Copyright: V0.31.001-XX for Tag's Broadcasting Services
Citation: Copyright ® 1993-1995 Tag's Broadcasting Services


Main index
 The Satellite's Encyclopedia

Alphabetical satellite index

Thematical index

Help: how to use this encyclopedia?


Thematic index
 Thematical index

Country of origin

International launch number

Launch vehicle

Mission

NASA's catalog number

The Clarke Belt

To be launched


 Alphabetical satellite index

A

ACTS

AEM 1

AEM 2

Program: Aeros

Aeros 1

Aeros 2

Program: AFP

AFP 658

AFP 731

Ajisai

Program: Alouette

Alouette 1

Alouette 2

Program: AMPTE

AMPTE CCE

AMPTE IRM

AMPTE UKS

Program: AMS

Program: AMSC

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 2

Program: Arabsat

Arabsat 1A

Arabsat 1B

Arabsat 1C

Arabsat 1D

Arabsat 1E

Program: Argos

Program: Ariel

Ariel 1

Ariel 2

Ariel 3

Ariel 4

Ariel 5

Ariel 6

ARS

Arsène

Aryaghata

Program: ASC

ASC 1

ASC 2

Program: Asiasat

Asiasat 1

Astérix

Program: Astra

Astra 1A

Astra 1B

Astra 1C

Astra 1D

Astrid

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: Aussat

Aussat A1

Aussat A2

Aussat A3

Aussat B1

Aussat B2

Aussat B3

Program: Ayame

Ayame 1

Ayame 2

Azur

B

Badr A

Program: Bhaskara

Bhaskara 1

Bhaskara 2

Program: Brazilsat

Brazilsat A1

Brazilsat A2

Brazilsat B1

Brazilsat B2

Bremsat

Program: BSB

BSB 1

BSB 2

C

Castor

Program: Cat

Cat 1

Cat 2

Cat 3

Cat 4

Program: Chalet

COBE

Program: Comstar

Comstar 1

Comstar 2

Comstar 3

Comstar 4

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 2177

Cosmos 2178

Cosmos 2179

Cosmos 2204

Cosmos 2205

Cosmos 2206

Cosmos 2209

Cosmos 2219

Cosmos 2220

Cosmos 2221

Cosmos 2222

Cosmos 2223

Cosmos 2224

Cosmos 2234

Cosmos 2235

Cosmos 2236

Cosmos 2245

Cosmos 2246

Cosmos 2247

Cosmos 2248

Cosmos 2249

Cosmos 2250

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

Courier 1B

CTA

CTS

D

Program: Dash

Program: DBS

DBS 1

DBS 2

Delta

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 B5D2-8

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

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 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

Program: DSP

DSP F12

DSP F13

DSP F14

DSP F15

DSP 3-4

DSP 3-5

Dynamics Explorer 1

Dynamics Explorer 2

E

Program: Echo

Echo 1

Echo 2

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

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

Eureca 1

Program: Eutelsat

Eutelsat 1F1

Eutelsat 1F2

Eutelsat 1F3

Eutelsat 1F4

Eutelsat 1F5

Eutelsat 2F1

Eutelsat 2F2

Eutelsat 2F3

Eutelsat 2F4

Eutelsat 2F5

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 01

Eyesat

F

Faisat

Firewheel

Program: Fleetsatcom

Fleetsatcom 1

Fleetsatcom 2

Fleetsatcom 3

Fleetsatcom 4

Fleetsatcom 5

Fleetsatcom 6

Fleetsatcom 7

Fleetsatcom 8

Program: Foton

Foton 09

Foton 10

FR 1

Freja

Program: Fuji

Fuji 1A

Fuji 1B

G

Program: Galaxy

Galaxy 1

Galaxy 1R

Galaxy 1R failure

Galaxy 2

Galaxy 3

Galaxy 4

Galaxy 5

Galaxy 6

Galaxy 7

Program: GALS

GALS 1

Gamma

GEO-IK

Geos 3

Geotail

GFZ 1

Program: GGSE

GGSE 1

GGSE 2

GGSE 3

GGSE 4

GGSE 5

Program: Glonass

Program: GMS

GMS 1

GMS 2

GMS 3

GMS 4

GMS 5

Program: Goes

Goes 1

Goes 2

Goes 3

Goes 4

Goes 5

Goes 6

Goes 7

Goes 8

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

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

Granat

GRO

Program: Gstar

Gstar 1

Gstar 2

Gstar 3

Gstar 4

Gurwin 1

H

Healthsat

Program: Heoa

Heao 1

Heao 2

Heao 3

Program: Heos

Heos 1

Heos 2

Hipparcos

Program: Hispasat

Hispasat 1A

Hispasat 1B

Hiten

Hotbird 1

HST

I

Program: IDSCP

Program: IMEWS

Informator

Injun 3

Program: Inmarsat

Inmarsat 2F1

Inmarsat 2F2

Inmarsat 2F3

Inmarsat 2F4

Program: Insat

Insat 1A

Insat 1B

Insat 1C

Insat 1D

Insat 2A

Insat 2B

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 K

Program: Intercosmos

Intercosmos 01

Intercosmos 18

Intercosmos Bulgaria 1300

Program: Intersputnik

IRAS

Program: IRS

IRS 1A

IRS 1B

IRS P2

Program: ISEE

ISEE 1

ISEE 2

Program: Isis

Isis 1

Isis 2

Program: Italsat

Italsat 1

Itamsat

Itos

IUE

J

Program: JCSAT

JCSAT 1

JCSAT 2

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 11-6

KH 12-1

Program: Kitsat

Kitsat A

Kitsat B

Koronas 1

L

Program: Lacrosse

Program: Lageos

Lageos 1

Lageos 2

Program: Landsat

Landsat 1

Landsat 2

Landsat 3

Landsat 4

Landsat 5

Landsat 6

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

Luch

Lusat

M

Program: Magion

Magion 1

Magion 2

Magion 3

Magsat

Program: Marecs

Marecs A

Marecs B1

Marecs B2

Program: Marisat

Marisat 1

Marisat 2

Marisat 3

Program: Meteor

Meteor 1-01

Meteor 1-02

Meteor 2-01

Meteor 3-03

Meteor 3-05

Meteor 3-06

Program: Meteosat

Meteosat 1

Meteosat 2

Meteosat 3

Meteosat 4

Meteosat 5

Meteosat 6

Microlab 1

Program: Midas

Midas 2

Midas 3

Midas 4

Midas 5

Midas 6

Midas 7

Midas 8

Midas 9

Miranda

Program: Molnya

Molnya 1-01

Molnya 1-71

Molnya 1-72

Molnya 1-74

Molnya 1-86

Molnya 1-88

Molnya 2-01

Molnya 3-01

Molnya 3-34

Molnya 3-35

Molnya 3-36

Molnya 3-37

Molnya 3-42

Molnya 3-46

Molnya 1-S

Program: Momo

Momo 1A

Momo 1B

Program: Morelos

Morelos 1

Morelos 2

MSTI 1

MSTI 2

Myojo

N

Program: Nadejda

Nadejda 1

Nadejda 2

Nadejda 3

Nadejda 4

Program: NATO

Nato 1

Nato 2

Nato 3A

Nato 3B

Nato 3C

Nato 3D

Nato 4A

Nato 4B

Program: Nimbus

Nimbus 1

Nimbus 2

Nimbus 3

Nimbus 4

Nimbus 5

Nimbus 6

Nimbus 7

Program: NOAA

NOAA 01

NOAA 02

NOAA 03

NOAA 04

NOAA 05

NOAA 06

NOAA 07

NOAA 07C

NOAA 08

NOAA 09

NOAA 10

NOAA 11

NOAA 12

NOAA 13

NOAA 14

Program: Nova

Nova 1

Nova 2

Nova 3

O

Program: OAO

OAO 1

OAO 2

OAO 3

OAO 4

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

OFO

Program: OGO

OGO 1

OGO 2

OGO 3

OGO 4

OGO 5

OGO 6

Program: Okean

Okean 1

Okean 2

Okean 3

Okean O1

Olympus

Program: Orbcomm

Orbcomm X

Orbcomm XP 1

Orbcomm FM 1

Orbcomm FM 2

Program: Orion

Orion 1

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

Oshumi

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

Program: Panamsat

Panamsat 1

Panamsat 2

Panamsat 3

Program: Pegasus

Pegasus 1

Pegasus 2

Pegasus 3

Pegsat

Péole

Polaire

Pollux

Posat

Program: Prognoz

Prognoz 01

Prognoz 02

Prognoz 03

Prognoz 04

Prognoz 05

Prognoz 06

Prognoz 07

Prognoz 08

Prognoz 09

Prospero

Program: Proton

Proton 1

Proton 2

Proton 3

Proton 4

R

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 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

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 500

Resurs O1-3

Program: Rohini

Rohini 1B

Rohini 2

Rohini 3

Rosat

RS 15

Ryusei

S

S80T

Program: Safir

Program: Sakura

Sakura 1

Sakura 2A

Sakura 2B

Sakura 3A

Sakura 3B

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

Program: SBS

SBS 1

SBS 2

SBS 3

SBS 4

SBS 5

SBS 6

SCD

Score

Seasat

Program: Secor

Secor 01B

Secor 02

Secor 03

Secor 04

Secor 05

Secor 06

Secor 07

Secor 08

Secor 09

Secor 13

SFU

Shinsei

Signe 3

Program: Sirio

Sirio 1

Sirio 2

Sirius

Program: Skynet

Skynet 1A

Skynet 1B

Skynet 2A

Skynet 2B

Skynet 4A

Skynet 4B

Skynet 4C

SMM

Program: SMS

SMS 1

SMS 2

SME

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 201-1

Spartan 201-2

Spartan 201-3

Spartan 201-4

Program: Spas

Spas 1

Spas 1A

Spas 2

Spas 3

Spas 4

Program: Spot

Spot 1

Spot 2

Spot 3

Program: Sputnik

Sputnik 01

Sputnik 02

Sputnik 03

Sputnik 04

Sputnik 05

Sputnik 06

Sputnik 07

Sputnik 09

Sputnik 10

Program: Sret

Sret 1

Sret 2

Program: Sross

Sross 1

Sross 2

Sross 3

Sross C2

Starlette

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

STEP 2

Program: STRV

STRV 1A

STRV 1B

Program: Superbird

Superbird A1

Superbird A2

Superbird B1

Superbird D

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

TELE X

Program: Telecom

Telecom 1A

Telecom 1B

Telecom 1C

Telecom 2A

Telecom 2B

Program: Telstar

Telstar 1

Telstar 2

Telstar 301

Telstar 302

Telstar 303

Telstar 401

Telstar 402

Temisat

Program: Thaicom

Thaicom 1

Thaicom 2

Thor

Program: Tiros

Tiros 01

Tiros 02

Tiros 03

Tiros 04

Tiros 05

Tiros 06

Tiros 07

Tiros 08

Tiros 09

Tiros 10

Topex Poseidon

Tournesol

Traac

Program: Transit

Transit 2A

Transit 4A

Transit 4B

Transit 5BN1

Transit 5BN2

TTS

Program: Tubsat

Tubsat A

Tubsat B

Program: Turksat

Turksat 1A

Turksat 1B

Program: Tvsat

Tvsat 1

Tvsat 2

U

UARS

Program: UHF

UHF 1

UHF 2

UHF 3

UHF 4

Ume 1

Ume 2

Unamsat 1

Program: Uosat

Uosat 1

Uosat 2

Uosat 3

Uosat 4

Uosat 5

Program: USA

V

Program: Vanguard

Vanguard 1

Vanguard 2

Vanguard 3

Vela

Viking

W

Webersat

Program: Westar

Westar 1

Westar 2

Westar 3

Westar 4

Westar 5

Westar 6

Dial-Wika

Wind 1

Wresat

Y

Program: Yuri

Yuri 1

Yuri 2A

Yuri 2B

Yuri 2X

Yuri 3A

Yuri 3B

Yuri 3N


 NASA's catalog number

Each object in space is tracked by NASA. Therefore every object is identified by a number you'll find in the General section of the satellite's data.

To search a satellite by its catalog number, call the search tool and enter "CATNR " followed by that number.


 International launch number

Each launch is identified by NASA (US Space Command). This 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 launched. Thus number 91026 means the 26th launch in 1991.

To search for a launch by its number, call the search tool and enter "LAUNR " followed by that number.

Last launches

1995

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	Brazilsat B2

95___	28 Mar	Gurwin 1

95___	28 Mar	Unamsat 1

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

95015A	24 Mar	DMSP B5D2-9

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 201-4

95004A	03 Feb	STS 63

95003A	29 Jan	UHF 4

95002C	24 Jan	Faisat

95002B	24 Jan	Astrid

95002A	24 Jan	Tsikada (was previously part of Cosmos?)

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

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

94081A	14 Dec	Molnya 1-88

94080A	29 Nov	Dong Fang Hong 41

94079A	29 Nov	Orion 1

94078A	24 Nov	GEO-IK

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 01

94066A	11 Oct	Okean O1

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 201-3

94059A	09 Sep	STS 64

94058A	09 Sep	Telstar 402

94057A	29 Aug	USA 106

94056A	28 Aug	ETS 6

94055A	27 Aug	Aussat B3

94054A	27 Aug	USA 105

94053A	26 Aug	Cosmos 2290

94052A	25 Aug	Progress M-24

94051A	23 Aug	Molnya 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	Brazilsat 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	Nadejda 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


 Tag's Broadcasting Services

This file is shareware, belongs to Tag (Jean­Philippe Donnio), © all rights reserved, 1993­1995.

Section en français

Also to be read:

License Agreement

Bibliography reference

Acknowledgment

Versions

Help: how to use this encyclopedia?

Philosophy of this encyclopedia

I expect this encyclopedia to be widely distributed to get in touch with people having missing information. It would be kind of you to help me to complete it.

I intend to release a new version every 3 months or so. Therefore this software is not a final version and I need your help to continue. Don't hesitate to contact me.

If you are any kind of satellite specialist, satellite operator or constructor, or a space organization I would be very glad to get in touch with you. If for some reason you feel I am not treating your organization's satellites correctly, understand I only take notice of the data I have. If you want a better coverage please consider sending me directly data.

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

Pass this encyclopedia around: the more people it'll reach, the larger it'll grow!

The fair play

This file is shareware: you can use it on a trial basis during SEVEN days. Because of distribution problems this version has been limited to fit on a 3.5" floppy. Thus numerous EIRP maps are not included so as the Cosmos program. That's why you get an error when clicking on those items.

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

The full > 3.5 MB help file with:

140 EIRP maps

a listing of satellites on the Clarke Belt

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

Turn to the license agreement for more details. I also ask you, to provide me with the data you may have that is not in this encyclopedia.

In any case, this file remains my property. No reverse engineering.

Providing data

I need:

Your name or alias (that will be quoted in the acknowledgment section)

Your postal address (and electronic if you have any)

The information with it's precise origin & date

The version of the encyclopedia you currently use

You will be thanked with the latest version of the encyclopedia.

Who am I and how to contact me?

I am a 21 year old student currently preparing a Bachlor's degree of computer science and telecommunications (I should pass it in June 95). I might go on studying if I find something worth it... I'd like to learn more about computer networks and multimedia applications, you know building the real data highways! I speak French (!), English quite fluently and I understand German…

Apart from space related topics I am a Rave music lover.

Jean­Philippe Donnio

Tag's Broadcasting Services

16 rue du bourg Saint­Jean

F-41000 Blois

France

jpdonnio@dialup.francenet.fr

jp donnio @ Fidonet 2:321/1

Please mention the version of the encyclopedia you currently use.

How to obtain the latest release?

1°/ By registering: see the license agreement

2°/ By downloading:

Canada Dry BBS: +33-4729-3385 (28.8 kbps) or FREQ "SATELLITE" @ 2:321/1

CIS: go WSHARE in the "Loisirs et Jeux" zone

Internet: http://xan.esrin.esa.it:2602/msdos/

3°/ Via any good shareware dealer


 License Agreement

Please feel free to upload this software to any electronic bulletin board, demonstrate the software and its capabilities or give copies to potential users, so that others may have the opportunity to obtain a copy for use in accordance with the license terms contained in this file.

Credit Card order form (with invoice)

Alternative order form (no invoice)

License Agreement

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

The Satellite's Encyclopedia is copyrighted material. It is protected by the copyright laws. You may not make any changes or modifications to The Satellite's Encyclopedia. You may not decompile, disassemble, or otherwise reverse-engineer the software in any way.

You may use The Satellite's 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's Encyclopedia further on or for COMMERCIAL PURPOSES, you must purchase a license for its use.

How much is a license:

A license is FRF 100. This license is effective for one year from the date of your registration.

You will receive a personal most updated version which includes:

The full > 3.5 MB help file with:

140 EIRP maps

a listing of satellites on the Clarke Belt

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

You may get a license with the subscription option which provides you updates during a whole year. This license + subscription is FRF 200.

Those are basic prices. Exact prices depend on your payment mean. See the order forms at the top of this topic.

Special offers:

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

Please note I reserve myself the right to refuse your application.

Title to the licensed software is not transferred to the end user. The end-user is granted an 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.

Limited Warranty

I do not warrant that the licensed software will meet your requirements or that the software and data will be error-free. The software warranty does not cover any copy of the licensed software which has been altered or changed in any way.

I 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 me responsible for any problems arising from the use of the software.

I 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 I have been advised of the possibility of such damages.

In no case shall my 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's Encyclopedia's Distribution

The Satellite's 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 my express written permission.

Public Domain disk vendors may not charge a fee for The Satellite's Encyclopedia itself. However you may include The Satellite's 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 me a free copy of this CD-ROM. The purchaser of said media must be informed in advance that the fee paid to acquire the diskette does not relieve said purchaser from paying the registration fee for The Satellite's Encyclopedia if said purchaser uses The Satellite's Encyclopedia.

Operators of electronic Bulletin Board Systems (sysops) may post The Satellite's 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's Encyclopedia files without first obtaining express written permission from myself 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's Encyclopedia.

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


Order form
 Credit card order form

FROM:

      Name: ______________________________________________________

 [Company]: ______________________________________________________

  Reg Name: ______________________________________________________

            [Used to register your software, 30 characters max]

   Address: ______________________________________________________

      City: ____________________________ State: __________________

   Country: ____________________________ Postal Code: ____________

     Phone: ________________________ Fax: ________________________

     Email: ______________________________________________________

SIMPLE REGISTRATION for the use of The Satellite's Encyclopedia

at FRF 100+80 each.....................................___x 180   ______

REGISTRATION & SUBSCRIPTION for updates during 1 year

at FRF 200+80 each.....................................___x 280   ______

TOTAL FRF......................................................   ______

Credit card Payment (Visa/MasterCard):

    Number: ________________________________

Expiration: __________

      Date: ________________________________

Authorized signature: __________________________________________________

SEND TO:

            WindowShare SARL

            B.P. 2078

            57051-METZ cedex 2

            FRANCE

            VOX: +33-8730-8557

            FAX: +33-8732-3775

            CIS: 100031,3257

WindowShare will send you an invoice including VAT

V0.31.001


 Alternative order form

FROM:

      Name: ______________________________________________________

 [Company]: ______________________________________________________

  Reg Name: ______________________________________________________

            [Used to register your software, 30 characters max]

   Address: ______________________________________________________

      City: ____________________________ State: __________________

   Country: ____________________________ Postal Code: ____________

     Phone: ________________________ Fax: ________________________

     Email: ______________________________________________________

SIMPLE REGISTRATION for the use of The Satellite's Encyclopedia

at FRF 100 each........................................___x 100   ______

REGISTRATION & SUBSCRIPTION for updates during 1 year

at FRF 200 each........................................___x 200   ______

TOTAL..........................................................   ______

Payment:

( ) Check (payable to Jean-Philippe Donnio)

    If not payable through a French bank (Eurocheque) add 20%     ______

                                             TOTAL FRF ENCLOSED   ______

Date: ________________________________

Authorized signature: __________________________________________________

SEND TO:

            Jean-Philippe Donnio

            Tag's Broadcasting Services

            16 rue du bourg Saint-Jean

            F-41000 BLOIS

            FRANCE

V0.31.001


 Bibliography

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

L'état des sciences et des techniques (Fr)

Sous la direction de Nicolas Witkowski

La découverte, 1991

ISBN 2-7071-2069-3

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

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

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

Edition 91/92

Media Presse Information (MPI), 1991

ISBN 2-9505754-0-4

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

Infosat (Ger)

ISSN 0933-6907

Megahertz Magazine (Fr)

ISSN 0755-4419

Revue des Télécoms (Fr)

ISSN 0183-8636

Satellites Infos (Fr)

ISSN n/a

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>

M (Eng)

From M2 Communications Limited <m@m2.com>

MediaScan (Eng)

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

no title (Eng)

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

Satellite Journal International (Eng)

Contact: <gtorrens@tenet.edu>

Skyguide (Eng)

By Antony Purvis <bignoise@cix.compulink.co.uk>

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>

TS-ND: TELE-satellit News Desk (Ger)

By Peter C. Klanowski <100103.1341@compuserve.com>

TELE-satellit News (Eng)

By Martyn Williams <martyn@euro.demon.co.uk>

Transponder (Eng)

Contact: <editor@trponder.win-uk.net>


Acknolegdment
 Acknowledgment

In this section I want to thank all those who collaborated to improve The Satellite's Encyclopedia. Thank you very much... and I expect to see your name here soon!!!

Special thanks

Bart Kuperus

Bart Kuperus is the author of the WRTH Satellite Broadcasting Guide, a handbook full of valuable data. It starts with a comprehensive introduction to satellite TV including everything you need to know to install your own reception station. It includes EIRP maps of numerous well-known satellites and a frequency guide of almost every geostationary bird. Also features a guide to US DBS. If you are a satellite freak, you ought to have this book. See the bibliography for complete reference.

Satellite TV Club

A French club that promotes satellite TV and organizes a yearly satellite event in May. It gathers amateurs and specialists. The club compiles a weekly program chart devoted to language study via Astra, very useful to teachers (available in alt.satellite.tv.europe). Maintains the Minitel 3615 SATTV service. For further details contact: Satellite TV Club, Place de Mons, F-33360 CENAC

TELE-satellit

A monthly satellite magazine edited in Munich, Germany. It consists of 192 pages, full color with tables, charts and news with many off-screen photos of the satellite channels plus an informative technical section. Simply the best! For further details about TELE-satellit ask for a sample copy at: TELE-satellit customer service, Silheimerstr. 6a, D-89278 Nersingen, Fax +49-7308-919001, CompuServe 100543,660. A 12-issue subscription (=1 year) costs approx. 90 US-Dollar within Europe or 120 US-Dollar outside Europe (airmail included).

Data providers

Date	Provider	Description
Apr 1995	Curt Swinehart <cswineha@emerald.tufts.edu>	Satellite operators information sheet
Apr 1995	Anna Laurin <aln@ssc.se>  and Olle Norberg <Olle.Norberg@irf.se>	Astrid info
Mar 1995	Stuart A. MacMillan	Info on Telesat Canada's satellites
Mar 1995 on	Jonathan McDowell <jmcdowell@cfa.harvard.edu>	JSR info feed and support answering my numerous questions
24 Feb 1995	Daniel Audeon	Astronautique 1, a database he built containing astronauts and manned launches.
Feb 1995 on	Dr TS Kelso Adjunct Professor of Space Operations <tkelso@afit.af.mil>	Provides me with elements from the Air Force Institute of Technology database
24 Nov 1994	Jean-Claude Durand Club Européen de DX Radio TV	Payload of flights 40-44, 46-56, 58-63, 65-70 of Ariane
25 Jul 1994	Franck Nony	Matra Marconi Space European Spacecraft Directory 1992
23 Jul 1994	Satellite TV Club	Documentation on Loutch, Coupon, Rimsat, Gorizont 17, Astra, Thor, Panamsat, Orion, etc. satellites
23 Jul 1994	Pierre A. Sicart	Matra Marconi Space Earth Observation Directory 1993/94 Matra Marconi Space World Spacecraft Directory 1993/94
5 Jul 1994	Robert Smathers <roberts@nmia.com>	Enabled me to include data from his South Scanner Satellite Services Chart
Bugs hunters

Romain Guesdon <romain.guesdon@p6.f10.n322.z2.fidonet.org>

Nemo

Philippe Plumecocq <? @compuserve.com>

Progfou <progfou@mycrob.cafard.freenix.fr>


 Versions

Version	Release date	Comments
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
0.06.002	6 Mar 1994	Minor modifications
0.06.001	7 Feb 1994	Modification of the maps Bug correction
0.05.001	17 Jan 1994	License agreement, first public release


 How to use this encyclopedia?

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

Glossary

What's hypertext?

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 ask it differently.

You also can search through indexes.


 Tag's Broadcasting Services

Ce fichier est un shareware qui appartient à Tag (Jean­Philippe Donnio), © tous droits réservés, 1993­1995.

Ce document fut nommé second meilleur shareware français 95 catégorie Home and Hobby par Ziff Davis.

A lire également :

Licence d'utilisation

Philosophie de cette encyclopédie

J'espère que cette encyclopédie sera suffisamment diffusée pour rentrer en contact avec des personnes possédant des informations manquantes. Il serait aimable à vous de m'aider à la compléter.

J'ai l'intention de sortir une nouvelle version tous les 3 mois. Ce logiciel n'est donc pas une version finale et j'ai besoin de vous pour continuer. N'hésitez donc pas à me contacter.

Si vous êtes un spécialiste du satellite, un opérateur ou un constructeur satellite, une organisation spatiale, je serai 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 je ne travaille qu'avec les informations que j'ai entre les mains. Si vous voulez améliorer les choses, envoyez moi simplement 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 mon offre spéciale dans la licence.

Diffusez cette encyclopédie autour de vous : plus elle touchera de monde, plus elle aura de chances de s'enrichir !

La règle du jeu

Ce logiciel est en libre essai, c'est un shareware : vous pouvez donc l'essayer gratuitement pendant SEPT jours. A cause de problèmes de distribution cette version a été tronquée 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's Encyclopedia après la période d'essai ou à des fins commerciales, vous DEVEZ vous enregistrer. La version enregistrée comprend:

Le fichier complet (> 3,5 Mo) avec :

140 cartes PIRE

la liste des satellites sur l'orbite de Clarke

un calendrier des lancements futurs et des satellites concernés

Reportez vous à la licence pour en savoir plus. D'autre part je vous demande de me faire parvenir les informations dont vous disposez et qui ne sont pas dans cette encyclopédie.

Dans tous les cas, ce fichier reste ma propriété. Pas de décompilation, merci.

Comment apporter des compléments ?

Pour cela, fournissez :

Votre nom et prénom ou pseudo (qui seront cités dans la section des remerciements)

Votre adresse postale (et électronique si vous en avez une)

L'information avec sa source et date

La version de l'encyclopédie dont vous disposez actuellement

Je vous remercierai en vous envoyant la prochaine version de l'encyclopédie.

Qui suis-je et comment me contacter ?

Je suis un étudiant de 21 ans préparant une Maîtrise Science et Technique en informatique et télécommunications (que je devrais avoir en juin 95). Je poursuivrai peut être mes études si je trouve quelque chose de valable à faire... J'aimerai en apprendre plus sur les réseaux informatiques et leurs applications aux médias, bref construite les autoroutes de l'information ! Je parle français (!), anglais couramment et je me débrouille en allemand...

Mis à part les satellites et tout ce qui s'y rapporte, je suis un fan de Rave music.

Jean­Philippe Donnio

Tag's Broadcasting Services

16 rue du bourg Saint­Jean

F-41000 Blois

France

jpdonnio@dialup.francenet.fr

jp donnio @ Fidonet 2:321/1

SVP : précisez la version de l'encyclopédie dont vous disposez actuellement.

Comment vous procurer la dernière version disponible ?

1°/ En vous enregistrant : voir la licence.

2°/ En la téléchargeant :

Canada Dry BBS : +33-4729-3385 (28,8 kbps) ou FREQ "SATELLITE" @ 2:321/1

CIS : go WSHARE dans la zone "Loisirs et Jeux"

Internet: http://xan.esrin.esa.it:2602/msdos/

3°/ Par l'intermédiaire d'un distributeur de shareware (WindowShare)


 Licence d'utilisation

N'hésitez pas à déposer ce logiciel sur des serveurs ou BBS, à faire état de ces capacités et à en donner des copies à des utilisateurs potentiels, pour que d'autres aient la possibilité d'obtenir une copie pour utilisation conformément à la présente licence d'utilisation.

Bon de commande (sans facture)

Bon de commande WindowShare (avec facture)

Licence

L'utilisation de The Satellite's Encyclopedia est soumise aux termes et conditions suivantes :

The Satellite's Encyclopedia est protégée par les lois sur les droits d'auteurs. Vous ne devez faire aucun changement ou modification à The Satellite's Encyclopedia. Vous ne devez pas la décompiler, la désassembler, ou lui appliquer toute autre rétrotechnique.

Vous pouvez utiliser The Satellite's Encyclopedia pour une période d'essai à condition de ne pas violer la protection que lui procure les lois sur les logiciels, et d'accepter les termes de cette licence. Vous avez le droit d'évaluer gratuitement ce logiciel pendant sept jours. Si vous utilisez The Satellite's Encyclopedia par la suite ou à des FINS COMMERCIALES, vous DEVEZ acquérir une licence d'utilisation.

Combien coûte une licence ?

Une licence coûte 100 F. Cette licence est valable pendant un an à compter de la date d'enregistrement. L'utilisateur enregistré recevra un version personnelle du logiciel avec :

Le fichier complet (> 3,5 Mo) avec :

140 cartes PIRE

la liste des satellites sur l'orbite de Clarke

un calendrier des lancements futurs et des satellites concernés

Vous pouvez opter pour une licence avec abonnement au service de mise à jour pendant 1 an. Cela vous coûtera 200 F.

Ces prix sont de base. Le prix exact dépend de votre moyen de paiement. Lisez les bons de commande en haut de cette section.

Offre spéciale:

Si vous êtes une société qui publie un périodique papier ou électronique concernant les satellites (en Français, Anglais ou Allemand), vous pouvez obtenir gratuitement une licence d'utilisation avec mise à jour pendant un an contre un abonnement gratuit d'un an à votre publication.

Si vous êtes l'auteur d'un livre concernant les satellites (en Français, Anglais ou Allemand), vous pouvez obtenir gratuitement une licence d'utilisation avec mise à jour pendant 1 an contre un exemplaire gratuit de votre livre.

Si vous êtes l'auteur d'un shareware concernant les satellites (en Français, Anglais ou Allemand), vous pouvez obtenir gratuitement une licence d'utilisation avec mise à jour pendant 1 an contre une licence d'utilisation gratuite de votre shareware.

Je me réserve toutefois le droit de refuser votre demande.

L'utilisateur final ne se voit pas accorder le titre de propriété du logiciel sous licence. On lui fournit une licence exclusive pour utiliser, à tous moments, le logiciel sur un unique ordinateur ou station de travail. De plus, il s'engage à ne dupliquer ce logiciel que pour en faire une sauvegarde.

Garantie

Je ne garantie pas que le logiciel sous licence répondra à vos attentes ou que le logiciel comme les informations seront sans erreurs. La garantie ne couvre aucune copie du logiciel altérée ou modifiée.

Je ne suis pas responsable des problèmes ou dommages causés par le logiciel sous licence qui pourrait résulter de son utilisation. Ceci comprend, mais ne se limite pas au matériel informatique, logiciel informatique, système d'exploitation, et autre accessoire informatique. L'utilisateur final s'engage à me reconnaître irresponsable de problèmes dus à l'utilisation du logiciel.

Je ne serai en aucun cas tenu des dommages-intérêts particuliers, accidentels, conséquents, indirects ou similaires provenant d'une quelconque rupture de ces garanties même si j'ai été prévenu de la possibilité de tels dommages-intérêts.

Ma responsabilité ne pourra en aucun cas excéder le montant de la licence payée en contre partie de l'utilisation du logiciel sous licence.

Dans le cas où quelque disposition de cette licence serait invalide, les parties s'accordent que cette invalidité n'affectera pas la validité du reste des dispositions de cette licence.

Distribution de The Satellite's Encyclopedia

The Satellite's Encyclopedia doit être copiée sans modifications et doit contenir tous les fichiers nécessaires à son installation automatique. Aucune taxe, frais ou autre compensation ne doit être acceptée ou demandée par personne sans mon accord écrit exprès.

Les vendeurs de disques du Domaine Public ne peuvent pas facturer une taxe pour The Satellite's Encyclopedia en elle-même. Toutefois, vous pouvez inclure The Satellite's Encyclopedia sur une disquette ou CD-ROM pour laquelle vous facturez un montant nominal de distribution. Si vous diffuser ce shareware sur un CD-ROM vous devez m'en envoyer une copie gratuitement. L'acquéreur du dit support doit être informé à l'avance que la somme versée pour obtenir le support ne relève pas ledit acquéreur de payer les droits d'utilisation de The Satellite's Encyclopedia si l'utilisateur l'utilise.

Les opérateurs des serveurs et BBS (les sysops) peuvent mettre The Satellite's Encyclopedia à la disposition de leurs utilisateurs sans permission écrite tant qu'ils respectent les conditions ci-dessus. Une redevance peut être perçue pour accéder au système mais aucune taxe spécifique ne peut être facturée pour le téléchargement des fichiers de The Satellite's Encyclopedia sans l'obtention préalable de mon accord écrit exprès pour facturer une telle somme. Ceci s'applique également à Internet et Compuserve; les autres systèmes en ligne doivent demander une autorisation. En ce qui concerne le Minitel, les fournisseurs de service NE sont PAS autorisés à mettre The Satellite's Encyclopedia en ligne.

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


 Countries of origin

Statistics (partly from NASA, Jan 1995)

	Objects in orbit	Decayed objects
	Payload	Debris	Total	Payload	Debris	Total
Argentina	1	0	1	0	0	0
Australia	7	2	9	1	1	2
Brazil	5	0	5	0	0	0
Bulgaria	1	1	2	0	0	0
Canada	16	0	16	1	0	1
China	15	92	107	24	81	105
CIS	1322	2491	3813	1626	9677	11303
Czechoslovakia	1	0	1	1	0	1
France	25	19	44	7	59	66
Germany	15	2	17	6	5	11
Hong Kong	1	0	1	0	0	0
India	10	3	13	6	8	14
Indonesia	6	0	6	1	1	2
Israel	0	0	0	2	2	4
Italy	4	0	4	5	0	5
Japan	53	50	103	10	76	86
Korea (South)	2	0	2	0	0	0
Luxemburg	4	2	6	0	0	0
Mexico	4	0	4	0	0	0
Netherlands	0	0	0	1	3	4
Pakistan	0	0	0	1	0	1
Portugal	1	0	1	0	0	0
Spain	3	0	3	0	0	0
Sweden	4	0	4	0	0	0
Thailand	2	0	2	0	0	0
Turkey	1	0	1	0	0	0
United Kingdom	18	1	19	8	4	12
United States	650	2805	3455	660	2890	3550
Arab States	3	0	3	0	0	0
Europe	25	155	180	11	458	469
International	46	0	46	1	0	1
NATO	8	2	10	0	0	0
Column	2253	5625	7878	2372	13265	15637
Total						23515


Countries of origin

Countries

Argentina Australia Brazil Bulgaria Canada CIS China Czechoslovakia France Germany	Hong Kong India Indonesia Israel Italy Japan Korea (South) Luxemburg Mexico Netherlands	Norway Pakistan Portugal Spain Sweden Thailand Turkey United Kingdom United States
Organizations

Arab States Europe (ESA)	International NATO


 Argentina

Satellite launched

1990

Lusat


 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

Aussat A1

Aussat A2

1987

Aussat A3

1992

Aussat B1

Aussat B2

1994

Aussat B3

Main program

Aussat


 Brazil

The national research center INPE was created on 3 Aug 1961.

Satellites launched

1985

Brazilsat A1 (SBTS A1)

1986

Brazilsat A2 (SBTS A2)

1990

Dove

1993

SCD

1994

Brazilsat B1 (SBTS B1)

1995

Brazilsat B2 (SBTS B2)

Main program

Brazilsat


 Bulgaria

Bulgaria launched a satellite with the help of the CIS.

Satellite launched

1981

Intercosmos Bulgaria 1300


 Canada

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

Canada is member of ESA since 1978 and created the Canadian Space Agency on 1 Mar 1989.

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

Main programs

Alouette

Anik

Isis


 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 to launch foreign satellites.

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

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

Dong Fang Hong 38 (Shijian 4)

Dong Fang Hong 39 (Shijian 4-2)

Dong Fang Hong 40 (FSW 2)

Dong Fang Hong 41

Main programs

Dong Fang Hong


 CIS

CIS has a very complex space organization that I can't describe here for the moment.

Main programs

Cosmos

Ekran

Elektron

Express

Foton

GALS

Glonass

Gorizont

Intercosmos

Meteor

Molnya

Nadejda

Okean

Prognoz

Proton

Raduga

Resurs

Sputnik

Statsionar


 Czechoslovakia

Developed a scientific program with the CIS.

Satellites launched

1978

Magion 1

1989

Magion 2

1991

Magion 3

Main program

Magion


 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.

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

Main programs

Argos

Auréole

Spot

Sret

Symphonie

TDF

Telecom


 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.

Between 1964 and 1975 European project were not very successful (Europa, Europa 2...).

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

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

Main programs

Aeros

DFS Kopernikus

Safir

Symphonie

Tubsat

Tvsat


 Hong Kong

Satellites launched

1990

Asiasat 1

1994

Apstar 1

Main program

Apstar


 India

Indian space agency is the ISRO (Indian Space Research Organisation) created in 1969.

Satellites launched

1975

Aryaghata

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

IRS P2

Main programs

Bhaskara

Insat

IRS

Rohini

Sross


 Indonesia

Satellites launched

1976

Palapa A1

1977

Palapa A2

1983

Palapa B1

1987

Palapa B2P

1990

Palapa B2R

1992

Palapa B4

Main program

Palapa


 Israel

Israel has a space agency since 1983

Satellites launched

1988

Offek 1

1990

Offek 2

1995

Offek 3

Main program

Offek


 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).

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

1992

Temisat

1993

Itamsat

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).

Satellites launched

1970

Oshumi

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)

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

Main programs

Astro

Ayame

ETS

Fuji

GMS

Jcsat

Momo

Sakura

Superbird

Tansei

Yuri


 Korea (South)

Satellites launched

1992

Kitsat A

1993

Kitsat B

Main program

Kitsat


 Luxemburg

Satellites launched

1988

Astra 1A

1991

Astra 1B

1993

Astra 1C

1994

Astra 1D

Main program

Astra


 Mexico

Satellites launched

1985

Morelos 1

Morelos 2

1993

Solidaridad 1

1994

Solidaridad 2

Main programs

Morelos

Solidaridad


 Netherlands

Member of ESA

Satellites launched

1974

ANS

1974

IRAS


 Norway

Member of ESA since 1987.

Satellite bought in orbit

1992

Thor


 Pakistan

Satellite launched

1990

Badr A


 Portugal

Satellite launched

1993

Posat


 Spain

Spain is part of ESA.

Satellites launched

1974

Intasat

1992

Hispasat 1A

1993

Hispasat 1B

Main program

Hispasat


 Sweden

Member of ESA

Satellites launched

1986

Viking

1989

Tele X

1992

Freja

1994

Sirius (bought in orbit)

1995

Astrid


 Thailand

Satellite launched

1993

Thaicom 1

1994

Thaicom 2

Main program

Thaicom


 Turkey

Satellite launched

1994

Turksat 1B

Main program

Turksat


 United Kingdom

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

Satellites launched

1962

Ariel 1 (UK 1)

1964

Ariel 2 (UK 2)

1967

Ariel 3 (UK 3)

1969

Skynet 1A

1971

Skynet 1B

Prospero

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

Main programs

Ariel

BSB

Skynet

STRV

Uosat


 United States

A whole book could be devoted to the United States...

Main programs

AFP

AMS

AMSC

Argos

ASC

ATS

Aurora

Chalet

Comstar

Dash

DBS

Discoverer

DMSP

DSCS

DSP

Echo

Essa

Explorer

Fleetsatcom

Galaxy

GGSE

Goes

GPS

Gstar

Heao

IDSCP

IMEWS

KH

Lacrosse

Lageos

Landsat

LCS

Leasat

LES

Marisat

Midas

Nimbus

NOAA

Nova

OAO

Oderacs

OGO

Orbcomm

Orion

OSO

OV

Panamsat

Pegasus

Relay

Satcom

Discoverer

SBS

Secor

SMS

Solrad

Spacenet

Spartan

Syncom

TDRS

Telstar

Tiros

Transit

UHF

USA

Vanguard

Westar


 Arab States

Satellites launched

1985

Arabsat 1A

Arabsat 1B

1992

Arabsat 1C

1993

Arabsat 1D (bought in orbit)

Main program

Arabsat


 Europe

I use the name Europe so simplify naming. In fact, it may be the ESA or the ESRO.

In the early 60ies the COPERS (COmmission Préparatoire Européenne pour la Recherche Spatiale) was created. In 1964 the ESRO (European Science Research Organization) was created to develop satellites.

After numerous problems with the former organizations the ESA (European Space Agency) was created on 31 May 1975.

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

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

LDEF

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

Main programs

Cat

Esro

ERS

Eutelsat

Heos

Marecs

Meteosat

OTS


 International

Here are the satellites developed by an international organization. Intersputnik isn't in here because the satellites are owned by the CIS.

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

Main programs

Inmarsat

Intelsat

ISEE

Oscar

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

This chart keeps track of the satellites on the Clarke Belt.

First column is the slot or position 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 anf 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. The "Frequency bands" column relates the downlink bands in which the satellite can be active, blank means unknown.

Slot	Inc.	Satellite	Mis.	Freq. bands	Comment
-178.0	12.4	Marisat 3	C	L, C
-177.6	5.05	UHF 4	M	UHF, X, EHF
-177.5	5.60	Leasat 2	M
-177.0	5.21	Intelsat 503	C	C, Ku
-174.3	0.03	TDRS 5	M	S, C, Ku
-170.0	5.06	Raduga 21	C/M	C, X
-139.0	0.07	Aurora 2	C	C
-137.0	0.04	Satcom C1	C	C
-136.5	2.21	Goes 7	W	VHF, L, S
-135.0	0.06	Satcom C4	C	C
-133.0	0.02	Galaxy 1R	C	C
-131.0	0.06	Satcom C3	C	C
-130.1	4.32	DSCS 3-01	M	X
-125.0	0.03	Galaxy 5	C	C
-124.9	0.10	Gstar 2	C	Ku
-123.0	0.02	Telstar 303	C	C
-123.0	0.03	SBS 5	C	Ku
-116.8	0.04	Morelos 2	C	C, Ku
-114.9	3.10	Anik C3	C	Ku
-113.0	0.04	Solidaridad 2	C	L, C, Ku
-111.0	0.03	Anik E1	C	C, Ku
-109.2	0.03	Solidaridad 1	C	L, C, Ku
-109.0	14.3	DSCS 2-01	M		alive?
-107.3	0.01	Anik E2	C	C, Ku
-106.0	11.8	Marisat 1	C	L, C
-105.8	14.5	Nato 2	M		alive?
-105.5	16.1	LES 9	M		alive?
-105.4	14.8	ATS 3	C	VHF
-105.2	3.43	Aurora 1	C	C
-105.0	0.04	Gstar 4	C	Ku
-104.9	5.03	Leasat 3	M
-103	0.64	ASC 1	C	C, Ku	drifting East
-103.0	0.04	Gstar 1	C	Ku
-101.2	0.02	DBS 1	C	Ku
-101.0	0.03	ASC 2	C	C, Ku
-100.8	0.02	DBS 2	C	Ku
-100.0	0.04	ACTS	C	Ka
-99	0.11	AMSC 1	C	L, Ku	new, drifting East
-99.5	2.01	Fleetsatcom 7	M	UHF, X
-99.0	0.03	Galaxy 4	C	C, Ku
-97.0	0.04	Telstar 401	C	C, Ku
-95.0	0.03	SBS 6	C	Ku
-93.5	0.27	Galaxy 3	C	C
-93.0	6.50	Gstar 3	C	Ku
-94.5	16.1	LES 8	M		alive?
-91.0	0.04	Galaxy 7	C	C, Ku
-87.0	0.04	Spacenet 3R	C	L, C, Ku
-85.1	0.26	Telstar 302	C	C
-85.0	0.03	Satcom K1	C	Ku
-81.0	0.03	Satcom K2	C	Ku
-77.0	1.86	SBS 4	C	Ku
-76.0	8.10	Comstar 4	C	C
-75.8	3.04	Anik C2	C	Ku
-74.3	0.06	Goes 8	W	VHF, L, S
-74.0	0.02	Galaxy 6	C	C
-73.9	3.06	SBS 3	C	Ku
-71.8	0.04	Anik C1	C	Ku
-71.1	6.20	SBS 2	C	Ku
-70.0	0.07	Brazilsat B1	C	C, X
-69.0	0.06	Spacenet 2	C	C, Ku
-68.6	2.37	Meteosat 3	W	VHF, L, S
-65.0	0.04	Brazilsat A2	C	C
-65.0	0.03	Brazilsat B2	C	C, X	new
-63.1	0.50	Brazilsat A1	C	C
-54.0	2.62	Inmarsat 2F4	C	L, C
-53		Intelsat 706	C	C, Ku	new
-53.0	0.05	Intelsat 513	C	C, Ku
-50.0	0.08	Intelsat 705	C	C, Ku
-46.5	1.72	TDRS 6	M	S, C, Ku
-45.0	0.04	Panamsat 1	C	C, Ku
-40.9	0.05	TDRS 4	M	S, C, Ku
-40.3	5.53	Intelsat 502	C	C, Ku
-37.5	0.04	Orion 1	C	Ku
-34.5	0.02	Intelsat 603	C	C, Ku
-34.0	1.98	Skynet 4A	M	UHF, X, EHF
32	3.70	Intelsat 506	C	L, C, Ku	just moved
-31.5	5.22	Intelsat 504	C	C, Ku
-30.0	0.03	Hispasat 1A	C	X, Ku
-30.0	0.03	Hispasat 1B	C	X, Ku
-27.5	0.04	Intelsat 601	C	C, Ku
-25.0	3.70	Raduga 23	MC	C, X
-24.5	0.03	Intelsat 605	C	C, Ku
-24.0	1.72	Cosmos 2282	MW
-23.4	0.75	Cosmos 2209	MW
-23.0	9.88	Fleetsatcom 3	M	UHF, X
-22.4	2.09	Fleetsatcom 8	M	UHF, X
-21.5	0.06	Intelsat K	C	Ku
-21.2	0.95	Intelsat 512	C	C, Ku
-21.0	3.13	Nato 3D	M	X
-18.8	0.08	TDF 2	C	Ku
-18.8	0.05	TDF 1	C	Ku
-18.0	0.05	Intelsat 515	C	C, Ku
-17.8	2.26	Nato 4A	M	UHF, X
-17.0	6.76	Cosmos 1738	MC		moving?
-16.2	3.02	Cosmos 2054	MS	C, Ku
-15.5	5.06	Cosmos 1888	MC
-15.5	2.15	Inmarsat 2F2	C	L, C
-15.0	5.30	Marecs B2	C	L, C
-14.8	12.1	Fleetsatcom 1	M	UHF, X
-14.5	4.77	UHF 3	M	UHF, X
-13.8	1.36	Cosmos 2172	MC	C
-13.4	0.10	Express 01	C	C, Ku
-11.0	0.74	Gorizont 26	C	L, C, Ku
-10.0	0.25	Meteosat 6	W	VHF, L, S
-8.0	0.03	Telecom 2A	C/M	C, X, Ku
-7.9	1.10	Meteosat 4	W	VHF, L, S
-5.0	0.04	Telecom 2B	C/M	C, X, Ku
-1.1	1.32	Skynet 4C	M	UHF, X, EHF
-1.0	0.02	Intelsat 702	C	C, Ku
-0.8	0.01	Thor	C	Ku
-0.6	0.06	Tvsat 2	C	Ku
-0.5	0.17	Meteosat 5	W	VHF, L, S
3.0	0.05	Telecom 1C	C/M	C, X, Ku
5.0	0.06	TELE X	C	Ku
5.2	0.03	Sirius	C	Ku
6.0	3.45	Nato 4B	M	UHF, X
7.0	0.12	Eutelsat 2F4	C	Ku
9	2.62	Gorizont 20	C	L, C, Ku	moving East
10.0	0.12	Eutelsat 2F2	C	Ku
11.1	0.11	Raduga 29	MC	C, X
11.7	0.70	Cosmos 2224	MW
12.5	4.10	Raduga 22	MC	C, X
12.9	0.03	Hotbird 1	C	Ku	new
13.0	0.05	Eutelsat 2F1	C	Ku
13.2	0.65	Italsat 1	C	Ka
16.0	0.05	Eutelsat 2F3	C	Ku
19.2	0.11	Astra 1A	C	Ku
19.2	0.03	Astra 1D	C	Ku
19.3	0.20	Astra 1B	C	Ku
19.3	0.07	Astra 1C	C	Ku
20.0	1.28	Telstar 301	C	C
21.5	0.83	Eutelsat 1F5	C	Ku
22.5	7.23	Marecs A	C	L, C
23.5	0.04	DFS 3	C	Ku, Ka
25.5	1.64	Eutelsat 1F4	C	Ku
28.5	0.04	DFS 2	C	Ku, Ka
31.0	0.20	Arabsat 1C	C	S, C
33.5	0.04	DFS 1	C	Ku, Ka
34		Gorizont 17	C	L, C, Ku	alive?
35.0	1.25	Raduga 28	MC	C, X
40.0	2.20	Gorizont 22	C	L, C, Ku
42.1	0.04	Turksat 1B	C	Ku
45	0.59	Raduga 31	MC	C, X	drifting West
47.0	4.12	Intelsat 507	C	L, C, Ku
48.0	4.82	Eutelsat 1F1	C	Ku
48.7	0.62	Raduga 1-3	MC	C, X
49.2	2.10	Raduga 1-2	MC	C, X
53.1	2.47	Skynet 4B	M	UHF, X, EHF
54.4	0.52	Gorizont 27	C	L, C, Ku	moving?
58	4.74	Insat 1C	C/W	S, C	drifting East
57.0	2.25	Intelsat 510	C	C, Ku
60.0	0.03	Intelsat 604	C	C, Ku
63.0	0.01	Intelsat 602	C	C, Ku
64.5	1.71	Inmarsat 2F1	C	L, C
65.0	4.68	Intelsat 505	C	L, C, Ku
64.8	7.42	DSCS 2-15	M
	4.93	Cosmos 1897	MS		!moving West
66.0	0.05	Intelsat 704	C	C, Ku
69.7	1.21	Raduga 32	MC	C, X
70.0	3.52	Raduga 1-1	MC	C, X
71.0	0.04	GALS 1	C	Ku
71.5	4.58	UHF 2	M	UHF, X
71.7	3.07	Leasat 5	M
72.5	11.0	Marisat 2	C	L, C
74.0	0.06	Insat 2A	C/W	S, C
75.3	2.55	Cosmos 2085	MC		drifting West
76.2	0.82	Electro 1	W
79.5	4.34	Cosmos 1961	MC		drifting East
78.5	0.04	Thaicom 1	C	C, Ku
78.5	0.04	Thaicom 2	C	C, Ku
79.0	1.14	Cosmos 2133	MW
80.0	1.39	Gorizont 24	C	L, C, Ku
80.1	0.97	Cosmos 2291	MC	C
83.0	0.02	Insat 1D	C/W	S, C
84.7	10.2	DSCS 2-14	M
85.0	8.28	TDRS 1	M	S, C, Ku
85.5	0.35	Raduga 30	MC	C, X
87.3	1.60	Dong Fang Hong 22	C	C
90.0	0.37	Gorizont 28	C	L, C, Ku
91.5	6.11	Intelsat 501	C	C, Ku
92	5.75	Dong Fang Hong 18	C	C	drifting West
93.5	0.04	Insat 2B	C/W	S, C
95.1	2.28	Luch	MT	C, Ku
95	2.19	Raduga 26	MC	C, X	drifting East
96.5	3.31	Gorizont 19	C	L, C, Ku
98.0	0.05	Dong Fang Hong 26	C	C
99	3.13	Raduga 24	MC	C, X	drifting West
99.0	0.51	Ekran 20	C	UHF
99.0	4.09	Ekran 19	C	UHF
103.2	1.05	Gorizont 25	C	L, C, Ku
105	1.68	TDRS 3	M	S, C, Ku	drifting West
105.5	0.03	Asiasat 1	C	C
108.0	0.04	Palapa B2R	C	C
109.8	0.05	Yuri 3N	C	Ku
110.0	0.03	Yuri 3A	C	Ku
110.0	0.03	Yuri 3B	C	Ku
110.5	0.12	Dong Fang Hong 25	C	C
113.0	0.05	Palapa B2P	C	C
115.5	0.06	Spacenet 1	C	C, Ku
118.0	0.02	Palapa B4	C	C
120.0	5.88	GMS 3	W	UHF, L, S
127.9	2.12	Raduga 27	MC	C, X
130.0	0.42	Gorizont 29	C	C, Ku
132.0	0.03	Sakura 3A	C	C, Ka
134.0	4.19	Palapa B1	C	C
136.0	0.04	Sakura 3B	C	C, Ka
138.0	0.04	Apstar 1	C	C
140.2	0.93	GMS 4	W	UHF, L, S
140.3	3.42	Gorizont 18	C	L, C, Ku
142.7	0.71	Gorizont 30	C	C, Ku
144.7	2.29	Gorizont 21	C	L, C, Ku
150.0	0.02	Jcsat 1	C	Ku
150.3	3.14	ETS 5	C	L, C
152.0	0.36	Aussat B3	C	L, Ku
154.0	0.04	Jcsat 2	C	Ku
156.0	0.03	Aussat A3	C	Ku
158.0	0.01	Superbird A2	C	X, Ku, Ka
159.7	0.99	GMS 5	W	UHF, L, S	new
160.0	0.03	Aussat B1	C	L, Ku
162.0	0.04	Superbird B1	C	X, Ku, Ka
164.0	1.60	Aussat A2	C	Ku
169.0	0.02	Panamsat 2	C	C, Ku
172.0	10.2	Fleetsatcom 4	M	UHF, X
174.0	0.02	Intelsat 701	C	C, Ku
177.0	0.03	Intelsat 703	C	C, Ku
178.0	0.72	Inmarsat 2F3	C	L, C
180.0	1.90	Intelsat 511	C	C, Ku


 To be launched

May 1995

??	CTA (telecom, LLV 1, Vandenberg)
??	UHF 5
??	NOAA K
19	Step 3 (Pegasus)
20	TOMS (Pegasus)
29	COMET (Conestoga)
30	MSX (Delta)
June 1995

??	Asiasat 2
??	DBS 3 (Ariane V74)
??	Koreasat 1
??	Lifesat 02
08	Interbol 1/Prognoz M2 (scientific, Molnya M)
08	STS 70
19	STS 71
July 1995

??	HETE SAC B (Argentine)
??	Helios (Ariane V75)
??	Sich 1 (Cyclone, Ukraine)
??	FAST
??	UHF 6
15	SWAS
01	Seastar
18	Mungunghwa 1 (South Korea, 116°E)
20	STS 69
August 1995

??	IRS 1C
??	N Star 1 (Ariane V76)
??	Echostar 1
17	Jcsat 3
31	XTE (Delta 2)
September 1995

??	Galaxy 3R
??	Panamsat 4 (Ariane V77) Amos 1
19	Infrared Space Observatory (ISO) (Ariane)
20	Radarsat Surfsat 1
21	STS 73
October 1995

??	Intelsat 708
??	Koreasat 2
??	UHF 7
26	STS 74
31	Soho (Atlas 2AS)
November 1995

??	Astra 1E (Ariane V78)
??	NOAA K (Titan 2)
??	Mungunghwa 2 (South Korea, 116°E)
29	Cluster (ESA/NASA, Ariane 5)
30	STS 72
December 1995

??	Telecom 2C (Ariane V79) Insat 2C
??	DRS (ESA)
??	Intelsat 709
??	Polar
??	Lifesat 03
??	P91-1/Argos (Delta 2)
??	SAX
??	SMEX 06
1995

??	Coupon 1
??	Coupon 2
??	Coupon 3
??	Gals 2
??	Lifesat 01
??	Safir 1
January 1996

??	VSOP
??	Intelsat 801
February 1996

Feb	ADEOS/NSCAT
Feb	STS 75
Feb	Intelsat 802
March 1996

??	Astra 1F (Proton)
21	STS 76 (Atlantis, 3rd Shuttle-Mir Mission, SPACEHAB)
April 1996

25	STS 77 (Endeavour, Spacehab 4)
1996

??	N Star 2 (Ariane V80)
??	Intelsat 707 (Ariane V81)
??	Palapa C1 (Ariane V82) Measat 1
??	Panamsat 3R (Ariane)
??	M Sat (Ariane)
??	Italsat 2 (Ariane)
??	GOES L
??	Arabsat 2A
??	Arabsat 2B
??	DBS 4
??	Gals 3
??	Inmarsat 3
??	Insat 2D
??	Meteosat 7
??	Panamsat 5
??	Thaicom 3
??	Apstar 1A
May	Intelsat 803
Aug	Echostar 2
Aug	Hotbird 2
Aug	Intelsat 804
Dec	Intelsat 806
1997

??	Astra 1G
??	BSAT
??	Hotbird 3
??	Eutelsat 3
??	Orion 2
??	Telstar 5
Mar	Intelsat 805
1998

??	Afristar
??	Asiastar
??	Caribstar
??	CERS 1
??	Insat 2E
??	Meteosat 8
??	Odyssey
??	Skynet 4E
1999

??	Telstar 6
2000

??	Telstar 7
No date

??	Elekon
??	Nahuel 1
??	Orion 3
??	Spaceway
??	Spot 4
??	SSTP
??	Superbird C


 Glossary

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

Apogee Kick Motor	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

BOL	Begin Of Life

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

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

CONUS	Continental United States

Coverage	Zone were the satellite's signals can be received

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

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

EOL	End Of Life

Footprint	A zone covered by a satellite's signals

Frequencies

L-band	1.530-2.700
FCC's digital radio	2.310-2.360
S-band	2.700-3.500
C-band	Downlink: 3.700-4.200 Uplink: 5.925-6.425
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:
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.

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

IOL	Inter-Orbit Link

Launch id	Launch number that identifies the flight, see LAUNR

LEO	Low Earth Orbit

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

Power	The transponder amplification power

SSPA	Solid State Power Amplifier

RHCP	Right Hand Circular Polarization

TWTA	Traveling Wave Tube Amplifier

Uplink	The earth to satellite signal path


 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

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

Contact

NASA

600 Independence Avenue, SW, Washington DC 20546

Tel: +1-202-453-1000

Technical data

Specifications

Prime contractor	GE Astro Space
Platform	GE 4000 modified
Mass at launch	2545 kg
Mass in orbit	1555 kg
Length	2.03 m
Width	2.13 m
Height	1.92 m
Stabilization	3 axis
DC power	BOL: 1770 W
Design lifetime	2 years
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	spot beam: 60 dBW contiguous sectors: 59 dBW steerable: 53 dBW
Polarization


 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
Launch site	Vandenberg
Mass at launch
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
Launch site	Wallops Island
Mass at launch
End of life

Decay	11 Apr 1989


 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
Launch site	Vandenberg
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
Launch site	Vandenberg
Mass at launch	127 kg
End of life

Decay	25 Sep 1975


 Program: AFP

American military program for electronical listening


Program: AFP

AFP 658

AFP 731


 AFP 658

Also called USA 067

General

Designation	20963 / 90097B
Launch date	15 Nov 1990
Country of origin	United States
Mission	Military: electronical listening
Perigee/Apogee	n/a
Inclination	n/a
Period	n/a
Launch vehicle	STS 38
Mass at launch

Aimed to listen to the Persian Gulf


 AFP 731

Also called USA 053

General

Designation	20516 / 90019B
Launch date	28 Feb 1990
Country of origin	United States
Mission	Military: electronical listening
Perigee/Apogee	n/a
Inclination	n/a
Period	n/a
Launch vehicle	STS 36
Mass at launch

Was expected to give digital pictures and listen to radioelectric emissions.

End of life

Out of service	7 Mar 1990?
Cause	Explosion?
Decay	19 Mar 1990 in the Pacific Ocean?


Afristar

American satellite operated by Worldspace. Designed to reach third world with digital radio. The satellite should be constructed by a consortium led by Alcatel Espace and launched from 1998 on.

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.

The satellites of this program are Afristar, Asiastar & Caribstar.


 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
Launch site	Tanegashima

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

Payload: Retroflectors mounted on the surface of the sphere

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.


 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
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


Amos 1

General

Designation
Launch date	planned in Jul 1995 or Jan 1996?
Country of origin	Israel
Mission	Telecommunications
Geostationary orbit	4°W
Launch vehicle	Ariane
Mass at launch

Cost: $250 million

The Israeli government supports the program since 1991 with $15 million per year

It should be co-located with CERS

Technical data

Specifications

Prime contractor	DASA
Platform
Mass at launch
Mass in orbit
Length
Width
Height
Stabilization
DC power
Design lifetime	> 10 years
Ku-band

Main transponders	7
Backup transponders
Power
Bandwidth
Coverage	from Lybia to Iran and Ukraine to Sudan
EIRP
Polarization

Would have 3 spots: Middle East, Eastern Europe and Central Europe


 Program: AMPTE

Active Magnetospheric Particle Tracer Explorers

International scientific program; composed of 3 small satellites launch together.


Program: AMPTE

AMPTE CCE

AMPTE IRM

AMPTE UKS


 AMPTE CCE

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
Launch site	Cape Canaveral
Mass at launch


 AMPTE IRM

General

Designation	15200 / 84088B
Launch date	16 Aug 1984
Country of origin	Germany
Mission	Scientific: magnetophere study
Perigee/Apogee	402/113818 km
Inclination	27°
Period	2653.4 min
Launch vehicle
Launch site	Cape Canaveral
Mass at launch


 AMPTE UKS

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
Launch site	Cape Canaveral
Mass at launch


 Program: AMS

Advanced Meteorological Satellite

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


 Program: AMSC

Operated by American Mobile Satellite Corporation

For mobile communications, designed to provide mobile voice, fax and data services to land mobile maritime, aeronautical and fixed site customers. The company currently offers fleet management mobile data and position reporting services to the maritime, trucking and rail industries throughout the U.S. via leased satellite capacity.

Contact

American Mobile Satellite Corporation (AMSC)

1150 Connecticut Avenue N.W., Washington, DC 20036, USA

Tel: +1-202-331-5858


Program: AMSC

AMSC 1


 AMSC 1

Also called MSAT 1

General

Designation	23553 / 95019A
Launch date	7 Apr 1995 at 23:47 UT
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	101°W
Launch vehicle	Atlas 2A AC 114
Launch site	Cape Canaveral LC 36A
Mass at launch
Technical data

Specifications

Prime contractor	Hugues and SPAR Aerospace
Platform	HS 601
Mass at launch	2550 kg
Mass in orbit	1510 kg
Length	2.27 m
Width	2.27 m
Height	2.27 m
Solar array	20.96 m span
Stabilization	3 axis
DC power	BOL: 3600 W
Design lifetime	12 years
L-band

Main transponders	16
Backup transponders	4
Power	38 W (SSPA)
Bandwidth
Coverage	CONUS, Carribean, Alaska and Hawaii
EIRP	58 dBW
Polarization

Total bandwith: 3200 x 5 KHz

Ku-band

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


 Program: Anik

In Esquimau language Anik means "brother"

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. Telesat Canada belongs for half to the State and private companies.

Contact

Telesat Canada

1601 Telesat Court, Gloucester K1B 5P4, Ontario, Canada

Tel: +1-613-748-0123

Fax: +1-613-748-8712

Email: info@telesat.ca


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 C's specifications

Prime contractor	Hugues
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	10 years


Anik C's Ku-band

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


Anik D's specifications

Prime contractor	Spar Aerospace with technology licensed from Hugues
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
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	36 dBW
Polarization	linear


Anik E's Ku-band

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


Anik E's C-band EIRP


Anik E's Ku-band EIRP


 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
Launch vehicle
Launch site	Cape Canaveral
Mass at launch	381.7 kg

First satellite of the Anik system; linked 37 earth stations

End of life

Out of service	yes
Technical data

Specifications

Transponders	12
Phone circuits capacity	6.000


 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
Launch site	Cape Canaveral
Mass at launch	288 kg
End of life

Out of service	yes


 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
Launch vehicle
Launch site	Cape Canaveral
Mass at launch	270 kg
End of life

Out of service	yes


 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
Launch site	Cape Canaveral
Mass in orbit	473 kg
End of life

Out of service	yes
Technical data

Specifications

C-band	12 transponders
Ku-band (12/15 GHz)	4 transponders


 Anik C1

Also called Telesat 9

General

Designation	15642 / 85028B
Launch date	13 Apr 1985
Country of origin	Canada
Mission	Telecommunications
Geostationary orbit	72°W
Launch vehicle	STS 16

Was sold to Paracomsat an Argentine operator

Contact

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

Technical data

Specifications

Ku-band


 Anik C2

Also called Telesat 7

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

Contact

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

Location

Begin	End	Position
L: 18 Jun 1983		76.2°W
Feb 1995		75.8°W
Technical data

Specifications

Ku-band


 Anik C3

Also called Telesat 5

General

Designation	13652 / 82110C
Launch date	12 Nov 1982
Country of origin	Canada
Mission	Telecommunications
Geostationary orbit	114.9°W
Launch vehicle	STS 05
Technical data

Specifications

Ku-band

Transponder frequency chart (GHz)

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


 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	Delta
Launch site	Cape Canaveral
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	110.5°W before being sold
Launch vehicle	STS 14

Replaces Anik 1B in November 1986.

Was sold in September 1993 and became 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.

Technical data

Specifications

C-band

Ku-band

EIRP coverage (dBW)

C-band

Ku-band

C-band transponder frequency chart (GHz)

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

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


 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 an system that calculates and orders the satellite's movements from an Earth station.

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

Technical data

Specifications

C-band

Ku-band

EIRP coverage (dBW)

C-band

Ku-band

C-band transponder frequency chart (GHz)

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

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


 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
Launch site	Cape Canaveral
Mass at launch


 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
Launch site	Vandenberg
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 at 11:38 UT
Country of origin	United States
Mission	Scientific: magnetosphere study
Perigee/Apogee	360/2534 km
Inclination	69.9°
Period	115 min
Launch vehicle	Pegasus rocket carried by a B-52
Launch site	Vandenberg
Mass at launch	260 kg

The spacecraft carries three diagnostic instruments including a cosmic ray monitor to check the impact of radiation in the Van Allen belt on the other two target instruments.

Technical data

Platform: Pegastar


 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
End of life

Out of service	19 Sep 1983


 Program: Apstar

Hong Kong program operated by Asia Pacific Telecommunication (APT)

Contact

Asia Pacific Telecommunication Satellites Company

Room 3111-2, 31st floor, One Pacific Plaza, 88 Queens way, Hong Kong

Tel: +852-526-2281

Fax: +852-522-0419


Program: Apstar

Apstar 1

Apstar 2


 Apstar 1

General

Designation	23185 / 94043A
Launch date	21 Jul 1994 at 10:31 UT
Country of origin	Hong Kong
Mission	Telecommunications
Geostationary orbit	138°E
Launch vehicle	Long March 3
Launch site	Xichang
Mass at launch	1400 kg
Technical data

Specifications

Prime contractor	Hugues
Platform	HS 376
Mass at launch
Mass in orbit
Diameter
Height
Stabilization	Spin stabilized
DC power
Design lifetime
C-band

Main transponders	24
Backup transponders
Power
Bandwidth
Coverage	South East Asia
EIRP
Polarization


 Apstar 2

General

Designation	n/a
Launch date	25 Jan 1995 at 19:26 UT
Country of origin	Hong Kong
Mission	Telecommunications
Geostationary orbit	should have been 77°E
Launch vehicle	Long March 2E
Launch site	Xichang

Six people had been killed by falling debris from the explosion which also injured 27.

End of life

Out of service	25 Jan 1995
Cause	Exploded with the launcher?
Technical data

Specifications

Prime contractor	Hugues
Platform	HS 601
Mass at launch
Mass in orbit
Stabilization	3 axis
DC power
Design lifetime
C-band

Main transponders	26
Backup transponders
Power
Bandwidth
Coverage	South East Asia
EIRP
Polarization
Ku-band

Main transponders	8
Backup transponders
Power
Bandwidth
Coverage
EIRP
Polarization


Apstar 1A

This satellite should be based on a HS 376 to cover the same area as Apstar 1 + the Indian sub-continent. shoud be launched before mid-1996


 Program: Arabsat

Satellite program of the Arab States operated by Arabsat

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.

Contact

Arabsat

PO Box 1038, 11431 Riyadh, Saudi Arabia

Tel: +966-1-464-6666

Fax: +966-1-465-6983


Program: Arabsat

Arabsat 1A

Arabsat 1B

Arabsat 1C

Arabsat 1D

Arabsat 1E


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

Prime contractor	Aerospatiale
Platform	Spacebus 100
Payload mass	140 kg
Length	2.26 m
Width	1.64 m
Height	2.26 m
Solar array	20.7 m span
Stabilization	3 axis
DC power	BOL: 1400 W EOL: 1300 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	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	31 dBW
Polarization	circular


 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
End of life

Out of service	Mar 1992
Cause	Satellite 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	see below
Launch vehicle	STS 18
Mass at launch	1270 kg
Location

Begin	End	Position
L: 18 Jun 1985
Mar 1991	Oct 1992	26°E
Jan 1993	Jan 1993	43°E
End of life

Out of service	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	1310 kg
Location

Begin	End	Position
L: 26 Feb 1992
Mar 1992	Oct 1992	31°E
Jan 1993	Jan 1993	26°E
Jul 1993	...	31°E
Technical data

Specifications

S-band

C-band

S-band EIRP coverage (dBW)

C-band EIRP coverage (dBW)


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

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	...	20°E


Arabsat 2A

General

Designation
Launch date	planned in 1996
Country of origin	Arab States
Mission	Telecommunications
Geostationary orbit
Launch vehicle	Ariane
Launch site
Mass at launch

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


Arabsat 2B

General

Designation
Launch date	planned in 1996
Country of origin	Arab States
Mission	Telecommunications
Geostationary orbit	26°E
Launch vehicle
Launch site
Mass at launch


 Program: Argos

Localization and data transmission program. Was created by French and American organizations (CNES/NASA/NOAA). Started in 1978, it uses fixed or mobile instruments for meteorology with an transmitter. Data is collected by NOAA satellites.

The system is actually only 20% booked with 2500 beacons and 170 users. The reception stations are:Fairbanks, Alaska; Wallops Island, Virginia US; Lannion, France.

Contact

North America:

Service Argos Inc.

Suite 10, Mc Cormick Drive, Landover MD 20785 -- USA

Tel: +1-301-925-4411

Fax: +1-301-925-8995

Telex: 898 146

Other parts of the World:

CLS Argos

18, avenue Edouard Belin, 31055 Toulouse Cedex -- FRANCE

Tel: +33-6139-4700

Fax: +33-6175-1014

Telex: 531 752 F


 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	Delta
Launch site	Cape Canaveral
Mass at launch
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
Launch site	Cape Canaveral
Mass at launch
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
Launch site	Vandenberg
Mass at launch

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
Launch site	Vandenberg
Mass at launch
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	Delta
Launch site	San Marco
Mass at launch
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
Launch site	Wallops Island
Mass at launch
End of life

Decay	23 Sep 1990


 ARS

Aerosym Rescare Satellite

General

Designation	No satellite launched at that date: error!
Launch date	21 May 1965
Country of origin	United States
Mission	Scientific
Perigee/Apogee	3020 km
Inclination
Period
Launch vehicle
Launch site
Mass at launch

First satellite launched anti-earthwise. Brought into orbit 400 millions metallic needles.


 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


 Aryaghata

General

Designation	07752 / 75033A
Launch date	19 May 1975
Country of origin	India
Mission	Scientific: ionosphere study
Perigee/Apogee	398/409 km
Inclination	50.7°
Period	92.6 min
Launch vehicle	Intercosmos
Launch site	Kapustin Yar
Mass at launch	360 kg

Studies astronomy sources and relations between Earth and Sun.

End of life

Out of service	After 4 days
Cause	Failure
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
Length	1.63 m
Width	1.32 m
Height	0.99 m
Solar array	14.33 m span
Stabilization	3 axis
Design lifetime	10 years


 ASC 1

General

Designation	15994 / 85076C
Launch date	27 Aug 1985
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	STS 20
Location

Begin	End	Position
L: 27 Aug 1985	late-1994	128°W
Feb 1995	...	drifting East
Technical data

Specifications

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	34 dBW
Polarization	linear
C-band transponder frequency chart (GHz)

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

Main transponders	6
Backup transponders
Power	16.2 W (TWTA)
Bandwidth	72 MHz
Coverage
EIRP	42 dBW
Polarization	linear H
Ku-band transponder frequency chart (GHz)

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


 ASC 2

Otherwise knowned 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
Launch site	Cape Canaveral
Technical data

Specifications

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	37 dBW
Polarization	linear
C-band transponder frequency chart (GHz)

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

Main transponders	6
Backup transponders
Power	6 of 16.2 W (TWTA) 2 of 30 W (TWTA)
Bandwidth	72 MHz
Coverage
EIRP	46 dBW
Polarization	linear H
Ku-band transponder frequency chart (GHz)

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


 Program: Asiasat

Telecommunication program

Contact

Asia Satellite Telecommunications Company Ltd

23-24/F, East Exchange Tower, 38-40 Leighton Road, Causeway Bay, Hong Kong

Tel: +852-805-6666

Fax: +852-576-4111


Program: Asiasat

Asiasat 1


 Asiasat 1

General

Designation	20558 / 90030A
Launch date	7 Apr 1990
Country of origin	Hong Kong
Mission	Telecommunications
Geostationary orbit	105.5°E
Launch vehicle	Long March 3
Launch site	Xichang

This satellite was Westar 6 that was brought back from Space by the Shuttle in 1984.

Technical data

Specifications

Prime contractor	Hugues
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	North beam: 36 dBW South beam: 37 dBW
Polarization	linear
Transponder frequency chart (GHz)

Horizontal Downlink	Transponder	Vertical Downlink
	1	3.740
3.760	2
	3	3.780
3.800	4
	5	3.820
3.840	6
	7	3.860
3.880	8
	9	3.900
3.920	10
	11	3.940
3.960	12
	13	3.980
4.000	14
	15	4.020
4.040	16
	17	4.060
4.080	18
	19	4.100
4.120	20
	21	4.140
4.160	22
	23	4.180
4.200	24


Asiasat 1's EIRP (North beam)


Asiasat 1's EIRP (South beam)


Asiasat 2

General

Designation
Launch date	planned in Jun 1995
Country of origin	Hong-Kong
Mission	Telecommunications
Geostationary orbit	100.5°E
Launch vehicle	Long March 2E
Launch site	Xichang
Specifications

Prime contractor	GE Astro Space
Platform	GE 7000
Mass at launch	3460 kg
Mass in orbit
Length
Width
Height
Stabilization	3 axis
DC power
Design lifetime	12 years
C-band

Main transponders	24
Backup transponders	6
Power	24 W (TWTA)
Bandwidth	36 MHz 72 MHz
Coverage
EIRP
Polarization
Ku-band

Main transponders	6 or 9?
Backup transponders
Power	45 W (TWTA)
Bandwidth	27 MHz 54 MHz
Coverage
EIRP
Polarization


Asiastar

American satellite operated by Worldspace. Designed to reach third world with digital radio. The satellite should be constructed by a consortium led by Alcatel Espace and launched from 1998 on.

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.

The satellites of this program are Afristar, Asiastar & Caribstar.


 Astérix

Also called A1

General

Designation	01778 / 65096A
Launch date	26 Nov 1965 at 15:47 local time
Country of origin	France
Mission	Scientific
Perigee/Apogee	527/1697 km
Inclination	64.3°
Period	107.5 min
Launch vehicle	Diamant A
Launch site	Hammahuir, Algeria
Mass at launch	42 kg

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

End of life

Out of service	26 Nov 1965
Cause	Stopped transmitting


 Program: Astra

Direct TV system that covers western Europe. Operated by SES (Société Européenne de Satellites), a compagny founded in March 1985 by 11 shareholders. Its center is located at the Betzdorff castle in Luxemburg.

Contact

SES

Château de Betzdorf, 6815 Betzdorf, Luxembourg

Tel: +352-7172-51

Fax: +352-7172-5324

Technical data

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 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.

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	150 kg
Length	2.9 m
Width	1.6 m
Height	1 m
Solar array	19.3 m span
Stabilization	3 axis
DC power	BOL: 2310 W
Design lifetime	10 years
Ku-band (11.2-11.45 GHz)

Main transponders	16
Backup transponders	6
Power	45 W
Bandwidth	26 MHz
Coverage	Europe
EIRP	50 dBW
Polarization	linear
Uplink frequencies	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
Length	2.2 m
Width	2.9 m
Height	2.3 m
Solar array	21.5 m span
Stabilization	3 axis
DC power	BOL: 2310 W
Design lifetime	10 years
Ku-band (11.45-11.7 GHz)

Main transponders	16
Backup transponders	6
Power	60 W
Bandwidth	26 MHz
Coverage	Europe
EIRP	52.5 dBW
Polarization	linear
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	Hugues
Platform	HS 601
Mass at launch	2700 kg
Length	2.3 m
Width	2.5 m
Height	2.5 m
Stabilization	3 axis
DC power
Design lifetime	14 years
Ku-band (10.9-11.2 GHz)

Main transponders	18
Backup transponders	6
Power	63 W
Bandwidth	27 MHz
Coverage	Europe
EIRP	52.5 dBW
Polarization	linear
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	19.2°E
Launch vehicle	Ariane V69
Technical data

EIRP coverage (dBW)

Horizontal polarization mode 1

Horizontal polarization mode 2

Vertical polarization mode 1

Vertical polarization mode 2

Specifications

Prime contractor	Hugues
Platform	HS 601
Mass at launch	2924 kg
Length	2.3 m
Width	2.5 m
Height	2.5 m
Solar array	21 m span
Stabilization	3 axis
DC power	3300 W
Design lifetime	13 years

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

Ku-band (10.7-10.9 GHz)

Main transponders	18
Backup transponders
Power	63 W
Bandwidth	26 MHz in 10 GHz 33 MHz in 12 GHz (DBS)
Coverage	Europe
EIRP	52 dBW
Polarization	linear
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
	V1	66	11.73900
11.75850	H2	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
Launch date	planned in Aug 1995
Country of origin	Luxemburg
Mission	Direct TV
Geostationary orbit	19.2°E
Launch vehicle	Ariane
Mass at launch
Technical data

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	H2	81
	V1	82	12.05100


Astra 1F

General

Designation
Launch date	planned in 1996
Country of origin	Luxemburg
Mission	Direct TV
Geostationary orbit	19.2°E
Launch vehicle	Proton
Launch site
Mass at launch
Technical data

Specifications

Prime contractor	Hugues
Platform	HS 601
Ku-band (12.1-12.5 GHz)

Main transponders	20
Backup transponders	8
Power	82 W


Astra 1G

General

Designation
Launch date	mid-1997
Country of origin	Luxemburg
Mission	Direct TV
Geostationary orbit	19.2°E
Launch vehicle
Launch site
Mass at launch
Technical data

Specifications

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

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

Ku-band (11.7-12.75 GHz)

Main transponders	16
Backup transponders	18 backup for 1E and 22 backup for 1F
Power	100 W (TWTA)
Bandwidth	26 MHz in FSS band 33 MHz in BSS band
Coverage
EIRP	52 dBW
Polarization


Astra 1H

SES has until 1996 to exercise its option on this additional satellite.


Astra 2A

Astra 2A is intended to replace 1A after its lifecycle, and will be the last Astra satellite for analog TV transmissions.


 Astrid

General

Designation	23464 / 95002B
Launch date	24 Jan 1999 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.

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	-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	-6- 2 dB
Polarization	RHCP
Data flow	128 kbps


 Program: Astro

Astronomy Japanese program


Program: Astro

Astro A

Astro B

Astro C

Astro D


 Astro A

Also called Hinotori

General

Designation	12307 / 81017A
Launch date	21 Feb 1981
Country of origin	Japan
Mission	Scientific: Sun study
Perigee/Apogee	274/279 km
Inclination	31.3°
Period	90.1 min
Launch vehicle
Launch site	Kagoshima
Mass at launch
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
Launch site	Tanegashima
Mass at launch
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
End of life

Decay	1 Nov 1991


 Astro D

Also called Asuka

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

Built by Nagoya's university and the Goddard Space Flight Center. Is equiped with 4 focal mirrors of 3.5 m and CCD detectors. The sensitiveness should be 100 times greater than HEAO 2.


 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
Launch site	Tyuratam
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: ATS

Application Technology Satellite

American satellites for technology tests.


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 experimentation
Geostationary orbit	149°W
Launch vehicle
Launch site	Cape Canaveral
Mass at launch

Transmitted the first high resolution photos of the Earth.

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
Launch site	Cape Canaveral
Mass at launch

Provided the first color pictures of the Earth and proved the interest in maritim communications via satellite. Transmitted the first space communication between an Earth station and a plane on 21 Nov 1967 above the Atlantic.

Location

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

Technical data

Transmits on 136.37 and 137.35 MHz (weak signals) or 149.175 - 149.265 ?


 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
Mass at launch

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
Launch site	Cape Canaveral
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.

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 B P4 N° 3
Launch site	Kourou
Mass at launch	120 kg
End of life

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


 Program: Auréole

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
Launch site	Plesetsk
Mass at launch


 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
Launch site	Plesetsk
Mass at launch


 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
Launch site	Plesetsk
Mass at launch


 Program: Aurora

Telecommunication program operated by Alascom Inc. a subsidiary of Pacific Telecom.

Contact

Alascom Inc.

210 Bluff Road, Box 6607, Anchorage, AK99502-7649, USA

Tel: +1-907-264-7000

Fax: +1-907-264-7704


Program: Aurora

Aurora 1

Aurora 2


Aurora's specifications

Prime contractor	GE Astro Space
Platform	GE 3000
Mass in orbit	760 kg
Length	1.63 m
Width	1.32 m
Height	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	Delta 3910
Launch site	Cape Canaveral
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	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 7925
Launch site	Cape Canaveral
Mass at launch	1338 kg
Technical data

Specifications

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	34 dBW
Polarization	linear
Transponder frequency chart (GHz)

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


 Program: Aussat

Australian national telecommunications system. It was renamed Optus when Optus Communications Ltd. bought Aussat.

Contact

Optus Communications Ltd

54 Carrington Street, Sydney, NSW 2000, Australia

Tel: +61-2-238-7987

Fax: +61-2-238-8119


Program: Aussat

Aussat A1	Aussat A2	Aussat A3
Aussat B1	Aussat B2	Aussat B3


Aussat A's specifications

Prime contractor	Hugues
Platform	HS 376
Mass at launch	1250 kg
Mass in orbit	655 kg
Diameter	2.16 m
Height	6.6 m (2.84 m stowed)
Stabilization	Spin stabilized
DC power	BOL: 1000 W
Design lifetime	7 years (10 for the A3)


Aussat 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	12 W: 41 dBW 30 W: 51 dBW
Polarization


Aussat B's specifications

Prime contractor	Hugues
Platform	HS 601
Mass at launch	2858 kg
Mass in orbit	1582 kg
Length	2.27 m
Width	2.27 m
Height	2.27 m
Solar array	20 m span
Stabilization	3 axis
DC power	BOL: 3500 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.


Aussat B's L-band

Main transponders	8
Backup transponders
Power	30 W
Bandwidth
Coverage
EIRP	55 dBW
Polarization


Aussat B's Ku-band

Main transponders	16
Backup transponders
Power	50 W (TWTA)
Bandwidth	45 MHz
Coverage	Australia (1 central beam and 5 regional beams) South West Pacific region
EIRP	47 dBW
Polarization	linear


Aussat B's EIRP (central beam)


Aussat B's EIRP (Australian spot beams)


 Aussat A1

Also called Optus 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 20
End of life

Out of service	yes
Technical data

Specifications

Ku-band


 Aussat A2

Also called Optus A2

General

Designation	16275 / 85109C
Launch date	27 Nov 1985
Country of origin	Australia
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	STS 23
Location

Begin	End	Position
L: 27 Nov 1985		156°E
Feb 1995	...	164°E
Technical data

Specifications

Ku-band


 Aussat A3

Also called Optus 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
Technical data

Specifications

Ku-band


 Aussat B1

Also called 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
Launch site	Xichang

First commercial flight of a Long March 2E

Technical data

Specifications

L-band

Ku-band

EIRP coverage (dBW)

Central beam

Australian spot beam


 Aussat B2

Also called 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
Launch site	Xichang
End of life

Out of service	21 Dec 1992
Cause	Apogee kick motor failure
Technical data

Specifications

L-band

Ku-band

EIRP coverage (dBW)

Central beam

Australian spot beam


 Aussat B3

Also called Optus B3; is in fact the B2-R

General

Designation	23227 / 94055A
Launch date	27 Aug 1994 at 21:10 UT
Country of origin	Australia
Mission	Telecommunications
Geostationary orbit	152°E
Launch vehicle	Long March 2E
Launch site	Kichang
Mass at launch
Technical data

Specifications

L-band

Ku-band

EIRP coverage (dBW)

Central beam

Australian spot beam


 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
Launch site	Tanegashima
Mass at launch	130 kg
End of life

Out of service	After 20 min (or 3 days?)


 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
Launch site	Tanegashima
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
Launch site	Vandenberg
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
Launch site	Xichang
Mass at launch
End of life

Decay	8 Dec 1990


 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	Intercosmos
Launch site	Kapustin Yar
Mass at launch	444 kg
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	368/372 km
Inclination	50.6°
Period	92 min
Launch vehicle	Intercosmos
Launch site	Kapustin Yar
Mass at launch	436 kg
End of life

Decay	30 Nov 1991


 Program: Brazilsat

Brazilian telecommunication system operated by Embratel.

Contact

Embratel

Empressa do Sistema Telebras

Avenida Presidente Vargas 1012-1602, Riode Janeiro 20071, Brazil

Tel: +55-21-216-8879

Fax: +55-21-216-8902


Program: Brazilsat

Brazilsat A1	Brazilsat A2
Brazilsat B1	Brazilsat B2


Brazilsat 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
Design lifetime	1: 9 years 2: 11 years


Brazilsat A's C-band

Main transponders	26
Backup transponders	6
Power	10 W (TWTA)
Bandwidth	36 MHz
Coverage
EIRP	36 dBW
Polarization	linear


Brazilsat B's specifications

Prime contractor	Hugues
Platform	HS 376W
Mass at launch	1760 kg
Mass in orbit
Dry mass	800 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


Brazilsat B's C-band

Main transponders	28
Backup transponders
Power	15 W
Bandwidth	31 MHz
Coverage	Brazil and South-America
EIRP	38 dBW
Polarization


Brazilsat B's X-band

Main transponders	1
Backup transponders
Power
Bandwidth
Coverage
EIRP
Polarization


 Brazilsat A1

Also called SBTS A1

General

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

Begin	End	Position
L: 8 Feb 1985		65°W
late-1994	Feb 1995...	63°W
Technical data

Specifications

C-band


 Brazilsat A2

Also called SBTS A2

General

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

Begin	End	Position
L: 28 Mar 1986		70°W
late-1994	Feb 1995...	65°W
Technical data

Specifications

C-band


 Brazilsat B1

Also called SBTS B1

General

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

Cost: $140 million

Technical data

Specifications

C-band

X-band


 Brazilsat B2

Also called SBTS B2

General

Designation	23536 / 95016A
Launch date	28 Mar 1995
Country of origin	Brazil
Mission	Telecommunications
Geostationary orbit	65°W
Launch vehicle	Ariane V71

Cost: $125 million

Technical data

Specifications

C-band

X-band


 Bremsat

General

Designation	22998 / 94006H
Launch date	3 Feb 1994
Country of origin	Germany
Mission	Scientific: high atmosphere study
Perigee/Apogee	344/363 km
Inclination	56.9°
Period	91.4 min
Launch vehicle	STS 60
Mass at launch	mini satellite

Operated by DASA and built by OHB

End of life

Decay	12 Feb 1995


Program: BSAT

Japanese telecommunication program

2 satellites (1A & 1B) built by Hugues that will be launched in 97 and 98 by Ariane (1250 kg each)


 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	Hugues
Platform	HS 376
Mass at launch	1250 kg
Mass in orbit	660 kg
Diameter	2.16 m
Height	4.8 m
Stabilization	Spin stabilized
DC power	BOL: 1.024 W
Design lifetime	10 years

Equiped with steerable antennas


BSB's Ku-band

Main transponders	5
Backup transponders	1
Power	2 x 55 W (TWTA)
Bandwidth	27 MHz
Coverage
EIRP	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	Delta 4925
Launch site

Stopped transmitting on 31 Dec 1992 and became Sirius in 1994.

Location

Begin	End	Position
L: 27 Aug 1989
Nov 1991	Dec 1992	31°W
1994	...	Sirius
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 6925
Launch site	Cape Canaveral

Was sold in September 1992 and became Thor.

Location

Begin	End	Position
L: 18 Aug 1990
	Aug 1992	31°W
Sep 1992	...	Thor
Technical data

Specifications

Ku-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 B P4 N° 2
Mass at launch	76 kg

Tests a high precision micro-acceleratometer.

Its the counterpart of the first Castor that was lost with Pollux on 22 May 1973.

End of life

Decay	18 Feb 1979


Caribstar

American satellite operated by Worldspace. Designed to reach third world with digital radio. The satellite should be constructed by a consortium led by Alcatel Espace and launched from 1998 on.

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.

The satellites of this program are Afristar, Asiastar & Caribstar.


 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
Mass at launch
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
Mass at launch
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
Mass at launch

Measures the Sun light

End of life

Out of service	9 Jan 1982
Cause	Stopped transmitting


CERS

Central Europe Regional Satellite also called Magyarsat or Maggarsat

General

Designation
Launch date	1998
Country of origin	Hungary
Mission	Telecommunication
Geostationary orbit	4°W co-located with Amos
Launch vehicle
Launch site
Mass at launch

4 transponders will be reserved to Hungary

Technical data

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

Main transponders	16
Backup transponders
Power
Bandwidth	36 MHz
Coverage
EIRP	50 dBW
Polarization


 Program: Chalet

Also called Vortex

American geostationary spy satellites. Used from 1975 on.


 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
Launch site	Vandenberg
Mass at launch

Studies the thermical radiation of the sky (gave its precise temperature: 2.735 K).


 Program: Comstar

American telecommunication satellite program operated by Comsat. Capacity is leased to AT&T.

Contact

COMSAT Corporation

6560 Rock Spring Drive, Bethesda, MD 20817, USA

Tel: +1-301-214-3658

Fax: +1-301-214-7130


Program: Comstar

Comstar 1

Comstar 2

Comstar 3

Comstar 4


Comstar's specifications

Prime contractor	Hugues
Platform	Hugues (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

Disposes of 2 Ka-band beacons for propagation research (19 and 28.6 GHz).


Comstar's C-band

Main transponders	24
Backup transponders
Power	5 and 5.5 W (TWTA)
Bandwidth	36 MHz
Coverage
EIRP	33 dBW
Polarization


 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
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
Technical data

Specifications

C-band


 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
Launch site	Kagoshima
Mass at launch
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	Delta
Launch site	Vandenberg
Mass at launch	280 kg


Coupon 1

General

Designation
Launch date	planned in Oct 1994
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	55°E
Launch vehicle
Launch site
Mass at launch
Technical data

Ku-band

Main transponders	16
Backup transponders
Power
Bandwidth	36 MHz
Coverage	Europe and Asia
EIRP	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

Launch scheduled for April 1995, slotted in 9.5°W


Coupon 3

Launch scheduled for October 1995 slotted in 162°E


 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
Launch site	Cape Canaveral
Mass at launch

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
Mass at launch
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
Launch site	Cape Canaveral
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.

End of life

Out of service	November 1979


 Program: Dash

American program for radars calibration


 Program: DBS

American digital direct TV program operated by Hugues Communications Inc. (HCI).

Two companies provided TV programs: DirecTV a subsidiary of GM Hugues Electronics used 11 transponders (per satellite) while the 5 ones left were managed by USSB (United States Satellite Broadcasting) a division of Hubbard Broadcasting Inc. The receivers were first provided by Thomson Consumer Electronics (RCA trademark). This equipment (DSS for Digital Satellite System) was MPEG 2 compatible.

Contact

Hugues Communications Inc.

PO Box 82424, Worldway Postal Center, Los Angeles, CA 90009, USA

Tel: +1-213-607-4003

Fax: +1-213-607-4065

DirecTv

PO Box 92424, Los Angeles, CA 90009, USA

Tel: +1-818-569-7700

USSB

3415 University Avenue, St Paul, NM 55114, USA

Tel: +1-612-646-5555

Fax: +1-612-642-4103


Program: DBS

DBS 1

DBS 2


DBS' specifications

Prime contractor	Hugues
Platform	HS 601 S
Mass at launch	2930 kg
Mass in orbit	1700 kg
Length	2.27 m
Width	2.27 m
Height	2.27 m
Solar array	35.1 m span
Stabilization	3 axis
DC power	4300 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	52 dBW
Polarization	LHCP

The system can be configured as 8 transponders with 240 W power.

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


 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
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 2A
Launch site	Cape Canaveral
Mass at launch

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


DBS 3

General

Designation
Launch date	planned in Jun 1995
Country of origin	United States
Mission	Direct TV
Geostationary orbit	157°W or 101°W (power enforcement)
Launch vehicle	Ariane
Mass at launch


DBS 4

General

Designation
Launch date	planned in 1996
Country of origin	United States
Mission	Direct TV
Geostationary orbit	157°W
Launch vehicle	Ariane
Mass at launch


 Debut

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
Launch site	Tanegashima
Mass at launch


 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
Launch site	Cape Canaveral
Mass at launch

Part of the Star War program. Payload: radar, laser and 7 optical sensors (IR).

End of life

Decay	23 Jun 1992


 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
End of life

Decay	19 May 1980


 Program: DFS Kopernikus

Deutscher FernmeldeSatellit

German telecommunication program operated by DBP (Deutsche BundesPost)

Contact

Deutsche Bundespost Telekom

Godesberger Alle 87-91, 53175 Bonn, Germany

Tel: +49-228-181-1211

Fax: +49-228-181-8872


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	137 kg
Length	1.4 m
Width	1.9 m
Height	4.1 m
Solar array	15.4 m span
Stabilization	3 axis
DC power	BOL: 1990 W EOL: 1580 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 11 GHz transponders: 90 MHz 7 12 GHz transponders: 44 MHz
Coverage
EIRP	49 dBW
Polarization	linear


DFS Kopernikus's Ka-band (20/30 GHz)

Main transponders	1
Backup transponders
Power	20 W (TWTA)
Bandwidth	90 MHz
Coverage
EIRP	48 dBW
Polarization


DFS Kopernikus 3's EIRP


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	...	33.5°E
Technical data

Specifications

Ku-band

Ka-band

Transponder frequency chart


 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


 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
Launch site	Cape Canaveral
Technical data

Specifications

Ku-band

Ka-band

EIRP Coverage (dBW)

Transponder frequency chart


 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
Perigee/Apogee	545/1083 km
Inclination	39.9°
Period	101.2 min
Launch vehicle	Diamant A
Launch site	Hammaguir
Mass at launch	20 kg
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
Perigee/Apogee	586/1731 km
Inclination	39.4°
Period	108.5 min
Launch vehicle	Diamant A
Launch site	Hammaguir
Mass at launch	20 kg
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
Perigee/Apogee	502/2484 km
Inclination	34.1°
Period	115.8 min
Launch vehicle	Diamant A
Launch site	Hammaguir
Mass at launch	18.5 kg

Also used to test technology.

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


 Program: DMSP

Defense Meteorological Satellite Program

USAF meteorology 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. 5 DMSP B5D3 have been ordered


Program: DMSP

DMSP B5D2-3

DMSP B5D2-8

DMSP B5D2-9


 DMSP B5D2-3

Also called USA 026

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 E
Launch site	Vandenberg
Mass at launch	822 kg

Must detect tropical cyclones and evaluate the intensity of storms.


 DMSP B5D2-8

Also called USA 106 and DMSP 5D F12

General

Designation	23233 / 94057A
Launch date	29 Aug 1994 at 14:38 UT
Country of origin	United States
Mission	Military: meteorology
Perigee/Apogee	840/860 km
Inclination	98.9°
Period	101.9 min
Launch vehicle	Atlas E
Launch site	Vandenberg
Mass at launch

It carries instruments to measure energetic particles in the magnetosphere and photometers to scan auroral displays.


 DMSP B5D2-9

Also called USA 109 and DMSP 5D F13

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 E
Launch site	Vandenberg SLC3
Mass at launch

The satellite carries the OLS (Operational Linescan System) weather imager, and a set of microwave sounders and particle detectors.

The launch vehicule was the last Atlas E, a refurbished intercontinental ballistic missile which had been built in the early 1960s.


 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 on this program.


Program: Dong Fang Hong

Dong Fang Hong ²01 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


Feng Yun 1'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

Equiped with 2 of those radiometers


STTW's specifications

Shiyan Tongbu Tongxin Weixing means experimental synchronus 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	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	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
Length
Width
Height
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	6 transponders: 38 dBW 18 transponders: 35 dBW
Polarization


 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
Launch site	Jiuquan
Mass at launch	173 kg


 Dong Fang Hong 02

Also called Mao 2

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
Launch site	Jiuquan
Mass at launch


 Dong Fang Hong 03

Also called Mao 3

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
Launch site	Jiuquan
Mass at launch
End of life

Decay	14 Sep 1975


 Dong Fang Hong 04

Also called Mao 4

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
Launch site	Jiuquan
Mass at launch
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

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
Launch site	Jiuquan
Mass at launch
End of life

Decay	27 Jan 1976


 Dong Fang Hong 06

Also called Mao 6

General

Designation	09394 / 76087A
Launch date	30 Aug 1976
Country of origin	China
Mission	(JSSW)
Perigee/Apogee	195/2145 km
Inclination	69.2°
Period	108.8 min
Launch vehicle
Launch site	Jiuquan
Mass at launch
End of life

Decay	25 Nov 1978


 Dong Fang Hong 07

Also called Mao 7

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
Launch site	Jiuquan
Mass at launch
End of life

Decay	2 Jan 1977


 Dong Fang Hong 08

Also called Mao 8

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
Launch site	Jiuquan
Mass at launch
End of life

Decay	7 Feb 1978


 Dong Fang Hong 09

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
Launch site	Jiuquan
Mass at launch
End of life

Decay	19 Sep 1981


 Dong Fang Hong 10

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
Launch site	Jiuquan
Mass at launch
End of life

Decay	6 Oct 1982


 Dong Fang Hong 11

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
Launch site	Jiuquan
Mass at launch
End of life

Decay	17 Aug 1982


 Dong Fang Hong 12

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
Launch site	Jiuquan
Mass at launch
End of life

Decay	21 Sep 1982


 Dong Fang Hong 13

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
Launch site	Jiuquan
Mass at launch
End of life

Decay	3 Sep 1983


 Dong Fang Hong 14

General

Designation	14670 / 84008A
Launch date	29 Jan 1984
Country of origin	China
Mission	(Shijian Wexing)
Perigee/Apogee	484/6446 km
Inclination	36.1°
Period	162 min
Launch vehicle
Launch site	Jiuquan
Mass at launch


 Dong Fang Hong 15

Also called STTW 0

General

Designation	14899 / 84035A
Launch date	8 Apr 1984
Country of origin	China
Mission	Telecommunications
Geostationary orbit
Launch vehicle
Launch site	Xichang
Mass at launch
End of life

Out of service	yes
Technical data

Specifications

C-band


 Dong Fang Hong 16

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
Launch site	Jiuquan
Mass at launch
End of life

Decay	29 Sep 1984


 Dong Fang Hong 17

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
Launch site	Jiuquan
Mass at launch
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
Geostationary orbit	see below
Launch vehicle
Launch site	Xichang
Mass at launch
Location

Begin	End	Position
L: 1 Feb 1986	Mar 1995	103°E
Apr 1995	Apr 1995	100°E
Technical data

Specifications

C-band


 Dong Fang Hong 19

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
Launch site	Jiuquan
Mass at launch
End of life

Decay	23 Oct 1986


 Dong Fang Hong 20

General

Designation	18306 / 87067A
Launch date	5 Aug 1987
Country of origin	China
Mission	(FSW)
Perigee/Apogee	169/366 km
Inclination	63°
Period	89.9 min
Launch vehicle
Launch site	Jiuquan
Mass at launch
End of life

Decay	23 Aug 1987


 Dong Fang Hong 21

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
Launch site	Jiuquan
Mass at launch
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
Launch vehicle
Launch site	Xichang
Mass at launch
Technical data

Specifications

C-band


 Dong Fang Hong 23

General

Designation	19368 / 88067A
Launch date	5 Aug 1988
Country of origin	China
Mission	(FSW)
Perigee/Apogee	204/311 km
Inclination	63°
Period	89.7 min
Launch vehicle
Launch site	Jiuquan
Mass at launch
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
Launch site	Taiyuan

Mission: weather forcasting 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
Launch vehicle
Launch site	Xichang
Mass at launch
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
Launch vehicle
Launch site	Xichang
Mass at launch
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 3
Launch site	Taiyuan

Mission: weather forcasting and environment monitoring; cloud, ice, snow and flood monitoring; sea color and surface temperature.

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
Perigee/Apogee	789/811 km
Inclination	99°
Period	100.9 min
Launch vehicle
Launch site	Taiyuan
Mass at launch
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
Perigee/Apogee	596/629 km
Inclination	99°
Period	97 min
Launch vehicle
Launch site	Taiyuan
Mass at launch
End of life

Decay	24 Jul 1991


 Dong Fang Hong 33

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
Launch site	Juiquan
Mass at launch
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
Perigee/Apogee	2017/34047 km
Inclination	31.5°
Period	632.6 min
Launch vehicle
Launch site
Mass at launch
End of life

Out of service	28 Dec 1991
Cause	Did not reach GEO
Technical data

Specifications

C-band


 Dong Fang Hong 35

General

Designation	22072 / 92051A
Launch date	9 Aug 1992
Country of origin	China
Mission
Perigee/Apogee	171/332 km
Inclination	63.1°
Period	89.5 min
Launch vehicle
Launch site	Juiquan
Mass at launch
End of life

Decay	1 Sep 1992


 Dong Fang Hong 36

General

Designation	22162 / 92064B
Launch date	6 Oct 1992
Country of origin	China
Mission
Perigee/Apogee	213/309 km
Inclination	63°
Period	89.7 min
Launch vehicle
Launch site	Jiuquan
Mass at launch
End of life

Decay	31 Oct 1992


 Dong Fang Hong 37

Also called Jianbing 93

General

Designation	22859 / 93063A
Launch date	8 Oct 1993
Country of origin	China
Mission
Perigee/Apogee	177/2629 km
Inclination	56.5°
Period	113.9 min
Launch vehicle	Long March
Launch site	Jiuquan
Mass at launch

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.

End of life

Out of service	16 Oct 1993
Cause	Technical problem
Decay	27 Oct 1993 in the Pacific


 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
Perigee/Apogee	221/34459 km
Inclination	28.41°
Period	605.89 min
Launch vehicle	Long March 3A
Launch site	Xichang
Mass at launch

It carried six instruments for measuring particle fluxes and spacecraft electric potential.


 Dong Fang Hong 39

Also called Shijian 4-2 or SJ 4-2. Means "Practice 4-2"

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
Launch site	Xichang
Mass at launch

Mockup of the new DFH 3 telecommunication series (see Dong Fang Hong 40)


 Dong Fang Hong 40

General

Designation	23145 / 94037A
Launch date	3 Jul 1994 at 07:00 UT
Country of origin	China
Mission	Remote sensing, experimental (FSW 2)
Perigee/Apogee	176/355 km
Inclination	62.9°
Period	89.6 min
Launch vehicle	Long March 2D
Launch site	Jiuquan
Mass at launch

Separated in two pieces

End of life

Decay	payload: 15 Jul 1994 service module: 13 Sep 1994


 Dong Fang Hong 41

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
Launch site	Xichang

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


 Dove

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
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


 Program: DSCS

Defence Satellite Communication System, also called USGCSS

American geostationary satellite program. Satellites are launched by pairs since 1971. Designed to provide military telecommunications. Operated by the Space Command


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 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 2-01

General

Designation	05587 / 71095A
Launch date	3 Nov 1971
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit	see below
Launch vehicle
Launch site	Cape Canaveral
Mass at launch
Location

Begin	End	Position
L: 3 Nov 1971		?
Mar 1995	...	109°W


 DSCS 2-02

General

Designation	05588 / 71095B
Launch date	3 Nov 1971
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit
Launch vehicle
Launch site	Cape Canaveral
Mass at launch
End of life

Out of service	yes


 DSCS 2-03

General

Designation	06973 / 73100A
Launch date	13 Dec 1973
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit
Launch vehicle
Launch site	Cape Canaveral
Mass at launch
End of life

Out of service	yes


 DSCS 2-04

General

Designation	06974 / 73100B
Launch date	13 Dec 1973
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit
Launch vehicle
Launch site	Cape Canaveral
Mass at launch
End of life

Out of service	yes


 DSCS 2-05

General

Designation	07807 / 75040A
Launch date	20 May 1975
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit
Launch vehicle
Launch site	Cape Canaveral
Mass at launch
End of life

Out of service	20 May 1975
Cause	Launch failure
Decay	26 May 1975


 DSCS 2-06

General

Designation	07808 / 75040B
Launch date	20 May 1975
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit
Launch vehicle
Launch site	Cape Canaveral
Mass at launch
End of life

Out of service	20 May 1975
Cause	Launch failure
Decay	26 May 1975


 DSCS 2-07

General

Designation	10000 / 77034A
Launch date	12 May 1977
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit
Launch vehicle
Launch site	Cape Canaveral
Mass at launch
End of life

Out of service	yes


 DSCS 2-08

General

Designation	10001 / 77034B
Launch date	12 May 1977
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit
Launch vehicle
Launch site	Cape Canaveral
Mass at launch
End of life

Out of service	yes


 DSCS 2-11

General

Designation	11144 / 78113A
Launch date	14 Dec 1978
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit
Launch vehicle
Launch site	Cape Canaveral
Mass at launch
End of life

Out of service	yes


 DSCS 2-12

General

Designation	11145 / 78113B
Launch date	14 Dec 1978
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit
Launch vehicle
Launch site	Cape Canaveral
Mass at launch
End of life

Out of service	yes


 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
Launch site	Cape Canaveral
Mass at launch
End of life

Out of service	yes


 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
Launch site	Cape Canaveral
Mass at launch
Location

Begin	End	Position
L: 21 Nov 1979		?
Mar 1995	...	85°E
Technical data

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
Launch site	Cape Canaveral
Mass at launch
Location

Begin	End	Position
L: 30 Oct 1982		?
Mar 1995	...	65°E
Technical data

Downlinks in X-band


 DSCS 3-01

General

Designation	13637 / 82106A
Launch date	30 Oct 1982
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit	see below
Launch vehicle
Launch site	Cape Canaveral
Mass at launch
Location

Begin	End	Position
L: 30 Oct 1982		?
Mar 1995	...	130°W
Technical data

Downlinks in S- and X-band


 DSCS 3-02

General

Designation	14675 / 84009A
Launch date	31 Jan 1984
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit	n/a
Launch vehicle
Launch site	Cape Canaveral
Mass at launch
Technical data

Downlinks in S- and X-band


 DSCS 3-03

Also called USA 011

General

Designation	16116 / 85092B
Launch date	3 Oct 1985
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit	n/a
Launch vehicle	STS 21
Launch site	Cape Canaveral
Mass at launch
Technical data

Downlinks in S- and X-band


 DSCS 3-04

Also called USA 012

General

Designation	16117 / 85092C
Launch date	3 Oct 1985
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit	n/a
Launch vehicle	STS 21
Launch site	Cape Canaveral
Mass at launch
Technical data

Downlinks in S- and X-band


 DSCS 3-05

Also called USA 037

General

Designation	19976 / 89035A
Launch date	10 May 1989
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit	n/a
Launch vehicle
Launch site	Cape Canaveral
Mass at launch
Technical data

Downlinks in S- and X-band


 DSCS 3-06

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
Launch site	Cape Canaveral
Mass at launch
Technical data

Downlinks in S- and X-band


 DSCS 3-07

Also called USA 044

General

Designation	20203 / 89069B
Launch date	4 Sep 1989
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit	n/a
Launch vehicle
Launch site	Cape Canaveral
Mass at launch
Technical data

Downlinks in S- and X-band


 DSCS 3-08

Also called USA 078

General

Designation	21873 / 92006A
Launch date	11 Feb 1992
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit	n/a
Launch vehicle	Atlas 2
Launch site	Cape Canaveral
Mass at launch

This satellite is part of a set equiped with reinforced plating to resist to the explosion of an atomic bomb.

Technical data

Downlinks in S- and X-band


 DSCS 3-09

Also called USA 082

General

Designation	22009 / 92037A
Launch date	2 Jul 1992 at 21:54 UT
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit	n/a
Launch vehicle	Atlas
Launch site	Cape Canaveral
Mass at launch
Technical data

Downlinks in S- and X-band


 DSCS 3-10

Also called USA 093

General

Designation	22719 / 93046A
Launch date	19 Jul 1993
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit	n/a
Launch vehicle	Atlas 2
Launch site	Cape Canaveral
Mass at launch
Technical data

Downlinks in S- and X-band


 DSCS 3-11

Also called USA 097

General

Designation	22915 / 93074A
Launch date	28 Nov 1993
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit	n/a
Launch vehicle
Launch site	Cape Canaveral
Mass at launch
Technical data

Downlinks in S- and X-band


 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.


Program: DSP

DSP F12

DSP F13

DSP F14

DSP F15

DSP 3-4

DSP 3-5


 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
Launch site	Cape Canaveral
Mass at launch


 DSP F13

Also called USA 028

General

Designation	18583 / 87097A
Launch date	29 Nov 1987
Country of origin	United States
Mission	Military: early warning
Geostationary orbit	n/a
Launch vehicle
Launch site	Cape Canaveral
Mass at launch


 DSP F14

Also called USA 039

General

Designation	20066 / 89046A
Launch date	14 Jun 1989
Country of origin	United States
Mission	Military: early warning
Geostationary orbit	n/a
Launch vehicle
Launch site	Cape Canaveral
Mass at launch


 DSP F15

Also called USA 065

General

Designation	20929 / 90095A
Launch date	13 Nov 1990
Country of origin	United States
Mission	Military: early warning
Geostationary orbit	n/a
Launch vehicle
Launch site	Cape Canaveral
Mass at launch


 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	n/a
Launch vehicle	STS 44
Mass at launch	2350 kg

Cost: $275 million


 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	n/a
Launch vehicle	Titan 4
Launch site	Cape Canaveral LC40
Mass at launch


 Dynamics Explorer 1

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
Launch site	Vandenberg
Mass at launch


 Dynamics Explorer 2

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
Launch site	Vandenberg
Mass at launch
End of life

Decay	19 Feb 1983


 Program: Echo

American experimental telecommunication program


Program: Echo

Echo 1

Echo 2


 Echo 1

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
Launch site	Cape Canaveral
Mass at launch	61 kg

Plastic 30.5 m ball covered of mylar aluminumed that reflected radioelectric signals.

First telecommunication satellite. 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
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


Echostar 1

General

Designation
Launch date	planned in August 1995
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	119°W
Launch vehicle	Long March 2E
Launch site
Mass at launch

Total Echostar project: $335 million

$700. for the receiving kit and $100. subcription per month

Technical data

Specifications

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

23 transponders, 100 W each, 8 MPEG channels per transponder


Echostar 2

scheduled for August 1996, co-located

Built by GE Astro


 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 sepecifications

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
Launch site	Tyuratam
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
Launch site	Tyuratam
End of life

Out of service	yes
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
Launch site	Tyuratam
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
Launch site	Tyuratam
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
Launch site	Tyuratam
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
Launch site	Tyuratam
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
Launch site	Tyuratam
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
Launch site	Tyuratam
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
Launch site	Tyuratam
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
Launch site
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
Launch site	Plesetsk
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
Launch site	Tyuratam
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
Launch site	Tyuratam
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
Launch site
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
Launch site	Tyuratam
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
Launch site	Tyuratam
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
Launch site
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
Launch site
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
Launch vehicle	Proton
Launch site	Tyuratam
Technical data

Specifications


 Ekran 20

General

Designation	22210 / 92074A
Launch date	30 Oct 1992
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	99°E
Launch vehicle	Proton
Launch site	Tyuratam
Technical data

Specifications


 Electro 1

General

Designation	23327 / 94069A
Launch date	31 Oct 1994
Country of origin	CIS
Mission	Meteorology
Geostationary orbit	76.5°E
Launch vehicle	Proton
Launch site	Tyuratam
Mass at launch

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.

Technical data

Specifications

Prime contractor	VNII-EM
Platform	Electro
Mass at launch
Mass in orbit
Length
Width
Height
Stabilization
DC power
Design lifetime	3 years


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
Launch site	Tyuratam
Mass at launch


 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
Launch site	Tyuratam
Mass at launch


 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
Launch site	Tyuratam
Mass at launch


 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
Launch site	Tyuratam
Mass at launch
End of life

Decay	10 Jul 1964


 Eole

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
Launch site	Wallops Island
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 cause 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


 ERBS

Earth Radiation Budget Satellite

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 13
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.

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

Payload: 2 radiometers and SAGE 2 (Stratospheric Aerosol and Gas Experiment) to monitor vertical distribution of aerosols, ozone and carbone dioxide in the stratosphere.


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	Spot (Matra)
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 equiped 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
Technical data

Specifications

Prime contractor	Dornier
Platform	Spot (Matra)
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
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 equiped with Laser Reflectometer (LR), Precise Range and Range-rate Equipment (PRARE) and Instrument Data Handling and Transmission (IDHT).

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
Launch site	Cape Canaveral
Mass at launch


 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
Launch site	Cape Canaveral
Mass at launch


 Program: Esro

European Science Research Organisation

First European scientific program


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
Launch site	Vandenberg
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
Launch site	Vandenberg
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
Launch site	Vandenberg
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
Launch site	Vandenberg
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 or this program are evolved Tiros: better surface resolution.


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
Launch site	Cape Canaveral
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
Launch site	Cape Canaveral
Mass at launch


 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
Launch site	Vandenberg
Mass at launch


 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
Launch site	Vandenberg
Mass at launch


 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
Launch site	Vandenberg
Mass at launch


 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
Launch site	Vandenberg
Mass at launch


 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
Launch site	Vandenberg
Mass at launch


 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
Launch site	Vandenberg
Mass at launch


 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
Launch site	Cape Canaveral
Mass at launch


 Program: ETS

Engineering Test Satellite

Primary purpose of the Japanese ETS is to develop and prove bus technology. Operated by NASDA


Program: ETS

ETS 1

ETS 2

ETS 3

ETS 4

ETS 5

ETS 6


 ETS 1

Also called Kiku 1 which means "chrysanthemum"

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	N
Launch site	Tanegashima
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
Launch site	Tanegashima
Mass at launch
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
Launch site	Tanegashima
Mass at launch


 ETS 4

Also called Kiku 3

General

Designation	12295 / 81012A
Launch date	11 Feb 1984
Country of origin	Japan
Mission
Perigee/Apogee	240/20680 km
Inclination	28.2°
Period	362.4 min
Launch vehicle
Launch site	Tanegashima
Mass at launch


 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
Launch vehicle	H1
Launch site	Tanegashima

First 3 axis stabilized Japanese satellite with a built in apogee kick motor. It also carried a experimental mobile communications payload.

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	23.2 dBW
Polarization
C-band

Transponders	1
Power	6 W
Bandwidth	20 MHz
Coverage	Northern Pacific (used for a link to NASDA)
EIRP
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 slot 154°E
Launch vehicle	H2
Launch site	Tanegashima
Mass at launch

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.

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 was blocked
Technical data

Specifications

Prime contractor	Toshiba
Platform	Mitsubishi
Mass at launch	3800 kg
Mass in orbit	2000 kg
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	31.5 dBW
Polarization
C-band

Main transponders	4
Power	8 W
Bandwidth	35 MHz
Coverage
EIRP	35 dBW
Polarization
Ka-band (20/30 GHz)

Main transponders	6
Power	10 W (TWTA)
Bandwidth	120 MHz forward/30 MHz return
Coverage
EIRP	48 dBW
Polarization
O-band (38/43 GHz)

Main transponders	1
Power	10 W (TWTA)
Bandwidth
Coverage
EIRP
Polarization


 Eureca 1

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
Mass at launch

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
Technical data

Specifications

Prime contractor	MBB
Mass at launch	4450 kg
Payload mass	1000 kg
Length	4.5 m
Width	2.3 m
Height	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)


 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).

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

Contact

Eutelsat

Tour Maine-Montparnasse, 33 avenue du Maine, 75755 Paris cedex 15, France

Tel: +33-1-4538-4747

Fax: +33-1-4538-3700

Fax on demand: +33-1-4321-2338


Program: Eutelsat

Eutelsat 1F1	Eutelsat 1F2	Eutelsat 1F3	Eutelsat 1F4
Eutelsat 1F5
Eutelsat 2F1	Eutelsat 2F2	Eutelsat 2F3	Eutelsat 2F4
Eutelsat 2F5
Hotbird 1


Eutelsat 1's transponder frequency chart (GHz)

Uplink frequencies	14-14.5 GHz
Downlink frequencies	10.95-11.2 GHz, 11.45-11.7 GHz and 12.5-12.75 GHz (not on F1)
Horizontal Uplink	Horizontal Downlink	Transponder	Beam	Vertical Uplink	Vertical Downlink
	10.991667	1	Euro/West	14.291667
	11.075000	2	East	14.375000
	11.158333	3	Euro/West	14.458333
	14.491667	4	West	14.041667
	11.575000	5	East/Atlantic	14.125000
	11.658333	6	West	14.208333
14.291667		7	Euro/West		10.991667
14.375000		8	East		11.075000
14.458333		9	Euro/West		11.158333
14.041667		10	West		14.491667
14.125000		11	Atlantic		11.575000
14.208333		12	West		11.658333
	12.541667	13	SMS	?
?		14	SMS		12.541667


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	115 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
Design lifetime	7 years

Apogee kick motor: Mage 2


Eutelsat 1's Ku-band

Main transponders	10 (11 GHz) + 2 (12 GHz (none for F1))
Backup transponders	2
Power	20 W (TWTA)
Bandwidth	72 MHz
Coverage & EIRP	Atlantic, West & East spotbeams: 46 dBW Eurobeam: 41 dBW SMS beam: 43.5 dBW
Polarization	linear


Eutelsat 1's EIRP (Atlantic, West & East spots)


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	196 kg
Length	2.8 m
Width	2.2 m
Height	2.5 m
Solar array	22.4 m span
Stabilization	3 axis
DC power	BOL: 3000 W EOL: 2890 W
Design lifetime	10 years
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	wide or super beam
EIRP	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

Inclined since Sep 1989. Transponders 1, 2, 3, 4, 5, 6, 8, 9 and 11 have failed.

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
Dec 1991	Feb 1992	17.5°E
late-1992	Jul 1993	25.5°E
Sep 1993	...	48°E
Technical data

EIRP coverage (dBW)

Specifications

Ku-band

Transponder frequency chart

Beacon: 11.451091 GHz

This satellite is not as efficient as other Eutelsat 1 series. It can 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 Broadcasted 634,969 hours
Technical data

EIRP coverage (dBW)

Specifications

Ku-band

Transponder frequency chart


 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
Technical data

EIRP coverage (dBW)

Specifications

Ku-band

Transponder frequency chart

Beacon: 11.49650 GHz


 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.

Location

Begin	End	Position
L: 21 Jul 1988	Oct 1988	10°E, tests
14 Oct 1988	Apr 1991	10°E
15 Apr 1991	...	21.5°E
Technical data

EIRP coverage (dBW)

Specifications

Ku-band

Transponder frequency chart

Beacon: 11.448950 GHz


 Eutelsat 2F1

General

Designation	20777 / 90079B
Launch date	30 Aug 1990
Country of origin	Europe
Mission	Telecommunications
Geostationary orbit	13°E
Launch vehicle	Ariane V38

Operational since 24 Sep 1990.

Technical data

Specifications

Ku-band

Transponder frequency chart

EIRP coverage (dBW)

Wide beam

Super beam

Beacons: 11.451091 and 12.541667 GHz

Transponder frequency chart (GHz)

Horizontal Uplink	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	10°E
Launch vehicle	Ariane V41

Test were conducted in 21.5°E slot, operational since 8 Mar 1991

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	16°E
Launch vehicle	Atlas 2 AC-102
Launch site	Cape Canaveral

Operational since 10 Jan 1992.

Technical data

Specifications

Ku-band

Transponder frequency chart

EIRP coverage (dBW)

Wide beam

Super beam

Beacons: 11.452570 and 12.541667 GHz

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	7°E
Launch vehicle	Ariane V51

Operational since 18 Sep 1992.

Technical data

Specifications

Ku-band

Transponder frequency chart

EIRP coverage (dBW)

Wide beam

Super beam

Beacons: 11.451091 and 12.541667 GHz

Transponder frequency chart (GHz)

Horizontal Uplink	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 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


 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

Specifications

EIRP coverage (dBW)

Beacon: 11.450 GHz

Ku-band (11.2-11.55 GHz)

Main transponders	16
Backup transponders	8
Power	70 W (TWTA)
Bandwidth	36 MHz
Coverage and EIRP	super wide beam: 49 dBW
Polarization	linear
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

Uplink: 12.89-13.25 GHz


Hotbird 1's EIRP


Hotbird 2

General

Designation
Launch date	planned in Aug 1996
Country of origin	Europe
Mission	Telecommunications
Geostationary orbit	13°E
Launch vehicle	Atlas IIA
Launch site
Mass at launch
Technical data

Specifications

Prime contractor	Matra Marconi Space
Platform
Mass at launch
Mass in orbit
Length
Width
Height
Stabilization
DC power
Design lifetime	12 years
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	Superbeam: 52 dBW Widebeam: 49 dBW
Polarization	linear

6 transponders in 12 GHz can be switched in 11 GHz and the 36 MHz transponders can be operated in half-transponder mode.

Uplink: 13.8-14.0 GHz and 17.3-18.1 GHz


Hotbird 3

will be launched by Ariane in early 1997

should have a spot to South Africa


Program: Eutelsat 3

The supplier will be selected in the first quarter of 1995 and the contract will call for up to seven satellites, with the first available in orbit by late 1997.

The satellites will each be equiped with 24 transponders with 72 MHz bandwidth, operating in the Fixed Satellite Services (FSS) frequency band. There will be full coverage of the entire European continent and the Mediterranean Basin, as well as possibility for expansion at orbital positions covering far Eastern Europe.


 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
Launch site	Cape Canaveral
Mass at launch


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
Launch site	Kagoshima
Mass at launch


 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
Launch site	Kagoshima
Mass at launch


 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
Launch site	Kagoshima
Mass at launch
End of life

Decay	19 Jul 1989


 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


 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	Delta 3914
Launch site	Vandenberg
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
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
31 Jan 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)

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.

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
Mass at launch
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
Mass at launch
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
Launch site	Cape Canaveral
Mass at launch
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
Launch site	Wallops Island
Mass at launch
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
Launch site	Cape Canaveral
Mass at launch
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
Mass at launch


 Explorer 12

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
Launch site	Cape Canaveral
Mass at launch
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
Launch site	Cape Canaveral
Mass at launch
End of life

Decay	28 Aug 1961


 Explorer 14

Energetic Particules Explorer

Also called S 3A

General

Designation	00432 / 62051A
Launch date	2 Oct 1962
Country of origin	United States
Mission	Scientific: magnetosphere study
Perigee/Apogee	2558/96229 km
Inclination	42.3°
Period	2184.6 min
Launch vehicle
Launch site	Cape Canaveral
Mass at launch
End of life

Decay	1 Jul 1966


 Explorer 15

Energetic Particules Explorer

Also called 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
Launch site	Cape Canaveral
Mass at launch
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
Launch site	Cape Canaveral
Mass at launch


 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
Launch site	Cape Canaveral
Mass at launch
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
Launch site	Cape Canaveral
Mass at launch
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
Launch site	Vandenberg
Mass at launch

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
Launch site	Vandenberg
Mass at launch


 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
Launch site	Cape Canaveral
Mass at launch
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
Launch site	Vandenberg
Mass at launch


 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
Launch site	Cape Canaveral
Mass at launch
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
Launch site	Vandenberg
Mass at launch

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
Launch site	Vandenberg
Mass at launch


 Explorer 26

General

Designation	00963 / 64086A
Launch date	21 Dec 1964
Country of origin	United States
Mission	Scientific: ionosphere study
Perigee/Apogee	284/1043 km
Inclination	19.8°
Period	205.7 min
Launch vehicle
Launch site	Cape Canaveral
Mass at launch


 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
Launch site	Wallops Island
Mass at launch


 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
Launch site	Cape Canaveral
Mass at launch
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
Launch site	Cape Canaveral
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
Launch site	Vandenberg
Mass at launch


 Explorer 31

Also called DME A

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
Launch site	Vandenberg
Mass at launch


 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
Launch site	Cape Canaveral
Mass at launch
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
Launch site	Cape Canaveral
Mass at launch


 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
Launch site	Vandenberg
Mass at launch
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
Launch site	Vandenberg
Mass at launch


 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
Launch site	Vandenberg
Mass at launch


 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
Launch site	Vandenberg
Mass at launch

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
Launch site	Vandenberg
Mass at launch


 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
Launch site	Vandenberg
Mass at launch
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
Launch site	San Marco
Mass at launch
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
Launch site	Cape Canaveral
Mass at launch
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
Launch site	San Marco
Mass at launch
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
Launch site	Wallops Island
Mass at launch
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
Launch site	Cape Canaveral
Mass at launch


 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
Launch site	San Marco
Mass at launch
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
Inclination	28.7°
Period	17279 min
Launch vehicle
Launch site	Cape Canaveral
Mass at launch


 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
Launch site	Vandenberg
Mass at launch
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
Launch site	Vandenberg
Mass at launch
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
Launch site	San Marco
Mass at launch
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
Launch site	Vandenberg
Mass at launch
End of life

Decay	12 Mar 1976


 Explorer 55

Also 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
Launch site	Cape Canaveral
Mass at launch
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

The payload uses 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. The reentry capsule and the service module, still attached to each other, 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 between 16:00 and 16:30 UT


 Program: Express

Also called Glavstar

Russian telecommunication program replacing Gorizont. Operated by Intersputnik.

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 01


Express' specifications

Prime contractor	NPO PM
Platform	NPO Express (similar to GALS)
Mass at launch	approx 2500 kg
Mass in orbit
Diameter	2 m
Height	5 m
Solar array	twin panels
Stabilization	3 axis
DC power	2000 W
Design lifetime	5 years

Carries an advanced Xenon ion engine that reduces the amount of propellant needed to fine-tune the initial orbit and perform station-keeping maneuvers.

Beacons: 11.400 GHz (power: 0.1 W; EIRP: 14.5 dBW) and 3.800 GHz (power: 0.2 W; EIRP: 9 dBW)


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	1 global beam (17°x17°): 34 dBW 2 quasi global beams (15°x15°): 29 dBW 2 zone beams (5°x11°): 35 dBW 1 spot beam (5°x5°): 47 dBW
Polarization	RHCP
Transponder frequency chart (GHz)

Transponder	Downlink	Uplink	Comment
6	3.675	6.000	global or spot beam, 41 MHz
7	3.725	6.050	quasi global or zone beam
8	3.775	6.100	quasi global or zone beam
9	3.825	6.150	quasi global or zone beam
10	3.875	6.200	quasi global or zone beam
11	3.925	6.250	quasi global or zone beam
14	3.975	6.300	zone or spot beam
15	4.025	6.350	quasi global or zone beam
16	4.075	6.400	zone or spot beam
17	4.125	6.450	quasi global or zone beam


Express' Ku-band

Main transponders	2
Backup transponders
Power	60 W (TWTA)
Bandwidth	34 MHz
Coverage and EIRP	spot beam: 40 dBW
Polarization	linear H
Transponder frequency chart (GHz)

Transponder	Downlink	Uplink
12	11.525	14.325
20	11.675	14.425


 Express 01

General

Designation	23319 / 94067A
Launch date	13 Oct 1994 at 16:19 UT
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar 04, 14°W
Launch vehicle	Proton K
Launch site	Tyuratam LC200
Technical data

Specifications

C-band

Ku-band


Express 06

General

Designation
Launch date	planned in Apr 1995
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	80°E
Launch vehicle
Launch site
Mass at launch

GE American Communications Inc. announced it will launch a international video programming satellite service on Intersputnik Express 6 aimed at the Indian sub-continent. The television service is expected to begin July 1. 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.


 Eyesat

Also called AO-27 or Oscar 27

General

Designation	22825 / 93061C
Launch date	25 Sep 1993
Country of origin	United States
Mission	Telecommunications
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.

Technical data

Specifications

Prime contractor	Associazione Radioamatori Italiani
Platform
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


FAST

General

Designation
Launch date	planned in Jul 1995
Country of origin
Mission
Perigee/Apogee
Inclination
Period
Launch vehicle	Pegasus
Launch site
Mass at launch


 Faisat

General

Designation	23465 / 95002C
Launch date	24 Jan 1995 at 03:54 UT
Country of origin	United States
Operator	Final Analysis Incorporated
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

Faisat is store and forward communications satellite modified by FAI, an American company from an existing satellite bus whose mission was cancelled (probably a DARPA satellite). FAI plans to have 5 satellites operating in mid-1997.

FAI plans to launch a constellation of 26 such satellites -- four planes of six each at 66°, plus two birds in individual 83° orbits for polar coverage -- to build a complete low data rate LEO comsat system; Russian launchers will be used throughout. This experimental prototype also carries a small thermal-control experiment for USAF Phillips Lab.


 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 operated by USAF, US Navy and the DoD.

UHF-band (244-400 MHz)

Transponders	23
Mass	1900 kg
Capacity	1300 phone circuits


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
Launch site	Cape Canaveral
Mass at launch
Location

Begin	End	Position
L: 9 Feb 1978		100°W
Mar 1995	...	15°W


 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
Launch site	Cape Canaveral
Mass at launch
End of life

Out of service	yes


 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
Launch vehicle
Launch site	Cape Canaveral
Mass at launch


 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
Launch vehicle
Launch site	Cape Canaveral
Mass at launch


 Fleetsatcom 5

General

Designation	12635 / 81073A
Launch date	6 Aug 1981
Country of origin	United States
Mission	Military: telecommunications
Geostationary orbit
Launch vehicle
Launch site	Cape Canaveral
Mass at launch
End of life

Out of service	yes


 Fleetsatcom 6

End of life

Out of service	26 Mar 1987
Cause	Echec au lancement


 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
Launch vehicle
Launch site	Cape Canaveral
Mass at launch


 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	22.8°W
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
Mass at launch


 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 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 U
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.


 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 A
Launch site	Vandenberg
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 3
Launch site	Jiuqua
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

Technical data

Specifications

Prime contractor	Swedish Space Corp.
Mass at launch	265 kg
Stabilization	Spin stabilized
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 (S-band)


 Program: Fuji

Means "glycine flower"

Japanese small telecommunications satellite program


Program: Fuji

Fuji 1A

Fuji 1B


 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
Launch site	Tanegashima
Mass at launch


 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
Launch site
Mass at launch
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


 Program: Galaxy

Operated by Hugues Communications Inc (HCI)

Contact

Hugues Communications Inc.

PO Box 82424, Worldway Postal Center, Los Angeles, CA 90009, USA

Tel: +1-213-607-4003

Fax: +1-213-607-4065


Program: Galaxy

Galaxy 1

Galaxy 1R

Galaxy 1R failure

Galaxy 2

Galaxy 3

Galaxy 4

Galaxy 5

Galaxy 6

Galaxy 7


Galaxy 1, 2, 3 & 5's specifications

Prime contractor	Hugues
Platform	HS 376
Mass at launch	1200 kg
Mass in orbit	654 kg
Diameter	2.16 m
Height	6.6 m stowed
Stabilization	Spin stabilized
DC power	BOL: 990 W
Design lifetime	10 years


Galaxy 1, 2, 3 & 5's C-band

Main transponders	24
Backup transponders	6
Power	9 W (TWTA)
Bandwidth	36 MHz
Coverage
EIRP	34 dBW
Polarization	linear


Galaxy 4 & 7's specifications

Prime contractor	Hugues
Platform	HS 601
Mass at launch	2950 kg
Mass in orbit	BOL: 1692 kg EOL: 1320 kg
Length	2.27 m
Width	2.27 m
Height	2.27 m
Solar array	24.7 m span
Stabilization	3 axis
DC power	BOL: 6000 W EOL: 4700 W
Design lifetime	15 years


Galaxy 4 & 7's C-band

Main transponders	24
Backup transponders	6
Power	16 W (SSPA)
Bandwidth	36 MHz
Coverage
EIRP	40.1 dBW
Polarization	linear


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	45 dBW
Polarization	linear


 Galaxy 1

General

Designation	14158 / 83065A
Launch date	28 Jun 1983
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	133°W
Launch vehicle	Delta 3920
Launch site	Cape Canaveral
End of life

Out of service	yes
Technical data

Specifications

C-band

Transponder frequency chart (GHz)

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


 Galaxy 1R failure

General

Designation	n/a
Launch date	23 Aug 1992
Country of origin	United States
Mission	Telecommunications
Geostationary orbit
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
Mass at launch
End of life

Out of service	23 Aug 1992
Cause	Fail to orbit because the launcher's 3rd stage malfunctioned


 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 7925
Launch site	Cape Canaveral
Mass at launch
Technical data

Specifications

Prime contractor	Hugues
Platform	HS-376
Mass at launch
Mass in orbit
Length
Width
Height
Stabilization	Spin stabilized
DC power
Design lifetime
C-band

Main transponders	24
Backup transponders	6
Power	16 W (SSPA)
Bandwidth	36 MHz
Coverage
EIRP
Polarization	linear
Transponder frequency chart (GHz)

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


 Galaxy 2

General

Designation	14365 / 83098A
Launch date	22 Sep 1983
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	74°W
Launch vehicle	Delta 3920
Launch site	Cape Canaveral
Mass at launch
End of life

Out of service	yes?
Technical data

Specifications

C-band

Transponder frequency chart (GHz)

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


 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	Delta 3920
Launch site	Cape Canaveral
Technical data

Specifications

C-band

Transponder frequency chart (GHz)

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


Galaxy 3R

General

Designation
Launch date	planned in Sep 1995
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	95°W
Launch vehicle	Atlas 2A
Launch site	Cape Canaveral
Mass at launch

Using a combination of digital compression and tightly focused spot beams, Galaxy III-R will use 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-centimeter) dishes.

In 1998, an even more powerful satellite, Hughes Communications' Galaxy VIII-(I) International, will transmit the DIRECTV Latin America programming, subject to FCC approval.


 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
Technical data

Specifications

C-band

Ku-band

EIRP C-band coverage (dBW)

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.

C-band transponder frequency chart (GHz)

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

Horizontal Uplink	Horizontal Downlink	Transponder	Vertical Uplink	Vertical Downlink
14.020	11.720	1
		2	14.050	11.750
14.050	11.750	3
14.080	11.780	4
		5	14.110	11.810
14.110	11.810	6
14.140	11.840	7
		8	14.170	11.870
14.170	11.870	9
14.200	11.900	10
		11	14.230	11.930
14.230	11.930	12
14.260	11.960	13
		14	14.290	11.990
14.290	11.990	15
14.320	12.020	16
		17	14.350	12.050
14.350	12.050	18
14.380	12.080	19
		20	14.410	12.110
14.410	12.110	21
14.440	12.140	22
		23	14.470	12.170
14.470	12.170	24

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 4's EIRP (C-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 1
Launch site	Cape Canaveral
Technical data

Specifications

C-band

Transponder frequency chart (GHz)

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


 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.

Location

Begin	End	Position
L: 12 Oct 1990		93°W
		99°W
	Oct 1993	103°W
May 1994	Feb 1995...	74°W
Technical data

EIRP coverage (dBW)

Horizontal

Vertical

Specifications

Prime contractor	Hugues
Platform	HS 376
Mass at launch	1212 kg
Mass in orbit	708 kg
Diameter	2.16 m
Height	6.6 m stowed
Stabilization	Spin stabilized
DC power	990 W
Design lifetime	10 years
C-band

Main transponders	24
Backup transponders	6
Power	10.2 W (TWTA)
Bandwidth	36 MHz
Coverage
EIRP	39 dBW
Polarization	linear
Transponder frequency chart (GHz)

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


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
Technical data

Specifications

C-band

Ku-band

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.

C-band transponder frequency chart (GHz)

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

Horizontal Uplink	Horizontal Downlink	Transponder	Vertical Uplink	Vertical Downlink
		1	14.020	11.720
14.050	11.750	2
		3	14.050	11.750
		4	14.080	11.780
14.110	11.810	5
		6	14.110	11.810
		7	14.140	11.840
14.170	11.870	8
		9	14.170	11.870
		10	14.200	11.900
14.230	11.930	11
		12	14.230	11.930
		13	14.260	11.960
14.290	11.990	14
		15	14.290	11.990
		16	14.320	12.020
14.350	12.050	17
		18	14.350	12.050
		19	14.380	12.080
14.410	12.110	20
		21	14.410	12.110
		22	14.440	12.140
14.470	12.170	23
		24	14.470	12.170

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 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)


 Program: GALS

Soviet direct TV program operated by Intersputnik.

The system should count 5 satellites and allow DTH with 60 to 90 cm antennas.


Program: GALS

GALS 1


 GALS 1

General

Designation	22963 / 94002A
Launch date	20 Jan 1994
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	71°E
Launch vehicle	Proton
Launch site	Tyuratam
Technical data

Specifications

Prime contractor	NPO PM
Platform	NPO GALS
Mass at launch	approx 2500 kg
Mass in orbit
Diameter	2.5 m
Solar array	twin panels
Stabilization	3 axis
DC power
Design lifetime	7 years
Ku-band (12/18 GHz)

Main transponders	6
Backup transponders
Power	150-300 W (TWTA)
Bandwidth	24 MHz
Coverage
EIRP	60 dBW
Polarization


GALS 2

for 1995


GALS 3

for 1996


 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
Launch site	Tyuratam
Mass at launch
End of life

Decay	28 Feb 1992


 GEO-IK

General

Designation	23411 / 94078A
Launch date	24 Nov 1994 at 02:54 UT
Country of origin	CIS
Mission	Scientific: geodetic survey
Perigee/Apogee	1480/1526 km
Inclination	73.6°
Period	116 min
Launch vehicle	Tsiklon 3
Launch site	Plesetsk LC32
Mass at launch

It also carried an experimental Elekon positioning equipment to monitor movements of land and sea transportations, to optimize and increase efficiency.


 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
Launch site	Vandenberg
Mass at launch	241 kg

Mission: Ocean and islands map-making.


 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
Launch site
Mass at launch


 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, known as catalog number 23557.

25 observatories all over the world will execute measurements by laserreflections. Stations are among others: London, Grasse (France), Potsdam,Easterisland, Graz (Austria) and even one in Kirgizie. The stations can 'catch' GFZ-1 with a beamwidth of 200 meters.

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
Launch site	Vandenberg
Mass at launch


 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
Launch site	Vandenberg
Mass at launch


 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
Launch site	Vandenberg
Mass at launch


 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
Launch site	Vandenberg
Mass at launch


 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
Launch site	Vandenberg
Mass at launch


Program: Globalstar

Operated by Qualcom Inc

McDonnell Douglas Corp.  has been awarded a contract valued at about $50 million with SpaceSystems/Loral for the inaugural launch of the Globalstar telecommunications system. The contract also provides for optional additional launches. The Globalstar satellites will be launched in 1997 from Cape Canaveral Air Station, Fla., on a two-stage version of the Delta II rocket. The Delta II rocket will be placing four satellites in a transfer orbit for Loral.

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.

The telecommunications system will consist of a constellation of 48 LEO satellites in circular orbits at 756 nautical miles altitude. These satellites will be launched into eight orbital planes, with six satellites in each plane to provide continuous global coverage. Commercial service is anticipated early in 1998.


 Program: Glonass

Russian navigation program

Planes and slots

Slot	Plane 1 RAAN: 103	Plane 2 RAAN: 222	Plane 3 RAAN: 343
1	769 (Cosmos 2179)
2	757 (Cosmos 2236)
3	763 (Cosmos 2295)
4	762 (Cosmos 2294)
5	249 (Cosmos 2111)
6	764 (Cosmos 2296)
7	759 (Cosmos 2235)
8	769 (Cosmos 2178)
12		767 (Cosmos 2287)
14		770 (Cosmos 2288)
16		775 (Cosmos 2289)
17			760 (Cosmos 2276)
18			758 (Cosmos 2275)
20			765 (Cosmos 2307)
21			556 (Cosmos 2204)
22			766 (Cosmos 2308)
23			761 (Cosmos 2277)
24			774 (Cosmos 2206)
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel


 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


Program: GMS

GMS 1

GMS 2

GMS 3

GMS 4

GMS 5


GMS's specifications

Prime contractor	Hugues/NEC
Platform	HS 378
Mass at launch	682 kg
Diameter	2.15 m
Height	3.45 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	Delta
Launch site	Cape Canaveral
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
Launch site	Tanegashima
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
Launch site	Tanegashima
Location

Begin	End	Position
L: 2 Aug 1984		140°E
Feb 1995		119.8°E
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	140°E
Launch vehicle	H1
Launch site	Tanegashima
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 at 08:01 UT
Country of origin	Japan
Mission	Meteorology
Geostationary orbit	140°E
Launch vehicle	H2
Launch site	Tanegashima
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)


Program: Goes

Goes 1

Goes 2

Goes 3

Goes 4

Goes 5

Goes 6

Goes 7

Goes 8


Goes 6 & 7's specifications

Prime contractor	Hugues
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 equiped 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 1

Also called SMS 3

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
Launch site	Cape Canaveral
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

Transmits on 136.38 MHz


 Goes 2

General

Designation	10061 / 77048A
Launch date	16 Jun 1977
Country of origin	United States
Mission	Meteorology
Geostationary orbit	see below
Launch vehicle
Launch site	Cape Canaveral
Mass at launch
Location

Begin	End	Position
L: 16 Oct 1975		105°W
24 Oct 1993		135.95°W; inclination: 9.4°
End of life

Out of service	yes?
Technical data

Downlink frequency: 136.38, 1691 and 2297.5925 MHz


 Goes 3

General

Designation	10953 / 78062A
Launch date	16 Jun 1978
Country of origin	United States
Mission	Meteorology
Geostationary orbit	see below
Launch vehicle
Launch site	Cape Canaveral
Mass at launch
Location

Begin	End	Position
L: 16 Jun 1978		60°E
24 Oct 1993		176.2°W, inclination: 8°
End of life

Out of service	yes?
Technical data

Transmits on 136.38 MHz (frequency drifts caused by temperature variations)


 Goes 4

General

Designation	11964 / 80074A
Launch date	9 Sep 1980
Country of origin	United States
Mission	Meteorology
Geostationary orbit	135°W
Launch vehicle
Launch site	Cape Canaveral
Mass at launch
End of life

Out of service	yes


 Goes 5

General

Designation	12472 / 81049A
Launch date	22 May 1981
Country of origin	United States
Mission	Meteorology
Geostationary orbit	75°W
Launch vehicle
Launch site	Cape Canaveral
Mass at launch	900 kg
End of life

Out of service	yes?


 Goes 6

General

Designation	14050 / 83041A
Launch date	28 Apr 1983
Country of origin	United States
Mission	Meteorology
Geostationary orbit	see below
Launch vehicle	Delta
Launch site	Cape Canaveral

Mission: high altitude windspeed and direction monitoring (via cloud movement); high altitude cloud top detectin (electrical storms, tornadoes); sea surface temperature mapping, etc. Image acquisition, distribution of image data and other met info, collection and relay of weather data from data collection platforms (DCPs) - land, sea, airborne.

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 7

General

Designation	17561 / 87022A
Launch date	26 Feb 1987
Country of origin	United States
Mission	Meteorology
Geostationary orbit	see below
Launch vehicle	Delta
Launch site	Cape Canaveral

Mission: high altitude windspeed and direction monitoring (via cloud movement); high altitude cloud top detectin (electrical storms, tornadoes); sea surface temperature mapping, etc. Image acquisition, distribution of image data and other met info, collection and relay of weather data from data collection platforms (DCPs) - land, sea, airborne.

Location

Begin	End	Position
L: 26 Feb 1987	1989	79.5°W
1989	?	98°W
Feb 1995	...	136°W
Technical data

Specifications

Payload

Transmits in VHF-, L- and S-band


 Goes 8

General

Designation	23051 / 94022A
Launch date	13 Apr 1994 at 20:44 UT
Country of origin	United States
Mission	Meteorology
Geostationary orbit	75°W
Launch vehicle	Atlas 1
Launch site	Cape Canaveral
Mass at launch

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.

Technical data

Transmits in VHF-, L- and S-band


Goes J

General

Designation
Launch date	planned in Jun 1995
Country of origin	United States
Mission	Meteorology
Geostationary orbit
Launch vehicle	Atlas 1
Launch site	Cape Canaveral
Mass at launch

is to replace Goes 7


 Program: Gorizont

The Gorizont satellite system is a general purpose network for communications operated by Intersputnik.


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's specifications

Prime contractor	NPO PM
Platform	NPO Gorizont
Mass at launch	2500 kg
Diameter	about 2 m
Height	about 5 m
Stabilization	3 axis
DC power	approx. 4000 W
Design lifetime	3 years

Those are the specifications of the most recent Gorizont. They also are equiped with 1 X or L band transponder.


Gorizont's C-band

Main transponders	6
Backup transponders
Power	1 spot transponder of 40 W (TWTA) 5 transponders of 15 W (TWTA)
Bandwidth	spot: 40 MHz others: 34 MHz
Coverage	spot: 40 W others: 15 W
EIRP	Spot: 45 dBW Hemispheric: 32 dBW Global: 29 dBW
Polarization	circular R
Frequencies	Uplink: 5.975-6.275 GHz Downlink: 3.65-3.95 GHz

Those are the specifications of the most recent Gorizont


Gorizont's Ku-band

Main transponders	1
Backup transponders
Power	20 W (TWTA)
Bandwidth	68 dBW
Coverage
EIRP	40 dBW
Polarization	circular L
Frequencies	Uplink: 14.308-14.342 GHz Downlink: 11.508-11.542 GHz

Those are the specifications of the most recent Gorizont


Gorizont's transponder frequency chart (GHz)

LHCP Downlink	Transponder	RHCP Downlink
	6	3.675
	7	3.725
	8	3.775
	9	3.825
	10	3.875
	11	3.925
11.525	K1


 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
Launch site	Tyuratam
End of life

Out of service	yes
Technical data

Specifications

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
Launch site	Tyuratam
End of life

Out of service	yes
Technical data

Specifications

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
Launch site	Tyuratam
End of life

Out of service	yes
Technical data

Specifications

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
Launch site	Tyuratam

Launched to broadcast the Olympic Games

End of life

Out of service	yes
Technical data

Specifications

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
Launch site	Tyuratam
End of life

Out of service	yes
Technical data

Specifications

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
Launch site	Tyuratam
End of life

Out of service	yes
Technical data

Specifications

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
Launch site	Tyuratam
End of life

Out of service	yes
Technical data

Specifications

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
Launch site	Tyuratam
End of life

Out of service	yes
Technical data

Specifications

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
Launch site	Tyuratam
End of life

Out of service	yes
Technical data

Specifications

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
Launch site	Tyuratam
End of life

Out of service	yes
Technical data

Specifications

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
Launch site	Tyuratam
End of life

Out of service	yes
Technical data

Specifications

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
Launch site	Tyuratam
End of life

Out of service	yes
Technical data

Specifications

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
Launch site	Tyuratam
End of life

Out of service	yes
Technical data

Specifications

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
Launch site	Tyuratam
End of life

Out of service	yes
Technical data

Specifications

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
Launch site	Tyuratam
End of life

Out of service	yes
Technical data

Specifications

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
Launch site	Tyuratam
End of life

Out of service	yes
Technical data

Specifications

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
Launch site	Tyuratam
Location

Begin	End	Position
L: 26 Jan 1989	?	Statsionar 05, 53°E
End of life

Out of service	1993
Technical data

Specifications

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
Launch vehicle	Proton
Launch site	Tyuratam
Technical data

Specifications

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	Statsionar 14, 96.5°E
Launch vehicle	Proton
Launch site	Tyuratam
Technical data

Specifications

C-band

Ku-band

Transponder frequency chart

EIRP coverage (dBW)

C-band, global

C-band, hemispheric


Gorizont 19's C-band EIRP (global)


Gorizont 19's C-band EIRP (hemispheric)


 Gorizont 20

General

Designation	20659 / 90054A
Launch date	20 Jun 1990
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar 04, 14°W
Launch vehicle	Proton
Launch site	Tyuratam
Technical data

Specifications

C-band

Ku-band

Transponder frequency chart


 Gorizont 21

General

Designation	20923 / 90094A
Launch date	3 Nov 1990
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Proton
Launch site	Tyuratam
Location

Begin	End	Position
L: 3 Nov 1990		Statsionar 06, 90°E
		Statsionar 16, 145°E
Technical data

Specifications

C-band

Ku-band

Transponder frequency chart


 Gorizont 22

General

Designation	20953 / 90102A
Launch date	23 Nov 1990
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar 12, 40°E
Launch vehicle	Proton
Launch site	Tyuratam
Technical data

Specifications

C-band

Ku-band

Transponder frequency chart

EIRP coverage (dBW)

C-band, global

C-band, hemispheric


Gorizont 22's C-band EIRP (global)


Gorizont 22's C-band EIRP (hemispheric)


 Gorizont 23

General

Designation	21533 / 91046A
Launch date	2 Jul 1991
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar 21, 103°E
Launch vehicle	Proton
Launch site	Tyuratam
End of life

Out of service	yes
Technical data

Specifications

C-band

Ku-band

Transponder frequency chart


 Gorizont 24

General

Designation	21759 / 91074A
Launch date	23 Oct 1991
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar 13, 80°E
Launch vehicle	Proton
Launch site	Tyuratam
Technical data

Specifications

C-band

Ku-band

Transponder frequency chart

EIRP coverage (dBW)

C-band, global

C-band, hemispheric


Gorizont 24's C-band EIRP (global)


Gorizont 24's C-band EIRP (hemispheric)


 Gorizont 25

General

Designation	21922 / 92017A
Launch date	2 Apr 1992
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar 21, 103°E
Launch vehicle	Proton
Launch site	Tyuratam
Technical data

Specifications

C-band

Ku-band

Transponder frequency chart

EIRP coverage (dBW)

C-band, global

C-band, hemispheric


Gorizont 25's C-band EIRP (global)


Gorizont 25's C-band EIRP (hemispheric)


 Gorizont 26

General

Designation	22041 / 92043A
Launch date	14 Jul 1992
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar 11, 11°W
Launch vehicle	Proton
Launch site	Tyuratam
Technical data

Specifications

C-band

Ku-band

Transponder frequency chart

EIRP coverage (dBW)

C-band, global

C-band, hemispheric


Gorizont 26's C-band EIRP (global)


Gorizont 26's C-band EIRP (hemispheric)


 Gorizont 27

General

Designation	22245 / 92082A
Launch date	27 Nov 1992
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar 05, 53°E
Launch vehicle	Proton
Launch site	Tyuratam
Technical data

Specifications

C-band

Ku-band

Transponder frequency chart

EIRP coverage (dBW)

C-band, global

C-band, hemispheric


Gorizont 27's C-band EIRP (global)


Gorizont 27's C-band EIRP (hemispheric)


 Gorizont 28

General

Designation	22880 / 93069A
Launch date	28 Oct 1993
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar 06, 90°E
Launch vehicle	Proton
Launch site	Tyuratam
Technical data

Specifications

C-band

Ku-band

Transponder frequency chart

EIRP coverage (dBW)

C-band, global

C-band, hemispheric


Gorizont 28's C-band EIRP (global)


Gorizont 28's C-band EIRP (hemispheric)


 Gorizont 29

Also called Rimsat 1

General

Designation	22907 / 93072A
Launch date	18 Nov 1993
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	130°E
Launch vehicle	Proton
Launch site	Tyuratam

Leased to the US-Malaysian Rimsat company that intends to offer telecommunications services over Asia and the Pacific region. Rimsat will use the satellite 3 years for a cost of $12 million

Contact

Rimsat Ltd

1911 Production Way, Fort Wayne, IN 46808, USA

Tel: +1-219-484-6474

Fax: +1-219-484-4547

Technical data

Specifications

C-band

Ku-band

Transponder frequency chart

EIRP coverage (dBW)

C-band, global

C-band, zone


Gorizont 29's C-band EIRP (global)


Gorizont 29's C-band EIRP (zone)


 Gorizont 30

Also called Rimsat 2

General

Designation	23108 / 94030A
Launch date	20 May 1994 at 02:01 UT
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	142.5°E
Launch vehicle	Proton K
Launch site	Tyuratam

Leased to the US-Malaysian Rimsat company.

Contact

Rimsat Ltd

1911 Production Way, Fort Wayne, IN 46808, USA

Tel: +1-219-484-6474

Fax: +1-219-484-4547

Technical data

Specifications

C-band

Ku-band

Transponder frequency chart


 Program: GPS

Global Positionary Satellite

Also called Navstar (NAVigation System using Tuning 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 equiped with atomic clocks.

The IIA satellites series were built by Rockwell

Planes and slots

Plane	RAAN of plane	Slot 1	Slot 2	Slot 3	Slot 4
A	245	2-21	2-12	2-15	2-04
B	305	2-18	2-07	2-02	2-22
C	6	2-24	2-13	2-19	2-20
D	69	2-11	2-09	2-05	2-23
E	129	2-01	2-08	2-03	2-10
F	186	2-16	2-14	2-06	2-17


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 BI-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
Launch site	Vandenberg
Mass at launch
End of life

Out of service	July 1985


 GPS BI-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
Launch site	Vandenberg
Mass at launch
End of life

Out of service	September 1985


 GPS BI-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
Launch site	Vandenberg
Mass at launch


 GPS BI-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
Launch site	Vandenberg
Mass at launch
End of life

Out of service	14 Oct 1989


 GPS BI-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
Launch site	Vandenberg
Mass at launch
End of life

Out of service	May 1985


 GPS BI-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
Launch site	Vandenberg
Mass at launch
End of life

Out of service	11 Dec 1990


 GPS BI-07

End of life

Out of service	18 Dec 1981
Cause	Launch failure


 GPS BI-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
Launch site	Vandenberg
Mass at launch
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

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
Launch site	Vandenberg
Mass at launch
Technical data

Transmits on 1575.42 and 1227.6 MHz


 GPS BI-10

Also called USA 005

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
Launch site	Vandenberg
Mass at launch
Technical data

Transmits on 1575.42 and 1227.6 MHz


 GPS BI-11

Also called USA 010

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
Launch site	Vandenberg
Mass at launch

Deactivated on 13 Apr 1994

Technical data

Transmits on 1575.42 and 1227.6 MHz


 GPS BII-01

Also called USA 035

General

Designation	19802 / 89013A
Launch date	14 Feb 1989
Country of origin	United States
Mission	Navigation
Perigee/Apogee	20088/20274 km
Inclination	55.2°
Period	717.9 min
Launch vehicle	Delta
Launch site	Cape Canaveral
Mass at launch
Technical data

Transmits on 1575.42 and 1227.6 MHz


 GPS BII-02

Also called USA 038

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
Launch site	Cape Canaveral
Mass at launch
Technical data

Transmits on 1575.42 and 1227.6 MHz


 GPS BII-03

Also called USA 042

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
Launch site	Cape Canaveral
Mass at launch
Technical data

Transmits on 1575.42 and 1227.6 MHz


 GPS BII-04

Also called USA 047

General

Designation	20302 / 89085A
Launch date	21 Oct 1989
Country of origin	United States
Mission	Navigation
Perigee/Apogee	20176/20188 km
Inclination	54.3°
Period	718 min
Launch vehicle
Launch site	Cape Canaveral
Mass at launch
Technical data

Transmits on 1575.42 and 1227.6 MHz


 GPS BII-05

Also called USA 049

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
Launch site	Cape Canaveral
Mass at launch
Technical data

Transmits on 1575.42 and 1227.6 MHz


 GPS BII-06

Also called USA 050

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
Launch site	Cape Canaveral
Mass at launch
Technical data

Transmits on 1575.42 and 1227.6 MHz


 GPS BII-07

Also called USA 054

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	Douglas 2
Launch site	Cap Canaveral
Mass at launch
Technical data

Transmits on 1575.42 and 1227.6 MHz


 GPS BII-08

Also called USA 063

General

Designation	20724 / 90068A
Launch date	2 Aug 1990
Country of origin	United States
Mission	Navigation
Perigee/Apogee	19891/20473 km
Inclination	54.8°
Period	718 min
Launch vehicle
Launch site	Cape Canaveral
Mass at launch
Technical data

Transmits on 1575.42 and 1227.6 MHz


 GPS BII-09

Also called USA 064

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
Launch site	Cape Canaveral
Mass at launch
Technical data

Transmits on 1575.42 and 1227.6 MHz


 GPS BIIA-10

Also called USA 066

General

Designation	20959 / 90103A
Launch date	26 Nov 1990
Country of origin	United States
Mission	Navigation
Perigee/Apogee	19968/20394 km
Inclination	55°
Period	718 min
Launch vehicle
Launch site	Cape Canaveral
Mass at launch
Technical data

Transmits on 1575.42 and 1227.6 MHz


 GPS BIIA-11

Also called USA 071

General

Designation	21552 / 91047A
Launch date	4 Jul 1991
Country of origin	United States
Mission	Navigation
Perigee/Apogee	20031/20331 km
Inclination	55.9°
Period	718 min
Launch vehicle
Launch site	Cape Canaveral
Mass at launch
Technical data

Transmits on 1575.42 and 1227.6 MHz


 GPS BIIA-12

Also called USA 079

General

Designation	21890 / 92009A
Launch date	23 Feb 1992
Country of origin	United States
Mission	Navigation
Perigee/Apogee	20031/20335 km
Inclination	54°
Period	718 min
Launch vehicle
Launch site	Cape Canaveral
Mass at launch
Technical data

Transmits on 1575.42 and 1227.6 MHz


 GPS BIIA-13

Also called USA 080

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
Launch site	Cape Canaveral
Mass at launch
Technical data

Transmits on 1575.42 and 1227.6 MHz


 GPS BIIA-14

Also called USA 083

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
Launch site	Cape Canaveral
Mass at launch
Technical data

Transmits on 1575.42 and 1227.6 MHz


 GPS BIIA-15

Also called USA 084

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
Launch site	Cape Canaveral
Mass at launch
Technical data

Transmits on 1575.42 and 1227.6 MHz


 GPS BIIA-16

Also called USA 085

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 7 925
Launch site	Cape Canaveral
Mass at launch
Technical data

Transmits on 1575.42 and 1227.6 MHz


 GPS BIIA-17

Also called USA 087

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
Launch site	Cape Canaveral
Mass at launch
Technical data

Transmits on 1575.42 and 1227.6 MHz


 GPS BIIA-18

Also called USA 088

General

Designation	22446 / 93007A
Launch date	3 Feb 1993
Country of origin	United States
Mission	Navigation
Perigee/Apogee	19995/20370 km
Inclination	54.5°
Period	718 min
Launch vehicle
Launch site	Cape Canaveral
Mass at launch
Technical data

Transmits on 1575.42 and 1227.6 MHz


 GPS BIIA-19

Also called USA 090

General

Designation	22581 / 93017A
Launch date	30 Mar 1993
Country of origin	United States
Mission	Navigation
Perigee/Apogee	20072/20293 km
Inclination	55.2°
Period	718 min
Launch vehicle
Launch site	Cape Canaveral
Mass at launch
Technical data

Transmits on 1575.42 and 1227.6 MHz


 GPS BIIA-20

Also called USA 091

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
Launch site	Cape Canaveral
Mass at launch
Technical data

Transmits on 1575.42 and 1227.6 MHz


 GPS BIIA-21

Also called USA 092

General

Designation	22700 / 93042A
Launch date	26 Jun 1993
Country of origin	United States
Mission	Navigation
Perigee/Apogee	20112/20250 km
Inclination	54.4°
Period	717.9 min
Launch vehicle
Launch site	Cape Canaveral
Mass at launch
Technical data

Transmits on 1575.42 and 1227.6 MHz


 GPS BIIA-22

Also called USA 094

General

Designation	22779 / 93054A
Launch date	30 Aug 1993
Country of origin	United States
Mission	Navigation
Perigee/Apogee	20127/20236 km
Inclination	54.6°
Period	718 min
Launch vehicle
Launch site	Cape Canaveral
Mass at launch
Technical data

Transmits on 1575.42 and 1227.6 MHz


 GPS BIIA-23

Also called USA 096

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
Launch site	Cape Canaveral
Mass at launch
Technical data

Transmits on 1575.42 and 1227.6 MHz


 GPS BIIA-24

Also called USA 100

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
Launch site	Cape Canaveral
Mass at launch
Technical data

Transmits on 1575.42 and 1227.6 MHz


 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
Mass at launch

Astronomy satellite carrying the French Sigma telescope


 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
Technical data

Specifications

Prime contractor	TRW
Length	7.7 m
Width	5.5 m
Height	4.6 m
Stabilization	3 axis
DC power	EOL: 3980 W
Design lifetime	2 years (min)
BATSE (Burst and Transcient Source Experiment)

Payload mass	976 kg
Industrial responsibility	Marshall SFC
Gamma-ray energy range	20-600 keV

Equiped 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


 Program: Gstar

American telecommunication satellite program operated by GE Americom

Contact

GE Americom

4 Research Way, Princeton, NJ 08540-6684, USA

Tel: +1-609-987-4419


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
Length	1.63 m
Width	1.32 m
Height	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	20 W: 38 dBW 27 W: 48 dBW
Polarization	linear


Gstar's transponder frequency chart (GHz)

Horizontal Uplink	Horizontal Downlink	Transponder	Vertical Uplink	Vertical Downlink
14.030	11.730	1
		9	14.044	11.744
14.091	11.791	2
		10	14.105	11.805
14.152	11.852	3
		11	14.166	11.866
14.213	11.913	4
		12	14.227	11.927
14.274	11.974	5
		13	14.288	11.988
14.335	12.035	6
		14	14.349	12.049
14.396	12.096	7
		15	14.410	12.110
14.457	12.157	8
		16	14.471	12.171


 Gstar 1

General

Designation	15677 / 85035A
Launch date	8 May 1985
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	103°W
Launch vehicle	Ariane V13
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	125°W
Launch vehicle	Ariane V17
Technical data

Specifications

Ku-band

Transponder frequency chart


 Gstar 3

General

Designation	19483 / 88081A
Launch date	8 Sep 1988
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	93°W
Launch vehicle	Ariane V25

This satellite has a motor problem and so is inclined.

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	105°W
Launch vehicle	Ariane V40
Technical data

Specifications

Ku-band

Transponder frequency chart


 Gurwin 1

Also called Techsat 1

General

Designation	n/a
Launch date	28 Mar 1995
Country of origin	Israel
Mission	Telecommunications
Perigee/Apogee	n/a
Inclination	n/a
Period	n/a
Launch vehicle	Start 1 (refurbished SS-25 ballistic missile)
Launch site	Plesetsk
End of life

Cause	Launcher failure (fifth stage 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 cable of 1200 bps BPSK.

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


 Healthsat

General

Designation	22827 / 93061E
Launch date	25 Sep 1993
Country of origin	United States
Operator	SateLife
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.

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


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


 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

Equiped with a 58 cm diameter telescope

End of life

Decay	25 Mar 1982


 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


Program: Helios

In Greek mythology Helios was all-seeing and all-knowing

European military observations satellite. It is financed by France (79%), Italy (14%) and Spain (7%).

Helios 1A should be launched in 1995. only optical Helios 1B is for 1996 (10 MF)

Orbit: LEO, Polar, Sun-synchronous

Re-visit period: about 1 day

Specifications

Prime contractor	Matra Marconi Space under control of the CNES
Platform	Spot (Matra)
Mass at launch	2500 kg
Mass in orbit
Length
Width
Height
Stabilization
DC power	2200 W
Design lifetime	5 years

Helios 2 is scheduled for 2002 It is supposed to cost between $1.5 and $3 million. optical and IR

the futur radar satellite Osiris (electromagnetic reconnaissance) should cost $2.4 million

Also planned: Zenon (eavesdropping satellite)


 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
Launch site	Cape Canaveral
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
Launch site	Vandenberg
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


HETE

High-Energy Transient Experiment

General

Designation
Launch date	planned in Jul 1995
Country of origin	United States
Mission	Scientific
Perigee/Apogee
Inclination
Period
Launch vehicle	Pegasus XL
Launch site	Cape Canaveral
Mass at 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.

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).


 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. The data it provided was recalculated to match his orbit position. With its high precision numerous double stars were discovered.

End of life

Out of service	15 Aug 1993
Cause	Stopped transmitting
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
Hipparcos catalog

No of target stars	120,000
Measurement accuracy	0.002 arcsecs
Tycho catalog

No of target stars	> 400,000
Measurement accuracy	0.03 arcsecs


 Program: Hispasat

Spanish telecommunication program operated by Hispasat S.A.

Contact

Hispasat S.A.

Gobelas 41-45 Planta, 28023 Madrid -- SPAIN

Tel: +34-1-307-6040

Fax: +34-1-307-6683


Program: Hispasat

Hispasat 1A

Hispasat 1B


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
Length	2.21 m
Width	1.7 m
Height	1.9 m
Solar array	22.02 m
Stabilization	3 axis
DC power	3237 W
Design lifetime	10 years


Hispasat's direct TV mission (Ku-DBS-band)

Main transponders	3
Backup transponders	1
Power	110 W (TWTA)
Bandwidth	27 MHz
EIRP	58 dBW
Polarization	circular L


Hispasat's telecommunication to Europe mission

Main transponders	8
Backup transponders	4
Power	50 W (TWTA)
Bandwidth	72 & 36 MHz
EIRP	51 dBW
Polarization	linear


Hispasat's telecommunication to America mission (Ku-band)

Main transponders	2
Backup transponders	1
Power	110 W (TWTA)
Bandwidth	36 MHz
Coverage and EIRP	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	42 dBW
Polarization


Hispasat's transponder frequency chart (GHz)

LHCP	Horizontal	Transponder	Vertical	Coverage
	11.517	19 / 7	11.517	Europe
	11.597	20 / 8	11.597	Europe
	11.668	21 / 9	11.668	Europe
		15	12.015	Europe to America
		6	12.078	Europe to America
12.149		23		DBS to Europe
12.226		27		DBS to Europe
12.303		31		DBS to Europe
12.380		35		DBS to Europe
12.456		39		DBS to Europe
	12.517	16		America to Europe
	12.540	10 / 1	12.540	Europe
	12.591	11 / 2	12.591	Europe
	12.597	17		America to Europe?
	12.631	12 / 3	12.631	Europe
	12.668	18		America to Europe
	12.671	13 / 4	12.671	Europe
	12.711	14 / 5	12.711	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
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


 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


 Hiten

Means "elf", also called Muses A

General

Designation	20448 / 90007A
Launch date	24 Jan 1990
Country of origin	Japan
Mission	Scientific: magnetophere study
Perigee/Apogee	n/a
Inclination	n/a
Period	n/a
Launch vehicle	Mu 3S 2
Launch site	Kagoshima
Mass at launch

Launched with Hagoromo


 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	592/609 km
Inclination	28.4°
Period	96.7 min
Launch vehicle	STS 32

The satellite was designed by Lynan Spitzer and proposed to NASA in the early 60ies. Was repared in 1993 by STS 61

Cost: $3 billion

Technical data

Specifications

Prime contractor	Lockheed (spacecraft) Perkin Elmer (mirror & telescope)
Mass at launch	11250 kg
Diameter	4.25 m
Height	13.1 m
Stabilization	3 axis
DC power	BOL: 5500 W
Design lifetime	15 years
Payload

Wide-field Planetary Camera, Faint Object Camera (ESA), Faint Object Spectrograph, High Resolution Spectrograph, High Speed Photometer

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


 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.


 Program: IMEWS

Integrated Multipurpose Early Warning Satellite

American military program designed to warn on rocket launch or warhead fall. Equiped with IR detectors.


 Informator

Also called AO-21 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
Launch site	Plesetsk
Mass at launch
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


 Injun 3

General

Designation	00504 / 62067B
Launch date	13 Dec 1962
Country of origin	United States
Mission
Perigee/Apogee	240/2406 km
Inclination	70.3°
Period	112.1 min
Launch vehicle
Launch site	Vandenberg
Mass at launch
End of life

Decay	25 Aug 1968


 Program: Inmarsat

INternational MARitime SATellite

Inmarsat was created by the International Maritim Organization (dependent of the United Nations) on 16 Jul 1979. Its center is in London; 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 so that the CIS could enter it.

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.

Contact

Inmarsat Ltd

40 Melton Street, NW1 2EE, London, United Kingdom

Tel: +44-171-728-1000

Fax: +44-171-728-1044


Program: Inmarsat

Inmarsat 2F1

Inmarsat 2F2

Inmarsat 2F3

Inmarsat 2F4


Inmarsat 2's specifications

Prime contractor	Britsh Aerospace
Platform	Eurostar
Mass at launch	1310 kg
Mass in orbit	BOL: 824 kg
Payload mass	132 kg
Length	1.6 m
Width	1.5 m
Height	2.6 m
Solar array	15.23 m span
Stabilization	3 axis
DC power	1150 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

Main transponders	4
Backup transponders	2
Power	45 W (TWTA)
Bandwidth	5 and 22.5 KHz
Coverage	global
EIRP	24 dBW
Polarization

This capacity is used for communications with the mobils.


Inmarsat 2's C-band

Main transponders	1
Backup transponders	1
Power	10 W (TWTA)
Bandwidth	5 and 22.5 KHz
Coverage	global
EIRP	39 dBW
Polarization

This capacity is used for communications with earth stations.


 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
Launch site	Cape Canaveral
Location

Begin	End	Position
L: 30 Oct 1991	> Jan 1994	63°E
Jun 1994	...	64.5°E

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	15.5°W
Launch vehicle	Delta 2
Launch site	Cape Canaveral

Tel: 871, Telex: 581

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	178°E
Launch vehicle	Ariane V48

Tel: 872, Telex: 582

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		55°W
Feb 1995	...	54.5°W

Tel: 874, Telex: 584

Technical data

Specifications

L-band

C-band


Inmarsat 3

4 satellites scheduled for 1995: 1950 kg, 2600 W

GE Astro clains to have 5 satellites ordered


 Program: Insat

Indian National Satellite

Indian telecommunication and meteorology program operated by the Department of Space

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.

Contact

Insat, Departement of Space/Government of India

System F-Block Cauvery, Bhavan, Bangalore 560 009, India

Tel: +91-812-27371

Fax: +91-845-2499


Program: Insat

Insat 1A	Insat 1B	Insat 1C	Insat 1D
Insat 2A	Insat 2B


Insat 1's specifications

Prime contractor	Ford Aerospace
Platform	INSAT
Mass at launch	1152 kg
Mass in orbit	650 kg
Length	2.18 m
Width	1.42 m
Height	1.55 m
Solar array	asymmetric pannel, 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	42 dBW
Polarization


Insat 1's C-band

Main transponders	12
Backup transponders
Power	4.5 W (TWTA)
Bandwidth	36 MHz
Coverage	India
EIRP	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
Mass at launch	1906 kg
Mass in orbit	1162 kg
Length	1.93 m
Width	1.64 m
Height	1.7 m
Solar array	asymmetric pannel
Stabilization	3 axis
DC power	1400 W
Design lifetime	7 years

Also equiped with 2 single channels for data and search & rescue, 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	42 dBW
Polarization


Insat 2's C-band

Main transponders	18
Backup transponders
Power	4.5 W
Bandwidth	36 MHz
Coverage	India
EIRP	32 dBW
Polarization


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	Delta
Launch site	Cape Canaveral
End of life

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
End of life

Out of service	yes
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	see below
Launch vehicle	Ariane V24

It had difficulties to open out the solar array. After a power failure, only half its payload is functional.

Location

Begin	End	Position
L: 21 Jul 1998		93.5°E
Feb 1995	...	56.5°E
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	82.9°E
Launch vehicle	Delta 2
Launch site	Cape Canaveral

Was damaged when a crane hook fell on it at the launch site and while it was being repared it suffered further damage during the October 1989 California earthquake.

Technical data

Specifications

S-band

C-band

Payload


 Insat 2A

General

Designation	22027 / 92041A
Launch date	9 Jul 1992
Country of origin	India
Mission	Telecommunications and meteorology
Geostationary orbit	74°E
Launch vehicle	Ariane V51
Technical data

Specifications

S-band

C-band

Payload

C-band EIRP coverage (dBW)


Insat 2A'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

Specifications

S-band

C-band

Payload


Insat 2C

scheduled for launch in 1995 by Ariane, 74°E


Insat 2D

scheduled for launch in 1996


Insat 2E

General

Designation
Launch date	last quarter of 1997
Country of origin	India
Mission	Telecommunications and meteorology
Geostationary orbit
Launch vehicle
Launch site
Mass at launch

Intelsat will pay India's Department of Space $100 million over 10 years for the use of 11 transponders. A special capability will be built into the satellite for use by Intelsat in addition to the INSAT system requirement.


 Intasat

General

Designation	07531 / 74089C
Launch date	15 Nov 1974
Country of origin	Espagne
Mission	Scientific: ionosphere study
Perigee/Apogee	1441/1455 km
Inclination	101.9°
Period	114.8 min
Launch vehicle	Thor Delta 104
Launch site	Vandenberg
Mass at launch	24.5 kg

Studies the ionosphere's density and its movement throughout the year.


 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 134 members.

Contact

Intelsat

3400 International drive NW, Box 63, Washington DC, 20008, USA

Tel: +1-202-944-7500

Fax: +1-202-944-7890

http://www.intelsat.int:8080/


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 701	Intelsat 702	Intelsat 703	Intelsat 704
Intelsat 705	Intelsat 706


Intelsat 2's specifications

Mass at launch	162 kg
Mass in orbit	86 kg
Length
Width	1.42 m
Height	0.67 m
DC power	BOL: 83 W EOL: 75 W
Design lifetime	3 years


Intelsat 2's C-band

Main transponders	1
Power	18 W
Bandwidth	125 MHz
EIRP	15.5 dBW
Phone circuits	240
Reserved TV channel	1


Intelsat 3's specifications

Mass at launch	293 kg
Mass in orbit	151 kg
Length
Width	1.41 m
Height	2.02 m
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	23 dBW
Phone circuits	1200
Reserved TV channels	4


Intelsat 4's specifications

Mass at launch	1415 kg
Mass in orbit	700 kg
Length
Width	2.38 m
Height	5.28 m
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	Global: 22.5 dBW Spot beam: 33.7 dBW
Phone circuits	4000
Reserved TV channels	2


Intelsat 4A's specifications

Mass at launch	1515 kg
Mass in orbit	793 kg
Length
Width	2.38 m
Height	6.93 m
DC power	BOL: 700 W EOL: 500 W
Design lifetime	7 years


Intelsat 4A's C-band

Main transponders	20
Power	6.5 W
Bandwidth	36 MHz
Coverage and EIRP	Global: 22 dBW Hemispheric: 26 dBW Spot beam: 29 dBW
Phone circuits	6000
Reserved TV channels	2


Intelsat 5's specifications

Prime contractor	Ford Aerospace
Platform	Intelsat 5
Mass at launch	1900 kg
Mass in orbit	1040 kg
Payload mass	235 kg
Length	1.66 m
Width	2 m
Height	1.77 m
Solar array	15.58 m span
DC power	BOL: 1800 W EOL: 1270 W
Stabilization	3 axis
Design lifetime	7 years
Phone circuits	12000
Reserved TV channels	2


Intelsat 5's L-band

Main transponders	2
Backup transponders
Power
Bandwidth
Coverage
EIRP	33 dBW
Polarization

Only on 505, 506, 507, 508 & 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	Global: 23.5 dBW Hemispheric and zone: 29 dBW Spot beam: 32.5 dBW
Polarization	circular R/L


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	44.4 and 41.4 dBW
Polarization	linear


Intelsat 5A's specifications

Prime contractor	Ford Aerospace
Platform	Intelsat 5
Mass at launch	1900 kg
Mass in orbit	1040 kg
Payload mass	280 kg
Length	1.66 m
Width	2 m
Height	1.77 m
Solar array	15.58 m span
DC power	BOL: 1800 W EOL: 1270 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	Global: 23.5 dBW Hemispheric and zone beams: 29 dBW Spot beams: 32.5 dBW
Polarization	circular R/L


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	44.4 dBW
Polarization	linear


Intelsat 6's specifications

Prime contractor	Hugues
Platform	Intelsat 6
Mass at launch	4300 kg
Mass in orbit	2560 kg
Payload mass	326 kg
Diameter	3.63 m
Height	6.4 m (11.84 m stowed)
DC power	BOL: 2600 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	6+32
Backup transponders	2+10
Power	(6+2) transponders of 16 W (TWTA) (32+10) transponders of 10 W (SSPA)
Bandwidth	36 and 72 MHz
Coverage and EIRP	Global beam: 26.5 dBW Hemispheric: 29 dBW Zone: 31 dBW
Polarization	circular R/L


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	36 MHz
Coverage and EIRP	2 spot beams: 47 and 44.7 dBW
Polarization	linear


Intelsat 7's specifications

Prime contractor	Space Systems Loral
Platform	Intelsat 7 (Ford FS 1300 and Aerospatiale Spacebus 2000)
Mass at launch	3750 kg
Mass in orbit	1800 kg
Length	2.45 m
Width	2.2 m
Height	2.7 m
Solar array	21.8 m span
DC power	3900 W
Stabilization	3 axis
Design lifetime	13 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	26
Backup transponders
Power
Bandwidth	8 transponders of 36 MHz 2 transponders of 41 MHz 16 transponders of 72 MHz
Coverage and EIRP	Spot beam: 33 dBW Hemispheric & Zone beam: 33 dBW Global beam: 26 dBW
Polarization

Four 36 MHz and the two 41 MHz transponders are either in global or in spot configuration. All other transponders are either Hemispheric or Zone. 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	3 spot beams: 46.5 dBW
Polarization	linear

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 7A's specifications

Prime contractor	Space Systems Loral
Platform	Ford FS 1300
Mass at launch	4500 kg
Mass in orbit
Length
Width
Height
Solar array	25.7 m span
DC power	5200 W
Stabilization	3 axis
Design lifetime	15 years
Phone circuits	22500 (112500 with DCME)
Reserved TV channels	3

(706, 707 & 708)


Intelsat 7A's C-band

Main transponders	26
Backup transponders
Power
Bandwidth	72 MHz
Coverage and EIRP	Spot beam: 29 dBW Hemispheric beam: 33 dBW Global beam: 29 dBW
Polarization


Intelsat 7A's Ku-band

Main transponders	14
Backup transponders
Power
Bandwidth
Coverage and EIRP	3 spot beams: 47 dBW
Polarization


Intelsat 8's specifications

Prime contractor	GE Astro Space
Design lifetime	16 years
Phone circuits	22500 (112500 with DCME)
Reserved TV channels	3

Intelsat has ordered 3 satellites 8 and 3 8A ones. Intelsat also leased a russian Express satellite.


Intelsat 8's C-band

Main transponders	32
Backup transponders
Power	20-30 W
Bandwidth	36 and 72 MHz
Coverage	Global, hemispheric, zone and spot
EIRP
Polarization


Intelsat 8's Ku-band

Main transponders	9 to 12
Backup transponders
Power	50 W
Bandwidth	72 and 112 MHz
Coverage
EIRP
Polarization

Equiped with steerable Ku spots for VSAT.


 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	Delta
Launch site	Cape Canaveral
End of life

Out of service	yes
Technical data

Specifications

Mass at launch	68 kg
Mass in orbit	38 kg
Length
Width	0.72 m
Height	0.59 m
DC power	BOL: 45 W EOL: 33 W
Design lifetime	1.5 year
C-band

Main transponders	2
Power	6 W
Bandwidth	25 MHz
EIRP	11.5 dBW
Phone circuits	240
Reserved TV channel	1


 Intelsat 201

General

Designation	02514 / 66096A
Launch date	26 Oct 1966
Country of origin	International
Mission	Telecommunications
Perigee/Apogee
Launch vehicle
Launch site	Cape Canaveral
Mass at launch
End of life

Out of service	26 Oct 1966
Cause	Remained on the transfert orbit
Technical data

Specifications

C-band


 Intelsat 202

General

Designation	02639 / 67001A
Launch date	11 Jan 1967
Country of origin	International
Mission	Telecommunications
Geostationary orbit
Launch vehicle
Launch site	Cape Canaveral
Mass at launch
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
Launch site	Cape Canaveral
Mass at launch
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
Launch site	Cape Canaveral
Mass at launch
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
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
Launch site	Cape Canaveral
Mass at launch
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
Launch site	Cape Canaveral
Mass at launch
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
Launch site	Cape Canaveral
Mass at launch
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
Launch vehicle
Launch site	Cape Canaveral
Mass at launch
End of life

Out of service	26 Jul 1969
Cause	Placed on a wrong orbit
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
Launch site	Cape Canaveral
Mass at launch
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
Launch site	Cape Canaveral
Mass at launch
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
Launch site	Cape Canaveral
Mass at launch
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
Launch site	Cape Canaveral
Mass at launch
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
Launch site	Cape Canaveral
Mass at launch
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
Launch site	Cape Canaveral
Mass at launch
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
Launch site	Cape Canaveral
Mass at launch
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
Launch site	Cape Canaveral
Mass at launch
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
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
Launch site	Cape Canaveral
Mass at launch
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
Launch site	Cape Canaveral
Mass at launch
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
Launch site	Cape Canaveral
Mass at launch
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
Launch site	Cape Canaveral
Mass at launch
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
Launch site	Cape Canaveral
Mass at launch
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
Launch site	Cape Canaveral
Mass at launch
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: 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
Launch site	Cape Canaveral
Mass at launch
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
late 1991	late 1991	177°W
Oct 1992	...	91.5°E
Technical data

Specifications

C-band

Ku-band

EIRP coverage (dBW)

C-band

Ku-band


Intelsat 501's C-band EIRP


Intelsat 501's Ku-band EIRP


 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
Jan 1991	Jan 1991	1°W
Feb 1992	Oct 1994	21.5°W
Oct 1994	...	40.5°W

On inclined orbit since the mid 80ies

Technical data

Specifications

C-band

Ku-band

The antenna's platform was rotated in December 1992 to enable a direct link between Somalia and the US. The Eastern spot was pointed on 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
1 Jan 1991	late 1991	174°E
Oct 1992	...	177°W
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
Jan 1991	Oct 1992	34.5°W
July 1993	Sep 1993	32°W
Dec 1993	Jan 1994	40.5°W
May 1994	...	31.5°W
Technical data

Specifications

C-band

Ku-band


 Intelsat 505

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
Jan 1991	end of 1991	63°E
Feb 1992	Aug 1994	66°E
Nov 1994	...	65°E
Technical data

Specifications

L-band

C-band

Ku-band


 Intelsat 506

General

Designation	14077 / 83047A
Launch date	19 May 1983
Country of origin	International
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Altas Centaur
Launch site	Cape Canaveral
Location

Begin	End	Position
L: 19 May 1983
Jan 1991	Feb 1992	18.5°W
Jul 1992	Jul (Sep?) 1992	34.5°W
Oct 1992	May 1995	50°W
...		32.4°W
Technical data

Specifications

L-band

C-band

Ku-band


 Intelsat 507

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
Mar 1991	Mar 1991	66°E
end of 1991	Mar 1995	57°E
Apr 1995	...	47°E
Technical data

Specifications

L-band

C-band

Ku-band

EIRP coverage (dBW)

C-band

Ku-band


Intelsat 507's C-band EIRP


Intelsat 507's Ku-band EIRP


 Intelsat 508

Also called "PolySat"

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

End of life

Out of service	end of 1984
Cause	Launch failure
Technical data

Specifications

L-band

C-band

Ku-band


 Intelsat 510

General

Designation	15629 / 85025A
Launch date	22 Mar 1984
Country of origin	International
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral

Transmits the phone communications in the Pacific.

Location

Begin	End	Position
L: 22 mar 1984		174°E
Feb 1995	Mar 1995	66°E
Apr 1995	...	57°E
Technical data

Specifications

C-band

Ku-band


 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

Transmits the phone communications in the Pacific

Location

Begin	End	Position
L: 30 Jun 1985
Jan 1991	Jan 1991	27.5°W
late 1991	Sep 1992	63°E
Oct 1992	Nov 1994	177°E
Feb 1995	...	180°E
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
Launch site	Cape Canaveral
Location

Begin	End	Position
L: 29 Sep 1985
Jan 1991	Jan 1991	34.5°W
Mar 1991	Aug 1994	1°W
Sep 1994	...	21.5°W
Technical data

Specifications

C-band

Ku-band

Ku-band used: 11.01-11.59 GHz

EIRP coverage (dBW)

C-band

Ku-band


Intelsat 512's C-band EIRP


Intelsat 512's Ku-band EIRP


 Intelsat 513

General

Designation	19121 / 88040A
Launch date	17 May 1988
Country of origin	International
Mission	Telecommunications
Geostationary orbit	53°W
Launch vehicle	Ariane V22
Technical data

Specifications

C-band

Ku-band

Would have transponders in Ku's Telecom band and a mobile 32 dBW spot but no global beam?

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	...	18°W
Technical data

Specifications

C-band

Ku-band

EIRP coverage (dBW)

C-band

Ku-band


Intelsat 515's C-band EIRP


Intelsat 515's Ku-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	...	27.5°W
Technical data

Specifications

C-band

Ku-band

EIRP coverage (dBW)

C-band

Ku-band Eastern spot

Ku-band Western spot


Intelsat 601's C-band EIRP


Intelsat 601's EIRP (Ku-band Eastern spot)


Intelsat 601's EIRP (Ku-band Western spot)


 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	...	63°E
Technical data

Specifications

C-band

Ku-band

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	34.5°W
Launch vehicle	Titan 3
Launch site	Cape Canaveral

The satellite was repared (apogee kick motor changed) by STS 49 in May 1992.

Technical data

Specifications

C-band

Ku-band

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
Launch site	Cape Canaveral
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

EIRP coverage (dBW)

C-band

Ku-band

Ku-band used: 10.97-11.6 GHz


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
Location

Begin	End	Position
L: 14 Aug 1991
late 1991	late 1991	21.5°W
Jul 1992	...	24.5°W
Technical data

Specifications

C-band

Ku-band

EIRP coverage (dBW)

C-band

Ku-band


Intelsat 605's C-band EIRP


Intelsat 605's Ku-band EIRP


 Intelsat K

General

Designation	21989 / 92032A
Launch date	10 Jun 1992
Country of origin	International
Mission	Telecommunications
Geostationary orbit	21.5°W
Launch vehicle	Atlas 2A
Launch site	Cape Canaveral

First Intelsat Ku-band only satellite for TV channels transmission. This satellite is a modified Satcom bought to respond to urgent needs over Atlantic.

Technical data

EIRP coverage (dBW)

EIRP coverage to America (dBW)

EIRP coverage to Europe (dBW)

Specifications

Prime contractor	GE Astro Space
Platform	GE 5000
Mass at launch	2836 kg
Mass in orbit	1547 kg
Length	2.84 m
Width	2.26 m
Height	2.18 m
Solar array	31.2 m span
Stabilization	3 axis
DC power	BOL: 4800 W
Design lifetime	10 years
Ku-band

Main transponders	16
Backup transponders
Power	62.5 W (TWTA)
Bandwidth	54 MHz
Coverage and EIRP	South America: 42/45 dBW United States: 42/49 dBW Europe: 47/49 dBW
Polarization	linear
Transponder frequency chart (GHz)

Transponder	Polarization	Frequency	Coverage
1	V	11.735	To America
2	H/V	11.795	To America
3	H/V	11.855	To America
4	H/V	11.915	To America
5	H/V	11.485	Switchable
6	V	11.545	Switchable
7	V	11.605	Switchable
8	H/V	11.665	Switchable
9	H/V	12.536	To Europe
10	H/V	12.595	To Europe
11	H/V	12.655	To Europe
12	H/V	12.715	To Europe


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	174°E
Launch vehicle	Ariane V60

Cost: $103 million

Technical data

Specifications

C-band

Ku-band

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	...	1°W
Technical data

Specifications

C-band

Ku-band

EIRP coverage (dBW)

C-band

Ku-band

Made from a FS-1300 platform

C-band

Coverage	Hemispheric beam 1: Europe, Africa & Middle East Zone beam 1: Europe Zone beam 2: Southern Africa and part of Indian Ocean Hemispheric beam 2: Central & South America Zone beam 3: Southern South America Zone beam 4: Central America
C-band transponder frequency chart (GHz)

LHCP Zone 1	LHCP Zone 2	Downlink	RHCP Hemi 1	RHCP Hemi 2	Bandwith (MHz)
51A	x	x	21A	x
51	x	3.7425	21	x	72 MHz
51B	x	x	21B	x
52A	x	x	22A	x
52	x	3.825	22	x	72 MHz
52B	x	3.840	22B	x
53A	x	x	23A	x
53	x	3.905	23	x	72 MHz
53B	x	x	23B	x
54A	x	x	24A	x
54	x	3.995	24	x	72 MHz
54B	x	4.022	24B	x
55	x	4.055	25	x	36 MHz
LHCP Global or Spot		Downlink		RHCP Global or Spot
x		4.095		x	36 MHz
x		4135		x	36 MHz
x		4.1775		x	41 MHz
Ku-band

Coverage & EIRP	Spot 1: Northern & Central Europe: 46.5 dBW Spot 2: Northen & Central Europe and Eastern Russia: 44.5 dBW Spot 3: Par of Middle East (centered on Israel): 44.5 or 46.5 dBW

Transponders 61, 62, 63, 71, 72 and 73 can be swiched all together on either FSS, DBS or Telecom Ku-band.

Spot 1 is composed of the vertical transponders whereas spot 2 is composed of horizontal transponders. These transponders ( 5 max) can be moved to spot 3 keeping their original polarization.

Ku-band transponder frequency chart (GHz)

Horizontal	FSS	DBS	Telecom	Vertical
61A	10.971	11.726	12.526	71A
61	10.9925	11.7475	12.5475	71	72 MHz
61B	11.014	11.769	12.569	71B
62A	11.055	11.810	12.610	72A
62	11.075	11.830	12.630	72	72 MHz
62B	11.095	11.850	12.650	72B
63A	11.133	11.877	12.677	73A
63	11.155	11.910	12.710	73	72 MHz
63B	11.178	11.943	12.743	73B
68A	11.478	n/a	n/a	78A
68/68B	11.514	n/a	n/a	78/78B	112 MHz
68C	11.555	n/a	n/a	78C
69A	11.597	n/a	n/a	79A
69/69B	11.638	n/a	n/a	79/79B	112 MHz
69C	11.679	n/a	n/a	79C


Intelsat 702's C-band EIRP


Intelsat 702's Ku-band EIRP


 Intelsat 703

General

Designation	23305 / 94064A
Launch date	6 Oct 1994 at 06:35 UT
Country of origin	International
Mission	Telecommunications
Geostationary orbit	177°E
Launch vehicle	Atlas 2AS AC-111
Launch site	Cape Canaveral 36B
Mass at launch
Technical data

Specifications

C-band

Ku-band

EIRP coverage (dBW)

C-band

Ku-band

Made from a FS-1300 platform


Intelsat 703's C-band EIRP


Intelsat 703's Ku-band EIRP


 Intelsat 704

General

Designation	23461 / 95001A
Launch date	10 Jan 1995 at 06:18 UT
Country of origin	International
Mission	Telecommunications
Geostationary orbit	66°E
Launch vehicle	Atlas 2AS
Launch site	Cape Canaveral LC36
Mass at launch

Began operations on 25 Feb 1995

Technical data

Specifications

EIRP coverage (dBW)

C-band

Ku-band

C-band

Main transponders	26
Backup transponders
Power
Bandwidth	10 transponders of 36 MHz 16 transponders of 72 MHz
Coverage and EIRP	Spot beam: 41.6 dBW (36 MHz) Hemispheric beam: 40 dBW (8x72 MHz + 2x36 MHz) Zone beam: 40 dBW (8x72 MHz + 2x36 MHz) Global beam: 34 dBW (36 MHz)
Polarization	linear

Six 36 MHz transponders are either in global or in spot configuration.

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	3 spot beams: 46.5 dBW, up to 51.4 dBW
Polarization	linear

Five transponders max per spot.


Intelsat 704's C-band EIRP


Intelsat 704's Ku-band EIRP


 Intelsat 705

General

Designation	23528 / 95013A
Launch date	22 Mar 1995 at 06:18 UT
Country of origin	International
Mission	Telecommunications
Geostationary orbit	50°W
Launch vehicle	Atlas 2AS AC 115
Launch site	Cape Canaveral LC36B
Mass at launch

Test carried out in 56°W slot

Technical data

Specifications

EIRP coverage (dBW)

C-band

Ku-band

C-band

Main transponders	26
Backup transponders
Power
Bandwidth	10 transponders of 36 MHz 16 transponders of 72 MHz
Coverage and EIRP	Spot beam (steerable): 41.6 dBW (36 MHz) Hemispheric beam: 40 dBW (8 x 72 MHz + 2 x 36 MHz) Zone beam: 40 dBW (8 x 72 MHz + 2 x 36 MHz) Global beam: 34 dBW (36 MHz)
Polarization	linear

Six 36 MHz transponders are either in global or in spot configuration.

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	3 spot beams: 46.5 dBW, up to 51.8 dBW
Polarization	linear

Five transponders max per spot.


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
Mass at launch
Technical data

Specifications

C-band

Ku-band


Intelsat 707

General

Designation
Launch date	planned in May 1995
Country of origin	International
Mission	Telecommunications
Geostationary orbit	18°W
Launch vehicle	Ariane
Launch site
Mass at launch

has 14 transponders in Ku-band

Technical data

Specifications

C-band

Ku-band


Intelsat 708

General

Designation
Launch date	planned in Oct 1995
Country of origin	International
Mission	Telecommunications
Geostationary orbit	1°W (or 57°E)
Launch vehicle	Long March 3B
Launch site
Mass at launch
Technical data

Specifications

C-band

Ku-band


Intelsat 709

General

Designation
Launch date	planned in Jan 1996
Country of origin	International
Mission	Telecommunications
Geostationary orbit	91.5°E
Launch vehicle	Ariane
Launch site
Mass at launch
Technical data

Specifications

C-band

Ku-band


Intelsat 801

General

Designation
Launch date	planned in Jan 1996
Country of origin	International
Mission	Telecommunications
Geostationary orbit	174°E
Launch vehicle	Long March 3B
Launch site
Mass at launch
Technical data

Specifications

C-band

Ku-band


Intelsat 802

General

Designation
Launch date	planned in Feb 1996
Country of origin	International
Mission	Telecommunications
Geostationary orbit	177°E
Launch vehicle	Ariane
Launch site
Mass at launch
Technical data

Specifications

C-band

Ku-band


Intelsat 803

General

Designation
Launch date	planned in May 1996
Country of origin	International
Mission	Telecommunications
Geostationary orbit	66°E
Launch vehicle	Ariane
Launch site
Mass at launch
Technical data

Specifications

C-band

Ku-band


Intelsat 804

General

Designation
Launch date	planned in Aug 1996
Country of origin	International
Mission	Telecommunications
Geostationary orbit	21.5°W
Launch vehicle	Ariane
Launch site
Mass at launch
Technical data

Specifications

C-band

Ku-band


Intelsat 805

General

Designation
Launch date	planned in Mar 1997
Country of origin	International
Mission	Telecommunications
Geostationary orbit	110.5°E
Launch vehicle	Long March 3B
Launch site
Mass at launch

The 805 satellite will have a large coverage in C and Ku band with an 36 dBW EIRP to cover Asia.

Technical data

Specifications

C-band

Ku-band


Intelsat 806

General

Designation
Launch date	planned in Dec 1996
Country of origin	International
Mission	Telecommunications
Geostationary orbit	40.5°W
Launch vehicle	Ariane
Launch site
Mass at launch


 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 Bulgaria 1300


 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
Launch site	Kapustin Yar
Mass at launch
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
Launch site	Plesetsk
Mass at launch
End of life

Decay	17 Mar 1981


 Intercosmos Bulgaria 1300

Also called Intercosmos 22

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
Launch site	Plesetsk
Mass at launch	350 kg


 Program: Intersputnik

Organization created in 1971 by the former USSR; started working in 1972. It was supposed to break Intelsat's monopoly (they didn't expect members not to belong to other telecommunications organizations). In 1987, 16 states belonged to the organization (Intercosmos members and other friend states).

Earth stations had 12 m antennas. The price payed for the communications was often lower than it should have been. Intersputnik used Molnya satellites before turning to geostationary Gorizont satellites.

Contact

Intersputnik

2 Smolensky Lane 1/4, Moscow, 121099, CIS

Tel: +7-95-244-0333

Fax: +7-95-253-9906


 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	Delta 3910
Launch site	Vandenberg

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
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
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 evaporated helium

Temperature control	2 K
Telemetry/data	S-band (1 Mbps)


Program: Iridium

Operated by Motorola


 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.


Program: IRS

IRS 1A	IRS 1B
IRS P2


IRS's specifications

Prime contractor	ISRO
Mass at launch	1150 kg
Length	1.6 m
Width	1.56 m
Height	1.1 m
Solar array	8.5 m²
Stabilization	3 axis
Design lifetime	3 years


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
LISS 2 A & B (2 identical push-broom scanners with CCD detector arrays

Wavebands	as LISS 1
Resolution	36.25 m
Swath width	74 km either side of ground track with 3 km overlap: total 145 km

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	Semoirka (Intercosmos or Vostok?)
Launch site	Tyuratam
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	Intercosmos
Launch site	Vostok
Mass at launch
Technical data

Specifications

Payload


 IRS P2

General

Designation	23323 / 94068A
Launch date	15 Oct 1994 at 05:07 UT
Country of origin	India
Mission	Remote sensing
Perigee/Apogee	818/820 km
Inclination	98.7°
Period	102.3 min
Launch vehicle	4-stage PSLV D2
Launch site	Sriharikota
Mass at launch	870 kg

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.

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


IRS 1C

should be launched mid-1995 by a Russian launcher


 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.


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
Launch site	Cape Canaveral
Mass at launch

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
Launch site	Cape Canaveral
Mass at launch

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
Launch site	Cape Canaveral
Mass at launch	237 kg


 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
Launch site	Cape Canaveral
Mass at launch	262 kg


 Program: Italsat

Italian experimental satellites operated by the Telespazio

Contact

Telespazio

Via Alberto Bergamini 50, Roma, 00159, Italia

Tel: +39-6-4987-2240

Fax: +39-6-4987-2743


Program: Italsat

Italsat 1


 Italsat 1

General

Designation	21055 / 91003A
Launch date	15 Jan 1991
Country of origin	Italy
Mission	Telecommunications
Geostationary orbit	13.1°E
Launch vehicle	Ariane V41
Technical data

Specifications

Prime contractor	Selenia Spazio
Platform	Italsat
Mass at launch	1850 kg
Payload mass	275 kg
Length	3.5 m
Width	2.7 m
Height	2.3 m
Solar array	21.8 m span
Stabilization	3 axis
DC power	BOL: 1564 W
Design lifetime	7 years
Ka-band

Main transponders	3 in 20/30 GHz: national beam 6 in 20/60 GHz: multi-beam
Backup transponders	2 in 20/30 GHz 4 in 20/60 GHz
Power	20 W (TWTA)
Bandwidth	national beam: 36 MHz multi-beam: 120 MHz
Coverage	national beam: all Italy multi-beam: 6 spots
EIRP	national beam: 42.2 dBW multi-beam: 57 dBW
Polarization

Equiped with 1 (+1 backup) 1 W propagation beacon, EIRP 27 dBW


Italsat 2

scheduled to be launched in 1996 by Ariane


 Itamsat

Also called IO-26 or Oscar 26

General

Designation	22826 / 93061D
Launch date	26 Sep 1993
Country of origin	Italy
Operator	Interferometrics (USA)
Mission	Telecommunications
Perigee/Apogee	789/803 km
Inclination	98.7°
Period	100.8 min
Launch vehicle	Ariane V59
Technical data

Specifications

Prime contractor	Associazione Radioamatori Italiani
Platform
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
Transponder frequency chart (MHz)

Downlink freq.	Transponder/Beacon	Mode
435.867		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

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
Launch site	Vandenberg
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
Mission	Scientific: UV astronomy
Perigee/Apogee	30252/41315 km
Inclination	34.5°
Period	1435.9 min
Launch vehicle	Delta
Launch site	Cape Canaveral
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.

Technical data

Specifications

Mass at launch	644 kg
Length	4.17 m
Width	1.45 m
Solar array	45 m²
Stabilization	3 axis

Payload: 0.45 m diameter UV telescope

Transmits on 136.86 MHz


 Program: Jcsat

Japanese telecommunication program operated by Japan Communications Satellite Co. Its Japan first commercial satellite system providing TV and cable distribution, telephony, business services and satellite news gathering.

Contact

Japan Satellite Systems Inc. (JSAT)

Toranomon 17 Mori Bldg. 5th Fl., 1-26-5 Toranomon, Minato-ku, Tokyo 105 Japan

Tel: +81-3-5511-7778

Fax: +81-3-3597-0601


Program: Jcsat

Jcsat 1

Jcsat 2


Jcsat's specifications

Prime contractor	Hugues
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's Ku-band

Main transponders	32
Backup transponders	8
Power	20 W (TWTA)
Bandwidth	27 MHz
Coverage	Japan and offshore territories
EIRP	51 dBW
Polarization


 Jcsat 1

General

Designation	19874 / 89020A
Launch date	6 Mar 1989
Country of origin	Japan
Mission	Telecommunications
Geostationary orbit	150°E
Launch vehicle	Ariane V29
Technical data

Specifications

Ku-band


 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
Launch site	Cape Canaveral
Technical data

Specifications

Ku-band


Jcsat 3

General

Designation
Launch date	planned in Aug 1995
Country of origin	Japan
Mission	Telecommunications
Geostationary orbit	124 or 128°E
Launch vehicle
Launch site

Could replace Apstar 2. Six Ku-band digital channels are available and will be marketed to broadcasters in South Asia.

Technical data

Specifications

Prime contractor	Hugues
Platform	HS 601
Mass at launch
Mass in orbit
Length
Width
Height
Stabilization
DC power
Design lifetime


 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
Launch site	Tanegashima
Mass at launch	1340 kg

Had problems to open out its SAR antenna that were solved

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 photograph program. The first satellites had a very limited lifetime.

KH 1 series

8 satellites launched

Also called Samos (Satellite And Missile Observatory System)

KH 4 series

8 satellites launched

KH 4A series

41 satellites launched

KH 7 series

36 satellites launched

KH 8 series

49 satellites launched

KH 9 series

19 satellites launched

KH 11 series

At least 7 satellites launched

Belong to the CIA. They operate on a heliodynchronous orbit (300-500 km). Images are transmitted in real time via TDRS.


Program: KH

KH 1-2

KH 1-5

KH 4-01

KH 4A-03

KH 7-01

KH 9-01

KH 11-1

KH 11-6

KH 12-1


 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
Launch site	Vandenberg
Mass at launch

First american spy satellite. Transmits 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
Mass at launch
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
Mass at launch
End of life

Decay	7 Jan 1963


 KH 4A-03

Also called Corona

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
Mass at launch
End of life

Decay	27 May 1963


 KH 7-01

Also called Gambit

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
Launch site	Vandenberg
Mass at launch
End of life

Decay	17 Jul 1963


 KH 9-01

Also called Big Bird

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
Mass at launch
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
Mass at launch
End of life

Decay	28 Jan 1979


 KH 11-6

Also called USA 006

General

Designation	15423 / 84122A
Launch date	4 Dec 1984
Country of origin	United States
Mission	Military: photography
Perigee/Apogee	n/a
Inclination	n/a
Period	n/a
Launch vehicle
Launch site	Vandenberg
Mass at launch


 KH 12-1

Also caled USA 040

General

Designation	20167 / 89061B
Launch date	8 Aug 1989
Country of origin	United States
Mission	Military: photography
Perigee/Apogee	n/a
Inclination	n/a
Period	n/a
Launch vehicle	STS 28
Mass at launch


 Program: Kitsat

Korean program operated by the Korean Institute of Science and Technology


Program: Kitsat

Kitsat A

Kitsat B


 Kitsat A

Also called KO-23 or Oscar 23

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.

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
DC power
Design lifetime
Transponder frequency chart (MHz)

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

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

Will image with a CCD detector and support HAM radio.

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	gravity gradient
DC power
Design lifetime	5 years
Transponder 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


Koreasat 1

General

Designation
Launch date	planned in Apr 1995
Country of origin	South Korea
Mission	Telecommunications
Geostationary orbit	116°E
Launch vehicle	Delta 2
Launch site	Cape Canaveral
Mass at launch
Contact

Koreasat - ETRI

PO Box 8, Daeduk Science Town Daejeon, 305-608, Korea

Tel: +82-42-880-6830

Fax: +82-42-860-6430

Technical data

Specifications

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


Koreasat 2

General

Designation
Launch date	planned in Oct 1995
Country of origin	South Korea
Mission	Telecommunications
Geostationary orbit	116°E
Launch vehicle	Delta 2
Launch site	Cape Canaveral
Mass at launch
Technical data

Specifications

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


 Koronas 1

General

Designation	23019 / 94014A
Launch date	2 Mar 1994
Country of origin	Russia-Ukrain
Mission	Scientific: ionosphere, magnetosphere and Sun study
Perigee/Apogee	483/526 km
Inclination	82.5°
Period	94.7 min
Launch vehicle	Tsyklon 3
Launch site	Plesetsk
Mass at launch

It carried UV and X-ray instruments to map the Sun, and plasma monitors to study the ionosphere and magnetosphere.

Operated by RKA, built by Yuzhnoe (platform: AUOS-SM)


 Program: Lacrosse

Also called Indigo

American military reconnaissance program. Equiped with an optic and radar captor. Perigee/Apogee: 650/700 km; Inclination: 57°


 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 10 cm; drift to 2 cm/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	Delta
Launch site	Vandenberg
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


 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

Constructed on the Nimbus platform. We equiped 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


Program: Landsat

Landsat 1

Landsat 2

Landsat 3

Landsat 4

Landsat 5

Landsat 6


Landsat 4 & 5's specifications

Prime contractor	GE Astro
Mass at launch	1941 kg
Length	4 m
Stabilization	3 axis
Design lifetime	3 years


Landsat 4 & 5's payload

MMS (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
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
Launch site	Vandenberg
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
Launch site	Vandenberg
Mass at launch
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
Launch site	Vandenberg
Mass at launch


 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	Delta
Launch site	Vandenberg
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	Delta
Launch site	Vandenberg
Technical data

Specifications

Payload


 Landsat 6

End of life

Out of service	5 Oct 1993
Cause	Titan 2G launch failure

Cost: $220 million

Technical data

Specifications

Payload


 Program: LCS

American radar calibration military program


Program: LCS

LCS 1

LCS 2:see OV 2-1?

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
Launch site	Cape Canaveral
Mass at launch


 LCS 4

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
Mass at launch
End of life

Decay	11 Jun 1972


 LDEF

Long Duration Exposure Facility

General

Designation	14898 / 84034B
Launch date	6 Apr 1984
Country of origin	Europe
Mission	Scientific: Meteorite observation
Perigee/Apogee	344/348 km
Inclination	28.5°
Period	91.5 min
Launch vehicle	STS 11
Mass at launch

Mass at retrieval: 10.5 t with 10000 samples

End of life

Out of service	9 Jan 1990
Cause	Retrieved by STS 32
Decay	20 Jan 1990


 Program: Leasat

LEAsed SATellite

American military telecommunication satellite program. The satellites (Syncom 4 series) are owned by HCI and leased to US Navy. They are believed to downlink in UHF- and X-band.


Program: Leasat

Leasat 1

Leasat 2

Leasat 3

Leasat 4

Leasat 5


 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 14
Mass at launch
End of life

Out of service	yes


 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 12
Mass at launch
Location

Begin	End	Position
L: 30 Aug 1984
Feb 1995	...	177.2°W


 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
Mass at launch

When released from STS 16 it failed to reach GEO and was repaired by STS 20

Location

Begin	End	Position
L: 12 Apr 1985
Feb 1995	...	104.8°W


 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 20
Mass at launch
End of life

Out of service	Sep 1985
Cause	failed in GEO


 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 32
Mass at launch
Location

Begin	End	Position
L: 12 Apr 1985
Feb 1995		71.5°W


 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
Launch site	Cape Canaveral
Mass at launch


 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
Launch site	Cape Canaveral
Mass at launch


 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
Launch site	Cape Canaveral
Mass at launch
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
Launch site	Cape Canaveral
Mass at launch
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
Launch site	Cape Canaveral
Mass at launch


 LES 6

General

Designation	03431 / 68081D
Launch date	26 Sep 1968
Country of origin	United States
Mission	Military: telecommunications
Geostationary orbit
Launch vehicle
Launch site	Cape Canaveral
Mass at launch
End of life

Out of service	yes


 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 C
Launch site	Cape Canaveral
Mass at launch	450 kg

LES 8 & 9 were placed in geostationary orbit with 90° between each other. Equiped 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


 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 C
Launch site	Cape Canaveral
Mass at launch	450 kg

LES 8 & 9 were placed in geostationary orbit with 90° between each other. Equiped 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		105.5°W


Lifesat 01

Should be launched in Dec 1994 by a Delta 2


Lifesat 02

General

Designation
Launch date
Country of origin	planned in Jun 1995
Mission
Perigee/Apogee
Inclination
Period
Launch vehicle	Delta 2
Launch site
Mass at launch


 Luch

Means "beam"

General

Designation	23426 / 94082A
Launch date	16 Dec 1994 at 12:00 UT
Country of origin	CIS
Mission	Telecommunications (Al'tair)
Geostationary orbit	95°E
Launch vehicle	Proton
Launch site	Tyuratam LC81
Mass at launch	2000 kg

Part of the SDRN network. Transmits data to and from Mir station and monitors and relay general distress and rescue calls.

Technical data

Specifications

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

Operates in C- and Ku-band


 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
Technical data

Uplink	1200bps Manchester coded (Biphase-L) FSK (FM) AX.25 145.840 145.860 145.880 145.900 MHz
Downlink	1200bps 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: Magion

Czech scientific program designed with the Soviets


Program: Magion

Magion 1

Magion 2

Magion 3


 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
Launch site	Plesetsk
Mass at launch
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
Launch site	Plesetsk
Mass at launch


 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
Launch site	Plesetsk
Mass at launch
Technical data

Downlink frequency: 135.150/137.850 MHz


 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
Launch site	Vandenberg
Mass at launch
End of life

Decay	11 Jun 1980


 Program: Marecs

European maritim telecommunication program designed with the Eutelsat platform. Program mainly supported by the UK.

Satellites used by Inmarsat


Program: Marecs

Marecs A

Marecs B1

Marecs B2


Marecs's specifications

Prime contractor	British Aerospace
Platform	ECS
Mass at launch	1056 kg
Payload mass	100 kg
Length	1.9 m
Width	1.4 m
Height	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
Polarization


Marecs's C-band

Main transponders	1
Backup transponders
Power
Bandwidth
Coverage	global
EIRP
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
21 Mar 1993	...	22.8°E
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	...	14.9°W
Technical data

Specifications

L-band

C-band


 Program: Marisat

American maritim telecommunication satellite program launched by NASA for Comsat. Were first used by military forces before been used by private companies. Used by Inmarsat.

Contact

COMSAT Corporation

6560 Rock Spring Drive, Bethesda, MD 20817, USA

Tel: +1-301-214-3658

Fax: +1-301-214-7130


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
Launch site	Cape Canaveral
Mass at launch
Location

Begin	End	Position
L: 19 Feb 1976		105°W
Mar 1995	...	106°W
Technical data

Transmits in L- and C-band


 Marisat 2

General

Designation	08882 / 76053A
Launch date	10 Jun 1976
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle
Launch site	Cape Canaveral
Mass at launch
Location

Begin	End	Position
L: 10 Jun 1976		73°E
Mar 1995	...	72.5°E
Technical data

Transmits in L- and C-band


 Marisat 3

General

Designation	09478 / 76101A
Launch date	14 Oct 1976
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle
Launch site	Cape Canaveral
Mass at launch
Location

Begin	End	Position
L: 14 Oct 1976		15°W
Mar 1995	...	178°W
Technical data

Transmits in L- and C-band


Measat 1

Malaysian East Asia Satellite

General

Designation
Launch date	planned in Nov 1995
Country of origin	Malaysia
Operator	Binariang SDN BHD
Mission	Telecommunications
Geostationary orbit
Launch vehicle	Ariane
Mass at launch
Contact

Measat

Binariang Sdn. Bhd., 2nd floor, 11 Jalan Tandang, 46050 Petaling Jaya, Selangor Darul Ehsan, Malaysia

Tel: +60-3-794-2000

Fax: +60-3-791-3993

Technical data

Specifications

Prime contractor	Hugues
Platform	HS 376
Mass at launch	1400 kg
Mass in orbit
Length
Width
Height
Stabilization
DC power
Design lifetime
C-band

Main transponders	10
Backup transponders
Power
Bandwidth
Coverage	Malaysia, Philippines & South-India
EIRP
Polarization
Ku-band

Main transponders	4
Backup transponders
Power
Bandwidth
Coverage	Malaysia, Philippines & South-India
EIRP
Polarization


 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

28 satellites launched

Meteor 2 series

15 satellites launched

Meteor 3 series

Since 1985


Program: Meteor

Meteor 1-01	Meteor 1-02
Meteor 2-01
Meteor 3-03	Meteor 3-06


Meteor 2's specifications

Prime contractor	VNII Elektromekaniki
Mass in orbit	1500 kg
Diameter	2 m
Height	5 m
Solar array	2 10 m pannels
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 10 m pannels
Stabilization	3 axis


Meteor 3'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

+TOMS (Total Ozone mapping Spectrometer): provided by the United States


 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
Launch site	Plesetsk
Mass at launch	2200 kg

First Soviet meteorology satellite


 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
Launch site	Plestesk
Mass at launch


 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
Launch site	Plesetsk
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
Launch site	Plesetsk
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
Launch site	Plesetsk
Technical data

Transmits on 137.85 MHz


 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
Launch site	Plesetsk

On board was a German PRARE navigational system to measure parameters of spacecraft motion.

Technical data

Specifications

Payload


 Program: Meteosat

A series of meteorological satellites operated by ESA on behalf of Eumetsat. The satellites observe cloud formation across the full Earth disk and generate images in 3 spectral bands every 30 minutes.

Mission: observation of cloud cover, windspeeds, sea and cloud surface temperature, water vapor distribution in upper troposphere. Images acquisition, distribution of image data and other met info, collection and relay of weather data from data collection platforms (DCPs) - and, sea and airborne.

The 3 first satellites are experimental, the next ones are operational: MOP (Meteosat OPerational).

The satellites are owned by Eumetsat (European Meteorologic Satellite), an organization created on 19 Jun 1986 centered 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 millions (1985-1995); Germany 24%, France 18%, Italy 15% and UK 14%


Program: Meteosat

Meteosat 1

Meteosat 2

Meteosat 3

Meteosat 4

Meteosat 5

Meteosat 6


Meteosat 4, 5, 6 & 7'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 & 7'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)
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

Equiped with an UHF- and a S-band transponder


 Meteosat 1

General

Designation	10489 / 77108A
Launch date	23 Nov 1977
Country of origin	Europe
Mission	Meteorology
Geostationary orbit
Launch vehicle	Thor Delta 2914
Launch site	Cape Canaveral
Mass at launch	700 kg
End of life

Out of service	yes


 Meteosat 2

General

Designation	12544 / 81057A
Launch date	19 Jun 1981
Country of origin	Europe
Mission	Meteorology
Geostationary orbit
Launch vehicle	Ariane L03
Mass at launch

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
Mass at launch
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		71°W
Mar 1995		69°W
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	...	7.6°W
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
Feb 1995	...	1°W
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.

Cost: $67.5 million

Location

Begin	End	Position
L: 20 Nov 1993	...	9.5°W
Technical data

Specifications

Payload

Downlink frequency: 137.08 MHz, 1691 & 1694.5 MHz

Equiped with 1 S-band transponder. Data rate: 2.6 Mbps


Meteosat 7

scheduled for 1996


Meteosat 8

scheduled for 1998 with 13 channels


 Microlab 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
Launch site	Cape Canaveral

The Pegasus was launched from a Lockheed L-1011 carrier airplane.

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.

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


 Program: Midas

MIssile Defense Alarm System

American military satellites for missile launch warning. Equiped with IR detectors and TV cameras.


Program: Midas

Midas 2

Midas 3

Midas 4

Midas 5

Midas 6

Midas 7

Midas 8

Midas 9


 Midas 2

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
Launch site	Cape Canaveral
Mass at launch
End of life

Decay	7 Feb 1974


 Midas 3

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
Launch site	Vandenberg
Mass at launch


 Midas 4

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
Launch site	Vandenberg
Mass at launch


 Midas 5

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
Launch site	Vandenberg
Mass at launch


 Midas 6

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
Launch site	Vandenberg
Mass at launch


 Midas 7

Also called ERS 10

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
Launch site	Vandenberg
Mass at launch


 Midas 8

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
Launch site	Vandenberg
Mass at launch


 Midas 9

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
Launch site	Vandenberg
Mass at launch


 Miranda

Also called UK 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
Launch site	Vandenberg
Mass at launch	93 kg

Tested a stabilization system, solar pannels and cells


 Mika

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 B
Launch site	Kourou
Mass at launch

First launch from Kourou

End of life

Decay	9 Sep 1974


 Program: Molnya

Means "flash of lightning" in Russian

Soviet telecomunication program. Satellites are placed on very excentric orbits (460/40000 km, inclination: 45°) with a 12 hours period. Such a satellite remains almost 8 hours above the CIS. Molnya satellites are used by the Orbita network equiped with 12 m antennas.

Mission: provide long distance reliable telephone and TV links


Program: Molnya

Molnya 1-01	Molnya 1-71	Molnya 1-72	Molnya 1-74
Molnya 1-86
Molnya 2-01
Molnya 3-01	Molnya 3-34	Molnya 3-35	Molnya 3-36
Molnya 3-37	Molnya 3-42
Molnya 1-S


 Molnya 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
Launch site	Tyuratam
Mass at launch
End of life

Decay	16 Aug 1979


 Molnya 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
Launch site	Tyuratam
Mass at launch


 Molnya 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
Launch site	Plesetsk
Mass at launch


 Molnya 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	Molnya
Launch site	Plesetsk
Mass at launch


Molnya_1-86
 Molnya 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
Launch site	Plesetsk
Mass at launch


Molnya_1-88
 Molnya 1-88

Also known as Molnya 1-T

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	Molnya M
Launch site	Plesetsk LC43
Mass at launch


 Molnya 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
Launch site	Plesetsk
Mass at launch
End of life

Decay	10 May 1976


 Molnya 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
Launch site	Plesetsk
Mass at launch
End of life

Decay	15 May 1986


 Molnya 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	Molnya
Launch site	Plesetsk
Mass at launch


 Molnya 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	Molnya
Launch site	Plesetsk
Mass at launch


 Molnya 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	Molnya
Launch site	Plesetsk
Mass at launch


 Molnya 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
Launch site	Plesetsk
Mass at launch


 Molnya 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
Launch site	Plesetsk
Mass at launch


 Molnya 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	Molnya M
Launch site	Plesetsk
Mass at launch


 Molnya 1-S

General

Designation	07392 / 74060A
Launch date	29 Jul 1974
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit
Launch vehicle
Launch site	Tyuratam
Mass at launch
End of life

Out of service	yes


 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
Length	1.26 m
Width	1.48 m
Height	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
Launch site	Tanegashima
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
Launch site	Tanegashima
Technical data

Specifications

Payload

Downlink frequency: 136.12 MHz


 Program: Morelos

Mexican telecommunication program operated by the Secretaria de Communicaciones y Transportes (SCT). The program has been replaced by Solidaridad.


Program: Morelos

Morelos 1

Morelos 2


Morelos's specifications

Prime contractor	Hugues
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	39 dBW
Polarization	linear


Morelos's Ku-band

Main transponders	4
Backup transponders	2
Power	20 W (TWTA)
Bandwidth	108 MHz
Coverage	Mexico
EIRP	44 dBW
Polarization	linear H


 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 18
Mass at launch
End of life

Out of service	yes
Technical data

Specifications

C-band

Ku-band

C-band transponder frequency chart (GHz)

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

Horizontal Uplink	Horizontal Downlink	Transponder	Vertical Uplink	Vertical Downlink
14.064	11.764	1K
14.188	11.888	2K
14.312	12.012	3K
14.436	12.136	4K


 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 23
Mass at launch
Technical data

Specifications

C-band

Ku-band

C-band transponder frequency chart (GHz)

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

Horizontal Uplink	Horizontal Downlink	Transponder	Vertical Uplink	Vertical Downlink
14.064	11.764	1K
14.188	11.888	2K
14.312	12.012	3K
14.436	12.136	4K


 MSTI 1

Miniature Seeker Technology Integration

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
Launch site	Cape Canaveral
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


 MSTI 2

Miniature Sensor Technology Integration

General

Designation	23101 / 94028A
Launch date	9 May 1994
Country of origin	United States
Mission	Technology experimentation
Perigee/Apogee	411/427 km
Inclination	97.1°
Period	92.9 min
Launch vehicle	Scout
Launch site	Vandenberg
Mass at launch	135 kg

It was the last of the now discontinued Scout series. During an orbit it successfully spotted and locked onto a test rocket launched from Edwards AFB.


 Myojo

Also called VEP (Vehicule Evaluation Payload)

General

Designation	22979 / 94007B
Launch date	3 Feb 1994 at 22:20 UT
Country of origin	Japan
Mission	Technology
Perigee/Apogee	430/36114 km
Inclination	29.12°
Period	641.95 min
Launch vehicle	H2
Launch site	Tanegashima
Mass at launch

Operated by NASDA


Program: N Star

Japanese telecommunication program that follows the Sakura series. The satellites wil provideinter-orbit links, high quality DBS TV and mobile links. The NTT corp. will operate the system.


N Star's specifications

Prime contractor	Space Loral Systems
Platform	FS 1300
Mass at launch	3800 kg
Mass in orbit	approx. 2000 kg
Length
Width
Height
Solar array	25.7 m
Stabilization	3 axis
DC power	5200 W
Design lifetime	10 years


N Star's S-band

Main transponders	1
Backup transponders
Power
Bandwidth
Coverage	Japan
EIRP
Polarization


N Star's C-band

Main transponders	5
Backup transponders
Power	20 W (TWTA)
Bandwidth
Coverage	Japan
EIRP
Polarization


N Star's Ku-band

Main transponders	8
Backup transponders
Power	40 W (TWTA)
Bandwidth
Coverage	Japan
EIRP
Polarization


N Star's Ka-band

Main transponders	11
Backup transponders
Power	20 W (TWTA)
Bandwidth
Coverage	Japan
EIRP
Polarization


N Star 1

General

Designation
Launch date	planned in Jul 1995
Country of origin	Japan
Mission	Telecommunications
Geostationary orbit	132°E
Launch vehicle	Ariane
Mass at launch
Technical data

Specifications

S-band

C-band

Ku-band

Ka-band


N Star 2

General

Designation
Launch date	planned in Sep 1995
Country of origin	Japan
Mission	Telecommunications
Geostationary orbit	136°E
Launch vehicle	Ariane
Mass at launch
Technical data

Specifications

S-band

C-band

Ku-band

Ka-band


 Program: Nadejda

Also called "Nadezhda"

Soviet navigation program. Part of the Cosmos-Tsikada system. The civil part (Tsikada which means cicada) is operational since 1978 and is carried on the Cosmos platform. It became the Nadejda series since a Cospas receiver is on-board.


Program: Nadejda

Nadejda 1

Nadejda 2

Nadejda 3

Nadejda 4


 Nadejda 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
Launch site	Plesetsk
Mass at launch


 Nadejda 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
Launch site	Plesetsk
Mass at launch
Technical data

Used to transmit on 150 & 400 MHz (replaced by Nadejda 4)


 Nadejda 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
Launch site	Plesetsk
Mass at launch
Technical data

Downlink frequency: 150 & 400 MHz


 Nadejda 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
Launch site	Plesetsk
Mass at launch
Technical data

Downlink frequency: 150 & 400 MHz

Platform: Tsikada


Program: Nahuel

Argentine first telecommunication program operated by Nahuelsat


Nahuel 1

General

Designation
Launch date	1997
Country of origin	Argentina
Mission	Telecommunications
Geostationary orbit	85 or 59° West
Launch vehicle	Long March 3C
Launch site
Mass at launch
Technical data

Specifications

Prime contractor	Aerospatiale with DASA
Platform	Spacebus 2000
Mass at launch	1820 kg
Mass in orbit
Length
Width
Height
Stabilization
DC power
Design lifetime
Ku-band

Main transponders	18
Backup transponders
Power
Bandwidth
Coverage
EIRP
Polarization


 Program: Nato

North Atlantic Treaty Organization

Military communications satellites for the NATO


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
Platform	ECS
Mass at launch	1430 kg
Payload mass	215 kg
Length	2.2 m
Height	2.3 m
Solar array	16 m span
Stabilization	3 axis
DC power	BOL: 1200 W
Design lifetime	7 years


Nato 4's UHF-band (250-315 MHz)

Main transponders	4
Backup transponders
Power	40 W
Bandwidth	25 KHz
Coverage	Europe
EIRP


Nato 4's X-band

Main transponders	4
Backup transponders
Power	40 W
Bandwidth	60 and 135 MHz
Coverage	global
EIRP
Polarization


 Nato 1

General

Designation	04353 / 70021A
Launch date	20 Mar 1970
Country of origin	NATO
Mission	Military: telecommunications
Geostationary orbit	see below
Launch vehicle
Launch site	Cape Canaveral
Mass at launch
Location

Begin	End	Position
L: 20 Mar 1970		?
Mar 1995	...	107°W


 Nato 2

General

Designation	04902 / 71009A
Launch date	3 Feb 1971
Country of origin	NATO
Mission	Military: telecommunications
Geostationary orbit	see below
Launch vehicle
Launch site	Cape Canaveral
Mass at launch
Location

Begin	End	Position
L: 3 Feb 1971		?
Mar 1995	...	106°W


 Nato 3A

General

Designation	08808 / 79035A
Launch date	22 Apr 1976
Country of origin	NATO
Mission	Military: telecommunications
Geostationary orbit	18°W
Launch vehicle
Launch site	Cape Canaveral
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
Launch site	Cape Canaveral
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
Launch site	Cape Canaveral
Mass at launch
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
Launch site	Cape Canaveral
Mass at launch
Location

Begin	End	Position
L: 14 Nov 1984
Feb 1995		21°W


 Nato 4A

General

Designation	21047 / 91001A
Launch date	8 Jan 1991
Country of origin	NATO
Mission	Military: telecommunications
Geostationary orbit	18°W
Launch vehicle	Delta 2
Launch site	Cape Canaveral
Technical data

Specifications

UHF-band

X-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	6°E
Launch vehicle
Launch site	Cape Canaveral
Mass at launch
Technical data

Specifications

UHF-band

X-band


Nilesat

General

Designation
Launch date	1998
Country of origin	Egypt
Mission	Telecommunications
Geostationary orbit
Launch vehicle
Launch site
Mass at launch

Ku-band to the Middle East


 Program: Nimbus

American experimental meteorology program operated by the NOAA

Those satellites have given atmosphere temperature at different altitudes


Program: Nimbus

Nimbus 1

Nimbus 2

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
Launch site	Vandenberg
Mass at launch	376 kg

First high resolution photos

End of life

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
Launch site	Vandenberg
Mass at launch


 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
Launch site	Vandenberg
Mass at launch


 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
Launch site	Vandenberg
Mass at launch


 Nimbus 5

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
Launch site	Vandenberg
Mass at launch


 Nimbus 6

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
Launch site	Vandenberg
Mass at launch	829 kg

Measures sea color


 Nimbus 7

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
Launch site	Vandenberg
Mass at launch	827 kg

Nimbus 7 was notable for providing the fisrt daily mapping ozone concentration and the first global ocean color measurements.

Technical data

Specifications

Prime contractor	GE Astro
Stabilization	3 axis

Equiped 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


 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.

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)

COSPAS/SARSAT [on NOAA 08 onwards]


Program: NOAA

NOAA 01

NOAA 02

NOAA 03

NOAA 04

NOAA 05

NOAA 06

NOAA 07

NOAA 07C

NOAA 08

NOAA 09

NOAA 10

NOAA 11

NOAA 12

NOAA 13

NOAA 14


NOAA's specifications

Prime contractor	GE Astro
Mass at launch	1420 kg
Length	6.4 m
Width	1.22 m
Stabilization	3 axis
Design lifetime	3 years


NOAA's payload

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 A

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
Launch site	Vandenberg
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
Launch site	Vandenberg
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	Delta
Launch site	Vandenberg
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
Launch site	Vandenberg
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
Launch site	Vandenberg
Mass at launch


 NOAA 06

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
Launch site	Vandenberg
Mass at launch


 NOAA 07

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
Launch site	Vandenberg
Mass at launch
End of life

Decay	3 May 1981


 NOAA 07C

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
Launch site	Vandenberg
Mass at launch	1405 kg

Relays data form other platforms

End of life

Out of service	1993


 NOAA 08

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
Launch site	Vandenberg
Mass at launch


 NOAA 09

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
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

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
Technical data

Specifications

Payload

APT downlink freq.	137.500 MHz (standby)
HRPT downlink freq.	1698.0 MHz
Beacon	136.770 MHz


 NOAA 11

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

End of life

Out of service	early 95
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

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
Launch vehicle	Atlas E
Launch site	Vandenberg
Technical data

Specifications

Payload

APT downlink freq.	137.500 MHz (standby)
HRPT downlink freq.	1698.0 MHz
Beacon	136.770 MHz


 NOAA 13

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
Launch site	Vandenberg

Cost: $100 million

End of life

Out of service	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 11E ICBM
Launch site	Vandenberg SLC3
Mass at launch

It will replace NOAA 11 whose cloud cover imaging instrument had failed a few months ago. 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.

Technical data

Specifications

Payload

APT downlink freq.	137.500 MHz (standby)
HRPT downlink freq.	1698.0 MHz
Beacon	136.770 MHz


NOAA K

General

Designation
Launch date	planned in May 1995
Country of origin	United States
Mission	Meteorology
Perigee/Apogee
Inclination
Period
Launch vehicle	Titan 2
Launch site	Vandenberg
Mass at launch


 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
Launch site	Vandenberg
Mass at launch
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
Launch site	Vandenberg
Mass at launch
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
Launch site	Vandenberg
Mass at launch
Technical data

Transmits with 3 W on 150 MHz and 5 W on 400 MHz


 Program: OAO

Orbiting Astronomical Observatory

American astronomy mission


Program: OAO

OAO 1

OAO 2

OAO 3

OAO 4


 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 Centaur
Launch site	Cape Canaveral
Mass at launch
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
Mass at launch


 OAO 3

End of life

Out of service	30 Nov 1970
Cause	Launch failure


 OAO 4

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
Launch site	Cape Canaveral
Mass at launch	2200 kg
End of life

Out of service	18 Jan 1973


Oderacs
 Program: Oderacs

US military spacecrafts intended to provide radar cross-sections of very small objects.

Oderacs 2

Six subsatellites: a 5.08 cm diameter steel sphere, a 10.16 cm diameter Al sphere, a 15.24 cm dia. Al sphere, a 4.318 cm length dipole wire, and two 13.208 cm long dipole wires.


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
Mass at launch
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
Mass at launch
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
Mass at launch
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
Mass at launch
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
Mass at launch
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
Mass at launch
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
Mass at launch

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
Mass at launch

15.24 cm dia. Al sphere


 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
Mass at launch

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
Mass at launch

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
Mass at launch

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
Mass at launch

4.318 cm length dipole wire


Program: Odyssey

TRW and Canada's Teleglobe announce intent to form Odyssey Worldwide Services to operate and market TRW's medium-orbit Odyssey cellular-comsat system. Odyssey first launch is set for 1998, FCC licensing permitting. The full constellation will be four satellites in each of three 50deg 5591nmi orbits, to be launched two at a time by Atlas 2AS class launchers. Connections will go via one satellite to one of 10-11 ground stations, where they will be routed into the normal phone system; there will be no intersatellite links.


 Program: Offek

First Israeli program


Program: Offek

Offek 1

Offek 2

Offek 3


 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
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
Launch site	Palmahim
Mass at launch
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	Technology
Perigee/Apogee	369/729 km
Inclination	143.4° (retrograd orbit)
Period	95.6 min
Launch vehicle	Shavit
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. With its three-axis stabilization, 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. Equiped with a high-resolution camera.


 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
Launch site	Wallops
Mass at launch
End of life

Decay	9 May 1971


 Program: OGO

Orbiting Geophysical Observatory

American scientific program


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
Launch site	Cape Canaveral
Mass at launch


 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
Launch site	Vandenberg
Mass at launch
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
Launch site	Vandenberg
Mass at launch


 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
Launch site	Vandenberg
Mass at launch
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
Launch site	Cape Canaveral
Mass at launch


 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
Launch site	Vandenberg
Mass at launch
End of life

Decay	12 Oct 1979


 Program: Okean

Soviet 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: Okean

Okean 1

Okean 2

Okean 3

Okean O1


Okean's specifications

Mass at launch	1400 kg
Radar antenna	12 m
Stabilization	3 axis


Okean's payload

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


 Okean 1

General

Designation	19274 / 88056A
Launch date	5 Jul 1988
Country of origin	CIS
Mission	Remote sensing
Perigee/Apogee	606/633 km
Inclination	82.5°
Period	97.1 min
Launch vehicle	Tsyklon
Launch site	Plesetsk
Technical data

Specifications

Payload


 Okean 2

General

Designation	20510 / 90018A
Launch date	28 Feb 1990
Country of origin	CIS
Mission	Remote sensing
Perigee/Apogee	618/645 km
Inclination	82.5°
Period	97.3 min
Launch vehicle	Cyclone
Launch site	Plesetsk
Technical data

Specifications

Payload


 Okean 3

General

Designation	21397 / 91039A
Launch date	4 Jun 1991
Country of origin	CIS
Mission	Remote sensing
Perigee/Apogee	620/655 km
Inclination	82.5°
Period	97.5 min
Launch vehicle
Launch site	Plesetsk
Technical data

Specifications

Payload

Downlink frequency: 137.4 MHz


 Okean O1

General

Designation	23317 / 94066A
Launch date	11 Oct 1994 at 13:30 UT
Country of origin	CIS (Russian/Ukrainian)
Mission	Remote sensing
Perigee/Apogee	631/665 km
Inclination	88.5°
Period	97.7 min
Launch vehicle	Tsiklon
Launch site	Plesetsk


 Olympus

Also called L SAT

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. NASA's radars found it 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. 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.

Technical data

Specifications

Prime contractor	British Aerospace
Platform	Olympus
Mass at launch	2595 kg
Payload mass	359 kg
Length	2.9 m
Width	2.7 m
Height	5.6 m
Solar array	26 m span
DC power	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	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	52.1 dBW
Polarization

Equiped with 5 steerable antennas for numerous experiments (direct TV and HDTV). Also equiped 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.


 Program: Orbcomm

Operated by Orbital Sciences Corp. (Boulder, Colorado)

Telecommunication program: network of 20 LEO satellites to relay the GPS-determined locations of cargo trucks, and data from oil pipeline monitors.


Program: Orbcomm

Orbcomm X

Orbcomm XP 1

Orbcomm FM 1

Orbcomm FM 2


 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

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
Launch site	Vandenberg
Mass at launch

Experimental satellite.


 Orbcomm FM 1

General

Designation	23545 / 95017A
Launch date	3 Apr 1995 at 13:48 UT
Country of origin	United States
Operator	Orbital Communications (OSC's subsidiary)
Mission	Telecommunications
Perigee/Apogee	727/756 km
Inclination	70°
Period
Launch vehicle	Pegasus
Launch site	Vandenberg

The Pegasus was launched from a Lockheed L-1011 carrier airplane.

Has stopped sending signals short after launch.

Technical data

Specifications

Prime contractor	OSC
Platform	Microstar
Mass at launch	40 kg
Mass in orbit
Diameter	1 m
Height	0.16 m
Stabilization
DC power
Design lifetime

Deploys a 3.3 m long VHF/UHF communications antenna and a pair of solar panels spanning 2.2 m.


 Orbcomm FM 2

General

Designation	23546 / 95017A
Launch date	3 Apr 1995 at 13:48 UT
Country of origin	United States
Operator	Orbital Communications (OSC's subsidiary)
Mission	Telecommunications
Perigee/Apogee	727/756 km
Inclination	70°
Period
Launch vehicle	Pegasus
Launch site	Vandenberg

The Pegasus was launched from a Lockheed L-1011 carrier airplane.

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

Prime contractor	OSC
Platform	Microstar
Mass at launch	40 kg
Mass in orbit
Diameter	1 m
Height	0.16 m
Stabilization
DC power
Design lifetime

Deploys a 3.3 m long VHF/UHF communications antenna and a pair of solar panels spanning 2.2 m.


 Program: Orion

American telecommunication program operated by Orion Satellite Corporation

Orion Atlantic is a joint venture of eight multinational corporations: Martin Marietta, British Aerospace and Kingston Communications of England, COM DEV of Canada, Matra of France, Nissho Iwai of Japan, STET of Italy and Orion Network Systems of the United States.

Contact

Orion Network Systems Inc.

2440 Research Boulevard, Suite 400, Rockville, MD 20850, USA

Tel:	US: 1-800-78-ORION
Int: +1-301-258-8101
Fax:	+1-301-258-8119


Program: Orion

Orion 1


Orion's EIRP (Broad beam to Europe)


Orion's EIRP (Spot beams to Europe)


Orion's EIRP (Broad beam to US)


Orion's EIRP (Spot beams to US)


 Orion 1

General

Designation	23413 / 94079A
Launch date	29 Nov 1994 at 10:21 UT
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	37.5°W
Launch vehicle	Atlas 2A AC-110
Launch site	Cape Canaveral LC36A
Mass at launch

Of note is that the Centaur boosted Orion 1 into a supersynchronous transfer orbit, to minimize fuel needed to enter Clarke orbit.

Technical data

EIRP coverage (dBW)

Broad beam to Europe

Spot beams to Europe

Broad beam to US

Spot beams to US

Specifications

Prime contractor	Britsh Aerospace
Platform	Eurostar 2000
Mass at launch
Mass in orbit	2350 kg
Length
Width
Height
Stabilization	3 axis
DC power	3200 W
Design lifetime	12 years
Ku-band

Main transponders	34
Backup transponders
Power	15 W
Bandwidth	6 transponders of 36 MHz 28 transponders of 54 MHz
Coverage	3 spot beams to Europe 4 spot beams to America
EIRP	Spot beam: 50 dBW Zone beam: 45 dBW
Polarization	Linear
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 to Europe (GHz)

Horizontal Downlink	Transponder	Vertical Downlink	Bandwidth
	5	11.483	54 MHz
11.483	14		54 MHz
	6	11.546	54 MHz
11.546	15		54 MHz
	7	11.609	54 MHz
11.609	16		54 MHz
	8	11.672	54 MHz
11.672	17		54 MHz
	1	12.528	54 MHz
12.528	9		54 MHz
	2	12.591	54 MHz
12.591	10		54 MHz
12.645	11		36 MHz
	3	12.654	54 MHz
12.685	12		36 MHz
	4	12.717	54 MHz
12.726	13		36 MHz


Orion 2

Construction is to begin mid-1995

Scheduled for 1997, slot: 12°W (or 47°W?)


Orion 3

Construction is to begin in 1997

slot: 126°E (or 12°W?)


 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.


Program: Oscar

Oscar 01 Oscar 02 Oscar 03 Oscar 04 Oscar 05 AO-06: Oscar 06 AO-07: Oscar 07 AO-08: Oscar 08 Oscar 09 failure UO-09: Uosat 1	AO-10: Oscar 10 UO-11: Uosat 2 FO-12: Fuji 1A AO-13: Oscar 13 UO-14: Uosat 3 UO-15: Uosat 4 AO-16: Pacsat DO-17: Dove WO-18: Webersat LO-19: Lusat	FO-20: Fuji 1B AO-21: Informator UO-22: Uosat 5 KO-23: Kitsat A KO-25: Kitsat B IO-26: Itamsat AO-27: Eyesat PO-28: Posat


 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
Launch site	Vandenberg
Mass at launch
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
Launch site	Vandenberg
Mass at launch
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
Launch site	Vandenberg
Mass at launch


 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
Launch site	Cape Canaveral
Mass at launch
End of life

Decay	12 Apr 1976


 Oscar 05

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
Mass at launch


 Oscar 06

Also called AO-06

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
Mass at launch


  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
Launch site	Vandenberg
Mass at launch


 Oscar 08

Also called AO-08

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
Launch site	Vandenberg
Mass at launch


 Oscar 09 failure

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

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
Technical data

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

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
Mass at launch
Technical data

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.


 Oshumi

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


 Program: OSO

Orbiting Solar Observatory

American Sun observation program


Program: OSO

OSO 1

OSO 2

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
Launch site	Cape Canaveral
Mass at launch
End of life

Decay	8 Oct 1981


 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
Launch site	Cape Canaveral
Mass at launch
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
Launch site	Cape Canaveral
Mass at launch
End of life

Decay	4 Apr 1982


 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
Launch site	Cape Canaveral
Mass at launch
End of life

Decay	15 Jun 1982


 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
Launch site	Cape Canaveral
Mass at launch
End of life

Decay	2 Apr 1984


 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
Launch site	Cape Canaveral
Mass at launch
End of life

Decay	7 Mar 1981


 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
Launch site	Cape Canaveral
Mass at launch
End of life

Decay	9 Jul 1974


 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
Launch site	Cape Canaveral
Mass at launch	1064 kg
End of life

Decay	9 Jul 1986


 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
Platform	OTS
Mass at launch	865 kg
Mass in orbit
Length	2.4 m
Width	2.1 m
Height	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	6.000


OTS' Ku-band

Main transponders	4+2
Backup transponders
Power	20 W
Bandwidth	40 and 120 MHz
Coverage	Hemispheric
EIRP
Polarization	4 linear and 2 circular transponders


 OTS 1

End of life

Out of service	13 Sep 1977 (Friday 13th!)
Cause	Launch failure of a Thor Delta 3914
Technical data

Specifications

Ku-band


 OTS 2

General

Designation	10855 / 78044A
Launch date	11 May 1978
Country of origin	Europe
Mission	Telecommunications
Geostationary orbit
Launch vehicle	Thor Delta 3914
Launch site	Cape Canaveral
Mass at launch
End of life

Out of service	1990
Technical data

Specifications

Ku-band


 Program: OV

Orbiting Vehicle

American program


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
Launch site	Vandenberg
Mass at launch


 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
Launch site	Vandenberg
Mass at launch


 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
Launch site	Vandenberg
Mass at launch


 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
Launch site	Vandenberg
Mass at launch
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
Launch site	Vandenberg
Mass at launch


 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
Launch site	Vandenberg
Mass at launch


 OV 1-13

General

Designation	03173 / 68026A
Launch date	6 Apr 1966
Country of origin	United States
Mission
Perigee/Apogee	564/9241 km
Inclination	99.9°
Period	198.7 min
Launch vehicle
Launch site	Vandenberg
Mass at launch


 OV 1-14

General

Designation	03174 / 68026B
Launch date	6 Apr 1966
Country of origin	United States
Mission
Perigee/Apogee	540/9892 km
Inclination	100°
Period	207.1 min
Launch vehicle
Launch site	Vandenberg
Mass at launch


 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
Launch site	Vandenberg
Mass at launch


 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
Launch site	Vandenberg
Mass at launch


 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
Launch site	Cape Canaveral
Mass at launch
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
Launch site	Cape Canaveral
Mass at launch
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
Perigee/Apogee	35086/35774 km
Inclination	12.7°
Period	1417.9 min
Launch vehicle
Launch site	Cape Canaveral
Mass at launch


 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
Launch site	Vandenberg
Mass at launch


 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
Launch site	Vandenberg
Mass at launch
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
Launch site	Vandenberg
Mass at launch


 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
Launch site	Wallops
Mass at launch


 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
Mass at launch


 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
Mass at launch


 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
Mass at launch


 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
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


 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
Launch site	Vandenberg
Mass at launch

Inflatable 41 meters sphere


 Program: Palapa

Indonesian telecommunication program

The program was developped to solve communications (phone, TV) problems between the numerous islands that compose the country. 2 years after  the Philippines asked to use to system for their national communications. In 1979 Intelsat recognized the system as regional.

Nowadays 6 South Eastern Asia countries use Palapa.

Contact

PT Satellit Palapa Indonesia (Satelindo)

Mulia Center, Suite #1201, Ji HR Rasuna Said Kav X6, N° 8, Jakarta 12940, Indonesia

Tel: +62-21-522-9322

Fax: +62-21-522-9320


Program: Palapa

Palapa A1

Palapa A2

Palapa B1

Palapa B2

Palapa B2 P

Palapa B2 R

Palapa B4


Palapa B's specifications

Prime contractor	Hugues
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	34 dBW
Polarization


 Palapa A1

General

Designation	09009 / 76066A
Launch date	8 Jul 1976
Country of origin	Indonesia
Mission	Telecommunications
Geostationary orbit
Launch vehicle
Launch site	Cape Canaveral
Mass at launch
End of life

Out of service	1985


 Palapa A2

General

Designation	09862 / 77018A
Launch date	10 Mar 1977
Country of origin	Indonesia
Mission	Telecommunications
Geostationary orbit
Launch vehicle
Launch site	Cape Canaveral
Mass at launch
End of life

Out of service	1988


 Palapa B1

General

Designation	14134 / 83059C
Launch date	18 Jun 1983
Country of origin	Indonesia
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	STS 07
Mass at launch
Location

Begin	End	Position
L: 30 Oct 1982
Mar 1995	...	134°E
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 10
Mass at launch

Launched on a bad orbit it was retrieved on 12 Nob 1984 by STS 14. It became Palapa B2R.

Technical data

Specifications

C-band


 Palapa B2P

General

Designation	17706 / 87029A
Launch date	20 Mar 1987
Country of origin	Indonesia
Mission	Telecommunications
Geostationary orbit	113°E
Launch vehicle
Launch site	Cape Canaveral
Technical data

Specifications

C-band

C-band EIRP coverage (dBW)


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
Launch site	Cape Canaveral

Its Palapa B2 retrieved from orbit and modernized.

Technical data

Specifications

C-band

C-band EIRP coverage (dBW)


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
Launch site	Cape Canaveral

Cost: $56.4 million

Technical data

Specifications

C-band


Palapa C1

General

Designation
Launch date	planned in Nov 1995
Country of origin	Indonesia
Mission	Telecommunications
Geostationary orbit
Launch vehicle	Ariane
Mass at launch
Technical data

Mass: 3 tonnes, 32 transponders in C-band and 4 in Ku-band


Palapa C2

General

Designation
Launch date	planned in 1996
Country of origin	Indonesia
Mission	Telecommunications
Geostationary orbit
Launch vehicle	not Ariane
Mass at launch


 Program: Panamsat

American telecommunication program operated by Alpha Lyracom, the first private company to provide international services.

Contact

Alpha Lyracom (PanAmSat)

One Pichwick Plaza, Greenwich, CT 06830, USA

Tel: +1-203-622-6664

Fax: +1-203-622-9163


Program: Panamsat

Panamsat 1

Panamsat 2

Panamsat 3


 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

Specifications

Prime contractor	GE Astro Space
Platform
Mass at launch	1220 kg
Mass in orbit	708 kg
Length	1.63 m
Width	1.32 m
Height	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 Uplink	Vertical Downlink
		1	1	5.945	3.720
5.965	3.740	7	2
		2	3	5.985	3.760
6.005	3.780	8	4
		3	5	6.025	3.800
6.045	3.820	9	6
		4	7	6.065	3.840
6.085	3.860	10	8
		5	9	6.105	3.880
6.125	3.900	11	10
		6	11	6.145	3.920
6.165	3.940	12	12
		13A	13	6.185	3.960
6.205	3.980	16A	14
		13B	15	6.225	4.000
6.245	4.020	16B	16
		14A	17	6.265	4.040
6.285	4.060	17A	18
		14B	19	6.305	4.080
6.325	4.100	17B	20
		16A	21	6.345	4.120
6.365	4.140	18A	22
		16B	23	6.385	4.160
6.405	4.180	18B	24
Ku-band (11.5-11.75 GHz)

Main transponders	6
Backup transponders	1
Power	16.2 W (TWTA)
Bandwidth	72 MHz
Coverage and EIRP	Europe (19, 20 & 21): 47 dBW North America (22, 23 & 24): 45 dBW
Polarization	linear H
Transponder frequency chart (GHz)

Horizontal Uplink	Horizontal Downlink	Transponder
14.040	11.500	19
14.120	11.580	20
14.200	11.660	21
14.280	11.790	22
14.360	11.820	23
14.440	11.900	24


Panamsat 1's EIRP (C-band)


Panamsat 1's EIRP (Ku-band to Europe)


Panamsat 1's EIRP (Ku-band to US)


 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

Ku-band

Specifications

Prime contractor	Hugues
Platform	HS 601
Mass at launch	2920 kg
Mass in orbit
Length
Width
Height
Stabilization	3 axis
DC power	5400 W
Design lifetime	15 years
C-band

Main transponders	16
Backup transponders
Power	34 W
Bandwidth
Coverage and EIRP	Global: 27 dBW CIS, China to Australia: 36 dBW Alaska to California: ?
Polarization
Ku-band

Main transponders	16
Backup transponders
Power	63 W
Bandwidth
Coverage and EIRP	South Korean beam: 50 dBW and rest of Asia: 42 dBW Chinese beam: 50 dBW Australian beam: 46 dBW
Polarization


Panamsat 2's C-band EIRP


Panamsat 2's Ku-band EIRP


 Panamsat 3

Also called PAS 3

General

Designation	n/a
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	Hugues
Platform	HS 601
Mass at launch	2985 kg
Mass in orbit
Length	2.84 m
Width	3.53 m
Height	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
Power
Bandwidth
Coverage and EIRP	America: 36 dBW Europe and Africa
Polarization
Ku-band

Main transponders	16
Backup transponders
Power
Bandwidth	54 MHz
Coverage and EIRP	Europe: 46.2 dBW North America South America
Polarization


Panamsat 4

Also called PAS 4

General

Designation
Launch date	planned in Jul 1995
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	72°E
Launch vehicle	Ariane
Launch site
Mass at launch
Technical data

Specifications

Prime contractor	Hugues
Platform	HS 601
C-band

Main transponders	16
Backup transponders
Power
Bandwidth	54 MHz
Coverage and EIRP	Europe and Africa South-East Asia and Australia Singapore and South of China
Polarization
Ku-band

Main transponders	24
Backup transponders
Power
Bandwidth	16 transponders of 27 MHz 8 transponders of 54 MHz
Coverage and EIRP	Europe Middle East Japan: Indonesia:
Polarization


Panamsat 5

Also called PAS 5

General

Designation
Launch date	planned in 1996
Country of origin	United States
Mission	Telecommunications
Geostationary orbit
Launch vehicle
Launch site
Mass at launch

Will provide up to 225 digital channels for television broadcasting to South America. The satellite will enhance the services provided by the PAS 3 satellite.

Technical data

Specifications

Prime contractor	Space Systems/Loral
Platform	FS-1300
Transponders	30


Hughes has agreed to design and develop a new satellite for

PanAmSat Corp.  The new satellite will be an enhanced version of

Hughes' HS 601 satellite.  The HP version uses gallium arsenide

solar cells, advanced battery technology and a xenon ion-propulsion

system.


 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
Mass at launch
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
Mass at launch
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
Mass at launch
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	Rocket launched from a B52 at 13000 m
Launch site	Vandenberg
Mass at launch	191 kg


 Péole

Means "Préliminaire à EOLE"

General

Designation	04801 / 70109A
Launch date	12 Dec 1970
Country of origin	France
Mission	Scientific: high atmosphere study
Perigee/Apogee	634/750 km
Inclination	15°
Period	98.6 min
Launch vehicle	Diamant B2
Launch site	Kourou
Mass at launch	58 kg

First geodetic satellite of an equatorial orbit

End of life

Out of service	23 Mar 1972
Decay	16 Jun 1980


 Polaire

End of life

Out of service	5 Dec 1971
Cause	Launch failure (Diamant B4)


 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 B P4
Launch site	Kourou
Mass at launch	37 kg

Must test a hydrazin motor. Counterpart of the first Pollux that was destroy at launch with Castor on 22 May 1973.

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.

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)


 Program: Prognoz

Soviet 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 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
Launch site	Tyuratam
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
Launch site	Tyuratam
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
Launch site	Tyuratam
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
Launch site	Tyuratam
Mass at launch


 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
Launch site	Tyuratam
Mass at launch


 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
Launch site	Tyuratam
Mass at launch


 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
Launch site	Tyuratam
Mass at launch
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
Launch site	Tyuratam
Mass at launch


 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	Proton
Launch site	Tyuratam
Mass at launch


 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
Launch site	Tyuratam
Mass at launch


 Prospero

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
Launch site	Woomera
Mass at launch	66 kg

Tested solar cells

Technical data

Transmits on 137.56 MHz


 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
Launch site	Tyuratam
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
Launch site	Tyuratam
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
Launch site	Tyuratam
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
Launch site	Tyuratam
Mass at launch	17 t
End of life

Decay	24 Jul 1969


Radarsat

General

Designation
Launch date	planned in Aug 1995
Country of origin	Canada
Mission	Remote sensing
Perigee/Apogee
Inclination
Period
Launch vehicle	Delta 2
Launch site	Vandenberg
Mass at launch


 Program: Raduga

Soviet telecommunication program operated by RKA

Provides 3 missions: GALS: military telecommunications in X-band (7.25-7.75 GHz); STATSIONAR: telecommunications in C-band and VOLNA: mobile telecommunications in L-band


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 1-1 Raduga 1-2 Raduga 1-3


 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
Launch site	Tyuratam
Mass at launch
End of life

Out of service	yes


 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
Launch site	Tyuratam
Mass at launch
End of life

Out of service	yes


 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
Launch site	Tyuratam
Mass at launch
End of life

Out of service	yes


 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
Launch site	Tyuratam
Mass at launch
End of life

Out of service	yes


 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
Launch site	Tyuratam
Mass at launch
End of life

Out of service	yes


 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
Launch site	Tyuratam
Mass at launch
End of life

Out of service	yes


 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
Launch site	Tyuratam
Mass at launch
End of life

Out of service	yes


 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
Launch site	Tyuratam
Mass at launch
End of life

Out of service	yes


 Raduga 09

General

Designation	12618 / 81069
Launch date	30 Jul 1981
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	??? 25°E
Launch vehicle
Launch site	Tyuratam
Mass at launch
End of life

Out of service	yes


 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
Launch site	Tyuratam
Mass at launch
End of life

Out of service	yes


 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
Launch site	Tyuratam
Mass at launch
End of life

Out of service	yes


 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
Launch site	Tyuratam
Mass at launch
End of life

Out of service	yes


 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
Launch site	Tyuratam
Mass at launch
End of life

Out of service	yes


 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
Launch site	Tyuratam
Mass at launch
End of life

Out of service	yes


 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
Launch site	Tyuratam
Mass at launch
End of life

Out of service	yes


 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
Launch site	Tyuratam
Mass at launch
End of life

Out of service	yes


 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
Launch site	Tyuratam
Mass at launch
End of life

Out of service	yes


 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
Launch site	Tyuratam
Mass at launch
End of life

Out of service	yes


 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
Launch site	Tyuratam
Mass at launch
End of life

Out of service	yes


 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
Launch site	Tyuratam
Mass at launch
End of life

Out of service	yes


 Raduga 21

General

Designation	18631 / 87100A
Launch date	10 Dec 1987
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle
Launch site	Tyuratam
Mass at launch
Location

Begin	End	Position
L: 10 Dec 1987		Statsionar 15, 128°E
?	...	Statsionar 10, 170°W


 Raduga 22

General

Designation	19596 / 88095A
Launch date	20 Oct 1988
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle
Launch site	Tyuratam
Mass at launch
Location

Begin	End	Position
L: 20 Oct 1988		Statsionar 02, 35°E
?		Statsionar 27, 12°E


 Raduga 23

General

Designation	19928 / 89030A
Launch date	14 Apr 1989
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar 08, 25°W
Launch vehicle
Launch site	Tyuratam
Mass at launch


 Raduga 1-1

General

Designation	20083 / 89048A
Launch date	21 Jun 1989
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar 20, 70°E
Launch vehicle	Proton
Launch site	Tyuratam
Mass at launch


 Raduga 24

General

Designation	20367 / 89098A
Launch date	15 Dec 1989
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle
Launch site	Tyuratam
Mass at launch
Location

Begin	End	Position
L: 15 Dec 1989	?	Statsionar 09, 45°E
?		104.6°E


 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
Launch site	Tyuratam
Mass at launch
End of life

Out of service	Mar 1995
Cause	Sent to the junk orbit


 Raduga 26

General

Designation	21016 / 90112A
Launch date	20 Dec 1990
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle
Launch site	Tyuratam
Mass at launch
Location

Begin	End	Position
L: 20 Dec 1990	Feb 1995	Statsionar 03, 85°E
Mar 1995		90°E


 Raduga 1-2

General

Designation	21038 / 90116A
Launch date	27 Dec 1990
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar 09, 45°E
Launch vehicle
Launch site	Tyuratam
Mass at launch


 Raduga 27

General

Designation	21132 / 91014A
Launch date	28 Feb 1991
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar 15, 128°E
Launch vehicle
Launch site	Tyuratam
Mass at launch


 Raduga 28

General

Designation	21821 / 91087A
Launch date	19 Dec 1991
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar 02, 35°E
Launch vehicle
Launch site	Tyuratam
Mass at launch


 Raduga 29

General

Designation	22557 / 93013A
Launch date	25 Mar 1993
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar 27, 12°E
Launch vehicle
Launch site	Tyuratam
Mass at launch


 Raduga 30

General

Designation	22836 / 93062A
Launch date	30 Sep 1993
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar 03, 85°E
Launch vehicle
Launch site	Tyuratam
Mass at launch


 Raduga 1-3

General

Designation	22981 / 94008A
Launch date	5 Feb 1994
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar 09, 45°E
Launch vehicle	Proton K
Launch site	Tyuratam
Mass at launch


 Raduga 31

General

Designation	23010 / 94012A
Launch date	18 Feb 1994 at 07:56 UT
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar 09, 45°E
Launch vehicle	Proton K
Launch site	Tyuratam
Mass at launch


 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
Launch vehicle	Proton K
Launch site	Tyuratam LC81
Mass at launch


 Program: Relay

American experimental telecommunication program operated by NASA.


Program: Relay

Relay 1

Relay 2


 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
Launch site	Cape Canaveral
Mass at launch	80 kg

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

Emission power:10 W


 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
Launch site	Cape Canaveral
Mass at launch	86 kg

Enabled 10 to 70 minutes transmissions

End of life

Out of service	26 Sep 1965


 Program: Resurs

Soviet remote sensing satellite program operated by Priroda.

The F serie satellites had very little lifetime.


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 500 Resurs O0 is Cosmos 1939 Resurs O1-3


Resurs F's specifications

Prime contractor	KB Photon
Mass at launch	6.5 t (capsule 2.5 t)
Diameter	2.3 m
Stabilization	3 axis


Resurs F'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 equiped with an LK 1000 camera and a MK 4 camera


Resurs O's specifications

Prime contractor	VNII Elektromekaniki
Mass at launch	1500 kg
Height	5 m
Solar array	10 m
Stabilization	3 axis


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


 Resurs F01

General

Designation	20006 / 89038A
Launch date	25 May 1989
Country of origin	CIS
Mission	Remote sensing
Perigee/Apogee	174/232 km
Inclination	82.3°
Period	88.6 min
Launch vehicle
Launch site	Plesetsk
Mass at launch
End of life

Decay	17 Jun 1989
Technical data

Specifications

Payload


 Resurs F02

General

Designation	20095 / 89049A
Launch date	27 Jun 1989
Country of origin	CIS
Mission	Remote sensing
Perigee/Apogee	255/269 km
Inclination	82.6°
Period	89.8 min
Launch vehicle
Launch site	Tyuratam
Mass at launch
End of life

Decay	11 Jul 1989
Technical data

Specifications

Payload


 Resurs F03

General

Designation	20134 / 89055A
Launch date	18 Jul 1989
Country of origin	CIS
Mission	Remote sensing
Perigee/Apogee	178/214 km
Inclination	82.6°
Period	88.4 min
Launch vehicle
Launch site	Plesetsk
Mass at launch
End of life

Decay	8 Aug 1989
Technical data

Specifications

Payload


 Resurs F04

General

Designation	20175 / 89063A
Launch date	15 Aug 1989
Country of origin	CIS
Mission	Remote sensing
Perigee/Apogee	178/226 km
Inclination	82.3°
Period	88.5 min
Launch vehicle
Launch site	Tyuratam
Mass at launch

Carries CAMEX (Carrier for Microgravity Experiment), a German experiment for Kayser Threde

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
Perigee/Apogee	176/229 km
Inclination	82.3°
Period	88.6 min
Launch vehicle
Launch site	Plesetsk
Mass at launch
End of life

Decay	22 Sep 1989
Technical data

Specifications

Payload


 Resurs F06

General

Designation	20632 / 90047A
Launch date	29 May 1990
Country of origin	CIS
Mission	Remote sensing
Perigee/Apogee	175/231 km
Inclination	82.4°
Period	88.6 min
Launch vehicle
Launch site	Plesetsk
Mass at launch
End of life

Decay	14 Jun 1990
Technical data

Specifications

Payload


 Resurs F07

General

Designation	20687 / 90060A
Launch date	17 Jul 1990
Country of origin	CIS
Mission	Remote sensing
Perigee/Apogee	177/236 km
Inclination	82.3°
Period	88.6 min
Launch vehicle
Launch site	Plesetsk
Mass at launch
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
Perigee/Apogee	176/229 km
Inclination	82.3°
Period	88.5 min
Launch vehicle
Launch site	Plesetsk
Mass at launch
End of life

Decay	1 Sep 1990
Technical data

Specifications

Payload


 Resurs F09

General

Designation	20794 / 90082A
Launch date	7 Sep 1990
Country of origin	CIS
Mission	Remote sensing
Perigee/Apogee	177/238 km
Inclination	82.5°
Period	88.7 min
Launch vehicle
Launch site	Plesetsk
Mass at launch
End of life

Decay	21 Sep 1990
Technical data

Specifications

Payload


 Resurs F10

General

Designation	21313 / 91035A
Launch date	21 May 1991
Country of origin	CIS
Mission	Remote sensing
Perigee/Apogee	178/242 km
Inclination	82.3°
Period	88.7 min
Launch vehicle
Launch site	Plesetsk
Mass at launch
End of life

Decay	20 Jun 1991
Technical data

Specifications

Payload


 Resurs F11

General

Designation	21524 / 91044A
Launch date	28 Jun 1990
Country of origin	CIS
Mission	Remote sensing
Perigee/Apogee	253/268 km
Inclination	82.3°
Period	89.7 min
Launch vehicle
Launch site	Plesetsk
Mass at launch
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
Perigee/Apogee	178/230 km
Inclination	82.4°
Period	88.6 min
Launch vehicle
Launch site	Plesetsk
Mass at launch
End of life

Decay	8 Aug 1991
Technical data

Specifications

Payload


 Resurs F13

General

Designation	21664 / 91058A
Launch date	21 Aug 1991
Country of origin	CIS
Mission	Remote sensing
Perigee/Apogee	178/240 km
Inclination	82.3°
Period	88.7 min
Launch vehicle
Launch site	Plesetsk
Mass at launch
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
Perigee/Apogee	225/230 km
Inclination	82.1°
Period	89.1 min
Launch vehicle
Launch site	Plesetsk
Mass at launch
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
Perigee/Apogee	177/226 km
Inclination	82.3°
Period	88.5 min
Launch vehicle
Launch site	Plesetsk
Mass at launch
End of life

Decay	9 Jul 1992
Technical data

Specifications

Payload


 Resurs F16

General

Designation	22093 / 92056A
Launch date	19 Aug 1992
Country of origin	CIS
Mission	Remote sensing
Perigee/Apogee	178/226 km
Inclination	82.6°
Period	88.6 min
Launch vehicle
Launch site	Plesetsk
Mass at launch
End of life

Decay	4 Sep 1992
Technical data

Specifications

Payload


 Resurs F17

General

Designation	22663 / 93033A
Launch date	21 May 1993
Country of origin	CIS
Mission	Remote sensing
Perigee/Apogee	176/255 km
Inclination	82.6°
Period	88.8 min
Launch vehicle
Launch site	Plesetsk
Mass at launch
End of life

Decay	20 Jun 1993
Technical data

Specifications

Payload


 Resurs F18

General

Designation	22696 / 93040A
Launch date	25 Jun 1993
Country of origin	CIS
Mission	Remote sensing
Perigee/Apogee	173/240 km
Inclination	82.6°
Period	88.6 min
Launch vehicle
Launch site	Plesetsk
Mass at launch
End of life

Decay	12 Jul 1993
Technical data

Specifications

Payload


 Resurs F19

General

Designation	22777 / 93053A
Launch date	24 Aug 1993
Country of origin	CIS
Mission	Remote sensing
Perigee/Apogee	174/236 km
Inclination	82.6°
Period	88.6 min
Launch vehicle
Launch site	Plesetsk
Mass at launch
End of life

Decay	10 Sep 1993
Technical data

Specifications

Payload


 Resurs 500

General

Designation	22217 / 92075A
Launch date	15 Nov 1992 at 20:45
Country of origin	CIS
Mission
Perigee/Apogee	177/237 km
Inclination	82.6°
Period	88.6 min
Launch vehicle	Semoirka
Launch site	Plesetsk
Mass at launch

Carries objects and messages. After a 6 day flight the capsule falls in the Pacific. It is 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.

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°
Period	98 min
Launch vehicle	Zenith 2
Launch site	Tyuratam LC45
Mass at launch

Carried Safir R1. The payload costed DM 6 million (half financed by DARA)

Technical data

Specifications

Payload


 Program: Rohini

Indian scientific program


Program: Rohini

Rohini 1B

Rohini 2

Rohini 3


Rohini?

Indian satellite for gamma ray studies. Launched by ASLV (Augmented Satellite Launch Vehicle) mass 450/106 kg


 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
Launch site	Sriharikota
Mass at launch	35 kg
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
Inclination	46.2°
Period	90.6 min
Launch vehicle	SLV 3
Launch site	Sriharikota
Mass at launch	38 kg
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	326/485 km
Inclination	46.6°
Period	92.7 min
Launch vehicle	SLV 3
Launch site	Sriharikota
Mass at launch	41.5 kg
End of life

Decay	17 Apr 1983


 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
Launch site	Cape Canaveral

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.

Technical data

Specifications

Prime contractor	Dornier
Mass at launch	2426 kg
Payload mass	1555 kg
Length	2.4 m
Width	2.1 m
Height	4.5 m
Stabilization	3 axis
DC power	EOL: 1000 W
Design lifetime	1.5 years
X-ray telescope

Maximum aperture	835 mm
Focal length	2.4 m
On-axis resolution	1.8 arcsecs
Wavelength	0.6-1 µm
Wield Field Camera

Maximum aperture	576 mm
Focal length	525 mm
On-axis resolution	1 arcmin
Wavelength	0.6-3 µm


 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 at 03:00 UT
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1881/2163 km
Inclination	64.8°
Period	128 min
Launch vehicle	Rokot
Launch site	Tyuratam LC175
Mass at launch	70 kg

The RS-18 (soviet name) or SS-19 (Otan name) launcher is a former 2 stage balistic missile converted to a 3 stage rocket. It can orbit 1800 kg in LEO. First satellite launched by that rocket. The spent third stage exploded a few hours after launch.

The satellite is a spherical-like unit about 1 meter in diameter. 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.

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).

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

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)


 Ryusei

Also called OREX (Orbital Re-entry Experiment vehicle)

General

Designation	22978 / 94007A
Launch date	3 Feb 1994 at 22:20 UT
Country of origin	Japan
Mission	Technology
Perigee/Apogee	6828/6829 km
Inclination	30.5°
Period	93.5 min
Launch vehicle	H2
Launch site	Tanegashima
Mass at launch

Operated by NASDA

End of life

Decay	5 Feb 1994


 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
Platform	UoSAT
Mass at launch	50 kg
Payload mass	7 kg
Length	0.7 m
Width	0.35 m
Height	0.35 m
Stabilization
DC power	Consummation: 41 W
Design lifetime	3 years

Frequencies: uplink: 148 MHz, downlink: 137 MHz


 Program: Safir

Satellite For Information Relay

Program of OHB System (Bremen, Germany) with 6 satellites (3 stand-alone and 3 piggybacked).

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 1

General

Designation
Launch date	planned in mid 1995
Country of origin	Germany
Mission	Telecommunications
Perigee/Apogee
Inclination
Period
Launch vehicle
Launch site
Mass at launch

Safir 1 will be half financed by DARA


SAINT

SAtellite INspector sysTem


 Program: Sakura

Means "cherry tree"

Japanese telecommunications satellite program. Ka-band transponders are used by NTT


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	29 dBW
Polarization


Sakura 3's Ka-band

Main transponders	10
Backup transponders	5
Power	4.2 W (TWTA)
Bandwidth	100 MHz
Coverage
EIRP	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	Delta
Launch site	Cape Canaveral
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
Launch site	Tanegashima
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
Launch site	Tanegashima
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
Launch site	Tanegashima
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	136°E
Launch vehicle	H1
Launch site	Tanegashima
Technical data

Specifications

C-band

Ka-band


 Program: San Marco

Italian high atmosphere study program


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
Launch site	Wallops Island
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
Launch site	San Marco
Mass at launch	128 kg
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
Launch site	San Marco
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
Launch site	San Marco
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
Launch site	San Marco
Mass at launch	235 kg

Designed by Rome's university

End of life

Decay	6 Dec 1988


 Sara

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
Mass at launch	28 kg

Must study Jupiter's radio renvironment. Its signals are received at Nancay (Meudon?), France

Technical data

Specifications

Prime contractor	Club ESIEE Espace
Mass at launch	28 kg
Mass in orbit	20 kg
Design lifetime	11 years

Telemetry beacon: 145.955 MHz, 300 bps FSK, FM


 Program: Sarsat

Search And Rescue Satellite Aided Tracked

International cooperation: United States, Canada, France and since 1979 the CIS which decided to make its system COSPAS compatible.

Mission: search and rescue of persons and boats in distress. Uses Soviet Nadejda satellites and American NOAA satellites. 10 Earth stations and 250000 markers exist. The service was opened on 1 Sep 1982.


 Program: Satcom

Also called RCA

American telecommunication program operated by GE Americom.

Contact

GE Americom

4 Research Way, Princeton, NJ 08540-6684, USA

Tel: +1-609-987-4419


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


Satcom K's specifications

Prime contractor	GE Astro Space
Platform	GE 4000
Mass at launch	1930 kg
Mass in orbit	1050 kg
Length	1.7 m
Width	2.13 m
Height	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	48 dBW
Polarization	linear H/V


 Satcom 1

General

Designation	08479 / 75117C
Launch date	13 Dec 1975
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	80°W
Launch vehicle
Launch site	Cape Canaveral
Mass at launch	465 kg
End of life

Out of service	yes


 Satcom 1R

Also called Satcom 6

General

Designation	13984 / 83030A
Launch date	11 Apr 1983
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	139°W
Launch vehicle	Delta
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	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	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
Launch site	Cape Canaveral
Mass at launch
End of life

Out of service	yes
Location

Begin	End	Position
L: 26 Mar 1976		119°W
1984		72°W


 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	Delta 3924
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	36 dBW
Polarization	linear H/V
Transponder frequency chart (GHz)

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


 Satcom 3

General

Designation	11635 / 79101A
Launch date	7 Dec 1979
Country of origin	United States
Mission	Telecommunications
Geostationary orbit
Launch vehicle
Launch site	Cape Canaveral
End of life

Out of service	7 Dec 1979
Cause	Placed on a bad orbit


 Satcom 3R

General

Designation	12967 / 81114A
Launch date	20 Nov 1981
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	131°W
Launch vehicle	Delta
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	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	Delta
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	1.070 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	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

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
C-band

Main transponders	24
Backup transponders	4
Power	8.5 W
Bandwidth	36 MHz
Coverage
EIRP	36 dBW
Polarization	linear H/V
Transponder frequency chart (GHz)

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


 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
Mass at launch
Technical data

Specifications

Prime contractor	GE Astro Space
Platform
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
Polarization	linear H/V
Transponder frequency chart (GHz)

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


 Satcom C4

General

Designation	22096 / 92057A
Launch date	31 Aug 1992
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	135°W
Launch vehicle
Launch site	Cape Canaveral
Mass at launch
Technical data

C-band

Main transponders	24
Backup transponders
Power	17 W
Bandwidth
Coverage
EIRP
Polarization	linear H/V
Transponder frequency chart (GHz)

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


 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	85°W
Launch vehicle	STS 24
Mass at launch
Technical data

Specifications

Ku-band

Transponder frequency chart (GHz)

Horizontal Uplink	Horizontal Downlink	Transponder	Vertical Uplink	Vertical Downlink
14.0290	11.7290	1
		2	14.0585	11.7585
14.0880	11.7880	3
		4	14.1175	11.8175
14.1470	11.8470	5
		6	14.1765	11.8765
14.2060	11.9060	7
		8	14.2350	11.9350
14.2650	11.9650	9
		10	14.2945	11.9945
14.3240	12.0240	11
		12	14.3535	12.0530
14.3830	12.0830	13
		14	14.4125	12.1125
14.4420	12.1420	15
		16	14.4715	12.1715


 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	81°W
Launch vehicle	STS 23
Mass at launch
Technical data

Specifications

Ku-band

Transponder frequency chart (GHz)

Horizontal Uplink	Horizontal Downlink	Transponder	Vertical Uplink	Vertical Downlink
14.0290	11.7290	1
		2	14.0585	11.7585
14.0880	11.7880	3			Spot to Western US
		4	14.1175	11.8175
14.1470	11.8470	5
		6	14.1765	11.8765
14.2060	11.9060	7
		8	14.2350	11.9350
14.2650	11.9650	9
		10	14.2945	11.9945
14.3240	12.0240	11
		12	14.3535	12.0530
14.3830	12.0830	13
		14	14.4125	12.1125
14.4420	12.1420	15
		16	14.4715	12.1715


SAX

General

Designation
Launch date	planned in Dec 1995
Country of origin	Italy and Netherlands
Mission	Scientic: high energy astrophysics
Perigee/Apogee
Inclination
Period
Launch vehicle	Atlas 1
Launch site	Cape Canaveral
Mass at launch


 Program: SBS

Satellite Business System

Also called CNS (Communication Network Service) or USASAT

First private professional satellite digital communications network. Company created on 15 Dec 1975 by IBM, Comsat and Aetna Life and Casualty Inc. The satellites are owned by STLC (Satellite Transponder Leasing Company) an IBM's subsidiary.


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
Launch site	Cape Canaveral
Mass at launch
End of life

Out of service	yes


 SBS 2

General

Designation	12855 / 81096A
Launch date	24 Sep 1981
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Delta 3910
Launch site	Cape Canaveral
Mass at launch
Location

Begin	End	Position
L: 24 Sep 1981		97°W
Jun 1994	Feb 1995...	71°W
Technical data

Ku-band

Main transponders	10
Backup transponders
Power	8 transponders of 20 W 2 transponders of 40 W
Bandwidth	43 MHz
Coverage
EIRP
Polarization	linear H
Transponder frequency chart (GHz)

Horizontal Uplink	Horizontal Downlink	Transponder
14.025	11.725	1
14.080	11.780	2
14.123	11.823	3
14.172	11.872	4
14.221	11.921	5
14.270	11.970	6
14.319	12.019	7
14.368	12.068	8
14.417	12.117	9
14.466	12.166	10


 SBS 3

General

Designation	13651 / 82110B
Launch date	11 Nov 1982
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	74°W
Launch vehicle	STS 05
Mass at launch
Technical data

Ku-band

Main transponders	10
Backup transponders
Power
Bandwidth
Coverage
EIRP	46 dBW
Polarization


 SBS 4

General

Designation	15235 / 84093B
Launch date	31 Aug 1984
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	77°W
Launch vehicle	STS 12
Technical data

Specifications

Prime contractor	Hugues
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	10
Backup transponders	4
Power	5 transponders of 20 W (TWTA) 5 transponders of 40 W (TWTA)
Bandwidth	43 MHz
Coverage
EIRP	46 dBW
Polarization	linear H
Transponder frequency chart (GHz)

Horizontal Uplink	Horizontal Downlink	Transponder
14.025	11.725	1
14.080	11.780	2
14.123	11.823	3
14.172	11.872	4
14.221	11.921	5
14.270	11.970	6
14.319	12.019	7
14.368	12.068	8
14.417	12.117	9
14.466	12.166	10


 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
Technical data

Specifications

Prime contractor	Hugues
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
EIRP	46 dBW
Polarization	linear H/V
Transponder frequency chart (GHz)

Horizontal Uplink	Horizontal Downlink	Transponder
14.025	11.725	1
14.080	11.780	2
14.123	11.823	3
14.172	11.872	4
14.221	11.921	5
14.270	11.970	6
14.319	12.019	7
14.368	12.068	8
14.417	12.117	9
14.466	12.166	10
14.048	11.748	11
14.198	11.898	12
14.294	11.994	13
14.441	12.141	14


 SBS 6

General

Designation	20872 / 90091A
Launch date	12 Oct 1990
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	95°W
Launch vehicle	Ariane V39
Technical data

EIRP coverage (dBW)

Horizontal

Vertical

Specifications

Prime contractor	Hugues
Platform	HS 393
Mass at launch	2478 kg
Mass in orbit	1514 kg
Diameter	3.66 m
Height	10 m deployed
Stabilization	Spin stabilized
DC power	BOL: 2300 W
Design lifetime	10 years
Ku-band

Main transponders	19
Backup transponders	11
Power	41 W (TWTA)
Bandwidth	43 MHz
Coverage and EIRP	50.4 dBW
Polarization	linear H
Transponder frequency chart (GHz)

Horizontal Uplink	Horizontal Downlink	Transponder
14.0250	11.7250	1
14.0495	11.7495	2
14.0740	11.7740	3
14.0985	11.7985	4
14.1230	11.8230	5
14.1475	11.8475	6
14.1720	11.8720	7
14.1965	11.8965	8
14.2210	11.9210	9
14.2455	11.9455	10
14.2700	11.9700	11
14.2945	11.9945	12
14.3190	12.0190	13
14.3435	12.0435	14
14.3680	12.0680	15
14.3925	12.0925	16
14.4170	12.1170	17
14.4415	12.1415	18
14.4660	12.1660	19


SBS 6's EIRP (Vertical)


SBS 6's EIRP (Horizontal)


 SCD

General

Designation	22490 / 93009B
Launch date	9 Feb 1993
Country of origin	Brazil
Mission	Remote sensing
Perigee/Apogee	729/793 km
Inclination	25°
Period	100.1 min
Launch vehicle	Pegasus
Launch site	Cape Canaveral
Mass at launch

First satellite buit by Brazil. Must provide a map of CO² distribution in atmosphere above South America. Will collected and transmit data from 500 ground platforms.


 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
Launch site	Cape Canaveral
Mass at launch	70 kg

Broadcast President Eisenhower Christmas wishes that had been recorded.

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

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
Cause	Power supply failure
Technical data

Specifications

Prime contractor	Lockheed
Mass at launch	2300 kg
Length	21 m
Stabilization	3 axis
Design lifetime	2 years
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


Seastar

General

Designation
Launch date	planned in May 1995
Country of origin
Mission
Perigee/Apogee
Inclination
Period
Launch vehicle	Pegasus
Launch site
Mass at launch


 Program: Secor

SEquential COllation of Range

Also called EGRS (Experimental Geodetic Research Satellite)

American geodetic satellites for triangulation


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
Launch site
Mass at launch


 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
Launch site	Vandenberg
Mass at launch
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
Launch site	Vandenberg
Mass at launch


 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
Mass at launch


 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
Launch site	Wallops Island
Mass at launch


 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
Mass at launch
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
Mass at launch


 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
Mass at launch


 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
Launch site	Vandenberg
Mass at launch


 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
Launch site	Vandenberg
Mass at launch


 SFU

Space Flyer Unit

General

Designation	23521 / 95011A
Launch date	17 Mar 1995 at 08:01 UT
Country of origin	Japan
Mission	Scientific
Perigee/Apogee	467/496 km
Inclination	28.5°
Period	92 min
Launch vehicle	H2
Launch site	Tanegashima
Mass at launch

The SFU will carry out materials processing, technology and astronomy experiments, and will be retrieved by the STS-72 mission in December. It carries 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 carries 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.


 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


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
Launch site	Tyuratam
Mass at launch	102 kg
End of life

Decay	20 Jun 1979


 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
Launch site
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


 Sirius

General

Old name	BSB 1
Country	Sweden
Mission	Direct TV
Geostationary orbit	5.2°E
Contact

Tele TV AS

Storingsgt 4, 0158 Oslo, Norway

Tel: +47-2-415960

Fax: +47-2-415970

Technical data

Specifications

Ku-band

EIRP coverage (dBW)


Sirius' EIRP


 Program: Skynet

English military program


Program: Skynet

Skynet 1A

Skynet 1B

Skynet 2A

Skynet 2B

Skynet 4A

Skynet 4B

Skynet 4C


Skynet 4's specifications

Prime contractor	British Aerospace
Platform	ECS
Mass at launch	1430 kg
Masse de la charge utile	225 kg
Length	2.2 m
Width
Height	2.3 m
Solar array	16 m span
Stabilization	3 axis
DC power	BOL: 1200 W
Design lifetime	7 years


Skynet 4's UHF-band (250-315 MHz)

Main transponders	2
Backup transponders
Power	40 W
Bandwidth	25 KHz
Coverage
EIRP


Skynet 4's X-band

Main transponders	4
Backup transponders
Power	40 W
Bandwidth	60 and 135 MHz
Coverage
EIRP
Polarization
Frequencies	Downlink:  7.23-7.75 GHz


Skynet 4's EHF-band (42 GHz)

Main transponders	1
Backup transponders
Power
Bandwidth
Coverage
EIRP
Polarization


 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	Delta
Launch site	Cape Canaveral
Mass at launch	125 kg
Location

Begin	End	Position
L: 22 Nov 1969		43°E
Mar 1995	...	107°W


 Skynet 1B

General

Designation	04493 / 70062A
Launch date	19 Aug 1970
Country of origin	United Kingdom
Mission	Military: telecommunications
Geostationary orbit
Launch vehicle	Thor Delta
Launch site	Cape Canaveral
Mass at launch
End of life

Out of service	19 Aug 1970
Cause	Remained on transfert orbit


 Skynet 2A

General

Designation	07096 / 74002A
Launch date	22 Jan 1974
Country of origin	United Kingdom
Mission	Military: telecommunications
Geostationary orbit
Launch vehicle	Thor Delta
Launch site	Cape Canaveral
Mass at launch
End of life

Out of service	22 Jan 1974
Cause	Placed on a bad orbit


 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	Delta
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
Launch site	Cape Canaveral
Location

Begin	End	Position
L: 1 Jan 1990		5°E
Feb 1995		34°W
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		53.4°E
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
Technical data

Specifications

UHF-band

X-band

EHF-band


Skynet 4E

General

Designation
Launch date	planned in 3rd quarter of 1998
Country of origin	United Kingdom
Mission	Military: telecommunications
Geostationary orbit
Launch vehicle	Ariane
Launch site
Mass at launch
Technical data

Specifications

Prime contractor	British Aerospace
Platform
Mass at launch	1510 kg
Mass in orbit
Length
Width
Height
Stabilization
DC power
Design lifetime


 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
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: observation du Soleil
Perigee/Apogee	405/408 km
Inclination	28.5°
Period	92.7 min
Launch vehicle
Launch site	Cape Canaveral
Mass at launch	2315 kg

Studied solar eruption in the year of the most important solar activity

Its the first satellite repared in orbit by the shuttle (STS 11)

End of life

Decay	2 Dec 1989


 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
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


 SMS 2

General

Designation	07648 / 75011A
Launch date	6 Feb 1975
Country of origin	United States
Mission	Meteorology
Geostationary orbit	see below
Launch vehicle
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


Soho

General

Designation
Launch date	planned in Sep 1995
Country of origin	ESA/NASA
Mission	Scientific:
Perigee/Apogee
Inclination
Period
Launch vehicle	Atlas 2AS
Launch site	Cape Canaveral
Mass at launch


 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
Mass at launch


 Program: Solidaridad

Mexican telecommunication program operated by SCT. Replaces Morelos


Program: Solidaridad

Solidaridad 1

Solidaridad 2


Solidaridad's specifications

Prime contractor	Hugues
Platform	HS 601
Mass at launch	2740 kg
Mass in orbit	1650 kg
Length	2.27 m
Width	2.27 m
Height	2.27 m
Solar array	18.3 m span
Stabilization	3 axis
DC power	3300 W
Design lifetime	14 years


Solidaridad's L-band

Main transponders	1
Backup transponders
Power	100 W
Bandwidth	34 MHz
Coverage
EIRP	45 dBW
Polarization


Solidaridad's C-band

Main transponders	18
Backup transponders
Power	10 W (TWTA)
Bandwidth	12 36 MHz transponders 6 72 MHz transponders
Coverage
EIRP	40 dBW
Polarization


Solidaridad's Ku-band

Main transponders	16
Power	42.5 W (TWTA)
Bandwidth	54 MHz
Coverage
EIRP	47 dBW
Polarization


 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
Technical data

Specifications

L-band

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


 Program: Solrad

American astronomy program operated by US Navy and NASA


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
Launch site	Cape Canaveral
Mass at launch


 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
Launch site	Cape Canaveral
Mass at launch


 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
Launch site	Vandenberg
Mass at launch
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
Launch site	Vandenberg
Mass at launch


 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
Launch site	Vandenberg
Mass at launch


 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
Launch site	Vandenberg
Mass at launch


 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
Launch site	Wallops Island
Mass at launch
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
Launch site	Wallops Island
Mass at launch
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
Launch site	Cape Canaveral
Mass at launch


 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
Launch site	Cape Canaveral
Mass at launch


 Solwind

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
Launch site	Vandenberg
Mass at launch
End of life

Decay	20 Jul 1992


 Program: Spacenet

American telecommunication program operated by GE Americom

Contact

GE Americom

4 Research Way, Princeton, NJ 08540-6684, USA

Tel: +1-609-987-4419


Program: Spacenet

Spacenet 1

Spacenet 2

Spacenet 3

Spacenet 3R


Spacenet's specifications

Prime contractor	GE Astro Space
Platform	GE 3000
Mass at launch	1195 kg
Mass in orbit	692 kg
Length	1.63 m
Width	1.32 m
Height	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	36 dBW
Polarization	linear H/V


Spacenet's Ku-band

Main transponders	6
Backup transponders	1
Power	16 W (TWTA)
Bandwidth	72 MHz
Coverage
EIRP	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
Location

Begin	End	Position
L: 23 May 1984		102°W
Feb 1995	...	115.5°E
Technical data

Specifications

C-band

Ku-band


 Spacenet 2

General

Designation	15385 / 84114A
Launch date	10 Nov 1984
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	69°W
Launch vehicle	Ariane V11
Technical data

Specifications

C-band

Ku-band

C-band transponder frequency chart (GHz)

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

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


 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	87°W
Launch vehicle	Ariane V21
Technical data

Specifications

C-band

Ku-band

Carries at least 1 L-band transponder used by Qualcomm Inc. for a localization service

C-band transponder frequency chart (GHz)

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

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


Program: Spaceway

Project of Hugues: geostationary satellites in 5 different slots (25°E, 50°W, 110°W, 175°E). Up to 4 satellites per slot. uplink: 29-30 GHz, downlink: 19.2-20.2 GHz With 48 spots (of 650 km diameter)

It would provide 11520 data circuits Global cost of the project: $3.2 billion. The first satellite in Europe should be launched in 1998


 Program: Spartan

American scientific program. The satellites carry experiments in space with the Shuttle.


Program: Spartan

Spartan 201-1

Spartan 201-2

Spartan 201-3

Spartan 201-4


 Spartan 201-1

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 18
Mass at launch
End of life

Cause	Retrieved by the Shuttle
Decay	24 Jun 1985


 Spartan 201-2

General

Designation	22623 / 93023B
Launch date	10 Apr 1993
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
End of life

Cause	Retrieved by the Shuttle
Decay	13 Apr 1993


 Spartan 201-3

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
Mass at launch

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 201-4

Also called Spartan 204

General

Designation	23470 / 95004B
Launch date	7 Feb 1995 at 12:26 UT
Country of origin	United States
Mission	Scientific: astronomy
Perigee/Apogee	310/342 km
Inclination	51.6°
Period	91 min
Launch vehicle	STS 63
Mass at launch

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


 Program: Spas

Shuttle PAllet Satellite

Reusable free-flying multi-purpose platform on which experiments can be carried into space by the space shuttle.

Technical data

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


Program: Spas

Spas 1

Spas 1A

Spas 2

Spas 3


 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
Mass at launch
End of life

Cause	Retrieved by the Shuttle
Decay	24 Jun 1983


 Spas 1A

Also called 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 10
Mass at launch
End of life

Cause	Retrieved by the Shuttle
Decay	11 Feb 1984


 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
Mass at launch
End of life

Cause	Retrieved by the Shuttle
Decay	6 May 1991


 Spas 3

Also called Orfeus

General

Designation	22798 / 93058C
Launch date	12 Sep 1993
Country of origin	Germany
Mission	Scientific
Perigee/Apogee	301/331 km
Inclination	28.5°
Period	90.9 min
Launch vehicle	STS 51
Mass at launch
End of life

Cause	Retrieved by the Shuttle
Decay	22 Sep 1993


 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


 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.


Program: Spot

Spot 1

Spot 2

Spot 3


Spot 1, 2 & 3's specifications

Prime contractor	Matra Marconi Space
Platform	Spot
Mass at launch	1900 kg
Payload mass	790 kg
Length	2 m
Width	2 m
Height	3.5 m
Solar array	8 m span
Stabilization	3 axis
DC power	1100 W
Design lifetime	3 years
Telemetry/data	X-band


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
Technical data

Specifications

Payload


 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
Technical data

Specifications

Payload

Beacon frequency: 8.307 GHz. Data: 8.253 GHz; output rate: 2 x 25 Mbit/s


 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)

Technical data

Specifications

Payload


Spot 4

Will have an MK2 platform for more payload & lifetime


 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 01

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 (R7)
Launch site	Tyuratam
Mass at launch	83.6 kg

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


 Sputnik 02

General

Designation	00003 / 57002A
Launch date	3 Nov 1957
Country of origin	CIS
Mission	Scientific: Sun observation
Perigee/Apogee	212/1660 km
Inclination	65.3°
Period	103.7 min
Launch vehicle
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


 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
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
Launch site	Tyuratam
Mass at launch
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
Mass at launch
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
Mass at launch
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
Mass at launch
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
Mass at launch

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
Mass at launch

Vostok 1 repetition

End of life

Decay	25 Mar 1961


 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
Launch site	Plesetsk
Mass at launch	15 kg

Technological satellite to test solar cell

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
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

End of life

Out of service	24 Mar 1987
Cause	ASLV launch failure


 Sross 2

General

Designation
Launch date	13 Jul 1988???
Country of origin	India
Mission
Perigee/Apogee
Inclination
Period
Launch vehicle	ASLV
Launch site
Mass at launch


 Sross 3

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
Launch site	Srikarikota
Mass at launch
End of life

Decay	14 Jul 1992


 Sross C2

General

Designation	23099 / 94027A
Launch date	4 May 1994 at 00:00 UT
Country of origin	India
Mission	Scientific: ionosphere study
Perigee/Apogee	430/619 km
Inclination	46°
Period	95.1 min
Launch vehicle	ASLU-D4
Launch site	Srikarikota
Mass at launch	113 kg

It carried a Retarding Potential Analyzer (RPA) for measuring ionospheric plasma, and a Gamma ray detector.


Program: SSTP

Space Spacecraft Technology Program

scheduled for 1995, 230 kg, remote sensing


 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
Perigee/Apogee	805/1108 km
Inclination	49.8°
Period	104.2 min
Launch vehicle	Diamant B P4 N° 1
Launch site	Kourou
Mass at launch	47 kg

Sphere of 24 cm of uranium covered with reflectors. Measured the continental drift.


 Program: Statsionar

Soviet denomination for geostationary slots reservation used by Raduga and Gorizont satellites.


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		Raduga 28


 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		Raduga 26
30 Sep 1993		Raduga 30


 Statsionar 04

Location: 14°W

Begin	End	Satellite
14 Jun 1980		Gorizont 04
30 Mar 1988		Gorizont 15
20 Jun 1990		Gorizont 20
13 Oct 1994		Express 01


 Statsionar 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		Gorizont 27


 Statsionar 06

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

Location: 140°E

Begin	End	Satellite
11 May 1987		Gorizont 14
6 Jul 1989		Gorizont 18


 Statsionar 08

Location: 25°W

Begin	End	Satellite
5 Oct 1980		Raduga 07
17 Jan 1986		Raduga 18
14 Apr 1989		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		Raduga 31


 Statsionar 10

Location: 170°W

Begin	End	Satellite
20 Oct 1982		Gorizont 06
25 Oct 1986		Raduga 19
?		Raduga 21


 Statsionar 11

Location: 11°W

Begin	End	Satellite
30 Jun 1983		Gorizont 07
15 Jul 1992		Gorizont 26


 Statsionar 12

Location: 40°E

Begin	End	Satellite
10 Jun 1986		Gorizont 12
23 Nov 1990		Gorizont 22


 Statsionar 13

Location: 80°E

Begin	End	Satellite
1 Aug 1984		Gorizont 10
18 Aug 1988		Gorizont 16
23 Oct 1991		Gorizont 24


 Statsionar 14

Location: 96.5°E

Begin	End	Satellite
15 Mar 1982		Gorizont 05
28 Sep 1989		Gorizont 19


 Statsionar 15

Location: 128°E

Begin	End	Satellite
22 Jun 1984		Raduga 15
10 Dec 1987	? moved	Raduga 21
28 Feb 1991		Raduga 27


 Statsionar 16

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		Raduga 1-1
15 Feb 1990		Raduga 25
28 Dec 1994		Raduga 32


 Statsionar 21

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		Raduga 1-2
5 Feb 1994		Raduga 1-3


 Statsionar 25

Location: 37.5°W

Begin	End	Satellite


 Statsionar 26

Location: 155°W

Begin	End	Satellite


 Statsionar 27

Location: 12°E

Begin	End	Satellite
?		Raduga 22
25 Mar 1993		Raduga 29


 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
Mass at launch
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 its 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.


 STEP 1

Space Test Experiment Platform 1, also called P90 A

General

Designation	n/a
Launch date	27 Jun 1994
Country of origin	United States
Mission	Military: technology
Perigee/Apogee	n/a
Inclination	n/a
Period	n/a
Launch vehicle	Pegasus XL
Launch site	plane: L-1011 Tristar
Mass at launch

Operated by USAF and built by TRW from an Eagle platform

End of life

Out of service	27 Jun 1994
Cause	Destroyed on launch: the launcher exploded (2nd stage) destroying the satellite


 STEP 2

Space Test Experiment Platform 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
Launch site	Vandenberg?
Mass at launch

Operated by USAF and built by TRW from an Eagle platform


 Program: STRV

Space Technology Research Vehicle

English experimental program operated by DRA. Must test spacecraft systems and technologies in orbit and investigate the effect of high radiation doses, atomic oxygen reosion and spacecraft charging.


Program: STRV

STRV 1A

STRV 1B


STRV's specifications

Prime contractor	DRA (Defense Research Agency) Aerospace Division
Mass at launch	50 kg
Length	0.4 m
Width	0.5 m
Height	0.5 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

Designed to 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

Designed to test new solar cells and measure static charge on its surfaces.

Technical data

Specifications

Payload

Spin rate: 5 rpm


 Program: Superbird

Japanese telecommunication program operated by the Space Communications Corporation (SCC)


Program: Superbird

Superbird A1

Superbird A2

Superbird B1

Superbird D


Superbird's specifications

Prime contractor	Ford Aerospace/Loral Space Systems
Platform	Ford FS 1300
Mass at launch	2492 kg
Mass in orbit	1505 kg
Length	2.41 m
Width	2.58 m
Height	2.2 m
Solar array	20.3 m span
Stabilization	3 axis
DC power	4460 W
Design lifetime	10 years


Superbird's X-band

Main transponders	2
Backup transponders
Power	40 W (TWTA)
Bandwidth	40 MHz
Coverage
EIRP	37 dBW
Polarization


Superbird's Ku-band

Main transponders	19
Backup transponders
Power	35 W (TWTA)
Bandwidth	36 MHz
Coverage
EIRP	53 dBW
Polarization


Superbird's Ka-band

Main transponders	3 (spot beam)+7
Backup transponders
Power	29 W (TWTA)
Bandwidth	100 MHz
Coverage
EIRP	spot beam: 59 dBW others: 55 dBW
Polarization


 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 D

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

Ka-band

Ku-band EIRP coverage (dBW)


Superbird B1's EIRP


 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

Ka-band


Superbird C

Satellite based on an HS 601 platform. 24 active transponders to carry television signals and business-communications services throughout Japan, Southern and Eastern Asia and Hawaii.

In addition to two conventional antennas the spacecraft will also feature a steerable spot beam designed and built by Mitsubishi to increase service where needed.


Surfsat 1

General

Designation
Launch date	planned in Aug 1995
Country of origin	Canada
Mission
Perigee/Apogee
Inclination
Period
Launch vehicle	Delta 2
Launch site	Vandenberg
Mass at launch


SWAS

General

Designation
Launch date	planned in Kun 1995
Country of origin	United States
Mission	Scientific:
Perigee/Apogee
Inclination
Period
Launch vehicle	Pegasus
Launch site
Mass at launch


 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 and SAT.


Program: Symphonie

Symphonie 1

Symphonie 2


Symphonie's specifications

Capacity	2 TV channels or 600 phone circuits
Stabilization	3 axis
DC power	300 W
Design lifetime	5 years


 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 2914
Launch site	Cape Canaveral
Mass at launch	400 kg
Location

Begin	End	Position
L: 19 Dec 1974	1977	11.5°W
1977	Aug 1979	Indian ocean (for India)
Aug 1979	19 Feb 1983	Atlantic ocean
End of life

Out of service	19 Feb 1983
Technical data

Specifications


 Symphonie 2

General

Designation	08132 / 75077A
Launch date	27 Aug 1975
Country of origin	Germany and France
Mission	Telecommunications
Geostationary orbit	26°W
Launch vehicle	Thor Delta 2914
Launch site	Cape Canaveral
Mass at launch	400 kg
End of life

Out of service	yes
Technical data

Specifications


 Program: Syncom

SYNchronous COMmunication

First american geostationary program. Satellites built by Hugues Aircraft


Program: Syncom

Syncom 1

Syncom 2

Syncom 3


 Syncom 1

General

Designation	00553 / 63004A
Launch date	14 Feb 1963
Country of origin	United States
Mission	Telecommunications
Geostationary orbit
Launch vehicle	Thor Delta
Launch site	Cape Canaveral
Mass at launch	39 kg
End of life

Out of service	14 Feb 1963
Cause	Lost on the way to geostationary orbit


 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
Launch site	Cape Canaveral
Mass at launch	40.5 kg

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


 Syncom 3

General

Designation	00858 / 64047A
Launch date	19 Aug 1964
Country of origin	United States
Mission	Telecommunications
Geostationary orbit
Launch vehicle
Launch site	Cape Canaveral
Mass at launch	40 kg

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


 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


 Program: Tansei

Means "blue light necklace"

Japanese program


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
Perigee/Apogee	986/1106 km
Inclination	29.7°
Period	106.1 min
Launch vehicle	Mu 4S
Launch site	Kagoshima
Mass at launch	63 kg


 Tansei 2

General

Designation	07122 / 74008A
Launch date	16 Feb 1974
Country of origin	Japan
Mission
Perigee/Apogee	284/3231 km
Inclination	31.2°
Period	121.7 min
Launch vehicle	Mu 4C
Launch site	Kagoshima
Mass at launch	56 kg
End of life

Decay	22 Jan 1983


 Tansei 3

General

Designation	09841 / 77012A
Launch date	19 Feb 1977
Country of origin	Japan
Mission
Perigee/Apogee	796/3804 km
Inclination	65.8°
Period	134.1 min
Launch vehicle
Launch site	Kagoshima
Mass at launch


 Tansei 4

General

Designation	11706 / 80015A
Launch date	17 Feb 1980
Country of origin	Japan
Mission
Perigee/Apogee	517/608 km
Inclination	38.7°
Period	95.9 min
Launch vehicle
Launch site	Kagoshima
Mass at launch
End of life

Decay	12 May 1983


 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
Launch site	Vandenberg
Mass at launch	472 kg
End of life

Decay	9 Jan 1980


 Program: TDF

Télédiffusion De France

French direct TV program operated by TDF. Designed to promote the D2MAC TV standard

Contact

TDF

21-27 rue Barbès, 92120 Montrouge, France

Tel: +33-1-4965-1000

Fax: +33-1-4657-4850


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	220 kg
Length	2.4 m
Width	1.65 m
Height	6.4 m
Solar array	19.3 m span
Stabilization	3 axis
DC power	BOL: 4500 W EOL: 3200 W
Design lifetime	7 years


TDF's Ku-band

Main transponders	5
Backup transponders	1
Power	230 W
Bandwidth	27 MHz
Coverage and EIRP	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
Technical data

Specifications

Ku-band

EIRP coverage (dBW)

Transponder 1 was destroyed by propellant leaks.


 TDF 2

General

Designation	20705 / 90063A
Launch date	24 Jul 1990
Country of origin	France
Mission	Direct TV
Geostationary orbit	18.9°W
Launch vehicle	Ariane V37
Technical data

Specifications

Ku-band

EIRP coverage (dBW)


 Program: TDRS

Tracking and Data Relay Satellite

American telecommunication program operated by NASA. 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. Control center is in White Sands, New Mexico.

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 and other military missions.

Contact

Columbia Communications Corp.

888 17th Street NW, 12th floor, Washington DC 20006, USA

Tel: +1-202-429-9033

Fax: +1-202-296-2962


Program: TDRS

TDRS 1

TDRS 2

TDRS 3

TDRS 4

TDRS 5

TDRS 6


TDRS's specifications

Prime contractor	Contel & NASA
Platform	TRW Space and Communications
Mass at launch	approx. 2200 kg
Mass in orbit	? 2120 kg
Dimensions	Hexagonal shape
Stabilization	3 axis
DC power	2000 W
Design lifetime	10 years

Serie made of 7 satellites. The satellites can communicate without the help of a ground station.


TDRS's S-band

Main transponders	2+8
Backup transponders	2+4
Power	(2+2) transponders of 26 W (8+4) transponders of 3.5 W
Bandwidth
Coverage
EIRP
Polarization


TDRS's C-band

Main transponders	12
Backup transponders
Power	5 W
Bandwidth	36 MHz
Coverage
EIRP	32 dBW
Polarization


TDRS's Ku-band

Main transponders	4+2
Backup transponders	2+2
Power	(4+2) transponders of 25 W (2+2) transponders of 1.5 W?
Bandwidth	50 & 225 MHz
Coverage
EIRP	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.

Location

Begin	End	Position
L: 4 Apr 1983		GTO
17 Oct 1983		41°W
1989		79°W
Feb 1995	...	85°E
End of life

Out of service	yes
Technical data

Specifications

S-band

C-band

Ku-band


 TDRS 2

General

Designation	n/a
Launch date	28 Jan 1986
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	n/a
Launch vehicle	STS 25
End of life

Out of service	28 Jan 1986
Cause	Explosed 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 26
Location

Begin	End	Position
L: 29 Sep 1988	Apr 1995	171°W
Jun 1995	...	85°E
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
Launch vehicle	STS 29
Technical data

Specifications

S-band

C-band

Ku-band

C-band

Ku-band downlink:13.750-15.115 GHz. Beacon: 2.211 GHz


TDRS 4's C-band EIRP


 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
Technical data

Specifications

S-band

C-band

Ku-band


 TDRS 6

General

Designation	22314 / 93003B
Launch date	13 Jan 1993
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	46°W
Launch vehicle	STS 54
Technical data

Specifications

S-band

C-band

Ku-band


TDRS 7

Also called TDRS G

General

Designation
Launch date	Jun 1995
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	171°W
Launch vehicle	STS 70 and Inertial Upper Stage

The IUS consists of two Solid Rocket Motors (SRM's) which will inject the TDRS/IUS into geostationary orbit.  The IUS SRM-1 will first place the TDRS/IUS into a transfer orbit with an apogee near geosynchronous altitude. At the first apogee the IUS SRM-2 will fire to place the TDRS/IUS in geostationary orbit. The TDRS/IUS will be maneuvered to the appropriate orientation and TDRS-G will separate from the IUS.

Technical data

Specifications

S-band

C-band

Ku-band


TDRS 8, 9 & 10

Those 3 satellites will be built by Hugues and made from an modified HS 601 platform


 TELE X

General

Designation	19919 / 89027A
Launch date	2 Apr 1989
Country of origin	Sweden
Mission	Direct TV
Geostationary orbit	5°E
Launch vehicle	Ariane V30
Contact

Swedish Space Corporation

PO Box 4207, 17104 Solna, Sweden

Tel: +46-8-6276200

Fax: +46-8-987069

Technical data

EIRP coverage (dBW)

Specifications

Prime contractor	Eurosatellite & Aérospatiale
Platform	Spacebus 300
Mass at launch	2089 kg
Masse de la charge utile	170 kg
Length	2.4 m
Width	1.65 m
Height	2.4 m
Solar array	19 m span
Stabilization	3 axis
DC power	BOL: 3200 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	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 (designed by the CNES).

Mission: telecommunication to over-sea territories, military communications and TV and data transmission.

Contact

France Telecom

103 rue de Grenelle, 75007 Paris, France

Tel: +33-1-4444-4522

Fax: +33-1-4555-9072


Program: Telecom

Telecom 1A

Telecom 1B

Telecom 1C

Telecom 2A

Telecom 2B


Telecom 1's specifications

Prime contractor	Matra Marconi Espace
Platform	ECS
Mass at launch	1210 kg
Mass in orbit	653 kg
Payload mass	140 kg
Length	2.06 m
Width	1.9 m
Height	2.2 m
Solar array	16 m span
Stabilization	3 axis
DC power	1150 W
Design lifetime	7 years


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	Hemispheric
EIRP	35.5 dBW
Polarization


Telecom 1's X-band

Main transponders	2
Power	20 W (TWTA)
Bandwidth
Coverage	Atlantic and Indian ocean
EIRP	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	49 dBW
Polarization	lineair V
Transponder frequency chart (GHz)

Transponder	Vertical Downlink
K1	12.522
K2	12.564
K3	12.606
K4	12.648
K5	12.690
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	400 kg
Length	2 m
Width	2.1 m
Height	2 m
Solar array	22 m span
Stabilization	3 axis
DC power	BOL: 3850 W EOL: 3450 W
Design lifetime	10 years

Equiped with nickel hydrogen 86 A/H batteries


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 montante	Global
Coverage descendante	Spot: France, St Pierre & Miquelon, West Indies and Guyana Semi global: Reunion
EIRP	Spot: 39 dBW Semi global: 32.5 dBW
Polarization	circular R/L
Capacity	16000 phone circuits and 4 TV channels
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


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	40, 60 & 80 MHz
Coverage	global: center Europe & mobile
EIRP	31.3 dBW
Access	MRF (Multiple à Répartition en Fréquence) or MRC (Multiple à Répartition par Code)


Telecom 2's Ku-band

Main transponders	11
Backup transponders	4
Power	55 W (TWTA)
Bandwidth	36 MHz
Coverage and EIRP	Europe: 52.5 dBW
Polarization	linear H/V
Transponder frequency chart (GHz)

Horizontal Downlink	Transponder	Vertical Downlink
	K1	12.522
12.543	K7
	K2	12.564
12.585	K8
	K3	12.606
12.627	K9
	K4	12.648
12.669	K10
	K5	12.690
12.711	K11
	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	...	3°E
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

Technical data

Specifications

C-band

X-band

Ku-band

EIRP coverage (dBW)

C-band

Ku-band

Ku-band

Bandwidth	32 MHz
Video excursion	22 MHz/v
Mono bandwidth	310 KHz
Mono de-emphasis	50 µs
Stereo bandwidth	130 KHz
Stereo de-emphasis	75 µs
Stereo expansion	Panda 1


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

Ku-band

Bandwidth	32 MHz
Video excursion	22 MHz/v
Mono bandwidth	180 KHz
Mono de-emphasis	J17
Mono expansion	Alcatel
Stereo bandwidth	130 KHz
Stereo de-emphasis	J17
Stereo expansion	Alcatel


Telecom 2B's C-band EIRP


Telecom 2C

General

Designation
Launch date	planned in Aug 1995
Country of origin	France
Mission	Telecommunications
Geostationary orbit	3°E
Launch vehicle	Ariane
Mass at launch


 Program: Telstar

American telecommunication program operated by AT&T

Contact

AT&T Skynet services

Route 202-206, Room 2A-101, Bedminster, NJ 07921, USA

Tel: +1-201-234-4354

Fax: +1-201-234-7940


Program: Telstar

Telstar 1

Telstar 2

Telstar 301

Telstar 302

Telstar 303

Telstar 401

Telstar 402


Telstar 3's specifications

Prime contractor	Hugues
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	18+12
Backup transponders
Power	18 transponders of 5.5 W 12 transponders of 5.5 W (TWTA)
Bandwidth	36 MHz
Coverage and EIRP	CONUS: 34 dBW
Polarization	linear H/V

Maybe 24 transponders of 8.5 W with a 36 dBW EIRP?


Telstar 4's specifications

Prime contractor	GE Astro Space
Platform	GE 7000
Mass at launch	3331 kg
Mass in orbit
Length	2.22 m
Width	2.54 m
Height	4.08 m
Solar array	24.5 m span
Stabilization	3 axis
DC power	BOL: 6400 W
Design lifetime	12 years


Telstar 4's C-band

Main transponders	24
Backup transponders	4
Power	variable 11-21 W
Bandwidth	36 MHz
Coverage
EIRP	38 dBW
Polarization	linear H/V


Telstar 4's Ku-band

Main transponders	16
Backup transponders	6
Power	variable 60-120 W (TWTA)
Bandwidth	54 MHz
Coverage
EIRP	50 dBW
Polarization


Telstar 30x's EIRP


 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
Launch site	Cape Canaveral
Mass at launch	80 kg

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!

End of life

Out of service	21 Feb 1963


 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
Launch site	Cape Canaveral
Mass at launch	79.5 kg
End of life

Out of service	May 1965


 Telstar 301

General

Designation	14234 / 83077A
Launch date	28 Jul 1983
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Delta 3920
Launch site	Cape Canaveral
Mass at launch
Location

Begin	End	Position
L: 28 Jul 1983		96°W
Mar 1994	Aug 1994	107.3°W (Anik E2 replacement)
Jan 1995	...	see Arabsat 1E
Technical data

EIRP coverage (dBW)

Specifications

C-band

Transponder frequency chart (GHz)

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


 Telstar 302

General

Designation	15237 / 84093D
Launch date	1 Sep 1984
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	85°W
Launch vehicle	STS 12
Technical data

EIRP coverage (dBW)

Specifications

C-band

Transponder frequency chart (GHz)

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


 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 18
Location

Begin	End	Position
L: 19 Jun 1985		125°W
May 1992	Feb 1995...	123°W
Technical data

EIRP coverage (dBW)

Specifications

C-band

Transponder frequency chart (GHz)

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


 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 2AS
Launch site	Cape Canaveral
Technical data

Specifications

C-band

Ku-band

EIRP coverage (dBW)

C-band

Ku-band


Telstar 401's C-band EIRP


Telstar 401's Ku-band EIRP


 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	Kick apogee motor failure?
Technical data

Specifications

C-band

Ku-band


Telstar 402R

being readyed for a launch in late-1995.


Telstar 5

Planned in mid-1997 for 93° W slot

Designed with 28 100-Watt Ku-band transponders and 24 16-Watt C-band transponders.


Telstar 6

Planned in 1999 for 129° W slot

Designed with 28 100-Watt Ku-band transponders and 24 16-Watt C-band transponders.


Telstar 7

Planned in 2000 for 83° W slot

Designed with 28 100-Watt Ku-band transponders and 24 16-Watt C-band transponders.


 Temisat

General

Designation	22783 / 93055B
Launch date	31 Aug 1993
Country of origin	Italy
Operator	Telespazio
Mission	Telecommunications
Perigee/Apogee	932/967 km
Inclination	82.5°
Period	104 min
Launch vehicle
Launch site	Plesetsk
Mass at launch
Technical data

Specifications

Prime contractor	Kayser-Threde


 Program: Thaicom

Thai telecommunication program operated by Shinawatra

Contact

Shinawatra Satellite Company Ltd

41/103 Rattanathibet Road, Nonthaburi, 11000, Thailand

Tel: +662-591-0736

Fax: +662-591-0706


Program: Thaicom

Thaicom 1

Thaicom 2


Thaicom's specifications

Prime contractor	Hugues
Platform	HS 376
Mass at launch	1080 kg
Mass in orbit	629 kg
Diameter	2.16 m
Height	6.6 m deployed
Stabilization	Spin stabilized
DC power	BOL: 700 W
Design lifetime	10 years
Perigee motor	Star 30 BP


Thaicom's C-band

Main transponders	10
Backup transponders	2
Power	11 W
Bandwidth	36 MHz
Coverage and EIRP	South Eastern Asia: 37 dBW
Polarization	linear


Thaicom's Ku-band

Main transponders	2
Backup transponders	1
Power	47 W (TWTA)
Bandwidth	54 MHz
Coverage and EIRP	Thailand: 50 dBW
Polarization	linear


Thaicom C-band's EIRP


Thaicom Ku-band's EIRP


 Thaicom 1

General

Designation	22931 / 93078B
Launch date	18 Dec 1993
Country of origin	Thailand
Mission	Telecommunications
Geostationary orbit	78.5°E
Launch vehicle	Ariane V62

First Thai satellite

Technical data

Specifications

C-band

Ku-band

Polarization: H

EIRP coverage (dBW)

C-band

Ku-band


 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

Polarization: V

EIRP coverage (dBW)

C-band

Ku-band


Thaicom 3

planned for 1996

Cost: $200 million

Thaicom 4 should be launched 6 months after Thaicom 3

Technical data

Specifications

Prime contractor	Aerospatiale
Platform
Mass at launch	2700 kg
Mass in orbit
Length
Width
Height
Stabilization
DC power
Design lifetime
C-band

Main transponders	24
Backup transponders
Power
Bandwidth
Coverage
EIRP
Polarization
Ku-band

Main transponders	12
Backup transponders
Power
Bandwidth
Coverage
EIRP
Polarization


 Thor

General

Old name	BSB 2
Country	Norway
Mission	Direct TV
Geostationary orbit	0.8°W

Bought for $42 million

Contact

Tele TV AS

Storingst 4, 0158 Oslo, Norway

Tel: +47-2-415960

Fax: +47-2-415970

Technical data

Specifications

Ku-band

EIRP Coverage (dBW)


Thor's EIRP


 Program: Tiros

Television and Infra Red Observation Satellite

American meteorological program


Program: Tiros

Tiros 01

Tiros 02

Tiros 03

Tiros 04

Tiros 05

Tiros 06

Tiros 07

Tiros 08

Tiros 09

Tiros 10


 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
Launch site	Cape Canaveral
Mass at launch


 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	Delta
Launch site	Cape Canaveral
Mass at launch


 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	Delta
Launch site	Cape Canaveral
Mass at launch


 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
Launch site	Cape Canaveral
Mass at launch


 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
Launch site	Cape Canaveral
Mass at launch


 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
Launch site	Cape Canaveral
Mass at launch
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
Launch site	Vandenberg
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	Delta
Launch site	Cape Canaveral
Mass at launch


 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
Launch site	Cape Canaveral
Mass at launch


 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
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.

Technical data

Specifications

Prime contractor	Jet Propulsion Laboratory (+ bus: Fairchild, Poseidon: Alcatel Espace)
Mass at launch	2100 kg
DC power	1500 W
Design lifetime	4 years
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 B3
Launch site	Kourou
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
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).


 Program: Transit

American navigation program

First navigation program launched in 1959 by the US Navy. it was operational in 1964 and commercialized in 1967. Nova is the evoluted program

First geodetic program to use the Doppler effect.


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
Launch site	Cape Canaveral
Mass at launch


 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
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
Launch site	Cape Canaveral
Mass at launch	90.4 kg

Was launched with Traac: first time 2 satellites were launched with the same vehicle


 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
Launch site	Vandenberg
Mass at launch


 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
Launch site	Vandenberg
Mass at launch


 TTS

Tethered Test Satellite, also called TSS (Tethered Satellite System)

General

Designation	n/a
Launch date	6 Aug 1992
Country of origin	Italy
Operator	CNR/PSN/NASA
Mission	Scientific
Perigee/Apogee
Inclination
Period
Launch vehicle	STS 46

First satellite pulled by a cable to test power production (by induction). The satellite couldn't be deployed properly on STS 46.

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


 Program: Tubsat

Technische Universität Berlin SATellit

German small satellites program


Program: Tubsat

Tubsat A

Tubsat B


 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


 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
Launch site	Plesetsk
Mass at launch


 Program: Turksat

Turkish telecommunication program

Contact

General Directorate of PTT

Ruzgarli Sokak, Ankara 06101, Turkey

Tel: +90-312-366-1972

Fax: +90-312-311-7748


Program: Turksat

Turksat 1A

Turksat 1B


Turksat's specifications

Prime contractor	Aerospatiale
Platform	Spacebus 100 B
Mass at launch	1775 kg
Mass in orbit	1078 kg
Length	2.8 m
Width	2.2 m
Height	2.5 m
Solar array	22.4 m span
Stabilization	3 axis
DC power	2900 W
Design lifetime	10 years


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	Turkey: 51 dBW Central Europe: 48 dBW Central Asia: 45 dBW
Polarization	linear H/V


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	42°E
Launch vehicle	Ariane V66

Cost: $300 million

Technical data

Specifications

Ku-band

EIRP coverage (dBW)

Transponder frequency chart (GHz)

Horizontal Downlink	Transponder	Vertical Downlink	Bandwidth (MHz)	Coverage
	4	10.970	36	Europe/Turkey
10.980	12		36	Turkey
	5	11.012	36	Europe/Turkey
11.030	13		36	Turkey
	6	11.054	36	Turkey
11.080	14		36	Turkey
	7	11.096	36	Turkey
11.130	15		36	Turkey
	8	11.162	72	Europe/Turkey
11.180	16		36	Turkey
11.486	9		72	Turkey
	1	11.490	72	Europe
11.574	10		72	Turkey
	2	11.590	72	Turkey/Asia
11.662	11		72	Turkey
	3	11.678	36	Turkey/Asia


Turksat 1C

planned for launch in second half 1996


 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	109 kg
Length	2.4 m
Width	1.64 m
Height	6.4 m
Stabilization	3 axis
DC power	BOL: 4500 W EOL: 3000 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	65 dBW
Polarization	circular L
Frequencies	Uplink: 17.7-18.1 GHz Downlink: 11.7-12.5 GHz


Tvsat's EIRP


 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°E
Launch vehicle	Ariane V20
Mass at launch

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
Mass at launch

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

Location

Begin	End	Position
L: 8 Aug 1989	Feb 1995	19.2°W
Mar 1995	...	0.6°W
Technical data

Specifications

Ku-band

EIRP coverage (dBW)

Video

Video excursion	13.5 MHz/v


 UARS

Upper Atmospheric Research Satellite

General

Designation	21701 / 91063B
Launch date	12 Sep 1991
Country of origin	United States
Mission	Scientific
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

Technical data

Specifications

Prime contractor	GE Astro
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
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

Also called UHF Follow On, short: UFO

US Navy telecommunication program


Program: UHF

UHF 1

UHF 2

UHF 3

UHF 4


 UHF 1

Also called USA 089

General

Designation	22563 / 93015A
Launch date	25 Mar 1993 at 22:48 UT
Country of origin	United States
Mission	Military: telecommunications
Geostationary orbit	n/a
Launch vehicle	Atlas Centaur
Launch site	Cap Canaveral, pad 36
Mass at launch
End of life

Out of service	?
Cause	May be malfunctionning?
Technical data

Specifications

Prime contractor	Hugues
Platform	HS 601
Mass at launch
Mass in orbit
Length
Width
Height
Stabilization
DC power
Design lifetime


 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	71.2°E
Launch vehicle
Launch site	Cape Canaveral
Mass at launch
Technical data

Downlinks in UHF- and X-band


 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	14.4°W
Launch vehicle	Atlas 1
Launch site	Cape Canaveral
Mass at launch
Technical data

Downlinks in UHF- and X-band


 UHF 4

Also known as EHF 4 and USA 108

General

Designation	23467 / 95003A
Launch date	29 Jan 1995 at 01:25 UT
Country of origin	United States
Mission	Military: telecommunications
Geostationary orbit	178°W
Launch vehicle	Atlas 2A
Launch site	Cape Canaveral LC36
Mass at launch

Tested in 170.5°W

Technical data

Specifications

Prime contractor	Hugues
Platform	HS 601
Mass at launch	3000 kg (approx.)
Mass in orbit	1200 kg (approx.)
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
Design lifetime
Technical data

Downlinks in UHF-, X- and EHF-band


UHF 5

General

Designation
Launch date	planned on 28 Mar 1995
Country of origin	United States
Mission	Military:
Geostationary orbit
Launch vehicle	Atlas 2A
Launch site	Cape Canaveral
Mass at launch


UHF 6

General

Designation
Launch date	planned in Jul 1995
Country of origin	United States
Mission	Military:
Geostationary orbit
Launch vehicle	Atlas 2A
Launch site	Cape Canaveral
Mass at launch


UHF 7

General

Designation
Launch date	planned in Oct 1995
Country of origin	United States
Mission	Military:
Geostationary orbit
Launch vehicle	Atlas 2A
Launch site	Cape Canaveral
Mass at launch


 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
Launch site	Tanegashima
Mass at launch


 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
Launch site	Tanegashima
Mass at launch


 Unamsat 1

General

Designation	n/a
Launch date	28 mar 1995
Country of origin	Mexico
Mission	Telecommunications
Perigee/Apogee	n/a
Inclination	n/a
Period	n/a
Launch vehicle	Start 1 (refurbished SS-25 ballistic missile)
Launch site	Plesetsk
Mass at launch
End of life

Cause	Launcher failure (fifth stage 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


 Program: Uosat

University Of Surrey sATellite

Satellites built by Surrey's university in the UK


Program: Uosat

Uosat 1

Uosat 2

Uosat 3

Uosat 4

Uosat 5


 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	Delta
Launch site	Vandenberg

Cost: $38000

End of life

Decay	13 Oct 1989
Technical data

Specifications

Prime contractor	University of Surrey (UK)
Platform	UoSAT
Mass at launch	52 kg
Length	0.74 m
Width	0.42 m
Height	0.42 m
Stabilization	3 axis
DC power
Design lifetime	3 years

Equiped 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
Launch site	Vandenberg

Function: Bulletin store and forward experiment, synthetic voice experiment.

Technical data

Specifications

Prime contractor	University of Surrey (UK)
Platform	UoSAT
Mass at launch	60 kg
Length	0.58 m
Width	0.36 m
Height	0.36 m
Stabilization	3 axis
DC power
Design lifetime	3 years
Downlink	1200 bps AFSK/FM (1200 and 2400 Hz tones), synthetic voice and CW. 145.826 MHz, 435.025 MHz, 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

Technical data

Specifications

Prime contractor	University of Surrey (UK)
Platform	UoSAT
Mass at launch	46 kg
Length	0.6 m
Width	0.34 m
Height	0.34 m
Stabilization	3 axis
DC power
Design lifetime	3 years
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


 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
Technical data

Specifications

Prime contractor	University of Surrey (UK)
Platform	UoSAT
Mass at launch	48 kg
Length	0.6 m
Width	0.34 m
Height	0.34 m
Stabilization	3 axis
DC power
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.

Technical data

Specifications

Prime contractor	University of Surrey (UK)
Platform	UoSAT
Mass at launch	49 kg
Length	0.68 m
Width	0.34 m
Height	0.34 m
Stabilization	3 axis
DC power
Design lifetime	3 years
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


 Program: USA

Designation used by the United States since mid-1984 to name military spacecrafts.

USA 001	USA 002	USA 003
USA 004	USA 005	USA 006
USA 007	USA 008	USA 009
USA 010	USA 011	USA 012
USA 013	USA 014	USA 015
USA 016	USA 017	USA 018
USA 019	USA 020	USA 021
USA 022	USA 023	USA 024
USA 025	USA 026	USA 027
USA 028	USA 029	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
USA 049	USA 050	USA 051
USA 052	USA 053	USA 054
USA 055	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	USA 069
USA 070	USA 071	USA 072
USA 073	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 099

General

Designation	22988 / 94009A
Launch date	7 Feb 1994
Country of origin	United States
Mission	Military:
Geostationary orbit	n/a
Launch vehicle	Titan 4
Launch site	Cape Canaveral
Mass at launch

First of the six Milstar geostationary satellites. Buit by Lockheed and operated by USAF or Space Command?


 USA 101

Also called P90-5 TAOS

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
Launch site	Vandenberg
Mass at launch

Operated by USAF, built by TRW from an Eagle platform


 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
Launch site	Vandenberg
Mass at launch

Operated by DARPA, built by Ball


 USA 103

General

Designation	23097 / 94026A
Launch date	3 May 1994
Country of origin	United States
Mission	Military:
Perigee/Apogee	1323/39034 km
Inclination	64.4°
Period	717.9 min
Launch vehicle
Launch site
Mass at launch


 USA 105

General

Designation	23223 / 94054A
Launch date	27 Aug 1994
Country of origin	United States
Mission	Military: ?
Perigee/Apogee	n/a
Inclination	n/a
Period	n/a
Launch vehicle	Titan 4/Centaur
Launch site	Cape Canaveral
Mass at launch

Could be geostationary (advanced Orion)?


 USA 110

General

Designation	? / 95022A
Launch date	14 May 1995 at 13:45 UT
Country of origin	United States
Mission	Military: intelligence?
Geostationary orbit	n/a
Launch vehicle	Titan 4 Centaur
Launch site	Cape Canaveral pad 40
Mass at launch


 Program: Vanguard

American experimental program

Date	Satellite	Launch vehicle
6 Dec 1967	Echec	Test Vehicle 3
5 Feb 1958	Echec	Test Vehicle 3 backup
17 Mar 1958	Vanguard_1	Test Vehicle 4
28 Apr 1958	Echec	Test Vehicle 5
27 May 1958	Echec	Satellite Launch Vehicle 1
26 Jun 1958	Echec	Satellite Launch Vehicle 2
26 Sep 1958	Echec	Satellite Launch Vehicle 3
17 Feb 1959	Vanguard_2	Satellite Launch Vehicle 4
13 Apr 1959	Echec	Satellite Launch Vehicle 5
22 Jun 1959	Echec	Satellite Launch Vehicle 6
18 Sep 1959	Vanguard_3	Test Vehicle 4 backup


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	Test Vehicle 4
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	Satellite Launch Vehicle 4
Launch site	Cape Canaveral
Mass at launch


 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	Test Vehicle 4 backup
Launch site	Cape Canaveral
Mass at launch


 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

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


 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
Mass at launch

Designed at Weber State College

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: Westar

American telecommunication program operated by the Western Union Telegraph and since 1988 by Hugues.


Program: Westar

Westar 1

Westar 2

Westar 3

Westar 4

Westar 5

Westar 6


Westar 4, 5 & 6's specifications

Prime contractor	Hugues
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	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
Launch site	Cape Canaveral
End of life

Out of service	yes
Technical data

Specifications

Mass at launch	572 kg
Mass in orbit	208 kg
Design lifetime	7 years
Capacity	14400 phone circuits or 12 TV channels


 Westar 2

General

Designation	07466 / 74075A
Launch date	10 Oct 1974
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	125°W
Launch vehicle
Launch site	Cape Canaveral
Mass at launch
End of life

Out of service	yes


 Westar 3

General

Designation	11484 / 79072A
Launch date	10 Aug 1979
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	91°W
Launch vehicle
Launch site	Cape Canaveral
Mass at launch
End of life

Out of service	yes


 Westar 4

General

Designation	13069 / 82014A
Launch date	26 Feb 1982
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	99°W
Launch vehicle	Delta
Launch site	Cape Canaveral
End of life

Out of service	late 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	Delta
Launch site	Cape Canaveral
End of life

Out of service	yes
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 10

Placed on a bad orbit, it was retrieved on 16 Nov 1984 by STS 14. It then became Asiasat 1.

Technical data

Specifications

C-band


 Dial-Wika

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 B
Launch site	Kourou
Mass at launch

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 7925
Launch site	Cape Canaveral LC17B
Mass at launch	1200 kg

Cost: $173 million

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.

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.


 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

Wake Shield Facility

General

Designation
Launch date	not launched
Country of origin	United States
Mission	Scientific
Perigee/Apogee
Inclination
Period
Launch vehicle	STS 60
Launch site
Mass at launch

Should have tested new electrical chips

Technical data

Specifications

Mass at launch	1760 kg
Diameter	3.6 m
Design lifetime	a few hours


 Program: Yuri

Means "tiger lily"

Japanese telecommunication program operated by Telecommunication Satellite Corporation of Japan


Program: Yuri

Yuri 1

Yuri 2A

Yuri 2B

Yuri 2X

Yuri 3A

Yuri 3B

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
Length	1.2 m
Width	1.32 m
Height	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	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
Length	1.63 m
Width	1.32 m
Height	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
EIRP	54 dBW
Polarization


 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
Launch site	Cape Canaveral
Mass at launch
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
Launch site	Tanegashima
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
Launch site	Tanegashima
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
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
Launch site	Tanegashima
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
Launch site	Tanegashima
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
Technical data

Specifications

Ku-band


 Program: Cosmos

Soviet program


 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
Launch site	Kapustin Yar
Mass at launch
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
Launch site	Tyuratam
Mass at launch


 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
Launch site	Tyuratam
Mass at launch

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
Launch site	Tyuratam
Mass at launch

First soviet meteorology satellite

End of life

Decay	14 Nov 1989


 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
Launch site	Plesetsk
Mass at launch
End of life

Decay	14 Sep 1982


 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
Mass at launch
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
Mass at launch

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
Mass at launch

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
Mass at launch

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
Perigee/Apogee	1318/1507 km
Inclination	74°
Period	114.1 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 0445

General

Designation	05548 / 71086B
Launch date	13 Oct 1971
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1348/1509 km
Inclination	74°
Period	114.4 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 0446

General

Designation	05549 / 71086C
Launch date	13 Oct 1971
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1378/1509 km
Inclination	74°
Period	114.8 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 0447

General

Designation	05550 / 71086D
Launch date	13 Oct 1971
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1408/1512 km
Inclination	74°
Period	115.1 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 0448

General

Designation	05551 / 71086E
Launch date	13 Oct 1971
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1438/1514 km
Inclination	74°
Period	115.5 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 0449

General

Designation	05552 / 71086F
Launch date	13 Oct 1971
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1480/1540 km
Inclination	74°
Period	116.2 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 0450

General

Designation	05553 / 71086G
Launch date	13 Oct 1971
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1460/1527 km
Inclination	74°
Period	115.8 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 0451

General

Designation	05554 / 71086H
Launch date	13 Oct 1971
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1487/1571 km
Inclination	74°
Period	116.6 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 0500

General

Designation	06097 / 72053A
Launch date	10 Jul 1972
Country of origin	CIS
Mission
Perigee/Apogee	505/548 km
Inclination	74°
Period	95.2 min
Launch vehicle
Launch site	Plesetsk
Mass at launch
End of life

Decay	29 Mar 1980


 Cosmos 0504

General

Designation	06117 / 72057A
Launch date	20 Jul 1972
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1319/1493 km
Inclination	74°
Period	113.9 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 0505

General

Designation	06118 / 72057B
Launch date	20 Jul 1972
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1349/1494 km
Inclination	74°
Period	114.3 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 0506

General

Designation	06119 / 72057C
Launch date	20 Jul 1972
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1380/1494 km
Inclination	74°
Period	114.6 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 0507

General

Designation	06120 / 72057D
Launch date	20 Jul 1972
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1409/1494 km
Inclination	74°
Period	114.9 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 0508

General

Designation	06121 / 72057E
Launch date	20 Jul 1972
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1441/1493 km
Inclination	74°
Period	115.3 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 0509

General

Designation	06122 / 72057F
Launch date	20 Jul 1972
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1471/1496 km
Inclination	74°
Period	115.6 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 0510

General

Designation	06123 / 57057G
Launch date	20 Jul 1972
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1493/1507 km
Inclination	74°
Period	116 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 0511

General

Designation	06124 / 72057H
Launch date	20 Jul 1972
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1493/1543 km
Inclination	74°
Period	116.4 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 0588

General

Designation	06845 / 73069A
Launch date	2 Oct 1973
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1446/1490 km
Inclination	74°
Period	155.3 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 0589

General

Designation	06846 / 73069B
Launch date	2 Oct 1973
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1412/1486 km
Inclination	74°
Period	114.9 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 0590

General

Designation	06847 / 73069C
Launch date	2 Oct 1973
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1431/1485 km
Inclination	74°
Period	115.1 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 0591

General

Designation	06848 / 73069D
Launch date	2 Oct 1973
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1344/1483 km
Inclination	74°
Period	114.4 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 0592

General

Designation	06849 / 73069E
Launch date	2 Oct 1973
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1328/1482 km
Inclination	74°
Period	133.9 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 0593

General

Designation	06850 / 73069F
Launch date	2 Oct 1973
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1361/1483 km
Inclination	74°
Period	114.3 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 0594

General

Designation	06851 / 73069G
Launch date	2 Oct 1973
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1378/1484 km
Inclination	74°
Period	114.5 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 0595

General

Designation	06852 / 73069H
Launch date	2 Oct 1973
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1396/1483 km
Inclination	74°
Period	114.7 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 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
Mass at launch
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
Mass at launch
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
Mass at launch
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
Mass at launch
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
Mass at launch
End of life

Decay	23 Oct 1973


 Cosmos 0605

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
Launch site	Plesetsk
Mass at launch

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
Launch site	Tyuratam
Mass at launch

First Soviet geostationary satellite


 Cosmos 0641

General

Designation	07265 / 74024A
Launch date	23 Apr 1974
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1385/1479 km
Inclination	74°
Period	114.5 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 0642

General

Designation	07266 / 74024B
Launch date	23 Apr 1974
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1316/1478 km
Inclination	74°
Period	113.7 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 0643

General

Designation	07267 / 74024C
Launch date	23 Apr 1974
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1350/1479 km
Inclination	74°
Period	114.4 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 0644

General

Designation	07268 / 74024D
Launch date	23 Apr 1974
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1332/1479 km
Inclination	74°
Period	113.9 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 0645

General

Designation	07269 / 74024E
Launch date	23 Apr 1974
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1367/1479 km
Inclination	74°
Period	114.3 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 0646

General

Designation	07270 / 74024F
Launch date	23 Apr 1974
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1402/1482 km
Inclination	74°
Period	114.7 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 0647

General

Designation	07271 / 74024G
Launch date	23 Apr 1974
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1420/1481 km
Inclination	74°
Period	114.9 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 0648

General

Designation	07272 / 74024H
Launch date	23 Apr 1974
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1435/1487 km
Inclination	74°
Period	115.1 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 0677

General

Designation	07435 / 74072A
Launch date	19 Sep 1974
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1394/1464 km
Inclination	74°
Period	114.4 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 0678

General

Designation	07436 / 74072B
Launch date	19 Sep 1974
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1464/1530 km
Inclination	74°
Period	115.9 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 0679

General

Designation	07437 / 74072C
Launch date	19 Sep 1974
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1464/1508 km
Inclination	74°
Period	115.7 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 0680

General

Designation	07438 / 74072D
Launch date	19 Sep 1974
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1464/1489 km
Inclination	74°
Period	115.5 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 0681

General

Designation	07439 / 74072E
Launch date	19 Sep 1974
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1463/1470 km
Inclination	74°
Period	115.3 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 0682

General

Designation	07440 / 74072F
Launch date	19 Sep 1974
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1450/1464 km
Inclination	74°
Period	115 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 0683

General

Designation	07441 / 74072G
Launch date	19 Sep 1974
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1432/1464 km
Inclination	74°
Period	114.8 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 0684

General

Designation	07442 / 74072H
Launch date	19 Sep 1974
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1413/1464 km
Inclination	74°
Period	114.6 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 0711

General

Designation	07678 / 75016A
Launch date	28 Feb 1975
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1459/1490 km
Inclination	74°
Period	115.4 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 0712

General

Designation	07679 / 75016B
Launch date	28 Feb 1975
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1409/1488 km
Inclination	74°
Period	114.8 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 0713

General

Designation	07680 / 75016C
Launch date	28 Feb 1975
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1393/1485 km
Inclination	74°
Period	114.6 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 0714

General

Designation	07681 / 75016D
Launch date	28 Feb 1975
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1442/1489 km
Inclination	74°
Period	115.2 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 0715

General

Designation	07682 / 75016E
Launch date	28 Feb 1975
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1467/1502 km
Inclination	74°
Period	115.7 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 0716

General

Designation	07683 / 75016F
Launch date	28 Feb 1975
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1477/1512 km
Inclination	74°
Period	115.9 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 0717

General

Designation	07684 / 75016G
Launch date	28 Feb 1975
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1477/1533 km
Inclination	74°
Period	116.1 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 0718

General

Designation	07685 / 75016H
Launch date	28 Feb 1975
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1427/1487 km
Inclination	74°
Period	115 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 0732

General

Designation	07820 / 75045A
Launch date	28 May 1975
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1401/1468 km
Inclination	74°
Period	114.6 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 0733

General

Designation	07822 / 75045B
Launch date	28 May 1975
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1467/1552 km
Inclination	74°
Period	116.2 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 0734

General

Designation	07823 / 75045C
Launch date	28 May 1975
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1441/1469 km
Inclination	74°
Period	115 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 0735

General

Designation	07824 / 75045D
Launch date	28 May 1975
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1459/1472 km
Inclination	74°
Period	115.2 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 0736

General

Designation	07825 / 75045E
Launch date	28 May 1975
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1467/1484 km
Inclination	74°
Period	115.5 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 0737

General

Designation	07826 / 75045F
Launch date	28 May 1975
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1468/1484 km
Inclination	74°
Period	115.9 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 0738

General

Designation	07827 / 75045G
Launch date	28 May 1975
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1467/1506 km
Inclination	74°
Period	115.7 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 0739

General

Designation	07828 / 75045H
Launch date	28 May 1975
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1421/1506 km
Inclination	74°
Period	115.7 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 0775

General

Designation	08357 / 75097A
Launch date	8 Oct 1975
Country of origin	CIS
Mission	Military: Telecommunications
Geostationary orbit
Launch vehicle
Launch site	Tyuratam
Mass at launch


 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
Mass at launch
End of life

Decay	3 Jun 1976


 Cosmos 0782

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
Launch site	Plesetsk
Mass at launch

Study of animals and vegetals in space

End of life

Decay	15 Dec 1975


 Cosmos 0936

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
Launch site	Plesetsk
Mass at launch

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
Perigee/Apogee	251/265 km
Inclination	65°
Period	89.7 min
Launch vehicle
Launch site	Tyuratam
Mass at launch
End of life

Decay	24 Jan 1978

Decayed in Canada. It was equiped of a 508 kg Romachka nuclear reactor for power supply with 49 kg of uranium. The CIS payed $2.55 million


 Cosmos 1000

General

Designation	10776 / 78034A
Launch date	31 Mar 1978
Country of origin	CIS
Mission	Navigation
Perigee/Apogee	954/1006 km
Inclination	82.9°
Period	104.7 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 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
Mass at launch
End of life

Decay	7 Nov 1979


 Cosmos 1267

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
Launch site	Tyuratam
Mass at launch

First spacecraft to dock with Saliout 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
Geostationary orbit	80°E
Launch vehicle
Launch site	Tyuratam
Mass at launch


 Cosmos 1402

General

Designation	13441 / 82084A
Launch date	30 Aug 1982
Country of origin	CIS
Mission
Perigee/Apogee	250/266 km
Inclination	656°
Period	89.6 min
Launch vehicle
Launch site	Tyuratam
Mass at launch

Equiped with a nuclear reactor (50 kg of uranium), it decayed in 3 parts on 30 Dec 1982, 23 Jan 1983 (Indian ocean) and on 7 Feb 1983 (Atlantic)

End of life

Decay	23 Jan 1983


 Cosmos 1443

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
Launch site	Tyuratam
Mass at launch

First spacecraft to dock with Saliout 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
Geostationary orbit	141°E
Launch vehicle
Launch site	Tyuratam
Mass at launch


 Cosmos 1546

General

Designation	14867 / 84031A
Launch date	29 Mar 1984
Country of origin	CIS
Mission	Military: Telecommunications
Geostationary orbit	24°W
Launch vehicle
Launch site	Tyuratam
Mass at launch


 Cosmos 1629

General

Designation	15574 / 85016A
Launch date	21 Feb 1985
Country of origin	CIS
Mission	Military: Telecommunications
Geostationary orbit	24°W
Launch vehicle
Launch site	Tyuratam
Mass at launch


 Cosmos 1700

General

Designation	16199 / 85102A
Launch date	25 Oct 1985
Country of origin	CIS
Mission	Military: Telecommunications (Al'tair)
Geostationary orbit	95°E
Launch vehicle
Launch site	Tyuratam
Mass at launch

Part of the SDRN network

End of life

Out of service	Feb 1995
Cause	replaced by Luch
Technical data

Specifications

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


 Cosmos 1738

General

Designation	16667 / 86027A
Launch date	4 Apr 1986
Country of origin	CIS
Mission	Military: Telecommunications (Geizer)
Geostationary orbit	14°W
Launch vehicle
Launch site	Tyuratam
Mass at launch
Technical data

Specifications

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


 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
Launch site	Plesetsk
Mass at launch


 Cosmos 1850

General

Designation	18095 / 87049A
Launch date	9 Jun 1987
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	775/798 km
Inclination	74°
Period	100.6 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 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
Launch site	Plesetsk
Mass at launch


 Cosmos 1852

General

Designation	18113 / 87051A
Launch date	16 Jun 1987
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1471/1497 km
Inclination	74°
Period	115.6 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 1853

General

Designation	18114 / 87051B
Launch date	16 Jun 1987
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1470/1480 km
Inclination	74°
Period	115.4 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 1854

General

Designation	18115 / 87051C
Launch date	16 Jun 1987
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1456/1478 km
Inclination	74°
Period	115.3 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 1855

General

Designation	18116 / 87051D
Launch date	16 Jun 1987
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1444/1475 km
Inclination	74°
Period	115.1 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 1856

General

Designation	18117 / 87051E
Launch date	16 Jun 1987
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1429/1475 km
Inclination	74°
Period	114.9 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 1857

General

Designation	18118 / 87051F
Launch date	16 Jun 1987
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1414/1475 km
Inclination	74°
Period	114.8 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 1858

General

Designation	18119 / 87051G
Launch date	16 Jun 1987
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1399/1476 km
Inclination	74°
Period	114.6 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 1859

General

Designation	18120 / 87051H
Launch date	16 Jun 1987
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1385/1474 km
Inclination	74°
Period	114.4 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 1860

General

Designation	18122 / 87052A
Launch date	18 Jun 1987
Country of origin	CIS
Mission
Perigee/Apogee	900/992 km
Inclination	65°
Period	104 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 1861

General

Designation	18129 / 87054A
Launch date	23 Jun 1987
Country of origin	CIS
Mission	Navigation
Perigee/Apogee	996/996 km
Inclination	82.9°
Period	104.9 min
Launch vehicle
Launch site	Plesetsk
Mass at launch
Technical data

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
Perigee/Apogee	263/278 km
Inclination	71.9°
Period	89.9 min
Launch vehicle
Launch site	Plesetsk
Mass at launch	15 to 20 t

Satellite developped with the United States, France, Finland and Sweden

End of life

Decay	29 Jul 1989


 Cosmos 1887

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
Launch site	Plesetsk
Mass at launch

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
Launch site	Tyuratam
Mass at launch
Location

Begin	End	Position
L: 1 Oct 1987		80°E
Feb 1995	...	15°W
Technical data

Specifications

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


 Cosmos 1894

General

Designation	18443 / 87091A
Launch date	28 Oct 1987
Country of origin	CIS
Mission	Military: telecommunications
Geostationary orbit	24°W
Launch vehicle
Launch site	Tyuratam
Mass at launch
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 (Al'tair)
Geostationary orbit	see below
Launch vehicle
Launch site	Tyuratam
Mass at launch

Part of the SDRN network

Location

Begin	End	Position
L: 26 Nov 1987		95°E
Feb 1995		70°E drifting East
Mar 1995		65°E drifting East
Technical data

Specifications

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


 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
Launch site	Plesetsk
Mass at launch
End of life

Decay	22 Mar 1988


 Cosmos 1924

General

Designation	18937 / 88016A
Launch date	11 Mar 1988
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1458/1512 km
Inclination	74°
Period	115.7 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 1925

General

Designation	18938 / 88016B
Launch date	11 Mar 1988
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1457/1495 km
Inclination	74°
Period	115.5 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 1926

General

Designation	18939 / 88016C
Launch date	11 Mar 1988
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1458/1477 km
Inclination	74°
Period	115.3 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 1927

General

Designation	18940 / 88016D
Launch date	11 Mar 1988
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1452/1465 km
Inclination	74°
Period	115.1 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 1928

General

Designation	18941 / 88016E
Launch date	11 Mar 1988
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1442/1459 km
Inclination	74°
Period	114.9 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 1929

General

Designation	18942 / 88016F
Launch date	11 Mar 1988
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1426/1459 km
Inclination	74°
Period	114.7 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 1930

General

Designation	18943 / 88016G
Launch date	11 Mar 1988
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1412/1458 km
Inclination	74°
Period	114.6 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 1931

General

Designation	18944 / 88016H
Launch date	11 Mar 1988
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1395/1459 km
Inclination	74°
Period	114.4 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 1932

General

Designation	18957 / 88019A
Launch date	14 Mar 1988
Country of origin	CIS
Mission	Military: ocean observation
Perigee/Apogee	921/1007 km
Inclination	65°
Period	104.4 min
Launch vehicle
Launch site	Tyuratam
Mass at launch

Equiped with a nuclear reactor


 Cosmos 1933

General

Designation	18958 / 88020A
Launch date	15 Mar 1988
Country of origin	CIS
Mission	Military: remote sensing (Priroda)
Perigee/Apogee	604/630 km
Inclination	82.5°
Period	97 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 1934

General

Designation	18985 / 88023A
Launch date	22 Mar 1988
Country of origin	CIS
Mission	Navigation
Perigee/Apogee	946/1005 km
Inclination	83°
Period	104.6 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 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
Launch site	Plesetsk
Mass at launch
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	Soyouz
Launch site	Plesetsk
Mass at launch
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
Launch site	Plesetsk
Mass at launch
End of life

Decay	21 Mar 1969


 Cosmos 1959

General

Designation	19324 / 88062A
Launch date	18 Jul 1988
Country of origin	CIS
Mission	Navigation
Perigee/Apogee	952/1002 km
Inclination	83°
Period	104.6 min
Launch vehicle	Cosmos
Launch site	Plesetsk
Mass at launch


 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
Launch site	Plesetsk
Mass at launch
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
Launch site	Tyuratam
Mass at launch
Location

Begin	End	Position
L: 1 Aug 1988		14°W
Feb 1995		77°E
Mar 1995		78°E
Technical data

Specifications

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


 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	SL 16
Launch site	Tyuratam
Mass at launch
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	Soyouz
Launch site	Plesetsk
Mass at launch
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	Soyouz
Launch site	Tyuratam
Mass at launch
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	Soyouz
Launch site	Plesetsk
Mass at launch
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
Launch site	Plesetsk
Mass at launch


 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	Soyouz
Launch site	Plesetsk
Mass at launch
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	Soyouz
Launch site	Plesetsk
Mass at launch
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	Soyouz
Launch site	Plesetsk
Mass at launch
End of life

Decay	13 Nov 1988


 Cosmos 1970

General

Designation	19501 / 88085A
Launch date	16 Sep 1988
Country of origin	CIS
Mission	Navigation
Perigee/Apogee	19099/19159 km
Inclination	65.7°
Period	675.7 min
Launch vehicle	Proton
Launch site	Tyuratam
Mass at launch


 Cosmos 1971

General

Designation	19502 / 88085B
Launch date	16 Sep 1988
Country of origin	CIS
Mission	Navigation
Perigee/Apogee	19099/19159 km
Inclination	65.7°
Period	675.7 km
Launch vehicle	Proton
Launch site	Tyuratam
Mass at launch


 Cosmos 1972

General

Designation	19503 / 88085C
Launch date	16 Sep 1988
Country of origin	CIS
Mission	Navigation
Perigee/Apogee	19113/19145 km
Inclination	65.7°
Period	675.7 min
Launch vehicle	Proton
Launch site	Tyuratam
Mass at launch


 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	Soyouz
Launch site	Plesetsk
Mass at launch
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	Plesetsk
Launch site	Molnya
Mass at launch


 Cosmos 1975

General

Designation	19573 / 88093A
Launch date	11 Oct 1988
Country of origin	CIS
Mission	Military: remote sensing
Perigee/Apogee	3188/36556 km
Inclination	82.5°
Period	97.1 min
Launch vehicle	Cyclone
Launch site	Plesetsk
Mass at launch


 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	Soyouz
Launch site	Plesetsk
Mass at launch
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	Molnya
Launch site	Plesetsk
Mass at launch


 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	Soyouz
Launch site	Plesetsk
Mass at launch
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
Mass at launch
End of life

Decay	25 Dec 1989


 Cosmos 1980

General

Designation	19649 / 88102A
Launch date	23 Nov 1988
Country of origin	CIS
Mission	Military: electronic listening (Elint)
Perigee/Apogee	840/850 km
Inclination	71°
Period	101.8 min
Launch vehicle
Launch site	Tyuratam
Mass at launch


 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	Soyouz
Launch site	Plesetsk
Mass at launch
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	Soyouz
Launch site	Plesetsk
Mass at launch
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	Soyouz
Launch site	Plesetsk
Mass at launch
End of life

Decay	13 Feb 1989


 Cosmos 1985

General

Designation	19720 / 88113A
Launch date	23 Dec 1988
Country of origin	CIS
Mission	Military: electronic listening
Perigee/Apogee	206/220 km
Inclination	73.5°
Period	88.8 min
Launch vehicle	Cyclone
Launch site	Plesetsk
Mass at launch
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	Soyouz
Launch site	Tyuratam
Mass at launch
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
Perigee/Apogee	19113/19145 km
Inclination	64.9°
Period	675.7 min
Launch vehicle	Proton
Launch site	Tyuratam
Mass at launch
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
Perigee/Apogee	19111/19147 km
Inclination	65°
Period	675.7 min
Launch vehicle	Proton
Launch site	Tyuratam
Mass at launch
End of life

Out of service	yes


 Cosmos 1989

General

Designation	19751 / 89001C
Launch date	10 Jan 1989
Country of origin	CIS
Mission	Navigation
Perigee/Apogee	19097/19152 km
Inclination	64.9°
Period	675.5 min
Launch vehicle	Proton
Launch site	Tyuratam
Mass at launch


 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	Soyouz
Launch site	Plesetsk
Mass at launch
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	Soyouz
Launch site	Tyuratam
Mass at launch
End of life

Decay	1 Feb 1989


 Cosmos 1992

General

Designation	19769 / 89005A
Launch date	26 Jan 1989
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	764/798 km
Inclination	74°
Period	100.5 min
Launch vehicle	Soyouz
Launch site	Plesetsk
Mass at launch


 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	Soyouz
Launch site	Tyuratam
Mass at launch
End of life

Decay	27 Mar 1989


 Cosmos 1994

General

Designation	19785 / 89009A
Launch date	10 Feb 1989
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1391/1414 km
Inclination	82.6°
Period	113.9 min
Launch vehicle	Tsyclon
Launch site	Plesetsk
Mass at launch


 Cosmos 1995

General

Designation	19786 / 89009B
Launch date	10 Feb 1989
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1409/1415 km
Inclination	82.6°
Period	114.1 min
Launch vehicle	Tsyclon
Launch site	Plesetsk
Mass at launch


 Cosmos 1996

General

Designation	19787 / 89009C
Launch date	10 Feb 1989
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1403/1414 km
Inclination	82.6°
Period	114 min
Launch vehicle	Tsyclon
Launch site	Plesetsk
Mass at launch


 Cosmos 1997

General

Designation	19788 / 89009D
Launch date	10 Feb 1989
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1397/1414 km
Inclination	82.6°
Period	113.9 min
Launch vehicle	Tsyclon
Launch site	Plesetsk
Mass at launch


 Cosmos 1998

General

Designation	19789 / 89009E
Launch date	10 Feb 1989
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1387/1414 km
Inclination	82.6°
Period	113.8 min
Launch vehicle	Tsyclon
Launch site	Plesetsk
Mass at launch


 Cosmos 1999

General

Designation	19790 / 89009F
Launch date	10 Feb 1989
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1381/1414 km
Inclination	82.6°
Period	113.7 min
Launch vehicle	Tsyclon
Launch site	Plesetsk
Mass at launch


 Cosmos 2000

General

Designation	19792 / 89010A
Launch date	10 Feb 1989
Country of origin	CIS
Mission	Military: telecommunications
Perigee/Apogee	175/243 km
Inclination	82.3°
Period	88.7 min
Launch vehicle	Tsyclon
Launch site	Plesetsk
Mass at launch
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	Molnya
Launch site	Plesetsk
Mass at launch


 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
Launch site	Plesetsk
Mass at launch
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	Soyouz
Launch site	Plesetsk
Mass at launch
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
Launch site	Plesetsk
Mass at launch
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	Soyouz
Launch site	Plesetsk
Mass at launch
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	Soyouz
Launch site	Plesetsk
Mass at launch
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
Perigee/Apogee	224/262 km
Inclination	64.7°
Period	89.4 min
Launch vehicle	Soyouz
Launch site	Plesetsk
Mass at launch
End of life

Decay	22 Sep 1989


 Cosmos 2008

General

Designation	19902 / 89025A
Launch date	24 Mar 1989
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1391/1469 km
Inclination	74°
Period	114.4 min
Launch vehicle	Soyouz
Launch site	Plesetsk
Mass at launch


 Cosmos 2009

General

Designation	19903 / 89025B
Launch date	24 Mar 1989
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1406/1470 km
Inclination	74°
Period	114.6 min
Launch vehicle	Soyouz
Launch site	Plesetsk
Mass at launch


 Cosmos 2010

General

Designation	19904 / 89025C
Launch date	24 Mar 1989
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1421/1470 km
Inclination	74°
Period	114.8 min
Launch vehicle	Soyouz
Launch site	Plesetsk
Mass at launch


 Cosmos 2011

General

Designation	19905 / 89025D
Launch date	24 Mar 1989
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1437/1470 km
Inclination	74°
Period	115 min
Launch vehicle	Soyouz
Launch site	Plesetsk
Mass at launch


 Cosmos 2012

General

Designation	19906 / 89025E
Launch date	24 Mar 1989
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1453/1470 km
Inclination	74°
Period	115.1 min
Launch vehicle	Soyouz
Launch site	Plesetsk
Mass at launch


 Cosmos 2013

General

Designation	19907 / 89025F
Launch date	24 Mar 1989
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1462/1478 km
Inclination	74°
Period	115.3 min
Launch vehicle	Soyouz
Launch site	Plesetsk
Mass at launch


 Cosmos 2014

General

Designation	19908 / 89025G
Launch date	24 Mar 1989
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1469/1487 km
Inclination	74°
Period	115.5 min
Launch vehicle	Soyouz
Launch site	Plestesk
Mass at launch


 Cosmos 2015

General

Designation	19909 / 89025H
Launch date	24 Mar 1989
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1467/1507 km
Inclination	74°
Period	115.7 min
Launch vehicle	Soyouz
Launch site	Plesetsk
Mass at launch


 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
Launch site	Plesetsk
Mass at launch


 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	Soyouz
Launch site	Plesetsk
Mass at launch
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
Mass at launch
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	Soyouz
Launch site	Plesetsk
Mass at launch
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	Soyouz
Launch site	Plesetsk
Mass at launch
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	Soyouz
Launch site	Plesetsk
Mass at launch
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
Perigee/Apogee	19119/19139 km
Inclination	65.5°
Period	675.7 min
Launch vehicle	Proton
Launch site	Tyuratam
Mass at launch
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
Perigee/Apogee	19087/19170 km
Inclination	65.5°
Period	675.7 min
Launch vehicle	Proton
Launch site	Tyuratam
Mass at launch
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
Perigee/Apogee	19095/19146 km
Inclination	65.5°
Period	675.4 min
Launch vehicle	Proton
Launch site	Tyuratam
Mass at launch


 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	Soyouz
Launch site	Plesetsk
Mass at launch
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
Launch site	Plesetsk
Mass at launch
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
Launch site	Plesetsk
Mass at launch
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	Soyouz
Launch site	Plesetsk
Mass at launch
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	Soyouz
Launch site	Plesetsk
Mass at launch
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
Launch site	Plesetsk
Mass at launch
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	Soyouz
Launch site	Tyuratam
Mass at launch
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	Soyouz
Launch site	Plesetsk
Mass at launch
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	Zenith (derived from SL 16)
Launch site	Tyuratam
Mass at launch
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
Launch site	Plesetsk
Mass at launch


 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	Soyouz
Launch site	Plesetsk
Mass at launch
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	Soyouz
Launch site	Plesetsk
Mass at launch
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
Perigee/Apogee	1482/1522 km
Inclination	73.6°
Period	116 min
Launch vehicle	Tsyclon
Launch site	Plesetsk
Mass at launch


 Cosmos 2038

General

Designation	20232 / 89074A
Launch date	14 Sep 1989
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1389/1408 km
Inclination	82.6°
Period	113.8 min
Launch vehicle	Tsyclon
Launch site	Plesetsk
Mass at launch


 Cosmos 2039

General

Designation	20233 / 89074B
Launch date	14 Sep 1989
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1382/1408 km
Inclination	82.6°
Period	113.7 min
Launch vehicle	Tsyclon
Launch site	Plesetsk
Mass at launch


 Cosmos 2040

General

Designation	20234 / 89074C
Launch date	14 Sep 1989
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1407/1413 km
Inclination	82.6°
Period	114 min
Launch vehicle	Tsyclon
Launch site	Plesetsk
Mass at launch


 Cosmos 2041

General

Designation	20235 / 89074D
Launch date	14 Sep 1989
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1394/1408 km
Inclination	82.6°
Period	113.8 min
Launch vehicle	Tsyclon
Launch site	Plesetsk
Mass at launch


 Cosmos 2042

General

Designation	20236 / 89074E
Launch date	14 Sep 1989
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1398/1409 km
Inclination	82.6°
Period	113.9 min
Launch vehicle	Tsyclon
Launch site	Plesetsk
Mass at launch


 Cosmos 2043

General

Designation	20237 / 89074F
Launch date	14 Sep 1989
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1406/1407 km
Inclination	82.6°
Period	113.9 min
Launch vehicle	Tsyclon
Launch site	Plesetsk
Mass at launch


 Cosmos 2044

Also called BioCosmos 9 or Bion 9

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	Soyouz
Launch site	Plesetsk
Mass at launch

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	Zenith
Launch site	Tyuratam
Mass at launch
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	Zenith
Launch site	Plesetsk
Mass at launch
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	Soyouz
Launch site	Plesetsk
Mass at launch
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
Perigee/Apogee	232/251 km
Inclination	64.8°
Period	89.3 min
Launch vehicle	Soyouz
Launch site	Tyuratam
Mass at launch
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	Molnya
Launch site	Plesetsk
Mass at launch


 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
Mass at launch
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
Launch site	Plesetsk
Mass at launch
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 (Al'tair)
Geostationary orbit	16°W
Launch vehicle
Launch site	Tyuratam
Mass at launch

Part of SDRN network: relays communications with LEO satellites (e.g. Mir)

Technical data

Specifications

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

Transponders: 1 downlink between 10.810 & 10.835 GHz and another between 11 & 11.5 GHz + C-band capacity


 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	Soyouz
Launch site	Plesetsk
Mass at launch
End of life

Decay	29 Jan 1990


 Cosmos 2056

General

Designation	20432 / 90004A
Launch date	18 Jan 1990
Country of origin	CIS
Mission	Military: navigation
Perigee/Apogee	769/802 km
Inclination	74°
Period	100.6 min
Launch vehicle	Cosmos
Launch site	Plesetsk
Mass at launch


 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
Launch site	Plesetsk
Mass at launch
End of life

Decay	19 Mar 1990


 Cosmos 2058

General

Designation	20465 / 90010A
Launch date	30 Jan 1989
Country of origin	CIS
Mission	Earth observation
Perigee/Apogee	616/645 km
Inclination	82.5°
Period	97.3 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 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
Launch site	Plesetsk
Mass at launch
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
Launch site	Plesetsk
Mass at launch


 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	Soyouz
Launch site	Plesetsk
Mass at launch
End of life

Decay	5 Apr 1990


 Cosmos 2063

General

Designation	20536 / 90026A
Launch date	27 Mar 1990
Country of origin	CIS
Mission	Military: warning
Perigee/Apogee	1706/38633 km
Inclination	63.8°
Period	717.5 min
Launch vehicle	Molnya
Launch site	Plesetsk
Mass at launch


 Cosmos 2064

General

Designation	20549 / 90029A
Launch date	6 Apr 1990
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1460/1488 km
Inclination	74°
Period	115.4 min
Launch vehicle	Cosmos
Launch site	Plesetsk
Mass at launch


 Cosmos 2065

General

Designation	20550 / 90029B
Launch date	6 Apr 1990
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1459/1473 km
Inclination	74°
Period	115.2 min
Launch vehicle	Cosmos
Launch site	Plesetsk
Mass at launch


 Cosmos 2066

General

Designation	20551 / 90029C
Launch date	6 Apr 1990
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1383/1461 km
Inclination	74°
Period	114.3 min
Launch vehicle	Cosmos
Launch site	Plesetsk
Mass at launch


 Cosmos 2067

General

Designation	20552 / 90029D
Launch date	6 Apr 1990
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1398/1461 km
Inclination	74°
Period	114.4 min
Launch vehicle	Cosmos
Launch site	Plesetsk
Mass at launch


 Cosmos 2068

General

Designation	20553 / 90029E
Launch date	6 Apr 1990
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1413/1460 km
Inclination	74°
Period	114.6 min
Launch vehicle	Cosmos
Launch site	Plesetsk
Mass at launch


 Cosmos 2069

General

Designation	20554 / 90029F
Launch date	6 Apr 1990
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1427/1461 km
Inclination	74°
Period	114.8 min
Launch vehicle	Cosmos
Launch site	Plesetsk
Mass at launch


 Cosmos 2070

General

Designation	20555 / 90029G
Launch date	6 Apr 1990
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1441/1461 km
Inclination	74°
Period	114.9 min
Launch vehicle	Cosmos
Launch site	Plesetsk
Mass at launch


 Cosmos 2071

General

Designation	20556 / 90029H
Launch date	6 Apr 1990
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1457/1461 km
Inclination	74°
Period	115.1 min
Launch vehicle	Cosmos
Launch site	Plesetsk
Mass at launch


 Cosmos 2072

General

Designation	20568 / 90033A
Launch date	13 Apr 1990
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	232/270 km
Inclination	64.7°
Period	89.5 min
Launch vehicle	Soyouz
Launch site	Plesetsk
Mass at launch
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	Soyouz
Launch site	Plesetsk
Mass at launch
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	Soyouz
Launch site	Tyuratam
Mass at launch
Technical data

Downlink frequency: 149.910 MHz


 Cosmos 2079

Also called Glonass 44

General

Designation	20619 / 90045A
Launch date	19 May 1990
Country of origin	CIS
Mission	Navigation
Perigee/Apogee	19069/19189 km
Inclination	65.3°
Period	675.7 min
Launch vehicle
Launch site
Mass at launch
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
Perigee/Apogee	19107/19151 km
Inclination	65.3°
Period	675.7 min
Launch vehicle
Launch site
Mass at launch
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
Perigee/Apogee	19107/19151 km
Inclination	65.3°
Period	675.7 min
Launch vehicle
Launch site
Mass at launch
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	see below
Launch vehicle
Launch site	Tyuratam
Mass at launch
Location

Begin	End	Position
L: 18 Jul 1990
Feb 1995		78°E
Mar 1995		77°E
Technical data

Specifications

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


 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
Launch site	Plesetsk
Mass at launch
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 observation
Perigee/Apogee	402/416 km
Inclination	65°
Period	92.8 min
Launch vehicle
Launch site	Plesetsk
Mass at launch
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	Soyouz
Launch site	Plesetsk
Mass at launch
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
Perigee/Apogee	18975/19283 km
Inclination	64.9°
Period	675.7 min
Launch vehicle	Proton
Launch site	Tyuratam
Mass at launch
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
Perigee/Apogee	19036/19223 km
Inclination	64.9°
Period	675.7 min
Launch vehicle	Proton
Launch site	Tyuratam
Mass at launch
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
Perigee/Apogee	19110/19148 km
Inclination	64.96°
Period	675.7 min
Launch vehicle	Proton
Launch site	Tyuratam
Mass at launch
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
Perigee/Apogee	765/807 km
Inclination	74°
Period	100.6 min
Launch vehicle
Launch site	Plesetsk
Mass at launch


 Cosmos 2123

General

Designation	21089 / 91007A
Launch date	5 Feb 1991
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	961/1003 km
Inclination	82.9°
Period	104.7 min
Launch vehicle
Launch site	Plesetsk
Mass at launch
Technical data

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)
Geostationary orbit	80°E
Launch vehicle
Launch site	Tyuratam
Mass at launch
Technical data

Specifications

Prime contractor	NPO Lavochkin
Platform
Mass at launch
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
Perigee/Apogee	19103/19155 km
Inclination	65.1°
Period	675.7 min
Launch vehicle
Launch site
Mass at launch
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
Perigee/Apogee	19102/19156 km
Inclination	65.1°
Period	675.7 min
Launch vehicle
Launch site
Mass at launch
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
Perigee/Apogee	19109/19149 km
Inclination	65.1°
Period	675.7 min
Launch vehicle
Launch site
Mass at launch
End of life

Out of service	yes


 Cosmos 2142

General

Designation	21230 / 91029A
Launch date	16 Apr 1991
Country of origin	CIS
Mission
Perigee/Apogee	958/1017 km
Inclination	83°
Period	104.9 min
Launch vehicle
Launch site	Plesetsk
Mass at launch
Technical data

Downlink frequency: 150.030 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
Mass at launch


 Cosmos 2172

General

Designation	21789 / 91079A
Launch date	22 Nov 1991
Country of origin	CIS
Mission	Military: telecommunications (Geizer)
Geostationary orbit	14°W
Launch vehicle
Launch site	Tyuratam
Mass at launch
Technical data

Specifications

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


 Cosmos 2177

Also called Glonass 53

General

Designation	21853 / 92005A
Launch date	29 Jan 1992
Country of origin	CIS
Mission	Navigation
Perigee/Apogee	19112/19146 km
Inclination	64.8°
Period	675.7 min
Launch vehicle
Launch site
Mass at launch
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
Perigee/Apogee	19088/19170 km
Inclination	64.9°
Period	675.7 min
Launch vehicle
Launch site
Mass at launch
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
Perigee/Apogee	19109/19149 km
Inclination	64.9°
Period	675.7 min
Launch vehicle
Launch site
Mass at launch
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 756

General

Designation	22056 / 92047A
Launch date	30 Jul 1992
Country of origin	CIS
Mission	Navigation
Perigee/Apogee	19114/19144 km
Inclination	64.9°
Period	675.7 min
Launch vehicle
Launch site
Mass at launch
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel	24
Plane	3
Slot	21


 Cosmos 2205

Also called Glonass 57

General

Designation	22057 / 92047B
Launch date	30 Jul 1992
Country of origin	CIS
Mission	Navigation
Perigee/Apogee	19110/19148 km
Inclination	64.9°
Period	675.7 min
Launch vehicle
Launch site
Mass at launch
End of life

Out of service	yes


 Cosmos 2206

Also called Glonass 58 or Glonass 774

General

Designation	22058 / 92047C
Launch date	30 Jul 1992
Country of origin	CIS
Mission	Navigation
Perigee/Apogee	19098/19160 km
Inclination	64.9°
Period	675.7 min
Launch vehicle
Launch site
Mass at launch
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel	1
Plane	3
Slot	24


 Cosmos 2209

General

Designation	22112 / 92059A
Launch date	10 Sep 1992
Country of origin	CIS
Mission	Military: early warning (early Prognoz)
Geostationary orbit	24°W
Launch vehicle
Launch site	Tyuratam
Mass at launch
Technical data

Specifications

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

S-band capacity


 Cosmos 2219

General

Designation	22219 / 92076A
Launch date	17 Nov 1992
Country of origin	CIS
Mission	Earth observation
Perigee/Apogee	843/855 km
Inclination	71°
Period	101.9 min
Launch vehicle	Zenith
Launch site	Tyuratam
Mass at launch


 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	Soyouz
Launch site	Plesetsk
Mass at launch
End of life

Decay	18 Jan 1993


 Cosmos 2221

General

Designation	22236 / 92080A
Launch date	24 Nov 1992
Country of origin	CIS
Mission	Meteorology
Perigee/Apogee	629/662 km
Inclination	82.5°
Period	97.6 min
Launch vehicle	Tsyclon
Launch site	Plesetsk
Mass at launch


 Cosmos 2222

General

Designation	22238 / 92081A
Launch date	25 Nov 1992
Country of origin	CIS
Mission	Military: warning
Perigee/Apogee	1172/39195 km
Inclination	62.9°
Period	718.1 min
Launch vehicle	Molnya
Launch site	Plesetsk
Mass at launch


 Cosmos 2223

General

Designation	22260 / 92087A
Launch date	9 Dec 1992
Country of origin	CIS
Mission	Earth observation
Perigee/Apogee	238/271 km
Inclination	64.6°
Period	89.6 min
Launch vehicle	Soyouz
Launch site	Tyuratam
Mass at launch
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)
Geostationary orbit	12°E
Launch vehicle
Launch site	Tyuratam
Mass at launch
Technical data

Specifications

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

S-band capacity


 Cosmos 2234

Also called Glonass 59

General

Designation	22512 / 93010A
Launch date	17 Feb 1993
Country of origin	CIS
Mission	Navigation
Perigee/Apogee	19106/19152 km
Inclination	64.9°
Period	675.7 min
Launch vehicle
Launch site
Mass at launch
End of life

Out of service	yes


 Cosmos 2235

Also called Glonass 60 or Glonass 759

General

Designation	22513 / 93010B
Launch date	17 Feb 1993
Country of origin	CIS
Mission	Navigation
Perigee/Apogee	19111/19147 km
Inclination	64.9°
Period	675.7 min
Launch vehicle
Launch site
Mass at launch
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel	21
Plane	1
Slot	7


 Cosmos 2236

Also called Glonass 61 or Glonass 757

General

Designation	22514 / 93010C
Launch date	17 Feb 1993
Country of origin	CIS
Mission	Navigation
Perigee/Apogee	19093/19165 km
Inclination	64.9°
Period	675.7 min
Launch vehicle
Launch site
Mass at launch
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel	5
Plane	1
Slot	2


 Cosmos 2245

General

Designation	22646 / 93030A
Launch date	11 May 1993
Country of origin	CIS
Mission	Military: telecommunications
Perigee/Apogee	1394/1414 km
Inclination	82.6°
Period	113.9 min
Launch vehicle	Cyclone
Launch site	Plesetsk
Mass at launch


 Cosmos 2246

General

Designation	22647 / 93030B
Launch date	11 May 1993
Country of origin	CIS
Mission	Military: telecommunications
Perigee/Apogee	1394/1414 km
Inclination	82.6°
Period	113.9 min
Launch vehicle	Cyclone
Launch site	Plesetsk
Mass at launch


 Cosmos 2247

General

Designation	22648 / 93030C
Launch date	11 May 1993
Country of origin	CIS
Mission	Military: telecommunications
Perigee/Apogee	1394/1414 km
Inclination	82.6°
Period	113.9 min
Launch vehicle	Cyclone
Launch site	Plesetsk
Mass at launch


 Cosmos 2248

General

Designation	22649 / 93030D
Launch date	11 May 1993
Country of origin	CIS
Mission	Military: telecommunications
Perigee/Apogee	1394/1414 km
Inclination	82.6°
Period	113.9 min
Launch vehicle	Cyclone
Launch site	Plesetsk
Mass at launch


 Cosmos 2249

General

Designation	22650 / 93030E
Launch date	11 May 1993
Country of origin	CIS
Mission	Military: telecommunications
Perigee/Apogee	1394/1414 km
Inclination	82.6°
Period	113.9 min
Launch vehicle	Cyclone
Launch site	Plesetsk
Mass at launch


 Cosmos 2250

General

Designation	22651 / 93030F
Launch date	11 May 1993
Country of origin	CIS
Mission	Military: telecommunications
Perigee/Apogee	1394/1414 km
Inclination	82.6°
Period	113.9 min
Launch vehicle	Cyclone
Launch site	Plesetsk
Mass at launch


 Cosmos 2268

General

Designation	22999 / 94011A
Launch date	12 Feb 1994
Country of origin	CIS
Mission	Military: communications (Gonets)
Perigee/Apogee	1411/1426 km
Inclination	82.57°
Period	114.2 min
Launch vehicle	Cyclone 3
Launch site	Plesetsk
Mass at launch


 Cosmos 2269

General

Designation	23000 / 94011B
Launch date	12 Feb 1994
Country of origin	CIS
Mission	Military: communications (Gonets)
Perigee/Apogee	1410/1421 km
Inclination	82.56°
Period	114.2 min
Launch vehicle	Cyclone 3
Launch site	Plesetsk
Mass at launch


 Cosmos 2270

General

Designation	23001 / 94011C
Launch date	12 Feb 1994
Country of origin	CIS
Mission	Military: communications (Gonets)
Perigee/Apogee	1406/1417 km
Inclination	82.57°
Period	114.05 min
Launch vehicle	Cyclone 3
Launch site	Plesetsk
Mass at launch


 Cosmos 2271

General

Designation	23002 / 94011D
Launch date	12 Feb 1994
Country of origin	CIS
Mission	Military: communications (Gonets)
Perigee/Apogee	1403/1415 km
Inclination	82.57°
Period	114 min
Launch vehicle	Cyclone 3
Launch site	Plesetsk
Mass at launch


 Cosmos 2272

General

Designation	23003 / 94011E
Launch date	12 Feb 1994
Country of origin	CIS
Mission	Military: communications (Gonets)
Perigee/Apogee	1396/1415 km
Inclination	82.57°
Period	113.9 min
Launch vehicle	Cyclone 3
Launch site	Plesetsk
Mass at launch


 Cosmos 2273

General

Designation	23004 / 94011F
Launch date	12 Feb 1994
Country of origin	CIS
Mission	Military: communications (Gonets)
Perigee/Apogee	1408/1416 km
Inclination	82.57°
Period	113.9 min
Launch vehicle	Cyclone 3
Launch site	Plesetsk
Mass at launch


 Cosmos 2274

General

Designation	23033 / 94018A
Launch date	17 Mar 1994 at 16:30 UT
Country of origin	CIS
Mission	Military: reconnaissance (Yantar)
Perigee/Apogee	176.1/371.7 km
Inclination	67.15°
Period	89.65 min
Launch vehicle
Launch site	Plesetsk
Mass at launch
End of life

Cause	Landed in Kazakhstan
Decay	21 May 1994


 Cosmos 2275

Also called Glonass 62 or Glonass 758

General

Designation	23043 / 94021A
Launch date	11 Apr 1994 at 08:49 UT
Country of origin	CIS
Mission	Navigation
Perigee/Apogee	19120/19197 km
Inclination	64.81°
Period	676.6 min
Launch vehicle	Proton K
Launch site	Tyuratam
Mass at launch
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel	10
Plane	3
Slot	18


 Cosmos 2276

Also called Glonass 63 or Glonass 760

General

Designation	23044 / 94021B
Launch date	11 Apr 1994 at 08:49 UT
Country of origin	CIS
Mission	Navigation
Perigee/Apogee	19120/19197 km
Inclination	64.81°
Period	676.6 min
Launch vehicle	Proton K
Launch site	Tyuratam
Mass at launch
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel	24
Plane	3
Slot	17


 Cosmos 2277

Also called Glonass 64 or Glonass 761

General

Designation	23045 / 94021C
Launch date	11 Apr 1994 at 08:49 UT
Country of origin	CIS
Mission	Navigation
Perigee/Apogee	19120/19197 km
Inclination	64.80°
Period	676.6 min
Launch vehicle	Proton K
Launch site	Tyuratam
Mass at launch
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel	3
Plane	3
Slot	23


 Cosmos 2278

General

Designation	23087 / 94023A
Launch date	23 Apr 1994 at 08:02 UT
Country of origin	CIS
Mission	Military: intelligence
Perigee/Apogee	854/858 km
Inclination	71°
Period	102 min
Launch vehicle	Zenit 2
Launch site	Tyuratam
Mass at launch


 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
Launch site	Plesetsk
Mass at launch


 Cosmos 2280

General

Designation	23095 / 94025A
Launch date	28 Apr 1994
Country of origin	CIS
Mission	Military: reconnaissance (Yantor'?)
Perigee/Apogee	244/305 km
Inclination	70.3°
Period	90 min
Launch vehicle	Soyuz 5
Launch site	Tyuratam
Mass at launch
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 (Zenit/Oblik)
Perigee/Apogee	192/265 km
Inclination	82.6°
Period	88.7 min
Launch vehicle	Soyuz
Launch site	Plesetsk
Mass at launch

The number 2281 had earlier been assigned to an identical spacecraft that was launched on May 26 but failed to attain orbit.

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)
Geostationary orbit	24°W
Launch vehicle	Proton
Launch site	Tyuratam
Mass at launch
Technical data

Specifications

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

S-band capacity


 Cosmos 2283

General

Designation	23182 / 94042A
Launch date	20 Jul 1994
Country of origin	CIS
Mission	Military: reconnaissance (Yantar')
Perigee/Apogee	179/356 km
Inclination	67.1°
Period	89.5 min
Launch vehicle	Soyuz
Launch site	Plesetsk
Mass at launch
End of life

Decay	29 Sep 1994


 Cosmos 2284

General

Designation	23187 / 94044A
Launch date	29 Jul 1994
Country of origin	CIS
Mission	Military: ?
Perigee/Apogee	206/296 km
Inclination	70.4°
Period	89.2 min
Launch vehicle	Soyuz
Launch site	Tyuratam
Mass at launch
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: calibration?
Perigee/Apogee	974/1013 km
Inclination	74°
Period	105 min
Launch vehicle	Cosmos
Launch site	Plesetsk
Mass at launch


 Cosmos 2286

General

Designation	23194 / 94048A
Launch date	5 Aug 1994
Country of origin	CIS
Mission	Military: early warning (Oko)
Perigee/Apogee	747/39608 km
Inclination	63.4°
Period	718 min
Launch vehicle	Molnya
Launch site	Plesetsk
Mass at launch


 Cosmos 2287

Also called Glonass 65 or Glonass 767

General

Designation	23203 / 94050A
Launch date	11 Aug 1994
Country of origin	CIS
Mission	Navigation
Perigee/Apogee	19109/19150 km
Inclination	64.8°
Period	676 min
Launch vehicle	Proton K
Launch site	Tyuratam
Mass at launch
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
Perigee/Apogee	19091/19168 km
Inclination	64.8°
Period	676 min
Launch vehicle	Proton K
Launch site	Tyuratam
Mass at launch
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
Perigee/Apogee	19126/19133 km
Inclination	64.8°
Period	676 min
Launch vehicle	Proton K
Launch site	Tyuratam
Mass at launch
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)
Perigee/Apogee	181/392 km
Inclination	64.8°
Period	90.2 min
Launch vehicle	Zenith
Launch site	Tyuratam
Mass at launch

This is a 6th 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 t and live for 90 to 120 days. The payload which takes place in a 4.3 m3 capsule weighs 1.2 t.

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 deg to 181 x 571 km x 64.8 deg, and four new small objects were tracked in the post-manouevre 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	80°E
Launch vehicle	Proton
Launch site	Tyuratam
Mass at launch
Technical data

Specifications

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


 Cosmos 2292

General

Designation	23278 / 94061A
Launch date	27 Sep 1994 at 13:00 UT
Country of origin	CIS
Mission	Military: calibration (vektor?)
Perigee/Apogee	400/1951 km
Inclination	82.9°
Period	108.9 min
Launch vehicle	Cosmos 3M
Launch site	Plesetsk
Mass at launch


 Cosmos 2293

General

Designation	23336 / 94072A
Launch date	2 Nov 1994
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	402/418 km
Inclination	65°
Period	92.8 min
Launch vehicle	Tsiklon 2
Launch site
Mass at launch


 Cosmos 2294

Also called Glonass 68 or Glonass 762

General

Designation	23396 / 94076A
Launch date	20 Nov 1994 at 00:09 UT
Country of origin	CIS
Mission	Navigation
Perigee/Apogee	19052/19207 km
Inclination	64.9°
Period	675 min
Launch vehicle	Proton K
Launch site	Tyuratam LC200
Mass at launch
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel	12
Plane	1
Slot	4


 Cosmos 2295

Also called Glonass 69 or Glonass 763

General

Designation	23397 / 94076B
Launch date	20 Nov 1994 at 00:09 UT
Country of origin	CIS
Mission	Navigation
Perigee/Apogee	19052/19207 km
Inclination	64.9°
Period	675 min
Launch vehicle	Proton K
Launch site	Tyuratam LC200
Mass at launch
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel	21
Plane	1
Slot	3


 Cosmos 2296

Also called Glonass 70 or Glonass 764

General

Designation	23398 / 94076C
Launch date	20 Nov 1994 at 00:09 UT
Country of origin	CIS
Mission	Navigation
Perigee/Apogee	19118/19114 km
Inclination	64.9°
Period	675 min
Launch vehicle	Proton K
Launch site	Tyuratam LC200
Mass at launch
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel	13
Plane	1
Slot	6


 Cosmos 2297

General

Designation	23404 / 94077A
Launch date	24 Nov 1994 at 09:16 UT
Country of origin	CIS
Mission	Military: intelligence
Perigee/Apogee	845/857 km
Inclination	71°
Period	102 min
Launch vehicle	Zenit 2
Launch site	Tyuratam LC45
Mass at launch


 Cosmos 2298

General

Designation	23431 / 94083A
Launch date	20 Dec 1994 at 05:11 UT
Country of origin	CIS
Mission	Military: see below
Perigee/Apogee	785/810 km
Inclination	74°
Period	100.8 min
Launch vehicle	Cosmos 3M
Launch site	Plesetsk LC132
Mass at launch

Satellites are launched into this orbit at the rate of about one a year; Cosmos 2298 is the 48th to reach orbit since Kosmos-372 in 1970. Western analysts have suggested that the series are communications satellites for sensitive military or intelligence communications.


 Cosmos 2299

General

Designation	23441 / 94086A
Launch date	26 Dec 1994 at 22:27 UT
Country of origin	CIS
Mission	Military: telecommunications (Gonets)
Perigee/Apogee	1402/1415 km
Inclination	82.6°
Period	114 min
Launch vehicle	Tsiklon 3
Launch site	Plesetsk LC32
Mass at launch


 Cosmos 2300

General

Designation	23442 / 94086B
Launch date	26 Dec 1994 at 22:27 UT
Country of origin	CIS
Mission	Military: telecommunications (Gonets)
Perigee/Apogee	1410/1414 km
Inclination	82.5°
Period	114 min
Launch vehicle	Tsiklon 3
Launch site	Plesetsk LC32
Mass at launch


 Cosmos 2301

General

Designation	23443 / 94086C
Launch date	26 Dec 1994 at 22:27 UT
Country of origin	CIS
Mission	Military: telecommunications (Gonets)
Perigee/Apogee	1410/1414 km
Inclination	82.5°
Period	114 min
Launch vehicle	Tsiklon 3
Launch site	Plesetsk LC32
Mass at launch


 Cosmos 2302

General

Designation	23444 / 94086D
Launch date	26 Dec 1994 at 22:27 UT
Country of origin	CIS
Mission	Military: telecommunications (Gonets)
Perigee/Apogee	1413/1423 km
Inclination	82.6°
Period	114.2 min
Launch vehicle	Tsiklon 3
Launch site	Plesetsk LC32
Mass at launch


 Cosmos 2303

General

Designation	23445 / 94086E
Launch date	26 Dec 1994 at 22:27 UT
Country of origin	CIS
Mission	Military: telecommunications (Gonets)
Perigee/Apogee	1413/1430 km
Inclination	82.6°
Period	114.3 min
Launch vehicle	Tsiklon 3
Launch site	Plesetsk LC32
Mass at launch


 Cosmos 2304

General

Designation	23446 / 94086F
Launch date	26 Dec 1994 at 22:27 UT
Country of origin	CIS
Mission	Military: telecommunications (Gonets)
Perigee/Apogee	1412/1417 km
Inclination	82.6°
Period	114.1 min
Launch vehicle	Tsiklon 3
Launch site	Plesetsk LC32
Mass at launch


 Cosmos 2305

General

Designation	23453 / 94088A
Launch date	29 Dec 1994 at 11:31 UT
Country of origin	CIS
Mission	Military: reconnaissance (Yantar')
Perigee/Apogee	231/288 km
Inclination	64.9°
Period	89.7 min
Launch vehicle	Soyuz U
Launch site	Tyuratam LC31
Mass at launch


 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 3M
Launch site	Plesetsk
Mass at launch

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	64.8°
Period	279 min
Launch vehicle	Proton K
Launch site	Tyuratam
Mass at launch
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
Perigee/Apogee	19132 km
Inclination	64.8°
Period	279 min
Launch vehicle	Proton K
Launch site	Tyuratam
Mass at launch
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
Perigee/Apogee	19132 km
Inclination	64.8°
Period	279 min
Launch vehicle	Proton K
Launch site	Tyuratam
Mass at launch
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 3M
Launch site	Plesetsk
Mass at launch

For the Russian navy

Technical data

Specifications

Prime contractor	PO Polyot of Omsk
Platform
Mass at launch
Mass in orbit
Length
Width
Height
Stabilization
DC power
Design lifetime


 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 U
Launch site	Plesetsk
Mass at launch

Design lifetime: 2 months


 Launch vehicles

Ariane

STS

World Launch Vehicle Overview

Vehicle	First launch	LEO capacity (kg)	GTO capacity (kg)
CIS (Sheldon / DoD)
Vostok (A1 / SL3)	1959	4700
Soyuz (A2 / SL4)	1963	7000
Molnya (A2e / SL6)	1961		1500
Cosmos (C1 / SL8)	1964	1350
Cosmos (F1 / SL11)	1966	3500
Tsyklon (F2 / SL14)	1977	4000
Proton (D1 / SL13)	1968	20000
Proton (D1e / SL12)	1967		5500 (GEO)
Zenit 2 (J1 / SL16)	1985	13740
Energia (K1 / SL17)	1987	88000	18000 (GEO)
Start 1	Mar 1993
United States
Scout G1	1979	270	54
Scout 2	1993?	525	110
Delta 2 6925	1989	3990	1450
Delta 2 7925	1990	5050	1800
Atlas 1	1990	5600	2250
Atlas 2	1991	6400	2700
Atlas 2A	1991	6800	2800
Atlas 2AS	1993	8400	3500
Atlas RD 180	?
Titan 2	1964	2000
Titan 2S	?
Titan 34D	1982	12500	1900
Titan 3	1989	14500	5000 (with TOS)
Titan 4	1989	17700	5500
Titan 4SRMU	?
STS	12 Apr 1981	24200	5900 (with IUS)
Pegasus	1990	455	125 (with TOS)
Pegasus Turbo	?
Pegasus XL	?
Taurus	13 Mar 1994 (94017)	1400
Lockheed LLV	Mar 1995?	3600
Conestoga	May 1995?
Europe
Ariane 1	24 Dec 1979		1700
Ariane 2	30 May 1986		2065
Ariane 3	4 Aug 1984		2580
Ariane 4, 40	22 Jan 1990	4900	2020
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 4, 44LP	15 Jun 1988	8300	4030
Ariane 4, 44L	4 Jun 1989	9600	4460
Ariane 5	Nov 1995?	18000	6800
Japan
Mu 4S	1970
Mu 3C	1974
Mu 3H	1977
Mu 3S	1981	250
Mu 3S 2	1985	770
N1	1975
N2	1980		350
H1	1986	3200	1100
H2	3 Feb 1994 (94007)	10500?	4000?
J1	1996?
M5	1996?
China
Long March 1D	?
Long March 2C	1975	3200	1000 + PKM
Long March 2E	1990	9300	3370 + PKM
Long March 3	1984	5000	1500
Long March 3A	1992	7200	2500
Long March 3B	1996?
Long March 4	1988	4000
India
SLV 3	1979	40
ASLV	1987	150
PSLV	1993	3000	450
GSLV	1996?	8000	2500


 Ariane

European launch vehicle program

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)
4, 40	22 Jan 1990	21 Apr 1995	4900/2020	4
4, 42P	20 Nov 1990	1 Dec 1994	6100/2740	6 (1 failure)
4, 44P	4 Apr 1991	9 Sep 1994	6900/3290	4
4, 42L	12 May 1993	12 May 1993	7400/3350	1
4, 44LP	15 Jun 1988	17 May 1995	8300/4030	16 (1 failure)
4, 44L	4 Jun 1989	8 Oct 1994	9600/4460	14 (1 failure)


Ariane

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


SYLDA: SYstème de Lancement Double d'Ariane

SPELDA: Système Porteur Externe pour le Lancement Double Ariane

Ariane 5

Premier essai du booster à Kourou le 16 Feb 1993. Fabriqué en guyane, ce booster est une fusée à poudre de 30 m de longueur. Sa pousée est à elle seule comparable à la plus puissante des versions d'Ariane 4.

Deux boosters de ce type flanqueront un corps central muni, d'un gros moteur à hydrogène Vulcain.

Le premier lancement d'une Ariane 5 est prévu au cours du second semestre 1995. Ariane 5 présentera la caractéristique d'être plus fiable qu'Ariane 4, tout en étant moins chère de 10 %. Son aptitude à effectuer des lancements doubles de gros satellites devrait être un atout supplémentaire pour l'Europe.


 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 Oscar 09 (failure)
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	201/36.206 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: Brazilsat 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: Brazilsat 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: Aussat 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


 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 D 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


 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


 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	3500 kg
Payload	A: Panamsat 2 B: Yuri 3N
GTO	199.6/35977 km; inclination: 7°


 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: Brazilsat 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 id	n/a
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


 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: Brazilsat 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

Third stage was a H-10+ type


 Ariane V73

General

Launch id	95023
Launch date	17 May 1995 at 6:34 UT
Launch site	Kourou
Type	4, 44LP
Payload mass
Payload	Intelsat 706

Third stage was a H-10-3 type (second use)


Ariane V74

General

Launch id
Launch date	planned on 9 Jun 1995
Launch site	Kourou
Type	4, 42P or 40
Payload mass
Payload	DBS 3


Ariane V75

General

Launch id
Launch date	planned in Jun 1995
Launch site	Kourou
Type	4, 40 or 42P
Payload mass
Payload	Helios


Ariane V76

General

Launch id
Launch date	planned in Jun 1995
Launch site	Kourou
Type	4, 44P
Payload mass
Payload	N Star A


Ariane V77

General

Launch id
Launch date	planned in Jul 1995
Launch site	Kourou
Type	4, 44L
Payload mass
Payload	Panamsat 4 Amos


Ariane V78

General

Launch id
Launch date	planned in Aug 1995
Launch site	Kourou
Type	4, 42L
Payload mass
Payload	Astra 1E


Ariane V79

General

Launch id
Launch date	planned in Aug 1995
Launch site	Kourou
Type	4, 44L
Payload mass
Payload	Telecom 2C Insat 2C


Ariane V80

General

Launch id
Launch date	planned in Sep 1995
Launch site	Kourou
Type	4, 44P
Payload mass
Payload	N Star B*


Ariane V81

General

Launch id
Launch date	planned in Oct 1995
Launch site	Kourou
Type	4, 44LP
Payload mass
Payload	Intelsat 707


Ariane V82

General

Launch id
Launch date	planned in Nov 1995
Launch site	Kourou
Type	4, 44L
Payload mass
Payload	Palapa C1 Measat 1


Ariane V83

General

Launch id
Launch date	planned in Dec 1995
Launch site	Kourou
Type	4, 42P
Payload mass
Payload	M Sat


 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.


STS

STS 01 STS 02 STS 03 STS 04 STS 05 STS 06 STS 07 STS 08 STS 09 STS 10 STS 11 STS 12 STS 13 STS 14 STS 15 STS 16 STS 17 STS 18 STS 19 STS 20	STS 21 STS 22 STS 23 STS 24 STS 25 STS 26 STS 27 STS 28 STS 29 STS 30 STS 31 STS 32 STS 33 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 68


 STS 01

General

Launch id	81034
Launch date	12 Apr 1981
Launch site	Cape Canaveral pad 39A
Type	Columbia
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


 STS 02

General

Launch id	81111
Launch date	12 Nov 1981
Launch site	Cape Canaveral pad 39A
Type	Columbia
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


 STS 03

General

Launch id	82022
Launch date	22 Mar 1982
Launch site	Cape Canaveral pad 39A
Type	Columbia
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


 STS 04

General

Launch id	82065
Launch date	27 Jun 1982
Launch site	Cape Canaveral pad 39A
Type	Columbia
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


 STS 05

General

Launch id	82110
Launch date	11 Nov 1982
Launch site	Cape Canaveral
Type	Columbia
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


 STS 06

General

Launch id	83026
Launch date	4 Apr 1983
Launch site	Cape Canaveral
Type	Challenger
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


 STS 07

General

Launch id	83059
Launch date	18 Jun 1983
Launch site	Cape Canaveral
Type	Challenger
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


 STS 08

General

Launch id	83089
Launch date	30 Aug 1983
Launch site	Cape Canaveral
Type	Challenger
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


 STS 09

Also called STS 41A

General

Launch id	83116
Launch date	28 Nov 1983
Launch site	Cape Canaveral pad 39A
Type	Columbia
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)


 STS 10

Also called STS 41B

General

Launch id	84011
Launch date	3 Feb 1984
Launch site	Cape Canaveral
Type	Challenger
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)


 STS 11

Also called STS 41C

General

Launch id	84034
Launch date	6 Apr 1984
Launch site	Cape Canaveral
Type	Challenger
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


 STS 12

Also called STS 41D

General

Launch id	84093
Launch date	30 Aug 1984
Launch site	Cape Canaveral
Type	Discovery
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


 STS 13

Also called STS 41G

General

Launch id	84108
Launch date	5 Oct 1984
Launch site	Cape Canaveral
Type	Challenger
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


 STS 14

Also called STS 51A

General

Launch id	84113
Launch date	8 Nov 1984
Launch site	Cape Canaveral
Type	Discovery
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 10). Operation financed by the insurance companies.


 STS 15

Also called STS 51C

General

Launch id	85010
Launch date	24 Jan 1985
Launch site	Cape Canaveral
Type	Discovery
Crew	Thomas Mattingly Loren Shriver Ellison Onizuka James Buchli Gary Payton
Landing date	27 Jan 1985
Landing site	Cape Canaveral
Payload	Aquacade or Magnum or Sigint, geostationary orbit?

Flight of 3 days 1 h 33 min

Military mission


 STS 16

Also called STS 51D

General

Launch id	85028
Launch date	12 Apr 1985
Launch site	Cape Canaveral
Type	Discovery
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


 STS 17

Also called STS 51B

General

Launch id	85034
Launch date	29 Apr 1985
Launch site	Cape Canaveral
Type	Challenger
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


 STS 18

Also called STS 51G

General

Launch id	85048
Launch date	17 Jun 1985
Launch site	Cape Canaveral
Type	Discovery
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 201-1 (launched and retrieved)

Flight of 7 days 1 h 38 min 53 s


 STS 19

Also called STS 51F

General

Launch id	85063
Launch date	29 Jul 1985
Launch site	Cape Canaveral
Type	Challenger
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


 STS 20

Also called STS 51I

General

Launch id	85076
Launch date	27 Aug 1985
Launch site	Cape Canaveral
Type	Discovery
Crew	Joe Engle Richard Covey James Van Hoften William Fisher John Lounge
Landing date	3 Sep 1985
Landing site	Edwards
Payload	B: Aussat A1 C: ASC 1 D: Leasat 4

Flight of 7 days 2 h 18 min 29 s

Leasat 3 was repared


 STS 21

Also called STS 51J

General

Launch id	85092
Launch date	3 Oct 1985
Launch site	Cape Canaveral
Type	Atlantis
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


 STS 22

Also called STS 61A

General

Launch id	85104
Launch date	30 Oct 1985
Launch site	Cape Canaveral
Type	Columbia
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)


 STS 23

Also called STS 61B

General

Launch id	85109
Launch date	27 Nov 1985
Launch site	Cape Canaveral
Type	Atlantis
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: Aussat A2 D: Satcom K2

Flight of 6 days 21 h 4 min 50 s


 STS 24

Also called STS 61C

General

Launch id	86003
Launch date	12 Jan 1986
Launch site	Cape Canaveral pad 39A
Type	Columbia
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


 STS 25

Also called STS 61D

General

Launch date	28 Jan 1986
Launch site	Cape Canaveral
Type	Challenger
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

Explosion after 73 s


 STS 26

Also called STS 81A

General

Launch id	88091
Launch date	29 Sep 1988
Launch site	Cape Canaveral
Type	Discovery
Crew	R. Hauck Richard Covey John Lounge George Nelson David Hilmers
Landing date	3 Oct 1988
Landing site	Edwards
Payload	B: TDRS 3


 STS 27

Also called STS 91A

General

Launch id	88106
Launch date	2 Dec 1988
Launch site	Cape Canaveral
Type	Atlantis
Crew	Robert Gibson Guy Gardner Rochard Mullane Jerry Ross William Sheperd
Landing date	6 Dec 1988
Landing site	Edwards
Payload	B: Lacrosse (USA 34)

Flight of 4 days 9 h


 STS 28

Also called STS 91D

General

Launch id	89061
Launch date	8 Aug 1989
Launch site	Cape Canaveral pad 39B
Type	Columbia
Crew	Brewster Shaw Richard Richards David Leetsma James Adamson Mark Brown
Landing date	13 Aug 1989
Landing site	Edwards
Payload	B: KH 12-1 (USA 40) C: (USA 41)


 STS 29

Also called STS 91B

General

Launch id	89021
Launch date	13 Mar 1989
Launch site	Cape Canaveral
Type	Discovery
Crew	Michel Coats John Blaha James Buchli Robert Springer James Bagion
Landing date	18 Mar 1989
Landing site	Edwards
Payload	B: TDRS 4


 STS 30

Also called STS 91C

General

Launch id	89033
Launch date	4 May 1989
Launch site	Cape Canaveral
Type	Atlantis
Crew	David Walker Ronald Grabe Norman Thagard Mary Cleave Mark Lee
Landing date	8 May 1989
Landing site	Edwards
Payload	B: Magellan


 STS 31

Also called STS 0E

General

Launch id	90037
Launch date	24 Apr 1990
Launch site	Cape Canaveral
Type	Discovery
Crew	Loren Shriver Charles Boden Steven Hawley Bruce Mc Candless Catherin Sullivan
Landing date	29 Apr 1990
Landing site
Payload	B: HST


 STS 32

Also called STS 0C

General

Launch id	90002
Launch date	9 Jan 1990
Launch site	Cape Canaveral pad 39A
Type	Columbia
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


 STS 33

Also called STS 0B

General

Launch id	89090
Launch date	23 Nov 1989
Launch site	Cape Canaveral
Type	Discovery
Crew	Frederik Gregory David Griggs F. Story Musgrave Kathryn Thurnton Manley Carter
Landing date	28 Nov 1989
Landing site	Edwards
Payload	B: Sigint? (USA 48)


 STS 34

Also called STS 0A

General

Launch id	89084
Launch date	18 Oct 1989
Launch site	Cape Canaveral
Type	Atlantis
Crew	Donald Williams Michael Mc Cully Shannon Lucid Ellen Baker Franklin Chang-Diaz
Landing date	23 Oct 1989
Landing site	Edwards
Payload	B: Galileo


 STS 35

General

Launch id	90106
Launch date	2 Dec 1990
Launch site	Cape Canaveral pad 39B
Type	Columbia
Crew	Brand Gardner Lounge Hoffman Parker Parise
Landing date	10 Dec 1990
Landing site	Edwards
Payload	none

ASTRO 1 mission


 STS 36

Also called STS 0D

General

Launch id	90019
Launch date	28 Feb 1990
Launch site	Cape Canaveral
Type	Atlantis
Crew	John Creighton John Casper Richard Mullane David Hilmers Pierre Thuot
Landing date	4 Mar 1990
Landing site	Edwards
Payload	B: AFP 731


 STS 37

General

Launch id	91027
Launch date	5 Apr 1991
Launch site	Cape Canaveral
Type	Atlantis
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


 STS 38

General

Launch id	90097
Launch date	15 Nov 1990
Launch site	Cape Canaveral
Type	Atlantis
Crew	Covey Culbertson Springer Meade Gemar
Landing date	20 Nov 1990
Landing site	Cape Canaveral
Payload	AFP 658

Military mission


 STS 39

General

Launch id	91031
Launch date	28 Apr 1991
Launch site	Cape Canaveral
Type	Discovery
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


 STS 40

General

Launch id	91040
Launch date	5 Jun 1991
Launch site	Cape Canaveral pad 39B
Type	Columbia
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


 STS 41

General

Launch id	90090
Launch date	6 Oct 1990
Launch site	Cape Canaveral
Type	Discovery
Crew	Richard Richards Robert Parker Bruce Melnick William Shepperd Thomas Akers
Landing date	10 Oct 1990
Landing site	Edwards
Payload	B: Ulysse


 STS 42

General

Launch id	92002
Launch date	22 Jan 1992
Launch site	Cape Canaveral
Type	Discovery
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


 STS 43

General

Launch id	91054
Launch date	2 Aug 1991
Launch site	Cape Canaveral
Type	Atlantis
Crew	John Blaha Michael Baker James Adamson David Low Shannon Lucid
Landing date	11 Aug 1991
Landing site	Cape Canaveral
Payload	B: TDRS 5


 STS 44

General

Launch id	91080
Launch date	25 Nov 1991
Launch site	Cape Canaveral
Type	Atlantis
Crew	Gregory Henricks Voss Musgrave Runco Hennen
Landing date	1 Dec 1991
Landing site	Edwards
Payload	DSP 3-4


 STS 45

General

Launch id	92015
Launch date	24 Mar 1992
Launch site	Cape Canaveral
Type	Atlantis
Crew	Bolden Duffy Leetsma Sullivan Foale Lichtenberg Dirck Frimout (Belgium)
Landing date	2 Apr 1992
Landing site	Cape Canaveral
Payload	none

ATLAS 1 mission


 STS 46

General

Launch id	92049
Launch date	31 Jul 1992
Launch site	Cape Canaveral
Type	Atlantis
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


 STS 47

General

Launch id	92061
Launch date	12 Sep 1992 at 14:23 UT
Launch site	Cape Canaveral, pad 39A
Type	Endeavour
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


 STS 48

General

Launch id	91063
Launch date	12 Sep 1991
Launch site	Cape Canaveral
Type	Discovery
Crew	Creighton Reightler Gemar Brown Buchli
Landing date	18 Sep 1991
Landing site	Edwards
Payload	B: UARS


 STS 49

General

Launch id	92026
Launch date	7 May 1992
Launch site	Cape Canaveral
Type	Endeavour
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


 STS 50

General

Launch id	92034
Launch date	25 Jun 1992
Launch site	Cape Canaveral pad 39A
Type	Columbia
Crew	Richards Bowersox Dunbar Baker Meade Delucas Trinh
Landing date	9 Jul 1992
Landing site	Cape Canaveral
Payload	none

USML 1 mission


 STS 51

General

Launch id	93058
Launch date	12 Sep 1993
Launch site	Cape Canaveral
Type	Discovery
Crew	5 persons
Landing date	22 Sep 1993
Landing site
Payload	B: ACTS C: Orfeus-Spas (launched and retrieved)


 STS 52

General

Launch id	92070
Launch date	22 Oct 1992
Launch site	Cape Canaveral pad 39B
Type	Columbia
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


 STS 53

General

Launch id	92086
Launch date	2 Dec 1992
Launch site	Cape Canaveral
Type	Discovery
Crew	Walker Cabana Bluford Voss Clifford
Landing date	9 Dec 1992
Landing site	Edwards
Payload	DoD 1 (USA 89)


 STS 54

General

Launch id	93003
Launch date	13 Jan 1993 at 13:59:30
Launch site	Cape Canaveral, pad 39 B
Type	Endeavour
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


 STS 55

General

Launch id	93027
Launch date	26 Apr 1993
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
Landing site	Cape Canaveral
Payload	none

Spacelab D2 mission


 STS 56

General

Launch id	93023
Launch date	8 Apr 1993
Launch site	Cape Canaveral
Type	Discovery
Crew	Cameron Oswald Foale Cockrell Ochoa
Landing date	17 Apr 1993
Landing site	Cape Canaveral
Payload	B: Spartan 201-2 (launched and retrieved)

ATLAS 2 mission


 STS 57

General

Launch id	93037
Launch date	21 Jun 1993 at 13:07:22
Launch site	Cape Canaveral
Type	Endeavour
Crew	Grabe Duffy Low Sherlock Wisoff Voss
Landing date	1 Jul 1993
Landing site	Cape Canaveral
Payload	none

Spacehab 1 (SH 1) mission

Retrieval of Eureca


 STS 58

General

Launch id	93065
Launch date	18 Oct 1993
Launch site	Cape Canaveral pad 39B
Type	Columbia
Crew	Blaha Searfoss Seddon Mc Arthur Wolf Lucid Fettman
Landing date	1 Nov 1993
Landing site	Edwards
Payload	none

SLS 2 mission


 STS 59

General

Launch id	94020
Launch date	9 Apr 1994 at 12:05 UT
Launch site	Cape Canaveral
Type	Endeavour
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.


 STS 60

General

Launch id	94006
Launch date	3 Feb 1994 at 12:10 UT
Launch site	Cape Canaveral
Type	Discovery
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.


 STS 61

General

Launch id	93075
Launch date	2 Dec 1993
Launch site	Cape Canaveral
Type	Endeavour
Crew	Covey Bowerbox Akers Hoffman Musgrave Thornton Nicollier
Landing date	13 Dec 1993
Landing site	Cape Canaveral
Payload	none

Reparation of Hubble


 STS 62

General

Launch id	94015
Launch date	4 Mar 1994
Launch site	Cape Canaveral
Type	Columbia
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.


 STS 63

General

Launch id	95004
Launch date	3 Feb 1995 at 05:22:04 UT
Launch site	Cape Canaveral LC39B
Type	Discovery
Crew	Jim Wetherbee Eileen Collins Bernard Harris (mission specialist) Mike Foale (mission specialist) Janice Voss Vladimir Titov (Russian Space Agency)
Landing date	Cape Canaveral
Landing site	11 Feb 1995 at 11:50 UT
Payload	Spartan 201-4 (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.


 STS 64

General

Launch id	94059
Launch date	9 Sep 1994 at 22:22 UT
Launch site	Cape Canaveral, pad 39B
Type	Discovery
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 201-3 (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).


 STS 65

General

Launch id	94039
Launch date	8 Jul 1994 at 16:43 UT
Launch site	Cape Canaveral pad 39A
Type	Columbia
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.


 STS 66

General

Launch id	94073
Launch date	3 Nov 1994 at 06:59 UT
Launch site	Cape Canaveral
Type	Atlantis
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.


 STS 67

General

Launch id	95007
Launch date	2 Mar 1995 at 06:38:14 UT
Launch site	Cape Canaveral LC39A
Type	Endeavour
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.


 STS 68

General

Launch id	94062
Launch date	30 Sep 1994
Launch site	Cape Canaveral
Type	Endeavour
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.


STS 70

General

Launch id
Launch date	planned on 8 Jun 1995
Launch site	Cape Canaveral pad 39B
Type	Discovery
Crew	Tom Henricks (commander) Kevin Kregel (pilot) Nancy Currie (mission specialist) Dr. Donald Thomas (mission specialist) Dr. Mary Weber (mission specialist)
Landing date	duration 5-8 days
Landing site
Payload	TDRS 7

STS-70 will mark 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.  On STS-73,

scheduled for launch in late September 1995, all three of the SSME's will be of

the Block I design.


STS 71

General

Launch id
Launch date	planned on 19-24 Jun 1995
Launch site	Cape Canaveral pad 39A
Type	Atlantis
Crew
Landing date
Landing site
Payload

Space Life Sciences (SL M) and trim with Mir


STS 69

General

Launch id
Launch date	planned on 20 Jul 1995
Launch site	Cape Canaveral
Type	Endeavour
Crew
Landing date
Landing site
Payload

Wake Shield Facility (WSF 2)


STS 73

General

Launch id
Launch date	planned in Sep 1995
Launch site	Cape Canaveral
Type	Columbia
Crew
Landing date	16-day mission
Landing site
Payload

Spacelab USML-2


STS 74

General

Launch id
Launch date	planned in Oct 1995
Launch site	Cape Canaveral
Type	Atlantis
Crew
Landing date
Landing site
Payload

2nd Mir Docking


STS 72

General

Launch id
Launch date	planned in Nov 1995
Launch site	Cape Canaveral
Type	Endeavour
Crew
Landing date
Landing site
Payload

SFU retrieval


STS 75

General

Launch id
Launch date	planned on 15 Feb 1996
Launch site	Cape Canaveral
Type	Columbia
Crew	Claude Nicollier (mission specialist, ESA) Maurizio Cheli (mission specialist, ESA)
Landing date
Landing site
Payload

Second deployment of TSS and the third flight of scientific investigations using the US Microgravity Payload (USMP) complement. The mission is scheduled to last 13 days.

See ESA-002.95.TXT


STS 78

General

Launch id
Launch date	scheduled for mid-1996
Launch site	Cape Canaveral
Type	Columbia
Crew	7
Landing date
Landing site
Payload

Spacelab

See NASA-212.94.TXT


 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

LEO satellites

Remote sensing satellites

Telecommunications

Geostationary satellites

LEO satellites

Navigation

Navigation satellites


 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

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 4

1974

(070)	ANS

1975

(092)	Aura

1977

(012)	IUE

1983

(020)	Astron

1992

(031)	EUVE

1994

(004)	Spartan 201-4

X-ray astronomy

1968

Cosmos 0208

1970

(107)	Explorer 42

1972

(065)	OAO 4

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 201-1

1987

(012)	Astro C

1989

(096)	Granat

1990

(049)	Rosat

(058)	Gamma

1993

(011)	Astro D

Radio astronomy

1968

(055)	Explorer 38

1983

(067)	Prognoz 09

1991

(050)	Sara


 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

1981

Cosmos 1410

1982

Cosmos 1510

1984

Cosmos 1589

1985

Cosmos 1660

1986

Cosmos 1732

(061)	Ajisai

Cosmos 1803

1987

Cosmos 1823

1988

Cosmos 1950

1989

Etalon 1

Etalon 2

(068)	Cosmos 2037

1990

Etalon 3

Cosmos 2088

1992

(070)	Lageos 2

1993

(061)	Stella

1994

(078)	GEO-IK

1995

GFZ 1


 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)	Aryaghata

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)	Koronas 1

(027)	Sross C2

1995

(002)	Astrid


 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

1993

(023)	Spartan 201-2

1994

(006)	Bremsat


 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

1990

(007)	Hiten

1991

(086)	Magion 3

1992

(064)	Freja

1994

(014)	Koronas 1

(046)	Apex

1995

(002)	Astrid


 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


 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

1993

(023)	Spartan 201-2

1994

(014)	Koronas 1

(059)	Spartan 201-3

(071)	Wind 1


 Meteorological geostationary satellites

1966

(110)	ATS 1

1967

(111)	ATS 3

1974

(033)	SMS 1

1975

(011)	SMS 2

(100)	Goes 1

1977

(048)	Goes 2

(065)	GMS 1

(108)	Meteosat 1

1978

(062)	Goes 3

1980

(074)	Goes 4

1981

(049)	Goes 5

(057)	Meteosat 2

(076)	GMS 2

1982

(031)	Insat 1A

(041)	Goes 6

1983

(089)	Insat 1B

1984

(080)	GMS 3

1987

(022)	Goes 7

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 8

(069)	Electro 1

1995

(011)	GMS 5


 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

(087)	Essa 3

1967

(006)	Essa 4

DMSP B4-2

(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)

(098)	Nimbus 7

Tiros N

1979

Meteor 1-29

Meteor 2-04

DMSP B5D1-4 (AMS 4)

(057)	NOAA 06

Meteor 2-05

1980

(043)	NOAA 07

Meteor 1-30

Meteor 2-06

1981

Meteor 2-07

(059)	NOAA 07C

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 B5D2-8

(089)	NOAA 14

1995

(015)	DMSP B5D2-9


 Remote sensing satellites

1972

(058)	Landsat 1

1975

(004)	Landsat 2

(070)	Dong Fang Hong 03

(110)	Dong Fang Hong 04

(119)	Dong Fang Hong 05

1976

(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

(051)	Bhaskara 1

Intercosmos 20

1980

Cosmos 1151

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

1984

(021)	Landsat 5

(098)	Dong Fang Hong 16

Cosmos 1602

1985

(096)	Dong Fang Hong 17

Cosmos 1689

1986

(019)	Spot 1

Cosmos 1766

(076)	Dong Fang Hong 19

1987

(018)	Momo 1A

Cosmos 1869

(064)	Cosmos 1870

(075)	Dong Fang Hong 21

1988

(021)	IRS 1A

(056)	Okean 1

Cosmos 1939

1989

(038)	Resurs F01

(047)	Resurs F02

(055)	Resurs F03

(063)	Resurs F04

(073)	Resurs F05

1990

(005)	Spot 2

(013)	Momo 1B

(018)	Okean 2

(047)	Resurs F06

(060)	Resurs F07

(073)	Resurs F08

(082)	Resurs F09

(089)	Dong Fang Hong 33

1991

Almaz

(035)	Resurs F10

(039)	Okean 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

1993

(009)	SCD

(033)	Resurs F17

(040)	Resurs F18

(053)	Resurs F19

(061)	Spot 3

1994

(066)	Okean O1

(068)	IRS P2

(074)	Resurs O1-3

1995

(021)	ERS 2


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)	Molnya 1-01

Molnya 1-02

(108)	Oscar 04

1966

Cosmos 103

Molnya 1-03

IDSCP 1-1

IDSCP 1-2

IDSCP 1-3

IDSCP 1-4

IDSCP 1-5

IDSCP 1-6

IDSCP 1-7

Molnya 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

Molnya 1-05

IDSCP 3-1

IDSCP 3-2

IDSCP 3-3

IDSCP 3-4

Molnya 1-06

Molnya 1-07

1968

Molnya 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

Molnya 1-09

Cosmos 236

Molnya 1-10

1969

Molnya 1-11

Molnya 1-12

Cosmos 292

Cosmos 304

1970

(008)	Oscar 05

Molnya 1-13

Cosmos 332

Cosmos 336

Cosmos 337

Cosmos 338

Cosmos 339

Cosmos 340

Cosmos 341

Cosmos 342

Cosmos 343

Molnya 1-14

Molnya 1-15

Cosmos 371

Cosmos 372

Molnya 1-16

Molnya 1-17

1971

SDS A

Cosmos 407

Cosmos 411

Cosmos 412

Cosmos 413

Cosmos 414

Cosmos 415

Cosmos 416

Cosmos 417

Cosmos 418

Molnya 1-18

(086)	Cosmos 0444

(086)	Cosmos 0445

(086)	Cosmos 0446

(086)	Cosmos 0447

(086)	Cosmos 0448

(086)	Cosmos 0449

(086)	Cosmos 0450

(086)	Cosmos 0451

(100)	Molnya 2-01

Cosmos 468

Molnya 1-19

1972

Molnya 1-20

Molnya 2-02

Cosmos 494

(057)	Cosmos 0504

(057)	Cosmos 0505

(057)	Cosmos 0506

(057)	Cosmos 0507

(057)	Cosmos 0508

(057)	Cosmos 0509

(057)	Cosmos 0510

(057)	Cosmos 0511

Molnya 2-03

Molnya 1-21

(082)	Oscar 06

Cosmos 528

Cosmos 529

Cosmos 530

Cosmos 531

Cosmos 532

Cosmos 533

Cosmos 534

Cosmos 535

Molnya 1-22

Molnya 2-04

Cosmos 540

1973

Molnya 1-23

Molnya 2-05

Cosmos 564

Cosmos 565

Cosmos 566

Cosmos 567

Cosmos 568

Cosmos 569

Cosmos 570

Cosmos 571

Molnya 2-06

SDS B

Molnya 1-24

(069)	Cosmos 0588

(069)	Cosmos 0589

(069)	Cosmos 0590

(069)	Cosmos 0591

(069)	Cosmos 0592

(069)	Cosmos 0593

(069)	Cosmos 0594

(069)	Cosmos 0595

Molnya 2-07

Molnya 1-25

Molnya 1-26

Cosmos 614

Cosmos 617

Cosmos 618

Cosmos 619

Cosmos 620

Cosmos 621

Cosmos 622

Cosmos 623

Cosmos 624

Molnya 2-08

1974

Molnya 1-27

(024)	Cosmos 0641

(024)	Cosmos 0642

(024)	Cosmos 0643

(024)	Cosmos 0644

(024)	Cosmos 0645

(024)	Cosmos 0646

(024)	Cosmos 0647

(024)	Cosmos 0648

Molnya 2-09

Molnya 2-10

(072)	Cosmos 0677

(072)	Cosmos 0678

(072)	Cosmos 0679

(072)	Cosmos 0680

(072)	Cosmos 0681

(072)	Cosmos 0682

(072)	Cosmos 0683

(072)	Cosmos 0684

Molnya 1-28

(089)	Oscar 07

Molnya 3-01

Molnya 2-11

1975

Molnya 2-12

(016)	Cosmos 0711

(016)	Cosmos 0712

(016)	Cosmos 0713

(016)	Cosmos 0714

(016)	Cosmos 0715

(016)	Cosmos 0716

(016)	Cosmos 0717

(016)	Cosmos 0718

SDS 1

Molnya 3-02

Molnya 1-29

(045)	Cosmos 0732

(045)	Cosmos 0733

(045)	Cosmos 0734

(045)	Cosmos 0735

(045)	Cosmos 0736

(045)	Cosmos 0737

(045)	Cosmos 0738

(045)	Cosmos 0739

Molnya 1-30

Molnya 2-13

Molnya 1-31

Molnya 2-14

Cosmos 761

Cosmos 762

Cosmos 763

Cosmos 764

Cosmos 765

Cosmos 766

Cosmos 767

Cosmos 768

Cosmos 773

Molnya 3-03

Cosmos 783

Molnya 2-15

Molnya 3-04

1976

Molnya 1-32

Cosmos 791

Cosmos 792

Cosmos 793

Cosmos 794

Cosmos 795

Cosmos 796

Cosmos 797

Cosmos 798

Molnya 1-33

Molnya 1-34

Molnya 3-05

SDS 2

Cosmos 825

Cosmos 826

Cosmos 827

Cosmos 828

Cosmos 829

Cosmos 830

Cosmos 831

Cosmos 832

Cosmos 836

Cosmos 841

Molnya 1-35

SDS 3

Cosmos 858

Molnya 2-16

Cosmos 871

Cosmos 872

Cosmos 873

Cosmos 874

Cosmos 875

Cosmos 876

Cosmos 877

Cosmos 878

Molnya 3-06

1977

Molnya 2-17

Molnya 1-36

Molnya 3-07

Molnya 1-37

Cosmos 923

Cosmos 939

Cosmos 940

Cosmos 941

Cosmos 942

Cosmos 943

Cosmos 944

Cosmos 945

Cosmos 946

Molnya 1-38

Molnya 3-08

Cosmos 968

1978

Cosmos 976

Cosmos 977

Cosmos 978

Cosmos 979

Cosmos 980

Cosmos 981

Cosmos 982

Cosmos 983

Molnya 3-09

Cosmos 990

SDS 4

Molnya 1-39

(026)	Oscar 08

Molnya 1-40

Cosmos 1013

Cosmos 1014

Cosmos 1015

Cosmos 1016

Cosmos 1017

Cosmos 1018

Cosmos 1019

Cosmos 1020

Cosmos 1023

Molnya 1-41

SDS 5

Molnya 1-42

Cosmos 1034

Cosmos 1035

Cosmos 1036

Cosmos 1037

Cosmos 1038

Cosmos 1039

Cosmos 1040

Cosmos 1041

Molnya 3-10

Cosmos 1048

Cosmos 1051

Cosmos 1052

Cosmos 1053

Cosmos 1054

Cosmos 1055

Cosmos 1056

Cosmos 1057

Cosmos 1058

1979

Molnya 3-11

Cosmos 1081

Cosmos 1082

Cosmos 1083

Cosmos 1084

Cosmos 1085

Cosmos 1086

Cosmos 1087

Cosmos 1088

Molnya 1-43

Molnya 3-12

Cosmos 1110

Molnya 1-44

Cosmos 1125

Cosmos 1130

Cosmos 1131

Cosmos 1132

Cosmos 1133

Cosmos 1134

Cosmos 1135

Cosmos 1136

Cosmos 1137

Cosmos 1140

Molnya 1-45

1980

Molnya 1-46

Cosmos 1156

Cosmos 1157

Cosmos 1158

Cosmos 1159

Cosmos 1160

Cosmos 1161

Cosmos 1162

Cosmos 1163

Cosmos 1175

Molnya 1-47

Cosmos 1190

Cosmos 1192

Cosmos 1193

Cosmos 1194

Cosmos 1195

Cosmos 1196

Cosmos 1197

Cosmos 1198

Cosmos 1199

Molnya 3-13

Molnya 1-48

SDS 6

Cosmos 1228

Cosmos 1229

Cosmos 1230

Cosmos 1231

Cosmos 1232

Cosmos 1233

Cosmos 1234

Cosmos 1235

1981

Molnya 3-14

Molnya 1-49

Cosmos 1250

Cosmos 1251

Cosmos 1252

Cosmos 1253

Cosmos 1254

Cosmos 1255

Cosmos 1256

Cosmos 1257

Molnya 3-15

SDS 7

Cosmos 1269

Molnya 3-16

Molnya 1-50

Cosmos 1287

Cosmos 1288

Cosmos 1289

Cosmos 1290

Cosmos 1291

Cosmos 1292

Cosmos 1293

Cosmos 1294

Cosmos 1302

Cosmos 1305

(100)	Uosat 1

Molnya 3-17

Cosmos 1320

Cosmos 1321

Cosmos 1322

Cosmos 1323

Cosmos 1324

Cosmos 1325

Cosmos 1326

Cosmos 1327

Molnya 1-51

Molnya 1-52

Cosmos 1331

1982

Molnya 1-53

Molnya 3-18

Cosmos 1354

Cosmos 1357

Cosmos 1358

Cosmos 1359

Cosmos 1360

Cosmos 1361

Cosmos 1362

Cosmos 1363

Cosmos 1364

Molnya 1-54

Cosmos 1371

Molnya 1-55

Cosmos 1388

Cosmos 1389

Cosmos 1390

Cosmos 1391

Cosmos 1392

Cosmos 1393

Cosmos 1394

Cosmos 1395

Molnya 1-55

Molnya 3-19

Cosmos 1420

1983

Cosmos 1429

Cosmos 1430

Cosmos 1431

Cosmos 1432

Cosmos 1433

Cosmos 1434

Cosmos 1435

Cosmos 1436

Molnya 3-20

Molnya 1-56

Molnya 1-57

Cosmos 1452

(058)	Oscar 10

Cosmos 1473

Cosmos 1474

Cosmos 1475

Cosmos 1476

Cosmos 1477

Cosmos 1478

Cosmos 1479

Cosmos 1480

Molnya 1-58

SDS 8

Cosmos1486

Molnya 3-21

Cosmos 1503

Molnya 1-59

Molnya 3-22

1984

Cosmos 1522

Cosmos 1523

Cosmos 1524

Cosmos 1525

Cosmos 1526

Cosmos 1527

Cosmos 1528

Cosmos 1529

Cosmos 1538

(021)	Uosat 2

Molnya 1-60

Cosmos 1559

Cosmos 1560

Cosmos 1561

Cosmos 1562

Cosmos 1563

Cosmos 1564

Cosmos 1565

Cosmos 1566

Cosmos 1570

Molnya 1-61

Molnya 1-62

SDS 9

Molnya 1-63

1985

Cosmos 1617

Cosmos 1618

Cosmos 1619

Cosmos 1620

Cosmos 1621

Cosmos 1622

Molnya 3-23

Cosmos 1624

SDS 10

Cosmos 1635

Cosmos 1636

Cosmos 1637

Cosmos 1638

Cosmos 1639

Cosmos 1640

Cosmos 1641

Cosmos 1642

Molnya 3-24

Molnya 3-25

Molnya 1-64

Cosmos 1680

Molnya 3-26

Molnya 1-65

Molnya 1-66

Molnya 3-27

1986

Cosmos 1616

Cosmos 1617

Cosmos 1618

Cosmos 1619

Cosmos 1620

Cosmos 1621

Cosmos 1622

Cosmos 1623

Cosmos 1741

Molnya 3-28

Molnya 3-29

Cosmos 1763

Molnya 1-67

Cosmos 1770

(061)	Fuji 1A

Molnya 1-68

Molnya 3-30

Molnya 1-69

Cosmos 1794

Cosmos 1795

Cosmos 1796

Cosmos 1797

Cosmos 1798

Cosmos 1799

Cosmos 1800

Cosmos 1801

Molnya 1-70

1987

Cosmos 1814

Molnya 3-31

SDS 11

Cosmos 1827

Cosmos 1828

Cosmos 1829

Cosmos 1830

Cosmos 1831

Cosmos 1832

(049)	Cosmos 1850

(051)	Cosmos 1852

(051)	Cosmos 1853

(051)	Cosmos 1854

(051)	Cosmos 1855

(051)	Cosmos 1856

(051)	Cosmos 1857

(051)	Cosmos 1858

(051)	Cosmos 1859

Cosmos 1875

Cosmos 1876

Cosmos 1877

Cosmos 1878

Cosmos 1879

Cosmos 1880

Cosmos 1898

1988

Cosmos 1909

Cosmos 1910

Cosmos 1911

Cosmos 1911

Cosmos 1912

Cosmos 1913

Cosmos 1914

(016)	Cosmos 1924

(016)	Cosmos 1925

(016)	Cosmos 1926

(016)	Cosmos 1927

(016)	Cosmos 1928

(016)	Cosmos 1929

(016)	Cosmos 1930

(016)	Cosmos 1931

(017)	Molnya 1-71

(022)	Molnya 1-72

Cosmos 1937

Molnya 3-32

(051)	Oscar 13

Cosmos 1954

Molnya 1-73

Molnya 3-33

SDS 12

(112)	Molnya 3-34

(115)	Molnya 1-74

1989

(005)	Cosmos 1992

(009)	Cosmos 1994

(009)	Cosmos 1995

(009)	Cosmos 1996

(009)	Cosmos 1997

(009)	Cosmos 1998

(009)	Cosmos 1999

Molnya 1-75

(025)	Cosmos 2008

(025)	Cosmos 2009

(025)	Cosmos 2010

(025)	Cosmos 2011

(025)	Cosmos 2012

(025)	Cosmos 2013

(025)	Cosmos 2014

(025)	Cosmos 2015

(043)	Molnya 3-35

(074)	Cosmos 2038

(074)	Cosmos 2039

(074)	Cosmos 2040

(074)	Cosmos 2041

(074)	Cosmos 2042

(074)	Cosmos 2043

Molnya 1-76

(094)	Molnya 3-36

1990

(005)	Uosat 3

(005)	Uosat 4

(005)	Pacsat

(005)	Dove

(005)	Webersat

(005)	Lusat

(006)	Molnya 3-37

(013)	Fuji 1B

(029)	Cosmos 2064

(029)	Cosmos 2065

(029)	Cosmos 2066

(029)	Cosmos 2067

(029)	Cosmos 2068

(029)	Cosmos 2069

(029)	Cosmos 2070

(029)	Cosmos 2071

Molnya 1-77

Molnya 3-38

Cosmos 2090

Cosmos 2091

Cosmos 2092

Cosmos 2093

Cosmos 2094

Cosmos 2095

Molnya 1-78

Molnya 3-39

Molnya 1-79

(111)	Cosmos 2112

Cosmos 2114

Cosmos 2115

Cosmos 2116

Cosmos 2117

Cosmos 2118

Cosmos 2119

1991

(006)	Informator

Cosmos 2125

Cosmos 2126

Cosmos 2127

Cosmos 2128

Cosmos 2129

Cosmos 2130

Cosmos 2131

Cosmos 2132

Molnya 1-80

Molnya 3-40

Cosmos 2143

Cosmos 2144

Cosmos 2145

Cosmos 2146

Cosmos 2147

Cosmos 2148

Cosmos 2150

Molnya 1-81

(050)	Uosat 5

(050)	Orbcomm X

Molnya 1-82

Molnya 3-41

Cosmos 2157

Cosmos 2158

Cosmos 2159

Cosmos 2160

Cosmos 2161

Cosmos 2162

Cosmos 2165

Cosmos 2166

Cosmos 2167

Cosmos 2168

Cosmos 2169

Cosmos 2170

1992

Molnya 1-83

Cosmos 2187

Cosmos 2188

Cosmos 2189

Cosmos 2190

Cosmos 2191

Cosmos 2192

Cosmos 2193

Cosmos 2194

Cosmos 2197

Cosmos 2198

Cosmos 2199

Cosmos 2200

Cosmos 2201

Cosmos 2202

Molnya 1-84

(052)	Kitsat A

Cosmos 2208

(067)	Molnya 3-42

Cosmos 2211

Cosmos 2212

Cosmos 2213

Cosmos 2214

Cosmos 2215

Cosmos 2216

Molnya 3-43

1993

Molnya 1-85

(009)	Orbcom XP 1

Molnya 3-44

Cosmos 2244

Cosmos 2245

Cosmos 2246

Cosmos 2247

Cosmos 2248

Cosmos 2249

Cosmos 2250

(035)	Molnya 1-86

Cosmos 2251

Cosmos 2252

Cosmos 2253

Cosmos 2254

Cosmos 2255

Cosmos 2256

Cosmos 2257

(055)	Temisat

Molnya 3-45

(061)	Eyesat

(061)	Itamsat

(061)	Healthsat

(061)	Kitsat B

(061)	Posat

Molnya 1-87

1994

(051)	Molnya 3-46

(081)	Molnya 1-88

(085)	RS 15

1995

(002)	Faisat

(017)	Orbcomm FM 1

(017)	Orbcomm FM 2


Telecommunications geostationary satellites
 Geostationary telecommunication satellites

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)	Molnya 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

(097)	Cosmos 0775

(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

(009)	DSCS 3-02

(016)	Raduga 14

(022)	Cosmos 1540

(023)	Intelsat 508

(028)	Ekran 12

(031)	Cosmos 1546

(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)	Brazilsat A1

(016)	Cosmos 1629

(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)	Aussat A1

(076)	ASC 1

(076)	Leasat 4

(087)	Intelsat 512

(092)	DSCS 3-03

(092)	DSCS 3-04

(102)	Cosmos 1700

(107)	Raduga 17

(109)	Morelos 2

(109)	Aussat A2

(109)	Satcom K2

1986

(003)	Satcom K1

(007)	Raduga 18

(010)	Dong Fang Hong 18

(016)	Yuri 2B

(026)	Gstar 2

(026)	Brazilsat 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)	Aussat A3

(078)	Eutelsat 1F4

(084)	Cosmos 1888

(091)	Cosmos 1894

(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

(035)	DSCS 3-05

(041)	Superbird A1

(041)	DFS 1

(048)	Raduga 1-1

(052)	Gorizont 18

(053)	Olympus

(062)	Tvsat 2

(067)	BSB 1

(069)	DSCS 3-06

(069)	DSCS 3-07

(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 3-08

(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 3-09

(041)	Insat 2A

(041)	Eutelsat 2F4

(043)	Gorizont 26

(054)	Aussat 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 3-10

(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 3-11

(076)	Nato 4B

(077)	Telstar 401

(078)	DBS 1

(078)	Thaicom 1

1994

(002)	GALS 1

(008)	Raduga 1-3

(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)	Brazilsat B1

(049)	Turksat 1B

(055)	Aussat B3

(064)	Intelsat 703

(065)	Solidaridad 2

(065)	Thaicom 2

(067)	Express 01

(070)	Astra 1D

(079)	Orion 1

(080)	Dong Fang Hong 41

(082)	Luch

(087)	Raduga 32

1995

(001)	Intelsat 704

(003)	UHF 4

(013)	Intelsat 705

(016)	Brazilsat B2

(016)	Hotbird 1

(019)	AMSC 1

(023)	Intelsat 706


 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

1975

Cosmos 726

Cosmos 729

Cosmos 755

Triad 2 (TIP 2)

Cosmos 778

1976

Cosmos 789

Cosmos 800

Cosmos 807

Cosmos 823

Cosmos 842

Cosmos 846

Triad 3 (TIP 3)

Cosmos 864

Cosmos 883

Cosmos 887

1977

Cosmos 890

Cosmos 894

Cosmos 911

Cosmos 926

Cosmos 928

Cosmos 951

NNSS 30 110

Cosmos 962

Cosmos 971

1978

Cosmos 985

(020)	GPS BI-01

Cosmos 991

Cosmos 994

Cosmos 996

(034)	Cosmos 1000

(047)	GPS BI-02

Cosmos 1011

Cosmos 1027

(093)	GPS BI-03

(112)	GPS BI-04

Cosmos 1064

1979

Cosmos 1072

Cosmos 1089

Cosmos 1091

Cosmos 1092

Cosmos 1104

Cosmos 1141

1980

Cosmos 1150

Cosmos 1153

(011)	GPS BI-05

Cosmos 1168

(032)	GPS BI-06

Cosmos 1181

Cosmos 1225

Cosmos 1226

1981

Cosmos 1244

(044)	Nova 1

Cosmos 1275

Cosmos 1295

Cosmos 1304

Cosmos 1308

1982

Cosmos 1333

Cosmos 1339

Cosmos 1344

Cosmos 1349

Cosmos 1380

Cosmos 1383

Cosmos 1386

Cosmos 1413

Cosmos 1414

Cosmos 1415

Cosmos 1417

1983

Cosmos 1428

Cosmos 1447

Cosmos 1448

Cosmos 1459

Cosmos 1464

(072)	GPS BI-08

Cosmos 1490

Cosmos 1491

Cosmos 1492

Cosmos 1506

Cosmos 1513

Cosmos 1519

Cosmos 1520

Cosmos 1521

1984

Cosmos 1531

Cosmos 1535

Cosmos 1550

Cosmos 1553

Cosmos 1554

Cosmos 1555

Cosmos 1556

(059)	GPS BI-09

Cosmos 1574

Cosmos 1577

Cosmos 1593

Cosmos 1594

Cosmos 1595

(097)	GPS BI-10

Cosmos 1598

Cosmos 1605

(110)	Nova 2

Cosmos 1610

1985

Cosmos 1627

Cosmos 1634

Cosmos 1650

Cosmos 1651

Cosmos 1652

Cosmos 1655

(095)	GPS BI-11

SOOS ? Transit 19 (SOOS 240 - 300)

SOOS ?Transit 20

Cosmos 1704

Cosmos 1709

Cosmos 1710

Cosmos 1711

Cosmos 1712

1986

Cosmos 1725

Cosmos 1727

Cosmos 1745

Cosmos 1759

Cosmos 1778

Cosmos 1779

Cosmos 1780

Cosmos 1791

Polar Bear (17070)

Cosmos 1802

Cosmos 1808

1987

Cosmos 1816

Cosmos 1821

Cosmos 1838

Cosmos 1839

Cosmos 1840

(054)	Cosmos 1861

Cosmos 1864

Cosmos 1883

Cosmos 1884

Cosmos 1885

SOOS 270 (Oscar 27)

SOOS 290 (Oscar 29)

Cosmos 1891

Cosmos 1904

1988

Cosmos 1917

Cosmos 1918

Cosmos 1919

(023)	Cosmos 1934

SOOS 230 (Oscar 23)

SOOS 320 (Oscar 32)

Cosmos 1946

Cosmos 1947

Cosmos 1948

(052)	Nova 3

(062)	Cosmos 1959

SOOS 250 (Oscar 25)

SOOS 310 (Oscar 31)

(085)	Cosmos 1970

(085)	Cosmos 1971

(085)	Cosmos 1972

1989

(001)	Cosmos 1987

(001)	Cosmos 1988

(001)	Cosmos 1989

(013)	GPS BII-01

(017)	Cosmos 2004

(028)	Cosmos 2016

(039)	Cosmos 2022

(039)	Cosmos 2023

(039)	Cosmos 2024

(042)	Cosmos 2026

(044)	GPS BII-02

(050)	Nadejda 1

(059)	Cosmos 2034

(064)	GPS BII-03

(085)	GPS BII-04

(097)	GPS BII-05

1990

(008)	GPS BII-06

(017)	Nadejda 2

(023)	Cosmos 2061

(025)	GPS BII-07

(036)	Cosmos 2074

(045)	Cosmos 2079

(045)	Cosmos 2080

(045)	Cosmos 2081

(068)	GPS BII-08

Cosmos 2100

(088)	GPS BII-09

(103)	GPS BIIA-10

(110)	Cosmos 2109

(110)	Cosmos 2110

(110)	Cosmos 2111

1991

Cosmos 2123

Cosmos 2135

(019)	Nadejda 3

(025)	Cosmos 2139

(025)	Cosmos 2140

(025)	Cosmos 2141

(047)	GPS BIIA-11

Cosmos 2154

Cosmos 2173

1992

(005)	Cosmos 2177

(005)	Cosmos 2178

(005)	Cosmos 2179

Cosmos 2180

Cosmos 2181

(009)	GPS BIIA-12

(019)	GPS BIIA-13

Cosmos 2184

Cosmos 2195

(039)	GPS BIIA-14

(047)	Cosmos 2204

(047)	Cosmos 2205

(047)	Cosmos 2206

(058)	GPS BIIA-15

Cosmos 2218

(079)	GPS BIIA-16

(089)	GPS BIIA-17

1993

Cosmos 2230

(007)	GPS BIIA-18

Cosmos 2233

(010)	Cosmos 2234

(010)	Cosmos 2235

(010)	Cosmos 2236

(017)	GPS BIIA-19

Cosmos 2239

(032)	GPS BIIA-20

(042)	GPS BIIA-21

(054)	GPS BIIA-22

(068)	GPS BIIA-23

Cosmos 2266

1994

(016)	GPS BIIA-24

(021)	Cosmos 2275

(021)	Cosmos 2276

(021)	Cosmos 2277

(041)	Nadejda 4

(050)	Cosmos 2287

(050)	Cosmos 2288

(050)	Cosmos 2289

(076)	Cosmos 2294

(076)	Cosmos 2295

(076)	Cosmos 2296

1995

(009)	Cosmos 2307

(009)	Cosmos 2308

(009)	Cosmos 2309

(012)	Cosmos 2310