x 2.2 m
Solar array
Stabilization	3-axis
DC power	EOL: 3150 W
Design lifetime	12 years
Ku-band

Main transponders	16
Backup transponders	6
Power	55 W
Bandwidth	54 MHz
Coverage	CONUS
EIRP max	47 dBW
G/T max
Polarization
Frequencies	11.7-12.5 GHz
Ku-band Transponder frequency chart (GHz)

Horizontal Uplink	Horizontal Downlink	Transponder	Vertical Downlink	Vertical Uplink
14.030		01K	11.730
	11.743	02K		14.043
14.091		03K	11.791
	11.804	04K		14.104
14.152		05K	11.852
	11.865	06K		14.165
14.213		07K	11.913
	11.926	08K		14.226
14.274		09K	11.974
	11.987	10K		14.287
14.335		11K	12.035
	12.048	12K		14.348
14.396		13K	12.096
	12.109	14K		14.409
14.457		15K	12.157
	12.170	16K		14.470


GE 5's Ku-band EIRP


 GE 6

General

Designation
Launch date	fall 2000
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	105°W
Launch vehicle
Technical data

Specifications

Prime contractor	Lockheed Martin
Platform	A2100
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime
C-band

Main transponders
Backup transponders
Power
Bandwidth
Coverage	conus
EIRP max
G/T max
Polarization
Ku-band

Main transponders
Backup transponders
Power
Bandwidth
Coverage	conus
EIRP max
G/T max
Polarization


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 GE 7

General

Designation
Launch date	2000
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	137°W
Launch vehicle
Technical data

EIRP coverage (dBW)

C-band

Specifications

Prime contractor	Lockheed Martin
Platform	A2100
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime
C-band

Main transponders	24
Backup transponders	8
Power	20 W
Bandwidth	36 MHz
Coverage	Conus, Alaska, Hawaii, Caribbean
EIRP max
G/T max
Polarization	linear H/V
Beacons	3.7005 GHz H & 4.1995 GHZ V

C-band transponder frequency chart


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 GE 8

Aurora 3

General

Designation
Launch date	2001
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	139°W
Launch vehicle

Satellite the be jointly owned by Alascom. Capacity will be used for communication with Alaska.

Technical data

EIRP coverage (dBW)

C-band

Specifications

Prime contractor	Lockheed Martin
Platform	A2100
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime
C-band

Main transponders	24
Backup transponders	8
Power	20 W
Bandwidth	36 MHz
Coverage	Conus, Alaska, Hawaii, Caribbean
EIRP max
G/T max
Polarization	linear H/V
Beacons	3.7005 GHz H & 4.1995 GHZ V

C-band transponder frequency chart


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GE 7 & 8 C-band EIRP coverage


 GE 9

General

Designation
Launch date	2001
Country of origin	United States
Mission	Telecommunications
Geostationary orbit
Launch vehicle
Technical data

Specifications

Prime contractor	Lockheed Martin
Platform	A2100
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime
C-band

Main transponders
Backup transponders
Power
Bandwidth
Coverage	conus
EIRP max
G/T max
Polarization


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 Program: GE*Star

Telecommunication program operated by GE Americom. It is made of colocated Ka-band satellites. It was approved by the FCC in May 1997

The GE*Star system will allow symmetric and asymmetric data communications transmission rates ranging from 384 Kbps to 40 Mbps.

Slots: 105°W, 85°W, 17°W, 56°E and 114.5°E, 2 satellites per slot except at 56°E (only 1 satellite)

The spacecraft will feature on-board processors that can accommodate large streams of data traffic and switch them between spot beams to provide full connectivity and worldwide coverage.

Technical data

Ka-band

Main transponders
Backup transponders
Power
Bandwidth
Coverage	44 spot beams
EIRP max	54 dBW
Polarization	linear H/V
Frequencies	Uplink: 28.35-28.6 and 29.25-30.0 GHz Downlink: 19.7-20.2 GHz

11 times frequency reuse through the use of spatially diverse satellite beams


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 Program: Geizer

Russian military telecommunication program. The satellites composing this program are part of the Cosmos fleet. Those geostationary satellites are located on the 'Potok' slots. Potok was a telecommunication project designed in the early 80ies; was to operate in C-band. Three slots were registered with the ITU as Potok: 13.5°W, 80°E and 168°E.

Some satellites could have been leased as standard telecommunication satellites to transmit phone traffic.


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Program: Geizer

Cosmos 1366

Cosmos 1540

Cosmos 1738

Cosmos 1888

Cosmos 1961

Cosmos 2085

Cosmos 2172

Cosmos 2291

Cosmos 2319


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Geizer's specifications

Prime contractor	NPO-PM
Platform	Geizer
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime	probably 3 to 5 years


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 Gemstar

Global Messaging Satellite, also called Vitasat

General

Launch date	15 Aug 1995
Country of origin	United States
Mission	Telecommunications
Launch vehicle	Athena #1
Mass at launch	150 kg
End of life

Out of service	15 Aug 1995
Cause	Launch failure

Cost: between $2 million and $3 million, built by CTA Inc of Rockville, Md (base on the Gemstar bus).

Was designed to provide electronic mail services and global location services for trucking fleet operators. Was also to be used by VITA


 Geolite

Geosynchronous Lightweight Technology Experiment

General

Designation
Launch date	2001
Country of origin	United States
Mission
Operator	NRO
Geostationary orbit	? not sure it will be geostationary
Launch vehicle	Delta 2
Launch site

Advanced technology demonstration satellite with a laser communications experiment and an operational UHF communications mission.

Contract worth $77.8 million (including launch)

Technical data

Specifications

Prime contractor	TRW
Platform	STEP
Mass at launch	2000 kg
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime


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 Geos 3

General

Designation	07734 / 75027A
Launch date	9 Apr 1975
Country of origin	United States
Mission	Scientific: geodesy
Perigee/Apogee	820/845 km
Inclination	115°
Period	101.6 min
Launch vehicle	Thor Delta #109
Mass at launch	241 kg

Mission: Ocean and islands map-making.


 GFO 1

Also called Geosat Follow-on

General

Designation	25157 / 98007A
Launch date	10 Feb 1998
Country of origin	United States
Operator	Ball Corporation
Mission	Military: remote sensing
Perigee/Apogee	800 km
Inclination	108°
Period	101 min
Launch vehicle	Taurus #2
Launch site	Vandenberg

Using an advanced radar altimeter (13.5 GHz), the GFO satellite is designed to provide precise information on changes in sea surface heights, eddies and warm/cold water fronts.  The data will be used to support Navy tactical operations. The GFO contract was awarded to Ball Aerospace Systems Group in August 1992 by the U.S. Navy's Space and Naval Warfare systems command. The Navy contract calls for a "turnkey" satellite system, and contract options for two additional spacecraft. GFO will follow the successful Geosat satellite that completed service in January 1990.

Will downlink directly to vessels.

For the GFO mission, Taurus will use Thiokol's Castor 120 solid rocket motor as the vehicle's first stage, and incorporate a larger, Orbital-developed payload fairing, providing a 120% increase in payload volume. Modifications to the Taurus booster, particularly a new payload fairing twice the size of the one used on the first flight, will result in a much more capable rocket. This configuration was proposed for NASA's MedLite program, and another that results in an extra 500 pounds of secondary payload capability for the GFO mission.

The initial contract worth $115 million calls for 3 GFO satellites, the last one should be launched in 2007

External resources

http://gfo.bmpcoe.org/Gfo/

http://osb3.wff.nasa.gov/gfo/

http://www.fas.org/spp/military/program/met/gfo.htm

Technical data

Specifications

Prime contractor	Ball Aerospace & Technologies Corp.
Platform	Techstar
Mass at launch	365 kg
Mass in orbit
Dimension
Solar array
Stabilization
DC power	126 W
Design lifetime	8 years

96 MB on-board storage

carriers at 400.033 & 150.0125 MHz


 GFO 2

Also called Geosat Follow-on 2

General

Designation
Launch date	2001
Country of origin	United States
Mission
Perigee/Apogee
Inclination
Period
Launch vehicle
Launch site

To be built by the NRL, Washington.

Will provide wave height, and wind speed. Will downlink directly to vessels.


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 Geotail

General

Designation	22049 / 92044A
Launch date	24 Jul 1992 at 14:26 UT
Country of origin	United States and Japan
Mission	Scientific: lunar gravity study
Perigee/Apogee	41363/58542 km
Inclination	22.4°
Period	4750.6 min
Launch vehicle	Delta 2 #212

Launched under the MELVS contract

External resources

http://www.gtl.isas.ac.jp/

http://spacelink.nasa.gov/NASA.Projects/Space.Science/Sun-Earth.Connection/GEOTAIL/

http://hurlbut.jhuapl.edu/Geotail/


 GFZ 1

General

Designation	23558 / 86017JE
Launch date	19 Apr 1995 at 19:12 UT
Country of origin	Germany
Operator	GeoForschungsZentrum Postdam, Germany
Mission	Scientific: geodesy
Perigee/Apogee	383/394 km
Inclination	51.6°
Period	92.3 min
Launch vehicle	n/a
Launch site	Mir

A fake replica was launched on 17 Apr 1995 (catnr: 23557).

25 observatories all over the world will execute measurements by laserreflections. Stations are among others: London, Grasse (France), Postdam, Easterisland, Graz (Austria) and even one in Kirgizie. The stations can 'catch' GFZ 1 with a beamwidth of 200 meters.

End of life

Out of service	23 Jun 1999
Cause	reentered
Decay	23 Jun 1999
External resources

http://op.gfz-potsdam.de/gfz1/gfz1_frame.html

Technical data

Specifications

Prime contractor	Kayser-Threde
Platform
Mass at launch	20 kg
Diameter	21 cm
Width
Height
Stabilization
DC power
Design lifetime

Sphere covered with laser retroreflectors


 Program: GGSE

Gravity Gradient Stabilization Experiment

American scientific program


Program: GGSE

GGSE 1

GGSE 2

GGSE 3

GGSE 4

GGSE 5


 GGSE 1

General

Designation	00728 / 64001B
Launch date	11 Jan 1964
Country of origin	United States
Mission	Scientific
Perigee/Apogee	899/916 km
Inclination	69.9°
Period	103.2 min
Launch vehicle	Thor Agena
Launch site	Vandenberg


 GGSE 2

General

Designation	01244 / 65016B
Launch date	9 Mar 1965
Country of origin	United States
Mission	Scientific: geodesy
Perigee/Apogee	896/928 km
Inclination	70.1°
Period	103.2 min
Launch vehicle	Thor Agena
Launch site	Vandenberg


 GGSE 3

General

Designation	01292 / 65016C
Launch date	9 Mar 1965
Country of origin	United States
Mission	Scientific: geodesy
Perigee/Apogee	896/915 km
Inclination	70.1°
Period	103.0 min
Launch vehicle	Thor Agena D
Launch site	Vandenberg


 GGSE 4

General

Designation	02828 / 67053C
Launch date	31 May 1967
Country of origin	United States
Mission	Scientific: geodesy
Perigee/Apogee	903/910 km
Inclination	70.0°
Period	103.1 min
Launch vehicle	Thor Agena D
Launch site	Vandenberg


 GGSE 5

General

Designation	02834 / 67053D
Launch date	31 May 1967
Country of origin	United States
Mission	Scientific: geodesy
Perigee/Apogee	906/913 km
Inclination	70.0°
Period	103.2 min
Launch vehicle	Thor Agena D
Launch site	Vandenberg


 Program: Globalstar

Globalstar is a low-earth orbit (LEO) satellite-based telecommunications system founded by Loral Corp. and Qualcomm Inc. that will offer low-cost, high-quality global telephony and other digital telecommunications services to areas currently underserved or not served by existing wireline and cellular telecommunications systems. Operated by Loral Qualcomm Satellite Services Inc.

The satellites will be launched into eight orbital planes, with six satellites in each plane to provide continuous global coverage. Commercial service is anticipated 1999.

Space Systems/Loral has a fixed-price contract for the construction of Globalstar's satellites, which it will perform in conjunction with various other members of the international Space Systems/Alliance, which includes Aerospatiale and Alcatel of France, Daimler-Benz Aerospace of Germany, Alenia and Finmeccanica of Italy, and with Hyundai of South Korea.

Total system cost: $4 billion

Globalstar proposed next generation would be composed of 64 LEO satellites and 4 GEO satellites.

Technical data

Slots and planes

slot	satellites #
plane 1 (44)	1, 2, 3, 4
plane 2 (90)	6, 8, 14, 15
Launches

9 Delta-2 flights (4 satellites per flight), 7 left

3 Zenit flights (12 satellites per flight), 0 left (others cancelled?)

3 Soyuz-Icare flights (4 satellites per flight), 3 left

1 Ariane-4 flight (6 satellites per flight), 1 left

Constellation overview

Orbit type	LEO
Orbit range	1414 km, circular
Nb of satellites	48 + 8 backup
Nb of planes	8
Inclination	52°
Nb beams per satellite	16
Coverage	5796 km²
Modulation	CDMA
Mobile frequencies	Uplink: 2483.5 - 2500 MHz Downlink: 1610-1626.5 MHz
Fixed frequencies	Uplink: 5091 - 5250 GHz Downlink: 6875 - 7055 GHz
Satellite mass	425 kg
Coverage	all longitudes, 74N - 74S latitudes
Operational date	1999 (planned)


Program: Globalstar

Globalstar 1 Globalstar 2 Globalstar 3 Globalstar 4 Globalstar 5, 7, 9, 10, 11, 12, 13, 16, 17, 18, 20, 21 Globalstar 6 Globalstar 8 Globalstar 14 Globalstar 15 Globalstar 19 Globalstar 22 Globalstar 23 Globalstar 24 Globalstar 25 Globalstar 26	Globalstar 27 Globalstar 28 Globalstar 30 Globalstar 32 Globalstar 35 Globalstar 36 Globalstar 37 Globalstar 38 Globalstar 40 Globalstar 41 Globalstar 42 Globalstar 43 Globalstar 44	Globalstar 45 Globalstar 46 Globalstar 47 Globalstar 48 Globalstar 49 Globalstar 51 Globalstar 52 Globalstar 53 Globalstar 54


Globalstar's specifications

Prime contractor	Space Systems/Loral
Platform	LS-400
Mass at launch	450 kg
Mass in orbit
Dry mass	400 kg
Dimension	trapezoidal shape
Solar array	10.75 m span (2 panels)
Stabilization	3-axis (orbit determination with GPS)
DC power	1100 W
Design lifetime	7.5 years

Satellites are built by Alenia Spazio in Rome. The structure and thermic control is built by Aerospatiale, the payload by Alcatel and the propulsion and solar arrays by Dasa.


Globalstar's payload

Capacity	2800 phone circuits
Voice	9600 bps
Fax	yes
Data	9600 bps
Mobile uplink	2483.5 - 2500 MHz via 91-element phased-array antenna
Mobile downlink	1610 - 1626.5 MHz via 61-element phased-array antenna
Gateway uplink	5091 - 5250 MHz
Gateway downlink	6875 - 7055 MHz

Compatible with GSM, CDMA and AMPS.


 Globalstar 1

General

Designation	25162 / 98008A
Launch date	14 Feb 1998
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	1400 km
Inclination	52°
Period
Launch vehicle	Delta 2 #253
Technical data

Specifications

Payload


 Globalstar 2

General

Designation	25163 / 98008B
Launch date	14 Feb 1998
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	1400 km
Inclination	52°
Period
Launch vehicle	Delta 2 #253
Technical data

Specifications

Payload


 Globalstar 3

General

Designation	25164 / 98008C
Launch date	14 Feb 1998
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	1400 km
Inclination	52°
Period
Launch vehicle	Delta 2 #253
Technical data

Specifications

Payload


 Globalstar 4

General

Designation	25165 / 98008D
Launch date	14 Feb 1998
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	1400 km
Inclination	52°
Period
Launch vehicle	Delta 2 #253
Technical data

Specifications

Payload


 Globalstar 6

General

Designation	25306 / 98023A
Launch date	24 Apr 1998
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	1400 km
Inclination	52°
Period
Launch vehicle	Delta 2 #256
Technical data

Specifications

Payload


 Globalstar 8

General

Designation	25307 / 98023B
Launch date	24 Apr 1998
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	1400 km
Inclination	52°
Period
Launch vehicle	Delta 2 #258
Technical data

Specifications

Payload


 Globalstar 14

General

Designation	25308 / 98023C
Launch date	24 Apr 1998
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	1400 km
Inclination	52°
Period
Launch vehicle	Delta 2 #256
Technical data

Specifications

Payload


 Globalstar 15

General

Designation	25309 / 98023D
Launch date	24 Apr 1998
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	1400 km
Inclination	52°
Period
Launch vehicle	Delta 2 #256
Technical data

Specifications

Payload


Globalstar 5, 7, 9, 10, 11, 12, 13, 16, 17, 18, 20, 21
 Globalstar 5, 7, 9, 10, 11, 12, 13, 16, 17, 18, 20 & 21

General

Designation	n/a
Launch date	9 Sep 1998
Country of origin	United States
Mission	Telecommunications
Launch vehicle	Zenit 2 #30
End of life

Out of service	9 Sep 1998
Cause	launcher failure


 Globalstar 19

General

Designation	25679 / 99019D
Launch date	15 Apr 1999
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	1400 km
Inclination	52°
Period	110 min
Launch vehicle	Soyuz
Technical data

Specifications

Payload


 Globalstar 22

General

Designation	25649 / 99012A
Launch date	15 Mar 1999
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	1400 km
Inclination	52°
Period
Launch vehicle	Soyuz
Technical data

Specifications

Payload


 Globalstar 23

General

Designation	25622 / 99004B
Launch date	9 Feb 1999
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	1400 km
Inclination	52°
Period
Launch vehicle	Soyuz
Technical data

Specifications

Payload


 Globalstar 24

General

Designation	25883 / 99043A
Launch date	17 Aug 1999
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	1400 km
Inclination	52°
Period	110 min
Launch vehicle	Delta 2 #274
Technical data

Specifications

Payload


 Globalstar 25

General

Designation	25772 / 99031C
Launch date	10 Jun 1999
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	1400 km
Inclination	52°
Period	110 min
Launch vehicle	Delta 2 #270
Technical data

Specifications

Payload


 Globalstar 26

General

Designation	25872 / 99041A
Launch date	23 Jul 1999
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	1400 km
Inclination	52°
Period	110 min
Launch vehicle	Delta 2 #273
Technical data

Specifications

Payload


 Globalstar 27

General

Designation	25884 / 99043B
Launch date	17 Aug 1999
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	1400 km
Inclination	52°
Period	110 min
Launch vehicle	Delta 2 #274
Technical data

Specifications

Payload


 Globalstar 28

General

Designation	25873 / 99041B
Launch date	23 Jul 1999
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	1400 km
Inclination	52°
Period	110 min
Launch vehicle	Delta 2 #273
Technical data

Specifications

Payload


 Globalstar 30

General

Designation	25852 / 99037B
Launch date	10 Jul 1999
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	1400 km
Inclination	52°
Period	110 min
Launch vehicle	Delta 2 #272
Technical data

Specifications

Payload


 Globalstar 32

General

Designation	25851 / 99037A
Launch date	10 Jul 1999
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	1400 km
Inclination	52°
Period	110 min
Launch vehicle	Delta 2 #272
Technical data

Specifications

Payload


 Globalstar 35

General

Designation	25853 / 99037C
Launch date	10 Jul 1999
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	1400 km
Inclination	52°
Period	110 min
Launch vehicle	Delta 2 #272
Technical data

Specifications

Payload


 Globalstar 36

General

Designation	25621 / 99004A
Launch date	9 Feb 1999
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	1400 km
Inclination	52°
Period
Launch vehicle	Soyuz
Technical data

Specifications

Payload


 Globalstar 37

General

Designation	25652 / 99012D
Launch date	15 Mar 1999
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	1400 km
Inclination	52°
Period
Launch vehicle	Soyuz
Technical data

Specifications

Payload


 Globalstar 38

General

Designation	25623 / 99004C
Launch date	9 Feb 1999
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	1400 km
Inclination	52°
Period
Launch vehicle	Soyuz
Technical data

Specifications

Payload


 Globalstar 40

General

Designation	25624 / 99004D
Launch date	9 Feb 1999
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	1400 km
Inclination	52°
Period
Launch vehicle	Soyuz
Technical data

Specifications

Payload


 Globalstar 41

General

Designation	25650 / 99012B
Launch date	15 Mar 1999
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	1400 km
Inclination	52°
Period
Launch vehicle	Soyuz
Technical data

Specifications

Payload


 Globalstar 42

General

Designation	25677 / 99019B
Launch date	15 Apr 1999
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	1400 km
Inclination	52°
Period
Launch vehicle	Soyuz
Technical data

Specifications

Payload


 Globalstar 43

General

Designation	25874 / 99041C
Launch date	23 Jul 1999
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	1400 km
Inclination	52°
Period	110 min
Launch vehicle	Delta 2 #273
Technical data

Specifications

Payload


 Globalstar 44

General

Designation	25678 / 99019C
Launch date	15 Apr 1999
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	1400 km
Inclination	52°
Period
Launch vehicle	Soyuz
Technical data

Specifications

Payload


 Globalstar 45

General

Designation	25676 / 99019A
Launch date	15 Apr 1999
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	1400 km
Inclination	52°
Period
Launch vehicle	Soyuz
Technical data

Specifications

Payload


 Globalstar 47

General

Designation	25773 / 99031D
Launch date	10 Jun 1999
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	1400 km
Inclination	52°
Period	110 min
Launch vehicle	Delta 2 #270
Technical data

Specifications

Payload


 Globalstar 46

General

Designation	25651 / 99012C
Launch date	15 Mar 1999
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	1400 km
Inclination	52°
Period
Launch vehicle	Soyuz
Technical data

Specifications

Payload


 Globalstar 48

General

Designation	25875 / 99041D
Launch date	23 Jul 1999
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	1400 km
Inclination	52°
Period	110 min
Launch vehicle	Delta 2 #273
Technical data

Specifications

Payload


 Globalstar 49

General

Designation	25771 / 99031B
Launch date	10 Jun 1999
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	1400 km
Inclination	52°
Period	110 min
Launch vehicle	Delta 2 #270
Technical data

Specifications

Payload


 Globalstar 51

General

Designation	25854 / 99037D
Launch date	10 Jul 1999
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	1400 km
Inclination	52°
Period	110 min
Launch vehicle	Delta 2 #272
Technical data

Specifications

Payload


 Globalstar 52

General

Designation	25770 / 99031A
Launch date	10 Jun 1999
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	1400 km
Inclination	52°
Period	110 min
Launch vehicle	Delta 2 #270
Technical data

Specifications

Payload


 Globalstar 53

General

Designation	25885 / 99043C
Launch date	17 Aug 1999
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	1400 km
Inclination	52°
Period	110 min
Launch vehicle	Delta 2 #274
Technical data

Specifications

Payload


 Globalstar 54

General

Designation	25886 / 99043D
Launch date	17 Aug 1999
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	1400 km
Inclination	52°
Period	110 min
Launch vehicle	Delta 2 #274
Technical data

Specifications

Payload


 Program: Glonass

Global'naya Navigatsionnaya Sputnikovaya Sistema

Russian navigation program part of the Cosmos constellation. The satellites carry an atomic clock.

Planes and slots

The Glonass series orbit in three distinct planes that are 120 deg apart. Each plane has eight "slots".

Slot	Plane 1	Plane 2	Plane 3
1	779 (Cosmos 2364) 771 (Cosmos 2179)
2	757 (Cosmos 2235)
3	763 (Cosmos 2294)
4	762 (Cosmos 2296)
5	249 (Cosmos 2111)
6	764 (Cosmos 2295)
7	786 (Cosmos 2363) 759 (Cosmos 2236)
8	784 (Cosmos 2362) 769 (Cosmos 2178)
9		776 (Cosmos 2323)
10		781 (Cosmos 2317)
11		785 (Cosmos 2318)
12		767 (Cosmos 2287)
13		782 (Cosmos 2325)
14		770 (Cosmos 2288)
15		780 (Cosmos 2316)
16		775 (Cosmos 2289)
17			760 (Cosmos 2275)
18			758 (Cosmos 2277)
19			777 (Cosmos 2309)
20			765 (Cosmos 2307)
21			756 (Cosmos 2205)
22			766 (Cosmos 2308)
23			761 (Cosmos 2276)
24			774 (Cosmos 2204)
External resources

http://www.rssi.ru/SFCSIC/SFCSIC_main.html

http://satnav.atc.ll.mit.edu/

Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel


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 Program: GMS

Geostationary Meteorological Satellite, also called Himawari which means "sunflower"

Japanese Meteorology Agency satellite program

Originated as Japan's contribution to the international GARP and WWW programs. The satellites are designed to observe cloud cover, land and sea surface and cloud-top temperature, image acquisition, distribution of image data and other met info, collection and relay of weather data from data collection platforms (DCPs) - land, sea and airborne.

Contact

Ministry of Transport

2-1-3 Kasumigaseki, Chiyoda-ku, Tokyo

Tel: +81-03-3212-8341

External resources

http://www.kishou.go.jp


Program: GMS

GMS 1

GMS 2

GMS 3

GMS 4

GMS 5


GMS's specifications

Prime contractor	NEC (with Hughes as major subcontractor)
Platform	HS-378
Mass at launch	682 kg
Mass in orbit	~300 kg
Diameter	2.15 m
Height	3.45 m (except GMS 1: 2.7 m)
Stabilization	Spin stabilized
DC power	291 W
Design lifetime	5 years


GMS's payload

VISSR (Visible and IR Spin Scan Radiometer)

Wavebands	0.5-0.75 µm (visible) 10.5-12.5 µm (IR)
Resolution	visible: 1.25 km IR: 5 km
Image repeat frequency	30 minutes (full Earth)
SEM (Space Environment Monitor)

Solar particle flux measurement; XRS (Solar X-ray Sensor); ion chamber sensitive in 2 bands; EPS (Energetic Particle Sensor); detector groups for electron, proton and alpha particle flux.

Communications instruments

WEFAX (Weather Facsimile)

DCS (Data Collection System)


 GMS 1

Also called Himawari 1

General

Designation	10143 / 77065A
Launch date	14 Jul 1977
Country of origin	Japan
Mission	Meteorology
Geostationary orbit	140°E
Launch vehicle	Thor Delta #132
End of life

Out of service	yes
Technical data

Specifications

Payload


 GMS 2

Also called Himawari 2

General

Designation	12677 / 81076A
Launch date	10 Aug 1981
Country of origin	Japan
Mission	Meteorology
Geostationary orbit	140°E
Launch vehicle	N2
End of life

Out of service	yes
Technical data

Specifications

Payload


 GMS 3

Also called Himawari 3

General

Designation	15152 / 84080A
Launch date	2 Aug 1984
Country of origin	Japan
Mission	Meteorology
Geostationary orbit	see below
Launch vehicle	N2
Location

Begin	End	Position
L: 2 Aug 1984		140°E
Feb 1995	Jun 1995	120°E
End of life

Out of service	Jul 1995
Technical data

Specifications

Payload

Downlink frequency-bands: UHF or VHF, L and S-band


 GMS 4

Also called Himawari 4

General

Designation	20217 / 89070A
Launch date	5 Sep 1989
Country of origin	Japan
Mission	Meteorology
Geostationary orbit	see below
Launch vehicle	H1
Location

Begin	End	Position
L: 5 Sep 1989	mid-Jun 1995	140°E
Aug 1995		120°E, inclined
Technical data

Specifications

Payload

Downlink frequency-bands: UHF or VHF, L and S-band


 GMS 5

Also called Himawari 5

General

Designation	23522 / 95011B
Launch date	17 Mar 1995
Country of origin	Japan
Mission	Meteorology
Geostationary orbit	140°E, inclined
Launch vehicle	H2

Tested in 159.5°E

Technical data

Specifications

Payload

The spacecraft spins at 100 rpm. It carries a Star 27 solid motor which placed it in geostationary orbit.

The satellite can produce a new image of the Earth every 25 minutes(resolution of 1.25 km (visible) and 5.0 km (infrared)). GMS-5 carries an extra infrared channel to measure atmospheric water-vapour distribution.

Downlink frequency-bands: UHF or VHF, L and S-band


 Program: Goes

Geostationary Operational Environmental Satellite

American program developed for GARP (Global Atmospheric Research Program) and operated by NOAA

External resources

http://www.goes.noaa.gov/

http://www.nnic.noaa.gov/SOCC/SOCC_Home.html

http://psbsgi1.nesdis.noaa.gov:8080/EBB/ml/goes.html

http://goes1.gsfc.nasa.gov/

http://rsd.gsfc.nasa.gov/goes/

Notes: the imager and sounder sensors of Goes N and O (planned not before 2002) will be provided by ITT DEFENSE & ELECTRONICS (contract worth $177 million)  Goes N to Q should have a solar X-ray imager built by Lockheed Martin. The Goes N and O satellites will be designed by Hughes (HS-601 based), the contract is worth $423 million An option for Goes P and Q is available for $191 million and $185 million respectively.

Since 1974 the NIST began broadcasting time information from the Goes satellites. This time-code is available from Goes-East and Goes-West at 468.82 & 468.8375 GHz. More details at:

http://www.boulder.nist.gov/timefreq/pubs/sp432/s_goes.htm


Program: Goes

Goes 01

Goes 02

Goes 03

Goes 04

Goes 05

Goes 06

Goes G

Goes 07

Goes 08

Goes 09

Goes 10

Goes 11

Goes 12


Goes 6 & 7's specifications

Prime contractor	Hughes
Mass at launch	835 kg
Length	2.16 m
Height	3.53 m
Stabilization	Spin stabilized
Design lifetime	5 years


Goes 6 & 7's payload

VAS (VISSR (Visible and IR Spin Scan Radiometer) Atmospheric Sounder)

Wavebands	0.55-075 µm (visible): 8 channels 3.7-7.3 µm (near IR): 2 channels 7.7-14.7 µm (mid IR): 2 channels 6.7-14.7 µm (mid IR): 2 channels
Resolution	visible: 1, 2, 4 and 8 km IR: 8-14 km
Image repeat frequency	full Earth: 30 minutes sectors: 3 minutes

Also equipped with 12 IR channels in a detector array for measurement of 3D structure of atmospheric temperature and water vapor distribution.

SEM (Space Environment Monitor)

Measures solar particule flux: XRS (Solar X-ray Sensor); ion chamber sensitive in 2 bands; EPS (Energetic Particle Sensor); 3 detector groups for electron, proton and alpha particle flux.

Communications instruments

WEFAX (Weather Facsimile)

DCS (Data Collection System)


Goes 8, 9, 10, 11 and 12's specifications (Goes Next)

Prime contractor	Space Systems/Loral
Mass at launch	2300 kg
Stabilization	3-axis
Design lifetime	5 years

Telemetry: 2209.086 & 2208.586 MHz (2 kbps)

Command: 2034.2 MHz (250 bps)

Data: 1694.0 MHz MHz


Goes 8, 9, 10, 11 and 12's payload (Goes Next)

Imager (5-channel imaging radiometer)

Wavebands	3.7, 6.7, 10.7, 12µ: visible, IR
Resolution	visible: 1 km IR: 4 km
Sounder (vertical sounder)

Wavebands	visible: 1 channel IR: 18 channels
Resolution	visible: 1 km IR: 2 km
SEM (Space Environment Monitor)

XRS (Solar X-ray Sensor): ion chamber sensitive in 2 bands

EPS (Energetic Particle Sensor): 3 detector groups for electron, proton and alpha particle flux

Communications instruments

WEFAX (Weather Facsimile)

DCS (Data Collection System)

Also equipped with SXI (Solar X-ray Imager) and a Sarsat repeter.


 Goes 01

Also called SMS 3 or Goes A

3rd satellite of the SMS series and first operational satellite operated by the NOAA

General

Designation	08366 / 75100A
Launch date	16 Oct 1975
Country of origin	United States
Mission	Meteorology
Geostationary orbit	see below
Launch vehicle	Thor Delta #116
Mass at launch	627 kg (294 kg?)

Visible and IR photos

Location

Begin	End	Position
L: 16 Oct 1975		60°E
		90°W
		115°W
		135°W
29 Jun 1991		81.2°W; inclination: 10.5°
End of life

Out of service	yes
Technical data

Built by Ford Aerospace

Transmits on 136.38 MHz


 Goes 02

Also called Goes B

General

Designation	10061 / 77048A
Launch date	16 Jun 1977
Country of origin	United States
Mission	Meteorology
Geostationary orbit	see below
Launch vehicle	Thor Delta #131

The satellite has been reactivated in April 1995 to transmit educational programming in S-band (used by Peacesat (see Goes 07)). Used by the NSF to transmit live television broadcasts from its South Pole Station to public broadcasting facilities in the United States.

Location

Begin	End	Position
L: 16 Oct 1975		105°W
24 Oct 1993		136°W, inclination: 9.4°
?		see the Clarke Belt chart for latest location
Technical data

Built by Ford Aerospace

Downlink frequency: 136.38, 1691 and 2297.5925 MHz


 Goes 03

Also called Goes C

General

Designation	10953 / 78062A
Launch date	16 Jun 1978
Country of origin	United States
Mission	Meteorology
Geostationary orbit	see below
Launch vehicle	Thor Delta #142

The satellite has been reactivated in 1995 to transmit educational programming in S-band. Used by the University of Hawaii to transmit educational programming throughout the Hawaiian Islands. In 1989 the satellite started being used by Peacesat (see Goes 07)

Location

Begin	End	Position
L: 16 Jun 1978		60°E
24 Oct 1993		176.2°W, inclination: 8°
~Jan 1995	Jan 1996	drifting East
Feb 1996		103°W, inclination: 11°
End of life

Out of service	probably
Technical data

Built by Ford Aerospace

Downlink frequency: 136.38, 1691 and 2297.5925 MHz


 Goes 04

Also called Goes D

General

Designation	11964 / 80074A
Launch date	9 Sep 1980
Country of origin	United States
Mission	Meteorology
Geostationary orbit	135°W
Launch vehicle	Thor Delta #152
End of life

Out of service	yes
Technical data

Built by Hughes


 Goes 05

Also called Goes E

General

Designation	12472 / 81049A
Launch date	22 May 1981
Country of origin	United States
Mission	Meteorology
Geostationary orbit	see below
Launch vehicle	Thor Delta #154
Mass at launch	900 kg
Location

Begin	End	Position
L: 22 May 1981		75°W
End of life

Out of service	probably
Technical data

Built by Hughes


 Goes 06

Also called Goes F

General

Designation	14050 / 83041A
Launch date	28 Apr 1983
Country of origin	United States
Mission	Meteorology
Geostationary orbit	see below
Launch vehicle	Thor Delta #168
Location

Begin	End	Position
L: 28 Apr 1983		135°W
1984		100°W
		110°W
1989	1989	135°W
End of life

Out of service	21 Jan 1989
Cause	Failure
Technical data

Specifications

Payload


 Goes G

General

Launch date	3 May 1986
Country of origin	United States
Mission	Meteorology
Launch vehicle	Thor Delta #178
End of life

Out of service	3 May 1986
Cause	Launch failure
Technical data

Specifications

Payload


 Goes 07

Also called Goes H

General

Designation	17561 / 87022A
Launch date	26 Feb 1987
Country of origin	United States
Mission	Meteorology
Geostationary orbit	see below
Launch vehicle	Thor Delta #180
Location

Begin	End	Position
L: 26 Feb 1987	1989	79.5°W
1989	?	98°W
Feb 1995	Dec 1995	136°W
Jun 1996	Apr 1997	approx. 94°W
Since Jul 1996 the satellite seems without stabilization. It is constantly drifting and from time to time, its orbit is adjusted. After Jun 1997 no adjustement seems to be made, and the satellite is drifting West.

In June 1999 we learn the satellite is now loaned to Peacesat (PanPacific Education and Communications Experiment by Satellite). Previously Peacesat used Goes 2 and Goes 3

External resources

http://obake.peacesat.hawaii.edu/

Technical data

Specifications

Payload

Transmits in VHF-, L- and S-band. It is equipped with a Sarsat repeter


 Goes 08

Also known as Goes I

General

Designation	23051 / 94022A
Launch date	13 Apr 1994
Country of origin	United States
Mission	Meteorology
Geostationary orbit	75°W
Launch vehicle	Atlas Centaur

On board were instruments for high resolution visible and UV imagers, and "sounders" for temperature and moisture profiles. Also on board were energetic particle detectors and a magnetometer.

The satellite experienced loss of attitude control on 9 Jan 1997. One of the two momentum wheels was lost due to a tachometer failure.  Goes 8 is now using its functioning momentum wheel in concert with the reaction wheel to maintain attitude control.

Technical data

Specifications

Payload


 Goes 09

Also known as Goes J

General

Designation	23581 / 95025A
Launch date	23 May 1995
Country of origin	United States
Mission	Meteorology
Geostationary orbit	see below
Launch vehicle	Atlas Centaur

It has replaced Goes 7 Cost: $220 million

Location

Begin	End	Position
L: 23 May 1995	Dec 1995	90°W
Feb 1996	Aug 1998	135°W
Aug 1998		106°W, drifting
Nov 1998		101°W, drifting
Feb 1999	Mar 1999	98°W
		drifting
May 1999		98°W, drifting
Technical data

Specifications

Payload

The satellite lost a backup motor because of overheating. To cope with this problem the spacecraft, normally facing the earth all the time, will periodically be turned into another direction (4 times a year when the problem is more important).


 Goes 10

Was named Goes K before launch

General

Designation	24786 / 97019A
Launch date	25 April 1997
Country of origin	United States
Mission	Meteorology
Geostationary orbit	see below
Launch vehicle	Atlas Centaur #107

worth $220 million

The satellite has got a default: it's solar arrays cannot rotate properly. The satellite had to be put upside down to maximize solar energy reception, thus inverting the reception images.

Location

Begin	End	Position
L: 25 April 1997	Jul 1998	105°W (spare)
		135°W ? (goes 9 replacement)
Technical data

Specifications

Payload


 Goes 11

Named Goes L until it is launched

General

Designation
Launch date	initially planned in Dec 2003
Country of origin	United States
Mission	Meteorology
Geostationary orbit	135 or 75°W
Launch vehicle	Atlas Centaur
Technical data

Specifications

Payload


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 Goes 12

Named Goes M until it is launched

General

Designation
Launch date	initially planned in Aug 1999
Country of origin	United States
Mission	Meteorology
Geostationary orbit	135 or 75°W
Launch vehicle	Atlas Centaur

Goes N (not this one) will introduce a new system to replace WEFAX: LRIT (Low Rate Image Transmission). This system should be digital, 128 kbps

Technical data

Specifications

Payload


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 Program: Gorizont

The Gorizont satellite system is a general purpose network for communications owned by Informcosmos and operated by several firms, including Intersputnik. The network is composed of 370 ground stations.

The payloads are Statsionar (C-band) and Loutch (Ku-band).


Program: Gorizont

Gorizont 01 Gorizont 02 Gorizont 03 Gorizont 04 Gorizont 05 Gorizont 06 Gorizont 07 Gorizont 08 Gorizont 09 Gorizont 10 Gorizont 11 Gorizont 12 Gorizont 13 Gorizont 14 Gorizont 15	Gorizont 16 Gorizont 17 Gorizont 18 Gorizont 19 Gorizont 20 Gorizont 21 Gorizont 22 Gorizont 23 Gorizont 24 Gorizont 25 Gorizont 26 Gorizont 27 Gorizont 28 Gorizont 29 Gorizont 30	Gorizont 31 Gorizont 32


Gorizont's specifications

Prime contractor	NPO PM
Platform	NPO Gorizont
Mass at launch	2120 kg
Diameter	about 2 m
Height	about 5 m
Stabilization	3-axis
DC power	1300 W
Design lifetime	3 to 5 years

No North-South stabilisation. They also are equipped with one X- or L-band (20 W) transponder.


Antenna Specifications

Antenna	Frequency band	Function / max gain	Coverage	Beam width	Steerability
					North/South	West/East
A1	C	TX / 19.0	global	17°x17°	none	none
A2	C	RX / 19.0	global	17°x17°	none	none
A3	C	TX / 30.0	spot	5°x5°	none	once West to East or East to West
A4	C	TX / 22.0	hemi	9°x18°	none	none
A5	C	RX / 19.0	global	17°x17°	none	none
A6	C	TX / 19.0	global	17°x17°	none	none
A7	C	RX / 25.0	elliptical	6°x12°	none	none
A8	C	TX / 25.0	elliptical	6°x12°	none	none
A9	Ku	RX and TX / 30.0	spot	5°x5°	none	once East to East or East to West

See also the transponder/antenna connection diagram


Gorizont's C-band

Main transponders	6
Backup transponders
Power	1 transponder (#6) of 40 W (TWTA) 5 transponders of 15 W (TWTA)
Bandwidth	spot (#6): 40 MHz others: 36 MHz
Coverage and EIRP max	transponder #6: global beam (A1): 35.6 dBW spot beam (A3): 46.1 dBW 1 global beam(A6): 28.5 dBW 1 large hemispheric beam (A4): 31 dBW 1 little hemispheric beam (A8): 34 dBW
Polarization	uplink: LHCP downlink: RHCP


Gorizont's Ku-band

Main transponders	1
Backup transponders
Power	20 W (TWTA)
Bandwidth	36 MHz
Coverage & EIRP max	spot: 39.2 dBW
Polarization	uplink: LHCP downlink: RHCP


Gorizont's transponder frequency chart (GHz)

LHCP Uplink	LHCP Downlink	Transponder	RHCP Downlink	RHCP Uplink
6.000		6	3.675
6.050		7	3.725
6.100		8	3.775
6.150		9	3.825
6.200		10	3.875
6.250		11	3.925
	11.525	K1		14325


Gorizont transponder/antenna connections


 Gorizont 01

General

Designation	11158 / 78118A
Launch date	19 Dec 1978
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-05, 53°E
Launch vehicle	Proton #74
End of life

Out of service	yes
Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart


 Gorizont 02

General

Designation	11440 / 79062A
Launch date	5 Jul 1979
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-05, 53°E
Launch vehicle	Proton #79
End of life

Out of service	yes
Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart


 Gorizont 03

General

Designation	11648 / 79105A
Launch date	28 Dec 1979
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-05, 53°E
Launch vehicle	Proton #81
End of life

Out of service	yes
Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart


 Gorizont 04

General

Designation	11841 / 80049A
Launch date	14 Jun 1980
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-04, 14°W
Launch vehicle	Proton #83

Launched to broadcast the Olympic Games

End of life

Out of service	yes
Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart


 Gorizont 05

General

Designation	13092 / 82020A
Launch date	15 Mar 1982
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-14, 96.5°E
Launch vehicle	Proton #95
End of life

Out of service	yes
Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart


 Gorizont 06

General

Designation	13624 / 82103A
Launch date	20 Oct 1982
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-10, 170°W
Launch vehicle	Proton #101
End of life

Out of service	yes
Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart


 Gorizont 07

General

Designation	14160 / 83066A
Launch date	30 Jun 1983
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-11, 11°W
Launch vehicle	Proton #110
End of life

Out of service	yes
Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart


 Gorizont 08

General

Designation	14532 / 83118A
Launch date	30 Nov 1983
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-06, 90°E
Launch vehicle	Proton #114
End of life

Out of service	yes
Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart


 Gorizont 09

General

Designation	14940 / 84041A
Launch date	22 Apr 1984
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-05, 53°E
Launch vehicle	Proton #120
End of life

Out of service	yes
Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart


 Gorizont 10

General

Designation	15144 / 84078A
Launch date	1 Aug 1984
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-13, 80°E
Launch vehicle	Proton #123
End of life

Out of service	yes
Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart


 Gorizont 11

General

Designation	15484 / 85007A
Launch date	18 Jan 1985
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-05, 53°E
Launch vehicle	Proton #129
End of life

Out of service	yes
Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart


 Gorizont 12

General

Designation	16769 / 86044A
Launch date	10 Jun 1986
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-12, 40°E
Launch vehicle	Proton #143
End of life

Out of service	yes
Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart


 Gorizont 13

General

Designation	17083 / 86090A
Launch date	18 Nov 1986
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-06, 90°E
Launch vehicle	Proton #146
End of life

Out of service	yes
Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart


 Gorizont 14

General

Designation	17969 / 87040A
Launch date	11 May 1987
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-07, 140°E
Launch vehicle	Proton #152
End of life

Out of service	yes
Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart


 Gorizont 15

General

Designation	19017 / 88028A
Launch date	30 Mar 1988
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-04, 14°W
Launch vehicle	Proton #163
End of life

Out of service	yes
Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart


 Gorizont 16

General

Designation	19397 / 88071A
Launch date	18 Aug 1988
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-13, 80°E
Launch vehicle	Proton #170
End of life

Out of service	yes
Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart


 Gorizont 17

General

Designation	19765 / 89004A
Launch date	26 Jan 1989
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Proton #175
Location

Begin	End	Position
L: 26 Jan 1989	?	Statsionar-05, 53°E
Jun 1995	Jan 1997	34°E, inclined
End of life

Out of service	Jan 1997
Cause	deorbited
Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart


 Gorizont 18

General

Designation	20107 / 89052A
Launch date	5 Jul 1989
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-07, 140°E, inclined
Launch vehicle	Proton #179
End of life

Out of service	Sep 1996?
Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart


 Gorizont 19

General

Designation	20263 / 89081A
Launch date	28 Sep 1989
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Proton #180
Location

Begin	End	Position
L: 28 Sep 1989	Oct 1996	Statsionar-14, 96.5°E, inclined
Dec 1996	Jul 1998	34°E, inclined
End of life

Out of service	July 1998
Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart


Gorizont 19's C-band EIRP: global A6

To get the EIRP of the A1 Global beam add 7.1 dBW


Gorizont 19's C-band EIRP: large hemispheric A4


Gorizont 19's C-band EIRP: narrow hemispheric A8


Gorizont 19's Ku-band EIRP: spot A9


 Gorizont 20

Gorizont #31

General

Designation	20659 / 90054A
Launch date	20 Jun 1990
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Proton #188
Location

Begin	End	Position
L: 20 Jun 1990	Mar 1995	Statsionar-04, 14°W
Jun 1995	Apr 1998	26°E, inclined
Sep 1998	Feb 1999	Statsionar-14, 96.5°E inclined
		drifting West
Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart

EIRP coverage (dBW)

C-band, global (A6)

C-band, large hemispheric (A4)

C-band, narrow hemispheric (A8)


Gorizont 20's C-band EIRP: global A6

To get the EIRP of the A1 Global beam add 7.1 dBW


Gorizont 20's C-band EIRP: large hemispheric A4


Gorizont 20's C-band EIRP: narrow hemispheric A8


 Gorizont 21

Gorizont #32

General

Designation	20923 / 90094A
Launch date	3 Nov 1990
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Proton #191
Location

Begin	End	Position
L: 3 Nov 1990		Statsionar-06, 90°E
		Statsionar-16, 145°E, inclined
Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart

EIRP coverage (dBW)

C-band, global (A6)

C-band, large hemispheric (A4)

C-band, narrow hemispheric (A8)

Ku-band, spot (A9)


Gorizont 21's C-band EIRP: global A6

To get the EIRP of the A1 Global beam add 7.1 dBW


Gorizont 21's C-band EIRP: large hemispheric A4


Gorizont 21's C-band EIRP: narrow hemispheric A8


Gorizont 21's Ku-band EIRP: spot A9


 Gorizont 22

Gorizont #33

General

Designation	20953 / 90102A
Launch date	23 Nov 1990
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Proton #192
Location

Begin	End	Position
L: 23 Nov 1990	Jan 1996	Statsionar-12, 40°E, inclined
mid April 1996		Statsionar-07, 140°E, inclined
Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart

EIRP coverage (dBW)

C-band, global (A6)

C-band, large hemispheric (A4)

C-band, narrow hemispheric (A8)

C-band, spot (A3)

Ku-band, spot (A9)


Gorizont 22's C-band EIRP: global A6

To get the EIRP of the A1 Global beam add 7.1 dBW


Gorizont 22's C-band EIRP: large hemispheric A4


Gorizont 22's C-band EIRP: narrow hemispheric A8


Gorizont 22's C-band EIRP: spot A3


Gorizont 22's Ku-band EIRP: spot A9


 Gorizont 23

Gorizont #34

General

Designation	21533 / 91046A
Launch date	2 Jul 1991
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-21, 103°E
Launch vehicle	Proton #200

The transponder thermoregulation failed

End of life

Out of service	yes
Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart


 Gorizont 24

Gorizont #35

General

Designation	21759 / 91074A
Launch date	23 Oct 1991
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-13, 80°E, inclined
Launch vehicle	Proton #202
End of life

Out of service	late Mar 1998
Cause	failure/deorbited
Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart


 Gorizont 25

Gorizont #36

General

Designation	21922 / 92017A
Launch date	2 Apr 1992
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-21, 103°E, inclined
Launch vehicle	Proton #206
Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart

EIRP coverage (dBW)

C-band, global (A6)

C-band, large hemispheric (A4)

C-band, narrow hemispheric (A8)

Ku-band, spot (A9)


Gorizont 25's C-band EIRP: global A6

To get the EIRP of the A1 Global beam add 7.1 dBW


Gorizont 25's C-band EIRP: large hemispheric A4


Gorizont 25's C-band EIRP: narrow hemispheric A8


Gorizont 25's Ku-band EIRP: spot A9


 Gorizont 26

Gorizont #37

General

Designation	22041 / 92043A
Launch date	14 Jul 1992
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-11, 11°W, inclined
Launch vehicle	Proton #207
Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart

EIRP coverage (dBW)

C-band, global (A6)

C-band, large hemispheric (A4)

C-band, narrow hemispheric (A8)

Ku-band, spot (A9)


Gorizont 26's C-band EIRP: global A6

To get the EIRP of the A1 Global beam add 7.1 dBW


Gorizont 26's C-band EIRP: large hemispheric A4


Gorizont 26's C-band EIRP: narrow hemispheric A8


Gorizont 26's Ku-band EIRP: spot A9


 Gorizont 27

Gorizont #38

General

Designation	22245 / 92082A
Launch date	27 Nov 1992
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Proton #211
Location

Begin	End	Position
L: 27 Nov 1992	Jul 1996	Statsionar-05, 53°E, inclined
Aug 1996	Nov 1998	Statsionar-14, 96.5°E, inclined
Jan 1999		50°E
Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart

EIRP coverage (dBW)

C-band, global (A6)

C-band, large hemispheric (A4)

C-band, narrow hemispheric (A8)

Ku-band, spot (A9)


Gorizont 27's C-band EIRP: global A6

To get the EIRP of the A1 Global beam add 7.1 dBW


Gorizont 27's C-band EIRP: large hemispheric A4


Gorizont 27's C-band EIRP: narrow hemispheric A8


Gorizont 27's Ku-band EIRP: spot A9


 Gorizont #39

End of life

Out of service	27 May 1993
Cause	Third stage failure of the Proton #215 launcher
Decay	In the pacific Ocean


 Gorizont 28

Gorizont #40

General

Designation	22880 / 93069A
Launch date	28 Oct 1993 at 15:17 UT
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-06, 90°E
Launch vehicle	Proton #217
Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart

EIRP coverage (dBW)

C-band, global (A6)

C-band, large hemispheric (A4)

C-band, narrow hemispheric (A8)

C-band, spot (A3)

Ku-band, spot (A9)


Gorizont 28's C-band EIRP: global A6

To get the EIRP of the A1 Global beam add 7.1 dBW


Gorizont 28's C-band EIRP: large hemispheric A4


Gorizont 28's C-band EIRP: narrow hemispheric A8


Gorizont 28's C-band EIRP: spot A3


Gorizont 28's Ku-band EIRP: spot A9


 Gorizont 29

Gorizont #41, also called Rimsat 1 or Rimsat G1 or Statsionar R1 or PASI 0 or LMI AP1

General

Designation	22907 / 93072A
Launch date	18 Nov 1993 at 13:55 UT
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Proton #218
Location

Begin	End	Position
L: 18 Nov 1993	Jan 1997	130°E
Mar 1997	Nov 1998	161°E, inclined
Jan 1999		130°E

Was leased to the US-Malaysian Rimsat company to offer telecommunications services over Asia and the Pacific region. Rimsat was to use the satellite 3 years for a cost of $12 million. In September 1995 the satellite was taken over by Intersputnik after a complex dispute

In 1997, it was sold to the PASI group

Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart

EIRP coverage (dBW)

C-band, global (A6)

C-band, large hemispheric (A4)

C-band, narrow hemispheric (A8)

Ku-band, spot (A9)

The satellite provides slightly better performance than the standard Gorizont: at least 1 dBW more in C-band and 3 dBW in Ku-band (see footprint maps for details). This improvment could be due to a little more power available, perhaps because of the lack of auxilliary (X- or L-band) transponders.


Gorizont 29's C-band EIRP: global A6

At BOL the satellite had 1 dBW additional power
To get the EIRP of the A1 Global beam add 8.1 dBW


Gorizont 29's C-band EIRP: large hemispheric A4

At BOL the satellite had 2 dBW additional power


Gorizont 29's C-band EIRP: narrow hemispheric A8

At BOL the satellite had 1 dBW additional power


Gorizont 29's Ku-band EIRP: spot A9

At BOL the satellite had 3 dBW additional power


 Gorizont 30

Gorizont #42, also called Rimsat 2 or Rimsat G2 or Statsionar R2 or Asiasat G

General

Designation	23108 / 94030A
Launch date	20 May 1994 at 02:01 UT
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Proton #223

Was leased to the US-Malaysian Rimsat company. In September 1995 the satellite was taken over by Intersputnik after a complex dispute

Location

Begin	End	Position
L: 20 May 1994	Dec 1997	142.5°E (Statsionar-R2)
Jan 1998	May 1999	122°E, inclined
Jul 1999		142.5°E (Statsionar-R2) inclined
Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart

EIRP coverage (dBW)

C-band, global (A6)

C-band, spot (A3)

C-band, large hemispheric (A4)

C-band, narrow hemispheric (A8)

Ku-band, spot (A9)

The satellite provides slightly better performance than the standard Gorizont: at least 1 dBW more in C-band and 3 dBW in Ku-band (see footprint maps for details). This improvment could be due to a little more power available, perhaps because of the lack of auxilliary (X- or L-band) transponders.


Gorizont 30's C-band EIRP: global A6

At BOL the satellite had 1 dBW additional power
To get the EIRP of the A1 Global beam add 8.1 dBW


Gorizont 30's C-band EIRP: spot A3

At BOL the satellite had 2 dBW additional power


Gorizont 30's C-band EIRP: large hemispheric A4

At BOL the satellite had 2 dBW additional power


Gorizont 30's C-band EIRP: narrow hemispheric A8

At BOL the satellite had 1 dBW additional power


Gorizont 30's Ku-band EIRP: spot A9

At BOL the satellite had 3 dBW additional power


 Gorizont 31

Gorizont #43

General

Designation	23775 / 96005A
Launch date	25 Jan 1996 at 10:00 UT
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-12, 40°E
Launch vehicle	Proton #239
Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart

EIRP coverage (dBW)

C-band, global (A6)

C-band, large hemispheric (A4)

C-band, narrow hemispheric (A8)

Ku-band, spot (A9)


Gorizont 31's C-band EIRP: global A6

To get the EIRP of the A1 Global beam add 7.1 dBW


Gorizont 31's C-band EIRP: large hemispheric A4


Gorizont 31's C-band EIRP: narrow hemispheric A8


Gorizont 31's Ku-band EIRP: spot A9


 Gorizont 32

Gorizont #44, also called Presidentsky

General

Designation	23880 / 96034A
Launch date	25 May 1996
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-05, 53°E, inclined
Launch vehicle	Proton #242
Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart

EIRP coverage (dBW)

C-band, global (A6)

C-band, large hemispheric (A4)

C-band, narrow hemispheric (A8)

C-band, spot (A3)

Ku-band, spot (A9)


Gorizont 32's C-band EIRP: global A6

To get the EIRP of the A1 Global beam add 7.1 dBW


Gorizont 32's C-band EIRP: large hemispheric A4


Gorizont 32's C-band EIRP: narrow hemispheric A8


Gorizont 32's C-band EIRP: spot A3


Gorizont 32's Ku-band EIRP: spot A9


 Program: GPS

Global Positioning Satellite, also called Navstar (NAVigation System using Timing And Ranging)

American navigation satellite program operated by USAF. The satellites were placed by pairs on 20200 km circular orbits to provide localization (with 10 m precision). They were equipped with atomic clocks.

The program started with the launch between 1978 and 1985 of 10 satellites: block 1 (BI).  Those enabled to check the concept and helped design the first operational generation. In 1987 28 block 2 (BII) satellites were ordered to Rockwell (9 BII and 19 BIIA, lifetime: 7 years).  On 8 Dec 1993 the system was operational with 24 satellites available (4 satellites (slots) on 6 planes 60° apart).  In 1989 Lockheed Martin (GE Astro Space) was ordered 21 satellites for the Block 2R (BIIR), for a total value of $800 million.  The Block 2R satellites weigh about 2000 kg and have 10 years lifetime.  They can operate during 180 days without groundstation intervention.

After the success encountered by the system in the civilian world, a new policy was taken in 1996 to stop degrading civil GPS signals within the next decade.

The follow-on generation is called Block 2F.  51 satellites should be launched from 2001 on. Those satellites should have a second civilian frequency (1227.60 MHz). The satellites are to be provided by Boeing under a $1.3 billion contract. A third civilian frequency is planned at 1176.45 MHz.

Planes and slots

Plane	Slot 1	Slot 2	Slot 3	Slot 4	Slot 5
A	2-21	2-12	2-15	2-04	2-28
B	2-18	2-27	2-02	2-22	2-07
C	2-24	2-25	2-19	2-20	2-13
D	2-11	2-09	2-05	2-23
E	2-01	2-08	2-26	2-10	2-03
F	2-16	2-14	2-06	2-17	2R-02
Contact

Air Force Space Command

External resources

http://www.spacecom.af.mil/usspace/gps.htm

http://www.fas.org/spp/military/program/nav/gps.htm

http://www.navcen.uscg.mil/gps/geninfo/


Program: GPS

GPS BI-01	GPS BI-02	GPS BI-03	GPS BI-04
GPS BI-05	GPS BI-06	GPS BI-07	GPS BI-08
GPS BI-09	GPS BI-10	GPS BI-11
GPS BII-01	GPS BII-02	GPS BII-03	GPS BII-04
GPS BII-05	GPS BII-06	GPS BII-07	GPS BII-08
GPS BII-09
GPS BIIA-10	GPS BIIA-11	GPS BIIA-12	GPS BIIA-13
GPS BIIA-14	GPS BIIA-15	GPS BIIA-16	GPS BIIA-17
GPS BIIA-18	GPS BIIA-19	GPS BIIA-20	GPS BIIA-21
GPS BIIA-22	GPS BIIA-23	GPS BIIA-24	GPS BIIA-25
GPS BIIA-26	GPS BIIA-27	GPS BIIA-28
GPS BIIR-01	GPS BIIR-02	GPS BIIR-03


GPS frequencies

Military: 1227.6 MHz

Civilian: 1575.42 MHz

Nuclear burst detection: 1381.05 MHz

Telemetry on 2227.5 MHz.


 GPS BI-01

Also called OPS 5111 or Navstar 1 or GPS 01

General

Designation	10684 / 78020A
Launch date	22 Feb 1978
Country of origin	United States
Mission	Navigation
Perigee/Apogee	20230/20578 km
Inclination	64.6°
Period	727 min
Launch vehicle	Atlas F
Launch site	Vandenberg
End of life

Out of service	July 1985


 GPS BI-02

Also called OPS 5112 or Navstar 2 or GPS 02

General

Designation	10893 / 78047A
Launch date	13 May 1978
Country of origin	United States
Mission	Navigation
Perigee/Apogee	19522/20653 km
Inclination	63.6°
Period	714.2 min
Launch vehicle	Atlas F
Launch site	Vandenberg
End of life

Out of service	July 1981


 GPS BI-03

Also called OPS 5113 or Navstar 3 or GPS 03

General

Designation	11054 / 78093A
Launch date	7 Oct 1978
Country of origin	United States
Mission	Navigation
Perigee/Apogee	20705/20942 km
Inclination	63.3°
Period	744.2 min
Launch vehicle	Atlas F
Launch site	Vandenberg

Was equipped with corner-cube reflectors for satellite laser ranging (SLR). SLR tracking of the satellites permit onboard clock errors and satellite ephemeris errors in GPS tracking to be differentiated.

End of life

Out of service	May 1992


 GPS BI-04

Also called OPS 5114 or Navstar 4 or GPS 04

General

Designation	11141 / 78112A
Launch date	11 Dec 1978
Country of origin	United States
Mission	Navigation
Perigee/Apogee	20748/21013 km
Inclination	64.6°
Period	746.5 min
Launch vehicle	Atlas F
Launch site	Vandenberg
End of life

Out of service	Oct 1989


 GPS BI-05

Also called OPS 5117 or Navstar 5 or GPS 05

General

Designation	11690 / 80011A
Launch date	9 Feb 1980
Country of origin	United States
Mission	Navigation
Perigee/Apogee	19807/20557 km
Inclination	65°
Period	718 min
Launch vehicle	Atlas F
Launch site	Vandenberg

Was equipped with corner-cube reflectors for satellite laser ranging (SLR). SLR tracking of the satellites permit onboard clock errors and satellite ephemeris errors in GPS tracking to be differentiated.

End of life

Out of service	Nov 1983


 GPS BI-06

Also called OPS 5118 or Navstar 6 or GPS 06

General

Designation	11783 / 80032A
Launch date	26 Apr 1980
Country of origin	United States
Mission	Navigation
Perigee/Apogee	19378/20480 km
Inclination	62.7°
Period	707.8 min
Launch vehicle	Atlas F
Launch site	Vandenberg
End of life

Out of service	Mar 1991


 GPS BI-07

Also called Navstar 7 or GPS 07

End of life

Out of service	18 Dec 1981
Cause	Launch failure (Atlas F)


 GPS BI-08

Also called OPS 9794 or Navstar 8 or GPS 08

General

Designation	14189 / 83072A
Launch date	14 Jul 1983
Country of origin	United States
Mission	Navigation
Perigee/Apogee	20801/21183 km
Inclination	64.3°
Period	751.1 min
Launch vehicle	Atlas F
Launch site	Vandenberg
End of life

Out of service	May 1993
Cause	Replaced by GPS BIIA-20
Technical data

Used to transmit on 1575.42 and 1227.6 MHz


 GPS BI-09

Also called USA 001 or Navstar 9 or GPS 09

General

Designation	15039 / 84059A
Launch date	13 Jun 1984
Country of origin	United States
Mission	Navigation
Perigee/Apogee	20032/20332 km
Inclination	63.9°
Period	718 min
Launch vehicle	Atlas F
Launch site	Vandenberg
End of life

Out of service	Jun 1994
Technical data

Transmits on 1575.42 and 1227.6 MHz


 GPS BI-10

Also called USA 005 or Navstar 10 or GPS 10

General

Designation	15271 / 84097A
Launch date	8 Sep 1984
Country of origin	United States
Mission	Navigation
Perigee/Apogee	19952/20411 km
Inclination	62.2°
Period	718 min
Launch vehicle	Atlas E14
Launch site	Vandenberg
End of life

Out of service	26 Mar 1996 (orbit raised)
Technical data

Transmited on 1575.42 and 1227.6 MHz


 GPS BI-11

Also called USA 010 or Navstar 11 or GPS 11

General

Designation	16129 / 85093A
Launch date	9 Oct 1985
Country of origin	United States
Mission	Navigation
Perigee/Apogee	20449/21211 km
Inclination	64.1°
Period	744.4 min
Launch vehicle	Atlas E55
Launch site	Vandenberg
End of life

Out of service	Apr 1994
Technical data

Transmits on 1575.42 and 1227.6 MHz


 GPS BII-01

Also called USA 035 or Navstar 2-1 or GPS 14

General

Designation	19802 / 89013A
Launch date	14 Feb 1989
Country of origin	United States
Mission	Navigation
Perigee/Apogee	20088/20274 km
Inclination	55.0°
Period	717.9 min
Launch vehicle	Delta 2 #183
Technical data

Frequencies


 GPS BII-02

Also called USA 038 or Navstar 2-2 or GPS 13

General

Designation	20061 / 89044A
Launch date	10 Jun 1989
Country of origin	United States
Mission	Navigation
Perigee/Apogee	19847/20517 km
Inclination	54.5°
Period	718 min
Launch vehicle	Delta 2 #185
Technical data

Frequencies


 GPS BII-03

Also called USA 042 or Navstar 2-3 or GPS 16

General

Designation	20185 / 89064A
Launch date	18 Aug 1989
Country of origin	United States
Mission	Navigation
Perigee/Apogee	20154/20207 km
Inclination	55.0°
Period	717.9 min
Launch vehicle	Delta 2 #186
Technical data

Frequencies


 GPS BII-04

Also called USA 047 or Navstar 2-4 or GPS 19

General

Designation	20302 / 89085A
Launch date	21 Oct 1989
Country of origin	United States
Mission	Navigation
Perigee/Apogee	20176/20188 km
Inclination	53.4°
Period	718 min
Launch vehicle	Delta 2 #188
Technical data

Frequencies


 GPS BII-05

Also called USA 049 or Navstar 2-5 or GPS 17

General

Designation	20361 / 89097A
Launch date	11 Dec 1989
Country of origin	United States
Mission	Navigation
Perigee/Apogee	19995/20369 km
Inclination	55.7°
Period	718 min
Launch vehicle	Delta 2 #190
Technical data

Frequencies


 GPS BII-06

Also called USA 050 or Navstar 2-6 or GPS 18

General

Designation	20452 / 90008A
Launch date	24 Jan 1990
Country of origin	United States
Mission	Navigation
Perigee/Apogee	20038/20324 km
Inclination	54°
Period	717.9 min
Launch vehicle	Delta 2 #191
Technical data

Frequencies


 GPS BII-07

Also called USA 054 or Navstar 2-7 or GPS 20

General

Designation	20533 / 90025A
Launch date	26 Mar 1990
Country of origin	United States
Mission	Navigation
Perigee/Apogee	20071/20292 km
Inclination	54.9°
Period	718 min
Launch vehicle	Delta 2 #193
End of life

Out of service	21 May 1996?
Cause
Technical data

Frequencies


 GPS BII-08

Also called USA 063 or Navstar 2-8 or GPS 21

General

Designation	20724 / 90068A
Launch date	2 Aug 1990
Country of origin	United States
Mission	Navigation
Perigee/Apogee	19891/20473 km
Inclination	54.7°
Period	718 min
Launch vehicle	Delta 2 #197
End of life

Out of service	10 May 1996
Cause	wheels failure
Technical data

Frequencies


 GPS BII-09

Also called USA 064 or Navstar 2-9 or GPS 15

General

Designation	20830 / 90088A
Launch date	1 Oct 1990
Country of origin	United States
Mission	Navigation
Perigee/Apogee	20002/20363 km
Inclination	55.6°
Period	718 min
Launch vehicle	Delta 2 #199
Technical data

Frequencies


 GPS BIIA-10

Also called USA 066 or Navstar 2A-10 or GPS 23

General

Designation	20959 / 90103A
Launch date	26 Nov 1990
Country of origin	United States
Mission	Navigation
Perigee/Apogee	19968/20394 km
Inclination	55.1°
Period	718 min
Launch vehicle	Delta 2 #201
Technical data

Frequencies


 GPS BIIA-11

Also called USA 071 or Navstar 2A-11 or GPS 24

General

Designation	21552 / 91047A
Launch date	4 Jul 1991
Country of origin	United States
Mission	Navigation
Perigee/Apogee	20031/20331 km
Inclination	56°
Period	718 min
Launch vehicle	Delta 2 #206
Technical data

Frequencies


 GPS BIIA-12

Also called USA 079 or Navstar 2A-12 or GPS 25

General

Designation	21890 / 92009A
Launch date	23 Feb 1992
Country of origin	United States
Mission	Navigation
Perigee/Apogee	20031/20335 km
Inclination	54.2°
Period	718 min
Launch vehicle	Delta 2 #207
Technical data

Frequencies


 GPS BIIA-13

Also called USA 080 or Navstar 2A-13 or GPS 28

General

Designation	21930 / 92019A
Launch date	10 Apr 1992
Country of origin	United States
Mission	Navigation
Perigee/Apogee	20026/20338 km
Inclination	55.7°
Period	718 min
Launch vehicle	Delta 2 #208
End of life

Out of service	5 May 1997
Cause	navigation hardware failure
Technical data

Frequencies


 GPS BIIA-14

Also called USA 083 or Navstar 2A-14 or GPS 26

General

Designation	22014 / 92039A
Launch date	7 Jul 1992
Country of origin	United States
Mission	Navigation
Perigee/Apogee	19961/20402 km
Inclination	54.9°
Period	718 min
Launch vehicle	Delta 2 #211
Technical data

Frequencies


 GPS BIIA-15

Also called USA 084 or Navstar 2A-15 or GPS 27

General

Designation	22108 / 92058A
Launch date	9 Sep 1992
Country of origin	United States
Mission	Navigation
Perigee/Apogee	19909/20453 km
Inclination	54.2°
Period	718 min
Launch vehicle	Delta 2 #214
Technical data

Frequencies


 GPS BIIA-16

Also called USA 085 or Navstar 2A-16 or GPS 32

General

Designation	22231 / 92079A
Launch date	22 Nov 1992 at 20:53 UT
Country of origin	United States
Mission	Navigation
Perigee/Apogee	20088/20275 km
Inclination	54.7°
Period	717.9 min
Launch vehicle	Delta 2 #216
Technical data

Frequencies


 GPS BIIA-17

Also called USA 087 or Navstar 2A-17 or GPS 29

General

Designation	22275 / 92089A
Launch date	18 Dec 1992 at 10:16 UT
Country of origin	United States
Mission	Navigation
Perigee/Apogee	20044/20320 km
Inclination	54.6°
Period	718 min
Launch vehicle	Delta 2 #217
Technical data

Frequencies


 GPS BIIA-18

Also called USA 088 or Navstar 2A-18 or GPS 22

General

Designation	22446 / 93007A
Launch date	3 Feb 1993 at 02:55 UT
Country of origin	United States
Mission	Navigation
Perigee/Apogee	19995/20370 km
Inclination	54.5°
Period	718 min
Launch vehicle	Delta 2 #218
Technical data

Frequencies


 GPS BIIA-19

Also called USA 090 or Navstar 2A-19 or GPS 31

General

Designation	22581 / 93017A
Launch date	30 Mar 1993 at 03:29 UT
Country of origin	United States
Mission	Navigation
Perigee/Apogee	20072/20293 km
Inclination	55.2°
Period	718 min
Launch vehicle	Delta 2 #219

Equipped with a Star 37 solid motor

Technical data

Frequencies


 GPS BIIA-20

Also called USA 091 or Navstar 2A-20 or GPS 37

General

Designation	22657 / 93032A
Launch date	13 May 1993
Country of origin	United States
Mission	Navigation
Perigee/Apogee	20017/20345 km
Inclination	55.2°
Period	718 min
Launch vehicle	Delta 2 #220
Technical data

Frequencies


 GPS BIIA-21

Also called USA 092 or Navstar 2A-21 or GPS 39

General

Designation	22700 / 93042A
Launch date	26 Jun 1993 at 13:27 UT
Country of origin	United States
Mission	Navigation
Perigee/Apogee	20112/20250 km
Inclination	54.4°
Period	717.9 min
Launch vehicle	Delta 2 #221
Technical data

Frequencies


 GPS BIIA-22

Also called USA 094 or Navstar 2A-22 or GPS 35

General

Designation	22779 / 93054A
Launch date	30 Aug 1993 at 12:35 UT
Country of origin	United States
Mission	Navigation
Perigee/Apogee	20127/20236 km
Inclination	54.6°
Period	718 min
Launch vehicle	Delta 2 #222
Technical data

Frequencies


 GPS BIIA-23

Also called USA 096 or Navstar 2A-23 or GPS 34

General

Designation	22877 / 93068A
Launch date	26 Oct 1993
Country of origin	United States
Mission	Navigation
Perigee/Apogee	20104/20260 km
Inclination	55.2°
Period	718 min
Launch vehicle	Delta 2 #223
Technical data

Frequencies


 GPS BIIA-24

Also called USA 100 or Navstar 2A-24 or GPS 36

General

Designation	23027 / 94016A
Launch date	10 Mar 1994
Country of origin	United States
Mission	Navigation
Perigee/Apogee	20023/20339 km
Inclination	55.1°
Period	717.95 min
Launch vehicle	Delta 2 #226
Technical data

Frequencies


 GPS BIIA-25

Also called USA 117 or Navstar 2A-25 or GPS 33

General

Designation	23833 / 96019A
Launch date	28 Mar 1996
Country of origin	United States
Mission	Navigation
Perigee/Apogee	20252/20548 km
Inclination	54.8°
Period
Launch vehicle	Delta 2 #234

The satellite was worth $55 million. A solid Thiokol Star 37 apogee motor was used to circularize the orbit

After this launch, 3 BIIA satellites are still to be launched

Technical data

Frequencies

Telemetry on 2227.5 MHz


 GPS BIIA-26

Also called USA 126 or Navstar 2A-26 or GPS 40

General

Designation	23953 / 96041A
Launch date	16 Jul 1996
Country of origin	United States
Mission	Navigation
Perigee/Apogee	20275/20368 km
Inclination	54.8°
Period	723 min
Launch vehicle	Delta 2 #237
Technical data

Frequencies

Telemetry on 2227.5 MHz (telemetry number PRN 10)


 GPS BIIA-27

Also called USA 128 or Navstar 2A-27 or GPS 30

General

Designation	24320 / 96056A
Launch date	12 Sep 1996
Country of origin	United States
Mission	Navigation
Perigee/Apogee	20275/20368 km
Inclination	54.8°
Period	723 min
Launch vehicle	Delta 2 #238
Technical data

Frequencies


 GPS BIIA-28

Also called USA 134 or Navstar 2A-28 or GPS 38

General

Designation	25030 / 97067A
Launch date	6 Nov 1997
Country of origin	United States
Mission	Navigation
Perigee/Apogee	19914/20626 km
Inclination	54.9°
Period	723 min
Launch vehicle	Delta 2 #249

Last of the GPS 2A series

Technical data

Frequencies

Mass at launch: 1881 kg; Dry mass: 930 kg


 GPS BIIR-01

Also called Navstar 2R-1 or GPS #39

General

Designation	n/a
Launch date	17 Jan 1997
Country of origin	United States
Mission	Navigation
Perigee/Apogee	n/a
Inclination	n/a
Period	n/a
Launch vehicle	Delta 2 #241

Worth $40 million

End of life

Out of service	17 Jan 1997
Cause	launch failure


 GPS BIIR-02

Also called USA 132 or Navstar 2R-1 or GPS 43

General

Designation	24876 / 97035A
Launch date	23 July 1997
Country of origin	United States
Mission	Navigation
Perigee/Apogee	20000 km
Inclination	55°
Period	714 min
Launch vehicle	Delta 2 #245

Worth $43 million

This new GPS series has among advantages the ability to be launched into any of the required orbits on any day of the year with 60-day advanced scheduling. The GPS Block IIR has an estimated life span of 10 years and is equipped with advanced on-board computers to allow for in-flight software modifications.

This was the first DOD mission controlled from the 45th Space Wing's new Launch Control Center, located in the 1st SLS Operations Building.

Technical data

Frequencies


 GPS BIIR-03

Also called GPS 50

General

Designation
Launch date
Country of origin	United States
Mission	Navigation
Perigee/Apogee	20000 km
Inclination	55°
Period	714 min
Launch vehicle	Delta 2

Was damaged by rain in May 1999 before launch: the shields in the white room were not properly installed.

Technical data

Frequencies


 Program: Grace

Gravity Recovery and Climate Experiment

NASA scientific program composed of 2 satellites to be launched in 2001. Intended to measure the earth's gravitational field over that period with extreme accuracy.

External resources

http://essp.gsfc.nasa.gov/grace/

http://www.csr.utexas.edu/grace/

Technical data

General

Designation
Launch date	August 2001
Country of origin	United States
Mission
Perigee/Apogee	450 km
Inclination
Period
Launch vehicle	Cosmos
Launch site

Operator: JPL

Specifications

Prime contractor
Platform	Flexbus (DSS)
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime	5 years

The platform contract is worth $16.9 million


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 Program: Gramsat

Gramsat are Indian satellites to be launched by GSLV

The Gramsat payloads include two high power S-band, and one single channel C-band tranponders. It would also carry C-band transponders for evaluation of indigenoulsy developed 10 W solid state power amplifier.


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 GRO

Gamma Ray Observatory, also called Compton gamma-ray observatory

General

Designation	21225 / 91027B
Launch date	5 Apr 1991
Country of origin	United States
Operator	NASA
Mission	Scientific: Astronomy
Perigee/Apogee	437/462 km
Inclination	28.4°
Period	93.5 min
Launch vehicle	STS 37
Mass at launch	15620 kg

The objective of the Compton GRO is to make comprehensive observations of gamma ray sources throughout the Universe. The observatory carries four scientific instruments that make gamma ray energy measurements from 0.1 million electron volts to 30,000 million electron volts.

Orbit reboost maneuver planned in mid-1997.

External resources

http://cossc.gsfc.nasa.gov

http://www.gsfc.nasa.gov/education/curricula/GRO_Ed_Brfs.html

Technical data

Specifications

Prime contractor	TRW
Dimension	7.7 x 5.5 x 4.6 m
Solar array	21.5 m
Stabilization	3-axis
DC power	EOL: 3980 W
Design lifetime	2 years (min)

Realtime acquisition via TDRS (tape recorders have failed).

Telemetry: 2287.5 MHz (realtime: 1/32 kbps, playback: upto 512 kbps)

Command: 2106.4 MHz (1/0.125 kbps)

BATSE (Burst and Transcient Source Experiment)

Payload mass	976 kg
Industrial responsibility	Marshall SFC
Gamma-ray energy range	20-600 keV

Equipped with 8 detectors

OSSE (Oriented Scintillation Spectrometer Experiment)

Payload mass	1820 kg
Industrial responsibility	Ball Aerospace
Gamma-ray energy range	100 keV-10 MeV
COMTEL (imaging COMpton TELescope)

Payload mass	1460 kg
Industrial responsibility	MBB
Gamma-ray energy range	1-30 MeV
Angular resolution	1.7-4.4°
EGRET (Energetic Gamma Ray Experiment Telescope)

Payload mass	1830 kg
Industrial responsibility	Goddard SFC
Gamma-ray energy range	20 MeV-30 GeV


 Gsat

General

Designation
Launch date	initially planned in first quarter 2000
Country of origin	India
Mission
Geostationary orbit
Launch vehicle	GSLV D1
Launch site	Sriharikota (second launch pad)

Aimed at demonstrating advanced communication technologies such as digital audio, data and video broadcasting. The payload includes two S-band transponders, a high power C-band transponder and two indigenously developed C-band transponders. 2500 kg

The first flight of GSLV is expected to cost Rs 11.05 billion  The second launch pad was being built at a cost of Rs 2.89 billion.


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 Program: Gstar

American telecommunication satellite program operated by GE Americom, formerly GTE Spacenet Corp.


Program: Gstar

Gstar 1

Gstar 2

Gstar 3

Gstar 4


Gstar's specifications

Prime contractor	GE Astro Space
Platform	GE 3000
Mass dry	543 kg
Mass at launch	1270 kg
Mass in orbit	759 kg
Dimension	1.63 x 1.32 x 0.99 m
Solar array	13.93 m span
Stabilization	3-axis
DC power	BOL: 1750 W
Design lifetime	10 years


Gstar's Ku-band

Main transponders	14+2
Backup transponders	5+1
Power	14 transponders of 20 W (TWTA) 2 transponders of 27 W (TWTA)
Bandwidth	54 MHz
Coverage
EIRP max	20 W: 38 dBW 27 W: 48 dBW
Polarization	linear


Gstar's transponder frequency chart (GHz)

Horizontal Uplink	Horizontal Downlink	Transponder	Vertical Downlink	Vertical Uplink
	11.730	1		14.030
14.044		9	11.744
	11.791	2		14.091
14.105		10	11.805
	11.852	3		14.152
14.166		11	11.866
	11.913	4		14.213
14.227		12	11.927
	11.974	5		14.274
14.288		13	11.988
	12.035	6		14.335
14.349		14	12.049
	12.096	7		14.396
14.410		15	12.110
	12.157	8		14.457
14.471		16	12.171


 Gstar 1

General

Designation	15677 / 85035A
Launch date	8 May 1985
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V13

Will be colocated with GE 1 and de-orbited when GE 2 is operational

Location

Begin	End	Position
L: 8 May 1985	Nov 1996	103°W
Jan 1997		105°W
Technical data

Specifications

Ku-band

Transponder frequency chart


 Gstar 2

General

Designation	16649 / 86026A
Launch date	28 Mar 1986
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V17
Location

Begin	End	Position
L: 28 Mar 1986
< May 1992	May 1992 >	105°W
<Oct 1993		125°W, inclined
End of life

Out of service	Aug 1997
Cause	deorbited
Technical data

EIRP coverage (dBW)

Specifications

Ku-band

Transponder frequency chart


Gstar 2's Ku-band EIRP


 Gstar 3

General

Designation	19483 / 88081A
Launch date	8 Sep 1988
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	93°W, inclined
Launch vehicle	Ariane V25

This satellite had a motor problem and so is inclined

End of life

Out of service	Apr 1997
Cause	decommissioned, inclination too important
Technical data

Specifications

Ku-band

Transponder frequency chart


 Gstar 4

General

Designation	20946 / 90100B
Launch date	20 Nov 1990
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V40
Location

Begin	End	Position
L: 20 Nov 1990
< May 1992	May 1992 >	125°W
<Oct 1993		105°W
Technical data

EIRP coverage (dBW)

Specifications

Ku-band

Transponder frequency chart


Gstar 4's Ku-band EIRP


 Haruka

Means "far away", also called Muses B and Halca (Highly Advanced Laboratory for Communications and Astronomy)

General

Designation	24720 / 97005A
Launch date	12 Feb 1997
Country of origin	Japan
Mission	Scientific: astronomy
Perigee/Apogee	565 / 21462 km
Inclination	31.3°
Period	374 min
Launch vehicle	Mu 5

Operated by Isas

Haruka is the space segment of the VSOP (VLBI Space Observatory Programme), and will unfurl an 8-meter radiotelescope antenna to make joint observations with ground based radio observatories, simulating a telescope larger than the Earth. Haruka carries detectors operating at 1.6, 5 and 22 GHz, and will be able to make radio images with very high spatial resolution, permitting precise measurements of quasar jets and galactic maser sources.

Downlinks at 128 kbps (2.2636 GHz). Lifetime: 3 to 5 years

External resources

http://www.vsop.isas.ac.jp/MUSES_B.html

http://www.vsop.isas.ac.jp/VSOP.html


 Healthsat

Also called Healthsat 2 because Uosat 3 provided services as Healthsat 1

General

Designation	22827 / 93061E
Launch date	25 Sep 1993
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	788/803 km
Inclination	98.7°
Period	100.8 min
Launch vehicle	Ariane V59
Mass at launch	47.5 kg

Transmits medical data (provided by the United States, Canada and the UK) to African universities, hospitals and documentation centers.

Contact

SatelLife

1360 Soldier's Field Rd., Boston, MA 02135, USA

Tel: +1-617-789-5455

Fax: +1-617-789-4771

Email: hnet@usa.healthnet.org

External resources

http://www.healthnet.org/

http://www.ee.surrey.ac.uk/CSER/UOSAT/missions/hs2.html

Technical data

Specifications

Prime contractor	SSTL (Surrey Satellite Technology Ltd.)
Platform	SSTL
Mass at launch	50.5 kg
Mass in orbit
Length	352 mm
Width	356 mm
Height	670 mm
Stabilization	gravity gradient
DC power
Design lifetime	5 years


 Program: Heao

High Energy Astronomy Observatory

American scientific program made of 3 large observatories designed to study the "high energy universe," i.e., X-rays, gamma rays, and cosmic particles.

The scientific objectives of the HEAO program were to learn more about some of the most puzzling objects in the universe: pulsars, neutron stars, black holes, quasars, radio galaxies, and supernovas. Many of these radiate only in the X-ray, gamma ray, and cosmic ray regions of the electromagnetic spectrum and cannot be studied from the ground.


Program: Heao

Heao 1

Heao 2

Heao 3


 Heao 1

General

Designation	10217 / 77075A
Launch date	12 Aug 1977
Country of origin	United States
Mission	Scientific: X-ray astronomy
Perigee/Apogee	429/447 km
Inclination	22.7°
Period	93.4 min
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
Mass at launch	approx. 3 t
End of life

Decay	15 Mar 1979
External resources

http://heasarc.gsfc.nasa.gov/docs/heasarc/missions/heao1.html


 Heao 2

Also called "Einstein observatory"

General

Designation	11101 / 78103A
Launch date	13 Nov 1978
Country of origin	United States
Mission	Scientific: X-ray astronomy
Perigee/Apogee	526/548 km
Inclination	23.5°
Period	95.4 min
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
Mass at launch	approx. 3 t

Equipped with a 58cm diameter telescope with a 3.3m focal length. The satellite also contained five other instruments, 4 of which shared the use of the telescope to make a variety of measurements of X-rays emitted by stellar objects. The fifth instrument, independent of the telescope, measured properties of X-rays beyond the telescope's energy range.

Built by TRW Defense and Space Systems for NASA's Marshall Space Flight Center

End of life

Decay	25 Mar 1982
External resources

http://heasarc.gsfc.nasa.gov/docs/heasarc/missions/heao2.html


 Heao 3

General

Designation	11532 / 79082A
Launch date	20 Sep 1979
Country of origin	United States
Mission	Scientific: gamma-ray astronomy
Perigee/Apogee	487/503 km
Inclination	43.6°
Period	94.5 min
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
Mass at launch	approx. 3 t
End of life

Decay	7 Dec 1981
External resources

http://heasarc.gsfc.nasa.gov/docs/heasarc/missions/heao3.html


 Program: Hélios

In Greek mythology Helios was all-seeing and all-knowing

French military observation program. The first generation is financed by France (79%), Italy (14%) and Spain (7%). Operated by the DGA (Délégation Générale à l'Armement) and the CNES. Each country can use the satellite in proportion of its financial participation. Each country can order observations and obtain the results via its Earth station. Each country's results are cyphered so that only the orderer can use the data.

The second generation (Helios 2) is planned for 2002 and will be achieved by France and Spain (3%). It is supposed to cost $1.2 billion. It would be equipped with for optical and IR observation. 2 identical satellites are to be built, based on the MMS Mark 2+ bus (3600 kg)  Belgium is willing to participate to the project.

Zenon (eavesdropping satellite) and Clementine (the Cerise companion). Also for military communications see Bimilsatcom


Program: Hélios

Hélios 1A

Hélios 1B


 Hélios 1A

General

Designation	23605 / 95033A
Launch date	7 Jul 1995
Country of origin	France
Mission	Military: reconnaissance
Perigee/Apogee	673/676 km
Inclination	98.1°
Period	98.2 min
Launch vehicle	Ariane V75

Hélios 1A carries an eavesdroppring payload called Euracom, built by Dassault Electronique

Technical data

Specifications

Prime contractor	Matra Marconi Space (under control of CNES)
Platform	Spot (Mark 2)
Mass at launch	2537 kg
Mass in orbit
Dimension
Stabilization	guidance by momentum wheels
DC power	2200 W
Design lifetime	5 years

2 tape recorders, only optical observation

The Hélios system downlinks in S-band at 2206.53 MHz and in X-band at 8253.0 MHz


 Hélios 1B

General

Designation
Launch date	initially planned for late 1996 / early 1997
Country of origin	France
Mission	Military: reconnaissance
Perigee/Apogee
Inclination
Period
Launch vehicle	Ariane

When this satellite is launched the revisit period will be about 1 day. Same orbit but 180 degrees separation

Probably identical to Helios 1A


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 Program: Heos

Highly Eccentric Orbit Satellite

European scientific program


Program: Heos

Heos 1

Heos 2


 Heos 1

General

Designation	03595 / 68109A
Launch date	5 Dec 1968
Country of origin	Europe
Mission	Scientific: magnetophere study
Perigee/Apogee	20020/202780 km
Inclination	60.5°
Period	6704.3 min
Launch vehicle	Thor Delta #61
Mass at launch	128 kg

Study of the inter-planetary magnetic field, solar wind and space particles.

End of life

Decay	28 Oct 1975


 Heos 2

General

Designation	05814 / 72005A
Launch date	31 Jan 1972
Country of origin	Europe
Mission	Scientific: magnetophere study
Perigee/Apogee	405/240164 km
Inclination	89.9°
Period	7477.1 min
Launch vehicle	Thor Delta #87
Mass at launch	117 kg

Study of the high altitude magnetosphe limits and inter-planetary magnetic fields and particles.

End of life

Decay	2 Aug 1974


 HESSI

High Energy Solar Spectroscopic Imager

General

Designation
Launch date	2000
Country of origin	United States
Mission	Scientific: Sun study
Perigee/Apogee
Inclination
Period
Launch vehicle	Pegasus
Launch site

HESSI will investigate the physics of particle acceleration and energy release in solar flares through an unprecedented combination of high resolution imaging and spectroscopy of X-rays and gamma rays from 2 keV to 20 MeV during the next solar maximum. It uses Fourier-transform imaging with 12 bi-grid modulation collimators and cooled germanium and silicon detectors mounted on a Sun-pointed spin-stabilized spacecraft in a low-altitude equatorial orbit. HESSI will carry out the first imaging spectroscopy in hard X-rays with 2 arcseconds angular resolution, time resolution to tens of ms, and \sim1 keV energy resolution; the first gamma-ray line spectroscopy from a spacecraft with \sim1 keV energy resolution; and the first gamma-ray line and continuum imaging with 20 arcseconds angular resolution.

Project cost: $12 million

External resources

http://hesperia.gsfc.nasa.gov/sftheory/hessi.htm

Technical data

Specifications

Prime contractor	Spectro Astro Inc
Platform
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization	spin stabilized
DC power
Design lifetime


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 HETE

High-Energy Transient Experiment

General

Designation	n/a / 96061A Failed to separate with SAC B
Launch date	4 Nov 1996
Country of origin	United States
Mission	Scientific
Perigee/Apogee
Inclination
Period
Launch vehicle	Pegasus XL #14

The prime objective of HETE is to carry out the first multiwavelength study of gamma-ray bursts with UV, X-ray, and gamma-ray instruments mounted on a single, compact spacecraft. A unique feature of the HETE mission is its capability to localize GRBs with ~10 arc second accuracy, in near real time aboard the spacecraft, and to transmit these positions directly to a network of receivers at existing ground-based observatories, enabling rapid, sensitive follow-up studies in the radio, IR, and optical bands.

HETE was carried inside the Dual Payload Attach Fixture on which SAC B was mounted, so it was trapped and was unable to deploy its solar panels.

External resources

http://nis-www.lanl.gov/nis-projects/hete/

http://space.mit.edu/HETE/

Technical data

Omnidirectional Gamma-Ray Spectrometer

Build by	CESR (France)
Instrument type	NaI(Tl); cleaved
Energy range	6 keV to > 1 MeV
Timing resolution	4 ms
Spectral resolution	~40% @ 6 keV; ~7% @ 1 MeV
Effective area	120 cm**2 (total for 4 units)
Sensitivity (10 sigma)	3 x 10**-8 erg/cm**2/s for 8-1000 keV
FOV	~ 2 pi sr
Angular resolution	~ 1 sr
Wide Field X-ray Monitor

Build by	RIKEN (Japan) and LANL (USA)
Instrument type	2 1-dim Coded aperture cameras, with PSPCs
Energy range	2 to 25 keV
Timing resolution	1 ms
Spectral resolution	~18% @ 6 keV
Effective area	200 cm**2 (each of 2 units)
Sensitivity (10 sigma)	8 x 10**-9 erg/cm**2/s for 2-10 keV
FOV	~ 2 sr (combined)
Angular resolution (1 sigma)	about 10 arcmin (location accuracy better than that)
Ultraviolet Transient Camera Array

Build by	MIT (USA)
Instrument type	4 UV CCD Detectors with 35 mm f/2 optics
Energy range	5 to 7 eV
Timing resolution	~ 4 s
Spectral resolution	n/a (Broadband imaging photometer)
Effective area	2.5 cm**2 (each of 4 units)
Sensitivity (10 sigma)	1 x 10**-9 erg/cm**2/s
FOV	~ 1.7 sr (total for 4 units)
Angular resolution (1 sigma)	+/- 3 arcsec

The spacecraft hardware and software is being developed by Aeroastro (USA).

Downlink frequencies: 137.963 (300 bps) & 2272 MHz


 HETE 2

High-Energy Transient Experiment

General

Designation
Launch date	initially planned in Oct 1999
Country of origin	United States
Mission	Scientific
Perigee/Apogee
Inclination
Period
Launch vehicle	Pegasus XL

This satellite was funded to replace HETE which was lost right after launch.

The prime objective of HETE is to carry out the first multiwavelength study of gamma-ray bursts with UV, X-ray, and gamma-ray instruments mounted on a single, compact spacecraft. A unique feature of the HETE mission is its capability to localize GRBs with ~10 arc second accuracy, in near real time aboard the spacecraft, and to transmit these positions directly to a network of receivers at existing ground-based observatories, enabling rapid, sensitive follow-up studies in the radio, IR, and optical bands.

HETE was carried inside the Dual Payload Attach Fixture on which SAC B was mounted, so it was trapped and was unable to deploy its solar panels.

External resources

http://nis-www.lanl.gov/nis-projects/hete/

Technical data

Omnidirectional Gamma-Ray Spectrometer (Fregate)

Build by	CESR (France)
Instrument type	NaI(Tl); cleaved
Energy range	6 keV to > 1 MeV
Timing resolution	4 ms
Spectral resolution	~40% @ 6 keV; ~7% @ 662 keV
Effective area	120 cm^2
Sensitivity (10 sigma)	3 x 10^-8 erg/cm**2/s for 8-1000 keV
FOV	~ 2 pi sr
Angular resolution	~ 1 sr
Wide Field X-ray Monitor

Build by	RIKEN (Japan) and Los Alamos
Instrument type	Coded Mask with Position Sensitive Proportional Counter
Energy range	2 to 25 keV
Timing resolution	1 ms
Spectral resolution	~15% @ 6 keV
Effective area	200 cm^2 (each of 2 units)
Sensitivity (10 sigma)	8 x 10^-9 erg/cm^2/s for 2-10 keV
FOV	~ 2 sr (combined)
Angular resolution (1 sigma)	+-6 arcmin
Soft X-ray Camera

Build by	MIT CSR
Instrument type	4 CCD20 Detectors, 2 optical CCD22
Energy range	500 eV to 14 keV
Timing resolution	1 s
Spectral resolution	46 eV @ 525 eV, 129 eV @ 5.9 keV
Effective area	6.1x6.1 cm^2 (each of 2 units)
FOV	~0.91 sr
Dimension	10 cm x 10 cm x 17.5 cm

The spacecraft hardware and software is being developed by Aeroastro (USA).

Downlink frequencies: 137.963 (300 bps) & 2272 MHz


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 Hipparcos

HIgh Precision PARallax COllecting Satellite, named as a Greek astronomer of the 2nd century before JC: Hipparkhos

General

Designation	20169 / 89062B
Launch date	8 Aug 1989
Country of origin	Europe
Mission	Scientific: astronomy
Perigee/Apogee	498/35889 km
Inclination	6.5°
Period	638.7 min
Launch vehicle	Ariane V33

Was intended on geostationary 12°W slot but its Mage motor didn't work. The data it provided from Nov 1989 on was recalculated to match its orbital position.

Hipparcos observed 118274 stars with a precision between 0.0008 and 0.002 arcsec depending on the objects magnitude. 10000 double stars were observed including 7000 which were discovered by the satellite. It also discovered numerous variable stars.

End of life

Out of service	15 Aug 1993
Cause	Stopped transmitting in June 1993
External resources

http://astro.estec.esa.nl/SA-general/Projects/Hipparcos/hipparcos.html

Technical data

Specifications

Prime contractor	Matra Marconi Space
Mass at launch	1140 kg
Payload mass	200 kg
Diameter	2.5 m
Height	3 m
Stabilization	3-axis
DC power	380 W
Design lifetime	2.5 years
Schmidt telescope & photon detector

Telescope aperture	0.29 m
Field of view	0.9 x 0.9°
Frequency band	visible: 375-750 nm
Telemetry/data	S-band


 Program: Hispasat

Spanish telecommunication program operated by Hispasat


Program: Hispasat

Hispasat 1A

Hispasat 1B

Hispasat 1C


Hispasat's specifications

Prime contractor	Matra Marconi Space
Platform	Eurostar 2000
Mass at launch	2120 kg
Mass in orbit	1325 kg
Payload mass	280 kg
Dimension	2.21 x 1.7 x 1.9 m
Solar array	22.02 m
Stabilization	3-axis
DC power	EOL: 3790 W
Design lifetime	10 years
Telemetry	Ku-band (backup: S-band)


Hispasat's direct TV mission

Main transponders	3
Backup transponders	1
Power	110 W (TWTA)
Bandwidth	27 MHz
EIRP max	58 dBW
Polarization	circular L
Uplink	12.1-12.5 GHz
Downlink	17.3-17.7 GHz


Hispasat's telecommunication to Europe mission

Main transponders	8
Backup transponders	4
Power	50 W (TWTA)
Bandwidth	4 x 36 MHz 2 x 46 MHz 2 x 72 MHz
EIRP max	51 dBW
Polarization	linear
Uplink	14.0-14.25 GHz & 14.25-14.5 GHz
Downlink	12.5-12.75 GHz & 11.45-11.7 GHz


Hispasat's telecommunication to America mission (Ku-band)

Main transponders	2
Backup transponders	1
Power	110 W (TWTA)
Bandwidth	36 MHz
Coverage and EIRP max	South and Central America: 53 dBW
Polarization	linear V


Hispasat's X-band

Main transponders	1
Backup transponders	1
Power	40 W (TWTA)
Bandwidth	40 MHz
Coverage
EIRP max	42 dBW
Polarization


Hispasat's transponder frequency chart (GHz)

Transponder	Uplink	Downlink	Bandwidth	Main	Reserve	Coverage
16	14.317 V	11.517 H	72	1B	1A	switchable Europe / America
7	14.317 H	11.517 V	72	1A	1B	Europe
17	14.397 V	11.597 H	72	1A	1B	Europe
8	14.397 H	11.597 V	72	1B	1A	Europe
18	14.464 V	11.664 H	46	1B		switchable Europe / America
9	14.468 H	11.668 V	54	1A		Europe
15	14.249 V	12.015 V	36	1B	1A	America
6	14.249 H	12.078 V	36	1A	1B	America
23	17.32748 RHCP	12.14944 LHCP	27	?		DBS
27	17.40420 RHCP	12.22616 LHCP	27	?		DBS
31	17.48092 RHCP	12.30288 LHCP	27	?		DBS
35	17.55764 RHCP	12.37960 LHCP	27	?		DBS
39	17.63436 RHCP	12.45632 LHCP	27	?		DBS
10	14.035 V	12.540 H	54	1A		Europe
1	14.039 H	12.544 V	46	1B		Europe
11	14.086 V	12.591 H	36	1B	1A	Europe
2	14.086 H	12.591 V	36	1A	1B	Europe
12	14.126 V	12.631 H	36	1B		Europe
3	14.126 H	12.631 V	36	1A		Europe
13	14.166 V	12.671 H	36	1A	1B	Europe
4	14.166 H	12.671 V	36	1B	1A	Europe
14	14.206 V	12.711 H	36	1A		Europe
5	14.206 H	12.711 V	36	1B		Europe


Hispasat's EIRP (Direct TV)


Hispasat's EIRP (Telecommunication to Europe)


Hispasat's EIRP (Telecommunication to America)


 Hispasat 1A

General

Designation	22116 / 92060A
Launch date	10 Sep 1992
Country of origin	Spain
Mission	Telecommunications
Geostationary orbit	30°W
Launch vehicle	Ariane V53

The X-band payload failed on 18 Dec 1997

Technical data

Specifications

Direct TV

Telecommunication to Europe

Telecommunication to America

X-band

Transponder frequency chart

EIRP coverage (dBW)

Direct TV

Telecommunication to Europe

Telecommunication to America

Beacon: 12.7475 GHz vertical (backup in S-band)


 Hispasat 1B

General

Designation	22723 / 93048A
Launch date	22 Jul 1993
Country of origin	Spain
Mission	Telecommunications
Geostationary orbit	30°W
Launch vehicle	Ariane V58
Technical data

Specifications

Direct TV

Telecommunication to Europe

Telecommunication to America

X-band

Transponder frequency chart

EIRP coverage (dBW)

Direct TV

Telecommunication to Europe

Telecommunication to America

Beacon: 12.749 GHz vertical (backup in S-band)


 Hispasat 1C

General

Designation
Launch date	late-1999
Country of origin	Spain
Mission	Telecommunications
Geostationary orbit	30°W
Launch vehicle	Atlas

Satellite worth approx. $85 million

Technical data

Specifications

Iberia

Europe

America

Specifications

Prime contractor	Aerospatiale
Platform	Spacebus-3000
Mass at launch	2800 kg
Mass in orbit
Dimension
Solar array
Stabilization	3-axis
DC power	EOL: 6000 W (+ NiH2 batteries)
Design lifetime	15 years

Command: S-band (before GEO and emergency) & Ku-band (normal status)

Ku-band to America

Main transponders	up to 12
Backup transponders
Power	120 W
Bandwidth	36 MHz
Coverage	America
EIRP max	47 dBW
G/T max	America: +1 dB/K Europe: +3 dB/K Iberia: +8 dB/K
Polarization
Ku-band to Europe

Main transponders	up to 17
Backup transponders
Power	120 W
Bandwidth	36 MHz
Coverage	full Europe
EIRP max	47 dBW
G/T max	America: +1 dB/K Europe: +3 dB/K Iberia: +8 dB/K
Polarization
Ku-band to Iberia

Main transponders	up to 17
Backup transponders
Power	120 W
Bandwidth	36 MHz
Coverage	Iberia peninsule + Balearic, Canary, Madeira and Azores islands
EIRP max	56 dBW
G/T max	America: +1 dB/K Europe: +3 dB/K Iberia: +8 dB/K
Polarization

total simultaneous transponder in use: 22


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Hispasat 1C's Iberia EIRP


Hispasat 1C's Europe EIRP


Hispasat 1C's America EIRP


 HST

Hubble Space Telescope, named as the American astrophysician Edwin Powell Hubble

General

Designation	20580 / 90037B
Launch date	24 Apr 1990
Country of origin	United States
Operator	NASA
Mission	Scientific: astronomy
Perigee/Apogee	589/598 km
Inclination	28.5°
Period	96 min
Launch vehicle	STS 31R

The Hubble Space Telescope (HST) was the first of the Great Observatories launched, and is exploring our universe in the visible, ultraviolet, near-infrared regions of our electromagnetic spectrum. It was designed by Lynan Spitzer and proposed to NASA in the early 60ies. It is maintained by the Shuttle: first servicing mission: STS 61.

Next missions planned: Feb 1997 (STS 82) and May 2000 (STS 106)

In Feb 1999 it is announced that 3 of the 6 gyroscopes failed and that an advanced service mission is needed to replace them. A service mission is expected in 1999.

Cost: $3 billion

External resources

http://www.stsci.edu/top.html

Technical data

Specifications

Prime contractor	Lockheed (spacecraft) Perkin Elmer (mirror & telescope)
Mass at launch	11250 kg
Diameter	4.25 m
Height	13.1 m
Solar array	12 x 2.83 m
Stabilization	3-axis
DC power	BOL: 5500 W
Design lifetime	15 years

Data acquisition via TDRS

Telemetry: 2287.5 MHz (500 bps, 4 kbps, 32 kbps)

Command: 2106 MHz (1/0.125 kbps)

Data: 2255.5 MHz (1024 kbps)

Payload

Primary mirror diameter	2.4 m
Primary mirror mass	800 kg
Frequency bands	UV, visible and near IR
Resolution	0.1 arcsecs
Pointing stability	0.007 arcsecs

Wide-Field Planetary Camera, Faint Object Camera (ESA), Faint Object Spectrograph, High Resolution Spectrograph, High Speed Photometer

The WFPC 2 replaced the original camera on 1st servicing mission and Costar replaced the High Speed Photometer

On the second servicing mission, the Space Telescope Imaging Spectrograph replaced both GHRS (the Goddard High Res Spectrograph) and FOS (the Faint Object Spectrograph). NICMOS, the Near Infrared Camera and Multi-Object Spectrometer was added to overs the 0.8 to 2.5 micron spectral range.


 Program: ICO

Intermediate Circular Orbit, also known as Inmarsat P

Global mobile telephone system operated by ICO Global Communications, expected to begin service in 2000.

The 12 satellites are worth $1.3 billion. The launch cost is estimated at $925 million (for 12 satellites)  Cost per satellite: $275 million. The global cost of the program is estimated at $4.6 billion (including $625 million for the ground segment and $1.5 billion for exploitation). Hughes invested $93.8 million to become a strategic partner in ICO (4% of the company).

TRW cancelled its Odyssey MEO satellite system and bought 7% of ICO ($150 million), becoming the largest shareholder in late 1997.

The system has insurance for $200 million if more than 2 satellites were lost at launch or during the first 60 months in-orbit.

In Aug 1999 the company is reported in serious trouble to make its interest payments. The company is reported to be short of $1.0 to $1.7 billion!

External resources

http://www.ico.com/

Technical data

planned:

3 launches on Atlas 2AS

4 launches on Proton

5 launches on Delta 3

1 launches on on Zenit/Sea Launch

Overview

Orbit type	MEO
Orbit range	10335 km, circular
Nb of satellites	10 + 2 backup
Nb of planes	2
Inclination	45°
Nb beams per satellite	121
Coverage	12900 km²
Modulation	combined FDMA/TDMA
Mobile frequencies	1980 - 2010 MHz
Satellite mass	2300 kg
Coverage	Worldwide
Operational date	2000 (planned)

6 satellites are needed to start operating

Specifications

Prime contractor	Hughes
Platform	HS-601MEO
Mass at launch	2750 kg
Mass in orbit
Dimension
Solar array
Stabilization
DC power	EOL: 8700 W
Design lifetime	12 years

Will feature C- and S-band payloads. Links between terminals and satellites: 1.6/1.5 GHz, 1.6/2.4 GHz. Links between gateways and satellites: 5 and 7 GHz

Designed to work with terrestrial GSM


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 Program: IDSCP

Initial Defence Satellite Communication Program

American military program: 26 satellites of 45 kg on a 33000 km orbit launched between 1966 and 1968 to built the IDSCS network.

External resources

http://www.fas.org/spp/military/program/com/dscs_1.htm


 Ikonos 1

Also called CRSS 1

General

Designation	n/a
Launch date	27 Apr 1999
Country of origin	United States
Mission	Remote sensing
Perigee/Apogee	640 km (sun-synchronous)
Inclination	98°
Period
Launch vehicle	Athena #5
End of life

Out of service	27 Apr 1999
Cause	launch failure

Was to be the first 1 meter commercial remote sensing satellite  Owned and operated by Eosat Its launched was delayed 1 year because of difficulties to setup the onboard software to prevent pictures of US allies to be taken and because of gyroscopes problems.

The satellite was insured for $157 million.

Technical data

Specifications

Prime contractor	Lockheed Martin
Platform	LM-900
Mass at launch	817 kg
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime	7 years

Equipped with a Kodak digital camera. This payload will enable Ikonos 1 to collect 1-meter resolution panchromatic (gray-scale) resolution and 4-meter resolution, four-band multispectral (red, green, blue, near infrared) imagery of the Earth.

The camera is comprised of a Kodak-designed and -manufactured focal plane array and a lightweight telescope using a state-of-the-art mirror fabricated with Kodaks advanced ion figuring technology. To speed the downloading of data to Space Imaging EOSATs ground receiving stations, the original 11-bit data will be compressed using Kodaks proprietary bandwidth compression technology.

X-band downlink at 320 Mbps. 64 Gb onboard storage


 Ikonos 2

Also called CRSS 2

General

Designation
Launch date	mid 1998
Country of origin	United States
Mission	Remote sensing
Perigee/Apogee
Inclination
Period
Launch vehicle
Launch site

Will be a duplicate of Ikonos 1


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 Image

Imager for Magnetopause-to-Aurora Global Exploration

General

Designation
Launch date	initially planned in 2000
Country of origin	United States
Mission	Scientific:
Perigee/Apogee
Inclination	polar orbit
Period
Launch vehicle	Delta
Launch site	Vandenberg

The Image mission will use three dimensional imaging techniques to study the global response of the Earth's magnetosphere to variations in the magnetic activity of the Sun. It will be the first satellite that will take pictures of the magnetosphere as it changes shape.

External resources

http://image.gsfc.nasa.gov/

Technical data

Specifications

Prime contractor	NASA
Platform
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime	2 years

Will have the Far Ultraviolet Spectrographic Image instrument (Fuv-Si)


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 Program: IMEWS

Integrated Multipurpose Early Warning Satellite

American military program designed to warn on rocket launch or warhead fall. Equipped with IR detectors.


 IMEX

Build and operated by The University of Colorado, it will prevent communications satellites from being disabled by radiation.


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 Injun 3

General

Designation	00504 / 62067B
Launch date	13 Dec 1962
Country of origin	United States
Mission	Scientific:
Perigee/Apogee	240/2406 km
Inclination	70.3°
Period	112.1 min
Launch vehicle	Thor Agena D
Launch site	Vandenberg
End of life

Decay	25 Aug 1968
External resources

http://uss-enterprise.bu.edu/BUSPACE/INJUN3/injun3.html


 Program: Inmarsat

INternational MARitime SATellite

Inmarsat was created by the International Maritim Organization (dependent of the United Nations) on 16 Jul 1979. It is based in London and started working on 1 Feb 1982. Inmarsat must provide links between maritime mobiles and ground networks using geostationary satellites. The services are telephone, telex, fax and an access to the emergency system Sarsat/Cospas.

Inmarsat's structure is close to Intelsat's one. It isn't dominated by the United States which enabled USSR to join in.

The organization gathered 48 members in 1986 and 64 in 1991. The first operational system opened in 1985. Transponders were leased on 6 satellites: Marisat, Marecs and Intelsat. With the success encountered Inmarsat decided in 1983 to operate its own satellites.

Over 20 ground stations have been installed and in 1992 over 15000 terminals had been sold. The states that mostly participate in the funding are the United States, Norway, the UK and Japan.

Inmarsat is also working on aeronautical links and a project of personnal communication medium. Inmarsat might develop low orbit satellites on polar orbits to cover Northern and Southern regions.

Once the 3rd generation is fully deployed the 2nd generation satellites should be moved by 40° off their current position to allow frequency reuse. This would let Inmarsat offer new, long term services. Slots at 110°E and 98°W should be used.

Inmarsat should be privatized in March 1999. An intergovernmental body called International Mobile Satellite Organization (IMSO) should be created to manage the public service obligations (mainly the Global Maritime Distress and Safety System (GMDSS)). A private entity should control the rest of the activity.


Program: Inmarsat

Inmarsat 2F1

Inmarsat 2F2

Inmarsat 2F3

Inmarsat 2F4

Inmarsat 3F1

Inmarsat 3F2

Inmarsat 3F3

Inmarsat 3F4

Inmarsat 3F5


Inmarsat 2's specifications

Prime contractor	British Aerospace (now MMS)
Platform	Eurostar 1000
Mass at launch	1310 kg with Ariane 1385 kg with Delta
Mass in orbit	BOL: 824 kg
Payload mass	132 kg
Dimension	1.6 x 1.5 x 2.6 m
Solar array	15.23 m span
Stabilization	3-axis
DC power	EOL: equinox: 1156 W, solstice: 1040 W
Payload power	660 W
Design lifetime	10 years
Capacity	250 duplex voice channels

The Inmarsat system has downlinks in L-band that are uplinked in C-band (6 GHz) and uplinks in L-band are downlinked in C-band (4 GHz).

The Inmarsat M standard defines the use on a 10 kg case which cover is the antenna. The uplink frequencies are 1.626-1.660 GHz and 1.525-1.559 GHz for download. Data can be transmitted at 2400 bauds.


Inmarsat 2's L-band (1.6/1.5 GHz)

Main transponders	4
Backup transponders	2
Power	45 W (TWTA)
Bandwidth	total: 18 MHz  carriers: 5 and 22.5 KHz
Coverage	global
EIRP max	39 dBW
G/T	12.5 dB/K
Polarization

This capacity is used for communications with the mobiles.


Inmarsat 2's C-band (6.4/3.6 GHz)

Main transponders	1
Backup transponders	1
Power	10 W (TWTA)
Bandwidth	18 MHz
Coverage	global
EIRP max	24 dBW
G/T	14.0 dB/K
Polarization

This capacity is used for communications with earth stations.


Inmarsat 3's specifications

Prime contractor	Lockheed Martin (formerly GE Astro Space)
Platform	GE 4000
Mass at launch	1850-2000 kg
Dry mass	895 kg
Mass in orbit	1150 kg
Payload mass	208 kg
Dimension	2.1 x 1.8 x 1.7 m
Solar array	16.7 m
Stabilization	3-axis
DC power	2800 W
Payload power	sunlight: 2138 W, eclipse: 1725 W
Design lifetime	13 years

Equipped with Matra Marconi Space communications payload and a Star 37 solid apogee motor


Inmarsat 3's L-band (1.6/1.5 GHz)

Main transponders
Backup transponders
Power	20 W
Bandwidth	forward: 29 MHz, return: 39 MHz
Coverage & EIRP max	Navigation beam: global 5 spots: 47.4 dBW Global: 40.5 dBW
Polarization


Inmarsat 3's C-band (6.4/3.6 GHz)

Main transponders
Backup transponders
Power	15 W
Bandwidth	39 MHz
Coverage	Global
EIRP max
Polarization


 Inmarsat 2F1

Also called IOR

General

Designation	20918 / 90093A
Launch date	30 Oct 1990
Country of origin	International
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Delta 2 #200
Location

Begin	End	Position
L: 30 Oct 1991	> Jan 1994	63°E
Jun 1994	Apr 1996	64.5°E, inclined
Nov 1996		178°E, inclined

Tel: 873, Telex: 583

Technical data

Specifications

L-band

C-band


 Inmarsat 2F2

Also called AOR-E

General

Designation	21149 / 91018A
Launch date	8 Mar 1991
Country of origin	International
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Delta 2 #203

Tel: 871, Telex: 581

Location

Begin	End	Position
L: 8 Mar 1991	Sep 1996	15.5°W, inclined
Jan 1997	May 1999	55.5°W, inclined
Jul 1999		98°W, inclined
Technical data

Specifications

L-band

C-band


 Inmarsat 2F3

Also called POR

General

Designation	21814 / 91084B
Launch date	16 Dec 1991
Country of origin	International
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V48

Tel: 872, Telex: 582

Location

Begin	End	Position
L: 16 Dec 1991	Mar 1997	178°E, inclined
Mar 1997		65°E, inclined
Technical data

Specifications

L-band

C-band


 Inmarsat 2F4

Also called AOR-W

General

Designation	21940 / 92021B
Launch date	15 Apr 1992
Country of origin	International
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V50
Location

Begin	End	Position
L: 15 Apr 1992	end of tests	32°W
end of tests	Jul 1997	54°W, inclined
Oct 1997	May 1999	17°W, inclined
Jul 1999		109°E, inclined

Tel: 874, Telex: 584

Technical data

Specifications

L-band

C-band


 Inmarsat 3F1

General

Designation	23839 / 96020A
Launch date	3 Apr 1996
Country of origin	International
Mission	Telecommunications
Geostationary orbit	64°E
Launch vehicle	Atlas Centaur #99

Tested at 27°E

Technical data

Specifications

L-band

C-band


 Inmarsat 3F2

General

Designation	24307 / 96053A
Launch date	6 Sep 1996
Country of origin	International
Mission	Telecommunications
Geostationary orbit	16°W
Launch vehicle	Proton #243

Was said to cost $80 million

Technical data

Specifications

L-band

C-band


 Inmarsat 3F3

General

Designation	24674 / 96070A
Launch date	18 Dec 1996
Country of origin	International
Mission	Telecommunications
Geostationary orbit	178°W
Launch vehicle	Atlas 2A #104

Went operational on 25 Jan 1997

Technical data

Specifications

L-band

C-band


 Inmarsat 3F4

General

Designation	24819 / 97027A
Launch date	3 Jun 1997
Country of origin	International
Mission	Telecommunications
Geostationary orbit	54°W
Launch vehicle	Ariane V97

Entered service on 26 July 1997

Technical data

L-band

C-band

Specifications

Prime contractor	Lockheed Martin
Platform
Mass at launch	2000 kg
Mass in orbit	1149 kg
Dry mass	895 kg
Dimension	3.2 x 2.3 x 2.1 m
Solar array	20.7 m span
Stabilization	3-axis
DC power	BOL: 3726 W
Design lifetime	13 years


 Inmarsat 3F5

General

Designation	25153 / 98006B
Launch date	4 Feb 1998
Country of origin	International
Mission	Telecommunications
Geostationary orbit	24.5°E
Launch vehicle	Ariane V105
Technical data

Specifications

L-band

C-band

Has onboard the first payload of the GNSS 1 system, to enhance the GPS navigation system.


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 Program: Insat

Indian National Satellite

Indian telecommunication and meteorology program operated by ISRO  The commercial arm of the system is Antrix

Meteorology mission: image acquisition, distribution of image data and other met info, collection and relay of weather data from data collection platforms (DCPs). Data on upper atmosphere winds and sea surface temperatures, flood and storm early warning, etc.

5 satellites of the 3rd series are planned, starting in 1999.  The last 3 satellites of the series should be launched by GSLV.

Insat has applied for 29 new GEO slots in 1997: from 51.5°E to 113.5°E and 13°W and 108°W!


Program: Insat

Insat 1A

Insat 1B

Insat 1C

Insat 1D

Insat 2A

Insat 2B

Insat 2C

Insat 2D

Insat 2E

Insat 2R

Insat 3A

Insat 3B

Insat 3C


Insat 1's specifications

Prime contractor	Ford Aerospace
Platform	INSAT
Mass at launch	1152 kg
Mass in orbit	650 kg
Dimension	2.18 x 1.42 x 1.55 m
Solar array	asymmetric panel, 11.5 m²
Stabilization	3-axis
DC power	1185 W
Design lifetime	7 years


Insat 1's S-band (2.6/5.9 GHz)

Main transponders	2
Backup transponders	1
Power	50 W (TWTA)
Bandwidth
Coverage	India
EIRP max	42 dBW
Polarization


Insat 1's C-band

Main transponders	12
Backup transponders
Power	4.5 W (TWTA)
Bandwidth	36 MHz
Coverage	India
EIRP max	32 dBW
Polarization


Insat 1's payload

VHRR (Very High Resolution Radiometer)

Wavebands	0.55-0.75 µm (visible) 10.5-12.5 µm (IR)
Resolution	visible: 2.75 km IR: 11 km
Image repeat frequency	30 minutes


Insat 2's specifications

Prime contractor	ISRO/ISAC
Platform	INSAT2
Mass at launch	1906 kg
Mass in orbit	1162 kg
Dimension	1.93 x 1.64 x 1.7 m
Solar array	asymmetric pannel
Stabilization	3-axis
DC power	1400 W
Design lifetime	7 years

Also equipped with 2 single channels for data and search & rescue(Sarsat): 402.75 & 406 MHz


Insat 2's S-band (2.6/5.9 GHz)

Main transponders	2
Backup transponders	1
Power	50 W (TWTA)
Bandwidth	36 MHz
Coverage	India
EIRP max	42 dBW
Polarization	LHCP


Insat 2's C-band

Main transponders	18
Backup transponders
Power	4.5 W
Bandwidth	36 MHz
Coverage	India
EIRP max	32 dBW
Polarization	H/V linear


Insat 2's payload

VHRR (Very High Resolution Radiometer)

Wave bands	0.55-0.75 µm (visible) 10.5-12.5 µm (IR)
Resolution	visible: 2 km IR: 8 km
Image repeat frequency	30 minutes


 Insat 1A

General

Designation	13129 / 82031A
Launch date	10 Apr 1982
Country of origin	India
Mission	Telecommunications and meteorology
Geostationary orbit	74°E
Launch vehicle	Thor Delta #161

Insurance paid $64 million for the failure

End of life

Out of service	4 Sep 1982
Cause	Solar panel didn't open out
Technical data

Specifications

S-band

C-band

Payload


 Insat 1B

General

Designation	14318 / 83089B
Launch date	31 Aug 1983
Country of origin	India
Mission	Telecommunications and meteorology
Geostationary orbit	74°E
Launch vehicle	STS 08

The deployment of one antenna was difficult and was not succeeded until mid Sep 1983. Went operational in Nov 1983. Became spare in Jul 1990.

End of life

Out of service	Aug 1993
Technical data

Specifications

S-band

C-band

Payload


 Insat 1C

General

Designation	19330 / 88063A
Launch date	21 Jul 1988
Country of origin	India
Mission	Telecommunications and meteorology
Geostationary orbit	93.5°E
Launch vehicle	Ariane V24

It had difficulties to deloy its solar array. After a power failure, only half its payload was functional.

Insurance paid $72 million for the failure

End of life

Out of service	22 Nov 1989
Cause	Earth lock lost
Technical data

Specifications

S-band

C-band

Payload


 Insat 1D

General

Designation	20643 / 90051A
Launch date	12 Jun 1990
Country of origin	India
Mission	Telecommunications and meteorology
Geostationary orbit	see below
Launch vehicle	Thor Delta #196

Was damaged when a crane hook (34 kg) fell on it at the launch site. Damages were worth $10 million reparation. While being repared it suffered further damages (October 1989 California earthquake).

Location

Begin	End	Position
L: 12 Jun 1990	Jun 1999	83°E
		drifting West
Technical data

C-band EIRP coverage (dBW)

Specifications

S-band

C-band

Payload


Insat 1D's EIRP (C-band)


 Insat 2A

General

Designation	22027 / 92041A
Launch date	9 Jul 1992
Country of origin	India
Mission	Telecommunications and meteorology
Geostationary orbit	74°E, inclined
Launch vehicle	Ariane V51
Technical data

C-band EIRP coverage (dBW)

Specifications

S-band

C-band

Payload


Insat 2A & 2B's EIRP (C-band)


 Insat 2B

General

Designation	22724 / 93048B
Launch date	22 Jul 1993
Country of origin	India
Mission	Telecommunications and meteorology
Geostationary orbit	93.5°E
Launch vehicle	Ariane V58
Technical data

C-band EIRP coverage (dBW)

Specifications

S-band

C-band

Payload


 Insat 2C

General

Designation	23731 / 95067B
Launch date	6 Dec 1995
Country of origin	India
Mission	Telecommunications
Geostationary orbit	93.5°E
Launch vehicle	Ariane V81

Unlike other satellites of the program, Insat 2C is totally devoted to telecommunications and doesn't have any meteorology payload.

Tested at 92.5°E

Technical data

EIRP maps (dBW)

C-band, standard

C-band, extended

Specifications

Prime contractor	ISRO/ISAC
Platform	INSAT2
Mass at launch	2020 kg
Mass in orbit	980 kg ?
Dimension	1.93 x 1.64 x 1.7 m
Solar array	asymmetric pannel
Stabilization	3-axis
DC power	BOL: 1600 W
Design lifetime	10 years

The internal LAM (Liquid Apogee Motor) was built by ISRO with its Indian industrial partners.

The satellite will have a meteorology payload made of a VHRR with an additional water vapour channel and a 1-km resolution, 3-visible-channel CCD camera.

S-band (2.6/5.9 GHz)

Main transponders	3
Backup transponders
Power	50 W (TWTA)
Bandwidth	36 MHz
Coverage	India
EIRP max	42 dBW
Polarization	LHCP

Aimed at mobile communications

C-band

Main transponders	17 + 6 (extended C-band)
Backup transponders
Power	4.5 W
Bandwidth	36 MHz
Coverage	between the Middle East and southeast Asia
EIRP max	standard: 32 dBW 2 extended transponders: 34 dBW
Polarization	H/V linear

Aimed at TV broadcasting

Ku-band

Main transponders	3
Backup transponders
Power
Bandwidth
Coverage
EIRP max
Polarization

Aimed at business communications among India's frou major cities (Delhi, Bombay, Calcutta and Madras)


Insat 2C's EIRP (C-band, standard)


Insat 2C's EIRP (C-band, extended)


 Insat 2D

General

Designation	24820 / 97027B
Launch date	3 Jun 1997
Country of origin	India
Mission	Telecommunications
Geostationary orbit	74°E
Launch vehicle	Ariane V97

Cost: $50 million to build and $64 million to launch, some sources claim total $148 million

Went operational in July 1997. Encountered a few problems before dying in Oct 1997. Insurances are to pay approx $65 million for the loss.

In September, ISRO hired 6 transponders to increase their capacity for a year until they launch two future satellites.

End of life

Out of service	5 Oct 1997
Cause	After a power problem (short-circuit on 1 Oct 1997), the attitude was lost and could not be regained
Technical data

Specifications

Prime contractor	ISRO/ISAC
Platform	INSAT2
Mass at launch	2079 kg
Mass in orbit
Dimension	1.7 x 1.93 x 2.99 m (14.7 m deployed)
Solar array	asymmetric pannel
Stabilization	3-axis
DC power	BOL: 1910 W
Design lifetime	10 years
S-band (2.6/5.9 GHz)

Main transponders	1
Backup transponders
Power
Bandwidth
Coverage	India
EIRP max
Polarization
C-band

Main transponders	18
Backup transponders
Power
Bandwidth
Coverage	between the Middle East and southeast Asia
EIRP max
Polarization
Ku-band

Main transponders	3
Backup transponders
Power
Bandwidth
Coverage
EIRP max
Polarization


 Insat 2E

General

Designation	25666 / 99016A
Launch date	2 Apr 1999
Country of origin	India
Mission	Telecommunications and meteorology
Geostationary orbit	83°E
Launch vehicle	Ariane V117

Wen operational on 18 May 1999. Intelsat payed India's Department of Space $100 million over 10 years, for the use of 11 transponders.

The satellite is said to have cost Rs. 220 crores to build ($53 million). Launch costed $69 million and insurance $12 million

Technical data

EIRP map coverage (dBW)

Specifications

Prime contractor	ISRO/ISAC
Platform	INSAT2
Mass at launch	2550 kg
Mass in orbit	1526 kg
Dry mass	1148 kg
Dimension	1.93 x 1.77 x 2.3 m
Solar array	24.7 m
Stabilization	3-axis
DC power	2143 W (60 Ah Nickel-Hydrogen batteries)
Design lifetime	12 years
VHRR (Very High Resolution Radiometer)

Wave bands	0.55-0.75 µm (visible) 10.5-12.5 µm (IR) + a water vapour band
Resolution	visible: 2 km IR: 8 km
Image repeat frequency	30 minutes

The satellite also carries a Charged Coupled Device (CCD) camera with one kilometre resolution (compared to VHRR's best of 2 km). The CCD camera's higher resolution would allow better tracking of cloud movements and more accurate estimation of winds.

C-band

Main transponders	15 + 2
Backup transponders
Power	10 x 32 W 7 x 60 W
Bandwidth	15 x 36 MHz 2 x 72 MHz
Coverage & EIRP max	Quasi global Wide beam: 36 dBW Zone: 36 dBW
G/T max
Polarization	linear (uplink: H, downlink: V)
Frequencies	uplink: 5.850 - 6.650 GHz downlink: 3.400 - 4.200 GHz

Beacons: 4.190976 GHz (primary) and 4.197504 GHz (maneuver)

Transponder frequency chart (GHz)

Horizontal  Uplink	Transponder	Vertical  Downlink	Intelsat use	Beams (uplink/dowlink)
6.470	1	3.445	yes	wide/zone
6.510	2	3.485	yes	wide/zone
6.550	3	3.525	yes	wide/zone
6.590	4	3.565	yes	wide/zone
6.630	5	3.605	yes	wide/zone
5.890	6 (72 MHz)	3.665	yes	wide/wide
5.950	7	3.725		wide/zone
5.990	8	3.765		wide/wide
6.030	9	3.805		wide/zone
6.070	10	3.845		wide/wide
6.110	11	3.885		wide/zone
6.150	12	3.925		wide/wide
6.190	13	3.965		wide/zone
6.230	14	4.005	yes	wide/wide
6.270	15	4.045	yes	wide/wide
6.310	16	4.085		wide/zone
6.370	17 (72 MHz)	4.145	yes	wide/wide


Insat 2E's EIRP (C-band)


 Insat 2R

Also called Insat 2DT

General

Old name	Arabsat 1C
Country	India
Mission	Telecommunications
Geostationary orbit	55°E

Bought in Nov 1997 for $40 million

Technical data

Specifications

S-band

C-band


 Insat 3A

General

Designation
Launch date	initially planned mid-1999
Country of origin	India
Mission	Telecommunications and meteorology
Geostationary orbit	38°E
Launch vehicle
Launch site
Technical data

Specifications

Prime contractor
Platform	INSAT 3
Mass at launch	2700kg
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime

Has a meteorology payload.

C-band

Main transponders	12 + 6 (extended)
Backup transponders
Power
Bandwidth
Coverage & EIRP max	Quasi global Wide beam: 36 dBW Zone: 36 dBW
G/T max
Polarization

Also has Ku-band transponders


 Insat 3B

General

Designation
Launch date	2nd quarter of 1999
Country of origin	India
Mission	Telecommunications and meteorology
Geostationary orbit
Launch vehicle	Ariane

Launch cost: $83 million

Technical data

Specifications

Prime contractor
Platform	INSAT 3
Mass at launch	~2070kg
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime
C-band

Main transponders	17
Backup transponders
Power
Bandwidth
Coverage & EIRP max
G/T max
Polarization

Extended C-band

Ku-band: 6 transponders.

S-band: 3 transponders.


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 Insat 3C

General

Designation
Launch date
Country of origin	India
Mission	Telecommunications
Geostationary orbit
Launch vehicle	GSLV
Launch site

Insat 3D will ba primarily a meteorological satellite

Insat 3E will weigh 3500 kg. It would carry an upgraded bus capable of carrying 20 Ku band channels.

Technical data

Specifications

Prime contractor
Platform	INSAT 3
Mass at launch	~2070kg
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime

No weather payload

C-band (normal and extended)

Main transponders
Backup transponders
Power
Bandwidth
Coverage & EIRP max
G/T max
Polarization

Ku-band: 6 transponders.

S-band: 3 transponders.


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 Intasat

General

Designation	07531 / 74089C
Launch date	15 Nov 1974
Country of origin	Spain
Mission	Scientific: ionosphere study
Perigee/Apogee	1441/1455 km
Inclination	101.9°
Period	114.8 min
Launch vehicle	Thor Delta #104
Mass at launch	24.5 kg

Studies the ionosphere's density and its movement throughout the year.


 Integral

European satellite to be launched in Apr 2001 by Proton. The launch is provided against 25% of the observation time to Russian scientists.

Integral is a 4-ton gamma-astronomy satellite. It will be placed on an elliptical orbit.

External resources

http://astro.estec.esa.nl/SA-general/Projects/Integral/integral.html

Technical data

Instruments

Spectrometer Spi

Imager Ibis

X-Ray Monitor Jem-X

Optical Monitoring Camera Omc

Integral Science Data Centre Isdc


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 Program: Intelsat

INTernational TELecommunication SATellite

Intelsat was created by 11 states (leaded by the United States) on 24 Aug 1964. The Comsat (controled by the US federal government) was created to manage the system because the US had 61% of the voting part. In 1979 the structure changed so that each member can't possess more that 40% of the voting parts.

Since 1966, all the continents are covered by Intelsat and nowadays numerous services are offered. Intelsat counts 142 members.

The commercial arm of Intelsat, temporarily called New Skies Satellites, was created in April 1998. This limited liability company is based in The Hague, The Netherlands. Intelsat 513, Intelsat 703, Intelsat 803, Intelsat 806, Intelsat K and Intelsat KTV have been transfered to the new entity. Those satellites are worth $700 million.  Intelsat should keep 10% of the company with non-voting shares. The maximum shareholder ownership was set at 17%. The ownership will be diluted through an IPO.

In Dec 1998 in a move to set an example, Intelsat has announced it will deregistered from some unused ITU slots: 63°E, 64.9°E, 69°E, 91.5°E, 180°E, 174°W, 22°W, 21.5°W


Program: Intelsat

Intelsat 101
Intelsat 201	Intelsat 202	Intelsat 203	Intelsat 204
Intelsat 301	Intelsat 302	Intelsat 303	Intelsat 304	Intelsat 305
Intelsat 306	Intelsat 307	Intelsat 308
Intelsat 401	Intelsat 402	Intelsat 403	Intelsat 404	Intelsat 405
Intelsat 406	Intelsat 407	Intelsat 408
Intelsat 4A01	Intelsat 4A02	Intelsat 4A03	Intelsat 4A04	Intelsat 4A05
Intelsat 4A06
Intelsat 501	Intelsat 502	Intelsat 503	Intelsat 504	Intelsat 505
Intelsat 506	Intelsat 507	Intelsat 508	Intelsat 509	Intelsat 510
Intelsat 511	Intelsat 512	Intelsat 513	Intelsat 514	Intelsat 515
Intelsat 601	Intelsat 602	Intelsat 603	Intelsat 604	Intelsat 605
Intelsat K	Intelsat KTV
Intelsat 701	Intelsat 702	Intelsat 703	Intelsat 704	Intelsat 705
Intelsat 706	Intelsat 707	Intelsat 708	Intelsat 709
Intelsat 801	Intelsat 802	Intelsat 803	Intelsat 804	Intelsat 805
Intelsat 806
Intelsat 901	Intelsat 902	Intelsat 903	Intelsat 904	Intelsat 905


Intelsat 2's specifications

Mass at launch	162 kg
Mass in orbit	86 kg
Length
Width	1.42 m
Height	0.67 m
Stabilization	Spin stabilised
DC power	BOL: 83 W EOL: 75 W
Design lifetime	3 years

The antenna platform didn't counter rotate thus most of the power didn't reach the Earth. 360° omnidirectional antenna!


Intelsat 2's C-band

Main transponders	1
Power	18 W
Bandwidth	125 MHz
EIRP max	15.5 dBW
Capacity	240 phone circuits or 1 TV channel

Allows multiple access


Intelsat 3's specifications

Mass at launch	293 kg
Mass in orbit	151 kg
Length
Width	1.41 m
Height	2.02 m
Stabilization	spin stabilized
DC power	BOL: 160 W EOL: 125 W
Design lifetime	5 years


Intelsat 3's C-band

Main transponders	2
Power	11 W
Bandwidth	225 MHz
EIRP max	23 dBW
Capacity	1500 phone circuits and 2 TV channels


Intelsat 4's specifications

Mass at launch	1415 kg
Mass in orbit	700 kg
Length
Width	2.38 m
Height	5.28 m
Stabilization	spin stabilized
DC power	BOL: 600 W EOL: 400 W
Design lifetime	7 years


Intelsat 4's C-band

Main transponders	12
Power	6 W
Bandwidth	36 MHz
Coverage and EIRP max	Global (4 beams): 22.5 dBW 2 spot beams: 33.7 dBW
Capacity	4000 phone circuits and 2 TV channels


Intelsat 4A's specifications

Mass at launch	1515 kg
Mass in orbit	793 kg
Length
Width	2.38 m
Height	6.93 m
Stabilisation	Spin stabilized (60 rpm)
DC power	BOL: 700 W EOL: 500 W
Design lifetime	7 years


Intelsat 4A's C-band

Main transponders	20
Power	6.5 W or 8 W?
Bandwidth	36 MHz
Coverage and EIRP max	Global: 22 dBW Hemispheric (2 beams): 26 dBW Spot beam: 29 dBW
Capacity	6000 phone circuits and 2 TV channels

First generation with separated hemispheric beams which allowed the reuse of same frequencies on the 2 antennas.


Intelsat 5's specifications

Prime contractor	Ford Aerospace
Platform	Intelsat 5
Mass at launch	1900 kg
Mass in orbit	1040 kg
Payload mass	233.5 kg: transponders: 174.6 kg, antennas: 58.9 kg
Dimension	1.66 x 2 x 1.77 m (with tower: 6.4 m)
Solar array	15.58 m span
DC power	BOL: 1800 W EOL: equinox: 1400 W, solstice: 1288 W
Payload power	753.8 W
Stabilization	3-axis
Design lifetime	7 years
Capacity	12000 phone circuits and 2 TV channels


Intelsat 5's L-band

Main transponders	2
Backup transponders
Power
Bandwidth
Coverage
EIRP max	33 dBW
Polarization

Only on 505 to 509. Those transponders are leased to Inmarsat


Intelsat 5's C-band

Main transponders	21
Backup transponders
Power	Global, hemispheric and zone beams: 8.5 W (TWTA) Spot beam: 4.5 W
Bandwidth	36 and 72 MHz
Coverage and EIRP max	Global: 23.5 dBW Hemispheric and zone: 29 dBW
Polarization	circular R/L
Frequencies	3.7-4.2 GHz
Beacons	3.9475 & 3.9525 GHz RHCP

First generation with orthogonal polarizations. Together with the use of 2 separated hemispheric beams more frequency space could be saved.


Intelsat 5's Ku-band

Main transponders	6
Backup transponders	4
Power	10 W (TWTA)
Bandwidth	2 transponders of 72 MHz 2 transponders of 241 MHz
Coverage	2 spot beams
EIRP max	West: 44.4 dBW East: 41.1 dBW
Polarization	linear
Frequencies	10.9-11.7 & 11.7-11.95 GHz
Beacons	11.198 & 11.452 GHz RHCP


Intelsat 5A's specifications

Prime contractor	Ford Aerospace
Platform	Intelsat 5
Mass at launch	1900 kg
Mass in orbit	1040 kg
Payload mass	262.7 kg: transponders: 187.2 kg, antennas: 58.9 kg
Dimension	1.66 x 2 x 1.77 m
Solar array	15.58 m span
DC power	BOL: 1800 W EOL: equinox: 1427 W, solstice: 1351 W
Payload power	875.3 W
Stabilization	3-axis
Design lifetime	7 years
Phone circuits	15000
Reserved TV channels	2


Intelsat 5A's C-band

Main transponders	32
Backup transponders	12
Power	Global, hemispheric and zone beams: 8.5 W (TWTA) Spot beams: 4.5 W
Bandwidth	36 and 72 MHz
Coverage and EIRP max	Global: 23.5 dBW Hemispheric and zone beams: 29 dBW Spot beam: 32.5 dBW
Polarization	circular R/L
Frequencies	3.7-4.2 GHz
Beacons	3.9475, 3.948, 3.952 & 3.9525 GHz RHCP


Intelsat 5A's Ku-band

Main transponders	6
Backup transponders	4
Power	10 W (TWTA)
Bandwidth	2 transponders of 72 MHz 2 transponders of 241 MHz
Coverage	2 spot beams
EIRP max	West: 44.4 dBW East: 41.1 dBW
Polarization	linear
Frequencies	10.9-11.7 & 11.7-11.95 GHz + 12.5-12.75 GHz on 513 & 515 only
Beacons	11.198 & 11.452 GHz RHCP


Intelsat 6's specifications

Prime contractor	Hughes
Platform	Intelsat 6 (HS389)
Mass at launch	~4300 kg
Mass in orbit	2560 kg
Payload mass	660 kg: transponders: 332 kg, antennas: 330 kg
Diameter	3.63 m
Height	6.4 m (11.84 m stowed)
DC power	BOL: 2600 W EOL: equinox: 2204 W, solstice: 2083 W
Payload power	~1600 W
Stabilization	Spin stabilized
Design lifetime	13 years
Phone circuits	24000 (120000 with DCME)
Reserved TV channels	3

2 telemetry and remote control antennas.


Intelsat 6's C-band

Main transponders	38
Backup transponders	12
Power	(6+2) transponders of 16 W (TWTA) (32+10) transponders of 10 W (SSPA)
Bandwidth	36, 41 and 72 MHz
Coverage and EIRP max	Global beam: 26.5 dBW Hemispheric: 29 dBW Zone: 31 dBW
Polarization	circular R/L
Frequencies	3.62-4.2 GHz
Beacons	3.9475, 3.948, 3.952 & 3.9525 GHz V


Intelsat 6's Ku-band

Main transponders	8+2
Backup transponders	3+1
Power	(8+3) transponders of 20 W (TWTA) (2+1) transponders of 40 W (TWTA)
Bandwidth	8 x 72 MHz 2 x 150 MHz
Coverage and EIRP max	West & East spots: 44.7 dBW
Polarization	linear
Frequencies	10.95-11.2 & 11.45-11.70 GHz
Beacons	11.198 & 11.452 GHz


Intelsat 6 transponder frequency plan
Intelsat 6's transponder frequency plan

The transponder frequency plan is extremly complex, this is a simplified view.

C-band slot chart

slot #	Uplink (GHz)	Downlink (GHz)	West hemi	East hemi	NW zone	NE zone	SW zone	SE zone	global A	global B	Bandwidth (MHz)
1'-2'	5.890	3.665	10	20							72
1-2	5.970	3.745	11	21	41	51	91	101			72
3-4	6.050	3.825	12	22	42	52	92	102			72
5-6	6.130	3.905	13	23	43	53	93	103			72
7-8	6.220	3.995	14	24	44	54	94	104			72
9	6.280	4.055	15	25	45	55	95	105	35	85	36
10	6.320	4.095							36	86	36
11	6.360	4.135							37	87	36
12	6.4025	4.1775							38	88	41
Pol.:			A	A	B	B	B	B	A	B

It is possible to connect transponders with A pol up to both A or B pol down (same applies to pol B). A pol stands for uplink in LHCP & downlink in RHCP. B pol stands for uplink in RHCP & downlink in LHCP.

Can be used for satellite-switched TDMA (SS/TDMA). Such facility is provided individually for each bank of transponders denoted (12) and (34) and is designed to permit dynamic interconnection between the following beams:  West Hemi, East Hemi, NW Zone, SW Zone, NE Zone and SE Zone.

A compatibility mode with Intelsat 5 & 5A is available, in which 2 zone beams are combined to form an older generation zone beam. This does not change the hemi, spot or global beams.

Beacons: telemetry beacons: 3947.5 MHz and 3952.5 MHz (RHCP).  Additional maneuver beacons: 3948.0 MHz and 3952.0 MHz (RHCP).

C-band interconnection chart

Uplink beam	slot #	Downlink beam	Band
global A	9, 10, 11, 12	global A	C
global B	9, 10, 11, 12	global B	C
east hemi	1'-2', 1-2, 3-4, 5-6, 7-8, 9	east or west hemi	C
west hemi	1'-2', 1-2, 3-4, 5-6, 7-8, 9	east or west hemi	C
east hemi	1-2, 3-4, 5-6, 7-8	east or west spot	Ku
west hemi	1-2, 3-4, 5-6, 7-8	east or west spot	Ku
east hemi	1-2, 3-4, 5-6, 7-8, 9	NW, SW, NE or SE zone	C
west hemi	1-2, 3-4, 5-6, 7-8, 9	NW, SW, NE or SE zone	C
NW zone	1-2, 3-4, 5-6, 7-8, 9	east or west hemi	C
NW zone	1-2, 3-4, 5-6, 7-8, 9	NW, SW, NE or SE zone	C
NW zone	1-2, 3-4, 5-6, 7-8	east or west spot	Ku
SW zone	1-2, 3-4, 5-6, 7-8, 9	east or west hemi	C
SW zone	1-2, 3-4, 5-6, 7-8, 9	NW, SW, NE or SE zone	C
SW zone	1-2, 3-4, 5-6, 7-8	east or west spot	Ku
NE zone	1-2, 3-4, 5-6, 7-8, 9	east or west hemi	C
NE zone	1-2, 3-4, 5-6, 7-8, 9	NW, SW, NE or SE zone	C
NE zone	1-2, 3-4, 5-6, 7-8	east or west spot	Ku
SE zone	1-2, 3-4, 5-6, 7-8, 9	east or west hemi	C
SE zone	1-2, 3-4, 5-6, 7-8, 9	NW, SW, NE or SE zone	C
SE zone	1-2, 3-4, 5-6, 7-8	east or west spot	Ku
Ku-band slot chart (GHz)

slot #	Uplink (GHz)	Downlink 11	west spot	east spot	Bandwith (MHz)
1-2	14.0425	10.9925	61	71	77
3-4	14.125	11.075	62	72	72
5-6	14.205	11.155	63	73	72
7-8	14.295	11.495	64	74	72
9-12	14.4185	11.6185	69	79	150

Ku-band polarization: East spot: uplink in Horizontal, downlink in Vertical. West Spot uplink in Vertical, downlink in Horizontal.

Beacons: 11.198 GHz and 11.452 GHz (RHCP)

Ku-band interconnection chart

Uplink beam	slot #	Downlink beam	Band
east spot	1-2, 3-4, 5-6, 7-8, 9-12	east or west spot	Ku
west spot	1-2, 3-4, 5-6, 7-8, 9-12	east or west spot	Ku
east spot	1-2, 3-4, 5-6, 7-8	east or west hemi	C
west spot	1-2, 3-4, 5-6, 7-8	east or west hemi	C
east spot	5-6, 7-8	NW, SW, NE or SE zone	C
west spot	5-6, 7-8	NW, SW, NE or SE zone	C


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Intelsat 7's specifications

Prime contractor	Space Systems/Loral
Platform	Intelsat 7 (based on Ford FS-1300 and Aerospatiale Spacebus-2000)
Mass at launch	3750 kg
Mass in orbit	1800 kg
Dry mass	1500 kg
Payload mass	446 kg: transponders: 338kg, antennas: 108 kg
Dimension	2.45 x 2.2 x 2.7 m
Solar array	21.8 m span
DC power	EOL: equinox: 3968 W, solstice: 3650 W
Payload power	2580 W
Stabilization	3-axis
Design lifetime	10-15 years
Phone circuits	18000 (90000 with DCME)
Reserved TV channels	3

Cross-strapping: uplink in C-band and downlink in Ku-band (701, 702, 703, 704, 705 & 709)


Intelsat 7's C-band

Main transponders	28
Backup transponders
Power	10, 16, 20 & 30 W
Bandwidth	10 transponders of 36 MHz 2 transponders of 41 MHz 16 transponders of 72 MHz
Coverage and EIRP max	Global beam: 26/29 dBW Hemispheric beam: 33 dBW (2x36 MHz & 8x72 MHz) Zone beam: 33 dBW (2x36 MHz & 8x72 MHz) Spot beam: 33.3/36.3 dBW
Polarization	circular R/L
Frequencies	3.6-4.2 GHz
Beacons	tracking: 3.3950 GHz V telemetry: 3.9475 & 3.9522 GHz RHCP

The two 41 MHz transponders are 3 dBW stronger than the others.


Intelsat 7's Ku-band

Main transponders	10
Backup transponders
Power	5 transponders of 35 W 5 transponders of 50 W
Bandwidth	6 transponders of 72 MHz 4 transponders of 112 MHz
Coverage and EIRP max	Spot 1: 45.4 dBW Spot 2: 44.5 dBW Spot 3: 46 dBW (the nominal power can be increased)
Polarization	linear
Frequencies	downlink can be switched to 10.95-11.20 GHz, 11.45-11.70 GHz, 11.70-11.95 GHz & 12.50-12.75 GHz
Beacons	11.701 & 12.501 GHz linear 11.198 & 11.452 GHz RHCP

Five transponders max per spot. Spot 1 is V, spot 2 is H and spot 3 is either H or V depending on the spot (1 or 2) it belonged to (only 701, 702 & 703 have this polarization limitation, on the others the polarization can be choosen).


Intelsat 7 transponder frequency plan
Intelsat 7's transponder frequency plan

The transponder frequency plan is extremly complex, this is a simplified view.

Depending upon the needs of different orbital locations, the satellites can be operated in either normal pitch, roll, and yaw attitude or in an inverted attitude (i.e. the satellite is rotated 180° along the yaw axis).  Inversion results in a change in the geographical orientation of the physical beam patterns.

C-band slot chart

slot #	Uplink (GHz)	Downlink (GHz)	West hemi	East hemi	NW zone	NE zone	SW zone	SE zone	global A	global B	C spot A	C spot B	Bandwidth (MHz)
1-2	5.9675	3.7425	11	21	41	51	91	101					77
3-4	6.050	3.825	12	22	42	52	92	102					72
5	6.111	3.886	13A	23A	43A	53A	93A	103A					34
6	6.149	3.924	13B	23B	43B	53B	93B	103B					34
7-8	6.220	3.995	14	24	44	54	94	104					72
9	6.280	4.055	15	25	45	55	95	105	35	85	135	185	36
10	6.320	4.095							36	86	136	186	36
11	6.360	4.135							37	87	137	187	36
12	6.4025	4.1775							38	88	138	188	41
Pol.:			A	A	B	B	B	B	A	B	A	B

When the zone beams are operated in the enhanced mode the uplink beam connection ID numbers are signated as 141, 142, etc. for the NW & SE beam combination and as 151, 152, etc. for the NE & SW beam combination. In Enhanced zone mode the extension zone is added in the uplink coverage to the original zone coverage, but for downlink each transponders is independantly affected to either the original coverage or its extension.

It is possible to connect transponders with A pol up to both A or B pol down (same applies to pol B). A pol stands for uplink in LHCP & downlink in RHCP. B pol stands for uplink in RHCP & downlink in LHCP.

Beacons: telemetry beacons: 3947.5 MHz and 3952.5 MHz (RHCP).  Additional maneuver beacons: 3948.0 MHz and 3952.0 MHz (RHCP). Tracking beacon: 3950 MHz V

C-band interconnection chart

Uplink beam	slot #	Downlink beam	Band
global A	9	hemi 1, global A or C spot A	C
global A	10, 11, 12	global A or C spot A	C
global B	9	hemi 2, global B or C spot B	C
global B	10, 11, 12	global B or C spot B	C
C spot A	9	hemi 1, global A or C spot A	C
C spot A	10, 11, 12	global A or C spot A	C
C spot B	9	hemi 2, global B or C spot B	C
C spot B	10, 11, 12	global B or C spot B	C
hemi 1	1-2, 3-4, 5, 6, 7-8	hemi 1, hemi 2, zone 1 or zone 2	C
hemi 1	9	hemi 1, hemi 2, zone 1, zone 2, C spot A, global A	C
hemi 1	1-2, 3-4, 5, 6, 7-8	spot 1, spot 2 or spot 3	Ku
hemi 2	1-2, 3-4, 5, 6, 7-8	hemi 1, hemi 2, zone 1 or zone 2	C
hemi 2	9	hemi 1, hemi 2, zone 1, zone 2, C spot B, global B	C
hemi 2	1-2, 3-4, 5, 6, 7-8	spot 1, spot 2 or spot 3	Ku
zone 1	1-2, 3-4, 5, 6, 7-8, 9	hemi 1, hemi 2, zone 1 or zone 2	C
zone 1	1-2, 3-4, 5, 6, 7-8	spot 1, spot 2 or spot 3	Ku
zone 2	1-2, 3-4, 5, 6, 7-8, 9	hemi 1, hemi 2, zone 1 or zone 2	C
zone 2	1-2, 3-4, 5, 6, 7-8	spot 1, spot 2 or spot 3	Ku
Ku-band slot chart (GHz)

slot #	Uplink (GHz)	Downlink 11	Downlink 12 low	Downlink 12 high	Spot 2 (West)	Spot 1 (East)	Spot 3	Bandwith (MHz)
1-2	14.0425	10.9925	11.7475	12.5475	61	71	111	77
3-4	14.125	11.075	11.830	12.630	62	72	112	72
5	14.186	11.136	11.891	12.691	63A	73A	113A	34
6	14.224	11.174	11.929	12.729	63B	73B	113B	34
7-8	14.295	11.495			64	74	114	72
7-9	14.314	11.514			65	75	115	112
10-12	14.438	11.638			69	79	119	112

When the Ku-band transponders are operated in the lower portion of the 12 GHz band downlink (12 low), the beam connection IDs are changed from 61 to 261, 71 to 271, 111 to 211, etc.; likewise in the upper portion of the 12 GHz band the IDs are changed from 61 to 361, 71 to 371, 111 to 311, etc. The band selection if for the whole spots except for transponders 1-2, 3-4 & 5-6 in spot 1 and 2 and for all transponders in spot 3. The use of spot 3 in any uplink or downlink channel excludes the availability of the correspondig uplink or downlink channel for either spot 1 or 2.

A suffix of E is added to the ID numbers for the spot 2 beam to indicate that the satellite is operating in the enhanced spot 2 mode (Spot 2 and 2A), e.g., 61 becomes 61E, 62 become 62E, etc. In this case the coverage of both spots are linked (not independant from each other), they function as a single beam.

Ku-band polarization: Spot 1 & Spot 3 uplink in Horizontal, downlink in Vertical. Spot 2 uplink in Vertical, downlink in Horizontal. Spot 3 can be set to uplink in Vertical and downlink in Horizontal.

Beacons: 11.198 GHz, 11.452 GHz, 11.701 GHz and 12.501 GHz (RHCP); not all simultaneously active, depending on the spot and the frequency band in which it operates.

Ku-band interconnection chart

Uplink beam	slot #	Downlink beam	Band
spot 1	1-2, 3-4, 5, 6, 7-9, 10-12	spot 1, spot 2 or spot 3	Ku
spot 1	1-2, 3-4, 5, 6, 7-9/7-8	hemi 1, hemi 2, zone 1 or zone 2	C
spot 2	1-2, 3-4, 5, 6, 7-9, 10-12	spot 1, spot 2 or spot 3	Ku
spot 2	1-2, 3-4, 5, 6, 7-9/7-8	hemi 1, hemi 2, zone 1 or zone 2	C
spot 3	1-2, 3-4, 5, 6, 7-9, 10-12	spot 1, spot 2 or spot 3	Ku
spot 3	1-2, 3-4, 5, 6, 7-9/7-8	hemi 1, hemi 2, zone 1 or zone 2	C


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Intelsat 7A's specifications

Prime contractor	Space Systems/Loral
Platform	FS-1300
Mass at launch	4500 kg
Payload mass	525 kg: transponders: 412 kg, antennas: 113 kg
Dimension	2.7 x 2.2 x 2.45 m
Solar array	25.7 m span
DC power	EOL: equinox: 5326 W, solstice: 4884 W
Payload power	3612 W
Stabilization	3-axis
Design lifetime	10-15 years
Phone circuits	22500 (112500 with DCME)
Reserved TV channels	3

(706, 707 & 708)


Intelsat 7A's C-band

Main transponders	28
Backup transponders
Power	10, 20 & 30 W
Bandwidth	10 transponders of 36 MHz 2 transponders of 41 MHz 16 transponders of 72 MHz
Coverage and EIRP max	Global beam (36 & 41 MHz): 29 dBW Hemispheric beam (8x72 MHz & 2x36 MHz): 33 dBW Zone beam (8x72 MHz & 2x36 MHz): 33 dBW Spot beam (36 & 41 MHz): 36.1 dBW
Polarization	circular R/L
Beacons	tracking: 3.3950 GHz V telemetry: 3.9475 & 3.9522 GHz RHCP

A total of 6 transponder are switched either to global or to spot beam.


Intelsat 7A's Ku-band

Main transponders	14
Backup transponders
Power	5 transponders of 49 W 5 transponders of 73 W
Bandwidth	6 transponders of 72 MHz 8 transponders of 112 MHz
Coverage and EIRP max	Spot 1: 47 dBW Spot 2: 47 dBW Spot 3: 42.8 dBW (the nominal power can be increased)
Polarization	linear
Frequencies	downlink can be switched to 10.95-11.20 GHz, 11.45-11.70 GHz, 11.70-11.95 GHz & 12.50-12.75 GHz
Beacons	11.701 & 12.501 GHz linear 11.198 & 11.452 GHz RHCP

Five transponders max per spot.


Intelsat 7A transponder frequency plan
Intelsat 7A's transponder frequency plan

The transponder frequency plan is extremly complex, this is a simplified view.

Depending upon the needs of different orbital locations, the satellites can be operated in either normal pitch, roll, and yaw attitude or in an inverted attitude (i.e. the satellite is rotated 180° along the yaw axis).  Inversion results in a change in the geographical orientation of the physical beam patterns.

C-band slot chart

slot #	Uplink (GHz)	Downlink (GHz)	West hemi	East hemi	NW zone	NE zone	SW zone	SE zone	global A	global B	C spot A	C spot B	Bandwidth (MHz)
1-2	5.9675	3.7425	11	21	41	51	91	101					77
3-4	6.050	3.825	12	22	42	52	92	102					72
5	6.111	3.886	13A	23A	43A	53A	93A	103A					34
6	6.149	3.924	13B	23B	43B	53B	93B	103B					34
7-8	6.220	3.995	14	24	44	54	94	104					72
9	6.280	4.055	15	25	45	55	95	105	35	85	135	185	36
10	6.320	4.095							36	86	136	186	36
11	6.360	4.135							37	87	137	187	36
12	6.4025	4.1775							38	88	138	188	41
Pol.:			A	A	B	B	B	B	A	B	A	B

When the zone beams are operated in the enhanced mode the uplink beam connection ID numbers are signated as 141, 142, etc. for the NW & SE beam combination and as 151, 152, etc. for the NE & SW beam combination. In Enhanced zone mode the extension zone is added in the uplink coverage to the original zone coverage, but for downlink each transponders is independantly affected to either the original coverage or its extension.

It is possible to connect transponders with A pol up to both A or B pol down (same applies to pol B). A pol stands for uplink in LHCP & downlink in RHCP. B pol stands for uplink in RHCP & downlink in LHCP.

Beacons: telemetry beacons: 3947.5 MHz and 3952.5 MHz (RHCP).  Additional maneuver beacons: 3948.0 MHz and 3952.0 MHz (RHCP). Tracking beacon: 3950 MHz V

C-band interconnection chart

Uplink beam	slot #	Downlink beam	Band
global A	9	hemi 1, global A or C spot A	C
global A	10, 11, 12	global A or C spot A	C
global B	9	hemi 2, global B or C spot B	C
global B	10, 11, 12	global B or C spot B	C
C spot A	9	hemi 1, global A or C spot A	C
C spot A	10, 11, 12	global A or C spot A	C
C spot B	9	hemi 2, global B or C spot B	C
C spot B	10, 11, 12	global B or C spot B	C
hemi 1	1-2, 3-4, 5, 6, 7-8	hemi 1, hemi 2, zone 1 or zone 2	C
hemi 1	9	hemi 1, hemi 2, zone 1, zone 2, C spot A, global A	C
hemi 1	1-2, 3-4, 5, 6, 7-8	spot 1, spot 2 or spot 3	Ku
hemi 2	1-2, 3-4, 5, 6, 7-8	hemi 1, hemi 2, zone 1 or zone 2	C
hemi 2	9	hemi 1, hemi 2, zone 1, zone 2, C spot B, global B	C
hemi 2	1-2, 3-4, 5, 6, 7-8	spot 1, spot 2 or spot 3	Ku
zone 1	1-2, 3-4, 5, 6, 7-8, 9	hemi 1, hemi 2, zone 1 or zone 2	C
zone 1	1-2, 3-4, 5, 6, 7-8	spot 1, spot 2 or spot 3	Ku
zone 2	1-2, 3-4, 5, 6, 7-8, 9	hemi 1, hemi 2, zone 1 or zone 2	C
zone 2	1-2, 3-4, 5, 6, 7-8	spot 1, spot 2 or spot 3	Ku
Ku-band slot chart (GHz)

slot #	Uplink (GHz)	Downlink 11	Downlink 12 low	Downlink 12 high	Spot 2 (West)	Spot 1 (East)	Spot 3	Spot 2X (West)	Spot 1X (East)	Bandwith (MHz)
1-2	14.0425	10.9925	11.7475	12.5475	61	71	111			77
1-3	14.060	11.010	11.765	12.565			111X	61X	71X	112
3-4	14.125	11.075	11.830	12.630	62	72	112			72
4-6	14.185	11.135	11.890	12.690			113X	63X	73X	112
5	14.186	11.136	11.891	12.691	63A	73A	113A			34
6	14.224	11.174	11.929	12.729	63B	73B	113B			34
7-8	14.295	11.495			64	74	114			72
7-9	14.314	11.514			65	75	115	65X	79X	112
10-12	14.438	11.638			69	79	119	69X	79X	112
12	14.4775						118			41

When the Ku-band transponders are operated in the lower portion of the 12 GHz band downlink (12 low), the beam connection IDs are changed from 61 to 261, 71 to 271, 111 to 211, 65X to 265X etc.; likewise in the upper portion of the 12 GHz band the IDs are changed from 61 to 361, 71 to 371, 111 to 311, 75X to 375X, etc. The band selection can be set per transponder for 1-2, 3-4, 5-6, 1-3 and 4-6. The spot 3 can be used in any frequency band, selectable transponder per transponder. The use of any transponder uplink or downlink in spot 3 makes it unavailable for use by one of the other spots.

A suffix of E is added to the ID numbers for the spot 2 beam to indicate that the satellite is operating in the enhanced spot 2 mode (Spot 2 and 2A), e.g., 61 becomes 61E, 62 become 62E, etc. In this case the coverage of both spots are linked (not independant from each other), they function as a single beam.

Ku-band polarization: Spot 1, Spot 2X & Spot 3 uplink in Horizontal, downlink in Vertical. Spot 2 & Spot 1X uplink in Vertical, downlink in Horizontal. Spot 3's polarization can be modified at will.

Spot 1X has opposite polarization but same coverage than Spot 1; respectively for spot 2X & spot 2. Two transponders downlink max per X spot. A high power mode can be achived by using the transponders of the X spots, up to 2 such configarations per Spot 1, 2 or 3. May only be used in transponders 1-3 and 4-6 in X spots and 1-2 and 5-6 in Spot 3.

Beacons: 11.198 GHz, 11.452 GHz, 11.701 GHz and 12.501 GHz (RHCP); not all simultaneously active, depending on the spot and the frequency band in which it operates.

Ku-band interconnection chart

Uplink beam	slot #	Downlink beam	Band
spot 1	1-2, 3-4, 5, 6, 7-9, 10-12	spot 1, spot 2 or spot 3	Ku
spot 1	1-2, 3-4, 5, 6, 7-9/7-8	hemi 1, hemi 2, zone 1 or zone 2	C
spot 1X	1-3/7-9, 4-6/10-12	spot 1X or spot 2X	Ku
spot 1X	1-3, 4-6, 7-9, 10-12	spot 3	Ku
spot 2	1-2, 3-4, 5, 6, 7-9, 10-12	spot 1, spot 2 or spot 3	Ku
spot 2	1-2, 3-4, 5, 6, 7-9/7-8	hemi 1, hemi 2, zone 1 or zone 2	C
spot 2X	1-3/7-9, 4-6/10-12	spot 1X or spot 2X	Ku
spot 2X	1-3, 4-6, 7-9, 10-12	spot 3	Ku
spot 3	1-2, 3-4, 5, 6, 7-9, 10-12	spot 1, spot 2 or spot 3	Ku
spot 3	1-2, 3-4, 5, 6, 7-9/7-8	hemi 1, hemi 2, zone 1 or zone 2	C
spot 3	1-2, 5-6, 7-9, 10-12	spot 1X or spot 2X	Ku
spot 3	12	global A, C spot A, global B or C spot B	C


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Intelsat 8's specifications

Prime contractor	Lockheed Martin Astro Space
Platform	GE 7000
Mass at launch	3400 kg
Dry mass	1601 kg
Dimension	2.52 x 2.19 x 3.44 m (10.8 m deployed)
Stabilization	3-axis
DC power	BOL: 6400 W EOL: 4760 W
Design lifetime	13 years
Phone circuits	22500 (112500 with DCME)
Reserved TV channels	3

4 satellites ordered (801-804)


Intelsat 8's C-band

Main transponders	38
Backup transponders
Power	7-22 W (SSPA) for zone transponders 27-38W (SSPA) for hemi & global transponders
Bandwidth	36 and 72 MHz
Coverage & EIRP	(beam peak to outer edge) Global: 33.1-29.0 dBW Hemispheric: 40.2-34.5 dBW Zone: 42.8-34.5 dBW
G/T (beam peak to outer edge)	Global: -7.9 - -12.0 dB/K Hemispheric: -0.5 - -9.5 dB/K Zone: +5.2 - -6.5 dB/K
SFD	-89.0 - -67.0 dBW/m² (< 2 dB adjustments)
Polarization	Circular Right and Left
Frequencies	Uplink: 5.850-6.425 GHz Downlink: 3.625-4.200 GHZ
Beacons	tracking: 3.3950 GHz linear telemetry: 3.9475 & 3.9522 GHz RHCP


Intelsat 8's Ku-band

Main transponders	6 (5 max per beam)
Backup transponders
Power	43 W (TWTA)
Bandwidth	72 and 112 MHz
Coverage & EIRP	(beam peak to outer edge), steerable Spot 1: 52.6-44.0 dBW Spot 2: 51.6-44.0 dBW
G/T (beam peak to outer edge)	Spot 1: +11.1 - +2.0 dB/K Spot 2: +9.5 - +2.0 dB/K
SFD	-89.0 - -67.0 dBW/m² (< 2 dB adjustments)
Polarization	linear H/V (in-orbit switching possible)
Frequencies	Uplink: 14.00-14.50 GHz Downlink: each transponder can be switched into 1 of the 3 bands: 10.95-11.2 GHz 11.7-11.95 GHz 12.5-12.75 GHz & 11.45-11.70 GHz
Beacons	11.701 & 12.501 GHz linear 11.198 & 11.452 GHz RHCP

Spot 1 is circular (same as spot 3 of Intelsat 7) and spot 2 is elliptical (same as spot 1 of Intelsat 7)


Intelsat 8 transponder frequency plan
Intelsat 8's transponder frequency plan

Depending upon the needs of different orbital locations, the satellites can be operated in either normal pitch, roll, and yaw attitude or in an inverted attitude (i.e. the satellite is rotated 180° along the yaw axis).  Inversion results in a change in the geographical orientation of the physical beam patterns.

C-band slot chart

slot #	Uplink (GHz)	Downlink (GHz)	West hemi	East hemi	NW zone	NE zone	SW zone	SE zone	MW zone	global A	global B	Bandwidth (MHz)
1'-2'	5.890	3.665	10	20								72
1-2	5.970	3.745	11	21	41	51	91	101	121			77
3-4	6.050	3.825	12	22	42	52	92	102	122			72
5	6.111	3.886	13A	23A	43A	53A	93A	103A	123A			34
6	6.149	3.924	13B	23B	43B	53B	93B	103B	123B			34
7-8	6.220	3.995	14	24	44	54	94	104	124			72
9	6.280	4.055	15	25	45	55	95	105	125	35	85	36
10	6.320	4.095								36	86	36
11	6.360	4.135								37	87	36
12	6.4025	4.1775								38	88	41
Pol.:			A	A	B	B	B	B	B	A	B

The letter C is added to the NW zone beam when the NW and MW zones are combined; 41 becomes 41C, 43A becomes 43AC.

It is possible to connect transponders with A pol up to both A or B pol down (same applies to pol B). A pol stands for uplink in LHCP & downlink in RHCP. B pol stands for uplink in RHCP & downlink in LHCP.

The uplink transponders on zone 3 can be switch independently to the transmit beams of zone 1, zone 2 and zone 4 simultaneously.

Beacons: telemetry beacons: 3947.5 MHz and 3952.5 MHz (RHCP).  Additional maneuver beacons: 3948.0 MHz and 3952.0 MHz (RHCP). Tracking beacon: 3950 MHz V

C-band interconnection chart

Uplink beam	slot #	Downlink beam	Band
global A	9	hemi 1	C
global A	9, 10, 11, 12	global A	C
global A	12	spot 1 or spot 2	Ku
global B	9	hemi 2	C
global B	9, 10, 11, 12	global B or C spot B	C
global B	12	spot 1 or spot 2	Ku
hemi 1	1'-2'	hemi 1 or hemi 2	C
hemi 1	1-2, 3-4, 5, 6, 7-8, 9	hemi 1, hemi 2, zone 1, zone 2, zone 3 or zone 4	C
hemi 1	1-2, 3-4, 5, 6, 7-8, 9	hemi 1, hemi 2, zone 3, zone 4 or zone 5	C
hemi 1	1-2, 3-4, 5, 6, 7-8	spot 1 or spot 2	Ku
hemi 1	9	global A	C
hemi 2	1'-2'	hemi 1 or hemi 2	C
hemi 2	1-2, 3-4, 5, 6, 7-8, 9	hemi 1, hemi 2, zone 1, zone 2, zone 3 or zone 4	C
hemi 2	1-2, 3-4, 5, 6, 7-8, 9	hemi 1, hemi 2, zone 3, zone 4 or zone 5	C
hemi 2	1-2, 3-4, 5, 6, 7-8	spot 1 or spot 2	Ku
hemi 2	9	global B	C
zone 1	1-2, 3-4, 5, 6, 7-8	spot 1 or spot 2	Ku
zone 1	1-2, 3-4, 5, 6, 7-8, 9	hemi 1, hemi 2, zone 1, zone 2, zone 3 or zone 4	C
zone 2	1-2, 3-4, 5, 6, 7-8	spot 1 or spot 2	Ku
zone 2	1-2, 3-4, 5, 6, 7-8, 9	hemi 1, hemi 2, zone 1, zone 2, zone 3 or zone 4	C
zone 3	1-2, 3-4, 5, 6, 7-8	spot 1 or spot 2	Ku
zone 3	1-2, 3-4, 5, 6, 7-8, 9	hemi 1, hemi 2, zone 1, zone 2, zone 3 or zone 4	C
zone 3	1-2, 3-4, 5, 6, 7-8, 9	hemi 1, hemi 2, zone 3, zone 4 or zone 5	C
zone 4	1-2, 3-4, 5, 6, 7-8	spot 1 or spot 2	Ku
zone 4	1-2, 3-4, 5, 6, 7-8, 9	hemi 1, hemi 2, zone 1, zone 2, zone 3 or zone 4	C
zone 4	1-2, 3-4, 5, 6, 7-8, 9	hemi 1, hemi 2, zone 3, zone 4 or zone 5	C
zone 5	1-2, 3-4, 5, 6, 7-8	spot 1 or spot 2	Ku
zone 5	1-2, 3-4, 5, 6, 7-8, 9	hemi 1, hemi 2, zone 3, zone 4 or zone 5	C
Ku-band slot chart (GHz)

slot #	Uplink (GHz)	Downlink 11	Downlink 12 low	Downlink 12 high	Spot 2 (West)	Spot 1 (East)	Bandwith (MHz)
1-2	14.0425	10.9925	11.7475	12.5475	61	71	77
3-4	14.125	11.075	11.830	12.630	62	72	72
5	14.186	11.136	11.891	12.691	63A	73A	34
6	14.224	11.174	11.929	12.729	63B	73B	34
7-9	14.314	11.514			65	75	112
10-12	14.438	11.638			69	79	112

When the Ku-band transponders are operated in the lower portion of the 12 GHz band downlink (12 low), the beam connection IDs are changed from 61 to 261, 71 to 271, etc.; likewise in the upper portion of the 12 GHz band the IDs are changed from 61 to 361, 71 to 371, etc. The band selection can be set per transponder for 1-2, 3-4 and 5-6. Up to 6 transponders per spot.

Ku-band polarization: Spot 1 uplink in Horizontal, downlink in Vertical. Spot 2 uplink in Vertical, downlink in Horizontal. This can be inverted, but both spots always have orthogonal signals.

Spot 1X has opposite polarization but same coverage than Spot 1; respectively for spot 2X & spot 2. Two transponders downlink max per X spot. A high power mode can be achived by using the transponders of the X spots, up to 2 such configarations per Spot 1, 2 or 3. May only be used in transponders 1-3 and 4-6 in X spots and 1-2 and 5-6 in Spot 3.

Beacons: 11.198 GHz, 11.452 GHz, 11.701 GHz and 12.501 GHz (RHCP); not all simultaneously active, depending on the spot and the frequency band in which it operates.

Ku-band interconnection chart

Uplink beam	slot #	Downlink beam	Band
spot 1	1-2, 3-4, 5, 6, 7-9	hemi 1, hemi 2, zone 1, zone 2, zone 3 or zone 4	C
spot 1	1-2, 3-4, 5, 6, 7-9	hemi 1, hemi 2, zone 3, zone 4 or zone 5	C
spot 1	1-2, 3-4, 5, 6, 7-9, 10-12	spot 1, spot 2	Ku
spot 1	12	global A or global B	C
spot 2	1-2, 3-4, 5, 6, 7-9	hemi 1, hemi 2, zone 1, zone 2, zone 3 or zone 4	C
spot 2	1-2, 3-4, 5, 6, 7-9	hemi 1, hemi 2, zone 3, zone 4 or zone 5	C
spot 2	1-2, 3-4, 5, 6, 7-9, 10-12	spot 1, spot 2	Ku
spot 2	12	global A or global B	C


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Intelsat 8A's specifications

Prime contractor	Lockheed Martin Astro Space
Platform	GE 7000
Mass at launch	3520 kg
Dimension
Stabilization	3-axis
DC power
Design lifetime	13 years
Phone circuits
Reserved TV channels

2 satellites ordered (805-806), will be specifically customized


Intelsat 8A's C-band

Main transponders	28
Backup transponders
Power	60W (TWTA)
Bandwidth	20 x 36 MHz 8 x 72 MHz
Coverage & EIRP	(beam peak to outer edge) 39.7-37.5 dBW
G/T (beam peak to outer edge)	-5.9 - -8.0 dB/K
SFD	-89.0 - -70.0 dBW/m² (< 2 dB adjustments)
Polarization	switchable: circular or linear, default: circular
Frequencies	Uplink: 5.850-6.650 GHz Downlink: 3.400-4.200 GHz (extended C-band)

Beacons: telemetry beacons: 3947.5 MHz and 3952.5 MHz (RHCP).  Additional maneuver beacons: 3948.0 MHz and 3952.0 MHz (RHCP). Tracking beacon: 3950 MHz V


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Intelsat 8A's Ku-band

Main transponders	3
Backup transponders
Power	134 W (TWTA)
Bandwidth	72 and 112 MHz
Coverage & EIRP	(beam peak to outer edge), 1 steerable spot 805: 51.7-49.7 dBW 806: 50.4-48.0 dBW
G/T (beam peak to outer edge)	805: +4.2 - +2.7 dB/K 806: +2.6 - +1.0 dB/K
SFD	805: -96.0 - -74.0 dBW/m² (< 2 dB adjustments) 806: -95.0 - -73.0 dBW/m² (< 2 dB adjustments)
Polarization	linear 805: V (down) 806: H (down)
Frequencies	Uplink: 14.00-14.50 GHz Downlink 806: 11.7-11.95 GHz Downlink 805: 12.5-12.75 GHz


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Intelsat 9's specifications

Prime contractor	Space Systems/Loral
Platform
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime	15 years

Payload provided by Alcatel


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Intelsat 9's C-band

Main transponders	44
Backup transponders
Power
Bandwidth	32 transponders of 72 MHz 12 transponders of 36 MHz
Coverage
EIRP max	hemispheric beam: 43 dBW zone beam: 44.8 dBW global beam: 34 dBW
Polarization	circular L/R
Frequencies	uplink: 5.850-6.425 GHz downlink: 3.625-4.200 GHz
Beacons	3.9475, 3.948, 3.952 & 3.9525 GHz


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Intelsat 9's Ku-band

Main transponders	16
Backup transponders
Power
Bandwidth	8 transponders of 72 MHz 8 transponders or 36 MHz
Coverage
EIRP max	spot 1: 52 dBW spot 2: 52 dBW
Polarization	linear H/V
Frequencies	uplink: 14.00-14.50 GHz downlink: 10.95-11.20 and 11.45-11.70 GHz
Beacons	11.198 & 11.452 GHz


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Intelsat 9 transponder frequency plan
Intelsat 9's transponder frequency plan

C-band slot chart

slot #	Uplink (GHz)	Downlink (GHz)	West hemi	East hemi	NW zone (1)	SW zone (2)	ME zone (3)	SE zone (4)	NE zone (5)	CE zone (4-5)	global A	global B	Bandwidth (MHz)
1'-2'	5.890	3.665	10	20	40	90	120	100	50	100C			72
1-2	5.970	3.745	11	21	41	91	121	101	51	101C			72
3-4	6.050	3.825	12	22	42	92	122	102	52	102C			72
5-6	6.130	3.905	13	23	43	93	123	103	53	103C			72
7-8	6.220	3.995	14	24	44	94	124	104	54	104C			72
9	6.280	4.055	15	25	45	95	125	105	55	105C			36
9A	6.270	4.055	15A	25A									16
9B	6.290	4.055	15B	25B									16
10	6.320	4.095									36	86	36
11	6.360	4.135									37	87	36
12	6.4025	4.1775									38	88	41
12A	6.391	4.166									38A	88A	18
12B	6.414	4.189									38B	88B	18
Pol.:			A	A	B	B	B	B	B	B	A	B

When in five Zone mode, only one transponder can be actived between Z2 and Z4 for each channel bank except in channels 1-2 and 3-4 (i.e., total of 44 C-Band transponders are active.) When in four Zone mode, Z4 and Z5 can be combined into a single broader Zone coverage (Combined East) in IOR.  Therefore, total of 42 C-Band transponders are available in four Zone mode.

The uplink receive Hemi beam of channel 9 can be split into two segments each with an usable bandwidth of 16 MHz so that half of the transponder is connected in loopback mode and the other half is inter-connected between the Hemi beams.  This capability allows the provision of a DAMA type of service in the Hemi transponders with quasi-global coverage and a 6 dB higher e.i.r.p. as compared to the Global transponders.  The downlink of channel 9A and 9B is combined into 36 MHz channel labelled as 9.

The uplink receive Global beam of channel 12 can be split into two segments each with an usable bandwidth of 18 MHz.  Particularly for SNG services, this capability will allow multiple carrier operation of the transponder with half of the transponder optimized for large transmit earth station antennas and the other half optimized for small transmit earth station antennas.  The downlink of channel 12A and 12B is combined into 41 MHz channel labelled as 12.

A pol stands for uplink in LHCP & downlink in RHCP. B pol stands for uplink in RHCP & downlink in LHCP.

Beacons: telemetry beacons: 3947.5 MHz and 3952.5 MHz (RHCP).  Additional maneuver beacons: 3948.0 MHz and 3952.0 MHz (RHCP). Tracking beacon: 3950 MHz V

C-band interconnection chart

Uplink beam	slot #	Downlink beam	Band
global A	10, 11, 12, 12A, 12B	global A	C
global B	10, 11, 12, 12A, 12B	global B	C
hemi 1	9A	hemi 2	C
hemi 1	9B	hemi 1	C
hemi 2	9A	hemi 1	C
hemi 2	9B	hemi 2	C
hemi 1, 2, zone 1, 2, 3, 4, 5	1'-2', 1-2, 3-4, 5-6, 7-8, 9	hemi 1, 2, zone 1, 2, 3, 4+5	C
hemi 1, 2, zone 1, 2, 3, 4, 5	1'-2', 5-6, 7-8, 9	hemi 1, 2, zone 1, 2 or zone 4, 3, 5	C
hemi 1, 2, zone 1, 2, 3, 4, 5	1-2, 3-4	hemi 1, 2, zone 1, 2, 3, 4, 5	C
hemi 1, 2, zone 1, 2, 3, 4, 5	1-2, 3-4, 5-6, 7-8	spot 1, 2	Ku
hemi 1, 2, zone 1, 2, 3, 4, 5	1-2, 3-4, 5, 6, 7-8	spot 1 or spot 2	Ku
hemi 1, 2, zone 1, 2, 3, 4+5	1'-2', 1-2, 3-4, 5-6, 7-8, 9	hemi 1, 2, zone 1, 2, 3, 4+5	C
hemi 1, 2, zone 1, 2, 3, 4+5	1'-2', 5-6, 7-8, 9	hemi 1, 2, zone 1, 2 or zone 4, 3, 5	C
hemi 1, 2, zone 1, 2, 3, 4+5	1-2, 3-4	hemi 1, 2, zone 1, 2, 3, 4, 5	C
hemi 1, 2, zone 1, 2, 3, 4+5	1-2, 3-4, 5, 6, 7-8	spot 1 or spot 2	Ku
Ku-band slot chart (GHz)

slot #	Uplink (GHz)	Downlink 11	Spot 1 (East)	Spot 2 (West)	Bandwith (MHz)
1-2	14.0425	10.9925	61	71	77
3-4	14.125	11.075	62	72	72
5-6	14.205	11.155	63	73	72
7-8	14.295	11.495	64	74	72
9	14.355	11.555	65	75	36
10	14.395	11.595	66	76	36
11	14.435	11.635	67	77	36
12	14.475	11.675	68	78	36

In Ku-band, only 12 transponders out of the 16 available channels can be actived simultaneously.  The selection of 12 transponders has been specified to be any 12 out of 16, with a maximum of 8 transponders per Spot beam.  The uplink and downlink polarization senses of the Spot beams can be independently reversed in-orbit by ground command.

Ku-band polarization: Spot 1 uplink in Horizontal, downlink in Vertical. Spot 2 uplink in Vertical, downlink in Horizontal. This can be inverted, but both spots always have orthogonal signals.

Beacons: 11.198 GHz and 11.452 GHz (RHCP)

Ku-band interconnection chart

Uplink beam	slot #	Downlink beam	Band
spot 1, 2	1-2, 3-4, 5, 6, 7-8	hemi 1, 2, zone 1, 2, 3, 4+5	C
spot 1, 2	1-2, 3-4	hemi 1, 2, zone 1, 2, 3, 4, 5	C
spot 1, 2	5-6, 7-8	hemi 1, 2, zone 1, 2 or zone 3, 4, 5	C
spot 1, 2	1-2, 3-4, 5-6, 7-8, 9, 10, 11, 12	spot 1, spot 2	Ku


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 Intelsat 101

Also called Early Bird

General

Designation	01317 / 65028A
Launch date	6 Apr 1965
Country of origin	International
Mission	Telecommunications
Geostationary orbit	35752/35823 km, 27.5°W
Launch vehicle	Thor Delta #30
End of life

Out of service	May 1970
Technical data

Specifications

Prime contractor	Hughes
Mass at launch	68 kg
Mass in orbit	38.5 kg
Length
Width	0.72 m
Height	0.59 m
Stabilization	spin stabilized (120 rpm)
DC power	BOL: 45 W EOL: 33 W
Design lifetime	1.5 year

The antenna platform didn't counter rotate thus most of the power didn't reach the Earth. The antenna was 360° omnidirectional!

C-band

Main transponders	2
Power	6 W
Bandwidth	25 MHz
EIRP max	11.5 dBW
Capacity	240 phone circuits or 1 TV channel

Didn't allow multiple access: the European stations: Pleumeur-Bodou (France), Goonhilly Downs (UK), Raisting (Germany) and Fucino (Italy) used to operated 1 week per month!


 Intelsat 201

General

Designation	02514 / 66096A
Launch date	26 Oct 1966
Country of origin	International
Mission	Telecommunications
Geostationary orbit	n/a (3424 km x 37531 km x 17.2° x 730 min)
Launch vehicle	Thor Delta #42
End of life

Out of service	26 Oct 1966
Cause	Remained on the transfert (the apogee kick motor failed)
Technical data

Specifications

C-band


 Intelsat 202

General

Designation	02639 / 67001A
Launch date	11 Jan 1967
Country of origin	International
Mission	Telecommunications
Geostationary orbit	Pacific Ocean Region
Launch vehicle	Thor Delta #44
End of life

Out of service	yes
Technical data

Specifications

C-band


 Intelsat 203

General

Designation	02717 / 67026A
Launch date	23 Mar 1967
Country of origin	International
Mission	Telecommunications
Geostationary orbit	4°W
Launch vehicle	Thor Delta #47
End of life

Out of service	yes
Technical data

Specifications

C-band


 Intelsat 204

General

Designation	02969 / 67094A
Launch date	28 Sep 1967
Country of origin	International
Mission	Telecommunications
Geostationary orbit	179°E
Launch vehicle	Thor Delta #52
End of life

Out of service	yes
Technical data

Specifications

C-band


 Intelsat 301

End of life

Out of service	18 Sep 1968
Cause	Launch failure (Thor Delta #59)
Technical data

Specifications

C-band


 Intelsat 302

General

Designation	03623 / 68116A
Launch date	19 Dec 1968
Country of origin	International
Mission	Telecommunications
Geostationary orbit	31°W
Launch vehicle	Thor Delta #63
End of life

Out of service	yes
Technical data

Specifications

C-band


 Intelsat 303

General

Designation	03674 / 69011A
Launch date	6 Feb 1969
Country of origin	International
Mission	Telecommunications
Geostationary orbit	57°E
Launch vehicle	Thor Delta #66
End of life

Out of service	yes
Technical data

Specifications

C-band


 Intelsat 304

General

Designation	03947 / 69045A
Launch date	22 May 1969
Country of origin	International
Mission	Telecommunications
Geostationary orbit	174°E
Launch vehicle	Thor Delta #68
End of life

Out of service	yes
Technical data

Specifications

C-band


 Intelsat 305

General

Designation	04051 / 69064A
Launch date	26 Jul 1969
Country of origin	International
Mission	Telecommunications
Geostationary orbit	n/a
Launch vehicle	Thor Delta #71
End of life

Out of service	26 Jul 1969
Cause	Placed on a wrong orbit (271 km x 5397 km x 30.7° x 176.6 min)
Decay	14 Oct 1988
Technical data

Specifications

C-band


 Intelsat 306

General

Designation	04297 / 70003A
Launch date	15 Jan 1970
Country of origin	International
Mission	Telecommunications
Geostationary orbit	27.5°W
Launch vehicle	Thor Delta #75
End of life

Out of service	yes
Technical data

Specifications

C-band


 Intelsat 307

General

Designation	04376 / 70032A
Launch date	23 Apr 1970
Country of origin	International
Mission	Telecommunications
Geostationary orbit	24.5°W
Launch vehicle	Thor Delta #78
End of life

Out of service	yes
Technical data

Specifications

C-band


 Intelsat 308

General

Designation	04478 / 70055A
Launch date	23 Jul 1970
Country of origin	International
Mission	Telecommunications
Geostationary orbit
Launch vehicle	Thor Delta #79
End of life

Out of service	yes
Technical data

Specifications

C-band


 Intelsat 401

General

Designation	07815 / 75042A
Launch date	22 May 1975
Country of origin	International
Mission	Telecommunications
Geostationary orbit	18.5°W
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
End of life

Out of service	yes
Technical data

Specifications

C-band


 Intelsat 402

General

Designation	04881 / 71006A
Launch date	26 Jan 1971
Country of origin	International
Mission	Telecommunications
Geostationary orbit	19.5°W
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
End of life

Out of service	yes
Technical data

Specifications

C-band


 Intelsat 403

General

Designation	05709 / 71116A
Launch date	20 Dec 1971
Country of origin	International
Mission	Telecommunications
Geostationary orbit	21.5°W
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
End of life

Out of service	yes
Technical data

Specifications

C-band


 Intelsat 404

General

Designation	05775 / 72003A
Launch date	23 Jan 1972
Country of origin	International
Mission	Telecommunications
Geostationary orbit	179°E
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
End of life

Out of service	yes
Technical data

Specifications

C-band


 Intelsat 405

General

Designation	06052 / 72041A
Launch date	13 Jun 1972
Country of origin	International
Mission	Telecommunications
Geostationary orbit	57°E
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
End of life

Out of service	yes
Technical data

Specifications

C-band


 Intelsat 406

End of life

Out of service	20 Feb 1975
Cause	Launch failure (Atlas Centaur)
Technical data

Specifications

C-band


 Intelsat 407

General

Designation	06796 / 73058A
Launch date	23 Aug 1973
Country of origin	International
Mission	Telecommunications
Geostationary orbit	1°W
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
End of life

Out of service	yes
Technical data

Specifications

C-band


 Intelsat 408

General

Designation	07544 / 74093A
Launch date	21 Nov 1974
Country of origin	International
Mission	Telecommunications
Geostationary orbit	174°E
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
End of life

Out of service	yes
Technical data

Specifications

C-band


 Intelsat 4A01

General

Designation	08330 / 75091A
Launch date	26 Sep 1975
Country of origin	International
Mission	Telecommunications
Geostationary orbit	24.5°W
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
End of life

Out of service	yes
Technical data

Specifications

C-band


 Intelsat 4A02

General

Designation	08620 / 76010A
Launch date	29 Jan 1976
Country of origin	International
Mission	Telecommunications
Geostationary orbit	27.5°W
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
End of life

Out of service	yes
Technical data

Specifications

C-band


 Intelsat 4A03

General

Designation	10557 / 78002A
Launch date	7 Jan 1978
Country of origin	International
Mission	Telecommunications
Geostationary orbit	60°E
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
End of life

Out of service	yes
Technical data

Specifications

C-band


 Intelsat 4A04

General

Designation	10024 / 77041A
Launch date	26 May 1977
Country of origin	International
Mission	Telecommunications
Geostationary orbit	34.5°W
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
End of life

Out of service	yes
Technical data

Specifications

C-band


 Intelsat 4A05

End of life

Out of service	29 Sep 1977
Cause	Launch failure (Atlas Centaur): explosion after 55 s
Technical data

Specifications

C-band


 Intelsat 4A06

General

Designation	10778 / 78035A
Launch date	31 Mar 1978
Country of origin	International
Mission	Telecommunications
Geostationary orbit	63°E
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
End of life

Out of service	yes
Technical data

Specifications

C-band


 Intelsat 501

General

Designation	12474 / 81050A
Launch date	23 May 1981
Country of origin	International
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
Location

Begin	End	Position
L: 23 May 1981
May 1988		went inclined
late 1991	late 1991	177°W, inclined
Oct 1992	Jan 1996	91.5°E, inclined (left to leave the slot to Measat 1)
late Feb 1996	Jan 1997	72°E, inclined
End of life

Out of service	Feb 1997
Cause	deorbited
Technical data

Specifications

C-band

Ku-band


 Intelsat 502

General

Designation	12089 / 80098A
Launch date	6 Dec 1980
Country of origin	International
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
Location

Begin	End	Position
L: 6 Dec 1980		21.5°W
Dec 1988		went inclined
Jan 1991	Jan 1991	1°W, inclined
Feb 1992	Oct 1994	21.5°W, inclined
Oct 1994	Apr 1998	40.5°W, inclined
End of life

Out of service	14 Apr 1998
Cause	deorbited
Technical data

Specifications

C-band

Ku-band

When in 21.5°W, the antenna's platform was rotated in December 1992 to enable a direct link between Somalia and the US. The Eastern spot was pointed to Somalia.


 Intelsat 503

General

Designation	12994 / 81119A
Launch date	15 Dec 1981
Country of origin	International
Mission	Telecommunications
Geostationary	see below
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
Location

Begin	End	Position
L: 15 Dec 1981
May 1989		went inclined
1 Jan 1991	late 1991	174°E, inclined
Oct 1992	Aug 1995	177°W, inclined
Aug 1995	mid-Dec 1995	drifting West
mid-Dec 1995	Jan 1998	157°E, inclined
End of life

Out of service	mid Jan 1998
Cause	deorbited
Technical data

Specifications

C-band

Ku-band


 Intelsat 504

General

Designation	13083 / 82017A
Launch date	5 Mar 1982
Country of origin	International
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
Location

Begin	End	Position
L: 5 Mar 1982
Apr 1989		went inclined
Jan 1991	Oct 1992	34.5°W, inclined
July 1993	Sep 1993	32°W, inclined
Dec 1993	Jan 1994	40.5°W, inclined
May 1994	May 1995	31.5°W, inclined
Jul 1995	Nov 1995	29.4°W, inclined
End of life

Out of service	late Nov 1995
Cause	end of life: deorbited
Technical data

Specifications

C-band

Ku-band


 Intelsat 505

Also called Intelsat MCS-A

General

Designation	13595 / 82097A
Launch date	28 Sep 1982
Country of origin	International
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
Location

Begin	End	Position
L: 28 Sep 1982
Dec 1989		went inclined
Jan 1991	end of 1991	63°E, inclined
Feb 1992	Aug 1994	66°E, inclined
Nov 1994	Jun 1996	65°E, inclined
Aug 1996	Nov 1996	33°E, inclined
Apr 1997		72°E, inclined
Technical data

Specifications

L-band

C-band

Ku-band

EIRP coverage (dBW)

C-band

Ku-band


Intelsat 505's C-band EIRP


Intelsat 505's Ku-band EIRP


 Intelsat 506

Also called Intelsat MCS-B

General

Designation	14077 / 83047A
Launch date	19 May 1983
Country of origin	International
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
Location

Begin	End	Position
L: 19 May 1983
Jan 1991		went inclined
Jan 1991	Feb 1992	18.5°W, inclined
Jul 1992	Jul (Sep?) 1992	34.5°W, inclined
Oct 1992	May 1995	50°W, inclined
Jun 1995	Apr 1998	31.4°W, inclined
May 1998	Jul 1998	29.5°W, inclined
End of life

Out of service	Jul 1998
Cause	deorbited
Technical data

Specifications

L-band

C-band

Ku-band

EIRP coverage (dBW)

C-band

Ku-band


Intelsat 506's C-band EIRP


Intelsat 506's Ku-band EIRP


 Intelsat 507

Also called Intelsat MCS-C

General

Designation	14421 / 83105A
Launch date	19 Oct 1983
Country of origin	International
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane L07

First Intelsat launched by a non US vehicle.

Location

Begin	End	Position
L: 19 Oct 1983
Aug 1990		went inclined
Mar 1991	Mar 1991	66°E, inclined
end of 1991	Mar 1995	57°E, inclined
Apr 1995	mid-Jul 1996	47°E, inclined
End of life

Out of service	Aug 1996
Technical data

Specifications

L-band

C-band

Ku-band


Intelsat 507's C-band EIRP


Intelsat 507's Ku-band EIRP


 Intelsat 508

Also called "PolySat" and Intelsat MCS-D

General

Designation	14786 / 84023A
Launch date	5 Mar 1984
Country of origin	International
Mission	Telecommunications
Geostationary orbit	180°E
Launch vehicle	Ariane L08
End of life

Out of service	yes
Technical data

Specifications

L-band

C-band

Ku-band


 Intelsat 509

General

Designation	15034 / 84057A
Launch date	9 Jun 1984
Country of origin	International
Mission	Telecommunications
Geostationary orbit	n/a
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
End of life

Out of service	9 Jun 1984
Cause	Launcher partial failure
Decay	24 Oct 1984
Technical data

Specifications

L-band

C-band

Ku-band


 Intelsat 510

General

Designation	15629 / 85025A
Launch date	22 Mar 1985
Country of origin	International
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Atlas Centaur
Location

Begin	End	Position
L: 22 mar 1984		174°E
Aug 1992		went inclined
Feb 1995	Mar 1995	66°E, inclined
Apr 1995	Jun 1996	57°E, inclined
Nov 1996		33°E, inclined
Technical data

Specifications

C-band

Ku-band

EIRP coverage (dBW)

C-band

Ku-band


Intelsat 510's C-band EIRP


Intelsat 510's Ku-band EIRP


 Intelsat 511

General

Designation	15873 / 85055A
Launch date	30 Jun 1985
Country of origin	International
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
Location

Begin	End	Position
L: 30 Jun 1985
Jan 1991	Jan 1991	27.5°W
late 1991	Sep 1992	63°E
Oct 1992	Feb 1993	177°E
Feb 1993	Nov 1994	177°E, went inclined
Feb 1995	Sep 1997	180°E, inclined
mid-Jun 1998		29.5°W, inclined

At 29.5°W the satellite will provide the cable restoration service (the average cable outage can last from 7 to 10 days)

In 1997, INTELSAT restored a total of 17 cable systems, and provided the equivalent to 200 units of 36 MHz, which generated revenues of US$ 24 million. Cable owners from the following countries have leased capacity on the INTELSAT 511 satellite in case of cable failure: Brazil, Canada, France, Iceland, Italy, Portugal, Venezuela, South Africa, Spain, the United Kingdom and the United States.

Technical data

Specifications

C-band

Ku-band

EIRP coverage (dBW)

C-band

Ku-band


Intelsat 511's C-band EIRP


Intelsat 511's Ku-band EIRP


 Intelsat 512

General

Designation	16101 / 85087A
Launch date	29 Sep 1985
Country of origin	International
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Atlas Centaur #65
Location

Begin	End	Position
L: 29 Sep 1985
Jan 1991	Jan 1991	34.5°W
Mar 1991	Jun 1994	1°W
Jun 1994	Aug 1994	1°W, went inclined
Sep 1994	Sep 1996	21.5°W, inclined
Feb 1997	Jun 1998	55.5°W, inclined
End of life

Out of service	Jul 1998
Cause	deorbited?
Technical data

Specifications

C-band

Ku-band

Ku-band downlink: 11.01-11.59 GHz


Intelsat 512's C-band EIRP


Intelsat 512's Ku-band EIRP


 Intelsat 513

Also called NSS 513

General

Designation	19121 / 88040A
Launch date	17 May 1988
Country of origin	International
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V22

Transfered to NSS on 30 Nov 1998

Location

Begin	End	Position
L: 17 May 1988	Jul 1995	53°W
Aug 1995		177°W, inclined (from Aug 1995 on)
Technical data

Specifications

C-band

Ku-band

EIRP coverage (dBW)

C-band

Ku-band


Intelsat 513's C-band EIRP


Intelsat 513's Ku-band EIRP


 Intelsat 514

End of life

Out of service	30 May 1986
Cause	Explosion of Ariane V18
Technical data

Specifications

C-band

Ku-band


 Intelsat 515

General

Designation	19772 / 89006A
Launch date	27 Jan 1989
Country of origin	International
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V28
Location

Begin	End	Position
L: 27 Jan 1989
Jan 1991	Feb 1992	60°E
Apr 1992	Aug 1996	18°W
Sep 1996	Dec 1997	21.5°W
Mar 1998		37.8°W

From 1st Apr 1998 on the satellite is used by Columbia Communications Corp. and renamed Columbia 515. The Ku-band payload will not be used anymore.

Columbia Communications Corp was granted by FCC to operate a C-Band satellite as a replacement at this location.

Technical data

Specifications

C-band

Ku-band

EIRP coverage map (dBW)


Intelsat 515's C-band EIRP


 Intelsat 601

General

Designation	21765 / 91075A
Launch date	29 Oct 1991
Country of origin	International
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V47
Location

Begin	End	Position
L: 29 Oct 1991
late 1991	Oct 1997	27.5°W
16 Oct 1997		34.5°W
Technical data

Specifications

C-band

Ku-band

Transponder frequency plan

EIRP coverage (dBW)

C-band

Ku-band


Intelsat 601's C-band EIRP


Intelsat 601's Ku-band EIRP


 Intelsat 602

General

Designation	20315 / 89087A
Launch date	27 Oct 1989
Country of origin	International
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V34
Location

Begin	End	Position
L: 27 Oct 1989
Jan 1991	Feb 1992	24.5°W
Apr 1992	Apr 1992	60°E
Oct 1992	Oct 1997	63°E
Oct 1997		62°E
Technical data

Specifications

C-band

Ku-band

Transponder frequency plan

EIRP coverage (dBW)

C-band

Ku-band


Intelsat 602's C-band EIRP


Intelsat 602's Ku-band EIRP


 Intelsat 603

General

Designation	20523 / 90021A
Launch date	14 Mar 1990
Country of origin	International
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Titan 3 #154

The satellite was repared (apogee kick motor changed) by STS 49 in May 1992.

Location

Begin	End	Position
L: 14 Mar 1990	May 1997	LEO
May 1992	Oct 1997	34.5°W
Nov 1997		24.5°W
Technical data

Specifications

C-band

Ku-band

Transponder frequency plan

EIRP coverage (dBW)

C-band

Ku-band


Intelsat 603's C-band EIRP


Intelsat 603's Ku-band EIRP


 Intelsat 604

General

Designation	20667 / 90056A
Launch date	23 Jun 1990
Country of origin	International
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Titan 3 #155
Location

Begin	End	Position
L: 23 Jun 1990
Jan 1991	Feb 1992	27.5°W
Oct 1992		60°E
Technical data

Specifications

C-band

Ku-band

Transponder frequency plan

EIRP coverage (dBW)

C-band

Ku-band


Intelsat 604's C-band EIRP


Intelsat 604's Ku-band EIRP


 Intelsat 605

General

Designation	21653 / 91055A
Launch date	14 Aug 1991
Country of origin	International
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V45

Should move to 31.5°W or 29.5°W

Location

Begin	End	Position
L: 14 Aug 1991
late 1991	late 1991	21.5°W
Jul 1992	Nov 1997	24.5°W
Dec 1997		27.5°W

In early September the satellite experienced an "anomaly" with telemetry. For more safety, the fleet in AOR was redeployed. The telemetry problem affects the attitude control: the satellite is not reporting its location anymore. Therefore the position has to be computed by ground stations (by measuring signal strength). Those telemetry problems were solved in Dec 1997 so that the satellite could resume normal operations.

Technical data

Specifications

C-band

Ku-band

Transponder frequency plan

EIRP coverage (dBW)

C-band

Ku-band Eastern spot

Ku-band Western spot


Intelsat 605's C-band EIRP


Intelsat 605's EIRP (Ku-band Eastern spot)


Intelsat 605's EIRP (Ku-band Western spot)


 Intelsat K

Also called Intelsat Star and NSS K

General

Designation	21989 / 92032A
Launch date	10 Jun 1992
Country of origin	International
Mission	Telecommunications
Geostationary orbit	21.5°W
Launch vehicle	Atlas Centaur

First Intelsat Ku-band only satellite for TV channels transmission. This satellite is a modified Satcom bought to respond to urgent needs over Atlantic.

Transfered to NSS on 30 Nov 1998

Technical data

EIRP coverage (dBW)

America (dBW)

Europe (dBW)

Specifications

Prime contractor	GE Astro Space
Platform	GE 5000
Mass at launch	2836 kg
Mass in orbit	1547 kg
Dimension	2.84 x 2.26 x 2.18 m
Solar array	31.2 m span
Stabilization	3-axis
DC power	BOL: 4800 W EOL: equinox: 3639 W
Design lifetime	10 years
Ku-band

Main transponders	16
Backup transponders
Power	62.5 W (TWTA)
Bandwidth	54 MHz
Coverage and EIRP (beam peak to outer edge)	Europe: 50.5-47 dBW United States: 52.2-47 dBW South America: 47.7-45 dBW North & South America: 45.5-42.7 dBW
G/T (beam peak to outer edge)	Europe: +7.3 - +3.0 dB/K United States: +7.3 - +3.0 dB/K South America: +10 - +3.0 dB/K North America + Europe: +4 - -0.3 dB/K
Polarization	linear H/V
Frequencies	Uplink: 14.00-14.50 GHz Downlink: 11.45-11.70 GHz (all beams) 11.70-11.95 GHz (Americas) 12.50-12.75 GHz (Europe)

Beacons: 11.452 & 11.699 GHz (polarization H to North America and V to South America and Europe)

Transponder frequency chart (GHz)

Uplink	Downlink  NAH	Downlink  EUV	Downlink  EUH	Downlink  SAV	Possible combined downlink
14.035	11.735	12.535		11.735	(NAH + SAV)
14.095	11.795	12.595		11.795	(NAH + SAV)
14.155	11.855	12.655		11.855	(NAH + SAV)
14.215	11.915	12.715		11.915	(NAH + SAV)
14.285	11.485	11.485	11.485	11.485	(NAH + SAV) (NAH + EUV) (NAH + EUV + SAV)
14.345	11.545	11.545	11.545	11.545	(NAH + SAV) (NAH + EUV) (NAH + EUV + SAV)
14.405	11.605	11.605	11.605	11.605	(NAH + SAV) (NAH + EUV) (NAH + EUV + SAV)
14.465	11.665	11.665	11.665	11.665	(NAH + SAV) (NAH + EUV) (NAH + EUV + SAV)

NAH = North America Horizontal; EUV = Europe Vertical; EUH = Europe Horizontal; SAV = South America Vertical


Intelsat K's Ku-band to America


Intelsat K's EIRP to Europe


 Intelsat 701

General

Designation	22871 / 93066A
Launch date	22 Oct 1993
Country of origin	International
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V60

Cost: $103 million

Location

Begin	End	Position
L: 22 Oct 1993	Aug 1997	174°E
Sep 1997		180°E
Technical data

Specifications

C-band

Ku-band

Transponder frequency plan

EIRP coverage (dBW)

C-band

Ku-band


Intelsat 701's C-band EIRP


Intelsat 701's Ku-band EIRP


 Intelsat 702

General

Designation	23124 / 94034A
Launch date	17 Jun 1994
Country of origin	International
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V64
Location

Begin	End	Position
L: 17 Jun 1994	end of tests	37.75°W
end of tests	early April 1996	1°W
May 1996		177°E
Technical data

Specifications

C-band

Ku-band

Transponder frequency plan

EIRP coverage (dBW)

C-band

Ku-band


Intelsat 702's C-band EIRP


Intelsat 702's Ku-band EIRP


 Intelsat 703

Also called NSS 703

General

Designation	23305 / 94064A
Launch date	6 Oct 1994
Country of origin	International
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Atlas Centaur

Transfered to NSS on 30 Nov 1998

Location

Begin	End	Position
L: 6 Oct 1994	May 1996	177°E
mid-Jun 1996		57°E
Technical data

Specifications

C-band

Ku-band

Transponder frequency plan

EIRP coverage (dBW)

C-band

Ku-band


Intelsat 703's C-band EIRP


Intelsat 703's Ku-band EIRP


 Intelsat 704

General

Designation	23461 / 95001A
Launch date	10 Jan 1995
Country of origin	International
Mission	Telecommunications
Geostationary orbit	66°E
Launch vehicle	Atlas Centaur

Operational since 25 Feb 1995

Technical data

Specifications

C-band

Ku-band

Transponder frequency plan

EIRP coverage (dBW)

C-band

Ku-band


Intelsat 704's C-band EIRP


Intelsat 704's Ku-band EIRP


 Intelsat 705

General

Designation	23528 / 95013A
Launch date	22 Mar 1995
Country of origin	International
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Atlas Centaur
Location

Begin	End	Position
L: 22 Mar 1995		56°W, testing
May 1995	mid-Jul 1996	50°W
Aug 1996		18°W
Technical data

Specifications

C-band

Ku-band

Transponder frequency plan

EIRP coverage (dBW)

C-band

Ku-band


Intelsat 705's C-band EIRP


Intelsat 705's Ku-band EIRP


 Intelsat 706

General

Designation	23571 / 95023A
Launch date	17 May 1995
Country of origin	International
Mission	Telecommunications
Geostationary orbit	53°W
Launch vehicle	Ariane V73

Tests carried out in 56°W. Operational in mid-July 1995.

Technical data

Specifications

C-band

Ku-band

Transponder frequency plan

EIRP coverage (dBW)

C-band

Ku-band


Intelsat 706's C-band EIRP


Intelsat 706's Ku-band EIRP


 Intelsat 707

General

Designation	23816 / 96015A
Launch date	14 Mar 1996
Country of origin	International
Mission	Telecommunications
Geostationary orbit	1°W
Launch vehicle	Ariane V84

has 14 transponders in Ku-band

The insured value of the satellite, launch and insurance was $319.1 million.

Technical data

Specifications

C-band

Ku-band

Transponder frequency plan

EIRP coverage (dBW)

C-band

Ku-band


Intelsat 707's C-band EIRP


Intelsat 707's Ku-band EIRP


 Intelsat 708

General

Designation	FTO
Launch date	14 Feb 1996
Country of origin	International
Mission	Telecommunications
Geostationary orbit	50°W
Launch vehicle	Long March 3B

The launch vehicle went off course shortly after leaving the pad and was destroyed about 20s after liftoff with its payload. Six people were killed and 57 injured, officially. Unofficial, deaths were said to be hundreds, and injured in the thousands. Two seconds after lift-off of the Long March 3B, the inertia platform became abnormal and the inertia baseline veered.

The satellite was insured for $205 million.

Technical data

Specifications

C-band

Ku-band

Transponder frequency plan


 Intelsat 709

General

Designation	23915 / 96035A
Launch date	15 Jun 1996
Country of origin	International
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V87
Location

Begin	End	Position
L: 15 Jun 1996	mid-Jul 1996	57°W, testing
mid-Jul 1996		50°W

The East Hemi beam had problems and was deactivated in early 1997.

Technical data

Specifications

C-band

Ku-band

Transponder frequency plan

EIRP coverage (dBW)

C-band

Ku-band


Intelsat 709's C-band EIRP


Intelsat 709's Ku-band EIRP


 Intelsat 801

General

Designation	24742 / 97009A
Launch date	1 Mar 1997
Country of origin	International
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V94

It was built for $76 million, launched for $86 million and insured for $27 million

It was damaged during in-orbit testing and has experienced some operational anomalies.

Location

Begin	End	Position
L: 1 Mar 1997	Apr 1997	47°E
May 1997	Dec 1997	62°E
Dec 1997	Jan 1997	64°E
May 1998		31.5°W
Technical data

Specifications

C-band

Ku-band

Transponder frequency plan

EIRP coverage (dBW)

C-band

Ku-band


Intelsat 801's C-band EIRP


Intelsat 801's Ku-band EIRP


 Intelsat 802

General

Designation	24846 / 97031A
Launch date	25 Jun 1997
Country of origin	International
Mission	Telecommunications
Geostationary orbit	174°E
Launch vehicle	Ariane V96

Value: $179 million

tested at 166°E

Technical data

Specifications

C-band

Ku-band

Transponder frequency plan

EIRP coverage (dBW)

C-band

Ku-band


Intelsat 802's C-band EIRP


Intelsat 802's Ku-band EIRP


 Intelsat 803

Also called NSS 803

General

Designation	24957 / 97053A
Launch date	23 Sep 1997
Country of origin	International
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V100

Insured for $187 million

Transfered to NSS on 30 Nov 1998

Location

Begin	End	Position
L: 23 Sep 1997	mid-Dec 1997	27.5°W (replaced 601)
Jan 1998		21.5°W
Technical data

Specifications

C-band

Ku-band

Transponder frequency plan

EIRP coverage (dBW)

C-band

Ku-band


Intelsat 803's C-band EIRP


Intelsat 803's Ku-band EIRP


 Intelsat 804

General

Designation	25110 / 97083A
Launch date	22 Dec 1997
Country of origin	International
Mission	Telecommunications
Geostationary orbit	64°E
Launch vehicle	Ariane V104

to replace the 801 which has problems. Tested at 44°E

Technical data

Specifications

C-band

Ku-band

Transponder frequency plan

EIRP coverage (dBW)

C-band

Ku-band


Intelsat 804's C-band EIRP


Intelsat 804's Ku-band EIRP


 Intelsat 805

Part of the 8A series

General

Designation	25371 / 98037A
Launch date	18 Jun 1998
Country of origin	International
Mission	Telecommunications
Geostationary orbit	55.5°W
Launch vehicle	Atlas 2AS #116
Technical data

EIRP coverage (dBW)

Specifications

C-band

Ku-band

C-band slot chart

slot #	Uplink (GHz)	Downlink (GHz)	Hemi A	Hemi B	Bandwidth (MHz)
7'	6.467	3.442	13'A	23'A	36
6'	6.507	3.482	12'B	22'B	36
5'	6.547	3.522	12'A	22'A	36
4'	6.587	3.562	11'B	21'B	36
3'	6.627	3.602	11'A	21'A	36
1'	5.908	3.683	10A	20A	36
1-2	5.970	3.745	11	21	72
3-4	6.050	3.825	12	22	72
5-6	6.130	3.905	13	23	72
7-8	6.220	3.995	14	24	72
9	6.280	4.055	15	25	36
10	6.320	4.095	16	26	36
11	6.360	4.135	17	27	36
12	6.4025	4.1775	18	28	41
Pol.:			A	B

It is possible to connect transponders with A pol up to both A or B pol down (same applies to pol B). A pol stands for uplink in LHCP & downlink in RHCP. B pol stands for uplink in RHCP & downlink in LHCP. If the polarization is switched to linear, replace LHCP by Horizontal and RHCP by Vertical.

C-band interconnection chart

Uplink beam	slot #	Downlink beam	Band
hemi A	1', 1-2, 3-4, 5-6, 7-8, 9, 10, 11, 12, 7', 6', 5', 4', 3'	hemi A	C
hemi A	1-2, 3-4, 5-6	spot 1	Ku
hemi B	1', 1-2, 3-4, 5-6, 7-8, 9, 10, 11, 12, 7', 6', 5', 4', 3'	hemi B	C
Ku-band slot chart

slot #	Uplink (GHz)	Downlink (GHz)	Spot 1	Bandwith (MHz)
1-2	14.0425	12.5475	361	77
3-4	14.125	12.630	362	72
5-6	14.205	12.701	363	72
Pol:	H	V
Ku-band interconnection chart

Uplink beam	slot #	Downlink beam	Band
spot 1	1-2, 3-4, 5-6	spot 1	Ku
spot 1	1-2, 3-4, 5-6	hemi A	C

Ku-band beacon: 12.501 GHz


Intelsat 805's EIRP


 Intelsat 806

Also called NSS 806

General

Designation	25239 / 98013A
Launch date	28 Feb 1998
Country of origin	International
Mission	Telecommunications
Geostationary orbit	40.5°W
Launch vehicle	Atlas 2AS #114

part of the 8A series. Tested at 55.5°W until late Apr 1998.

Transfered to NSS on 30 Nov 1998

Technical data

EIRP coverage (dBW)

Specifications

C-band

Ku-band

C-band slot chart

slot #	Uplink (GHz)	Downlink (GHz)	Hemi A	Hemi B	Bandwidth (MHz)
5'-6'	6.527	3.502	12'	22'	72
3'-4'	6.607	3.582	11'	21'	72
1'-2'	5.888	3.663	10	20	72
1-2	5.968	3.743	11	21	72
3	6.028	3.803	12A	22A	36
4	6.068	3.843	12B	22B	36
5	6.108	3.883	13A	23A	36
6	6.148	3.923	13B	23B	36
7	6.201	3.976	14A	24A	36
8	6.240	4.014	14B	24B	36
9	6.280	4.055	15	25	36
10	6.320	4.095	16	26	36
11	6.360	4.135	17	27	36
12	6.4025	4.1775	18	28	41
Pol.:			A	B

It is possible to connect transponders with A pol up to both A or B pol down (same applies to pol B). A pol stands for uplink in LHCP & downlink in RHCP. B pol stands for uplink in RHCP & downlink in LHCP. If the polarization is switched to linear, replace LHCP by Horizontal and RHCP by Vertical.

C-band interconnection chart

Uplink beam	slot #	Downlink beam	Band
hemi A	1'-2', 1-2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 3'-4', 5'-6'	hemi A	C
hemi A	1-2, 4/3-4, 6/5-6	spot 1	Ku
hemi B	1'-2', 1-2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 3'-4', 5'-6'	hemi B	C

4/3-4 means uplink in channel 4 C-band, downlink in channel 3-4 Ku-band

Ku-band slot chart

slot #	Uplink (GHz)	Downlink (GHz)	Spot 1	Bandwith (MHz)
1-2	14.0425	11.7475	261	77
3-4	14.125	11.830	262	72
5-6	14.205	11.910	263	72
Pol:	V	H
Ku-band interconnection chart

Uplink beam	slot #	Downlink beam	Band
spot 1	1-2, 3-4, 5-6	spot 1	Ku
spot 1	1-2, 3-4/4, 5-6/6	hemi A	C

3-4/4 means uplink in channel 3-4 Ku-band, downlink in channel 4 Ku-band

Ku-band beacon: 11.701 GHz


Intelsat 806's C- & Ku-band EIRP


 Intelsat KTV

Also called NSS KTV

General

Designation
Launch date	initially planned in late 1998
Country of origin	International
Mission	Telecommunications
Geostationary orbit	95°E
Launch vehicle	Ariane

Contract worth $100 million

Transfered to NSS on 30 Nov 1998

Technical data

EIRP coverage (dBW)

Fixed 1 and Steerable 1 Ku beams

Fixed 2 and Steerable 2 Ku beams

Specifications

Prime contractor	MMS
Platform	Eurostar 2000+
Mass at launch	3250 kg
Mass in orbit	2017 kg
Dry mass	1462 kg
Dimension	3.19 x 3.48 x 7.89 m
Solar array	32.32 m span
Stabilization	3-axis
DC power	7600 W
Design lifetime	12 years

The satellite can operate in collocation with up to 3 satellites

Ku-band

Main transponders	30
Backup transponders
Power	Fixed & Steerable beam 1: 101 W (TWTA) Fixed & Steerable beam 2: 105 W (TWTA)
Bandwidth	36 MHz
Coverage 1 EIRP	Fixed beam 1: India (dual polarization), 52-49 dBW Fixed beam 2: China, 50-32 dBW Steerable beam 1: Far East (dual polarization), 54-50 dBW Steerable beam 2: Indonesia/Malaysia, 53-47 dBW
G/T	Fixed beam 1: +4.4 - -1 dB/K Fixed beam 2: +4.8 - -3 dB/K Steerable beam 1: +8.7- 0 dB/K Steerable beam 2: +7.2 - -1 dB/K
SFD	-91 - -73 dBW/m²
Polarization	linear H/V
Frequencies	Uplink: 13.75-14 GHz / 14-14.25 GHz / 14.25-14.5 GHz  Downlink: 12.5-12.75 GHz / 10.95-11.2 GHz / 11.45-11.7 GHz

Beacon: 11.4515 GHz

12 transponders for the India beam and 6 transponders for the Far East beam are permanently assigned. Additionally, there are 12 transponders that can be switched on a transponder-by-transponder basis among 18 available channels. The chart below details the possibilities:

group	transp.	transp.	transp.	setting
1	F2 / 21	S1 / 353	S2 / 167	Any 2 of these 3 downlinks can be active at one time.
2	F2 / 22	S1 / 354	S2 / 168	Any 2 of these 3 downlinks can be active at one time.
3	F2 / 23	S1 / 355	S2 / 169	Any 2 of these 3 downlinks can be active at one time.
4	F2 / 24	S1 / 356	S2 / 170	Any 2 of these 3 downlinks can be active at one time.
5	F2 / 25	S1 / 357	S2 / 171	Any 2 of these 3 downlinks can be active at one time.
6	F2 / 26	S1 / 358	S2 / 172	Any 2 of these 3 downlinks can be active at one time.
Slot frequency plan (GHz)

Horizontal  Downlink	Horizontal  Uplink	Slot	Vertical  Uplink	Vertical  Downlink	Uplink/Downlink beams
12.524		13/313	13.768		F1/F1
	13.768	13X/313X		12.524	F1/F1
12.565		14/314	13.809		F1/F1
	13.809	14X/314X		12.565	F1/F1
12.606		15/315	13.850		F1/F1
	13.805	15X/315X		12.606	F1/F1
12.647		16/316	13.891		F1/F1
	13.891	16X/316X		12.647	F1/F1
12.688		17/317	13.932		F1/F1
	13.932	17X/317X		12.688	F1/F1
12.729		18/318	13.973		F1/F1
	13.973	18X/318X		12.729	F1/F1
12.524		61/313	14.024		S2/F1
	14.024	61X/313X		12.524	S2/F1
12.565		62/314	14.065		S2/F1
	14.065	62X/314X		12.565	S2/F1
12.606		63/315	14.106		S2/F1
	14.106	63X/315X		12.606	S2/F1
12.647		64/316	14.147		S2/F1
	14.147	64X/316X		12.647	S2/F1
12.688		65/317	14.188		S2/F1
	14.188	65X/317X		12.688	S2/F1
12.729		66/318	14.229		S2/F1
	14.229	66X/318X		12.729	S2/F1
10.971		21/21	14.021		F2/F2
11.012		22/22	14.062		F2/F2
11.053		23/23	14.103		F2/F2
11.094		24/24	14.144		F2/F2
11.135		25/25	14.185		F2/F2
11.176		26/26	14.226		F2/F2
12.524		53/353	13.768		S1/S1
	13.768	53X/353X		12.524	S1/S1
12.565		54/354	13.809		S1/S1
	13.809	54X/354X		12.565	S1/S1
12.606		55/355	13.850		S1/S1
	13.805	55X/355X		12.606	S1/S1
12.647		56/356	13.891		S1/S1
	13.891	56X/356X		12.647	S1/S1
12.688		57/357	13.932		S1/S1
	13.932	57X/357X		12.688	S1/S1
12.729		58/358	13.973		S1/S1
	13.973	58X/358X		12.729	S1/S1
11.471		67/167	14.271		S2/S2
11.512		68/168	14.312		S2/S2
11.553		69/169	14.353		S2/S2
11.594		70/170	14.394		S2/S2
11.635		71/171	14.435		S2/S2
11.676		72/172	14.476		S2/S2


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Intelsat KTV's Ku-band F1 & S1 EIRP


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Intelsat KTV's Ku-band F2 & S2 EIRP


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 Intelsat 901

General

Designation
Launch date	July 2000
Country of origin	International
Mission	Telecommunications
Geostationary orbit	60°E
Launch vehicle	Proton

Contract for the construction of the 2 first satellites is worth $600 million

launch cost: $109 million

Technical data

Specifications

C-band

Ku-band

Transponder frequency plan


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 Intelsat 902

General

Designation
Launch date	late 2000
Country of origin	International
Mission	Telecommunications
Geostationary orbit	62°E
Launch vehicle	Ariane 5
Technical data

Specifications

C-band

Ku-band

Transponder frequency plan


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 Intelsat 903

General

Designation
Launch date
Country of origin	International
Mission	Telecommunications
Geostationary orbit	24.5°W
Launch vehicle	Ariane 5
Technical data

Specifications

C-band

Ku-band

Transponder frequency plan


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 Intelsat 904

General

Designation
Launch date
Country of origin	International
Mission	Telecommunications
Geostationary orbit	34.5°W
Launch vehicle	Ariane 5
Technical data

Specifications

C-band

Ku-band

Transponder frequency plan


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 Intelsat 905

General

Designation
Launch date	2002
Country of origin	International
Mission	Telecommunications
Geostationary orbit	27.5°W
Launch vehicle
Technical data

Specifications

C-band

Ku-band

Transponder frequency plan


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 Program: Intersputnik

Intersputnik is an organization created in 1971 by the former USSR; started working in 1972. It was aimed to break Intelsat's monopoly (they didn't expect members not to belong to other telecommunications organizations). In 1997, 22 states belonged to the organization (Intercosmos members and other friend states).

Intersputnik used Molniya satellites before turning to geostationary satellites (Raduga, Gorizont, Gals and Express). Earth stations use typical 12 m antennas.

Informcosmos is an important partner

In June 1997 it was announced that Intersputnik and Lockheed Martin had formed a joint venture to become a global satellite operator. The new company is called Lockheed Martin Interputnik Ltd.. The new company should be operating from numerous slots around the world. The deployment should start by slots in Asia to serve the CIS.

In Oct 1998 LMI leased two slots at 130°E & 142.5°E from Panda Communications Ltd which is a joint venture between Tonga and a russian company named Inspace Communications.

In Jan 1999 LMI 2 is announced at 83°W in 2000 (16 Ku & 28 C-band transp.), LMI 3 at 3°W also in 2000 (16 Ku & 28 C-band transp.), LMI 4 at 130°E in 2001 (16 Ku & 28 C-band transp.)


Program: Intersputnik

LMI 1

see also Gorizont and Express


 LMI 1

General

Designation
Launch date	late 1998
Country of origin	?
Mission	Telecommunications
Geostationary orbit	75°E
Launch vehicle	Proton

Main control center in Dubna, near Moscow. A second center is located in Australia. Cost: approx $3 million per center

Technical data

EIRP coverage (dBW)

C-band, broad (A) beam

C-band, narrow (B) beam

Ku-band, north (A1) beam

Ku-band, south (A2) beam

Specifications

Prime contractor	LM
Platform	A2100AX
Mass at launch
Dry mass	1730 kg
Dimension
Solar array
Stabilization	3-axis
DC power	7560 W
Design lifetime	15 years
C-band

Main transponders	28
Backup transponders	4
Power	45 W
Bandwidth	36 MHz
Coverage	A: Africa, the Middle East, Australasia and South East Asia excluding central Asia B: central Asia
EIRP max	38 dBW
G/T max	-3.5 dB/K
Polarization	linear H/V
Frequencies	Uplink: A: 5.725-6.025 GHz; B: 6.425-6.725 GHz Downlink: A: 3.7-4.0 GHz; B: 3.4-3.7 GHz
Ku-band

Main transponders	16
Backup transponders	6
Power	90 & 135 W
Bandwidth	27 MHz
Coverage	A1: Northern part of the North hemisphere including Russia, part of China to Irak A2: Central part of the North hemisphere, including the Middle East, India, Thailand, Vietnam and most of China
EIRP max	northern: 48 dBW southern: 47 dBW
G/T max	northern beam: +2.5 dB/K southern beam: +0.35 dB/K
Polarization	linear H/V
Frequencies	Uplink: 13.750-14.000 GHz Downlink: 12.5-12.75 GHz


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LMI 1's C-band broad (A) beam


LMI 1's C-band narrow (B) beam


LMI 1's ku-band north (A1) beam


LMI 1's ku-band south (A2) beam


Intersputnik 8
 Program: Intersputnik 8

Russian telecommunication satellite program lead by Intersputnik. A special purpose company was formed with Daimler Benz Aerospace (Germany), Aerospatiale (France) and SS/L named Space Alliance.

First satellite to be launched in late 1998 over the Indian Ocean. Another one will be positioned over the Atlantic Ocean in mid-1999.

Technical data

Specifications

Prime contractor	Aerospatiale
Platform
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization
DC power	4000 W
Design lifetime	> 15 years

SS/Loral will manufacture basic subsystems such as satellite repeaters and Daimler-Benz Aerospace will provide antennas, solar arrays and an attitude control system.

C-band

Main transponders	24
Backup transponders
Power
Bandwidth	36 MHz?
Coverage	global and regional
EIRP max	37 - 40 dBW
Polarization
Ku-band

Main transponders	16
Backup transponders
Power
Bandwidth	36, 54 and 72 MHz
Coverage	steerable spot beam
EIRP max	50 dBW
Polarization	linear


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 IRAS

Infra Red Astronomy Satellite

General

Designation	13777 / 83004A
Launch date	26 Jan 1983
Country of origin	Netherlands, United Kingdom and United States
Mission	Scientific: IR astronomy
Perigee/Apogee	884/903 km
Inclination	99°
Period	102.9 min
Launch vehicle	Thor Delta #166

It mapped 250,000 IR sources in the 300 days before its helium coolant was exhausted.

End of life

Out of service	23 Nov 1983
External resources

http://www.gsfc.nasa.gov/astro/iras/iras_home.html

Technical data

Specifications

Industrial responsabilities	Netherlands Aerospace Agency (bus) NASA Ames Research Center, JPL (telescope) SERC (TT&C and data collection) Prime contractors: ICIRAS (bus) Ball Aerospace (telescope) Perkin-Elmer (optics)
Mass at launch	1077 kg
Telescope mass	810 kg
Diameter	2.2 m
Height	3.6 m
Solar array	5 m² (2 panels)
Stabilization	3-axis
DC power	EOL: 500 W
Design lifetime	11 months
Payload

Ritchey-Chretien-type reflecting telescope with a local plane array of 62 IR detectors surrounded by a dewar containing 475 l of liquid helium. Plus 2 photometers and a low-resolution spectrometer.

Telescope diameter	0.57 m
Focal length	5.5 m
Field of view	30 arcmin

Spectral range:

IR Telescope	(band 1) 8.5-15 µm (band 2) 19-30 µm (band 3) 40-80 µm (band 4) 83-119 µm
Spectrometer	7.4-23 µm
Short wavelength photometer	4.1-8 µm

Cooling system by evaporated helium

Temperature control	2 K
Telemetry/data	S-band (1 Mbps)


Iridium
 Program: Iridium

As the program was originaly thought with 77 satellites, it was named after the 77th element in the periodical table: Iridium

The Iridium system is owned by Iridium LLC, an international consortium of 17 investor organizations representing telecommunications and industrial companies worldwide, with Motorola Satellite Communications Group serving as the prime contractor. The investors are: Iridium Africa Corporation, Iridium Canada, Inc., Iridium China (Hong Kong), Ltd., Iridium India Telecom Limited, Iridium Middle East Corporation, Iridium SudAmerica Corporation, Khrunichev State Research and Production Space Center of the Russian Federation, Korea Mobile Telecommunications of Korea, Lockheed Martin Corporation and Motorola, Inc. of the U.S., Nippon Iridium Corporation of Japan, o.tel.o communications GmbH of Germany, Pacific Electric Wire & Cable Co., Ltd. of Taiwan, Raytheon Company of the U.S., Sprint Corporation of the U.S., STET Group - Societa Finanziara Telefonica per Azioni of Italy, and Thai Satellite Telecommunications Co., Ltd. of Thailand.

The cost of the global system is close to $7 billion.  The commercial launch date is 23 Sep 1998  Cost per satellite: $62 million

Iridium next generation (called MacroCell): a system with 96 satellites capable of handling 384 kbps communications (4.8 kbps with the 1st system)

In Jun 1999 the company is reported in serious trouble and close of bankrupcy

External resources

http://www.iridium.com/

http://www2.satellite.eu.org/sat/vsohp/iridium.html

http://www2.gsoc.dlr.de/satvis/iridiumhelp.html

Technical data

Slots and planes

slot	satellites #
plane 1 (158)	62, 63, 64, 65, 66, 67, 68, 70, 72, 73, 74, 75
plane 2 (189)	11, 20, 22, 23, 24, 25, 26, 45, 46, 47, 48, 49, 69, 76, 71
plane 3 (221)	27, 28, 29, 30, 31, 32, 33, 55, 57, 58, 59, 60
plane 4 (252)	4, 5, 6, 7, 8, 19, 34, 35, 36, 37, 51, 61
plane 5 (284)	9, 10, 11, 12, 13, 14, 16, 50, 52, 53, 54, 56, 83, 84, 85, 86
plane 6 (316)	15, 17, 18, 20, 21, 38, 39, 40, 41, 42, 43, 44, 77, 79, 80, 81, 82

In early 1999 12 satellites are reported as failed

Constellation overview

Orbit type	LEO
Orbit range	780 km, circular
Nb of satellites	66 + 7 backup
Nb of planes	6
Inclination	86.4°
Nb beams per satellite	48
Coverage	4700 km²
Modulation	FNMA/TDMA
Mobile frequencies	Uplink: L-band Downlink: 1610-1626.5 MHz
Satellite mass	725 kg
Coverage	all longitudes, 80N - 80S latitudes
Operational date	1998 (planned)


Program: Iridium

Iridium 04 Iridium 05 Iridium 06 Iridium 07 Iridium 08 Iridium 09 Iridium 10 Iridium 11 Iridium 12 Iridium 13 Iridium 14 Iridium 14A Iridium 15 Iridium 16	Iridium 17 Iridium 18 Iridium 19 Iridium 20 Iridium 21 Iridium 21A Iridium 22 Iridium 23 Iridium 24 Iridium 25 Iridium 26 Iridium 27 Iridium 28 Iridium 29	Iridium 30 Iridium 31 Iridium 32 Iridium 33 Iridium 34 Iridium 35 Iridium 36 Iridium 37 Iridium 38 Iridium 39 Iridium 40 Iridium 41 Iridium 42 Iridium 43	Iridium 44 Iridium 45 Iridium 46 Iridium 47 Iridium 48 Iridium 49 Iridium 50 Iridium 51 Iridium 52 Iridium 53 Iridium 54 Iridium 55 Iridium 56 Iridium 57	Iridium 58 Iridium 59 Iridium 60 Iridium 61 Iridium 62 Iridium 63 Iridium 64 Iridium 65 Iridium 66 Iridium 67 Iridium 68 Iridium 69 Iridium 70 Iridium 71	Iridium 72 Iridium 73 Iridium 74 Iridium 75 Iridium 76 Iridium 77 Iridium 78 Iridium 79 Iridium 80 Iridium 81 Iridium 82 Iridium 83 Iridium 84 Iridium 85	Iridium 86 Iridium 87 Iridium 88 Iridium 89


Iridium's specifications

Prime contractor	Lockheed Martin
Platform	Iridium (LM700 bus)
Mass at launch	689 kg
Mass in orbit
Dry mass	556 kg
Dimension	1 x 2 m
Solar array
Stabilization	3-axis
DC power
Design lifetime	5 years


Iridium's payload

Modulation	TDMA (Time Division Multiple Access)
Capacity	3840 phone circuits
Voice	4800 bps
Fax	2400 bps
Data	2400 bps
Total Bandwith	200 MHz
Mobile links	1.5/1.6 GHz
Intersatellite links	Ka-band: 18.8-20.2/27.5-30 GHz

On-board commutation. Inter satellite links, each satellite talks with its 4 neighbors

Communications between the gateways and the satellites: Uplink: 29.1-29.3 GHz, Downlink: 19.4-19.6 GHz

Payload built by Motorola's Satcom division in Chandler, Arizona.


 Iridium 04

Also called Iridium SV004

General

Designation	24796 / 97020E
Launch date	5 May 1997
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	771/783 km
Inclination	86.4°
Launch vehicle	Delta 2 #242
Technical data

Specifications

Payload


 Iridium 05

Also called Iridium SV005

General

Designation	24795 / 97020D
Launch date	5 May 1997
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	771/783 km
Inclination	86.4°
Launch vehicle	Delta 2 #242
Technical data

Specifications

Payload


 Iridium 06

Also called Iridium SV006

General

Designation	24794 / 97020C
Launch date	5 May 1997
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	774/780 km
Inclination	86.4°
Launch vehicle	Delta 2 #242
Technical data

Specifications

Payload


 Iridium 07

Also called Iridium SV007

General

Designation	24793 / 97020B
Launch date	5 May 1997
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	773/781 km
Inclination	86.4°
Launch vehicle	Delta 2 #242
Technical data

Specifications

Payload


 Iridium 08

Also called Iridium SV008

General

Designation	24972 / 97020A
Launch date	5 May 1997
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	776/779 km
Inclination	86.4°
Launch vehicle	Delta 2 #242
Technical data

Specifications

Payload


 Iridium 09

Also called Iridium SV009

General

Designation	24839 / 97030D
Launch date	18 Jun 1997
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	774/778 km
Inclination	86.4°
Launch vehicle	Proton #249
Technical data

Specifications

Payload


 Iridium 10

Also called Iridium SV010

General

Designation	24838 / 97030C
Launch date	18 Jun 1997
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	773/780 km
Inclination	86.4°
Launch vehicle	Proton #249
Technical data

Specifications

Payload


 Iridium 11

Also called Iridium SV011

General

Designation	24842 / 97030G
Launch date	18 Jun 1997
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	770 km
Inclination	86.4°
Launch vehicle	Proton #249

Currently on reserve orbit

Technical data

Specifications

Payload


 Iridium 12

Also called Iridium SV012

General

Designation	24837 / 97030B
Launch date	18 Jun 1997
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	772/781 km
Inclination	86.4°
Launch vehicle	Proton #249
Technical data

Specifications

Payload


 Iridium 13

Also called Iridium SV013

General

Designation	24840 / 97030E
Launch date	18 Jun 1997
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	774/780 km
Inclination	86.4°
Launch vehicle	Proton #249
Technical data

Specifications

Payload


 Iridium 14

Also called Iridium SV014

General

Designation	24836 / 97030A
Launch date	18 Jun 1997
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	775/778 km
Inclination	86.4°
Launch vehicle	Proton #249
End of life

Out of service	yes
Cause
Decay
Technical data

Specifications

Payload


 Iridium 14A

General

Designation	25777 / 99032A
Launch date	11 Jun 1999
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee
Inclination
Launch vehicle	Long March 2C #55
Technical data

Specifications

Payload


 Iridium 15

Also called Iridium SV015

General

Designation	24869 / 97034A
Launch date	9 Jul 1997
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780 km
Inclination	86.4°
Launch vehicle	Delta #244

Was to be launched with Proton #249 but was dropped during a loading operation in the US.

Technical data

Specifications

Payload


 Iridium 16

Also called Iridium SV016

General

Designation	24841 / 97030F
Launch date	18 Jun 1997
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	775/779 km
Inclination	86.4°
Launch vehicle	Proton #249
Technical data

Specifications

Payload


 Iridium 17

Also called Iridium SV017

General

Designation	24870 / 97034B
Launch date	9 Jul 1997
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780 km
Inclination	86.4°
Launch vehicle	Delta #244
Technical data

Specifications

Payload


 Iridium 18

Also called Iridium SV018

General

Designation	24871 / 97034C
Launch date	9 Jul 1997
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780 km
Inclination	86.4°
Launch vehicle	Delta #244
Technical data

Specifications

Payload


 Iridium 19

Also called Iridium SV019

General

Designation	24965 / 97056A
Launch date	27 Sep 1997
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780 km
Inclination	86.4°
Launch vehicle	Delta #248
Technical data

Specifications

Payload


 Iridium 20

Also called Iridium SV020

General

Designation	24872 / 97034D
Launch date	9 Jul 1997
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780 km
Inclination	86.4°
Launch vehicle	Delta #244
Technical data

Specifications

Payload


 Iridium 21

Also called Iridium SV021

General

Designation	24873 / 97034E
Launch date	9 Jul 1997
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	626/656 km
Inclination	86.3°
Launch vehicle	Delta #244
End of life

Out of service	9 Jul 1997
Cause	no communications with the spacecraft
Decay
Technical data

Specifications

Payload


 Iridium 21A

General

Designation	25778 / 99032B
Launch date	11 Jun 1999
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee
Inclination
Launch vehicle	Long March 2C #55
Technical data

Specifications

Payload


 Iridium 22

Also called Iridium SV022

General

Designation	24907 / 97043E
Launch date	21 Aug 1997
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780 km
Inclination	86.4°
Launch vehicle	Delta #246
Technical data

Specifications

Payload


 Iridium 23

Also called Iridium SV023

General

Designation	24906 / 97043D
Launch date	21 Aug 1997
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780 km
Inclination	86.4°
Launch vehicle	Delta #246
Technical data

Specifications

Payload


 Iridium 24

Also called Iridium SV024

General

Designation	24905 / 97043C
Launch date	21 Aug 1997
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780 km
Inclination	86.4°
Launch vehicle	Delta #246
Technical data

Specifications

Payload


 Iridium 25

Also called Iridium SV025

General

Designation	24904 / 97043B
Launch date	21 Aug 1997
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780 km
Inclination	86.4°
Launch vehicle	Delta #246
Technical data

Specifications

Payload


 Iridium 26

Also called Iridium SV026

General

Designation	24903 / 97043A
Launch date	21 Aug 1997
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780 km
Inclination	86.4°
Launch vehicle	Delta #246
Technical data

Specifications

Payload


 Iridium 27

Also called Iridium SV027

General

Designation	24947 / 97051D
Launch date	14 Sep 1997
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780 km
Inclination	86.4°
Launch vehicle	Proton #252
End of life

Out of service	yes
Cause	failed during the maneuver to its operational orbit.
Decay
Technical data

Specifications

Payload


 Iridium 28

Also called Iridium SV028

General

Designation	24948 / 97051E
Launch date	14 Sep 1997
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780 km
Inclination	86.4°
Launch vehicle	Proton #252
Technical data

Specifications

Payload


 Iridium 29

Also called Iridium SV029

General

Designation	24944 / 97051A
Launch date	14 Sep 1997
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780 km
Inclination	86.4°
Launch vehicle	Proton #252
Technical data

Specifications

Payload


 Iridium 30

Also called Iridium SV030

General

Designation	24949 / 97051F
Launch date	14 Sep 1997
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780 km
Inclination	86.4°
Launch vehicle	Proton #252
Technical data

Specifications

Payload


 Iridium 31

Also called Iridium SV031

General

Designation	24950 / 97051G
Launch date	14 Sep 1997
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780 km
Inclination	86.4°
Launch vehicle	Proton #252
Technical data

Specifications

Payload


 Iridium 32

Also called Iridium SV032

General

Designation	24945 / 97051B
Launch date	14 Sep 1997
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780 km
Inclination	86.4°
Launch vehicle	Proton #252
Technical data

Specifications

Payload


 Iridium 33

Also called Iridium SV033

General

Designation	24946 / 97051C
Launch date	14 Sep 1997
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780 km
Inclination	86.4°
Launch vehicle	Proton #252
Technical data

Specifications

Payload


 Iridium 34

Also called Iridium SV034

General

Designation	24969 / 97056E
Launch date	27 Sep 1997
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780 km
Inclination	86.4°
Launch vehicle	Delta #248
Technical data

Specifications

Payload


 Iridium 35

Also called Iridium SV035

General

Designation	24968 / 97056D
Launch date	27 Sep 1997
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780 km
Inclination	86.4°
Launch vehicle	Delta #248
Technical data

Specifications

Payload


 Iridium 36

Also called Iridium SV036

General

Designation	24967 / 97056C
Launch date	27 Sep 1997
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780 km
Inclination	86.4°
Launch vehicle	Delta #248
Technical data

Specifications

Payload


 Iridium 37

Also called Iridium SV037

General

Designation	24966 / 97056B
Launch date	27 Sep 1997
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780 km
Inclination	86.4°
Launch vehicle	Delta #248
Technical data

Specifications

Payload


 Iridium 38

Also called Iridium SV038

General

Designation	25043 / 97069E
Launch date	9 Nov 1997
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780 km
Inclination	86.4°
Launch vehicle	Delta #250
Technical data

Specifications

Payload


 Iridium 39

Also called Iridium SV039

General

Designation	25042 / 97069D
Launch date	9 Nov 1997
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780 km
Inclination	86.4°
Launch vehicle	Delta #250
Technical data

Specifications

Payload


 Iridium 40

Also called Iridium SV040

General

Designation	25041 / 97069C
Launch date	9 Nov 1997
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780 km
Inclination	86.4°
Launch vehicle	Delta #250
Technical data

Specifications

Payload


 Iridium 41

Also called Iridium SV041

General

Designation	25040 / 97069B
Launch date	9 Nov 1997
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780 km
Inclination	86.4°
Launch vehicle	Delta #250
Technical data

Specifications

Payload


 Iridium 42

Also called Iridium SV042

General

Designation	25077 / 97077A
Launch date	8 Dec 1997
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780 km
Inclination	86.4°
Launch vehicle	Long March 2C #47
Technical data

Specifications

Payload


 Iridium 43

Also called Iridium SV043

General

Designation	25039 / 97069A
Launch date	9 Nov 1997
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780 km
Inclination	86.4°
Launch vehicle	Delta #250
Technical data

Specifications

Payload


 Iridium 44

Also called Iridium SV044

General

Designation	25078 / 97077B
Launch date	8 Dec 1997
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780 km
Inclination	86.4°
Launch vehicle	Long March 2C
End of life

Out of service
Cause	hardware failure
Decay
Technical data

Specifications

Payload


 Iridium 45

Also called Iridium SV045

General

Designation	25104 / 97082A
Launch date	20 Dec 1997
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780 km
Inclination	86.4°
Launch vehicle	Delta #251
Technical data

Specifications

Payload


 Iridium 46

Also called Iridium SV046

General

Designation	25105 / 97082B
Launch date	20 Dec 1997
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780 km
Inclination	86.4°
Launch vehicle	Delta #251
Technical data

Specifications

Payload


 Iridium 47

Also called Iridium SV047

General

Designation	25106 / 97082C
Launch date	20 Dec 1997
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780 km
Inclination	86.4°
Launch vehicle	Delta #251
Technical data

Specifications

Payload


 Iridium 48

Also called Iridium SV048

General

Designation	25107 / 97082D
Launch date	20 Dec 1997
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780 km
Inclination	86.4°
Launch vehicle	Delta #251
Technical data

Specifications

Payload


 Iridium 49

Also called Iridium SV049

General

Designation	25108 / 97082E
Launch date	20 Dec 1997
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780 km
Inclination	86.4°
Launch vehicle	Delta #251
Technical data

Specifications

Payload


 Iridium 50

Also called Iridium SV050

General

Designation	25169 / 98010A
Launch date	18 Feb 1998
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780 km
Inclination	86.4°
Launch vehicle	Delta #254
Technical data

Specifications

Payload


 Iridium 51

Also called Iridium SV051

General

Designation	25262 / 98018A
Launch date	25 Mar 1998
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780 km
Inclination	86.4°
Launch vehicle	Long March 2 #48
Technical data

Specifications

Payload


 Iridium 52

Also called Iridium SV052

General

Designation	25171 / 98010C
Launch date	18 Feb 1998
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780 km
Inclination	86.4°
Launch vehicle	Delta #254
Technical data

Specifications

Payload


 Iridium 53

Also called Iridium SV053

General

Designation	25172 / 98010D
Launch date	18 Feb 1998
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780 km
Inclination	86.4°
Launch vehicle	Delta #254
Technical data

Specifications

Payload


 Iridium 54

Also called Iridium SV054

General

Designation	25173 / 98010E
Launch date	18 Feb 1998
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780 km
Inclination	86.4°
Launch vehicle	Delta #254
Technical data

Specifications

Payload


 Iridium 55

Also called Iridium SV055

General

Designation	25272 / 98019A
Launch date	30 Mar 1998
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780 km
Inclination	86.4°
Launch vehicle	Delta #256
Technical data

Specifications

Payload


 Iridium 56

Also called Iridium SV056

General

Designation	25170 / 98010B
Launch date	18 Feb 1998
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780 km
Inclination	86.4°
Launch vehicle	Delta #254
Technical data

Specifications

Payload


 Iridium 57

Also called Iridium SV057

General

Designation	25273 / 98019B
Launch date	30 Mar 1998
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780 km
Inclination	86.4°
Launch vehicle	Delta #255
Technical data

Specifications

Payload


 Iridium 58

Also called Iridium SV058

General

Designation	25274 / 98019C
Launch date	30 Mar 1998
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780 km
Inclination	86.4°
Launch vehicle	Delta #255
Technical data

Specifications

Payload


 Iridium 59

Also called Iridium SV059

General

Designation	25275 / 98019D
Launch date	30 Mar 1998
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780 km
Inclination	86.4°
Launch vehicle	Delta #255
Technical data

Specifications

Payload


 Iridium 60

Also called Iridium SV060

General

Designation	25276 / 98019E
Launch date	30 Mar 1998
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780 km
Inclination	86.4°
Launch vehicle	Delta #255
Technical data

Specifications

Payload


 Iridium 61

Also called Iridium SV061

General

Designation	25263 / 98018B
Launch date	25 Mar 1998
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780 km
Inclination	86.4°
Launch vehicle	Long March 2 #48
Technical data

Specifications

Payload


 Iridium 62

Also called Iridium SV062

General

Designation	25285 / 98021A
Launch date	7 Apr 1998
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780 km
Inclination	86.4°
Launch vehicle	Proton #256
Technical data

Specifications

Payload


 Iridium 63

Also called Iridium SV063

General

Designation	25286 / 98021B
Launch date	7 Apr 1998
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780 km
Inclination	86.4°
Launch vehicle	Proton #256
Technical data

Specifications

Payload


 Iridium 64

Also called Iridium SV064

General

Designation	25287 / 98021C
Launch date	7 Apr 1998
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780 km
Inclination	86.4°
Launch vehicle	Proton #256
Technical data

Specifications

Payload


 Iridium 65

Also called Iridium SV065

General

Designation	25288 / 98021D
Launch date	7 Apr 1998
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780 km
Inclination	86.4°
Launch vehicle	Proton #256
Technical data

Specifications

Payload


 Iridium 66

Also called Iridium SV062

General

Designation	25289 / 98021E
Launch date	7 Apr 1998
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780 km
Inclination	86.4°
Launch vehicle	Proton #256
Technical data

Specifications

Payload


 Iridium 67

Also called Iridium SV067

General

Designation	25290 / 98021F
Launch date	7 Apr 1998
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780 km
Inclination	86.4°
Launch vehicle	Proton #256
Technical data

Specifications

Payload


 Iridium 68

Also called Iridium SV068

General

Designation	25291 / 98021G
Launch date	7 Apr 1998
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780 km
Inclination	86.4°
Launch vehicle	Proton #256
Technical data

Specifications

Payload


 Iridium 69

Also called Iridium SV069

General

Designation	25319 / 98026A
Launch date	2 May 1998
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780 km
Inclination	86.4°
Launch vehicle	Long March 2 #49
Technical data

Specifications

Payload


 Iridium 70

Also called Iridium SV070

General

Designation	25342 / 98032A
Launch date	17 May 1998
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780 km
Inclination	86.4°
Launch vehicle	Delta #257
Technical data

Specifications

Payload


 Iridium 71

Also called Iridium SV071

General

Designation	25320 / 98026B
Launch date	2 May 1998
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780 km
Inclination	86.4°
Launch vehicle	Long March 2 #49
End of life

Out of service
Cause	hardware failure
Decay
Technical data

Specifications

Payload


 Iridium 72

Also called Iridium SV072

General

Designation	25343 / 98032B
Launch date	17 May1998
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780 km
Inclination	86.4°
Launch vehicle	Delta #257
Technical data

Specifications

Payload


 Iridium 73

Also called Iridium SV073

General

Designation	25344 / 98032C
Launch date	17 May 1998
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780 km
Inclination	86.4°
Launch vehicle	Delta #257
Technical data

Specifications

Payload


 Iridium 74

Also called Iridium SV074

General

Designation	25345 / 98032D
Launch date	17 May 1998
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780 km
Inclination	86.4°
Launch vehicle	Delta #257
Technical data

Specifications

Payload


 Iridium 75

Also called Iridium SV075

General

Designation	25346 / 98032E
Launch date	17 May 1998
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780 km
Inclination	86.4°
Launch vehicle	Delta #257
Technical data

Specifications

Payload


 Iridium 76

Also called Iridium SV076

General

Designation	25432 / 98048B
Launch date	19 Aug 1998 at 23:01 UT
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee
Inclination
Launch vehicle	Long March 2 #52
Technical data

Specifications

Payload


 Iridium 77

Also called Iridium SV077

General

Designation	25471 / 98051E
Launch date	8 Sept 1998 at 21:13 UT
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee
Inclination
Launch vehicle	Delta #260
Technical data

Specifications

Payload


 Iridium 78

General

Designation	25431 / 98048A
Launch date	19 Aug 1998 at 23:01 UT
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee
Inclination
Launch vehicle	Long March 2 #52
Technical data

Specifications

Payload


 Iridium 79

Also called Iridium SV079

General

Designation	25470 / 98051D
Launch date	8 Sept 1998 at 21:13 UT
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee
Inclination
Launch vehicle	Delta #260
Technical data

Specifications

Payload


 Iridium 80

Also called Iridium SV080

General

Designation	25469 / 98051C
Launch date	8 Sept 1998 at 21:13 UT
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee
Inclination
Launch vehicle	Delta #260
Technical data

Specifications

Payload


 Iridium 81

Also called Iridium SV081

General

Designation	25468 / 98051B
Launch date	8 Sept 1998 at 21:13 UT
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee
Inclination
Launch vehicle	Delta #260
Technical data

Specifications

Payload


 Iridium 82

Also called Iridium SV082

General

Designation	25467 / 98051A
Launch date	8 Sept 1998 at 21:13 UT
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee
Inclination
Launch vehicle	Delta #260
Technical data

Specifications

Payload


 Iridium 83

Also called Iridium SV083

General

Designation	25531 / 98066E
Launch date	6 Nov 1998
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee
Inclination
Launch vehicle	Delta 2 #262
Technical data

Specifications

Payload


 Iridium 84

Also called Iridium SV084

General

Designation	25530 / 98066D
Launch date	6 Nov 1998
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee
Inclination
Launch vehicle	Delta 2 #262
Technical data

Specifications

Payload


 Iridium 85

Also called Iridium SV085

General

Designation	25529 / 98066C
Launch date	6 Nov 1998
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee
Inclination
Launch vehicle	Delta 2 #262
Technical data

Specifications

Payload


 Iridium 86

Also called Iridium SV086

General

Designation	25528 / 98066B
Launch date	6 Nov 1998
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee
Inclination
Launch vehicle	Delta 2 #262
Technical data

Specifications

Payload


 Iridium 87

General

Designation	25527 / 98066A
Launch date	6 Nov 1998
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee
Inclination
Launch vehicle	Delta 2 #262
Technical data

Specifications

Payload


 Iridium 88

Also called Iridium SV088

General

Designation	25577 / 98074A
Launch date	19 Dec 1998
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780 km
Inclination	86.4°
Launch vehicle	Long March 2 #53
Technical data

Specifications

Payload


 Iridium 89

Also called Iridium SV089

General

Designation	25578 / 98074B
Launch date	19 Dec 1998
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780 km
Inclination	86.4°
Launch vehicle	Long March 2 #53
Technical data

Specifications

Payload


 Program: IRS

Indian Remote Sensing

Indian program to develop an indigenous capability to image Earth, particulary India. Mission: ground water exploration, land use, forest and flood mapping, inventory of surface water.

Antrix markets the images


Program: IRS

IRS 1A

IRS 1B

IRS 1C

IRS 1D

IRS 1E

IRS 2A

IRS P2

IRS P3

IRS P4

IRS P5

IRS P6

IRS P7


IRS's specifications

Prime contractor	ISRO
Mass at launch	1150 kg
Dimension	1.6 x 1.56 x 1.1 m
Solar array	8.5 m²
Stabilization	3-axis
DC Power	620 W
Design lifetime	3 years

Telemetry in S-band, Command in VHF and S-band; X-band beacon


IRS's payload

LISS 1 (Linear Imaging Self Scanner) with CCD detector arrays

Wavebands	0.45-0.52 µm (visible): sedimetation and coastal studies 0.52-0.59 µm (visible): vegetation. rock and soil discremination 0.62-0.68 µm (visible): chlorophyll absorption in vegetation. rock/soil 0.77-0.86 µm (IR): moisture in vegetation. land/water discremination
Resolution	72.5 m
Swath width	148 km
Data downlinked in S-band

LISS 2 A & B (2 identical push-broom scanners with CCD detector arrays

Wavebands	same as LISS 1
Resolution	36.25 m
Swath width	74 km either side of ground track with 3 km overlap: total 145 km
Data downlinked in X-band

IRS 1C and D to feature near and shortwave IR sensors with 20 m resolution (color); 10 m (monochrome)


 IRS 1A

General

Designation	18960 / 88021A
Launch date	17 Mar 1988
Country of origin	India
Mission	Remote sensing
Perigee/Apogee	893/913 km
Inclination	98.8°
Period	103.1 min
Launch vehicle	Semiorka A1
Mass at launch	960 kg

First commercial satellite launched by the CIS's organization Glavcosmos.

Technical data

Specifications

Payload


 IRS 1B

General

Designation	21688 / 91061A
Launch date	29 Aug 1991
Country of origin	India
Mission	Remote sensing
Perigee/Apogee	890/917 km
Inclination	99.1°
Period	103.1 min
Launch vehicle	Semiorka A1
Technical data

Specifications

Payload


 IRS 1E

General

Launch date	20 Sep 1993
Country of origin	India
Mission	Remote sensing
Launch vehicle	PSLV #1
End of life

Out of service	20 Sep 1993
Cause	launcher failure, the payload ended in the ocean


 IRS P2

General

Designation	23323 / 94068A
Launch date	15 Oct 1994
Country of origin	India
Mission	Remote sensing
Perigee/Apogee	818/820 km
Inclination	98.7°
Period	102.3 min
Launch vehicle	PSLV #2

The spacecraft is in a Sun-synchronous orbit and carries a linear imaging self-scanner camera. The images will be marketed through a private company in the U.S.A.  An X-ray telescope is also onboard for astronomical observations.

Technical data

Specifications

Prime contractor	ISRO
Platform	IRS P
Mass at launch	870 kg
Mass in orbit
Length
Width
Height
Stabilization	3-axis
DC power
Design lifetime
LISS 2 A & B (2 identical push-broom scanners with CCD detector arrays

Wavebands	0.45-0.52 µm (visible): sedimetation and coastal studies 0.52-0.59 µm (visible): vegetation. rock and soil discremination 0.62-0.68 µm (visible): chlorophyll absorption in vegetation. rock/soil 0.77-0.86 µm (IR): moisture in vegetation. land/water discremination
Resolution	32 x 37 m
Swath width	67 km


 IRS 1C

General

Designation	23751 / 95072A
Launch date	28 Dec 1995 at 06:45 UT
Country of origin	India
Mission	Remote sensing
Perigee/Apogee	816/818 km (sun-synchronous, Descending node: 10:30)
Inclination	98.6°
Period	101 min (revisit: 5 days)
Launch vehicle	Molniya
Launch site	Tyuratam

This was the first Russian launch into a retrograde (99 degree) orbit using the Molniya-M four stage rocket; earlier Russian retrograde launches used the Vostok rocket which has now been retired. The The Block-I third stage appears to have been suborbital, the first time such a flight profile has been used.

Launched by Glavkosmos, Russia's commercial space organisation. The launch contract between Russia and India cost 60 billion roubles ($12.9 million).

The American Eosat company has a contract to commercially distribute the data generated by this satellite so as the 9 other remote sensing satellites to be launched by ISRO during the 10-year period ending 2005. This contract is worth a billion dollar. Eosat has been receiving data from IRS 1B since June 1994 and from IRS-P2 since march this year on an experimental basis. Its ground station at Norman in Oklahoma was the first to receive IRS data outside India.

Technical data

Specifications

Prime contractor	ISRO
Platform
Mass at launch	1250 kg
Mass in orbit
Dimension	1.65 x 1.5 x 2.1 m
Solar array	9.6 m²
Stabilization	3-axis
DC power	809 W
Design lifetime	3 years
LISS 3 (Linear Imaging Self Scanner) with CCD detector arrays

Wavebands	Green: 0.52-0.59 µm Red: 0.62-0.68 µm Near Infrared: 0.77-0.86 µm SW Infrared: 1.55-1.70 µm
Resolution	23.6 m except for SW IR: 70.8 m
Swath width	142 km except for SW IR: 148 km
WiFS

Wavebands	Red: 0.62-0.68 µm Near IR: 0.77-0.86 µm
Resolution	189 m
Swath width	810 km
Panchromatic

Wavebands	0.5-0.75 µm
Resolution	5.8 m
Swath width	70 km


 IRS P3

General

Designation	23827 / 96017A
Launch date	21 Mar 1996
Country of origin	India
Mission	Remote sensing
Perigee/Apogee	802/848 km (sunsynchronous, descending node: 10:30)
Inclination	98.8°
Period
Launch vehicle	PSLV #3
Mass at launch	930 kg
Technical data

Specifications

Prime contractor	ISRO
Platform
Mass at launch	922 kg
Mass in orbit
Dimension
Solar array	9.6 m²
Stabilization	3-axis
DC power	817 W
Design lifetime
MOS A

Spectral range	755-768 nm (4 bands)
Resolution	1569x1395 m
Swath width	195 km
MOS B

Spectral range	408-1010 nm (13 bands)
Resolution	523x523 m
Swath width	200 km
MOS C

Spectral range	1500-1700 nm (1 band)
Resolution	523x644 m
Swath width	192 km
WiFS

Wavebands	Red: 0.62-0.68 µm Near IR: 0.77-0.86 µm SW IR: 1.55-1.70 µm
Resolution	189 m
Swath width	810 km

X-ray astronomy payload: PPC range: 2-20 keV, XSM range: 2-8 keV


 IRS 1D

General

Designation	24971 / 97057A
Launch date	29 Sep 1997
Country of origin	India
Mission	Remote sensing
Perigee/Apogee	736/825 km (sunsynchronous, descending node: 10:30)
Inclination	98.6°
Period	101.35 min (revisit: 5 days)
Launch vehicle	PSLV #4
Mass at launch	1200 kg

Is a clone of IRS 1C with a few minor improvements. It will server as in-orbit replacement for IRS 1C.

Was launched in a bad orbit: 300 x 823 km. The correction to the initial orbit would have consumed too much fuel so the satellite was placed in an elliptical sunsynchronous orbit. The manoeuvres consumed about 67 kg of its fuel, leaving slightly over 16 kg.

Technical data

Specifications

Prime contractor	ISRO
Platform
Mass at launch	1250 kg
Mass in orbit
Dimension	1.65 x 1.5 x 2.1 m
Solar array	9.6 m²
Stabilization	3-axis
DC power	809 W
Design lifetime	3 years
LISS 3 (Linear Imaging Self Scanner) with CCD detector arrays

Wavebands	Green: 0.52-0.59 µm Red: 0.62-0.68 µm Near Infrared: 0.77-0.86 µm SW Infrared: 1.55-1.70 µm
Resolution	23 m except for SW IR: 70 m
Swath width	142 km except for SW IR: 148 km
WiFS

Wavebands	Red: 0.62-0.68 µm Near IR: 0.77-0.86 µm
Resolution	189 m
Swath width	774 km
Panchromatic

Wavebands	0.5-0.75 µm
Resolution	6 m
Swath width	70 km

Has a 4.5 kg GPS receiver


 IRS P4

Also called Ocean Sat

General

Designation	25758 / 99029C
Launch date	26 May 1999
Country of origin	India
Mission	Remote sensing
Perigee/Apogee	720 km
Inclination	98.3°
Period	99.3 min (2-day revisit)
Launch vehicle	PSLV #5

A 100 kg piggybacked payload from Korea will be included

External resources

http://www.ioccg.org/general/ocm/ocm.html

Technical data

Specifications

Prime contractor
Platform
Mass at launch	1036 kg
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime
Multi-Channel Microwave Radio Meter

Will provide information about sea surface temperatures, wind speed and water vapour, all conducive for fisheries forecasts

Ocean Colour Monitor

Will measure sea temperatures even up to 1 to 2 kelvins identifying them with colours with the help of spectral bands. Swath 1420 km


 IRS P5

Also called Carto Sat or Cartosat 1

planned in 1999-2000, to be launched by PSLV

Would have a pan camera with 1 or 2.5 meter resolution and a 10 to 12 km swath capability and would be mainly useful for map making and terrain modelling. Other sources claim steerable swath of 30 km.


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 IRS P6

Also called Resource Sat or Resourcesat

planned in 2000-2001, environnemental satellite, to be launched by PSLV

Would have a 3-band spectral camera with a 6 m resolution and could be used for select mapping with its advance wide field sensor. It would be very effective during floods with its 1,400 km swath.

Other sources claim the satellite will have a LISS 3 instrument (23 m resolution) and a LISS 4 (6 m resolution + a AWiFS instrument.


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 IRS P7

Also called Oceansat 2

planned in 2002

Oceansat-2, with a payload mix of microwave, thermal and optical sensors, would provide greater insight into global understanding of ocean dynamics/resources.


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 IRS 2A

to be launched in 1999 by a PSLV


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 IRT

General

Designation	14689 / 84011C
Launch date	5 Feb 1984
Country of origin	United States
Mission	Scientific
Perigee/Apogee	279/288 km
Inclination	28.5°
Period	90.2 min
Launch vehicle	STS 11

IRT was a inflatable balloon to be used as a rendezvous target to get practise for shuttle rendezvous manoeuvres. IRT blow appart shortly after beeing released.

End of life

Cause	Retrieved by the Shuttle
Decay	11 Feb 1984


 Program: ISEE

International Sun Earth Explorer

International scientific program

The 3rd satellite of the program, launched on 12 Aug 1978 was placed on a Sun orbit thus it isn't detailed in here. It has observed the Giacobini-Zinner comet on 11 Sep 1985.

External resources

http://uss-enterprise.bu.edu/BUSPACE/ISEE/isee.html


Program: ISEE

ISEE 1

ISEE 2


 ISEE 1

General

Designation	10422 / 77102A
Launch date	22 Oct 1977
Country of origin	International
Mission	Scientific: magnetosphere study
Perigee/Apogee	436/137806 km
Inclination	12.7°
Period	3441 min
Launch vehicle	Thor Delta #135

Built by NASA

End of life

Decay	26 Sep 1987


 ISEE 2

General

Designation	10423 / 77102B
Launch date	22 Oct 1977
Country of origin	International
Mission	Scientific: magnetosphere study
Perigee/Apogee	406/137765 km
Inclination	13.5°
Period	3438.5 min
Launch vehicle	Thor Delta #135

Built by ESA

End of life

Decay	26 Sep 1987


 Program: Isis

Canadian scientific program for ionospheric studies


Program: Isis

Isis 1

Isis 2


 Isis 1

General

Designation	03669 / 69009A
Launch date	30 Jan 1969
Country of origin	Canada
Mission	Scientific: ionosphere study
Perigee/Apogee	574/3470 km
Inclination	88.4°
Period	127.7 min
Launch vehicle	Thor Delta #65
Mass at launch	237 kg
Technical data

Transmits on 136.410 MHz


 Isis 2

General

Designation	05104 / 71024A
Launch date	1 Apr 1971
Country of origin	Canada
Mission	Scientific: ionosphere study
Perigee/Apogee	1353/1423 km
Inclination	88.5°
Period	113.5 min
Launch vehicle	Thor Delta #84
Mass at launch	262 kg


 ISO

Infrared Space Observatory

General

Designation	23715 / 95062A
Launch date	17 Nov 1995
Country of origin	Europe
Operator	ESTEC (European Space TEchnology Center) for ESA
Mission	Scientific: IR astronomy
Perigee/Apogee	1036/70578 km
Inclination	5.2°
Period	1436 min
Launch vehicle	Ariane V80

The primary objectives of the Infrared Space Observatory are to provide spectroscopic, photometric, imaging, and polarimetric observations of selected celestial sources at infrared wavelengths from 2.3 um to 200 um with the highest possible sensitivity and spatial resolution. The instruments are cooled at -270°C in a cryostat which contained 2400 liters of superfluid helium at liftoff.

The satellite was initially planned for 1993 but the mission was delayed for two years while engineers worked on problems related to the temperature control system. The two-year delay added 20 percent to the project's final cost of $850 million for the satellite and launch. US astronomers will be granted 20 percent of the ISO's observation time in exchange for ground station support.

The first light image was taken on Nov 28.

End of life

Out of service	8 Apr 1998
Cause	lack of helium
Decay

The helium consumption was smaller than planned; this enabled the satellite to operate during 28 months. The satellite was deorbited and shutoff on 16 May 1998.

External resources

http://isowww.estec.esa.nl

Technical data

Specifications

Prime contractor	Aerospatiale
Platform
Mass at launch	2498 kg
Payload mass	1515 kg
Mass in orbit	2418 kg
Dimension	3.56 x 2.77 x 5.31 m
Solar array
Stabilization	3-axis
DC power
Design lifetime	1.5 years

Telemetry: 2266.5 MHz (4, 8, 16 & 32 kbps)

Command: 2087.069 MHz (2000 bps)

Cassegrain telescope

Diameter	0.6 m
Focal length	9.0 m
Camera	ISOCAM
Temperature control	3K (-270°C)
Other payloads

Imaging photopolarimeter: ISOPHOT

Long Wavelength Spectrometer: LWS

Short Wavelength Spectrometer: SWS

Frequency bands

ISOCAM	3-17 µm
ISOPHOT	3-200 µm
LWS	45-180 µm
SWS	3-45 µm

Pointing stability: 2.7 arcsecs


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 Program: Italsat

Italian experimental satellites operated by Telespazio


Program: Italsat

Italsat 1

Italsat 2


Italsat's Ka-band National coverage


Italsat's Ka-band Multibeam coverage


 Italsat 1

General

Designation	21055 / 91003A
Launch date	15 Jan 1991
Country of origin	Italy
Mission	Telecommunications
Geostationary orbit	13.2°E
Launch vehicle	Ariane V41
Technical data

EIRP coverage

Ka-band National

Ka-band Multibeam

Specifications

Prime contractor	Selenia Spazio
Platform	Italsat
Mass at launch	1850 kg
Mass in orbit	1122 kg
Payload mass	273.4 kg: transponders: 198 kg, antennas: 75.4 kg)
Dimension	3.5 x 2.7 x 2.3 m
Solar array	21.8 m span
Stabilization	3-axis
DC power	EOL: equinox: 1760 W, solstice: 1633 W
Payload power	937 W
Design lifetime	6 years

Equipped with 1 (+1 backup) 1 W propagation beacon, EIRP 27 dBW at 20 GHz for telemetry

Also aboard: a 40 GHz beacon phase modulated by a 505 MHz coherent subcarrier, and a polarization-switched (but otherwise unmodulated) 50 GHz beacon

Ka-band - National beam (20/30 GHz)

Main transponders	3
Backup transponders
Power	20 W (TWTA)
Bandwidth	36 MHz
Coverage	Italy (1.55 x 1.06 deg)
EIRP max	46.2 dBW
G/T	5.5 dB/K
Polarization	linear V (both upload and download)

Those transponders are intended for TV feeds

Ka-band - Multi beam

Main transponders	6 in 20/60 GHz
Backup transponders	2 in 20/30 GHz 4 in 20/60 GHz
Power	20 W (TWTA)
Bandwidth	120 MHz
Coverage	Italy (6 spots of 0.49°)
EIRP max	57 dBW
G/T	16.1 dB/K
Polarization	linear V (both upload and download)

The spot beams carry domestic telephone traffic with a total capacity of about 12,000 voice channels. Each beam operates in the SS-TDMA mode with QPSK modulation at 147 Mbits/sec in a 100 MHz RF bandwidth. On-board regeneration (demodulation and remodulation) is provided, and the beams are fully interconnected by a space-division switching matrix. Satellite resources can be allocated on a call-by-call basis or left as assigned until changed by ground control. Reconfiguration is by ground command; the satellite is not autonomous.


 Italsat 2

General

Designation	24208 / 96044A
Launch date	8 Aug 1996
Country of origin	Italy
Mission	Telecommunications
Geostationary orbit	16.4°E
Launch vehicle	Ariane V90

Insured cost (satellite + launch): $200 million

EMS service began on 31 Oct 1996

Technical data

EIRP coverage

Ka-band National

Ka-band Multibeam

EMS (L- and Ku-band)

Specifications

Prime contractor	Selenia Spazio
Platform	Italsat
Mass at launch	1983 kg
Mass in orbit	1185 kg
Payload mass	275 kg
Dimension	3.5 x 2.7 x 2.3 m
Solar array	24 m span
Stabilization	3-axis
DC power	EOL: solstice: 1990 W
Payload power	1266 W
Design lifetime	8 years
Beacons	Telemetry: 18.685 & 2.202 GHz Command: 2.028 GHz
Ka-band (20/30 GHz)

Main transponders	3 national beam + 6 multi-beam
Backup transponders
Power	20 W (TWTA)
Bandwidth	national beam: 36 MHz multi-beam: 110 MHz
Coverage	national beam: Italy multi-beam: Italy (6 spots)
EIRP max	national beam: 48 dBW multi-beam: 54 dBW
Polarization
European Mobile System (EMS) payload

Main transponders	L-band (1.5/1.6 GHz): 3 (forward) Ku-band (12/14 GHz): 12 (return)
Power	20 W
Bandwidth	L-band: 4 MHz Ku-band: 0.9 MHz
Coverage	Europe
EIRP max	L-band: 42.5 dBW Ku-band: 32 dBW

Payload developed by ESA. part of the capacity is leased to to Nuova Telespazio of the STET Group.


Italsat 2's EMS coverage


 Itamsat

Also called IO-26 or Oscar 26

General

Designation	22826 / 93061D
Launch date	26 Sep 1993
Country of origin	Italy
Mission	Telecommunications
Perigee/Apogee	789/803 km
Inclination	98.7°
Period	100.8 min
Launch vehicle	Ariane V59
External resources

http://joshua.micronet.it/english/itamsat/itamsathome.html

Technical data

Specifications

Prime contractor	Associazione Radioamatori Italiani
Platform	Amsat-NA Microsat
Mass at launch	12.5 kg
Mass in orbit
Length	230 mm
Width	230 mm
Height	235 mm
Stabilization	magnetic
DC power
Design lifetime	7-10 years
Frequency chart (MHz)

Downlink freq.	Transponder/Beacon	Mode
435.820		?
435.870		1200 bps PSK Digital
Uplink freq.	Transponder/Beacon	Mode
145.875		1200 bps FM Digital
145.900		1200 bps FM Digital
145.925		1200 bps FM Digital
145.950		1200 bps FM Digital


Itos
 Itos A

Improved Tiros Operational Satellite, also called Tiros M

General

Designation	04320 / 70008A
Launch date	23 Jan 1970
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	1431/1477 km
Inclination	101.4°
Period	115 min
Launch vehicle	Thor Delta #76
Mass at launch	310 kg

This satellite is an evolved Tiros: it enables real time observation, night and day.


 IUE

International Ultraviolet Explorer

General

Designation	10637 / 78012A
Launch date	26 Jan 1978
Country of origin	International
Operator	NASA + ESA
Mission	Scientific: UV astronomy
Perigee/Apogee	30252/41315 km
Inclination	34.5°
Period	1435.9 min
Launch vehicle	Thor Delta #132
Mass at launch	671 kg

A joint NASA/ESA/SERC (Search and Engineering Research Council) observatory satellite designed for ultraviolet spectrometry of cosmic UV sources. ESA's contribution was the construction of the spacecraft's solar panels and a ground station at Villafranca, Spain.

On 1st October 1995 the primary control of the still operating spacecraft was transferred from NASA to ESA. This because of NASA's cost reduction efforts.

External resources

http://iuewww.gsfc.nasa.gov/iuedac/iuedac_homepage.html

http://archive.stsci.edu/iue/

End of life

Out of service	30 Sep 1996
Cause	planned end of exploitation
Technical data

Specifications

Mass at launch	644 kg
Length	4.17 m
Width	1.45 m
Solar array	45 m²
Stabilization	3-axis
Design lifetime	3 years

Payload: 0.45 m diameter UV telescope + 4 spectrographs

Telemetry: 138.86 & 2249.0 MHz

Command: 149.0 MHz


 Jason 1

General

Designation
Launch date	initially planned in late 1999
Country of origin	France
Mission	Scientific: ocean remote sensing
Perigee/Apogee	1336 km
Inclination	66°
Period	(9.9 days repeat)
Launch vehicle	Delta 2

Is to replace Topex Poseidon

First of CNES' Proteus small satellite missions. Are planned: Corot in 2002, Picasso-Cena in 2003, 3S in 2003 or 2004.

External resources

http://topex-www.jpl.nasa.gov/jason1/

http://sirius-ci.cst.cnes.fr:8090/HTML/information/frames/missions/jason_uk.html

Technical data

Specifications

Prime contractor	Aerospatiale
Platform	Spacebus-L
Mass at launch	500 kg
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime

The Poseidon 2

Payload

Poseidon 2: dual frequency radar altimetry to be built by Alcatel Telecom for about $29 million

Doris

JMR

TRSR

LRA


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 Jawsat

General

Designation
Launch date	planned in 1999
Country of origin	United States
Mission
Perigee/Apogee
Inclination
Period
Launch vehicle
Launch site

This is a joint USAF and Weber State university satellite. It will deploy 4 satellites:

Asusat 1

Opal

Falconsat (http://www.usafa.af.mil/falconsat.html) (USAF)

Optical calibration sphere (air force research lab)

The PEST experiment (http://www.ssl.msfc.nasa.gov/newhome/headlines/ast22mar99_1.htm) and the Weber State Attitude Control Platform will remain attached to Jawsat.

External resources

http://cast.weber.edu/jawsat/


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 Program: Jcsat

Japanese telecommunication program operated by JSAT (Kabushiki-gaisha Nihon Sateraito Sisutemuzu).

It is Japan's first commercial satellite system providing TV and cable distribution, telephony, business services and satellite news gathering.


Program: Jcsat

Jcsat 1

Jcsat 2

Jcsat 3

Jcsat 4

Jcsat 5

Jcsat 6


Jcsat 1 & 2's specifications

Prime contractor	Hughes
Platform	HS-393
Mass at launch	2280 kg
Mass in orbit	1376 kg
Diameter	3.66 m
Height	10 m deployed
Stabilization	Spin stabilized
DC power	BOL: 2240 W
Design lifetime	10 years


Jcsat 1 & 2's Ku-band

Main transponders	32
Backup transponders	8
Power	20 W (TWTA)
Bandwidth	27 MHz
Coverage	Japan and offshore territories
EIRP max	51 dBW
Polarization


ASC's C-band transponder frequency chart
 Jcsat 1 & 2's transponder frequency chart (GHz)

Horizontal Uplink	Horizontal Downlink	Transponder	Vertical Downlink	Vertical Uplink
14.01625		1	12.26825
	12.28325	2		14.03125
14.04625		3	12.29825
	12.31325	4		14.06125
14.07625		5	12.32825
	12.34325	6		14.09125
14.10625		7	12.35825
	12.37325	8		14.12125
14.13625		9	12.38825
	12.40325	10		14.15125
14.16625		11	12.41825
	12.43325	12		14.18125
14.19625		13	12.44825
	12.46325	14		14.21125
14.22625		15	12.47825
	12.49325	16		14.24125
14.25625		17	12.50825
	12.52325	18		14.27125
14.28625		19	12.53825
	12.55325	20		14.30125
14.31625		21	12.56825
	12.58325	22		14.33125
14.34625		23	12.59825
	12.61325	24		14.36125
14.37625		25	12.62825
	12.64325	26		14.39125
14.40625		27	12.65825
	12.67325	28		14.42125
14.43625		29	12.68825
	12.70325	30		14.45125
14.46625		31	12.71825
	12.73325	32		14.48125


Jcsat 1 & 2's EIRP


 Jcsat 1

General

Designation	19874 / 89020A
Launch date	6 Mar 1989
Country of origin	Japan
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V29

Due to a leak in the fuel tank, the satellite will reach end of life in mid-1997

Location

Begin	End	Position
L: 6 Mar 1989	Jul 1997	150°E
Sep 1997	Oct 1997	148°E
Feb 1998	Jul 1998	111°E
End of life

Out of service	Jul 1998
Cause	deorbited
Technical data

EIRP coverage (dBW)

Specifications

Ku-band

Transponder frequency chart


 Jcsat 2

General

Designation	20402 / 90001B
Launch date	1 Jan 1990
Country of origin	Japan
Mission	Telecommunications
Geostationary orbit	154°E
Launch vehicle	Titan 3 #153
Technical data

EIRP coverage (dBW)

Specifications

Ku-band

Transponder frequency chart


 Jcsat 3

General

Designation	23649 / 95043A
Launch date	29 Aug 1995
Country of origin	Japan
Mission	Telecommunications
Geostationary orbit	128°E
Launch vehicle	Atlas Centaur #94

GTO: 167 km x 81432 km x 23.5°

In 1995 leases were said to cost ¥550 million a year for 27 MHz transponders and ¥600 million a year for 36 MHz transponders.

Technical data

EIRP coverage (dBW)

C-band

Ku-band

Specifications

Prime contractor	Hughes
Platform	HS-601
Mass at launch
Mass in orbit
Length
Width
Height
Stabilization	3-axis
DC power	4600 W
Design lifetime	12 years

NEC Corp. of Japan is a major subcontractor to Hughes for the payload electronics.

C-band

Main transponders	12
Backup transponders
Power	34 W (SSPA)
Bandwidth	36 MHz
Coverage	Asia & Australia
EIRP max	37 dBW
Polarization	linear
Transponder frequency chart (GHz)

Horizontal downlink	Transponder	Vertical downlink
	C1	3.960
3.980	C2
	C3	4.000
4.020	C4
	C5	4.040
4.060	C6
	C7	4.080
4.100	C8
	C9	4.120
4.140	C10
	C11	4.160
4.180	C12
Ku-band

Main transponders	28
Backup transponders
Power	60 W (TWTA)
Bandwidth	16 transponders of 27 MHz 12 transponders of 36 MHz
Coverage & EIRP max	Japan: 55 dBW Eastern Asia, India & Australia: 43-35 dBW
Polarization	Linear
Transponder frequency chart (GHz)

Horizontal downlink	Transponder	Vertical downlink	Bandwidth (MHz)
	K1	12.258	36
12.288	K2		36
	K3	12.308	36
12.328	K4		36
	K5	12.348	36
12.368	K6		36
	K7	12.388	36
12.408	K8		36
	K9	12.428	36
12.448	K10		36
	K11	12.468	36
12.488	K12		36
	K13	12.508	27
12.523	K14		27
	K15	12.538	27
12.553	K16		27
	K17	12.568	27
12.583	K18		27
	K19	12.598	27
12.613	K20		27
	K21	12.628	27
12.643	K22		27
	K23	12.658	27
12.673	K24		27
	K25	12.688	27
12.703	K26		27
	K27	12.718	27
12.733	K28		27


Jcsat 3's C-band EIRP


Jcsat 3's Ku-band EIRP


 Jcsat 4

Also called Jcsat 1A and Jcsat R

General

Designation	24732 / 97007A
Launch date	17 Feb 1997
Country of origin	Japan
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Atlas 2AS
Location

Begin	End	Position
L: 17 Feb 1997	Apr 1997	141°E
May 1997	Feb 1998	150°E (became Jcsat 1A)
Mar 1998	Jun 1999	124°E (became Jcsat R on 15 Jun 1999)
Jul 1999		127°E

Satellite ordered after a Jcsat 1 problem (slight leak) was detected

Technical data

Specifications

Prime contractor	Hughes
Platform	HS-601 (#58)
Mass at launch
Mass in orbit
Length
Width
Height
Stabilization	3-axis
DC power	5000 W
Design lifetime	12 years

Features 4 octagonal communications antennas

C-band

Main transponders	12
Backup transponders
Power	34 W (SSPA)
Bandwidth	36 MHz
Coverage	Asia & Australia
EIRP max	37 dBW
Polarization	linear
Ku-band

Main transponders	28
Backup transponders
Power	60 W (TWTA) + four 90 W (TWTA) for 4 36 MHz transponders
Bandwidth	8 transponders of 36 MHz 16 transponders of 27 MHz (4 transponders can be switched to 54 MHz with 120 W)
Coverage & EIRP max	Japan: 55 dBW Eastern Asia, India & Australia: 43-35 dBW
Polarization	Linear


 Jcsat 5

General

Designation	25067 / 97075A
Launch date	2 Dec 1997
Country of origin	Japan
Mission	Telecommunications
Geostationary orbit	150°E
Launch vehicle	Ariane V103

JCSAT 5 was tested at 139°E.

Technical data

Specifications

Prime contractor	Hughes
Platform	HS-601
Mass at launch	2982 kg
Mass in orbit	1819 kg
Dry mass	1308 kg
Length
Width
Height
Stabilization	3-axis
DC power	5000 W
Design lifetime	12 years
Ku-band

Main transponders	32
Backup transponders
Power	20 transponders of 60 W (TWTA) 12 transponders of 90 W (TWTA) for 36 MHz transponders
Bandwidth	16 transponders of 27 MHz 12+4 transponders of 36 MHz (4 36 MHz transponders can be switched to two with 76 MHz with 90 watts)
Coverage & EIRP max	Japan, Asia-Pacific region and Hawaii
Polarization


 Jcsat 6

Also called Jcsat 4A

General

Designation	25630 / 99006A
Launch date	16 Feb 1999
Country of origin	Japan
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Atlas 2AS #119

Had to be removed from atop the rocket in Jan 1999 and shipped back to the manufacturer justs days before planned launch. The satellite had already experienced bad luck when it was damaged by a power surge when lightning stroke its processing facility.

Location

Begin	End	Position
L: 16 Feb 1999	Apr 1999	120°E
Jun 1999		124°E (became Jcsat 4A)
Technical data

Specifications

Prime contractor	Hughes
Platform	HS-601
Mass at launch	2900 kg
Dry mass	1230 kg
Length
Width
Height
Stabilization	3-axis
DC power	5000 W
Design lifetime	12 years
Ku-band

Main transponders	32
Backup transponders
Power	70 W (TWTA)
Bandwidth	27 MHz
Coverage & EIRP max
Polarization


 JERS 1

Japanese Earth Resource Sensing satellite, also called Fuyo 1

General

Designation	21867 / 92007A
Launch date	11 Feb 1992 at 01:50 UT
Country of origin	Japan
Mission	Remote sensing
Perigee/Apogee	567/568 km
Inclination	97.7°
Period	96 min
Launch vehicle	H1
Mass at launch	1340 kg

Had problems to open out its SAR antenna that were solved. Is working with 1 third of its power (4000 W instead of 12) thus the performance is not maximum

End of life

Out of service	12 Oct 1998
Cause	unknown
Decay
External resources

http://www.eurimage.it/Products/JERS_1.html

Technical data

Specifications

Prime contractor	Mitsubishi
Mass at launch	1400 kg
Length	0.93 m
Width	1.83 m
Height	3.16 m
Solar array	7 x 3.5 m
SAR Antenna	11.9 x 2.4 m
Stabilization	3-axis
Design lifetime	2 years
SAR (Synthetic Aperture Radar)

Frequency	1.3 GHz (L-band)
Resolution	18 x 18 m
Swath width	75 km

Mission: high resolution monitoring of land use and type, glacier extent, snow cover, surface topography, ocean currents and waves.

OPS (Optical Scanner)

Wavebands	0.52-0.6 µm (visible) 0.63-0.69 µm (visible) 0.76-0.96 µm (near IR) 1.6-1.7 µm (near IR) 2.0-2.4 µm (near IR)
Resolution	18 x 24 m
Swath width	75 km

Mission: pollution monitoring in oceans and lakes, land use classification, cloud and snow discrimination.


 Program: KH

Key Hole

American military reconnaissance program. The first satellites had a very limited lifetime. From 1959 to 1992: 266 launched including 50 failures

Sorry, this section is under total reconstruction

External resources

http://www.milnet.com/milnet/declass.htm

http://www.fas.org/spp/military/program/imint/index.html


to be processed

Samos KH 1 series

Satellite And Missile Observatory System

KH 1 series

8 satellites launched

Discovery: kh 1, 2 & 3

1st generation: discovery, samos and KH 3

KH 4 series

Corona

8 satellites launched

KH 4A series

Corona adv

41 satellites launched

1.5 t, launched by Thor Agena, resolution = 3 m, capsule for retrieval of data

KH 4B series

Corona adv (1966-72)

1.9 t, launched by Thor Agena, resolution = 1.5 m, capsule for retrieval of data?

KH 5 series

Argon

launched by Thor Agena, topographical camera, radio transmission

KH 6 series

Lanyard, samos adv

launched by Atlas Agena, program stopped in 1963

KH 7 series

Gambit

36 satellites launched

2 tons, launched by Atlas Agena, 50 cm resolution, 1963-67, capsule retrieval, high resolution camera

KH 8 series

Gambit adv

49 satellites launched

1966-85, 3.4 tons, titan 3b, high resolution camera + topographical camera + multispectral camera

KH 9 series

Hexagon or Big Bird

19 satellites launched

11.3 tons, titan 3d, 1971-86, replace KH 4B and KH 8

The images were returned on film contained in capsules. The typical orbit was a 250 km sun-synchronous orbit which was maintained against drag by frequent maneuvring engine firings. Lifetime was close to 18 months

KH 12 series

Kennan adv or Crystal adv?

Intl Des  Cat No  Name                      Launch     Decay Perigee

--------- ------  ---------------------- --------- --------- -------

1964 036B    826  KH  7-09 SUBSATELLITE     7/6/64    1/3/65    156

1964 045B    851  KH  7-10 SUBSATELLITE    8/14/64    3/8/79    272

1967 043B   2780  KH  4A-01 SUBSATELLITE    5/9/67   3/14/93    399

1967 062B   2851  KH  4A-02 SUBSATELLITE   6/16/67  10/22/68    501

1967 109B   3025  KH  4A-44 SUBSATELLITE   11/2/67   3/28/69    454

1968 008B   3114  KH  4A-45 SUBSATELLITE   1/24/68    3/4/70    470

1968 020B   3153  KH  4A-46 SUBSATELLITE   3/14/68    1/3/70    481

1968 052B   3297  KH  4A-47 SUBSATELLITE   6/20/68   1/11/70    435

1968 078B   3409  KH  4A-48 SUBSATELLITE   9/18/68   9/28/69    500

1968 112B   3605  KH  4A-49 SUBSATELLITE  12/12/68             1380

1969 010B   3673  KH  4B-06 SUBSATELLITE    2/5/69             1393

1969 026B   3830  KH  4A-50 SUBSATELLITE   3/19/69   12/6/71    502

1969 041B   3915  KH  4A-51 SUBSATELLITE    5/2/69   2/16/70    407

1969 079B   4103  KH  4A-52 SUBSATELLITE   9/22/69   5/16/71    490

1970 016B   4343  KH  4B-09 SUBSATELLITE    3/4/70  11/10/71    441

1970 098B   4722  KH  4B-12 SUBSATELLITE  11/18/70   9/14/77    493

1971 076B   5469  KH  4B-15 SUBSATELLITE   9/10/71    2/3/76    489

1972 002D   5772  KH  9-02 SUBSATELLITE    1/20/72   4/17/79    474

1972 052C   6096  KH  9-03 SUBSATELLITE     7/7/72    5/6/78    498

1972 079C   6822  KH  9-04 SUBSATELLITE   10/10/72             1420

1973 088D   6938  KH  9-07 SUBSATELLITE   11/10/73             1416

1974 085B   7498  KH  9-09 SUBSATELLITE   10/29/74   1/23/80    521

1975 114B   8468  KH  9-11 SUBSATELLITE    12/4/75    5/1/78    236

1976 065C   9008  KH  9-12 SUBSATELLITE     7/8/76              628

1978 029B  10734  KH  9-14 SUBSATELLITE    3/16/78              639

1979 025B  11306  KH  9-15 SUBSATELLITE    3/16/79              621

1980 052C  11852  KH  9-16 SUBSATELLITE    6/18/80             1331

1982 041C  13172  KH  9-17 SUBSATELLITE    5/11/82              660

1983 060C  14139  KH  9-18 SUBSATELLITE    6/20/83

1984 065C  15071  USA 3 (KH  9-19 SUBSAT)  6/25/84              655


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Program: KH

KH 1-2

KH 1-5

KH 4-01

KH 4A-03

KH 7-01

KH 9-01

KH 11-1

KH 11-2

KH 11-3

KH 11-6

KH 11-7

KH 11-8

KH 12-1

KH 12-2

KH 12-3

KH 12-4


KH 11 specifications

Also called Kennan

Those satellites operate on a sun-synchronous orbit (250/500 km for the first satellites, from KH 11-6 on 300/1000 km). Images are transmitted in real time via TDRS. Lifetime at least 4 years, variable. 13 tons

The constellation consists of two satellites in separate planes, spaced by the angle through which the Earth rotates during two of their orbital periods, about 48.7 deg. Each satellite repeats its groundtrack every four days; and the east satellite follows the west satellite's groundtrack two days later.

They operate with CCDs, estimated resolution: 15 cm


 KH 1-2

Also called Samos 2

General

Designation	00070 / 61001A
Launch date	31 Jan 1961
Country of origin	United States
Mission	Military: reconnaissance
Perigee/Apogee	474/557 km
Inclination	97.4°
Period	95 min
Launch vehicle	Atlas Agena B
Launch site	Vandenberg

First american spy satellite transmitting images by radio

End of life

Decay	21 Oct 1973


 KH 1-5

Also called Samos 5

General

Designation	00219 / 61035C
Launch date	22 Dec 1961
Country of origin	United States
Mission	Military: reconnaissance
Perigee/Apogee	187/310 km
Inclination	89.6°
Period	89.4 min
Launch vehicle
Launch site	Vandenberg
End of life

Decay	9 Jan 1962


 KH 4-01

Also called Close Look

General

Designation	00256 / 62007A
Launch date	7 Mar 1962
Country of origin	United States
Mission	Military: reconnaissance
Perigee/Apogee	236/686 km
Inclination	90.9°
Period	93.9 min
Launch vehicle
Launch site	Vandenberg
End of life

Decay	May 1963?


 KH 4A-03

General

Designation	00578 / 63016A
Launch date	18 May 1963
Country of origin	United States
Mission	Military: reconnaissance
Perigee/Apogee	147/506 km
Inclination	91°
Period	74.5 min
Launch vehicle
Launch site	Vandenberg
End of life

Decay	27 May 1963


 KH 7-01

General

Designation	00618 / 63028A
Launch date	12 Jul 1963
Country of origin	United States
Mission	Military: reconnaissance
Perigee/Apogee	173/212 km
Inclination	95.3°
Period	88.3 min
Launch vehicle	Atlas Agena D
Launch site	Vandenberg
End of life

Decay	17 Jul 1963


 KH 9-01

General

Designation	05297 / 71056A
Launch date	15 Jun 1971
Country of origin	United States
Mission	Military: reconnaissance
Perigee/Apogee	180/300 km
Inclination	96.4°
Period	89.3 min
Launch vehicle
Launch site	Vandenberg
End of life

Decay	6 Aug 1971


 KH 11-1

General

Designation	09627 / 76125A
Launch date	19 Dec 1976
Country of origin	United States
Mission	Military: reconnaissance
Perigee/Apogee	246/531 km
Inclination	96.9°
Period	92.3 min
Launch vehicle
Launch site	Vandenberg
End of life

Decay	28 Jan 1979


 KH 11-2

General

Designation	10947 / 78060A
Launch date	14 Jun 1978
Country of origin	United States
Mission	Military: reconnaissance
Perigee/Apogee	223/509 km
Inclination	97°
Period	91.9 min
Launch vehicle
Launch site	Vandenberg
End of life

Decay	23 Aug 1981
Technical data

Specifications


 KH 11-3

General

Designation	11687 / 80010A
Launch date	7 Feb 1980
Country of origin	United States
Mission	Military: reconnaissance
Perigee/Apogee	220/498 km
Inclination	97°
Period	91.7 min
Launch vehicle
Launch site	Vandenberg
End of life

Decay	30 Oct 1982
Technical data

Specifications


 KH 11-6

Also called USA 006

General

Designation	15423 / 84122A
Launch date	4 Dec 1984
Country of origin	United States
Mission	Military: reconnaissance
Perigee/Apogee	335/758 km
Inclination	98°
Period
Launch vehicle
Launch site	Vandenberg

Was active during the gulf war.

End of life

Decay	Oct 1994?
Technical data

Specifications


 KH 11-7

Also called USA 027

General

Designation	18441 / 87090A
Launch date	26 Oct 1987
Country of origin	United States
Mission	Military: reconnaissance
Perigee/Apogee	300/1000 km
Inclination	98°
Period
Launch vehicle
Launch site
Technical data

Specifications


 KH 11-8

Also called USA 033

General

Designation	19625 / 88099A
Launch date	6 Nov 1988
Country of origin	United States
Mission	Military: reconnaissance
Perigee/Apogee	300/1000 km
Inclination	98°
Period
Launch vehicle
Launch site
Technical data

Specifications


 KH 12-1

Also called USA 053

General

Designation	20516 / 90019B
Launch date	28 Feb 1990
Country of origin	United States
Mission	Military: reconnaissance (Kennan advanced)
Perigee/Apogee	800 km
Inclination	65°
Period
Launch vehicle	STS 36
Mass at launch	14000 kg

Optical reconnaissance satellite. Believed resolution: 15 cm. Downlinks via TDRS. Built by Lockheed


 KH 12-2

Also called USA 086

General

Designation	22251 / 92083A
Launch date	28 Nov 1992
Country of origin	United States
Mission	Military: reconnaissance (Kennan advanced)
Perigee/Apogee	287 / 1021 km
Inclination	97.8°
Period	97 min
Launch vehicle	Titan 4
Mass at launch	14000 kg

Optical reconnaissance satellite. Believed resolution: 15 cm. Downlinks via TDRS. Built by Lockheed

Was found in the orbit once occupied by KH 11-7


 KH 12-3

Also called USA 116

General

Designation	23728 / 95066A
Launch date	5 Dec 1995 at 21:18 UT
Country of origin	United States
Mission	Military: reconnaissance (Kennan advanced or Crystal)
Perigee/Apogee	270/980 km
Inclination	96.8°
Period	97 min
Launch vehicle	Titan 4
Mass at launch	14000 kg

Optical (and IR?) reconnaissance satellite. Believed resolution: 15 cm. Downlinks via TDRS. Built by Lockheed


 KH 12-4

Also called USA 129

General

Designation	24680 / 96072A
Launch date	20 Dec 1996
Country of origin	United States
Mission	Military: reconnaissance (improved Crystal 4?)
Perigee/Apogee	n/a
Inclination	n/a
Period	n/a
Launch vehicle	Titan 4 #19


Program: Kitcomm

LEO messaging system to be operated by Kitcomm pty of Australia. Should be composed of 6 satellites for a start, to be launched with Rokot rockets.

In the future a constellation of 21 satellites on 3 planes could be launched. Would orbit at 2800 km.

Should use L-band


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 Program: Kitsat

Also named Uribyol (Woo-Ree-Byul) which means "Our Star"

Korean program operated by the Korean Institute of Science and Technology

External resources

http://satrec.kaist.ac.kr


Program: Kitsat

Kitsat A

Kitsat B

Kitsat 3

Kitsat 4


 Kitsat A

Also called KO-23 or Oscar 23 or Woo-Ree-Byul Ir Ho

General

Designation	22077 / 92052B
Launch date	10 Aug 1992
Country of origin	South Korea
Mission	Telecommunications
Perigee/Apogee	1304/1324 km
Inclination	66.1°
Period	111.9 min
Launch vehicle	Ariane V52
Mass at launch	50.5 kg

Function: Packet Radio Mailbox, Digipeater, a CCD camera experiment and a synthesized voice experiment. The Earth Imaging System (EIS) has 2 CCD cameras.

Technical data

Specifications

Prime contractor	Korean Advanced Institute of Science and Technology
Platform	SSTL (Surrey Satellite Technology Ltd.)
Mass at launch	50.5 kg
Mass in orbit
Length
Width
Height
Stabilization	3-axis (gravity gradient & magnetotorquer)
DC power
Design lifetime
Frequency chart

Uplink	9600 bps K9NG/G3RUH modulated FSK (FM) AX.25 145.850 145.900 MHz
Downlink	9600 bps K9NG/G3RUH modulated FSK (FM) AX.25 435.175 MHz


 Kitsat B

Also called KO-25 or Oscar 25 or Woo-Ree-Byul Ee Ho

General

Designation	22830 / 93061H
Launch date	26 Sep 1993
Country of origin	South Korea
Mission	Telecommunications
Perigee/Apogee	787/803 km
Inclination	98.6°
Period	100.8 min
Launch vehicle	Ariane V59
Mass at launch	47.5 kg

It carries CCD cameras, store/forward communication equipment (HAM radio) and a radiation detector.

Technical data

Specifications

Prime contractor	SaTRec (Satellite Technology Research Center)
Platform	SSTL (Surrey Satellite Technology Ltd.)
Mass at launch	50.5 kg
Mass in orbit
Length	352 mm
Width	356 mm
Height	670 mm
Stabilization	3-axis (gravity gradient & magnetotorquer)
DC power
Design lifetime	5 years
Frequency chart (MHz)

Downlink freq.	Transponder/Beacon	Mode
435.175	T	9600 bps FSK FM Digital
436.500	T	9600 bps FSK FM Digital
Uplink freq.	Transponder/Beacon	Mode
145.870	T	9600 bps FSK FM Digital
145.980	T	9600 bps FSK FM Digital


 Kitsat 3

General

Designation	25756 / 99029A
Launch date	26 May 1999
Country of origin	South Korea
Mission	Telecommunications
Perigee/Apogee	720 km, sunsynchronous
Inclination	98.4°
Period	99.4 min
Launch vehicle	PSLV #5
Technical data

Specifications

Prime contractor	Korea Advanced Inst. of Technology (KAIST)
Platform	KAIST
Mass at launch	107 kg
Mass in orbit
Dimension	49.5 x 60.4 x 85.2 cm
Solar array
Stabilization	3-axis
DC power	150 W
Design lifetime

uplink: 148 MHz

downlink: 401.375 MHz, 2.2 GHz, 8 GHz

Remote Sensing Payload

15m Ground Resolution, 3-channel (Red, Green, Near-IR), Linear CCD Camera

Space Science Payloads

Radiation Effect on Micro-Electronics (REME)

High Energy Particle Telescope (HEPT)

Scientific Magnetometer (SMAG)

Electron Temperature Probe (ETP)


 Kitsat 4

General

Designation
Launch date	2002
Country of origin	South Korea
Mission	Telecommunications
Perigee/Apogee	720 km, sunsynchronous
Inclination	98.9°
Period
Launch vehicle

It will carry a sophisticated communications package (UHF- and S-band) developed in Australia by Research Centre for Satellite Systems (CRCSS).

External resources

http://www.crcss.csiro.au/


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 Kompsat 1

Korea Multi Purpose Satellite

General

Designation
Launch date	initially planned in 1999
Country of origin	South Korea
Mission	Scientific
Perigee/Apogee	685 km
Inclination
Period
Launch vehicle	Taurus
Launch site

KOMPSAT will carry remote sensing instruments to measure ocean and land as well as upper atmospheric instruments. Some experiments will focus on ionospheric and magnetic fields. Also includes an electro-optical camera with 7 meter resolution built by TRW. The camera will provide cartography data for developing digital elevation maps of the Korean peninsula for land use and planning purposes.

Contact

KARI (Korea Aerospace Research Institute)

52 Eoeun Dong, Yusong Gu, Taejon 305-333, Korea

Tel: +82-042-860-2611

Technical data

Specifications

Prime contractor	TRW
Platform	STEP
Mass at launch	420 kg or 510 kg?
Mass in orbit
Dimension
Solar array
Stabilization	3-axis
DC power
Design lifetime

Should have Ka-band capacity

Daewoo provided the attitude and orbit control subsystem; Halla and Hanwah, the propulsion subsystem; Hyundai, electrical power system components; Korean Air and Doowon, the structural and thermal subsystem; and Samsung, the on-board computer and satellite system test equipment.


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 Program: Koreasat

Also called Mugunghwa (name of the national flower)

Korean geostationary telecommunication program operated by Korea Telecom. The first generation is made of 3 satellites operating in DBS & FSS band.

The second generation satellites are planned for 2005


Program: Koreasat

Koreasat 1

Koreasat 2

Koreasat 3


Koreasat's specifications

Prime contractor	Lockheed Martin Astro Space
Platform	GE 3000
Mass at launch	1464 kg
Dry mass	652 kg
Payload mass	202 kg
Dimension	1.74 x 1.96 x 1.9 m
Stabilization	3-axis
DC power	BOL: 1600 W
Design lifetime	12 years

Beacons would be at: 12.25125, 12.25175 & 12.74875 GHz


Koreasat's Ku-band FSS

Main transponders	12
Backup transponders	4
Power	14 W
Bandwidth	36 MHz
Coverage	South Korea
EIRP max	50.2 dBW
G/T max	13.5 dB/K
Polarization	Koreasat 1: H uplink; V downlink Koreasat 2: V uplink; H downlink
Frequencies	Uplink: 14.00-14.5 GHz Downlink: 12.25-12.75 GHz
Beam coverage	0.74° x 0.74° uplink; 0.86° x 0.86° downlink


Koreasat's Ku-band DBS

Main transponders	3
Backup transponders	3
Power	120 W
Bandwidth	27 MHz
Coverage	South Korea
EIRP max	59.4 dBW
G/T max	13.0 dB/K
Polarization	LHCP (up and down)
Frequencies	Uplink: 14.5-14.8 GHz Downlink: 11.7-12.0 GHZ
Beam coverage	0.82° x 0.67° uplink; 1.06° x 0.86° downlink


Koreasat 1 & 2's FSS EIRP


Koreasat's DBS EIRP


 Koreasat 1

Also called Mugunghwa Ir Ho

General

Designation	23639 / 95041A
Launch date	5 Aug 1995 at 11:10 UT
Country of origin	South Korea
Mission	Telecommunications
Geostationary orbit	116°E
Launch vehicle	Delta 2 #228

The launch experienced a partial failure: a booster rocket to separate. The preliminary reports indicate that explosive lines on the Delta 2 vehicle were damaged by exposure to excessive temperatures, causing one of the solid motors not to separate. The booster separation malfunction was blamed on the heat-related failure of insulation protecting the rocket's booster separation circuits.

This resulted in a wrong orbit delivery. The satellite reached GEO at the end of August on its own and used part of is propellant. Thus its lifetime was reduced to 4.5 years.

Should move to 113°E after the launch of Koreasat 3

Technical data

Specifications

Ku-band (telecom)

Ku-band (DBS)

EIRP coverage (dBW)

Telecom

DBS

Equipped with a Star 30 solid apogee motor. Carries 625 kg of fuel for the apogee motor and 187 kg of hydrazine propellant.


 Koreasat 2

Also called Mugunghwa Ee Ho

General

Designation	23768 / 96003A
Launch date	14 Jan 1996
Country of origin	South Korea
Mission	Telecommunications
Geostationary orbit	116°E
Launch vehicle	Delta 2 #231
Mass at launch	1608 kg
Technical data

Specifications

Ku-band (telecom)

Ku-band (DBS)

EIRP coverage (dBW)

Telecom

DBS


 Koreasat 3

Also called Mugunghwa Sahm Ho

General

Designation
Launch date	initially planned in Aug 1999
Country of origin	South Korea
Mission	Telecommunications
Geostationary orbit	116°E
Launch vehicle	Ariane
Mass at launch

The satellite total cost: $219 million.

Will replace Koreasat 1

Delayed because of potential solar panels problems.

Technical data

EIRP coverage (dBW)

Telecom

DBS

Specifications

Prime contractor	Lockheed Martin
Platform	A2100
Mass at launch	2790 kg
Dry mass	1300 kg
Dimension
Solar array
Stabilization
DC power	4700 W
Design lifetime	15 years

Antennas provided by Spar Aerospace

Ku-band DBS

Main transponders	6
Backup transponders	3
Power	120 W
Bandwidth	27 MHz
Coverage	South Korea
EIRP max	59.4 dBW
G/T max	14.0 dB/K
Polarization	LHCP (up and down)
Beam coverage	0.82° x 0.67° uplink; 1.06° x 0.86° downlink
Ku-band FSS

Main transponders	group-1 12 + group-2 12
Backup transponders	8
Power	45 W
Bandwidth	36 MHz
Coverage	G1: South Korea G2: South Korea or South-East Asia (steerable)
EIRP max	G1: 50.5 dBW G2 South Korea: 55.1 dBW G2 South-East Asia: 50.2 dBW
G/T max	G1: 13.6 dB/K G2 South Korea: 13.7 dB/K G2 South-East Asia: 8.0 dB/K
Polarization	G1: H uplink, V downlink G2: V uplink, H downlink
Beam Coverage	G1: 0.74° x 0.74° uplink; 0.86° x 0.86° downlink G2 South-East Asia: 3.0° circular
Ka-band

Main transponders	3
Backup transponders	2
Power	70 W
Bandwidth	200 MHz
Coverage	Korean peninsula
EIRP max	55.0 dBW
G/T max	9.4 dB/K
Polarization	RHCP uplink; LHCP downlink
Beam coverage	1.2° x 1.0°


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Koreasat 3's FSS EIRP


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 Kwangmyongsong 1

Kwangmyongsong means "Bright Light Star"

General

Designation	n/a
Launch date	31 Aug 1998 at 03:07 UT
Country of origin	North Korea
Mission	Test
Perigee/Apogee
Inclination
Period
Launch vehicle	Taepo Dong
Launch site	Musudan

Sources observed the third stage burning. No signal was spotted on radar, it seems that the satellite did not reach orbit but fell into the Pacific.

End of life

Out of service	31 Aug 1998 ??
Cause
Decay


 L Star 1

Also called LaoStar

General

Designation
Launch date	initially planned in early 1998
Country of origin	Thailand
Mission	Telecommunications
Geostationary orbit	116°E or 126°E
Launch vehicle	Ariane
Launch site

Program of Asia Broadcasting and Communications Network, Ltd (ABCN) of Bangkok. ABCN is a subsidiary of Thailand's M. Group. After launch, the satellite is to be handed over to Lao-Star Co. Ltd., a company held 80 percent by ABCN and 20 percent by the government of Laos.

ABCN also awarded a contract to Telesat Canada to monitor and test the L-Star program as technical advisers. Telesat will also operate the satellite during the first 24 months. Telesat is building a control center in Perth Australia. This center will be remote controlled from their main control center in Canada.

Japan's Itochu Corp. said it will join the project. Sondhi Satellite would also be involved

The contract (2 satellites with launch) is worth $480 million. Options can be taken for 3rd and 4th satellites. The ground station will be located in Vientianne

The program might be delayed or cancelled because of the Asian currency crisis.

Technical data

EIRP coverage (dBW)

Specifications

Prime contractor	Space Systems/Loral
Platform	FS-1300HP
Mass at launch	3500 kg
Mass in orbit
Dimension
Solar array
Stabilization	3-axis
DC power	EOL: 8200 W
Design lifetime	14 years
Ku-band

Main transponders	32
Backup transponders
Power	113 W
Bandwidth	33 MHz
Coverage	East: East Asia (Taiwan, Southern and Eastern coast of China, HongKong, Korea) West: Indian subcontinent (India, Pakistan, Nepal, Bangladesh, Sri Lanka) Central: Golden Peninsula (Thailand, Laos, Cambodia, Vietnam, Malaysia Singapore) + Japan uplink
EIRP max
Polarization
Frequencies	Uplink: 17.3-17.8 GHz Downlink: 11.7-12.2 GHz


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L Star's EIRP


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 L Star 2

General

Designation
Launch date	initially planned in mid 1998
Country of origin	Thailand
Mission	Telecommunications
Geostationary orbit	116°E or 126°E
Launch vehicle	Ariane
Launch site

See L Star 1 for more details... the satellites are identical

The satellite might be delayed or cancelled because of the Asian currency crisis.

Technical data

EIRP coverage (dBW)


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 Program: Lacrosse

Also called Indigo

American military reconnaissance program

Equipped with a Synthetic Aperture Radar which provides 1 m resolution data. Lifetime = 5 years, 14 tons, built by Lockheed Martin. Solar pannel are believed to measure amost 50 m, which could provide 10 to 20 kW power.

Can take pictures as much as 1000 km off of the ground track. The great advantage of those satellites over the KH imaging satellites is that it can view through clouds. The system probably uses high and low resolution modes and transmits large amount of data for computer processing on the ground. It probably downlinks via TDRS

External resources

http://www.fas.org/spp/military/program/imint/lacrosse.htm

http://www.fas.org/spp/military/program/imint/indigo.htm


Program: Lacrosse

Lacrosse 1

Lacrosse 2

Lacrosse 3


 Lacrosse 1

Also called USA 034

General

Designation	19671 / 88106B
Launch date	2 Dec 1988
Country of origin	United States
Mission	Military: reconnaissance
Perigee/Apogee	680/690 km
Inclination	57°
Period
Launch vehicle	STS 27R
End of life

Out of service	March 1997
Cause	deorbited
Decay	March 1997


 Lacrosse 2

Also called USA 069

General

Designation	21147 / 91017A
Launch date	8 Mar 1991
Country of origin	United States
Mission	Military: reconnaissance
Perigee/Apogee	700 km
Inclination	68°
Period
Launch vehicle	Titan 4


 Lacrosse 3

Also called USA 133

General

Designation	25017 / 97064A
Launch date	24 Oct 1997
Country of origin	United States
Mission	Military: reconnaissance
Perigee/Apogee	700 km
Inclination	57°
Period
Launch vehicle	Titan 4 #22

Apparently replaces Lacrosse 1

has a Lockheed/Sunnyvale Bus-1


 Program: Ladybug

Ka-band telecommunication program operated by KaStar Satellite Communications Corp. Was approved by the FCC in May 1997 except for the inter satellite link

The first satellite should be delivered on orbit before Feb 2002

2 satellites planned: Ladybug 1 at 73°W and Ladybug 2 at 109.2°W. The company also has applied for two other slots at 52 degrees and 175 degrees.

cost: $300 for the 2 satellites

Will provide T1 and high bandwidth pipes

Technical data

Specifications

Prime contractor	SS/L
Platform
Mass at launch	4242 kg
Dry mass	2385 kg
Dimension	2 x 2 x 3.6 m
Solar array	28 m span
Stabilization	3-axis
DC power	EOL: 10000 W
Design lifetime	10-15 years

Command and telemetry in C- and Ka-band

Ka-band

Main transponders	48
Backup transponders	6
Power	30 W
Bandwidth	125 MHz
Coverage	all the 50 states with: 4 spotbeams 1 CONUS
EIRP max
Polarization
Frequencies	Uplink: 28.35-28.60 and 29.25-29.5 GHz Downlink: 19.7-20.2 GHz

plans 60 GHz inter-satellite links (120 MHz)

on-board switching

12 times frequency reuse?


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 Program: Lageos

LAser GEOdynamic Satellite

American scientific program operated by CNR/PSN/NASA

Series of satellites designed to provide an orbiting benchmark for geodynamical studies of the Earth. Mission: accurate measurement of satellite's position with respect to Earth; determination of the planet's shape (geoid) and determination of tectonic plate movements associated with continental drift.


Program: Lageos

Lageos 1

Lageos 2


Lageos's specifications

Mass at launch	410 kg
Diameter	0.6 m
Stabilization	passive
Design lifetime	50 years


Lageos's payload

Retroreflectors mounted on the surface of the sphere

Number of retroreflectors	426 (422 fused silica, 4 germanium)
Individual diameter	3.8 cm
Accuracy	ground transmitter position can be determined to a few cm; tectonic motion to a few mm/year
Contruction material	aluminum with a brass core


 Lageos 1

General

Designation	08820 / 76039A
Launch date	4 May 1976
Country of origin	United States
Mission	Scientific: geodesy
Perigee/Apogee	5836/5947 km
Inclination	109.8°
Period	225.4 min
Launch vehicle	Thor Delta #123
Technical data

Specifications

Payload


 Lageos 2

General

Designation	22195 / 92070B
Launch date	22 Oct 1992
Country of origin	United States
Mission	Scientific: geodesy
Perigee/Apogee	5615/5952 km
Inclination	52.6°
Period	222.5 min
Launch vehicle	STS 52
Technical data

Specifications

Payload

Prime contractor: Aeritalia


 Program: Landsat

Also called ERTS (Earth Resources Technology Satellites)

The idea of a civil Earth observation program came in 1962 but the first Landsat was launched only 10 years after because of political and technical choices. In fact alot of technology was classified and could be used for civil purposes. Agencies like the Geological Survey had to put pressure to make the program start. The sensibility of the resolution was longly discussed (efficient but not too efficient!).

In 1984 the Congress gave EOSAT (Earth Observation SATellite corporation) the right to commercialize the pictures but it didn't make Landsat self financed.

Landsat 1 series

Made of Landsat 1, 2 & 3. Descending node at 09:30 and 18 days orbital cycle

Based on the Nimbus platform. Were equipped with the RBV (Return Beam Vidicon) TV camera and the MSS (MultiSpectral Scanner) radiometer. Such a camera had been used by the lunar observation program Ranger. The satellites transmit their data in real time to Eath stations when they are available otherwise the data is recorded on-board.

Has the same MSS as Landsat 4 & 5

Landsat 2 series

Made of Landsat 4 & 5. Descending node at 09:37 and 16 days orbital cycle

The data is transmitted by the TDRS network.

Specifications

Payload

Landsat 3 series

Made of Landsat 6 & 7. 16 days orbital cycle

Specifications

Payload

External resources

http://geo.arc.nasa.gov/sge/landsat/landsat.html

http://edcwww.cr.usgs.gov/glis/hyper/guide/landsat

http://edcwww.cr.usgs.gov/glis/hyper/guide/landsat_tm

http://mtpe.gsfc.nasa.gov/landsat/default.htm


Program: Landsat

Landsat 1

Landsat 2

Landsat 3

Landsat 4

Landsat 5

Landsat 6

Landsat 7


Landsat 4 & 5's specifications

Prime contractor	GE Astro
Platform	MultiMission Spacecraft (MMS)
Mass at launch	1941 kg
Length	4 m
Stabilization	3-axis
Design lifetime	3 years


Landsat 4 & 5's payload

MSS (Multispectral Scanner System)

Wavebands	0.5-0.6 µm (green): mapping coastal features in sediment-laden water 0.6-0.7 µm (red): mapping roads and urban areas 0.7-0.8 µm (red to near IR): as below 0.8-1.1 µm (near IR): vegetation studies and mapping land/water boundaries
Resolution	80 m
Swath width	185 km
TM (Thematic Mapper)

Wavebands	0.45-0.52 µm (visible): soil/vegetation differentiation & coastal water mapping 0.52-0.60 µm (visible): vegetation mapping 0.63-0.69 µm (visible): plant species differentiation 0.76-0.90 µm (near IR): biomass survey 1.55-1.75 µm (IR): snow/cloud differentiation 10.4-12.5 µm (thermal IR): thermal mapping 2.08-1.35 µm (IR): geological mapping
Resolution	30 m (visible, near & middle IR); 120 m (thermal IR)
Swath width	185 km


Landsat 6 & 7's specifications

Prime contractor	GE Astro
Platform	Tiros N / DMSP
Mass at launch	2750 kg
Mass in orbit	2000 kg
Length	6.4 m
Width	1.22 m
Stabilization	3-axis
DC Power	1500 W
Design lifetime	5 years


Landsat 6 & 7's payload

MSS identical to Landsat 4 & 5

ETM (Enhanced Thematic Mapper)

Wavebands	0.45-0.52 µm (visible) 0.52-0.60 µm (visible) 0.63-0.69 µm (visible) 0.76-0.90 µm (near IR) 1.55-1.75 µm (IR) 10.4-12.5 µm (thermal IR) 2.08-2.35 µm (IR) 0.5-0.9 µm (panchromatic)
Resolution	15 m (panchromatic), 30 m (visible. near & middle IR)
Swath width	185 km
SeaWiFS (Sea-viewing Wide Field Sensor)

Wavebands	0.43-0.45 µm (visible): low chlorophyll 0.49-0.51 µm (visible): other pigments 0.55-0.57 µm (visible): baseline chlorophyll 0.65-0.67 µm (visible): subsurface scattering 0.74-1.78 µm (near IR): atmospheric correction 0.84-0.89 µm (near IR): atmospheric correction 10.5-11.5 µm (IR): sea-surface temperature 11.5-12.5 µm (IR): sea-surface temperature
Resolution	1.13 km (local area coverage) 4.5 km (global area coverage)
Swath width	2800 km
Revisit interval	1 day


 Landsat 1

Also called ERTS 1

General

Designation	06126 / 72058A
Launch date	23 Jul 1972
Country of origin	United States
Mission	Remote sensing
Perigee/Apogee	895/908 km
Inclination	99.4°
Period	103 min
Launch vehicle	Thor Delta #89
Mass at launch	816 kg

Has provided over 1 million multispectral photos

End of life

Out of service	1980


 Landsat 2

Also called ERTS 2

General

Designation	07615 / 75004A
Launch date	22 Jan 1975
Country of origin	United States
Mission	Remote sensing
Perigee/Apogee	898/912 km
Inclination	98.9°
Period	103.1 min
Launch vehicle	Thor Delta #107
End of life

Out of service	Feb 1982


 Landsat 3

Also called ERTS 3

General

Designation	10702 / 78026A
Launch date	5 Mar 1978
Country of origin	United States
Mission	Remote sensing
Perigee/Apogee	895/915 km
Inclination	98.9°
Period	103.1 min
Launch vehicle	Thor Delta #139


 Landsat 4

General

Designation	13367 / 82072A
Launch date	16 Jul 1982
Country of origin	United States
Mission	Remote sensing
Perigee/Apogee	696/708 km
Inclination	98.1°
Period	98.8 min
Launch vehicle	Thor Delta #163
Technical data

Specifications

Payload

Downlink frequency: 2229.5 / 2265.5 MHz


 Landsat 5

General

Designation	14780 / 84021A
Launch date	1 Mar 1984
Country of origin	United States
Mission	Remote sensing
Perigee/Apogee	698/706 km
Inclination	98.1°
Period	98.8 min
Launch vehicle	Thor Delta #174
Technical data

Specifications

Payload


 Landsat 6

General

Designation	n/a
Launch date	5 Oct 1993 at 17:56 UT
Country of origin	United States
Mission	Remote sensing
Launch vehicle	Titan 2 #16
End of life

Out of service	5 Oct 1993
Cause	Attitude control failure

Cost: $220 million

After rupture of a hydrazine manifold disabled attitude control the satellite began to tumble at the start of the apogee-motor (Thiokol Star 37XFP) firing, and did not reach orbit.

Technical data

Specifications

Payload


 Landsat 7

General

Designation	25682 / 99020A
Launch date	15 Apr 1999
Country of origin	United States
Mission	Remote sensing
Perigee/Apogee	705 km sun synchronous (descending node: 10:00)
Inclination	98.2°
Period	99 min (16-day cycle)
Launch vehicle	Delta 2 #268

Launch under the MELVS contract. The satellite will be operated by NASA's Goddard until Oct 2000 and then be transfered to thr US Geological Survey.

External resources

http://geo.arc.nasa.gov/sge/landsat/l7.html

Technical data

Specifications

Payload

TDRS used for telemetry and command:

Telemetry: 2287.5 MHz (1.216 Mbps or upto 4.864 Mbps in SSA mode)

Command: 2106.4 MHz (125 kbps or upto 1 kbps in SSA mode)

Data: 8212.5 & 8342.5 MHz (150 Mbps each, can be used at the same time)


 Program: LCS

American radar calibration military program


Program: LCS

LCS 1

LCS 2

LCS 4


 LCS 1

General

Designation	01361 / 65034C
Launch date	6 May 1965
Country of origin	United States
Mission	Military
Perigee/Apogee	2786/2795 km
Inclination	32.1°
Period	145.6 min
Launch vehicle	Titan 3 #4


 LCS 4

Also called Gridsphere 1

General

Designation	05396 / 71067F
Launch date	7 Aug 1971
Country of origin	United States
Mission	Military
Perigee/Apogee	779/910 km
Inclination	87.6°
Period	101.8 min
Launch vehicle
Launch site	Vandenberg
End of life

Decay	11 Jun 1972


 LDEF

Long Duration Exposure Facility

General

Designation	14898 / 84034B
Launch date	6 Apr 1984
Country of origin	United States
Mission	Scientific: Meteorite observation
Perigee/Apogee	344/348 km
Inclination	28.5°
Period	91.5 min
Launch vehicle	STS 13

Mass at retrieval: 10.5 t with 10000 samples

Developed by NASA (Langley Research Center)

End of life

Out of service	9 Jan 1990
Cause	Retrieved by STS 32R
Decay	20 Jan 1990
External resources

http://dbdev.larc.nasa.gov/setas/LDEF/


 Program: Leasat

LEAsed SATellite

American military telecommunication satellite program launched in 1978 (under contract from the DoD). The satellites (Syncom 4 series) are operated by US Navy. The Leasat system is connected to the Navel Telecommunications Command Operational Center (NTCOC) in Washington, DC

5 satellites were ordered, 1 initially intended as ground spare together with an operational center, 4 fixed ground stations and 2 mobile ones.

Contact

Operator: Naval Space Command

External resources

http://www.fas.org/spp/military/program/com/leasat.htm


Program: Leasat

Leasat 1

Leasat 2

Leasat 3

Leasat 4

Leasat 5


Leasat's specifications

Prime contractor	Hughes
Platform	HS-381
Mass at launch	6895 kg (after STS crade separation)
Mass in orbit	1388 kg
Dimension	4.26 m diameter x 6.17 m high deployed (4.29 m stowed)
Solar array
Stabilization	spin stabilized
DC power	EOL: 1238 W Eclipse: 3 25 A-hr nickel-cadmium batteries
Design lifetime
Telemetry & beacon	7250 to 7500 MHz, and 7975 to 8025 MHz

Designed only for launch from STS


Leasat's UHF-band (240 - 400 MHz)

Main transponders	13
Backup transponders
Power
Bandwidth
Coverage
EIRP max
Polarization


 Leasat 1

Also called Syncom 401

General

Designation	15384 / 84113C
Launch date	10 Nov 1984
Country of origin	United States
Mission	Military: telecommunications
Geostationary orbit
Launch vehicle	STS 19

It wasn't launched first because of an aborted STS launch in June 1984

End of life

Out of service	yes
Technical data

Specifications

UHF-band


 Leasat 2

Also called Syncom 402

General

Designation	15236 / 84093C
Launch date	30 Aug 1984
Country of origin	United States
Mission	Military: telecommunications
Geostationary orbit	see below
Launch vehicle	STS 23
Location

Begin	End	Position
L: 30 Aug 1984
early 1994	early 1994	73°E
Feb 1995	Sep 1996	177.5°W, inclined
End of life

Out of service	Sep 1996
Cause	Deorbited
Technical data

Specifications

UHF-band


 Leasat 3

Also called Syncom 403

General

Designation	15643 / 85028C
Launch date	12 Apr 1985
Country of origin	United States
Mission	Military: telecommunications
Geostationary orbit	see below
Launch vehicle	STS 16

When released from STS 16 it failed to reach GEO and was repaired by STS 27

Location

Begin	End	Position
L: 12 Apr 1985
early 1994	Sep 1996	105°W, inclined
End of life

Out of service	Sep 1996
Cause	Deorbited
Technical data

Specifications

UHF-band


 Leasat 4

Also called Syncom 404

General

Designation	15995 / 85076D
Launch date	29 Aug 1985
Country of origin	United States
Mission	Military: telecommunications
Geostationary orbit	n/a
Launch vehicle	STS 27
End of life

Out of service	Sep 1985
Cause	UHF downlink failed during tests in GEO
Technical data

Specifications

UHF-band


 Leasat 5

Also called Syncom 405

General

Designation	20410 / 90002B
Launch date	9 Jan 1990
Country of origin	United States
Mission	Military: telecommunications
Geostationary orbit	see below
Launch vehicle	STS 32R
Location

Begin	End	Position
L: 12 Apr 1985
early 1994	early 1994	177°W
Feb 1995	May 1997	71.5°E, inclined
May 1997	Feb 1998	drifting 72°E - 77°E, inclined
Apr 1998		156°E, inclined

In May 1998 the satellite was leased to Australian Defence Force (Royal Australian Navy) for up to 5 years. The satellite was relocated at 156°E.

Leasat 5 began limited service to the Australian Defence Force on Oct. 17, 1997. The PanAmSat Operations Center in Long Beach, Calif. provided the tracking, telemetry, and control capability via its Guam ground station.

Technical data

Specifications

UHF-band


 Program: LEO One

US program from dBX Corp.  It comprises 48 LEO satellites (8 planes, 50° inclination) at 950 km for mobile messaging (vehicle tracking, pager alerts, monitoring). Worth $250 million  Operator: LEO One FCC authorized.

Each satellite should weigh 125 kg, lifetime: 5 to 7 years

Uplink: 148-150.05 MHz

Downlink: 137-137.025 MHz and 400.15-401 MHz


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 Program: LES

Lincoln Experimental Satellite

American military tactical program designed by the Lincoln lab


Program: LES

LES 1

LES 2

LES 3

LES 4

LES 5

LES 6

LES 8

LES 9


 LES 1

General

Designation	01002 / 65008C
Launch date	11 Feb 1965
Country of origin	United States
Mission	Military: ?
Perigee/Apogee	2783/2809 km
Inclination	32.1°
Period	145.8 min
Launch vehicle	Titan 3 #3


 LES 2

General

Designation	01360 / 65034B
Launch date	6 May 1965
Country of origin	United States
Mission	Military: ?
Perigee/Apogee	2771/14810 km
Inclination	32.2°
Period	309.9 min
Launch vehicle	Titan 3 #4


 LES 3

General

Designation	01941 / 65108D
Launch date	21 Dec 1965
Country of origin	United States
Mission	Military: ?
Perigee/Apogee	267/4829 km
Inclination	26.5°
Period	139.9 min
Launch vehicle	Titan 3 #7
End of life

Decay	6 Apr 1968


 LES 4

General

Designation	01870 / 65108B
Launch date	21 Dec 1965
Country of origin	United States
Mission	Military: ?
Perigee/Apogee	189/33632 km
Inclination	26.6°
Period	589.2 min
Launch vehicle	Titan 3 #7
End of life

Decay	1 Aug 1977


 LES 5

General

Designation	02866 / 67066E
Launch date	1 Jul 1967
Country of origin	United States
Mission	Military: ?
Perigee/Apogee	33188/33618 km
Inclination	11.6°
Period	1316.1 min
Launch vehicle	Titan 3 #19

Could be equipped with a SNAP generator?


 LES 6

General

Designation	03431 / 68081D
Launch date	26 Sep 1968
Country of origin	United States
Mission	Military: telecommunications
Geostationary orbit
Launch vehicle	Titan 3 #31
End of life

Out of service	yes

Could be equipped with a SNAP generator?


 LES 8

General

Designation	08746 / 76023A
Launch date	15 Mar 1976
Country of origin	United States
Mission	Military: telecommunications
Geostationary orbit	see below
Launch vehicle	Titan 3 #93
Mass at launch	450 kg

LES 8 & 9 were placed in geostationary orbit with 90° between each other. Equipped with a radio isotropic 238 plutonium generator, they could communicate without the help of a ground station.

Location

Begin	End	Position
L: 15 Mar 1976		?
Mar 1995		94.5°W, inclined
Jan 1996		103°W, inclined


 LES 9

General

Designation	08747 / 76023B
Launch date	15 Mar 1976
Country of origin	United States
Mission	Military: telecommunications
Geostationary orbit	see below
Launch vehicle	Titan 3 #93
Mass at launch	450 kg

LES 8 & 9 were placed in geostationary orbit with 90° between each other. Equipped with a radio isotropic 238 plutonium generator, they could communicate without the help of a ground station.

In 1998 the satellite is still active, relaying communications with the South Pole

Location

Begin	End	Position
L: 15 Mar 1976		?
Mar 1995		105°W, inclined
Technical data

Transponder frequency chart (MHz)

Uplink	Transponder	Downlink
303.150	1	249.350
303.175	2	249.375
303.200	3	249.400
303.225	4	249.425
303.250	5	249.450
303.275	6	249.475
303.300	7	249.500
303.325	8	249.525
303.350	9	249.550
303.375	10	249.575
303.400	11	249.600
303.425	12	249.625
303.450	13	249.650
303.475	14	249.675
303.500	15	249.700
303.525	16	249.725
303.550	17	249.750
303.575	18	249.775
303.600	19	249.800
303.625	20	249.825
303.650	21	249.850


 Lewis

Named for 19th century explorer Meriwether Lewis

General

Designation	24909 / 97044A
Launch date	23 Aug 1997
Country of origin	USA
Mission	Scientific: Remote sensing
Perigee/Apogee	300 km
Inclination	97.5°
Period	95 min
Launch vehicle	Athena #2
Launch site	Vandenberg SLC6

Part of the Small Spacecraft Technology Initiative (SSTI), for NASA.

End of life

Out of service	26 Aug 1997
Cause	Went out of control after wrong maneuver
Decay	28 Sep 1997

It would have flown 3 imaging spectrometers to gather high resolution spectral images of the Earth's surface and atmosphere, celestial objects. 5 m resolution Panchromatic, 30 m resolution Multispectral

Total cost for NASA: $64.8 million  An additional $6.2 million was spent for 1-year storage and maintenance due to delayed launch

External resources

http://crsphome.ssc.nasa.gov/SSTI/WELCOME.HTM

Technical data

Specifications

Prime contractor	TRW
Platform
Mass at launch	385 kg
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime	5 years

Telemetry: 2275.3 MHz (8 kbps)

Command: 2095.172 MHz (2 kbps)

Data: 2275.3 MHz (2.048 Mbps)

Payload

HSI: Hyper Spectral Imager (will enable to collect data in 384 channels whereas currently standard instruments are limited to 20 channels (range 0.4 µm to 2.5 µm)) (built by TRW)

LEISA: Linear Etalon Imaging Spectral Array (built by NASA Goddard)

UCB: Ultraviolet Cosmic Background Experiment (built by Berkeley)

Lewis will also carry 15 technology demonstrations experiments.


 Lightsar

General

Designation
Launch date
Country of origin	United States
Operator	NASA
Mission	Scientific: remote sensing
Perigee/Apogee
Inclination
Period
Launch vehicle
Launch site

Would use advanced technologies to reduce the cost and enhance the quality of radar-based information for scientific research, commercial remote-sensing and emergency management applications.

External resources

http://southport.jpl.nasa.gov/lightsar/index.html


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 Program: LLMSIRIS

Little Leo Messaging System - Intercontinental Retrieval of Information via Satellite

Belgian project for a LEO messaging system. It is supported by SAIT Systems. The total program is said to cost $33 million. Part of the ARTES (Advanced research in telecommunications systems) program of ESA

The first payload (approx 50 kg?) was attached to Resurs O1-4

Technical data

Specifications

Prime contractor	SAIT Systems
Platform
Mass at launch	60 kg
Mass in orbit
Dimension	0.5 x 0.5 x 0.5 m
Solar array
Stabilization
DC power	EOL: 30 W
Design lifetime	3 years

frequencies probably close to 400 MHz & 388 MHz


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 Program: Loralsat

Telecommunication satellite programm operated by Loral Space & Communications Ltd

In Ku-band 2 satellites are planned (Loralsat 101 & 102) plus 1 ground spare. Project worth $250 million.

For Ku-band there are other projects: a satellite could be located at 81°W to broadcast over all america (14.0-14.5/11.7-12.2 GHz for North America, 13/75-14.0/11.45-11.7 GHz for South). At 77°W yet another satellite is planned to cover all America (13.75-14.0/11.45-11.7 GHz for North and South America and 6.425-6.725/3.4-3.7 GHz for South America)

From the same operator, in Ka-band see Cyberstar

Technical data


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Program: Loralsat

Loralsat 101

Loralsat 102


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Loralsat 101 & 102's specifications

Prime contractor	Space Systems/Loral
Platform
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime	12 years


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Loralsat 101 & 102's C-band

Main transponders	24
Backup transponders
Power	20 W
Bandwidth
Coverage
EIRP max
Polarization


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Loralsat 101 & 102's Ku-band

Main transponders	32
Backup transponders
Power	110 W
Bandwidth
Coverage	USA (including Hawaii and Alaska, Puerto Rico and the Virgin Islands)
EIRP max
Polarization


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 Loralsat 101

General

Designation
Launch date	initially planned in 1999
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	129°W
Launch vehicle	Ariane

Loralsat 102 should be identical and located at 77°W.

It should be identical to Telstar 7.

Technical data

Specifications

C-band

Ku-band


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 Loralsat 102

General

Designation
Launch date	initially planned in 2000
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	77°W
Launch vehicle	Ariane
Technical data

Specifications

C-band

Ku-band


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 Lusat

Also called Microsat 4 or LO-19 or Oscar 19

General

Designation	20442 / 90005G
Launch date	22 Jan 1990
Country of origin	Argentina
Mission	Telecommunications
Perigee/Apogee	779/797 km
Inclination	98.6°
Period	100.6 min
Launch vehicle	Ariane V35
Mass at launch	9 kg

Based on an Amsat-NA Microsat bus

External resources

http://www.amsat.org/amsat/sats/nk6k/msatmain.html

Technical data

Passive stabilization

Uplink	1200 bps Manchester coded (Biphase-L) FSK (FM) AX.25 145.840 145.860 145.880 145.900 MHz
Downlink	1200 bps BPSK (SSB) AX.25, either one of the two frequencies below: 437.154 MHz (LHCP in northern hemisphere), normal unfiltered PSK 437.126 MHz (RHCP in northern hemisphere), Raised Cosine modulation
CW beacon	437.126 MHz (when active)


 Program: M-Star

Planned global satellite network; to be designed by Motorola; total cost: $6.1 billion  The company plans to earn $32 billion from the system over a 10-year period.

Would be made of 72 LEO satellites. First launches planned in early 1997. throughput: 40 Gbps

Should be operational in 2002


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 M2A

Multi-Media Asia, M²A

General

Designation
Launch date	initially planned in mid-1999
Country of origin	Indonesia
Operator	PT PSN
Mission	Telecommunications
Geostationary orbit	134°E or 118°E
Launch vehicle	Proton
Launch site

Project worth $350 million. To be delivered in-orbit With this order an option for 5 additional satellites was secured. See also Palapa

M2A is a joint venture between Pasifik Satelit Nusantara and Indosat

The ground segment of the program is worth $115 million, granted to Alcatel

The satellite might be delayed or cancelled because of the Asian currency crisis.

Technical data

Specifications

Prime contractor	Space Systems/Loral
Platform	FS-1300
Mass at launch
Mass in orbit
Dry mass	1960 kg
Dimension
Solar array
Stabilization	3-axis
DC power	10400 W
Design lifetime	12 years
C-band

Main transponders	24
Backup transponders
Power
Bandwidth
Coverage
EIRP
Polarization
Frequencies	3.7-4.2 GHz
Extended C-band

Main transponders	28
Backup transponders
Power
Bandwidth
Coverage
EIRP
Polarization
Frequencies	3.4-3.7 GHz
X-band

Main transponders	2
Backup transponders
Power
Bandwidth
Coverage
EIRP
Polarization

Direct broadcast is planned in C-band

Will have 7 shaped spot beams and 1 global beam. Coverage of the Asia Pacific region, including Indonesia, Australia, India, China, Indochina, Korea, Japan and ASEAN

The repeater module is provided by Alcatel Espace


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 Program: Mabuhay

Geostationary telecommunication program operated by MPSC.

Mabuhay Philippines Satellite Corp. (MPSC) is controlled by PLDT (51%).  Partners are Philippines Communications Satellite Corp (Philcomsat), Republic Broadcasting System, China Everbright Group, Cable Entertainment Group, PT PSN.

PLDT announced they would launch 3 satellites in late 1996-1998.  In mid 1996 Palapa B2P was bought in orbit to act as the first Mabuhay bird

Agila means "Philippines Eagle"  This name is a kind of brand name in the Philippines as the national satellite system. Competitors are fighting to be able to use that name...

Mabuhay 2 should go to 153°E (after year 2000)


Program: Mabuhay

Mabuhay 0 (Palapa B2P)

Mabuhay 1


 Mabuhay 1

Should be called Agila 2 after successful launch

General

Designation	24901 / 97042A
Launch date	19 Aug 1997
Country of origin	Philippines
Mission	Telecommunications
Geostationary orbit	146°E
Launch vehicle	Long March #44

Cost: $230 million.  Two transponders are owned by PT Pasifik Satelit Nusantara

Was not delivered in the exact orbit and had to burn extra fuel to move 3000 km. The lifetime is said not to have been reduced by this operation.

The planned location was 144°E, but there are interference problems in Ku-band with nearby Superbird C satellite. Despite the move, only 18 transponders can be activated in Ku-band.

Technical data

EIRP coverage (dBW)

C-band

Ku-band

G/T coverage (dB/K)

C-band

Specifications

Prime contractor	Space Systems/Loral
Platform	FS-1300
Mass at launch	3775 kg
Mass in orbit	1700 kg
Dimension	30.7 x 5.12 x 8.6 m
Solar array
Stabilization	3-axis
DC power	BOL: 10000 W EOL: 8000 W
Design lifetime	12 years
C-band

Main transponders	24 + 6
Backup transponders	8
Power	27 W
Bandwidth	36 MHz
Coverage	entire South-East and Pacific Rim & Hawaii
EIRP max	35 dBW
Polarization	linear H/V
Beacons	4.196 H & 4.198 V GHz
C-band Transponder frequency chart (GHz)

Horizontal  Uplink	Horizontal Downlink	Transponder	Vertical Downlink	Vertical  Uplink
	3.580	25		6.605
6.625		26	3.600
	2.620	27		6.645
6.665		28	3.640
	3.660	29		6.685
6.705		30	3.680
	3.720	1		5.945
5.965		2	3.740
	3.760	3		5.985
6.005		4	3.780
	3.800	5		6.025
6.045		6	3.820
	3.840	7		6.065
6.085		8	3.860
	9.880	9		6.105
6.125		10	3.900
	3.920	11		6.145
6.165		12	3.940
	3.960	13		6.185
6.205		14	3.980
	4.000	15		6.225
6.245		16	4.020
	4.040	17		6.265
6.285		18	4.060
	4.080	19		6.305
6.325		20	4.100
	4.120	21		6.345
6.365		22	4.140
	4.160	23		6.385
6.402		24	4.177
Ku-band

Main transponders	24
Backup transponders	8
Power	110 W
Bandwidth	36 MHz
Coverage	Philippines, Coastal China, Taiwan and northern Vietnam
EIRP max	55 dBW
Polarization	linear H/V
Beacons	12.255755 H & 12.24915 V GHz

Can operate as 12 transponders at 220 W

Ku-band Transponder frequency chart (GHz)

Horizontal  Uplink	Horizontal Downlink	Transponder	Vertical Downlink	Vertical  Uplink
14.039		1	12.221
	12.221	13		14.039
14.079		2	12.261
	12.261	14		14.079
14.119		3	12.301
	12.301	15		14.119
14.159		4	12.341
	12.341	16		14.159
14.199		5	12.381
	12.381	17		14.199
14.239		6	12.421
	12.421	18		14.239
14.279		7	12.461
	12.461	19		14.279
14.319		8	12.501
	12.501	20		14319
14.359		9	12.541
	12.541	21		14.359
14.399		10	12.581
	12.581	22		14.399
14.439		11	12.621
	12.621	23		14.439
14.479		12	12.661
	12.661	24		14479


Mabuhay 1's C-band EIRP coverage


Mabuhay 1's Ku-band EIRP coverage


Mabuhay 1's C-band G/T coverage


 Program: Magion

Czech scientific program designed with the help of the Russians and other former East-bloc countries.

External resources

http://www.ufa.cas.cz/html/magion/magion.html

http://www.iki.rssi.ru/interball/magion.html


Program: Magion

Magion 1

Magion 2

Magion 3

Magion 4

Magion 5


 Magion 1

General

Designation	11110 / 78099C
Launch date	24 Oct 1978
Country of origin	Czechoslovakia
Mission	Scientific
Perigee/Apogee	404/762 km
Inclination	83°
Period	96.4 min
Launch vehicle	Cosmos C
Launch site	Plesetsk
End of life

Decay	11 Sep 1981


 Magion 2

General

Designation	20281 / 89080B
Launch date	28 Sep 1989
Country of origin	Czechoslovakia
Mission	Scientific: magnetosphere study
Perigee/Apogee	498/2441 km
Inclination	82.6°
Period	115.3 min
Launch vehicle	Cyclone 3 #79


 Magion 3

General

Designation	21835 / 91086E
Launch date	18 Dec 1991
Country of origin	Czechoslovakia
Mission	Scientific: magnetosphere study
Perigee/Apogee	435/3045 km
Inclination	82.6°
Period	121.3 min
Launch vehicle	Cyclone 3 #97
Technical data

Downlink frequency: 135.150/137.850 MHz


 Magion 4

Also called C2-X

General

Designation	23646 / 95039F
Launch date	2 Aug 1995 at 23:59 UT
Country of origin	Czech Republic
Mission	Scientific: magnetosphere study
Perigee/Apogee	760/191760 km
Inclination	63.3°
Period	5454 min
Launch vehicle	Molniya M
Launch site	Plesetsk LC43
Mass at launch	50 kg

It carries instruments to measure electric and magnetic fields for comparison with the Prognoz instruments.


 Magion 5

Also called C2-A

General

Designation	24293 / 96050C
Launch date	29 Aug 1996 at 05:22 UT
Country of origin	CIS
Mission	Scientific: aurora study
Perigee/Apogee	782/19140 km
Inclination	62.8°
Period
Launch vehicle	Molniya M
Launch site	Plesetsk LC43
Mass at launch	58 kg

Had problems to unfold one of its solar panels.  In May 1998, the satellite could finally be activated (by repeatedy sending telemetry commands).


 Maqsat B

General

Designation	25024 / 97066B
Launch date	30 Oct 1997
Country of origin	Europe
Mission	Technology
Perigee/Apogee	554/26612 km
Inclination	7.7°
Period	468 min
Launch vehicle	Ariane V101

Built by Kayser-Threde of Munich, Germany. It is a smaller dummy satellite stored below the SPELTRA dual launch adapter and which remains attached to the EPS stage.

External resources

http://www.estec.esa.nl/teamsat/


 Maqsat H

Also called Teamsat (Technology, science and Education experiments Added to Maqsat)

General

Designation	25023 / 97066A
Launch date	30 Oct 1997
Country of origin	Europe
Mission	Technology
Perigee/Apogee	554/26612 km
Inclination	7.7°
Period	468 min
Launch vehicle	Ariane V101

Dummy satellite full of instruments to measure environment of launch. This satellite contained the Teamsat experiment, which released the YES satellite.

External resources

http://www.estec.esa.nl/teamsat/

Technical data

Built by Kayser-Threde of Munich, Germany. Teamsat was produced in 7 months at ESTEC. 2300 kg

Experiments:

Orbiting Debris Device(ODD) - Automation & Informatics Department, ESTEC. The MAQSAT-H satellite is painted with contrasting patterns (75% white and 25% black) to support testing and calibration of ground-based optical and radar stations in Europe. The contrasting paint should also allow detection of the rotation or tumbling of MAQSAT-H. Additionally, surface paint degradation will be studied.

Autonomous Vision System (AVS) - Technical University of Denmark. AVS is a camera which automatically recognises and tracks stars or non-stellar objects (such as satellites). AVS can be used to identify specific stars, determine the attitude of satellites for navigation purposes and acquire images.

Visual Telemetry System (VTS) - MMS Bristol (UK) / IMEC and OIP (Belgium). VTS is an imaging system to monitor spacecraft activities such as the operations of critical mechanisms. TEAMSAT hosts a system of three cameras and a master unit to provide compressed image sequences of the fairing opening and satellite separations.

Flux Probe Experiment (FIPEX) - University of Stuttgart. FIPEX will measure the concentration of atomic oxygen at altitudes up to 1000 kilometres. Atomic oxygen is known for its erosion effect and degradation of optical surfaces and lenses.


 Maqsat 3

General

Designation	25503 / 98059A
Launch date	21 Oct 1998
Country of origin	Europe
Mission	Technology
Perigee/Apogee	1152 x 36612 km
Inclination	7.0°
Period	655.9 min
Launch vehicle	Ariane V112

Maqsat 3 was not fully instrumented; the number of sensors was limited to a dozen shock transducers and strain gauges situated particularly around the interface with the payload adapter.

The satellite was not separated at GTO injection point to avoid increasing space debris.

Technical data

Specifications

Prime contractor	Kayser-Threde of Munich
Platform
Mass at launch	2730 kg
Mass in orbit
Dimension	2 m diameter x 2.5 m long
Solar array
Stabilization
DC power
Design lifetime


 Program: Marathon

Planned by Russian and Italian companies: system for fixed and mobile communications made of 9 satellites

The operator would be Informcosmos and the prime contractor NPO PM

The satellite could also be called Arkos


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 Program: Marecs

European maritim telecommunication program designed from the Eutelsat platform. Operated by ESA.

Satellites used by Inmarsat

External resources

http://www.vilspa.esa.es/marecs/marecs.html

http://www.esoc.esa.de/external/mso/marecs.html


Program: Marecs

Marecs A

Marecs B1

Marecs B2


Marecs's specifications

Prime contractor	British Aerospace (now MMS)
Platform	ECS
Mass at launch	1056 kg
Payload mass	100 kg
Dimension	1.9 x 1.4 x 2.56 m
Solar array	13.9 m span
Stabilization	3-axis
DC power	EOL: 789 W
Design lifetime	7 years
Capacity	50 duplex voice channels


Marecs's L-band

Main transponders	1
Backup transponders	1
Power	50 to 60 W
Bandwidth
Coverage	global
EIRP max	35 dBW
Polarization


Marecs's C-band

Main transponders	1
Backup transponders
Power	20 W?
Bandwidth
Coverage	global
EIRP max
Polarization


 Marecs A

General

Designation	13010 / 81122A
Launch date	20 Dec 1981
Country of origin	Europe
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane L04
Location

Begin	End	Position
L: 20 Dec 1981		15°W / 26°W
21 Mar 1993	Aug 1996	22.8°E, inclined
End of life

Out of service	Aug 1996
Cause	deorbited
Technical data

Specifications

L-band

C-band

Transmits on 137.17 MHz


 Marecs B1

End of life

Out of service	10 Sep 1982
Cause	Ariane L05's launch failure
Technical data

Specifications

L-band

C-band


 Marecs B2

General

Designation	15386 / 84114B
Launch date	10 Nov 1984
Country of origin	Europe
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V11
Location

Begin	End	Position
L: 10 Nov 1984		55°W
21 Mar 1993	Feb 1997	14.9°W, inclined
Mar 1997		26°W, inclined
Technical data

Specifications

L-band

C-band

Transmits on 137.17 MHz


 Program: Marisat

Also called Gapfiller

American maritim telecommunication satellite program operated by Comsat. Was first used by military forces before been used by private companies. Also used by Inmarsat.

External resources

http://www.fas.org/spp/military/program/com/marisat.htm


Program: Marisat

Marisat 1

Marisat 2

Marisat 3


 Marisat 1

General

Designation	08697 / 76017A
Launch date	19 Feb 1976
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Thor Delta #120
Location

Begin	End	Position
L: 19 Feb 1976		105°W
Mar 1995	Mar 1997	106°W, inclined
End of life

Out of service	1 Apr 1997
Cause	deorbited
Technical data

Transmits in P- (250 MHz), L- (1.537-1.541 GHz) and C-band (4.195-4.199 GHz)

The satellite uses the military aviation band in the 248.850 and 249.325 MHz (25 KHz raster): 20 channels for voice and data. They are also two 500 KHz channels for wideband transmissions (254.150-257.550 MHz).


 Marisat 2

General

Designation	08882 / 76053A
Launch date	10 Jun 1976
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Thor Delta #124
Location

Begin	End	Position
L: 10 Jun 1976		73°E
Mar 1995	Sep 1996	72.5°E, inclined
End of life

Out of service	Sep 1996
Cause	deorbited
Technical data

Transmits in P- (250 MHz), L- (1.537-1.541 GHz) and C-band (4.195-4.199 GHz)

The satellite uses the military aviation band in the 248.850 and 249.325 MHz (25 KHz raster): 20 channels for voice and data. They are also two 500 KHz channels for wideband transmissions (254.150-257.550 MHz).


 Marisat 3

General

Designation	09478 / 76101A
Launch date	14 Oct 1976
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Thor Delta #127
Location

Begin	End	Position
L: 14 Oct 1976		15°W
Mar 1995		178°W, inclined
Oct 1996		72°E, inclined
Technical data

Transmits in P- (250 MHz), L- (1.537-1.541 GHz) and C-band (4.195-4.199 GHz)

The satellite uses the military aviation band in the 248.850 and 249.325 MHz (25 KHz raster): 20 channels for voice and data (uplink: 302.450 to 302.925 MHz). They are also two 500 KHz channels for wideband transmissions (254.150-257.550 MHz; uplink: 307.750-311.150 MHz). TT&C: 3945.5/3954.5 MHz


 Program: MDS

Mission Demonstration test Satellite

Japanese (NASDA) test satellites

External resources

http://oss1.tksc.nasda.go.jp/mds/index-e.html


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Program: MDS

MDS 1

MDS 2


 MDS 1

General

Designation
Launch date	initally planned in mid-2000
Country of origin	Japan
Mission	Scientific
Perigee/Apogee	500 / 36000 km
Inclination
Period
Launch vehicle	H2 #7
Launch site

To demonstrate and verify in orbit commercial parts mand miniature compoments. Will aslo measure cosmic radiation and space environment.

External resources

http://yyy.tksc.nasda.go.jp/Home/Satellites/e/mds_1_e.html

Technical data

Specifications

Prime contractor
Platform
Mass at launch	450 kg
Mass in orbit
Dimension
Solar array
Stabilization	spin-stabilized
DC power	900 W
Design lifetime	1 year


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 MDS 2

General

Designation
Launch date
Country of origin	Japan
Mission	Scientific
Perigee/Apogee	550 km
Inclination
Period
Launch vehicle
Launch site

To test the Experimental Lidar In Space Experiment (ELISE).

External resources

http://yyy.tksc.nasda.go.jp/Home/Satellites/e/mds_2_e.html

Technical data

Specifications

Prime contractor
Platform
Mass at launch	800 kg
Mass in orbit
Dimension
Solar array
Stabilization	3-axis
DC power	EOL: 1400 W
Design lifetime	1 year

Will illuminate earth with 2 lasers (different wave lengths) and measure the reflected light with a 1 m aperture telescope.


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 Program: Measat

Malaysian East Asian Satellite

Telecommunication program operated by Measat Broadcast Network Systems, a subsidiary of a 1987 privatized company.

Cost of the program: $235 million. Hughes also supplied equipment for a satellite control station on Malaysia's Langkawi Island and trained the Malaysian spacecraft controllers.


Program: Measat

Measat 1

Measat 2

Measat 3


 Measat 1

General

Designation	23765 / 96002B
Launch date	12 Jan 1996
Country of origin	Malaysia
Mission	Telecommunications
Geostationary orbit	91.5°E
Launch vehicle	Ariane V82
Technical data

EIRP coverage (dBW)

C-band

Ku-band

Specifications

Prime contractor	Hughes
Platform	HS-376 enhanced
Mass at launch	1450 kg
Mass in orbit	650 kg
Diameter	2.16 m
Height	7.82 m deployed
Stabilization	Spin stabilized
DC power	BOL: 1705 W? EOL: 800 W
Design lifetime	12 years

The satellite uses gallium arsenide solar cells instead of silicon.  It also features a specially contoured surface that eliminates the need for multiple feed horns. Also its has bipropellant propulsion system for stationkeeping and attitude control.

C-band

Main transponders	12
Backup transponders
Power	12 W (SSPA)
Bandwidth	36 MHz
Coverage	Malaysia, Philippines & South-India
EIRP max	39 dBW
G/T max	+3 dB/K
Polarization	linear
Frequencies	Uplink: 5.925-6.425 GHz Downlink: 3.700-4200 GHz
C-band transponder frequency chart (GHz)

Horizontal Downlink	Channel	Vertical Uplink
3.720	1	5.945
3.760	2	5.985
3.800	3	6.025
3.840	4	6.065
3.880	5	6.105
3.920	6	6.145
3.960	7	6.185
4.000	8	6.225
4.040	9	6.265
4.080	10	6.305
4.120	11	6.345
4.160	12	6.385
Ku-band

Main transponders	4
Backup transponders	1
Power	112 W (TWTA)
Bandwidth	54 MHz
Coverage	narrow spots: Malaysia or Philippines or South-India
EIRP max	57 dBW
G/T max	+11 dB/K
Polarization	linear
Frequencies	Uplink: 14.000-14.250 GHz Downlink: 10.950-11.200 GHz, switchable to 11.45-11.7 or 12.2-12.75 GHz
Ku-band transponder frequency chart (GHz)

Transponder	Vertical  Downlink	Horizontal  Uplink	Beam
1	10.982	14.032	Malaysia + Philippines
2	11.044	14.094	Malaysia + Philippines
3	11.106	14.156	Malaysia
4	11.168	14.218	Malaysia
5	12.284	13.784	South-India
6	12.346	13.846	South-India


Measat 1's C-band EIRP


Measat 1's Ku-band EIRP spots


 Measat 2

General

Designation	24653 / 96063B
Launch date	13 Nov 1996
Country of origin	Malaysia
Mission	Telecommunications
Geostationary orbit	148°E
Launch vehicle	Ariane V92
Technical data

EIRP coverage (dBW)

C-band

Ku-band

Specifications

Prime contractor	Hughes
Platform	HS-376HP
Mass at launch	1520 kg
Mass in orbit
Dimension	2.17 m diameter x 3.11 m (7.82 m deployed)
Solar array
Stabilization	spin stabilized
DC power	1705 W
Design lifetime	11 years

The satellite uses gallium arsenide solar cells instead of silicon.  It also features a specially contoured surface that eliminates the need for multiple feed horns. Also its has bipropellant propulsion system for stationkeeping and attitude control.

C-band

Main transponders	6
Backup transponders
Power	12 W
Bandwidth	72 MHz
Coverage	South-East Asia, East Australia and Hawaii
EIRP max	39 dBW
Polarization	linear
Frequencies	Uplink: 5.925-6.425 GHz Downlink: 3.700-4200 GHz
Ku-band

Main transponders	11
Backup transponders
Power	8 x 95 W 3 x 62 W
Bandwidth	48 MHz
Coverage	switchable (by transponder) to: Malaysia, Queensland/Australia, Philippines, India or Vietnam +Taiwan spot
EIRP max	57 dBW
Polarization	linear
Frequencies	Uplink: 14.000-14.250 GHz Downlink: 10.950-11.200 GHz, switchable to 11.45-11.7 or 12.2-12.75 GHz
Ku-band transponder frequency chart (GHz)

Transponder	Horizontal  Downlink	Vertical  Uplink	Beam
1	10.982	14.032
2	11.044	14.094
3	11.106	14.156
4	11.168	14.218
further specs. lacking


Measat 2's C-band EIRP


Measat 2's Ku-band EIRP spots


 Measat 3

General

Designation
Launch date	2001
Country of origin	Malaysia
Mission	Telecommunications
Geostationary orbit	91.5°E
Launch vehicle

Bidding for this satellite: HCI, Lockheed Martin, Loral Space and Aerospatiale

A new tender was issued in Feb 1999

Cost expected: below $300 million

Technical data

Specifications

Prime contractor
Platform
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime
C-band

Main transponders
Backup transponders
Power
Bandwidth	36 MHz
Coverage	East Asia and Australia Switchable beams over China, India, Middle East and Africa
EIRP max	41 dBW
G/T max	+4 dB/K
Polarization	linear
Frequencies	Uplink: 5.925-6.725 GHz Downlink: 3.400-4.200 GHz
Ku-band

Main transponders
Backup transponders
Power
Bandwidth	36 MHz
Coverage	Malaysia, India and Indochina (switchable beams)
EIRP max	54 dBW
G/T max	+13.5 dBW
Polarization	linear
Frequencies	Uplink: 14.000-14.250 GHz Downlink: 10.950-11.200 GHz, switchable to 11.45-11.7 or 12.2-12.75 GHz
Ka-band

Main transponders
Backup transponders
Power
Bandwidth	120 MHz
Coverage	Middle East and Asia (switchable/steerable beams)
EIRP max	62 dBW
G/T max	+21.5 dB/K
Polarization	linear
Frequencies	Uplink: 29.115-29.36 GHz Downlink:19.315-19.56 GHz


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 Megsat 0

General

Designation	25722 / 99022B
Launch date	28 April 1999
Country of origin	Italy
Mission	Technology
Perigee/Apogee	580 km
Inclination	48°
Period
Launch vehicle	Cosmos C
Launch site	Kapustin Yar

Operated by Megasat Space Division, a subsidiary of Meggiorin S.p.A.

A Megsat 1 is planned in 2000, should weigh 50 kg, 1000 km orbit, 81° inc. Should carry 2 payloads

External resources

http://www.megsat.com

Technical data

Specifications

Prime contractor
Platform
Mass at launch	34 kg
Mass in orbit
Dimension	43.5 x 40.5 x 55 cm
Solar array
Stabilization
DC power	35 W
Design lifetime

64 kbps downlink, for store-and-forward communications. Downlink: 137.935 MHz


 Meteor (US)

Multiple Experiment Transportation to Earth Orbit and Return

General

Designation	n/a
Launch date	23 Oct 1995
Country of origin	United States
Mission	Scientific: Microgravity
Perigee/Apogee	n/a
Inclination	n/a
Period	n/a
Launch vehicle	Conestoga #01
Mass at launch	~1000 kg

The satellite was a commercial microgravity recoverable spacecraft operated by EER Systems. Equipped with a Star 48 solid motor

The loss is amounted $20 million for the launcher and at least $73 million for the experiments

3 commercial experiments onboard:  an atomic-oxygen experiment from S-Cubed, a concentrator solar array from Able Engineering, and a Motorola payload whose details are unrevealed.

End of life

Out of service	23 Oct 1995
Cause	Launcher failed


 Program: Meteosat

Series of meteorological satellites operated by Eumetsat. The satellites observe cloud formation across the full Earth disk and generate images in 3 spectral bands every 30 minutes.

The 3 first satellites are experimental, the 3 next are operational: MOP (Meteosat OPerational). Then the program will use MTP (Meteosat Transition Program) and finally MSG (Meteosat Second Generation).

External resources

http://www.esoc.esa.de/external/mso/meteosat.html


Program: Meteosat

Meteosat 1

Meteosat 2

Meteosat 3

Meteosat 4

Meteosat 5

Meteosat 6

Meteosat 7

MSG


Meteosat 4, 5, 6's specifications

Prime contractor	Aerospatiale
Mass at launch	681 kg
Mass in orbit	316 kg
Diameter	2.1 m
Height	3.1 m
Stabilization	Spin stabilized (100 rpm)
DC power	BOL: 387 W EOL: 225 W
Design lifetime	5 years


Meteosat 4, 5, 6's payload

Multispectral Radiometer

Wavebands	0.4-1.1 µm (visible) 5.7-7.1 µm (IR): water vapor absorption 10.5-12.5 µm (thermal IR)
Resolution	visible: 2.5 km others: 5 km
Image repeat frequency	30 minutes (3 bands)
Telemetry - Data	UHF- and S-band (1 transponder per band)
Data rate	333 kbps (normal), 2.7 Mbps (burst)
MMD (Meteorological Data Dissemination)

Channel frequencies	digital high resolution (HR): 1694.5 MHz analogue weather facsimile (WEFAX): 1691 MHz
MDD (A & B)	1.695.77 +/- 0.165 MHz


 Meteosat 1

General

Designation	10489 / 77108A
Launch date	23 Nov 1977
Country of origin	Europe
Mission	Meteorology
Geostationary orbit
Launch vehicle	Thor Delta #136
Mass at launch	700 kg
End of life

Out of service	Oct 1984


 Meteosat 2

General

Designation	12544 / 81057A
Launch date	19 Jun 1981
Country of origin	Europe
Mission	Meteorology
Geostationary orbit
Launch vehicle	Ariane L03

Has provided 284000 images

End of life

Out of service	6 Dec 1991 to the junk orbit (36119/36334 km)


 Meteosat 3

General

Designation	19215 / 88051A
Launch date	15 Jun 1988
Country of origin	Europe
Mission	Meteorology
Geostationary orbit	see below
Launch vehicle	Ariane V23
Location

Begin	End	Position
L: 15 Jun 1988	Jun 1989	0°E
Jun 1989	Jan 1990	50°W
Jan 1990	Apr 1990	0°E
Apr 1990	?Nov 1990	5°W
Jul 1991		50°W
late 1992		75°W
Apr 1993		72.8°W
Feb 1995	Nov 1995	70°W, inclined

In May 1995 Eumetsat decided it didn't need the satellite back so it remained in reserve around 70°W before final burn.

End of life

Out of service	mid Nov 1995
Cause	pushed to the junk orbit
Technical data

Downlink frequency: 137.08 & 1691 MHz + in S-band


 Meteosat 4

Also called MOP 1

General

Designation	19876 / 89020B
Launch date	6 Mar 1989
Country of origin	Europe
Mission	Meteorology
Geostationary orbit	see below
Launch vehicle	Ariane V29

First operational satellite

Location

Begin	End	Position
L: 6 Mar 1989		0°E
Feb 1995	May 1995	7.7°W
Aug 1995	Oct 1995	10°E, inclined
End of life

Out of service	Early Nov 1995
Cause	pushed to the junk orbit
Technical data

Specifications

Payload

Downlink frequency: 137.08 MHz, 1691 & 1694.5 MHz + in S-band


 Meteosat 5

Also called MOP 2

General

Designation	21140 / 91015B
Launch date	2 Mar 1991
Country of origin	Europe
Mission	Meteorology
Geostationary orbit	see below
Launch vehicle	Ariane V42
Location

Begin	End	Position
L: 2 Mar 1991		0°E
May 1997	Feb 1998	9°W
Jun 1998		63.5°E

Moved to 65°E to take part in the INDOEX experiment (interaction between clouds and pollution)

Technical data

Specifications

Payload

Downlink frequency: 137.08 MHz, 1691 & 1694.5 MHz + in S-band


 Meteosat 6

Also called MOP 3

General

Designation	22912 / 93073B
Launch date	20 Nov 1993
Country of origin	Europe
Mission	Meteorology
Geostationary orbit	see below
Launch vehicle	Ariane V61

The radiometer didn't work in IR band thus temperature couldn't be measured. The problem could be solved in April 1995 after a software was developped to correct the data.

Cost: $67.5 million

Location

Begin	End	Position
L: 20 Nov 1993	Jan 1996	10°W
Feb 1996	Jun 1998	0°
Jul 1998		9°W
Technical data

Specifications

Payload

Downlink frequency: 137.08 MHz, 1691 & 1694.5 MHz

Equipped with 1 S-band transponder. Data rate: 2.6 Mbps


 Meteosat 7

Also called MTP 1

General

Designation	24932 / 97049B
Launch date	2 Sep 1997
Country of origin	Europe
Mission	Meteorology
Geostationary orbit	see below
Launch vehicle	Ariane V99

part of MTP (Meteosat Transitional Program)

satellite + launch: $150 million

Location

Begin	End	Position
L: 2 Sep 1997	May 1998	10°W
Jun 1998		0°
Technical data

Specifications

Prime contractor	Aerospatiale
Platform
Mass at launch	690 kg
Mass in orbit	320 kg
Dry mass	281 kg
Dimension	4.23 m height x 2.10 m diameter
Solar array
Stabilization	spin stabilized (90/100 rpm)
DC power	BOL: 240 W EOL: 225 W
Design lifetime	5 years

1 UHF- and 1 S-band transponder


Program: MSG
 Program: Meteosat Second Generation (MSG)

3 satellites are to be launched by Ariane in 2000, 2002 and 2006 by Ariane 5  Aerospatiale will build the 3 satellites.

12 channels, 15 min image repeat, lifetime: 14 years; resolution: 1.6 km²  Program worth $4.5 billion

With the SEVIRI (Spinning Enhanced Visible & Infrared Imager) built by Matra Marconi Space   The HRV channel (Haute Resolution Visible) has a 1 km resolution (others have a 3 km resolution)

Will carry the GERB (Geostationary Earth Radiation Budget) payload and a Sarsat beacon.

External resources

http://www.esrin.esa.it/msg/

http://www.esrin.esa.it/htdocs/esa/progs/MSG.html


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 Program: Metop

Also called Eumetsat Polar System (EPS)

Meteorology program financed by Eumetsat and ESA. 3 satellites planned. The system should be operational between 2003 and 2017.

The satellites should be built by MMS, 4700 kg, with 10 instruments on board.

It will be the first satellite to feature LRPT (Low Resolution Picture Transmission) which replaces APT. Spatial resolution is increased to 1 km. Will operate at 72 kbps


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 Microlab 1

Also called Orbview 1

General

Designation	23547 / 95017C
Launch date	3 Apr 1995 at 13:48 UT
Country of origin	United States
Operator	Orbital Science Corporation
Mission	Scientific
Perigee/Apogee	727/756 km
Inclination	70°
Period
Launch vehicle	Pegasus #8
Launch site	Cape Canaveral

It carries NASA-MSFC's Optical Transient Detector experiment to study the global distribution of lightning, and the University Corporation for Atmospheric Research's GPS-MET experiment which will study the occultation of GPS navigation satellite signals by the atmosphere to derive meteorological information.

Microlab is owned by OSC, with NASA and NSF renting the space for and operation of their experiments.

External resources

http://www.orbimage.com/satellite/orbview1/orbview1.html

Technical data

Specifications

Prime contractor	OSC
Platform	Microstar
Mass at launch	68 kg
Mass in orbit
Diameter	1 m
Height	0.3 m
Stabilization
DC power
Design lifetime	2 years


 Program: Midas

MIssile Defense Alarm System

American military satellites for missile launch warning. Equipped with IR detectors and TV cameras.

External resources

http://www.fas.org/spp/military/program/warning/midas.htm


Program: Midas

Midas 02

Midas 03

Midas 04

Midas 05

Midas 06

Midas 07

Midas 08

Midas 09

Midas 10


 Midas 02

Also called LASP (Low Altitude Surveillance Platform)

General

Designation	00043 / 60006A
Launch date	24 May 1960
Country of origin	United States
Mission	Military: early warning
Perigee/Apogee	473/494 km
Inclination	33°
Period	94.3 min
Launch vehicle	Atlas Agena A
Launch site	Cape Canaveral
End of life

Decay	7 Feb 1974


 Midas 03

General

Designation	00163 / 61018A
Launch date	12 Jul 1961
Country of origin	United States
Mission	Military: early warning
Perigee/Apogee	3342/3541 km
Inclination	91.2°
Period	161.4 min
Launch vehicle	Atlas Agena B
Launch site	Vandenberg


 Midas 04

General

Designation	00192 / 61028A
Launch date	21 Oct 1961
Country of origin	United States
Mission	Military: early warning
Perigee/Apogee	3482/3763 km
Inclination	95.9°
Period	165.9 min
Launch vehicle	Atlas Agena B
Launch site	Vandenberg


 Midas 05

Also called Strongback

General

Designation	00271 / 62010A
Launch date	9 Apr 1962
Country of origin	United States
Mission	Military: early warning
Perigee/Apogee	2784/3405 km
Inclination	86.7°
Period	152.9 min
Launch vehicle	Atlas Agena B
Launch site	Vandenberg


 Midas 06

Also called FTV 1169

General

Designation	00574 / 63014A
Launch date	9 May 1963
Country of origin	United States
Mission	Military: early warning
Perigee/Apogee	3607/3676 km
Inclination	87.3°
Period	166.4 min
Launch vehicle	Atlas Agena B
Launch site	Vandenberg


 Midas 07

Also called ERS 10 or FTV

General

Designation	00622 / 63030A
Launch date	18 Jul 1963
Country of origin	United States
Mission	Military: early warning
Perigee/Apogee	3672/3725 km
Inclination	88.4°
Period	167.8 min
Launch vehicle	Atlas Agena B
Launch site	Vandenberg


 Midas 08

Also called OPS 1960

General

Designation	02200 / 66051A
Launch date	9 Jun 1966
Country of origin	United States
Mission	Military: early warning
Perigee/Apogee	154/3678 km
Inclination	90°
Period	125.2 min
Launch vehicle	Atlas Agena D
Launch site	Vandenberg


 Midas 09

Also called OPS 0856

General

Designation	02403 / 66077A
Launch date	19 Aug 1966
Country of origin	United States
Mission	Military: early warning
Perigee/Apogee	3658/3708 km
Inclination	89.7°
Period	167.4 min
Launch vehicle	Atlas Agena D
Launch site	Vandenberg


 Midas 10

Also called OPS 1920

General

Designation	02481 / 66089A
Launch date	5 Oct 1966
Country of origin	United States
Mission	Military: early warning
Perigee/Apogee	3656/3721 km
Inclination	90°
Period	167.5 min
Launch vehicle	Atlas Agena D
Launch site	Vandenberg


 Mightysat

General

Designation	25551 / 98069C
Launch date	15 Dec 1998
Country of origin	United States
Mission	Technology
Perigee/Apogee	380/392 km
Inclination	51.6°
Period	92 min
Launch vehicle	STS 88
Technical data

Specifications

Prime contractor	USAF Phillips lab
Platform
Mass at launch	70 kg
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime

Carries 5 experiments:

Advanced Composite Structure: its the satellite's structure

Advanced Solar Cell Experiment: to test solar cells made of Gallium Indium Phosphide layers and Gallium Arsenide (GaAs) [triple junction]

Microsystem and Packaging for Low Power Electronics (MAPLE): will test advanced microelectronics and electronics packaging techniques

Shape-Memory Actuated Release Device (SMARD): a low-shock release device

Micro-Particle Impact Detector (MPID): debris survey


 Program: Millennium

Program operated by a wholly owned subsidiary of Motorola. GEO Ka-band telecommunication system. To support residential and business communications that include: telecommuting, education, medical information access, home shopping, information services, access to on-line services and the Internet.

Each satellite in the Millennium system will carry 57 transponders with 32 antenna beams, approximately 25 of which will be capable of using dual polarization.  Both right- and left-hand circular polarization will be used. The system should use inter satellite links

Based on ATM. Each satellite would have a maximum 7.5 Gbps throughput, each user could use 384 Kbps up to 51.84 Mbps. Near 60 GHz, 2000 MHz should be used for inter satellite links, 6 MHz are required in C-band for satellite control.

Slots: 91°W, 87°W, 77°W, and 75°W, 1 satellite per slot

Downlink: 19.7-20.2 GHz

Uplink: 28.35-28.6 and 29.5-30.0 GHz

Cost: $2.3 billion  Should be operational in 2002

Contact

Comm, Inc


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 Program: Milstar

US military communication system. To provide secure worldwide wartime telecommunications

The Milstar program estimated cost is $17.3 billion (1992-2011). Air Force officials said $8.8 billion of the unclassified $17.3 billion portion paid for the six satellites while another $8.5 billion will be spent on new radio gear needed by military units to use the satellites.

Lockheed Martin Missiles & Space, Sunnyvale, CA, is the prime contractor for Milstar. The Milstar team is led by the MILSATCOM Joint Program Office at the Air Force Space and Missile Systems Center in El Segundo, CA. TRW Space and Electronics Group provides the low data rate payload for the satellite. Hughes Aircraft Company is providing the medium data rate payload for Milstar Block 2. The major technologies aboard are on-board signal processing and routing and inter-satellite links.

The GAO reported the first 2 Milstar have serious problems which hinder there capability to carry out their missions. The report notes that there us a chance that the system (even with the second series of Milstar) could degrade below a minimally acceptable level in 2003.

Contact

50th Space Wing

300 O'Malley Ave, Suite 24, Falcon AFB, CO 80912-3024, USA

External resources

http://www.spacecom.af.mil/usspace/milstar1.htm

http://www.fas.org/spp/military/program/com/milstar1.htm

http://www.fas.org/spp/military/program/com/milstar2.htm

http://www.milsatcom.org/


Program: Milstar

Milstar 1-1

Milstar 1-2

Milstar 2-1

Milstar 2-2


Milstar 1 series

Specifications

Prime contractor	Lockheed Martin
Platform
Mass at launch	~4500 kg
Mass in orbit
Dimension
Solar array	8000 W
Stabilization
DC power
Design lifetime
Payload

Low Data Rate (LDR) payload (75 bps to 2400 bps):

EHF (44.5 GHz) uplink

SHF (20 GHz) downlink

+ 4 UHF AFSATCOM transponders

The satellites also have a 60 GHz crosslink to enable it to communicate with other Milstars


Milstar 2 series

Specifications

Prime contractor	Lockheed Martin
Platform
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime
Payload

LDR (see Milstar 1 series)

Medium Data Rate (MDR) payload (4.8 kbps to 1544 kbps)

+ 4 UHF AFSATCOM transponders

The satellites also have a 60 GHz crosslink to enable it to communicate with other Milstars


 Milstar 1-1

Also called USA 099

General

Designation	22988 / 94009A
Launch date	7 Feb 1994
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit	120°W guess (orbit classified)
Launch vehicle	Titan 4
Mass at launch	4670 kg
Technical data

Details


 Milstar 1-2

Also called USA 115

General

Designation	23712 / 95060A
Launch date	6 Nov 1995
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit	4°E guess (orbit classified)
Launch vehicle	Titan 4 #14

This satellite is estimated worth $1 billion

Technical data

Details


 Milstar 2-1

General

Designation	25724 / 99023A
Launch date	30 Apr 1999
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit	n/a
Launch vehicle	Titan 4 #27

loss worth $800 million

End of life

Out of service	30 Apr 1999
Cause	The top stage fired the intended 3 times but did so much too early. The satellite separated 4 hours early, and this caused the spacecraft to remain in LEO.

The spacecraft was raised to a slightly higher orbit, using its onboard thrusters. Satellite controllers then turned off all functions, deliberately exhausted the on-board liquid fuel supply and drained all remaining electrical power from the spacecraft. The decision to raise the satellite to a terminal orbit was made after controllers exhausted all possible options to salvage it or raise it to a geostationary orbit.

Technical data

Details


 Milstar 2-2

General

Designation
Launch date	late 1999
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit	n/a
Launch vehicle
Technical data

Details

The payload is the first to carry a consolidated agile beam antenna, which merges the functions of five previously separate agile beam antennas into a single, smaller, less costly unit.


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 Program: Minisat

Spanish microsatellite bus and program. Designed with low costs in mind, the bus is modular and aimed at the Pegasus launcher

3 different buses are available: Minisat 0 (for varius scientific payloads), Minisat 1 (for remote sensing applications) and Minisat 2 (for communication payloads)

External resources

http://www.laeff.esa.es/~trapero/EURD/minisat.html


Program: Minisat

Minisat 01


 Minisat 01

General

Designation	24779 / 97018A
Launch date	4 Apr 1997
Country of origin	Spain
Mission	Scientific: UV Astronomy
Perigee/Apogee	562 / 581 km
Inclination	151° (inclination record)
Period	96.1 min
Launch vehicle	Pegasus #17
Launch site	Canary Islands

3 experiments are onboard: EURD (a spectrograph that will study the background radiation in the extreme ultraviolet range), LEGRI (will study the low energy gamma radiation from astronomic sources) and CPLM (to study the behaviour of liquid bridges in microgravity conditions).

External resources

http://www.laeff.esa.es/~trapero/EURD/satellite.html

Technical data

Specifications

Prime contractor	CASA
Platform	Minisat 0
Mass at launch	195 kg
Mass in orbit
Dimension	2.487 x 2.554 x 1.170 m
Solar array	4 panels, 45 W per panel
Stabilization	1 axis
DC power
Design lifetime

Data can be stored onboard (32 Mb) and transmitted at 1 Mbps through a 5 W S-band link

Transmits on 2.223 GHz


 Miranda

Also called X4

General

Designation	07213 / 74013A
Launch date	9 Mar 1974
Country of origin	United Kingdom
Mission	Technology experimentation
Perigee/Apogee	677/865 km
Inclination	97.9°
Period	100.3 min
Launch vehicle	Scout #86
Mass at launch	93 kg

Built and operated by the RAE. Tested a stabilization system, solar panels and cells


 Mika

MIni KApsel

General

Designation	04345 / 70017B
Launch date	10 Mar 1970
Country of origin	France
Mission
Perigee/Apogee	302/1180 km
Inclination	5.4°
Period	99.6 min
Launch vehicle	Diamant #5

First launch from Kourou, was aimed at measuring the performance and Diamant B; it was attached to the final stage.

End of life

Out of service	10 Mar 1970
Cause	failed 17 seconds into launch, stopped transmitting
Decay	9 Sep 1974


 Program: Momo

Means "peach tree"

Also called MOS (Marine Observation Satellite)

Japanese remote sensing program. Mission: observethe oceans and marine/land phenomena, measure sea surface temperature and color, suspended sediment, stratospheric water vapor, ice and snow, vegetation characteristics and land use, geology, cartography, environmental monitoring, oceanography, etc.

Orbital cycle: 17 days (237 periods)


Program: Momo

Momo 1A

Momo 1B


Momo's specifications

Prime contractor	NEC
Mass at launch	740 kg
Dimension	1.26 x 1.48 x 2.4 m
Solar array	asymmetric, 2 x 5.3 m
Stabilization	3-axis
Design lifetime	2 years


Momo's payload

MESSR (Multispectral Electronic Self-Scanning Radiometer)

Wavebands	0.51-0.59 µm (visible): water body mapping 0.61-0.69 µm (visible): vegetation differentiation 0.72-0.80 µm (near IR): imaging through haze 0.80-1.10 µm (near IR): land/water separation
Resolution	50 m
Swath width	100 km
VTIR (Visible and Thermal IR Radiometer)

Wavebands	0.50-0.70 µm (visible): snow. ice and cloud 6-7 µm (water vapor band): upper atmosphere water vapor, cirrus 10.5-11.5 µm (thermal IR): ocean currents. sea surface temperature, snow 10.5-12.5 µm (thermal IR): ocean currents. sea surface temperature, snow
Resolution	visible: 0.9 km; others: 2.7 km
Swath width	1500 km
MSR (Microwave Scanning Radiometer)

Wavebands	23.8 +/- 0.2 GHz: water vapor, rain and snowfall 31.4 +/- 0.25 GHz: ice, cloud, snowfall
Resolution	32 km in 23 GHz and 23 in 31 GHz
Swath width	317 km


 Momo 1A

Also called MOS 1A

General

Designation	17527 / 87018A
Launch date	19 Feb 1987
Country of origin	Japan
Mission	Remote sensing
Perigee/Apogee	907/909 km
Inclination	99°
Period	103.2 min
Launch vehicle	N2
End of life

Out of service	yes
Technical data

Specifications

Payload

Downlink frequency: 136.12 MHz


 Momo 1B

Also called MOS 1B

General

Designation	20478 / 90013A
Launch date	7 Feb 1990
Country of origin	Japan
Mission	Remote sensing
Perigee/Apogee	907/909 km
Inclination	99°
Period	103.2 min
Launch vehicle	H1
End of life

Out of service	19 May 1996
Technical data

Specifications

Payload

Downlink frequency: 136.12 MHz


 Program: Morelos

Mexican telecommunication program operated by Satmex. The program has been replaced by Solidaridad.


Program: Morelos

Morelos 1

Morelos 2

Morelos 3


Morelos's specifications

Prime contractor	Hughes
Platform	HS-376
Mass at launch	1140 kg
Mass in orbit	666 kg
Diameter	2.16 m
Height	6.6 m deployed
Stabilization	Spin stabilized
DC power	BOL: 940 W
Design lifetime	10 years


Morelos's C-band

Main transponders	12+6
Backup transponders	4+2
Power	(6+2) transponders of 72 MHz: 10.5 W (TWTA) (12+4) transponders of 36 MHz: 7.5 W (TWTA)
Bandwidth	(6+2) transponders of 72 MHz (12+4) transponders of 36 MHz
Coverage	Mexico
EIRP max	39 dBW
G/T max	3.6 dB/K
Polarization	linear


Morelos's Ku-band

Main transponders	4
Backup transponders	2
Power	20 W (TWTA)
Bandwidth	108 MHz
Coverage	Mexico
EIRP max	40 dBW
G/T max	1.6 dB/K
Polarization	linear H


Morelos' C-band transponder frequency chart
 Morelos' C-band transponder frequency chart (GHz)

Horizontal Uplink	Horizontal Downlink	Transponder	Channel	Vertical Downlink	Vertical Uplink
	3.720	1W/L	1		5.945
5.965		1N	2	3.740
	3.760	1W/U	3		5.985
6.005		2N	4	3.780
	3.800	3W/L	5		6.025
6.045		3N	6	3.820
	3.840	2W/U	7		6.065
6.085		4N	8	3.860
	3.880	3W/L	9		6.105
6.125		5N	10	3.900
	3.920	3W/U	11		6.145
6.125		6N	12	3.940
	3.960	4W/L	13		6.185
6.205		7N	14	3.980
	4.000	4W/U	15		6.225
6.245		8N	16	4.020
	4.040	5W/L	17		6.265
6.285		9N	18	4.060
	4.080	5W/U	19		6.305
6.325		10N	20	4.100
	4.120	6W/L	21		6.345
6.365		11N	22	4.140
	4.160	6W/U	23		6.385
6.405		12N	24	4.180


Morelos' Ku-band transponder frequency chart (GHz)

Horizontal Uplink	Horizontal Downlink	Transponder	Vertical Downlink	Vertical Uplink
	11.764	1K		14.064
	11.888	2K		14.188
	12.012	3K		14.312
	12.136	4K		14.436


 Morelos 1

General

Designation	15824 / 85048B
Launch date	17 Jun 1985
Country of origin	Mexico
Mission	Telecommunications
Geostationary orbit	113.5°W
Launch vehicle	STS 25
End of life

Out of service	March 1994
Technical data

Specifications

C-band

Ku-band

C-band transponder frequency chart

Ku-band transponder frequency chart


 Morelos 2

General

Designation	16274 / 85109B
Launch date	27 Nov 1985
Country of origin	Mexico
Mission	Telecommunications
Geostationary orbit	116.8°W
Launch vehicle	STS 31

Is said to be moved and sold to Nahuelsat for provision of the Argentinian market.

Location

Begin	End	Position
L: 27 Nov 1985	Dec 1998	116.8°W
Jan 1999		120.3°W
Technical data

Specifications

C-band

Ku-band

C-band transponder frequency chart

Ku-band transponder frequency chart

EIRP coverage (dBW)

C-band

Ku-band


Morelos 2's C-band EIRP coverage


Morelos 2's Ku-band EIRP coverage


 Morelos 3

Also called SatMex 5

General

Designation	25558 / 98070A
Launch date	6 Dec 1998
Country of origin	Mexico
Mission	Telecommunications
Geostationary orbit	116.8°W
Launch vehicle	Ariane V114

Total cost: $230 million

Became operational on 1st Feb 1999

Technical data

EIRP coverage (dBW)

C-band

Ku-band, beam 1

Ku-band, beam 2

Specifications

Prime contractor	Hughes
Platform	HS-601HP
Mass at launch	3550 kg
Mass in orbit	BOL: 1950 kg
Dimension	6 x 2.8 x 3.4 m at launch
Solar array	26.3 m deployed
Stabilization	3-axis
DC power	BOL: 8400 W 7615 W
Design lifetime	15 years

Xenon ion propulsion device (XIPS)

C-band

Main transponders	24
Backup transponders	6
Power	36 W (TWTA)
Bandwidth	36 MHz
Coverage	fully covers the United States, southern Canada and virtually all of Latin America. Its only shortcoming is Brazil, where it covers about one-half of the country.
G/T max	-3.0 dB/K
EIRP max	38 dBW
Polarization	linear H/V

C-band transponder frequency chart

Ku-band

Main transponders	24
Backup transponders	8
Power	12 transponders: 110 W (TWTA) 12 transponders: 132 W (TWTA)
Bandwidth	36 MHz
Coverage	beam 1: Mexico and CONUS beam 2: Canada to Argentina
EIRP max	ku1: 49 dBW ku2: 46 dBW
G/T max	ku1: 1.5 dB/K ku2: -1.5 dB/K
Polarization	linear H/V


Morelos 3's C-band EIRP coverage


Morelos 3's Ku-band beam 1 EIRP coverage


Morelos 3's Ku-band beam 2 EIRP coverage


 MSAT 1

General

Designation	23846 / 96022A
Launch date	20 Apr 1996
Country of origin	Canada
Operator	TMI Communications
Mission	Telecommunications
Geostationary orbit	106.5°W
Launch vehicle	Ariane V85

This satellite is a twin of AMSC 1. Both satellites were ordered at the same time (with separate contracts). Both operators will provide complementary mobile telephone, radio, data, and positioning service to land, aviation, and maritime users. Each operator also will provide the other with backup and restoration capacity.

Should move to 101°W and be jointly operated by AMSC and TMI in mid-1998

External resources

http://www.msat.tmi.ca/

Technical data

Specifications

Prime contractor	SPAR Hughes (bus) and SPAR Aerospace (payload)
Platform	HS-601
Mass at launch	2830 kg
Mass in orbit	1600 kg
Dimension	2.5 m x 3.5 m x 7.9 m
Solar array	20.96 m span
Stabilization	3-axis
DC power	BOL: 4000 W
Design lifetime	12 years

Springback antennas: 6.7 x 4.9 m x 20 kg (for launch the 2 antennas as rolled together into a 4.9 m high cone shape atop the satellite)

L-band (1545-1559/1646.5-1660.5 MHz)

Main transponders	16
Backup transponders	4
Power	38 W (SSPA)
Bandwidth
Coverage	North America (4 spot beams) Alaska and Hawaii (1 beam) Carribean (1 beam)
EIRP max	57 dBW

Total bandwith: 3200 x 5 KHz

Each beam transponder is equipped with eight surface acoustic wave filters covering the 29 MHz L-band allocation, allowing selection of filters to math traffic needs and to coordinate with other international users. Frequency reuse is incorporated between the North American east and west beams. The beams are combined into two L-band power pools, one covering the east and central beams, and the other covering the remaining service areas. Each power pool is generated by a hybrid matrix amplifier assembly.

Ku-band

Main transponders	1
Backup transponders	2
Power	100 W (TWTA)
Bandwidth
Coverage	CONUS, Carribean, Canada, Alaska and Hawaii
EIRP max	37 dBW
Polarization

Beacon: 11.70275 MHz


 Program: Morning Star

Morning Star is Delaware-based LLC company. It plans to launch 4 satellites to offer services such as high speed data, voice, and interactive video communications. The systems uses Ku-band as forward path and Ka-band as return path. The system should be operational in May 2002.

Although FCC has granted authorization for Ka-band operations in May 1997, Ku-band operations in delayed. Cost: $847 million

GEO slots: 147°W, 107.5°W, 62°W, 30°E

Technical data

Ku-band (forward path)

Main transponders	16
Backup transponders
Power
Bandwidth	24 MHz
Coverage
EIRP
Polarization
Ka-band (return path, up to 64 kbps channels)

Main transponders
Backup transponders
Power
Bandwidth
Coverage
EIRP max
Polarization
Frequencies	Uplink: Downlink:

a single steerable spot will be used for Ku-band uplink and Ka-band downlink to the control center.


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 Program: MSTI

Miniature Seeker Technology Integration

US technological program lead by the Air Force Phillips labs. Previously funded by the Ballistic Missile Defense Organization (BMDO), the MSTI program is now under the direction of USAF. It is probably mostly of military interest

External resources

http://www.actgate.com/msti3/default.html


Program: MSTI

MSTI 1

MSTI 2

MSTI 3


 MSTI 1

General

Designation	22229 / 92078A
Launch date	21 Nov 1992 at 13:45 UT
Country of origin	United States
Mission	Technology experimentation
Perigee/Apogee	289/366 km
Inclination	96.7°
Period	91.1 min
Launch vehicle	Scout #116
Mass at launch	135 kg

Designed to test instruments for star war. Two other satellites should be launched.

Cost of the 3 satellites: $19 million

External resources

http://www.actgate.com/msti3/msti1.html

http://www.spectrumastro.com/Programs/Msti/MSTI1.asp

Technical data

Specifications

Prime contractor	Spectrum Astro
Platform	ARPA ASSTD
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime


 MSTI 2

General

Designation	23101 / 94028A
Launch date	9 May 1994 at 02:47 UT
Country of origin	United States
Mission	Technology
Perigee/Apogee	411/427 km
Inclination	97.1°
Period	92.9 min
Launch vehicle	Scout #118
Mass at launch	135 kg

It was the last of the now discontinued Scout series. The satellite successfully tracked a Minuteman III ICBM on June 8, 1994, and collected over 3 million images for analysis during its mission.

On 15 Sep 1997 this spacecraft passed by Mir, only at 470 m distance!

End of life

Out of service	Sep 1994
External resources

http://www.actgate.com/msti3/msti2.html

http://www.spectrumastro.com/Programs/Msti/MSTI2.asp


 MSTI 3

General

Designation	23868 / 96031A
Launch date	17 May 1996
Country of origin	United States
Mission	Technology
Perigee/Apogee	425 km (sunsynchronous)
Inclination	97°
Period
Launch vehicle	Pegasus #11
Mass at launch	211 kg

Experimental satellite to collect data on short- and medium-wave infrared band, radiating from ground features, bodies of water and atmospheric bodies, such as clouds. Will demonstrate more sophisticated sensors and data gathering capabilities.

On 19 Oct 1997 the Army's Miracl laser was tested against it. Two beams were fired, the first of less than one second duration (in order to lock on to the satellite) and the second of about 10 seconds (in order to kill it).  It is believed the experiment failed, the satellite was not destroyed.

External resources

http://www.actgate.com/msti3/msti3.html

http://www.spectrumastro.com/Programs/Msti/MSTI3.asp

http://www.fas.org/spp/military/program/asat/miracl.htm

Technical data

Built by Spectrum Astro Inc

MTSI 3 is about 3 m long and 1 m in diameter

Payload: MWIR camera, SWIR camera, and a visible imaging spectrometer (provided by Science Applications International Corporation (San Diego, CA))  The vehicle also has a 12 channel onboard GPS receiver for real time orbit determination.


 MSX

Middlecourse Space Experiment

General

Designation	23851 / 96024A
Launch date	24 Apr 1996
Country of origin	United States
Operator	Ballistic Missile Defense Organization (BMDO)
Mission
Perigee/Apogee	896/906 km
Inclination	99°
Period
Launch vehicle	Delta 2 #235
Mass at launch	2600 kg

Will study the infrared, visible and ultraviolet signatures of ballistic missiles in their midcourse phase (after the launch vehicle rocket plume has shut down). MSX will also perform civilian scientific research, with atmospheric observations and astronomical studies. It will provide data on small debris in space.

Johns Hopkins University's Applied Physics Laboratory built the MSX spacecraft for the BMDO. The Spirit III cryogenic-cooled infrared sensor system was supplied to BMDO by Utah State University/Space Dynamics Laboratory.

Released a few tiny sub-satellites

External resources

http://www.mrcnh.com/msx/index.htm

Technical data

Telemetry: 2282.5 MHz

Data: 8475.0 MHz

Payload

SPIRIT III: 0.34m Spatial IR Imaging Telescope, 2.5 -28 microns

UVISI: UV and Visible Imagers and Spectrographic Imagers

CIC: Contamination Instrumentation Complement (to study outgassing and contamination of optical surfaces)

SBV: Space Based Visible camera, 0.15m telescope/CCD

Spirit III is the first cryogenic infrared telescope to use solid hydrogen instead of the liquid helium that has been used by infrared astronomy satellites in the past. The hydrogen will maintain the dewar at 8.5K.


 MTSat

Multi-functional Transport Satellite

General

Designation
Launch date	mid 1999
Country of origin	Japan
Mission	Telecommunications and meteorology
Geostationary orbit	140°E
Launch vehicle	H2
Launch site

Japanese system for air traffic control and weather observation. Ordered by the Japanese Ministry for Transport & Meteorological agency to Space Systems/Loral ($102 million). Is the successor of the GMS program

In Jun 1999 the satellite had to be shipped back to SS/L after a part for the power supply in a similar product was found defective.

Possible option for a second satellite in 2004

External resources

http://www.mpt.go.jp/index-e.html

Technical data

Specifications

Prime contractor	SS/L
Platform	FS-1300
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime

Would operate in UHF-, L-, S-, Ku- and Ka-band

Weather sensor built by ITT Aerospace/Commnucations division


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 Mublcom

Multiple beam Beyond Line-of-sight Communications

General

Designation	25736 / 99026B
Launch date	18 May 1999
Country of origin	United States
Mission	Technology
Perigee/Apogee	770 km
Inclination	97.7°
Period
Launch vehicle	Pegasus #27

Funded by Defense Advanced Research Projects Agency (DARPA) and managed by the US Army's Communications-Electronics Command (CECOM) at Ft Monmouth, New Jersey. Estimed project cost: $15 million

The MUBLCOM system will address the military's need for secure, mobile, terrain-independent, all-weather communications. It will support combat network radios, as well as special missions such as long-range surveillance and fire support.

Technical data

Specifications

Prime contractor	Orbital
Platform	Microstar
Mass at launch	48 kg
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime	2 years

Payload and hand-held terminals provided by Torrey Science Corporation

Telemetry: 370-390 MHz range (40 W) + 401.5 MHz


 Musat

Also called Microsatelite

General

Designation	24291 / 96050A
Launch date	29 Aug 1996 at 05:22 UT
Country of origin	Argentina
Mission	Scientific
Perigee/Apogee	244/1192 km
Inclination	62.8°
Period
Launch vehicle	Molniya M
Launch site	Plesetsk LC43

Small experimental payload from the Instituto Universitario Aeronautico de Cordoba, Argentina

The launch costed $200,000

The satellite carries 2 CCD cameras (70 m and 2 km resolution)

Technical data

Specifications

Prime contractor
Platform
Mass at launch	34.5 kg
Mass in orbit	32 kg
Dimension	33 x 43 x 50 cm
Solar array
Stabilization
DC power
Design lifetime

Beacon: 137.95 MHz

Data & telemetry: 400.95 MHz & 2260.5 MHz


 Myojo

Also called VEP (Vehicle Evaluation Payload)

General

Designation	22979 / 94007B
Launch date	3 Feb 1994
Country of origin	Japan
Operator	NASDA
Mission	Technology
Perigee/Apogee	430/36114 km
Inclination	29.12°
Period	641.95 min
Launch vehicle	H2


 Mysat 1

Also called Tiungsat 1

General

Designation
Launch date	initially planned in Mar 1998
Country of origin	Malaysia
Mission	Scientific: remote sensing & telecomunications
Perigee/Apogee
Inclination
Period
Launch vehicle	Zenit
Launch site

Payload includes a 1 km resolution camera for meteorology (storm alert), a 80 m multispectral camera and a telecommunication transponder (HAM)

Satellite cost: $7.4 million  Owned by Astronautic Technology Sdn Bhd (ATSB)

Technical data

Specifications

Prime contractor	SSTL
Platform
Mass at launch	50 kg
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime

Built by SSTL with engineers from ATSB. The main ground station will be in Kuala Lumpur.

Will have communication capabilities (email?)


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 NSat 110

General

Designation
Launch date	late 2000
Country of origin	Japan
Mission	Telecommunications
Geostationary orbit	110°E ?
Launch vehicle	Ariane

Space Communication Corp. (SCC) and Japan Satellite Systems Inc. (JSAT) will equally finance and operate the satellite.

Technical data

Specifications

Prime contractor	Lockheed Martin
Platform	A2100
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime
Ku-band

Main transponders	12
Backup transponders
Power
Bandwidth	36 MHz
Coverage	Japan
EIRP max
G/T max
Polarization

Some of the payload will be provided by Melco


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 Program: N Star

Japanese telecommunication operated by NTT program that follows the Sakura series.

The satellites will provide inter-orbit links, high quality DBS TV and mobile links. They will enable the use of cellular phones anywhere in Japan (in 1995 the existing cellular phone system covers 95% of Japan's populated areas but does not cover mountainous areas). This service will be provided by NTT's mobile phone unit, NTT Mobile Communications Network Inc.

Designed to replace the Sakura 3A & 3B satellites


Program: N Star

N Star a

N Star b


N Star's specifications

Prime contractor	Space Systems/Loral
Platform	FS-1300
Mass at launch	3400 kg
Mass in orbit	2050 kg
Dry mass	1617 kg
Dimension	3.1 x 2.4 x 2.2 m
Solar array	27.3 m
Stabilization	3-axis
DC power	5200 W, nickel-hydrogen batteries
Design lifetime	10 to 12 years


N Star's S-band

Main transponders	4
Backup transponders
Power
Bandwidth
Coverage	Japan, 4 beams
EIRP max
Polarization


N Star's C-band

Main transponders	6
Backup transponders
Power	20 W (TWTA)
Bandwidth
Coverage	Japan
EIRP max
Polarization


N Star's Ku-band

Main transponders	8
Backup transponders
Power	40 W (TWTA)
Bandwidth
Coverage	Japan
EIRP max
Polarization
Frequencies	Downlink: 12.19-12.91 GHz


N Star's Ka-band

Main transponders	11
Backup transponders
Power	20 W (TWTA)
Bandwidth
Coverage	Japan
EIRP max
Polarization
Frequencies	Downlink: 17.75-19.45 GHz

For military purposes & switched TDMA service on Ka-band multi-beam


 N Star a

General

Designation	23651 / 95044A
Launch date	29 Aug 1995
Country of origin	Japan
Mission	Telecommunications
Geostationary orbit	132°E
Launch vehicle	Ariane V77

An accident during transportation to the launch site damaged the spacecraft which delayed it. Was delivered in orbit in late October 1995

Technical data

Specifications

S-band

C-band

Ku-band

Ka-band


 N Star b

General

Designation	23781 / 96007A
Launch date	5 Feb 1996
Country of origin	Japan
Mission	Telecommunications
Geostationary orbit	136°E
Launch vehicle	Ariane V83
Technical data

Specifications

S-band

C-band

Ku-band

Ka-band


 Program: Nahuel

Argentine first telecommunication program operated by Nahuelsat. The broadcasting license will be for 24 years, with an extension option for an additional 6 years.

The Nahuelsat control center will be collocated with the Ground Station in the Buenos Aires area.  After an agreement with Embratel (the operator of Brasilsat) the system will be operated by the Brazilian company.


Program: Nahuel

Nahuel 1A

Nahuel 2


 Nahuel 1A

General

Designation	24714 / 97002B
Launch date	30 Jan 1997
Country of origin	Argentina
Mission	Telecommunications
Geostationary orbit	71.8°W
Launch vehicle	Ariane V93

The launch was also contracted with Long March.

The satellite was reported to experience a 15-hour outage in May 1999.

Technical data

EIRP coverage (dBW)

Argentina beam

Brazil beam

Large beam

Specifications

Prime contractor	DASA
Platform	Spacebus-2000
Mass at launch	1780 kg
Dry mass	828 kg
Dimensions	1.64 x 1.46 x 2.2 m (22.3 deployed)
Stabilization	3-axis
DC power	BOL: 3200 W
Design lifetime	12 years

control station at Benevidez, Buenos Aires province

Ku-band

Main transponders	18
Backup transponders	6
Power	55 W (TWTA)
Bandwidth	54 MHz
Coverage & EIRP max	Argentina: 50 dBW Brazil: 51 dBW Large: 41 dBW
Polarization	linear H/V
Transponder frequency chart (GHz)

Horizontal Uplink	Horizontal Downlink	Transponder	Vertical Downlink	Vertical Uplink	Beam
		1	11.730	14.030	A
14.043	11.743	2			B / A
		3	11.791	14.091	A
14.104	11.804	4			B / A
		5	11.852	14.152	A
14.165	11.865	6			B / A
		7	11.913	14.213	A
14.226	11.926	8			B / A
		9	11.974	14.274	A
14.287	11.987	10			B
		11	12.035	14.335	A
14.348	12.048	12			B
		13	12.096	14.396	A
14.409	12.109	14			B
		15	12.157	14.457	A
14.470	12.170	16			B
		17	11.48867	13.77700	L
		19	11.54967	13.83800	L
		21	11.61067	13.89900	L
		23	11.67034	13.95867	L

Transponder 23 only has 51.3 MHz bandwidth


Nahuel 1A's Argentina beam


Nahuel 1A's Brazil beam


Nahuel 1A's Large beam


 Nahuel 2

General

Designation
Launch date	planned in 2002
Country of origin	Argentina
Mission	Telecommunications
Geostationary orbit	81°W
Launch vehicle

Will have both C- and Ku-band transponders.


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 Program: Nato

North Atlantic Treaty Organization

Military communications satellites for the NATO

External resources

http://www.fas.org/spp/military/program/com/nato_3.htm


Program: Nato

Nato 1

Nato 2

Nato 3A

Nato 3B

Nato 3C

Nato 3D

Nato 4A

Nato 4B


Nato 3's specifications

Downlink frequecies	7.2 to 7.5 GHz
Design lifetime	7 years


Nato 4's specifications

Prime contractor	Britsh Aerospace (now MMS)
Platform	ECS
Mass at launch	1430 kg
Mass in orbit	770 kg
Payload mass	215 kg
Length	2.2 m
Height	2.3 m
Solar array	16 m span
Stabilization	3-axis
DC power	EOL: 1200 W
Design lifetime	7 years

Based on the design of the Skynet 4 satellites


Nato 4's UHF-band (250-315 MHz)

Main transponders	2
Backup transponders
Power	25 W (TWTA)
Bandwidth	25 KHz
Coverage	Europe
EIRP max


Nato 4's X-band

Main transponders	3
Backup transponders
Power	40 W (TWTA)
Bandwidth	60 and 135 MHz
Coverage	global
EIRP max
Frequency	Downlink: 7.250-7.750 GHz


 Nato 1

General

Designation	04353 / 70021A
Launch date	20 Mar 1970
Country of origin	NATO
Mission	Military: telecommunications
Geostationary orbit
Launch vehicle	Thor Delta #77
End of life

Out of service	yes


 Nato 2

General

Designation	04902 / 71009A
Launch date	3 Feb 1971
Country of origin	NATO
Mission	Military: telecommunications
Geostationary orbit	see below
Launch vehicle	Thor Delta #82
End of life

Out of service	yes


 Nato 3A

General

Designation	08808 / 76035A
Launch date	22 Apr 1976
Country of origin	NATO
Mission	Military: telecommunications
Geostationary orbit	18°W
Launch vehicle	Thor Delta #122
Mass at launch	376 kg
End of life

Out of service	yes
Technical data

Specifications


 Nato 3B

General

Designation	09785 / 77005A
Launch date	28 Jan 1977
Country of origin	NATO
Mission	Military: telecommunications
Geostationary orbit
Launch vehicle	Thor Delta #128
Mass at launch	680 kg
End of life

Out of service	yes
Technical data

Specifications


 Nato 3C

General

Designation	11115 / 78106A
Launch date	19 Nov 1978
Country of origin	NATO
Mission	Military: telecommunications
Geostationary orbit
Launch vehicle	Thor Delta #146
End of life

Out of service	yes
Technical data

Specifications


 Nato 3D

General

Designation	15391 / 84115A
Launch date	14 Nov 1984
Country of origin	NATO
Mission	Military: telecommunications
Geostationary orbit	see below
Launch vehicle	Thor Delta #177
Location

Begin	End	Position
L: 14 Nov 1984
Feb 1995	Mar 1997	21°W, inclined
Apr 1997		18.5°W, inclined
Technical data

Specifications

Prime contractor	Ford Aerospace
Platform
Mass at launch
Mass in orbit	385 kg ?
Dimension	2.13 m (diameter) x 2.74 m (high)
Solar array
Stabilization
DC power	500 W
Design lifetime

Downlinks in UHF- (250-315 MHz), C- and X-band


 Nato 4A

General

Designation	21047 / 91001A
Launch date	8 Jan 1991
Country of origin	NATO
Mission	Military: telecommunications
Geostationary orbit	18°W, inclined
Launch vehicle	Delta 2 #202
Technical data

Specifications

UHF-band

X-band

Also downlinks in C-band


 Nato 4B

Also called USA 098

General

Designation	22921 / 93076A
Launch date	8 Dec 1993
Country of origin	NATO
Mission	Military: telecommunications
Geostationary orbit	see below
Launch vehicle	Delta 2 #224
Location

Begin	End	Position
L: 8 Dec 1993	Jan 1998	5°E
Mar 1998		20°W
Technical data

Specifications

UHF-band

X-band

Also downlinks in C-band


 NEMO

Navy Earth Map Observer

General

Designation
Launch date	mid-2000
Country of origin	United States
Mission	Remote Sensing
Perigee/Apogee	605 km sunsynchronous (10:30 nodal crossing)
Inclination	97.81°
Period	(7 days revisit)
Launch vehicle	Rokot
Launch site

Will provide dual-use, space based system for collecting broad-area Hyperspectral Imagery to characterize land and sea environments for the Naval forces and commercial users.

Military use: use of hyperspectral imagery for characterization of littoral battlespace environment and littoral model development (e.g. detailed bathymetry, water clarity and trafficability). support to u.s. forces with realtime on-board processing and tactical downlink of hyperspectral data directly from spacecraft to the field.

Commercial application: provides hyperspectral and panchromatic imaging data to support land use management, agriculture, forestry, environmental monitoring, geology, mineral exploration and hydrology.

Cost: $140 million

External resources

http://nemo.nrl.navy.mil/

Technical data

Specifications

Prime contractor
Platform	LS-400 (globalstar)
Mass at launch	295 kg
Payload mass	141 kg
Dimension
Solar array
Stabilization
DC power
Design lifetime	3 to 5 years
Instruments:

COIS (Coastal Ocean Imaging Spectrometer): 210 hyperspectral channels between 0.4 and 2.5 µm (swath width 30 km, 30 m resolution). Will also have 2 spectrometers (visible & near-IR)

PIC (Panchromatic Imager): black & white camera with 5 m resolution


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 Netsat 28

Netsat 28 is a Delaware LLC which plans to launch this Ka-band satellite for data communications (on-demand rates from 64 kbps to 1.544 Mbps)

General

Designation
Launch date	before May 2002
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	95°W
Launch vehicle
Launch site

Will provide onboard switching

Technical data

Ka-band

Main transponders	48
Backup transponders
Power
Bandwidth	40 MHz
Coverage
EIRP max
Polarization
Frequencies	Uplink: 28.35-28.6 and 29.25-30.0 GHz Downlink: 19.7-20.2 GHz


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 Nilesat 101

Also called Nilesat 1

General

Designation	25311 / 98024A
Launch date	28 Apr 1998
Country of origin	Egypt
Operator	Nilesat
Mission	Telecommunications
Geostationary orbit	7°W
Launch vehicle	Ariane V108

On the contract: 2 satellites (1 = ground spare) + 2 earth stations on the contract: total amount: $158 million for Matra Marconi Space.  The second satellite could be modified and launched to cover more of the African continent

Telesat Canada provided the consultancy to setup the whole system.

Technical data

EIRP coverage (dBW)

Specifications

Prime contractor	Matra Marconi Space
Platform	Eurostar 2000
Mass at launch	1840 kg
Mass in orbit	1100 kg
Dry mass	795 kg
Dimension	2.3 x 2.4 x 1.7 m
Solar array	21.5 m span
Stabilization	3-axis
DC power	3750 W
Design lifetime	16 years

Equipped with Fokker-made solar arrays which might have a defect.

Ku-band

Main transponders	12
Backup transponders	6
Power	105 W
Bandwidth	33 MHz
Coverage	Middle East & North Africa
EIRP max	50.3 dBW
Polarization
Frequencies	downlink: 11.7 - 12.5 GHz

2.3 m diameter onboard antenna

Payload provided by Alcatel Espace

NileSat 101 reception is far better than predicted: reception in London was predicted with 4.5 m dish but only 1.2 m ones are required. As far as the Arabian Gulf is concerned, viewers in Oman can receive signals on 90cm dishes.

Transponder frequency chart (GHz)

Transponder	Polarization	Frequency
2	H	11.765
3	V	11.785
4	H	11.804
5	V	11.823
6	H	11.842
7	V	11.861
8	H	11.881
9	V	11.900
10	H	11.919
11	V	11.938
12	H	11.957
13	V	11.956
14	H	11.996
15	V	12.015
16	H	12.034
17	V	12.053
18	H	12.072


Nilesat EIRP map


 Nilesat 102

Also called Nilesat 2

General

Designation
Launch date	planned mid 2000 (was: late 1999)
Country of origin	Egypt
Operator	Nilesat
Mission	Telecommunications
Geostationary orbit	7°W
Launch vehicle	Ariane

Contract including the satellite, the launch, insurance and in-orbit delivery

Technical data

Specifications

Prime contractor	Matra Marconi Space
Platform	Eurostar 2000
Mass at launch	1800 kg
Mass in orbit
Dry mass
Dimension	2.3 x 2.4 x 1.7 m
Solar array	21.5 m span
Stabilization	3-axis
DC power
Design lifetime	16 years

2.3 m diameter antenna

Ku-band

Main transponders	12
Backup transponders	6
Power	100 W
Bandwidth	33 MHz
Coverage	Middle East & North Africa
EIRP max	50.3 dBW
Polarization
Frequencies

Will carry 2 active and 1 backup Skyplex unit (see hotbird 5 for details)


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 Program: Nimbus

American experimental meteorology program operated by the NOAA

Those satellites have given atmosphere temperature at different altitudes

External resources

http://www.met.fsu.edu/explores/Guide/nimbusindex.html


Program: Nimbus

Nimbus 1

Nimbus 2

Nimbus 3A

Nimbus 3

Nimbus 4

Nimbus 5

Nimbus 6

Nimbus 7


 Nimbus 1

General

Designation	00872 / 64052A
Launch date	28 Aug 1964
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	429/937 km
Inclination	98.7°
Period	98.4 min
Launch vehicle	Thor Agena B
Launch site	Vandenberg
Mass at launch	376 kg

A circular orbit was intended but a partial failure of Agena (early shutdown) caused an elliptical orbit instead.

The project objectives were to provide improved photographs of local cloud conditions by an automatic picture transmission (APT) system, and to evaluate an advanced vidicon camera system for daylight coverage and a high-resolution infrared radiometer system for night-time cloud cover observation.

First high resolution photos (27000 photos taken) Five hurricanes and two typhoons were spotted in photographing 70 percent of the world each day. The APT system supplied daytime photos to more than 60 low-cost ground stations. Radiometer photos were remarkably clear and covered a 12,500 square mile area.

End of life

Out of service	23 Sep 1964
Cause	solar panel drive failed
Decay	16 May 1974


 Nimbus 2

General

Designation	02173 / 66040A
Launch date	15 May 1966
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	1090/1174 km
Inclination	100.6°
Period	108 min
Launch vehicle	Thor Agena B
Launch site	Vandenberg

The project objectives were to provide global weather photography on a 24-hour basis for meteorological research and operational use, and provide infrared data for study of earth's heat balance.

Four sensor systems weighing a total of 142 pounds were carried. The advanced vidicon camera system (AVCS) included three 1-inch cameras with 800-line resolution designed to photograph a 800,000 square mile area. A high resolution infrared radiometer provided time and was expected to yield a variety of geophysical and atmospheric data including cloud height information.


 Nimbus 3A

Also called Nimbus B

General

Designation	n/a
Launch date	18 May 1968
Country of origin	United States
Mission	Meteorology
Launch vehicle	Thor Agena D
Launch site	Vandenberg

Two minutes after launch, a booster malfunction forced a command destruct. The booster and spacecraft fell into the Pacific Ocean between Vandenberg Air Force Base and San Miguel Island off the coast of California.

The radioactive fuel for the two generators (plutonium 238) was contained in two high-strength alloy and graphite capsules, which had been designed and tested to withstand ocean impact and seawater corrosion in case of such an abort.

End of life

Out of service	18 May 1968
Cause	Launcher failure


 Nimbus 3

General

Designation	03890 / 69037A
Launch date	14 Apr 1969
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	1069/1128 km
Inclination	100°
Period	107.2 min
Launch vehicle	Thor Agena D
Launch site	Vandenberg

Nimbus 3 was a replacement for Nimbus 3A. Nimbus 3 was the first United States satellite to make night and day global measurements from space of temperatures of the atmosphere, both over extended periods and, for the first time, at varying levels vertically. While meteorological objectives were primary, this mission also gathered vital oceanographic data for scientific purposes other than solely for weather forecasting. Another mission objective was to provide data for the first experiment of the U.S.A. portion of the Global Atmospheric Research Program (GARP), which was an international program of formulating and coordinating research for achieving long-range global weather forecasting.

Technical data

Specifications

Prime contractor
Platform
Mass at launch
Mass in orbit	635 kg
Dimension	3 x 3.35 m
Solar array
Stabilization	3-axis
DC power
Design lifetime

Has a SNAP engine


 Nimbus 4

General

Designation	04362 / 70025A
Launch date	8 Apr 1970
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	1085/1097 km
Inclination	99.9°
Period	107.1 min
Launch vehicle	Thor Agena D
Launch site	Vandenberg

It made world-wide weather observations twice a day - once in daylight and once in darkness.

Technical data

Specifications

Prime contractor
Platform
Mass at launch
Mass in orbit	683 kg
Dimension	3 x 3.35 m
Solar array	two panels: 0.91 x 2.44m
Stabilization
DC power	200 W
Design lifetime

Transmits on 136.500 MHz


 Nimbus 5

Also called Nimbus E

General

Designation	06305 / 72097A
Launch date	11 Dec 1972
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	1086/1098 km
Inclination	99.8°
Period	107.1 min
Launch vehicle	Thor Delta #93

It was also used for testing advanced systems collecting meteorological and geological data.

Technical data

Specifications

Prime contractor
Platform
Mass at launch
Mass in orbit	790 kg
Dimension	3 x 3.35 m
Solar array	two panels: 0.91 x 2.44m
Stabilization
DC power	200 W
Design lifetime


 Nimbus 6

Also called Nimbus F

General

Designation	07924 / 75052A
Launch date	12 Jun 1975
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	1098/1111 km
Inclination	99.8°
Period	107.4 min
Launch vehicle	Thor Delta #111
Mass at launch	829 kg or 911 kg?

Measures sea color


 Nimbus 7

Also called Nimbus G

General

Designation	11080 / 78098A
Launch date	24 Oct 1978
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	944/956 km
Inclination	99°
Period	104 min
Orbital cycle	6 days
Launch vehicle	Thor Delta #145
Mass at launch	827 kg

Nimbus 7 was notable for providing the first daily mapping ozone concentration and the first global ocean color measurements. Data was for the first time used by ESA

Spacecraft and experiment data were transmitted to Earth stations immediately, or stored in an on-board high-speed tape recorder for subsequent playback when the satellite was in view of a ground acquisition station.

Technical data

Specifications

Prime contractor	GE Astro
Stabilization	3-axis

Equipped with numerous instruments: CZCS (Coastal Zone Color Scanner) out of service on 18 Dec 1986; ERBE (Earth Radiation Budget Experiment); LIMS (Limb IR Monitor of the Stratosphere) out of service mid 1989; SAM 2 (Stratospheric Aerosol Measurement 2) still working in 1992; SAMS (Stratospheric and Mesospheric Sounder) out of service in June 1983; SBUV/TOMS (Solar Backscatter Ultra-Violet/Total Ozone Mapping Spectrometer) SBUV out of service in February 1987, TOMS still working in 1992; SMMR (Scanning Multichannel Microwave Radiometer) out of service on 6 Jul 1988 and last but not least THIR (Temperature Humidity IR Radiometer) out of service in March 1985


 Nimiq

Nimiq is an Inuit word for any object or force that unites things or binds them together. The name Nimiq was selected through a national contest in April 1998.

General

Designation	25740 / 99027A
Launch date	21 May 1999
Country of origin	Canada
Mission	Telecommunications
Geostationary orbit	91°W
Launch vehicle	Proton #266

GEO DBS satellite operated by Telesat Canada, the well known operator of Anik. The satellite should cost $240 million (in-orbit delivery). ExpressVu Inc. will acquire 17 of the 32 transponders.

The satellite was shipped to Tyuratam for launch but had to be flown back to the US because of technical problems with wiring (on TWTAs). Test in orbit were finished on 22 Jun 1999.

Technical data

Specifications

Prime contractor	Lockheed Martin / Spar Aerospace
Platform	A2100AX
Mass at launch	3600 kg
Mass in orbit
Dimension	5.8 height x 2.4 x 2.4 m
Solar array	27 m
Stabilization
DC power	EOL: 8600 W
Design lifetime	12 years
Ku-band

Main transponders	32
Backup transponders
Power	120 W
Bandwidth	24 MHz
Coverage
EIRP max	55 dBW (no official EIRP coverage is provided but reports indicate that Canada and the CONUS receive at least 50 dBW)
G/T max
Polarization	circular
Frequencies	uplink: 17.3-17.8 GHz downlink: 12.2-12.7 GHz

The transponders can be dual-combined to provide 230 W per transponder

Ku-band transponder frequency chart (GHz)

Vertical Downlink	Transponder	Horizontal Downlink
12.224	1
	2	12.239
12.253	3
	4	12.268
12.282	5
	6	12.297
12.311	7
	8	12.326
12.341	9
	10	12.355
12.370	11
	12	12.384
12.399	13
	14	12.414
12.428	15
	16	12.443
12.457	17
	18	12.472
12.486	19
	20	12.501
12.516	21
	22	12.530
12.545	23
	24	12.559
12.574	25
	26	12.588
12.603	27
	28	12.618
12.632	29
	30	12.647
12.661	31
	32	12676


 Program: NOAA

National Oceanic and Atmospheric Administration

Series of American weather satellites which evolved from a long line of experimental and operational satellites beginning with Tiros 1. Operated by NOAA

External resources

http://ns.noaa.gov/NESDIS/NESDIS_Home.html

http://140.90.207.25:8080/EBB/ml/nic00.html

http://www.ccrs.nrcan.gc.ca/ccrs/satsens/satellit/noaae.html

http://poes2.gsfc.nasa.gov/

Instruments

Instruments on all satellites

Other instruments are used occasionnaly:

SBUV (Solar Backscatter UV radiometer) [on NOAA 11 onwards]: ozone distribution

ERBE (Earth Radiation Budget Experiment) [on NOAA 09 & 10]: radiation gains and losses (scanning instruments and non-scanner)

SARSAT [on NOAA 08 onwards]

Argos for data collection on NOAA second generation: 06 onwards

The primary command and data acquisition (CDA) stations are located in Fairbanks, Alaska, and Wallops Island, Va.


Program: NOAA

NOAA 01

NOAA 02

NOAA 03

NOAA 04

NOAA 05

NOAA 06

NOAA B

NOAA 07

NOAA 08

NOAA 09

NOAA 10

NOAA 11

NOAA 12

NOAA 13

NOAA 14

NOAA 15


NOAA's specifications (2nd generation: Tiros N)

Prime contractor	GE Astro
Platform	based on the Tiros N bus
Mass at launch	1418 kg
Mass in orbit	735 kg
Dimension	3.71 m long x 1.88 m diameter
Solar array	2.37 x 4.91 m
Stabilization	3-axis
DC power
Design lifetime	3 years


NOAA's specifications (3rd generation)

Prime contractor	GE Astro
Platform	evolved from NOAA 2nd generation
Mass at launch	1420 kg
Mass in orbit	~1050 kg
Dimension	4.18 m long x 1.88 m diameter
Stabilization	3-axis
Design lifetime	3 years
APT downlink freq.	137.620 MHz (standby)
HRPT downlink freq.	1698.0 MHz
Beacon	136.770 MHz

Telemetry: 2247.5 MHz (8.32 or 16.64 kbps)

Command: 2026.0 MHz (2 kbps)

Data: (2.66 Mbps)


NOAA's payload (NOAA 9 onwards)

AVHRR (Advanced Very High Resolution Radiometer)

Wavebands	0.58-0.68 µm (visible): cloud, snow and ice monitoring 0.725-1.10 µm (near IR): water, vegetation and agriculture surveys 3.55-3.93 µm (near IR): sea surface temperature, volcano, forest fire activity 10.3-11.3 µm (thermal IR): sea surface temperature, soil moisture 11.3-12.5 µm (thermal IR): sea surface temperature, soil moisture
Resolution	1.1 km
Swath width	3000 km
TOVS (Tiros Operational Vertical Sounder)

HIRS/2 (High Resolution IR Sounder): 20 channels in the 0.69 - 14 - 95 µm band; 17.4 km resolution

SSU (Stratospheric Sounding Unit): step-scanned far IR spectrometer with 3 channels in the CO² absorption band (15 µm);147.3 km resolution

MSU (Microwave Sounding Unit): passive 4-channel radiometer operating around 55 GHz; 109 km resolution


 NOAA 01

Also called Itos B

General

Designation	04793 / 70106A
Launch date	11 Dec 1970
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	1421/1471 km
Inclination	101.3°
Period	114.8 min
Launch vehicle	Thor Delta #81
Mass at launch	306.8 kg

Images 24 hours a day


 NOAA 02

Also called Itos D

General

Designation	06235 / 72082A
Launch date	15 Oct 1972
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	1446/1453 km
Inclination	102°
Period	114.9 min
Launch vehicle	Thor Delta #91
Mass at launch	340 kg


 NOAA 03

Also called Itos F

General

Designation	06920 / 73086A
Launch date	6 Nov 1973
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	1499/1508 km
Inclination	102.2°
Period	116.1 min
Launch vehicle	Thor Delta #98
Mass at launch	340 kg


 NOAA 04

Also called Itos G

General

Designation	07529 / 74089A
Launch date	15 Nov 1974
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	1442/1457 km
Inclination	102°
Period	114.9 min
Launch vehicle	Thor Delta #104
Mass at launch	340 kg


 NOAA 05

Also called Itos H

General

Designation	09057 / 76077A
Launch date	29 Jul 1976
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	1504/1520 km
Inclination	102.2°
Period	116.3 min
Launch vehicle	Thor Delta #126


 NOAA 06

Also called NOAA A

General

Designation	11416 / 79057A
Launch date	27 Jun 1979
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	785/800 km
Inclination	98.7°
Period	100.7 min
Launch vehicle	Atlas F
Launch site	Vandenberg

Based on Tiros N

End of life

Out of service	31 Mar 1987


 NOAA B

General

Designation	11819 / 80043A
Launch date	29 May 1980
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	264/1445 km
Inclination	92.2°
Period	102.1 min
Launch vehicle	Atlas F
Launch site	Vandenberg
End of life

Out of service	29 May 1980
Cause	failed to reach a usable orbit
Decay	3 May 1981
Technical data

Specifications


 NOAA 07

Also called NOAA C

General

Designation	12553 / 81059A
Launch date	23 Jun 1981
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	828/847 km
Inclination	98.9°
Period	101.7 min
Launch vehicle	Atlas F
Launch site	Vandenberg
Mass at launch	1405 kg
End of life

Out of service	Jun 1986
Cause	power system failure
Technical data

Specifications


 NOAA 08

Also called NOAA E

General

Designation	13923 / 83022A
Launch date	28 Mar 1983
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	792/817 km
Inclination	98.6°
Period	101 min
Launch vehicle	Atlas F
Launch site	Vandenberg

Was a longer spacecraft than NOAA D (12) and was used to carry an additional Sarsat payload.

End of life

Out of service	29 Dec 1985
Cause	clock and power system failures
Technical data

Specifications

Prime contractor	GE Astro
Platform	based on the Tiros N bus, extended
Mass at launch	1418 kg?
Mass in orbit	735 kg?
Dimension	6.8 m long x 1.88 m diameter
Solar array	2.37 x 4.91 m?
Stabilization	3-axis
DC power
Design lifetime	3 years


 NOAA 09

Also called NOAA F

General

Designation	15427 / 84123A
Launch date	12 Dec 1984
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	835/858 km
Inclination	99.158°
Period	101.8 min
Launch vehicle	Atlas E
Launch site	Vandenberg
Technical data

Specifications

Payload

APT downlink freq.	137.620 MHz (inoperative)
HRPT downlink freq.	1707.0 MHz
Beacon	137.770 MHz


 NOAA 10

Also called NOAA G

General

Designation	16969 / 86073A
Launch date	17 Sep 1986
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	799/818 km
Inclination	98.549°
Period	101 min
Launch vehicle	Atlas E
Launch site	Vandenberg

The ERBE scanner had a scan sticking anomaly

End of life

Out of service	17 Sep 1991
Cause	placed in standby after arrival of NOAA 12, several units had failed
Technical data

Specifications

Payload

APT downlink freq.	137.500 MHz (standby)
HRPT downlink freq.	1698.0 MHz
Beacon	136.770 MHz


 NOAA 11

Also called NOAA H

General

Designation	19531 / 88089A
Launch date	24 Sep 1988
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	814/856 km
Inclination	99.059°
Period	101.9 min
Launch vehicle	Atlas E
Launch site	Vandenberg

Studies ozone

The attitude control subsystem lost two of its four gyros and was operated successfully with specialized onboard software. Several instruments failed in 1994 (AVHRR, SBUV/2, etc.)  It was reactivedted to provide HIRS/2 after the partial failure of this instrument on NOAA 12

End of life

Out of service	Mar 1995 but reactivated in May 1997
Cause	replaced by NOAA 14
Technical data

Specifications

Payload

APT downlink freq.	137.620 MHz (inoperative)
HRPT downlink freq.	1707.0 MHz
Beacon	137.770 MHz (inoperative?)


 NOAA 12

Also called NOAA D

General

Designation	21263 / 91032A
Launch date	14 May 1991
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	804/824 km
Inclination	98.6°
Period	101.2 min
Equator crossing	19:30 northbound
Launch vehicle	Atlas E
Launch site	Vandenberg

No Sarsat package

End of life

Out of service	Nov 1998
Cause	replaced by NOAA 15, placed in standby. HIRS failure in May 1997
Technical data

Specifications

Payload

APT downlink freq.	137.500 MHz (standby)
HRPT downlink freq.	1698.0 MHz
Beacon	136.770 MHz


 NOAA 13

Also called NOAA I

General

Designation	22739 / 93050A
Launch date	9 Aug 1993
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	846/860 km
Inclination	98.9°
Period	102 min
Launch vehicle	Atlas E

Cost: $100 million

End of life

Out of service	21 Aug 1993
Cause	Failure (a screw damaged the power supply)
Technical data

Specifications

Payload


 NOAA 14

Also called NOAA J

General

Designation	23455 / 94089A
Launch date	30 Dec 1994 at 10:02 UT
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	847/861 km
Inclination	98.9°
Period	102 min
Launch vehicle	Atlas E
Launch site	Vandenberg SLC3

Replaced NOAA 11 whose cloud cover imaging instrument had failed a few months before this launch. Besides an imaging radiometer, it carries optical sounders to monitor temperature and moisture content in the atmosphere, and counters to measure energetic electrons and protons.

A gas leak caused some difficulties in attitude control shortly after launch, but this has been resolved. The motor for the Microwave Sounding Unit on the NOAA 14 spacecraft has stopped working. Records show the unit is from a delivery made to Martin Marietta dating back to 1984! The microwave sounder returned to normal operation in May 1995 after a software patch was installed to cope with any repeat failure. Its life expectancy remains uncertain.

In Feb 1995, the SARP failed, the SBUV/2 Cloud Cover Radiometer (CCR) failed, and DTR 4A/B was deemed inoperable.

NOAA 14 also has a power-supply problem in its Sarsat receiver.

Technical data

Specifications

Payload


 NOAA 15

Previously known as NOAA K, also known as POES 1 (Polar-orbiting Operational Environmental Satellite)

General

Designation	25338 / 98030A
Launch date	13 May 1998
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	833 km (sunsynchronous)
Inclination	98.7°
Period	101 min
Launch vehicle	Titan 2 #30
Launch site	Vandenberg

This is the first in a series of five satellites called POES with improved imaging and sounding capabilities. This satellite will replace NOAA 12

After launch, the satellite had problems to deploy one of its antennas. The APT transmissions are disturbed. Nevertheless, high resolution transmissions are operational.

Downlinks at 137.5 MHz

External resources

http://poes2.gsfc.nasa.gov/klm.htm

Technical data

Specifications

Prime contractor
Platform
Mass at launch	2232 kg
Mass in orbit
Dimension	4.2 m long x 1.88 m diameter
Solar array	2.73 x 6.14 m
Stabilization
DC power	833 W
Design lifetime	> 2 years
Frequencies

Command	2026 MHz
Beacon	137.77 & 137.35 MHz
APT downlink freq.	137.5 & 137.620 MHz
HRPT downlink freq.	1698 & 1707 MHz (665.4 kbps realtime or 2.6616 Mbps playback)
Data collection uplink	401.65 MHz (400 bps)
Telemetry	2247,5 MHz (8.32 kbps)
SAR downlink	1544.5 MHz
AVHRR/3 (Advanced Very High Resolution Radiometer)

Wavebands	0.58-0.68 µm (1/ visible): cloud, snow and ice monitoring 0.725-1.10 µm (2/ near IR): water, vegetation and agriculture surveys 1.58-1.64 µm: (3A) snow, ice and cloud discrimination 3.55-3.93 µm (3B/ near IR): sea surface temperature, volcano, forest fire activity 10.3-11.3 µm (4/ thermal IR): sea surface temperature, soil moisture 11.3-12.5 µm (5/ thermal IR): sea surface temperature, soil moisture
Resolution	1.09 km
Swath width	3000 km
TOVS (Tiros Operational Vertical Sounder)

HIRS/3 (High Resolution IR Sounder)

SEM/2 (Space Environnment Monitor): enhanced to measure a lower energy (0.05 keV) and a detector for 140+ MeV

AMSU (Advanced Microwave Sounding Unit): AMSU-A is a 15-channel unit while AMSU-B has got 5 channels.

DCS/2 (Data Collection System): enhanced rate: 2560 bps

SBUB/2


NOAA

NOAA L, M, N and N prime are still to come, built by Martin Marietta. N and N' will be launched after the end of the contury

NOAA N & N prime will use new APT frequencies: 137.1 & 137.9125 MHz


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 Program: NOSS

Naval Ocean Surveillance System, also called Parcae, also called Triplet

American military ocean reconnaissance system. The first experimental satellite of this program could be 05678 / 71110A

Whitecloud (1976-1987, 9 satellites)

The NOSS constellation consists of three orbital planes, each containing four satellites flying in formation; a main satellite and three sub-satellites. Some believe that the satellites periodically deploy solar sails to provide the propulsion required to maintain their precise formation flight.

Another theory says the satellites would be connected by long (several km!) wires?

Some of the NOSS launches carried a LIPS (Living Plume Shield) subsatellite. In those cases a jetisonable toroidal plume shield, which protected the satellite from the exhaust of the Star-37E motor, was fittet with some solar-cell experiments.

The use of the Star-37E motor for the NOSS launches is somewhat conjectural, but is performance fits good with the published wights of the NOSS satellites.

Triplet (1990-..., 3 satellites)

Satellites equipped with infrared sensors, built by Martin Marietta, 3600 kg

The cluster could be composed of only the 3 sub-satellites?

External resources

http://www.fas.org/spp/military/program/surveill/noss.htm


Program: NOSS

NOSS 01

NOSS 02

NOSS 03

NOSS 04

NOSS 05

NOSS 06

NOSS 07

NOSS 08

NOSS 09

NOSS 12

NOSS 13

NOSS 14

NOSS 15


 NOSS 01

Also called OPS 6431

General

Designation	08818 / 76038A
Launch date	30 Apr 1976
Country of origin	United States
Mission	Military: ocean reconnaissance (Whitecloud)
Perigee/Apogee	1128/1092 km
Inclination	63.5°
Period	107.5 min
Launch vehicle	Atlas F
Launch site	Vandenberg
Sub satellites

SSU 1 (08835 / 76038C)

SSU 2 (08836 / 76038D)

SSU 3 (08884 / 76038J)


 NOSS 02

Also called OPS 8781

General

Designation	10502 / 77112A
Launch date	8 Dec 1977
Country of origin	United States
Mission	Military: ocean reconnaissance (Whitecloud)
Perigee/Apogee	1054 / 1169 km
Inclination	63.4°
Period	107.5 min
Launch vehicle	Atlas F
Launch site	Vandenberg
Sub satellites

SSU 4 (10529 / 77112D)

SSU 5 (10544 / 77112E)

SSU 6 (10594 / 77112F)


 NOSS 03

Also called OPS 7245

General

Designation	11720 / 80019A
Launch date	3 Mar 1980
Country of origin	United States
Mission	Military: ocean reconnaissance (Whitecloud)
Perigee/Apogee	1035/1150 km
Inclination	63.0°
Period	107.1 min
Launch vehicle	Atlas F
Launch site	Vandenberg
Sub satellites

EP 1 (11731 / 80019C)

EP 2 (11732 / 80019D)

EP 3 (11745 / 80019G)


 NOSS 04

General

Launch date	9 Dec 1980
Country of origin	United States
Mission	Military: ocean reconnaissance (Whitecloud)
Launch vehicle	Atlas F
Launch site	Vandenberg
End of life

Out of service	9 Dec 1980
Cause	Launch failure


 NOSS 05

Also called OPS 0252

General

Designation	13791 / 83008A
Launch date	9 Feb 1983
Country of origin	United States
Mission	Military: ocean reconnaissance (Whitecloud)
Perigee/Apogee	1063/1186 km
Inclination	63.4°
Period	107.8 min
Launch vehicle	Atlas F
Launch site	Vandenberg
Sub satellites

SSA (13844 / 83008E)

SSB (13845 / 83008F)

SSC (13874 / 83008H)


 NOSS 06

Also called OPS 6432

General

Designation	14112 / 83056A
Launch date	9 Jun 1983
Country of origin	United States
Mission	Military: ocean reconnaissance (Whitecloud)
Perigee/Apogee	1051 / 1170 km
Inclination	63°
Period
Launch vehicle	Atlas F
Launch site	Vandenberg
Sub satellites

GB 1 (14143 / 83056C)

GB 2 (14144 / 83056D)

GB 3 (14180 / 83056G)


 NOSS 07

Also called OPS 8737

General

Designation	14690 / 84012A
Launch date	5 Feb 1984
Country of origin	United States
Mission	Military: ocean reconnaissance (Whitecloud)
Perigee/Apogee	1052 / 1168 km
Inclination	63.4°
Period
Launch vehicle	Atlas F
Launch site	Vandenberg
Sub satellites

JD 1 (14728 / 84012C)

JD 2 (14729 / 84012D)

JD 3 (14795 / 84012F)


 NOSS 08

Also called USA 015

General

Designation	16591 / 86014A
Launch date	9 Feb 1986
Country of origin	United States
Mission	Military: ocean reconnaissance (Whitecloud)
Perigee/Apogee	1049/1166 km
Inclination	63°
Period
Launch vehicle	Atlas F
Launch site	Vandenberg
Sub satellites

USA 016 (16624 / 86014E)

USA 017 (16625 / 86014F)

USA 018 (16631 / 86014H)


 NOSS 09

Also called USA 022

General

Designation	17997 / 87043A
Launch date	15 May 1987
Country of origin	United States
Mission	Military: ocean reconnaissance (Whitecloud)
Perigee/Apogee	1045/1179 km
Inclination	63°
Period
Launch vehicle	Atlas E/F
Launch site	Vandenberg
Sub satellites

USA 023 (18009 / 87043E)

USA 024 (18010 / 87043F)

USA 025 (18025 / 87043H)


 NOSS 12

Also called USA 059

General

Designation	20641 / 90050A
Launch date	8 Jun 1990
Country of origin	United States
Mission	Military: ocean reconnaissance (Triplet)
Perigee/Apogee	1200 km
Inclination	63°
Period
Launch vehicle	Titan 4

Could be in the same orbit as NOSS 09

Sub satellites

USA 060 (20682 / 90050B)

USA 061 (20691 / 90050C)

USA 062 (20692 / 90050D)


 NOSS 13

Also called USA 072

General

Designation	21775 / 91076A
Launch date	8 Nov 1991
Country of origin	United States
Mission	Military: ocean reconnaissance (Triplet)
Perigee/Apogee	1200 km
Inclination	63°
Period
Launch vehicle	Titan 4
Sub satellites

USA 074 (21799 / 91076C)

USA 076 (21808 / 91076D)

USA 077 (21809 / 91076E)


 NOSS 14

General

Launch date	2 Aug 1993
Country of origin	United States
Mission	Military: ocean reconnaissance (Triplet)
Launch vehicle	Titan 4
End of life

Out of service	2 Aug 1993
Cause	launcher explosion


 NOSS 15

Also called NOSS 2-3 or USA 119

General

Designation	23893 / 96029A
Launch date	12 May 1996
Country of origin	United States
Mission	Military: ocean reconnaissance (Triplet)
Orbit	1022 km?
Inclination	63.4°?
Launch vehicle	Titan 4 #17
Sub satellites

USA 120 (23907 / 96029B)

USA 121 (23908 / 96029C)

USA 122 (23862 / 96029D)

TiPS

A tether satellite was carried with this launch called: Tether Physics and Survivability (TiPS)  This experiment consists of 2 small end-masses connected by a 4 km nonconductuve braided tether (total mass: 53 kg). TiPS was jettisoned from its "host vehicle" on 20 June. It is aimed to test the survivability of the tether. The tether is predicted to have a mean life of 5 years before it is cut by orbital debris. The observed life of TiPS will help understand and validate these theoretical predictions.

The two objects could be USA 123 (23936 / 96029E) & 124 (23937 / 96029F)

External resources

http://hyperspace.nrl.navy.mil/TiPS/


 Program: Nova

American navigation program linked to Transit

Evolution compared to Transit satellites: transmitters (150 and 400 MHz) more powerful, on-board computer with larger memory (252 Kbits) that can save 5 days' data, better clock stability and capable of correcting its orbit.


Program: Nova

Nova 1

Nova 2

Nova 3


 Nova 1

Also called NNSS 30 480

General

Designation	12458 / 81044A
Launch date	15 May 1981
Country of origin	United States
Mission	Navigation
Perigee/Apogee	1164/1182 km
Inclination	90.1°
Period	108.9 min
Launch vehicle	Scout #102
Technical data

Transmits with 3 W on 150 MHz and 5 W on 400 MHz.


 Nova 2

Also called NNSS 30 500

General

Designation	15362 / 84110A
Launch date	12 Oct 1984
Country of origin	United States
Mission	Navigation
Perigee/Apogee	1149/1199 km
Inclination	89.9°
Period	108.9 min
Launch vehicle	Scout #104
Technical data

transmits with 3 W on 150 MHz and 5 W on 400 MHz


 Nova 3

Also called NNSS 30 490

General

Designation	19223 / 88052A
Launch date	16 Jun 1988
Country of origin	United States
Mission	Navigation
Perigee/Apogee	1150/1198 km
Inclination	90°
Period	108.9 min
Launch vehicle	Scout #111
Launch site	Vandenberg
Technical data

Transmits with 3 W on 150 MHz and 5 W on 400 MHz


 Program: NPOESS

National Polar-orbiting Operational Environmental Satellite System

Program to be launched in 2006. Is the follow on of DMSP and NOAA. This unique program is designed to save $300 million. it will consist of 3 satellites

External resources

http://www.laafb.af.mil/SMC/PK/NPOESS/rfp.htm

http://www.fas.org/spp/military/program/met/npoess.htm


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 Program: OAO

Orbiting Astronomical Observatory

American astronomy mission


Program: OAO

OAO 1

OAO 2

OAO B

OAO 3


 OAO 1

General

Designation	02142 / 66031A
Launch date	8 Apr 1966
Country of origin	United States
Mission	Scientific: UV astronomy
Perigee/Apogee	782/793 km
Inclination	35°
Period	100.6 min
Launch vehicle	Atlas Agena D
Launch site	Cape Canaveral
End of life

Out of service	8 Apr 1966
Cause	Power failure


 OAO 2

General

Designation	03597 / 68110A
Launch date	7 Dec 1968
Country of origin	United States
Mission	Scientific: UV astronomy
Perigee/Apogee	751/757 km
Inclination	35°
Period	99.9 min
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral


 OAO B

End of life

Out of service	30 Nov 1970
Cause	Launch failure (Atlas Centaur)


 OAO 3

Also called Copernicus for the 500th anniversary of Copernic

General

Designation	06153 / 72065A
Launch date	21 Aug 1972
Country of origin	United States
Mission	Scientific: UV astronomy
Perigee/Apogee	714/723 km
Inclination	35°
Period	99.2 min
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
Mass at launch	2200 kg
End of life

Out of service	18 Jan 1973
External resources

http://heasarc.gsfc.nasa.gov/docs/heasarc/missions/copernicus.html

http://archive.stsci.edu/copernicus/


Oderacs
 Program: Oderacs

Orbital DEbris RAdar Calibration System

US military spacecrafts intended to provide radar cross-sections of very small objects.

External resources

http://www.mae.ncsu.edu/mmrc/Projects/ODERACS/index.html


Program: Oderacs

Oderacs 1A

Oderacs 1B

Oderacs 1C

Oderacs 1D

Oderacs 1E

Oderacs 1F

Oderacs 2A

Oderacs 2B

Oderacs 2C

Oderacs 2D

Oderacs 2E

Oderacs 2F


 Oderacs 1A

General

Designation	22990 / 94006B
Launch date	3 Feb 1994
Country of origin	USA
Mission	Military: radar calibration
Perigee/Apogee	358/386 km
Inclination	59.9°
Period	91.7 min
Launch vehicle	STS 60

10 cm rough Aluminum sphere

End of life

Decay	2 Oct 1994


 Oderacs 1B

General

Designation	22991 / 94006C
Launch date	3 Feb 1994
Country of origin	USA
Mission	Military: radar calibration
Perigee/Apogee	358/386 km
Inclination	59.9°
Period	91.7 min
Launch vehicle	STS 60

10 cm polished Aluminum sphere

End of life

Decay	4 Oct 1994


 Oderacs 1C

General

Designation	22992 / 94006D
Launch date	3 Feb 1994
Country of origin	USA
Mission	Military: radar calibration
Perigee/Apogee	358/386 km
Inclination	59.9°
Period	91.7 min
Launch vehicle	STS 60

5 cm Aluminum sphere

End of life

Decay	?


 Oderacs 1D

General

Designation	22993 / 94006E
Launch date	3 Feb 1994
Country of origin	USA
Mission	Military: radar calibration
Perigee/Apogee	358/386 km
Inclination	59.9°
Period	91.7 min
Launch vehicle	STS 60

5 cm Aluminum sphere

End of life

Decay	?


 Oderacs 1E

General

Designation	22994 / 94006F
Launch date	3 Feb 1994
Country of origin	USA
Mission	Military: radar calibration
Perigee/Apogee	223/226 km
Inclination	57°
Period	89 min
Launch vehicle	STS 60

15 cm Aluminum sphere

End of life

Decay	3 Mar 1995


 Oderacs 1F

General

Designation	22995 / 94006G
Launch date	3 Feb 1994
Country of origin	USA
Mission	Military: radar calibration
Perigee/Apogee	198/202 km
Inclination	57°
Period	88.5 min
Launch vehicle	STS 60

15 cm Aluminum sphere

End of life

Decay	24 Feb 1995


 Oderacs 2A

General

Designation	23471 / 95004C
Launch date	4 Feb 1995 at 04:57 UT
Country of origin	USA
Mission	Military: radar calibration
Perigee/Apogee	314/336 km
Inclination	51.6°
Period	91 min
Launch vehicle	STS 63

10.16 cm diameter Al sphere


 Oderacs 2B

General

Designation	23472 / 95004D
Launch date	4 Feb 1995 at 04:57 UT
Country of origin	USA
Mission	Military: radar calibration
Perigee/Apogee	314/336 km
Inclination	51.6°
Period	91 min
Launch vehicle	STS 63

15.24 cm dia. Al sphere

End of life

Decay	29 Sep 1995


 Oderacs 2C

General

Designation	23473 / 95004E
Launch date	4 Feb 1995 at 04:57 UT
Country of origin	USA
Mission	Military: radar calibration
Perigee/Apogee	314/336 km
Inclination	51.6°
Period	91 min
Launch vehicle	STS 63

5.08 cm diameter steel sphere


 Oderacs 2D

General

Designation	23474 / 95004F
Launch date	4 Feb 1995 at 04:57 UT
Country of origin	USA
Mission	Military: radar calibration
Perigee/Apogee	314/336 km
Inclination	51.6°
Period	91 min
Launch vehicle	STS 63

13.208 cm long dipole wire

End of life

Decay	2 Mar 1995


 Oderacs 2E

General

Designation	23475 / 95004G
Launch date	4 Feb 1995 at 04:57 UT
Country of origin	USA
Mission	Military: radar calibration
Perigee/Apogee	314/336 km
Inclination	51.6°
Period	91 min
Launch vehicle	STS 63

13.208 cm long dipole wire

End of life

Decay	27 Feb 1995


 Oderacs 2F

General

Designation	23476 / 95004H
Launch date	4 Feb 1995 at 04:57 UT
Country of origin	USA
Mission	Military: radar calibration
Perigee/Apogee	314/336 km
Inclination	51.6°
Period	91 min
Launch vehicle	STS 63

4.318 cm length dipole wire


 Program: Offek

Also called offeq

First Israeli program, mainly for military experimentation purposes, especially for remote sensing and optical reconnaissance.


Program: Offek

Offek 1

Offek 2

Offek 3

Offek 4


 Offek 1

Means "Horizon 1"

General

Designation	19519 / 88087A
Launch date	19 Sep 1988
Country of origin	Israel
Mission	Technology
Perigee/Apogee	250/1149 km
Inclination	142.9° (retrograd orbit)
Period	98.8 min
Launch vehicle	Shavit #1
Launch site	Palmahim
Mass at launch	156 kg

First Israeli satellite

End of life

Decay	14 Jan 1989


 Offek 2

Means "Horizon 2"

General

Designation	20540 / 90027A
Launch date	3 Apr 1990
Country of origin	Israel
Mission	Technology
Perigee/Apogee	149/251 km
Inclination	143.2° (retrograd orbit)
Period	88.5 min
Launch vehicle	Shavit #2
Launch site	Palmahim
End of life

Decay	9 Jul 1990


 Offek 3

Means "Horizon 3"

General

Designation	23549 / 95018A
Launch date	5 Apr 1995 at 11:16 UT
Country of origin	Israel
Mission	Military: reconnaissance
Perigee/Apogee	369/729 km
Inclination	143.4° (retrograd orbit)
Period	95.6 min
Launch vehicle	Shavit #4
Launch site	Palmahim
Mass at launch	225 kg

Reported by Israel's media as the first spy satellite... but it's most likely not a fullyfleged spy satellite.

Offek 3 is the first of the second-generation light satellites for Israel. The system is being proposed and marketed by Israel Aircraft Industries and MLM System Engineering and Integration to carry payloads for astronomy and remote sensing purposes. The light-weight electro-optical scanner or Earth Resources Monitoring System carried aboard this mission was developed by El-Op. Equipped with a high-resolution camera.

End of life

Out of service	late 1997

After Israel Space Agency, the satellite might be working 2 more years.

Technical data

Specifications

Prime contractor	IAI
Platform
Mass at launch
Payload mass	36 kg
Dimension
Solar array
Stabilization	3-axis
DC power	180 W
Design lifetime


 Offek 4

Means "Horizon 4"

General

Designation	FTO
Launch date	22 Jan 1998
Country of origin	Israel
Mission	Military: reconnaissance
Launch vehicle	Shavit #5
Launch site	Palmahim

The satellite was said to cost $50 million

End of life

Out of service	22 Jan 1998
Cause	launch failure due to a malfunction in the second stage of the rocket.


 OFO

General

Designation	04690 / 70094A
Launch date	9 Nov 1970
Country of origin	United States
Mission	Scientific
Perigee/Apogee	304/518 km
Inclination	37.4°
Period	92.6 min
Launch vehicle	Scout #70
End of life

Decay	9 May 1971


 Program: OGO

Orbiting Geophysical Observatory

American scientific program of standardized spacecraft capable of conducting many related experiments.

External resources

http://heasarc.gsfc.nasa.gov/docs/heasarc/missions/ogo.html


Program: OGO

OGO 1

OGO 2

OGO 3

OGO 4

OGO 5

OGO 6


 OGO 1

General

Designation	00879 / 64054A
Launch date	5 Sep 1964
Country of origin	United States
Mission	Scientific: magnetosphere study
Perigee/Apogee	4930/144824 km
Inclination	40.7°
Period	3841.9 min
Launch vehicle	Atlas Agena B
Launch site	Cape Canaveral

OGO I carried 20 experiments, more than any previous satellite. The spacecraft's highly elliptical orbit was planned to permit correlated investigations of geophysical and solar phenomena in the Earth's atmosphere and magnetosphere, and in interplanetary space.

Two experiment booms failed to deploy properly, however, and one of these booms obscured the horizon scanner's view of Earth. As a result, spacecraft attitude could not be Earth oriented and OGO I remained spin stabilized at 5 rpm. The solar panels were turned to a more favorable sun angle and all 20 experiments were able to provide data.

OGO 1, together with data from Explorer 21, has indicated the source of much of the Van Allen belt's high-energy radiation as the solar wind - entering the magnetosphere through weak field lines in the magnetosphere's tail on the side of the Earth opposite the sun.

Technical data

Specifications

Prime contractor
Platform
Mass at launch	523 kg
Payload mass	95 kg
Dimension	18 x 6 m
Solar array	32000 solar cells + nickel-cadmium batteries
Stabilization	spin stabilized
DC power
Design lifetime

Spacecraft systems included a communication and data handling system to store up to 128,000 bits per second.


 OGO 2

General

Designation	01620 / 65081A
Launch date	14 Oct 1965
Country of origin	United States
Mission	Scientific: magnetosphere study
Perigee/Apogee	419/1515 km
Inclination	87.4°
Period	104.4 min
Launch vehicle	Thor Agena
Launch site	Vandenberg
End of life

Decay	17 Sep 1981


 OGO 3

General

Designation	02195 / 66049A
Launch date	7 Jun 1966
Country of origin	United States
Mission	Scientific: magnetosphere study
Perigee/Apogee	19519/102806 km
Inclination	77.6°
Period	2911.5 min
Launch vehicle	Atlas Agena B
Launch site	Vandenberg?

The orbit of this satellite remains uncertain. Other sources give 319/122173 km x 31.39 deg x 2915 min. This seems unprobable since with such a low perigee the satellite would have reentred.


 OGO 4

General

Designation	02895 / 67073A
Launch date	28 Jul 1967
Country of origin	United States
Mission	Scientific: magnetosphere study
Perigee/Apogee	422/885 km
Inclination	86°
Period	97.8 min
Launch vehicle	Thor Agena D
Launch site	Vandenberg
End of life

Decay	16 Aug 1972


 OGO 5

General

Designation	03138 / 68014A
Launch date	4 Mar 1968
Country of origin	United States
Mission	Scientific: magnetosphere study
Perigee/Apogee	271/148186 km
Inclination	54°
Period	3795.9 min
Launch vehicle	Atlas Agena D
Launch site	Cape Canaveral


 OGO 6

General

Designation	03986 / 69051A
Launch date	5 Jun 1969
Country of origin	United States
Mission	Scientific: magnetosphere study
Perigee/Apogee	397/1089 km
Inclination	82°
Period	99.7 min
Launch vehicle	Atlas Agena D
Launch site	Vandenberg
End of life

Decay	12 Oct 1979


 Ohsumi

Named as its launch site

General

Designation	04330 / 70011A
Launch date	11 Feb 1970
Country of origin	Japan
Mission
Perigee/Apogee	323/2.416 km
Inclination	31°
Period	113.1 min
Launch vehicle	Lambda L 4S
Launch site	Kagoshima
Mass at launch	23.8 kg

First Japanese satellite


 Oicets

Optical Inter-orbit Communications Engineering Test Satellite

General

Designation
Launch date	early 2000
Country of origin	Japan
Mission	Technology
Perigee/Apogee	600 km
Inclination	35°
Period
Launch vehicle	J1 (3-stage)
Launch site

For orbital testing of elementary technology, particularly light beam acquisition, tracking and directional control for optical intersatellite communications, an important element of future space technology.

There are plans to conduct experiments together with the Artemis geostationary satellite of the European Space Agency.

Technical data

Specifications

Prime contractor
Platform
Mass at launch	570 kg
Mass in orbit
Dimension	0.78 x 1.1. x 1.5 m
Solar array
Stabilization
DC power
Design lifetime

Control in S-band


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 Olympus

Also called L SAT (Large SATellite)

General

Designation	20122 / 89053A
Launch date	12 Jul 1989
Country of origin	Europe
Mission	Telecommunications
Geostationary orbit	19°W
Launch vehicle	Ariane V32
End of life

Out of service	12 Aug 1993
Cause	Out of control

The control's satellite was lost on 29 May 1991 because of a stabilization problem that caused an electric interruption. The satellite then drifted over Pacific and Atlantic. It was found by radars and the control was taken over by the ESA's station in Darmstadt on 19 Jun 1992. It was then put back into service on 7 Aug 1992.

On 12 Aug 1993 it started rotating and fell in backup mode to try to stabilize (during the Perseid shower, because of a meteor impact). It consumed so much ergols that there was not enough left to bring it back in service. The spacecraft was send to the junk orbit.

External resources

http://www.esoc.esa.de/external/mso/olympus.html

Technical data

Specifications

Prime contractor	British Aerospace (now MMS)
Platform	Olympus
Mass at launch	2595 kg
Payload mass	359 kg
Dimension	2.9 x 2.7 x 5.6 m
Solar array	26 m span
DC power	EOL: 3600 W
Stabilization	3-axis
Design lifetime	7 years
Ku-band

Main transponders	2 (DBS) + 4
Backup transponders
Power	DBS: 2 transponders of 230 W (TWTA) others: 4 transponders of 30 W (TWTA)
Bandwidth	DBS: 27 MHz others: 18 & 36 MHz
Coverage	DBS: Italy and Europe (steerable) others: 5 spots
EIRP max	DBS: 63 dBW others: 33.3 dBW
Polarization
Frequencies	DBS: 12/18 GHz others: 12/14 GHz
Ka-band (20/30 GHz)

Main transponders	2
Backup transponders	1
Power	30 W (TWTA)
Bandwidth	40 & 700 MHz
Coverage	2 steerable spot beams
EIRP max	52.1 dBW
Polarization

Equipped with 5 steerable antennas for numerous experiments (direct TV and HDTV). Also equipped with 3 beacons at 12, 20 and 30 GHz for propagation measurements. Non Ku-band DBS transponders are designed for digital transmissions in AMRT with an on-board matrix commuter.


 Opal

Orbiting Picosat Automatic Launcher

General

Designation
Launch date	planned in 1999
Country of origin	United States
Mission
Perigee/Apogee
Inclination
Period
Launch vehicle
Launch site

Stanford University's second Satellite QUIck Research Testbed (SQUIRT) satellite. The SQUIRT program, offered by the Satellite Systems Development Laboratory (SSDL) in the Stanford University Dept. of Aeronautics and Astronautics, is designed to expose graduate level students to all aspects of the design and construction of a satellite. Each SQUIRT micro-satellite is meant to be constructed in one year on a budget of just $50,000. The design for OPAL was started in early April of 1995.

OPAL's (Orbiting Picosat Automatic Launcher) primary mission is to test the feasibility of launching several picosatellites from a mothership satellite. OPAL uses a mechanical launching system to eject three hockey-puck sized picosats. The satellite's secondary payloads consist of a suite of miniature accelerometers and a flux gate magnetometer that will be validated in space.

Four experimental payloads are supplied by various US organisations including RF Beacon, GPS Ionospheric Sounding Payload, Polymer Battery, and Ultra Quiet Stabilisation Platform

Operator: USAF

External resources

http://ssdl.stanford.edu/opal/index.html

Technical data

Specifications

Prime contractor	SSTL
Platform
Mass at launch	50 kg
Mass in orbit
Dimension	hexagonal prism 23.5 cm height, 21 cm outside radius
Solar array
Stabilization	none
DC power
Design lifetime

Uplink: in 420-450 MHz band

Downlink: in 420-450 MHz band

data rate 9600 baud, 2.2 W power


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 Program: Optus

Australian telecommunication satellite system operated by Optus communications. Formerly known as Aussat.


Program: Optus

Optus A1

Optus A2

Optus A3

Optus B1

Optus B2

Optus B3

Optus C1


Optus A's specifications

Prime contractor	Hughes
Platform	HS-376
Mass at launch	1250 kg
Dry mass	540 kg
Mass in orbit	655 kg
Diameter	2.16 m
Height	6.6 m (2.84 m stowed)
Stabilization	Spin stabilized
DC power	1000 W
Design lifetime	7 years (10 for the A3)
Video carrier

Receiver bandwidth	30 MHz
Peak to peak deviation	22.3 MHz/V


Optus A's Ku-band

Main transponders	11+4
Backup transponders	2+2
Power	(11+2) transponders of 12 W (TWTA) (4+2) transponders of 30 W (TWTA)
Bandwidth	45 MHz
Coverage	Australia, New Zealand and New Guinea
EIRP max	12 W: 41 dBW 30 W: 51 dBW
Polarization


Optus A's antenna specifications

Beam	Transponders
National A	1, 3, 4, 6 and 7
South Eastern Australia	1, 3, 5, 7 and 8
Western Australia	2, 4, 7 and 8
Papua New Guinea or South West pacific	4, 6 and 7
National B	9, 10, 12, 13, 14 and 15
North Eastern	9, 11, 14 and 15
Central Australia	10, 12, 14 and 15

This chart gives the possible transponders with beams connections. Alternative selection of Papua New Guinea or South West pacific beams is possible with Optus A3.


Optus A's transponder frequency chart (GHz)

Horizontal uplink	Horizontal downlink	Transponder	Vertical downlink	Vertical uplink
14.025		1	12.277
14.089		2	12.341
14.153		3	12.405
14.217		4	12.469
14.281		5	12.553
14.345		6	12.597
14.409		7 (30 W)	12.661
14.473		8 (30 W)	12.725
	12.309	9		14.057
	12.373	10		14.121
	12.437	11		14.185
	12.501	12		14.249
	12.565	13		14.313
	12.629	14 (30 W)		14.377
	12.693	15 (30 W)		14.441


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Optus B's specifications

Prime contractor	Hughes
Platform	HS-601
Mass at launch	2858 kg
Dry mass	1270 kg
Mass in orbit	1582 kg
Dimension	2.27 x 2.27 x 2.27 m
Solar array	20 m span
Stabilization	3-axis
DC power	BOL: 3500 W EOL: 3000 W
Design lifetime	13.7 years

Carries a Ka-band beacon (30 GHz) and a laser retroreflector for precise satellite location and time transfer demonstrations.

Video carrier

Receiver bandwidth	25 MHz
Peak to peak deviation	17.74 MHz/V


Optus B's L-band

Main transponders	2 (inbound and outband)
Power	150 W (8 SSPA)
Total bandwidth	14 MHz
Coverage	Australia
EIRP max	49 dBW
Polarization	RHCP


Optus B's Ku-band

Main transponders	15+1 (L-band downlink)
Backup transponders	6
Power	50 W (TWTA)
Bandwidth	54 MHz
Coverage	Australia (1 national beam and 5 regional beams) High Performance beam
EIRP max	47 dBW
Polarization	linear


Optus B's antenna specifications

Beam	Transponders
National A	1, 2, 3, 4, 5, 6, 7 and 8
New Zealand	1, 2, 3, 4, 5, 6, 7 and 8
South Eastern Australia	1, 2, 3, 4, 5, 6, 7 and 8
Western Australia	6, 7 and 8
National B	9, 10, 11, 12, 13, 14 and 15
High performance	9, 10, 11, 12, 13, 14 and 15
North Eastern	11, 14 and 15
Central Australia	12, 14 and 15

This chart gives the possible transponders with beams connections. The National A, South Eastern Australia and Western Australia beams can be combined with the New Zealand beam: the power split is 20% to New Zealand and 80% for the other beam.


Optus B's transponder frequency chart (GHz)

Horizontal uplink	Horizontal downlink	Transponder	Vertical downlink	Vertical uplink
14.0299		1	12.2819
14.0925		2	12.3445
14.1551		3	12.4071
14.2177		4	12.4697
14.2803		5	12.5323
14.3429		6	12.5949
14.4055		7	12.6575
14.4681		8	12.7201
	12.3132	9		14.0612
	12.3758	10		14.1238
	12.4384	11		14.1864
	12.5010	12		14.2490
	12.5636	13		14.3116
	12.6262	14		14.3742
	12.6888	15		14.4368
Mobile communication (L-band to Ku-band & Ku-band to L-band):

	12.2705	M (16)		1.6535 (RHCP)
	1.5520 (RHCP)	M (16)		14.0185


Optus B's EIRP (National beam)


Optus B's EIRP (Australian spot beams)


Optus B's EIRP (High Performance beam)


 Optus A1

Also called Aussat A1

General

Designation	15993 / 85076B
Launch date	27 Aug 1985
Country of origin	Australia
Mission	Telecommunications
Geostationary orbit	life time in 160°E
Launch vehicle	STS 27
End of life

Out of service	yes
Technical data

Specifications

Antenna specifications

Ku-band

Transponder frequency chart


 Optus A2

Also called Aussat A2

General

Designation	16275 / 85109C
Launch date	27 Nov 1985
Country of origin	Australia
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	STS 31
Location

Begin	End	Position
L: 27 Nov 1985		156°E
Feb 1995		164°E, inclined
Technical data

Specifications

Antenna specifications

Ku-band

Transponder frequency chart


 Optus A3

Also called Aussat A3

General

Designation	18350 / 87078A
Launch date	16 Sep 1987
Country of origin	Australia
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V19
Location

Begin	End	Position
L: 16 Sep 1987		164°E
Feb 1995		156°E
Aug 1995	Jun 1999	152°E, inclined
Jul 1999		164°E, inclined
Technical data

Specifications

Antenna specifications

Ku-band

Transponder frequency chart

EIRP coverage (dBW)

Central beam

Australian spot beams


Optus A3's EIRP (National beam)

Add 4 to 5 dBW for 30 W transponders


Optus A3's EIRP (Australian spot beams)

Add 4 to 5 dBW for 30 W transponders


 Optus B1

General

Designation	22087 / 92054A
Launch date	13 Aug 1992
Country of origin	Australia
Mission	Telecommunications
Geostationary orbit	160°E
Launch vehicle	Long March 2E (first commercial flight)
Launch site	Xichang
Technical data

Specifications

Antenna specifications

L-band

Ku-band

Transponder frequency chart

EIRP coverage (dBW)

Central beam

Australian spot beams

High Performance beam


 Optus B2

General

Designation	22278 / 92090A
Launch date	21 Dec 1992 at 11:20 UT
Country of origin	Australia
Mission	Telecommunications
Geostationary orbit	n/a
Launch vehicle	Long March 2E
End of life

Out of service	21 Dec 1992
Cause	The satellite was destroyed when the fairing area of the launch vehicle was destroyed some 47 seconds after liftoff. The cause of the failure is still subject to some speculation and disagreement but was almost certainly due to wind shear effects encountered just after liftoff. The Optus B series of satellites have a liquid propulsion apogee engine (not solid propelled motor). They do, however, have a solid perigee stage when launched on Long March 2E. It is almost certain that this solid motor (plus a few remnants of the satellite itself) is all that was delivered into orbit.
Technical data

Specifications

Antenna specifications

L-band

Ku-band

Transponder frequency chart

EIRP coverage (dBW)

Central beam

Australian spot beams

High Performance beam


 Optus B3

This spacecraft is also called Optus B2R

General

Designation	23227 / 94055A
Launch date	27 Aug 1994 at 21:10 UT
Country of origin	Australia
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Long March 2E
Location

Begin	End	Position
L: 27 Aug 1994	Jul 1995	152°E
Aug 1995		156°E

In mid-1998 the satellite was sold to Commonwealth Bank of Australia Ltd (CBA) for A$206 million and leased back from the bank.

Technical data

Specifications

Antenna specifications

L-band

Ku-band

Transponder frequency chart

EIRP coverage (dBW)

Central beam

Australian spot beams

High Performance beam


 Optus C1/D

The "/D" means defense

General

Designation
Launch date	early 2001
Country of origin	Australia
Mission	Telecommunications
Geostationary orbit	156°E
Launch vehicle

The projet is worth $316 million.

A key factor in the decision to go with the Mitsubishi-SS/L proposal was the opportunity for Optus to develop a strategic alliance with the Loral Global alliance of satellite operators.

Technical data

Specifications

Prime contractor	Mitsubishi Electric Co. (MELCO)
Platform	provided by SS/L
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime

The Department of Defence will own and use about half the capability of the satellite for high-capacity, long-range communications to support Australian Defence Force command and control systems.

Ku-band

Main transponders
Backup transponders
Power
Bandwidth
Coverage	entire Australian land mass, as well as East Asia and New Zealand
EIRP max
G/T max
Polarization

direct to home services


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 Program: Orbcomm

Telecommunication program operated by Orbcomm a subsidiary of OSC. It will consist of a network of LEO satellites to relay the GPS-determined locations of cargo trucks, and data from oil pipeline monitors. Orbcomm terminal will also be able to determine their own position based upon Doppler ranging of the satellite. Initial FCC authorization: Oct 1994.

Orbcomm has signed in Sep 1995 the final financing and contruction agreements for an expanded 36-Orbcomm satellite constellation, with Canada's Teleglobe investing $85 million and OSC $75 million.  Technology Resources Industries Bhd. of Malaysia is also a shareholder.

Full-time service began in Dec 1998 (28 satellites). The full network is composed of 4 near-polar satellites and 32 satellites inclined at 45°. Altitude: about 775 km. The global cost of the system is evaluated $330 million

In April 1998 Orbcomm was granted by the FCC to operate 12 more satellites and to higher the altitude of some satellites to 815 km.


Program: Orbcomm

Orbcomm X Orbcomm XP 1 Orbcomm FM 1 Orbcomm FM 2 Orbcomm FM 5 Orbcomm FM 6 Orbcomm FM 7 Orbcomm FM 8 Orbcomm FM 9 Orbcomm FM 10 Orbcomm FM 11 Orbcomm FM 12 Orbcomm FM 13 Orbcomm FM 14 Orbcomm FM 15	Orbcomm FM 16 Orbcomm FM 17 Orbcomm FM 18 Orbcomm FM 19 Orbcomm FM 20 Orbcomm FM 21 Orbcomm FM 22 Orbcomm FM 23 Orbcomm FM 24 Orbcomm FM 25 Orbcomm FM 26 Orbcomm FM 27 Orbcomm FM 28


Orbcomm FM's specifications

Prime contractor	OSC
Platform	Microstar
Mass at launch	40 kg
Mass in orbit
Diameter	1.04 m stowed
Height	0.165 m stowed
Width	2.2235 m deployed
Stabilization	gravity gradient
DC power
Design lifetime
Telemetry	57.6 kbps in VHF

Deploys a 3.28 m long VHF/UHF communications antenna.

Frequencies

Gateway to satellite: 148 - 149.9 MHz (57.6 kbps)

Satellite to client: 137 - 138 MHz (4.8 kbps)

Client to satellite: 148 - 149.9 MHz (2.4 kbps)

Satellite to gateway: 137 - 138 MHz (57.6 kbps)

Beacons: 400.05 - 400.15 MHz (often 400.100 MHz)

Addressing based on X400 protocol. Signals in symmetric differential PSK (SDPSK)


 Orbcomm X

General

Designation	21576 / 91050C
Launch date	17 Jul 1991
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	764/771 km
Inclination	98.4°
Period	100.2 min
Launch vehicle	Ariane V44
Mass at launch	22.8 kg

Experimental satellite. Should provide emergency services.


 Orbcomm XP 1

Also called OXP 1 or Orbcomm CDS (Capabilities Demonstration Satellite)

General

Designation	22489 / 93009A
Launch date	9 Feb 1993
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	727/790 km
Inclination	25°
Period	100 min
Launch vehicle	Pegasus #3
Launch site	Vandenberg

Experimental satellite


 Orbcomm FM 1

General

Designation	23545 / 95017A
Launch date	3 Apr 1995 at 13:48 UT
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	727/756 km
Inclination	70°
Period
Launch vehicle	Pegasus #8
Launch site	Vandenberg

Had stopped sending signals short after launch but control was regained in mid May 1995.

Technical data

Specifications

Plane F

Main downlink: 137.460 MHz


 Orbcomm FM 2

General

Designation	23546 / 95017B
Launch date	3 Apr 1995 at 13:48 UT
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	727/756 km
Inclination	70°
Period
Launch vehicle	Pegasus #8
Launch site	Vandenberg

The uplink antenna was malfunctionning after launch and the satellite didn't receive any signals from the ground station. After a month the problems appeared to be solved.

Technical data

Specifications

Plane F

Main downlink: 137.460 MHz


 Orbcomm FM 3

General

Designation	25158 / 98007B
Launch date	10 Feb 1998
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee
Inclination	108°
Period
Launch vehicle	Taurus #2
Technical data

Specifications

Plane G

Main downlink: 137.6875 MHz


 Orbcomm FM 4

General

Designation	25159 / 98007C
Launch date	10 Feb 1998
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee
Inclination	108°
Period
Launch vehicle	Taurus #2
Technical data

Specifications

Plane G

Main downlink: 137.6875 MHz


 Orbcomm FM 5

General

Designation	25117 / 97084F
Launch date	23 Dec 1997
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	815 / 822 km
Inclination	45°
Period
Launch vehicle	Pegasus #19
Launch site	Wallops Island
Technical data

Specifications

Plane A

Main downlink: 137.7175 MHz


 Orbcomm FM 6

General

Designation	25118 / 97084G
Launch date	23 Dec 1997
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	815 / 822 km
Inclination	45°
Period
Launch vehicle	Pegasus #19
Launch site	Wallops Island
Technical data

Specifications

Plane A

Main downlink: 137.7175 MHz


 Orbcomm FM 7

General

Designation	25119 / 97084H
Launch date	23 Dec 1997
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	815 / 822 km
Inclination	45°
Period
Launch vehicle	Pegasus #19
Launch site	Wallops Island
Technical data

Specifications

Plane A

Main downlink: 137.4400 MHz


 Orbcomm FM 8

General

Designation	25112 / 97084A
Launch date	23 Dec 1997
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	815 / 822 km
Inclination	45°
Period
Launch vehicle	Pegasus #19
Launch site	Wallops Island
Technical data

Specifications

Plane A

Main downlink: 137.7175 MHz


 Orbcomm FM 9

General

Designation	25116 / 97084E
Launch date	23 Dec 1997
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	815 / 822 km
Inclination	45°
Period
Launch vehicle	Pegasus #19
Launch site	Wallops Island
Technical data

Specifications

Plane A

Main downlink: 137.7175 MHz


 Orbcomm FM 10

General

Designation	25113 / 97084B
Launch date	23 Dec 1997
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	815 / 822 km
Inclination	45°
Period
Launch vehicle	Pegasus #19
Launch site	Wallops Island
Technical data

Specifications

Plane A

Main downlink: 137.7175 MHz


 Orbcomm FM 11

General

Designation	25114 / 97084C
Launch date	23 Dec 1997
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	815 / 822 km
Inclination	45°
Period
Launch vehicle	Pegasus #19
Launch site	Wallops Island
Technical data

Specifications

Plane A

Main downlink: 137.4400 MHz


 Orbcomm FM 12

General

Designation	25115 / 97084D
Launch date	23 Dec 1997
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	815 / 822 km
Inclination	45°
Period
Launch vehicle	Pegasus #19
Launch site	Wallops Island
Technical data

Specifications

Plane A

Main downlink: 137.6625 MHz


 Orbcomm FM 13

General

Designation	25413 / 98046A
Launch date	2 Aug 1998
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	815 / 827 km
Inclination	45°
Period	101.3 min
Launch vehicle	Pegasus #19
Launch site	Wallops Island
Technical data

Specifications

Plane B

Main downlink: 137.8000 MHz


 Orbcomm FM 14

General

Designation	25414 / 98046B
Launch date	2 Aug 1998
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	815 / 827 km
Inclination	45°
Period	101.3 min
Launch vehicle	Pegasus #19
Launch site	Wallops Island
Technical data

Specifications

Plane B

Main downlink: 137.7375 MHz


 Orbcomm FM 15

General

Designation	25415 / 98046C
Launch date	2 Aug 1998
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	815 / 827 km
Inclination	45°
Period	101.3 min
Launch vehicle	Pegasus #19
Launch site	Wallops Island
Technical data

Specifications

Plane 3

Main downlink: 137.6625 MHz


 Orbcomm FM 16

General

Designation	25416 / 98046D
Launch date	2 Aug 1998
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	815 / 827 km
Inclination	45°
Period	101.3 min
Launch vehicle	Pegasus #19
Launch site	Wallops Island
Technical data

Specifications

Plane B

Main downlink: 137.7375 MHz


 Orbcomm FM 17

General

Designation	25420 / 98046E
Launch date	2 Aug 1998
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	815 / 827 km
Inclination	45°
Period	101.3 min
Launch vehicle	Pegasus #19
Launch site	Wallops Island
Technical data

Specifications

Plane B

Main downlink: 137.8000 MHz


 Orbcomm FM 18

General

Designation	25419 / 98046F
Launch date	2 Aug 1998
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	815 / 827 km
Inclination	45°
Period	101.3 min
Launch vehicle	Pegasus #19
Launch site	Wallops Island
Technical data

Specifications

Plane B

Main downlink: 137.7375 MHz


 Orbcomm FM 19

General

Designation	25418 / 98046G
Launch date	2 Aug 1998
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	815 / 827 km
Inclination	45°
Period	101.3 min
Launch vehicle	Pegasus #19
Launch site	Wallops Island
Technical data

Specifications

Plane B

Main downlink: 137.7375 MHz


 Orbcomm FM 20

General

Designation	25417 / 98046H
Launch date	2 Aug 1998
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	815 / 827 km
Inclination	45°
Period	101.3 min
Launch vehicle	Pegasus #19
Launch site	Wallops Island
Technical data

Specifications

Plane B

Main downlink: 137.8000 MHz


 Orbcomm FM 21

General

Designation	25475 / 98053A
Launch date	23 Sep 1998
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	~834 /823 km
Inclination	45°
Period	101.3 min
Launch vehicle	Pegasus #23
Technical data

Specifications

Plane C

Main downlink: 137.2500 MHz


 Orbcomm FM 22

General

Designation	25476 / 98053B
Launch date	23 Sep 1998
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	~834 /823 km
Inclination	45°
Period	101.3 min
Launch vehicle	Pegasus #23
Technical data

Specifications

Plane C

Main downlink: 137.2500 MHz


 Orbcomm FM 23

General

Designation	25477 / 98053C
Launch date	23 Sep 1998
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	~834 /823 km
Inclination	45°
Period	101.3 min
Launch vehicle	Pegasus #23
Technical data

Specifications

Plane C

Main downlink: 137.6625 MHz


 Orbcomm FM 24

General

Designation	25478 / 98053D
Launch date	23 Sep 1998
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	~834 /823 km
Inclination	45°
Period	101.3 min
Launch vehicle	Pegasus #23
Technical data

Specifications

Plane C

Main downlink: 137.2500 MHz


 Orbcomm FM 25

General

Designation	25479 / 98053E
Launch date	23 Sep 1998
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	~834 /823 km
Inclination	45°
Period	101.3 min
Launch vehicle	Pegasus #23
Technical data

Specifications

Plane C

Main downlink: 137.2500 MHz


 Orbcomm FM 26

General

Designation	25480 / 98053F
Launch date	23 Sep 1998
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	~834 /823 km
Inclination	45°
Period	101.3 min
Launch vehicle	Pegasus #23
Technical data

Specifications

Plane C

Main downlink: 137.6625 MHz


 Orbcomm FM 27

General

Designation	25481 / 98053G
Launch date	23 Sep 1998
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	~834 /823 km
Inclination	45°
Period	101.3 min
Launch vehicle	Pegasus #19
Technical data

Specifications

Plane C

Main downlink: 137.2500 MHz


 Orbcomm FM 28

General

Designation	25482 / 98053H
Launch date	23 Sep 1998
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	~834 /823 km
Inclination	45°
Period	101.3 min
Launch vehicle	Pegasus #23
Technical data

Specifications

Plane C

Main downlink: 137.6625 MHz


 Program: Orblink

OSC's global satellite network project to provide broadband fixed-site communications services. This program should become operational in 2002.

The system is made of 7 satellites in MEO (9000 km, equatorial orbit). It should use inter-satellite links (65-71 GHz) to provide 15 Gbps links. Uplink and Downlink would take place between 37.5-38.5 GHz and 47.7-48.7 GHz. The coverage is limited to zones between 50° North and South latitudes.

The satellites will be based on Orbital Starbus platform intended for GEO satellites (previously designed by CTA). Each satellite will have 4000 W of power, 100 spot beams for earth links and 2 inter-satellite links. Each should have 9 years lifetime and weigh approx 1600 kg.

They can be launched 2 or 3 at a time on Delta 3, Atlas 2 or Ariane 4 vehicles, or 4 at a time on larger vehicles. Individual satellites also can be launched on a Taurus-derivative launch vehicle.

The system cost is $900 million.


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 Program: Orbview

This is an remote sensing program operated by Orbimage. a subsidiary of OSC

External resources

http://www.orbimage.com/


Program: Orbview

Orbview 1

Orbview 2

Orbview 3

Orbview 4


 Orbview 2

Also called Seastar

General

Designation	24883 / 97037A
Launch date	1 Aug 1997
Country of origin	United States
Mission	Remote sensing
Perigee/Apogee	705 km (sun-synchronous)
Inclination	98.2°
Period	99 min (16 day cycle)
Launch vehicle	Pegasus

Carries NASA's SeaWiFS instrument as the sensor payload, also designated "Oceans Color Data Set."  The objective for global ocean coverage is desired to estimate ocean color, and to derive from these measurements, various biological indicators and other useful scientific products.

The SeaWiFS Team has developed, and will operate, a data system that will process, calibrate, validate, archive, and distribute SeaWiFS data for research. All other aspects of the mission -- satellite construction, launch, command and control and tracking -- are the responsibility of OSC. NASA has contracted with OSC to provide, for five years, the raw satellite data which will be used for research purposes. This contract is worth $43.5 million. OSC will own the data rights for operational and commercial purposes.

External resources

http://seawifs.gsfc.nasa.gov/SEAWIFS.html

Technical data

Specifications

Prime contractor	OSC
Platform	Microstar
Mass at launch	309 kg
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime	10 years

Telemetry: 1702.5 MHz (665.4 kbps)

Command: 2092.59 MHz (19.2 kbps)

Data: 2272.5 MHz (2000 kbps)

SeaWiFS

Wavebands	412 nm (20 nm bandwidth) 443 nm (20 nm bandwidth) 490 nm (20 nm bandwidth) 510 nm (20 nm bandwidth) 555 nm (20 nm bandwidth) 670 nm (20 nm bandwidth) 765 nm (40 nm bandwidth) 865 nm (40 nm bandwidth)
Swath width
Resolution

Has a rotating scanning telescope to achieve a scan angle > 58.3°.

The SeaWiFS instrument is built by Hughes Electronics


 Orbview 3

General

Designation
Launch date	initially planned in 1999
Country of origin	United States
Mission
Perigee/Apogee	470 km sun-synchronous (10:30 AM)
Inclination	97°
Period
Orbital cycle	< 3 days
Launch vehicle	Pegasus

USAF contract worth $41.5 million

Technical data

Specifications

Prime contractor	OSC
Platform	Microstar
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime	5 years

On board storage: 4 GB Maximum data rate: 150 Mbps  Should operate in the 8025-8400 MHz frequency band, TT&C communications would be in UHF-, S- and X-band.

Ability to turn from side to side up to 45° from the polar orbit path

Payload

Wavebands	Panchromatic: 450-900 nm Multispectral: 450-520 nm 520-600 nm 625-695 nm 760-900 nm
Swath width	8 km
Resolution	Panchromatic: 1 m Multispectral: 4 m


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 Orbview 4

General

Designation
Launch date	initially planned in 2000
Country of origin	United States
Mission
Perigee/Apogee	470 km sun-synchronous (10:30 AM)
Inclination	97°
Period
Orbital cycle	< 3 days
Launch vehicle
Technical data

Specifications

Prime contractor	OSC
Platform	Microstar
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime	5 years

On board storage: 4 GB. Maximum data rate: 150 Mbps  Should operate in the 8025-8400 MHz frequency band, TT&C communications would be in UHF-, S- and X-band.

Ability to turn from side to side up to 45° from the polar orbit path

Panchromatic and Multispectral payload

Wavebands	Panchromatic: 450-900 nm Multispectral: 450-520 nm 520-600 nm 625-695 nm 760-900 nm
Swath width	8 km
Resolution	Panchromatic: 1 m Multispectral: 4 m
Hyperspectral payload

Wavebands	450-2000 nm (200 channels)
Swath width	5 km
Resolution	8 m


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 Program: Orion

American telecommunication program operated by Orion Networks  This company was bought by Loral Space & Communications Ltd in late-1997 for approx $479 million. Other companies are involved in Orion: Orion Atlantic L.P. and Orion Asia Pacific Corp.

External resources

http://www.loralorion.net/


Program: Orion

Orion 1

Orion 2

Orion 3

Orion 3R

Orion 4

Orion 7


Orion 1's EIRP (Broad beam to Europe)


Orion 1's EIRP (Spot beams to Europe)


Orion 1's EIRP (Broad beam to US)


Orion 1's EIRP (Spot beams to US)


Orion 1's G/T coverage (Broad beam to Europe)


Orion 1's G/T coverage (Spot beam to Europe)


Orion 1's G/T coverage (Broad beam to US)


Orion 1's G/T coverage (Spot beam to US)


 Orion 1

General

Designation	23413 / 94079A
Launch date	29 Nov 1994
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	37.5°W
Launch vehicle	Atlas Centaur

The Centaur delivered Orion 1 into an unprecedented elliptical transfer orbit of 403 x 122762 km x 25.5°. The orbit was then raised to 25010 km x 122766 km x 3.0°. The apogee was then lowered until reaching GEO. The fuel-saving high apogee transfer technique had been used before, but never with such an extreme apogee.

Technical data

EIRP coverage (dBW)

Broad beam to Europe

Spot beams to Europe

Broad beam to US

Spot beams to US

G/T coverage (dB/K)

Broad beam to Europe

Spot beam to Europe

Broad beam to US

Spot beam to US

Specifications

Prime contractor	Matra Marconi Space
Platform	Eurostar 2000
Mass at launch	2350 kg
Payload mass	375 kg
Dimension	1.7 x 1.6 x 2.1 m
Stabilization	3-axis
DC power	EOL: 3200 W
Payload power	2500 W (in eclipse)
Design lifetime	12 years

Beacon frequency: 11.4505 GHz LHCP (and 11.4510 LHCP GHz backup) Minimum EIRP: 4.5 dBW BPSK modulated

Ku-band

Main transponders	34
Backup transponders
Power	15 W
Bandwidth	6 transponders of 36 MHz 28 transponders of 54 MHz
Coverage	3 spots and 1 zone beam to Europe 4 spots and 1 zone beam to America
EIRP max	Spot beam: 50 dBW Zone beam: 45 dBW
G/T max
SFD	-90 dBW/m²
Polarization	Linear H/V
Transponder frequencies

Europe uplink	14.0 - 14.5 GHz
Europe downlink	11.45 - 11.7 GHz & 12.5 - 12.75 GHz
North Am. uplink	14.0 - 14.5 GHz
North Am. downlink	11.7 - 12.2 GHz
Transponder frequency chart (GHz)

Horizontal  Downlink	Transponder	Vertical  Downlink	Bandwidth (MHz)	Downlink  Beam	European uplink	US uplink	Type
	5	11.483	54	EU broad	14.278 H	14.278 V	trans. or reg.
11.483	14		54	EU spots	14.278 V	14.278 H	net., trans. or reg.
	6	11.546	54	EU broad	14.341 H	n/a	regional
11.546	15		54	EU spots	n/a	14.341 H	trans atlantic
	7	11.609	54	EU broad	14.404 H	14.431 V	trans. or reg.
11.609	16		54	EU spots	n/a	14.404 H	trans atlantic
	8	11.672	54	EU broad	n/a	14.467 V	trans atlantic
11.672	17		54	EU spots	n/a	14.467 H	trans atlantic
11.728	18		54	US broad	14.028 H	14.028 V	network
	26	11.728	54	US spots	14.028 V	14.028 H	network
11.791	19		54	US broad	14.091 H	14.091 V	network
	27	11.791	54	US spots	14.091 V	14.091 H	network
11.854	20		54	US broad	14.154 H	14.154 V	trans. or reg.
	28	11.854	36	US spots	14.145 V	14.145 H	trans. or reg.
	29	11.885	36	US spots	14.1855 V	n/a	trans atlantic
11.917	21		54	US broad	n/a	14.217 V	regional
	30	11.926	36	US spots	14.226 V	14.226 H	trans. or reg.
11.978	22		54	US broad	14.278 H	14.278 V	trans. or reg.
	31	11.978	54	US spots	14.278 V	14.278 V	net., trans. or reg.
12.041	23		54	US broad	n/a	14.341 V	regional
	32	12.041	54	US spots	14.341 V	n/a	trans atlantic
12.104	24		54	US broad	14.404 H	14.404 V	trans. or reg.
	33	12.104	54	US spots	14.404 V	n/a	trans atlantic
12.167	25		54	US broad	14.467 H	n/a	trans atlantic
	34	12.167	54	US spots	14.467 V	n/a	trans atlantic
	1	12.528	54	EU broad	14.028 H	14.028 V	network
12.528	9		54	EU spots	14.028 V	14.028H	network
	2	12.591	54	EU broad	14.091 H	14.091 V	network
12.591	10		54	EU spots	14.091 V	14.091 H	network
12.645	11		36	EU spots	14.145 V	14.145 H	trans. or reg.
	3	12.654	54	EU broad	14.154 H	14.154 V	trans. or reg.
12.685	12		36	EU spots	n/a	14.1855 H	trans atlantic
	4	12.717	54	EU broad	14.217 H	n/a	regional
12.726	13		36	EU spots	14.226 V	14.226 H	trans. or reg.


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 Orion 2

General

Designation
Launch date	mid-1999
Country of origin	United States
Operator	Orion Atlantic L.P.
Mission	Telecommunications
Geostationary orbit	12°W (from there it might interfere with a Eutelsat satellite)
Launch vehicle	Ariane

47°W is the slot for which Orion got FCC's permission for Ka-band, so if the satellite carries Ka-band transponders it should be there, otherwise it should be at 12°W

Warning: due to the prime contractor change, the technical data provided may be completely changed.

Technical data

EIRP coverage (dBW)

Ku-band

Specifications

Prime contractor	SS/L
Platform	FS-1300
Mass at launch	3200 kg
Dry mass	1600 kg
Dimension
Stabilization	3-axis
DC power	EOL: 9000 W
Design lifetime	15 years

In July 1998, Loral replaced the prime contractor Matra Marconi by Space Systems Loral.

Antenna diameters: 2 x 2.4 m, 1 x 1.3 m and 1 x 1.1 m

Ku-band

Main transponders	38 (16 for america, 22 for europe)
Backup transponders
Power	125 W
Bandwidth	54 MHz
Coverage & EIRP max	Europe: 50 dBW America: 47 dBW
G/T max	Europe: -5.2 to 0.5 dB/K  Americas: -2.25 to -0.25 dB/k  South Africa: -5.5 dB/K (uplink only)
Polarization	linear
Frequencies	Uplink: Europe: 13.75 - 14.5 GHz , Americas: 14.0 - 14.5 GHz  Downlink: Europe extended band: 10.95 - 11.2 GHz; European low band: 11.45 - 11.7 GHz; Europe band: 12.5 - 12.75 GHz; Americas: 11.7 - 12.2 GHz

The transponder frequency chart and transponder connectivity is said to be equal to the one of Orion 1 plus additional transponders via extended band for Europe (13.75 - 14 GHz, 10.95 - 11.2 GHz).

Europe to Europe and Europe to Americas

18 transponders fixed for Pan-European (including South Africa)

1 transponder fixed for Trans-Atlantic (shared band)

2 transponders switchable Trans-Atlantic or Pan-American (dedicated band)

1 transponder switchable Trans-Atlantic or Pan-American (shared band)

Americas to Europe and Americas to Americas

4 transponders fixed for Pan-American

1 transponder for fixed Trans-Atlantic (shared band)

2 transponders switchable Trans-Atlantic or Pan-American (dedicated band)

1 transponder switchable Trans-Atlantic or Pan-American (shared band)


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Orion 2's Ku-band EIRP


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 Orion 3

General

Designation	25727 / 99024A
Launch date	5 May 1999
Country of origin	United States
Operator	Orion Asia Pacific Corp.
Mission	Telecommunications
Geostationary orbit	(139°E)
Launch vehicle	Thor Delta #269

To be delivered in orbit. Insured for $265 million

End of life

Out of service	5 May 1999?
Cause	Launch failed, delivered in 162 x 1378 km x 29.5°. Orbit was raised to 420 x 1280 km. A moon flyby (see Asiasat 3) is probable to try and salvage the satellite.
Technical data

EIRP coverage (dBW)

C-band

Ku-band

G/T coverage (dB/K)

C-band

Ku-band, NEA and India

Ku-band, SEA

Specifications

Prime contractor	Hughes
Platform	HS-601HP
Mass at launch	4159 kg
Dry mass	1935 kg
Dimension	5.9 x 2.7 x 3.6 m stowed
Solar array	26 m span (dual-junction gallium arsenide cells)
Stabilization	3-axis
DC power	BOL: 10000 W EOL: 7800 W
Design lifetime	15 years
C-band

Main transponders	10
Backup transponders	4
Power	55 W
Bandwidth	36 MHz
Coverage	Asean and Hawaii
EIRP max	37 dBW
G/T max	-1 dB/K
Polarization	linear H/V
Frequencies	Uplink: 6.425 - 6.725 GHz Downlink: 3.4 - 3.7 GHz

Onboard antenna of 1.3 m diameter

Transponder frequency chart (GHz)

Horizontal Uplink	Horizontal Downlink	Transponder	Vertical Downlink	Vertical Uplink
6.445		1A	3.420
	3.420	1B		6.435
6.485		2A	3.460
	3.460	2B		6.485
6.525		3A	3.500
	3.500	3B		6.525
6.565		4A	3.540
	3.540	4B		6.565
6.605		5A	3.580
	3.580	5B		6.605
Ku-band

Main transponders	25
Backup transponders
Power	80, 140 W
Bandwidth	23 x 54 MHz 2 x 27 MHz
Coverage & EIRP max	NE Asia: 54 dBW, 8 transponders (horizontal) SE Asia: 51 dBW, 6 transponders (vertical, up to 9 when Oceana transponders are switched on this beam) India: 54 dBW, 8 transponders (horizontal) Oceana: 45 dBW, 3 transponders (vertical)
G/T max	2 dB/K
Polarization	linear H/V
Frequencies	Uplink: 14 - 14.5 GHz Downlink: 12.25 - 12.75 GHz

Onboard antenna of 1.8 m diameter

Ku-band 2

Main transponders	8
Backup transponders	3
Power	50 W
Bandwidth	36 MHz
Coverage & EIRP max
G/T max	2 dB/K
Polarization	linear H/V
Frequencies	Uplink: 13.75 - 14.0 GHz Downlink: 11.45 - 11.7 GHz

Onboard antenna of 2 x 2.5 m


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Orion 3's C-band EIRP coverage


Orion 3's Ku-band EIRP coverage


Orion 3's C-band G/T coverage


Orion 3's Ku-band NEA and India G/T coverage


Orion 3's Ku-band SEA G/T coverage


 Orion 3R

General

Designation
Launch date
Country of origin	United States
Operator	Orion Asia Pacific Corp.
Mission	Telecommunications
Geostationary orbit	139°E
Launch vehicle

To replace the failed Orion 3

To be built by Loral


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 Orion 4

For 1999 between 127°W and 135°W

total cost: $210 million

3-axis stabilized, 16 transponders in Ku-band


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Orion 7
 Orion 7, 8 & 9

General

Designation
Launch date	all 3 before May 2002
Country of origin	United States
Operator	Orion Network Systems
Mission	Telecommunications
Geostationary orbit	89°W, 81°W & 78°W
Launch vehicle
Launch site

The project is evaluated at $757 million

A fourth Ka-band satelltie for 127°W is under consideration

Technical data

Specifications

Prime contractor
Platform
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime
Ka-band

Main transponders	32
Backup transponders
Power	60 W
Bandwidth
Coverage	25 fixed and 2 steerable spot beams
EIRP max
Polarization
Frequencies	Uplink: 28.35-28.6 and 29.25-30.0 GHz (in FDMA) Downlink: 19.7-20.2 GHz (in TDM)


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 Orsted

General

Designation	25635 / 99008B
Launch date	Feb 1999
Country of origin	Denmark
Mission	Scientific
Perigee/Apogee	831/847 km
Inclination	98.7°
Period
Launch vehicle	Delta 2 #267

NASA provided a GPS receiver and magnetometer.

Orsted will be delivered to a near sun-synchronous orbit, carrying scientific equipment to study the Earth's magnetic fields and electrical properties. The satellite is semiautonomous with control provided by its onboard computer.

Technical data

Specifications

Prime contractor	CRI of Kobenhavn
Platform
Mass at launch	62 kg
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime

Transmissions: 2215 MHz


 Program: Oscar

Orbiting Satellite Carrying Amateur Radio

HAM radio satellite program. Oscar is a generical name for numerous satellites, they are often identified as #O-xx where # is the initial of an organization and xx the number of the satellite in the Oscar program.

External resources

http://www.amsat.org/amsat/sats/n7hpr/satsum.html


Program: Oscar

Oscar 01	AO-10: Oscar 10	FO-20: Fuji 1B
Oscar 02	UO-11: Uosat 2	AO-21: Informator
Oscar 03	FO-12: Fuji 1A	UO-22: Uosat 5
Oscar 04	AO-13: Oscar 13	KO-23: Kitsat A
Oscar 05	UO-14: Uosat 3	#24 was reserved for Arsène
AO-06: Oscar 06	UO-15: Uosat 4	KO-25: Kitsat B
AO-07: Oscar 07	AO-16: Pacsat	IO-26: Itamsat
AO-08: Oscar 08	DO-17: Dove	AO-27: Eyesat
Phase 3A	WO-18: Webersat	PO-28: Posat
UO-09: Uosat 1	LO-19: Lusat	FO-29: Fuji 2
MO-30: Unamsat 2	TO-31: Tmsat	GO-32: Techsat 2
SO-33: Sedsat	PO-34: Pansat	SO-35: Sunsat
Phase 3D


 Oscar 01

General

Designation	00214 / 61034B
Launch date	12 Dec 1961
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	245/474 km
Inclination	81.2°
Period	91.8 min
Launch vehicle	Thor Agena B
Launch site	Vandenberg
Mass at launch	4.5 kg
End of life

Decay	31 Jan 1962


 Oscar 02

General

Designation	00305 / 62022B
Launch date	2 Jun 1962
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	188/339 km
Inclination	74.2°
Period	89.8 min
Launch vehicle	Thor Agena B
Launch site	Vandenberg
End of life

Decay	21 Jun 1962


 Oscar 03

General

Designation	01293 / 65016F
Launch date	9 Mar 1965
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	874/902 km
Inclination	70.1°
Period	102.7 min
Launch vehicle	Thor Agena D
Launch site	Vandenberg

First Amateur satellite with solar power. First transponder. Transponder operational life 18 days (battery-limited). The 2 beacons operated for several months from the solar cells.

Technical data

Specifications

Mass at launch	18 kg
Stabilization	none
DC power	2.5 W: solar cells; battery

Transponder: 1W, 50kHz bandwidth, 146 MHz uplink, 144 MHz downlink (linear translator).


 Oscar 04

General

Designation	01902 / 65108C
Launch date	21 Dec 1965
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	162/33549 km
Inclination	26.8°
Period	587.5 min
Launch vehicle	Titan 3 #7
End of life

Decay	12 Apr 1976

Built by TRW radio club. Intended on a high altitude but the launch vehicle had a partial failure

Technical data

Specifications

Stabilization	Spin generated by a spring on separation from launch vehicle
DC power	10 W, battery

Beacon: 432 MHz. No telemetry


 Oscar 05

Also called Australis

General

Designation	04321 / 70008B
Launch date	23 Jan 1970
Country of origin	Australia
Mission	Telecommunications
Perigee/Apogee	1431/1475 km
Inclination	101.4°
Period	115 min
Launch vehicle
Launch site	Vandenberg

Built at University of Melbourne, Australia. Launched with Tiros weather satellite. Command receiver (on 2m) and hardwired decoder (first remote control of an amateur satellite). Operational life: 46 days.

Technical data

Specifications

Stabilization	Passive magnetic


 Oscar 06

Also called AO-06 or Phase 2A

General

Designation	06236 / 72082B
Launch date	15 Oct 1972
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	1446/1452 km
Inclination	102°
Period	114.9 min
Launch vehicle
Launch site	Vandenberg

First complex control system (discrete logic). First satellite-satellite communication (via Oscar 07). Demonstrated Doppler-location of ground stations for search and rescue. Demonstrated low-cost medical data relay from remote locations.

End of life

Out of service	21 Jun 1977
Cause	Battery failure
Technical data

Specifications

Stabilization	Passive magnetic
DC power	5.5 W (NiCd battery)

1 W downlink, 435 MHz beacon


  Oscar 07

Also called AO-07

General

Designation	07530 / 74089B
Launch date	15 Nov 1974
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	1438/1456 km
Inclination	101.9°
Period	114.8 min
Launch vehicle	Thor Delta #104

Early demonstrations of low-budget medical data relay and doppler location of ground transmitters for search-and-rescue operations were done using this satellite.

End of life

Out of service	1980
Cause	Battery failure
Technical data

Specifications

Stabilization	Passive magnetic
DC power	15 W (NiCd battery)


 Oscar 08

Also called AO-08 or Phase 2D

General

Designation	10703 / 78026B
Launch date	5 Mar 1978
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	893/903 km
Inclination	99.2°
Period	103 min
Launch vehicle	Thor Delta #139
End of life

Out of service	24 Jun 1983
Cause	Battery failure
Technical data

Specifications

Mass at launch	25.8 kg
Stabilization	Passive magnetic
DC power	15 W (NiCd battery)

Beacons: 29.402 MHz 110mW, 435.095 MHz 100 mW, both Morse CW.


 Phase 3A

End of life

Out of service	23 May 1980
Cause	Launch failure of Ariane L02
Decay	23 May 1980


 Oscar 10

Also called AO-10 or Phase 3B

General

Designation	14129 / 83058B
Launch date	16 Jun 1983
Country of origin	Germany
Mission	Telecommunications
Perigee/Apogee	4007/35442 km
Inclination	27.2°
Period	699.5 min
Launch vehicle	Ariane L06
Mass at launch	155 kg

First amateur satellite with onboard propulsion. The booster bumped Oscar 10 shortly after separation which damaged one or more of its antennas and also caused other internal injuries because the second and subsequent kick motor firings never happended. This left the spacecraft in a lower inclination elliptical orbit. This meant that the bird didn't have the intended operational coverage nor enough solar panel illumination to sustain full operations.

External resources

http://www.amsat.org/amsat/sats/n7hpr/ao10.html

Technical data

Specifications

Prime contractor
Platform
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization	Magnetorquer
DC power	50 W (2 NiCd batteries)
Design lifetime
General beacon	145.809 MHz (unmodulated carrier)
Engineering beacon	145.987 MHz (switched off)
Mode B uplink	435.030 - 435.180 MHz (SSB, CW)
Mode B downlink	145.825 - 145.975 MHz (SSB, CW, inverting)


 Oscar 13

Also called AO-13 or Phase 3C

General

Designation	19216 / 88051B
Launch date	15 Jun 1988
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	809/37995 km
Inclination	57.9°
Period	686.6 min
Launch vehicle	Ariane V23

Much improved brother to Oscar 10: it has the ability to automatically select transponders for each mode at different points in its orbit. However problems occured: it had a RUDAK experiment onboard that failed shortly after launch. Also, in June 1993, the 70 cm downlink transmitter ceased to function, putting an end to Mode J and L operation.

End of life

Decay	6 Dec 1996
External resources

http://www.amsat.org/amsat/sats/n7hpr/ao13.html

Technical data

Specifications

Prime contractor
Platform
Mass at launch	140 kg
Mass in orbit	90 kg
Dimension
Solar array
Stabilization	Magnetorquer
DC power	50 W (NiCd battery)
Design lifetime

Payload power: 145 MHz - 50 W; 435 MHz - 111 W; 2350 MHz - 1.25 W

general beacon	145.812 mhz (psk, cw, rtty)
engineering beacon	145.985 mhz (psk, cw, rtty)
mode b uplink	435.423 - 435.573 mhz (ssb, cw)
mode b downlink	145.825 - 145.975 mhz (ssb, cw, inverting)
general beacon	435.651 mhz (psk, rtty)
engineering beacon	435.677 mhz (psk, rtty)
mode l uplink	1269.351 - 1269.641 mhz (ssb, cw)
mode l downlink	435.715 -  436.005 mhz (ssb, cw, inverting)
mode j uplink	144.423 - 144.473 mhz (ssb, cw)
mode j downlink	435.940 - 435.990 mhz (ssb, cw, inverting)
beacon	2400.325 mhz (psk, rtty)
beacon	2400.664 mhz (psk, rtty)
mode s uplink	435.603 -  435.639 mhz (ssb, cw, fm)
mode s downlink	2400.711 - 2400.747 mhz (ssb, cw, fm)
rudak uplink	1269.710 mhz (inoperative)
rudak downlink	435.677 mhz (inoperative)

The beacon output alternates between CW, 50 baud RTTY and 400 bps PSK. Beacon transmissions contain satellite engineering data and bulletins from ground control.


 Program: OSO

Orbiting Solar Observatory

American Sun observation program


Program: OSO

OSO 1

OSO 2

OSO C destroyed by Thor Delta #33

OSO 3

OSO 4

OSO 5

OSO 6

OSO 7

OSO 8


 OSO 1

General

Designation	00255 / 62006A
Launch date	7 Mar 1962
Country of origin	United States
Mission	Scientific: Sun observation
Perigee/Apogee	522/553 km
Inclination	32.8°
Period	95.3 min
Launch vehicle	Thor Delta #8
End of life

Out of service	Apr 1963
Decay	8 Oct 1981
External resources

http://heasarc.gsfc.nasa.gov/docs/heasarc/missions/oso1.html


 OSO 2

General

Designation	00987 / 65007A
Launch date	3 Feb 1965
Country of origin	United States
Mission	Scientific: Sun observation
Perigee/Apogee	294/306 km
Inclination	32.8°
Period	90.5 min
Launch vehicle	Thor Delta #29
End of life

Decay	9 Aug 1989


 OSO 3

General

Designation	02703 / 67020A
Launch date	8 Mar 1967
Country of origin	United States
Mission	Scientific: Sun observation
Perigee/Apogee	546/570 km
Inclination	32.8°
Period	95.8 min
Launch vehicle	Thor Delta #46
End of life

Out of service	Nov 1969
Decay	4 Apr 1982
External resources

http://heasarc.gsfc.nasa.gov/docs/heasarc/missions/oso3.html


 OSO 4

General

Designation	03000 / 67100A
Launch date	18 Oct 1967
Country of origin	United States
Mission	Scientific: Sun observation
Perigee/Apogee	552/555 km
Inclination	32.9°
Period	95.7 min
Launch vehicle	Thor Delta #53
End of life

Out of service	Dec 1971
Decay	15 Jun 1982
External resources

http://heasarc.gsfc.nasa.gov/docs/heasarc/missions/oso4.html


 OSO 5

General

Designation	03663 / 69006A
Launch date	22 Jan 1969
Country of origin	United States
Mission	Scientific: Sun observation
Perigee/Apogee	538/559 km
Inclination	33°
Period	95.6 min
Launch vehicle	Thor Delta #64
End of life

Out of service	Jul 1975
Decay	2 Apr 1984
External resources

http://heasarc.gsfc.nasa.gov/docs/heasarc/missions/oso5.html


 OSO 6

General

Designation	04065 / 69068A
Launch date	9 Aug 1969
Country of origin	United States
Mission	Scientific: Sun observation
Perigee/Apogee	489/554 km
Inclination	32.9°
Period	95.1 min
Launch vehicle	Thor Delta #72
End of life

Out of service	Jan 1972
Decay	7 Mar 1981
External resources

http://heasarc.gsfc.nasa.gov/docs/heasarc/missions/oso6.html


 OSO 7

General

Designation	05491 / 71083A
Launch date	29 Sep 1971
Country of origin	United States
Mission	Scientific: Sun observation
Perigee/Apogee	326/572 km
Inclination	33.1°
Period	93.5 min
Launch vehicle	Thor Delta #85
End of life

Out of service	Jul 1974
Decay	9 Jul 1974
External resources

http://heasarc.gsfc.nasa.gov/docs/heasarc/missions/oso7.html


 OSO 8

General

Designation	07970 / 75057A
Launch date	21 Jun 1975
Country of origin	United States
Mission	Scientific: Sun observation
Perigee/Apogee	539/553 km
Inclination	32.9°
Period	95.6 min
Launch vehicle	Thor Delta #112
Mass at launch	1064 kg
End of life

Out of service	Sep 1978
Decay	9 Jul 1986
External resources

http://heasarc.gsfc.nasa.gov/docs/heasarc/missions/oso8.html


 Program: OTS

Orbital Test Satellite

European experimental telecommunication program decided by the CEPT (Conférence Européenne des Postes et Télécommunications) with the EBU.


Program: OTS

OTS 1

OTS 2


OTS' specifications

Prime contractor	British Aerospace (now MMS)
Platform	OTS
Mass at launch	865 kg
Mass in orbit	444 kg
Dimension	2.4 x 2.1 x 1.7 m
Solar array	9.3 m span
Stabilization	3-axis
DC power	BOL: 750 W EOL: 555 W
Design lifetime	3 years
Phone circuits	6000


OTS' Ku-band (downlink in 11 GHz)

Module A

Main transponders	4
Backup transponders
Power	20 W
Bandwidth	2 of 40 MHz 2 of 120 MHz
Coverage	40 MHz: European beam A 120 MHz: spot beam
Polarization	linear H/V
Module B

Main transponders	2
Backup transponders
Power	20 W
Bandwidth	5 MHz
Coverage	European beam B
Polarization	circular L/R


 OTS 1

End of life

Out of service	13 Sep 1977 (Friday 13th!)
Cause	Launch failure of a Thor Delta #134
Technical data

Specifications

Ku-band


 OTS 2

General

Designation	10855 / 78044A
Launch date	11 May 1978
Country of origin	Europe
Mission	Telecommunications
Geostationary orbit	10°E
Launch vehicle	Thor Delta #141
End of life

Out of service	Jan 1991
Technical data

Specifications

Ku-band


 Program: OV

Orbiting Vehicle

American program

Each OV1 payload had its own propulsion module. Some OV1 missions carried also a suborbital payload (FIRE 1 & 2, ABRES 6, SSP 29)


Program: OV

OV 1-02

OV 1-04

OV 1-05

OV 1-08

OV 1-09

OV 1-10

OV 1-13

OV 1-14

OV 1-19

OV 1-21

OV 2-1

OV 2-3

OV 2-5

OV 3-1

OV 3-2

OV 3-3

OV 3-4

OV 5-5

OV 5-6

OV 5-9


 OV 1-02

General

Designation	01613 / 65078A
Launch date	5 Oct 1965
Country of origin	United States
Mission
Perigee/Apogee	406/2731 km
Inclination	144.2°
Period	117.5 min
Launch vehicle	Atlas D
Launch site	Vandenberg


 OV 1-04

General

Designation	02121 / 66025A
Launch date	30 Mar 1966
Country of origin	United States
Mission
Perigee/Apogee	884/1008 km
Inclination	144.5°
Period	104 min
Launch vehicle	Atlas D
Launch site	Vandenberg


 OV 1-05

General

Designation	02122 / 66025B
Launch date	30 Mar 1966
Country of origin	United States
Mission
Perigee/Apogee	985/1055 km
Inclination	144.6°
Period	105.6 min
Launch vehicle	Atlas D
Launch site	Vandenberg


 OV 1-08

General

Designation	02324 / 66063A
Launch date	14 Jul 1966
Country of origin	United States
Mission
Perigee/Apogee	985/1022 km
Inclination	144.2°
Period	105.2 min
Launch vehicle	Atlas D
Launch site	Vandenberg
End of life

Decay	4 Jan 1978


 OV 1-09

General

Designation	02610 / 66111A
Launch date	11 Dec 1966
Country of origin	United States
Mission
Perigee/Apogee	471/4626 km
Inclination	99.1°
Period	139.9 min
Launch vehicle	Atlas D
Launch site	Vandenberg


 OV 1-10

General

Designation	02611 / 66111B
Launch date	11 Dec 1966
Country of origin	United States
Mission
Perigee/Apogee	538/604 km
Inclination	93.4°
Period	96.1 min
Launch vehicle	Atlas D
Launch site	Vandenberg


 OV 1-13

General

Designation	03173 / 68026A
Launch date	6 Apr 1968
Country of origin	United States
Mission
Perigee/Apogee	564/9241 km
Inclination	99.9°
Period	198.7 min
Launch vehicle	Atlas F
Launch site	Vandenberg


 OV 1-14

General

Designation	03174 / 68026B
Launch date	6 Apr 1968
Country of origin	United States
Mission
Perigee/Apogee	540/9892 km
Inclination	100°
Period	207.1 min
Launch vehicle	Atlas F
Launch site	Vandenberg


 OV 1-19

General

Designation	03825 / 69025C
Launch date	18 Mar 1969
Country of origin	United States
Mission
Perigee/Apogee	482/5583 km
Inclination	104.8°
Period	151.4 min
Launch vehicle	Atlas F
Launch site	Vandenberg


 OV 1-21

General

Designation	05397 / 71067B
Launch date	7 Aug 1971
Country of origin	United States
Mission
Perigee/Apogee	774/899 km
Inclination	87.6°
Period	101.7 min
Launch vehicle	Atlas F
Launch site	Vandenberg


 OV 2-1

Also called LCS 2

General

Designation	01624 / 65082A
Launch date	15 Oct 1965
Country of origin	United States
Mission
Perigee/Apogee	708/791 km
Inclination	32.6°
Period	99.8 min
Launch vehicle	Titan 3 #6
End of life

Decay	27 Jul 1972


 OV 2-3

General

Designation	01863 / 65108A
Launch date	21 Dec 1965
Country of origin	United States
Mission
Perigee/Apogee	167/33662 km
Inclination	26.4°
Period	589.3 min
Launch vehicle	Titan 3 #7
End of life

Decay	17 Aug 1975


 OV 2-5

General

Designation	03428 / 68081A
Launch date	26 Sep 1968
Country of origin	United States
Mission
Geostationary orbit
Launch vehicle	Titan 3 #31
End of life

Out of service	yes


 OV 3-1

General

Designation	02150 / 66034A
Launch date	22 Apr 1966
Country of origin	United States
Mission
Perigee/Apogee	339/4068 km
Inclination	82.4°
Period	131.9 min
Launch vehicle	Scout #44


 OV 3-2

General

Designation	02517 / 66097A
Launch date	28 Oct 1966
Country of origin	United States
Mission
Perigee/Apogee	319/1599 km
Inclination	81.9°
Period	104.2 min
Launch vehicle	Scout #49
End of life

Decay	29 Sep 1971


 OV 3-3

General

Designation	02389 / 66070A
Launch date	4 Aug 1966
Country of origin	United States
Mission
Perigee/Apogee	348/3132 km
Inclination	81.4°
Period	121.3 min
Launch vehicle	Scout #47


 OV 3-4

General

Designation	02201 / 66052A
Launch date	9 Jun 1966
Country of origin	United States
Mission
Perigee/Apogee	643/4704 km
Inclination	40.9°
Period	142.9 min
Launch vehicle	Scout #44


 OV 5-5

General

Designation	03950 / 69046A
Launch date	23 May 1969
Country of origin	United States
Mission
Perigee/Apogee	59630/69130 km
Inclination	33°
Period	3121.9 min
Launch vehicle
Launch site	Cape Canaveral


 OV 5-6

General

Designation	03951 / 69046B
Launch date	23 May 1969
Country of origin	United States
Mission
Perigee/Apogee	59540/69022 km
Inclination	33.6°
Period	3115.4 min
Launch vehicle
Launch site	Cape Canaveral
Technical data

Transmits on 136.380 MHz


 OV 5-9

General

Designation	03952 / 69046C
Launch date	23 May 1969
Country of origin	United States
Mission
Perigee/Apogee	59543/69011 km
Inclination	33.5°
Period	3115.1 min
Launch vehicle
Launch site	Cape Canaveral


 Quick Bird

General

Designation
Launch date	late 1998
Country of origin	United States
Mission
Perigee/Apogee	600 km, sun-synchronous
Inclination	52°
Period
Launch vehicle	Cosmos C
Launch site

US satellite operated by Earth Watch Inc. The cost of the systems is $200 million

External resources

http://www.ball.com/aerospace/qbird.html

http://www.digitalglobe.com/company/spacecraft/

Technical data

Specifications

Prime contractor	Ball aerospace
Platform
Mass at launch	900 kg
Payload mass	300 kg
Dimension
Solar array
Stabilization
DC power	350 W
Design lifetime	5 years

Body-pointed spacecraft with ± 30° fore-and-aft, and side-to-side pointing capability

Panchromatic Sensor

Wavebands	450-900 nm
Resolution	0.82 m, image size: 22 km x 22 km
Multispectral Sensor

Wavebands	Blue: 450-520 nm Green: 520-600 nm Red: 630-690 nm Near IR: 760-900 nm
Resolution	3.28 m, image size: 22 km x 22 km

Camera provided by Kodak

On-board data storage: 137 Gigabits

The uplink and downlink receivers both use NSA-approved encryption/decryption, with an emergency time-out on the uplink decryptor to allow unencrypted access in case of a system failure. Uplink: S-band (2 kbps), Downlink: X-band (4, 16 or 256 kbps)


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 Quickscat

Quick Scattermeter, also called Seawinds

General

Designation	25789 / 99034A
Launch date	20 Jun 1999
Country of origin	United States
Mission	Remote sensing
Perigee/Apogee	803 km sun-synchronous (ascending node crossing: 6:00)
Inclination	98.7°
Period
Launch vehicle	Titan 2 #20

Mission worth $93 million ($32 for the satellite alone)

To replace the NSCAT payload aboard Adeos 1

External resources

http://winds.jpl.nasa.gov/missions/quikscat/quikindex.html

http://www.jpl.nasa.gov/quikscat/

Technical data

Specifications

Prime contractor	Ball Aerospace
Platform	BCP 2000
Mass at launch	970 kg
Payload mass	200 kg
Dimension	2.2 x 1.7 x 1.4 m
Solar array
Stabilization	3-axis
DC power	300 W
Design lifetime	2 years

The payload (Seawinds) is provided by JPL. It's a specialized microwave radar that measures near-surface wind speed and direction under all weather and cloud conditions over Earths oceans. It will collect wind-speed and wind direction data. The radar works ar 13.4 GHz. It has a 1800 km swath width. Can measure winds from 3 to 20 meter per second with an accuracy of 2 meters and direction with an accuracy of 20°

S-band telemetry and command

data downlink in S-band at 2 Mbps; 2 kbps S-band uplink

8 Gbit solid-state recorder

Ball will provide launch support and mission control and operations for a two-year period following launch.


 QuickTOMS

General

Designation
Launch date	planned in 2000
Country of origin	United States
Mission	Remote sensing
Perigee/Apogee	probably sun-synchronous
Inclination
Period
Launch vehicle	Taurus

Mission operated by NASA to study ozone.

worth $23 million including the launch

Technical data

Specifications

Prime contractor	OSC
Platform	Microstar
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime	3 years

Will carry a Total Ozone Mapping Spectrometer (TOMS)


 Pacsat

Also called Microsat 1 or AO-16 or Oscar 16

General

Designation	20439 / 90005D
Launch date	22 Jan 1990
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	781/797 km
Inclination	98.6°
Period	100.6 min
Launch vehicle	Ariane V35
Mass at launch	9 kg

Based on a Amsat-NA Microsat bus

External resources

http://www.amsat.org/amsat/sats/nk6k/msatmain.html

http://www.amsat.org/amsat/sats/n7hpr/ao16.html

Technical data

S-Band beacon	2401.143 MHz
Uplink	1200 bps Manchester coded (Biphase-L) FSK (FM) AX.25 145.900 145.920 145.940 145.960 MHz
Downlink	1200 bps BPSK (SSB) AX.25, either one of the two frequencies below:
	437.026 MHz (LHCP in northern hemisphere), normal unfiltered PSK 437.051 MHz (RHCP in northern hemisphere), Raised Cosine modulation

Passive magnetic stabilization


 Pageos

Passive Geodetic Earth Orbiting Satellite

General

Designation	02253 / 66056A
Launch date	24 Jun 1966
Country of origin	United States
Mission	Scientific: Geodesy
Perigee/Apogee	2953/5207 km
Inclination	84.4°
Period	177.4 min
Launch vehicle	Thor Agena D
Launch site	Vandenberg

Was an inflatable 30 (or 41?) m diameter aluminum coated mylar balloon weighing 55 kg.

In 1975 the satellite broke up into dozens of pieces... numerous decayed but some remain in orbit. They are of special interest for scientist studying solar radiation pressure (SRP)... because on some orbits, the debris actually gain altitude!


 Paksat

Satellite planned by the Pakistani government, to be ordered from Alcatel Espace. Contract worth $220 million.

The satellite should carry 26 transponders and have 15 years lifetime.


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 Program: Palapa

"Palapa" means "unity" in Indonesian

Indonesian telecommunication program

The program was developped in 1975 to solve communications (phone, TV) problems between the numerous islands that compose the country. Two years after the Philippines asked to use to system for their national communications. In 1979 Intelsat recognized the system as a regional operator.

Nowadays the Palapa system is operated by two companies. PT Telkom is state owned and operates (and operated) the Palapa A, B and D's. Palapa C's are operated by a private company, PT Satelindo. A third company owns and operates a few transponders: PT PSN

PT Telkom (state-owned) and PT Satelindo should join forces...


Program: Palapa

Palapa A1

Palapa A2

Palapa B1

Palapa B2

Palapa B2 P

Palapa B2 R

Palapa B4

Palapa C1

Palapa C2

Palapa C3

Palapa D1


Palapa A's C-band

Main transponders	12
Backup transponders
Power
Bandwidth	36 MHz
Coverage	Indonesia
EIRP max	34 dBW
Polarization

Satellite designed by Hughes (HS-333), lifetime: 7 years


Palapa B's specifications

Prime contractor	Hughes
Platform	HS-376
Mass at launch	1200 kg
Mass in orbit	628 kg
Diameter	2.16 m
Height	6.83 m deployed
Stabilization	Spin stabilized
DC power	BOL: 1062 W
Design lifetime	8 years


Palapa B's C-band

Main transponders	24
Backup transponders	6
Power	10 W (TWTA)
Bandwidth	36 MHz
Coverage	Indonesia
EIRP max	34 dBW
Polarization


Palapa C's specifications

Prime contractor	Hughes
Platform	HS-601
Mass at launch	2990 kg
Mass in orbit	1800 kg
Dimension	4.5 x 3.4 x 2.8 m
Solar array	20 m
Stabilization	3-axis
DC power	EOL: 3400 W
Design lifetime	14 years

Features 4 octogonal antennas


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Palapa C's C-band

Main transponders	24 + 6 (extended)
Backup transponders	8
Power	standard freq.: 21.5 W (SSPA) extended freq.: 26.75 W (SSPA)
Bandwidth	36 Mhz
Coverage & EIRP max	Indonesia and New Zealand: 36.5 dBW Indonesia: 37 dBW Asia beam (India to Japan): 36 dBW
G/T max	-1 dB/K
Polarization	linear
Frequencies	Uplink: 5.925-6.665 GHz Downlink: 3.400-4.200 GHz


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Palapa C's Ku-band

Main transponders	4
Backup transponders	2
Power	130 W
Bandwidth	72 MHz
Coverage & EIRP max	K1 (Indonesia, Thailand to HongKong): 50 dBW (horizontal) K2 (Japan & Korea): 50 dBW (vertical)
G/T max	+3 dB/K
Polarization	linear H/V
Frequencies	Uplink: 13.750-14.490 GHz Downlink: 10.950-11.690 GHz


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Palapa C's C-band transponder frequency chart (GHz)

Horizontal Uplink	Horizontal Downlink	Channel	Vertical Downlink	Vertical Uplink	Coverage
	3.720	1H		5.945	C1 or C2
5.965		1V	3.740		C1
	3.760	2H		5.985	C1 or C1'
6.005		2V	3.780		C1
	3.800	3H		6.025	C1 or C2
6.045		3V	3.820		C1
	3.840	4H		6.065	C1 or C1'
6.085		4V	3.860		C1
	3.880	5H		6.105	C1 or C2
6.125		5V	3.900		C1
	3.920	6H		6.145	C1 or C1'
6.125		6V	3.940		C1
	3.960	7H		6.185	C1 or C2
6.205		7V	3.980		C1
	4.000	8H		6.225	C1 or C1'
6.245		8V	4.020		C1
	4.040	9H		6.265	C1 or C2
6.285		9V	4.060		C1
	4.080	10H		6.305	C1 or C1'
6.325		10V	4.100		C1
	4.120	11H		6.345	C1 or C2
6.365		11V	4.140		C1
	4.160	12H		6.385	C1 or C1'
6.405		12V	4.180		C1
	3.420	1EH		6.445	C1 or C2
	3.460	2EH		6.485	C1 or C1'
	3.500	3EH		6.525	C1 or C2
	3.540	4EH		6.565	C1 or C1'
	3.580	5EH		6.605	C1 or C2
	3.620	6EH		6.645	C1 or C1'


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Palapa C's Ku-band transponder frequency chart (GHz)

Uplink	Channel	Downlink
13.790	1K	10.990
13.950	2K	11.150
14.290	3K	11.490
14.450	4K	11.650

Horizontal downlink polarization is K1 coverage; Vertical downlink polarization is K2 coverage

Signal can be uplinked in both polarization so that the 2 coverage zones are used


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 Palapa A1

General

Designation	09009 / 76066A
Launch date	8 Jul 1976
Country of origin	Indonesia
Mission	Telecommunications
Geostationary orbit	83°E
Launch vehicle	Thor Delta #125
End of life

Out of service	1985
Technical data

C-band


 Palapa A2

General

Designation	09862 / 77018A
Launch date	10 Mar 1977
Country of origin	Indonesia
Mission	Telecommunications
Geostationary orbit	77°E
Launch vehicle	Thor Delta #129
End of life

Out of service	1988
Technical data

C-band


 Palapa B1

Palapa Pacific 1 (PP1)

General

Designation	14134 / 83059C
Launch date	18 Jun 1983
Country of origin	Indonesia
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	STS 07

This satellite was taken over in 1991 by an affiliate of Satelindo, PT Pasifik Satelit Nusantara and renamed Palapa Pacific 1

Location

Begin	End	Position
L: 30 Oct 1982		replaced Palapa A1
Mar 1995	Sep 1995	134°E, inclined
End of life

Out of service	Oct 1995
Cause	drifting but not removed from the belt... probably ran out of fuel!
Technical data

Specifications

C-band


 Palapa B2

General

Designation	14692 / 84011D
Launch date	6 Feb 1984
Country of origin	Indonesia
Mission	Telecommunications
Geostationary orbit
Launch vehicle	STS 11

Launched on a bad orbit (faulty perigee motor) it was retrieved on 12 Nov 1984 by STS 19. This retrieval was financed by the insurance companies, despite the operator's refusal to retrieve it and asked for the insurance money (then used to order Palapa B2P). Some time later the operator changed it's mind and relaunched it as Palapa B2R.

Technical data

Specifications

C-band


 Palapa B2P

Also called Mabuhay 0

General

Designation	17706 / 87029A
Launch date	20 Mar 1987
Country of origin	Indonesia
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Thor Delta #181

In mid 1996 the bird was sold to PLDT (by PT Pasifik Satelit Nusantara) for a little over $3 million to become the first satellite of the Mabuhay system.

Location

Begin	End	Position
L: 20 Mar 1987	May 1996	113°E
Aug 1996	Aug 1997	144°E, inclined
Sep 1997		142°E, inclined
End of life

Out of service	Jan 1998
Cause	deorbited
Technical data

C-band EIRP coverage (dBW)

Specifications

C-band


Palapa B2P's EIRP


 Palapa B2R

General

Designation	20570 / 90034A
Launch date	13 Apr 1990
Country of origin	Indonesia
Mission	Telecommunications
Geostationary orbit	108°E
Launch vehicle	Delta 2 #194

It's Palapa B2 retrieved from orbit and modernized.

Technical data

C-band EIRP coverage (dBW)

Specifications

C-band


Palapa B2R's EIRP


 Palapa B4

General

Designation	21964 / 92027A
Launch date	14 May 1992 at 00:40 UT
Country of origin	Indonesia
Mission	Telecommunications
Geostationary orbit	118°E
Launch vehicle	Delta 2 #209

Cost: $56.4 million

Technical data

C-band EIRP coverage (dBW)

Specifications

C-band


Palapa B4's EIRP


 Palapa C1

General

Designation	23779 / 96006A
Launch date	1 Feb 1996
Country of origin	Indonesia
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Atlas Centaur #98
Location

Begin	End	Position
L: 1 Feb 1996	Mar 1996	124°E
mid-Mar 1996	Jun 1996	113°E
late Aug 1996	May 1999	150.5°E
		? moving east

GTO: 240 x 89462 km x 21.9°  Launch cost: $90 million. Contract for both Hughes Palapa C: $128 million

After testing faulty batteries for Ku-band transponders were discovered. This could lead to the transponders not being marketed. Each transponder is worth $799,000 in revenue a year. The satellite entered service on 23 March 1996.

6 of the 34 transponders are owned by PT Pasifik Satelit Nusantara, the remaining by PT Satelindo

The satellite experienced a failure on 1 Dec 1998 of electrical nature which caused the satellite to loose ability to recharge batteries. This mean eclipse backup loss.

Technical data

Specifications

C-band

Ku-band

C-band transponder frequency chart

Ku-band transponder frequency chart

EIRP maps

C-band: Asean beam (C1)

C-band: Asean & New Zealand beam (C1')

C-band: Asia beam (C2)

Ku-band (K1+K2)


Palapa C1's Asean & New Zealand beam (C1') EIRP


Palapa C1's Asean beam (C1) EIRP


Palapa C1's Asia beam (C2) EIRP


Palapa C1's Ku band beams (K1+K2) EIRP


 Palapa C2

General

Designation	23864 / 96030A
Launch date	16 May 1996
Country of origin	Indonesia
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V86

Launch was insured for over $200 million

6 transponders are owned by PT Pasifik Satelit Nusantara

Location

Begin	End	Position
L: 16 May 1996	Jun 1996	124°E
Jul 1996		113°E
Technical data

Specifications

C-band

Ku-band

C-band transponder frequency chart

Ku-band transponder frequency chart

EIRP maps

C-band: Asean beam (C1)

C-band: Asean & New Zealand beam (C1')

C-band: Asia beam (C2)

Ku-band (K1+K2)


 Palapa C3

to be launched (this was an option on the 2 Cs contract)

118°E


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 Palapa D1

Also called Telkom 1

General

Designation	25880 / 99042A
Launch date	12 Aug 1999
Country of origin	Indonesia
Mission	Telecommunications
Geostationary orbit	108°E
Launch vehicle	Ariane V118

contract worth $192 million including launch cost $90 million, $15.5 million for insurance, $1.6 million for consultancy (Telesat Canada).

Should replace Palapa B2R

The launch had to be delayed because of unnamed problems with the satellite sub-components. Right after launch problem with the solar panels were rumored.

Technical data

Specifications

Prime contractor	Lockheed Martin
Platform	A2100
Mass at launch	2655 kg
Mass in orbit	1700 kg
Dimension	4.1 x 22.5 m
Solar array
Stabilization	3-axis
DC power	EOL: 4024 W
Design lifetime	15 years
C-band

Main transponders	24 + 12
Backup transponders
Power
Bandwidth	36 MHz
Coverage	Indonesia
EIRP
Polarization	linear H/V
C-band standard frequency plan (GHz)

Horizontal Uplink	Horizontal Downlink	Channel	Vertical Downlink	Vertical Uplink
	3.720	1		5.945
5.965		13	3.740
	3.760	2		5.985
6.005		14	3.780
	3.800	3		6.025
6.045		15	3.820
	3.840	4		6.065
6.085		16	3.860
	3.880	5		6.105
6.125		17	3.900
	3.920	6		6.145
6.165		18	3.940
	3.960	7		6.185
6.205		19	3.980
	4.000	8		6.225
6.245		20	4.020
	4.040	9		6.265
6.285		21	4.060
	4.080	10		6.305
6.325		22	4.100
	4.120	11		6.345
6.365		23	4.140
	4.160	12		6.385
6.405		24	4.180
C-band extended frequency plan (GHz)

Horizontal Downlink	Channel	Vertical Downlink
3.420	25
	31	3.440
3.460	26
	32	3.480
3.500	27
	33	3.520
3.540	28
	34	3.560
3.580	29
	35	3.600
3.620	30
	36	3.640


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 Program: Panamsat

American telecommunication program operated by Panamsat Corporation, a merger between Panamsat (Alpha Lyracom) and HCI (merger in April 1997).


Program: Panamsat

Panamsat 1

Panamsat 1R

Panamsat 2

Panamsat 3

Panamsat 3R

Panamsat 4

Panamsat 5

Panamsat 6

Panamsat 6B

Panamsat 7

Panamsat 8

Panamsat 10 & 11

Panamsat 21


 Panamsat 1

Also called PAS 1

General

Designation	19217 / 88051C
Launch date	15 Jun 1988
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	45°W
Launch vehicle	Ariane V23
Technical data

EIRP coverage (dBW)

C-band

Ku-band to Europe

Ku-band to US

G/T coverage (dB/K)

C-band, Central America

C-band, South America

Ku-band, Europe

Ku-band, US

Specifications

Prime contractor	GE Astro Space
Platform
Mass at launch	1220 kg
Mass in orbit	708 kg
Dimension	1.63 x 1.32 x 1.9 m
Stabilization	3-axis
DC power	BOL: 1400 W
Design lifetime	11 years

Panamsat 1 is in fact ASC 3, a backup satellite of the ASC program.

C-band

Main transponders	12+6
Backup transponders	2+1
Power	(12+2) transponders of 36 MHz : 8.5 W (SSPA) (6+1) transponders of 72 MHz: 16.2 W (TWTA)
Bandwidth	12 transponders of 36 MHz 6 transponders 72 MHz
Coverage and EIRP	to North America (7, 9, 11, 16 & 18): ? to Central America (8, 10, 12 & 13): 40 dBW to Latin America (1, 3, 5 & 15): 37 dBW to South America (2, 4, 6 & 14): 38 dBW
Polarization	to Latin and South America: linear V to Central and North America: linear H
Transponder frequency chart (GHz)

Horizontal Uplink	Horizontal Downlink	Transponder	Channel	Vertical Downlink	Vertical Uplink
5.945		1	1	3.720
	3.740	7	2		5.965
5.985		2	3	3.760
	3.780	8	4		6.005
6.025		3	5	3.800
	3.820	9	6		6.045
6.065		4	7	3.840
	3.860	10	8		6.085
6.105		5	9	3.880
	3.900	11	10		6.125
6.145		6	11	3.920
	3.940	12	12		6.165
6.185		13A	13	3.960
	3.980	16A	14		6.205
6.225		13B	15	4.000
	4.020	16B	16		6.245
6.265		14A	17	4.040
	4.060	17A	18		6.285
6.305		14B	19	4.080
	4.100	17B	20		6.325
6.345		16A	21	4.120
	4.140	18A	22		6.365
6.385		16B	23	4.160
	4.180	18B	24		6.405
Ku-band (11.5-11.75 GHz)

Main transponders	6
Backup transponders	1
Power	16.2 W (TWTA)
Bandwidth	72 MHz
Coverage and EIRP max	Europe (19, 20 & 21): 47 dBW North America (22, 23 & 24): 45 dBW
Polarization	linear H
Transponder frequency chart (GHz)

Horizontal Downlink	Transponder	Vertical Uplink
11.500	19	14.040
11.580	20	14.120
11.660	21	14.200
11.790	22	14.280
11.820	23	14.360
11.900	24	14.440


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Panamsat 1's C-band EIRP coverage


Panamsat 1's Ku-band Europe EIRP coverage


Panamsat 1's Ku-band US EIRP coverage


Panamsat 1's C-band Central America G/T coverage


Panamsat 1's C-band South America G/T coverage


Panamsat 1's Ku-band Europe G/T coverage


Panamsat 1's Ku-band Europe G/T coverage


 Panamsat 1R

Also called PAS 1R

General

Designation
Launch date	initially planned in 1999 (second quarter)
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	45°W
Launch vehicle	Ariane
Technical data

EIRP coverage (dBW)

C-band America and Africa

C-band global

Ku-band horizontal

Ku-band vertical

Ku-band South America beam 2

G/T coverage (dB/K)

C-band America horizontal

C-band America vertical

C-band Europe/Africa

C-band Global

Ku-band US, Europe, South America horizontal

Ku-band US, Europe, South America vertical

Specifications

Prime contractor	Hughes
Platform	HS-702
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization	3-axis
DC power
Design lifetime	15 years
C-band

Main transponders	36
Backup transponders	9
Power	24 x 55 W (TWTA) 12 x 34 W (SSPA)
Bandwidth	36 MHz
Coverage	America Africa Global
EIRP max	41 dBW (34 dBW for global beam)
G/T max	0 dB/K (-9 dB/K for global beam)
Polarization	linear H/V
Frequencies	uplink: 5.925-6.425 GHz downlink: 3.700-4.200 GHz
C-band Uplink transponder frequency chart 1 (GHz)

Vertical Uplink  (Africa)	Transponder	Horizontal Uplink  (Global)	Downlink beam
5.960	1		Europe/Africa
	2	5.960	America (H or V) or Europe/Africa (H) or Global (V)
6.000	3		Europe/Africa
	4	6.000	America (H or V) or Europe/Africa (H) or Global (V)
6.040	5		Europe/Africa
	6	6.040	America (H or V) or Europe/Africa (H) or Global (V)
6.080	7		Europe/Africa
	8	6.080	America (H or V) or Europe/Africa (H) or Global (V)
6.120	9		Europe/Africa
	10	6.120	America (H or V) or Europe/Africa (H) or Global (V)
6.160	11		Europe/Africa
	12	6.160	America (H or V) or Europe/Africa (H) or Global (V)
6.200	13		Europe/Africa or Europe Ku (2K) or US Ku (2K)
	14	6.200	America (H or V) or Europe/Africa (H) or Global (V)
6.240	15		Europe/Africa or Europe Ku (4K) or US Ku (4K)
	16	6.240	America (H or V) or Europe/Africa (H) or Global (V)
6.280	17		Europe/Africa or Europe Ku (6K) or US Ku (6K)
	18	6.280	America (H or V) or Europe/Africa (H) or Global (V)
6.320	19		Europe/Africa or Europe Ku (8K) or US Ku (8K)
	20	6.320	America (H or V) or Europe/Africa (H) or Global (V)
6.360	21		Europe/Africa or Europe Ku (10K) or US Ku (10K)
	22	6.360	America (H or V) or Europe/Africa (H) or Global (V)
6.400	23		Europe/Africa or Europe Ku (12K) or US Ku (12K)
	24	6.400	America (H or V) or Europe/Africa (H) or Global (V)
C-band Uplink transponder frequency chart 2 (GHz)

Vertical Uplink  (America)	Transponder	Horizontal Uplink  (America)	Downlink beam
5.960	1		America (H or V) or Europe/Africa (H) or Global (V)
	2	5.960	America (H or V) or Global (V)
6.000	3		America (H or V) or Europe/Africa (H) or Global (V)
	4	6.000	America (H or V) or Global (V)
6.040	5		America (H or V) or Europe/Africa (H) or Global (V)
	6	6.040	America (H or V) or Global (V)
6.080	7		America (H or V) or Europe/Africa (H) or Global (V)
	8	6.080	America (H or V) or Global (V)
6.120	9		America (H or V) or Europe/Africa (H) or Global (V)
	10	6.120	America (H or V) or Global (V)
6.160	11		America (H or V) or Europe/Africa (H) or Global (V)
	12	6.160	America (H or V) or Global (V)
6.200	13		America (H or V) or Europe/Africa (H) or Global (V) or Europe Ku (2K) or US Ku (2K)
	14	6.200	America (H or V) or Global (V)
6.240	15		America (H or V) or Europe/Africa (H) or Global (V) or Europe Ku (4K) or US Ku (4K)
	16	6.240	America (H or V) or Global (V)
6.280	17		America (H or V) or Europe/Africa (H) or Global (V) or Europe Ku (6K) or US Ku (6K)
	18	6.280	America (H or V) or Global (V)
6.320	19		America (H or V) or Europe/Africa (H) or Global (V) or Europe Ku (8K) or US Ku (8K)
	20	6.320	America (H or V) or Global (V)
6.360	21		America (H or V) or Europe/Africa (H) or Global (V) or Europe Ku (10K) or US Ku (10K)
	22	6.360	America (H or V) or Global (V)
6.400	23		America (H or V) or Europe/Africa (H) or Global (V) or Europe Ku (12K) or US Ku (12K)
	24	6.400	America (H or V) or Global (V)
C-band Downlink transponder frequency chart 1 (GHz)

Vertical Downlink	Transponder	Horizontal Downlink	Downlink Beam
	1	3.735	America (H)
3.735	2		America (V) or Global (V)
	3	3.775	America (H)
3.775	4		America (V) or Global (V)
	5	3.815	America (H)
3.815	6		America (V) or Global (V)
	7	3.855	America (H)
3.855	8		America (V) or Global (V)
	9	3.895	America (H)
3.895	10		America (V) or Global (V)
	11	3.935	America (H)
3.935	12		America (V) or Global (V)
	13	3.975	America (H)
3.975	14		America (V) or Global (V)
	15	4.015	America (H)
4.015	16		America (V) or Global (V)
	17	4.055	America (H)
4.055	18		America (V) or Global (V)
	19	4.095	America (H)
4.095	20		America (V) or Global (V)
	21	4.135	America (H)
4.135	22		America (V) or Global (V)
	23	4.175	America (H)
4.175	24		America (V) or Global (V)
C-band Downlink transponder frequency chart 2 (GHz)

Transponder	Horizontal Downlink	Downlink Beam
1	3.735	Europe/Africa (H)
3	3.775	Europe/Africa (H)
5	3.815	Europe/Africa (H)
7	3.855	Europe/Africa (H)
9	3.895	Europe/Africa (H)
11	3.935	Europe/Africa (H)
13	3.975	Europe/Africa (H)
15	4.015	Europe/Africa (H)
17	4.055	Europe/Africa (H)
19	4.095	Europe/Africa (H)
21	4.135	Europe/Africa (H)
23	4.175	Europe/Africa (H)
Ku-band

Main transponders	36
Backup transponders	10
Power	12 x 140 W (TWTA) (transp 25K to 36K) 24 x 125 W (TWTA)
Bandwidth	36 MHz
Coverage	US/Mexico Europe/North Africa South America 1 South America 2
EIRP max	51 dBW
G/T max	4 dB/K
Polarization	linear H/V
Frequencies	uplink: 13.750-14.500 GHz downlink: 10.950-11.200, 11.450-11.950 GHz

Beacon frequency: 11.699 GHz LHCP & RHCP

Ku-band Uplink transponder frequency chart 1 (GHz)

Vertical Uplink  (US/Mexico or South America)	Transponder	Horizontal Uplink  (South America)	Downlink beam
13.770	1		US
	2	13.770	Europe or US
13.810	3		US
	4	13.810	Europe or US
13.850	5		US
	6	13.850	Europe or US
13.890	7		US
	8	13.890	Europe or US
13.930	9		US
	10	13.930	Europe or US
13.970	11		US
	12	13.970	Europe or US
Ku-band Uplink transponder frequency chart 2 (GHz)

Vertical Uplink  (US/Mexico or Europe or combined)	Transponder	Horizontal Uplink  (South America or Europe)	Downlink beam
14.020	13		Europe or US
	14	14.020	South America 2 or Europe
14.060	15		Europe or US
	16	14.060	South America 2 or Europe
14.100	17		Europe or US
	18	14.100	South America 2 or Europe
14.140	19		Europe or US
	20	14.140	South America 2 or Europe
14.180	21		Europe or US
	22	14.180	South America 2 or Europe
14.220	23		Europe or US
	24	14.220	South America 2 or Europe
Ku-band Uplink transponder frequency chart 3 (GHz)

Vertical Uplink  (US/Mexico or South America Europe)	Transponder	Horizontal Uplink  (US/Mexico or South America Europe)	Downlink beam
14.270	25		South America (H)
	26	14.270	South America 1 (V)
14.310	27		South America (H)
	28	14.310	South America 1 (V)
14.350	29		South America (H)
	30	14.350	South America 1 (V)
14.390	31		South America (H)
	32	14.390	South America 1 (V)
14.430	33		South America (H)
	34	14.430	South America 1 (V)
14.470	35		South America (H)
	36	14.470	South America 1 (V)
Ku-band Downlink transponder frequency chart (GHz)

Vertical	Transponder	Horizontal	Downlink beam
	1	10.970	US/Mexico
10.970	2		Europe/North Africa or US/Mexico
	3	11.010	US/Mexico
11.010	4		Europe/North Africa or US/Mexico
	5	11.050	US/Mexico
11.050	6		Europe/North Africa or US/Mexico
	7	11.090	US/Mexico
11.090	8		Europe/North Africa or US/Mexico
	9	11.130	US/Mexico
11.130	10		Europe/North Africa or US/Mexico
	11	11.170	US/Mexico
11.170	12		Europe/North Africa or US/Mexico
	13	11.470	Europe/North Africa or US/Mexico
11.470	14		Europe/North Africa or South America V2
	15	11.510	Europe/North Africa or US/Mexico
11.510	16		Europe/North Africa or South America V2
	17	11.550	Europe/North Africa or US/Mexico
11.550	18		Europe/North Africa or South America V2
	19	11.590	Europe/North Africa or US/Mexico
11.590	20		Europe/North Africa or South America V2
	21	11.630	Europe/North Africa or US/Mexico
11.630	22		Europe/North Africa or South America V2
	23	11.670	Europe/North Africa or US/Mexico
11.670	24		Europe/North Africa or South America V2
	25	11.720	South America
11.720	26		South America V1
	27	11.760	South America
11.760	28		South America V1
	29	11.800	South America
11.800	30		South America V1
	31	11.840	South America
11.840	32		South America V1
	33	11.880	South America
11.880	34		South America V1
	35	11.920	South America
11.920	36		South America V1


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Panamsat 1R's C-band America & Africa EIRP coverage


Panamsat 1R's C-band global EIRP coverage


Panamsat 1R's Ku-band horizontal EIRP coverage


Panamsat 1R's Ku-band vertical EIRP coverage


Panamsat 1R's Ku-band South America beam 2 EIRP coverage


Panamsat 1R's C-band America horizontal G/T coverage


Panamsat 1R's C-band America vertical G/T coverage


Panamsat 1R's C-band Africa vertical G/T coverage


Panamsat 1R's C-band global G/T coverage


Panamsat 1R's Ku-band horizontal G/T coverage


Panamsat 1R's Ku-band vertical G/T coverage


 Panamsat 2

Also called PAS 2

General

Designation	23175 / 94040A
Launch date	8 Jul 1994
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	169°E
Launch vehicle	Ariane V65
Technical data

EIRP coverage (dBW)

C-band, Pacific Rim

C-band, Oceania

Ku-band

G/T coverage (dB/K)

C-band horizontal

C-band vertical

Ku-band horizontal

Ku-band vertical

Specifications

Prime contractor	Hughes
Platform	HS-601
Mass at launch	2920 kg
Mass in orbit
Dimension
Stabilization	3-axis
DC power	5400 W
Design lifetime	15 years
Beacons	4.1985 & 4.1995 GHz (0 dBW, H) 12.5 GHz (5 dBW, RHCP + LHCP)
C-band

Main transponders	16
Backup transponders	4
Power	34 W
Bandwidth	12 transponder of 54 MHz 4 transponder of 64 MHz
Coverage and EIRP max	Oceania and Pacific Rim beams (see footprint maps)
Polarization	linear H/V
Transponder frequency chart (GHz)

Horizontal Downlink	Transponder	Vertical Downlink	Bandwidth (MHz)	Beam
	1	3.720	54	Pacific
3.720	2		54	Pacific
	3	3.790	54	Pacific
3.790	4		54	Pacific
	5	3.850	54	Pacific
3.850	6		54	Pacific
	7	3.915	64	Pacific / Oceania
3.915	8		64	Pacific
	9	3.980	54	Pacific
3.980	10		54	Pacific
	11	4.040	54	Pacific / Oceania
4.040	12		54	Pacific
	13	4.100	54	Pacific
4.100	14		54	Pacific
	15	4.165	64	Pacific / Oceania
4.165	16		64	Pacific
Ku-band

Main transponders	16
Backup transponders	4
Power	63 W
Bandwidth	12 transponder of 54 MHz 4 transponder of 64 MHz
Coverage and EIRP	South Korean beam: 50 dBW and rest of Asia: 42 dBW Chinese beam: 50 dBW Australian beam: 46 dBW
Polarization	linear H/V
Frequencies	Uplink: 14.000 - 14.500 GHz  Downlink: 12.250 - 12.750 GHz
Transponder frequency chart (GHz)

Vertical Downlink	Transponder	Horizontal Downlink	Bandwidth (MHz)	Beam
12.281	1		54	China 1
	2	12.281	54	Australia
12.341	3		54	China 2
	4	12.341	54	NE Asia
12.401	5		54	China 1
	6	12.401	54	Australia
12.466	7		64	China 2 / Australia
	8	12.466	64	NE Asia
12.531	9		54	China 1
	10	12.531	54	Australia
12.591	11		54	China 2 / Australia
	12	12.591	54	NE Asia
12.651	13		54	China 1
	14	12.651	54	Australia
12.716	15		64	China 2 / Australia
	16	12.716	64	NE Asia


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Panamsat 2's C-band EIRP: Pacific Rim


Panamsat 2's C-band EIRP: Oceania


Panamsat 2's Ku-band EIRP


Panamsat 2's C-band horizontal G/T coverage


Panamsat 2's C-band vertical G/T coverage


Panamsat 2's Ku-band horizontal G/T coverage


Panamsat 2's Ku-band vertical G/T coverage


 Panamsat 3

Also called PAS 3

General

Launch date	1 Dec 1994
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	n/a
Launch vehicle	Ariane V70

Cost: $150 million

End of life

Cause	Launcher failure
Decay	1 Dec 1994
Technical data

Specifications

Prime contractor	Hughes
Platform	HS-601
Mass at launch	2985 kg
Mass in orbit
Dimension	2.84 x 3.53 x 3.6 m
Stabilization	3-axis
DC power	BOL: 5400 W EOL: 4300 W
Design lifetime	15 years
C-band

Main transponders	16
Backup transponders	4
Power
Bandwidth
Coverage and EIRP max	America: 36 dBW Europe and Africa
Polarization	linear H/V
Ku-band

Main transponders	16
Backup transponders	4
Power
Bandwidth	54 MHz
Coverage and EIRP max	Europe: 46.2 dBW North America South America
Polarization	linear H/V


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 Panamsat 3R

Also called PAS 3R

General

Designation	23764 / 96002A
Launch date	12 Jan 1996
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	43°W
Launch vehicle	Ariane V82
Technical data

EIRP coverage (dBW)

C-band beam 1

C-band beam 2

Ku-band

G/T coverage (dB/K)

C-band america horizontal

C-band america vertical

C-band africa

Ku-band horizontal

Ku-band vertical

Specifications

Prime contractor	Hughes
Platform	HS-601
Mass at launch	2918 kg
Mass in orbit
Dimension	2.84 x 3.53 x 3.6 m
Solar array	26.5 m span
Stabilization	3-axis
DC power	BOL: 5400 W EOL: 4300 W
Design lifetime	15 years
Beacons	4.1985 & 4.1990 GHz (0 dBW) 11.7 GHz (5 dBW, RHCP + LHCP)

It uses Hughes' advanced shaped-reflector technology, which concentrates the satellite's beam over targeted land areas while avoiding uninhabited oceans. Hughes' patented, highly efficient design eliminates the need for multiple feedhorn configurations.

C-band

Main transponders	16
Backup transponders	4
Power	34 W (SSPA)
Bandwidth	12 transponders of 54 MHz 4 transponders of 64 MHz
Coverage and EIRP max	Pan America beam 1 Pan America beam 2 Africa
Polarization	linear H/V
Frequencies	Uplink: 5.925-6.425 GHz Downlink: 3.700-4.200 GHz
Downlink transponder frequency chart (GHz)

Horizontal Downlink	Transponder	Vertical Downlink	Bandwidth (MHz)	Beam
	1	3.730	54	PAN AM V2
3.730	2		54	PAN AM H2
	3	3.790	54	PAN AM V1
3.790	4		54	PAN AM H1
	5	3.850	54	PAN AM V2
3.850	6		54	PAN AM H2
	7	3.915	64	PAN AM V1 or Africa
3.915	8		64	PAN AM H1
	9	3.980	54	PAN AM V2
3.980	10		54	PAN AM H2
	11	4.040	54	PAN AM V1 or Africa
4.040	12		54	PAN AM H1
	13	4.100	54	PAN AM V2
4.100	14		54	PAN AM H2
	15	4.165	64	PAN AM V1 or Africa
4.165	16		64	PAN AM H1
Uplink transponder frequency chart (GHz)

Vertical Uplink	Transponder	Horizontal Uplink	Bandwidth (MHz)	Beam
	1	5.955	54	PAN America
5.955	2		54	PAN America
	3	6.015	54	PAN America or Africa or North America
6.015	4		54	PAN America
	5	6.075	54	PAN America
6.075	6		54	PAN America
	7	6.140	64	PAN America or Africa or North America
6.140	8		64	PAN America
	9	6.205	54	PAN America
6.205	10		54	PAN America
	11	6.265	54	PAN America or Africa or North America
6.265	12		54	PAN America
	13	6.325	54	PAN America
6.375	14		54	PAN America
	15	6.390	64	PAN America or Africa or North America
6.390	16		64	PAN America
Ku-band

Main transponders	16
Backup transponders	4
Power	63 W (TWTA)
Bandwidth	12 transponders of 54 MHz 4 transponders of 64 MHz
Coverage and EIRP max	Europe: 50 dBW North-America: 50 dBW North South-America: 50 dBW South South-America: 52 dBW Brazil: 50 dBW
Polarization	Linear H/V
Frequencies	Uplink: 14.00-14.500 GHz Downlink: 11.700-12.200 GHz and 12.500-12.750 GHz
Downlink transponder frequency chart (GHz)

Vertical Downlink	Transponder	Horizontal Downlink	Bandwidth (MHz)	Beam
	1	11.729	54	North South-America or Europe
11.729	2		54	North-America or South South-America
	4	11.789	54	North-America (but no 4B)
11.789	4B		54	Brazil (but no 4)
	5	11.849	54	North South-America or Europe
11.849	6		54	North-America or South South-America
	8	11.914	64	North-America (but no 8B)
11.914	8B		64	Brazil (but no 8)
	9	11.979	54	North South-America or Europe
11.979	10		54	North-America or South South-America (H)
	12	12.039	54	North-America (but no 12B)
12.039	12B		54	Brazil (but no 12)
	13	12.099	54	North South-America or Europe
12.099	14		54	North-America or South South-America (H)
	16	12.164	64	North-America (but no 16B)
12.164	16B		64	Brazil (but no 16)
	1E	12.531	54	Europe or North South-America
12.531	9E		54	Europe or North South-America
	3E	12.591	54	Europe
12.591	11E		54	Europe
	5E	12.651	54	Europe or North South-America
12.651	13E		54	Europe or North South-America
	7E	12.716	64	Europe
12.716	15E		64	Europe
Uplink transponder frequency chart (GHz)

Vertical Uplink	Transponder	Horizontal Uplink	Bandwidth (MHz)	Beam
14.029	1		54	Europe or North-America
	1S	14.029	54	South-America
	2	14.029	54	Europe or North-America
14.089	3		54	Europe or North-America
	4	14.089	54	Europe or North-America
	4S	14.089	54	South-America
14.149	5		54	Europe or North-America
	1S	14.149	54	South-America
	6	14.149	54	Europe or North-America
14.214	7		64	Europe or North-America
	8	14.214	64	Europe or North-America
	8S	14.214	64	South-America
14.279	9		54	Europe or North-America
	9S	14.279	54	South-America
	10	14.279	54	Europe or North-America
14.339	11		54	Europe or North-America
	12	14.339	54	Europe or North-America
	12S	14.339	54	South-America
14.399	13		54	Europe or North-America
	13S	14.399	54	South-America
	14	14.399	54	Europe or North-America
14.464	15		64	Europe or North-America
	16	14.464	64	Europe or North-America
	16S	14.464	64	South-America


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Panamsat 3R's C-band beam 1 EIRP


Panamsat 3R's C-band beam 2 EIRP


Panamsat 3R's Ku-band EIRP

NAv stands for North America vertical polarization, NAh stands for North America horizontal polarization


Panamsat 3R's C-band America horizontal G/T coverage


Panamsat 3R's C-band America vertical G/T coverage


Panamsat 3R's C-band Africa G/T coverage


Panamsat 3R's Ku-band horizontal G/T coverage


Panamsat 3R's Ku-band vertical G/T coverage


 Panamsat 4

Also called PAS 4

General

Designation	23636 / 95040A
Launch date	3 Aug 1995
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	68.5°E
Launch vehicle	Ariane V76

The primary control processor failed.

Technical data

EIRP coverage (dBW)

C-band: Africa & Asia

C-band: Asia/Middle East horizontal

C-band: Asia/Middle East vertical

Ku-band

G/T coverage (dB/K)

C-band: Africa/Middle East vertical

C-band: Asia/Middle East horizontal

C-band: Asia vertical

Ku-band: horizontal

Ku-band: vertical

Specifications

Prime contractor	Hughes
Platform	HS-601
Mass at launch	3043 kg
Dry mass	1671 kg
Mass in orbit
Dimension	2.84 x 3.53 x 3.6 m
Solar array	26.2 m span
Stabilization	3-axis
DC power	BOL: 5400 W EOL: 4300 W
Design lifetime	15 years
Beacons	4.1990 & 4.1995 GHz (0 dBW) 12.5 GHz (5 dBW, RHCP + LHCP)
C-band

Main transponders	16
Backup transponders	4
Power	30 W (SSPA)
Bandwidth	12 transponders of 54 MHz 4 transponders of 64 MHz
Coverage and  EIRP max	Africa South Asia/Middle East: Horizontal or Vertical Asia
Polarization	Linear H/V
Frequencies	Uplink: 5.925-6.425 GHz Downlink: 3.700-4.200 GHz
Downlink transponder frequency chart (GHz)

Vertical Downlink	Transponder	Horizontal Downlink	Bandwidth (MHz)	Beam
	1	3.730	54	South Asia/Middle East
3.730	2		54	Africa or South Asia/Middle East
	3	3.790	54	South Asia/Middle East
3.790	4		54	Asia
	5	3.850	54	South Asia/Middle East
3.850	6		54	Africa or South Asia/Middle East
	7	3.915	64	South Asia/Middle East
3.915	8		64	Asia
	9	3.980	54	South Asia/Middle East
3.980	10		54	Africa
	11	4.040	54	South Asia/Middle East
4.040	12		54	Africa or South Asia/Middle East
	13	4.100	54	South Asia/Middle East
4.100	14		54	Africa
	15	4.165	64	South Asia/Middle East
4.165	16		64	Africa or South Asia/Middle East
Uplink transponder frequency chart (GHz)

Horizontal Uplink	Transponder	Vertical Uplink	Bandwidth (MHz)	Beam
	1	5.955	54	South Asia/Middle East
5.955	2		54	India/Asia/Australia or Africa/Europe
	3	6.015	54	South Asia/Middle East
6.015	4		54	India/Asia/Australia or Africa/Europe
	5	6.075	54	South Asia/Middle East
6.075	6		54	India/Asia/Australia or Africa/Europe
	7	6.140	64	South Asia/Middle East
6.140	8		64	India/Asia/Australia or Africa/Europe
	9	6.205	54	South Asia/Middle East
6.205	10		54	India/Asia/Australia
	11	6.265	54	South Asia/Middle East
6.265	12		54	India/Asia/Australia or Africa/Europe
	13	6.325	54	South Asia/Middle East
6.375	14		54	India/Asia/Australia or Africa/Europe
	15	6.390	64	South Asia/Middle East
6.390	16		64	India/Asia/Australia or Africa/Europe
Ku-band

Main transponders	24
Backup transponders	6
Power	60 W (TWTA)
Bandwidth	16 transponders of 27 MHz 6 transponders of 54 MHz 2 transponders of 64 MHz
Coverage and EIRP max	Europe/Russia North East Asia Middle East India South-Africa
Polarization	Linear H/V
Frequencies	Uplink: 14.00-14.500 GHz Downlink: 11.450-11.700 GHz and 12.250-12.750 GHz
Downlink transponder frequency chart (GHz)

Vertical Downlink	Transponder	Horizontal Downlink	Bandwidth (MHz)	Beam
	17	11.464	27	Middle East (if not Europe)
11.464	17		27	Europe (if not ME)
	19	11.524	27	Middle East (if not Europe)
11.524	19		27	Europe (if not ME)
	21	11.584	27	Middle East (if not Europe)
11.584	21		27	Europe (if not ME)
	23	11.649	27	Middle East (if not Europe)
11.649	23		27	Europe (if not ME)
12.266	9		27	India
	10	12.296	27	India
12.326	11		27	India
	12	12.356	27	India
12.386	13		27	India
	14	12.416	27	India
12.451	15		27	India
		12.481	27	India
	1	12.531	54	South-Africa
12.531	5		54	South-Africa or Europe
	18	12.546	27	India or Asia
	2	12.591	54	South-Africa
12.591	6		54	South-Africa or Europe
	20	12.606	27	India or Asia
	3	12.651	54	South-Africa
12.651	7		54	South-Africa or Europe
	22	12.666	27	India or Asia
	4	12.716	64	South-Africa
12.716	8		64	South-Africa or Europe
	24	12.731	27	India or Asia
Uplink transponder frequency chart (GHz)

Vertical Uplink	Transponder	Horizontal Uplink	Bandwidth (MHz)	Beam
14.029	1		54	Europe/South-Africa/Asia
	9	14.014	27	Europe/Middle East/India/Asia
	10	14.044	27	Europe/Middle East/India/Asia
14.089	2		54	Europe/South-Africa/Asia
	11	14.074	27	Europe/Middle East/India/Asia
	12	14.104	24	Europe/Middle East/India/Asia
14.149	3		54	Europe/South-Africa/Asia
	13	14.134	27	Europe/Middle East/India/Asia
	14	14.164	27	Europe/Middle East/India/Asia
14.214	4		64	Europe/South-Africa/Asia
	15	14.199	27	Europe/Middle East/India/Asia
	16	14.229	27	Europe/Middle East/India/Asia
14.279	5		54	Europe/South-Africa/Asia
	17	14.264	27	Europe/Middle East/India/Asia
	18	14.294	27	Europe/Middle East/India/Asia
14.339	6		54	Europe/South-Africa/Asia
	19	14.324	27	Europe/Middle East/India/Asia
	20	14.354	27	Europe/Middle East/India/Asia
14.399	7		54	Europe/South-Africa/Asia
	21	14.384	27	Europe/Middle East/India/Asia
	22	14.414	27	Europe/Middle East/India/Asia
14.464	8		64	Europe/South-Africa/Asia
	23	14.449	27	Europe/Middle East/India/Asia
	24	14.479	27	Europe/Middle East/India/Asia


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Panamsat 4's C-band Asia & Africa beam EIRP


Panamsat 4's C-band Asia & Middle East horizontal EIRP


Panamsat 4's C-band Asia & Middle East vertical EIRP


Panamsat 4's Ku-band EIRP


Panamsat 4's C-band Africa vertical G/T coverage


Panamsat 4's C-band Asia/Middle East horizontal G/T coverage


Panamsat 4's C-band Asia vertical G/T coverage


Panamsat 4's Ku-band horizontal G/T coverage


Panamsat 4's Ku-band vertical G/T coverage


 Panamsat 5

Also called PAS 5

General

Designation	24916 / 97046A
Launch date	28 Aug 1997
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	58°W
Launch vehicle	Proton #246

One of the antennas was damaged on launch site in mid August 1997. The satellite has power problems during eclipses which causes the need to shutdown part of the transponders during such times.

Therefore a claim was filled for insurances as a constructive total loss of the satellite because the company has ceased using all of the Ku-band capacity of the satellite on a full-time basis, and this capacity represents more than 50% of the satellite's communications capacity.

Technical data

EIRP coverage (dBW)

C-band

Ku-band, US

Ku-band, Mexico

G/T coverage (dB/K)

C-band horizontal

C-band vertical

Ku-band

Specifications

Prime contractor	Hughes
Platform	HS-601HP
Mass at launch	3720 kg
Dry mass
Mass in orbit	2519 kg
Length	26 m
Width	7 m
Height
Solar array	gallium arsenide
Stabilization	3-axis
DC power	8000 W
Design lifetime	15 years

Has GaAs (gallium arsenide) solar cells, "advanced" batteries. It is the first commercial satellite to launch with the XIPS thrusters that should provide 5 additional lifetime years. Liquid propellant thrusters provide 15 years lifetime. Some problems developped with XIPS and software patches were uploaded.

The battery degradation is said to be owing to "soft" short circuits inside the battery caused by too much electrolyte. PAS-5 is the first HS-601HP model in orbit, and the problem would be corrected in future satellites.

Is the first satellite to use dual-junction solar cells from Spectrolabs.

C-band

Main transponders	24
Backup transponders	4
Power	50 W
Bandwidth	36 MHz
Coverage & EIRP max	1 single beam: Americas: 38 dBW Europe: 31 dBW
Polarization	linear H/V
Frequencies	Uplink: 5.925 - 6.425 GHz Downlink: 3.700 - 4.200 GHz
SFD	-96 dBW/m²
G/T max	-1.8 dB/K
C-band transponder frequency chart (GHz)

Vertical  Uplink	Vertical  Downlink	Transponder	Horizontal  Downlink	Horizontal  Uplink
5.945		1	3.720
	3.720	2		5.945
5.985		3	3.760
	3.760	4		5.985
6.025		5	3.800
	3.800	6		6.025
6.065		7	3.840
	3.840	8		6.065
6.105		9	3.880
	3.880	10		6.105
6.145		11	3.920
	3.920	12		6.145
6.185		13	3.960
	3.960	14		6.185
6.225		15	4.000
	4.000	16		6.225
6.265		17	4.040
	4.040	18		6.265
6.305		19	4.080
	4.080	20		6.305
6.345		21	4.120
	4.120	22		6.345
6.385		23	4.160
	4.160	24		6.385
Ku-band

Main transponders	18 + 6
Backup transponders	4
Power	18 at 110 W 6 at 60 W
Bandwidth	36 MHz
Coverage & EIRP max	US: 49 dBW Steerable: n/a Mexico (and US North-East): 49 dBW
Polarization	linear H/V
Frequencies	Uplink: 12.750 - 13.250 GHz Downlink: 10.700 - 11.450 GHz Uplink: 14.000 - 14.250 GHz Downlink: 11.450 - 11.700 GHz (Spot)
SFD	-89 dBW/m²
G/T max	-2.8 dB/K
Beacon	11.454 GHz
Downlink transponder frequency chart (GHz)

Vertical Downlink	Transponder	Horizontal Downlink	Beam
	7	10.727	Mexico
	8	10.768	Mexico
	9	10.809	Mexico
	10	10.850	Mexico
	11	10.891	Mexico
	12	10.932	Mexico
11.219	19		US
	1	11.219	Mexico
11.261	20		US
	2	11.261	Mexico
11.303	21		US
	3	11.303	Mexico
11.345	22		US
	4	11.345	Mexico
11.387	23		US
	5	11.387	Mexico
11.429	24		US
	6	11.429	Mexico
11.476	13		steerable
11.517	14		steerable
11.558	15		steerable
11.599	16		steerable
11.640	17		steerable
11.681	18		steerable
Uplink transponder frequency chart (GHz)

Vertical Uplink	Transponder	Horizontal Uplink	Beam
	1	12.769	US / Latin America / Europe
12.769	19		US / Europe
	2	12.811	US / Latin America / Europe
12.811	20		US / Europe
	3	12.853	US / Latin America / Europe
12.853	21		US / Europe
	4	12.895	US / Latin America / Europe
12.895	22		US / Europe
	5	12.937	US / Latin America / Europe
12.937	23		US / Europe
	6	12.979	US / Latin America / Europe
12.979	24		US / Europe
	7	13.026	US / Latin America / Europe
	8	13.067	US / Latin America / Europe
	9	13.108	US / Latin America / Europe
	10	13.149	US / Latin America / Europe
	11	13.190	US / Latin America / Europe
	12	13.231	US / Latin America / Europe
	13	14.019	US / Latin America / Europe
	14	14.060	US / Latin America / Europe
	15	14.101	US / Latin America / Europe
	16	14.142	US / Latin America / Europe
	17	14.183	US / Latin America / Europe
	18	14.224	US / Latin America / Europe


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Panamsat 5's C-band EIRP coverage


Panamsat 5's Ku-band US beam EIRP coverage


Panamsat 5's Ku-band Mexico beam EIRP coverage


Panamsat 5's C-band horizontal G/T coverage


Panamsat 5's C-band vertical G/T coverage


Panamsat 5's Ku-band G/T coverage


 Panamsat 6

Also called PAS 6

General

Designation	24891 / 97040A
Launch date	8 Aug 1997
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	43°W
Launch vehicle	Ariane V98

Satellite, launch and insurance: $225 million

The satellite is probably out of use. Power problems have been rumored. Those could be linked to solar arrays.

Technical data

EIRP coverage (dBW)

Ku-band, NTSC & Argentina

Ku-band, Brasil

Specifications

Prime contractor	Space Systems/Loral
Platform	FS-1300
Mass at launch	3420 kg
Dry mass	1285 kg
Dimension	3.4 x 2.7 x 3 m
Solar array	27.5 m span (provided by Dasa)
Stabilization	3-axis
DC power	10000 W
Design lifetime	15 years
Ku-band

Main transponders	36
Backup transponders	12
Power	24 x 110 W (TWTA) 12 x 100 W (TWTA)
Bandwidth	36 MHz
Coverage	Argentina beam (Argentina, Chile, Paraguay, Uruguay), 12 transp. Brasil beam, 12 transp. NTSC beam (Columbia, Venezuela, Bolivia, Peru, Ecuador), 12 transp.
EIRP max	50 dBW
Polarization	linear H/V
Frequencies	uplink: 12.75-13.25 & 13.75-14.00 GHz downlink: 10.7-10.95 & 11.2-11.45 GHz
Downlink transponder frequency chart (GHz)

Vertical Downlink	Transponder	Horizontal Downlink	Beam
10.722	1		Brasil
	13	10.722	Brasil
10.762	2		Argentina
	14	10.762	Argentina
10.802	3		Brasil
	15	10.802	Brasil
10.842	4		Argentina
	16	10.842	Argentina
10.882	5		Brasil
	17	10.882	Brasil
10.922	6		Argentina
	18	10.922	Argentina
10.970	25		Brasil
	31	10.970	Brasil
11.010	26		NTSC
	32	11.010	NTSC
11.050	27		Brasil
	33	11.050	Brasil
11.090	28		NTSC
	34	11.090	NTSC
11.130	29		Brasil
	35	11.130	Brasil
11.170	30		NTSC
	36	11.170	NTSC
11.222	7		Argentina or Brasil
	19	11.222	Argentina
11.262	8		NTSC
	20	11.262	NTSC
11.302	9		Argentina or Brasil
	21	11.302	Argentina
11.342	10		NTSC
	22	11.342	NTSC
11.382	11		Argentina
	23	11.382	Argentina
11.422	12		NTSC
	24	11.422	NTSC
Uplink transponder frequency chart (GHz)

Vertical Uplink	Transponder	Horizontal Uplink	Beam
12.772	1
	13	12.772
12.812	2
	14	12.812
12.852	3
	15	12.852
12.892	4
	16	12.892
12.932	5
	17	12.932
12.972	6
	18	12.972
13.022	7
	19	13.022
13.062	8
	20	13.062
13.102	9
	21	13.102
13.142	10
	22	13.142
13.182	11
	23	13.182
13.222	12
	24	13.222
13.774	25
	31	13.774
13.814	26
	32	13.814
13.854	27
	33	13.854
13.894	28
	34	13.894
13.934	29
	35	13.934
13.974	30
	36	13.974


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Panamsat 6's Ku-band NTSC & Argentina beam EIRP


Panamsat 6's Ku-band Brasil beam EIRP


 Panamsat 6B

Also called PAS 6B

General

Designation	25585 / 98075A
Launch date	22 Dec 1998
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	43°W
Launch vehicle	Ariane

Replacement satellite for Panamsat 6. tested at 46°W

Technical data

Specifications

Prime contractor	Hughes
Platform	HS-601HP
Mass at launch	3594 kg
Mass in orbit	2134 kg
Dimension	3.4 x 2.8 x 6 m at launch
Solar array	26.2 m span
Stabilization	3-axis
DC power	BOL: 8600 W
Design lifetime	15 years

has XIPS propulsion and dual-junction gallium arsenide solar cells

Ku-band

Main transponders	32
Backup transponders
Power	105/140 W
Bandwidth	36 MHz
Coverage	16 transponders for Brazil 16 transpoinders for Latin America (Venezuela to Paraguay including Columbia, Equator, Uruguay)
EIRP max
Polarization	linear H/V
Frequencies	uplink: 12.75-13.25 & 13.75-14.00 GHz downlink: 10.7-10.95 & 11.2-11.45 GHz


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 Panamsat 7

Also called PAS 7

General

Designation	25473 / 9852A
Launch date	16 Sep 1998
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	68.5°E
Launch vehicle	Ariane V110

Panamsat 7 will expand Panamsat's (Panamsat 4) Southern Africa satellite capacity and will extend its high-power Ku-band satellite coverage for DTH and other applications into Sub-Saharan Africa.

Technical data

EIRP coverage (dBW)

C-band

Ku-band, India, Europe/Middle East, South Africa

G/T coverage (dB/K)

C-band, horizontal

C-band, vertical

Ku-band

Specifications

Prime contractor	Space Systems/Loral
Platform	FS-1300
Mass at launch	3838 kg
Mass in orbit	2118 kg
Dimension	2.4 x 2.2 x 3.6 m
Solar array
Stabilization	3-axis
DC power	11000 W
Design lifetime	15 years
C-band

Main transponders	14
Backup transponders	4
Power	50 W
Bandwidth	36 MHz
Coverage	1 single beam for Africa, Europe, Asia
EIRP max	36 dBW
G/T max	-3.5 dB/K
Polarization	linear H/V
Frequencies	uplink: 6.425-6.725 GHz downlink: 3.400-3.700 GHz

Beacon: 3.698 GHz, 6 dBW global

C-band transponder frequency chart (GHz)

Vertical  Uplink	Vertical  Downlink	Transponder	Horizontal  Downlink	Horizontal  Uplink
	3.430	1		6.455
6.455		8	3.430
	3.470	2		6.495
6.495		9	3.470
	3.510	3		6.535
6.535		10	3.510
	3.550	4		6.575
6.575		11	3.550
	3.590	5		6.615
6.615		12	3.590
	3.630	6		6.655
6.655		13	3.630
	3.670	7		6.695
6.695		14	3.670
Ku-band

Main transponders	30
Backup transponders	10
Power	100 W
Bandwidth	36 MHz
Coverage	3 beams: Europe/Middle East India South Africa
EIRP max	54 dBW
G/T max	+2 dB/K
Polarization	linear H/V
Frequencies	uplink: 13.75-14.00 & 14.00-14.25 GHz downlink: 10.950-11.200 & 11.450-11.700 GHz
Ku-band transponder frequency chart (GHz)

Vertical  Uplink	Vertical  Downlink	Transponder	Horizontal  Downlink	Horizontal  Uplink	Beam
13.774		A1	10.970		Uplink: see note 1; Downlink: South Africa or Middle East
	10.970	A7		13.774	Uplink: see note 1; Downlink: South Africa or Middle East
13.814		A2	11.010		Uplink: see note 1; Downlink: South Africa or Middle East
	11.010	A8		13.814	Uplink: see note 2; Downlink: South Africa or Middle East
13.854		A3	11.050		Uplink: see note 1; Downlink: South Africa or Middle East
	11.050	A9		13.854	Uplink: see note 1; Downlink: South Africa or Middle East
13.894		A4	11.090		Uplink: see note 1; Downlink: South Africa or Middle East
	11.090	A10		13.894	Uplink: see note 2; Downlink: South Africa or Middle East
13.934		A5	11.130		Uplink: see note 1; Downlink: South Africa or Middle East
	11.130	A11		13.934	Uplink: see note 1; Downlink: South Africa or Middle East
13.974		A6	11.170		Uplink: see note 1; Downlink: South Africa or Middle East
	11.170	A12		13.974	Uplink: see note 2; Downlink: South Africa or Middle East
	11.474	B1		14.024	South Africa
	11.514	B2		14.064	South Africa
	11.554	B3		14.104	South Africa
	11.594	B4		14.144	South Africa
	11.634	B5		14.184	South Africa
	11.674	B6		14.224	South Africa
13.774		C1	10.970		Uplink: see note 3; Downlink: India or China
	10.970	C7		13.774	Uplink: see note 3; Downlink: India or China
13.814		C2	11.010		Uplink: see note 3; Downlink: India or China
	11.010	C8		13.814	Uplink: see note 4; Downlink: India or China
13.854		C3	11.050		Uplink: see note 3; Downlink: India or China
	11.050	C9		13.854	Uplink: see note 3; Downlink: India or China
13.894		C4	11.090		Uplink: see note 3; Downlink: India or China
	11.090	C10		13.894	Uplink: see note 4; Downlink: India or China
13.934		C5	11.130		Uplink: see note 3; Downlink: India or China
	11.130	C11		13.934	Uplink: see note 3; Downlink: India or China
13.974		C6	11.170		Uplink: see note 3; Downlink: India or China
	11.170	C12		13.974	Uplink: see note 4; Downlink: India or China
1: uplink from Europe / Middle East / South Africa

2: uplink from Europe / Middle East / South Africa or from India / China if the "C" transponder with the same number operates with Europe / Middle East / South Africa uplink

3: uplink from India / China

4: uplink from India / China or from Europe / Middle East / South Africa if the "A" transponder with the same number operates with India / China


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Panamsat 7's C-band EIRP coverage


Panamsat 7's Ku-band EIRP coverage


Panamsat 7's C-band horizontal G/T coverage


Panamsat 7's C-band vertical G/T coverage


Panamsat 7's Ku-band G/T coverage


 Panamsat 8

Also called PAS 8

General

Designation	25522 / 98065A
Launch date	4 Nov 1998
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	166°E
Launch vehicle	Proton #260

In October 1998, FCC authorized PanAmSat to operate and launch the satellite. Launch worth $70 million

Two Ku-band antennas have pointing problems. The satellite is not providing its intended footprint coverage. A partial loss was claimed from insurances because of the loss in geographic coverage, connectivity and switchability of certain of the Ku-band transponders.

Technical data

EIRP coverage (dBW)

C-band

Ku-band, Northeast Asia, Australia

Ku-band, Southeast Asia

G/T coverage (dB/K)

C-band

Ku-band

Specifications

Prime contractor	Space Systems/Loral
Platform	FS-1300
Mass at launch	3800 kg
Mass in orbit
Dimension
Solar array
Stabilization	3-axis
DC power	10000 W
Design lifetime	15 years
C-band

Main transponders	24
Backup transponders	8
Power	50 W
Bandwidth	36 MHz
Coverage	Eastern Asia & Pacific Rim
EIRP max	40 dBW
G/T max	0 dB/K
Polarization	linear H/V
Frequencies	uplink: 5.925-6.425 GHz downlink: 3.7-4.2 GHz

Beacon: 3.702 GHz, 6 dBW global

C-band transponder frequency chart (GHz)

Horizontal  Uplink	Horizontal  Downlink	Transponder	Vertical  Downlink	Vertical  Uplink
5.945		1	3.720
	3.740	2		5.965
5.985		3	3.760
	3.780	4		6.005
6.025		5	3.800
	3.820	6		6.045
6.065		7	3.840
	3.860	8		6.085
6.105		9	3.880
	3.900	10		6.125
6.145		11	3.920
	3.940	12		6.165
6.185		13	3.960
	3.980	14		6.205
6.225		15	4.000
	4.020	16		6.245
6.265		17	4.040
	4.060	18		6.285
6.305		19	4.080
	4.100	20		6.325
6.345		21	4.120
	4.140	22		6.365
6.385		23	4.160
	4.180	24		6.405
Ku-band

Main transponders	24
Backup transponders	8
Power	100 W
Bandwidth	36 MHz
Coverage	3 beams (all beams have a weak spot to California): Northeast Asia Southeast Asia (not usable?) Australia
EIRP max	54 dBW
G/T max	-2 dB/K
Polarization	linear H/V
Frequencies	uplink: 14.00-14.50 GHz downlink: 12.250-12.750 GHz
Ku-band transponder frequency chart (GHz)

Vertical  Uplink	Vertical  Downlink	Transponder	Horizontal  Downlink	Horizontal  Uplink	Beam
14.036		13K	12.286		SE Asia or Australia
	12.286	1K		14.036	Northeast Asia
14.076		14K	12.326		SE Asia or Australia
	12.326	2K		14.076	Northeast Asia
14.116		15K	12.366		SE Asia or Australia
	12.366	3K		14.116	Northeast Asia
14.156		16K	12.406		SE Asia or Australia
	12.406	4K		14.156	Northeast Asia
14.196		17K	12.446		SE Asia or Australia
	12.446	5K		14.196	Northeast Asia
14.236		18K	12.486		SE Asia or Australia
	12.486	6K		14.236	Northeast Asia
14.276		19K	12.526		SE Asia or Australia
	12.526	7K		14.276	Northeast Asia
14.316		20K	12.566		SE Asia or Australia
	12.566	8K		14.316	Northeast Asia
14.356		21K	12.606		SE Asia or Australia
	12.606	9K		14.356	Northeast Asia
14.396		22K	12.646		SE Asia or Australia
	12.646	10K		14.396	Northeast Asia
14.436		23K	12.686		SE Asia or Australia
	12.686	11K		14.436	Northeast Asia
14.476		24K	12.726		SE Asia or Australia
	12.726	12K		14.476	Northeast Asia


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Panamsat 8's C-band EIRP coverage


Panamsat 8's Northeast Asia & Australia Ku-band beam EIRP


Panamsat 8's Southeast Asia Ku-band beam EIRP


Panamsat 8's C-band G/T coverage


Panamsat 8's Ku-band G/T coverage


 Panamsat 9

This is not the old PAS 9 renamed Galaxy 3C

General

Designation
Launch date	initially planned in 1Q 2000
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	58°W
Launch vehicle
Launch site

will offer significant expansion capabilities in Latin America and also will serve as the permanent platform for Sky's direct-to-home (DTH) television service in Mexico. Will replace Panamsat 5

Ordered in October 1998

Technical data

Specifications

Prime contractor	Hughes
Platform	HS-601HP
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime

Europe, Latin America, Carribbean coverage. in C- and Ku-band


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Panamsat 10
 Panamsat 10 & 11

Also called PAS 10 & PAS 11

General

Designation
Launch date	initially both planned before May 2002
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	125°W and 58°W
Launch vehicle
Launch site
Technical data

Ka-band

Main transponders	24
Backup transponders
Power	40 & 60 W (TWTA)
Bandwidth	54 MHz
Coverage	multiple steerable spots
EIRP max
Polarization	linear H/V
Frequencies	Uplink: 28.35-28.6 and 29.5-30.0 GHz  Downlink: 19.7-20.2 GHz

Onboard switching for at least half the transponders


 Panamsat 21

Also called PAS 21

General

Designation
Launch date
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	68,5°W co-located with PAS 6
Launch vehicle
Launch site

The satellite will have fourteen 36 MHz C-band and thirty 36 MHz Ku-band transponders.


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 Pansat

Petite Amateur Navy Satellite, also called PO-34

General

Designation	25520 / 98064B
Launch date	29 Oct 1998
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	550 km
Inclination	28.5°
Period	95.6 min
Launch vehicle	STS 95

Small, spread-spectrum communication satellite developed by the Naval Postgraduate School (NPS) as an educational project for officer students.

Through use by the amateur radio community PANSAT will supply a means to demonstrate spread-spectrum communications. In addition, PANSAT provides many potential applications for low-cost communications. The low probability-of-intercept would be an important feature for the military in downed-pilot-rescues. The pilot could obtain his/her location through a GPS system and uplink the information to the orbiting satellite at low risk. Examples of civilian uses include emergency rescue and communication to remote areas.

External resources

http://www.sp.nps.navy.mil/pansat/pansat.html

Technical data

Specifications

Prime contractor
Platform
Mass at launch	75 kg
Mass in orbit
Dimension
Solar array
Stabilization	tumbling spacecraft
DC power
Design lifetime	2 years

Upload: 435.250 - 437.750 MHz

Download: 435.250 - 437.750 MHz

The spacecraft will supply direct-sequence, spread-spectrum modulation with an operating center frequency of 436.5 MHz, a bit rate of 9600 bits per second and 4 MB of message storage.


 Program: Parus

Means sail

Russian military navigation program. The constellation is made of 1 satellite per plane on 6 planes spaced by 30°. The first Parus spacecraft was Cosmos 0700, launched in 1974. The system was operational in November 1976. The Tsikada system is a civilian counterpart.

Occupation of the planes

Plane 1	Plane 2	Plane 3	Plane 4	Plane 5	Plane 6
150.03 MHz 400.08 MHz	149.91 MHz 399.76 MHz	149.94 MHz 399.84 MHz	149.97 MHz 399.92 MHz	150.03 MHz 400.08 MHz	149.94 MHz 399.84 MHz
Cosmos 0778	Cosmos 0789	Cosmos 0726	Cosmos 0864	Cosmos 0700	Cosmos 0755
Cosmos 0971	Cosmos 0951	Cosmos 0887	Cosmos 0996	Cosmos 0894	Cosmos 0928
Cosmos 1141	Cosmos 1089	Cosmos 0991	Cosmos 1091	Cosmos 0985	Cosmos 1011
Cosmos 1275	Cosmos 1225	Cosmos 1072	Cosmos 1153	Cosmos 1104	Cosmos 1150
Cosmos 1308	Cosmos 1386	Cosmos 1181	Cosmos 1349	Cosmos 1244	Cosmos 1333
Cosmos 1417	Cosmos 1531	Cosmos 1295	Cosmos 1459	Cosmos 1344	Cosmos 1428
Cosmos 1513	Cosmos 1610	Cosmos 1464	Cosmos 1605	Cosmos 1577	Cosmos 1535
Cosmos 1634	Cosmos 1709	Cosmos 1448	Cosmos 1802	Cosmos 1725	Cosmos 1550
Cosmos 1759	Cosmos 1904	Cosmos 1627	Cosmos 1934	Cosmos 1821	Cosmos 1598
Cosmos 1891	Cosmos 2074	Cosmos 1745	Cosmos 2016	Cosmos 1864	Cosmos 1704
Cosmos 2004	Cosmos 2184	Cosmos 2026	Cosmos 2100	Cosmos 2034	Cosmos 1808
Cosmos 2135	Cosmos 2310	Cosmos 2154	Cosmos 2173	Cosmos 2142	Cosmos 1959
Cosmos 2266	Cosmos 2341	Cosmos 2218	Cosmos 2239	Cosmos 2233	Cosmos 2061
Cosmos 2327			Cosmos 2336	Cosmos 2361	Cosmos 2180
Cosmos 2334					Cosmos 2279
Cosmos 2346
At least Cosmos 660, 807, 1064, 2321 were Parus satellites but failed to reach the correct orbit.

Technical data

Orbit

Perigee/Apogee	1000 km
Inclination	83°
Period	105 min
Orbital cycle	3 days (same ground tracks every 41 revolutions)
Specifications

Prime contractor	PO Polyot of Omsk
Platform	Musson bus
Mass at launch	1550 kg
Mass in orbit
Diameter	~ 2 m (cylinder shape with a long mast)
Height	1.4 m for the first birds, then 2 m (without the mast)
Stabilization
DC power
Design lifetime

Broadcast in VHF and UHF at frequencies around 150 and 400 MHz

Parus, Tsikada, Nadezhda, Kurs,Informator and GEO-IK all use the same basic bus, although Parus has older design systems and tends not to last as long.


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 PASI 1

Also called Agila 3

General

Designation
Launch date	initially planned on 31 Dec 1996
Country of origin	Philippine
Operator	PASI
Mission	Telecommunications
Geostationary orbit	153°E or 161°E (both have been coordinated) It was also reported that the 144°E slot could be "shared" with Indonesia
Launch vehicle	Ariane

The project is led by the government together with firms like: Philippine Telegraph and Telephone, Smart Communications, Globe Telecom, Eastern telecommunication Philippines, etc. Domsat Holdings Inc holds over 60%.

2 satellites (identical) and 2 ground control stations (in Manila and Cebu, $16.5 million) ordered from Aerospatiale (PASI 1: $97 million, PASI 2: $73 million). The second satellite is a ground spare (the primary satellite will be delivered in orbit)

Launch cost: $78 million

PASI 0 is Gorizont 29

Technical data

Specifications

Prime contractor	Aerospatiale
Platform	Spacebus-3000
Mass at launch	2560 kg
Mass in orbit
Dimension	7.3 m high
Solar array	26.3 m span
Stabilization
DC power	EOL: 4750 W
Design lifetime	15 years
C-band

Main transponders	26
Backup transponders
Power
Bandwidth
Coverage	West: India East: US North: China
EIRP max
Polarization
Ku-band

Main transponders	12
Backup transponders
Power
Bandwidth
Coverage
EIRP max
Polarization

One transponder will be donated to the government


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 Program: Pegasus

American scientific program


Program: Pegasus

Pegasus 1

Pegasus 2

Pegasus 3


 Pegasus 1

General

Designation	01085 / 65009A
Launch date	16 Feb 1965
Country of origin	United States
Mission	Scientific: observation of meteorites
Perigee/Apogee	510/726 km
Inclination	31.7°
Period	97 min
Launch vehicle
Launch site	Cape Canaveral
End of life

Decay	17 Sep 1978


 Pegasus 2

General

Designation	01381 / 65039A
Launch date	25 May 1965
Country of origin	United States
Mission	Scientific: observation of meteorites
Perigee/Apogee	502/740 km
Inclination	31.7°
Period	97 min
Launch vehicle
Launch site	Cape Canaveral
End of life

Decay	3 Nov 1979


 Pegasus 3

General

Designation	01467 / 65060A
Launch date	30 Jul 1965
Country of origin	United States
Mission	Scientific: observation of meteorites
Perigee/Apogee	441/449 km
Inclination	28.9°
Period	93.4 min
Launch vehicle
Launch site	Cape Canaveral
End of life

Decay	4 Aug 1969


 Pegsat

General

Designation	20546 / 90028A
Launch date	5 Apr 1990
Country of origin	United States
Mission	Scientific: high atmosphere study
Perigee/Apogee	395/500 km
Inclination	94.1°
Period	93.5 min
Launch vehicle	Pegasus #1
Launch site	Vandenberg
Mass at launch	191 kg
External resources

http://uss-enterprise.bu.edu/BUSPACE/CRRES/crrespro.html

End of life

Decay	14 Nov 1998


 Péole

Means "Préliminaire à EOLE"

General

Designation	04801 / 70109A
Launch date	12 Dec 1970
Country of origin	France
Operator	CNES
Mission	Scientific: high atmosphere study
Perigee/Apogee	634/750 km
Inclination	15°
Period	98.6 min
Launch vehicle	Diamant #6
Mass at launch	58 kg

First geodetic satellite on an equatorial orbit

End of life

Out of service	23 Mar 1972
Decay	16 Jun 1980


 Phase 3D

General

Designation
Launch date	initially planned in Jun 1997
Country of origin
Mission	Telecommunications
Perigee/Apogee	4000 / 47000 km
Inclination	63.4°
Period
Launch vehicle	Ariane 4
Launch site
External resources

http://www.amsat.org/amsat/sats/phase3d.html

Technical data

Specifications

Prime contractor	AMSAT-DL
Platform
Mass at launch	~ 500 kg (including 250 kg fuel)
Mass in orbit
Dimension	1120 x 675 cm
Solar array
Stabilization	3-axis
DC power	~ 600 W
Design lifetime

Orbit control with GPS (12 antennas); capable of computing it's own Kepler elements

Uplink frequency chart (MHz)

Uplink	Digital	Analog Passband	Center
15 m	none	21.210 - 21.250	21.230
2 m	145.800 - 145.840	145.840 - 145.990	145.915
70 cm	435.300 - 435.550	435.550 - 435.800	435.675
23 cm (1)	1269.000 - 1269.250	1269.250 - 1269.500	1269.375
23 cm (2)	1268.075 - 1268.350	1268.325 - 1268.575	1268.450
13 cm (1)	2400.100 - 2400.350	2400.350 - 2400.600	2400.475
13 cm (2)	2449.200 - 2446.450	2446.450 - 2446.700	2446.575
6 cm	5668.300 - 5668.550	5668.550 - 5668.800	5668.675
Downlink frequency chart (MHz)

Downlink	Digital	Analog Passband	Center
10 m	29.330
2 m	145.955-145.990	145.805-145.955	145.880
70 cm	435.900-436.200	435.475-435.725	435.600
13 cm	2400.650-2400.950	2400.225-2400.475	2400.350
3 cm	10451.450-10451.750	10451.025-10451.275	10451.150
1.5 cm	24048.450-24048.750	24048.025-24048.275	24048.150
Beacons (MHz)

	Beacon 1	Beacon 2
2 m	none	none
70 cm	435.450	435.850
13 cm	2400.200	2400.600
3 cm	10451.000	10451.400
1.5 cm	24048.000	24048.400


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 Picasso-Cena

Pathfinder Instruments for Cloud and Aerosol Spaceborne Observations -- Climatologie Etendue des Nuages et des Aerosols

General

Designation
Launch date	2003
Country of origin
Operator	NASA (Langley)
Mission
Perigee/Apogee
Inclination
Period
Launch vehicle
Launch site

Part of the ESSP (Earth System Science Pathfinder) program. Includes the Institut Pierre Simon Laplace, Paris, France. The estimated mission cost of PICASSO-CENA, including launch vehicle, is $173.5 million. NASA will provide $117.4 million, with France providing $56.1 million.

Alternate missions for this one are: CloudSat and VOLCAM (the Volcanic Ash Mission).

Technical data

Specifications

Prime contractor
Platform	Proteus
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime

will employ innovative light-detection and ranging (LIDAR) instrumentation to profile the vertical distribution of clouds and aerosols, while another instrument will simultaneously image the infrared (heat) emission of the atmosphere. During the daylight half of its orbit, PICASSO-CENA will measure the reflected sunlight in an oxygen-absorption band and take images of the atmosphere with a wide-field camera.


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 PMG

Plasma Motor Generator

General

Designation	22701 / 93042B
Launch date	26 Jun 1993 at 13:27 UT
Country of origin	United States
Mission	Tether experiment
Perigee/Apogee	192/850 km
Inclination	26°
Period
Launch vehicle	Delta 2 7925
Launch site	Cape Canaveral

The PMG experiment uses somewhat different hardware from the Seds deployer, although it is for the most part built by the same groups. The PMG tether remained attached to the Delta stage.

PMG was launched with a 500m conducting tether containing a copper cable. The tether deployer and end mass contained a xenon gas dispenser to complete a 0.1 kV electrical circuit through the tether with a 0.3 amp current, in a 6-hour experiment to study space tethers' electrodynamic properties.

External resources

http://liftoff.msfc.nasa.gov/academy/tether/tethers.html


 Polaire

End of life

Out of service	5 Dec 1971
Cause	Launch failure (Diamant B4)


 Polar

General

Designation	23802 / 96013A
Launch date	24 Feb 1996 at 11:24 UT
Country of origin	United States
Operator	NASA
Mission	Scientific: magnetosphere study (auroral plasma physics)
Perigee/Apogee
Inclination	86°
Period
Launch vehicle	Delta 2 #33

Launched under the MELVS contract (Medium Expendable Launch Vehicle Services, between NASA and McDonnell Douglas)

Polar is one of two spacecraft in NASA's Global Geospace Science (GGS) mission, which is part of the International Solar-Terrestrial Physics program. Polar and a sister spacecraft, Wind 1, will perform simultaneous, coordinated measurements of key regions of Earth's space environment. Included are observations of the entry and transport of solar plasma over Earth's magnetic poles, imaging of the northern aurora (Northern Lights), and investigations of solar wind properties. Polar was built by Lockheed Martin Astro Space.

External resources

http://ggsfot.gsfc.nasa.gov/words/polar.html

http://uss-enterprise.bu.edu/BUSPACE/POLAR/polar.html

Technical data

Polar carries two booms and 6 long wire antennae. In the 'equatorial' plane of the satellite are a pair of antennae spanning 130 meters and, at right angles, another pair of antennae spanning 100 meters. Along the spin axis of the satellite are another pair of antennae with a span of 14 meters. These antennae are used to study electric and magnetic fields for the PWI (Plasma Wave Investigation) and EFI (Electric Field Instrument) experiments. Two larger but shorter (6 m long) booms carry more PWI instruments and the MFE (Magnetic Field Experiment).

Other instruments:

TIMAS (Toroidal Imaging Mass-Angle Spectrograph) to study fluxes of ions as a function of direction

TIDE (Thermal Ion Dynamics Experiment) and PSI (Plasma Source Instrument) which study connections between the polar ionosphere and the magnetotail

VIS (Visible Imaging System) and  UVI (Ultraviolet Imager) which measure auroral emissions.

PIXIE (Polar Ionospheric X-ray Imaging Experiment) studies X-rays produced by energetic electrons in the upper atmosphere.

CAMMICE (Charge and Mass Magnetospheric Ion Composition Experiment) studies the isotopic composition of energetic ions.

CEPPAD (Comprehensive Energetic Particle Pitch Angle Distribution) studies high energy protons and electrons.

(JSR)

Telemetry: 2265.0 MHz (realtime: 55.6 kbps, playback: 512 kbps)

Command: 2085.688 MHz


 Pollux

Also called D5A

General

Designation	07801 / 75039A
Launch date	17 May 1975
Country of origin	France
Mission	Technology experimentation
Perigee/Apogee	299/1256 km
Inclination	30°
Period	100.4 min
Launch vehicle	Diamant #11
Mass at launch	37 kg

To test a hydrazin motor. Counterpart of the first Pollux that was destroy at launch with Castor on 22 May 1973. Was spin stabilized and had solar cells attached to its body.

End of life

Decay	5 Aug 1975


 Posat

Also called PO-28 or Oscar 28

General

Designation	22829 / 93061G
Launch date	25 Sep 1993
Country of origin	Portugal
Operator	Consorcio Po-SAT of the LNETI (Laboratorio Nacional de Engenhario e Technologia Industrial)
Mission	Telecommunications
Perigee/Apogee	787/803 km
Inclination	98.7°
Period	100.8 min
Launch vehicle	Ariane V59
Mass at launch	45.5 kg

First Portuguese satellite. Built by Surrey's University. Is very similar to Kitsat B with a GPS reception system.

External resources

http://www.ee.surrey.ac.uk/CSER/UOSAT/research/gps.html

Technical data

Specifications

Prime contractor	SSTL (Surrey Satellite Technology Ltd.)
Platform	SSTL
Mass at launch	50.5 kg
Mass in orbit
Length	352 mm
Width	356 mm
Height	670 mm
Stabilization	gravity gradient
DC power
Design lifetime	5 years
Transponder frequency chart (MHz)

Downlink freq.	Transponder/Beacon	Mode
145.975		JD 9600 bps FSK (Primary)
145.925		JD 9600 bps FSK (Secondary)
Uplink freq.	Transponder/Beacon	Mode
435.075		JD 9600 bps FSK (Primary)
435.050		JD 9600 bps FSK (Secondary)

Can be switched to downlink at 429.950 MHz


 Proba

Project for On Board Autonomy

General

Designation
Launch date	June 2000
Country of origin	Europe
Mission	Scientific
Perigee/Apogee
Inclination
Period
Launch vehicle	PSLV
Launch site

Total cost: $14.5 million

Will conduct autonomous science observations on requests from Earth stations. Launch is planned piggyback on a PSLV.

Technical data

Specifications

Prime contractor	Verhaert Design & Development (Kruibeke, Belgium)
Platform
Mass at launch	100 kg
Mass in orbit
Dimension	0.8 x 0.6 x 0.6 m
Solar array
Stabilization
DC power
Design lifetime	3 years

Has a 25 m resolution spectrometer and a radiation and dust detectors


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 Prospero

Also called X3

General

Designation	05580 / 71093A
Launch date	28 Oct 1971
Country of origin	United Kingdom
Mission	Technology experimentation
Perigee/Apogee	531/1402 km
Inclination	82°
Period	104.4 min
Launch vehicle	Black Arrow #4
Mass at launch	66 kg

Designed and operated by the RAE. Only satellite launched by a British rocket. Tested solar cells.

Technical data

Transmits on 137.56 MHz

spin stabilized, 4 rpm

11 m diameter


 Radarsat

General

Designation	23710 / 95059A
Launch date	4 Nov 1995
Country of origin	Canada
Operator	Canadian Space Agency
Mission	Remote sensing
Perigee/Apogee	783/787 km (polar orbit)
Inclination	98.6°
Period	100 min
Launch vehicle	Delta 2 #229
Mass at launch	2750 kg

Launched under the MELVS contract

Radarsat is a cooperative program between the Canadian Space Agency, NASA and NOAA. The Canadian Space Agency built and operated the satellite; NASA furnished the launch. In exchange, U.S. government agencies will have access to all archived Radarsat data and have approximately 15% of the satellite's observing time.

The satellite is worth C$640 million and the launch about $50 million.

Radarsat International, Inc. will be the commercial distributor of Radarsat data worldwide. Lockheed Martin has distribution rights in the United States.

Contact

Canadian Space Agency

Tel: +1-514-926-4436

Fax: +1-514-926-4973

Email: coord@adro.radar1.sp-agency.ca

Contact

RadarSat International (RSI)

275 Slater Street, Suite 1203

Ottawa, Ontario K1P5H9

Canada

Tel: +1-613-238-6413

Fax: +1-613-238-5425

http://www.rsi.ca/

External resources

http://www.ball.com/aerospace/radrsat.html

Technical data

Specifications

Prime contractor	Spar Aerospace (Canada)
Platform
Mass at launch	3150 kg?
Payload mass	1500 kg
Dimension
Solar array	18 m span
Stabilization	3-axis
DC power	2200 W
Design lifetime	5 years

15 m long x 1.5 m wide Synthetic Aperture C-band Radar

Resolution: between 30 m and 90 m

On-board storage: 96 MB

Uplink: S-band (2 kbps)

Downlink: S-band (2.5, 2, 4, 32 or 128 kbps)

Another downlink for science data is at: 2230.000 MHz


 Radarsat 2

General

Designation
Launch date	Nov 2001
Country of origin	Canada
Mission	Remote sensing
Perigee/Apogee
Inclination
Period
Launch vehicle
Launch site

Worth C$305 million. MacDonald Dettwiler will be responsible for the in-orbit satellite and commercialisation. Orbimage will market the pictures worldwide.

The launch vehicle is not yet known as the US are reluctant to launch it because of its advanced performance. Further problems are arising in 1999 because of the difficulties US firms have to obtain licences to work on sensible technologies with foreign countries.

Technical data

Specifications

Prime contractor	MacDonald Dettwiler
Platform	OSC-made, new model
Mass at launch	2500 kg
Mass in orbit
Dimension
Solar array
Stabilization
DC power	3000 W
Design lifetime

SAR antenna 15 x 1.5 m. 5.3 GHz radar. Resolution from 3 m (25 km² pictures) to 100 m (500 km² pictures). Lateral vision. Revisit every 24 days.

The SAR will be provided by Spar Aerospace for $90 million


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 Radcal

Also known as P92-1

General

Designation	22698 / 93041A
Launch date	25 Jun 1993 at 23:30 UT
Country of origin	United States
Mission	Radar calibration
Perigee/Apogee	751/884 km
Inclination	89.5°
Period	101.2 min
Launch vehicle	Scout #117
Mass at launch	87 kg

Was built by Defense Systems Inc. for the USAF Space Test Program

Radcal carries a C-band transponder operating on the same frequency as the radars, and a GPS navigation package so that its orbit can be precisely determined. This calibration will allow the Space Command radars to determine orbital positions of other satellites to within a few metres.

Dowlinks on 400.033 and 150.013 MHz


 Radiosat 1

General

Designation
Launch date	initially planned in 1999
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	??? previously 80°W was planned
Launch vehicle

Program composed of 4 GEO satellites operated by CD Radio Inc.  It will broadcast digital radio in the continental US. Was granted an FCC license ($83.3 million paid), slots: 80°W & 110°W.  CD Radio acquired $105 million from Arianespace Finance S.A. to help financing the project. The satellites will be delivered in orbit by Loral.

The launches of the first 2 satellites had been bought from Ariane 5 in July 1997. The order was cancelled in May 1998 because of the unability to deliver the satellites in inclined orbit. The Ariane 5 vehicle would not have been able to place these craft in orbit until the advent of the new launcher's reignitable upper stage in 2001. As the prime contractor, Loral will try to use the 2 vacant ariane slots or will have to pay 6% of the $290 million contract.

The new system needs 3 satellites to be operational. It is yet unclear in what orbit those birds will be, maybe in some circular 35870 km with 40 to 70° inclination.

The fourth satellite will serve as a ground spare (this will cost an additional $290 million). At the same time (Aug 1997) Loral announced to have invested $25 million in CD Radio (approx 15%)  The total system cost is now approx $950 million

Its competitor will be AMRC

Contact

CD Radio, Inc.

Washington DC, USA

http://www.cdradio.com/

NASDAQ:CDRD

Technical data

Specifications

Prime contractor	SS/L
Platform	FS-1300
Mass at launch	3500 kg
Mass in orbit
Dimension
Solar array
Stabilization	3-axis
DC power
Design lifetime	15 years

downlink: 2320-2332.5 MHz


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 Program: Raduga

Means rainbow

Soviet telecommunication program. The payloads are Statsionar (C-band), Gals (X-band, 7.25-7.75 GHz) and maybe Volna (L-band).

The Raduga 1-xx are code named Gran' and the others are named Globus


Program: Raduga

Raduga 01 Raduga 02 Raduga 03 Raduga 04 Raduga 05 Raduga 06 Raduga 07 Raduga 08 Raduga 09 Raduga 10 Raduga 11 Raduga 12 Raduga 13 Raduga 14 Raduga 15	Raduga 16 Raduga 17 Raduga 18 Raduga 19 Raduga 20 Raduga 21 Raduga 22 Raduga 23 Raduga 24 Raduga 25 Raduga 26 Raduga 27 Raduga 28 Raduga 29 Raduga 30	Raduga 31 Raduga 32 Raduga 33 Raduga 1-1 Raduga 1-2 Raduga 1-3 Raduga 1-4


Raduga's specifications

Prime contractor	NPO PM
Platform	Raduga
Mass at launch	1965 kg
Diameter
Height
Stabilization	3-axis
DC power	1300 W
Design lifetime	3 to 5 years

No North-South stabilisation. Equipped 1 X-band transponder.


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Raduga's C-band

Main transponders	3
Backup transponders
Power	15 W (TWTA)
Bandwidth	36 MHz
Coverage and EIRP max	hemispheric beam (9°x18°): 32 dBW
Polarization	RHCP: downlink LHCP: uplink


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 Raduga 01

General

Designation	08513 / 75123A
Launch date	22 Dec 1975
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-01, 75°E
Launch vehicle	Proton #56
End of life

Out of service	yes
Technical data

Specifications

C-band


 Raduga 02

General

Designation	09416 / 76092A
Launch date	11 Sep 1976
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-02, 35°E
Launch vehicle	Proton #59
End of life

Out of service	yes
Technical data

Specifications

C-band


 Raduga 03

General

Designation	10159 / 77071A
Launch date	23 Jul 1977
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-02, 35°E
Launch vehicle	Proton #63
End of life

Out of service	yes
Technical data

Specifications

C-band


 Raduga 04

General

Designation	10987 / 78073A
Launch date	18 Jul 1978
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-02, 35°E
Launch vehicle	Proton #69
End of life

Out of service	yes
Technical data

Specifications

C-band


 Raduga 05

General

Designation	11343 / 79035A
Launch date	25 Apr 1979
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-03, 85°E
Launch vehicle	Proton #77
End of life

Out of service	yes
Technical data

Specifications

C-band


 Raduga 06

General

Designation	11708 / 80016A
Launch date	20 Feb 1980
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-02, 35°E
Launch vehicle	Proton #82
End of life

Out of service	yes
Technical data

Specifications

C-band


 Raduga 07

General

Designation	12003 / 80081A
Launch date	5 Oct 1980
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-08, 25°O
Launch vehicle	Proton #85
End of life

Out of service	yes
Technical data

Specifications

C-band


 Raduga 08

General

Designation	12351 / 81027A
Launch date	18 Mar 1981
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-02, 35°E
Launch vehicle	Proton #87
End of life

Out of service	yes
Technical data

Specifications

C-band


 Raduga 09

General

Designation	12618 / 81069
Launch date	30 Jul 1981
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	??? 25°E
Launch vehicle	Proton #90
End of life

Out of service	yes
Technical data

Specifications

C-band


 Raduga 10

General

Designation	12897 / 81102A
Launch date	9 Oct 1981
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-02, 35°E
Launch vehicle	Proton #91
End of life

Out of service	yes
Technical data

Specifications

C-band


 Raduga 11

General

Designation	13669 / 82113A
Launch date	26 Nov 1982
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-02, 35°E
Launch vehicle	Proton #102
Launch site	Tyuratam
End of life

Out of service	yes
Technical data

Specifications

C-band


 Raduga 12

General

Designation	13974 / 83028A
Launch date	8 Apr 1983
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-03, 85°E
Launch vehicle	Proton #107
End of life

Out of service	yes
Technical data

Specifications

C-band


 Raduga 13

General

Designation	14307 / 83088A
Launch date	25 Aug 1983
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-09, 45°E
Launch vehicle	Proton #112
End of life

Out of service	yes
Technical data

Specifications

C-band


 Raduga 14

General

Designation	14725 / 84016A
Launch date	15 Feb 1984
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-03, 85°E
Launch vehicle	Proton #116
End of life

Out of service	yes
Technical data

Specifications

C-band


 Raduga 15

General

Designation	15057 / 84063A
Launch date	22 Jun 1984
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-15, 128°E
Launch vehicle	Proton #122
End of life

Out of service	yes
Technical data

Specifications

C-band


 Raduga 16

General

Designation	15946 / 85070A
Launch date	8 Aug 1985
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-09, 45°E
Launch vehicle	Proton#134
End of life

Out of service	yes
Technical data

Specifications

C-band


 Raduga 17

General

Designation	16250 / 85107A
Launch date	15 Nov 1985
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-02, 35°E
Launch vehicle	Proton #137
End of life

Out of service	yes
Technical data

Specifications

C-band


 Raduga 18

General

Designation	16497 / 86007A
Launch date	17 Jan 1986
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-08, 25°W
Launch vehicle	Proton #139
End of life

Out of service	yes
Technical data

Specifications

C-band


 Raduga 19

General

Designation	17046 / 86082A
Launch date	25 Oct 1986
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-10, 170°W
Launch vehicle	Proton #145
End of life

Out of service	yes
Technical data

Specifications

C-band


 Raduga 20

General

Designation	17611 / 87028A
Launch date	19 Mar 1987
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-03, 85°E
Launch vehicle	Proton #149
End of life

Out of service	yes
Technical data

Specifications

C-band


 Raduga 21

General

Designation	18631 / 87100A
Launch date	10 Dec 1987
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Proton #159
Location

Begin	End	Position
L: 10 Dec 1987		Statsionar-15, 128°E
?	Dec 1997	Statsionar-10, 170°W, inclined
End of life

Out of service	Dec 1997 ?
Technical data

Specifications

C-band

EIRP coverage (dBW)


Raduga 21's EIRP


 Raduga 22

General

Designation	19596 / 88095A
Launch date	20 Oct 1988
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Proton #172
Location

Begin	End	Position
L: 20 Oct 1988		Statsionar-02, 35°E
?	Aug 1998	Statsionar-27, 12°E, inclined
End of life

Out of service	Sep 1998
Technical data

Specifications

C-band

EIRP coverage (dBW)


Raduga 22's EIRP


 Raduga 23

General

Designation	19928 / 89030A
Launch date	14 Apr 1989
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Proton #176
Location

Begin	End	Position
L: 14 Apr 1989	Jul 1995	Statsionar-08, 25°W
Sep 1995	Jul 1996	Statsionar-09, 45°E
End of life

Out of service	Jul 1996
Technical data

Specifications

C-band


 Raduga 1-1

General

Designation	20083 / 89048A
Launch date	21 Jun 1989
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-20, 70°E, inclined
Launch vehicle	Proton #178
End of life

Out of service	yes, early 1997?
Technical data

Specifications

C-band

EIRP coverage (dBW)


Raduga 1-1's EIRP


 Raduga 24

General

Designation	20367 / 89098A
Launch date	15 Dec 1989
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-09, 45°E
Launch vehicle	Proton #183
End of life

Out of service	yes
Technical data

Specifications

C-band


 Raduga 25

General

Designation	20499 / 90016A
Launch date	15 Feb 1990
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-20, 70°E
Launch vehicle	Proton #185
End of life

Out of service	Mar 1995
Cause	Sent to the junk orbit
Technical data

Specifications

C-band


 Raduga 26

General

Designation	21016 / 90112A
Launch date	20 Dec 1990
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-03, 85°E
Launch vehicle	Proton #194
End of life

Out of service	before Feb 1995
Technical data

Specifications

C-band


 Raduga 1-2

General

Designation	21038 / 90116A
Launch date	27 Dec 1990
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Proton #195
Location

Begin	End	Position
L: 27 Dec 1990	Jul 1996	Statsionar-24, 49°E, inclined
End of life

Out of service	Aug 1996
Cause	drifting out of control?
Technical data

Specifications

C-band

EIRP coverage (dBW)


Raduga 1-2's EIRP


 Raduga 27

General

Designation	21132 / 91014A
Launch date	28 Feb 1991
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Proton #197
Location

Begin	End	Position
L: 28 Feb 1991	Aug 1998	Statsionar-15, 128°E
End of life

Out of service	Aug 1998
Cause	out of control?
Technical data

Specifications

C-band


 Raduga 28

General

Designation	21821 / 91087A
Launch date
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Proton #204
Location

Begin	End	Position
L: 19 Dec 1991		Statsionar-02, 35°E, inclined
May 1999		Statsionar-09, 45°E
Technical data

Specifications

C-band

EIRP coverage (dBW)


Raduga 28's EIRP


 Raduga 29

General

Designation	22557 / 93013A
Launch date	25 Mar 1993 at 02:40 UT
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-27, 12°E
Launch vehicle	Proton #214
Technical data

Specifications

C-band

EIRP coverage (dBW)


Raduga 29's C-band EIRP


 Raduga 30

General

Designation	22836 / 93062A
Launch date	30 Sep 1993 at 17:06 UT
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-03, 85°E
Launch vehicle	Proton #216
Technical data

EIRP coverage (dBW)

Specifications

C-band


Raduga 30's C-band EIRP


 Raduga 1-3

General

Designation	22981 / 94008A
Launch date	5 Feb 1994
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-24, 49°E
Launch vehicle	Proton #220
Technical data

Specifications

C-band

EIRP coverage (dBW)


Raduga 1-3's EIRP


 Raduga 31

General

Designation	23010 / 94012A
Launch date	18 Feb 1994 at 07:56 UT
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Proton #221
Location

Begin	End	Position
L: 18 Feb 1994	Jul 1995	Statsionar-09, 45°E
Mar 1996	May 1996	83°E
Jul 1996	Aug 1996	105°E
End of life

Out of service	Aug 1996
Technical data

Specifications

C-band


 Raduga 32

General

Designation	23448 / 94087A
Launch date	28 Dec 1994 at 11:31 UT
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-20, 70°E, inclined
Launch vehicle	Proton #231
Technical data

Specifications

C-band

EIRP coverage (dBW)


Raduga 32's C-band EIRP


 Raduga 33

General

Designation	23794 / 96010A
Launch date	19 February 1996
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	n/a
Launch vehicle	Proton #240

The upper stage (Block-DM2) failed to restart after first burn to circularize the orbit. Thus the satellite remained in GTO. Failure analysis determined that at second ignition of the Block DM, the main engine experienced an emergency commanded shutdown. The probable cause of the failure was a pressure leak in the engine start system. The leak was most likely caused by an inadequate lockwire installation on a start system tube joint nut, which allowed the nut to back off under vibration. Corrective actions include increasing the lockwire diameter and adding a second, redundant lockwire to the affected joint.

End of life

Out of service	19 Feb 1996
Technical data

Specifications

C-band


 Raduga 1-4

Also called Globus 14

General

Designation	25642 / 99010A
Launch date	28 Feb 1999
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-02, 35°E
Launch vehicle	Proton #264
Technical data

Built by NPO PM, this satellite is said to be an enhanced Raduga, no details known


 Program: Rascom

Regional African Satellite Communications Organisation

Telecommunication project by a group of African countries. It is aimed to deliver telecommunication services throughout Africa. The cost of the project is approx. $1.2 billion

The first satellite, Rascom 1, is expected to be in orbit in 2001. It should cost $200 million and be operational for 10 years. It should enable telephone service inside Africa and with the rest of the world.

Alcatel Spacecom is leading the race for the contract which includes the funding, the construction and the operation of the satellite during 10 years.

Rascom hopes to install 456,000 fixed solar-powered telephone stations with international access across the continent over a 7-year period.

For the moment the wannabe operators are leasing space to the Intelsat organization

Rascom is based in Abidjan (Ivory Coast), it was established in May 1992 by over 40 African countries


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 Program: Relay

American experimental telecommunication program operated by NASA.

External resources

http://sulu.lerc.nasa.gov/dglover/relay.html


Program: Relay

Relay 1

Relay 2


Relay's specifications

Prime contractor
Platform
Mass at launch	80 kg
Mass in orbit
Length
Width
Height
Stabilization	Spin?
DC power
Design lifetime


Relay's C-band (upload at 1.7 GHz)

Main transponders	1
Backup transponders
Power	10 W
Bandwidth	600 phone circuits
Coverage
EIRP max
Polarization


 Relay 1

General

Designation	00503 / 62068A
Launch date	13 Dec 1962
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	1323/7433 km
Inclination	47.5°
Period	185.1 min
Launch vehicle	Thor Delta #15

Breaks down on 3 Jan 1963 because of an important power demand but could be mended.

End of life

Out of service	February 1965
Technical data

Specifications

C-band


 Relay 2

General

Designation	00737 / 64003A
Launch date	21 Jan 1964
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	1960/7541 km
Inclination	46.4°
Period	194.7 min
Launch vehicle	Thor Delta #23
Mass at launch	86 kg

Enabled 10 to 70 minutes transmissions

End of life

Out of service	26 Sep 1965
Technical data

Specifications

C-band


 Program: Resource21

US program for a network of 4 satellites in LEO to do remote sensing. To be operational in 2000. Agriculture is the targeted business.

The satellite should provide Multispectral imaging with 10 to 100 meter resolution.

Company based in Denver, Colorado.


 REX 2

Also called P94-2

General

Designation	23814 / 96014A
Launch date	9 Mar 1996
Country of origin	United States
Mission	Military: technology
Operator	USAF
Perigee/Apogee	803 x 332 km
Inclination	90°
Period	101 min
Launch vehicle	Pegasus #10 (XL)

The payload, sponsored by USAF Rome Lab, will study ionospheric electron density irregularities that affect radio communications. A secondary experiment will use GPS for on-orbit attitude determination and control.

Built by CTA/SS (formerly DSI)


 Program: Rocsat

Republic Of China SATellites

Taiwan's satellite program. This comprises ground equipment including dynamic testing provided by TRW. 3 satellites are planned (2 LEO, 1 GEO)

External resources

http://www.nspo.gov.tw/


Program: Rocsat

Rocsat 1

Rocsat 2

Rocsat 3


 Rocsat 1

General

Designation	25616 / 99002A
Launch date	27 Jan 1999
Country of origin	Taiwan
Operator	NSPO (National Space Program Office)
Mission	Scientific: ionosphere study
Perigee/Apogee	600 km
Inclination	35°
Period	97 min
Launch vehicle	Athena #4

The satellite will be used for scientific research including ocean color imaging, experiments on ionospheric plasma and elecrodynamics, and K-band communications experiments. The K-band cannot be used because of a license problem.

Contract worth $61 million for the satellite, $19 million for its launch

External resources

http://www.nspo.gov.tw/e30/rocsat1.html

Technical data

Specifications

Prime contractor	TRW
Platform	STEP
Mass at launch	425 kg
Mass in orbit
Dimension
Solar array
Stabilization	3-axis
DC power
Design lifetime	1 year
Ocean Color Imager (OCI)

Wavebands	443 nm (+/- 4) 490 nm (+/- 4) 510 nm (+/- 4) 555 nm (+/- 4) 670 nm (+/- 4) 865 nm (+/- 5)
Swath width	691.2 km
Resolution	800 m
Ionospheric Plasma and Electrodynamics Instrument (IPEI)

Will help scientists gain a better understanding of the ionospheric structure above Taiwan, which is of great importance in determining effects on radio communications

Experimental Communication Payload (ECP)

Main transponders	1
Backup transponders
Power	10 W
Bandwidth	27 MHz
Coverage
EIRP max
G/T max
Polarization	circular
Frequencies	uplink: 28.25 GHz (RHCP) downlink: 14.45 GHz (LHCP)

Beacon: 19.5 GHz (1.77 W)


 Rocsat 2

General

Designation
Launch date	no date yet, before 2003
Country of origin	Taiwan
Mission
Geostationary orbit	120°E
Launch vehicle
Launch site

A 12-month study contract for this Ka-band satellite was granted to TRW.

Should have 10 transponders in Ka-band

External resources

http://www.nspo.gov.tw/e30/rocsat2.html

Technical data

Specifications

Prime contractor	DASA
Platform
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime

In addition to building the satellite's spacecraft, Dornier will also develop a payload system -- a remote sensing instrument -- which has a high resolution (up to 2 meters) and varied-band spectra to give the research and communications satellite high-performance capabilities.

The other payload system to be installed on ROCSAT-2 will be built by a Taiwan group.


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 Rocsat 3

General

Designation
Launch date	early 2000s
Country of origin	Taiwan
Mission
Perigee/Apogee
Inclination
Period
Launch vehicle
Launch site

There should be 8 such satellites to study climate changes.

External resources

http://www.nspo.gov.tw/e30/rocsat3.html


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 Program: Rohini

Indian scientific program


Program: Rohini

Rohini 1A: launch failure of 10 Aug 1979

Rohini 1B

Rohini 2

Rohini 3


 Rohini 1B

Also called RS E2

General

Designation	11899 / 80062A
Launch date	18 Jul 1980
Country of origin	India
Mission	Scientific
Perigee/Apogee	307/921 km
Inclination	44.7°
Period	97 min
Launch vehicle	SLV 3 #2
Mass at launch	35 kg

First Indian satellite launched by an Indian rocket. Was used to measure the performance of the launcher.

End of life

Decay	20 May 1981


 Rohini 2

Also called RS D1

General

Designation	12491 / 81051A
Launch date	31 May 1981
Country of origin	India
Mission	Scientific
Perigee/Apogee	188/419 km (296/834 km was the intended orbit)
Inclination	46.2°
Period	90.6 min
Launch vehicle	SLV 3 #3
Mass at launch	38 kg

Carried a land-mark sensor

End of life

Decay	31 May 1981


 Rohini 3

Also called RS D2

General

Designation	14002 / 83033A
Launch date	17 Apr 1983
Country of origin	India
Mission	Scientific
Perigee/Apogee	371/861 km
Inclination	46.6°
Period	92.7 min
Launch vehicle	SLV 3 #4
Mass at launch	41.5 kg

Carried 2 cameras

End of life

Out of service	24 Sep 1984
Decay	19 Apr 1990


Rorsat
 Program: Rorsat

Radar Ocean Reconnaissance Satellite

Russian program part of the Cosmos constellation. Those satellites are observation satellites using a radar powered by a nuclear engine (50 kg uranium). They are designed to monitor activity of foreign navies. They have a short lifetime (3 to 4 months).

32 spacecrafts launched, 2 already decayed!

Rorsat first generation

1965

(111)	Cosmos 0102 (model)

1966

(067)	Cosmos 0125 (model)

1967

(127)	Cosmos 0198 (model)

1968

(023)	Cosmos 0209 (model)

1970

(079)	Cosmos 0367 (model)

1971

(025)	Cosmos 0402 (model)

(117)	Cosmos 0469 (model)

1972

(066)	Cosmos 0516 (Buk nuclear engine test)

1973

(108)	Cosmos 0626 (Buk nuclear engine test)

1974

(029)	Cosmos 0651 (Buk nuclear engine test)

(032)	Cosmos 0654 (Buk nuclear engine test)

1975

(024)	Cosmos 0723 (first operational)

(025)	Cosmos 0724

(116)	Cosmos 0785

1976

(103)	Cosmos 0860

(104)	Cosmos 0861

1977

(088)	Cosmos 0952

(090)	Cosmos 0954 (decayed)

Rorsat second generation

Those satellites separate from their fuel core once out of service

1980

(034)	Cosmos 1176

1981

(021)	Cosmos 1249

(037)	Cosmos 1266

(081)	Cosmos 1299

1982

(043)	Cosmos 1365

(052)	Cosmos 1372

(084)	Cosmos 1402 (decayed)

(099)	Cosmos 1412

Rorsat third generation

Those satellites separate from their fuel core once out of service

1984

(069)	Cosmos 1579

(112)	Cosmos 1607

1985

(064)	Cosmos 1670

(075)	Cosmos 1677

1986

(024)	Cosmos 1736

(062)	Cosmos 1771

1987

(052)	Cosmos 1860

(101)	Cosmos 1900 (is leaking coolant (sodium potassium) from its nuclear power source)

1988

(019)	Cosmos 1932


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 Rosat

RÖntgen SATellit

General

Designation	20638 / 90049A
Launch date	1 Jun 1990
Country of origin	Germany
Operator	DLR (German aerospace research establishment)
Mission	Scientific: X-ray astronomy
Perigee/Apogee	538/553 km
Inclination	53°
Period	95.6 min
Launch vehicle	Delta 2 #195

Designed to produce an all-sky survey of some 100,000 X-ray sources, and first all-sky survey in the extreme ultraviolet (XUV) spectrum using the UK-provided Wide Field Camera.

External resources

http://nssdca.gsfc.nasa.gov/rosat/rosat.html

End of life

Out of service	Sep 1998
Cause	pointed accidentaly towards the sun which destroyed the payload
Technical data

Specifications

Prime contractor	Dornier
Mass at launch	2426 kg
Payload mass	1555 kg
Dimension	2.4 x 2.1 x 4.5 m
Solar array	4.7 x 8.9 m
Stabilization	3-axis
DC power	EOL: 1000 W
Design lifetime	1.5 years
Telemetry - Data	S-band
X-ray telescope

Maximum aperture	835 mm
Focal length	2.4 m
On-axis resolution	1.8 arcsecs
Wavelength	0.6-1 µm

It monitors soft 0.1-2.4 keV X-rays.

Wield Field Camera

Maximum aperture	576 mm
Focal length	525 mm
On-axis resolution	1 arcmin
Wavelength	0.6-3 µm


 Program: Ruslan

Russian project for GEO telecommunication proposed by NPO Mashinostroyenie (NPO Mash). The 3 satellites would be launched from 2001, would weigh 2400 kg. They would relay digital TV and data throughout CIS.

An additional satellite could be developped for DBS

Technical data

Specifications

Prime contractor	NPO Mash
Platform
Mass at launch
Paylaod mass	550 kg
Dimension
Solar array
Stabilization	3-axis
DC power	5200 W
Design lifetime	10 years
C-band

Main transponders	37
Backup transponders
Power	up to 30 W
Bandwidth	36 MHz
Coverage	3 beams (7.5 x 3.5°)
EIRP
Polarization
Ku-band

Main transponders	24
Backup transponders
Power	25 W
Bandwidth
Coverage	spots
EIRP
Polarization


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 Ryusei

Also called OREX (Orbital Re-entry Experiment vehicle)

General

Designation	22978 / 94007A
Launch date	3 Feb 1994
Country of origin	Japan
Operator	NASDA
Mission	Technology
Perigee/Apogee	457/449 km
Inclination	30.5°
Period	93.5 min
Launch vehicle	H2
End of life

Decay	5 Feb 1994 in the Pacific


 S80T

General

Designation	22078 / 92052C
Launch date	10 Aug 1992
Country of origin	France
Operator	CNES
Mission	Scientific
Perigee/Apogee	1302/1324 km
Inclination	66.1°
Period	111.9 min
Launch vehicle	Ariane V52
Technical data

Specifications

Prime contractor	Club ESIE Espace or MMS?
Platform	UoSAT
Mass at launch	50 kg
Payload mass	7 kg
Dimension	0.7 x 0.35 x 0.35 m
Stabilization
DC power	Consummation: 41 W
Design lifetime	3 years

Frequencies: uplink: 148 MHz, downlink: 137 MHz, 401.715 MHz


 SAC A

General

Designation	25550 / 98069B
Launch date	14 Dec 1998
Country of origin	Argentina
Mission	Scientific
Perigee/Apogee	378/395 km
Inclination	51.6°
Period	92.3 min
Launch vehicle	STS 88

SAC A is a technological payload: it has an experimental remote sensing satellite and a tracking device to follow a whale

External resources

http://www.conae.gov.ar/sac-a/sac_a.html

Technical data

Specifications

Prime contractor	INVAP (Bariloche, AR)
Platform
Mass at launch	60 kg
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime

Downlink: 242 MHz

Uplink: 401.520 MHz


 SAC B

Satelite de Aplicaciones Cientificas

General

Designation	24645 / 96061A Failed to separate with HETE
Launch date	4 Nov 1996
Country of origin	Argentina
Mission	Scientific
Perigee/Apogee	550 km, circular
Inclination	38°
Period	95.6 min
Launch vehicle	Pegasus XL #14

Cooperative project between NASA and Argentinas National Commission of Space Activities (CONAE). The satellite is designed to advance the study of solar physics and astrophysics through the examination of solar flares, gamma ray bursts, diffuse X-ray cosmic background, and energetic neutral atoms.

External resources

http://www.conae.gov.ar/sac-prueba.html

http://pao.gsfc.nasa.gov/gsfc/service/gallery/fact_sheets/spacesci/sacb.htm

http://www.astro.psu.edu/xray/cubic/SAC-B.html

Technical data

Specifications

Prime contractor
Platform	designed and constructed in Argentina
Mass at launch	181 kg
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime	3 years

Telemetry & data: 2255.5 MHz (realtime: 0.032 kbps, playback: 50, 100 or 200 kbps)

Command: 2076.9 MHz (0.992 kbps)

Primary ground operations should have been performed by the Argentine Mission Operations Control Center (MOCC) located in San Miguel (just outside of Buenos Aires) which incorporates a 3.6-meter antenna system used for tracking, telemetry, telecommand and data acquisition and which is collocated and integrated with the MOCC systems.


 SAC C

General

Designation
Launch date	mid 1999
Country of origin	Argentina
Mission	Scientific
Perigee/Apogee	702 km sun synchronous
Inclination	98.3°
Period
Launch vehicle	Delta 2

It will provide multispectral imaging of terrestrial and coastal environments. The spacecraft will provide studies of the structure and dynamics of the Earths atmosphere and ionosphere. The Earths geomagnetic field will also be studied. SAC-C will verify autonomous methods of attitude and orbit determination.

External resources

http://www.conae.gov.ar/sac-c/folleto.html

Technical data

Specifications

Prime contractor
Platform
Mass at launch	463 kg
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime	4 years

Multiple instruments. Will also have a digital transponder for amateur radio


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 Saci 1

General

Designation
Launch date
Country of origin	Brasil
Mission
Perigee/Apogee	750 km sun-synchronous
Inclination
Period
Launch vehicle	Long March 4B
Launch site
Technical data

Specifications

Prime contractor
Platform
Mass at launch	60 kg
Payload mass	28 kg
Dimension	65 x 40 x 40 cm
Solar array
Stabilization	spin stabilized
DC power	> 30 W (eclipse: 2 x 22 NiCd battery cells providing 4.5 Ah)
Design lifetime	18 months

S-band downlink (256 kbps, 2025-2120 MHz) & uplink (19.2 kbps, 2200-2300 MHz). 2 W RF power

Payload:

Plasmex: study of plasma bubbles and geomagnetic experiments

The main objective of this experiment in the ionosphere is to investigate the generation, development and decay of the plasma bubbles, particularly in the Brazilian region. This investigation intends to elucidate the strong influence of the bubbles and associated plasma turbulence in several space application systems (remote sensing with radar, space geodesy, trans-ionosphere telecommunication etc). The discovery of such phenomenon in the Brazilian ionosphere was reported by measurements with rocket-borne photometers and ground-based ionosond.

Fotsat: airglow photometer

This experiment has the objective of measuring the intensity of the terrestrial airglow emissions in global ranges of Oxygen OI 557.7nm, OI 630.0nm and OH(8,3) in global ranges. Special interests in this investigation are the equatorial ionosphere anomaly, the South-Atlantic anomaly, and the longitudinal and latitudinal variations of the dynamical process in the ionosphere. The photometer was designed and manufactured by INPE.

Orcas: solar and anomalous cosmic rays observation in the magnetosphere

The main objective of the telescope ORCAS is to measure the Anomalous Cosmic Rays (ACR) fluxes, from C to Ne, "trapped" into the belt by using solid detectors and by identifying the time and the direction of particle arrivals. The ORCAS will allow studies of the space distribution and of the dynamics associated to the population of the trapped particles in conditions of minimum solar activity with intense fluxes.


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 Saci 2

General

Designation
Launch date
Country of origin	Brasil
Mission
Perigee/Apogee
Inclination
Period
Launch vehicle	VLS #2
Launch site	Alcantara

Built by INPE, costed $2 million

Technical data

Specifications

Prime contractor
Platform
Mass at launch	80 kg
Mass in orbit
Dimension	57 cm x 44 cm
Solar array
Stabilization
DC power
Design lifetime

The satellite will have 4 scientific experiments developed by several Brazilian universities.

It will carry a transponder for the collection of environmental data and a payload that the China-Brazil Earth Resources Satellite (CBERS) will also have. This system will transmit UHF signals to small receiver stations.


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 Program: Safir

Satellite For Information Relay

Program of OHB System (Bremen, Germany) with 6 satellites (3 stand-alone and 3 piggybacked). The 3 satellites are planned in 1997, 1998, 1999

Stand-alone satellites

General

Perigee/Apogee	678/696 km
Inclination	98.4°
Period	98 min
Uplinks	401 MHz
Downlinks	400 MHz
Specifications

Prime contractor
Platform
Mass at launch	55 kg
Mass in orbit
Length	45 cm
Width	45 cm
Height	45 cm
Stabilization
DC power
Design lifetime


Program: Safir

Safir R1: on Resurs O1-3

Safir 2


 Safir 1

General

Designation
Launch date	1997
Country of origin	Germany
Mission	Telecommunications
Perigee/Apogee
Inclination
Period
Launch vehicle
Launch site

Safir 1 will be half financed by DARA

Should be launched with Abrixas


 Safir 2

General

Designation	25399 / 98043F
Launch date	10 Jul 1998
Country of origin	Germany
Mission	Telecommunications
Perigee/Apogee	815 / 818 km
Inclination	98.8°
Period	101 minutes
Launch vehicle	Zenit

The satellite data transmissions have rates of 300, 600, 1200, 2400 and 4800 Baud, over two telemetry systems (TS1 13.722 GHz, TS2 400 MHz).


 Program: Sakura

Means "cherry tree", also called CS (Communication Satellite)

Japanese telecommunications satellite program. Ka-band transponders are used by NTT

Contact

Telecommunication Satellite Corporation of Japan

2-31-19 Shiba, Minato-ku, Tokyo 105, Japan

Tel: +81-3-3769-6811

Fax: +81-3-3452-7600


Program: Sakura

Sakura 1

Sakura 2A

Sakura 2B

Sakura 3A

Sakura 3B


Sakura 3's specifications

Prime contractor	Mitsubishi Electric Co. with NEC (transponders)
Platform	Mitsubishi
Mass at launch	1099 kg
Mass in orbit	550 kg
Diameter	2.184 m
Height	2.429 m
Stabilization	Spin stabilized
DC power	833 to 750 W (depending on the season)
Design lifetime	7 years


Sakura 3's C-band

Main transponders	2
Backup transponders	1
Power	4 W (TWTA)
Bandwidth	180 MHz
Coverage
EIRP max	29 dBW
Polarization


Sakura 3's Ka-band

Main transponders	10
Backup transponders	5
Power	4.2 W (TWTA)
Bandwidth	100 MHz
Coverage
EIRP max	37 dBW
Polarization


 Sakura 1

Also called CS 1A

General

Designation	10516 / 77118A
Launch date	15 Dec 1977
Country of origin	Japan
Mission	Telecommunications
Geostationary orbit	135°E
Launch vehicle	Thor Delta #137
Mass at launch	350 kg
End of life

Out of service	yes


 Sakura 2A

Also called CS 2A

General

Designation	13782 / 83006A
Launch date	4 Feb 1983
Country of origin	Japan
Mission	Telecommunications
Geostationary orbit	132°E
Launch vehicle	N2
Mass at launch	350 kg
End of life

Out of service	yes
Technical data

Ka-band 20/30 GHz

Phone circuits	4000


 Sakura 2B

Also called CS 2B

General

Designation	14248 / 83081A
Launch date	5 Aug 1983
Country of origin	Japan
Mission	Telecommunications
Geostationary orbit	136°E
Launch vehicle	N2
Mass at launch	350 kg
End of life

Out of service	yes
Technical data

Ka-band 20/30 GHz

Phone circuits	4000


 Sakura 3A

Also called CS 3A

General

Designation	18877 / 88012A
Launch date	19 Feb 1988
Country of origin	Japan
Mission	Telecommunications
Geostationary orbit	132°E
Launch vehicle	H1
End of life

Out of service	Sep 1996
Cause	deorbited
Technical data

Specifications

C-band

Ka-band


 Sakura 3B

Also called CS 3B

General

Designation	19508 / 88086A
Launch date	16 Sep 1988
Country of origin	Japan
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	H1
Location

Begin	End	Position
L: 16 Sep 1988	Feb 1997	136°E
Mar 1997	Nov 1997	154°E
End of life

Out of service	Nov 1997
Cause	deorbited
Technical data

Specifications

C-band

Ka-band


 Sampex

Also called Solar Anomalous and Magnetospheric Particle Explorer and SMEX 1

General

Designation	22012 / 92038A
Launch date	3 Jul 1992
Country of origin	United States
Mission	Scientific: Sun observation
Perigee/Apogee	550/675 km
Inclination	82°
Period	96 min
Launch vehicle	Scout

To conduct studies of solar, anomalous, galactic, and magnetospheric energetic particles.

External resources

http://sunland.gsfc.nasa.gov/smex/sampex/

http://lepsam.gsfc.nasa.gov/www/public_sampex.html

Technical data

Specifications

Prime contractor
Platform
Mass at launch	157 kg
Payload mass	40 kg
Dimension
Solar array
Stabilization
DC power	100 W
Design lifetime	1 year

Downlink: S-band, 900 kbps

Uplink: 2 kbps


 Program: San Marco

Italian high atmosphere study program. The specificity of this program was the launch site: a sea platform located at 2.9°S in Formosa Bay, at 5 km of Kenya's coast. The launch platform was linked to a control ship.


Program: San Marco

San Marco 1

San Marco 2

San Marco 3

San Marco 4

San Marco 5


 San Marco 1

General

Designation	00957 / 64084A
Launch date	15 Dec 1964
Country of origin	Italy
Mission	Scientific: high atmosphere study
Perigee/Apogee	200/846 km
Inclination	37.8°
Period	95.1 min
Launch vehicle	Scout #35
Mass at launch	115 kg
End of life

Decay	13 Sep 1965


 San Marco 2

General

Designation	02761 / 67038A
Launch date	26 Apr 1967
Country of origin	Italy
Mission	Scientific: high atmosphere study
Perigee/Apogee	219/741 km
Inclination	2.9°
Period	94.2 min
Launch vehicle	Scout #52
Mass at launch	128 kg

First equatorial launch

End of life

Decay	14 Oct 1967


 San Marco 3

General

Designation	05176 / 71036A
Launch date	24 Apr 1971
Country of origin	Italy
Mission	Scientific: high atmosphere study
Perigee/Apogee	222/707 km
Inclination	3.2°
Period	93.8 min
Launch vehicle	Scout #72
Mass at launch	161 kg
End of life

Decay	29 Nov 1971


 San Marco 4

General

Designation	07154 / 74009A
Launch date	18 Feb 1974
Country of origin	Italy
Mission	Scientific: high atmosphere study
Perigee/Apogee	270/875 km
Inclination	2.9°
Period	96.1 min
Launch vehicle	Scout #85
Mass at launch	164 kg
End of life

Decay	4 May 1976


 San Marco 5

General

Designation	19013 / 88026A
Launch date	25 Mar 1988
Country of origin	Italy
Mission	Scientific: high atmosphere study
Perigee/Apogee	268/625 km
Inclination	3°
Period	93.5 min
Launch vehicle	Scout #109
Mass at launch	235 kg

Designed by Rome's university

End of life

Decay	6 Dec 1988


 Sara

Satellite Amateur de Radio Astronomie

General

Designation	21578 / 91050E
Launch date	17 Jul 1991
Country of origin	France
Mission	Scientific: radio astronomy
Perigee/Apogee	755/764 km
Inclination	98.4°
Period	100 min
Launch vehicle	Ariane V44

Must study Jupiter's radio environment by listening in the 2-15 MHz range. It is controlled and received at Nançay in France

Technical data

Specifications

Prime contractor	Club ESIEE Espace (built by students)
Mass at launch	28 kg
Mass in orbit	20 kg
Dimension	0.34 x 0.34 x 0.34 m
Design lifetime	11 years

Telemetry beacon: 145.955 MHz, 300 bps FSK, FM, 0.5 W transmitter


 Program: Sarsat

Search And Rescue Satellite Aided Tracked

International cooperation program with the United States, Canada, France and since 1979 the CIS which made its Cospas system compatible.

Mission: search and rescue of persons and boats in distress. The service started on 1 Sep 1982. In 1995 28 earth stations and 15 control centers in 16 countries were operational.

The system uses reception beacons operating at 121.5 MHz, 243 MHz and at 406 MHz. When a distress signal is received 1544.5 MHz can be heard. Polar orbiting satellites can detect and localize beacons whereas geostationary satellites can't localize them. Thus beacons to work with geostationary birds have to include a GPS receptor.

Satellites carrying a Sarsat-Cospas payload

83082	NOAA 08 (EOL)

84123	NOAA 09

87022	Goes 07

88089	NOAA 11

89050	Nadezhda 1

90017	Nadezhda 2

91019	Nadezhda 3

92041	Insat 2A

93048	Insat 2B

94022	Goes 08

94041	Nadezhda 4

94082	Luch 0

94089	NOAA 14

95025	Goes 09

Future satellites:

Nadezhda 5

NOAA 15

External resources

http://www.cospas-sarsat.org/overview/sumystat.htm

http://psbsgi1.nesdis.noaa.gov:8080/SARSAT/homepage.html


 Program: Satcom

Also called RCA (former owner)

American telecommunication program operated by GE Americom.


Program: Satcom

Satcom 1

Satcom 1R

Satcom 2

Satcom 2R

Satcom 3

Satcom 3R

Satcom 4

Satcom C1

Satcom C3

Satcom C4

Satcom C5 (Aurora 2)

Satcom K1

Satcom K2


Satcom 1 & 2's C-band

Main transponders	24
Backup transponders
Power
Bandwidth	36 MHz
Coverage
EIRP max	32 dBW
Polarization


Satcom K's specifications

Prime contractor	GE Astro Space
Platform	GE 4000
Mass at launch	1930 kg
Mass in orbit	1050 kg
Dimension	1.7 x 2.13 x 1.52 m
Solar array	19.3 m
Stabilization	3-axis
DC power	BOL: 3000 W
Design lifetime	10 year


Satcom K's Ku-band

Main transponders	16
Backup transponders	4
Power	47 W (TWTA)
Bandwidth	54 MHz
Coverage
EIRP max	48 dBW
Polarization	linear H/V


Satcom C3 & C4's EIRP


 Satcom 1

General

Designation	08479 / 75117A
Launch date	13 Dec 1975
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	80°W
Launch vehicle	Thor Delta #118
Mass at launch	465 kg
End of life

Out of service	yes
Technical data

C-band


 Satcom 1R

Also called Satcom 6

General

Designation	13984 / 83030A
Launch date	11 Apr 1983
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Thor Delta #167
Launch site	Cape Canaveral
Location

Begin	End	Position
L: 11 Apr 1983		139°W
< May 1992	May 1992 >	131°W
End of life

Out of service	yes
Technical data

Specifications

Prime contractor	GE Astro Space
Platform	GE 3000
Mass at launch	1120 kg
Mass in orbit	approx. 600 kg
Length	1.63 m
Width	1.32 m
Height	0.99 m
Solar array	14.33 m span
Stabilization	3-axis
DC power
Design lifetime	10 years
C-band

Main transponders	24
Backup transponders	4
Power	8.5 W
Bandwidth	36 MHz
Coverage
EIRP max	36 dBW
Polarization	linear H/V


 Satcom 2

General

Designation	08774 / 76029A
Launch date	26 Mar 1976
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Thor Delta #121
Launch site	Cape Canaveral
End of life

Out of service	yes
Location

Begin	End	Position
L: 26 Mar 1976		119°W
1984		72°W
Technical data

C-band


 Satcom 2R

Also called Satcom 7

General

Designation	14328 / 83094A
Launch date	8 Sep 1983
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	72°W
Launch vehicle	Thor Delta #172
Launch site	Cape Canaveral
End of life

Out of service	Mar 1995
Cause	Sent to the junk orbit
Technical data

Specifications

Prime contractor	GE Astro Space
Platform	GE 3000
Mass at launch	1120 kg
Mass in orbit	approx. 600 kg
Length	1.63 m
Width	1.32 m
Height	0.99 m
Solar array	14.33 m
Stabilization	3-axis
DC power
Design lifetime	10 year
C-band

Main transponders	24
Backup transponders	4
Power	8.5 W
Bandwidth	36 MHz
Coverage
EIRP max	36 dBW
Polarization	linear H/V

Transponder frequency chart


 Satcom 3

General

Designation	11635 / 79101A
Launch date	7 Dec 1979
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	n/a
Launch vehicle	Thor Delta #150
Launch site	Cape Canaveral
End of life

Out of service	7 Dec 1979
Cause	Satellite failure


 Satcom 3R

General

Designation	12967 / 81114A
Launch date	20 Nov 1981
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	131°W
Launch vehicle	Thor Delta #158
Launch site	Cape Canaveral
End of life

Out of service	yes
Technical data

Specifications

Prime contractor	GE Astro Space
Platform	GE 3000
Mass at launch	1070 kg
Mass in orbit	approx. 600 kg
Length	1.6 m
Width	1.27 m
Height	1.29 m
Solar array	11.2 m span
Stabilization	3-axis
DC power
Design lifetime	10 years
C-band

Main transponders	18+6
Backup transponders	3+1
Power	(18+3) transponders of 5.5 W (6+1) transponders of 8.5 W
Bandwidth	36 MHz
Coverage
EIRP max	37 dBW
Polarization	linear H/V


 Satcom 4

General

Designation	13035 / 82004A
Launch date	16 Jan 1982
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	82°W
Launch vehicle	Thor Delta #159
Launch site	Cape Canaveral
End of life

Out of service	yes
Technical data

Specifications

Prime contractor	GE Astro Space
Platform	GE 3000
Mass at launch	1070 kg
Mass in orbit	approx. 600 kg
Length	1.6 m
Width	1.27 m
Height	1.29 m
Solar array	11.2 m span
Stabilization	3-axis
DC power
Design lifetime	10 years
C-band

Main transponders	18+6
Backup transponders	3+1
Power	(18+3) transponders 5.5 W (6+1) transponders 8.5 W
Bandwidth	36 MHz
Coverage
EIRP max	37 dBW
Polarization	linear H/V


 Satcom C1

General

Designation	20945 / 90100A
Launch date	20 Nov 1990
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	137°W
Launch vehicle	Ariane V40
Technical data

EIRP coverage (dBW)

Specifications

Prime contractor	GE Astro Space
Platform	GE 3000
Mass dry	517 kg
Mass at launch	1169 kg
Mass in orbit	682 kg
Length	1.63 m
Width	1.32 m
Height	0.99 m
Solar array	14.33 m
Stabilization	3-axis
DC power	BOL: 1390 W
Design lifetime	10 years
Beacons	telemetry: 3.7005 GHz (H), 4.1995 GHz (V) command: 6.4235 GHz (H)
C-band

Main transponders	24
Backup transponders	4
Power	8.5 W (SSPA)
Bandwidth	36 MHz
Coverage & EIRP max	Conus: 36 dBW Alaska: 34 dBW Hawaii: 32 dBW
Polarization	linear H/V

Transponder frequency chart


Satcom C1's EIRP


 Satcom C3

General

Designation	22117 / 92060B
Launch date	10 Sep 1992
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	131°W
Launch vehicle	Ariane V53
Technical data

EIRP coverage (dBW)

Specifications

Prime contractor	GE Astro Space
Platform	GE 3000
Mass at launch	1370 kg
Mass in orbit	784 kg
Length	1 m
Width	1.6 m
Height	1.5 m
Solar array	15.1 m span
Stabilization	3-axis
DC power	1400 W
Design lifetime	12 years
C-band

Main transponders	24
Backup transponders
Power	17 W
Bandwidth	36 MHz
Coverage & EIRP max	see footprint
Polarization	linear H/V

Transponder frequency chart


 Satcom C4

General

Designation	22096 / 92057A
Launch date	31 Aug 1992
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	135°W
Launch vehicle	Delta 2 #213
Launch site	Cape Canaveral
Technical data

EIRP coverage (dBW)

Specifications

Prime contractor	GE Astro Space
Platform	GE 3000
Mass at launch	1370 kg
Mass in orbit	784 kg
Length	1 m
Width	1.6 m
Height	1.5 m
Solar array	15.1 m span
Stabilization	3-axis
DC power	1400 W
Design lifetime	12 years
C-band

Main transponders	24
Backup transponders
Power	17 W
Bandwidth	36 MHz
Coverage
EIRP max
Polarization	linear H/V

Transponder frequency chart


 Satcom K1

Also called Satcom Ku 1

General

Designation	16482 / 86003B
Launch date	12 Jan 1986
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	STS 32
Location

Begin	End	Position
L: 12 Jan 1986	Apr 1997	85°W
May 1997	late-Jun 1997	86.5°W
End of life

Out of service	Jul 1997
Technical data

EIRP coverage (dBW)

Specifications

Ku-band

Satcom K1 would have a spot to Hawaii

Transponder frequency chart (GHz)

Horizontal Uplink	Horizontal Downlink	Transponder	Vertical Downlink	Vertical Uplink
	11.7290	1		14.0290
14.0585		2	11.7585
	11.7880	3		14.0880
14.1175		4	11.8175
	11.8470	5		14.1470
14.1765		6	11.8765
	11.9060	7		14.2060
14.2350		8	11.9350
	11.9650	9		14.2650
14.2945		10	11.9945
	12.0240	11		14.3240
14.3535		12	12.0530
	12.0830	13		14.3830
14.4125		14	12.1125
	12.1420	15		14.4420
14.4715		16	12.1715


Satcom K's EIRP


 Satcom K2

Also called Satcom Ku 2

General

Designation	16276 / 85109D
Launch date	28 Nov 1985
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	STS 31
Location

Begin	End	Position
L: 28 Nov 1985	Nov 1996	81°W
Nov 1996	Jun 1997	85°W
Jul 1997		81°W
Technical data

EIRP coverage (dBW)

Specifications

Ku-band

Transponder frequency chart (GHz)

Horizontal Uplink	Horizontal Downlink	Transponder	Vertical Downlink	Vertical Uplink
	11.7290	1		14.0290
14.0585		2	11.7585
	11.7880	3		14.0880	Spot to Western US
14.1175		4	11.8175
	11.8470	5		14.1470
14.1765		6	11.8765
	11.9060	7		14.2060
14.2350		8	11.9350
	11.9650	9		14.2650
14.2945		10	11.9945
	12.0240	11		14.3240
14.3535		12	12.0530
	12.0830	13		14.3830
14.4125		14	12.1125
	12.1420	15		14.4420
14.4715		16	12.1715


 SAX

Satellite per Astronomia a raggi X, also called BeppoSAX

General

Designation	23857 / 96027A
Launch date	30 Apr 1996
Country of origin	Italy and Netherlands (with the help of ESA)
Mission	Scientific: high energy astrophysics (X-ray astronomy)
Perigee/Apogee	581/605 km
Inclination	4°
Period	~ 97 min
Launch vehicle	Atlas Centaur #100
External resources

http://astro.estec.esa.nl/SA-general/Research/Sax/

Technical data

Specifications

Prime contractor	Alenia Spazio
Platform
Mass at launch	1400 kg
Payload mass	490 kg
Diameter	2.7 m
Height	3.6 m
Solar array	9 m span (2 panels of 2.6 x 3.5 m)
Stabilization	3 axis
DC power	EOL: 2300 W
Design lifetime	4 years
Payload

4 X-ray concentrators/spectrometers

2 wide-field X-ray cameras (WFC)

large area phoswich detector system (PDS)

high-pressure gas-scintillation proportional counter HPCPC)

command: 2 kbps, S-band

telemetry/data: 2245.500 MHz (16/131/917 kbps)

Other possible frequencies: 2067.5 MHz & 2245.24887 MHz

X-ray energy detection range	0.1-300 keV
Field of view	WFC: 20 x 20 deg others: 0.5-1.5 deg
Angular resolution	WFC: 5 arcmin others: ~ 1 arcmin


 Program: SBS

Satellite Business System, also called CNS (Communication Network Service) or USASAT

Satellite Business Systems was created on 15 Dec 1975 by IBM, Comsat and Aetna Life and Casualty Inc. It was the first private professional satellite digital communications network. In Jul 1984, Comsat left the consortium. In Jul 1985, Satellite Business Systems was sold to MCI; four satellites were then in orbit. Sometime around 1987, the fleet was sold off. SBS 1 and 2 were sold to Comsat, SBS 3 remained with MCI, and SBS 4 was sold to IBM's Satellite Transponder Leasing Corp (STLC) together with the SBS 5 and 6 satellites still on the ground. In Apr 1990, Hughes Communications Inc (HCI) bought STLC from IBM. Sometime later (in 1992?) SBS 3 was sold to Comsat so that currently:

SBS 1, 2 & 3 are owned by Comsat

SBS 4, 5 & 6 are owned by HCI

All SBS satellites are based on HS-376 buses but SBS 6


Program: SBS

SBS 1

SBS 2

SBS 3

SBS 4

SBS 5

SBS 6


 SBS 1

General

Designation	12065 / 80091A
Launch date	15 Nov 1980
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	100°W
Launch vehicle	Thor Delta #153
Launch site	Cape Canaveral
End of life

Out of service	June 1990
Technical data

Specifications

Prime contractor	Hughes
Platform	HS-376
Mass at launch
Mass in orbit
Diameter
Height
Stabilization	Spin stabilized
DC power
Design lifetime	7 years
Ku-band

Main transponders	10
Backup transponders
Power
Bandwidth
Coverage
EIRP max	46 dBW
Polarization


 SBS 2

General

Designation	12855 / 81096A
Launch date	24 Sep 1981
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Thor Delta #156
Launch site	Cape Canaveral
Location

Begin	End	Position
L: 24 Sep 1981
< May 1992	Oct 1993 >	97°W
< Jun 1994	Aug 1996	71°W, inclined
End of life

Out of service	Sep 1996
Cause	Deorbited
Technical data

Specifications

Prime contractor	Hughes
Platform	HS-376
Mass at launch
Mass in orbit
Diameter
Height
Stabilization	Spin stabilized
DC power
Design lifetime	7 years
Ku-band

Main transponders	10
Backup transponders
Power	8 transponders of 20 W 2 transponders of 40 W
Bandwidth	43 MHz
Coverage	US
EIRP max	43-40 dBW
Polarization	linear H
Transponder frequency chart (GHz)

Horizontal Downlink	Transponder	Vertical Uplink
11.725	1	14.025
11.774	2	14.074
11.823	3	14.123
11.872	4	14.172
11.921	5	14.221
11.970	6	14.270
12.019	7	14.319
12.068	8	14.368
12.117	9	14.417
12.166	10	14.466


 SBS 3

General

Designation	13651 / 82110B
Launch date	11 Nov 1982
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	STS 05
Location

Begin	End	Position
L: 11 Nov 1982
< May 1992	May 1992 >	95°W
< May 1994	2 Jun 1995	74°W
End of life

Out of service	2 Jun 1995
Cause	moved to the graveyard
Technical data

Specifications

Prime contractor	Hughes
Platform	HS-376
Mass at launch
Mass in orbit
Diameter
Height
Stabilization	Spin stabilized
DC power
Design lifetime	7 years
Ku-band

Main transponders	10
Backup transponders
Power
Bandwidth
Coverage
EIRP max	46 dBW
Polarization


 SBS 4

General

Designation	15235 / 84093B
Launch date	31 Aug 1984
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	STS 16
Location

Begin	End	Position
L: 31 Aug 1984		?
< May 1992	Oct 1992 >	91°W
< Oct 1993		77°W, inclined
Technical data

Specifications

Prime contractor	Hughes
Platform	HS-376
Mass at launch	1241 kg
Mass in orbit	725 kg
Diameter	2.16 m
Height	6.6 m
Stabilization	Spin stabilized
DC power	BOL: 1200 W
Design lifetime	7 years
Ku-band

Main transponders	10
Backup transponders	4
Power	5 transponders of 20 W (TWTA) 5 transponders of 40 W (TWTA)
Bandwidth	43 MHz
Coverage	CONUS
EIRP max	46 dBW
Polarization	linear H
Transponder frequency chart (GHz)

Horizontal Downlink	Transponder	Vertical Uplink
11.725	1	14.025
11.780	2	14.080
11.823	3	14.123
11.872	4	14.172
11.921	5	14.221
11.970	6	14.270
12.019	7	14.319
12.068	8	14.368
12.117	9	14.417
12.166	10	14.466


 SBS 5

General

Designation	19484 / 88081B
Launch date	8 Sep 1988
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	123°W
Launch vehicle	Ariane V25

Should retire in 2000.

Technical data

EIRP coverage (dBW)

Specifications

Prime contractor	Hughes
Platform	HS-376
Mass at launch	1241 kg
Mass in orbit	725 kg
Diameter	2.16 m
Height	6.6 m
Stabilization	Spin stabilized
DC power	BOL: 1200 W
Design lifetime	10 years
Ku-band

Main transponders	14
Backup transponders
Power	4 H transponders: variable 20-40 W (TWTA) 6 H transponders: 20 W (TWTA) 4 V transponders: variable 20-40 W (TWTA)
Bandwidth	H transponders: 43 MHz V transponders: 110 MHz
Coverage	CONUS
EIRP max	46 dBW
Polarization	linear H/V

SBS 5 might also have coverage for Hawaii and Alaska, but this is unconfirmed.

Transponder frequency chart (GHz)

Horizontal Uplink	Horizontal Downlink	Transponder	Vertical Downlink	Vertical Uplink
	11.725	1		14.025
	11.780	2		14.080
	11.823	3		14.123
	11.872	4		14.172
	11.921	5		14.221
	11.970	6		14.270
	12.019	7		14.319
	12.068	8		14.368
	12.117	9		14.417
	12.166	10		14.466
14.048		11	11.748
14.198		12	11.898
14.294		13	11.994
14.441		14	12.141


SBS 5's EIRP


 SBS 6

General

Designation	20872 / 90091A
Launch date	12 Oct 1990
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V39
Location

Begin	End	Position
L: 12 Oct 1990		77°W
< May 1992	May 1992 >	99°W
< Oct 1993	15 Oct 1995	95°W
Nov 1995		74°W
Technical data

EIRP coverage (dBW)

Horizontal

Vertical

Specifications

Prime contractor	Hughes
Platform	HS-393
Mass at launch	2478 kg
Mass in orbit	1514 kg
Diameter	3.66 m
Height	10 m deployed
Stabilization	Spin stabilized (55 rpm)
DC power	BOL: 2300 W
Design lifetime	10 years

Telemetry: 12.190-12.200 GHz H in PCM/FM and 14.495-14.500 GHz V in FM

Ku-band

Main transponders	19
Backup transponders	11
Power	41 W (TWTA)
Bandwidth	43 MHz
Coverage	CONUS, Alaska, Hawaii
EIRP max	50 dBW
Polarization	linear H/V

Antenna: 2.4 m

Transponder frequency chart (GHz)

Horizontal  Uplink	Horizontal Downlink	Transponder	Vertical  Downlink	Vertical  Uplink
	11.7250	1		14.0250
14.0495		2	11.7495
	11.7740	3		14.0740
14.0985		4	11.7985
	11.8230	5		14.1230
14.1475		6	11.8475
	11.8720	7		14.1720
14.1965		8	11.8965
	11.9210	9		14.2210
14.2455		10	11.9455
	11.9700	11		14.2700
14.2945		12	11.9945
	12.0190	13		14.3190
14.3435		14	12.0435
	12.0680	15		14.3680
14.3925		16	12.0925
	12.1170	17		14.4170
14.4415		18	12.1415
	12.1660	19		14.4660


SBS 6's EIRP (Vertical)


SBS 6's EIRP (Horizontal)


 Program: SCD

Satelite de Coleta de Dados

Brasilian first home-built satellite program. The program focuses on remote sensing. It is conducted by INPE


Program: SCD

SCD 1

SCD 2

SCD 2A


 SCD 1

Satelite de Coleta de Dados

General

Designation	22490 / 93009B
Launch date	9 Feb 1993
Country of origin	Brazil
Operator	INPE
Mission	Remote sensing
Perigee/Apogee	729/793 km
Inclination	25°
Period	100.1 min
Launch vehicle	Pegasus #3
Launch site	Cape Canaveral

Provided a map of CO² distribution in atmosphere above South America. Collected and transmited data from 500 ground platforms.

Technical data

Specifications

Prime contractor	INPE
Platform
Mass at launch	115 kg
Mass in orbit
Dimension
Solar array
Stabilization	spin stabilized
DC power	70 W
Design lifetime

Transmits at 2 GHz and 401 MHz


 SCD 2A

General

Designation	n/a
Launch date	2 Nov 1997
Country of origin	Brazil
Mission	Technology: test
Perigee/Apogee	700 km
Inclination
Period
Launch vehicle	VLS #1
Launch site	Alcantara

Mockup of the SCD 2 remote sensing satellite.  Cost of the satellite: $3 million

End of life

Out of service	2 Nov 1997
Cause	launch failed, rocket had to be destroyed because one motor failed and it fell in the secure area in the sea about 2 km from the base
Technical data

Specifications

Prime contractor	INPE?
Platform
Mass at launch	115 kg
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime

the altitude control and orientation system components were made by Russia

Downlink: 2208 & 2267.515 MHz

Uplink: 401.635 & 2033.2 MHz


 SCD 2

General

Designation	25504 / 98060A
Launch date	23 Oct 1998
Country of origin	Brazil
Mission	Remote sensing
Perigee/Apogee	750 km
Inclination	25°
Period	100 min
Launch vehicle	Pegasus #24

Construction costed $11 million and launch is worth $15 million

Technical data

Specifications

Prime contractor	INPE?
Platform
Mass at launch	150 kg or 115 kg?
Mass in orbit
Dimension	1 m diameter, 1.45 m height
Solar array
Stabilization	spin stabilized
DC power	70 W
Design lifetime

Downlink: 2208 & 2267.515 MHz

Uplink: 401.635 & 2033.2 MHz

the main differences with SCD 1 are: Inclusion of a reaction wheel experiment, control of the spin rate by means of magnetic coils and a greater degree of brazilian made equipments.


 Score

Signal Communication by Orbiting Relay Experiment

General

Designation	00010 / 58006A
Launch date	18 Dec 1958
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	185/1484 km
Inclination	32.3°
Period	101.5 min
Launch vehicle	Atlas
Launch site	Cape Canaveral
Mass at launch	70 kg

Broadcast President Eisenhower Christmas wishes that had been recorded during 13 days.

End of life

Decay	21 Jan 1959


 Seasat

General

Designation	10967 / 78064A
Launch date	27 Jun 1978
Country of origin	United States
Mission	Remote sensing
Perigee/Apogee	761/764 km
Inclination	108°
Period	100.1 min
Launch vehicle	Atlas Agena D
Launch site	Vandenberg

Seasat was designed to demonstrate techniques for global monitoring of oceanographic phenomena and features, to provide oceanographic data, and to determine key features of an operational ocean-dynamics monitoring system. The major difference between Seasat and previous Earth observation satellites was the use of active and passive microwave sensors to achieve an all-weather capability.

Dedicated ocean monitoring satellite that carried the first spaceborne synthetic aperture radar (SAR) and other microwave instruments.

End of life

Out of service	10 Oct 1978 (106 days of returning data)
Cause	a short circuit drained all power from its batteries
External resources

http://www.belspo.be/telsat/seasat/samm_300.htm

Technical data

Specifications

Prime contractor	Lockheed
Platform	Agena
Mass at launch	2300 kg
Length	21 m
Stabilization	3 axis (momentum wheel/horizon sensing system)
Design lifetime	2 years

The second stage of the Atlas-Agena launch vehicle served as the satellite bus and provided attitude control, power, guidance, telemetry, and command functions. Attached to the Agena was a sensor module which carried the payload of five microwave instruments and their antennas. Together, the two modules were about 21 meters long with a maximum diameter of 1.5 m without appendages deployed. After burnout of the Agena stage and injection into orbit, Seasat-A weighed 2300 kg. In orbit the satellite appeared to stand on end with the sensor and communications antennas pointing toward Earth and the Agena rocket nozzle and solar panels pointing toward space.

SAR (Synthetic Aperture Radar)

Frequency	1.275 GHz (L-band)
Resolution	25 m
Swath width	100 km

Mission: deep ocean wave pattern imaggery, coastal sea/land interaction, ice and snow imagery

ALT (Radar Altimeter)

Frequency	Ku-band
Accuracy	10 cm

Mission: measure satellite altitude above sea surface, significant wave height at sub-satellite point, establish characteristics of marine geoid

SASS (Seasat-A Satellite Scatterometer) - Wind scatterometer

Frequency	1.275 GHz (L-band)
Accuracy	windspeed +/- 2 m/s; direction better than 20°

Mission: windspeed and direction

SMMR (Scanning Multichannel Microwave Radiometer) (passive)

Frequencies	6.6, 18, 37, 10.7 & 21 GHz (H & V polarization)
Swath width	600 km
Accuracy	ocean surface temperature 2 K ocean surface windspeed 2 m/s

Mission: ocean surface temperature and windspeed, water vapor, icecover, rain rate, propagation corrections for other instruments

VIRR (Visible and IR Radiometer)

Wavebands	0.25-0.73 µm 10.5-12.5 µm
Field of view	2-5 km
Swath width	1900 km

Mission: image feature identification in support of other instruments, thermal images of ocean

Downlink frequency: 2287.5 MHz


 Program: Secor

SEquential COllation of Range

Also called EGRS (Experimental Geodetic Research Satellite)

US army geodetic satellites for triangulation (early navigation).

17 to 20 kg, box shape


Program: Secor

Secor 01B

Secor 02

Secor 03

Secor 04

Secor 05

Secor 06

Secor 07

Secor 08

Secor 09

Secor 13


 Secor 01B

Also called EGRS 01

General

Designation	00729 / 64001C
Launch date	11 Jan 1964
Country of origin	United States
Mission	Scientific: geodesy
Perigee/Apogee	902/922 km
Inclination	69.9°
Period	103.3 min
Launch vehicle	Thor Agena
Launch site	Vandenberg


 Secor 02

Also called EGRS 2

General

Designation	01250 / 65017B
Launch date	11 Mar 1965
Country of origin	United States
Mission	Scientific: geodesy
Perigee/Apogee	296/1014 km
Inclination	90°
Period	97.9 min
Launch vehicle	Thor Ablestar
Launch site	Vandenberg
End of life

Decay	26 Feb 1968


 Secor 03

Also called EGRS 3

General

Designation	01208 / 65016E
Launch date	9 Mar 1965
Country of origin	United States
Mission	Scientific: geodesy
Perigee/Apogee	897/926 km
Inclination	70.1°
Period	103.2 min
Launch vehicle	Thor Agena
Launch site	Vandenberg


 Secor 04

Also called EGRS 4

General

Designation	01315 / 65027B
Launch date	3 Apr 1965
Country of origin	United States
Mission	Scientific: geodesy
Perigee/Apogee	1266/1311 km
Inclination	90.2°
Period	111.4 min
Launch vehicle
Launch site	Vandenberg


 Secor 05

Also called EGRS 5

General

Designation	01506 / 65063A
Launch date	10 Aug 1965
Country of origin	United States
Mission	Scientific: geodesy
Perigee/Apogee	1137/2416 km
Inclination	69.2°
Period	122.2 min
Launch vehicle	Scout #37


 Secor 06

Also called EGRS 6

General

Designation	02205 / 66051B
Launch date	9 Jun 1966
Country of origin	United States
Mission	Scientific: geodesy
Perigee/Apogee	168/3646 km
Inclination	90°
Period	125 min
Launch vehicle
Launch site	Vandenberg
End of life

Decay	6 Jul 1967


 Secor 07

Also called EGRS 7

General

Designation	02411 / 66077B
Launch date	19 Aug 1966
Country of origin	United States
Mission	Scientific: geodesy
Perigee/Apogee	3671/3700 km
Inclination	89.7°
Period	167.5 min
Launch vehicle
Launch site	Vandenberg
Technical data

Transmits on 136.800 MHz


 Secor 08

Also called EGRS 8

General

Designation	02520 / 66089B
Launch date	5 Oct 1966
Country of origin	United States
Mission	Scientific: geodesy
Perigee/Apogee	3673/3709 km
Inclination	90°
Period	167.6 min
Launch vehicle
Launch site	Vandenberg


 Secor 09

Also called EGRS 9

General

Designation	02861 / 67065A
Launch date	29 Jun 1967
Country of origin	United States
Mission	Scientific: geodesy
Perigee/Apogee	3792/3946 km
Inclination	90.1°
Period	172.2 min
Launch vehicle	Thor Burner
Launch site	Vandenberg


 Secor 13

Also called EGRS 13

General

Designation	03891 / 69037B
Launch date	14 Apr 1969
Country of origin	United States
Mission	Scientific: geodesy
Perigee/Apogee	1068/1126 km
Inclination	100°
Period	107.2 min
Launch vehicle	Thor Agena D
Launch site	Vandenberg
Technical data

Transmits on 136.800 MHz


 Seds 1

Small Expendable Deployer System

General

Designation	22582 / 93017B
Launch date	30 Mar 1993 at 03:29 UT
Country of origin	United States
Mission	Tether experiment
Operator	NASA
Perigee/Apogee	184/746 km
Inclination	34°
Period
Launch vehicle	Delta 2 #219
Launch site	Cape Canaveral LC17A
Mass at launch	23 kg

The system consisted of a small 10 kg deployer cylinder 33 cm long and a tiny 23 kg satellite (`end mass') of similar size. The satellite was connected to the cylinder by a rope made of Spectra-1000 which was 0.75 mm in diameter and 20 km long. The cylinder remained attached to the Delta second stage rocket in orbit.

Seds was developed and built by NASA-Marshall, the Harvard-Smithsonian Center for Astrophysics, and Tether Applications of San Diego, CA. The end mass was built by NASA-Langley.

End of life

Decay	30 Mar 1993
External resources

http://ixeab9.larc.nasa.gov/seds/


 Seds 2

Small Expendable Deployer System

General

Designation	23028 / 94016B
Launch date	10 Mar 1994 at 03:40 UT
Country of origin	United States
Mission	Tether experiment
Operator	NASA
Perigee/Apogee	347 / 352 km
Inclination	34.9°
Period
Launch vehicle	Delta 2 #226
Launch site	Cape Canaveral LC17
Mass at launch	23 kg

It is a package attached to the Delta second stage rocket which was to deploy a 20 km tether to compare actual tether dynamics with theoretical models. The end mass behaved as expected and unreeled in 1 h 48 min  to a maximum length of 19.8 km.

Unlike Seds 1 for which the tether was severed after deploy, the tether remained attached to the Delta rocket. The end mass mini-satellite transmitted for 10 hours. On 15 Mar 1995 Seds separated from the tether because of an impact and reentred.

The success of Seds 2 confirms that tether systems can be used to deploy sensors which require a particular orientation to the local vertical, such as atmospheric composition experiments.

End of life

Out of service	15 Mar 1994
Decay	8 May 1994
External resources

http://ixeab9.larc.nasa.gov/seds/


 Sedsat

Students for the Exploration and Development of Space Satellite, also called SO-33

General

Designation	25509 / 98061B
Launch date	24 Oct 1998
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	574/ 1078 km
Inclination	31.5°
Period	101 min
Launch vehicle	Delta 2 #261

Built by students at the University of Alabama's Huntsville campus.

Power problems started on 27 Oct 1998. Those were later solved but it was found the 2 receivers were not functional.

External resources

http://www.seds.org/sedsat/

http://seds.lpl.arizona.edu/seds/seds.html

Technical data

Specifications

Prime contractor	seds
Platform
Mass at launch	38 kg
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime
Mode A transponder

Uplink	145.915 to 145.975 MHz (2 Meter band) Modulation: SSB, CW, FM, AM
Downlink	29.350 to 29.420 Mhz (10 Meter Band) Modulation: SSB, CW, FM, AM AFSK 300 bps Hf Packet Compatible telemetry downlink
Mode L transponder

Uplink	1268.175 to 1268.250 MHz (23cm band) Modulation: FSK digital data at 9.6, 19.2, 38.4 and 56 kbit/sec
Downlink	437.850 to 438.000 MHz (70 cm band) Modulation: FSK digital data at 9.6, 19.2, 38.4 and 56 kbit/sec

Data Rate: 300 bits/sec AFSK packet data 9600 bits/sec or 57,600 bits/sec

RF output per transponder will be 3 watts average and 15 watts max


 SFU

Space Flyer Unit

General

Designation	23521 / 95011A
Launch date	17 Mar 1995
Country of origin	Japan
Mission	Scientific
Perigee/Apogee	467/496 km
Inclination	28.5°
Period	92 min
Launch vehicle	H2

SFU carried out materials processing, technology and astronomy experiments. It carried the 0.15 m liquid helium cooled IR Telescope in Space (IRTS), with near and mid infrared spectrometers; a biology experiment studying salamander eggs; an electron density experiment; materials processing furnaces; and technology experiments with solar arrays and an electric thruster. It also carried an experimental platform to test technology for the JEM Exposed Facility planned for the Space Station, and as such it is the first flight element of Japan's Station program.

End of life

Out of service	20 Jan 1996
Cause	Retrieved by STS 72

Downlink frequency: 2263.602 MHz

External resources

http://koala.astro.isas.ac.jp/irts/irts_E.html


 Shinsei

Means "new star"

General

Designation	05485 / 71080A
Launch date	28 Sep 1971
Country of origin	Japan
Mission	Scientific: ionosphere study
Perigee/Apogee	872/1866 km
Inclination	32.1°
Period	113.1 min
Launch vehicle	Mu 4S
Launch site	Kagoshima
Mass at launch	66 kg
External resources

http://www.isas.ac.jp/info/sat/shinsei-e3.html

Technical data

Transmits on 136.695 MHz


 Sich 1

General

Designation	23657 / 95046A
Launch date	31 Aug 1995 at 06:50 UT
Country of origin	Ukraine
Operator	National Space Agency of Ukraine (NKAU)
Mission	Remote sensing (Ocean-O1)
Perigee/Apogee	682/651 km
Inclination	82.5°
Period	98.7 min
Launch vehicle	Cyclone 3 #114

First Ukrainian satellite (although numerous Ukrainian-made satellite were launched before under the CIS flag)

Was launched with Fasat Alfa which failed to separate

Technical data

Specifications

Payload


 Sich 2

To be launched in 1996 by a Zenit 2 from Tyuratam


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 SICRAL

Sistema Italiana de Communicazione Riservente Allarmi

General

Designation
Launch date	initially planned in 1999
Country of origin	Italy
Mission	military: telecommunications
Geostationary orbit	?
Launch vehicle	Ariane 5
Launch site

Should weigh 2500 kg at lift-off. Prime contractor is Alenia Spazio

It will provide secure communications for Italy's Ministry of Defense and the country's civil security forces, catering for domestic needs and operations abroad.


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Signe_3
 Signe 3

General

Designation	10064 / 77049A
Launch date	17 Jun 1977
Country of origin	France
Mission	Scientific: gamma-ray astronomy
Perigee/Apogee	449/522 km
Inclination	50.7°
Period	94.3 min
Launch vehicle	Cosmos C
Launch site	Tyuratam
Mass at launch	102 kg
End of life

Decay	20 Jun 1979


 Sinosat 1

Also called Sinostar

General

Designation	25404 / 98044A
Launch date	18 Jul 1998
Country of origin	China
Mission	Telecommunications
Geostationary orbit	110.5°E
Launch vehicle	Long March 3B #51

Operated by Sino Satellite Communications. The satellite is insured for $350 million (by China Space Pool). Options for 2 other satellites are available. Project financed by CASC and DASA.

Operational since 4 Dec 1998

Technical data

EIRP coverage (dBW)

C-band

Ku-band

Specifications

Prime contractor	EuraSpace (with Aerospatiale as lead)
Platform	Spacebus-3000
Mass at launch	2820 kg
Mass in orbit	1600 kg
Dry mass	1160 kg
Dimension
Solar array	26.3 m span
Stabilization	3-axis
DC power	EOL: 5300 W (payload power: 3913 W)
Design lifetime	15 years

Has 2 deployable 1.6 and 1.8 m diameter antennas and a fixed 1 m antenna.

EurasSpace had to ask Aerospatiale to handle the design because of the failure of EurasSpace's first satellite failure, Dong Fang Hong 41. Sinosat 2 should be the real second EurasSpace satellite.

C-band

Main transponders	23 + 1 (crosslink 54 MHz)
Backup transponders	8
Power	21 W
Bandwidth	36 MHz
Coverage	China down to Indonesia
EIRP max	39.5 dBW
G/T max	0 dB/K
Polarization	linear H/V
Frequencies	uplink: 5.845-6.425 GHz downlink: 3.625-4.200 GHz telemetry in transfer orbit: 4.193 & 4.198 GHz

Command: 6.412 & 6.418 GHz

C-band transponder frequency chart (GHz)

Horizontal Uplink	Horizontal Downlink	Transponder	Vertical Downlink	Vertical Uplink
	3.700	1B		5.925
5.945		1A	3.720
	3.740	2B		5.965
5.985		2A	3.760
	3.780	3B		6.005
6.025		3A	3.800
	3.820	4B		6.045
6.065		4A	3.840
	3.860	5B		6.085
6.105		5A	3.880
	3.900	6B		6.125
6.145		6A	3.920
	3.940	7B		6.165
6.185		7A	3.960
	3.980	8B		6.205
6.225		8A	4.000
	4.020	9B		6.245
6.265		9A	4.040
	4.060	10B		6.285
6.305		10A	4.080
	4.100	11B		6.325
6.345		11A	4.120
	4.151	12B (54 MHz)		6.376
6.385		12A	4.160
Ku-band

Main transponders	14 + 1 (crosslink)
Backup transponders	4
Power	97 W
Bandwidth	54 MHz
Coverage	China, Hong Kong and Taiwan
EIRP max	54.5 dBW
G/T max	10 dB/K
Polarization	linear H/V
Frequencies	uplink: 14-14.5 GHz downlink: 12.25-12.75 GHz beacons: 12.260 & 12.26040 GHz

includes a pair of C- Ku- band crosslinked channels

Ku-band transponder frequency chart (GHz)

Horizontal Uplink	Horizontal Downlink	Transponder	Vertical Downlink	Vertical Uplink
14.070		1A	12.320
	12.350	1B		14.100
14.130		2A	12.380
	12.410	2B		14.160
14.190		3A	12.440
	12.470	3B		14.220
14.250		4A	12.500
	12.530	4B		14.280
14.310		5A	12.560
	12.590	5B		14.340
14.370		6A	12.620
	12.650	6B		14.400
14.430		7A	12.680
	12.710	7B		14.460


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Sinosat 1's C-band EIRP


Sinosat 1's Ku-band EIRP


 Program: Sirio

Satellite Italiano Ricerca Industriale Operativa

Italian program


Program: Sirio

Sirio 1

Sirio 2


 Sirio 1

General

Designation	10294 / 77080A
Launch date	25 Aug 1977
Country of origin	Italy
Mission
Geostationary orbit
Launch vehicle	Thor Delta #133
Launch site	Cape Canaveral
Mass at launch	218 kg or 398?
End of life

Out of service	yes


 Sirio 2

End of life

Out of service	10 Sep 1982
Cause	Launch failure of Ariane L05

420 kg satellite aimed for meteorology


 Program: Sirius

Swedish telecommunication program operated by NSAB.

NSAB is owned 37.5% by Teracom, 37.5% by Rymdbolaget and 25% by Tele Danmark. Teracom is in charge of the exploitation


Program: Sirius

Sirius 1

Sirius 2

Sirius 3


 Sirius 1

General

Old name	BSB 1
Country	Sweden
Mission	Telecommunications
Geostationary orbit	5.2°E
Technical data

EIRP coverage (dBW)

Specifications

Ku-band


Sirius 1's EIRP


 Sirius 2

Also called GE 1E

General

Designation	25049 / 97071A
Launch date	12 Nov 1997
Country of origin	Sweden
Operator	NSAB & GE Capital Satellites-Europe
Mission	Telecommunications
Geostationary orbit	4.8°E
Launch vehicle	Ariane V102

Operated by NSAB a joint venture by Teracom Svensk Rundradio and Swedish Space Corporation, and GE Capital Satellites-Europe, a subsidiary of GE Capital Satellites International itself a subsidiary of GE Americom

Became operational in mid-Dec 1997.

Technical data

EIRP coverage (dBW)

Europe

Scandinavia

Northern and Central Europe

G/T coverage (dB/K)

Europe

Northern and Central Europe

Specifications

Prime contractor	Aerospatiale
Platform	Spacebus-3000B
Mass at launch	2930 kg
Mass in orbit	1250 kg
Dimension	1.8 x 2.3 x 2.86 m
Solar array	26.3 m span
Stabilization	3 axis
DC power	BOL: 6100 W EOL: 5845 W
Design lifetime	15 years
Beacon	11.70685 GHz H

two 1.8 m fixed antennas and one 1.4 m steerable antenna

Beacons: 11.70685 GHz V & 11.74950 GHz H

Ku-band for NSAB: Scandinavia (BSS)

Main transponders	13
Backup transponders	20-for-16
Power	52 W
Bandwidth	33 MHz
Coverage & EIRP max	Scandinavia: 60 dBW
Polarization	linear V
Frequencies	Uplink: 17.3 - 18.1 GHz Downlink: 11.7 - 12.5 GHz
Ku-band for GE: Europe (BSS)

Main transponders	13
Backup transponders	20-for-16
Power	72 W
Bandwidth	33 MHz
Coverage & EIRP max	Europe: 50 dBW
G/T max	4.5 dB/K
Polarization	linear H
Frequencies	Uplink: 17.3 - 18.1 GHz Downlink: 11.7 - 12.5 GHz
Ku-band for North & Central Europe (FSS)

Main transponders	3 (NSAB) + 3 (GE)
Backup transponders	20-for-16
Power	88 W
Bandwidth	36 MHz
Coverage & EIRP max	Northern and Central Europe: 48 dBW
G/T max	4.5 dB/K
Polarization	linear
Frequencies	Uplink: 14.0 - 14.25 GHz Downlink: 12.5 - 12.75 GHz
Transponder frequency chart (GHz)

Horizontal  uplink	Horizontal downlink	Transponder	Vertical downlink	Vertical  uplink	Beam
	11.72748	1		17.32748	Europe
17.34666		2	11.74666		Scandinavia
	11.76684	3		12.36584	Europe
17.50010		10	11.90010		Scandinavia
	12.07272	19		12.67272	Europe
17.69190		20	12.09190		Scandinavia
	12.11108	21		17.71108	Europe
17.73026		22	12.13026		Scandinavia
	12.14944	23		17.74944	Europe
17.76862		24	12.16862		Scandinavia
	12.18780	25		17.78780	Europe
17.80698		26	12.20698		Scandinavia
	12.22616	27		17.82616	Europe
17.84534		28	12.24534		Scandinavia
	12.22616	29		17.86452	Europe
17.88370		30	12.28370		Scandinavia
	12.30288	31		17.90288	Europe
17.92206		32	12.32206		Scandinavia
	12.34124	33		17.94124	Europe
17.96042		34	12.36042		Scandinavia
	12.37960	35		17.97960	Europe
17.99878		36	12.39878		Scandinavia
	12.41796	37		18.01790	Europe
18.03714		38	12.43714		Scandinavia
	12.45632	39		18.05632	Europe
18.07550		40	12.47550		Scandinavia
		3	12.60416		North/Central
		4	12.64582		North/Central
		5	12.68748		North/Central
	12.64582	10			North/Central
	12.68748	11			North/Central
	12.72914	12			North/Central


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Sirius 2's BSS European EIRP coverage


Sirius 2's BSS Scandinavian EIRP coverage


Sirius 2's FSS North/Central EIRP coverage


Sirius 2's BSS European G/T coverage


Sirius 2's FSS North/Central G/T coverage


 Sirius 3

General

Designation	25492 / 98056B
Launch date	5 Oct 1998
Country of origin	Sweden
Operator	NSAB
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V111
Location

Begin	End	Position
L: 5 Oct 1998		28°E (backup)
Oct 1999?		5°E

NSAB is leasing the satellite to Astra for 1 year

Technical data

EIRP coverage (dBW)

Specifications

Prime contractor	Hughes
Platform	HS-376HP
Mass at launch	1465 kg
Mass in orbit	815 kg
Dry mass	630 kg
Dimension	2.16 m diameter, 7.76 m height deployed
Solar array
Stabilization	spin stabilized
DC power	EOL: 1500 W
Design lifetime	12 years
Ku-band

Main transponders	15
Backup transponders	2
Power	44 W
Bandwidth	33 MHz
Coverage	Scandinavia
EIRP max	54 dBW
Polarization	linear
Frequencies	uplink: 17.3-18.1 GHz downlink: 11.7-12.5 GHz
Transponder frequency chart (GHz)

Horizontal downlink	Transponder	Vertical downlink
	4	11.78502
11.80420	5
	6	11.82338
11.84256	7
	8	11.83174
11.88092	9
	10	11.90010
11.91928	11
	12	11.93846
11.95764	13
	14	11.97682
11.99600	15
	16	12.01518
12.03736	17
	18	12.05354


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Sirius 3's BSS Scandinavian EIRP


 Skipper

General

Designation	23752 / 95072B
Launch date	28 Dec 1995 at 06:45 UT
Country of origin	United States
Mission	Scientific
Perigee/Apogee	804/813 km
Inclination	98.6°
Period	101 min
Launch vehicle	Molniya M
Launch site	Tyuratam
Mass at launch	257 kg
End of life

Out of service	28 Dec 1995
Cause	Failed after deployment because the solar panels were wired to discharge instead of charge.

Joint US-Russian satellite: Utah State University provided the forward instrument section an the Moscow Aviation Institute the satellite bus. Shape is a cylinder, 0.8 m diameter and 1.3 m long.

Utah State University's Space Dynamics laboratory in Logan, Utah is the prime contractor and has already conducted similar bow shock test with sub-orbital rockets in April 1990 and February 1991: Bow Shock Ultraviolet 1 and 2. These tests showed ultraviolet light are generated by the bow shock, but tests at higher altitudes and faster speeds needs to be done.

Skipper is to investigate bow shock emissions and aerothermal chemistry reactions produced in Earth's upper atmosphere by manoeuvering and re-entering missile warheads having velocity profiles similar to those expected from the next generation of fast-burning solid propellant missiles.  Skipper spacecraft is an orbital successor to the suborbital Bow Shock 1 and 2 sounding rocket missions which revealed unexpected date on re-entering warhead signatures and which now require more extended experiment and observation time provided by an orbital test.

Spacecraft will carry instrumentation including three scanning spectrometers, a hydrazine thruster system and a photometer plus instrumentation support systems, attitude control and manoeuvering thrusters and science and engineering telemetry to acquire data from higher altitudes and velocities where significant changes in physical processes associated with re-entering warheads are encountered.

On subsequent revolutions perigee will be gradually reduced through controlled manoeuvres to between 120 km and 130 km, spacecraft traverses through very low perigees being observed to simulate warhead re-entries into Earth's upper atmosphere.  Perigee will be decreased until atmospheric drag threatens to initiate re-entry.


Skybridge
 Program: Skybridge

Formely known as Sativod

Project led by Alcatel. It aims to place 80 LEO satellites in orbit to provide high speed data communications. Financing needs: $3.5 billion  Partners are Loral Space & Communications, Toshiba, Spar Aerospace Ltd, Aerospatiale, Ste Regionale d'Investissements de Wallonie (Belgium), Mitsubishi Electric Corp and Sharp Corp of Japan. A strategic partnership was drawn with SS/L's Cyberstar The French space agency CNES should also join.

The program should be operational in 2001 (32 satellites)

A unique feature of the SkyBridge system is its ability to share spectrum with existing geostationary (GEO) satellite systems in the Ku-band. Through technological and system design breakthroughs achieved by Alcatel engineers, there will be no interference to those GEO systems. ITU approved this technology on 19 Jun 1999.

The SkyBridge satellite in low earth orbit (LEO) will shut off transmissions when passing through the area where GEO satellites are transmitting.  This shut-off of transmissions will not affect the user, because the traffic will be "handed" over to another satellite in the SkyBridge constellation.  The use of a LEO constellation also assures real-time transmissions, without the delays that affect transmissions to GEO satellites, which are located much farther away from the Earth.

Orbit: 1450 km  ATM-based  16 kbps to 60 mbps for downlink, 16 kbps to 2 mbps for uplink. Uplink: 12.75-13.25 GHz + 13.75-14.50 GHz + 17.30-18.10 GHz  Downlink: 10.70-12.75 GHz

Satellites should weigh 4000 kg. bent-pipe mode. 4 solar panels (cross). a dozen of deployable antennas

To reduce space debris the satellite as planned to be sent in 2000 km order after their useful lifetime.

External resources

http://www.skybridgesatellite.com/


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 Program: Skynet

English military program

Skynet 5 is currently under study. It would be developed with the US (Lockheed Martin involved) and compatible with US communication systems. Would be based on the A2100 bus and would operate in the EHF, SHF and UHF bands.


Program: Skynet

Skynet 1A

Skynet 1B

Skynet 2A

Skynet 2B

Skynet 4A

Skynet 4B

Skynet 4C

Skynet 4D

Skynet 4E

Skynet 4F


Skynet 4's (A, B, C) specifications

Prime contractor	British Aerospace (now MMS)
Platform	ECS
Mass at launch	1430 kg
Mass in orbit	770 kg
Payload mass	225 kg
Length	2.2 m
Width
Height	2.3 m
Solar array	16 m span
Stabilization	3 axis
DC power	1500 W
Design lifetime	7 years


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Skynet 4's (A, B, C) UHF-band (250-315 MHz)

Main transponders	2
Backup transponders
Power	40 W
Bandwidth	25 KHz
Coverage	Europe
EIRP max


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Skynet 4's (A, B, C) X-band

Main transponders	4
Backup transponders
Power	40 W
Bandwidth	60 and 135 MHz
Coverage	Global
EIRP max
Polarization
Frequencies	Downlink: 7.23-7.75 GHz


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Skynet 4's (A, B, C) EHF-band (42 GHz)

Main transponders	1
Backup transponders
Power
Bandwidth
Coverage
EIRP max
Polarization


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Skynet 4's (D, E, F) specifications

Prime contractor	MMS
Platform	ECS
Mass at launch	1500 kg
Mass in orbit	830 kg
Dry mass	760 kg
Payload mass	275 kg
Dimension	1.45 x 1.76 x 1.91 m at launch
Solar array	16 m span
Stabilization	3-axis
DC power	1800-2000 W
Design lifetime	7 years

has a Thiokol Star 30 solid apogee motor


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Skynet 4's (D, E, F) UHF-band (254-318 MHz)

Main transponders	2
Backup transponders
Power	50 W
Bandwidth	25 KHz
Coverage	Europe
EIRP max


Skynet 4's (D, E, F) X-band

Main transponders	4
Backup transponders
Power	50 W
Bandwidth	60 and 125 MHz
Coverage	Global
EIRP max
Polarization
Frequencies	Downlink: 7.23-7.75 GHz


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Skynet 4's (D, E, F) EHF-band (42 GHz)

Main transponders	1
Backup transponders
Power
Bandwidth
Coverage	steerable
EIRP max
Polarization


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 Skynet 1A

General

Designation	04250 / 69101A
Launch date	22 Nov 1969
Country of origin	United Kingdom
Mission	Military: telecommunications
Geostationary orbit	see below
Launch vehicle	Thor Delta #74
Launch site	Cape Canaveral
Mass at launch	125 kg
End of life

Out of service	yes


 Skynet 1B

General

Designation	04493 / 70062A
Launch date	19 Aug 1970
Country of origin	United Kingdom
Mission	Military: telecommunications
Geostationary orbit	n/a
Launch vehicle	Thor Delta #80
Launch site	Cape Canaveral
End of life

Out of service	19 Aug 1970
Cause	Remained on transfert orbit


 Skynet 2A

General

Designation	07096 / 74002A
Launch date	19 Jan 1974
Country of origin	United Kingdom
Mission	Military: telecommunications
Geostationary orbit	n/a
Launch vehicle	Thor Delta #100
Launch site	Cape Canaveral
End of life

Out of service	25 Jan 1974
Cause	Placed on a bad orbit (96 km x 3406 km x 37.6°)


 Skynet 2B

General

Designation	07547 / 74094A
Launch date	23 Nov 1974
Country of origin	United Kingdom
Mission	Military: telecommunications
Geostationary orbit	42°E
Launch vehicle	Thor Delta #105
Launch site	Cape Canaveral
Mass at launch	235 kg
End of life

Out of service	yes


 Skynet 4A

General

Designation	20401 / 90001A
Launch date	1 Jan 1990
Country of origin	United Kingdom
Mission	Military: telecommunications
Geostationary orbit	see below
Launch vehicle	Titan 3 #153
Location

Begin	End	Position
L: 1 Jan 1990		5°E
Feb 1995		34°W, inclined
Technical data

Specifications

UHF-band

X-band

EHF-band


 Skynet 4B

General

Designation	19687 / 88109A
Launch date	11 Dec 1988
Country of origin	United Kingdom
Mission	Military: telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V27
Location

Begin	End	Position
L: 11 Dec 1988		7°E
Feb 1995	Jun 1998	53°E, inclined
End of life

Out of service	mid-Jun 1998
Cause	deorbited
Technical data

Specifications

UHF-band

X-band

EHF-band


 Skynet 4C

General

Designation	20776 / 90079A
Launch date	30 Aug 1990
Country of origin	United Kingdom
Mission	Military: telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V38
Location

Begin	End	Position
L: 30 Aug 1990
Feb 1995		1.1°W, inclined
Technical data

Specifications

UHF-band

X-band

EHF-band


 Skynet 4D

General

Designation	25134 / 98002A
Launch date	10 Jan 1998
Country of origin	United Kingdom
Mission	Military: telecommunications
Geostationary orbit	see below
Launch vehicle	Delta 2 #252
Location

Begin	End	Position
L: 10 Jan 1998	Apr 1998	5°E
Jun 1998	Jul 1999	53°E
Technical data

Specifications

UHF-band

X-band

EHF-band

The Skynet 4D, E & F are modified & enhanced satellites. They have steerable spot beam SHF antennas and more power.


 Skynet 4E

General

Designation	25639 / 99009B
Launch date	26 Feb 1999
Country of origin	United Kingdom
Mission	Military: telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V116
Location

Begin	End	Position
L: 26 Feb 1999	Jun 1999	5°E
Jul 1999		52°E
Technical data

Specifications

UHF-band

X-band

EHF-band


 Skynet 4F

General

Designation
Launch date	initially planned in 1999
Country of origin	United Kingdom
Mission	Military: telecommunications
Geostationary orbit	1°W
Launch vehicle	Ariane
Launch site

Contract value: £130 million including delivery-in-orbit of the satellite, with Ariane launch and operational control and in-orbit testing before turnover.

Technical data

Specifications

UHF-band

X-band

EHF-band

Equipped with Fokker-made solar arrays which might have a defect.


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 SME

Solar Mesosphere Explorer

General

Designation	12887 / 81100A
Launch date	6 Oct 1981
Country of origin	United States
Mission	Scientific: high atmosphere study
Perigee/Apogee	335/337 km
Inclination	97.6°
Period	91.3 min
Launch vehicle	Thor Delta #157
Launch site	Vandenberg
Mass at launch	437 kg
End of life

Decay	5 Mar 1991


 SMM

Solar Maximum Mission, also called Solmax

General

Designation	11703 / 80014A
Launch date	14 Feb 1980
Country of origin	United States
Mission	Scientific: Sun observation
Perigee/Apogee	405/408 km
Inclination	28.5°
Period	92.7 min
Launch vehicle	Thor Delta #151
Launch site	Cape Canaveral
Mass at launch	2315 kg

Studied solar eruption in the year of the most important solar activity. First use of the MultiMission Spacecraft bus

Its the first satellite repared in orbit by the shuttle (STS 11)

End of life

Decay	2 Dec 1989
External resources

http://trmm.gsfc.nasa.gov/trmm_office/index.html


 Program: SMS

Synchronous Meteorological Satellite

American meteorological program that was followed by GOES


Program: SMS

SMS 1

SMS 2


 SMS 1

General

Designation	07298 / 74033A
Launch date	17 May 1974
Country of origin	United States
Mission	Meteorology
Geostationary orbit	see below
Launch vehicle	Thor Delta #102
Launch site	Cape Canaveral
Mass at launch	627 kg

First meteorological geostationary satellite. Used for the Gate experiment: covered the Atlantic and Eastern United States

Location

Begin	End	Position
L: 17 May 1974		45°W
		75°W
1980		132°W
End of life

Out of service	yes
External resources

http://www.met.fsu.edu/explores/Guide/Smsgoes_Html/sms1.html


 SMS 2

General

Designation	07648 / 75011A
Launch date	6 Feb 1975
Country of origin	United States
Mission	Meteorology
Geostationary orbit	see below
Launch vehicle	Thor Delta #108
Launch site	Cape Canaveral
Mass at launch	627 kg
Location

Begin	End	Position
L: 6 Feb 1975		125°W
1980		75°W
End of life

Out of service	yes
External resources

http://www.met.fsu.edu/explores/Guide/Smsgoes_Html/sms2.html


 SNOE

Student Nitric Oxide Explorer, also called STEDI 1 and UNEX 01; pronounced "snowy"

General

Designation	25233 / 98012A
Launch date	26 Feb 1998
Country of origin	United States
Mission	Scientific:
Perigee/Apogee	536/580 km
Inclination	97.7°
Period	95.8 min
Launch vehicle	Pegasus XL #20

Built at the University of Colorado's Laboratory for Atmospheric Research and Space Physics. It will analyse and measure the contributions of nitric oxide from the Sun and magnetoshpere to the lower atmosphere. First satellite of the Student Explorer Demonstration Initiative program.

Worth $4.4 million

External resources

http://maia.colorado.edu/snoe/

Technical data

Specifications

Prime contractor
Platform
Mass at launch	132 kg
Mass in orbit
Dimension	99 x 91 cm
Solar array
Stabilization
DC power	35 W consumption
Design lifetime

It carries 3 instruments: an ultraviolet spectrometer to measure nitric oxide altitude profiles, a two-channel auroral photometer to measure auroral emissions beneath the spacecraft, and a five-channel solar soft X-ray photometer.

downlink: 2272.9 MHz

downlink rate: 128 kbps


 Solar A

Also called Yohkoh

General

Designation	21694 / 91062A
Launch date	30 Aug 1991
Country of origin	Japan
Mission
Perigee/Apogee	516/754 km
Inclination	31.3°
Period	97.4 min
Launch vehicle	Mu 3S 2
Launch site	Kagoshima


 Program: Solidaridad

Mexican telecommunication program operated by Satmex. Replaces Morelos

The Movisat network is composed of a band L transponder and a Ku band transponder in each Solidaridad satellite.


Program: Solidaridad

Solidaridad 1

Solidaridad 2


Solidaridad's specifications

Prime contractor	Hughes
Platform	HS-601
Mass at launch	2740 kg
Mass in orbit	1650 kg
Dimension	2.27 x 2.27 x 2.27 m
Solar array	18.3 m span
Stabilization	3 axis
DC power	3300 W
Design lifetime	14 years


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Solidaridad's L-band

Main transponders	1
Backup transponders
Power	100 W
Bandwidth	34 MHz
Coverage
EIRP max	45 dBW
Polarization	RHCP


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Solidaridad's C-band

Main transponders	18
Backup transponders
Power	10 W (36 MHz) 14 W (72 MHz)
Bandwidth	12 transponders of 36 MHz 6 transponders of 72 MHz (on spot 1)
Coverage & EIRP max	Spot 1: 40.5 dBW Spot 2: 37.5 dBW Spot 3: 37.5 dBW
G/T max	2.9 dB/K
Polarization	linear


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Solidaridad's Ku-band

Main transponders	16
Power	42.5 W (TWTA)
Bandwidth	54 MHz
Coverage & EIRP max	Spot 4: 47 dBW Spot 5: 46 dBW Spot 6: 45.5 dBW
G/T max	3.7
Polarization	linear


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 Solidaridad 1

General

Designation	22911 / 93073A
Launch date	20 Nov 1993
Country of origin	Mexico
Mission	Telecommunications
Geostationary orbit	109.2°W
Launch vehicle	Ariane V61

Experienced a power failure on 28 Apr 1999. The service was restaured within 36 hours. An other failure occured a few days later, fixed withing hours. An extensive report was requested. It was then known the the primary Satellite Control Processor (SCP) had failed.

Technical data

Specifications

L-band

C-band

Ku-band

EIRP coverage (dBW)

C-band

Ku-band


 Solidaridad 2

General

Designation	23313 / 94065A
Launch date	8 Oct 1994
Country of origin	Mexico
Mission	Telecommunications
Geostationary orbit	113°W
Launch vehicle	Ariane V68
Technical data

Specifications

L-band

C-band

Ku-band

EIRP coverage (dBW)

C-band

Ku-band


Solidaridad's C-band EIRP


Solidaridad's Ku-band EIRP


 Program: Solrad

American astronomy program operated by US Navy and NASA

External resources

http://heasarc.gsfc.nasa.gov/Images/pretty_pictures_solrad.html


Program: Solrad

Solrad 01

Solrad 03

Solrad 06A

Solrad 06B

Solrad 07A

Solrad 07B

Solrad 09

Solrad 10

Solrad 11A

Solrad 11B


 Solrad 01

Also called GREB

General

Designation	00046 / 60007B
Launch date	22 Jun 1960
Country of origin	United States
Mission	Scientific
Perigee/Apogee	590/940 km
Inclination	66.7°
Period	100.1 min
Launch vehicle	Thor Ablestar
Launch site	Cape Canaveral


 Solrad 03

Also called Injun 1

General

Designation	00117 / 61015B
Launch date	29 Jun 1961
Country of origin	United States
Mission	Scientific: ionosphere study
Perigee/Apogee	869/991 km
Inclination	66.8°
Period	103.6 min
Launch vehicle	Thor Ablestar
Launch site	Cape Canaveral


 Solrad 06A

General

Designation	00599 / 63021C
Launch date	15 Jun 1963
Country of origin	United States
Mission
Perigee/Apogee	170/869 km
Inclination	69.9°
Period	95.1 min
Launch vehicle	Thor Agena D
Launch site	Vandenberg
End of life

Decay	1 Aug 1963


 Solrad 06B

Also called GREB 6

General

Designation	01271 / 65016A
Launch date	9 Mar 1965
Country of origin	United States
Mission
Perigee/Apogee	895/926 km
Inclination	70.1°
Period	103.2 min
Launch vehicle	Thor Agena D
Launch site	Vandenberg


 Solrad 07A

General

Designation	00730 / 64001D
Launch date	11 Jan 1964
Country of origin	United States
Mission	Scientific
Perigee/Apogee	900/921 km
Inclination	69.9°
Period	103.2 min
Launch vehicle	Thor Agena
Launch site	Vandenberg


 Solrad 07B

General

Designation	01291 / 65016D
Launch date	9 Mar 1965
Country of origin	United States
Mission	Scientific
Perigee/Apogee	900/928 km
Inclination	70.1°
Period	103.3 min
Launch vehicle	Thor Agena D
Launch site	Vandenberg


 Solrad 09

Also called Explorer 37

General

Designation	03141 / 68017A
Launch date	5 Mar 1968
Country of origin	United States
Mission	Scientific: observation if the sun
Perigee/Apogee	353/433 km
Inclination	59.3°
Period	92.4 min
Launch vehicle	Scout #60
End of life

Decay	16 Nov 1990


 Solrad 10

Also called Explorer 44

General

Designation	05317 / 71058A
Launch date	8 Jul 1971
Country of origin	United States
Mission	Scientific: observation if the sun
Perigee/Apogee	433/632 km
Inclination	51.1°
Period	95.2 min
Launch vehicle	Scout #74
End of life

Decay	15 Dec 1979


 Solrad 11A

General

Designation	08748 / 76023C
Launch date	15 Mar 1976
Country of origin	United States
Mission	Scientific
Perigee/Apogee	118383/119180 km
Inclination	25.7°
Period	7344.3 min
Launch vehicle	Titan 3 #93


 Solrad 11B

General

Designation	08749 / 76023D
Launch date	15 Mar 1976
Country of origin	United States
Mission	Scientific
Perigee/Apogee	115720/116645 km
Inclination	25.6°
Period	7116.7 min
Launch vehicle	Titan 3 #93


 Solwind

Also called P78-1

General

Designation	11278 / 79017A
Launch date	24 Feb 1979
Country of origin	United States
Mission	Scientific: high atmosphere study
Perigee/Apogee	310/317 km
Inclination	97.8°
Period	90.8 min
Launch vehicle	Atlas F
Launch site	Vandenberg
End of life

Decay	20 Jul 1992
External resources

http://lasco-www.nrl.navy.mil/solwind.html


Program: Spacenet
 Spacenet

American telecommunication program operated by GE Spacenet, a subsidiary of GE Americom


Program: Spacenet

Spacenet 1

Spacenet 2

Spacenet 3

Spacenet 3R

Spacenet 4 (ASC 2)


Spacenet's specifications

Prime contractor	GE Astro Space
Platform	GE 3000
Mass at launch	1195 kg
Mass in orbit	692 kg
Dimension	1.63 x 1.32 x 0.99 m
Solar array	14.33 m span
Stabilization	3 axis
DC power	BOL: 1530 W
Design lifetime	10 years


Spacenet's C-band

Main transponders	12+6
Backup transponders	2+1
Power	(12+2) transponders of 8.5 W (TWTA) (6+1) transponders of 16 W (TWTA)
Bandwidth	8.5 W transponders: 36 MHz 16 W transponders: 72 MHz
Coverage
EIRP max	36 dBW
Polarization	linear H/V


Spacenet's Ku-band

Main transponders	6
Backup transponders	1
Power	16 W (TWTA)
Bandwidth	72 MHz
Coverage	CONUS
EIRP max	44 dBW
Polarization	linear H


 Spacenet 1

General

Designation	14985 / 84049A
Launch date	23 May 1984
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V09

Was sold by GTE Spacenet to the Chinese and became Chinasat 5. Then the Chinese found an arrangement with Intelsat for 50% of it's capacity. At the same time China provided a Chinese orbital slot at 110.5°E for Intelsat 805.

Location

Begin	End	Position
L: 23 May 1984		102°W
< May 1992	May 1992 >	120°W
Feb 1995		115.5°E
Technical data

C-band EIRP coverage (dBW)

Specifications

C-band

Ku-band

C-band transponder frequency chart

Ku-band transponder frequency chart (GHz)

Horizontal Downlink	Transponder	Vertical Uplink
11.740	19	14.040
11.820	20	14.120
11.900	21	14.200
11.980	22	14.280
12.060	23	14.360
12.140	24	14.440


Spacenet 1's EIRP


 Spacenet 2

Also called Satcom SN2

General

Designation	15385 / 84114A
Launch date	10 Nov 1984
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V11

Went inclined after 30 Apr 1997

Location

Begin	End	Position
L: 10 Nov 1984	Jul 1997	69°W
Sep 1997	May 1998	115.5°E
End of life

Out of service	May 1998
Cause	reached end of life
Technical data

C-band EIRP coverage (dBW)

Specifications

C-band

Ku-band

C-band transponder frequency chart

Ku-band transponder frequency chart (GHz)

Horizontal Downlink	Transponder	Vertical Uplink
11.740	19	14.040
11.820	20	14.120
11.900	21	14.200
11.980	22	14.280
12.060	23	14.360
12.140	24	14.440


Spacenet 2's C-band EIRP


 Spacenet 3

End of life

Out of service	13 Sep 1985
Cause	Launch failure: Ariane V15
Technical data

Specifications

C-band

Ku-band


 Spacenet 3R

General

Designation	18951 / 88018A
Launch date	11 Mar 1988
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V21
Location

Begin	End	Position
L: 11 Mar 1988	Sep 1997	87°W
Oct 1997		83°W
Technical data

EIRP coverage (dBW)

C-band, 36 MHz transponders

C-band, 72 MHz transponders

Ku-band, East and West spots

Specifications

C-band

Ku-band

C-band transponder frequency chart

Carries one L-band transponder previously used by Qualcomm Inc. for a localization service. Now and since 1993 Mobile Datacom Corporation has been leasing the transponder.

Ku-band transponder frequency chart (GHz)

Horizontal Downlink	Transponder	Vertical Uplink
11.740	19	14.040
11.820	20	14.120
11.900	21	14.200
11.980	22	14.280
12.060	23	14.360	West spot
12.140	24	14.440	East spot


Spacenet 3R's C-band 36 MHz EIRP


Spacenet 3R's C-band 72 MHz EIRP


Spacenet 3R's Ku-band EIRP


C-band frequency chart (Spacenet)
 C-band frequency chart (Spacenet) (GHz)

Vertical Uplink	Horizontal Downlink	Transponder	Channel	Vertical Downlink	Horizontal Uplink
	3.720	1	1		5.945
5.965		13L	2	3.740
	3.760	2	3		5.985
6.005		13U	4	3.780
	3.800	3	5		6.025
6.045		14L	6	3.820
	3.840	4	7		6.065
6.085		14U	8	3.860
	3.880	5	9		6.105
6.125		15L	10	3.900
	3.920	6	11		6.145
6.125		15U	12	3.940
	3.960	7	13		6.185
6.205		16L	14	3.980
	4.000	8	15		6.225
6.245		16U	16	4.020
	4.040	9	17		6.265
6.285		17L	18	4.060
	4.080	10	19		6.305
6.325		17U	20	4.100
	4.120	11	21		6.345
6.365		18L	22	4.140
	4.160	12	23		6.385
6.405		18U	24	4.180


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 Program: Spaceway

Also called Galaxy/Spaceway

HCI program made of GEO Ka-band satellite payloads. Hughes proposes to offer services such as direct-to-home services and high speed personal computer access to the Internet and on-line services, telephony, narrow-band data, high-speed data, videoconferencing, high capacity two-way communications. Cost: $6.2 billion

In May 1997 FCC approved the Ka-band usage at the following locations: 101°W, 99°W, (67°W,) 49°W, 25°E, (36°E, 40°E, 48°E,) 54°E, 101°E, 111°E, (124.5°E, 149°E,) 164°E (and 173°E). Use of inter satellite link was not approved, nor addition of Ku-band payloads, yet. 20 satellites were approved. Up to 4 satellites per slot. Each satellite should be able to process 2880 simplex T1 circuits simultaneously

In March 1999 Hughes announces it will invest $1.4 billion. Operations are scheduled to start in North America in 2002. The North American network will consist of two HS-702 satellites plus an in-orbit spare. On-board digital processing, packet switching and multiple spot beams

A second phase of the program is later planned, with non-geosynchronous satellites. 20 such satellites would operate from a medium orbit

External resources

http://www.spaceway.com

Technical data

Specifications

Prime contractor	Hughes
Platform	HS-702
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime	15 years
Ka-band

Main transponders	68
Backup transponders
Power
Bandwidth	64 x 125 MHz (user terminals) 4 x 250 MHz (gateway terminals)
Coverage	48 steerable spot beams (of 650 km diameter)
EIRP max	56 dBW
Polarization	linear H/V
Frequencies	Uplink: 28.35-28.60 and 29.25-30.0 GHz Downlink: 19.7-20.2 GHz

uplink: FDM/TDMA

downlink: TDM (92 Mbps)

Inter-satellite links


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 Program: Spartan

American scientific program. The satellites are reused to carry experiments in space with the Shuttle. 3-axis spacecrafts.

Spartan 203 was destroyed on STS 33, Spartan 202 (UV Stellar Astronomy) and 205 (Plasma Physics) were cancelled

External resources

http://SPARTANS.GSFC.NASA.GOV/


Program: Spartan

Spartan 101

Spartan 201-1

Spartan 201-2

Spartan 201-3

Spartan 201-4

Spartan 201-5

Spartan 204

Spartan 206

Spartan 207


 Spartan 101

General

Designation	15831 / 85048E
Launch date	20 Jun 1985
Country of origin	United States
Mission	Scientific: X-ray astronomy
Perigee/Apogee	359/395 km
Inclination	28.5°
Period	92.1 min
Launch vehicle	STS 25

High Energy Astrophysics (NRL)

End of life

Cause	Retrieved by the Shuttle
Decay	24 Jun 1985


 Spartan 201-1

General

Designation	22623 / 93023B
Launch date	11 Apr 1993 at 06:11 UT
Country of origin	United States
Mission	Scientific: high atmosphere and Sun study
Perigee/Apogee	291/298 km
Inclination	57°
Period	90.4 min
Launch vehicle	STS 56
Mass at launch	1290 kg

It carried an ultraviolet coronagraph and a white light coronagraph for studies of the Sun.

End of life

Cause	Retrieved by the Shuttle
Decay	13 Apr 1993


 Spartan 201-2

General

Designation	23253 / 94059B
Launch date	9 Sep 1994
Country of origin	United States
Mission	Scientific: Sun study
Perigee/Apogee	259/269 km
Inclination	56.9°
Period	89.5 min
Launch vehicle	STS 64

It carried optical instruments to measure the speed and acceleration of the solar wind in the corona.

End of life

Cause	Retrieved by the Shuttle
Decay	20 Sep 1994


 Spartan 204

General

Designation	23470 / 95004B
Launch date	7 Feb 1995 at 12:26 UT
Country of origin	United States
Mission	Scientific: UV astronomy
Perigee/Apogee	310/342 km
Inclination	51.6°
Period	91 min
Launch vehicle	STS 63

The spacecraft carried NRL's FUVIS Far Ultraviolet Imaging Spectrograph which will be used to study the Shuttle environment and make astronomical observations. This is the first Spartan mission to be sponsored by the USAF Space Test Program rather than NASA. It made about 40 hours of observation of Galactic dust clouds.

End of life

Cause	Retrieved by the Shuttle
Decay	9 Feb 1995


 Spartan 201-3

General

Designation	23668 / 95048B
Launch date	8 Sep 1995 at 16.43 UT
Country of origin	United States
Mission	Scientific: Sun study
Perigee/Apogee
Inclination
Period
Launch vehicle	STS 69
Mass at launch	2209 kg

Carried the IEH-1 (International EUV Hitchhiker) built by the Smithsonian Astrophysical Observatory. This includes a solar EUV telescope (SEH), and an Italian-US EUV telescope, UVSTAR, which will observe a variety of astronomical targets in the 500-1250A range. Prime target for this mission is Io plasma torus around Jupiter. Comet 6P/D'Arrest, currently near perihelion, may also be observed. UVSTAR has two 0.3 m telescopes.

The spacecraft also carried the GLO-3 airglow experiment in a canister and the CONCAP materials processing experiment in another canister.

End of life

Cause	Retrieved by the Shuttle
Reentry	18 Sep 1995


 Spartan 206

Also called OAST (Office of Aeronautical and Space Technology) Flyer

General

Designation	23763 / 96001B
Launch date	11 Jan 1996
Country of origin	United States
Mission	Scientific: Sun study
Perigee/Apogee	302/311 km
Inclination	28.5°
Period
Launch vehicle	STS 72

Carried an experiment to measure contamination caused by spacecraft outgassing, and a test of a laser-fired explosive separation device to make sure the device doesn't go off accidentally in sunlight. It also carried an amateur radio experiment.

End of life

Cause	Retrieved by the Shuttle
Reentry	20 Sep 1994


 Spartan 207

General

Designation	23871 / 96032B
Launch date	19 May 1996
Country of origin	United States
Mission	Inflatable Antenna Experiment
Perigee/Apogee	280/290 km
Inclination	39°
Period	90.1 min
Launch vehicle	STS 77

The IAE is an inflatable antenna 14 meters in diameter which is mounted on three 28m struts.  The struts are attached to the Spartan spacecraft, which were deployed and then recovered by the Shuttle.  Once in low-Earth orbit, the Spartan became a platform for the antenna which, once inflated in space, was roughly the size of a tennis court. An optical system surveyed the antenna and measured the accuracy of the surface at a variety of internal pressures and thermal conditions. The antenna was developed by L'Garde Inc., of Tustin, CA, a small aerospace business, and NASA's Jet Propulsion Laboratory (JPL) of Pasadena, CA, under NASA's In-Space Technology Experiments Program., or IN-STEP.

The IAE experiment is meant to lay the groundwork for future technology development in inflatable space structures, which will be launched and then inflated like a balloon on-orbit.  SP207/IAE will validate the deployment (inflation) and performance of a large inflatable antenna during a ninety-minute mission before jettisoning the antenna structure and recovering the Spartan spacecraft at mission end. The inflation process will be captured by the crew on the nearby Shuttle, using a variety of still cameras, a motion picture camera, and video cameras. The on-orbit performance of the antenna (surface accuracy) will be determined by illuminating the antenna surface with light panels mounted on the Spartan and capturing the resulting patterns on video recorders onboard the Spartan. These will be analyzed after the Spartan is returned to Earth by the Space Shuttle.

IAE was ejected from Spartan once the experiment has completed (just the Spartan carrier with the experiment recorders was returned to the cargo bay). This is the same carrier as for Spartan 201-2

End of life

Out of service	May 1996
Cause	Retrieved by NASA (IAE burned up into atmosphere on 22 May)
External resources

http://sspp.gsfc.nasa.gov/sp207.html


 Spartan 201-4

General

Designation	25062 / 97073B
Launch date	21 Nov 1997
Country of origin	United States
Mission	SOHO Calibration & Spartan Development
Perigee/Apogee	296 km
Inclination	28.5°
Period
Launch vehicle	STS 87
Mass at launch

Mission duration planned: 16 days  In fact the initial deployment failed (pre release activation was not done). The satellite could not be later released by lack of propellant on Columbia.

Worth $10 million

End of life

Out of service	21 Nov 1997
Cause	Retrieved by STS
External resources

http://SPARTANS.GSFC.NASA.GOV/201/


 Spartan 201-5

General

Designation	25521 / 98064C
Launch date	29 Oct 1998
Country of origin	United States
Mission	SOHO / Solar physics
Perigee/Apogee	550 km
Inclination	28.5°
Period	95.8 min
Launch vehicle	STS 95
Mass at launch	1360 kg

This is the re-flight of Spartan 201-4 which was not successful.

End of life

Out of service	7 Nov 1998
Cause	Retrieved by STS
External resources

http://SPARTANS.GSFC.NASA.GOV/201/


 Program: Spas

Shuttle PAllet Satellite

Reusable free-flying multi-purpose platform on which experiments can be carried into space by the space shuttle.


Program: Spas

Spas 1

Spas 2

Spas 3


Spas's specifications

Prime contractor	MBB
Stabilization	3 axis
Total system mass	3600 kg
Payload mass	2000 kg
Length in payload bay	1.7 m
Mission lifetime	4 to 10 days
Electrical energy	up to 70 kWh


Astro Spas's specifications

Prime contractor	MBB
Total system mass	3200-3600 kg
Payload mass	500-2000 kg
Length in payload bay	4.05 m
Width (basic system)	1.75 m
Width (with payload)	2-3 m
Height	4.05 m
Stabilization	3 axis
Mission lifetime	4 to 10 days
Electrical energy	110 kWh (batteries) 30-50 kWh (payload)
Frequency (to Shuttle)	S-band: 2.04885/2.2250 GHz to Shuttle: 16 kbps From Shuttle: 2 kbps


 Spas 1

General

Designation	14142 / 83059F
Launch date	18 Jun 1983
Country of origin	Germany
Mission	Scientific
Perigee/Apogee	295/300 km
Inclination	28.5°
Period	90.5 min
Launch vehicle	STS 07
End of life

Cause	Retrieved by the Shuttle
Decay	24 Jun 1983
Technical data

Specifications


 Spas 2

Also called IBSS

General

Designation	21244 / 91031B
Launch date	28 Apr 1991
Country of origin	United States
Mission	Scientific
Perigee/Apogee	245/255 km
Inclination	57°
Period	89.5 min
Launch vehicle	STS 39
End of life

Cause	Retrieved by the Shuttle
Decay	6 May 1991
Technical data

Specifications


 Spas 3

Also called Orfeus (Orbiting and Retrievable Far and Extreme UV Spectrometer)

General

Designation	22798 / 93058C
Launch date	12 Sep 1993
Country of origin	Germany
Mission	Scientific: Astronomy
Operator	DARA
Perigee/Apogee	301/331 km
Inclination	28.5°
Period	90.9 min
Launch vehicle	STS 51

The main instrument is the 1-meter Orfeus telescope with EUV (400-1150A) and far UV (900-1250A) spectrometers with high spectral resolution. A secondary experiment is the Princeton Interstellar Medium Absorption Profile Spectrograph which studied very fine structure in ultraviolet absorption lines caused by interstellar gas in stellar spectra.

End of life

Cause	Retrieved by the Shuttle
Decay	22 Sep 1993
Technical data

Specifications


 Spas 4

Also called Crista

General

Designation	23341 / 94073B
Launch date	4 Nov 1994
Country of origin	Germany
Mission	Scientific
Perigee/Apogee	296/310 km
Inclination	57°
Period	90.6 min
Launch vehicle	STS 66
Mass at launch	3500 kg

It carried spectraphotometers to monitor gases in the middle atmosphere and lower thermosphere.

End of life

Cause	Retrieved by the Shuttle
Decay	12 Nov 1994
Technical data

Specifications


 Program: Spot

Satellite Pour l'Observation de la Terre

French remote sensing program decided in 1978 by the French government after a refusal of the ESA. Belgium and Sweden participated. Data is commercialized by a private company: Spot Image. Applications include geological, petroleum and mining research, cartography, agricultural forcasting and survey of natural disasters.

Geological mission: detection of geochemical and structural anomalies through stereo imagery useful for oil and mineral exploration

Agricultural mission: crop yield forecasting, flood damage analysis, etc.

Cartographical mission: 1:50000 maps (1:25000 possible in some cases)

Planning mission: land use monitoring e.g. urban/rural boundary

Main Earth stations: Toulouse, France; Kiruna, Sweden; Prince Albert and Gatinea, Canada; Ladkraban, Thailand; Hatoyama, Japan; Islamabad, Pakistan; Hyderabad, India; Maspalamas, Spain and Ryad, Saudi Arabia.

External resources

http://www.spotimage.fr

http://www.spot.com

http://edcwww.cr.usgs.gov/glis/hyper/guide/spot


Program: Spot

Spot 1

Spot 2

Spot 3

Spot 4

Spot 5

Spot 6


Spot 1, 2 & 3's specifications

Prime contractor	Matra Marconi Space
Platform	Spot (Mark 1)
Mass at launch	1900 kg
Payload mass	790 kg
Dimension	2 x 2 x 3.5 m
Solar array	8 m span
Stabilization	3 axis
DC power	1100 W
Design lifetime	3 years
Telemetry/data	X-band (20 W)


Spot 1, 2 & 3's payload

2 HRV (High Resolution Visible) detectors - linear array CCD detectors using push-broom scanning

Wavebands	Panchromatic (PAN): 0.51-0.73 µm (visible, near IR) Multispectral (XS): 0.50-0.59 µm (green) 0.61-0.68 µm (red) 0.79-0.89 µm (near IR)
Swath width	60 km (each HRV)
Resolution	Panchromatic: 10 m Multispectral: 20 m

HRVs are steerable to either side of the ground track (+/- 27°) to provide re-visits and stereoscopic images


 Spot 1

General

Designation	16613 / 86019A
Launch date	22 Feb 1986
Country of origin	France
Mission	Remote sensing
Perigee/Apogee	821/823 km
Inclination	98.7°
Period	101.3 min
Orbital cycle	26 days
Launch vehicle	Ariane V16

Was returned to operational service on 13 Jan 1997 to fill the gap caused by the loss of Spot 3. Although the recorders have failed it can operate when in contact with a ground station.

Technical data

Specifications

Payload

CCD at 1728 points provided by Fairchild


 Spot 2

General

Designation	20436 / 90005A
Launch date	22 Jan 1990
Country of origin	France
Mission	Remote sensing
Perigee/Apogee	821/823 km, same plan as Spot 1 but at its antipode
Inclination	98.7°
Period	101.3 min
Launch vehicle	Ariane V35

On-board recorders were out of use after 2 years of service

Technical data

Specifications

Payload

Beacon frequency: 8.307 GHz. Data: 8.253 GHz; output rate: 2 x 25 Mbit/s

CCD at 1728 points provided by Thomson CSF


 Spot 3

General

Designation	22823 / 93061A
Launch date	26 Sep 1993
Country of origin	France
Mission	Remote sensing
Perigee/Apogee	821/823 km
Inclination	98.7°
Period	101.3 min
Launch vehicle	Ariane V59

Cost: $250 million ($125 million for launch)

On 14 November 1996 the satellite stopped operating. Decision was taken to launch Spot 4 as soon as possible and to reactivate Spot 1.

End of life

Out of service	14 Nov 1996
Cause	failure: attitude control was lost, after several gyroscope problems
Decay
Technical data

Specifications

Payload

CCD with 6000 points


 Spot 4

General

Designation	25260 / 98017A
Launch date	24 Mar 1998
Country of origin	France
Mission	Remote sensing
Perigee/Apogee	832 km
Inclination	98.7°
Period	101 min
Orbital cycle	3.7, 26 days
Launch vehicle	Ariane V107

The total cost of the satellite over 6 years (contruction, launch, exploitation) is approx. $500 million

External resources

http://spot4.cnes.fr/

http://www-vegetation.cst.cnes.fr:8050/

Technical data

Specifications

Prime contractor	Matra Marconi Space
Platform	Spot (Mark 2)
Mass at launch	2755 kg
Dry mass	2600 kg
Payload mass	1390 kg
Dimension	2.5 x 2.5 x 5.35 m
Solar array	4 x 8 m
Stabilization	3-axis
DC power	EOL: 2200 W
Design lifetime	5 years

Telemetry: 1704 MHz

Telemetry: 2218 MHz (4096 kbps)

Telemetry: 8253 MHz

Command: 2042.408 MHz (2 kbps)

Command: 5690 MHz

2 HRVIR (High Resolution Visible IR) detectors

Wavebands	0.50-0.59 µm (green) 0.61-0.68 µm (red) 0.79-0.89 µm (near IR) 1.53-1.75 µm (mid-IR)
Swath width	60 km (each HRV)
Resolution	Monospectral: 10 m Multispectral: 20 m

CCD with 6000 points. Has the same on-board recorder as Helios 1A provided by Enertec (2 x 120 Gbits). HRVs are steerable to either side of the ground track (+/- 27°) to provide re-visits and stereoscopic images

Vegetation

Wavebands	0.43-0.47 µm (blue) 0.61-0.68 µm (red) 0.78-0.89 µm (near IR) 1.58-1.75 µm (mid-IR)
Swath width	2000 km
Resolution	1.15 to 1.7 km

Vegetation monitoring Instrument. Onboard storage: 2.25 Gbit

The PASTEL system (PAssager Spot de TElécommunication Laser) use the SILEX (Semiconductor Intersatellite Link Experiment) payload to downlink via Artemis at 50 mpbs. The link is operated at optical frequencies at a wavelength of 800 to 860 nanometers. The light source is a solid state laser diode operated typically at 60 mW optical power. The applied modulation scheme is direct intensity modulation. A photo diode is used as optical data detector.

The difficulty involves aligning and stabilizing two terminals which are on average 38 500 km away from each other, with a pointing error of less than 2 micro-radians. In other words, the beam from PASTEL (which at that distance, would have a diameter of 200 m) would have to be kept centred on OPALE with a tolerance of +/- 38m. This is equivalent to to hitting an orange with a rifle shot from 51 km!


 Spot 5

General

Designation
Launch date	initially planned in Sep 2001
Country of origin	France
Mission	Remote sensing
Perigee/Apogee
Inclination
Period
Launch vehicle	Ariane 5
Launch site

The satellite and launch and associated expenses should total $400 million

Technical data

Specifications

Prime contractor	MMS
Platform	Mark 2+
Mass at launch	~3000 kg
Mass in orbit
Dimension
Solar array
Stabilization
DC power	2800 W
Design lifetime

Will have CCDs at 12000 points providing a 5 m resolution on 60 km swath width. Will have the same onboard recorders as Helios 2 Will provide 10 m resolution in multispectral mode and 20 m in infrared mode. Should also carry the vegetation instrument.

It should enable stereoscopy with the HRS instrument from Matra.


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 Spot 6

Also called 3S

General

Designation
Launch date	initially planned in 2004
Country of origin	France
Mission
Perigee/Apogee
Inclination
Period
Launch vehicle
Launch site

Will have a 2.5 m resolution and 60 to 100 km view span.  Based on a Proteus platform, this is a much smaller satellite than the other Spots.


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 Program: Sret

Satellite de Recherche et d'Etudes Technologiques

French experimentation program


Program: Sret

Sret 1

Sret 2


 Sret 1

General

Designation	05928 / 72025B
Launch date	4 Apr 1972
Country of origin	France
Mission	Technology experimentation
Perigee/Apogee	480/39248 km
Inclination	65.6°
Period	735 min
Launch vehicle	Molniya
Launch site	Plesetsk
Mass at launch	15 kg

Technological satellite to test solar cells

End of life

Decay	26 Feb 1974


 Sret 2

General

Designation	07910 / 75049B
Launch date	6 Jun 1975
Country of origin	France
Mission	Technology experimentation
Perigee/Apogee	513/40825 km
Inclination	62.8°
Period	737.8 min
Launch vehicle	Molniya
Launch site	Plesetsk
Mass at launch	30 kg

Tested a passive cryogenic radiative system


 Program: Sross

Streach ROhini Sat Services

Indian experimental program


Program: Sross

Sross 1

Sross 2

Sross 3

Sross C2


 Sross 1

General

Launch date	24 Mar 1987
Country of origin	India
Mission	Scientific
Launch vehicle	ASLV #1

Carried a measurement payload for the launch vehicle and a Gamma-ray astronomy payload.

End of life

Out of service	24 Mar 1987
Cause	launch failure


 Sross 2

General

Launch date	12 Jul 1988
Country of origin	India
Mission	Scientific
Launch vehicle	ASLV #2

Carried a German (MEsOSS) remote sensing payload and a gamma-ray astronomy payload

End of life

Out of service	12 Jul 1988
Cause	launch failure


 Sross 3

Also called Sross C

General

Designation	21968 / 92028A
Launch date	20 May 1992
Country of origin	India
Mission
Perigee/Apogee	251/436 km
Inclination	46°
Period	91.4 min
Launch vehicle	ASLV #3

Carried Gamma Ray astronomy and aeronomy payload.

End of life

Decay	14 Jul 1992


 Sross C2

General

Designation	23099 / 94027A
Launch date	4 May 1994
Country of origin	India
Mission	Scientific: ionosphere study
Perigee/Apogee	430/619 km
Inclination	46°
Period	95.1 min
Launch vehicle	ASLV #4
Mass at launch	113 kg

It carried a Retarding Potential Analyzer (RPA) for measuring ionospheric plasma, and a Gamma ray detector. Is identical to Sross 3

Beacon freq.: 137.400 MHz  It operates only on command so data reception is limited to sites close to India.


 ST 1

General

Designation	25460 / 98049A
Launch date	25 Aug 1998
Country of origin	Singapore & Taiwan
Operator	Singapore Telecom and Chunghwa Telecom (50/50)
Mission	Telecommunications
Geostationary orbit	88°E
Launch vehicle	Ariane V109

Delivered in-orbit. Contract worth $240 million (with 2 control centers in Seletar, Singapour and Taipei, Taiwan; and training).Wen operational on 1 Dec 1998.

External resources

http://www.singtel.com/ST1/

Technical data

EIRP coverage (dBW)

C-band

Ku-band

Specifications

Prime contractor	Matra Marconi Space
Platform	Eurostar 2000
Mass at launch	3255 kg
Mass in orbit	1753 kg
Dry mass	1502 kg
Dimension	2.5 x 1.7 x 2.9 m
Solar array	32.3 m span
Stabilization	3-axis
DC power	8300 W
Design lifetime	12 years
C-band

Main transponders	14
Backup transponders
Power
Bandwidth
Coverage	middle to far East Asia
EIRP max	40 dBW
G/T max	-2.1 dB/K
Polarization	linear H/V
Ku-band

Main transponders	16
Backup transponders
Power	90-135 W (TWTA)
Bandwidth
Coverage	K1: Taiwan, Philippines, Malaysia, Singapore K2: India
EIRP max	K1: 53 dBW K2: 52 dBW
G/T max	K1: 5 dB/K K2: 3 dB/K
Polarization	linear H/V

Transponders are switchable on either beam


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ST 1's C-band EIRP


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ST 1's Ku-band EIRP


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 Program: Stacksat

US military program composed of 3 similar satellites named POGS, TEX & SCE. This program is also known as P87-2

General

Designation	POGS or USA 56: 20560 / 90031A TEX or USA 57: 20561 / 90031B SCE or USA 58: 20562 / 90031C
Launch date	11 Apr 1990
Country of origin	United States
Mission	military: study ionospheric effects on signal propagation
Perigee/Apogee	741 km
Inclination	90°
Period
Launch vehicle	Atlas #51

TEX is a USAF satellite, POGS & SCE are from US Navy

Technical data

Specifications

Prime contractor	CTA
Platform
Mass at launch	68 kg each
Mass in orbit
Dimension
Solar array	15 W
Stabilization	gradient
DC power
Design lifetime	3 years

possible downlink: 327.250 or 328.250 MHz


 Starlette

Satellite de Taille Adaptée avec Réflecteur Laser pour l'ETude de la TErre

General

Designation	07646 / 75010A
Launch date	6 Feb 1975
Country of origin	France
Mission	Scientific: geodesy
Operator	CNES
Perigee/Apogee	805/1108 km
Inclination	49.8°
Period	104.2 min
Launch vehicle	Diamant #10
Mass at launch	47 kg

Sphere of 24 cm of uranium covered with 60 reflectors. Measured the continental drift.


 Program: Starlite

US military project lead by DARPA.  This would be a constellation of 24 satellites configured with Synthetic Aperture Radar (SAR) to allow direct tasking control to a deployed tactical commander. The constellation would allow for a very rapid revisit rate (about 15 minutes) to most areas of the earth. The system would be capable of generating very high resolution elevation data (1 meter post spacings) and highly accurate radar imagery.

Two satellite should be built in 2000 for demonstration purposes. If successful the system should be deployed in 2005.


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 Starshine

Student Tracked Atmospheric Research Satellite for Heuristic International Networking Equipment

General

Designation	25769 / 99030B
Launch date	5 Jun 1999
Country of origin	United States
Mission	Scientific
Perigee/Apogee	379/396 km
Inclination	51.6°
Period
Launch vehicle	STS 96

To be observed by students to measure density of the atmosphere. It is planned to launch 1 such satellite per year over 11 years.

Technical data

Specifications

Prime contractor	NRL
Platform
Mass at launch	39.3 kg
Mass in orbit
Dimension	48.2 cm diameter sphere
Solar array
Stabilization
DC power
Design lifetime

It is covered with 878 aluminum mirrors of 2.54 cm diameter.


 Program: Starsys

GE program made of 24 LEO satelllites to be built by Alcatel Telecom (MMS will supply the Leostar busses). Can provide tracking and monitoring services around the globe. GE Americom concluded the acquisition of an 80% interest in Starsys Global Positioning, Inc.

These satellites will operate in the VHF/UHF frequency bands, and will have the capability for adaptive on-board filtering of terrestrial interference.  The 80 kg (approx.) spacecraft will be used to relay short data packet bursts between a gateway site and small remote terminals.

GE Starsys will offer satellite-based data messaging services for a variety of applications, including fleet and cargo management, logistics, remote data collection and asset security.  Transportation service providers will use GE Starsys to monitor their assets, increasing their fleet productivity and effectiveness.

As currently envisioned, the system will consist of up to 24 orbit-controlled satellites at 965 km in altitude. Each bird should weigh 70 kg.

Alcatel will aslo provide the control stations and the terminals.

Program was abandonned in 1997. The license was transfered to Esat


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 Stella

General

Designation	22824 / 93061B
Launch date	26 Sep 1993
Country of origin	France
Mission	Scientific: geodesy
Perigee/Apogee	793/803 km
Inclination	98.7°
Period	100.8 min
Launch vehicle	Ariane V59
Technical data

Specifications

Prime contractor	CNES
Platform
Mass at launch	48 kg
Mass in orbit
Diameter	24 cm (sphere)
Stabilization
DC power
Design lifetime

Its a sphere of 24 cm diameter with 20 sides and 60 laser reflectors. As Starlette or Lageos 2 Stella is designed to be tracked by laser (1 cm accuracy) by ground stations all around the world (in France: le Cergue in Grasse). It is made of impoverish uranium for the maximum stability. Will enable to make a map of the globe.


 Program: Step

Space Test Experiment Platform

American small satellite program to test technology. The STEP program is run by the DoD Space Test Program (SMC/TEL) an office of the Space and Missile Systems Center, Test and Evaluation Directorate (SMC/TE).


Program: Step

Step 0

Step 1

Step 2

Step 3

Step 4


 Step 1

Also called P90 A

General

Launch date	27 Jun 1994
Country of origin	United States
Mission	Military: technology
Launch vehicle	Pegasus #6 (XL)
End of life

Out of service	27 Jun 1994
Cause	Destroyed on launch with the launcher

Operated by USAF and built by TRW from an Eagle platform

It carried radio propagation experiments, a plasma environment analyser, the CHAMPION ionosphere-magnetosphere coupling experiment, and an accelerometer and mass spectrometer to study the upper atmosphere.


 Step 2

Also called P91 A

General

Designation	23105 / 94029A
Launch date	19 May 1994
Country of origin	United States
Mission	Military: technology
Perigee/Apogee	604/818 km
Inclination	81.9°
Period	99 min
Launch vehicle	Pegasus #5

Operated by USAF and built by TRW from a lightstar Eagle platform. It will study propagation of radio signals through the ionosphere; carries SIDEX, a signal indentification experiment.


 Step 3

General

Launch date	22 Jun 1995
Country of origin	United States
Mission	Military: technology
Launch vehicle	Pegasus #9 (XL)
Mass at launch	265 kg
End of life

Out of service	22 Jun 1995
Cause	Launch failure

Built by TRW, it carried the SAMME (Space Active Modular Materials Experiments) payload to study exposure to space of solar cells and advanced materials, as well as vibration suppression technology and experimental computer disk drives.


 Step 4

Also called P95-1

General

Designation	25013 / 97063A
Launch date	22 Oct 1997
Country of origin	United States
Mission	Military: ?
Perigee/Apogee	434/501 km (600 km planned)
Inclination	45°
Period	94 min
Launch vehicle	Pegasus #18

Cost: $52 million

Contact was lost right after launch and the solar panels did not deploy. In such conditions the lifetime of the satelllite is limited by the batteries.

Technical data

Specifications

Prime contractor	TRW
Platform	STEP
Mass at launch	391.5 kg
Mass in orbit
Dimension	1.52 x 0.91 m
Solar array
Stabilization	3-axis
DC power	183 W
Design lifetime	2 years

S-band telemetry

Payload

Digital Ion Drift Meter (DIDM)

Electromagnetic Propagation Experiment (EMPE)

Orbiting Ozone and Aerosol Measurement (OOAM)


 Stex

Space Technology EXperiments

General

Designation	25489 / 98055A
Launch date	3 Oct 1998
Country of origin	United States
Mission	Military: technology
Geostationary orbit
Launch vehicle	Taurus #3

It carries experimental solar arrays and batteries and a 6 km tether. STEX is connected to ATEX thanks to this tether. The deployement failed on 16 Jan 1999: only 22 m were deployed because the automatic safety separation was triggered by a dangerous separation angle.

The STEX satellite was built by Lockheed Martin Astronautics (Denver) for the National Reconnaissance Office. STEX's main experiments are provided by the Naval Research Lab, including Hall Effect electric thrusters derived from Russian technology and a 6 km tether experiment, a follow-on to the earlier TIPS satellite. STEX also carries experimental solar arrays and batteries.


 Program: Strela

Means "arrow"

Russian military telecommunication program based on LEO satellites. This program has 3 differents series.

Strela 1

Those satellites form a network of 3 satellites orbiting in planes separated by 120°. They are used for long range communications by low power transmitters.

Specifications overview:

Prime contractor	NPO PM
Platform
Mass	800 kg
Dimension	cylinder, 2 m diameter x 2 m high
Perigee/Apogee	circular, 800 km
Inclination	74°
Orbital cycle	6 days
Design lifetime	2 years

Satellites:

Cosmos 372	Cosmos 407	Cosmos 468	Cosmos 494	Cosmos 540	Cosmos 614
Cosmos 676	Cosmos 773	Cosmos 783	Cosmos 836	Cosmos 841	Cosmos 858
Cosmos 923	Cosmos 968	Cosmos 990	Cosmos 1023	Cosmos 1048	Cosmos 1110
Cosmos 1125	Cosmos 1140	Cosmos 1190	Cosmos 1269	Cosmos 1302	Cosmos 1331
Cosmos 1354	Cosmos 1371	Cosmos 1420	Cosmos 1452	Cosmos 1486	Cosmos 1503
Cosmos 1538	Cosmos 1570	Cosmos 1624	Cosmos 1680	Cosmos 1741	Cosmos 1763
Cosmos 1770	Cosmos 1814	Cosmos 1850	Cosmos 1898	Cosmos 1937	Cosmos 1954
Cosmos 1992	Cosmos 2056	Cosmos 2112	Cosmos 2150	Cosmos 2208	Cosmos 2251
Cosmos 2298
Strela 2

Those satellites were launched 8 at a time, more or less in the same plane. They were used for military radio communications.

Specifications overview:

Prime contractor
Platform
Mass	~ 200 kg
Dimension
Perigee/Apogee	circular, 1500 km
Inclination	74°
Orbital cycle
Design lifetime	1.5 years

The full list of satellites launched is available here

Strela 3

Launched by 6, those satellites offer realtime and store and forward data communications between military aircraft, ships and bases. Also called Locsyst. All crafts were launched onboard Cyclone 3

Two planes are spaced 90 degrees apart with six satellites per plane.

Specifications overview:

Prime contractor	NPO PM
Platform
Mass	225 kg
Dimension
Perigee/Apogee	circular, 1400 km
Inclination	82.6°
Orbital cycle
Design lifetime	2 years

They have an uplink in 312-315 MHz range and downlinks 387-390 MHz

Satellites:

Cosmos 1617-22	Cosmos 1690-95	Cosmos 1827-32	Cosmos 1875-80	Cosmos 1909-14
Cosmos 1994-99	Cosmos 2038-43	Cosmos 2090-95	Cosmos 2114-19	Cosmos 2143-48
Cosmos 2157-62	Cosmos 2165-70	Cosmos 2197, 2198, 2200, 2202	Cosmos 2211-16	Cosmos 2245-50
Cosmos 2252-57	Cosmos 2268-73	Cosmos 2299-2304	Cosmos 2328-2330	Cosmos 2337-2339
Cosmos 2352-57


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 Program: STRV

Space Technology Research Vehicle

English experimental program operated by DRA (Defence Research Agency), the new name for the RAE (Royal Aircraft Establishment). RAE was the lead agency for all of Britain's technology

(as opposed to science or communications) satellites.

Designed to test spacecraft systems and technologies in orbit and investigate the effect of high radiation doses, atomic oxygen erosion and spacecraft charging.

External resources

http://www.ee.surrey.ac.uk/EE/CSER/UOSAT/SSHP/data_strv.html


Program: STRV

STRV 1A

STRV 1B


STRV's specifications

Prime contractor	DRA (Defense Research Agency) Aerospace Division
Mass at launch	~ 50 kg
Dimension	0.45 x 0.45 x 0.47 m
Stabilization	Spin stabilized
DC power	BOL: 27 W EOL: 24 W
Design lifetime	1 year


STRV's Payload

Several instruments to measure radiation dose, particle fluxes, electrostatic charging, etc.

Telemetry data rate	1 kbps
Transmitter power	0.5 W, 2 W
Frequencies	Uplink: 2.025-2.12 GHz Downlink: 2.2-2.3 GHz


 STRV 1A

General

Designation	23125 / 94034B
Launch date	17 Jun 1994
Country of origin	United Kingdom
Mission	Military: technology
Perigee/Apogee	251/35518 km
Inclination	7.3°
Period	627 min
Launch vehicle	Ariane V64
Mass at launch	50 kg

Carries experiments to study surface erosion effects on spacecraft materials, a cosmic ray detector, and a gamma ray burst experiment. Will test new solar cells and measure static charge on its surfaces.

Technical data

Specifications

Payload

Spin rate: 10 rpm


 STRV 1B

General

Designation	23126 / 94034C
Launch date	17 Jun 1994
Country of origin	United Kingdom
Mission	Military: technology
Perigee/Apogee	239/35588 km
Inclination	7.3°
Period	628 min
Launch vehicle	Ariane V64
Mass at launch	53 kg

Carries an experimental cooler, solar cells, and electronics.

Technical data

Specifications

Payload

Spin rate: 5 rpm


 Sunsat

Stellenbosch UNiversity SATellite, also called SO-35, Oscar 35

General

Designation	25636 / 99008C
Launch date	Feb 1999
Country of origin	South Africa
Mission	Telecommunication, HAM
Perigee/Apogee	831/847 km
Inclination	98.7°
Period
Launch vehicle	Delta 2 #267

Micro satellite being designed, built and tested by students at the Electronic Systems Laboratory in the Department of Electrical and Electronic Engineering at Stellenbosch University. In exchange for a US National Aeronautics and Space Administration launch, Sunsat will carry a precision GPS receiver and a set of Laser retro-reflectors, provided by, and for use of NASA.

Contact

SED, University of Stellenbosch, Stellenbosch, 7600, South Africa

Tel: +27-21-8084103

Fax:+27-21-8084981

External resources

http://sunsat.ee.sun.ac.za/

http://www.amsat.org/amsat/sats/n7hpr/sunsat.html

Technical data

Specifications

Prime contractor
Platform
Mass at launch	60 kg
Mass in orbit
Dimension	45 x 45 x 62 cm
Solar array
Stabilization
DC power
Design lifetime

The payload includes duplicate transmitters and receivers for the 2-meter (145.825 MHz) and 70-cm bands, a 24-cm (1260 MHz) receiver and 13-cm (2400 MHz) receiver. A number of uplink and downlink frequency combinations are possible. Sunsat will offer extensive digital communication capability. One of the 2-meter receivers has four IF sections connected to 1200-baud AFSK packet modems. The satellite carries three G3RUH-compatible 9600-baud modems that can be switched to various receivers and transmitters.

Telemetry on 436.25 & 436.30 MHz

It carries two NASA experiments and an experimental pushbroom imager capable of taking pictures of the earth. The high resolution imager providing 50x50 km coverage will operate in real time on S band.


 Program: Superbird

Japanese telecommunication program operated by SCC

The 2 control centers are located in Ibaraki (space port east) and Yamaguchi (space port west).


Program: Superbird

Superbird A1

Superbird A2

Superbird B

Superbird B1

Superbird C

Superbird 4


Superbird's specifications

Prime contractor	Ford Aerospace / Space Systems/Loral
Platform	FS-1300
Mass at launch	2492 kg
Mass in orbit	1505 kg
Dimension	2.41 x 2.58 x 2.2 m
Solar array	20.3 m span
Stabilization	3 axis
DC power	4460 W EOL: 3800 W
Design lifetime	10 years


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Superbird's X-band

Main transponders	2
Backup transponders
Power	40 W (TWTA)
Bandwidth	40 MHz
Coverage
EIRP max	37 dBW
Polarization


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Superbird's Ku-band

Main transponders	23
Backup transponders	8
Power	50 W (TWTA)
Bandwidth	36 MHz
Coverage	Japan: 49 dBW Taiwan: 38 dBW Korea: 45 dBW
EIRP max	53 dBW
Polarization	linear
Frequencies	uplink: 14.00 - 14.50 GHz downlink: 12.25 - 12.75 GHz


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Superbird's Ka-band

Main transponders	2
Backup transponders	1
Power	29 W (TWTA)
Bandwidth	100 MHz
Coverage	Japan
EIRP max	spot beam: 59 dBW others: 55 dBW
Polarization
Frequencies	uplink: 28.40 - 28.80 GHz downlink: 18.80 - 19.00 GHz


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Superbird's Ku-band transponder frequency chart (GHz)

Horizontal Uplink	Horizontal Downlink	Transponder	Vertical Downlink	Vertical Uplink
14.02		1	12.29
	12.31	13		14.04
14.06		2	12.33
	12.35	14		14.08
14.10		3	12.37
	12.39	15		14.12
14.14		4	12.41
	12.43	16		14.16
14.18		5	12.45
	12.47	17		14.20
14.22		6	12.49
	12.51	18		14.24
14.26		7	12.53
	12.55	19		14.28
14.30		8	12.57
	12.59	20		14.32
14.34		9	12.61
	12.63	21		14.36
14.38		10	12.65
	12.67	22		14.40
14.42		11	12.69
	12.71	23		14.44
14.46		12	12.73


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 Superbird A1

General

Designation	20040 / 89041A
Launch date	5 Jun 1989
Country of origin	Japan
Mission	Telecommunications
Geostationary orbit	life time in 158°E
Launch vehicle	Ariane V31
End of life

Out of service	Dec 1990
Cause	Propellant leak
Technical data

Specifications

X-band

Ku-band

Ka-band


 Superbird B

End of life

Out of service	22 Feb 1990
Cause	Launch failure: Ariane V36
Technical data

Specifications

X-band

Ku-band

Ka-band


 Superbird B1

General

Designation	21893 / 92010A
Launch date	26 Feb 1992
Country of origin	Japan
Mission	Telecommunications
Geostationary orbit	162°E
Launch vehicle	Ariane V49
Technical data

Specifications

X-band

Ku-band

Ku-band frequency chart

Ka-band

Ku-band EIRP coverage (dBW)

Ku-band G/T coverage (dBW)

beacons: 12.251 V & 12.253 H GHz


Superbird A & B's Ku-band EIRP coverage


Superbird B1's Ku-band G/T coverage


 Superbird A2

General

Designation	22253 / 92084A
Launch date	1 Dec 1992
Country of origin	Japan
Mission	Telecommunications
Geostationary orbit	158°E
Launch vehicle	Ariane V55
Technical data

Specifications

X-band

Ku-band

Ku-band frequency chart

Ka-band

Ku-band EIRP coverage (dBW)

beacons: 12.250 V & 12.252 H GHz


 Superbird C

General

Designation	24880 / 97036A
Launch date	28 Jul 1997
Country of origin	Japan
Mission	Telecommunications
Geostationary orbit	144°E
Launch vehicle	Atlas 2AS #108

Investment is evaluated to $416 million including insurance. The satellite alone is worth $100 million

Technical data

EIRP coverage (dBW)

Japan & Hawaii beams

North East Asia beam

South East Asia beam

G/T coverage (dB/K)

Japan beam

North East Asia beam

South East Asia beam

Specifications

Prime contractor	Hughes
Platform	HS-601
Mass at launch	3130 kg
Mass in orbit	1850 kg
Dimension	2.3 x 2.3 x 2.2 m
Solar array	26.6 m span
Stabilization	3-axis
DC power	EOL: 4500 W
Design lifetime	13 years
Ku-band

Main transponders	24
Backup transponders	6
Power	90 W
Bandwidth	16 x 27 MHz 4 x 36 MHz 4 x 54 MHz (convertible to 2 x 114 MHz at 180 W)
Coverage & EIRP max	Japan: 57.6 dBW North East Asia: 54.6 dBW South East Asia: 51.5 dBW Steerable: 50.4 dBW hawaii: 52.3 dBW
Polarization	linear H/V
Frequencies	uplink: 14.00 - 14.50 GHz downlink: 12.25 - 12.75 GHz downlink: 11.70 - 12.70 GHz (Hawaii only)

In addition to two conventional antennas (2.16 m) the spacecraft will also feature a steerable spot beam designed and built by Mitsubishi to increase service where needed.

Superbird C would have 125 MHz of X-band in the payload for mobile communication.

Uplink transponder frequency chart (GHz)

Vertical Uplink	Transponder	Horizontal Uplink	Bandwidth (MHz)	Beam
14.05	1		54	Japan-Hawaii or SE Asia (Tr 1 & 2 can be combined)
	13	14.05	54	Japan-Hawaii or NE Asia (Tr 13 & 14 can be combined)
14.11	2		54	Japan-Hawaii or SE Asia (Tr 1 & 2 can be combined)
	14	14.11	54	Japan-Hawaii or NE Asia (Tr 13 & 14 can be combined)
14.16	3		36	Japan-Hawaii or SE Asia
	15	14.16	36	Japan-Hawaii or NE Asia
14.20	4		36	Japan-Hawaii
	16	14.20	36	Japan-Hawaii or Steerable
	17	14.238	27	Japan-Hawaii or Steerable
14.253	5		27	Japan-Hawaii or SE Asia
	18	14.268	27	Japan-Hawaii or NE Asia
14.283	6		27	Japan-Hawaii
	19	14.298	27	Japan-Hawaii or Steerable
14.313	7		27	Japan-Hawaii or SE Asia
	20	14.328	27	Japan-Hawaii or NE Asia
14.343	8		27	Japan-Hawaii
	21	14.358	27	Japan-Hawaii or Steerable
14.373	9		27	Japan-Hawaii or SE Asia
	22	14.388	27	Japan-Hawaii or NE Asia
14.403	10		27	Japan-Hawaii
	23	14.418	27	Japan-Hawaii or NE Asia
14.433	11		27	Japan-Hawaii or SE Asia
	24	14.448	27	Japan-Hawaii or NE Asia
14.463	12		27	Japan-Hawaii or SE Asia
Downlink transponder frequency chart (GHz)

Vertical Downlink	Transponder	Horizontal Downlink	Bandwidth (MHz)	Beam
	1	12.32	54	Japan or SE Asia (Tr 1 & 2 can be combined)
12.32	13		54	Japan or NE Asia (Tr 13 & 14 can be combined)
	2	12.38	54	Japan or SE Asia (Tr 1 & 2 can be combined)
12.38	14		54	Japan or NE Asia (Tr 13 & 14 can be combined)
	3	12.43	36	Japan or SE Asia
12.43	15		36	Japan or NE Asia
	4	12.47	36	Japan or Hawaii
12.47	16		36	Japan or Steerable
12.508	17		27	Japan or Steerable
	5	12.523	27	Japan or SE Asia
12.538	18		27	Japan or NE Asia
	6	12.553	27	Japan or Hawaii
12.568	19		27	Japan or Steerable
	7	12.583	27	Japan or SE Asia
12.598	20		27	Japan or NE Asia
	8	12.613	27	Japan or Hawaii
12.628	21		27	Japan or Steerable
	9	12.643	27	Japan or SE Asia
12.658	22		27	Japan or NE Asia
	10	12.673	27	Japan or Hawaii
12.688	23		27	Japan or NE Asia
	11	12.703	27	Japan or SE Asia
12.718	24		27	Japan or NE Asia
	12	12.733	27	Japan or SE Asia

Beacons: 12.250 V & 12.252 H GHz on Japan beam, 11.101 H GHz on Hawaii beam, 12.254 V GHz on NE Asia beam, 12.255 H GHz on SE Asia beam, 12.749 V GHz on Steerable beam


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Superbird C's Japan & Hawaii EIRP coverage


Superbird C's North East Asia EIRP coverage


Superbird C's South East Asia EIRP coverage


Superbird C's Japan G/T coverage


Superbird C's North East Asia G/T coverage


Superbird C's South East Asia G/T coverage


 Superbird 4

General

Designation
Launch date	initially planned in early 2000
Country of origin	Japan
Mission	Telecommunications
Geostationary orbit	162°E
Launch vehicle

Will replace Superbird B1

Technical data

Specifications

Prime contractor	Hughes
Platform	HS-601HP
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime
Ku-band

Main transponders	23
Backup transponders
Power
Bandwidth	36 MHz
Coverage	domestic beam, Okinawa beam, steerable beam
EIRP max
G/T max
Polarization
Ka-band

Main transponders	6
Backup transponders
Power
Bandwidth	1 x 200 MHz 5 x 100 MHz
Coverage	Domestic beam
EIRP max
G/T max
Polarization

The satellite will carry a steerable Ku-Band spot beam.


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 Surfsat 1

Summer Undergraduate Research Fellowship SATellite

General

Designation	23711 / 95060B
Launch date	4 Nov 1995
Country of origin	Canada
Mission	Scientific
Perigee/Apogee	934/1494 km
Inclination	100.6°
Period	109 min
Launch vehicle	Delta 2 #229
Mass at launch	55 kg

Surfsat is bolted to Delta's second stage. It has its own solar cells and is not electricaly dependent of Delta.

Surfsat will be used as a test vehicle for NASA, supporting deep space communications research and training of tracking station personnel at NASA's Deep Space Network. The Deep Space Network transponders will operate in Ka-band at 32 GHz (atmospheric studies). The VLBI transponders (X- and Ku-band) will enable testing of ground equipment for VSOP (Japan) and Radioastron (Russian project).

Designed by Caltech undergraduates with the help of JPL.

External resources

http://sgra.jpl.nasa.gov/html_surfsat/SURFSATHomePage.html


 SWAS

Submillimeter Wave Astronomy Satellite

General

Designation	25560 / 98071A
Launch date	6 Dec 1998
Country of origin	United States
Mission	Scientific: Astronomy
Perigee/Apogee	600/650 km
Inclination	70°
Period
Launch vehicle	Pegasus XL #25

The SWAS mission is an outgrowth of the scientific interest in the exploration of the submillimeter wavelength region for astronomy.  SWAS will be a pioneering step in submillimeter astronomy in space.  The SWAS mission is designed to study molecular clouds in the galactic plane, providing a mini and full survey of the clouds, leading towards the development of maps.  It will also perform quick-look chemistry on the structure and content of these molecular clouds, and will research extragalactic sources.

External resources

http://sunland.gsfc.nasa.gov/smex/swas/

http://cfa-www.harvard.edu/cfa/oir/Research/swas.html

Technical data

Specifications

Prime contractor
Platform
Mass at launch	288 kg
Payload mass	102 kg
Dimension
Solar array
Stabilization	3-axis
DC power	230 W
Design lifetime	2 years

Telemetry: 2215 MHz (realtime: 18.75 kbps, playback: 1.8 Mbps), 5 W transmitter

Command: 2039.65 MHz (2 kbps)

The instrument consists of an off-axis Cassegrain telescope, receiver, Acousto-Optical Spectrometer (AOS), instrument control electronics (ICE) and a thermal control subsystem.

The satellite has a 0.6m telescope with a 490 to 550 GHz submillimeter receiver and an acousto-optical spectrometer.


 Program: Symphonie

French and German telecommunication program. The French Saros project and the German Olympia project merged with the help of a cooperation signed on 22 Jan 1963 and 16 Jun 1967. The satellites were built by CIFAS, a consortium gathering Aérospatiale, Thomson CSF, SAT and MBB, Siemens and AEG Telefunken.

The program enabled the use of the SAMSON (Station à Antenne Miniature pour Service Occasionnel Numérique) portable station: transportable in 2 containers containing telecommunication equipments and a 4.8 m diameter antenna.

External resources

http://www.op.dlr.de/wt-rm/symphony.htm


Program: Symphonie

Symphonie 1

Symphonie 2


Symphonie's specifications

Prime contractor	CIFAS
Platform
Mass at launch	400 kg
Mass in orbit	235 kg
Diameter	1.7 m
Height	0.5 m
Solar array	6.8 m span
Stabilization	3 axis (first civilian satellites 3 axis stabilized)
DC power	BOL: 300 W EOL: 180 W
Design lifetime	5 years
Capacity	600 phone circuits or 2 TV channels


Symphonie's C-band

Main transponders	2
Backup transponders
Power
Bandwidth	90 MHz
Coverage
EIRP max	30 dBW
Polarization


 Symphonie 1

General

Designation	07578 / 74101A
Launch date	19 Dec 1974
Country of origin	Germany and France
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Thor Delta #106
Launch site	Cape Canaveral
Location

Begin	End	Position
L: 19 Dec 1974	1977	11.5°W
1977	Aug 1979	49°E (for India, STEP project)
Aug 1979	19 Feb 1983	11.5°W
End of life

Out of service	19 Feb 1983
Technical data

Specifications

C-band


 Symphonie 2

General

Designation	08132 / 75077A
Launch date	27 Aug 1975
Country of origin	Germany and France
Mission	Telecommunications
Geostationary orbit	11.5°W
Launch vehicle	Thor Delta #114
Launch site	Cape Canaveral
End of life

Out of service	late 1985
Technical data

Specifications

C-band


 Program: Syncom

SYNchronous COMmunication

First american geostationary program. Satellites built by Hughes Aircraft

External resources

http://sulu.lerc.nasa.gov/dglover/syncom.html


Program: Syncom

Syncom 1

Syncom 2

Syncom 3


Syncom's specifications

Prime contractor
Platform
Mass in orbit	40 kg
Length
Width
Height
Stabilization	Spin?
DC power
Design lifetime


Syncom's transmission payload

Main transponders	2
Backup transponders
Power	2 W
Bandwidth	300 phone circuits
Coverage
EIRP max
Frequencies	upload: 7.4 GHz download: 1.8 GHz


 Syncom 1

General

Designation	00553 / 63004A
Launch date	14 Feb 1963
Country of origin	United States
Mission	Telecommunications
Geostationary orbit
Launch vehicle	Thor Delta #16
Launch site	Cape Canaveral
End of life

Out of service	14 Feb 1963
Cause	Lost on the way to geostationary orbit
Technical data

Specifications

Transmission payload


 Syncom 2

General

Designation	00634 / 63031A
Launch date	26 Jul 1963
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	35797/35785 km, 33° inclined, above Brazil
Launch vehicle	Thor Delta #20
Launch site	Cape Canaveral

On 31 Oct 1963 the president of the radiocommunications conference in Geneva, Mr Gunnar Pedersen, inaugurated a telephone link to UN's center in New York by Syncom 2.

End of life

Out of service	yes
Technical data

Specifications

Transmission payload


 Syncom 3

General

Designation	00858 / 64047A
Launch date	19 Aug 1964
Country of origin	United States
Mission	Telecommunications
Geostationary orbit
Launch vehicle	Thor Delta #25
Launch site	Cape Canaveral

First geostationary satellite. Used to broadcast Tokyo's Olympic Games to the US in October 1964 and then for military links to Vietnam.

End of life

Out of service	yes
Technical data

Specifications

Transmission payload


 Taiyo

Means "sun", also called SRATS (Solar Radiation And Thermospheric Structure)

General

Designation	07671 / 75014A
Launch date	24 Feb 1975
Country of origin	Japan
Mission	Scientific: ionosphere and Sun study
Perigee/Apogee	250/2800 km
Inclination	33°
Period	116 min
Launch vehicle	Mu 3C
Launch site	Kagoshima
Mass at launch	86 kg
End of life

Decay	29 Jun 1980
External resources

http://www.isas.ac.jp/info/sat/taiyo-e3.html


 Program: Tansei

Means "blue light necklace"

Japanese program aimed at testing launchers and various technology


Program: Tansei

Tansei 1

Tansei 2

Tansei 3

Tansei 4


 Tansei 1

Also called Tansei MRT

General

Designation	04952 / 71011A
Launch date	16 Feb 1971
Country of origin	Japan
Mission	technology
Perigee/Apogee	986/1106 km
Inclination	29.7°
Period	106.1 min
Launch vehicle	Mu 4S
Launch site	Kagoshima
Mass at launch	63 kg
External resources

http://www.isas.ac.jp/info/sat/tansei-e3.html


 Tansei 2

General

Designation	07122 / 74008A
Launch date	16 Feb 1974
Country of origin	Japan
Mission	technology
Perigee/Apogee	284/3231 km
Inclination	31.2°
Period	121.7 min
Launch vehicle	Mu 3C
Launch site	Kagoshima
Mass at launch	56 kg
End of life

Decay	22 Jan 1983
External resources

http://www.isas.ac.jp/info/sat/tanseiII-e3.html


 Tansei 3

General

Designation	09841 / 77012A
Launch date	19 Feb 1977
Country of origin	Japan
Mission	technology
Perigee/Apogee	796/3804 km
Inclination	65.8°
Period	134.1 min
Launch vehicle	Mu 3H
Launch site	Kagoshima
Mass at launch	134 kg
External resources

http://www.isas.ac.jp/info/sat/tanseiIII-e3.html


 Tansei 4

General

Designation	11706 / 80015A
Launch date	17 Feb 1980
Country of origin	Japan
Mission	technology
Perigee/Apogee	517/608 km
Inclination	38.7°
Period	95.9 min
Launch vehicle	Mu 3S1
Launch site	Kagoshima
Mass at launch	185 kg
End of life

Decay	12 May 1983
External resources

http://www.isas.ac.jp/info/sat/tanseiIV-e3.html


 TD 1A

Thor Delta 1A

General

Designation	05879 / 72014A
Launch date	12 Mar 1972
Country of origin	Europe
Mission	Scientific: UV astronomy
Perigee/Apogee	523/550 km
Inclination	97.6°
Period	95.4 min
Launch vehicle	Thor Delta #88
Launch site	Vandenberg
Mass at launch	472 kg
End of life

Decay	9 Jan 1980
External resources

http://www.esoc.esa.de/external/mso/td.html


 Program: TDF

Télédiffusion De France

French direct TV program operated by TDF. Was designed to promote the D2MAC TV standard.


Program: TDF

TDF 1

TDF 2


TDF's specifications

Prime contractor	Eurosatellite/Aerospatiale
Platform	Spacebus-300
Mass at launch	2100 kg
Mass in orbit	1300 kg
Payload mass	206 kg: transponders: 114 kg, antennas: 92 kg
Dimension	2.4 x 1.65 x 6.4 m
Solar array	19.3 m span
Stabilization	3 axis
DC power	BOL: 4500 W EOL: equinox: 3642 W, solstice: 3311 W
Payload power	2455 W
Design lifetime	7 years


TDF's Ku-band

Main transponders	5
Backup transponders	1
Power	230 W
Bandwidth	27 MHz
Coverage and EIRP max	1 beam centered on France: 63 dBW
Polarization	RHCP
Frequencies	Uplink: 17.3-17.7 GHz Donwlink: 11.7-12.1 GHz
Video excursion	13.5 MHz/v


TDF's EIRP


 TDF 1

General

Designation	19621 / 88098A
Launch date	28 Oct 1988
Country of origin	France
Mission	Direct TV
Geostationary orbit	18.9°W
Launch vehicle	Ariane V26
End of life

Out of service	mid October 1996
Cause	deorbited after stability problems
Technical data

Specifications

Ku-band

Transponder 1 was destroyed by a propellant leak.


 TDF 2

General

Designation	20705 / 90063A
Launch date	24 Jul 1990
Country of origin	France
Mission	Direct TV
Geostationary orbit	see below
Launch vehicle	Ariane V37
Location

Begin	End	Position
L: 24 Jul 1990	Jul 1997	18.9°W
Oct 1997	Oct 1997	29°E (tests)
Nov 1997	May 1999	36°E

In August 1997 the bird joined the Eutelsat fleet. Apparently the satellite was sold. TDF 2 is expected to remain in service at least until early 1999.

End of life

Out of service	May 1999
Cause	deorbited
Technical data

EIRP coverage (dBW)

Specifications

Ku-band


 Program: TDRS

Tracking and Data Relay Satellite

American telecommunication program operated by NASA. Some TDRS satallites have got a so called commercial payload, operated by Columbia Communications (C-band). Provides communications, tracking, telemetry, data acquisition and command services essential to Shuttle and low-Earth orbital spacecraft missions. The TDRS system can provide communications services to orbital spacecraft over 85 percent of each orbit for most satellites, and continuous service for some orbital positions.

The TDRS system was initiated following studies in the early 1970s which showed that a system of telecommunications satellites, operated from a single ground station, could meet the needs of NASA's mission better and more cost-effectively than the then existing network of tracking and communications ground stations located around the world.

In addition to the Shuttle, TDRS customers include GRO, UARS, HST, ERBS, EUVE, Topex Poseidon, XTE and other military missions.

Future clients include: ISS, TRMM, Landsat 7, EOS

Retired missions: Landsat 4, Landsat 5, SMM, COBE, SME

TDRS control center is in White Sands, New Mexico.

Commercial telecommunication services (C-band) are available via Columbia through 31 Dec 2001 (option to extend TDRS 5 & 6 through 2003)

External resources

http://www.tdrss.com

http://www530.gsfc.nasa.gov/tdrss/

http://www530.gsfc.nasa.gov/TUBE/

http://www.fas.org/spp/military/program/com/tdrss.htm


Program: TDRS

TDRS 1

TDRS 2

TDRS 3

TDRS 4

TDRS 5

TDRS 6

TDRS 7

TDRS 8-10 (or H-J)


TDRS 1 to 7's specifications

Prime contractor	Contel & NASA
Platform	TRW Space and Communications
Mass at launch	approx. 2200 kg
Mass in orbit	2120 kg
Dimension	Hexagonal shape
Stabilization	3 axis
DC power	BOL: 2000 W EOL: 1700 W
Design lifetime	10 years

Each satellite has 5 antenna systems: 2 for single access, multiple access, STGL and S-band omni for satellite control.

For SA service, each TDRS has two dual-feed S-band, Ku-band parabolic antennas. These antennas are free to be positioned in two axes, directing the radio beam to orbiting user spacecraft below. These antennas are used primarily to relay communications to and from user spacecraft. The high data rate provided by these antennas is available to users on a time-shared basis. Each antenna is capable of supporting two-user spacecraft services simultaneously -one at S-band and one at Ku-band- provided both users are within the beam width of the antenna.

The MA antenna array, consisting of 30 elements, is hard-mounted on the spacecraft body on the surface of the antenna module facing the Earth.

Another antenna, a 2-meter parabolic reflector, provides the prime link for relaying transmissions to and from the ground terminal at Ku-band.


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TDRS's S-band

Main transponders	2+8
Backup transponders	2+4
Power	(2+2) transponders of 26 W (TWTA) (8+4) transponders of 3.5 W (SSPA)
Bandwidth
Coverage
EIRP max
Polarization
Frequency	2025-2110 MHz & 2200-2290 MHz


TDRS's C-band

Main transponders	12
Backup transponders
Power	5.5 W (TWTA)
Bandwidth	36 MHz
Coverage	hemispheric
EIRP max	34 dBW
G/T max	-2.7 dB/K
Polarization	linear
Frequencies	Uplink: 5.925-6.425 GHz V Downlink: 3.700-4.200 GHz H

Nominal SFD: -86.4 dBW/m²


TDRS's Ku-band

Main transponders	4+2
Backup transponders	2+2
Power	(4+2) transponders of 25 W (TWTA) (2+2) transponders of 1.5 W (TWTA)
Bandwidth	50 & 225 MHz
Coverage
EIRP max	50 dBW
Polarization


 TDRS 1

General

Designation	13969 / 83026B
Launch date	4 Apr 1983
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	STS 06

Its propulsion device (IUS) didn't work. The satellite reached the geostationary orbit by himself, using much of his propellant.

Still partially operational, it is though to provide communication services with the South Pole.

On 3 Feb 1997 a failure occured on 1 of the gyros. The traffic was taken over be TDRS 6

Location

Begin	End	Position
L: 4 Apr 1983		GTO
17 Oct 1983		41°W
1989		79°W
Feb 1995	May 1995	85°E, inclined
Jul 1995	mid-Dec 1995	139°W, inclined
mid-Jun 1996		49°W, inclined (to support ELVs over the South Atlantic)
Technical data

Specifications

S-band

C-band

Ku-band


 TDRS 2

General

Launch date	28 Jan 1986
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	n/a
Launch vehicle	STS 33
End of life

Out of service	28 Jan 1986
Cause	Exploded with Challenger
Technical data

Specifications

S-band

C-band

Ku-band


 TDRS 3

General

Designation	19548 / 88091B
Launch date	29 Sep 1988
Country of origin	United States
Mission	Telecommunications
Geostationary	see below
Launch vehicle	STS 26R

Still partially operational

Location

Begin	End	Position
L: 29 Sep 1988	Apr 1995	171°W
Jun 1995		85°E, inclined: supports GRO and tested with HST
Technical data

Specifications

S-band

C-band

Ku-band


 TDRS 4

General

Designation	19883 / 89021B
Launch date	13 Mar 1989
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	41°W, inclined
Launch vehicle	STS 29

C-band marketed by CCC. On 15 May 1998 the C-band should not be used anymore to avoid interferences with Intelsat 806. In exchange Intelsat will use Intelsat 515 (to be renamed Columbia 515) at 37.5°W.

Technical data

C-band EIRP coverage (dBW)

C-band G/T coverage (dB/K)

Specifications

S-band

C-band

Ku-band

Ku-band downlink:13.750-15.115 GHz. Beacon: 2.211 GHz

Went inclined on 15 Oct 1996


TDRS 4's C-band EIRP coverage


TDRS 4's C-band G/T coverage


 TDRS 5

General

Designation	21639 / 91054B
Launch date	2 Aug 1991
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	174°W
Launch vehicle	STS 43

C-band marketed by CCC

Technical data

C-band EIRP coverage (dBW)

C-band G/T coverage (dB/K)

Specifications

S-band

C-band

Ku-band


TDRS 5's C-band EIRP coverage


TDRS 5's C-band G/T coverage


 TDRS 6

Also called TDRS F

General

Designation	22314 / 93003B
Launch date	13 Jan 1993
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	STS 54

C-band marketed by CCC

Location

Begin	End	Position
L: 13 Jan 1993	Jun 1996	46°W, inclined (reserve)
1 Jul 1996		47°W

Columbia Communications Corp. reached an agreement with NASA for commercial operations (C-band telecommunications) on this satellite. The satellite will be marketed as COLUMBIA/TDRSS AOR-II and will join two other NASA Tracking and Data Relay Satellite System (TDRSS) satellites currently being operated by Columbia under and exclusive agreement with NASA.

Technical data

C-band EIRP coverage (dBW)

C-band G/T coverage (dB/K)

Specifications

S-band

C-band

Ku-band


TDRS 6's C-band EIRP coverage


TDRS 6's C-band G/T coverage


 TDRS 7

Also called TDRS G

General

Designation	23613 / 95035A
Launch date	13 Jul 1995 at 19:55 UT
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	STS 70 + IUS
Location

Begin	End	Position
L: 13 Jul 1995	May 1996	150°W (testing)
Jun 1996		171°W (spare)

The IUS consists of two Solid Rocket Motors (SRM's) which inject the TDRS/IUS into geostationary orbit. The IUS SRM 1 first place the TDRS/IUS into a transfer orbit with an apogee near geosynchronous altitude (burn at 20:55 UT). At the first apogee the IUS SRM 2 fired to place the TDRS/IUS in geostationary orbit (14 Jul at 02:30 UT). The TDRS/IUS was then maneuvered to the appropriate orientation and TDRS 7 separated from the IUS.

Technical data

Specifications

S-band

C-band

Ku-band


TDRS 8
 TDRS 8, 9 & 10

Or TDRS H, I, J

Those 3 satellites will be built by Hughes and made from a modified HS-601 platform. First launch planned in July 1999  NASA required to be reimbursed for failures! Contract worth $481 million

TDRS 8: 147°W, TDRS 9: 172°E

Those satellites will have S-, Ku- and Ka-band capacity with potential data rates up to 650Mb/s. No C-band, Ka-band is new to the system

Technical data

Specifications

Prime contractor	Hughes
Platform	HS-601
Mass at launch
Mass in orbit	1670 kg
Dimension	stowed: 3.4 x 8.4 m
Solar array	21 m
Stabilization	3-axis
DC power	2300 W
Design lifetime	11 years

Telemetry: 2211.5 MHz (0.5, 1 or 4 kbps)

Telemetry: 2206.5 MHz (0.5, 1 or 4 kbps)

Telemetry: 13731 MHz

Telemetry: not yet known

Command: 2035.96 or 2031.81 MHz (2 kbps)

Command: 14786 MHz (+ 15150 MHz)


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 Teamsat

General

Designation
Launch date
Country of origin	Europe
Mission
Perigee/Apogee	GTO
Inclination
Period
Launch vehicle	Ariane 502
Launch site

Will contain 5 experiments provided by ESTEC students.

Technical data

Specifications

Prime contractor
Platform
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime	1 week, duration of the batteries

It will carry a video camera to record and transmit the separation of the cap, the Speltra structure, and of the other Ariane payloads.

Once in GTO the satellite might deploy a sub-satellite named Yes (160 kg) attached by a 30 km long tether. Such experiment was tested with TTS 1 & TTS 2, Seds 1 & Seds 2. This experiment is subject to controversy regarding space debris.


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 Program: Techsat

Israeli small satellite program operated by Technion, the space department of the polytechnic school of Israel. Also called Gurwin after the name of one of the sponsors.


Program: Techsat

Techsat 1

Techsat 2

Techsat 3


 Techsat 1

Also called Gurwin 1

General

Launch date	28 Mar 1995
Country of origin	Israel
Mission	Telecommunications
Launch vehicle	Start #2
End of life

Cause	Launcher failure
Decay	28 Mar 1995

The satellite carried a CCD camera, a radiation detector, an ozone monitor as well as satellite technology tests. It carried a multi-user store-and-forward Amateur Radio digital communications transponder. Gurwin could primarily operate at 9600 bits per second FSK although it was also capable of 1200 bps BPSK.

External resources

http://www.technion.ac.il/pub/projects/techsat/

Technical data

Specifications

Prime contractor	Technion-Israel Institute of Technology in Haifa
Platform
Mass at launch	50 kg
Mass in orbit
Length	0.45 m
Width	0.5 m
Height	0.5 m
Stabilization
DC power
Design lifetime
Frequency chart

145 MHz uplink	1269 MHz uplink	435 MHz downlink
145.850	1269.700	435.225
145.890	1269.800	435.325
145.910	1269.900
145.930	1269.950


 Techsat 2

Also called Gurwin Techsat, or Techsat 1B, also called GO-32 (Gurwin Oscar 32)

General

Designation	25397 / 98043D
Launch date	10 Jul 1998
Country of origin	Israel
Mission	Telecommunications
Launch vehicle	Zenit #29

The cost of the satellite is estimated at $8 million. Launch cost: $400,000

It carries several scientific experiments.

External resources

http://www.technion.ac.il/pub/projects/techsat/

http://techsat.internet-zahav.net/

Technical data

Specifications

Prime contractor	Technion University in Haifa, Israel
Platform
Mass at launch	50 kg
Mass in orbit
Dimension	48 x 48 x 48 cm
Solar array	4 solar panels
Stabilization
DC power	20W
Design lifetime	3 years

It will carry an array of laser reflectorsin order to determine its position with an accuracy of 2-4 inches.

Techsat has a downlink on 435.325 MHz.


 Techsat 3

General

Designation
Launch date	initially planned in 2003
Country of origin	Israel
Mission
Perigee/Apogee
Inclination
Period
Launch vehicle
Launch site

To experiment new technologies


 TELE X

General

Designation	19919 / 89027A
Launch date	2 Apr 1989
Country of origin	Sweden
Operator	NSAB
Mission	Direct TV
Geostationary orbit	5°E, inclined
Launch vehicle	Ariane V30
End of life

Out of service	16 Jan 1998
Cause	deorbited
Technical data

EIRP coverage (dBW)

Specifications

Prime contractor	Eurosatellite & Aérospatiale
Platform	Spacebus-300
Mass at launch	2089 kg
Payload mass	170 kg
Dimension	2.4 x 1.65 x 2.4 m
Solar array	19 m span
Stabilization	3 axis
DC power	BOL: 3200 W
Payload power	2000 W
Design lifetime	7 years
Ku-band

Main transponders	4
Backup transponders	2
Power	230 W (TWTA)
Bandwidth	(2+1) transponders of 27 MHz (2+1) transponders of 40 & 86 MHz
Coverage and EIRP max	Scandinavia: 61 dBW
Polarization	LHCP
Frequencies	Uplink: 17.7-18.1 GHz Downlink: 12.1-12.65 GHz


TELE X's EIRP


 Program: Telecom

French program decided on 20 Feb 1979 operated by France Telecom but designed by the CNES.

Mission: telecommunication to over-sea territories, military communications and TV and data transmission.

The program is to be abandonned once the satellites end their useful lifetime.


Program: Telecom

Telecom 1A

Telecom 1B

Telecom 1C

Telecom 2A

Telecom 2B

Telecom 2C

Telecom 2D


Telecom 1's specifications

Prime contractor	Matra Marconi Espace
Platform	ECS
Mass at launch	1210 kg
Mass in orbit	653 kg
Payload mass	134.4 kg: transponders: 107 kg, antennas: 27.4 kg
Dimension	2.06 x 1.9 x 2.2 m
Solar array	16 m span
Stabilization	3 axis
DC power	EOL: equinox: 1483 W, solstice: 1450 W
Payload power	717.3 W
Design lifetime	7 years

Telemetry is transmitted in S-band in backup mode and in C-band in normal mode.


Telecom 1's C-band

Main transponders	4
Backup transponders	2
Power	8.5 W (TWTA)
Bandwidth	1 transponder of 36 MHz 3 transponder of 120 MHz
Coverage & EIRP max	Hemispheric: 29.5 dBW Spot: to West Indies and Guyana (transponder #2): 35 dBW
Polarization	LHCP
Transponder frequency chart (GHz)

RHCP Uplink	Transponder	LHCP Downlink
5.945	C1	3.720
6.040	C2	3.775
6.135	C3	3.910
6.360	C4	4.135


Telecom 1's X-band (7.3 and 8 GHz)

Main transponders	2
Power	20 W (TWTA)
Bandwidth	40 MHz
Coverage	Atlantic and Indian ocean
EIRP max	31.3 dBW

Syracuse is the communication system used on the transponders


Telecom 1's Ku-band

Main transponders	6
Backup transponders	3
Power	20 W (TWTA)
Bandwidth	36 MHz
Coverage	Europe
EIRP max	49 dBW
Polarization	linear V
Transponder frequency chart (GHz)

Horizontal Uplink	Transponder	Vertical Downlink
14.022	K1	12.522
14.064	K2	12.564
14.106	K3	12.606
14.148	K4	12.648
14.190	K5	12.690
14.232	K6	12.732


Telecom 2's specifications

Prime contractor	Matra Marconi Espace
Platform	Eurostar 2000
Mass at launch	2225 kg
Mass in orbit	1005 kg
Payload mass	407.4 kg: transponders: 307.4 kg, antennas: 100 kg
Dimension	2 x 2.1 x 2 m
Solar array	22 m span
Stabilization	3 axis
DC power	BOL: 3850 W EOL: equinox: 3397 W, solstice: 3143 W (nickel hydrogen 86 A/H batteries)
Payload power	2549 W
Design lifetime	10 years


Telecom 2's C-band

Main transponders	10
Backup transponders	4
Power	11.5 W
Bandwidth	4 transponders of 90 MHz 6 transponders of 50 MHz
Coverage (uplink)	Global
Coverage (downlink)	Spot: France, St Pierre & Miquelon, West Indies and Guyana Semi global: Reunion
EIRP max	Spot: 39 dBW Semi global: 32.5 dBW
Polarization	circular R/L
Uplink	5.925-6.425 GHz
Transponder frequency chart (GHz)

LHCP Downlink	Transponder	RHCP Downlink
	C1A	3.710
	C1B	3.738
	C2A	3.768
	C2B	3.795
3.849	C3
3.907	C4
3.965	C5
4.019	C6
4.154	C7


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Telecom 2's X-band

Main transponders	4+2
Backup transponders	2+1
Power	(2+1) transponders of 40 W (TWTA) (4+2) transponders of 20 W (TWTA)
Bandwidth	3 transponders of 40 MHz 1 transponder of 60 MHz 1 transponder of 80 MHz
Coverage	global: center Europe & mobile
EIRP max	31.3 dBW
Access	MRF (Multiple à Répartition en Fréquence) or MRC (Multiple à Répartition par Code)
Uplink	7.9-8.395 GHz
Downlink	7.25-7.745 GHz


Telecom 2's Ku-band

Main transponders	11
Backup transponders	4
Power	55 W (TWTA)
Bandwidth	36 MHz
Coverage and EIRP max	Europe: 52.5 dBW
Polarization	linear H/V
Uplink	14.0-14.25 GHz
Transponder frequency chart (GHz)

Horizontal  Uplink	Horizontal  Downlink	Transponder	Vertical  Downlink	Vertical  Uplink
14.022		K1	12.522
	12.543	K7		14.043
14.064		K2	12.564
	12.585	K8		14.085
14.106		K3	12.606
	12.627	K9		14.127
14.148		K4	12.648
	12.669	K10		14.169
14.190		K5	12.690
	12.711	K11		14.211
14.232		K6	12.732


Telecom 2's EIRP (Ku-band)


 Telecom 1A

General

Designation	15159 / 84081B
Launch date	4 Aug 1984
Country of origin	France
Mission	Telecommunications
Geostationary orbit	8°W
Launch vehicle	Ariane V10

Had insulation failures that caused the communication system Syracuse problems

End of life

Out of service	Apr 1992?
Technical data

Specifications

C-band

X-band

Ku-band

Apogee kick motor: Mage 2


 Telecom 1B

General

Designation	15678 / 85035B
Launch date	8 May 1985
Country of origin	France
Mission	Telecommunications
Geostationary orbit	5°W
Launch vehicle	Ariane V13
End of life

Out of service	15 Jan 1988
Cause	Stabilization power supply failure
Technical data

Specifications

C-band

X-band

Ku-band


 Telecom 1C

General

Designation	18952 / 88018B
Launch date	11 Mar 1988
Country of origin	France
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V21
Location

Begin	End	Position
L: 11 Mar 1988		5°W
Aug 1992	Feb 1996	3°E (inclined since fall 1995)
End of life

Out of service	Feb 1996
Cause	Moved to the junk orbit
Technical data

Specifications

C-band

X-band

Ku-band


 Telecom 2A

General

Designation	21813 / 91084A
Launch date	16 Dec 1991
Country of origin	France
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V48
Location

Begin	End	Position
L: 16 Dec 1991	Apr 1992 (tests)	3°E
Apr 1992		8°W

Test from Mulhouse in Ku-band, Pleumeur Bodou in C-band and from Southern France in X-band. It entered service for the Olympic Games and then it was re-tested in eclipse period. Finaly it was positioned in 8°W

In Jul 1999 the satellite was incorporated in the Eutelsat fleet. The partnership between France Telecom and Eutelsat will last till the end of the nominal lifetime of the satellite, anticipated in 2004. This agreement will enable Eutelsat to take over the 11 Ku-band transponders of the satellite.

Technical data

Specifications

C-band

X-band

Ku-band

EIRP coverage (dBW)

C-band

Ku-band

Beacons: 3.816 GHz RHCP, 12.5005 GHz V, 12.5025 GHZ H


Telecom 2A's C-band EIRP


 Telecom 2B

General

Designation	21939 / 92021A
Launch date	15 Apr 1992
Country of origin	France
Mission	Telecommunications
Geostationary orbit	5°W
Launch vehicle	Ariane V50

Entered in service on 22 Jul 1992

Technical data

Specifications

C-band

X-band

Ku-band

EIRP coverage (dBW)

C-band

Ku-band

Beacons: 3.815 GHz RHCP (or 3737.500 MHz?), 12.5005 GHZ V, 12.5025 GHZ H


Telecom 2's C-band EIRP


 Telecom 2C

General

Designation	23730 / 95067A
Launch date	6 Dec 1995
Country of origin	France
Mission	Telecommunications
Geostationary orbit	3°E
Launch vehicle	Ariane V81

Tested at 1°E

Technical data

Specifications

C-band

X-band

Ku-band

EIRP coverage (dBW)

C-band

Ku-band

The spacecraft has an R-4D-12 liquid apogee engine. The mass of Telecom 2C is 1120 kg, with a fuel load of 1163 kg giving a launch mass of 2283 kg.

Beacons: 12.5005 GHz V, 12.5025 GHz H


 Telecom 2D

General

Designation	24209 / 96044B
Launch date	8 Aug 1996
Country of origin	France
Mission	Telecommunications
Geostationary orbit	5°W
Launch vehicle	Ariane V90

Had interference problems with the 1° appart Amos 1 satellite

S-band beacon: 2207.130 MHz

Technical data

Specifications

C-band

X-band

EIRP coverage (dBW)

C-band

Ku-band

Ku-band

Main transponders	11
Backup transponders	4
Power	55 W (TWTA)
Bandwidth	36 MHz
Coverage and EIRP max	Europe: 52.5 dBW
Polarization	linear H/V
Uplink	14.0-14.25 GHz

Beacons: 11.4525 GHz V, 11.4505 GHz H

Transponder frequency chart (GHz)

Horizontal Uplink	Horizontal Downlink	Transponder	Vertical Downlink	Vertical Uplink
	11.472	K1		14.272
14.293		K7	11.493
	11.514	K2		14.314
14.335		K8	11.535
	11.556	K3		14.356
14.377		K9	11.577
	11.598	K4		14.398
14.419		K10	11.619
	11.640	K5		14440
14.461		K11	11.661
	11.682	K6		14.482


 Program: Teledesic

Teledesic is a Delaware corporation owned by McCaw Cellular Communications Inc. and Microsoft Corporation. It was founded in 1990 and the FCC application was made in March 1994.

Teledesic proposes to construct, launch, and operate a constellation consisting of 840 satellites in non-geostationary satellite orbits.  The constellation is organized into 21 circular orbit planes with each plane containing a minimum of 40 active satellites spaced evenly, and up to four operational spares per orbital plane.  Additional spares will be constructed to replace failed satellites so that no orbital plane contains fewer than 40 operational satellites at any time. The orbit planes are at a sun-synchronous inclination, 98.2 degrees, which keeps them at a constant angle relative to the sun. These satellites will operate at an altitude between 695 and 700 kilometers (LEO) and will communicate with earth stations operating above a 40 degree elevation angle.

Teledesic was authorized in March 1997 to operate in the United States in the 28.6 - 29.1 GHz (uplink) and 18.8 -19.3 GHz (downlink) band segments for its service links and 27.6-28.4 GHz bands for its "gigalink" gateway terminal uplink and the 17.8-18.6 GHz band for its "gigalink" gateway terminal downlinks.  Teledesic will also use inter-satellite links (in the 65-71 GHz band) to interconnect each satellite with eight other satellites in the same and adjacent planes.

In late April 1997 Boeing decided to invest up to $100 million for 10 percent of the current ownership of Teledesic. As the prime contractor, Boeing will lead an international effort to design, build and launch the Teledesic Network. The estimated contract value will be $9 billion. Boeing proposed to reduce the constellation to 288 satellites using new technology. It is foreseen that Sea Launch will be a major space carrier to setup the Teledesic network. In Oct 1997 it is said that the orbit could be changed to circular, 1375 km.

In May 1998 it was announced that Motorola would cancel its Celestri program and take a 26% stake into Teledesic. This has yet to be approved. Motorola would lead the industrial and technological team comprising Boeing, and MMS.

In Dec 1998 it is rumored that the system would be made a 3-ton satellites (approx. 50 of them) and that the system would not be operational before 2005.

In Jan 1999 Teledesic filled for a 30 medium-earth-orbit (MEO) satellite system dubbed Ku-Band Supplement (KuBS)

In Jul 1999 an agreement with Lockheed Martin was revealed. It defines the launch vehicles as Proton and Atlas 5. Three launches for both vehicles were booked and 5 more on both rockets are options. Nor the financial terms nor specifications of the satellites were diclosed. A second agreement with Motorola was disclosed. It makes Motorola the main contractor for the satellites.

Service is targeted to begin in 2003.

External resources

http://www.teledesic.com

http://www.fcc.gov/Bureaus/International/Orders/1997/da970527.txt


Program: Teledesic

Teledesic 1


 Teledesic 1

Also called Batsat and T1

General

Designation	25234 / 98012B
Launch date	26 Feb 1998
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	535/581 km
Inclination	97.7°
Period	95.8 min
Launch vehicle	Pegasus XL
Launch site	Vandenberg

Batsat was the name used to cover the real purpose of the satellite; it was advertised as a small technology satellite to operate in X- and Ka-band.

Is reported not to operate as planned.

Technical data

Specifications

Prime contractor	Orbital & Boeing
Platform	Microstar
Mass at launch	70 kg
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime

Carries a Boeing Ka-band payload


 Program: Telstar

American telecommunication program operated by Loral Skynet after being AT&T Skynet

Skynet was sold to Loral in 1997 so the operator will become Loral Skynet.  The deal was fixed at $478.1 million

External resources

http://www.loralskynet.com/

http://sulu.lerc.nasa.gov/dglover/telstar.html


Program: Telstar

Telstar 1

Telstar 2

Telstar 301

Telstar 302

Telstar 303

Telstar 401

Telstar 402

Telstar 402R

Telstar 5

Telstar 6

Telstar 7

Telstar 8


Telstar 1 & 2's specifications

Prime contractor	Bell Labs
Platform	Telstar
Mass at launch	80 kg
Mass in orbit
Diameter	86 cm
Height
Stabilization	Spin?
DC power
Design lifetime


Telstar 1 & 2's C-band

Main transponders	1
Backup transponders
Power	2 W
Bandwidth	600 phone circuits
Coverage
EIRP max
Polarization


Telstar 3's specifications

Prime contractor	Hughes
Platform	HS-376
Mass at launch	3423 kg (with PAM-D)
Mass in orbit	625 kg
Diameter	2.16 m
Height	6.8 m deployed
Stabilization	Spin stabilized
DC power	BOL: 800 W
Design lifetime	10 years


Telstar 3's C-band

Main transponders	24
Backup transponders
Power	8.5 W (TWTA)
Bandwidth	36 MHz
Coverage and EIRP max	CONUS: 34 dBW
Polarization	linear H/V


Telstar 4's specifications

Prime contractor	GE Astro Space
Platform	GE 7000
Mass at launch	3331 kg
Mass in orbit
Dimension	4.08 x 2.22 x 2.54 m
Solar array	24.5 m span
Stabilization	3 axis
DC power	BOL: 6400 W EOL: 5000 W
Design lifetime	12 years

Cross-strapping possible in both directions


Telstar 4's C-band

Main transponders	24
Backup transponders	4
Power	variable 11-21 W
Bandwidth	36 MHz
Coverage
EIRP max	38 dBW
Polarization	linear H/V


Telstar 4's Ku-band

Main transponders	16 to 24 (variable)
Backup transponders	12
Power	60 W standard, up to 120 W (TWTA)
Bandwidth	54 MHz & 27 MHz
Coverage
EIRP max	50 dBW
Polarization

8 transponders can be splited in 16 transponders of 27 MHz. The 120 W transponders are achieved by using the backup transponders


Telstar 4's Ku-band frequency chart
 Telstar 4's Ku-band frequency plan (GHz)

Horizontal Uplink	Horizontal Downlink	Transponder	Vertical Downlink	Vertical Uplink	Notes
14.030		1	11.730
	11.743	2		14.043
14.090		3	11.790
	11.803	4		14.103
14.150		5	11.850		120 W capable
	11.863	6		14.163	120 W capable
14.210		7	11.910		120 W capable
	11.923	8		14.223	120 W capable
14.271		9 (A/B)	11.971		full or A: 120 W capable
	11.984	10 (A/B)		14.284	full or A: 120 W capable
14.333		11 (A/B)	12.033		full or A: 120 W capable
	12.046	12 (A/B)		14.346	full or A: 120 W capable
14.395		13 (A/B)	12.095		full or A: 120 W capable
	12.108	14 (A/B)		14.408	full or A: 120 W capable
14.457		15 (A/B)	12.157		full or A: 120 W capable
	12.170	16 (A/B)		14.470	full or A: 120 W capable


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Telstar 30x's EIRP coverage


Telstar 4's C-band EIRP coverage


Telstar 4's Ku-band EIRP coverage


Telstar 4's C-band horizontal G/T coverage


Telstar 4's C-band vertical G/T coverage


Telstar 4's Ku-band horizontal G/T coverage


Telstar 4's Ku-band vertical G/T coverage


 Telstar 1

General

Designation	00340 / 62029A
Launch date	10 Jul 1962
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	942/5646 km
Inclination	44.8°
Period	157.8 min
Launch vehicle	Thor Delta #11
Launch site	Cape Canaveral

First live broadcasts between the United States and Europe. At the end of 1962, after 4 months, a transistor of the system failed. AT&T managed to repair it! First satellite equipped with transponders and thus amplification: thus first active satellite.

The transistor failure has been blamed on the explosion of a DOD 1.5 megaton explosion at 160 km altitude (project Stafish) days before launch. Source: Appointment on the Moon, Richard S. Lewis, p. 308

End of life

Out of service	21 Feb 1963
Technical data

Specifications

C-band


 Telstar 2

General

Designation	00573 / 63013A
Launch date	7 May 1963
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	966/10807 km
Inclination	42.8°
Period	225.3 min
Launch vehicle	Thor Delta #18
Launch site	Cape Canaveral
Mass at launch	79.5 kg
End of life

Out of service	May 1965
Technical data

Specifications

C-band


 Telstar 301

General

Designation	14234 / 83077A
Launch date	28 Jul 1983
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Thor Delta #171
Launch site	Cape Canaveral
Location

Begin	End	Position
L: 28 Jul 1983		96°W
Mar 1994	Aug 1994	107.3°W (Anik E2 replacement)
Jan 1995	Sep 1996	see Arabsat 1E
End of life

Out of service	Sep 1996
Technical data

Specifications

C-band

Transponder frequency chart


 Telstar 302

General

Designation	15237 / 84093D
Launch date	1 Sep 1984
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	STS 16
Location

Begin	End	Position
L: 1 Sep 1984	Jan 1997	85°W
Feb 1997	Aug 1997	97°W, inclined
End of life

Out of service	5 Sep 1997
Cause	deorbited
Technical data

EIRP coverage (dBW)

Specifications

C-band

Transponder frequency chart


 Telstar 303

General

Designation	15826 / 85048D
Launch date	19 Jun 1985
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	STS 25
Location

Begin	End	Position
L: 19 Jun 1985		125°W
< May 1992	May 1996	123°W, inclined
Jun 1996	Jan 1999	120°W, inclined
End of life

Out of service	Jan 1999
Cause	deorbited
Technical data

EIRP coverage (dBW)

Specifications

C-band

Transponder frequency chart


 Telstar 401

General

Designation	22927 / 93077A
Launch date	16 Dec 1993
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	97°W
Launch vehicle	Atlas Centaur

Entered service on 1 Feb 1994

The loss is evaluated about $132.5 million

End of life

Out of service	11 Jan 1997
Cause	destroyed by a magnetic storm
Technical data

Specifications

C-band

Ku-band

Transponder frequency chart

Ku-band Transponder frequency chart

EIRP coverage (dBW)

C-band

Ku-band


 Telstar 402

General

Designation	23249 / 94058A
Launch date	9 Sep 1994
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	was expected in slot 89°W
Launch vehicle	Ariane V67

Cost: $200 million

End of life

Out of service	9 Sep 1994
Cause	Explosion after pressurisation

The second of two pyrovalve firings to enable its propulsion system set off an explosion and a disastrous leak. A lawsuit by AT&T and a countersuit by Lockheed Martin were settled out of court in 1995 on this subject.

Technical data

Specifications

C-band

Ku-band

Transponder frequency chart

Ku-band Transponder frequency chart


 Telstar 402R

Was renamed Telstar 4 on 28 Feb 1997

General

Designation	23670 / 95049A
Launch date	24 Sep 1995
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	89°W
Launch vehicle	Ariane V78

Started serving on 1st December 1995.

A Canadian company, Tee-Comm Electronics, created AlphaStar in March 1995 by leasing more than half the 24 Ku-band transponders on Telstar 402R. The new service to 61-cm home antennas, offers 110 television and 20 audio channels. It will be expanded to over 200 channels in 1997 using Telstar 5. Customers in Alaska and Hawaii will also be served via slightly larger (76-cm) antennas.

The satellite was renamed Telstar 4 after the loss of Telstar 401

Technical data

Specifications

C-band

Ku-band

C-band Transponder frequency chart

Ku-band Transponder frequency chart

EIRP coverage (dBW)

C-band

Ku-band

G/T coverage (dB/K)

C-band horizontal

C-band vertical

Ku-band horizontal

Ku-band vertical


 Telstar 5

General

Designation	24812 / 97026A
Launch date	24 May 1997
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	97°W
Launch vehicle	Proton #247

Entered service in early July

Technical data

EIRP coverage (dBW)

C-band

Ku-band

Specifications

Prime contractor	Space Systems/Loral
Platform	FS-1300
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization	3 axis
DC power	? (3200 W RF)
Design lifetime	15 years
C-band

Main transponders	24
Backup transponders
Power	16 W
Bandwidth	36 MHz
Coverage	US (50 states) + Caribbean
EIRP max	CONUS: 37 dBW Alaska: 32 dBW Hawaii: 36 dBW Puerto Rico/US Virgin Islands: 33 dBW
Polarization	linear H/V

C-band Transponder frequency chart

Ku-band

Main transponders	28
Backup transponders
Power	100 W
Bandwidth	24 transponders of 27 MHz 4 transponders of 54 MHz
Coverage	US (50 states) + Caribbean, Mexico and Southern Canada
EIRP max	CONUS: 46.5 dBW Alaska: 42 dBW Hawaii: 45.5 dBW Puerto Rico/US Virgin Islands: 44.7 dBW Mexico: 43.5 dBW Southern Canada: 44.5 dBW
Polarization	linear H/V

Ku-band: No variable power nor cross-strapping like on the 40x series


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Telstar 5's C-band EIRP


Telstar 5's Ku-band EIRP


 Telstar 6

General

Designation	25626 / 99005A
Launch date	15 Feb 1999
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	93°W
Launch vehicle	Proton #263

Started operational service on 15 March 1999.

Technical data

EIRP coverage (dBW)

C-band

Ku-band

Specifications

Prime contractor	SS/L
Platform	FS-1300
Mass at launch	3700 kg
Mass in orbit
Dimension
Solar array
Stabilization	3-axis
DC power	? (3200 W RF)
Design lifetime	15 years
C-band

Main transponders	24
Backup transponders
Power	20 W
Bandwidth	36 MHz
Coverage	CONUS + Puerto Rico, the Caribbean, and parts of Canada and Latin America
EIRP
Polarization	linear

beacons: 4.1955 & 4.1965 GHz

Transponder frequency chart

Ku-band

Main transponders	28
Backup transponders
Power	100 W (TWTA)
Bandwidth	4 x 54 Mhz  24 x 27 MHz
Coverage
EIRP
Polarization	linear

Ku-band: No variable power nor cross-strapping like on the 40x series

The Ku TWTAs were changed just before launch, the satellite had to be flown back to California in Oct 1998. The replacement was completed in early Dec 1998. The original satellite's travelling wave tubes (TWTs) supplied by AEG of Germany were susceptible to thermally induced fatigue. Originally this replacement was planned to be made at launch site.

Ku-band Transponder frequency chart (GHz)

Horizontal Uplink	Horizontal Downlink	Transponder	Vertical Downlink	Vertical Uplink	Notes
14.0285		1	11.7285		54 MHz
	11.735	2		14.735	54 MHz
14.0895		3	11.7895		54 MHz
	11.796	4		14.096	54 MHz
14.136		5	11.836
	14.8452	6		14.1425
14.167		7	11.867
	11.8735	8		14.1735
14.198		9	11.898
	11.9045	10		14.2045
14.229		11	11.929
	11.9355	12		14.2355
14.260		13	11.960
	11.9665	14		14.2665
14.291		15	11.991
	11.9975	16		14.2975
14.322		17	12.022
	12.0285	18		13.3285
14.353		19	12.053
	12.0595	20		14.3595
14.384		21	12.084
	12.0905	22		14.3905
14.415		23	12.115
	12.1215	24		14.4215
14.446		25	12.146
	12.1525	26		14.4525
14.477		27	12.177
	12.1835	28		14.4835


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Telstar 6's C-band EIRP coverage


Telstar 6's Ku-band EIRP coverage


 Telstar 7

General

Designation
Launch date	early 1999
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	129°W
Launch vehicle	Ariane

The satellite was originally to be launched aboard the first Atlas 3A but this was changed for Ariane.

Could be identical to Loralsat 101.

Technical data

EIRP coverage (dBW)

C-band

Ku-band

Specifications

Prime contractor	SS/L
Platform	FS3000
Mass at launch	3753 kg
Mass in orbit
Dimension
Solar array
Stabilization	3-axis
DC power
Design lifetime	15 years
C-band

Main transponders	24
Backup transponders
Power	16 W
Bandwidth
Coverage
EIRP max
G/T max
Polarization
Ku-band

Main transponders	28
Backup transponders
Power	100 W
Bandwidth	4 x 54 MHz 24 x 27 MHz
Coverage
EIRP max
G/T max
Polarization

Ku-band: No variable power nor cross-strapping like on the 40x series


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Telstar 7's C-band EIRP coverage


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Telstar 7's Ku-band EIRP coverage


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 Telstar 8

Should be a ground backup for satellites of the 5 to 7 series, same design


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 Temisat

Telespazio Micro Satellite

General

Designation	22783 / 93055B
Launch date	31 Aug 1993 at 04:40 UT, released at 15:20 UT from Meteor 2-21
Country of origin	Italy
Operator	Telespazio
Mission	Telecommunications
Perigee/Apogee	932/967 km
Inclination	82.5°
Period	104 min
Launch vehicle	Cyclone 3 #106

Will relay environmental data from field sites

Technical data

Specifications

Prime contractor	Kayser-Threde
Mass at launch	30 or 42 kg
Dimension	0.35 x 0.35 x 0.35 m
Stabilization	3 axis (magnetotorquer)
Design lifetime	5 years
Payload

Frequency	148-150 MHz 137-138 MHz
Uplink	10 channels (9 simultaneously) 1200 baud
Downlink	6 channels (3 simultaneously) 2 x 4800 baud + 1200 baud


 Program: Tempo

DBS satellite program operated by Tempo Satellite Inc, a wholly-owned subsidiary of Tsat. Aimed at direct TV broadcasting to Conus, Alaska, Hawaii and Puerto Rico.

2 satellites planned. The 2 satellites costed $487 million

Since TCI couldn't get its own GEO slot, they tried to operate a DBS service from a Canadian slot, but the FCC refused. In Jan 1999 it was announced that Hughes Electronics would acquire Tempo and other satellite TV business stuff. Cost: $1.82 billion, $500 for Tempo alone

DirecTV would operate the medium-power PrimeStar business for a period of approximately two years, during which time it will try to move subscribers to to the high-power DirecTV service. FCC has approved the merger in mid-Feb 1999. Hughes completed the acquisition in Jun 1999. They now own the 2 satellites and the broadcast licence at 119 deg West.


Program: Tempo

Tempo 1

Tempo 2


Tempo's specifications

Prime contractor	Space Systems/Loral
Platform	FS-1300
Mass at launch	3558 kg
Mass in orbit
Dimension
Solar array	30 m span
Stabilization
DC power	BOL: 10000 W
Design lifetime	10 years

Solar pannels provided by Dasa

Telemetry and command: 12.201 GHz, 12.202 GHz, 12.203 GHz and 12.204 GHz, with a 450 kHz bandwidth


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Tempo's Ku-band

Main transponders	32
Backup transponders
Power	107 W (TWTA)
Bandwidth	24 MHz
Coverage	CONUS+
EIRP max
Polarization

Can be operated as 16 transponders of 214 W each


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 Tempo 1

General

Designation
Launch date	initially planned in Jun 1996
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	119°W
Launch vehicle	Proton
Technical data

Specifications

Ku-band


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 Tempo 2

General

Designation	24748 / 97011A
Launch date	8 Mar 1997
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Atlas 2A (#106)

The satellite experienced solar flare after launch (11 Apr 1997) and its solar arrays have experienced problems. The satellite is said to suffer from "temporary power fluctuations". It is also claimed that the satellite was not operating normally before the solar flare. Up to 4 transponders might be out of order.

TSAT did not accept the satellite (as of Nov 1997) since it is believed that only 85% of the design output power can be achieved. It the satellite is not usable, SS/L has 29 months to provide a replacement satellite.

Location

Begin	End	Position
L: 8 Mar 1997	Apr 1997	109.5°W
mid-Apr 1997		119°W
Technical data

Specifications

Ku-band


 Terriers

Tomographic Experiment using Radiative Recombinative Ionospheric EUV and Radio Sources, also called STEDI 2 and UNEX 02

General

Designation	25735 / 99026A
Launch date	18 May 1999
nCountry of origin	United States
Mission	Scientific: ionosphere study
Perigee/Apogee	550 km sunsynchronous (9:00)
Inclination	97.7°
Period
Launch vehicle	Pegasus #27

After launch the satellite experienced attitude control problems causing the battery to discharge.

End of life

Out of service	yes?
Cause
Decay
External resources

http://net.bu.edu/terriers.html

Technical data

Specifications

Prime contractor	Boston University
Platform	Aeroastro
Mass at launch	125 kg
Mass in orbit
Dimension
Solar array
Stabilization	spin stabilized
DC power	31 W
Design lifetime	1 year

The satellite bus is being built by AeroAstro while the instrument package is produced by the Center for Space Physics at Boston University and the University of Illinois at Urbana-Champain (UIUC). Cleveland Heights High School is also constructing a small experiment to go on the satellite.

Terriers primary goal is to, for the first time, demonstrate meridional 2D (latitude-altitude) and global 3D imaging of the ionospheric electron density and thermospheric photo-emission profiles using EUV emissions and tomographic techniques. Secondary goals of Terriers focus on the study of several ionospheric and thermospheric phenomena through the use of this novel combination of techniques and observations. As a tertiary goal, Terriers will test the utility of long term solar EUV irradiance measurements using a new technique that we have recently proven on a sounding rocket. GISSMO measures the solar EUV, one of the primary sources for the upper atmosphere.

Telemetry: 2.2729 GHz

Might also use 150/400 MHz


 Program: Thaicom

Thai telecommunication program operated by Shinawatra, a national operator which has secured a 30-year concession.


Program: Thaicom

Thaicom 1

Thaicom 2

Thaicom 3

Thaicom 4


Thaicom 1 & 2's specifications

Prime contractor	Hughes
Platform	HS-376L
Mass at launch	1080 kg
Mass in orbit	723 kg
Diameter	2.16 m
Height	7.7 m deployed (2.8 m stowed)
Stabilization	Spin stabilized
DC power	BOL: 700 W
Design lifetime	10 years
Apogee motor	Thiokol Star 30


Thaicom 1 & 2's C-band

Main transponders	10
Backup transponders	2
Power	11 W
Bandwidth	36 MHz
Coverage and EIRP max	South Eastern Asia: 37 dBW A spot covers central Europe
Polarization	1: V linear 2: H linear


Thaicom 1 & 2's Ku-band

Main transponders	2
Backup transponders	1
Power	47 W (TWTA)
Bandwidth	54 MHz
Coverage and EIRP max	Thailand: 50 dBW
Polarization	1: H linear 2: V linear


Thaicom 1 & 2 Ku-band's EIRP


 Thaicom 1

Also called Thaicom 1A

General

Designation	22931 / 93078B
Launch date	18 Dec 1993
Country of origin	Thailand
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V62

First Thai satellite

Location

Begin	End	Position
L: 18 Dec 1993	Jul 1997	78.5°E
Aug 1997		120°E
Technical data

Specifications

C-band

Ku-band

EIRP coverage (dBW)

C-band

Ku-band


Thaicom 1's C-band EIRP


 Thaicom 2

General

Designation	23314 / 94065B
Launch date	8 Oct 1994
Country of origin	Thailand
Mission	Telecommunications
Geostationary orbit	78.5°E
Launch vehicle	Ariane V68
Technical data

Specifications

C-band

Ku-band

EIRP coverage (dBW)

C-band

Ku-band


Thaicom 2's C-band EIRP


 Thaicom 3

General

Designation	24768 / 97016A
Launch date	16 Apr 1997
Country of origin	Thailand
Mission	Telecommunications
Geostationary orbit	78.5°E
Launch vehicle	Ariane V95

Cost: over $200 million (including satellite, launch, ground stations and insurance)

test slot: 87.5°E

Technical data

EIRP coverage (dBW)

C-band, quasi global

C-band, zone

Ku-band

Specifications

Prime contractor	Aerospatiale
Platform	Spacebus-3000A
Mass at launch	2650 kg
Dry Mass	1179 kg
Dimension	3.25 x 2.26 x 3.48 m
Solar array	26.27 m span
Stabilization	3-axis
DC power	BOL: 6400 W
Design lifetime	14 years
C-band

Main transponders	24
Backup transponders
Power	6 x 42 W 18 x 19 W
Bandwidth	36 MHz
Coverage & EIRP max	Quasi global: 37.5 dBW (6 transponders in 3.4 - 3.7 GHz range) Zone (sub continent): 38 dBW
Polarization	linear

ISRO hired 6 transponders to increase their capacity for a year.

C-band transponder frequency chart (GHz)

Horizontal Downlink	Transponder	Vertical Downlink	Beam
	1VE	3.425	Zone
	2VE	3.465	Zone
3.480	1HE		Quasi global
	3VE	3.505	Zone
3.520	2HE		Quasi global
	4VE	3.545	Zone
3.560	3HE		Quasi global
	5VE	3.585	Zone
3.600	4HE		Quasi global
	6VE	3.625	Zone
3.640	5HE		Quasi global
3.680	6HE		Quasi global
	1VS	3.720	Zone
	2VS	3.760	Zone
	3VS	3.800	Zone
	4VS	3.840	Zone
	5VS	3.880	Zone
	6VS	3.920	Zone
	7VS	3.960	Zone
	8VS	4.000	Zone
	9VS	4.040	Zone
	10VS	4.080	Zone
	11VS	4.120	Zone
	12VS	4.160	Zone
Ku-band

Main transponders	14
Backup transponders
Power	100 W
Bandwidth	36 MHz
Coverage & EIRP max	Thailand: 55 dBW India (steerable): 50 dBW
Polarization	linear
Frequencies	12.25 - 12.75 GHz

Only 38 transponders can be on simultaneously

Ku-band transponder frequency chart (GHz)

Uplink	Transponder	Downlink	Beam
14.0198	55	12.2718	Thailand or steerable
14.0613	56	12.3133	Thailand or steerable
14.1024	57	12.3548	Thailand or steerable
14.1443	58	12.3963	Thailand or steerable
14.1858	59	12.4378	Thailand
14.2273	60	12.4793	Thailand
14.2688	61	12.5208	Thailand
14.3103	62	12.5623	Thailand
14.3513	63	12.6038	Thailand
14.4055	64	12.6575	Thailand
14.4681	65	12.7201	Thailand
14.2066	66	12.4586	steerable
14.2481	67	12.5001	steerable
14.2896	68	12.5416	steerable


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Thaicom 3's C-band quasi global EIRP map


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Thaicom 3's C-band zone EIRP map


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Thaicom 3's Ku-band EIRP map


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 Thaicom 4

General

Designation
Launch date	2000
Country of origin	Thailand
Mission	Telecommunications
Geostationary orbit	120°E, colocated with Thaicom 1
Launch vehicle	Ariane
Launch site

Cost: $200 million

identical to Thaicom 3

The order was cancelled and the satellite is to be transformed for a yet-to-be-found customer.

Technical data

Specifications

Prime contractor	Aerospatiale
Platform	Spacebus 3000A
Mass at launch	2600/2700 kg
Mass in orbit
Length
Width
Height
Stabilization
DC power
Design lifetime

The 2 C-band and 3 Ku-band antennas are manufactured by Spar Aerospace Ltd.

C-band

Main transponders	24
Backup transponders
Power
Bandwidth
Coverage & EIRP max	Thailand: ? Vietnam to Western Europe: 34.5 dBW
Polarization
Ku-band

Main transponders	12
Backup transponders
Power
Bandwidth
Coverage
EIRP max
Polarization


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 Program: Thor

Named for Norwegian explorer Thor Heyerdahl

Telecommunication program operated by Telenor


Program: Thor

Thor 1

Thor 2

Thor 3


 Thor 1

General

Old name	BSB 2
Country	Norway
Mission	Direct TV
Geostationary orbit	0.8°W

Bought for $42 million

Technical data

EIRP Coverage (dBW)

Specifications

Ku-band


Thor 1's EIRP


 Thor 2

General

Designation	24808 / 97025A
Launch date	20 May 1997
Country of origin	Norway
Mission	Telecommunications
Geostationary orbit	1°W
Launch vehicle	Delta 2 #243

To be delivered in orbit

Technical data

EIRP Coverage (dBW)

Specifications

Prime contractor	Hughes
Platform	HS-376HP (49th to be built)
Mass at launch
Mass in orbit
Dimension
Solar array	(gallium arsenide)
Stabilization	spin stabilized
DC power	EOL: 1400 W
Design lifetime	11 years
Ku-band

Main transponders	15
Backup transponders
Power	40 W (TWTA)
Bandwidth	26 MHz
Coverage	Northern Europe
EIRP max	52 dBW
Polarization	linear H/V

A wiring error in the antenna waveguides at construction time cause the polarization to be reverse. Financial compensation is expected.

Transponder frequency chart (GHz)

Transponder	Polarization	Frequency
1	V	11.215625
2	H	11.228625
3	V	11.246875
4	H	11.260750
5	V	11.278125
6	H	11.292875
7	V	11.309375
8	H	11.325000
9	V	11.340625
10	H	11.357125
11	V	11.371875
12	H	11.389250
13	V	11.403125
14	H	11.421375
15	V	11.434375


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Thor 2's EIRP


 Thor 3

General

Designation	25358 / 98035A
Launch date	10 Jun 1998
Country of origin	Norway
Mission	Telecommunications
Geostationary orbit	0.8°W
Launch vehicle	Delta 2 #258

Delivered in orbit.  The contract for this satellite has an option for another Hughes satellite

Technical data

EIRP Coverage (dBW)

Specifications

Prime contractor	Hughes
Platform	HS-376HP
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization
DC power	1400 W
Design lifetime	11.5 years

has a Thiokol Star 30 apogee motor

Ku-band

Main transponders	14
Backup transponders
Power	47 W
Bandwidth	33 MHz
Coverage	Scandinavia and central Europe
EIRP
Polarization
Frequencies	downlink: 11.7 - 12.5 GHz
Transponder frequency chart (GHz)

Transponder	Polarization	Frequency
1	V	11.727
2	H	11.747
6	H	11.823
18	H	12.054
23	V	12.149
24	H	12.169
27	V	12.226
28	H	12.245
31	V	12.303
32	H	12.322
35	V	12.380
36	H	12.399
39	V	12.456
40	H	12.476


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Thor 3's EIRP


 Program: Thuraya

Thuraya means "Chandelier", a space constellation

Project of Etisalat, the United Arab Emirates (UAE) telecommunications firm (60% government-owned) to launch a one billion dollar satellite system to boost its mobile telephones network. The operator will be Thuraya Satellite Telecommunications Co. Other share holders include Arabsat, Hughes, and the Abu Dhabi Investment Co.  Lybia's General Post and Telecommunication has a 5% stake in the project ($25 million)

The satellite system, named Thuraya, will provide services to UAE users of Two-way mobile telephones compatible with the Global System for Mobile communications (GSM). The system will make services available to remote sea and rural areas and will cover most Arab states, parts of the Indian subcontinent and Europe. Two satellites are planned, the first one expected in orbit in mid-2000. Launches via Sea Launch or Ariane or Proton

The satellite is expected to handle between 1.75 million and 2.4 million subscribers by 2005. A second satellite would add another 40 percent capacity if demand required it (ground spare). To be located at 44°E

SED Systems Inc (Canada) will provide an in-orbit test system based in Sharjah, UAE.

Total cost for the project as planned: $1 billion A consortium of local and international banks has arranged a US$600 million loan to finance the project.

External resources

http://www.thuraya.com/

http://www.etisalat.co.ae/

Technical data

Specifications

Prime contractor	Hughes
Platform	HS-GEM (derived from the HS-702)
Mass at launch	5250 kg
Mass in orbit	3200 kg
Dimension	stowed: 7.6 m x 3.75 m x 3.75 m
Solar array	34.5 m
Stabilization
DC power	BOL: 13000 W EOL: 11000 W
Design lifetime	12 years

single 12.25 m diameter antenna on board to be built by Astro Aerospace (Canada)

C-band

Main transponders	2
Backup transponders	2
Power	125 W (TWTA)
Bandwidth
Coverage
EIRP max
G/T max
Polarization
L-band

Main transponders	128 active elements
Backup transponders
Power	17 W
Bandwidth
Coverage
EIRP max
G/T max
Polarization


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 Timed

Thermosphere, Ionosphere, Mesosphere Energy and Dynamics

General

Designation
Launch date	initially Planned in May 2000
Country of origin	United States
Operator	NASA
Mission	Scientific:
Perigee/Apogee	600 km
Inclination	74.4°
Period
Launch vehicle	Delta 2
Launch site

It will obtain global measurements of geophysical parameters of the lower thermosphere, ionosphere, and mesosphere and will be used to determine the seasonal and annual variations of these regions.

Design and development: Johns Hopkins University Applied Physics Laboratory

External resources

http://sd-www.jhuapl.edu/TIMED/


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 Program: Tiros

Television and Infra Red Observation Satellite

American meteorological program

In 1960, Tiros 1, the first true weather satellite, was launched. With each succeeding generation of satellites, remote sensing instruments became increasingly sophisticated and today's high quality pictures are a far cry from the first tentative trials.

TIROS was a simple hatbox-shaped craft carrying special television cameras that viewed Earth's cloud cover from a 450 mile orbit. The pictures radioed back to Earth provided meteorologists with a new tool - a nephanalysis, or cloud chart.

By 1965, nine more TIROS satellites were launched. They had progressively longer operational times, carried infrared radiometers to study Earth's heat distribution, and several were placed in polar orbits to increase picture coverage over the first TIROS in its near-equatorial orbit.

TIROS 8 had the first Automatic Picture Transmission (APT) equipment that allowed pictures to be sent back right after they were taken instead of having to be stored for later transmission. Eventually, APT pictures could be received on fairly simple ground stations anywhere in the world, even in high school classrooms.

TIROS 9 and 10 were test satellites of improved configurations for the Tiros Operational Satellite (TOS) system. Operational use started in 1966. In orbit, the TOS satellites were called ESSA. TOS satellites were placed in Sun-synchronous orbits, so they passed over the same position on Earth's surface at exactly the same time each day; this allowed meteorologists to view local cloud changes on a 24-hour basis.

Several ITOS (for Improved TOS satellites) have been launched since 1970 and are the workhorses of the meteorologists. In orbit they are called NOAA for the National Oceanographic and Atmospheric Administration which is responsible for their operation.

External resources

http://www.met.fsu.edu/explores/Guide/tirosindex.html


Program: Tiros

Tiros 01

Tiros 02

Tiros 03

Tiros 04

Tiros 05

Tiros 06

Tiros 07

Tiros 08

Tiros 09

Tiros 10

Tiros N


 Tiros 01

General

Designation	00029 / 60002B
Launch date	1 Apr 1960
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	656/696 km
Inclination	48.4°
Period	98.3 min
Launch vehicle	Thor Able
Launch site	Cape Canaveral
Mass at launch	119.5 kg

Transmits the first pictures of the cloud cover


 Tiros 02

General

Designation	00063 / 60016A
Launch date	23 Nov 1960
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	546/610 km
Inclination	48.5°
Period	96.2 min
Launch vehicle	Thor Delta #3
Launch site	Cape Canaveral


 Tiros 03

General

Designation	00162 / 61017A
Launch date	12 Jul 1961
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	723/790 km
Inclination	47.9°
Period	100 min
Launch vehicle	Thor Delta #5
Launch site	Cape Canaveral


 Tiros 04

General

Designation	00226 / 62002A
Launch date	8 Feb 1962
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	693/811 km
Inclination	48.3°
Period	99.9 min
Launch vehicle	Thor Delta #7
Launch site	Cape Canaveral


 Tiros 05

General

Designation	00309 / 62025A
Launch date	19 Jun 1962
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	571/889 km
Inclination	58.1°
Period	99.4 min
Launch vehicle	Thor Delta #10
Launch site	Cape Canaveral


 Tiros 06

General

Designation	00397 / 62047A
Launch date	18 Sep 1962
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	639/645 km
Inclination	58.3°
Period	97.6 min
Launch vehicle	Thor Delta #12
Launch site	Cape Canaveral


 Tiros 07

General

Designation	00604 / 63024A
Launch date	19 Jun 1963
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	275/281 km
Inclination	58.2°
Period	90.1 min
Launch vehicle	Thor Delta #19
Launch site	Cape Canaveral
End of life

Decay	3 Jun 1994


 Tiros 08

General

Designation	00716 / 63054A
Launch date	21 Dec 1963
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	669/703 km
Inclination	58.5°
Period	98.5 min
Launch vehicle	Thor Delta #22
Launch site	Cape Canaveral
Mass at launch	102.4 kg

The APT (Automatic Puncture Transmission) camera enabled, for the first time, small antennas to receive pictures.


 Tiros 09

General

Designation	00978 / 65004A
Launch date	22 Jan 1965
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	702/2563 km
Inclination	96.4°
Period	118.9 min
Launch vehicle	Thor Delta #28
Launch site	Cape Canaveral

Test satellite for the Tiros Operational Satellite (TOS)


 Tiros 10

General

Designation	01430 / 65051A
Launch date	2 Jul 1965
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	721/807 km
Inclination	98.8°
Period	100.1 min
Launch vehicle	Thor Delta #32
Launch site	Cape Canaveral

Test satellite for the Tiros Operational Satellite (TOS)

End of life

Out of service	31 Jul 1966
Cause	desactivated
Technical data

Specifications

Prime contractor
Platform
Mass at launch
Dry mass	127 kg
Dimension	was in the form of an 18-sided right prism, 107 cm across opposite corners and 56 cm high
Solar array
Stabilization	spin-stabilized (between 8 and 12 rpm)
DC power
Design lifetime

Can be heard at 136.235 MHz

The satellite was equipped with two identical wide-angle TV cameras with 1.27 cm vidicon for taking earth cloudcover pictures. The pictures could be transmitted directly to either of two ground receiving stations or stored in a tape recorder on board for subsequent playback if the spacecraft was beyond the communication range of the station.


 Tiros N

General

Designation	11060 / 78096A
Launch date	13 Oct 1978
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	829/845 km
Inclination	98.7°
Period	101.7 min
Launch vehicle	Atlas F
Launch site	Vandenberg

Was a research and development spacecraft serving as a protoflight for the operational follow-on series

Technical data

Specifications

Prime contractor	GE Astro Space
Platform	Tiros N
Mass at launch	~720 kg
Mass in orbit
Diameter	1.88 m
Heigth	3.71 m
Solar array	1 single panel
Stabilization
DC power
Design lifetime


 Tmsat

Thai micro satellite, also called TO-31

General

Designation	25396 / 98043C
Launch date	10 Jul 1998
Country of origin	Thailand
Mission	Remote sensing
Perigee/Apogee	821 km sun-synchronous orbit
Inclination	110°
Period	90 minutes
Launch vehicle	Zenit

Was built by Thai engineers at the University of Surrey in Britain and it will operate in a low-earth orbit to monitor forest fires and water pollution and forecast weather.

TMSAT is under funding by The Thai Micro Satellite Company Co.,Ltd.(TMSC), that is a new joint venture between Mahanakorn University of Technology (MUT) and Thai Satellite Telecommunication (TSC) of Bangkok, Thailand.

Cost: $9.8 million

External resources

http://www.ee.surrey.ac.uk/EE/CSER/UOSAT/missions/tmsat/

Technical data

Specifications

Prime contractor	SSTL
Platform
Mass at launch	150 kg
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime

TMSAT has a downlink on 436.925 MHz, uplink on 145.925 MHz, both at 9600 bps FSK


 TOMS

Total Ozone Mapping Satellite

General

Designation	23940 / 96037A
Launch date	2 Jul 1996
Country of origin	United States
Mission	Remote sensing
Perigee/Apogee	500 km (sunsynchronous)
Inclination	97.4°
Period	96.7 min
Launch vehicle	Pegasus XL #12

TOMS will focus on tropospheric ozone, to monitor its depletion. It measures total ozone by observing both incoming solar energy and backscattered ultraviolet radiation at six wavelengths. Backscattered radiation is solar radiation that has penetrated the Earth's lower atmosphere and been reflected by air molecules and clouds back through the stratosphere to the satellite sensors.

In Dec 1998 the satellite was hit by a high-energy particle which disrupted the on-board computer and the satellite ended in safe mode. There was a problem with this mode and the stabilization processed exhumed the fuel. TRW came up with a solution to regain control over the satellite by using its magnetic torque. This was successful and the satellite uses this stabilization method since Jan 1999.

External resources

http://pao.gsfc.nasa.gov/gsfc/service/gallery/fact_sheets/earthsci/toms.htm

http://jwocky.gsfc.nasa.gov

Technical data

Specifications

Prime contractor	TRW
Platform	STEP/Eagle
Mass at launch	261 kg
Mass in orbit	215 kg
Dimension	2.4 x 3.9 m
Solar array
Stabilization	3 axis
DC power	128 W
Design lifetime	2 years

Single instrument: TOMS which already flew on Nimbus 7 (1978) and Meteor 3-05 (1991). It should also fly on Adeos 1

Telemetry: 2273.50 MHz (3 downlink rates: 1.1 kbps, 50 kbps, 200 kbps)

Command: 2093.51 MHz


 Topex Poseidon

ocean TOPography EXperiment

General

Designation	22076 / 92052A
Launch date	10 Aug 1992
Country of origin	France and United States
Operator	NASA & CNES
Mission	Remote sensing
Perigee/Apogee	1330/1342 km
Inclination	66°
Period	112.4 min
Orbital cycle	10 days
Launch vehicle	Ariane V52

Mission: global ocean circulation, ocean currents, tides and surface topography

Cost: $480 million

The inclined orbit samples from 66 North to 66 South latitude: it allows the satellite to observe 90% of the ice-free oceans and all major straits. The orbit is not sun-synchronous and is prograde. The repeat-cycle is about 10 days, ie the satellite passes vertically over the same location in a 1-kilometer bandwidth every 10 days. It has been chosen to optimize the study of the temporal large scale oceanic variability. The distance between successive tracks is on the order of 310 km at the Equator. The local time of successive passes shifts by nearly two hours.

In late 1998 the satellite was used to experiment an autonomous orbit control mode. A program was uploaded to enable the satellite to control its orbit on its own. The experiment was successful.

In Mar 1999 it is known that the satellite operated with the backup altimeter

Technical data

Specifications

Prime contractor	Jet Propulsion Laboratory (+ bus: Fairchild, Poseidon: Alcatel Espace)
Platform	MultiMission Spacecraft bus
Mass at launch	2100 kg
DC power	1500 W
Stabilization	3 axis
Design lifetime	4 years

Telemetry: 2287.5 MHz (realtime 1/16 kbps)

Command: 2106.5 MHz (realtime 1/0.125 kbps)

ALT (dual frequency radar altimeter) / NRA (NASA Radar Altimeter) (Topex)

Frequencies	5.3 GHz (C-band) 13.6 GHz (Ku-band)
Resolution	2-3 cm

NRA (206 Kg including redundance, 237 W) is the primary sensor for the TOPEX/POSEIDON mission. It has been provided by NASA. It is the fifth generation of altimeter (see Seasat and Geosat altimeters). The measurements made at the two frequencies are combined to obtain altimeter height of the satellite above the sea (altimeter range), the wind speed magnitude, the significant wave height and the ionospheric correction.

SSALT (Single-frequency Solid-state Radar Altimeter) (Poseidon)

Frequency	13.65 GHz (Ku-band)
Resolution	2-5 cm

SSALT (23 Kg without redundance, 49 W) validates the new technology of a low-power, light-weight altimeter for future Earth observing missions. It has been provided by the French Space Agency (CNES). It shares the same antenna as the NRA, thus only one altimeter operates at any given time. SSALT operates about 10% of the time that is one cycle in ten. The measurements give the same geophysical information as NRA's. However since this sensor uses a single frequency, an external correction for the ionosphere must be supplied (see the DORIS instrument).

TMR (Topex Microwave Radiometer)

Frequencies	18, 21 & 31 GHz

TMR (50 Kg including partial redundance, 25 W) measures the sea surface microwave brightness temperatures at three frequencies to provide the total vapor content in the troposphere along the altimeter beam. The 21 GHz channel is the primary channel for water vapor measurement. The 18 GHz channel is used to remove the effects of wind and the 37 GHz channel to remove cloud cover in the water vapor measurements. The measurements are combined to obtain the error in the satellite range measurements caused by pulse delay due to water vapor.

LRA (Laser Retroflector Array)

LRA (29 Kg) reflects laser signals from a network of 10 to 15 ground laser tracking stations to provide the baseline tracking data for precise orbit determination and to calibrate the altimeter bias.

DORIS (Doppler Orbitography and Radiopositioning Integrated by Satellite)

Frequencies	401.25 MHz 2036.25 MHz
Altitude accuracy	10 cm

DORIS (43 Kg including redundance, 21 W) is a French system that uses a two-channel receiver to observe the Doppler signals from a network of 40 to 50 ground transmitting beacons, spaced around the world. It provides all-weather global tracking of the satellite for precise orbit determination and an accurate correction for the influence of the ionosphere on both the Doppler signal and altimeter signals.

GPSDR (Global Positioning System Demonstration Receiver)

Frequencies	1227.6/1574.4 MHz

GPSDR (28 Kg without redundance, 29 W) uses a new GPS differential ranging technique for precise orbit determination. It receives signals from up to 6 GPS satellites. The GPS antenna is mounted on a long boom to reduce multipath effects which can severely corrupt the measurements. These data plus tracking of GPS from ground sites (3 minimum, 6 planned) allow nearly geometrical solutions.


 Tournesol

Also called D2A

General

Designation	05128 / 71030A
Launch date	15 Apr 1971
Country of origin	France
Mission	Scientific: Sun study and UV astronomy
Perigee/Apogee	457/696 km
Inclination	46.3°
Period	96.2 min
Launch vehicle	Diamant #7
Mass at launch	96 kg
End of life

Out of service	22 Jul 1973
Decay	28 Jan 1980


 Traac

General

Designation	00205 / 61031B
Launch date	15 Nov 1961
Country of origin	United States
Mission
Perigee/Apogee	955/1108 km
Inclination	32.4°
Period	105.8 min
Launch vehicle	Thor Ablestar
Launch site	Cape Canaveral
Mass at launch	90.4 kg

One of the 2 first satellites launched with the same vehicle (the other one is Transit 4B).


 Trace

Transitional Region and Coronal Explorer

General

Designation	25280 / 98020A
Launch date	2 Apr 1998
Country of origin	United States
Operator	NASA
Mission	Scientific: sun observation
Perigee/Apogee	602/652 km sun-synchronous
Inclination	97.8°
Period	97 min
Launch vehicle	Pegasus XL
Launch site	Vandenberg
Mass at launch	224 kg

Launch worth $12 million

The TRACE satellite, designed by an international team of 13 scientists from America, Britain, Sweden and the Netherlands, will explore the connections between fine-scale magnetic fields and the associated plasma structures of the Sun. Will be built at the Lockheed Palo Alto Research Laboratory.

External resources

http://sunland.gsfc.nasa.gov/smex/trace/

Technical data

Specifications

Prime contractor	LM
Platform
Mass at launch	213 kg
Mass in orbit
Dimension	0.86 m octogonal prism
Solar array	4 panels, total: 2 m²
Stabilization	3-axis
DC power	220 W
Design lifetime	1 year

Telemetry: 2215 MHz (realtime: 23.4375 kpbs, playback: 1.125 or 2.25 Mbps) (5 W transmitter)

Command: 2039.65 MHz (2 kbps)

Field of view: 8.5 x 8.5 arcminute

Telescope: 30 cm diameter x 160 cm length, 8.66 m focal length Cassegrain


 Program: Transit

American navigation program

First navigation program launched in 1959 and operational in 1964. These satellites were for the U.S. Navy and in particular, the Fleet Ballistic Missile Submarines, to accurately verify their location. This program was superseded by NOVA and finally by the Global Positioning Satellites. It was commercialized in 1967. First geodetic program to use the Doppler effect.

There were 7 pre-operational Transit-5xxx satellites: 3 Transit-5A launched by Scout, 3 Transit-5BN (nuclear powered) launched by Thor Able-Star, an 1 Transit-5C launched by Scout. The Transit-5C was mostly identical with the operational Transit-O series. The first 5 Transit-O's transfered to the Thor Ablestar launch vehicle, because the Scout lacked reliability at this time.

Since 1 Jan 1997 the satellite system is used for ionospheric studies (was retired from service for navigation at the end of 1996). It has been renamed NIMS (Navy Ionospheric Monitoring System).

Contact

Operator: Naval Space Command

External resources

http://www.fas.org/spp/military/program/nav/transit.htm

http://www.arlut.utexas.edu/~cir/transit.html

http://sd-www.jhuapl.edu/Transit/index.html

Technical data

Frequencies: uplink 149.982 / 149.988 (operational channel) MHz and downlink 399.9413 / 399.952 / 399.968 (operational channel) MHz


Program: Transit

Transit 2A

Transit 4A

Transit 4B

Transit 5BN1

Transit 5BN2


 Transit 2A

General

Designation	00045 / 60007A
Launch date	22 Jun 1960
Country of origin	United States
Mission	Navigation
Perigee/Apogee	604/988 km
Inclination	66.7°
Period	100.8 min
Launch vehicle	Thor Ablestar
Launch site	Cape Canaveral


 Transit 4A

General

Designation	00116 / 61015A
Launch date	29 Jun 1961
Country of origin	United States
Mission	Navigation
Perigee/Apogee	866/985 km
Inclination	66.8°
Period	103.5 min
Launch vehicle	Thor Ablestar
Launch site	Cape Canaveral
Mass at launch	79.1 kg

First satellite using a SNAP nuclear generator for power supply


 Transit 4B

General

Designation	00202 / 61031A
Launch date	15 Nov 1961
Country of origin	United States
Mission	Navigation
Perigee/Apogee	953/1104 km
Inclination	32.4°
Period	105.7 min
Launch vehicle	Thor Ablestar
Launch site	Cape Canaveral
Mass at launch	90.4 kg

Was launched with Traac: first time 2 satellites were launched with the same vehicle

Has a SNAP engine


 Transit 5BN1

General

Designation	00670 / 63038B
Launch date	28 Sep 1963
Country of origin	United States
Mission	Navigation
Perigee/Apogee	1062/1125 km
Inclination	90°
Period	107.1 min
Launch vehicle	Thor Ablestar
Launch site	Vandenberg


 Transit 5BN2

General

Designation	00704 / 63049B
Launch date	5 Dec 1963
Country of origin	United States
Mission	Navigation
Perigee/Apogee	1058/1109 km
Inclination	90.1°
Period	106.9 min
Launch vehicle	Thor Ablestar
Launch site	Vandenberg


 Triana

Named after Rodrigo de Triana, the lookout who first saw the New World from Columbus' ship

US satellite project. This spacecraft would be located at the L1 point to broadcast pictures of the Earth viewed from space. It would have science goals to especially regarding solar radiations.

This project is supported by Al Gore (US Vice president)

External resources

http://triana.gsfc.nasa.gov/home/


 TRMM

Tropical Rainfall Measuring Mission

General

Designation	25063 / 97074A
Launch date	27 Nov 1997
Country of origin	United States
Mission	Remote sensing
Perigee/Apogee	350 km
Inclination	35°
Period
Launch vehicle	H2 #5

The volume of rainfall in the tropics accounts for about two-thirds of total rainfall on the earth. Acting as the "engine" of the atmospheric cycle, this rainfall has a major influence on climate formation on a global scale. TRMM is a satellite that will measure the amount and distribution of rainfall in tropical and meta-tropical areas. Remote sensing of rainfall by the satellite will make a major contribution in predicting climatic changes on a global scale, providing long-range predictions on abnormal weather created by the E1 Nino phenomenon, and helping to prevent natural disasters.

TRMM is a joint project of Japan and the United States. It is worth $512 million

External resources

http://trmm.gsfc.nasa.gov/

Technical data

Specifications

Prime contractor	NASA GSFC
Platform
Mass at launch	3820 kg
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime	3 years

Acquisition via TDRS

Telemetry/Data: 2255.5 MHz (upto 2 Mbps)

Command: 2076.94 MHz (500 or 1024 bps)

Payload

PR: Precipitation Radar (Ku-band)

TMI: TRMM Microwave Imager

VIRS: Visible and Infrared Scanner

CERES: Clouds and the Earth's Radiant Energy System

LIS: Lightning Imaging Sensor

The CERES instrument (TRW-built) is the first of a series of 6 to fly. CERES is a scanning broadband radiometer that measures reflected sunlight and emitted thermal energy from the surface of the Earth and the atmosphere. The radiometer is made up of three sensors, each with its own telescope mounted on a gimballed platform that continuously scans across the Earth in a 6.6-second cycle.


 TRSSS

Thai Remote Sensing Small Satellite

General

Designation
Launch date	initially planned in 2000
Country of origin	Thailand
Mission	Remote sensing / Spy satellite
Perigee/Apogee	550 km
Inclination	polar
Period
Launch vehicle
Launch site

To weigh 300 to 400 kg, to be built by Spar Aerospace


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 TTS 1

Tethered Test Satellite, also called TSS (Tethered Satellite System)

General

Launch date	6 Aug 1992
Country of origin	Italy
Operator	CNR/PSN/NASA
Mission	Scientific
Launch vehicle	STS 46

To test power production (by induction). The satellite couldn't be deployed properly on STS 46 (only a few hundred meters).

Technical data

Specifications

Prime contractor	Aeritalia
Mass at launch	518 kg
Payload mass	66 kg
Diameter	1.6 m
Stabilization	Gravity gradient
DC power	180-200 W
Design lifetime	10 missions

Payload: instruments to measure electrodynamic properties of the ionosphere, magnetic fields and plasma

Tether (diameter: 2.54 mm) made from Kevlar sheated in Nomex with insulated copper-wire core


 TTS 2

Tethered Test Satellite, also called TSS 1R (Tethered Satellite System)

General

Designation	23805 / 96012B
Launch date	22 Feb 1996
Country of origin	Italy
Operator	CNR/PSN/NASA
Mission	Scientific
Launch vehicle	STS 75

The TSS project is a joint NASA/ASI (Italian Space Agency) effort. The 1.6 m diameter satellite is to be deployed on the end of a 20 kilometre long conductive tether to study the electrodynamic effects of moving such a tether through the Earth's magnetic field. The experiment will also test techniques for managing the tethered spacecraft at great distances. Second flight of the satellite which was worth about $200-400M (depending on whether or not you count the cost for the original satellite, modifications after the first flight, etc.)

The tether broke near full deployment (19 km) on 26 Feb at 01:30 UT. The initial orbit for the satellite was 316 x 413 km; meanwhile the shuttle was at 291 x 299 km. The break was due to an electrical shortcut inside the cable.

End of life

Decay	19 Mar 1996

Frequency downlink: 2260 MHz, uplink at 2081 MHz, 16 kbps data stream


 Program: Tubsat

Technische Universität Berlin SATellit

German small satellites program for data relay applications. 3-axis stabilized satellites

Transmissions are made on 143,075 MHz (mode: AFSK 1200 Baud, 1200/1800 Hz tones)

External resources

http://tubsat.fb12.tu-berlin.de/


Program: Tubsat

Tubsat A

Tubsat B

Tubsat C

Tubsat N

Tubsat N1


 Tubsat A

General

Designation	21577 / 91050D
Launch date	17 Jul 1991
Country of origin	Germany
Mission	Scientific: animal migration studies for Berlin's university
Perigee/Apogee	762/772 km
Inclination	98.4°
Period	100.2 min
Launch vehicle	Ariane V44
Mass at launch	38 kg
Technical data

Specifications

Prime contractor
Platform
Mass at launch
Mass in orbit
Dimension	length: 38 cm
Solar array
Stabilization
DC power
Design lifetime


 Tubsat B

General

Designation	22970 / 94003B
Launch date	25 Jan 1994
Country of origin	Germany
Mission	Technology
Perigee/Apogee	1183/1209 km
Inclination	82.55°
Period	109.35 min
Launch vehicle	Cyclone 3 #107


 Tubsat N

General

Designation	25389 / 98042A
Launch date	7 Jul 1998 at 3:15 UT
Country of origin	Germany
Mission	Telecommunications
Perigee/Apogee	400 / 776 km
Inclination	78.9°
Period
Launch vehicle	Shtil'-1

The Shtil'-1 launch vehicle is a converted R-29RM (RSM-54) 3-stage liquid propellant submarine-launched ballistic missile made by the Makeev design bureau.

It is the first launch from a submarine that took place from the Barents Sea off the coast of the Kol'skiy Peninsula, at approximately 35.3 deg E 69.3 deg N.

The launch plaform was the  K-407 `Novomoskovsk'

Technical data

Specifications

Prime contractor
Platform
Mass at launch	8 kg
Mass in orbit
Dimension	320 x 320 x 104 mm
Solar array
Stabilization
DC power
Design lifetime


 Tubsat N1

General

Designation	25390 / 98042B
Launch date	7 Jul 1998 at 3:15 UT
Country of origin	Germany
Mission	Telecommunications
Perigee/Apogee	400 / 776km
Inclination	79°
Period
Launch vehicle	Shtil'-1

This satellite weighs 3 kg


 Tubsat C

Also called DLR-TUBSAT

General

Designation	25757 / 99029B
Launch date	26 May 1999
Country of origin	Germany
Mission	Scientific
Perigee/Apogee	720 km
Inclination	98.4°
Period	99.4 min
Launch vehicle	PSLV #5

High resolution earth observation tasks. This is done in a live TV mode with a 3-head camera system with different focal lengths(16, 50 & 1000 mm), resulting in a resolution of 370 meter down to six meter per pixel.

Technical data

Specifications

Prime contractor	Technical University of Berlin
Platform
Mass at launch	45 kg
Mass in orbit
Dimension	32 cm cube
Solar array
Stabilization
DC power
Design lifetime

S-band downlink


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 Program: Turksat

Telecommunication program operated by Turk Telekom


Program: Turksat

Turksat 1A

Turksat 1B

Turksat 1C

Turksat 2A


Turksat's specifications

Prime contractor	Aerospatiale
Platform	Spacebus-100B
Mass at launch	1775 kg
Mass in orbit	1078 kg
Dimension	2.8 x 2.2 x 2.5 m
Solar array	22.4 m span
Stabilization	3 axis
DC power	EOL equinox: 2900 W
Design lifetime	12 years
Apogee motor	MBB S400 (liquid fuel)


Turksat's Ku-band

Main transponders	16
Backup transponders	8
Power	55 W (TWTA)
Bandwidth	10 transponders of 36 MHz 6 transponders of 72 MHz
Coverage and EIRP max	Turkey: 55 dBW Central Europe: 58 dBW Central Asia: 50 dBW (centered on Afghanistan)
G/T max	Turkey: 12 dB/K Central Europe: 13 dB/K Central Asia: 12 dB/K
Polarization	linear H/V
Frequencies:	uplink: 14-14.5 GHz Downlink: 10.95-11.2 GHz and 11.45-11.7 GHz


Turksat 1B's EIRP (European & Turkish spots)


 Turksat 1A

End of life

Out of service	24 Jan 1994
Cause	Failure of Ariane V63
Technical data

Specifications

Ku-band


 Turksat 1B

General

Designation	23200 / 94049B
Launch date	10 Aug 1994
Country of origin	Turkey
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V66

Cost: $300 million

Location

Begin	End	Position
L: 10 Aug 1994	Sep 1996	42°E
mid Oct 1996		31°E
Technical data

Specifications

Ku-band

EIRP maps (dBW)

Turkey

Central Europe

Transponder frequency chart (GHz)

Horizontal  Uplink	Horizontal  Downlink	Transponder	Vertical  Downlink	Vertical Uplink	Bandwidth (MHz)	Coverage (downlink)
14.270		4	10.970		36	Europe/Turkey
	10.980	12		14.280	36	Turkey
14.312		5	11.012		36	Europe/Turkey
	11.030	13		14.330	36	Turkey
14.354		6	11.054		36	Turkey
	11.080	14		14.380	36	Turkey
14.396		7	11.096		36	Turkey
	11.130	15		14.430	36	Turkey
14.462		8	11.162		72	Europe/Turkey
	11.180	16		14.480	36	Turkey
	11.486	9		14.036	72	Turkey
14.040		1	11.490		72	Europe
	11.574	10		14.124	72	Turkey
14.140		2	11.590		72	Turkey/Asia
	11.662	11		14.212	72	Turkey
14.228		3	11.678		36	Turkey/Asia

beacon: 11.105 GHz V


 Turksat 1C

General

Designation	23949 / 96040B
Launch date	9 Jul 1996
Country of origin	Turkey
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V89
Mass at launch	1743 kg

Is rumored to be quite unstable

Location

Begin	End	Position
L: 9 Jul 1996	tests	31.3°E
late Sep 1996		42°E
Technical data

Specifications

EIRP map (dBW)

Central Europe & Turkey

Central Asia & Turkey

Ku-band

Main transponders	16
Backup transponders	8
Power	55 W (TWTA)
Bandwidth	9 transponders of 36 MHz 2 transponders of 54 MHz 5 transponders of 72 MHz
Coverage and EIRP max	West: Central Europe & Turkey: 53 dBW East: Central Asia & Turkey: 53 dBW
G/T max	11 dB/K
Polarization	linear H/V

The satellite beams were modified to have wider coverage (but only 2 beams)

Transponder frequency chart (GHz)

Horizontal  Uplink	Horizontal  Downlink	Transponder	Vertical  Downlink	Vertical Uplink	Bandwidth (MHz)	Coverage (downlink)
	10.970	12 (but not 4)		14.270	36	East
14.270		4 (but not 12)	10.970		36	West
14.312		5	11.012		36	West
	11.030	13		14.330	36	East
14.354		6	11.054		36	West
	11.080	14		14.380	36	East
14.396		7	11.096		36	West
	11.130	15		14.430	36	East
14.462		8	11.162		72	West
	11.180	16		14.480	36	East
	11.486	9		14.036	72	East
14.040		1	11.490		72	West
	11.574	10		14.124	72	East
14.140		2	11.590		72	West
	11.669	11 (but not 3)		14.219	54	East
14.219		3 (but not 11)	11.669		54	West


Turksat 1C's Cental Europe + Turkey EIRP


Turksat 1C's Central Asia + Turkey EIRP


 Program: Tvsat

German direct TV program operated by the DBP (Deutsche BundesPost Telekom)


Program: Tvsat

Tvsat 1

Tvsat 2


Tvsat's specifications

Prime contractor	Eurosatellite and MBB
Platform	Spacebus-300
Mass at launch	2144 kg
Payload mass	195.9 kg: transponders: 97.6 kg, antennas: 98.3 kg
Dimension	2.4 x 1.64 x 6.4 m
Stabilization	3 axis
DC power	BOL: 4500 W EOL: equinox: 3312 W, solstice: 3060 W
Design lifetime	9 years


Tvsat's Ku-band

Main transponders	4
Backup transponders	2
Power	230 W (TWTA)
Bandwidth	27 MHz
Coverage	Europe
EIRP max	65 dBW
Polarization	circular L
Frequencies	Uplink: 17.7-18.1 GHz Downlink: 11.7-12.5 GHz


 Tvsat 1

General

Designation	18570 / 87095A
Launch date	21 Nov 1987
Country of origin	Germany
Mission	Direct TV
Geostationary orbit	was expected in slot 19.2°W
Launch vehicle	Ariane V20

Not functional because a solar pannel remains in front of the antennas. In fact 2 bolts had been forgotten that screw the antenna tight for transportation before launch!

End of life

Out of service	February 1988
Technical data

Specifications

Ku-band


 Tvsat 2

General

Designation	20168 / 89062A
Launch date	8 Aug 1989
Country of origin	Germany
Mission	Direct TV
Geostationary orbit	see below
Launch vehicle	Ariane V33

Was available on 25 Aug 1989 to broadcast the Berlin's TV show. Was leased to Tele TV AS and co-located with Intelsat 702 in 1995. Was leased to Eutelsat and moved to 12.5°W

Location

Begin	End	Position
L: 8 Aug 1989	Feb 1995	19.2°W
Mar 1995	Oct 1998	0.6°W
Nov 1998		12.5°W
Technical data

EIRP coverage (dBW)

Specifications

Ku-band

Video

Video excursion	13.5 MHz/v


Tvsat 2's EIRP map


 UARS

Upper Atmospheric Research Satellite

General

Designation	21701 / 91063B
Launch date	12 Sep 1991
Country of origin	United States
Mission	Scientific: high atmosphere study
Perigee/Apogee	555/586 km
Inclination	56.9°
Period	96 min
Launch vehicle	STS 48

Mission: systematic study of Earth's stratosphere, mesosphere and lower thermosphere with specialized payloads.

Cost: $630 million

External resources

http://uarsfot08.gsfc.nasa.gov/

Technical data

Specifications

Prime contractor	GE Astro
Platform	MultiMission Spacecraft bus
Mass at launch	6800 kg (2500 kg for the payload)
Diameter	5 m
Height	10 m
Solar array	1.5 x 3.3 m
Stabilization	3 axis
Design lifetime	3 years

Telemetry: 2287.5 MHz (realtime: 32/1 kbps, playback: 512 kbps)

Command: 2106.4 MHz (1/0.12 kbps)

CLAES (Cryogenic Limb Array Etalon Spectrometer)

Vertical profiles of minor species (between 10-60 km)

HALOE (Halogen Occultation Experiment)

Vertical distribution of minor species in stratosphere

ISAMS (Improved Stratospheric and Mesospheric Sounder)

Temperature and ozone concentrations in stratosphere and mesosphere

MLS (Microwave Limb Sounder)

ozone and other trace gases in stratosphere and mesosphere

HRDI (High Resolution Doppler Imager)

Horizontal windspeeds and temperature in upper troposhere and thermosphere

WINDII (Wind Imaging Interferometer)

Windspeed and temperature in mesosphere and lower thermosphere

PEM (Particule Environment Monitor)

Global input of charged particle energy

SOLSTICE (Solar Stellar Irradiance Comparison Experiment)

Full disk solar UV irradiance

SUSIM (Solar UV Spectral Irradiance Monitor)

solar irradiance, solar flux variability

ACRIM 2 (Active Cavity Radiometer Irradiance Monitor)

wide band total solar irradiance


Program: UHF
 Program: UHF Follow On

Also called for short UHF or UFO

Military telecommunication program composed of 10 satellites, advanced Fleetsatcom

Contact

Operator: Naval Space Command

Command & control: Air Force Space Command

A second generation of satellites is planned so as a 11th UHF satellite. This would cost nearly $2 billion. The new generation would be launched from 2007 on.

External resources

http://www.fas.org/spp/military/program/com/ufo.htm


Program: UHF

UHF 1

UHF 2

UHF 3

UHF 4

UHF 5

UHF 6

UHF 7

UHF 8

UHF 9

UHF 10


UHF's specifications

Prime contractor	Hughes
Platform	HS-601
Mass at launch	3000 kg (approx.)
Mass in orbit	1 to 3: 1120 kg 4 to 7: 1360 kg 8 to 10: 1600 kg
Length	3.2 m
Width	3.4 m
Height	3.4 m (7.0 m deployed)
Solar array	18.3 m span
Stabilization	3 axis
DC power	1 to 3: EOL: 2500 W 4 to 7: EOL: 2800 W 8 to 10: EOL: 3800 W
Design lifetime


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UHF-band

Channels	39
Amplifiers	11
Power
Bandwidth	21 x 5 KHz (narrow) 17 x 25 KHz (relay) 1 x 25 KHz (fleet) total: 555 KHz
Coverage
EIRP max
Polarization
Frequencies	240-270 MHz


EHF-band (44.5 GHz)

Channels	11
Power
Bandwidth	total: 2 GHz
Coverage & EIRP max	global beam steerable 5° spot beam
Polarization

Only on satellites 4 to 10. The EHF package provides enhanced anti-jam telemetry as well as command, broadcast andfleet interconnectivity communications. It was first tested on Fleetsatcom 7 & 8 and is also used on Milstar


GBS (30/20 GHz)

Main transponders	4
Backup transponders
Power	130 W
Bandwidth	24 MHz
Coverage
EIRP max
G/T max
Polarization

Has a fixed antenna, an omni antenna and a steerable receive antenna.


 UHF 1

General

Designation	22563 / 93015A
Launch date	25 Mar 1993
Country of origin	United States
Mission	Military: telecommunications
Geostationary orbit	n/a
Launch vehicle	Atlas Centaur #074
End of life

Cause	was delivered in a wrong orbit due to a partial launch failure
Technical data

Specifications

UHF

+ an SHF payload


 UHF 2

Also called USA 095

General

Designation	22787 / 93056A
Launch date	3 Sep 1993
Country of origin	United States
Mission	Military: telecommunications
Geostationary orbit	71.5°E, inclined (till Mar 1999 when the orbit was classified)
Launch vehicle	Atlas Centaur #79
Technical data

Specifications

UHF

+ an SHF payload


 UHF 3

Also called USA 104

General

Designation	23132 / 94035A
Launch date	24 Jun 1994
Country of origin	United States
Mission	Military: telecommunications
Geostationary orbit	15.5°W, inclined (till Mar 1999 when the orbit was classified)
Launch vehicle	Atlas Centaur #83
Technical data

Specifications

UHF

+ an SHF payload

Equipped with an ARC 490N (liquid fuel) apogee engine


 UHF 4

Also known as USA 108

General

Designation	23467 / 95003A
Launch date	29 Jan 1995
Country of origin	United States
Mission	Military: telecommunications
Geostationary orbit	178°W, inclined (till Mar 1999 when the orbit was classified)
Launch vehicle	Atlas Centaur #88

Tested in 170.5°W

Technical data

Specifications

UHF

EHF

+ an SHF payload


 UHF 5

Also called USA 111

General

Designation	23589 / 95027A
Launch date	31 May 1995
Country of origin	United States
Mission	Military: telecommunications
Geostationary orbit	70.5°E, inclined (till Mar 1999 when the orbit was classified)
Launch vehicle	Atlas Centaur #92
Technical data

Specifications

UHF

EHF

+ an SHF payload


 UHF 6

Also called USA 114

General

Designation	23696 / 95057A
Launch date	22 Oct 1995
Country of origin	United States
Mission	Military: telecommunications
Geostationary orbit	106°W (till Mar 1999 when the orbit was classified)
Launch vehicle	Atlas Centaur #95

Tested in 171.5°W and replaced Leasat 3

Technical data

Specifications

UHF

EHF

+ an SHF payload


 UHF 7

Also called USA 127

General

Designation	23967 / 96042A
Launch date	25 Jul 1996
Country of origin	United States
Mission	Military: telecommunications
Geostationary orbit	see below
Launch vehicle	Atlas Centaur #101

Tested in 171.5°W

Location

Begin	End	Position
L: 25 Jul 1996	Aug 1996	171.5°W
Oct 1996	Jan 1999	25°W
		orbit classified

It is the first of the series to have an enhanced EHF payload, adding nine more channels.  This was accomplished on a very short schedule with advanced, miniaturized digital technology so that no additional spacecraft resources were required.

Technical data

Specifications

UHF

EHF

+ an SHF payload


 UHF 8

Also called USA 138

General

Designation	25258 / 98016A
Launch date	16 Mar 1998
Country of origin	United States
Mission	Military: telecommunications
Geostationary orbit	169°E (till Mar 1999 when the orbit was classified)
Launch vehicle	Atlas Centaur #115

First UHF satellite with the GBS (Global Broadcast System) payload. It replaces the current SHF capability with four 130 W, 24 MHz military Ka band transponders, 3 steerable downlink spot beam antennas and one steerable uplink (+ 1 fixed) receive antenna per satellite. This will provide 96 Mbps throughput. The GBS payload is provided by Hughes Information Systems (HIS, Reston, Virginia)

Location

Begin	End	Position
L: 16 Mar 1998	Apr 1998	172°W
Jun 1998		169°E
Technical data

Specifications

UHF

EHF

GBS

S-band telemetry.


 UHF 9

Also called USA 140

General

Designation	25501 / 98058A
Launch date	20 Oct 1998
Country of origin	United States
Mission	Military: telecommunications
Geostationary orbit	see below
Launch vehicle	Atlas #118
Location

Begin	End	Position
L: 20 Oct 1998	Dec 1998	175°W
Jan 1999	Mar 1999	24°W
		orbit classified
Technical data

Specifications

Prime contractor	Hughes
Platform	HS-601
Mass at launch	3200 kg
Mass in orbit	1550 kg
Dry mass	~1250 kg
Dimension
Solar array
Stabilization
DC power
Design lifetime

UHF

EHF

GBS


 UHF 10

General

Designation
Launch date	1999
Country of origin	United States
Mission	Military: telecommunications
Geostationary orbit
Launch vehicle	Atlas 2
Technical data

Specifications

Prime contractor	Hughes
Platform	HS-601
Mass at launch	3200 kg
Mass in orbit	1550 kg
Dry mass	~1250 kg
Dimension
Solar array
Stabilization
DC power
Design lifetime

UHF

EHF

GBS


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 Ume 1

Means "apricot tree flower", also called ISS 1

General

Designation	08709 / 76019A
Launch date	29 Feb 1976
Country of origin	Japan
Mission	Scientific: ionosphere study
Perigee/Apogee	985/1006 km
Inclination	69.7°
Period	105 min
Launch vehicle	N1


 Ume 2

Also called ISS 2

General

Designation	10674 / 78018A
Launch date	16 Feb 1978
Country of origin	Japan
Mission	Scientifique
Perigee/Apogee	970/1219 km
Inclination	69.4°
Period	107.2 min
Launch vehicle	N1


 Unamsat 1

General

Launch date	28 mar 1995
Country of origin	Mexico
Mission	Telecommunications
Launch vehicle	Start #2
End of life

Cause	Launcher failure
Decay	28 Mar 1995

Built by UNAM, the Autonomous University of Mexico.

Technical data

Frequency chart (MHz)

Downlink freq.	Transponder/Beacon	Mode
437.135	TX1	default
437.179	TX2
Uplink freq.	Transponder/Beacon	Mode
145.922	Channel A
145.942	Channel B
145.962	Channel C
145.872	Channel E/F


 Unamsat 2

Autonomous University of Mexico Satellite, also called MO-30

General

Designation	24305 / 96052B
Launch date	5 Sep 1996
Country of origin	Mexico
Mission	Telecommunications
Perigee/Apogee	966/1010 km
Inclination	82.9°
Period	104.8 min
Launch vehicle	Cosmos 3M
Launch site	Plesetsk

On board a 40.997 MHz pulse transmitter and a wide band receiver centered on the same freq. will enable the search for echoes produced on the ionized trails of meteors as they enter the atmosphere.

The launch of the satellite costed $112,000

External resources

http://serpiente.dgsca.unam.mx/unamsat/unameng.htm

End of life

Out of service	6 Sep 1996
Cause	failed to operate, died after 1 day The uplink receiver did not survive the launch conditions
Technical data

Specifications

Prime contractor
Platform	Amsat Microbus
Mass at launch	10.7 kg
Mass in orbit
Dimension	25 x 25 x 25 cm
Solar array
Stabilization
DC power
Design lifetime
Frequency chart (MHz)

Downlink freq.	Transponder/Beacon	Mode
437.206	TX1	default
437.138	TX2
Uplink freq.	Transponder/Beacon	Mode
145.815	Channel A
145.835	Channel B
145.855	Channel C
145.875	Channel D


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 Program: Uosat

University Of Surrey sATellite

Satellites built by and operated by a unit of Surrey's university in the UK: SSTL


Program: Uosat

Uosat 1

Uosat 2

Uosat 3

Uosat 4

Uosat 5

Uosat 12


 Uosat 1

Also called UO-09 or Oscar 09

General

Designation	12888 / 81100B
Launch date	6 Oct 1981
Country of origin	United Kingdom
Mission	Telecommunications
Perigee/Apogee	372/374 km
Inclination	97.6°
Period	92 min
Launch vehicle	Thor Delta #157
Launch site	Vandenberg

Cost: $38000

First on-board computer (IHU - Integrated Housekeeping Unit) for battery and attitude management, remote control, and experiments.

End of life

Decay	13 Oct 1989
Technical data

Specifications

Prime contractor	University of Surrey (UK)
Platform	UoSAT
Mass at launch	52 kg
Dimension	0.74 x 0.42 x 0.42 m
Stabilization	3 axis (gravity gradient, magnetorquer)
DC power	BOL: 17 W EOL: 10 W
Design lifetime	3 years

Equipped with a vocal synthetisor and a TV camera.


 Uosat 2

Also called UO-11 or Oscar 11

General

Designation	14781 / 84021B
Launch date	1 Mar 1984
Country of origin	United Kingdom
Mission	Telecommunications
Perigee/Apogee	651/669 km
Inclination	97.8°
Period	98 min
Launch vehicle	Thor Delta #174
Launch site	Vandenberg

Function: Bulletin store and forward experiment, synthetic voice experiment, space dust and radiation experiments.

External resources

http://www.users.zetnet.co.uk/clivew/oscar11.htm

Technical data

Specifications

Prime contractor	University of Surrey (UK)
Platform	UoSAT
Mass at launch	60 kg
Dimension	0.58 x 0.36 x 0.36 m
Stabilization	3 axis (gravity gradient, magnetorquer)
DC power	BOL: 25 W (12 v, 6.4 Ah NiCd battery) EOL: 10 W
Design lifetime	3 years

Identical to Uosat 1

Frequency chart

Downlink	1200 bps AFSK/FM (1200 and 2400 Hz tones), synthetic voice and CW. 145.826 MHz, 435.025 MHz, 2401.500 MHz
Beacon	2401.500 MHz


 Uosat 3

Also called UO-14 or Oscar 14

General

Designation	20437 / 90005B
Launch date	22 Jan 1990
Country of origin	United Kingdom
Mission	Telecommunications
Perigee/Apogee	781/797 km
Inclination	98.6°
Period	100.7 min
Launch vehicle	Ariane V35

Function: Packet Radio Mailbox and Digipeater

Since 1992 it is used by VITA (see also Gemstar)

End of life

Out of service	late 1996
Cause	onboard computer failure
Decay
Technical data

Specifications

Prime contractor	University of Surrey (UK)
Platform	UoSAT (modular)
Mass at launch	46 kg
Dimension	0.6 x 0.34 x 0.34 m
Stabilization	3 axis
DC power	EOL: 10 W
Design lifetime	3 years
Frequency chart

Uplink	9600 bps K9NG/G3RUH modulated FSK (FM) AX.25 145.975 MHz
Downlink	9600 bps K9NG/G3RUH modulated FSK (FM) AX.25 435.070 MHz
Beacon	1200 bps AFSK NBFM 435.070 MHz


 Uosat 4

Also called UO-15 or Oscar 15

General

Designation	20438 / 90005C
Launch date	22 Jan 1990
Country of origin	United Kingdom
Mission	Telecommunications
Perigee/Apogee	784/799 km
Inclination	98.6°
Period	100.7 min
Launch vehicle	Ariane V35
End of life

Out of service	23 Jan 1990
Cause	Failed
Technical data

Specifications

Prime contractor	University of Surrey (UK)
Platform	UoSAT
Mass at launch	46 kg
Dimension	0.6 x 0.34 x 0.34 m
Stabilization	3 axis
DC power	EOL: 10 W
Design lifetime	3 years


 Uosat 5

Also called UO-22 or Oscar 22

General

Designation	21575 / 91050B
Launch date	17 Jul 1991
Country of origin	United Kingdom
Mission	Telecommunications and Remote sensing
Perigee/Apogee	759/772 km
Inclination	98.4°
Period	100.2 min
Launch vehicle	Ariane V44

Function: Packet Radio Mailbox, Digipeater and a CCD camera experiment (EIS).

Technical data

Specifications

Prime contractor	University of Surrey (UK)
Platform	UoSAT
Mass at launch	49 kg
Dimension	0.68 x 0.34 x 0.34 m
Stabilization	3 axis (gravity gradient)
DC power	EOL: 10 W
Design lifetime	3 years
Frequency chart

Uplink	9600 bps K9NG/G3RUH modulated FSK (FM) AX.25 145.900 145.975 MHz
Downlink	9600 bps K9NG/G3RUH modulated FSK (FM) AX.25 435.120 MHz


 Uosat 12

General

Designation	25693 / 99021A
Launch date	21 Apr 1999 at 05:00 UT
Country of origin	United Kingdom
Mission	Telecommunications and Remote sensing
Perigee/Apogee	650 km
Inclination	65°
Period	97.8 min
Launch vehicle	Dnepr #1
Launch site	Tyuratam

Note: there is a confusion about the object number. At launch 25694 reflected the actual satellite.

Estimate cost: $9 million ?

The launch was provided by Kosmotras, a joint stock company consisting of Russian and Ukrainian companies and government agencies registered in Russia. Kosmotras was given the rights by the Russian Government to convert and launch over 150 SS-18 missiles as Dnepr launch vehicles in compliance with the provisions of the START II treaty. This first launch was made with no additional third stage.

External resources

http://www.ee.surrey.ac.uk/EE/CSER/UOSAT/missions/uo12/

Technical data

Specifications

Prime contractor	SSTL
Platform	new SSTL platform
Mass at launch	300 kg
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime

UoSAT-12 carries a number of imaging payloads (Earth Imaging System;up to 10 meter resolution). It carries a propulsion system for orbital housekeeping experiments. The S -and downlink can run at speeds up to 1Mb/s for downloading imaging data.

Equipped with 2 cameras (10 m resolution panchromatic, 40 m multispectral). CCDs are from Eastman Kodak. Also has a colour wide angle camera.

Merlion payload: for use of the Nanyang Technological University, Singapore. Aim is to help develop a future LEO equatorial amateur radio system. The payload consist of an L-band receive and S-band transmit transponder. Uplink: 1265 MHz, Downlink: 2420 MHz Output power: 7 W

telemetry: 437.4 MHz

UoSAT-12 carries a newly developed Space GPS receiver, the SGR, that is designed to provide an experimental testbed for orbit and attitude determination. It has 5 antennas to accurately calculate the spacecraft attitude through applying interferometry techniques to the phase difference measurements.


 UPMsat 1

Politechnical University of Madrid (UPM in spanish) Satellite

General

Designation	23607 / 95033C
Launch date	7 Jul 1995
Country of origin	Spain
Mission	Technology (microgravity and telecommunications)
Perigee/Apogee	665/675 km
Inclination	98.1°
Period	98.2 min
Launch vehicle	Ariane V75
Mass at launch	47 kg


 Program: USA

Designation used by the United States since mid-1984 to name military spacecrafts.

USA 001	USA 002 = KH 9-19	USA 003 = subsat
USA 004 = SDS 5	USA 005	USA 006
USA 007	USA 008	USA 009 = SDS 6
USA 010	USA 011	USA 012
USA 013 = ITV 1	USA 014 = ITV 2	USA 015
USA 016	USA 017	USA 018
USA 019	USA 020	USA 021 = SDS 7
USA 022	USA 023	USA 024
USA 025	USA 026	USA 027
USA 028	USA 029 = DMSP B5D2-4	USA 030
USA 031	USA 032	USA 033
USA 034	USA 035	USA 036
USA 037	USA 038	USA 039
USA 040	USA 041	USA 042
USA 043	USA 044	USA 045
USA 046	USA 047	USA 048 = Magnum 2 = Mentor
USA 049	USA 050	USA 051 = LACE
USA 052 = RME	USA 053	USA 054
USA 055 = GLOMR 2	USA 056	USA 057
USA 058	USA 059	USA 060
USA 061	USA 062	USA 063
USA 064	USA 065	USA 066
USA 067	USA 068 = DMSP B5D2-5	USA 069
USA 070	USA 071	USA 072
USA 073 = DMSP B5D2-6	USA 074	USA 075
USA 076	USA 077	USA 078
USA 079	USA 080	USA 081
USA 082	USA 083	USA 084
USA 085	USA 086	USA 087
USA 088	USA 089	USA 090
USA 091	USA 092	USA 093
USA 094	USA 095	USA 096
USA 097	USA 098	USA 099
USA 100	USA 101	USA 102
USA 103	USA 104	USA 105
USA 106	USA 107	USA 108
USA 109	USA 110	USA 111
USA 112	USA 113	USA 114
USA 115	USA 116	USA 117
USA 118	USA 119	USA 120
USA 121	USA 122	USA 123
USA 124	USA 125	USA 126
USA 127	USA 128	USA 129
USA 130	USA 131	USA 132
USA 133	USA 134
USA 136	USA 137	USA 138
USA 139	USA 140
USA 142	USA 143	USA 144


 USA 008

Also called Magnum 1

General

Designation	15543 / 85010B
Launch date	24 Jan 1985
Country of origin	United States
Mission	Military: SIGINT (Magnum)
Geostationary orbit	n/a
Launch vehicle	STS 20
Technical data

Magnum type satellite, built by TRW. Carried a 76 m diameter antenna.

This type of satellite (SIGINT) has seen its performance increase with the diameter of the receiving antenna. Thus the Canyon satellites (1968-72) had 10 m antennas, the Rhyolite / Aquacade (1973-78) and the Jumpseat (1973-78) 18 m, the Vortex / Chalet (1978-89) 38 m and the Magnum / Orion 76 m.

External resources

http://www.fas.org/spp/military/program/sigint/index.html


 USA 032

Also called Singleton 1

General

Designation	19460 / 88078A
Launch date	5 Sep 1988
Country of origin	United States
Mission	Military: SIGINT (Singleton)
Perigee/Apogee	900 km
Inclination	85°
Period
Launch vehicle	Titan 2 #13

Equipped with a 10 m diameter rotating radar, built by TRW, 1500 kg

part of the Wide Area Surveillance System (WASS) of the USAF and US Navy


 USA 040

Also called SDS 2-1

General

Designation	20167 / 89061B
Launch date	8 Aug 1989
Country of origin	United States
Mission	Military:
Perigee/Apogee	996/39358 km
Inclination	63.4°
Period	n/a
Launch vehicle	STS 28R
External resources

http://www.fas.org/spp/military/program/com/sds_2.htm


 USA 045

Also called Singleton 2

General

Designation	20220 / 89072A
Launch date	5 Sep 1989
Country of origin	United States
Mission	Military: SIGINT (Singleton)
Perigee/Apogee	900 km
Inclination	85°
Period
Launch vehicle	Titan 2 #14

Equipped with a 10 m diameter rotating radar, built by TRW, 1500 kg

part of the Wide Area Surveillance System (WASS) of the USAF and US Navy

End of life

Out of service	5 Sep 1989
Cause	?


 USA 048

Also called Mentor

General

Designation	20355 / 89090B
Launch date	23 Nov 1989
Country of origin	United States
Mission	Military: SIGINT (Magnum)
Geostationary orbit	n/a
Launch vehicle	STS 33R


 USA 067

Also called AFP 658 or Orion or Magnum 3

General

Designation	20963 / 90097B
Launch date	16 Nov 1990
Country of origin	United States
Mission	Military: SIGINT (Magnum)
Geostationary orbit	n/a
Launch vehicle	STS 38
Mass at launch	2700 kg

Aimed to listen to the Persian Gulf


 USA 081

Also called Singleton 3

General

Designation	21949 / 92023A
Launch date	25 Apr 1992
Country of origin	United States
Mission	Military: SIGINT (Singleton)
Perigee/Apogee	900 km
Inclination	85°
Period
Launch vehicle	Titan 2 #15

Equipped with a 10 m diameter rotating radar, built by TRW, 1500 kg

part of the Wide Area Surveillance System (WASS) of the USAF and US Navy


 USA 089

Also called SDS 2-2

General

Designation	22518 / 92086B
Launch date	2 Dec 1992
Country of origin	United States
Mission	Military:
Perigee/Apogee	Molniya type 1000/39000 km
Inclination	63.4°
Period
Launch vehicle	STS 53
Technical data

Specifications

Prime contractor	Hughes
Platform	HS-376W
Mass at launch
Mass in orbit
Dimension	3.65 m height x 3.46 m diameter
Solar array
Stabilization
DC power
Design lifetime

bipropellant propulsion system

3 relay antennas


 USA 101

Also called P90-5 or TAOS (Technology for Autonomous Operations Survivability) or Step 0

General

Designation	23030 / 94017A
Launch date	13 Mar 1994
Country of origin	United States
Mission	Military: technology
Perigee/Apogee	556/568 km
Inclination	105°
Period	95.9 min
Launch vehicle	Taurus 01
Mass at launch	500 kg

Operated by USAF, built by TRW from an Eagle platform

It carries autonomous navigation systems and a GPS receiver, in an attempt to reduce the need for ground controllers.


 USA 102

Also called Darpasat

General

Designation	23031 / 94017B
Launch date	13 Mar 1994
Country of origin	United States
Mission	Military: technology
Perigee/Apogee	550/550 km ?
Inclination	105° ?
Period	95.9 min ?
Launch vehicle	Taurus 01
Mass at launch	240 kg

Operated by DARPA, built by Ball


 USA 103

Also called Trumpet 1

General

Designation	23097 / 94026A
Launch date	3 May 1994
Country of origin	United States
Mission	Military: SIGINT (Trumpet)
Perigee/Apogee	1323/39034 km
Inclination	64.4°
Period	717.9 min
Launch vehicle	Titan 4


 USA 105

Also called Jeroboam and Mercury 1

General

Designation	23223 / 94054A
Launch date	27 Aug 1994
Country of origin	United States
Mission	Military: SIGINT (Mercury = Advanced Vortex)
Geostationary	n/a
Launch vehicle	Titan 4

Would feature a 100 m diameter antenna, built by Boeing and 4500 kg


 USA 110

Also called Mentor 1

General

Designation	23567 / 95022A
Launch date	14 May 1995
Country of origin	United States
Mission	Military: SIGINT (Mentor = Advanced Magnum)
Geostationary orbit	n/a
Launch vehicle	Titan 4

Would feature a 100 m diameter antenna, built by Boeing and 4500 kg.

Mentor are operated by CIA


 USA 112

Also called Trumpet 2

General

Designation	23609 / 95034A
Launch date	10 Jul 1995
Country of origin	United States
Mission	Military: SIGINT (Trumpet)
Perigee/Apogee	Molniya-like
Inclination	n/a
Period	n/a
Launch vehicle	Titan 4


 USA 118

Also called Mercury 2

General

Designation	23855 / 96026A
Launch date	24 Apr 1996
Country of origin	United States
Mission	Military: SIGINT (Mercury)
Geostationary orbit	?
Launch vehicle	Titan 4 #16

The orbit and mission is only a supposition


 USA 125

Also called SDS 2-3

General

Designation	23945 / 96038A
Launch date	3 Jul 1996
Country of origin	United States
Mission	Military:
Perigee/Apogee	Molniya-like
Inclination	n/a
Period	n/a
Launch vehicle	Titan 4 #18
External resources

http://www.fas.org/spp/military/program/com/sds_2.htm


 USA 136

Also called Trumpet 3

General

Designation	25034 / 97068A
Launch date	8 Nov 1997
Country of origin	United States
Mission	Military: SIGINT (Trumpet)
Perigee/Apogee	1100/39059 km (Molniya-like)
Inclination	63.6°
Period
Launch vehicle	Titan 4 #23

Has a 150 m diameter antenna. Should weigh 5 to 6 tons


 USA 137

Also called Capricorn

General

Designation	25148 / 98005A
Launch date	29 Jan 1998
Country of origin	United States
Mission	Military: Communication (Capricorn / SDS 3)
Perigee/Apogee	40000 x 300 km
Inclination	63°
Period
Launch vehicle	Atlas 2A #113

It may be a follow-on to the SDS communications data relay satellites used to pass on spy satellite imaging data, and may also have either infrared missile warning or signals intelligence secondary payloads aboard. Another theory is that it may be the COBRA BRASS payload for infrared early warning satellite technology development, which was announced as due to fly this year.

It is believed that Capricorn's ground station is the Defense complexe known as Area 58 located 20 miles south of Washington D.C.

Cost: estimated at $250 million


 USA 139

Also called Mentor 2

General

Designation	25336 / 98029A
Launch date	9 May 1998
Country of origin	United States
Mission	Military: SIGINT (Mentor)
Geostationary orbit
Launch vehicle	Titan 4 #24


 USA 144

General

Designation	25744 / 99028A
Launch date	22 May 1999
Country of origin	United States
Mission	Military:
Perigee/Apogee	initial orbit: 200 x 293 km
Inclination	initial orbit: 63.4°
Period
Launch vehicle	Titan 4 #28

NRO satellite, could be a Lacrosse or a NOSS


V-Stream
 Program: V-stream

Telecommunication program planned by Panamsat. It would be made of 12 satellites operating in V-band (50/40 GHz). 3 GHz bandwidth per satellite. Planned in the 2000s

Each satellite would have high power spots, on-board processing and capable of inter-satellite links

PanAmSat has requested FCC authorization to operate the global V-band network in 11 orbital slots, ranging from 99°W for service over North America to 124.5°E for service over the Asia-Pacific.


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 Program: Vanguard

American experimental program. Eleven satellites where built but only 3 were successfully launched. See the Vanguard launch vehicle for details.


Program: Vanguard

Vanguard 1

Vanguard 2

Vanguard 3


 Vanguard 1

Also called grapefruit

General

Designation	00005 / 58002B
Launch date	17 Mar 1958
Country of origin	United States
Mission	Scientific: high atmosphere study
Perigee/Apogee	656/3866 km
Inclination	34.3°
Period	133.2 min
Launch vehicle	Vanguard #3
Launch site	Cape Canaveral
Mass at launch	1.47 kg

Sphere of 16 cm diameter. Carries a temperature sounder and a radio transmitter.


 Vanguard 2

General

Designation	00011 / 59001A
Launch date	17 Feb 1959
Country of origin	United States
Mission	Scientific: high atmosphere study
Perigee/Apogee	559/3047 km
Inclination	32.9°
Period	122.7 min
Launch vehicle	Vanguard #8
Launch site	Cape Canaveral


 Vanguard 3

General

Designation	00020 / 59007A
Launch date	18 Sep 1959
Country of origin	United States
Mission	Scientific: Sun study
Perigee/Apogee	512/3412 km
Inclination	33.3°
Period	126.3 min
Launch vehicle	Vanguard #11
Launch site	Cape Canaveral


 VCL

Vegetation Canopy Lidar

General

Designation
Launch date	initially planned in Feb 2000
Country of origin	United States
Mission	Scientific
Perigee/Apogee	400 km
Inclination	67°
Period
Launch vehicle	Athena 1
Launch site	Kodiak Island, Alaska

Part of NASA Earth System Science Pathfinder program. Will precisely measure the Earth's vegetation coverage, vegetation depth (or canopy) and topography by using short laser pulses from a LIDAR (Light Detection and Ranging) system.

External resources

http://essp.gsfc.nasa.gov/vcl/

http://www.inform.umd.edu/Geography/vcl/

Technical data

Specifications

Prime contractor	OSC
Platform
Mass at launch	430 kg
Mass in orbit
Dimension	2 x 1.15 m
Solar array
Stabilization
DC power
Design lifetime	2 years

A monthly orbit reboost is planned. For this, four 4.5 N thrusters with 45 kg hydrazine are onboard.

S-band telemetry and X-band for science downlink

32 Gbits of onboard memory (36 hours of data)

Multi-Beam Laser Altimeter (MBLA)

The instrument is made by NASA GSFC. It will have a 0.9 m telescope and will provide 25 m resolution data with 8 km swath width.


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Program: Vela
 Vela

American satellites to check the 1963 Moscow treaty: no atmospheric atomic explosions


 Viking

General

Designation	16614 / 86019B
Launch date	22 Feb 1986
Country of origin	Sweden
Operator	Swedish Space Corp.
Mission	Scientific: ionosphere and magnetosphere study
Perigee/Apogee	818/13521 km
Inclination	98.8°
Period	261.6 min
Launch vehicle	Ariane V16

Designed to measure space plasma phenomena in the Earth's magnetosphere and produce UV images of the auroral zone. By September 1986 it had taken 20,000 images of the complete aurora.

Cost: $18 million

External resources

http://nis-www.lanl.gov/~mgh/viking_desc.html

Technical data

Specifications

Prime contractor	Saab Space
Mass at launch	538 kg
Payload mass	60 kg
Diameter	1.9 m
Height	0.5 m
DC power	80 W
Stabilization	magneto-torquers (3 rpm)
Design lifetime	8 months
Payload

2 UV imagers & instruments to measure electric and magnetic fields, charged particles, and wave/particle interaction in the magnetosphere

Telemetry/data	S-band
Data rate	55 kbps
RF power	2.5 W


 Program: Virgo

Telecommunication program from Virtual Geosatellite LLC. The aim is to have 15 satellites in non-geostationary, sub-geosynchrounous inclined elliptical orbits. It should provide fixed satellite services to world's populated land passes in C- and Ku-band. The satellites should be interconnected via inter-satellite links in optical freq. range.

Virtual Geosatellite is partly owned by Ellipsat the cost of the project is estimated at $2.6 billion. It is expected to be operational 5 years after the FCC approval.

[quoted from the FCC filing, Jan 1999] Using a continent-following orbital configuration that is covered by issued and pending patents, the VIRGO constellation, though operating at non-geostationary altitudes, will appear virtually geostationary to users within the systems coverage area. VIRGO is comprised of three five-satellite sub-constellations  two for Northern Hemisphere operation (and identified herein as "Aurora I" and "Aurora II") and one for Southern Hemisphere operation (identified herein as "Australis"). The active arcs of the VIRGO satellites in each sub-constellation occur only when the satellites are at latitudes above 45 degrees, when they are at high elevations over much of their primary service areas in the Northern and Southern Hemispheres, respectively. VIRGO thus achieves an optimized combination of very high elevation angles, low signal propagation delays compared to geostationary satellites, and limited satellite handoffs. VIRGO provides non-uniform distribution of capacity to the Northern and Southern Hemispheres in proportion with demand.

Moreover, VIRGO operates in a manner that is effectively transparent to the geostationary fixed-satellite service ("FSS") and geostationary broadcasting satellite service ("BSS") networks, and to the fixed service systems, with which it will operate on a co-primary and fully compatible basis. VIRGO satellites are separated from the geostationary arc by at least 40 degrees at all times within the systems service areas. This key feature of the virtual geostationary concept means that VIRGO not only fully protects current geostationary FSS and BSS networks, it leaves them an effectively unfettered opportunity to evolve their technologies to meet future service requirements.

At a minimum, VIRGO will provide continuous coverage of all points on the globe between 85º north latitude and 55º south latitude. This includes all of the worlds populated land masses.

Contact

Virtual Geosatellite, LLC

1133 21st Street, N.W., 8th Floor

Washington, DC 20036

USA

Tel: +1-202-466-5599

Fax: +1-202-466-4493

External resources

http://www.virtualgeo.com/

Technical data

Frequencies:

users: uplink: 14.0-14.5 GHz

users: downlink: 11.2-12.7 GHz

gateways: uplink: 13.8-14.0 GHz, 17.3-17.8 GHz, and 5.925-6.725 GHz

gateways: downlink: 10.7-11.2 GHz and 3.7-4.2 GHz

Each VIRGO satellite provides "bent pipe" communications channels in these bands, and achieves a frequency reuse factor of up to fourteen times in some frequency bands through the use of dual orthogonal circular polarizations and spatial separation of the individual uplink and downlink actively-steered beams (four times per satellite on feeder links). VIRGO will also provide multi-beam coverage using its phased array antennas on the satellites  a capability that will allow each VIRGO satellite to reconfigure its coverage for the service area corresponding to each apogee, and for the particular traffic requirements the satellite encounters as it traverses the globe.


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 Program: Visionstar

To operate a Ka-band GEO system. Licence granted by the FCC in May 1997.

It should provide nationwide video programming in the US: over 100 national television channels plus regional and local programming. CelluarVision's Local Multipoint Distribution Service ("LMDS") system is to be used. It also proposes a broadband infrastructure offering distance learning, high-speed Internet services, interactive data and e-mail and video conferencing abilities.  VisionStar proposes to offer services on a non-common carrier basis.

The cost is expected to reach $207.5 million

Contact

Visionstar Inc

New York

General

Designation
Launch date	before May 2002
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	113°W
Launch vehicle
Launch site
Technical data

Specifications

Prime contractor
Platform
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime
Ka-band

Main transponders	48
Backup transponders
Power	60 or 90 W
Bandwidth	40 MHz
Coverage
EIRP
Polarization
Frequencies	Uplink: 28.35-28.6 and 29.25-30 GHz  Downlink: 19.7-20.2 GHz


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 Program: Vitasat

Volunteers in Technical Assistance

VITA is a non-profit private organization which uses LEO satellites for communications. In the past they have used Uosat 2, Uosat 3 and Posat. Now they use their own satellite payload: Vitasat 1R which replaces the Vitasat payload.

VITA holds an FCC licence for its communications.

VITA plans to setup a consortium with other LEO satellite operators. SatelLife (Healthsat) and Posat have agreed to join in. The consortium will operate a global email system dedicated to humanitarian and development purposes.

Contact

VITA

1600 Wilson Boulevard  (Suite 500), Arlington, VA 22209, USA

Tel: +1-703-276-1800

Fax: +1-703-243-1865

External resources

http://www.vita.org/


 Program: Vortex

Also called Chalet

Operated by the USAF. Chalet was the second generation of US GEO COMINT satellites (Canyon was the first series, with first launch in 1968, targetting Russia). Chalet was operated from Menwith Hill, UK. Under NSA project P-285, US companies were contracted to install and assist in operating the satellite control system and downlinks (RUNWAY) and ground processing system (SILKWORTH).

After the name of the first satellite appeared in the US press, the program was renamed Vortex. In 1982, NSA obtained approval for expanded "new mission requirements" and were given funds and facilities to operate four Vortex satellites simultaneously. A new 5000 m² operations center (STEEPLEBUSH) was constructed to house processing equipment.

The followup satellites after the Vortex are Mercury (in the 90ies). They are in the USA program.

Equipped with a 38 m antenna.

Vortex satellites and Magnum satellites (US GEO sigint satellites in general) might be operating from the following slots: 0°E, 44°E, 75°E, 82°E, 92°E, 110°E, 10°W, 13°W, 24°W, 30°W, 141°W and 144°W. The frequencies for uplink/downlink of collected signals would be in 17.8-21.2 GHz and 30-31 GHz. Non GEO SIGINT satellites such as the Jumpseat and Trumpet satellites (63-64° with highly elliptical orbits) might also used the same frequencies.

External resources

http://www.fas.org/spp/military/program/sigint/chalet.htm


Program: Vortex

Vortex 1

Vortex 2

Vortex 3

Vortex 4

Vortex 5

Vortex 6


 Vortex 1

General

Designation	10941 / 78058A
Launch date	10 Jun 1978
Country of origin	United States
Mission	Military: SIGINT
Geostationary orbit	n/a
Launch vehicle	Titan 3 #111


 Vortex 2

General

Designation	11558 / 79086A
Launch date	1 Oct 1979
Country of origin	United States
Mission	Military: SIGINT
Geostationary orbit	n/a
Launch vehicle	Titan 3 #118


 Vortex 3

General

Designation	12930 / 81107A
Launch date	31 Oct 1981
Country of origin	United States
Mission	Military: SIGINT
Geostationary orbit	n/a
Launch vehicle	Titan 3 #127


 Vortex 4

General

Designation	14675 / 84009A
Launch date	31 Jan 1984
Country of origin	United States
Mission	Military: SIGINT
Geostationary orbit	n/a
Launch vehicle	Titan 3 #136


 Vortex 5

Also called USA 031

General

Designation	19458 / 88077A
Launch date	2 Sep 1988
Country of origin	United States
Mission	Military: SIGINT
Geostationary orbit	n/a
Launch vehicle	Titan 3 #149

The second burn of the transtage failed


 Vortex 6

Also called USA 037

General

Designation	19976 / 89035A
Launch date	10 May 1989
Country of origin	United States
Mission	Military: SIGINT
Geostationary orbit	n/a
Launch vehicle	Titan 3 #151


 Voxsat

General

Designation
Launch date	1999
Country of origin	Argentina
Mission
Perigee/Apogee	1000 km
Inclination
Period
Launch vehicle	russian launcher
Launch site

Amateur radio satellite

External resources

http://members.xoom.com/Amsat_LU

Technical data

Specifications

Prime contractor
Platform
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime

Will feature:

1 Cross Band FM repeater, UHF up / VHF down

2 Parrot UHF up / VHF down

3 Broadcast Voice, FAX, SSTV

4 CW Telemetry modulate FM

The VHF output power for the downlink repeater TX is 2 watts, and 4 for the broadcast TX.


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 Webersat

Also called Microsat 3 or WO-18 or Oscar 18

General

Designation	20441 / 90005F
Launch date	22 Jan 1990
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780/797 km
Inclination	98.6°
Period	100.6 min
Launch vehicle	Ariane V35

Designed at Weber State College (Ogden, Utah, USA), based on an Amsat-NA Microsat bus

External resources

http://www.amsat.org/amsat/sats/nk6k/msatmain.html

Technical data

Uplink	1200 bps Manchester coded (Biphase-L) FSK (FM) AX.25 145.900 MHz
	NTSC modulated ATV (not in use?) 1265.000 MHz
Downlink	1200 bps BPSK (SSB) AX.25, either one of the two frequencies below: 437.075 MHz (LHCP in northern hemisphere), normal unfiltered PSK 437.102 MHz (RHCP in northern hemisphere), Raised Cosine modulation


 Program: West

Wideband European Satellite Telecommunications

Program for a global satellite infrastructure, made of one or several GEO satellites and 9 MEO satellites. It is proposed to use Ka-band. It complements the East project.

MMS which plans to be the prime contractor for the project is looking for investors to become the operator of the system.


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 Westpac

Also called WPLTN 1

General

Designation	25398/ 98043E
Launch date	10 Jul 1998 at 6:30 UT
Country of origin	Australia
Mission	Geodesy
Perigee/Apogee	817/819 km
Inclination	98.8°
Period	101.3 min
Launch vehicle	Zenit #29

Is a copy of GFZ 1 It is a target for the Western Pacific Laser Tracking Network (WPLTN) and is a joint project of Electro Optic Systems of Queanbeyan, New South Wales, Australia, and the Russian Space Agency.

Technical data

Specifications

Prime contractor
Platform
Mass at launch	24 kg
Mass in orbit
Dimension	diameter: 0.24 m
Solar array
Stabilization
DC power
Design lifetime


 Program: Westar

American telecommunication program operated by the Western Union Telegraph and since 1988 by Hughes.


Program: Westar

Westar 1

Westar 2

Westar 3

Westar 4

Westar 5

Westar 6


Westar 1, 2 & 3's specifications

Mass at launch	572 kg
Mass in orbit	208 kg
Diameter
Height
Stabilization	Spin stabilized
DC power
Design lifetime	7 years
Capacity	14400 phone circuits


Westar 1, 2 & 3's C-band

Main transponders	12
Backup transponders
Power
Bandwidth	36 MHz
Coverage
EIRP max	33 dBW
Polarization


Westar 4, 5 & 6's specifications

Prime contractor	Hughes
Platform	HS-376
Mass at launch	1100 kg
Mass in orbit	585 kg
Diameter	2.16 m
Height	6.6 m deployed
Stabilization	Spin stabilized
DC power	BOL: 820 W EOL: 700 W
Design lifetime	10 years


Westar 4, 5 & 6's C-band

Main transponders	24
Backup transponders
Power	7.5 W (TWTA)
Bandwidth	36 MHz
Coverage
EIRP max	34 dBW
Polarization


 Westar 1

General

Designation	07250 / 74022A
Launch date	13 Apr 1974
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	99°W
Launch vehicle	Thor Delta #101
Launch site	Cape Canaveral
End of life

Out of service	yes
Technical data

Specifications

C-band


 Westar 2

General

Designation	07466 / 74075A
Launch date	10 Oct 1974
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	125°W
Launch vehicle	Thor Delta #103
Launch site	Cape Canaveral
End of life

Out of service	yes
Technical data

Specifications

C-band


 Westar 3

General

Designation	11484 / 79072A
Launch date	10 Aug 1979
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	91°W
Launch vehicle	Thor Delta #149
Launch site	Cape Canaveral
End of life

Out of service	yes
Technical data

Specifications

C-band


 Westar 4

General

Designation	13069 / 82014A
Launch date	26 Feb 1982
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	99°W
Launch vehicle	Thor Delta #160
Launch site	Cape Canaveral
End of life

Out of service	Nov 1991
Technical data

Specifications

C-band


 Westar 5

General

Designation	13269 / 82058A
Launch date	9 Jun 1982
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	122.5°W
Launch vehicle	Thor Delta #162
Launch site	Cape Canaveral
End of life

Out of service	May 1992
Technical data

Specifications

C-band


 Westar 6

General

Designation	14688 / 84011B
Launch date	3 Feb 1984
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	n/a
Launch vehicle	STS 11

Placed on a bad orbit (because the perigee kick motor failed), it was retrieved on 16 Nov 1984 by STS 19. It then became Asiasat 1.

Technical data

Specifications

C-band


 Dial-Wika

Wissenschaftlich Kapsel

General

Designation	04344 / 70017A
Launch date	10 Mar 1970
Country of origin	Germany
Mission	Scientific: high atmosphere study
Perigee/Apogee	301/1631 km
Inclination	5.4°
Period	104.2 min
Launch vehicle	Diamant #5

First launch from Kourou

End of life

Decay	5 Oct 1978


 Wind 1

General

Designation	23333 / 94071A
Launch date	1 Nov 1994 at 09:31 UT
Country of origin	United States
Operator	NASA (part of the Global Geospace Science program)
Mission	Scientific: study of Sun
Perigee/Apogee	n/a
Inclination	n/a
Period	n/a
Launch vehicle	Delta 2 #227
Mass at launch	1200 kg

Cost: $173 million, Launched under the MELVS contract

Wind is a spacecraft in the International Solar-Terrestrial Program (ISTP). It carried instruments to measure the solar wind plasma and magnetic field, besides several instruments to measure very energetic particles and gamma rays. Operates together with Polar

After several orbits extending to close proximity of the Moon (at about 60 Earth-radii) and involving several thrust-firings during that phase, the spacecraft will eventually reach the first Lagrangian point (L-1) located at about 275 Earth-radii in the Sun-ward direction and orbit around that point. Orbital parameters are very variable even during the first two years.

Built by Martin Marietta Astra Space

External resources

http://ggsfot.gsfc.nasa.gov/words/wind.html

Technical data

Telemetry: 2275.5 MHz (realtime: 5.56 kbps, playback: 32 or 64 kbps)

Command: 2094.9 MHz (realtime: 250 kbps)


 WIRE

Also called Wide-Field Infrared Explorer

General

Designation	25646 / 99011A
Launch date	5 Mar 1999
Country of origin	United States
Mission	Scientific: IR astronomy
Perigee/Apogee	539/587 km
Inclination	97.5°
Period
Launch vehicle	Pegasus XL #26

The cover of Wire was ejected too early (3 days early?) and caused cryogen to leak out. This was caused by faulty electronics which caused the ejection of the cover. The satellite lost proper stabilization after launch. All the cryogen was lost, primary mission failed. The spacecraft is now to be used as an engineering testbed to evaluate advanced attitude control systems, communications, and data handling and operations.

WIRE would have used a single cryogenically cooled infrared telescope to survey selected target areas in two infrared bands.  WIRE was specifically designed to detect the maximum number of high-red shift starburst galaxies using the smallest, simplest instrument possible.  The WIRE survey would have been over 500 times fainter than the IRAS Faint Source Survey at 12 and 25 µm.

External resources

http://www.ipac.caltech.edu/wire/

http://sunland.gsfc.nasa.gov/smex/wire/

Technical data

Specifications

Prime contractor
Platform
Mass at launch	254 kg
Mass in orbit
Dimension
Solar array
Stabilization
DC power	160 W
Design lifetime	4 months

Telemetry: 2215 MHz (realtime: 23.4375 kbps, playback: 1.125 or 2.25 Mbps)

Command: 2039.65 MHz (2 kbps)

Telescope: 30 cm Cassegrain


Program: Wordstar
 Program: Worldstar

American program operated by Worldspace to reach the third World with digital radio sent by 3 satelllites. The satellites will be constructed by a consortium led by Alcatel Espace and launched from 1998 on. They will use L-band in DAB mode. The control center will be located in Toulouse, France.

The Digital Audio Broadcasting service will transmit to a new generation of receiver called Starman, which will have a satellite antenna the size of a business card. It's been developed by Motorola.

A fourth satellite was ordered in May 1998 from Alcatel for $57.3 million. Should be used as ground spare for the moment (will be delivered in early 2000).

The entire project including satellites, launches & insurance cost $700 million


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Program: Worldstar

Afristar

Asiastar

Caribstar


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Worldstar's specifications

Prime contractor	MMS
Platform	Eurostar 2000+
Mass at launch	2740 kg
Dry mass	1207 kg
Mass in orbit	1705 kg
Dimension	2.6 m x 1.8 m x 3 m
Solar array	28 m span
Stabilization	3-axis
DC power	EOL: 5500 W
Design lifetime	12 years


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Worldstar's L-band

Main transponders	12
Backup transponders	6
Power	150 W
Bandwidth	16 kbps per channel
Coverage	Uplink: global Downlink: 3 beams with 4 transponders each
EIRP max	33.5 dBW
G/T	-12.6 dB/K over the global beam
Frequencies	Upload: 7.025 - 7.075 GHz (SCPC) Downlink: 1.467 - 1.492 GHz

288 channels (24 channels per transponder), 16 kbps per channel

a mono voice-only service requires 1 channel

a mono music service requires 2 channels

a stereo service requires 4 channels


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 Wresat

General

Designation	03054 / 67118A
Launch date	29 Nov 1967
Country of origin	Australia
Mission	Scientific: high atmosphere and sun?
Perigee/Apogee	198/1252 km
Inclination	83.3°
Period	99.3 min
Launch vehicle	Redstone (US)
Launch site	Woomera
Mass at launch	50 kg


 WSF 2

Wake Shield Facility

General

Designation	23669 / 95048C
Launch date	11 Sep 1995 at 11:25 UT
Country of origin	United States
Mission	Scientific: Microgravity
Perigee/Apogee	370 km
Inclination	28.4°
Period	91.9 min
Launch vehicle	STS 69
Mass at launch	1979 kg

The WSF Free Flyer generates an ultra-hard vacuum in its wake for production of semiconductors and other experiments. WSF is built and operated by the Space Vacuum Epitaxy Center in Houston.

Was troubled by control problems and overheating.

End of life

Out of service	14 Sep 1995
Reentry	18 Sep 1995 with STS 69


 XMM

X-ray Multi-Mirror

General

Designation
Launch date	initially planned in Dec 1999
Country of origin	Europe
Mission	Scientific: astronomy
Perigee/Apogee	7000/114000 km
Inclination	60°
Period	2 days
Launch vehicle	Ariane 5
Launch site

ESA astronomy satellite worth DM 400 million

Will focus on black holes

External resources

http://astro.estec.esa.nl/XMM/xmm.html

Technical data

Specifications

Prime contractor	Dornier
Platform
Mass at launch	~ 4000 kg
Mass in orbit
Dimension	10 m long x 4 m diameter
Solar array
Stabilization
DC power
Design lifetime	10 years

Will carry 3 telescopes of 70 cm diameter (with 58 overlapping mirrors each)


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 XTE

X-ray Timing Explorer, Also called RXTE (Bruno B. Rossi X-ray Timing Explorer)

General

Designation	23757 / 95074A
Launch date	30 Dec 1995 13:48 UT
Country of origin	United States
Mission	Scientific: X-ray astronomy
Perigee/Apogee	565/583 km
Inclination	23°
Period	96.1 min
Launch vehicle	Delta 2 #230

Cost: $195 million, Launched under the MELVS contract

Delta's new avionics system will use an array of redundant laser gyros and accelerometers to sense the vehicle's velocity and attitude movement, which includes its angular position and direction. The avionics system feeds data to onboard computers which control Delta 2's engines and power, engine start, main engine cutoff, staging and payload separation. The avionics system now has two power sources and is completely redundant. If one data system is lost, the other will complete the mission.

External resources

http://heasarc.gsfc.nasa.gov/docs/xte/

Technical data

Specifications

Built under coordination of NASA-Goddard Space Flight Center. It includes two high gain antennae, allowing an almost continuous telemetry stream using TDRS's Multiple Access mode.

Proportional Counter Array (PCE)

Instrument with large collecting area but low spatial resolution, for accurate timing and spectral measurements of bright X-ray sources. Built by the LHEA at GSFC

The PCA is an array of five proportional counters with a total collecting area of 6500 square cm. The instrumental properties are:

Energy range	2 - 60 keV
Energy resolution	&< 18% at 6 keV
Time resolution	1 microsec
Spatial resolution	collimator with 1 degree FWHM
Detectors	5 proportional counters
Collecting area	6500 square cm
Layers	1 Propane veto; 3 Xenon, each split into two; 1 Xenon veto layer
Sensitivity	0.1 mCrab
Background	2 mCrab

Events detected by the PCA will be processed on board by the EDS before insertion into the telemetry stream.

High Energy X-ray Timing Experiment (HEXTE)

Intrument built by CASS at UCSD which will study X-rays. HEXTE consists of two clusters each containing four phoswich scintillation counters. The clusters can rock at right angles to each other, with amplitudes of 1.5 or 3 degrees, to provide accurate background measurements. The total collecting area is 1600 square cm. The instrumental properties are:

Energy range	20 - 250 keV
Energy resolution	&< 18% at 60 keV
Time resolution	10 microsec
Spatial resolution	collimator with 1 degree FWHM
Detectors	2 times 4 scintillation counters
Collecting area	1600 square cm
Phoswich	NaI / CsI
Sensitivity	10 mCrab
Background	100 mCrab

Events detected by HEXTE will be processed on board by its own data system before insertion into the telemetry stream. It will allow event mode, histogram binned mode, multiscalar mode, PHA/PSA spectral mode, and burst mode formats.

All-Sky Monitor (ASM)

ASM, built by the CSR at MIT, will spot X-ray flare stars and burst sources. It consists of three wide-angle shadow cameras equipped with proportional counters with a total collecting area of 90 square cm. The instrumental properties are:

Energy range	2 - 10 keV
Time resolution	80% of the sky every 90 minutes
Spatial resolution	3' x 15'
Number of shadow cameras	3, each with 6 x 90 degrees FOV
Collecting area	90 square cm
Detector	Xenon proportional counter, position-sensitive
Sensitivity	30 mCrab

Events detected by the ASM will be processed on board by the EDS before insertion into the telemetry stream.

Experiment Data System (EDS)

The EDS consists of eight Event Analyzers (EA), of which two are dedicated to the PCA and six to the ASM. Each EA contains an Intel 80286 processor and associated memory. The EAs can be programmed independently to process incoming events from the instruments in any of the following modes:

Transparent mode, using 1, 2, or 3 EAs

Event mode, using 1 or 2 EAs

Binned mode (time and/or energy)

Burst catcher mode

Fourier transform mode

Pulsar fold mode

Autocorrelation mode

Arrival time differences histogram mode

It is being built by the CSR at MIT.

Downlink frequency

Telemetry: 2287.5 MHz (realtime: 16/32 kbps, playback: upto 1024 kbps)

Command: 2106.4 MHz (1/0.125 kbps)


 Program: Yamal

Program of 2 Russian-built communication satellites operated by GasCom Corporation (Moscow). GasCom is a joint venture between RAO "Gazprom", the Russian natural gas monopoly, and RKK "Energia", the Russian aerospace company (design and operation of Mir).

The first generation of satellites, called Yamal 100, are to be launched in 1997 by Proton.  Slots reserved are: 19.5°W and 75°E

A new generation called Yamal 200 is in preparation for 1999. They will use 28 C- and 16 Ku-band transponders with 35-40 and 54 dBW max respectively

Yamal 100

Specifications

Prime contractor	Energia (payload: Space Systems/Loral)
Platform	Yamal 100
Mass at launch	1360 kg
Payload mass	315 kg
Dimension
Solar array
Stabilization
DC power	2200 W
Design lifetime	10 years
C-band

Main transponders	10
Backup transponders
Power
Bandwidth
Coverage	most of the CIS
EIRP max	40 dBW
Polarization
Yamal 200

Specifications

Prime contractor	Energia (payload: Space Systems/Loral)
Platform	Yamal 200
Mass at launch	2570 kg
Payload mass
Dimension
Solar array
Stabilization
DC power	3140 W
Design lifetime	12 years
C-band

Main transponders	28
Backup transponders
Power
Bandwidth
Coverage	most of the CIS + Asia
EIRP max	41 dBW
Polarization
Ku-band

Main transponders	16
Backup transponders
Power
Bandwidth
Coverage	most of CIS, Northeast Asia + steerable
EIRP max	49 dBW
G/T max
Polarization
Yamal 300

Specifications

Prime contractor	Energia (payload: Space Systems/Loral)
Platform	Yamal 200
Mass at launch	2870 kg
Payload mass
Dimension
Solar array
Stabilization
DC power	10000 W
Design lifetime	15 years
C-band

Main transponders	28
Backup transponders
Power
Bandwidth
Coverage	most of the CIS + Asia
EIRP max	41 dBW
Polarization
Ku-band

Main transponders	20
Backup transponders
Power
Bandwidth
Coverage	most of CIS, India + steerable
EIRP max	50 dBW
G/T max
Polarization


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 YES

Young Engineers' Satellite

General

Designation	25025 / 97066C
Launch date	30 Oct 1997
Country of origin	Europe
Mission	Technology
Perigee/Apogee	545/26626 km
Inclination	7.7°
Period	468 min
Launch vehicle	Ariane V101

Was released by Maqsat H.

Developed by Delta-Utec Space Research and Consultancy YES is a sub-satellite to study the dynamics of tethered satellites. It was designed, assembled and integrated in record time by young graduates and students at ESTEC. A GPS receiver is installed to evaluate the use of GPS for navigation, especially above the GPS satellite constellation. YES also contains technology validation experiments which will measure radiation, the solar angle and acceleration in autonomous mode, after separation from MAQSAT-H. It also carried a commercial technology PC and camera experiment.

Originally it should have been tether-attached (double strand tether, 35 km).

There is another 12 kg satellite, TORI (Tethered ORbit Insertable) that is attached to the other side of the tether and would also be released form MAQSAT-H, but due to the cancellation is still attached. TORI carries the first application of an 1.5 m absorptive tether in space as a passively extensible rod and for shock absorption. TORI carries some autonomous electronics that are part of the tether experiment.

External resources

http://www.estec.esa.nl/teamsat/


 Program: Yuri

Means "tiger lily", also called BS (Broadcast Satellite)

Japanese telecommunication program operated by Telecommunication Satellite Corporation of Japan (TSCJ)


Program: Yuri

Yuri 1

Yuri 2A

Yuri 2B

Yuri 2X

Yuri 3A

Yuri 3B

Yuri 3H

Yuri 3N


Yuri 2's specifications

Prime contractor	Toshiba with GE Astro Space
Platform	GE 3000
Mass at launch	1290 kg
Mass in orbit	760 kg
Dimension	1.2 x 1.32 x 2.89 m
Stabilization	3 axis
DC power	BOL: 1400 W
Design lifetime	5 years


Yuri 2's Ku-band

Main transponders	2
Backup transponders	1
Power	100 W (TWTA)
Bandwidth	27 MHz
Coverage
EIRP max	54 dBW
Polarization


Yuri 3's specifications

Prime contractor	NEC with GE Astro Space
Platform	GE 3000
Mass at launch	1115 kg
Mass in orbit	550 kg
Dimension	1.63 x 1.32 x 0.99 m
Solar array	14.3 m span
Stabilization	3 axis
DC power	BOL: 1443 W
Design lifetime	7 years


Yuri 3's Ku-band

Main transponders	3
Backup transponders	3
Power	120 W (TWTA)
Bandwidth	27 MHz
Coverage	Japan
EIRP max	54 dBW
Polarization	Circular
Frequencies	uplink: 14.0-14.3 GHz downlink: 11.7-12.0 GHz


 Yuri 1

Also called BS E

General

Designation	10792 / 78039A
Launch date	7 Apr 1978
Country of origin	Japan
Mission	Telecommunications
Geostationary orbit	110°E
Launch vehicle	Thor Delta #140
Launch site	Cape Canaveral

Bus: Toshiba/GE Satcom

Owner: NASDA

End of life

Out of service	January 1982


 Yuri 2A

Also called BS 2A

General

Designation	14659 / 84005A
Launch date	23 Jan 1984
Country of origin	Japan
Mission	Telecommunications
Geostationary orbit	110°E
Launch vehicle	N2

Suffered from in-orbit equipment failures

Owner: NASDA/TSCJ

End of life

Out of service	yes
Technical data

Specifications

Ku-band


 Yuri 2B

Also called BS 2B

General

Designation	16597 / 86016A
Launch date	12 Feb 1986
Country of origin	Japan
Mission	Telecommunications
Geostationary orbit	110°E
Launch vehicle	N2

Owner: NASDA/TSCJ

End of life

Out of service	yes
Technical data

Specifications

Ku-band

2 out of 3 transponders failed 3 months after launch


 Yuri 2X

Also called BS 2X

End of life

Out of service	23 Feb 1990
Cause	Explosed with Ariane V36

Owner: NHK

Technical data

Specifications

Ku-band


 Yuri 3A

Also called BS 3A

General

Designation	20771 / 90077A
Launch date	28 Aug 1990
Country of origin	Japan
Mission	Telecommunications
Geostationary orbit	110°E
Launch vehicle	H1

Started having stability problems in Sep 1995 with a peak in November. Traffic had to be taken over by Yuri 3N which is less powerful.

Owner: NASDA/TSCJ

End of life

Out of service	Apr 1998
Technical data

Specifications

Ku-band


 Yuri 3H

Also called BS 3H

General

Launch date	19 Apr 1991
Country of origin	Japan
Mission	Telecommunications
Geostationary orbit	n/a
Launch vehicle	Atlas Centaur #070

Owner: NHK

End of life

Out of service	19 Apr 1991
Cause	Launch failure

This satellite was a replacement for the Yuri 2X spacecraft which failed and was in turn a replacement for Yuri 2A spacecraft in orbit which had been suffering equipment failures.

Technical data

Specifications

Ku-band


 Yuri 3B

Also called BS 3B

General

Designation	21668 / 91060A
Launch date	25 Aug 1991
Country of origin	Japan
Mission	Telecommunications
Geostationary orbit	110°E
Launch vehicle	H1

Owner: NASDA/TSCJ

End of life

Out of service	Mar 1999
Cause	deorbited
Technical data

Specifications

Ku-band


 Yuri 3N

Also called BS 3N

General

Designation	23176 / 94040B
Launch date	8 Jul 1994
Country of origin	Japan
Mission	Telecommunications
Geostationary orbit	110°E
Launch vehicle	Ariane V65
Mass at launch	1210 kg

Owner: NHK/JSB

Technical data

Specifications

Ku-band

Equipped with a Star 30BP apogee motor


 Zeya

Also called Mozhaets and RS 16

General

Designation	24744 / 97010A
Launch date	4 Mar 1997
Country of origin	CIS
Mission	Scientific: Geodesy
Perigee/Apogee	467 / 480 km
Inclination	97.3°
Period	94 min
Launch vehicle	Start 1 #3
External resources

http://www.users.wineasy.se/svengrahn/zeya.htm

Technical data

Specifications

Prime contractor	NPO-PM
Platform	possibly based on Strela 1M
Mass at launch	87 kg
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime

The satellite was designed by the students of the Mozhaiskiy military space engineering academy, in Saint Petersburg

Carries 20 laser reflectors for geodesy and Glonass and GPS receivers.

Transponders (RS-16)

Beacons	29.408 MHz 29.451 MHz 435.504 MHz (1.6 W) 435.548 MHz
Uplink	145.915 - 145.948 MHz
Downlink	29.415 - 29.448 MHz (4 W)


 Program: Cosmos

Soviet denomination for satellites part of plenty of different programs. Some have a specific fact sheet in TSE:

Sub programs

Bion

Eorsat

Geizer

Geo-IK

Glonass

Gonets

Luch

Parus

Rorsat

Strela

Tsikada


 Cosmos 0001

Also called Sputnik 11

General

Designation	00266 / 62008A
Launch date	16 Mar 1962
Country of origin	CIS
Mission	Scientific: ionosphere study
Perigee/Apogee	207/649 km
Inclination	49°
Period	93.1 min
Launch vehicle	Cosmos B
Launch site	Kapustin Yar
End of life

Decay	25 May 1962


 Cosmos 0100

General

Designation	01843 / 65106A
Launch date	17 Dec 1965
Country of origin	CIS
Mission
Perigee/Apogee	485/547 km
Inclination	65°
Period	95 min
Launch vehicle	Semiorka A1


 Cosmos 0110

General

Designation	02070 / 66015A
Launch date	22 Feb 1966
Country of origin	CIS
Mission
Perigee/Apogee	181/887 km
Inclination	51.8°
Period	95.3 min
Launch vehicle	Soyuz
Launch site	Tyuratam

Study of animals and vegetals in space

End of life

Decay	16 Mar 1966


 Cosmos 0122

General

Designation	02254 / 66057A
Launch date	25 Jun 1966
Country of origin	CIS
Mission	Meteorology
Perigee/Apogee	371/388 km
Inclination	65°
Period	92.1 min
Launch vehicle	Semiorka A1

First soviet meteorology satellite

End of life

Decay	14 Nov 1989
Technical data

Specifications


 Cosmos 0144

General

Designation	02695 / 67018A
Launch date	28 Feb 1967
Country of origin	CIS
Mission	Meteorology
Perigee/Apogee	574/644 km
Inclination	81.3°
Period	96.9 min
Launch vehicle	Semiorka A1
End of life

Decay	14 Sep 1982
Technical data

Specifications


 Cosmos 0169

General

Designation	02878 / 67069A
Launch date	17 Jul 1967
Country of origin	CIS
Mission
Perigee/Apogee	135/200 km
Inclination	49.7°
Period	87.8 min
Launch vehicle
Launch site	Tyuratam
End of life

Decay	17 Jul 1967


 Cosmos 0186

General

Designation	03014 / 67105A
Launch date	27 Oct 1967
Country of origin	CIS
Mission
Perigee/Apogee	179/223 km
Inclination	51.6°
Period	88.6 min
Launch vehicle
Launch site	Tyuratam

Docked with Cosmos 0188

End of life

Decay	31 Oct 1967


 Cosmos 0188

General

Designation	03020 / 67107A
Launch date	30 Oct 1967
Country of origin	CIS
Mission
Perigee/Apogee	180/247 km
Inclination	51.7°
Period	88.7 min
Launch vehicle
Launch site	Tyuratam

Docked with Cosmos 0186

End of life

Decay	2 Nov 1967


 Cosmos 0368

General

Designation	04571 / 70080A
Launch date	8 Oct 1970
Country of origin	CIS
Mission
Perigee/Apogee	202/383 km
Inclination	65°
Period	90.4 min
Launch vehicle
Launch site	Tyuratam

Study of animals and vegetals in space

End of life

Decay	14 Oct 1970


 Cosmos 0444

General

Designation	05547 / 71086A
Launch date	13 Oct 1971
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1318/1507 km
Inclination	74°
Period	114.1 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 0445

General

Designation	05548 / 71086B
Launch date	13 Oct 1971
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1348/1509 km
Inclination	74°
Period	114.4 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 0446

General

Designation	05549 / 71086C
Launch date	13 Oct 1971
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1378/1509 km
Inclination	74°
Period	114.8 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 0447

General

Designation	05550 / 71086D
Launch date	13 Oct 1971
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1408/1512 km
Inclination	74°
Period	115.1 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 0448

General

Designation	05551 / 71086E
Launch date	13 Oct 1971
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1438/1514 km
Inclination	74°
Period	115.5 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 0449

General

Designation	05552 / 71086F
Launch date	13 Oct 1971
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1480/1540 km
Inclination	74°
Period	116.2 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 0450

General

Designation	05553 / 71086G
Launch date	13 Oct 1971
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1460/1527 km
Inclination	74°
Period	115.8 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 0451

General

Designation	05554 / 71086H
Launch date	13 Oct 1971
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1487/1571 km
Inclination	74°
Period	116.6 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 0500

General

Designation	06097 / 72053A
Launch date	10 Jul 1972
Country of origin	CIS
Mission	Military: SIGINT (Tselina)
Perigee/Apogee	505/548 km
Inclination	74°
Period	95.2 min
Launch vehicle	Cosmos C
Launch site	Plesetsk
End of life

Decay	29 Mar 1980


 Cosmos 0504

General

Designation	06117 / 72057A
Launch date	20 Jul 1972
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1319/1493 km
Inclination	74°
Period	113.9 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 0505

General

Designation	06118 / 72057B
Launch date	20 Jul 1972
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1349/1494 km
Inclination	74°
Period	114.3 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 0506

General

Designation	06119 / 72057C
Launch date	20 Jul 1972
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1380/1494 km
Inclination	74°
Period	114.6 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 0507

General

Designation	06120 / 72057D
Launch date	20 Jul 1972
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1409/1494 km
Inclination	74°
Period	114.9 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 0508

General

Designation	06121 / 72057E
Launch date	20 Jul 1972
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1441/1493 km
Inclination	74°
Period	115.3 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 0509

General

Designation	06122 / 72057F
Launch date	20 Jul 1972
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1471/1496 km
Inclination	74°
Period	115.6 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 0510

General

Designation	06123 / 57057G
Launch date	20 Jul 1972
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1493/1507 km
Inclination	74°
Period	116 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 0511

General

Designation	06124 / 72057H
Launch date	20 Jul 1972
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1493/1543 km
Inclination	74°
Period	116.4 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 0588

General

Designation	06845 / 73069A
Launch date	2 Oct 1973
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1446/1490 km
Inclination	74°
Period	155.3 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 0589

General

Designation	06846 / 73069B
Launch date	2 Oct 1973
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1412/1486 km
Inclination	74°
Period	114.9 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 0590

General

Designation	06847 / 73069C
Launch date	2 Oct 1973
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1431/1485 km
Inclination	74°
Period	115.1 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 0591

General

Designation	06848 / 73069D
Launch date	2 Oct 1973
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1344/1483 km
Inclination	74°
Period	114.4 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 0592

General

Designation	06849 / 73069E
Launch date	2 Oct 1973
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1328/1482 km
Inclination	74°
Period	133.9 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 0593

General

Designation	06850 / 73069F
Launch date	2 Oct 1973
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1361/1483 km
Inclination	74°
Period	114.3 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 0594

General

Designation	06851 / 73069G
Launch date	2 Oct 1973
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1378/1484 km
Inclination	74°
Period	114.5 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 0595

General

Designation	06852 / 73069H
Launch date	2 Oct 1973
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1396/1483 km
Inclination	74°
Period	114.7 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 0596

General

Designation	06856 / 73070A
Launch date	3 Oct 1973
Country of origin	CIS
Mission	spying?
Perigee/Apogee	206/287 km
Inclination	65.4°
Period	89.4 min
Launch vehicle
Launch site	Plesetsk
End of life

Decay	9 Oct 1973


 Cosmos 0597

General

Designation	06858 / 73071A
Launch date	6 Oct 1973
Country of origin	CIS
Mission	spying?
Perigee/Apogee	206/290 km
Inclination	65.4°
Period	89.5 min
Launch vehicle
Launch site	Plesetsk
End of life

Decay	12 Oct 1973


 Cosmos 0598

General

Designation	06862 / 73072A
Launch date	10 Oct 1973
Country of origin	CIS
Mission	spying?
Perigee/Apogee	208/334 km
Inclination	72.8°
Period	89.9 min
Launch vehicle
Launch site	Plesetsk
End of life

Decay	16 Oct 1973


 Cosmos 0599

General

Designation	06867 / 73073A
Launch date	15 Oct 1973
Country of origin	CIS
Mission	spying?
Perigee/Apogee	202/280 km
Inclination	64.9°
Period	89.3 min
Launch vehicle
Launch site	Plesetsk
End of life

Decay	28 Oct 1973


 Cosmos 0600

General

Designation	06873 / 73074A
Launch date	16 Oct 1973
Country of origin	CIS
Mission	spying?
Perigee/Apogee	205/340 km
Inclination	72.8°
Period	90 min
Launch vehicle
Launch site	Plesetsk
End of life

Decay	23 Oct 1973


 Cosmos 0605

Also called Bion 01

General

Designation	06913 / 73083A
Launch date	31 Oct 1973
Country of origin	CIS
Mission
Perigee/Apogee	213/403 km
Inclination	62.8°
Period	90.7 min
Launch vehicle	Soyuz
Launch site	Plesetsk

Study of animals and vegetals in space

End of life

Decay	22 Nov 1973


 Cosmos 0637

General

Designation	07229 / 74017A
Launch date	26 Mar 1974
Country of origin	CIS
Mission	Military: Telecommunications
Perigee/Apogee	35475/35819 km, 65°E
Inclination	13,7°
Period	1429 min
Launch vehicle	Proton #46

First Soviet geostationary satellite


 Cosmos 0641

General

Designation	07265 / 74024A
Launch date	23 Apr 1974
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1385/1479 km
Inclination	74°
Period	114.5 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 0642

General

Designation	07266 / 74024B
Launch date	23 Apr 1974
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1316/1478 km
Inclination	74°
Period	113.7 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 0643

General

Designation	07267 / 74024C
Launch date	23 Apr 1974
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1350/1479 km
Inclination	74°
Period	114.4 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 0644

General

Designation	07268 / 74024D
Launch date	23 Apr 1974
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1332/1479 km
Inclination	74°
Period	113.9 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 0645

General

Designation	07269 / 74024E
Launch date	23 Apr 1974
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1367/1479 km
Inclination	74°
Period	114.3 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 0646

General

Designation	07270 / 74024F
Launch date	23 Apr 1974
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1402/1482 km
Inclination	74°
Period	114.7 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 0647

General

Designation	07271 / 74024G
Launch date	23 Apr 1974
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1420/1481 km
Inclination	74°
Period	114.9 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 0648

General

Designation	07272 / 74024H
Launch date	23 Apr 1974
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1435/1487 km
Inclination	74°
Period	115.1 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 0677

General

Designation	07435 / 74072A
Launch date	19 Sep 1974
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1394/1464 km
Inclination	74°
Period	114.4 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 0678

General

Designation	07436 / 74072B
Launch date	19 Sep 1974
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1464/1530 km
Inclination	74°
Period	115.9 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 0679

General

Designation	07437 / 74072C
Launch date	19 Sep 1974
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1464/1508 km
Inclination	74°
Period	115.7 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 0680

General

Designation	07438 / 74072D
Launch date	19 Sep 1974
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1464/1489 km
Inclination	74°
Period	115.5 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 0681

General

Designation	07439 / 74072E
Launch date	19 Sep 1974
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1463/1470 km
Inclination	74°
Period	115.3 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 0682

General

Designation	07440 / 74072F
Launch date	19 Sep 1974
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1450/1464 km
Inclination	74°
Period	115 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 0683

General

Designation	07441 / 74072G
Launch date	19 Sep 1974
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1432/1464 km
Inclination	74°
Period	114.8 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 0684

General

Designation	07442 / 74072H
Launch date	19 Sep 1974
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1413/1464 km
Inclination	74°
Period	114.6 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 0711

General

Designation	07678 / 75016A
Launch date	28 Feb 1975
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1459/1490 km
Inclination	74°
Period	115.4 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 0712

General

Designation	07679 / 75016B
Launch date	28 Feb 1975
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1409/1488 km
Inclination	74°
Period	114.8 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 0713

General

Designation	07680 / 75016C
Launch date	28 Feb 1975
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1393/1485 km
Inclination	74°
Period	114.6 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 0714

General

Designation	07681 / 75016D
Launch date	28 Feb 1975
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1442/1489 km
Inclination	74°
Period	115.2 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 0715

General

Designation	07682 / 75016E
Launch date	28 Feb 1975
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1467/1502 km
Inclination	74°
Period	115.7 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 0716

General

Designation	07683 / 75016F
Launch date	28 Feb 1975
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1477/1512 km
Inclination	74°
Period	115.9 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 0717

General

Designation	07684 / 75016G
Launch date	28 Feb 1975
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1477/1533 km
Inclination	74°
Period	116.1 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 0718

General

Designation	07685 / 75016H
Launch date	28 Feb 1975
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1427/1487 km
Inclination	74°
Period	115 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 0732

General

Designation	07820 / 75045A
Launch date	28 May 1975
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1401/1468 km
Inclination	74°
Period	114.6 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 0733

General

Designation	07822 / 75045B
Launch date	28 May 1975
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1467/1552 km
Inclination	74°
Period	116.2 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 0734

General

Designation	07823 / 75045C
Launch date	28 May 1975
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1441/1469 km
Inclination	74°
Period	115 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 0735

General

Designation	07824 / 75045D
Launch date	28 May 1975
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1459/1472 km
Inclination	74°
Period	115.2 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 0736

General

Designation	07825 / 75045E
Launch date	28 May 1975
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1467/1484 km
Inclination	74°
Period	115.5 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 0737

General

Designation	07826 / 75045F
Launch date	28 May 1975
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1468/1484 km
Inclination	74°
Period	115.9 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 0738

General

Designation	07827 / 75045G
Launch date	28 May 1975
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1467/1506 km
Inclination	74°
Period	115.7 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 0739

General

Designation	07828 / 75045H
Launch date	28 May 1975
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1421/1506 km
Inclination	74°
Period	115.7 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 0775

General

Designation	08357 / 75097A
Launch date	8 Oct 1975
Country of origin	CIS
Mission	Military: early warning (Oko GEO, also called Prognoz 1st generation)
Geostationary orbit	25°W
Launch vehicle	Proton #54

First satellite of the Oko series for early warning put on geostationary orbit. It was the same design as the Oko satellites on molniya type orbit. Four such satellites were launched: Cosmos 0775, Cosmos 1546, Cosmos 1629 and Cosmos1894. The replacement series is called Prognoz 2nd generation.


 Cosmos 0777

General

Designation	08416 / 75102A
Launch date	29 Oct 1975
Country of origin	CIS
Mission
Perigee/Apogee	425/442 km
Inclination	65°
Period	93.9 min
Launch vehicle
Launch site	Tyuratam
End of life

Decay	3 Jun 1976


 Cosmos 0782

Also called Bion 03

General

Designation	08450 / 75110A
Launch date	25 Nov 1975
Country of origin	CIS
Mission	Scientific
Perigee/Apogee	218/384 km
Inclination	62.8°
Period	90.5 min
Launch vehicle	Soyuz
Launch site	Plesetsk

Study of animals and vegetals in space

End of life

Decay	15 Dec 1975


 Cosmos 0936

Also called Bion 04

General

Designation	10172 / 77074A
Launch date	3 Aug 1977
Country of origin	CIS
Mission	Scientific
Perigee/Apogee	219/396 km
Inclination	62.8°
Period	90.6 min
Launch vehicle	Soyuz
Launch site	Plesetsk

Study of animals and vegetals in space

End of life

Decay	22 Aug 1977


 Cosmos 0954

General

Designation	10361 / 77090A
Launch date	18 Sep 1977
Country of origin	CIS
Mission	Military: ocean reconnaissance (Rorsat)
Perigee/Apogee	251/265 km
Inclination	65°
Period	89.7 min
Launch vehicle
Launch site	Tyuratam
End of life

Decay	24 Jan 1978

Decayed in Canada. It was equipped with a 508 kg Romachka nuclear reactor for power supply with 49 kg of uranium. The CIS payed $2.55 million as compensation


 Cosmos 1000

General

Designation	10776 / 78034A
Launch date	31 Mar 1978
Country of origin	CIS
Mission	Navigation (Tsikada)
Perigee/Apogee	954/1006 km
Inclination	82.9°
Period	104.7 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 1094

General

Designation	11333 / 79033A
Launch date	18 Apr 1979
Country of origin	CIS
Mission	Ocean observation
Perigee/Apogee	426/442 km
Inclination	65°
Period	93.3 min
Launch vehicle
Launch site	Tyuratam
End of life

Decay	7 Nov 1979


 Cosmos 1267

Also called TKS Merkur #2

General

Designation	12419 / 81039A
Launch date	15 Apr 1981
Country of origin	CIS
Mission
Perigee/Apogee	192/259 km
Inclination	51.6°
Period	88.9 min
Launch vehicle	Proton #88

First spacecraft to dock with Salyout 6

End of life

Decay	29 Jul 1982


 Cosmos 1366

General

Designation	13177 / 82044A
Launch date	17 May 1982
Country of origin	CIS
Mission	Military: Telecommunications (Geizer)
Geostationary orbit	80°E
Launch vehicle	Proton #97
End of life

Out of service	late 1987


 Cosmos 1402

General

Designation	13441 / 82084A
Launch date	30 Aug 1982
Country of origin	CIS
Mission	Military: ocean reconnaissance (Rorsat)
Perigee/Apogee	250/266 km
Inclination	65.6°
Period	89.6 min
Launch vehicle
Launch site	Tyuratam

This satellite was powered by a nuclear reactor which separated. The satellite itself decayed in 2 parts on 30 Dec 1982 and 23 Jan 1983 (Indian ocean) Those part were not, or not very radioactive. The nuclear engine decayed on 7 Feb 1983 in the Atlantic.

End of life

Decay	23 Jan 1983


 Cosmos 1443

Also called TKS Merkur #3

General

Designation	13868 / 83013A
Launch date	2 Mar 1983
Country of origin	CIS
Mission
Perigee/Apogee	194/261 km
Inclination	51.6°
Period	89 min
Launch vehicle	Proton #104

First spacecraft to dock with Salyout 7 (10 Mar 1983)

End of life

Decay	19 Sep 1983


 Cosmos 1540

General

Designation	14783 / 84022A
Launch date	2 Mar 1984
Country of origin	CIS
Mission	Military: Telecommunications (Geizer)
Geostationary orbit	80°E or 141°E
Launch vehicle	Proton #117
End of life

Out of service	late 1988


 Cosmos 1546

General

Designation	14867 / 84031A
Launch date	29 Mar 1984
Country of origin	CIS
Mission	Military: early warning (Oko GEO, also called Prognoz 1st generation)
Geostationary orbit	24°W
Launch vehicle	Proton #119
End of life

Out of service	yes


 Cosmos 1629

General

Designation	15574 / 85016A
Launch date	21 Feb 1985
Country of origin	CIS
Mission	Military: early warning (Oko GEO, also called Prognoz 1st generation)
Geostationary orbit	24°W
Launch vehicle	Proton #130
End of life

Out of service	yes


 Cosmos 1700

General

Designation	16199 / 85102A
Launch date	25 Oct 1985
Country of origin	CIS
Mission	Military: Telecommunications: Luch
Geostationary orbit	95°E
Launch vehicle	Proton #136
End of life

Out of service	Feb 1995
Cause	replaced by Luch 0
Technical data

Specifications


 Cosmos 1738

General

Designation	16667 / 86027A
Launch date	4 Apr 1986
Country of origin	CIS
Mission	Military: Telecommunications (Geizer)
Geostationary orbit	13.5°W
Launch vehicle	Proton #141
End of life

Out of service	late 1989
Technical data

Specifications


 Cosmos 1849

General

Designation	18083 / 87048A
Launch date	4 Jun 1987
Country of origin	CIS
Mission	Military: warning
Perigee/Apogee	3104/37311 km
Inclination	67.1°
Period	719 min
Launch vehicle	Molniya
Launch site	Plesetsk


 Cosmos 1850

General

Designation	18095 / 87049A
Launch date	9 Jun 1987
Country of origin	CIS
Mission	Telecommunications (Strela-1)
Perigee/Apogee	775/798 km
Inclination	74°
Period	100.6 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 1851

General

Designation	18103 / 87050A
Launch date	12 Jun 1987
Country of origin	CIS
Mission	Military: warning
Perigee/Apogee	3671/36713 km
Inclination	65.5°
Period	718.4 min
Launch vehicle	Molniya
Launch site	Plesetsk


 Cosmos 1852

General

Designation	18113 / 87051A
Launch date	16 Jun 1987
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1471/1497 km
Inclination	74°
Period	115.6 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 1853

General

Designation	18114 / 87051B
Launch date	16 Jun 1987
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1470/1480 km
Inclination	74°
Period	115.4 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 1854

General

Designation	18115 / 87051C
Launch date	16 Jun 1987
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1456/1478 km
Inclination	74°
Period	115.3 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 1855

General

Designation	18116 / 87051D
Launch date	16 Jun 1987
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1444/1475 km
Inclination	74°
Period	115.1 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 1856

General

Designation	18117 / 87051E
Launch date	16 Jun 1987
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1429/1475 km
Inclination	74°
Period	114.9 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 1857

General

Designation	18118 / 87051F
Launch date	16 Jun 1987
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1414/1475 km
Inclination	74°
Period	114.8 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 1858

General

Designation	18119 / 87051G
Launch date	16 Jun 1987
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1399/1476 km
Inclination	74°
Period	114.6 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 1859

General

Designation	18120 / 87051H
Launch date	16 Jun 1987
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1385/1474 km
Inclination	74°
Period	114.4 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 1860

General

Designation	18122 / 87052A
Launch date	18 Jun 1987
Country of origin	CIS
Mission	Military: ocean reconnaissance (Rorsat)
Perigee/Apogee	900/992 km
Inclination	65°
Period	104 min
Launch vehicle
Launch site	Plesetsk

Equipped with a nuclear reactor


 Cosmos 1861

General

Designation	18129 / 87054A
Launch date	23 Jun 1987
Country of origin	CIS
Mission	Navigation (Tsikada)
Perigee/Apogee	996/996 km
Inclination	82.9°
Period	104.9 min
Launch vehicle	Cosmos C
Launch site	Plesetsk
Technical data

Plane 12

Radio Sputnik 10

beacon/robot	29.357 Mhz (cw)
beacon/robot	29.403 Mhz (cw)
mode a uplink	145.860 - 145.900 Mhz (ssb,cw)
mode a downlink	29.360 - 29.400 Mhz (ssb,cw)
robot a uplink	145.820 Mhz (cw)
robot a downlink	29.357 or 29.403 Mhz (cw)
beacon/robot	29.357 Mhz (cw)
beacon/robot	29.403 Mhz (cw)
mode k uplink	21.160 - 21.200 Mhz (ssb,cw)
mode k downlink	29.360 - 29.400 Mhz (ssb,cw)
robot k uplink	21.120 Mhz (cw)
robot k downlink	29.357 or 29.403 Mhz (cw)
beacon/robot	145.857 Mhz (cw)
beacon/robot	145.903 Mhz (cw)
mode t uplink	21.160 - 21.200 Mhz (ssb,cw)
mode t downlink	145.860 - 145.900 Mhz (ssb,cw)
robot t uplink	21.120 Mhz (cw)
robot t downlink	145.857 or 145.903 Mhz (cw)
Radio Sputnik 11

beacon/robot	29.407 Mhz (cw)
beacon/robot	29.453 Mhz (cw)
mode a uplink	145.910 - 145.950 Mhz (ssb,cw)
mode a downlink	29.410 - 29.450 Mhz (ssb,cw)
robot a uplink	145.830 Mhz (cw)
robot a downlink	29.407 or 29.453 Mhz (cw)
beacon/robot	29.407 Mhz (cw)
beacon/robot	29.453 Mhz (cw)
mode k uplink	21.210 - 21.250 Mhz (ssb,cw)
mode k downlink	29.410 - 29.450 Mhz (ssb,cw)
robot k uplink	21.130 Mhz (cw)
robot k downlink	29.407 or 29.453 Mhz (cw)
beacon/robot	145.907 Mhz (cw)
beacon/robot	145.953 Mhz (cw)
mode t uplink	21.210 - 21.250 Mhz (ssb,cw)
mode t downlink	145.910 - 145.950 Mhz (ssb,cw)
robot t uplink	21.130 Mhz (cw)
robot t downlink	145.907 or 145.953 Mhz (cw)


 Cosmos 1870

General

Designation	18225 / 87064A
Launch date	25 Jul 1987
Country of origin	CIS
Mission	Remote sensing (Almaz-T #2)
Perigee/Apogee	263/278 km
Inclination	71.9°
Period	89.9 min
Launch vehicle	Proton #154
Mass at launch	15 to 20 t

Satellite developped with the United States, France, Finland and Sweden. The SAR module had a resolution of 15 to 30 meters.

End of life

Decay	29 Jul 1989


 Cosmos 1887

Also called Bion 08

General

Designation	18380 / 87083A
Launch date	29 Sep 1987
Country of origin	CIS
Mission
Perigee/Apogee	214/382 km
Inclination	62.8°
Period	90.5 min
Launch vehicle	Soyuz
Launch site	Plesetsk

On board: 2 macaques, 10 rats and 6 fishes

End of life

Decay	12 Oct 1987


 Cosmos 1888

General

Designation	18384 / 87084A
Launch date	1 Oct 1987
Country of origin	CIS
Mission	Military: telecommunications: Geizer
Geostationary orbit	see below
Launch vehicle	Proton #156
Location

Begin	End	Position
L: 1 Oct 1987	Aug 1990	80°E
Sep 1990	Dec 1994	13.5°W
End of life

Out of service	Dec 1994
Technical data

Specifications


 Cosmos 1894

General

Designation	18443 / 87091A
Launch date	28 Oct 1987
Country of origin	CIS
Mission	Military: early warning (Oko GEO, also called Prognoz 1st generation)
Geostationary orbit	24°W
Launch vehicle	Proton #157
End of life

Out of service	yes


 Cosmos 1897

General

Designation	18575 / 87096A
Launch date	26 Nov 1987
Country of origin	CIS
Mission	Military: telecommunications: Luch
Geostationary orbit	95°E
Launch vehicle	Proton #158
End of life

Out of service	yes
Technical data

Specifications


 Cosmos 1923

General

Designation	18931 / 88015A
Launch date	10 Mar 1988
Country of origin	CIS
Mission
Perigee/Apogee	190/302 km
Inclination	72.9°
Period	89.4 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	22 Mar 1988


 Cosmos 1924

General

Designation	18937 / 88016A
Launch date	11 Mar 1988
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1458/1512 km
Inclination	74°
Period	115.7 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 1925

General

Designation	18938 / 88016B
Launch date	11 Mar 1988
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1457/1495 km
Inclination	74°
Period	115.5 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 1926

General

Designation	18939 / 88016C
Launch date	11 Mar 1988
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1458/1477 km
Inclination	74°
Period	115.3 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 1927

General

Designation	18940 / 88016D
Launch date	11 Mar 1988
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1452/1465 km
Inclination	74°
Period	115.1 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 1928

General

Designation	18941 / 88016E
Launch date	11 Mar 1988
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1442/1459 km
Inclination	74°
Period	114.9 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 1929

General

Designation	18942 / 88016F
Launch date	11 Mar 1988
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1426/1459 km
Inclination	74°
Period	114.7 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 1930

General

Designation	18943 / 88016G
Launch date	11 Mar 1988
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1412/1458 km
Inclination	74°
Period	114.6 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 1931

General

Designation	18944 / 88016H
Launch date	11 Mar 1988
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1395/1459 km
Inclination	74°
Period	114.4 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 1932

General

Designation	18957 / 88019A
Launch date	14 Mar 1988
Country of origin	CIS
Mission	Military: ocean reconnaissance (Rorsat)
Perigee/Apogee	921/1007 km
Inclination	65°
Period	104.4 min
Launch vehicle
Launch site	Tyuratam
End of life

Out of service	20 May 1988

Equipped with a nuclear reactor


 Cosmos 1933

General

Designation	18958 / 88020A
Launch date	15 Mar 1988
Country of origin	CIS
Mission	Military: SIGINT (Tselina-D)
Perigee/Apogee	605/628 km
Inclination	82.5°
Period	97 min
Launch vehicle	Cyclone 3 #67


 Cosmos 1934

General

Designation	18985 / 88023A
Launch date	22 Mar 1988
Country of origin	CIS
Mission	Military: Navigation (Parus)
Perigee/Apogee	946/1005 km
Inclination	83°
Period	104.6 min
Launch vehicle	Cosmos C
Launch site	Plesetsk
End of life

Out of service	yes


 Cosmos 1935

General

Designation	19011 / 88025A
Launch date	24 Mar 1988
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	179/356 km
Inclination	67°
Period	89.5 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	8 Apr 1988


 Cosmos 1957

General

Designation	19276 / 88057A
Launch date	7 Jul 1988
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	179/225 km
Inclination	82.6°
Period	88.5 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	21 Jul 1988


 Cosmos 1958

General

Designation	19320 / 88060A
Launch date	14 Jul 1988
Country of origin	CIS
Mission	Military:
Perigee/Apogee	360/411 km
Inclination	65.8°
Period	92.3 min
Launch vehicle	Cosmos C
Launch site	Plesetsk
End of life

Decay	21 Mar 1969


 Cosmos 1959

General

Designation	19324 / 88062A
Launch date	18 Jul 1988
Country of origin	CIS
Mission	Military: Navigation (Parus)
Perigee/Apogee	952/1002 km
Inclination	83°
Period	104.6 min
Launch vehicle	Cosmos C
Launch site	Plesetsk
End of life

Out of service	yes


 Cosmos 1960

General

Designation	19338 / 88065A
Launch date	28 Jul 1988
Country of origin	CIS
Mission	Military
Perigee/Apogee	369/379 km
Inclination	65.8°
Period	92 min
Launch vehicle	Cosmos C
Launch site	Plesetsk
End of life

Decay	9 Apr 1990


 Cosmos 1961

General

Designation	19344 / 88066A
Launch date	1 Aug 1988
Country of origin	CIS
Mission	Military: Telecommunications: Geizer
Geostationary orbit	see below
Launch vehicle	Proton #169
Location

Begin	End	Position
L: 1 Aug 1988	Mar 1992	13.5°W
Apr 1992	mid 1993	0°E
End of life

Out of service	mid 1993
Technical data

Specifications


 Cosmos 1962

General

Designation	19372 / 88068A
Launch date	8 Aug 1988
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	205/265 km
Inclination	70°
Period	89.2 min
Launch vehicle	Soyuz
Launch site	Tyuratam
End of life

Decay	22 Aug 1988


 Cosmos 1963

General

Designation	19384 / 88070A
Launch date	16 Aug 1988
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	176/350 km
Inclination	64.8°
Period	89.8 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	2 Oct 1988


 Cosmos 1964

General

Designation	19412 / 88072A
Launch date	23 Aug 1988
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	206/271 km
Inclination	70°
Period	89.3 min
Launch vehicle	Soyuz
Launch site	Tyuratam
End of life

Decay	7 Sep 1988


 Cosmos 1965

General

Designation	19414 / 88073A
Launch date	23 Aug 1988
Country of origin	CIS
Mission	Military: remote sensing (Priroda)
Perigee/Apogee	179/228 km
Inclination	82.3°
Period	88.6 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	22 Sep 1988


 Cosmos 1966

General

Designation	19445 / 88076A
Launch date	30 Aug 1988
Country of origin	CIS
Mission	Military: telecommunications (experimental)
Perigee/Apogee	2592/37777 km
Inclination	67.4°
Period	718.1 min
Launch vehicle	Molniya
Launch site	Plesetsk


 Cosmos 1967

General

Designation	19462 / 88079A
Launch date	6 Sep 1988
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	191/380 km
Inclination	72.9°
Period	90.2 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	15 Sep 1988


 Cosmos 1968

General

Designation	19488 / 88082A
Launch date	9 Sep 1988
Country of origin	CIS
Mission	Military: remote sensing
Perigee/Apogee	177/230 km
Inclination	82.3°
Period	88.6 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	23 Sep 1988


 Cosmos 1969

General

Designation	19495 / 88084A
Launch date	15 Sep 1988
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	165/344 km
Inclination	67.1°
Period	89.6 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	13 Nov 1988


 Cosmos 1970

General

Designation	19501 / 88085A
Launch date	16 Sep 1988
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19099/19159 km
Inclination	65.7°
Period	675.7 min
Launch vehicle	Proton #171


 Cosmos 1971

General

Designation	19502 / 88085B
Launch date	16 Sep 1988
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19099/19159 km
Inclination	65.7°
Period	675.7 km
Launch vehicle	Proton #171


 Cosmos 1972

General

Designation	19503 / 88085C
Launch date	16 Sep 1988
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19113/19145 km
Inclination	65.7°
Period	675.7 min
Launch vehicle	Proton #171


 Cosmos 1973

General

Designation	19521 / 88088A
Launch date	22 Sep 1988
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	192/359 km
Inclination	72.8°
Period	90 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	10 Oct 1988


 Cosmos 1974

General

Designation	19554 / 88092A
Launch date	3 Oct 1988
Country of origin	CIS
Mission	Military: warning
Perigee/Apogee	3323/37025 km
Inclination	64.7°
Period	717.7 min
Launch vehicle	Molniya


 Cosmos 1975

General

Designation	19573 / 88093A
Launch date	11 Oct 1988
Country of origin	CIS
Mission	Military: SIGINT (Tselina-D)
Perigee/Apogee	604/634 km
Inclination	82.5°
Period	97.1 min
Launch vehicle	Cyclone 3 #72


 Cosmos 1976

General

Designation	19582 / 88094A
Launch date	13 Oct 1988
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	190/366 km
Inclination	72.9°
Period	90.1 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	27 Oct 1988


 Cosmos 1977

General

Designation	19608 / 88096A
Launch date	25 Oct 1988
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	3263/37085 km
Inclination	64.7°
Period	717.7 min
Launch vehicle	Molniya
Launch site	Plesetsk


 Cosmos 1978

General

Designation	19612 / 88097A
Launch date	27 Oct 1988
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	190/364 km
Inclination	72.9°
Period	90.1 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	10 Nov 1988


 Cosmos 1979

General

Designation	19647 / 88101A
Launch date	18 Nov 1988
Country of origin	CIS
Mission	Military
Perigee/Apogee	402/415 km
Inclination	65°
Period	92.7 min
Launch vehicle
Launch site	Tyuratam
End of life

Decay	25 Dec 1989


 Cosmos 1980

General

Designation	19649 / 88102A
Launch date	23 Nov 1988
Country of origin	CIS
Mission	Military: SIGINT (Tselina-2)
Perigee/Apogee	840/850 km
Inclination	71°
Period	101.8 min
Launch vehicle	Zenit


 Cosmos 1982

General

Designation	19662 / 88105A
Launch date	30 Nov 1988
Country of origin	CIS
Mission	Military: photography reconnaissance
Perigee/Apogee	204/377 km
Inclination	70°
Period	90.3 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	14 Dec 1988


 Cosmos 1983

General

Designation	19672 / 88107A
Launch date	8 Dec 1988
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	243/256 km
Inclination	62.8°
Period	89.5 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	22 Dec 1988


 Cosmos 1984

General

Designation	19705 / 88110A
Launch date	16 Dec 1988
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	186/323 km
Inclination	62.8°
Period	89.6 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	13 Feb 1989


 Cosmos 1985

General

Designation	19720 / 88113A
Launch date	23 Dec 1988
Country of origin	CIS
Mission	Military: radar calibration (Radar-Cal-2 #1)
Perigee/Apogee	206/220 km
Inclination	73.5°
Period	88.8 min
Launch vehicle	Cyclone 3 #73
End of life

Decay	4 May 1992


 Cosmos 1986

General

Designation	19734 / 88116A
Launch date	29 Dec 1988
Country of origin	CIS
Mission	Military: observation
Perigee/Apogee	193/289 km
Inclination	64.8°
Period	89.3 min
Launch vehicle	Soyuz
Launch site	Tyuratam
End of life

Decay	11 Feb 1989


 Cosmos 1987

Also called Glonass 40

General

Designation	19749 / 89001A
Launch date	10 Jan 1989
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19113/19145 km
Inclination	64.9°
Period	675.7 min
Launch vehicle	Proton #174
End of life

Out of service	yes


 Cosmos 1988

Also called Glonass 41

General

Designation	19750 / 89001B
Launch date	10 Jan 1989
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19111/19147 km
Inclination	65°
Period	675.7 min
Launch vehicle	Proton #174
End of life

Out of service	yes


 Cosmos 1989

General

Designation	19751 / 89001C
Launch date	10 Jan 1989
Country of origin	CIS
Mission	Navigation (Etalon #1)
Perigee/Apogee	19097/19152 km
Inclination	64.9°
Period	675.5 min
Launch vehicle	Proton #174


 Cosmos 1990

General

Designation	19756 / 89002A
Launch date	12 Jan 1989
Country of origin	CIS
Mission	Military: remote sensing (Priroda)
Perigee/Apogee	177/227 km
Inclination	82.6°
Period	88.5 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	11 Feb 1989


 Cosmos 1991

General

Designation	19758 / 89003A
Launch date	18 Jan 1989
Country of origin	CIS
Mission	Military: remote sensing (Priroda)
Perigee/Apogee	204/375 km
Inclination	70°
Period	90.3 min
Launch vehicle	Soyuz
Launch site	Tyuratam
End of life

Decay	1 Feb 1989


 Cosmos 1992

General

Designation	19769 / 89005A
Launch date	26 Jan 1989
Country of origin	CIS
Mission	Telecommunications (Strela-1)
Perigee/Apogee	764/798 km
Inclination	74°
Period	100.5 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 1993

General

Designation	19774 / 89007A
Launch date	28 Jan 1989
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	171/347 km
Inclination	64.8°
Period	89.7 min
Launch vehicle	Soyuz
Launch site	Tyuratam
End of life

Decay	27 Mar 1989


 Cosmos 1994

General

Designation	19785 / 89009A
Launch date	10 Feb 1989
Country of origin	CIS
Mission	Telecommunications (Strela-3)
Perigee/Apogee	1391/1414 km
Inclination	82.6°
Period	113.9 min
Launch vehicle	Cyclone 3 #74


 Cosmos 1995

General

Designation	19786 / 89009B
Launch date	10 Feb 1989
Country of origin	CIS
Mission	Telecommunications (Strela-3)
Perigee/Apogee	1409/1415 km
Inclination	82.6°
Period	114.1 min
Launch vehicle	Cyclone 3 #74


 Cosmos 1996

General

Designation	19787 / 89009C
Launch date	10 Feb 1989
Country of origin	CIS
Mission	Telecommunications (Strela-3)
Perigee/Apogee	1403/1414 km
Inclination	82.6°
Period	114 min
Launch vehicle	Cyclone 3 #74


 Cosmos 1997

General

Designation	19788 / 89009D
Launch date	10 Feb 1989
Country of origin	CIS
Mission	Telecommunications (Strela-3)
Perigee/Apogee	1397/1414 km
Inclination	82.6°
Period	113.9 min
Launch vehicle	Cyclone 3 #74


 Cosmos 1998

General

Designation	19789 / 89009E
Launch date	10 Feb 1989
Country of origin	CIS
Mission	Telecommunications (Strela-3)
Perigee/Apogee	1387/1414 km
Inclination	82.6°
Period	113.8 min
Launch vehicle	Cyclone 3 #74


 Cosmos 1999

General

Designation	19790 / 89009F
Launch date	10 Feb 1989
Country of origin	CIS
Mission	Telecommunications (Strela-3)
Perigee/Apogee	1381/1414 km
Inclination	82.6°
Period	113.7 min
Launch vehicle	Cyclone 3 #74


 Cosmos 2000

General

Designation	19792 / 89010A
Launch date	10 Feb 1989
Country of origin	CIS
Mission	Military: ?
Perigee/Apogee	175/243 km
Inclination	82.3°
Period	88.7 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	2 Mar 1989


 Cosmos 2001

General

Designation	19796 / 89011A
Launch date	14 Feb 1989
Country of origin	CIS
Mission	Military: warning
Perigee/Apogee	2437/37977 km
Inclination	66.5°
Period	719 min
Launch vehicle	Molniya
Launch site	Plesetsk


 Cosmos 2002

General

Designation	19800 / 89012A
Launch date	14 Feb 1989
Country of origin	CIS
Mission	Military: radar calibration
Perigee/Apogee	179/1525 km
Inclination	65.8°
Period	102 min
Launch vehicle	Cosmos C
Launch site	Plesetsk
End of life

Decay	15 Oct 1989


 Cosmos 2003

General

Designation	19818 / 89015A
Launch date	17 Feb 1989
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	244/255 km
Inclination	62.8°
Period	89.5 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	3 Mar 1989


 Cosmos 2004

General

Designation	19826 / 89017A
Launch date	22 Feb 1989
Country of origin	CIS
Mission	Navigation
Perigee/Apogee	968/1015 km
Inclination	82.9°
Period	104.9 min
Launch vehicle	Cosmos C
Launch site	Plesetsk
Technical data

Downlink frequency: 149.940 MHz


 Cosmos 2005

General

Designation	19862 / 89019A
Launch date	2 Mar 1989
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	188/324 km
Inclination	62.8°
Period	89.6 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	25 Apr 1989


 Cosmos 2006

General

Designation	19893 / 89022A
Launch date	16 Mar 1989
Country of origin	CIS
Mission	Military: observation
Perigee/Apogee	240/380 km
Inclination	62.8°
Period	90.7 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	31 Mar 1989


 Cosmos 2007

General

Designation	19900 / 89024A
Launch date	23 Mar 1989
Country of origin	CIS
Mission	Military: reconnaissance (5th generation)
Perigee/Apogee	224/262 km
Inclination	64.7°
Period	89.4 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	22 Sep 1989


 Cosmos 2008

General

Designation	19902 / 89025A
Launch date	24 Mar 1989
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1391/1469 km
Inclination	74°
Period	114.4 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 2009

General

Designation	19903 / 89025B
Launch date	24 Mar 1989
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1406/1470 km
Inclination	74°
Period	114.6 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 2010

General

Designation	19904 / 89025C
Launch date	24 Mar 1989
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1421/1470 km
Inclination	74°
Period	114.8 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 2011

General

Designation	19905 / 89025D
Launch date	24 Mar 1989
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1437/1470 km
Inclination	74°
Period	115 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 2012

General

Designation	19906 / 89025E
Launch date	24 Mar 1989
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1453/1470 km
Inclination	74°
Period	115.1 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 2013

General

Designation	19907 / 89025F
Launch date	24 Mar 1989
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1462/1478 km
Inclination	74°
Period	115.3 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 2014

General

Designation	19908 / 89025G
Launch date	24 Mar 1989
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1469/1487 km
Inclination	74°
Period	115.5 min
Launch vehicle	Cosmos C
Launch site	Plestesk


 Cosmos 2015

General

Designation	19909 / 89025H
Launch date	24 Mar 1989
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1467/1507 km
Inclination	74°
Period	115.7 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 2016

General

Designation	19921 / 89028A
Launch date	4 Apr 1989
Country of origin	CIS
Mission	Navigation
Perigee/Apogee	952/1010 km
Inclination	83°
Period	104.7 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 2017

General

Designation	19923 / 89029A
Launch date	6 Apr 1989
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	244/260 km
Inclination	62.8°
Period	89.6 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	19 Apr 1989


 Cosmos 2018

General

Designation	19938 / 89031A
Launch date	20 Apr 1989
Country of origin	CIS
Mission	Military: Navigation (Tsigal)
Perigee/Apogee	185/327 km
Inclination	62.9°
Period	89.6 min
Launch vehicle	Cosmos
Launch site	Plesetsk
End of life

Decay	19 Jun 1989


 Cosmos 2019

General

Designation	19972 / 89034A
Launch date	5 May 1989
Country of origin	CIS
Mission	Military: observation
Perigee/Apogee	241/256 km
Inclination	62.9°
Period	89.5 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	18 May 1989


 Cosmos 2020

General

Designation	19986 / 89036A
Launch date	17 May 1989
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	178/280 km
Inclination	64.8°
Period	89.7 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	15 Jul 1989


 Cosmos 2021

General

Designation	20000 / 89037A
Launch date	24 May 1989
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	204/280 km
Inclination	69.9°
Period	89.4 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	6 Jul 1989


 Cosmos 2022

Also called Glonass 42

General

Designation	20024 / 89039A
Launch date	31 May 1989
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19119/19139 km
Inclination	65.5°
Period	675.7 min
Launch vehicle	Proton #177
End of life

Out of service	yes


 Cosmos 2023

Also called Glonass 43

General

Designation	20025 / 89039b
Launch date	31 May 1989
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19087/19170 km
Inclination	65.5°
Period	675.7 min
Launch vehicle	Proton #177
End of life

Out of service	yes


 Cosmos 2024

General

Designation	20026 / 89039C
Launch date	31 May 1989
Country of origin	CIS
Mission	Military: geodesy (Etalon #2)
Perigee/Apogee	19095/19146 km
Inclination	65.5°
Period	675.4 min
Launch vehicle	Proton #177


 Cosmos 2025

General

Designation	20035 / 89040A
Launch date	1 Jun 1989
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	236/256 km
Inclination	62.8°
Period	89.4 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	15 Jun 1989


 Cosmos 2026

General

Designation	20045 / 89042A
Launch date	7 Jun 1989
Country of origin	CIS
Mission	Navigation
Perigee/Apogee	948/1006 km
Inclination	82.9°
Period	104.6 min
Launch vehicle	Cosmos C
Launch site	Plesetsk
Technical data

Downlink frequency: 149.97 MHz


 Cosmos 2027

General

Designation	20064 / 89045A
Launch date	14 Jun 1989
Country of origin	CIS
Mission	Military: radar calibration
Perigee/Apogee	394/427 km
Inclination	65.8°
Period	92.8 min
Launch vehicle	Cosmos C
Launch site	Plesetsk
End of life

Decay	14 Apr 1992


 Cosmos 2028

General

Designation	20073 / 89047A
Launch date	16 Jun 1989
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	204/243 km
Inclination	70°
Period	89 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	6 Jul 1989


 Cosmos 2029

General

Designation	20105 / 89051A
Launch date	5 Jul 1989
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	178/238 km
Inclination	82.3°
Period	88.7 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	19 Jul 1989


 Cosmos 2030

General

Designation	20124 / 89054A
Launch date	12 Jul 1989
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	162/349 km
Inclination	67.2°
Period	89.6 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	29 Jul 1989


 Cosmos 2031

General

Designation	20136 / 89056A
Launch date	18 Jul 1989
Country of origin	CIS
Mission	Military
Perigee/Apogee	211/264 km
Inclination	50.4°
Period	89.6 min
Launch vehicle	Soyuz
Launch site	Tyuratam
End of life

Decay	15 Sep 1989


 Cosmos 2032

General

Designation	20145 / 89057A
Launch date	20 Jul 1989
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	179/241 km
Inclination	82.3°
Period	88.7 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	3 Aug 1989


 Cosmos 2033

General

Designation	20147 / 89058A
Launch date	24 Jul 1989
Country of origin	CIS
Mission	Military
Perigee/Apogee	196/322 km
Inclination	65°
Period	89.7 min
Launch vehicle
Launch site	Tyuratam
End of life

Decay	6 Jan 1991


 Cosmos 2034

General

Designation	20149 / 89059A
Launch date	25 Jul 1989
Country of origin	CIS
Mission	Navigation
Perigee/Apogee	962/1010 km
Inclination	82.9°
Period	104.8 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 2035

General

Designation	20151 / 89060A
Launch date	2 Aug 1989
Country of origin	CIS
Mission	Military: observation
Perigee/Apogee	176/306 km
Inclination	82.6°
Period	88.6 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	16 Aug 1989


 Cosmos 2036

General

Designation	20188 / 89065A
Launch date	22 Aug 1989
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	244/259 km
Inclination	62.8°
Period	89.5 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	5 Sep 1989


 Cosmos 2037

General

Designation	20196 / 89068A
Launch date	28 Aug 1989
Country of origin	CIS
Mission	Scientific: geodesy (Geo-IK)
Perigee/Apogee	1482/1522 km
Inclination	73.6°
Period	116 min
Launch vehicle	Cyclone 3 #77


 Cosmos 2038

General

Designation	20232 / 89074A
Launch date	14 Sep 1989
Country of origin	CIS
Mission	Telecommunications (Strela-3)
Perigee/Apogee	1389/1408 km
Inclination	82.6°
Period	113.8 min
Launch vehicle	Cyclone 3 #78


 Cosmos 2039

General

Designation	20233 / 89074B
Launch date	14 Sep 1989
Country of origin	CIS
Mission	Telecommunications (Strela-3)
Perigee/Apogee	1382/1408 km
Inclination	82.6°
Period	113.7 min
Launch vehicle	Cyclone 3 #78


 Cosmos 2040

General

Designation	20234 / 89074C
Launch date	14 Sep 1989
Country of origin	CIS
Mission	Telecommunications (Strela-3)
Perigee/Apogee	1407/1413 km
Inclination	82.6°
Period	114 min
Launch vehicle	Cyclone 3 #78


 Cosmos 2041

General

Designation	20235 / 89074D
Launch date	14 Sep 1989
Country of origin	CIS
Mission	Telecommunications (Strela-3)
Perigee/Apogee	1394/1408 km
Inclination	82.6°
Period	113.8 min
Launch vehicle	Cyclone 3 #78


 Cosmos 2042

General

Designation	20236 / 89074E
Launch date	14 Sep 1989
Country of origin	CIS
Mission	Telecommunications (Strela-3)
Perigee/Apogee	1398/1409 km
Inclination	82.6°
Period	113.9 min
Launch vehicle	Cyclone 3 #78


 Cosmos 2043

General

Designation	20237 / 89074F
Launch date	14 Sep 1989
Country of origin	CIS
Mission	Telecommunications (Strela-3)
Perigee/Apogee	1406/1407 km
Inclination	82.6°
Period	113.9 min
Launch vehicle	Cyclone 3 #78


 Cosmos 2044

Also called BioCosmos 9 or Bion 09

General

Designation	20242 / 89075A
Launch date	15 Sep 1989
Country of origin	CIS
Mission	Scientific
Perigee/Apogee	203/264 km
Inclination	82.3°
Period	89.2 min
Launch vehicle	Soyuz
Launch site	Plesetsk

Satellite with German, Austrian, Canadian, Danish, Spanish, American, French, Hungarian, Norwegian, Rumanian, Swiss and Czech experiments.

End of life

Decay	29 Sep 1989


 Cosmos 2045

General

Designation	20244 / 89076A
Launch date	22 Sep 1989
Country of origin	CIS
Mission	Military: observation
Perigee/Apogee	205/295 km
Inclination	70°
Period	89.5 min
Launch vehicle	Soyuz
Launch site	Tyuratam
End of life

Decay	2 Oct 1989


 Cosmos 2047

General

Designation	20279 / 89082A
Launch date	3 Oct 1989
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	165/330 km
Inclination	67.1°
Period	89.5 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	21 Nov 1989


 Cosmos 2048

General

Designation	20292 / 89083A
Launch date	17 Oct 1989
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	253/269 km
Inclination	62.6°
Period	89.7 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	26 Oct 1989


 Cosmos 2049

General

Designation	20320 / 89088A
Launch date	17 Nov 1989
Country of origin	CIS
Mission	Military: reconnaissance (5th generation)
Perigee/Apogee	232/251 km
Inclination	64.8°
Period	89.3 min
Launch vehicle	Soyuz
Launch site	Tyuratam
End of life

Decay	19 Jun 1990


 Cosmos 2050

General

Designation	20330 / 89091A
Launch date	23 Nov 1989
Country of origin	CIS
Mission	Military: warning
Perigee/Apogee	2273/38112 km
Inclination	62.7°
Period	718.4 min
Launch vehicle	Molniya
Launch site	Plesetsk


 Cosmos 2051

General

Designation	20334 / 89092A
Launch date	24 Nov 1989
Country of origin	CIS
Mission	Military
Perigee/Apogee	293/310 km
Inclination	64.9°
Period	90.6 min
Launch vehicle
Launch site	Tyuratam
End of life

Decay	21 Jan 1990


 Cosmos 2052

General

Designation	20350 / 89095A
Launch date	30 Nov 1989
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	174/320 km
Inclination	67.1°
Period	89.5 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	24 Jan 1990


 Cosmos 2054

General

Designation	20391 / 89101A
Launch date	27 Dec 1989
Country of origin	CIS
Mission	Military: Telecommunications: Luch
Geostationary orbit	16°W, inclined
Launch vehicle
Launch site	Tyuratam
End of life

Out of service	mid-1997
Cause	drifting West, probably out of control
Technical data

Specifications


 Cosmos 2055

General

Designation	20426 / 90003A
Launch date	17 Jan 1990
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	248/260 km
Inclination	62.8°
Period	89.6 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	29 Jan 1990


 Cosmos 2056

General

Designation	20432 / 90004A
Launch date	18 Jan 1990
Country of origin	CIS
Mission	Telecommunications (Strela-1)
Perigee/Apogee	769/802 km
Inclination	74°
Period	100.6 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 2057

General

Designation	20457 / 90009A
Launch date	25 Jan 1990
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	183/330 km
Inclination	62.8°
Period	89.6 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	19 Mar 1990


 Cosmos 2058

General

Designation	20465 / 90010A
Launch date	30 Jan 1989
Country of origin	CIS
Mission	Military: SIGINT (Tselina-D)
Perigee/Apogee	616/645 km
Inclination	82.5°
Period	97.3 min
Launch vehicle	Cyclone 3 #82


 Cosmos 2059

General

Designation	20476 / 90012A
Launch date	6 Feb 1990
Country of origin	CIS
Mission	Military: radar calibration
Perigee/Apogee	184/1585 km
Inclination	65.8°
Period	102.7 min
Launch vehicle	Cosmos C
Launch site	Plesetsk
End of life

Decay	12 Nov 1990


 Cosmos 2061

General

Designation	20527 / 90023A
Launch date	20 Mar 1990
Country of origin	CIS
Mission	Navigation
Perigee/Apogee	967/1015 km
Inclination	82.9°
Period	104.9 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 2062

General

Designation	20529 / 90024A
Launch date	22 Mar 1990
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	178/221 km
Inclination	82.3°
Period	88.5 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	5 Apr 1990


 Cosmos 2063

General

Designation	20536 / 90026A
Launch date	27 Mar 1990
Country of origin	CIS
Mission	Military: early warning (Oko)
Perigee/Apogee	1706/38633 km
Inclination	63.8°
Period	717.5 min
Launch vehicle	Molniya
Launch site	Plesetsk


 Cosmos 2064

General

Designation	20549 / 90029A
Launch date	6 Apr 1990
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1460/1488 km
Inclination	74°
Period	115.4 min
Launch vehicle	Cosmos
Launch site	Plesetsk


 Cosmos 2065

General

Designation	20550 / 90029B
Launch date	6 Apr 1990
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1459/1473 km
Inclination	74°
Period	115.2 min
Launch vehicle	Cosmos
Launch site	Plesetsk


 Cosmos 2066

General

Designation	20551 / 90029C
Launch date	6 Apr 1990
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1383/1461 km
Inclination	74°
Period	114.3 min
Launch vehicle	Cosmos
Launch site	Plesetsk


 Cosmos 2067

General

Designation	20552 / 90029D
Launch date	6 Apr 1990
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1398/1461 km
Inclination	74°
Period	114.4 min
Launch vehicle	Cosmos
Launch site	Plesetsk


 Cosmos 2068

General

Designation	20553 / 90029E
Launch date	6 Apr 1990
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1413/1460 km
Inclination	74°
Period	114.6 min
Launch vehicle	Cosmos
Launch site	Plesetsk


 Cosmos 2069

General

Designation	20554 / 90029F
Launch date	6 Apr 1990
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1427/1461 km
Inclination	74°
Period	114.8 min
Launch vehicle	Cosmos
Launch site	Plesetsk


 Cosmos 2070

General

Designation	20555 / 90029G
Launch date	6 Apr 1990
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1441/1461 km
Inclination	74°
Period	114.9 min
Launch vehicle	Cosmos
Launch site	Plesetsk


 Cosmos 2071

General

Designation	20556 / 90029H
Launch date	6 Apr 1990
Country of origin	CIS
Mission	Telecommunications (Strela-2)
Perigee/Apogee	1457/1461 km
Inclination	74°
Period	115.1 min
Launch vehicle	Cosmos
Launch site	Plesetsk


 Cosmos 2072

General

Designation	20568 / 90033A
Launch date	13 Apr 1990
Country of origin	CIS
Mission	Military: reconnaissance (5th generation)
Perigee/Apogee	232/270 km
Inclination	64.7°
Period	89.5 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	22 Nov 1990


 Cosmos 2073

General

Designation	20573 / 90035A
Launch date	17 Apr 1990
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	173/239 km
Inclination	82.4°
Period	88.6 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	28 Apr 1990


 Cosmos 2074

General

Designation	20577 / 90036A
Launch date	13 Apr 1990
Country of origin	CIS
Mission	Navigation
Perigee/Apogee	962/1002 km
Inclination	82.9°
Period	104.7 min
Launch vehicle	Cosmos C
Launch site	Tyuratam
End of life

Out of service
Cause	failed
Decay
Technical data

Downlink frequencies: 149.910 & 399.760 MHz


 Cosmos 2079

Also called Glonass 44

General

Designation	20619 / 90045A
Launch date	19 May 1990
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19069/19189 km
Inclination	65.3°
Period	675.7 min
Launch vehicle
Launch site
End of life

Out of service	yes


 Cosmos 2080

Also called Glonass 45

General

Designation	20620 / 90045B
Launch date	19 May 1990
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19107/19151 km
Inclination	65.3°
Period	675.7 min
Launch vehicle
Launch site
End of life

Out of service	yes


 Cosmos 2081

Also called Glonass 46

General

Designation	20621 / 90045C
Launch date	19 May 1990
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19107/19151 km
Inclination	65.3°
Period	675.7 min
Launch vehicle
Launch site
End of life

Out of service	yes


 Cosmos 2085

General

Designation	20693 / 90061A
Launch date	18 Jul 1990
Country of origin	CIS
Mission	Military: telecommunications: Geizer
Geostationary orbit	80°E
Launch vehicle
Launch site	Tyuratam
End of life

Out of service	mid 1995?
Technical data

Specifications


 Cosmos 2100

General

Designation	20804 / 90083A
Launch date	14 Sep 1990
Country of origin	CIS
Mission
Perigee/Apogee	957/1010 km
Inclination	82,9°
Period	104.8 min
Launch vehicle	Cosmos C
Launch site	Plesetsk
Technical data

Downlink frequency: 149.970 MHz


 Cosmos 2107

General

Designation	20985 / 90108A
Launch date	4 Dec 1990
Country of origin	CIS
Mission	Military: ocean reconnaissance (Eorsat)
Perigee/Apogee	402/416 km
Inclination	65°
Period	92.8 min
Launch vehicle
Launch site	Plesetsk
End of life

Decay	6 Apr 1992


 Cosmos 2108

General

Designation	21000 / 90109A
Launch date	4 Dec 1990
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	164/289 km
Inclination	62.8°
Period	89 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	28 Jan 1991


 Cosmos 2109

Also called Glonass 47

General

Designation	21006 / 90110A
Launch date	8 Dec 1990
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	18975/19283 km
Inclination	64.9°
Period	675.7 min
Launch vehicle	Proton #193
End of life

Out of service	yes


 Cosmos 2110

Also called Glonass 48

General

Designation	21007 / 90110B
Launch date	8 Dec 1990
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19036/19223 km
Inclination	64.9°
Period	675.7 min
Launch vehicle	Proton #193
End of life

Out of service	yes


 Cosmos 2111

Also called Glonass 49 or Glonass 249

General

Designation	21008 / 90110C
Launch date	8 Dec 1990
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19110/19148 km
Inclination	65°
Period	675.7 min
Launch vehicle	Proton #193
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel	23
Plane	1
Slot	5


 Cosmos 2112

General

Designation	21014 / 90111A
Launch date	10 Dec 1990
Country of origin	CIS
Mission	Telecommunications (Strela-1)
Perigee/Apogee	765/807 km
Inclination	74°
Period	100.6 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 2123

General

Designation	21089 / 91007A
Launch date	5 Feb 1991
Country of origin	CIS
Mission	Navigation (Tsikada)
Perigee/Apogee	961/1003 km
Inclination	82.9°
Period	104.7 min
Launch vehicle
Launch site	Plesetsk
End of life

Out of service
Cause	failed
Decay
Technical data

Downlink frequencies (navigation payload): 150 & 400 MHz

Plane 13

Radio Sputnik 12

beacon/robot	29.408 mhz (cw)
beacon/robot	29.454 mhz (cw)
mode a uplink	145.910 - 145.950 mhz (ssb,cw)
mode a downlink	29.410 - 29.450 mhz (ssb,cw)
robot a uplink	145.831 mhz (cw)
robot a downlink	29.408 or 29.454 mhz (cw)
beacon/robot	29.408 mhz (cw)
beacon/robot	29.454 mhz (cw)
mode k uplink	21.210 - 21.250 mhz (ssb,cw)
mode k downlink	29.410 - 29.450 mhz (ssb,cw)
robot k uplink	21.129 mhz (cw)
robot k downlink	29.408 or 29.454 mhz (cw)
beacon/robot	145.912 mhz (cw)
beacon/robot	145.959 mhz (cw)
mode t uplink	21.210 - 21.250 hz (ssb,cw)
mode t downlink	145.910 - 145.950 mhz (ssb,cw)
robot t uplink	21.129 mhz (cw)
robot t downlink	145.912 or 145.959 mhz (cw)
Radio Sputnik 13

beacon/robot	29.458 mhz (cw)
beacon/robot	29.504 mhz (cw)
mode a uplink	145.960 - 146.000 mhz (ssb,cw)
mode a downlink	29.460 - 29.500 mhz (ssb,cw)
robot a uplink	145.840 mhz (cw)
robot a downlink	29.458 or 29.504 mhz (cw)
beacon/robot	29.458 mhz (cw)
beacon/robot	29.504 mhz (cw)
mode k uplink	21.260 - 21.300 mhz (ssb,cw)
mode k downlink	29.460 - 29.500 mhz (ssb,cw)
robot k uplink	21.138 mhz (cw)
robot k downlink	29.458 or 29.504 mhz (cw)
beacon/robot	145.862 mhz (cw)
beacon/robot	145.908 mhz (cw)
mode t uplink	21.260 - 21.300 mhz (ssb,cw)
mode t downlink	145.960 - 146.000 mhz (ssb,cw)
robot t uplink	21.138 mhz (cw)
robot downlink	145.862 or 145.908 mhz (cw)


 Cosmos 2133

General

Designation	21111 / 91010A
Launch date	14 Feb 1991
Country of origin	CIS
Mission	Military: early warning (Prognoz 2nd generation)
Geostationary orbit	80°E, inclined
Launch vehicle
Launch site	Tyuratam
End of life

Out of service	Oct 1995
Technical data

Specifications

Prime contractor	NPO Lavochkin
Platform
Mass at launch	2600 kg
Mass in orbit
Length
Width
Height
Stabilization
DC power
Design lifetime

S-band capacity


 Cosmos 2139

Also called Glonass 50

General

Designation	21216 / 91025A
Launch date	4 Apr 1991
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19103/19155 km
Inclination	65.1°
Period	675.7 min
Launch vehicle
Launch site
End of life

Out of service	yes


 Cosmos 2140

Also called Glonass 51

General

Designation	21217 / 91025B
Launch date	4 Apr 1991
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19102/19156 km
Inclination	65.1°
Period	675.7 min
Launch vehicle
Launch site
End of life

Out of service	yes


 Cosmos 2141

Also called Glonass 52

General

Designation	21218 / 91025C
Launch date	4 Apr 1991
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19109/19149 km
Inclination	65.1°
Period	675.7 min
Launch vehicle
Launch site
End of life

Out of service	yes


 Cosmos 2142

General

Designation	21230 / 91029A
Launch date	16 Apr 1991
Country of origin	CIS
Mission	Military: Navigation (Parus)
Perigee/Apogee	958/1017 km
Inclination	83°
Period	104.9 min
Launch vehicle	Cosmos C
Launch site	Plesetsk
Technical data

Downlink frequencies: 150.030 & 400.080 MHz


 Cosmos 2155

General

Designation	21702 / 91064A
Launch date	13 Sep 1991
Country of origin	CIS
Mission	Military: early warning
Geostationary orbit
Launch vehicle
Launch site	Tyuratam


 Cosmos 2172

General

Designation	21789 / 91079A
Launch date	22 Nov 1991
Country of origin	CIS
Mission	Military: telecommunications: Geizer
Geostationary orbit	see below
Launch vehicle
Launch site	Tyuratam
Location

Begin	End	Position
L: 22 Nov 1991	Feb 1996	13.5°W, inclined
End of life

Out of service	Mar 1996
Technical data

Specifications


 Cosmos 2173

General

Designation	21796 / 91081A
Launch date	26 Nov 1991
Country of origin	CIS
Mission	Military: Navigation (Parus)
Perigee/Apogee	944/1015 km
Inclination	82.9°
Period	104.7 min
Launch vehicle	Cosmos C
Launch site
End of life

Out of service	yes
Technical data

Downlink frequency: 149.97 & 399.92 MHz

Plane 4


 Cosmos 2177

Also called Glonass 53

General

Designation	21853 / 92005A
Launch date	29 Jan 1992
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19112/19146 km
Inclination	64.8°
Period	675.7 min
Launch vehicle
Launch site
End of life

Out of service	yes


 Cosmos 2178

Also called Glonass 54 or Glonass 769

General

Designation	21854 / 92005B
Launch date	29 Jan 1992
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19088/19170 km
Inclination	65°
Period	675.7 min
Launch vehicle
Launch site
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel	2
Plane	1
Slot	8


 Cosmos 2179

Also called Glonass 55 or Glonass 771

General

Designation	21855 / 92005C
Launch date	29 Jan 1992
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19109/19149 km
Inclination	65°
Period	675.7 min
Launch vehicle
Launch site
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel	23
Plane	1
Slot	1


 Cosmos 2204

Also called Glonass 56 or Glonass 774

General

Designation	22056 / 92047A
Launch date	30 Jul 1992
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19114/19144 km
Inclination	64°
Period	675.7 min
Launch vehicle
Launch site
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel	1
Plane	3
Slot	24


 Cosmos 2205

Also called Glonass 57 or Glonass 756

General

Designation	22057 / 92047B
Launch date	30 Jul 1992
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19110/19148 km
Inclination	64°
Period	675.7 min
Launch vehicle
Launch site
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel	24
Plane	3
Slot	21


 Cosmos 2206

Also called Glonass 58 or Glonass 772

General

Designation	22058 / 92047C
Launch date	30 Jul 1992
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19098/19160 km
Inclination	64°
Period	675.7 min
Launch vehicle
Launch site
End of life

Out of service	27 Aug 1994


 Cosmos 2209

General

Designation	22112 / 92059A
Launch date	10 Sep 1992
Country of origin	CIS
Mission	Military: early warning (Prognoz 2nd generation)
Geostationary orbit	24°W, inclined
Launch vehicle
Launch site	Tyuratam
End of life

Out of service	Oct 1996
Cause	?, drifting
Technical data

Specifications

Prime contractor	NPO Lavochkin
Platform
Mass at launch	2600 kg
Mass in orbit
Length
Width
Height
Stabilization
DC power
Design lifetime

S-band capacity


 Cosmos 2218

General

Designation	22207 / 92073A
Launch date	29 Oct 1992
Country of origin	CIS
Mission	Military: Navigation (Parus)
Perigee/Apogee	963/1013 km
Inclination	82.9°
Period	104.9 min
Launch vehicle	Cosmos C
Launch site
Technical data

Downlink frequency: 149.940 & 399.840 MHz

Plane 3


 Cosmos 2219

General

Designation	22219 / 92076A
Launch date	17 Nov 1992
Country of origin	CIS
Mission	Military: SIGINT (Tselina-2)
Perigee/Apogee	843/855 km
Inclination	71°
Period	101.9 min
Launch vehicle	Zenit


 Cosmos 2220

General

Designation	22226 / 92077A
Launch date	20 Nov 1992
Country of origin	CIS
Mission	Military
Perigee/Apogee	164/341 km
Inclination	67.2°
Period	89.6 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	18 Jan 1993


 Cosmos 2221

General

Designation	22236 / 92080A
Launch date	24 Nov 1992
Country of origin	CIS
Mission	Military: SIGINT (Tselina-D)
Perigee/Apogee	629/662 km
Inclination	82.5°
Period	97.6 min
Launch vehicle	Cyclone 3 #100


 Cosmos 2222

General

Designation	22238 / 92081A
Launch date	25 Nov 1992
Country of origin	CIS
Mission	Military: early warning (Oko)
Perigee/Apogee	1172/39195 km
Inclination	62.9°
Period	718.1 min
Launch vehicle	Molniya
Launch site	Plesetsk


 Cosmos 2223

General

Designation	22260 / 92087A
Launch date	9 Dec 1992
Country of origin	CIS
Mission	Reconnaissance (5th generation)
Perigee/Apogee	238/271 km
Inclination	64.6°
Period	89.6 min
Launch vehicle	Soyuz
Launch site	Tyuratam
End of life

Decay	16 Dec 1993


 Cosmos 2224

General

Designation	22269 / 92088A
Launch date	17 Dec 1992
Country of origin	CIS
Mission	Military: early warning (Prognoz 2nd generation)
Geostationary orbit	12°E, inclined
Launch vehicle
Launch site	Tyuratam
Mass at launch	2600 kg

Built by NPO Lavochkin. S-band capacity

End of life

Out of service	Jun 1999?
Cause	left its slot


 Cosmos 2230

General

Designation	22307 / 93001A
Launch date	12 Jan 1993
Country of origin	CIS
Mission	Navigation (Tsikada)
Perigee/Apogee	968/1005 km
Inclination	82.9°
Period	104.8 min
Launch vehicle	Cosmos C
Launch site	Plesetsk

Built by PO Polyot

Technical data

Downlink frequency: 150 & 400 MHz

Plane 11?


 Cosmos 2231

General

Designation	22317 / 93004A
Launch date	19 Jan 1993
Country of origin	CIS
Mission	Military: Reconnaissance
Perigee/Apogee	176/369 km
Inclination	67.1°
Period	89.6 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	25 mar 1993


 Cosmos 2232

General

Designation	22321 / 93006A
Launch date	26 Jan 1993
Country of origin	CIS
Mission	Military: Early Warning
Perigee/Apogee	786/39557 km
Inclination	62.9°
Period	717.6 min
Launch vehicle	Molniya
Launch site	Plesetsk

Built by NPO PM, operated by the Russian Air Defense Forces (Voyska PVO)


 Cosmos 2233

General

Designation	22487 / 93008A
Launch date	9 Feb 1993 at 02:50 UT
Country of origin	CIS
Mission	Military: Navigation (Parus)
Perigee/Apogee	949/1007 km
Inclination	82.9°
Period	104.7 min
Launch vehicle	Cosmos C
Launch site	Plesetsk
Technical data

Downlink frequency: 150.030 & 400.075 MHz

Plane 5


 Cosmos 2234

Also called Glonass 59

General

Designation	22512 / 93010A
Launch date	17 Feb 1993 at 20:30 UT
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19106/19152 km
Inclination	64.9°
Period	675.7 min
Launch vehicle	Proton #213
End of life

Out of service	yes


 Cosmos 2235

Also called Glonass 60 or Glonass 757

General

Designation	22513 / 93010B
Launch date	17 Feb 1993 at 20:30 UT
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19111/19147 km
Inclination	65°
Period	675.7 min
Launch vehicle	Proton #213
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel	5
Plane	1
Slot	2


 Cosmos 2236

Also called Glonass 61 or Glonass 759

General

Designation	22514 / 93010C
Launch date	17 Feb 1993 at 20:30 UT
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19093/19165 km
Inclination	65°
Period	675.7 min
Launch vehicle	Proton #213
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel	21
Plane	1
Slot	7


 Cosmos 2237

General

Designation	22565 / 93016A
Launch date	26 Mar 1993 at 02:25 UT
Country of origin	CIS
Mission	Military: SIGINT (Tselina-2)
Perigee/Apogee	846/852 km
Inclination	71.0°
Period	101.9 min
Launch vehicle	Zenit


 Cosmos 2238

General

Designation	22585 / 93018A
Launch date	30 Mar 1993 at 12:00 UT
Country of origin	CIS
Mission	Military: ocean reconnaissance (Eorsat)
Perigee/Apogee	127/143 km
Inclination	65.0°
Period	87.2 min
Launch vehicle	Cyclone 2
Launch site	Tyuratam
End of life

Decay	9 Dec 1994


 Cosmos 2239

General

Designation	22590 / 93020A
Launch date	1 Apr 1993 at 19:00 UT
Country of origin	CIS
Mission	Military: Navigation (Parus)
Perigee/Apogee	963/996 km
Inclination	82.9°
Period	104.7 min
Launch vehicle	Cosmos C
Launch site	Plesetsk
Technical data

Downlink frequency: 149.970 & 399.92 MHz

Plane 4


 Cosmos 2240

General

Designation	22592 / 93021A
Launch date	2 Apr 1993 at 14:10 UT
Country of origin	CIS
Mission	Military: Reconnaissance (Yantar; 4th generation)
Perigee/Apogee	196/342 km
Inclination	62.8°
Period	89.6 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	7 Jun 1993
4th generation Russian reconnaissance satellites (extracted from JSR)

It appears that, unlike all earlier Soviet imaging reconnaissance satellites, they do not use the 1959-vintage Vostok satellite bus, although they are probably still made by the same company, the TsSKB (Central Specialized Design Bureau), formerly a subdivision of NPO Energiya. They were introduced in 1975, and originally had a lifetime of 30 days which was a big improvement on the Vostok satellites, at that time limited to 15 day missions. Later minor improvements increased the lifetime, first to 44 days and then, in 1984, to 59 days. The two flights so far this year [1993] show a further improvement, lasting 65 and 66 days. This modest increase is nevertheless significant as the first sign of an upgrade to this satellite class in a decade. By my count [Jonathan McDowell speaking], Kosmos-2240 is the 107th in the series, although the classification of several flights is controversial.


 Cosmos 2241

General

Designation	22594 / 93022A
Launch date	6 Apr 1993 at 19:10 UT
Country of origin	CIS
Mission	Military: Early Warning
Perigee/Apogee	832/39520 km
Inclination	63.6°
Period	717.7 min
Launch vehicle	Molniya
Launch site	Plesetsk


 Cosmos 2242

General

Designation	22626 / 93024A
Launch date	16 Apr 1993 at 08:00 UT
Country of origin	CIS
Mission	Military: SIGINT (Tselina-D)
Perigee/Apogee	632/666 km
Inclination	82.5°
Period	97 min
Launch vehicle	Cyclone 3 #103


 Cosmos 2243

General

Designation	22641 / 93028A
Launch date	27 Apr 1993 at 12:30 UT
Country of origin	CIS
Mission	Military: Reconnaissance (Kometa; 4th generation)
Perigee/Apogee	180/220 km
Inclination	70.4°
Period	88 min
Launch vehicle	Soyuz
Launch site	Tyuratam
End of life

Cause	Exploded with the 3rd stage of the launcher
Decay	6 May 1993


 Cosmos 2244

General

Designation	22643 / 93029A
Launch date	28 Apr 1993 at 03:35 UT
Country of origin	CIS
Mission	Military: ocean reconnaissance (Eorsat)
Perigee/Apogee	401/417 km
Inclination	65°
Period	92.8 min
Launch vehicle	Cyclone 2
Launch site	Tyuratam


 Cosmos 2245

General

Designation	22646 / 93030A
Launch date	11 May 1993
Country of origin	CIS
Mission	Telecommunications (Strela-3)
Perigee/Apogee	1393/1415 km
Inclination	82.6°
Period	113.9 min
Launch vehicle	Cyclone 3 #104


 Cosmos 2246

General

Designation	22647 / 93030B
Launch date	11 May 1993
Country of origin	CIS
Mission	Telecommunications (Strela-3)
Perigee/Apogee	1397/1415 km
Inclination	82.6°
Period	113.9 min
Launch vehicle	Cyclone 3 #104


 Cosmos 2247

General

Designation	22648 / 93030C
Launch date	11 May 1993
Country of origin	CIS
Mission	Telecommunications (Strela-3)
Perigee/Apogee	1400/1415 km
Inclination	82.6°
Period	114.0 min
Launch vehicle	Cyclone 3 #104


 Cosmos 2248

General

Designation	22649 / 93030D
Launch date	11 May 1993
Country of origin	CIS
Mission	Telecommunications (Strela-3)
Perigee/Apogee	1398/1415 km
Inclination	82.6°
Period	113.9 min
Launch vehicle	Cyclone 3 #104


 Cosmos 2249

General

Designation	22650 / 93030E
Launch date	11 May 1993
Country of origin	CIS
Mission	Telecommunications (Strela-3)
Perigee/Apogee	1400/1415 km
Inclination	82.6°
Period	114.0 min
Launch vehicle	Cyclone 3 #104


 Cosmos 2250

General

Designation	22651 / 93030F
Launch date	11 May 1993
Country of origin	CIS
Mission	Telecommunications (Strela-3)
Perigee/Apogee	1400/1415 km
Inclination	82.6°
Period	114.0 min
Launch vehicle	Cyclone 3 #104


 Cosmos 2251

General

Designation	22675 / 93036A
Launch date	16 Jun 1993 at 04:17 UT
Country of origin	CIS
Mission	Telecommunications (Strela-1)
Perigee/Apogee	778/803 km
Inclination	74.0°
Period	100.7 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 2252

General

Designation	22687 / 93038A
Launch date	24 Jun 1994 at 04:12 UT
Country of origin	CIS
Mission	Telecommunications (Strela-3)
Perigee/Apogee	1400/1415 km
Inclination	82.6°
Period	114.0 min
Launch vehicle	Cyclone 3 #105


 Cosmos 2253

General

Designation	22688 / 93038B
Launch date	24 Jun 1994 at 04:12 UT
Country of origin	CIS
Mission	Telecommunications (Strela-3)
Perigee/Apogee	1405/1424 km
Inclination	82.6°
Period	114.1 min
Launch vehicle	Cyclone 3 #105


 Cosmos 2254

General

Designation	22689 / 93038C
Launch date	24 Jun 1994 at 04:12 UT
Country of origin	CIS
Mission	Telecommunications (Strela-3)
Perigee/Apogee	1390/1412 km
Inclination	82.6°
Period	113.8 min
Launch vehicle	Cyclone 3 #105


 Cosmos 2255

General

Designation	22690 / 93038D
Launch date	24 Jun 1994 at 04:12 UT
Country of origin	CIS
Mission	Telecommunications (Strela-3)
Perigee/Apogee	1401/1413 km
Inclination	82.6°
Period	113.9 min
Launch vehicle	Cyclone 3 #105


 Cosmos 2256

General

Designation	22691 / 93038E
Launch date	24 Jun 1994 at 04:12 UT
Country of origin	CIS
Mission	Telecommunications (Strela-3)
Perigee/Apogee	1397/1412 km
Inclination	82.6°
Period	113.9 min
Launch vehicle	Cyclone 3 #105


 Cosmos 2257

General

Designation	22692 / 93038F
Launch date	24 Jun 1994 at 04:12 UT
Country of origin	CIS
Mission	Telecommunications (Strela-3)
Perigee/Apogee	1404/1419 km
Inclination	82.6°
Period	114.0 min
Launch vehicle	Cyclone 3 #105


 Cosmos 2258

General

Designation	93044A / 22709
Launch date	8 Jul 1993 at 07:15 UT
Country of origin	CIS
Mission	Military: ocean reconnaissance (Eorsat)
Perigee/Apogee	400/417 km
Inclination	65°
Period	92.8 min
Launch vehicle	Cyclone 2
Launch site	Tyuratam
End of life

Decay	8 Jun 1995


 Cosmos 2259

General

Designation	22716 / 93045A
Launch date	14 Jul 1993 at 16:40 UT
Country of origin	CIS
Mission	Military: Reconnaissance (Yantar; 4th generation)
Perigee/Apogee	168/349 km
Inclination	67.1°
Period	89.7 min
Launch vehicle	Soyuz
Launch site	Plesetsk

It reentered after only 11 days in space. It was expected to stay up for two months.

End of life

Landed	25 Jul 1993


 Cosmos 2260

General

Designation	22721 / 93047A
Launch date	22 Jul 1993 at 08:56 UT
Country of origin	CIS
Mission	Military: Remote Sensing (Resurs T)
Perigee/Apogee	177/224 km
Inclination	82.3°
Period	88.5 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Landed	5 Aug 1993


 Cosmos 2261

General

Designation	22741 / 93051A
Launch date	10 Aug 1993 at 15:00 UT
Country of origin	CIS
Mission	Military: Early Warning (Oko)
Perigee/Apogee	690/39674 km
Inclination	63°
Period	718 min
Launch vehicle	Molniya
Launch site	Plesetsk

built by NPO Lavochkin


 Cosmos 2262

General

Designation	22789 / 93057A
Launch date	7 Sep 1993 at 13:30 UT
Country of origin	CIS
Mission	Military: Reconnaissance (6th generation)
Perigee/Apogee	207/323 km
Inclination	65°
Period	89 min
Launch vehicle	Soyuz
Launch site	Tyuratam

Fifth in a new series of imaging satellites which fly two-month long missions. Previous satellites were 2031, 2101, 2163, and 2225.


 Cosmos 2263

General

Designation	22802 / 93059A
Launch date	16 Sep 1993 at 07:36 UT
Country of origin	CIS
Mission	Military: SIGINT (Tselina-2)
Perigee/Apogee	848/854 km
Inclination	71°
Period	102 min
Launch vehicle	Zenit

The program had three consecutive launch failures in 1990-1992, but the last 4 launches have been successful.


 Cosmos 2264

General

Designation	22808 / 93060A
Launch date	17 Sep 1993
Country of origin	CIS
Mission	Military: ocean reconnaissance (Eorsat)
Perigee/Apogee	402/418 km
Inclination	65°
Period	92.8 min
Launch vehicle	Cyclone 2
Launch site	Tyuratam LC90

It carries a low thrust engine to maintain precise separation with other EORSATs and uses radio interferometry to locate transmissions from ships.


 Cosmos 2265

General

Designation	22875 / 93067A
Launch date	26 Oct 1993 at 10:00 UT
Country of origin	CIS
Mission	Military: calibration
Perigee/Apogee	291/1573 km
Inclination	83°
Period	103.5 min
Launch vehicle	Cosmos C
Launch site	Plesetsk LC132


 Cosmos 2266

General

Designation	22888 / 93070A
Launch date	2 Nov 1993 at 12:10 UT
Country of origin	CIS
Mission	Military: Navigation (Parus)
Perigee/Apogee	945/1017 km
Inclination	83°
Period	104 min
Launch vehicle	Cosmos
Launch site	Plesetsk LC132
End of life

Out of service	yes
Technical data

Downlink frequency: 149.97 & 399.92 MHz

Plane 1


 Cosmos 2267

General

Designation	22904 / 93071A
Launch date	5 Nov 1993 at 08:25 UT
Country of origin	CIS
Mission	Military: Reconnaissance (advanced Yantar'; 5th generation)
Perigee/Apogee	241/282 km
Inclination	70.4°
Period	89 min
Launch vehicle	Soyuz
Launch site	Tyuratam LC1


 Cosmos 2268

General

Designation	22999 / 94011A
Launch date	12 Feb 1994 at 08:54 UT
Country of origin	CIS
Mission	Telecommunications (Strela-3)
Perigee/Apogee	1411/1426 km
Inclination	82.57°
Period	114.2 min
Launch vehicle	Cyclone 3 #108


 Cosmos 2269

General

Designation	23000 / 94011B
Launch date	12 Feb 1994 at 08:54 UT
Country of origin	CIS
Mission	Telecommunications (Strela-3)
Perigee/Apogee	1410/1421 km
Inclination	82.56°
Period	114.2 min
Launch vehicle	Cyclone 3 #108


 Cosmos 2270

General

Designation	23001 / 94011C
Launch date	12 Feb 1994 at 08:54 UT
Country of origin	CIS
Mission	Telecommunications (Strela-3)
Perigee/Apogee	1406/1417 km
Inclination	82.57°
Period	114.05 min
Launch vehicle	Cyclone 3 #108


 Cosmos 2271

General

Designation	23002 / 94011D
Launch date	12 Feb 1994 at 08:54 UT
Country of origin	CIS
Mission	Telecommunications (Strela-3)
Perigee/Apogee	1403/1415 km
Inclination	82.57°
Period	114 min
Launch vehicle	Cyclone 3 #108


 Cosmos 2272

General

Designation	23003 / 94011E
Launch date	12 Feb 1994 at 08:54 UT
Country of origin	CIS
Mission	Telecommunications (Strela-3)
Perigee/Apogee	1396/1415 km
Inclination	82.57°
Period	113.9 min
Launch vehicle	Cyclone 3 #108


 Cosmos 2273

General

Designation	23004 / 94011F
Launch date	12 Feb 1994 at 08:54 UT
Country of origin	CIS
Mission	Telecommunications (Strela-3)
Perigee/Apogee	1408/1416 km
Inclination	82.57°
Period	113.9 min
Launch vehicle	Cyclone 3 #108


 Cosmos 2274

General

Designation	23033 / 94018A
Launch date	17 Mar 1994 at 16:30 UT
Country of origin	CIS
Mission	Military: reconnaissance (Yantar'; 4th generation)
Perigee/Apogee	176.1/371.7 km
Inclination	67.15°
Period	89.65 min
Launch vehicle	Soyuz
Launch site	Plesetsk LC43
End of life

Cause	Landed in Kazakhstan
Decay	21 May 1994


 Cosmos 2275

Also called Glonass 62 or Glonass 760

General

Designation	23043 / 94021A
Launch date	11 Apr 1994 at 08:49 UT
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19120/19197 km
Inclination	64°
Period	676 min
Launch vehicle	Proton #222
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel	24
Plane	3
Slot	17


 Cosmos 2276

Also called Glonass 63 or Glonass 761

General

Designation	23044 / 94021B
Launch date	11 Apr 1994 at 08:49 UT
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19120/19197 km
Inclination	64°
Period	676 min
Launch vehicle	Proton #222
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel	3
Plane	3
Slot	23


 Cosmos 2277

Also called Glonass 64 or Glonass 758

General

Designation	23045 / 94021C
Launch date	11 Apr 1994 at 08:49 UT
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19120/19197 km
Inclination	64°
Period	676 min
Launch vehicle	Proton #222
End of life

Out of service	28 Jul 1995
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel	10
Plane	3
Slot	18


 Cosmos 2278

General

Designation	23087 / 94023A
Launch date	23 Apr 1994 at 08:02 UT
Country of origin	CIS
Mission	Military: SIGINT (Tselina-2)
Perigee/Apogee	854/858 km
Inclination	71°
Period	102 min
Launch vehicle	Zenit


 Cosmos 2279

General

Designation	23092 / 94024A
Launch date	26 Apr 1994 at 02:14 UT
Country of origin	CIS
Mission	Military: Navigation (Parus)
Perigee/Apogee	955/1007 km
Inclination	83°
Period	104.7 min
Launch vehicle	Cosmos C
Launch site	Plesetsk LC133
Technical data

Donwlink frequencies: 149.940 & 399.840 MHz

Plane 6


 Cosmos 2280

General

Designation	23095 / 94025A
Launch date	28 Apr 1994
Country of origin	CIS
Mission	Military: reconnaissance (advanced Yantar'; 5th generation)
Perigee/Apogee	244/305 km
Inclination	70.3°
Period	90 min
Launch vehicle	Soyuz
Launch site	Tyuratam LC31
End of life

Decay	22 Mar 1995


 Cosmos 2281

General

Designation	23119 / 94032A
Launch date	7 Jun 1994 at 07:20 UT
Country of origin	CIS
Mission	Military: reconnaissance (Vostok/Zenit or Oblik; 4th generation)
Perigee/Apogee	192/265 km
Inclination	82.6°
Period	88.7 min
Launch vehicle	Soyuz
Launch site	Plesetsk

The number 2281 had earlier been assigned to an identical spacecraft that was launched on May 26 but failed to attain orbit.

This flight could be similar to Cosmos 2207 in 1992. The first Vostok based spy satellites were the Zenit 2 series. The first one to reach orbit, in 1962, was given the code name Cosmos 0004. The Zenit derived spy satellites have now been almost entirely phased out in favour of a newer bus called Yantar'.

End of life

Decay	29 Jun 1994


 Cosmos 2282

General

Designation	23168 / 94038A
Launch date	6 Jul 1994 at 23:59 UT
Country of origin	CIS
Mission	Military: early warning (Prognoz 2nd generation)
Geostationary orbit	24°W, inclined
Launch vehicle	Proton #224
Mass at launch	2600 kg
End of life

Out of service	Dec 1995?
Technical data

Built by NPO Lavochkin

Equipped with a 500 kg 1 m diameter telescope


 Cosmos 2283

General

Designation	23182 / 94042A
Launch date	20 Jul 1994
Country of origin	CIS
Mission	Military: reconnaissance (Yantar'; 4th generation)
Perigee/Apogee	179/356 km
Inclination	67.1°
Period	89.5 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	29 Sep 1994


 Cosmos 2284

General

Designation	23187 / 94044A
Launch date	29 Jul 1994 at 09:29 UT
Country of origin	CIS
Mission	Military: reconnaissance (Kometa; 4th generation)
Perigee/Apogee	206/296 km
Inclination	70.4°
Period	89.2 min
Launch vehicle	Soyuz
Launch site	Tyuratam LC31

It is presumably the 17th in the 'Kometa' series of topographic mapping satellites, based on the Yantar' spy satellite design. Kometa satellite imagery would be commercially distributed by AO Sovinformsputnik.

The last Kometa satellite, Kosmos-2243, was damaged during launch in Apr 1993. Typical mission length is 44 days. The first Kometa satellite was Kosmos-1246, in 1981. All the Kometa satellites are launched by Soyuz-U from Baykonur.

End of life

Decay	11 Sep 1994


 Cosmos 2285

General

Designation	23189 / 94045A
Launch date	2 Aug 1994 at 20:00 UT
Country of origin	CIS
Mission	Military: remote sensing (Obzor 1)
Perigee/Apogee	974/1013 km
Inclination	74°
Period	105 min
Launch vehicle	Cosmos C
Launch site	Plesetsk LC132


 Cosmos 2286

General

Designation	23194 / 94048A
Launch date	5 Aug 1994 at 01:12 UT
Country of origin	CIS
Mission	Military: early warning (Oko, means "eye")
Perigee/Apogee	747/39608 km
Inclination	63.4°
Period	718 min
Launch vehicle	Molniya
Launch site	Plesetsk

It carries a large telescope to detect ballistic missile launches.


 Cosmos 2287

Also called Glonass 65 or Glonass 767

General

Designation	23203 / 94050A
Launch date	11 Aug 1994 at 15:27 UT
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19109/19150 km
Inclination	64°
Period	676 min
Launch vehicle	Proton #225
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel	22
Plane	2
Slot	12


 Cosmos 2288

Also called Glonass 66 or Glonass 770

General

Designation	23204 / 94050B
Launch date	11 Aug 1994
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19091/19168 km
Inclination	64°
Period	676 min
Launch vehicle	Proton #225
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel	9
Plane	2
Slot	14


 Cosmos 2289

Also called Glonass 67 or Glonass 775

General

Designation	23205 94050C
Launch date	11 Aug 1994
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19126/19133 km
Inclination	64°
Period	676 min
Launch vehicle	Proton #225
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel	22
Plane	2
Slot	16


 Cosmos 2290

General

Designation	23218 / 94053A
Launch date	26 Aug 1994 at 12:00 UT
Country of origin	CIS
Mission	Military: reconnaissance (Kuban; 7th generation)
Perigee/Apogee	211/292 km
Inclination	64.8°
Period	90.2 min
Launch vehicle	Zenit

This is a 7th generation "Kuban" reconnaissance satellite. Five such satellites had been launched in 1986 and 1987. Built by the TsSKB in Samara, they were prototypes of a new spacecraft generation. Civilian applications are knowned as Nika-T (microgravity), Nika-B (medical/biology) and Nika-E (high energy particles). Are supposed to weigh 9 tons and stay in orbit 90 to 120 days. The payload which takes place in a 4.3 m3 capsule weighs 1.2 t.

This specific satellite could be a digital imaging satellite. A commercial version should be available in September 1996; it should be equipped with a 2 m resolution imager.

In late March 1995 (between Mar 24 and 29) the spacecraft raised its apogee by 200 km, from an orbit of 181 x 382 km x 64.8° to 181 x 571 km x 64.8°, and four new small objects were tracked in the post-maneuver orbit. It seems likely that this marks the end of the Kosmos-2290 mission. Russian spy satellites are usually deorbited at the end of their mission, and it is not clear whether the orbit raise of Kosmos-2290 reflects a new operational regime, a new disposal strategy, a deorbit burn that went in the wrong direction, or (less likely) a tracking by US Space Command of a residual part of the spacecraft following recovery of a reentry vehicle.

End of life

Decay	4 Apr 1995


 Cosmos 2291

General

Designation	23267 / 94060A
Launch date	21 Sep 1994 at 17:53 UT
Country of origin	CIS
Mission	Military: telecommunications: Geizer
Geostationary orbit	see below
Launch vehicle	Proton #226
Location

Begin	End	Position
L: 21 Sep 1994	late-Sep 1995	80°W
Nov 1995		13.5°W
Technical data

Specifications


 Cosmos 2292

General

Designation	23278 / 94061A
Launch date	27 Sep 1994 at 14:00 UT
Country of origin	CIS
Mission	Military: calibration (vektor?)
Perigee/Apogee	400/1951 km
Inclination	82.9°
Period	108.9 min
Launch vehicle	Cosmos C
Launch site	Plesetsk LC132


 Cosmos 2293

General

Designation	23336 / 94072A
Launch date	2 Nov 1994 at 01:04  UT
Country of origin	CIS
Mission	Military: ocean reconnaissance (Eorsat)
Perigee/Apogee	402/418 km
Inclination	65°
Period	92.8 min
Launch vehicle	Cyclone 2
Launch site	Tyuratam

Replaced Cosmos 2238

End of life

Decay	13 May 1996


 Cosmos 2294

Also called Glonass 68 or Glonass 763

General

Designation	23396 / 94076A
Launch date	20 Nov 1994 at 00:09 UT
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19052/19207 km
Inclination	64.9°
Period	675 min
Launch vehicle	Proton #229
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel	21
Plane	1
Slot	3


 Cosmos 2295

Also called Glonass 69 or Glonass 764

General

Designation	23397 / 94076B
Launch date	20 Nov 1994 at 00:09 UT
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19052/19207 km
Inclination	64.9°
Period	675 min
Launch vehicle	Proton #229
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel	13
Plane	1
Slot	6


 Cosmos 2296

Also called Glonass 70 or Glonass 762

General

Designation	23398 / 94076C
Launch date	20 Nov 1994 at 00:09 UT
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19118/19114 km
Inclination	65°
Period	675 min
Launch vehicle	Proton #229
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel	12
Plane	1
Slot	4


 Cosmos 2297

General

Designation	23404 / 94077A
Launch date	24 Nov 1994 at 09:16 UT
Country of origin	CIS
Mission	Military: SIGINT (Tselina-2)
Perigee/Apogee	845/857 km
Inclination	71°
Period	102 min
Launch vehicle	Zenit

The satellite carries an array of electronic intelligence detectors to monitor radio emissions.


 Cosmos 2298

General

Designation	23431 / 94083A
Launch date	20 Dec 1994 at 05:11 UT
Country of origin	CIS
Mission	Telecommunications (Strela-1)
Perigee/Apogee	785/810 km
Inclination	74°
Period	100.8 min
Launch vehicle	Cosmos C
Launch site	Plesetsk LC132


 Cosmos 2299

General

Designation	23441 / 94086A
Launch date	26 Dec 1994 at 22:27 UT
Country of origin	CIS
Mission	Telecommunications (Strela-3)
Perigee/Apogee	1402/1415 km
Inclination	82.6°
Period	114 min
Launch vehicle	Cyclone 3 #113


 Cosmos 2300

General

Designation	23442 / 94086B
Launch date	26 Dec 1994 at 22:27 UT
Country of origin	CIS
Mission	Telecommunications (Strela-3)
Perigee/Apogee	1410/1414 km
Inclination	82.5°
Period	114 min
Launch vehicle	Cyclone 3 #113


 Cosmos 2301

General

Designation	23443 / 94086C
Launch date	26 Dec 1994 at 22:27 UT
Country of origin	CIS
Mission	Telecommunications (Strela-3)
Perigee/Apogee	1410/1414 km
Inclination	82.5°
Period	114 min
Launch vehicle	Cyclone 3 #113


 Cosmos 2302

General

Designation	23444 / 94086D
Launch date	26 Dec 1994 at 22:27 UT
Country of origin	CIS
Mission	Telecommunications (Strela-3)
Perigee/Apogee	1413/1423 km
Inclination	82.6°
Period	114.2 min
Launch vehicle	Cyclone 3 #113


 Cosmos 2303

General

Designation	23445 / 94086E
Launch date	26 Dec 1994 at 22:27 UT
Country of origin	CIS
Mission	Telecommunications (Strela-3)
Perigee/Apogee	1413/1430 km
Inclination	82.6°
Period	114.3 min
Launch vehicle	Cyclone 3 #113


 Cosmos 2304

General

Designation	23446 / 94086F
Launch date	26 Dec 1994 at 22:27 UT
Country of origin	CIS
Mission	Telecommunications (Strela-3)
Perigee/Apogee	1412/1417 km
Inclination	82.6°
Period	114.1 min
Launch vehicle	Cyclone 3 #113


 Cosmos 2305

General

Designation	23453 / 94088A
Launch date	29 Dec 1994 at 11:31 UT
Country of origin	CIS
Mission	Military: reconnaissance (advanced Yantar'; 5th generation)
Perigee/Apogee	231/288 km
Inclination	64.9°
Period	89.7 min
Launch vehicle	Soyuz
Launch site	Tyuratam LC31

This spacecraft raises its orbit periodically

End of life

Cause	deorbit
Decay	18 Dec 1995


 Cosmos 2306

General

Designation	23501 / 95008A
Launch date	2 Mar 1995 at 13:00 UT
Country of origin	CIS
Mission	Military: calibration (cosmos 816 type)
Perigee/Apogee	469/516 km
Inclination	65.8°
Period	94.5 min
Launch vehicle	Cosmos C
Launch site	Plesetsk

Releases a series of small objects at intervals, to act as calibration targets for the radars.


 Cosmos 2307

Also called Glonass 71 or Glonass 765

General

Designation	23511 / 95009A
Launch date	7 Mar 1995 at 09:23 UT
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19132 km
Inclination	64°
Period	279 min
Launch vehicle	Proton #232
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel	1
Plane	3
Slot	20


 Cosmos 2308

Also called Glonass 72 or Glonass 766

General

Designation	23512 / 95009B
Launch date	7 Mar 1995 at 09:23 UT
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19132 km
Inclination	64°
Period	279 min
Launch vehicle	Proton #232
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel	10
Plane	3
Slot	22


 Cosmos 2309

Also called Glonass 73 or Glonass 777

General

Designation	23513 / 95009C
Launch date	7 Mar 1995 at 09:23 UT
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19132 km
Inclination	64°
Period	279 min
Launch vehicle	Proton #232
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel	3
Plane	3
Slot	19


 Cosmos 2310

General

Designation	23526 / 95012A
Launch date	22 Mar 1995 at 04:05 UT
Country of origin	CIS
Mission	Military: Navigation (Parus)
Perigee/Apogee	980/1010 km
Inclination	82.9°
Period	105 min
Launch vehicle	Cosmos C
Launch site	Plesetsk
Technical data

Downlink frequencies: 149.910 & 399.760 MHz

Plane 2


 Cosmos 2311

General

Designation	23530 / 95014A
Launch date	22 Mar 1995 at 16:45 UT
Country of origin	CIS
Mission	Military: reconnaissance (Yantar')
Perigee/Apogee	169/334 km
Inclination	67.1°
Period	89.54 min
Launch vehicle	Soyuz
Launch site	Plesetsk

Design lifetime: 2 months

End of life

Decay	31 May 1995


 Cosmos 2312

General

Designation	23584 / 95026A
Launch date	24 May 1995 at 20:10 UT
Country of origin	CIS
Mission	Military: early warning (Oko)
Perigee/Apogee	614/40166 km
Inclination	62.8°
Period	709 min
Launch vehicle	Molniya
Launch site	Plesetsk

Other birds of this program are: 2063, 2097, 2176, 2217, 2222, 2232, 2241, 2261, 2286

Technical data

Specifications

Prime contractor	NPO Lavotchkin
Platform
Mass at launch	2300 kg
Mass in orbit
Length
Width
Height
Stabilization
DC power	2800 W
Design lifetime	5 years?

Equipped with an infrared telescope


 Cosmos 2313

General

Designation	23596 / 95028A
Launch date	8 Jun 1995 at 04:30 UT
Country of origin	CIS
Mission	Military: ocean reconnaissance (Eorsat)
Perigee/Apogee	403/415 km
Inclination	65°
Period	92.7 min
Launch vehicle	Cyclone 2
Launch site	Tyuratam

Replaced Cosmos 2258


 Cosmos 2314

General

Designation	23601 / 95031A
Launch date	28 Jun 1995 at 18:30 UT
Country of origin	CIS
Mission	Military: reconnaissance (Yantar')
Perigee/Apogee	166/339 km
Inclination	67.1°
Period	89.6 min
Launch vehicle	Soyuz
Launch site	Plesetsk

Built by TsSKB (Central Specialized Design Bureau) of Samara, Russia and will obtain images for the Russian GRU intelligence agency. Has the ability to raise its orbit.

End of life

Decay	6 Sep 1995


 Cosmos 2315

General

Designation	23603 / 95032A
Launch date	5 Jul 1995 at 03:10 UT
Country of origin	CIS
Mission	Navigation (Kurs)
Perigee/Apogee	988/1027 km
Inclination	82.9°
Period	105 min
Launch vehicle	Cosmos C
Launch site	Plesetsk LC132 pad 1

Part of a new series: the Kurs system enables maritime traffic control and messages to individual vessels.

Technical data

Downlink frequencies: 150 & 400 MHz

Plane 11


 Cosmos 2316

Also called Glonass 74 or Glonass 780

General

Designation	23620 / 95037A
Launch date	24 Jul 1995 at 15:52 UT
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19101/19134 km
Inclination	64.8°
Period	675 min
Launch vehicle	Proton #234
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel	4
Plane	2
Slot	15


 Cosmos 2317

Also called Glonass 75 or Glonass 781

General

Designation	23621 / 95037B
Launch date	24 Jul 1995 at 15:52 UT
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19101/19134 km
Inclination	64.8°
Period	675 min
Launch vehicle	Proton #234
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel	9
Plane	2
Slot	10


 Cosmos 2318

Also called Glonass 76 or Glonass 785

General

Designation	23622 / 95037C
Launch date	24 Jul 1995 at 15:52 UT
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19101/19134 km
Inclination	64.8°
Period	675 min
Launch vehicle	Proton #234
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel	4
Plane	2
Slot	11


 Cosmos 2319

General

Designation	23653 / 95045A
Launch date	30 Aug 1995 at 19:33 UT
Country of origin	CIS
Mission	Military: Telecommunications: Geizer
Geostationary orbit	80°E
Launch vehicle	Proton #235
Technical data

Specifications


 Cosmos 2320

General

Designation	23674 / 95051A
Launch date	29 Sep 1995 at 04:25 UT
Country of origin	CIS
Mission	Military: reconnaissance (advanced Yantar'; 5th generation)
Perigee/Apogee	189/304 km
Inclination	64.9°
Period	89 min
Launch vehicle	Soyuz
Launch site	Tyuratam LC31
End of life

Out of service	28 Sep 1996
Cause	deorbited
Decay


 Cosmos 2321

General

Designation	23676 / 95052A
Launch date	6 Oct 1995 at 03:23 UT
Country of origin	CIS
Mission	Military: Navigation (Parus)
Perigee/Apogee	257/790 km
Inclination	82.9°
Period	95.1 min
Launch vehicle	Cosmos C
Launch site	Plesetsk LC132

The second stage of the launcher malfunctioned; thus the satellite couldn't reach the intended 960 km x 1010 km x 83° orbit.

End of life

Out of service	6 Oct 1995
Decay	21 Aug 1997


 Cosmos 2322

General

Designation	23704 / 95058A
Launch date	31 Oct 1995 at 20:19 UT
Country of origin	CIS
Mission	Military: SIGINT (Tselina-2)
Perigee/Apogee	849/852 km
Inclination	71°
Period	101.9 min
Launch vehicle	Zenit

The booster is said to reduce air pollution to a minimum... The Zenit rocket produced by Ukraine is fuelled by a mixture of liquid oxygen and kerosene. Zenit was fired 14 times since 1987 with 3 failures.


 Cosmos 2323

Also called Glonass 776

General

Designation	23734 / 95068A
Launch date	14 Dec 1995 at 06:10 UT
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19114/19141 km
Inclination	64.8°
Period	675 min
Launch vehicle	Proton #238
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel	6
Plane	2
Slot	9


 Cosmos 2324

Also called Glonass 778

General

Designation	23735 / 95068B
Launch date	14 Dec 1995 at 06:10 UT
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19117/19139 km
Inclination	64.8°
Period	675 min
Launch vehicle	Proton #238
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel
Plane	2
Slot	spare


 Cosmos 2325

Also called Glonass 782

General

Designation	23736 / 95068C
Launch date	14 Dec 1995 at 06:10 UT
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19109/19148 km
Inclination	64.8°
Period	675 min
Launch vehicle	Proton #238
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel	6
Plane	2
Slot	13


 Cosmos 2326

General

Designation	23748 / 95071A
Launch date	20 Dec 1995 at 00:52 UT
Country of origin	CIS
Mission	Military: ocean reconnaissance (Eorsat)
Perigee/Apogee
Inclination
Period
Launch vehicle	Cyclone 2
Launch site	Tyuratam LC90

It  also carries 'Konus-A', a secondary science payload made in the A.F.Ioffe Physics and Technology Institute in St.Petersburg.

End of life

Out of service
Cause
Decay	8 Nov 1997


 Cosmos 2327

General

Designation	23773 / 96004A
Launch date	16 Jan 1996 at 15:34 UT
Country of origin	CIS
Mission	Military: Navigation (Parus)
Perigee/Apogee	974/1033 km
Inclination	83°
Period	105 min
Launch vehicle	Cosmos C
Launch site	Plesetsk LC132
End of life

Out of service
Cause	failed
Decay
Technical data

Downlink frequencies: 149.970 & 399.920 MHz

Plane 1


 Cosmos 2328

General

Designation	23790 / 96009D
Launch date	19 Feb 1996
Country of origin	CIS
Mission	Telecommunications (Strela-3)
Perigee/Apogee	~1400 km
Inclination	~82°
Period
Launch vehicle	Cyclone 3 #115

This is the 3000th Russian satellite


 Cosmos 2329

General

Designation	23791 / 96009E
Launch date	19 Feb 1996
Country of origin	CIS
Mission	Telecommunications (Strela-3)
Perigee/Apogee	~1400 km
Inclination	~82°
Period
Launch vehicle	Cyclone 3 #115


 Cosmos 2330

General

Designation	23792 / 96009F
Launch date	19 Feb 1996
Country of origin	CIS
Mission	Telecommunications (Strela-3)
Perigee/Apogee	~1400 km
Inclination	~82°
Period
Launch vehicle	Cyclone 3 #115


 Cosmos 2331

General

Designation	23818 / 96016A
Launch date	14 Mar 1996 at 17:45 UT
Country of origin	CIS
Mission	Military: reconnaissance (Yantar')
Perigee/Apogee	164/355 km
Inclination	67.1°
Period
Launch vehicle	Soyuz
Launch site	Plesetsk

This Russian Defense Ministry payload carries a US DoD secondary experiment launched as part of the Space Test Program (STP), the BINRAD package which will attempt to detect the presence of beryllium at orbital altitudes. BINRAD was flown twice before on Russian civilian Resurs F remote sensing missions.


 Cosmos 2332

General

Designation	23853 / 96025A
Launch date	24 Apr 1996 at 13:03 UT
Country of origin	CIS
Mission	Military: calibration
Perigee/Apogee	303/1575 km
Inclination	83°
Period
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 2333 failure

General

Designation	n/a
Launch date	14 May 1996
Country of origin	CIS
Mission	Military: reconnaissance (Kometa; 4th generation)
Launch vehicle	Soyuz U
Launch site	Tyuratam

The rocket was lost 2 minutes after launch during the burn of the first stage.

The SPIN-2 payload was onboard (US mapping project)  During 45 days in low orbit this satelite would have taken photos of 1.2 million square miles of the Earth's surface for American companies.  In particular, the satellite was to have taken high-resolution photographs (2 m) of the United States to fulfill a contract signed last summer by Russia's Sovinformsputnik and the U.S. Aerial Images company.

The insurer for the satellite payed $2.7 million  The experts revealed that the boosters had production errors (on the nose cones and with low quality of the latches). The report said the nose cones split apart and disintegrated during launch.

External resources

http://www.spin-2.com/


 Cosmos 2333

General

Designation	24297 / 96051A
Launch date	4 Sep 1996 at 09:01 UT
Country of origin	CIS
Mission	Military: SIGINT (Tselina-2)
Perigee/Apogee	848/852 km
Inclination	71°
Period	101.9 min
Launch vehicle	Zenit


 Cosmos 2334

General

Designation	24304 / 96052A
Launch date	5 Sep 1996 at 12:47 UT
Country of origin	CIS
Mission	Military: Navigation (Parus)
Perigee/Apogee	968/1009 km
Inclination	82.9°
Period	104.8 min
Launch vehicle	Cosmos C
Launch site	Plesetsk LC132/1

Plane 5


 Cosmos 2335

General

Designation	24670 / 96069A
Launch date	11 Dec 1996 at 12:00 UT
Country of origin	CIS
Mission	Military: ocean reconnaissance (Eorsat)
Perigee/Apogee	403/417 km
Inclination	65.4°
Period	92.7 min
Launch vehicle	Cyclone 2
Launch site	Tyuratam LC90


 Cosmos 2336

General

Designation	24677 / 96071A
Launch date	20 Dec 1996 at 06:44 UT
Country of origin	CIS
Mission	Military: Navigation (Parus)
Perigee/Apogee	979/1012 km
Inclination	82.9°
Period	105 min
Launch vehicle	Cosmos C
Launch site	Plesetsk

Plane 4


 Cosmos 2337

General

Designation	24725 / 97006A
Launch date	14 Feb 1997
Country of origin	CIS
Mission	Telecommunications (Strela-3)
Perigee/Apogee	~1400 km
Inclination	~82°
Period
Launch vehicle	Cyclone 3 #116


 Cosmos 2338

General

Designation	24726 / 97006B
Launch date	14 Feb 1997
Country of origin	CIS
Mission	Telecommunications (Strela-3)
Perigee/Apogee	~1400 km
Inclination	~82°
Period
Launch vehicle	Cyclone 3 #116


 Cosmos 2339

General

Designation	24727 / 97006C
Launch date	14 Feb 1997
Country of origin	CIS
Mission	Telecommunications (Strela-3)
Perigee/Apogee	~1400 km
Inclination	~82°
Period
Launch vehicle	Cyclone 3 #116


 Cosmos 2340

General

Designation	24761 / 97015A
Launch date	9 Apr 1997
Country of origin	CIS
Mission	Military: early warning (Oko)
Perigee/Apogee	527/39367 km
Inclination	62.9°
Period	708 min
Launch vehicle	Molniya
Launch site	Plesetsk

Previous bird of this program: 2312


 Cosmos 2341

General

Designation	24772 / 97017A
Launch date	17 Apr 1997
Country of origin	CIS
Mission	Military: Navigation (Parus)
Perigee/Apogee	977/1014 km
Inclination	82.9°
Period	105 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Cosmos 2342

General

Designation	24800 / 97022A
Launch date	14 May 1997
Country of origin	CIS
Mission	Military: early warning (Oko)
Perigee/Apogee	514/39377 km
Inclination	62.8°
Period	708 min
Launch vehicle	Molniya
Launch site	Plesetsk

Previous bird of this program: 2340


 Cosmos 2343

General

Designation	24805 / 97024A
Launch date	15 May 1997
Country of origin	CIS
Mission	Military: reconnaissance (Kuban?; 7th generation)
Perigee/Apogee	216/338 km
Inclination	64.9°
Period	90 min
Launch vehicle	Soyuz

It was 1495th success space launch of a launcher based on the R-7 ICBM, 666th launch of Soyuz-U in total score, 250th launch of Soyuz-U from Baykonur and 350th launch in total score (including space launchers and ICBMs) from LC31 of Baykonur.

The satellite caused a great deal of controversy when in burned into the atmosphere on 23 Sep 1997 from the Western Isles to the north of England (UK).

End of life

Out of service	18 Sep 1997
Cause	deorbited and destroyed intentionally
Decay	23 Sep 1997


 Cosmos 2344

General

Designation	24827 / 97028A
Launch date	6 Jun 1997
Country of origin	CIS
Mission	Military: reconnaissance (8th generation, called Arkon)
Perigee/Apogee	1509/2747 km
Inclination	63.4°
Period	130.1 min
Launch vehicle	Proton #248
Technical data

Specifications

Prime contractor
Platform
Mass at launch	6 tons?
Mass in orbit
Dimension	2.3 m diameter x 7 m long
Solar array
Stabilization
DC power
Design lifetime


 Cosmos 2345

General

Designation	24894 / 97041A
Launch date	14 Aug 1997
Country of origin	CIS
Mission	Military: early warning (Prognoz 2nd generation)
Geostationary orbit	see below
Launch vehicle	Proton #250
Location

Begin	End	Position
L: 14 Aug 1997	Feb 1999	24°W
		drifting East
Technical data

Built by NPO Lavochkin


 Cosmos 2346

General

Designation	24953 / 97052A
Launch date	23 Sep 1997 at 16:44 UT
Country of origin	CIS
Mission	Military: Navigation (Parus)
Perigee/Apogee	968/1009 km
Inclination	82.9°
Period	104.8 min
Launch vehicle	Cosmos C
Launch site	Plesetsk

810 kg, built by NPO PM

Plane 1


 Cosmos 2347

General

Designation	25088 / 97079A
Launch date	9 Dec 1997 at 7:17 UT
Country of origin	CIS
Mission	Military: ocean reconnaissance (Eorsat)
Perigee/Apogee	410 km
Inclination	65°
Period
Launch vehicle	Cyclone 2
Launch site	Tyuratam LC90

Said to weigh 3150 kg


 Cosmos 2348

General

Designation	25095 / 97080A
Launch date	15 Dec 1997 at 15:40 UT
Country of origin	CIS
Mission	Military: reconnaissance (Yantar' 3/4, also called Kobalt)
Perigee/Apogee	176/370 km
Inclination	67.1°
Period
Launch vehicle	Soyuz U
Launch site	Plesetsk
End of life

Decay	14 Apr 1998


 Cosmos 2349

General

Designation	25167 / 98009A
Launch date	17 Feb 1998
Country of origin	CIS
Mission	Military: reconnaissance (Kometa; 4th generation)
Perigee/Apogee	228/286 km
Inclination	70.4°
Period	90 min
Launch vehicle	Soyuz

The SPIN-2 payload was onboard (US mapping project)  During 45 days in low orbit this satellite has taken photos of 1.2 million square miles of the Earth's surface for American companies.  In particular, the satellite has taken high-resolution photographs (2 m) of the United States to fulfill a contract signed last summer by Russia's Sovinformsputnik and the U.S. Aerial Images company.

The photos were properly recovered after decay. They will be on sale on the TerraServer.

Downlink: 15.03 GHz  40.08 GHz

External resources

http://www.spin-2.com/

http://www.terraserver.com/

End of life

Out of service	before 2 Apr 1998
Cause	decay
Decay	2 Apr 1998


 Cosmos 2350

General

Designation	25315 / 98025A
Launch date	29 Apr 1998
Country of origin	CIS
Mission	Military: early warning (Prognoz 2nd generation)
Geostationary orbit	69°E
Launch vehicle	Proton #235
Technical data

Specifications


 Cosmos 2351

General

Designation	25327 / 98027A
Launch date	7 May 1998
Country of origin	CIS
Mission	Military: early warning (Oko)
Perigee/Apogee	514/39377 km
Inclination	62.8°
Period	708 min
Launch vehicle	Molniya
Launch site	Plesetsk

Previous bird of this program: 2342


 Cosmos 2352

General

Designation	25363 / 98036A
Launch date	15 Jun 1998
Country of origin	CIS
Mission	Telecommunications (Strela-3)
Perigee/Apogee	1300 / 1900 km
Inclination
Period
Launch vehicle	Cyclone 3 #117

These spacecraft, Cosmos 2352 to 2357 were placed in an abnormal orbit by the Cyclone.This new group was launched into an elliptical orbit reaching about 300 km.


 Cosmos 2353

General

Designation	25364 / 98036B
Launch date	15 Jun 1998
Country of origin	CIS
Mission	Telecommunications (Strela-3)
Perigee/Apogee	1300 / 1900 km
Inclination
Period
Launch vehicle	Cyclone 3 #117


 Cosmos 2354

General

Designation	25365 / 98036C
Launch date	15 Jun 1998
Country of origin	CIS
Mission	Telecommunications (Strela-3)
Perigee/Apogee	1300 / 1900 km
Inclination
Period
Launch vehicle	Cyclone 3 #117


 Cosmos 2355

General

Designation	25366 / 98036D
Launch date	15 Jun 1998
Country of origin	CIS
Mission	Telecommunications (Strela-3)
Perigee/Apogee	1300 / 1900 km
Inclination
Period
Launch vehicle	Cyclone 3 #117


 Cosmos 2356

General

Designation	25367 / 98036E
Launch date	15 Jun 1998
Country of origin	CIS
Mission	Telecommunications (Strela-3)
Perigee/Apogee	1300 / 1900km
Inclination
Period
Launch vehicle	Cyclone 3 #117


 Cosmos 2357

General

Designation	25368 / 98036F
Launch date	15 Jun 1998
Country of origin	CIS
Mission	Telecommunications (Strela-3)
Perigee/Apogee	1300 / 1900 km
Inclination
Period
Launch vehicle	Cyclone 3 #117

The Cosmos satellites from 2352 through 2357 did not arrive on the correct orbit. This problem is due to an incorrect command sent to the rocket's accelerator blocks.

A re-programmation will be needed to serve their purpose


 Cosmos 2358

General

Designation	25373 / 98038A
Launch date	24 Jun 1998 at 18
Country of origin	CIS
Mission	Military: reconnaissance (Yantar' 3/4, also called Kobalt)
Perigee/Apogee	167/334 km
Inclination	67.1°
Period
Launch vehicle	Soyuz
Launch site	Plesetsk

It has a large reentry vehicle containing the camera system, and probably at least two small reentry capsules which return film during the mission, expected to last about three months. The low perigee, 67 degree inclination orbit used by this satellite is characteristic of the high resolution recoverable Yantars. [JSR]


 Cosmos 2359

General

Designation	25376 / 98039A
Launch date	25 Jun 1998 at 14:00 UT
Country of origin	CIS
Mission	Military
Perigee/Apogee	240 / 302 km
Inclination	64.9°
Period
Launch vehicle	Soyuz
Launch site	Tyuratam

It was built by TsSKB-Progress.


 Cosmos 2360

General

Designation	25406 / 98045A
Launch date	28 Jul 1998 at 9:15 UT
Country of origin	CIS
Mission	Military: Sigint (Tselina-2)
Perigee/Apogee	848/852 km
Inclination	71°
Period	101.9 min
Launch vehicle	Soyuz


 Cosmos 2361

General

Designation	25590 / 98076A
Launch date	24 Dec 1998
Country of origin	CIS
Mission	Military: Navigation (Parus)
Perigee/Apogee	969/1013 km
Inclination	83°
Period	105 min
Launch vehicle	Cosmos C

Plane 5


 Cosmos 2362

Also called Glonass 784

General

Designation	25593 / 98077A
Launch date	30 Dec 1998
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19119/19128 km
Inclination	64.8°
Period	675 min
Launch vehicle	Proton #262
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel	8
Plane	1
Slot	8


 Cosmos 2363

Also called Glonass 786

General

Designation	25594 / 98077B
Launch date	30 Dec 1998
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19119/19128 km
Inclination	64.8°
Period	675 min
Launch vehicle	Proton #262
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel	7
Plane	1
Slot	7


 Cosmos 2364

Also called Glonass 779

General

Designation	25595 / 98077C
Launch date	30 Dec 1998
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19119/19128 km
Inclination	64.8°
Period	675 min
Launch vehicle	Proton #262
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel	7
Plane	1
Slot	1


 Cosmos 2365

General

Designation	25889 / 99044A
Launch date	18 Aug 1999
Country of origin	CIS
Mission	Military: reconnaissance (Yantar' 3/4, also called Kobalt)
Perigee/Apogee	166/342 km
Inclination	67.1°
Period
Launch vehicle	Soyuz
Launch site	Plesetsk


 Astron

General

Designation	13901 / 83020A
Launch date	23 Mar 1983
Country of origin	CIS
Mission	Scientific: astronomy
Perigee/Apogee	25731/178615 km
Inclination	34.1°
Period	5932.2 min
Launch vehicle	Proton #106
Mass at launch	3500 kg (450 kg of instruments)

Carries the French and Russian experiment UFT for UV astronomy. Payload: 1 telescope (80 cm diameter and 5 m long) and a spectrometer (1.15-3.5 µm)


 Program: Bion

Russian recoverable scientific satellites program

The recoverable Bion spacecraft, built by TsSKB-Progress of Samara, is based on the Zenit/Vostok spaceship in use since 1960.

External resources

http://baby.indstate.edu/asgsb/bion.html


Program: Bion

Bion 01

Bion 02 (Cosmos 0690)

Bion 03

Bion 04

Bion 05 (Cosmos 1129)

Bion 06 (Cosmos 1514)

Bion 07 (Cosmos 1667)

Bion 08

Bion 09

Bion 10 (Cosmos 2229)

Bion 11


 Bion 11

General

Designation	24702 / 96073A
Launch date	24 Dec 1996
Country of origin	CIS
Mission	Scientific: life
Perigee/Apogee	217/378 km
Inclination	62.8°
Period	90.4 min
Launch vehicle	Soyuz U
Launch site	Plesetsk

It carries newts, snails, Drosophila flies and other insects, bacteria, and two macaque monkeys, Lapik and Multik. Both monkeys were safe at landing but Multik died of an heart attack during medical tests under general anaesthetic on January 8.

Could downlink in the 136 MHz area

End of life

Out of service	7 Jan 1997
Decay	7 Jan 1997


 Bion 12

General

Designation
Launch date
Country of origin	CIS
Mission	Scientific: life
Perigee/Apogee	217/378 km
Inclination	62.8°
Period	90.4 min
Launch vehicle	Soyuz U
Launch site	Plesetsk

NASA should not participate to this mission, probably because of public pressure after the monkey experimentation that went on on Bion 11. This could lead to monkey being replaced by rats for the future life experiments

Could downlink in the 136 MHz area


 Program: Ekran

Soviet direct TV program


Program: Ekran

Ekran 01	Ekran 02	Ekran 03	Ekran 04
Ekran 05	Ekran 06	Ekran 07	Ekran 08
Ekran 09	Ekran 10	Ekran 11	Ekran 12
Ekran 13	Ekran 14	Ekran 15	Ekran 16
Ekran 17	Ekran 18	Ekran 19	Ekran 20


Ekran's specifications

Prime contractor	NPO Prikadnoy Mekaniki (PM)
Platform	Ekran
Mass at launch	1970 kg
Diameter	2 m
Height	5 m
Stabilization	3-axis
Design lifetime	3 years
UHF-band

Main transponders	1
Backup transponders	1
Power	200 W
Bandwidth	24 MHz
Coverage	CIS and part of Asia
EIRP	55.5 dBW
Frequencies	Uplink: C-band (6 GHz) Downlink: 714 MHz


 Ekran 01

General

Designation	09503 / 76107A
Launch date	26 Oct 1976
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	99°E
Launch vehicle	Proton #60
End of life

Out of service	yes
Technical data

Specifications


 Ekran 02

General

Designation	10365 / 77092A
Launch date	20 Sep 1977
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit
Launch vehicle	Proton #65
End of life

Out of service	yes
Cause	The satellite broke up in GEO because of a nickel-hydrogen battery explosion on 23 Jun 1978. [The Soviets photographed the explosion accidentally. No other space power noted the explosion - the Russians revealed that the satellite had exploded at a conference in Moscow in February 1992.] <DSFPortree@aol.com>
Technical data

Specifications


 Ekran 03

General

Designation	11273 / 79015A
Launch date	21 Feb 1979
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit
Launch vehicle	Proton #76
End of life

Out of service	yes
Technical data

Specifications


 Ekran 04

General

Designation	11561 / 79087A
Launch date	3 Oct 1979
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit
Launch vehicle	Proton #80
End of life

Out of service	yes
Technical data

Specifications


 Ekran 05

General

Designation	11890 / 80060A
Launch date	14 Jul 1980
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit
Launch vehicle	Proton #84
End of life

Out of service	yes
Technical data

Specifications


 Ekran 06

General

Designation	12120 / 80104A
Launch date	26 Dec 1980
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit
Launch vehicle	Proton #86
End of life

Out of service	yes
Technical data

Specifications


 Ekran 07

General

Designation	12564 / 81061A
Launch date	25 Jun 1981
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit
Launch vehicle	Proton #89
End of life

Out of service	yes
Technical data

Specifications


 Ekran 08

General

Designation	13056 / 82009A
Launch date	5 Feb 1982
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	99°E
Launch vehicle	Proton #94
End of life

Out of service	yes
Technical data

Specifications


 Ekran 09

General

Designation	13554 / 82093A
Launch date	16 Sep 1982
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	99°E
Launch vehicle	Proton #99
End of life

Out of service	yes
Technical data

Specifications


 Ekran 10

General

Designation	13878 / 83016A
Launch date	12 Mar 1983
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit
Launch vehicle	Proton #105
End of life

Out of service	yes
Technical data

Specifications


 Ekran 11

General

Designation	14377 / 83100A
Launch date	30 Sep 1983
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	99°E
Launch vehicle	Proton #113
End of life

Out of service	yes
Technical data

Specifications


 Ekran 12

General

Designation	14821 / 84028A
Launch date	16 Mar 1984
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	99°E
Launch vehicle	Proton #118
End of life

Out of service	yes
Technical data

Specifications


 Ekran 13

General

Designation	15219 / 84090A
Launch date	24 Aug 1984
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	99°E
Launch vehicle	Proton #124
End of life

Out of service	yes
Technical data

Specifications


 Ekran 14

General

Designation	15626 / 85024A
Launch date	22 Mar 1985
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	99°E
Launch vehicle	Proton #131
End of life

Out of service	yes
Technical data

Specifications


 Ekran 15

General

Designation	16729 / 86038A
Launch date	24 May 1986
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	99°E
Launch vehicle	Proton #142
End of life

Out of service	yes
Technical data

Specifications


 Ekran 16

General

Designation	18328 / 87073A
Launch date	4 Sep 1987
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	99°E
Launch vehicle	Proton #154
End of life

Out of service	yes
Technical data

Specifications


 Ekran 17

General

Designation	18715 / 87109A
Launch date	27 Dec 1987
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	99°E
Launch vehicle	Proton #160
End of life

Out of service	yes
Technical data

Specifications


 Ekran 18

General

Designation	19090 / 88036A
Launch date	6 May 1988
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	99°E
Launch vehicle	Proton #165
End of life

Out of service	yes
Technical data

Specifications


 Ekran 19

General

Designation	19683 / 88108A
Launch date	8 Dec 1988
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	99°E, inclined
Launch vehicle	Proton #173
End of life

Out of service	Oct 1996
Technical data

Specifications


 Ekran 20

General

Designation	22210 / 92074A
Launch date	30 Oct 1992
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	99°E, inclined
Launch vehicle	Proton #210
Technical data

Specifications


 Electro 1

Also called GOMS N1

General

Designation	23327 / 94069A
Launch date	31 Oct 1994
Country of origin	CIS
Mission	Meteorology
Geostationary orbit	see below
Launch vehicle	Proton #228

It will provide cloud cover and sea temperature maps, along with the data on the upper boundaries of clouds and wind speeds, to enable hurricane, floods, and typhoon warnings.

Operational since 1 Jun 1996. It broadcasts on 1691 MHz (WEFAX with a minimum filter of 50 KHz)

Location

Begin	End	Position
L: 31 Oct 1994	Sep 1998	76.5°E
Mar 1999		66°E drifting
Aug 1999		72°E drifting
External resources

http://sputnik.infospace.ru/goms/engl/goms_e.htm

Technical data

Specifications

Prime contractor	VNII-EM
Platform	Electro
Mass at launch	2400 kg
Mass in orbit
Length
Width
Height
Stabilization	3-axis
DC power	1500 W
Design lifetime	3 years

L-band (1.6 GHz) capable

Wave bands: 0.46-0.7 µm (visible) & 10.5-12.5 µm (infrared)

One image every 30 minutes, transmission at 2.56 mbps

The satellite downlinks at 1.76 GHz and 7.5 GHz. It receives data (for retransmission) at 2.1 GHz and 8.2 GHz. Other frequencies at 470 & 402 MHz are said to be used for data collection.


 Program: Elekon

LEO system project from the Russian NPO-PM firm with Elbe Space & Technology and KG. Elekon. The system would be carried by 7 modules on Kosmos satellites.

Would be on polar orbits (1150 km apogee). Communications with mobiles: 1.6 GHz (uplink) and 2.5 GHz (downlink). Controling would be in C-band.


 Program: Elektron

Soviet scientific program: Earth's magnetic field, solar radioelectric emissions and Van Allen belts.


Program: Elektron

Elektron 1

Elektron 2

Elektron 3

Elektron 4


 Elektron 1

General

Designation	00746 / 64006A
Launch date	30 Jan 1964
Country of origin	CIS
Mission	Scientific: magnetophere and ionosphere study
Perigee/Apogee	404/6577 km
Inclination	60.8°
Period	162.6 min
Launch vehicle	Semiorka A1


 Elektron 2

General

Designation	00748 / 64006B
Launch date	30 Jan 1964
Country of origin	CIS
Mission	Scientific: magnetophere study
Perigee/Apogee	5082/63341 km
Inclination	59.9°
Period	1356.4 min
Launch vehicle	Semiorka A1
End of life

Decay	22 Apr 1997


 Elektron 3

General

Designation	00829 / 64038A
Launch date	10 Jul 1964
Country of origin	CIS
Mission	Scientific: magnetophere and ionosphere study
Perigee/Apogee	405/6441 km
Inclination	60.8°
Period	161 min
Launch vehicle	Semiorka A1


 Elektron 4

General

Designation	00830 / 64038B
Launch date	10 Jul 1964
Country of origin	CIS
Mission	Scientific: magnetophere study
Perigee/Apogee	447/66269 km
Inclination	60.8°
Period	1313.8 min
Launch vehicle	Semiorka A1
End of life

Decay	10 Jul 1964


 Program: Foton

Also called Photon

Scientific Russian program


Program: Foton

Foton 01 was Cosmos 1645

Foton 02 was Cosmos 1744

Foton 03 was Cosmos 1841

Foton 08 was in Oct 1992

Foton 09

Foton 10

Foton 11


 Foton 09

General

Designation	23122 / 94033A
Launch date	14 Jun 1994 at 16:00 UT
Country of origin	CIS
Mission	Scientific
Perigee/Apogee	229/385 km
Inclination	62.8°
Period	90.4 min
Launch vehicle	Soyuz
Launch site	Plesetsk
Mass at launch	8200 kg

The spacecraft, with a research payload of 700 kg, is expected to orbit for 18 days, conducting microgravity experiments in solid state and biological disciplines.

End of life

Landing	2 Jul 1994


 Foton 10

General

Designation	23497 / 95006A
Launch date	16 Feb 1995 at 17:40 UT
Country of origin	CIS
Mission	Scientific: microgravity studies
Perigee/Apogee	228/391 km
Inclination	62.8°
Period	94 min
Launch vehicle	Soyuz
Launch site	Plesetsk LC43
Mass at launch	6300 kg (retrievable experiment: 2250 kg)

The mission carried "KASHTAN", "ZONA", "SPLAV", "Biobox 2", "IBIS" instruments for zero-gravity material, and biotechnological experiments.

Biobox 2 is an incubator with experiments on cells responsible for bone mineralization and on small living organism. These experiments will contribute to a better understanding of the phenomenon of bone mass loss experienced by astronauts in space and will help identify and quantify the influence of absence of gravity on living systems.

End of life

Landing	3 Mar 1995

The descent cabin was severly damaged when it was dropped by the helicopter carrying it back for deintegration. Thus many experiments were destroyed.

Technical data

The Foton recoverable materials processing satellite, built by the Central Specialized Design Bureau in Samara, is based on the Vostok/Zenit spy satellite bus.


 Foton 11

General

Designation	25006 / 97060A
Launch date	9 Oct 1997 at 18:00 UT
Country of origin	CIS
Mission	Scientific: microgravity studies
Perigee/Apogee	218 / 371 km
Inclination	62.8°
Period
Launch vehicle	Soyuz
Launch site	Plesetsk
Mass at launch	7000 kg

Has 3 packages on board: for ESA (biobox), CNES and DARA.

End of life

Landing	23 Oct 1997 (Foton and Mirka were separated before reentry, both landed safely)
Technical data

The Mirka capsule built by Kayser-Threde and Jena-Optronik GmbH is a 154 kg  1m diameter sphere which contains a 40 kg payload. Onboard will be the following experiments:

Heatin (Heatshield Instrumentation)

Raflex (Rarefied Flow Experiment)

Pyrex (Pyrometer Experiment)

Mirka's re-entry capabilities were tested.

IBIS 2, 75 kg (replacement for the IBIS payload on Foton 10)


 Gamma

General

Designation	20683 / 90058A
Launch date	11 Jul 1990
Country of origin	CIS
Mission	Scientific: gamma-ray astronomy
Perigee/Apogee	382/387 km
Inclination	51.6°
Period	92.3 min
Launch vehicle	Soyuz
Launch site	Tyuratam
End of life

Decay	28 Feb 1992


 Program: Geo-IK

Russian geodesy program. It is probably military aimed, to provide precise localisation of military targets for ICBM/IRBM attacks.

The satellites of this series are based on the Musson bus (see Parus for details). The satellites are all named in the Cosmos program both the most recent one.

Technical data

Specifications

Prime contractor
Platform	Musson bus
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization	Gravity gradient
DC power
Design lifetime

These satellites transmit broadband PCM-FM signals on 150.3 MHz and a CW carrier on 400.8 MHz


Program: Geo-IK

Cosmos (1242): Failure

Cosmos 1312

Cosmos 1410

Cosmos 1510

Cosmos 1589

Cosmos 1660

Cosmos 1732

Cosmos 1803

Cosmos 1823

Cosmos 1950

Cosmos 2037

Cosmos 2088

Cosmos 2226

Geo-IK 1


 Geo-IK 1

General

Designation	23411 / 94078A
Launch date	24 Nov 1994 at 02:54 UT
Country of origin	CIS
Mission	Scientific: geodetic survey (Geo-IK)
Perigee/Apogee	1480/1526 km
Inclination	73.6°
Period	116 min
Launch vehicle	Cyclone 3 #112

It also carried an experimental Elekon positioning equipment to monitor movements of land and sea transportations, to optimize and increase efficiency.


 Program: Gonets

Russian LEO telecommunication system, designed from the reconvertion of military technology. The system should be composed of 36 satellites on 6 orbital planes. The project was launched in 1992. The satellites are probably less than 300 kg.

The system should use the GPS and GLONASS positioning systems for geolocation services. Gonets will operate in the 300-400 MHz range VHF/UHF band and the 1.5/1.6 GHz band. Uplinks will be from 312-315 MHz and 1624.5-1643.4 MHz, and downlinks from 387-390 MHz and 1541.0-1541.9 MHz.

The system is derived from the Strela-3 military series. The Gonets-D crafts were most probably test satellites.


Program: Gonets

Gonets D

Cosmos 2199	Cosmos 2201
Gonets D1

Gonets D1-1	Gonets D1-2	Gonets D1-3	Gonets D1-4	Gonets D1-5	Gonets D1-6


 Gonets D1-1

General

Designation	23787 / 96009A
Launch date	19 Feb 1996
Country of origin	CIS
Mission	Military: telecommunications (Gonets)
Perigee/Apogee	~1400 km
Inclination	~82°
Period
Launch vehicle	Cyclone 3 #115


 Gonets D1-2

General

Designation	23788 / 96009B
Launch date	19 Feb 1996
Country of origin	CIS
Mission	Military: telecommunications (Gonets)
Perigee/Apogee	~1400 km
Inclination	~82°
Period
Launch vehicle	Cyclone 3 #115


 Gonets D1-3

General

Designation	23789 / 96009C
Launch date	19 Feb 1996
Country of origin	CIS
Mission	Military: telecommunications (Gonets)
Perigee/Apogee	~1400 km
Inclination	~82°
Period
Launch vehicle	Cyclone 3 #115


 Gonets D1-4

General

Designation	24728 / 97006D
Launch date	14 Feb 1997
Country of origin	CIS
Mission	Military: telecommunications (Gonets)
Perigee/Apogee	1410 km
Inclination	82.6°
Period	114 min
Launch vehicle	Cyclone 3 #116


 Gonets D1-5

General

Designation	24729 / 97006E
Launch date	14 Feb 1997
Country of origin	CIS
Mission	Military: telecommunications (Gonets)
Perigee/Apogee	1410 km
Inclination	82.6°
Period	114 min
Launch vehicle	Cyclone 3 #116


 Gonets D1-6

General

Designation	24730 / 97006F
Launch date	14 Feb 1997
Country of origin	CIS
Mission	Military: telecommunications (Gonets)
Perigee/Apogee	1410 km
Inclination	82.6°
Period	114 min
Launch vehicle	Cyclone 3 #116


 Granat

General

Designation	20352 / 89096A
Launch date	1 Dec 1989
Country of origin	CIS
Mission	Scientific: astronomy
Perigee/Apogee	57435/146072 km
Inclination	86.7°
Period	5897.8 min
Launch vehicle
Launch site	Tyuratam

Astronomy satellite carrying the French Sigma telescope

End of life

Out of service	Dec 1998
Cause	EOL for Sigma, maybe other experiments are still operational
Decay
External resources

http://hea.iki.rssi.ru/GRANAT/granat.html

http://kisa.iki.rssi.ru/GRANAT/sigma/sigma.html


 Informator

Also called AO-21 or RS-14 or Rudak 2 or Oscar 21

General

Designation	21087 / 91006A
Launch date	29 Jan 1991
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	955/1005 km
Inclination	82.9°
Period	104.7 min
Launch vehicle	Cosmos C
Launch site	Plesetsk
End of life

Out of service	mid-October 1994
Technical data

Analog transponders and a digital signal processing (DSP) experiment. The DSP experiment being a bit of a chameleon, can serve many different functions, one of them being an FM repeater, another being a mailbox experiment like the Pacsat's.

Transponder 1:

Mode B up	435.102 - 435.022 MHz
Mode B down	145.852 - 145.932 MHz
Beacons	145.822 MHz CW, 145.952 MHz 1100 bps PSK
Transponder 2:

Mode B up	435.123 - 435.043 MHz
Mode B down	145.866 - 145.946 MHz
Beacons	145.948 MHz CW, 145.838 MHz 1100 bps PSK
RUDAK Transponder:

Uplink 1	435.016 MHz 1200 bps Manchester FSK + FM repeater input frq.
Uplink 2	435.155 MHz 2400 bps BPSK
Uplink 3A	435.193 MHz 4800 bps RSM NRZI
Uplink 3B	435.193 MHz 9600 bps RSM NRZI
Uplink 4	435.041 MHz Digital Signal Processor input
Downlink	145.987 MHz
Mode 1	Pacsat / FO-20 compatible
Mode 2	AO-13 400 bps BPSK compatible
Mode 3	AO-13 RUDAK I compatible
Mode 4	4800 bps
Mode 5	9600 bps
Mode 6	CW
Mode 7	FSK (F1 or F2B) RTTY, FAX, SSTV, etc.
Mode 8	FM using D/A converter and DSP output


 Program: Intercosmos

Cooperation program created in 1967 between countries of the former East block. It was controlled by the Soviets and worked without money exchange, each state payed for the research in his own country and USSR launched the rockets (Intercosmos). The mission of the program was scientific research.

That program enabled cosmonauts of member states to fly.


Program: Intercosmos

Intercosmos 01

Intercosmos 18

Intercosmos 22


 Intercosmos 01

General

Designation	04128 / 69088A
Launch date	14 Oct 1969
Country of origin	CIS
Mission	Scientific: high atmosphere study
Perigee/Apogee	264/617 km
Inclination	48.3°
Period	93.4 min
Launch vehicle	Cosmos B
Launch site	Kapustin Yar
End of life

Decay	2 Jan 1970


 Intercosmos 18

General

Designation	11082 / 78099A
Launch date	24 Oct 1978
Country of origin	CIS
Mission	Scientific: ionosphere and magnetosphere study
Perigee/Apogee	403/757 km
Inclination	83°
Period	96.3 min
Launch vehicle	Cosmos C
Launch site	Plesetsk
End of life

Decay	17 Mar 1981


 Intercosmos 22

Also called Intercosmos Bulgaria 1300

General

Designation	12645 / 81075A
Launch date	7 Aug 1981
Country of origin	Bulgaria
Mission	Scientific
Perigee/Apogee	788/882 km
Inclination	81.2°
Period	101.6 min
Launch vehicle	Semiorka A1
Mass at launch	350 kg


 Program: Luch

Means "beam"; also called Al'tair or SDRN

Russian program for LEO communications relay (e.g. Mir). This program is also known as SDRN (Satellite Data Relay Network).

The first generation satellites of this program were based on the Al'tair platform. The second generation's performance is said to increase the capacity of the channels by nearly 3 and its lifetime would be twice as long.


Program: Luch

Cosmos 1700

Cosmos 1897

Cosmos 2054

Luch 0

Luch 1


Luch's specifications

Prime contractor	NPOPM
Platform	Al'tair
Mass at launch	2000 kg
Dimension	8.5 x 11 x 16 m
Stabilization	3-axis, 0.5° GEO precision
DC power	1800 W
Design lifetime	5 years
UHF-band (0.9/0.7 GHz)

Main transponders	1
Coverage	6° spotbeam
EIRP	40.7 dBW
Ku-band - data

Main transponders	1
Power	30 W
Bandwidth	50 MHz
Coverage	0.5° spotbeam
EIRP	55.2 dBW
Uplink	15.130-15.180 GHz LHCP (16/64 kbps)
Downlink	13.511-13.545 GHz RHCP (16/64/256 kbps)
Ku-band

Main transponders	1
Coverage	1° spotbeam (1.6 m diam onboard antenna)
EIRP	42.3 dBW
Uplink	14.591-14.625 GHz LHCP
Downlink	10.810-10.860 GHz RHCP


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 Luch 0

General

Designation	23426 / 94082A
Launch date	16 Dec 1994
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Proton #230
Mass at launch	2000 kg

Transmits data to and from Mir station. It is equipped with a Cospas payload.

Location

Begin	End	Position
L: 16 Dec 1994	Mar 1997	95°E
May 1997	Oct 1998	16°W
End of life

Out of service	Oct 1998
Technical data

Specifications


 Luch 1

General

Designation	23680 / 95054A
Launch date	11 Oct 1995 at 16:26 UT
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	77°E
Launch vehicle	Proton #236
Mass at launch	2400 kg

Equipped with a Cospas payload?

Its performance is said to increase the capacity of the channels by nearly 3 and its service lifetime would be twice as long compared to the Al'tair design.

End of life

Out of service	12 April 1999
Cause	failure


 Program: Meteor

Soviet meteorology satellite program. Mission: met observation: clouds, ice cover and atmospheric radiation; high speed natural phenomena: cyclone, tidal action, dust storms, etc.

Meteor 1 series

30/31 satellites launched

Meteor 2 series

21 satellites launched

Meteor 3 series

6 since 1985


Program: Meteor

Meteor-Cosmos

Cosmos 0122	Cosmos 0144	Cosmos 0156	Cosmos 0184	Cosmos 0206
Cosmos 0226
Meteor 1

Meteor 1-01	Meteor 1-02
Meteor 2

Meteor 2-01	Meteor 2-21
Meteor 3

Meteor 3-03	Meteor 3-05	Meteor 3-06


Meteor-Cosmos' specifications

Prime contractor
Mass at launch	2000 kg
Diameter	1.5 m?
Height	5 m?
Solar array	2 solar panels
Stabilization	3-axis?


Meteor 1's specifications

Prime contractor
Mass at launch	2200 kg
Diameter	1.5 m?
Height	5 m?
Solar array	2 solar panels
Stabilization	3-axis?


Meteor 2's specifications

Prime contractor	VNII Elektromekaniki
Mass in orbit	1500 kg
Diameter	2 m
Height	5 m
Solar array	2 panels of 10 m
Stabilization	3-axis


Meteor 2's payload

Scanning Telephotometer (direct imaging)

Wavebands	0.5-7.0 µm (visible)
Resolution	global coverage: 2 km regional coverage: 1 km
Scanning IR Radiometer

Wavebands	8-12 µm (IR)
Resolution	global coverage: 8 km
Scanning IR Spectrometer

Wavelengths	11, 10-18, 70 µm (IR)
Resolution	30 km


Meteor 3's specifications

Prime contractor	VNII Elektromekaniki
Mass in orbit	1500 kg
Diameter	2 m
Height	5 m
Solar array	2 panels of 10 m
Stabilization	3-axis


Meteor 3's payload

Scanning Telephotometer (direct imaging)

Wavebands	0.5-8.0 µm (visible)
Swath width	3100 km
Resolution	global coverage: 2 km regional coverage: 1 km
Scanning IR Radiometer

Wavebands	10.5-12.5 µm (IR)
Swath width	3100 km
Resolution	global coverage: 8 km
Scanning IR Spectrometer

Wavelengths	9.65, 18.7 µm (IR)
Swath width	400 km
Resolution	30 km

Downlink: 466.5 MHz (to control centers) & 137.850 MHz


 Meteor 1-01

General

Designation	03835 / 69029A
Launch date	26 Mar 1969
Country of origin	CIS
Mission	Meteorology
Perigee/Apogee	548/575 km
Inclination	81.2°
Period	95.9 min
Launch vehicle	Semiorka A1
Mass at launch	2200 kg
Technical data

Specifications


 Meteor 1-02

General

Designation	04119 / 69084A
Launch date	6 Oct 1969
Country of origin	CIS
Mission	Meteorology
Perigee/Apogee	514/550 km
Inclination	81.2°
Period	95.3 min
Launch vehicle	Semiorka A1
Technical data

Specifications


 Meteor 2-01

General

Designation	08026 / 75064A
Launch date	11 Jul 1975
Country of origin	CIS
Mission	Meteorology
Perigee/Apogee	844/876 km
Inclination	81.3°
Period	102.2 min
Launch vehicle	Semiorka A1
Technical data

Specifications

Payload


 Meteor 2-21

General

Designation	22782 / 93055A
Launch date	31 Aug 1993 at 04:40 UT
Country of origin	CIS
Mission	Meteorology
Perigee/Apogee	934/966 km
Inclination	82.5°
Period	104.1 min
Launch vehicle	Cyclone 3 #106
End of life

Out of service	24 Jun 1998
Cause	possible modulation failure
Decay
Technical data

Specifications

Payload


 Meteor 3-03

General

Designation	20305 / 89086A
Launch date	24 Oct 1989
Country of origin	CIS
Mission	Meteorology
Perigee/Apogee	1235/1248 km
Inclination	82.6°
Period	110.3 min
Launch vehicle	Cyclone 3 #80
End of life

Out of service	yes
Technical data

Specifications

Payload

APT downlink frequency: 137.300 MHz (current status unknown)


 Meteor 3-05

General

Designation	21655 / 91056A
Launch date	15 Aug 1991
Country of origin	CIS
Mission	Meteorology
Perigee/Apogee	1184/1203 km
Inclination	82.55°
Period	109.3 min
Launch vehicle	Cyclone 3 #94

Carried the TOMS instrument which failed in 1994.  Replaced Meteor 2-21

Technical data

Transmits on 137.30 MHz (APT) (earlier it transmitted at 137.850 MHz but this caused interference when Resurs O1-4 was launched)

TOMS

Wavebands	312.5; 317.5; 331.3; 339.8; 360.0; 380.0 nm.
Resolution	63 x 63 km²
Swath width	2900 km


 Meteor 3-06

General

Designation	22969 / 94003A
Launch date	25 Jan 1994
Country of origin	CIS
Mission	Meteorology
Perigee/Apogee	1184/1209 km
Inclination	82.55°
Period	109.36 min
Launch vehicle	Cyclone 3 #107

On board was a German PRARE navigational system to measure parameters of spacecraft motion.

The French Scarab payload for radiation budget failed in April 1995. The data collected provided a radiation budget similar to NASA's ERBE program.

Technical data

Specifications

Payload


 Program: Molniya

Means "flash of lightning" in Russian

Soviet telecomunication program. Satellites are placed on very excentric orbits (460/40000 km, inclination: 63°, satellites in 8 planes separated by 45°) with a 12 hours period. Such satellites remain almost 8 hours above the CIS, slowly drifting high in the sky.

Molniya satellites are used by the Orbita network equipped with 12 m antennas. Mars transportable stations could also use the network with 7 m antennas. Mission: provide long distance reliable telephone and TV links. Molniya-1 are used for government and military communications whereas Molniya-3 are used for TV programs.

As the first Molniya-2 satellites were launched the system became available for Intersputnik. The first satellite operated at 1.0/0.8 GHz. C-band (6/4 GHz) was introduced from Molniya 1-07 on. Satellites also use L-band.

In the future, the system could be replaced by Mayak

Molniya 1

Specifications

Prime contractor	NPO PM (design OKB-1)
Platform	Molniya
Mass at launch
Mass in orbit	1600 kg
Dimension
Solar array	1500 W
Stabilization	spin stabilized
DC power	BOL: 1000 W
Design lifetime	2 years
X-band

Main transponders	1 to 3
Backup transponders
Power	40 W (TWTA)
Bandwidth
Coverage
EIRP
Polarization
External resources

http://www.ninfinger.org/~sven/models/sovietsp/molniya.html


Program: Molniya

Molniya 1-01	Molniya 1-71	Molniya 1-72	Molniya 1-74
Molniya 1-85	Molniya 1-86	Molniya 1-87	Molniya 1-88
Molniya 1-89	Molniya 1-90	Molniya 1-91
Molniya 2-01
Molniya 3-01	Molniya 3-34	Molniya 3-35	Molniya 3-36
Molniya 3-37	Molniya 3-42	Molniya 3-44	Molniya 3-45
Molniya 3-46	Molniya 3-47	Molniya 3-48	Molniya 3-49
Molniya 3-50
Molniya 1-S


 Molniya 1-01

General

Designation	01324 / 65030A
Launch date	23 Apr 1965
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	538/39300 km
Inclination	65.5°
Period	707.3 min
Launch vehicle	Molniya
Launch site	Tyuratam
End of life

Out of service	7.5 months after launch
Decay	16 Aug 1979
Technical data

Transmission (upload: 0.8 GHz, download: 1 GHz)

Main transponders	3
Backup transponders
Power	40 W
Bandwidth	240 phone circuits
Coverage
EIRP
Polarization


 Molniya 1-71

General

Designation	18946 / 88017A
Launch date	11 Mar 1988
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	491/38976 km
Inclination	62.5°
Period	699 min
Launch vehicle	Molniya


 Molniya 1-72

General

Designation	18980 / 88022A
Launch date	17 Mar 1988
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	655/40584 km
Inclination	62.9°
Period	735 min
Launch vehicle	Molniya


 Molniya 1-74

General

Designation	19730 / 88115A
Launch date	28 Dec 1988
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	654/38870 km
Inclination	62.8°
Period	700 min
Launch vehicle	Molniya


 Molniya 1-85

General

Designation	22309 / 93002A
Launch date	12 Jan 1993
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	528/39822 km
Inclination	63.4°
Period	717.7 min
Launch vehicle	Molniya


 Molniya 1-86

General

Designation	22671 / 93035A
Launch date	26 May 1993
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	681/39672 km
Inclination	62.9°
Period	717.8 min
Launch vehicle	Molniya


 Molniya 1-87

General

Designation	22949 / 93079A
Launch date	22 Dec 1993
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	446/39206 km
Inclination	62.8°
Period	703 min
Launch vehicle	Molniya

Molniya 1-T


 Molniya 1-88

General

Designation	23420 / 94081A
Launch date	14 Dec 1994
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	516/39833 km
Inclination	62.8°
Period	718 min
Launch vehicle	Molniya

Molniya 1-T


 Molniya 1-89

General

Designation	24274 / 96045A
Launch date	14 Aug 1996 at 22:21 UT
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	516/39833 km
Inclination	62.8°
Period	12 hours
Launch vehicle	Molniya

Molniya 1-T series

This is said to be the 200th Molniya

Mass at launch: 1600 kg?


 Molniya 1-90

General

Designation	24960 / 97054A
Launch date	24 Sep 1997 at 21:32 UT
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	506/39920 km
Inclination	62.8°
Period	12 hours
Launch vehicle	Molniya

Molniya 1-T series


 Molniya 1-91

General

Designation	25485 / 98054A
Launch date	28 Sep 1998
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	506/39920 km
Inclination	62.8°
Period	12 hours
Launch vehicle	Molniya #308

Molniya 1-T series


 Molniya 2-01

General

Designation	05620 / 71100A
Launch date	25 Nov 1971
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	516/39553 km
Inclination	65°
Period	712 min
Launch vehicle	Molniya
End of life

Decay	10 May 1976


 Molniya 3-01

General

Designation	07540 / 74092A
Launch date	21 Nov 1974
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	250/40095 km
Inclination	64.1°
Period	717.6 min
Launch vehicle	Molniya
Mass at launch	1600 kg
End of life

Decay	15 May 1986


 Molniya 3-34

General

Designation	19713 / 88112A
Launch date	22 Dec 1988
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	899/39481 km
Inclination	63.9°
Period	718.3 min
Launch vehicle	Molniya


 Molniya 3-35

General

Designation	20052 / 89043A
Launch date	8 Jun 1989
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1436/38918 km
Inclination	64.8°
Period	717.8 min
Launch vehicle	Molniya


 Molniya 3-36

General

Designation	20338 / 89094A
Launch date	28 Nov 1989
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	698/39655 km
Inclination	64.8°
Period	717.8 min
Launch vehicle	Molniya


 Molniya 3-37

General

Designation	20444 / 90006A
Launch date	23 Jan 1990
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	982/39367 km
Inclination	64.9°
Period	717.7 min
Launch vehicle	Molniya


 Molniya 3-42

General

Designation	22178 / 92067A
Launch date	14 Oct 1992
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	466/39103 km
Inclination	62.9°
Period	701 min
Launch vehicle	Molniya


 Molniya 3-44

General

Designation	22633 / 93025A
Launch date	21 Apr 1993 at 00:30 UT
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	744/39603 km
Inclination	62.9°
Period	717.7 min
Launch vehicle	Molniya


 Molniya 3-45

General

Designation	22729 / 93049A
Launch date	4 Aug 1993 at 00:52 UT
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	511/39841 km
Inclination	62.8°
Period	717.7 min
Launch vehicle	Molniya


 Molniya 3-46

General

Designation	23211 / 94051A
Launch date	23 Aug 1994 at 14:31 UT
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	622/39726 km
Inclination	63°
Period	618 min
Launch vehicle	Molniya


 Molniya 3-47

General

Designation	23642 / 95042A
Launch date	9 Aug 1995 at 01:21 UT
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	472/40851 km
Inclination	62.3°
Period
Launch vehicle	Molniya


 Molniya 3-48

General

Designation	24640 / 96060A
Launch date	24 Oct 1996 at 11:37 UT
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	611/39768 km
Inclination	62.8°
Period	718.2 min
Launch vehicle	Molniya


 Molniya 3-49

General

Designation	25379 / 98040A
Launch date	1 Jul 1998
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	462/39889 km
Inclination	62.8°
Period	717.7 min
Launch vehicle	Molniya #307


 Molniya 3-50

General

Designation	25847 / 99036A
Launch date	8 Jul 1999
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	462/39889 km
Inclination	62.8°
Period	717.7 min
Launch vehicle	Molniya #309


 Molniya 1-S

General

Designation	07392 / 74060A
Launch date	29 Jul 1974
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit
Launch vehicle	Proton #49
End of life

Out of service	yes


 Program: Nadezhda

Nadezhda means 'hope'

Russian navigation program using the Tsikada platform. The satellites of this program carry a Cospas receiver.

The Nadezhda M generation (started with Cosmos 2315) carries hardware that can either provide Cospas or Kurs services.

Designed by AO Polyot and NPO PM


Program: Nadezhda

Nadezhda 1

Nadezhda 2

Nadezhda 3

Nadezhda 4

Nadezhda 5


 Nadezhda 1

General

Designation	20103 / 89050A
Launch date	4 Jul 1989
Country of origin	CIS
Mission	Navigation
Perigee/Apogee	954/1011 km
Inclination	83°
Period	104.8 min
Launch vehicle	Cosmos C
Launch site	Plesetsk


 Nadezhda 2

General

Designation	20508 / 90017A
Launch date	27 Feb 1990
Country of origin	CIS
Mission	Navigation
Perigee/Apogee	950/1018 km
Inclination	83°
Period	104.8 min
Launch vehicle	Cosmos C
Launch site	Plesetsk
End of life

Out of service
Cause	failed
Decay
Technical data

Used to transmit on 150 & 400 MHz (replaced by Nadezhda 4)

Also carried a Sarsat payload.


 Nadezhda 3

General

Designation	21152 / 91019A
Launch date	12 Mar 1991
Country of origin	CIS
Mission	Navigation
Perigee/Apogee	952/1015 km
Inclination	82.9°
Period	104.8 min
Launch vehicle	Cosmos C
Launch site	Plesetsk
Technical data

Downlink frequencies: 150 & 400 MHz

Plane 12


 Nadezhda 4

General

Designation	23179 / 94041A
Launch date	14 Jul 1994 at 06:13 UT
Country of origin	CIS
Mission	Navigation
Perigee/Apogee	951/1007 km
Inclination	82.9°
Period	104.7 min
Launch vehicle	Cosmos C
Launch site	Plesetsk
Technical data

Downlink frequencies: 150 & 400 MHz

Plane 14


 Nadezhda 5

General

Designation	25567 / 98072A
Launch date	10 Dec 1998
Country of origin	CIS
Mission	Navigation
Perigee/Apogee	987/1040 km
Inclination	83°
Period	105 min
Launch vehicle	Cosmos C
Technical data

Downlink frequencies: 150 & 400 MHz

Plane 14

mass at launch: 870 kg

lifetime: 2 years


 Program: Ocean

Russian remote sensing program devoted to oceanographic applications.

Mission: all-weather ice and sea monitoring, including ice floe/ice pack movements. Flood and pollution monitoring.


Program: Ocean

Ocean-E

Cosmos 1076	Cosmos 1151
Ocean-OE

Cosmos 1500	Cosmos 1602
Ocean-O1

Cosmos 1766	Cosmos 1869	Ocean O1-1	Ocean O1-2
Ocean O1-3	Ocean O1-4	Sich 1
Ocean-O2

Ocean O2-1


Ocean-O1's specifications

Platform	built by NPO Yuzhnoe
Mass at launch	1400 kg
Diameter	1.4 m
Height	3 m
Radar antenna	12 m
Stabilization	3-axis

Transmissions: APT-like at 137.4 MHz & FM at 465 MHz


Ocean-O1's payload

SLR (Side-Looking Radar)

Frequency	9.5 GHz (X-band)
Resolution	1.5 km
Swath width	460 km
MSU-M (Multispectral Scanner)

Wavebands	0.5-0.6; 0.6-0.7; 0.7-0.8; 0.8-1.1 µm
Resolution	1.5 km
Swath width	2000 km
MSU-S (Scanning Radiometer)

Wavebands	0.5-0.6; 0.6-0.7; 0.7-0.8; 0.8-1.1 µm
Resolution	200 m
Swath width	600 km
RM08 (microwave radiometer)

Frequency	36.5 - 36.8 GHz
Resolution	25 km
Swath width	550 km


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Ocean-O2's specifications

Platform	built by NPO Yuzhnoe
Mass at launch	6500 kg
Diameter
Height
Radar antenna
Stabilization

Has a side-looking radar (RSL-BO), and a set of visible and infrared scanners and radiometers.


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 Ocean O1-1

General

Designation	19274 / 88056A
Launch date	5 Jul 1988
Country of origin	CIS
Mission	Remote sensing (Ocean-O1)
Perigee/Apogee	606/633 km
Inclination	82.5°
Period	97.1 min
Launch vehicle	Cyclone 3 #70
Technical data

Specifications

Payload


 Ocean O1-2

General

Designation	20510 / 90018A
Launch date	28 Feb 1990
Country of origin	CIS
Mission	Remote sensing (Ocean-O1)
Perigee/Apogee	618/645 km
Inclination	82.5°
Period	97.3 min
Launch vehicle	Cyclone 3 #83
Technical data

Specifications

Payload


 Ocean O1-3

General

Designation	21397 / 91039A
Launch date	4 Jun 1991
Country of origin	CIS
Mission	Remote sensing (Ocean-O1)
Perigee/Apogee	620/655 km
Inclination	82.5°
Period	97.5 min
Launch vehicle	Cyclone 3 #92
Technical data

Specifications

Payload

Downlink frequency: 137.4 MHz


 Ocean O1-4

General

Designation	23317 / 94066A
Launch date	11 Oct 1994 at 13:30 UT
Country of origin	CIS (Russian/Ukrainian)
Mission	Remote sensing (Ocean-O1)
Perigee/Apogee	631/665 km
Inclination	88.5°
Period	97.7 min
Launch vehicle	Cyclone 3 #111
Mass at launch	1950 kg
Technical data

Specifications

Payload


 Ocean O2-1

General

Designation	25860 / 99039A
Launch date	17 Jul 1999
Country of origin	CIS (Russian/Ukrainian)
Mission	Remote sensing (Ocean-O2)
Perigee/Apogee	660 km
Inclination	98°
Period
Launch vehicle	Zenit #32

Joint project of the Russian Aviation/Space Agency (RAKA) and the Ukrainian National Space Agency (NKAU)

Technical data

Specifications


 Program: Prognoz

Russian scientific program. Designed to study the Sun's activity and its influence on Earth's magnetosphere.


Program: Prognoz

Prognoz 01

Prognoz 02

Prognoz 03

Prognoz 04

Prognoz 05

Prognoz 06

Prognoz 07

Prognoz 08

Prognoz 09

Prognoz 10

Prognoz 11

Prognoz 12


 Prognoz 01

General

Designation	05941 / 72029A
Launch date	14 Apr 1972
Country of origin	CIS
Mission	Scientific: magnetosphere study
Perigee/Apogee	1005/199667 km
Inclination	65°
Period	5782.1 min
Launch vehicle	Molniya
Mass at launch	845 kg


 Prognoz 02

General

Designation	06068 / 72046A
Launch date	29 Jun 1972
Country of origin	CIS
Mission	Scientific: magnetosphere study
Perigee/Apogee	517/201804 km
Inclination	65.3°
Period	5849.2 min
Launch vehicle	Molniya
Mass at launch	845 kg

Carries two French experiments (Calypso and Signe) to studies particles from the Sun.

End of life

Decay	15 Dec 1982


 Prognoz 03

General

Designation	06364 / 73009A
Launch date	15 Feb 1973
Country of origin	CIS
Mission	Scientific: magnetosphere study
Perigee/Apogee	590/200000 km
Inclination	65°
Period	5783 min
Launch vehicle	Molniya
Mass at launch	845 kg


 Prognoz 04

General

Designation	08510 / 75122A
Launch date	22 Dec 1975
Country of origin	CIS
Mission	Scientific: magnetosphere study
Perigee/Apogee	634/199000 km
Inclination	65°
Period	5740 min
Launch vehicle	Molniya


 Prognoz 05

General

Designation	09557 / 76112A
Launch date	25 Nov 1976
Country of origin	CIS
Mission	Scientific: magnetosphere study
Perigee/Apogee	777/198560 km
Inclination	65.2°
Period	5728 min
Launch vehicle	Molniya


 Prognoz 06

General

Designation	10370 / 77093A
Launch date	22 Sep 1977
Country of origin	CIS
Mission	Scientific: magnetosphere study
Perigee/Apogee	488/197867 km
Inclination	65°
Period	5688 min
Launch vehicle	Molniya


 Prognoz 07

General

Designation	11088 / 78101A
Launch date	30 Oct 1978
Country of origin	CIS
Mission	Scientific: magnetosphere study
Perigee/Apogee	472/202627 km
Inclination	64.9°
Period	5881.1 min
Launch vehicle	Molniya
End of life

Decay	22 Oct 1980


 Prognoz 08

General

Designation	12116 / 80103A
Launch date	25 Dec 1980
Country of origin	CIS
Mission	Scientific: magnetosphere study
Perigee/Apogee	978/197364 km
Inclination	65.8°
Period	5687.8 min
Launch vehicle	Molniya


 Prognoz 09

General

Designation	14163 / 83067A
Launch date	1 Jul 1983
Country of origin	CIS
Mission	Scientific: radio astronomy and Sun study
Perigee/Apogee	n/a
Inclination	n/a
Period	n/a
Launch vehicle	Molniya


 Prognoz 10

General

Designation	15661 / 85033A
Launch date	26 Apr 1985
Country of origin	CIS
Mission	Scientific
Perigee/Apogee	5975/194734 km
Inclination	76.8°
Period	5783.7 min
Launch vehicle	Molniya
End of life

Out of service	Jan 1986


 Prognoz 11

Also called Interbol 1 or SO-M2 #512

General

Designation	23633 / 95039A
Launch date	2 Aug 1995 at 23:59 UT
Country of origin	CIS
Mission	Scientific: magnetosphere study (Prognoz M2)
Perigee/Apogee	505/193064 km
Inclination	63.8°
Period	5472 min
Launch vehicle	Molniya
Mass at launch	1200 kg

This satellite is the Khvostovoy Zond ("Tail") satellite of Project Interbol, intended to investigate the Earth's geomagnetic tail.

External resources

http://www.iki.rssi.ru/interball.html

On-board science instruments

SKA-1, PROMICS-3, VDP, AMEI-2, CORAL, ALPHA3 (plasma ions)

ELECTRON, (plasma electrons)

MONITOR-3 (solar wind ions with high time resolution)

IFPE (ion and electron flux variations)

MIF-M, FGS-1, FM-31 (magnetometers); OPERA (electric field)

AKR-X (solar radio emission 0.1-1.5 MHz)

RF-15-1 (solar X-rays 2-240 keV)

SKA-2, DOK-2, SOSNA-2, RKA-2 (energetic particles)


 Prognoz 12

Also called Interbol 2 or SO-M2 #513

General

Designation	24291 / 96050B
Launch date	29 Aug 1996 at 05:22 UT
Country of origin	CIS
Mission	Scientific: aurora study (Prognoz M2)
Perigee/Apogee	782/19140 km
Inclination	62.8°
Period
Launch vehicle	Molniya
Mass at launch	1250 kg
External resources

http://www.kiam1.rssi.ru/I_BALL/I_BALL.HTM

http://www.iki.rssi.ru/interball.html

Technical data

built by NPO Lavochkin


 Program: Proton

Soviet heavy satellite program to study cosmic radiations.

Satellites have 4 solar pannels and a 9.7 m span.


Program: Proton

Proton 1

Proton 2

Proton 3

Proton 4


 Proton 1

General

Designation	01466 / 65054A
Launch date	16 Jul 1965
Country of origin	CIS
Mission	Scientific: ionosphere study
Perigee/Apogee	181/578 km
Inclination	63.4°
Period	92.2 min
Launch vehicle	Proton #1
Mass at launch	12.2 t
End of life

Decay	11 Oct 1965


 Proton 2

General

Designation	01701 / 65087A
Launch date	2 Nov 1965
Country of origin	CIS
Mission	Scientific: ionosphere study
Perigee/Apogee	189/608 km
Inclination	63.5°
Period	92.5 min
Launch vehicle	Proton #2
Mass at launch	12.2 t
End of life

Decay	6 Feb 1966


 Proton 3

General

Designation	02290 / 66060A
Launch date	6 Jul 1966
Country of origin	CIS
Mission	Scientific: ionosphere study
Perigee/Apogee	185/594 km
Inclination	63.5°
Period	92.3 min
Launch vehicle	Proton #4
Mass at launch	12.2 t
End of life

Decay	16 Sep 1966


 Proton 4

General

Designation	03544 / 68103A
Launch date	16 Nov 1968
Country of origin	CIS
Mission	Scientific: ionosphere study
Perigee/Apogee	248/477 km
Inclination	51.6°
Period	91.8 min
Launch vehicle	Proton #13
Mass at launch	17 t
End of life

Decay	24 Jul 1969


 Program: Resurs

Soviet remote sensing satellite program operated by the Priroda ('Nature') center of the Russian Central Geodesy and Cartography Agency (GUGK).

The F2-series satellites had about 1 month lifetime while the F1 series had only half. The results of the mission (films) are sent back to earth in a reentry vehicle.

A new series named Resurs DK should be launched in 1999. With 3 years lifetime this satellite will be placed in 400 km orbit by a Rus launcher. It's payload called Geoton-L will provide 2 - 2.5 m resolution panchromatic pictures, 2.5 - 3 m resolution multispectral pictures.

Chronology

Resurs F20 is 60th in Resurs-F series. There were 4 types of Resurs-F spacecrafts: three of Resurs-F1 type and Resurs-F2. First Resurs-F1 named Cosmos 1127 was launched at 10:20 UTC on 5 Sep 1979 from LC41 of Plesetsk cosmodrome. First one of Resurs-F2 series (Cosmos 1906) was launched at 11:30 UTC on 26 Dec 1987 from LC16 of Plesetsk.

There were a total of 50 spacecrafts of Resurs-F1 types (28 of the 1st type, 6 of the 2nd and 16 of the 3rd) and 10 of Resurs-F2 type launched. There were also two launch failures at the launch of Resurs-F1 of the 2nd and the 3rd types. So, there were 62 launch attempts of Resurs-F spacecrafts.

External resources

http://www.ssc.se/sb/resurs/


Program Resurs

Resurs F01 Resurs F02 Resurs F03 Resurs F04 Resurs F05 Resurs F06 Resurs F07 Resurs F08 Resurs F09 Resurs F10 Resurs F11 Resurs F12 Resurs F13 Resurs F14 Resurs F15 Resurs F16 Resurs F17 Resurs F18 Resurs F19 Resurs F20	Resurs F21 Resurs 500 Resurs O1-0 is Cosmos 1484 Resurs O1-1 is Cosmos 1689 Resurs O1-2 is Cosmos 1939 Resurs O1-3 Resurs O1-4


Resurs F1's specifications

Prime contractor	KB Photon
Platform	modified Vostok
Mass at launch	?
Diameter	?
Stabilization	3-axis


Resurs F2's specifications

Prime contractor	KB Photon
Platform	modified Vostok
Mass at launch	6.5 t (capsule 2.5 t)
Diameter	2.3 m
Stabilization	3-axis


Resurs F2's payload

KFA 1000 film camera system

Wavebands	0.57-0.67 µm (visible) 0.67-0.8 µm (near IR)
Resolution	5-10 m
Swath width	60 km
KATE 200

Wavebands	0.5-0.6, 0.6-0.7, 0.7-0.9 µm (visible/near IR)
Resolution	15-30 m
Swath width	180 km

Also equipped with an LK 1000 camera and a MK 4 camera


Resurs O's specifications

Prime contractor	VNII Elektromekaniki
Mass at launch	1950 kg
Payload mass	550 kg
Dimensions	6 m long x 1.4 m diameter
Solar array	10 m
Stabilization	3-axis
Lifetime	2 years


Resurs O's payload

MSU-M (low resolution - visible and IR)

Wavebands	0.5-0.6 µm, 0.6-0.7 µm, 0.7-0.8 µm, 0.8-1.0 µm
MSU-S (medium resolution - visible and IR)

Wavebands	0.58-0.7 µm, 0.7-1.0 µm
MSU-SK (5-channel visible and IR scanner)

Wavebands	0.5-0.6 µm, 0.6-0.7 µm, 0.7-08 µm, 0.8-1.0 µm, 10.4-12.6 µm
Resolution	150 m (4 channels), 600 m (1 channel)
Swath width	600 km
MSU-E (3-channel steerable push-broom scanner)

Wavebands	0.5-0.67 µm, 0.65-0.8 µm, 0.8-1.0 µm
Resolution	30 m
Swath width	85 km
FRAGMENT (8-channel TV camera)

Wavebands	0.4-2.1 µm


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 Resurs F01

General

Designation	20006 / 89038A
Launch date	25 May 1989
Country of origin	CIS
Mission	Remote sensing (F2)
Perigee/Apogee	174/232 km
Inclination	82.3°
Period	88.6 min
Launch vehicle	Soyuz
Launch site	Plesetsk

Carried two Pion subsatellites aimed to air density research which were released. They were built by students at the Korolev Aviation Institute in Kubyshev.

End of life

Decay	17 Jun 1989
Subsatellites

PION 1 (20056 / 89038C) decayed on 23 Jul 1989

PION 2 (20060 / 89038D) decayed on 24 Jul 1989

Technical data

Specifications

Payload


 Resurs F02

General

Designation	20095 / 89049A
Launch date	27 Jun 1989
Country of origin	CIS
Mission	Remote sensing (F1)
Perigee/Apogee	255/269 km
Inclination	82.6°
Period	89.8 min
Launch vehicle	Soyuz
Launch site	Tyuratam
End of life

Decay	11 Jul 1989
Technical data

Specifications


 Resurs F03

General

Designation	20134 / 89055A
Launch date	18 Jul 1989
Country of origin	CIS
Mission	Remote sensing (F2)
Perigee/Apogee	178/214 km
Inclination	82.6°
Period	88.4 min
Launch vehicle	Soyuz
Launch site	Plesetsk

Carried two Pion air density subsatellites

End of life

Decay	8 Aug 1989
Subsatellites

PION 1 (20160 / 89055C) decayed on 19 Sep 1989

PION 2 (20161 / 89055D) decayed on 19 Sep 1989

Technical data

Specifications

Payload


 Resurs F04

General

Designation	20175 / 89063A
Launch date	15 Aug 1989
Country of origin	CIS
Mission	Remote sensing (F2)
Perigee/Apogee	178/226 km
Inclination	82.3°
Period	88.5 min
Launch vehicle	Soyuz
Launch site	Tyuratam
End of life

Decay	14 Sep 1989
Technical data

Specifications

Payload


 Resurs F05

General

Designation	20222 / 89073A
Launch date	6 Sep 1989
Country of origin	CIS
Mission	Remote sensing (F1)
Perigee/Apogee	176/229 km
Inclination	82.3°
Period	88.6 min
Launch vehicle	Soyuz
Launch site	Plesetsk

Carried CAMEX (Carrier for Microgravity Experiment), a German experiment for Kayser Threde

End of life

Decay	22 Sep 1989
Technical data

Specifications


 Resurs F06

General

Designation	20632 / 90047A
Launch date	29 May 1990
Country of origin	CIS
Mission	Remote sensing (F1)
Perigee/Apogee	175/231 km
Inclination	82.4°
Period	88.6 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	14 Jun 1990
Technical data

Specifications


 Resurs F07

General

Designation	20687 / 90060A
Launch date	17 Jul 1990
Country of origin	CIS
Mission	Remote sensing (F2)
Perigee/Apogee	177/236 km
Inclination	82.3°
Period	88.6 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	16 Aug 1990
Technical data

Specifications

Payload


 Resurs F08

General

Designation	20754 / 90073A
Launch date	16 Aug 1990
Country of origin	CIS
Mission	Remote sensing (F1)
Perigee/Apogee	176/229 km
Inclination	82.3°
Period	88.5 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	1 Sep 1990
Technical data

Specifications


 Resurs F09

General

Designation	20794 / 90082A
Launch date	7 Sep 1990
Country of origin	CIS
Mission	Remote sensing (F1)
Perigee/Apogee	177/238 km
Inclination	82.5°
Period	88.7 min
Launch vehicle	Soyuz
Launch site	Plesetsk

Carried a German experiment

End of life

Decay	21 Sep 1990
Technical data

Specifications


 Resurs F10

General

Designation	21313 / 91035A
Launch date	21 May 1991
Country of origin	CIS
Mission	Remote sensing (F2)
Perigee/Apogee	178/242 km
Inclination	82.3°
Period	88.7 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	20 Jun 1991
Technical data

Specifications

Payload


 Resurs F11

General

Designation	21524 / 91044A
Launch date	28 Jun 1991
Country of origin	CIS
Mission	Remote sensing (F2)
Perigee/Apogee	253/268 km
Inclination	82.3°
Period	89.7 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	21 Jul 1991
Technical data

Specifications

Payload


 Resurs F12

General

Designation	21611 / 91052A
Launch date	23 Jul 1991
Country of origin	CIS
Mission	Remote sensing (F1)
Perigee/Apogee	178/230 km
Inclination	82.4°
Period	88.6 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	8 Aug 1991
Technical data

Specifications


 Resurs F13

General

Designation	21664 / 91058A
Launch date	21 Aug 1991
Country of origin	CIS
Mission	Remote sensing (F2)
Perigee/Apogee	178/240 km
Inclination	82.3°
Period	88.7 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	20 Sep 1991
Technical data

Specifications

Payload


 Resurs F14

General

Designation	21951 / 92024A
Launch date	29 Apr 1992
Country of origin	CIS
Mission	Remote sensing (F2)
Perigee/Apogee	225/230 km
Inclination	82.1°
Period	89.1 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	29 May 1992
Technical data

Specifications

Payload


 Resurs F15

General

Designation	21998 / 92033A
Launch date	23 Jun 1992
Country of origin	CIS
Mission	Remote sensing (F1)
Perigee/Apogee	177/226 km
Inclination	82.3°
Period	88.5 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	9 Jul 1992
Technical data

Specifications


 Resurs F16

General

Designation	22093 / 92056A
Launch date	19 Aug 1992
Country of origin	CIS
Mission	Remote sensing (F2)
Perigee/Apogee	178/226 km
Inclination	82.6°
Period	88.6 min
Launch vehicle	Soyuz
Launch site	Plesetsk

Two passive Pion crafts were released on 1st September. Tracking of their decay will allow studies of atmospheric density and radar calibration.

End of life

Decay	4 Sep 1992
Subsatellites

PION 1 (22099 / 92056C) decayed on 25 Sep 1992

PION 2 (22100 / 92056D) decayed on 24 Sep 1992

Technical data

Specifications

Payload


 Resurs F17

General

Designation	22663 / 93033A
Launch date	21 May 1993 at 09:20 UT
Country of origin	CIS
Mission	Remote sensing (F2)
Perigee/Apogee	176/255 km
Inclination	82.6°
Period	88.8 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	20 Jun 1993
Technical data

Specifications

Payload


 Resurs F18

General

Designation	22696 / 93040A
Launch date	25 Jun 1993 at 08:20 UT
Country of origin	CIS
Mission	Remote sensing (F1)
Perigee/Apogee	173/240 km
Inclination	82.6°
Period	88.6 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	12 Jul 1993
Technical data

Specifications


 Resurs F19

General

Designation	22777 / 93053A
Launch date	24 Aug 1993 at 10:45 UT
Country of origin	CIS
Mission	Remote sensing (F1)
Perigee/Apogee	174/236 km
Inclination	82.6°
Period	88.6 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	10 Sep 1993
Technical data

Specifications


 Resurs F20

General

Designation	23672 / 95050A
Launch date	26 Sep 1995 at 11:20 UT
Country of origin	CIS
Mission	Remote sensing (F2)
Perigee/Apogee	231/233 km
Inclination	82.3°
Period	89 min
Launch vehicle	Soyuz
Launch site	Plesetsk LC43-4
Mass at launch	~6000 kg

Would be the last Resurs F mission

End of life

Cause	Normal end of mission
Decay	26 Oct 1995
Technical data

Specifications

Payload


 Resurs F21

Also called Resurs F1M

General

Designation	25059 / 97072A
Launch date	17 Nov 1997
Country of origin	CIS
Mission	Remote sensing (F1M?)
Perigee/Apogee	208/243 km
Inclination	82.3°
Period
Launch vehicle	Soyuz
Launch site	Plesetsk
Mass at launch	6300 kg

It is unknown what type of satellite this is exactly, if it is a F1 or F2 or a new model.

Might be equipped of 2 KFA-3000 cameras with 5 to 8 m resolution and a multispectral camera KATE-200 with 10 to 12 m resolution.


 Resurs 500

Also called Zvezda Kolumba which means "Columbus Star"

General

Designation	22217 / 92075A
Launch date	15 Nov 1992 at 21:50 UT
Country of origin	CIS
Mission
Perigee/Apogee	177/237 km
Inclination	82.6°
Period	88.6 min
Launch vehicle	Soyuz
Launch site	Plesetsk

Carries objects and messages. After a 6 day flight the capsule decayed in the Pacific. It was then moved to Seattle for thanksgiving Day. This mission is called Europe-America Space Flight 500. It celebrates the international space year, the 500th anniversary of the new world's discovery and must start a cooperation between US and Russia.

Resurs F1 type

End of life

Decay	22 Nov 1992


 Resurs O1-3

General

Designation	23342 / 94074A
Launch date	4 Nov 1994 at 05:46 UT
Country of origin	CIS
Mission	Remote sensing
Perigee/Apogee	660/663 km
Inclination	98°
Cycle	21 days
Period	98 min
Launch vehicle	Zenit

Carried Safir R1. The payload costed DM 6 million (half financed by DARA)

External resources

http://www.eurimage.it/Products/RESURS_O1.html

Technical data

Specifications

Payload

Downlink: 8.192 GHz, 7.68 mbps


 Resurs O1-4

General

Designation	25394 / 98043A
Launch date	10 Jul 1998
Country of origin	CIS
Mission	Remote sensing
Perigee/Apogee	815 / 818 km
Inclination	98.8°
Period	101.2 min
Launch vehicle	Zenit #29

Also carries a LLMSIRIS payload.

In mid-Apr 1999 it is known that a transmitter (8.2 GHz?) has failed.

External resources

http://www.eurimage.it/Products/RESURS_O1.html

http://www.lmd.ens.fr/~raberant/english/home.htm

Technical data

Specifications

Prime contractor
Platform
Mass at launch	1950 kg
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime

Downlinks at 137.40 MHz & APT on 137.85 MHz

MSU-SK (5-channel visible and IR scanner)

Wavebands	0.5-0.6 µm, 0.6-0.7 µm, 0.7-08 µm, 0.8-1.0 µm, 10.4-12.6 µm + a 6th one
Resolution	161 m (4 channels), 528 m (1 channel)
Swath width	714 km
MSU-E (3-channel steerable push-broom scanner)

Wavebands	0.5-0.67 µm, 0.65-0.8 µm, 0.8-1.0 µm
Resolution	30 m
Swath width	60 km

Downlink: 8.2 GHz, 16 mbps

Scarab 2 (Scanner for Radiation Budget)

Telescopes wavebands	0.2 - 4 µm (solar reflections) 4 - 100 µm (earth IR) 10.5 - 12.5 µm (IR) 0.5 - 0.7 µm (visible)

40 kg. Scarab 2's flight has been paid for by the CNES. Should have 2 years of lifetime


 RS 15

Also called Radio-Rosto (Rosto is an acronyme for Russian Defense, Sports, and Technical Organization)

General

Designation	23439 / 94085A
Launch date	26 Dec 1994
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1881/2163 km
Inclination	64.8°
Period	128 min
Launch vehicle	Rokot #1

All the electronics onboard the satellite was designed and built by a group of Radio Amateurs from the town of Kaluga (180 km SW of Moscow) under the leaderships of Aleksander Papkov. The work was coordinated and supervised by NILAKT POSTO (aero-cosmic laboratory), Moscow, under the direction of Valentin Yamnikov. Full control of RS 15 as well as RS 10/11 and RS 12/13 is implemented by the RS3A control station at Moscow (headed by Leonid Maksakov).

RS-15 suffered from power supply problems, as it goes off almost immediately upon entering earth eclipse, not to return until is 'sees' sunlight again.

Contact

RS3A

PO Box 59, Moscow 105122, Russia

Fax: +7-095-916-2949

Email: rsgroup@olymp.msk.su

Packet: RS3A @ RS3A.MSK.RUS.EU

Technical data

Specifications

Prime contractor
Platform	similar to RS 3 to 8 satellites
Mass at launch	70 kg
Mass in orbit
Diameter	1 m (spherical-like)
Solar array
Stabilization	none
DC power
Design lifetime

On board the satellite, there is a Mode A transponder and two CW beacons, one of which consists of a broadcast bulletin board with 2 kilobytes of storage space. A remote control system and telemetry system also exist on the satellite. RS 15 does not have not orientation or attitude stabilization systems.

Transponders

Beacons	29.3525 MHz (0.4 - 1.2 W) 29.3987 MHz (0.4 - 1.2 W)
Uplink	145.858 - 145.898 MHz (approx. 100 W EIRP)
Downlink	29.354 - 29.394 MHz (up to 5 W)

RS 15 lost its beacon in June 1998, however the transponder remains on and working.


 Program: Sputnik

Soviet experimental program


Program: Sputnik

Sputnik 01

Sputnik 02

Sputnik 03

Sputnik 04

Sputnik 05

Sputnik 06

Sputnik 07

Sputnik 09

Sputnik 10

Sputnik 40

Sputnik 41

Sputnik 99


 Sputnik 01

Also called PS 1

General

Designation	00002 / 57001B
Launch date	4 Oct 1957
Country of origin	CIS
Mission	Scientific: ionosphere study
Perigee/Apogee	227/945 km
Inclination	65°
Period	96.1 min
Launch vehicle	Semiorka A (8K71PS)
Launch site	Tyuratam

First satellite ever launched

Sphere made of aluminum of 58 cm diameter with 4 antennas. Its 2 radio transmitters send signals during 21 days. It enabled propagation and ionospherical studies.

End of life

Decay	3 Jan 1958
Technical data

Specifications

Prime contractor
Platform
Mass at launch	83.6 kg
Mass in orbit
Dimension	58 cm diameter
Solar array
Stabilization
DC power
Design lifetime

Frequencies: 20.005 & 40.002 MHz


 Sputnik 02

General

Designation	00003 / 57002A
Launch date	3 Nov 1957
Country of origin	CIS
Mission	Scientific: Sun observation
Perigee/Apogee	225/1670 km
Inclination	65.3°
Period	103.7 min
Launch vehicle	Semiorka A
Launch site	Tyuratam
Mass at launch	508.3 kg

1.2 m high cone that carried Laika (a dog) the first living creature in Space. Also studied X-rays and UV radiations from the Sun. The dog died after a few days.

End of life

Decay	14 Apr 1958
Technical data

Specifications

Prime contractor
Platform
Mass at launch	508 kg
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime

Frequencies: 20.005 & 40.002 MHz (Tral-D TM system)

The satellite also featured a slow-scan TV camera (100 lines per frame, 10 frames per second), which relayed images to the ground.

There was also a spectrophotometer for UV (1216 A) and Soft-X-rays (1-120 A) using a photomultiplier tube and a filterwheel. This instrument sent data through a commutated telemetry channel. The instrument was designed by the St. Peterburg physicist A. Jefremov under the direction of Academicians A. Lebedev and S. Mandelstam.


 Sputnik 03

General

Designation	00008 / 58004B
Launch date	15 May 1958
Country of origin	CIS
Mission	Scientific: ionosphere study
Perigee/Apogee	217/1.864 km
Inclination	65.2°
Period	106 min
Launch vehicle	Semiorka (R7) A
Launch site	Tyuratam
Mass at launch	1327 kg (payload: 970 kg)
End of life

Decay	6 Apr 1960


 Sputnik 04

General

Designation	00034 / 60005A
Launch date	15 May 1960
Country of origin	CIS
Mission
Perigee/Apogee	284/514 km
Inclination	65°
Period	92.5 min
Launch vehicle	Vostok L
Launch site	Tyuratam
End of life

Decay	5 Sep 1962


 Sputnik 05

General

Designation	00055 / 60011A
Launch date	19 Aug 1960
Country of origin	CIS
Mission
Perigee/Apogee	281/340 km
Inclination	64.6°
Period	90.7 min
Launch vehicle
Launch site	Tyuratam
End of life

Decay	20 Aug 1960


 Sputnik 06

General

Designation	00065 / 60017A
Launch date	1 Dec 1960
Country of origin	CIS
Mission
Perigee/Apogee	123/269 km
Inclination	65°
Period	88.4 min
Launch vehicle
Launch site	Tyuratam
End of life

Decay	2 Dec 1960


 Sputnik 07

General

Designation	00071 / 61002A
Launch date	4 Feb 1961
Country of origin	CIS
Mission
Perigee/Apogee	212/318 km
Inclination	64.9°
Period	89.8 min
Launch vehicle
Launch site	Tyuratam
End of life

Decay	26 Feb 1960


 Sputnik 09

General

Designation	00091 / 61008A
Launch date	9 Mar 1961
Country of origin	CIS
Mission
Perigee/Apogee	173/239 km
Inclination	64.9°
Period	88.6 min
Launch vehicle
Launch site	Tyuratam

Vostok 1 repetition

End of life

Decay	9 Mar 1961


 Sputnik 10

General

Designation	00095 / 61009A
Launch date	25 Mar 1961
Country of origin	CIS
Mission
Perigee/Apogee	175/175 km
Inclination	64.9°
Period	88.6 min
Launch vehicle
Launch site	Tyuratam

Vostok 1 repetition

End of life

Decay	25 Mar 1961


 Sputnik 40

Also called PS 2 or Sputnik Jr or RS 17

General

Designation	24958 / 97058C
Launch date	3 Nov 1997 at 04:05 UT
Country of origin	CIS
Mission	Technology
Perigee/Apogee	383/391 km
Inclination	51.6°
Period
Launch vehicle	none
Launch site	Mir space station

1/3 model of Sputnik 01  The model was built by high school students in the republic of Kabardin-Balakarsk in the Russian Federation, in the Caucasus near Chechnya.  The radio transmitter payload was built by students on Reunion island, a French territory in the Indian Ocean.

Frequency: 145.820 MHz

End of life

Out of service	29 Dec 1997
Cause	stopped transmitting
Decay
External resources

http://www.ccr.jussieu.fr/physio/Satedu/sputnik40.html


 Sputnik 41

Also called RS 18

General

Designation	25533 / 98062C
Launch date	10 Nov 1998
Country of origin	CIS
Mission	Technology
Perigee/Apogee
Inclination
Period
Launch vehicle	none
Launch site	Mir space station

1/3 scale replica of Sputnik 01

End of life

Out of service	11 Dec 1998
Cause	batteries exhausted
Decay
External resources

http://www.ccr.jussieu.fr/physio/Satedu/sputnik41.html

Technical data

Specifications

Prime contractor
Platform
Mass at launch	4 kg
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime	2 months (lifetime of batteries)

A 200 mW transmitter is located in the satellite, transmitting on the radioamateur 144 MHz (2 m) band using FM modulation. The frequency is 145,812 MHz.

The beacon will send two pre recorded messages in three languages, one recording of the "beep-beep". The frequency of the tone will translate the satellite internal temperature.


 Sputnik 99

General

Designation	25685 / 99015C
Launch date	16 Apr 1999 at approx 10:30 UT
Country of origin	CIS
Mission	Technology
Perigee/Apogee	340 km
Inclination	51.7°
Period	91 min
Launch vehicle	none
Launch site	Mir space station

Sputnik 99 is at the center of a controversy over use of the amateur radio band. The satellite was developed by AMSAT-F and AMSAT-R the French  and Russian amateur radio satellite groups, with help from the Russian Space Agency's flight control center, TsUP.  Apparently TsUP made the mistake of arranging with Swatch, a commercial company for messages to be broadcast from the satellite including a trademarked advertising slogan, a flagrant misuse of the amateur radio band. After numerous protests, it was decided before launch to launch the satellite without its batteries, turning it into a passive piece of junk.


 Start 1

General

Designation	22561 / 93014A
Launch date	25 Mar 1993
Country of origin	CIS
Mission	Test
Perigee/Apogee	680/968 km
Inclination	75.8°
Period	101.4 min
Launch vehicle	Start #1


 Program: Statsionar

Soviet denomination for geostationary slots reservation used by Raduga and Gorizont satellites.

The "Express" denomination is used for the Express program.


Program: Statsionar

Statsionar-01, 75°E Statsionar-02, 35°E Statsionar-03, 85°E Statsionar-04, 14°W Statsionar-05, 53°E Statsionar-06, 90°E Statsionar-07, 140°E Statsionar-08, 25°W Statsionar-09, 45°E Statsionar-10, 170°W	Statsionar-11, 11°W Statsionar-12, 40°E Statsionar-13, 80°E Statsionar-14, 96.5°E Statsionar-15, 127°E Statsionar-16, 145°E Statsionar-17, 26.5°W Statsionar-18, 8°E Statsionar-19, 23°E Statsionar-20, 70°E	Statsionar-21, 103°E Statsionar-22, 1°E Statsionar-23, 15°E Statsionar-24, 49°E Statsionar-25, 37.5°W Statsionar-26, 155°W Statsionar-27, 12°E


 Statsionar-01

Location: 75°E

Begin	End	Satellite
22 Dec 1975		Raduga 01


 Statsionar-02

Location: 35°E

Begin	End	Satellite
11 Sep 1976		Raduga 02
23 Jul 1977		Raduga 03
18 Jul 1978		Raduga 04
20 Feb 1980		Raduga 06
18 Mar 1981		Raduga 08
9 Oct 1981		Raduga 10
26 Nov 1982		Raduga 11
15 Feb 1984		Raduga 14
15 Nov 1985		Raduga 17
20 Oct 1988	?	Raduga 22
19 Dec 1991	Apr 1999	Raduga 28
Mar 1999		Raduga 1-4


 Statsionar-03

Location: 85°E

Begin	End	Satellite
25 Apr 1979		Raduga 05
8 Apr 1983		Raduga 12
19 Mar 1987		Raduga 20
20 Dec 1990	< Feb 1995	Raduga 26
30 Sep 1993		Raduga 30


Statsionar-04
 Statsionar-04 / Loutch-02 / Express-02

Location: 14°W

Begin	End	Satellite
14 Jun 1980		Gorizont 04
30 Mar 1988		Gorizont 15
20 Jun 1990	Mar 1995	Gorizont 20
13 Oct 1994		Express 1


Statsionar-05
 Statsionar-05 / Express-05

Location: 53°E

Begin	End	Satellite
19 Dec 1978		Gorizont 01
6 Jul 1979		Gorizont 02
28 Dec 1979		Gorizont 03
22 Apr 1984		Gorizont 09
18 Jan 1985		Gorizont 11
26 Jan 1989	? moved	Gorizont 17
22 Nov 1992	Jul 1996	Gorizont 27
Jul 1996		Gorizont 32


Statsionar-06
 Statsionar-06 / Loutch-03 / Express-07

Location: 90°E

Begin	End	Satellite
30 Nov 1983		Gorizont 08
18 Nov 1986		Gorizont 13
3 Nov 1990		Gorizont 21
28 Oct 1993		Gorizont 28


Statsionar-07
 Statsionar-07 / Loutch-04 / Express-10

Location: 140°E

Begin	End	Satellite
11 May 1987		Gorizont 14
6 Jul 1989		Gorizont 18
mid-April 1996		Gorizont 22


 Statsionar-08

Location: 25°W

Begin	End	Satellite
5 Oct 1980		Raduga 07
17 Jan 1986		Raduga 18
14 Apr 1989	Jul 1995	Raduga 23


 Statsionar-09

Location: 45°E

Begin	End	Satellite
25 Aug 1983		Raduga 13
8 Aug 1985		Raduga 16
15 Dec 1989	?	Raduga 24
18 Feb 1994	Jul 1995	Raduga 31
Sep 1995	Jul 1996	Raduga 23
May 1999		Raduga 28


 Statsionar-10

Location: 170°W

Begin	End	Satellite
20 Oct 1982		Gorizont 06
25 Oct 1986		Raduga 19
?	Dec 1997	Raduga 21


Statsionar-11
 Statsionar-11 / Loutch-06 / Express-03

Location: 11°W

Begin	End	Satellite
30 Jun 1983		Gorizont 07
15 Jul 1992		Gorizont 26


Statsionar-12
 Statsionar-12 / Loutch-07 / Express-04

Location: 40°E

Begin	End	Satellite
10 Jun 1986		Gorizont 12
23 Nov 1990	Jan 1996	Gorizont 22
Feb 1996		Gorizont 31


Statsionar-13
 Statsionar-13 / Loutch-08 / Express-06

Location: 80°E

Begin	End	Satellite
1 Aug 1984		Gorizont 10
18 Aug 1988		Gorizont 16
23 Oct 1991	Mar 1998	Gorizont 24
26 Sep 1996		Express 2


Statsionar-14
 Statsionar-14 / Loutch-09 / Express-08

Location: 96.5°E

Begin	End	Satellite
15 Mar 1982		Gorizont 05
28 Sep 1989		Gorizont 19
Aug 1996	Nov 1998	Gorizont 27
Sep 1998	Feb 1999	Gorizont 20


 Statsionar-15

Location: 128°E

Begin	End	Satellite
22 Jun 1984		Raduga 15
10 Dec 1987	? moved	Raduga 21
28 Feb 1991	Aug 1998	Raduga 27


Statsionar-16
 Statsionar-16 / Loutch-10 / Express-11

Location: 145°E

Begin	End	Satellite
		Gorizont 21


 Statsionar-17

Location: 26.5°W

Begin	End	Satellite


 Statsionar-18

Location: 8°E

Begin	End	Satellite


 Statsionar-19

Location: 23°E

Begin	End	Satellite


 Statsionar-20

Location: 70°E

Begin	End	Satellite
21 Jun 1989	early 1997	Raduga 1-1
15 Feb 1990	Mar 1995	Raduga 25
28 Dec 1994		Raduga 32


Statsionar-21
 Statsionar-21 / Loutch-05 / Express-09

Location: 103°E

Begin	End	Satellite
2 Jul 1991		Gorizont 23
2 Apr 1992		Gorizont 25


 Statsionar-22

Location: 1°E

Begin	End	Satellite


 Statsionar-23

Location: 15°E

Begin	End	Satellite


 Statsionar-24

Location: 49°E

Begin	End	Satellite
22 Jun 1989	?	Raduga 24
27 Dec 1990	Jul 1996	Raduga 1-2
5 Feb 1994		Raduga 1-3


Statsionar-25
 Statsionar-25 / Express-01

Location: 37.5°W

Begin	End	Satellite


Statsionar-26
 Statsionar-26 / Express-12

Location: 155°W

Begin	End	Satellite


 Statsionar-27

Location: 12°E

Begin	End	Satellite
?	Aug 1998	Raduga 22
25 Mar 1993		Raduga 29


 Program: Tselina

Russian SIGINT program started in October 1967. It is composed of several generations

1st generation

From 1967 to march 1982 40 satellites of the first generation were launched from Plesetsk onboard Cosmos rockets. The network was composed of 4 satellites on 45° distant planes.

Specifications overview:

Prime contractor
Platform
Mass	900 kg
Dimension	2 m high x 1 m diameter
Perigee/Apogee	circular orbit, 500-550 km
Inclination	74°
Orbital cycle	15 revolutions = 1 day
Design lifetime

Satellites:

Cosmos 0189	Cosmos 0200	Cosmos 0250	Cosmos 0269	Cosmos 0315	Cosmos 0330
Cosmos 0358	Cosmos 0387	Cosmos 0395	Cosmos 0425	Cosmos 0436	Cosmos 0437
Cosmos 0460	Cosmos 0479	Cosmos 0500	Cosmos 0536	Cosmos 0544	Cosmos 0549
Cosmos 0582	Cosmos 0610	Cosmos 0631	Cosmos 0655	Cosmos 0661	Cosmos 0698
Cosmos 0707	Cosmos 0749	Cosmos 0781	Cosmos 0787	Cosmos 0790	Cosmos 0812
Cosmos 0845	Cosmos 0870	Cosmos 0899	Cosmos 0924	Cosmos 0960	Cosmos 1008
Cosmos 1062	Cosmos 1114	Cosmos 1215	Cosmos 1345
2nd generation

From Dec 1970 to Feb 1983 35 second generation satellites were launched from Plesetsk by Vostok vehicles. When operational the network was composed of 6 satellites orbiting in 60° apart planes.

Specifications overview:

Prime contractor
Platform
Mass	2500 kg
Dimension	5 m high x 1.5 m diameter
Perigee/Apogee	circular, 650 km
Inclination	81.2°
Orbital cycle
Design lifetime

Rainer Kracht reports a standard magnitude of 5.44 +/- 0.02 for those satellites.

Satellites:

Cosmos 0389	Cosmos 0405	Cosmos 0476	Cosmos 0542	Cosmos 0604	Cosmos 0673
Cosmos 0744	Cosmos 0756	Cosmos 0808	Cosmos 0851	Cosmos 0895	Cosmos 0925
Cosmos 0955	Cosmos 0975	Cosmos 1005	Cosmos 1043	Cosmos 1063	Cosmos 1077
Cosmos 1093	Cosmos 1116	Cosmos 1143	Cosmos 1145	Cosmos 1154	Cosmos 1184
Cosmos 1206	Cosmos 1222	Cosmos 1242	Cosmos 1271	Cosmos 1315	Cosmos 1340
Cosmos 1346	Cosmos 1356	Cosmos 1400	Cosmos 1437	Cosmos 1441
3rd generation - Tselina D

From Jun 1983 to Apr 1993 37 satellites of the third generation were launched by Cyclone 3 rockets from Plesetsk. When operational the network was composed of 6 satellites orbiting in 60° apart planes.

Specifications overview:

Prime contractor
Platform
Mass	2200 kg
Dimension	5 m high x 1.5 m diameter
Perigee/Apogee	635/665 km
Inclination	82.5°
Orbital cycle	44 revolutions = 3 days
Design lifetime

Those satellites are also known as Tselina-D or Ferret D. They could have a beacon at 51.140 and 51.160 MHz. Rainer Kracht reports a standard magnitude of 5.21 +/- 0.04 for those satellites.

Satellites:

Cosmos 1025	Cosmos 1300	Cosmos 1328	Cosmos 1378	Cosmos 1408	Cosmos 1455
Cosmos 1470	Cosmos 1515	Cosmos 1536	Cosmos 1544	Cosmos 1606	Cosmos 1626
Cosmos 1633	Cosmos 1666	Cosmos 1674	Cosmos 1703	Cosmos 1707	Cosmos 1726
Cosmos 1733	Cosmos 1743	Cosmos 1758	Cosmos 1782	Cosmos 1805	Cosmos 1812
Cosmos 1825	Cosmos 1842	Cosmos 1862	Cosmos 1892	Cosmos 1908	Cosmos 1933
Cosmos 1953	Cosmos 1975	Cosmos 2058	Cosmos 2151	Cosmos 2221	Cosmos 2228
Cosmos 2242
4th generation - Tselina 2

In 1983 a new generation was started named Tselina 2. Those heavy satellites are launched by Zenit 2 vehicles except the 2 first satellites launched on Proton. The satellites are placed on 4 planes spaced 45° apart. The system went operational with Cosmos 2227 in Dec 1992.

Specifications overview:

Prime contractor	NPO Yuzhnoye
Platform
Mass	~9000 kg
Dimension
Perigee/Apogee	850 km
Inclination	71°
Orbital cycle
Design lifetime	3 years

Telemetry for those satellites could be around 166 MHz

Satellites:

Cosmos 1603	Cosmos 1656	Cosmos 1697	Cosmos 1714	Cosmos 1833	Cosmos 1844
Cosmos 1943	Cosmos 1980	Cosmos 2082	Cosmos 2219	Cosmos 2227	Cosmos 2237
Cosmos 2263	Cosmos 2278	Cosmos 2297	Cosmos 2322	Cosmos 2333	Cosmos 2360


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 Program: Tsikada

Means cicada

Russian navigation program operational since April 1979 (deployment started in late-1976). The satellites composing this system based on the Tsikada bus. This bus carries the Tsikada navigation transponders and optional secondary payloads, e.g. RS, etc. The Cospas (Nadezhda) package is carried as this secondary payload on some satellites.

Lately the satellites are known as Nadezhda when they carry a Cospas receiver or part of Cosmos. A new generation is known as Kurs or Nadezhda M has just started and the satellites are in the Cosmos program (since it is still experimental). This generation is an new implementation of some equipment which can switch (on ground command) between two modes. The standard mode is Cospas for search and rescue. The other mode is the Kurs geolocation/data store-forward mode. The first use of this hardware was on Cosmos 2315. It was designed by Moscow's space instrumentation institute.

The system is based on 4 planes separated by 45° covering space in order to complete the Parus system.

Occupation of the planes

Plane 11	Plane 12	Plane 13	Plane 14
Cosmos 0883	Cosmos 0926	Cosmos 1000	Cosmos 1092
Cosmos 1168	Cosmos 1304	Cosmos 1226	Cosmos 1339
Cosmos 1383	Cosmos 1506	Cosmos 1447	Cosmos 1574
Cosmos 1553	Cosmos 1727	Cosmos 1655	Cosmos 1816
Cosmos 1791	Cosmos 1861	Cosmos 2123	Nadezhda 2
Nadezhda 1	Nadezhda 3	Tsikada 1	Nadezhda 4
Cosmos 2181			Nadezhda 5
Cosmos 2230
Cosmos 2315
Note: Cosmos 1380 failed to replace Cosmos 1168 in 1982 (placed on a wrong orbit)

The satellites of this program are based on the Musson bus (see Parus for details).

Those satellites downlink at 150.000/400.000 MHz.


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Program: Tsikada

Tsikada 1


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 Tsikada 1

General

Designation	23463 / 95002A
Launch date	24 Jan 1995 at 03:54 UT
Country of origin	CIS
Mission	Navigation
Perigee/Apogee	965/1020 km
Inclination	82.9°
Period
Launch vehicle	Cosmos C
Launch site	Plesetsk
Technical data

Downlink frequencies: 150 & 400 MHz

Plane 13


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 Launch vehicles

Section directed by Jean-Jacques Serra

A:	Ariane	ASLV	Athena	Atlas
B:	Black Arrow
C:	Cyclone	Conestoga	Cosmos B	Cosmos C
D:	Delta	Diamant
H:	H1 & H2
I:	ISAS vehicles	ISRO vehicles
L:		Long March
M:	Molniya	Mu
N:	N1 & N2	NASDA vehicles
P:	Pegasus	Proton	PSLV
R:	Rokot
S:	Scout	Semiorka	Shavit	SLV 3	Soyuz	Start	STS
T:	Taurus	Thor	Titan
V:	Vanguard	VLS
Z:	Zenit
World Launch Vehicle Overview

Vehicle	First launch	LEO capacity (kg)	GTO capacity (kg)	Comments
CIS (Sheldon / DoD)				Detailed soviet chart here
Semiorka (A / SL1)	4 Oct 1957	1300		2-stage (--> 1958)
Luna (A1 / SL2)	(Aug 1958) 2 Jan 1959			3-stage (--> 1960)
Vostok (A1 / SL3)	15 May 1960	4700		3-stage
Molniya (A2e / SL6)	(10 Oct 1960) 4 Feb 1961		1600 (THEO)	4-stage, Molniya or Prognoz orbit
Cosmos B (B1 / SL7)	16 Mar 1962	450		2-stage (--> 1977), 144 launches
Voskhod (A2 / SL4)	16 Nov 1963	5500		3-stage
Cosmos C (C1 / SL8)	18 Aug 1964	1400		2-stage
Proton (D / SL9)	16 Jul 1965	12500		2-stage (--> 1968)
Cosmos (F1r / SL11)	17 Sep 1966			2-stage (--> 1971)
Soyuz (A2 / SL4)	28 Nov 1966	7500		3-stage
Proton (D1e / SL12)	10 Mar 1967		4600 (GEO)	4-stage
Cyclone 2 (F1m / SL11)	27 Oct 1967	4000		2-stage
N1 (G / SL15?)	(21 Feb 1969)			Lunar vehicle launcher
Proton (D1 / SL13)	16 Nov 1968	20000		3-stage
Cyclone 3 (F2 / SL14)	24 Jun 1977	5500		3-stage
Zenit (J1 / SL16)	21 Jun 1985	15000		2-stage
Energia (K1 / SL17)	15 May 1987	140000	18000 (GEO)	shuttle, 2 successful flights
Start	25 Mar 1993	500		5-stage
Rokot	26 Dec 1994	1850		3-stage (RS18K)
Shtil	7 Jul 1998			3-stage, converted R-29RM (RSM-54), submarine launch
Dnepr	21 Apr 1999	3000		2-stage, converted SS-18 (R-36M2 / 15A18M)
Strela	2000?			Redived from the UR-100N, launch from Svobodny
Angara 1	2000			Breeze KM or Bloc 1 top stage. To replace Cosmos 3 and Cyclone 3 launchers
Angara 3	2003			Breeze M top stage / launch from Plesetsk
Angara 4E	2005			heavy launcher / launch from Plesetsk
United States
Vanguard	(6 Dec1957) 17 Mar 1958	25		3-stage (--> 1959), 3 successful flights
Juno 1	31 Jan 1958	40		4-stage (--> 1959)
Thor Able	(17 Aug 1958) 11 Oct 1958	200		3-stage (--> Thor Delta)
Juno 2	6 Dec 1958	50		4-stage (--> 1961)
Atlas	18 Dec 1958	1300		Mercury launcher
Thor Agena	28 Feb 1959	1000		2-stage (--> LTT Agena)
Atlas Able	(26 Nov 1959)			3-stage (--> 1960)
Atlas Agena	(26 Feb 1960) 24 May 1960	2300		2-stage (--> 1978)
Thor Ablestar	13 Apr 1960			2-stage (--> 1965)
Thor Delta	(13 May 1960) 18 Aug 1960			3-stage, (--> Delta)
Scout	(4 Dec 1960) 16 Feb 1961			4-stage (--> 1994)
Atlas Centaur	(8 May 1962) 16 Feb 1961	5600	2250	4-stage (--> Atlas 2)
Saturn 1	29 Jan 1964	6800		2/3-stage (--> 1965)
Titan 2	08 Apr 1964	3500		Gemini launcher
Titan 3A	(01 Sep 1964) 10 Dec 1964			3-stage (--> 1965)
Titan 3C	18 Jun 1965	11300	4500	3-stage + boosters (--> Titan 34D)
Saturn 1B	05 Jul 1966	12900		Apollo launcher
Titan 3B	29 Jul 1966	3500	700 (THEO)	3-stage (--> Titan 34B)
LTTAT Agena	09 Aug 1966	2000		2-stage (--> 1972)
Saturn 5	09 Nov 1967	140000		Lunar vehicle launcher
Titan 3D	15 Jun 1971	13000		3-stage + boosters (--> Titan 34D)
Delta 29xx	09 Nov 1972	2000	720	2/3-stage (--> Delta 39xx)
Delta 39xx	13 Dec 1975		1250	2/3 stage (--> Delta 2)
STS	12 Apr 1981	24200	5900 (with IUS)	Space Shuttle
Titan 34D	30 Oct 1982	15800	1900	2/3-stage + boosters (--> Titan 4)
Delta-2 69xx	14 Feb 1989	4000	1400	Interim Delta 2
Titan 4	14 Jun 1989	17700	5500	2/3-stage + boosters
Pegasus	5 Apr 1990	400		air launched rocket
Delta-2 79xx	26 Nov 1990	5000	1610
Atlas 2	7 Dec 1991	6400	2700	2-stage
Atlas 2A	10 Jun 1992	6800	2900	2-stage
Atlas 2AS	16 Dec 1993	8400	3600	2-stage + boosters
Taurus	13 Mar 1994	1400		4-stage
Pegasus XL	(27 Jun 1994)	455		air launched rocket
Athena 1	(15 Aug 1995)	1000		3-stage
Conestoga	(23 Oct 1995)	2100		4-stage
Titan 4B	23 Feb 1997	22000	?	4-stage
Delta 3	(27 Aug 1998)	8346	3810
Sea Launch	28 Mar 1999		5400
Eagle	1999?	1300
Atlas 2AR	?		4037
Titan 2S	?
Titan 4SRMU	?
Kister 1	2000	500 kg
Atlas 3A	mid-1999			it uses the russian RD180 engine
Delta 4	2002		2.1 t to 6.6 t	in May 1999 already 19 orders
Atlas 5	2002	10.3 t to 20 t	4.1 t to 8.2 t	in May 1999 already 9 orders (has a russian RD-180 motor)
France
Diamant A	26 Nov 1965	80		3-stage (--> 1967)
Diamant B	10 Mar 1970	115		3-stage (--> 1973)
Diamant BP4	6 Feb 1975	150		3-stage (--> 1975)
Japan
Lambda-4S	(26 Sep 1966) 11 Feb 1970	20		4-stage, 1 successful flight
Mu-4S	(25 Sep 1970) 16 Feb 1971	75		3-stage (--> 1972)
Mu-3C	16 Feb 1974	85		3-stage (--> 1976)
N1	9 Sep 1975			3-stage (--> 1982)
Mu-3H	19 Feb 1977	100		3-stage (--> 1979)
Mu-3S1	17 Feb 1981	200		3-stage (--> 1984)
N2	11 Feb 1981		350	3-stage (--> 1987)
Mu-3S2	8 Jan 1985	400
H1	13 Aug 1986	3200	1100	3-stage (--> 1995)
H2	3 Feb 1994	10500	4000 (2000 to GEO)	2-stage + boosters
Mu 5	12 Feb 1997	1800		solid 3-stage
J1	?	870		solid 3-stage consist of H2 strap-on first stage + 2 stages of Mu-3S2
H2A202	2000		4000	$85 million
H2A2022	?		4250	2 little boosters
H2A2024	?		4500	4 little boosters
H2A212	?	18000	7500	H2A202 heavy version wit ha lateral body
H2A222	?	23000	9500	2 lateral bodies
China
Long March 1D	no launches?	1000		liquid/solid 3-stage
Long March 1	(01 Nov 1969) 24 Apr 1970			3-stage (--> 1971)
Long March 2A	(05 Nov 1974)			No successful flight
FB 1	10 Aug 1972			2-stage (LEO) (--> 1981)
Long March 2C	26 Nov 1975	2500	1000 + PKM	liquid 2-stage 14 success
Long March 3	29 Jan 1984	5000	1400	liquid 3-stage
Long March 4	6 Sep 1988	4000	1550	liquid 3-stage
Long March 2E	16 Jul 1990	9200	3370 with PKM	liquid 2-stage + 4 liquid strap-ons
Long March 2D	9 Aug 1992	3300		liquid 2-stage
Long March 3A	8 Feb 1994	7200	2500	liquid 2-stage
Long March 3B	(14 Feb 1996)		4800	liquid 3-stage + 4 liquid strap-ons consist of Long March 3A with 4 2E strap-ons
Long March 3C	exp. 1999		3700	liquid 3-stage + 2 liquid strap-ons consist of Long March 3A with 2 2E strap-ons
Long March 4B 8S	exp. 2001	7800	2670	liquid 3-stage + 8 strap-ons
United Kingdom
Black Arrow	(1 Sep 1970) 28 Oct 1971			3-stage One successful flight
Europe
Europa 1 F8	(30 Nov 1968)			No successful flight
Europa 2	(05 Nov 1971)			No successful flight
Ariane 1	24 Dec 1979		1700	3-stage (--> 1986)
Ariane 3	4 Aug 1984		2580	3-stage + boosters
Ariane 2	30 May 1986		2065	3-stage
Ariane 4, 44LP	15 Jun 1988	8300	4030
Ariane 4, 44L	4 Jun 1989	9600	4460
Ariane 4, 40	22 Jan 1990	4900	2020	3-stage
Ariane 4, 42P	20 Nov 1990	6100	2740
Ariane 4, 44P	4 Apr 1991	6900	3290
Ariane 4, 42L	12 May 1993	7400	3350
Ariane 5	(4 Jun 1996)  30 Oct 1997	18000	6800	liquid 2-stage + 2 solid strap-ons
India
SLV 3	(10 Aug 1979) 18 Jul 1980	40		4-stage (--> 1983)
ASLV	(24 Mar 1987) 20 May 1992	150		solid 4-stage + 2 solid strap-ons (--> 1994)
PSLV	(20 Sep 1993) 15 Oct 1994	3000		solid/liquid 4-stage + 2 solid strap-ons
GSLV	orig. late 1997	8000	2500
Israel
Shavit	19 Sep 1988	150		solid 3-stage
Brazil
VLS	(2 Nov 1997)	350 kg


 Soviet launch vehicles

Gunter Krebs

Sheldon / Dod	Name	Article	Designation	Comment
A / SL1		R7	8K71
A / SL1	Sputnik	?	8K71PS	for the first 2 Sputniks
A / SL2	Sputnik	?	8A91	for Sputnik (3) failure and Sputnik-3
A1 / SL3	Vostok L (Luna?)	?	8Kxx	for early Lunas and the first Korabl-Sputnik
A1 / SL3	Vostok K	?	8KxxK	for Korabl-Sputniks and Vostoks
A1 / SL3	Vostok	?	8A92	for Cosmos series (Zenit) spysats and early Meteors
A1 / SL3	Vostok M	?	8A92M	for sunsynchronous missions
A2 / SL4	Voskhod	?	11A57 ?	for the first missons and for Voskhod
A2 / SL4	Soyuz	?	11A511	for Soyuz capsules
A2 / SL4	Soyuz M	?	11A511M
A2 / SL4	Soyuz L	?	11A511L	to lift Cosmos 398 class Lunar lander tests into LEO
A2 / SL4	Soyuz U	?	11A511U	the current model for unmanned missions
A2 / SL4	Soyuz U2	?	11A511U2	the current version for manned missions (and possibly for Kuban type spysats)
A2e / SL6	Molniya	?	8K78	was used only until 1966
A2e / SL6	Molniya M	?	8K78M	the current model
Ae / SL5	Sputnik-Polyot	?	11A??	Polyot launch vehicle
A1m / SL10	?	?	11A510	Cosmos 125 / 102 launch vehicle
B1 / SL7	Cosmos 1	?	63S1	difference unknown
B1 / SL7	Cosmos B	?	11K63	difference unknown
C1 / SL8	?	?	65S1	Tyuratam launch
C1 / SL8	Cosmos 3	?	11K65	Tyuratam launch
C1 / SL8	Cosmos 3M	?	11K65M	Kapustin Yar and Plesetsk launch
D / SL9	Proton	UR500	8K82	two stage test version
D1 / SL13	Proton K	UR500K	8K82K	three stage version for LEO
D1e / SL12	Proton K Block D	UR-500K Block D	11S824	for early interplanetary probes
D1e / SL12	Proton K Block DM	UR-500K Block DM	11S86	for early GEO missions
D1e / SL12	Proton K Block DM2	UR-500K Block DM2	11S861	uprated version of Block DM
D1e / SL12	Proton K Block DM2M	UR-500K Block DM2M	11S861-01	lightwight version of Block DM2 for higher payloads
G1e / SL15		N1 / L3	?
G1e / SL15		N1 / L3 (7L)	L	N-1 L3 (7L) had different boattail
F1r / SL11		R36-0	8K69	for FOBS
F1m / SL11	Cyclone M (or 2)	?	11K69
F2 / SL14	Cyclone 3	?	11K68
J1 / SL16	Zenit 2	?	11K77
K1 / SL17	Energiya	?	?
	Dnepr		15A18M	RS-20 / SS-18 150 missiles in reserve before first space launch Operated by the Russian-Ukrainian Cosmotras company fired from a silo launch pad
	Strela			RS-18 first launch in late 2000 from Svobodny Can orbit 600 to 1700 kg to 300 to 1500 km orbit


needs sorting! (preparing new launcher items)

Angara

Should be replaced by the Angara booster The first stage will use the same kerosene-LOX four-engine cluster as Zenit; the second stage will use a single Energia-derived LH2-LOX engine. The configuration is rather odd: a cylindrical center body reminiscent of a Zenit (holding the fuel), with a pair of large drop tanks slung on the outside of each stage to hold the LOX. The initial configuration will launch 26t into a 63deg orbit from Plesetsk (slightly more than Proton from Baikonur); a third stage (LH2-LOX) will be added to put 4.5t payloads into GSO.

There is talk of an Angara offshoot using a modified second stage air-launched from an An-124, launching 6t into 51deg at about $1500/kg.

Burlak

Russian project of LEO launcher released from a bomber. Burlak will be a wingless two-stage liquid-fuel vehicle, derived from (unspecified) missile technology.  Payload to LEO would be up to 800kg at perhaps $5000/kg.


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 Ariane

by Jean-Jacques Serra

European launch vehicle program operated by Arianespace.

After the failure of the Europa 1/2 program, the ELDO was to design a totally new Europa 3. This launcher was to have a first stage L150 with stockable propellant powered by 4 Viking motors from SEP and a second cryogenic stage H20 equipped with a hight pressure HM-20 motor from Cryorocket. This project was found too risky both technically and financially especially by Germany which wanted to focus on the construction of Spacelab.

In 1972 the CNES proposed to built a launcher with the same performance but using only European tested technology like the low-pressure cryogenic propulsion. This project designed L-IIIS (substitution third generation launcher) was to use an H6 cryogenic top stage with a HM-4 motor designed by SEP. The poor performance of the H6 compared to the H20 required the use of two base stages, on L140 (reduced version of the Europa 3 L150) and an L33 (featuring a single Viking motor adapted to altitude use).

In December 1972 the 5th European Space Conference ended on 3 agreements: creation of a European Space Agency (ESA to replace both ELDO and ESRO) and the start of the L-IIIS and Spacelab.

The following year the L-IIIS project was further precised (increased propellant of the H6 to become H8 and replacement of the 4-chamber HM-4 by a single-nozzle HM-7) and changed denomination: Ariane. The CNES granted Aerospatiale as the industrial architect of the project.

Ariane 1

The first Ariane version was a 208-ton launcher (without payload) of 47.4 m high. The first stage (L140) was 3.8 m diameter, 18.4 m high, containing 147.6 tons propellant (NTO + UDMH). It was powered by a set of 4 Viking 5 motors which fired during 146 seconds, providing 2485 kN thrust at takeoff (Isp = 247 s) and 2770 kN in vacuum (Isp = 278 s). The second stage (L33) was 2.6 m diameter for 11.6 m high. It was loaded with 34.2 tons propellant identical to first stage. It's Viking 4 motor provided 723 kN thrust (Isp = 296 s) during 138 seconds. The top stage (H8) of same diameter was 9.1 m high. It's cryogenic motor HM-7 developped 61.3 kN thrust (Isp = 441 s) and consumned 8.2 tons liquid oxygen and hydrogen in 545 seconds. The first and third stage were assembled in France by Aerospatiale, the second stage in Germany by ERNO.

Ariane was optimized for launches in GTO to which it could deliver 1750 kg.

Ariane 2 & 3

As soon as 1977 the CNES started enhancing the performance of the launcher. The first derivatives named Ariane 2 & 3 had the following characteristics:

- On the two first stages: enhancement of the thrust of the Viking 4 and 5 by increasing the pressure of the combustion chamber and replacement of UDMH by UH25 (75% UDMH and 25% hydrazine hydrate). The combustion duration where then respectively 135 and 123 seconds.

- On the third stage: lengthening by 1.3 m of the tanks (10.7 tons propellant on this new H10) and increased specific impulsion of the motor (HM-7B). The combustion duration was then 720 s.

- Extension of the payload volume

The Ariane 3 version had also two additional solid booster: 8 m high, 1.07 m diameter, 9.7 tons (including 7.3 tons solid propellant: Flexadyne). Each booster provided 666 kN thrust during 28 s. They were manufactured by BPD in Italy.

The two launchers were 48.7 high. Ariane 2 weighed 212 tons at takeoff while Ariane 3 weighed 230 tons. The payload weights then reached 2065 kg and 2580 kg in GTO.

Ariane 4

The construction of a series of launchers named Ariane 4 with enhanced performance was decided in 1981. Those launchers are directly derived from the previous version, retaining the 3 stages and lengthening the first one and addition solid and/or liquid boosters.

The first stage of Ariane 4 named L220 is 23.2 m high. It transports 227 tons propellant identical to Ariane 2/3. It is still powered by a set of Viking 5 motors (version C) which provide during 205 seconds 2710 kN thrust at takeoff (3010 kN in vacuum, Isp = 278 s). The two other stages are those of Ariane 2/3 with a reinforced structure. The 3rd stage has been lengthened twice giving the H10+ (11 tons propellant) and H10-3 (11.8 tons propellant) versions. The latter burns during 13 minutes.

The flexibility of Ariane 4 is due to the adaptation of the payload by addition of boosters on the first stage. Those are of 2 types: PAP (solid) and PAL (liquid). The PAPs are a enhancement of the Ariane 3 boosters. They are 12 m high, weigh 12.6 tons (including 9.5 tons powder) and provide 650 kN thrust (Isp = 224 s) during 36 seconds. The PALs are built by MBB/ERNO. They are 19 m high, 2.2 m diameter, weigh 43.5 tons (39 tons of the same propellant as the first stage). Their Viking 6 motor fires during 143 seconds and provides 678 kN at ground level, 752 kN in vacuum.

The possible configurations are:

- Ariane 40: no boosters

- Ariane 42: 2 boosters, 42P with 2 PAP and 42L with 2 PAL

- Ariane 44: 4 boosters, 44P with 4 PAP, 44L with 4 PAL, 44LP with 2 PAP and 2 PAL

The launcher's height ranges from 54.1 m to 58.4 m depending on the cap used. Its mass ranges from 243 tons (Ariane 40) to 480 tons (Ariane 44L) and the GTO performance from 2020 kg to 4460 kg. Ariane 4 should remain in active service until the end of the century.

Ariane 5

The launch of the Ariane 5 program was decided by ESA members in November 1987 following an initial study launched in early 1985. Built with Aerospatiale as prime contractor, Ariane 5 is totally different from the previous Arianes in terms of architecture. It's configuration is closer to Titan or STS or H2. Like those launchers, Ariane 5 has got a main body with liquid propulstion and 2 large solid boosters.

The EAP (Etage d'Accélération à Poudre, acceleration solid stage) is composed of two MPS (Moteurs à Propulsion Solide, solid propulsion motors) also named P230 built by Europropulsion (a 50/50 groupement of SEP (France) and BDP (Italy)). Each MPS is 27 m high and 3 m diameter and weighs 267 tons including 237 tons of propellant (3 PBHT segments). They provide 6 MN thrust at takeoff (ISp = 273 s) and work during 123 s before being jettisonned at 56 km altitude.

The main body is made of an EPC (Etage Principal Cryotechnique, cryogenic main stage) and an ETS (Etage à Propergols Stockables, stockable propellant stage). The EPC is 30.5 m high and 5.4 m diameter. It is propulsed by a Vulcain flux-derived motor from SEP. It's thrust is 880 kN at ground level and reaches 1130 kN in vacuum (ISp = 430 s). The MPS are ignited only after the Vulcain motor has prooved to be working properly; it then burns 131 tons of LOX and 26 tons of LH2 within 600 seconds. The EPS alias L9 uses 9.7 tons of conventional ergols (NTP and MMH-H) and care for the precise orbital release. It is equipped with a MBB-ERNO (DASA group) Aestus motor of 28 kN thrust in vacuum than can work 1150 seconds and can be re-ignited.

With the equipment compartment and the cap (2 different versions are available) Ariane 5 is 45.7 to 55.9 m high. It weighs 710 tons. It's capacity to GTO is 6.8 tons with one satellite or 5.9 tons with 2 satellites or 5.5 tons with 3.

Ariane statistics

Type	First launch	Last launch	LEO/GTO capacity (kg)	Number of launches
1	24 Dec 1979	22 Feb 1986	/ 1700	11 (2 failures)
2	30 May 1986	2 Apr 1989	/ 2065	6 (1 failure)
3	4 Aug 1984	12 Jul 1989	/ 2580	11 (1 failure)
40	22 Jan 1990	24 Mar 1998	4900 / 2020	6
42P	20 Nov 1990	12 Aug 1999	6100 / 2740	12 (1 failure)
44P	4 Apr 1991	25 Aug 1998	6900 / 3290	14
42L	12 May 1993	22 Dec 1998	7400 / 3350	8
44LP	15 Jun 1988	16 Sep 1998	8300 / 4030	21 (1 failure)
44L	4 Jun 1989	26 Feb 1999	9600 / 4460	25 (1 failure)
5	4 Jun 1996	21 Oct 1998	18000 / 6800	3 (1 failure)
Motor performance

Type	First launch	4 Viking 5	4 Viking 5  Thrust (kN)	4 Viking 5  Isp (s)	Viking 4	Viking 4  Thrust (kN)	Viking 4  Isp (s)	HM7	HM7  Thrust (kN)	HM7  Isp (s)
1	1979	A	2485s/2770v	247s/278v	A	723	296	-	61.3	441
2/3	1984	B	2690s/2980v		B	785	296	B	62.8	445
4	1988	C	2710s/3010v		B	-	-	B	-	-
External resources

http://www.arianespace.com/


Ariane

[launch vehicle index]

Ariane L01 Ariane L02 Ariane L03 Ariane L04 Ariane L05 Ariane L06 Ariane L07 Ariane L08 Ariane V09 Ariane V10 Ariane V11 Ariane V12 Ariane V13 Ariane V14 Ariane V15 Ariane V16 Ariane V17 Ariane V18 Ariane V19 Ariane V20	Ariane V21 Ariane V22 Ariane V23 Ariane V24 Ariane V25 Ariane V26 Ariane V27 Ariane V28 Ariane V29 Ariane V30 Ariane V31 Ariane V32 Ariane V33 Ariane V34 Ariane V35 Ariane V36 Ariane V37 Ariane V38 Ariane V39 Ariane V40	Ariane V41 Ariane V42 Ariane V43 Ariane V44 Ariane V45 Ariane V46 Ariane V47 Ariane V48 Ariane V49 Ariane V50 Ariane V51 Ariane V52 Ariane V53 Ariane V54 Ariane V55 Ariane V56 Ariane V57 Ariane V58 Ariane V59 Ariane V60	Ariane V61 Ariane V62 Ariane V63 Ariane V64 Ariane V65 Ariane V66 Ariane V67 Ariane V68 Ariane V69 Ariane V70 Ariane V71 Ariane V72 Ariane V73 Ariane V74 Ariane V75 Ariane V76 Ariane V77 Ariane V78 Ariane V79 Ariane V80	Ariane V81 Ariane V82 Ariane V83 Ariane V84 Ariane V85 Ariane V86 Ariane V87 Ariane V88 Ariane V89 Ariane V90 Ariane V91 Ariane V92 Ariane V93 Ariane V94 Ariane V95 Ariane V96 Ariane V97 Ariane V98 Ariane V99 Ariane V100	Ariane V101 Ariane V102 Ariane V103 Ariane V104 Ariane V105 Ariane V106 Ariane V107 Ariane V108 Ariane V109 V110 V111 V112 V113 V114 V115 V116 V117 V118


foo title

SYLDA: SYstème de Lancement Double d'Ariane

SPELDA: Système Porteur Externe pour le Lancement Double Ariane


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 Ariane L01

General

Launch id	79104
Launch date	24 Dec 1979
Launch site	Kourou
Type	1
Payload mass
Payload	A: Cat 1
GTO	203/35996 km


 Ariane L02

General

Launch date	23 May 1980 at 09:29:39 UT
Launch site	Kourou
Type	1
Payload mass
Payload	Cat 2 Firewheel Phase 3A
Failure cause	First stage motor injection failure


 Ariane L03

General

Launch id	81057
Launch date	19 Jun 1981 at 12:32:52 UT
Launch site	Kourou
Type	1
Payload mass	1635 kg
Payload	A: Meteosat 2 B: Apple C: Cat 3
GTO	201/36206 km


 Ariane L04

General

Launch id	81122
Launch date	20 Dec 1981 at 01:29 UT
Launch site	Kourou
Type	1
Payload mass	> 1056 kg
Payload	A: Marecs A B: Cat 4

First night launch


 Ariane L05

General

Launch date	10 Sep 1982 at 01:12 UT
Launch site	Kourou
Type	1
Payload mass	1476 kg
Payload	Marecs B1 Sirio 2
Failure cause	3rd stage motor turbo pump failure


 Ariane L06

General

Launch id	83058
Launch date	16 Jun 1983 at 11:59 UT
Launch site	Kourou
Type	1
Payload mass	1205 kg
Payload	A: Eutelsat 1F1 B: Oscar 10

First successful launch with the Sylda system


 Ariane L07

General

Launch id	83105
Launch date	18 Oct 1983 at 23:54 UT
Launch site	Kourou
Type	1
Payload mass	1870 kg
Payload	A: Intelsat 507


 Ariane L08

General

Launch id	84023
Launch date	5 Mar 1984 at 00:50 UT
Launch site	Kourou
Type	1
Payload mass	1900 kg
Payload	A: Intelsat 508


 Ariane V09

General

Launch id	84049
Launch date	22 May 1984
Launch site	Kourou
Type	1
Payload mass	1195 kg
Payload	A: Spacenet 1

First launch operated by Arianespace


 Ariane V10

General

Launch id	84081
Launch date	4 Aug 1984 at 11:32:54 UT
Launch site	Kourou
Type	3
Payload mass	2395 kg
Payload	A: Eutelsat 1F2 B: Telecom 1A

First Ariane 3 launch


 Ariane V11

General

Launch id	84114
Launch date	10 Nov 1984 at 01:14 UT
Launch site	Kourou
Type	3
Payload mass	2251 kg
Payload	A: Spacenet 2 B: Marecs B2
GTO	200/36.022 km, inclination: 7.01°


 Ariane V12

General

Launch id	85015
Launch date	8 Feb 1985
Launch site	Kourou
Type	3
Payload mass	2310 kg
Payload	A: Arabsat 1A B: Brasilsat A1


 Ariane V13

General

Launch id	85035
Launch date	8 May 1985 at 00:15 UT
Launch site	Kourou
Type	3
Payload mass	2480 kg
Payload	A: GStar 1 B: Telecom 1B


 Ariane V14

General

Launch id	85056
Launch date	2 Jul 1985
Launch site	Kourou
Type	1
Payload mass	960 kg
Payload	ESA's comet Halley interceptor Giotto

Recovery of the first stage failed because the parachutes didn't open


 Ariane V15

General

Launch date	13 Sep 1985
Launch site	Kourou
Type	3
Payload mass	2380 kg
Payload	Eutelsat 1F3 Spacenet 3
Failure cause	One of the 3rd stage motors didn't switch on. President Mitterrand was there. It was Friday 13th


 Ariane V16

General

Launch id	86019
Launch date	22 Feb 1986 at 01:44:35 UT
Launch site	Kourou
Type	1
Payload mass	2438 kg
Payload	A: Spot 1 B: Viking

First launch towards North to put the satellites on a polar orbit. Last launch of an Ariane 1


 Ariane V17

General

Launch id	86026
Launch date	28 Mar 1986
Launch site	Kourou
Type	3
Payload mass	2410 kg
Payload	A: GStar 2 B: Brasilsat A2

First launch on ELA 2


 Ariane V18

General

Launch date	30 May 1986 at 00:53 UT
Launch site	Kourou
Type	2
Payload mass	1900 kg
Payload	Intelsat 514
Failure cause	One the 3rd stage motors didn't switch on

First launch of an Ariane 2


 Ariane V19

General

Launch id	87078
Launch date	16 Sep 1987
Launch site	Kourou
Type	3
Payload mass	2435 kg
Payload	A: Optus A3 B: Eutelsat 1F4


 Ariane V20

General

Launch id	87095
Launch date	21 Nov 1987
Launch site	Kourou
Type	2
Payload mass	2144 kg
Payload	A: Tvsat 1


 Ariane V21

General

Launch id	88018
Launch date	11 Mar 1988 at 23:28 UT
Launch site	Kourou
Type	3
Payload mass	2405 kg
Payload	A: Spacenet 3R B: Telecom 1C
GTO	202/36087 km, inclination: 7.03°


 Ariane V22

General

Launch id	88040
Launch date	17 May 1988 at 00:58 UT
Launch site	Kourou
Type	2
Payload mass	1978 kg
Payload	A: Intelsat 513
GTO	463/35948 km


 Ariane V23

General

Launch id	88051
Launch date	15 Jun 1988
Launch site	Kourou
Type	4, 44LP
Payload mass
Payload	A: Meteosat 3 B: Oscar 13 C: Panamsat 1

First launch of Ariane 4

with cyclade adapter


 Ariane V24

General

Launch id	88063
Launch date	21 Jul 1988 at 23:12 UT
Launch site	Kourou
Type	3
Payload mass	2337 kg
Payload	A: Insat 1C B: Eutelsat 1F5
GTO	198/35993 km, inclination: 7°


 Ariane V25

General

Launch id	88081
Launch date	8 Sep 1988 at 23:00 UT
Launch site	Kourou
Type	3
Payload mass	2511 kg
Payload	A: GStar 3 B: SBS 5


 Ariane V26

General

Launch id	88098
Launch date	28 Oct 1988 at 02:17 UT
Launch site	Kourou
Type	2
Payload mass	2100 kg
Payload	A: TDF 1
GTO	266/36096 km inclination: 3.94°


 Ariane V27

General

Launch id	88109
Launch date	11 Dec 1988 at 00:33 UT
Launch site	Kourou
Type	4, 44LP
Payload mass	3230 kg
Payload	A: Skynet 4B B: Astra 1A


 Ariane V28

General

Launch id	89006
Launch date	27 Jan 1989 at 01:21 UT
Launch site	Kourou
Type	2
Payload mass	1981 kg
Payload	A: Intelsat 515
GTO	463/35959 km, inclination: 8°


 Ariane V29

General

Launch id	89020
Launch date	6 Mar 1989 at 23:29 UT
Launch site	Kourou
Type	4, 44LP
Payload mass	2976 kg
Payload	A: Jcsat 1 B: Meteosat 4


 Ariane V30

General

Launch id	89027
Launch date	2 Apr 1989 at 02:28 UT
Launch site	Kourou
Type	2
Payload mass	2089 kg
Payload	A: TELE X

Last launch of an Ariane 2


 Ariane V31

General

Launch id	89041
Launch date	5 Jun 1989
Launch site	Kourou
Type	4, 44L
Payload mass	3907 kg
Payload	A: Superbird A1 B: DFS 1


 Ariane V32

General

Launch id	89053
Launch date	12 Jul 1989 at 00:14 UT
Launch site	Kourou
Type	3
Payload mass	2595 kg
Payload	A: Olympus

Last launch of an Ariane 3 and last use of ELA 1


 Ariane V33

General

Launch id	89062
Launch date	8 Aug 1989
Launch site	Kourou
Type	4, 44LP
Payload mass	3284 kg
Payload	A: Tvsat 2 B: Hipparcos


 Ariane V34

General

Launch id	89087
Launch date	27 Oct 1989 at 23:05 UT
Launch site	Kourou
Type	4, 44LP
Payload mass	4200 kg
Payload	A: Intelsat 602
GTO	199.6/35965 km


 Ariane V35

General

Launch id	90005
Launch date	22 Jan 1990 at 01:35 UT
Launch site	Kourou
Type	4, 40
Payload mass	1990 kg
Payload	A: Spot 2 B: Uosat 3 C: Uosat 4 D: Pacsat E: Dove F: Webersat G: Lusat

The ASAP 1 (Ariane Structure for Auxiliary Payload) structure which carries up to 200 kg was used


 Ariane V36

General

Launch date	22 Feb 1990
Launch site	Kourou
Type	4, 44L
Payload mass	3782 kg
Payload	Superbird B Yuri 2X
Failure cause	A rag was forgotten in a water pipe for D motor's cooling


 Ariane V37

General

Launch id	90063
Launch date	24 Jul 1990
Launch site	Kourou
Type	4, 44L
Payload mass	4114 kg
Payload	A: TDF 2 B: DFS 2
GTO	300/35933 km, inclination: 4°


 Ariane V38

General

Launch id	90079
Launch date	30 Aug 1990 at 22:46 UT
Launch site	Kourou
Type	4, 44LP
Payload mass	3280 kg
Payload	A: Skynet 4C B: Eutelsat 2F1


 Ariane V39

General

Launch id	90091
Launch date	12 Oct 1990
Launch site	Kourou
Type	4, 44L
Payload mass	4208 kg
Payload	A: SBS 6 B: Galaxy 6


 Ariane V40

General

Launch id	90100
Launch date	20 Nov 1990
Launch site	Kourou
Type	4, 42P
Payload mass	2464 kg
Payload	A: Satcom C1 B: GStar 4


 Ariane V41

General

Launch id	91003
Launch date	15 Jan 1991
Launch site	Kourou
Type	4, 44L
Payload mass	3720 kg
Payload	A: Italsat 1 B: Eutelsat 2F2


 Ariane V42

General

Launch id	91015
Launch date	2 Mar 1991
Launch site	Kourou
Type	4, 44LP
Payload mass	3261 kg
Payload	A: Astra 1B B: Meteosat 5


 Ariane V43

General

Launch id	91026
Launch date	5 Apr 1991
Launch site	Kourou
Type	4, 44P
Payload mass	2923 kg
Payload	A: Anik E2


 Ariane V44

General

Launch id	91050
Launch date	17 Jul 1991
Launch site	Kourou
Type	4, 40
Payload mass	2513 kg
Payload	A: ERS 1 B: Uosat 5 C: Orbcomm X D: Tubsat_A E: Sara

ASAP 2 carried the micro-satellites


 Ariane V45

General

Launch id	91055
Launch date	14 Aug 1991
Launch site	Kourou
Type	4, 44L
Payload mass	4296 kg
Payload	A: Intelsat 605


 Ariane V46

General

Launch id	91067
Launch date	27 Sep 1991
Launch site	Kourou
Type	4, 44P
Payload mass	2923 kg
Payload	A: Anik E1


 Ariane V47

General

Launch id	91075
Launch date	29 Oct 1991
Launch site	Kourou
Type	4, 44L
Payload mass	4330 kg
Payload	A: Intelsat 601


 Ariane V48

General

Launch id	91084
Launch date	16 Dec 1991
Launch site	Kourou
Type	4, 44L
Payload mass	3605 kg
Payload	A: Telecom 2A B: Inmarsat 2F3


 Ariane V49

General

Launch id	92010
Launch date	26 Feb 1992
Launch site	Kourou
Type	4, 44L
Payload mass	3870 kg
Payload	A: Superbird B1 B: Arabsat 1C


 Ariane V50

General

Launch id	92021
Launch date	15 Apr 1992
Launch site	Kourou
Type	4, 44L
Payload mass	3600 kg
Payload	A: Telecom 2B B: Inmarsat 2F4


 Ariane V51

General

Launch id	92041
Launch date	9 Jul 1992 at 22:42 UT
Launch site	Kourou
Type	4, 44L
Payload mass	3750 kg
Payload	A: Insat 2A B: Eutelsat 2F4


 Ariane V52

General

Launch id	92052
Launch date	10 Aug 1992
Launch site	Kourou
Type	4, 42P
Payload mass	2200 kg
Payload	A: Topex Poseidon B: Kitsat A C: S80T

ASAP 3 carried the micro-satellites


 Ariane V53

General

Launch id	92060
Launch date	10 Sep 1992
Launch site	Kourou
Type	4, 44LP
Payload mass	> 2120 kg
Payload	A: Hispasat 1A B: Satcom C3


 Ariane V54

General

Launch id	92072
Launch date	28 Oct 1992 at 00:15 UT
Launch site	Kourou
Type	4, 42P
Payload mass	2725 kg
Payload	A: Galaxy 7


 Ariane V55

General

Launch id	92084
Launch date	1 Dec 1992
Launch site	Kourou
Type	4, 42P
Payload mass	2780 kg
Payload	A: Superbird A2


 Ariane V56

General

Launch id	93031
Launch date	12 May 1993 at 00:56:32 UT
Launch site	Kourou
Type	4, 42L
Payload mass	2854 kg
Payload	A: Astra 1C B: Arsène

Cyclade dual payload adapter


 Ariane V57

General

Launch id	93039
Launch date	25 Jun 1993 at 00:18 UT
Launch site	Kourou
Type	4, 42P
Payload mass	2988 kg
Payload	A: Galaxy 4


 Ariane V58

General

Launch id	93048
Launch date	22 Jul 1993 at 22:58:55 UT
Launch site	Kourou
Type	4, 44LP
Payload mass	4020 kg
Payload	A: Hispasat 1B B: Insat 2B
GTO	200/35957 km, inclination: 6.96°


 Ariane V59

General

Launch id	93061
Launch date	26 Sep 1993 at 01:45 UT
Launch site	Kourou
Type	4, 40
Payload mass	2117 kg
Payload	A: Spot 3 B: Stella C: Eyesat D: Itamsat E: Healthsat F: ASAP 4 (22828) G: Posat H: Kitsat B

ASAP 4 carried the micro-satellites


 Ariane V60

General

Launch id	93066
Launch date	22 Oct 1993 at 06:46 UT
Launch site	Kourou
Type	4, 44LP
Payload mass	3692 kg
Payload	A: Intelsat 701


 Ariane V61

General

Launch id	93073
Launch date	20 Nov 1993 at 01:17 UT
Launch site	Kourou
Type	4, 44LP
Payload mass	3500 kg
Payload	A: Solidaridad 1 B: Meteosat 6


 Ariane V62

General

Launch id	93078
Launch date	18 Dec 1993 at 01:27 UT
Launch site	Kourou
Type	4, 44L
Payload mass	3940 kg
Payload	A: DBS 1 B: Thaicom 1


 Ariane V63

General

Launch date	24 Jan 1994 at 21:37 UT
Launch site	Kourou
Type	4, 44LP
Payload mass	3663 kg
Payload	Eutelsat 2F5 Turksat 1A
Failure cause	3rd stage motor failure (H10+ turbopump)


 Ariane V64

General

Launch id	94034
Launch date	17 Jun 1994 at 07:07 UT
Launch site	Kourou
Type	4, 44LP
Payload mass	3800 kg
Payload	A: Intelsat 702 B: STRV 1A C: STRV 1B


 Ariane V65

General

Launch id	94040
Launch date	8 Jul 1994 at 23:05:32 UT
Launch site	Kourou
Type	4, 44L
Payload mass	4035 kg
Payload	A: Panamsat 2 B: Yuri 3N
GTO	199.6/35977 km; inclination: 7°

Total mass boosted into orbit: 4618 kg


 Ariane V66

General

Launch id	94049
Launch date	10 Aug 1994 at 23:05 UT
Launch site	Kourou
Type	4, 44LP
Payload mass
Payload	A: Brasilsat B1 B: Turksat 1B


 Ariane V67

General

Launch id	94058
Launch date	9 Sep 1994 at 00:29 UT
Launch site	Kourou
Type	4, 44P
Payload mass	3300 kg
Payload	A: Telstar 402


 Ariane V68

General

Launch id	94065
Launch date	8 Oct 1994 at 01:07 UT
Launch site	Kourou
Type	4, 44L
Payload mass
Payload	A: Solidaridad 2 B: Thaicom 2


 Ariane V69

General

Launch id	94070
Launch date	1 Nov 1994 at 00:37 UT
Launch site	Kourou
Type	4, 42P
Payload mass	2924 kg
Payload	A: Astra 1D


 Ariane V70

General

Launch date	1 Dec 1994 at 22:57 UT
Launch site	Kourou
Type	4, 42P
Payload mass	2985 kg
Payload	Panamsat 3
Failure cause	3rd stage gave only 70% of its power

Boosters had been enhanced to transport the satellite which was 200 kilos heavier than normal maximal weight. The third stage was a H-10-3 type, first time used; this didn't cause the failure.


 Ariane V71

General

Launch id	95016
Launch date	28 Mar 1995 at 23:14:20 UT
Launch site	Kourou
Type	4, 44LP
Payload mass
Payload	A: Brasilsat B2 B: Hotbird 1 +1 meteo satellite?

Third stage was a H-10+ type


 Ariane V72

General

Launch id	95021
Launch date	21 Apr 1995 at 01:44 UT
Launch site	Kourou
Type	4, 40
Payload mass	2400 kg
Payload	ERS 2

Last flight with a H-10+ type 3rd stage


 Ariane V73

General

Launch id	95023
Launch date	17 May 1995 at 6:34 UT
Launch site	Kourou
Type	4, 44LP
Payload mass	4180 kg
Payload	Intelsat 706

Third stage was a H-10-3 type (second use) It increases the performance by 60 to 140 kg depending on the launcher version


 Ariane V74

General

Launch id	95029
Launch date	10 Jun 1995 at 00:24 UT
Launch site	Kourou
Type	4, 42P
Payload mass	2934 kg
Payload	DBS 3


 Ariane V75

General

Launch id	95033
Launch date	7 Jul 1995 at 16:23 UT
Launch site	Kourou
Type	4, 40
Payload mass	2634 kg
Payload	A: Hélios 1A B: Cerise C: UPMSat 1


 Ariane V76

General

Launch id	95040
Launch date	3 Aug 1995 at 22:58 UT
Launch site	Kourou
Type	4, 42L
Payload mass	3043 kg
Payload	A: Panamsat 4
Injection orbit	485.2 km x 35934 km x 4.21 deg


 Ariane V77

General

Launch id	95044
Launch date	29 Aug 1995 at 06:41 UT
Launch site	Kourou
Type	4, 44P
Payload mass	3398 kg
Payload	A: N Star A
GTO	199 km x 35922 km x 6.96 deg


 Ariane V78

General

Launch id	95049
Launch date	24 Sep 1995 at 00:06 UT
Launch site	Kourou
Type	4, 42L
Payload mass	3410 kg
Payload	A: Telstar 402R
GTO	249.1 km x 35919 km x 7.03°


 Ariane V79

General

Launch id	95055
Launch date	19 Oct 1995 at 00:38 UT
Launch site	Kourou
Type	4, 42L
Payload mass	3010 kg
Payload	A: Astra 1E
GTO	485.5 km x 36077 km x 4.19°


 Ariane V80

General

Launch id	95062
Launch date	17 Nov 1995 at 01:20 UT
Launch site	Kourou
Type	4, 44P
Payload mass
Payload	A: ISO
GTO	500 km x 71860 km x 5.25°

Equipped with an H-10-III upper stage, but with the No. 02 type payload fairing.


 Ariane V81

General

Launch id	95067
Launch date	6 Dec 1995 at 23:23 UT
Launch site	Kourou
Type	4, 44L
Payload mass	4296 kg
Payload	A: Telecom 2C B: Insat 2C
GTO	199.8 x 35976 km x 7°

Total mass boosted into orbit: 4804 kg


 Ariane V82

General

Launch id	96002
Launch date	12 Jan 1996 at 23:10 UT
Launch site	Kourou
Type	4, 44L
Payload mass	4368 kg
Payload	A: Panamsat 3R B: Measat 1
GTO	199.6 x 35992 km x 6.99°


 Ariane V83

General

Launch id	96007
Launch date	5 Feb 1996 at 07:19 UT
Launch site	Kourou
Type	4, 44P
Payload mass	3420 kg
Payload	N Star B
GTO	199.7 x 35952 km x 7°


 Ariane V84

General

Launch id	96015
Launch date	14 Mar 1996 at 07:11 UT
Launch site	Kourou
Type	4, 44LP
Payload mass	4175 kg
Payload	Intelsat 707
GTO	199.7 x 35913 km x 7.04°


 Ariane V85

General

Launch id	96022
Launch date	20 Apr 1996 at 10:36 UT
Launch site	Kourou
Type	4, 42P
Payload mass	2855 kg
Payload	MSAT 1
GTO	199.5 x 35923 km x 7°


 Ariane V86

General

Launch id	96030
Launch date	16 May 1996 at 01:56 UT
Launch site	Kourou
Type	4, 44L
Payload mass	3952 kg
Payload	A: Palapa C2 B: Amos 1
GTO


 Ariane V87

General

Launch id	96035
Launch date	15 Jun 1996 at 06:55 UT
Launch site	Kourou
Type	4, 44P
Payload mass	3420 kg
Payload	Intelsat 709
GTO	199.6 km x 35955 km x 6.99°


 Ariane V88

General

Launch id	n/a
Launch date	4 Jun 1996 at 12:34 UT
Launch site	Kourou ELA3
Type	5
Payload mass
Payload	Cluster
External resources

http://www.esrin.esa.it/htdocs/tidc/Press/Press96/ariane5rep.html


 Ariane V89

General

Launch id	96040
Launch date	9 Jul 1996 at 11:24 UT
Launch site	Kourou
Type	4, 44L
Payload mass	4360 kg
Payload	A: Arabsat 2A B: Turksat 1C
GTO	199.2 km x 35915 km x 7°


 Ariane V90

General

Launch id	96044
Launch date	8 Aug 1996 at 22:49 UT
Launch site	Kourou
Type	4, 44L
Payload mass	4200 kg
Payload	A: Italsat 2 B: Telecom 2D
GTO	200 km x 35980 km x 5.52°


 Ariane V91

General

Launch id	96054
Launch date	11 Sep 1996 at 00:00 UT
Launch site	Kourou
Type	4, 42P
Payload mass
Payload	Echostar 2
GTO	199.8 km x 35923 km x 6.97°


 Ariane V92

General

Launch id	96063
Launch date	13 Nov 1996 at 22:40 UT
Launch site	Kourou
Type	4, 44L
Payload mass	4173 kg
Payload	Arabsat 2B Measat 2
GTO	249.6 km x 35885 km x 3.98°


 Ariane V93

General

Launch id	97002
Launch date	30 Jan 1997 at 22:04 UT
Launch site	Kourou
Type	4, 44L
Payload mass	4899 kg (4441 kg for satellites)
Payload	A: GE 2 B: Nahuel 1A
GTO	200 km x 36000 km x 7.01°


 Ariane V94

General

Launch id	97009
Launch date	1 Mar 1997 at 1:07 UT
Launch site	Kourou
Type	4, 44P
Payload mass	3420 kg
Payload	Intelsat 801
GTO	199.1 km x 35941 km x 6.978°


 Ariane V95

General

Launch id	97016
Launch date	16 Apr 1997 at 23:08 UT
Launch site	Kourou
Type	4, 44LP
Payload mass
Payload	A: Thaicom 3 B: Bsat 1A
GTO	199 km x 35,936 km x 6.99°


 Ariane V96

General

Launch id	97031
Launch date	25 Jun 1997 at 23:44 UT
Launch site	Kourou
Type	4, 44L
Payload mass
Payload	Intelsat 802
GTO	200 km x 35,974 km x 7°


 Ariane V97

General

Launch id	97027
Launch date	3 Jun 1997 at 23:30 UT
Launch site	Kourou
Type	4, 44L
Payload mass	4079 kg
Payload	A: Inmarsat 3F4 B: Insat 2D
GTO	199.7 km x 35989 km x 7°


 Ariane V98

General

Launch id	97040
Launch date	8 Aug 1997 at 06:45 UT
Launch site	Kourou
Type	4, 44P
Payload mass	3420 kg
Payload	Panamsat 6
GTO	181 x 37143 km x 7.1°


 Ariane V99

General

Launch id	97049
Launch date	2 Sep 1997 at 22:21 UT
Launch site	Kourou
Type	4, 44LP
Payload mass	3830 kg
Payload	A: Hotbird 3 B: Meteosat 7
GTO	199 x 35948 km x 7°


 Ariane V100

General

Launch id	97053
Launch date	23 Sep 1997 at 23:58 UT
Launch site	Kourou
Type	4, 42L
Payload mass	3455 kg
Payload	Intelsat 803
GTO	249 x 35965 km x 7°


 Ariane V101

General

Launch id	97066
Launch date	30 Oct 1997 at 13:43 UT
Launch site	Kourou ELA 3
Type	5
Payload mass
Payload	A: Maqsat H B: Maqsat B C: YES
GTO	534 x 26631 km x 7.8° (instead of 581 x 36000 km)

Partial failure: the satellites were not injected in correct orbit. The EPC core stage shut down early (5 seconds) and had a roll control problem. The EAP solid boosters and the EPS final stage appear to have operated correctly.

A dummy ballast mass replaced Phase 3D which was pulled off the mission because of a predicted rougher ride than originally specified.


 Ariane V102

General

Launch id	97071
Launch date	12 Nov 1997 at 21:48 UT
Launch site	Kourou
Type	4, 44L
Payload mass
Payload	A: Sirius 2 B: Cakrawarta 1
GTO


 Ariane V103

General

Launch id	97075
Launch date	2 Dev 1997 at 22:53 UT
Launch site	Kourou
Type	4, 44P
Payload mass
Payload	A: Jcsat 5 B: Equator S
GTO

Cyclade dual payload adapter


 Ariane V104

General

Launch id	97083
Launch date	22 Dec 1997 at 00:16 UT
Launch site	Kourou
Type	4, 42L
Payload mass	3455 kg
Payload	Intelsat 804
GTO	249.7 x 35931 km x 6.98°


 Ariane V105

General

Launch id	98006
Launch date	4 Feb 1998 at 23:29 UT
Launch site	Kourou
Type	4, 44LP
Payload mass	3760 kg
Payload	A: Brasilsat B3 B: Inmarsat 3F5
GTO	199 x 36010 km x 7°


 Ariane V106

General

Launch id	98013
Launch date	27 Feb 1998 at 22:38 UT
Launch site	Kourou
Type	4, 42P
Payload mass	2885 kg
Payload	Hotbird 4
GTO


 Ariane V107

General

Launch id	98017
Launch date	24 Mar 1998 at 01:46 UT
Launch site	Kourou
Type	4, 40
Payload mass	2750 kg
Payload	Spot 4


 Ariane V108

General

Launch id	98024
Launch date	28 Apr 1998 at 22:53 UT
Launch site	Kourou
Type	4, 44P
Payload mass	3070 kg
Payload	A: Nilesat 101 B: Bsat 1B
GTO	199.4 x 35985 km x 7°


 Ariane V109

General

Launch id	98049
Launch date	25 Aug 1998 at 23:07 UT
Launch site	Kourou
Type	4, 44P
Payload mass	3255 kg
Payload	A: ST 1
GTO	280.4 km x 35976 km x 3.97°


 Ariane V110

General

Launch id	98052
Launch date	16 Sep 1998 at 06:31 UT
Launch site	Kourou
Type	4, 44LP
Payload mass
Payload	A: Panamsat 7
GTO


 Ariane V111

General

Launch id	98056
Launch date	5 Oct 1998 at 22:51 UT
Launch site	Kourou
Type	4, 44L
Payload mass	4415 kg
Payload	A: Eutelsat 3F2 B: Sirius 3
GTO


 Ariane V112

General

Launch id	98059
Launch date	21 Oct 1998 at 16:38 UT
Launch site	Kourou
Type	5
Payload mass	5440 kg
Payload	ARD A: Maqsat 3
GTO


 Ariane V113

General

Launch id	98063
Launch date	28 Oct 1998 at 22:16 UT
Launch site	Kourou
Type	4, 44L
Payload mass	4946 kg
Payload	A: Afristar B: GE 5
GTO	200 x 35788 km x 6.5°


 Ariane V114

General

Launch id	98069
Launch date	6 Dec 1998 at 00:43 UT
Launch site	Kourou
Type	4, 42L
Payload mass
Payload	Morelos 3
GTO	211 x 21516 km x 7°


 Ariane V115

General

Launch id	98075
Launch date	22 Dec 1998 at 01:08 UT
Launch site	Kourou
Type	4, 42L
Payload mass	3594 kg
Payload	Panamsat 6B
GTO	199.2 x 35969 km x 7°


 Ariane V116

General

Launch id	99009
Launch date	26 Feb 1999 at 10:44 UT
Launch site	Kourou
Type	4, 44L
Payload mass	4198 kg
Payload	Arabsat 3A Skynet 4E
GTO	199.4 x 35968 km x 7.01°


 Ariane V117

General

Launch id	99016
Launch date	2 Apr 1999 at 22:03 UT
Launch site	Kourou
Type	4, 42P
Payload mass	2550 kg
Payload	Insat 2E
GTO


 Ariane V118

General

Launch id	99042
Launch date	12 Aug 1999 at 22:52 UT
Launch site	Kourou
Type	4, 42P
Payload mass	2655 kg
Payload	Palapa D1
GTO	199.8 x 35914 km x 7°


 Athena

by Jean-Jacques Serra

listing by Gunter Krebs

Lockheed Launch Vehicle (LLV) or Lockheed-Martin Launch Vehicle (LMLV), later renamed Athena

The first achievement of Lockheed Missiles & Space Co. in the large solid missiles category was in the late 50ies with the FBM (Fleet Ballistic Missile) Polaris program. Lockheed built all the US SLBM (Submarine-Launched Ballistic Missile): Polaris A1 (first fire i 1958), A2 (1960), A3 (1962), Poseidon C3 (1965), Trident-1 C4 (1977) and Trident-2 D5 (1987).

In Jan 1993 Lockheed started designing a launch vehicle program aimed at light satellites (civilian and military). Those launchers are based on the existant solid boosters: Thiokol Castor 120, UTC/CSD Orbus 21 with eventually Thiokol Castor 4 boosters.

The LLV-1 is the smallest rocket of the series. It's a 66.3 tons vehicle of 19.8 m high and 2.34 m diameter (2 first stages). The first stage is a Castor-120 GT, derived from the first stage of the MX Peacekeeper missile. It is also used by OSC's Taurus. This booster is 8.89 m long and weights 54 tons. It provides 1550 kN thrust (in vaccum) during 86 seconds. The second stage uses an Orbus-21D which is also used for the IUS first stage and on TOS perigee stages. The Orbus-21D is 3.15 m long and weighs upto 10.4 tons (including 9.7 tons powder). It can provide a mean thrust of 196 kN during 154 seconds. LLV-1 has an OAM (Orbit Adjust Module) which has ten 200 N hydrazine Olin boosters. The AOM is used to pilote the rocket during the ballistic phase and provide a high precision orbit insertion.

The LLV-1 will be able to orbit upto 1 ton in LEO, the 3-stage LLV-2 should launch 2 tons and the LLV-3 assisted by 2 Castor-4 boosters upto 4 tons.

Lockheed Martin has an agreement with the US Air Force to launch as many as 10 of the rockets over the next 15 years.

Athena launches

#	Launch id	Payload	Launch date	Site	Type	Status (orbit in perigee x apogee x inc. x period)
1	n/a	Gemstar	15 Aug 1995	V	1	Failure: The first stage separated on time, but the rocket started oscillating a few secons earlier
2	97044	Lewis	23 Aug 1997 at 06:51 UT	V	1	289 x 603 km x 97.6°
3	98001	Lunar Prospector	7 Jan 1998 at 02:28 UT	C LC46	2
4	99002	Rocsat 1	27 Jan 1999 at 00:34 UT	C LC46	1	588 x 601 km x 35°
5	n/a	Ikonos 1	27 Apr 1999 at 18:22 UT	V SLC6	2	failure: cap failed to eject. This extra mass caused the 4th stage not to reach orbit
Notes: V for Vandenberg, C for Cape Canaveral launches


 Atlas

by Jean-Jacques Serra

Launchers operated by Lockheed Martin Launch Services, formerly General Dynamics. Since mid-1995 the launchers are marketed by ILS

External resources

http://www.lmco.com/ILS/

Origins of Atlas

Atlas without top stage

Atlas with an Agena stage

Atlas with solid top stage

Atlas with a Centaur stage

Origin: Inter Continental Ballistic Missile (ICBM) of first generation

In January 1955 the General Dynamics' Convair division was selected to build the Atlas system. In 1946 this firm was awarded a contract to design a 8000 km range ICBM: the MX-774. Three of those were launched in 1948 before the project was cancelled. Notheless those studies had lead to 3 major innovations: the engine with gimbaled nozzle, the monocoque structure and the releasable payload.

In the mid-50ies the problems related to high altitude ignition of liquid ergol engines were not solved. The only known solution was to ignite them all at takeoff: the Russians picked a bundle structure for their Semiorka while the Americans opted for a one-and-a-half stage vehicle. A main Rocketdyne LR105 sustainer of 670 kN was supported by 2 LR89 boosters. The propulsion bay containing 3 motors was named MA-1. Those engines consumed ergols (liquid oxygen and kerosene) provided by the same tanks. On each side a vernier LR101 rocket of 4.45 kN provided fine tuning of the thrust. The missile itself was 3.05 m diameter and 22.9 m in height (with an Mk2 Reentry Vehicle) and weighed over 110 tons.

On 11 Jun 1957 for its first test, the missile was only propulsed by its lateral motors... but it failed. The first success occured at the third try, on 17 Dec 1957. On 2 Aug 1958 the first 3-motor Atlas (named version B) ranged over 4000 km and the nominal range was achieved on 28 Nov 1958 (version C). Less than a month later on 18 Dec 1958 Atlas was used for a space mission: Score.

The propulsion system kept on evolving, first as a missile then as a space launcher. The first improved MA-2 was used for the Atlas-D ICBM. Then the MA-3 was introduced as a simplified version for the Atlas-E and -F ICBMs and derived launchers. The MA-5 was a civilian version of the MA-2; it was used by Atlas SLV-3 until the MA-5A version became available for Atlas-2.

Atlas propulsion system

Designation	Year of first launch	Main engine Thrust (kN)	Main engine SI (sec.)	Additional engines Thrust (kN)	Additional engines SI (sec.)	Application
MA-1	1957	240	210	1335	245	Atlas A, B, C
MA-2	1958	255	213	1375	248	Atlas D
MA-3	1960	255	214	1470	250	Atlas E, F, launchers
MA-5	1961	270	220	1680	259	launchers
MA-5A	1991	270	220	1885	264	launchers

Atlas was equipped with the top stages of Thor Able -derived from those of Vanguard- in 1959. This launcher named Atlas Able was to launch the Pioneer probes to the Moon. But after 3 failures between November 1959 and December 1960 it was abandonned.

Statistics

Between 1956 and 1989, 189 MA-1/MA-2, 238 MA-3 and 213 MA-5 propulsion systems were manufactured that is 640 Atlas. The great majority of those Altas were used as ICBM. Thus the 150th Atlas was fired on 7 Nov 1962 and within those 150 rockets only 31 did launch satellites.


Atlas

[launch vehicle index]

Origins of Atlas

Atlas without top stage

Atlas with an Agena stage

Atlas with solid top stage

Atlas with a Centaur stage


 Atlas without top stage

by Jean-Jacques Serra

The Score experiment proved that Atlas could orbit payloads without any top stage. So it was decided to use it for the manned Mercury program, without major modifications. The Redstone rocket used for the first tests of this program wasn't powerful enough to orbit the 1300 kg Mercury spacecraft.

Atlas launches for the Mercury program

#	Launch id	Payload	Launch date	Type	Status (orbit in perigee x apogee x inc. x period)
1	n/a	Mercury MA-1	29 Jul 1960	D	Ballistic flight
2	n/a	Mercury MA-2	21 Feb 1961	D	Ballistic flight
3	n/a	Mercury MA-3	25 Apr 1961	D	Failled to orbit
4	61025	Mercury MA-4	13 Sep 1961	D	161 x 256 x 32.8 x 88.4
5	61033	Mercury MA-5 (chimpanzee Enos)	29 Nov 1961	D	150 x 242 x 32.6 x 88.3
6	62003	Mercury MA-6 (J. Glenn)	20 Feb 1962	D	161 x 263 x 32.5 x 88.6
7	62019	Mercury MA-7 (S. Carpenter)	24 May 1962	D	161 x 268 x 32.5 x 88.5
8	62052	Mercury MA-8 (W. Schirra)	03 Oct 1962	D	161 x 283 x 32.5 x 88.8
9	63015	Mercury MA-9 (G. Cooper)	15 May 1963	D	161 x 267 x 32.5 x 88.7

Notes: All launches from Cape Canaveral


 Atlas Agena

by Jean-Jacques Serra

The Agena stage had been developped by Lockheed for the USAF. The first version featured a Bell 8096 motor (nitric acid/UDMH) of 67 kN. It couldn't be re-ignited unlike the Agena-B version introduced in 1960. Agena-D used a more powerful motor (71 kN) time double operational time. Those stages were all 1.52 m in diameter but had a variable length depending on the nature of the payload to which they were often integrated in.

Most of the payloads had military missions:

- reconnaissance (Samos, KH 6 and KH 7)

- early warning (Midas, Vela)

- SIGINT (Canyon, Ryolithe)

But Atlas Agena also launched:

- lunar probes (Ranger, Lunar Orbiter) & planetary probes (Mariner)

- target for the Gemini manned program (GATV, ATDA)

- scientific (OAO, OGO, Seasat) and technology (Snapshot, ATS) satellites

Atlas Agena launches

#	Launch id	Payload	Launch date	Site	Type	Status (orbit in perigee x apogee x inclination x period)
1	n/a	Midas-01	26 Feb 1960	C	Agena-A	Failure
2	60006	Midas 02	24 May 1960	C	Agena-A
3	n/a	Samos 1	11 Oct 1960	V		Failure
4	61001	Samos 2	31 Jan 1961	V	Agena-B
5	61018	Midas 03	12 Jul 1961	V	Agena-B
6	61021	Ranger-1	23 Aug 1961	C	Agena-B	169 x 502 x 32.9 x 90.6
7	n/a	Samos 3	09 Sep 1961	V	Agena-B	Failure
8	61028	Midas 04	21 Oct 1961	V	Agena-B
9	61032	Ranger-2	18 Nov 1961	V	Agena-B	158 x 237 x 33.3 x 88.3
10	n/a	Samos 4	22 Nov 1961	V	Agena-B	Failure
11	61035	Samos 5	22 Dec 1961	V	Agena-B	244 x 702 x 89.6 x 91.1
12	62001	Ranger-3	26 Jan 1962	C	Agena-B	Solar orbit
13	62007	Samos 6?	07 Mar 1962	V	Agena-B	249 x 635 x 90.9 x 93.9
14	62010	Midas 05	09 Apr 1962	V	Agena-B
15	62012	Ranger-4	23 Apr 1962	C	Agena-B	Moon impact
16	62016	KH 7 prototype? (FTV 2401)	26 Apr 1962	V	Agena-B
17	62023	KH 7 prototype? (FTV 2402)	17 Jun 1962	V	Agena-B
18	62030	KH 7 prototype? (FTV 2403)	18 Jul 1962	V	Agena-B	184 x 236 x 96.1 x 88.7
19	n/a	Mariner-1	22 Jul 1962	C	Agena-B	Failure
20	62035	KH 7 prototype? (FTV 2404)	05 Aug 1962	V	Agena-B	205 x 205 x 96.3 x 88.6
21	62041	Mariner-2	27 Aug 1962	C	Agena-B	Probe to Venus
22	62055	Ranger-5	18 Oct 1962	C	Agena-B	Solar orbit
23	62064	KH 7 prototype? (FTV 2405)	11 Nov 1962	V	Agena-B	206 x 206 x 96 x 88.7
24	n/a	Midas	17 Dec 1962	V	Agena-B	Failure
25	63014	Midas 06	09 May 1963	V	Agena-B
26	n/a	Midas	12 Jun 1963	V	Agena-D	Failure
27	63028	KH 7-01	12 Jul 1963	V	Agena-D
28	63030	Midas 07	18 Jul 1963	V	Agena-B
29	63036	KH7#2	06 Sep 1963	V	Agena-D	168 x 263 x 94.4 x 89.1
30	63039	Vela Hotel-1/2 (+)	17 Oct 1963	C	Agena-D	107000 x 113000 x 38.3 x 6270
31	63041	KH7#3	25 Oct 1963	V	Agena-D	144 x 332 x 99.1 x 89
32	63051	KH7#4	18 Dec 1963	V	Agena-D	122 x 266 x 97.9 x 88.5
33	64007	Ranger-6	30 Jan 1964	C	Agena-B	Lunar impact
34	64009	KH7#5 (OPS 2423)	25 Feb 1964	V	Agena-D	173 x 190 x 95.7 x 88.2
35	64012	KH7#6 (OPS 3435)	11 Mar 1964	V	Agena-D	163 x 202 x 95.7 x 88.2
36	64020	KH7#7 (OPS 3743)	23 Apr 1964	V	Agena-D	150 x 336 x 103.6 x 89.4
37	64024	KH7#8 (OPS 3592)	19 May 1964	V	Agena-D	141 x 380 x 101.1 x 89.7
38	64036	KH7#9 (OPS 3684) OPS 4923	06 Jul 1964	V	Agena-D	121 x 346 x 92.9 x 89.2
39	64040	Vela 3 (OPS 3662) Vela 4 (OPS 3674) ERS 13	17 Jul 1964	C	Agena-D	98000 x 108000 x 39.6 x 6023
40	64041	Ranger-7	28 Jul 1964	C	Agena-B	Moon impact
41	64045	KH7#10 (OPS 3802 + 3316)	14 Aug 1964	V	Agena-D	149 x 307 x 95.5 x 89
42	64054	OGO 1	05 Sep 1964	C	Agena-B
43	64058	KH7#11 (OPS 4262)	23 Sep 1964	V	Agena-D	145 x 303 x 92.9 x 89
44	n/a	KH7	08 Oct 1964	V	Agena-D	Failure
45	64068	KH7#12 (OPS 4384 + 5063)	23 Oct 1964	V	Agena-D	139 x 271 x 95.6 x 88.6
46	64073	Mariner-3	05 Nov 1964	C	Agena-D	Probe to Mars
47	64077	Mariner-4	28 Nov 1964	C	Agena-D	Probe to Mars
48	64079	KH7#13 (OPS 4439)	04 Dec 1964	V	Agena-D	158 x 357 x 97 x 89.7
49	65005	KH7#14 (OPS 4703)	23 Jan 1965	V	Agena-D	146 x 291 x 102.5 x 88.9
50	65010	Ranger-8	17 Feb 1965	C	Agena-B	Moon impact
51	65019	KH7#15 (OPS 4920)	12 Mar 1965	V	Agena-D	155 x 247 x 107.7 x 88.5
52	65023	Ranger-9	21 Mar 1965	C	Agena-B	Moon impact
53	65027	SNAPSHOT (OPS 4682) Secor 4 (EGRS 4)	03 Apr 1965	V	Agena-D	1282 x 1313 x 90 x 111.6
54	65031	KH7#16 (OPS 4983 + 6717)	28 Apr 1965	V	Agena-D	180 x 259 x 95.6 x 89
55	65041	KH7#17 (OPS 5236)	27 May 1965	V	Agena-D	149 x 267 x 95.8 x 88.7
56	65050	KH7#18 (OPS 6749 + 5501)	25 Jun 1965	V	Agena-D	151 x 283 x 107.6 x 88.8
57	n/a	KH7	12 Jul 1965	V	Agena-D	Failure
58	65058	Vela 5 (OPS 6577) Vela 6 (OPS 6564) ERS 17	20 Jul 1965	C	Agena-D	95000 x 107000 x 35.3 x 5148
59	65062	KH7#19 (OPS 5698 + 6761)	03 Aug 1965	V	Agena-D	149 x 307 x 107.5 x 89.1
60	65076	KH7#20 (OPS 6004)	30 Sep 1965	V	Agena-D	158 x 264 x 95.6 x 88.8
61	n/a	Agena GATV	25 Oct 1965	C	Agena-D	Failure
62	65090	KH7#21 (OPS 8293 + 6232)	08 Nov 1965	V	Agena-D	145 x 277 x 93.9 x 88.7
63	66002	KH7#22 (OPS 7253 + 3179)	19 Jan 1966	V	Agena-D	154 x 246 x 93.9 x 88.5
64	66012	KH7#23 (OPS 1184 + 3011 + 3031)	15 Feb 1966	V	Agena-D	148 x 293 x 96.5 x 89
65	66019	Agena GATV-8	16 Mar 1966	C	Agena-D	285 x 298 x 28.9 x 90.2
66	66022	KH7#24 (OPS 0879 + 0974)	18 Mar 1966	V	Agena-D	152 x 284 x 101 x 88.9
67	66031	OAO 1	08 Apr 1966	C	Agena-D
68	66032	KH7#25 (OPS 0910)	19 Apr 1966	V	Agena-D	145 x 398 x 117 x 89.9
69	66039	KH7#26 (OPS 1950 + 6785)	14 May 1966	V	Agena-D	133 x 358 x 110.6 x 89.4
70	n/a	Agena GATV-9	17 May 1966	C	Agena-D	Failure
	66046	ATDA	01 Jun 1966	C	model	292 x 296 x 28.9 x 90.2
71	66048	KH7#27 (OPS 1577 + 1856)	03 Jun 1966	V	Agena-D	143 x 288 x 87 x 88.9
72	66049	OGO 3	07 Jun 1966	C	Agena-B
73	66051	Midas 08	09 Jun 1966	V	Agena-D
74	66062	KH7#28 (OPS 1850)	12 Jul 1966	V	Agena-D	137 x 236 x 95.5 x 88.3
75	66065	Agena GATV-10	18 Jul 1966	C	Agena-D	290 x 296 x 28.9 x 90.2
76	66073	Lunar Orbiter 1	10 Aug 1966	C	Agena-D	Lunar orbit
77	66074	KH7#29 (OPS 1832 + 6810)	16 Aug 1966	V	Agena-D	146 x 358 x 93.3 x 89.6
78	66077	Midas 09	19 Aug 1966	V	Agena-D
79	66080	Agena GATV-11	12 Sep 1966	C	Agena-D	298 x 298 x 28.8 x 90.3
80	66083	KH7#30 (OPS 1686 + 6874)	16 Sep 1966	V	Agena-D	148 x 333 x 94 x 98.4
81	60089	Midas 10	05 Oct 1966	V	Agena-D
82	66090	KH7#31 (OPS 2055) SGLS 1 (OPS 5345)	12 Oct 1966	V	Agena-D	181 x 258 x 90.9 x 89
83	66098	KH7#32 (OPS 2070 + 5424)	02 Nov 1966	V	Agena-D	159 x 305 x 91 x 89.2
84	66100	Lunar Orbiter 2	06 Nov 1966	C	Agena-D	Lunar orbit
85	66103	Agena GATV-12	11 Nov 1966	C	Agena-D	243 x 310 x 28.8 x 89.9
86	66109	KH7#33 (OPS 1890)	05 Dec 1966	V	Agena-D	137 x 388 x 104.6 x 89.8
87	66110	ATS 1	07 Dec 1966	C	Agena-D
88	67007	KH7#34 (OPS 4399)	02 Feb 1967	V	Agena-D	136 x 357 x 103 x 89.5
89	67008	Lunar Orbiter-3	05 Feb 1967	C	Agena-D	Lunar orbit
90	67031	ATS-2	06 Apr 1967	C	Agena-D	178 x 11124 x 28.4 x 218.9
91	67041	Lunar Orbiter 4	04 May 1967	C	Agena-D	Lunar orbit
92	67050	KH7#35 (OPS 4321 + 5557)	22 May 1967	V	Agena-D	135 x 292 x 91.5 x 88.4
93	67055	KH7#36 (OPS 4360)	04 Jun 1967	V	Agena-D	149 x 456 x 104.9 x 90.6
94	67060	Mariner-5	14 Jun 1967	C	Agena-D	Venus probe
95	67075	Lunar Orbiter 5	01 Aug 1967	C	Agena-D	Lunar probe
96	67111	ATS 3	05 Nov 1967	C	Agena-D
97	68014	OGO 5	04 Mar 1968	C	Agena-D
98	68063	Canyon 1 (OPS 2222)	06 Aug 1968	C	Agena-D	31680 x 39860 x 9.9
99	69036	Canyon 2 (OPS 3148)	13 Apr 1969	C	Agena-D	31680 x 39860 x 9.9
100	70046	Rhyolite 1 (OPS 5346)	19 Jun 1970	C	Agena-D	31680 x 39860 x 9.9
101	70069	Canyon 3 (OPS 7329)	01 Sep 1970	C	Agena-D	31680 x 39860
102	n/a	Canyon 4	04 Dec 1971	C	Agena-D	Failure
103	72101	Canyon 5 (OPS 9390)	20 Dec 1972	C	Agena-D
104	73013	Canyon 6	06 Mar 1973	C	Agena-D	32100 x 39660 x 10.1
105	75055	Rhyolite 2 (OPS 4966)	18 Jun 1975	C	Agena-D	GEO
106	77038	Canyon 7 (OPS 9751)	23 May 1977	C	Agena-D	GEO
107	77114	Rhyolite 3 (OPS 4258)	11 Dec 1977	C	Agena-D	Failure: 146 x 188 x 29.9 x 87.9
108	78038	Rhyolite 4 (OPS 8790)	07 Apr 1978	C	Agena-D	GEO
109	78064	Seasat	26 Jul 1978	V	Agena-D	769 x 799 x 108 x 100.7

Notes: in the launcher date & site column C stands for Cape Canaveral and V for Vandenberg.


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Atlas with solid top stage
 Atlas with a solid fuel top stage

by Jean-Jacques Serra

listing by Gunter Krebs

Some Atlas missiles were reconverted in space launchers by addition of solid fuel top stages. OV-1, the first of these programs enabled to orbit two LEO 1.2 tons satellites. 11 flights took place between 1965 and 1971, with 2 or 3 OV-1 stages.

The Star-37S booster was used to launch meteorology satellites: civilians (Tiros N and 10 NOAAs) and military (8 DMSPs) between 1978 and 1995. This motor with 658 kg powder provided 43.5 KN thrust during 42 seconds. A similare motor (Star-37E ?) was used for 4 NOSS payloads between 1976 and 1980.

The 2-stage SGS-1 from McDonnell Douglas was used from 1977 to 1981 to launch 8 navigation satellites (NTS 2 and 7 of the first Navstars) SGS-1 weighed 2.5 tons and features 2 Star-37N motors providing each 68.8 kN thrust during 42 seconds. The next generation, SGS-2, weighed 4.5 tons. It featured two Star-48 motors providing each 66.7 kN during 87 seconds. It launched the 4 last preo-operational Navstars. Those two 2-stage launchers could orbit 460 and 860 kg respectively in a 250/21000 km, 63° transfert orbit.

A few specific configurations were also reported. Thus the STP program made use of Atlas with Burner 2 twice, of the Star-17A and of the Altair-3 (Star-20). NTS 1 was launched with a PTS top stage, and Solsat & Geosat with OIS stages. No information is available on the Atlas H top stages which launched 5 payloads betwee 1983 and 1987.

The last launch occured in March 1995 and Titan-2 will take over the launch of those payloads.

Atlas with solid top stage launches

#	Launch id	Payload	Launch date	Type	Status/Comment (orbit in perigee x apogee x inclination x period)
1, 172D	n/a	OV1-1 ABRES 6 (reentry experiment)	21 Jan 1965	D OV1	Failure
2, 68D	n/a	OV1-3	27 May 1965	D OV1	Failure
3, 34D	65078	OV 1-02 SSP 29 (reentry experiment)	05 Oct 1965	D OV1
4, 72D	66025	OV 1-04 OV 1-05	30 Mar 1966	D OV1
5, 58D	66063	OV 1-08 OV1-7	14 Jul 1966	D OV1	Partial failure: OV1-7 didn't reach orbit
6, 89D	66111	OV 1-09 OV 1-10	11 Dec 1966	D OV1
7, 92D	67072	OV 1-11 /1-12 / 1-86	27 Jul 1967	D OV1	Partial failure: OV1-11 didn't reach orbit
8, 107F	68026	OV 1-13 OV 1-14	06 Apr 1968	F OV1
9, 75F	68059	OV1-16 (Spades) OV1-17 (Cannonball 1)	11 Jul 1968	F OV1
10, 7004	n/a	STP, 10 satellites: Orbiscal 1 OV5-8 Gridsphere 1 & 2 Mylar Ballon 1 Rigidsphere 1 & 2 + 3 more	16 Aug 1968	SLV3 Burner2	Failure: the vehicle was destroyed due to a collapse of the payload fairing
11, 104F	69025	OV1-17 OV1-18 OV 1-19 OV1-17A (Orbiscal 2)	18 Mar 1969	F OV1
12, 76F	71067	OV 1-20 OV 1-21 Rigidsphere 1 & 2 Gridsphere 1 & 2 Cannonball 2 Musketball Mylar Balloon	07 Aug 1971	F OV1
13, 102F	72076	STP (Radcat + Radsat)	02 Oct 1972	F Burner2	530 x 750 x 98.4 x 99.5
14, 69F	74054	NTS-1	14 Jul 1974	F PTS	21600 x 22200 x 63 x 720
15, 71F	n/a	STP (P72-2)	12 Apr 1975	F Star-17A	Failure
16, 59F	76038	NOSS 01	30 Apr 1976	F Star-37E
17, 65F	77053	NTS-2	24 Jun 1977	F SGS1	20300 x 20300 x 63 x 720
18, 50F	77112	NOSS 02	08 Dec 1977	F Star-37E
19, 64F	78020	GPS BI-01	22 Feb 1978	F SGS1
20, 49F	78047	GPS BI-02	13 May 1978	F SGS1
21, 47F	78093	GPS BI-03	07 Oct 1978	F SGS1
22, 29F	78096	Tiros N	13 Oct 1978	F Star-37S ISS	846 x 862 x 98.9 x 102
23, 39F	78112	GPS BI-04	11 Dec 1978	F SGS1
24, 27F	79017	Solwind	24 Feb 1979	F OIS
25, 25F	79057	NOAA 06	27 Jun 1979	F Star-37SISS
26, 35F	80011	GPS BI-05	09 Feb 1880	F SGS1
27, 64F	80019	NOSS 03	03 Mar 1980	F Star-37E
28, 34F	80032	GPS BI-06	26 Apr 1980	F SGS1
29, 19F	80043	NOAA B	29 May 1980	F Star-37S ISS
30, 68E	n/a	NOSS 04	08 Dec 1980	E Star-37E	Failure
31, 87F	81059	NOAA 07	23 Jun 1981	F Star-37S ISS
32, 76E	n/a	GPS BI-07	18 Dec 1981	E SGS1	Failure
33, 60E	82118	DMSP/Block-5D2#1	21 Dec 1982	E Star-37S ISS	815 x 828 x 98.8 x 101.2
34, 6001H	83008	NOSS 05	09 Feb 1983	H
35, 73E	83022	NOAA 08	28 Mar 1983	E Star-37S ISS
36, 6002H	83056	NOSS 06	09 Jun 1983	H
37, 75E	83072	GPS BI-08	14 Jul 1983	E SGS2
38, 58E	83113	DMSP/Block-5D2#2	17 Nov 1983	E Star-37S ISS	823 x 835 x 98.7 x 101.4
39, 6003H	84012	NOSS 07	05 Feb 1984	H
40, 42E	84059	GPS BI-09	13 Jun 1984	E SGS2
41, 14E	84097	GPS BI-10	08 Sep 1984	E SGS2
42, 39E	84123	NOAA 09	12 Dec 1984	E Star-37S ISS
43, 41E	85021	Geosat	12 Mar 1985	E OIS	757 x 814 x 108.1 x 100.6
44, 55E	85093	GPS BI-11	09 Oct 1985	E SGS2
45, 6004H	86014	NOSS 08	09 Feb 1986	H
46, 52E	86073	NOAA 10	17 Sep 1986	E Star-37S ISS
47, 6005H	87043	NOSS 09	15 May 1987	H
48, 59E	87053	DMSP B5D2-3	20 Jun 1987	E Star-37S ISS
49, 54E	88006	DMSP/Block-5D2#4	03 Feb 1988	E Star-37S ISS	820 x 830 x 98.7 x 101.5
50, 63E	88089	NOAA 11	24 Sep 1988	E Star-37S ISS
51, 28E	90031	Stacksat (3)	11 Apr 1990	E Altair-3	760 x 780 x 90 x 100
52, 61E	90105	DMSP/Block-5D2#5	01 Dec 1990	E Star-37S ISS	730 x 850 x 98.9 x 100.7
53, 50E	91032	NOAA 12	14 May 1991	E Star-37S ISS
54, 53E	91082	DMSP/Block-5D2#6	28 Nov 1991	E Star-37S ISS	840 x 860 x 98.9 x 102
55, 34E	93050	NOAA 13	09 Aug 1993	E Star-37S ISS
56, 20E	94057	DMSP B5D2-7	29 Aug 1994	E Star-37S ISS
57, 11E	94089	NOAA 14	30 Dec 1994	E Star-37S ISS
58, 45E	95015	DMSP B5D2-8	24 Mar 1995	E Star-37S ISS

Notes: All launches from Vandenberg.


 Atlas Centaur

by Jean-Jacques Serra

listing by Gunter Krebs

The Atlas Centaur launchers are the most powerful versions in the Atlas familly and the only to be used since 1995. They use the Centaur top-stage which was the first cryogenic rocket stage.

The Pratt & Whitney RL10 engine consuming liquid oxygen and hydrogen had a long and difficult development. Its design started in 1958. It first flew in 1962 but didn't launch a real payload before 1966. The Centaur stage was designed to be used by Atlas. It had the same diameter and was 9.1 m long. In its operational version it was equipped with two RL10 A-3-3 engines with a thrust of 66.7 kN each.

In the late-70ies the total height of the Atlas Centaur reached 40 m (originally 34 m) and its mass at launch increased from 132 to 150 tons. At this time the launch program was to be abandonned since NASA had decided to transfer all launches to the Shuttle. In fact STS was less available than expected and the Atlas launch program was resumed with a simplified motor: the RL10 A-3-3A with 73.4 kN thrust which first flew in 1984.

During its first activity period (see chart 6) the Atlas Centaur launched:

- probes to the Moon (Surveyor) and to other planets (Marnier, Pioneer)

- heavy scientific satellites (OAO, HEAO)

- geostationary telecommunication satellites (ATS, Intelsat, Comstar, Fleetsatcom)

In 1987 the augmented Atlas Centaur was selected by the USAF as the MLV2 standard launcher. This new launcher is refered to as Atlas-2 and the former version as Atlas-1. The basic Atlas-2 is an Atlas Centaur which has a 2.7 m longer first stage and a 0.9 m longer second stage. Furthermore the first stage is equipped with the new MA-5A motors. Atlas-2A is different by its second stage RL10 A-4 engines with deployable nozzle. Those rockets range from 45.6 to 47.5 m high and weigh 187 tons (Atlas-1 was 42-44 m high and weigh 164 tons).

Atlas-2AS is still more powerful. It is made from Atlas-2A to which two pairs of Castor-4A boosters of 436 kN thrust each are added. Each pair ignites one after the other. Thus Atlas-2AS weighs 234 tons and can deliver 3.6 tons in GTO compared to 2.7 and 2.9 tons for Atlas-2 and -2A, and 2.3 tons for Atlas-1.

Atlas Centaur rockets are optimized for geostationary orbit satellites.

Statistics

The RL-10 motor made its 100th flight on the top stage Centaur of AC-114

Atlas Centaur launches

#	Launch id	Payload	Launch Date	Site	Type	Status/Comment (orbit in perigee x apogee x inclination x period)
1, AC001	n/a	suborbital test	08 May 1962	C	LV3C C-A	Failure because of collapse of payload shroud
2, AC002	63047	test	27 Nov 1963	C	LV3C C-B	544 x 1699 x 30.3 x 170.5
3, AC003	n/a	test	30 Jun 1964	C	LV3C C-C	Hydraulic failure in Centaur
4, AC004	64082	test (Surveyor Mass Model 1)	11 Dec 1964	C	LV3C C-C	165 x 178 x 30.7 x 87.8
5, AC005	n/a	Surveyor SD 1	02 Mar 1965	C	LV3C C-C	Failure: exploded on launch pad
6, AC006	65064	Surveyor SD 2	11 Aug 1965	C	LV3C C-D	Solar orbit
7, AC008	66030	test (Surveyor Mass Model 2)	08 Apr 1966	C	LV3C C-D	175 x 334 x 30.7 x 89.5
8, AC010	66045	Surveyor-1	30 May 1966	C	LV3C C-D	Payload landed on the Moon
9, AC007	66084	Surveyor-2	20 Sep 1966	C	LV3C C-D	Payload impacted on the Moon
10, AC009	66095	test (Surveyor Mass Model 3)	26 Oct 1966	C	LV3C C-D	200 x 47000 x 22.9
11, AC012	67035	Surveyor-3	17 Apr 1967	C	LV3C C-D	Payload landed on the Moon
12, AC011	67068	Surveyor-4	14 Jul 1967	C	LV3C C-D	Payload impacted on the Moon
13, AC013	67084	Surveyor-5	08 Sep 1967	C	SLV3C C-D	Payload landed on the Moon
14, AC014	67112	Surveyor-6	07 Nov 1967	C	SLV3C C-D	Payload landed on the Moon
15, AC015	68001	Surveyor-7	07 Jan 1968	C	SLV3C C-D	Payload landed on the Moon
16, AC017	68068	ATS-4	10 Aug 1968	C	SLV3C C-D	Failure: Centaur failed on second ignition
17, AC016	68110	OAO 2	07 Dec 1968	C	SLV3C C-D
18, AC020	69014	Mariner-6	25 Feb 1969	C	SLV3C C-D	Mars probe
19, AC019	69030	Mariner-7	27 Mar 1969	C	SLV3C C-D	Mars probe
20, AC018	69069	ATS 5	12 Aug 1969	C	SLV3C C-D
21, AC021	n/a	OAO 3	30 Nov 1970	C	SLV3C C-D	Failure: payload shroud failed to seperate
22, AC025	71006	Intelsat 402	26 Jan 1971	C	SLV3C C-D
23, AC024	n/a	Mariner-8	08 May 1971	C	SLV3C C-D	Failure: Centaur guidance failure
24, AC023	71051	Mariner-9	30 May 1971	C	SLV3C C-D	Mars probe
25, AC026	71116	Intelsat 403	20 Dec 1971	C	SLV3C C-D
26, AC028	72003	Intelsat 404	23 Jan 1972	C	SLV3C C-D
27, AC027	72012	Pioneer-10	03 Mar 1972	C	SLV3C C-D Star-37E	Jupiter probe
28, AC029	72041	Intelsat 405	13 Jun 1972	C	SLV3C C-D
29, AC022	72065	OAO 3	21 Aug 1972	C	SLV3C C-D
30, AC030	73019	Pioneer-11	06 Apr 1973	C	SLV3D C-D1A Star-37E	Jupiter & Saturn probe
31, AC031	73058	Intelsat 407	23 Aug 1973	C	SLV3D C-D1A
32, AC034	73085	Mariner-10	03 Nov 1973	C	SLV3D C-D1A	Venus and Mercury probe
33, AC032	74073	Intelsat 408	21 Nov 1974	C	SLV3D C-D1A
34, AC033	n/a	Intelsat 406	20 Feb 1975	C	SLV3D C-D1A	Failure: 1st stage failes due to electrical shortcut
35, AC035	75042	Intelsat 401	22 May 1975	C	SLV3D C-D1A
36, AC036	75091	Intelsat 4A01	26 Sep 1975	C	SLV3D C-D1AR
37, AC037	76010	Intelsat 4A02	29 Jan 1976	C	SLV3D C-D1AR
38, AC038	76042	Comstar 1	13 May 1976	C	SLV3D C-D1AR
39, AC040	76073	Comstar 2	22 Jul 1976	C	SLV3D C-D1AR
40, AC039	77041	Intelsat 4A04	26 May 1977	C	SLV3D C-D1AR
41, AC045	77075	Heao 1	12 Aug 1977	C	SLV3D C-D1AR
42, AC043	n/a	Intelsat 4A05	30 Sep 1977	C	SLV3D C-D1AR	Failure: Atlas boostersection turbopump failed
43, AC046	78002	Intelsat 4A03	07 Jan 1978	C	SLV3D C-D1AR
44, AC044	78016	Fleetsatcom 1	09 Feb 1978	C	SLV3D C-D1AR
45, AC048	78035	Intelsat 4A06	31 Mar 1978	C	SLV3D C-D1AR
46, AC050	78051	Pioneer-12 (Pioneer Venus-1)	20 May 1978	C	SLV3D C-D1AR	Probe to Venus, Venus orbit
47, AC048	78068	Comstar 3	29 Jun 1978	C	SLV3D C-D1AR
48, AC051	78078	Pioneer-13 (Pioneer Venus-2)	08 Aug 1978	C	SLV3D C-D1AR	Probe to Venus: soil module
49, AC052	78103	Heao 2	13 Nov 1978	C	SLV3D C-D1AR
50, AC047	79038	Fleetsatcom 2	04 May 1979	C	SLV3D C-D1AR
51, AC053	79082	Heao 3	20 Sep 1979	C	SLV3D C-D1AR
52, AC049	80004	Fleetsatcom 3	18 Jan 1980	C	SLV3D C-D1AR
53, AC057	80087	Fleetsatcom 4	31 Oct 1980	C	SLV3D C-D1AR
54, AC054	80098	Intelsat 502	06 Dec 1980	C	SLV3D C-D1AR
55, AC042	81018	Comstar 4	21 Feb 1981	C	SLV3D C-D1AR
56, AC056	81050	Intelsat 501	23 May 1981	C	SLV3D C-D1AR
57, AC059	81073	Fleetsatcom 5	06 Aug 1981	C	SLV3D C-D1AR
58, AC055	81119	Intelsat 503	15 Dec 1981	C	SLV3D C-D1AR
59, AC058	82017	Intelsat 504	04 Mar 1982	C	SLV3D C-D1AR
60, AC060	82097	Intelsat 505	28 Sep 1982	C	SLV3D C-D1AR
61, AC061	83047	Intelsat 506	19 May 1983	C	SLV3D C-D1AR
62, AC062	84057	Intelsat 509	09 Jun 1984	C	G C-D1AR	Partial failure: Centaur LOX-tank exploded on LEO
63, AC063	85025	Intelsat 510	22 Mar 1985	C	G C-D1AR
64, AC064	85055	Intelsat 511	30 Jun 1985	C	G C-D1AR
65, AC065	85087	Intelsat 512	29 Sep 1985	C	G C-D1AR
66, AC066	86096	Fleetsatcom 7	05 Dec 1986	C	G C-D1AR
67, AC067	n/a	Fleetsatcom 6	26 Mar 1987	C	G C-D1AR	Failure because of lightning strike
68, AC068	89077	Fleetsatcom 8	25 Sep 1989	C	G C-D1AR
69, AC069	90065	CRRES	25 Jul 1990	C	1	330 x 33600 x 18.1 x 591
70, AC070	n/a	Yuri 3H (BS 3H)	19 Apr 1991 at 23:30 UT	C	1	Failure: one of the two Centaur engines didn't ignite
71, AC102	91083	Eutelsat 2F3	07 Dec 1991 at 22:47 UT	C	2 (8102)
72, AC101	92006	DSCS 3-05	11 Feb 1992 at 00:41 UT	C	2 IABS
73, AC072	92013	Galaxy 5	14 Mar 1992	C	1
74, AC105	92032	Intelsat K	10 Jun 1992 at 00:00 UT	C	2A
75, AC103	92037	DSCS 3-06	02 Jul 1992 at 21:54 UT	C	2 IABS
76, AC071	n/a	Galaxy 1R failure	22 Jul 1992	C	1	Failure: 3rd stage failed to ignite
77, AC074	93015	UHF 1	25 Mar 1993 at 22:48 UT	C	1	Partial failure
78, AC104	93046	DSCS 3-07	19 Jul 1993	C	2 IABS
79, AC075	93056	UHF 2	03 Sep 1993 at 11:17 UT	C	1
80, AC106	93074	DSCS 3-08	28 Nov 1993	C	2 IABS
81, AC108	93077	Telstar 401	16 Dec 1993 at 00:40 UT	C	2AS
82, AC073	94022	Goes 08	13 Apr 1994 at 06:44 UT	C 36B	1
83, AC076	94035	UHF 3	24 Jun 1994 at 13:50 UT	C 36B	1
84, AC107	94047	DBS 2	03 Aug 1994 at 23:57 UT	C 36A	2A
85, AC111	94064	Intelsat 703	06 Oct 1994 at 06:35 UT	C 36B	2AS
86, AC110	94079	Orion 1	23 Nov 1994 at 10:21 UT	C 36A	2A
87, AC113	95001	Intelsat 704	10 Jan 1995 at 06:18 UT	C	2AS
88, AC112	95003	UHF 4	29 Jan 1995 at 01:25 UT	C	2
89, AC115	95013	Intelsat 705	22 Mar 1995 at 06:18 UT	C 36B	2AS
90, AC114	95019	AMSC 1	07 Apr 1995 at 23:47 UT	C 36A	2A
91, AC077	95025	Goes 09	23 May 1995 at 05:52 UT	C 36B	1
92, AC116	95027	UHF 5	31 May 1995 at 15:27 UT	C 36A	2
93, AC118	95038	DSCS 3-09	31 Jul 1995 at 23:30 UT	C	2A IABS
94, AC117	95043	Jcsat 3	29 Aug 1995 at 00:53 UT	C 36B	2AS
95, AC119	95057	UHF 6	22 Oct 1995 at 08:00 UT	C 36B	2
96, AC121	95065	Soho	02 Dec 1995 at 08:08 UT	C 36B	2AS
97, AC120	95069	Galaxy 3R	15 Dec 1995 at 00:23 UT	C 36A	2A
98, AC126	96006	Palapa C1	1 Feb 1996 at 01:15 UT	C 36B	2AS
99, AC122	96020	Inmarsat 3F1	3 Apr 1996 at 23:01 UT	C 36A	2A
100, AC078	96027	SAX	30 Apr 1996 at 04:31 UT	C 36B	1
101, AC125	96042	UHF 7	25 Jul 1996 at 12:42 UT	C 36A	2
102, AC123	96054	GE 1	8 Sep 1996 at 21.49 UT	C 36B	2A
103, AC124	96067	Hotbird 2	21 Nov 1996 at 20:47 UT	C 36B	2A	168 km x 35784 km x 23.8°
104, AC129	96070	Inmarsat 3F3	18 Dec 1996 at 01:57 UT	C	2A	1017 km x 35820 km x 22.7°
105, AC127	97007	Jcsat 4	17 Feb 1997 at 01:42 UT	C 36B	2AS	221 km x 94251 km x 23.5°
106, AC128	97011	Tempo 2	8 Mar 1997 at 06:01 UT	C 36A	2A
107, AC079	97019	Goes 10	25 Apr 1997 at 05:49 UT	C 36B	1	announced as the last launch of an Atlas 1
108, AC133	97036	Superbird C	28 Jul 1997 at 01:15 UT	C 36B	2AS	333 x 91062 km x 25.3°
109, AC146	97050	GE 3	4 Sep 1997 at 12:03 UT	C 36A	2AS	309 x 43913 km x 19.1°
110, AC135	97059	Echostar 3	5 Oct 1997 at 21:01 UT	C 36B	2AS
111, AC131	97065	A: DSCS 3-10 B: Falcon Gold	25 Oct 1997 at 00:46 UT	C 36A	2A
112, AC149	97078	Galaxy 8i	8 Dec 1997 at 23:52 UT	C 36B	2AS	280 x 50607 km x 26.8°
113, AC109	98005	USA 137	29 Jan 1998 at 18:37 UT	C 36A	2A
114, AC151	98013	Intelsat 806	28 Feb 1998 at 00:21 UT	C 36B	2AS	190 x 35656 km x 23°
115, AC132	98016	UHF 8	16 Mar 1998 at 21:32 UT	C 36A	2	last Atlas 2
116, AC153	98037	Intelsat 805	18 Jun 1998 at 22:48 UT	C 36A	2AS
117, AC134	98057	Hotbird 5	9 Oct 1998 at 22:50	C 36B	2A
118, AC130	98058	UHF 9	20 Oct 1998 at 07:19 UT	C 36A	2A
119, AC152	99006	Jcsat 6	16 Feb 1999 at 01:45 UT	C 36A	2AS	258 x 96736 km x 24.1°
120, AC154	99018	Eutelsat 3F3	12 Apr 1999 at 22:50 UT	C 36A	2AS	166 x 46076 km x 19.7°

Note: In the launch site column C stands for Cape Canaveral and may be followed by the launch pad number. In the type column the second part of the type beginning with C- stands for Centaur-


Atlas

[launch vehicle index]

Origins of Atlas

Atlas without top stage

Atlas with an Agena stage

Atlas with solid top stage

Atlas Centaur

AC070

AC074


 Atlas AC070

General

Launch date	19 Apr 1991 at 23:30 UT
Launch site	Cape Canaveral
Type	1
Payload mass	1115 kg
Payload	Yuri 3H
Failure cause	one of the two Centaur engines didn't ignite


 Atlas AC074

General

Launch id	93015
Launch date	25 Mar 1993 at 22:48 UT
Launch site	Cape Canaveral LC36
Type	1
Payload mass	~3000 kg
Payload	A: UHF 1

The Atlas lost some power during the booster burn, and the Centaur had to burn longer to make up and get into parking orbit. As a result, the second Centaur burn to transfer orbit ran out of fuel during the burn. The payload satellite was left in a 219 x 9158 km x 27.3 deg orbit.

This was the third failure of the Atlas 1 class rocket in the last 4 launches!


 Black Arrow

by Jean-Jacques Serra

listing by Gunter Krebs

Origin: Black Knight experimental rocket

In 1957 the UK Royal Aircraft Establishment began the development of the Black Knight rocket to study atmosphere reentry of ballistic warheads.

The Black Knight was a long cylinder surmounted by a conical rounded head with 4 ribs equipped of stabilization rockets. It was powered by a Gamma 301 made by Bristol Siddeley; its thrust increased from 74 to 106 kN. On its first launch at Woomera in September 1958 it broke the world altitude record with 564 km. It was fired 22 times successfuly between 1958 and 1965.

Black Arrow

The development of the space launcher Black Arrow began in 1964 under direction of the Royal Aircraft Establishment. It was 3-stage rocket of only 13 m high weighing 18.1 tons at takeoff time with a LEO payload capacity of nearly 100 kg.

The first stage weighed 14.1 tons and measured 5.9 m high for 2  diameter. It was equipped with a Gamma-8 motor that featured 8 combustion chambers (gimbaled nozzles). It fired during 125 seconds providing 218 kN thrust and 251 kN in vacuum. Second stage was 3.55 m high per 1.37 m diameter and weighed 3.5 tons. Its Gamma-2 motor featuring 2 combustion chambes (gimbaled nozzles) consummed the same propellant and delivered 69 kN thrust during 120 seconds. The third stage was underthe 1.37 m diameter cap and layed on a spinning table. It was 1.3 m high, 71 cm diameter and 0.5 t weight. This stage was powered by a Waxwing solid fuel motor providing a mean thrust of 21 kN over 40 seconds.

The first ballistic flight which occured in Jun 1969 failed but the second in March 1970 was successful. The first orbiting attempt failed in Sep 1970 when second stage shutdown 13 seconds early. In July 1971 the British government decided to drop the national program although one flight was still to be carried out. Nonetheless it was fired in Oct 1971 and orbited the Prospero satellite.

Black Arrow launches

#	Launch id	Payload	Launch Date	Site	Type	Status/Comment
1	n/a	Ballistic flight	29 Jun 1969	W	2-stage	Failure: control lost after 50 s
2	n/a	Ballistic flight	04 Mar 1970	W	2-stage
3	n/a	Orba (X2)	02 Sep 1970	W		Failure: 2nd stage produced unsufficient thrust
4	71093	Prospero (X3)	28 Oct 1971	W

Notes: All launches from Woomera Rocket Range in Australia


 Cosmos B

by Jean-Jacques Serra

Origin: MRBM of first generation (Medium Range Ballistic Missile)

The design of Soviet stockable liquid propellant ballistic missiles started in 1954 under management of M.K. Yangel at the SKB 586 of Dniepropetrosk (now NPO Yuzhnoye) in Ukraine. At this time the motorist V.P. Glouchko started to develop a nitric acid - kerosen 4-chamber motor, roviding 650 kN in vacuum.

The first realization of Yangel was the R12 (SS-4 Sandal) of 1800 km range. This single stage rocket was 22.4 m high and 1.65 m diameter, and weighed 28 tons. It was aimed by a 4-chamber RD-214 using nitric acid & kerosen. It burned during 140 seconds providing 635 kN thrust at ground level, 730 kN in vacuum (Isp = 264 s). The tuning of the thrust vector was made with control jets but the rocket also has 4 little directional aerodynamical rudder.

The R12 was launched for the first time on 22 Jun 1957 from Kapustin Yar. It was declared operational in 1959. Its deployment in Cuba in 1962 cause a major international crisis.

Note: the R12 without top stage was used to launch a Vertikal payload of 35 kg at 4400 km on 12 Oct 1967.

Cosmos 1 (B1 / SL7)

In 1962 the R12 rocket was transformed in a ligh launcher by addition of a top stage. This stage of same diameter as the first one was powered by a RD-119 single-nozzle motor using the unusual couple LOX/UDMH. It provided 105 kN thrust in vacuum (Isp = 352 s) during 260 seconds.

This 49 tons launcher measured 32 m high and could place 0.5 tons into low earth orbit. It was used 144 times successfully between 1962 and 1977 from Kapustin Yar and Plesetsk.

Launch statistics

	Kapustin Yar	Plesetsk	Total
1962	7		7
1963	4		4
1964	7		7
1965	7		7
1966	7		7
1967	7	6	13
1968	8	8	16
1969	4	10	14
1970	5	13	18
1971	1	11	12
1972	2	10	12
1973	1	9	10
1974		6	6
1975		5	5
1976		4	4
1977		2	2
Cosmos B launches

#	Launch id	Payload	Launch date	Site	Status/Comment (orbit in perigee x apogee x inc. x period)
1	62008	Cosmos 0001	16 Mar 1962	K	217 x 980 km x 49.0°
2	62009	Cosmos-2	06 Apr 1962	K	212 x 1546 km x 49.0°
3	62013	Cosmos-3	24 Apr 1962	K	229 x 720 km x 49.0°
4	62020	Cosmos-5	28 May 1962	K	203 x 1600 km x 49.1°
5	62028	Cosmos-6	30 Jun 1962	K	274 x 360 km x 49.0°
6	62038	Cosmos-8	18 Aug 1962	K	256 x 604 km x 49.0°
7	62056	Cosmos-11	20 Oct 1962	K	245 x 921 km x 49.0°
8	63010	Cosmos-14	13 Apr 1963	K	265 x 512 km x 49.0°
9	63017	Cosmos-17	22 May 1963	K	260 x 788 km x 49.0°
10	63033	Cosmos-19	06 Aug 1963	K	270 x 519 km x 49.0°
11	63050	Cosmos-23	13 Dec 1963	K	240 x 613 km x 49.0°
12	64010	Cosmos-25	27 Feb 1964	K	272 x 526 km x 49.0°
13	64013	Cosmos-26	18 Mar 1964	K	271 x 403 km x 49.0°
14	64028	Cosmos-31	06 Jun 1964	K	228x 508 km x 49.0°
15	64042	Cosmos-36	30 Jul 1964	K	259x 503 km x 49.0°
16	64050	Cosmos-42/43	22 Aug 1964	K	232x 1099 km x 49.0°
17	64069	Cosmos-49	24 Oct 1964	K	260x 490 km x 49.0°
18	64080	Cosmos-51	10 Dec 1964	K	264x 554 km x 48.8°
19	65006	Cosmos-53	30 Jan 1965	K	227 x 1192 km x 48.8°
20	65052	Cosmos-70	02 Jul 1965	K	229 x 1154 km x 48.8°
21	65059	Cosmos-76	23 Jul 1965	K	261 x 530 km x 48.8°
22	65084	Cosmos-93	19 Oct 1965	K	220 x 522 km x 48.4°
23	65088	Cosmos-95	04 Nov 1965	K	207 x 521 km x 48.4°
24	65095	Cosmos-97	26 Nov 1965	K	220 x 2100 km x 49.0°
25	65107	Cosmos-101	21 Dec 1965	K	260 x 550 km x 49.0°
26	66004	Cosmos-106	25 Jan 1966	K	290 x 564 km x 48.4°
27	66011	Cosmos-108	11 Feb 1966	K	227 x 865 km x 48.9°
28	66036	Cosmos-116	26 Apr 1966	K	294 x 478 km x 48.4°
29	66043	Cosmos-119	24 May 1966	K	219 x 1305 km x 48.5°
30	66061	Cosmos-123	08 Jul 1966	K	263 x 529 km x 48.8°
31	66112	Cosmos-135	12 Dec 1966	K	259 x 662 km x 48.5°
32	66117	Cosmos-137	21 Dec 1966	K	230 x 1720 km x 48.8°
33	67013	Cosmos-142	14 Feb 1967	K	214 x 1362 km x 48.4°
34	67019	Cosmos-145	03 Mar 1967	K	220 x 2135 km x 48.4°
35	67023	Cosmos-148	16 Mar 1967	P	275 x 436 km x 71.0°
36	67024	Cosmos-149	21 Mar 1967	K	248 x 297 km x 48.4°
37	67028	Cosmos-152	25 Mar 1967	P	283 x 512 km x 71.0°
38	67056	Cosmos-163	05 Jun 1967	K	261 x 616 km x 48.4°
39	67059	Cosmos-165	12 Jun 1967	P	211 x 1542 km x 81.9°
40	67061	Cosmos-166	16 Jun 1967	K	283 x 578 km x 48.4°
41	67081	Cosmos-173	24 Aug 1967	P	280 x 528 km x 71.0°
42	67086	Cosmos-176	12 Sep 1967	P	206 x 1581 km x 81.9°
43	67115	Cosmos-191	21 Nov 1967	P	281 x 518 km x 71.0°
44	67125	Cosmos-196	19 Dec 1967	K	224 x 884 km x 49.0°
45	67126	Cosmos-197	26 Dec 1967	K	219 x 502 km x 48.5°
46	68010	Cosmos-202	20 Feb 1968	K	220 x 502 km x 48.4°
47	68015	Cosmos-204	05 Mar 1968	P	282 x 873 km x 71.0°
48	68028	Cosmos-211	09 Apr 1968	P	210 x 1574 km x 81.9°
49	68033	Cosmos-215	19 Apr 1968	K	261 x 426 km x 48.5°
50	68038	Cosmos-219	26 Apr 1968	K	222 x 1770 km x 48.4°
51	68043	Cosmos-221	24 May 1968	K	220 x 2108 km x 48.4°
52	68044	Cosmos-222	30 May 1968	P	277 x 528 km x 71.0°
53	68048	Cosmos-225	12 Jun 1968	K	257 x 530 km x 48.4°
54	68056	Cosmos-230	05 Jul 1968	K	290 x 580 km x 48.5°
55	68061	Cosmos-233	18 Jul 1968	P	210 x 2545 km x 82.0°
56	68079	Cosmos-242	20 Sep 1968	P	280 x 440 km x 71.0°
57	68083	Cosmos-245	03 Oct 1968	P	282 x 509 km x 71.0°
58	68107	Cosmos-257	03 Dec 1968	P	282 x 470 km x 71.0°
59	68113	Cosmos-259	14 Dec 1968	K	219 x 1353 km x 48.5°
60	68117	Cosmos-261	19 Dec 1968	P	217 x 670 km x 71.0°
61	68119	Cosmos-262	26 Dec 1968	K	263 x 818 km x 48.5°
62	69012	Cosmos-265	07 Feb 1969	P	283 x 485 km x 71.0°
63	69020	Cosmos-268	05 Mar 1969	K	219 x 2186 km x 48.4°
64	69031	Cosmos-275	28 Mar 1969	P	284 x 805 km x 71.0°
65	69033	Cosmos-277	04 Apr 1969	P	280 x 494 km x 71.0°
66	69047	Cosmos-283	27 May 1969	P	210 x 1539 km x 82.0°
67	69049	Cosmos-285	03 Jun 1969	P	279 x 518 km x 71.0°
68	69073	Cosmos-295	22 Aug 1969	P	282 x 500 km x 71.0°
69	69088	Intercosmos 01	14 Oct 1969	K	260 x 640 km x 48.4°
70	69090	Cosmos-303	18 Oct 1969	P	282 x 4920 km x 71.0°
71	69094	Cosmos-307	24 Oct 1969	K	220 x 2178 km x 48.4°
72	69096	Cosmos-308	04 Nov 1969	P	281 x 422 km x 71.0°
73	69102	Cosmos-311	24 Nov 1969	P	284 x 496 km x 71.0°
74	69106	Cosmos-314	11 Dec 1969	P	282 x 491 km x 71.0°
75	69110	Intercosmos-2	25 Dec 1969	K	206 x 1200 km x 48.4°
76	70004	Cosmos-319	15 Jan 1970	P	209 x 1537 km x 82.0°
77	70005	Cosmos-320	16 Jan 1970	K	240 x 343 km x 48.5°
78	70006	Cosmos-321	20 Jan 1970	P	280 x 507 km x 71.0°
79	70014	Cosmos-324	27 Feb 1970	P	446 x 705 km x 71.0°
80	70020	Cosmos-327	18 Mar 1970	P	269 x 822 km x 70.9°
81	70033	Cosmos-334	23 Apr 1970	P	272 x 483 km x 70.9°
82	70035	Cosmos-335	24 Apr 1970	K	249 x 400 km x 48.4°
83	70043	Cosmos-347	12 Jun 1970	K	215 x 2050 km x 48.4°
84	70044	Cosmos-348	13 Jun 1970	P	200 x 652 km x 71.0°
85	70051	Cosmos-351	27 Jun 1970	P	270 x 467 km x 71.0°
86	70057	Intercosmos-3	07 Aug 1970	K	200 x 1295 km x 48.4°
87	70059	Cosmos-356	10 Aug 1970	P	232 x 573 km x 81.9°
88	70063	Cosmos-357	19 Aug 1970	P	272 x 476 km x 71.0°
89	70073	Cosmos-362	16 Sep 1970	P	272 x 817 km x 71.0°
90	70081	Cosmos-369	08 Oct 1970	P	269 x 505 km x 70.9°
91	70084	Intercosmos-4	14 Oct 1970	K	251 x 627 km x 48.4°
92	70100	Cosmos-380	24 Nov 1970	P	199 x 1519 km x 81.9°
93	70112	Cosmos-388	18 Dec 1970	P	270 x 505 km x 71.0°
94	71002	Cosmos-391	14 Jan 1971	P	267 x 803 km x 70.9°
95	71007	Cosmos-393	26 Jan 1971	P	274 x 484 km x 71.0°
96	71037	Cosmos-408	24 Apr 1971	P	211 x1542 km x 81.8°
97	71044	Cosmos-421	19 May 1971	P	283 x 492 km x 70.9°
98	71047	Cosmos-423	27 May 1971	P	282 x 511 km x 71.0°
99	71072	Cosmos-435	27 Aug 1971	P	282 x 505 km x 71.0°
100	71079	Cosmos-440	24 Sep 1971	P	282 x 814 km x 71.0°
101	71090	Cosmos-453	19 Oct 1971	P	281 x 522 km x 71.0°
102	71097	Cosmos-455	17 Nov 1971	P	282 x 516 km x 71.0°
103	71101	Cosmos-458	29 Nov 1971	P	281 x 523 km x 71.0°
104	71104	Intercosmos-5	02 Dec 1971	K	205 x 1200 km x 48.4°
105	71113	Cosmos-467	17 Dec 1971	P	279 x 502 km x 71.0°
106	72004	Cosmos-472	25 Jan 1972	P	207 x 1568 km x 82.0°
107	72020	Cosmos-481	25 Mar 1972	P	279 x 540 km x 71.0°
108	72023	Cosmos-485	11 Apr 1972	P	280 x 506 km x 71.0°
109	72033	Cosmos-487	21 Apr 1972	P	278 x 531 km x 71.0°
110	72047	Intercosmos-7	30 Jun 1972	K	267 x 568 km x 48.4°
111	72048	Cosmos-497	30 Jun 1972	P	282 x 812 km x 71.0°
112	72050	Cosmos-498	05 Jul 1972	P	282 x 511 km x 71.0°
113	72054	Cosmos-501	12 Jul 1972	K	222 x 2149 km x 48.5°
114	72078	Cosmos-523	05 Oct 1972	P	283 x 507 km x 71.0°
115	72080	Cosmos-524	11 Oct 1972	P	277 x 537 km x 71.0°
116	72084	Cosmos-526	25 Oct 1972	P	282 x 511 km x 71.0°
117	72094	Intercosmos-8	30 Nov 1972	P	214 x 679 km x 71.0°
118	73004	Cosmos-545	24 Jan 1973	P	279 x 521 km x 71.0°
119	73020	Cosmos-553	12 Apr 1973	P	262 x 519 km x 71.0°
120	73022	Intercosmos-9	19 Apr 1973	K	202 x 1551 km x 48.4°
121	73029	Cosmos-558	17 May 1973	P	279 x 526 km x 71.0°
122	73035	Cosmos-562	05 Jun 1973	P	282 x 510 km x 71.0°
123	73057	Cosmos-580	22 Aug 1973	P	283 x 518 km x 71.0°
124	73075	Cosmos-601	16 Oct 1973	P	210 x 1561 km x 82.0°
125	73091	Cosmos-608	20 Nov 1973	P	281 x 528 km x 71.0°
126	73094	Cosmos-611	28 Nov 1973	P	270 x 507 km x 71.0°
127	73099	Cosmos-615	13 Dec 1973	P	280 x 859 km x 71.0°
128	74010	Cosmos-633	27 Feb 1974	P	280 x 516 km x 71.0°
129	74012	Cosmos-634	05 Mar 1974	P	281 x 516 km x 71.0°
130	74047	Cosmos-662	26 Jun 1974	P	290 x 795 km x 70.9°
131	74058	Cosmos-668	25 Jul 1974	P	281 x 519 km x 71.0°
132	74074	Cosmos-686	26 Sep 1974	P	281 x 515 km x 71.0°
133	74091	Cosmos-695	20 Nov 1974	P	283 x 493 km x 71.0°
134	75003	Cosmos-703	21 Jan 1975	P	207 x 1545 km x 82.0°
135	75006	Cosmos-705	28 Jan 1975	P	281 x 508 km x 71.0°
136	75026	Cosmos-725	08 Apr 1975	P	283 x 540 km x 71.0°
137	75058	Cosmos-745	24 Jun 1975	P	274 x 540 km x 71.0°
138	75067	Cosmos-750	17 Jul 1975	P	281 x 830 km x 71.0°
139	76012	Cosmos-801	05 Feb 1976	P	290 x 723 km x 71.0°
140	76044	Cosmos-818	18 May 1976	P	281 x 506 km x 71.0°
141	76083	Cosmos-849	13 Aug 1976	P	276 x 889 km x 71.0°
142	76084	Cosmos-850	26 Aug 1976	P	280 x 518 km x 71.0°
143	77025	Cosmos-901	05 Apr 1977	P	279 x 845 km x 71.0°
144	77051	Cosmos-919	18 Jun 1977	P	278 x 847 km x 71.0°
Notes: K for Kapustin Yar, P for Plesetsk launches


 Cosmos C

by Jean-Jacques Serra

Origin: IRBM of first generation

The second realization of M.K. Yangel at SKB-586 in Dniepropetrosk (now NPO Yuzhnoye), Ukraine, was the R14 (SS-5 Skean), 4000 kg range. This single stage rocket was 24.3 m high and 2.4 m diameter and weighed 50 tons. It was powered by 2 RD-216 motors with 2 chambers each, consuming nitric acid and UDMH. The motors provided 863 kN thrust in vacuum during 170 seconds (Isp = 291 s).

The R14 was first launched in 1960 in Kapustin Yar and became operational in 1962. It was used as a probe since 1975. It can launch 1300 kg at 500 km or 860 kg at 1500 km altitude.

Cosmos 2 (C1 / SL8)

The first use of the R14 as a space launcher was in 1964. It was equipped with a top stage, same diameter as the first one, whose motor (unidentified) use NTO/UDMH. Jane's Space Directory claims it can burn for 375 seconds with 157 kN thrust. It can be re-ignited to circularize an orbit.

This 106 tons launcher, approx. 32 m high. It is still used as 11K65. It can orbit 1.7 tons in LEO, but its missions generally limits to place 1 ton into 800 to 1500 km altitude orbit.  This is the only launcher to have been fired from Baikonour, Plesetsk and Kapustin Yar. It was used for:

- geodesy and military or civilian navigation (Parus, Tsikada, etc.)

- telecommunications mainly military (Strela) but also civilian

- ELINT

- interception targets, radar calibration

- technology (BOR-4 mini shuttles)

- scientific (Cosmos, Intercosmos, Aureole, etc.)

Launch statistics

	Baikonour	Plesetsk	Kapustin Yar	Total
1964	1			1
1965	6			6
1966				0
1967	1	3		4
1968	1	5		6
1969		6		6
1970		10		10
1971		19		19
1972		13		13
1973		14	1	15
1974		16	1	17
1975		17	1	18
1976		27	1	28
1977		26	2	28
1978		20	1	21
1979		16	2	18
1980		15	1	16
1981		17	1	18
1982		18	4	22
1983		18	4	22
1984		16	2	18
1985		10	1	11
1986		15		15
1987		12	1	13
1988		7		7
1989		9		9
1990		10		10
1991		10		10
1992		7		7
1993		6		6
1994		5		5
Cosmos C launches

#	Launch id	Payload	Launch date	Site	Status/Comment (orbit in perigee x apogee x inc. x period)
1	64046	Cosmos-38/40	18 Aug 1964	T	210 x 876 km x 56.2°
2	65011	Cosmos-54/56	21 Feb 1965	T	280 x 1856 km x 56.1°
3	65020	Cosmos-61/63	15 Mar 1965	T	273 x 1887 km x 56.0°
4	65053	Cosmos-71/75	16 Jul 1965	T	540 x 600 km x 56.1°
5	65070	Cosmos-80/84	03 Sep 1965	T	1440 x 1550 km x 56.0°
6	65073	Cosmos-86/90	18 Sep 1965	T	1340 x 1670 km x 56.0°
7	65112	Cosmos-103	28 Dec 1965	T	600 x 600 km x 56.0°
8	67027	Cosmos-151	24 Mar 1967	T	630 x 630 km x 56.0°
9	67045	Cosmos-158	15 May 1967	P	850 x 850 km x 74.4°
10	67108	Cosmos-189	30 Oct 1967	P	535 x 600 km x 74.0°
11	67116	Cosmos-192	23 Nov 1967	P	755 x 7550 km x 74.0°
12	68006	Cosmos-200	20 Jan 1968	P	536 x 536 km x 74.0°
13	68011	Cosmos-203	20 Feb 1968	P	1200 x 1200 km x 74.1°
14	68040	Cosmos-220	07 May 1968	P	670 x 760 km x 74.0°
15	68070	Cosmos-236	27 Aug 1968	T	600 x 655 km x 56.0°
16	68095	Cosmos-250	30 Oct 1968	P	523 x 556 km x 74.0°
17	68106	Cosmos-256	30 Nov 1968	P	1168 x 1234 km x 74.1°
18	69021	Cosmos-269	05 Mar 1969	P	526 x 558 km x 74.0°
19	69024	Cosmos-272	17 Mar 1969	P	1195 x 1220 km x 74.0°
20	69070	Cosmos-292	14 Aug 1969	P	747 x 7866 km x 74.0°
21	69091	Cosmos-304	21 Oct 1969	P	747 x 774 km x 74.0°
22	69103	Cosmos-312	24 Nov 1969	P	1145 x 1187 km x 74.0°
23	69107	Cosmos-315	20 Dec 1969	P	521 x 556 km x 74.1°
24	70024	Cosmos-330	07 Apr 1970	P	512 x 549 km x 74.1°
25	70028	Cosmos-332	11 Apr 1970	P	755 x 761 km x 74.0°
26	70036	Cosmos-336/343	25 Jun 1970	P	1412 x 1490 km x 74.0°
27	70064	Cosmos-358	20 Aug 1970	P	515 x 539 km x 74.0°
28	70083	Cosmos-371	12 Oct 1970	P	746 x 761 km x 74.0°
29	70086	Cosmos-372	16 Oct 1970	P	785 x 806 km x 74.1°
30	70097	Cosmos-378	17 Nov 1970	P	233 x 1741 km x 74.0°
31	70102	Cosmos-381	02 Dec 1970	P	985 x 1023 km x 74.0°
32	70108	Cosmos-385	12 Dec 1970	P	978 x 986 km x 74.0°
33	70111	Cosmos-387	16 Dec 1970	P	528 x 537 km x 74.0°
34	71010	Cosmos-394	09 Feb 1971	P	574 x 619 km x 65.9°
35	71013	Cosmos-395	17 Feb 1971	P	529 x 545 km x 74.0°
36	71020	Cosmos-400	18 Mar 1971	P	996 x 1016 km x 65.8°
37	71035	Cosmos-407	23 Apr 1971	P	799 x 844 km x 74.1°
38	71038	Cosmos-409	28 Apr 1971	P	1185 x 1222 km x 74.0°
39	71041	Cosmos-411/418	07 May 1971	P	1405 x 1530 km x 74.5°
40	71046	Cosmos-422	22 May 1971	P	994 x 1020 km x 74.0°
41	71050	Cosmos-425	29 May 1971	P	511 x 556 km x 74.0°
42	71052	Cosmos-426	04 Jun 1971	P	394 x 2012 km x 74.0°v
43	71074	Cosmos-436	07 Sep 1971	P	514 x 550 km x 74.0°
44	71075	Cosmos-437	10 Sep 1971	P	523 x 559 km x 74.0°
45	71086	A: Cosmos 0444 B: Cosmos 0445 C: Cosmos 0446 D: Cosmos 0447 E: Cosmos 0448 F: Cosmos 0449 G: Cosmos 0450 H: Cosmos 0451	13 Oct 1971	P	1415 x 1550 km x 74.0°
46	71099	Cosmos-457	20 Nov 1971	P	1129 x 1192 km x 74.0°
47	71102	Cosmos-459	29 Nov 1971	P	226 x 277 km x 65.8°
48	71103	Cosmos-460	30 Nov 1971	P	520 x 553 km x 74.0°
49	71105	Cosmos-461	02 Dec 1971	P	490 x 524 km x 69.2°
50	71111	Cosmos-465	15 Dec 1971	P	984 x 1023 km x 74.0°
51	71114	Cosmos-468	17 Dec 1971	P	788 x 830 km x 74.0°
52	71119	Aureole 1	27 Dec 1971	P	410 x 2500 km x 74.0°
53	72009	Cosmos-475	25 Feb 1972	P	977 x 1013 km x 74.0°
54	72017	Cosmos-479	22 Mar 1972	P	517 x 549 km x 74.0°
55	72019	Cosmos-480	25 Mar 1972	P	1183 x 1212 km x 83.0°
56	72035	Cosmos-489	06 May 1972	P	980 x 1010 km x 74.0°
57	72043	Cosmos-494	23 Jun 1972	P	791 x 825 km x 74.0°
58	72053	Cosmos 0500	10 Jul 1972	P	509 x 554 km x 74.0°
59	72057	A: Cosmos 0504 B: Cosmos 0505 C: Cosmos 0506 D: Cosmos 0507 E: Cosmos 0508 F: Cosmos 0509 G: Cosmos 0510 H: Cosmos 0511	19 Jul 1972	P	1425 x 1504 km x 74.0°
60	72062	Cosmos-514	16 Aug 1972	P	959 x 999 km x 83.0°
61	72074	Cosmos-521	29 Sep 1972	P	965 x 1192 km x 65.9°
62	72087	Cosmos-528/535	01 Nov 1972	P	1375 x 1495 km x 74.0°
63	72088	Cosmos-536	03 Nov 1972	P	514 x 555 km x 74.0°
64	72102	Cosmos-539	21 Dec 1972	P	1353 x 1392 km x 74.0°
65	72104	Cosmos-540	25 Dec 1972	P	779 x 823 km x 74.0°
66	73003	Cosmos-544	20 Jan 1973	P	513 x 561 km x 74.0°
67	73005	Cosmos-546	26 Jan 1973	K	584 x 630 km x 50.7°
68	73010	Cosmos-549	28 Feb 1973	P	513 x 556 km x 74.0°
69	73037	Cosmos-564/571	08 Jun 1973	P	1395 x 1485 km x 74.0°
70	73042	Cosmos-574	20 Jun 1973	P	996 x 1026 km x 83.0°
71	73060	Cosmos-582	28 Aug 1973	P	521 x 559 km x 74.0°
72	73064	Cosmos-585	08 Sep 1973	P	1385 x 1416 km x 74.0°
73	73065	Cosmos-586	14 Sep 1973	P	986 x 1020 km x 83.0°
74	73069	A: Cosmos 0588 B: Cosmos 0589 C: Cosmos 0590 D: Cosmos 0591 E: Cosmos 0592 F: Cosmos 0593 G: Cosmos 0594 H: Cosmos 0595	03 Oct 1973	P	1397 x 1512 km x 74.0°
75	73082	Intercosmos-10	30 Oct 1973	P	265 x 1477 km x 74.0°
76	73093	Cosmos-610	27 Nov 1973	P	515 x 560 km x 74.0°
77	73098	Cosmos-614	04 Dec 1973	P	770 x 830 km x 74.0°
78	73104	Cosmos-617/624	19 Dec 1973	P	1400 x 1487 km x 74.0°
79	73107	Aureole 2	26 Dec 1973	P	407 x 1995 km x 74.0°
80	73109	Cosmos-627	29 Dec 1973	P	974 x 1019 km x 82.9°
81	74001	Cosmos-628	18 Jan 1974	P	975 x 1026 km x 83.0°
82	74005	Cosmos-631	06 Feb 1974	P	522 x 656 km x 74.0°
83	74024	A: Cosmos 0641 B: Cosmos 0642 C: Cosmos 0643 D: Cosmos 0644 E: Cosmos 0645 F: Cosmos 0646 G: Cosmos 0647 H: Cosmos 0648	23 Apr 1974	P	1385 x 1508 km x 74.0°
84	74028	Cosmos-650	29 Apr 1974	P	1380 x 1413 km x 74.0°
85	74034	Intercosmos-11	17 May 1974	K	483 x 511 km x 50.6°
86	74035	Cosmos-655	21 May 1974	P	520 x 549 km x 74.0°
87	74044	Cosmos-660	18 Jun 1974	P	409 x 1995 km x 83.0°
88	74045	Cosmos-661	21 Jun 1974	P	514 x 544 km x 74.0°
89	74048	Cosmos-663	27 Jun 1974	P	983 x 1017 km x 83.0°
90	74069	Cosmos-675	30 Aug 1974	P	1370 x 1429 km x 74.0°
91	74071	Cosmos-676	11 Sep 1974	P	799 x 840 km x 74.0°
92	74072	A: Cosmos 0677 B: Cosmos 0678 C: Cosmos 0679 D: Cosmos 0680 E: Cosmos 0681 F: Cosmos 0682 G: Cosmos 0683 H: Cosmos 0684	19 Sep 1974	P	1451 x 1519 km x 74.0°
93	74076	Cosmos-687	11 Oct 1974	P	292 x 717 km x 74.0°
94	74079	Cosmos-689	19 Oct 1974	P	992 x 1032 km x 83.0°
95	74086	Intercosmos-12	31 Oct 1974	P	264 x 708 km x 74.1°
96	74100	Cosmos-698	18 Dec 1974	P	515 x 566 km x 74.0°
97	74105	Cosmos-700	26 Dec 1974	P	976 x 1012 km x 83.0°
98	75008	Cosmos-707	05 Feb 1975	P	505 x 550 km x 74.0°
99	75012	Cosmos-708	12 Feb 1975	P	1387 x 1428 km x 82.9°
100	75016	A: Cosmos 0711 B: Cosmos 0712 C: Cosmos 0713 D: Cosmos 0714 E: Cosmos 0715 F: Cosmos 0716 G: Cosmos 0717 H: Cosmos 0718	28 Feb 1975	P	1449 x 1530 km x 74.0°
101	75022	Intercosmos-13	27 Mar 1975	P	296 x 1714 km x 83.0°
102	75028	Cosmos-726	11 Apr 1975	P	972 x 1008 km x 83.0°
103	75033	Aryabhata	19 Apr 1975	K	569 x 610 km x 50.7°
104	75034	Cosmos-729	23 Apr 1975	P	995 x 1023 km x 83.0°
105	75045	A: Cosmos 0732 B: Cosmos 0733 C: Cosmos 0734 D: Cosmos 0735 E: Cosmos 0736 F: Cosmos 0737 G: Cosmos 0738 H: Cosmos 0739	28 May 1975	P	1475 x 1532 km x 74.0°
106	n/a	Intercosmos	03 Jun 1975	P	failure
107	75062	Cosmos-749	04 Jul 1975	P	511 x 557 km x 74.0°
108	75069	Cosmos-752	24 Jul 1975	P	480 x 526 km x 65.9°
109	75074	Cosmos-755	14 Aug 1975	P	991 x 1025 km x 82.9°
110	75086	Cosmos-761/768	17 Sep 1975	P	1454 x 1537 km x 74.0°
111	75089	Cosmos-770	24 Sep 1975	P	1188 x 1222 km x 83.0°
112	75094	Cosmos-773	30 Sep 1975	P	791 x 828 km x 74.1°
113	75103	Cosmos-778	04 Nov 1975	P	989 x 1018 km x 83.0°
114	75109	Cosmos-781	21 Nov 1975	P	508 x 557 km x 74.0°
115	75112	Cosmos-783	28 Nov 1975	P	797 x 838 km x 74.0°
116	75115	Intercosmos-14	11 Dec 1975	P	345 x 1707 km x 74.0°
117	76001	Cosmos-787	06 Jan 1976	P	519 x 564 km x 74.0°
118	76005	Cosmos-789	21 Jan 1976	P	993 x 1029 km x 83.0°
119	76007	Cosmos-790	23 Jan 1976	P	513 x 559 km x 74.0°
120	76008	Cosmos-791/798	28 Jan 1976	P	1453 x 1538 km x 74.0°
121	76011	Cosmos-800	03 Feb 1976	P	1000 x 1027 km x 83.0°
122	76014	Cosmos-803	12 Feb 1976	P	554 x 624 km x 66.0°
123	76022	Cosmos-807	12 Mar 1976	P	403 x 1985 km x 83.0°
124	76031	Cosmos-812	06 Apr 1976	P	504 x 558 km x 74.0°
125	76037	Cosmos-816	28 Apr 1976	P	482 x 525 km x 65.9°
126	76049	Cosmos-822	28 May 1976	P	284 x 729 km x 74.0°
127	76051	Cosmos-823	03 Jun 1976	P	996 x 1023 km x 83.0°
128	76054	Cosmos-825/832	15 Jun 1976	P	1450 x 1530 km x 74.0°
129	76056	Intercosmos-15	19 Jun 1976	P	487 x 520 km x 74.0°
130	76061	Cosmos-836	29 Jun 1976	P	796 x 843 km x 74.0°
131	76067	Cosmos-839	08 Jul 1976	P	984 x 2102 km x 65.9°
132	76069	Cosmos-841	15 Jul 1976	P	789 x 826 km x 74.0°
133	76070	Cosmos-842	21 Jul 1976	P	987 x 1023 km x 83.0°
134	76075	Cosmos-845	27 Jul 1976	P	505 x 557 km x 74.0°
135	76076	Intercosmos-16	27 Jul 1976	K	465 x 876 km x 50.6°
136	76078	Cosmos-846	30 Jul 1976	P	967 x 1025 km x 83.0°
137	76098	Cosmos-858	29 Sep 1976	P	792 x 833 km x 74.0°
138	76108	Cosmos-864	29 Oct 1976	P	980 x 1021 km x 83.0°
139	76115	Cosmos-870	02 Dec 1976	P	514 x 560 km x 74.0°
140	76118	Cosmos-871/878	07 Dec 1976	P	1480 x 1520 km x 74.0°
141	76120	Cosmos-880	09 Dec 1976	P	562 x 624 km x 66.0°
142	76122	Cosmos-883	15 Dec 1976	P	975 x 1073 km x 83.0°
143	76124	Cosmos-885	17 Dec 1976	P	470 x 513 km x 66.0°
144	76128	Cosmos-887	28 Dec 1976	P	973 x 1030 km x 83.0°
145	77004	Cosmos-890	20 Jan 1977	P	1000 x 1032 km x 83.0°
146	77006	Cosmos-891	02 Feb 1977	P	466 x 518 km x 65.8°
147	77011	Cosmos-893	15 Feb 1977	P	341 x 1703 km x 74.0°
148	77013	Cosmos-894	21 Feb 1977	P	988 x 1026 km x 83.0°
149	77022	Cosmos-899	25 Mar 1977	P	505 x 552 km x 74.1°
150	77023	Cosmos-900	30 Mar 1977	P	460 x 523 km x 83.0°
151	77031	Cosmos-906	27 Apr 1977	K	466 x 523 km x 50.7°
152	77036	Cosmos-909	19 May 1977	P	991 x 2112 km x 65.8°
153	77039	Cosmos-911	25 May 1977	P	984 x 1018 km x 82.9°
154	77042	Cosmos-913	31 May 1977	P	475 x 523 km x 74.0°
155	77049	Signe 3	17 Jun 1977	K	457 x 522 km x 50.6°
156	77059	Cosmos-923	01 Jul 1977	P	804 x 842 km x 74.0°
157	77060	Cosmos-924	05 Jul 1977	P	514 x 560 km x 74.0°
158	77062	Cosmos-926	09 Jul 1977	P	997 x 1025 km x 82.9°
159	77064	Cosmos-928	13 Jul 1977	P	977 x 1022 km x 83.0°
160	77067	Cosmos-930	19 Jul 1977	P	482 x 528 km x 74.0°
161	77070	Cosmos-933	22 Jul 1977	P	385 x 418 km x 65.8°
162	77079	Cosmos-939/946	24 Aug 1977	P	1448 x 1518 km x 74.0°
163	77087	Cosmos-951	13 Sep 1977	P	989 x 1029 km x 83.0°
164	77096	Intercosmos-17	24 Sep 1977	P	468 x 519 km x 83.0°
165	77101	Cosmos-959	21 Oct 1977	P	153 x 890 km x 66.0°
166	77103	Cosmos-960	25 Oct 1977	P	505 x 549 km x 74.0°
167	77107	Cosmos-962	28 Oct 1977	P	983 x 1022 km x 83.0°
168	77109	Cosmos-963	23 Nov 1977	P	1182 x 1210 km x 82.9°
169	77111	Cosmos-965	08 Dec 1977	P	469 x 520 km x 74.0°
170	77116	Cosmos-967	13 Dec 1977	P	973 x 1013 km x 66.0°
171	77119	Cosmos-968	16 Dec 1977	P	783 x 822 km x 74.0°
172	77122	Cosmos-971	23 Dec 1977	P	993 x 1021 km x 83.0°
173	78005	Cosmos-976/983	10 Jan 1978	P	1450 x 1500 km x 74.0°
174	78007	Cosmos-985	17 Jan 1978	P	960 x 1032 km x 83.0°
175	78019	Cosmos-990	17 Feb 1978	P	783 x 824 km x 74.0°
176	78022	Cosmos-991	28 Feb 1978	P	972 x 1022 km x 83.0°
177	78028	Cosmos-994	15 Mar 1978	P	996 x 1023 km x 82.9°
178	78031	Cosmos-996	28 Mar 1978	P	970 x 1021 km x 82.9°
179	78034	Cosmos 1000	31 Mar 1978	P	978 x 1024 km x 83.0°
180	78046	Cosmos-1006	12 May 1978	P	383 x 417 km x 65.8°
181	78049	Cosmos-1008	17 May 1978	P	501 x 551 km x 74.0°
182	78053	Cosmos-1011	23 May 1978	P	978 x 1026 km x 82.9°
183	78056	Cosmos-1013/1020	07 Jun 1978	P	1456 x 1539 km x 74.0°
184	78063	Cosmos-1023	21 Jun 1978	P	784 x 822 km x 74.1°
185	78074	Cosmos-1027	27 Jul 1978	P	979 x 1015 km x 82.9°
186	78091	Cosmos-1034/1041	04 Oct 1978	P	1458 x 1538 km x 74.0°
187	78099	A: Intercosmos 18 B: Magion 1	25 Oct 1978	P	407 x 768 km x 83.0°
188	78105	Cosmos-1048	17 Nov 1978	P	788 x 824 km x 74.0°
189	78109	Cosmos-1051/1058	05 Dec 1978	P	1451 x 1530 km x 74.0°
190	78115	Cosmos-1062	15 Dec 1978	P	508 x 548 km x 74.0°
191	78119	Cosmos-1064	21 Dec 1978	P	435 x 991 km x 83.0°
192	78120	Cosmos-1065	23 Dec 1978	K	346 x 556 km x 50.7°
193	78122	Cosmos-1067	26 Dec 1978	P	1184 x 1226 km x 83.0°
194	79003	Cosmos-1072	16 Jan 1979	P	983 x 1030 km x 83.0°
195	79010	Cosmos-1075	08 Feb 1979	P	475 x 521 km x 65.8°
196	79020	Intercosmos-19	28 Feb 1979	P	502 x 996 km x 74.0°
197	79026	Cosmos-1081/1088	15 Mar 1979	P	1455 x 1586 km x 74.0°
198	79026	Cosmos-1089	21 Mar 1979	P	986 x 1016 km x 83.0°
199	79028	Cosmos-1091	07 Apr 1979	P	985 x 1024 km x 83.0°
200	79030	Cosmos-1092	12 Apr 1979	P	983 x 1021 km x 83.0°
201	79046	Cosmos-1104	31 May 1979	P	979 x 1022 km x 83.0°
202	79051	Bhaskara 1	07 Jun 1979	K	512 x 557 km x 50.7°
203	79060	Cosmos-1110	28 Jun 1979	P	792 x 833 km x 74.0°
204	79063	Cosmos-1112	06 Jul 1979	K	345 x 552 km x 50.7°
205	79065	Cosmos-1114	11 Jul 1979	P	507 x 558 km x 74.0°
206	79078	Cosmos-1125	28 Aug 1979	P	795 x 834 km x 74.0°
207	79084	Cosmos-1130/1137	26 Sep 1979	P	1446 x 1514 km x 74.0°
208	79089	Cosmos-1140	11 Oct 1979	P	781 x 818 km x 74.0°
209	79090	Cosmos-1141	16 Oct 1979	P	976 x 1014 km x 82.9°
210	79096	Intercosmos-20	01 Nov 1979	P	467 x 523 km x 74.0°
211	79100	Cosmos-1146	05 Dec 1979	P	441 x 497 km x 65.9°
212	80003	Cosmos-1150	14 Jan 1980	P	989 x 1023 km x 83.0°
213	80007	Cosmos-1153	25 Jan 1980	P	983 x 1031 km x 83.0°
214	80012	Cosmos-1156/1163	11 Feb 1980	P	1450 x 1528 km x 74.0°
215	80022	Cosmos-1168	18 Mar 1980	P	981 x 1026 km x 82.9°
216	80023	Cosmos-1169	27 Mar 1980	P	478 x 521 km x 65.8°
217	80026	Cosmos-1171	03 Apr 1980	P	976 x 1017 km x 65.8°
218	80037	Cosmos-1179	14 May 1980	P	310 x 1570 km x 83.0°
219	80039	Cosmos-1181	20 May 1980	P	992 x 1020 km x 83.0°
220	80047	Cosmos-1186	06 Jun 1980	P	473 x 519 km x 74.0°
221	80056	Cosmos-1190	01 Jul 1980	P	792 x 829 km x 74.0°
222	80058	Cosmos-1192/1199	09 Jul 1980	P	1451 x 1522 km x 74.0°
223	80067	Cosmos-1204	31 Jul 1980	K	346 x 546 km x 50.7°
224	80083	Cosmos-1215	14 Oct 1980	P	499 x 553 km x 74.0°
225	80097	Cosmos-1225	05 Dec 1980	P	967 x 1041 km x 82.9°
226	80099	Cosmos-1226	10 Dec 1980	P	982 x 1025 km x 83.0°
227	80102	Cosmos-1228/1235	24 Dec 1980	P	1415 x 1491 km x 74.0°
228	81003	Cosmos-1238	16 Jan 1981	P	411 x 1976 km x 83.0°
229	81006	Cosmos-1241	21 Jan 1981	P	973 x 1009 km x 65.8°
230	81011	Intercosmos-21	06 Feb 1981	P	475 x 520 km x 74.0°
231	81013	Cosmos-1244	12 Feb 1981	P	975 x 1024 km x 82.9°
232	81022	Cosmos-1250/1257	06 Mar 1981	P	1450 x 1500 km x 74.0°
233	81033	Cosmos-1263	09 Apr 1981	P	430 x 1989 km x 83.0°
234	81041	Cosmos-1269	07 May 1981	P	797 x 833 km x 74.0°
235	81053	Cosmos-1275	04 Jun 1981	P	983 x 1026 km x 83.0°
236	81074	Cosmos-1287/1294	06 Aug 1981	P	1446 x 1508 km x 74.0°
237	81077	Cosmos-1295	12 Aug 1981	P	966 x 1026 km x 82.9°
238	81084	Cosmos-1302	28 Aug 1981	P	783 x 824 km x 74.0°
239	81087	Cosmos-1304	04 Sep 1981	P	917 x 984 km x 83.0°
240	81091	Cosmos-1308	18 Sep 1981	P	978 x 1017 km x 82.9°
241	81095	Cosmos-1310	23 Sep 1981	P	478 x 524 km x 65.9°
242	81097	Cosmos-1311	29 Sep 1981	P	470 x 521 km x 83.0°
243	81115	Bhaskara 2	20 Nov 1981	K	514 x 557 km x 50.7°
244	81116	Cosmos-1320/1327	28 Nov 1981	P	1507 x 1632 km x 74.0°
245	81120	Radio 3 to 8	17 Dec 1981	P	1685 x 1794 km x 83.0°
246	82001	Cosmos-1331	07 Jan 1982	P	776 x 819 km x 74.0°
247	82003	Cosmos-1333	14 Jan 1982	P	989 x 1029 km x 82.9°
248	82007	Cosmos-1335	29 Jan 1982	P	487 x 535 km x 74.0°
249	82012	Cosmos-1339	18 Feb 1982	P	975 x 1029 km x 82.9°
250	82024	Cosmos-1344	24 Mar 1982	P	987 x 1023 km x 82.9°
251	82026	Cosmos-1345	31 Mar 1982	P	507 x 550 km x 74.0°
252	82030	Cosmos-1349	08 Apr 1982	P	989 x 1025 km x 83.0°
253	82034	Cosmos-1351	21 Apr 1982	K	349 x 555 km x 50.7°
254	82037	Cosmos-1354	28 Apr 1982	P	795 x 829 km x 74.0°
255	82040	Cosmos-1357/1364	06 May 1982	P	1449 x 1520 km x 74.0°
256	82051	Cosmos-1371	01 Jun 1982	P	793 x 833 km x 74.1°
257	82054	Cosmos-1374	03 Jun 1982	K	158 x 204 km x 50.7°
258	82055	Cosmos-1375	06 Jun 1982	P	990 x 1021 km x 65.9°
259	82061	Cosmos-1380	18 Jun 1982	P	156 x 732 km x 82.9°
260	82066	Cosmos-1383	29 Jun 1982	P	1004 x 1041 km x 83.0°
261	82069	Cosmos-1386	07 Jul 1982	P	965 x 1010 km x 83.0°
262	82073	Cosmos-1388/1395	21 Jul 1982	P	1448 x 1515 km x 74.0°
263	82076	Cosmos-1397	29 Jul 1982	K	346 x 549 km x 50.7°
264	82102	Cosmos-1417	19 Oct 1982	P	978 x 1023 km x 83.0°
265	82104	Cosmos-1418	21 Oct 1982	K	362 x 417 km x 50.7°
266	82109	Cosmos-1420	11 Nov 1982	P	782 x 820 km x 74.0°
267	82121	Cosmos-1427	29 Dec 1982	P	460 x 494 km x 65.8°
268	83001	Cosmos-1428	12 Jan 1983	P	972 x 1017 km x 82.9°
269	83002	Cosmos-1429/1436	19 Jan 1983	P	629 x 678 km x 81.2°
270	83017	Cosmos-1445	15 Mar 1983	K	158 x 208 km x 50.7°
271	83021	Cosmos-1447	25 Mar 1983	P	975 x 1025 km x 83.0°
272	83023	Cosmos-1448	28 Mar 1983	P	977 x 1017 km x 83.0°
273	83027	Cosmos-1450	07 Apr 1983	P	474 x 515 km x 65.9°
274	83031	Cosmos-1452	12 Apr 1983	P	786 x 826 km x 74.0°
275	83034	Cosmos-1453	19 Apr 1983	P	473 x 520 km x 74.0°
276	83042	Cosmos-1459	06 May 1983	P	960 x 1028 km x 83.0°
277	83046	Cosmos-1463	19 May 1983	P	307 x 1530 km x 82.9°
278	83048	Cosmos-1464	24 May 1983	P	985 x 1022 km x 82.9°
279	83049	Cosmos-1465	26 May 1983	K	349 x 551 km x 50.7°
280	83069	Cosmos-1473/1480	06 Jul 1983	P	1488 x 1511 km x 74.0°
281	83079	Cosmos-1486	03 Aug 1983	P	786 x 820 km x 74.1°
282	83091	Cosmos-1494	31 Aug 1983	K	341 x 561 km x 50.7°
283	83101	Cosmos-1501	30 Sep 1983	P	470 x 516 km x 82.9°
284	83102	Cosmos-1502	05 Oct 1983	P	372 x 411 km x 65.8°
285	83103	Cosmos-1503	12 Oct 1983	P	791 x 827 km x 74.0°
286	83108	Cosmos-1506	26 Oct 1983	P	969 x 1026 km x 83.0°
287	83111	Cosmos-1508	11 Nov 1983	P	400 x 1964 km x 83.0°
288	83120	Cosmos-1513	08 Dec 1983	P	977 x 1029 km x 83.0°
289	83125	Cosmos-1517	27 Dec 1983	K	208 x 288 km x 50.7°
290	84001	Cosmos-1522/1529	05 Jan 1984	P	1449 x 1510 km x 74.0°
291	84003	Cosmos-1531	11 Jan 1984	P	994 x 1023 km x 82.9°
292	84007	Cosmos-1534	26 Jan 1984	P	470 x 519 km x 65.8°
293	84010	Cosmos-1535	01 Feb 1984	P	974 x 1029 km x 83.0°
294	84019	Cosmos-1538	21 Feb 1984	P	781 x 820 km x 74.0°
295	84043	Cosmos-1550	11 May 1984	P	993 x 1025 km x 83.0°
296	84046	Cosmos-1553	17 May 1984	P	997 x 1020 km x 82.9°
297	84052	Cosmos-1559/1566	28 May 1984	P	1444 x 1512 km x 74.0°
298	84056	Cosmos-1570	08 Jun 1984	P	792 x 830 km x 74.0°
299	84062	Cosmos-1574	21 Jun 1984	P	985 x 1021 km x 83.0°
300	84067	Cosmos-1577	27 Jun 1984	P	974 x 1023 km x 83.0°
301	84068	Cosmos-1578	28 Jun 1984	K	296 x 1673 km x 50.7°
302	84100	Cosmos-1598	13 Sep 1984	P	987 x 1029 km x 83.0°
303	84104	Cosmos-1601	27 Sep 1984	P	477 x 521 km x 65.8°
304	84109	Cosmos-1605	11 Oct 1984	P	969 x 1031 km x 82.9°
305	84118	Cosmos-1610	15 Nov 1984	P	987 x 1027 km x 83.0°
306	84126	Cosmos-1614	19 Dec 1984	K	208 x 228 km x 50.7°
307	84127	Cosmos-1615	20 Dec 1984	P	437 x 501 km x 65.9°
308	85006	Cosmos-1624	17 Jan 1985	P	787 x 825 km x 74.0°
309	85011	Cosmos-1627	01 Feb 1985	P	977 x 1031 km x 82.9°
310	85018	Cosmos-1631	27 Feb 1985	T	474 x 517 km x 65.9°
311	85022	Cosmos-1634	14 Mar 1985	P	976 x 1024 km x 82.9°
312	85023	Cosmos-1635/1642	21 Mar 1985	P	1482 x 1526 km x 74.0°
313	85041	Cosmos-1655	30 May 1985	P	992 x 1019 km x 82.9°
314	85050	Cosmos-1662	19 Jun 1985	P	478 x 521 km x 65.9°
315	85079	Cosmos-1680	04 Sep 1985	P	787 x 822 km x 74.1°
316	85089	Cosmos-1688	02 Oct 1985	K	347 x 548 km x 50.7°
317	85110	Cosmos-1704	28 Nov 1985	P	986 x 1023 km x 82.9°
318	85116	Cosmos-1709	19 Dec 1985	P	982 x 1026 km x 82.9°
319	86002	Cosmos-1716/1723	09 Jan 1986	P	1447 x 1516 km x 74.0°
320	86005	Cosmos-1725	16 Jan 1986	P	989 x 1016 km x 82.9°
321	86008	Cosmos-1727	23 Jan 1986	P	982 x 1029 km x 82.9°
322	86030	Cosmos-1741	18 Apr 1986	P	784 x 824 km x 74.0°
323	86037	Cosmos-1745	23 May 1986	P	984 x 1024 km x 83.0°
324	86042	Cosmos-1748/1755	06 Jun 1986	P	1400 x 1500 km x 74.0°
325	86047	Cosmos-1759	18 Jun 1986	P	985 x 1016 km x 82.9°
326	86052	Cosmos-1763	16 Jul 1986	P	761 x 814 km x 74.1°
327	86067	Cosmos-1776	03 Sep 1986	P	478 x 521 km x 74.0°
328	86070	Cosmos-1777	09 Sep 1986	P	781 x 819 km x 74.0°
329	86083	Cosmos-1788	27 Oct 1986	P	468 x 517 km x 65.8°
330	86086	Cosmos-1791	13 Nov 1986	P	972 x 1026 km x 83.0°
331	86092	Cosmos-1794/1801	21 Nov 1986	P	1500 x 1500 km x 74.0°
332	86093	Cosmos-1802	24 Nov 1986	P	985 x 1038 km x 83.0°
333	86100	Cosmos-1808	17 Dec 1986	P	995 x 1033 km x 83.0°
334	87006	Cosmos-1814	21 Jan 1987	P	775 x 815 km x 74.0°
335	87007	Cosmos-1815	22 Jan 1987	K	345 x 550 km x 50.7°
336	87009	Cosmos-1816	29 Jan 1987	P	980 x 1024 km x 82.9°
337	87017	Cosmos-1821	18 Feb 1987	P	983 x 1029 km x 82.9°
338	87049	Cosmos 1850	09 Jun 1987	P	783 x 806 km x 74.0°
339	87051	A: Cosmos 1852 B: Cosmos 1853 C: Cosmos 1854 D: Cosmos 1855 E: Cosmos 1856 F: Cosmos 1857 G: Cosmos 1858 H: Cosmos 1859	16 Jun 1987	P	1440 x 1507 km x 74.0°
340	87054	Cosmos 1861	23 Jun 1987	P	982 x 997 km x 82.9°
341	87057	Cosmos-1864	07 Jul 1987	P	977 x 1019 km x 83.0°
342	87061	Cosmos-1868	14 Jul 1987	P	279 x 726 km x 74.0°
343	87087	Cosmos-1891	14 Oct 1987	P	957 x 1030 km x 83.0°
344	87098	Cosmos-1898	01 Dec 1987	P	777 x 810 km x 74.0°
345	87103	Cosmos-1902	15 Dec 1987	P	373 x 417 km x 66.0°
346	87106	Cosmos-1904	23 Dec 1987	P	969 x 1008 km x 82.9°
347	88016	A: Cosmos 1924 B: Cosmos 1925 C: Cosmos 1926 D: Cosmos 1927 E: Cosmos 1928 F: Cosmos 1929 G: Cosmos 1930 H: Cosmos 1931	11 Mar 1988	P	1400 x 1500 km x 74.0°
348	88023	Cosmos 1934	22 Mar 1988	P	952 x 1009 km x 83.0°
349	88029	Cosmos-1937	05 Apr 1988	P	774 x 813 km x 74.0°
350	88053	Cosmos-1954	21 Jun 1988	P	780 x 806 km x 74.0°
351	88060	Cosmos 1958	14 Jul 1988	P	375 x 417 km x 65.8°
352	88062	Cosmos 1959	18 Jul 1988	P	975 x 1019 km x 83.0°
353	88065	Cosmos 1960	28 Jul 1988	P	475 x 518 km x 65.9°
354	89005	Cosmos 1992	26 Jan 1989	P	777 x 814 km x 74.0°
355	89012	Cosmos 2002	14 Feb 1989	P	187 x 2315 km x 65.8°
356	89017	Cosmos 2004	22 Feb 1989	P	993 x 1031 km x 83.0°
357	89025	A: Cosmos 2008 B: Cosmos 2009 C: Cosmos 2010 D: Cosmos 2011 E: Cosmos 2012 F: Cosmos 2013 G: Cosmos 2014 H: Cosmos 2015	24 Mar 1989	P	1445 x 1510 km x 74.0°
358	89028	Cosmos 2016	04 Apr 1989	P	970 x 1010 km x 82.9°
359	89042	Cosmos 2026	07 Jun 1989	P	970 x 1020 km x 82.9°
360	89045	Cosmos 2027	14 Jun 1989	P	480 x 510 km x 65.8°
361	89050	Nadezhda 1	04 Jul 1989	P	980 x 1020 km x 83.0°
362	89059	Cosmos 2034	25 Jul 1989	P	970 x 1010 km x 82.9°
363	90004	Cosmos 2056	18 Jan 1990	P	775 x 810 km x 74.0°
364	90012	Cosmos 2059	06 Feb 1990	P	190 x 2280 km x 65.8°
365	90017	Nadezhda 2	27 Feb 1990	P	956 x 1021 km x 83.0°
366	90023	Cosmos 2061	20 Mar 1990	P	973 x 1017 km x 82.9°
367	90029	A: Cosmos 2064 B: Cosmos 2065 C: Cosmos 2066 D: Cosmos 2067 E: Cosmos 2068 F: Cosmos 2069 G: Cosmos 2070 H: Cosmos 2071	06 Apr 1990	P	1415 x 1563 km x 74.0°
368	90036	Cosmos 2074	20 Apr 1990	P	967 x 1006 km x 83.0°
369	90038	Cosmos-2075	25 Apr 1990	P	515 x 584 km x 74.0°
370	90078	Cosmos-2098	28 Aug 1990	P	407 x 2001 km x 82.9°
371	90083	Cosmos 2100	14 Sep 1990	P	984 x 1027 km x 82.9°
372	90111	Cosmos 2112	10 Dec 1990	P	770 x 820 km x 74.1°
373	91006	Informator	29 Jan 1991	P	960 x 1000 km x 83.0°
374	91007	Cosmos 2123	05 Feb 1991	P	981 x 1019 km x 82.9°
375	91009	Cosmos-2125/2132	12 Feb 1991	P	1452 x 1495 km x 74.0°
376	91013	Cosmos-2135	26 Feb 1991	P	925 x 1020 km x 82.8°
377	91019	Nadezhda 3	12 Mar 1991	P	960 x 1000 km x 82.9°
378	91021	Cosmos-2137	19 Mar 1991	T	448 x 495 km x 65.8°
379	91029	Cosmos 2142	16 Apr 1991	P	983 x 1031 km x 83.0°
380	91041	Cosmos-2150	11 Jun 1991	P	780 x 810 km x 74.0°
381	91059	Cosmos-2154	22 Aug 1991	P	990 x 1020 km x 82.9°
382	91072	Cosmos-2164	10 Oct 1991	P	290 x 720 km x 74.0°
383	91081	Cosmos 2173	27 Nov 1991	P	965 x 1030 km x 82.9°
384	92008	Cosmos-2180	17 Feb 1992	P	980 x 1030 km x 82.9°
385	92012	Cosmos-2181	09 Mar 1992	P	995 x 1030 km x 82.9°
386	92020	Cosmos-2184	15 Apr 1992	P	990 x 1030 km x 82.9°
387	92030	Cosmos-2187 to 2194	03 Jun 1992	P	1445 x 1505 km x 74.0°
388	92036	Cosmos-2195	01 Jul 1992	P	975 x 1025 km x 82.9°
389	92053	Cosmos-2208	12 Aug 1992	P	790 x 810 km x 74.0°
390	92073	Cosmos 2218	29 Oct 1992	P	970 x 1015 km x 82.9°
391	93001	Cosmos 2230	12 Jan 1993	P	990 x 1020 km x 83.0°
392	93008	Cosmos 2233	09 Feb 1993	P	970 x 1020 km x 82.9°
393	93020	Cosmos 2239	01 Apr 1993	P	980 x 1010 km x 82.9°
394	93036	Cosmos 2251	16 Jun 1993	P	780 x 820 km x 74.0°
395	93067	Cosmos 2265	26 Oct 1993	P	300 x 1600 km x 82.9°
396	93070	Cosmos 2266	02 Nov 1993	P	960 x 1030 km x 82.9°
397	94024	Cosmos 2279	26 Apr 1994	P	973 x 1019 km x 82.9°
398	94041	Nadezhda 4	14 Jul 1994	P	977 x 1018 km x 82.9°
399	94045	Cosmos 2285	02 Aug 1994	P	974 x 1013 km x 74.0°
400	94061	Cosmos 2292	27 Sep 1994	P	400 x 1950 km x 83.0°
401	94083	Cosmos 2298	20 Dec 1994	P	785 x 810 km x 74.0°
402	95002	Tsikada 1	24 Jan 1995	P	982 x 1031 km x 82.9°
403	95008	Cosmos 2306	02 Mar 1995	P	472 x 519 km x 65.5°
404	95012	Cosmos 2310	22 Mar 1995	P	996 x 1024 km x 82.9°
405	95032	Cosmos 2315	05 Jul 1995	P	988 x 1027 km x 82.9°
406	95052	Cosmos 2321	06 Oct 1995	P	258 x 793 km x 82.9°
407	96004	Cosmos 2327	16 Jan 1996	P	952 x 1021 km x 83.0°
408	96025	Cosmos 2332	24 Apr 1996	P	303 x 1575 km x 83.0°
409	96052	Cosmos 2334	05 Sep 1996	P
410	96071	Cosmos 2336	20 Dec 1996	P
411	97017	Cosmos 2341	17 Apr 1997	P
412	97052	Cosmos 2346	23 Sep 1997	P
	98072	A: Nadezhda 5 B: Astrid 2	10 Dec 1998 at 11:57 UT	P
	98076	Cosmos 2361	24 Dec 1998 at 20:03 UT	P
	99022	Abrixas Megat 0	28 Apr 1999 at 20:30 UT	K
Notes: P stands for launches from Plesetsk, K for launches from Kapustin Yar


 Cyclone

by Jean-Jacques Serra

listing by Gunter Krebs

Origin: ICBM of third generation

In the early sixties, Yangel was successful in the competition opposing the R-9 of Korolev to the UR-200 of Chelomei missiles for the providing of ICBMs of second generation. His two-stage R-16 missile (SS-7 Saddler) was 31 m in height, 3 m diameter and weighed 150 tons. Despite the important accident that occured on first test in October 1960 the R-16 was deployed in 190 silos. A space launcher project derived from the R-16 named 64S2 or Cyclone was abandonned.

The second ICBM of the KB Yantel was the R-26/8K66 missile. It seems that this program did not reach the flight tests phase. (some sources state that R-26 is the ground surface of SS-8)

The third ICBM of the KB Yantel (now NPO Yuzhnoye) in Ukraine was the R-36 /8K67 (SS-9 Scarp). The DoD counted 5 variants of this third generation missile: Mod 1 the original design, Mod 2 the serial model with unique payload. From Mod 3, tested as a FOBS (Fractional Orbit Bomb System), the missile was designated R-36-0/8K69. It was followed by the Mod 4 equipped with 4 MRVs and the Mod 5, an ASAT (AntiSATellite) weapon.

The basic rocket had 2 stages both 3 m diameter wide. The SS-9 Mod 2 was 36 m in height and weighed 190 tons. It was the biggest known missile at that time. The first stage featured a propulsion system with 6 combustion chambers (RD-251) using NTO/UDMH. The engines burned during 120 seconds providing 2450 kN at ground level and 2750 kN in vacuum thrust (Isp = 309 seconds). Four steerable verniers enabled the flight control and the motor thrust balance during the stages separation. The second stage was powered by a two-chambers RD-252 motor burning the same propellants. It provided 883 kN thrust (Isp = 293 seconds) during 125 seconds. Moreover the missile's RV had it's own engine... making the vehicle 3 stages.

The testings went on during several years (1963-65 for Mod 1 & 2, the 1969-70 and 1973 for Mod 4). A total of about 300 missiles were deployed from 1966 on.

2-stage R-36 launchers

In the early sixties two projects of Fractional Orbit Bombardment Systems (FOBS) launchers were being designed by the soviets: the GR-1 (SS-10 Scrag) and the Yantel R-36 in version 3. The former was cancelled after 1965.The second named F1r / SL11 in the US was tested 18 times from Tyuratam between 1966 and 1971: 2 un-official flights in 1966 and 16 Cosmos (including Cosmos 316 which decayed accidentally in the Western USA).

Note: a FOBS-type RV (provided by Khrunichev/KB Saliout) was used in January 1995 for the German & Japanese EXPRESS experiment which was incorrectly orbited by Mu-3S.

The launcher known as F1m / SL-11 was developed as antisatellite system. In a first stage (1968-1970) the same launcher was used from Tyuratam to launch target and interceptors in the Cosmos program. From February 1971 on, targets were launched by Cosmos C1 / SL8 from Plesetsk. The program stopped in 1982.

Meanwhile the launcher would have been equipped on an enhanced second stage for conventional space operations. According to Jane's Space Directory the new motor would provide 956 kN in vacuum (ISp = 324 seconds) during up to 160 seconds. This launcher known as Cyclone 2 (11K79) was used to launch reconnaissance satellites from Tyuratam: Rorsat and Eorsat.

3-stage R-36 launcher: Cyclone 3

In 1977 the two-stage basic model was equipped with a S5M top stage powered by an RD-861 (NTO/UDMH) providing 78 kN thrust during 118 seconds. It could be re-ignited in orbit. In this version Cyclone 3 (11K68) weighs around 185 tons for 39.3 m heigh and a 2.7 m diameter cap.

Launched from Plesetsk it can orbit 3.6 tons in LEO but it is used for satellite in circular 650, 850, 100 or 1500 km altitude:

- civilian satellites: Meteor, Ocean, Intercosmos

- military satellites: SIGINT, geodesy, telecommunications (Gonets)

Commercial version

A firmed named Satellite Delivery Systems, a subsidiary of Rockwell Aerospace (USA) and Younoye (Ukraine) was founded in 1996 to sell Cyclone launchers.

This launcher which flies from Plesetsk was never used to polar-orbit satellites because is should fly over the US (all polar launches are from Tyuratam). Therefore the Cyclone launcher will get an additional top stage. This stage is built by Youjnoye. Its reignitable motor burns stockable propellant (NTO-UDMH) and was already used more than 50 times for military missions.

Cyclone 3 launches

#	Launch id	Payload	Launch date	Status/Comment (orbit in perigee x apogee x inc. x period)
1	77055	Cosmos 921	24 Jun 1977
2	77095	Cosmos 956	24 Sep 1977
3	77123	Cosmos 972	27 Dec 1977
4	78067	Cosmos 1025 [Tselina-D]	28 Jun 1978
5	78100	A: Cosmos 1045 B: RS 1 C: RS 2	26 Oct 1978
6	79011	Cosmos 1076 [Ocean-E]	12 Feb 1979
7	80005	Cosmos 1151 [Ocean-E]	23 Jan 1980
8	n/a	Cosmos (1242) [Geo-IK #[1a]]	23 Jan 1981	Failure
9	81082	Cosmos 1300 [Tselina-D]	24 Aug 1981
10	81093	Auréole 3	21 Sep 1981
11	81098	Cosmos 1312 [Geo-IK]	30 Sep 1981
12	81117	Cosmos 1328 [Tselina-D]	03 Dec 1981
13	82085	Meteor 2-8	25 Mar 1982
14	82059	Cosmos 1378 [Tselina-D]	10 Jun 1982
15	82092	Cosmos 1408 [Tselina-D]	16 Spe 1982
16	82096	Cosmos 1410 [Geo-IK]	29 Sep 1982
17	83037	Cosmos 1455 [Tselina-D]	23 Apr 1983
18	83061	Cosmos 1470 [Tselina-D]	23 Jun 1983
19	83099	Cosmos 1500 [Ocean-OE]	28 Sep 1983
20	83115	Cosmos 1510 [Geo-IK]	24 Oct 1983
21	83122	Cosmos 1515 [Tselina-D]	15 Dec 1983
22	84013	Cosmos 1536 [Tselina-D]	08 Feb 1984
23	84027	Cosmos 1544 [Tselina-D]	15 Mar 1984
24	84072	Meteor 2-11	05 Jul 1984
25	84084	Cosmos 1589 [Geo-IK]	8 Aug 1984
26	84105	Cosmos 1602 [Ocean-OE]	28 Sep 1984
27	84111	Cosmos 1606 [Tselina-D]	18 Oct 1984
28	84120	Cosmos 1612 [Meteor (3-1a)]	27 Nov 1984	Failure: stage 3 failed to reignite
29	85003	Cosmos 1617 - 1622 [Strela-3]	15 Jan 1985
30	85009	Cosmos 1626 [Tselina-D]	24 Jan 1985
31	85013	Meteor 2-12	06 Feb 1985
32	85020	Cosmos 1633 [Tselina-D]	05 Mar 1985
33	85047	Cosmos 1660 [Geo-IK]	14 Jun 1985
34	85058	Cosmos 1666 [Tselina-D]	08 Jul 1985
35	85069	Cosmos 1674 [Tselina-D]	08 Jul 1985
36	85094	Cosmos 1690 - 1695 [Strela-3]	09 Oct 1985
37	85100	Meteor 3-1	24 Oct 1985
38	85108	Cosmos 1703 [Tselina-D]	22 Nov 1985
39	85113	Cosmos 1707 [Tselina-D]	12 Dec 1985
40	85119	Meteor 2-13	26 Dec 1985
41	86006	Cosmos 1726 [Tselina-D]	17 Jan 1986
42	86015	Cosmos 1732 [Geo-IK]	11 Feb 1986
43	86018	Cosmos 1733 [Tselina-D]	19 Feb 1986
44	86034	Cosmos 1743 [Tselina-D]	15 May 1986
45	86039	Meteor 2-14	27 May 1986
46	86046	Cosmos 1758 [Tselina-D]	16 Jun 1986
47	86055	Cosmos 1766 [Ocean-O]	28 Jun 1986
48	86074	Cosmos 1782 [Tselina-D]	30 Sep 1986
49	n/a	Cosmos (1786) - (1791)  [Strela-3]	15 Oct 1986	Failure
50	86094	Cosmos 1803 [Geo-IK]	02 Dec 1986
51	86097	Cosmos 1805 [Tselina-D]	10 Dec 1986
52	86101	Cosmos 1809	18 Dec 1986
53	87001	Meteor 2-15	05 Jan 1987
54	87003	Cosmos 1812 [Tselina-D]	14 Jan 1987
55	87020	Cosmos 1823 [Geo-IK]	20 Feb 1987
56	87024	Cosmos 1825 [Tselina-D]	03 Mar 1987
57	87026	Cosmos 1827 - 1832 [Strela-3]	13 Mar 1987
58	87038	Cosmos 1842 [Tselina-D]	27 Apr 1987
59	87055	Cosmos 1862 [Tselina-D]	01 Jul 1987
60	87062	Cosmos 1869 [Ocean-O]	16 Jul 1987
61	87068	Meteor 2-16	18 Aug 1987
62	87074	Cosmos 1875 - 1880 [Strela-3]	07 Sep 1987
63	87088	Cosmos 1892 [Tselina-D]	20 Oct 1987
64	88001	Cosmos 1908 [Tselina-D]	06 Jan 1988
65	88002	Cosmos 1909 - 1914 [Strela-3]	15 Jan 1988
66	88005	Meteor 2-17	30 Jan 1988
67	88020	Cosmos 1933	15 Mar 1988
68	88046	Cosmos 1950 [Geo-IK]	30 Apr 1988
69	88050	Cosmos 1953 [Tselina-D]	14 Jun 1988
70	88056	Ocean O1-1	5 Jul 1988
71	88064	Meteor 3-2	26 Jul 1988
72	88093	Cosmos 1975	11 Oct 1988
73	88113	Cosmos 1985	23 Dec 1988
74	89009	A: Cosmos 1994 B: Cosmos 1995 C: Cosmos 1996 D: Cosmos 1997 E: Cosmos 1998 F: Cosmos 1999	10 Feb 1989
75	89018	Meteor 2-18	28 Feb 1989
76	n/a	Ocean (2) [Ocean-O]	6 Jun 1989	Failure: 3rd stage
77	89068	Cosmos 2037	28 Aug 1989
78	89074	A: Cosmos 2038 B: Cosmos 2039 C: Cosmos 2040 D: Cosmos 2041 E: Cosmos 2042 F: Cosmos 2043	14 Sep 1989
79	89080	A: Intercosmos 24 (Aktivny-IK) B: Magion 2	28 Sep 1989
80	89086	Meteor 3-03	24 Oct 1989
81	89100	Cosmos 2053 [Radar-Cal-2 #2]	26 Dec 1989
82	90010	Cosmos 2058	30 Jan 1990
83	90018	Ocean O1-2	28 Feb 1990
84	90057	Meteor 2-19	27 Jun 1990
85	90066	Cosmos 2088 [Geo-IK]	30 Jun 1990
86	90070	Cosmos 2090 - 2095 [Strela-3]	8 Aug 1990
87	90086	Meteor 2-20	28 Sep 1990
88	90104	Cosmos 2106 [Tselina-D]	28 Nov 1990
89	90114	Cosmos 2114 - 2119 [Strela-3]	22 Dec 1990
90	91030	Meteor 3-4	24 Apr 1991
91	91033	Cosmos 2143 - 2148 [Strela-3]	16 May 1991
92	91039	Ocean O1-3	4 Jun 1991
93	91042	Cosmos 2151 [Tselina-D]	13 Jun 1991
94	91056	Meteor 3-05	15 Aug 1991
95	91068	Cosmos 2157 - 2162 [Strela-3]	28 Sep 1991
96	91077	Cosmos 2165 - 2170 [Strela-3]	12 Nov 1991
97	91086	A: Intercosmos 25 (Apex) E: Magion 3	18 Dec 1991
98	92042	Cosmos 2197, 2198, 2200, 2202 [Strela-3] Cosmos 2199,2201 [Gonets-D]	13 Jul 1992
99	92068	Cosmos 2211 - 2116 [Strela-3]	20 Oct 1992
100	92080	Cosmos 2221	24 Nov 1992
101	92092	Cosmos 2226 [Geo-IK]	22 Dec 1992
102	92094	Cosmos 2228 [Tselina-D]	25 Dec 1992
103	93024	Cosmos 2242	16 Apr 1993
104	93030	A: Cosmos 2245 B: Cosmos 2246 C: Cosmos 2247 D: Cosmos 2248 E: Cosmos 2249 F: Cosmos 2250	11 May 1993
105	93038	A: Cosmos 2252 B: Cosmos 2253 C: Cosmos 2254 D: Cosmos 2255 E: Cosmos 2256 F: Cosmos 2257	25 Jun 1993
106	93055	A: Meteor 2-21 B: Temisat	31 Aug 1993
107	94003	A: Meteor 3-06 B: Tubsat B	25 Jan 1994
108	94011	A: Cosmos 2268 B: Cosmos 2269 C: Cosmos 2270 D: Cosmos 2271 E: Cosmos 2272 F: Cosmos 2273	12 Feb 1994
109	94014	Coronas 1	2 Mar 1994
110	n/a	Cosmos [2281] [Tselina-D]	25 May 1994	Failure: 2nd and 3rd stage failed to separate
111	94066	Ocean O1-4	11 Oct 1994
112	94078	Geo-IK 1	29 Nov 1994
113	94086	A: Cosmos 2299 B: Cosmos 2300 C: Cosmos 2301 D: Cosmos 2302 E: Cosmos 2303 F: Cosmos 2304	28 Dec 1994
114	95046	A: Sich 1 Fasat Alfa	31 Aug 1995	Fasat failed to separate from Sich
115	96009	A: Gonets-D1 1 B: Gonets-D1 2 C: Gonets-D1 3 D: Cosmos 2328 E: Cosmos 2329 F: Cosmos 2330	19 Feb 1996 at 00:58 UT
116	97006	A: Gonets-D1 4 B: Gonets-D1 5 C: Gonets-D1 6 D: Cosmos 2337 E: Cosmos 2338 F: Cosmos 2339	14 Feb 1997 at 03:47 UT
117	98036	A: Cosmos 2352 B: Cosmos 2353 C: Cosmos 2354 D: Cosmos 2355 E: Cosmos 2356 F: Cosmos 2357	15 Jun 1998 at 22:58 UT	Partial failure, the satellites were delivered in wrong orbit Refer to: Cosmos 2357
Notes: All launches from Plesetsk


 Conestoga

by Jean-Jacques Serra

listing by Gunter Krebs

The Conestoga launchers are based on a program of Space Services Inc (SSI) in the early 80ies. The company was bought by EER Systems in December 1990 and became it's Space Service Division.

Percheron project

The first achievement of SSI was a liquid rocket named Percheron. It should have been the base for a launcher series made of modules of 1.2 m diameter and 12 m high with each a motor and a propellant tank. The first Percheron rocket exploded on the first motor static test on the Matagorda island (Texas) launch pad on 5 Aug 1981.

Conestoga 1

Following this failure SSI changed to solid propulsion with missile or rocket elements already operational. For it's first test on 9 Sep 1982 the Conestoga 1 (11.5 m high, 6.5 tons) was based on a single active stage: an Aerojet M56-A1 of 207 kN (the second stage of the Minuteman 1 ICBM) also used for Aries rockets. The flight was a success and the payload was ejected at apogee (313 km).

Note: in the late 80ies SSI started working on commercial flights for microgravity experiments (Consort program). They used Starfire rockets (Canadian Black Brant 9 rockets with a Terrier missile booster).

Conestoga launchers

EER Systems stayed with the modular concept to offer a series of light launchers based on various Thiokol boosters: Castor-4, Star-37 and Star-48.

The most powerful version (Conestoga 1620) features 6 Castor-4 (4 Castor-4B and 2 Castor-4A) surrounding a Castor-4B. Four Castor are on at liftoff (first stage), two more (second stage) and the central Castor acts as the third stage. The Star 48 top stage copes with orbit injection. This launcher is 15.7 m high, 87.3 tons and can deliver 460 km in orbit (40.5°).

The first launch was a failure. There are doubts on the ability of EER to finance another flight.

Configurations

Designation	Length (m)	Diameter (m)	Mass (tons)	Thrust in vaccum (kN)	Burn duration (s)
Castor 4A (TX780)	8.09-9.20	1,02	11,58	436-476	53.1
Castor-4B (TX859)	8,98	1,02	11,48	429	60.9
Star -37 FM (TEM-784)	1,68	0,93	1,15	48	63,7
Star-48 (TEM-711)	2,03	1,25	2,14	66	84
Conestoga launches

#	Launch id	Payload	Launch date	Type	Status (orbit in perigee x apogee x inc. x period)
1	n/a	Meteor (US)	23 Oct 1995 at 22:03 UT	1620	Failure: The vehicle was destroyed 45s into the first stage burn, at an altitude of 11 km
Notes: launches from Wallops


 Diamant

by Jean-Jacques Serra

listing by Gunter Krebs

Origin: Pierre Précieuses (precious stones) experimental rocket series

The SEREB (Société pour l'Etude et la Réalisation d'Engins Balistiques, firm for the study and developpement of ballistic missiles) was founded in 1959 to support the DMA missile department which was in charge of the French strategic ballistic missile programs SSBS and MSBS. Work begin by a ballistic study program to acquire the technology necessary to development of such missiles. This program achieved several carriers in the Pierre Précieuses series: Agate, Topaze, Emeraude and Saphir.

The VE-110 Agate was the first of the series. It was a 1-stage solid-fuel (Isolane) non piloted carrier of 80 cm diameter. The VE-111 Topaze was similar to Agate but guided by 4 rotative nozzles. The VE-121 Emeraude was 1.40 m diameter; it was the first is the series to use liquid propellant (nitric acid and turpentine). The VE-231 Saphir had 2 stages: Emeraude + Topaze. Saphir enabled in-flight experiments of cap release, stage separation, inertial guidance and reentry.

In December 1961 it was decided to build the Diamant launcher by replacing the payload of Saphir by a third stage. In May 1962 CNES selected DMA to manage the Diamant program, SEREB being the prime contractor. The Rubis rocket was designed to test the third stage in-flight, on top of an Agate stage.

Diamant A

The diamant A launcher was made of a 10 m high, 1.4 m diameter Emeraude first stage weighing 14.7 tons. Its Vexin LRBA directional-nozzle motor burned during 93 seconds and delivered 269 kN thrust at sea level (304 kN in vacuum). The second stage was Topaze: 4.7 m high per 80 cm diameter and weighed 2.9 tons. It provided a mean thrust of 156 kN during 44 seconds. The P064 third stage was 2 m high and 65 cm diameter. It weighed 709 kg including 640 kg Isolane (thus its name). It burned for 45 seconds providing 27 to 53 kN thrust. With its cap Diamant was 18.95 m high and weighed 18.4 tons.

Diamant achieved orbiting at first try on 26 Nov 1965. The payload was the simple technological capsule Astérix. After this launch the 3 remaining rockets were used to orbit geodesy satellites (D1 program) between Feb 1966 and Feb 1967. All launches were carried out from the CIEES (Centre InterArmées d'Essais d'Engins Spéciaux, inter-army special machine test center) in Sahara which was closed in July 1967.

Once the Diamant A program ended Rubis was still used as sounding rocket: in July 1967 it delivered an experiment of the Paris-Meudon observatory's space radioastronomy department at 1560 km altitude. The third stage of Diamant A was then used twice as top stage of the Tibère launcher for the Electre experiments between Feb 1971 and Mar 1972.

Diamant B

After Diamant numerous projects appear but CNES decides to built a launcher directly derived from Diamant A. The main evolution was the lengthened first stage which used more energy-providing propellants. This first stage called Améthyste was 14.2 m high, 1.4 m diameter, and 20.1 t weight. Its Valois motor delivered 316 kN thrust at sea level (400 kN in vacuum) during 116 seconds. The second stage was identical the Diamant A's one; The top stage (P068) was also enhanced: 1.67 m high, 80 cm diameter and 50 kN thrust during 46s. With its cap (85 cm diameter instead of 65 cm for Diamant A) Diamant B was 23.5 m high and weighed 24.6 tons.

Six Diamant B were ordered: 2 for CNES and 4 for ELDO (in single stage version) which were to be used to test the PAS (Perigee-Apogee System) for Europa 2. Finaly ELDO dropped the idea and the 5 rocket built were used by CNES.

After the launch of the German Wika technological capsule Diamant B launched Peole (technology) and Tournesol (astronomy). The last 2 launches were failures. All launches occured from the CSG (Centre Spatial Guyanais, Guyana space center) which is operational since April 1968 when the first sounding rocket Veronique was launched.

Diamant BP4

Development of Diamant BP4 started in Jan 1972. It was based on the first and third stage of its ancestor. The new second stage P4 (Rita) was from the ballistic missile MSBS guided by jet deviation (freon injection). It was 2.28 m long and 1.5 m diamter; it provided a mean 180 kN thrust during 55 seconds. With the 1.38 m cap from the Black Arrow program Diamant BP4 was 21.6 m high and weighed 27 tons.

After 1975 France stopped its sounding rocket and national launcher programs to devote entirely to the european Ariane launcher.

Diamant launchers evolution

Designation	First launch	1st stage	2nd stage	3rd stage	300 km	500 km	1000 km
A	1965	Emeraude	Topaze	P064		80
B	1970	Amethyste	Topaze	P068	160	115	25
BP4	1975	Amethyste	Rita	P068	200	153	45
Diamant launches

#	Launch id	Payload	Launch Date	Site	Type	Status/Comment
1	65096	Asterix	26 Nov 1965	H	A
2	66013	Diapason	17 Feb 1966	H	A
3	67011	Diadème 1	08 Fab 1967	H	A	Partial failure: orbit too low
4	67014	Diadème 2	15 Feb 1967	H	A
5	70017	A: Dial-Wika B: Mika	10 Mar 1970	K	B
6	70109	Péole	12 Dec 1970	K	B
7	71030	Tournesol	15 Apr 1971	K	B
8	n/a	Polaire	5 Dec 1971	K	B	Failure: 2nd stage failed
9	n/a	Castor Pollux	22 May 1972	K	B	Failure: 3rd stage failed
10	75010	Starlette	6 Feb 1975	K	BP4
11	75039	A: Pollux B: Castor	17 May 1975	K	BP4
12	75092	Aura	27 Sep 1975	K	BP4

Notes: Launch site: H for Hammaguir, Algeria; K for Kourou


 ISAS launchers

by Jean-Jacques Serra

The first japanese sounding rockets were designed in the mid-50ies bu the TOkyo Department of Applied Industries (TODAI) to contribute to the International Geophysical Year of 1957-58.

In the early sixties, university of Tokyo decided to design 3-stage rockets named Lambda while going on developping new 2-stage sounding rockets of the Kappa series. The most powerful Kappa rockets (9 & 10) weighed 1.5 to 1.7 tons and had 42 cm base stages; despite the Lambda-3 had a 73 cm diameter first stage and weighed over 7 tons. For the International Quiet Sun Year (IQSY) of 1964-65 those launchers performed 1000 km altitude orbit with 100 kg payload. The rocket workgroup at University of Tokyo then became the ISAS.

Lambda-4S

In 1965 the TODAI started developping a satellite launcher derived from the Lambda-3 sounding rocket which in its most powerful configuration (Lambda-3H) was able to orbit 100 kg at 2000+ km. This launcher was achieved by adding a fourth stage and solid fuel boosters to Lambda-3.

Four orbit injection attempts were made in Sep & Dec 1966, Apr 1967 and Sep 1969. Those launches occured from Uchinoura (31.2° North, 130.6° East) near Kagoshima on the Kyushu island. Finaly success occured in 1970.

This first Japanese launcher named Lambda-4S was 16.5 m high, weighed 9.5 tons and burned only solid fuel. The first stage was 73 cm in diameter and provided 363 kN during 28 seconds. It was assisted during the first 7 seconds by 2 solid fuel boosters of 255 kN thrust. The second stage (same diameter) provided 118 kN during 28 seconds. The third stage was 50 cm in diameter; it was capable of 64 kN during 27 seconds. The top stage was made of a 113 kg powder bloc providing 7.8 kN during 27 seconds which spherical shield made up the satellite's structure. The latter was only a technological capsule which mass at burn shutdown didn't exceed 23 kg. The vehicle was launched from an inclined ramp. It wasn't piloted; a gyroscopic system only controled the fourth stage's altitude before ignition after the ballistic phase (which follows the third stage shutdown).

On 11 Feb 1970 the Lambda-4S number 5 orbited the first capsule named Ohsumi at 351 km x 5142 km x 31.2°. This is the only object launched by a Lambda rocket... because it was abandonned as a space launcher.

Mu series rockets

Seven months after the successful Lambda-4S orbiting the Japanese fired the first model of a new launcher. The Mu-4S kept the same technology but had much greater performances. It was 23.6 m high, 43.6 tons in weight and could put a 100 kg payload in a 31°, 500 km circular orbit.

It's first stage was 1.41 m in diameter and thrusted 834 kN during 61 seconds. It was assisted by eight 127 kN boosters during the first 5.5 seconds of the flight. The second stage had the same diameter whereas the third was 86 cm and while the 77 cm fourth stage supported a 79 cm diameter cap. The respective thrusts were: 285, 127 and 26.5 kN. The guidance system remained simplistic: only the fourth stage was piloted by jet deviation.

After a failure in September 1970 for the first flight, Mu-4S succeeded the 3 next attempts between Feb 1971 and Aug 1972.

In 1974 a new version of Mu with only 3 stages was introduced. This launcher named Mu-3C was equipped with the old first stage and boosters. The second stage was modified and equipped with a radio-inertial guidance which controlled a jet deviation piloting device (freon injection) and a roll control using lateral propellers. This stage provided 343 kN thrust during 55 seconds. The third stage was inherited from Mu-4S fourth stage; it had 65 kN thrust capability during 45 seconds. It was also under the 1.41 m diameter fuse cap.

This 41.6 t launcher with its 20.2 m height had similar performances to Mu-4S although lowerer at high altitude. It was used 4 times between Feb 1974 and Feb 1979; 3 launches were successful.

A more powerful launcher appeared in 1977: Mu-3H. The first stage was longer than the former one: its solid fuel engine (27 tons) provided 1080 kN during 56 seconds. The cap had been lengthened and could host a fourth stage to reach very elliptical orbits.

Mu-3H was 23.8 m high for 48.7 tons at takeoff. It could orbit 100 kg at 700 km in the 3-stage version and more twice as much in the 4-stage version. It was used 3 times with success between Feb 1977 and Feb 1979 including a launch with 30500 km apogee orbit.

The fourth version of the launcher, Mu-3S, only differed from the former vehicle by the addition of a piloting system to the first stage. It was based on a nozzle freon injection device and on a roll control system provided by 4 gas generators fixed at the end of the 4 empannages. The vehicle had the same performances as Mu-3H performances. It was used to launch 4 satellites between Feb 1980 and Feb 1984.

The next version was Mu-3S2; it was complety modified, only the first stage remained the same. The number of boosters was brought back to two but they mesured 74 cm in height and 285 kN (31 seconds duration). The second stage was lenghtened; it provided 490 kN during 52 seconds. The third stage's diameter was increased to 1.41 m; it provided 108 kN during 82 seconds. The launchers reached 61.2 tons in mass and 27.2 m in height. The orbitable payload which took place in an enlarged cap of 1.65 m diameter was almost twice as heavy as for Mu-3S1: 680 kg at 31°, 250 km altitude.

Mu-3S2 was used 8 times (1 failure) between Jan 1985 and Jan 1995. It launched 2 interplanetary probes to the Moon and to the Halley comet.

Mu-5 series

While the Mu-5 series were based on a 1.41 m diameter first stage Mu-5 uses a new first stage. It is 2.51 m in diameter and much more powerful. It enable the doublement of the payload mass in LEO.

This M-14 stage is 13.7 m long and weighs 80.8 tons with over 70 tons propellant (PBHT) in 2 segments. It provides 3870 kN thrust during 49 seconds. The second stage, M-24, has the same diameter. It is 6.7 m in length and 33.2 tons in mass, including 30 tons solid fuel. It makes use of the FIH (Fire In the Hole) technology, i.e. it is linked to the first stage by a mesh structure and ignited at separation between first and second stage. It provides 1370 kN during 63 seconds.

The third stage M-34 is 4.1 m long and 2.2 m diameter. It used advanced technologies such as a CFRP (Carbon Fiber Reinforced Plastic) envelope and a deployable nozzle which enables to shorten the 3rd stage by 1 meter and to leighten it from 300 kg. Thus is weighs 11 tons including 10 tons propellant and provides 300 kN thrust during 101 seconds.

Mu-5 is 30.5 m high with the cap. It weighs 135 tons. It can place 1.8 tons in low orbit at 240 km. For its first flight on 12 Feb 1997 from Kagoshima it delivered Haruka in correct orbit (220/21000 km).

Configuration summary

Designation	First launch	1st stage	2nd stage	3rd stage	4th stage
Mu-4S	1970	M-10	M-20	M-30	M-40
Mu-3C	1974	M-10	M-22	M-3A
Mu-3H	1977	M-13	M-22	M-3A
Mu-3S	1980	M-13*	M-22	M-3A
Mu-3S2	1985	M-13*	M-23	M-3A
(*) M-13 stage with thrust vector control

Mu launches

#	Launch id	Payload	Launch date	Type	Status/Comment (orbit in perigee x apogee x inc. x period)
1	n/a	MS-F1	25 Sep 1970	Mu-4S	Failure (61 kg)
2	71011	Tansei 1 (MS-T1)	16 Feb 1971	Mu-4S
3	71080	Shinsei (MS-F2)	28 Sep 1971	Mu-4S
4	72064	Denpa (REXS)	19 Aug 1972	Mu-4S
5	74008	Tansei 2 (MS-T2)	16 Feb 1974	Mu-3C
6	75014	Taiyo (SRATS)	24 Feb 1975	Mu-3C
7	n/a	Corsa A	04 Feb 1976	Mu-3C	Failure (86 kg)
8	77012	Tansei 3 (MS-T3)	19 Feb 1977	Mu-3H	824 x 3932 x 65.8 x 134.3
9	78014	Kyokko (Exos A)	04 Feb 1978	Mu-3H
10	78087	Jikiken (Exos B)	16 Sep 1978	Mu-3H
11	79014	Hakucho (Corsa B)	21 Feb 1979	Mu-3C
12	80015	Tansei 4 (MS-T4)	17 Feb 1980	Mu-3S1
13	81017	Hinotori (Astro A)	21 Feb 1981	Mu-3S1
14	83011	Tenma (Astro B)	20 Feb 1983	Mu-3S1
15	84015	Ohzora (Exos C)	14 Feb 1984	Mu-3S1
16	85001	Sakigake/MS-T5	07 Jan 1985	Mu-3S2	probe to Halley comet (138 kg)
17	85073	Suisei/PLANET-A	18 Aug 1985	Mu-3S2	probe to Halley comet (140 kg)
18	87012	Ginga (Astro C)	05 Feb 1987	Mu-3S2
19	89016	Akebono (Exos D)	21 Feb 1989	Mu-3S2
20	90007	Hiten (Muses A) Hagoromo	24 Jan 1990	Mu-3S2	Probe to the Moon (193 kg)
21	91062	Yohkoh (Solar A)	30 Aug 1991	Mu-3S2
22	93011	Asuka (Astro D)	20 Feb 1993	Mu-3S2
23	n/a	EXPRESS	15 Jan 1995	Mu-3S2	Partial failure
24	97005	Haruka (Muses B)	12 Feb 1997	Mu-5
25	98041	Nozomi	3 Jul 1998	Mu-5

Note: All launches from Kagoshima


ISRO launchers
 ISRO vehicles

by Jean-Jacques Serra

listing by Gunter Krebs

Indian founded its space agency ISRO in 1969 and then a Ministry of Space in 1972. The next step was to decide to build a national space launcher.

SLV 3 (Satellite Launch Vehicle) and ASLV (Advanced SLV)

SLV 3 was a 4-stage solid-fuel light launcher (polybutadiene). It was 17.8 tons and 22.7 m high with a 1 m diameter max. Its payload mass in circular 500 km orbit was around 40 kg.

The first stage was 9 m high; it delivered 420 kN t (sea level) thrust during 53 seconds. The second stage (80 cm diameter) operated during 42 seconds and provided 200 kN thrust. The third stage (same diameter as stage 2) was fired for 46 seconds and delivered over 60 kN thrust. The 4th stage (65 cm diameter) was fired for 30 seconds and provided about 22 kN thrust. Two ballistic phases occured during the flight: one after second stage shutdown (until 88 km altitude) and after third stage shutdown (to reach perigee altitude).

Rockets were launched from the Sriharikota base on the Indian East coast. This site is operational since the success of a RH-125 sounding rocket in October 1971. After a first attempt which failed in August 1979 the SLV 3 rocket orbited 3 little Rohini scientific satellites in July 1980, Mai 1981 and April 1983. Then the launcher was abandonned for the ASLV.

ASLV was dirived from SLV 3 by the addition of two boosters which dimensions and performances were similar to those of the first stage. Those boosters provided the takeoff of the vehicle by providing each 440 kN thrust during 49 seconds. This caused the first stage to be modified to operate in the air. ASLV was 24 m high and its capacity reached 150 kg payload in LEO (40 km).

The first two launches were failures in March 1987 and July 1988. Then ASLV orbited two SROSS satellites in May 1992 and May 1994.

Noticeable is the fact the the first stage of the SLV 3 was used from 1989 on as first stage of the experimental Agni IRBM (2500 km range). This is perhaps a unique example of transfert of a civilian stage to a military application.

PSLV (Polar Satellite Launch Vehicle)

PSLV is a 4-stage launcher measuring 44 m high for 2.8 m diameter max, weighing 275 tons.It can orbit around 1 ton payload in sun-synchronous polar orbit.

The first stage is 20 m high and weighs 129 tons. It is powered by a solid fuel motor (HTPB: Hydroxyl-Terminated PolyButadiene) which burns during 100 seconds and provides 3500 kN thrust at sea level (4600 kN in vacuum). It is supported by 6 boosters --switched on by group of two then four-- derived from the SLV 3 and ASLV first stage. Each of those deliver 440 kN thrust at sea level (660 kN in vacuum). The second stage is 11 m high for 2.8 m diameter and weighs 38 tons. Its Vikas motor --built under French SEP licence-- consumes liquid propellant (nitrogen tetraoxide and UDMH: Unsymmetrical DiMethylHydrazine). It provides 725 kN thrust during 150 seconds. The third stage is 3.5 m high and 2 m diameter; it weighs 7 tons. Its solid fuel motor (HTPB) provides 340 kN thrust. The fourth stage protected by a bulb cap is 2.6 m long by 1.34 m diameter. It is propulsed by 2 ergols motors (peroxyde d'azote and MMH: MonoMethylHydrazine) of 7.5 kN thrust each which burn during about 7 minutes.

The first launch failed in Sep 1993 because of a software problem in the guidance system. The second launch in Oct 1994 orbited IRS P2. The next flights are scheduled every 12 to 18 months for the IRS remote sensing satellites.

SLV 3 launches

#	Launch id	Payload	Launch date	Type	Status (orbit in perigee x apogee x inc. x period)
1	n/a	Rohini 1A	10 Aug 1979	SLV 3	Failure
2	80062	Rohini 1B	18 Jul 1980	SLV 3
3	81051	Rohini 2	31 May 1981	SLV 3	Partial failure
4	83033	Rohini 3	17 Apr 1983	SLV 3

Notes: All launches from Sriharikota

ASLV launches

#	Launch id	Payload	Launch date	Type	Status (orbit in perigee x apogee x inc. x period)
1, D1	n/a	Sross 1	24 Mar 1987	ASLV	Failure
2, D2	n/a	Sross 2	12 Jul 1988	ASLV	Failure
3, D3	92028	Sross 3	20 May 1992	ASLV	Partial failure
4, D4	94027	Sross C2	4 May 1994 at 00:00 UT	ASLV

Notes: All launches from Sriharikota

PSLV launches

#	Launch id	Payload	Launch date	Type	Status (orbit in perigee x apogee x inc. x period)
1, D1	n/a	IRS 1E	20 Sep 1993 at 00:12 UT	PSLV	Failure: computer error
2, D2	94068	IRS P2	15 Oct 1994 at 05:07 UT	PSLV
3, D3	96017	IRS P3	21 Mar 1996 at 04:53 UT	PSLV
4, C1	97057	IRS 1D	29 Sep 1997 at 04:47 UT	PSLV	Partial failure: 822 x 306 km (not circular)
5, C2	99029	A: Kitsat 3 B: Tubsat C C: IRS P4	26 May 1999 at 06:22 UT	PSLV

Notes: All launches from Sriharikota (2100 km southeast of New Dehli)


Long March
 Long March (Chang Zheng)

by Jean-Jacques Serra

listing by Gunter Krebs

After the rupture between China and USSR in June 1959 the Chinese started to develop a series a ballistic missiles powered with stockable propellant. The first of these was the CSS-1: a single stage rocket very close to the Soviet SS-3 which was 22 m in length and 1.65 m in diameter that could cover 1100 km. It was tested in the sixties and entered service in 1970. The first Chinese IRBM, the CSS-2 was also single staged. It was 23 m long, 2.23 m diameter and ranged 2500 km. The first in-flight tests were carried out on 1969 and was deployed in 1972. The CSS-3 version with 6500 km range was made by adding a second stage to the CSS-2 (with same diameter). It never entered operational service was was used as the basis of the first Chinese launcher: CZ-1.

CZ-1 launchers

The CZ-1 rocket (Chang Zheng = Long March) was derived from the CSS-3 (also called DF-4 by the Chinese, Dong Feng = East Wind) which was added a solid fuel third stage. The first stage was 17.8 m long and weighed 64.1 tons including 60 tons of propellant (Nitric Acid and UDMH). It was powered by a YF-2A motor featuring 4 chambers of 1100 kN at ground level, burning during 130 seconds (ISp = 241 s). The 5.4 m second stage weighed 15.9 tons including 13.2 tons of ergols (NTO and UDMH). It used a YF-3 motor providing 294 kN thrust in vacuum during 126 seconds (ISp = 287 s). The spin-stabilized third stage required a GF=02 powder bloc weighing 1.8 tons which provides 29 kN thrust.

The full CZ-1 launcher was 29.45 m high for 81.6 tons at takeoff and could orbit a 300 kg payload at 440 km with 70° inclination. It launched the 2 first Chinese satellites from Juiquan in April 1970 and March 1971 after a failure in November 1969.

Enhanced version of this launcher: CZ-1C and CZ-1D completly Chinese and CZ-1M featuring an Italian 3rd stage (IRIS) were announced...

Second generation launchers: FB-1 and CZ-2A/D

The first Chinese ICBM CSS-3 (or DF-5 in the Chinese jargon) was over 30 m high for 3.35 m diameter. It featured two liquid fuel stages (NTO and UDMH) and ranged 11000 km. In-flight tests were carried out in 1979 and only few exemplars (8 to 12 ?) were deployed after 1980.

Its development was carried out in the same time as two space launcher programs: FB-1 (Feng Bao = storm) and CZ-2. Very little is known on the FB-1 but it is probably similar to CZ-2 with lower performances (1.2 tons is LEO against 1.7 tons). Some sources believe the two launchers were developped by two different agencies (SBA (Shanghai Bureau of Astronautics) et la BWYIC (Beijing Wan Yuan Industry Corporation)) from the same specifications. It was launched successfully 4 times from Jiuquan between July 1975 and September 1981; 4 failures and 3 suborbital flights were also reported.

The most important launcher of the other series is the CZ-2C. The CZ-2A was indeed only fired once in November 1974 and the B designation used for the FB-1. The CZ-2C featured a L-140 first stage of 20.5 m long which weighed 151 tons including 142 tons of propellant. It was powered by 4 YF-20 motors of 696 kN thrust at ground level (ISp = 260 s) which burned during 132 seconds. The second stage (L-35) was 7.5 m long and 39 tons (35 tons for propellant). It was equipped with an YF-22 motor providing 762 kN in vacuum (ISp = 290 s) associated with 4 deployable YF-23 verniers providing a total of 44 kN. The main engine burned 110 seconds while the verniers 300 seconds.

The CZ-2C launcher is 32.6 to 35.1 m high (depending on the cap) and weighed about 191 tons. It can deliver 2 to 2.5 tons in LEO. From Juiquan it orbited 9 retrievable FSW-0 (Fanhui Shi Weixing) satellites between November 1975 and August 1987 and 5 FSW-1 since September 1987. An enhanced version named CZ-2D launched two FSW-2 satellites in August 1992 and July 1994.

Three-stage versions of the CZ-2C were announced (with a solid SD or CPKM stage). Only the CZ-2C/SD should be used for Iridium.

CZ-3 launchers

The CZ-3 rocket is a 3-stage launcher which makes use of modified versions of the 2 first stages of CZ-2C (same performances) and adds a cryogenic third stage. This H-8 cryogenic stage is 7.5 m long for 2.25 m diameter. It weighs 10.5 tons including 8.5 tons of propellant (LH2 and LOX). it is equipped with a 4-chamber YF-73 motor providing 44 kN thurst in vacuum (ISp = 420 s). The reignitable motor is used for two burns during 500 and 300 seconds.

This launcher is 43.2 to 43.8 m high and weighs 202 tons. It can orbit 1.4 tons in GTO. It was used from Xichang from January 1984 on to launch Chinese telecommunication satellites of foreign spacecrafts. It should still be used even after the introduction of enhanced versions designated CZ-3A and CZ-3B.

Third generation launchers: CZ-4, CZ-2E and CZ-3A/B

A new Chinese generation was introduced in the late eighties based on a streched L-180 first stage equipped with more powerful motors.

The first launcher to use those new elements was CZ-4 specialy designed for sunsynchronous orbits. The first stage is thus an L-180 with 24.7 m long carrying 138 tons propellant powered during 156 seconds by 4 YF-20 motors which unitary thrust was boosted to 735 kN. The second stage is an modified L-35 with 10.4 m long. Its main engine is a YF-25 of 766 kN assisted by 4 YF-23 verniers. The third stage (L-14) specific to the CZ-4 is 6.2 m long for 2.9 m diameter. It is equipped with a pair of YF-40 engines which burn NTO and UDMH. Their total thrust is 98 kN during 321 seconds (ISp = 303 s). This CZ-4 reaches 42 m high and 250 tons. It can deliver a 1.5 ton payload on sun-synchronous orbit at 900 km. It was used to launch 2 meteorological FY satellites from Taiyuan in Sep 1988 and Sep 1990.

The second launcher to use the L-180 and the enhanced motors is the CZ-2E devoted to heavy GEO payloads. The first stage is an L-180 with 23.7 m long (187 tons propellant) propulsed during 159 seconds by 4 YF-20 motors of 735 kN. It is assisted during 126 seconds by 4 LB-40 boosters of 15.6 m long and 2.25 m diameter (38 tons of propellant each) equipped with the same YF-20 engines. The second stage is an L-90 of 15.5 m long (86 tons ergols) with a YF-25 main engine of 831 kN. It is surrounded by 4 YF-23 verniers. The main engine burns during 300 seconds while the version 413 seconds.

The CZ-2E is 49.7 to 51.2 m high. It weighs 460 tons at takeoff. Its capacity reaches 8.8 tons in LEO but it is only used for geostationary satellites with a solid perigee stage. The first version with the American Thiokol Star-63F could place 3.14 tons in GTO. With the EPKM of the Chinese HCMC (Hexi Chemical & Manufacturing Corp) company used for the first time in Nov 1995 the performance reaches 3.46 tons. After a trial launch in July 1990 the CZ-2E was used to launch several telecommunications satellites from Xichang...

The third launcher based on the L-180 was the CZ-3A also devoted to heavy payloads aimed at GEO. The first stage is a 23 m long L-180 (170 tons of propellant) powered by four 735 kN YF-20 motors. The second stage is a L-35 of 11.5 m long (29.6 tons ergol) with an YF-25 main engine of 766 kN which burns during 110 seconds assited by 4 YF-23 verniers. The new H-18 cryogenic third stage is 8.8 m long and 3.0 m diameter (17.6 tons propellant). It features 2 YF-75 engines providing a total thrust of 157 kN (ISp = 425 s) during 470 seconds in 2 burns.

The CZ-3A has a total of 52.3 m high and 240 tons at takeoff. It can orbit 2.3 tons in GTO. After a trial launch in Feb 1994 to launched a 3rd generation telecommunication DFH satellite in Nov 1994.

The CZ-3B used the CZ-3A with 4 liquid boosters inherited from the CZ-2E. It then weighs 403 tons at takeoff and its capacity reaches 4.85 tons in GTO. It first launch failed in Feb 1996.

CZ-1 launches

#	Launch id	Payload	Launch date	Type	Status/Comment (orbit in perigee x apogee x inc. x period)
1, CZ-1	n/a	R&D suborbital	10 Jan 1970
2, CZ-1	70034	DFH 01	24 Apr 1970
3, CZ-1	71018	DFH 02	3 Mar 1971

Notes: All launches from Juiquan.

CZ-2, 3 & 4 launches

#	Launch id	Payload	Launch date	Site	Type	Status/Comment (orbit in perigee x apogee x inc. x period)
1, CZ-2	n/a	FSW 0	05 Nov 1974	Ji	A?	Failure: 1st stage control system failure
2, CZ-2	75111	FSW 0-1	26 Nov 1975	Ji	C
3, CZ-2	76116	FSW 0-2	07 Dec 1976	Ji	C
4, CZ-2	78011	FSW 0-3	26 Jan 1978	Ji	C
5, CZ-2	82090	FSW 0-4	09 Sep 1982	Ji	C
6, CZ-2	83086	FSW 0-5	19 Aug 1983	Ji	C
7, CZ-3	84008	STTW-T1	29 Jan 1984	Xi		Partial failure: 3rd stage failed to ignite
8, CZ-3	84035	STTW-T2	08 Apr 1984	Xi
9, CZ-2	84098	FSW 0-6	12 Sep 1984	Ji	C
10, CZ-2	85096	FSW 0-7	21 Oct 1985	Ji	C
11, CZ-3	86010	STTW 1	01 Feb 1986	Xi
12, CZ-2	86076	FSW 0-8	06 Oct 1986	Ji	C
13, CZ-2	87067	FSW 0-9	05 Aug 1987	Ji	C
14, CZ-2	87075	FSW 1-1	09 Sep 1987	Ji	C
15, CZ-3	88014	STTW 2	07 Mar 1988	Xi
16, CZ-2	88067	FSW 1-2	05 Aug 1988	Ji	C
17, CZ-4	88080	FY 1-1	06 Sep 1988	Ty
18, CZ-3	88111	STTW 3	22 Dec 1988	Xi
19, CZ-3	90011	STTW 4	04 Feb 1990	Xi
20, CZ-3	90030	Asiasat 1	07 Apr 1990	Xi
21, CZ-2	90059	Badr A	16 Jul 1990	Xi	E (PKM)	Failed to place the Optus model in GTO
22, CZ-4	90081	A: FY 1-2 B: DFH 31 C: DFH 32	03 Sep 1990	Ty
23, CZ-2	90089	FSW 1-3	05 Oct 1990	Ji	C
24, CZ-3	91088	STTW 5	28 Dec 1991	Xi		Partial failure: 3rd stage failed to ignite
25, CZ-2	92051	FSW 2-1	09 Aug 1992	Ji	D
26, CZ-2	92054	Optus B1	13 Aug 1992	Xi	E (Star-63F)
27, CZ-2	92064	A: Freja B: FSW 1-4	06 Oct 1992	Ji	C
28, CZ-2	92090	Optus B2	21 Dec 1992	Xi	E (Star-63F)	Partial failure: payload fairing collapsed
29, CZ-2	93063	FSW 1-5	08 Oct 1993	Ji	C
30, CZ-3	94010	A: SJ 4 B: DFH 3-0	08 Feb 1994	Xi	A
31, CZ-2	94037	FSW 2-2	3 Jul 1994	Ji	D
32, CZ-3	94043	Apstar 1	21 Jul 1994	Xi
33, CZ-2	94055	Optus B3	27 Aug 1994	Xi	E (Star-63F)
34, CZ-3	94080	DFH 3-1	29 Nov 1994	Xi	A
35, CZ-2	n/a	Apstar 2	25 Jan 1995	Xi	E (Star-63F)	Failure: vehicle destroyed due to wind shear
36, CZ-2	95064	Asiasat 2	28 Nov 1995	Xi	E (STPM-17)
37, CZ-2	95073	Echostar 1	28 Dec 1995	Xi	E (?)
38, CZ-3	n/a	Intelsat 708	14 Feb 1996	Xi	B	Failure: attitude control lost within seconds, due to an electrical failure
39, CZ-3	96039	Apstar 1A	03 Jul 1996	Xi		225 x 42184 km x 26.9°
40, CZ-3	96048	DFH 42	18 Aug 1996 at 10:27 UT	Xi		Partial failure: 3rd stage shutdown 48s early
41, CZ-2	96059	FSW 2-3	20 Oct 1996	Ji	D
42, CZ-3	97021	DFH 44	11 May 1997  at 16:17 UT	Xi	A
43, CZ-3	97029	DFH 45	10 Jun 1997 at 12:01 UT	Xi		206 x 35987 km x 28.4°
44, CZ-3	97042	Mabuhay 1	19 Aug 1997 at 17:30 UT	Xi	B	170 x 44499 km x 24.6°
45, CZ-2	97048	2 Iridium MFS (Mass Frequency Simulators) 650 kg each	1 Sep 1997 at 14:00 UT	Ty	C	First flight from Taiyan with Smart Dispenser upper stage
46, CZ-3	97062	Apstar 2R	16 Oct 1997 at 17:13 UT	Xi	B	201 x 47922 km x 24.4°
47, CZ-2	97077	A: Iridium 42 B: Iridium 44	8 Dec 1997 at 07:16 UT	Ty	C-3/SD	SD = Smart Dispenser
48, CZ-2	98018	A: Iridium 51 B: Iridium 61	25 Mar 1998 at 17:01 UT	Ty	C-3/SD
49, CZ-2	98026	A: Iridium 69 B: Iridium 71	2 May 1998	Ty	C-3/SD
50, CZ-3	98034	Chinastar 1	30 May 1998	Xi	B
51, CZ-3	98044	Sinosat 1	18 Jul 1998 at 09:20 UT	Xi	B
52, CZ-2	98048	A: Iridium 78 B: Iridium 76	19 Aug 1998 at 23:01 UT	Ty	C-3/SD
53, CZ-2	98074	A: Iridium 88 B: Iridium 89	19 Dec 1998 at 11:30 UT	Ty	C-3/SD
54, CZ-4	99025	A: FY 1C B: DFH 48	10 May 1999 at 01:33 UT	Ty	4B
55, CZ-2	99032	A: Iridium 14A B: Iridium 21A	11 Jun 1999 at 17:15 UT	Ty	C/SD

Notes: Launch sites: Xi = Xichang, Ji = Jiuquan, Ty = Taiyuan

FB-1 launches

#	Launch id	Payload	Launch date	Type	Status/Comment (orbit in perigee x apogee x inc. x period)
1, FB-1	n/a	R&D suborbital	10 Aug 1972
2, FB-1	n/a	JSSW?	18 Sep 1973		Failure
3, FB-1	n/a	JSSW?	14 Jul 1974		Failure: 2nd stage engine lost thrust
4, FB-1	75070	JSSW 1	26 Jul 1975
5, FB-1	75119	JSSW 2	16 Dec 1975
6, FB-1	76087	JSSW 3	30 Aug 1976
7, FB-1	n/a	JSSW?	10 Nov 1976		Failure
8, FB-1	n/a	(suborbital)	14 Sep 1977
9, FB-1	n/a	(suborbital)	16 Apr 1978
10, FB-1	n/a	SJ?	27 Jul 1979		Failure: 2nd stage thrusters failure
11, FB-1	81093	A: SJ 2 B: SJ 3A C: SJ 3B	19 Sep 1981

Notes: All launches from Juiquan.


 NASDA vehicles

by Jean-Jacques Serra

listing by Gunter Krebs

The NASDA (National Space Development Agency) was founded in October 1969 by the japanese Space Activity Commission to replace the NSDC (National Space Development Center) created in 1964. The NASDA's mission was to bring the application satellite programs to life and to develop launcher capable of orbiting them.

Three sounding rockets were already used by the NASDA for technological tests. Those were the single stage SB solid fuel rocket of 70 kg, the 2-stage 2.3 tons JCR solid fuel rocket and the 2-stage 2.5 tons LSC which was the only Japanese launcher with liquid propellant. The experience gained in the development of the second stage (stockable propellant) will later be used for the LE-3 motor of the N1.

N1 launchers

The N1 was not a Japan made rocket but a Thor-Delta rocket built under licence which second stage had been designed in Japan.

The first stage was a Long Tank Thor of 2.44 m diameter built by Mitsubishi Heavy Indutries (MHI) under McDonnell Douglas licence. It was powered by a 765 kN MB-3 motor (liquid oxygen and kerosene) built by Ishikawajima-Harima Heavy Industries (IHI) under licence Rocketdyne. This first stage was on during 219 seconds with the help of 3 Castor -2 boosters designed by Nissan under Thiokol licence. The second N1 stage was built by MHI with a TRW licence for the verniers. It was 5.44 m long for 1.62 m diameter and weighed 5.8 tons. It was propulsed by a Japanese LE-3 motor (nitrogen tetraoxide and Aerozine 50) which provided 53 kN (ISp = 285 s) in vacuum during 250 seconds. The solid fuel third stage used the Thiokol TEM-364-14 (Star-37N) propulsor capable of 39 kN during 41 seconds. The launcher was radiocontrolled, the guidance and piloting device was built by Nippon Electric Co Ltd, also under licence.

The complete vehicle was then 90.4 tons for 32.6 m high. It provided 1485 kN at takeoff and could orbit 130 kg in GEO.

The N1 launcher enabled to launch between 1975 and 1982 three technological satellites (Kiku 1, Kiku 2 and Kiku 4, one in GEO) and two scientific satellites (Ume 1 and Ume 2). Two other launchers ended as failures with telecommunication satellites (Ayame 1 and Ayame 2) because of the Aerojet apogee stage.

N2 launchers

First launched in 1981 the N2 rocket was a enhancement of the N1 entirely built under US licence. Even though equiped with the same motor, the new first stage had enlarged tanks (23% more fuel) which enabled 269 seconds burns. Moreover it was assisted by 9 Castor -2 boosters (6 fired at takeoff and the 3 remaining at shutdown of the latters) instead of 3.

The second stage used the AJ-10-118FJ motor built by IHI under Aerojet General licence. The re-ignitable motor herited from the Delta used NTO-Ax50 (Aerozine 50) as propellant and thus provided 48.3 kN (ISp = 314 s) with a total uptime of 420 seconds. The Delta inertial guidance system was installed at the top of the second stage. The third stage was the TEM-364-4 (Star-37E) capable of providing 67 kN thrust during 44 seconds, built by Nissan under Thiokol licence. N2 was 134.7 tons for 35.4 m high and developped a 2150 kN at takeoff. It could place 350 kg in GEO or 1.6 tons in 1000 km circular orbit. It was in fact some kind of clone of the Delta Straight-Eight (constant diameter of 2.44 m). It was fired 8 times between Feb 1981 and Feb 1987 to launch:

- 1 technological satellite: Kiku 3

- 2 meteorological satellites: Himawari 2 & Himawari 3

- 4 telecommunication satellites: Sakura 2s and Yuri 2s

- an ocean observation satellite: Momo 1A

H1 launchers

In the mid-1970 Japan carried out researches to build a launcher more powerful than the N series with a top stage using cryogenic propulsion built in Japan.  The first launcher of this new series was H1. It reused the first stage, the boosters and the cap of N2 while the 2nd and 3rd stage were developped in Japan (without US assistance) together with the ISAS and the National Aerospace Laboratory (NAL). The second stage used the LE-5, a cryogenic re-ignatable motor (liquid oxygen and hydrogren) built by MHI, IHI and NAL. It provided a 103 kN thrust (ISp = 448 s) during about 400 seconds. The stage (dry) weighed 1.1 tons and carried 8.7 tons propellant. The third stage designed by Nissan was made of a powder bloc (HTPB) of about 2 tons. It could provide a mean thrust of 92 kN (ISp = 291 s) during 62 seconds.

H1 was 138 tons and 40 m high. It could deliver 550 kg in GEO and 2.2 tons in circular 1000 km orbit (two-stage version). It was used 9 times between 1986 and 1992 for:

- a geodesy satellite: Ajisai with a HAM radio satellite: Fuji

- a technological satellite: Kiku 5

- a meteorology satellite: Himawari 4

- 4 telecommunication satellites: Sakura 3s and Yuri 3s

- an ocean observation satellite: Momo 1b

- a remote sensing satellite: Fuyo 1

H2 launchers

The Japanese Space Activity Commission (SAC) decided in 1984 not to enhance the H1 as planned but to develop an new launcher called H2. This H2 is a modern rocket with combined propulsion (two large solid boosters and a cryogenic main motor) entirely designed in Japan.

Each booster is 23.4 m is height, 1.81 m in diameter and weighs 70.4 tons including 60 tons powder (HTPB; ISp = 273 s) providing 1540 kN thrust during 94 seconds. The main body of 4 m diameter up to the cap has 2 stages. The first stage of 28 m heigh weighs 98.1 tons. It features a liquid oxygen and hydrogen LE-7 motor of 843 kN at ground level (1078 kN in vaccum; ISp = 446 s). The second stage weighs 19.7 tons for 10.6 m high and makes use of an enhanced version of LE-5A, the second stage motor of the H1. It provides 121.5 kN thrust (ISp = 452 s) during 610 seconds in two burns. MHI, the integrator of the launcher, also builds the cryogenic motors while Nissan provides the solid boosters.

H2 is nearly 50 m high and weighs 264 tons at takeoff. It can launch 4 tons in GTO, 5 to 6 tons in sun-synchronous orbit and 10 tons in LEO like for example the unmanned HOPE shuttle. It was launched 4 times since Feb 1994.

N launches

#	Launch id	Payload	Launch date	Type	Status/Comment (orbit in perigee x apogee x inc. x period)
1, N-1	75082	ETS 1	09 Sep 1975	N-1
2, N-2	76019	Ume 1	22 Feb 1976	N-1
3, N-3	77014	ETS 2	23 Feb 1977	N-1
4, N-4	78018	Ume 2	16 Feb 1978	N-1
5, N-5	79009	Ayame 1	6 Feb 1979	N-1	Failure: 3rd stage collided with the payload
6, N-6	80018	Ayame 2	22 Feb 1980	N-1
7, N-7	81012	ETS 4	11 Feb 1981	N-2 (3 stage)
8, N-8	81076	GMS 2	11 Aug 1981	N-2 (3 stage)
9, N-9	82087	ETS 3	3 Sep 1982	N-1
10, N-10	83006	Sakura 2A	4 Feb 1983	N-2 (3 stage)
11, N-11	83081	Sakura 2B	5 Aug 1983	N-2 (3 stage)
12, N-12	84005	Yuri 2A	23 Jan 1984	N-2 (3 stage)
13, N-13	84080	GMS 3	3 Aug 1984	N-2 (3 stage)
14, N-14	86016	Yuri 2B	12 Feb 1986	N-2 (3 stage)
15, N-15	87018	Momo 1A	19 Feb 1987	N-2 (2 stage)

Notes: All launches from Tanegashima.

H1 launches

#	Launch id	Payload	Launch date	Type	Status/Comment (orbit in perigee x apogee x inc. x period)
1, H-15	86061	A: Ajisai B: Fuji 1A	12 Aug 1986	H-1 (2 st,9 SO)
2, H-17	87070	ETS 5	27 Aug 1987	H-1 (3 st,9 SO)
3, H-18	88012	Sakura 3A	19 Feb 1988	H-1 (3 st,9 SO)
4, H-19	88086	Sakura 3B	16 Sep 1988	H-1 (3 st,9 SO)
5, H-20	89070	GMS 4	5 Sep 1989	H-1 (3 st,6 SO)
6, H-21	90013	A: Momo 1B B: Debut C: Fuji 1B	7 Feb 1990	H-1 (2 st,9 SO)
7, H-22	90077	Yuri 3A	28 Aug 1990	H-1 (3 st,9 SO)
8, H-23	91060	Yuri 3B	25 Aug 1991	H-1 (3 st,9 SO)
9, H-24	92007	JERS 1	11 Feb 1992	H-1 (2 st,9 SO)

Notes: All launches from Tanegashima. In type column: st = stages, SO = strap-ons

H2 launches

#	Launch id	Payload	Launch date	Type	Status/Comment (orbit in perigee x apogee x inc. x period)
1, H-26	94007	A: Ryusei B: Myojo	3 Feb 1994 at 22:20 UT	H2
2, H-27	94056	ETS 6	28 Aug 1994	H2 [LAPS]
3, H-28	95011	A: SFU B: GMS 5	18 Mar 1995 at 08:01 UT	H2 (2 SSB)
4,	96046	A: Adeos 1 B: Fuji 2	17 Aug 1996 at 01:53 UT	H2 (2 SSB)
5,	97074	A: TRMM B: ETS 7	27 Nov 1997 at 21:27 UT	H2
6,	98011	Comets	21 Feb 1998 at 07:55 UT	H2 [LAPS]	partial failure: the second burn of the top stage failed (after 44 s); maybe caused by a combustion chamber leak

Notes: All launches from Tanegashima.


 Pegasus

by Jean-Jacques Serra

Orbital Science Corp. (OSC) started the design of the Air-Launched Space Booster (ASLB) alias Pegasus in April 1987. Pegasus is composed of three stages with wings, made of composit structure, powered with solif fuel and inertial guidance.

In it's standard version, Pegasus is 14.8 m long by 1.27 m diameter. It has a triangular flying surface of 6.7 m span and a rear 3-drift empennage. It weighs about 18.3 tons without the payload.

The carrier aircraft (B52 or L1011) jettisons Pegasus at 12000 m altitude at Mach 0.8. The launcher's propulsion is provided by 3 Hercules stages. The first stage is a fixed-nozzle Orion 50S, piloted by aerodynamical control surfaces. It provides 49.6 t thrust during 73 s. The second stage (same diameter) is a flexible-nozzle Orion 50 which delivers 12.5 t thurst during 72 s. The third stage is an Orion 38 with flexible nozzle that burns during 65 seconds providing 4.4 t thrust. The 2nd and 3rd stage mobile nozzles provide yawing and pitching guidance while rolling guidance is made with gas propellers which are also used for attitude control during the ballistic phases, and orientation and initial spin of the payload.

The payload mass of the standard version ranges from 270 to 410 kg depending on the orbit inclination. OSC made enhanced versions available:

- additional 4th stage (liquid fuel): HAPS (Hydrazine Auxiliary Propulsion System)

- lengthement of the 2 first stages (+24% propellant in the first stage, +30% in the second)

This version named Pegasus XL is 16.5 m long and weighs 22.7 tons. Its performance are 60% better than the original design.

Introduced in 1990 Pegasus had a difficult time obtaining a working launcher. Eight standard Pegasus were launched with success, the last one in May 1996. Nowadays only the XL version is produced. The two first launches were failures. After 3 successes the 6th model performed correctly but failed to release its payload.

Pegasus launches

#	Launch id	Payload	Launch Date	Site	Type	Status/Comment (orbit in perigee x apogee x inclination x period)
1	90028	A: Pegsat B: Glomr 2 (USA 055)	5 Apr 1990	E, B52		480 km x 680 km x 94°
2	91051	Microsat 1 to 7	17 Jul 1991	E, B52	HAPS	Partial failure 350 km x 450 km x 82°
3	93009	A: Orbcomm XP 1 B: SCD 1	9 Feb 1993 at 14:30 UT	C, B52		730 km x 790 km x 25°
4	93026	Alexis	25 Apr 1993 at 13:56 UT	E, B52		Satellite damaged
5	94029	Step 2	19 May 1994 at 17:03 UT	E, B52	HAPS	The perigee was lower than expected 600 km x 830 km x 82°
6	n/a	Step 1	27 Jun 1994	V, L1011	XL	Failure: malfunctioned during the first stage burn, had to be destroyed
7	94046	Apex	3 Aug 1994 at 14:39 UT	V, B52		365 km x 2550 km x 70°
8	95017	A: Orbcomm FM 1 B: Orbcomm FM 2 C: Microlab 1	3 Apr 1995	V, L1011
9	n/a	Step 3	22 Jun 1995 at 19:58 UT	V, L1011	XL	Failure: interstage didn't separate from 2nd stage
10	96014	REX 2	09 Mar 1996 at 01:33 UT	V, L1011	XL
11	96031	MSTI 3	17 May 1996 at 02:44 UT	V, L1011
12	96037	TOMS	02 Jul 1996 at 07:48 UT	V, L1011	XL
13	96049	Fast	21 Aug 1996 at 09:47 UT	V, L1011	XL
14	96061	SAC B HETE	4 Nov 1996 at 17:09 UT	W	XL	the 2 payloads failed to separate from the third stage
15	97018	A: Minisat 01 B: Celestis 1	21 Apr 1997 at 11:59 UT	L1011	XL	launched from the Canary islands
16	97037	Orbview 2	1 Aug 1997 at 20:20 UT	V, L1011	XL
17	97047	Forte	29 Aug 1997 at 15:00 UT	V	XL
18	97063	Step 4	22 Oct 1997 at 13:15 UT	W	XL
19	97084	A: Orbcomm FM 5 B: Orbcomm FM 6 C: Orbcomm FM 7 D: Orbcomm FM 8 E: Orbcomm FM 9 F: Orbcomm FM 10 G: Orbcomm FM 11 H: Orbcomm FM 12	23 Dec 1997 at 19:11 UT	W	XL	HAPS fourth stage
20	98012	A: SNOE B: Teledesic 1	26 Feb 1998 at 07:07 UT	V	XL
21	98020	Trace	02 Apr 1998 at 02:42 UT	V	XL
22	98046	A: Orbcomm FM 13 B: Orbcomm FM 14 C: Orbcomm FM 15 D: Orbcomm FM 16 E: Orbcomm FM 17 F: Orbcomm FM 18 G: Orbcomm FM 19 H: Orbcomm FM 20	02 Aug 1998 at 16:24 UT	W	XL HAPS
23	98053	A: Orbcomm FM 21 B: Orbcomm FM 22 C: Orbcomm FM 23 D: Orbcomm FM 24 E: Orbcomm FM 25 F: Orbcomm FM 26 G: Orbcomm FM 27 H: Orbcomm FM 28	23 Sep 1998 at 17:06 UT	W	XL HAPS	HAPS
24	98060	SCD 2	23 Oct 1998 at 00:02 UT	C	H	this first stage carried a NASA experiment to study hypersonic boundary layer separation
25	98070	Swas	6 Dec 1998 at 00:57 UT	V	XL
26	99011	Wire	5 Mar 1999 at 02:56 UT	V	XL
27	99026	Terriers Mublcom	18 May 1999 at 05:09 UT	V	XL/H

Notes: in the launch site column C stands for Cape Canaveral and released at sea, E stands for Edwards and released at Point Arguello, V stands for Vandenberg and released at Point Arguello, and W stands for Wallops. This indication is followed by the airplane type

Future

OSC plans to equip Pegasus XL with two turbojets. Once released at 12000 m altitude the Pegasus Turbo will be accelerated by its turbojets to reach 30000 m altitude at over Mach 4. OSC claims the 30.8 t Pegasus Turbo will be 125% more powerful than Pegasus XL and could orbit 1000 kg in LEO.


Pegasus: other future flights

SeaWifs

Forte

Minisat

24 Orbcomm FM xx

Orbview (1m imaging satellite OSC plans to launch in late 1997. Planning is already starting on OrbView 2, which will have the same resolution over a wider swath (15km instead of 4km), longer life, and a radar system to supplement its optics.)


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 Proton

by Jean-Jacques Serra

listing by Gunter Krebs

The first activity of the Chelomei OKB-52 located at Reoutov near Moscow was navy missiles manufacturing. In 1959 it started producing the solid propulsion UR-96 ABM and the UR-100 (SS-11 Sego) ICBM with stockable liquid propellant. The Miassichtchev OKB-23 and the Latvotchkin OKB-301 were joined to it in 1960 and 1962 respectively.

First generation Proton

Chelomei started developping the heavy launcher UR-500 (SL-9/D) in 1961. The production started in 1962 in the Khrounitchev factory in Fili.

The first stage had a bundle structure like the US Saturn 1: 6 UDMH tanks of about 1.8 m diameter surrounder a 4.1 m diameter NTO tank. It was powered by 6 adjustable RD-253 motors (Glouchko, NPO Energomash) of 1460 kN thrust at ground level each (SI : 317 s, 1635 kN in vacuum). The thrust of the current version of those motors (modified in 1986) is 1475 kN at ground level and 1745 kN in vacuum.

The second stage of 4.15 m diameter features a bloc of 4 RD-0210 motors (Kosberg, KB Khimautomatiki) consuming the same propellant. Each motor provided 583 kN thrust (Specific Impulsion: 327 s) during 210 seconds.

The UR-500 rocket (8K82) was 38.7 m high, weighed 562 tons and could place 12.5 tons payload on low Earth orbit. It was fired four times from Tyouratam: 2 in 1965 and 2 in 1966 and resulted in 3 successes (Proton).

Four stages Proton (D1e / SL12)

The 4-stage RU-500K was originally developped to flyby the Moon with a manned capsule. Therefore the UR-500 was equipped with 2 upper stages resulting in a 690 tons and 58 meters rocket.

The third stage (Chelomei, KB Saliout) had the same diameter as the second. It was propulsed by a single 4-vernier RD-0210 motor. Its thrust was 630 kN during 250 seconds.

The Block-D fourth stage (Korolev, NPO Energia) was derived from the Korolev's N1 lunar launcher where it was the fith stage. It consumed oxygen and kerosene with a integrated-flux motor. The latter was refirable and provided 85 kN thrust (SI = 352 s) during 600 seconds. This stage was used until 1976 for interplanetary probes. From 1974 on , a modified version called Block-DM  was introduced for GEO launched, then followed by a DM2 version in 1982 and and DM3 in 1996.

Nowadays it seems the motor is RD-58

The 8K82K launcher introduced in 1967 was used for:

- lunar probes (Zond, Luna, up to 5.7 tons) and interplanetary probes (up to 4.6 tons to Mars and 5.3 tons to Venus)

- geostationary telecommunication satellites (Raduga, Ekran, Gorizont and then Luch, Gals, Express), meteorological satellite (Electro) and early warning satellite (in the Cosmos series) up to 2.4 tons.

Three stages Proton (SL13/D1)

The Proton launcher was also used in a 3-stage version to orbit payloads up to 21 tons (LEO at 200 km, 51.6° inclination)

After it's first flight in 1968 to orbit Proton 4, this version launched:

- the space stations of the manned programs (Saliout, Mir) and derived (Almaz)

- TKS type vessels (Cosmos Merkur, Kvant, Kristall, etc...)

Note: a modernized version named Proton M is announced for 1996-97. It should have new guidance systems and enhanced 2nd and 3rd stage motors. A cryogenic 4th stage is planned, so as a 5th stage derived from the Rokot Breeze.

The Proton launcher is marketed by International Launch Services (ILS)

Proton launches

#	Launch id	Payload	Launch date	Type	Status (orbit in perigee x apogee x inc. x period)
1	65054	Proton 1	16 Jul 1965
2	65087	Proton 2	2 Nov 1965
3	n/a	Proton (3a)	24 Mar 1966		Failure
4	66060	Proton 3	6 Jul 1966
5	67021	Cosmos 146 [L1 2]	10 Mar 1967	K Block-D	Partial failure: Stage 4 failed
6	67032	Cosmos 154 [L1 3]	8 Apr 1967	K Block-D	Partial failure: Stage 4 failed
7	n/a	Zond (4a) [L1 4]	28 Sep 1967	K Block-D	Failure: Stage 1 failed
8	n/a	Zond (4b) [L1 5]	21 Nov 1967	K Block-D	Failure: Stage 2 failed
9	68013	Zond 4 [L1 6]	2 Mar 1968	K Block-D
10	n/a	Zond (5a) [L1 7]	22 Apr 1968	K Block-D	Failure: Stage 2 failed at max Q
11	68076	Zond 5 [L1 9]	14 Sep 1968	K Block-D
12	68101	Zond 6 [L1 10]	10 Nov 1968	K Block-D
13	68103	Proton 4	16 Nov 1968	K
14	n/a	Zond (7a) [L1 11]	19 Jan 1969	K Block-D	Failure
15	n/a	Luna (15a) (Lunokhod [1])	19 Feb 1969	K Block-D	Failure
16	n/a	Mars (2b)	27 Mar 1969	K Block-D	Failure
17	n/a	Mars (2c)	2 Apr 1969	K Block-D	Failure
18	n/a	Luna (15b)	14 Apr 1969	K Block-D	Failure
19	n/a	Luna (15c)	4 Jun 1969	K Block-D	Failure
20	69058	Luna 15	13 Jul 1969	K Block-D
21	69067	Zond 7 [L1 12]	7 Aug 1969	K Block-D
22	68080	Cosmos 300 [Luna (16a)]	23 Sep 1969	K Block-D	Partial failure: Stage 4 failed
23	69092	Cosmos 305 [Luna (16b)]	22 Oct 1969	K Block-D	Partial failure: Stage 4 failed
24	n/a	Cosmos (311) [L1E 1, T1K #1]	16 Nov 1969	K Block-D	Failure
25	n/a	Cosmos (323)	6 Feb 1970	K Block-D	Failure
26	n/a	(?)	8 Aug 1970	K	Failure
27	70072	Luna 16	12 Sep 1970	K Block-D
28	70088	Zond 8 [L1 13]	20 Oct 1970	K Block-D
29	70095	Luna 17 (Lunokhod 1)	10 Nov 1970	K Block-D
30	70103	Cosmos 382 [L1E 2, T1K #2]	2 Dec 1970	K Block-D
31	71032	Salyut 1 [DOS 1]	19 Apr 1971	K
32	71042	Cosmos 419 [Mars (2d)]	10 May 1971	K Block-D	Partial failure: Stage 4 failed to ignite due to timer programming error
33	71045	Mars 2	19 May 1971	K Block-D
34	71049	Mars 3	28 May 1971	K Block-D
35	71073	Luna 18	2 Sep 1971	K Block-D
36	71082	Luna 19	28 Sep 1971	K Block-D
37	72007	Luna 20	14 Feb 1972	K Block-D
38	n/a	Salyut (2) [DOS 2]	29 Jul 1972	K	Failure: Stage 2 lost controll after 162 sec
39	73001	Luna 21 (Lunokhod 2)	8 Jan 1973	K Block-D
40	73017	Salyut 2 [OPS 1]	3 Apr 1973	K
41	73026	Cosmos 557 [Salyut (3), DOS 3]	11 May 1973	K
42	73047	Mars 4	21 Jul 1973	K Block-D
43	73049	Mars 5	25 Jul 1973	K Block-D
44	73052	Mars 6	5 Aug 1973	K Block-D
45	73053	Mars 7	9 Aug 1973	K Block-D
46	74017	Cosmos 0637	26 Mar 1974	K Block-DM
47	74037	Luna 22	29 May 1974	K Block-D
48	74046	Salyut 3 [OPS 2]	24 Jun 1974	K
49	74060	Molniya 1-S	29 Jul 1974	K Block-DM
50	74084	Luna 23	28 Oct 1974	K Block-D
51	74104	Salyut 4 [DOS 4]	26 Dec 1974	K
52	75050	Venera 9	8 Jun 1975	K Block-D
53	75054	Venera 10	14 Jun 1975	K Block-D
54	75097	Cosmos 0775	8 Oct 1975	K Block-DM
55	n/a	Luna (24a)	16 Oct 1975	K Block-D	Failure
56	75123	Raduga 01	22 Dec 1975	K Block-DM
57	76057	Salyut 5 [OPS 3]	22 Jun 1976	K
58	76081	Luna 24	9 Aug 1976	K Block-D
59	76092	Raduga 02	11 Sep 1976	K Block-DM
60	76107	Ekran 01	26 Oct 1976	K Block-DM
61	76121	Cosmos 881 Cosmos 882 [Merkur #1, #2]	15 Dec 1976	K
62	77066	Cosmos 929 [TKS Merkur #1]	17 Jun 1977	K
63	77071	Raduga 03	23 Jul 1977	K Block-DM
64	77077	Cosmos (937) Cosmos (938) [Merkur #3, #4]	4 Aug 1977	K	Failure
65	77092	Ekran 02	20 Sep 1977	K Block-DM
66	77097	Salyut 6 [DOS 5]	29 Sep 1977	K
67	78032	Cosmos 997 Cosmos 998 [Merkur #5, #6]	30 Mar 1978	K
68	n/a	Ekran (3a)	27 May 1978	K Block-DM	Failure
69	78073	Raduga 04	18 Jul 1978	K Block-DM
70	n/a	Ekran (3b)	17 Aug 1978	K Block-DM	Failure
71	78084	Venera 11	9 Sep 1978	K Block-DM
72	78086	Venera 12	14 Sep 1978	K Block-DM
73	n/a	Ekran (3c)	17 Oct 1978	K Block-DM	Failure
74	78118	Gorizont 01	19 Dec 1978	K Block-DM	Partial failure: Stage 4 failed to reignite
75	n/a	Cosmos (1070) / Cosmos (1071) [Merkur #7, #8]	5 Jan 1979	K	Failure
76	79015	Ekran 03	21 Feb 1979	K Block-DM
77	79035	Raduga 05	25 Apr 1979	K Block-DM
78	79042	Cosmos 1100 / Cosmos 1101 [Merkur #9, #10]	22 May 1979	K
79	79062	Gorizont 02	5 Jul 1979	K Block-DM
80	79087	Ekran 04	3 Oct 1979	K Block-DM
81	79105	Gorizont 03	28 Dec 1979	K Block-DM
82	80016	Raduga 06	20 Feb 1980	K Block-DM
83	80049	Gorizont 04	14 Jun 1980	K Block-DM
84	80060	Ekran 05	15 Jul 1980	K Block-DM
85	80081	Raduga 07	5 Oct 1980	K Block-DM
86	80104	Ekran 06	26 Dec 1980	K Block-DM
87	81027	Raduga 08	18 Mar 1981	K Block-DM
88	81039	Cosmos 1267	25 Apr 1981	K
89	81061	Ekran 07	26 Jun 1981	K Block-DM
90	81069	Raduga 09	30 Jul 1981	K Block-DM
91	81102	Raduga 10	9 Oct 1981	K Block-DM
92	81106	Venera 13	30 Oct 1981	K Block-DM
93	81110	Venera 14	4 Nov 1981	K Block-DM
94	82009	Ekran 08	5 Feb 1982	K Block-DM
95	82020	Gorizont 05	15 Mar 1982	K Block-DM
96	82033	Salyut 7 [DOS 6]	19 Apr 1982	K
97	82044	Cosmos 1366	17 May 1982	K Block-DM
98	n/a	Ekran (9a)	23 Jul 1982	K Block-DM	Failure
99	82093	Ekran 09	16 Sep 1982	K Block-DM
100	82100	Cosmos 1414 [Uragan #1]/Cosmos 1413,1415[Dummy]	12 Oct 1982	K Block-DM2
101	82103	Gorizont 06	20 Oct 1982	K Block-DM2
102	82113	Raduga 11	26 Nov 1982	K Block-DM2
103	n/a	Raduga (12a)	24 Dec 1982	K Block-DM2	Failure
104	83013	Cosmos 1443	2 Mar 1983	K
105	83016	Ekran 10	12 Mar 1983	K Block-DM2
106	83020	Astron	23 Mar 1983	K Block-DM2
107	83028	Raduga 12	8 Apr 1983	K Block-DM2
108	83053	Venera 15	2 Jun 1983	K Block-DM2
109	83054	Venera 16	7 Jun 1983	K Block-DM2
110	83066	Gorizont 07	1 Jul 1983	K Block-DM2
111	83084	Cosmos 1490-1491 [Uragan #2,3]/Cosmos 1492[Dummy]	10 Aug 1983	K Block-DM2
112	83088	Raduga 13	25 Aug 1983	K Block-DM2
113	83100	Ekran 11	29 Sep 1983	K Block-DM2
114	83118	Gorizont 08	30 Nov 1983	K Block-DM2
115	83127	Cosmos 1519-1520 [Uragan #4,5]/Cosmos 1521[Dummy]	29 Dec 1983	K Block-DM2
116	84016	Raduga 14	15 Feb 1984	K Block-DM2
117	84022	Cosmos 1540	2 Mar 1984	K Block-DM2
118	84028	Ekran 12	16 Mar 1984	K Block-DM2
119	84031	Cosmos 1546	29 Mar 1984	K Block-DM2
120	84041	Gorizont 09	22 Apr 1984	K Block-DM2
121	84047	Cosmos 1554-1555 [Uragan #6,7]/Cosmos 1556[Dummy]	19 May 1984	K Block-DM2
122	84063	Raduga 15	22 Jun 1984	K Block-DM2
123	84078	Gorizont 10	1 Aug 1984	K Block-DM2
124	84090	Ekran 13	24 Aug 1984	K Block-DM2
125	84095	Cosmos 1593,1595 [Uragan #8,9]/Cosmos 1594[Dummy]	4 Sep 1984	K Block-DM2
126	84106	Cosmos 1603 [Tselina-2 #1]	28 Sep 1984	K Block-DM2
127	84125	Vega 1	15 Dec 1984	K Block-DM2
128	84128	Vega 2	21 Dec 1984	K Block-DM2
129	85007	Gorizont 11	18 Jan 1985	K Block-DM2
130	85016	Cosmos 1629	21 Feb 1985	K Block-DM2
131	85024	Ekran 14	22 Mar 1985	K Block-DM2
132	85037	Cosmos 1650-1651 [Uragan #10-11]/Cosmos-1652[Dummy]	17 May 1985	K Block-DM2
133	85042	Cosmos 1656 [Tselina-2 #2]	30 May 1985	K Block-DM2
134	85070	Raduga 16	8 Aug 1985	K Block-DM2
135	85086	Cosmos 1686 [TKS Merkur #4]	27 Sep 1985	K
136	85102	Cosmos 1700 [Luch #1, Altair #1]	25 Oct 1985	K Block-DM2
137	85107	Raduga 17	15 Nov 1985	K Block-DM2
138	85118	Cosmos 1710-1711 [Uragan #12-13]/Cosmos-1712[Dummy]	24 Dec 1985	K Block-DM2
139	86007	Raduga 18	17 Jan 1986	K Block-DM2
140	86017	Mir 1 [DOS 7]	19 Feb 1986	K
141	86027	Cosmos 1738	4 Apr 1986	K Block-DM2
142	86038	Ekran 15	24 May 1986	K Block-DM2
143	86044	Gorizont 12	10 Jun 1986	K Block-DM2
144	86071	Cosmos 1778-1780 [Uragan #14-16]	16 Sep 1986	K Block-DM2
145	86082	Raduga 19	25 Oct 1986	K Block-DM2
146	86090	Gorizont 13	18 Nov 1986	K Block-DM2
147	87002	Cosmos [1811] [Almaz-T #1]	29 Dec 1986	K	Failure
148	87010	Cosmos 1817 <Geosynch Failure>	30 Jan 1987	K Block-DM2	Partial failure: Stage 4 failed
149	87028	Raduga 20	19 Mar 1987	K Block-DM2
150	87030	Kvant 1	31 Mar 1987	K
151	87036	Cosmos 1838-1840 [Uragan #17-19]	24 Apr 1987	K Block-DM2	Partial failure: Stage 4 failed to reignite
152	87040	Gorizont 14	11 May 1987	K Block-DM2
153	87064	Cosmos 1870	25 Jul 1987	K
154	87073	Ekran 16	3 Sep 1987	K Block-DM2
155	87079	Cosmos 1883-1885 [Uragan #20-22]	16 Sep 1987	K Block-DM2
156	87084	Cosmos 1888	1 Oct 1987	K Block-DM2
157	87091	Cosmos 1894	28 Oct 1987	K Block-DM2
158	87096	Cosmos 1897	26 Nov 1987	K Block-DM2
159	87100	Raduga 21	10 Dec 1987	K Block-DM2
160	87109	Ekran 17	27 Dec 1987	K Block-DM2
161	n/a	Gorizont [15]	18 Jan 1988	K Block-DM2	Failure: Stage 3 failed
162	88009	Cosmos 1917-1919 [Uragan #23-25]	17 Feb 1988	K Block-DM2	Partial failure: Stage 4 failed
163	88028	Gorizont 15	31 Mar 1988	K Block-DM2
164	88034	Cosmos 1940 [Prognoz #1]	26 Apr 1988	K Block-DM2
165	88036	Ekran 18	6 May 1988	K Block-DM2
166	88043	Cosmos 1946-1948 [Uragan #26-28]	21 May 1988	K Block-DM2
167	88058	Fobos 1	7 Jul 1988	K Block-DM2
168	88059	Fobos 2	12 Jul 1988	K Block-DM2
169	88066	Cosmos 1961	1 Aug 1988	K Block-DM2
170	88071	Gorizont 16	18 Aug 1988	K Block-DM2
171	88085	Cosmos 1970 Cosmos 1971 Cosmos 1972	16 Sep 1988	K Block-DM2
172	88095	Raduga 22	20 Oct 1988	K Block-DM2
173	88108	Ekran 19	10 Dec 1988	K Block-DM2
174	89001	Cosmos 1987 Cosmos 1988 Cosmos 1989	10 Jan 1989	K Block-DM2
175	89004	Gorizont 17	26 Jan 1989	K Block-DM2
176	89030	Raduga 23	14 Apr 1989	K Block-DM2
177	89039	Cosmos 2022 Cosmos 2023 Cosmos 2024	31 May 1989	K Block-DM2
178	89048	Raduga 1-1	21 Jun 1989	K Block-DM2
179	89052	Gorizont 18	5 Jul 1989	K Block-DM2
180	89081	Gorizont 19	28 Sep 1989	K Block-DM2
181	89093	Kvant 2	26 Nov 1989	K
182	89096	Granat	1 Dec 1989	K Block-DM2
183	89098	Raduga 24	15 Dec 1989	K Block-DM2
184	89101	Cosmos 2054	27 Dec 1989	K Block-DM2
185	90016	Raduga 25	15 Feb 1990	K Block-DM2
186	90045	Cosmos 2079 Cosmos 2080 Cosmos 2081	19 May 1990	K Block-DM2
187	90048	Kristall	31 May 1990	K
188	90054	Gorizont 20	20 Jun 1990	K Block-DM2
189	90061	Cosmos 2085	18 Jul 1990	K Block-DM2
190		?	9 Aug 1990	K Block-DM2	Failure: Stage 2 failed due to forgotten rag in a fuel line
191	90094	Gorizont 21	3 Nov 1990	K Block-DM2
192	90102	Gorizont 22	23 Nov 1990	K Block-DM2
193	90110	Cosmos 2109 Cosmos 2110 Cosmos 2111	8 Dec 1990	K Block-DM2
194	90112	Raduga 26	20 Dec 1990	K Block-DM2
195	90116	Raduga 1-2	27 Dec 1990	K Block-DM2
196	91010	Cosmos 2133	14 Feb 1991	K Block-DM2
197	91014	Raduga 27	28 Feb 1991	K Block-DM2
198	91024	Almaz 1 [Almaz-T #3]	31 Mar 1991	K
199	91025	Cosmos 2139 Cosmos 2140 Cosmos 2141	4 Apr 1991	K Block-DM2
200	91046	Gorizont 23	2 Jul 1991	K Block-DM2
201	91064	Cosmos 2155	13 Sep 1991	K Block-DM2
202	91074	Gorizont 24	23 Oct 1991	K Block-DM2
203	91079	Cosmos 2172	22 Nov 1991	K Block-DM2
204	91087	Raduga 28	19 Dec 1991	K Block-DM2
205	92005	Cosmos 2177 Cosmos 2178 Cosmos 2179	29 Jan 1992	K Block-DM2
206	92017	Gorizont 25	2 Apr 1992	K Block-DM2
207	92043	Gorizont 26	14 Jul 1992	K Block-DM2
208	92047	Cosmos 2204 Cosmos 2205 Cosmos 2206	29 Jul 1992	K Block-DM2
209	92059	Cosmos 2209	10 Sep 1992	K Block-DM2
210	92074	Ekran 20	30 Oct 1992	K Block-DM2
211	92082	Gorizont 27	27 Nov 1992	K Block-DM2
212	92088	Cosmos 2224	17 Dec 1992	K Block-DM2
213	93010	Cosmos 2234 Cosmos 2235 Cosmos 2236	17 Feb 1993	K Block-DM2
214	93013	Raduga 29	25 Mar 1993	K Block-DM2
215	n/a	Gorizont #39	27 May 1993	K Block-DM2	Failure: Stage 2 failed because contaminated UDMH destroyed an engine
216	93062	Raduga 30	30 Sep 1993	K Block-DM2
217	93069	Gorizont 28	28 Oct 1993	K Block-DM2
218	93072	Gorizont 29	18 Nov 1993	K Block-DM2
219	94002	Gals 1	20 Jan 1994	K Block-DM2M
220	94008	Raduga 1-3	5 Feb 1994	K Block-DM2
221	94012	Raduga 31	18 Feb 1994	K Block-DM2
222	94021	Cosmos 2275 Cosmos 2276 Cosmos 2277	11 Apr 1994	K Block-DM2
223	94030	Gorizont 30	20 May 1994	K Block-DM2
224	94038	Cosmos 2282	6 Jul 1994	K Block-DM2
225	94050	Cosmos 2287 Cosmos 2288 Cosmos 2289	11 Aug 1994	K Block-DM2
226	94060	Cosmos 2291	21 Sep 1994	K Block-DM2
227	94067	Express 1	13 Oct 1994	K Block-DM2M
228	94069	Electro 1	31 Oct 1994	K Block-DM2M
229	94076	Cosmos 2294 Cosmos 2295 Cosmos 2296	20 Nov 1994	K Block-DM2
230	94082	Luch 0	16 Dec 1994	K Block-DM2
231	94087	Raduga 32	28 Dec 1994	K Block-DM2
232	95009	Cosmos 2307 Cosmos 2308 Cosmos 2309	7 Mar 1995	K Block-DM2
233	95024	Spektr	20 May 1995	K
234	95037	Cosmos 2316 Cosmos 2317 Cosmos 2318	24 Jul 1995	K Block-DM2
235	95045	Cosmos 2319	30 Aug 1995	K Block-DM2
236	95054	Luch 1	11 Oct 1995	K Block-DM2M
237	95063	Gals 2	17 Nov 1995	K Block-DM2
238	95068	Cosmos 2323 Cosmos 2324 Cosmos 2325	14 Dec 1995	?
239	96005	Gorizont 31	25 Jan 1996	K Block-DM2
240	96010	Raduga 33	19 Feb 1996	K Block-DM2
241	96021	Astra 1F	8 Apr 1996 at 23:09 UT	K Block-DM3C	modified DM with less mass and SAAB adapter
242	96023	Priroda	23 Apr 1996	K
243	96022	Gorizont 32	25 May 1996	K Block-DM2
244	96053	Inmarsat 3F2	6 Sep 1996 at 17:37 UT	K Block-DM1C	single burn for GEO injection
245	96058	Express 2	26 Sep 1996 at 17:51 UT	K Block-DM2M
246	96064	Mars 96	16 Nov 1996	K Block-D2
247	97026	Telstar 5	24 May 1997 at 17.00 UT	K Block-DM4C
248	97028	Cosmos 2344	6 Jun 1997 at 17:57 UT	K Block-DM5
249	97030	A: Iridium 14 B: Iridium 12 C: Iridium 10 D: Iridium 09 E: Iridium 13 F: Iridium 16 G: Iridium 11	18 Jun 1997 at 14:02 UT	K Block-DM2C
250	97041	Cosmos 2345	14 Aug 1997 at 20:49 UT	K Block-DM2	164 x 190 km x 53.2°
251	97046	Panamsat 5	28 Aug 1997 at 00:33 UT	K Block-DM3C	214 x 36018 km x 51.6°
252	97051	A: Iridium 29 B: Iridium 32 C: Iridium 33 D: Iridium 27 E: Iridium 28 F: Iridium 30 G: Iridium 31	14 Sep 1997 at 01:36 UT	K Block-DM2C	516 x 516 km x 86.6°
253	97070	Coupon 1	12 Nov 1997 at 17:00 UT	K Block-DM2
254	97076	Astra 1G	2 Dec 1997 at 23:10 UT	K Block-DM3C
255	97086	Asiasat 3	24 Dec 1997 at 23:19 UT	K Block-DM3C	Partial failure: second burn of the Block DM3 failed and left the satellite in GTO (240 x 36000 km x 51.6°) Problem with a joint in the 11D58M motor.
256	98021	A: Iridium 62 B: Iridium 63 C: Iridium 64 D: Iridium 65 E: Iridium 66 F: Iridium 67 G: Iridium 68	7 Apr 1998 at 02:13 UT	K Block-DM2C
257	98025	Cosmos 2350	29 Apr 1998 at 04:40 UT	K Block-DM2
258	98028	Echostar 4	7 May 1998 at 23:45 UT	K Block-DM3C
259	98050	Astra 2A	30 Aug 1998 at 00:31 UT	K Block-DM3C
260	98065	Panamsat 8	4 Nov 1998 at 05:12 UT	K Block-DM3C
261	98067	Zarya	20 Nov 1998 at 06:40 UT	K
262	98077	A: Cosmos 2362 B: Cosmos 2363 C: Cosmos 2364	30 Dec 1998 at 18:35 UT	K Block-DM2
263	99005	Telstar 6	15 Feb 1999 at 05:12 UT	K Block-DM3C
264	99010	Raduga 1-4	28 Feb 1999 at 04:00 UT	K Block-DM2
265	99013	Asiasat 3S	21 Mar 1999 at 00:09 UT	K Block-DM3C
266	99027	Nimiq	20 May 1999 at 22:30 UT	K Block-DM3C	7050 x 35790 km x 15.9°
267	99033	Astra 1H	18 Jun 1999 at 01:49 UT	K Block-DM3C	7474 x 35842 km x 16.4°
268	n/a	Raduga	05 Jul 1999 at 13:32 UT	Briz-M	Failure: second stage. One of the motors failed, melted and caused an explosion

Notes: All launches from Tyouratam.


 Rokot

by Jean-Jacques Serra

The primary activity of Chelomei's OKB-52 was navy missiles production. In 1959 the firm started producing more important missiles such as the solid propulsion UR-96 ABM and the UR-100 (SS-11 Sego) ICBM with stockable liquid propellant. 1030 copies of this light ICBM (50 tons) of 3rd generation were deployed in the 60ies and 70ies.

Origin: Inter Continental Ballistic Missile (ICBM) of fourth generation

After designing the RU-200 ICBM and the UR-500 Proton space launcher Chelomei's OKB (now NPO Saliout) developped a new ICBM know as UR-100N or RS-18 (or SS-19 Stilleto) between 1964 and 1975. 360 copies of the 4th generation ICBM were manufactured in the 70ies and 80ies.

Few characteristics on this missile are known apart that it has two stages with storable liquid propellants. It uses four steerable engines (RD-0233/0234) in stage 1 and a single-chamber main engine with a four-chamber steering engine (RD-0235/0236) in stage 2. All these engines are from Kosberg (KB Khimautomatiki). The UR-100N is about 27 meters long and 2.5 meters in diameter, with a gross takeoff mass of 90 tons.

The rokot launcher

The launcher is a SS-19 missile to which a Breeze 3rd stage has been added (or Briz?). Breeze weighs 6.4 tons and is 3.4 m long for 2.2 m diameter. Its in-flight refirable motor uses stockable propellant (NTO-UDMH). The launcher can orbit 1 to 2 tons of payload in LEO.

Two suborbital tests of Rokot were carried out on 20 Nov 1990 and 20 Dec 1991 before launching its first satellite.

It should be marketed by Eurockot Launch Services GmbH (Khrunichev and DASA) in 1997. A launch should cost from 7 to 10 million dollars. The first launches should take place in Plesetsk before being transfered at Svobodny in the Russian far East.

External resources

http://www.eurockot.com/

Rokot launches

#	Launch id	Payload	Launch date	Status (orbit in perigee x apogee x inc. x period)
1	94085	RS 15	26 Dec 1994 at 03:00 UT	The spent third stage exploded a few hours after launch

Notes: All launches from Tyuratam.


 Scout

by Jean-Jacques Serra

listing by Gunter Krebs

The Scout rocket was designed in 1957 by the NACA Langley center (which becamed the NASA Langley Research Center). It was mass produced from 1959 on by Vought Corp. (to become LTV). Scout was 21 m high, weighed 16 tons and was solid fuel only. It was used as light launcher so as sounding rocket. The first stage was an Algol made by Aerojet of 1.1 m diameter which provided 52 t thrust. Algol was controlled by a jet deflector called jetavator which has been designed for the Polaris program. The second stage was a Thiokol Castor derived from the tactical Sergeant missile and provided 24 t thrust. The two upper stages were built by Alleghany Ballistics (now Hercules). The third stage was a 6.2 t thrust Antares and the fourth stage a 1.4 t Altair.

The first launches of Scout in 1960 were ballistic flights. The first orbiting attempt failed in December 1960, but on 16 February 1961 Scout successfuly delivered Explorer 09 in orbit. Since then all its stages have been improved. One USAF specific version was called Blue Scout and a Blue Scout Junior (3-stage, Algol-less) was fired 22 times on ballistic missions.

Scouts were fired from 3 locations: Wallops Island, Vandenberg and San Marco. The latter is an italian oil platform at large from Kenya which only fired Scouts. Production of the Scout stopped in 1982 but the last vehicle was fired in 1994. This latter version (Scout G1) was 23 m high and weighed 21.7 tons.

Evolution of Scout

Designation	First launch	1st stage	2nd stage	3rd stage	4th stage	inc: 90° (1)	inc: 38° (1)	inc: 2.9° (1)
Scout X-1	1960	Algol 1C	Castor 1	Antares 1	Altair 1	45	59
Scout X-2	1962	Algol 1D	Castor 1	Antares 2	Altair 1	59	76
Scout X-3	1963	Algol 2A	Castor 1	Antares 2	Altair 1	68	87
Scout X-4	1964	Algol 2B	Castor 1	Antares 2	Altair 2	80	103
Scout A-1	1965	Algol 2B	Castor 2	Antares 2	Altair 2	94	122
Scout B-1	1965	Algol 2B	Castor 2A	Antares 2A	Altair 3A	116	143	151
Scout D-1	1972	Algol 3A	Castor 2A	Antares 2A	Altair 3A	148	185	198
Scout F-1	1974	Algol 3A	Castor 2A	Antares 2B	Altair 3A	156	193	203
Scout G-1	1974	Algol 3A	Castor 2A	Antares 3A	Altair 3A	166	208	220

Notes: (1) Payload (kg) in circular 550 km orbit; Launches from Vandenberg (90°), Wallops Island (38°) and San Marco (2.9°)

Scout was used both by NASA and USAF. It was used for:

- Scientific satellites of America (Explorer program), international organizations (ESRO) and other countries (Ariel, San Marco, FR 1, Eole, Azur, Aeros, Miranda, ANS)

- US satellites for military, navigation (Transit, Triad, Nova, etc.) and technology (OV3, MSTI, etc.) purposes

Scout launches

#	Launch id	Payload	Launch Date	Site	Type	Status/Comment (orbit in perigee x apogee x inclination x period)
1, ST-1	n/a	NASA radiation probe	02 Sep 1960	W	X1	Ballistic flight
2, ST-2	n/a	USAF radiation probe	4 Oct 1960	W	X1	Failure Ballistic flight
3, ST-3	n/a	Explorer S56	04 Dec 1960	W	X1	Failure
4, ST-4	61004	Explorer 09	16 Feb 1961	W	X1	634x2583x38.9
5, ST-5	n/a	Explorer S55	30 Jun 1961	W	X1	Failure
6, ST-6	61022	Explorer 13	25 Aug 1961	W	X1	Partial failure
7, ST-7	n/a	P 21	19 Oct 1961	W	X1	Failure Ballistic flight
8, ST-8	n/a	Reentry 1	1 Mar 1962	W	X1A	Ballistic flight
9, ST-9	n/a	P 21A	29 Mar 1962	W	X2	Ballistic flight
10, 111	n/a	Solrad 4B	26 Apr 1962	V	X2	Failure
11, 112	n/a	P35 1	24 May 1962	V	X2M	Failure
12, 117	62039	P35 2 (FTV 3502)	23 Aug 1962	V	X2M	650x858x98.6
13, 114	n/a	Reentry 2	31 Aug 1962	W	X3A	Failure
14, 115	62070	Explorer 16	16 Dec 1962	W	X3
15, 118	62071	Transit 5A-1	19 Dec 1962	V	X3	698x725x90.6
16, 126	63005	P35 3 (FTV 0240)	19 Feb 1963	V	X3M	505x791x100.5
17, 119	n/a	Transit 5A-2	05 Apr 1963	V	X3	Failure
18, 121	n/a	P35 4	26 Apr 1963	V	X2M	Failure
19, 116	n/a	RFD 1	22 May 1963	W	X3	Ballistic flight
20, 120	63022	Transit 5A-3	16 Jun 1963	V	X3	727x757x90.0
21, 113	63026	GRS (CRL 1)	28 Jun 1963	W	X4	411x1311x69.7
22, 110	n/a	Reentry 3	27 Jul 1963	W	X3M	Failure Ballistic flight
23, 132	n/a	P35 5	27 Sep 1963	V	X2B	Failure
24, 122R	63053	Explorer 19	19 Dec 1963	V	X4
25, 127R	64015	Ariel 2	27 Mar 1964	W	X3
26, 125R	64026	Transit 5C-1	04 Jun 1964	V	X4	854x956x90.4
27, 128R	n/a	ESRS (CRL 2)	25 Jun 1964	V	X4	Failure
28, 124R	n/a	SERT 1	20 Jul 1964	W	X4	Ballistic flight
29, 129R	n/a	Reentry 4A	18 Aug 1964	W	X4A	Ballistic flight
30, 134R	64051	Explorer 20	25 Aug 1964	V	X4
31, 130R	n/a	RFD 2	9 Oct 1964	W	X3C	Ballistic flight
32, 123R	64064	Explorer 22	10 Oct 1964	V	X4
33, 133R	64074	Explorer 23	06 Nov 1964	W	X4
34, 135R	64076	A: Explorer 24 B: Explorer 25	21 Nov 1964	V	X4
35, 137R	64084	San Marco 1	15 Dec 1964	W	X4
36, 136R	65032	Explorer 27	29 Apr 1965	W	X4
37, 131R	65063	Secor 05	10 Aug 1965	W	B
38, 138R	65093	Explorer 30	19 Nov 1965	W	X4
39, 139R	65101	FR 1	06 Dec 1965	V	X4
40, 140C	65109	Transit-O 6	22 Dec 1965	V	A	909x1086x89.1
41, 142C	66005	Transit-O 7	28 Jan 1966	V	A	861x1217x89.7
42, 141C	n/a	Reentry 4B	9 Feb 1966	W	X4A	Ballistic flight
43, 143C	66024	Transit-O 8	26 Mar 1966	V	A	891x1128x89.7
44, 145C	66034	OV 3-1	22 Apr 1966	V	B
45, 146C	66041	Transit-O 9	19 May 1966	V	A	863x980x90.0
46, 147C	66052	OV 3-4	10 Jun 1966	W	B
47, 148C	66070	OV 3-3	04 Aug 1966	V	B
48, 149C	66076	Transit-O 10	18 Aug 1966	V	A	1056x1101x88.9
49, 150C	66097	OV 3-2	28 Oct 1966	V	B
50, 151C	n/a	OV3-5	31 Jan 1967	V	B	Failure
51, 154C	67034	Transit-O 12	14 Apr 1967	V	A	1053x1083x90.2
52, 153C	67038	San Marco 2	26 Apr 1967	S	B
53, 155C	67042	Ariel 3	05 May 1967	V	A
54, 156C	67048	Transit-O 13	18 May 1967	V	A	1074x1116x89.3
55, 156C	n/a	Esro 2A (Iris 1)	29 May 1967	V	B	Failure
56, 157C	67092	Transit-O 14	25 Sep 1967	V	A	1041x1116x89.3
57, 159C	n/a	RAM C1	19 Oct 1967	W	B	Ballistic flight
58, 158C	67120	OV 3-6 (Atcos 2)	05 Dec 1967	V	B	412x439x90.7
59, 162C	68012	Transit-O 18	02 Mar 1968	V	A	1035x1139x90.0
60, 160C	68017	Solrad 09	05 Mar 1968	W	B	Partial failure
61, 160C	n/a	Reentry 5	27 Apr 1968	W	X5A	Ballistic flight
62, 164C	68041	Esro 2B	17 may 1968	V
63, 165C	68066	A: Explorer 39 B: Explorer 40	08 Aug 1968	V	B
64, 168C	n/a	RAM C2	22 Aug 1968	W	B	Ballistic flight
65, 167C	68084	Esro 1A	03 Oct 1968	V	B
66, 172C	69083	Esro 1B	01 Oct 1969	V	B
67, 169C	69097	Azur	08 Nov 1969	V	B
68, 176C	70067	Transit-O 19	27 Aug 1970	V	A	954x1221x90.2
69, 171C	n/a	RAM C3	30 Sep 1970	W	B	Ballistic flight
70, 174C	70094	A: OFO B: RM 1	09 Nov 1970	W	B
71, 175C	70107	Explorer 42	12 Dec 1970	S	B
72, 173C	71036	San Marco 3	24 Apr 1971	S	B
73, 144CR	n/a	PAET	20 Jun 1971	W	B	Ballistic flight
74, 177C	71058	Solrad 10	08 Jul 1971	W	B
75, 180C	71071	Eole	16 Aug 1971	W	B1
76, 166CR	n/a	GRP	20 Sep 1971	W	B	Ballistic flight
77, 163CR	71096	Explorer 45	15 Nov 1971	S	B
78, 183C	71109	Ariel 4	11 Dec 1971	V	B1
79, 184C	72061	Explorer 46	13 Aug 1972	W	D1
80, 182C	72069	Triad 1 (TIP 1)	02 Sep 1972	V	B1	716x863x90.1
81, 170CR	72091	Explorer 48	15 Nov 1972	S	D1
82, 185C	72092	Esro 4	22 Nov 1972	V	D1
83, 181C	72100	Aeros 1	16 Dec 1972	V	D1
84, 178C	73081	Transit-O 20	30 Oct 1973	V	A1	907x1136x90.2
85, 190C	74009	San Marco 4	18 Feb 1974	S	D1
86, 188C	74013	Miranda	09 Mar 1974	V	D1
87, 191C	74040	Explorer 52	03 Jun 1974	V	E1
88, 186C	74055	Aeros 2	16 Jul 1974	V	D1
89, 189C	74070	ANS	30 Aug 1974	V	D1
90, 187C	74077	Ariel 5	15 Oct 1974	S	B1
91, 194	75037	Explorer 53	07 May 1975	S	F1
92, 195C	75099	Triad 2 (TIP 2)	12 Oct 1975	V	D1	362x705x90.7
93, 196C	n/a	Explorer [56] Explorer [57]	05 Dec 1975	V	F1	Failure
94, 179CR	76047	Wideband (P76 5)	22 May 1976	V	B1	995x1059x99.6
95, 193C	n/a	Gravity probe	18 Jun 1976	W	D1	Ballistic flight
96, 197C	76089	Triad 3 (TIP 3)	01 Sep 1976	V	D1	475x930x89.9
97, 200C	77106	Transat (O 11)	28 Oct 1977	V	D1	1000x1000x89.9
98, 201C	78041	AEM 1	26 Apr 1978	V	D1
99, 202C	79013	AEM 2	18 Feb 1979	W	D1
100, 198C	79047	Ariel 6	02 Jun 1979	W	D1
101, 203C	79094	AEM 3	30 Oct 1979	V	G1
102, 192C	81044	Nova 1	15 May 1981	V	G1
103, 205C	83063	Hilat (T83 1)	27 Jun 1983	V	G1	770x838x82.0
104, 208C	84110	Nova 2	12 Oct 1984	V	G1
105, 209C	85066	Transit-O 24 Transit-O 30	03 Aug 1985	V	G1	1000x1260x89.8
106, 207C	85114	ITV 1/2	13 Dec 1985	W	G1	316x770x37.0
107, 199C	86088	Polar Bear (P87 1)	14 Nov 1986	V	G1	1170x1180x90.0
108, 204C	87080	Transit-O 27 Transit-O 29	16 Sep 1987	V	G1	1020x1180x90.0
109, 209C	88026	San Marco 5	25 Mar 1988	S	G1
110, 211C	88033	Transit-O 23 Transit-O 32	25 Apr 1988	V	G1	1020x1300x90.0
111, 213C	88052	Nova 3	16 Jun 1988	V	G1
112, 214C	88074	Transit-O 25 Transit-O 31	25 Aug 1988	V	G1	1030x1180x90.0
113, 212C	90043	Macsat 1 Macsat 2	09 May 1990	V	G1	610x770x90.0
114, 216C	91045	REX 1	29 Jun 1991	V	G1	770x870x89.6
115, 215C	92038	Sampex	03 Jul 1992	V	G1
116, 210C	92078	MSTI 1	21 Nov 1992	V	G1
117, 217C	93041	Radcal	25 Jun 1993	V	G1
118, 218C	94028	MSTI 2	09 May 1994	V	G1

Notes: Launch site: C for Cape Canaveral, V for Vandenberg, W for Wallops Island and S for San Marco

[Gunter Krebs adds:]

Although mostly neglected and not part of the "official" launch history, the Blue-Scout-1 and Blue Scout-2 versions. The main difference was, that the Blue-Scouts had an different aft section of the first stage as they stood on the launch pad (the "normal" Scout was suspended on a launch tower). The Blue-Scout-1 was a 3 stage version of the Scout-X1, the Blue Scout-2 was mostly identical to the Scout-X1.

The Blue-Scout-2 made one ill-fated attempt to launch a satellite from Cape Canaveral:

01.11.1961 Mercury-MS 1

The Mercury-MS 1 payload was a small communication satellite to simmulate the telemetry from a manned Mercury capsule. No replacement was launched.


 Semiorka and derived from R7

by Jean-Jacques Serra

Origin: ICBM of first generation (R7 Semiorka)

In Feb 1953 the Soviet government decided to built a intercontinental rocket. The project management was affected to S.P. Korolev's OKB while V.P. Gouchko's one was in charge of the motors.

Originaly the program planned to send a 3 ton payload at 8000 km. It transformed in late 1953 when the thermonuclear warheadwas found to weigh 6 tons. The modified project was accepted in August 1954 under the name R7 (or Semiorka).

The R7 was a rocket made of a central body with 4 lateral boosters as the first stage. The conical boosters, were 19.8 m high and 2.68 m diameter (base). The main body, known as Block A, was 28.75 m high and a maximum diameter of 2.95 m at the upper fixation point of the boosters. The missile was known in the US as SS-6 Sapwood; it weighed 267 tons at takeoff and was 30.5 m high.

The first tests of the motors (static bench) took place in Sep 1956. The motors had 4 chambers consuming the couple oxygen-kerosen. The RD-107 was active during 320 seconds and provided 976 kN thrust in vacuum (Isp = 305 s). It featured two verniers. The RD-108 active 120 seconds developped 912 kN in vacuum (Isp = 308 s) and featured 4 verniers.

Missiles tests started on 15 May 1957 from Tyuratam (near Baïkonour), specially created for the R7. After 3 failures the first successful flight took place on 21 August the same year. A second success on 7 September set on the green light to try and achieve a satellisation.

Usage of Semiorka without top stage

The first artifical satellite Sputnik 1 was launched on 4 Oct. 1957 from Tyuratam. Only the top stage of the R7 rocket was modified to create the rocket named 8K71 in USSR and A / SL1 in the US.

This launcher was further used for 2 satellites. On 3 Nov 1957 it put the 508 kg Sputnik 2 into orbit and its Laïka passenger. On 15 May 1958 after a failure in April Sputnik 3 (1327 kg) was also put onto orbit.

The Semiorka configuration was such that it was a military device difficult to use. On the contrary it was a great base for a space launcher and therefore it is still used 40 years after its first launch. The constructor of this rocket is now KB Photon, a division of TsSKB Samara.

The RD-107 and RD-108 motors, now built by NPO Energomash, have been enhanced. Their performance is now 1000 kN in vacuum (Isp = 314 s) for the former and 941 kN (Isp = 315 s) for the latter.

Usage of Semiorka with a Block E third stage

The project of Lunar probe launches required a third stage for the R7. This Block E top stage was ordered from the S.A. Kosberg KB (now KB Khimautomatiki) in Feb 1958. It was to be the first liquid stage fired up in vacuum. Its RO-7 motor (or RD-0105) using liquid onxygen and kerosen developped 49 kN thrust (Isp 316 s). It was 2.58 m diameter, 2.98 m long and weighed 8.1 tons, including 7 tons propellant.

After several failures since August 1958 the first sucessful launch of the 3-stage R7 occured to send Luna 1 to the moon on 2 Jan 1959. The probe flowby 6400 km from the objective before acquiring a solar orbit. A second failure in August occured before the first moon impact with Luna 2, launched on 12 Sep 1959. Then Luna 3 launched on 4 October took the first pictures of moon's hidden side. Two failures ended the 8K72 carrier, also known as A1 / SL2.

The Block E will be enhanced in 1960 for a piloted launch. A new RD(448 (or RD-0109) developped 54.5 kN thrust (Isp = 324 s).

The first Korabl spacecraft (Sputnik 4) was launched on 15 May 1960. It was the first of 7 tentatives including 5 successful launches which preceded the 6 Vostok flights. The Vostok rocket alias 8A92 or A1 / SL3 in the West will also be used to launch automatic satellites. In this configuration it is 38.4 m high and weighs 287 tons. It was 38.4 m high, 287 tons, and could orbit 4.7 tons in LEO or 1.1 tons in 900 km sunsynchronous orbit. This rocket launched:

- reconnaissance satellites of first generation (Cosmos Zenith) until 1967

- meteorological (Cosmos, Meteor) and observation (Cosmos, IRS) satellites until 1991

Note: it seems that the Poliot satellites (1963-1964) built by OKB Chelomei were launched by a modified Vostok named SL5. The SL10 launched used to launch Cosmos 101 and Cosmos 125 (1965-1966) would also have been launched by a modified R7.

Usage of Semiorka with a Block I third stage

The 4-stage version of Semiorka was designed in 1959-1960 for interplanetary missions. The Block I third stage was built by KB S.A. Kosberg. It was 2.66 m diameter and 8.1 m long. It weighed 24 tons including 21 tons propellant. It's 4-chamber motor block RO-9 (or RD-0107) used liquid oxygen and Kerosen. It provided 298 kN (Isp = 324 s). The fourth stage, Block L, was built by OKB S.P. Korovev. It was aimed by a CI-5400 integrated flux motor developping 67 kN (Isp = 340 s) with the same propellant.

The two first tentatives to Mars failed in October 1960. In Februry 1961 the first probe to Venus stayed in transfert orbit because of a Block L failure. The second launched on 12 Feb was correctly placed on solar orbit and became Venus 1. in 1962 the 3 launches towards Venus failed and only 1 launch to Mars in Oct.-Nov. succeeded on 1 Nov.

After such a difficult start the 8K78 (A2e / SL6) became more reliable and launched several types of space probes (Luna, Zond, Venus and Mars).

A version without fourth stage designed to launch manned vehicles was named 11A57 (or A2 / SL4). It was first tested in Nov 1963 with Cosmos 22, and then was used for the Voskhod program and to launch second generation Zenith reconnaissance satellites.

In Feb 1964 the 4-stage launcher was improved by replacing the 3rd stage motor by a RD-461 (or RD-0110) giving birth to the 8K78M rocket better known an Molniya. This launcher is 42 m high and weighs 306 tons. It can orbit 1.6 tons on an elliptic 12 hours path used by the Molniya telecommunication satellites. This launcher is also used for:

- space probes to the moon (1.6 tons), Venus (1.2 tons) or Mars (0.95 tons)

- scientific satellites Prognoz (0.9 tons) on very eccentric orbits

- early warning satellites Oko (Cosmos series) on 12 hour Molniya-type orbits

The 3-stage version Soyuz alias 11A511 appeared in Nov 1966 for the launch of Cosmos 133, then the version Soyuz M (11A511M) in Dec 1971 for Cosmos 470. The last version Soyuz U (11A511U) was launched for the first time in Mai 1973 with Cosmos 559.

For the manned flight a Soyuz U2 version exist; it is more powerful. It's central motor (RD-118) uses cycline instead of kerosen as propellant. The thrust of each booster is 1030 kN (ground level) and 1250 kN in vacuum (Soyuz U: 1015 kN and 1240 kN respectively). The thrust of the central motor is 1010 kN (980 kN for Soyuz U). But the manned launches will from now on be made with kerosen, because the cycline plant in Oufa (Bachkirie) was closed of budget problems. NPO Energomach which produces the motors plan to compensate the performance with new injectors which enhance the combustion fo propellant.

Soyuz is in fact the most launched vehicle in the world (over 700 times). It measures 45 to 50 m depending on the versions, weighs 310 tons and can orbit ~7 tons in LEO. In addition to the Soyuz spacecrafts which gave them its name, the rocket was used for:

- several types of reconnaissance satellites (Zenith, Kometa, Yantar, etc.)

- their civilian counterparts (Bion, Resurs F, Foton, etc.)

- the Progress supply ships

A2e / SL6 (Molniya) launches

A2 / SL4 (Soyuz) launches

Commercial version: Soyouz-Ikar

The maximum capacity of the Soyuz U is only attained for launches of retrievable probes in LEO (200 km 51.8°) when the cap is jettisoned early. This performance falls to 6.2 tons at 200 km when the cap is released later, as for the more fragile commercial payloads; and 5 tons at 300 km. The Molniya M can place 1.75 tons on a 500/40000 km orbit, 62.8° inclination, or 1.5 tons in sunsynchronous orbit at 800 km altitude.

The Russian-French firm Starsem set up by Aerospatiale (35%), Arianespace (15%), RKA (25%) and Samara center (25%) was created in August 1996 to sell Semiorka vehicles (Soyuz, Molniya and derivatives).

The new version is tailored for satellite constellation launches. It has an Ika stage under the cap like Molniya's Block L. This stage equipped with re-ignitable motors has already flown over 30 times with maneuverable observation satellites. The Soyuz-Ikar will be able to deliver 2.5 tons payload in 1400 km 51.8° orbits or 2.35 tons in polar orbit at the same altitude. The first use of the vehicle should be for 4 Globalstar satellites.

Soyuz 2 (Rus)

A enhanced Semiorka named Rus should be available in 1999. It will be used to launch the Cosmos, Foton, Bion and Resurs F satellites with a 3-stage version and Molniya, Meteor, Tselina and Resurs O satellites with a 4-stage version.

This new launcher, 51.2 m high, will have the same 3 stages of Soyuz with an improved propulsion and guidance systems. The RD-0101 motor of the 3rd stage will be replaced by a RD-0124 with integrated flux of same thrust, but with a 359 s Isp and a burn duration extended at 300 s. Moreover deployable nozzle will suppress the need for the 4 vernier motors. The top stage (in 4-stage version) will be the Fregat of NPO Lavotchkine. It weighs 6.5 tons including 5.3 tons of stockable propellant (NTO-UDMH). It will be equipped with a S5-92 motor from KB KhimMach of 20 kN which can be re-ignited up to 20 times. This rocket will have 900 kg more performance than the current Soyuz.

Launch statistics

	A / SL1	A1 / SL2	A1 / SL3	A2 / SL4	A1 / SL5	A2e / SL6	A1 / SL10	Total
1957	2							2
1958	1							1
1959		3						3
1960			3					3
1961			4			2		6
1962			7			6		13
1963			8	1	1	3		13
1964			12	5	1	4		22
1965			9	12		11	1	33
1966			11	14		8	1	34
1967			8	21		7		36
1968			2	34		5		41
1969			2	37		4		43
1970			5	31		7		43
1971			4	33		3		40
1972			5	31		11		47
1973			3	40		10		53
1974			6	36		7		49
1975			6	40		12		58
1976			5	38		11		54
1977			7	37		10		54
1978			5	45		9		59
1979			8	45		7		60
1980			6	45		12		63
1981			6	41		14		61
1982			5	43		11		59
1983			4	42		11		57
1984				44		11		55
1985			1	40		16		57
1986				36		14		50
1987				43		4		47
1988			2	42		11		55
1989				38		6		44
1990				30		12		42
1991			1	24		5		30
1992				24		8		32
1993				17		8		25
1994				15		3		18

As of 31 Dec 1998, 1627 Semiorka-based satellites were launched.

A / SL1 launches

#	Launch id	Payload	Launch date	Site	Type	Status (orbit in perigee x apogee x inc. x period)
1	57001	Sputnik 01	04 Oct 1957	T	8K71PS	228 x 204 km x 65.1°
2	57002	Sputnik 02	03 Nov 1957	T	8K71PS	225 x 204 km x 65.1°
3	n/a	(Sputnik)	24 Apr 1958	T	8K91	Failure
4	58004	Sputnik 03	15 May 1958	T	8K91	226 x 1881 km x 65.2°
Ae / SL5 launches

#	Launch id	Payload	Launch date	Site	Type	Status (orbit in perigee x apogee x inc. x period)
1	63043	Poliot-1	01 Nov 1963	T	11A59	343 x 1437 km x 58.9°
2	64019	Poliot-2	12 Apr 1964	T	11A59	310 x 500 km x 58.6°
A1m / SL10 launches

#	Launch id	Payload	Launch date	Site	Type	Status (orbit in perigee x apogee x inc. x period)
1	65111	Cosmos-102	28 Dec 1965	T	11A510	218 x 278 km x 65.0°
2	66067	Cosmos-125	20 Jul 1966	T	11A510	250 x 250 km x 65.0°
A1 / SL2 & SL3 launches

#	Launch id	Payload	Launch date	Site	Type	Status (orbit in perigee x apogee x inc. x period)
		(Luna)	23 Sep 1958	T	8K72	Failure
		(Luna)	12 Oct 1958	T	8K72	Failure
		(Luna)	04 Dec 1958	T	8K72	Failure
	59012	Luna-1	02 Jan 1959	T		orbit
		(Luna)	18 Jul 1959	T	8K72	Failure
	59014	Luna-2	12 Sep 1959	T		impact
	59008	Luna-3	04 Oct 1959	T	8K72	probe
		(Luna)	15 Apr 1960	T	8K72	Failure
		(Luna)	16 Apr 1960	T	8K72	Failure
	60005	Korabl-1 S-4	15 May 1960	T	8K72	307 x 690 km x 65.0°
		(Korabl)	23 Jul 1960	T	8K72	Failure
	60011	Korabl-2 S-5	19 Aug 1960	T	8K72	306 x 339 km x 65.0°
	60017	Korabl-3 S-6	01 Dec 1960	T	8K72K	180 x 249 km x 65.0°
		(Korabl)	22 Dec 1960	T	8K72K	Failure
	61008	Korabl-4 S-9	09 Mar 1961	T	8K72K	184 x 249 km x 64.9°
	61009	Korabl-5 S-10	25 Mar 1961	T	8K72K	178 x 247 km x 64.9°
	61012	Vostok-1	12 Apr 1961	T	8K72K	181 x 327 km x 65.0°
	61019	Vostok-2	06 Aug 1961	T	8K72K	183 x 244 km x 64.9°
		(Cosmos)	11 Dec 1961	T	8K72K	Failure
	62014	Cosmos-4	26 Apr 1962	T	8K72K	298 x 330 km x 65.0°
		(Cosmos)	01 Jun 1962	T	8A92	Failure
	62033	Cosmos-7	28 Jul 1962	T	8A92 <?	210 x 369 km x 65.0°
	62036	Vostok-3	11 Aug 1962	T	8K72K	181 x 234 km x 65.0°
	62037	Vostok-4	12 Aug 1962	T	8K72K	180 x 237 km x 65.0°
	62048	Cosmos-9	27 Sep 1962	T		301 x 353 km x 65.0°
	62054	Cosmos-10	17 Oct 1962	T		210 x 380 km x 65.0°
	62072	Cosmos-12	22 Dec 1962	T		211 x 405 km x 65.0°
	63006	Cosmos-13	21 Mar 1963	T		205 x 337 km x 65.0°
	63011	Cosmos-15	22 Apr 1963	T		173 x 371 km x 65.0°
	63012	Cosmos-16	28 Apr 1963	T		207 x 401 km x 65.0°
	63018	Cosmos-18	24 May 1963	T		209 x 301 km x 65.0°
	63020	Vostok-5	14 Jun 1963	T	8K72K	175 x 222 km x 65.0°
	63023	Vostok-6	16 Jun 1963	T	8K72K	181 x 231 km x 65.0°
	63040	Cosmos-20	18 Oct 1963	T		206 x 311 km x 65.0°
	63052	Cosmos-24	19 Dec 1963	T		211 x 408 km x 65.0°
	64006	A: Elektron 1 B: Elektron 2	30 Jan 1964	T	8K72K	460 x 68200 km x 61.0°
	64017	Cosmos-28	04 Apr 1964	T		209 x 395 km x 65.0°
	64021	Cosmos-29	25 Apr 1964	T		204 x 309 km x 65.1°
	64029	Cosmos-32	10 Jun 1964	T		209 x 333 km x 51.3°
	64033	Cosmos-33	23 Jun 1964	T		209 x 293 km x 65.0°
	64038	A: Elektron 3 B: Elektron 4	11 Jul 1964	T	8K72K	459 x 66235 km x 60.9°
	64039	Cosmos-35	15 Jul 1964	T		217 x 268 km x 51.3°
	64044	Cosmos-37	14 Aug 1964	T		205 x 300 km x 65.0°
	64053	Cosmos-44	28 Aug 1964	T		618 x 860 km x 65.0°
	64059	Cosmos-46	24 Sep 1964	T		215 x 271 km x 51.3°
	64066	Cosmos-48	14 Oct 1964	T		203 x 295 km x 65.1°
	64070	Cosmos-50	28 Oct 1964	T		196 x 241 km x 51.3°
	65001	Cosmos-52	11 Jan 1965	T		205 x 304 km x 65.0°
	65014	Cosmos-58	26 Feb 1965	T		581 x 659 km x 65.0°
	65025	Cosmos-64	25 Mar 1965	T		206 x 271 km x 65.0°
	65035	Cosmos-66	07 May 1965	T		197 x 291 km x 65.0°
	65046	Cosmos-68	15 Jun 1965	T		205 x 334 km x 65.0°
	65066	Cosmos-78	14 Aug 1965	T		206 x 329 km x 69.0°
	65097	Cosmos-98	27 Nov 1965	T		216 x 570 km x 65.0°
	65103	Cosmos-99	10 Dec 1965	T		199 x 320 km x 65.0°
	65106	Cosmos 0100	17 Dec 1965	T		630 x 650 km x 65.0°
	66001	Cosmos-104	07 Jan 1966	T		204 x 401 km x 65.0°
	66003	Cosmos-105	22 Jan 1966	T		204 x 324 km x 65.0°
	66010	Cosmos-107	10 Feb 1966	T		204 x 322 km x 65.0°
	66021	Cosmos-112	17 Mar 1966	P		214 x 565 km x 72.0°
	66033	Cosmos-115	20 Apr 1966	T		190 x 294 km x 65.0°
	66037	Cosmos-117	06 May 1966	T		207 x 308 km x 65.0°
	66038	Cosmos-118	11 May 1966	P		640 x 640 km x 65.0°
	66057	Cosmos 0122	25 Jun 1966	P		550 x 690 km x 65.0°
	66091	Cosmos-129	14 Oct 1966	T		202 x 307 km x 65.0°
	66106	Cosmos-132	19 Nov 1966	T		207 x 280 km x 65.0°
	66115	Cosmos-136	19 Dec 1966	T		198 x 35 km x 64.6°
	67004	Cosmos-138	19 Jan 1967	T?		193 x 293 km x 65.0°
	67017	Cosmos-143	27 Feb 1967	T?		204 x 302 km x 65.0°
	67018	Cosmos 0144	28 Feb 1967	P		630 x 630 km x 81.2°
	67022	Cosmos-147	13 Mar 1967	T?		198 x 317 km x 65.0°
	67030	Cosmos-153	04 Apr 1967	T?		202 x 291 km x 64.9°
	67039	Cosmos-156	27 Apr 1967	P		630 x 630 km x 81.2°
	67044	Cosmos-157	12 May 1967	T		202 x 296 km x 51.3°
	67102	Cosmos-184	25 Oct 1967	P		635 x 635 km x 81.2°
	68019	Cosmos-206	14 Mar 1968	P		630 x 630 km x 81.0°
	68049	Cosmos-226	12 Jun 1968	P		603 x 650 km x 81.2°
	69029	Meteor 1-01	26 Mar 1969	P		644 x 713 km x 81.2°
	69084	Meteor 1-02	06 Oct 1969	P		630 x 690 km x 81.2°
	70019	Meteor-1#3	17 Mar 1970	P		537 x 632 km x 81.1°
	70037	Meteor-1#4	28 Apr 1970	P		624 x 710 km x 81.2°
	70047	Meteor-1#5	23 Jun 1970	P		830 x 888 km x 81.2°
	70085	Meteor-1#6	15 Oct 1970	P		626 x 648 km x 81.2°
	70113	Cosmos-389	18 Dec 1970	P		642 x 687 km x 81.2°
	71003	Meteor-1#7	20 Jan 1971	P		629 x 656 km x 81.2°
	71028	Cosmos-405	07 Apr 1971	P	?	676 x 705 km x 81.3°
	71031	Meteor-1#8	17 Apr 1971	P		610 x 632 km x 81.2°
	71059	Meteor-1#9	16 Jul 1971	P		618 x 650 km x 81.2°
	71120	Meteor-1#10	29 Dec 1971	P		880 x 905 km x 81.2°
	72011	Cosmos-476	01 Mar 1972	P		618 x 651 km x 81.2°
	72022	Meteor-1#11	30 Mar 1972	P		878 x 903 km x 81.2°
	72049	Meteor-1#12	30 Jun 1972	P		897 x 929 km x 81.2°
	72085	Meteor-1#13	16 Oct 1972	P		893 x 904 km x 81.2°
	72106	Cosmos-542	28 Dec 1972	P		554 x 653 km x 81.2°
	73015	Meteor-1#14	20 Mar 1973	P		882 x 903 km x 81.2°
	73034	Meteor-1#15	29 May 1973	P		867 x 909 km x 81.2°
	73079	Cosmos-604 (603)	27 Oct 1973	P		624 x 647 km x 81.2°
	74011	Meteor-1#16	05 Mar 1974	P		853 x 906 km x 81.2°
	74025	Meteor-1#17	24 Apr 1974	P		877 x 907 km x 81.2°
	74052	Meteor-1#18	10 Jul 1974	P		877 x 905 km x 81.2°
	74066	Cosmos-673	16 Aug 1974	P		608 x 634 km x 81.2°
	74083	Meteor-1#19	29 Oct 1974	P		855 x 917 km x 81.2°
	74099	Meteor-1#20	17 Dec 1974	P		861 x 910 km x 81.2°
	75023	Meteor-1#21	01 Apr 1975	P		877 x 906 km x 81.2°
	75056	Cosmos-744	20 Jun 1975	P		612 x 650 km x 81.2°
	75064	Meteor 2-01	08 Jul 1975	P		872 x 903 km x 81.3°
	75076	Cosmos-756	22 Aug 1975	P		627 x 649 km x 81.2°
	75087	Meteor-1#22	18 Sep 1975	P		867 x 918 km x 81.2°
	75124	Meteor-1#23	25 Dec 1975	P		857 x 913 km x 81.3°
	76024	Cosmos-808	16 Mar 1976	P		618 x 647 km x 81.3°
	76032	Meteor-1#24	07 Apr 1976	P		863 x 906 km x 81.2°
	76043	Meteor-1#25	15 May 1976	P		866 x 908 km x 81.2°
	76085	Cosmos-851	27 Aug 1976	P		592 x 649 km x 81.0°
	76102	Meteor-1#26	16 Oct 1976	P		871 x 904 km x 81.3°
	77002	Meteor-2#2	07 Jan 1977	P		893 x 932 km x 81.3°
	77015	Cosmos-895	27 Feb 1977	P		613 x 648 km x 81.2°
	77024	Meteor-1#27	05 Apr 1977	P		869 x 909 km x 81.2°
	77057	Meteor-1#28	29 Jun 1977	T		602 x 685 km x 98.0°
	77061	Cosmos-925	07 Jul 1977	P		622 x 645 km x 81.2°
	77091	Cosmos-955	20 Sep 1977	P		631 x 664 km x 81.2°
	77117	Meteor-2#3	14 Dec 1977	P		872 x 906 km x 81.2°
	78004	Cosmos-975	10 Jan 1978	P		637 x 680 km x 81.2°
	78045	Cosmos-1005	12 May 1978	P		626 x 672 km x 81.2°
	78094	Cosmos-1043	10 Oct 1978	P		625 x 650 km x 81.1°
	78117	Cosmos-1063	19 Dec 1978	P		632 x 661 km x 81.2°
	78121	Cosmos-1066	23 Dec 1978	P		848 x 908 km x 81.2°
	79005	Meteor-1#29	25 Jan 1979	T		628 x 656 km x 98.0°
	79012	Cosmos-1077	14 Feb 1979	P		629 x 651 km x 81.2°
	79021	Meteor-2#4	01 Mar 1979	P		857 x 908 km x 81.2°
	79032	Cosmos-1093	13 Apr 1979	P		625 x 650 km x 81.3°
	79067	Cosmos-1116	20 Jul 1979	P		608 x 649 km x 81.2°
	79093	Cosmos-1143	20 Oct 1979	P		625 x 665 km x 81.2°
	79095	Meteor-2#5	31 Oct 1979	P		877 x 904 km x 81.2°
	79099	Cosmos-1145	27 Nov 1979	P		629 x 622 km x 81.2°
	80008	Cosmos-1154	30 Jan 1980	P		634 x 671 km x 81.3°
	80044	Cosmos-1184	04 Jun 1980	P		621 x 662 km x 81.2°
	80051	Meteor-1#30	18 Jun 1980	T		589 x 678 km x 98.0°
	80069	Cosmos-1206	15 Aug 1980	P		630 x 659 km x 81.3°
	80073	Meteor-2#6	09 Sep 1980	P		868 x 906 km x 81.2°
	80093	Cosmos-1222	21 Nov 1980	P		624 x 659 km x 81.2°
	81008	Cosmos-1242	28 Jan 1981	P		635 x 684 km x 81.2°
	81043	Meteor-2#7	14 May 1981	P		868 x 904 km x 81.3°
	81046	Cosmos-1271	19 May 1981	P		628 x 670 km x 81.2°
	81065	Meteor Priroda	10 Jul 1981	T		611 x 689 km x 97.9°
	81075	Intercosmos 22	07 Aug 1981	P		825 x 906 km x 81.2°
	81103	Cosmos-1315	14 Oct 1981	P		628 x 685 km x 81.2°
	82013	Cosmos-1340	19 Feb 1982	P		636 x 679 km x 81.2°
	82027	Cosmos-1346	31 Mar 1982	P		623 x 675 km x 81.0°
	82039	Cosmos-1356	05 May 1982	P		632 x 684 km x 81.2°
	82079	Cosmos-1400	05 Aug 1982	P		631 x 675 km x 81.2°
	82116	Meteor-2#9	14 Dec 1982	P		836 x 904 km x 81.3°
	83003	Cosmos-1437	20 Jan 1983	P		629 x 678 km x 81.2°
	83010	Cosmos-1441	16 Feb 1983	P		632 x 667 km x 81.0°
	83075	Cosmos-1484	24 Jul 1983	T		595 x 673 km x 98.0°
	83109	Meteor-2#10	28 Oct 1983	P		780 x 901 km x 81.2°
	85090	Cosmos-1689	03 Oct 1985	T		573 x 657 km x 98.0°
	88021	IRS 1A	17 Mar 1988	T		863 x 917 km x 99.0°
	88032	Cosmos-1939	20 Apr 1988	T		620 x 678 km x 98.0°
	91061	IRS-1B	29 Aug 1991	T	8A92M	860 x 920 km x 99.2°


 A2e / SL6 (Molniya) launches

by Jean-Jacques Serra

Semiorka with a Block I third stage

#	Launch id	Payload	Launch date	Site	Status (orbit in perigee x apogee x inc. x period)
1		(Mars)	10 Oct 1960	T	Failure
2		(Mars)	14 Oct 1960	T	Failure
3	61002	Venus S-7	04 Feb 1961	T	223 x 328 km x 65.0°
4	61003	Venus-1 S-8	12 Feb 1961	T	Probe
5		(Venus)	25 Aug 1962	T	173 x 252 km x 64.9°
6		(Venus)	03 Sep 1962	T	180 x 310 km x 64.9°
7		(Venus)	12 Sep 1962	T	176 x 176 km x 64.8°
8		(Mars)	24 Oct 1962	T	180 x 485 km x 64.9°
9	62061	Mar-01	01 Nov 1962	T	Probe
10		(Mars)	04 Nov 1962	T	200 x 226 km x 64.8°
11		(Luna)	04 Jan 1963	T	150 x 150 km x 64.9°
12		(Luna)	03 Mar 1963	T	Failure
13	63008	Luna-4	02 Apr 1963	T	orbit
14	63004	Cosmos-21	11 Nov 1963	T	195 x 229 km x 64.8°
15		(Zond)	19 Feb 1964	T	Failure
16		(Zond)	01 Mar 1964	T	Failure
17		(Luna)	21 Mar 1964	T	Failure
18	64014	Cosmos-27	27 Mar 1964	T	192 x 237 km x 64.8°
19	64016	Zond-1	02 Apr 1964	T	Probe
20		(Luna)	20 Apr 1964	T	Failure
21		(Molniya)	04 Jun 1964	T	Failure
22	64049	Cosmos-41	22 Aug 1964	T	394 x 39855 km x 64.0° (failed Molniya 1)
23	64078	Zond-2	30 Nov 1964	T	Probe
24	65018	Cosmos-60	12 Mar 1965	T	201 x 287 km x 64.7°
25		(Luna)	10 Apr 1965	T	Failure
26	65030	Molniya 1-01	23 Apr 1965	T	548 x 39957 km x 65.0°
27	65036	Luna-5	09 May 1965	T	impact
28	65044	Luna-6	08 Jun 1965	T	flyby
29	65056	Zond-3	18 Jul 1965	T	Probe
30	65077	Luna-7	04 Oct 1965	T	impact
31	65080	Molniya-1#2	14 Oct 1965	T	500 x 40000 km x 65.0°
32	65091	Venus-2	12 Nov 1965	T	Probe
33	65092	Venus-3	16 Nov 1965	T	fall
34	65094	Cosmos-96	23 Nov 1965	T	227 x 310 km x 51.9°
35		(Venus)	26 Nov 1965	T	Failure
36	65099	Luna-8	03 Dec 1965	T	impact
37	66006	Luna-9	31 Jan 1966	T	landing
38	66017	Cosmos-111	01 Mar 1966	T	191 x 226 km x 51.8°
		Molniya?	27 Mar 1966		failure?
39	66027	Luna-10	31 Mar 1966	T	orbit
40	66035	Molniya-1#3	25 Apr 1966	T	499 x 39500 km x 64.5°
41		(Luna)	30 Apr 1966	T	Failure
42	66078	Luna-11	24 Aug 1966	T	orbit
43	66092	Molniya-1#4	20 Oct 1966	T	485 x 39700 km x 64.9°
44	66094	Luna-12	22 Oct 1966	T	orbit
45	66116	Luna-13	21 Dec 1966	T	landing
46	67046	Cosmos-159	16 May 1967	T	380 x 60600 km x 51.8°
47	67052	Molniya-1#5	24 May 1967	T	460 x 39810 km x 64.8°
48	67055	Venus-4	12 Jun 1967	T	fall
49	67063	Cosmos-167	17 Jun 1967	T	201 x 286 km x 51.8°
50	67082	Cosmos-174	31 Aug 1967	T	500 x 39750 km x 64.5° (failed Molniya 1)
51	67095	Molniya-1#6	03 Oct 1967	T	465 x 39600 km x 65.0°
52	67101	Molniya-1#7	22 Oct 1967	T	456 x 39740 km x 64.7°
53		(Luna)	07 Feb 1968	T	Failure
54	68027	Luna-14	07 Apr 1968	T	orbit
55	68035	Molniya-1#8	21 Apr 1968	T	460 x 39700 km x 65.0°
56	68057	Molniya-1#9	05 Jul 1968	T	470 x 39770 km x 65.0°
57	68085	Molniya-1#10	05 Oct 1968	T	490 x 39600 km x 65.0°
58	68115	Cosmos-260	16 Dec 1968	T	500 x 39600 km x 65.0° (failed Molniya 1)
59	69001	Venus-5	05 Jan 1969	T	Probe
60	69002	Venus-6	10 Jan 1969	T	Probe
61	69035	Molniya-1#11	11 Apr 1969	T	470 x 39700 km x 65.0°
62	69061	Molniya-1#12	22 Jul 1969	T	320 x 39540 km x 64.9°
63	70013	Molniya-1#13	11 Feb 1970	T	488 x 39176 km x 65.3°
64	70049	Molniya-1#14	26 Jun 1970	P	447 x 39260 km x 65.4°
65	70060	Venus-7	17 Aug 1970	T	Probe
66	70065	Cosmos-359	22 Aug 1970	T	208 x 890 km x 51.1°
67	70077	Molniya-1#15	29 Sep 1970	P	480 x 39300 km x 65.6°
68	70101	Molniya-1#16	27 Nov 1970	P	471 x 39348 km x 65.5°
69	70114	Molniya-1#17	25 Dec 1970	P	495 x 39556 km x 65.0°
70	71064	Molniya-1#18	28 Jul 1971	P	470 x 39300 km x 65.4°
71	71100	Molniya 2-01	24 Nov 1971	P	460 x 39350 km x 65.4°
72	71115	Molniya-1#19	19 Dec 1971	P	490 x 39200 km x 65.5°
73	72021	Venus-8	27 Mar 1972	T	Probe
74	72023	Cosmos-482	31 Mar 1972	T	210 x 9812 km x 52.0°
75	72025	Molniya-1#20	04 Apr 1972	T?	480 x 39360 km x 65.6°
76	72029	Prognoz 01	14 Apr 1972	T	1005 x 199667 km x 65.0°
77	72037	Molniya-2#2	19 May 1972	P	460 x 39300 km x 65.5°
78	72046	Prognoz 02	29 Jun 1972	T	500 x 200000 km x 65.0°
79	72072	Cosmos-520	19 Sep 1972	P	652 x 39319 km x 62.8°
80	72075	Molniya-2#3	30 Sep 1972	P	480 x 39200 km x 65.3°
81	72081	Molniya-1#21	14 Oct 1972	P	480 x 39300 km x 65.3°
82	72095	Molniya-1#22	02 Dec 1972	P	500 x 39100 km x 65.0°
83	72098	Molniya-2#4	12 Dec 1972	P	470 x 39300 km x 65.3°
84	73007	Molniya-1#23	03 Feb 1973	P	470 x 39200 km x 65.0°
85	73009	Prognoz 03	15 Feb 1973	T	590 x 200000 km x 65.0°
86	73018	Molniya-2#5	05 Apr 1973	P	500 x 39100 km x 65.5°
87	73045	Molniya-2#6	11 Jul 1973	P	980 x 39280 km x 65.3°
88	73061	Molniya-1#24	30 Aug 1973	P	480 x 37970 km x 65.3°
89	73076	Molniya-2#7	19 Oct 1973	P	630 x 40600 km x 62.8°
90	73084	Cosmos-606	02 Nov 1973	P	710 x 39360 km x 62.8°
91	73089	Molniya-1#25	14 Nov 1973	P	480 x 39140 km x 65.0°
92	73097	Molniya-1#26	30 Nov 1973	P	460 x 40900 km x 62.7°
93	73106	Molniya-2#8	25 Dec 1973	P	466 x 40865 km x 62.8°
94	74023	Molniya-1#27	20 Apr 1974	P	646 x 40170 km x 62.9°
95	74026	Molniya-2#9	26 Apr 1974	P	463 x 40850 km x 62.9°
96	74050	Cosmos-665	29 Jun 1974	P	633 x 39385 km x 62.9°
97	74056	Molniya-2#10	23 Jul 1974	P	460 x 40900 km x 62.8°
98	74081	Molniya-1#28	24 Oct 1974	P	683 x 40167 km x 62.8°
99	74092	Molniya 3-01	21 Nov 1974	P	650 x 40690 km x 62.8°
100	74102	Molniya-2#11	22 Dec 1974	P	641 x 40675 km x 62.9°
101	75007	Cosmos-706	30 Jan 1975	P	635 x 39810 km x 62.8°
102	75009	Molniya-2#12	06 Feb 1975	P	640 x 40685 km x 62.8°
103	75029	Molniya-3#2	14 Apr 1975	P	636 x 40660 km x 63.0°
104	75036	Molniya-1#29	29 Apr 1975	P	468 x 40848 km x 63.0°
105	75049	Molniya-1#30 +	05 Jun 1975	P	450 x 40536 km x 63.0°
106	75063	Molniya-2#13	08 Jul 1975	P	465 x 40864 km x 62.8°
107	75079	Molniya-1#31	03 Sep 1975	P	639 x 40618 km x 62.8°
108	75081	Molniya-2#14	09 Sep 1975	P	470 x 40836 km x 62.8°
109	75105	Molniya-3#3	14 Nov 1975	P	470 x 40830 km x 62.4°
110	75121	Molniya-2#15	17 Dec 1975	P	451 x 40836 km x 62.8°
111	75122	Prognoz 04	22 Dec 1975	T	634 x 199000 km x 65.0°
112	75125	Molniya-3#4	27 Dec 1975	P	470 x 40800 km x 62.8°
113	76006	Molniya-1#32	22 Jan 1976	P	491 x 38934 km x 62.5°
114	76021	Molniya-1#33	11 Mar 1976	P	518 x 40683 km x 62.5°
115	76026	Molniya-1#34	18 Mar 1976	P	494 x 38984 km x 63.0°
116	76041	Molniya-3#2(5)	12 May 1976	P	652 x 40660 km x 62.8°
117	76062	Cosmos-837	01 Jul 1976	P	505 x 860 km x 62.8°
118	76074	Molniya-1#35	23 Jul 1976	P	499 x 39059 km x 62.9°
119	76088	Cosmos-853	01 Sep 1976	P	243 x 498 km x 62.8°
120	76105	Cosmos-862	22 Oct 1976	P	620 x 39300 km x 62.5°
121	76112	Prognoz 05	25 Nov 1976	T	510 x 190000 km x 65.0°
122	76116	Molniya-2#16	02 Dec 1976	P	657 x 40608 km x 62.8°
123	76127	Molniya-3#6	28 Dec 1976	P	640 x 40630 km x 62.8°
124	77010	Molniya-2#17	11 Feb 1977	P	493 x 40757 km x 62.5°
125	77021	Molniya-1#36	24 Mar 1977	P	484 x 40816 km x 62.8°
126	77027	Cosmos-903	11 Apr 1977	P	630 x 40170 km x 62.8°
127	77032	Molniya-3#7	28 Apr 1977	P	467 x 40807 km x 62.8°
128	77047	Cosmos-917	16 Jun 1977	P	625 x 40150 km x 62.9°
129	77054	Molniya-1#37	24 Jun 1977	P	480 x 39016 km x 62.9°
130	77068	Cosmos-931	20 Jul 1977	P	600 x 40180 km x 62.8°
131	77082	Molniya-1#38	30 Aug 1977	P	449 x 40843 km x 62.8°
132	77093	Prognoz 06	22 Sep 1977	T	498 x 198000 km x 65.0°
133	77105	Molniya-3#8	28 Oct 1977	P	478 x 40764 km x 62.8°
134	78009	Molniya-3#9	24 Jan 1978	P	661 x 40631 km x 62.8°
135	78024	Molniya-1#39	03 Mar 1978	P	632 x 40733 km x 62.8°
136	78055	Molniya-1#40	02 Jun 1978	P	457 x 40837 km x 62.5°
137	78066	Cosmos-1024	28 Jun 1978	P	630 x 40000 km x 62.8°
138	78072	Molniya-1#41	14 Jul 1978	P	650 x 40660 km x 62.8°
139	78080	Molniya-1#42	22 Aug 1978	P	442 x 40793 km x 62.8°
140	78083	Cosmos-1030	06 Sep 1978	P	650 x 40100 km x 62.8°
141	78095	Molniya-3#10	13 Oct 1978	P	467 x 40825 km x 62.8°
142	78101	Prognoz 07	30 Oct 1978	T	483 x 202965 km x 65.0°
143	79004	Molniya-3#7(11)	18 Jan 1979	P	474 x 40806 km x 62.8°
144	79031	Molniya-1#43	12 Apr 1979	P	656 x 40590 km x 62.9°
145	79048	Molniya-3#12	06 Jun 1979	P	473 x 40769 km x 62.5°
146	79058	Cosmos-1109	27 Jun 1979	P	626 x 40130 km x 62.8°
147	79070	Molniya-1#44	31 Jul 1979	P	470 x 40860 km x 62.8°
148	79077	Cosmos-1124	28 Aug 1979	P	620 x 40070 km x 62.8°
149	79091	Molniya-1#45	20 Oct 1979	P	640 x 40640 km x 62.8°
150	80002	Molniya-1#46	11 Jan 1980	P	478 x 40830 km x 62.8°
151	80013	Cosmos-1164	12 Feb 1980	P	220 x 640 km x 62.8°
152	80028	Cosmos-1172	12 Apr 1980	P	637 x 40160 km x 62.8°
153	80031	Cosmos-1175	18 Apr 1980	P	317 x 485 km x 62.5°
154	80050	Cosmos-1188	14 Jun 1980	P	628 x 40165 km x 62.8°
155	80053	Molniya-1#47	21 Jun 1980	P	658 x 40707 km x 62.5°
156	80057	Cosmos-1191	02 Jul 1980	P	646 x 40165 km x 62.8°
157	80063	Molniya-3#13	18 Jul 1980	P	467 x 40185 km x 62.8°
158	80085	Cosmos-1217	24 Oct 1980	P	642 x 40165 km x 62.8°
159	80092	Molniya-1#48	16 Nov 1980	P	640 x 40651 km x 62.3°
160	80095	Cosmos-1223	28 Nov 1980	P	614 x 40165 km x 62.8°
161	80103	Prognoz 08	25 Dec 1980	T	550 x 199000 km x 65.0°
162	81002	Molniya-3#14	09 Jan 1981	P	485 x 40784 km x 62.5°
163	81009	Molniya-1#49	30 Jan 1981	P	461 x 40801 km x 62.8°
164	81016	Cosmos-1247	19 Feb 1981	P	613 x 39540 km x 62.8°
165	81030	Molniya-3#15	22 Mar 1981	P	641 x 40655 km x 62.8°
166	81031	Cosmos-1261	31 Mar 1981	P	615 x 40170 km x 62.8°
167	81054	Molniya-3#16	09 Jun 1981	P	471 x 40645 km x 62.8°
168	81058	Cosmos-1278	19 Jun 1981	P	645 x 40165 km x 62.8°
169	81060	Molniya-1#50	25 Jun 1981	P	645 x 40645 km x 62.8°
170	81071	Cosmos-1285	04 Aug 1981	P	630 x 40165 km x 62.8°
171	81088	Cosmos-1305	11 Sep 1981	P	648 x 13870 km x 63.0°
172	81105	Molniya-3#17	17 Oct 1981	P	649 x 40644 km x 63.0°
173	81108	Cosmos-1317	02 Nov 1981	P	636 x 40165 km x 62.8°
174	81113	Molniya-1#51	17 Nov 1981	P	472 x 39117 km x 62.8°
175	81123	Molniya-1#52	23 Dec 1981	P	485 x 38990 km x 63.0°
176	82015	Molniya-1#53	26 Feb 1982	P	490 x 40765 km x 62.8°
177	82016	Cosmos-1341	03 Mar 1982	P	614 x 40165 km x 62.8°
178	82023	Molniya-3#18	24 Mar 1982	P	656 x 40615 km x 62.9°
179	82029	Cosmos-1348	07 Apr 1982	P	613 x 39342 km x 62.8°
180	82045	Cosmos-1367	20 May 1982	P	612 x 39530 km x 62.8°
181	82050	Molniya-1#54	29 May 1982	P	653 x 40633 km x 62.8°
182	82064	Cosmos-1382	25 Jun 1982	P	614 x 39540 km x 62.8°
183	82074	Molniya-1#55	21 Jul 1982	P	650 x 38900 km x 63.0°
184	82083	Molniya-3#19	27 Aug 1982	P	494 x 40814 km x 62.8°
185	82095	Cosmos-1409	22 Sep 1982	P	613 x 39340 km x 62.8°
186	82115	Cosmos-1423	08 Dec 1982	P	401 x 575 km x 62.8°
187	83015	Molniya-3#20	11 Mar 1983	P	474 x 40773 km x 62.8°
188	83019	Molniya-1#56	16 Mar 1983	P	488 x 40821 km x 62.8°
189	83025	Molniya-1#57	02 Apr 1983	P	483 x 39023 km x 62.9°
190	83038	Cosmos-1456	25 Apr 1983	P	613 x 39343 km x 62.8°
191	83067	Prognoz 09	01 Jul 1983	T	380 x 720000 km x 65.5°
192	83070	Cosmos-1481	08 Jul 1983	P	615 x 40165 km x 62.8°
193	83073	Molniya-1#58	19 Jul 1983	P	480 x 39025 km x 62.9°
194	83090	Molniya-3#21	30 Aug 1983	P	497 x 40815 km x 62.8°
195	83114	Molniya-1#59	18 Nov 1983	P	465 x 39150 km x 62.8°
196	83123	Molniya-3#22	21 Dec 1983	P	617 x 40591 km x 62.8°
197	83126	Cosmos-1518	28 Dec 1983	P	614 x 39345 km x 62.8°
198	84024	Cosmos-1541	06 Mar 1984	P	584 x 39424 km x 62.9°
199	84029	Molniya-1#60	16 Mar 1984	P	646 x 40579 km x 62.9°
200	84033	Cosmos-1547	04 Apr 1984	P	615 x 39340 km x 62.8°
201	84055	Cosmos-1569	06 Jun 1984	P	614 x 40165 km x 62.8°
202	84071	Cosmos-1581	04 Jul 1984	P	614 x 40165 km x 62.8°
203	84079	Cosmos-1586	02 Aug 1984	P	614 x 40165 km x 62.8°
204	84085	Molniya-1#61	10 Aug 1984	P	479 x 40772 km x 62.7°
205	84089	Molniya-1#62	24 Aug 1984	P	467 x 40877 km x 62.8°
206	84096	Cosmos-1596	07 Sep 1984	P	613 x 39342 km x 62.8°
207	84107	Cosmos-1604	04 Oct 1984	P	613 x 39342 km x 62.8°
208	84124	Molniya-1#63	14 Dec 1984	P	461 x 40900 km x 62.8°
209	85004	Molniya-3#23	16 Jan 1985	P	646 x 40653 km x 62.9°
210	85033	Prognoz 10	26 Apr 1985	T	400 x 200000 km x 65.0°
211	85040	Molniya-3#24	29 May 1985	P	465 x 40850 km x 62.8°
212	85045	Cosmos-1658	11 Jun 1985	P	613 x 39342 km x 62.8°
213	85049	Cosmos-1661	18 Jun 1985	P	613 x 40164 km x 62.8°
214	85061	Molniya-3#25	17 Jul 1985	P	462 x 40850 km x 62.8°
215	85071	Cosmos-1675	12 Aug 1985	P	613 x 39342 km x 62.8°
216	85074	Molniya-1#64	22 Aug 1985	P	656 x 40638 km x 62.8°
217	85084	Cosmos-1684	24 Sep 1985	P	613 x 39342 km x 62.8°
218	85088	Cosmos-1687	30 Sep 1985	P	613 x 39330 km x 62.8°
219	85091	Molniya-3#26	03 Oct 1985	P	623 x 40592 km x 62.8°
220	85098	Cosmos-1698	23 Oct 1985	P	601 x 39434 km x 62.9°
221	85099	Molniya-1#67	23 Oct 1985	P	633 x 38849 km x 62.9°
222	85103	Molniya-1#66	28 Oct 1985	P	465 x 39129 km x 62.8°
223	85105	Cosmos-1701	09 Nov 1985	P	613 x 39342 km x 62.8°
224	85117	Molniya-3#27	24 Dec 1985	P	477 x 40793 km x 62.8°
225	86011	Cosmos-1729	01 Feb 1986	P	632 x 39170 km x 62.9°
226	86031	Molniya-3#28	18 Apr 1986	P	638 x 40664 km x 62.9°
227	86049	Molniya-3#29	19 Jun 1986	P	640 x 40679 km x 62.9°
228	86050	Cosmos-1761	05 Jul 1986	P	607 x 39325 km x 62.9°
229	86057	Molniya-1#67	30 Jul 1986	P	658 x 40615 km x 62.9°
230	86065	Cosmos-1774	28 Aug 1986	P	614 x 39342 km x 62.8°
231	86068	Molniya-1#68	05 Sep 1986	P	645 x 40558 km x 63.0°
232	86075	Cosmos-1783	03 Oct 1986	P	613 x 20045 km x 62.8°
233	86078	Cosmos-1785	15 Oct 1986	P	596 x 39300 km x 63.0°
234	86079	Molniya-3#30	20 Oct 1986	P	645 x 38988 km x 62.9°
235	86089	Molniya-1#69	15 Nov 1986	P	469 x 40817 km x 62.5°
236	86091	Cosmos-1793	20 Nov 1986	P	611 x 39323 km x 63.0°
237	86098	Cosmos-1806	12 Dec 1986	P	612 x 39307 km x 63.0°
238	86103	Molniya-1#70	26 Dec 1986	P	484 x 39075 km x 63.0°
239	87008	Molniya-3#31	22 Jan 1987	P	473 x 40800 km x 62.8°
240	87048	Cosmos 1849	04 Jun 1987	P	613 x 39342 km x 62.9°
241	87050	Cosmos 1851	12 Jun 1987	P	592 x 39402 km x 62.8°
242	87105	Cosmos-1903	21 Dec 1987	P	614 x 38342 km x 62.8°
243	88013	Cosmos-1922	26 Feb 1988	P	614 x 39300 km x 62.9°
244	88017	Molniya 1-71	11 Mar 1988	P	490 x 38960 km x 62.5°
245	88022	Molniya 1-72	17 Mar 1988	P	655 x 40584 km x 62.9°
246	88044	Molniya-3#32	26 May 1988	P	587 x 39782 km x 62.8°
247	88069	Molniya-1#73	12 Aug 1988	P	615 x 40754 km x 62.9°
248	88076	Cosmos 1966	30 Aug 1988	P	617 x 39299 km x 62.9°
249	88090	Molniya-3#33	29 Sep 1988	P	646 x 38937 km x 62.9°
250	88092	Cosmos 1974	03 Oct 1988	P	585 x 39341 km x 62.9°
251	88096	Cosmos 1977	25 Oct 1988	P	613 x 39342 km x 62.8°
252	88112	Molniya 3-34	22 Dec 1988	P	440 x 39800 km x 62.8°
253	88115	Molniya 1-74	28 Dec 1988	P	630 x 38900 km x 62.8°
254	89011	Cosmos 2001	14 Feb 1989	P	613 x 39242 km x 62.8°
255	89014	Molniya-1#75	15 Feb 1989	P	486 x 38937 km x 62.5°
256	89043	Molniya 3-35	08 Jun 1989	P	630 x 40700 km x 62.9°
257	89078	Molniya-1#76	27 Sep 1989	P	640 x 39700 km x 62.8°
258	89091	Cosmos 2050	23 Nov 1989	P	600 x 39760 km x 63.0°
259	89094	Molniya 3-36	28 Nov 1989	P	640 x 39670 km x 62.9°
260	90006	Molniya 3-37	23 Jan 1990	P	600 x 39690 km x 62.8°
261	90026	Cosmos 2063	27 Mar 1990	P	608 x 39739 km x 62.8°
262	90039	Molniya-1#77	26 Apr 1990	P	630 x 39720 km x 62.8°
263	90040	Cosmos-2076	28 Apr 1990	P	577 x 39780 km x 63.0°
264	90052	Molniya-3#38	13 Jun 1990	P	464 x 39890 km x 62.8°
265	90055	Cosmos-2084	21 Jun 1990	P	586 x 757 km x 62.8°
266	90064	Cosmos-2087	25 Jul 1990	P	613 x 39432 km x 62.8°
267	90071	Molniya-1#78	10 Aug 1990	P	646 x 40634 km x 62.7°
268	90076	Cosmos-2097	28 Aug 1990	P	619 x 38881 km x 62.8°
269	90084	Molniya-3#39	20 Sep 1990	P	454 x 40782 km x 62.8°
270	90099	Cosmos-2105	20 Nov 1990	P	606 x 39339 km x 63.0°
271	90101	Molniya-1#79	23 Nov 1990	P	650 x 40600 km x 62.8°
272	91012	Molniya-1#80	15 Feb 1991	P	471 x 39133 km x 62.8°
273	91022	Molniya-3#40	22 Mar 1991	P	430 x 39090 km x 62.8°
274	91043	Molniya-1#81	18 Jun 1991	P	450 x 39900 km x 62.9°
275	91053	Molniya-1#82	01 Aug 1991	P	650 x 40680 km x 62.9°
276	91065	Molniya-3#41	17 Sep 1991	P	460 x 40850 km x 62.7°
277	92003	Cosmos-2176	24 Jan 1992	P	580 x 39350 km x 62.8°
278	92011	Molniya-1#83	04 Mar 1992	P	630 x 39000 km x 62.9°
279	92040	Cosmos-2196	08 Jul 1992	P	590 x 39250 km x 63.0°
280	92050	Molniya-1#84	06 Aug 1992	P	635 x 40600 km x 63.0°
281	92067	Molniya 3-42	14 Oct 1992	P	460 x 40850 km x 62.8°
282	92069	Cosmos-2217	21 Oct 1992	P	600 x 39400 km x 62.8°
283	92081	Cosmos 2222	25 Nov 1992	P	590 x 39300 km x 62.9°
284	92085	Molniya-3#43	02 Dec 1992	P	460 x 39100 km x 62.9°
285	93002	Molniya 1-85	13 Jan 1993	P	650 x 40600 km x 63.0°
286	93006	Cosmos 2232	26 Jan 1993	P	620 x 39700 km x 62.7°
287	93022	Cosmos 2241	06 Apr 1993	P	620 x 39170 km x 62.8°
288	93025	Molniya 3-44	21 Apr 1993	P	670 x 40600 km x 62.8°
289	93035	Molniya 1-86	26 May 1993	P	450 x 40880 km x 62.7°
290	93049	Molniya 3-45	04 Aug 1993	P	410 x 39930 km x 62.8°
291	93051	Cosmos 2261	10 Aug 1993	P	610 x 39400 km x 62.8°
292	93079	Molniya 1-87	22 Dec 1993	P	450 x 39200 km x 62.8°
293	94048	Cosmos 2286	05 Aug 1994	P	750 x 39600 km x 63.4°
294	94051	Molniya 3-46	23 Aug 1994	P	630 x 39730 km x 63.0°
295	94081	Molniya 1-88	14 Dec 1994	P	515 x 39830 km x 62.8°
296	95026	Cosmos 2312	24 May 1995	P	708 x 39275 km x 62.9°
297	95039	Prognoz 11	03 Aug 1995	P	505 x 193060 km x 63.8°
298	95042	Molniya 3-47	09 Aug 1995	P	427 x 39970 km x 62.8°
299	95072	IRS 1C	28 Dec 1995	T	816 x 818 km x 98.6°
300	94081	Molniya 1-89	14 Aug 1996 at 22:21 UT	P
301	96050	Prognoz 12	29 Aug 1996	P
302	96060	Molniya 3-48	24 Oct 1996	P
303	97015	Cosmos 2340	09 Apr 1997	P
304	97022	Cosmos 2342	14 May 1997	P
305	97054	Molniya 1-90	24 Sep 1997 at 21:32 UT	P
306	98027	Cosmos 2351	7 May 1998at 08:53 UT	P
307	98040	Molniya 3-49	1 Jul 1998 at 00:48 UT	P
308	98054	Molniya 1-91	28 Sep 1998 at 23:41 UT	P
309	99036	Molniya 3-50	5 Jul 1999 at 08:46 UT	P


 A2 / SL4 (Soyuz) launches

by Jean-Jacques Serra

Semiorka with a Block I third stage

#	Launch id	Payload	Launch date	Site	Status (orbit in perigee x apogee x inc. x period)
	63045	Cosmos-22	16 Nov 1963	T	205 x 394 km x 64.9°
	64023	Cosmos-30	18 May 1964	T	207 x 383 km x 64.9°
	64034	Cosmos-34	01 Jul 1964	T	205 x 360 km x 65.0°
	64055	Cosmos-45	13 Sep 1964	T	206 x 327 km x 64.9°
	64062	Cosmos-47	06 Oct 1964	T	177 x 413 km x 64.8°
	64065	Voskhod-1	12 Oct 1964	T	177 x 408 km x 64.8°
	65012	Cosmos-57	22 Feb 1965	T	175 x 512 km x 64.8°
	65015	Cosmos-59	07 Mar 1965	T	209 x 339 km x 65.0°
	65021	Voskhod-2	18 Mar 1965	T	174 x 498 km x 64.8°
	65029	Cosmos-65	17 Apr 1965	T	210 x 342 km x 65.0°
	65040	Cosmos-67	25 May 1965	T	207 x 350 km x 51.8°
	65049	Cosmos-69	25 Jun 1965	T	211 x 332 km x 64.9°
	65061	Cosmos-77	03 Aug 1965	T	200 x 350 km x 51.8°
	65069	Cosmos-79	25 Aug 1965	T	211 x 359 km x 64.9°
	65071	Cosmos-85	09 Sep 1965	T	212 x 319 km x 65.0°
	65075	Cosmos-91	23 Sep 1965	T	212 x 342 km x 65.0°
	65083	Cosmos-92	16 Oct 1965	T	212 x 342 km x 65.0°
	65085	Cosmos-94	28 Oct 1965	T	211 x 293 km x 65.0°
	66014	Cosmos-109	19 Feb 1966	T	209 x 309 km x 65.0°
	66015	Cosmos 0110	22 Feb 1966	T	187 x 904 km x 51.9°
	66023	Cosmos-113	21 Mar 1966	T	210 x 327 km x 65.0°
	66028	Cosmos-114	06 Apr 1966	P	210 x 374 km x 73.0°
	66050	Cosmos-120	08 Jun 1966	T	200 x 300 km x 51.8°
	66054	Cosmos-121	17 Jun 1966	P	210 x 354 km x 72.9°
	66064	Cosmos-124	14 Jul 1966	T	208 x 303 km x 51.8°
	66068	Cosmos-126	28 Jul 1966	T	212 x 359 km x 51.8°
	66071	Cosmos-127	08 Aug 1966	T	204 x 279 km x 51.9°
	66079	Cosmos-128	27 Aug 1966	T	212 x 364 km x 65.0°
	66093	Cosmos-130	20 Oct 1966	T	211 x 340 km x 65.0°
	66105	Cosmos-131	12 Nov 1966	P	205 x 360 km x 72.9°
	66107	Cosmos-133	28 Nov 1966	T	181 x 232 km x 51.9°
	66108	Cosmos-134	03 Dec 1966	T?	214 x 319 km x 65.0°
	67009	Cosmos-140	07 Feb 1967	T	170 x 241 km x 51.7°
	67012	Cosmos-141	08 Feb 1967	P	210 x 345 km x 72.9°
	67025	Cosmos-150	22 Mar 1967	P	206 x 373 km x 65.7°
	67033	Cosmos-155	12 Apr 1967	T	203 x 286 km x 51.8°
	67037	Soyouz-1	23 Apr 1967	T	201 x 224 km x 51.7°
	67049	Cosmos-161	22 May 1967	P	205 x 343 km x 65.7°
	67054	Cosmos-162	01 Jun 1967	T	201 x 280 km x 51.8°
	67057	Cosmos-164	08 Jun 1967	P	202 x 320 km x 65.7°
	67067	Cosmos-168	04 Jul 1967	T	199 x 268 km x 51.8°
	67078	Cosmos-172	09 Aug 1967	T	202 x 301 km x 51.8°
	67085	Cosmos-175	11 Sep 1967	P	210 x 386 km x 72.9°
	67088	Cosmos-177	16 Sep 1967	T	202 x 292 km x 51.8°
	67093	Cosmos-180	26 Sep 1967	P	212 x 370 km x 72.9°
	67097	Cosmos-181	11 Oct 1967	P	200 x 344 km x 65.6°
	67097	Cosmos-182	16 Oct 1967	T?	209 x 353 km x 65.0°
	67098	Cosmos-186	27 Oct 1967	T	208 x 234 km x 51.7°
	67107	Cosmos-188	30 Oct 1967	T	200 x 276 km x 51.7°
	67110	Cosmos-190	03 Nov 1967	P	201 x 347 km x 65.7°
	67117	Cosmos-193	25 Nov 1967	P	204 x 352 km x 65.7°
	67119	Cosmos-194	03 Dec 1967	P	204 x 332 km x 65.7°
	67124	Cosmos-195	16 Dec 1967	P	210 x 373 km x 65.7°
	68003	Cosmos-199	16 Jan 1968	P	204 x 386 km x 65.7°
	68009	Cosmos-201	06 Feb 1968		210 x 355 km x 65.0°
	68016	Cosmos-205	05 Mar 1968	P	201 x 310 km x 65.7°
	68021	Cosmos-207	16 Mar 1968	P	210 x 342 km x 65.6°
	68022	Cosmos-208	21 Mar 1968	T	207 x 305 km x 65.0°
	68024	Cosmos-210	03 Apr 1968	P	217 x 395 km x 81.2°
	68029	Cosmos-212	14 Apr 1968	T	210 x 239 km x 51.7°
	68030	Cosmos-213	15 Apr 1968	T	205 x 291 km x 51.4°
	68032	Cosmos-214	18 Apr 1968	P	211 x 403 km x 81.4°
	68034	Cosmos-216	20 Apr 1968	T	199 x 277 km x 51.8°
	68045	Cosmos-223	01 Jun 1968	P	212 x 374 km x 72.9°
	68046	Cosmos-224	04 Jun 1968	T	200 x 270 km x 51.8°
	68051	Cosmos-227	18 Jun 1968	T	194 x 281 km x 51.8°
	68053	Cosmos-228	21 Jun 1968	T	206 x 259 km x 51.6°
	68054	Cosmos-229	26 Jun 1968	P	210 x 354 km x 72.8°
	68058	Cosmos-231	10 Jul 1968	T	211 x 330 km x 65.0°
	68060	Cosmos-232	16 Jul 1968	T	202 x 352 km x 65.0°
	68062	Cosmos-234	30 Jul 1968	T	210 x 310 km x 51.8°
	68067	Cosmos-235	09 Aug 1968	T	207 x 303 km x 51.8°
	68071	Cosmos-237	27 Aug 1968	P	201 x 343 km x 65.4°
	68072	Cosmos-238	28 Aug 1968	T	199 x 219 km x 51.7°
	68073	Cosmos-239	05 Sep 1968	T	202 x 289 km x 51.8°
	68075	Cosmos-240	14 Sep 1968	T	197 x 293 km x 51.8°
	68077	Cosmos-241	16 Sep 1968	P	201 x 343 km x 65.4°
	68080	Cosmos-243	23 Sep 1968	P	210 x 319 km x 71.3°
	68087	Cosmos-246	07 Oct 1968	P	147 x 348 km x 65.4°
	68088	Cosmos-247	11 Oct 1968	P	205 x 362 km x 65.4°
	68093	Soyouz-2	25 Oct 1968	T	185 x 224 km x 51.7°
	68094	Soyouz-3	26 Oct 1968	T	205 x 225 km x 51.7°
	68096	Cosmos-251	31 Oct 1968	T	198 x 270 km x 65.0°
	68102	Cosmos-253	13 Nov 1968	P	206 x 335 km x 65.4°
	68104	Cosmos-254	21 Nov 1968	P	203 x 350 km x 65.4°
	68105	Cosmos-255	29 Nov 1968	P	201 x 336 km x 65.4°
	68111	Cosmos-258	10 Dec 1968	T	210 x 325 km x 65.0°
	69003	Cosmos-263	12 Jan 1969	P	205 x 346 km x 65.4°
	69004	Soyouz-4	14 Jan 1969	T	173 x 225 km x 51.7°
	69005	Soyouz-5	15 Jan 1969	T	200 x 230 km x 51.7°
	69008	Cosmos-264	23 Jan 1969	T	219 x 330 km x 70.0°
	69015	Cosmos-266	05 Feb 1969	P	208 x 358 km x 72.9°
	69017	Cosmos-267	26 Feb 1969	T	210 x 346 km x 65.0°
	69022	Cosmos-270	06 Mar 1969	P	205 x 350 km x 65.4°
	69023	Cosmos-271	15 Mar 1969	P	200 x 342 km x 65.4°
	69027	Cosmos-273	22 Mar 1969	P	205 x 356 km x 65.4°
	69028	Cosmos-274	24 Mar 1969	T	213 x 323 km x 65.0°
	69032	Cosmos-276	04 Apr 1969	P	214 x 410 km x 81.4°
	69034	Cosmos-278	09 Apr 1969	T	203 x 338 km x 65.0°
	69038	Cosmos-279	15 Apr 1969	T	194 x 280 km x 51.8°
	69040	Cosmos-280	23 Apr 1969	T	206 x 272 km x 51.6°
	69042	Cosmos-281	13 May 1969	P	194 x 317 km x 65.4°
	69044	Cosmos-282	20 May 1969	P	209 x 343 km x 65.4°
	69048	Cosmos-284	29 May 1969	T	207 x 308 km x 51.8°
	69052	Cosmos-286	15 Jun 1969	P	206 x 349 km x 65.4°
	69054	Cosmos-287	24 Jun 1969	T	190 x 281 km x 51.8°
	69055	Cosmos-288	27 Jun 1969	T	201 x 281 km x 51.8°
	69057	Cosmos-289	10 Jul 1969	P	200 x 350 km x 65.4°
	69060	Cosmos-290	22 Jul 1969	P	200 x 352 km x 65.4°
	69066	Cosmos-291	06 Aug 1969	T	153 x 574 km x 62.3°
	69071	Cosmos-293	16 Aug 1969	T	208 x 270 km x 51.8°
	69072	Cosmos-294	19 Aug 1969	P	202 x 348 km x 65.4°
	69075	Cosmos-296	29 Aug 1969	T	211 x 322 km x 65.0°
	69076	Cosmos-297	02 Sep 1969	P	211 x 334 km x 72.9°
	69078	Cosmos-299	18 Sep 1969	T	214 x 311 km x 65.0°
	69081	Cosmos-301	24 Sep 1969	P	197 x 307 km x 65.4°
	69085	Soyouz-6	11 Oct 1969	T	186 x 223 km x 51.7°
	69086	Soyouz-7	12 Oct 1969	T	207 x 226 km x 51.7°
	69087	Soyouz-8	13 Oct 1969	T	205 x 223 km x 51.7°
	69089	Cosmos-302	17 Oct 1969	P	202 x 340 km x 65.4°
	69093	Cosmos-306	24 Oct 1969	T	208 x 332 km x 65.0°
	69098	Cosmos-309	12 Nov 1969	P	203 x 384 km x 65.4°
	69100	Cosmos-310	15 Nov 1969	T	208 x 347 km x 65.0°
	69104	Cosmos-313	03 Dec 1969	P	204 x 276 km x 65.4°
	69109	Cosmos-317	23 Dec 1969	P	209 x 302 km x 65.4°
	70001	Cosmos-318	09 Jan 1970	T	204 x 295 km x 65.0°
	70007	Cosmos-322	21 Jan 1970	P	200 x 336 km x 65.4°
	70010	Cosmos-323	10 Feb 1970	P	206 x 348 km x 65.4°
	70015	Cosmos-325	04 Mar 1970	P	208 x 348 km x 65.4°
	70018	Cosmos-326	14 Mar 1970	P	212 x 393 km x 81.4°
	70022	Cosmos-328	27 Mar 1970	P	212 x 304 km x 72.9°
	70023	Cosmos-329	03 Apr 1970	P	203 x 240 km x 81.3°
	70026	Cosmos-331	08 Apr 1970	T	212 x 348 km x 65.0°
	70030	Cosmos-333	15 Apr 1970	P	217 x 265 km x 81.4°
	70038	Cosmos-344	12 May 1970	P	203 x 328 km x 72.9°
	70039	Cosmos-345	20 May 1970	T	191 x 270 km x 51.7°
	70041	Soyouz-9	02 Jun 1970	T	175 x 227 km x 51.6°
	70042	Cosmos-346	10 Jun 1970	T	196 x 274 km x 51.7°
	70045	Cosmos-349	17 Jun 1970	P	200 x 332 km x 65.4°
	70050	Cosmos-350	26 Jun 1970	T	203 x 257 km x 51.7°
	70052	Cosmos-352	07 Jul 1970	T	208 x 294 km x 51.8°
	70053	Cosmos-353	09 Jul 1970	P	204 x 283 km x 65.4°
	70058	Cosmos-355	07 Aug 1970	P	200 x 322 km x 65.4°
	70068	Cosmos-360	29 Aug 1970	T	209 x 306 km x 65.0°
	70071	Cosmos-361	08 Sep 1970	P	209 x 298 km x 72.9°
	70074	Cosmos-363	17 Sep 1970	T	208 x 295 km x 65.0°
	70075	Cosmos-364	22 Sep 1970	P	211 x 330 km x 65.4°
	70078	Cosmos-366	01 Oct 1970	T	204 x 294 km x 64.9°
	70080	Cosmos-368	08 Oct 1970	T	204 x 401 km x 65.0°
	70082	Cosmos-370	09 Oct 1970	T	203 x 288 km x 64.9°
	70092	Cosmos-376	30 Oct 1970	P	207 x 286 km x 65.4°
	70096	Cosmos-377	11 Nov 1970	T	204 x 286 km x 65.0°
	70099	Cosmos-379	24 Nov 1970	T	191 x 232 km x 51.6°
	70104	Cosmos-383	03 Dec 1970	P	204 x 278 km x 65.4°
	70105	Cosmos-384	10 Dec 1970	P	203 x 291 km x 72.9°
	70110	Cosmos-386	15 Dec 1970	T	214 x 275 km x 65.0°
	71001	Cosmos-390	12 Jan 1971	T	204 x 275 km x 65.0°
	71004	Cosmos-392	21 Jan 1971	T	204 x 278 km x 65.0°
	71014	Cosmos-396	18 Feb 1971	P	204 x 286 km x 65.4°
	71016	Cosmos-398	26 Feb 1971	T	195 x 275 km x 51.6°
	71017	Cosmos-399	03 Mar 1971	T	201 x 283 km x 65.0°
	71023	Cosmos-401	27 Mar 1971	P	185 x 290 km x 72.8°
	71026	Cosmos-403	02 Apr 1971	P	216 x 251 km x 81.4°
	71029	Cosmos-406	14 Apr 1971	P	223 x 264 km x 81.3°
	71034	Soyouz-10	23 Apr 1971	T
	71040	Cosmos-410	06 May 1971	T	207 x 300 km x 65.0°
	71043	Cosmos-420	18 May 1971	T	200 x 242 km x 51.8°
	71048	Cosmos-424	28 May 1971	P	214 x 309 km x 65.4°
	71053	Soyouz-11	06 Jun 1971	T
	71055	Cosmos-427	11 Jun 1971	P	211 x 227 km x 72.9°
	71057	Cosmos-428	24 Jun 1971	T	204 x 243 km x 51.8°
	71061	Cosmos-429	20 Jul 1971	T	204 x 260 km x 51.8°
	71062	Cosmos-430	23 Jul 1971	P	206 x 322 km x 65.4°
	71065	Cosmos-431	30 Jul 1971	T	202 x 262 km x 51.8°
	71066	Cosmos-432	05 Aug 1971	T	209 x 262 km x 51.8°
	71069	Cosmos-434	12 Aug 1971	T	197 x 285 km x 51.6°
	71077	Cosmos-438	14 Sep 1971	P	212 x 321 km x 65.4°
	71078	Cosmos-439	21 Sep 1971	P	219 x 308 km x 65.4°
	71081	Cosmos-441	28 Sep 1971	T	209 x 288 km x 65.0°
	71084	Cosmos-442	29 Sep 1971	P	182 x 312 km x 72.8°
	71085	Cosmos-443	07 Oct 1971	P	211 x 325 km x 65.4°
	71088	Cosmos-452	14 Oct 1971	T	201 x 270 km x 65.0°
	71094	Cosmos-454	02 Nov 1971	P	210 x 284 km x 65.5°
	71098	Cosmos-456	19 Oct 1971	P	218 x 328 km x 72.9°
	71107	Cosmos-463	06 Dec 1971	T	215 x 307 km x 65.0°
	71108	Cosmos-464	10 Dec 1971	P	206 x 405 km x 72.9°
	71112	Cosmos-466	16 Dec 1971	T	207 x 302 km x 65.0°
	71118	Cosmos-470	27 Dec 1971	P	195 x 273 km x 65.4°
	72001	Cosmos-471	12 Jan 1972	T	202 x 323 km x 65.0°
	72006	Cosmos-473	03 Feb 1972	T	209 x 333 km x 65.0°
	72008	Cosmos-474	16 Feb 1972	T	207 x 347 km x 65.0°
	72013	Cosmos-477	04 Mar 1972	P	212 x 328 km x 72.9°
	72015	Cosmos-478	15 Mar 1972	P	213 x 319 km x 65.4°
	72024	Cosmos-483	03 Apr 1972	P	212 x 345 km x 72.9°
	72026	Cosmos-484	06 Apr 1972	P	203 x 236 km x 81.3°
	72027	Intercosmos-6	07 Apr 1972	T	203 x 256 km x 51.8°
	72030	Cosmos-486	14 Apr 1972	P	214 x 267 km x 81.4°
	72034	Cosmos-488	05 May 1972	P	211 x 319 km x 65.4°
	72036	Cosmos-490	17 May 1972	P	212 x 310 km x 65.4°
	72038	Cosmos-491	25 May 1972	T	210 x 303 km x 65.0°
	72040	Cosmos-492	09 Jun 1972	T	210 x 342 km x 65.0°
	72042	Cosmos-493	21 Jun 1972	T	213 x 308 km x 65.0°
	72044	Cosmos-495	23 Jun 1972	P	206 x 298 km x 65.4°
	72045	Cosmos-496	26 Jun 1972	T	195 x 342 km x 51.6°
	72051	Cosmos-499	06 Jul 1972	T	209 x 283 km x 51.8°
	72055	Cosmos-502	13 Jul 1972	P	206 x 284 km x 65.4°
	72056	Cosmos-503	19 Jul 1972	P	208 x 304 km x 65.4°
	72059	Cosmos-512	28 Jul 1972	P	207 x 294 km x 65.4°
	72060	Cosmos-513	02 Aug 1972	T	209 x 340 km x 65.0°
	72063	Cosmos-515	18 Aug 1972	P	205 x 300 km x 72.9°
	72067	Cosmos-517	30 Aug 1972	T	207 x 305 km x 65.0°
	72070	Cosmos-518	15 Sep 1972	P	208 x 330 km x 72.9°
	72071	Cosmos-519	16 Sep 1972	P	210 x 343 km x 71.3°
	72077	Cosmos-522	04 Oct 1972	P	214 x 342 km x 72.9°
	72083	Cosmos-525	18 Oct 1972	P	208 x 292 km x 65.4°
	72086	Cosmos-527	31 Oct 1972	P	207 x 306 km x 65.4°
	72093	Cosmos-537	25 Nov 1972	T	207 x 324 km x 65.0°
	72099	Cosmos-538	14 Dec 1972	P	212 x 305 km x 65.4°
	72105	Cosmos-541	27 Dec 1972	P	242 x 271 km x 81.4°
	73002	Cosmos-543	08 Jan 1973	T	211 x 333 km x 65.0°
	73006	Cosmos-547	01 Feb 1973	T	208 x 330 km x 65.0°
	73008	Cosmos-548	08 Feb 1973	P	214 x 322 km x 65.4°
	73011	Cosmos-550	01 Mar 1973	P	217 x 325 km x 65.4°
	73012	Cosmos-551	06 Mar 1973	T	210 x 316 km x 65.0°
	73016	Cosmos-552	22 Mar 1973	P	211 x 377 km x 72.9°
	73021	Cosmos-554	19 Apr 1973	P	212 x 318 km x 72.9°
	73024	Cosmos-555	25 Apr 1973	P	216 x 253 km x 81.3°
	73025	Cosmos-556	05 May 1973	P	209 x 252 km x 81.3°
	73030	Cosmos-559	18 May 1973	P	217 x 345 km x 65.4°
	73031	Cosmos-560	23 May 1973	P	211 x 336 km x 72.9°
	73033	Cosmos-561	25 May 1973	P	215 x 317 km x 65.4°
	73036	Cosmos-563	06 Jun 1973	P	213 x 320 km x 65.4°
	73038	Cosmos-572	10 Jun 1973	T	211 x 294 km x 51.8°
	73041	Cosmos-573	15 Jun 1973	T	196 x 329 km x 51.6°
	73043	Cosmos-575	21 Jun 1973	P	208 x 299 km x 65.4°
	73044	Cosmos-576	27 Jun 1973	P	212 x 356 km x 72.9°
	73048	Cosmos-577	25 Jul 1973	P	209 x 312 km x 65.4°
	73051	Cosmos-578	01 Aug 1973	P	207 x 308 km x 65.4°
	73055	Cosmos-579	21 Aug 1973	P	209 x 315 km x 65.4°
	73059	Cosmos-581	24 Aug 1973	T	165 x 272 km x 51.6°
	73062	Cosmos-583	30 Aug 1973	T	200 x 306 km x 65.0°
	73063	Cosmos-584	06 Sep 1973	P	213 x 360 km x 72.9°
	73066	Cosmos-587	21 Sep 1973	P	215 x 330 km x 65.4°
	73067	Soyouz-12	27 Sep 1973	T	326 x 345 km x 51.6°
	73070	Cosmos-596	03 Oct 1973	P	211 x 310 km x 65.4°
	73071	Cosmos-597	06 Oct 1973	P	212 x 312 km x 65.4°
	73072	Cosmos-598	10 Oct 1973	P	213 x 360 km x 72.9°
	73073	Cosmos-599	15 Oct 1973	T	206 x 294 km x 65.0°
	73074	Cosmos-600	16 Oct 1973	P	215 x 366 km x 72.9°
	73077	Cosmos-602	20 Oct 1973	P	213 x 365 km x 72.9°
	73079	Cosmos-603	27 Oct 1973	P	204 x 356 km x 72.9°
	73083	Cosmos 0605	31 Oct 1973	P	221 x 474 km x 62.8°
	73087	Cosmos-607	10 Nov 1973	P	214 x 364 km x 72.9°
	73092	Cosmos-609	21 Nov 1973	T	207 x 370 km x 70.0°
	73095	Cosmos-612	28 Nov 1973	P	206 x 346 km x 72.8°
	73096	Cosmos-613	30 Nov 1973	T	195 x 295 km x 51.6°
	73102	Cosmos-616	17 Dec 1973	P	214 x 355 km x 72.9°
	73103	Soyouz-13	18 Dec 1973	T	225 x 272 km x 51.6°
	73105	Cosmos-625	21 Dec 1973	P	214 x 346 km x 72.8°
	74003	Cosmos-629	24 Jan 1974	P	195 x 304 km x 62.8°
	74004	Cosmos-630	30 Jan 1974	P	213 x 367 km x 72.9°
	74006	Cosmos-632	12 Feb 1974	T	174 x 333 km x 65.0°
	74014	Cosmos-635	14 Mar 1974	P	212 x 350 km x 72.9°
	74016	Cosmos-636	16 Mar 1974	T	164 x 385 km x 65.0°
	74018	§Cosmos-638	03 Apr 1974	T	195 x 325 km x 51.8°
	74019	Cosmos-639	04 Apr 1974	P	209 x 238 km x 81.3°
	74021	Cosmos-640	11 Apr 1974	P	205 x 236 km x 81.3°
	74027	Cosmos-649	29 Apr 1974	P	189 x 320 km x 62.8°
	74030	Cosmos-652	15 May 1974	T	180 x 362 km x 51.8°
	74031	Cosmos-653	15 May 1974	P	196 x 309 km x 62.8°
	74036	Cosmos-656	27 May 1974	T	194 x 354 km x 51.6°
	74038	Cosmos-657	30 May 1974	P	182 x 360 km x 62.8°
	74041	Cosmos-658	06 Jun 1974	T	206 x 304 km x 65.0°
	74043	Cosmos-659	13 Jun 1974	P	190 x 360 km x 62.8°
	74049	Cosmos-664	29 Jun 1974	P	212 x 364 km x 72.9°
	74051	Soyouz-14	03 Jul 1974	T
	74053	Cosmos-666	12 Jul 1974	P	191 x 351 km x 62.8°
	74057	Cosmos-667	25 Jul 1974	T	182 x 343 km x 65.0°
	74059	Cosmos-669	26 Jul 1974	P	210 x 244 km x 81.3°
	74061	Cosmos-670	06 Aug 1974	T	217 x 307 km x 50.6°
	74062	Cosmos-671	07 Aug 1974	P	191 x 369 km x 62.8°
	74064	Cosmos-672	12 Aug 1974	T	191 x 249 km x 51.8°
	74067	Soyouz-15	26 Aug 1974	T
	74068	Cosmos-674	29 Aug 1974	T	182 x 343 km x 65.0°
	74073	Cosmos-685	20 Sep 1974	T	208 x 303 km x 65.0°
	74078	Cosmos-688	18 Oct 1974	P	188 x 371 km x 62.8°
	74080	Cosmos-690	22 Oct 1974	P	233 x 389 km x 62.8°
	74082	Cosmos-691	25 Oct 1974	T	180 x 362 km x 65.0°
	74087	Cosmos-692	03 Nov 1974	P	201 x 315 km x 62.8°
	74088	Cosmos-693	04 Nov 1974	P	215 x 271 km x 81.3°
	74090	Cosmos-694	16 Nov 1974	P	213 x 344 km x 72.9°
	74095	Cosmos-696	27 Nov 1974	P	212 x 345 km x 72.9°
	74096	Soyouz-16	02 Dec 1974	T	177 x 223 km x 51.8°
	74098	Cosmos-697	14 Dec 1974	P	182 x 415 km x 62.8°
	74106	Cosmos-701	27 Dec 1974	P	210 x 339 km x 71.4°
	75001	Soyouz-17	11 Jan 1975	T	LIAISON SALIOUT-4
	75002	Cosmos-702	17 Jan 1975	P	210 x 334 km x 71.4°
	75005	Cosmos-704	23 Jan 1975	P	213 x 329 km x 72.9°
	75013	Cosmos-709	12 Feb 1975	P	188 x 333 km x 62.8°
	75015	Cosmos-710	26 Feb 1975	T	187 x 299 km x 65.0°
	75018	Cosmos-719	12 Mar 1975	T	182 x 329 km x 65.0°
	75019	Cosmos-720	21 Mar 1975	P	223 x 280 km x 62.8°
	75020	Cosmos-721	26 Mar 1975	P	210 x 241 km x 81.3°
	75021	Cosmos-722	27 Mar 1975	P	210 x 359 km x 71.4°
		Soyouz	05 Apr 1975	T	Failure
	75030	Cosmos-727	16 Apr 1975	T	180 x 358 km x 65.0°
	75031	Cosmos-728	18 Apr 1975	P	211 x 350 km x 72.8°
	75035	Cosmos-730	24 Apr 1975	P	212 x 251 km x 81.3°
		Cosmos-727	21 May 1975	T	207 x 313 km x 65.0°
	75044	Soyouz-18	24 May 1975	T
	75046	Cosmos-740	28 May 1975	T	181 x 347 km x 65.0°
	75047	Cosmos-741	30 May 1975	P	210 x 246 km x 81.4°
	75048	Cosmos-742	03 Jun 1975	P	189 x 357 km x 62.8°
	75053	Cosmos-743	12 Jun 1975	P	190 x 355 km x 62.8°
	75059	Cosmos-746	25 Jun 1975	P	188 x 346 km x 62.8°
	75060	Cosmos-747	27 Jun 1975	P	197 x 309 km x 62.8°
	75061	Cosmos-748	03 Jul 1975	P	184 x 339 km x 62.8°
	75065	Soyouz-19	15 Jul 1975	T
	75068	Cosmos-751	23 Jul 1975	P	203 x 235 km x 62.8°
	75073	Cosmos-754	13 Aug 1975	P	210 x 345 km x 71.4°
	75078	Cosmos-757	27 Aug 1975	P	190 x 337 km x 62.8°
	75080	Cosmos-758	06 Sep 1975	P	181 x 370 km x 67.2°
	75084	Cosmos-759	12 Sep 1975	P	234 x 281 km x 62.8°
	75085	Cosmos-760	16 Sep 1975	T	181 x 355 km x 65.0°
	75088	Cosmos-769	23 Sep 1975	P	211 x 331 km x 72.9°
	75090	Cosmos-771	25 Sep 1975	P	219 x 247 km x 81.3°
	75093	Cosmos-772	29 Sep 1975	T	201 x 320 km x 51.8°
	75095	Cosmos-774	01 Oct 1975	P	212 x 333 km x 71.4°
	75101	Cosmos-776	17 Oct 1975	P	203 x 310 km x 62.8°
	75104	Cosmos-779	04 Nov 1975	P	188 x 334 km x 62.8°
	75106	Soyouz-20	17 Nov 1975	T
	75108	Cosmos-780	21 Nov 1975	T	206 x 298 km x 65.0°
	75110	Cosmos 0782	25 Nov 1975	P	227 x 405 km x 62.8°
	75113	Cosmos-784	03 Dec 1975	P	216 x 252 km x 81.3°
	75120	Cosmos-786	16 Dec 1975	T	180 x 347 km x 65.0°
	76002	Cosmos-788	07 Jan 1976	P	191 x 343 km x 62.8°
	76009	Cosmos-799	29 Jan 1976	P	210 x 328 km x 71.4°
	76013	Cosmos-802	11 Feb 1976	T	180 x 355 km x 65.0°
	76018	Cosmos-805	20 Feb 1976	P	182 x 372 km x 67.2°
	76020	Cosmos-806	10 Mar 1976	P	182 x 363 km x 72.4°
	76025	Cosmos-809	19 Mar 1976	T	210 x 322 km x 65.0°
	76028	Cosmos-810	26 Mar 1976	P	188 x 358 km x 62.8°
	76030	Cosmos-811	31 Mar 1976	P	212 x 361 km x 72.9°
	76033	Cosmos-813	09 Apr 1976	P	212 x 250 km x 81.2°
	76036	Cosmos-815	28 Apr 1976	P	218 x 254 km x 81.3°
	76040	Cosmos-817	05 May 1976	T	178 x 347 km x 65.0°
	76045	Cosmos-819	20 May 1976	T	204 x 307 km x 65.0°
	76046	Cosmos-820	21 May 1976	P	214 x 236 km x 81.4°
	76048	Cosmos-821	26 May 1976	P	212 x 338 km x 72.8°
	76052	Cosmos-824	08 Jun 1976	P	209 x 345 km x 71.4°
	76055	Cosmos-833	16 Jun 1976	P	189 x 335 km x 62.8°
	76058	Cosmos-834	24 Jun 1976	P	223 x 263 km x 81.4°
	76060	Cosmos-835	29 Jun 1976	T	180 x 338 km x 65.0°
	76064	Soyouz-21	06 Jul 1976	T
	76068	Cosmos-840	14 Jul 1976	P	212 x 343 km x 72.9°
	76072	Cosmos-844	22 Jul 1976	P	181 x 285 km x 67.1°
	76079	Cosmos-847	04 Aug 1976	P	189 x 342 km x 62.8°
	76082	Cosmos-848	12 Aug 1976	P	214 x 325 km x 62.8°
	76086	Cosmos-852	28 Aug 1976	T	179 x 354 km x 65.0°
	76090	Cosmos-854	03 Sep 1976	P	177 x 337 km x 81.4°
	76093	Soyouz-22	15 Sep 1976	T	250 x 280 km x 65.0°
	76095	Cosmos-855	21 Sep 1976	P	212 x 366 km x 72.9°
	76096	Cosmos-856	22 Sep 1976	P	210 x 322 km x 63.0°
	76097	Cosmos-857	24 Sep 1976	P	185 x 346 km x 62.8°
		Cosmos	04 Oct 1976		Failure
	76099	Cosmos-859	10 Oct 1976	T	180 x 360 km x 65.0°
	76100	Soyouz-23	14 Oct 1976	T
	76106	Cosmos-863	26 Oct 1976	P	187 x 370 km x 62.8°
	76109	Cosmos-865	01 Nov 1976	P	212 x 350 km x 72.9°
	76110	Cosmos-866	11 Nov 1976	T	182 x 306 km x 65.0°
	76111	Cosmos-867	23 Nov 1976	P	258 x 418 km x 62.8°
	76114	Cosmos-869	30 Nov 1976	T	202 x 307 km x 51.8°
	76119	Cosmos-879	09 Dec 1976	P	217 x 241 km x 81.4°
	76123	Cosmos-884	17 Dec 1976	T	178 x 346 km x 65.0°
	77001	Cosmos-888	06 Jan 1977	T	178 x 327 km x 65.0°
	77003	Cosmos-889	20 Jan 1977	P	210 x 353 km x 71.4°
	77008	Soyouz-24	07 Feb 1977	T
	77009	Cosmos-892	09 Feb 1977	P	170 x 454 km x 72.9°
	77016	Cosmos-896	03 Mar 1977	P	194 x 216 km x 72.9°
	77017	Cosmos-897	10 Mar 1977	P	182 x 371 km x 72.9°
	77020	Cosmos-898	17 Mar 1977	P	222 x 258 km x 81.4°
	77026	Cosmos-902	07 Apr 1977	P	179 x 307 km x 81.4°
	77028	Cosmos-904	20 Apr 1977	P	210 x 350 km x 71.4°
	77030	Cosmos-905	26 Apr 1977	P	179 x 366 km x 67.1°
	77033	Cosmos-907	05 May 1977	P	187 x 388 km x 62.8°
	77035	Cosmos-908	17 May 1977	T	180 x 307 km x 51.8°
	77040	Cosmos-912	26 May 1977	P	219 x 257 km x 81.4°
	77043	Cosmos-914	31 May 1977	T	210 x 327 km x 65.0°
	77045	Cosmos-915	08 Jun 1977	P	182 x 306 km x 62.8°
	77046	Cosmos-916	10 Jun 1977	P	250 x 307 km x 62.8°
	77052	Cosmos-920	22 Jun 1977	T	180 x 364 km x 65.0°
	77058	Cosmos-922	30 Jun 1977	P	212 x 323 km x 62.8°
	77063	Cosmos-927	12 Jul 1977	P	178 x 403 km x 72.9°
	77069	Cosmos-932	20 Jul 1977	T	180 x 342 km x 65.0°
	77072	Cosmos-934	27 Jul 1977	P	238 x 264 km x 62.8°
	77073	Cosmos-935	29 Jul 1977	P	225 x 276 km x 81.3°
	77074	Cosmos 0936	03 Aug 1977	P	224 x 419 km x 62.8°
	77078	Cosmos-938	24 Aug 1977	P	189 x 365 km x 62.8°
	77081	Cosmos-947	27 Aug 1977	P	211 x 346 km x 72.8°
	77083	Cosmos-948	02 Sep 1977	P	217 x 265 km x 81.4°
	77085	Cosmos-949	06 Sep 1977	P	184 x 348 km x 62.8°
	77086	Cosmos-950	13 Sep 1977	P	213 x 305 km x 62.8°
	77089	Cosmos-953	16 Sep 1977	P	188 x 354 km x 62.8°
	77098	Cosmos-957	30 Sep 1977	T	181 x 381 km x 65.0°
	77099	Soyouz-25	09 Oct 1977	T
	77100	Cosmos-958	11 Oct 1977	P	265 x 369 km x 62.8°
	77110	Cosmos-964	04 Dec 1977	P	180 x 391 km x 72.9°
	77113	Soyouz-26	10 Dec 1977	T
	77115	Cosmos-966	12 Dec 1977	T	210 x 316 km x 65.0°
	77120	Cosmos-969	20 Dec 1977	P	188 x 340 km x 62.8°
	77124	Cosmos-973	27 Dec 1977	P	210 x 348 km x 71.4°
	78001	Cosmos-974	06 Jan 1978	P	188 x 356 km x 62.8°
	78003	Soyouz-27	10 Jan 1978	T
	78006	Cosmos-984	13 Jan 1978	P	215 x 313 km x 62.8°
	78008	Progress-1	20 Jan 1978	T
	78010	Cosmos-986	24 Jan 1978	T	179 x 341 km x 65.0°
	78013	Cosmos-987	31 Jan 1978	P	175 x 321 km x 62.8°
	78015	Cosmos-988	08 Feb 1978	P	210 x 363 km x 72.8°
	78017	Cosmos-989	14 Feb 1978	T	178 x 354 km x 65.0°
	78023	Soyouz-28	02 Mar 1978	T
	78025	Cosmos-992	04 Mar 1978	P	210 x 346 km x 71.4°
	78027	Cosmos-993	10 Mar 1978	P	182 x 368 km x 72.9°
	78030	Cosmos-995	17 Mar 1978	P	221 x 262 km x 81.4°
	78033	Cosmos-999	30 Mar 1978	P	180 x 376 km x 71.4°
	78036	Cosmos-1001	04 Apr 1978	T	200 x 300 km x 51.6°
	78037	Cosmos-1002	06 Apr 1978	T	209 x 305 km x 65.0°
	78040	Cosmos-1003	20 Apr 1978	P	185 x 349 km x 62.8°
	78043	Cosmos-1004	05 May 1978	P	213 x 311 km x 62.8°
	78048	Cosmos-1007	16 May 1978	P	180 x 384 km x 72.9°
	78052	Cosmos-1010	23 May 1978	P	218 x 257 km x 81.4°
	78054	Cosmos-1012	25 May 1978	P	214 x 280 km x 62.8°
	78057	Cosmos-1021	10 Jun 1978	T	180 x 336 km x 65.0°
	78059	Cosmos-1022	12 Jun 1978	P	182 x 374 km x 72.9°
	78061	Soyouz-29	15 Jun 1978	T
	78065	Soyouz-30	27 Jun 1978	T
	78069	Cosmos-1026	02 Jul 1978	T	209 x 261 km x 51.8°
	78070	Progress-2	07 Jul 1978	T
	78076	Cosmos-1028	05 Aug 1978	P	182 x 272 km x 67.1°
	78077	Progress-3	07 Aug 1978	T
	78081	Soyouz-31	26 Aug 1978	T
	78082	Cosmos-1029	29 Aug 1978	P	186 x 353 km x 62.8°
	78085	Cosmos-1031	09 Sep 1978	P	191 x 351 km x 62.8°
	78088	Cosmos-1032	19 Sep 1978	P	218 x 249 km x 81.4°
	78089	Cosmos-1033	03 Oct 1978	P	223 x 268 km x 81.4°
	78090	Progress-4	03 Oct 1978	T
	78092	Cosmos-1042	06 Oct 1978	P	187 x 326 km x 62.8°
	78097	Cosmos-1044	20 Oct 1978	P	211 x 315 km x 62.8°
	78102	Cosmos-1046	01 Nov 1978	P	212 x 353 km x 72.9°
	78104	Cosmos-1047	15 Nov 1978	P	182 x 378 km x 72.9°
	78107	Cosmos-1049	21 Nov 1978	P	183 x 375 km x 72.9°
	78108	Cosmos-1050	28 Nov 1978	P	258 x 398 km x 62.8°
	78110	Cosmos-1059	07 Dec 1978	P	188 x 360 km x 62.8°
	78111	Cosmos-1060	08 Dec 1978	T	209 x 311 km x 65.0°
	78114	Cosmos-1061	14 Dec 1978	P	211 x 233 km x 62.8°
	78123	Cosmos-1068	26 Dec 1978	P	187 x 408 km x 62.8°
	78124	Cosmos-1069	28 Dec 1978	P	244 x 290 km x 62.8°
	79001	Cosmos-1070	11 Jan 1979	P	214 x 316 km x 62.8°
	79002	Cosmos-1071	13 Jan 1979	P	190 x 360 km x 62.8°
	79006	Cosmos-1073	30 Jan 1979	P	187 x 350 km x 62.8°
	79008	Cosmos-1074	31 Jan 1979	T	203 x 258 km x 51.6°
	79016	Cosmos-1078	23 Feb 1979	P	180 x 306 km x 72.9°
	79018	Soyouz-32	25 Feb 1979	T
	79019	Cosmos-1079	27 Feb 1979	P	179 x 359 km x 67.1°
	79022	Progress-5	12 Mar 1979	T
	79023	Cosmos-1080	14 Mar 1979	P	180 x 320 km x 72.9°
	79027	Cosmos-1090	31 Mar 1979	P	212 x 354 km x 72.9°
	79029	Soyouz-33	10 Apr 1979	T
	79034	Cosmos-1095	20 Apr 1979	P	209 x 404 km x 72.9°
	79037	Cosmos-1097	28 Apr 1979	P	180 x 357 km x 62.8°
	79039	Progress-6	13 May 1979	T
	79040	Cosmos-1098	15 May 1979	P	130 x 382 km x 72.9°
	79041	Cosmos-1099	17 May 1979	P	224 x 275 km x 81.4°
	79043	Cosmos-1102	25 May 1979	P	222 x 288 km x 81.4°
	79045	Cosmos-1103	31 May 1979	P	264 x 396 km x 62.8°
	79049	Soyouz-34	06 Jun 1979	T
	79052	Cosmos-1105	08 Jun 1979	P	223 x 281 km x 81.4°
	79054	Cosmos-1106	12 Jun 1979	P	222 x 264 km x 81.4°
	79055	Cosmos-1107	14 Jun 1979	P	209 x 328 km x 72.9°
	79056	Cosmos-1108	22 Jun 1979	P	224 x 272 km x 81.3°
	79059	Progress-7	28 Jun 1979	T
	79061	Cosmos-1111	29 Jun 1979	P	264 x 353 km x 63.0°
	79064	Cosmos-1113	10 Jul 1979	T	180 x 350 km x 65.0°
	79066	Cosmos-1115	13 Jul 1979	P	222 x 263 km x 81.4°
	79068	Cosmos-1117	25 Jul 1979	P	187 x 349 km x 62.8°
	79069	Cosmos-1118	27 Jul 1979	P	222 x 273 km x 81.4°
	79071	Cosmos-1119	03 Aug 1979	P	222 x 267 km x 81.3°
	79073	Cosmos-1120	11 Aug 1979	T	181 x 376 km x 70.4°
	79074	Cosmos-1121	15 Aug 1979	P	180 x 375 km x 67.2°
	79075	Cosmos-1122	17 Aug 1979	P	218 x 260 km x 81.4°
	79076	Cosmos-1123	21 Aug 1979	P	221 x 266 km x 81.4°
	79079	Cosmos-1126	31 Aug 1979	P	208 x 421 km x 72.9°
	79080	Cosmos-1127	05 Sep 1979	P	226 x 300 km x 81.4°
	79081	Cosmos-1128	14 Sep 1979	P	184 x 352 km x 62.8°
	79083	Cosmos-1129	25 Sep 1979	P	226 x 406 km x 62.8°
	79085	Cosmos-1138	28 Sep 1979	P	210 x 398 km x 72.9°
	79088	Cosmos-1139	05 Oct 1979	P	212 x 357 km x 72.9°
		Cosmos	12 Oct 1979		Failure
	79092	Cosmos-1142	22 Oct 1979	P	208 x 408 km x 72.9°
	79097	Cosmos-1144	02 Nov 1979	P	179 x 378 km x 67.2°
	79102	Cosmos-1147	12 Dec 1979	P	207 x 407 km x 72.9°
	79103	Soyouz-T1	16 Dec 1979	T
	79106	Cosmos-1148	28 Dec 1979	P	180 x 367 km x 67.1°
	80001	Cosmos-1149	09 Jan 1980	P	208 x 414 km x 72.9°
	80006	Cosmos-1152	24 Jan 1980	P	181 x 370 km x 67.1°
	80009	Cosmos-1155	07 Feb 1980	P	206 x 422 km x 72.9°
	80017	Cosmos-1165	21 Feb 1980	P	188 x 379 km x 72.9°
	80020	Cosmos-1166	04 Mar 1980	P	208 x 406 km x 72.9°
	80024	Progress-8	28 Mar 1980	T
	80025	Cosmos-1170	01 Apr 1980	T	181 x 386 km x 70.4°
	80027	Soyouz-35	09 Apr 1980	T
	80029	Cosmos-1173	17 Apr 1980	T	379 x 180 km x 70.3°
	80033	Progress-9	27 Apr 1980	T
	80035	Cosmos-1177	29 Apr 1980	P	181 x 365 km x 67.2°
	80036	Cosmos-1178	07 May 1980	P	207 x 417 km x 72.9°
	80038	Cosmos-1180	15 May 1980	P	240 x 296 km x 62.8°
	80040	Cosmos-1182	23 May 1980	P	221 x 278 km x 82.3°
	80041	Soyouz-36	26 May 1980	T
	80042	Cosmos-1183	28 May 1980	P	208 x 414 km x 72.9°
	80045	Soyouz-T2	05 Jun 1980	T
	80046	Cosmos-1185	06 Jun 1980	P	226 x 308 km x 82.3°
	80048	Cosmos-1187	12 Jun 1980	P	210 x 332 km x 72.9°
	80054	Cosmos-1189	26 Jun 1980	P	209 x 330 km x 72.9°
	80055	Progress-10	29 Jun 1980	T
	80059	Cosmos-1200	09 Jul 1980	P	209 x 304 km x 72.9°
	80061	Cosmos-1201	15 Jul 1980	P	220 x 274 km x 82.3°
	80064	Soyouz-37	23 Jul 1980	T
	80065	Cosmos-1202	24 Jul 1980	P	209 x 333 km x 72.9°
	80066	Cosmos-1203	31 Jul 1980	P	227 x 303 km x 82.3°
	80068	Cosmos-1205	12 Aug 1980	P	208 x 332 km x 72.8°
	80070	Cosmos-1207	22 Aug 1980	P	218 x 282 km x 82.3°
	80071	Cosmos-1208	26 Aug 1980	P	181 x 362 km x 67.1°
	80072	Cosmos-1209	03 Sep 1980	P	222 x 306 km x 82.3°
	80075	Soyouz-38	18 Sep 1980	T
	80076	Cosmos-1210	19 Sep 1980	P	195 x 268 km x 82.3°
	80077	Cosmos-1211	23 Sep 1980	P	215 x 261 km x 82.4°
	80078	Cosmos-1212	26 Sep 1980	P	216 x 275 km x 82.3°
	80079	Progress-11	28 Aug 1980	T
	80080	Cosmos-1213	03 Oct 1980	P	207 x 343 km x 72.8°
	80082	Cosmos-1214	10 Oct 1980	P	181 x 368 km x 67.2°
	80084	Cosmos-1216	16 Oct 1980	P	209 x 404 km x 72.9°
	80086	Cosmos-1218	30 Oct 1980	T	178 x 374 km x 64.9°
	80088	Cosmos-1219	31 Oct 1980	P	205 x 353 km x 72.9°
	80090	Cosmos-1221	12 Nov 1980	P	207 x 424 km x 72.9°
	80094	Soyouz-T#3	27 Nov 1980	T
	80096	Cosmos-1224	01 Dec 1980	P	209 x 403 km x 72.9°
	80101	Cosmos-1227	16 Dec 1980	P	209 x 325 km x 72.9°
	80105	Cosmos-1236	26 Dec 1980	P	180 x 338 km x 67.1°
	81001	Cosmos-1237	06 Jan 1981	P	207 x 410 km x 72.9°
	81004	Cosmos-1239	16 Jan 1981	P	222 x 265 km x 82.3°
	81005	Cosmos-1240	20 Jan 1981	T	178 x 377 km x 64.9°
	81007	Progress-12	24 Jan 1981	T
	81014	Cosmos-1245	13 Feb 1981	P	208 x 403 km x 72.9°
	81015	Cosmos-1246	18 Feb 1981	T	202 x 292 km x 64.9°
	81020	Cosmos-1248	05 Mar 1981	P	180 x 371 km x 67.1°
	81023	Soyouz-T4	12 Mar 1981	T
	81026	Cosmos-1259	17 Mar 1981	T	215 x 405 km x 70.4°
	81029	Soyouz-39	22 Mar 1981	T
	81032	Cosmos-1262	07 Apr 1981	P	207 x 418 km x 72.9°
	81035	Cosmos-1264	15 Apr 1981	T	216 x 411 km x 70.4°
	81036	Cosmos-1265	16 Apr 1981	P	210 x 317 km x 72.9°
	81040	Cosmos-1268	28 Apr 1981	T	217 x 391 km x 70.4°
	81042	Soyouz-40	14 May 1981	T
	81045	Cosmos-1270	18 May 1981	T	180 x 370 km x 64.9°
	81047	Cosmos-1272	21 May 1981	T	217 x 403 km x 70.4°
	81048	Cosmos-1273	22 May 1981	P	221 x 277 km x 82.3°
	81052	Cosmos-1274	03 Jun 1981	P	183 x 380 km x 67.2°
	81055	Cosmos-1276	16 Jun 1981	P	224 x 265 km x 82.3°
	81056	Cosmos-1277	17 Jun 1981	T	216 x 393 km x 70.4°
	81062	Cosmos-1279	01 Jul 1981	T	218 x 385 km x 70.4°
	81063	Cosmos-1280	02 Jul 1981	P	222 x 312 km x 82.3°
	81064	Cosmos-1281	08 Jul 1981	P	208 x 419 km x 72.8°
	81066	Cosmos-1282	15 Jul 1981	T	179 x 357 km x 64.9°
	81067	Cosmos-1283	17 Jul 1981	P	184 x 278 km x 82.3°
	81068	Cosmos-1284	29 Jul 1981	P	195 x 270 km x 82.3°
	81078	Cosmos-1296	12 Aug 1981	P	181 x 377 km x 67.2°
	81079	Cosmos-1297	18 Aug 1981	P	209 x 389 km x 72.9°
	81080	Cosmos-1298	21 Aug 1981	T	179 x 351 km x 64.9°
	81083	Cosmos-1301	27 Aug 1981	P	224 x 300 km x 82.3°
	81086	Cosmos-1303	04 Sep 1981	T	216 x 398 km x 70.4°
	81090	Cosmos-1307	15 Sep 1981	P	209 x 419 km x 72.9°
	81092	Cosmos-1309	18 Sep 1981	P	225 x 282 km x 82.3°
	81099	Cosmos-1313	01 Oct 1981	T	214 x 314 km x 70.4°
	81101	Cosmos-1314	09 Oct 1981	P	220 x 263 km x 82.3°
	81104	Cosmos-1316	15 Oct 1981	T	215 x 407 km x 70.3°
	81109	Cosmos-1318	03 Nov 1981	P	183 x 379 km x 67.2°
	81112	Cosmos-1319	13 Nov 1981	T	216 x 400 km x 70.4°
	81118	Cosmos-1329	04 Dec 1981	T	237 x 283 km x 65.0°
	81121	Cosmos-1330	19 Dec 1981	T	177 x 403 km x 70.4°
	82002	Cosmos-1332	12 Jan 1982	P	218 x 275 km x 82.3°
	82005	Cosmos-1334	20 Jan 1982	P	206 x 315 km x 72.9°
	82008	Cosmos-1336	29 Jan 1982	T	179 x 379 km x 70.4°
	82011	Cosmos-1338	16 Feb 1982	P	208 x 393 km x 72.0°
	82018	Cosmos-1342	05 Mar 1982	P	207 x 326 km x 72.9°
	82021	Cosmos-1343	17 Mar 1982	P	208 x 314 km x 72.9°
	82028	Cosmos-1347	02 Apr 1982	T	181 x 364 km x 70.4°
	82032	Cosmos-1350	15 Apr 1982	P	187 x 380 km x 67.2°
	82035	Cosmos-1352	21 Apr 1982	T	216 x 382 km x 70.4°
	82036	Cosmos-1353	23 Apr 1982	P	218 x 269 km x 82.3°
	82042	Soyouz-T5	13 May 1982	T
		Cosmos	15 May 1982		Failure
	82046	Cosmos-1368	21 May 1982	T	218 x 365 km x 70.4°
	82047	Progress-13	23 May 1982	T
	82048	Cosmos-1369	25 May 1982	P	229 x 296 km x 82.3°
	82049	Cosmos-1370	28 May 1982	T	203 x 290 km x 64.9°
	82053	Cosmos-1373	01 Jun 1982	T	217 x 368 km x 70.4°
	82056	Cosmos-1376	08 Jun 1982	P	227 x 274 km x 82.3°
	82057	Cosmos-1377	08 Jun 1982	T	179 x 362 km x 64.9°
		Cosmos	12 Jun 1982		Failure
	82062	Cosmos-1381	18 Jun 1982	T	216 x 395 km x 70.4°
	82063	Soyouz-T6	24 Jun 1982	T
	82067	Cosmos-1384	30 Jun 1982	P	181 x 381 km x 67.1°
	82068	Cosmos-1385	06 Jul 1982	P	197 x 264 km x 82.3°
	82070	Progress-14	10 Jul 1982	T
	82071	Cosmos-1387	13 Jul 1982	P	219 x 271 km x 82.3°
	82075	Cosmos-1396	27 Jul 1982	P	208 x 323 km x 72.9°
	82077	Cosmos-1398	03 Aug 1982	P	225 x 262 km x 82.3°
	82078	Cosmos-1399	04 Aug 1982	T	179 x 371 km x 64.9°
	82080	Soyouz-T7	19 Aug 1982	T
	82081	Cosmos-1401	20 Aug 1982	P	226 x 282 km x 82.3°
	82085	Cosmos-1403	01 Sep 1982	T	216 x 380 km x 70.4°
	82086	Cosmos-1404	01 Sep 1982	P	211 x 394 km x 72.9°
	82089	Cosmos-1406	08 Sep 1982	P	222 x 253 km x 82.3°
	82091	Cosmos-1407	15 Sep 1982	P	181 x 364 km x 67.2°
	82094	Progress-15	18 Sep 1982	T
	82098	Cosmos-1411	30 Sep 1982	P	208 x 384 km x 72.9°
	82101	Cosmos-1416	15 Oct 1982	T	217 x 380 km x 70.4°
	82107	Progress-16	31 Oct 1982	T
	82108	Cosmos-1419	02 Nov 1982	T	216 x 290 km x 70.4°
	82112	Cosmos-1421	18 Nov 1982	T	216 x 286 km x 70.4°
	82114	Cosmos-1422	03 Dec 1982	P	208 x 314 km x 73.0°
	82117	Cosmos-1424	16 Dec 1982	T	179 x 371 km x 64.9°
	82119	Cosmos-1425	23 Dec 1982	T	237 x 374 km x 70.0°
	82120	Cosmos-1426	28 Dec 1982	T	209 x 377 km x 50.6°
	83005	Cosmos-1438	27 Jan 1983	T	213 x 254 km x 70.4°
	83007	Cosmos-1439	06 Feb 1983	T	180 x 371 km x 70.4°
	83009	Cosmos-1440	10 Feb 1983	P	223 x 293 km x 82.3°
	83012	Cosmos-1442	25 Feb 1983	P	180 x 364 km x 67.2°
	83014	Cosmos-1444	02 Mar 1983	P	203 x 413 km x 72.9°
	83018	Cosmos-1446	16 Mar 1983	T	237 x 368 km x 70.0°
	83024	Cosmos-1449	31 Mar 1983	P	207 x 402 km x 72.9°
	83029	Cosmos-1451	08 Apr 1983	P	194 x 264 km x 82.3°
	83035	Soyouz-T8	19 Apr 1983	T
	83036	Cosmos-1454	22 Apr 1983	P	181 x 374 km x 67.2°
	83039	Cosmos-1457	26 Apr 1983	T	180 x 376 km x 70.4°
	83040	Cosmos-1458	28 Apr 1983	P	220 x 275 km x 82.3°
	83043	Cosmos-1460	06 May 1983	T	218 x 369 km x 70.3°
	83045	Cosmos-1462	17 May 1983	P	224 x 318 km x 82.3°
	83050	Cosmos-1466	26 May 1983	T	180 x 367 km x 64.9°
	83052	Cosmos-1467	31 May 1983	P	209 x 389 km x 72.9°
	83055	Cosmos-1468	07 Jun 1983	P	227 x 283 km x 82.3°
	83057	Cosmos-1469	14 Jun 1983	P	211 x 377 km x 72.8°
	83062	Soyouz-T9	27 Jun 1983	T
	83064	Cosmos-1471	28 Jun 1983	P	182 x 369 km x 67.2°
	83068	Cosmos-1472	05 Jul 1983	P	197 x 264 km x 82.4°
	83071	Cosmos-1482	13 Jul 1983	T	217 x 376 km x 70.0°
	83074	Cosmos-1483	20 Jul 1983	P	227 x 305 km x 82.3°
	83076	Cosmos-1485	26 Jul 1983	P	209 x 395 km x 72.9°
	83080	Cosmos-1487	05 Aug 1983	P	226 x 305 km x 82.3°
	83082	Cosmos-1488	09 Aug 1983	P	208 x 397 km x 72.8°
	83083	Cosmos-1489	10 Aug 1983	T	182 x 323 km x 64.7°
	83085	Progress-17	17 Aug 1983	T
	83087	Cosmos-1493	23 Aug 1983	P	207 x 396 km x 72.9°
	83092	Cosmos-1495	02 Sep 1983	P	211 x 248 km x 82.3°
	83093	Cosmos-1496	07 Sep 1983	P	182 x 362 km x 67.2°
	83095	Cosmos-1497	09 Sep 1983	P	208 x 403 km x 72.8°
	83096	Cosmos-1498	14 Sep 1983	P	222 x 305 km x 82.3°
	83097	Cosmos-1499	17 Sep 1983	P	208 x 396 km x 72.9°
	83104	Cosmos-1504	14 Oct 1983	T	180 x 323 km x 64.9°
	83106	Progress-18	20 Oct 1983	T
	83107	Cosmos-1505	21 Oct 1983	P	210 x 377 km x 72.9°
	83112	Cosmos-1509	17 Nov 1983	P	209 x 309 km x 72.9°
	83117	Cosmos-1511	30 Nov 1983	P	181 x 368 km x 67.2°
	83119	Cosmos-1512	07 Dec 1983	P	208 x 392 km x 72.9°
	83121	Cosmos-1514	14 Dec 1983	P	226 x 288 km x 82.3°
	83124	Cosmos-1516	27 Dec 1983	T	205 x 299 km x 65.0°
	84002	Cosmos-1530	11 Jan 1984	P	206 x 391 km x 72.8°
	84004	Cosmos-1532	13 Jan 1984	P	178 x 382 km x 67.2°
	84006	Cosmos-1533	26 Jan 1984	T	235 x 382 km x 70.4°
	84014	Soyouz T-10	08 Feb 1984	T
	84017	Cosmos-1537	16 Feb 1984	P	220 x 317 km x 82.4°
	84018	Progress-19	21 Feb 1984	T
	84020	Cosmos-1539	28 Feb 1984	P	179 x 367 km x 67.1°
	84025	Cosmos-1542	07 Mar 1984	T	236 x 373 km x 70.4°
	84026	Cosmos-1543	10 Mar 1984	P	224 x 416 km x 62.8°
	84030	Cosmos-1545	21 Mar 1984	P	208 x 396 km x 72.9°
		Cosmos	26 Mar 1984		Failure
	84032	Soyouz-T11	03 Apr 1984	T
	84036	Cosmos-1548	10 Apr 1984	P	177 x 359 km x 67.1°
	84038	Progress-20	15 Apr 1984	T
	84040	Cosmos-1549	19 Apr 1984	P	208 x 394 km x 72.9°
	84042	Progress-21	07 May 1984	T
	84044	Cosmos-1551	11 May 1984	P	209 x 305 km x 72.9°
	84045	Cosmos-1552	14 May 1984	T	191 x 344 km x 64.9°
	84048	Cosmos-1557	22 May 1984	P	221 x 276 km x 82.3°
	84050	Cosmos-1558	25 May 1984	P	178 x 318 km x 67.2°
	84051	Progress-22	28 May 1984	T
	84054	Cosmos-1568	01 Jun 1984	P	209 x 396 km x 72.8°
	84058	Cosmos-1571	11 Jun 1984	T	218 x 398 km x 70.0°
	84060	Cosmos-1572	15 Jun 1984	P	227 x 297 km x 82.4°
	84061	Cosmos-1573	19 Jun 1984	P	209 x 317 km x 72.9°
	84064	Cosmos-1575	22 Jun 1984	P	231 x 292 km x 82.3°
	84066	Cosmos-1576	26 Jun 1984	P	180 x 376 km x 67.1°
	84070	Cosmos-1580	30 Jun 1984	P	249 x 367 km x 62.8°
	84073	Soyouz-T12	17 Jul 1984	T
	84074	Cosmos-1582	19 Jul 1984	P	227 x 308 km x 82.4°
	84075	Cosmos-1583	24 Jul 1984	P	209 x 388 km x 72.9°
	84076	Cosmos-1584	27 Jul 1984	P	193 x 268 km x 82.4°
	84077	Cosmos-1585	31 Jul 1984	T	181 x 324 km x 64.8°
	84082	Cosmos-1587	06 Aug 1984	P	209 x 394 km x 72.9°
	84086	Progress-23	14 Aug 1984	T
	84087	Cosmos-1590	16 Aug 1984	P	221 x 293 km x 82.4°
	84092	Cosmos-1591	30 Aug 1984	P	220 x 300 km x 82.3°
	84094	Cosmos-1592	04 Sep 1984	P	209 x 380 km x 72.9°
	84099	Cosmos-1597	13 Sep 1984	P	219 x 272 km x 82.3°
	84102	Cosmos-1599	25 Sep 1984	P	179 x 275 km x 67.2°
	84103	Cosmos-1600	27 Sep 1984	T	215 x 404 km x 70.0°
	84116	Cosmos-1608	14 Nov 1984	T	195 x 248 km x 70.0°
	84117	Cosmos-1609	14 Nov 1984	P	208 x 385 km x 73.0°
	84119	Cosmos-1611	21 Nov 1984	T	181 x 326 km x 64.8°
	84121	Cosmos-1613	29 Nov 1984	P	209 x 382 km x 72.8°
	85002	Cosmos-1616	09 Jan 1985	T	180 x 381 km x 64.9°
	85005	Cosmos-1623	16 Jan 1985	T	216 x 405 km x 70.0°
	85012	Cosmos-1628	06 Feb 1985	P	206 x 407 km x 72.8°
	85017	Cosmos-1630	27 Feb 1985	T	182 x 357 km x 64.9°
	85019	Cosmos-1632	01 Mar 1985	P	203 x 261 km x 72.9°
	85026	Cosmos-1643	25 Mar 1985	T	190 x 300 km x 64.8°
	85027	Cosmos-1644	03 Apr 1985	T	217 x 398 km x 70.4°
	85029	Cosmos-1645	16 Apr 1985	P	223 x 411 km x 62.8°
	85031	Cosmos-1647	19 Apr 1985	P	180 x 348 km x 67.1°
	85032	Cosmos-1648	25 Apr 1985	P	196 x 265 km x 82.3°
	85036	Cosmos-1649	15 May 1985	P	208 x 396 km x 72.9°
	85038	Cosmos-1653	22 May 1985	P	222 x 322 km x 82.3°
	85039	Cosmos-1654	23 May 1985	T	180 x 365 km x 64.0°
	85043	Soyouz-T.13	06 Jun 1985	T
	85044	Cosmos-1657	07 Jun 1985	P	195 x 313 km x 82.3°
	85046	Cosmos-1659	13 Jun 1985	P	210 x 379 km x 72.9°
	85051	Progress-24	21 Jun 1985	T
	85052	Cosmos-1663	21 Jun 1985	P	227 x 298 km x 82.3°
	85054	Cosmos-1664	26 Jun 1985	P	207 x 405 km x 72.9°
	85057	Cosmos-1665	03 Jul 1985	P	208 x 316 km x 72.9°
	85059	Cosmos-1667	10 Jul 1985	P	222 x 297 km x 82.3°
	85060	Cosmos-1668	15 Jul 1985	T	216 x 297 km x 70.4°
	85062	Cosmos-1669	19 Jul 1985	T
	85065	Cosmos-1671	02 Aug 1985	P	210 x 310 km x 72.8°
	85067	Cosmos-1672	07 Aug 1985	P	199 x 290 km x 82.3°
	85068	Cosmos-1673	08 Aug 1985	T	204 x 294 km x 64.8°
	85072	Cosmos-1676	16 Aug 1985	P	178 x 371 km x 67.2°
	85077	Cosmos-1678	29 Aug 1985	P	196 x 311 km x 82.3°
	85078	Cosmos-1679	29 Aug 1985	T	182 x 364 km x 64.9°
	85080	Cosmos-1681	06 Sep 1985	P	216 x 261 km x 82.4°
	85081	Soyouz-T14	17 Sep 1985	T
	85083	Cosmos-1683	19 Sep 1985	P	208 x 399 km x 72.5°
	85085	Cosmos-1685	26 Sep 1985	P	209 x 379 km x 72.9°
	85095	Cosmos-1696	16 Oct 1985	T	230 x 281 km x 70.4°
	85101	Cosmos-1699	25 Oct 1985	P	168 x 338 km x 67.1°
	85106	Cosmos-1702	13 Nov 1985	P	207 x 399 km x 72.8°
	85111	Cosmos-1705	03 Dec 1985	P	208 x 387 km x 72.8°
	85112	Cosmos-1706	11 Dec 1985	P	178 x 360 km x 67.2°
	85115	Cosmos-1708	13 Dec 1985	P	197 x 313 km x 82.3°
	85120	Cosmos-1713	27 Dec 1985	P	224 x 419 km x 62.8°
	86001	Cosmos-1715	08 Jan 1986	P	207 x 317 km x 72.8°
	86004	Cosmos-1724	15 Jan 1986	P	179 x 358 km x 67.2°
	86009	Cosmos-1728	28 Jan 1986	T	214 x 305 km x 70.0°
	86012	Cosmos-1730	04 Feb 1986	P	194 x 300 km x 72.9°
	86013	Cosmos-1731	07 Feb 1986	T	232 x 312 km x 64.7°
	86020	Cosmos-1734	26 Feb 1986	P	167 x 345 km x 67.1°
	86022	Soyouz-T15	13 Mar 1986	T
	86023	Progress-25	19 Mar 1986	T
	86028	Cosmos-1739	09 Apr 1986	T	182 x 352 km x 64.9°
	86029	Cosmos-1740	15 Apr 1986	P	208 x 396 km x 72.9°
	86032	Progress-26	23 Apr 1986	T
	86033	Cosmos-1742	14 May 1986	P	209 x 388 km x 73.0°
	86035	Soyouz-TM1	21 May 1986	T
	86036	Cosmos-1744	21 May 1986	P	227 x 395 km x 62.8°
	86040	Cosmos-1746	28 May 1986	P	195 x 308 km x 82.3°
	86041	Cosmos-1747	29 May 1986	T	217 x 420 km x 70.4°
	86043	Cosmos-1756	06 Jun 1986	T	173 x 343 km x 64.9°
	86045	Cosmos-1757	11 Jun 1986	P	189 x 252 km x 82.3°
	86048	Cosmos-1760	19 Jun 1986	T	218 x 421 km x 70.0°
	86051	Cosmos-1762	10 Jul 1986	P	196 x 304 km x 82.6°
	86053	Cosmos-1764	17 Jul 1986	T	182 x 368 km x 64.9°
	86054	Cosmos-1765	24 Jul 1986	P	207 x 395 km x 72.9°
	86058	Cosmos-1768	02 Aug 1986	P	199 x 303 km x 82.6°
	86060	Cosmos-1770	06 Aug 1986	T	189 x 302 km x 64.8°
	86063	Cosmos-1772	21 Aug 1986	P	210 x 370 km x 72.9°
	86064	Cosmos-1773	27 Aug 1986	T	180 x 365 km x 64.9°
	86066	Cosmos-1775	03 Sep 1986	T	216 x 405 km x 70.3°
	86072	Cosmos-1781	17 Sep 1986	T	346 x 416 km x 70.4°
	86077	Cosmos-1784	06 Oct 1986	T	211 x 281 km x 64.7°
	86081	Cosmos-1787	22 Oct 1986	T	230 x 281 km x 70.0°
	86084	Cosmos-1789	31 Oct 1986	P	196 x 316 km x 82.6°
	86085	Cosmos-1790	04 Nov 1986	P	207 x 315 km x 72.9°
	86087	Cosmos-1792	13 Nov 1986	T	181 x 357 km x 64.9°
	86095	Cosmos-1804	04 Dec 1986	T	210 x 448 km x 70.0°
	86099	Cosmos-1807	16 Dec 1986	P	177 x 370 km x 67.0°
	86102	Cosmos-1810	26 Dec 1986	T	189 x 302 km x 65.0°
	87002	Cosmos-1811	09 Jan 1987	T	200 x 286 km x 64.6°
	87004	Cosmos-1813	15 Jan 1987	P	208 x 387 km x 72.8°
	87005	Progress-27	16 Jan 1987	T
	87013	Soyouz-TM2	05 Feb 1987	T
	87014	Cosmos-1819	07 Feb 1987	P	197 x 254 km x 72.8°
	87019	Cosmos-1822	19 Feb 1987	P	205 x 331 km x 73.0°
	87021	Cosmos-1824	26 Feb 1987	P	177 x 370 km x 67.2°
	87023	Progress-28	03 Mar 1987	T
	87025	Cosmos-1826	11 Mar 1987	P	206 x 403 km x 72.9°
	87032	Cosmos-1835	09 Apr 1987	T	172 x 344 km x 65.0°
	87033	Cosmos-1836	16 Apr 1987	T	241 x 293 km x 64.8°
	87034	Progress-29	21 Apr 1987	T
	87035	Cosmos-1837	22 Apr 1987	P	226 x 247 km x 82.3°
	87037	Cosmos-1841	24 Apr 1987	P	218 x 381 km x 62.8°
	87039	Cosmos-1843	05 May 1987	T	205 x 287 km x 70.3°
	87042	Cosmos-1845	13 May 1987	T	217 x 400 km x 70.0°
	87044	Progress-30	19 May 1987	T
	87045	Cosmos-1846	21 May 1987	P	196 x 314 km x 82.4°
	87046	Cosmos-1847	26 May 1987	P	169 x 346 km x 67.1°
	87047	Cosmos-1848	28 May 1987	P	208 x 400 km x 72.9°
	87056	Cosmos-1863	04 Jul 1987	P	208 x 383 km x 72.9°
	87058	Cosmos-1865	08 Jul 1987	T	204 x 327 km x 64.8°
	87059	Cosmos-1866	09 Jul 1987	P	177 x 386 km x 67.0°
	87063	Soyouz-TM3	22 Jul 1987	T
	87066	Progress-31	03 Aug 1987	T
	87069	Cosmos-1872	19 Aug 1987	P	208 x 333 km x 72.9°
	87072	Cosmos-1874	03 Sep 1987	P	225 x 291 km x 73.0°
	87076	Cosmos-1881	11 Sep 1987	T	190 x 297 km x 64.8°
	87077	Cosmos-1882	15 Sep 1987	P	196 x 253 km x 82.3°
	87081	Cosmos-1886	17 Sep 1987	P	178 x 384 km x 67.2°
	87082	Progress-32	24 Sep 1987	T
	87083	Cosmos 1887	29 Sep 1987	P	244 x 406 km x 62.8°
	87085	Cosmos-1889	09 Oct 1987	T	216 x 400 km x 70.0°
	87089	Cosmos-1893	22 Oct 1987	P	179 x 374 km x 67.0°
	87092	Cosmos-1895	11 Nov 1987	T	210 x 380 km x 70.4°
	87093	Cosmos-1896	14 Nov 1987	T	210 x 270 km x 64.8°
	87094	Progress-33	20 Nov 1987	T
	87099	Cosmos-1899	07 Dec 1987	T	206 x 272 km x 70.4°
	87102	Cosmos-1901	14 Dec 1987	T	181 x 376 km x 65.0°
	87104	Soyouz-TM4	21 Dec 1987	T
	87107	Cosmos-1905	25 Dec 1987	T	198 x 216 km x 70.4°
	87108	Cosmos-1906	26 Dec 1987	P	190 x 274 km x 82.6°
	87110	Cosmos-1907	29 Dec 1987	P	208 x 398 km x 72.9°
	88003	Progress-34	20 Jan 1988	T
	88004	Cosmos-1915	26 Jan 1988	P	200 x 375 km x 72.9°
	88007	Cosmos-1916	03 Feb 1988	T	174 x 358 km x 64.9°
	88010	Cosmos-1920	18 Feb 1988	P	193 x 270 km x 82.6°
	88011	Cosmos-1921	19 Feb 1988	T	215 x 408 km x 70.2°
	88015	Cosmos 1923	10 Mar 1988	P	205 x 332 km x 72.8°
	88024	Progress-35	23 Mar 1988	T
	88025	Cosmos 1935	24 Mar 1988	P	179 x 356 km x 67.0°
	88027	Cosmos-1936	30 Mar 1988	T	230 x 298 km x 64.8°
	88030	Cosmos-1938	11 Apr 1988	P	225 x 290 km x 72.8°
	88031	Photon-1	14 Apr 1988	P	225 x 397 km x 62.8°
	88035	Cosmos-1941	27 Apr 1988	T	217 x 293 km x 70.3°
	88037	Cosmos-1942	12 May 1988	P	166 x 361 km x 67.1°
	88038	Progress-36	13 May 1988	T
	88041	Cosmos-1944	19 May 1988	T	212 x 261 km x 64.8°
	88042	Cosmos-1945	19 May 1988	T	232 x 321 km x 70.4°
	88047	Cosmos-1951	01 Jun 1988	P	259 x 275 km x 82.3°
	88048	Soyouz-TM5	07 Jun 1988	T
	88049	Cosmos-1952	11 Jun 1988	T	230 x 287 km x 70.0°
	88054	Cosmos-1955	22 Jun 1988	T	258 x 273 km x 64.7°
	88055	Cosmos-1956	23 Jun 1988	P	333 x 368 km x 82.3°
	88057	Cosmos 1957	07 Jul 1988	P	194 x 256 km x 82.6°
		Cosmos	09 Jul 1988		Failure
	88061	Progress-37	18 Jul 1988	T
	88068	Cosmos 1962	08 Aug 1988	T	215 x 297 km x 70.0°
	88070	Cosmos 1963	16 Aug 1988	T	181 x 367 km x 64.8°
	88072	Cosmos 1964	23 Aug 1988	T	216 x 297 km x 70.0°
	88073	Cosmos 1965	23 Aug 1988	P	195 x 265 km x 82.3°
	88075	Soyouz-TM6	29 Aug 1988	T
	88079	Cosmos 1967	06 Sep 1988	P	206 x 409 km x 72.9°
	88082	Cosmos 1968	09 Sep 1988	P	192 x 262 km x 82.3°
	88083	Progress-38	09 Sep 1988	T
	88084	Cosmos 1969	15 Sep 1988	P	178 x 373 km x 67.0°
	88088	Cosmos 1973	22 Sep 1988	P	194 x 368 km x 72.8°
	88094	Cosmos 1976	13 Oct 1988	P	191 x 366 km x 72.9°
	88097	Cosmos 1978	27 Oct 1988	P	191 x 364 km x 72.8°
		Cosmos	11 Nov 1988		Failure
	88103	Cosmos-1981	24 Nov 1988	P	240 x 360 km x 62.8°
	88104	Soyouz-TM7	26 Nov 1988	T
	88105	Cosmos 1982	30 Nov 1988	T	210 x 400 km x 70.0°
	88107	Cosmos 1983	08 Dec 1988	P	200 x 250 km x 62.8°
	88110	Cosmos 1984	16 Dec 1988	P	195 x 345 km x 62.8°
	88114	Progress-39	25 Dec 1988	T
	88116	Cosmos 1986	29 Dec 1988	T	200 x 310 km x 64.8°
	89002	Cosmos 1990	12 Jan 1989	P	190 x 260 km x 82.6°
	89003	Cosmos 1991	18 Jan 1989	T	210 x 400 km x 70.0°
	89007	Cosmos 1993	28 Jan 1989	T	180 x 380 km x 64.8°
	89008	Progress-40	10 Feb 1989	T
	89010	Cosmos 2000	10 Feb 1989	P	191 x 275 km x 82.3°
	89015	Cosmos 2003	17 Feb 1989	P	249 x 271 km x 62.8°
	89019	Cosmos 2005	02 Mar 1989	P	197 x 347 km x 62.8°
	89022	Cosmos 2006	16 Mar 1989	P	250 x 400 km x 62.9°
	89023	Progress-41	16 Mar 1989	T
	89024	Cosmos 2007	23 Mar 1989	T	190 x 300 km x 64.8°
	89029	Cosmos 2017	06 Apr 1989	P	240 x 280 km x 62.8°
	89031	Cosmos 2018	20 Apr 1989	P	194 x 350 km x 62.8°
	89032	Photon-2	26 Apr 1989	P	225 x 400 km x 62.8°
	89034	Cosmos 2019	05 May 1989	P	240 x 260 km x 62.9°
	89036	Cosmos 2020	17 May 1989	T	180 x 365 km x 64.8°
	89037	Cosmos 2021	24 May 1989	T	200 x 300 km x 70.0°
	89038	Resurs F01	25 May 1989	P	188 x 263 km x 82.3°
	89040	Cosmos 2025	01 Jun 1989	P	180 x 350 km x 62.8°
	89047	Cosmos 2028	16 Jun 1989	T	210 x 290 km x 70.0°
	89049	Resurs F02	27 Jun 1989	P	195 x 260 km x 82.6°
	89051	Cosmos 2029	05 Jul 1989	P	190 x 270 km x 82.3°
	89054	Cosmos 2030	12 Jul 1989	P	170 x 350 km x 67.2°
	89055	Resurs F03	18 Jul 1989	P	260 x 275 km x 82.6°
	89056	Cosmos 2031	18 Jul 1989	T	250 x 350 km x 50.6°
	89057	Cosmos 2032	20 Jul 1989	P	180 x 360 km x 82.3°
	89060	Cosmos 2035	02 Aug 1989	P	190 x 270 km x 82.6°
	89063	Resurs F04	15 Aug 1989	P	190 x 260 km x 82.3°
	89065	Cosmos 2036	22 Aug 1989	P	260 x 300 km x 62.8°
	89066	Progress-M1	23 Aug 1989	T
	89071	Soyouz-TM8	05 Sep 1989	T
	89073	Resurs F05	06 Sep 1989	P	190 x 260 km x 82.3°
	89075	Cosmos 2044	15 Sep 1989	P	210 x 270 km x 82.3°
	89076	Cosmos 2045	22 Sep 1989	T	210 x 320 km x 70.0°
	89082	Cosmos 2047	03 Oct 1989	P	170 x 280 km x 67.2°
	89083	Cosmos 2048	17 Oct 1989	P	250 x 270 km x 62.8°
	89088	Cosmos 2049	17 Nov 1989	T	223 x 270 km x 64.8°
	89095	Cosmos 2052	30 Nov 1989	P	175 x 370 km x 67.2°
	89099	Progress-M2	20 Dec 1989	T
	90003	Cosmos 2055	17 Jan 1990	P	249 x 321 km x 62.8°
	90009	Cosmos 2057	25 Jan 1990	P	185 x 332 km x 62.8°
	90014	Soyouz-TM9	11 Feb 1990	T
	90020	Progress-M3	28 Feb 1990	T
	90024	Cosmos 2062	22 Mar 1990	P	241 x 375 km x 82.3°
	90032	Photon-3	11 Apr 1990	P	218 x 376 km x 62.8°
	90033	Cosmos 2072	13 Apr 1990	T	183 x 253 km x 64.8°
	90035	Cosmos 2073	17 Apr 1990	P	232 x 297 km x 82.4°
	90041	Progress-42	05 May 1990	T
	90042	Cosmos-2077	07 May 1990	P	184 x 329 km x 62.8°
	90044	Cosmos-2078	15 May 1990	T	213 x 278 km x 70.0°
	90047	Resurs F06	29 May 1990	P	259 x 273 km x 82.4°
	90053	Cosmos-2083	19 Jun 1990	P	298 x 410 km x 82.6°
	90058	Gamma	11 Jul 1990	T	420 x 440 km x 51.6°
	90060	Resurs F07	17 Jul 1990	P	200 x 280 km x 82.3°
	90062	Cosmos-2086	20 Jul 1990	P	191 x 258 km x 82.3°
	90067	Soyouz-TM10	01 Aug 1990	T
	90069	Cosmos-2089	03 Aug 1990	P	196 x 342 km x 62.8°
	90072	Progress-M4	15 Aug 1990	T
	90073	Resurs F08	16 Aug 1990	P	260 x 270 km x 82.3°
	90080	Cosmos-2099	31 Aug 1990	P	191 x 258 km x 82.3°
	90082	Resurs F09	07 Sep 1990	P	180 x 238 km x 82.5°
	90085	Progress-M5	27 Sep 1990	T
	90087	Cosmos-2101	01 Oct 1990	P	210 x 290 km x 64.7°
	90092	Cosmos-2102	16 Oct 1990	P	190 x 360 km x 62.8°
	90098	Cosmos-2104	16 Nov 1990	P	247 x 387 km x 62.8°
	90107	Soyouz-TM11	02 Dec 1990	T
	90109	Cosmos 2108	04 Dec 1990	P	196 x 339 km x 62.8°
	90113	Cosmos-2113	21 Dec 1990	T	189 x 307 km x 64.8°
	90115	Cosmos-2120	26 Dec 1990	P	188 x 253 km x 82.6°
	91002	Progress-M6	14 Jan 1991	T
	91004	Cosmos-2121	17 Jan 1991	P	177 x 275 km x 82.6°
	91008	Cosmos-2124	07 Feb 1991	P	180 x 290 km x 62.8°
	91011	Cosmos-2134	15 Feb 1991	T	190 x 310 km x 64.7°
	91016	Cosmos-2136	07 Mar 1991	P	257 x 336 km x 62.9°
	91020	Progress-M7	19 Mar 1991	T
	91023	Cosmos-2138	26 Mar 1991	P	190 x 330 km x 67.1°
	91034	Soyouz-TM12	18 May 1991	T
	91035	Resurs F10	21 May 1991	P	230 x 230 km x 82.3°
	91036	Cosmos-2149	24 May 1991	P	180 x 380 km x 67.1°
	91038	Progress-M8	30 May 1991	T
	91044	Resurs F11	28 Jun 1991	P	260 x 270 km x 82.3°
	91048	Cosmos-2152	09 Jul 1991	P	190 x 270 km x 82.3°
	91049	Cosmos-2153	10 Jul 1991	T	190 x 290 km x 64.9°
	91052	Resurs F12	23 Jul 1991	P	260 x 260 km x 82.3°
	91057	Progress-M9	20 Aug 1991	T
	91058	Resurs F13	21 Aug 1991	P	230 x 230 km x 82.3°
	91066	Cosmos-2156	19 Sep 1991	P	190 x 360 km x 67.1°
	91069	Soyouz-TM13	02 Oct 1991	T
	91070	Photon-4	04 Oct 1991	P	220 x 410 km x 62.8°
	91071	Cosmos-2163	09 Oct 1991	T	170 x 330 km x 64.8°
	91073	Progress-M10	17 Oct 1991	T
	91078	Cosmos-2171	20 Nov 1991	P	200 x 340 km x 62.8°
	91085	Cosmos-2174	17 Dec 1991	T	200 x 330 km x 64.9°
	92001	Cosmos-2175	21 Jan 1992	P	170 x 370 km x 67.1°
	92004	Progress-M11	25 Jan 1992	T
	92014	Soyouz-TM14	17 Mar 1992	T
	92016	Cosmos-2182	01 Apr 1992	P	165 x 330 km x 67.2°
	92018	Cosmos-2183	08 Apr 1992	T	190 x 290 km x 64.9°
	92022	Progress-M12	19 Apr 1992	T
	92024	Resurs F14	29 Apr 1992	P	230 x 230 km x 82.1°
	92025	Cosmos-2185	29 Apr 1992	T	205 x 315 km x 70.0°
	92029	Cosmos-2186	28 May 1992	P	195 x 350 km x 62.9°
	92033	Resurs F15	23 Jun 1992	P	230 x 230 km x 82.3°
	92035	Progress-M13	30 Jun 1992	T
	92045	Cosmos-2203	24 Jul 1992	P	190 x 310 km x 62.8°
	92046	Soyouz-TM15	27 Jul 1992	T
	92048	Cosmos-2207	30 Jul 1992	P	230 x 310 km x 82.3°
	92055	Progress-M14	16 Aug 1992	T
	92056	Resurs F16	19 Aug 1992	P	190 x 260 km x 82.6°
	92062	Cosmos-2210	22 Aug 1992	P	175 x 380 km x 67.2°
	92065	Foton-5	08 Oct 1992	P	230 x 380 km x 62.8°
	92071	Progress-M15	27 Oct 1992	T
	92075	Resurs 500	17 Nov 1992	P	180 x 300 km x 82.6°
	92077	Cosmos 2220	20 Nov 1992	P	180 x 370 km x 67.2°
	92087	Cosmos 2223	09 Dec 1992	T	190 x 300 km x 64.7°
	92091	Cosmos-2225	22 Dec 1992	T	210 x 310 km x 64.9°
	92095	Cosmos-2229	29 Dec 1992	P	220 x 380 km x 62.8°
	93004	Cosmos 2231	19 Jan 1993	P	180 x 370 km x 67.2°
	93005	Soyouz-TM16	24 Jan 1993	T
	93012	Progress-M16	21 Feb 1993	T
	93019	Progress-M17	31 Mar 1993	T
	93021	Cosmos 2240	02 Apr 1993	P	200 x 340 km x 62.8°
	93028	Cosmos 2243	27 Apr 1993	T	190 x 250 km x 70.3°
	93033	Resurs F17	21 May 1993	P	240 x 240 km x 82.6°
	93034	Progress-M18	22 May 1993	T
	93040	Resurs F18	25 Jun 1993	P	230 x 230 km x 82.6°
	93043	Soyouz-TM17	01 Jul 1993	T
	93045	Cosmos 2259	14 Jul 1993	P	170 x 370 km x 67.2°
	93047	Cosmos 2260	22 Jul 1993	P	240 x 300 km x 82.3°
	93052	Progress-M19	10 Aug 1993	T
	93053	Resurs F19	24 Aug 1993	P	230 x 230 km x 82.6°
	93057	Cosmos 2262	07 Sep 1993	T	200 x 320 km x 64.9°
	93064	Progress-M20	11 Oct 1993	T
	93071	Cosmos 2267	05 Nov 1993	T	250 x 280 km x 70.4°
	94001	Soyouz-TM18	08 Jan 1994	T
	94005	Progress-M21	28 Jan 1994	T
	94018	Cosmos 2274	17 Mar 1994	P	176 x 371 km x 67.1°
	94019	Progress-M22	22 Mar 1994	T
	94025	Cosmos 2280	28 Apr 1994	T	245 x 305 km x 70.4°
	94031	Progress-M23	22 May 1994	T
	94032	Cosmos 2281	07 Jun 1994	P	236 x 292 km x 82.6°
	94033	Foton 09	14 Jun 1994	P	229 x 385 km x 62.8°
	94036	Soyouz-TM19	01 Jul 1994	T
	94042	Cosmos 2283	20 Jul 1994	P	179 x 356 km x 67.1°
	94044	Cosmos 2284	29 Jul 1994	T	206 x 296 km x 70.4°
	94052	Progress-M24	25 Aug 1994	T
	94063	Soyouz-TM20	03 Oct 1994	T
	94075	Progress-M25	11 Nov 1994	T
	94088	Cosmos 2305	29 Dec 1994	T	240 x 297 km x 64.9°
	95005	Progress-M26	15 Feb 1995	T
	95006	Foton 10	16 Feb 1995	P	228 x 391 km x 62.8°
	95010	Soyouz-TM21	14 Mar 1995	T
	95014	Cosmos 2311	22 Mar 1995	P	178 x 359 km x 67.2°
	95020	Progress-M27	09 Apr 1995	T
	95031	Cosmos 2314	28 Jun 1995	P	177 x 368 km x 67.1°
	95036	Progress-M28	20 Jul 1995	T
	95047	Soyouz-TM22	03 Sep 1995	T
	95050	Resurs F20	26 Sep 1995	P	231 x 235 km x 82.3°
	95051	Cosmos 2320	29 Sep 1995	P	242 x 3.2 km x 64.9°
	95053	Progress-M29	08 Oct 1995	T
	95070	Progress-M30	18 Dec 1995	T
	96011	Soyouz-TM23	21 Feb 1996	T
	96016	Cosmos 2331	14 Mar 1996	P	164 x 355 km x 67.1°
	96028	Progress-M31	05 May 1996	T
	n/a	Cosmos	14 May 1996	T	Failure
	n/a	Cosmos	21 Jun 1996	P	Failure
	96043	Progress-M32	31 Jul 1996	T
	96047	Soyouz-TM24	17 Aug 1996	T
	96066	Progress-M33	19 Nov 1996	T
	96073	Bion-11	24 Dec 1996	P	217 x 379 km x 90.5°
	96047	Soyouz-TM25	10 Feb 1997	T
	97014	Progress-M34	06 Apr 1997	T
666?	97024	Cosmos 2343	15 May 1997	T
	97033	Progress-M35	05 Jul 1997	T
	97038	Soyouz-TM26	05 Aug 1997	T
	97058	Progress-M36	05 Oct 1997	T
	97080	Cosmos 2348	15 Dec 1997	P
	97081	Progress-M37	20 Dec 1997	T
	98004	Soyouz-TM27	29 Jan 1998	T
	98009	Cosmos 2349	17 Feb 1998	T
	98015	Progress-M38	14 Mar 1998	T
	98031	Progress-M39	14 May 1998 at 22:12 UT	T
	98038	Cosmos 2358	24 Jun 1998 at 18:30 UT	P
	98039	Cosmos 2359	25 Jun 1998 at 14:00 UT	T
	98047	Soyouz-TM28	13 Aug 1998 at 09:43 UT	T
	98062	Progress-M40	25 Oct 1998 at 04:14 UT	T
	99004	A: Globalstar 36 B: Globalstar 23 C: Globalstar 38 D: Globalstar 40	9 Feb 1999 at 03:54 UT	T	Ikar has a Melnikov 17D61 UDMH/N2O4 engine. It is derived from the Yantar' reconnaissance satellite's propulsion module
	99006	Soyouz TM-29	20 Feb 1999 at 04:18 UT	T
	99012	A: Globalstar 22 B: Globalstar 41 C: Globalstar 46 D: Globalstar 37	15 Mar 1999 at 03:06 UT	T	Ikar
	99015	Progress-M41	2 Apr 1999 at 11:28 UT	T
	99019	A: Globalstar 45 B: Globalstar 42 C: Globalstar 44 D: Globalstar 19	15 Apr 1999 at 00:46 UT	T	Ikar
	99038	Progress-M42	16 Jul 1999 at 16:36 UT	T
	99044	Cosmos 2365	18 Aug 1999 at 18:00 UT	P


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 Shavit

by Jean-Jacques Serra

Origin: Jericho ballistic missiles

The developpement of the first Israeli ballistic missile named Jericho started in the early sixties. This rocket would have been designed with the help of the French company Dassault-Breguet which was studying the MD-600 ballistic missiles at that time. After the French export embargo of armement to Israel in 1967 the developpement would have been continued by Israel Defense Industries with internal technology. Jericho 1 went operational in 1973. It was apparently a single stage solid missile range approx. 500 km.

Its follow up Jericho 2 was 2-stage. It would have been designed in in seventies and first launched in 1986. The Jericho 3 was 12 m long and 1.2 m diameter. It would have been capable of launching 1 ton at 1500 km distance.

Shavit launchers (Comet)

We still only have few details on Shavit. It is a 3-stage solid launcher whose 2 first stages are inherited from Jericho 2. The third stage was built by Raphael. The two first stages have a composit structure. They are identical and weigh approx. 13 tons. The third stage is spherical, with a titanium structure. It weighs 2 tons and its 60 kN motor burns during 92.5 seconds. The equipement case with its rotation table is located under the third stage and is jettisoned before its ignition.

The Shavit launches take place from the Palmahim air force base, south of Tel Aviv. The launches have a 143 degrees inclination to avoid launching above neighboring countries. This conditions restricts satellisation capabilities: Offek 1 and Offek 2 launched in Sep 1988 and Apr 1990 weighed ~160 kg while Offek 3 launched in Apr 1995 weighed 225 kg.

Israel had proposed, with no success, a commercial version of the Shavit named Next. Nowadays another derivative with a fourth stage for a more precise orbit injection is proposed for export.

Shavit launches

#	Launch id	Payload	Launch date	Type	Status (orbit in perigee x apogee x inc. x period)
1	88087	Offek 1	19 Sep 1988
2	90027	Offek 2	3 Apr 1990
3	FTO	?	?		unofficial launch failure
4	95018	Offek 3	5 Apr 1995 at 11:16 UT
5	FTO	Offek 4	22 Jan 1998 at 13:00 UT	3-stage	Failure: second stage?
All launches from Palamchim Air Force Base


 Start

by Jean-Jacques Serra

The development of powder ballistic missiles started in 1958 in Russia. It was carried out by a division created by Korolev (today NPO Soyouz) directed by I. Sadovsky and after 1966 by A.D. Nadiradze. The first ICBM was the 3-stage RS-12 (SS-13 Savage) with metallic structure. Only 60 items were produced. Two mobile missiles were then derived from it: the SS-14 which used the 2 upper stages of the SS-13 and the SS-15 which refurbished the first and third stage.

In the seventies the RS-14 ICBM (SS-16 Sinner) was a much improved version of the RS-12, especially for the reeled structure and the guidance. This ICBM was not deployed following the SALT agreements. The RSD-10 IRBM (SS-20 Sabre) produced to replace the aging SS-4 and SS-5 were deployed (up to 378 operational) before being retrieved with the INF agreements.

Origin: Inter Continental Ballistic Missile (ICBM) of fith generation

At the beginning of the eighties the NPO Soyouz designed a new mobile ICBM named RS-12M Topol (SS-25 Sickle) to replace old launching silos. This fith generation missile which was operational in 1985 is the biggest mobile strategic missile of the CIS. According to the Russians the SS-25 is derived from the SS-13. With 3 stages it is 18.5 m long, 1.8 m diameter and weighs about 40 tons. It can send a 1 ton payload to more than 10000 km.

The Start launcher

The first version Start 1 is a 4-stage launcher which 3 first stages are derived from the SS-25. it is 22.7 m high, weighs 47 tons at takeoff and can deliver 300 kg on polar orbit ot 500 kg in equatorial orbit. It was tested only once in March 1993.

The Start offered for commercial flights has an additional stage: an improved version of SS-20's second stage is inserted between the first and second stage. The whole is then 29 m high and 60 tons. It can put 450 kg in polar orbit. It's first launch in March 1995 failed. An agreement with Akjuit Aerospace (Canada) was signed to launch vehicles from SpacePort Canada from late 1998.

Start launches

#	Launch id	Payload	Launch date	Type	Status (orbit in perigee x apogee x inc. x period)
1	93014	Start 1	25 Mar 1993	4-stage	launched from Plesetsk
2	FTO	Techsat 1 Unamsat 1	28 Mar 1995	5-stage	Failure cause: 5th stage failed launched from Plesetsk
3	97010	Zeya	4 Mar 1997 at 2:00 UT	4-stage
4	97085	Early Bird	24 Dec 1997 at 13:32 UT
All launches from Svobodny (51.2 N 128.0 E) unless otherwise stated


 STS

Space Transport System

American space Shutle program

The orbiter is 45 m long, 14.4 m wide and weights 67.5 t. It can carry 8 persons and a 29 t bay. It is launched with a 700 t tank.

External resources

http://shuttle.nasa.gov/


STS

[launch vehicle index]

STS 01 STS 02 STS 03 STS 04 STS 05 STS 06 STS 07 STS 08 STS 09 STS 11 STS 13 STS 16 STS 17 STS 19 STS 20 STS 23 STS 24 STS 25 STS 26 STS 26R	STS 27 STS 27R STS 28 STS 28R STS 29 STS 30 STS 30R STS 31 STS 31R STS 32 STS 32R STS 33 STS 33R STS 34 STS 35 STS 36 STS 37 STS 38 STS 39 STS 40	STS 41 STS 42 STS 43 STS 44 STS 45 STS 46 STS 47 STS 48 STS 49 STS 50 STS 51 STS 52 STS 53 STS 54 STS 55 STS 56 STS 57 STS 58 STS 59 STS 60	STS 61 STS 62 STS 63 STS 64 STS 65 STS 66 STS 67 STS 68 STS 69 STS 70 STS 71 STS 72 STS 73 STS 74 STS 75 STS 76 STS 77 STS 78 STS 79 STS 80	STS 81 STS 82 STS 83 STS 84 STS 85 STS 86 STS 87 STS 88 STS 89 STS 90 STS 91 STS 93 STS 94 STS 95 STS 96


 STS 01

General

Launch id	81034
Launch date	12 Apr 1981
Launch site	Cape Canaveral pad 39A
Type	Columbia #01
Crew	John Young Robert Crippen
Landing date	14 Apr 1981
Landing site	Edwards
Payload	none

Flight of 54 h 20 min 52 s

DFI mission

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-1/mission-sts-1.html


 STS 02

General

Launch id	81111
Launch date	12 Nov 1981
Launch site	Cape Canaveral pad 39A
Type	Columbia #02
Crew	Richard Truly Joseph Engle
Landing date	14 Nov 1981
Landing site	Edwards
Payload	none

Flight of 54 h 13 min 12 s. The flight was shorten

OSTA 1 mission: 7 experiences

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-2/mission-sts-2.html


 STS 03

General

Launch id	82022
Launch date	22 Mar 1982
Launch site	Cape Canaveral pad 39A
Type	Columbia #03
Crew	Jack Lousma Charles Fullerton
Landing date	30 Mar 1982
Landing site	White Sands
Payload	none

Flight of 8 days 5 min

OSS 1 mission

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-3/mission-sts-3.html


 STS 04

General

Launch id	82065
Launch date	27 Jun 1982
Launch site	Cape Canaveral pad 39A
Type	Columbia #04
Crew	Thomas Mattingly Henry Harstfield
Landing date	4 Jul 1982
Landing site	Edwards
Payload	none

Flight of 7 days 1 h 9 min 39 s

DoD 82-1 mission

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-4/mission-sts-4.html


 STS 05

General

Launch id	82110
Launch date	11 Nov 1982
Launch site	Cape Canaveral
Type	Columbia #05
Crew	Vance Brand Robert Overmyer Joseph Allen William Lenoir
Landing date	16 Nov 1982
Landing site	Edwards
Payload	B: SBS 3 C: Anik C3

First operational flight: 5 days 2 h 14 min 25 s

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-5/mission-sts-5.html


 STS 06

General

Launch id	83026
Launch date	4 Apr 1983
Launch site	Cape Canaveral
Type	Challenger #01
Crew	Donald Peterson Story Musgrave Paul Weitz Karol Bobko
Landing date	9 Apr 1983
Landing site	Edwards
Payload	B: TDRS 1

Flight of 5 days 24 min 32 s

Musgrave and Peterson worked 3 h 50 min in space to simulate repairings

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-6/mission-sts-6.html


 STS 07

General

Launch id	83059
Launch date	18 Jun 1983
Launch site	Cape Canaveral
Type	Challenger #02
Crew	Robert Crippen Frederik Hauck Sally Ride (first american woman in space) Normand Thagard John Fabian
Landing date	24 Jun 1983
Landing site	Edwards
Payload	B: Anik C2 C: Palapa B1 D: Spas 1 (launched and retrieved)

Flight of 6 days 2 h 24 min 10 s

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-7/mission-sts-7.html


 STS 08

General

Launch id	83089
Launch date	30 Aug 1983
Launch site	Cape Canaveral
Type	Challenger #03
Crew	Richard Truly Daniel Brandenstein Dale Gardner Gruion Bluford William Thornton
Landing date	5 Sep 1983
Landing site	Edwards
Payload	B: Insat 1B

Flight of 6 days 1 h 8 min 40 s

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-8/mission-sts-8.html


 STS 09

Also called STS 41A

General

Launch id	83116
Launch date	28 Nov 1983
Launch site	Cape Canaveral pad 39A
Type	Columbia #06
Crew	John Young Brewster Shaw Owen Garriott Robert Parker Byron Lichtenberg Ulf Merbold (Germany)
Landing date	8 Dec 1983
Landing site	Edwards
Payload	none

Flight of 10 days 7 h 47 min

Spacelab 1 mission (70 experiences)

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-9/mission-sts-9.html


 STS 11

Also called STS 41B

General

Launch id	84011
Launch date	3 Feb 1984
Launch site	Cape Canaveral
Type	Challenger #04
Crew	Vance Brand Robert Gibson Ronald Mc Nair Bruce Mc Candless Robert Stewart
Landing date	11 Feb 1984
Landing site	Cape Canaveral
Payload	B: Westar 6 C: IRT (launched and retrieved) D: Palapa B2

Flight of 7 days 23 h 17 min

First free flight for Mc Candless and Stewart with the Manned Manoeuvring Unit (MMU)

External resources

http://www.ksc.nasa.gov/shuttle/missions/41-b/mission-41-b.html


 STS 13

Also called STS 41C

General

Launch id	84034
Launch date	6 Apr 1984
Launch site	Cape Canaveral
Type	Challenger #05
Crew	Robert Crippen Francis Scobee Terry Hart George Nelson James Van Hoften
Landing date	13 Apr 1984
Landing site	Edwards
Payload	LDEF

Flight of 6 days 23 h 40 min

Reparation of SMM in orbit by Nelson and Van Hoften

External resources

http://www.ksc.nasa.gov/shuttle/missions/41-c/mission-41-c.html


 STS 16

Also called STS 41D

General

Launch id	84093
Launch date	30 Aug 1984
Launch site	Cape Canaveral
Type	Discovery #01
Crew	Henry Hartsfield Michael Coats Richard Mullane Steven Hawley Charles Walker (first non astronaut) Judith Resnik
Landing date	5 Sep 1984
Landing site	Edwards
Payload	B: SBS 4 C: Leasat 2 D: Telstar 302

Flight of 6 days 56 min

OATS 1 mission

External resources

http://www.ksc.nasa.gov/shuttle/missions/41-d/mission-41-d.html


 STS 17

Also called STS 41G

General

Launch id	84108
Launch date	5 Oct 1984
Launch site	Cape Canaveral
Type	Challenger #06
Crew	Robert Crippen John McBride Kathryn Sullivan (first woman out in space) Sally Ride David Leetsma Paul Scully-Power Marc Garneau (Canada)
Landing date	13 Oct 1984
Landing site	Cape Canaveral
Payload	ERBS

Flight of 8 days 5 h 23 min

SIR C

External resources

http://www.ksc.nasa.gov/shuttle/missions/41-g/mission-41-g.html


 STS 19

Also called STS 51A

General

Launch id	84113
Launch date	8 Nov 1984
Launch site	Cape Canaveral
Type	Discovery #02
Crew	Frederik Hauck Joseph Allen David Walker Dale Gardner Anna Fisher
Landing date	16 Nov 1984
Landing site	Cape Canaveral
Payload	B: Anik D2 C: Leasat 1

Flight of 7 days 23 h 45 min

Palapa B2 and Westar 6 are brought back on Earth (were placed on a bad orbit by STS 11). Operation financed by the insurance companies.

External resources

http://www.ksc.nasa.gov/shuttle/missions/51-a/mission-51-a.html


 STS 20

Also called STS 51C

General

Launch id	85010
Launch date	24 Jan 1985
Launch site	Cape Canaveral
Type	Discovery #03
Crew	Thomas Mattingly Loren Shriver Ellison Onizuka James Buchli Gary Payton
Landing date	27 Jan 1985
Landing site	Cape Canaveral
Payload	B: USA 008

Flight of 3 days 1 h 33 min

DoD mission

External resources

http://www.ksc.nasa.gov/shuttle/missions/51-c/mission-51-c.html


 STS 23

Also called STS 51D

General

Launch id	85028
Launch date	12 Apr 1985
Launch site	Cape Canaveral
Type	Discovery #04
Crew	Karol Bobko Donald Williams David Griggs Margaret Seddon Jeffrey Hoffman David Mc Walker Jack Garn (senator)
Landing date	19 Apr 1985
Landing site	Cape Canaveral
Payload	B: Anik C1 C: Leasat 3

Flight of 6 days 23 h 55 min 20 s

External resources

http://www.ksc.nasa.gov/shuttle/missions/51-d/mission-51-d.html


 STS 24

Also called STS 51B

General

Launch id	85034
Launch date	29 Apr 1985
Launch site	Cape Canaveral
Type	Challenger #07
Crew	Robert Overmyer Frederik Gregory Don Lind William Thornton Taylor Wang Norman Thagard Lodewijk Vandenberg
Landing date	6 May 1985
Landing site	Edwards
Payload	B: Nusat 1 (radar calibration?) C: Glomr (couldn't be ejected)

Flight of 7 days 8 min

Spacelab 3 mission

External resources

http://www.ksc.nasa.gov/shuttle/missions/51-b/mission-51-b.html


 STS 25

Also called STS 51G

General

Launch id	85048
Launch date	17 Jun 1985
Launch site	Cape Canaveral
Type	Discovery #05
Crew	Daniel Brandestein John Creighton John Fabian Shannon Lucid Steven Nagel Patrick Baudry (France) Sultan Al Saud (Saudi Arabia)
Landing date	24 Jun 1985
Landing site	Edwards
Payload	B: Morelos 1 C: Arabsat 1B D: Telstar 303 E: Spartan 101 (launched and retrieved)

Flight of 7 days 1 h 38 min 53 s

External resources

http://www.ksc.nasa.gov/shuttle/missions/51-g/mission-51-g.html


 STS 26

Also called STS 51F

General

Launch id	85063
Launch date	29 Jul 1985
Launch site	Cape Canaveral
Type	Challenger #08
Crew	Story Musgrave Antony England John Bartoe Roy Bridges Karl Henise Loren Acton Gordon Fullerton
Landing date	6 Aug 1985
Landing site	Edwards
Payload	B: PDP (launched and retrieved)

Flight of 7 days 22 h 45 min 26 s. One of the 3 main motors stopped after 5 min 45 s. The shuttle was orbited 70 km below the nominal orbit

Spacelab 2 mission

External resources

http://www.ksc.nasa.gov/shuttle/missions/51-f/mission-51-f.html


 STS 26R

Also called STS 81A

General

Launch id	88091
Launch date	29 Sep 1988
Launch site	Cape Canaveral
Type	Discovery #07
Crew	R. Hauck Richard Covey John Lounge George Nelson David Hilmers
Landing date	3 Oct 1988
Landing site	Edwards
Payload	B: TDRS 3
External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-26/mission-sts-26.html


 STS 27

Also called STS 51I

General

Launch id	85076
Launch date	27 Aug 1985
Launch site	Cape Canaveral
Type	Discovery #06
Crew	Joe Engle Richard Covey James Van Hoften William Fisher John Lounge
Landing date	3 Sep 1985
Landing site	Edwards
Payload	B: Optus A1 C: ASC 1 D: Leasat 4

Flight of 7 days 2 h 18 min 29 s

Leasat 3 was repared

External resources

http://www.ksc.nasa.gov/shuttle/missions/51-i/mission-51-i.html


 STS 27R

Also called STS 91A

General

Launch id	88106
Launch date	2 Dec 1988
Launch site	Cape Canaveral
Type	Atlantis #03
Crew	Robert Gibson Guy Gardner Rochard Mullane Jerry Ross William Sheperd
Landing date	6 Dec 1988
Landing site	Edwards
Payload	B: Lacrosse 1

Flight of 4 days 9 h

DoD mission

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-27/mission-sts-27.html


 STS 28

Also called STS 51J

General

Launch id	85092
Launch date	3 Oct 1985
Launch site	Cape Canaveral
Type	Atlantis #01
Crew	Karol Bobko Ronald Grabe David Hilmers Robert Stewart William Pailes
Landing date	7 Oct 1985
Landing site	Edwards
Payload	B: DSCS 3-03 C: DSCS 3-04

Flight of 4 days 1 h 45 min

DoD mission

External resources

http://www.ksc.nasa.gov/shuttle/missions/51-j/mission-51-j.html


 STS 28R

Also called STS 91D

General

Launch id	89061
Launch date	8 Aug 1989
Launch site	Cape Canaveral pad 39B
Type	Columbia #08
Crew	Brewster Shaw Richard Richards David Leetsma James Adamson Mark Brown
Landing date	13 Aug 1989
Landing site	Edwards
Payload	B: USA 040 C: USA 41

DoD mission

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-28/mission-sts-28.html


 STS 29

Also called STS 91B

General

Launch id	89021
Launch date	13 Mar 1989
Launch site	Cape Canaveral
Type	Discovery #08
Crew	Michel Coats John Blaha James Buchli Robert Springer James Bagion
Landing date	18 Mar 1989
Landing site	Edwards
Payload	B: TDRS 4
External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-29/mission-sts-29.html


 STS 30

Also called STS 61A

General

Launch id	85104
Launch date	30 Oct 1985
Launch site	Cape Canaveral
Type	Challenger #09
Crew	Henry Hartsfield Steven Nagel James Buchli Guion Bluford Bonnie Dunbar Ernst Messerschmidt (Germany) Reinhardt Furrer (Germany) Wubbo Ockels (Netherlands)
Landing date	6 Nov 1985
Landing site	Edwards
Payload	B: Glomr (Global Low Orbiting Message Relay)

Flight of 7 days 44 min 51 s

Spacelab D1 mission (76 experiences including BIORAK)

External resources

http://www.ksc.nasa.gov/shuttle/missions/61-a/mission-61-a.html


 STS 30R

Also called STS 91C

General

Launch id	89033
Launch date	4 May 1989
Launch site	Cape Canaveral
Type	Atlantis #04
Crew	David Walker Ronald Grabe Norman Thagard Mary Cleave Mark Lee
Landing date	8 May 1989
Landing site	Edwards
Payload	B: Magellan
External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-30/mission-sts-30.html


 STS 31

Also called STS 61B

General

Launch id	85109
Launch date	27 Nov 1985
Launch site	Cape Canaveral
Type	Atlantis #02
Crew	Brewster Shaw Brian O'Connor Mary Cleave Sherwood Springs Jerry Ross Charles Walker Rodolfo Vela (Mexico)
Landing date	3 Dec 1985
Landing site	Edwards
Payload	B: Morelos 2 C: Optus A2 D: Satcom K2

Flight of 6 days 21 h 4 min 50 s

External resources

http://www.ksc.nasa.gov/shuttle/missions/61-b/mission-61-b.html


 STS 31R

Also called STS 0E

General

Launch id	90037
Launch date	24 Apr 1990
Launch site	Cape Canaveral
Type	Discovery #10
Crew	Loren Shriver Charles Boden Steven Hawley Bruce Mc Candless Catherin Sullivan
Landing date	29 Apr 1990
Landing site
Payload	B: HST
External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-31/mission-sts-31.html


 STS 32

Also called STS 61C

General

Launch id	86003
Launch date	12 Jan 1986
Launch site	Cape Canaveral pad 39A
Type	Columbia #07
Crew	Robert Gibson Charles Bolden Robert Cenker Steven Hawley George Nelson Franklin Chang-Diaz Bill Nelson
Landing date	18 Jan 1986
Landing site	Edwards
Payload	B: Satcom K1

Flight of 6 days 1 h 4 min 9 s

MSL 2

External resources

http://www.ksc.nasa.gov/shuttle/missions/61-c/mission-61-c.html


 STS 32R

Also called STS 0C

General

Launch id	90002
Launch date	9 Jan 1990
Launch site	Cape Canaveral pad 39A
Type	Columbia #09
Crew	Daniel Brandenstein James Wetherbee Bonnie Dunbar David Low Marsha Ivins
Landing date	20 Jan 1990
Landing site	Edwards
Payload	B: Leasat 5

Flight of 10 days 21 h 1 min

Retrieval of LDEF

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-32/mission-sts-32.html


 STS 33

Also called STS 51L

General

Launch date	28 Jan 1986
Launch site	Cape Canaveral
Type	Challenger #10
Crew	Francis Scobee Michael Smith Gregory Jarvis Judith Resnik Sharon Mc Auliffe Ronald Mc Nair Ellison Onizuka
Landing date
Landing site
Payload	TDRS 2 Spartan 203

Explosion after 73 s

External resources

http://www.ksc.nasa.gov/shuttle/missions/51-l/mission-51-l.html


 STS 33R

Also called STS 0B

General

Launch id	89090
Launch date	23 Nov 1989
Launch site	Cape Canaveral
Type	Discovery #09
Crew	Frederik Gregory David Griggs F. Story Musgrave Kathryn Thurnton Manley Carter
Landing date	28 Nov 1989
Landing site	Edwards
Payload	B: USA 48

DoD mission

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-33/mission-sts-33.html


 STS 34

Also called STS 0A

General

Launch id	89084
Launch date	18 Oct 1989
Launch site	Cape Canaveral
Type	Atlantis #05
Crew	Donald Williams Michael Mc Cully Shannon Lucid Ellen Baker Franklin Chang-Diaz
Landing date	23 Oct 1989
Landing site	Edwards
Payload	B: Galileo
External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-34/mission-sts-34.html


 STS 35

General

Launch id	90106
Launch date	2 Dec 1990
Launch site	Cape Canaveral pad 39B
Type	Columbia #10
Crew	Brand Gardner Lounge Hoffman Parker Parise
Landing date	10 Dec 1990
Landing site	Edwards
Payload	none

ASTRO 1 mission

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-35/mission-sts-35.html


 STS 36

Also called STS 0D

General

Launch id	90019
Launch date	28 Feb 1990
Launch site	Cape Canaveral
Type	Atlantis #06
Crew	John Creighton John Casper Richard Mullane David Hilmers Pierre Thuot
Landing date	4 Mar 1990
Landing site	Edwards
Payload	B: KH 12-1

DoD mission

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-36/mission-sts-36.html


 STS 37

General

Launch id	91027
Launch date	5 Apr 1991
Launch site	Cape Canaveral
Type	Atlantis #08
Crew	Jerry Ross Jay Apt Linda Godwin Steven Nagel Henneth Cameron
Landing date	11 Apr 1991
Landing site	Edwards
Payload	B: GRO

Ross and Apt went out twice (5 h 46 min and 3 h 30 min) to free GRO's antenna

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-37/mission-sts-37.html


 STS 38

General

Launch id	90097
Launch date	15 Nov 1990
Launch site	Cape Canaveral
Type	Atlantis #07
Crew	Covey Culbertson Springer Meade Gemar
Landing date	20 Nov 1990
Landing site	Cape Canaveral
Payload	USA 067

DoD mission

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-38/mission-sts-38.html


 STS 39

General

Launch id	91031
Launch date	28 Apr 1991
Launch site	Cape Canaveral
Type	Discovery #12
Crew	Donald Mc Monagle Blaine Hammond Charles Veach Guion Bluford Michael Coats Gregory Harbaugh Richard Hieb
Landing date	6 May 1991
Landing site	Cape Canaveral
Payload	B: IBSS (launched and retrieved) C: Mpec (USA 70)

Flight of 8 days 7 h 26 min

DoD mission

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-39/mission-sts-39.html


 STS 40

General

Launch id	91040
Launch date	5 Jun 1991
Launch site	Cape Canaveral pad 39B
Type	Columbia #11
Crew	James Bagian Bryan O'Connor Drew Gaffney Sidney Gutierrez Margareth Rhea Seddon Millie Hughes-Fulford Tamara Jernigan
Landing date	14 Jun 1991
Landing site	Edwards
Payload	none

Flight of 9 days 3 h 30 min

SLS 1 (Space Laboratory Science) mission

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-40/mission-sts-40.html


 STS 41

General

Launch id	90090
Launch date	6 Oct 1990
Launch site	Cape Canaveral
Type	Discovery #11
Crew	Richard Richards Robert Parker Bruce Melnick William Shepperd Thomas Akers
Landing date	10 Oct 1990
Landing site	Edwards
Payload	B: Ulysses (http://ulysses.jpl.nasa.gov/)
External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-41/mission-sts-41.html


 STS 42

General

Launch id	92002
Launch date	22 Jan 1992
Launch site	Cape Canaveral
Type	Discovery #14
Crew	Grabe Oswald Thagard Readdy Hilmers Roberta Bondar (Canada) Ulf Merbold (Germany)
Landing date	30 Jan 1992
Landing site	Edwards
Payload	none

Flight of 8 days 1 h 14 min

IML 1 mission

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-42/mission-sts-42.html


 STS 43

General

Launch id	91054
Launch date	2 Aug 1991
Launch site	Cape Canaveral
Type	Atlantis #09
Crew	John Blaha Michael Baker James Adamson David Low Shannon Lucid
Landing date	11 Aug 1991
Landing site	Cape Canaveral
Payload	B: TDRS 5
External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-43/mission-sts-43.html


 STS 44

General

Launch id	91080
Launch date	25 Nov 1991
Launch site	Cape Canaveral
Type	Atlantis #10
Crew	Gregory Henricks Voss Musgrave Runco Hennen
Landing date	1 Dec 1991
Landing site	Edwards
Payload	DSP 3-4

DoD mission

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-44/mission-sts-44.html


 STS 45

General

Launch id	92015
Launch date	24 Mar 1992
Launch site	Cape Canaveral
Type	Atlantis #11
Crew	Bolden Duffy Leetsma Sullivan Foale Lichtenberg Dirck Frimout (Belgium)
Landing date	2 Apr 1992
Landing site	Cape Canaveral
Payload	none

ATLAS 1 mission

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-45/mission-sts-45.html


 STS 46

General

Launch id	92049
Launch date	31 Jul 1992
Launch site	Cape Canaveral
Type	Atlantis #12
Crew	Shriver Allen Nicollier Ivins Chang_Diaz Hoffman Malerba
Landing date	8 Aug 1992
Landing site	Cape Canaveral
Payload	B: Eureca 1

Tried to deploy TTS 1

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-46/mission-sts-46.html


 STS 47

General

Launch id	92061
Launch date	12 Sep 1992 at 14:23 UT
Launch site	Cape Canaveral, pad 39A
Type	Endeavour #02
Crew	Robert Gibson Brown Lee Jerome Apt Jan Davis Mae Jemison Mamoru Mohri (Japanese)
Landing date	20 Sep 1992 at 14:53 UT
Landing site	Cape Canaveral
Payload	none

Spacelab J mission

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-47/mission-sts-47.html


 STS 48

General

Launch id	91063
Launch date	12 Sep 1991
Launch site	Cape Canaveral
Type	Discovery #13
Crew	Creighton Reightler Gemar Brown Buchli
Landing date	18 Sep 1991
Landing site	Edwards
Payload	B: UARS
External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-48/mission-sts-48.html


 STS 49

General

Launch id	92026
Launch date	7 May 1992
Launch site	Cape Canaveral
Type	Endeavour #01
Crew	Brandenstein Chilton Melnick Thornton Pierre Thuot Richard Hieb Thomas Aker
Landing date	16 May 1992
Landing site	Edwards
Payload	none

Astronauts went out during 8 h 29 min on 13 May 1992 to repair Intelsat 603

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-49/mission-sts-49.html


 STS 50

General

Launch id	92034
Launch date	25 Jun 1992
Launch site	Cape Canaveral pad 39A
Type	Columbia #12
Crew	Richards Bowersox Dunbar Baker Meade Delucas Trinh
Landing date	9 Jul 1992
Landing site	Cape Canaveral
Payload	none

USML 1 mission

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-50/mission-sts-50.html


 STS 51

General

Launch id	93058
Launch date	12 Sep 1993
Launch site	Cape Canaveral
Type	Discovery #17
Crew	5 persons
Landing date	22 Sep 1993
Landing site	Cape Canaveral
Payload	B: ACTS C: Orfeus-Spas (launched and retrieved)
External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-51/mission-sts-51.html


 STS 52

General

Launch id	92070
Launch date	22 Oct 1992
Launch site	Cape Canaveral pad 39B
Type	Columbia #13
Crew	Wetherbee Baker Jernigan Veach Shepherd Mc Learn
Landing date	1 Nov 1992
Landing site	Cape Canaveral
Payload	B: Lageos 2 C: CTA (launched and retrieved)

USMP 1 mission

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-52/mission-sts-52.html


 STS 53

General

Launch id	92086
Launch date	2 Dec 1992
Launch site	Cape Canaveral
Type	Discovery #15
Crew	Walker Cabana Bluford Voss Clifford
Landing date	9 Dec 1992
Landing site	Edwards
Payload	B: USA 089

DoD mission

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-53/mission-sts-53.html


 STS 54

General

Launch id	93003
Launch date	13 Jan 1993 at 13:59:30 UT
Launch site	Cape Canaveral, LC39B
Type	Endeavour #03
Crew	John Casper Donald Mc Monagle Gregory Harbaugh Mario Runco Susan Helms
Landing date	19 Jan 1993
Landing site	Cape Canaveral
Payload	B: TDRS 6

PARE (Physiological and Anatomical Rodent Experiment) experiment

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-54/mission-sts-54.html


 STS 55

General

Launch id	93027
Launch date	26 Apr 1993 at 14:50 UT
Launch site	Cape Canaveral pad 39A
Type	Columbia
Crew	Steven Nagel Terence Henricks Jerry Ross Charles Precourt Bernard Harris Ulrich Walter (Germany) Hans William Schlegel (Germany)
Landing date	6 May 1993 at 14:30 UT
Landing site	Edwards
Payload	none

Spacelab D2 mission

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-55/mission-sts-55.html


 STS 56

General

Launch id	93023
Launch date	8 Apr 1993
Launch site	Cape Canaveral
Type	Discovery #16
Crew	Cameron Oswald Foale Cockrell Ochoa
Landing date	17 Apr 1993 at 11:37 UT
Landing site	Cape Canaveral
Payload	B: Spartan 201-1 (launched and retrieved)

ATLAS 2 mission

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-56/mission-sts-56.html


 STS 57

General

Launch id	93037
Launch date	21 Jun 1993 at 13:07 UT
Launch site	Cape Canaveral
Type	Endeavour #04
Crew	Grabe Duffy Low Sherlock Wisoff Voss
Landing date	1 Jul 1993 at 12:52 UT
Landing site	Cape Canaveral
Payload	none

Spacehab 1 (SH 1) mission

Retrieval of Eureca

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-57/mission-sts-57.html


 STS 58

General

Launch id	93065
Launch date	18 Oct 1993
Launch site	Cape Canaveral pad 39B
Type	Columbia #15
Crew	Blaha Searfoss Seddon Mc Arthur Wolf Lucid Fettman
Landing date	1 Nov 1993 at 10:05 UT
Landing site	Edwards
Payload	none

SLS 2 mission

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-58/mission-sts-58.html


 STS 59

General

Launch id	94020
Launch date	9 Apr 1994 at 12:05 UT
Launch site	Cape Canaveral
Type	Endeavour #06
Crew	At least: Dr. Jay Apt (N5QWL), commander Dr. Linda Godwin (N5RAX), specialist
Landing date	20 Apr 1994 at 17:54 UT
Landing site	Edwards
Payload

SRL 1 and SAREX missions

It carried synthetic aperture radars at three wavelengths: 23 cm (C-band), 6 cm (C-band), and 3 cm (X-band). For each wavelength, there was an array of six, electronically steerable antenna panels; the polarization plane of the emitted radiation could be varied as needed. It was expected to cover 46 million square kilometers of terrain and vegetation, yielding 32 trillion bits of data for capturing in 183 high-density tapes on board.

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-59/mission-sts-59.html


 STS 60

General

Launch id	94006
Launch date	3 Feb 1994 at 12:10 UT
Launch site	Cape Canaveral
Type	Discovery #18
Crew	7 persons (1 woman)
Landing date	11 Feb 1994
Landing site
Payload	B: Oderacs 1A C: Oderacs 1B D: Oderacs 1C E: Oderacs 1D F: Oderacs 1E G: Oderacs 1F H: Bremsat

On board was the Spacehab 2 (SH 2) facility to conduct 12 experiments. Among them were the following four GAS (Get Away Special) microgravity experiments: G-536--Pool Boiling experiment; G-557--Capillary Pumped Loop experiment; G-071--Ball Bearing experiment; and G-514--Orbiter Stability experiment. It also carried resources for high school/college science experiments.

Repeated efforts to deploy a three-meter diameter, retrievable shield (Wake Shield Facility) behind which pure crystals of Gallium Arsenide were planned to be grown were unsuccessful.

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-60/mission-sts-60.html


 STS 61

General

Launch id	93075
Launch date	2 Dec 1993
Launch site	Cape Canaveral
Type	Endeavour #05
Crew	Covey Bowerbox Akers Hoffman Musgrave Thornton Nicollier
Landing date	13 Dec 1993
Landing site	Cape Canaveral
Payload	none

Reparation of Hubble

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-61/mission-sts-61.html


 STS 62

General

Launch id	94015
Launch date	4 Mar 1994
Launch site	Cape Canaveral
Type	Columbia #16
Crew	Casper Allen Thuot Geman Ivins
Landing date	18 Mar 1994
Landing site	Cape Canaveral
Payload

It carried a U.S. Microgravity Payload (USMP 2) and an Office of Aeronautics and Space Technology Second payload (OAST 2). Among the experiments were the Solar Array Module Plasma Interaction Experiment (SAMPIE), the Thermal Energy Storage (TES) experiment, the Experimental Investigation of Spacecraft Glow (EISG) experiment, the Spacecraft Kinetic InfraRed Test (SKIRT) experiment, the Emulsion Chamber Technology (ECT) experiment, and the CRYOgenic Two Phase (CRYOTP) experiment. A new high-speed, Ku-band communication link between mission control and the shuttle enabled transmission of 162 megabytes of data.

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-62/mission-sts-62.html


 STS 63

General

Launch id	95004
Launch date	3 Feb 1995 at 05:22:04 UT
Launch site	Cape Canaveral LC39B
Type	Discovery #20
Crew	Jim Wetherbee (commander) Eileen Collins (pilot) Bernard Harris (mission specialist) Mike Foale (mission specialist) Janice Voss (mission specialist) Vladimir Titov (Russian Space Agency)
Landing date	Cape Canaveral
Landing site	11 Feb 1995 at 11:50 UT
Payload	Spartan 204 (launched and retrieved) Oderacs 2A Oderacs 2B Oderacs 2C Oderacs 2D Oderacs 2E Oderacs 2F

Spacehab 3 (SH 03) mission

The Spacehab module is a pressurized laboratory containing experiment racks and lockers. FU-1 has a new window in the roof to help in the Mir rendezvous operation.

It carried the Spacehab module containing microgravity experimental apparatus. Despite a thruster leak from the shuttle, STS 63 was finally allowed to come close to the MIR station, within about twelve meters, as a prelude to a planned docking in the future.

This was the second time there had been three women in space (STS 40 was the first), and the second time that a Russian had flown on a US spaceship.

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-63/mission-sts-63.html


 STS 64

General

Launch id	94059
Launch date	9 Sep 1994 at 22:22 UT
Launch site	Cape Canaveral, pad 39B
Type	Discovery #19
Crew	Richard (Dick) Richards, commander L. Blaine Hammond Jr. (KC5HBS), pilot Jerry L. Linenger (KC5HBR) Susan Helms Carl Meade Mark Lee
Landing date	20 Sep 1994
Landing site
Payload	Spartan 201-2 (launched and retrieved)

Lidar In-Space Technology Experiment (LITE 1) and SAREX

Also on board were 12 Get Away Special (GAS) experiments designed and built by high school and university students, an Orbit Stability Experiment (OSE), and a Robot Operated Materials Processing System (ROMPS).

Lidar is essentially radar using an optical wavelength laser instead of microwaves. LITE consists of a Spacelab pallet with a laser transmitter and a receiver telescope. In an interesting historical note, the 96-cm receiver telescope was built in the 1960s as the engineering model for the telescope on the OAO-B satellite, lost in a 1970 launch failure. It was refurbished for the LITE mission.

LITE 1 results (made from the June 16 issue of RESEARCHER NEWS, Langley Research Center)

According to Dr. M. Patrick McCormick, LITE project scientist and branch head of Langley's Aerosol Research Branch, the LITE mission was 100 percent successful. One mission highlight was the collection of spectacular data on Super Typhoon Melissa. From the cargo bay of Space Shuttle Discovery, LITE passed directly over the eye of the typhoon and profiled the eye-wall clouds from the top to the sea surface below.

Unlike passive instruments which measure the amount of heat emitted or light reflected by only the highest layer of multi-layered clouds, LITE is able to penetrate the highest clouds and provide scientists with data about clouds at many levels below. The LITE data also revealed high cirrus clouds which were not seen in the standard meteorological satellite data and are often not expressed in atmospheric models.

Using the three different wavelengths aboard LITE also allowed Browell [Dr. Edward Browell is a senior scientist in Langley's Chemistry and Dynamics Branch] and his team to identify the types of aerosols they were measuring. Browel said, "Remotely, we can detect whether the aerosols we're seeing are biomass burning or whether they're desert aerosols (sands)." Biomass burning generates green-house gases such as carbon dioxide, methane and ozone. Aerosols also affect the Earth's energy budget by scattering sunlight back into space, thereby cooling the Earth. Aerosols can also increase the amount of clouds present by acting as surfaces upon which water vapor can condense.

The LITE system obtained a spectacular data set, demonstrating the ability of lidar remote sensing techniques to study the Earth's atmosphere. A future space-based lidar system is being studied. This future system would fly on a satellite in low-earth orbit and provide daily coverage of global cloud characteristics and aerosols created by dust storms, biomass burning and urban pollution.

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-64/mission-sts-64.html


 STS 65

General

Launch id	94039
Launch date	8 Jul 1994 at 16:43 UT
Launch site	Cape Canaveral pad 39A
Type	Columbia #17
Crew	Robert D. Cabena (KC5HBV), commander James Halsell, pilot Richard Hieb Carl Walz Leroy Chiao Donald Thomas Chiaki Naito, cardiolog (first Japanese woman in space)
Landing date	23 Jul 1994 at 10:38 UT
Landing site	Cape Canaveral
Payload

Spacelab IML 2 and SAREX. On board were six goldfish, four Japanese Medeka fish, four red-bellied newts, 500 fruit flies, 126 jelly fish, and thousands of sea urchins.

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-65/mission-sts-65.html


 STS 66

General

Launch id	94073
Launch date	3 Nov 1994 at 06:59 UT
Launch site	Cape Canaveral
Type	Atlantis #13
Crew	1 ESA astronaut
Landing date	14 Nov 1994
Landing site	Edwards
Payload	Spas 4 (launched and retrieved)

Atmospheric Lab (Atlas 3)

The primary payload was the ATLAS 3 laboratory containing two instruments (SOLCON and SOLSPEC) to measure solar emissions in the visible and UV bands, and a UV backscatter monitor to measure ozone concentrations. The shuttle also carried many pregnant and nonpregnant rats for biological studies.

MAS, a German instrument which was ATLAS 3's only sensor capable of measuring chlorine monoxide (a crucial intermediate in CFCs' effect on ozone), died after only about six hours of operation.

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-66/mission-sts-66.html


 STS 67

General

Launch id	95007
Launch date	2 Mar 1995 at 06:38:14 UT
Launch site	Cape Canaveral LC39A
Type	Endeavour #08
Crew	Steve Oswald (commander) William Gregory (pilot, KC5MGA) Tamara Jernigan (payload commander, KC5MGF) Wendy Lawrence (mission specialist) John Grunsfeld (mission specialist) Ron Parise (payload specialist, Computer Sciences Corp.) Sam Durrance (Johns Hopkins University)
Landing date	18 Mar 1995 at 21:47:00 UT
Landing site	Edwards
Payload

Ultraviolet Astronomy (ASTRO 2) mission

New endurance record: 16 days 15 hours 9 min 46 s

School groups in 26 places around the world made voice contacts with the STS 67 crew as part of the Shuttle Amateur Radio EXperiment (SAREX) component of this mission.

Astro 2 is a Spacelab mission, using two Spacelab Pallets with the Spacelab Igloo avionics container and the IPS instrument pointing system. Mounted on the IPS are three ultraviolet telescopes. The 0.9-m Hopkins Ultraviolet Telescope (HUT) takes spectra in the 900 to 1900 Angstrom short wavelength UV range and the 500 to 900 A extreme ultraviolet range. The 0.5m Wisconsin Ultraviolet Photo-Polarimeter Experiment (WUPPE) telescope studies spectra in the longer wavelength 1400-3200A ultraviolet range. The 0.38m Ultraviolet Imaging Telescope (UIT) is a wide-field (0.6 degree) imaging telescope which uses ultraviolet-sensitive film.

Also in the cargo bay are the Extended Duration Orbiter (EDO) pallet and two Getaway Special (GAS) cans (G-387/G-388) which constitute the Endeavour Telescope, a project of the Australian Space Office. The 0.1m telescope takes a narrow-band, 2-degree wide-field ultraviolet image. Unlike UIT, it uses CCDs rather than film. The Australian Endeavour telescope first flew (as G-609/G-610) aboard Discovery in Jan 1992, but failed to work correctly. On that mission it was attached to a cross-bay GAS Bridge Assembly (GBA) with other GAS cans; this time the cans are mounted on a GAS Beam Adapter (GABA) on the side of the payload bay wall.

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-67/mission-sts-67.html


 STS 68

General

Launch id	94062
Launch date	30 Sep 1994
Launch site	Cape Canaveral
Type	Endeavour #07
Crew
Landing date	11 Oct 1994
Landing site	Edwards
Payload

SRL 2 mission

It carried the Space Radar Laboratory (SRL) containing SIR-C, a dual polarization radar at C- and L-bands, X-SAR, an X-band vertical polarization radar, and MAPS, an infrared sensor for measurement of air pollution.

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-68/mission-sts-68.html


 STS 69

General

Launch id	95048
Launch date	7 Sep 1995 at 15:09 UT
Launch site	Cape Canaveral LC39A
Type	Endeavour #09
Crew	David Walker (Commander) Ken Cockrell (Pilot) James Voss (Payload Commander) James Newman (Mission Specialist) Michael Gernhardt (Mission Specialist)
Landing date	18 Sep 1995 at 11:37 UT
Landing site	Cape Canaveral
Payload	Spartan 201-3 WSF 2

WSF 2 and the IEH astronomy experiment

Also on board: a GAS Bridge Assembly with four standard GAS can experiments, plus the CAPL Hitchhiker experiment to test a cooling system for EOS satellites and the Thermal Energy Storage (TES) GAS can experiment to do research on solar dynamic power for the Space Station.

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-69/mission-sts-69.html


 STS 70

General

Launch id	95035
Launch date	13 Jul 1995 at 13:41:55 UT
Launch site	Cape Canaveral LC39B
Type	Discovery #21
Crew	Tom Henricks (commander) Kevin Kregel (pilot) Nancy Currie (mission specialist) Dr. Donald Thomas (mission specialist) May Ellen Weber (mission specialist)
Landing date	22 Jul 1995 at 12:02 UT
Landing site	Cape Canaveral
Payload	B: TDRS 7

STS-70 marked another significant milestone with the first flight of the new Block I Space Shuttle main engine. Main Engine #1 - engine 2036 - features improvements that increase the reliability and safety margins of the main engines. SSME's No. 2 and No. 3 are the current design.

The Block I engine features improvements such as a new liquid oxidizer turbopump produced through a casting process that eliminates all but six of the 300 welds that exist in the current pump. A new two-duct powerhead improves fluid flows within the engine to decrease pressure and loads. A new single-coil heat exchanger in the powerhead eliminates all seven weld joints inside the engine, reducing wear, maintenance and post-flight inspections.

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-70/mission-sts-70.html


 STS 71

General

Launch id	95030
Launch date	27 Jun 1995 at 19:32 UT
Launch site	Cape Canaveral LC39A
Type	Atlantis #14
Crew
Landing date	7 Jul 1995 at 14:54 UT
Landing site	Cape Canaveral
Payload

Space Life Sciences (SL M) and first trim with Mir

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-71/mission-sts-71.html


 STS 73

General

Launch id	95056
Launch date	20 Oct 1995 at 13.53 UT
Launch site	Cape Canaveral LC39B
Type	Columbia #18
Crew
Landing date	5 Nov 1995 at 11:45 UT
Landing site	Cape Canaveral
Payload

Spacelab USML-2

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-73/mission-sts-73.html


 STS 74

General

Launch id	95061
Launch date	12 Nov 1995 at 12:30 UT
Launch site	Cape Canaveral LC39A
Type	Atlantis #15
Crew
Landing date	20 Nov 1995 at 17:01 UT
Landing site	Cape Canaveral
Payload	316GK Mir docking modules and supplies

2nd Mir docking

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-74/mission-sts-74.html


 STS 72

General

Launch id	96001
Launch date	11 Jan 1996 at 09:41 UT
Launch site	Cape Canaveral LC39B
Type	Endeavour #10
Crew	Brian Duffy Brent Jett Leroy Chiao Winston Scott Koichi Wakata (NASDA) Daniel Barry
Landing date	20 Jan 1996 at 07:42 UT
Landing site	Cape Canaveral
Payload	Spartan 206

SFU retrieval on 13 January

2 spacewalks to test out Space Station tools and equipment.

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-72/mission-sts-72.html


 STS 75

General

Launch id	96012
Launch date	22 Feb 1996 at 11:24 UT
Launch site	Cape Canaveral
Type	Columbia #19
Crew	Andrew Allen (commander) Dr. Scott Horowitz (pilot) Dr. Franklin Chang-Diaz (payload commander) Dr. Jeff Hoffmann (mission specialist) Claude Nicollier (mission specialist, ESA) Maurizio Cheli (mission specialist, ESA) Dr. Umberto Guidoni (mission specialist, ASI)
Landing date	9 Mar 1996
Landing site	Cape Canaveral
Payload

Deployment of the TTS 2 (first was on STS 46) also known as TSS 1R. Third flight of scientific investigations using the US Microgravity Payload (USMP) complement.

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-75/mission-sts-75.html


 STS 76

General

Launch id	96018
Launch date	22 Mar 1996
Launch site	Cape Canaveral
Type	Atlantis #16
Crew	Kevin Chilton (commander) Rick Searfoss (pilot) Ron Sega (payload commander) Linda Godwin (mission specialist) RichClifford (mission specialist) Shannon Lucid (mission specialist, to remain on Mir)
Landing date
Landing site
Payload

3rd Shuttle-Mir mission, Spacehab, SAREX

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-76/mission-sts-76.html


 STS 77

General

Launch id	96032
Launch date	19 May 1996 at 10:30 UT
Launch site	Cape Canaveral LC 39B
Type	Endeavour #11
Crew	John H. Casper: commandant Curtis L. Brown: pilot Daniel W. Bursch: mission specialist Mario Runco: mission specialist Marc Garneau (Canadian space agency): mission specialist Andrew S.W. Thomas: mission specialist
Landing date	29 May 1996 at 11:09 UT
Landing site	Cape Canaveral
Payload	Spartan 207 (launched and retrieved)

Spacehab 4

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-77/mission-sts-77.html


 STS 78

General

Launch id	96036
Launch date	20 Jun 1996 at 14:49 UT
Launch site	Cape Canaveral LC 39B
Type	Columbia #20
Crew	Tom Henricks: commander ?: pilot Susan J. Helms: mission specialist Richard M. Linnehan: mission specialist Charles E. Brady: mission specialist Jean-Jacques Favier (France, CEA/CNES): payload specialist Robert Brent Thirsk (Canadian space agency): payload specialist
Landing date	7 Jul 1996 at 12:36 UT
Landing site	Cape Canaveral
Payload

Spacelab, life and microgravity Spacehab (LMS), SAREX

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-78/mission-sts-78.html


 STS 79

General

Launch id	96057
Launch date	16 Sep 1996 at 08:55 UT
Launch site	Cape Canaveral
Type	Atlantis #17
Crew	Bill Readdy: commander 5 other crew members
Landing date	26 Sep 1996
Landing site	Cape Canaveral
Payload

Mir docking 4, SAREX

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-79/mission-sts-79.html


 STS 80

General

Launch id	96065
Launch date	19 Nov 1996 at 19:55:50 UT
Launch site	Cape Canaveral LC 39B
Type	Columbia #21
Crew	Cockrell, Rominger, Jernigan, Jones, Musgrave
Landing date	7 Dec 1996 at 11:49 UT
Landing site	Cape Canaveral
Payload	Spas 3 (launched and retrieved) WSF 3 (launched and retrieved)

SAREX

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-80/mission-sts-80.html


 STS 81

General

Launch id	97001
Launch date	12 Jan 1997 at 9:28 UT
Launch site	Cape Canaveral
Type	Atlantis #18
Crew	Michael A. Baker, Mission Commander  Brent W. Jett, Jr, Pilot  John M. Grunsfeld, Mission Specialist  Marsha S. Ivins, Mission Specialist  Peter J.K. Wisoff, Mission Specialist  Jerry M. Linenger, Mission Specialist
Landing date	22 Jan 1997 at 14:23 UT
Landing site	Cape Canaveral
Payload	none

Mir docking 5, SAREX

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-81/mission-sts-81.html


 STS 82

General

Launch id	97004
Launch date	11 Feb 1997 at 08:55 UT
Launch site	Cape Canaveral
Type	Discovery #22
Crew	Ken Bowersox (Commander) Scott Horowitz (Pilot) Mark C. Lee (Payload commander) Steve Hawley Gregory J. Harbaugh Steven L. Smith Joseph R. Tanner
Landing date	21 Feb 1997 at 08:32 UT
Landing site	Cape Canaveral
Payload	HST instruments

Second flight to service the Hubble Space Telescope

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-82/mission-sts-82.html


 STS 83

General

Launch id	97013
Launch date	4 Apr 1997 at 19:20 UT
Launch site	Cape Canaveral LC39A
Type	Columbia #22
Crew	James D. Halsell, Commander  Susan L. Still, Pilot  Janice E. Voss, Payload Commander  Donald A. Thomas, Mission Specialist  Michael L. Gernhardt, Mission Specialist  Roger Crouch, Payload Specialist  Greg Linteris, Payload Specialist
Landing date	8 Apr 1997 at 18:33 UT
Landing site	Cape Canaveral
Payload	none

Microgravity Science Laboratory (MSL-1), Sarex

One of the orbiter's three fuel cells malfunctioned shortly after launch, and flight rules require that all 3 must be operating. The fuel cells combine hydrogen and oxygen to make water and electricity. Therefore a Minimum Duration Flight (MDF) was performed.

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-83/mission-sts-83.html


 STS 84

General

Launch id	97023
Launch date	15 May 1997 at 08:08 UT
Launch site	Cape Canaveral LC39A
Type	Atlantis #19
Crew	Charles J. Precourt, Commander  Eileen M. Collins, Pilot  C. Michael Foale Carlos I. Noriega Edward T. Lu Jean-Francois Clervoy (ESA) Elena V. Kondakova (RSA)
Landing date	24 May 1997 at 13:27 UT
Landing site	Cape Canaveral
Payload	none

6th Mir docking

Michael Foale will stay aboard Mir and Jerry Linenger (STS 81) will come back to earth

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-84/mission-sts-84.html


 STS 85

General

Launch id	97039
Launch date	7 Aug 1997 at 14:41 UT
Launch site	Cape Canaveral LC39A
Type	Discovery #23
Crew	Curt Brown, commander Kent Rominger, pilot Jan Davis, payload commander Bob Curbeam Stephen Robinson Bjarni Tryggvason (Canada)
Landing date	19 Aug 1997 at 11:08 UT
Landing site	Cape Canaveral
Payload	Crista-Spas (launched and retrieved)

Crista-Spas mission

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-85/mission-sts-85.html


 STS 86

General

Launch id	97055
Launch date	26 Sep 1997 at 02:34 UT
Launch site	Cape Canaveral LC39A
Type	Atlantis #20
Crew	James Wetherbee, Commander  Michael Bloomfield, Pilot  Vladimar Titov, (RSA) Mission Specialist  Scott Parazynski, Mission Specialist  Jean-Loup Chretien, (CNES) Mission Specialist  Wendy Lawrence, Mission Specialist  David Wolf, Mission Specialist (left on Mir) + Michael Foale (retrieved from Mir)
Landing date	6 Oct 1997 at 21:55 UT
Landing site	Cape Canaveral
Payload	none

7th Mir docking mission

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-86/mission-sts-86.html


 STS 87

General

Launch id	97073
Launch date	19 Nov 1997
Launch site	Cape Canaveral LC39A
Type	Columbia #24
Crew	Kevin R. Kregel, Commander  Steven W. Lindsey, Pilot  Winston E. Scott, Mission Specialist  Kalpana Chawla, Mission Specialist  Takao Doi, (NASDA) Mission Specialist  Leonid K. Kadenyuk, (NSAU) Payload Specialist
Landing date	5 Dec 1997
Landing site	Cape Canaveral
Payload	Spartan 201-4 (launched and retrieved)

Microgravity (USMP 4)

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-87/mission-sts-87.html


 STS 88

General

Launch id	98069
Launch date	4 Dec 1998 at 08:35 UT
Launch site	Cape Canaveral LC 39A
Type	Endeavour #13
Crew	Robert D. Cabana, Mission Commander  Frederick W. Sturckow, Pilot  Nancy J. Currie, Mission Specialist  Jerry L. Ross, Mission Specialist  James H. Newman, Ph.D, Mission Specialist  Sergei K. Krikalev, Mission Specialist (Russia)
Landing date	15 Dec 1998
Landing site	Cape Canaveral
Payload	Unity (space station) SAC A MightySat 1

ISS-01-2A

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-88/mission-sts-88.html


 STS 89

General

Launch id	98003
Launch date	22 Jan 1998 at 02:48 UT
Launch site	Cape Canaveral LC 39A
Type	Endeavour #12
Crew	Terrence W. Wilcutt, Commander  Joe F. Edwards, Jr., Pilot  Bonnie J. Dunbar, Payload Commander  Michael P. Anderson, Mission Specialist  James F. Reilly, Mission Specialist  Salizhan Shakirovich Sharipov, Mission Specialist  Andrew S. W. Thomas, Mission Specialist
Landing date	31 Jan 1998 at 22:35 UT
Landing site	Cape Canaveral
Payload

Mir Docking 8

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-89/mission-sts-89.html


 STS 90

General

Launch id	98022
Launch date	17 Apr 1998 at 18:19 UT
Launch site	Cape Canaveral LC39B
Type	Columbia #25
Crew	Richard Searfoss, Commander  Scott Altman, Pilot  Richard Linnehan DVM, Mission Specialist  Dafydd Rhys Williams MD (CSA), Mission Specialist  Kathryn Hire, Mission Specialist  Dr. Jay Buckey, Payload Specialist  Dr. James Pawelczyk, Payload Specialist
Landing date	3 May 1998 at 16:09 UT
Landing site	Cape Canaveral
Payload	none

The Neurolab mission will carry out life science studies.


 STS 91

General

Launch id	98034
Launch date	2 Jun 1998 at 22:06 UT
Launch site	Cape Canaveral LC39A
Type	Discovery #24
Crew	Charles J. Precourt, Commander  Dominic L. Pudwill Gorie, Pilot  Wendy B. Lawrence, Mission Specialist  Franklin R. Chang-Diaz, Mission Specialist  Janet L. Kavandi, Mission Specialist  Valery Victorovitch Ryumin, Mission Specialist
Landing date	12 Jun 1998 at 18:00 UT
Landing site	Cape Canaveral
Payload	none

Mir Docking 9 and AMS (magnetic spectrometer to detect cosmic-ray antiprotons)

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-91/mission-sts-91.html

http://hpamsmi2.mi.infn.it/~wwwams/A_AMS.html


 STS 93

General

Launch id	99040
Launch date	23 Jul 1999 at 04:28 UT
Launch site	Cape Canaveral LC39B
Type	Columbia #26
Crew	Eileen M. Collins, Mission Commander  Jeffrey S. Ashby, Pilot  Steven A. Hawley, Mission Specialist  Catherine G. Coleman, Mission Specialist  Michel Tognini (CNES), Mission Specialist
Landing date	28 Jul 1999 at 03:20 UT
Landing site	Cape Canaveral
Payload	Chandra
External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-93/mission-sts-93.html


 STS 94

General

Launch id	97032
Launch date	1 Jul 1997 at 18:02 UT
Launch site	Cape Canaveral LC39A
Type	Columbia #23
Crew	James D. Halsell, Commander  Susan L. Still, Pilot  Donald A. Thomas, Mission Specialist  Greg Linteris, Payload Specialist Janice E. Voss, Payload Commander  Michael L. Gernhardt, Mission Specialist  Roger Crouch, Payload Specialist
Landing date	17 Jul 1997 at 10:46 UT
Landing site	Cape Canaveral
Payload	none

Re-run of the aborted STS 83 mission

Microgravity Science Laboratory replay (MSL-1R), Sarex

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-94/mission-sts-94.html


 STS 95

General

Launch id	98064
Launch date	29 Oct 1998 at 19:19 UT
Launch site	Cape Canaveral LC39A
Type	Discovery #25
Crew	Curtis L. Brown, Commander  Steven W. Lindsey, Pilot  Scott E. Parazynski, Mission Specialist  Stephen K. Robinson, Mission Specialist  Pedro Duque, (ESA) Mission Specialist  Chiaki Mukai, (NASDA) Payload Specialist  John H. Glenn, Payload Specialist
Landing date	7 Nov 1998 at 17:03 UT
Landing site	Cape Canaveral
Payload	B: Pansat C: Spartan 201-5
External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-95/mission-sts-95.html


 STS 96

General

Launch id	99030
Launch date	27 May 1999 at 10:49 UT
Launch site	Cape Canaveral LC 39B
Type	Discovery #26
Crew	Kent V. Rominger, Commander  Rick D. Husband, Pilot  Ellen Ochoa, Mission Specialist  Tamara E. Jernigan, Mission Specialist  Daniel T. Barry, Mission Specialist  Julie Payette, (Canada) Mission Specialist  Valery Ivanovich Tokarev, (Russia) Mission Specialist
Landing date	6 Jun 1999
Landing site	Cape Canaveral
Payload	Starshine

ISS-02-2A.1

External resources

http://www.ksc.nasa.gov/shuttle/missions/sts-96/mission-sts-96.html


 Taurus

by Jean-Jacques Serra

In 1989 OSC was selected by DARPA to design the Standard Small Launch Vehicle (SSLV). This solid 4-stage rocket called Taurus is made of the first stage of the MX and the 3 stages of Pegasus. The base stage, called stage-0, is a Thiokol TU 903 of 8.4 m long, 2.34 m diameter and 48 tons. It delivers the 3 Pegasus stages at 38000 m altitude at 2030 m/s.

In the future (standard type), the stage-0 will be a Thiokol Castor 120 which is a MX motor modified to provide a weaker acceleration (6.5 G max). Taurus is 27.5 m in height and can launch 1.36 tons in LEO.

Taurus versions

Prototype	Taurus
Standard Type (with Castor-120)	Taurus-120
stretched standard type	Taurus-120XL
stretched standard type with strap-ons	Taurus-120XL/S
Taurus launches

#	Launch id	Payload	Launch Date	Site	Type	Status/Comment (orbit in perigee x apogee x inclination x period)
1	94017	A: USA 101 B: USA 102	13 Mar 1994 at 22:32 UT	V 576E		540 km x 560 km x 105°
2	98007	A: GFO 1 B: Orbcomm FM 3 C: Orbcomm FM 4 D: Celestis 2	10 Feb 1998 at 13:20 UT	V 576E	120	775 km x 108°
3	98055	A: Stex	3 Oct 1998 at 10:04 UT	V 576E


Thor (launch vehicle)
 Thor

by Jean-Jacques Serra

Origins

Thor Able

Thor Ablestar

Thor Agena

Thor Delta

Thor with solid top stage (Altair, Burner)

Origin: first generation of American Intermediate Range Ballistic Missiles

Until 1953 the USAF had stressed on aerodynamic missiles (while the Army was developping the Jupiter) because they believed long distance ballistic missiles would not appear before ten years. The construction of Thor wasn't awarded to Douglas Aircraft before December 1955. The program was given a very high priority and the first missile was delivered to the USAF in October 1956.

The MB-1 propulsion system was made of a Rocketdyne LR79 (liquid oxygen and kerosene) engine with 670 kN derived from Jupiter and Atlas' booster. An LR101 vernier rocket on each side of the missile' base controled the roll and the final ajustement of the speed after the main engine shutdown. The missile used Atlas' Reentry Vehicle, measured 2.44 m in diameter and 19.8 m in height, and weighed over 46 tons.

The first four tests carried out from 25 January 1957 on were failures. The first successful launch occured on 20 September and was commissioned in 1959.

Thor's propulsion system quickly evolved to an MB-3 version used by IRBMs and space launchers, especially by USAF's Thor SLV-2 and NASA's Thor Delta launchers. In the seventies the MB-3 motor was used by the Japanese N-1, N-2 and H-1 launch vehicles. An improvement program conducted between 1957 and 1959 named X-1 leaded to an H-1 version designed for Saturn-1. Later on H-1 was modified for the propulsion of Thor Deltas (39xx series) and became RS-27. The latest version RS-27A intended to Delta-2 launchers is optimized for greater performance at high altitude.

Thor propulsion system

Designation	Year of first launch	Main engine Thrust (kN)	Main engine SI (sec.)	Application
MB-1	1957	600	250	IRBM
MB-3	1958	670, 735, 755 (1)	252	IRBM, launchers
RS-27	1973	920-1030 (2)	263-295 (2)	Delta
RS-27A	1991	890-1055 (2)	255-305 (2)	Delta-2

Notes: (1) Blk 1, 2 and 3; (2) values given at sea level in vacuum

In 1963 Thor's thrust became insufficient to carry out its missions. The solution (innovative at that time) found was to enhance it with 3 solid fuel strap on Thiokol Castor boosters. This resulted in TAT: Thrust Augmented Thor. Those boosters were used grouped by 3 then 6 and up to 9. After 1975 when the only Thor first stage used was the Delta the Castor-2 boosters were replaced by the 1 m-diameter Castor-4.

The burn duration of Thor (160 seconds) was also enhanced by lenghtening its tanks. This gave birth to the LTT (Long Tank Thor) for which the burning time reached about 220 seconds, used from 1966 wih Agena stages and from 1968 with Delta stages. The first stage was streched again in early 70' giving ELTT (Extended Long Tank Thor); the burning time wasn't much modified but the thrust was increased. The Delta-2 version, used since 1989, was lengthened in order to obtain a 265 seconds burning time.


Thor

[launch vehicle index]

Origins

Thor Able

Thor Ablestar

Thor Agena

Thor Delta

Thor with solid top stage (Altair, Burner)


 Thor Able

by Jean-Jacques Serra

listing by Gunter Krebs

Thor used with Vanguard top stages

In 1958 the only top stages available for space launches were those of Vanguard. The second stage was 8.5 m long and 0.9 m in diameter. It was equipped with an adjustable Aerojet AJ10 motor (nitric acid/UDMH) capable of a 33 kN thrust during 120 seconds. The spin-stabilized third stage was equipped with a solid fuel motor of 14 kN and 30 second burn duration. The Thor Able rocket was 26.9 m high and weighed over 50 tons.

Thor Able was tested in April and May 1958 with the intercontinental launch of Reentry vehicles containing a mouse. But the first 3 space launches carrying Pioneer probes to the Moon between August and November 1958 ended as 2 failures and 1 partial success.

The launcher was used until 1961 to launch a scientific satellite (Explorer) a interplanetary probe (Pioneer) and a meteorological satellite (Tiros).

Thor Able launches

# and serial	Launch id	Payload	Launch date	Type	Status (orbit in perigee x apogee x inc. x period)
1, 116	n/a	ARTV 1 (suborbital)	23 Apr 1958	DM18 Able	Failure: Thor exploded after 146 s
2, 118	n/a	ARTV 2 (suborbital)	10 Jul 1958	DM18 Able
3, 119	n/a	ARTV 3 (suborbital)	23 Jul 1958	DM18 Able
4, 127	n/a	Pioneer 0 (Moon)	17 Aug 1958	DM18 Able 1	Failure: Thor exploded after 17 s
5, 130	n/a	Pioneer 1 (Moon)	11 Oct 1958	DM18 Able 1	Partial failure: 3rd stage produced unsufficient thrust
6, 129	n/a	Pioneer 2 (Moon)	08 Nov 1958	DM18 Able 1	Failure: 3rd stage failed
7, 128	n/a	PGRTV 1 (suborbital)	23 Jan 1959	DM18 Able 2	Partial failure: 1st stage shut down at wrong time
8, 131	n/a	PGRTV 2 (suborbital)	28 Feb 1959	DM18 Able 2
9, 132	n/a	PGRTV 3 (suborbital)	21 Mar 1959	DM18 Able 2
10, 133	n/a	PGRTV 4 (suborbital)	8 Mar 1959	DM18 Able 2
11, 135	n/a	PGRTV 5 (suborbital)	20 May 1959	DM18 Able 2
12, 137	n/a	PGRTV 6 (suborbital)	11 Jun 1959	DM18 Able 2
13, 134	59004	Explorer 06	07 Aug 1959	DM18 Able 3
14, 136	n/a	Transit 1A	17 Sep 1959	DM18 Able 2	Failure: 3rd stage failed
15, 219	60001	Pioneer 5	11 Mar 1960	DM18 Able 4	Probe to solar orbit
16, 148	60002	Tiros 01	01 Apr 1960	DM18 Able 2

Notes: all launches from Cape Canaveral


 Thor Ablestar

by Jean-Jacques Serra

listing by Gunter Krebs

The Ablestar stage was developped for the US Navy by Space General Co. It was 5.3 m long and 1.63 m in diameter, equipped with an adjustable Aerojet AJ10-104 motor (nitric acid/UDMH). This engine could be reignited and provided a 35 kN thrust during about 300 seconds. Thor Ablestar was 24.2 m high for about 54 tons.

Thor Ablestar was used to launch navigation satellites (Transit) so as numerous technologic and scientific spacecrafts (Solrad) for the US Navy. Some satellites were launched together with NASA. Thor Ablestar was used during 5 years and achieved the first in-orbit reignition in April 1960 and the first double, triple and sextuple -satellite launch.

Thor Ablestar launches

# and serial	Launch id	Payload	Launch date	Site	Type	Status (orbit in perigee x apogee x inc. x period)
1, 257	60003	Transit 1B	13 Apr 1960	C	DM21 AbleStar	373 x 748 x 51.3 x 95.8
2, 281	60007	Transit 2A Solrad 01	22 Jun 1960	C	DM21 AbleStar
3, 262	n/a	Courier 1A	18 Aug 1960	C	DM21 AbleStar	Failure: Thor failed after 134 s
4, 293	60013	Courier 1B	04 Oct 1960	C	DM21 AbleStar
5, 283	n/a	Transit 3A Solrad 2	30 Nov 1960	C	DM21 AbleStar	Failure: Thor shud down too early
6, 313	61007	Transit 3B LOFTI	22 Feb 1961	C	DM21 AbleStar	Partial failure: satellites failed to separate 188 x 822 x 28.4 x 96.2
7, 315	61015	Transit 4A Solrad 03	29 Jun 1961	C	DM21 AbleStar	Partial failure: Injun 1 and Solrad 3 failed to separate
8, 305	61031	Transit 4B Traac	15 Nov 1961	C	DM21 AbleStar
9, 311	n/a	Lofti 2 Secor 1 Solrad 4 Surcal 1	24 Jan 1962	C	DM21 AbleStar	Failure: AbleStar produced unsufficient thrust Surcal 1 was fixed to AbleStar
10, 314	n/a	Anna 1A	10 May 1962	C	DM21 AbleStar	Failure: AbleStar failed to ignite
11, 319	62060	Anna 1B	31 Oct 1962	C	DM21 AbleStar
12, 375	63038	Transit 5BN1 5E1	28 Sep 1963	V	DM21 AbleStar
13, 385	63049	Transit 5BN2 5E3	05 Dec 1963	V	DM21 AbleStar
14, 379	n/a	Transit 5BN3	21 Apr 1964	V	DM21 AbleStar	Failure: AbleStar failed
15, 250	64063	Transit-O 1 (OPS 5798, NNS 30010) Calsphere 1 & 2	06 Oct 1964	V	DM21 AbleStar	1035 x 1080 x 89.9 x 106.6
16, 423	64083	Transit-O 2 (OPS 6582 NNS 30020) 5E5	13 Dec 1964	V	DM21 AbleStar	1027 x 1086 x 90 x 106.3
17, 440	65017	Transit-O 3 (OPS 7087 NNS 30030) Secor 02	11 Mar 1965	V	DM21 AbleStar
18, 447	65048	Transit-O 4 (OPS 8480, NNS 30040)	24 Jun 1965	V	DM21 AbleStar	1025 x 1114 x 90 x 106.9
19, 455	65065	Transit-O 5 (OPS 8464, NNS 30050) Surcal (x3?) Dodecapole 2 Tempsat 1	13 Aug 1965	V	DM21 AbleStar	1089 x 1194 x 90 x 108.2

Notes: in the launcher date & site column C stands for Cape Canaveral and V for Vandenberg.


 Thor Agena

by Jean-Jacques Serra

The Agena stage was developped by Lockheed for the USAF. The first Thor Agena (with Discoverer 1) was 23.2 m in height and weighed 48.5 tons. This version was Agena-A equipped with a Bell 8096 motor of 67 kN during 2 minutes. It couldn't be re-ignited on the contrary of the 1960 Agena-B. The Agena-D version featured a more powerful engine with 71 kN delivered during 4 minutes. All those rockets had the same diameter (1.52 m) and a variable length depending on the payload.

Agena was used from 1959 to 1987 becoming the most used American top-stage with 350 launches mainly with military payloads:

- reconnaissance satellites (Discoverer, Keyhole) sometimes orbited with military payloads (Ferret) or civilian payloads (Oscar).

- ELINT satellites: large ones were launched as unique payload and small size ones together with reconnaissance satellites.

But Thor Agena also launched:

- scientific satellites (Solrad, Starad, STP), geodesy satellites (Secor, Starflash, Topo) and technological spacecrafts (TRS, GGSE, LOFTI, Surcal, LCS, Timation, SERT).

- satellites for NASA (Alouette, Explorer 31, Echo 2, Pageos, OGO, Nimbus)

Thor Agena launches

#	Launch id	Payload	Launch date	Type	Perigee (km)	Apogee (km)	inc. (deg)	period (min)
1	59002	Discoverer-1	28 Feb 1959	T AA	163	968	89.7	96
2	59003	Discoverer-2	13 Apr 1959	T AA	239	346	89.9	90.4
3	n/a	Discoverer-3	03 Jun 1959	T AA	failure
4	n/a	Discoverer-4 (KH-1 9001)	25 Jun 1959	T AA	failure
5	59005	Discoverer-5 (KH-1 9002)	13 Aug 1959	T AA	217	739	80	94.2
6	59006	Discoverer-6 (KH-1 9003)	19 Aug 1959	T AA	212	848	84	95.3
7	59010	Discoverer-7 (KH-1 9004)	07 Nov 1959	T AA	159	847	81.6	94.7
8	59011	Discoverer-8 (KH-1 9005)	20 Nov 1959	T AA	187	1 679	80.7	103.7
9	n/a	Discoverer-9 (KH-1 9006)	04 Feb 1960	T AA	failure
10	n/a	Discoverer-10 (KH-1 9007)	19 Feb 1960	T AA	failure
11	60004	Discoverer-11 (KH-1 9008)	15 Apr 1960	T AA	170	589	80.1	92.2
12	n/a	Discoverer-12	29 Jun 1960	T AA	failure
13	60008	Discoverer-13	10 Aug 1960	T AA	259	701	82.9	94
14	60010	Discoverer-14 (KH-1 9009)	18 Aug 1960	T AA	186	805	79.7	94.6
15	60012	Discoverer-15 (KH-1 9010)	13 Sep 1960	T AA	209	724	80.9	94.2
16	n/a	Discoverer-16 (KH-1 9011)	26 Oct 1960	T AB	failure
17	60015	Discoverer-17 (KH-1 9012)	12 Nov 1960	T AB	187	991	81.7	96.5
18	60018	Discoverer-18 (KH-1 9013)	07 Dec 1960	T AB	233	661	81.5	93.7
19	60019	Discoverer-19	20 Dec 1960	T AB	206	520	83.4	93
20	61005	Discoverer-20 (KH-5 9014A)	17 Feb 1961	T AB	288	786	80.9	95.4
21	61006	Discoverer-21	18 Feb 1961	T AB	240	1 069	80.7	97.9
22	n/a	Discoverer-22 (KH-2 9015)	30 Mar 1961	T AB	failure
23	61011	Discoverer-23 (KH-5 9016A)	08 Apr 1961	T AB	295	651	82.3	94.1
24	n/a	Discoverer-24 (KH-5 9018A)	08 Jun 1961	T AB	failure
25	61014	Discoverer-25 (KH-2 9017)	16 Jun 1961	T AB	222	409	82.1	90.9
26	61016	Discoverer-26 (KH-2 9019)	08 Jul 1961	T AB	235	809	82.9	95
27	n/a	Discoverer-27 (KH-5 9025A)	21 Jul 1961	T AB	failure
28	n/a	Discoverer-28 (KH-2 9028)	03 Aug 1961	T AB	failure
29	61023	Discoverer-29 (KH-3 9023)	30 Aug 1961	T AB	225	555	82.1	91.5
30	61024	Discoverer-30 (KH-3 9022)	12 Sep 1961	T AB	235	546	82.7	92.4
31	61026	Discoverer-31 (KH-3 9024)	17 Sep 1961	T AB	235	396	82.7	90.9
32	61027	Discoverer-32 (KH-3 9025)	13 Oct 1961	T AB	234	395	81.7	90.8
33	n/a	Discoverer-33 (KH-3 9026)	23 Oct 1961	T AB	failure
34	61029	Discoverer-34 (KH-3 9027)	05 Nov 1961	T AB	227	1 011	82.5	97.1
35	61030	Discoverer-35 (KH-3 9028)	15 Nov 1961	T AB	238	278	81.6	89.7
36	61034	A: Discoverer-36 (KH-3 9029) B: Oscar 01	12 Dec 1961	T AB	238	450	81.2	91.8
37	n/a	Discoverer-37 (KH-3 9030)	13 Jan 1962	T AB	failure
38	62004	?	21 Feb 1962	T AB	167	374	82	90
39	62005	Discoverer-38 (KH-4 9031)	27 Feb 1962	T AB	208	341	82.2	90
40	62011	KH-4 #2   (9032)	18 Apr 1962	T AB	199	297	73.5	90.9
41	62017	KH-4 #3   (9033)	29 Apr 1962	T AB	177	364	73.1	91.1
42	62018	KH-5 #5   (9034A)	15 May 1962	T AB	305	634	82.3	94
43	62021	KH-4 #4   (9035)	30 May 1962	T AB	199	319	74.1	89.7
44	62022	A: KH-4 #5   (9036) B: Oscar 02	02 Jun 1962	T AB	211	385	74.3	90.5
45	62024	ELINT 1#1	18 Jun 1962	T AB	370	411	82.1	92.4
46	62026	KH-4 #6   (9037)	23 Jun 1962	T AB	213	293	75.1	89.6
47	62027	KH-4 #7   (9038)	28 Jun 1962	T AD	211	689	76	93.6
48	62031	KH-4 #8   (9039)	21 Jul 1962	T AB	208	381	70.9	90.4
49	62032	KH-4 #9   (9040)	28 Jul 1962	T AB	222	293	71.1	90.6
50	62034	KH-4 #10 (9041)	02 Aug 1962	T AD	204	418	82.2	90.8
51	62042	KH-4 #11 (9044)	29 Aug 1962	T AD	187	400	65.2	90.4
52	62044	KH-5 #6   (9042A)	01 Sep 1962	T AB	333	637	82.8	94.4
53	62046	KH-4 #12 (9043) + TRS-1	17 Sep 1962	T AB	204	668	81.8	93.3
54	62049	Alouette 1	29 Sep 1962	T AB	996	1 032	80.5	105.5
55	62050	KH-4 #13 (9045)	29 Sep 1962	T AD	203	376	65.4	90.3
56	62053	KH-5 #7   (9046A)	09 Oct 1962	T AB	213	427	82	91
57	62058	Starad 1	26 Oct 1962	T AD	198	5 570	71.4	147.9
58	62063	KH-4 #14 (9047)	05 Nov 1962	T AB	208	409	75	90.7
59	62065	KH-4 #15 (9048)	24 Nov 1962	T AB	204	337	65.1	89.9
60	62066	KH-4 #16 (9049)	04 Dec 1962	T AD	194	273	65.1	89.2
61	62067	A: Black Sphere B: Injun 3 C: Surcal 1 D: Surcal 1A E: Calsphere 1A	13 Dec 1962	T AD	235	2 785	70.4	116.3
62	62069	KH-4 #17 (9050)	14 Dec 1962	T AD	199	392	71	90.5
63	63002	KH-4 #18 (9051)	07 Jan 1963	T AD	205	399	82.2	90.5
64	63003	ELINT 1#2	16 Jan 1963	T AB?D?	459	533	81.9	94.7
65	n/a	KH-4 #19 (9052)	28 Feb 1963	TAT AD	failure
66	n/a	KH-6 #1   (8001)	18 Mar 1963	TAT AD	failure
67	63007	KH-4 #20 (9053)	01 Apr 1963	T AD	201	408	75.4	90.7
68	n/a	KH-5 #8   (9055A)	26 Apr 1963	T AD	failure
69	63016	KH-6 #2   (8002)	18 May 1963	TAT AD	153	497	74.5	91.1
70	63019	KH-4 #21 (9054)	13 Jun 1963	TAT AD	192	419	81.9	90.7
71	63021	A: classified B: LOFTI 2A C: Solrad 06A D: Radose 112 E: FTV 1292 F: Surcal 1B	15 Jun 1963	T AD	185	890	69.9	93
72	63025	KH-4 #22 (9056)+ HitchHiker-1	27 Jun 1963	TAT AD	196	396	81.6	90.5
73	63027	ELINT 1#3	29 Jun 1963	T AB	484	536	82.3	94.8
74	63029	KH-4 #23 (9057)	18 Jul 1963	T AD	194	387	82.9	90.4
75	63032	KH-6 #3   (8003)	31 Jul 1963	TAT AD	157	411	75	90.4
76	63034	KH-4A #1   (1001)	24 Aug 1963	TAT AD	225	322	75	89.4
77	63035	KH-5 #9   (9058A) + Ferret	29 Aug 1963	T AD	292	324	81.9	90.8
78	63037	KH-4A #2   (1002)	24 Sep 1963	TAT AD	161	441	74.9	90.6
79	63042	KH-5 #10 (9059A) + Ferret	29 Oct 1963	TAT AD	279	345	89.9	90.8
80	n/a	KH-4 #24 (9060)	09 Nov 1963	T AD	failure
81	63048	KH-4 #25 (9061)	27 Nov 1963	T AD	175	386	70	90.2
82	63055	KH-4 #26 (9062) + Ferret	21 Dec 1963	TAT AD	176	355	64.9	90
83	64001	A: US Navy classified B: GGSE 1 C: Secor 01B D: Solrad 07A	11 Jan 1964	T AD	905	935	69.9	103.5
84	64002	(2)	19 Jan 1964	T AD	810	825	99.1	101.3
85	64004	Echo 2	25 Jan 1964	T AB	1 092	1 316	81.5	108.9
86	64008	KH-4A #3   (1004)	15 Feb 1964	TAT AD	179	444	75	90.9
87	64011	ELINT 1#4	28 Feb 1964	T AD	479	520	82	94.7
88	n/a	KH-4A #4   (1003)	24 Mar 1964	TAT AD	failure
89	64022	KH-4A #5   (1005)	27 Apr 1964	TAT AD	178	446	79.9	90.8
90	64026 or 027	KH-4A #6   (1006)	05 Jun 1964	TAT AD	149	429	80	90.3
91	64030	KH-5 #11 (9065A) + Starflash-1A	13 Jun 1964	T AD	350	364	115	91.7
92	64031	(2)	18 Jun 1964	T AD	828	842	99.8	101.6
93	64032	KH-4A #7   (1007)	19 Jun 1964	TAT AD	176	462	85	90.9
94	64035	ELINT 1#5	03 Jul 1964	T AD	501	529	82.1	94.9
95	64037	KH-4A #8   (1008)	10 Jul 1964	TAT AD	180	461	85	91
96	64043	KH-4A #9   (1009)	05 Aug 1964	TAT AD	182	436	80	90.7
97	64048	KH-5 #11 (9065A) + Starflash-1B	21 Aug 1964	T AD	349	363	115	91.6
98	64052	Nimbus 1	28 Aug 1964	T AB	429	937	98.4	98.7
99	64056	KH-4A #10 (1010)	14 Sep 1964	TAT AD	238	466	85	90.9
100	64061	KH-4A #11 (1011)	05 Oct 1964	TAT AD	182	440	78	90.7
101	64067	KH-4A #12 (1012)	17 Oct 1964	TAT AD	189	416	75	90.6
102	64071	KH-4A #13 (1013)	02 Nov 1964	TAT AD	180	448	79.9	90.7
103	64072	ELINT 1#6	04 Nov 1964	T AD	512	526	82	95.1
104	64075	KH-4A #14 (1014)	18 Nov 1964	TAT AD	180	339	70	89.7
105	64085	KH-4A #15 (1015)	19 Dec 1964	TAT AD	183	410	75	90.5
106	64087	?	21 Dec 1964	TAT AD	238	264	70.1	89.5
107	65002	KH-4A #16 (1016)	15 Jan 1965	TAT AD	180	420	75	90.5
108	65013	KH-4A #17 (1017)	25 Feb 1965	TAT AD	177	377	75.1	90.1
109	65016	A: Solrad 06B B: GGSE 2 C: GGSE 3 D: Solrad 07B E: Secor 03 F: Oscar 03 G: Surcal 2 H: Porcupine 1 (Dodecapole 1)	09 Mar 1965	T AD	910	939	70.1	103.5
110	65026	KH-4A #18 (1018)	25 Mar 1965	TAT AD	186	265	96.1	89.1
111	65033	KH-4A #19 (1019)	29 Apr 1965	TAT AD	178	473	85	91
112	65037	KH-4A #20 (1021)	18 May 1965	TAT AD	198	331	75	89.7
113	65045	KH-4A #21 (1020)	09 Jun 1965	TAT AD	176	362	75.1	89.8
114	65055	ELINT 1#7	17 Jul 1965	T AD	471	512	70.2	94.5
115	65057	KH-4A #22 (1022)	19 Jul 1965	TAT AD	182	464	85.1	91
116	65067	KH-4A #23 (1023)	17 Aug 1965	TAT AD	180	407	70	90.4
117	n/a	Starad 2	02 Sep 1965	TAT AD	failure
118	65074	KH-4A #24 (1024)	22 Sep 1965	TAT AD	191	364	80	90
119	65079	KH-4A #25 (1025)	05 Oct 1965	TAT AD	203	323	75	89.8
120	65081	OGO-2	14 Oct 1965	TAT AD	415	1 517	87.4	104.4
121	65086	KH-4A #26 (1026)	28 Oct 1965	TAT AD	176	430	75	90.5
122	65098	Alouette 2 Explorer 31	29 Nov 1965	Thor A	505	2 987	79.8	121.4
123	65102	KH-4A #27 (1027)	09 Dec 1965	TAT AD	183	437	80	90.7
124	65110	KH-4A #28 (1028)	24 Dec 1965	TAT AD	178	446	80	90.8
125	66007	KH-4A #29 (1029)	02 Feb 1966	TAT AD	185	425	75.1	90.6
126	66009	ELINT 1#8	09 Feb 1966	T AD	508	512	82.1	94.8
127	66018	KH-4A #30 (1030)	09 Mar 1966	TAT AD	178	432	75	90.6
128	66029	KH-4A #31 (1031)	07 Apr 1966	TAT AD	193	312	75.1	89.6
129	n/a	KH-4A #32 (1032)	03 May 1966	TAT AD	failure
130	66040	Nimbus 2	15 May 1966	TAT AD	1 103	1 179	100.3	108.2
131	66042	KH-4A #33 (1033)	24 May 1966	TAT AD	179	271	66	89
132	66055	KH-4A #34 (1034)	21 Jun 1966	TAT AD	194	367	80.1	90.2
133	66056	Pageos	24 Jun 1966	TAT AD	4 207	4 271	87.1	181.4
134	66072	KH-4A #35 (1035)	09 Aug 1966	LTTAT AD	194	287	100.1	89.4
135	66085	KH-4A #36 (1036)	20 Sep 1966	TAT AD	188	442	85.1	90.9
136	66102	KH-4A #37 (1037)	08 Nov 1966	TAT AD	172	318	100.1	89.4
137	66118	ELINT 1#9	29 Dec 1966	T AD	486	496	75	94.4
138	67002	KH-4A #38 (1038)	14 Jan 1967	TAT AD	180	380	80.1	90.1
139	67015	KH-4A #39 (1039)	22 Feb 1967	TAT AD	180	380	80	90.1
140	67029	KH-4A #40 (1040)	30 Mar 1967	TAT AD	167	326	85	89.5
141	67043	KH-4A #41 (1041) + Ferret	09 May 1967	LTTAT AD	200	777	85.1	94.4
142	67053	A: navigation satellite (OPS 5712) C: GGSE 4 D: GGSE 5 E: Timation 1 F: Surcal 159 J: Surcal 150B	31 May 1967	T AD	914	928	70	103.5
143	67062	KH-4A #42 (1042) + Ferret	16 Jun 1967	LTTAT AD	181	367	80	90
144	67071	ELINT 1#10	25 Jul 1967	T AD	390	582	75.1	94.3
145	67073	OGO 4	28 Jul 1967	TAT AD	411	903	86	97.9
146	67076	KH-4A #43 (1043)	07 Aug 1967	LTTAT AD	174	346	79.9	89.7
147	67087	KH-4B #1   (1101)	15 Sep 1967	LTTAT AD	150	389	80.1	89.9
148	67109	KH-4A #44 (1044) + Ferret	02 Nov 1967	LTTAT AD	183	410	81.5	90.5
149	67122	KH-4B #2   (1102)	09 Dec 1967	LTTAT AD	158	237	81.7	88.5
150	68004	ELINT 1#11	17 Jan 1968	T AD	450	576	75.2	94.5
151	68008	KH4A #45 (1045) + Ferret	24 Jan 1968	LTTAT AD	176	430	81.5	90.6
152	68020	KH-4A #46 (1046) + Ferret	14 Mar 1968	LTTAT AD	178	391	83	90.2
153	68039	KH-4B #3   (1103)	01 May 1968	LTTAT AD	164	243	83.1	88.6
154	n/a	Nimbus 3A Secor-10	18 May 1968	TAT AD	failure
155	68052	KH-4A #47 (1047) + Ferret	20 Jun 1968	LTTAT AD	193	326	85	89.7
156	68065	KH-4B #4   (1104)	07 Aug 1968	LTTAT AD	152	257	82.1	88.6
157	68078	KH-4A #48 (1048) + Ferret	18 Sep 1968	LTTAT AD	167	343	83	90.1
158	68086	ELINT 2#1	05 Oct 1968	T AD	483	511	75	94.6
159	68098	KH-4B #5   (1105)	03 Nov 1968	LTTAT AD	150	288	82.2	88.9
160	68112	KH-4A #49 (1049) + Ferret ABM	12 Dec 1968	LTTAT AD	169	248	81	88.7
161	69010	KH-4B #6   (1106) + Ferret ABM	05 Feb 1969	LTTAT AD	178	239	81.5	88.7
162	69026	KH-4A #50 (1050) + Ferret	19 Mar 1969	LTTAT AD	179	241	83	88.7
163	69037	Nimbus 3 Secor 13	14 Apr 1969	TAT AD	1 075	1 130	99.9	107.4
164	69041	KH-4A #51 (1051) + Ferret	02 May 1969	LTTAT AD	179	326	66	89.5
165	69051	OGO 6	05 Jun 1969	TAT AD	397	1 089	82	99.7
166	69063	KH-4B #7   (1107)	24 Jul 1969	LTTAT AD	187	211	75	88.5
167	69065	ELINT 2#2	31 Jul 1969	LTTAT AD	153	574	75	91.5
168	69079	KH-4A #52 (1052) + Ferret	22 Sep 1969	LTTAT AD	180	250	85	88.8
169	?	Anonymous ELINT ? Timation 2A nonymous (5) Tempsat 2 Soical Cylinder Soical Cone	30 Sep 1969	TAT AD	450	480	70	93.9
170	69105	KH-4B #8   (1108)	04 Dec 1969	LTTAT AD	159	251	81.5	88.6
171	70009	SERT-2	04 Feb 1970	TAT AD	995	1 006	99.1	105
172	70016	KH-4B #9   (1109) + Ferret	04 Mar 1970	LTTAT AD	159	167	88	87.7
173	70025	Nimbus 4 Topo-1 (SECOR)	08 Apr 1970	TAT AD	1 093	1 107	99.8	107
174	70040	KH-4B #10 (1110) + Ferret	20 May 1970	LTTAT AD	162	246	83	88.6
175	70054	KH-4B #11 (1111)	23 Jul 1970	LTTAT AD	158	398	60	90
176	70066	ELINT 2#3	26 Aug 1970	LTTAT AD	484	504	75	94.5
177	70098	KH-4B #12 (1112) + Ferret	18 Nov 1970	LTTAT AD	185	232	83	88.7
178	71012	KH-4B #13 (1113)	17 Feb 1971	LTTAT AD	failure
179	71022	KH-4B #14 (1114)	24 Mar 1971	LTTAT AD	158	246	81.5	88.6
180	71060	ELINT 2#4	16 Jul 1971	LTTAT AD	488	507	75	94.6
181	71076	KH-4B #15 (1115) + Ferret	10 Sep 1971	LTTAT AD	156	244	74.9	88.5
182	71089	STP-1 (ASTEX)	17 Oct 1971	LTTAT AD	772	803	92.7	100.6
183	71110	NOSS (experimental)	14 Dec 1971	LTTAT AD	984	998	70	104.9
184	72032	KH-4B #16 (1116)	19 Apr 1972	LTTAT AD	154	277	81.5	88.8
185	72039	KH-4B #17 (1117)	25 May 1972	LTTAT AD	158	305	96.3	89.2
Notes: in the type column, AA, AB & AD stand for Agena A, B et D; T stands for Thor, TAT for Thrust Augmented Thor and LTTAT for Long Tank Thrust Augmented Thor. All launches from Vandenberg.

Additional payloads

Ferret: U.S. piggyback electronic intelligence gathering (60 kg)

1) with KH-5 satellites (Thor and TAT Agena): 3 ferrets

2) with KH-7 satellites (Atlas Agena): 8 ferrets

3) with KH-4A/B (LTTAT Agena): 16 ferrets of which 2 ferrets ABM

4) with KH-9 (Titan 3D and 34D): 14 ferrets of which 4 ferrets ABM (plus a failure on April 18, 1986)

5) USA 41 (STS-28): 1 ferret ?

HitchHiker 1 (80 kg) Measurement of radiation in the Earth's Van Allen belts; Returned data for three months.

Starflash 1A/B : Geodetic function

TRS 1 (Tetraedral Research Satellite) = ERS 2 (Environmental Research Satellite)

Mass = 667 g; Tetraedral shape measuring 15 cm across the base; 28 solar cells producing 1.2 W; 1 m long antenna; Measurement of radiation from the Starfish nuclear detonation; ERS 2 failed to eject from the KH-4/Agena assembly and was unusable.

Main payloads

ELINT (1st generation) : U.S. electronic intelligence gathering (700 kg)

Launched at six-months intervals, a total of eleven 1st generation ELINT satellites were flown on Thor-Agena B and Thor-Agena D.

ELINT (2nd generation) : U.S. electronic intelligence gathering (900 kg)

On-board processor to analyze electronic data; A total of four 2nd generation ELINT satellites were flown on LTTAT-Agena D in 1968, 1969, 1970 and 1971.

NOSS (700 kg) Navy Ocean Surveillance System

Three separate satellites.

Starad 1 (1100 kg) Measurement of radiation from the Starfish nuclear detonation

End of ops : 18 Jan 1963; Reentered : 5 Oct 1967

STP 1 (ASTEX) : Space Test Program (Advanced Space Technology) 1185 kg

Two primary experiments : ERIS (Earth Reflecting Ionospheric Sounder, 19 separate instruments for collecting data on proton, alpha and electron particles entering the upper atmosphere) and FRUSA (Flexible Rolled-Up Solar Array, 1.7 x 5.0 m array supporting 34,000 solar cells and producing 1,500 W)

Multiple payload launches

13 Dec 1962: 5 satellites; combined payload weighing 138 kg

- Black Sphere

- Injun 3 (52 kg) Radiation belt monitor (magnetic field, solar wind and particles)

- Surcal 1 :   Surveillance Calibration

- Surcal 1A : Surveillance Calibration

- Calsphere 1A : Calibration Sphere

15 Jun 1963: 6 satellites; Total mass = 1628 kg

- Primary : Agena D classified satellite (1500 kg)

- Lofti 2A (26 kg) Low Frequency Trans Ionosphere

- Solrad 6A (39 kg) Solar Radiation

- Radose (25 kg) Radiation Dosimeter

- Anonymous (35 kg) classified satellite; FTV 1292

- Surcal 1C (3 kg) Surveillance Calibration

11 Jan 1964: 5 satellites

- Primary: US Navy classified satellite (700 kg)

- GGSE 1 (39 kg) Gravity-Gradient Stabilization Experiment

- Secor 1 (18 kg) Sequential Collation of Range; Beacon transmitter for geodetic function

- Solrad 7A (45 kg) Solar Radiation

- Greb (Galactic Radiation Energy Background)

9 Mar 1965: 8 satellites; Total mass = 136 kg

- Solrad 6B (40 kg) Solar Radiation

- GGSE 2 & 3 (4 kg) Gravity-Gradient Stabilization Experiment

- Solrad 7B (47 kg) Solar Radiation

- Secor 3 (18 kg) Sequential Collation of Range; Geodetic monitor

- Oscar 3 (14 kg)

- Surcal 2 (5 kg) Surveillance Calibration

- Dodecahedron (4 kg) Surveillance Calibration (or Porcupine, or Dodecapole)

31 May 1967: 9 satellites

- Anonymous navigation satellite (38 kg)

- Timation 1 (4 kg) Test of quartz clocks for navigation equipments

- Surcal (3 objects): Surveillance Calibration

- Calsphere (2.4 kg, 50 cm) Calibration Sphere

- Calsphere (1.5 kg, 40 cm) Calibration Sphere

- GGSE 4 & 5 (4 kg) Gravity-Gradient Stabilization Experiment

30 Sep 1969: 10 satellites

- Anonymous ELINT ?

- Timation 2 (4 kg) Test of quartz clocks for navigation equipments

- Anonymous (5 objects)

- Tempsat 2

- Soical Cylinder: Space Object Identification Calibration

- Soical Cone: Space Object Identification Calibration


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 Thor Delta

by Jean-Jacques Serra

listing by Gunter Krebs

At the end of 1958, not long after NASA was founded, the necessity of a new civilian launcher arose. This vehicle was to be available quickly until the arrival of the Atlas and Centaur. The basic stage could only be Thor associated with one of the 3 top stages available: Able, Ablestar and Agena. Refering to the fourth letter of the Greek alphabet NASA named this new stage Delta in January 1959. Three months later the construction was granted to Douglas Aircraft (a dozen rockets were ordered) and the naming Thor Delta (or simply Delta) was adopted.

The original Delta was almost identical to Thor Able: first stage was Thor, and the second and third stage was inherited from Vanguard. The improvments were in the field of inertial guiding and active piloting during the ballistic phase between shutdown of the second stage and ignition of the third stage. This first version was 27.8 m high and weighed 51 tons; it could put 45 kg in LEO.

Its first launch on 13 May 1960 ended in a failure; the third stage didn't work. But the 12 August the second Delta was successful in orbiting Echo 1; this was the first of 22 successes. NASA went on using such launchers because of their reliability and their low cost and because of the improvements made by Douglas then McDonnell Douglas.

The A version (1962) resulted of the use of the MB3-3 motor; the B version (1962) of the lengthening of the second stage; the C version (1963) had a new third stage; the D version (1964) had Castor boosters added to the first stage. The TAD (Thrust Augmented Delta) could place 450 kg on a 800 km orbit.

The second stage was replaced in the E version (1965) resulting in the TAID (Thrust Augmented Improved Delta). The diameter of the second stage changed from 0.92 m to 1.43 m. This tripled the combustion time. The LTTAD (Long Tank Thrust Augmented Delta) appeared in the M version in 1968. the M-6 version of 1969 featured 6 Castor boosters; 3 ignited at takeoff and the others burned after the first ones shutdowned. Then not 6 but 9 boosters were included which enabled Delta to deliver 350 kg in GEO and 650 kg in a 550 km circular orbit (in 2-stage configuration).

"Straight 8" appeared in the early 70ies; this Delta version had a constant diameter: 2.44 m (8 ft). The version naming changed at the same time to become a 4-digit number: the two first digits specify the type of the first stage and the number of strap-on boosters. The two last digits refer to the type of the second and the third stage.

The 2910 version featured a Rocketdyne RS-27 first stage motor burning during 225 seconds and 9 Castor-2 boosters. The second stage was made from an Aerojet AJ10-118F motor (aerozin 50 & N204) delivering 4.3 t thrust during 320 seconds or a TRW TR-201 motor derived from the Lem descent motor using the same propellants. The 2-stage 2910 Delta could deliver 2 tons in orbit. The 3-stage 2914 version launched for the first time in 1972 featured a Thiokol TE 364-4 third stage motor providing 6.5 tons thrust during 44 seconds; it could launch 720 kg payloads in geosynchronous orbit.

The 2900 series was to be the last Delta series but as the Shuttle wasn't operational before 1980 NASA ordered the development of a new series for heavier payloads.

The 3914 Delta appeared in 1975. This version had its Castor-2s replaced by Castor-4s of 1 m diameter and 10 m high providing each 42 tons thrust during 56 seconds. The GEO capacity reached 930 kg. In 1980 as the third stage was replaced by a PAM-D (Payload Assist Module / Delta) equipped with a Thiokol Star 48 engine capable of 8.6 tons thrust during 85 seconds; Delta 3910 PAM peformance reached 1090 kg in GEO. In 1982 the second stage was replaced by a larger version (+30% propellant) with an Aerojet AJ10-118K (borrowed from Titan-3's Transtage) providing 4.35 tons thrust during 430 seconds. This Delta 3920 PAM of 35.5 m high could launch 1250 kg in GEO.

In 1984 NASA transfered Delta to a private company: Transpace Carrier Inc. At the end on the year it was believed that the launcher would be abandonned and replaced by the Shuttle. But after Challenger's accident in 1986 the launcher reappeared.

In 1987 the improved Delta was selected by the USAF as Medium Launch Vehicle (MLV) to place in orbit the second generation of Navstar satellites. The new launched was named Delta-2 and was designed in two stages: first the 6920 series then the 7920 series. The 6925 version was derived from Delta 3920 PAM by replacing the boosters by Castor-4As and lengthening the first stage of 3.65 m, extending the burn duration to 265 seconds. The diameter of the bulb cap was upped to 2.83 m. The launcher which first flew in 1989 was 39.6 m high, weighed 215 tons and could place 1400 kg in GEO.

The latest version is model 7925 which first launch occured in 1991. Its first stage is equipped with a RS-27 motor which nozzle was lengthened (12:1 instead of 8:1). The Thiokol boosters were replaced by Hercules GEM (Graphite Epoxy Motors) with weight reduced structure. Those boosters are 12 m long, weigh over 12.7 tons and provide 4.8 tons thrust. Delta 7925 weighs 225 tons and can place 1610 kg in GEO.

Current versions

Model	Description
7320	Delta II Lite with 3 strapons
7326	Delta II Lite with 3 strapons and Star 37FM third stage
7420	Delta II Lite with 4 strapons
7425	Delta II Lite with 4 strapons and PAM-D (Star 48) stage
7426	Delta II Lite with 4 strapons and Star 37FM
7920	Delta II standard, LEO missions
7925	Delta II with PAM-D third stage for GEO and escape missions
8930	Delta III with GEM LDXL strapons and LH2/LOX second stage

Delta in its different Delta-1 configurations launched numerous satellites on various orbits especially scientific satellites:

- with low perigee (ADE)

- with high apogee (IMP, ISEE 1 & ISEE 2, Exosat)

- in lunar orbit (IMP-F, RAE-B)

- to the Solar-Earth Lagrange point (ISEE-3)

- and interplanetary probes (Pioneer, ICE former-ISEE-3)

Among the scientific mission satellites some were launched:

- with collaboration (ISEE, IUE, AMPTE)

- for foreign states (Ariel, Isis, IRAS)

- or for international organizations (Heos, TD 1A, ISEE 2, COS B, ESA-Geos 1, ESA-Geos 2, Exosat)

Application missions were aimed at:

- meteorology (Tiros, Essa, Itos / NOAA, Nimbus, SMS, Goes)

- remote sensing (Landsat)

Especially for telecommunication satellites such as:

- American satellites (Telstar, Relay, Syncom, Westar, Satcom, SBS, Galaxy)

- International satellites (Intelsat, NATO)

- or foreign satellites (Skynet, Anik, Symphonie, CTS, Palapa, OTS, Sirio, Insat...)

Delta-2 versions were initially developped for the Navstar-2 satellites... but is not limited to them:

- scientific satellites (Cobe, Rosat, EUVE, Geotail)

- telecommunication satellites (BSB, Satcom, NATO,...)

Currently Delta is owned by McDonnell Douglas

Thor Delta launches

#	Launch id	Payload	Launch date	Site	Type	Status (orbit in perigee x apogee x inc. x period)
1	n/a	Echo 1	13 May 1960	C	DM19	Failure
2	60009	Echo 1A	12 Aug 1960	C	DM19
3	60016	Tiros 02	23 Nov 1960	C	DM19
4	61010	Explorer 10	25 Mar 1961	C	DM19
5	61017	Tiros 03	12 Jul 1961	C	DM19
6	61020	Explorer 12	15 Aug 1961	C	DM19
7	62002	Tiros 04	08 Feb 1962	C	DM19
8	62006	OSO 1	07 Mar 1962	C	DM19
9	62015	Ariel 1	26 Apr 1962	C	DM19
10	62025	Tiros 05	19 Jun 1962	C	DM19
11	62029	Telstar 1	10 Jul 1962	C	DM19
12	62047	Tiros 06	18 Sep 1962	C	DM19
13	62051	Explorer 14	02 Oct 1962	C	A
14	62059	Explorer 15	27 Oct 1962	C	A
15	62068	Relay 1	13 Dec 1962	C	B
16	63004	Syncom 1	14 Feb 1963	C	B
17	63009	Explorer 17	03 Apr 1963	C	B
18	63013	Telstar 2	07 May 1963	C	B
19	63024	Tiros 07	19 Jun 1963	C	B
20	63031	Syncom 2	26 Jul 1963	C	B
21	63046	Explorer 18	27 Nov 1963	C	C
22	63054	Tiros 08	21 Dec 1963	C	B
23	64003	Relay 2	21 Jan 1964	C	B
24	n/a	Explorer (BE A)	19 Mar 1964	C	B	Failure
25	64047	Syncom 3	19 Aug 1964	C	D
26	64060	Explorer 21	04 Oct 1964	C	C
27	64086	Explorer 26	21 Dec 1964	C	C
28	65004	Tiros 09	22 Jan 1965	C	C
29	65007	OSO 2	03 Feb 1965	C	C
30	65028	Intelsat 101	06 Apr 1965	C	D
31	65042	Explorer 28	29 May 1965	C	C
32	65051	Tiros 10	02 Jul 1965	C	C
33	n/a	OSO C	25 Aug 1965	C	C	Failure
34	65089	Explorer 29	06 Nov 1965	C	E
35	65105	Pioneer-6	16 Dec 1965	C	E	Interplanetary probe
36	66008	Essa 1	03 Feb 1966	C	C
37	66016	Essa 2	28 Feb 1966	C	E
38	66044	Explorer 32	25 May 1966	C	C1
39	66058	Explorer 33	01 Jul 1966	C	E1	30532 x 494230 x 29 x 19488
40	66075	Pioneer-7	17 Aug 1966	C	E1	Interplanetary probe
41	66087	Essa 3	02 Oct 1966	V	E
42	66096	Intelsat 201	26 Oct 1966	C	E1	Partial failure
43	66114	Biosat-1	14 Dec 1966	C	G	295 x 309 x 33.5 x 90.4
44	67001	Intelsat 202	11 Jan 1967	C	E1
45	67006	Essa 4	26 Jan 1967	V	E
46	67020	OSO 3	08 Mar 1967	C	C
47	67026	Intelsat 203	23 Mar 1967	C	E1
48	67036	Essa 5	20 Apr 1967	V	E
49	67051	Explorer 34	24 May 1967	V	E1
50	67070	Explorer 35 (IMP)	19 Jul 1967	C	E1	Lunar orbit
51	67083	Biosat-2	07 Sep 1967	C	G	286 x 313 x 33.5 x 90.4
52	67094	Intelsat 204	28 Sep 1967	C	E1
53	67100	OSO 4	18 Oct 1967	C	E1
54	67114	Essa 6	10 Nov 1967	V	C1
55	67123	Pioneer-8 TATS 1 (TETR 1)	13 Dec 1967	C	E1	Interplanetary probe
56	68002	Explorer 36	11 Jan 1968	V	E1
57	68055	Explorer 38	04 Jul 1968	V	J
58	68069	Essa 7	16 Aug 1968	V	N
59	n/a	Intelsat 301	18 Sep 1968	C	M	Failure
60	68100	Pioneer-9 TETR 2	08 Nov 1968	C	E1	Interplanetary probe
61	68109	Heos 1	05 Dec 1968	C	E1
62	68114	Essa 8	15 Dec 1968	V	N
63	68116	Intelsat 302	19 Dec 1968	C	M
64	69006	OSO 5	22 Jan 1969	C	C1
65	69009	Isis 1	30 Jan 1969	V	E1
66	69011	Intelsat 303	06 Feb 1969	C	M
67	69016	Essa 9	26 Feb 1969	C	E1
68	69045	Intelsat 304	22 May 1969	C	M
69	69053	Explorer 41	21 Jun 1969	V	E1
70	69056	Biosat-3	29 Jun 1969	C	N
71	69064	Intelsat 305	25 Jul 1969	C	N	Partial failure
72	69068	OSO 6	09 Aug 1969	C	N
73	n/a	Pioneer-10A	28 Sep 1969	C	L	Failure
74	69101	Skynet 1A	22 Nov 1969	C	M
75	70003	Intelsat 306	15 Jan 1970	C	M
76	70008	Itos Oscar 05	23 Jan 1970	V	N6
77	70021	Nato 1	20 Mar 1970	C	M
78	70032	Intelsat 307	23 Apr 1970	C	M
79	70055	Intelsat 308	23 Jul 1970	C	M
80	70062	Skynet 1B	19 Aug 1970	C	M
81	70106	NOAA 01 CEP 1	11 Dec 1970	V	N6	CEP 1 was attached to the 2nd stage
82	71009	Nato 2	03 Feb 1971	C	L
83	71019	Explorer 43	13 Mar 1971	C	M6
84	71024	Isis 2	01 Apr 1971	V	E1
85	71083	OSO 7	29 Sep 1971	C	N
86	71091	ITOS-3/NOAA	21 Oct 1971	V	N6	payload exploded?
87	72005	Heos 2	31 Jan 1972	V	L
88	72014	TD-1A	12 Mar 1972	V	N
89	72058	Landsat 1	23 Jul 1972	V	900
90	72073	Explorer 47	23 Sep 1972	C	1604
91	72082	NOAA 02	15 Oct 1972	V	300
92	72090	Anik A1	10 Nov 1972	C	1914
93	72097	Nimbus 5	11 Dec 1972	V	900
94	73023	Anik A2	20 Apr 1973	C	1914
95	73039	Explorer 49 (RAE B)	10 Jun 1973	C	1913	Lunar orbit
96	n/a	Itos E	16 Jul 1973	V	300	Failure
97	73078	Explorer 50	26 Oct 1973	C	1604
98	73086	NOAA 03	06 Nov 1973	V	300
99	73101	Explorer 51	16 Dec 1973	V	900
100	74002	Skynet 2A	19 Jan 1974	C	2913	Partial failure
101	74022	Westar 1	13 Apr 1974	C	2914
102	74033	SMS 1	17 May 1974	C	2914
103	74075	Westar 2	10 Oct 1974	C	2914
104	74089	NOAA 04 Oscar 07 Intasat	15 Nov 1974 at 17:11 UT	V	2310
105	74094	Skynet 2B	23 Nov 1974	C	2913
106	74101	Symphonie 1	19 Dec 1974	C	2914
107	75004	Landsat 2	22 Jan 1975	V	2910
108	75011	SMS 2	06 Feb 1975	C	2914
109	75027	Geos 3	09 Apr 1975	V	2310
110	75038	Anik A3	07 May 1975	C	2914
111	75052	Nimbus 6	12 Jun 1975	V	2910
112	75057	OSO 8	21 Jun 1975	C	2913
113	75072	Cos B	09 Aug 1975	V	2914
114	75077	Symphonie 2	27 Aug 1975	C	2914
115	75096	Explorer 54	06 Oct 1975	V	2910
116	75100	Goes 01	16 Oct 1975	C	2914
117	75107	Explorer 55	20 Nov 1975	C	2910
118	75117	Satcom 1	13 Dec 1975	C	3914
119	76004	CTS	17 Jan 1976	C	2914
120	76017	Marisat 1	19 Feb 1976	C	2914
121	76029	Satcom 2	26 Mar 1976	C	3914
122	76035	Nato 3A	22 Apr 1976	C	2914
123	76039	Lageos 1	04 May 1976	V	2913
124	76053	Marisat 2	10 Jun 1976	C	2914
125	76066	Palapa A1	08 Jul 1976	C	2914
126	76077	NOAA 05	29 Jul 1976	V	2310
127	76101	Marisat 3	14 Oct 1976	C	2914
128	77005	Nato 3B	28 Jan 1977	C	2914
129	77018	Palapa A2	10 Mar 1977	C	2914
130	77029	ESA-Geos 1	20 Apr 1977	C	2914
131	77048	Goes 02	16 Jun 1977	C	2914
132	77065	GMS 1	14 Jul 1977	C	2914
133	77080	Sirio 1	25 Aug 1977	C	2913
134	n/a	OTS 1	13 Sep 1977	C	3914	Failure
135	77102	ISEE 1 ISEE 2	22 Oct 1977	C	2914
136	77108	Meteosat 1	23 Nov 1977	C	2914
137	77118	Sakura 1	15 Dec 1977	C	2914
138	78012	IUE	26 Jan 1978	C	2914
139	78026	Landsat 3 Oscar 08 PIX 1	5 Mar 1978	V	2910	PIX 1 was attached to the 2nd stage
140	78039	Yuri 1	07 Apr 1978	C	2914
141	78044	OTS 2	11 May 1978	C	3914
142	78062	Goes 03	16 Jun 1978	C	2914
143	78071	ESA-Geos 2	14 Jul 1978	C	2914
144	78079	ISEE-3	11 Aug 1978	C	2914	To the Lagrange point and then became ICE
145	78098	Nimbus 7 Cameo	24 Oct 1978	V	2910	Cameo was attached to the 2nd stage
146	78106	Nato 3C	19 Nov 1978	C	2914
147	78116	Anik B1 Drims	16 Dec 1978	C	3914	Drims was attached to the 2nd stage
148	79007	Scatha (P78 2)	30 Jan 1979	C	2914	27800 x 42300 x 8.3 x 1441
149	79072	Westar 3	10 Aug 1979	C	2914
150	79101	Satcom 3	07 Dec 1979	C	3914
151	80014	SMM	14 Feb 1980	C	3910
152	80074	Goes 04	09 Sep 1980	C	3914
153	80091	SBS 1	15 Nov 1980	C	3910/PAM
154	81049	Goes 05	22 May 1981	C	3914
155	81070	Dynamics Explorer 1 Dynamics Explorer 2	03 Aug 1981	V	3913	Partial failure
156	81096	SBS 2	24 Sep 1981	C	3910/PAM
157	81100	SME Uosat 1	06 Oct 1981	V	2310
158	81114	Satcom 3R	20 Nov 1981	C	3910/PAM
159	82004	Satcom 4	16 Jan 1982	C	3910/PAM
160	82014	Westar 4	26 Feb 1982	C	3910/PAM
161	82031	Insat 1A	10 Apr 1982	C	3910/PAM
162	82058	Westar 5	09 Jun 1982	C	3910/PAM
163	82072	Landsat 4	16 Jul 1982	V	3920
164	82082	Anik D1	26 Aug 1982	C	3920/PAM
165	82105	Aurora 1	28 Oct 1982	C	3924
166	83004	IRAS PIX 2	26 Jan 1983	V	3910	PIX 2 was attached to the 2nd stage
167	83030	Satcom 1R	11 Apr 1983	C	3924
168	83041	Goes 06	28 Apr 1983	C	3914
169	83051	Exosat	26 May 1983	V	3914
170	83065	Galaxy 1	28 Jun 1983	C	3920/PAM
171	83077	Telstar 301	28 Jul 1983	C	3920/PAM
172	83094	Satcom 2R	08 Sep 1983	C	3924
173	83098	Galaxy 2	22 Sep 1983	C	3920/PAM
174	84021	Landsat 5 Uosat 2	01 Mar 1984	V	3920
175	84088	AMPTE CCE AMPTE IRM AMPTE UKS	16 Aug 1984	C	3924
176	84101	Galaxy 3	21 Sep 1984	C	3920/PAM
177	84115	Nato 3D	14 Nov 1984	C	3914
178	n/a	Goes G	03 May 1986	C	3914	Failure
179	86069	USA 019 (SDIO)	05 Sep 1986	C	3920
180	87022	Goes 07	26 Feb 1987	C	3924
181	87029	Palapa B2P	20 Mar 1987	C	3920/PAM
182	88008	USA-30 (SDIO)	08 Feb 1988	C	3920 or 3910	220 x 340 x 28.6 x 90
183	89013	GPS BII-01	14 Feb 1989	C	6925
184	89026	Delta Star	24 Mar 1989	C	3920
185	89044	GPS BII-02	10 Jun 1989	C	6925
186	89064	GPS BII-03	18 Aug 1989	C	6925
187	89067	BSB 1	27 Aug 1989	C	4925
188	89085	GPS BII-04	21 Oct 1989	C	6925
189	89089	Cobe	18 Nov 1989	V	5920
190	89097	GPS BII-05	11 Dec 1989	C	6925
191	90008	GPS BII-06	24 Jan 1990	C	6925
192	90015	USA 051 + 052 (LACE + RME; SDIO)	14 Feb 1990	C	6920-8	500 x 500 x 43.1
193	90025	GPS BII-07	26 Mar 1990	C	6925
194	90034	Palapa B2R	13 Apr 1990	C	6925-8
195	90049	Rosat	01 Jun 1990	C	6920-10
196	90051	Insat 1D	12 Jun 1990	C	4925
197	90068	GPS BII-08	02 Aug 1990	C	6925
198	90074	BSB 2	19 Aug 1990	C	6925
199	90088	GPS BII-09	01 Oct 1990	C	6925
200	90093	Inmarsat 2F1	30 Oct 1990	C	6925
201	90103	GPS BIIA-10	26 Nov 1990	C	7925
202	91001	Nato 4A	08 Jan 1991	C	7925
203	91018	Inmarsat 2F2	08 Mar 1991	C	6925
204	91028	ASC 2	13 Apr 1991	C	7925
205	91037	Aurora 2	29 May 1991	C	7925
206	91047	GPS BIIA-11 Losat-X	04 Jul 1991	C	7925
207	92009	GPS BIIA-12	23 Feb 1992	C	7925
208	92019	GPS BIIA-13	10 Apr 1992	C	7925
209	92027	Palapa B4	14 May 1992	C	7925-8
210	92031	EUVE	07 Jun 1992	C	6920-10
211	92039	GPS BIIA-14	07 Jul 1992	C	7925
212	92044	Geotail Duve	24 Jul 1992	C	6925	Duve was attached to the 2nd stage
213	92057	Satcom C4	31 Aug 1992	C	7925
214	92058	GPS BIIA-15	09 Sep 1992	C	7925
215	92066	DFS 3	12 Oct 1992	C	7925
216	92079	GPS BIIA-16	22 Nov 1992	C	7925
217	92089	GPS BIIA-17	18 Dec 1992	C	7925
218	93007	GPS BIIA-18	03 Feb 1993	C	7925
219	93017	GPS BIIA-19 Seds 1	30 Mar 1993	C 17A	7925	Seds 1 was tethered to 2nd stage
220	93032	GPS BIIA-20	13 May 1993	C	7925
221	93042	GPS BIIA-21 PMG	26 Jun 1993	C	7925	PMG was tethered to 2nd stage
222	93054	GPS BIIA-22	30 Aug 1993	C 17	7925
223	93068	GPS BIIA-23	26 Oct 1993	C 17	7925
224	93076	Nato 4B	08 Dec 1993	C	7925
225	94013	Galaxy 1R	19 Feb 1994	C 17	7925-8
226	94016	GPS BIIA-24 Seds 2	10 Mar 1994	C 17	7925	Seds 2 was tethered to 2nd stage
227	94071	Wind 1	01 Nov 1994	C 17B	7925-10
228	95041	Koreasat 1	05 Aug 1995	C 17B	7925	Partial failure: a booster failed to separate
229	95059	Radarsat Surfsat 1	04 Nov 1995 at 14:22 UT	V SLC2	7920-10	Surfsat is attached to Delta's second stage
230	95074	XTE	30 Dec 1995 at 13:48 UT	C 17A	7920-10
231	96003	Koreasat 2	14 Jan 1996 at 11:11 UT	C 17B	7925
232	96008	NEAR probe	17 Feb 1996 at 20:43 UT	C 17B	7925-8
233	96011	Polar	24 Feb 1996	V SLC2	7925-10	185 x 50494 km x 86°
234	96019	GPS BIIA-25	28 Mar 1996 at 00:21 UT	C 17A	7925	192 x 20269 km x 34.9°
235	96024	MSX	24 Apr 1996 at 12:27 UT	V SLC2	7920-10
236	96033	Galaxy 9	24 May 1996 at 01:10 UT	C 17B	7925-8
237	96041	GPS BIIA-26	16 Jul 1996 at 00:50 UT	C 17B	7925
238	96056	GPS BIIA-27	12 Sep 1996 at 08:49 UT	C 17A	7925
239	96062	Mars Global Surveyor	7 Nov 1996	C	7925
240	96068	Mars Pathfinder	4 Dec 1996	C	7925
241	n/a	GPS BIIR-01	17 Jan 1997 at 16:28 UT	C 17A	7925	Failure: was destroyed by controllers after 13 s flight. Caused damages to the launch pad. A split in the casing of one of nine solid rocket motors caused the accident.
242	97020	A: Iridium 08 B: Iridium 07 C: Iridium 06 D: Iridium 05 E: Iridium 04	5 May 1997 at 14:55 UT	V SLC 2	7920-10C	595 x 949 km x 86.7° initial orbit
243	97025	Thor 2	20 May 1997 at 22:39 UT	C 17A	7925
244	97034	A: Iridium 15 B: Iridium 17 C: Iridium 18 D: Iridium 20 E: Iridium 21	9 Jul 1997 at 13:04 UT	V SLC 2	7920-10C
245	97035	GPS BIIR-02	23 Jul 1997	C 17A	7925
246	97043	A: Iridium 26 B: Iridium 25 C: Iridium 24 D: Iridium 23 E: Iridium 22	21 Aug 1997 at 00:38 UT	V	7920-10C
247	97045	ACE	25 Aug 1997 at 14:39 UT	C 17A	7920-8
248	97056	A: Iridium 19 B: Iridium 37 C: Iridium 36 D: Iridium 35 E: Iridium 34	27 Sep 1997 at 01:23 UT	V SLC2	7920-10C
249	97067	GPS BIIR-02	6 Nov 1997 at 00:30 UT	C 17A	7925
250	97069	A: Iridium 43 B: Iridium 41 C: Iridium 40 D: Iridium 39 E: Iridium 38	9 Nov 1997 at 01:34 UT	V SLC2	7920-10C
251	97082	A: Iridium 45 B: Iridium 46 C: Iridium 47 D: Iridium 48 E: Iridium 49	20 Dec 1997 at 13:16 UT	V SLC2	7920-10C
252	98002	Skynet 4D	10 Jan 1998 at 00:32 UT	C 17B	7925
253	98008	A: Globalstar 1 B: Globalstar 2 C: Globalstar 3 D: Globalstar 4	14 Feb 1998 at 14:34 UT	C 17A	7420-10C	with satellite dispenser
254	98010	A: Iridium 50 B: Iridium 56 C: Iridium 52 D: Iridium 53 E: Iridium 54	18 Feb 1998 at 13:58 UT	V SLC2	7920-10C
255	98019	A: Iridium 55 B: Iridium 57 C: Iridium 58 D: Iridium 59 E: Iridium 60	30 Mar 1998 at 06:02 UT	V SLC2	7920-10C
256	98023	A: Globalstar 6 B: Globalstar 8 C: Globalstar 14 D: Globalstar 15	24 Apr 1998 at 22:38 UT	C 17A	7420-10C
257	98032	A: Iridium 70 B: Iridium 72 C: Iridium 73 D: Iridium 74 E: Iridium 75	17 May 1998 at 21:16 UT	V SLC2	7920-10C
258	98035	Thor 3	10 Jun 1998 at 00:35 UT	C 17A	7925
259	FTO	Galaxy 10	27 Aug 1998 at 1:17 UT	C 17B	8930	Failure: explosion 80 seconds after liftoff
260	98051	A: Iridium 77 B: Iridium 79 C: Iridium 80 D: Iridium 81 E: Iridium 82	8 Sep 1998 at 21:13 UT	V SLC2	7920-10C
261	98061	A: Deep Space B: Sedsat	24 Oct 1998 at 12:08 UT	C 17A	7326	Delta 7326 is a new variant of Delta II which uses three solid Alliant GEM-40 strapons
262	98066	A: Iridium 87 B: Iridium 86 C: Iridium 85 D: Iridium 84 E: Iridium 83	6 Nov 1998 at 13:37 UT	V SLC2	7920-10C
263	98068	Bonum 1	22 Nov 1998 at 23:54 UT	C 17B	7925
264	98073	Mars Climate Observer	11 Dec 1998	C 17A	7425
265	99001	Mars Polar Lander	3 Jan 1999 at 20:21 UT	C 17B	7425
266	99003	Stardust	7 Feb 1999 at 21:04 UT	C 17A	7426
267	99008	A: Argos B: Orsted C: Sunsat	23 Feb 1999 at 10:30 UT	V SLC2	7920
268	99020	Landsat 7	15 Apr 1999 at 18:32 UT	V SLC2	7920-10
269	99024	Orion 3	3 May 1999 at 01:00 UT	C 17B	8930	Failure: second stage failed to complete second burn (1 second). Could be because of a breach in the combustion chamber
270	99031	A: Globalstar 52 B: Globalstar 49 C: Globalstar 25 D: Globalstar 47	10 Jun 1999 at 13:48 UT	C 17B	7420-10
271	99035	Fuse	24 Jun 1999 at 15:44 UT	C 17A	7320
272	99037	A: Globalstar 32 B: Globalstar 30 C: Globalstar 35 D: Globalstar 51	10 Jul 1999 at 08:45 UT	C 17B	7420-10
273	99041	A: Globalstar 26 B: Globalstar 28 C: Globalstar 43 D: Globalstar 48	25 Jul 1999 at 07:46 UT	C 17A	7420-10
274	99043	A: Globalstar 24 B: Globalstar 27 C: Globalstar 53 D: Globalstar 54	17 Aug 1999 at 04:37 UT	C 17B	7420-10

Notes: in the launcher date & site column C stands for Cape Canaveral and V for Vandenberg.


Thor with solid top stage
 Thor with a solid fuel top stage

by Jean-Jacques Serra

listing by Gunter Krebs

The first solid fuel top stage associated with Thor in 1965 was Altair, the former third stage of Vanguard equipped with a 3-axis control by Boeing. Called Burner this top stage was also adapted on Thor and other USAF vehicles. Despite Burner 1 used an Altair motor, Burner 2 featured a Thiokol Star-37B motor (TE-M-364-2) derived from the Surveyor lunar retro-rocket. The Burner 2A was a two stage version which second stage Star-37S (TE-M-364-15) provided a slightly weaker thrust than Star-37B.

Thor Altair and Thor Burner were mainly used for US military meteorological programs although they also launched technological satellites.

Thor with solid top stage launches

# and serial	Launch id	Payload	Launch date	Type	Status (orbit in perigee x apogee x inclination x period)
1, 224		DMSP B4A-01	19 Jan 1965	LV2D Burner1	471 x 822 x 98.8 x 97.7
2, 306		DMSP B4A-02	18 Mar 1965	LV2D Burner1	525 x 764 x 99.1 x 97.7
3, 282		DMSP B4A-03	20 May 1965	LV2D Burner1	567 x 953 x 98.7 x 100.1
4, 213		DMSP B4A-04	10 Sep 1965	LV2D Burner1	649 x 1054 x 98.7 x 101.9
5, 251		DMSP B4A-05	06 Jan 1966	LV2D Burner1	Failure: 2nd stage failed
6, 147		DMSP B4A-06	31 Mar 1966	LV2D Burner1	634 x 933 x 98.6 x 100.6
7, 167		DMSP B4A-07	16 Sep 1966	LV2D Burner2	705 x 891 x 98.5 x 100.9
8, 169		DMSP B4A-08	08 Feb 1967	LV2D Burner2	796 x 868 x 98.8 x 101.6
9, 171	67065	Secor 09 Aurora 1 (P67-1)	29 Jun 1967	LV2D Burner2
10, 266		DMSP B4A-09	23 Aug 1967	LV2D Burner2	834 x 892 x 99 x 102.2
11, 268		DMSP B4A-10	11 Oct 1967	LV2D Burner2	694 x 837 x 99.1 x 100.2
12, 277		DMSP B5A-1	23 May 1968	LV2D Burner2	817 x 904 x 98.9 x 102.2
13, 173		DMSP B5A-2	23 Oct 1968	LV2D Burner2	797 x 855 x 99 x 101.4
14, 279		DMSP B5A-3	23 Jul 1969	LV2D Burner2	791 x 863 x 99 x 101
15, 287		DMSP B5A-4	11 Feb 1970	LV2D Burner2	764 x 974 x 98.7 x 101.6
16, 288		DMSP B5A-5	03 Sep 1970	LV2D Burner2	764 x 874 x 98.7 x 101.3
17, 249		DMSP B5A-6 Calsphere 3, 4, 5	17 Feb 1971	LV2D Burner2	767 x 833 x 98.8 x 100.9
18, 210		SESP-1 (P70-1)	08 Jun 1971	LV2D Burner2	545 x 581 x 90.2 x 95.9
19, 159		DMSP B5B-1	14 Oct 1971	LV2D Burner2A	796 x 877 x 99 x 101.7
20, 153		DMSP B5B-2	24 Mar 1972	LV2D Burner2A	803 x 885 x 98.8 x 101.8
21, 294		DMSP B5B-3	09 Nov 1972	LV2D Burner2A	813 x 872 x 98.6 x 101.8
22, 291		DMSP B5B-4	17 Aug 1973	LV2D Burner2A	811 x 852 x 98.9 x 101.6
23, 207		DMSP B5B-5	16 Mar 1974	LV2D Burner2A	780 x 876 x 98.9 x 101.5
24, 275		DMSP B5B-6	09 Aug 1974	LV2D Burner2A	808 x 870 x 98.8 x 101.7
25, 197		DMSP B5C-1	24 May 1975	LV2D Burner2A	830 x 904 x 98.9 x 102.2
26, 182		DMSP B5C-2	21 Feb 1976	LV2D Burner2A	Partial failure: Thor failed, wrong orbit attained
27, 172		DMSP B5D1-1	11 Sep 1976	LV2F S3B S37B-ISS	820 x 845 x 99
28, 183		DMSP B5D1-2	05 Jun 1977	LV2F S3B S37B-ISS	811 x 869 x 99.2 x 101.7
29, 143		DMSP B5D1-3	01 May 1978	LV2F S3B S37B-ISS	564 x 653 x 97.6 x 96.9
30, 264		DMSP B5D1-4	06 Jun 1979	LV2F S3B S37B-ISS	820 x 838 x 98.8 x 101.1
31, 304		DMSP B5D1-5	14 Jul 1980	LV2F S3B S37B-ISS	Failure: 2nd stage exploded

Notes: All launches from Vandenberg.


 Titan

by Jean-Jacques Serra

Origins of Titan

Titan without top stage (2)

Titan 3

Titan 4

Origin: Inter Continental Ballistic Missile (ICBM) of second generation

As building ICBMs was a very risky venture, it was decided in 1955 to develop another two-stage missille despite Atlas. This contract was awarded to the Martin Company (then Martin Marietta, then Lockheed Martin).

The first stage of 3.05 m diameter like Atlas were planned to be powered by two Aerojet LR-87 which delivered 1335 kN thrust at takeoff. The second stage of 2.44 m diameter was made of 1 Aerojet LR-91 motor of 356 kN. The two stages burned the same fuel: liquid oxygen and kerosene. The missile was 29.9 m high (with a Mk4 RV) and weighed 99.8 tons.

For the first launch on 9 Feb 1959 the missile had only 1 stage active, the second was full of water. Enhancements of the motors were started the following month and the version 3 (simplified and lighter) flew in May 1960. Titan 1 was deployed in silos from 1962 to 1965 but not space launcher was derived from it.

The reaction time of the Titan 1's evaluated to 15 minutes could be reducted to only 1 minute by replacing its propellant by stockable propellant. The studies started in 1960 and resulted in Titan 2. This is an enhanced vehicle with a doubled payload/range ratio. The 2 stages measuring respectivly 21.4 m and 12.2 m long had a uniform 3.05 m diameter. The motors were modified (5th version) and used Nitrogen TetraOxide and Aerozine 50. Titan 2 was 31.4 m high (with a Mk6 RV) and weighed 150 tons.

The missile was operational in March 1962 and deployed in silos from 1964 to 1987.

Titan propulsion system

Designation	Year of first launch	LR 87 thrust (kN)	LR 87 SI (sec)	LR 91 thrust (kN)	LR 91 SI (sec)	Application
1-3	1959-1961	1335 (g)	249 (g)	356	311	Titan 1
5	1962	1910 (g)	259 (g)	445	315	Titan 2
7	1964	1910 (g)	259 (g)	445	315	Gemini
9	1964	1910 (g) / 2030 (v)	259 (g) / 275 (v)	445	316	Titan 3
11	1968	2045 (g) / 2350 (v)	258 (g) / 302 (v)	445	316	Titan 3
11A	1989	2440 (v)	301 (v)	467	316	Titan 4
(g): ground value; (v): vacuum value


Titan

[launch vehicle index]

Origins of Titan

Titan 2 (without top stage)

Titan 3

Titan 4


 Titan without top stage

by Jean-Jacques Serra

The selecting of the launcher for the manned Gemini flight was profitable to Titan 2 because of its capacity to orbit the necessary load (3.5 tons), its ease of use with stockable propellant and it's reliability. Only little modifications were made to enable it to launch manned capsules, and the motors (v7) had the same performances as v5.

After a suborbital flight in 1964 and a non piloted one in early 1965 ten manned capsules from the Gemini program were launched from Cap Canaveral between March 1965 and November 1966. All were orbited correctly.

In early 1986 Martin Marietta was granted a contract to evolve some retired Titan 2 ICBM into Titan 2 SLV. The first of those was launched in September 1988 from vandenberg in G (or 23G) version. The main modifications involve the cap and the the guidance.

Two other versions were proposed: Titan 2B (basic), a simplified version which keeps the original cap, and Titan 2S (Solid Thrust Augmented) which get 2 to 8 Castor 4A solid boosters.

Titan 2 launches

#	Launch id	Payload	Launch Date	Site	Type	Status/Comment (orbit in perigee x apogee x inclination x period)
1		Gemini 1	8 Apr 1964	CC	Titan-2 Gemini
2		Gemini 2	19 Jan 1965*	CC	Titan-2 Gemini
3		Gemini 3	23 Mar 1965	CC	Titan-2 Gemini
4		Gemini 4	3 Jun 1965	CC	Titan-2 Gemini
5		Gemini 5 / REP	21 Aug 1965	CC	Titan-2 Gemini
6		Gemini 7	4 Dec 1965	CC	Titan-2 Gemini
7		Gemini 6	15 Dec 1965	CC	Titan-2 Gemini
8		Gemini 8	16 Mar 1966	CC	Titan-2 Gemini
9		Gemini 9	3 Jun 1966	CC	Titan-2 Gemini
10		Gemini 10	18 Jul 1966	CC	Titan-2 Gemini
11		Gemini 11	12 Sep 1966	CC	Titan-2 Gemini
12		Gemini 12	11 Nov 1966	CC	Titan-2 Gemini
13, 2B-98/-56	88078	Singleton 1	5 Sep 1988	V	Titan-2(23)G
14, 2B-106	89072	Singleton 2	5 Sep 1989	V	Titan-2(23)G
15	92023	Singleton 3	25 Apr 1992	V	Titan-2(23)G
16	n/a	Landsat 6	5 Oct 1993	V SLC4W	Titan-2(23)G Star-37XFP-ISS	Failure: Star-37XFP-ISS kick-motor malfunctioned
17	94004	Clementine 1 / DSPSE-ISA [Star-37FM]	25 Jan 1994	V	Titan-2(23)G
18, G6	97012	DMSP B5D2-9	4 Apr 1997	V	Titan-2(23)G Star-37S-ISS
19, G12	98030	NOAA 15	13 May 1998 at 15:52 UT	V SLC4W	Titan-2(23)G Star 37XFP	#12 ?
20, G7	99034	Quickscat	20 Jun 1999 at 02:15 UT	V SLC4W	Titan-2(23)G


 Titan 3

by Jean-Jacques Serra

Titan 3 without solid boosters

The first Titan 3 vehicles were based on the 2-stage Titan 2 to which a top stage was added. The motors (version 9) had the same performance as the former versions but were qualified for in-orbit ignition. From 1968 on, the version 11 formerly developped for the MOL program was used for the Titan 3.

Titan 3A was an intermediate rocket to be used for the development of the Titan 3C top stage. This third stage named Transtage was 4.5 m long and 3.05 m diameter. It could be re-ignited in orbit. It was equiped of an 2 Aerojet motor AJ10-138 propulsion bay. Those used the same propellant as the firsts stages and provided a total 71 kN.

It was not used much: only 4 launches from Sep 1964 to May 1965 from Cape Canaveral; first launch was a failure, and the following successes.

Titan 3B was a military launcher exclusivly used from Vandenberg. It used an Agena top stage. It was used to launch reconnaissance satellites from the KH-8 series between 1966 and 1984. The same launcher was used for the classified SDS and Jumpseat launches to Molniya type orbits. In 1975 a version with a a longer first stage and wider cap was introduced: Titan 34B (or Titan 3B Ascent Agena). It was specifically devoted to those military launches.

Titan 3 with solid boosters

Titan 3C was made of the 3 stages of Titan 3A plus two lateral solid boosters of 3.05 m diameter. Unlike Thor's boosters, those built by UTC/CSD did not assist the first stage motors but provided alone the launcher's propulsion during about 2 minutes. With 25.5 m high and 250 tons, each (composed of 5 segments) provided 5340 kN.

The Transtage which contained the full command module of the vehicle including the guidance system could deliver payloads directly in GEO. It was the first rocket to fire 4 times during a flight.

Titan 3C was 39 m high and could orbit 12 tons in LEO and 1 ton in GEO. It was used from 1965 to 1982 to launch telecommunication satellites (ISDCP, LES, DSCS), early warning birds (Vela, DSP) and SIGINT (Chalet) from Cape Canaveral.

Titan 3D was assembled with 3 stages from Titan 3B and the 2 lateral 5-segment boosters of Titan 3C. It was launched from Vandenberg between 1971 and 1982 with KH 9 and KH 11 on board.

The Titan 3E developped for civilian applications of NASA the top stage was a cryogenic Centaur. This 9.1 m long stage had the same diameter as the 2 first stages but was under a 4.27 m diameter cap. With 48 m high and 640 tons Titan 3E could put 3.6 tons on escape orbit. It was thus used for interplanetary missions as Helios, Voyager and Viking between 1974 and 1977.

An enhanced version of the Titan 3 rockets was introduced in 1982. The new launcher named Titan 34D used the first stage of Titan 34B. The solid boosters were elongated (5.5 compared to 5 segments) and delivered 6230 kN during 114 seconds each. The motors of the first stage provided 2440 kN (in vacuum) during 160 s and the second stage 467 kN during 225 s. The top stage could be either Transtage or IUS.

This launcher (680 tons) was fired 15 times between 1982 and 1989. It could place 14.8 tons on LEO and 1.9 tons in GEO.

In the late eighties Martin Marietta derived 2 commercial versions of the Titan 34D: one for the launch of satellites directly in GEO with Transtage and the other to launch satellites with perigee motor in LEO. Only the latter was bought and fired 4 times between 1990 and 1992 under the Titan 3 commercial designation.

Titan 3 launches

#	Launch id	Payload	Launch Date	Site	Type	Status/Comment (orbit in perigee x apogee x inclination x period)
1, 3A-2	n/a	Transtage 1	2 Sep 1964	CC	Titan-3A	Failure
2, 3A-1		Transtage 2	10 Dec 1964	CC	Titan-3A
3, 3A-3	65008	LES 1	11 Feb 1965	CC	Titan-3A
4, 3A-4	65034	B: LES 2 C: LCS 1	6 May 1965	CC	Titan-3A
5, 3C-7	65047	Transtage 5	18 Jun 1965	CC	Titan-3C
6, 3C-4	65082	OV 2-1	15 Oct 1965	CC	Titan-3C	Failure
7, 3C-8	65108	A: OV 2-3 B: LES 4 C: Oscar 04 D: LES 3	21 Dec 1965	CC	Titan-3C
8, 3C-11	66053	IDCSP 1 to 7 GGTS 1 (OPS 9381)	16 Jun 1966	CC	Titan-3C
9, 3B-1	66069	KH-8 1 (OPS 3014)	29 Jul 1966	Va	Titan-3B Agena-D
10, 3C-12	n/a	IDCSP (8) ... IDCSP (14) / GGTS 2	26 Aug 1966	CC	Titan-3C	Failure
11, 3B-2	66086	KH-8 2 (OPS 4096)	28 Sep 1966	Va	Titan-3B Agena-D
12, 3C-9	66099	B: OV-4 1R C: OV-1 6 D: OV-4 1T OV-4 3 Gemini B	3 Nov 1966	CC	Titan-3C	Gemini B was on a suborbital orbit
13, 3B-3	66113	KH-8 3 (OPS 8968)	14 Dec 1966	Va	Titan-3B Agena-D
14, 3C-13	67003	IDCSP 8 to 15	18 Jan 1967	CC	Titan-3C
15, 3B-4	?	KH-8 4	24 Mar 1967	Va	Titan-3B Agena-D
16, 3B-5	n/a	KH-8 5	26 Apr 1967	Va	Titan-3B Agena-D	Failure
17, 3C-10	67040	A: Vela 7 B: Vela 8 C: ERS 18 D: OV-5 3 (ERS 20) E: OV-5 1 (ERS 27)	28 Apr 1967	CC	Titan-3C
18, 3B-8	67064	KH-8 6 (OPS 4282)	20 Jun 1967	Va	Titan-3B Agena-D
19, 3C-14	67066	IDCSP 16 to 19 E: LES 5 F: Dodge	1 Jul 1967	CC	Titan-3C
20, 3B-9	67079	KH-8 7	16 Aug 1967	Va	Titan-3B Agena-D
21, 3B-10	67090	KH-8 8	19 Sep 1967	Va	Titan-3B Agena-D
22, 3B-11		KH-8 9	25 Oct 1967	Va	Titan-3B Agena-D
23, 3B-12		KH-8 10	5 Dec 1967	Va	Titan-3B Agena-D
24, 3B-13		KH-8 11	18 Jan 1968	Va	Titan-3B Agena-D
25, 3B-14		KH-8 12	13 Mar 1968	Va	Titan-3B Agena-D
26, 3B-15		KH-8 13	17 Apr 1968	Va	Titan-3B Agena-D
27, 3B-16		KH-8 14	5 Jun 1968	Va	Titan-3B Agena-D
28, 3C-16	68050	IDCSP 19 to 26	13 Jun 1968	CC	Titan-3C
29, 3B-17		KH-8 15	6 Aug 1968	Va	Titan-3B Agena-D ?
30, 3B-18		KH-8 16	10 Sep 1968	Va	Titan-3B Agena-D ?
31, 3C-5	68081	A: OV 2-5 B: OV-5 2 C: OV-5 4 D: LES 6	26 Sep 1968	CC	Titan-3C
32, 3B-19		KH-8 17	6 Nov 1968	Va	Titan-3B Agena-D ?
33, 3B-20		KH-8 18	4 Dec 1968	Va	Titan-3B Agena-D ?
34, 3B-6		KH-8 19	22 Jan 1969	Va	Titan-3B Agena-D
35, 3C-17	69013	TACSAT 1	9 Feb 1969	CC	Titan-3C
36, 3B-7		KH-8 20	4 Mar 1969	Va	Titan-3B Agena-D
37, 3B-21		KH-8 21	15 Apr 1969	Va	Titan-3B Agena-D ?
38, 3C-15	69046	A: OV-5 5 B: OV-5 6 C: OV-5 9 D: Vela 9 E: Vela 10	23 May 1969	CC	Titan-3C
39, 3B-22		KH-8 22	3 Jun 1969	Va	Titan-3B Agena-D ?
40, 3B-23		KH-8 23	22 Aug 1969	Va	Titan-3B Agena-D ?
41, 3B-24		KH-8 24	24 Oct 1969	Va	Titan-3B Agena-D ?
42, 3B-25		KH-8 25	14 Jan 1970	Va	Titan-3B Agena-D ?
43, 3C-18	70027	A: Vela 11 B: Vela 12	8 Apr 1970	CC	Titan-3C
44, 3B-26		KH-8 26	15 Apr 1970	Va	Titan-3B Agena-D ?
45, 3B-27		KH-8 27	25 Jun 1970	Va	Titan-3B Agena-D ?
46, 3B-28		KH-8 28	18 Aug 1970	Va	Titan-3B Agena-D ?
47, 3B-29		KH-8 29	23 Oct 1970	Va	Titan-3B Agena-D ?
48, 3C-19	70093	DSP 1	6 Nov 1970	CC	Titan-3(23)C	Partial failure
49, 3B-30		KH-8 30	21 Jan 1971	Va	Titan-3B Agena-D ?
50, 3B-36	71021	Jumpseat 1	21 Mar 1971	Va	Titan-3(33)B Agena-D
51, 3B-31		KH-8 31	22 Apr 1971	Va	Titan-3B Agena-D ?
52, 3C-20	71039	DSP 2	5 May 1971	CC	Titan-3(23)C
53, 3D-1		KH-9 1	15 Jun 1971	Va	Titan-3D
54, 3B-32		KH-8 32	12 Aug 1971	Va	Titan-3B Agena-D ?
55, 3B-33		KH-8 33	23 Oct 1971	Va	Titan-3B Agena-D ?
56, 3C-21	71095	A: DSCS 2-01 B: DSCS-2 02	3 Nov 1971	CC	Titan-3(23)C
57, 3D-2		KH-9 2 / Subsat Ferret 28	20 Jan 1972	Va	Titan-3D
58, 3B-37	n/a	Jumpseat 2	16 Feb 1972	Va	Titan-3(33)B Agena-D	Failure
59, 3C-22		DSP 3	1 Mar 1972	CC	Titan-3(23)C
60, 3B-34		KH-8 34	17 Mar 1972	Va	Titan-3B Agena-D ?
61, 3B-35		KH-8 35	20 May 1972	Va	Titan-3B Agena-D ?	Failure
62, 3D-5		KH-9 3 / Subsat Ferret 29	7 Jul 1972	Va	Titan-3D
63, 3B-39		KH-8 36	1 Sep 1972	Va	Titan-3B Agena-D ?
64, 3D-3		KH-9 4 / Subsat Ferret 30	10 Oct 1972	Va	Titan-3D
65, 3B-40		KH-8 37	21 Dec 1972	Va	Titan-3B Agena-D ?
66, 3D-6		KH-9 5	9 Mar 1973	Va	Titan-3D
67, 3B-41		KH-8 38	16 May 1973	Va	Titan-3B Agena-D ?
68, 3C-24		DSP 4	12 Jun 1973	CC	Titan-3(23)C
69, 3B-43		KH-8 39	26 Jun 1973	Va	Titan-3B Agena-D ?	Failure
70, 3D-7		KH-9 6	13 Jul 1973	Va	Titan-3D
71, 3B-38		Jumpseat 3	21 Aug 1973	Va	Titan-3(33)B Agena-D
72, 3B-42		KH-8 40	27 Sep 1973	Va	Titan-3B Agena-D ?
73, 3D-8		KH-9 7 / Subsat Ferret 31 / Subsat Ferret 32	10 Nov 1973	Va	Titan-3D
74, 3C-26	73100	A: DSCS 2-03 B: DSCS 2-04	13 Dec 1973	CC	Titan-3(23)C
75, 3E-1/ TC-1	n/a	Sphinx / Viking SD	12 Feb 1974	CC	Titan-3E Centaur-D1T	F
76, 3B-44		KH-8 41	13 Feb 1974	Va	Titan-3B Agena-D ?
77, 3D-9		KH-9 8 / Subsat Ferret 33 / P73 7	10 Apr 1974	Va	Titan-3D
78, 3C-27	74039	ATS 6	30 May 1974	CC	Titan-3(23)C
79, 3B-45		KH-8 42	6 Jun 1974	Va	Titan-3B Agena-D ?
80, 3B-46		KH-8 43	14 Aug 1974	Va	Titan-3B Agena-D ?
81, 3D-4		KH-9 9 / Subsat Ferret 34 / P73 5	29 Oct 1974	Va	Titan-3D
82, 3E-2/ TC-2	74097	Helios 1	10 Dec 1974	CC	Titan-3E Centaur-D1T St-37E
83, 3B-50		Jumpseat 4	10 Mar 1975	Va	Titan-3(34)B Agena-D
84, 3B-48		KH-8 44	18 Apr 1975	Va	Titan-3B Agena-D ?
85, 3C-25	75040	A: DSCS 2-05 B: DSCS 2-06	20 May 1975	CC	Titan-3(23)C	Partial failure
86, 3D-10		KH-9 10 / Subsat Ferret 35	8 Jun 1975	Va	Titan-3D
87, 3E-4/ TC-4	75075	Viking 1	20 Aug 1975	CC	Titan-3E Centaur-D1T
88, 3E-3/ TC-3	75083	Viking 2	9 Sep 1975	CC	Titan-3E Centaur-D1T
89, 3B-47		KH-8 45	9 Oct 1975	Va	Titan-3B Agena-D ?
90, 3D-13		KH-9 11 / Subsat Ferret 36	4 Dec 1975	Va	Titan-3D
91, 3C-29		DSP 5	14 Dec 1975	CC	Titan-3(23)C
92, 3E-5/ TC-5	76003	Helios 2	15 Jan 1976	CC	Titan-3E Centaur-D1T St-37E
93, 3C-30	76023	A: LES 8 B: LES 9 C: Solrad 11A D: Solrad 11B	15 Mar 1976	CC	Titan-3(23)C
94, 3B-52		KH-8 46	22 Mar 1976	Va	Titan-3(23)B Agena-D
95, 3B-55		SDS 1	2 Jun 1976	Va	Titan-3(34)B Agena-D
96, 3C-28		DSP 6	26 Jun 1976	CC	Titan-3(23)C
97, 3D-14		KH-9 12 / Subsat Ferret 37 / P74 2	8 Jul 1976	Va	Titan-3D
98, 3B-56		SDS 2	6 Aug 1976	Va	Titan-3(34)B Agena-D
99, 3B-51		KH-8 47	15 Sep 1976	Va	Titan-3(24)B Agena-D
100, 3D-15		KH-9 13 /Subsat Ferret 38 /Subsat Ferret 39	19 Dec 1976	Va	Titan-3D
101, 3C-23		DSP 7	6 Feb 1977	CC	Titan-3(23)C
102, 3B-54		KH-8 48	13 Mar 1977	Va	Titan-3(23)B Agena-D
103, 3C-32	77034	A: DSCS 2-07 B: DSCS 2-08	12 May 1977	CC	Titan-3(23)C
104, 3D-17		KH-9 14	27 Jun 1977	Va	Titan-3D
105, 3E-7/ TC-7		Voyager 2 [Star-37E]	20 Aug 1977	CC	Titan-3E Centaur-D1T
106, 3E-6/ TC-6		Voyager 1 [Star-37E]	5 Sep 1977	CC	Titan-3E Centaur-D1T
107, 3B-58		KH-8 49	23 Sep 1977	Va	Titan-3(23)B Agena-D
108, 3B-49		Jumpseat 5	25 Feb 1978	Va	Titan-3(34)B Agena-D
109, 3D-20		KH-9 15 / Subsat Ferret 40	16 Mar 1978	Va	Titan-3D
110, 3C-35	n/a	DSCS-2 9 / DSCS-2 10	25 Mar 1978	CC	Titan-3(23)C	Failure
111, 3C-33	78058	Vortex 1	10 Jun 1978	CC	Titan-3(23)C
112, 3D-18		KH-11 1	14 Jun 1978	Va	Titan-3D
113, 3B-57		SDS 3	5 Aug 1978	Va	Titan-3(34)B Agena-D
114, 3C-36	78113	A: DSCS 2-11 B: DSCS 2-12	14 Dec 1978	CC	Titan-3(23)C
115, 3D-21		KH-11 2 / Subsat Ferret 41	16 Mar 1979	Va	Titan-3D
116, 3B-61		KH-8 50	28 May 1979	Va	Titan-3(24)B Agena-D
117, 3C-31		DSP 8	10 Jun 1979	CC	Titan-3(23)C
118, 3C-34	79086	Vortex 2	1 Oct 1979	CC	Titan-3(23)C
119, 3C-37	79098	A: DSCS 2-13 B: DSCS 2-14	21 Nov 1979	CC	Titan-3(23)C
120, 3D-19		KH-11 3	7 Feb 1980	Va	Titan-3D
121, 3D-16		KH-9 16 / Subsat Ferret 42	18 Jun 1980	Va	Titan-3D
122, 3B-53		Jumpseat 6	13 Dec 1980	Va	Titan-3(34)B Agena-D
123, 3B-59		KH-8 51	28 Feb 1981	Va	Titan-3(24)B Agena-D
124, 3C-40		DSP 9	16 Mar 1981	CC	Titan-3(23)C
125, 3B-60		SDS 4	24 Apr 1981	Va	Titan-3(34)B Agena-D	Partial failure
126, 3D-22		KH-11 4	3 Sep 1981	Va	Titan-3D
127, 3C-39	81107	Vortex 3	31 Oct 1981	CC	Titan-3(23)C
128, 3B-62		Indigo Test + 4 Subsat	21 Jan 1982	Va	Titan-3(23)B Agena-D
129, 3C-38		DSP 10	6 Mar 1982	CC	Titan-3(23)C
130, 3D-24		KH-9 17 / Subsat Ferret 43	11 May 1982	Va	Titan-3D
131, 34D-1	82106	A: DSCS 2-15 B: DSCS 3-01	30 Oct 1982	CC	Titan-34D IUS
132, 3D-23		KH-11 5	17 Nov 1982	Va	Titan-3D
133, 3B-63		KH-8 52	15 Apr 1983	Va	Titan-3(24)B Agena-D
134, 34D-5		KH-9 18 / Subsat Ferret 44	20 Jun 1983	Va	Titan-34D
135, 3B-65		Jumpseat 7	31 Jul 1983	Va	Titan-3(34)B Agena-D
136, 34D-10	84009	Vortex 4	31 Jan 1984	CC	Titan-34D Transtage
137, 34D-11		DSP 11	15 Apr 1984	CC	Titan-34D Transtage
138, 3B-67		KH-8 53	17 Apr 1984	Va	Titan-3(24)B Agena-D
139, 34D-4		KH-9 19	25 Jun 1984	Va	Titan-34D
140, 3B-64		SDS 5	28 Aug 1984	Va	Titan-3(34)B Agena-D
141, 34D-6		KH-11 6	4 Dec 1984	Va	Titan-34D
142, 34D-13	84129	DSP F12	22 Dec 1984	CC	Titan-34D Transtage
143, 3B-69		SDS 6	8 Feb 1985	Va	Titan-3(34)B Agena-D
144, 34D-7		KH-11 7	28 Aug 1985	Va	Titan-34D	Failure
145, 34D-9		KH-9 20	18 Apr 1986	Va	Titan-34D	Failure
146, 3B-66		SDS 7	12 Feb 1987	Va	Titan-3(34)B Agena-D
147, 34D-15		KH-11 8	26 Oct 1987	Va	Titan-34D
148, 34D-8	87097	DSP 3-1	29 Nov 1987	CC	Titan-34D Transtage
149, 34D-3	88077	Vortex 5	2 Sep 1988	CC	Titan-34D Transtage	Failure
150, 34D-14	88099	KH-11 9	6 Nov 1988	Va	Titan-34D
151, 34D-16	89035	Vortex 6	10 May 1989	CC	Titan-34D Transtage
152, 34D-2	89069	A: DSCS 2-16 B: DSCS 3-04	4 Sep 1989	CC	Titan-34D Transtage
153, CT-1	90001	A: Skynet 4A B: JCSat 2	1 Jan 1990	CC	Commercial-Titan-3	Skynet 4A: PAM-D2 JCSat 2: Orbus-7S
154, CT-2	90021	Intelsat 603	14 Mar 1990	CC	Commercial-Titan-3	Partial failure [Orbus-21S]
155, CT-3	90056	Intelsat 604	23 Jun 1990	CC	Commercial-Titan-3	[Orbus-21S]
156, CT-4	92063	Mars Observer	25 Sep 1992	CC	Commercial-Titan-3	[TOS-21H]


 Titan 4

by Jean-Jacques Serra

listing by Gunter Krebs

After being called CELV (Complementary Expendable Launch Vehicle) for a while and then Titan 34D7, the Titan 4 is the most recent and most powerful one. The solid booster were again elongated (7 segments i.e. 34.4 m) and provide now 7120 kN each during 126 seconds. The first stage was enhanced by 2.3 m (26.4 m) and burns during 186 seconds. The second stage was enhanced by 0.5 m (9.9 m) and burns during 240 s.

Titan 4 exists in 5 versions. Titan 401 feature a Centaur G' top stage and can deliver 4.5 tons in GEO. Titan 402 equiped with a solid IUS orbits 2.4 tons on the Clarke Belt. Titan 403, 404 and 405 have no top stage. The 2 first ones deliver 14 and 13.4 tons respectivly in low polar orbit while the latter (405) delivers 17.6 tons in low orbit from Cape Canaveral.

An enhanced version named Titan 4B should be introduced late 1996. The major modification is the replacement of the 7-segment boosters (UTC/CSD) by 3-segment ones (HTPB) built by Hercules. Those new boosters will measure 34.2 m high for 3.2 m diameter and will provide 7560 kN during 145 seconds. The payload in orbit will then reach 21.9 tons in LEO, and versions 401 & 402 will offer 5.8 and 2.9 tons in GEO.

Titan 4 types

Titan 401: always with Centaur-G' (GEO)

Titan-402: always with IUS (polar orbit)

Titan-403: no upper stage, Vandenberg (LEO)

Titan-404: no upper stage, Vandenberg (LEO)

Titan-405: no upper stage, Cape Canaveral (LEO)

The difference between 403 and 404 is the type of payload adapter. One has a system for acomodating Shuttle type payloads, but information is conflicting, which one.

Titan 4 launches

#	Launch id	Payload	Launch Date	Site	Type	Status/Comment (orbit in perigee x apogee x inclination x period)
1, K1	89046	DSP 3-2	14 Jun 1989	C LC41	402 IUS
2, K4	90050	NOSS 12	08 Jun 1990	C LC41	405
3, K6	90095	DSP 3-3	13 Nov 1990	C LC41	402 IUS
4, K5	91017	Lacrosse 2	08 Mar 1991	V SLC4E	404
5, K8	91076	NOSS 13	08 Nov 1991	V SLC4E	403
6, K3	92083	KH 12-2	28 Nov 1992	V SLC4E	404 TPA
7, K11	n/a	NOSS 14	2 Aug 1993 at 19:59 UT	V SLC4E	403	Failure: exploded after 1 min 41 s
8, K10	94009	Milstar 1-1	7 Feb 1994 at 21:47 UT	C LC40	401 Centaur-G' (TC12)
9, K7	94026	USA 103	3 May 1994 at 15:55 UT	C LC41	401 Centaur-G' (TC10)
10, K9	94054	USA 105	27 Aug 1994 at 08:58 UT	C LC41	401 Centaur-G' (TC11)
11, K14	94084	DSP 3-5	22 Dec 1994 at 22:19 UT	C LC40	402 (K14) IUS
12, K23	95022	USA 110	14 May 1995 at 13:45 UT	C LC40	401 (K23) Centaur-G' (TC17)
13, K19	95034	USA 112	10 Jul 1995 at 12:38 UT	C LC41	401 (K19) Centaur-G' (TC8)	26 m payload shroud
14, K21	95060	Milstar 1-2	06 Nov 1995 at 05:15 UT	C LC40	401 (K21) Centaur-G' (TC13)
15, K15	95066	KH 12-3	05 Dec 1995 at 21:18 UT	V SLC4E	404 (K15)
16, K16	96026	USA 118	24 Apr 1996 at 23:37 UT	C LC41	401 Centaur (TC15)	23 m payload shroud
17, K22	96029	NOSS 15	12 May 1996 at 21:32 UT	V SLC4E	403
18, K2	96038	USA 125	03 Jul 1996 at 00:31 UT	C	405
19, K13	96072	KH 12-4	20 Dec 1996 at 06:44 UT	V SLC4E	403
20, B24	97008	DSP 3-6	23 Feb 1997 at 20:20 UT	C LC40	402B IUS
21, B33	97061	Cassini & Huygens	15 Oct 1997 at 08:43 UT	C LC40	401B Centaur-G' (TC21)	payload: 5650 kg
22, A18	97064	Lacrosse 3	24 Oct 1997 at 02:32 UT	V SLC4E	403A
23, A17	97068	USA 136	8 Nov 1997 at 02:05 UT	C LC41	401A Centaur-G' (TC16)
24, B25	98029	USA 139	9 May 1998 at 01:38 UT	C LC40	401B Centaur-G' (TC18)
25, A20	n/a	USA (adv Vortex / Mercury)	12 Aug 1998 at 11:30 UT	C LC41	401A Centaur-G' (TC9)	Failure: exploded after  42 s, wiring failure (short) in a harness
26, B32	99017	DSP 3-7	9 Apr 1999 at 17:01 UT	C LC41	402B IUS	Partial failure: the second stage of the upper stage vehicle IUS (Boeing) failed to separate. Problem with an electrical plug.
27,	99023	Milstar 2-1	30 Apr 1999 at 16:30 UT	C	401B Centaur-G' (TC14)	Partial failure: the top stage malfunctionned: the 3 burns were done on the first orbit instead of over 6 hours. Software error.
28, B12	99028	USA 144	22 May 1999 at 09:36 UT	V SLC4E	4B	no upper stage

40 more titan 4 have been ordered in Oct 1998


Vanguard launch vehicle
 Vanguard

by Jean-Jacques Serra

listing by Gunter Krebs

Origin: sounding rocket Viking

In 1946 the US Navy's NRL (Naval Research Laboratory) launched the study of a high performance sounding rocket named HASR-2 (High Altitude Sounding Rocket) to replace the V2s when there would be no more left. This leaded th the developement of the Neptune rocket, later renamed Viking. The Glenn L. Martin company was contacted to built 10 rockets, 4 were reordered later.

The Viking propulsion was granted to Reaction Motors which already produced the Bell X1 rocket-plane. The new motor was feed with alcohol and liquid oxygen by turbopomps. It provided 91.5 kN thrust. Names XLR-10 this motor was a high technology one at the time because it used regenerating cooling system and a deployable nozzle. The rocket also had integral tanks to lighten the structure and a 3-axis stabilization with little nozzles around the it to orient it after the shutdown of the main engine.

There are 2 generations in the Viking series: the models 1 to 7 that were 81 cm diameter and models 8 to 14 (shorter) that were 114 cm diameter. The heights were ranging from 14.8 m to 12.8 m and the takeoff weights were between 4.37 tons and 6.81 tons. Between May 1949 and May 1959 only one failure occured with Viking-8. All Vikings were launched from White Sands except Viking-4 which was launched from the deck of USS Norton Sound and the 2 last ones which where used as test vehicles for the Vanguard program, launched from Cape Canaveral.

Vanguard

In July 1955 the United States announced their intention of launching small earth artificial satellites as their contribution to the International Geophysical Year of 1957-1958. Two months later the Vanguard project was selected to launch those satellites.

The project was granted to the Glenn L. Martin Company which was to use a modified Viking rocket as first stage. In fact the differences were important: the diameter stayed the same but the length was extended to 13.4 m and the propulsion system was changed. This new motor built by General Electric was derived from the Hermes A-3B project. Named X-405 it used kerosene and LOX, had a deployable nozzle and provided 120 kN (A-3B: 100 kN) during 145 seconds. The X-405 had a re-generated cooling system and was powered by turbopomps.

The second stage of Vanguard was designed by Aerojet General. It was an extrapolation of the Aerobee Hi: the diameter was extended to 81 cm. The AJ-10 motor had a deployable nozzle and its thrust was then  33 kN with a lifetime of 120 s. It was feeded with a mix a stockable propellant helium-pressurized: UDMH (Unsymmetrical DiMethyl Hydrazine) and WIFNA (White Inhibited Fuming Nitric Acid). This second stage also contained the flight control equipement and the 3rd stage table rotator. During the propulsed flight phases the rocket was controled with the nozzles and during the balistic phase after the 2nd stage shutdown by helium jets.

The third stage was equipped with a 33-KS-2800 solid booster from Grand Central Rocket Company which provided 12.5 kN thrust during 33 seconds. It was replaced for the last launch by a lighter motor developped by Alleghany Ballistics Laboratories. This glass fiber reinforced platic structure X-248 Altair engine provided 13.8 kN.

Finally the Vanguard rocket weighed 21.6 m high with the cap. The payload was only of a few kilograms in the first version and reached 20 kg with the last model.

After 2 test flights with a Viking first stage (TV-0 & TV-1) in Dec 1956 & May 1957 the launch of a Vanguard first stage with mockups of the top stages (TV-2) occured in Oct 1957, a few days after the launch of Sputnik 01. The successful Russian launch cause the program to be accelerated despite reliability questions. Two failures (TV-3 & TV-3A) occured before the success of Vanguard 1 in March 1958. Four failures (TV-5 & SLV-1 to -3) occured before a success in Feb 1959. The third and last success occured in Sep 1959 after 2 more failures (SLV-5 & -6).

Three success out of 11 flights was not a good score especially because the Russian failures were keep secret. Worth to be noted the Vanguard top stages were used to design the Able (see Thor Able) and then the Delta (see Thor Delta) which were very reliable. Also the stages derived from Altair were used on several launchers (Thor, Atlas, Scout, etc.).

Vanguard launches

#	Launch id	Payload	Launch Date	Site	Status/Comment (orbit in perigee x apogee x inclination x period)
1, TV-3	FTO	Vanguard 1A	6 Dec 1957	C	Failure: exploded after 2 s
2, TV-3BU	FTO	Vanguard 1B	5 Feb 1958	C	Failure: control lost after 57 s
3, TV-4	58002	Vanguard 1	17 Mar 1958	C
4, TV-5	FTO	Vanguard 2A	28 Apr 1958	C	Failure: 3rd stage failed to ignite
5, SLV-1	FTO	Vanguard 2B	27 May 1958	C	Failure
6, SLV-2	FTO	Vanguard 2C	26 Jun 1958	C	Failure
7, SLV-3	FTO	Vanguard 2D	29 Sep 1958	C	Failure
8, SLV-4	59001	Vanguard 2	17 Feb 1959	C
9, SLV-5	FTO	Vanguard 3A	13 Apr 1959	C	Failure
10, SLV-6	FTO	Vanguard 3B	22 Jun 1959	C	Failure
11, TV-4BU	59007	Vanguard 3	18 Sep 1959	C	Partial failure: 3rd stage failed to separate from payload


 VLS

by Jean-Jacques Serra

Brazil's spance activity started in the early sixties with the creation of a space research national commission. It was composed of the space physics lab of Sao José dos Campos and a sounding rocket launch site 20 km south of Natal.

The first Brazilian realization was the Sonda-1 rocket. It weighed 60 kg and could send 4 kg to 60-75 km altitude. In 1966 the 360 kg Sonda-2 could send 45 kg at 80 km altitude. This 30 cm diameter rocket was later used as top stage for the Sonda-3 which could reach 600 km altitude with 60 kg of payload. Sonda-3 was 1.6 tons, 8 m high. It featured a 56 cm diameter first stage. It was first launched on 26 Feb 1976.

The startup of this rocket was soon followed by a US and French embargo on hardware (solid fuel and electronic equipment) needed to build them. Brazil then asked Germany and Taiwan for help to go on with their civilian and military rocket program.

A new sounding rocket (being prepared since 1974 with the help of Germany by the Instituto de Atividades Espacias, later known as Instituto de Aeronautica e Espaco) was launched on 21 Nov 1984 from the Barreira do Inferno launch site. This two-stage rocket was 11 m high. It weighed 7.3 tons at takeoff and reaches 650 km altitude with 500 kg payload. The first stage is 1 m diameter and 7.7 tons. It provides 203 kN thrust (ground level) during 60 seconds. The second stage is 56 cm diameter and provides 95 kN during 28 seconds.

In the mid eighties Brazil started several ballistic missiles programs. The SS-300 (Avibas) had a 300 km range. It was 11.5 m long and 1 m diameter. It weighed 8 tons at takeoff with a 1 ton charge. Several test flights where carried on in 1987 but the program was cancelled in 1989. The MB/EE-150 (Orbita) has 150 km range; it was 12 m long and weighed 4.5 tons with 500 kg of military payload. This program was also cancelled but it contributed to reinforce the embargo on inertial and pyrotechnic components.

VLS (Veiculo Lancador de Satelites)

The VLS launcher was developped by the Orbita company under control of the Centro Tecnico Aerospacial (CTA) and of the Instituto de Aeronautica e Espaco (IAE). It is a 4-stage solid fuel rocket that weighs approx. 50 tons and measures 19 m high. It is made of a central body to which 4 boosters (derived from Sonda-4) are attached. Those boosters are 1 m diameter, 9 m long and weigh 8.5 tons. They provide 309 kN thrust during 60 seconds. The central body has 3 parts of 1 m diameter. The first one is very similar to the boosters with a nozzle adapted to altitude. The second provides 213 kN thrust during 57 seconds while the third provides 34 kN during 68 seconds. The VLS is designed to deliver 200 kg of payload in LEO at 750 km, 25° orbit or at 500 km in sun-synchronous orbit.

A first test of the 1/3 model failed in December 1985. A second one was successful in May 1989. This VLS-R2 confirmed correct separation of the stages. Those tests were made from the Barreira do Inferno base but the VLS should be launched from a new base at Alcantara (2.2° south) from where a Sonda-4 was launched in February 1990. In April 1993 Brazil fired an experimental vehicle (VS-40) made of the last two stages of VLS. The vehicle reached 1248 km altitude.

The VLS program developement is slow due to the embargo which bares importation of the inertial module.

VLS launches

#	Launch id	Payload	Launch Date	Site	Type	Status/Comment (orbit in perigee x apogee x inclination x period)
1	FTO	SCD 2A	2 Nov 1997 at 12:25 UT	A		Failure: 1 1-stage motor failed
Notes: A: Alcantara, Maranhao state Brazil (2°17' S, 44°23' W)


 Zenit

by Jean-Jacques Serra

listing by Gunter Krebs

The Zenit rockets are not derived from ballistic missiles as most of the NPO Yuzhnoye (Dniepropetrovsk, Ukraine) achievements. There ware designed from the start for space missions. The first stage of the Zenits is used as booster for the Energia launcher (known as Zenit-1).

Two-stage Zenit-2 (J-1/SL-16)

The Zenit 2 (11K77) has a constant diameter of 3.9 m. It is 57 m high and weighs 460 tons at liftoff with a 15-ton payload. Both stages use liquid propellant: kerosene-LOX

The first stage is equipped with a RD-170/171 motor (Glouchko, NPO Energomash) with 4 combustion chambers. It provides 7259 kN thrust at ground level and 7911 kN is vaccum (ISp = 337 s). The RD-171 version of the motor can be oriented on 2 axis, the RD-170 Energia on 1 axis. The stage contains 318.8 tons propellant and burns during 140 seconds.

The second stage features an RD-120 (Glouchko, NPO Energomash) with single fixed nozzle. It is joined with 4 vernier motors (NPO Yuzhnoye) for pilotage. It provides 834 kN thrust (ISp = 350 s) and can function during upto 315 seconds to match the mission's need.

Zenit 2 is intended for LEO and MEO upto 1500 km altitude. The maximum payload weight is 13.74 tons in circular 200 km orbit 51° or 11.38 tons in sun-synchronous 200 km/99° from Tyuratam.

Until now it has launched:

- MEO: SIGINT (Cosmos series) and remote sensing (Resurs O)

- LEO: Kuban photographic reconnaissance satellites (Cosmos series)

Possible evolutions:

- 3-stage version with a Block-DM of Proton

- 3 or 4 stage version with NTO-UDMH propellant

Zenit launches

#	Launch id	Payload	Launch date	Type	Status (orbit in perigee x apogee x inc. x period)
1	n/a	R&D suborbital	13 Apr 1985	Zenit-2
2	85053	R&D suborbital	21 Jun 1985	Zenit-2	intended to be suborbital but some debris reached orbit
3	85097	Cosmos 1697 [Tselina-2]	22 Oct 1985	Zenit-2
4	85121	Cosmos 1714 [Tselina-2]	28 Dec 1985	Zenit-2	Failure: second stage failed to ignite
5	86056	Cosmos 1767	30 Jul 1986	Zenit-2
6	86080	Cosmos 1786	22 Oct 1986	Zenit-2
7	87016	Cosmos 1820	14 Feb 1987	Zenit-2
8	87027	Cosmos 1833 [Tselina-2]	18 Mar 1987	Zenit-2
9	87041	Cosmos 1844 [Tselina-2]	13 May 1987	Zenit-2
10	87065	Cosmos 1871	1 Aug 1987	Zenit-2
11	87071	Cosmos 1873	28 Aug 1987	Zenit-2
12	88039	Cosmos 1943 [Tselina-2]	15 May 1988	Zenit-2
13	88102	Cosmos 1980	23 Nov 1988	Zenit-2
14	90046	Cosmos 2082 [Tselina-2]	22 May 1990	Zenit-2
15	n/a	[Tselina-2]	4 Oct 1990	Zenit-2	Failure: first stage engine exploded after 3 seconds
16	n/a	[Tselina-2]	30 Aug 1991	Zenit-2	Failure: second stage exploded
17	n/a	[Tselina-2]	5 Feb 1992	Zenit-2	Failure: second stage malfunction
18	92076	Cosmos 2219	17 Nov 1992	Zenit-2
19	92093	Cosmos 2227 [Tselina-2]	25 Dec 1992	Zenit-2
20	93016	Cosmos 2237	26 Mar 1993	Zenit-2
21	93059	Cosmos 2263	16 Sep 1993	Zenit-2
22	93059	Cosmos 2278	23 Apr 1994	Zenit-2
23	94053	Cosmos 2290	26 Aug 1994	Zenit-2
24	94074	Resurs O1-3	4 Nov 1994	Zenit-2
25	94077	Cosmos 2297	24 Nov 1994	Zenit-2
26	95058	Cosmos 2322	30 Oct 1995	Zenit-2
27	96051	Cosmos 2333	4 Sep 1996	Zenit-2
28	n/a	[Tselina-2]	20 May 1997 at 07:07 UT	Zenit-2	Failure: first stage engines shutdown 48 s after takeoff
29	98043	A: Resurs O1-4 B: Fasat Bravo C: Tmsat D: Techsat 2 E: Wespac F: Safir 2	10 Jul 1998 at 06:27 UT	Zenit-2
?	98045	Cosmos 2360	28 Jul 1998 at 9:15 UT	Zenit-2
30	n/a	Globalstar 5, 7, 9, 10, 11, 12, 13, 16, 17, 18, 20, 21	9 Sep 1998 at 20:29 UT	Zenit-2	Failure: second stage main engines shut down 272s after takeoff.
31	99014	Demosat	28 Mar 1999 at 01:30 UT	Zenit-3SL	First Sea Launch
32	99039	Okean O2-1	17 Jul 1999 at 06:38 UT	Zenit-2
Notes: All launches from Tyouratam.


 Agena top stages

by Jean-Jacques Serra

The Agena stage was developped by Lockheed for the USAF. The first version used for Discoverer in 1959 was equipped with a Bell 8096 motor derived from the Hustler designed for the PDBP (Powered Disposable Bomb Pod) for the B-58 bombardier. This motor used the nitric acid/UDMH couple as propellant; it was capable of 67 kN during 2 minutes (ISp = 250 seconds). It couldn't be re-ignited on the contrary of the 1960 Agena-B. The Agena-D version featured a more powerful engine with 71 kN and a doubled burning time. All those rockets had the same diameter (1.52 m) and a variable length depending on the payload to which there wore most often attached.

The Agena was used from 1959 to 1987. It's the American most used top stage with 362 launches including a majority of military payloads.

Thor Agena

Atlas Agena

Titan 3 Agena

The titan 3B was a military launcher using an Agena top stage. It was used to launch reconnaissance satellites from the KH-8 series between 1966 and 1984. The same launcher was used for the classified SDS and Jumpseat launches to Molniya type orbits. In 1975 a version with a a longer first stage and wider cap was introduced: Titan 34B (or Titan 3B Ascent Agena). It was specifically devoted to those military launches.


 Burner top stages

by Jean-Jacques Serra

Altair, the old solid fuel third stage of the Vanguard rocket was spin stabilized. It was used the same way as top stage for Delta and Scout. The X-248, which was the motor of the Altair, had a plastic structure reinforced by fiberglass. It was developped by Alleghany Ballistics Laboratories and provided 13.8 kN thrust during 27 seconds.

Boeing's Burner used the same booster but equipped with a 3-axis stabilization system. It was associated to Thor in 1965 to launch meteorological satellites (6 flights: 5 successful).

An enhanced version designated Burner-2 was introduced in Sep 1966. It was based on the use of the Thiokol Star-37B (TE-M-364-2) derived from the retro-rocket of the Surveyor lunar probes. This 94 cm diameter motor weighed 807 kg (including 654 kg propellant) and provided 44.5 kN suring 42 seconds. It was placed inside a 1.65 m diameter cap. This stage was used upon:

- Thor first stage to launch 10 DMSPs and 2 STP satellite

- Atlas first stage to launch STP payloads (2 flights: 1 failure)

Burner-2A was introduced in 1971. It was a 2-stage version with the second stage based on a Star-37D (TE-M-364-15) which performances were close to Star-37B. Il was mounted on Thor first stages to launch DMSP meteorology satellites (13 flights: 2 failures).


 Castor

by Jean-Jacques Serra

Castor 1 & 2

The Thiokol Castor booster, used since 1960 as second stage for Scout were derived from the tactical Sergeant missile. This missile, built by Sperry, was 10.6 m long for 79 cm diameter and weighed 4.5 tons. Its range was: 45 to 140 km.

The Castor 1 was used by all the Scout-X version and was replaced my Castor 2 (TX354-3) when Scout-A1 was introduced in 1965.

Castor

Designation	Length (m)	Diameter (m)	Mass (t)	Main engine Thrust (kN)	Main engine SI (sec.)
Castor 1 (TX33)	5.92	0.79	3.85	286	27.4
Castor 2 (TX354)	5.96-6.27	0.79	4.32-4.42	259-275	37
Castor 4 (TX526)	9.07	1.02	10.53	428	53.9
Castor 4A (TX780)	8.09-920	1.02	11.58	436-476	53.1
Castor 4B (TX859)	8.98	1.02	11.48	429	60.9

From 1963 on, the Thor first-stage-based launchers were equipped with Castor solid boosters to get the TAT (Thrust Augmented Thor). The TAT Agena was launched in 1963, the TAT Delta (or TAD) in 1964. Those Castor-1 & Castor-2 boosters were then used by groups of 3, 6 (Delta M6) and finally 9 (Delta 900). The last models were used from 1975 on by the Japanese N1, N2 and H1 rockets.

The boosters of Sergeant missiles are still used by OSC for Starbird (targets for the ERINT program), LCLV (Low Cost Launch Vehicle) and Storm (targets for the THAAD program).

Castor 4 & 4A

After 1975, when the only Thor first stage-based was the Delta (3900 series) the Castor-2 were replaced by Castor-4 (TX526) of 1.02 m diameter that we herited from the Athena-H sounding rocket. In 1989 an enhanced version was introduced on the Delta 2 (6900 series): Castor-4A (TX780) weighing 11.6 tons. Two pairs of Castor-4A boosters also equip the Atlas 2 (2AS version) since 1993.

The light launcher Conestoga was designed from associated Castor-4. The most powerful version, Conestoga 1620, is made of 6 Castor-4 (4 Castor-4B with deployable nozzle and 2 Castor-4A with fixed nozzle) surrounding a Castor-4B. Four Castors are fired at launch time (1st stage), 2 are ignited then (2nd stage) and the central Castor-4 acts as the third stage. The top stage is a Star-48, also built by Thiokol.

The Castor-4A boosters are also used by OSC for Prospector sounding rockets since 1991. The Maxus rocket (German & Swedish) is the largest sounding rocket fired from Europe (Kiruna). It is also made of a Castor-4B; with 12.3 tons and 500 kg payload.

Castor 120 GT

The Castor-120 is a large solid fuel booster derived from the MX Peacekeeper (TU 903) missile. This booster is 8.89 m long and 2.34 m diameter. It weighs about 54 tons. Castor-120 was modified to provide a smaller acceleration than the TU 903: 1546 kN (in vacuum) during 86 seconds.

Two light launchers are based on it: Taurus from OSC (with the 3 Hercules stages of Pegasus) and Athena from LM (with an Orbus 21 UTC/CSD).


 Centaur top stages

by Jean-Jacques Serra

Centaur on Atlas

The Centaur top-stage was the first cryogenic rocket stage. The Pratt & Whitney RL10 engine consuming liquid oxygen and hydrogen had a long and difficult development. Its design started in 1958. It first flew in 1962 but didn't launch a real payload before 1966. The Centaur stage was designed to be used by Atlas. It was 3.05 m in diameter and 9.1 m in length. In its operational version it was equipped with two RL10 A-3-3 engines with a thrust of 66.7 kN each. It carried 13.8 tons propellant and could burn during 450 seconds with several ignitions.

In the late-70ies the Atlas Centaur program was to be abandonned since NASA had decided to transfer all launches to the Shuttle. In fact STS was less available than expected and the Atlas launch program was resumed (with the help of Intelsat finances) with a simplified motor. On the RL10 A-3-3A (73.4 kN thrust) the turbopump feeding was replaced by a pressurized tank system. This new Centaur was first launched in 1984 with an Atlas-G (streched by 2 meters). The GTO capacity then reached 2.3 tons.

In 1987 the augmented Atlas Centaur was selected by the USAF as the MLV2 standard launcher. This new launcher is refered to as Atlas-2. The first stage was streched by 2.7 m and the second stage by 0.9 m. This new Centaur takes 16.8 tons of propellant and can burn up to 473 seconds. Atlas-2A is different by its second stage RL10 A-4 engines with deployable nozzle. Atlas-2AS is still more powerful. It is made from Atlas-2A to which two pairs of Castor-4A boosters are added. Each pair ignites one after the other. Thus GTO capacity raises to 2.8, 3.1 and 3.7 tons respectively for Atlas 2, 2A and 2AS.

Evolution of Centaur's propulsion system

Designation	First launch	Main engine Thrust (kN)	Main engineSI (sec.)	Applications
RL10 A-1	1962	66.7	425	Tests
RL10 A-3-1	1963	66.7	431	Atlas Centaur
RL10 A-3-3	1966	66.7	444	Atlas Centaur
RL10 A-3-3A	1984	73.4	446	Atlas-1 & -2
RL10 A-4	1991	92.6	449	Atlas-2A & -2AS

Statistics: the RL-10 motor made its 100th flight on the top stage Centaur of AC-114

Centaur on Titan

Between 1974 and 1977, seven Centaur were used as top stages for Titan 3 rockets, designated as Titan 3E with no major transformation. In this configuration the Centaur was placed into the cap (4.1 m diameter) which provided the thermic protection. Those launchers were devoted to US and German probles and could send 3.6 tons to Mars or Venus.

In 1983 an agreement between NASA and USAF was reached to finance the development of a stage derived from Centaur to launch military satellites and probes from the Shuttle. This new cryogenic stage was a wide body of the Centaur to optimize the volume into the Shuttle's bay. The same motors remained so as the 3.05 m diamater liquid oxygen tank while the hydrogen tank was enhanced to 4.3 m diameter. Two versions of this new stage were developped: Centaur G of 6.1 m long for the USAF and a longer version named Centaur G-prime of 9.1 m long for NASA. After the Challenger accident usage of a cryogenic stage was prohibited for security reasons.

The Centaur G-prime was then adapted to the Titan 4. This version is 4.5 m diameter and about 9 m long. It weighs 26 tons including 23 tons propellant. The motors are RL10-3-3A of 73.4 kN which can operate for up to 617 seconds. The Titan 4 with Centaur top stage is designated Titan 401. It can orbit 4.5 tons in GEO. An enhanced version with Hercules SRMU boosters will enable to place 5.8 tons on such orbits.

External resources

http://hea-www.harvard.edu/~jcm/space/misc/centaur.html


IUS
 IUS top stages

by Jean-Jacques Serra

At first called Interim Upper Stage since it was devoted to fill the gap until the Space Tug shuttle became available, it became the Intertial Upper Stage when the project was stopped.

Boeing developped the IUS from 1976 to 1981. The vehicle was aimed to act as a top stage for STS but also for the Titan military launchers. IUS is a 2-stage solid fuel vehicle featuring UTC/CSD boosters with deployable nozzles. The propellant load (HTPB) can be adjusted depending of the mission (up to -50%).

Note: a 3-stage version designed for NASA was dropped, but some of the launches did required a third stage (probes).

The whole vehicle is 5.17 m high for 2.9 m diameter and weighs 14.76 tons (Shuttle version) or 13.1 tons (Titan 34D version). The first stage (SRM 1) is 3.52 m long and 2.34 m diameter. It used the Orbus-21 motor (up to 9.7 tons propellant) providing a mean thrust of 196 kN during 154 seconds (ISp = 295 seconds). This motor is also used for the TOS perigee stages, and those (spinned) of Intelsat 6 series and for the LLV top stage. The second stage (SRM 2) is 2.1 m long and 1.61 m diameter. It features an Orbus motor (up to 2.75 tons of propellant) available in 2 versions: 6 or 6E depending on the presence of an extensible nozzle. It provides 80 kN during 103 seconds (ISp = 289 seconds or 303 seconds respectively for version 6 and 6E).

This 3-axis stabilized vehicle is very reliable. Its launch capacity to GEO is:

- 2.27 tons from STS

- 1.82 tons from Titan 34D

- 2.36 tons or 2.86 tons from Titan 4 (CSD or Hercules boosters)

Titan IUS

IUS was used twice on Titan 34D: in Octiber 1982 (1st IUS launch) and in September 1989 to launch DSCS satellites.

The Titan 4 + IUS configuration is named Titan 402. It was introduced in June 1989 and is used to launch DSP satellites.

STS IUS

IUS succeeded all its missions from the Shuttle except the first one (partial failure). After the Challenger accident the Centaur was banned from STS so IUS became the only available vehicle.

Late 1995 the missions carried out by STS IUS were: TDRS, Magnum, DSCS, DSP and probes such as Magellan, Galileo, Ulysses


 Missions

Scientific

Astronomy

Geodesy

Observation of ionosphere

Observation of high atmosphere

Observation of magnetosphere

Observation of meteorites

Observation of the Sun

Observation of the Earth

Meteorology: Geostationary satellites

Meteorology: LEO satellites

Remote sensing satellites

Telecommunications

Geostationary satellites

LEO satellites

Navigation

Navigation satellites

Special topics

Radioactive payload and debris


 Astronomy

Gamma-ray astronomy

1961

(014)	Explorer 11

1964

Cosmos 0051

1968

Cosmos 0208

Cosmos 0251

Cosmos 0264

1972

(090)	Explorer 48

1973

Cosmos 0561

1975

(072)	Cos B

1977

(049)	Signe 3

1979

(082)	Heao 3

1987

(012)	Astro C

1989

(096)	Granat

1990

(058)	Gamma

1991

(027)	GRO

IR astronomy

1983

(004)	Iras

1989

(089)	Cobe

1995

(062)	ISO

Multi-band astronomy

1989

(062)	Hipparcos

1990

(037)	HST

UV astronomy

1964

Cosmos 0051

1966

(031)	OAO 1

1968

(110)	OAO 2

1971

(030)	Tournesol

1972

(014)	TD 1A

(065)	OAO 3

1974

(070)	ANS

1975

(092)	Aura

1977

(012)	IUE

1983

(020)	Astron

1992

(031)	EUVE

1993

(062)	Alexis

1995

(004)	Spartan 204

(048)	Spartan 201-3

1997

(018)	Minisat 01

1999

(035)	Fuse

X-ray astronomy

1968

Cosmos 0208

1970

(107)	Explorer 42

1972

(065)	OAO 3

1974

(070)	ANS

(077)	Ariel 5

1975

(037)	Explorer 53

1977

(075)	Heao 1

1978

(103)	Heao 2

1979

(014)	Corsa B

(047)	Ariel 6

1983

(011)	Astro B

(051)	Exosat

1985

(048)	Spartan 101

1987

(012)	Astro C

1989

(096)	Granat

1990

(049)	Rosat

(058)	Gamma

1993

(011)	Astro D

1995

(074)	XTE

1996

(027)	SAX

1999

(022)	Abrixas

(040)	Chandra

Radio astronomy

1968

(055)	Explorer 38

1983

(067)	Prognoz 09

1991

(050)	Sara

1997

(005)	Haruka

1998

(071)	Swas

External resources

http://heasarc.gsfc.nasa.gov/

http://cossc.gsfc.nasa.gov/code661/code661.html

http://lheawww.gsfc.nasa.gov/docs/xray/branch/homepage.html


 Geodesy

1960

(009)	Echo 1

1962

(060)	Anna 1B

1964

(001)	Secor 01B

(004)	Echo 2

(064)	Explorer 22

1965

(016)	GGSE 2

(016)	GGSE 3

(016)	Secor 03

(017)	Secor 02

(027)	Secor 04

(032)	Explorer 27

(063)	Secor 05

(089)	Explorer 29

1966

(013)	Diapason

(051)	Secor 06

GGTS 1

(056)	Pageos

(077)	Secor 07

(089)	Secor 08

1967

(011)	Diadème 1

(014)	Diadème 2

(053)	GGSE 4

(053)	GGSE 5

(065)	Secor 09

DODGE

1968

(002)	Explorer 36

Cosmos 0203

Cosmos 0256

1969

Cosmos 0272

(037)	Secor 13

Cosmos 0312

1970

TOPO 1

1971

Cosmos 0409

Cosmos 0457

1972

Cosmos 0480

Cosmos 0539

1973

Cosmos 0585

1974

Cosmos 0650

Cosmos 0675

1975

(010)	Starlette

Cosmos 0708

(027)	Geos 3

(039)	Castor

Cosmos 0770

1976

Cosmos 0807

(039)	Lageos 1

Cosmos 842

1977

Cosmos 0911

Cosmos 0963

1979

Cosmos 1067

1980

Cosmos 1312 (Geo-IK)

1981

Cosmos 1410 (Geo-IK)

1982

Cosmos 1510 (Geo-IK)

1984

Cosmos 1589 (Geo-IK)

1985

Cosmos 1660 (Geo-IK)

1986

Cosmos 1732 (Geo-IK)

(061)	Ajisai

Cosmos 1803 (Geo-IK)

1987

Cosmos 1823 (Geo-IK)

1988

Cosmos 1950 (Geo-IK)

1989

Etalon 1

Etalon 2

(068)	Cosmos 2037 (Geo-IK)

1990

Etalon 3

Cosmos 2088 (Geo-IK)

1992

(052)	Topex Poseidon

(070)	Lageos 2

Cosmos 2226 (Geo-IK)

1993

(061)	Stella

1994

(078)	Geo-IK 1 (Geo-IK)

1995

GFZ 1

1997

Zeya

External resources

http://www.dgfi.badw-muenchen.de/edc/satellites.html


 Observation of ionosphere

1957

(001)	Sputnik 01

1958

(001)	Explorer 01

(003)	Explorer 03

(004)	Sputnik 03

(005)	Explorer 04

1960

(014)	Explorer 08

1961

(015)	Solrad 03

1962

(008)	Cosmos 0001

Cosmos 0002

Cosmos 0003

(015)	Ariel 1

Cosmos 0007

Cosmos 0008

(049)	Alouette 1

Cosmos 0010

Cosmos 0012

1963

Cosmos 0013

Cosmos 0015

Cosmos 0016

Cosmos 0017

Cosmos 0018

Cosmos 0019

1964

(006)	Elektron 1

(015)	Ariel 2

(038)	Elektron 3

(051)	Explorer 20

(064)	Explorer 22

(076)	Explorer 25

(086)	Explorer 26

1965

(031)	Explorer 27

(054)	Proton 1

(087)	Proton 2

(098)	Explorer 31

(098)	Alouette 2

(101)	FR 1

1966

(060)	Proton 3

1967

(042)	Ariel 3

Cosmos 0163

1968

(041)	Esro 2B

(66)	Explorer 40

(084)	Esro 1A

(103)	Proton 4

Cosmos 0255

1969

(009)	Isis 1

(083)	Esro 1B

(097)	Azur

Intercosmos 02

1970

Cosmos 0321

Intercosmos 03

Cosmos 0381

1971

(024)	Isis 2

(080)	Shinsei

Intercosmos 05

(109)	Ariel 4

(119)	Auréole 1

1972

Cosmos 0477

Cosmos 0484

Intercosmos 06

Cosmos 0490

(064)	Denpa

(092)	Esro 4

Intercosmos 08

(100)	Aeros 1

1973

Intercosmos 09

Intercosmos 10

(107)	Auréole 2

1974

(055)	Aeros 2

(089)	Intasat

1975

(014)	Taiyo

Intercosmos 13

(033)	Aryabhata

Intercosmos 14

1976

(019)	Ume 1

Intercosmos 15

1977

Cosmos 0900

Intercosmos 17

1978

(014)	Exos A

(099)	Intercosmos 18

1979

Intercosmos 19

1981

(070)	Dynamics Explorer 2

(093)	Dong Fang Hong 09

(094)	Auréole 3

1984

Cosmos 1543

1986

(019)	Viking

1989

(016)	Exos D

1994

(014)	Coronas 1

(027)	Sross C2

1995

(002)	Astrid 1

1998

(072)	Astrid 2

1999

(002)	Rocsat 1

(026)	Terriers


 Observation of high atmosphere

1958

(002)	Vanguard 1

1959

(001)	Vanguard 2

(009)	Explorer 07

1961

(004)	Explorer 09

1963

(009)	Explorer 17

(053)	Explorer 19

1964

(015)	Ariel 2

Cosmos 0049

(076)	Explorer 24

(084)	San Marco 1

1966

(043)	Explorer 32

1967

(038)	San Marco 2

(042)	Ariel 3

1968

(066)	Explorer 39

Cosmos 0261

Cosmos 0262

1969

(088)	Intercosmos 01

1970

(017)	Dial-Wika

Cosmos 0348

Intercosmos 04

(109)	Péole

1971

(036)	San Marco 3

(071)	Eole

(109)	Ariel 4

1972

Intercosmos 07

1973

(101)	Explorer 51

1974

(009)	San Marco 4

Intercosmos 11

Intercosmos 12

1975

(096)	Explorer 54

(107)	Explorer 55

1979

(013)	AEM 2

(017)	Solwind

1981

(100)	SME

1984

(015)	Exos C

(108)	ERBS

1988

(026)	San Marco 5

1989

Pion 1

Pion 2

Pion 3

Pion 4

1990

(028)	Pegsat

CRRES

(081)	Dong Fang Hong 31

(081)	Dong Fang Hong 32

1991

(063)	UARS

1992

Pion 5

Pion 6

1993

(023)	Spartan 201-1

1994

(006)	Bremsat

1996

(037)	TOMS


 Observation of magnetosphere

1959

(004)	Explorer 06

1961

(020)	Explorer 12

1962

(050)	Explorer 14

1963

(046)	Explorer 18

1964

(006)	Elektron 1

(006)	Elektron 2

(038)	Elektron 3

(038)	Elektron 4

Cosmos 0041

(054)	OGO 1

(060)	Explorer 21

1965

(042)	Explorer 28

(081)	OGO 2

1966

(049)	OGO 3

1967

(073)	OGO 4

1968

(014)	OGO 5

(109)	Heos 1

1969

(051)	OGO 6

(053)	Explorer 41

1971

(019)	Explorer 43

(096)	Explorer 45

1972

(005)	Heos 2

(029)	Prognoz 01

(046)	Prognoz 02

(073)	Explorer 47

1973

(009)	Prognoz 03

(078)	Explorer 50

1974

(040)	Explorer 52

1975

Intercosmos 14

(122)	Prognoz 04

1976

(112)	Prognoz 05

1977

Cosmos 0900

(029)	ESA-Geos 1

(093)	Prognoz 06

(102)	ISEE 1

(102)	ISEE 2

1978

(071)	ESA-Geos 2

(079)	ISEE 3

(087)	Exos B

(099)	Intercosmos 18

(101)	Prognoz 07

1980

(103)	Prognoz 08

1981

(070)	Dynamics Explorer 1

(070)	Dynamics Explorer 2

(094)	Auréole 3

1984

(088)	AMPTE CCE

(088)	AMPTE IRM

(088)	AMPTE UKS

1986

(019)	Viking

1989

(016)	Exos D

Aktivny

(080)	Magion 2

1991

(086)	Magion 3

1992

(038)	Sampex

(044)	Geotail

(064)	Freja

1994

(010)	Dong Fang Hong 38

(014)	Coronas 1

(046)	Apex

1995

(002)	Astrid 1

(039)	Prognoz 11

(039)	Magion 4

1996

(013)	Polar

(049)	Fast

(050)	Prognoz 12

(050)	Magion 5

1998

(072)	Astrid 2


 Observation of meteorites

1961

(022)	Explorer 13

1962

(070)	Explorer 16

1964

(074)	Explorer 23

1965

(009)	Pegasus 1

(039)	Pegasus 2

(060)	Pegasus 3

1972

(061)	Explorer 46

1984

(034)	LDEF

1994

(006)	Bremsat


 Observation of the Sun

1957

(002)	Sputnik 02

1959

(007)	Vanguard 3

1962

(006)	OSO 1

1965

(007)	OSO 2

Solrad 08

1967

(020)	OSO 3

Cosmos 166

(100)	OSO 4

1968

(17)	Solrad 09

Cosmos 215

Cosmos 230

1969

(006)	OSO 5

(068)	OSO 6

1970

Cosmos 381

1971

(030)	Tournesol

(058)	Solrad 10

(083)	OSO 7

1972

Cosmos 484

1975

(014)	Taiyo

(057)	OSO 8

(092)	Aura

1976

Intercosmos 16

1978

(079)	ISEE 3

1980

(014)	SMM

1981

(017)	Astro A

1983

(067)	Prognoz 09

1991

(062)	Solar A

1992

(038)	Sampex

1993

(023)	Spartan 201-1

1994

(014)	Coronas 1

(059)	Spartan 201-2

(071)	Wind 1

1995

(048)	Spartan 201-3

(065)	Soho

1998

(020)	Trace

(064)	Spartan 201-5


 Meteorological geostationary satellites

1966

(110)	ATS 1

1967

(111)	ATS 3

1974

(033)	SMS 1

1975

(011)	SMS 2

(100)	Goes 01

1977

(048)	Goes 02

(065)	GMS 1

(108)	Meteosat 1

1978

(062)	Goes 03

1980

(074)	Goes 04

1981

(049)	Goes 05

(057)	Meteosat 2

(076)	GMS 2

1982

(031)	Insat 1A

(041)	Goes 06

1983

(089)	Insat 1B

1984

(080)	GMS 3

1987

(022)	Goes 07

1988

Cosmos 1940

(051)	Meteosat 3

(063)	Insat 1C

1989

(020)	Meteosat 4

(070)	GMS 4

1990

(051)	Insat 1D

1991

(015)	Meteosat 5

1992

(041)	Insat 2A

1993

(048)	Insat 2B

(073)	Meteosat 6

1994

(022)	Goes 08

(069)	Electro 1

1995

(011)	GMS 5

(025)	Goes 09

1997

(019)	Goes 10

(029)	DFH 45

(049)	Meteosat 7

External resources

http://www.met.fsu.edu/explores/Guide/satguide.html

http://rsd.gsfc.nasa.gov/goes/text/geonews.html


 Meteorological LEO satellites

1959

(009)	Explorer 07

1960

(002)	Tiros 01

(016)	Tiros 02

1961

(017)	Tiros 03

1962

(002)	Tiros 04

(025)	Tiros 05

(047)	Tiros 06

1963

(024)	Tiros 07

(054)	Tiros 08

1964

(052)	Nimbus 1

1965

(004)	Tiros 09

(051)	Tiros 10

DMSP B2-1

1966

(008)	Essa 1

(016)	Essa 2

DMSP B2-2

(040)	Nimbus 2

DMSP B4-1

(057)	Cosmos 0122

(087)	Essa 3

1967

(006)	Essa 4

DMSP B4-2

(018)	Cosmos 0144

(036)	Essa 5

DMSP B4-3

DMSP B4-4

(114)	Essa 6

1968

DMSP B4-5

(069)	Essa 7

DMSP B4-6

(114)	Essa 8

1969

(016)	Essa 9

(029)	Meteor 1-01

(037)	Nimbus 3

DMSP B4-7

(084)	Meteor 1-02

1970

(008)	Itos

DMSP B5A-01

Meteor 1-03

(025)	Nimbus 4

Meteor 1-04

Meteor 1-05

DMSP B5A-02

Meteor 1-06

(106)	NOAA 01

1971

Meteor 1-07

DMSP B5A-03

Meteor 1-08

Meteor 1-09

DMSP B5A-04

Meteor 1-10

1972

DMSP B5B-05

Meteor 1-11

Meteor 1-12

(082)	NOAA 02

Meteor 1-13

DMSP B5C-06

(097)	Nimbus 5

1973

Meteor 1-14

Meteor 1-15

DMSP B5C-07

(086)	NOAA 03

1974

Meteor 1-16

DMSP B5C-08

Meteor 1-17

Meteor 1-18

DMSP B5C-09

Meteor 1-19

(089)	NOAA 04

Meteor 1-20

1975

Meteor 1-21

DMSP B5C-10

(052)	Nimbus 6

Meteor 2-01

Meteor 1-22

Meteor 1-23

1976

DMSP B5C-11

Meteor 1-24

Meteor 1-25

(077)	NOAA 05

DMSP B5D1-1 (AMS 1)

Meteor 1-26

1977

Meteor 2-02

Meteor 1-27

DMSP B5D1-2 (AMS 2)

Meteor 1-28

Meteor 2-03

1978

DMSP B5D1-3 (AMS 3)

(096)	Tiros N

(098)	Nimbus 7

1979

Meteor 1-29

Meteor 2-04

DMSP B5D1-4 (AMS 4)

(057)	NOAA 06

Meteor 2-05

1980

(043)	NOAA B

Meteor 1-30

Meteor 2-06

1981

Meteor 2-07

(059)	NOAA 07

Meteor 1-31

1982

Meteor 2-08

Meteor 2-09

DMSP B5D2-1 (AMS 5)

1983

(022)	NOAA 08

Meteor 2-10

DMSP B5D2-2

1984

Meteor 2-11

(123)	NOAA 09

1985

Meteor 2-12

Meteor 3-01

Meteor 2-13

1986

Meteor 2-14

(073)	NOAA 10

1987

Meteor 2-15

(053)	DMSP B5D2-3

Meteor 2-16

1988

Meteor 2-17

DMSP B5D2-4 (USA 29)

Meteor 3-02

(080)	Dong Fang Hong 24(Feng Yun 1-1)

(089)	NOAA 11

1989

Meteor 2-18

(086)	Meteor 3-03

1990

Meteor 2-19

(081)	Dong Fang Hong 30(Feng Yun 1-2)

Meteor 2-20

DMSP B5D2-5 (USA 68)

1991

Meteor 3-04

(032)	NOAA 12

(056)	Meteor 3-05

DMSP B5D2-6 (USA 73)

1993

Meteor 2-21

1994

(003)	Meteor 3-06

(057)	DMSP B5D2-7

(089)	NOAA 14

1995

(015)	DMSP B5D2-8

1998

(030)	NOAA 15

External resources

http://www.met.fsu.edu/explores/Guide/satguide.html

http://edcwww.cr.usgs.gov/china/china.htm


 Remote sensing satellites

Chronology

1972

(058)	Landsat 1

1975

(004)	Landsat 2

(070)	Dong Fang Hong 03

(110)	Dong Fang Hong 04

(119)	Dong Fang Hong 05

1976

(087)	Dong Fang Hong 06

(117)	Dong Fang Hong 07

1977

Meteor 1-28

1978

(011)	Dong Fang Hong 08

(026)	Landsat 3

(041)	AEM 1

(064)	Seasat

(098)	Nimbus 7

1979

Meteor 1-29

Cosmos 1076 (Ocean-E)

(051)	Bhaskara 1

Intercosmos 20

1980

Cosmos 1151 (Ocean-E)

Meteor 1-30

1981

Intercosmos 21

Meteor 1-31

(115)	Bhaskara 2

1982

(072)	Landsat 4

(090)	Dong Fang Hong 12

1983

(086)	Dong Fang Hong 13

Cosmos 1484

Cosmos 1500 (Ocean-OE)

1984

(021)	Landsat 5

(098)	Dong Fang Hong 16

Cosmos 1602 (Ocean-OE)

1985

(096)	Dong Fang Hong 17

Cosmos 1689

1986

(019)	Spot 1

Cosmos 1766 (Ocean-O1)

(076)	Dong Fang Hong 19

1987

(018)	Momo 1A

Cosmos 1869 (Ocean-O1)

(064)	Cosmos 1870

(067)	Dong Fang Hong 20

(075)	Dong Fang Hong 21

1988

(021)	IRS 1A

(056)	Ocean O1-1

Cosmos 1939

(067)	Dong Fang Hong 23

1989

(038)	Resurs F01

(047)	Resurs F02

(055)	Resurs F03

(063)	Resurs F04

(073)	Resurs F05

1990

(005)	Spot 2

(013)	Momo 1B

(018)	Ocean O1-2

(047)	Resurs F06

(060)	Resurs F07

(073)	Resurs F08

(082)	Resurs F09

(089)	Dong Fang Hong 33

1991

Almaz

(035)	Resurs F10

(039)	Ocean O1-3

(044)	Resurs F11

(050)	ERS 1

(050)	Uosat 5

(052)	Resurs F12

(058)	Resurs F13

(061)	IRS 1B

1992

(007)	JERS 1

(024)	Resurs F14

(033)	Resurs F15

(052)	Topex Poseidon

(056)	Resurs F16

(051)	Dong Fang Hong 35

(064)	Dong Fang Hong 36

1993

(009)	SCD 1

(033)	Resurs F17

(040)	Resurs F18

(053)	Resurs F19

(061)	Spot 3

(063)	Dong Fang Hong 37

1994

(037)	Dong Fang Hong 40

(066)	Ocean O1-4

(068)	IRS P2

(074)	Resurs O1-3

1995

(021)	ERS 2

(046)	Sich 1

(050)	Resurs F20

(059)	Radarsat

(072)	IRS 1C

1996

(017)	IRS P3

(037)	TOMS

(046)	Adeos 1

(059)	Dong Fang Hong 43

1997

(037)	Orbview 2

(044)	Lewis

(057)	IRS 1D

(072)	Resurs F21

(074)	TRMM

(085)	Early Bird

1998

(017)	Spot 4

(060)	SCD 2

1999

(020)	Landsat 7

(034)	Quickscat

(039)	Ocean O2-1

SAR performances

Satellite	Launch date	Resolution
United States
Seasat	1978	25 m
CIS
Cosmos 1870	1987	15 to 30 m
Almaz 1A	1991	10 to 15 m
Europe
ERS 1	1991	26 m
ERS 2	1995	26 m
Envisat	?	30 m
Japan
JERS 1	1992	25-30 m
Canada
Radarsat	1995	9 m
External resources

http://quercus.art.man.ac.uk/rs/

http://www.ccrs.nrcan.gc.ca/ccrs/satsens/satsense.html


Telecommunications LEO satellites
 LEO Telecommunication satellites

1958

(006)	Score

1960

(009)	Echo 1

(013)	Courier 1B

1961

(???)	Oscar 01

1962

(022)	Oscar 02

(029)	Telstar 1

(068)	Relay 1

1963

(013)	Telstar 2

1964

(003)	Relay 2

(004)	Echo 2

1965

(016)	Oscar 03

(030)	Molniya 1-01

Molniya 1-02

(108)	Oscar 04

1966

Cosmos 103

Molniya 1-03

IDSCP 1-1

IDSCP 1-2

IDSCP 1-3

IDSCP 1-4

IDSCP 1-5

IDSCP 1-6

IDSCP 1-7

Molniya 1-04

1967

IDSCP 2-1

IDSCP 2-2

IDSCP 2-3

IDSCP 2-4

IDSCP 2-5

IDSCP 2-6

IDSCP 2-7

IDSCP 2-8

Cosmos 151

Molniya 1-05

IDSCP 3-1

IDSCP 3-2

IDSCP 3-3

IDSCP 3-4

Molniya 1-06

Molniya 1-07

1968

Molniya 1-08

IDSCP 4-1

IDSCP 4-2

IDSCP 4-3

IDSCP 4-4

IDSCP 4-5

IDSCP 4-6

IDSCP 4-7

IDSCP 4-8

Molniya 1-09

Cosmos 236

Molniya 1-10

1969

Molniya 1-11

Molniya 1-12

Cosmos 292 (exp. Strela-1)

Cosmos 304 (exp. Strela-1)

1970

(008)	Oscar 05

Molniya 1-13

Cosmos 332 (exp. Strela-1)

Cosmos 336 (Strela-2)

Cosmos 337 (Strela-2)

Cosmos 338 (Strela-2)

Cosmos 339 (Strela-2)

Cosmos 340 (Strela-2)

Cosmos 341 (Strela-2)

Cosmos 342 (Strela-2)

Cosmos 343 (Strela-2)

Molniya 1-14

Molniya 1-15

Cosmos 371 (exp. Strela-1)

(086)	Cosmos 372 (Strela-1)

Molniya 1-16

Molniya 1-17

1971

SDS A

Cosmos 407 (Strela-1)

Cosmos 411 (Strela-2)

Cosmos 412 (Strela-2)

Cosmos 413 (Strela-2)

Cosmos 414 (Strela-2)

Cosmos 415 (Strela-2)

Cosmos 416 (Strela-2)

Cosmos 417 (Strela-2)

Cosmos 418 (Strela-2)

Molniya 1-18

(086)	Cosmos 0444 (Strela-2)

(086)	Cosmos 0445 (Strela-2)

(086)	Cosmos 0446 (Strela-2)

(086)	Cosmos 0447 (Strela-2)

(086)	Cosmos 0448 (Strela-2)

(086)	Cosmos 0449 (Strela-2)

(086)	Cosmos 0450 (Strela-2)

(086)	Cosmos 0451 (Strela-2)

(100)	Molniya 2-01

Cosmos 468 (Strela-1)

Molniya 1-19

1972

Molniya 1-20

Molniya 2-02

(043)	Cosmos 494 (Strela-1)

(057)	Cosmos 0504 (Strela-2)

(057)	Cosmos 0505 (Strela-2)

(057)	Cosmos 0506 (Strela-2)

(057)	Cosmos 0507 (Strela-2)

(057)	Cosmos 0508 (Strela-2)

(057)	Cosmos 0509 (Strela-2)

(057)	Cosmos 0510 (Strela-2)

(057)	Cosmos 0511 (Strela-2)

Molniya 2-03

Molniya 1-21

(082)	Oscar 06

Cosmos 528 (Strela-2)

Cosmos 529 (Strela-2)

Cosmos 530 (Strela-2)

Cosmos 531 (Strela-2)

Cosmos 532 (Strela-2)

Cosmos 533 (Strela-2)

Cosmos 534 (Strela-2)

Cosmos 535 (Strela-2)

Molniya 1-22

Molniya 2-04

Cosmos 540 (Strela-1)

1973

Molniya 1-23

Molniya 2-05

Cosmos 564 (Strela-2)

Cosmos 565 (Strela-2)

Cosmos 566 (Strela-2)

Cosmos 567 (Strela-2)

Cosmos 568 (Strela-2)

Cosmos 569 (Strela-2)

Cosmos 570 (Strela-2)

Cosmos 571 (Strela-2)

Molniya 2-06

SDS B

Molniya 1-24

(069)	Cosmos 0588 (Strela-2)

(069)	Cosmos 0589 (Strela-2)

(069)	Cosmos 0590 (Strela-2)

(069)	Cosmos 0591 (Strela-2)

(069)	Cosmos 0592 (Strela-2)

(069)	Cosmos 0593 (Strela-2)

(069)	Cosmos 0594 (Strela-2)

(069)	Cosmos 0595 (Strela-2)

Molniya 2-07

Molniya 1-25

Molniya 1-26

Cosmos 614 (Strela-1)

Cosmos 617 (Strela-2)

Cosmos 618 (Strela-2)

Cosmos 619 (Strela-2)

Cosmos 620 (Strela-2)

Cosmos 621 (Strela-2)

Cosmos 622 (Strela-2)

Cosmos 623 (Strela-2)

Cosmos 624 (Strela-2)

Molniya 2-08

1974

Molniya 1-27

(024)	Cosmos 0641 (Strela-2)

(024)	Cosmos 0642 (Strela-2)

(024)	Cosmos 0643 (Strela-2)

(024)	Cosmos 0644 (Strela-2)

(024)	Cosmos 0645 (Strela-2)

(024)	Cosmos 0646 (Strela-2)

(024)	Cosmos 0647 (Strela-2)

(024)	Cosmos 0648 (Strela-2)

Molniya 2-09

Cosmos 676 (Strela-1)

Molniya 2-10

(072)	Cosmos 0677 (Strela-2)

(072)	Cosmos 0678 (Strela-2)

(072)	Cosmos 0679 (Strela-2)

(072)	Cosmos 0680 (Strela-2)

(072)	Cosmos 0681 (Strela-2)

(072)	Cosmos 0682 (Strela-2)

(072)	Cosmos 0683 (Strela-2)

(072)	Cosmos 0684 (Strela-2)

Molniya 1-28

(089)	Oscar 07

Molniya 3-01

Molniya 2-11

1975

Molniya 2-12

(016)	Cosmos 0711 (Strela-2)

(016)	Cosmos 0712 (Strela-2)

(016)	Cosmos 0713 (Strela-2)

(016)	Cosmos 0714 (Strela-2)

(016)	Cosmos 0715 (Strela-2)

(016)	Cosmos 0716 (Strela-2)

(016)	Cosmos 0717 (Strela-2)

(016)	Cosmos 0718 (Strela-2)

SDS 1

Molniya 3-02

Molniya 1-29

(045)	Cosmos 0732 (Strela-2)

(045)	Cosmos 0733 (Strela-2)

(045)	Cosmos 0734 (Strela-2)

(045)	Cosmos 0735 (Strela-2)

(045)	Cosmos 0736 (Strela-2)

(045)	Cosmos 0737 (Strela-2)

(045)	Cosmos 0738 (Strela-2)

(045)	Cosmos 0739 (Strela-2)

Molniya 1-30

Molniya 2-13

Molniya 1-31

Molniya 2-14

Cosmos 761 (Strela-2)

Cosmos 762 (Strela-2)

Cosmos 763 (Strela-2)

Cosmos 764 (Strela-2)

Cosmos 765 (Strela-2)

Cosmos 766 (Strela-2)

Cosmos 767 (Strela-2)

Cosmos 768 (Strela-2)

Cosmos 773 (Strela-1)

Molniya 3-03

Cosmos 783 (Strela-1)

Molniya 2-15

Molniya 3-04

1976

Molniya 1-32

Cosmos 791 (Strela-2)

Cosmos 792 (Strela-2)

Cosmos 793 (Strela-2)

Cosmos 794 (Strela-2)

Cosmos 795 (Strela-2)

Cosmos 796 (Strela-2)

Cosmos 797 (Strela-2)

Cosmos 798 (Strela-2)

Molniya 1-33

Molniya 1-34

Molniya 3-05

SDS 2

Cosmos 825 (Strela-2)

Cosmos 826 (Strela-2)

Cosmos 827 (Strela-2)

Cosmos 828 (Strela-2)

Cosmos 829 (Strela-2)

Cosmos 830 (Strela-2)

Cosmos 831 (Strela-2)

Cosmos 832 (Strela-2)

Cosmos 836 (Strela-1)

Cosmos 841 (Strela-1)

Molniya 1-35

SDS 3

Cosmos 858 (Strela-1)

Molniya 2-16

Cosmos 871 (Strela-2)

Cosmos 872 (Strela-2)

Cosmos 873 (Strela-2)

Cosmos 874 (Strela-2)

Cosmos 875 (Strela-2)

Cosmos 876 (Strela-2)

Cosmos 877 (Strela-2)

Cosmos 878 (Strela-2)

Molniya 3-06

1977

Molniya 2-17

Molniya 1-36

Molniya 3-07

Molniya 1-37

Cosmos 923 (Strela-1)

Cosmos 939 (Strela-2)

Cosmos 940 (Strela-2)

Cosmos 941 (Strela-2)

Cosmos 942 (Strela-2)

Cosmos 943 (Strela-2)

Cosmos 944 (Strela-2)

Cosmos 945 (Strela-2)

Cosmos 946 (Strela-2)

Molniya 1-38

Molniya 3-08

Cosmos 968 (Strela-1)

1978

Cosmos 976 (Strela-2)

Cosmos 977 (Strela-2)

Cosmos 978 (Strela-2)

Cosmos 979 (Strela-2)

Cosmos 980 (Strela-2)

Cosmos 981 (Strela-2)

Cosmos 982 (Strela-2)

Cosmos 983 (Strela-2)

Molniya 3-09

Cosmos 990 (Strela-1)

SDS 4

Molniya 1-39

(026)	Oscar 08

Molniya 1-40

Cosmos 1013 (Strela-2)

Cosmos 1014 (Strela-2)

Cosmos 1015 (Strela-2)

Cosmos 1016 (Strela-2)

Cosmos 1017 (Strela-2)

Cosmos 1018 (Strela-2)

Cosmos 1019 (Strela-2)

Cosmos 1020 (Strela-2)

Cosmos 1023 (Strela-1)

Molniya 1-41

SDS 5

Molniya 1-42

Cosmos 1034 (Strela-2)

Cosmos 1035 (Strela-2)

Cosmos 1036 (Strela-2)

Cosmos 1037 (Strela-2)

Cosmos 1038 (Strela-2)

Cosmos 1039 (Strela-2)

Cosmos 1040 (Strela-2)

Cosmos 1041 (Strela-2)

Molniya 3-10

Cosmos 1048 (Strela-1)

Cosmos 1051 (Strela-2)

Cosmos 1052 (Strela-2)

Cosmos 1053 (Strela-2)

Cosmos 1054 (Strela-2)

Cosmos 1055 (Strela-2)

Cosmos 1056 (Strela-2)

Cosmos 1057 (Strela-2)

Cosmos 1058 (Strela-2)

1979

Molniya 3-11

Cosmos 1081 (Strela-2)

Cosmos 1082 (Strela-2)

Cosmos 1083 (Strela-2)

Cosmos 1084 (Strela-2)

Cosmos 1085 (Strela-2)

Cosmos 1086 (Strela-2)

Cosmos 1087 (Strela-2)

Cosmos 1088 (Strela-2)

Molniya 1-43

Molniya 3-12

Cosmos 1110 (Strela-1)

Molniya 1-44

Cosmos 1125 (Strela-1)

Cosmos 1130 (Strela-2)

Cosmos 1131 (Strela-2)

Cosmos 1132 (Strela-2)

Cosmos 1133 (Strela-2)

Cosmos 1134 (Strela-2)

Cosmos 1135 (Strela-2)

Cosmos 1136 (Strela-2)

Cosmos 1137 (Strela-2)

(089)	Cosmos 1140 (Strela-1)

Molniya 1-45

1980

Molniya 1-46

Cosmos 1156 (Strela-2)

Cosmos 1157 (Strela-2)

Cosmos 1158 (Strela-2)

Cosmos 1159 (Strela-2)

Cosmos 1160 (Strela-2)

Cosmos 1161 (Strela-2)

Cosmos 1162 (Strela-2)

Cosmos 1163 (Strela-2)

Cosmos 1175

Molniya 1-47

(056)	Cosmos 1190 (Strela-1)

Cosmos 1192 (Strela-2)

Cosmos 1193 (Strela-2)

Cosmos 1194 (Strela-2)

Cosmos 1195 (Strela-2)

Cosmos 1196 (Strela-2)

Cosmos 1197 (Strela-2)

Cosmos 1198 (Strela-2)

Cosmos 1199 (Strela-2)

Molniya 3-13

Molniya 1-48

SDS 6

Cosmos 1228 (Strela-2)

Cosmos 1229 (Strela-2)

Cosmos 1230 (Strela-2)

Cosmos 1231 (Strela-2)

Cosmos 1232 (Strela-2)

Cosmos 1233 (Strela-2)

Cosmos 1234 (Strela-2)

Cosmos 1235 (Strela-2)

1981

Molniya 3-14

Molniya 1-49

Cosmos 1250 (Strela-2)

Cosmos 1251 (Strela-2)

Cosmos 1252 (Strela-2)

Cosmos 1253 (Strela-2)

Cosmos 1254 (Strela-2)

Cosmos 1255 (Strela-2)

Cosmos 1256 (Strela-2)

Cosmos 1257 (Strela-2)

Molniya 3-15

SDS 7

Cosmos 1269 (Strela-1)

Molniya 3-16

Molniya 1-50

Cosmos 1287 (Strela-2)

Cosmos 1288 (Strela-2)

Cosmos 1289 (Strela-2)

Cosmos 1290 (Strela-2)

Cosmos 1291 (Strela-2)

Cosmos 1292 (Strela-2)

Cosmos 1293 (Strela-2)

Cosmos 1294 (Strela-2)

Cosmos 1302 (Strela-1)

Cosmos 1305

(100)	Uosat 1

Molniya 3-17

Cosmos 1320 (Strela-2)

Cosmos 1321 (Strela-2)

Cosmos 1322 (Strela-2)

Cosmos 1323 (Strela-2)

Cosmos 1324 (Strela-2)

Cosmos 1325 (Strela-2)

Cosmos 1326 (Strela-2)

Cosmos 1327 (Strela-2)

Molniya 1-51

Molniya 1-52

Cosmos 1331 (Strela-1)

1982

Molniya 1-53

Molniya 3-18

(037)	Cosmos 1354 (Strela-1)

Cosmos 1357 (Strela-2)

Cosmos 1358 (Strela-2)

Cosmos 1359 (Strela-2)

Cosmos 1360 (Strela-2)

Cosmos 1361 (Strela-2)

Cosmos 1362 (Strela-2)

Cosmos 1363 (Strela-2)

Cosmos 1364 (Strela-2)

Molniya 1-54

Cosmos 1371 (Strela-1)

Molniya 1-55

Cosmos 1388 (Strela-2)

Cosmos 1389 (Strela-2)

Cosmos 1390 (Strela-2)

Cosmos 1391 (Strela-2)

Cosmos 1392 (Strela-2)

Cosmos 1393 (Strela-2)

Cosmos 1394 (Strela-2)

Cosmos 1395 (Strela-2)

Molniya 1-55

Molniya 3-19

Cosmos 1420 (Strela-1)

1983

Cosmos 1429 (Strela-2)

Cosmos 1430 (Strela-2)

Cosmos 1431 (Strela-2)

Cosmos 1432 (Strela-2)

Cosmos 1433 (Strela-2)

Cosmos 1434 (Strela-2)

Cosmos 1435 (Strela-2)

Cosmos 1436 (Strela-2)

Molniya 3-20

Molniya 1-56

Molniya 1-57

Cosmos 1452 (Strela-1)

(058)	Oscar 10

Cosmos 1473 (Strela-2)

Cosmos 1474 (Strela-2)

Cosmos 1475 (Strela-2)

Cosmos 1476 (Strela-2)

Cosmos 1477 (Strela-2)

Cosmos 1478 (Strela-2)

Cosmos 1479 (Strela-2)

Cosmos 1480 (Strela-2)

Molniya 1-58

SDS 8

(079)	Cosmos1486 (Strela-1)

Molniya 3-21

Cosmos 1503 (Strela-1)

Molniya 1-59

Molniya 3-22

1984

Cosmos 1522 (Strela-2)

Cosmos 1523 (Strela-2)

Cosmos 1524 (Strela-2)

Cosmos 1525 (Strela-2)

Cosmos 1526 (Strela-2)

Cosmos 1527 (Strela-2)

Cosmos 1528 (Strela-2)

Cosmos 1529 (Strela-2)

Cosmos 1538 (Strela-1)

(021)	Uosat 2

Molniya 1-60

Cosmos 1559 (Strela-2)

Cosmos 1560 (Strela-2)

Cosmos 1561 (Strela-2)

Cosmos 1562 (Strela-2)

Cosmos 1563 (Strela-2)

Cosmos 1564 (Strela-2)

Cosmos 1565 (Strela-2)

Cosmos 1566 (Strela-2)

Cosmos 1570 (Strela-1)

Molniya 1-61

Molniya 1-62

SDS 9

Molniya 1-63

1985

Cosmos 1617 (Strela-3)

Cosmos 1618 (Strela-3)

Cosmos 1619 (Strela-3)

Cosmos 1620 (Strela-3)

Cosmos 1621 (Strela-3)

Cosmos 1622 (Strela-3)

Molniya 3-23

(006)	Cosmos 1624 (Strela-1)

SDS 10

Cosmos 1635 (Strela-2)

Cosmos 1636 (Strela-2)

Cosmos 1637 (Strela-2)

Cosmos 1638 (Strela-2)

Cosmos 1639 (Strela-2)

Cosmos 1640 (Strela-2)

Cosmos 1641 (Strela-2)

Cosmos 1642 (Strela-2)

Molniya 3-24

Molniya 3-25

Molniya 1-64

Cosmos 1680 (Strela-1)

Molniya 3-26

Cosmos 1690 (Strela-3)

Cosmos 1691 (Strela-3)

Cosmos 1692 (Strela-3)

Cosmos 1693 (Strela-3)

Cosmos 1694 (Strela-3)

Cosmos 1695 (Strela-3)

Molniya 1-65

Molniya 1-66

Molniya 3-27

1986

Cosmos 1716 (Strela-2)

Cosmos 1717 (Strela-2)

Cosmos 1718 (Strela-2)

Cosmos 1719 (Strela-2)

Cosmos 1720 (Strela-2)

Cosmos 1721 (Strela-2)

Cosmos 1722 (Strela-2)

Cosmos 1723 (Strela-2)

(030)	Cosmos 1741 (Strela-1)

Molniya 3-28

Molniya 3-29

Cosmos 1763 (Strela-1)

Molniya 1-67

Cosmos 1770 (Strela-1)

(061)	Fuji 1A

Molniya 1-68

Molniya 3-30

Molniya 1-69

Cosmos 1794 (Strela-2)

Cosmos 1795 (Strela-2)

Cosmos 1796 (Strela-2)

Cosmos 1797 (Strela-2)

Cosmos 1798 (Strela-2)

Cosmos 1799 (Strela-2)

Cosmos 1800 (Strela-2)

Cosmos 1801 (Strela-2)

Molniya 1-70

1987

Cosmos 1814 (Strela-1)

Molniya 3-31

SDS 11

Cosmos 1827 (Strela-3)

Cosmos 1828 (Strela-3)

Cosmos 1829 (Strela-3)

Cosmos 1830 (Strela-3)

Cosmos 1831 (Strela-3)

Cosmos 1832 (Strela-3)

(049)	Cosmos 1850 (Strela-1)

(051)	Cosmos 1852 (Strela-2)

(051)	Cosmos 1853 (Strela-2)

(051)	Cosmos 1854 (Strela-2)

(051)	Cosmos 1855 (Strela-2)

(051)	Cosmos 1856 (Strela-2)

(051)	Cosmos 1857 (Strela-2)

(051)	Cosmos 1858 (Strela-2)

(051)	Cosmos 1859 (Strela-2)

Cosmos 1875 (Strela-3)

Cosmos 1876 (Strela-3)

Cosmos 1877 (Strela-3)

Cosmos 1878 (Strela-3)

Cosmos 1879 (Strela-3)

Cosmos 1880 (Strela-3)

Cosmos 1898 (Strela-1)

1988

Cosmos 1909 (Strela-3)

Cosmos 1910 (Strela-3)

Cosmos 1911 (Strela-3)

Cosmos 1911 (Strela-3)

Cosmos 1912 (Strela-3)

Cosmos 1913 (Strela-3)

Cosmos 1914 (Strela-3)

(016)	Cosmos 1924 (Strela-2)

(016)	Cosmos 1925 (Strela-2)

(016)	Cosmos 1926 (Strela-2)

(016)	Cosmos 1927 (Strela-2)

(016)	Cosmos 1928 (Strela-2)

(016)	Cosmos 1929 (Strela-2)

(016)	Cosmos 1930 (Strela-2)

(016)	Cosmos 1931 (Strela-2)

(017)	Molniya 1-71

(022)	Molniya 1-72

Cosmos 1937 (Strela-1)

Molniya 3-32

(051)	Oscar 13

Cosmos 1954 (Strela-1)

Molniya 1-73

Molniya 3-33

SDS 12

(112)	Molniya 3-34

(115)	Molniya 1-74

1989

(005)	Cosmos 1992 (Strela-1)

(009)	Cosmos 1994 (Strela-3)

(009)	Cosmos 1995 (Strela-3)

(009)	Cosmos 1996 (Strela-3)

(009)	Cosmos 1997 (Strela-3)

(009)	Cosmos 1998 (Strela-3)

(009)	Cosmos 1999 (Strela-3)

Molniya 1-75

(025)	Cosmos 2008 (Strela-2)

(025)	Cosmos 2009 (Strela-2)

(025)	Cosmos 2010 (Strela-2)

(025)	Cosmos 2011 (Strela-2)

(025)	Cosmos 2012 (Strela-2)

(025)	Cosmos 2013 (Strela-2)

(025)	Cosmos 2014 (Strela-2)

(025)	Cosmos 2015 (Strela-2)

(043)	Molniya 3-35

(074)	Cosmos 2038 (Strela-3)

(074)	Cosmos 2039 (Strela-3)

(074)	Cosmos 2040 (Strela-3)

(074)	Cosmos 2041 (Strela-3)

(074)	Cosmos 2042 (Strela-3)

(074)	Cosmos 2043 (Strela-3)

Molniya 1-76

(094)	Molniya 3-36

1990

(004)	Cosmos 2056 (Strela-1)

(005)	Uosat 3

(005)	Uosat 4

(005)	Pacsat

(005)	Dove

(005)	Webersat

(005)	Lusat

(006)	Molniya 3-37

(013)	Fuji 1B

(029)	Cosmos 2064 (Strela-2)

(029)	Cosmos 2065 (Strela-2)

(029)	Cosmos 2066 (Strela-2)

(029)	Cosmos 2067 (Strela-2)

(029)	Cosmos 2068 (Strela-2)

(029)	Cosmos 2069 (Strela-2)

(029)	Cosmos 2070 (Strela-2)

(029)	Cosmos 2071 (Strela-2)

Molniya 1-77

Molniya 3-38

Cosmos 2090 (Strela-3)

Cosmos 2091 (Strela-3)

Cosmos 2092 (Strela-3)

Cosmos 2093 (Strela-3)

Cosmos 2094 (Strela-3)

Cosmos 2095 (Strela-3)

Molniya 1-78

Molniya 3-39

Molniya 1-79

(111)	Cosmos 2112 (Strela-1)

Cosmos 2114 (Strela-3)

Cosmos 2115 (Strela-3)

Cosmos 2116 (Strela-3)

Cosmos 2117 (Strela-3)

Cosmos 2118 (Strela-3)

Cosmos 2119 (Strela-3)

1991

(006)	Informator

Cosmos 2125 (Strela-2)

Cosmos 2126 (Strela-2)

Cosmos 2127 (Strela-2)

Cosmos 2128 (Strela-2)

Cosmos 2129 (Strela-2)

Cosmos 2130 (Strela-2)

Cosmos 2131 (Strela-2)

Cosmos 2132 (Strela-2)

Molniya 1-80

Molniya 3-40

Cosmos 2143 (Strela-3)

Cosmos 2144 (Strela-3)

Cosmos 2145 (Strela-3)

Cosmos 2146 (Strela-3)

Cosmos 2147 (Strela-3)

Cosmos 2148 (Strela-3)

Cosmos 2150 (Strela-1)

Molniya 1-81

(050)	Uosat 5

(050)	Orbcomm X

Molniya 1-82

Molniya 3-41

Cosmos 2157 (Strela-3)

Cosmos 2158 (Strela-3)

Cosmos 2159 (Strela-3)

Cosmos 2160 (Strela-3)

Cosmos 2161 (Strela-3)

Cosmos 2162 (Strela-3)

Cosmos 2165 (Strela-3)

Cosmos 2166 (Strela-3)

Cosmos 2167 (Strela-3)

Cosmos 2168 (Strela-3)

Cosmos 2169 (Strela-3)

Cosmos 2170 (Strela-3)

1992

Molniya 1-83

Cosmos 2187 (Strela-2)

Cosmos 2188 (Strela-2)

Cosmos 2189 (Strela-2)

Cosmos 2190 (Strela-2)

Cosmos 2191 (Strela-2)

Cosmos 2192 (Strela-2)

Cosmos 2193 (Strela-2)

Cosmos 2194 (Strela-2)

Cosmos 2197 (Strela-3)

Cosmos 2198 (Strela-3)

Cosmos 2199 (Gonets-D)

Cosmos 2200 (Strela-3)

Cosmos 2201 (Gonets-D)

Cosmos 2202 (Strela-3)

Molniya 1-84

(052)	Kitsat A

Cosmos 2208 (Strela-1)

(067)	Molniya 3-42

Cosmos 2211 (Strela-3)

Cosmos 2212 (Strela-3)

Cosmos 2213 (Strela-3)

Cosmos 2214 (Strela-3)

Cosmos 2215 (Strela-3)

Cosmos 2216 (Strela-3)

Molniya 3-43

1993

(002)	Molniya 1-85

(009)	Orbcom XP 1

(025)	Molniya 3-44

(030)	Cosmos 2245 (Strela-3)

(030)	Cosmos 2246 (Strela-3)

(030)	Cosmos 2247 (Strela-3)

(030)	Cosmos 2248 (Strela-3)

(030)	Cosmos 2249 (Strela-3)

(030)	Cosmos 2250 (Strela-3)

(035)	Molniya 1-86

(036)	Cosmos 2251 (Strela-1)

(038)	Cosmos 2252 (Strela-3)

(038)	Cosmos 2253 (Strela-3)

(038)	Cosmos 2254 (Strela-3)

(038)	Cosmos 2255 (Strela-3)

(038)	Cosmos 2256 (Strela-3)

(038)	Cosmos 2257 (Strela-3)

(055)	Temisat

(049)	Molniya 3-45

(061)	Eyesat

(061)	Itamsat

(061)	Healthsat

(061)	Kitsat B

(061)	Posat

(079)	Molniya 1-87

1994

(011)	Cosmos 2268 (Strela-3)

(011)	Cosmos 2269 (Strela-3)

(011)	Cosmos 2270 (Strela-3)

(011)	Cosmos 2271 (Strela-3)

(011)	Cosmos 2272 (Strela-3)

(011)	Cosmos 2273 (Strela-3)

(051)	Molniya 3-46

(081)	Molniya 1-88

(085)	RS 15

(083)	Cosmos 2298 (Strela-1)

(086)	Cosmos 2299 (Strela-3)

(086)	Cosmos 2300 (Strela-3)

(086)	Cosmos 2301 (Strela-3)

(086)	Cosmos 2302 (Strela-3)

(086)	Cosmos 2303 (Strela-3)

(086)	Cosmos 2304 (Strela-3)

1995

(002)	Faisat 1

(017)	Orbcomm FM 1

(017)	Orbcomm FM 2

(042)	Molniya 3-47

1996

(009)	Gonets-D1-1

(009)	Gonets-D1-2

(009)	Gonets-D1-3

(009)	Cosmos 2328 (Strela-3)

(009)	Cosmos 2329 (Strela-3)

(009)	Cosmos 2330 (Strela-3)

(045)	Molniya 1-89

(046)	Fuji 2

(052)	Unamsat 2

(060)	Molniya 3-48

1997

(006)	Cosmos 2337 (Strela-3)

(006)	Cosmos 2338 (Strela-3)

(006)	Cosmos 2339 (Strela-3)

(020)	Iridium 04

(020)	Iridium 05

(020)	Iridium 06

(020)	Iridium 07

(020)	Iridium 08

(030)	Iridium 09

(030)	Iridium 10

(030)	Iridium 11

(030)	Iridium 12

(030)	Iridium 13

(030)	Iridium 14

(030)	Iridium 16

(034)	Iridium 15

(034)	Iridium 17

(034)	Iridium 18

(034)	Iridium 20

(034)	Iridium 21

(043)	Iridium 22

(043)	Iridium 23

(043)	Iridium 24

(043)	Iridium 25

(043)	Iridium 26

(051)	Iridium 27

(051)	Iridium 28

(051)	Iridium 29

(051)	Iridium 30

(051)	Iridium 31

(051)	Iridium 32

(052)	Faisat 2V

(054)	Molniya 1-90

(056)	Iridium 19

(056)	Iridium 34

(056)	Iridium 35

(056)	Iridium 36

(056)	Iridium 37

(069)	Iridium 43

(069)	Iridium 41

(069)	Iridium 40

(069)	Iridium 39

(069)	Iridium 38

(077)	Iridium 42

(077)	Iridium 44

(082)	Iridium 45

(082)	Iridium 46

(082)	Iridium 47

(082)	Iridium 48

(082)	Iridium 49

(085)	Orbcomm FM 5

(085)	Orbcomm FM 6

(085)	Orbcomm FM 7

(085)	Orbcomm FM 8

(085)	Orbcomm FM 9

(085)	Orbcomm FM 10

(085)	Orbcomm FM 11

(085)	Orbcomm FM 12

1998

(007)	Orbcomm FM 3

(007)	Orbcomm FM 4

(008)	Globalstar 1

(008)	Globalstar 2

(008)	Globalstar 3

(008)	Globalstar 4

(010)	Iridium 50

(010)	Iridium 52

(010)	Iridium 53

(010)	Iridium 54

(010)	Iridium 56

(012)	Teledesic 1

(018)	Iridium 51

(018)	Iridium 61

(019)	Iridium 55

(019)	Iridium 57

(019)	Iridium 58

(019)	Iridium 59

(019)	Iridium 60

(021)	Iridium 62

(021)	Iridium 63

(021)	Iridium 64

(021)	Iridium 65

(021)	Iridium 66

(021)	Iridium 67

(021)	Iridium 68

(023)	Globalstar 6

(023)	Globalstar 8

(023)	Globalstar 14

(023)	Globalstar 15

(026)	Iridium 69

(026)	Iridium 71

(032)	Iridium 70

(032)	Iridium 72

(032)	Iridium 73

(032)	Iridium 74

(032)	Iridium 75

(036)	Cosmos 2352 (Strela-3)

(036)	Cosmos 2353 (Strela-3)

(036)	Cosmos 2354 (Strela-3)

(036)	Cosmos 2355 (Strela-3)

(036)	Cosmos 2356 (Strela-3)

(036)	Cosmos 2357 (Strela-3)

(040)	Molniya 3-49

(042)	Tubsat N

(042)	Tubsat N1

(046)	Orbcomm FM 13

(046)	Orbcomm FM 14

(046)	Orbcomm FM 15

(046)	Orbcomm FM 16

(046)	Orbcomm FM 17

(046)	Orbcomm FM 18

(046)	Orbcomm FM 19

(046)	Orbcomm FM 20

(048)	Iridium 76

(048)	Iridium 78

(051)	Iridium 77

(051)	Iridium 79

(051)	Iridium 80

(051)	Iridium 81

(051)	Iridium 82

(053)	Orbcomm FM 21

(053)	Orbcomm FM 22

(053)	Orbcomm FM 23

(053)	Orbcomm FM 24

(053)	Orbcomm FM 25

(053)	Orbcomm FM 26

(053)	Orbcomm FM 27

(053)	Orbcomm FM 28

(054)	Molniya 1-91

(061)	Sedsat

(064)	Pansat

(066)	Iridium 83

(066)	Iridium 84

(066)	Iridium 85

(066)	Iridium 86

(066)	Iridium 87

(074)	Iridium 88

(074)	Iridium 89

1999

(004)	Globalstar 36

(004)	Globalstar 23

(004)	Globalstar 38

(004)	Globalstar 40

(008)	Sunsat

(012)	Globalstar 22

(012)	Globalstar 41

(012)	Globalstar 46

(012)	Globalstar 37

(019)	Globalstar 45

(019)	Globalstar 42

(019)	Globalstar 44

(019)	Globalstar 19

(022)	Uosat 12

(031)	Globalstar 52

(031)	Globalstar 49

(031)	Globalstar 25

(031)	Globalstar 47

(032)	Iridium 14A

(032)	Iridium 21A

(036)	Molniya 3-50

(037)	Globalstar 32

(037)	Globalstar 30

(037)	Globalstar 35

(037)	Globalstar 51

(041)	Globalstar 26

(041)	Globalstar 28

(041)	Globalstar 43

(041)	Globalstar 48

(043)	Globalstar 24

(043)	Globalstar 27

(043)	Globalstar 53

(043)	Globalstar 54


Telecommunications geostationary satellites
 Geostationary telecommunication satellites

See also the Clarke Belt list

1964

(047)	Syncom 3

1965

(028)	Intelsat 101

1966

(110)	ATS 1

1967

(001)	Intelsat 202

(026)	Intelsat 203

(094)	Intelsat 204

(111)	ATS 3

1968

(081)	LES 6

(116)	Intelsat 302

1969

(011)	Intelsat 303

(045)	Intelsat 304

(069)	ATS 5

(101)	Skynet 1A

1970

(003)	Intelsat 306

(021)	Nato 1

(032)	Intelsat 307

(055)	Intelsat 308

1971

(006)	Intelsat 402

(009)	Nato 2

(095)	DSCS 2-01

(095)	DSCS 2-02

(116)	Intelsat 403

1972

(003)	Intelsat 404

(041)	Intelsat 405

(090)	Anik A1

1973

(023)	Anik A2

(058)	Intelsat 407

(100)	DSCS 2-03

(100)	DSCS 2-04

1974

(014)	Cosmos 0637

(022)	Westar 1

(039)	ATS 6

(060)	Molniya 1S

(075)	Westar 2

(093)	Intelsat 408

(094)	Skynet 2B

(101)	Symphonie 1

1975

(038)	Anik A3

(042)	Intelsat 401

(077)	Symphonie 2

(091)	Intelsat 4A01

(117)	Satcom 1

(123)	Raduga 01

1976

(004)	CTS

(010)	Intelsat 4A02

(017)	Marisat 1

(023)	LES 8

(023)	LES 9

(029)	Satcom 2

(035)	Nato 3A

(042)	Comstar 1

(053)	Marisat 2

(066)	Palapa A1

(073)	Comstar 2

(092)	Raduga 02

(101)	Marisat 3

(107)	Ekran 01

1977

(014)	ETS 2

(018)	Palapa A2

(034)	DSCS 2-07

(034)	DSCS 2-08

(041)	Intelsat 4A04

(071)	Raduga 03

(092)	Ekran 02

(118)	Sakura 1

1978

(002)	Intelsat 4A03

(016)	Fleetsatcom 1

(035)	Intelsat 4A06

(039)	Yuri 1

(044)	OTS 2

(068)	Comstar 3

(073)	Raduga 04

(106)	Nato 3C

(113)	DSCS 2-11

(113)	DSCS 2-12

(116)	Anik B1

(118)	Gorizont 01

1979

(015)	Ekran 03

(035)	Raduga 05

(038)	Fleetsatcom 2

(062)	Gorizont 02

(072)	Westar 3

(087)	Ekran 04

(098)	DSCS 2-13

(098)	DSCS 2-14

(105)	Gorizont 03

1980

(004)	Fleetsatcom 3

(016)	Raduga 06

(049)	Gorizont 04

(060)	Ekran 05

(081)	Raduga 07

(087)	Fleetsatcom 4

(091)	SBS 1

(098)	Intelsat 502

(104)	Ekran 06

1981

(018)	Comstar 4

(027)	Raduga 08

(050)	Intelsat 501

(057)	Apple

(061)	Ekran 07

(069)	Raduga 09

(073)	Fleetsatcom 5

(096)	SBS 2

(102)	Raduga 10

(114)	Satcom 3R

(119)	Intelsat 503

(122)	Marecs A

1982

(004)	Satcom 4

(009)	Ekran 08

(014)	Westar 4

(017)	Intelsat 504

(020)	Gorizont 05

(031)	Insat 1A

(044)	Cosmos 1366

(058)	Westar 5

(082)	Anik D1

(093)	Ekran 09

(097)	Intelsat 505

(103)	Gorizont 06

(105)	Aurora 1

(106)	DSCS 2-15

(106)	DSCS 3-01

(110)	SBS 3

(110)	Anik C3

(113)	Raduga 11

1983

(006)	Sakura 2A

(016)	Ekran 10

(026)	TDRS 1

(028)	Raduga 12

(030)	Satcom 1R

(047)	Intelsat 506

(058)	Eutelsat 1F1

(059)	Anik C2

(059)	Palapa B1

(065)	Galaxy 1

(066)	Gorizont 07

(077)	Telstar 301

(081)	Sakura 2B

(088)	Raduga 13

(089)	Insat 1B

(094)	Satcom 2R

(098)	Galaxy 2

(100)	Ekran 11

(105)	Intelsat 507

(118)	Gorizont 08

1984

(005)	Yuri 2A

(016)	Raduga 14

(022)	Cosmos 1540

(023)	Intelsat 508

(028)	Ekran 12

(035)	Dong Fang Hong 15

(041)	Gorizont 09

(049)	Spacenet 1

(063)	Raduga 15

(078)	Gorizont 10

(081)	Eutelsat 1F2

(081)	Telecom 1A

(090)	Ekran 13

(093)	SBS 4

(093)	Leasat 2

(093)	Telstar 302

(101)	Galaxy 3

(113)	Anik D2

(113)	Leasat 1

(114)	Spacenet 2

(114)	Marecs B2

(115)	Nato 3D

1985

(007)	Gorizont 11

(015)	Arabsat 1A

(015)	Brasilsat A1

(024)	Ekran 14

(025)	Intelsat 510

(028)	Anik C1

(028)	Leasat 3

(035)	Gstar 1

(035)	Telecom 1B

(048)	Morelos 1

(048)	Arabsat 1B

(048)	Telstar 303

(055)	Intelsat 511

(070)	Raduga 16

(076)	Optus A1

(076)	ASC 1

(076)	Leasat 4

(087)	Intelsat 512

(092)	DSCS 3-02

(092)	DSCS 3-03

(102)	Cosmos 1700

(107)	Raduga 17

(109)	Morelos 2

(109)	Optus A2

(109)	Satcom K2

1986

(003)	Satcom K1

(007)	Raduga 18

(010)	Dong Fang Hong 18

(016)	Yuri 2B

(026)	Gstar 2

(026)	Brasilsat A2

(027)	Cosmos 1738

(038)	Ekran 15

(044)	Gorizont 12

(082)	Raduga 19

(090)	Gorizont 13

(096)	Fleetsatcom 7

1987

(028)	Raduga 20

(029)	Palapa B2P

(040)	Gorizont 14

(070)	ETS 5

(073)	Ekran 16

(078)	Optus A3

(078)	Eutelsat 1F4

(084)	Cosmos 1888

(096)	Cosmos 1897

(100)	Raduga 21

(109)	Ekran 17

1988

(012)	Sakura 3A

(014)	Dong Fang Hong 22

(018)	Spacenet 3R

(018)	Telecom 1C

(028)	Gorizont 15

(036)	Ekran 18

(040)	Intelsat 513

(051)	Panamsat 1

(063)	Insat 1C

(063)	Eutelsat 1F5

(066)	Cosmos 1961

(071)	Gorizont 16

(081)	Gstar 3

(081)	SBS 5

(086)	Sakura 3B

(091)	TDRS 3

(095)	Raduga 22

(098)	TDF 1

(108)	Ekran 19

(109)	Skynet 4B

(109)	Astra 1A

(111)	Dong Fang Hong 25

1989

(004)	Gorizont 17

(006)	Intelsat 515

(020)	Jcsat 1

(021)	TDRS 4

(027)	TELE X

(030)	Raduga 23

(041)	Superbird A1

(041)	DFS 1

(048)	Raduga 1-1

(052)	Gorizont 18

(053)	Olympus

(062)	Tvsat 2

(067)	BSB 1

(069)	DSCS 2-16

(069)	DSCS 3-04

(077)	Fleetsatcom 8

(081)	Gorizont 19

(087)	Intelsat 602

(098)	Raduga 24

(101)	Cosmos 2054

1990

(001)	Skynet 4A

(001)	Jcsat 2

(002)	Leasat 5

(011)	Dong Fang Hong 26

(016)	Raduga 25

(021)	Intelsat 603

(030)	Asiasat 1

(034)	Palapa B2R

(051)	Insat 1D

(054)	Gorizont 20

(056)	Intelsat 604

(061)	Cosmos 2085

(063)	TDF 2

(063)	DFS 2

(074)	BSB 2

(077)	Yuri 3A

(079)	Skynet 4C

(079)	Eutelsat 2F1

(091)	SBS 6

(091)	Galaxy 6

(093)	Inmarsat 2F1

(094)	Gorizont 21

(100)	Satcom C1

(100)	Gstar 4

(102)	Gorizont 22

(112)	Raduga 26

(116)	Raduga 1-2

1991

(001)	Nato 4A

(003)	Italsat 1

(003)	Eutelsat 2F2

(014)	Raduga 27

(015)	Astra 1B

(018)	Inmarsat 2F2

(026)	Anik E2

(028)	ASC 2

(037)	Aurora 2

(046)	Gorizont 23

(054)	TDRS 5

(055)	Intelsat 605

(060)	Yuri 3B

(067)	Anik E1

(074)	Gorizont 24

(075)	Intelsat 601

(079)	Cosmos 2172

(083)	Eutelsat 2F3

(084)	Telecom 2A

(084)	Inmarsat 2F3

(087)	Raduga 28

1992

(006)	DSCS 3-05

(010)	Superbird B1

(010)	Arabsat 1C

(013)	Galaxy 5

(017)	Gorizont 25

(021)	Telecom 2B

(021)	Inmarsat 2F4

(027)	Palapa B4

(032)	Intelsat K

(037)	DSCS 3-06

(041)	Insat 2A

(041)	Eutelsat 2F4

(043)	Gorizont 26

(054)	Optus B1

(057)	Satcom C4

(060)	Hispasat 1A

(060)	Satcom C3

(066)	DFS 3

(072)	Galaxy 7

(074)	Ekran 20

(082)	Gorizont 27

(084)	Superbird A2

1993

(003)	TDRS 6

(029)	Raduga 29

(015)	UHF 1

(031)	Astra 1C

(039)	Galaxy 4

(046)	DSCS 3-07

(048)	Hispasat 1B

(048)	Insat 2B

(056)	UHF 2

(058)	ACTS

(062)	Raduga 30

(066)	Intelsat 701

(069)	Gorizont 28

(072)	Gorizont 29

(074)	DSCS 3-08

(076)	Nato 4B

(077)	Telstar 401

(078)	DBS 1

(078)	Thaicom 1

1994

(002)	Gals 1

(008)	Raduga 1-3

(009)	Milstar 1-1

(012)	Raduga 31

(013)	Galaxy 1R

(030)	Gorizont 30

(034)	Intelsat 702

(035)	UHF 3

(040)	Panamsat 2

(040)	Yuri 3N

(043)	Apstar 1

(047)	DBS 2

(049)	Brasilsat B1

(049)	Turksat 1B

(055)	Optus B3

(060)	Cosmos 2291

(064)	Intelsat 703

(065)	Solidaridad 2

(065)	Thaicom 2

(067)	Express 1

(070)	Astra 1D

(079)	Orion 1

(080)	Dong Fang Hong 41

(082)	Luch 0

(087)	Raduga 32

1995

(001)	Intelsat 704

(003)	UHF 4

(013)	Intelsat 705

(016)	Brasilsat B2

(016)	Hotbird 1

(019)	AMSC 1

(023)	Intelsat 706

(027)	UHF 5

(029)	DBS 3

(035)	TDRS 7

(038)	DSCS 3-09

(040)	Panamsat 4

(041)	Koreasat 1

(043)	Jcsat 3

(044)	N Star A

(045)	Cosmos 2319

(049)	Telstar 402R

(054)	Luch 1

(055)	Astra 1E

(057)	UHF 6

(060)	Milstar 1-2

(063)	Gals 2

(064)	Asiasat 2

(067)	Telecom 2C

(067)	Insat 2C

(069)	Galaxy 3R

(073)	Echostar 1

1996

(002)	Panamsat 3R

(002)	Measat 1

(003)	Koreasat 2

(005)	Gorizont 31

(006)	Palapa C1

(007)	N Star B

(015)	Intelsat 707

(020)	Inmarsat 3F1

(021)	Astra 1F

(022)	MSAT 1

(030)	Palapa C2

(030)	Amos 1

(033)	Galaxy 9

(034)	Gorizont 32

(035)	Intelsat 709

(039)	Apstar 1A

(040)	Arabsat 2A

(040)	Turksat 1C

(042)	UHF 7

(044)	Italsat 2

(044)	Telecom 2D

(053)	Inmarsat 3F2

(054)	GE 1

(055)	Echostar 2

(058)	Express 2

(063)	Arabsat 2B

(063)	Measat 2

(067)	Hotbird 2

(070)	Inmarsat 3F3

1997

(002)	GE 2

(002)	Nahuel 1A

(007)	Jcsat 4

(009)	Intelsat 801

(011)	Tempo 2

(016)	Thaicom 3

(016)	Bsat 1A

(021)	DFH 44

(025)	Thor 2

(026)	Telstar 5

(027)	Inmarsat 3F4

(027)	Insat 2D

(031)	Intelsat 802

(036)	Superbird C

(040)	Panamsat 6

(041)	Mabuhay 1

(049)	Hotbird 3

(050)	GE 3

(053)	Intelsat 803

(059)	Echostar 3

(062)	Apstar 2R

(065)	DSCS 3-10

(070)	Coupon 1

(071)	Sirius 2

(071)	Cakrawarta 1

(075)	Jcsat 5

(076)	Astra 1G

(078)	Galaxy 8i

(083)	Intelsat 804

1998

(002)	Skynet 4D

(006)	Brasilsat B3

(006)	Inmarsat 3F5

(013)	Hotbird 4

(014)	Intelsat 806

(016)	UHF 8

(024)	Nilesat 101

(024)	Bsat 1B

(028)	Echostar 4

(033)	Chinastar 1

(035)	Thor 3

(037)	Intelsat 805

(038)	Sinosat 1

(049)	ST 1

(050)	Astra 2A

(052)	Panamsat 7

(056)	Eutelsat 3F2

(056)	Sirius 3

(057)	Hotbird 5

(058)	UHF 9

(063)	Afristar

(063)	GE 5

(065)	Panamsat 8

(068)	Bonum 1

(070)	Morelos 3

(075)	Panamsat 6B

1999

(005)	Telstar 6

(006)	Jcsat 6

(009)	Arabsat 3A

(009)	Skynet 4E

(010)	Raduga 1-4

(013)	Asiasat 3S

(016)	Insat 2E

(018)	Eutelsat 3F3

(027)	Nimiq

(033)	Astra 1H

(042)	Palapa D1


 Navigation satellites

1960

Transit 1B

(007)	Transit 2A

1961

Transit 3B (loft 1)

(015)	Transit 4A

(031)	Transit 4B

1962

Transit 5A

1963

Transit 7 (5A3)

(038)	Transit 5BN1

(049)	Transit 5BN2

1964

Transit 9 (5C 1)

Transit 5B 4

Transit 5B 5

1965

NNSS 30 030 (Transit 5B 6)

NNSS 30 040 (Transit 5B 7)

NNSS 30 050 (Transit 10)

1966

NNSS 30 060 (Transit 11)

NNSS 30 070 (Transit 12)

NNSS 30 080 (Transit 13)

NNSS 30 090 (Transit 14)

1967

NNSS 30 120 (Transit 15)

NNSS 30 130 (Transit 16)

Timation 1

NNSS 30 140 (Transit 17)

Cosmos 192

1968

NNSS 30 180 (Transit 18)

Cosmos 220

1969

Cosmos 292

Timation 2 (+ 6 ss sat)

Cosmos 304

1970

Cosmos 332

NNSS 30 190

Cosmos 371

Cosmos 381

Cosmos 385

1971

Cosmos 422

Cosmos 465

1972

Cosmos 475

Cosmos 489

Cosmos 514

Triad 1

1973

Cosmos 574

Cosmos 586

NNSS 30 200

Cosmos 627

1974

Cosmos 628

Cosmos 660

Cosmos 663

Timation 3 (NTS 1)

Cosmos 689

Cosmos 700 (Parus)

1975

Cosmos 726 (Parus)

Cosmos 729

Cosmos 755 (Parus)

Triad 2 (TIP 2)

Cosmos 778 (Parus)

1976

Cosmos 789 (Parus)

Cosmos 800

Cosmos 807

Cosmos 823

Cosmos 842

Cosmos 846

Triad 3 (TIP 3)

Cosmos 864 (Parus)

Cosmos 883 (Tsikada)

Cosmos 887 (Parus)

1977

Cosmos 890

Cosmos 894 (Parus)

Cosmos 911

Cosmos 926 (Tsikada)

Cosmos 928 (Parus)

Cosmos 951 (Parus)

NNSS 30 110

Cosmos 962

Cosmos 971 (Parus)

1978

Cosmos 985 (Parus)

(020)	GPS BI-01

Cosmos 991 (Parus)

Cosmos 994

Cosmos 996 (Parus)

(034)	Cosmos 1000 (Tsikada)

(047)	GPS BI-02

Cosmos 1011 (Parus)

Cosmos 1027

(093)	GPS BI-03

(112)	GPS BI-04

Cosmos 1064

1979

Cosmos 1072 (Parus)

Cosmos 1089 (Parus)

Cosmos 1091 (Parus)

Cosmos 1092 (Tsikada)

Cosmos 1104 (Parus)

Cosmos 1141 (Parus)

1980

Cosmos 1150 (Parus)

Cosmos 1153 (Parus)

(011)	GPS BI-05

Cosmos 1168 (Tsikada)

(032)	GPS BI-06

Cosmos 1181 (Parus)

Cosmos 1225 (Parus)

Cosmos 1226 (Tsikada)

1981

Cosmos 1244 (Parus)

(044)	Nova 1

Cosmos 1275 (Parus)

Cosmos 1295 (Parus)

Cosmos 1304 (Tsikada)

Cosmos 1308 (Parus)

1982

Cosmos 1333 (Parus)

Cosmos 1339 (Tsikada)

Cosmos 1344 (Parus)

Cosmos 1349 (Parus)

Cosmos 1380

Cosmos 1383 (Tsikada)

Cosmos 1386 (Parus)

Cosmos 1413 (dummy)

Cosmos 1414 (Glonass)

Cosmos 1415 (dummy)

Cosmos 1417 (Parus)

1983

Cosmos 1428 (Parus)

Cosmos 1447 (Tsikada)

Cosmos 1448 (Parus)

Cosmos 1459 (Parus)

Cosmos 1464 (Parus)

(072)	GPS BI-08

Cosmos 1490 (Glonass)

Cosmos 1491 (Glonass)

Cosmos 1492 (dummy)

Cosmos 1506 (Tsikada)

Cosmos 1513 (Parus)

Cosmos 1519 (Glonass)

Cosmos 1520 (Glonass)

Cosmos 1521 (dummy)

1984

Cosmos 1531 (Parus)

Cosmos 1535 (Parus)

Cosmos 1550 (Parus)

Cosmos 1553 (Tsikada)

Cosmos 1554 (Glonass)

Cosmos 1555 (Glonass)

Cosmos 1556 (dummy)

(059)	GPS BI-09

Cosmos 1574 (Tsikada)

Cosmos 1577

Cosmos 1593 (Glonass)

Cosmos 1594 (dummy)

Cosmos 1595 (Glonass)

(097)	GPS BI-10

Cosmos 1598 (Parus)

Cosmos 1605 (Parus)

(110)	Nova 2

Cosmos 1610 (Parus)

1985

Cosmos 1627 (Parus)

Cosmos 1634 (Parus)

Cosmos 1650 (Glonass)

Cosmos 1651 (Glonass)

Cosmos 1652 (dummy)

Cosmos 1655 (Tsikada)

(095)	GPS BI-11

SOOS ? Transit 19 (SOOS 240 - 300)

SOOS ?Transit 20

Cosmos 1704 (Parus)

Cosmos 1709 (Parus)

Cosmos 1710 (Glonass)

Cosmos 1711 (Glonass)

Cosmos 1712 (dummy)

1986

Cosmos 1725 (Parus)

Cosmos 1727 (Tsikada)

Cosmos 1745 (Parus)

Cosmos 1759 (Parus)

Cosmos 1778 (Glonass)

Cosmos 1779 (Glonass)

Cosmos 1780 (Glonass)

Cosmos 1791 (Tsikada)

Polar Bear (17070)

Cosmos 1802 (Parus)

Cosmos 1808 (Parus)

1987

Cosmos 1816 (Tsikada)

Cosmos 1821 (Parus)

Cosmos 1838 (Glonass)

Cosmos 1839 (Glonass)

Cosmos 1840 (Glonass)

(054)	Cosmos 1861 (Tsikada)

Cosmos 1864 (Parus)

Cosmos 1883 (Glonass)

Cosmos 1884 (Glonass)

Cosmos 1885 (Glonass)

SOOS 270 (Oscar 27)

SOOS 290 (Oscar 29)

Cosmos 1891 (Parus)

Cosmos 1904 (Parus)

1988

Cosmos 1917 (Glonass)

Cosmos 1918 (Glonass)

Cosmos 1919 (Glonass)

(023)	Cosmos 1934 (Parus)

SOOS 230 (Oscar 23)

SOOS 320 (Oscar 32)

Cosmos 1946 (Glonass)

Cosmos 1947 (Glonass)

Cosmos 1948 (Glonass)

(052)	Nova 3

(062)	Cosmos 1959 (Parus)

SOOS 250 (Oscar 25)

SOOS 310 (Oscar 31)

(085)	Cosmos 1970 (Glonass)

(085)	Cosmos 1971 (Glonass)

(085)	Cosmos 1972 (Glonass)

1989

(001)	Cosmos 1987 (Glonass)

(001)	Cosmos 1988 (Glonass)

(001)	Cosmos 1989

(013)	GPS BII-01

(017)	Cosmos 2004 (Parus)

(028)	Cosmos 2016 (Parus)

(031)	Cosmos 2018

(039)	Cosmos 2022 (Glonass)

(039)	Cosmos 2023 (Glonass)

(039)	Cosmos 2024 (Glonass)

(042)	Cosmos 2026 (Parus)

(044)	GPS BII-02

(050)	Nadezhda 1

(059)	Cosmos 2034 (Parus)

(064)	GPS BII-03

(085)	GPS BII-04

(097)	GPS BII-05

1990

(008)	GPS BII-06

(017)	Nadezhda 2

(023)	Cosmos 2061 (Parus)

(025)	GPS BII-07

(036)	Cosmos 2074 (Parus)

(045)	Cosmos 2079 (Glonass)

(045)	Cosmos 2080 (Glonass)

(045)	Cosmos 2081 (Glonass)

(068)	GPS BII-08

Cosmos 2100 (Parus)

(088)	GPS BII-09

(103)	GPS BIIA-10

(110)	Cosmos 2109 (Glonass)

(110)	Cosmos 2110 (Glonass)

(110)	Cosmos 2111 (Glonass)

1991

(007)	Cosmos 2123 (Tsikada)

Cosmos 2135 (Parus)

(019)	Nadezhda 3

(025)	Cosmos 2139 (Glonass)

(025)	Cosmos 2140 (Glonass)

(025)	Cosmos 2141 (Glonass)

(029)	Cosmos 2142 (Parus)

(047)	GPS BIIA-11

Cosmos 2154 (Parus)

(081)	Cosmos 2173 (Parus)

1992

(005)	Cosmos 2177 (Glonass)

(005)	Cosmos 2178 (Glonass)

(005)	Cosmos 2179 (Glonass)

Cosmos 2180 (Parus)

Cosmos 2181 (Tsikada)

(009)	GPS BIIA-12

(019)	GPS BIIA-13

Cosmos 2184 (Parus)

Cosmos 2195

(039)	GPS BIIA-14

(047)	Cosmos 2204 (Glonass)

(047)	Cosmos 2205 (Glonass)

(047)	Cosmos 2206 (Glonass)

(058)	GPS BIIA-15

(073)	Cosmos 2218 (Parus)

(079)	GPS BIIA-16

(089)	GPS BIIA-17

1993

(001)	Cosmos 2230 (Tsikada)

(007)	GPS BIIA-18

(008)	Cosmos 2233 (Parus)

(010)	Cosmos 2234 (Glonass)

(010)	Cosmos 2235 (Glonass)

(010)	Cosmos 2236 (Glonass)

(017)	GPS BIIA-19

(020)	Cosmos 2239 (Parus)

(032)	GPS BIIA-20

(042)	GPS BIIA-21

(054)	GPS BIIA-22

(068)	GPS BIIA-23

(070)	Cosmos 2266 (Parus)

1994

(016)	GPS BIIA-24

(021)	Cosmos 2275 (Glonass)

(021)	Cosmos 2276 (Glonass)

(021)	Cosmos 2277 (Glonass)

(024)	Cosmos 2279 (Parus)

(041)	Nadezhda 4

(050)	Cosmos 2287 (Glonass)

(050)	Cosmos 2288 (Glonass)

(050)	Cosmos 2289 (Glonass)

(076)	Cosmos 2294 (Glonass)

(076)	Cosmos 2295 (Glonass)

(076)	Cosmos 2296 (Glonass)

1995

(009)	Cosmos 2307 (Glonass)

(009)	Cosmos 2308 (Glonass)

(009)	Cosmos 2309 (Glonass)

(012)	Cosmos 2310 (Parus)

(032)	Cosmos 2315 (Kurs)

(037)	Cosmos 2316 (Glonass)

(037)	Cosmos 2317 (Glonass)

(037)	Cosmos 2318 (Glonass)

(052)	Cosmos 2321 (Parus)

(068)	Cosmos 2323 (Glonass)

(068)	Cosmos 2324 (Glonass)

(068)	Cosmos 2325 (Glonass)

1996

(004)	Cosmos 2327 (Parus)

(019)	GPS BIIA-25

(041)	GPS BIIA-26

(051)	Cosmos 2333 (Parus)

(056)	GPS BIIA-27

1997

(017)	Cosmos 2333 (Parus)

(035)	GPS BIIR-02

(052)	Cosmos 2346 (Parus)

(067)	GPS BIIA-28

1998

(072)	Nadezhda 5

(076)	Cosmos 2361 (Parus)

(077)	Cosmos 2362 (Glonass)

(077)	Cosmos 2363 (Glonass)

(077)	Cosmos 2364 (Glonass)


 Radioactive payload and debris

Radioactive payloads have been a concern for the community ever since radioactive debris decayed on Earth and contaminated entire regions. The first such event was in Jan 1978 when Cosmos 0954 decayed. Since then radioactive debris are closely monitored.

Those nuclear reactors which are to remain in orbit for a hundred years or so also caused problems to scientists. "Nuclear noise" as it is called cause gamma ray disturbances to astronomers. Indeed those reactors interfere periodically with gamma-ray surveys.

Russian satellites

The Russian Rorsat program is the most important program with nuclear reactor equipped satellites (32 spacecrafts). This engine (named Topol or Topaz) contains 50 kg of uranium and provides about 2000 W.

Two other Russian satellites are known to have a Topaz 1 reactor (also named Buk): Cosmos 1818 (87011A) and Cosmos 1867 (87060A), probably for test missions. This reactor provides around 5-6 kW power. It weighs 1350 kg.

A third engine named Enissei or Topaz 2 was built but has never been launched. It provides 6 kW and weighs 1 ton.

US satellites

The United States also used nuclear power on space missions. Two types of engines were used:

- Nuclear reactors which produce energy by nuclear fission (space based reactors use Uranium-235).

- RTGs (Radioisotope Thermoelectric Generator) which use the energy of radioactive decay (current SNAPs use Plutonium-238).

The SNAP (Systems for Nuclear Auxiliary Power) series include:

RTG engines	Nuclear reactors	Uncertain
Transit 4A	OPS 4682 also called SNAPSHOT (65027A)	LES 5
Transit 4B		LES 6
Nimbus 3		OPS 0757 also called Tacsat (69013A)
LES 8
LES 9

Other missions required nuclear power such as the Apollo moon missions experiments, the Viking Mars Landers, Pioneer and Voyager missions and the Galileo probe:

LAUNR	Spacecraft	Orbit
69-099	APOLLO 12	Moon
71-008	APOLLO 14	Moon
71-063	APOLLO 15	Moon
72-012A	PIONEER 10	escaped solar system
72-031	APOLLO 16	Moon
72-096	APOLLO 17	Moon
73-019A	PIONEER 11	escaped solar system
75-075	VIKING 1 LANDER	Mars
75-083	VIKING 2 LANDER	Mars
77-076A	VOYAGER 2	escaped solar system
77-084A	VOYAGER 1	escaped solar system
89-084B	GALILEO	Jupiter
90-090B	ULYSSES	Sun
96-068A	PATHFINDER	Mars
97-061A	CASSINI	to Saturn

Pathfinder had RHUs (Radioisotope Heater Units) on the Sojourner rover.

Finally 3 missions failed:

Transit 5BN3 on 21 Apr 1964 aboard Thor Ablestar

Nimbus 3A

Apollo 13 (70029A) on 11 Apr 1970 which decayed on 17 Apr 1970


 Addresses

Air Force Space Command

Alascom Inc.

Alcatel Telecom

AMSC

Antrix

APT

Arabsat

Arianespace

Asiasat

COTS

Chinasat

Columbia Communications Corp.

Comsat Corporation

DTAG

Earth Watch Inc.

Echostar Satellite Corp.

Embratel

Eosat

Eumetsat

Eutelsat

FAI

France Telecom

GE Americom

GE Capital Satellites-Europe

Globalstar L.P.

HCI

Hispasat S.A.

ILS

Informcosmos

Inmarsat Ltd

Intelsat

Intersputnik

Iridium LLC

ISRO

JSAT

KaStar Satellite Communications Corp.

Korea Telecom

LEO One

Lockheed Martin Global Telecommunications

Lockheed Martin Intersputnik

Loral Orion

Loral Skynet

Loral Space & Communications Ltd

Mabuhay

Measat

Mobile Communications Holdings, Inc.

Nahuelsat S.A.

NASA

Nilesat

NOAA

NSAB

NTT

Odyssey Telecommunications

Optus Communications

Orbcomm

Orbital Science Corporation

Panamsat Corporation

Paracomsat

PASI

PLDT

PT Pasifik Satelit Nusantara

PT Satelindo

PT Telkom

RadarSat International (RSI)

Satmex

SCC

SES

Shinawatra Satellite Company Ltd

Singapore Telecom

Sinosat

Spacecom Ltd.

SSTL

TDF

Teledesic

Telenor

Telesat Canada

Telespazio

Teracom

Thuraya Satellite Telecommunications Co

TMI Communications

Tsat

Turk Telekom

USSB

Worldspace


Asia Broadcasting and Communications Network, Ltd.

(ABCN)

SM Tower, 979/66-70 Phaholyothin Road, Phayathai, Bangkok, 10400, Thailand

Tel: +662-298-0044

Fax: +662-271-3076


Air Force Space Command

50th Space Wing, 300 O'Malley Ave, Suite 24, Falcon AFB, CO 80912-3024, USA

http://www.spacecom.af.mil/hqafspc/

Programs: DMSP, Fleetsatcom, GPS, UHF


Alascom
Alascom Inc.

210 Bluff Road, Box 6607, Anchorage, AK99502-7649, USA

Tel: +1-907-264-7000

Fax: +1-907-264-7704

Program: Aurora

a subsidiary of AT&T


Alcatel Telecom

10, Rue Latécoère, BP 57, 78141 VELIZY CEDEX, France

Tel: +33-1-3077-8010

Fax: +33-1-3077-8066

http://www.alcatel.com/telecom/space/

Program: Skybridge


American Mobile Satellite Corporation

(AMSC)

10802 Parkridge Blvd., Reston, VA 22091, USA

Tel: +1-703-758-6000

Fax: +1-703-758-6111

http://www.ammobile.com/

NASDAQ:SKYC

Program: AMSC


Antrix Corporation Limited

Antrix Complex, New BEL Road, Bangalore, 560 094, India

Tel: +91-80-3415474

Fax: +91-80-3418981


Asia Pacific Telecommunication Satellites Company Ltd

(APT)

Room 3111-2, 31st floor, One Pacific Plaza, 88 Queens way, Hong Kong

Tel: +852-2-526-2281

Fax: +852-2-522-0419

http://www.apstar.com

NYSE:ATS

Program: Apstar


Arabsat

PO Box 1038, Riyadh 11431, Saudi Arabia

Tel: +966-1-464-6666

Fax: +966-1-462-4169

Email: arabsat@arab.net

http://www.arabsat.com/

Program: Arabsat


Arianespace

Boulevard de l'Europe, BP 177, 91006 EVRY cedex, France

Fax: +33-1-6087-6217

http://www.arianespace.com

Program: Ariane


Asia Satellite Telecommunications Company Ltd

(Asiasat)

23-24/F, East Exchange Tower, 38-40 Leighton Road, Causeway Bay, Hong Kong

Tel: +852-2-805-6666

Fax: +852-2-504-3875

http://www.asiasat.com.hk

NYSE:SAT

Program: Asiasat

Asiasat is owned by Hong Kong's Hutchison Whampoa Ltd, Beijing's China International Trust and Investment Corp (CITIC) and SES. In Jan 1999, SES bought 34.13% of Asiasat, buying the full stake of Cable and Wireless (29%) and the rest from Hutchison Whampoa (cost of the transaction: $331 million).


COTS

China Orient Telecommunications Satellite

7/F Ande road, East City district, Beijing, 100011, China

Tel: +86-10-642-423-70

Fax: +86-10-642-423-66

http://www.chinastar.com.cn/

Limited liability company formed in April 1995. Main investor: MPT.


Chinasat

China Telecommunications Broadcast Satellite

42 Xue Yuan road, Hai Dian District, Beijin, 100083, China

Tel: +86-10-623-035-53

Fax: +86-10-623-035-50

http://www.chinasat.com/

Program: DFH

Established in 1983 as an affiliate of MPT. It later became a subsidiary of China Telecom. Prior to Chinasat 5, the DFH program was purely military; Chinasat 5 was the first civilian satellite.


Columbia Communications Corp.

7200 Wisconsin Ave., Suite 701, Bethesda, MD 20814, USA

Tel: +1-301-907-8800

Fax: +1-301-907-2420

columbia@tdrss.com

http://www.tdrss.com

Program: Columbia


Comsat Corporation

6560 Rock Spring Drive, Bethesda, MD 20817, USA

Tel: +1-301-214-3658

Fax: +1-301-214-7130

http://www.comsat.com

NYSE:CQ

Should be purchased by Lockheed martin upon FCC aproval for $2.7 billion.

Programs: Comstar, Intelsat, Marisat, SBS


Deutsche Telekom AG

(DTAG)

Godesberger Alle 87-91, 53175 Bonn, Germany

Tel: +49-228-181-1211

Fax: +49-228-181-8872

http://www.dtag.de

Programs: DFS Kopernikus, Tvsat


Earth Watch Inc.

1900 Pike Road, Longmont, CO 80501, USA

Tel: +1-800-496-1225

Tel: +1-303-702-5561

Fax: +1-303-702-5562

Email: info@digitalglobe.com

http://www.digitalglobe.com


Echostar Satellite Corp.

5701 S. Santa Fe Drive, Littleton, CO 80120, USA

Tel: +1-303-723-1000

Fax: +1-303-252-1845

http://www.echostar.com

NASDAQ:DISH

Program: Echostar

Echostar is owned at 50% by News Corp.


Mobile Communications Holdings, Inc.

(MCHI)

1120 19th Street, N.W., Suite 460, Washington, DC 20036, USA

Tel +1-202-466-4488

Fax +1-202-466-4493

http://www.ellipso.com

Email: jtedino@mchi.com

Program: Ellipsat

Principal Subsidiaries: Ellipsat International Inc. & Ellipsat Corporation


Empresa Brasileira de Telecomunicações S.A.

(Embratel)

Avenida Presidente Vargas 1012, Rio de Janeiro 20279-900, Brazil

Tel: +55-21-519-8879

Fax: +55-21-519-8902

http://www.embratel.com.br/

Program: Brasilsat


EOSAT

Space Imaging

4300 Forbes Boulevard, Lanham, MD 20706, USA

Tel: +1-301-552-0537 or +1-800-344-9933

Fax: +1-301-552-3762

http://www.spaceimage.com


Eurasiasat

Athos Palace, 2 rue de la Lugernetta, MC98000 Monaco

Tel: +377-97-98-5750

Fax: +377-97-77-8220

http://www.eurasiasat.com/

Email: eurasiasat@atsat.com

Program: Eurasiasat


European Meteorologic Satellite

Eumetsat

Am Kavalleriesand 31, D-64295 Darmstadt, Germany

Tel: +49-6151-807-7

Fax: +49-6151-807-555

http://www.eumetsat.de/

Program: Meteosat

Organization created in May 1983 based at Darmstadt, Germany, that counts 17 members: Austria, Belgium, Denmark, Finland, France, Germany, Greece, Ireland, Italy, Netherlands, Norway, Portugal, Spain, Sweden, Switzerland, Turkey and United Kingdom.

Funding: $4.5 million (1985-1995); Germany 24%, France 18%, Italy 15% and UK 14%


EUropean TELecommunication SATellite

Eutelsat

70 rue Balard, 75502 Paris cedex 15, France

Tel: +33-1-5398-4747

Fax: +33-1-5398-3700

Fax on demand: +33-1-5398-2338

http://www.eutelsat.org

Program: Eutelsat

When Eutelsat was created it gathered 17 countries. Currently 48 countries are members of Eutelsat: Albania, Andorra, Armenia, Austria, Azerbaidjan, Belarus, Belgium, Bosnia, Cyprus, Croatia, Denmark, Finland, France, Georgia, Greece, Germany, Hungary, Ireland, Iceland, Italy, Liechtenstein, Lithuania, Luxemburg, Malta, Moldavia, Monte-Carlo, Netherlands, Norway, Poland, Portugal, Rumania, Russia, San Marino, Slovaky, Sloveny, Spain, Sweden, Switzerland, Czechy, Turkey, United Kingdom, Ukraine, Vatican, Yugoslovia


Final Analysis Inc.
Final Analysis, Inc.

(FAI)

9701-E Philadelphia Court, Lanham, MD 20706, USA

Tel: +1-301-459-0100

Fax: +1-301-459-0101

http://www.finalanalysis.com/

Program: Faisat


France Telecom

21 rue de la vanne, BP 800, 92542 Montrouge cedex, France

Tel: +33-1-5595-2600

Fax: +33-1-5595-2700

FTE.PA

http://www.francetelecom.fr

http://www.globecast.com

Program: Telecom


GE American Communications, Inc.

GE Americom

4 Research Way, Princeton, NJ 08540-6684, USA

Tel: +1-800-273-0329

Tel: +1-609-987-4000

Fax: +1-609-987-4517

Email: americom.info@capital.ge.com

http://www.ge.com/capital/americom/

Programs: GE, GE*Star, Gstar, Satcom, Spacenet, Starsys

Company formed in 1975. Wholly-owned subsidiary of GE Capital Services, a General Electric company.


GE Capital Satellites-Europe

Sweden House, 2nd floor, 20 St. James' Street, London SW1A 1ES, UK

Tel: +44-171-302-6302

Fax: +44-171-302-6352

Email: satellites@ge.geis.com

Program: Sirius 2

Subsidiary of GE Americom


Globalstar L.P.

3200 Zanker Road, P.O. Box 640670, San Jose, CA 95164-0670, USA

Tel +1-408-473-5550

Fax +1-408-473-5750

http://www.globalstar.com/

Program: Globalstar

Founded by Loral Corp. and Qualcomm Inc.


Hughes Communications Inc.
Hughes Space and Communications Inc.

(HCI)

PO Box 9712, Long Beach, CA 90810, USA

Tel: +1-310-525-5211

Fax: +1-310-525-5220

http://www.hughespace.com/

Programs: DBS, Expressway, Galaxy, Panamsat, Spaceway

a subsidiary of GM Hughes Electronics

In Jan 1999 Hughes filled for for 2 new Ku-band systems: Hughes Net, a 70 satellite LEO system and Hughes Link, a 15 satellite MEO system.


Hispasat S.A.

Apartado P.O. Box: 95.000, 28080 Madrid, Spain

Tel: +34-1-372-9000

Fax: +34-1-307-7705

http://www.hispasat.es/

Programs: Hispasat


International Launch Services

(ILS)

101 West Broadway, Suite 2000, San Diego, CA 92101, USA

Tel: +1-619-645-6400

Fax: +1-619-645-6500

http://www.ilslaunch.com/


Informcosmos

16 Kazakova Street, Moscow 103064 Russia

Tel: +7-095-261-5494

Fax: +7-095-261-0090


Inmarsat Ltd

99 City Road, London EC1Y 1AX, United Kingdom

Tel: +44-171-728-1000

Fax: +44-171-728-1044

http://www.inmarsat.org

Programs: Inmarsat, ICO


Intelsat

3400 International drive NW, Box 63, Washington DC, 20008, USA

Tel: +1-202-944-6800

Fax: +1-202-944-7890

http://www.intelsat.int

Program: Intelsat


Intersputnik

2 Smolensky Lane 1/4, Moscow, 121099, CIS

Tel: +7-095-244-0333

Fax: +7-095-253-9906

Email: dir@intersputnik.com

http://www.intersputnik.com

Programs: Express, Gorizont, Intersputnik

Today Intersputnik has the following 22 members: Afghanistan, Belarus, Bulgaria, Cuba, Czechoslovakia, Georgia, Germany, Hungary, Kazakhstan, Kirghistan, North-Korea, Laos, Mongolia, Nicaragua, Poland, Tajikistan, Turkmenistan, Romania, Russia, Syria, Yemen and Vietnam.


Iridium LLC

1575 Eye Street, NW, Suite 500, Washington, DC 20005, USA

http://www.iridium.com

Program: Iridium


ISRO

Antariksh Bhavan, New B.E.L. road, Bangalore 560 094, India

Tel: +91-80-341-5275

Fax: +91-80-341-2253

http://www.isro.org/

Programs: Insat, IRS


JSAT

Japan Satellite Systems Inc. - Kabushiki-gaisha Nihon Sateraito Sisutemuzu

Toranomon 17 Mori Bldg. 5th Fl., 1-26-5 Toranomon, Minato-ku, Tokyo 105 Japan

Tel: +81-3-5511-7777

Fax: +81-3-3597-0601

http://www.jcsat.co.jp/

Program: Jcsat

JSAT was formed in 1993 by the merger of Japan Communications Satellite Co (JCSAT, which operated the first two JCSAT satellites) and Satellite Japan Corp (SAJAC). JSAT is owned by Itochu Corp , Mitsui & Co , Nissho Iwai Co and Sumitomo Corp. NTT should join in.


KaStar Satellite Communications Corp.

P.O. Box 1471, Evergreen, CO 80437, USA

DMDTV@aol.com

http://www.kastarcom.com

Program: Ladybug


Korea Telecom

Satellite Business Group, Korea Telecom

680-63, Jayang-dong, Kwangjin-gu, Seoul, Korea

Tel: +82-2-201-0082

Fax: +82-2-458-6430

Email: koreasat@ktweb.kotel.co.kr

Program: Koreasat


LEO One (firm)
LEO One

150 North Meramec Avenue, #620, St Louis, MO 63105, USA

Tel: +1-314-746-0567

Fax: +1-314-721-3410

Email: info@leoone.com

http://www.leoone.com

Program: LEO One


Lockheed Martin Global Telecommunications

LM Corporation

6801 Rockledge Drive, MP 200-12, Bethesda, MD  20817, USA

Tel: +1-301-897-6975

Fax: +1-301-897-6296

This wholly owned LM subsidiary comprises: LM Intersputnik, Astrolink, LM Telecommunications and the stake in the joint venture with GE Americom (GE 1A).


Lockheed Martin Intersputnik

43-45 Portman Square, 4th floor, London W1H 9TH, UK

Tel: +44-171-864-4100

Fax: +44-171-864-4101

http://www.lmiglobal.com

Partially owned by LM Global Telecommunications


Loral Skynet

500 Hills Drive, Box 7018, Bedminster, NJ 07921, USA

Tel: +1 908 470-2300

Fax: +1 908 470-2459

http://www.loralskynet.com/

The Brasilian subsidiary has won a $18 million bid for the 63°W slot use. A satellite is to be located there (within 3 years, reference Mar 1999) to serve at least for half for Brazil. This concession is for 30 years.


Loral Space & Communications Ltd

600 Third Ave., New York, NY 10016, USA

Tel: +1-212-338-5658

Fax: +1-212-338-5662

http://www.loral.com

Program: Loralsat, Morelos, Orion, Solidaridad


Mabuhay Philippines Satellite Corp.

(MPSC)

20/F PLDT tower 2, 6799 Ayala Avenue, Makati City 1226, Philippines

Tel: +63-2-887-5788

Fax: +63-2-887-5789

http://www.mabuhaysat.com/

Program: Mabuhay


Measat
Measat - Binariang Satellite Systems Sdn Bhd

Menara Maxis, 37th Floor, Kuala Lumpur 50088, Malaysia

Tel : +60-3-380-7121

Fax : +60-3-380-7018

http://www.measat.com.my/

Program: Measat


Nahuelsat S.A.

Lavalle 472, Piso 3, 1047 Buenos Aires, Argentina

Tel: +54-1-327-2292

Fax: +54-1-327-2319

http://www.nahuelsat.com.ar/

Program: Nahuelsat

Nahuelsat is owned by Deutsche Aerospace (Germany) 21%, and Alenia Spazio (Italy). Other private corporate and institutional equity investors, mainly from Argentina, Brazil, and Europe, have acquired stakes in Nahuelsat as well. Telecom Argentina acquired 5.57 percent. In mid-Jan 1997 GE Americom acquired 17.25 percent of the $100-million equity of Nahuelsat S.A.


NASA

600 Independence Avenue, SW, Washington DC 20546

Tel: +1-202-453-1000

http://www.nasa.gov/


New Skies Satellites N.V.

Rooseveltplantsoen 4, The Hague NL-2517 KR, Netherlands

Tel: +31-70-306-4100

Fax: +31-70-306-4101

http://www.newskiessat.com/


Nilesat

6th October City, Egypt

Tel: +202-400145

Fax: +202-400119

http://www.nilesat.com.eg/


NOAA

Office of Satellite Operations

Federal Building 4, Room 135, 4401 Suitland Road, Suitland, MD 20233

Tel: +1-301-457-5130

http://www.noaa.gov/

Programs: DMSP, Goes, Nimbus, NOAA, NPOESS, Tiros


Nordiska Satellitaktiebolaget

(NSAB)

Vretenvägen 10, Solna SE-171 54, Sweden

Tel: +46-8-445-1750

Fax: +46-8-28-24-80

http://www.nsab.se/

Programs: Sirius, Tele X


Nippon Telegraph and Telephone Corporation

(NTT)

1-6 Uchisaiwai-cho, 1-chome, Chiyoda-Ku, Tokyo 100, Japan

Tel: +81-3-3509-3101

Fax: +81-3-3509-4290

http://www.ntt.co.jp

Programs: N Star, Sakura


Odyssey Telecommunications

One Space Park, Redondo Beach, CA 90278, USA

Tel: +1-310-814-8888

Fax: +1-310-814-1400


Optus Communications

101 Miller Street, North Sydney, NSW 2060, Australia

Tel: +61-2-342-7800

Fax: +61-2-342-7100

http://www.optus.net.au

Program: Optus

49% of the firm is owned by Cable & Wireless, 25% by Mayne Nickless Ltd of Australia.


Orbcomm

21700 Atlantic Boulevard, Dulles, Virginia 20166-6801 USA

Tel: 1-800-orbcomm

Tel: +1-703-406-6000

Fax: +1-703-406-3504

Email: orbcomm@orbital.com

http://www.orbcomm.net

Programs: Orbcomm

Parent companies are Orbital Sciences Corp. (50%), Teleglobe Inc. and TRI Inc. of Malaysia.


Orbital Science Corporation

(OSC)

21700 Atlantic Boulevard, Dulles, Virginia 20166-6801, USA

Tel: 1-800-orbcomm

Tel: +1-703-406-5000

Fax: +1-703-406-5511

http://www.orbital.com

NASDAQ:ORBI

Subsidiaries: Orbcomm, Orbimage


Loral Orion

Was Orion Network Systems Inc.

2440 Research Boulevard, Rockville, MD 20850, USA

Tel:1-800-786-7466

Tel: +1-301-258-8101

Fax: +1-301-258-3222

http://www.loralorion.com/

NASDAQ:ONSI

Program: Orion

Was bought by Loral Space & Communications Ltd


Panamsat Corporation

One Pichwick Plaza, Greenwich, CT 06830, USA

Tel: +1-203-622-6664

Fax: +1-203-622-9163

http://www.panamsat.com

NASDAQ: SPOT

Program: Panamsat

81% of the firm is owned by Hughes Electronics Corporation


Paracomsat

25 de Mayo 516, 6 Piso, (1002) Buenos Aires, Argentina

Tel: +54-1-313-5058 or 313-5158 or 313-9829

Fax: +54-1-311-1852


Philippine Agila Satellite Inc

(PASI)

Domsat Holdings Inc

18th floor Pearlbank Center, 146 Valero St., Salcedo Village, City of Makati, Philippine

Tel: +632-840-30-21

Fax: +632-750-57-64


Philippine Long Distance Telephone Co

(PLDT)

7/F Ramon Cojuangco Building, Makati Ave., Makati, Metro Manila, Philippine

Tel: +632-816-8911

Fax +632-818-6800

TEL.PS

Program: Mabuhay


PT Media Citra Indostar

Elektrindo Building, 8/F, Jl. Kuningan Barat No. 8, Jakarta 12710 Indonesia

Tel: +62-21-526-9380

Fax: +62-21-526-9389

http://www.indovision.co.id/

Media Citra is owned by Matahari Lintas Cakrawala which is 61 percent controlled by PT Datakom Asia.


PT Pasifik Satelit Nusantara

Mulia Centre # 1201, Jl. Rasuna Said Kav X/6 No. 8, Jakarta 12940, Indonesia

Tel: +62-21-5229292

Fax: +62-21-5229293

Email: psn@psn.co.id

http://www.psn.co.id

NASDAQ:PSNRY

Program: M2A, Palapa


PT Satelindo

PT Satellit Palapa Indonesia (Satelindo)

Ji Daan Mogot KM 11, Jakarta Barat 11710, Indonesia

Tel: +62-21-545-1745

Fax: +62-21-545-1746

http://www.satelindo.co.id

Program: Palapa


PT Telkom

Jl. Japati No. 1, Bandung, Indonesia

Tel: +62-22-452-2330

Fax: +62-22-706-225

Program: Palapa


RadarSat International

(RSI)

275 Slater Street, Suite 1203, Ottawa, Ontario K1P5H9, Canada

Tel: +1-613-238-6413

Fax: +1-613-238-5425

Program: Radarsat


Satmex

Satelites Mexicanos, S.A. de C.V.

Blvd. M. Avila Camacho 40, Col. Lomas de Chapultepec, Mexico D.F. 11000, Mexico

Tel: +52-5-201-0898

Fax: +52-5-201-0852

http://www.satmex.com.mx/

Mexican satellite program now owned by a joint venture with Loral (49% Loral, 26% Telefonica Autrey and 25% Mexican government). The privatization occured in Oct 1997, the 75% of Satmex costed $688 million.

Programs: Morelos and Solidaridad


Singapore Telecom

31 Exeter Road, Comcentre, Singapore 0923, Singapore

Tel: +65-838-3388

Fax: +65-734-8119

http://www.singtel.com


Sino Satellite Communications Company Ltd

F11, Capital Plaza, 132 Xiwaidajie, Western District, Beijin 100044, China

Tel: +86-10-6833-1916

Fax: +86-10-6833-1927

http://www.sinosat.com.cn/

Joint venture of CASC, Defense Science and Technology and People's Bank of China. Non-MPT project.


Shinawatra Satellite Company Ltd

41/103 Rattanathibet Road, Nonthaburi 11000, Thailand

Tel: +662-591-0736

Fax: +662-591-0719

http://www.thaicom.net/

Program: Thaicom


Société Européenne de Satellites

(SES)

Château de Betzdorf, 6815 Betzdorf, Luxembourg

Tel: +352-710-7251

Fax: +352-710-725526

http://www.astra.lu

Program: Astra

Holds shares of Asiasat which provides 49.5% of the voting power


Space Communications Corporation

(SCC)

2-2-8, Higashi-shinagawa, Shinagawa-ku,Tokyo, 140-0002, Japan

Tel: +81-3-5462-1350

Fax: +81-3-5462-1391

http://www.superbird.co.jp

Program: Superbird

The company formed in 1985 is mainly owned by Mitsubishi


Spacecom Ltd.

Twin Towers II, suite 917, 35 Jabotinsky St., Ramat Gan 52511, ISRAEL

Tel: +972-3-613-4720

Fax: +972-3-613-4723

Email: spacecom@netvision.net.il

http://www.spacecom.co.il/

Program: Amos

Spacecom is a joint venture of Gilat Communication Engineering, Israel Aircraft Industries, General Satellite Services Company and MER Services Group.


Surrey Satellite Technology Limited

(SSTL)

Centre for Satellite Engineering Research, University of Surrey, Guildford, Surrey GU2 5XH, UK

Tel: +44-1483-259143

Fax: +44-1483-259503

http://www.ee.surrey.ac.uk/EE/CSER/UOSAT/

Program: Uosat


Télédiffusion De France

(TDF)

21-27 rue Barbès, 92120 Montrouge, France

Tel: +33-1-4965-1000

Fax: +33-1-4657-4850

Program: TDF


Teledesic

2300 Carillon Point, Kirkland, WA 98033, USA

Tel +1-425-602-0000

Fax: +1-425-602-0001

Email: info@teledesic.com

http://www.teledesic.com

Program: Teledesic


Telenor Satellite Services

P.O.Box 6914, St. Olavs pl., Olso, 0130, Norway

Tel: +47-22-77-79-50

Fax: +47-22-77-79-80

http://www.telenor.com/

Program: Thor


Telesat Canada

1601 Telesat Court, Gloucester K1B 5P4, Ontario, Canada

Tel: +1-613-748-0123

Fax: +1-613-748-8712

Email: info@telesat.ca

http://www.telesat.ca

Program: Anik

Telesat Canada belongs for half to the State and private companies.


Telespazio

Via Alberto Bergamini 50, Roma 00159, Italy

Tel: +39-6-4987-2240

Fax: +39-6-4987-2743

http://www.Telespazio.it

Program: Italsat

On 31 Dec 1993 Telespazio was equally owned by STET, ITALCABLE and RAI. In 1999 it is a Telecom Italia company


Teracom

Agnesfridsvägen 113 C, S-202 50 Malmö, Sweden

Tel: +46-40-14-18-00

Fax: +46-40-14-18-12

info@teracom.se

http://www.teracom.se

Program: Sirius


Thuraya Satellite Telecommunications Co

PO Box 33344, Abu Dhabi, UAE

Tel: +971 2 2084235

Fax: +971 2 330064

thuraya@emirates.net.ae

http://www.thuraya.com/

Program: Thuraya


TMI Communications

P.O. Box 9826, Ottawa, Ontario, K1G 5M2, Canada

Tel: +1-613-742-0000

Fax: +1-613-742-4100

Program: MSAT


TCI Satellite Entertainment, Inc.

(TSAT)

4100 East Dry Creek Road, Littleton, CO 80122, USA

Tel: +1-303-486-3800

Fax: +1-303-486-3891

NASDAQ:TSATA, NASDAQ:TSATB

Program: Tempo


Turk Telekom

Aydinlikevler, Ankara 06103, Turkey

Tel: +90-312-313-15 71

Fax: +90-312-313-15 98

http://www.telekom.gov.tr/

Turksat Earth Station

Golbasi, Ankara 06839, Turkey

Tel: +90-312-555-1000

Fax: +90-312-499-5204

http://www.satcom.gov.tr/

Program: Turksat


United States Satellite Broadcasting

USSB

3415 University Avenue, St Paul, NM 55114, USA

Tel: +1-612-646-5555

Fax: +1-612-642-4103

NASDAQ:USSB

Program: DBS

A division of Hubbard Broadcasting Inc


Worldspace

11 Dupont Circle, N.W., 9th Floor, Washington, DC 20036, USA

Tel: +1-202-884-7800

Fax: +1-202-884-7900

Email: gene@mail.worldspace.com

http://www.worldspace.com

Program: Worldstar

Financial backers: Sheikh Mohammed Hussein Al Amoudi, Khalid Bin Mahfouz


 Platforms

UNDER CONSTRUCTION

Platform	First launch	Number launched	Max. power capacity	Comments
Hughes
HS-376	15 Nov 1980
HS-376W		~40
HS-376L	18 Dec 1993
HS-378
HS-389
HS-601	13 Aug 1992	~33	8700 W	73 ordered
HS-601HP	28 Aug 1997	~7
HS-601MEO	1999?			for ICO, 12 planned
HS-702	1999?		15000 W	10 ordered, first launch should be Galaxy 11
HS-GEM	2000?		13000 W	4 ordered, first launch should be Thuraya


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