?_Kcr$SJl|5#1V0.41.001-xxx for ******************************2Copyright 1993-1998 Tag's Broadcasting ServicesBrowseButtons()PCB("A_propos", "&About...", "JI(`satellit.hlp', `Tags_Broadcasting_Services')")ZmainO mainOThe Satellite Encyclopedia %m##O,l/P_;)z4dd|CONTEXTZ|CTXOMAPXW|FONTRW|KWBTREEW|KWDATAXW|KWMAPW|SYSTEM|TOPIC|TTLBTREEZ|bm0[|bm1[|bm10`\|bm117]|bm12%]|bm13EG]|bm14i]|bm15U]|bm160]|bm17]|bm18O]|bm19^|bm2[|bm20z8^|bm21x^|bm22j^|bm23#I_|bm24_|bm25`|bm26o`|bm27`|bm284a|bm29a|bm3[|bm30/a|bm31)Kb|bm32b|bm33Sc|bm349`c|bm35c|bm36Nd|bm37d|bm38@e|bm39e|bm4\|bm40ef|bm41f|bm42$g|bm43ug|bm44g|bm45jh|bm46+h|bm47Zi|bm48i|bm49CNj|bm5G6\|bm50j|bm51>k|bm52lk|bm53/l|bm54Ψl|bm55 m|bm56Bm|bm57n|bm58Rn|bm59ao|bm6X\|bm60o|bm61o|bm62op|bm63Bp|bm64b_q|bm65Rq|bm66POr|bm67 r|bm68as|bm69Pt|bm7{z\|bm70u|bm71u|bm72Cv|bm73xv|bm74v|bm75`w|bm76ow|bm77w|bm78 x|bm79Yx|bm8s\|bm80yx|bm81y|bm82Dy|bm83g z|bm84z|bm85z|bm86{|bm87B||bm88)||bm89J]}|bm9k\|bm90~~gindex_]MWTMW 1=1W=C # @page intentionally left blank&=# ; 1dMain indexF'( <ȘThe Satellite Encyclopediasp ց )C "H̀"N " "py؀")"/ۀ"+Ip"pUՀ" %e&" devoted to unmanned artificial Earth satellites S)'* $RcHelp: how to use this encyclopedia?11WrT+r) "VȠ$To view this page you need to register&# 1r1zI"' Dpage intentionally left blankM_1I)_W Alphabetical satellite indexY$5 :JNJ"  Alphabetical satellite index{_\) "+IpThis index does not contain future satellites or programs; use the launch schedule or the search tool to access those.($ A*\ U KUisεSϵSеS˜klr& b "H6I63 㖨ԜZ=n YSS ?QQ@QQACTSAdeos 1AEM 1AEM 2AEM 3Program: AerosAeros 1Aeros 2AjisaiAlexisProgram: AlouetteAlouette 1Alouette 2Amos 1Program: AMPTEAMPTE CCEAMPTE IRMAMPTE UKSProgram: AMSAMSC 1Program: AnikAnik A1Anik A2* UAQQjQQQQQQQQQQQQQQQQWRD|KUc&SttXXb i"鉂 b "鉂u䉂4鉂5鉂6鉂7鉂Anik A3Anik B1Anik C1Anik C2Anik C3Anik D1Anik D2Anik E1Anik E2Anna 1BANSApexAppleProgram: ApstarApstar 1Apstar 1AApstar 2Apstar 2RProgram: ArabsatArabsat 1AArabsat 1BArabsat 1CArabsat 1D1 c8鉂_鉂`鉂wڜhڜd$te$tf$tg$th$ti$t:GZSiSiS%kkk;S ܜArabsat 1EArabsat 2AArabsat 2BProgram: ArgosProgram: ArielAriel 1Ariel 2Ariel 3Ariel 4Ariel 5Ariel 6ArsneAryabhataProgram: ASCASC 1ASC 2Program: AsiasatAsiasat 1Asiasat 2Asiasat 3AstrixProgram: Astra% K(~(~(~(~(~)~)~ ~ ܜ"MZSSSSSRKUqe2y`3y`Astra 1AAstra 1BAstra 1CAstra 1DAstra 1EAstra 1FAstra 1GAstrid 1Program: AstroAstro AAstro BAstro CAstro DAstronProgram: ATSATS 1ATS 3ATS 5ATS 6AuraProgram: AuroleAurole 1Aurole 2o g 4y`[Y]]✉KUAurole 3Program: AuroraAurora 1Aurora 2Program: AyameAyame 1Ayame 2Azur( $ B@ J(ce艂e艂0pCDb􉂃b􉂃"c􉂃#c􉂃쉂gWR􉂃S􉂃JaSSSBadr AProgram: BhaskaraBhaskara 1Bhaskara 2Program: BionBion 11Program: BrasilsatBrasi@lsat A1Brasilsat A2Brasilsat B1Brasilsat B2BremsatProgram: BsatBsat 1ABsat 1BProgram: BSBBSB 1BSB 2(@$ C .@B ]L M@ )eSscTtcTucTvcT97D9H H fNj)ቂvMU\doXLXYLXZLX[LX^~NUXTqiCakrawarta 1CastorProgram: CatCat 1Cat 2Cat 3Cat 4Program: CelestisCelestis 1Celestis 2CeriseChinastar 1COBEProgram: Comstar Comstar 1 Comstar 2 Comstar 3 Comstar 4 Coronas 1Corsa BCos B Program: CosmosB@D |ځف?فففEځGځc聟BCDEFGsj}~Cosmos 0001Cosmos 0100Cosmos 0110Cosmos 0122Cosmos 0144Cosmos 0169Cosmos 0186Cosmos 0188Cosmos 0368Cosmos 0444Cosmos 0445Cosmos 0446Cosmos 0447Cosmos 0448Cosmos 0449Cosmos 0450Cosmos 0451Cosmos 0500Cosmos 0504Cosmos 0505BBG |+,XOPQRSTUVWCosmos 0506Cosmos 0507Cosmos 0508Cosmos 0509Cosmos 0510Cosmos 0511Cosmos 0588Cosmos 0589Cosmos 0590Cosmos 0591Cosmos 0592Cosmos 0593Cosmos 0594Cosmos 0595Cosmos 0596Cosmos 0597Cosmos 0598Cosmos 0599Cosmos 0600Cosmos 0605BDI |89:f]^_`ijkCosmos 0637Cosmos 0641Cosmos 0642Cosmos 0643Cosmos 0644Cosmos 0645Cosmos 0646Cosmos 0647Cosmos 0648Cosmos 0677Cosmos 0678Cosmos 0679Cosmos 0680Cosmos 0681Cosmos 0682Cosmos 0683Cosmos 0684Cosmos 0711Cosmos 0712Cosmos 0713BG8K |lmnopoq6u0wD0wCosmos 0714Cosmos 0715Cosmos 0716Cosmos 0717Cosmos 0718Cosmos 0732Cosmos 0733Cosmos 0734Cosmos 0735Cosmos 0736Cosmos 0737Cosmos 0738Cosmos 0739Cosmos 0775Cosmos 0777Cosmos 0782Cosmos 0936Cosmos 0954Cosmos 1000Cosmos 1094BIQM |v6vwwV wR w8www!w,!w#!w$!w%!w&!w'!w(!w)!w*!w+!wCosmos 1267Cosmos 1366Cosmos 1402Cosmos 1443Cosmos 1540Cosmos 1546Cosmos 1629Cosmos 1700Cosmos 1738Cosmos 1849Cosmos 1850Cosmos 1851Cosmos 1852Cosmos 1853Cosmos 1854Cosmos 1855Cosmos 1856Cosmos 1857Cosmos 1858Cosmos 1859B8KjO |W!wN!w!w!w!w!w!w'w'w'w'w'w'w'w(w(w(w(w (w (wCosmos 1860Cosmos 1861Cosmos 1870Cosmos 1887Cosmos 1888Cosmos 1894Cosmos 1897Cosmos 1923Cosmos 1924Cosmos 1925Cosmos 1926Cosmos 1927Cosmos 1928Cosmos 1929Cosmos 1930Cosmos 1931Cosmos 1932Cosmos 1933Cosmos 1934Cosmos 1935BQM |b(wc(wd(w(w(w(w(w(w(w(w(w(w(wjO(w(w(w(w(w(w(wCosmos 1957Cosmos 1958Cosmos 1959Cosmos 1960Cosmos 1961Cosmos 1962Cosmos 1963Cosmos 1964Cosmos 1965Cosmos 1966Cosmos 1967Cosmos 1968Cosmos 1969Cosmos 1970Cosmos 1971Cosmos 1972Cosmos 1973Cosmos 1974Cosmos 1975Cosmos 1976BjO |(w(w(w(w(w(w(w(w(w(w(w(w)w)w )w )w )w )w )w)wCosmos 1977Cosmos 1978Cosmos 1979Cosmos 1980Cosmos 1982Cosmos 1983Cosmos 1984Cosmos 1985Cosmos 1986Cosmos 1987Cosmos 1988Cosmos 1989Cosmos 1990Cosmos 1991Cosmos 1992Cosmos 1993Cosmos 1994Cosmos 1995Cosmos 1996Cosmos 1997B |)w)wgxfxgxgxgxgxgxgxgxgxex|ex}ex~exexexexexCosmos 1998Cosmos 1999Cosmos 2000Cosmos 2001Cosmos 2002Cosmos 2003Cosmos 2004Cosmos 2005Cosmos 2006Cosmos 2007Cosmos 2008Cosmos 2009Cosmos 2010Cosmos 2011Cosmos 2012Cosmos 2013Cosmos 2014Cosmos 2015Cosmos 2016Cosmos 2017Bڇ |exexexexexexexexexexexexexexexexexexexexCosmos 2018Cosmos 2019Cosmos 2020Cosmos 2021Cosmos 2022Cosmos 2023Cosmos 2024Cosmos 2025Cosmos 2026Cosmos 2027Cosmos 2028Cosmos 2029Cosmos 2030Cosmos 2031Cosmos 2032Cosmos 2033Cosmos 2034Cosmos 2035Cosmos 2036Cosmos 2037B |exexfxexexexfxfxfxfxfx1fx(fx)fx+fx,fx-fx.fx/fx0fxCosmos 2038Cosmos 2039Cosmos 2040Cosmos 2041Cosmos 2042Cosmos 2043Cosmos 2044Cosmos 2045Cosmos 2047Cosmos 2048Cosmos 2049Cosmos 2050Cosmos 2051Cosmos 2052Cosmos 2054Cosmos 2055Cosmos 2056Cosmos 2057Cosmos 2058Cosmos 2059Bڇ |SfxTfxUfxVfxWfxXfxYfxZfx[fxfx~fxfxfxfxfxfxfxfx&x&xCosmos 2061Cosmos 2062Cosmos 2063Cosmos 2064Cosmos 2065Cosmos 2066Cosmos 2067Cosmos 2068Cosmos 2069Cosmos 2070Cosmos 2071Cosmos 2072Cosmos 2073Cosmos 2074Cosmos 2079Cosmos 2080Cosmos 2081Cosmos 2085Cosmos 2100Cosmos 2107B% |&x&x$x{$x|$x$x$x$x%x$x$x~%x%x%x%x%x:-x;-x<-x?-xCosmos 2108Cosmos 2109Cosmos 2110Cosmos 2111Cosmos 2112Cosmos 2123Cosmos 2133Cosmos 2139Cosmos 2140Cosmos 2141Cosmos 2142Cosmos 2172Cosmos 2173Cosmos 2177Cosmos 2178Cosmos 2179Cosmos 2204Cosmos 2205Cosmos 2206Cosmos 2209B J |+x+x+x+x+x+x+x,x ,x ,x ,x ,x,x,x,x,x,x>,x5,x6,xCosmos 2218Cosmos 2219Cosmos 2220Cosmos 2221Cosmos 2222Cosmos 2223Cosmos 2224Cosmos 2230Cosmos 2231Cosmos 2232Cosmos 2233Cosmos 2234Cosmos 2235Cosmos 2236Cosmos 2237Cosmos 2238%JCosmos 2239Cosmos 2240Cosmos 2241Cosmos 2242B%c |7,x8,x9,x:,x;,x<,x=,xi,x`,xa,xb,xc,xd,xe,xf,xg,xh,x,x,x,xCosmos 2243Cosmos 2244Cosmos 2245Cosmos 2246Cosmos 2247Cosmos 2248Cosmos 2249Cosmos 2250Cosmos 2251Cosmos 2252Cosmos 2253Cosmos 2254Cosmos 2255Cosmos 2256Cosmos 2257Cosmos 2258Cosmos 2259Cosmos 2260Cosmos 2261Cosmos 2262BJ| |,x,x,x,x,x,x,x,x,x,x,x,x,x,x,x,x,x,x,x,xCosmos 2263Cosmos 2264Cosmos 2265Cosmos 2266Cosmos 2267Cosmos 2268Cosmos 2269Cosmos 2270Cosmos 2271Cosmos 2272Cosmos 2273Cosmos 2274Cosmos 2275Cosmos 2276Cosmos 2277Cosmos 2278Cosmos 2279Cosmos 2280Cosmos 2281Cosmos 2282Bc |,x,x,x,x,x,x,x-x -x -x-x-x-x-x-x-x-xy4xp4xq4xCosmos 2283Cosmos 2284Cosmos 2285Cosmos 2286Cosmos 2287Cosmos 2288Cosmos 2289Cosmos 2290Cosmos 2291Cosmos 2292Cosmos 2293Cosmos 2294Cosmos 2295Cosmos 2296Cosmos 2297Cosmos 2298Cosmos 2299Cosmos 2300Cosmos 2301Cosmos 2302B| |r4xs4xt4xu4xv4xw4xx4x2x2x2x2x2x2x2x2x2x2x!3x3x3xCosmos 2303Cosmos 2304Cosmos 2305Cosmos 2306Cosmos 2307Cosmos 2308Cosmos 2309Cosmos 2310Cosmos 2311Cosmos 2312Cosmos 2313Cosmos 2314Cosmos 2315Cosmos 2316Cosmos 2317Cosmos 2318Cosmos 2319Cosmos 2320Cosmos 2321Cosmos 2322B |3x3x3x3x3x3x 3xL3xC3xD3xE3xF3xG3xH3xI3xJ3xK3xw3xn3xo3xCosmos 2323Cosmos 2324Cosmos 2325Cosmos 2326Cosmos 2327Cosmos 2328Cosmos 2329Cosmos 2330Cosmos 2331Cosmos 2332Cosmos 2333Cosmos 2334Cosmos 2335Cosmos 2336Cosmos 2337Cosmos 2338Cosmos 2339Cosmos 2340Cosmos 2341Cosmos 2342P yp3xq3xr3xs3xt3xu3xv3x3x3xɮ6DySSCosmos 2343Cosmos 2344Cosmos 2345Cosmos 2346Cosmos 2347Cosmos 2348Cosmos 2349Cosmos 2350Cosmos 2351Coupon 1Courier 1BCTA CTS (?$ D-B z[ElS~9T9T〽9T[@=T0`ʗ>T˗>T̗>T 㦼㧼&>QS =9㧢щ㫢щ㬢щProgram: DashProgram: DBSDBS 1DBS 2DBS 3DeltaDenpaProgram: DFS KopernikusDFS 1DFS 2DFS 3Program: DiadmeDiadme 1Diadme 2Dial-WikaDiapasonProgram: DiscovererProgram: DMSPDMSP B5D2-3DMSP B5D2-7DMSP B5D2-8a?a 2㭢щmS!(v&"(v&#(v&$(v&%(v&&(v&'(v&((v&)(v&&v&&v&&v&&v&&v&DMSP B5D2-9Program: Dong Fang HongDong Fang Hong 01Dong Fang Hong 02Dong Fang Hong 03Dong Fang Hong 04Dong Fang Hong 05Dong Fang Hong 06Dong Fang Hong 07Dong Fang Hong 08Dong Fang Hong 09Dong Fang Hong 10DBaong Fang Hong 11Dong Fang Hong 12Dong Fang Hong 13Dong Fang Hong 14bBv 4&v&&v&&v&&v&&v&&v&&v&&v&&v&&v&&v&&v&&v&&v&&v&&v&Dong Fang Hong 15Dong Fang Hong 16Dong Fang Hong 17Dong Fang Hong 18Dong Fang Hong 19Dong Fang Hong 20Dong Fang Hong 21Dong Fang Hong 22Dong Fang Hong 23Dong Fang Hong 24Dong Fang Hong 25Dong Fang Hong 26Dong Fang Hong 30Dong Fang Hong 31Dong Fang Hong 32Dong Fang Hong 33Ma} B&v&&v&&v&&v&&v&&v&('v&'v& 'v&!'v&"'v&#'v&eOUąy,dMz,dM{,dMDong Fang Hong 34Dong Fang Hong 35Dong Fang Hong 36Dong Fang Hong 37Dong Fang Hong 38Dong Fang Hong 39Dong Fang Hong 40Dong Fang Hong 41Dong Fang Hong 42Dong Fang Hong 43Dong Fang Hong 44Dong Fang Hong 45DoveProgram: DSCSDSCS 2-01DSCS 2-02DSCS 2-03(v Q|,dM},dM~,dM,dM,dM*dM*dM*dM*dM*dM*dM ceM ceMceMceMceMceMceMceMceMaeMDSCS 2-04DSCS 2-05DSCS 2-06DSCS 2-07DSCS 2-08DSCS 2-11DSCS 2-12DSCS 2-13DSCS 2-14DSCS 2-15DSCS 2-16DSCS 3-01DSCS 3-02DSCS 3-03DSCS 3-04DSCS 3-05DSCS 3-06DSCS 3-07DSCS 3-08DSCS 3-09DSCS 3-10}~q oS@c鉂c鉂 c鉂 c鉂 c鉂 c鉂Program: DSPDSP F12DSP 3-1DSP 3-2DSP 3-3DSP 3-4DSP 3-5Dynamics Explorer 1Dynamics Explorer 2($ E)~  S^`B㸈LV.MV.R4VR^ZWR^ZXR^ZYR^Z~񢝉eɉeɉeɉeɉeɉeɉeɉeɉeɉxdɉodɉEarly BirdProgram: EchoEcho 1Echo 2Program: EchostarEchostar 1Echostar 2Echostar 3Echostar 4Program: EkranEkran 01Ekran 02Ekran 03Ekran 04Ekran 05Ekran 06Ekran 07Ekran 08Ekran 09Ekran 10Ekran 11 )  SpdɉqdɉrdɉsdɉtdɉudɉvdɉwdɉdɉQL݉JPPU/{MUdPUvS_QT`QTEkran 12Ekran 13Ekran 14Ekran 15Ekran 16Ekran 17Ekran 18Ekran 19Ekran 20Electro 1Program: ElektronElektron 1Elektron 2Elektron 3Elektron 4EoleProgram: EorsatEquator SERBSProgram: ERSERS 1ERS 2   =㯃\㰃\obpbb#11111111111wSㅾTㆾTㇾT㈾T㉾T㊾TESA-Geos 1ESA-Geos 2Program: EsroEsro 1AEsro 1BEsro 2BEsro 4Program: EssaEssa 1Essa 2Essa 3Essa 4Essa 5Essa 6Essa 7Essa 8Essa 9Program: ETSETS 1ETS 2ETS 3ETS 4ETS 5ETS 6;  w㋾TIRH(نچۆ܆݆N}PU!q2q2q2q2r2j牂ETS 7Eureca 1Program: EutelsatEutelsat 1F1Eutelsat 1F2Eutelsat 1F3Eutelsat 1F4Eutelsat 1F5Eutelsat 2F1Eutelsat 2F2Eutelsat 2F3Eutelsat 2F4Eutelsat 2F5EUVEProgram: ExosExos AExos BExos CExos DExosatProgram: ExplorerB B |B```````l`c`d`e`f`g`h`i`j`k````Explorer 01Explorer 03Explorer 04Explorer 06Explorer 07Explorer 08Explorer 09Explorer 10Explorer 11Explorer 12Explorer 13Explorer 14Explorer 15Explorer 16Explorer 17Explorer 18Explorer 19Explorer 20Explorer 21Explorer 22BD |````````````````````Explorer 23Explorer 24Explorer 25Explorer 26Explorer 27Explorer 28Explorer 29Explorer 30Explorer 31Explorer 32Explorer 33Explorer 34Explorer 36Explorer 38Explorer 39Explorer 40Explorer 41Explorer 42Explorer 43Explorer 45~BE `````````-~wJ7J7|{3Explorer 46Explorer 47Explorer 48Explorer 50Explorer 51Explorer 52Explorer 53Explorer 54Explorer 55EXPRESS (German)Program: ExpressExpress 1Express 2Eyesat(DE$ FEEG lǥ #Ra{˝3д%"QU"dɉ2>>ቂ?>ቂ@>ቂA>ቂB>ቂC>ቂD>ቂE>ቂձTGܝeN Program: FaisatFaisat 1Faisat 2VFalcon GoldProgram: FasatFasat AlfaFastFirewheelProgram: FleetsatcomFleetsatcom 1Fleetsatcom 2Fleetsatcom 3Fleetsatcom 4Fleetsatcom 5Fleetsatcom 6Fleetsatcom 7Fleetsatcom 8FortProgram: FotonFoton 09aEHg L L QU1TATO뉂UO뉂J ;Foton 10Foton 11FR 1FrejaProgram: FujiFuji 1AFuji 1BFuji 2(GH$ G*HJ UӉ7up_b㉂-8up9upb㉂:up;up㉂o7U=v>UUЇmՅnՅIntelsat 707Intelsat 708Intelsat 709Intelsat 801Intelsat 802Intelsat 803Intelsat 804Intelsat 806Intelsat KProgram: IntercosmosIntercosmos 01Intercosmos 18Intercosmos Bulgaria 1300Program: IntersputnikIRASProgram: IridiumIridium 04Iridium 05. |]oՅpՅqՅrՅՅՅՅՅՅՅՅՅՅՅՅՅՅՅՅՅIridium 06Iridium 07Iridium 08Iridium 09Iridium 10Iridium 11Iridium 12Iridium 13Iridium 14Iridium 16Iridium 17Iridium 18Iridium 19Iridium 20Iridium 21Iridium 22Iridium 23Iridium 24Iridium 25Iridium 26. |]ՅՅՅFՅ=Յ>Յ?Յ@ՅAՅBՅCՅDՅEՅqՅhՅiՅjՅkՅlՅmՅIridium 27Iridium 28Iridium 29Iridium 30Iridium 31Iridium 32Iridium 33Iridium 34Iridium 35Iridium 36Iridium 37Iridium 38Iridium 39Iridium 40Iridium 41Iridium 42Iridium 43Iridium 44Iridium 45Iridium 46.  |]nՅoՅpՅՅՅՅՅՅՅՅՅՅՅՅՅՅՅՅՅՅIridium 47Iridium 48Iridium 49Iridium 50Iridium 51Iridium 52Iridium 53Iridium 54Iridium 55Iridium 56Iridium 57Iridium 58Iridium 59Iridium 60Iridium 61Iridium 62Iridium 63Iridium 64Iridium 65Iridium 66 % KՅՅՅՅՅՅՅՅՅ㿓SYTYTYTYTYT_T_T~ ֋UTVT֋Iridium 67Iridium 68Iridium 69Iridium 70Iridium 71Iridium 72Iridium 73Iridium 74Iridium 75Program: IRSIRS 1AIRS 1BIRS 1CIRS 1DIRS 1EIRS P2IRS P3IRTProgram: ISEEISEE 1ISEE 2Program: Isisi n TT~voGoGKBOUU~Isis 1Isis 2ISOProgram: ItalsatItalsat 1Italsat 2ItamsatItosIUE($ JZ_ ㆺ2ㇺ2㈺2㉺2㊺2ZProgram: JcsatJcsat 1Jcsat 2Jcsat 3Jcsat 4Jcsat 5JERS 1($ K $  I QdI%'d('dI֐҉X^z҉(҉e܌҉f܌҉g܌҉j܌҉k܌҉l܌҉҉҉҉G.rY Y Program: KHKH 1-2KH 1-5KH 4-01KH 4A-03KH 7-01KH 9-01KH 11-1KH 11-2KH 11-3KH 11-6KH 11-7KH 11-8KH 12-1KH 12-2KH 12-3Program: KitsatKitsat AKitsat BProgram: KoreasatKoreasat 1Koreasat 2 (5$ L 2 A e=Š--->ܝ ɉ ɉɉɉɉɉSIUIU}XUUg!Ag"AgProgram: LacrosseLacrosse 1Lacrosse 2Lacrosse 3Program: LageosLageos 1Lageos 2Program: LandsatLandsat 1Landsat 2Landsat 3Landsat 4Landsat 5Landsat 6Program: LCSLCS 1LCS 4LDEFProgram: LeasatLeasat 1Leasat 2z5 >#Ag$Ag%Ag;S㿶UUU¶UöUĶUƶUǶUUᇏvEomEo ULeasat 3Leasat 4Leasat 5Program: LESLES 1LES 2LES 3LES 4LES 5LES 6LES 8LES 9LewisProgram: LuchLuch 0Luch 1Lusat(A$ M7 o"Zn$aL$M$N$O$P$tYtYF^nڰ_ʴU˴U ݏ7ݏ7ݏ7*Program: MabuhayMabuhay 1Program: MagionMagion 1Magion 2Magion 3Magion 4Magion 5Maqsat BMaqsat HProgram: MarecsMarecs AMarecs B1Marecs B2Program: MarisatMarisat 1Marisat 2Marisat 3Program: MeasatMeasat 1Measat 2? r4+3xA>k>kDu ks k٫ k۫ kܫ k2_ϵaеaѵaҵaӵaԵaյaKtA.Meteor (US)Program: MeteorMeteor 1-01Meteor 1-02Meteor 2-01Meteor 2-21Meteor 3-03Meteor 3-05Meteor 3-06Program: MeteosatMeteosat 1Meteosat 2Meteosat 3Meteosat 4Meteosat 5Meteosat 6Meteosat 7Microlab 1Program: MidasMidas 025  tk.......c-c{AAK&Yu<щjQvVIWHWHWHWIWMidas 03Midas 04Midas 05Midas 06Midas 07Midas 08Midas 09Midas 10Program: MilstarMilstar 1-1Milstar 1-2Program: MinisatMinisat 01MirandaProgram: MolniyaMolniya 1-01Molniya 1-71Molniya 1-72Molniya 1-74Molniya 1-85D  hIWIWIWIW4IWX|YRYSYTYUY{Y}Y~YY〵YふY㘜7ӔMolniya 1-86Molniya 1-87Molniya 1-88Molniya 1-89Molniya 1-90Molniya 2-01Molniya 3-01Molniya 3-34Molniya 3-35Molniya 3-36Molniya 3-37Molniya 3-42Molniya 3-44Molniya 3-45Molniya 3-46Molniya 3-47Molniya 3-48Molniya 1-SProgram: Momo1 N  ?V$W$tz6wFFLw޲xxx㟛oK&VU +VMomo 1AMomo 1BProgram: MorelosMorelos 1Morelos 2MSAT 1Program: MSTIMSTI 1MSTI 2MSTI 3MSXMusatMyojo( v $ N 2N  e4) * .<:R򲟉S򲟉T򲟉U򲟉"%ljS_Euga }b }CdCdCdCdCdCdW􉂃ȉProgram: N StarN Star AN Star BProgram: NadezhdaNadezhda 1Nadezhda 2Nadezhda 3Nadezhda 4Program: NahuelNahuel 1AProgram: NATONato 1Nato 2Nato 3ANato 3BNato 3CNato 3DNato 4ANato 4BNilesat 101Program: Nimbus$v A IQ;CR;CS;C KT;CU;CV;CW;CTɑ܁ {A݁ {ށ {߁ { { { { { {b {Y {Z {[ {\ {Nimbus 1Nimbus 2Nimbus 3Nimbus 3ANimbus 4Nimbus 5Nimbus 6Nimbus 7Program: NOAANOAA 01NOAA 02NOAA 03NOAA 04NOAA 05NOAA 06NOAA 07NOAA 08NOAA 09NOAA 10NOAA 11NOAA 12NOAA 13NOAA 14C 1] {l̑X~X~X~X~X~X~X~X~X~"W~#W~$W~%W~̑www4) NOAA 15NOAA BProgram: NOSSNOSS 01NOSS 02NOSS 03NOSS 04NOSS 05NOSS 06NOSS 07NOSS 08NOSS 09NOSS 12NOSS 13NOSS 14NOSS 15Program: NovaNova 1Nova 2Nova 3Program: N StarN Star A(AC$ O&CE M6S?vV?vV?vV?vV뉢󓋉󓋉󓋉󓋉@ױBױBױBױBױBױBױBױBױBױBProgram: OAOOAO 1OAO 2OAO 3OAO BProgram: OceanOcean 1Ocean 2Ocean 3Ocean 4Program: OderacsOderacs 1AOderacs 1BOderacs 1COderacs 1DOderacs 1EOderacs 1FOderacs 2AOderacs 2BOderacs 2COderacs 2D CG ;ױBױB5ffff٧8S}V}V}V}V}V}V~gOvtމ_____Oderacs 2EOderacs 2FProgram: OffekOffek 1Offek 2Offek 3Offek 4OFOProgram: OGOOGO 1OGO 2OGO 3OGO 4OGO 5OGO 6OhsumiOlympusProgram: OptusOptus A1Optus A2Optus A3Optus B1Optus B2<EI dy_㐫9_P8s:9s::s:;s:s:?s:@s:rZыiZыjZыJe۴R*Optus B3Program: OrbcommOrbcomm XOrbcomm XP 1Orbcomm FM 1Orbcomm FM 2Orbcomm FM 3Orbcomm FM 4Orbcomm FM 5Orbcomm FM 6Orbcomm FM 7Orbcomm FM 8Orbcomm FM 9Orbcomm FM 10Orbcomm FM 11Orbcomm FM 12Orbview 2Program: OrionOrion 1%GK K䵟쉂쉂쉂쉂쉂쉂쉂쉂p#؉u쉂n쉂؉:9:92:93:9有有5:9]:9^:9?J$@hAhBh8MChDhEh RPacsatPageosProgram: PalapaPalapa A1Palapa A2Palapa B1Palapa B2Palapa B2PPalapa B2RPalapa B4Palapa C1Palapa C2Program: PanamsatPanamsat 1Panamsat 2Panamsat 3Panamsat 3RPanamsat 4Panamsat 5Panamsat N$6Program: Pegasus&N+ MOPQsg8GV7cnQVqwVl?|s}s~sssssssssPegasus 1Pegasus 2Pegasus 3PegsatPolePMGPolairePolarPolluxPosatProgram: PrognozPrognoz 01Prognoz 02Prognoz 03Prognoz 04Prognoz 05Prognoz 06Prognoz 07Prognoz 08Prognoz 09Prognoz 10Prognoz 11d$_ s'S*Ձ+܉㡄*㢄*㣄*㤄*Prognoz 12ProsperoProgram: ProtonProton 1Proton 2Proton 3Proton 4(+$ R* UgT8  -ꉂ5oމ5oމ5oމ5oމ5oމ5oމ5oމ5oމ5oމƭ\ƭ\ƭ\=4oމ44oމ54oމ64oމ74oމ84oމRadarsatRadcalProgram: RadugaRaduga 01Raduga 02Raduga 03Raduga 04Raduga 05Raduga 06Raduga 07Raduga 08Raduga 09Raduga 1-1Raduga 1-2Raduga 1-3Raduga 10Raduga 11Raduga 12Raduga 13Raduga 14Raduga 15($ Q94oމ:4oމ;4oމ<4oމh4oމ_4oމ`4oމa4oމb4oމc4oމd4oމe4oމf4oމg4oމ4oމ4oމ4oމ4oމ㾩ARaduga 16Raduga 17Raduga 18Raduga 19Raduga 20Raduga 21Raduga 22Raduga 23Raduga 24Raduga 25Raduga 26Raduga 27Raduga 28Raduga 29Raduga 30Raduga 31Raduga 32Raduga 33Program: RelayRelay 1Relay 22, zeY뉂y9z9{9|9}9~99997777777777Program: ResursResurs F01Resurs F02Resurs F03Resurs F04Resurs F05Resurs F06Resurs F07Resurs F08Resurs F09Resurs F10Resurs F11Resurs F12Resurs F13Resurs F14Resurs F15Resurs F16Resurs F17Resurs F18Resurs F19D$p e*8!8㹾SsɉW㐋 퉂~OaEF/{r#W (WResurs F20Resurs F21Resurs 500Resurs O1-3REX 2Program: RohiniRohini 1BRohini 2Rohini 3Program: EorsatRosatRS 15Ryusei(,$ S 6p |m>`U˓FWp\򉂃*߉J.K.u.v.~稉rJj777774`Uq󉂃Z󉂃>0*-S80TSAC BProgram: SafirProgram: SakuraSakura 1Sakura 2ASakura 2BSakura 3ASakura 3BSampexProgram: San MarcoSan Marco 1San Marco 2San Marco 3San Marco 4San Marco 5SaraProgram: SarsatProgram: SatcomSatcom 1Satcom 1R -?0*-@0*-A0*q-s-t---IS=HW=HW=HW=HW=HW=HWeSIWo\D'[IW㖯Satcom 2Satcom 2RSatcom 3Satcom 3RSatcom 4Satcom C1Satcom C3Satcom C4Satcom K1Satcom K2SAXProgram: SBSSBS 1SBS 2SBS 3SBS 4SBS 5SBS 6Program: SCDSCD 1SCD 2AScoreSeasat) Su l^{m^{n^{o^{p^{q^{r^{s^{^{RRe>w|o5_zcBdBڢ􉂃Program: SecorSecor 01BSecor 02Secor 03Secor 04Secor 05Secor 06Secor 07Secor 08Secor 09Secor 13Seds 1Seds 2SFUShinseiSich 1Signe 3Program: SirioSirio 1Sirio 2Program: SiriusSirius 1Sirius 25 k ȉ ȉ5 ȉ6 ȉ ȉ ȉ ȉ ȉ"S.UW/UWEaU©Hىw퉂L2L2d㬎Y㮎YProgram: SkynetSkynet 1ASkynet 1BSkynet 2ASkynet 2BSkynet 4ASkynet 4BSkynet 4CSkynet 4DSMESMMProgram: SMSSMS 1SMS 2SNOESolar AProgram: SolidaridadSolidaridad 1Solidaridad 2Program: SolradSolrad 01Solrad 03A v 4 4 4 4㴎Y2Y 4 4Acىv?qZIz[Iz\IzdDQ/̸~XDYDZD[DSolrad 06ASolrad 06BSolrad 07ASolrad 07BSolrad 09Solrad 10Solrad 11ASolrad 11BSolwindProgram: SpacenetSpacenet 1Spacenet 2Spacenet 3Spacenet 3RProgram: SpartanSpartan 101Spartan 201-1Spartan 201-2Spartan 201-3Spartan 201-4) SkӸ~mӸ~nӸ~~b竉c竉d竉e竉㥇㦇㧇㨇xZU~~~~~~~Spartan 204Spartan 206Spartan 207Program: SpasSpas 1Spas 2Spas 3Spas 4Program: SpotSpot 1Spot 2Spot 3Spot 4Program: SputnikSputnik 01Sputnik 02Sputnik 03Sputnik 04Sputnik 05Sputnik 06Sputnik 074 ri~~~ITJT㑲ㅊD􉂃ㆊD􉂃㇊D􉂃_G?1\x444444Sputnik 09Sputnik 10Sputnik 40Program: SretSret 1Sret 2Program: SrossSross 1Sross 2Sross 3Sross C2StarletteStart 1Program: StatsionarStatsionar 01Statsionar 02Statsionar 03Statsionar 04Statsionar 05Statsionar 06 F X444444444444H4?4@4B4C4D4Statsionar 07Statsionar 08Statsionar 09Statsionar 10Statsionar 11Statsionar 12Statsionar 13Statsionar 14Statsionar 15Statsionar 16Statsionar 17Statsionar 19Statsionar 20Statsionar 21Statsionar 22Statsionar 24Statsionar 25Statsionar 26C$ E4xټ 󼬉󼬉󼬉󼬉@djdj㉱vY'# OOO_Sk7`Sk7ۢ&?a׉@a׉~Statsionar 27StellaProgram: StepStep 1Step 2Step 3Step 4Program: STRVSTRV 1ASTRV 1BSurfsat 1Program: SuperbirdSuperbird A1Superbird A2Superbird B1Superbird CSuperbird DProgram: SymphonieSymphonie 1Symphonie 2Program: Syncomf)= JRsHsHsHSyncom 1Syncom 2Syncom 3($$ T& MzWoCoCoCoC4~WSw~Ww~W@ĘOMOMOMOMOMOMOM ډyk eeTaiyoProgram: TanseiTansei 1Tansei 2Tansei 3Tansei 4TD 1AProgram: TDFTDF 1TDF 2Program: TDRSTDRS 1TDRS 2TDRS 3TDRS 4TDRS 5TDRS 6TDRS 7Techsat 1TELE XProgram: TelecomTelecom 1ATelecom 1B; twe8e9e:e;eNꉂ5`1VckzzzzƵƵƵ͵͵㑑)zz4qTelecom 1CTelecom 2ATelecom 2BTelecom 2CTelecom 2DProgram: TeledesicTeledesic 1Program: TelstarTelstar 1Telstar 2Telstar 301Telstar 302Telstar 303Telstar 401Telstar 402Telstar 402RTelstar 5TemisatProgram: TempoTempo 2. ]v胉FˉGˉHˉfOgO:ܗ+;ܗ+<ܗ+=ܗ+>ܗ+?ܗ+@ܗ+Aܗ+Bܗ+ڗ+? bUue<Program: ThaicomThaicom 1Thaicom 2Thaicom 3Program: ThorThor 1Thor 2Program: TirosTiros 01Tiros 02Tiros 03Tiros 04Tiros 05Tiros 06Tiros 07Tiros 08Tiros 09Tiros 10Tiros NTOMSTopex PoseidonTournesol 3 |gzPW|ۉd؉㺶؉㻶؉ABŘbU 剂eL͉>W>WII]cKlvmmvmmѾmԐmԐTraacProgram: TransitTransit 2ATransit 4ATransit 4BTransit 5BN1Transit 5BN2TRMMProgram: TsikadaTsikada 1TTS 1TTS 2Program: TubsatTubsat ATubsat BProgram: TurksatTurksat 1ATurksat 1BProgram: TvsatTvsat 1Tvsat 2($ U lUcUS|W|W|W|W|W|W|W|WrWsW- - ~ꠉ͓F̉ΓF̉ϓF̉ГF̉ѓF̉#SUARSProgram: UHFUHF 1UHF 2UHF 3UHF 4UHF 5UHF 6UHF 7UHF 8Ume 1Ume 2Unamsat 1Unamsat 2Program: UosatUosat 1Uosat 2Uosat 3Uosat 4Uosat 5UPMsat 1Program: USA('$ Vp  u߉kkk71ĉ;9%>>>>>>Program: VanguardVanguard 1Vanguard 2Vanguard 3Program: VelaVikingProgram: VitasatProgram: VortexVortex 1Vortex 2Vortex 3Vortex 4Vortex 5Vortex 6(' $ W"   3 .`//////&>a͉caω*-XWebersatProgram: WestarWestar 1Westar 2Westar 3Westar 4Westar 5Westar 6Dial-WikaWind 1WresatWSF 2(  $ X3 < * $*XTE( d $ Yy< W z ĀO·ቂ㉂㉂㉂㉂㉂㉂ ㉂YESProgram: YuriYuri 1Yuri 2AYuri 2BYuri 2XYuri 3AYuri 3BYuri 3HYuri 3N< d  1u#   DesignationPW  5 :8NJ" Designation Numbers&  # 6 ? ' O Introduction& e2 2  Objects in space are tracked by the US Space Command. Each object is identified by 2 numbers called the Catalog Number (in the US Space Command database) and the International Launch number. You will find those 2 designators in the General section of each satellite sheet. The Catalog Number is just an incremented number from the first object launched in space on. To search a satellite by its catalog number, use the search tool (keyword search) and enter "CATNR " followed by that number.? 'A1 0   The International Launch Number is a code is composed of the year (2 first digits), by the number of te'AW he launch in the year (the 3 next digits) and 2 letters can be added to identify the objects resulting of a launch. Thus number 91026 means the 26th launch in 1991. To search for a launch by number, use the search tool (keyword search) and enter "LAUNR " followed by that number.7e^A'   Last launches+'AA$ 1998z^AC Pq~qSj)ቂՅՅՅՅՅ] {YR^Z3xՅՅ3x98033A30 MayChinastar 198032E17 MayIridium 7598032D17 MayIridium 7498032C17 MayIridium 7398032B17 MayIridium 7298032A17 MayIridium 7098031A14 MayProgress M-3998030A13 MayNOAA 1598029A09 MayUSA 13998028A07 MayEchostar 498027A07 MayCosmos 235198026B02 MayIridium 7198026A02 MayIridium 6998025A29 AprCosmos 2350+AE $Pq~qSS􉂃W􉂃{}{}㳝QP㱝QPボՅՅՅՅՅՅՅ98024B28 AprBsat 1B98024A28 AprNilesat 10198023D24 AprGlobalstar 1598023C24 AprGlobalstar 1498023B24 AprGlobalstar 898023A24 AprGlobalstar 698022A17 AprSTS 9098021G07 AprIridium 6898021F07 AprIridium 6798021E07 AprIridium 6698021D07 AprIridium 6598021C07 AprIridium 6498021B07 AprIridium 6398021A07 AprIridium 62qCG Pq~qSPWՅՅՅՅՅՅՅ㨇|Wĉ5`198020A02 AprTrace98019E30 MarIridium 6098019D30 MarIridium 5998019C30 MarIridium 5898019B30 MarIridium 5798019A30 MarIridium 5598018B25 MarIridium 6198018A25 MarIridium 5198017A24 MarSpot 498016A16 MarUHF 898015A14 MarProgress M-3898014A28 FebIntelsat 80698013A27 FebHotbird 498012B26 FebTeledesic 1(}E J $Pq~qSEaUˎՅՅՅՅՅv3x㯝QP㮝QP㭝QP㬝QPH ;s:98012A26 FebSNOE98011A21 FebComets98010E18 FebIridium 5498010D18 FebIridium 5398010C18 FebIridium 5298010B18 FebIridium 5198010A18 FebIridium 5098009A17 FebCosmos 234998008D14 FebGlobalstar 498008C14 FebGlobalstar 398008B14 FebGlobalstar 298008A14 FebGlobalstar 198007D10 FebCelestis 298007C10 FebOrbcomm FM 4GK{ ĀPq~qS:s:T-rG$c􉂃i뉂Wf ȉ98007B10 FebOrbcomm FM 398007A10 FebGFO 198006B04 FebInmarsat 3F598006A04 FebBrasilsat B398005A29 JanUSA 13798004A29 JanSoyuz TM-2798003A22 JanSTS 8998___22 JanOffek 498002A10 JanSkynet 4D98001A07 JanLunar Prospector+ JK$ 1997uKM Pq~qSk^`BjZыiZыrZы@s:?s:>s:=s:ՅՅrRUյaձTDhUՅՅՅՅ97051B14 SepIridium 3297051A14 SepIridium 2997050A04 SepGE 397049B02 SepMeteosat 797049A02 SepHotbird 397048B01 SepDummy Iridium 297048A01 SepDummy Iridium 197047A28 AugFort97046A28 AugPanamsat 597045A25 AugACE97044A23 AugLewis97043E21 AugIridium 2297043D21 AugIridium 2397043C21 AugIridium 2497043B21 AugIridium 25p Pq~qSՅnr3xEhSJe_Sk73Z݉ՅՅՅՅ97043A21 AugIridium 2697042A19 AugMabuhay 197041A14 AugCosmos 234597040A08 AugPanamsat 697039B07 AugSPAS97039A07 AugSTS 8597038A05 AugSoyuz TM-2697037A01 AugOrbview 297036A28 JulSuperbird C97035A23 JulGPS BIIR-0297034E09 JulIridium 2197034D09 JulIridium 2097034C09 JulIridium 1897034B09 JulIridium 17uΌ Pq~qSՅ}ĉՅՅՅrՅՅՅՅ#'v&q3xG@c97034A09 JulIridium 1597033A05 JulProgress M3597032A01 JulSTS 9497031A25 JunIntelsat 80297030G18 Juniridium 1197030F18 Juniridium 1697030E18 Juniridium 1397030D18 Juniridium 0997030C18 Juniridium 1097030B18 Juniridium 1297030A18 Juniridium 1497029A10 JunDFH 4597028A06 JunCosmos 234497027B03 JunInsat 2Do Pq~qS,rGzzgO'CM_剂p3xRo3x"'v&mՅnՅoՅpՅqՅ97027A03 JunInmarsat 3F497026A24 MayTelstar 597025A20 MayThor 297____20 MayCosmos (Zenit, was a Tselina 2)97024A15 MayCosmos 234397023A15 MaySTS 8497022A14 MayCosmos 234297021A11 MayDFH 4497020E05 MayIridium 0497020D05 MayIridium 0597020C05 MayIridium 0697020B05 MayIridium 0797020A05 MayIridium 08jΌ Pq~qS㝖.H K&n3xR􉂃Hˉw3xQ㭢щqJiUĉ c鉂97019A25 AprGoes 1097018B21 AprCelestis 197018A21 AprMinisat 0197017A17 AprCosmos 234197016B16 AW prBsat 1A97016A16 AprThaicom 397015A09 AprCosmos 234097014A06 AprProgress M3497013A04 AprSTS 8397012A04 AprDMSP B5D2-997011A08 MarTempo 297010A04 MarZeya97009A01 MarIntelsat 80197008A23 FebDSP 3-6!a! NPq~qS㉺2 K3x J3x I3x N, M, L,ӊHPS_ErRU2Z݉97007A17 FebJcsat 497006F14 FebCosmos 233997006E14 FebCosmos 233897006D14 FebCosmos 233797006C14 FebGonets-D1 697006B14 FebGonets-D1 597006A14 FebGonets-D1 497005A12 FebHaruka97004A11 FebSTS 8297003A10 FebSoyuz TM-2597002B30 JanNahuel 1A97002A30 JanGE 297____17 JanGPS BIIR-01No5 :2Pq~qSO97001A12 JanSTS 81+!$ 1996o Pq~qS0p҉H3x+rGG3xX`鉂!SU96073A24 DecBion 1196072A20 DecUSA 12996071A20 DecCosmos 233696070A17 DecInmarsat 3F396069A11 DecCosmos 233596068A04 DecPathfinder96067A21 NovHotbird 296066A20 NovProgress M-3396065C22 NovWSF96065B20 NovOrfeus96065A19 NovSTS 8096064A16 NovMars 9696063B13 NovMeasat 296063A13 NovArabsat 2B96062A07 NovMGS96061A04 NovHETE, $Pq~qS˓FWふY!'v&J7,6F݉WR^ZrRU*rG- F3xE3xP$s96061A04 NovSAC B96060A24 OctMolniya 3-4896059A20 OctDong Fang Hong 43 (FSW 2-3)96058A26 SepExpress 296057A16 SepSTS 7996056A12 SepGPS BIIA-2796055A11 SepEchostar 296054A08 SepGE 196053A06 SepInmarsat 3F296052B05 SepUnamsat 296052A05 SepCosmos 233496051A04 SepCosmos 233396050C29 AugMagion 596050B29 AugPrognoz 12{ Pq~qSoK&V"QU 'v&J ;isIW;eoG|W6F݉nvm_鉂96050A29 AugMusat96049A21 AugFast96048A18 AugDong Fang Hong 42 (Chinasat 7)96047A17 AugSoyuz TM-2496046B17 AugFuji 296046A17 AugAdeos 196045A14 AugMolniya 1-8996044B08 AugTelecom 2D96044A08 AugItalsat 296043A31 JulProgress M-3296042A25 JulUHF 796041A16 JulGPS BIIA-2696040B09 JulTurksat 1C96040A09 JulArabsat 2A!| Pq~qSi"鉂[i뉂 bU+ĉ_7ǥ#o?upnӸ~*x3 ^:996039A03 JulApstar 1A96038A03 JulUSA 12596037A02 JulTOMS960___20 JunCosmos (Yantar, aboard Soyuz)96036A20 JunSTS 7896035A15 JunIntelsat 709960___04 JunCluster 1, 2, 3, 496034A25 MayGorizont 3296033A23 MayGalaxy 996032B19 MaySpartan 20796032A19 MaySTS 7796031A17 MayMSTI 396030B16 MayAmos 196030A16 MayPalapa C2'F Pq~qSe剂%W~3i뉂D3x㟛Lw)~)rG6F݉)_TC3x96____14 MayCosmos 2333 failure96029A12 MayNOSS 1596028A05 MayProgress M-3196027A30 AprSAX96026A24 AprUSA 11896025A24 AprCosmos 233296024A24 AprMSX96023A23 AprPriroda96022A20 AprMSAT 196021A08 AprAstra 1F96020A03 AprInmarsat 3F196019A28 MarGPS BIIA-2596018A22 MarSTS 7696017A21 MarIRS P396016A14 MarCosmos 2331,~  Pq~qSĉWQV>W(4oމL3x 3x3xK,J,I,ĉ96015A14 MarIntelsat 70796014A09 MarREX 296013A24 FebPolar96012B26 FebTTS 296012A22 FebSTS 7596011A21 FebSoyuz TM-2396010A19 FebRaduga 3396009F19 FebCosmos 233096009E19 FebCosmos 232996009D19 FebCosmos 232896009C19 FebGoneF~W ts D1-396009B19 FebGonets D1-296009A19 FebGonets D1-196008A17 FebNEAR96____14 FebIntelsat 708nF~ ʀPq~qS* ]:9#o3xY 8MmӸ~%96007A05 FebN Star B96006A01 FebPalapa C196005A25 JanGorizont 3196004A16 JanCosmos 232796003A14 JanKoreasat 296002B12 JanMeasat 196002A12 JanPanamsat 3R96001B11 JanSpartan 20696001A11 JanSTS 72+~$ 1995'> Pq~qS*VR^ZWYT3xb㉂3x3x3xG@c:e҉k95074A30 DecXTE95073A28 DecEchostar 195072B28 DecSkipper95072A28 DecIRS 1C95071A20 DecCosmos 232695070A18 DecProgress M-3095069A15 DecGalaxy 3R95068C14 DecCosmos 232595068B14 DecCosmos 232495068A14 DecCosmos 232395067B06 DecInsat 2C95067A06 DecTelecom 2C95066A05 DecKH 12-395065A02 DecSoho95064A28 NovAsiasat 2*|h *Pq~qSO?~'㉱vgT3x4+|W&(~mEo3x!3x95063A17 NovGals 295062A17 NovISO95061A12 NovSTS 7495060A06 NovMilstar 1-295059B04 NovSurfsat 195059A04 NovRadarsat95058A31 OctCosmos 232295____23 OctMeteor (US)95057A22 OctUHF 695056A20 OctSTS 7395055A19 OctAstra 1E95054A11 OctLuch 195053A08 OctProgress M-2995052A06 OctCosmos 232195051A29 SepCosmos 2320n>{ Pq~qS*8㑑)*-XZD3д%>w|2x) ㈺2ߎ؉〵YY 95050A26 SepResurs F2095049A24 SepTelstar 402R95048C11 SepWSF 295048B08 SepSpartan 201-395048A07 SepSTS 6995047A03 SepSoyuz TM-2295046A31 AugFasat Alfa95046A31 AugSich 195045A30 AugCosmos 231995044A29 AugN Star A95043A29 AugJcsat 395____15 AugGemstar95042A09 AugMolniya 3-4795041A05 AugKoreasat 1kh  Pq~qSChO$sceM2x2x2xOM--i뉂#fNh휭95040A03 AugPanamsat 495039F02 AugMagion 495039A02 AugPrognoz 1195038A31 JulDSCS 3-0995037C24 JulCosmos 231895037C24 JulCosmos 231795037A24 JulCosmos 231695036A20 JulProgress M-2895035B13 JulTDRS 795035A13 JulSTS 7095034A10 JulUSA 11295033C07 JulUPMsat 195033B07 JulCerise95033A07 JulHlios 1Aw{  Pq~qS2x2x$󼬉〽9T2x|W2x.ĉ5i뉂`QTlJT95032A05 JulCosmos 231595031A28 JunCosmos 231495030A27 JunSTS 7195____22 JunStep 395029A10 JunDBS 395028A08 JunCosmos 231395027A31 MayUHF 595026A24 MayCosmos 231295025A23 MayGoes 0995024A20 MaySpektr95023A17 MayIntelsat 70695022A14 MayUSA 11095021A21 AprERS 286017JE19 AprGFZ 195020A09 AprProgress M-27 ~  Pq~qSS fK9s:8s:#c􉂃 ډ- 㬢щ2xĉ95019A07 AprAMSC 195018A05 AprOffek 395017C03 AprMicrolab 195017B03 AprOrbcomm FM295017A03 AprOrbcomm FM195016B28 MarHotbird 195016A28 MarBrasilsat B295___28 MarTechsat 195___28 MarUnamsat 195___28 MarEKA (Eksperimental'niy Kosmicheskiy Apparat)95015A24 MarDMSP B5D2-895014A22 MarCosmos 231195013A22 MarIntelsat 705o @ Pq~qS2xTx4xw4xv4xu4xL ױBױBױB95012A22 MarCosmos 231095011B17 MarGMS 595011A17 MarSFU95010A14 MarSoyuz TM-2195009C07 MarCosmos 230995009B07 MarCosmos 2308@W 95009A07 MarCosmos 230795008A02 MarCosmos 230695007A02 MarSTS 6795006A16 FebFoton 1095005A15 FebProgress M-2695004H04 FebOderacs 2F95004G04 FebOderacs 2E95004F04 FebOderacs 2D;B wPq~qSױBױBױBkӸ~|W# ~eL͉-ĉ95004E04 FebOderacs 2C95004D04 FebOderacs 2B95004C04 FebOderacs 2A95004B07 FebSpartan 20495004A03 FebSTS 6395003A29 JanUHF 495002C24 JanFaisat 195002B24 JanAstrid 195002A24 JanTsikada 195____15 JanEXPRESS (German) (no number assigned)95001A10 JanIntelsat 704+@B$ 1994!vBD $Pq~qS\ {t4x4oމs4xr4xq4xp4xy4x-x (W c鉂-xvEoIW94089A30 DecNOAA 1494088A29 DecCosmos 230594087A28 DecRaduga 3294086F26 DecCosmos 230494086E26 DecCosmos 230394086D26 DecCosmos 230294086C26 DecCosmos 230194086B26 DecCosmos 230094086A26 DecCosmos 229994085A26 DecRS 1594084A22 DecDSP 3-594083A20 DecCosmos 229894082A16 DecLuch 094081A14 DecMolniya 1-88'B"G Pq~qSBh'v&R*-l-x-x-x-xSsɉe竉-xa͉94____01 DecPanamsat 394080A29 NovDong Fang Hong 4194079A29 NovOrion 194078A24 NovGeo-IK 194077A24 NovCosmos 229794076C20 NovCosmos 229694076B20 NovCosmos 229594076A20 NovCosmos 229494075A11 NovProgress M-2594074A04 NovResurs O1-394073B04 NovSpas 4 (Crista)94073A03 NovSTS 6694072A02 NovCosmos 229394071A01 NovWind 1qD8I Pq~qS(~Q_TJ7󓋉GˉL2ĉ -x -xYD94070A01 NovAstra 1D94069A31 OctElectro 194068A15 OctIRS P294067A13 OctExpress 194066A11 OctOcean 494065B08 OctThaicom 294065A08 OctSolidaridad 294064A06 OctIntelsat 70394063A03 OctSoyuz TM-2094062A30 SepSTS 6894061A27 SepCosmos 229294060A21 SepCosmos 229194059B13 SepSpartan 201-294059A09 SepSTS 64#~"G[K Pq~qS͵㫢щ㊾T_j뉂-xY,x,x,xmvm"c􉂃,x94058A09 SepTelstar 40294057A29 AugDMSP B5D2-794056A28 AugETS 694055A27 AugOptus B394054A27 AugUSA 10594053A26 AugCosmos 229094052A25 AugProgress M-2494051A23 AugMolniya 3-4694050C11 AugCosmos 228994050B11 AugCosmos 228894050A11 AugCosmos 228794049B11 AugTurksat 1B94049A11 AugBrasilsat B194048A05 AugCosmos 2286n8InM Pq~qS9T|KU,x,xb ,xU򲟉 ㉂Ah,x('v&󼬉94047A03 AugDBS 294046A03 AugApex94045A02 AugCosmos 228594044A29 JulCosmos 228494043A21 JulApstar 194042A20 JulCosmos 228394041A14 JulNadezhda 494040B08 JulYuri 3N94040A08 JulPanamsat 294039A08 JulSTS 6594038A06 JulCosmos 228294037A03 JulDong Fang Hong 4094036A01 JulSoyuz TM-1994____27 JunStep 1&~[KO Pq~qS|WdjdjĉeN ,x#o󼬉x_Gj뉂,x,x94035A24 JunUHF 394034C17 JunSTRV 1B94034B17 JunSTRV 1A94034A17 JunIntelsat 70294033A14 JunFoton 0994032A07 JunCosmos 228194____25 MayCosmos94031A22 MayProgress M-2394030A20 MayGorizont 3094029A19 MayStep 294028A09 MayMSTI 294027A04 MaySross C294026A03 MayUSA 10394025A28 AprCosmos 228094024A26 AprCosmos 2279mnM Pq~qS,x.,x,x,x֛+xOW j뉂j뉂R6F݉^94023A23 AprCosmos 227894022A13 AprGoes 0894021C11 AprCosmos 227794021B11 AprCosmos 227694021A11 AprCosmos 227594020A09 AprSTS 5994019A22 MarProgress M-2294018A17 MarCosmos 227494017B13 MarUSA 10294017A13 MarUSA 10194016B10 MarSeds 294016A10 MarGPS BIIA-2494015A04 MarSTS 6294014A02 MarCoronas 1wO˃ Pq~qS_b㉂4oމ,x,x,x,x,x,x&v&&v&ƭ\94013A19 FebGalaxy 1R94012A18 FebRaduga 3194011F12 FebCosmos 227394011E12 FebCosmos 227294011D12 FebCosmos 227194011C12 FebCosmos 227094011B12 FebCosmos 226994011A12 FebCosmos 226894010B08 FebDong Fang Hong 3994010A08 FebDong Fang Hong 3894009A07 FebMilstar 1-194008A05 FebRaduga 1-394007B03 FebRyusei (OREX)| Pq~qSU +V쉂ױBױBױBױBױBױBܫ kIlvm94007A03 FebMyojo (VEP)94006H09 FebBremsat94006G09 FebOderacs 1F94006F09 FebOderacs 1E94006E09 FebOderacs 1D94006D09 FebOderacs 1C94006C09 FebOderacs 1B94006B09 FebOderacs 1A94006A03 FebSTS 6094005A28 JanProgress M-2194004A25 JanDSPSE (Clementine)94003A25 JanMeteor 3-0694003B25 JanTubsat B94____24 JanTurksat 1AP˃wA RPq~qSO?94____24 JanEutelsat 2F594002A20 JanGals 194001A08 JanSoyuz TM-18+$ 1993$ywƈ $Pq~qSIWFˉ~9T͵CdceMԵaL2#o,x,x#o6F݉93079A22 DecMolniya 1-8793078B18 DecThaicom 193078A18 DecDBS 193077A16 DecTelstar 40193076A08 DecNato 4B93075A02 DecSTS 6193074A28 NovDSCS 3-0893073B20 NovMeteosat 693073A20 NovSolidaridad 193072A18 NovGorizont 2993071A05 NovCosmos 226793070A02 NovCosmos 226693069A28 OctGorizont 2893068A26 OctGPS BIIA-23jՊ Pq~qS,xĉ՛&v&ɉ4oމVBK|{3xټ㧇93067A26 OctCosmos 226593066A22 OctIntelsat 70193065A18 OctSTS 5893064A11 OctProgress M-2093063A08 OctDong Fang Hong 3793____05 OctLandsat 693062A30 SepRaduga 3093061H26 SepKitsat B93061G26 SepPosat93061E26 SepHealthsat93061D26 SepItamsat93061C26 SepEyesat93061B26 SepStella93061A26 SepSpot 3iƈ Pq~qSYT,x,xd竉 KUΛ,x|W4s k6F݉7,x93____20 SepIRS 1E93060A17 SepCosmos 226493059A16 SepCosmos 226393058C13 SepSpas 393058B12 SepACTS93058A12 SepSTS 5193057A07 SepCosmos 226293056A03 SepUHF 293055C31 AugTemisat93055A31 AugMeteor 2-2193054A30 AugGPS BIIA-2293053A24 AugResurs F1993052A10 AugProgress M-1993051A10 AugCosmos 2261nՊ Pq~qS[ {~Y$W~G@cc͉,xceMh,xg,x76F݉8 793050A09 AugNOAA 1393049A04 AugMolniya 3-4593____02 AugNOSS 1493048B22 JulInsat 2B93048A22 JulHispasat 1B93047A22 JulCosmos 226093046A19 JulDSCS 3-0793045A14 JulCosmos 225993044A07 JulCosmos 225893043A01 JulSoyuz TM-1793042B26 JunPMG93042A26 JunGPS BIIA-2193041A25 JunRadcal93040A25 JunResurs F18(* Pq~qS:upf,xe,xd,xc,xb,xa,xԛ`,xn>IW7 6F݉93039A25 JunGalaxy 493038F20 JunCosmos 225793038E20 JunCosmos 225693038D20 JunCosm*W os 225593038C20 JunCosmos 225493038B20 JunCosmos 225393038A20 JunCosmos 225293037A21 JunSTS 5793036A16 JunCosmos 225193____27 MayGorizont #3993035A26 MayMolniya 1-8693034A22 MayProgress M-1893033A21 MayResurs F1793032A13 MayGPS BIIA-20$yN $Pq~qS:(~i,x=,x<,x;,x:,x9,x8,x7,xқb }Y6,x93031B12 MayArsne93031A12 MayAstra 1C93030F11 MayCosmos 225093030E11 MayCosmos 224993030D11 MayCosmos 224893030C11 MayCosmos 224793030B11 MayCosmos 224693030A11 MayCosmos 224593029A28 AprCosmos 224493028A27 AprCosmos 224393027A26 AprSTS 5593026A25 AprAlexis93025A21 AprMolniya 3-4493024A16 AprCosmos 2242v*c Pq~qSXDӛ5,x>,x,x,xR5F݉,x|W\g4oމ93023B11 AprSpartan 201-193023A08 AprSTS 5693022A06 AprCosmos 224193021A02 AprCosmos 224093020A01 AprCosmos 223993019A31 MarProgress M-1793018A30 MarCosmos 223893017B30 MarSeds 193017A30 MarGPS BIIA-1993016A26 MarCosmos 223793015A25 MarUHF 193014A25 MarStart 193013A25 MarRaduga 2993012A21 FebProgress M-16vN~ Pq~qS,x,x ,xIW9_P ,x5F݉ ,x ,xOMћIW93011A20 FebAstro D93010C17 FebCosmos 223693010B17 FebCosmos 223593010A17 FebCosmos 223493009B09 FebSCD 193009A09 FebOrbcomm XP 193008A09 FebCosmos 223393007A03 FebGPS BIIA-1893006A26 JanCosmos 223293005A24 JanSoyuz TM-1693004A19 JanCosmos 223193003B13 JanTDRS 693003A13 JanSTS 5493002A13 JanMolniya 1-85Sc5 :<Pq~qS,x93001A12 JanCosmos 2230+~$ 1992$  )Pq~qS_5F݉+x+xb뉂ЛO҉#o92095A29 DecCosmos 2229 (bion 10)92094A25 DecCosmos 222892093A25 DecCosmos 222792092A22 DecCosmos 222692091A22 DecCosmos 222592090A21 DecOptus B292089A18 DecGPS BIIA-1792088A17 DecCosmos 222492087A09 DecCosmos 222392086B02 DecUSA 08992086A02 DecSTS 5392085A02 DecMolniya 3-92084A01 DecSuperbird A292083A28 NovKH 12-292082A27 NovGorizont 27#C Pq~qS+x+x5F݉x+x+x㹾dɉ=upySϛ92081A25 NovCosmos 222292080A24 NovCosmos 222192079A23 NovGPS BIIA-1692078A21 NovMSTI 186017GX20 NovMak 292077A20 NovCosmos 222092076A17 NovCosmos 221992075A15 NovResurs 50092074A30 OctEkran 2092073A29 OctCosmos 221892072A28 OctGalaxy 792071A27 OctProgress M-1592070C31 OctCTA92070B23 OctLageos 292070A22 OctSTS 52 b Ѐ=Pq~qS{Y̗>T&v&1T㩛s-92069A21 OctCosmos 221792068F20 OctCosmos 221692068E20 OctCosmos 221592068D20 OctCosmos 221492068C20 OctCosmos 221392068B20 OctCosmos 221292068A20 OctCosmos 221192067A14 OctMolniya 3-4292066A12 OctDFS 392065A08 OctFoton92064B06 OctDong Fang Hong 3692064A06 OctFreja92063A25 SepMars Observer92062A22 SepCosmos 221092061A12 SepSTS 4792060B10 SepSatcom C31C +Pq~qSc͉?-x5F݉t--7_>`Uue&v&92060A10 SepHispasat 1A92059A10 SepCosmos 220992058A09 SepGPS BIIA-1592057A31 AugSatcom C492____22 AugGalaxy 1R failure92056D19 AugPion 292056C19 AugPion 192056A19 AugResurs F1692055A15 AugProgress M-1492054A13 AugObW ptus B192053A12 AugCosmos 220892052C10 AugS80T92052B10 AugKitsat A92052A10 AugTopex Poseidon92051A09 AugDong Fang Hong 35#b ܀9Pq~qSI㨛<-x;-x:-x؉#o92050A06 AugMolniya 1-92049B31 JulEureca 192049A31 JulSTS 4692048A30 JulCosmos 220792047C29 JulCosmos 220692047B29 JulCosmos 220592047A29 JulCosmos 220492046A27 JulSoyuz TM-1592045A24 JulCosmos 220392044B24 JulDUVE92044A24 JulGeotail92043A14 JulGorizont 2692042F13 JulCosmos 220292042E13 JulCosmos 220192042D13 JulCosmos 220092042C13 JulCosmos 2199 Pq~qSG@c5F݉~稉ceMכ7ƉN}PU92042B13 JulCosmos 219892042A13 JulCosmos 229792041B09 JulEutelsat 2F492041A09 JulInsat 2A92040A08 JulCosmos 219692039A07 JulGPS BIIA-1492038A03 JulSampex92037A02 JulDSCS 3-0692036A01 JulCosmos 219592035A30 JunProgress M-1392034A25 JunSTS 5092033A23 JunResurs F1592032A09 JunIntelsat K92031A07 JunEUVE92030H02 JunCosmos 2194" ЀCPq~qS㇊D􉂃5:9㫛7Z뉂jG92030G02 JunCosmos 219392030F02 JunCosmos 219292030E02 JunCosmos 219192030D02 JunCosmos 219092030C02 JunCosmos 218992030B02 JunCosmos 218892030A02 JunCosmos 218792029A28 MayCosmos 218692028A20 MaySross 392027A14 MayPalapa B492026A07 MaySTS 4992025A29 AprCosmos 218592024A29 AprResurs F1492023A25 AprUSA 08192022A19 AprProgress M-1292021B15 AprInmarsat 2F4  Pq~qS9e5F݉#o㧛;up6鉂O5F݉92021A15 AprTelecom 2B92020A15 AprCosmos 218492019A10 AprGPS BIIA-1392018A08 AprCosmos 218392017A02 AprGorizont 2592016A01 AprCosmos 218292015A24 AprSTS 4592014A17 MarSoyuz TM-1492013A14 MarGalaxy 592012A09 MarCosmos 218192011A04 MarMolniya 1-92010B26 FebArabsat 1C92010A26 FebSuperbird B192009A23 FebGPS BIIA-1292008A17 FebCosmos 2180x p Pq~qSZceM%x%x%x㤛92007A11 FebJERS 192006A10 FebDSCS 3-0592____05 FebCosmos FTO92005C29 JanCosmos 217992005B29 JanCosmos 217892005A29 JanCosmos 217792004A25 JanProgress M-1192003A24 JanCosmos 217692002A22 JanSTS 4292001A21 JanCosmos 21754  1    %TSE@  5 :NJ"  TSE/  a _㔗Xx Ƞ$2c%鉂 ЩecThe Satellite Encyclopedia is copyrighted by Tag's Broadcasting Services, all rights reserved, 1993-1998.Section en franaisAlso to be read:License Agreement - Order formsBibliography referenceAcknowledgmentVersionsCompatible softwareHelp: how to use this encyclopedia?I"  ' DO Philosophy of this encyclopedia*  @8 >㭄؉ This satellite encyclopedia is aimed to gather knowlegde into a single easy to use document. Contributions are welcome... You may even become a coauthor of TSE like Jean-Jacques Serra who manages the launch vehicle section! This encyclopedia is published every 3/4 months. Therefore this software is not a final version!If you are any kind of satellite specialist, satellite operator or constructor, or a space organization we would be very glad to get in touch with you. If for some reason you feel we are not treating your organization's satellites correctly, understand we only work with data we have! Operators are encouraged to send their Technical User Guide and other technical documentations, including preliminary data when available.  @  A, &Ƞ$If you are the author of a satellite related book or software, or if your organization publishes a magazine or newsletter related to space or satellite, see our special offer in the license agreement.7 @>A'  O The fair play AJC2 2  This encyclopedia is shareware: you can use it on a trial basis during SEVEN days; after this delay you should either register or delete it. The shareware version is size-limited to fit on a 3.5" floppy. Thus numerous EIRP maps are not included so as Russian programs. That's why you get an error when clicking on those items.If you use The Satellite Encyclopedia after 7 days of trial or for commercial purposes, you MUST register. The registered version includes:&>ApC# U"JCC3#6D3U the full 15 MB help file with:DpC D3#6"3U 390 EIRP mapsc0ClD3#6`3U the listing of satellites on the Clarke BeltR DD3#63U the calendar with the future launches and details about the related satellitesKlD JOnline support is available from the internet via our web server at http://www.tele-satellite.com/tse/ The online version of TSE is located at http://www.tele-satellite.com/tse/online/ Check it out for the latest updates of TSE!You may also subscribe to our mailing lists by email or online. To join the public mailing list, send an email:To: majordomo@tags1.dn.netSubject: noneBody: subscribe tse-pubA development list is also available under the name tse-dev&JL# 1 L M' O ContactoBLzM- *TBSBP 158, 14010 Caen cedex 1, Francetbs@TBS-satellite.comsH MM+ & Please mention the version of the encyclopedia you currently use.8zM%N' "O Providing data. MSN# We need:%NbO. *%鉂Your name or alias (that will be quoted in the aknowledgment section)Your postal address (and electronic if you have any)The information with it's precise origin & dateThe version of the encyclopedia you currently useSN%- (Please ensure that we receives press releases from your company by fax or email:fax: +33-1-5301-3114Email: pbO% ress@TBS-satellite.comCbOh1X hWorld Satellite CDO%5 :6FrÀ"  World Satellite CDhł% World Satellite CD is a unique piece of software! It contains the latest satellite information from the most respected sources, on a single CD. Yes, on this CD you will find listings with all tv and radio stations worldwide with parameters to tune in! Channels are documented with their contact information. The WSCD also contains the full edition of The Satellite Encyclopedia, a technical masterpiece. It documents past, present and future satellites with real technical information.dž. *World Satellite CD's concept is simple: compile the best satellite information on one CD. There are many satellite information sources around; we select the bests and put them together! Many are for free on the Internet, but are never handy when you need them! Now with WSCD you get the best information on a user-friendly CD. No complex interface to learn, it is as easy as the WWW: point and clic! In our World Satellite CD you will find:SATCO DX's full frequency listing. This is simply the most respected worldwide frequency listing available. It covers over 7000 TV and radio channels, analog & digital, C- & Ku-band. Each channel entry contains the frequency, audio and video modulation and parameters (this includes SR, FEC and PID values) plus broadcaster contact information (addresses, phone, fax, email & WWW) and links to TSE coverage maps. SATCO DX's frequencies tables document 163 satellites worldwide and is known on the internet as http://www.satcodx.commBł4+ $The Satellite Encyclopedia. This is TBS's reference guide published since 1994. It provides in depth technical satellite information for geostationary telecommunication satellites (footprints, frequency plans, power, etc.) as well as detailed descriptions for other satellites. With over 3000 pages and 1800 satellite fact sheets, TSE is a unique source for spacecraft information. It also provide specialized indexes such as the GEO map, schedule of future launches, thematic listings, rocket information, etc. It is available online at http://www.TELE-satellite.com/tse/`dž' With World Satellite CD you can now forget about accessing those resources on the internet! This CD brings you the whole set directly on your PC. Moreover you can search the data with a powerful search engine to access the information within seconds! To keep you updated, the WSCD is also available through a subscription, one CD per quarter. Our 1-year subscription will automatically provide you with the latest set of satellite information!The World Satellite CD fulfills the needs of broadcasters, telecom operators, cable operators, consultants, manufacturers and satellite equipement vendors worldwide. Moreover WSCD is available at a fraction of the price of yearly paper publications! The current CD is priced at 689 FRF (approx. $113). Our full year subscription (includes the current CD and 3 updates) is available for just 2429 FRF (approx. $399).r4R% To use World Satellite CD you need a personal computer with a 486 or higher processor & 8 MB or higher with Windows 95; or a Pentium or higher & 16 MB RAM or higher with Windows NT 4. You will also need a CDROM drive, a mouse and 3-18 MB of available hard-disk space. [all product and company names are trademarks or registered trademarks of their respective owners]B' 6O How to place your order?R' To order WSCD please print a form below. Please select your your delivery method: Airmail (1 to 2 weeks), Express (1 to 5 days) or provide your own express courier account number.As a general rule, prepayment is required. Our forms are in French Francs, use this currency converter to check the amount in your currency. W%e accept Mastercard and Visa cards (not AMEX, sorry), checks in French Francs drawn on a French bank, Eurochecks, SWIFT bank transfers (with charges on your end)..< Fpofxofpaper order form for the subscription (current CD + 3 updates)paper order form for the current CDVolume pricing and reseller information are available, please contact us. More information from:http://www.TBS-satellite.com/wscd/M+1 7 +jWSCD Subscription order formb-5 :\uP0"  WSCD Subscription order form - 199806#+3 4YES I want to subscribe to 4 issues (1 year) of the World Satellite CDfor 2429 FRF Name: ______________________________________________________ [Company]: ______________________________________________________ Address: ______________________________________________________ City: ____________________________ Postal Code: ____________ Country: ____________________________ [State]: ________________ Phone: ________________________ Fax: ________________________ 2 2 Email: ______________________________________________________POSTAGEAirmail Express Other------- ------- -----Europe 136 FRF Europe 792 FRF Charge my N-America 160 FRF N-America 932 FRF Fedex/other: ______Asia 190 FRF Asia 1012 FRF account #Other 218 FRF Other 1132 FRF _______TOTAL CHARGE: 2429 FRF + ______ (postage) = _______ FRF= HEuropean Union residents should apply 20.6% VAT or specify theirEU VAT number: _______________________PAYMENT( ) Check (must be drawn on a French bank in FRF, payable to TBS)( ) Credit card (Visa/MasterCard): Number: ________________________________Expiration: __________ Signature: __________________________________________________ Date: ________________________________SEND TO: TBS BP 158, 14010 Caen cedex 1, Francesj$  Fax: +33-1-5301-3114 (if you fax, please write in ALL CAPS) email: tbs@TBS-satellite.comG1) s  WSCD Single order form\'j 5 :PuP0"  WSCD Single order form - 199806 -3 4YES I want to get the most updated edition of the World Satellite CDfor 689 FRF Name: ______________________________________________________ [Company]: ______________________________________________________ Address: ______________________________________________________ City: ____________________________ Postal Code: ____________ Country: ____________________________ [State]: ________________ Phone: ________________________ Fax: ________________________ 52 2 Email: ______________________________________________________POSTAGEAirmail Express Other------- ------- -----Europe 34 FRF Europe 198 FRF Charge my N-America 40 FRF N-America 233 FRF Fedex/other: ______Asia 48 FRF Asia 253 FRF account #Other 55 FRF Other 283 FRF _______TOTAL CHARGE: 689 FRF + ______ (postage) = _______ FRF-[= HEuropean Union residents should apply 20.6% VAT or specify theirEU VAT number: _______________________PAYMENT( ) Check (must be drawn on a French bank in FRF, payable to TBS)( ) Credit card (Visa/MasterCard): Number: ________________________________Expiration: __________ Signature: __________________________________________________ Date: _____________________________5[j___SEND TO: TBS BP 158, 14010 Caen cedex 1, Frances5$  Fax: +33-1-5301-3114 (if you fax, please write in ALL CAPS) email: tbs@TBS-satellite.comB[417 4vJLicense AgreementN5 :4FrÀ"  License Agreementg344 8f(B QOrder form without VATOrder form with VAT;$' (O License AgreementYF Z     The use of The Satellite Encyclopedia is subject to the following terms and conditions.The Satellite Encyclopedia is copyrighted material. It is protected by the French copyright laws. You may not make any changes or modifications to The Satellite Encyclopedia. You may not decompile, disassemble, or otherwise reverse-engineer the software in any way. No reproduction whatever the method (including internet mirroring).You may use The Satellite Encyclopedia on a trial basis provided you do not violate the protection afforded the licensed software by the copyright laws, and you agree to the terms of the license agreement. You are entitled to evaluate the software freely for SEVEN days. If you use The Satellite Encyclopedia further on or for COMMERCIAL PURPOSES, you must purchase a license for its use. If you don't use it, delete it.B$' 6 How much is a license:m% See the order forms above. Registration provides you with a personal most updated version which includes:U"3#6D3U the full 15 MB help file with:D03#6"3U 390 EIRP mapsc03#6`3U the listing of satellites on the Clarke BeltR03#63U the calendar with the future launches and details about the related satellitesKc3#603U the Russian programsc% Subscriptions (4 issues) are available. A WWW edition is also available, see the prices online.;c& ' ( Special offers:c )  If you are a firm that publishes an electronic or paper periodical related to satellite (in French or English) you may obtain a free registration and a 1 year update subscription against a free one-year subscription to your publication.If you are the author of a book related to satellite (in French or English) you may obtain a free registration and a 1 year update subscription against a free copy of your book.If you are the author of a shareware related to satellite (in French or English) you may obtain a free registration and a 1 year update subscription against a free license for your shareware.lC&  ) "  Please note we reserve the right to refuse your application.  ( qTitle to the licensed software is not transferred to the end user. The end-user is granted an non exclusive license to use the software on one computer or computer workstation at any given time. Moreover he agrees to only copy the software for backup purpose. This also applies for the WWW edition.Tag's Broadcasting Services may include the buyers' name and contact information in The Satellite Encyclopedia's promotional materials.: 8' &O Limited Warrantyi @& While every precaution has been taken in the compilation of this data, the publisher assumes no responsability for errors or omissions. Neither is any liability assumed for damages resulting from the use of the information contained herein.We shall not be responsible for any problems or damage caused by the licensed software that may result from using the licensed software. This includes, but is not limited to, 8@computer hardware, computer software, operating systems, and any computer or computing accessories. End user agrees not to hold us responsible for any problems arising from the use of the software.!8B) We shall not in any case be liable for any special, incidental, consequential, indirect or other similar damages arising from any breach of these warranties even if we have been advised of the possibility of such damages.In no case shall our liability exceed the license fees paid for the right to use the licensed software.In the event of invalidity of any provision of this license, the parties agree that such invalidity shall not affect the validity of the remaining portions of this license.&@C# nDBC* $O The Satellite Encyclopedia's Distribution (Winhelp edition only)t0CFD Va     The Winhelp edition of The Satellite Encyclopedia must be copied in an unmodified form and must contain all the files required for an automatic installation. No fee, charge or other compensation may be accepted or requested by anyone without our express written permission.Public Domain disk vendors may not charge a fee for The Satellite Encyclopedia itself. However you may include The Satellite Encyclopedia on a diskette or CD-ROM for which you charge a nominal distribution fee. If it is included on a CD-ROM you must send us a free copy of this CD-ROM. The purchaser of said media must be informed in advance that the fee paid to acquire the media does not relieve said purchaser from paying the registration fee for The Satellite Encyclopedia if said purchaser uses The Satellite Encyclopedia. CI7 <   Operators of electronic Bulletin Board Systems (sysops) may post The Satellite Encyclopedia for downloading by their users without written permission only as long as the above conditions are met. A fee may be charged for access to the BBS as long as no specific fee is charged for downloading The Satellite Encyclopedia files without first obtaining express written permission from ourselves to charge such a fee. This also goes for Internet and Compuserve; other online services must apply for authorization. As far as the French Minitel is concerned, operators are NOT allowed to offer downloading of The Satellite Encyclopedia.FvJ+ $1 The above constitutes the license agreement for The Satellite Encyclopedia winhelp edition. It supersedes any and all previous license agreements.; IJ1s JKLOrder formSvJK5 :>Ƞ$"  Order form without VATJ"M5 8V0.41.001 Name: ______________________________________________________ [Company]: ______________________________________________________ Address: ______________________________________________________ City: ____________________________ Postal Code: ____________ Country: ____________________________ [State]: ________________ Phone: ________________________ Fax: ________________________ Email: ______________________________________________________'KIO1 0Current Winhelp issue: with floppiesat FRF 300 each........................................___x 300 ______Current Winhelp issue: ftp download (internet)at FRF 200 each........................................___x 200 ______4 issues (1 year) Winhelp subscription: with floppiesat FRF 1100 each.......................................___x1100 ______4 issues (1 year) Winhelp subscription: ftp download (internet)at FRF 720 each........................................___x 720 ______"M]< FTOTAL FRF WITHOUT VAT.......................................... ______EU VAT number (if applicable): ______________IO]vJ__________________PAYMENT( ) Check (must be drawn on a French bank in FRF, payable to Tag's Broadcasting Services)( ) Credit card (Visa/MasterCard): Number: ________________________________Expiration: __________ Signature: __________________________________________________ Date: ________________________________IOL0 .SEND TO: TBS BP 158, 14010 Caen cedex 1, France Fax: +33-1-5301-3114 (if you fax, please write in ALL CAPS) email: tbs@TBS-satellite.comD]1 ] 6Order form with VATPL5 :8Ƞ$"  Order form with VAT36 :V0.41.001WARNING: this order form is only applicable if you are in France or in European Union Name: ______________________________________________________ [Company]: ______________________________________________________ Address: ______________________________________________________ City: ____________________________ Postal Code: ____________ Country: ____________________________ [State]: ________________ Phone: ________________________ Fax: ________________________#62 2 Email: ______________________________________________________Current Winhelp issue: with floppiesat FRF 362 each........................................___x 362 ______Current Winhelp issue: ftp download (internet)at FRF 241 each........................................___x 241 ______4 issues (1 year) Winhelp subscription: with floppiesat FRF 1327 each.......................................___x1327 ______4 issues (1 year) Winhelp subscription: ftp download (internet)G< Fat FRF 868 each........................................___x 868 ______TOTAL FRF (including 20.6% VAT)................................ ______PAYMENT( ) Check (must be drawn on a French bank in FRF, payable to Tag's Broadcasting Services)( ) Credit card (Visa/MasterCard): Number: ________________________________Expiration: __________ Signature: __________________________________________________ Date: ________________________________660 .SEND TO: TBS BP 158, 14010 Caen cedex 1, France Fax: +33-1-5301-3114 (if you fax, please write in ALL CAPS) email: tbs@TBS-satellite.com= Gs1>  sBibliographyG65 :&FrÀ" References/s' (BooksN'7' N Atlas de gographie de l'Espace (Fr)' )Sous la direction de F. Verger, avec Isabelle Sourbs, Raymond Ghirardi et Yvette PalazotSIDES / RECLUS, 1992ISBN 2-86861-080-3 / 2-86912-044-1iB7[' O Encyclopdie Internationale des Sciences et des Techniques (Fr)+$ 1972C[Ɍ' 8O L'escalade du Cosmos (Fr)C % <Patrick MaurelBordas, 1972T-Ɍ`' ZO L'tat des sciences et des techniques (Fr)vP ֍& Sous la direction de Nicolas WitkowskiLa dcouverte, 1991ISBN 2-7071-2069-3F`' >O Fuses et Astronautique (Fr)U0֍q% `Camille Rougeron et Jean BodetLarousse, 1964S,Ď' XO Les fuses et missiles d'aujourd'hui (Fr)ql' Bill Gunston, translated from The Illustrated Encyclopedia of the World's Rockets & MissilesElsevier, 1979ISBN 2-8003-0351-4FĎ' >O Grand Atlas de l'Espace (Fr)L'l % NUniversalis, 1988ISBN 2-85229-910-0 6M&Y' LO Le Guide des Lanceurs Spatiaux (Fr)hB & Serguei GrichkovTessier & Ashpool Ltd, 1992ISBN 2-9094-6700-7sLY4' O History of Liquid Rocket Engines - Development in the United States (Eng)pJ& Stephen E. DoyleAmerican Astronautical Society 1992ISBN 0-87703-350-1I"4' DO L'Homme, l'Air et l'Espace (Fr)yTf% Charles Bollfis, Henry Beauboir, Camille Rougerondition de l'illustration, 1965_8' pO Matra Marconi Space Earth Observation Directory (Eng)6f$ $1993/94 editiona:\' tO Matra Marconi Space European Spacecraft Directory (Eng)8$ (3rd edition, 1992^7\' nO Matra Marconi Space World Spacecraft Directory (Eng)6($ $1993/94 editionJ#r' F Rception TV par satellites (Fr)Z4(& hRen BessonDunod, Paris, 1992ISBN 2-10-001462-5Br' 6O Rockets into Space (Eng)jDx& Frank H. WinterHarvard University Press, 1990ISBN 0-674-77660-7D' : La science au prsent (Fr)Y4x% hEncyclopdia Universalis, 1992ISBN 2-85229-501-6_8t' pO Les systmes de tlcommunications par satellite (Fr)oI& G. Maral, M. Bousquet, J. ParesMasson, Paris, 1982ISBN 2-225-75284-2R+t5' VO Les trente premires annes du CNES (Fr)|V& Claude Carlier and Marcel GilliLa documentation franaise, 1994ISBN 2-11-003206-5lE5' O L'univers satellite, Guide pratique de la rception satellite (Fr)nH& Edition 91/92Media Presse Information (MPI), 1991ISBN 2-9505754-0-4nG' O The Illustrated Encyclopedia of the World's Rockets & Missiles (Eng)kEd& Bill GunstonSalamander Books Ltd, London, 1979ISBN 0-517-26870-1F' >O Word Radio TV Handbook (Eng)Dd% >1993 editionBillboard BooksV/D' ^O WRTH Satellite Broadcasting Guide 1994 (Eng)X2& dBart KuperusBillboard BooksISBN 0-8230-5954-5V/D' ^O WRTH Satellite Broadcasting Guide 1995 (Eng)X2J& dBart KuperusBillboard BooksISBN 0-8230-5955-3&p# ;J' ((OPaper periodicals;p' (O Air & Cosmos (Fr)5$ "ISSN 1240-3113Fa' >O Arianespace Newsletter (Eng)5$ "ISSN 0984-84527a'  O Infosat (Ger)5$ "ISSN 0933-6907AC' 4O Megahertz Magazine (Fr)5x$ "ISSN 0755-4419AC' 4O Revue des Tlcoms (Fr)5x$ "ISSN 0183-8636?-' 0O Satellites Infos (Fr)/ \$ ISSN n/aD-' :O Satellite TV Magazine (Fr)5\$ "ISSN 0985-1542A' 4O Sciences et Avenir (Fr)/ E$ ISSN n/a=' ,O TELE-satellit (Ger)5E$ "ISSN 0943-9137= ' ,O Tl Satellite (Fr) 6/ ;$ ISSN n/a& a# @;' 2(OElectronic periodicalsG a' @O Jonathan's Space Report (Eng)_5G* $jBy Jonathan McDowell <jmcdowell@cfa.harvard.edu>9' $O MediaScan (Eng)R(G* $PFrom Radio Sweden <wood@stab.sr.se>`92' rO Space news from Aviation Week & Space Technology (Eng)W-* $ZBy Henry Spencer <henry@zoo.toronto.edu>?2' 0O Space News InNet (Fr)OH1 2By Jean Etienne <etiennj@interpac.be>http://www.sat-net.com/space-news/O(' PO Satellite Journal International (Eng)S)H* $RContact: <71165.2032@compuserve.com>V/@' ^O South Scanner Satellite Services Chart (Eng)T** $TBy Robert Smathers <roberts@nmia.com>>@' .O Space Calendar (Eng)Y/+* $^By Ron Baalke <baalke@kelvin.jpl.nasa.gov>9d' $O SpaceNews (Eng)V,+* $XBy John A. Magliacane <kd2bd@amsat.org>Bd' 6O Spacewarn Bulletin (Eng)~1 2From National Space Science Data Center <sardi@nssdc.gsfc.nasa.gov>http://nssdc.gsfc.nasa.gov/spacewarn/spacewarn.html=' ,O SAT News Desk (Eng)S);* $RBy Peter C. Klanowski <pck@lynet.de>C~' 8O TELE-satellite News (Eng)T*;* $TBy Martyn Williams <martyn@twics.com>?~1O] I\zAcknowlegdmentK\5 :.FrÀ"  Acknowledgment( 0 .9 eIn this section we want to thank all those who collaborated to improve The Satellite Encyclopedia. Please also check the compatible software section.4 \\ '  Co-authorsV&(  0 0L㭄؀>ɉJean-Jacques SerraGunter Krebs8\  ' "O Special thanks4  # " Curt Swinehart8  V + $Curt is our information center! When something is going on related to satellite somewhere in the world, he's back with the press releases. Curt also monitors activity on the Internet. He is a vital resource to TSE! You may contact him at cswineha@emerald.tufts.eduD   $ @ Tele Satellite InternationaluV ; , &A bimonthly satellite magazine edited in Munich, Germany. It consists of 200+ 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 satellite TV! For further details about Tele Satellite International have a look at their web site: http://www.tele-satellite.com& a #  B;  ' 6O Data providers - Thanks!a z% eWe used to have here a long list of contributors, but not very accurate, many names were missing. We want to thank every contributor. We will not publish such a list anymore.9 1SVersionsEz5 :"FrÀ"  Versions&# (q#P_  68 VersionRelease dateComments)[@o#R_[@z240.41.00106 Jun 1998normal updateBAu#_,.uP00.40.002May 1998First edition of the World Satellite CDW[@Ao#_240.40.00128 Feb 1998New launch vehicle sections, new future satellites/programs9ABo#r_240.39.00127 Nov 1997Normal update, more addresses(ACo#P_240.38.00220 Oct 1997minor update@BCo#_240.38.00128 Aug 1997new addresses section, normal updateyCDp#_240.37.00129 May 1997global update, more future satellites (especially LEOs & Ka-band)more organization addresses_CFs#_240.36.00125 Jan 1997New pricing scheme for both 2 editions: WWW and WinhelpAdded WWW pointers to each satellite programs when available New and updated launcher information Now over 300 footprints (including preliminary data)7DFo#n_240.35.00131 Aug 1996Important footprint upgradevFGv#_2 40.34.00110 Apr 1996First release of TSE Winhelp with TSE Online(http://www.tele-satellite.com/tse/online/)WFHu#_240.33.00115 Dec 1995Extension of the launcher section and the launch calendar (including details on future satellites)Added numerous EIRP mapsTSE can be called from WinOrbit 2.7 and upper (freeware tracking program)G J#̀)_002e։㰭=H0.32.0011 Sep 1995First in History sectionNumerous launch programs added especially AtlasSupport mailing list availableNew EIRP maps=HGKs#_020.31.0011 Jun 1995New CDROM distribution policy (compilers must send me a free copy)No Minitel distribution allowedAdded numerous EIRP mapsIntroduced the full International Designator numbers JLt#_020.30.0011 Mar 1995Included a calendar of future launchesIncluded a list of spacecrafts on the Clarke BeltMaps were redrawn and North-American satellites were addedSTS flights coverage was improvedAdded order forms and credit card registration=GKfMo#z_020.22.0011 Dec 1994New license agreement, data updateCLNo#_240.21.00120 Sep 1994Fixes numerous typos due to translation2fMNo#d_240.20.00112 Sep 1994Translation in EnglishJNsOp#_020.10.0011 Sep 1994Thematic index for missionsLast French versionNvq# _020.09.0011 Jul 1994IntsOvzegrity checking with NASA's catalog numberTechnical data for geostationary telecommunication satellitesIsO.o#_020.08.0011 Jun 1994Introduction of NASA's catalog & launch number.vˁo#\_240.07.00113 Apr 1994First STS missionsB.}p#_020.06.0017 Feb 1994Modification of the mapsBug correctionCˁ/o#_240.05.00117 Jan 1994License agreement, first public release$}S" D/1ICompatible softwarePS5 :8FrÀ"  Compatible software''  The Satellite Encyclopedia winhelp edition is compatible with some windows based software. This enables you to call your favorite satellite reference from those fine products with a single keystrike! Here is a list of those products with a description:0 >'  Logsat1 0This is a shareware tracking program which offer numerous goodies to ease your everyday monitoring. It handles an elements database and cares about the updates. It provides a logbook and a callbook to hold your records. It also provides antenna and propagation utilities.You can get the full information on Logsat from http://www.logsat.com or contact Logsat by mail: support@logsat.com3 >,'  SatmasterP1 0This is a satellite tool box gathering all you need to install a satellite dish and design a reception station (from personal dish to ground earth station). It can calculate link budgets (analog, digital, SCPC) so as all kind of look angles. Moreover giving parameters of your reception station it will tell you the diameter of the dish you need to get a signal. It is ready to use with a database of towns around the globe.You can get more information from here: http://arrowe.merseyworld.com/ (where a freeware version is available) or contact its author at djsteph@arrowe.u-net.com2 ,߉' O WinOrbit1 0+This is a program for computing artificial Earth-satellite position and visibility, with the Amateur Radio Satellite operator in mind. Quite simple to use it can operate with several different calculation models. Moreover it is freeware!You can find the full documentation of Winorbit at http://www.sat-net.com/winorbit/ so as download the software. You can contact its author at cgregory@uiuc.eduN߉1MHow to use this encyclopedia?Z%M5 :LFrÀ"  How to use this encyclopedia?;' (O What's hypertext?nM& If you never used a help file before and want to know more about them, press F1Hypertext 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.?[' 0O Using hypertext linksY( 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 prog[Yram it belongs to (if it exists of course) by clicking the upper left icon.J#[' FO Organization of the encyclopediatNY& 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.AX' 4 Search of specific datai$ The easiest way to find something is to question the searching tool. If your search is unsuccessful either your keyword is unknown or your question wasn't understood: try to express it differently. You also can browse through indexes.5X'  Other linksY)i0 0R %e&py؉Glossary of termsHelp on printing?616v= TSE (franais)@ v5 :FrÀ"  TSEg+6< FW  )񹉂The Satellite Encyclopedia est sous copyright de Tag's Broadcasting Services, tous droits rservs, 1993-1998.Ce document fut nomm second meilleur shareware franais 1995 catgorie Home and Hobby par Ziff Davis.A lire galement en franais:Licence d'utilisation - Bons de commandeK$v(' H Philosophie de cette encyclopdie< d2 2㭄؉ Cette encyclopdie a pour but de rassembler de l'information dans un document simple d'emploi. Les contributions sont bien venues.... Vous pouvez mme devenir un co-auteur de TSE comme Jean-Jacques Serra qui s'occupe de la section des lanceurs! Cette encyclopdie est publie tous les 3/4 mois environ. Ce logiciel n'est donc pas une version finale.Si vous tes un spcialiste du satellite, un oprateur ou un constructeur satellite, une organisation spatiale, nous serons trs heureux d'entrer en contact avec vous. Si pour une raison ou une autre vous pensez que vos satellites ne sont traits correctement, comprenez que nous ne travaillons qu' partir d'information que nous possdons. Si vous voulez amliorer les choses, envoyez nous directement vos informations.(, &)񹉂Si vous tes l'auteur d'un livre ou logiciel en rapport avec les satellites ou si votre organisation publie un magazine ou lettre d'information en rapport avec l'Espace et le satellite, consultez notre offre spciale dans la licence.9d' $O La rgle du jeu_'8 >O   Ce logiciel est en libre essai, c'est un shareware: vous pouvez donc l'essayer gratuitement pendant SEPT jours, ensuite vous devez soit vous enregistrer soit l'effacer. La version shareware est limite 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 lments.Si vous utilisez The Satellite Encyclopedia aprs la priode d'essai ou des fins commerciales, vous DEVEZ vous enregistrer. La version enregistre comprend:&># V#3#6Fr Le fichier complet 15 Mo avec:F>3#6&r 390 cartes PIREe2?3#6dr la liste des satellites sur l'orbite de ClarkevC3#6r un calendrier des lancements futurs et des satellites concernsL?3#62r les programmes Russes1>6 :)񹉂 uP0TSE est comme un magazine: la version shareware est comparable un magazine que vous lisez en kiosque. Achetez ce magazine est comme enregistrer votre version de TSE. Et si vous enregistrez TSE avec> l'abonnement vous obtenez 4 numeros de TSE conscutifs... ce qui revient s'abonner un magazine traditionnel. Bref c'est pas sorcier! Reportez vous la licence pour tous les dtails.Nouveau ! The Satellite Encyclopedia est maintenant disponible dans une nouvelle dition: World Satellite CD.wQ& Bien que toutes les prcautions aient t prises lors de la compilation de ces informations, l'diteur n'est pas responsable des erreurs ou omissions. De mme l'diteur ne peut tre tenu responsable de consquences de l'utilisation des informations contenues dans cette encyclopdie. Merci de nous signaler toute erreur ou omission.`9>' r Comment vous procurer la dernire version disponible?N4 8 )񹉂 1/ En vous enregistrant: voir la licence.2/ En la tlchargeant:g1 0?Internet: la liste des sites ftp se trouve http://www.tele-satellite.com/tse/ Le site ftp primaire se trouve ftp://ftp.tele-satellite.com/pub/tse/&# :g' &O Support en ligne> JeLe site Internet de TSE est http://www.tele-satellite.com/tse/ La version WWW de TSE se trouve a http://www.tele-satellite.com/tse/online/ Nous avons mis en place un certain nombre de listes de diffusion. Pour vous abonner (gratuitement) a la liste publique envoyez un mail:To: majordomo@tags1.dn.netSubject: noneBody: subscribe tse-pubUne liste consacre au developpement de TSE est disponible sous le nom de tse-dev1 ' O ContactoBW- *TBSBP 158, 14010 Caen cedex 1, Francetbs@TBS-satellite.com~S+ & SVP: prcisez la version de l'encyclopdie dont vous disposez actuellement.L%W!' JO Comment apporter des complments?=^# 4Pour cela, fournissez:!y ( Votre nom et prnom ou pseudo (qui seront cits dans la section des remerciements)Votre adresse postale (et lectronique si vous en avez une)L'information avec sa source et dateLa version de l'encyclopdie dont vous disposez actuellement^= - (/Assurez vous que nous recevons les communiqus de presse de votre compagnie par fax ou email:fax: +33-1-5301-3114Email: press@TBS-satellite.comFy  1J  Licence d'utilisationR=  5 :<FrÀ"  Licence d'utilisationzF O 4 8Q (BBon de commandeBon de commande (si vous tes hors de France)1  ' O LicenceaO 'F Z     L'utilisation de The Satellite Encyclopedia est soumise aux termes et conditions suivantes:The Satellite Encyclopedia est protge par les lois sur les droits d'auteurs. Vous ne devez faire aucun changement ou modification The Satellite Encyclopedia. Vous ne devez pas la dcompiler, la dsassembler, ou lui appliquer toute autre rtrotechnique. Aucune reproduction autorise (pas de mirroring web).Vous pouvez utiliser The Satellite Encyclopedia pour une priode d'essai 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'valuer gratuitement ce logiciel pendant sept jours. Si vous utilisez The Satellite Encyclopedia par la suite ou des FINS COMMERCIALES, vous DEVEZ acqurir une licence d'utilisation. Sinon vous devez effacer le logiciel.G n' @ Combien cote une licence?r'@% Voir les bons de commande ci-dessus! L'enregistrement donne droit une version personnelle du logiciel avecn@= :V#ng@3#6Fr Le fichier complet 15 Mo avec:F@@3#6&r 390 cartes PIREe2g@A3#6dr la liste des satellites sur l'orbite de ClarkevC@A3#6r un calendrier des lancements futurs et des satellites concernsLAA3#62r les programmes RusseskAdB% Un abonnement (4 numros) est disponible. Pour les tarifs de l'dition web, voir la page WWW d'accueil.;AB' ( Offre spciale:dBD'  Si vous tes une socit qui publie un priodique papier ou lectronique concernant les satellites (en Franais ou Anglais), vous pouvez obtenir gratuitement une licence d'utilisation avec mise jour pendant un an contre un abonnement gratuit d'un an votre publication.Si vous tes l'auteur d'un livre concernant les satellites (en Franais ou Anglais), vous pouvez obtenir gratuitement une licence d'utilisation avec mise jour pendant 1 an contre un exemplaire gratuit de votre livre.T)B F+ $S Si vous tes l'auteur d'un shareware concernant les satellites (en Franais ou Anglais), vous pouvez obtenir gratuitement une licence d'utilisation avec mise jour pendant 1 an contre une licence d'utilisation gratuite de votre shareware.Votre demande peut tre refuse sans justification.$D-H' L'utilisateur final ne se voit pas accorder le titre de proprit du logiciel sous licence. On lui fournit une licence non-exclusive pour utiliser, tous moments, le logiciel sur un unique ordinateur ou station de travail. De plus, il s'engage ne dupliquer ce logiciel que pour en faire une sauvegarde. Ceci s'applique galement l'dition web.Tag's Broadcasting Services peut inclure le nom et les informations de contact de l'acheteur dans les supports promotionnels de The Satellite Encyclopedia.& FSH# 2 -HH'  GarantieSHJ& Bien que toutes les prcautions aient t prises lors de la compilation de ces informations, l'diteur n'est pas responsable des erreurs ou omissions. De mme l'diteur ne peut tre tenu responsable de consquences de l'utilisation des informations contenues dans cette encyclopdie.Nous ne garantissons pas que le logiciel sous licence rpondra vos attentes ou que le logiciel comme les informations seront sans erreurs. La garantie ne couvre aucune copie du logiciel altre ou modifie.}H?M' Nous ne sommes pas responsable des problmes ou dommages causs par le logiciel sous licence qui pourrait rsulter de son utilisation. Ceci comprend, mais ne se limite pas au matriel informatique, logiciel informatique, systme d'exploitation, et autre accessoire informatique. 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Aucune taxe, frais ou autre compensation ne doit tre accepte ou demande par personne sans notre accord crit exprs.Les vendeurs de disques du Domaine Public ne peuvent pas facturer une taxe pour The Satellite Encyclopedia en elle-mme. Toutefois, vous pouvez inclure The Satellite 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'acqureur du dit support doit tre inform l'avance que la somme verse pour obtenir le support ne relve pas ledit acqureur de payer les droits d'utilisation de The Satellite Encyclopedia si l'utilisateur l'utilise.-O= H    Les oprateurs des serveurs et BBS (les sysops) peuvent mettre The Satellite Encyclopedia la disposition de leurs utilisateurs sans permission crite tant qu'ils respectent les conditions ci-dessus. Une redevance peut tre perue pour accder au systme mais aucune taxe spcifique ne peut tre facture pour le tlchargement des fichiers de The Satellite Encyclopedia sans l'obtention pralable de notre accord crit exprs pour facturer une telle somme. Ceci s'applique galement Internet et Compuserve; les autres systmes en ligne doivent demander une autorisation. En ce qui concerne le Minitel, les fournisseurs de service NE sont PAS autoriss mettre The Satellite Encyclopedia en ligne.+ $ Ce qui prcde constitue la licence de The Satellite Encyclopedia. Elle annule et remplace toutes les versions antrieures.Cن1ن(΋Jean-Jacques SerraO(5 :6%"  Jean-Jacques SERRALنt4 61 Contact: JJ.Serra@wanadoo.frJean-Jacques Serra is a 43 years old French citizen. He devotes most of his free time to astronautics since the age of 17. He is responsible of the launch vehicle section.He lives in eastern part of the Pyrenees mountains, a region famous for its solar ovens. He carries out research on new materials especially those aimed to extrem temperatures.Reading of articles and information sorting relative to rockets and satellites consume most of his hobby time. He also enjoys his natural environment.Z/(΋+ $_ J'ai 43 ans et je m'intresse l'astronautique et son histoire depuis l'age de 17 ans. Je vis l'est des Pyrnes, dans une rgion o se trouve la plus grande concentration de fours solaires. J'y fais de la recherche sur les matriaux nouveaux et plus particulirement ceux qui sont exposs des tempratures extrmes.La lecture d'articles, le classement d'informations sur les fuses et les satellites occupent une grande partie de mes loisirs. Pour le reste, je profite de mon environnement, la dcouverte de la montagne est un sujet inpuisable.= t 1J% TGunter KrebsI΋T5 :*%"  Gunter Krebs $ /Gunter is very busy writing his diploma thesis, so he had no time to prepare his presentation. His "biography" will be included in the next release.<TK' *O External resourcesj1 2Email: gk@smoky.ikf.physik.uni-frankfurt.dehttp://www.rz.uni-frankfurt.de/~gkrebs/space/space.htmlDK*1 * Countries of originU 5 :B?˝Ā" States and OrganizationsK$*ʎ' H Statistics (as of early Jun 1998)Gy#€kj  0 D CountrySatelliteDebrisTotal(including non Earth orbit)y ʎo#kj u#0kj"㉕U$*Argentina5056#Ҁ2kj" &,Australia628#Ҁ,kj"7 &Brazil7076f#Ҁ0kj"xW "(Canada15116#Ҁ4kj"6" *China23102125f#Ҁ8kj"  ,CIS132725983960=#Ҁ<kj"(*06Czechoslovakia404#ހ.kj(p$ "(Egypt101=u#Ҁ2kj"㱭+"*France301646$&#Hkj4㱭+ 24<BFrance / Germany202u#Ҁ2kj" $*Germany12115&Z#Ҁ2kj" &,Hong Kong303#Ҁ.kj"&€ &India17421Z#Ҁ2kj"b# &,Indonesia808##Ҁ,kj"ΝE &Israel202#Ҁ,kj"xE$Italy7310#T#Ҁ2kj"b (Japan6355122#Ҁ:kj";XJ&(.4Korea (South)404T#Ҁ2kj"L>  &,Luxemburg707-#ހ4kj(- (.Malaysia202#Ҁ,kj" &Mexico505-c#ހ0kj($*Norway202#ހ:kj(k8{$&.4Philippines202c#Ҁ0kj"ހ$*Portugal1016#Ҁ*kj"qǹ$Spain505#Ҁ,kj"ˆt &Sweden6066r #Ҁ0kjr ")`$*Thailand303 #ހ0kj(.$*Turkey202 r  #Ҁ@kj"R׀(*28United Kingdom16117% X #ҀJkj"㹌ל&(2>United States78932394069   {#ƀkj X z #Ҁ6kj" ?I*"$*0Arab States505  #Ҁ6kj"4"",Europe23206231Ez  #kjF<RH(㐮):CIxrt|International (Eutelsat, Inmarsat & Intelsat)76076  #Ҁ(kj"ķ+€"NATO808   {#ƀkj #  #Fkj  & 6 Total248862288800$   " 1  1z Z A R ) "0N Countries of origin3   '  CountriesoR 2 >#JIMM㉕U7Q_txW w6"6"p$ 㱭+ &‰b#ΝExEb;XJL> -㬹.鉂'ݓk8{މqn͉ˆt)`.eCR׉㹌לArgentinaAustraliaBrazilBulgariaCanadaCISChileChinaCzechoslovakiaEgyptFranceGermanyHong KongIndiaIndonesiaIsraelItalyJapanKorea (South)LuxemburgMalaysiaMexicoNetherlandsNorwayPakistanPhilippinesPortugalSpainSwedenThailandTurkeyUkraineUnited KingdomUnited States& X # 72 '   Organizations9X 4 l#rIMM0 ?I*4"*><ķ+‰nArab StatesEurope (ESA)InternationalNATO& Z # : 4 1 v ArgentinaFZ 5 :$?˝Ā" ArgentinaB  # >CONAE is the national agency< X ' *O External resourcesC ' 8http://www.conae.gov.ar/<X ' *O Satellite launched+  $ 19905 7 * $ ULusat+ b $ 1996F7 2 4(oK&V˓FWMusatSAC B+b $ 19979  * $S_ENahuel 1A6 B '  Main program4  v ) ""%ǀNahuel: B  1   B AustraliaFv  5 :$?˝Ā" Australia  & DAustralia owns an old launch site (Woomera) from which it's first satellite was launched. Has created a space comity on 21 Sep 1986.=  ' ,O Satellites launched+ @ $  @ v 19676  M@ * $caωWresat+@ x@ $ 19708M@ @ * $쉂Oscar 05+x@ @ $ 1985L@ 'A 2 44__Optus A1Optus A2+@ RA $ 19878'A A * $_Optus A3+RA A $ 1992LA B 2 44__Optus B1Optus B2+A ,B $ 19948B dB * $_Optus B36,B B '  Main program3 dB B ) "Optus7B C 1rC GC H BrazilCB GC 5 :?˝Ā" BrazilC D 2 2-D \The national space research center INPE (Instituto Nacional de Pesquisas Espacias) was created on 3 Aug 1961. Brazil has a launch program: VLS.<GC KD ' *O External resources>D D ' .http://www.inpe.br/=KD D ' ,O Satellites launched+D D $ 1985FD 7E * $8bBrasilsat A1 (SBTS A1)+D bE $ 1986F7E E * $8bBrasilsat A2 (SBTS A2)+bE E $ 19904 E F * $eOUDove+E 2F $ 19935 F gF * $IWSCD 1+2F F $ 1994FgF F * $8"cBrasilsat B1 (SBTS B1)+F G $ 1995FF IG * $8#cBrasilsat B2 (SBTS B2)+G tG $ 1998<IG G * $$$cBrasilsat B36tG G '  Main program7G H ) "CDBrasilsat9G VH 1hVH H I BulgariaEH H 5 :"?˝Ā" BulgariaVVH "I 1 2D o7U=Bulgaria launched a satellite with the help of the CIS. Member of Intersputnik.<H ^I ' *O Satellite launched+"I I $ 1981I^I I * $>>㉂Intercosmos Bulgaria 13007I J 1 rc J LJ CanadaCI LJ 5 :?˝Ā" CanadaC J L . *+D4"The Canadian Space Agency was created on 1 Mar 1989.Canada is an associate member of ESA since 1978. This means that Canada does not have the same rights and obligations as a full member. For instance, Canada is not participating in the Scientific Program or in the Technological Research Programme of ESA. Both these programs are part of the mandatory activities which are financed by the full members pro rata of their gross national product (GNP).Canada was the first country to develop a national telecommunication system.<LJ L ' *O External resourcesBL M ' 6http://www.space.gc.ca/=L JM ' ,O Satellites launched+ M uM $ 1962:JM M * $ H6Alouette 1+uM M $ 1965:M N * $ I6Alouette 2+M ?N $ 19696 N uN * $TIsis 1+?N N $ 19716 uN N * $TIsis 2+N O $ 1972CN DO * $2?QQAnik A1 (Telesat 1)+O oO $ 1973CDO O * $2@QQAnik A2 (Telesat 2)+oO O $ 1975CO , * $2O , I AQQAnik A3 (Telesat 3)+O W $ 19763 , * $SCTS+W $ 1978C * $2jQQAnik B1 (Telesat 4)+ # $ 1982b0 2 4`QQQQAnik D1 (Telesat 5)Anik C3 (Telesat 6)+# $ 1983C * $2QQAnik C2 (Telesat 7)+  $ 1984C a * $2QQAnik D2 (Telesat 8)+ $ 1985Ca ς * $2QQAnik C1 (Telesat 9)+ $ 1991d2ς ^ 2 4dQQQQAnik E2 (Telesat 10)Anik E1 (Telesat 11)+ $ 19923 ^ * $ySCTA+ $ 19958  * $gTRadarsat+ J $ 19966  * $LwMSAT 17J '   Main programsR 7 >6"֋AlouetteAnikIsis6 ? 1? K ChileB 5 :?˝Ā" Chile(? % D= ' ,O Satellites launched+  $ 1995: K * $ 3д%Fasat Alfa6 1c Æ $ ChinaB K Æ 5 :?˝Ā" China  & -DIn 1958 Mao tze-tung decided to launch a program named "mission 581" directed by Quian Xue-sen. The first Chinese rocket was launched in 1960 (so as the first missile). When the CIS stopped helping China the spatial program changed drastically. Two organizations were created (in Shangai and Beijin) that managed to launch their first satellite. Since 1986 China offers launch services to foreign firms.=Æ ' ,O Satellites launched+ $ 1970I 0 * $>!(v&Dong Fang Hong 01 (Mao 1)+ [ $ 1971I0 * $>"(v&Dong Fang Hong 02 (Mao 2)+[ ω $ 1975Y b : D#(v&$(v&%(v&Dong Fang Hong 03 (Mao 3)Dong Fang Hong 04 (Mao 4)Dong Fang Hong 05 (Mao 5)+ω $ 1976n<b 2 4x&(v&'(v&Dong Fang Hong 06 (Mao 6)Dong Fang Hong 07 (Mao 7)+ & $ 1978I o * $>((v&Dong Fang Hong 08 (Mao 8)+& $ 1981{Ao  : D)(v&&v&&v&Dong Fang Hong 09Dong Fang Hong 10Dong Fang Hong 11+ @ $ 1982A * $.&v&Dong Fang Hong 12+@ $ 1983A * $.&v&Dong Fang Hong 13+  $ 1984J : D&v&&v&&v&Dong Fang Hong 14Dong Fang Hong 15 (STTW 0)Dong Fang Hong 16+ Ǎ $ 1985A  * $.&v&Dong Fang Hong 17+Ǎ 3 $ 1986g5 2 4j&v&&v&Dong Fang Hong 18 (STTW 1)Dong Fang Hong 19+3 Ŏ $ 1987^, # 2 4X&v&&v&Dong Fang Hong 20Dong Fang Hong 21+Ŏ N $ 1988~#  B T&v&&v&&v&&v&Dong Fang Hong 22 (Chinasat 1)Dong Fang Hong 23Dong Fang Hong 24(Feng Yun 1-1)Dong Fang Hong 25 (N  K Chinasat 2)+N E $ 1990 4 K dI&v&&v&&v&&v&&v&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+E _ $ 1991N$4 * $H&v&Dong Fang Hong 34 (Chinasat 4)+_ $ 1992^, 6 2 4X&v&&v&Dong Fang Hong 35Dong Fang Hong 36+ a $ 1993O%6 * $J&v&Dong Fang Hong 37 (Jianbing 93)+a $ 1994x B T&v&&v&('v&'v&Dong Fang Hong 38 (Shijian 4)Dong Fang Hong 39 (Shijian 4-2)Dong Fang Hong 40 (FSW 2)Dong Fang Hong 41+ $ 1996uC 5 2 4 'v&!'v&Dong Fang Hong 42 (Chinasat 7)Dong Fang Hong 43 (FSW 2-3)+ ` $ 1997sA5 2 4"'v&#'v&Dong Fang Hong 44 (Chinasat 6)Dong Fang Hong 45 (FY 2B)+` $ 1998; 9 * $"j)ቂChinastar 17 p '   Main programs<9 ) "&mSDong Fang Hong3 p '  LaunchersE $ ) "89+SChinese launch vehicles4 X 1AX  CIS@ $ 5 :?˝Ā" CIS7X ' !DFor the moment, we name the Russian Federation and the Community of Independant States CIS. All launches by the former USSR are considered as Russian launches. Sorry for this simplification.CIS has a very complex space organization that we can't simply summarize here.< ' *O External resourcesN' Y ' Nhttp://arc.iki.rssi.ru/Welcome.html7 '   Main programsY %qi~񢝉L݉/{~wGܝ!&!ְM"ᇏ3xAjQv.<:뉢㼨ԟl?Ձ+܉ -ꉂY뉂d퉂xZUx< 剂BionCosmosEkranElektronEorsatExpressFotonGalsGeizerGeo-IKGlonassGonetsGorizontIntercosmosLuchMeteorMolniyaNadezhdaOceanParusPrognozProtonRadugaResursRorsatSputnikStatsionarStrelaTsikada3 '  LaunchersB  0 0$mKaKRokotStart? D 1 D J CzechoslovakiaK 5 :.?˝Ā" Czech RepublicD J 3 4D o7U=Formerly called Czechoslovakia, before the country splitted.Developed a scientific program with the CIS. Member of Intersputnik.= ' ,O Satellites launchedjGJ # Two of these satellites are not officially registered by the country+  $ 19788 T * $L$Magion 1+  $ 19898T * $M$Magion 2+ $ 19918  * $N$Magion 3+ E $ 19958 } * $O$Magion 4+E $ 19968} * $P$Magion 56  '  Main program4 J ) "$aMagion6 18A.! EgyptB J 5 :?˝Ā" Egyptd? 2 % ~DFormerly called Czechosl 2 J ovakia, before the country splitted.= o ' ,O Satellites launched+2 $ 1998;o * $"WNilesat 1017  1 N"  O ( FranceC O 5 :?˝Ā" France  = D VUD  4"4"4"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.<O y ' *O External resources>=  ' .http://www.cnes.fr/=y  ' ,O Satellites launched+  $ 1965L k 2 44;SQUAstrix (A1)FR 1+  $ 1966>k  * $(QSDiapason (D1A)+  $ 1967Z( Y 2 4P㦼㧼Diadme 1 (D1C)Diadme 2 (D1D)+  $ 1970=Y  , ("8GVMikaPole+  $ 1971d* P : DT<JPPU2y`Tournesol (D2A)EoleAurole 1+ { $ 19726 P  * $ITSret 1+{  $ 19739  * $3y`Aurole 2+ @ $ 1974; { * $"?a׉Symphonie 1+@  $ 1975V{ N R t?1qw )JT@a׉RKUStarlettePollux (D5A)Castor (D5B)Sret 2Symphonie 2Aura (D2B)+ y $ 19777 N  * $o5Signe 3+y  $ 19819  * $4y`Aurole 3+ ? $ 1984: y * $  eTelecom 1A+?  $ 1985:y  * $ eTelecom 1B+ $ 19866  ? * $㥇Spot 1+ j $ 1988K? 2 42ew~WTelecom 1CTDF 1+j $ 1990G ' 2 4*㦇w~WSpot 2TDF 2+ R $ 1991J' 2 404`U8eSaraTelecom 2A+R $ 1992J  2 409e>`UTelecom 2BS80T+ < $ 1993Z  : D@:㧇xټArsneSpot 3Stella+< $ 1995a' " : DNh휭fN:eHelios 1ACeriseTelecom 2C+ M $ 1996:" * $ ;eTelecom 2D+M $ 19986 * $㨇Spot 47  '   Main programsG Z wڜqehۢ&SkArgosAuroleHeliosSpotSretSymphonieTDFTelecom3  '  Launchers5 ( ) "ÀDiamant8 ` 1 .##`  _I GermanyD(  5 : ?˝Ā" GermanyE` LA W |D 4"4"4"4"  o7U=In the 30ies, a space organization (Verein fr 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 de LA ( veloped the V2 missile. In 1962 Germany started cooperating with European countries when the COPERS was created.Germany has been part of ESRO and ELDO. It is now member of ESA. Has created in July 1989 a federal space agency: DARA (Deutsche Agentur fr RaumfahrtAngelegenheiten). Member of Intersputnik.< A ' *O External resources=LA A ' ,http://www.dlr.de/=A B ' ,O Satellites launched+A -B $ 1969<B iB * $$KUAzur (GRS A)+-B B $ 19709iB B * $&>Dial-Wika+B B $ 1972?B 7C * $*kAeros 1 (GRS B)+B bC $ 1974N7C C 2 48l?a׉Aeros 2Symphonie 1+bC C $ 1975;C D * $"@a׉Symphonie 2+C AD $ 1983JD D 2 40u쉂b竉Oscar 10Spas 1+AD D $ 19849D D * $=AMPTE IRM+D E $ 19877 D QE * $mԐTvsat 1+E |E $ 1989HQE E 2 4,ʗ>TmԐDFS 1Tvsat 2+|E E $ 1990FE 5F 2 4(r#W˗>TRosatDFS 2+E `F $ 199185F F * $ITubsat A+`F F $ 19925 F F * $̗>TDFS 3+F #G $ 1993;F ^G * $"d竉Orfeus-Spas+#G G $ 1994O^G G 2 4:Ie竉Tubsat BCrista-Spas+G H $ 19955 G 8H * $lJTGFZ 1+H cH $ 199798H H * $MEquator S7cH H '   Main programs@H _I L h˜0`pۢ&mѾAerosDFS KopernikusSafirSymphonieTubsatTvsat: H I 1N$I I L Hong KongF_I I 5 :$?˝Ā" Hong Kong=I J ' ,O Satellites launched+I GJ $ 19909J J * $kAsiasat 1+GJ J $ 19948J J * $b Apstar 1+J K $ 19959J GK * $kAsiasat 2+K rK $ 19969GK K * $i"鉂Apstar 1A+rK K $ 1997NK $L 2 48"鉂kApstar 2RAsiasat 36K ZL '  Main programE$L L 0 0*ttXX%ApstarAsiasat6ZL L 1> #%L M ( IndiaB L M 5 :?˝Ā" IndiaL 4N D VD  #ZXgF}(Indian space agency is the ISRO (Indian Space Research Organisation) created in 1969. A Ministry of Space was created in 1972 and India has its own launch vehicles. ISRO has a commercial arm named Antrix.=M qN ' ,O Satellites launched+4N N $ 19759qN N * $GAryabhata+N O $ 1979:N :O * $ e艂Bhaskara 1+O eO $ 1980A:O O * $.~OaRohini 1B (RS E2)+eO O $ 1981g-O D : DZEc&SO D L e艂Rohini 2 (RS D1)AppleBhaskara 2+O o $ 19828D * $sG@cInsat 1A+o Ҁ $ 1983T" & 2 4DFtG@cRohini 3 (RS D2)Insat 1B+Ҁ Q $ 1988J& 2 40YTuG@cIRS 1AInsat 1C+Q Ɓ $ 19908 * $vG@cInsat 1D+Ɓ ) $ 19916 _ * $YTIRS 1B+) $ 1992K_ Ղ 2 42㇊D􉂃G@cSross 3Insat 2A+ $ 19938Ղ 8 * $G@cInsat 2B+ c $ 1994J8 2 40_G_TSross C2IRS P2+c ؃ $ 1995J " 2 40YTG@cIRS 1CInsat 2C+؃ M $ 19966 " * $_TIRS P3+M $ 1997J 2 40G@cYTInsat 2DIRS 1D7 / '   Main programsq, E ZXc:Gw㿓S㐋 퉂㑲BhaskaraInsatIRSRohiniSross3 / Ӆ '  LaunchersU, ( ) "X#ISRO launch vehicles(SLV 3, ASLV, PSLV): Ӆ b 1&b IndonesiaF( 5 :$?˝Ā" Indonesia=b ' ,O Satellites launched+  $ 19769 I * $:9Palapa A1+ t $ 19779I * $:9Palapa A2+t ؇ $ 19839  * $2:9Palapa B1+؇ < $ 1987: v * $ 有Palapa B2P+< $ 1990:v ۈ * $ 有Palapa B2R+  $ 19929ۈ ? * $5:9Palapa B4+ j $ 1996N? 2 48]:9^:9Palapa C1Palapa C2+j $ 1997<  * $$L M@Cakrawarta 16 U '  Main program4  ) ">؀Palapa7U 1V'  | IsraelC  5 :?˝Ā" IsraelL' O % NDIsrael has a space agency since 1983= ' ,O Satellites launched+O $ 19887 * $fOffek 1+  $ 19907 P * $fOffek 2+ { $ 19957 P * $fOffek 3+{ ݌ $ 19966  * $3 Amos 16݌ I '  Main program3  | ) "5Offek6I 1t( C ItalyB | 5 :?˝Ā" Italy 8 >yD4"  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).< $ ' *O External resources< ` ' *http://www.asi.it=$ ' ,O Satellites launched+` ȏ $ 1964;  * $"7San Marco 1ȏ  | +ȏ : $ 1967; u * $"7San Marco 2+: $ 1971;u * $"7San Marco 3+  $ 1974; A * $"7San Marco 4+ l $ 19777 A * $cBSirio 1+l $ 1988; * $"7San Marco 5+ 4 $ 19919 m * $oGItalsat 1+4 $ 19927 m * $4Temisat+ $ 19937 1 * $KItamsat+ \ $ 1996Y1 : D>>WoGTTS 2SAXItalsat 27\ '   Main programsW C 7 >@vrJj_zItalsatSan MarcoSirio6 y 1V)y V JapanB C 5 :?˝Ā" Japany > J=D    Japan has an important space program conducted by NASDA (National Space Development Agency) and ISAS (Institute of Space and Aeronautical Science).< ' *O External resourcesb4 5 . ,hhttp://www.nasda.go.jp/http://www.isas.ac.jp/= r ' ,O Satellites launched+5 $ 19706 r * $~gOOhsumi+ $ 1971K I 2 42oCeTansei 1Shinsei+ t $ 19725 I * $[@=TDenpa+t $ 19748 * $oCTansei 2+ 7 $ 1975O 2 4:zWㅾTTaiyoKiku 1 (ETS 1)+7 $ 1976= * $&rWUme 1 (ISS 1)+  $ 1977J B ToCㆾTT*߉Tansei 3Kiku 2 (ETS 2)Himawari 1 (GMS 1)Sakura 1 (CS 1A)+ $ 1978J \ B Tq2sW·ቂq2Kyokko (Exos A)Ume 2 (ISS 2)Yuri 1 (BSE)Jikiken (Exos B)+ $ 1979\*\ 2 4T~NAyame 1 (ECS 1)Hakucho (Corsa B)+  $ 1980S! a 2 4BoCTansei 4Ayame 2 (ECS 2)+ $ 1981z@a  : D㈾TTKiku 3 (ETS 4)Hinotori (Astro A)Himawari 2 (GMS 2)+ 1 $ 1982> o * $(ㇾTKiku 4 (ETS 3)+1 $ 1983y?o  : D~J.K.Sakura 2A (CS 2A)Tenma (Astro B)Sakura 2B (CS 2B)+ > $ 1984x> : D|㉂q2TYuri 2A (BS 2A)Ohzora (Exos C)Himawari 3 (GMS 3)+> $ 1986s9 T : Dr㉂r& TO뉂Yuri 2B (BS 2B)Ajisai (EGP)Fuji 1A (JAS 1A)+  $ 1987l2T : DdV$㉾TGinga (Astro C)Momo 1A (MOS 1A)ETS 5+  $ 1988^, t 2 4Xu.v.Sakura 3A (CS 3A)Sakura 3B (CS 3B)+ $ 1989Gt 4 B Tq2ㆺ2OTAkebono (Exos D)Jcsat 1 4 C Superbird A1Himawari 4 (GMS 4)+ _ $ 1990{4 & L hㇺ2W$   1{x*  ( Korea (South)JV  5 :,?˝Ā" Korea (South)=  ' ,O Satellites launched+ F $ 19928 ~ * $Kitsat A+F  $ 19938~  * $Kitsat B+ $ 1995: F * $ Y Koreasat 1+ q $ 1996:F * $ Y Koreasat 27q '   Main programsF ( 0 0,G.rKitsatKoreasat: b 1L+b  LuxemburgF( 5 :$?˝Ā" Luxemburg=b ' ,O Satellites launched+  $ 19888 H * $(~Astra 1A+ s $ 19918H * $(~Astra 1B+s $ 19938  * $(~Astra 1C+ 9 $ 19948 q * $(~Astra 1D+9 $ 19958q * $(~Astra 1E+ $ 19968 7 * $)~Astra 1F+ b $ 199787 * $)~Astra 1G6b '  Main program3  ) " ܜAstra9 < 1x ,<  @@ MalaysiaE  5 :"?˝Ā" Malaysiah<  ) "2!Malaysia plans to launch a micro satellite in the middle of 1997 (on Ariane) and the second in 2000< N ' *O Satellite launched+ y $ 1996LN  2 44Measat 1Measat 26y @ '  Main program @  4  @@ ) "*Measat7 @ w@ 1Lǀ-w@ @ %C MexicoC@@ @ 5 :?˝Ā" Mexico=w@ @ ' ,O Satellites launched+@ "A $ 1985N@ pA 2 48FFMorelos 1Morelos 2+"A A $ 1993=pA A * $&L2Solidaridad 1+A B $ 1994=A @B * $&L2Solidaridad 2+B kB $ 19969@B B * $- Unamsat 27kB B '   Main programsJB %C 0 04tz6ww퉂MorelosSolidaridad< B aC 1d ~.aC C E NetherlandsH%C C 5 :(?˝Ā" Netherlands=aC C + &$D4"Member of ESA<C "D ' *O External resourcesBC dD ' 6http://www.sron.ruu.nl/="D D ' ,O Satellites launched+dD D $ 19743 D D * $DANS+D *E $ 19834 D ^E * $v>UUIRAS+*E E $ 1996S#^E E 0 0FxESAX (considered as Italian)7E F 1<ǀ5/F VF aH NorwayCE VF 5 :?˝Ā" NorwayIF F + &<D4"Member of ESA since 1987.<VF F ' *O External resourcesEF G ' <http://www.spacecentre.no/<F \G ' *O Satellite launched+ G G $ 19976 \G G * $gOThor 2CG H ' 8O Satellite bought in orbit+G +H $ 19926 H aH * $fOThor 19+H H 1P~˂0H H I PakistanEaH H 5 :"?˝Ā" Pakistan]H aI % DThe Pakistan Space and Upper Atmosphere Research Commission (SUPARCO) was founded in 1961.<H I ' *O Satellite launched+aI I $ 19906 I I * $(Badr A< I :J 15W1:J J 3L PhilippinesHI J 5 :(?˝Ā" Philippines<:J J ' *O Satellite launched+J J $ 1997;J $K + & nMabuhay 1DJ hK ' :O Satellites bought in orbit+$K K $ 1996:hK K * $ 有Palapa B2P+K K $ 1997;K 3L * $"#oGorizont 299K lL 1˂2lL L MM PortugalE3L L 5 :"?˝Ā" Portugal<lL L ' *O Satellite launched+L M $ 19935 L MM * $VPosat6M M 1WR3M M Q SpainB MM M 5 :?˝Ā" SpainEM N + &4D4"Spain is part of ESA.<M FN ' *O External resources= N N ' ,http://www.inta.es=FN N ' ,O Satellites launched+N N $ 19747 N "O * $mgSIntasat+N MO $ 1992;"O O * $"c͉Hispasat 1A+MO O $ 1993;O * $"c͉Hispasat 1BO MM +O 7 $ 19958 o * $#UPMsat 1+7 $ 1997:o Ԁ * $ K&Minisat 016 '  Main programGԀ Q 0 0.&̀AHispasatMinisat7 1s-4 ˁ SwedenCQ ˁ 5 :?˝Ā" Sweden=  + &$D4"Member of ESA=ˁ E ' ,O Satellites launched+ p $ 19866 E * $1ĉViking+p т $ 19896  * $yTele X+т 2 $ 19925  g * $1TFreja+2 $ 1994J g ܃ * $@Sirius 1 (bought in orbit)+  $ 19958܃ ? * $ ~Astrid 1+ j $ 19978? * $Sirius 27j ل '   Main programs4 ) "ڢSirius9ل F 1R5F ^ ThailandE 5 :"?˝Ā" Thailand<F Dž ' *O Satellite launched+ $ 19939Dž + * $FˉThaicom 1+ V $ 19949+ * $GˉThaicom 2+V $ 19979 * $HˉThaicom 36 ) '  Main program5 ^ ) "v胀Thaicom7) 1-6 ؇ J TurkeyC^ ؇ 5 :?˝Ā" Turkey=  ' ,O Satellites launched+؇ @ $ 1994: z * $ mvmTurksat 1B+@ $ 1996:z ߈ * $ nvmTurksat 1C6  '  Main program5 ߈ J ) "]cKTurksat8 1:7 Ɖ ϊ UkraineDJ Ɖ 5 : ?˝Ā" UkrainekF 1 % DUkraine has a space agency: National Space Agency of Ukraine (NKAU)=Ɖ n ' ,O Satellites launched+1 $ 19956 n ϊ * $>w|Sich 1?  1 M8 Y  United KingdomKϊ Y 5 :.?˝Ā" United Kingdomw  7 >D  4"Has created the BNSC (British National Space Center), a space agency in 1985. United Kingdom is member of ESA.<Y C ' *O External resourcesS, ' Xhttp://www.open.gov.uk/bnsc/bnschome.htm4 C ʌ ' O Satellites+ $ 1962>ʌ 3 * $(d$tAriel 1 (UK 1)+ ^ $ 1964>3 * $(e$tAriel 2 (UK 2)+^ Ǎ $ 1967>  * $(f$tAriel 3 (UK 3)+Ǎ 0 $ 19699 i * $ ȉSkynet 1A+0 $ 1971l2i : Dd ȉ'S*g$tSkynet 1BProspero (X3)Ariel 4 (UK 4)+ + $ 1974? B T~5 ȉYu<щh$t6 ȉSkynet 2AMiranda (X 4)Ariel 5 (UK 5)Skynet 2B++ ׏ $ 1979> ! * $(i$t׏ ! ϊ Ariel 6 (UK 6)+׏ L $ 19817 ! * $͓F̉Uosat 1+L $ 19834 * $v>UUIRAS+ $ 1984L Y 2 44ΓF̉nUosat 2AMPTE UKS+ $ 19889Y * $ ȉSkynet 4B+ $ 1989J 2 2 40S ȉBSB 1Skynet 4A+ ] $ 1990p.2 B T\ϓF̉ГF̉S ȉUosat 3Uosat 4BSB 2Skynet 4C+] $ 19917 / * $ѓF̉Uosat 5+ Z $ 1994J/ 2 40djdjSTRV 1ASTRV 1B+Z $ 19989  * $ ȉSkynet 4D7 ? '   Main programsm( E ZPhڜJaS@~ꠉArielBSBSkynetSTRVUosat3 ? '  Launchers9  ) " XـBlack Arrow> V 19V United StatesJ 5 :,?˝Ā" United StatesqLV  % DThe US space program can't be described here... it requires a whole book!< M ' *O External resources? ' 0http://www.nasa.gov/7M '   Main programs   ԁ YSwڜZSMZS[Y\do݌RElS =9ąoS㸈R4j牂2ӉqPdIx≂ LS 9%k:uЇ QdI=Š>ܝAMSArgosASCATSAuroraComstarColumbiaDashDBSDiscovererDMSPDSCSDSPEchoEchostarEssaExplorerFleetsatcomGalaxyGEGGSEGlobalstarGoesGPSGstarHeaoIDSCPIMEWSIridiumKHLacrosseLageos    ԁ SUg;S tAc{A޲ȉTɑl̑̑6S@8S㐫۴WI4~W#1Heos 2TD 1AEsro 4+ $ 19755 _ * $UXTCos B+ $ 1977b( L : DP㯃\VTϵaESA-Geos 1ISEE 2Meteosat 1+ w $ 1978KL 2 42piV㰃\OTS 2ESA-Geos 2+w $ 19795 " * $scTCat 1+ M $ 1981p." B T\еaucTڰ_vcTMeteosat 2Cat 3Marecs ACat 4+M $ 1983N 6 2 48r2نExosatEutelsat 1F1+ a $ 1984Q6 2 4>چ˴UEutelsat 1F2Marecs B2+a $ 1987<  * $$܆Eutelsat 1F4+ D $ 1988R   2 4@ѵa݆Meteosat 3Eutelsat 1F5+D  $ 1989b( # : DPҵavtމMeteosat 4OlympusHipparcos+ N $ 1990<#  * $$Eutelsat 2F1+N  $ 1991{9 <@ B Trӵa_QTEutels <@ at 2F2Meteosat 5ERS 1Eutelsat 2F3+ g@ $ 1992P<@ @ 2 4<IEutelsat 2F4Eureca 1+g@ @ $ 1993:@ A * $ ԵaMeteosat 6+@ GA $ 1995YA A : D>`QT~Hotbird 1ERS 2ISO+GA A $ 19969A B * $Hotbird 2+A /B $ 1997<B B J dxյatYtYHotbird 3Meteosat 7Maqsat HMaqsat BYes+/B B $ 19989B C * $Hotbird 47B PC '   Main programsAC C Z eSvSRH(<F^n2_kSCatEsroERSEutelsatHeosMarecsMeteosatOTS3 PC D '  Launchers4 C RD ) "2!Ariane> D D 1<D D InternationalJRD D 5 :,?˝Ā" InternationalgD F ? LDCIx㐮):o7U=o7U=Here are the satellites developed by an international organization, either Intelsat or Inmarsat. Intersputnik isn't in here because the satellites are owned by the CIS... but this will change as soon as Intersputnik launches its first satellite.Numerous other programs were developed by multi-national partners but are still considered nationally.<D F ' *O External resourcesT-F G ' Zhttp://www.un.or.at/OOSA_Kiosk/index.html=F MG ' ,O Satellites launched+G xG $ 1965<MG G * $$rĉIntelsat 101+xG G $ 1966<G H * $$ĉIntelsat 201+G FH $ 1967l2H H : DdĉĉĉIntelsat 202Intelsat 203Intelsat 204+FH H $ 1968<H I * $$ĉIntelsat 302+H DI $ 1969T"I I 2 4DĉĉIntelsat 303Intelsat 304+DI I $ 1970l2I /J : DdĉĉĉIntelsat 306Intelsat 307Intelsat 308+I ZJ $ 1971T"/J J 2 4DĉĉIntelsat 402Intelsat 403+ZJ J $ 1972T"J -K 2 4D ĉ!ĉIntelsat 404Intelsat 405+J XK $ 1973<-K K * $$#ĉIntelsat 407+XK K $ 1974<K K * $$$ĉIntelsat 408+K &L $ 1975U#K {L 2 4Fĉ Intelsat 401Intelsat 4A01+&L L $ 1976={L L * $& Intelsat 4A02+L M $ 1977=L KM * $& Intelsat 4A04+M vM $ 1978V$KM M 2 4H  Intelsat 4A03Intelsat 4A06+vM M $ 1980<M 3N * $$WĉIntelsat 502+M ^N $ 1981T"3N N 2 4DVĉXĉIntelsat 501Intelsat 503+^N N $ 1982T"N 1O 2 4DYĉZĉIntelsat 504Intelsat 505+N \O $ 1983T"1O O 2 4D[ĉ\ĉIntelsat 506Intelsat 507+\O O $ 1984T"O ; 2 4D]O ; RD ĉ^ĉIntelsat 508Intelsat 509+O f $ 1985l2; Ҁ : DdĉĉĉIntelsat 510Intelsat 511Intelsat 512+f $ 1988<Ҁ 9 * $$ĉIntelsat 513+ d $ 1989T"9 2 4Dĉ ĉIntelsat 515Intelsat 602+d $ 1990l2 O : Dd ĉ ĉjGIntelsat 603Intelsat 604Inmarsat 2F1+ z $ 1991BO B TjG ĉ ĉjGInmarsat 2F2Intelsat 605Intelsat 601Inmarsat 2F3+z ) $ 1992R { 2 4@jGƉInmarsat 2F4Intelsat K+) $ 1993<{ * $$ĉIntelsat 701+ $ 1994T" a 2 4DĉĉIntelsat 702Intelsat 703+ $ 1995l2a : DdĉĉĉIntelsat 704Intelsat 705Intelsat 706+ # $ 1996R J dĉ)rGĉ*rG+rGIntelsat 707Inmarsat 3F1Intelsat 709Inmarsat 3F2Inmarsat 3F3+# $ 1997R J dĉ,rGĉĉĉIntelsat 801Inmarsat 3F4Intelsat 802Intelsat 803Intelsat 804+ $ 1998T"  2 4D-rGĉInmarsat 3F5Intelsat 8067 < '   Main programsf( > LP㐮):CIx ֋qInmarsatIntelsatISEESarsat5< ׇ 19=ׇ  ˋ NATOA  5 :?˝Ā" NATO=ׇ U ' ,O Satellites launched+ $ 19706 U * $a }Nato 1+ $ 19716  * $b }Nato 2+ B $ 19767  y * $CdNato 3A+B $ 19777 y ۉ * $CdNato 3B+  $ 19787 ۉ = * $CdNato 3C+ h $ 19847 = * $CdNato 3D+h ʊ $ 19917  * $CdNato 4A+ʊ , $ 19937  c * $CdNato 4B6, '  Main program2 c ˋ ) "ugNato@ 1d!> [ The Clarke BeltPˋ [ 5 :8NJ" Geostationary Orbit6 ' O Introductioni[ 2 , &This chart keeps track of the satellites on the Clarke Belt. The transponder loading of the telecommunication satellites listed here can be found at http://www.satcodx.comFirst column is the slot of the satellite above the Equator; negative values stand for degrees West and positive for degrees East. Second column is the inclination of the spacecraft in degrees i.e. the angle between the satellite's plan 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. Furthermore MC stands for Military Communications, MW for Military Warning. The "Frequency bands" column relates the downlink bands in which the satellite can be active, blank means unknown. The "Comment" column contains internal information, such as the "!" sign which indicates t 2 ˋ his data is unconfirmed or variable.* \ ' @2 N #4QN20 :JhjSlotInc.SatelliteMis.Freq. bandsComment-\ < #RZQN20"ceM24<>T-180DSCS 3-03MUHF, S, X!0N - #R`QN20 ""|W68@B\-178.03.99UHF 4MUHF, X, EHF1<  #RbQN20 ""ĉDFNP^-177.02.03Intelsat 513CC, Ku9-  #RrQN20".68@BH-17713.0Goes 02WS!wavering but alive.  #R\QN20 ""OM8:BDX-174.30.20TDRS 5MS, C, Ku. #R\QN20 ""OM8:BDX-171.01.94TDRS 7MS, C, Ku; #RvQN20"_4oމ:<HJV-1577.15Raduga 21C/MC, X!drifting East) #RRQN20 ""]<>FHN-139.00.07Aurora 2CC* #RTQN20 ""q->@HJP-137.00.09Satcom C1CC6 #RlQN20".68@BX-1350.27Goes 09WVHF, L, Swavering* #RTQN20 ""t->@HJP-135.00.10Satcom C4CC- #RZQN20"ceM24<>T-135DSCS 3-05MUHF, S, X!* #RTQN20 ""_b㉀>@HJP-133.00.05Galaxy 1RCC* n #RTQN20 ""s->@HJP-131.00.09Satcom C3CC3 b #RfQN20 "" ceM>@HJ`-130.06.26DSCS 3-01MUHF, S, X!)n X #RRQN20 "";up<>b X ˋ FHN-125.00.03Galaxy 5CC)b B #RRQN20 ""?up<>FHN-123.00.03Galaxy 9CC'X * #RNQN20 ""=HW68@BJ-122.90.07SBS 5CKu,B  #RXQN20 ""ƵBDLNT-120.02.11Telstar 303CC1*  #RbQN20"68@B^-120Milstar 1-1MUHF, Ka, EHF,  #RXQN20 ""VR^Z@BJLT-119.00.03Echostar 1CKu,   #RXQN20 ""WR^Z@BJLT-119.00.03Echostar 2CKu)  #RRQN20 ""q:<DFN-118.80.25Tempo 2CKu.  #R\QN20 ""F>@HJX-116.80.07Morelos 2CC, Ku5  #RjQN20"QQ68@BJ-1130.94Anik C1CKu!drifting East5 #RjQN20 ""L2FHPRf-113.00.05Solidaridad 2CL, C, Ku, #RXQN20 ""QQ:<DFT-111.10.07Anik E1CC, Ku3 #FfQN20 "L2DFLNb-109.20.05Solidaridad 1CL, C, Ku, p #RXQN20 ""QQ:<DFT-107.30.07Anik E2CC, Ku+ \ #RVQN20 ""Lw8:BDR-106.50.06MSAT 1CL, Ku0p M #R`QN20 ""|W68@B\-106.04.17UHF 6MUHF, X, EHF*\ 8 #RTQN20"S24<>H-10514.8ATS 3CVHF!old0M 5@ #R`QN20"]8:BDJ-1058 5@ ˋ 5.61Aurora 1CC!wavering)8 A #RRQN20 "":T:<DFN-105.11.39Gstar 1CKu)5@ B #RRQN20 ""=T:<DFN-105.00.09Gstar 4CKu.A B #R\QN20"㝖.68@BX-1050.31Goes 10WVHF, L, S& B C #RLQN20" c鉀.08:F-103DSP 3-5MS, X!)B D #RRQN20 ""rRU46>@N-103.00.05GE 1CC, Ku'C E #RNQN20 ""~9T68@BJ-101.20.05DBS 1CKu*D F #RTQN20 ""iS68@BP-101.00.05ASC 2CC, Ku+E G #RVQN20 ""S 8:BDR-101.00.07AMSC 1CL, Ku'F pH #RNQN20 ""〽9T68@BJ-101.00.03DBS 3CKu'G XI #RNQN20 ""9T68@BJ-100.80.03DBS 2CKu&pH ?J #RLQN20 "" KU46>@H-100.00.12ACTSCKa:XI :K #RtQN20" D>ቀDFNP`-99.73.82Fleetsatcom 7MUHF, Xwavering5?J 0L #RjQN20".46>@V-984.06Goes 07WVHF, L, Swavering-:K M #RZQN20" zz<>FHV-97.00.05Telstar 5CC, Ku-0L N #RZQN20" b㉀<>FHV-95.00.03Galaxy 3RCC, Ku*M N #RTQN20" c㉀<>FHP-95.00.03Galaxy 8iCKu, N #RXQN20" bBDLNT-92.01.24Brasilsat A2CCN ˋ ,N #RXQN20" =up:<DFT-91.00.05Galaxy 7CC, Ku0 #R`QN20" 㑑)BDLN\-89.00.05Telstar 402RCC, Ku( ӂ #RPQN20" rRU24<>L-87.00.05GE 3CC, Ku( #RPQN20" rRU24<>L-85.00.05GE 2CC, Ku-ӂ #RZQN20"$c>@HJV-830.14Brasilsat B3CC, X2 #RdQN20" d@BJL`-83.00.06Spacenet 3RCL, C, Ku* #RTQN20" -<>FHP-81.00.68Satcom K2CKu, u #RXQN20" bBDLNT-79.02.61Brasilsat A1CC& \ #RLQN20" =HW46>@H-77.03.86SBS 4CKu*u G #RTQN20" [LX<>FHN-76.09.62Comstar 4CC!5\ = #RjQN20".46>@V-750.32Goes 08WVHF, L, Swavering&G $ #RLQN20" =HW46>@H-74.10.07SBS 6CKu:=  #RtQN20" FHP-72.00.05Nahuel 1ACKu/ #R^QN20" "cBDLNZ-70.00.05Brasilsat B1CC, X/ #R^QN20" #cBDLNZ-65.00.05Brasilsat B2CC, X+ ֏ #RVQN20" XR^Z>@HJR-61.50.03Echostar 3CKu. #R\QN2֏ ˋ 0" Dh>@HJX-58.00.06Panamsat 5CC, Ku0֏ #R`QN20" ĉBDLN\-55.53.07Intelsat 512CC, Ku/ #R^QN20" jGBDLNZ-55.52.07Inmarsat 2F2CL, C/ #R^QN20" ,rGBDLNZ-54.00.05Inmarsat 3F4CL, C0 #R`QN20" ĉBDLN\-53.00.03Intelsat 706CC, Ku, #RXQN20"ceM02:<R-52DSCS 3-09MUHF, S, X!0 q #R`QN20" ĉBDLN\-50.00.05Intelsat 709CC, Ku- _ #RZQN20" OM68@BV-49.09.81TDRS 1MS, C, Ku-q M #RZQN20" OM68@BV-47.00.09TDRS 6MS, C, Ku._ < #R\QN20" @h>@HJX-45.00.07Panamsat 1CC, Ku/M , #R^QN20" 8M@BJLZ-43.00.05Panamsat 3RCC, Ku+<  #RVQN20" Eh>@HJR-43.00.09Panamsat 6CKu,,  #RXQN20" ceM02:<R-42DSCS 3-02MUHF, S, X!- #RZQN20" OM68@BV-41.01.14TDRS 4MS, C, Ku0 #R`QN20" ĉBDLN\-40.50.06Intelsat 806CC, Ku0 #R`QN20" ĉBDLN\-37.80.52Intelsat 515CC, Ku( #RPQN20" R*8:BDL-37.50.07Orion 1CKu0 #R`QN20 ˋ " ĉBDLN\-34.50.03Intelsat 601CC, Ku3 #RfQN20" ȉ<>FHb-34.03.17Skynet 4AMUHF, X, EHF0#R`QN20" ĉBDLN\-31.50.04Intelsat 801CC, Ku/#R^QN20" c͉@BJLZ-30.00.05Hispasat 1ACX, Ku/#R^QN20" c͉@BJLZ-30.00.05Hispasat 1BCX, Ku3t#RfQN20" [ĉBDLNb-29.55.79Intelsat 506CL, C, Ku0e#R`QN20" ĉBDLN\-27.50.05Intelsat 605CC, Ku,tR#RXQN20" ˴U<>FHT-26.07.30Marecs B2CL, C*e=#RTQN20" r3x@BJLP-25.00.93Cosmos 2345M0R. #R`QN20" ĉBDLN\-24.50.03Intelsat 603CC, Ku/= #R^QN20" |W46>@Z-24.04.44UHF 7MUHF, X, EHF2.  #RdQN20" E>ቀDFNP`-23.02.16Fleetsatcom 8MUHF, X+  #RVQN20" Ɖ>@HJR-21.50.09Intelsat KCKu0  #R`QN20" ĉBDLN\-21.50.03Intelsat 803CC, Ku,  #RXQN20" Cd8:BDT-20.41.91Nato 4BMUHF, XB #RQN20"ĉ68@BP-18Intelsat 511CC, Ku!drifting West to 29.5W/ #R^QN20" Cd8:BDJ-18.25.01Nato 3DMXwavering0@#R`QN20@ˋ " ĉBDLN\-18.00.03Intelsat 705CC, Ku,A#RXQN20" Cd8:BDT-18.02.14Nato 4AMUHF, X/@B#R^QN20" jGBDLNZ-17.02.64Inmarsat 2F4CL, C-AC#RZQN20" vEo68BDV-16.00.28Luch 0MCUHF, Ku/BD#R^QN20" *rGBDLNZ-15.81.69Inmarsat 3F2CL, C2CyE#RdQN20" |W46>@P-15.03.61UHF 3MUHF, Xwavering-DgF#RZQN20" J7<>FHV-14.00.09Express 1CC, Ku,yETG#RXQN20" -x@BLNT-13.51.13Cosmos 2291MCC,gFAH#RXQN20"ceM02:<R-12DSCS 3-06MUHF, S, X!:TGJL`-8.00.05Telecom 2AC/MC, X, Ku%F-7Nilesat 101CKu$/JK#RHQN20 " c鉀*,46B-7DSP 3-4MS, X!2KL#RdQN20"9e<>JL`-5.00.03Telecom 2BC/MC, X, Ku2KM#RdQN20";e<>JL`-5.00.24Telecom 2DC/MC, X, Ku'LN#RNQN20" 3 68@BJ-4.000.07Amos 1CKu2MO#RdQN20" ȉ:<DF`-1.01.53Skynet 4CMUHF, X, EHF-N#FZQN20Oˋ ĉ>@FHV-1.00.03Intelsat 707CC, Ku&O#RLQN20"fO46>@H-0.80.10Thor 1CKu&}#RLQN20"gO46>@H-0.80.05Thor 2CKu'e#RNQN20"mԐ68@BJ-0.60.09Tvsat 2CKu.}T#R\QN20 "Եa68@BX00.28Meteosat 6WVHF, L, S;eP#RvQN20"յa46>@V1.19Meteosat 7WVHF, L, S!drifting East1TB#RbQN20":e:<HJ^3.00.03Telecom 2CC/MC, X, Ku#P&#RFQN20 " c鉀(*24@4DSP 3-3MS, X!-B#RZQN20 "02:<T4Milstar 1-2MUHF, S, Ka!'&#RNQN20"68@BJ4.80.03Sirius 2CKu'#RNQN20"68@BJ5.20.08Sirius 1CKu+Њ#RVQN20">@HJR7.00.05Eutelsat 2F4CKu,#RXQN20"@BJLT10.00.05Eutelsat 2F2CKu,Њ#RXQN20"g4oމ:<FHT12.02.25Raduga 29MCC, X,#RXQN20"`4oމ:<FHT12.05.99Raduga 22MCC, X+#RVQN20"+x>@JLR12.01.66Cosmos 2224MWS)m#RRQN20":<DFN13.00.09Hotbird 1CKu)c#RRQN20":<mcˋ DFN13.00.09Hotbird 2CKu)mM#RRQN20":<DFN13.00.07Hotbird 3CKu)c7#RRQN20":<DFN13.00.03Hotbird 4CKu,M$#RXQN20"@BJLT13.00.10Eutelsat 2F1CKu)7#RRQN20"oG:<DFN13.20.55Italsat 1CKa,$#RXQN20"@BJLT16.00.05Eutelsat 2F3CKu'#RNQN20"oG46>@H16.4?Italsat 2CKa?(#RPQN20"(~8:BDL19.20.07Astra 1ACKu(#RPQN20"(~8:BDL19.20.21Astra 1BCKu(#RPQN20"(~8:BDL19.20.07Astra 1CCKu(#RPQN20"(~8:BDL19.20.05Astra 1ECKu&h#FLQN20)~68>@H19.20.05Astra 1FCKu&I#FLQN20)~68>@H19.20.03Astra 1GCKu,h6#RXQN20"݆@BJLT21.52.91Eutelsat 1F5CKu)I #RRQN20"̗>T24<>N23.50.05DFS 3CKu, Ka06#R`QN20"-rG>@HJV24.52.8Inmarsat 3F5CL, Cnew, #RXQN20"܆@BJLT25.53.70Eutelsat 1F4CKu- #RZQN20"_鉀<>FHV26.00.05Arabsat 2ACC, Ku ˋ (#RPQN20"(~8:BDL28.20.07Astra 1DCKu) #RRQN20"˗>T24<>N28.50.07DFS 2CKu, Ka-#RZQN20"`鉀<>FHV31.00.05Arabsat 2BCC, Ku*#RTQN20"mvm<>FHP31.20.05Turksat 1BCKu-#FZQN20ĉ>@FHV33.04.29Intelsat 510CC, Ku1#RbQN20"#o>@HJ^34.05.24Gorizont 19CL, C, Ku4#RhQN20"f4oމ:<FHT35.03.32Raduga 28MCC, Xwavering&n#RLQN20"O?46>@H36.00.27Gals 1CKu&U#RLQN20"O?46>@H36.00.18Gals 2CKu%n; #RJQN20"w~W24<>F36.00.06TDF 2CKu1U- #RbQN20"#o>@HJ^40.00.24Gorizont 31CL, C, Ku*;  #RTQN20"nvm<>FHP42.00.05Turksat 1CCKu9-  #RrQN20 "#o24<>R43Gorizont 20CL, C, Ku!drifting East-  #RZQN20"ƭ\<>HJV49.01.54Raduga 1-3MCC, X>  #R|QN20 " ȉ68@B\524.11Skynet 4DMUHF, X, EHF!drifting East: #RtQN20" ȉ:<DF`53.04.52Skynet 4BMUHF, X, EHFwavering.  @#R\QN20"#o>@HJX53.00.26Gorizont 32CC, Ku @ˋ *@#RTQN20"G@c8:BDP55.00.06Insat 2RCS, C/ @A#R^QN20"ĉ@BJLZ57.00.03Intelsat 703CC, Ku+@B#RVQN20 "ceM.08:P57DSCS 3-04MUHF, S, X!/AC#R^QN20" ĉ@BJLZ60.00.05Intelsat 604CC, Ku+BD#RVQN20 "ceM.08:P60DSCS 3-08MUHF, S, X!/CE#R^QN20" ĉ@BJLZ62.00.05Intelsat 602CC, Ku,DF#FXQN20)rG>@FHT63.61.36Inmarsat 3F1CL, C/EvG#R^QN20"ĉ@BJLZ64.00.09Intelsat 804CC, KuDF{H#RQN20 "ӵa02:<R64Meteosat 5WVHF, L, S!drifting to Indian ocean.vGjI#R\QN20"jG@BJLX65.00.61Inmarsat 2F3CL, C/{HZJ#R^QN20"ĉ@BJLZ66.00.03Intelsat 704CC, Ku-jIHK#RZQN20"Ch<>FHV68.50.05Panamsat 4CC, Ku,ZJ5L#RXQN20"4oމ:<FHT70.00.88Raduga 32MCC, X)HKM#RRQN20"|W24<>N71.53.52UHF 2MUHF, X.5LN#R\QN20"|W24<>X71.54.06UHF 5MUHF, X, EHF2MO#RdQN20">>ቀBDLN^72.013.4Fleetsatcom 1MUHF, X!2N #RdQN20"Zĉ@BJL`72.06.39Intelsat 505CL, C, KuO ˋ ,O#RXQN20"ݏ7:<DFR72.512.3Marisat 3CL, C!, #RXQN20"G@c8:FHT74.00.37Insat 2AC/WS, C(ς#RPQN20"Q:<DFL76.01.29Electro 1WL,#RXQN20""鉀:<DFT77.00.10Apstar 2RCC, Ku,ς#RXQN20"mEo46@BT77.01.25Luch 1MCUHF, Ku,#RXQN20"Hˉ:<DFT78.50.05Thaicom 3CC, Ku,#RXQN20"Gˉ:<DFT78.50.09Thaicom 2CC, Ku+o#RVQN20"2x>@JLR80.00.34Cosmos 2319MCC,\#RXQN20"J7:<DFT80.00.09Express 2CC, Ku,oI#RXQN20"vG@c8:FHT83.00.12Insat 1DC/WS, C4\>#RhQN20"4oމ:<FHT85.01.84Raduga 30MCC, Xwavering4I3#RhQN20"OM46>@T85.33.69TDRS 3MS, C, Kuwavering1>%#RbQN20"#o>@HJ^90.01.82Gorizont 28CL, C, Ku+3#RVQN20"8:BDR91.50.05Measat 1CC, Ku.%#R\QN20"G@c8:BDX93.50.09Insat 2CCS, C, Ku,#RXQN20"G@c8:FHT93.50.18Insat 2BC/WS, C.܏#R\QN20"#o>@HJX96.52.36Gorizont 27CC, Ku0#R`QN܏ˋ 20"&v&JLTV\98.01.99Dong Fang Hong 26CC)܏#RRQN20"dɉ8:BDN99.02.55Ekran 20CUHF-#RZQN20" k<>FHV100.50.03Asiasat 2CC, Ku2#RdQN20" #o@BJL`103.03.10Gorizont 25CL, C, Ku0#R`QN20" #'v&LNVX\104.00.72Dong Fang Hong 45W)#RRQN20" k<>FHN105.50.08Asiasat 1CC/o#R^QN20" L M@BDLNZ107.70.14Cakrawarta 1CL, S*Z#RTQN20" 有>@HJP108.00.09Palapa B2RCC0oK#R`QN20" ㉀8:BDL110.00.09Yuri 3NCKuwavering)Z5#RRQN20" ㉀8:BDL110.00.05Yuri 3ACKu?0K&#R`QN20" ㉀8:BDL110.00.13Yuri 3BCKuwavering(5#RPQN20" R8:BDL110.00.09Bsat 1ACKu1&#RbQN20" &v&LNVX^110.52.18Dong Fang Hong 25CC(#RPQN20" ㆺ28:BDL112.00.73Jcsat 1CKu-#RZQN20" ^:9<>FHV113.00.07Palapa C2CC, Ku.#R\QN20" ZIz>@HJX115.51.55Spacenet 1CC, Ku.#R\QN20" [Iz>@HJX115.50.72Spacenet 2CC, Ku+#RVQN20ˋ " Y >@HJR116.00.05Koreasat 1CKu+#RVQN20" Y >@HJR116.00.07Koreasat 2CKu)#RRQN20" 5:9<>FHN118.00.07Palapa B4CC-r#RZQN20" Fˉ<>FHV120.00.07Thaicom 1CC, Ku-`#RZQN20" T46>@V120.03.02GMS 4WUHF, L, S)rJ#RRQN20"S,.68@122Bsat 1BCKutesting/`:#R^QN20" #o@BJLZ122.01.41Gorizont 30CC, Ku+J&#RVQN20" ㉺28:BDR124.00.07Jcsat 4CC, Ku1:#RbQN20" "'v&LNVX^125.00.05Dong Fang Hong 44CC+& #RVQN20" ㈺28:BDR128.00.05Jcsat 3CC, Ku- #RZQN20" e4oމ<>HJV128.04.25Raduga 27MCC, X3  #RfQN20" ) :<DFb132.00.07N Star ACS, C, Ku, Ka)  #RRQN20" i"鉀<>FHN134.00.05Apstar 1ACC3  #RfQN20" * :<DFb136.00.09N Star BCS, C, Ku, Ka(  #RPQN20" b :<DFL138.00.07Apstar 1CC- #RZQN20" T46>@V140.00.43GMS 5WUHF, L, S2 #RdQN20" #o@BJL`140.04.24Gorizont 22CL, C, Ku,@#RXQN20" @ˋ _Sk7@BJLT144.00.05Superbird CCKu2zA#RdQN20" #o@BJL`145.04.31Gorizont 21CL, C, Ku%@`B#RJQN20" c鉀,.68D145DSP 3-2MS, X!-zANC#RZQN20" n<>FHV146.00.05Mabuhay 1CC, Ku,`B;D#RXQN20" :<DFT148.00.03Measat 2CC, Ku+NC'E#RVQN20" ㊺28:BDR150.00.03Jcsat 5CC, Ku-;DF#RZQN20" ]:9<>FHV150.50.07Palapa C1CC, Ku)'EF#RRQN20" _:<DFN152.01.83Optus A3CKu(FG#RPQN20" ㇺ28:BDL154.00.05Jcsat 2CKu+FH#RVQN20" %Ag:<DFR155.73.66Leasat 5MP, X,GI#RXQN20" _:<DFT156.00.05Optus B3CL, Ku4HJ#RhQN20" OBDLNd158.00.05Superbird A2CX, Ku, Ka,IK#RXQN20" _:<DFT160.00.03Optus B1CL, Ku/JL#R^QN20" #o@BJLZ161.01.76Gorizont 29CC, Ku4KM#RhQN20" OBDLNd162.00.07Superbird B1CX, Ku, Ka)LrN#RRQN20" _:<DFN164.03.65Optus A2CKu.MaO#R\QN20" Ah>@HJX169.00.05Panamsat 2CC, Ku7rNe#RnQN20"|W(*2aOeˋ 4N169UHF 8MUHF, X, EHF!drifting West3aOY#RfQN20" A>ቀDFNP`172.011.6Fleetsatcom 4MUHF, X!0eJ#R`QN20" ĉBDLN\174.00.05Intelsat 802CC, Ku,Y7#RXQN20"ceM02:<R175DSCS 3-07MUHF, S, X!0J(#R`QN20" ĉBDLN\177.00.03Intelsat 702CC, Ku/7#R^QN20" +rGBDLNZ178.01.81Inmarsat 3F3CL, C/(#R^QN20" jGBDLNZ179.01.82Inmarsat 2F1CL, C0#R`QN20" ĉBDLN\180.00.03Intelsat 701CC, Ku$" 1N1W?NȇT+) "VȠ$To view this page you need to register&Nȇ# 11z@BI"ȇB' Dpage intentionally left blank?1=z߁(A͈ЂTo be launchedLB͈5 :0NJ" Launch Schedule2 '  Jun 1998Z͈YD#X,5 02STS 91 (Mir 9)q!ʉP#pB5. hOp㉀09Thor 3 (Delta 2 7925){+YEP#pV5. ĉyj18Intelsat 805 (Atlas 2AS AC-153)eʉJ#d65" 'CM20Resurs O1 (Zenit)w'E!P#pN5. K㰭=H30Eutelsat 3F1 (Atlas AC-130)mP#p:5. &)~㉓g??Astra 2A (Proton)m !M#j@5( Sp㉂??GPS BIIR-06 (Delta 2)ojP#p>5. DJ{؉bnW"??Ikonos 1 (Athena 2)fЌJ#d85" ^]??Milstar (Titan 4B)Ujj#5b 'CM=JU -)l] ډW??Okean O2-N1 (Zenit)Fasat BravoLLMSIRIS Safir 1Techsat 2 Tmsatp ЌP#p@5. 㐫GKT??Orbcomm (Pegasus XL)s#rP#pF5. -9+S??Sinosat (Long March 3B)2 '  Jul 1998Br0J#d5" 01STRV 2 (http://www.te.plk.af.mil/tsx5home/strv2/jpl.htm)u1D#Xb5 09STS 88 (International Space Station 1-2A)k!0J#dB5" Gb㉀10Galaxy 10 B(1st delta 3)q!P#pB5. ㋺2㰭=H30Jcsat 6 (Atlas AC154)v&P#pL5. x'CM??Globalstar (12) #1 (Zenit)m pM#j@5( Sp㉂??GPS BIIR-03 (Delta 2)oP#p>5. Gh㉓g??Panamsat 8 (Proton)2 p'  Aug 1998j{P#p45. IW㻦ʼn01SCD 2 (Taurus)iM#j85( 2!15Sirius 3 (Ariane)m {QM#j@5( Sp㉂20GPS BIIR-07 (Delta 2)j J#d@5" yj22UHF 9 (Atlas 2 AC-130)Q_#S5J p㉀ 27P91 Argos (Delta 2 7920) (http://www.te.plk.af.mil/arpics/apage1.htm)SunsatORSTED (http://gate.dmi.dk:8080/fsweb/projects/oersted/mission/mission.html)q$4M#jH5( -1yj??EOS AM (Atlas 2AS AC-141)p P#p@5. M㉓g??Gorizont 33 (Proton)n4P#p<5. u㉓g??Yamal 100 (Proton)2 D'  Sep 1998jP#p45. ;KV㉓g03Nimiq (Proton)x'D&Q#rN50 L2!11Eutelsat 3F2 (Ariane 5)ARDjP#p45. LeUGKT20WIRE (Pegasus)i&P#p25. maU2!??ST 1 (Ariane)2 +'  Oct 1998lP#p85. p㉓g01Tempo 1 (Proton)i+M#j85( 㰭=H05Hotbird 5 (Atlas)RRD#X5 10STS 95eJ#d65" T*25Orion 3 (Delta 3)~.R5P#p\5. >b'CM30Galaxy 11 (1st Sea Launch / Zenit)iM#j85( -SH2!??Afristar (Ariane)y(5Q#rP50 p㉂OS??Deepspace 1 (Delta 2)Sedsat{$W#~H5< rRU2!G@c??GE 5 (Ariane)Insat 2Ev&P#pL5. x'CM??Globalstar (12) #2 (Zenit)muP#p:5. GC|2!??L Star 1 (Ariane)oP#p>5. &HbnW"??Rocsat 1 (Athena 1)q!uUP#pB5. IGKT??Terriers (Pegasus XL)_D#X65 ??titan 4B IUS launch2 U'  Nov 1998kQM#j<5( `QUp㉂15Fuse (Delta 2 7320)n!M#jB5( z?{ԉp㉂19Bonum 1 (Delta 2 7925)v&Q5P#pL5. x'CM??Globalstar (12) #3 (Zenit)WM#j5( aK??Odin (Start 1, http://www.ssc.se/ssd/ssat/odin.html, launch cost $5 million)g5LJ#d:5LB" ??Quickscat (Titan 2)jM#j:5( zz㉓g??Telstar 6 (Proton)lL"M#j>5( zz2!??Telstar 7 (Ariane 5)2 T'  Dec 1998a"J#d.5" 'KU03AXAF (STS 93)v&T+P#pL5. 6Syj06ICO 1 1 (Atlas 2AS AC-156)[D#X.5 09STS 96 (ISS 2A)t$+P#pH5. _TSWyj13MCI 1 (Atlas 2AR AC-155)mgP#p:5. )~㉓g??Astra 1H (Proton)r%M#jJ5( $'v&9+S??Chinasat 8 (Long March 3B)jgCP#p45. #U㉓g??LMI 1 (Proton)y/J#d^5" ??Milstar 2-1 (titan 4B Centaur launch)nC*P#p<5. F2!??Morelos 3 (Ariane)lM#j>5( 㩃M2!??Panamsat 6B (Ariane)o*P#p>5. Fh2!??Panamsat 7 (Ariane).3'  1998_J#d*5"6VearlyAgrani 2p 3P#p@5. EJ{؉bnW"midIkonos 2 (Athena 2)giJ#d:5" xmidMeteor (Conestoga)ZJ#d 5"'KUlateAXAF`i#G#^25b}lateIntersputnik 8q!P#pB5.HC|2!lateL Star 2 (Ariane 5)s## P#pF5.ʅs,梉lateQuick Bird (Cosmos C)SZ D#X5lateSky 3\  J#d$5" 6V??Agrani 1ZZ  J#d 5" 4 ??Amos 2o  P#p>5.  ~s,梉??Astrid 2 (Cosmos C)\  J#d$5" z'??Asusat 1r! M Q#rB50 )'CM??Badr B (Zenit)Meteorf  J#d85" 1p??Bion 12 (Soyuz U?)FM J Q#r50 fى9+S??CBERS 1 (Long March 4)SACI 1 (Brasilian micro sat, 60 kg)_  J#d*5" 〾u??Cyberstar 1n$J  J#dH5" 9+S??Feng Yun 2B (Long March 4)Z q J#d 5" O???Gals 3Z  J#d 5" O???Gals 4\q 'J#d$5" ??Gals R12m M#j@5( Sp㉂??GPS BIIR-04 (Delta 2)m 'M#j@5( Sp㉂??GPS BIIR-05 (Delta 2)noP#p<5. i휭2!??Helios 1B (Ariane)2 @Q#rd50 _T#??IRS P4 (PSLV)+ South Korean satelliteo @BHo@J#d5" ??Jawsat (Minuteman) (http://burst.unh.edu/RTSS/missummary.html)t$ @AP#pH5. ɉp㉀??Landsat 7 (Delta 2 7920)g@yAM#j45( Ӆ]'CM??Mysat 1 (Zenit)]AAJ#d&5" T_E??Nahuel 1BjyA@BP#p45. ^TSW㉓g??Sky 1 (Proton)nABP#p<5. ȉ2!??Skynet 4E (Ariane)g@BCJ#d:5" q??Spaceway (Delta 3?)i%B~CD#XJ5 ??titan 4B Centaur launch (B25)hCCM#j65( qOmK??Uosat 12 (Rokot)2 ~CD'  Jan 1999[CsDD#X.5 14STS 92 (ISS 3A)mDDP#p:5. gR2!15Asiastar (Ariane)isDIEM#j85( QaUGKT25SWAS (Pegasus XL)u%DEP#pJ5. ".㉓g??Eutelsat 3 SESAT (Proton)nIE,FP#p<5. :92!??Palapa D1 (Ariane)2 E^F'  Feb 1999u+,FFJ#dV5" ꉀ??Abrixas (Cosmos 3M, Kapustin Yar)i^F5. 2!??Arabsat 3A (Ariane)oGHP#p>5. H㉓g??Asiasat 3S (Proton)JNHWIP#p5. Hh2!??Panamsat 9 (Ariane 5) (second of the Galaxy/panamsat's HS-702)2 HI'  Apr 1999RWIID#X5 08STS 97p IKJP#p@5. M㰭=H??Eutelsat 3F3 (Atlas)2 I}J'  May 1999nKJJP#p<5. PO}2!??Caribstar (Ariane)H}JzKG#^5 ??Catsat (microsatellite, STEDI 3, http://www.catsat.sr.unh.edu/)kJKP#p65. rRU㉓g??GE 4 (Proton ?).zKL'  1999m#KLJ#dF5" x≀1QGlobalstar (4) #1 (Soyuz)m#LLJ#dF5" x≀1QGlobalstar (4) #2 (Soyuz)|,LiMP#pX5. mKearlyE-sat (3 launches with Rokot)jLMM#j:5(2!earlyPASI 1 (Ariane)liM?NP#p85. S*㰭=HJunOrion 2 (Atlas)m#MNJ#dF5" x≀2QGlobalstar (4) #3 (Soyuz)s#?NOP#pF5. סּ㉓gmidACeS (Garuda) (Proton)nNOP#p<5. ɮ6㉓gmidCoupon 2 (Proton)]O J#d&5" G@cmidInsat 3AO B_OkG#^05 b}midIntersputnik 8o ڀP#p>5. b㻦ʼnmidKompsat 1 (Taurus)w&kQQ#rL50 ̓FWp㉂midSAC C (Delta 2 7320)EO-1m&ڀG#^L5 @midSTRV 1C & 1D (Ariane 5 ASAP)nQ,P#p<5. OMyjmidTDRS 8 (Atlas 2A)l܂D#X5 JulArirang 1 (Korean Air satellite, for remote sensing and telecommunication experiments) (Vandenberg)i,EP#p25. 2!AugXMM (Ariane)n܂P#p<5. ')~2!SepAstra 2B (Ariane)lEM#j>5( Y 2!SepKoreasat 3 (Ariane)eM#j05( ㉓gOctM2A (Proton)_J#d*5"klateAsiasat 4^AJ#d(5")~lateAstra 1Kq!P#pB5.~w㉓glateExpress K1 (Proton)q!A#P#pB5.c͉㰭=HlateHispasat 1C (Atlas)oP#p>5.3!p㉀lateJason 1 (Delta 2)Z#A#R25lateNOAA L (titan 2)mYP#p:5.?|2!lateSicral (Ariane)XG#^"5 b ??Apstar 3jYP#p45.  ??Astro E (Mu 5)r"P#pD5. U/9+S??CBERS 2 (Long March 4)`A#R>5 ??Champ (Russian launcher)aNG#^45 2!??DRS (ESA, Ariane)|,ʉP#pX5. 72!??Envisat (Ariane 5, not official)ZN$G#^&5 QN??Eurasiasatq!ʉP#pB5. N2!??Eutelsat 3F4 (Ariane)}3$J#df5" a??Faisat 1A + Tubsat 2 (Cosmos 3, Plesetsk)j|P#p45. p@T㉓g??GE 1A (Proton)^ڋJ#d(5" L M@??Indostar 2e|?M#j05( ZT#??IRS 2A (PSLV)iڋP#p25. _T#??IRS P5 (PSLV)j?P#p45. #U㉓g??LMI 2 (Proton)q!P#pB5. p62!??Loralsat 101 (Ariane)t0D#X`5 ??Lybid (1st Ukrainian communication sat.)\SJ#d$5" ??Measat 3fP#p,5. %VJ??MTsat (H2)^SJ#d(5" ??Orbview 3Ay+N#lV5* 62!??Radiosat 1 (Ariane 5)Radiosat 2d J#d45" yj??UHF 10 (Atlas 2) Bx.J#d\5" ??VCL (http://essp.gsfc.nasa.gov/vcl/). '  2000s#%P#pF5.RQ2!earlyAnik F1 (Ariane 44L)n!M#jB5(vm2!earlyTurksat 2A (Ariane)l%P#p85. 㨼Wp㉀MayTimed (Delta 2)lkM#j>5( 㕖.yjAprGoes 12 (M) (Atlas)WG#^ 5 HAprAMRC 1ik+J#d>5" p㉀JunRelativity (Delta 2)iP#p25. V#JunProba (PSLV)n!+M#jB5( :#ĉ㉓gJulIntelsat 901 (Proton)WYG#^ 5 HJulAMRC 2XG#^"5 midThurayar1Y#A#Rb5 midEuropesat 1 (29E, 36 transp., MMS built)t*J#dT5" NovMAP (http://map.gsfc.nasa.gov/)]#J#d&5" )DecEOS PM-1]QG#^,5 ;#ĉDecIntelsat 902]J#d&5"U5‰lateAndesat^Q J#d(5" `lateOptus C1AD#X5lateStentor (Ariane 5) (ESA telecommunication sat., 2 tons)i% D#XJ5 ??AMRC 1 & 2 (HS-702 platforms)p jP#p@5. - 9+S??APMT (Long March 3B)aJ#d.5" ^"w??Artemis (H2A)`j+J#d,5" %c??Brasilsat B4fJ#d85" X[??Cluster 2 (Soyouz)`+J#d,5" (.Uډ??Columbia AOR`QJ#d,5" Uډ??Columbia POR_J#d*5" Yе??Europe*StarYQ J#d5" @T??GE 2AYbJ#d5" U??HESSIi P#p25. kKUp㉀??Image (Delta)TbD#X 5 ??Insat 3AiP#p25. _T#??IRS P6 (PSLV)]J#d&5" [d??Ladybug 1jOP#p45. #U㉓g??LMI 3 (Proton)q!P#pB5. p62!??Loralsat 102 (Ariane)lO,P#p85. °S2!??MSG 1 (Ariane 5):G#^t5 ??Optus 1C/D (should have a military addon payload)V,D#X$5 ??Radarsat 2^aJ#d(5" 6??Radiosat 3^J#d(5" RՉ??Resource21Xa#G#^"5 }#B??Starlitep P#p@5. PSk72!??Superbird 4 (Ariane)n#P#p<5. Iˉ2!??Thaicom 4 (Ariane)UVG#^5 ՏW??TRSSSLE#X5 ??Vietnam plans to launch a GEO telecom satellite with 15-20 years lifetime estimated to cost 250-300 million USD It would be operated by the Vietnam Post and Telecommunications (VNPT). bidders are: Hughes, LM, Loral, MMS, Alcatel and IAI (Amos HP platform)&V# .'  2001ndP#p<5. l㉓gAprIntegral (Proton);J#dv5" JulGlas (http://ltpwww.gsfc.nasa.gov/eib/Home.html)Wd@G#^ 5 㩇SepSpot 5n!M#jB5( <#ĉ2!midIntelsat 903 (Ariane)o"@M#jD5(=#ĉ2!lateIntelsat 904 (Ariane)[xJ#d"5" Vt??Aries 1XG#^"5 8D9??CelestriYx)J#d5" ??E-satXJ#d5" hOU??EASTX)J#d5" ᇆ??ECCOZ3G#^&5 ",Jꉂ??EuroskywaygJ#d:5" T??Galex (OSC vehicle)i3J#d>5" T??GFO 2 (lockheed EELV)beJ#d05" iJ??Grace (Cosmos)ZG#^&5 L M@??Indostar 3]e J#d&5" [d??Ladybug 2\x D#X05 ??NOAA M (titan 2)Z  J#d 5" c?ꉀ??RascomZx , J#d 5" R??Ruslane  J#d65" ㋗hP??Skybridge projectm,  P#p:5. OMyj??TDRS 9 (Atlas 2A). , '  2002d  J#d45" }̉DecEOS Chemistry 1^,  J#d(5" `KU??Alos (H2A)`  D#X5 ??Alsat (algerian communication satellite; should also monitor desert and water resources)Y  J#d5" t ܜ??Aster] H J#d&5" j??Astrolinkd  J#d45" R4??Echostar Ka-band_H  J#d*5" ㌾T??ETS 8 (H2A)W bG#^ 5 eF??GE Starc G#^85 㔖.??Goes 11 (L) (Atlas)Hb]P#p5. ??IRIS (Mu 5) (http://koala.astro.isas.ac.jp/iris/iris_E.html)VG#^5  N??M-Star^]@J#d(5" k??@BMillennium`}@J#d,5" &⼉??Morning Starx(@@P#pP5. °S2!??MSG 2 (Ariane 5, unofficial)]}@RAJ#d&5" K??Netsat 28[@AJ#d"5" k??OrblinkbRABJ#d05" X*??Orion 7, 8 & 9dAsBJ#d45" ʂM??Panamsat 10 & 11\BBJ#d$5" q??Spaceway^sB-CJ#d(5" I1 ??Visionstar.B[C'  2003T-CCD#X 5lateNOAA NZ[C DG#^&5 L M@??Indostar 4UC^DG#^5 b=??MetopY DDD#X*5 ??Rosetta (ESA).^DD'  2004=DlEJ#dz5" ??Glast (http://www701.gsfc.nasa.gov/glast/glast.htm)ZDEJ#d 5" 㪇??Spot 6.lEE'  2005`ETFJ#d,5" 5??Trimilsatcom.EF'  2006x(TFFP#pP5. °S2!??MSG 3 (Ariane 5, unofficial).F(G'  2007WFGG#^ 5 Wi<ʉJanNPOESSU(GHJ#d5" ??FIRST (ESA, http://astro.estec.esa.nl/SA-general/Projects/First/first.html)RGHM#j5( ??NGST (http://ngst.gsfc.nasa.gov/, http://ecf.hq.eso.org/ngst/ngst.html)9HH' $ No date or lateHIB#R5 ??Columbia: 2 telecommunications satellites, 1 for 172E with C-, extended C- and Ku-band and 1 for 47W with C- and extended C-band.YHJA#R05 ??COMET (Conestoga)\IwJJ#d$5" ɮ6??Coupon 3ZJJJ#d 5" =z??Elekon\wJ-KJ#d$5" S??EllipsatZJKG#^&5 Ve??Expressway[-KKJ#d"5" <`??Gramsat\K>LJ#d$5" ڒ|??LightsarXKLG#^"5 ujj??MarathonM>L-MJ#d5" ??OICETS (http://yyy.tksc.nasda.go.jp/Home/This/This-e/oisets_e.html)ZLMJ#d 5" _??PaksatZ-MMJ#d 5" G??Pansat\M=NJ#d$5" &Hꉀ??Rocsat 2q'MNJ#dN5" ?w|??Sich 2 (Cyclone 3 or Zenit 2)]=N OG#^,5 ۠L`??Simon BolivarnNyOP#p<5. ȉ2!??Skynet 4F (Ariane)S OOD#X5 ??SMEX 07AyO`G#^5O`B *??SMEX lite (http://sunland.gsfc.nasa.gov/smex/smexlite/)YOJ#d5" W*??SSTP[`J#d"5" ㄋQt??Starsys:G#^t5 ??TSX5 (http://www.te.plk.af.mil/tsx5home/tsx5.htm)g#D#XF5 ??Tubsat C (Russian launcher)\XJ#d$5" >*??V-StreamT G#^5 ^o??West$XЂ" 11WBU{T+ЂU) "VȠ$To view this page you need to register&{# 1U1zCI"{' Dpage intentionally left blank9.1%D.s7GlossaryEs5 :"c"  Glossary&.# $s` Tq}q       ADCAnalog to Digital ConversionApogeeThe orbital point were the satellite is furthest from the earthApogee Kick Motor (AKM)A motor on board the satellite that enables the satellite to move from GTO to GEOBandwidthRange on frequency the transponder can transmit, in MHz Give a measure of capacityBOLBegin Of LifeBUDBig Ugly DishCarrier to Noise ratio (C/N)Ratio which express the quality of a signal (the higher the better)4V zTq}q )    Catalog numberThe number that identifies a satellite, attributed by NASA. See CATNRCDMACode Division Multiple Access. Access method for several stations to go through a single transponder which uses spread spectrum modulations and orthogonal codes.Clarke beltThe geostationary orbit, named after Arthur Clarke that first said that such an orbit should existCOMINTCommunication IntelligenceCONUSContinental United States (all states but Alaska and Hawaii)gXq Tq}q         CoverageZone where the satellite's signals can be receivedDBSDirect Broadcast SatellitedBWratio of the power to one Watt in decibels (unit used to express EIRP values)DC powerTotal power produced by the solar panels or nuclear reactorDCMEDigital Circuit Multiplication EquipmentDCPData Collection PlatformDownlinkThe satellite to earth signal pathDTHDirect To HomeEIRPEffective Isotropic Radiated PowerTechnical value that evaluates the strength of receive signalsOH ^Tq}q    ELINTElectronic IntelligenceEOLEnd Of LifeFDMAFrequency Division Multiple Access Access method to a transponder by multiple stations each using 1 unique frequencyFootprintA map of EIRP values that express the signal strengths at a given locationS&X- *LPq}q Frequencies (GHz if not specified)YSA#R08HF-band1.8 - 30 MHzZA#R28VHF-band50 - 146 MHz]S A#R88P-band0.230 - 1.000 GHz\fA#R68UHF-band430 - 1300 MHzY A#R08L-band1.530 - 2.700f%f%A#RJ8,FCC's digital radio2.310 - 2.360Y~A#R08S-band2.700 - 3.500x%RP#p8.ھ#ھC-bandDownlink: 3.700 - 4.200Uplink: 5.925 - 6~R.425Standard US chart (horizontal)Standard US chart (vertical)z8~B#Tp8X-bandDownlink: 7.250 - 7.745Uplink: 7.900 - 8.395RM#hE8&&Ku-band (Europe)Downlink:FSS: 10.700 - 11.700DBS: 11.700 - 12.500Telecom: 12.500 - 12.750Uplink:FSS & Telecom: 14.000 - 14.800DBS: 17.300 - 18.100J#d8"(Ku-band (America)Downlink:FSS: 11.700 - 12.200DBS: 12.200 - 12.700Uplink:FSS: 14.000 - 14.500DBS: 17.300 - 17.800=B#Tz8Ka-bandhas multiple acceptations...roughly: 18 - 31 GHzY\A#R08V-band36 - 51.4 GHz_M h%Tq}q    GEOGeostationary Earth OrbitGeostationary orbitThe circular orbit at 35.780 km above the equator. Satellites slotted on this orbit always appear at the same position in the sky. In degrees towards East (E or positive) or West (W or negative) from the Greenwich meridian.G/TUnit of measurement for an antenna + LNA Expressed from the gain and and noise temperature. The higher the betterGTOGeostationary Transfer OrbitGeostationary satellites are usually launched on a temporary orbit before being moved to GEO \f ITq}q   )    Inclined OrbitTerm used for a GEO satellite that has turned off its North/South stabilization. From Earth, such a satellite seems to draw an 8 in the sky; part of the day it is above the Equator, and then below.IOLInter-Orbit LinkLaunch idLaunch number that identifies the flight, see LAUNRLEOLow Earth OrbitLNALow Noise AmplifierLHCPLeft Hand Circular PolarizationPAMPayload Assist ModuleSa Tq}q       PerigeeThe orbital point were the satellite is closest from the earthPolar orbitOrbit that is perpendicular to the plan of the EquatorPolarizationPlane of vibration of the electrical field of a signal Differerent polarizations enable better frequency re-usePowerThe transponder amplification powerRADINTRadar IntelligenceRHCPRight Hand Circular PolarizationSCPCSingle Channel Per Carrier Access method for a large number of signals to go through a single transponder7f sTq}q    jQv   SIGINTSignal IntelligenceSSPASolid State Power AmplifierTDMATime Division Multiple Access Access system where each station has a time slot for using a unique carrier shared with othersTHEOTwelve Hours Excentric Orbit (Molniya-type orbit)TransponderThe association of a receiver, frequency converter and transmiter devices in a satelliteTWTATraveling Wave Tube AmplifierUplinkThe earth to satellite signal path9p1D%EpPrintingF75 :$NJ" EIRP maps&p# 4 '  Footprints(8$ AmH ㇜5㕬N9㕬N9K6Q8Q8S7{!KO؝쉂?؝쉂WO^U󉂃WO^Amos 1: Central EuropeAmos 1: Middle EastAnik E1: C-bandAnik E1: Ku-bandAnik E2: C-bandAnik E2: Ku-bandApstar 1: C-bandApstar 1A: C-band horizontalApstar 1A: C-band verticalApstar 2R: C-bandApstar 2R: Ku-bandArabsat 1C: S-bandArabsat 1C: C-bandArabsat 2A: C-bandArabsat 2A: Ku-bandArabsat 2B: C-bandu8d U󉂃Z۪!剂<扂k+_vVҨYY^ZY<YՉ4 ԉ(uSӪuSӪuSӪuSӪZ$QEutelsat 1F4: spot beamsEutelsat 1F4: eurobeamEutelsat 1F4: SMS beamEutelsat 1F5: spot beamsEutelsat 1F5: eurobeamEutelsat 1F5: SMS beamEutelsat 2F1: Super beamEutelsat 2F1: Wide beamEutelsat 2F2: Super beamEutelsat 2F2: Wide beamEutelsat 2F3: Super beamEutelsat 2F3: Wide beamEutelsat 2F4: Super beamEutelsat 2F4: Wide beamc$ c /UOt|72t|70t|77t|7Eutelsat 3Express 1: C-band quasi-global A3 & A5Express 1: C-band hemispheric A4Express 1: C-band spot A2Express 1: Ku-band spot A9Express 2: C-band quasi-global A3Express 2: C-band hemispheric A4Express 2: Ku-band spot A9( L $ G$ f  !!B,BQ!Q`k5ĉnk5ĉB)RB)R㣦@㱦@&RGalaxy 1R: C-band HorizontalGalaxy 1R: C-band VerticalGalaxy 3R: C-band HorizontalGalaxy 3R: C-band VerticalGalaxy 4: C-band HorizontalGalaxy 4: C-band VerticalGalaxy 4: Ku-band HorizontalGalaxy 4: Ku-band VerticalGalaxy 5: C-band HorizontalGalaxy 5: C-band VerticalGalaxy 6: C-band HorizontalGalaxy 6: C-band VerticalGalaxy 7: C-band Horizontal{L t 4R~މ~މRRRꉂXTQW$ v,Galaxy 7: C-band VerticalGalaxy 7: Ku-band HorizontalGalaxy 7: Ku-band VerticalGalaxy 9: C-band HorizontalGalaxy 9: C-band VerticalGalaxy 9: C-band Alaska extendedGalaxy 10: C-bandGalaxy 10: Ku-bandGalaxy 11: C-bandGalaxy 11: Ku-band North AmericaGalaxy 11: Ku-band BrazilGalaxy 11: Ku-band LatinGE 1: C-bandGE 1: Ku-band#f A 1wPvz鉂wPvz鉂r͉p͉t͉o͉u͉}し*tA7GE 2: C-bandGE 2: Ku-bandGE 3: C-bandGE 3: Ku-bandGorizont 18: C-band global A6Gorizont 18: C-band large hemispheric A4Gorizont 18: C-band narrow hemispheric A8Gorizont 18: C-band spot A3Gorizont 18: Ku-band spot A9Gorizont 20: C-band global A6Gorizont 20: C-band large hemispheric A4Gorizont 20: C-band narrow hemispheric A8Gorizont 21: C-band global A6)tC{ Ā]***w$u$y$t$z$󦉂󦉂󦉂Gorizont 21: C-band large hemispheric A4Gorizont 21: C-band narrow hemispheric A8Gorizont 21: Ku-band spot A9Gorizont 22: C-band global A6Gorizont 22: C-band large hemispheric A4Gorizont 22: C-band narrow hemispheric A8Gorizont 22: C-band spot A3Gorizont 22: Ku-band spot A9Gorizont 25: C-band global A6Gorizont 25: C-band large hemispheric A4Gorizont 25: C-band narrow hemispheric A8AE{ ĀG󦉂]]]]\eZe^e_ezĉzĉGorizont 25: Ku-band spot A9Gorizont 26: C-band global A6Gorizont 26: C-band large hemispheric A4Gorizont 26: C-band narrow hemispheric A8Gorizont 26: Ku-band spot A9Gorizont 27: C-band global A6Gorizont 27: C-band large hemispheric A4Gorizont 27: C-band narrow hemispheric A8Gorizont 27: Ku-band spot A9Gorizont 28: C-band global A6Gorizont 28: C-band large hemispheric A4CH{ ĀCzĉzĉzĉ # # #! #ʁ.xǁ.xȁ.x́.xGorizont 28: C-band narrow hemispheric A8Gorizont 28: C-band spot A3Gorizont 28: Ku-band spot A9Gorizont 29: C-band global A6Gorizont 29: C-band large hemispheric A4Gorizont 29: C-band narrow hemispheric A8Gorizont 29: Ku-band spot A9Gorizont 30: C-band global A6Gorizont 30: C-band spot A3Gorizont 30: C-band large hemispheric A4Gorizont 30: C-band narrow hemispheric A8EJ Ԁ́.xa _ c d ㌆ƉN؉Gorizont 30: Ku-band spot A9Gorizont 31: C-band global A6Gorizont 31: C-band large hemispheric A4Gorizont 31: C-band narrow hemispheric A8Gorizont 31: Ku-band spot A9Gorizont 32: C-band global A6Gorizont 32: C-band large hemispheric A4Gorizont 32: C-band narrow hemispheric A8Gorizont 32: C-band spot A3Gorizont 32: Ku-band spot A9Gstar 2Gstar 4(H9wP6鉂p>9wP6鉂}ʃRꉂ\\\\\Hispasat 1A: Direct TVHispasat 1A: Telecommunication to EuropeHispasat 1A: Telecommunication to AmericaHispasat 1B: Direct TVHispasat 1B: Telecommunication to EuropeHispasat 1B: Telecommunication to AmericaHispasat 1CHotbird 1Hotbird 2: superbeamHotbird 2: widebeamHotbird 3: superbeamHotbird 3: widebeamHotbird 4: superbeamC!^>!_>!?!]>!^>!_>!?!C‰P&(Palapa B2PPalapa B2RPalapa B4Palapa C1: C-band: Asean & New Zealand beamPalapa C1: C-band: Asean beamPalapa C1: C-band: Asia beamPalapa C1: Ku-bandPalapa C2: C-band: Asean & New Zealand beamPalapa C2: C-band: Asean beamPalapa C2: C-band: Asia beamPalapa C2: Ku-bandPanamsat 1: C-bandPanamsat 1: Ku-band to EuropePanamsat 1: Ku-band to US ԀII=IX:1OY:1O;1OvvvV)o艂_2*Panamsat 2: C-band, Pacific RimPanamsat 2: C-band, OceaniaPanamsat 2: Ku-bandPanamsat 3R: C-band beam 1Panamsat 3R: C-band beam 2Panamsat 3R:َ7 Ku-bandPanamsat 4: C-band, Africa & AsiaPanamsat 4: C-band, Asia/Middle East horizontalPanamsat 4: C-band, Asia/Middle East verticalPanamsat 4: Ku-bandPanamsat 5: C-bandPanamsat 5: Ku-band, USَB T 1*)h*h)hPanamsat 5: Ku-band, MexicoPanamsat 6: Ku-band, ArgentinaPanamsat 6: Ku-band, BrasilPanamsat 6: Ku-band, NTSC($ Rzj nS)%[Pdؕ$zE=NwωRaduga 1-1Raduga 1-2Raduga 1-3Raduga 21Raduga 22Raduga 28Raduga 29Raduga 30Raduga 32($ S-z  4۠2A`@A`@kk]Mhhb򉂃\WӯK. 㽱*<2.+uο̉76Satcom C1Satcom C3Satcom C4Satcom K1Satcom K2SBS 5SBS 6: HorizontalSBS 6: VerticalSirius 1Sirius 2: EuropeSirius 2: Northern and Central EuropeSirius 2: ScandinaviaSirius 3: ScandinaviaSolidaridad 2: C-bandSolidaridad 2: Ku-bandSpacenet 1: C-bandSpacenet 2: C-bandSpacenet 3R: C-band, 36 MHz transpondersK d+86rr~ept&4Spacenet 3R: C-band, 72 MHz transpondersSpacenet 3R: Ku-band, East and West spotsST 1: C-bandST 1: Ku-bandSuperbird B1: Ku-band( $ TT 4XnXn ㉂HY-m ㅃ,pwۉ(]ӹwۉ(]ӹwۉ(]ӹwۉ&ǵ&ǵ&ǵ_εTDF 1TDF 2TDRS 4: C-bandTDRS 5: C-bandTDRS 6: C-bandTELE XTelecom 2A: C-bandTelecom 2A: Ku-bandTelecom 2B: C-band (*)Telecom 2B: Ku-band (*)Telecom 2C: C-bandTelecom 2C: Ku-bandTelecom 2D: C-bandTelecom 2D: Ku-bandTelstar 301Telstar 302Telstar 303Telstar 401: C-band j& r)_εr)9D4uljo9XCÇXC~RvRvSv; 퉂㰬k؆*a5Telstar 401: Ku-bandTelstar 402R: C-bandTelstar 402R: Ku-bandTelstar 5: C-bandTelstar 5: Ku-bandThaicom 1: C-bandThaicom 1: Ku-bandThaicom 2: C-bandThaicom 2: Ku-bandThaicom 3: C-band, quasi globalThaicom 3: C-band, zoneThaicom 3: Ku-bandThor 1Thor 2Thor 3Turksat 1B: European & Turkish spots (*) > JS㪜nIi3WTurksat 1C: Central Europe & TurkeyTurksat 1C: Central Asia & TurkeyTvsat 2*: this footprint is available as a preview in the WWW or the Winhelp edition7&D'  O Printing maps}U ( Winhelp is not a very good program for printing. To print a page, use the Print item of the File menu.To print footprints, you should use the following index: clic on one footprint to display it, then use the File Print function and come back to this page with the Back button of the toolbar.Beware: we have noted important variations of the printing quality with Winhelp. Grey colors are seldomly properly printed. Check the grey color configuration in the printer panel. If Winhelp doesn't provide good quality printing you should screen shot and print with an external tool (Paintbrush).`/D!1vF! C-band US frequency chart (starting horizontal)w=: D|back()"  C-band US frequency chart (starting horizontal) (GHz)&!# _#k * X n  HorizontalUplinkHorizontalDownlinkChannelVerticalDownlinkVerticalUplinkFt#,kF3.72015.945t#,k(5.96523.740FZt#,k3.76035.985t#,k(6.00543.780Znt#,k3.80056.025t#,k(6.04563.820nt#,k3.84076.065 t#,k(6.08583.860t#,k3.88096.105 !t#.k*6.125103.900t#.k 3.920116.145!7t#.k*6.125123.940t#.k 3.960136.1857Mt#.k*6.205143.980t#.k 4.000156.225Mct#.k*6.245164.020t#.k 4.040176.265cy t#.k*6.285184.060 t#.k 4.080196.305y  t#.k*6.325204.100  t#.k 4.120216.345  t#.k*6.365224.140 0 t#.k 4.160236.385  t#.k*6.405244.180$0  " ^- = 1G=  KC-band US frequency chart (starting vertical)u;  : Dxback()"  C-band US frequency chart (starting vertical) (GHz)&=  # _ #k * X n  HorizontalUplinkHorizontalDownlinkChannelVerticalDownlinkVerticalUplink Tt#,k(5.94513.720t#,k3.74025.965Tt@t#,t@ k(5.98533.760@t#,k3.78046.005t@At#,k(6.02553.800@Bt#,k3.82066.045ABt#,k(6.06573.840B&Ct#,k3.86086.085BCt#,k(6.10593.880&C;Dt#.k 3.900106.125CDt#.k*6.145113.920;DQEt#.k 3.940126.125DEt#.k*6.185133.960QEgFt#.k 3.980146.205EFt#.k*6.225154.000gF}Gt#.k 4.020166.245FHt#.k*6.265174.040}GHt#.k 4.060186.285HIt#.k*6.305194.080HIt#.k 4.100206.325I4Jt#.k*6.345214.120IJt#.k 4.140226.3654JJKt#.k*6.385234.160JKt#.k 4.180246.405$JKK" AK:L1!H:LLFirst in HistoryRKL5 :<NJ" First time in History+:LL$ 1957LM9 @1Pǀ=ƀ~~04 OctFirst satellite, first Russian satellite, Russia becomes the 1st space power: Sputnik 0103 NovFirst living creature in space: Sputnik 02+LM$ 1958MtN9 @Pǀ=ƀ`'[IW01 FebFirst American satellite, America becomes the 2nd space power: Explorer 0118 DecFirst telecommunication satellite: Score+MN$ 1959b2tNO0 0dPǀ=ƀ`13 OctFirst meteorology payload: Explorer 07+N,O$ 1960]-OO0 0ZPǀ=ƀ`03 NovFirst NASA satellite: Explorer 08+,OO$ 1961FO * $8Pǀ=ƀ12 AprFirst man in spaceO K+O7$ 1962U  I `Pǀ=ƀLV.d$tzzH624 FebFirst phone communication & TV broadcast via satellite: Echo 126 AprFirst English satellite: Ariel 110 JulFirst active telecommunication satellite and first time a company launchs a satellite: Telstar 129 SepFirst Canadian satellite: Alouette 1+7$ 1963H* $<Pǀ=ƀ16 JunFirst woman in space+*$ 19649 @%Pǀ=ƀsH719 AugFirst geostationary satellite, first geostationary telecommunication satellite: Syncom 315 DecFirst Italian satellite: San Marco 1+* $ 1965O0 0Pǀ=ƀ;S26 NovFirst French satellite, France becomes the 3rd space power: Astrix+ ʃ$ 1967fh8 @Pǀ=ƀScaω05 NovFirst geostationary meteorology payload: ATS 329 NovFirst Australian satellite: Wresat+ʃ$ 1968]-h0 0ZPǀ=ƀb17 MayFirst European satellite: ESRO 2B+$ 1969wE2 4Pǀ=ƀKU21 JulFirst man on the moon08 NovFirst German satellite: Azur+$ 1970̆A PPǀ=ƀ~gO]YU!(v&11 FebFirst Japanese satellite, Japan becomes the 4th space power: Ohsumi10 MarFirst launch from Kourou: Mika24 AprFirst Chinese satellite, China becomes the 5th space power: Dong Fang Hong 01+$ 1971V̆}0 0Pǀ=ƀ'S*28 OctFirst English launched satellite, UK becomes the 6th space power: Prospero+$ 1974}I `Pǀ=ƀSDmgS?a׉30 MayFirst direct broadcasting satellite: ATS 630 AugFirst Dutch satellite: ANS15 NovFirst Spanish satellite: Intasat19 DecFirst civilian satellite 3-axis stabilized: Symphonie 1+$ 1975]->0 0ZPǀ=ƀG19 MayFirst Indian satellite: Aryabhata+i$ 1976a1>ʉ0 0bPǀ=ƀ:908 JulFirst Indonesian satellite: Palapa A1+i$ 1978e5ʉZ0 0jPǀ=ƀL$24 OctFirst Czechoslovakian satellite: Magion 1+$ 1980YZ0 0Pǀ=ƀ~Oa18 JulFirst Indian launched satellite, India becomes the 7th space power: Rohini 1B+9$ 1981t8 @Pǀ=ƀ㥜>㉂12 AprFirst manned launch of the Shuttle: STS 0107 AugFirst Bulgarian satellite: Intercosmos Bulgaria 1300+9$ 1984͌9 @ Pǀ=ƀ*06 AprFirst satellite repared in orbit by the shuttle: SMM16 NovFirst time satellites were brought back from space: STS 19+$ 1985_͌8 @Pǀ=ƀb􉂃F08 FebFirst Brazilian satellite: Brasilsat A117 JunFirst Mexican satellite: Morelos 1+$ 1986[+0 0VPǀ=ƀ1ĉ22 FebFirst Swedish satellite: Viking+@$ 19888 @Pǀ=ƀf(~19 SepFirst Israeli satellite, Israel becomes the 8th space power: Offek 111 DecFirst Luxemburger satellite: Astra 1A+@"$ 1990Y8 @Pǀ=ƀ U(22 JanFirst Argentine satellite: Lusat16 JulFirst Pakistanese satellite: Badr A+"ޏ$ 1992b2L0 0dPǀ=ޏLKƀ10 AugFirst South Korean satellite: Kitsat A+ޏw$ 1993UL8 @Pǀ=ƀVFˉ25 SepFirst Portugese satellite: Posat18 DecFirst Thai satellite: Thaicom 1+w/$ 1994_/0 0^Pǀ=ƀmvm10 AugFirst Turkish satellite: Turksat 1B+/$ 1995A PmPǀ=ƀ>w|3д%?J$31 AugFirst Ukrainian satellite: Sich 131 AugFirst Chilean satellite: Fasat AlfaSepPanAmSat becomes the first private company ever to provide global satellite services.+$ 1996_/:0 0^Pǀ=ƀ12 JanFirst Malaysian satellite: Measat 1+e$ 1997c2:1 2dPǀ=ƀn19 AugFirst Philippine satellite: Mabuhay 1(e$ 8(1 4o)I(`Abrixas8 `, (" AbrixasY6(# lA Broadband Imaging X-Ratz All-shy Survey Satellite1 `'  GeneralYCG#^$") Designationd#A#RFLaunch dateplanned in Feb 1999n!CM#jB"N , Country of originGermanyw*M#jT"H̀_BMissionAstronomy: X-ray astronomyZA#R2"Perigee/Apogee500 kmT:A#R&Inclination51L A#RPeriode:G#^<" &Launch vehicleCosmos 3M]HA#R8Launch siteKapustin Yar2% DARA satellite developped with the help of the GFZ Postdam, Max-Planck-Institute for extraterrestrial Physics Garching, and the astronomy and astrophysics institute of the Tubingen university. <Hn' *O External resources2(/ ,http://www.aip.de:8080/~friedric/abrixas/abrixas_start.htmlhttp://zarm9.zarm.uni-bremen.de/2forschung/raumfahrt/abrixas/abrixas.html8n`' "(OTechnical data8(' " Specifications``A#R>&Prime contractorOHB SystemN FA#RPlatformZA#R2"Mass at launch450 kgSFA#R$ Mass in orbit^QA#R:Dimension2.5 x 3 x 1.2 mQA#R Solar arraySQA#R$ StabilizationN CA#RDC powerUA#R($Design lifetime&C# 11WJCiT+C) "VȠ$To view this page you need to register&i# 5C1).*K @ACeS>i, (&" Program: ACeS-9 @ "ZAsia Cellular Satellite systemMobile telecommunication satellite project to be operated by ACeS Regional Services Co., Ltd. ACeS is equally owned by Indonesia's PT Pasifik Satelit Nusantara (see M2A), the Philippines Long Distaince Telephone Company (see Mabuhay) and Thailand's Jasmine International Overseas Company Ltd which is a subdiary of Jasmine International Public Company Ltd JASM.BK The global cost is evaluated at $1 billionThe system will provide voice, facsimile, and pager services through new satellites to hand-held mobile and fixed terminals throughout Southeast Asia, India, and China. ACeS will allow a person to use the same Global System for Mobile communications (GSM) based number for both mobile and cellular telephones while traveling throughout Asia. A dual-mode satellite-cellular handset, capable of communicating directly with the satellite as well as connecting up with local terrestrial cellular and fixed networks, will be manufactured by Ericsson Corp. of Sweden. ^$ The ACeS system is expected to be commercial from January 1999, later deferred to mid-1999<' * External resourcesY2,' dhttp://goldsite.com/Profile/Jasmine/jas14.html&R# 8,' "(OTechnical dataRw% Two satellites and all ground installation are to be build by LM Astro Space for $650 million Those could be called Garuda. Planned for 1999, will be launched on Proton (launch cost: $70 million)2 '  OverviewSwA#R$ Orbit typeGEOYUA#R0 Orbit rangecircularb!A#RB &Nb of satellites1 + 1 backupSU A#R$ Nb of planes1S]A#R$ Inclination0^ A#R: 2Nb beams per satellite12T]A#R& ModulationTDMA^mA#R: *Mobile frequenciesL-band[A#R4 "Satellite mass4500 kgN m A#R CoverageZp A#R2 &Operational date1999&  # 8p  ' " Specificationse$ 3 A#RH&Prime contractorLockheed MartinS  A#R$PlatformA2100[3  A#R4"Mass at launch4400 kgS 4 A#R$ Mass in orbitO  A#RDimensionQ4  A#R Solar arrayS ' A#R$ StabilizationN u A#RDC power`'  A#R>$Design lifetime12-15 years&u  # 0 + '  L-bandW  A#R,(Main transpondersY+  A#R0,Backup transpondersK &A#RPowerO uA#RBandwidthN &A#RCoverageJ u A#REIRPR_A#R"Polarizations  @$ 2 antennas each 12 m diameter (to be built by Harris Aerospace (US))11000 simultaneous telephone communications_ @i1_=@1WL=@@@T+ @@) "VȠ$To view this page you need to register&=@@# 5@@18 o)*M@)A0NACTS= @)A2 4"  ACTSV0@A& ` Advanced Communications Technology Satellite1 )AA'  Generalg ABG#^@") Designation22796 / 93058B\AsBA#R6Launch date12 Sep 1993t'BBM#jN"N ,㹌לCountry of originUnited States^sBECJ#d("T@^gOperatorNASAo"BCM#jD"H̀‰MissionTelecommunicationsfECDG#^>"/ۀ0Geostationary orbit100WjCDM#j:" &ΛLaunch vehicleSTS 51D;E% %Experimental satellite intended to develop Ka-band mobile services to VSAT terminals from high-data rate personal and transportable terminals.<DwE' *O External resources\;EF. ,http://kronos.lerc.nasa.gov/acts/acts.htmlhttp://sulu.lerc.nasa.gov/dglover/acts.html8wE9F' "(OTechnical data8FqF' " Specificationsd#9FFA#RF&Prime contractorGE Astro Space^qF3GA#R:PlatformGE 4000 modified[FGA#R4"Mass at launch2545 kgZ3GGA#R2 Mass in orbit1555 kgd#GLHA#RFDimensions2.03 x 2.13 x 1.92 mYGHA#R0 Stabilization3 axislLHSIB#TDC powerBOL: 1770 W (batteries: 2 NiCd of 19 AH each)EOL: 1418 W (no payload operation during eclipse)\HIA#R6$Design lifetime4 yearsv5SI%JA#Rj,Telemetry & CommandKa-band with backup in C-bandkIJ% Orbit control: Blowdown Hydrazine System with redundant thrusters and 4 tanksStationkeeping: +/- 0.051 %JJ'  Ka-bandXJ>KA#R.(Main transponders4YJKA#R0,Backup transpondersV>KKA#R*Power40 W (TWTA)VKCLA#R*Bandwidth900 MHzK,MC#TMCoverageA beam-forming network of 45 horns gives a coverage of about 20% of CONUS providing 3 x 0.3 fixed beamsThere is a single 1.0 mechanically steered beamKCLMC#VEIRP maxspot beam: 60 dBWcontiguous sectors: 59 dBWsteerable: 53 dBWR,M NA#R"Polarization$M0N" 8 NhN1.*+NhNNVAdeos 18 0NN, (" Adeos 1lIhN O# Advanced Earth Observing Satellite, also called Midori (means "green")1 N=O'  Generalg OOG#^@") Designation24277 / 96046A\=O A#R6Launch date17 Aug 1996O 0NlOxM#j>"N ,bCountry of originJapan_ ׀J#d*OperatorNASDAkxBM#j<"H̀郉MissionRemote sensing^׀A#R:"Perigee/Apogee800/830 kmVBA#R*Inclination98.6SIA#R$Period101 minZG#^&Cycle41 daysiI M#j8" &JLaunch vehicleH2 #4g@s' To acquire global observation data corresponding to enviromental changes, such as global warming, depletion of the ozone layer, decrease of tropical rain forests, occurrence of unusual weather, etc. it will also help develop the platform bus interorbit data relay technologies necessary for next-generation Earth Observation Systems. The satellite encountered several problems after launch: first a thruster problem which required to use the 20 N adjusters to reach final orbit; then on 24th September 1996 the satellite shutdown all nonessential systems. At the same time a scanning mirror used by the Interferomic Monitor for Greenhouse Gases became stuck on 20 September. Also, it was found that cosmic radiations affected the on-board computer. In late 1996 it was also found that the OCTS instrument has a mirror blocked.C $ >Satelite cost: $474 million<s' *O External resources = Hhttp://www.eoc.nasda.go.jp/guide/guide/satellite/satdata/adeos_e.htmlhttp://jwocky.gsfc.nasa.gov/adeos/adeos.htmlhttp://www.spacer.com/spacenet/text/adeos-e.htmlhttp://mentor.eorc.nasda.go.jp/ADEOS/index.html5A'  End of life_ A#R<"Out of service30 Jun 1997fAGA#RCauseelectrical failure caused by the solar array paddle break itself caused by improper maneuver&m# 8G' "(OTechnical data8m݉' " Specifications`=A#R>&Prime contractorMitsubishiN ݉A#RPlatform[=A#R4"Mass at launch3500 kgS9A#R$ Mass in orbitZA#R2Dimension4 x 4 x 5 mY9A#R0Solar array3 x 26 mYEA#R0 Stabilization3-axisTA#R&DC power4500 W\EA#R6$Design lifetime3 yearsp+ &ˎTelemetry/data at: 2220, 8150, 8250, 8350 MHz perhaps also 467.7 MHz?Ka-band inter orbit links to Comets2 ' O PayloadsiV+ $Ocean Color and Temperature Scanner (OCTS)Advanced Visible and NearInfrared Radiometer (AVNIR)NASA Scatterometer (NSCAT)Total Ozone Mapping Spectrometer (TOMS)Polarization and Directionality of the Earth's reflectances (POLDER)Interferometric Monitor for Greenhouse Gases (IMG)Improved Limb Atmospheric Spectrometer (ILAS)Retroreflector in Space (RIS)81*+OƏAdeos 28 VƏ, (" Adeos 2\9.# rAdvanced Earth ObserviƏ.Vng Satellite, also called Midori1 Ə_'  GeneralY.G#^$") DesignationU_ A#R(Launch date1999lyM#j>"N ,bCountry of originJapan_ J#d*OperatorNASDAkyCM#j<"H̀郉MissionRemote sensing^A#R:"Perigee/Apogee800/830 kmVCA#R*Inclination98.6SJA#R$Period101 minZG#^&Cycle41 daysgJ M#j4" &JLaunch vehicleH2?&1# < m' *O External resourcesrK1' http://hdsn.eoc.nasda.go.jp/guide/guide/satellite/satdata/adeos2_e.html8m' "(OTechnical data}X% Mass: 3.5 tonsDownlink: 465.9875 or 468.875 MHz (EIRP > 27.1 dBm)Uplink: 401.65 MHz2 ' O Payloads( uGlobal Imager (GLI)Advanced Microwave Scanning Radiometer (AMSR)Improved Limb Atmospheric Spectrometer (ILAS 2)Polarization and Directionality of the Earth's reflectances (POLDER)11WP-ST+-) "VȠ$To view this page you need to register&S# 6-1+L+QAEM 16 S, (" AEM 1VA, (  Application Explorer Satellite, also called HCMM (Heat Capacity Mapping Mission)1 r'  Generalg AG#^@") Designation10818 / 78041A\r5A#R6Launch date26 Apr 1978t'M#jN"N ,㹌לCountry of originUnited States@56M#j"H̀郉MissionScientific: Remote sensing (Earth thermal study)^A#R:"Perigee/Apogee560/641 kmV6A#R*Inclination97.6T>A#R&Period96.7 minm M#j@" &g'KLaunch vehicleScout #98&># 5'  End of lifeV\A#R*Decay26 Apr 1978$" 6\1 +[,RAEM 26 , (" AEM 2b}/ .   Application Explorer Satellite, also called SAGE (Stratospheric Aerosol and Gas Experiment)1 '  Generalg }G#^@") Designation11270 / 79013A\qA#R6Launch date18 Feb 1979t'M#jN"N ,㹌לCountry of originUnited States~1qcM#jb"H߲̀-MissionScientific: high atmosphere study^A#R:"Perigee/Apogee456/506 kmTc!A#R&!Inclination55TuA#R&Period94.2 minm !M#j@" &g'KLaunch vehicleScout #99&u# 5='  End of lifeVA#R*Decay11 Apr 1989$=" 61L+,S'AEM 3: '/ ."  AEM 3`7) "n  Application Explorer Satellite, also called Magsat1 ''  Generalg G#^@") Designation11604 / 79094A\{A#R6Launch date30 Oct 1979t'M#jN"N ,㹌לCountry of originUnited States{4{jG#^h"H̀MissionScientific: Earth magnetic field study^A#R:"Perigee/Apogee352/561 kmVjA#R*Inclination96.8TrA#R&Period93.7 minn!M#jB" &g'KLaunch vehicleScout #101&r# 5;'  End of lifeVA#R*Decay11 Jun 1980$;" ?1p[,,T?~Program: AerosK?5 :.o " Program: Aeros?~# 8German scientific program1?1Ub(~: DP˜klProgram: AerosAeros 1Aeros 28I1,VIC Aeros 1D5 : o " Aeros 17I# (Also called GRS B1 '  Generalg \ G#^@") Designation06315 / 72100A\ A#R6Launch date16 Dec 1972n!\ & M#jB"N , Country of originGermanyy,  M#jX"H̀?vMissionScientific: ionosphere study^&  A#R:"Perigee/Apogee223/867 kmV S A#R*Inclination96.9T  A#R&Period95.6 minm S  M#j@" &g'KLaunch vehicleScout #83Z n A#R2"Mass at launch127 kg&  # 5n  '  End of lifeV  A#R*Decay22 Aug 1973$ C " 8 { 1',W{  RBAeros 2DC  5 : o " Aeros 21 {  '  Generalg WG#^@") Designation07371 / 74055A\ A#R6Launch date16 Jul 1974n!W!M#jB"N , Country of originGermanyy,M#jX"H̀?vMissionScientific: ionosphere study^! @A#R:"Perigee/Apogee224/869 km @C Vb@A#R*Inclination97.5T @@A#R&Period95.6 minm b@#AM#j@" &g'KLaunch vehicleScout #88Z@}AA#R2"Mass at launch127 kg&#AA# 5}AA'  End of lifeVA.BA#R*Decay25 Sep 1975$ARB" 9.BB1-,S,XBBFAfristarERBB5 :"$eT" Afristar9B C# ,Also called AfriBSS1 B:C'  GeneralY CCG#^$") Designationd#:CCA#RFLaunch dateplanned in mid-1998_CVDG#^0"N ,Country of origino"CDM#jD"H̀‰MissionTelecommunications]VD"EA#R8,Geostationary orbit21EjDEM#j:" &2!Launch vehicleAriane{"E+F$ The satellite might not be placed in GEO right after the launch in order to wait for the other satellites of the series8EcF' "(Technical datai7+FF2 4n0|SpecificationsL-bandOnboard signal processing1cFF1WYFQGwGT+FQG) "VȠ$To view this page you need to register&FwG# @QGG1,-ZGGOProgram: Agrani@wGG, (*" Program: Agrani$GJ( Wireless satellite telecommunications system for India: 2 geostationary satellites operated by Afro-Asian Satellite Communications Ltd. ASC is backed by India's Essel GroupOrdered from Hughes for $700 million; project worth $850 millionenhanced HS-601s with very large antennas, to provide direct links with handheld radios from Clarke orbit. One will cover Africa, the other central Asia from Moscow to Singapore. Gallium-arsenide solar cells and Hughes xenon-ion stationkeeping engines will be used.4GOK% One satellite will serve mobile users in 54 countries in Asia, the Middle East and the Indian sub-continent. The other satellite will be focused on Africa. Launch dates are tentatively set for late 1997 and mid 1998. Both satellites will be modified HS-601 spacecraft2 JK'  OverviewSOKKA#R$ Orbit typeGEOYK-LA#R0 Orbit rangecircularb!KLA#RB &Nb of satellites1 + 1 backupS-LLA#R$ Nb of planes1SL5MA#R$ Inclination0_LMA#R< 2Nb beams per satellite300T5MMA#R& ModulationTDMA^MFNA#R: *Mobile frequenciesS-band[MNA#R4 "Satellite mass4600 kgx7FNOA#Rn Coverage20E - 120E longitudes, 70N - 30N latitudesZNsOA#R2 &Operational date1999&OO# 1sOO1[[O*PT+O*) "VȠ$To view thisO*O page you need to register&OP# 7*1XS,-\Ajisai7 P, (" AjisaiH%# JMeans "hydrangea", also called EGP1 7'  Generalg G#^@") Designation16908 / 86061A\7A#R6Launch date12 Aug 1986lfM#j>"N ,bCountry of originJapanp#ւM#jF"H̀CV$MissionScientific: geodesy`f6A#R>"Perigee/Apogee1479/1497 kmTւA#R&Inclination50U6߃A#R(Period115.7 minfEM#j2" &JLaunch vehicleH1߃V% 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.<E' * External resourcesZV( http://gauss.crl.go.jp/targets/ajisai.htmlhttp://www.auslig.gov.au/geodesy/ajisai.htm8L' "(OTechnical data8' " SpecificationsZLކA#R2"Mass at launch685 kgT2A#R&Diameter2.15 mZކA#R2 StabilizationpassiveY22' eIt featured 1436 (120 sets) Corner-cube Reflectors and 318 Sunlight Reflection MirrorsMission: 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.71 --]SAlexis7 S, (" Alexis7# (Also called P89-11 S'  Generalg "G#^@") Designation22638 / 93026A\~A#R6Launch date23 Apr 1993t'"M#jN"N ,㹌לCountry of originUnited StatesR~DA#R"OperatorLANLv)M#jR"H̀_BMissionScientific: EUV astronomyZDA#R2"Perigee/Apogee800 kmThA#R&Inclination70L A#RPeriodn!h"M#jB" &GKTLaunch vehiclePegasus #49[$ *Cost: $17 million<"' *O External resourcesW0[' `http://nis-www.lanl.gov/nis-projects/alexis/%& When Alexis was launched, a bracket that had been damaged during ground testing broke loose, leaving one of the satellite's four solar panels dangling by only its electrical cabling and throwing off the carefully determined balance of the spin-stabilized spacecraft. When the Alexis team restored contact with the satellite more than two months after launch they discovered that not only did it have a serious wobble, but the spacecraft's magnetometer, which was intended to determine the satellite's orientation by sensing Earth's magnetic field lines, had broken when the solar paddle came loose. The Los Alamos science team and the manufacturers came up with a way to determine the satellite's orientation in May 1994. Since then it has been quite successful.% Alexis was designed to monitored the sky in three narrow energy bands between 0.06 and 0.1 keV; it also carried the Blackbeard experiment to study ionospheric effects on radio transmissions.8>' "(OTechnical data8v' " Specificationsd#>A#RF&Prime contractorAero Astro IncN v(A#RPlatformZA#R2"Mass at launch115 kgS(A#R$ Mass in orbith'=A#RNDimension1 m high x 0.6 m diameterQA#R Solar arrayj)=A#RR Stabilizationspin stabilized (2 rpm)RJA#R"DC power50 W[A#R4$Design lifetime1 year?J$ 6S-band telemetry & data51--^NAlos5 N, (" AlosG$# HAdvanced Land Observing Satellite1 N'  GeneralYG#^$") Designation`A#R>Launch dateplanned in 2002lM#j>"N ,bCountry of originJapan_JJ#d*OperatorNASDAkM#j<"H̀郉MissionRemote sensingTJ A#R&"Perigee/ApogeeQZA#R InclinationL A#RPeriodS ZG#^Cycle_XG#^0" &Launch vehicleH2AV*, (TZMass: 3900 kgHigh resolution JERS <X' *O External resourcesX1B' bhttp://eos-p71b.hq.nasda.go.jp/alos/alos.html8z' "(OTechnical data3 B( PRISM: Panchromatic Remote sensing Instrument for Stereo Mapping (2.5 m resolution)AVNIR-2: Advanced Visible and Near Infrared Radiometer (10 m resolution)PALSAR: Phased Array Lband Synthetic Aperture Radar (10 m resolution, L-band)Onboard storage: MDR, 706 Gb1z1W_2XT+2) "VȠ$To view this page you need to register&X# B21r-B.`)Program: AlouetteNX5 :4n݀" Program: AlouetteA)# <Canadian scientific program1Z1aZk1): Db"H6I6Program: AlouetteAlouette 1Alouette 2; Z1uf.bGAlouette 1GG5 :&n݀" Alouette 11 x'  Generalg GG#^@") Designation00424 / 62049A\xGA#R6GLaunch date29 Sep 1962m M#j@"N ,xW Country of originCanaday,G-M#jX"H̀?vMissionScientific: ionosphere study_A#R<"Perigee/Apogee988/1021 kmV-A#R*Inclination80.5U7A#R(Period105.2 minp#M#jF" &#*≂Launch vehicleThor Agena B[7A#R4Launch siteVandenbergZ\A#R2"Mass at launch145 kg&# <\' * External resourcesf?$' ~http://nssdc.gsfc.nasa.gov/cgi-bin/database/www-nmc?62-049A8\' "(OTechnical data8$# *Frequency: 136 MHz; \1-c Alouette 2G5 :&n݀" Alouette 21 G'  Generalg G#^@") Designation01804 / 65098A\G A#R6Launch date29 Nov 1965m wM#j@"N ,xW Country of originCanaday, M#jX"H̀?vMissionScientific: ionosphere study_wOA#R<"Perigee/Apogee499/2706 kmVA#R*Inclination79.8UOA#R(Period118.3 minp#jM#jF" &#*≂Launch vehicleThor Agena B[A#R4Launch siteVandenbergZj A#R2"Mass at launch147 kg&E # <  ' * External resourcesf?E  ' ~http://nssdc.gsfc.nasa.gov/cgi-bin/database/www-nmc?65-098A1  1^d R  : R , (" Amazonico-  & Remote sensing satellite to be developped by Brazil and Malaysia. It should cost $37 million and be put into orbit in 1998The satellite should cover the whole amazonian region to monitor the preservation of natural resources and facilitate weather forecasts.1R  1We  * T+  ) "VȠ$To view this page you need to register& * # 7 a 1-C/fa   Amos 17 *  , (" Amos 1L)a  # RAffordable Modular Optimised Satellite1  '  Generalg | G#^@") Designation23865 / 96030B\  A#R6Launch date16 May 1996m | EM#j@"N ,ΝECountry of originIsraelj P#p4(BOperatorSpacecomo"EM#jD"H̀‰MissionTelecommunications\zA#R6,Geostationary orbit4Wn! @M#jB" &2!Launch vehicleAriane V86z @* z@% Cost: $250 million. The Israeli government supports the program since 1991 with $15 million per year. Launch was insured for over $145 million The satellite was operational on 1st July 19968 @+A' "(OTechnical data=@hA' , EIRP coverage (dBW)Q!+AA0 0B⇜5Central EuropeMiddle East8hAA' " Specificationsv5AgBA#Rj&Prime contractorIsrael Aircraft Industries (IAI)RABA#R"PlatformAMOSZgBCA#R2"Mass at launch961 kgYBlCA#R0 Mass in orbit580 kgd#CCA#RFDimensions2.33 x 2.39 x 2.07 m]lC-DA#R8Solar array10.55 m spanYCDA#R0 Stabilization3 axisY-DDA#R0DC powerBOL: 1231 W]D l TransponderPolarizationDownlink FrequencyUplink FrequencyzIKc#.1V10.99014.040zJKc#.2V11.07414.124zKLc#.3V11.15814.208zKLc#.7H11.15814.208zLMc#.8H11.24214.292zL~Mc#.9H11.32614.376{MMc#0  10H11.41014.460z~MsNc#.4V11.49214.292zMNc#.5V11.57614.376zsNgOc#.6V11.66014.460_N $ Horizontal transponders are to Central Europe, Vertical transponders are to the Middle EastgO * 1gO=1g=R" 0 0F"Amos 1's Central Europe EIRP1=1hO0 0@"Amos 1's Middle East EIRP7F1B.g/iFAmos 2>, (&" Amos 2? CERS?L&FЁ& L Also called Magyarsat or Maggarsat1 '  GeneralYЁZG#^$") DesignationUA#R(Launch date1998m ZM#j@"N ,ΝECountry of originIsraelo"M#jD"H̀‰MissionTelecommunications\A#R6,Geostationary orbit4WcJG#^8" &Launch vehicleProton?QA#R Launch siteY/J* "_4 transponders would be reserved to Hungary. Hungarian Broadcasting Corp. (Nasdaq: HBCO) could bring 69% of the money, the remaining 31% would be shared 50/50 by Antenna Hungaria Rt. (state-owned) and IAI (also state-owned). Cost: $150 millionIn early 1998 the project is said to be abandonned.8,' "(OTechnical dataS,' X Ku-band (10.95 - 11.2 & 11.45 - 11.7 GHz)Y,؆A#R0(Main transponders16Y1A#R0,Backup transpondersK ؆|A#RPowerU1чA#R(Bandwidth36 MHze$|6A#RHCoverageat least Central EuropeTчA#R&EIRP max50 dBWR6܈A#R"Polarization$" 1܈11Wj1T+) "VȠ$To view this page you need to register&1# ?1C/X/k5Program: AMPTEK55 :. " Program: AMPTE) s Active Magnetospheric Particle Tracer ExplorersInternational scientific program; composed of 3 small satellites launched together in geostationary transfer orbit. CCE separated and fired its Star 13 rocket to move to a lower inclination orbit. The IRM satellite then fired its Hercules BE-3 motor to raise its apogee to more than 100 000 km. Finally the British UKS satellite separated from IRM (UKS didn't have propulsion of its own).<5S' *O External resourcesJ#' Fhttp://sd-www.jhuapl.edu/AMPTE/1SΌ1lΌGy8GA Rp㖨ԜZ=nProgram: AMPTEAMPTE CCEAMPTE IRMAMPTE UKS: Ό1l/mˍzAMPTE CCEJGˍ8 @& " AMPTE CCE1 '  Generalg ˍcG#^@") Designation15199 / 84088A\A#R6Launch date16 Aug 1984t'c3M#jN"N ,㹌לCountry of originUnited States{.M#j\"H̀d;plMissionScientific: magnetophere studya 3A#R@"Perigee/ApogeeG1121/49671 kmUpA#R(Inclination4.8UA#R(Period939.5 mins&p8M#jL" &p㉂Launch vehicleThor Delta #175Bz$ <Built by Johns Hopkins APL: 81/Ё/nSAMPTE IRMFz5 :$ " AMPTE IRM1 +'  Generalg G#^@") Designation15200 / 84088B\+A#R6Launch date16 Aug 1984n!\M#jB"N , Country of originGermany{.M#j\"H̀d;plMissionScientific: magnetophere studya \8A#R@"Perigee/Apogee560/120000 kmTA#R&Inclination27V8A#R*Period2653.4 mins&UM#jL" &p㉂Launch vehicleThor Delta #175P,$ XBuilt by the German Max Planck MPE group5U'  End of lifeU/A#R(Decay~ Nov 1987$S" : /1$l/oAMPTE UKSFS5 :$ " AMPTE UKS1 '  Generalg kG#^@") Designation15201 / 84088C\A#R6Launch date16 Aug 1984u(k<M#jP"N ,R׉Country of originUnited Kingdom{.M#j\"H̀d;plMissionScientific: magnetophere studyb!<A#RB"Perigee/Apogee1002/113417 kmVoA#R*Inclination26.9VA#R*Period2659.6 mins&o8M#jL" &p㉂Launch vehicleThor Delta #175j$ The IRM satellite created 3 'artifical comets' by releasing lithium and barium into the magnetosphere.> 81g/f/pBProgram: AMRC>B, (&" Program: AMRC4 61Ng'䉂US satellite program for broadcast of digital radio, operated by AMRC. AMRC is owned by AMSC, Worldspace, Hughes and Alcatel.Two HS-702 satellites were ordered from Hughes to be delivered in orbit in April and August 2000. An option for a 3rd satellite is included.Alcatel Espace of France, will provide the 9.5-kilowatts, S-band (2332.5-2345 MHz band), Digital Audio Radio Service (DARS) payload.1 B?' O ContactM(% PAmerican Mobile Radio Corp.Reston VA&?# 11Wq7]T+7) "VȠ$To view this page you need to register&]# = 71X//rxProgram: AMS=], ($" Program: AMSsx. , 9Advanced Meteorological SatelliteMilitary meteorological American program; see DMSP. 3 satellites launched.71,f/0s GAMSC 17 x , (" AMSC 1 xM*Y# TAmerican Mobile Satellite Corporation 11 '  Generalg YG#^@") Designation23553 / 95019A[LA#R4Launch date7 Apr 1995t'M#jN"N ,㹌לCountry of originUnited StatesfL&P#p,(NgOperatorAMSCo"M#jD"H̀‰MissionTelecommunicationsf&G#^>"/ۀ0Geostationary orbit101Wq$lM#jH" &yjLaunch vehicleAtlas CentaurT3 4kNgLwOperated by AMSC. This satellite is a twin of MSAT 1. Both satellites were ordered at the same time (with separate contracts). Both operators will provide complementary mobile telephone, radio, data, and positioning service to land, aviation, and maritime users. Each operator also will provide the other with backup and restoration capacity.While testing a transmission was sent to the satellite which caused certain components of the communication payload to overheat. The overheating damaged one of eight output hybrid matrix ports that serve the spotbeams covering the Eastern and Central United States. The other seven hybrid ports are operating in accordance with specifications. The remaining four spotbeams, covering the Mountain and Western portions of the United States, Alaska, Hawaii and the Caribbean, were not affected. Furthermore, adjustments in the operation of the satellite will be made to compensate for the power loss.l ' ;The satellite experienced in mid-1995, on separate occasions the shutdown of two solid state power amplifiers (SSPA) serving the Mountain, Central, Alaska/Hawaii and Caribbean spotbeams. These spotbeams were designed to be served by eight SSPAs with two spares. As a result of these unusual occurrences, AMSC is currently operating these spotbeams in a seven SSPA configuration which preserves one spare SSPA for such spot beams.Was leased to African Continental Telecommunications Ltd (ACTEL) of Gibraltar through 2003. The cost is $182 million. The satellite should be moved over Africa in mid-1998. ACTEL has signed with Telesat for TT&C services (building 2 earth stations + modifying 2 others) and the procurement of a new satellite by 2002. The 2 new earth stations will be in Gibraltar and Southern Africa. The total investments of ACTEL is $835 million. ACTEL has a South African subsidiary Elcor Holdings Ltd. {T $ The satellite should move to 106.5W fro two months for demonstration purposes before actually being moved over Africa.8  ' "(OTechnical data8 ' ' " SpecificationsE  B#T&Prime contractorHughesHughes (bus) and SPAR Aerospace (payload)T'  A#R&PlatformHS-601[ ] A#R4"Mass at launch2550 kgZ  A#R2 Mass in orbit1510 kgd#] A#RFDimension2.5 m x 3.5 m x 7.9 m] xA#R8Solar array20.96 m spanYA#R0 Stabilization3 axisYx*A#R0DC powerBOL: 3600 W]A#R8$Design lifetime12 years*C@% Springback antennas: 6.7 x 4.9 m x 20 kg (for launch the 2 antennas as rolled togeC@xther into a 4.9 m high cone shape atop the satellite)N'@' N L-band (1545-1559/1646.5-1660.5 MHz)YC@@A#R0(Main transponders16Z@DAA#R2,Backup transponders4V@AA#R*Power38 W (SSPA)ODAAA#RBandwidthWABC#VCoverageNorth America (4 spot beams)Alaska and Hawaii (1 beam)Carribean (1 beam)TABA#R&EIRP max58 dBWEBE' =Total bandwith: 3200 x 5 KHzEach beam transponder is equipped with eight surface acoustic wave filters covering the 29 MHz L-band allocation, allowing selection of filters to math traffic needs and to coordinate with other international users. Frequency reuse is incorporated between the North American east and west beams. The beams are combined into two L-band power pools, one covering the east and central beams, and the other covering the remaining service areas. Each power pool is generated by a hybrid matrix amplifier assembly.1 BME'  Ku-bandXEEA#R.(Main transponders1ZMEEA#R2,Backup transponders2WEVFA#R,Power100 W (TWTA)OEFA#RBandwidthy8VFGA#RpCoverageCONUS, Carribean, Canada, Alaska and HawaiiTFrGA#R&EIRP max36 dBWRGGA#R"Polarization$rGG" AG)H1/#0t)HjHQKProgram: AndesatAGjH, (," Program: Andesat)HSJ- (y 󉂂Satellite telecommunication program of the Andean countries (Bolivia, Colombia, Ecuador, Peru and Venezuela). The satellite system should be called Simon Bolivar. It should cost $300 millionFor the moment (before a satellite is launched) the company should lease capacity from Satmex The group has the 67, 78.5, 106 and 109W slots registered with the ITU, all in coordination phase. The first satellite should be launched in late 2000.1 jHJ' O ContactDSJJ% >Andesat S.A. E.M.A.Columbia<JK' *O External resourcesM&JQK' Lhttp://www.aseta.org.ec/simonb.htm1KK1WuKKKT+QKK) "VȠ$To view this page you need to register&KK# > K:L105v:LLb= # 4Anik C's specificationsď \ďiA#R60&Prime contractorHughesT A#R&0PlatformHS-376[iA#R40"Mass at launch1160 kgYqA#R00 Mass in orbit563 kgTA#R&0Diameter2.16 ma q&A#R@0Height6.6 m (2.84 m stowed)b!A#RB0 StabilizationSpin stabilizedY&A#R00DC powerBOL: 1135 W]>A#R80$Design lifetime10 years$b" 1>1U~!E6b# &Anik C's Ku-bandY"A#R00(Main transponders16Z|A#R20,Backup transponders4V"A#R*0Power15 W (TWTA)U|'A#R(0Bandwidth54 MHzN uA#R0CoverageT'A#R&0EIRP max48 dBWXu!A#R.0Polarizationlinear$E" 1!v1Uv5=E# 4Anik D's specificationsHv<A#R0&Prime contractorSpar Aerospace with technology licensed from HughesTA#R&0PlatformHS-376[<A#R40"Mass at launch1240 kgYDA#R00 Mass in orbit633 kgTA#R&0Diameter2.16 ma DA#R@0Height6.6 m (2.84 m stowed)b![A#RB0 StabilizationSpin stabilizedYA#R00DC powerBOL: 1000 W][A#R80$Design lifetime10 years$5" 1f1Uf55# $Anik D's C-bandYfA#R00(Main transponders24ZNA#R20,Backup transponders6XA#R.0Power11.5 W (TWTA)UNA#R(0Bandwidth36 MHzN IA#R0CoverageTA#R&0EIRP max36 dBWXIA#R.0Polarizationlinear$" 1J1UJy=# 4Anik E's specificationsr1JA#Rb0&Prime contractorSpar Aerospace with GE AstroUNA#R(0PlatformGE 5000[A#R40"Mass at launch2923 kgZNA#R20 Mass in orbit1781 kgRUA#R"0Length2.84 mQA#R 0Width2.26 mRU A#R"0Height2.18 m \hA#R60Solar array24.3 m spanY A#R00 Stabilization3 axisYhA#R00DC powerEOL: 3888 W_yA#R<0$Design lifetime13.5 years$" 1y1Ue5# $Anik E's C-bandY\A#R00(Main transponders24ZA#R20,Backup transponders6X\A#R.0Power11.5 W (SSPA)UcA#R(0Bandwidth36 MHzVG#^0"╬NCoverageTc A#R&0EIRP max36 dBWXeA#R.0Polarizationlinear$ " 1e1UPt6# &Anik E's Ku-bandYIA#R00(Main transponders16ZA#R20,Backup transponders2VIA#R*0Power50 W (TWTA)UNA#R(0Bandwidth54 MHzVG#^0"9CoverageTNA#R&0EIRP max51 dBWXPA#R.0Polarizationlinear$t" 1P1Rt6 <: żG"Anik E's C-band EIRP1(1({S{6 << żG"Anik E's Ku-band EIRP[*(1^H jOAnik's Ku-band transponder frequency chartr8{H : Drback()"  Anik's Ku-band transponder frequency chart (GHz)&n # kH  #$|xyxy * X v  ƀ HorizontalUplinkHorizontalDownlinkTransponderVerticalDownlinkVerticalUplinkBeam$n , #ڀH|xyxy,014.017111.717W, N, E, X!  #ڀB|xyxy"211.7301714.030E or N$, { #ڀH|xyxy,014.043211.743W, N, E, X! ! #ڀB|xyxy"211.7561814.056E or N${  #ڀH|xyxy,014.078311.778W, N, E, X!! p#ڀB|xyxy"211.7911914.091E or N$ #ڀH|xyxy,014.104411.804W, N, E, X!p#ڀB|xyxy"211.8172014.117E or N$t@#ڀH|xyxyt@{,014.139511.839W, N, E, XA#ڀ8|xyxy"211.8522114.152E$t@A#ڀH|xyxy,014.165611.865W, N, E, XA_B#ڀ8|xyxy"211.8782214.178E$AC#ڀH|xyxy,014.200711.900W, N, E, X_BC#ڀ8|xyxy"211.9132314.213E$CRD#ڀH|xyxy,014.226811.926W, N, E, XCD#ڀ8|xyxy"211.9392414.239ERDE#ڀ6|xyxy,014.261911.961WD4F#ڀ8|xyxy"211.9742514.274EEF#ڀ8|xyxy.214.2871011.987W4FvG#ڀ8|xyxy"212.0002614.300EFH#ڀ8|xyxy.214.3221112.022WvGH#ڀ8|xyxy"212.0352714.335EHYI#ڀ8|xyxy.214.3481212.048WHI#ڀ8|xyxy"212.0612814.361EYIJ#ڀ8|xyxy.214.3831312.083WIL;ˉH<SpecificationsC-bandKu-band8J14+4J]Anik C1D5 : żG" Anik C1F#J# FAlso called Telesat 9, Nahuel C11 '  Generalg lG#^@") Designation15642 / 85028B\A#R6Launch date13 Apr 1985m l5M#j@"N ,xW Country of originCanadao"M#jD"H̀‰MissionTelecommunicationsb!5A#RB,Geostationary orbitsee belowjpM#j:" &OLaunch vehicleSTS 231 0(㼉(㼉Was sold to Paracomsat an Argentine operator (when? in 1994?). Telesat obtained a 10% interest in Paracomsat and is to maintain the satellite in orbit until end-1996. The satellite was bought back by Telesat in 1997. : p- */ۀ LocationFm#:   " BeginEndPositionj#<$(*L: 13 Apr 1985107.5WFPj#0Mar 1993109.2Wj#:,.Apr 1993Apr 199772WPYj#0May 1997118.6WR.$ \Should remain non inclined throughout 19978Y' "(Technical datazC]7 >+<*$(*L: 18 Jun 1983114.5W?MXj#0Apr 1993109.1W.j#\68Jun 1993mid-June 199775.8W, inclined.Xj#\ 46mid-Aug 1997Dec 1997114.9W, inclined?$ 6Inclined since Aug 19935'  End of life\XA#R6"Out of serviceJan 1998TA#R&Causedeorbited&X# 8 ' "(Technical datazC7 >+<*+<*,Geostationary orbit104.5Ws& M#jL" &p㉂Launch vehicleThor Delta #164&# 5'  End of life\BA#R6"Out of serviceFeb 1995&h# 8B' "(Technical dataLh @0 08x `<SˉSpecificationsC-band @1 8D@1B΃3ހ3D@@HAnik D2D @@5 : żG" Anik D2H%D@@# JAlso called Telesat 8 or Satcom 4R1 @A'  Generalg @hAG#^@") Designation15383 / 84113B[AAA#R4Launch date9 Nov 1984m hA0BM#j@"N ,xW Country of originCanadao"ABM#jD"H̀‰MissionTelecommunicationsb!0BCA#RB,Geostationary orbitsee belowjBkCM#j:" &*Launch vehicleSTS 19[CC1 2jQQ7鉂Replaced Anik 1B in November 1986.Was sold in September 1993 and became Arabsat 1D2 kC)D'  LocationvCD^#0 BeginEndPosition)D%Ej#8"&(L: 9 Nov 1984113W?)DEj#R,.May 1992May 199282W (Satcom 4R)%E=Fj#6 ?110.5W (Anik D2)*EFp#T$(*7鉂September 199320E (Arabsat 1D)&=FF# 5F2G'  End of life\FGA#R6"Out of serviceMar 1995a 2GGA#R@CauseSent to the junk orbit&GH# 8GMH' "(Technical dataLHH0 08x `<SˉSpecificationsC-band8MHH1+45HIOAnik E1DHI5 : żG" Anik E1<HQI# 2Also called Telesat 111 II'  Generalg QIIG#^@") Designation21726 / 91067A\IEJA#R6Launch date26 Sep 1991m IJM#j@"N ,xW Country of originCanadao"EJ!KM#jD"H̀‰MissionTelecommunicationsfJKG#^>"/ۀ0Geostationary orbit111Wn!!KKM#jB" &bD+Launch vehicleAriane V46>K3N- (#QQOn January 20th, 1994 at 12:50 local time, the satellite ran out of control and thus all transmissions were interrupted. Control was regained at 19:00 and at 20:15 all was back into order. Soon after, it was Anik E2's turn! Those technical hitch were caused by magnetic storms.At 10:47 UT on March 26, 1996 Telesat lost both the C and Ku-bands on the satellite. This was caused by the disconnection of the South solar panel... After this, the satellite is limited to 9 C-band and 10 Ku-band transponders by lack of power.8KkN' "(Technical dataq3N!OE Z)K<ˉ<ھtXSpecificationsC-bandKu-bandC-band transponder frequency chartKu-band transponder frequency chart=kN^O' , EIRP coverage (dBW)E!OO0 0*╬N9C-bandKu-band8^OO1@ހ3}4O+4Anik E2DO+5 : żGO+O" Anik E2<Og# 2Also called Telesat 101 +'  Generalg gG#^@") Designation21222 / 91026A[ZA#R4Launch date5 Apr 1991m ǁM#j@"N ,xW Country of originCanadao"Z6M#jD"H̀‰MissionTelecommunicationsh!ǁG#^B"/ۀ0Geostationary orbit107.3Wn!6 M#jB" &_D+Launch vehicleAriane V43Ą, &QQAfter Anik E1's incident, this satellite run out of control January 20th, 1994 at 21:00 local time after a magnetic storm. It distroyed the on-board stabilization system. To face this problem, Telesat has built a system that calculates and orders the satellite's movements from an Earth station.This satellite was already victim of technical problems after launch to position its antennas.8 ' "(Technical dataqĄE Z)K<ˉ<ھtXSpecificationsC-bandKu-bandC-band transponder frequency chartKu-band transponder frequency chart=' , EIRP coverage (dBW)E40 0*╬N9C-bandKu-band8l1S }4lAnik F1D45 : żG" Anik F11 l'  GeneralY:G#^$") Designation[A#R4Launch dateearly 2000m :M#j@"N ,xW Country of originCanadao"qM#jD"H̀‰MissionTelecommunicationsh!وG#^B"/ۀ0Geostationary orbit107.3Wn!qGM#jB" &2!Launch vehicleAriane 44L&وm# 8G' "(OTechnical data8m݉' " Specifications\9A#R6&Prime contractorHughesT݉A#R&PlatformHS-702[9A#R4"Mass at launch4500 kgS;A#R$ Mass in orbitOA#RDimensionQ;ۋA#R Solar arrayS.A#R$ StabilizationUۋA#R(DC power15000 W].A#R8$Design lifetime15 years&# 0 6'  C-bandYA#R0(Main transponders36Y6A#R0,Backup transpondersK 3A#RPowerOA#RBandwidthN 3ЎA#RCoverageN A#REIRP maxM ЎkA#RG/T maxRA#R"Polarization&k #  41 ='  Ku-bandY A#R0(Main transponders48Y=A#R0,Backup transpondersK :A#RPowerOA#RBandwidthN :A#RCoverageN %A#REIRP maxM rA#RG/T maxR%A#R"Polarization&r# 11WoT+o) "VȠ$To view this page you need to register&# 8o1#05 Anna 1B@ 2 4"  Anna 1B1 >'  Generalg G#^@") Designation00446 / 62060A\>A#R6Launch date31 Oct 1962t'uM#jN"N ,㹌לCountry of originUnited Statesp#M#jF"H̀CV$MissionScientific: Geodesy`uEA#R>"Perigee/Apogee1075/1181 kmVA#R*Inclination50.1UEA#R(Period107.9 minq$aM#jH" &Gi4Launch vehicleThor Ablestar_A#R<Launch siteCape Canaveral$a" 415i5L3ANS4L, (" ANSH%# J Astronomical Netherlands Satellite1 L'  Generalg ,G#^@") Designation07427 / 74070A\A#R6Launch date30 Aug 1974r%,M#jJ"N ,㬹.Country of originNetherlands2yM#jd"H̀_BMissionScientific: UV and X-ray astronomy_A#R<"Perigee/Apogee268/2174 kmTy,A#R&Inclination98TA#R&Period99.1 minm ,M#j@" &g'KLaunch vehicleScout #89ZGA#R2"Mass at launch130 kg=$ 2First Dutch satellite5G'  End of lifeVA#R*Decay14 Jun 1977$3" 5h156hApex= 32 4"  ApexmGh&  Advanced Photovoltaic and Electronic eXperiments, also called P90-61 C'  Generalg G#^@") Designation23191 / 94046A[CA#R4Launch date3 Aug 1994t'yM#jN"N ,㹌לCountry of originUnited States|/ M#j^"H̀d;plMissionScientific: magnetosphere studyy 3_ykA#R<"Perigee/Apogee360/2534 kmV A#R*Inclination69.9SkA#R$Period115 minn!M#jB" &GKTLaunch vehiclePegasus #7ZA#R2"Mass at launch260 kgY45% iCarries a variety of advanced solar cell experiments for the US Air Force: Photovoltaic Array and Space Power Plus Diagnostics (PASP-Plus), Ferroelectric Experiment (FERRO), and Cosmic Ray Upset Experiment (CRUX) to check the impact of radiation in the Van Allen belt on the other two target instruments.8m' "(OTechnical data85# *Platform: Pegastar5m1i i56PAPMT>, (&" Program: APMT?W( /Asia Pacific Mobile TelecommunicationsHughes signed a $640 million contract awarded by a consortium of Chinese and Singaporean companies to provide satellite and ground communications equipment. The system will allow callers across a wide range of Asia to use mobile phones in areas without cellular or fixed-line service. 12000 voice channels capacity per satellite. The cost per minute should be < $1.Should be operational in 2000, 2 satellites to be launched by Long March 3B (maybe only 1 with the other one as ground spare)g@' APMT groups four Chinese companies, as well as Singapore Technologies Telemedia. The Chinese participants are China Aerospace Corp, China Unicom Satellite Telecommunication Co Ltd, China Telecommunications Broadcast Satellite Corp, and China Satellite Launch and Tracking Control General.Orbital location: 95-125E8W' "(OTechnical data8.' " Specifications\A#R6&Prime contractorHughesT.A#R&PlatformHS GEMT2 A#R&"Mass at launchS A#R$ Mass in orbitO2  A#RDimensionQ % A#R Solar arrayS x A#R$ StabilizationT%  A#R&DC power7000 W]x ) A#R8$Design lifetime12 years& O # 0 )  '  L-bandWO  A#R,(Main transpondersY / A#R0,Backup transpondersK z A#RPowerO/  A#RBandwidthN z  A#RCoverageN e A#REIRP maxM   A#RG/T maxRe A#R"PolarizationL( P$ Pwill have a 12.25 m diameter antenna11WT+P) "VȠ$To view this page you need to register&# 6116!61gDApple6 g, (" AppleI&1# L Ariane Passenger PayLoad Experiment1 g'  Generalg T@G#^@T@") Designation12545 / 81057B\@A#R6Launch date19 Jun 1981lT@AM#j>"N ,&‰Country of originIndiaV@rAD#X$OperatorISRO}0AAM#j`"H̀‰MissionTelecommunications, experimental^rAMBA#R:,Geostationary orbit102En!ABM#jB" &'+Launch vehicleAriane L03ZMBCA#R2"Mass at launch670 kgD BYC$ @Carried a C-band transponder5CC'  End of life_YCCA#R<"Out of service19 Sep 1983$CD" @CQD16o:QDD EProgram: ApstarLDD5 :0"" Program: ApstarnEQD E) "@OHong Kong program operated by APT mainly owned by Chinese firms.1D"/ۀ0Geostationary orbit138Ep#hM#jF" &9+SLaunch vehicleLong March 3~1 0u.#oThe satellite was to be slotted at 131E but this was too close from Sakura 3A (132E) and Gorizont 29 (130E). After protests from in-orbit satellite operators a slot at 138E was leased to Tonga (for about $15 million).8h' "(Technical dataA~) "0K6EIRP coverage (dBW)8/' " Specifications\A#R6&Prime contractorHughesT/ߎA#R&PlatformHS-376[:A#R4"Mass at launch1400 kgYߎA#R0 Mass in orbit650 kgT: A#R&Dry mass560 kg 1T`A#R&Diameter2.16 m` A#R>Height3.1m, 6.8 m deployedb!`"A#RB StabilizationSpin stabilizedY{A#R0DC powerEOL: 1022 W]"A#R8$Design lifetime10 years&{# 0 .'  C-bandYA#R0(Main transponders24Z.A#R2,Backup transponders6O0A#RPower15 W@B#TBandwidth20 transponders of 36 MHz4 transponders of 72 MHz~700G#^n,K6Coverage & EIRP maxSouth East Asia, up to 36 dBWSA#R$G/T max2 dB/K\0A#R6Polarizationlinear H/VEfB#TFrequenciesUplink: 5.850 - 6.425 GHzDownlink: 3.625 - 4.200 GHzh- *Telemetry: 4.198125 H & 4.199625 H GHzCommand: 5.928 H & 6.422 V GHzTransponder frequency chart1f,1,T6 <>b "Apstar 1's C-band EIRP: ,1 T88Apstar 1AF5 :$"" Apstar 1A1 1'  Generalg G#^@") Designation23943 / 96039A[1A#R4Launch date3 Jul 1996p#cM#jF"N ,Country of originHong Kongo"M#jD"H̀‰MissionTelecommunications^c0A#R:,Geostationary orbit134Et'M#jN" &9+SLaunch vehicleLong March 3 #39R.0$ \The satellite was insured for $130 million8.' "(OTechnical data=k' , EIRP coverage (dBW)J.0 04Q8Q8VerticalHorizontal8k' " Specifications\IA#R6&Prime contractorHughesTA#R&PlatformHS-376[IA#R4"Mass at launch1400 kgTLA#R&Dry mass560 kgSA#R$Diameter2.2 m`LA#R>Height3.1m, 7.5 m deployedQPA#R Solar arrayb!A#RB Stabilizationspin stabilizedN PA#RDC power]]A#R8$Design lifetime10 years&# F]' > C-band (and extended C-band)Y"A#R0(Main transponders24Z|A#R2,Backup transponders6O"A#RPower16 W@|YB#TYBandwidth4 transponders of 72 MHz20 transponders of 36 MHzSA#R$CoverageASEANTYA#R&EIRP max35 dBWTTA#R&G/T max-4 dB/K\A#R6Polarizationlinear H/VET7B#TFrequenciesUplink: 5.850 - 6.425 GHzDownlink: 3.625 - 4.200 GHzh- *Telemetry: 4.198125 H & 4.199375 H GHzCommand: 5.928 H & 6.422 V GHzTransponder frequency chart171]`*]6 ""Apstar 2R's EIRP (C-band)Warning: this map is for a 77E location only1V 1 P7 >""Apstar 2R's EIRP (Ku-band)Warning: this map is for a 77E location only9 18Apstar 3E5 :""" Apstar 32D# or Apstar 3D1 u'  GeneralYDG#^$") DesignationUu#A#R(Launch date1999p#M#jF"N ,Country of originHong Kongo"#M#jD"H̀‰MissionTelecommunicationsg&iA#RL,Geostationary orbit62, 80 or 92E\G#^*" &Launch vehicle7i$ &16 transponders1- 1W-   T+ ) "VȠ$To view this page you need to register&-  # A  1Q!6m> 5 U Program: ArabsatM 5 5 :2c" Program: Arabsat|8  D Vq=H%쉂\doZ`Satellite program of the Arab States operated by Arabsat also known as Arabsat Satellite Communications Organization (ASCO)In 1976 22 countries decided to build, launch and operate their own telecommunications geostationary satellites. At this time the Arabsat project was an innovation because even if Canada (Anik) and the United States (Comstar, Satcom and Westar) had their own satellites it was only for national communications. 3 satellites were ordered in 1981 to Arospatiale and the Earth stations were build from 1983 on by Japanese companies.1 5  '  ContactsG U , (=H%Arabsat Operation CenterTel: +966 1 404 2019Fax: +966 1 403 30721  1 h~U hd u45鉂6鉂7鉂8鉂_鉂`鉂鉂Program: ArabsatArabsat 1AArabsat 1BArabsat 1CArabsat 1DArabsat 1EArabsat 2AArabsat 2BArabsat 3A1 1UBBJ'h# NArabsat 1A, 1B & 1C's specificationsb!EA#RB&Prime contractorAerospatialeZA#R2PlatformSpacebus 100YE @A#R0 Mass in orbit700 kg @hB@B#TPayload mass122.4 kg:101.4 kg: transponders, 21 kg: antennasc" @@A#RDDimension2.26 x 1.64 x 2.26 m\@OAA#R6Solar array20.7 m spanY@AA#R0 Stabilization3 axisv5OABA#RjDC powerEOL: 1400 W (equinox), 1300 W (solstice)ZAxBA#R2 Payload power990.5 W\BBA#R6$Design lifetime7 years$xBB" 1B)C1U)CEEBBkC# >Arabsat 1A, 1B & 1C's S-bandX)CCA#R.0(Main transponders1YkCDA#R00,Backup transpondersZCvDA#R20Power2 x 50 W (TWTA)UDDA#R(0Bandwidth33 MHzVvD!EG#^0"O؝CoverageTDuEA#R&0EIRP max41 dBWZ!EEA#R20Polarizationlinear V$uEE" 1E$F1U$FHHBEfF# >Arabsat 1A, 1B & 1C's C-bandY$FFA#R00(Main transponders25YfFGA#R00,Backup transpondersPFhGA#R0Power8.5 WUGGA#R(0Bandwidth33 MHzVhGHG#^0"?؝CoverageTGgHA#R&0EIRP max31 dBWZHHA#R20Polarizationcircular$gHH" 1HI1UILL@HVI# :Arabsat 2's specificationsb!IIA#RB&Prime contractorAerospatiale[VIJA#R4PlatformSpacebus 3000[InJA#R4"Mass at launch2415 kgZJJA#R2 Mass in orbit1570 kgXnJ KA#R.Payload mass260 kg`JKA#R>Dimension2.4 x 1.6 x 2.3 mY KKA#R0 Stabilization3 axisYK2LA#R0DC powerEOL: 5000 W]KLA#R8$Design lifetime12 years$2LL" 1LL1UL48LM# *Arabsat 2's C-band]LyMA#R80(Main transponders14 + 8^MMA#R:0,Backup transponders6 + 4HyMaNB#T0Power14 transponders of 15 W (SSPA)8 transponders of 57.6 W (TWTA)KMNB#T0BandwidthMedium power: 12 x 36 MHz + 2 x 54 MHzHigh power: 8 x 36 MHzYaNGOA#R00CoverageArab StatesNNOB#T0EIRP maxMedium power transponders: 35 dBWHigh power transponders: 41 dBWTGO7A#R&0O7LG/T max-6 dB/KZOA#R20Polarizationcircular=7B#Tz0FrequenciesUplink: 5.925-6.425 GHzDownlink: 3.7-4.2 GHz$4" 1e1Ue .94# ,Arabsat 2's Ku-bandYeA#R00(Main transponders12ZQA#R20,Backup transponders5\A#R60Power93 to 96 W (TWTA)?Q.B#T~0Bandwidth8 transponders of 36 MHz4 transponders of 30 MHzYA#R00CoverageArab StatesT.ۃA#R&0EIRP max47 dBWS.A#R$0G/T max0 dB/KXۃA#R.0PolarizationlinearB. B#T0FrequenciesUplink: 13.750-14.000 GHzDownlink: 12.5-12.75 GHz$." 1 _1U_Z7.# nArabsat 2's C-band transponder frequency chart (GHz) `_Æ#$k   B X z  RHCP UplinkRHCPDownlinkChannelLHCPDownlinkLHCP UplinkBandwidth (MHz)f#ڀ<k"43.7202515.9452536Æ #ڀ<k045.9657523.7407536f#ڀ<k"43.7612535.9862536 O#ڀ<k046.0067543.7817536#ڀ<k"43.8022556.0272536O#ڀ:k.26.047756382275367#ڀ<k"43.8432576.0682536ڋ#ڀ<k046.0887583.86375367}#ڀ<k"43.8842596.1092536ڋ!#ڀ>k 266.12975103.9047536}ō#ڀ>k $63.92525116.1502536!i#ڀ>k 266.17075123.9457536ō #ڀ>k $63.97825136.2032554i#ڀ>k 266.22375143.9987554 a#ڀ>ka. $64.04375156.2687536#ڀ>k 266.28250164.0575036a#ڀ>k $64.08475176.3097536M#ڀ>k 266.32350184.0985036#ڀ>k $64.12575196.3507536M#ڀ>k 266.36450204.13950369#ڀ>k $64.16675216.3917536#ڀ>k 266.40550224.1805036$9" 121U2l[8# pArabsat 2's Ku-band transponder frequency chart (GHz) v2#$k , \ r  ƀ Horizontal UplinkHorizontal DownlinkChannelVertical DownlinkVertical UplinkBandwidth (MHz) R#ڀ@k $812.52100113.7680036 #ڀ@k 4813.78300212.5360036 R#ڀ@k $812.56277313.8097736 A#ڀ@k 4813.82477412.5777736 #ڀ@k $812.60453513.8515336 A#ڀ@k 4813.86653612.6195336 0#ڀ@k $812.64630713.8933036 #ڀ@k 4813.90830812.6613036 0z#ڀ@k $812.68506913.9320630! #ڀBk"6:13.947061012.7000630!z#ڀBk"&:12.720001113.9670030! l#ڀBk"6:13.982001212.7350030$" 1l1FNF7 >c"Arabsat 2's C-band EIRP mapFor the high power transponders, add 6 dBW1w1w Z$F 6 J)00SpecificationsS-bandC-band; K1K<<)C Arabsat 1BG)5 :&c" Arabsat 1B1 Z'  Generalg )G#^@") Designation15825 / 85048C\ZA#R6Launch date18 Jun 1985r%M#jJ"N , ?I*Country of originArab Stateso"M#jD"H̀‰MissionTelecommunications][A#R8,Geostationary orbit26EjM#j:" &QLaunch vehicleSTS 25[[ A#R4"Mass at launch1270 kg}Y $ In Oct 1992 the satellite started drifting East and was completly lost in early 1993.5  '  End of life^ 0 A#R:"Out of serviceearly 1993Y  A#R0CauseOut of control&0  # 8  ' "(Technical data\% C 7 >J)00SpecificationsS-bandC-band; ~ 1<<<~  BArabsat 1CGC  5 :&c" Arabsat 1C1 ~  '  Generalg ] G#^@") Designation21894 / 92010B\  A#R6Launch date26 Feb 1992r%] + M#jJ"N , ?I*Country of originArab Stateso"  M#jD"H̀‰MissionTelecommunicationsb!+  A#RB,Geostationary orbitsee belown! jM#jB" &eD+Launch vehicleAriane V49[ A#R4"Mass at launch1360 kgj1 0UG@cG@cWas sold to Insat in late Nov 1997 for $40 million. At that time it is said to have still 5 lifetime years. Replaced the failed Insat 2D and was renamed Insat 2R.: - */ۀ Locationp@m#:p@C    " BeginEndPosition#@j#F$8:L: 26 Feb 1992Dec 199731Ep@|Aj#*Jan 199855E&@A# 8|AA' "(Technical data|CAVB9 B)00SpecificationsS-bandC-bandBeacons: 3.7031 & 4.1999 GHz=AB' , EIRP coverage (dBW)DVBB0 0(O؝?؝쉂S-bandC-band1BC1C^CV B^C6 A#R<,Geostationary orbit30.5En!߆M#jB" &5E+Launch vehicleAriane V92K'>$ NArabsat 1C should then move to 20E8/' "(Technical datarF \]8-l =iBSpecificationsC-bandKu-bandC-band transponder frequency chartKu-band transponder frequency chart=/$' , EIRP coverage (dBW)Ei0 0*WO^UC-bandKu-band; $1!=RArabsat 3AGi5 :&c" Arabsat 3A?*# 8Also called Arabsat 2BSS11 ['  GeneralY*G#^$") Designation[[A#R4Launch dateearly 1999r%M#jJ"N , ?I*Country of originArab Stateso"M#jD"H̀‰MissionTelecommunications]MA#R8,Geostationary orbit26E\G#^*" &Launch vehicleI%M$ Jsatellite aimed at digital DBS TV8*' "(OTechnical data8b' " Specificationsb!*čA#RB&Prime contractorAerospatiale[bA#R4PlatformSpacebus 3000[čzA#R4"Mass at launch2600 kgS͎A#R$ Mass in orbitXz%A#R.Dimension29 m spanQ͎vA#R Solar arrayS%ɏA#R$ StabilizationTv)A#R&ɏ)iDC power6200 W]ɏA#R8$Design lifetime12 years&)# 1 '  Ku-bandY6A#R0(Main transponders20ZA#R2,Backup transponders8Q6A#R Power(TWTA)U6A#R(Bandwidth34 MHzN A#RCoverageV6A#R*EIRP max48.5 dBWU/A#R(G/T max0.2 dB/K\A#R6Polarizationlinear H/V=/ B#TzFrequenciesUplink: 17.3-18.1 GHzDownlink: 11.7-12.5 GHzpKz% Telecommand: 17.302 V & 17.305 H GHzTelemetry: 11.702 V & 11.705 H GHzK$ ' H Transponder Frequency chart (GHz)cz#k , \ r  Horizontal UplinkHorizontal DownlinkChannelVertical DownlinkVertical UplinkKt#8k $11.72748117.32748t#8k 417.34666211.74666Kkt#8k $11.76584317.36584t#8k 417.38502411.78502kt#8k $11.80420517.40420t#8k 417.42338611.82338t#8k $11.84256717.44256;t#8k 417.46174811.86174t#8k $11.88092917.48092;\t#:k"617.500101011.90010t#:k"&11.919281117.51928\~t#:k"617.538481211.93848t#:k"&11.957641317.55764~t#:k"617.576821411.976820t#8k"&11.996001517.5960t#:k"617.615181612.015180Rt#:k"&12.034361717.63436 t#:k"617.653541812.05354R iRt#:k"&12.072721917.67272 .t#:k"617.691902012.09190$R" 1.1W&R# 11W.TT+.) "VȠ$To view this page you need to register&T# ?.1Do:'> Program: Argos?T, ((" Program: Argos8 >-㱭+㹌לTɑLocalization 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.The ARGOS/DCS, provided by France, assists NOAA in its overall environmental mission and in the support of the Global Atmospheric Research Program. Approximately 2,000 platforms (buoys, free- floating balloons and remote weather stations) measure temperatures, pressure and altitude, and they transmit these data to the satellite. The onboard DCS receives the incoming signal, measures both the frequency and the relative time of occurrence of each transmission, and retransmits these data to the central processing facility. The DCS information is then sent to the CNES ARGOS processing center, where it is processed, distributed and stored on magnetic tape for archival purposes. The data rate is 720 bps.l% OThe system is actually only 20% booked with 2500 beacons and 170 users. The reception stations are:Fairbanks, Alaska; Wallops Island, Virginia US; Lannion, France.1 ' O Contact4l# " North America:{) Service Argos Inc.Suite 10, Mc Cormick Drive, Landover MD 20785, USATel: +1-301-925-4411Fax: +1-301-925-8995Telex: 898 146E' < Other parts of the World:~{f ( CLS Argos18, avenue Edouard Belin, 31055 Toulouse Cedex, FRANCETel: +33-5-6139-4700Fax: +33-5-6175-1014Telex: 531 752 F< ' *O External resourcesCf  ' 8http://www.argosinc.com/? $ 1rm><?$ o  Program: ArielK o 5 :.j " Program: ArielA$  # <First English space program1o  1  P  V |hڜd$te$tf$tg$th$ti$tProgram: ArielAriel 1Ariel 2Ariel 3Ariel 4Ariel 5Ariel 68  1w>  U@Ariel 1D  5 : j " Ariel 11 4 '  Generalg   G#^@") Designation00285 / 62015A\4  A#R6Launch date26 Apr 1962u( l M#jP"N ,R׉Country of originUnited Kingdomy,  M#jX"H̀?vMissionScientific: ionosphere study_l DA#R<"Perigee/Apogee398/1203 kmV A#R*Inclination53.8UDA#R(Period100.8 minq$`M#jH" &p㉂Launch vehicleThor Delta #9:$ ,First UK satellite5`'  End of lifeV1@A#R*1@ Decay24 May 1976$U@" 81@@1{>P>@@EAriel 2DU@@5 : j " Ariel 21 @A'  Generalg @iAG#^@") Designation00771 / 64015A\AAA#R6Launch date27 Mar 1964u(iA:BM#jP"N ,R׉Country of originUnited KingdomBABS#v"H̀(?v߲-MissionScientific: ionosphere and high atmosphere study_:B.CA#R<"Perigee/Apogee287/1349 kmVBCA#R*Inclination51.7U.CCA#R(Period101.3 minm CFDM#j@" &g'KLaunch vehicleScout #25&ClD# 5FDD'  End of lifeVlDDA#R*Decay18 Nov 1967$DE" 8DSE1>Ă>SEEJAriel 3DEE5 : j " Ariel 31 SEE'  Generalg E/FG#^@") Designation02773 / 67042A[EFA#R4Launch date5 May 1967u(/FFM#jP"N ,R׉Country of originUnited KingdomBFGS#v"H̀(?v߲-MissionScientific: ionosphere and high atmosphere study^FGA#R:"Perigee/Apogee499/604 kmVGHHA#R*Inclination80.6TGHA#R&Period95.6 minm HH IM#j@" &g'KLaunch vehicleScout #53P,HYI$ XFirst satellite entirely build in the UK5 II'  End of lifeVYIIA#R*Decay14 Dec 1970$IJ" 8I@J1wP>>@JJNAriel 4DJJ5 : j " Ariel 41 @JJ'  Generalg JKG#^@") Designation05675 / 71109A\JxKA#R6Launch date11 Dec 1971u(KKM#jP"N ,R׉Country of originUnited KingdomBxKLS#v"H̀(?v߲-MissionScientific: ionosphere and high atmosphere study^KLA#R:"Perigee/Apogee476/592 kmTL4MA#R&Inclination82TLMA#R&Period95.3 minm 4MMM#j@" &g'KLaunch vehicleScout #78&MN# 5MPN'  End of lifeVNNA#R*Decay12 Dec 1978$PNN" 8NO1[Ă>?OFO|Ariel 5DNFO5 : j " Ariel 51 OwO'  Generalg FOOG#^@") Designation07471 / 74077A\wOFA#R6OFNLaunch date15 Oct 1974u(OM#jP"N ,R׉Country of originUnited Kingdomx+F3M#jV"H̀_BMissionScientific: X-ray astronomy^A#R:"Perigee/Apogee504/549 kmU3A#R(Inclination2.9T:A#R&Period94.9 minm M#j@" &g'KLaunch vehicleScout #90&:͂# 5'  End of lifeV͂XA#R*Decay14 Mar 1980$|" 8X1>MAriel 6D|5 : j " Ariel 61 )'  Generalg G#^@") Designation11382 / 79047A[)A#R4Launch date2 Jun 1979u(`M#jP"N ,R׉Country of originUnited Kingdomx+؅M#jV"H̀_BMissionScientific: X-ray astronomy^`6A#R:"Perigee/Apogee472/383 kmT؅A#R&Inclination55T6ކA#R&Period92.1 minn!LM#jB" &g'KLaunch vehicleScout #100&ކr# 5L'  End of lifeVrA#R*Decay23 Sep 1990P,M$ XDownlink: 137.56 MHz, Uplink: 148.25 MHz81 '>Z?eAries 18 M, (" Aries 1_<# xAustralian Resource Information and Environment Satellite1 M'  GeneralYG#^$") DesignationUMA#R(Launch date2001p#kM#jF"N ,Country of originAustralia_ʊG#^0"H̀MissionScientific^k(A#R:"Perigee/Apogee400-450 kmQʊyA#R InclinationR(ˋA#R"Period90 min\y'G#^*" &Launch vehicleQˋxA#R Launch siteD') 7Developed by government scientific research body CSIRO, the Australian Centre for Remote Sensing (ACRES) and Auspace, a unit of MMS. Will be able to search for minerals as well as monitor environmental changes.Preliminary costs: A$200 millionA follow-up satellite could come8x' "(OTechnical data8,' " SpecificationsVA#R*&Prime contractorN ,ЎA#RPlatformZ*A#R2"Mass at launch400 kgSЎ}A#R$ Mass in orbitO*̏A#RDimensionQ})A#R ̏)MSolar arrayS̏|A#R$ StabilizationN )A#RDC power\|&A#R6$Design lifetime5 yearsqI( Its hyperspectral imaging spectrometer scanning the surface with up to 100 spectra bands covering the visible, near-infrared and shortwave infrared spectrum.Its sideways looking system means it can examine any region once every six to seven days. By building up a continuous spectrum of the earth passing below, scientists will be able to differentiate between thespectral signatures of various minerals in the rocks and soil even through moderate vegetation cover. In addition it will be able to differentiate various vegetation species and a range of environmental indicators.&e% SWhile its standard target will be a patch of ground 30 x 30 m, sophisticated software will enable the satellite to discern the mineral content of much smaller areas,11WT+e) "VȠ$To view this page you need to register&# 7G1@ <??G~Arsne7 ~, (" ArsneZ7G# n Ariane Radio-astronome Satellite ENseignement Espace1 ~ '  Generalg pG#^@") Designation22654 / 93031B\ A#R6Launch date12 May 1993m p9M#j@"N ,㱭+Country of originFranceo"M#jD"H̀㓉MissionTelecommunicationsb!9 A#RB"Perigee/Apogee17261/36793 kmU_A#R(Inclination1.8V A#R*Period1012.7 minn!_#M#jB" &D+Launch vehicleAriane V56Z}A#R2"Mass at launch154 kgu#* $ Built by Sup Aro students with the help of RACE (Radio Amateur Club de l'Espace). Made from recovery material.5}Q'  End of life`A#R>"Out of serviceOctober 1993RQA#R"CauseFailure&)# 8a' "(Technical datao)B#T,Packet radio uplink1200baud, BELL 202 (standard VHF packet radio) AFSK (FM)435.0625 435.1125 435.1375 MHz&a8# BB#T0Packet radio downlink1200baud, BELL 202 AFSK (FM)145.975 MHzJ 8* $@S-Mode linear transponder:q0wA#R`,CW telemetry beacon2446.4700 MHz, 110lpm CWh'A#RN S-mode uplink435.0625 MHz +/- 8kHzk*wJA#RT$S-mode downlink2446.5025 MHz +/- 8kHzC$ >Has a SEP Mars apogee motor8J1Z?@A Artemis8 , (" ArtemisK(H# PAdvanced Relay and Technology Mission1 y'  GeneralYHG#^$") Designation`y> A#R>> Launch dateplanned in 2000m  M#j@"N ,4"Country of originEuropeU>  G#^"H̀MissionY Y A#R0,Geostationary orbit_  G#^0" &Launch vehicleH2AYY  G#^$Launch siteR c 5 8;㨇7Artemis will test inter orbit links with SILEX (Semi-conductor Inter-satellite Link Experiment). Artemis will also provide data relay links at Ka-Band (23 to 27 GHz) and S-Band (2 GHz). It will also carry an advanced L-Band payload providing communications to mobile users.Artemis will be used as relay by Spot 4, Envisat, Oicets, etc. It is planned to lease one of the L-band transponders.A navigation terminal to guide civilian aircraft, boats and land vehicles will be placed on board. This modification will cost $8 million.%  ' Oicets (Optical Inter-orbit Communications Engineering Test Satellite) is a planned satellite, 500 kg in LEO capable of S-band and laser data relayThe satellite was developed by a consortium headed by the Italian company Alenia Aerospazio. Italy has a 40 percent share, France 21.25 percent, Germany 12 percent, Spain 7.5 percent, Britain 6.7 percent and Belgium four percent. In exchange for launching Artemis at no cost, Japan will be able to make use of 40 percent of its telecommunications capacity.8c  ' "(OTechnical data8  ' " Specificationsc" [ A#RD&Prime contractorAlenia SpazioN   A#RPlatform[[  A#R4"Mass at launch3100 kgU Y A#R(Dry mass1500 kgO  A#RDimensionQY  A#R Solar arrayY R A#R0 Stabilization3 axisT A#R&DC power2750 WUR A#R($Design lifetime % 3Has got liquid-propellant motors (1 of 410 N and 16 of 10 N thrust) and ion propulsion (15 mN and 18 mN). Tanks contain 1.5 t ergols and 40 kg Xenon.E ' < SKDR (S/Ka band Data Relay)W U A#R,(Main transpondersY A#R0,Backup transpondersK U A#RPowerO H A#RBandwidthN A#RCoverageN H A#REIRP maxM 1 A#RG/T maxR A#R"PolarizationC1  C#VFrequencies20/30 GHz23-26 GHz (interorbit)2 GHz (interorbit)~  2 47㨇The antenna is 2.85 m diameter, aimed at Envisat Silex uses optical frequencies; it will work with Spot 4 and Oicets-   '   LLMB j B#T(Main transpondersL-band (1.5/1.6 GHz): Ku-band (12/14 GHz): K   A#RPowerp.j 1@ B#T\Bandwidt 1@ hL-band: 4 MHz?Ku-band: 0.9 MHz?T @ A#R&CoverageEuropeN 1@ @ A#REIRP max@ A 1 0 㐮):A navigation payload (25 kg) was also added. It is part of the EGNOS program (European Geostationnary Navigation Overlay Service). Two Inmarsat 3 satellites are also part of this program.1@ A 1WA LB rB T+A LB ) "VȠ$To view this page you need to register&A rB # : LB B 1?o@B B cI Aryabhata:rB B , (" Aryabhataa>B GC # |Named after a ancient Indian mathematician (5th century AD)1 B xC '  Generalg GC C G#^@") Designation07752 / 75033A\xC ;D A#R6Launch date19 May 1975lC D M#j>"N ,&‰Country of originIndiay,;D E M#jX"H̀?vMissionScientific: ionosphere study^D ~E A#R:"Perigee/Apogee563/619 kmV E E A#R*Inclination50.7T~E (F A#R&Period92.6 minlE F M#j>" &s,梉Launch vehicleCosmos C](F F A#R8Launch siteKapustin YarZF KG A#R2"Mass at launch360 kgpF G $ Studied astronomy sources and relations between Earth and Sun (X-ray astronomy, solar physics and aeronomy).5KG H '  End of life`G tH A#R>"Out of serviceAfter 4 daysu4H H A#RhCauseFailure of the Indian-designed transformerVtH ?I A#R*Decay11 Feb 1992$H cI " = ?I I 1@BI I J Program: ASCMcI I 8 @,$c%" Program: ASCI J 5 8]   American Satellite CompanyProgram from ASC and CONTEL (CONtinental TELephone company). The satellites are used for GATS (Global Access Telecommunications Services).1I K 1K ]K \"J ]K : DDZSiSiSProgram: ASCASC 1ASC 21K K 1UK N N :]K K # .ASC's specificationsd#K ,L A#RF0&Prime contractorGE Astro SpaceUK L A#R(0PlatformGE 3000[,L L A#R40"Mass at launch1250 kgYL 5M A#R00 Mass in orbit665 kgc"L M A#RD0Dimension1.63 x 1.32 x 0.99 m]5M M A#R80Solar array14.33 m spanYM NN A#R00 Stabilization3 axis]M N A#R80$Design lifetime10 years$NN N " Y(N (O 1(O O ASC's C-band transponder frequency chartp6N O : Dnback()"  ASC's C-band transponder frequency chart (GHz)&(O O # nO #$j O N & P n   VerticalUplinkVerticalDownlinkTransponderChannelHorizontalDownlinkHorizontalUplinkO #ڀ2j $3.720115.945 #ڀ6j$25.96513L23.740 #ڀ2j $3.760235.985 ^ #ڀ6j$26.00513U43.780 #ڀ2j $3.800356.025^ #ڀ6j$26.04514L63.820 : #ڀ2j $3.840476.065 څ #ڀ6j$26.08514U83.860: x #ڀ2j $3.880596.105څ  #ڀ8j&46.12515L103.900x #ڀ4j"&3.9206116.145 Y #ڀ8j&46.12515U123.940 #ڀ4j"&3.9607136.185Y #ڀ8j&46.20516L143.980 8 #ڀ4j"&4.0008156.225 ي #ڀ8j&46.24516U164.0208 x #ڀ4j"&4.0409176.265ي  #ڀ8j&46.28517L184.060x #ڀ6j$(4.08010196.305 Z #ڀ8j&46.32517U204.100 #ڀ6j$(4.12011216.345Z #ڀ8j&46.36518L224.140 ; #ڀ6j$(4.16012236.385 ܏ #ڀ8j&46.40518U244.180$; " ܏ N 1܏ = 1U= [4 ' hASC's Ku-band transponder frequency chart (GHz)9= 4 c#r . L HorizontalDownlinkTransponderVerticalUplinkg R#t*11.7401914.040g4  R#t*11.8202014.120g i R#t*11.9002114.200g R#t*11.9802214.280gi 7 R#t*12.0602314.360g R#t*12.1402414.440$7 " 6 1 كA :  ASC 1B : 5 :$c%" ASC 11 k '  Generalg : G#^@") Designation15994 / 85076C\k . A#R6Launch date27 Aug 1985t' M#jN"N ,㹌לCountry of originUnited Stateso".  M#jD"H̀‰MissionTelecommunications^ o A#R:,Geostationary orbit128Wj M#j:" &SLaunch vehicleSTS 27&o # 5 4 '  End of life] A#R8"Out of serviceNov 1994?&4 # 8 ' "(Technical data^ 7 >! c~lSpecificationsC-band transponder frequency chartKu-band transponder frequency chart0 '  C-bandY A#R0(Main transponders18Y f A#R0,Backup transponders? B#T~Power36 MHz: 12 of 8.5 W (SSPA)72 MHz: 6 of 16.2 W (TWTA)h&f O B#TLBandwidth12 of 36 MHz6 of 72 MHzN A#RCoverageTO A#R&EIRP max34 dBWX I A#R.Polarizationlinear& o # 1 I '  Ku-bandXo A#R.(Main transponders6Y Q A#R0,Backup transpondersX A#R.Power16.2 W (TWTA)UQ A#R(Bandwidth72 MHzN L A#RCoverageT A#R&EIRP max42 dBWZL A#R2Polarizationlinear H$  " 6 T 1 AT  !ASC 2B  5 :$c%" ASC 2C T # @Otherwise known as Spacenet 41 '  Generalg q G#^@") Designation21227 / 91028A\ A#R6Launch date13 Apr 1991t'q M!M#jN"N M! ,㹌לCountry of originUnited Stateso" !M#jD"H̀‰MissionTelecommunicationsfM!"!G#^>"/ۀ0Geostationary orbit101Wp#!!M#jF" &p㉂Launch vehicleDelta 2 #204fB"!!$ [early 1998] Would have technical malfunctions in the Ku-band 8!0!' "(OTechnical data=!m!' , EIRP coverage (dBW)0!`!N jKZ۪!!퉂 c~lC-band, 36 MHz transpondersC-band, 72 MHz transpondersKu-bandSpecificationsC-band transponder frequency chartKu-band transponder frequency chart0 m!!'  C-bandY`!!A#R0(Main transponders18Y!B!A#R0,Backup transponders=!!B#TzPower36 MHz: 12 of 8.5 W (SSPA)72 MHz: 6 of 16 W (TWTA)h&B!)!B#TLBandwidth12 of 36 MHz6 of 72 MHzN !w!A#RCoverageT)!!A#R&EIRP max37 dBWXw!#!A#R.Polarizationlinear&!I!# 1 #!z!'  Ku-bandXI!!A#R.(Main transponders6Yz!+!A#R0,Backup transponderso-!!B#TZPower6 of 16.2 W (TWTA)2 of 30 W (TWTA)U+!!A#R(Bandwidth72 MHzN !=!A#RCoverageT!!A#R&EIRP max46 dBWZ=!!A#R2Polarizationlinear H$! !" 1!@ !1@ ! !X" ! !6 iS"#ASC 2's Ku-band EIRPThis map is for 16 W transponders, add 3 dBW for 30 W transpondersAR !) !1o@ G) !v ! !Program: AsiasatM !v !5 :2f" Program: Asiasat\3) ! !) "f품Telecommunication program operated by Asiasat 1v ! !1 ! !^ ! !V |%kkkHk#oProgram: AsiasatAsiasat 1Asiasat 2Asiasat 3Asiasat 3Asiasat 4Asiasat G:  ! !1.hC !7 !!Asiasat 1F !7 !5 :$f" Asiasat 11 !h !'  Generalg 7 ! !G#^@") Designation20558 / 90030A[h !*!A#R4Launch date7 Apr 1990p# !!M#jF"N ,Country of originHong Kongo"*! !M#jD"H̀‰MissionTelecommunicationsh!!q!G#^B"/ۀ0Geostationary orbit105.5Ep# !!M#jF" &9+SLaunch vehicleLong March 3}q!@!* $!@! !/This satellite was Westar 6 that was brought back from Space by the Shuttle in 1984. It was bought for only $58 million8!@!' "(OTechnical data=@! A!' , EIRP coverage (dBW)L@!UA!0 08<扂North beamSouth beam8 A!A!' " Specifications\UA!A!A#R6&Prime contractorHughesTA!=B!A#R&PlatformHS-376[A!B!A#R4"Mass at launch1244 kgY=B!B!A#R0 Mass in orbit620 kgTB!EC!A#R&Diameter2.16 ma B!C!A#R@Height6.6 m (2.84 m stowed)b!EC!D!A#RB StabilizationSpin stabilizedXC!`D!A#R.DC powerBOL: 850 W\D!D!A#R6$Design lifetime9 years&`D!D!# 0 D!E!'  C-bandYD!kE!A#R0(Main transponders24ZE!E!A#R2,Backup transponders6WkE!F!A#R,Power8.5 W (TWTA)UE!qF!A#R(Bandwidth36 MHzCF!G!O#n*0剂<扂Coverage andEIRP maxNorth beam: 36 dBWSouth beam: 37 dBWSqF!VG!A#R$G/T max3 dB/KZG!G!A#R2 SFD-81 to -90 dBW/m\VG! H!A#R6Polarizationlinear H/V&G!2H!# K$ H!}H!' H Transponder frequency chart (GHz)g2H!wI!# , \ z  Horizontal UplinkHorizontal DownlinkTransponderVertical DownlinkVertical Uplink}H!J!t#. 3.7201H5.945wI!J!t#.*5.9651V3.740J!K!t#. 3.7602H5.985J!K!t#.*6.0052B3.780K!.L!t#. 3.8003H6.025K!L!t#.*6.0453V3.820.L!DM!t#. 3.8404H6.065L!M!t#.*6.0854V3.860DM!ZN!t#. 3.8805H6.105M!N!t#.*6.1255V3.900ZN!pO!t#. 3.9206H6.145N! !t#.*6.1656V3.940pO! ! !pO!!t#. 3.9607H6.185 !"!t#.*6.2057V3.980!!t#. 4.0008H6.225"!8!t#.*6.2458V4.020!Â!t#. 4.0409H6.2658!N!t#.*6.2859V4.060Â!ڃ!t#0"4.08010H6.305N!f!t#0,6.32510V4.100ڃ!!t#0"4.12011H6.345f!~!t#0,6.36511V4.140! !t#0"4.16012H6.385~!!t#0,6.40512V4.180$ !!" 1!!1!F![%!F!6 ,Geostationary orbit100.5Eq$1!!M#jH" &9+SLaunch vehicleLong March 2EZ3!\!' gSecond stage orbit: 185 km x 309 km x 28 Then the Chinese perigee kick motor SPTM-17 (second flight) lifted Asiasat to 222 x 35039 km x 25.6 and the liquid apogee motor (a Leros-class dual mode liquid apogee engine built by Royal Ordnance plc, England) then circularized the orbit.Cost: $200 million8!!' "(OTechnical data=\!ь!' , EIRP coverage (dBW)E!!0 0*k+_vVC-bandKu-band8ь!N!' " Specificationsd#!!A#RF&Prime contractorGE Astro SpaceUN!!A#R(PlatformGE 7000[!b!A#R4"Mass at launch3460 kgZ!!A#R2 Mass in orbit1500 kgL b!!A#RLengthK !S!A#RWidthL !!A#RHeightYS! !A#R0 Stabilization3 axis! !҇!Y!e!A#R0DC powerBOL: 7100 W] !!A#R8$Design lifetime13 yearsrNe!4!$ The perigee engine was made in China and is being used for the first time.0 !d!'  C-bandY4!!A#R0(Main transponders24Zd!!A#R2,Backup transponders6V!m!A#R*Power55 W (TWTA)@!!B#TBandwidth20 transponders at 36 MHz4 transponders at 72 MHz`m!O!A#R>CoverageAsia and AustraliaT!!A#R&EIRP max39 dBWSO!!A#R$G/T max0 dB/KS!I!A#R$ SFD-97 dBW/m\!!A#R6PolarizationLinear H/V?I!&!B#T~FrequenciesUplink: 5.845-6.425 GHzDownlink: 3.625-4.2 GHz&!L!# K$&!!' H Transponder frequency chart (GHz)NL!_!z#Ā . L v HorizontaldownlinkTransponderVerticaldownlinkBandwidth (MHz)u!!c#$3.6401B36u_!I!c#$1A3.66036u!!c#$3.6802B36uI!3!c#$2A3.70036u!!c#$3.7203B36u3!!c#$3A3.74036u!!c#$3.7604B36u!!c#$4A3.78036u!|!c#$3.8005B36u!!c#$5A3.82036u|!f!c#$3.8406B36u!!c#$6A3.86036uf!P!c#$3.8807B36u!!c#$7A3.90036uP!:!c#$3.9208B36u!!c#$8A3.94036u:!$!c#$3.9609B36u!!c#$9A3.98036v$!!c#&4.00010B36v!!c#&10A4.02036v! "c#&4.06011B72! "҇!v!"c#&11A4.08072v ""c#&4.14012B72v"n"c#&12A4.16036&""# 1 n""'  Ku-bandX""A#R.(Main transponders9Z"w"A#R2,Backup transponders3W""A#R,Power115 W (TWTA)Uw"#"A#R(Bandwidth54 MHzh'""A#RNCoverageChina and nearby countriesT#""A#R&EIRP max52 dBWS"2"A#R$G/T max6 dB/KS""A#R$ SFD-97 dBW/mX2""A#R.PolarizationLinear="\"B#TzFrequenciesUplink: 14.0-14.3 GHzDownlink: 12.2-12.5 GHz&""# K$\""' H Transponder frequency chart (GHz);"k"c#v . L HorizontaldownlinkTransponderVerticaldownlink`""R#t12.2301`k"+"R#t 212.245`""R#t12.2903`+""R#t 412.305`"K"R#t12.3505`""R#t 612.365`K" "R#t12.4107`"k "R#t 812.425` " "R#t12.4709$k " "" 1 " "1 "u "U "u "6 <@k"&Asiasat 2's C-band EIRP1 " "1 " "V u " "6 jҨYY^ZC-bandKu-band North AsiaKu-band South Asia8E"E"' " Specifications\lE"F"A#R6&Prime contractorHughesVE"VF"A#R*PlatformHS-601HP[F"F"A#R4"Mass at launch3480 kgSVF"G"A#R$ Mass in orbitOF"SG"A#RDimensionQG"G"A#R Solar arrayYSG"G"A#R0 Stabilization3 axisTG"QH"A#R&DC power9900 W]G"H"A#R8$Design lifetime15 yearsU1QH"I"$ bHas a Marquardt R-4D-11-300 liquid propulsion0 H"3I"'  C-bandYI"I"A#R0(Main transponders28Z3I"I"A#R2,Backup transponders6VI",Geostationary orbit105.5Ej##M#j:" &㉓gLaunch vehicleProtonFL##* $8kIdentical to Asiasat 38#4#' "(OTechnical data=#q#' , EIRP coverage (dBW)l54##7 >jҨYY^ZC-bandKu-band North AsiaKu-band South Asia8q##' " Specifications\#q#A#R6&Prime contractorHughesV##A#R*PlatformHS-601HP[q#"#A#R4"Mass at launch3480 kgS#u#A#R$ Mass in orbitO"##A#RDimensionQu##A#R Solar arrayY#n#A#R0 Stabilization3 axisT##A#R&DC power9900 W]n##A#R8$Design lifetime15 years&#E## 0 #u#'  C-bandYE##A#R0(Main transponders28Zu#( #A#R2,Backup transponders6V#~ #A#R*Power55 W (TWTA)U( # #A#R(Bandwidth36 MHzI~ #] #A#RCoverageAsia, the Indian subcontinent, the Middle East and AustraliaT # #A#R&EIRP max40 dBWT] # #A#R&G/T max-1 dB/Kf% #k #A#RJ SFD-98 dBW/m (at G/T = -1 dB/K)\ # #A#R6Polarizationlinear H/V&k # ## K$ #8 #' H Transponder frequency chart (GHz)e #0 ## , Z x  Horizontal uplinkHorizontaldownlinkTransponderVerticaldownlinkVertical uplink8 # #t#. 3.6401B5.8650 #F#t#.*5.8851A3.660 ##t#. 3.6802B5.905F#\#t#.*5.9252A3.700# @#t#. 3.7203B5.945\# @##\#@#t#.*5.9653A3.740 @#"A#t#. 3.7604B5.985@#A#t#.*6.0054A3.780"A#8B#t#. 3.8005B6.025A#B#t#.*6.0455A3.8208B#NC#t#. 3.8406B6.065B#C#t#.*6.0856A3.860NC#dD#t#. 3.8807B6.105C#D#t#.*6.1257A3.900dD#zE#t#. 3.9208B6.145D#F#t#.*6.1658A3.940zE#F#t#. 3.9609B6.185F#G#t#.*6.2059A3.980F#G#t#0"4.00010B6.225G#3H#t#0,6.24510A4.020G#H#t#0"4.06011B6.2653H#KI#t#0,6.28511A4.080H#I#t#0"4.14012B6.305KI#cJ#t#0,6.32512A4.160I#J#t#0"4.12013B6.345cJ#{K#t#0,6.36513A4.140J#L#t#0"4.16014B6.385{K#L#t#0,6.40514A4.180&L#L## 1 L#L#'  Ku-bandYL#CM#A#R0(Main transponders16ZL#M#A#R2,Backup transponders4WCM#M#A#R,Power138 W (TWTA)UM#IN#A#R(Bandwidth54 MHzBM#N#B#TCoverage2 beams: 1 for China & 1 for India+ 1 steerable beamTIN#!O#A#R&EIRP max53 dBWSN#tO#A#R$G/T max6 dB/Kf%!O#O#A#RJ SFD-100 dBW/m (at G/T = 7 dB/K)\tO#B#A#R6O#B##Polarizationlinear H/V&O#h## K$B##' H Transponder frequency chart (GHz)"lh#Ձ##< * X v  ƀȀ HorizontaluplinkHorizontaldownlinkTransponderVerticaldownlinkVerticaluplinkbeam"### D $4612.2801B14.028North(Ձ#Y## P 04614.0481A12.300North/South"### D $4612.3402B14.088North(Y#݄## P 04614.1082A12.360North/South"### D $4612.4003B14.148North(݄#a## P 04614.1683A12.420North/South"# ## D $4612.4604B14.208North(a### P 04614.2284A12.480North/South" ### D $4612.5205B14.268North2#s## d 04614.2885A12.540North/South/Steerable"#2## D $4612.5806B14.328North2s### d 04614.3486A12.600North/South/Steerable"2### D $4612.6407B14.388North2### d 04614.4087A12.660North/South/Steerable"#N## D $4612.7008B14.448North2### d 04614.4688A12.720North/South/Steerable$N#A#" 1#r#1Wr#Ǝ##T+A#Ǝ#) "VȠ$To view this page you need to register&r### : Ǝ#&#1,F&#l##Asiasat 4F#l#5 :$f" Asiasat 41 &##'  GeneralYl# #G#^$") Designation# ##Q##A#RLaunch dateplanned in late 1999, will be delayed because of the Asian crisisp# ##M#jF"N ,Country of originHong-Kongo"#}#M#jD"H̀‰MissionTelecommunications^##A#R:,Geostationary orbit122E\}#7#G#^*" &Launch vehicleY##G#^$Launch site&7### 1##1W#;#a#T+#;#) "VȠ$To view this page you need to register&#a## 9;##1BSG##\#AsiastarEa##5 :"$eT" Asiastar9### ,Also called AsiaBSS1 #I#'  GeneralY##G#^$") Designatione$I##A#RHLaunch dateplanned in late-1998t'#{#M#jN"N ,㹌לCountry of originUnited Stateso"##M#jD"H̀‰MissionTelecommunications^{#H#A#R:,Geostationary orbit105Ej##M#j:" &2!Launch vehicleAriane&H### 8##' "(Technical dataL#\#0 080|SpecificationsL-band1##1W###T+\##) "VȠ$To view this page you need to register&### ?#F#1 GGF##G#Program: Aster?##, ((" Program: AsterI!F##( CTelecommunication program of Spectrum Astro Inc. Should offer communication in V-band in 2002. Would be composed of 5 GEO satellites, each providing coverage through 48 spot beams, 8 regional beams and 2 steerable beams. The system uses inter satellite links.Subject to FCC approval1 ##' O ContactH!#G#' Bhttp://www.spectrumastro.com/1#x#1Wx###T+G##) "VȠ$To view this page you need to register&x### 8#*#1SGHH*#b#?$Astrix8 #b#, (" Astrix4*### "Also called A11 b##'  Generalg #.#G#^@") Designation01778 / 65096Ap/##A#R^Launch date26 Nov 1965 at 15:47 local timem .# #M#j@"N ,㱭+Country of originFrance_#j#G#^0"H̀MissionScientific_ ##A#R<"Perigee/Apogee527/1697 kmVj##A#R*Inclination64.3U#t#A#R(Period107.5 minn!##M#jB" &A͉Launch vehicleDiamant #1Yt#;#A#R0"Mass at launch42 kg#,$' }First launch of a French satellite by a French launcher; makes France the 3rd space power. It's antenna was damaged during launch thus the technological c;#,$#apsule didn't provide any data5;#a$'  End of life_,$$A#R<"Out of service26 Nov 1965[a$$A#R4CauseNever transmited$$?$" ?$~$1GO~$$6$Program: AstraK?$$5 :.z " Program: AstraW1~$ $& cDirect Broadcasting System that covers western Europe. Operated by SES, a company founded in March 1985 by 11 shareholders. Based at the Betzdorff castle in Luxemburg.The first hotbird position of the program was 19.2E Another position at 28.8E will be started in 1997 with the Astra 2 generation.8$X$' "(OTechnical data; $$' ( Analog ModulationUX$$A#R(iBandwidth26 MHz]$E$A#R8i$Video excursion16 MHz/v[$$A#R4i"Mono bandwidth180 KHz[E$$A#R4i&Mono de-emphasis50 s]$X$A#R8i&Stereo bandwidth130 KHz]$$A#R8i*Stereo de-emphasis75 s]X$$A#R8i&Stereo expansionPanda 1$$6$" 1$g$18g$n$6$n$z € ܜ(~(~(~(~(~)~)~)~)~&)~')~Program: AstraAstra 1AAstra 1BAstra 1CAstra 1DAstra 1EAstra 1FAstra 1GAstra 1HAstra 1KAstra 2AAstra 2B9g$$1I$$M$Astra 1AEn$$5 :"z " Astra 1A1 $$'  Generalg $$G#^@") Designation19688 / 88109B\$$A#R6Launch date11 Dec 1988p#$P $M#jF"N ,L> Country of originLuxemburgf$ $M#j2"H̀‰MissionDirect TVg P $ $G#^@"/ۀ0Geostationary orbit19.2En! $ $M#jB" & D+Launch vehicleAriane V27` $ $' TV programs started on 5 Feb 1989. In 1994 a few transponders were taken over by Astra 1C because of technical problems.Astra 1A will probably be used for satellite news gathering duties from 1998 onwards (after Astra 1H is in position), being placed in an inclined orbit, and moved to either 24.3, 26, or 28.2 degrees East. ("What Satellite TV")8 $J $' "(OTechnical data= $ $' , EIRP coverage (dBW)J $H $? LY<Y9$$A#R|iPayload mass230 kg: transponders: 184 kg, antennas: 46 kg^$q$A#R:iDimension2.9 x 1.6 x 1 m\$$A#R6iSolar array19.3 m spanYq$2@$A#R0i$2@$n$ Stabilization3 axist3$@$A#RfiDC powerBOL: equinox: 2236 W, solstice: 2057 W[2@$A$A#R4i Payload power1674.4 W]@$^A$A#R8i$Design lifetime10 yearsz8A$A$B#TpiBeacon11.20300 GHz vertical11.44650 GHz horizontal&^A$A$# BA$@B$' 6 Ku-band (11.2-11.45 GHz)YA$B$A#R0i(Main transponders16Z@B$B$A#R2i,Backup transponders6OB$BC$A#RiPower45 WUB$C$A#R(iBandwidth26 MHzTBC$C$A#R&iCoverageEuropeTC$?D$A#R&iEIRP max50 dBWXC$D$A#R.iPolarizationlinearZ?D$D$A#R2iUplink14.25-14.5 GHz&D$E$# K$D$bE$' H Transponder frequency chart (GHz)?E$F$z#Ā~jk . > T HorizontalDownlinkBeamChannelVerticalDownlinkwbE$F$c#(jk$11.21425H11wF$ G$c#(jkV2211.22900wF$G$c#(jk$11.24375H23w G$G$c#(jkV1411.25850wG$nH$c#(jk$11.27325H15wG$H$c#(jkV2611.28800wnH$\I$c#(jk$11.30275H27wH$I$c#(jkV1811.31750w\I$JJ$c#(jk$11.33225H19xI$J$c#*jkV21011.34700xJJ$:K$c#*jk&11.36175H211xJ$K$c#*jkV11211.37650x:K$*L$c#*jk&11.39125H113xK$L$c#*jkV21411.40600x*L$M$c#*jk&11.42075H215xL$M$c#*jkV11611.43550$M$M$" 1M$M$1M$LN$e/M$LN$6 <`(~"+Astra 1A's EIRP (H polarization mode 1)1M$}N$1}N$N$e/LN$N$6 <`(~",Astra 1A's EIRP (H polarization mode 2)1}N$O$1O$xO$e/N$xO$6 <`(~"-Astra 1A's EIRP (V polarization mode 1)1O$O$1O$$e/xO$$6 <`(~".Astra 1A's EIRP (V polarizatioO$$xO$n mode 2)9O$S$1HIS$$e$Astra 1BE$$5 :"z " Astra 1B1 S$ɀ$'  Generalg $0$G#^@") Designation21139 / 91015A[ɀ$$A#R4Launch date2 Mar 1991p#0$$M#jF"N ,L> Country of originLuxemburgf$a$M#j2"H̀‰MissionDirect TVg $Ȃ$G#^@"/ۀ0Geostationary orbit19.2En!a$6$M#jB" &^D+Launch vehicleAriane V42&Ȃ$\$# 86$$' "(OTechnical data=\$у$' , EIRP coverage (dBW)$$? L[<[<[<[<Horizontal polarization mode 1Horizontal polarization mode 2Vertical polarization mode 1Vertical polarization mode 28у$ʄ$' " Specificationsd#$.$A#RFi&Prime contractorGE Astro SpaceUʄ$$A#R(iPlatformGE 5000[.$ޅ$A#R4i"Mass at launch2580 kgZ$8$A#R2i Mass in orbit1562 kg>ޅ$$A#R|iPayload mass354 kg: transponders: 308 kg, antennas: 46 kg`8$$A#R>iDimension2.2 x 2.9 x 2.3 m\$s$A#R6iSolar array21.5 m spanY$̇$A#R0i Stabilization3 axist3s$@$A#RfiDC powerBOL: equinox: 2790 W, solstice: 2567 WẎ$$A#R0i Payload power2136 W]@$$A#R8i$Design lifetime10 yearsz8$p$B#TpiBeacon11.45350 GHz vertical11.69650 GHz horizontal&$$# Bp$؉$' 6 Ku-band (11.45-11.7 GHz)Y$1$A#R0i(Main transponders16Z؉$$A#R2i,Backup transponders6O1$ڊ$A#RiPower60 WU$/$A#R(iBandwidth26 MHzTڊ$$A#R&iCoverageEuropeV/$ً$A#R*iEIRP max52.5 dBWX$1$A#R.iPolarizationlinearZً$$A#R2iUplink14.0-14.25 GHz&1$$# K$$$' H Transponder frequency chart (GHz)?$$z#Ā~jk . > T HorizontalDownlinkBeamChannelVerticalDownlinkx$-$c#*jk&11.46425H117x$$c#*jkV21811.47900x-$$c#*jk&11.49375H219x$$c#*jkV12011.50850x$$c#*jk&11.5232$$$5H121x$$c#*jkV22211.53800x$ $c#*jk&11.55275H223x$$c#*jkV12411.56750x $$c#*jk&11.58225H125x$q$c#*jkV22611.59700x$$c#*jk&11.61175H227xq$a$c#*jkV12811.62650x$$c#*jk&11.64125H129xa$Q$c#*jkV23011.65600x$$c#*jk&11.67075H231xQ$A$c#*jkV13211.68550$$e$" 1A$$1$$e/e$$6 <`(~"/Astra 1B's EIRP (H polarization mode 1)1$,$1,$$e/$$6 <`(~"0Astra 1B's EIRP (H polarization mode 2)1,$$1$'$e/$'$6 <`(~"1Astra 1B's EIRP (V polarization mode 1)1$X$1X$$e/'$$6 <`(~"2Astra 1B's EIRP (V polarization mode 2)9X$$1wIaJ$;$ %Astra 1CE$;$5 :"z " Astra 1C1 $l$'  Generalg ;$$G#^@") Designation22653 / 93031A\l$/$A#R6Launch date12 May 1993p#$$M#jF"N ,L> Country of originLuxemburgf/$$M#j2"H̀‰MissionDirect TVg $l$G#^@"/ۀ0Geostationary orbit19.2En!$$M#jB" &D+Launch vehicleAriane V56N*l$($$ TTests were carried out in 14.5E slot.8$`$' "(OTechnical data=($$' , EIRP coverage (dBW)`$^$? L5I\<6I\iDimension2.3 x 2.5 x 2.5 mY$Z$A#R0i Stabilization3 axisY$$A#R0iDC powerBOL: 3500 W]Z$$A#R8i$Design lifetime14 yearsr0$$B#T`iBeacon11.44850 vertical11.45100 horizontal&$$# A$ %' 4 Ku-band (10.9-11.2 GHz)$ %$Y$e%A#R0i(Main transponders18Z %%A#R2i,Backup transponders6Oe%%A#RiPower63 WU%c%A#R(iBandwidth27 MHzT%%A#R&iCoverageEuropeVc% %A#R*iEIRP max52.5 dBWX%e%A#R.iPolarizationlinearZ %%A#R2iUplink13.0-13.25 GHz;e%%$ .Backup for Astra 1AK$%E%' H Transponder frequency chart (GHz)?%%z#Ā~jk . > T HorizontalDownlinkBeamChannelVerticalDownlinkxE%v%c#*jk&10.96425H133x%%c#*jkV23410.97900xv%f%c#*jk&10.99375H235x%%c#*jkV13611.00850xf%V%c#*jk&11.02325H137x%%c#*jkV23811.03800xV%F%c#*jk&11.05275H239x%%c#*jkV14011.06750xF%6%c#*jk&11.08225H141x%%c#*jkV24211.09700x6%& %c#*jk&11.11175H243x% %c#*jkV14411.12650x& % %c#*jk&11.14125H145x % %c#*jkV24611.15600x % %c#*jk&11.17075H247x %~ %c#*jkV14811.18550x % %c#*jk&10.92075H263x~ %n %c#*jkV16410.93550$ % %" 1n % %1 %( %e/ %( %6 <`(~"3Astra 1C's EIRP (H polarization mode 1)1 %Y %1Y % %e/( % %6 <`(~"4Astra 1C's EIRP (H polarization mode 2)1Y % %1 %T%e/ %T%6 <`(~"5Astra 1C's EIRP (V polarization mode 1)1 %%1%%e/T%%6 <`(~"6Astra 1C's EIRP (V polarization mode 2)9%#%1IK#%h%֊%Astra 1DE%h%5 :"z " Astra 1D1 #%%'  Generalg h% @%G#^@") Designation23331 / 94070A% @%%[%g@%A#R4Launch date1 Nov 1994p# @%@%M#jF"N ,L> Country of originLuxemburgfg@%=A%M#j2"H̀‰MissionDirect TVg @%A%G#^@"/ۀ0Geostationary orbit19.2En!=A%B%M#jB" &D+Launch vehicleAriane V69&A%8B%# 2 B%jB%'  Location8B%B%m#:   " BeginEndPosition$jB%C%j#H"68L: 1 Nov 1994Feb 199819.2EB%D%j#.Mar 199828.2EnC%D%$ To enable the move from 19.2E to 28.2E, all services of the satellite were moved to Astra 1E & Astra 1G.8D%D%' "(OTechnical data=D% E%' , EIRP coverage (dBW)D%E%? L]<]<"]<#]<Horizontal polarization mode 1Horizontal polarization mode 2Vertical polarization mode 1Vertical polarization mode 28 E%F%' " Specifications\E%_F%A#R6i&Prime contractorHughesTF%F%A#R&iPlatformHS-601[_F%G%A#R4i"Mass at launch2924 kg`F%nG%A#R>iDimension2.3 x 2.5 x 2.5 mZG%G%A#R2iSolar array21 m spanYnG%!H%A#R0i Stabilization3 axisYG%zH%A#R0iDC powerBOL: 3500 W]!H%H%A#R8i$Design lifetime13 yearsr0zH%II%B#T`iBeacon11.44750 vertical11.45200 horizontallH%I%* $ Launched with the PVA (Perigee Velocity Augmentation) technic: initial parameters were 199.4/31123km.BII%!J%' 6 Ku-band (10.7-10.95 GHz)YI%zJ%A#R0(Main transponders14[!J%J%A#R4,Backup transponders6?OzJ%$K%A#RPower63 WUJ%yK%A#R(Bandwidth26 MHzT$K%K%A#R&CoverageEuropeTyK%!L%A#R&EIRP max52 dBWXK%yL%A#R.PolarizationlinearZ!L%L%A#R2Uplink12.75-13.0 GHz&yL%L%# R+L%KM%' V Ku-band (11.7-12.1 GHz), Astra 1E backupXL%M%A#R.(Main transponders4[KM%M%A#R4,Backup transponders18OM%MN%A#RPower63 WUM%N%A#R(Bandwidth33 MHzTMN%N%A#R&CoverageEuropeTN%JO%A#R&EIRP max52 dBWXN%O%A#R.PolarizationlinearYJO% %A#R0Uplink17.3-17.7 GHzO% %%BO%N%$ <+ Backup for Astra 1B & 1CK$ %%' H Transponder frequency chart (GHz)?N%R%z#Ā~jk . > T HorizontalDownlinkBeamChannelVerticalDownlinkx%ʁ%c#*jk&10.74125H149xR%B%c#*jkV25010.72900xʁ%%c#*jk&10.74375H251xB%2%c#*jkV15210.75850x%%c#*jk&10.77325H153x2%"%c#*jkV25410.78800x%%c#*jk&10.80275H255x"%%c#*jkV15610.81750x%%c#*jk&10.83225H157x%%c#*jkV25810.84700x%z%c#*jk&10.86175H259x%%c#*jkV16010.87650xz%j%c#*jk&10.89125H161x%%c#*jkV26210.90600xj%Z%c#*jk&10.92075H263x%҈%c#*jkV16410.93550xZ%J%c#*jk&11.71950H265x҈%‰%c#*jkV26611.73900xJ%:%c#*jk&11.75850H167x‰%%c#*jkV16811.77800$:%֊%" 1%%1%l%e/֊%l%6 <`(~"7Astra 1D's EIRP (H polarization mode 1)1%%1%%e/l%%6 <`(~"8Astra 1D's EIRP (H polarization mode 2)1%3%13%%e/%%6 <`(~"9Astra 1D's EIRP (V polarization mode 1)13%Ɍ%1Ɍ%.%e/%.%6 <`(~":Astra 1D's EIRP (V polarization mode 2)9Ɍ%g%1aJ+Lg%%&Astra 1EE.%%5 :"z " Astra 1E1 g%ݍ%'  Generalg %D%G#^@") Designation23686 / 95055A\ݍ%%A#R6Launch date19 Oct 1995p#D%%M#jF"N ,L> Country of originLuxemburgf%v%M#j2"H̀‰MissionDirect TV_%Տ%A#R<,Geostationary orbit19.2En!v%O%M#jB"Տ%O%.% &D+Launch vehicleAriane V79\8Տ%%$ pCost (launch, satellite and insurance): $320 million8O%%' "(OTechnical data=% %' , EIRP coverage (dBW)%%? L[^<\^<⵸^<ⶸ^<Horizontal polarization mode 1Horizontal polarization mode 2Vertical polarization mode 1Vertical polarization mode 28 %%' " Specifications\%u%A#R6i&Prime contractorHughesT%%A#R&iPlatformHS-601[u%$%A#R4i"Mass at launch3000 kg`%%A#R>iDimension4.5 x 3.4 x 2.8 m\$%%A#R6iSolar array26.2 m spanY%9%A#R0i Stabilization3 axisf$%%B#THiDC powerBOL: 5500 WEOL: 4700 W]9%%A#R8i$Design lifetime14 yearsz8%v%B#TpiBeacon11.20200 GHz vertical10.94850 GHz horizontal&%%# Av%%' 4 Ku-band (11.7-12.1 GHz)Y%6%A#R0(Main transponders18Z%%A#R2,Backup transponders6O6%%A#RPower85 WU%4%A#R(Bandwidth33 MHzT%%A#R&CoverageEuropeT4%%A#R&EIRP max52 dBWX%4%A#R.PolarizationlinearY%%A#R0Uplink17.3-17.7 GHzF"4%%$ D+ backup for Astra 1B, 1C & 1DK$%%' H Transponder frequency chart (GHz)?%%z#Ā~jk . > T HorizontalDownlinkBeamChannelVerticalDownlinkx%O%c#*jk&11.71950H165x%%c#*jkV26611.73900xO%?%c#*jk&11.75850H267x%%c#*jkV16811.77800x?%/%c#*jk&11.79750H169x%%c#*jkV27011.81700x/%%c#*jk&11.83650H271x%%c#*jkV17211.85600x%%c#*jk&11.87550H173x%%c#*jkV27411.89500x%%c#*jk&11.91450H275x%w%c#*jkV17611.93400x% &c#*jk&11.95350H177w% &.%xw%&c#*jkV27811.97300x &&c#*jk&11.99250H279x&t&c#*jkV18012.01200x&&c#*jk&12.03150H181xt&d&c#*jkV28212.05100$&&" 1d&&1&&e/&&6 <`(~";Astra 1E's EIRP (H polarization mode 1)1&O&1O&&e/&&6 <`(~"<Astra 1E's EIRP (H polarization mode 2)1O&&1&J&e/&J&6 <`(~"=Astra 1E's EIRP (V polarization mode 1)1&{&1{&&e/J&&6 <`(~">Astra 1E's EIRP (V polarization mode 2)9{&&1K.L &^&,L&Astra 1FE&^&5 :"z " Astra 1F1 &&'  Generalg ^&&G#^@") Designation23842 / 96021A[&Q&A#R4Launch date8 Apr 1996p#&&M#jF"N ,L> Country of originLuxemburgfQ&'&M#j2"H̀‰MissionDirect TV_&&A#R<,Geostationary orbit19.2Eo"'&&M#jD" &㉓gLaunch vehicleProton #241@&5&$ 8Launch cost: $60 million8&m&' "(OTechnical data=5&&' , EIRP coverage (dBW)m&k &? L_<_iDimension2.3 x 2.5 x 2.5 mZ & &A#R2iSolar array26 m spanYh & &A#R0i Stabilization3 axisY &t &A#R0iDC powerBOL: 4700 W] & &A#R8i$Design lifetime13 yearsr0t &C &B#T`iBeacon11.20100 vertical10.94650 horizontal& &i &# AC & &' 4 Ku-band (12.1-12.5 GHz)`i & &A#R>(Main transponders20 or 22?Z &d&A#R2,Backup transponders8O &&A#RPower82 WUd&&A#R(Bandwidth33 MHzT&\&A#R&CoverageEuropeT&&A#R&EIRP max52 dBWX\&@&A#R.Polarization&@&&linearY&m@&A#R0Uplink17.7-18.1 GHzB@&@&$ <+ backup for Astra 1A & 1EK$m@&@&' H Transponder frequency chart (GHz)?@&A&z#Ā~jk . > T HorizontalDownlinkBeamChannelVerticalDownlinkx@&+B&c#*jk&12.07050H283xA&B&c#*jkV18412.09000x+B&C&c#*jk&12.10950H185xB&C&c#*jkV28612.12900xC& D&c#*jk&12.14850H287xC&D&c#*jkV18812.16800x D&D&c#*jk&12.18750H189xD&sE&c#*jkV29012.20700xD&E&c#*jk&12.22650H291xsE&cF&c#*jkV19212.24600xE&F&c#*jk&12.26550H193xcF&SG&c#*jkV29412.28500xF&G&c#*jk&12.30450H295xSG&CH&c#*jkV19612.32400xG&H&c#*jk&12.34350H197xCH&3I&c#*jkV29812.36300xH&I&c#*jk&12.38250H299y3I&$J&c#,jkV110012.40200yI&J&c#,jk(12.42150H1101y$J&K&c#,jkV210212.44100yJ&K&c#,jk(12.46050H2103yK&L&c#,jkV110412.48000$K&,L&" 1L&]L&1 ]L&L&e/,L&L&6 <`)~"?Astra 1F's EIRP (H polarization mode 1)1]L&L&1 L&XM&e/L&XM&6 <`)~"@Astra 1F's EIRP (H polarization mode 2)1L&M&1 M&M&e/XM&M&6 <`)~"AAstra 1F's EIRP (V polarization mode 1)1M&N&1 N&N&e/M&N&6 <`)~"BAstra 1F's EIRP (V polarization mode 2)9N&N&1+L$MN&O&&Astra 1GEN&O&5 :"z " Astra 1G1 N&3O&'  Generalg O&O&G#^@") Designation25071 / 97076A[3O& &A#R4Launch date2 Dec 1997O& &N&p#O&|&M#jF"N ,L> Country of originLuxemburgf &&M#j2"H̀‰MissionDirect TV_|&A&A#R<,Geostationary orbit19.2Eo"&&M#jD" &㉓gLaunch vehicleProton #254&A&ց&# 8&&' "(OTechnical data=ց&K&' , EIRP coverage (dBW)6 &&) ".~Astra 1G8K&&' " Specifications\&&A#R6&Prime contractorHughesV&k&A#R*PlatformHS-601HP[&ƃ&A#R4"Mass at launch3379 kgSk&&A#R$ Mass in orbitPƃ&i&A#RDimensionsa &ʄ&A#R@Solar arraygallium arsenideYi&#&A#R0 Stabilization3 axisTʄ&w&A#R&DC power8000 W]#&ԅ&A#R8$Design lifetime15 yearsL w& &A#RBeaconkFԅ&&% Uses a new aerial design consisting of 2 ultra lightweight reflectors using Hughes' proprietary Contured Surface Technonlogy. Instead of conventional chemical rocket motors, Astra 1G incorporates a Xenon ion-drive for high power and reduced launch weight. But for security both standard and Xenon propulsion was installed.B &͇&' 6 Ku-band (12.5-12.75 GHz)Y&&&A#R0(Main transponders16Y͇&&A#R0,Backup transpondersX&&׈&A#R.Power98.5 W (TWTA)U&,&A#R(Bandwidth26 MHz\׈&&G#^*.~CoverageEuropeT,&܉&A#R&EIRP max52 dBWR&.&A#R"PolarizationM ܉&{&A#RUplink?&.&&# L%{&&' J Ku-band, backup for Astra 1E or 1Fm,&Z&A#RX(Main transponders18 for 1E or 22 for 1FY&&A#R0,Backup transpondersXZ& &A#R.Power98.5 W (TWTA)U&`&A#R(Bandwidth33 MHz\ &&G#^*.~CoverageEuropeT`&&A#R&EIRP max52 dBWR&b&A#R"Polarizationf& &B#TFrequenciesdownlink: 11.7-12.1 GHz for Astra 1E, 12.1-12.5 GHz for Astra 1Fuplink: 17.3-18.1 GHz&b&0&# K$ &{&' H Transponder frequency chart (GHz)?0&4&z#Ā~jk . > T HorizontalDownlinkBeamChannelVerticalDownlinkv{&&c#&jk"12.515H105v4&,&c#&jk &,&N&V10612.522v&&c#&jk"12.545H107v,&&c#&jk V10812.552v&&c#&jk"12.574H109v&&c#&jk V11012.581v&z&c#&jk"12.604H111v&&c#&jk V11212.610vz&f&c#&jk"12.633H113v&&c#&jk V11412.640vf&R&c#&jk"12.663H115v&&c#&jk V11612.670vR&>&c#&jk"12.692H117v&&c#&jk V11812.699v>&*&c#&jk"12.722H119v&&c#&jk V12012.728$*&&" 1&&1~&B&M&B&6 <0)~"CAstra 1G's EIRP9&{&1h.L&N{&&'Astra 1HEB&&5 :"z " Astra 1H1 {&&'  GeneralY&J&G#^$") DesignationU&&A#R(Launch date1997p#J&&M#jF"N ,L> Country of originLuxemburgf&u&M#j2"H̀‰MissionDirect TV_&&A#R<,Geostationary orbit19.2E|)u&P&S#vR" (&㉓g2!Launch vehicleProton or ArianeQ&&A#R Launch siteP&p&' QBackup of the 1A or 1E to 1G satellitesPARIS, May 6 1996 (Reuter) - Arianespace said it had signed a long-term contract with Societe Europeenne des Satellites (SES) to put six Astra television satellites in orbit with Ariane 4 and 5 rockets. The contract, signed by SES chief executive Romain Bausch and Arianespace executive chairman Charles Bigot, is for three firm launches and three options between 1997 and 2000.8&&' "(OTechnical data8p&&' " Specifications\&<&A#R6&Prime contractorHughesV&&A#R*PlatformHS-601HP[<&&A#R4"Mass at launch3300 kgS&@&A#R$ Mass in orbitL &&A#RLengthK @&&A#RWidthL &#&A#RHeighta &&A#R@Solar arraygallium arsenideY#&&A#R0 Stabilization3 axisT&='A#R&&='B&DC power8000 W]&'A#R8$Design lifetime15 years&=''# Q*''' T Ku-band (backup for Astra 1E, 1F or 1G)t3''A#Rf(Main transponders28 (32 for the first 5 years)Y''A#R0,Backup transpondersX'6'A#R.Power98.5 W (TWTA)k*''A#RTBandwidth26 MHz in FSS, 33 MHZ in BSSN 6''A#RCoverageT'C'A#R&EIRP max51 dBWR''A#R"PolarizationvC'M'B#TFrequenciesdownlink: 11.7-12.1 GHz for Astra 1E, 12.1-12.5 GHz for Astra 1F, 12.5-12.75 GHz for Astra 1Guplink ?&'s'# 1 M'''  Ka-bandXs''A#R.(Main transponders2Y'U'A#R0,Backup transpondersK ''A#RPowerOU''A#RBandwidthN '='A#RCoverageN ''A#REIRP maxR=''A#R"Polarization&''# 1'4'1W4'''T+'') "VȠ$To view this page you need to register&4''# 1''1~','M','6 <0)~"CAstra 1H's EIRP1']'1W]'''T+,'') "VȠ$To view this page you need to register&]''# 9' '1=O 'U 'mH'Astra 1KE'U '5 :"z " Astra 1K1  ' ''  GeneralYU ' 'G#^$") DesignationZ '9 'A#R2Launch datelate 2000p# ' 'M#jF"N ,L> Country of originLuxemburgf9 ' 'M#j2"H̀‰MissionDirect TV_ 'n 'A#R<,Geostationary orbit19.2E|) ' 'S#vR" (&2!㉓gLaunch vehicleAriane or ProtonQn '; 'A#R Launch sitej ' '% Astra's mega satellite to replace all Astra 1A to 1D. Will provide increased coverage in Eastern Europe and the CIS. It will also implement ARCS (Astra Return Channel System); this uses Ka-band to receive signals from satellite uplink systems on homes and businesses. The hardware needed on the client end is a simple as a 30 cm dish and a cheap transmitter.8; ''' "(OTechnical data= '?'' , EIRP coverage (dBW)J''0 04PjPjMission 1Mission 28?''' " Specificationsb!'#'A#RB&Prime contractorAerospatiale^''A#R:PlatformSpacebus 3000B3S[#''A#R4"Mass at launch4450 kgS';@'A#R$';@'' Mass in orbitP'@'A#RDimensionsQ;@'@'A#R Solar arrayY@'5A'A#R0 Stabilization3-axisU@'A'A#R(DC power13000 W]5A'A'A#R8$Design lifetime13 years<A'#B'$ 09 antenna reflectors1 A'TB''  Ku-bandl+#B'B'A#RV(Main transponders52 (46 after 5 years)ZTB'C'A#R2,Backup transponders7WB'qC'A#R,Power105 W (TWTA)UC'C'A#R(Bandwidth26 MHzqC'D'O#l*,PjPjCoverage & max EIRPMission 1: replacement & backup for Ku-low-band: 52 dBWMission 2: Continental Europe & UK: 53.5 dBWM C'D'A#RG/T maxRD'4E'A#R"Polarization&D'ZE'# 1 4E'E''  Ka-bandXZE'E'A#R.(Main transponders2YE' Country of originLuxemburgfL'M'M#j2"H̀‰MissionDirect TV_PM'N'A#R<,Geostationary orbit28.2EjM'N'M#j:" &㉓gLaunch vehicleProtonYN'N'G#^$Launch sitepJN'T'& Half of the capacity (14 transponders) has been booked by BskyB.The launched was originally booked with Ariane but due to technical problems with the satellite's bipropellant apogee motor the Proton launcher is more suitable (direct GEO injection). The ArN'T'~K'iane contract is not cancelled and will be used for another satellite.8N''' "(OTechnical data=T'ɀ'' , EIRP coverage (dBW)R"''0 0D}nYĂNorthern beamSouthern beam8ɀ'S'' " Specifications\''A#R6&Prime contractorHughesVS''A#R*PlatformHS-601HP['`'A#R4"Mass at launch3300 kgS''A#R$ Mass in orbitO`''A#RDimensionQ'S'A#R Solar arrayY''A#R0 Stabilization3 axisTS''A#R&DC power7000 W]']'A#R8$Design lifetime15 yearsfB'Ä'$ For security both standard and Xenon propulsion was installed.A]''' 4 Ku-band (11.7-12.5 GHz)t3Ä'x'A#Rf(Main transponders28 (32 for the first 5 years)Y'х'A#R0,Backup transpondersPx'!'A#RPower100 Wk*х''A#RTBandwidth26 MHz in FSS, 33 MHz in BSSN !'چ'A#RCoverageT'.'A#R&EIRP max52 dBWRچ''A#R"Polarization&.''# 1'ׇ'1Wׇ'+'Q'T+'+') "VȠ$To view this page you need to register&ׇ'Q'# 1+''1'؈'V Q'؈'6 Country of originLuxemburgf''M#j2"H̀‰MissionDirect TV_'L'A#R<,Geostationary orbit28.2Ej''M#j:" &2!Launch vehicleArianeYL''G#^$Launch site&'5'# 8'm'' "(OTechnical data85''' " Specificationsi(m''A#RP&Prime contractorMatra Marconi Space`'n'A#R>PlatformEurostar 2000 plus['ɏ'A#R4"Mass at launch3300 kgSn'('A#R$ɏ'('' Mass in orbitOɏ'w'A#RDimensionQ(''A#R Solar arrayYw'!'A#R0 Stabilization3 axisN 'o'A#RDC power]!''A#R8$Design lifetime15 years&o''# A'3'' 4 Ku-band (11.7-12.5 GHz)t3''A#Rf(Main transponders28 (30 for the first 5 years)Y3''A#R0,Backup transpondersP'P'A#RPower108 Wk*''A#RTBandwidth26 MHz in FSS, 33 MHz in BSSN P' 'A#RCoverageT']'A#R&EIRP max52 dBWR ''A#R"Polarization&]''# B''' 6 Ku-band (12.5-12.75 GHz)Y'p'A#R0(Main transponders16Y''A#R0,Backup transpondersK p''A#RPowerO'c'A#RBandwidthY''A#R0Coveragemobile beamN c' 'A#REIRP maxR'\'A#R"Polarization& ''# 1\''1W!''-'T+'') "VȠ$To view this page you need to register&'-'# 9'f'1HHOP"f''# (Astrid 1A-''2 4 "  Astrid 11 f'''  Generalg '?'G#^@") Designation23464 / 95002Bh'''A#RNLaunch date24 Jan 1995 at 03:54 UTm ?''M#j@"N ,ˆtCountry of originSwedeng&'{'A#RLOperatorSwedish Space Corporation@''S#v"H̀(?vd;plMissionScientific: ionosphere and magnetosphere study_{'m'A#R<"Perigee/Apogee968/1023 kmV''A#R*Inclination82.9Sm''A#R$Period105 mine'{'G#^<" &Launch vehicleCosmos 3M_''A#R<Launch sitePlesetsk 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.<'<'' *O External resourcesQ*''' Thttp://www.ssc.se/ssd/msat/astrid.html5<'''  End of life\'*(A#R6"'*(-'Out of serviceMar 1995X'(A#R.Causeshort circuitK *((A#RDecay&((# 8(+(' "(OTechnical data8(c(' " Specifications+(8(C#T%&Prime contractorPlatform: Swedish Space Corporation's Science Systems Division in SolnaPayload: Swedish Institute of Space Physics in KirunaUc((A#R(PlatformFreja CY8((A#R0"Mass at launch28 kgS(9(A#R$ Mass in orbitR((A#R"Length0.45 mQ9((A#R Width0.45 mQ(-(A#R Height0.4 ma ((A#R@Solar array4 wings, siliconb!-((A#RB Stabilizationspin stabilizedW(G(A#R,DC power28 V +-4v]((A#R8$Design lifetime3 months&G((# ?( (' 0 UHF-band (400.55 MHz)X(a(A#R.(Main transponders1Z ((A#R2,Backup transponders0N a( (A#RPower2 WU(^(A#R(Bandwidth50 kHz] ((A#R8CoverageomnidirectionalV^((A#R*EIRP max-12-0 dBV(g(A#R*PolarizationRHCPU((A#R(Data flow8 kbps&g((# ?(! (' 0 S-band (2208.629 MHz)X(y (A#R.(Main transponders1Z! ( (A#R2,Backup transponders0N y (! (A#RPower2 WV (w (A#R*Bandwidth890 kHz]! ( (A#R8CoverageomnidirectionalVw (* (A#R*EIRP max-6- 2 dBV ( (A#R*PolarizationRHCPW* ( (A#R,Data flow128 kbps& ( (# & (# (# 9 (\ (1@ OTP#\ ( (I(Astrid 2A# ( (2 4 "  Astrid 21 \ ( ('  GeneralY (' (G#^$") Designationd# ( (A#RFLaunch dateplanned in mid-1997m ' ( (M#j@"N ,ˆtCountry of originSwedeng& (_(A#RLOperatorSwedish Space Corporation@ ((S#v"H̀(?vd;plMissionScientific: ionosphere and magnetosphere study[_(M(A#R4"Perigee/Apogee1000 kmT((A#R&Inclination83L M( @(A#RPeriod( @(# (b(n@(G#^6" &Launch vehicleCosmosY @(@(A#R0Launch sitePlesetsk&n@(@(# <@()A(' *O External resourcesV/@(A(' ^http://www.ssc.se/ssc/ssd/msat/astrid2.html8)A(A(' "(OTechnical data8A(A(' " SpecificationsVA(EB(A#R*&Prime contractorN A(B(A#RPlatform[EB(B(A#R4"Mass at launch< 35 kgWB(EC(A#R,Payload mass10 kgRB(C(A#R"Length1.10 mQEC(C(A#R Width1.70 mRC(:D(A#R"Height0.30 ma C(D(A#R@Solar array4 wings, siliconb!:D(D(A#RB Stabilizationspin stabilizedWD(TE(A#R,DC power28 V +-4vUD(E(A#R($Design lifetime&TE(E(# <E( F(' *O Scientific payloadE($G(( EMMA (Electrical and Magnetic field Monitoring of the Aurora)LINDA (Langmuir INterferometer and Density experiment for Astrid-2)MEDUSA (Miniaturized Electrostatic DUal-tophat Spherical Analyzer)PIA (Photometers for Imaging the Aurora)0 F(TG('  S-bandX$G(G(A#R.(Main transponders1YTG(H(A#R0,Backup transpondersK G(PH(A#RPowerOH(H(A#RBandwidth]PH(H(A#R8CoverageomnidirectionalN H(JI(A#REIRP maxWH(I(A#R,Data flow128 kbps&JI(I(# 1I(I(1W$I(LJ(rJ(T+I(LJ() "VȠ$To view this page you need to register&I(rJ(# ?LJ(J(1OPQ%J(J(K(Program: AstroKrJ(J(5 :.z " Program: Astro@J("N ,bCountry of originJapanr%/N( O(M#jJ"H̀jMissionScientific: Sun study^N(kO(A#R:"Perigee/Apogee573/639 kmV O(O(A#R*Inclination31.3TkO(!(A#R&O(!(L(Period96.7 minjO((M#j:" & Launch vehicleMu 3S1Z!((A#R2Launch siteKagoshimaZ(?(A#R2"Mass at launch195 kg&(e(# 5?(('  End of lifeVe((A#R*Decay11 Jul 1991$((" 8(L(1=PQ(L(((Astro BD((5 : z " Astro B7L(ǂ(# (Also called Tenma1 (('  Generalg ǂ(_(G#^@") Designation13829 / 83011A\((A#R6Launch date20 Feb 1983l_('(M#j>"N ,bCountry of originJapanx+((M#jV"H̀_BMissionScientific: X-ray astronomy^'((A#R:"Perigee/Apogee431/438 kmV(S(A#R*Inclination31.5T((A#R&Period93.3 minjS((M#j:" & Launch vehicleMu 3S1\(m(A#R6Launch siteTanegashimaZ(dž(A#R2"Mass at launch220 kg&m((# 5dž("('  End of lifeV(x(A#R*Decay17 Dec 1988$"((" 8x(ԇ(1wQQ)ԇ(((Astro CD((5 : z " Astro C7ԇ(O(# (Also called Ginga1 (('  Generalg O((G#^@") Designation17480 / 87012A[(B(A#R4Launch date5 Feb 1987l((M#j>"N ,bCountry of originJapanx+B(&(M#jV"H̀_BMissionScientific: X-ray astronomy^((A#R:"Perigee/Apogee395/450 kmT&(؊(A#R&Inclination31R(*(A#R"Period93 mink؊((M#j<" & Launch vehicleMu 3S 2Z*((A#R2Launch siteKagoshimaZ(I(A#R2"Mass at launch420 kg&(o(# <I((' * External resourcese>o((' |http://www.astro.isas.ac.jp/xray/mission/ginga/gingaE.html&(6(# 5(k('  End of lifeU6((A#R(Decay1 Nov 1991$k((" 8((1% QQ*(`(`(Astro DD(`(5 : z " Astro DsP(ӎ(# Also called Asuka or ASCA (Advanced Satellite for Cosmology and Astrophysics)1 `(('  Generalg ӎ(k(G#^@") Designation22521 / 93011Ah'(ӏ(A#RNLaunch date20 Feb 1993 at 02:00 UTlk(K(M#j>"ӏ(K((N ,bCountry of originJapanRӏ((A#R"OperatorISASx+K((M#jV"H̀_BMissionScientific: X-ray astronomy^(s(A#R:"Perigee/Apogee538/645 kmV((A#R*Inclination31.1Ts((A#R&Period96.5 mink((M#j<" & Launch vehicleMu 3S 2Z((A#R2Launch siteKagoshimaZ(<(A#R2"Mass at launch420 kg((& _First truly telescopic telecope in space and first Japanese X-ray imaging telescope (its previous X-ray satellites have carried x-ray detectors without focussing optics).<<(M(' *O External resourcesi((. ,http://www.astro.isas.ac.jp/xray/mission/asca/ascaE.htmlhttp://nssdca.gsfc.nasa.gov/asca/asca.html8M((' "(OTechnical data8(T(' " SpecificationsL((A#R&Prime contractorNagoya's university and the Goddard Space Flight CenterN T(/(A#RPlatformZ((A#R2"Mass at launch420 kgS/((A#R$ Mass in orbity8(U(A#RpDimension1.2 m diameter x 2.8 m long (4 m deployed)Q((A#R Solar arraySU((A#R$ StabilizationX(Q(A#R.DC powerBOL: 600 W`((A#R>$Design lifetime2 + 2 yearsQ(`(- (۰FIIs equipped with 4 focal mirrors of 3.5 m and CCD detectors. The sensitiveness should be 100 times greater than HEAO 2. It carries CCD detectors and an imaging proportional counter. The spacecraft is sensitive to the 0.5-12 keV energy range. The Asuka telescope has a 30 arcmin field of view and 2 arcmin spatial resolution.Telemetry: 2256.22 MHz (playback: 262144 bps, via DSN)8((1cQ+(((Astro ED`((5 : z " Astro EL)(((# Rplanned to be launched in 1999 by Mu-5<(d(' *O External resources|(((. ,http://www.astro.isas.ac.jp/xray/mission/astroe/astroeE.htmlhttp://lheawww.gsfc.nasa.gov/docs/xray/astroe/astroe.html1d(?(1W,?(((T+(() "VȠ$To view this page you need to register&?((# C((1 TPl-(?( )Program: AstrolinkC(?(, (0" Program: Astrolink(0(, &H;eAstrolink is a Lockheed Martin telecommunication program, based on Ka-band. It was partially approved by FCC in May 1997 (not the inter orbit links). 9 GEO interconnected satellites are planned. Cost: $4.25 billion Should be ready in 2002. TRW should provide the payload Lockheed proposes to offer services such as global Internet service, videoconferencing, distance learning, telemedicine, high-speed data networks and "bandwidth on demand." <?(l(' *O External resourcesC0((' 8http://www.astrolink.com8l( )' "(Technical data( )(()* "[2 satellites per slots at 97W, 21.5W, 38E & 130E1 satellite at 175.25EUser terminals: 65 to 120 cm in diameter Fixed gateway terminals: 3 mSatellite to regional gateway links: 155 mbpsSatellite to user links: from 16 kbps to 9.6 mbps (depending on user requirements and dish sizes: the larger the dish, the faster the data rate)The standard low-cost terminal will enable transmission speeds from 16 kpbs to 384 kbps8 ))' " Specificationse$))A#RH&Prime contractorLockheed MartinS))A#R$PlatformA2100T)')A#R&"Mass at launchS)z)A#R$ Mass in orbitO'))A#RDimensionQz))A#R Solar arrayS)m)A#R$ StabilizationN ))A#RDC powerUm))A#R($Design lifetime&)6)# 1 )g)'  Ka-bandY6))A#R0(Main transponders68Yg))A#R0,Backup transpondersK )d)A#RPowerI))B#TBandwidth64 x 125 MHz (user terminal)4 x 250 MHz (gateway terminal)`d)O)A#R>Coveragemultiple spot beamN ))A#REIRP max\O))A#R6Polarizationlinear H/VM))B#TFrequenciesUplink: 28.35-28.6 and 29.25-29.5 GHzDownlink: 19.7-20.2 GHz%) )& On-board processingA Time Division Multiplexed (TDM)/Frequency Division Multiple Access (FDMA) scheme is to be used on the user terminal uplinks. On user terminal downlinks, a 130 Mbps TDM signal will be transmitted in each beam from each satellite.1) )1W. )2 )X )T+ )2 )) "VȠ$To view this page you need to register& )X )# 92 ) )1laR/ ) )c@)Asusat 19 X ) ), (" Asusat 11 ) )'  GeneralY )T )G#^$") Designationd# ) )A#RFLaunch dateplanned in mid 1998t'T ), )M#jN"N ,㹌לCountry of originUnited StatesU ) )G#^"H̀MissionT, ) )A#R&"Perigee/ApogeeQ )& )A#R InclinationL )r )A#RPeriodj& ) )M#j:" &㻦ʼnLaunch vehicleTaurus[r )7)A#R4Launch siteVandenberg ))' +Designed by Arizona State UniversityIt is equipped with 2 digital cameras for tracking changes to Earth's coasts and forests. Has a HAM payload<7)/)' *O External resourcesX1))' bhttp://enws229.eas.asu.edu/asusat/asusat.html8/))' "(OTechnical data?) @)' 0O Frequency chart (MHz)) @)X )W3)c@)$ fUplink: 145.990 MHz FM Downlink: 436.700 MHz FM1 @)@)1W0@)@)A)T+c@)@)) "VȠ$To view this page you need to register&@)A)# = @)KA)1RS1KA)A)VB)Program: ATSIA)A)5 :*_c%" Program: ATSKA)VB)) 3 Application Technology SatelliteAmerican multipurpose satellites designed to test new space instruments and demonstrate new satellite technologies.1A)B)12B)C)z2VB)C)H `dMZSSSSSProgram: ATSATS 1ATS 3ATS 5ATS 66B)7C)1R37C)yC)!I)ATS 1B C)yC)5 :_c%" ATS 11 7C)C)'  Generalg yC)D)G#^@") Designation02608 / 66110A[C)lD)A#R4Launch date7 Dec 1966t'D)D)M#jN"N ,㹌לCountry of originUnited States=lD)jE)M#jz"H̀DVMissionMeteorology and communication experimentation^D)E)A#R:,Geostationary orbit149Wq$jE)9F)M#jH" &mO{Launch vehicleAtlas Agena DE)4G)% Transmitted the first high resolution photos of the Earth. It also relayed color television across the U.S. and was the first satellite to permit two-way VHF communication between ground and aircraft in flight.<9F)pG)' *O External resourcesV/4G)G)' ^http://sulu.lerc.nasa.gov/dglover/ats1.html&pG)G)# 5G)!H)'  End of lifeWG)xH)A#R,"Out of serviceyes&!H)H)# 8xH)H)' "(OTechnical dataK(H)!I)# PTransmits on 137.35 MHz (weak signal)6H)WI)1cARS4WI)I)Ɓ)ATS 3B !I)I)5 :_c%" ATS 31 WI)I)'  Generalg I)1J)G#^@") Designation03029 / 67111A[I)J)A#R4Launch date5 Nov 1967t'1J)K)M#jN"N ,㹌לCountry of originUnited Statesx+J)xK)M#jV"H̀DVMissionMeteorology experimentationb!K)K)A#RB,Geostationary orbitsee belowq$xK)KL)M#jH" &mO{Launch vehicleAtlas Agena D_K)L)A#R<Launch siteCape CanaveralKL)YN)' Carried advanced communications, meteorology, and navigation experiments. Provided the first color pictures of the Earth and proved the interest of maritime communications via satellite. Transmitted the first space communication between an Earth station and a plane on 21 Nov 1967 above the Atlantic.Since 1980 the satellite transmit data to and from Antartica, especially the Internet.: L)N)- */ۀ LocationvYN) O)^#0 BeginEndPositionN)O)j#4"&(L: 5 Nov 196747W O))j#2"$Jun 198O))!I)8...105WL)O)h)# ROldest satellite still station keeping<))' *O External resourcesV/h))' ^http://sulu.lerc.nasa.gov/dglover/ats3.html&) )# 8)X)' "(OTechnical datanK )Ɓ)# Transmits on 136.37 and 137.35 MHz (weak signals) or 135.555-135.650 MHz6X))1RwS5)>) )ATS 5B Ɓ)>)5 :_c%" ATS 51 )o)'  Generalg >)ւ)G#^@") Designation04068 / 69069A\o)2)A#R6Launch date12 Aug 1969t'ւ))M#jN"N ,㹌לCountry of originUnited States22)%)M#jd"H̀‰MissionTelecommunications experimentationY)~)A#R0,Geostationary orbit\%)ڄ)G#^*" &Launch vehicle_~)9)A#R<Launch siteCape CanaveralkGڄ))$ Provided data on auroran phenomenons and propagation in ionosphere.<9))' * External resourcesV/)6)' ^http://sulu.lerc.nasa.gov/dglover/ats5.html&)\)# 56))'  End of lifeW\))A#R,"Out of serviceyes$) )" 6)B)1S6B)))ATS 6B ))5 :_c%" ATS 61 B))'  Generalg ))G#^@") Designation07318 / 74039A\)x)A#R6Launch date30 May 1974t'))M#jN"N ,㹌לCountry of originUnited Stateso"x)[)M#jD"H̀‰MissionTelecommunications]))A#R8,Geostationary orbit95Wo"[)')M#jD" &^]Launch vehicleTitan 3 #78Z))A#R2"Mass at launch930 kg')J)+ $= Numerous telecommunications experiments were carried out. With the satellite's 9 m antenna only small Earth antennas were needed. Scholar TV was provided to american children in the Rockies and Alaska. It was also used by SITE (Satellite Instructional Television Experiment) in 1975 to try and solve educational problems of India (half success). It also enabled communications between 2 unmanned spacecrafts.<))' *O External resourceseJ)). ,http://sulu.lerc.nasa.gov/dglover/ats6.htmlhttp://uss-enterprise.bu.edu/BUSPACE/ATS6/ats6.html&)?)# 5)t)'  End of life_?)Ӎ)A#R<"Out of service30 Jun 1979$t))" 5Ӎ),)1aR S7,)a))Aura5 )a), (" Aura5,))# $Also called D2B1 a)ǎ)'  Generalg ).)G#^@") Designation08332 / 75092A\ǎ))A#R6Launch date27 Sep 1975m .) )M#j@"N ,㱭+Country of originFrance) ))r%)~)M#jJ"H̀_BMissionScientific: astronomy^ ))A#R:"Perigee/Apogee476/697 kmV~)2)A#R*Inclination37.1T))A#R&Period96.5 mino"2))M#jD" &A͉Launch vehicleDiamant #12Z)O)A#R2"Mass at launch120 kg&)u)# 5O))'  End of life_u) )A#R<"Out of service28 Dec 1976_)h)A#R<CauseStopped transmittingV ))A#R*Decay30 Sep 1982$h))" A)#)1ST8#)t))Program: AuroleQ)t)8 @4x&" Program: AuroleT/#))% ^Also called OreolFrench scientific program1t))19)t){:)t)A Rtqe2y`3y`4y`Program: AuroleAurole 1Aurole 2Aurole 3: ))1S:)))Aurole 1Jt))8 @&x&" Aurole 11 )))'  Generalg ))G#^@") Designation05729 / 71119A\)))A#R6Launch date27 Dec 1971m )Y)M#j@"N ,㱭+Country of originFrancey,))M#jX"H̀?vMissionScientific: ionosphere study_Y)1)A#R<"Perigee/Apogee388/1954 kmT))A#R&Inclination74U1))A#R(Period108.8 minl)F)M#j>" &s,梉Launch vehicleCosmos CY))A#R0Launch sitePlesetsk$F))" : ))1SЃS;)G))Aurole 2J)G)8 @&x&" Aurole 21 )x)'  Generalg G))G#^@") Designation07003 / 73107A\x);)A#R6Launch date26 Dec 1973m ))M#j@"N ,㱭+Country of originFrancey,;)!)M#jX"H̀?vMissionScientific: ionosphere study_))A#R<"Perigee/Apogee387/1441 kmT!))A#R&Inclination74U)))A#R(Period103.3 minl))M#j>" &s,梉Launch vehicleCosmos CY)))A#R0Launch sitePlesetsk$))" : )L)1S<L)):*Aurole 3F))5 :$x&" Aurole 31 L))'  Generalg )*)G#^@") Designation12848 / 81093A\))A#R6Launch date21 Sep 1981m *) *M#j@"N ,㱭+Country of originFrance) *)@)*S#v"H̀(?vd;plMissionScientific: ionosphere and magnetosphere study_ **A#R<"Perigee/Apogee394/1672 kmV*T*A#R*Inclination82.5U**A#R(Period105.8 minm T**M#j@" &ቂLaunch vehicleCyclone 3$*:*" @*z*1 ST=z**e*Program: AuroraP:**8 @2Yl#" Program: Auroraez*e*6 <ap]D"Telecommunication program operated by Alascom. Aurora 2 is partly operated with GE Americom1**1>**e+e**: DV[Y]]Program: AuroraAurora 1Aurora 21*,*1U?,**!*=*i*# 4Aurora's specificationsd#,**A#RF0&Prime contractorGE Astro SpaceUi*"*A#R(0PlatformGE 3000Y*{*A#R00 Mass in orbit760 kgc""**A#RD0Dimension1.63 x 1.32 x 0.99 mY{*7*A#R00 Stabilization3 axisY**A#R00DC powerBOL: 1400 Wm+7**B#TV0$Design lifetime1: 10 years2: 12 years$*!*" 9*Z*1? T@Z**@*Aurora_1E!**5 :"Yl#" Aurora 1:Z**# .Also called Satcom 51 * *'  Generalg *q*G#^@") Designation13631 / 82105A\ **A#R6Launch date28 Oct 1982t'q*A *M#jN"N ,㹌לCountry of originUnited Stateso"* *M#jD"H̀‰MissionTelecommunicationsb!A * *A#RB,Geostationary orbitsee belows& * *M#jL" &p㉂Launch vehicleThor Delta #165[ * *A#R4"Mass at launch1084 kg& * *# : *@ *- */ۀ Location * *m#:   " BeginEndPosition@ *P *j#8$(*L: 28 Oct 1982139W} * *j#&1992?143WP *P *j#2"$Feb 1995...105W& *v *# 8P * *' "(Technical data<v * *) "&#Specifications0 **'  C-bandY *s*A#R0(Main transponders24Z**A#R2,Backup transponders4Ws*$*A#R,Power8.5 W (SSPA)U*y*A#R(Bandwidth36 MHzN $**A#RCoverageTy*'@*A#R&*'@*!*EIRP max34 dBWX*@*A#R.Polarizationlinear$'@*@*" 9@*@*1P:TA@*%A*DH*Aurora 2I@*%A*8 @$Yl#" Aurora 2;@*`A*# 0Also called Satcom C51 %A*A*'  Generalg `A*A*G#^@") Designation21392 / 91037A\A*TB*A#R6Launch date29 May 1991t'A*B*M#jN"N ,㹌לCountry of originUnited Stateso"TB*7C*M#jD"H̀‰MissionTelecommunicationsfB*C*G#^>"/ۀ0Geostationary orbit139Wp#7C* D*M#jF" &p㉂Launch vehicleDelta 2 #205[C*hD*A#R4"Mass at launch1338 kg& D*D*# 8hD*D*' "(Technical dataND*KE*7 >Z##ھEIRP coverage (dBW)SpecificationsC-band transponder frequency chart0 D*{E*'  C-bandYKE*E*A#R0(Main transponders24Z{E*.F*A#R2,Backup transponders8VE*F*A#R*Power11 W (SSPA)U.F*F*A#R(Bandwidth36 MHzYF*tG*B#TCoverageOdd transponders to the United StatesEven transponders to Alaska and CanadaTF*G*A#R&EIRP max34 dBWXtG* H*A#R.Polarizationlinear$G*DH*" 1 H*uH*1BuH*H*QDH*H*6 <8]"HAurora 2's EIRP map5uH*H*1T TUCH*0I*v*AXAF5 H*0I*, (" AXAFJ'H*zI*# NAdvanced X-ray Astrophysics Facility1 0I*I*'  GeneralYzI*J*G#^$") Designationd#I*hJ*A#RFLaunch dateplanned in Aug 1998t'J*J*M#jN"N ,㹌לCountry of originUnited StatesRhJ*.K*A#R"OperatorNASAx+J*K*M#jV"H̀_BMissionScientific: X-ray astronomyc".K* L*A#RD"Perigee/Apogee10000/140000 kmVK*_L*A#R*Inclination28.5L L*L*A#RPeriodk$_L*M*G#^H" &Launch vehicleSTS 93 with IUSQL*gM*A#R Launch siteM*(N*3 4r#W10 m focal length telescopeACIS: camera with 10 X-ray CCD imagers based on Astro D technologyHRC: camera similar to Rosat technology<gM*dN*' *O External resourcesn@(N*N*. ,http://xrtpub.harvard.edu/pub.htmlhttp://asc.harvard.edu/8dN* O*' "(OTechnical data8N*BO*' " SpecificationsY O*O*A#R0&Prime contractorTRWN BO* *A#RPlatformO* *H*[O*g*A#R4"Mass at launch5200 kgS **A#R$ Mass in orbitOg* *A#RDimensionQ*Z*A#R Solar arrayS **A#R$ StabilizationN Z**A#RDC powerU*P*A#R($Design lifetime&*v*# 1P**1WD**!*T+v**) "VȠ$To view this page you need to register&*!*# ?*`*1gTkUE`***Program: AyameK!**5 :.7 " Program: Ayamem`*C*+ & Means "iris", also called ECS (Experimental Communication Satellite)Japanese telecommunication program<**' *O External resourcesb;C**' vhttp://yyy.tksc.nasda.go.jp/Home/This/This-e/ecs_e.html1**1F*t*b(*t*: DP✀Program: AyameAyame 1Ayame 28**1UG***Ayame 1Dt**5 : 7 " Ayame 17*'*# (Also called ECS 11 *X*'  Generalg '**G#^@") Designation11261 / 79009A[X**A#R4Launch date6 Feb 1979l**M#j>"N ,bCountry of originJapanu.**G#^\"H̀MissionTelecommunications, experimentalb!*]*A#RB"Perigee/Apogee29259/37424 kmU**A#R(Inclination4.9T]**A#R&Period1313 minf*l*M#j2" &JLaunch vehicleN1Z*Ɖ*A#R2"Mass at launch130 kg&l**# 5Ɖ*!*'  End of lifeo.**A#R\"Out of serviceCollided with the top stage$!**" 8**1UH*0**Ayame 2D*0*5 : 7 " Ayame 21 *a*'  Generalg 0*ȋ*G#^@") Designation11715 / 80018A\a*$*A#R6Launch date22 Feb 1980lȋ**M#j>"N ,bCountry of originJapanu.$**G#^\"H̀MissionTelecommunications, experimentalb!*g*A#RB"Perigee/Apogee32785/36839 kmU**A#R(Inclination1.4Vg**A#R*Period1386.6 minf*x*M#j2" &JLaunch vehicleN1Z*Ҏ*A#R2"Mass at launch130 kg&x**# 5Ҏ*-*'  End of lifea **A#R@"Out of serviceAfter launch?$-**" 5* *1UUI *A**Azur* **5 *A*, (" Azur7 *x*# (Also called GRS A1 A**'  Generalg x**G#^@") Designation04221 / 69097A[*k*A#R4Launch date8 Nov 1969n!**M#jB"N , Country of originGermanyy,k*R*M#jX"H̀?vMissionScientific: ionosphere study_**A#R<"Perigee/Apogee373/2118 kmWR**A#R,Inclination102.7U*]*A#R(Period110.4 minm **M#j@" &g'KLaunch vehicleScout #67Y]*#*A#R0"Mass at launch72 kg{W**$ Studies aurora borealis, Earth's radiation belt and charged particles from the Sun.7#**1 kUUJ***Badr A? **2 4"  Badr A1 *E*'  Generalg **G#^@") Designation20685 / 90059A\E**A#R6Launch date16 Jul 1990o"*w*M#jD"N ,'ݓCountry of originPakistanU**G#^"H̀Mission^w***A#R:"Perigee/Apogee208/988 kmV**A#R*Inclination28.5T***A#R&Period96.7 minp#*D*M#jF" &9+SLaunch vehicleLong March 2X**A#R.Launch siteXichangU1D**$ bExperimental digital communications satellite5*&*'  End of life_**A#R<"Out of service21 Aug 1990e$&**A#RHCausefailure of onboard systemsU*?*A#R(Decay8 Dec 1990&*e*# 8?**' "(OTechnical data8e**' " SpecificationsZ*/*A#R2&Prime contractorSSTLN *}*A#RPlatformY/**A#R0"Mass at launch52 kgS}*)*A#R$ Mass in orbitO*x*A#RDimensionQ)**A#R Solar arraySx**A#R$ StabilizationN *j*A#RDC powerU**A#R($Design lifetime&j**# 7**1UVK*[*D+Badr B? *[*2 4"  Badr B1 **'  GeneralY[**G#^$") Designation`*E*A#R>Launch dateplanned in 1998o"**M#jD"N ,'ݓCountry of originPakistanaE*!+G#^4"H̀Mis*!+*sionScientific: T*u+A#R&"Perigee/ApogeeQ!++A#R InclinationL u++A#RPeriodi+{+M#j8" &'CMLaunch vehicleZenitQ++A#R Launch site{++) uShould weigh 70 kg. It will measure solar radiation and will collect information about Pakistan's natural resources.Operated by Suparcohas a CCD camera (250 m x 250 m resolution)<++' *O External resourcesY2+D+' dhttp://www.ssd.rl.ac.uk/news/cdrom/eo/badr.htm1+u+1WLu+++T+D++) "VȠ$To view this page you need to register&u++# B+1+1U%VM1+++Program: BhaskaraN++5 :4:6Ȁ" Program: BhaskarafC1++# Indian program named from a Indian mathematician and astronomer.1++1N++k1++: Dbcee艂Program: BhaskaraBhaskara 1Bhaskara 2; ++1VO++f +Bhaskara 1G++5 :&:6Ȁ" Bhaskara 11 +4+'  Generalg ++G#^@") Designation11392 / 79051A[4++A#R4Launch date7 Jun 1979l+b+M#j>"N ,&‰Country of originIndiak++M#j<"H̀郉MissionRemote sensing^b+++A#R:"Perigee/Apogee394/399 kmV++A#R*Inclination50.7T+++A#R&Period92.5 minl+A +M#j>" &s,梉Launch vehicleCosmos C]+ +A#R8Launch siteKapustin YarZA + +A#R2"Mass at launch444 kg + +% 5Carried two TV cameras, one in visible and the other in near-infrared band, and a 3-frequency passive microwave radiometer. The cameras malfunctioned.5 + +'  End of lifeV +B +A#R*Decay17 Feb 1989$ +f +" ; B + +1VP + +"N ,&‰Country of originIndiak + +M#j<"H̀郉MissionRemote sensing^H ++A#R:"Perigee/Apogee541/557 kmV +g+A#R*Inclination50.6R++A#R"Period92 minlg+%+M#j>" &s,梉Launch vehicleCosmos C]++A#R8Launch siteKapustin YarZ%++A#R2"Mass at launch436 kg+@+% +@+f +Carried two TV cameras, one in visible and the other in near-infrared band, and a 3-frequency passive microwave radiometer. 5+@+'  End of lifeV@+A+A#R*Decay30 Nov 1991$@+Brasilsat A's specificationsd#+=+A#RF0&Prime contractorSpar AerospaceTف++A#R&0PlatformHS-376[=++A#R40"Mass at launch1140 kgY+E+A#R00 Mass in orbit671 kgT++A#R&0Diameter2.19 m[E++A#R40Height7.09 m deployedb!+V+A#RB0 StabilizationSpin stabilizedd"++B#TD0DC powerBOL: 982 WEOL: 799 Wl*V+&+B#TT0$Design lifetime1: 9 years2: 11 years$+J+" 1&+{+1UV{+-+Q+:J++# .Brasilsat A's C-bandY{++A#R00(Main transponders26Z+h+A#R20,Backup transponders6V++A#R*0Power10 W (TWTA)Uh++A#R(0Bandwidth36 MHzn-++A#RZ0CoverageBrasil and neighboring countriesT+Շ+A#R&0EIRP max36 dBWX+-+A#R.0Polarizationlinear$Շ+Q+" 1-++1UW++ߌ+BQ+Ĉ+# >Brasilsat B's specifications\+ +A#R60&Prime contractorHughesUĈ+u+A#R(0PlatformHS-376W[ +Љ+A#R40"Mass at launch1760 kgZu+*+A#R20 Mass in orbit1052 kgTЉ+~+A#R&0Dry mass850 kgT*+Ҋ+A#R&0Diameter3.64 mc"~+5+A#RD0Height3.64 m, 8.38 m deployedb!Ҋ++A#RB0 Stabilizationspin stabilizedY5++A#R00DC powerBOL: 1650 W]+M+A#R80$Design lifetime12 yearsn-++A#RZ0Apogee motorThiokol Star 30 (solid fuel)$M+ߌ+" 1++1UX+++:ߌ+J+# .Brasilsat B's X-bandX++A#R.0(Main transponders1YJ++A#R00,Backup transpondersV+Q+A#R*0Power40 W (TWTA)O++A#R0BandwidthN Q++A#R0CoverageN +<+A#R0EIRP maxR++A#R"0Polarization$<++" = + +1cWY +U++Brasilsat A1+ ++I+U+5 :*hԞ" Brasilsat A19 ++# ,Also called SBTS A11 U++'  Generalg +&+G#^@") Designation15561 / 85015B[++A#R4Launch date8 Feb 1985m &++M#j@"N ,7Country of originBrasilo"+]+M#jD"H̀‰MissionTelecommunicationsb!++A#RB,Geostationary orbitsee belown!]+-+M#jB" &C+Launch vehicleAriane V12&+S+# : -++- */ۀ LocationS++m#:   " BeginEndPosition++j#4"&(L: 8 Feb 198565W,+1+j#X68late-1994mid-Jun 199663W, inclined#++j#F $&mid-Jul 199679W, inclined1+r+% Sold to HCI in October 1995. The antenna was re-aimed to North America. The control of the satellite was passed to Panamsat on 12 Nov 1997.8++' "(Technical dataq:r++7 >te2⨕܉ھSpecificationsC-bandTransponder frequency chart= +X+1OvW WZX+++Brasilsat A2I++5 :*hԞ" Brasilsat A29X++# ,Also called SBTS A21 + +'  Generalg +r+G#^@") Designation16650 / 86026B\ ++A#R6Launch date28 Mar 1986m r+;+M#j@"N ,7Country of originBrasilo"++M#jD"H̀‰MissionTelecommunicationsb!;+ +A#RB,Geostationary orbitsee belown!+z+M#jB" &C+Launch vehicleAriane V17& ++# : z++- */ۀ Location+d+m#:   " BeginEndPosition++j#6$(*L: 28 Mar 198670Wd+q+j#<.0late-1994Jun 199565W++j#*Aug 199592W&q++# 8+N+' "(Technical dataq:++7 >te2⨕܉ھSpecificationsC-bandTransponder Frequency Chart= N++1[cWX[+I+K,Brasilsat B1M+I+8 @,hԞ" Brasilsat B19++# ,Also called SBTS B11 I++'  Generalg ++G#^@") Designation23199 / 94049A\+v+A#R6Launch date10 Aug 1994m + ,M#j@"N ,7Country of originBrasilv+ ,+o"v+{,M#jD"H̀‰MissionTelecommunicationse ,,G#^<"/ۀ0Geostationary orbit70Wn!{,N,M#jB" &D+Launch vehicleAriane V66:,,$ ,Cost: $140 million8N,,' "(OTechnical data=,,' , EIRP coverage (dBW)O,,? N❜#  # g܉Brasil: NationalBrasil: Regional & ArgentinaSpecificationsX-band0 ,,'  C-bandY,,A#R00(Main transponders28Y,m,A#R00,Backup transpondersO,,A#R0Power15 WUm,,A#R(0Bandwidth31 MHz\,m,G#^*0❜# CoverageBrasilT,,A#R&0EIRP max38 dBWVm,,A#R*0G/T max-2.5 dB/K\,s,A#R60Polarizationlinear H/VN*,,$ TBeacon: 4.1985 - 4.1990 GHz horizontalK$s, ,' H Transponder frequency chart (GHz)h,*,#<k * X n   HorizontalUplinkHorizontalDownlinkChannelVerticalDownlinkVerticalUplinkBeam ,,# <k"&683.64151AE5.8665*,,# 8k .245.8851BE3.660,W ,# 8k $243.6802AE5.905, ,# 8k .245.9252BE3.700W , ,# 6k"023.7201A5.945 , ,# 6k,025.9651B3.740 ,8 ,# 6k"023.7602A5.985 , ,# 6k,026.0052B3.7808 , ,# 6k"023.8003A6.025 ,`,# 6k,026.0453B3.820 ,,# 6k"023.8404A6.065`,,# 6k,026.0854B3.860,@,# 6k,@,+"023.8805A6.105,LA,# 6k,026.1255B3.900@,B,# 6k"023.9206A6.145LA,B,# 6k,026.1256B3.940B,tC,# 6k"023.9607A6.185B,,D,# 6k,026.2057B3.980tC,D,# 6k"024.0008A6.225,D,E,# 6k,026.2458B4.020D,TF,# 6k"024.0409A6.265E, G,# 6k,026.2859B4.060TF,G,# 8k $244.08010A6.305 G,~H,# 8k .246.32510B4.100G,7I,# 8k $244.12011A6.345~H,I,# 8k .246.36511B4.1407I,J,# 8k $244.16012A6.385I,bK,# 8k .246.40512B4.180&J,K,# 1bK,K,1\K,L,`*K,L,6 -1 XZc>--d -Brasilsat B3I--5 :*hԞ" Brasilsat B39>--# ,Also called SBTS B31 --'  Generalg -X-G#^@") Designation25152 / 98006A[--A#R4Launch date4 Feb 1998m X- -M#j@"N ,7Country of originBrasilo"--M#jD"H̀‰MissionTelecommunicationse --G#^<"/ۀ0Geostationary orbit65Wo"-c-M#jD" &|g&\Launch vehicleAriane V105&--# 2 c--'  Location-E-m#:   " BeginEndPosition"--j#D"68L: 4 Feb 1998Apr 199865Ww E-H-j# 84W-"-% kCost: $70 million agreement (without launch?) This is an amendment to the Brasilsat B contract with Hughes signed in 1990, which gave EMBRATEL options for additional spacecraft.8H-Z-' "(Technical data<"--) "&gSpecifications=Z--' , EIRP coverage (dBW)f5-9 -1 2j❜#  # Brasil: NationalBrasil: Regional & Argentina0 -i -'  C-bandY9 - -A#R00(Main transponders28Yi - -A#R00,Backup transpondersO -j -A#R0Power18 WU - -A#R(0Bandwidth31 MHzp.j -/ -B#T\0CoverageBrasil: NationalBrasil: RegionalT - -A#R&0EIRP max38 dBWV/ - -A#R*0G/T max-2.5 dB/K\ -5 -A#R60Polarizationlinear H/V/  -d -% No X-band payload: the C-band only spacecraft will provide nearly 20 percent higher signal power than the 2 Brasilsat B's. It will have one C-band beam for national service, and a second C-band regional beam that will focus higher power on the major urban areas.= 5 - -1:Zd - -@-Brasilsat B4Id - -5 :*hԞ" Brasilsat B49 -#-# ,Also called SBTS B41 -T-'  GeneralY#--G#^$") Designation`T- -A#R>Launch dateplanned in 2000m -z-M#j@"N ,7Country of originBrasilo" - @-M#jD"H̀‰MissionTelecommunicationsz- @-d -az-m@-G#^4"/ۀ0Geostationary orbit\ @-@-G#^*" &Launch vehicle3m@-@-$ C-band only1@--A-1We-A-A-A-T+@-A-) "VȠ$To view this page you need to register&-A-A-# 8A-A-1&VZfA-B-H-Bremsat@A-B-2 4"  Bremsat1 A-PB-'  Generalg B-B-G#^@") Designation22998 / 94006H[PB-C-A#R4Launch date3 Feb 1994n!B-C-M#jB"N , Country of originGermanyp)C-C-G#^ROperatorZARM, University of Bremen~1C-nD-M#jb"H߲̀-MissionScientific: high atmosphere study^C-D-A#R:"Perigee/Apogee344/363 kmVnD-"E-A#R*Inclination56.9TD-vE-A#R&Period91.4 minj"E-E-M#j:" &Launch vehicleSTS 60YvE-9F-A#R0"Mass at launch63 kg}YE-F-$ Measured heat conductivity, micrometeorites, and the density of the upper atmosphere.<9F-F-' *O External resourcessLF-eG-' http://www.zarm.uni-bremen.de/2forschung/raumfahrt/bremsat/bremsat1.html5F-G-'  End of lifeVeG-G-A#R*Decay12 Feb 1995$G-H-" > G-RH-1lZ-[gRH-H-I-Program: BSATJH-H-5 :,mG" Program: BsatN"RH-I-, &EOAlso called BS 4, Broadcast Satellite 4Japanese telecommunication program to replace the Yuri program. Bsat (Broadcasting Satellite System Corp.) is a consortium of major Japanese broadcasters including NHK and the WOWOW group and provides direct broadcast services throughout Japan.1H-J-1hJ-|J-a'I-|J-: DNgWRSProgram: BsatBsat 1ABsat 1B1J-J-1UiJ-0N-TN-;|J-J-# 0Bsat's specifications\J-DK-A#R6&Prime contractorHughesTJ-K-A#R&PlatformHS-376[DK-K-A#R4"Mass at launch1250 kg[K-NL-A#R4 Mass in orbit~ 600 kgy8K-L-A#RpDimension2.17 m diameter x 2.54 m (7.82 m deployed)QNL-M-A#R Solar arrayb!L-zM-A#RB Stabilizationspin stabilizedYM-M-A#R0DC powerBOL: 1064 W]zM-0N-A#R8$Design lifetime12 years$M-TN-" 10N-N-1UjN--Ɓ-4TN-N-# "Bsat's Ku-bandXN-O-A#R.(Main transponders4ZN-kO-A#R2,Backup transponders4WO-O-A#R,Power106 W (TWTA)UkO-#-A#R(O-#-TN-Bandwidth27 MHzXO-{-A#R.CoverageJapan onlyN #-ɀ-A#REIRP maxZ{-#-A#R2Polarizationcircular=ɀ--B#TzFrequenciesUplink: 14.2-14.3 GHzDownlink: 11.9-12.0 GHz$#-Ɓ-" 8--1[k-B--Bsat 1ADƁ-B-5 : mG" Bsat 1A1 -s-'  Generalg B-ڂ-G#^@") Designation24769 / 97016B\s-6-A#R6Launch date16 Apr 1997lڂ--M#j>"N ,bCountry of originJapano"6--M#jD"H̀‰MissionTelecommunications^-o-A#R:,Geostationary orbit110En!-݄-M#jB" &8E+Launch vehicleAriane V95~Xo-[-& Estimated Cost: $150 million (satellite, launch and insurance)Test position: 122E8݄--' "(Technical dataM[--0 0: 唀LBfSpecificationsKu-band8--1|[l-\--Bsat 1BD-\-5 : mG" Bsat 1B1 --'  Generalg \--G#^@") Designation25312 / 98024B\-P-A#R6Launch date28 Apr 1998l--M#j>"N ,bCountry of originJapano"P-+-M#jD"H̀‰MissionTelecommunications^--A#R:,Geostationary orbit110Eo"+--M#jD" &g&\Launch vehicleAriane V108yT-q-% Estimated Cost: $150 million (satellite, launch and insurance)Tested from 122E8--' "(Technical dataMq--0 0: 唀LBfSpecificationsKu-band= -3-1ZJ\m3-|--Program: BSBI-|-5 :*\c%" Program: BSBz3--# English direct TV program abandonned in 1992. The satellites were ordered by BSB which merged with Sky TV giving BSkyB.1|-J-1nJ--\"--: DDJaSSSProgram: BSBBSB 1BSB 21J-׋-1o׋-d-:--# .BSB's specifications\׋-m-A#R60&Prime contractorHughesT--A#R&0PlatformHS-376[m--A#R40"Mass at launch1250 kgY-u-A#R00 Mass in orbit660 kg~=--A#Rz0Payload mass100 kg: transponders: 90 kg, antennas: 10 kgTu-G-A#R&0Diameter2.16 mQ--A#R 0Height4.8 mb!G--A#RB0 StabilizationSpin stabilizedY-S-A#R00DC powerBOL: 1024 W]--A#R80$Design lifetime10 years`S--A#R>0Beacon12.494--- or 12.495 GHzH$-d-$ HEquipped with steerable antennas1--1Up---3d--#  BSB's Ku-bandX- -A#R.0(Main transponders5Z-z-A#R20,Backup transponders1Z --A#R20Power2 x 55 W (TWTA)Uz-)-A#R(0Bandwidth27 MHzN -w-A#R0CoverageT)--A#R&0EIRP max59 dBW\w-'-A#R60Polarizationcircular RA--B#T0FrequenciesUplink: 17.3-17.6 GHzDownlink: 11.786-12.091 GHz$'--" 6--1|[q-F--BSB 1B -F-5 :\c%" BSB 1>--# 6Also called Marco Polo 11 F--'  Generalg --G#^@") Designation20193 / 89067A\-x-A#R6Launch date27 Aug 1989u(--M#jP"N ,R׉Country of originUnited Kingdomfx-S-M#j2"H̀‰MissionDirect TVb!--A#RB,Geostationary orbitsee belows&S-(-M#jL" &p㉂Launch vehicleThor Delta #187pF--* $Stopped transmitting on 31 Dec 1992 and became Sirius 1 in 1994.2 (--'  Location-T-m#:   " BeginEndPosition--j#.$(*L: 27 Aug 1989T-\-j#:,.Nov 1991Dec 199231W--p#41994...Sirius 1&\- -# 8-D-' "(Technical dataM --0 0:ٹZfܢaSpecificationsKu-band6D--1d[r- -.BSB 2B - -5 :\c%" BSB 2>-G-# 6Also called Marco Polo 21 -x-'  Generalg G--G#^@") Designation20762 / 90074A\x-;-A#R6Launch date18 Aug 1990u(--M#jP"N ,R׉Country of originUnited Kingdomf;--M#j2"H̀‰MissionDirect TVb!-x-A#RB,Geostationary orbitsee belowp#--M#jF" &p㉂Launch vehicleDelta 2 #198]3x-E-* $ffOWas sold in September 1992 and became Thor 1.2 -w-'  LocationE--m#:   " BeginEndPositionw--j#.$(*L: 18 Aug 1990- .j#*Aug 199231W- .--.p#8"$fOSep 1992...Thor 18 ..' "(Technical dataM..0 0:ٹZfܢaSpecificationsKu-band= .[.1}-[G\s[..@.Cakrawarta 1=.., ($" Cakrawarta 1<[..# 2Also called Indostar 11 ..'  Generalg .l.G#^@") Designation25050 / 97071B\..A#R6Launch date12 Nov 1997p#l.8.M#jF"N ,b#Country of originIndonesiau(..M#jP" H1OperatorPT Media Citra Indostaro"8..M#jD"H̀‰MissionTelecommunications`.|.A#R>,Geostationary orbit107.7Eo"..M#jD" &yg&\Launch vehicleAriane V102p|..' Up to 4 small satellites have been ordered: Indostar 2 at 115E and Indostar 3 at 106E (or all four satellite colocated at 107.5 and 119E) The full project (satellite, launch, ground station, etc) is worth $175 millionThe satellite has power supply problems which lead to the shutdown of 2 transponders. The lifetime of the satellite could be reduced by half.8..' "(OTechnical data8..' " Specificationso(.a.G#^P&xOPrime contractorCTA Inc (now OSC)U..A#R(PlatformSTARbus[a..A#R4"Mass at launch1385 kgY.j.A#R0 Mass in orbit802 kgT..A#R&Dry mass643 kgOj. .A#RDimensionQ.^ .A#R Solar arrayb! . .A#RB Stabilizationspin stabilizedT^ . .A#R&DC power3200 W] .q .A#R8$Design lifetime10 years& . .# @q . .' 2 L-band (1452-1492 GHz)X ./ .A#R.(Main transponders2Y . .A#R0,Backup transpondersK / . .A#RPowerO ." .A#RBandwidthW .y .A#R,CoverageIndonesiaN " . .A#REIRP maxRy . .A#R"Polarization` .y .A#R>Frequencies1.452-1.492 GHzF" . .$ DFor digital audio broadcasting@y . .' 2 S-band (2520-2670 GHz)X .W.A#R.(Main transponders3Y ..A#R0,Backup transpondersOW..A#RPower70 WO.N.A#RBandwidthW..A#R,CoverageIndonesiaN N. @.A#REIRP max. @..R.^@.A#R"Polarization` @.@.A#R>Frequencies2.520-2.670 GHz;^@.@.$ .For TV broadcasting7@.0A.1kJ\\t0A.gA.F.Castor7 @.gA., (" Castor50A.A.# $Also called D5B1 gA.A.'  Generalg A.4B.G#^@") Designation07802 / 75039B\A.B.A#R6Launch date17 May 1975m 4B.B.M#j@"N ,㱭+Country of originFrancep#B.mC.M#jF"H̀CV$MissionScientific: geodesy_B.C.A#R<"Perigee/Apogee277/1275 kmVmC."D.A#R*Inclination29.9UC.wD.A#R(Period100.3 mino""D.D.M#jD" &A͉Launch vehicleDiamant #11YwD.?E.A#R0"Mass at launch76 kgD.E., &qwTests a high precision micro-acceleratometer.It is the counterpart of the first Castor that was lost with Pollux on 22 May 1973.5?E.'F.'  End of lifeVE.}F.A#R*Decay18 Feb 1979$'F.F." : }F.F.1G\b\uF.!G.J.CaribstarFF.!G.5 :$$eT" Caribstar9F.ZG.# ,Also called CariBSS1 !G.G.'  GeneralYZG.G.G#^$") Designationd#G.HH.A#RFLaunch dateplanned in mid-1999t'G.H.M#jN"N ,㹌לCountry of originUnited Stateso"HH.+I.M#jD"H̀‰MissionTelecommunications^H.I.A#R:,Geostationary orbit120Wj+I.I.M#j:" &2!Launch vehicleAriane&I.J.# 8I.QJ.' "(Technical dataLJ.J.0 080|SpecificationsL-band1QJ.J.1WvJ."K.HK.T+J."K.) "VȠ$To view this page you need to register&J.HK.# = "K.K.1\Z]wK.K.(L.Program: CatIHK.K.5 :*⡱c%" Program: CatZ7K.(L.# nEuropean micro satellite program for experimentation1K.YL.1xYL.L.z2(L.L.H `deSscTtcTucTvcTProgram: CatCat 1Cat 2Cat 3Cat 46YL. M.1PI]y M.KM.u.Cat 1B L.KM.5 :⡱c%" Cat 11 M.|M.'  Generalg KM.M.G#^@") Designation11645 / 79104A\|M.?N.A#R6Launch date24 Dec 1979m M.N.M#j@"N ,4"Country of originEuropeo(?N.O.G#^P"H̀MissionTechnology experimentation`N.{O.A#R>"Perigee/Apogee125/14047 kmVO.O.A#R*Inclination17.8U{O.2.A#R(O.2.L.Period259.1 minn!O..M#jB" &%+Launch vehicleAriane L01&2.ƀ.# 5..'  End of lifeVƀ.Q.A#R*Decay27 Nov 1989$.u." 6Q..1X\]z...Cat 2B u..5 :⡱c%" Cat 25.".'  End of life_..A#R<"Out of service23 May 1980o("..G#^P&+CauseLaunch failure of Ariane L02$.." 6.J.1bI]]{J...Cat 3B ..5 :⡱c%" Cat 31 J..'  Generalg .$.G#^@") Designation12546 / 81057C\..A#R6Launch date19 Jun 1981m $..M#j@"N ,4"Country of originEuropeo(.\.G#^P"H̀MissionTechnology experimentation`..A#R>"Perigee/Apogee227/29240 kmV\..A#R*Inclination10.6U.g.A#R(Period508.8 minn!.Ն.M#jB" &'+Launch vehicleAriane L03&g..# 5Ն.0.'  End of lifei(..A#RP"Out of service96 hours after launch$0.." 6..1]|.5..Cat 4B .5.5 :⡱c%" Cat 48.m.# *Also called Thse1 5..'  Generalg m..G#^@") Designation13011 / 81122B\.a.A#R6Launch date20 Dec 1981m .Ή.M#j@"N ,4"Country of originEurope_a.-.G#^0"H̀MissionScientific`Ή..A#R>"Perigee/Apogee219/38645 kmV-..A#R*Inclination63.8U.8.A#R(Period534.3 minn!..M#jB" &(+Launch vehicleAriane L04>8..$ 4Measures the Sun light5..'  End of life^.w.A#R:"Out of service9 Jan 1982_.֌.A#R<CauseStopped transmitting$w.." ?֌.9.1b\]}9.. .Program: CBERSK..5 :.fـ" Program: CBERS}9.5.( China/Brazil Earth Resources SatelliteJoint venture to launch 2 satellites for remote monitoring of the environment related to agriculture, oceanography and geology. The Brazilian government has suggested to China that another two 1400-kilogram satellites should be developed.The two satellites will be assembled in China with parts manufactured in both countries and Brazil will invest 60 million dollars, covering 30% of the costs of the project. The two countries started manufacturing the two satellites in 1988 but the project was delayed by a budget shortfall on the Brazilian side (sa.5..tellites were planned for 1994 & 1995). .B.' The Brazilian Ministry of the Environment will use the two new satellites in the Amazon Integrated Program, created to develop the Amazon region based on sustained development policies.2 follow-on satellites are also planned<5.~.' *O External resources_B. .. ,http://www.dgi.inpe.br/html/eng/cbers.htmhttp://www.met.inpe.br/chinese/ch-br-satel.html1~.<.1W~<...T+ ..) "VȠ$To view this page you need to register&<..# 8..1? .2.@.CBERS 1D.2.5 : U/" CBERS 11 .c.'  GeneralY2..G#^$") Designationd#c. .A#RFLaunch dateplanned in Oct 1997_..G#^0"N ,Country of origink ..M#j<"H̀郉MissionRemote sensingr1.\.A#Rb"Perigee/Apogeeheliosynchronous orbit, 778 kmQ..A#R Inclinationb!\..A#RBPeriodrepeat period: 20 daysf.u.G#^>" &Launch vehicleLong MarchQ..A#R Launch site&u..# 8.$.' "(OTechnical data8.\.' " SpecificationsV$..A#R*&Prime contractorN \..A#RPlatform[.[.A#R4"Mass at launch1400 kgS..A#R$ Mass in orbitZ[..A#R2Dimension1.8 x 1.9 m\.d.A#R6Solar array8.3 x 3.3 mY..A#R0 Stabilization3 axisN d. .A#RDC powerU.`.A#R($Design lifetime& ..# c<`..' x 5-channel linear CCD detector (visible, IR, panchromatic)h&.Q.B#TL0Wavebands0.59-0.89 m0.5-12.9 mW..A#R,0Swath width120 kmg%Q..B#TJ0ResolutionVisible: 19 mIR: 80 m&.5.# ;.p.' ( Wide-field imagerU5..A#R(0Resolution260 mWp..A#R,0Swath width900 km$.@." 1.q.1Wq...T+@..) "VȠ$To view this page you need to register&q..# B.-.1~Z]1^-.{. /Program: CelestisN.{.5 :4_" Program: Celestisc@-..# US private program to launch ashes into space (space burial).1 {..' O Contact:.I.$ ,Tel: +1-800-6724811<..' *O External resourcesCI. /' 8http://www.celestis.com/. /.1.=/1=//k1 //: Db97D9H H Program: CelestisCelestis 1Celestis 2; =//1;]^/*/4/Celestis 1G/*/5 :&_" Celestis 11 /[/'  Generalg *//G#^@") Designation24780 / 97018B[[//A#R4Launch date4 Apr 1997t'//M#jN"N ,㹌לCountry of originUnited States[//G#^("H̀MissionBurial`/L/A#R>"Perigee/Apogee554 / 582 kmj)//A#RRInclination151 (inclination record)TL/ /A#R&Period96.1 mino"/y/M#jD" &GKTLaunch vehiclePegasus #17_ //A#R<Launch siteCanary Islands\8y/4/$ pSet of 24 capsules containing the ashes of 24 people; /o/11^^o//^ /Celestis 2G4//5 :&_" Celestis 21 o//'  Generalg /N/G#^@") Designation25160 / 98007D\//A#R6Launch date10 Feb 1998t'N//M#jN"N ,㹌לCountry of originUnited States[/y/G#^("H̀MissionBurial`//A#R>"Perigee/Apogee777 / 875 kmUy/./A#R(Inclination108L /z/A#RPeriodm .//M#j@" &㻦ʼnLaunch vehicleTaurus #2wSz/^ /$ The Celestis Payload Attach Container (CPAC) was attached to Taurus' top stage.B/ /1^.^ / /@/Program: CelestriB^ / /, (." Program: Celestrig9 /I /. *skMotorola telecommunication project. It comprises LEO and GEO satellites (63 satellites) in a single network to deliver high speed multimedia data. Should begin service in 2003The system should cost $12.9 billion It could be a replacement for the Millennium program. MMS will design and build the satellite buses; the contract is worth $1.2 billion. MMS will bring $500 million in the Celestri program.The LEO satellites will be at 1400 km altitude, in 7 planes. The GEO satellites will have a bus derived from Eurostar 3000 to provide 10000 W. Weigth: 3100 kg /] /? LЇk NNꉂMotorola has 3 other satellite programs: Iridium, Millennium and M-Star The last 2 should be cancelled and be integrated into CelestriCelestri could be cancelled and efforts integrated into Teledesic<I / /' *O External resourcesB] / /' 6http://www.celestri.com8 //' "(OTechnical datalC /@/) Uplink: 28.6-29.1 GHz & 29.5-30 GHzDownlink: 18.8-19 GHz & 19.7-20.2 GHzEach LEO satellite in the Celestri System is designed to have on-board switching and routing equipment, and six optical link terminals that will interconnect it to nearby satellites in the constellation. Contraves Space, a division of the Zurich-based Oerlikon Contraves Group, will design and produce the optical inter-satellite link (OISL) terminals that will allow the lo/@/^ /w earth orbit (LEO) satellites in the Celestri System to communicate with each other across multiple high-speed laser links. 1/@/1W@/A/6A/T+@/A/) "VȠ$To view this page you need to register&@/6A/# 7A/mA/1i ^^mA/A/J/Cerise7 6A/A/, (" Cerise1 mA/A/'  Generalg A/Launch dateplanned in 1999n!CL/M/M#jB"N , Country of originGermany_L/pM/G#^0"H̀MissionScientificZM/M/A#R2"Perigee/Apogee500 kmQpM/N/A#R InclinationL M/gN/A#RPeriod{4N/N/G#^h" &Launch vehicleRussian vehicle (Start, Cosmos)QgN/3O/A#R Launch site5N/hO/$ "6 instruments<3O/O/' *O External resourcesX1hO/ /' bhttp://www.gfz-potsdam.de/pb1/CHAMP/champ.htmO/ /J/8O/D/' "(OTechnical data8 /|/' " Specificationsa D/݀/A#R@&Prime contractorGFZ PostdamN |/+/A#RPlatformZ݀//A#R2"Mass at launch300 kgW+/܁/A#R,Payload mass25 kgO/+/A#RDimensionQ܁/|/A#R Solar arrayS+/ς/A#R$ StabilizationN |//A#RDC powerUς/r/A#R($Design lifetime&//# 1r/Ƀ/1WɃ//C/T+//) "VȠ$To view this page you need to register&Ƀ/C/# < //1l ^P_///Chinastar 1<C//, ("" Chinastar 1<//# 2Also called Zhongwei 11 /(/'  Generalg //G#^@") Designation25354 / 98033A\(//A#R6Launch date30 May 1998l/W/M#j>"N ,6"Country of originChina|//G#^OperatorChina Oriental Telecom Satellite (COTS) Company, an affiliate of the Ministry of Posts and Telecommunicationso"W//M#jD"H̀‰MissionTelecommunications_//A#R<,Geostationary orbit87.5Eq$/Y/M#jH" &9+SLaunch vehicleLong March 3B&//# <Y//' *O External resourcesc<//' xhttp://jefferson.vf.mmc.com/lmtoday/0995/chinastar1.html8/V/' "(OTechnical data8//' " Specificationse$V//A#RH&Prime contractorLockheed MartinS/F/A#R$PlatformA2100[//A#R4"Mass at launch2984 kgSF//A#R$ Mass in orbitO/C/A#RDimensionQ//A#R Solar arraySC//A#R$ StabilizationN /5/A#RDC power]//A#R8$Design lifetime15 years&5//# 0 //'  C-bandY/A/A#R0(Main transponders24Y//A#R0,Backup transpondersOA//A#RPower45 WU/>/A#R(Bandwidth36 MHzN //A#RCoverageN >/ڎ/A#REIRP maxR/,/A#R"Polarization&ڎ/R/# 1 ,//'  Ku-bandYR/܏/A#R0(Main transponders24Y/A/A#R0܏/A/C/,Backup transpondersK ܏//A#RPowerUA//A#R(Bandwidth36 MHzS/4/A#R$CoverageChinaN //A#REIRP maxR4//A#R"Polarization$//" A/9/1 _`9/z/;0Program: ClusterA/z/, (," Program: Clusterf9/ /) "2!European scientific program. The 4 satellites composing it were lost on Ariane 5's maiden flight.1 z/:/'  General\ //G#^*") Designationn/a[://A#R4Launch date4 Jun 1996m /^/M#j@"N ,4"Country of originEuroper%//M#jJ"H̀jMissionScientific: Sun studyn!^/>/M#jB" &E+Launch vehicleAriane V88\8//$ pThe total cost was evaluated at 2.9 billion francs. <>//' *O External resourcesc/g/. ,http://www.esoc.esa.de/external/mso/cluster.htmlhttp://cdhf3.bnsc.rl.ac.uk:8080/cluster.html8//' "(OTechnical data8g//' " Specifications]/4/A#R8&Prime contractorDornierN //A#RPlatform[4//A#R4"Mass at launch1200 kgW/4/A#R,Payload mass72 kg[//A#R4$Propellant mass650 kgT4//A#R&Dry mass550 kgS/6/A#R$Diameter2.9 mQ//A#R Height1.3 mQ6//A#R Solar arrayk*/C/A#RT Stabilizationspin stabilized (15 rpm)y8//A#RpDC powerEOL: 224 W (80 Ah silver cadmium batteries)WC//A#R, Payload power47 W\/o/A#R6$Design lifetime2 yearsY//A#R0Telemetry2-262 kbpsrNo/:/$ Tape recorder capacity: 1 gbit The final orbit was to be 25000/140000 km 5/o/'  Frequencies[://A#R4Cluster 12242.000 MHz[o/%/A#R4Cluster 22249.000 MHz[//A#R4Cluster 32277.000 MHz[%//A#R4Cluster 42270.000 MHz&//# 1 /2/' O Payload/;0. *STAFF ( Spatio-Temporal Analysis of Field Fluctuations)EFW (Electric Fields and Waves)WHISPER (Waves of High frequency and Sounder for probing of density by Relaxation)WBD (Wide Band Data)DWP (Digital Wave Processor)FGM (Fluxgate Magnetometer)EDI (Electronic Drift Instrument)CIS (Cluster Ion Spectrometry)PEACE (Plasma Electron And Current Analyser)RAPID (Research with Adaptive Particle Imaging Detectors2/;0/)ASPOC (Active Spacecraft Potential Control)C2/~01P_`~00}0Program: Cluster 2C;00, (0" Program: Cluster 2~0}04 6_7ǥE+Following the loss of the Cluster satellites with Ariane 501 a remplacement could be financed.This replacement will be composed of the Phenix satellite made from spare instruments of the first set and 3 new satellites to be built by Dornier. The satellites will be launched by pairs aboard Soyouz rockets.The program should be completed in mid-2000. It will cost about $265 million1001W00(0T+}00) "VȠ$To view this page you need to register&0(0# 50]01 ``]00n0Cobe5 (00, (" Cobe@]00# : COsmic Background Explorer1 00'  Generalg 0j0G#^@") Designation20322 / 89089A\00A#R6Launch date18 Nov 1989t'j0:0M#jN"N ,㹌לCountry of originUnited Statesr%00M#jJ"H̀_BMissionScientific: astronomy^:0 0A#R:"Perigee/Apogee872/886 kmT0^0A#R&Inclination99U 00A#R(Period102.5 mins&^0&0M#jL" &p㉂Launch vehicleThor Delta #189{W00$ Studies the thermical radiation of the sky (gave its precise temperature: 2.735 K).<&00' *O External resourcesc0n0. ,http://www.gsfc.nasa.gov/astro/cobe/cobe_home.htmlhttp://spectrum.lbl.gov/www/cobe/cobe.htmlB001`a00T 0Program: ColumbiaNn005 :4$" Program: ColumbiaV$0T 02 2Iur7@ĘProgram operated by Columbia Communications Corporation This company already operates the commercial C-band on the first generation TDRS satellites.Program of GEO telecommunication satellites to be launched in 2000. It will have 2 satellites, for Atlantic and Pacific ocean regions.10 01W 0 0 0T+T 0 0) "VȠ$To view this page you need to register& 0 0# 1 00 010 0 0{ 0 0W ~݌R(.UڀUډOMOMOMĉProgram: ColumbiaColumbia AORColumbia PORColumbia TDRS 4Columbia TDRS 5Columbia TDRS 6Columbia 51510 03 01W3 0 0 0T+ 0 0) "VȠ$To view this page you need to register&3 0 0# = 0 01 c` 03 0G0Columbia AORI 03 05 :*$" Columbia AOR1 0d 0'  GeneralY3 0 0G#^$") DesignationUd 00A#R(Launch date2000t' 00M#jN"N ,㹌לCountry of originUnited Stateso"00M#jD"H̀‰MissionTelecommunications]0R0A#R8,Geostationary orbit47W\00G#^*" &Launch vehicleYR0@0G#^$Launch sit0@0 0e&09@0# 8@0q@0' "(Technical dataA9@0@0) "016EIRP coverage (dBW)8q@0@0' " SpecificationsV@0@A0A#R*&Prime contractorN @0A0A#RPlatformT@A0A0A#R&"Mass at launchSA05B0A#R$ Mass in orbitOA0B0A#RDimensionQ5B0B0A#R Solar arraySB0(C0A#R$ StabilizationN B0vC0A#RDC powerU(C0C0A#R($Design lifetime&vC0C0# 0 C0!D0'  C-bandYC0zD0A#R0(Main transponders44Y!D0D0A#R0,Backup transpondersK zD0E0A#RPowerg%D0E0B#TJBandwidth32 x 54 MHz12 x 92 MHzUE0F0C#V,Coverage & EIRP maxWest Atlantic: 42 dBWEast Atlantic: 44 dBWSteerable: 43 dBWM E0jF0A#RG/T maxRF0F0A#R"Polarization]9jF0G0$ rBeam overlap with Columbia POR in Southern California1F0JG01WJG0G0G0T+G0G0) "VȠ$To view this page you need to register&JG0G0# 1G0G01G0FH0QG0FH06 <8(.Uڀ"OColumbia AOR's EIRP1G0wH01WwH0H0H0T+FH0H0) "VȠ$To view this page you need to register&wH0H0# = H0.I01 `.I0wI00Columbia PORIH0wI05 :*$" Columbia POR1 .I0I0'  GeneralYwI0J0G#^$") DesignationUI0VJ0A#R(Launch date2000t'J0J0M#jN"N ,㹌לCountry of originUnited Stateso"VJ09K0M#jD"H̀‰MissionTelecommunications^J0K0A#R:,Geostationary orbit172E\9K0K0G#^*" &Launch vehicleYK0LL0G#^$Launch site&K0rL0# 8LL0L0' "(OTechnical data=rL0L0' , EIRP coverage (dBW)EL0,M00 0*mBـo(~C-bandKu-band8L0dM0' " SpecificationsV,M0M0A#R*&Prime contractorN dM0N0A#RPlatformTM0\N0A#R&"Mass at launchSN0N0A#R$ Mass in orbitO\N0N0A#RDimensionQN0OO0A#R Solar arraySN0O0A#R$ StabilizationN OO0 0A#RDC powerO0 0H0UO0a0A#R($Design lifetime& 00# 0 a00'  C-bandY00A#R0(Main transponders36Y0i0A#R0,Backup transpondersK 00A#RPowerg%i00B#TJBandwidth32 x 72 MHz12 x 92 MHzF00C#V,Coverage & EIRP maxOceania: 45 dBWAsia: 45 dBWSteerable: 46 dBWM 00A#RG/T maxR0C0A#R"Polarization&0i0# 1 C00'  Ku-bandYi00A#R0(Main transponders24Y0L0A#R0,Backup transpondersK 00A#RPowerUL00A#R(Bandwidth72 MHz00H#^c,Coverage & EIRP maxWestern USA & Hawaii: 56 dBWAustralasia: 54 dBWPhilippines: 56 dBWSouth-East Asia: 57 dBWIndo-China: 56 dBWNorth-East Asia: 56 dBWSteerable: 58 dBWM 020A#RG/T maxR00A#R"Polarization^:200$ tBeam overlaps with Columbia AOR in Southern California1001W0g00T+0g0) "VȠ$To view this page you need to register&00# 1g00100X"006 "N ,bCountry of originJapano"ދ00M#jD"H̀‰MissionTelecommunicationsv5J0/0A#Rj,Geostationary orbitn/a (121E initially planned)i00M#j8" &JLaunch vehicleH2 #6`/00' Was to demonstrate inter-orbit links and Ka-band transmissions and mobile K-band transmissions (onboard relay). Cost: $36 millionEarly shutdown of the second stage left the satellite in low orbit (44 seconds out of the 192 seconds planned). The apogee motor should be used to higher the orbit and enable a few experiments on a 500/17700 km orbit)<0[0' *O External resourcese>00' |http://yyy.tksc.nasda.go.jp/Home/This/This-e/comets_e.html8[0 0' "(OTechnical data0 0080D0' " SpecificationsV 00A#R*&Prime contractorh!D00G#^B㊾TPlatformderived from ETS 6[0]0A#R4"Mass at launch3900 kgZ00A#R2 Mass in orbit2000 kgZ]00A#R2Dimension2 x 3 x 3 mZ0k0A#R2Solar array15 m spanY00A#R0 Stabilization3 axisYk00A#R0DC powerEOL: 5300 W\0y0A#R6$Design lifetime3 yearst00, (㊾TIs equipped with ETS 6's apogee motor. Has 4 Xenon thrustersSuffered an electrical overcharge before launch.1 y0J0'  Ka-bandX00A#R.(Main transponders5ZJ00A#R2,Backup transponders1P0L0A#RPower200 WO00A#RBandwidthXL00A#R.CoverageJapan onlyN 0A0A#REIRP maxR00A#R"PolarizationwQA0 0& + S-band capacity+ 1 transponder with uplink at 44 GHz, downlink at 476 GHzA0K01a4bK00#0Program: ComstarM 005 :20À" Program: ComstarbK0#0) "P/:American telecommunication satellite program operated by Comsat. Capacity was leased to AT&T.10T01T00J#00H `\doXLXYLXZLX[LXProgram: ComstarComstar 1 Comstar 2 Comstar 3 Comstar 4 1T00100>0U0# 6Comstar's specifications\00A#R60&Prime contractorHughesi(U00A#RP0PlatformHS 351 (same as Intelsat 4)[0u0A#R40"Mass at launch1516 kgY00A#R00 Mass in orbit911 kgTu0"0A#R&0Dimension2.5 mk*00A#RT0 StabilizationSpin stabilized (56 rpm)X"00A#R.0DC powerBOL: 570 W]0B0A#R80$Design lifetime10 yearsuQ00$ Equipped with two Ka-band beacons for propagation research (19 and 28.6 GHz).1B001U000600# &Comstar's C-bandY0w0A#R00(Main transponders24Y00A#R00,Backup transpondersy7w0I0B#Tn0PowerHorizontal: 5 W (TWTA)Vertical: 5.5 W (TWTA)U00A#R(0Bandwidth36 MHzSI00A#R$0CoverageCONUST0E0A#R&0EIRP max33 dBW\00A#R60Polarizationlinear H/V$E00" : 0 11Vb 1R11Comstar 10 10F0R15 :$0À" Comstar 11 11'  Generalg R11G#^@") Designation08838 / 76042A\1F1A#R6Launch date13 May 1976t'11M#jN"N ,㹌לCountry of originUnited Stateso"F1)1M#jD"H̀‰MissionTelecommunications^11A#R:,Geostationary orbit128Wq$)11M#jH" &yjLaunch vehicleAtlas Centaur_1W1A#R<Launch siteCape Canaveral&1}1# 5W11'  End of lifeW}1 1A#R,"Out of serviceyes&1/1# 8 1g1' "(Technical dataL/110 08K;TދrSpecificationsC-band: g111.ab131 1Comstar 2F1315 :$0À" Comstar 21 1d1'  Generalg 311G#^@") Designation09047 / 76073A\d1'1A#R6Launch date22 Jul 1976t'11M#jN"N ,㹌לCountry of originUnited Stateso"'1 1M#jD"H̀‰MissionTelecommunications]1g1A#R8,Geostationary orbit94Wq$ 11M#jH" &yjLaunch vehicleAtlas Centaur_g171A#R<Launch siteCape Canaveral&1]1# 5711'  End of lifeW]11A#R,"Out of serviceyes&1 1# 81G 1' "(Technical dataL 1 10 08K;TދrSpecificationsC-band: G 1 11Vbb 1 1s1Comstar 3F 1 15 :$0À" Comstar 31 1D 1'  Generalg  1 1G#^@") Designation10975 / 78068A\D 1 1A#R6Launch date29 Jun 1978t' 1{ 1M#jN"N ,㹌לCountry of originUnited Stateso" 1 1M#jD"H̀‰MissionTelecommunications]{ 1G 1A#R8,Geostationary orbit87Wq$ 1 1M#jH" &yjLaunch vehicleAtlas Centaur_G 1 1A#R<Launch siteCape Canaveral& 1= 1# 5 1r 1'  End of lifeW= 1 1A#R,"Out of serviceyes&r 1 1# 8 1'1' "(Technical dataL 1s10 08K;TދrSpecificationsC-band: '111b11QC1Comstar 4Js118 @&0À" Comstar 41 1(1'  Generalg 11G#^@") Designation12309 / 81018A\(1 @1A#R6Launch date21 Feb 19811 @1s1t'1@1M#jN"N ,㹌לCountry of originUnited Stateso" @1@1M#jD"H̀‰MissionTelecommunicationso(@1^A1G#^P"/ۀ0Geostationary orbit76W, inclinedq$@1A1M#jH" &yjLaunch vehicleAtlas Centaur_^A1.B1A#R<Launch siteCape Canaveral{A1B1$ Used for telephony and data transmission, especially to and from ships in U.S. coastal waters and the Caribbean region.8.B1C1' "(Technical dataLB1QC10 08K;TދrSpecificationsC-band: C1C11 C1C1\I1Coronas 1:QC1C1, (" Coronas 11 C1C1'  Generalg C1]D1G#^@") Designation23019 / 94014Ag&C1D1A#RLLaunch date2 Mar 1994 at 03:24 UTt']D18E1M#jN"N , Country of originRussia-UkrainGD1E1Y#"H̀4?vd;pljMissionScientific: ionosphere, magnetosphere and Sun studyE8E1^F1A#ROperatorRKA space agency (probably by the IKI science institute)^E1F1A#R:"Perigee/Apogee483/526 kmV^F1G1A#R*Inclination82.5TF1fG1A#R&Period94.7 minr%G1G1M#jJ" &ቂLaunch vehicleCyclone 3 #109]fG1\I1' The payload was developed by the IZMIRAN institute (Institute of Terrestrial Magnetism in Moscow) and includes the Terek spectroheliometer, the RES-K solar x-ray spectrograph, the Helikon solar gamma ray detector, the SUVR-SP-C ultraviolet radiometer, the DIFOS optical photometer, and other instruments.Built by NPO Yuzhnoe, platform: AUOS-SM8G1I11HabI1I1|O1Corsa B8 \I1I1, (" Corsa B9I1J1# ,Also called Hakucho1 I16J1'  Generalg J1J1G#^@") Designation11272 / 79014A\6J1J1A#R6Launch date21 Feb 1979lJ1eK1M#j>"N ,bCountry of originJapanx+J1K1M#jV"H̀_BMissionScientific: X-ray astronomy^eK1;L1A#R:"Perigee/Apogee543/566 kmVK1L1A#R*Inclination29.8T;L1L1A#R&Period95.7 miniL1NM1M#j8" & Launch vehicleMu 3CZL1M1A#R2Launch siteKagoshimaYNM1N1A#R0"Mass at launch96 kg&M1'N1# <N1cN1' * External resourcesjC'N1N1' http://heasarc.gsfc.nasa.gov/docs/heasarc/missions/hakucho.html5cN1O1'  End of lifeVN1XO1A#R*Decay15 Apr 1985$O1|O1" 6XO1O11I4bqO1 11Cos B6 |O1 1, (" Cos BO1 1|O1:O1F1# . COsmic ray Satellite1 1w1'  Generalg F1ހ1G#^@") Designation08062 / 75072A[w191A#R4Launch date9 Aug 1975m ހ11M#j@"N ,4"Country of originEurope|/91"1M#j^"H̀_BMissionScientific: gamma-ray astronomy`11A#R>"Perigee/Apogee442/99002 kmV"1؂1A#R*Inclination90.3V1.1A#R*Period2203.9 mins&؂11M#jL" &p㉂Launch vehicleThor Delta #113Z.11A#R2"Mass at launch280 kg&1!1# <1]1' *O External resources!1A16 :]http://www.esoc.esa.de/external/mso/cos.htmlhttp://astro.estec.esa.nl/SA-general/Archives/Cosb/cosb.htmlhttp://heasarc.gsfc.nasa.gov/docs/heasarc/missions/cosb.html&]1g1# 5A11'  End of life_g11A#R<"Out of service25 Apr 1982$11" 11P11zP11I"11' Dpage intentionally left blank9P1҆11c҆1 11Coupon 19 1 1, (" Coupon 11 ҆1<1'  Generalg 11G#^@") Designation25045 / 97070A\<11A#R6Launch date12 Nov 1997j1i1M#j:"N , Country of originCISo"1؈1M#jD"H̀‰MissionTelecommunications]i151A#R8,Geostationary orbit55Eo"؈11M#jD" &㉓gLaunch vehicleProton #2530 51Ԋ1' Operated by GIS: Global Information Systems and the Central Bank of Russia. Was originally to be launched in Oct 1994. The price of manufacture and launching of this satellite totalled 560 billion roubles. The insurance is to pay $70 million for the failure51 1'  End of life`Ԋ1i1A#R>"Out of servicemid-Mar 1998q 11A#RCausethe onboard frequency detector caused a computer failure. Other sources claim 2 stabilizers have failed&i1A1# 81y1' "(Technical data8A11' " Specifications~=y1/1A#Rz&Prime contractorLavochkin (first commercial comsat made)d#11A#RFPlatformPrognox 2nd generation[/11A#R4"Mass at launch2300 kgS1A1A#R$ Mass in orbitO11A#RDimensionQA11A#R Solar arrayS141A#R$ StabilizationN 11A#RDC powerU41׏1A#R($Design lifetimea=1D1$ zOnl׏1D11y 70% of the planned power is effectively operational.1 ׏1u1'  Ku-bandYD11A#R0(Main transponders16Yu1'1A#R0,Backup transpondersK 1r1A#RPowerU'11A#R(Bandwidth36 MHzl+r131A#RVCoverageEurope and Asia, several spotsT11A#R&EIRP max50 dBWX311A#R.Polarizationlinear&11# K$1P1' H Transponder frequency chart (GHz);11c#v . L HorizontalDownlinkTransponderVerticalDownlink_ P1M1R#t10.980_ 11R#t 10.980_ M1 1R#t11.060_ 1j1R#t 11.060_ 11R#t11.100_ j1(1R#t 11.100_ 11R#t11.180_ (11R#t 11.180_ 1E1R#t11.480_ 11R#t 11.480_ E11R#t11.560_ 1b1R#t 11.560_ 11R#t11.600_ b1 1R#t 11.600_ 11R#t11.680_ 11R#t 11.680$11" 91;11YKcEc;1t11Coupon 29 1t1, (" Coupon 21 ;11'  GeneralYt11G#^$") DesignationY1W1A#R0Launch datemid-1999j11M#j:"N , Country of originCISo"W101M#jD"H̀‰MissionTelecommunications]11A#R8,Geostationary orbit55Ej011M#j:" &㉓gLaunch vehicleProton|11) Originally planned for launch in April 1995, slotted in 9.5WThe atomic standard in the onboard synchronizing device will be discarded. Its malfunctions were responsible for putting the first satellite out of order. The second satellite will have its productivity doubled as compared with the first satellite, and its service life in orbit will reach 12 years.Kupon-M bus1111W1!1G1T+1!1) "VȠ$To view this page you need to register&1G1# 9!111c112Coupon 39 G11, (" Coupon 3U212# dLaunch planned in October 1995 slot12G1ted in 162E11K21WK222T+22) "VȠ$To view this page you need to register&K22# ; 221\qd2;2f2Courier 1B;2;2, ( " Courier 1B1 2l2'  Generalg ;22G#^@") Designation00058 / 60013A[l2.2A#R4Launch date4 Oct 1960t'22M#jN"N ,㹌לCountry of originUnited States7.2&2M#jn"H̀㓉MissionTelecommunications: recording satellite_22A#R<"Perigee/Apogee967/1214 kmV&22A#R*Inclination28.3U202A#R(Period107.1 minq$22M#jH" &Gi4Launch vehicleThor Ablestar_022A#R<Launch siteCape CanaveralfB2f2$ Could record messages from Earth station and rebroadcast them.4221.dd22- 2CTA4f22, (" CTA1 22'  Generalg 2f2G#^@") Designation22214 / 92070C\22A#R6Launch date22 Oct 1992m f2/2M#j@"N ,xW Country of originCanadaU22G#^"H̀Mission^/22A#R:"Perigee/Apogee164/243 kmV282A#R*Inclination28.4T22A#R&Period88.4 minj822M#j:" &ϛLaunch vehicleSTS 52&2 2# 52Q 2'  End of lifec" 2 2A#RDCauseRetrieved by the ShuttleUQ 2 2A#R(Decay1 Nov 1992$ 2- 2" 4 2a 21dda 2 2 @2CTS4- 2 2, (" CTS8a 2 2# *Also called Herms1 2 2'  Generalg 2e 2G#^@") Designation08585 / 76004A\ 2 2A#R6Launch date17 Jan 1976m e 2. 2M#j@"N ,xW Country of originCanadao" 2 2M#jD"H̀‰MissionTelecommunications^. 2 2A#R:,Geostationary orbit116Ws& 2n 2M#jL" &p㉂Launch vehicleThor Delta #119k* 2 2A#RT"Mass at launch674 kg, 347 kg in orbit{n 2x2$ Used by the United States and Canada for TV transmission tests with small Earth stations. Also used for computer links.< 22' *O External resourcesU.x2 2' \http://sulu.lerc.nasa.gov/dglover/cts.html&2/2# 5 2d2'  End of lifea /22A#R@"Out of serviceNovember 1979$d2 @2" 2 @2- 2C2O@21 d dO@2@2K2Program: CyberstarC @2@2, (0" Program: Cyberstar3O@2B2. * 'Telecommunication program operated by Loral The CyberStar network proposes to offer services such as video telephony and videoconferencing, medical and technical tele-imaging, high-speed data networks and "bandwidth on demand." Program worth $1.6 billion3 satellites operating in Ka-band to be located at: 28E, 105.5E, and 115W. Cost: $1.6 billionFirst satellite to be launched in 1998, meanwhile Ku-band capacity should be leased to start broadcasting in 1997. This schedule seems to be 1 year late now.j@@2/C2* $㋗hPA strategic partnership was drawn with Alcatel's Skybridge<B2kC2' *O External resourcesD/C2C2' :http://www.cyberstar.com/8kC2C2' "(OTechnical data8C2D2' " SpecificationsZC2yD2A#R2&Prime contractorSS/LN D2D2A#RPlatformTyD2E2A#R&"Mass at launchSD2nE2A#R$ Mass in orbitOE2E2A#RDimensionQnE2F2A#R Solar arraySE2aF2A#R$ StabilizationN F2F2A#RDC powerUaF2G2A#R($Design lifetime&F2*G2# 1 G2[G2'  Ka-bandW*G2G2A#R,(Main transpondersY[G2 H2A#R0,Backup transpondersK G2VH2A#RPowerO H2H2A#RBandwidth_VH2I2A#R<Coverage27 regional beamsN H2RI2A#REIRP max[I2I2A#R4PolarizationRHCP/LHCPLRI2;J2B#TFrequenciesUplink: 28.35-28.6 and 29.5-30.0 GHzDownlink: 19.7-20.2 GHzI2K2' [on-board switchingFrequency Division Multiple (FDM)/Time Division Multiplexed (TDM) protocol for uplink and TDM for downlink. Inter-satellite link at 60 GHz is planned1;J2@K21W@K2K2K2T+K2K2) "VȠ$To view this page you need to register&@K2K2# > K2K21~dIdK26L2L2Program: Dash>K26L2, (&" Program: DashM*K2L2# TAmerican program for radars calibration= 6L2L21t d3eL2 M2PO2Program: DBSML2 M28 @,c%" Program: DBS[L2N24 6?qO\@ggAmerican digital direct TV program operated by HCI.Two companies provide TV packages: DirecTV, a subsidiary of GM Hughes Electronics, and USSB a division of Hubbard Broadcasting Inc. The receivers were (at the beginning solely) provided by Thomson Consumer Electronics (RCA trademark).Six additional satellites are planned (in mid-1997)1 M2N2' O ContactGN2PO2< H?qO\@ggDirecTvTel: +1-818-569-7700http://www.directv.comHCIUSSB1N2O21O2 2z2PO2 2H `dlS~9T9T〽9Tぽ9TProgram: DBSDBS 1DBS 2DBS 3DBS 4O2 2PO21O2=21=2 29 2v2# ,DBS' specifications\=2Ҁ2A#R60&Prime contractorHughesUv2'2A#R(0PlatformHS-601S[Ҁ22A#R40"Mass at launch2930 kgZ'2܁2A#R20 Mass in orbit1700 kgc"2?2A#RD0Dimension2.27 x 2.27 x 2.27 m\܁22A#R60Solar array35.1 m spanY?22A#R00 Stabilization3 axisT2H2A#R&0DC power4500 W]22A#R80$Design lifetime12 years{WH2 2$ Transponders are optimized for digital TV: fixed gain and automatic level control. 12Q21qQ22B 22# >DBS' Ku-band (12.2-12.7 GHz)YQ22A#R00(Main transponders16Z2F2A#R20,Backup transponders8W22A#R,0Power120 W (TWTA)UF22A#R(0Bandwidth24 MHzd2V2G#^:0BTCoverageContinental UST22A#R&0EIRP max52 dBWVV22A#R*0PolarizationLHCPj22' The system can be configured as 8 transponders with 240 W power to provide 2.9 dBW more.The DSS architecture can broadcast 40Mbits/sec per transponder in either of two error control modes. In High mode, 30Mbps is allocated to information and 10Mbps to error control. In Low mode, 23Mbps is allocated to information and 17Mbps is allocated to error control.12ˆ21ˆ292w@2927 >c%"RDBS' EIRPAdd 2.9 dBW for transponders with 240 W power.6ˆ2o21eo22B2DBS 1B 9225 :c%" DBS 11 o22'  Generalg 2I2G#^@") Designation22930 / 93078A\22A#R6Launch date18 Dec 1993t'I22M#jN"N ,㹌לCountry of originUnited Statesf22M#j2"H̀‰MissionDirect TVh!22G#^B"/ۀ0Geostationary orbit101.2Wn!2U2M#jB" &D+Launch vehicleAriane V62&2{2# 8U22' "(Technical dataU{2B2: DBTYlƉoEIRP coverage (dBW)SpecificationsKu-bandUplink frequency: 17.3-18.8 GHz62x21eex222DBS 2FB228 @c%" DBS 21 x22'  Generalg 2V2G#^@") Designation23192 / 94047A[22A#R4Launch date3 Aug 1994t'V2%2M#jN"N ,㹌לCountry of originUnited Statesf22M#j2"H̀‰MissionDirect TVh!%2 2G#^B"/ۀ0Geostationary orbit100.8W2 2B2q$2}2M#jH" &yjLaunch vehicleAtlas CentaurH# 22% GIt carried a time capsule named SpaceArc containing messages from the vice-president of the U.S.A. (Al-Gore) and his predecessor. After its useful life span the spacecraft will be moved to a higher orbit so that only an explorer from a distant future generation may uncover the messages.8}22' "(Technical dataY22: DBTYlƉoEIRP coverage (dBW)SpecificationsKu-bandApogee motor: ARC490N (liquid fuel)6221ee222DBS 3B 225 :c%" DBS 31 292'  Generalg 22G#^@") Designation23598 / 95029A\922A#R6Launch date10 Jun 1995t'2p2M#jN"N ,㹌לCountry of originUnited Statesf22M#j2"H̀‰MissionDirect TV^p242A#R:,Geostationary orbit101Wn!22M#jB" &D+Launch vehicleAriane V74J&422$ LWill be used ofr power enforcement82$2' "(Technical datal4228 @hBTYlƉoEIRP coverage (dBW)SpecificationsKu-band6$2216e22 2DBS 4B 225 :c%" DBS 41 292'  GeneralY22G#^$") Designation`922A#R>Launch dateplanned in 1996t'2f2M#jN"N ,㹌לCountry of originUnited Statesf22M#j2"H̀‰MissionDirect TV^f2*2A#R:,Geostationary orbit157Wr%22M#jJ" &yjLaunch vehicleAtlas Centaur?qM*2 2$ Probably only a ground reserve, to be launch in case of problems in orbit12>21W>222T+ 22) "VȠ$To view this page you need to register&>22# 6221Id)e2,22Debut> 2,22 4"  DebutA2m2) "0 Also called Orizuru1 ,22'  Generalg m22G#^@") Designation20479 / 90013B[2`2A#R4Launch date8 Feb 1990l22M#j>"N ,bCountry of originJapanU`2!2G#^"H̀Mission_22A#R<"Perigee/Apogee908/1742 kmT!22A#R&Inclination99U2)2A#R(Period112.2 minf22M#j2" &JLaunch vehicleH1$)22" ; 2213e;f2)23Delta Star;2)2, ( " Delta Star92b2# ,Also called USA 0361 )22'  Generalg b2 3G#^@") Designation19911 / 89026A2 32\2h3A#R6Launch date24 Mar 1989t' 33M#jN"N ,㹌לCountry of originUnited States]h393G#^,"H̀MissionMilitary^33A#R:"Perigee/Apogee307/312 kmV933A#R*Inclination47.7T3A3A#R&Period90.7 mins&33M#jL" &p㉂Launch vehicleThor Delta #184wSA3+3$ Part of the Star War program. Payload: radar, laser and 7 optical sensors (IR).53`3'  End of lifeV+33A#R*Decay23 Jun 1992$`33" 6331)ef3F3 3Denpa6 3F3, (" Denpa83~3# *Means "radio wave"1 F33'  Generalg ~33G#^@") Designation06152 / 72064A\3r3A#R6Launch date19 Aug 1972l33M#j>"N ,bCountry of originJapany,r3W3M#jX"H̀?vMissionScientific: ionosphere study_33A#R<"Perigee/Apogee238/6322 kmTW3 3A#R&Inclination31U3_3A#R(Period157.4 mini 33M#j8" & Launch vehicleMu 4SZ_3"3A#R2Launch siteKagoshimaY3{3A#R0"Mass at launch75 kg&"33# <{33' *O External resourcesV/33 3' ^http://www.isas.ac.jp/info/sat/denpa-e.html&3Y 3# 53 3 3'  End of lifeVY 3 3A#R*Decay19 May 1980$ 3 3" H 3P 31;fgP 3 3' 3Program: DFS KopernikusT 3 35 :@ⰹc%" Program: DFS KopernikusUP 3' 3. , ѤRgDeutscher Fernmelde SatellitGerman telecommunication program operated by DTAG1 3X 31X 3 3v5' 3 3A Rj0`ʗ>T˗>T̗>TProgram: DFS KopernikusDFS 1DFS 2DFS 31X 3 31U 38A3\A3E" 3D 3# DDFS Kopernikus's specifications|; 3 3A#Rv&Prime contractorR-DFS consortium with ANT and MBB-ERNOZD 3 3A#R2PlatformSpacebus 100[ 3u 3A#R4"Mass at launch1415 kgY 3 3A#R0 Mass in orbit850 kg>u 3M3A#R|Payload mass158 kg: transponders: 126 kg, antennas: 32 kg` 33A#R>Dimension1.4 x 1.9 x 4.1 m\M3 3A#R6Solar array15.4 m spanY3b3A#R0 Stabilization3 axis? 3 @3B#T~DC powerBOL: 1990 WEOL: solstice: 1463 W, equinox: 1558 Wb3 @3 3Xb3d@3A#R. Payload power896 W] @3@3A#R8$Design lifetime10 yearsw6d@38A3A#RlCapacity1800 phone circuits and 200 data circuits$@3\A3" 18A3A31UA3D3E3>\A3A3# 6DFS Kopernikus's Ku-bandYA3$B3A#R00(Main transponders10YA3}B3A#R00,Backup transpondersV$B3B3A#R*0Power20 W (TWTA)O}B3dC3B#T0Bandwidth3 transponders in 11 GHz: 90 MHz7 transponders in 12 GHz: 44 MHzUB3C3A#R(0CoverageGermanyTdC3 D3A#R&0EIRP max49 dBWXC3eD3A#R.0PolarizationlinearP D3D3B#T0Uplink14.0-14.25 GHz for 11 GHz downlink14.25-14.5 GHz for 12 GHz downlink$eD3E3" 1D3LE31ULE3H3H3>E3E3# 6DFS Kopernikus's Ka-bandXLE3E3A#R.0(Main transponders1YE3;F3A#R00,Backup transpondersVE3F3A#R*0Power20 W (TWTA)U;F3F3A#R(0Bandwidth90 MHzUF3;G3A#R(0CoverageGermanyTF3G3A#R&0EIRP max48 dBWR;G3G3A#R"0PolarizationYG3:H3A#R00Uplink29.5-29.6 GHz[G3H3A#R40Downlink19.7-19.8 GHz$:H3H3" 1H3H31UH3N3N3X5H3BI3# jDFS Kopernikus's Transponder frequency chart (GHz);H3I3c#v . L HorizontalDownlinkTransponderVerticalDownlinkaBI3AJ3R#t11.475A1aI3J3R#t11.525A2aAJ3K3R#tB111.550aJ3dK3R#tB211.600aK3K3R#t11.625C1adK3&L3R#t11.675C2aK3L3R#tK112.524a&L3L3R#t12.559K2aL3IM3R#tK312.591aL3M3R#t12.625K4aIM3 N3R#tK512.658aM3lN3R#t12.692K6a N3N3R#tK712.725$lN3N3" 6N3'O31|g'O3iO3E3DFS 1B N3iO35 :ⰹc%" DFS 11 'O3O3'  Generalg iO3 3G#^@") Designation20041 / 89041BO3 3N3[O3h3A#R4Launch date5 Jun 1989n! 3ր3M#jB"N , Country of originGermanyo"h3E3M#jD"H̀‰MissionTelecommunicationsb!ր33A#RB,Geostationary orbitsee belown!E33M#jB" &2D+Launch vehicleAriane V31&3;3# : 3u3- */ۀ Location;33m#:   " BeginEndPositionu33j#,"&(L: 5 Jun 198933j#>,.Jan 1991Jan 199323.5E33j#>,.Jul 1993Nov 199533.5E383% Ran out of control a few days in Nov 1995. Control was regained in early December but DFS 1 escaped again in mid-December 199553m3'  End of life\83Ʌ3A#R6"Out of serviceNov 1995c"m3,3A#RDCausesatellite out of control&Ʌ3R3# 8,33' "(Technical data{R3E3@ Pߩ%##`#`WSpecificationsKu-bandKa-bandTransponder frequency chartBeacon: 11.450 GHz vertical & 11.4535 GHz horizontal63{31fg{33|3DFS 2B E335 :ⰹc%" DFS 21 {33'  Generalg 3U3G#^@") Designation20706 / 90063B\33A#R6Launch date24 Jul 1990n!U33M#jB"N , Country of originGermanyo"33M#jD"H̀‰MissionTelecommunicationsg 33G#^@"/ۀ0Geostationary orbit28.5En!3c3M#jB" &8D+Launch vehicleAriane V37&33# 8c33' "(Technical data{3|3@ Pߩ%##`#`WSpecificationsKu-bandKa-bandTransponder frequency chartBeacon: 11.450 GHz vertical & 11.4535 GHz horizontal6331|g333DFS 3B |335 :ⰹc%" DFS 31 3%3'  Generalg 33G#^@") Designation22175 / 92066A\%33A#R6Launch date12 Oct 1992n!3V3M#jB"N , Country of originGermanyo"3ō3M#jD"H̀‰MissionTelecommunicationsg V3,3G#^@"/ۀ0Geostationary orbit23.5Ep#ō33M#jF" &p㉂Launch vehicleDelta 2 #215&,3Ž3# 833' "(Technical data\Ž33F \ɇcߩ%##`#`WEIRP coverage (dBW)SpecificationsKu-bandKa-bandTransponder frequency chart13͏31͏3.3U3.36 <@̗>T"S͏3.33DFS Kopernikus 3's EIRPA͏3o31fgo33/3Program: DiadmeQ.338 @4⌥" Program: DiadmeoLo3/3# French scientific program: geodesy studies using laser and doppler effect13`31`33h./33: D\ 㦼㧼Program: DiadmeDiadme 1Diadme 2: `331g3H33Diadme 1F3H35 :$⌥" Diadme 153}3# $Also called D1C1 H33'  Generalg }33G#^@") Designation02674 / 67011A[3p3A#R4Launch date8 Feb 1967m 33M#j@"N ,㱭+Country of originFrancep#p3M3M#jF"H̀CV$MissionScientific: geodesyR33A#R"OperatorCNES_M33A#R<"Perigee/Apogee545/1083 kmV3T3A#R*Inclination39.9U33A#R(Period101.2 minn!T33M#jB" &A͉Launch vehicleDiamant #3Y3p3A#R0"Mass at launch20 kg&33# 5p33'  End of life^3)3A#R:"Out of service2 Jan 1970_33A#R<CauseStopped broadcasting$)33" : 331]g3,3X3Diadme 2F3,35 :$⌥" Diadme 253a3# $Also called D1D1 ,33'  Generalg a33G#^@") Designation02680 / 67014A\3U3A#R6Launch date15 Feb 1967m 33M#j@"N ,㱭+Country of originFrancep#U323M#jF"H̀CV$MissionScientific: geodesyR33A#R"OperatorCNES_233A#R<"Perigee/Apogee586/1731 kmV393A#R*Inclination39.4U33A#R(Period108.5 minn!933M#jB" &A͉Launch vehicleDiamant #4Y3U3A#R0"Mass at launch20 kg&3{3# 5U33'  End of lifeC{343A#R"Out of service16 Sep 1968 (stopped transmitting on 5 Apr 1967)$3X3" 94331gh33\4Diapason9 X33, (" Diapason533# $Also called D1A1 303'  Generalg 33G#^@") Designation02016 / 66013A\033A#R6Launch date17 Feb 1966m 3`3M#j@"N ,㱭+Country of originFrancep#33M#jF"H̀CV$MissionScientific: geodesyR`3.4A#R"3.4X3OperatorCNES_34A#R<"Perigee/Apogee502/2484 kmV.44A#R*Inclination34.1U484A#R(Period115.8 minn!44M#jB" &A͉Launch vehicleDiamant #2[844A#R4"Mass at launch18.5 kgD 4E4$ @Also used to test technology54z4'  End of life_E44A#R<"Out of service23 Jan 1972_z484A#R<CauseStopped transmitting$4\4" D8441#gh444Program: DiscovererD\44, (2" Program: Discoverer442 2 QdI#*≂USAF program: 38 satellites launched between 28 Feb 1959 and 27 Feb 1962It seems that all Discoverers beginning with number 14 are KH spysats. See Thor Agena listing for the launches.> 441hi4^44Program: DMSPJ4^45 :,?cG" Program: DMSPD44= H n։ YS?Defense Meteorological Satellite ProgramMilitary meteorology program operated by the Air Force Space Command. The technology was first tested by the AMS program. All DMSP satellites were built by RCA Astro Space, which is now Lockheed Martin Astro Space; based on the Tiros N bus. 5 DMSP B5D3 have been ordered<^44' *O External resources446 :!http://www.ngdc.noaa.gov/dmsp/dmsp.htmlhttp://www.spacecom.af.mil/usspace/dmsp.htmhttp://www.fas.org/spp/military/program/met/dmsp.htm1441_4@ 4.4@ 4P n9㧢щ㫢щ㬢щ㭢щProgram: DMSPDMSP B5D1-1 (76091A)DMSP B5D1-2 (77044A)DMSP B5D1-3 (78042A)DMSP B5D1-4 (79050A)DMSP B5D2-3DMSP B5D2-4 (88006A)DMSP B5D2-5 (90105A)DMSP B5D2-6 (91082A)DMSP B5D2-7DMSP B5D2-8DMSP B5D2-914q 41Uq 4 4. 4@@ 4 4# :DMSP B5D1's specificationsd#q 4 4A#RF&Prime contractorMM Astro SpaceN 4c 4A#RPlatformh' 4 4A#RN"Mass at launchbetween 450 & 513 kgSc 4 4A#R$ Mass in orbitT 4r 4A#R&Diameter1.68 mQ 4 4A#R Height6.4 mQr 4 4A#R Solar arrayS 4g 4A#R$ StabilizationN  4 4A#RDC powerUg 4 4A#R($Design lifetime$ 4. 4" 1 4_ 41U_ 4A4;A4@. 4 4# :DMSP B5D2's specificationsd#_ 44A#RF&Prime contractorLM Astro Spacen' 4q4G#^N?Platformbased on the Tiros N bus[44A#R4"Mass at launch750 kg?Sq44A#R$ Mass in orbitT4s4A#R&Diameter1.68 mQ44A#R Height6.4 mQs4!@4A#R 4!@4. 4Solar arrayS4t@4A#R$ StabilizationN !@4@4A#RDC powerUt@4A4A#R($Design lifetime$@4;A4" < A4wA41hhwA4A4F4DMSP B5D2-3H;A4A45 :(?cG" DMSP B5D2-3G$wA4B4# HAlso called USA 026 or DMSP 195431 A47B4'  Generalg B4B4G#^@") Designation18123 / 87053Ah'7B4C4A#RNLaunch date20 Jun 1987 at 02:34 UTt'B4zC4M#jN"N ,㹌לCountry of originUnited Statesr%C4C4M#jJ"H̀l/MissionMilitary: meteorology^zC4JD4A#R:"Perigee/Apogee828/848 kmVC4D4A#R*Inclination98.8UJD4D4A#R(Period101.7 minm D4bE4M#j@" &26Launch vehicleAtlas E59[D4E4A#R4Launch siteVandenbergZbE4F4A#R2"Mass at launch822 kgkGE4F4$ Must detect tropical cyclones and evaluate the intensity of storms.8F4F4' "(Technical data<F4F4) "&[\ Specifications< F42G41O5hh2G4zG4L4DMSP B5D2-7HF4zG45 :(?cG" DMSP B5D2-7W42G4G4# hAlso called USA 106 and DMSP 5D F12 or DMSP 235451 zG4H4'  Generalg G4iH4G#^@") Designation23233 / 94057Ah'H4H4A#RNLaunch date29 Aug 1994 at 17:38 UTt'iH4EI4M#jN"N ,㹌לCountry of originUnited Statesr%H4I4M#jJ"H̀l/MissionMilitary: meteorology^EI4J4A#R:"Perigee/Apogee840/860 kmVI4kJ4A#R*Inclination98.9UJ4J4A#R(Period101.9 minm kJ4-K4M#j@" &26Launch vehicleAtlas E20[J4K4A#R4Launch siteVandenbergx-K4$L4$ It carries instruments to measure energetic particles in the magnetosphere and photometers to scan auroral displays.8K4\L4' "(Technical data<$L4L4) "&[\ Specifications< \L4L41hiL4M44DMSP B5D2-8HL4M45 :(?cG" DMSP B5D2-8W4L4sM4# hAlso called USA 109 and DMSP 5D F13 or DMSP 245471 M4M4'  Generalg sM4 N4G#^@") Designation23533 / 95015Ah'M4sN4A#RNLaunch date24 Mar 1995 at 14:05 UTt' N4N4M#jN"N ,㹌לCountry of originUnited Statesr%sN4YO4M#jJ"H̀l/MissionMilitary: meteorology^N4O4A#R:"Perigee/Apogee846/854 kmVYO44A#R*InclinaO44L4tion98.8UO4n4A#R(Period101.9 minm 4ۀ4M#j@" &26Launch vehicleAtlas E45`n4;4A#R>Launch siteVandenberg SLC3: ۀ4u4- (26The satellite carries the OLS (Operational Linescan System) weather imager, and a set of microwave sounders and particle detectors.The launch vehicle was the last Atlas E, a refurbished intercontinental ballistic missile which had been built in the early 1960s.8;44' "(Technical data<u44) "&[\ Specifications< 4%41h%4m4 4DMSP B5D2-9H4m45 :(?cG" DMSP B5D2-9I&%44# LAlso called USA 131 and DMSP 5D F141 m44'  Generalg 4N4G#^@") Designation24753 / 97012A[44A#R4Launch date4 Apr 1997t'N44M#jN"N ,㹌לCountry of originUnited Statesr%44M#jJ"H̀l/MissionMilitary: meteorologyZ44A#R2"Perigee/Apogee850 kmT4=4A#R&Inclination99S44A#R$Period102 mino"=44M#jD" &^]Launch vehicleTitan 2 #18[4Z4A#R4Launch siteVandenberg?44$ 6Last of the B5D2 series8Z4ч4' "(Technical data<4 4) "&[\ SpecificationsHч4U41IhqU444Program: Dong Fang HongT 445 :@⥹c%" Program: Dong Fang HongU44( Means "The Orient is red", also called DFH or PRCPeople's Republic of China program which contains numerous sub-programs. Very few details are available...Among those subprograms the Zhongxing alias Chinasat telecommunication program1441U4Q4u4E474) "8mSProgram: Dong Fang Hong4Q4#!(v&"(v&#(v&$(v&%(v&&(v&'(v&((v&)(v&&v&&v&&v&&v&&v&&v&&v&&&v&&v&&v&&v&&v&&v&&v&&v&&v&&v&&v&&v&&v&&v&&v&&v&L&v&&v&&v&&v&('v&'v& 'v&!'v&"'v&#'v&$'v&DFH 01DFH 02DFH 03DFH 04DFH 05DFH 06DFH 07DFH 08DFH 09DFH 10DFH 11DFH 12DFH 13DFH 14DFH 15DFH 16DFH 17DFH 18DFH 19DFH 20DFH 21DFH 22DFH 23DFH 24DFH 25DFH 26DFH 30DFH 31DFH 32DFH 33DFH 34DFH 35DFH 36DFH 37DFH 38DFH 39DFH 40DFH 41DFH 42DFH 43DFH 44DFH 45DFH 46$74u4" 1Q44144:u44# .Feng Yun 1's payloadX+484- *V  VHRR (Very High Resolution Radiometer)44F#Z0Wavebands0.58-0.68 m (visible)0.725-1.1 m (near IR)0.48-0.53 m (visible)0.53-0.58 m (visible)10.5-12.5 m (thermal IR)k)84l4B#TR0Resolution1.1 km (visible)4 km (IR)X4ď4A#R.0Swath width3200 kmL(l44$ PEquipped with 2 of thoď44u4se radiometers1ď4M41UM4J4n444, & STTW's specificationsShiyan Tongbu Tongxin Weixing means experimental synchronous communications satellite. Could also be named DFH 1f%M4k4A#RJ0&Prime contractorChinese industryR44A#R"0PlatformSTTW[k44A#R40"Mass at launch1024 kga 4y4A#R@0 Mass in orbitapprox. 450 kgS44A#R$0Diameter2.1 mr1y4>4A#Rb0Solar arraycells mounted on cylindrical bodyb!44A#RB0 StabilizationSpin stabilizedN >44A#R0DC power\4J4A#R60$Design lifetime4 years$4n4" 1J441U4/4S43n44#  STTW's C-bandX4*4A#R.0(Main transponders2Y44A#R00,Backup transpondersV*44A#R*0Power10 W (TWTA)U4.4A#R(0Bandwidth36 MHzS44A#R$0CoverageChinaT.44A#R&0EIRP max32 dBWZ4/4A#R20Polarizationlinear H$4S4" 1/441U444<S44# 2DFH 2's specificationsf%4&4A#RJ0&Prime contractorChinese industryS4y4A#R$0PlatformDFH 2T&44A#R&0"Mass at launchSy4 4A#R$0 Mass in orbitN 4n4A#R0DiameterQ 44A#R 0Solar arrayb!n4!4A#RB0 StabilizationSpin stabilizedN 4o4A#R0DC power]!44A#R80$Design lifetime4 years?$o44" 14!41U!44444U4# "DFH 2's C-bandX!44A#R.0(Main transponders4YU44A#R00,Backup transpondersV4\4A#R*0Power10 W (TWTA)U44A#R(0Bandwidth36 MHzS\44A#R$0CoverageChinaT4X4A#R&0EIRP max32 dBWZ44A#R20Polarizationlinear H$X44" 1441U4"5F5<4C4# 2DFH 3's specifications_44A#R<0&Prime contractorCAST/DASASC44A#R$0PlatformDFH 3[4P4A#R40"Mass at launch2230 kgZ44A#R20 Mass in orbit1100 kgL P4 5A#R0Length4 54K 4W5A#R0WidthL 55A#R0HeightYW55A#R00 Stabilization3 axisN 5J5A#R0DC power\55A#R60$Design lifetime8 years|;J5"5A#Rv0Capacity6 tv channels and 8000 phone calls per minute!$5F5" 1"5w51Uw5\554F55# "DFH 3's C-bandYw55A#R00(Main transponders24Y5]5A#R00,Backup transpondersF55B#T0Power6 transponders of 20 W (TWTA)18 transponders of 10 W (TWTA)U]5:5A#R(0Bandwidth36 MHzS55A#R$0CoverageChina};:5 5B#Tv0EIRP max6 transponders: 38 dBW18 transponders: 35 dBWR5\5A#R"0Polarization$ 55" B\551Zj559 5Dong Fang Hong 01N555 :4⥹c%" Dong Fang Hong 0175G5# (Also called Mao 11 5x5'  Generalg G55G#^@") Designation04382 / 70034A\x5;5A#R6Launch date24 Apr 1970l55M#j>"N ,6"Country of originChina_;55G#^0"H̀MissionScientific_5e5A#R<"Perigee/Apogee431/2163 kmV55A#R*Inclination68.4Ue5 5A#R(Period111.5 minp#5 5M#jF" &9+SLaunch vehicleLong March 1Z 5 5A#R2"Mass at launch173 kg_; 59 5$ vFrequencies: 20.008 MHz, 202 MHz, 2752 MHz and 5600 MHzB 5{ 51jaj{ 5 55Dong Fang Hong 02N9 5 55 :4⥹c%" Dong Fang Hong 02?{ 5 5# 8Also called Mao 2 or SJ 11 59 5'  Generalg  5 5G#^@") Designation05007 / 71018A[9 5 5A#R4Launch date3 Mar 1971l 5g 5M#j>"N ,6"Country of originChinai" 5 5G#^D"H̀MissionScientific (Shijian)_g 5/ 5A#R<"Perigee/Apogee265/1833 kmV 5 5A#R*Inclination69.8U/ 5 5A#R(Period106.1 minp# 5J5M#jF" &9+SLaunch vehicleLong March 1kG 55$ Frequencies: 19.997 MHz, 20.008 MHz, 202 MHz, 2752 MHz and 5600 MHzBJ551jj5E5C5Dong Fang Hong 03N5E55 :4⥹c%" Dong Fang Hong 03A55# <Also called Mao 3 or JSSW 11 E55'  Generalg 5*@5G#^@") 5*@55Designation08053 / 75070A\5@5A#R6Launch date26 Jul 1975l*@5@5M#j>"N ,6"Country of originChinar%@5dA5M#jJ"H̀郉MissionRemote sensing (JSSW)^@5A5A#R:"Perigee/Apogee190/455 kmTdA5B5A#R&Inclination69TA5jB5A#R&Period90.9 minhB5B5M#j6" &9+SLaunch vehicleFB 1&jB5B5# 5B5-C5'  End of lifeVB5C5A#R*Decay14 Sep 1975$-C5C5" BC5C51QajtjC57D5WI5Dong Fang Hong 04NC57D55 :4⥹c%" Dong Fang Hong 04BC5yD5# >Also called Mao 4 or FSW 0-11 7D5D5'  Generalg yD5E5G#^@") Designation08452 / 75111A\D5mE5A#R6Launch date26 Nov 1975lE5E5M#j>"N ,6"Country of originChinaq$mE5JF5M#jH"H̀郉MissionRemote sensing (FSW)^E5F5A#R:"Perigee/Apogee173/483 kmTJF5F5A#R&Inclination63TF5PG5A#R&Period91.1 minq$F5G5M#jH" &9+SLaunch vehicleLong March 2C&PG5G5# 5G5H5'  End of life^G5zH5A#R:"Out of service3 Dec 1975c"H5H5A#RDCauseNormal (photos recovery)VzH53I5A#R*Decay29 Dec 1975$H5WI5" B3I5I51jjI5I5AN5Dong Fang Hong 05RWI5I58 @6⥹c%" Dong Fang Hong 05AI5,J5# <Also called Mao 5 or JSSW 21 I5]J5'  Generalg ,J5J5G#^@") Designation08488 / 75119A\]J5 K5A#R6Launch date16 Dec 1975lJ5K5M#j>"N ,6"Country of originChinar% K5K5M#jJ"H̀郉MissionRemote sensing (JSSW)^K5\L5A#R:"Perigee/Apogee186/387 kmTK5L5A#R&Inclination69T\L5M5A#R&Period90.3 minhL5lM5M#j6" &9+SLaunch vehicleFB 1&M5M5# 5lM5M5'  End of lifeVM5N5A#R*Decay27 Jan 1976$M5AN5" BN5N51tjkN5N5;5Dong Fang Hong 06RAN5N58 @6⥹c%" Dong Fang Hong 06AN5O5# <Also called Mao 6 or JSSW 31 N5GO5'  Generalg O5O5G#^@") Designation09394 / 76087A\GO55A#R6Launch date30 O55AN5Aug 1976lO55M#j>"N ,6"Country of originChinar%55M#jJ"H̀郉MissionRemote sensing (JSSW)_5S5A#R<"Perigee/Apogee195/2145 kmV55A#R*Inclination69.2US55A#R(Period108.8 minh5f5M#j6" &9+SLaunch vehicleFB 1&55# 5f55'  End of lifeV55A#R*Decay25 Nov 1978$5;5" B5}51jk}5σ5.5Dong Fang Hong 07R;5σ58 @6⥹c%" Dong Fang Hong 07B}55# >Also called Mao 7 or FSW 0-21 σ5B5'  Generalg 55G#^@") Designation09587 / 76117A[B55A#R4Launch date7 Dec 1976l5p5M#j>"N ,6"Country of originChinaq$55M#jH"H̀郉MissionRemote sensing (FSW)^p5?5A#R:"Perigee/Apogee172/489 kmV55A#R*Inclination59.4T?55A#R&Period91.1 minq$5Z5M#jH" &9+SLaunch vehicleLong March 2C&55# 5Z55'  End of lifeU5 5A#R(Decay2 Jan 1977$5.5" B 5p51kokp5ˆ5 5Dong Fang Hong 08R.5ˆ58 @6⥹c%" Dong Fang Hong 08Bp55# >Also called Mao 8 or FSW 0-31 ˆ555'  Generalg 55G#^@") Designation10611 / 78011A\555A#R6Launch date26 Jan 1978l5d5M#j>"N ,6"Country of originChinaq$5Պ5M#jH"H̀郉MissionRemote sensing (FSW)^d535A#R:"Perigee/Apogee186/507 kmTՊ55A#R&Inclination57T35ۋ5A#R&Period91.4 minq$5L5M#jH" &9+SLaunch vehicleLong March 2C&ۋ5r5# 5L55'  End of lifeUr55A#R(Decay7 Feb 1978$5 5" B5b51klkb555Dong Fang Hong 09N 555 :4⥹c%" Dong Fang Hong 096b55# &Also called SJ 21 55'  Generalg 5~5G#^@") Designation12842 / 81093A\5ڎ5A#R6Launch date19 Sep 1981l~5F5M#j>"N ,6"Country of originChina6ڎ5ɏ5M#jl"H̀?vMissionScientific: ionosphere study (Shijian)_F545A#R<ɏ545 5"Perigee/Apogee232/1598 kmVɏ55A#R*Inclination59.5U455A#R(Period103.3 minh5G5M#j6" &9+SLaunch vehicleFB 1&5m5# 5G55'  End of lifeVm55A#R*Decay19 Sep 1981$55" B5^51lokk^555Dong Fang Hong 10R558 @6⥹c%" Dong Fang Hong 107^55# (Also called SJ 3A1 55'  Generalg 55G#^@") Designation12843 / 81093B\55A#R6Launch date19 Sep 1981l5G5M#j>"N ,6"Country of originChina^55G#^."H̀Mission(Shijian)_G55A#R<"Perigee/Apogee233/1615 kmV5Z5A#R*Inclination59.4U55A#R(Period103.5 minhZ55M#j6" &9+SLaunch vehicleFB 1&5=5# 55r5'  End of lifeU=55A#R(Decay6 Oct 1982$r55" B5-51mlkӂk-555Dong Fang Hong 11R558 @6⥹c%" Dong Fang Hong 117-55# (Also called SJ 3B1 55'  Generalg 5N5G#^@") Designation12845 / 81093D\55A#R6Launch date19 Sep 1981lN55M#j>"N ,6"Country of originChina^5t5G#^."H̀Mission(Shijian)_55A#R<"Perigee/Apogee232/1608 kmVt5)5A#R*Inclination59.4U5~5A#R(Period103.4 minh)55M#j6" &9+SLaunch vehicleFB 1&~5 5# 55A5'  End of lifeV 55A#R*Decay17 Aug 1982$A55" B551k%l5O56Dong Fang Hong 12R5O58 @6⥹c%" Dong Fang Hong 12955# ,Also called FSW 0-41 O55'  Generalg 5 5G#^@") Designation13521 / 82090A[5{5A#R4Launch date9 Sep 1982l 55M#j>"N ,6"Country of originChinaq${5X5M#jH"H̀郉MissionRemote sensing (FSW)^55A#R:"Perigee/Apogee172/392 kmTX5 5A#R&Inclination63T5^5A#R&Period90.2 minq$ 55M#jH" &9+SLaunch vehicleLong March 2C&^5 6# 5 6555A6'  End of lifeV 66A#R*Decay21 Sep 1982$A66" B661ӂknl6O66Dong Fang Hong 13R6O68 @6⥹c%" Dong Fang Hong 13966# ,Also called FSW 0-51 O66'  Generalg 6 6G#^@") Designation14288 / 83086A\6|6A#R6Launch date19 Aug 1983l 66M#j>"N ,6"Country of originChinaq$|6Y6M#jH"H̀郉MissionRemote sensing (FSW)^66A#R:"Perigee/Apogee170/493 kmVY6 6A#R*Inclination63.3T6a6A#R&Period91.2 minq$ 66M#jH" &9+SLaunch vehicleLong March 2C&a66# 56-6'  End of lifeU66A#R(Decay3 Sep 1983$-66" B661o%l l6:6x 6Dong Fang Hong 14R6:68 @6⥹c%" Dong Fang Hong 1496s6# ,Also called STTW T11 :66'  Generalg s6 6G#^@") Designation14670 / 84008A\6g6A#R6Launch date29 Jan 1984l 66M#j>"N ,6"Country of originChina[g6.6G#^("H̀Mission(STTW)_66A#R<"Perigee/Apogee484/6446 kmV.66A#R*Inclination36.1S66 6A#R$Period162 minp#6 6M#jF" &9+SLaunch vehicleLong March 3&6 6 6# 5 6 6'  End of life_ 6` 6A#R<"Out of service29 Jan 1984n- 6 6A#RZCauseLauncher 3rd stage failed to ignite&` 6 6# 8 6, 6' "(Technical dataL 6x 60 08hSpecificationsC-bandB, 6 61hnll 6 6X@6Dong Fang Hong 15Rx 6 68 @6⥹c%" Dong Fang Hong 159 6E 6# ,Also called STTW T21 6v 6'  Generalg E 6 6G#^@") Designation14899 / 84035A[v 68 6A#R4Launch date8 Apr 1984l 6 6M#j>"N ,6"Country of originChinav)8 66M#jR"H̀‰MissionTelecommunications (STTW)Y 6s6A#R0,Geostationary orbitp#66M#jF" &9+SLaunch vehicleLong March 3&s6 6# 56>6'  End of lifeW 66A#R,"Out of serviceyes&>66# 86 @6' "(Technical data6 @6x 6L6X@60 08hSpecificationsC-bandB @6@61 lfl@6@6DE6Dong Fang Hong 16RX@6@68 @6⥹c%" Dong Fang Hong 169@6%A6# ,Also called FSW 0-61 @6VA6'  Generalg %A6A6G#^@") Designation15279 / 84098A\VA6B6A#R6Launch date12 Sep 1984lA6B6M#j>"N ,6"Country of originChinaq$B6B6M#jH"H̀郉MissionRemote sensing (FSW)^B6TC6A#R:"Perigee/Apogee172/398 kmVB6C6A#R*Inclination67.9TTC6C6A#R&Period90.2 minq$C6oD6M#jH" &9+SLaunch vehicleLong March 2C&C6D6# 5oD6D6'  End of lifeVD6 E6A#R*Decay29 Sep 1984$D6DE6" B E6E61llE6E6-J6Dong Fang Hong 17RDE6E68 @6⥹c%" Dong Fang Hong 179E6F6# ,Also called FSW 0-71 E6BF6'  Generalg F6F6G#^@") Designation16177 / 85096A\BF6G6A#R6Launch date21 Oct 1985lF6qG6M#j>"N ,6"Country of originChinaq$G6G6M#jH"H̀郉MissionRemote sensing (FSW)^qG6@H6A#R:"Perigee/Apogee171/393 kmTG6H6A#R&Inclination63T@H6H6A#R&Period90.2 minq$H6YI6M#jH" &9+SLaunch vehicleLong March 2C&H6I6# 5YI6I6'  End of lifeUI6 J6A#R(Decay7 Nov 1985$I6-J6" B J6oJ61mflloJ6J6N6Dong Fang Hong 18R-J6J68 @6⥹c%" Dong Fang Hong 188oJ6J6# *Also called STTW 11 J6*K6'  Generalg J6K6G#^@") Designation16526 / 86010A[*K6K6A#R4Launch date1 Feb 1986lK6XL6M#j>"N ,6"Country of originChinav)K6L6M#jR"H̀‰MissionTelecommunications (STTW)^XL6,M6A#R:,Geostationary orbit103Ep#L6M6M#jF" &9+SLaunch vehicleLong March 3&,M6M6# 5M6M6'  End of life\M6SN6A#R6"Out of serviceApr 1995&M6yN6# 8SN6N6' "(Technical dataLyN6N60 08hSpecificationsC-bandBN6?O61l m?O6O66Dong Fang Hong 19RN6O68 @6⥹c%" Dong Fang Hong 199?O6O6# ,Also called FSW 0-81 O6 6'  GeneralO6 6N6g O6s6G#^@") Designation17001 / 86076A[ 6΀6A#R4Launch date6 Oct 1986ls6:6M#j>"N ,6"Country of originChinaq$΀66M#jH"H̀郉MissionRemote sensing (FSW)^:6 6A#R:"Perigee/Apogee169/337 kmT6]6A#R&Inclination57T 66A#R&Period89.6 minq$]6"6M#jH" &9+SLaunch vehicleLong March 2C&6H6# 5"6}6'  End of lifeVH6Ӄ6A#R*Decay23 Oct 1986$}66" BӃ6961lSm9666Dong Fang Hong 20R668 @6⥹c%" Dong Fang Hong 20996Ą6# ,Also called FSW 0-91 66'  Generalg Ą6\6G#^@") Designation18306 / 87067A[66A#R4Launch date5 Aug 1987l\6#6M#j>"N ,6"Country of originChinaq$66M#jH"H̀郉MissionRemote sensing (FSW)^#66A#R:"Perigee/Apogee169/366 kmT6F6A#R&Inclination63T66A#R&Period89.9 minq$F6 6M#jH" &9+SLaunch vehicleLong March 2C&616# 5 6f6'  End of lifeV166A#R*Decay23 Aug 1987$f66" B6"61 mm"6t6ȍ6Dong Fang Hong 21R6t68 @6⥹c%" Dong Fang Hong 219"66# ,Also called FSW 1-11 t6މ6'  Generalg 6E6G#^@") Designation18341 / 87075A[މ66A#R4Launch date8 Sep 1987lE6 6M#j>"N ,6"Country of originChinaq$6}6M#jH"H̀郉MissionRemote sensing (FSW)^ 6ۋ6A#R:"Perigee/Apogee181/222 kmT}6/6A#R&Inclination63Tۋ66A#R&Period88.5 minq$/66M#jH" &9+SLaunch vehicleLong March 2C&66# 56O6'  End of lifeU66A#R(Decay4 Oct 1987$O6ȍ6" B6 61Sm܀m 6X6 6Dong Fang Hong 22Nȍ6X65 :4⥹c%" Dong Fang Hong 22F# 66# FAlso called STTW 2 or Chinasat 11 X6ώ6'  Generalg 666G#^@") Designation18922 / 88014A[ώ66A#R4Launch date7 Mar 1988l66 6M#j>"N ,6"Country of originChina6 6ȍ6o"6{6M#jD"H̀‰MissionTelecommunicationsi( 66A#RP,Geostationary orbit87.5E, inclinedp#{6T6M#jF" &9+SLaunch vehicleLong March 3&6z6# 5T66'  End of life\z6 6A#R6"Out of serviceDec 1997T6_6A#R&Causedeorbited& 66# 8_66' "(Technical dataL6 60 08Y "N ,6"Country of originChinaq$66M#jH"H̀郉MissionRemote sensing (FSW)^566A#R:"Perigee/Apogee204/311 kmT6X6A#R&Inclination63T66A#R&Period89.7 minq$X66M#jH" &9+SLaunch vehicleLong March 2C&6C6# 56x6'  End of lifeVC66A#R*Decay13 Aug 1988$x66" B6461܀mn466 7Dong Fang Hong 24R668 @6⥹c%" Dong Fang Hong 24V3466# fAlso called Feng Yun 1-1, means "wind and cloud"1 6 6'  Generalg 6t6G#^@") Designation19467 / 88080Ag& 66A#RLLaunch date6 Sep 1988 at 20:30 UTlt6G6M#j>"N ,6"Country of originChinah66M#j6"H̀l/MissionMeteorology^G6 6A#R:"Perigee/Apogee832/937 kmV6c6A#R*Inclination99.2U 66A#R(Period102.7 minp#c6(6M#jF" &9+SLaunch vehicleLong March 466%  Mission: weather forcasting and environment monitoring; cloud, ice, snow and flood monitoring; sea color and surface temperature.5(66'  End of life_6f6A#R<CauseFailed after 39 days&66# 8f66' "(Technical data5 66) "_jPayload8616' " Specificationsn-66A#RZ&Prime contractorState Met AdministrationZ166A#R2"Mass at launch750 kgY6R6A#R0 Stabilization3 axis]66A#R8$Design lifetime6 months?R6 7$ 6Transmits on 137.8 MHz.6 76B6N71#mBnN77A7Dong Fang Hong 25R 778 @6⥹c%" Dong Fang Hong 25F#N77# FAlso called STTW 3 or Chinasat 21 77'  Generalg 7~7G#^@") Designation19710 / 88111A\77A#R6Launch date22 Dec 1988l~7F7M#j>"N ,6"Country of originChinao"77M#jD"H̀‰MissionTelecommunicationsr+F7'7G#^V"/ۀ0Geostationary orbit110.5E, inclinedp#77M#jF" &9+SLaunch vehicleLong March 3&'77# 877' "(Technical dataL7A70 08Y "N ,6"Country of originChinao"77M#jD"H̀‰MissionTelecommunicationso(z7X7G#^P"/ۀ0Geostationary orbit98E, inclinedp#77M#jF" &9+SLaunch vehicleLong March 3&X77# 87&7' "(Technical dataL7r70 08Y "N ,6"Country of originChinahO 7# 7M#j6"H̀l/MissionMeteorology^ 7 7A#R:"Perigee/Apogee875/897 kmV# 7 7A#R*Inclination98.8U 7, 7A#R(Period102.7 minp# 7 7M#jF" &9+SLaunch vehicleLong March 4, 7F 7%  Mission: weather forcasting and environment monitoring; cloud, ice, snow and flood monitoring; sea color and surface temperature.8 7~ 7' "(Technical data5 F 7 7) "_jPayload8~ 7 7' " Specificationsn- 7Y7A#RZ&Prime contractorState Met AdministrationZ 77A#R2"Mass at launch750 kgYY7 7A#R0 Stabilization3 axis[7g7A#R4$Design lifetime1 yearpK 77% APT-Downlink is approximately 36kHz wide FM-modulated, APT-FAX format.y8g7\@7A#Rp7\@7r7*APT downlink freq.137.800MHz (currently not active)t37@7A#Rf,HRPT downlink freq.? (around 1700MHz?, active)S\@7#A7A#R$Beacon freq.?$@7GA7" B#A7A71nnA7A7BF7Dong Fang Hong 31RGA7A78 @6⥹c%" Dong Fang Hong 31>A7B7# 6Also called Atmosphere 11 A7JB7'  Generalg B7B7G#^@") Designation20789 / 90081B[JB7 C7A#R4Launch date3 Sep 1990lB7xC7M#j>"N ,6"Country of originChina~1 C7C7M#jb"H߲̀-MissionScientific: high atmosphere study^xC7TD7A#R:"Perigee/Apogee789/811 kmTC7D7A#R&Inclination99UTD7D7A#R(Period100.9 minp#D7mE7M#jF" &9+SLaunch vehicleLong March 4&D7E7# 5mE7E7'  End of lifeVE7F7A#R*Decay11 Mar 1991$E7BF7" BF7F71GnnF7F7:K7Dong Fang Hong 32RBF7F78 @6⥹c%" Dong Fang Hong 32>F7G7# 6Also called Atmosphere 21 F7EG7'  Generalg G7G7G#^@") Designation20790 / 90081C[EG7H7A#R4Launch date3 Sep 1990lG7sH7M#j>"N ,6"Country of originChina~1H7H7M#jb"H߲̀-MissionScientific: high atmosphere study^sH7OI7A#R:"Perigee/Apogee596/629 kmTH7I7A#R&Inclination99ROI7I7A#R"Period97 minp#I7eJ7M#jF" &9+SLaunch vehicleLong March 4&I7J7# 5eJ7J7'  End of lifeVJ7K7A#R*Decay24 Jul 1991$J7:K7" BK7|K71no|K7K707Dong Fang Hong 33R:K7K78 @6⥹c%" Dong Fang Hong 339|K7L7# ,Also called FSW 1-31 K78L7'  Generalg L7L7G#^@") Designation20838 / 90089A[8L7L7A#R4Launch date5 Oct 1990lL7fM7M#j>"N ,6"Country of originChinaq$L7M7M#jH"H̀郉MissionRemote sensing (FSW)^fM75N7A#R:"Perigee/Apogee209/312 kmTM7N7A#R&Inclination57T5N7N7A#R&Period89.7 minq$N7NO7M#jH" &9+SLaunch vehicleLong March 2C&N7tO7# 5NO7O7'  End of lifeVtO7 7A#R*Decay23 Oct 1990O7 7:K7$O707" B 7r71nor7Ā7m7Dong Fang Hong 34R07Ā78 @6⥹c%" Dong Fang Hong 34F#r7 7# FAlso called STTW 5 or Chinasat 41 Ā7;7'  Generalg 77G#^@") Designation21833 / 91088A\;77A#R6Launch date28 Dec 1991l7j7M#j>"N ,6"Country of originChinao"7ق7M#jD"H̀‰MissionTelecommunicationsdj7=7G#^:"/ۀ0Geostationary orbitn/ap#ق77M#jF" &9+SLaunch vehicleLong March 3&=7Ӄ7# 577'  End of life_Ӄ7g7A#R<"Out of service28 Dec 1991\7Ä7A#R6CauseDid not reach GEO&g77# 8Ä7!7' "(Technical dataL7m70 08Y "N ,6"Country of originChinas&-7 7M#jL"H̀郉MissionRemote sensing (FSW 2)^7j7A#R:"Perigee/Apogee171/332 kmV 77A#R*Inclination63.1Tj77A#R&Period89.5 minq$77M#jH" &9+SLaunch vehicleLong March 2D&77# 577'  End of lifeU757A#R(Decay1 Sep 1992$7Y7" B5771oo77B7Dong Fang Hong 36RY778 @6⥹c%" Dong Fang Hong 3697&7# ,Also called FSW 1-41 7W7'  Generalg &77G#^@") Designation22162 / 92064B[W77A#R4Launch date6 Oct 1992l77M#j>"N ,6"Country of originChinaq$77M#jH"H̀郉MissionRemote sensing (FSW)^7T7A#R:"Perigee/Apogee213/309 kmT77A#R&Inclination63TT77A#R&Period89.7 minq$7m7M#jH" &9+SLaunch vehicleLong March 2C&77# 5m7Ȏ7'  End of lifeV77A#R*Decay31 Oct 1992$Ȏ7B7" B771 oo7֏77Dong Fang Hong 37RB7֏78 @6⥹c%" Dong Fang Hong 37H%7*7# JAlso c֏7*7B7alled Jianbing 93 or FSW 1-51 ֏7[7'  General{4*77G#^h") Designation22859 / 93063A (or 22870 / 93063H)g&[7=7A#RLLaunch date8 Oct 1993 at 08:00 UTl77M#j>"N ,6"Country of originChinaq$=77M#jH"H̀郉MissionRemote sensing (FSW)_7y7A#R<"Perigee/Apogee177/2629 kmV77A#R*Inclination56.5Uy7$7A#R(Period113.9 minq$77M#jH" &9+SLaunch vehicleLong March 2CtM$7 7' Contained a Mao's medallion of 28 g made of 44 South-African diamants that should have been sold by auction at its return on earth by Zhonyu company.The reentry vehicle fired its deorbit motor successfully but, alas, in the wrong direction; the capsule ended up in a 187 x 3016 km orbit, starting from a low 196 x 251 km orbit.57>7'  End of lifeV 77A#R*Decay12 Mar 1996$>77" B771^o2o7L7y7Dong Fang Hong 38R7L78 @6⥹c%" Dong Fang Hong 38W477# hAlso called Shijian 4 or SJ 4. Means "Practice 4"1 L77'  Generalg 7;7G#^@") Designation22996 / 94010A[77A#R4Launch date8 Feb 1994l;77M#j>"N ,6"Country of originChinav/7x7G#^^"H̀MissionScientific & Technology (Shijian)`77A#R>"Perigee/Apogee221/34459 kmWx7/7A#R,Inclination28.41V77A#R*Period605.89 minq$/77M#jH" &9+SLaunch vehicleLong March 3A_7y7$ It carried six instruments for measuring particle fluxes and spacecraft electric potential.B771'oo7 77Dong Fang Hong 39Ry7 78 @6⥹c%" Dong Fang Hong 3997F7# ,Also called DFH 3-01 7w7'  Generalg F77G#^@") Designation23009 / 94010B[w797A#R4Launch date8 Feb 1994l77M#j>"N ,6"Country of originChinah!97 7G#^B"H̀MissionSimulated satellite`7m7A#R>"Perigee/Apogee211/32578 kmW 77A#R,Inclination27.49Vm77A#R*Period570.03 minq$77M#jH" &9+SLaunch vehicleLong March 3AxN77* $'v&Mockup of the new DFH 3 telecommunication series (see Dong Fang Hong 41)B7E712oIpE77\8Dong Fang Hong 40R778 @6⥹c%" Dong Fang Hong 40M*E7 8# TAlso called FSW 2-2, Fanhui Shi Weixing7 871 7=8'  Generalg 88G#^@") Designation23145 / 94037Ag&=8 8A#RLLaunch date3 Jul 1994 at 08:00 UTl8w8M#j>"N ,6"Country of originChinaq$ 88M#jH"H̀郉MissionRemote sensing (FSW)^w8F8A#R:"Perigee/Apogee176/355 kmV88A#R*Inclination62.9TF88A#R&Period89.6 minq$8a8M#jH" &9+SLaunch vehicleLong March 2D&88# 5a88'  End of life|:888B#TtDecaypayload: 15 Jul 1994service module: 13 Sep 1994$8\8" B8881QoCp88 8Dong Fang Hong 41R\888 @6⥹c%" Dong Fang Hong 4198)8# ,Also called DFH 3-11 8Z8'  Generalg )88G#^@") Designation23415 / 94080Ah'Z8)8A#RNLaunch date29 Nov 1994 at 17:02 UTl88M#j>"N ,6"Country of originChinao")88M#jD"H̀‰MissionTelecommunicationsw68{8A#Rl,Geostationary orbitshould have been in 125E slotq$88M#jH" &9+SLaunch vehicleLong March 3Ao{88$ First satellite of the DFH 3 generation, built with a 20% German participation (Daimler Benz Aerospace/MBB)588'  End of life^8 8A#R:"Out of service9 Jan 1995T8f 8A#R&Causefuel leak& 8 8# 8f 8 8' "(Technical dataL 8 80 08 8 u(SpecificationsC-bandB 8R 81 Ipp R 8 8tF8Dong Fang Hong 42R 8 88 @6⥹c%" Dong Fang Hong 42J'R 8 8# NAlso called Chinasat 7 (Zhongxing 7)1 8 8'  Generalg 8 8G#^@") Designation24282 / 96048A\ 8 8A#R6Launch date18 Aug 1996l 8N 8M#j>"N ,6"Country of originChinao" 8 8M#jD"H̀‰MissionTelecommunications\N 8 8A#R6,Geostationary orbitn/at' 8 8M#jN" &9+SLaunch vehicleLong March 3 #40  88. *ZIzInsured for $128 million. Should have replaced Spacenet 1 (Chinasat 5)to be operated by Chinasat (China Satellite Telecommunications) a company under the control of the Ministry of Post and Telecommunications (MPT)5 88'  End of life_8.8A#R<"Out of service18 Aug 1996b88A#RCauseThe satellite was not delivered in the correct transfer orbit (20 km x 17227 km x 27.2)&.8 @8# 8 @8 888D@8' "(OTechnical data8 @8|@8' " Specifications\D@8@8A#R6&Prime contractorHughesT|@8,A8A#R&PlatformHS-376T@8A8A#R&"Mass at launchS,A8A8A#R$ Mass in orbitOA8"B8A#RDimensionQA8sB8A#R Solar arrayS"B8B8A#R$ StabilizationN sB8C8A#RDC power]B8qC8A#R8$Design lifetime10 yearsS/C8C8$ ^The apogee motor onboard is a solid Star-300 qC8C8'  C-bandYC8MD8A#R0(Main transponders24YC8D8A#R0,Backup transpondersK MD8D8A#RPowerOD8@E8A#RBandwidthp/D8E8A#R^CoverageChina and the South China Sea areaN @E8E8A#REIRP maxRE8PF8A#R"Polarization$E8tF8" BPF8F81Cp p F8G8K8Dong Fang Hong 43RtF8G88 @6⥹c%" Dong Fang Hong 43M*F8UG8# TAlso called FSW 2-3, Fanhui Shi Weixing1 G8G8'  Generalg UG8G8G#^@") Designation24634 / 96059A\G8IH8A#R6Launch date20 Oct 1996lG8H8M#j>"N ,6"Country of originChinas&IH8(I8M#jL"H̀郉MissionRemote sensing (FSW-2)^H8I8A#R:"Perigee/Apogee172/335 kmV(I8I8A#R*Inclination63.0TI80J8A#R&Period89.5 minq$I8J8M#jH" &9+SLaunch vehicleLong March 2D&0J8J8# 5J8J8'  End of lifeb!J8^K8A#RBDecay4 Nov 1996 & 3 Dec 1996$J8K8" B^K8K81(pq K8L88Dong Fang Hong 44RK8L88 @6⥹c%" Dong Fang Hong 44H%K8^L8# JAlso called Chinasat 6 and DFH 3-21 L8L8'  Generalg ^L8L8G#^@") Designation24798 / 97021A\L8RM8A#R6Launch date11 May 1997lL8M8M#j>"N ,6"Country of originChinao"RM8-N8M#jD"H̀‰MissionTelecommunications^M8N8A#R:,Geostationary orbit125Eu(-N8O8M#jP" &9+SLaunch vehicleLong March 3A #42h<N8hO8, (x'v&Insured for $100 millionTo replace Dong Fang Hong 418O8O8' "(Technical datam;hO882 4v 8 u(SpecificationsC-bandBeacons: 3.7098 & O88K84.19202 GHzBO8[81w pcq [888Dong Fang Hong 45R888 @6⥹c%" Dong Fang Hong 45N+[88# VAlso called Feng Yun 2B or Feng Yun 2-1R1 8,8'  Generalg 88G#^@") Designation24834 / 97029A\,88A#R6Launch date10 Jun 1997l8[8M#j>"N ,6"Country of originChinah8Â8M#j6"H̀DVMissionMeteorologyf[8)8G#^>"/ۀ0Geostationary orbit105Ep#Â88M#jF" &9+SLaunch vehicleLong March 3{T)88' First Chinese GEO meteorology satellite. The 1R and B denomination stands for the replacement of the original satellite destroyed before even being installed on the Long March and launched, in 1994.The satellite is equipped with a scanning radiometer, a cloud coverage information system and a data collection and transmission system.88L8' "(OTechnical data888' " SpecificationsEL8 8A#R&Prime contractorShanghai Aerospace Technology Research InstituteN 8X8A#RPlatform[ 88A#R4"Mass at launch1380 kgSX88A#R$ Mass in orbitO8U8A#RDimensionQ88A#R Solar arrayb!U88A#RB Stabilizationspin-stabilizedN 8V8A#RDC power\88A#R6$Design lifetime3 years[1V8 8* $bTThe satellite is said to be a copy of GMS 5]08j8- *`  VISSR (Visible and IR Spin Scan Radiometer)P 88C#V4Wavebands0.55-1.05 m (visible)6.2-7.6 m (water vapour)10.5-12.5 m (IR)n,j8k8B#TX4Resolutionvisible: 1.25 kmIR& WV: 5 kmb!8͊8A#RB42Image repeat frequency1 heur&k88# B͊8581* q 588r8Dong Fang Hong 46R888 @6⥹c%" Dong Fang Hong 46<58Ë8# 2Also called Chinasat 81 88'  GeneralYË8M8G#^$") Designatione$88A#RHLaunch dateplanned in late 1998lM88M#j>"N ,6"Country of originChinao"88M#jD"H̀‰MissionTelecommunications`88A#R>,Geostationary orbit115.5Eq$8^8M#jH" &9+SLaunch vehicleLong March 3BX88A#R.Launch siteXichang^88& uContract calls for in-orbit delivery, worth $200 millionfor China Telecommunications Broadcast Satellite Corporation, a division of the Ministry of Post and Telecommunications (MPT)88Ώ8' "(Technical data888' " SpecificatΏ888ionsi(Ώ8{8A#RP&Prime contractorSpace Systems/LoralU88A#R(PlatformFS-1300T{8$8A#R&"Mass at launchS8w8A#R$ Mass in orbitO$88A#RDimensionQw88A#R Solar arrayY8p8A#R0 Stabilization3-axisU88A#R(DC power11000 W]p8"8A#R8$Design lifetime15 years&8H8# 0 "8x8'  C-bandYH88A#R0(Main transponders36Yx8*8A#R0,Backup transpondersO8y8A#RPower37 WO*88A#RBandwidthN y88A#RCoverageN 8d8A#REIRP maxR88A#R"Polarization&d88# 1 8 8'  Ku-bandY8f8A#R0(Main transponders16Y 88A#R0,Backup transpondersPf88A#RPower125 WO8^8A#RBandwidthN 88A#RCoverageN ^88A#REIRP maxR8L8A#R"Polarization&8r8# 1L881W888T+r88) "VȠ$To view this page you need to register&88# 58R81Gi@rR889Dove= 882 4"  Dove\R88/ . 䵟Short for Digital Orbiting Voice Encoder. Also called Microsat 2 or DO-17 or Oscar 171 8K8'  Generalg 88G#^@") Designation20440 / 90005E\K88A#R6Launch date22 Jan 1990m 8{8M#j@"N ,7Country of originBrazilo"88M#jD"H̀㓉MissionTelecommunications^{8H8A#R:"Perigee/Apogee781/797 kmV88A#R*Inclination98.6UH88A#R(Period100.6 minn!8a8M#jB" &6D+Launch vehicleAriane V35X88A#R."Mass at launch9 kgH$a88$ HBased on a Amsat-NA Microsat bus<8=8' *O External resources]688' lhttp://www.amsat.org/amsat/sats/nk6k/msatmain.html8=88' "(Technical datai8|8A#RDownlink1200 bps Bell 202 AX.25, same as used in terrestrial Packet Radio, Synthesized Voice Beacon.Z88A#R2145.825, 145.825 MHz&|8 9# 8 98_8k9A#R< S-Band beacon2401.221 MHzF" 99$ DPassive magnetic stabilization> k991qv9999Program: DSCSJ9995 :,G" Program: DSCS9"9)  Defense Satellite Communication System, also called USGCSSAmerican geostationary satellite program operated by the US Army Space Command. Designed to provide military telecommunications.1 99S9' O Contact"99) Operator: US Army Space CommandCommand and control:50th Space Wing300 O'Malley Ave, Suite 24, Falcon AFB, CO 80912-3024, USA<S9;9' *O External resources&9a9D Vhttp://www.spacecom.af.mil/usspace/dscs.htmhttp://www.fafb.af.mil/dscs/http://armyspace.com/SATCON.htmhttp://www.fas.org/spp/military/program/com/dscs_2.htmhttp://www.fas.org/spp/military/program/com/dscs_3.htm8;99' "(OTechnical data:a99' &O First generation79 9) "%kSee IDSCP;9E9' ( Second generationh= 99+ &zBP}SpecificationsSatellites were launched by pairs to GEO:E99' & Third generationm995 8zcSpecificationsPayloadThose satellites also carry an AFSATCOM package for the dissemination of Emergency Action Message and Single Integrated Operations Plan directives. It's purpose is to send orders to the nuclear capable forces.Fleet composed of 14 satellites. USAF asked LM [in mid-1995] for a cost estimate on upgrades to the remaining ground-spare DSCS-3s to extend their lives somewhat: improved thrusters, better solar cells, more efficient amplifiers in the high-power channels. The DSCS-3 production line shut down several years ago, and the USAF wants to postpone the start of development on DSCS-4.1991U99&9;99) "$ąProgram: DSCS(9 9d#P"y,dMz,dM6{,dMDSCS 2-01DSCS 2-02DSCS 2-03*9 9j#T(|,dM"},dM:~,dMDSCS 2-04DSCS 2-05DSCS 2-06( 9 9d#P",dM,dM6*dMDSCS 2-07DSCS 2-08DSCS 2-11( 9- 9d#P"*dM*dM6*dMDSCS 2-12DSCS 2-13DSCS 2-14 9 9g#@(*dM(*dM<DSCS 2-15DSCS 2-16-- 9T 9s#Z( ceM( ceM(<ceMDSCS 3-01DSCS 3-02DSCS 3-03- 9 9s#Z(ceM(ceM(<ceMDSCS 3-04DSCS 3-05DSCS 3-06-T 9 9s#Z(ceM(ceM(<ceMDSCS 3-07DSCS 3-08DSCS 3-09n 99[#&(aeM"DSCS 3-10$ 9&9" 19W91W9+B9=&99# 4DSCS 2's specificationsYW99A#R00&Prime contractorTRWN 9;9A#R0PlatformT99A#R&0"Mass at launchY;9 @9A#R00 Mass in orbit612 kg9 @9&9p/9|@9A#R^0Dimensions2.7 m (diameter) x 1.82 m (high)R @9@9A#R"0Solar arraysb!|@90A9A#RB0 Stabilizationspin stabilizedd"@9A9B#TD0DC powerBOL: 535 WEOL: 358 W\0A9A9A#R60$Design lifetime5 years;A9+B9$ .Had 2 dish antennas1A9\B91\B9IG9=+B9B9# 4DSCS 3's specifications}<\B9C9A#Rx0&Prime contractorLockheed martin (former GE Astro Space)N B9dC9A#R0Platform[C9C9A#R40"Mass at launch2615 kgZdC9D9A#R20 Mass in orbit1170 kgt3C9D9A#Rf0Dimensions2.07 m x 1.93 m x 1.96 m (L x W x D)XD9D9A#R.0Solar arrays11.4 mYD9>E9A#R00 Stabilization3-axis>D9E9C#V|0DC powerBOL: 1240 WEOL: 837 Wthree 35 AH NiCd batteries]>E9F9A#R80$Design lifetime10 years\E9xF9A#R60TelemetryS- and X-band_F9F9A#R<0Beacon7600.0 & 7604.7 MHzrNxF9IG9$ Features fixed (multiple-beam) antennas and a steerable high power antenna1F9zG91 zG9VM96IG9G9# &DSCS 3's payload0 zG9G9'  X-bandXG98H9A#R.(Main transponders6l+G9H9A#RVBackuptwo 40 W and two 10 W amplifiersB8H9(I9B#TPowerchannels 1 & 2: 40 W (TWTA)channels 3 to 6: 10 W (SSPA)\H9I9C#V0Coverage and EIRP max2 Global beams: 29 dBW2 Spot beams: 34 dBWGimballed dish: 44 dBW&(I9I9# K$I98J9' H Transponder frequency chart (GHz)+I9J9a#V  < ChannelBandwidth (MHz)Frequency] 8J9!K9R#t150?] J9~K9R#t275?] !K9K9R#t385?] ~K98L9R#t485?] K9L9R#t560?] 8L9L9R#t650?d@L9VM9$ Frequencies are probably in 250 MHz, S-band and X-band range: L9M91!msM9M99DSCS 2-01FVM9M95 :$G" DSCS 2-011 M9N9'  Generalg M9nN9G#^@") Designation05587 / 71095A[N9N9A#R4Launch date3 Nov 1971t'nN9=O9M#jN"N ,㹌לCountry of originUnited Statesy,N9O9M#jX"H̀‰MissionMilitary: Telecommunicationsb!=O9$9A#RB,GeostatiO9$9VM9onary orbitsee belowo"O99M#jD" &^]Launch vehicleTitan 3 #56&$99# 599'  End of lifeW9E9A#R,"Out of serviceyes89}9' "(Technical data<E99) "&BP}Specifications: }991^rs9999DSCS 2-02F9995 :$G" DSCS 2-021 9j9'  Generalg 99т9G#^@") Designation05588 / 71095B[j9,9A#R4Launch date3 Nov 1971t'т99M#jN"N ,㹌לCountry of originUnited Statesy,,99M#jX"H̀‰MissionMilitary: TelecommunicationsY9r9A#R0,Geostationary orbito"99M#jD" &^]Launch vehicleTitan 3 #56&r99# 59<9'  End of lifeW99A#R,"Out of serviceyes8<9˅9' "(Technical data<99) "&BP}Specifications: ˅9A91mssA99V9DSCS 2-03F995 :$G" DSCS 2-031 A99'  Generalg 99G#^@") Designation06973 / 73100A\9{9A#R6Launch date13 Dec 1973t'99M#jN"N ,㹌לCountry of originUnited Statesy,{9h9M#jX"H̀‰MissionMilitary: TelecommunicationsY99A#R0,Geostationary orbito"h909M#jD" &^]Launch vehicleTitan 3 #71&9V9# 5099'  End of lifeWV99A#R,"Out of serviceyes899' "(Technical data<9V9) "&BP}Specifications: 991ss9֊99DSCS 2-04FV9֊95 :$G" DSCS 2-041 99'  Generalg ֊9n9G#^@") Designation06974 / 73100B\9ʋ9A#R6Launch date13 Dec 1973t'n9>9M#jN"N ,㹌לCountry of originUnited Statesy,ʋ99M#jX"H̀‰MissionMilitary: TelecommunicationsY>99A#R0,Geostationary orbito"99M#jD" &^]Launch vehicleTitan 3 #71&99# 59ڍ9'  End of lifeW919A#R,"Out of serviceyes8ڍ9i9' "(Technical data<199) "&BP}Specifications: i9ߎ91s sߎ9%99DSCS 2-05F9%95 :$G" DSCS 2-051 ߎ9V9'  Generalg %99G#^@") Designation07807 / 75040A\V9%9A#R6L9%99aunch date20 May 1975t'99M#jN"N ,㹌לCountry of originUnited Statesy,%99M#jX"H̀‰MissionMilitary: TelecommunicationsY9k9A#R0,Geostationary orbito"99M#jD" &^]Launch vehicleTitan 3 #85&k99# 5959'  End of life_99A#R<"Out of service20 May 1975Y599A#R0CauseLaunch failureV9C9A#R*Decay26 May 197589{9' "(Technical data<C99) "&BP}Specifications: {991sqs9799DSCS 2-06F9795 :$G" DSCS 2-061 9h9'  Generalg 799G#^@") Designation07808 / 75040B\h9+9A#R6Launch date20 May 1975t'99M#jN"N ,㹌לCountry of originUnited Statesy,+99M#jX"H̀‰MissionMilitary: TelecommunicationsY9q9A#R0,Geostationary orbito"99M#jD" &^]Launch vehicleTitan 3 #85&q99# 59;9'  End of life_99A#R<"Out of service20 May 1975Y;99A#R0CauseLaunch failureV9I9A#R*Decay26 May 1975899' "(Technical data<I99) "&BP}Specifications: 991 ss9=9 9DSCS 2-07F9=95 :$G" DSCS 2-071 9n9'  Generalg =99G#^@") Designation10000 / 77034A\n919A#R6Launch date12 May 1977t'99M#jN"N ,㹌לCountry of originUnited Statesy,199M#jX"H̀‰MissionMilitary: TelecommunicationsY9w9A#R0,Geostationary orbitp#99M#jF" &^]Launch vehicleTitan 3 #103&w9 9# 59B9'  End of lifeW 99A#R,"Out of serviceyes8B99' "(Technical data<9 9) "&BP}Specifications: 9G91qsKtG99i:DSCS 2-08F 995 :$G" DSCS 2-081 G99'  Generalg 9%9G#^@") Designation10001 / 77034B\99A#R6Launch date12 May 1977t'%99M#jN"N ,㹌לCountry of originUnited Statesy,9n9M#jX"H̀‰MissionMilitary: TelecommunicationsY99A#R0,Geostationary orbitp#n9C:M#jF" 9C: 9&^]Launch vehicleTitan 3 #103&9i:# 5C::'  End of lifeWi::A#R,"Out of serviceyes8:-:' "(Technical data<:i:) "&BP}Specifications: -::1s{t:::DSCS 2-11Fi::5 :$G" DSCS 2-111 ::'  Generalg ::G#^@") Designation11144 / 78113A\::A#R6Launch date14 Dec 1978t':Q:M#jN"N ,㹌לCountry of originUnited Statesy,::M#jX"H̀‰MissionMilitary: TelecommunicationsYQ:#:A#R0,Geostationary orbitp#::M#jF" &^]Launch vehicleTitan 3 #114&#::# 5::'  End of lifeW:E:A#R,"Out of serviceyes8:}:' "(Technical data<E::) "&BP}Specifications: }::1Ktt:9: :DSCS 2-12F:9:5 :$G" DSCS 2-121 :j:'  Generalg 9::G#^@") Designation11145 / 78113B\j:-:A#R6Launch date14 Dec 1978t'::M#jN"N ,㹌לCountry of originUnited Statesy,-::M#jX"H̀‰MissionMilitary: TelecommunicationsY:s:A#R0,Geostationary orbitp#::M#jF" &^]Launch vehicleTitan 3 #114&s: :# 5:> :'  End of lifeW : :A#R,"Out of serviceyes8> : :' "(Technical data< : :) "&BP}Specifications: :C :1;{ttC : ::DSCS 2-13F : :5 :$G" DSCS 2-13:C : :# .Also called OPS 94431 : :'  Generalg :[ :G#^@") Designation11621 / 79098A\ : :A#R6Launch date21 Nov 1979t'[ :+ :M#jN"N ,㹌לCountry of originUnited Statesy, : :M#jX"H̀‰MissionMilitary: TelecommunicationsY+ : :A#R0,Geostationary orbitp# :m :M#jF" &^]Launch vehicleTitan 3 #119& : :# 5m : :'  End of lifeW ::A#R,"Out of serviceyes8 :W:' "(Technical data<::) "&BP}Specifications: W::1ltt ::dC:DSCS 2-14F::5 :$G" DSCS 2-14::M:# .Also called OPS 94441 :~:'  Generalg M: @:G#^@") Designation11622 / 79098B~: @::\~:h@:A#R6Launch date21 Nov 1979t' @:@:M#jN"N ,㹌לCountry of originUnited Statesy,h@:UA:M#jX"H̀‰MissionMilitary: Telecommunicationsb!@:A:A#RB,Geostationary orbitsee belowp#UA:'B:M#jF" &^]Launch vehicleTitan 3 #119&A:MB:# 5'B:B:'  End of lifeWMB:B:A#R,"Out of serviceyes8B:C:' "(Technical dataS(B:dC:+ &PBP}SpecificationsDownlinks in X-band: C:C:1t:1huju'>:::DSCS 3-05F::5 :$G" DSCS 3-05D!>::# BAlso called USA 078 (code B14)1 ::'  Generalg :`:G#^@") Designation21873 / 92006A\::A#R6Launch date11 Feb 1992t'`:0:M#jN"N ,㹌לCountry of originUnited Statesy,::M#jX"H̀‰MissionMilitary: Telecommunicationsd0: :G#^:"/ۀ0Geostationary orbitn/ax+::M#jV" &yjLaunch vehicleAtlas Centaur + IABS :6:% First satellite of the 3B generation. This generation is equipped with reinforced plating to resist to the explosion of an atomic bomb. 8:n:' "(Technical dataM6::0 0:zcSpecificationsPayload: n::1uu(:;::DSCS 3-06F:;:5 :$G" DSCS 3-06D!::# BAlso called USA 082 (code B12)1 ;::'  Generalg ::G#^@") Designation22009 / 92037A[:r:A#R4Launch date2 Jul 1992t'::M#jN"N ,㹌לCountry of originUnited Statesy,r:_:M#jX"H̀‰MissionMilitary: Telecommunicationsd::G#^:"/ۀ0Geostationary orbitn/ax+_:;:M#jV" &yjLaunch vehicleAtlas Centaur + IABS&:a:# 8;::' "(Technical dataMa::0 0:zcSpecificationsPayload: : :1juu) :f::DSCS 3-07F:f:5 :$G" DSCS 3-07C ::# @Also called USA 093 (code B9)1 f::'  Generalg :A:G#^@") Designation22719 / 93046A\::A#R6Launch date19 Jul 1993t'A::M#jN"N ,㹌לCountry of originUnited Statesy,::M#jX"H̀‰MissionMilitary: Telecommunicationsd::G#^:"/ۀ0Geostationary orbitn/ax+:f:M#jV" &yjLaunch vehicleAtlas Centaur + IABS&::# 8f::' "(Technical dataM::0 0:zcSpecificationsPayload: :K:1udv*K::l;DSCS 3-08F::5 :$G" DSCS 3-08D!K::# BAlso called USA 097 (code B10)1 :;'  Gen:;:eralg :y;G#^@") Designation22916 / 93074A\;;A#R6Launch date28 Nov 1993t'y;I;M#jN"N ,㹌לCountry of originUnited Statesy,;;M#jX"H̀‰MissionMilitary: Telecommunications\I;;A#R6,Geostationary orbitn/ax+;;M#jV" &yjLaunch vehicleAtlas Centaur + IABS&;;# 5;;'  End of life_;P;A#R<"Out of service28 Nov 1993q0;;A#R`Causedidn't reach GEO, failure of the IABS?&P;;# 8;;' "(Technical dataM;l;0 0:zcSpecificationsPayload: ;;1uv+;;;DSCS 3-09Fl;;5 :$G" DSCS 3-09C ;/;# @Also called USA 113 (code B7)1 ;`;'  Generalg /;;G#^@") Designation23628 / 95038A\`;#;A#R6Launch date31 Jul 1995t';;M#jN"N ,㹌לCountry of originUnited Statesy,#;;M#jX"H̀‰MissionMilitary: Telecommunicationsd;t;G#^:"/ۀ0Geostationary orbitn/ax+;;M#jV" &yjLaunch vehicleAtlas Centaur + IABS&t;;# 8;J;' "(Technical dataM;;0 0:zcSpecificationsPayload: J;;1dv,; ; ;DSCS 3-10F; ;5 :$G" DSCS 3-10D!;[ ;# BAlso called USA 134 (code B13)1  ; ;'  Generalg [ ; ;G#^@") Designation25019 / 97065A\ ;O ;A#R6Launch date25 Oct 1997t' ; ;M#jN"N ,㹌לCountry of originUnited Statesy,O ;< ;M#jX"H̀‰MissionMilitary: Telecommunicationsd ; ;G#^:"/ۀ0Geostationary orbitn/a}0< ; ;M#j`" &yjLaunch vehicleAtlas Centaur #111 + IABS& ;C ;# 8 ;{ ;' "(Technical dataMC ; ;0 0:zcSpecificationsPayload= { ; ;1@rw- ;R ;"@;Program: DSPM ;R ;8 @,ܻc%" Program: DSP ;6;1 0g :uDefense Support ProgramMilitary geostationary satellite program for early warning and detection of nuclear explosions.The first generation of those satellites was IMEWS.1 R ;g;' O Contact6;;) Operator: 21St Space WingPeterson AFB, COCommand and Control: 50th Space Wing300 O'Malley Ave, Suite 24, Falcon AFB, CO 80912-3024, USA<g;Z;' *O External resources;"@;6 : http://www.fafb.af.mil/dsp/http://www.spacecom.af.mil/usspace/dsp.htmhttp://www.fas.org/spp/military/progZ;"@; ;ram/warning/dsp.htm1Z;S@;1.S@;A;X"@;A;] oS@cc鉂 c鉂 c鉂 c鉂 c鉂 c鉂Program: DSPDSP F12DSP 3-1DSP 3-2DSP 3-3DSP 3-4DSP 3-5DSP 3-61S@;9A;1K/9A;SE;2A;kA;# DSP 3 seriesY9A;A;A#R0&Prime contractorTRWN kA;B;A#RPlatformb!A;tB;A#RB"Mass at launcharound 2200 kgSB;B;A#R$ Mass in orbitt3tB;;C;A#RfDimension6.7 m diameter x 10 m long (deployed)QB;C;A#R Solar arrayb!;C;C;A#RB Stabilizationspin stabilizedTC;BD;A#R&DC power1485 WUC;D;A#R($Design lifetimeBD;SE;% /Probably downlinks in S- and X-band. Has a wide field infrared telescope to provide real-time warning of missile launches (6000 infrared detectors)8D;E;1.قv0E;E;H;DSP F12HSE;E;8 @"ܻc%" DSP F129E; F;# ,Also called USA 0071 E;=F;'  Generalg F;F;G#^@") Designation15453 / 84129A\=F;G;A#R6Launch date22 Dec 1984t'F;tG;M#jN"N ,㹌לCountry of originUnited Statesl%G;G;G#^J"H̀MissionMilitary: early warning\tG;"/ۀ0Geostationary orbit145EkfO;C;M#j<" O;C;L;&^]Launch vehicleTitan 4_O;;A#R<Launch siteCape Canaveral&C;Ȁ;# 8;;' "(Technical data<Ȁ;<;) "&TSpecifications8;t;1vjw3t;;=;DSP 3-3H<;;8 @"ܻc%" DSP 3-3D!t;;# BAlso called USA 065 or DSP F151 ;1;'  Generalg ;;G#^@") Designation20929 / 90095A\1;;A#R6Launch date13 Nov 1990t';h;M#jN"N ,㹌לCountry of originUnited Statesl%;ԃ;G#^J"H̀MissionMilitary: early warningdh;8;G#^:"/ۀ0Geostationary orbit4Ekԃ;;M#j<" &^]Launch vehicleTitan 4&8;Ʉ;# 8;;' "(Technical data<Ʉ;=;) "&TSpecifications8;u;1 Eww4u;;;DSP 3-4H=;;8 @"ܻc%" DSP 3-4D!u;;# BAlso called USA 075 or DSP F161 ;2;'  Generalg ;;G#^@") Designation21805 / 91080B\2;;A#R6Launch date24 Nov 1991t';i;M#jN"N ,㹌לCountry of originUnited Statesl%;Շ;G#^J"H̀MissionMilitary: early warningdi;9;G#^:"/ۀ0Geostationary orbit7WjՇ;;M#j:" &㦛Launch vehicleSTS 44[9;;A#R4"Mass at launch2350 kg:;8;$ ,Cost: $275 million8;p;' "(Technical data<8;;) "&TSpecifications8p;;1jww5;,;;DSP 3-5H;,;8 @"ܻc%" DSP 3-5D!;p;# BAlso called USA 107 or DSP F171 ,;;'  Generalg p;;G#^@") Designation23435 / 94084Ah';p;A#RNLaunch date22 Dec 1994 at 22:19 UTt';;M#jN"N ,㹌לCountry of originUnited Statesl%p;P;G#^J"H̀MissionMilitary: early warningf;;G#^>"/ۀ0Geostationary orbit103WkP;!;M#j<" &^]Launch vehicleTitan 4&;G;# 8!;;' "(Technical data<G;;) "&TSpecifications8;;1w6;;;;DSP 3-6H;;;8 @"ܻc%" DSP 3-6D!;;# BAlso called USA 130 or DSP F181 ;;;'  Generalg ;;G#^@") Designation24737 / 97008A\;s;A#R6Launch date24 Feb 1997t'; ;M#jN"N ,㹌לCountry of originUnited Statess; ;;l%s;x;G#^J"H̀MissionMilitary: early warninga ;;G#^4"/ۀ0Geostationary orbitlx;E;M#j>" &^]Launch vehicleTitan 4B:;;$ ,worth $200 million8E;;' "(Technical data<;;) "&TSpecifications; ;.;1 vw7.;i;?;Early Bird;;i;, ( " Early Bird1 .;;'  Generalg i;;G#^@") Designation25121 / 97085A\;];A#R6Launch date24 Dec 1997t';;M#jN"N ,㹌לCountry of originUnited Statesk];<;M#j<"H̀郉MissionRemote Sensingk*;;A#RT"Perigee/Apogee470 km, sun-synchronousV<;;A#R*Inclination97.3e$;b;A#RHPeriodrevisit time: 2 to 5 daysk;;M#j<" &aKLaunch vehicleStart 1Yb;&;A#R0Launch siteSvobodnyW*;};- (UIUS satellite operated by Earth Watch Inc. The cost of the system is approx. $200 million. Launch cost is said to be $7 millionFive days after launch the satellite went silent, with no communications. This was the consequence of an electrical problem. Insurers paid $29 million for the loss.<&;;' *O External resourcesE};;' <http://www.terraserver.com8;6;' "(OTechnical data8;n;' " Specificationsg&6;;A#RL0&Prime contractorCTA Space SystemsN n;#;A#R0PlatformZ;};A#R20"Mass at launch317 kgR#;;A#R"0Payload massO};;A#R0DimensionQ;o;A#R 0Solar arrayS;;A#R$0 StabilizationN o;;A#R0DC power\;l;A#R60$Design lifetime5 years;;& On-board data storage: 2 GByteGimbaled-mirror pointing system for 30 in-track and 28 side-to-side pointing capability=l;O;' , Panchromatic SensorY;;A#R00Wavebands445-650 nmWO;;A#R,0Swath width280 kml+;k;A#RV0Resolution3 m, image size: 3 km x 3 km&;;# >k;;' . Multispectral SensorC;U;C#V0WavebandsGreen: 490-600 nmRed: 615-670 nmNear IR: 790-875 nmW;;A#R,0Swath width280 kmo.U;;A#R\0Resolution15 m, image size: 15 km x 15 km$;?;" > ;};1 wx8};; <Program: ECCO>?;;, (&" Program: ECCOF}; <( =Equatorial Constellation COm; <?;municationsLEO telecommunication system to be operated by Constellation Communications, Inc. ECCO is a joint project of CCI (backed by Bell Atlantic, SpaceVest and Raytheon E-Systems) and Brazil's Telebras. The system was merged with the Brazilian ECO-8 project.The system will have 12 satellites in equatorial orbit to provide telephony services to the 100 countries located in the tropical area. Further sets are satellites are planned. OSC should manufacture and launch the first 12 satellites (in 2001).;<' Orbital will receive a contract, valued at approximately US$450 million, to serve as the space segment prime contractor for ECCO's initial equatorial satellite network, including both the construction and launch services for 12 low-orbit communications satellites. At the same time, Orbital will also become a major investor in the ECCO project, with the company providing up to US$150 million in equity capital and vendor financing.Matra Marconi Space is the prime contractor for the space segment of its Low Earth Orbit (LEO) satellite system. Contract at least worth $600 million. Ground-segment provider: Raytheon E-Systems, DallasP) <<' SA future set of 35 satellites is plannedConstellation Communications Inc. (CCI) is a Delaware company formed in 1991 with headquarters in Fairfax, Virginia/USA. In 1997, CCI established CCI International N.V. in the Netherlands Antilles to design, build and launch the ECCO satellite system.1 <7<' O Contact[6<<% lConstellation Communications, Inc.Reston, Virginia87<<' "(OTechnical data@< <' 2 Constellation overviewS<]<A#R$ Orbit typeMEOb! <<A#RB Orbit range2000 km, circularX]<<A#R. &Nb of satellites12`<w<A#R> Nb of planes1 (equatorial)S<<A#R$ Inclination0\w<& <A#R6 2Nb beams per satelliteN <t <A#R CoverageT& < <A#R& ModulationCDMAx6t <@ <B#Tl *Mobile frequenciesUplink: L-bandDownlink: S-bandZ < <A#R2 "Satellite mass280 kgN @ < <A#R Coveraged# <L <A#RF &Operational date1998 (planned)kE < <& lifetime: 5 yearssatellite-gateway: C-bandinter-satellite links1L < <1W9 << <b <T+ << <) "VȠ$To view this page you need to register& <b <# D< < <1wx: < <}A<Dynamics Explorer 1Lb < <2 46"  Dynamics Explorer 16 <( <# &Also called DE A1 <Y <'  Generalg ( < <G#^@") Designation12624 / 81070A[Y <<A#R4Launch date3 Aug 1981t' <<M#jN"N ,㹌לCountry of originUnited States|/< <M#j^"H̀d;plMissionScientific: magnetosphere study`<k<A#R>"Perigee/Apogee468/23322 kmV <<A#R*Inclination88.8Uk<"@<A#R(<"@<b <Period409.7 mins&<@<M#jL" &p㉂Launch vehicleThor Delta #155&"@<@<# <@<@<' *O External resourcesX@<}A<. ,http://leadbelly.lanl.gov/de/DE_home.htmlhttp://nssdc.gsfc.nasa.gov/space/de.htmlD@<A<1xqx;A< B<tG<Dynamics Explorer 2L}A< B<2 46"  Dynamics Explorer 26A<CB<# &Also called DE B1 B<tB<'  Generalg CB<B<G#^@") Designation12625 / 81070B[tB<6C<A#R4Launch date3 Aug 1981t'B<C<M#jN"N ,㹌לCountry of originUnited States@6C<=D<S#v"H̀(d;pl?vMissionScientific: magnetosphere and ionosphere study_C<D<A#R<"Perigee/Apogee304/1002 kmT=D<D<A#R&Inclination90TD<DE<A#R&Period97.8 mins&D<E<M#jL" &p㉂Launch vehicleThor Delta #155&DE<E<# <E<F<' *O External resourcesXE<F<. ,http://leadbelly.lanl.gov/de/DE_home.htmlhttp://nssdc.gsfc.nasa.gov/space/de.html&F<F<# 5F<F<'  End of lifeVF<PG<A#R*Decay19 Feb 1983$F<tG<" ?PG<G<1 xgx<G<G<J<Program: E-sat?tG<G<, ((" Program: E-satG<J<( iLEO system program lead by Echostar and DBS industries; aimed at collection of remote data. Worth $50 million Authorized by FCC on 1st Apr 1998.6 satellites orbiting at 1260 km (2 planes of 3 satellites) planned for 2001. Should use CDMA. Terminals would transmit only twice a day during 400 ms. Uplink: 148-148.905 MHz, Downlink: 137.0725-137.9725 MHzE-SAT's system will offer data communications services including data messaging services for the gas and electric utility industry, data messaging and retrieval in support of the direct-to-home broadcast-satellite service, messaging for environmental monitoring, and other services to users in the United States and around the world.1G<J<1W=J<SK<yK<T+J<SK<) "VȠ$To view this page you need to register&J<yK<# 5SK<K<1 qxWy>K<K<DŽ<EAST5 yK<K<, (" EASTO,K<2L<# XEuro-African Satellite Telecommunications1 K<cL<'  GeneralY2L<L<G#^$") DesignationUcL<M<A#R(Launch date2001_L<pM<G#^0"N ,Country of origino"M<M<M#jD"H̀‰MissionTelecommunications]pM< L<<1gxy@<<<Program: EchoJr<<5 :,OG" Program: EchoU2<O<# dAmerican experimental telecommunication program<<<' *O External resourcesV/O<<' ^http://sulu.lerc.nasa.gov/dglover/echo.html1<<1A<q<_%<q<: DJ㸈LV.MV.Program: EchoEcho 1Echo 27<<1xyB<<<Echo 1Cq<<5 :OG" Echo 1eB<P<# Also called Echo 1A because the first Echo had a launch failure1 <<'  Generalg P<<G#^@") Designation00049 / 60009A\<D<A#R6Launch date12 Aug 1960t'<<M#jN"N ,㹌לCountry of originUnited States0D<;<S#v`"H̀(‰CV$MissionTelecommunications and geodesy_<<A#R<"Perigee/Apogee966/2157 kmV;<<A#R*Inclination47.3U<E<A#R(Period117.3 minq$<<M#jH" &p㉂Launch vehicleThor Delta #2YE<<A#R0"Mass at launch61 kg<<' Plastic 30.5 m ball covered of mylar aluminumed that reflected radioelectric signals.It enabled the first satellite telephone link and the broadcast of a TV program from California to Massachussets on 24 Feb 1962.5<F<'  End of lifeV<<A#R*Decay24 May 1968$F<<" 7<<1jyC<:<<Echo 2C<:<5 :OG" Echo 21 <k<'  Generalg :<Ҏ<G#^@") Designation00740 / 64004A\k<.<A#R6Launch date25 Jan 1964t'Ҏ<<M#jN"N ,㹌לCountry of originUnited States0.<1<S#v`"H̀(‰CV$Mission<1<<Telecommunications and geodesy`<<A#R>"Perigee/Apogee1030/1315 kmV1<<A#R*Inclination81.5U<<<A#R(Period108.8 minn!<<M#jB" &#*≂Launch vehicleThor Agena[<<<A#R4Launch siteVandenbergZ<_<A#R2"Mass at launch256 kgrN<<$ Plastic 41 m ball covered 2 aluminum sheets with a mylar sheet in between.5_<<'  End of lifeU<[<A#R(Decay7 Sep 1969$<<" B[<<1zWyD<<X<Program: EchostarN<<5 :4xˀ" Program: Echostark7<z<4 6o==American DBS program operated by EchoStar. The system broadcasts the DISH (Digital Sky Highway).The FCC granted EchoStar an extension of its satellite construction permit, and granted EchoStar subsidiary DirectSat an extension until Aug. 15, 1999, for construction and launch of its satellites to be located at 119 degrees and 175 degrees west longitude. Echostar controls frequency allocations at 61.5, 119, 148 and 175 degrees west longitude (90 transponders of DBS spectrum). Echostar has the 121W & 83W slots reserved for non-DBS Ku-band and Ka-band<<<' *O External resourcesEz<<' <http://www.dishnetwork.com]5<X<( kEchostar should launch 2 Ka-band satellites after the May 1997 FCC approval (83 & 121W). Each satellite would have 48 transponders, with narrow and wide spot beams. It would have on-board signal processing and on-board switching. Maximum EIRP: 63 dBWDownlink: 19.7-20.2 GHz; Uplink: 29.5-30.0 GHz band1<<1E<<KX<<H `R4VR^ZWR^ZXR^ZYR^ZProgram: EchostarEchostar 1Echostar 2Echostar 3Echostar 4; <W<1N 8zFW<<=Echostar 1G<<5 :&xˀ" Echostar 11 W<<'  Generalg <6<G#^@") Designation23754 / 95073Ah'<<A#RNLaunch date28 Dec 1995 at 11:50 UTt'6<<M#jN"N ,㹌לCountry of originUnited Stateso"<<M#jD"H̀‰MissionTelecommunicationsh!<<G#^B"/ۀ0Geostationary orbit119.2Wq$<Z<M#jH" &9+SLaunch vehicleLong March 2E&<<# 8Z<<' "(OTechnical data8<<' " Specificationsq0<a<A#R`&Prime contractorLockheed Martin Astro SpaceU<<A#R(PlatformGE 7000Ta< <A#R&"Mass at launchS<]<A#R$ Mass in orbitq$ <<M#jHDimension4.08 x 2.22 x 2.54 m?]]<+<A#R8Solar array24.5 m span?Y<<A#R0 Stabilization3 axish&+< =B#TLDC powerBOL: 6400 W?EOL: 5000 W?< =<c"<o=A#RD$Design lifetime12 or 15 years? ==$ 6Telemetry in the C-band1 o=='  Ku-bandY=8=A#R0(Main transponders16Y==A#R0,Backup transpondersP8==A#RPower130 WU=6=A#R(Bandwidth24 MHzI==B#T,Coverage & EIRP maxCONUS only: 53 dBW(US Virgin Island: 1.8 m dish)V6==A#R*PolarizationRHCP===B#TzFrequenciesuplink: 17.3-17.8 GHzdownlink: 12.2-12.7 GHz&==# ; ==1 y@zG=>=@=Echostar 2G=>=5 :&xˀ" Echostar 21 =o='  Generalg >==G#^@") Designation24313 / 96055A\o=2=A#R6Launch date11 Sep 1996t'==M#jN"N ,㹌לCountry of originUnited Stateso"2==M#jD"H̀‰MissionTelecommunicationsh!=}=G#^B"/ۀ0Geostationary orbit118.8Wn!==M#jB" &4E+Launch vehicleAriane V91}= =5 8㉓g2!Launch opportunities had been reserved with Long March and Proton but finally after the numerous launch problems, Echostar choose Ariane for launch.The total satellite, launch and insurance are estimated at $225 million The satellite entered service on 1st Nov 1996.The channels used by this satellite were originally licensed to Directsat Corp. This entity was transfered from SSE Telecom to Echostar in Nov 1994. Directsat was licensed to provide 11 channels of eastern half-CONUS or full-CONUS DBS service on even-numbered channels 2-20, at orbital position 119 West and on channel 24 at orbital position 110West, and 11 channels of western half-CONUS service on odd-numbered channels 1-21 at orbital position 175West.8=8 =' "(OTechnical data8 =p =' " Specificationsd#8 = =A#RF&Prime contractorLM Astro SpaceUp =) =A#R(PlatformGE 7000[ = =A#R4"Mass at launch2800 kgS) = =A#R$ Mass in orbitO =& =A#RDimensionQ =w =A#R Solar arrayY& = =A#R0 Stabilization3-axisN w = =A#RDC power] ={ =A#R8$Design lifetime10 years& = =# 1 { = ='  Ku-bandY =+=A#R0(Main transponders16Y ==A#R0,Backup transpondersP+==A#RPower130 WU=)=A#R(Bandwidth24 MHzI==B#T,Coverage & EIRP maxCONUS only: 53 dBW(US Virgin Island: 1.8 m dish)V)=@=A#R*Polarizati=@==onLHCP==@=B#TzFrequenciesuplink: 17.3-17.8 GHzdownlink: 12.2-12.7 GHz&@=@=# ; @=@=1 8z zH@==A=L=Echostar 3G@==A=5 :&xˀ" Echostar 38@=uA=# *Also called DBSC 11 =A=A='  Generalg uA= B=G#^@") Designation25004 / 97059A[A=hB=A#R4Launch date4 Oct 1997t' B=B=M#jN"N ,㹌לCountry of originUnited Stateso"hB=KC=M#jD"H̀‰MissionTelecommunicationsg B=C=G#^@"/ۀ0Geostationary orbit61.5Wr%KC=$D=M#jJ" &yjLaunch vehicleAtlas 2AS #110C= F=) }This satellite was originaly ordered by DBSC (Direct Broadcast Satellite Corporation) which merged with a subsidiary of Echostar in late 1995. The merger was approved by the FCC in August 1996.Echostar is only authorized to operate 11 transponders from 61.5W but was granted in Mar 1998 a special authorization to use the full frequency space at that location.Dominion Video Satellite, Inc. will operate 8 frequencies from this satellite8$D=CF=' "(OTechnical data8 F={F=' " Specificationsd#CF=F=A#RF&Prime contractorLM Astro Spacea {F=@G=A#R@PlatformAstro Space A2100AX[F=G=A#R4"Mass at launch3675 kgS@G=G=A#R$ Mass in orbitOG==H=A#RDimensionQG=H=A#R Solar arrayY=H=H=A#R0 Stabilization3 axisN H=5I=A#RDC power_H=I=A#R<$Design lifetime13.5 years&5I=I=# 1 I=I='  Ku-bandYI=DJ=A#R0(Main transponders32YI=J=A#R0,Backup transpondersPDJ=J=A#RPower120 WUJ=BK=A#R(Bandwidth24 MHzk*J=K=A#RT,Coverage & EIRP maxCONUS only: 53 dBWZBK=L=A#R2Polarizationcircular=K=L=B#TzFrequenciesuplink: 17.3-17.8 GHzdownlink: 12.2-12.7 GHzc?L=L=$ ~Can operate in double power mode (16 transponders at 240 W); L=$M=1@zI$M=kM==Echostar 4GL=kM=5 :&xˀ" Echostar 41 $M=M='  Generalg kM=N=G#^@") Designation25331 / 98028A[M=^N=A#R4Launch date7 May 1998t'N=N=M#jN"N ,㹌לCountry of originUnited Stateso"^N=AO=M#jD"H̀‰MissionTelecommunications^N=O=A#R:,Geostationary orbit119Eo"AO==M#jD" &㉓gLaunch vehicleO==L=Proton #258O&O=i=) MThe satellite (with 32 transponders) should replace Echostar 1 at 119W which would then move to 148W Only 24 transponders have been granted for use at 148W. The FCC licence for 148W costed $52 millionShould test from 127W (this is a Mexican DBS slot)The satellite has experienced anomalies in connection with solar panel deployment (two of five panels on one solar array have not unfolded). This means some transponders will not be operational, unless the solar array can be properly deployed. The satellite was insured for $220 million8==' "(OTechnical data8i=ق=' " SpecificationsX=1=A#R.&Prime contractorLMUق==A#R(PlatformA2100AXT1=ڃ=A#R&"Mass at launchS=-=A#R$ Mass in orbitOڃ=|=A#RDimensionQ-=̈́=A#R Solar arrayY|=&=A#R0 Stabilization3 axisN ̈́=t=A#RDC power]&=х=A#R8$Design lifetime15 yearst==& Has a Leros liquid apogee engineTelemetry and command: 12.2005 GHz, 12.2025 GHz, 12.6985 GHz and 17.308 GHz, with a 300 kHz bandwidth1 х=='  Ku-bandY= =A#R0(Main transponders32Y=d=A#R0,Backup transpondersP ==A#RPower120 WUd= =A#R(Bandwidth24 MHzy6==C#Vl,Coverage & EIRP maxCONUS: 53 dBWAlaska:Hawaii: Z =܈=A#R2Polarizationcircular==[=B#TzFrequenciesuplink: 17.3-17.8 GHzdownlink: 12.2-12.7 GHzV2܈==$ dTransponders can be dual-combined (16 x 240 W)B[==1 Ƅ{J=5==Program: EllipsatB=5=, (." Program: Ellipsat}Z==# Mobile satellite phone project with 2 types of satellites. Has been licensed by the FCC2 5=='  Overviewn=R=R#t8QQ "NameBorealisConcordiai==R#t.QQ $Orbit typeHEOMEO8R=E=R#tpQQ JOrbit range520/7846 km, elliptic8040 km, circularl==R#t4QQ &.Nb of satellites106gE==R#t*QQ $Nb of planes21l==R#t4QQ ,Inclination116.50s!==R#tBQQ 2:Nb beams per satellite6161s!=j=R#tBQQ ,Coverage11980 km11980 kml=֎=R#t4QQ &ModulationCDMACDMA j==U#xQQ *Mobile frequenciesUplink: 1610 - 1626.5 MHzDownlink: 2483.5 - 2500 MHzUplink: 1610 - 1626.5 MHzDownlink: 2483.5 - 2500 MHzt"֎=.=R#tDQQ "4=.==Satellite mass690 kg 880 kgU==R#tQQ `Coverageall longitudes, 70N - 20S latitudesall longitudes, 70N - 20S latitudes3.=Z=R#tfQQ &FOperational date1999 (planned)1999 (planned)\*==2 2UR@satellites to gateways: 6875 - 7075 MHzgateways to satellites: 15.45 - 15.65 GHzTo be operataed by Mobile Communications Holdings Inc. Boeing invested $200 million in the project.Boeing is the system integrator for design, development, construction and deployment of Ellipso. The estimated contract value is over $1.4 billion. First satellite launch expected in 2001. A second network named Ellipso 2G is planned. It will have 26 non-geostationary satellites to operate in 2 GHz band. The project is subject to FCC approval. Planned for 2003|WZ=2=% The satellites would be arrayed in five orbital planes in two sub-constellations. Three planes of five satellites each will be placed in inclined elliptical orbits for Northern Hemisphere coverage. A fourth plane of six satellites will be launched into circular equatorial orbits and another five satellites in elliptical equatorial orbit.<=n=' *O External resourcesuG2==. ,http://www.ellipso.comhttp://www.jaguNET.com/prism/ellipsat.html1n==1WK=h==T+=h=) "VȠ$To view this page you need to register&==# 8h==1 {A|L==>Envisat8 ==, (" Envisat1 =/='  GeneralY==G#^$") Designation`/==A#R>Launch dateplanned in 1999m =U=M#j@"N ,4"Country of originEurope1==S#vb"H̀(郉vSMissionRemote sensing (to replace ERS)[U=4=A#R4"Perigee/Apogee~800 kmQ==A#R InclinationL 4==A#RPeriodl===M#j>" &2!Launch vehicleAriane 5Q==A#R Launch site==p=7 Dimension26 m x 10 m x 5 m`f=&=A#R>Solar array(weighs 400 kg)S=y=A#R$ StabilizationT&==A#R&DC power6500 WUy=.>A#R(=.>=$Design lifetime=>+ $[J4 on-board recorders provide 30 Gbits storage. Inter orbit link in Ka-band will be possible with Artemis (another ESA satellite which could be launched in 1999 via H2)@.>F>' 2O 10 scientific payloads{M>>. *ASAR (radar imaging, 27 m resolution)GOMOS (ozone layer study)AATSR (radiometer)MWR (microwave radiometer)MERIS (visible and near IR imaging)MIPAS (atmospheric probe)SCIAMACHY (atmospheric cartography spectrometer)RA-2 (radar altimeter)DORIS (orbitography)LRR (laser reflectors)The French Scarab experiment was withdrawn1F>>1WM>F>l>T+>F>) "VȠ$To view this page you need to register&>l># 5F>>1J{|N>> >Eole5 l>>, (" Eole1 >>'  Generalg >n>G#^@") Designation05435 / 71071A\>>A#R6Launch date16 Aug 1971m n>7>M#j@"N ,㱭+Country of originFrance~1>>M#jb"H߲̀-MissionScientific: high atmosphere study^7>>A#R:"Perigee/Apogee651/835 kmV>i>A#R*Inclination50.2T>>A#R&Period99.7 minm i>*>M#j@" &g'KLaunch vehicleScout #75Y>>A#R0"Mass at launch80 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.<>>' *O External resourcesN'>9 >' Nhttp://neonet.nlr.nl/ceos/EOLE.html5>n >'  End of life]9 > >A#R8"Out of serviceJuly 1974$n > >" 7 >& >1eA|Ԃ|O& >f >I>Eorsat@ >f >, (*" Program: Eorsatd6& > >. *mqiElectronic Ocean Reconnaissance SatelliteRussian program part of the Cosmos constellation. Those satellites are observation satellites designed to monitor activity of foreign navies.The series started in 1974 and around 40 satellites had been launched in mid-1995. The system went operational in 1978.:f > >' & First generationZ > >#<ZxCosmos 0699Cosmos 0777Cosmos 0838Cosmos 0868Cosmos 0937Cosmos 1094O > >#ڀ6PjCosmos 1096Cosmos 1167Cosmos 1220Cosmos 1260Cosmos 1286Cosmos 1306O >>#ڀ6PjCosmos 1337Cosmos 1355Cosmos 1405Cosmos 1461Cosmos 1507Cosmos 1567O >>#ڀ6PjCosmos 1588Cosmos 1625Cosmos 1646Cosmos 1682Cosmos 1735Cosmos 1737O>`@>#ڀ6Pj>`@> >Cosmos 1769Cosmos 1890Cosmos 1949Cosmos 1979Cosmos 2033Cosmos 2046]>NA>#6Rn&xCosmos 2051Cosmos 2060Cosmos 2096Cosmos 2103Cosmos 2107Cosmos 2122 (decayed)c`@>TB>#8,x:g,xl,x-x2xCosmos 2238Cosmos 2244Cosmos 2258 (decayed)Cosmos 2264Cosmos 2293Cosmos 23134NA>C>#h"3x G3x>t3x\`dCosmos 2326Cosmos 2335Cosmos 2347&TB>EC># ;C>C>' ( Second generationMEC>RD>#ڀFCosmos 1867 (800 km, 65, Topaz)Cosmos 1818 (800 km, 65, Topaz)&C>xD># 8RD>D>' "(OTechnical data8xD>D>' " Specificationsi(D>QE>A#RP&Prime contractorNPO MachinostroenieN D>E>A#RPlatformTQE>E>A#R&"Mass at launchSE>FF>A#R$ Mass in orbitL E>F>A#RLengthK FF>F>A#RWidthL F>)G>A#RHeightZF>G>A#R2"Perigee/Apogee400 kmT)G>G>A#R&Inclination65RG>)H>A#R"Period92 minSG>|H>A#R$ StabilizationN )H>H>A#RDC power^|H>(I>A#R:$Design lifetime1.5 yearsZ6H>I>$ lIt uses a low thrust engine to maintain its orbit.1(I>I>1WPI>J>-J>T+I>J>) "VȠ$To view this page you need to register&I>-J># = J>jJ>1|~QjJ>J>>Program: EOSI-J>J>5 :*lc%" Program: EOS,jJ>L>&  Earth Observing SystemThe Earth Observing System is a multi-mission program with the objective of acquiring the geophysical, chemical, and biological information necessary for intense study of planet Earth. A scientific research effort is underway to ensure that the planning and execution of the mission fulfills its intended purpose. An EOS data and information system will build up over 10 years and then function for at least 20 years to allow accurate modeling of the processes that control the environment.oJ>>% The Earth Observing System (EOS) program involves the operation of numerous instruments on multiple spacecraft placed in polar and mid-inclination orbits in support of multiple disciplines within the Earth science user community. The EOS mission is composed of several series of flights beginning with the EOS AM-1 flight from the AM series in 1998. The other EOS series include PM, LALT (Laser Altimetry), and CHEM (Chemistry) flights. Each spacecraft with exception of LALT has a projected lifetime of 5 years with operational goal of 6 years. The Canadian Space Agency (CSA), the European Space Agency (ESA) and the Ministry of International Trade Industry (MITI) of Japan are planning Earth observing missions that complement the National Aeronautics andL>>-J> Space Administration (NASA) program. In addition, they are also supplying instruments on selected EOS flights.<L>>' *O External resourcesG >>' @http://eospso.gsfc.nasa.gov/1>3>1WR3>>>T+>>) "VȠ$To view this page you need to register&3>># 1>ށ>1Sށ>W>y8>W>A RpZvS-1)}̉Program: EOSEOS AMEOS PM-1EOS Chemistry 11ށ>>1WT>܂>>T+W>܂>) "VȠ$To view this page you need to register&>># 7܂>9>1[ !}U9>|>>EOS AMC>|>5 :lc%" EOS AM1 9>>'  GeneralY|>>G#^$") Designation`>f>A#R>Launch dateplanned in 1998t'>ڄ>M#jN"N ,㹌לCountry of originUnited States_f>9>G#^0"H̀MissionScientifick*ڄ>>A#RT"Perigee/Apogee705 km, sun-synchronousV9>>A#R*Inclination98.2S>M>A#R$Period100 minm >>M#j@" &yjLaunch vehicleAtlas 2ASQM> >A#R Launch site&>1># < >m>' *O External resourcesQ*1>>' Thttp://eos-am.gsfc.nasa.gov/index.html8m>>' "(OTechnical data8>.>' " Specificationse$>>A#RH&Prime contractorLockheed MartinN .>>A#RPlatform[><>A#R4"Mass at launch5200 kgS>>A#R$ Mass in orbitY<>>A#R0Paylaod mass1100 kgO>7>A#RDimensionQ>>A#R Solar arrayY7>>A#R0 Stabilization3-axisT>5>A#R&DC power7500 WU>>A#R($Design lifetime5>>2 2@ĘThe 45 m solar array will use 36,480 advanced gallium arsenide germanium (GaAs/Ge) and weigh 73 kgOperates at 2, 13 and 15 GHzAcquisition via TDRSTelemetry: 2287.5 MHzCommand: 2106.4 MHz Data: 15003.4 MHz (upto 150 Mbps)1>׌>1WV׌>+>Q>T+>+>) "VȠ$To view this page you need to register&׌>Q># 9+>>1 }}W>ύ>>EOS PM-1EQ>ύ>5 :"lc%" EOS PM-11 >>'  GeneralYύ>Y>G#^$") Designation`>>A#R>Launch dateplanned in 2000t'Y>->M#jN"N ,㹌לCountry of originUnited States_>>G#^0"H̀MissionScientifick*-> >A#RT"Perigee/Apogee705 km (sunsynchronous)> >Q>V>b>A#R*Inclination98.2S >>A#R$Period100 min\b>>G#^*" &Launch vehicleQ>b>A#R Launch site> >% Contracted together with EOS Chemistry 1 for $398 million; an option on two more crafts could amount the total to $668 million<b>E>' * External resourcesY2 >>' dhttp://mtpe.gsfc.nasa.gov/eos-pm1/PM1PROJ1.htm8E>>' "(OTechnical data8>>' " SpecificationsY>g>A#R0&Prime contractorTRWn->>A#RZPlatformAM1200 EOS commun spacecraft busTg>)>A#R&"Mass at launchS>|>A#R$ Mass in orbitO)>>A#RDimensionQ|>>A#R Solar arrayY>u>A#R0 Stabilization3-axisN >>A#RDC power\u>>A#R6$Design lifetime6 yearsg>>- *@ĘAcquisition via TDRSTelemetry: 2287.5 MHzCommand: 2106.4 MHz Data: 15003.4 MHz (upto 150 Mbps)1>>1WX>8>^>T+>8>) "VȠ$To view this page you need to register&>^># @8>>1!}Y>>~>EOS Chemistry 1L^>>5 :0lc%" EOS Chemistry 11 >>'  GeneralY>t>G#^$") Designation`>>A#R>Launch dateplanned in 2002t't>H>M#jN"N ,㹌לCountry of originUnited States_>>G#^0"H̀MissionScientificTH>>A#R&"Perigee/ApogeeQ>L>A#R InclinationL >>A#RPeriod\L>>G#^*" &Launch vehicleQ>E>A#R Launch site{>>$ Contracted together with EOS PM-1 for $398 million; an option on two more crafts could amount the total to $668 million8E>>' "(OTechnical data8>T>' " SpecificationsY>>A#R0&Prime contractorTRWn-T>>A#RZPlatformAM1200 EOS commun spacecraft busT>o>A#R&"Mass at launchS>>A#R$ Mass in orbitOo>>A#RDimensionQ>b>A#R Solar arrayS>>A#R$ StabilizationN b>>A#RDC powerU>X>A#R($Design lifetime&>~># 1X>>1WZ>?5?T+~>?) "VȠ$To view this page you need to register>?~>&>5?# : ?o?1 Ԃ|~[o??/ ?Equator S:5??, (" Equator S1 o??'  Generalg ?A?G#^@") Designation25068 / 97075B[??A#R4Launch date2 Dec 1997n!A? ?M#jB"N , Country of originGermanyy,??M#jX"H̀d;plMissionObservation of magnetosphereb! ??A#RB"Perigee/Apogee500 / 63700 kmS?8?A#R$Inclination4L ??A#RPeriodo"8??M#jD" &zg&\Launch vehicleAriane V103Y?v?* "The satellite is a small version (therefore Equator S) of an equatorial spacecraft originally planned by NASA for the International Solar-Terrestrial Physics program, but later abandonned. Will be measuring the effects of the solar winds on our planet's magnetic and electrical fields. Satellite cost: $12 millionNASA & ESA contribution<??' *O External resourcesSv?3?. ,http://www.go-ariane.com/main/feat/feat_18.htmlhttp://www-istp.gsfc.nasa.gov8?k?' "(OTechnical data83??' " Specificationss2k??A#Rd&Prime contractorMax Plank Institute (Germany)N ?d?A#RPlatformZ??A#R2"Mass at launch230 kgSd??A#R$ Mass in orbitO?`?A#RDimensionQ??A#R Solar arrayk*`? ?A#RT Stabilizationspin-stabilized (60 rpm)N ?j ?A#RDC powerU ? ?A#R($Design lifetimepLj ?/ ?$ Carries 8 experiments. Has a GPS receiver. On-board data storage: 192 Mo5 ?d ?1 ~~\d ? ?LD?ERBS5 / ? ?, (" ERBSb9d ? ?) "r  Earth Radiation Budget Satellite, also called SAGE 21 ?, ?'  Generalg ? ?G#^@") Designation15354 / 84108B[, ? ?A#R4Launch date5 Oct 1984t' ?b ?M#jN"N ,㹌לCountry of originUnited States~1 ? ?M#jb"H߲̀-MissionScientific: high atmosphere study^b ?> ?A#R:"Perigee/Apogee582/593 kmT ? ?A#R&Inclination57T> ? ?A#R&Period96.4 minj ?P?M#j:" &(Launch vehicleSTS 17Z ??A#R2"Mass at launch147 kgP?w?+ $E 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.<??' *O External resourceslw?Y@?. ,http://www.ngdc.noaa.gov/stp/S?Y@?/ ?OLAR/IRRADIANCE/erbs.htmlhttp://asd-www.larc.nasa.gov/sage/ASDsage.html8?@?' "(OTechnical data8Y@?@?' " SpecificationsZ@?#A?A#R2&Prime contractorBall[@?~A?A#R4"Mass at launch2300 kgQ#A?A?A#R Length1.6 mQ~A? B?A#R Height3.8 mYA?yB?A#R0Solar array7 m spanY B?B?A#R0 Stabilization3 axisz?yB?LD?; D  @ĘA 180 degree yaw maneuver is performed approximately every 5 weeks to keep sun on the solar arrays.Payload: 2 radiometers and SAGE 2 (Stratospheric Aerosol and Gas Experiment) to monitor vertical distribution of aerosols, ozone and carbone dioxide in the stratosphere.Telemetry and data via TDRS (S-band).4B?D?1~]D?D?EF?ERSILD?D?5 :*c%" Program: ERS|SD?EF?)  European Remote Sensing satelliteEuropean 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.1D?vF?1^vF?F?\"EF?F?: DDvS_QT`QTProgram: ERSERS 1ERS 26vF?G?1_G?JG?*?ERS 1B F?JG?5 :c%" ERS 11 G?{G?'  Generalg JG?G?G#^@") Designation21574 / 91050A\{G?>H?A#R6Launch date17 Jul 1991m G?H?M#j@"N ,4"Country of originEuropek>H?I?M#j<"H̀郉MissionRemote sensing^H?tI?A#R:"Perigee/Apogee768/769 kmVI?I?A#R*Inclination98.5UtI?J?A#R(Period100.2 mini%I?J?D#XJ Orbital cycle3, 35 and 176 daysn!J?J?M#jB" &`D+Launch vehicleAriane V44J?K?' WESA's first remote sensing satellite. Cost: $500 millionSince early 1994 the satellite transmits with the backup travelling wave tube because the primary one failed.<J?L?' *O External resources\5K?`L?' jhttp://info.man.ac.uk/Arts/geography/rs/ers1.html8L?L?' "(OTechnical data8`L?L?' " Specifications]L?-M?A#R8&Prime contractorDornier_L?M?A#R<PlatformMMS Spot (Mark 1)[-M?M?A#R4"Mass at launch2400 kgYM?@N?A#R0Payload mass1100 kgUM?N?A#R(Dry mass2080 kgR@N?N?A#R"Length11.8 m]N?DO?A#R8Solar array11.7 x 2.4 mYN?O?A#R0SAR antenna10 x 1 me$DO??A#RH$Radar altimeter1.2 m (diameter)O??F?YO?g?A#R0 Stabilization3 axisT??A#R&DC power2500 W\g??A#R6$Design lifetime3 years&?=?# S&??- *L  AMI (Active Microwave Instrument)_=??A#R<PFrequency5.3 GHz (C-band)X?G?A#R.P"SAR resolution26 mZ??A#R2P$SAR swath width99 kmc"G??A#RDP6Scatterometer resolution47 km@??B#TP8Scatterometer swath width613 km (fore and aft)809 km (mid)?1?%  Mission: payload all-weather high-resolution images of land and ocean, windspeed and direction, ice mapping, pollution monitoring.F?w?- *2  RA (Radar Altimeter)a 1?؄?A#R@PFrequency13.8 GHz (Ku-band)e$w?=?A#RHP2Accuracy (wave height)+/- 0.5 m\؄??A#R6P(Altitude accuracy0.1 mkG=??$ Mission: windspeed and sea surface elevation, ice sheet topography.X+?\?- *V  ATSR (Along-Track Scanning Radiometer)k*?dž?A#RTmWavelengths1.6, 3.7, 10.8 and 12.0 mq0\?8?A#R`mJAccuracy (sea surface temperature)+/- 0.5 Kdž??% #Mission: images of sea surface temperature, total water vapour content of atmosphere, cloud, aerosols, haze, land and ice surface emissivity.;8?)?' ( Microwave Sounder`??A#R>PFrequency23.8 and 36.5 GHz])??A#R8P(Altitude accuracy0.02 mZ?@?A#R2P"Telemetry/dataS-band?*?I `C      Also equipped with Laser Reflectometer (LR), Precise Range and Range-rate Equipment (PRARE) and Instrument Data Handling and Transmission (IDHT).6@?`?1n~``??V?ERS 2B *??5 :c%" ERS 21 `?ӊ?'  Generalg ?:?G#^@") Designation23560 / 95021A\ӊ??A#R6Launch date21 Apr 1995m :??M#j@"N ,4"Country of originEuropek?n?M#j<"H̀郉MissionRemote sensing^?̌?A#R:"Perigee/Apogee783/786 kmVn?"?A#R*Inclination98.6Ǔ?w?A#R(Period100.5 minn!"??M#jB" &D+Launch vehicleAriane V72[w?d?$ Cost: FF3.1 billion including FF2 billion for the satellite. The launch was not insured<??' *O External resources\5d??' jhttp://info.man.ac.uk/Arts/geography/rs/ers2.html8?4?' "(OTechnical data8?l?' " Specifications]4?ɏ?A#R8&Prime contractorDornier_l?4?A#R<ɏ?4?*?PlatformMMS Spot (Mark 1)[ɏ??A#R4"Mass at launch2500 kgY4??A#R0Payload mass1100 kgU?=?A#R(Dry mass2080 kgR??A#R"Length11.8 m]=??A#R8Solar array11.7 x 2.4 mY?E?A#R0SAR antenna10 x 1 me$??A#RH$Radar altimeter1.2 m (diameter)YE??A#R0 Stabilization3 axisT?W?A#R&DC power2500 W\??A#R6$Design lifetime3 years&W??# S&?,?- *L  AMI (Active Microwave Instrument)_??A#R<PFrequency5.3 GHz (C-band)X,??A#R.P"SAR resolution26 mZ?=?A#R2P$SAR swath width99 kmc"??A#RDP6Scatterometer resolution47 km@=?"?B#TP8Scatterometer swath width613 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.F"??- *2  RA (Radar Altimeter)a ?t?A#R@PFrequency13.8 GHz (Ku-band)e$??A#RHP2Accuracy (wave height)+/- 0.5 m\t?5?A#R6P(Altitude accuracy0.1 mkG??$ Mission: windspeed and sea surface elevation, ice sheet topography.X+5??- *V  ATSR (Along-Track Scanning Radiometer)k*?c?A#RTmWavelengths1.6, 3.7, 10.8 and 12.0 mq0??A#R`mJAccuracy (sea surface temperature)+/- 0.5 Kc??% #Mission: images of sea surface temperature, total water vapour content of atmosphere, cloud, aerosols, haze, land and ice surface emissivity.;??' ( Microwave Sounder`?%?A#R>PFrequency23.8 and 36.5 GHz]??A#R8P(Altitude accuracy0.02 m&%??# [.??- *\  GOME (Global Ozone Monitoring Experiment)Z?]?A#R2Waveband0.24-0.79 m};??B#TvResolution40 x 40 km max. (horizontal)1 km (vertical)[]?5?A#R4Swath width120-960 km!?V?M h      Mission: stratospheric and tropospheric ozone profiles, cloud distribution and surface spectral reflection.Also equipped with Laser Reflectometer (LR), Precise Range and Range-rate Equipment (PRARE) and Instrument Data Handling and Transmission (IDHT). The on board tape recorder (6.5 gigabit) can store data from a full orbit.The telemetry is sent in S-band. The scientific data and a replication of the telemetry is sent on 2 X-band transponders.; 5??1c~Ba??@ESA-Geos 1CV??2 4$"  ESA-Geos 11 ?@'  Gene?@V?ralg ?x@G#^@") Designation09931 / 77029A\@@A#R6Launch date20 Apr 1977m x@A@M#j@"N ,4"Country of originEurope|/@@M#j^"H̀d;plMissionScientific: magnetosphere studya A@@A#R@"Perigee/Apogee2767/38389 kmV@t@A#R*Inclination26.8U@@A#R(Period734.1 mins&t@<@M#jL" &p㉂Launch vehicleThor Delta #130&@b@# <<@@' *O External resourcesX1b@@' bhttp://www.esoc.esa.de/external/mso/geos.html; @1@1Ib1@t@@ESA-Geos 2C@t@2 4$"  ESA-Geos 21 1@@'  Generalg t@ @G#^@") Designation10981 / 78071A\@h@A#R6Launch date14 Jul 1978m @@M#j@"N ,4"Country of originEurope|/h@Q@M#j^"H̀d;plMissionScientific: magnetosphere studyb!@@A#RB"Perigee/Apogee36020/36061 kmVQ@ @A#R*Inclination11.8V@_@A#R*Period1449.1 mins& @@M#jL" &p㉂Launch vehicleThor Delta #143&_@@# <@4@' *O External resourcesX1@@' bhttp://www.esoc.esa.de/external/mso/geos.html> 4@@1:Bc@ @ @Program: EsroJ@ @5 :,G" Program: EsrouM@ @( European Science Research OrganisationFirst European scientific program< @ @' *O External resourcesX1 @ @' bhttp://www.esoc.esa.de/external/mso/esro.html1 @N @1dN @ @: @ @H `tobpbb#1Program: EsroEsro 1AEsro 1BEsro 2BEsro 48N @ @1e @L @?@@Esro 1AD @L @5 : G" Esro 1A9 @ @# ,Also called Aurorae1 L @ @'  Generalg @ @G#^@") Designation03459 / 68084A[ @x @A#R4Launch date3 Oct 1968m  @ @M#j@"N ,4"Country of originEuropey,x @^ @M#jX"H̀?vMissionScientific: ionosphere study_ @ @A#R<"Perigee/Apogee258/1538 kmV^ @@A#R*Inclination93.8S @f@A#R$Period103 minm @@M#j@" &g'KLaunch vehicleScout #65Yf@,@A#R0"Mass at launch86 kgX4@@$ hAimed to study auroras and involved phenomenons.5,@@'  End of lifeV@@@A#R*Decay@@@ @26 Jun 1970$@?@@" 8@@w@@1fw@@@@E@Esro 1BD?@@@@5 : G" Esro 1B8w@@@@# *Also called Boreas1 @@$A@'  Generalg @@A@G#^@") Designation04114 / 69083A[$A@A@A#R4Launch date1 Oct 1969m A@SB@M#j@"N ,4"Country of originEuropey,A@B@M#jX"H̀?vMissionScientific: ionosphere study^SB@*C@A#R:"Perigee/Apogee298/378 kmTB@~C@A#R&Inclination85T*C@C@A#R&Period91.3 minm ~C@?D@M#j@" &g'KLaunch vehicleScout #66YC@D@A#R0"Mass at launch85 kgX4?D@D@$ hAimed to study auroras and involved phenomenons.5D@%E@'  End of lifeVD@{E@A#R*Decay23 Nov 1969$%E@E@" 8{E@E@165gE@F@ K@Esro 2BDE@F@5 : G" Esro 2B6E@QF@# &Also called Iris1 F@F@'  Generalg QF@F@G#^@") Designation03233 / 68041A\F@EG@A#R6Launch date17 May 1968m F@G@M#j@"N ,4"Country of originEuropey,EG@+H@M#jX"H̀?vMissionScientific: ionosphere study_G@H@A#R<"Perigee/Apogee334/1085 kmV+H@H@A#R*Inclination97.2RH@2I@A#R"Period99 minm H@I@M#j@" &g'KLaunch vehicleScout #62Y2I@I@A#R0"Mass at launch86 kgzVI@rJ@$ Aimed to study cosmic rays, solar X-rays and the radiation belts around the Earth.5I@J@'  End of lifeUrJ@J@A#R(Decay8 May 1971$J@ K@" 7J@WK@1hWK@K@V@Esro 4C K@K@5 :G" Esro 41 WK@K@'  Generalg K@2L@G#^@") Designation06285 / 72092A\K@L@A#R6Launch date22 Nov 1972m 2L@L@M#j@"N ,4"Country of originEuropey,L@tM@M#jX"H̀?vMissionScientific: ionosphere study_L@M@A#R<"Perigee/Apogee245/1173 kmVtM@)N@A#R*Inclination91.1RM@{N@A#R"Period99 minm )N@N@M#j@" &g'KLaunch vehicleScout #82Z{N@BO@A#R2"Mass at launch115 kgY5N@O@$ jStudy of ionosphere, auroras and solar particles.5BO@O@'  End of lifeVO@2@A#R*O@2@ K@Decay15 Apr 1974$O@V@" > 2@@16i@ހ@N@Program: EssaJV@ހ@5 :,G" Program: Essa@@/ ,E Environmental Science Service AdministrationAmerican meteorology program. The satellites of this program are evolved Tiros with better surface resolution.<ހ@@' *O External resourcesc<@N@' xhttp://thunder.met.fsu.edu/explores/Guide/essaindex.html1@@1j@N@dN@N@k 111111111Program: EssaEssa 1Essa 2Essa 3Essa 4Essa 5Essa 6Essa 7Essa 8Essa 97@@1k@ȃ@@Essa 1CN@ȃ@5 :G" Essa 11 @@'  Generalg ȃ@`@G#^@") Designation01982 / 66008A[@@A#R4Launch date3 Feb 1966t'`@/@M#jN"N ,㹌לCountry of originUnited Statesh@@M#j6"H̀l/MissionMeteorology^/@@A#R:"Perigee/Apogee684/805 kmV@K@A#R*Inclination97.8T@@A#R&Period99.7 minr%K@@M#jJ" &p㉂Launch vehicleThor Delta #36\@m@A#R6"Mass at launch138.6 kg$@@" 7m@ȇ@1olȇ@ @{@Essa 2C@ @5 :G" Essa 21 ȇ@<@'  Generalg @@G#^@") Designation02091 / 66016A\<@@A#R6Launch date28 Feb 1966t'@s@M#jN"N ,㹌לCountry of originUnited Statesh@ۉ@M#j6"H̀l/MissionMeteorology`s@;@A#R>"Perigee/Apogee1352/1412 kmUۉ@@A#R(Inclination101U;@@A#R(Period113.4 minr%@W@M#jJ" &p㉂Launch vehicleThor Delta #37$@{@" 7W@@1m@@@Essa 3C{@@5 :G" Essa 37@,@# (Also called TOS A1 @]@'  Generalg ,@Č@G#^@") Designation02435 / 66087A[]@@A#R4Launch date2 Oct 1966t'Č@@M#jN"N ,㹌לCountry of originUnited Statesh@@M#j6"H̀l/MissionMeteorology`@[@A#R>"Perigee/Apogee1383/1484 kmU@@A#R(Inclination101U[@@A#R(Period114.5 minr%@w@M#jJ" &p㉂Launch vehicleThor Delta #41$@@" 7w@ҏ@1 nҏ@!@@Essa 4C@!@5 :G"ҏ@!@@ Essa 47ҏ@X@# (Also called TOS B1 !@@'  Generalg X@@G#^@") Designation02657 / 67006A\@L@A#R6Launch date26 Jan 1967t'@@M#jN"N ,㹌לCountry of originUnited StateshL@(@M#j6"H̀l/MissionMeteorology`@@A#R>"Perigee/Apogee1323/1437 kmU(@@A#R(Inclination102U@2@A#R(Period113.4 minr%@@M#jJ" &p㉂Launch vehicleThor Delta #45$2@@" 7@@1$o@F@@Essa 5G@F@8 @ G" Essa 57@}@# (Also called TOS C1 F@@'  Generalg }@@G#^@") Designation02757 / 67036A\@q@A#R6Launch date20 Apr 1967t'@@M#jN"N ,㹌לCountry of originUnited Stateshq@M@M#j6"H̀l/MissionMeteorology`@@A#R>"Perigee/Apogee1352/1419 kmWM@@A#R,Inclination101.9U@Y@A#R(Period113.5 minr%@@M#jJ" &p㉂Launch vehicleThor Delta #48$Y@@" 7@&@1 >p&@i@@Essa 6C@i@5 :G" Essa 67&@@# (Also called TOS D1 i@@'  Generalg @8@G#^@") Designation03035 / 67114A\@@A#R6Launch date10 Nov 1967t'8@@M#jN"N ,㹌לCountry of originUnited Statesh@p@M#j6"H̀l/MissionMeteorology`@@A#R>"Perigee/Apogee1406/1483 kmWp@'@A#R,Inclination102.2U@|@A#R(Period114.8 minr%'@@M#jJ" &p㉂Launch vehicleThor Delta #54$|@@" 7@I@1$qI@@AAEssa 7C@@5 :G" Essa 77I@@# (Also called TOS E1 @@'  Generalg @[@G#^@") Designation03345 / 68069A\@@A#R6Launch date16 Aug 1968t'[@+@M#jN"N ,㹌לCountry of originUnited Statesh@@M#j6"H̀l/MissionMeteorology`+@@A#R>"Perigee/Apogee1429/1470 kmW@J@A#R,Inclination101.5U@@A#R(Period114.9 minr%J@AM#jJ" &p㉂Launch vehicle@A@Thor Delta #58$@AA" 7AxA1>rxAAdAEssa 8CAAA5 :G" Essa 87xAA# (Also called TOS F1 A#A'  Generalg AAG#^@") Designation03615 / 68114A\#AAA#R6Launch date15 Dec 1968t'AZAM#jN"N ,㹌לCountry of originUnited StateshAAM#j6"H̀l/MissionMeteorology`ZA"AA#R>"Perigee/Apogee1411/1461 kmWAyAA#R,Inclination101.8U"AAA#R(Period114.6 minr%yA@AM#jJ" &p㉂Launch vehicleThor Delta #62$AdA" 7@AA1sAAAEssa 9CdAA5 :G" Essa 97AA# (Also called TOS G1 AFA'  Generalg AAG#^@") Designation03764 / 69016A\FA AA#R6Launch date26 Feb 1969t'A}AM#jN"N ,㹌לCountry of originUnited Statesh AAM#j6"H̀l/MissionMeteorology`}AEAA#R>"Perigee/Apogee1423/1502 kmWAAA#R,Inclination101.4UEAAA#R(Period115.2 minr%AcAM#jJ" &p㉂Launch vehicleThor Delta #67$AA" = cAA1ڂtA A AProgram: ETSMA A8 @,Cc%" Program: ETSA A/ ,[  Engineering Test Satellite, also called Kiku which means "chrysanthemum"Primary purpose of the Japanese ETS is to develop and prove bus technology. Operated by NASDA< A) A' * External resources^7 A A' nhttp://www.goin.nasda.go.jp/GOIN/NASDA/act/ets.html1) A A1u An AR An Ad 1wSㅾTㆾTㇾT㈾T㉾T㊾T㋾T㌾TProgram: ETSETS 1ETS 2ETS 3ETS 4ETS 5ETS 6ETS 7ETS 86 A A1=v A Ap@AETS 1Fn A A8 @Cc%" ETS 18 A" A# *Also called Kiku 11 AS A'  Generalg " A AG#^@") Designation08197 / 75082A[S A AA#R4Launch date9 Sep 1975l A AM#j>"N ,bCountry of originJapanU A AG#^"H̀Mission_ A5AA#R<"Perigee/Apogee976/1103 kmT AAA#R&Inclination47S5AAA#R$Period106 minfABAM#j2" &JLaunch vehicleN1[AAA#R4"Mass at launch82.5 kg&BAA# <A @A' *O External resourcesA @An Ad=Ap@A' zhttp://yyy.tksc.nasda.go.jp/Home/This/This-e/ets-1_e.html6 @A@A1ow@A@A*EAETS 2Fp@A@A8 @Cc%" ETS 28@A$AA# *Also called Kiku 21 @AUAA'  Generalg $AAAAG#^@") Designation09852 / 77014A\UAABAA#R6Launch date23 Feb 1977lAABAM#j>"N ,bCountry of originJapano"BABAM#jD"H̀‰MissionTelecommunicationsYBALCAA#R0,Geostationary orbitfBACAM#j2" &JLaunch vehicleN1&LCACA# 5CA DA'  End of lifeWCAdDAA#R,"Out of serviceyes& DADA# <dDADA' *O External resourcesd=DA*EA' zhttp://yyy.tksc.nasda.go.jp/Home/This/This-e/ets-2_e.html6DA`EA1s=x`EAEAIAETS 3F*EAEA8 @Cc%" ETS 38`EAEA# *Also called Kiku 41 EAFA'  Generalg EAvFAG#^@") Designation13492 / 82087A[FAFAA#R4Launch date3 Sep 1982lvFA=GAM#j>"N ,bCountry of originJapanu.FAGAG#^\"H̀MissionTelecommunications, experimental_=GAHAA#R<"Perigee/Apogee966/1226 kmVGAgHAA#R*Inclination44.6UHAHAA#R(Period107.2 minfgHA"IAM#j2" &JLaunch vehicleN1&HAHIA# <"IAIA' *O External resourcesd=HIAIA' zhttp://yyy.tksc.nasda.go.jp/Home/This/This-e/ets-3_e.html6IAJA1UJyJAdJANAETS 4FIAdJA8 @Cc%" ETS 48JAJA# *Also called Kiku 31 dJAJA'  Generalg JA4KAG#^@") Designation12295 / 81012A\JAKAA#R6Launch date11 Feb 1981l4KAKAM#j>"N ,bCountry of originJapanUKAQLAG#^"H̀Mission`KALAA#R>"Perigee/Apogee240/20680 kmVQLAMAA#R*Inclination28.2ULA\MAA#R(Period362.4 minfMAMAM#j2" &JLaunch vehicleN2&\MAMA# <MA$NA' *O External resourcesd=MANA' zhttp://yyy.tksc.nasda.go.jp/Home/This/This-e/ets-4_e.html6$NANA12zNAOA AETS 5B NAOA5 :Cc%" ETS 58NA8OA# *Also called Kiku 51 OAiOA'  Generalg 8OAOAG#^@") Designation18316 / 87070A\iOA8AA#R6OA8ANALaunch date27 Aug 1987lOAAM#j>"N ,bCountry of originJapano"8AAM#jD"H̀‰MissionTelecommunicationsh'A{AA#RN,Geostationary orbit150E, inclinedfAAM#j2" &JLaunch vehicleH1{AA% First 3 axis stabilized Japanese satellite with a built in apogee kick motor. It also carried a experimental mobile communications payload.<AтA' *O External resourcesjAiA. ,http://akebono.tksc.nasda.go.jp/ETS-V.htmlhttp://yyy.tksc.nasda.go.jp/Home/This/This-e/ets-5_e.html5тAA'  End of life`iAAA#R>"Out of servicemid-Oct 1997TARAA#R&Causedeorbited&AxA# 8RAA' "(Technical data8xAA' " Specificationsi(AQAA#RP&Prime contractorMitsubishi ElectricXAAA#R.PlatformMitsubishi[QAAA#R4"Mass at launch1081 kgYA]AA#R0 Mass in orbit550 kgOAAA#RLength3 mP]AAA#RWidth2.8 mOAKAA#RHeight2 mYAAA#R0 Stabilization3 axis^KAAA#R:$Design lifetime1.5 years&A(A# 0 AXA'  L-bandS(AAA#R$Transponders2OXAAA#RPower30 WUAOAA#R(Bandwidth10 MHzLA܉AA#RCoverageNorthern Pacific including Philippines, Indonesia and AustraliaVOA2AA#R*EIRP max23.2 dBWR܉AAA#R"Polarization&2AA# 0 AڊA'  C-bandSA-AA#R$Transponders1N ڊA{AA#RPower6 WU-AЋAA#R(Bandwidth20 MHzy8{AIAA#RpCoverageNorthern Pacific (used for a link to NASDA)N ЋAAA#REIRP maxRIAAA#R"Polarization$A A" 6ACA1{JP{CAABETS 6B AA5 :Cc%" ETS 68CAA# *Also called Kiku 61 AA'  Generalg AUAG#^@") Designation23230 / 94056Ah'AAA#RNLaunch date28 Aug 1994 at 22:10 UTlUA)AM#j>"N ,bCountry of originJapanu.AAG#^\"H̀MissionTelecommunications, experimentalu4)AAA#Rh,Geostationary orbitwas expecteAA Ad in 153.8E slotfAAM#j2" &JLaunch vehicleH2!AA- (lUcUWas designed to demonstrate amongst other things ion propulsion and liquid bi-propellant GEO orbit insertion. The payload would have supported mobile communications and inter satellite communication at radio and laser frequencies in preparation for Data Relay and Tracking Satellite systems.In mid-1995 it was reported than successful intersatellite communication had taken place with UARS Later in early 1996 bidirectionel laser communications between JPL and the satellite were carried out.5AA'  End of life_A:AA#R<"Out of service28 Aug 1994nAAA#RCauseUnable to reach GEO: a valve controlling the ergol input in the apogee kick motor (LAPS) was blocked&:AA# <AKA' *O External resourceskAA. ,http://akebono.tksc.nasda.go.jp/ETS-VI.htmlhttp://yyy.tksc.nasda.go.jp/Home/This/This-e/ets-6_e.html8KAA' "(OTechnical data8ATA' " Specifications]AAA#R8&Prime contractorToshibaXTA AA#R.PlatformMitsubishi[AdAA#R4"Mass at launch3800 kgZ AAA#R2 Mass in orbit2000 kg`dAAA#R>Dimension3.0 x 2.0 x 2.8 mZAxAA#R2Solar array30 m spanYAAA#R0 Stabilization3 axis\xA-AA#R6$Design lifetime2 years&ASA# 0 -AA'  S-bandXSAAA#R.(Main transponders1PA+AA#RPower100 Wk*AAA#RTBandwidth20 MHz forward/10 MHz returnZ+AAA#R2Coverage5 spot beamsVAFAA#R*EIRP max31.5 dBWRAAA#R"Polarization&FAA# 0 AA'  C-bandXAFAA#R.(Main transponders4N AAA#RPower8 WUFAAA#R(Bandwidth35 MHzN A7AA#RCoverageTAAA#R&EIRP max35 dBWR7AAA#R"Polarization&AA# =A@A' , Ka-band (20/30 GHz)XAAA#R.(Main transponders6V@AAA#R*Power10 W (TWTA)l+AZAA#RVBandwidth120 MHz forward/30 MHz returnN AAA#RCoverageTZAAA#R&EIRP max48 dBWRANAA#R"Polarization&AtA# <NAA' * O-band (38/43 GHz)XtABA#R.(Main transpondAB Aers1VAjBA#R*Power10 W (TWTA)OBBA#RBandwidthN jBBA#RCoverageN BUBA#REIRP maxRBBA#R"Polarization$UBB" 6BB1V f|BCBhBETS 7B BCB5 :Cc%" ETS 7hEBB# Also called Kiku 7, the two units are called Orihime and Hikoboshi1 CBB'  Generalg BCBG#^@") Designation25064 / 97074B\BBA#R6Launch date27 Nov 1997lCB BM#j>"N ,bCountry of originJapanaBlBG#^4"H̀MissionExperimentalZ BBA#R2"Perigee/Apogee550 kmTlBBA#R&Inclination35L BfBA#RPeriodiBBM#j8" &JLaunch vehicleH2 #5XfBN B' ETS 7 is composed of a chase satellite and a target satellite. Its objectives are to carry out experiments to confirm the basic technologies for rendezvous-docking and space robotics. It will enable future Japanese supply missions to dock reliably with the International Space Station.Success in orbit will be reliant on an internal navigation system which contains three sensors. A GPS receiver will be used to compute the relative positions and speeds of the separated satellite units from 10 km out to the 600 meter final approach stage. The rendezvous laser radar (LR) will then take over, computing the target satellite's position and azimuth from 660 to 2 meters, whereupon the proximity sensor will make final attitude and positional adjustments. Of the three sensing systems, the LR and the proximity sensor represent cutting-edge technology.vB B$ Had solar pannel problems right after launch. This was solved quickly but an automatic shutdown occured on Nov 30.<N B$ B' *O External resourcesd= B B' zhttp://yyy.tksc.nasda.go.jp/Home/This/This-e/ets-7_e.html7$ B B'  O Sub satellite`= B B# zTarget - Orihime, no id number yet. Transmits on 2.22 GHz8 BW B' "(OTechnical data8 B B' " Specifications]W B BA#R8&Prime contractorToshibaN B: BA#RPlatform}< B BA#Rx"Mass at launch2950 kg (chaser: 2540 kg, target: 410 kg)S: B BA#R$ Mass in orbitO BY BA#RDimensionQ B BA#R Solar arrayYY BBA#R0 Stabilization3 axisN BQBA#RDC power^BBA#R:$Design lifetime1.5 yearsQBhB- (ˎWill use Comets to demonstrate inter-orbit links. Transmits on 2.27699 & 2.04425 GHzThe docking system was developed by Mitsubishi.6BB1P}BByGBETS 8B hBB5 :Cc%" ETS 87B#@B# (B#@BhBAlso called ETS N1 BT@B'  GeneralY#@B@BG#^$") Designation`T@B ABA#R>Launch dateplanned in 2002l@ByABM#j>"N ,bCountry of originJapanu. ABABG#^\"H̀MissionTelecommunications, experimentalYyABGBBA#R0,Geostationary orbit_ABBBG#^0" &Launch vehicleH2A&GBBBB# 8BBCB' "(OTechnical data8BBEUropean REtrievable CArrier1 DBB'  Generalg BBG#^@") Designation22065 / 92049B\BzBA#R6Launch date31 Jul 1992m BBM#j@"N ,4"Country of originEurope_zBFBG#^0"H̀MissionScientific^BBA#R:"Perigee/Apogee484/509 kmVFBBA#R*Inclination28.5TBNBA#R&Period94.6 minjBBM#j:" &㨛Launch vehicleSTS 46NBB+ $vtމEureca was an ESA scientific satellite designed to be launched and retrieved by the Space Shuttle. It carried the first European inter-orbit communications (IOC) link to be conducted with Olympus.5BB'  End of lifet-BVBG#^ZԛDecayRetrieved by STS 57 on 1 Jul 1993&B|B# <VBB' *O External resourcesZ3|BB' fhttp://www.esoc.esa.de/external/mso/eureca.html8BJB' "(OTechnical data8BB' " SpecificationsYJBۈBA#R0&Prime contractorMBB[B6BA#R4"Mass at launch4450 kgYۈBBA#R0Payload mass1000 kg`6BBA#R>Dimension4.5 x 2.3 x 2.7 mZBIBA#R2Solar array18 m spanYBBA#R0 Stabilization3 axisTIBBA#R&DC power5000 W&BB# 1 BMB'  Payloadz8BNjBB#Tp*Telemetry and dataS-bandKa-band (experimental/IOC)m+MB4BB#TVRatesuplink: 2 kbpsdownlink: 256 kbps$NjBXB" E4BB1 [0BBBProgram: Europe*StarEXBB, (4" Program: Europe*StarL&B.B& MTelecommunication satellite program lead by Alcatel with Loral. Should use 3 German GEO slots (43, 45 & 47.5E) to beam to southern Africa, Asia, Europe, India and the Middle East. Cost: $300 millionThe program should be operational in early 2000. The first satellite should weigh 3600 kg.8BfB' "(OTechnical data8.BB' " SpecificationsZfBBA#R2&Prime contractorSS/LN BFBA#RPlatform[BBA#R4"Mass at launch3600 kgSFB BA#R$ Mass in orbitB BXBOB[BA#RDimensionQ BBA#R Solar arrayS[BBA#R$ StabilizationTBSBA#R&DC power9500 WUBBA#R($Design lifetimeCSBB$ >Payload provided by Alcatel1 BB'  Ku-bandYBuBA#R0(Main transponders30YBBA#R0,Backup transpondersK uBBA#RPowerOBhBA#RBandwidthN BBA#RCoverageN hBBA#REIRP maxM BQBA#RG/T maxRBBA#R"Polarization&QBB# 1BB1WBNBtBT+BNB) "VȠ$To view this page you need to register&BtB# DNBB1ǃBBBProgram: EuroskywayDtBB, (2" Program: EuroskywayQ+BMB& WTelecommunication program proposed by the Italian firm Alenia Spazio. It would offer large bandwidth for multimedia applications in Europe. It would use Ka-bandThe program would have 5 GEO satellites located at 5, 13, 22, 30 & 39E. The two first should be launched in 2001. The system would cover Europe, the Middle East, Africa, and Western Asia. Each satellite would weigh 4500 kg with 9000 W power onboard and 15 years lifetime. Each satellite would use 700 MHz bandwidth providing 9 Gbps. Each satellite will provide 82,000 channels od 64 kbps. I%BB$ JFinancing is still to be found...1MBB1WBBABT+BB) "VȠ$To view this page you need to register&BAB# BBB10BBIBProgram: EutelsatNABB5 :4xߪk" Program: Eutelsatq6BBB; Dm  QHkSEUropean TELecommunication SATellite, also called ECS (European Communication Satellite)In 1979 the European Space Agency decided to build five ECS satellites whose management were given to the European organization Eutelsat. The Satellites were aimed to respond to the post and telecommunications needs and to transmit EBU's TV channels. To avoid frequencies attribution problems in C-band the satellites were designed to operate in Ku-band. The OTS program had provided test transmissions with small Earth stations using on board powerful transponders.t;BB9 @wQHCIxQH≂Eutelsat was officialy created in 1985. The initial mission was to complete the telephone networks without acting contrary to Intelsat laws. In fact, Eutelsat mainly makes profit with TV channels (65% of its profits).Eutelsat plans to start a commercial branch that would be setup in France before 2001.<BBB' *O External resourcesW0BIB' `http://www.esoc.esa.de/external/mso/ecs.html1BzB1UzBCC?IBB) ",RH(Program: Eutelsat1zBNBd#b"ن"چBۆEutelsat 1F1Eutelsat 1F2Eutelsat 1F3#BB^#F"܆"݆BEutelsat 1F4Eutelsat 1F51NBpCd#b"BpCIB"BEutelsat 2F1Eutelsat 2F2Eutelsat 2F3&BCg#L(($HEutelsat 2F4Eutelsat 2F5-pCCs#Z(((<Hotbird 1Hotbird 2Hotbird 3 C$Cg#@((<Hotbird 4Hotbird 56CCs#l(K($L(HMEutelsat 3F1Eutelsat 3F2Eutelsat 3F3u$CBC[#4(".,0Eutelsat 3 SESATjCC[#(w~WTDF 2$BCC" 1CC1A CCT1CUC# bEutelsat 1's transponder frequency chart (GHz)kCjC#$ * X v  ƀ HorizontalUplinkHorizontalDownlinkTransponderVerticalDownlinkVerticalUplinkBeam)UCC#ڀR"&<10.991667114.291667Euro/West$jCC#ڀH"&<11.075000214.375000East)CoC#ڀR"&<11.158333314.458333Euro/West$CC#ڀH"&<14.491667414.041667West-oCC#ڀZ"&<11.575000514.125000East/Atlantic$Cs C#ڀH"&<11.658333614.208333West)C! C#ڀR"8<14.291667710.991667Euro/West$s C C#ڀH"8<14.375000811.075000East)! Cx C#ڀR"8<14.458333911.158333Euro/West% C" C#ڀJ$:>14.0416671011.491667West)x C C#ڀR$:>14.1250001111.575000Atlantic%" Cz C#ڀJ$:>14.2083331211.658333West$ C#C#ڀH$(>12.5416671314.041667SMS$z CC#ڀH$:>14.0416671412.541667SMSE!#CC$ BNo 12 GHz transponders on 1F11CBC1BBCuDCACC# <Eutelsat 1's specificationsg&BC @CA#RL&Prime contractorBritish AerospaceC @CCQC]@CA#R PlatformECSp. @C@CB#T\"Mass at launchF1: 1050 kgOthers: 1185 kgY]@C&ACA#R0 Mass in orbit585 kgX@C~ACA#R.Payload mass117 kgQ&ACACA#R Length1.9 mP~ACBCA#RWidth1.4 mQACpBCA#R Height2.3 m\BCBCA#R6Solar array13.8 m spanYpBC%CCA#R0 Stabilization3 axisYBC~CCA#R0DC powerEOL: 1000 WZ%CCCCA#R2 Payload power638.5 W\~CC4DCA#R6$Design lifetime7 yearsACCuDC$ :Apogee kick motor: Mage 214DCDC1QDCGC:uDCDC# .Eutelsat 1's Ku-band>DC_ECA#R|0(Main transponders10 in 11 GHz + 2 in 12 GHz (none for F1)ZDCECA#R20,Backup transponders2V_ECFCA#R*0Power20 W (TWTA)UECdFCA#R(0Bandwidth72 MHzoFCGCC#V0,Coverage & EIRP maxAtlantic, West & East spotbeams: 46 dBWEurobeam: 41 dBWSMS beam: 43.5 dBW (not on F1)XdFCnGCA#R.0PolarizationlinearX4GCGC$ hOnly 9 transponders can be active simultaneously1nGCGC1GCSHC\&GCSHC6 Dimension2.8 x 2.2 x 2.5 m\MCNCA#R6Solar array22.4 m spanY[NCOCA#R0 Stabilization3 axisf$NCvOCB#THDC powerBOL: 3000 WEOL: 2890 W]OCOCA#R8$Design lifetime10 yearsYvOC8CA#R0OC8CKC Payload power2090 WZOCCA#R2 G/T-3.5 to +2.5 dB/K$8CC" 1CC1UCCC:C!C# .Eutelsat 2's Ku-bandYCzCA#R00(Main transponders16Z!CԁCA#R20,Backup transponders8VzC*CA#R*0Power50 W (TWTA)?ԁCCB#T~0Bandwidth7 transponders of 72 MHz9 transponders of 36 MHz>*C1CH#`|0,uSӪCoverage & EIRP maxsuper beam: 52 dBWwide beam: 47 dBWXCCA#R.0Polarizationlinear$1CC" 1CރC1AރCCG$C%C# HEutelsat 3's specifications (W24)}<ރCCA#Rx&Prime contractorAerospatiale (with DASA, Alenia & SS/L)[%CCA#R4PlatformSpacebus 3000[CXCA#R4"Mass at launch2700 kgZCCA#R2 Mass in orbit1680 kgYXC CA#R0Dimension2.9 m highZCeCA#R2Solar array30 m spanS CCA#R$ StabilizationYeCCA#R0DC powerEOL: 5840 W]CnCA#R8$Design lifetime12 yearsUCC+ &2!Cost: $680 million for the 3 satellites2 satellites will be launched by Ariane1nCC1WCsCCT+CsC) "VȠ$To view this page you need to register&CC# 1sCʈC1UʈCBCfC@C C# :Eutelsat 3's Ku-band (W24)YʈCcCA#R0(Main transponders24Y CCA#R0,Backup transpondersOcC CA#RPower90 WUC`CA#R(Bandwidth72 MHzs CCH#`"/UCoveragefull coverage of the entire European continent and the Mediterranean Basinsteerable and fixed beamsN `CiCA#REIRP maxRCCA#R"PolarizationFiCBCA#RFrequency10.95-11.7 GHz (18 transp.) & 12.5-12.75 GHz (6 transp.)$CfC" 1BCC1WCCCT+fCC) "VȠ$To view this page you need to register&CC# 1CBC1BCC`*CC6 2416 Oct 1990Oct 19927E7DH Dj#<.0Oct 1992late-199236E!D Dj#BMay 199325.5E, inclined&H D D# 8 D1 D' "(Technical dataQ D D9 B⁎ ^ SpecificationsKu-bandTransponder frequency chartBeacon: 11.44965 GHz=1 D D' , EIRP coverage (dBW)W DO D7 >@ ~⛱~;>Spot beamsEurobeamSMS1 D D1 D Do9O D D6 @Հ4 ԉ(Spot beamsEurobeamSMS1CDDDD1DD:EDo9DD:ED6 DR#t 11.13022AbDDR#t 27A11.146b>DDR#t 11.16422BbDdDR#t 27B11.181aDDR#t11.55432adD&DR#t3711.575aDDR#t11.59533a&DDR#t3811.615bDJDR#t 11.63834AaDDR#t3911.658bJD DR#t 11.67534BaDnDR#t12.52140a DDR#t4512.542anD0DR#t12.56241aDDR#t4612.583a0DDR#t12.60442aDSDR#t4712.625aDDR#t12.64543aSDDR#t4812.666bDwDR#t 12.68844AaDDR#t4912.708bwD:DR#t 12.72844B$D^D" = :DD15$DD EEutelsat 2F3I^DD5 :*xߪk" Eutelsat 2F31 DD'  Generalg D|DG#^@") Designation21803 / 91083A[DDA#R4Launch date7 Dec 1991m |DDDM#j@"N ,4"Country of originEuropeo"DDM#jD"H̀‰MissionTelecommunicationseDDDG#^<"/ۀ0Geostationary orbit16Eq$DDM#jH" &yjLaunch vehicleAtlas CentaurF"DD$ DOperational since 10 Jan 1992.8DD' "(Technical dataDD; D 2ӂ✔7SpecificationsKu-bandTransponder frequency chartBeacons: 11.452570 and 12.541667 GHzEquipped with an S400 apogee engine=DD' , EIRP coverage (dBW)KDOD0 06uSӪWide beamSuper beamK$DD' H Transponder frequency chart (GHz);OD8Dc#v . L HorizontalDownlinkTransponderVerticalDownlinkbDDR#t 25A10.971b8D ER#t 10.98620AD E^DbDnER#t 25B11.005b EER#t 11.01620BbnE2ER#t 11.04921AbEER#t 26A11.055b2EER#t 11.08021BbEXER#t 26B11.095bEER#t 11.13022AbXEER#t 27A11.146bE~ER#t 11.16422BbEER#t 27B11.181a~EAER#t11.55432aEER#t3711.575aAEER#t11.59533aEdER#t3811.615bEER#t 11.63834AadE'ER#t3911.658bEER#t 11.67534Ba'EER#t12.52140aEKER#t4512.542aEER#t12.56241aKE ER#t4612.583aEnER#t12.60442a EER#t4712.625anE0 ER#t12.64543aE ER#t4812.666b0 E ER#t 12.68844Aa ET ER#t4912.708b E ER#t 12.72844B$T E E" = E E1t  E` E:LEEutelsat 2F4I E` E5 :*xߪk" Eutelsat 2F41  E E'  Generalg ` E EG#^@") Designation22028 / 92041B[ ES EA#R4Launch date9 Jul 1992m E EM#j@"N ,4"Country of originEuropeo"S E/ EM#jD"H̀‰MissionTelecommunicationsd E EG#^:"/ۀ0Geostationary orbit7En!/ EEM#jB" &D+Launch vehicleAriane V51F" EGE$ DOperational since 18 Sep 1992.8EE' "(Technical dataaGEE9 B2ӂ✔7SpecificationsKu-bandTransponder frequency chartBeacons: 11.451091 and 12.541667 GHz=EVE' , EIRP coverage (dBW)KEE0 06Z$QuSӪWide beamSuper beamK$VE @E' H Transponder frequency chart (GHz)E @E E9E@Ec#r * H HorizontalUplinkTransponderVerticalDownlinkb @E AER#t 10.97120Ab@ElAER#t 25A10.986b AEAER#t 11.00520BblAE0BER#t 25B11.016bAEBER#t 26A11.049b0BEBER#t 11.05521AbBEVCER#t 26B11.080bBECER#t 11.09521BbVCEDER#t 27A11.133bCE|DER#t 11.14622AbDEDER#t 27B11.163b|DE@EER#t 11.18122BaDEEER#t11.55432a@EEFER#t3711.575aEEcFER#t11.59533aFEFER#t3811.615bcFE&GER#t 11.63834AaFEGER#t3911.658b&GEGER#t 11.67534BaGEJHER#t12.52140aGEHER#t4512.542aJHE IER#t12.56341aHEmIER#t4612.583a IEIER#t12.60442amIE/JER#t4712.625aIEJER#t12.64543a/JEJER#t4812.666bJESKER#t 12.68844AaJEKER#t4912.708bSKELER#t 12.72844B$KE:LE" = LEwLE1wLELE)NEEutelsat 2F5I:LELE5 :*xߪk" Eutelsat 2F55wLELE'  End of life_LETMEA#R<"Out of service24 Jan 1994eLEMEG#^<D+CauseAriane V63 failurepKTME)NE% Was aimed to serve the eastern members in slot 36E.Cost: $200 million: MEcNE1 cNENEwEHotbird 1F)NENE5 :$xߪk" Hotbird 1>cNENE# 6Also called Eutelsat 2F61 NEOE'  Generalg NEOEG#^@") Designation23537 / 95016B\OEOEA#R6Launch date28 Mar 1995m OETEM#j@OETE)NE"N ,4"Country of originEuropeo"OEÀEM#jD"H̀‰MissionTelecommunicationseTE(EG#^<"/ۀ0Geostationary orbit13En!ÀEEM#jB" &D+Launch vehicleAriane V71&(EE# 8EE' "(Technical data|JEpE2 4R2ӂEIRP coverage (dBW)SpecificationsBeacon: 11.44961 GHz horizontalBEE' 6 Ku-band (11.2-11.56 GHz)YpE EA#R0i(Main transponders16ZEeEA#R2i,Backup transponders8V EEA#R*iPower70 W (TWTA)UeEEA#R(iBandwidth36 MHzz3EEG#^fi0RꉂCoverage and EIRP maxsuper wide beam: 49 dBWXEEA#R.iPolarizationlinear[E=EA#R4iUplink12.89-13.25 GHz&EcE# K$=EE' H Transponder frequency chart (GHz);cELEc#v . L HorizontalDownlinkTransponderVerticalDownlink`EER#t11.2211`LE ER#t 211.242`ElER#t11.2623` ĖER#t 411.283`lE,ER#t11.3045`̇EER#t 611.325`,EER#t11.3457`ELER#t 811.366`EER#t11.3879aLE ER#t1011.408aEnER#t11.42811a EϊER#t1211.449anE0ER#t11.47113aϊEER#t1411.492a0EER#t11.51315aESER#t1611.534$EwE" 1SEE1EENwEE6 <2"^Hotbird 1's EIRP1E'E1'EE_)EE6 EA#RB,Geostationary orbitsee belowv)EEM#jR" &yjLaunch vehicleAtlas Centaur #103>EYE& Worth $200 millionIt seems that the satellite has a fuel tank leak, which has been detected by abnormal fuel consumption.: EE- */ۀ LocationYEEm#:   " BeginEndPosition%EEj#J$<>L: 21 Nov 19965 Dec 199629EE.Ej#0"$16 Dec 199613E&ETE# 8.EE' "(OTechnical data=TEE' , EIRP coverage (dBW)IEE0 02\\SuperbeamWidebeam8EJE' " Specificationsi(EEA#RP&Prime contractorMatra Marconi Space\JEEA#R6PlatformEurostar 2000+TEcEA#R&"Mass at launch>EEA#R|Payload mass268 kg: transponders: 192 kg, antennas: 76 kg`cEBEA#R>Dimension2.5 x 1.7 x 2.6 mYEEA#R0 Stabilization3 axiso.BE EA#R\DC powerequinox: 5500 W, solstice: 4988 WYEcEA#R0 Payload power4188 W` EEA#R>$Design lifetime12-15 years?cEE$ 6Telemetry: 2264.818 MHzR+ETE' V Ku-band (11.45-11.7 GHz & 11.7-12.5 GHz)YEEA#R0(Main transponders20[TEEA#R4,Backup transponders10WE_EA#R,Power110 W (TWTA)E:EE#X-Bandwidth20 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)_E6ED#VqCoveragesuper beam: Europe from West to Eastwide beam: from the Canary Islands to the republics South of Russia and Gulf countriesTransponders switchable one by one on each zoneq/:EEB#T^EIRP maxSuperbeam: 52 dBWWidebeam: 49 dBWX6EEA#R.Polarizationlinear|EE$ 6 transponders in 12 GHz can be switched in 11 GHz and the 36 MHz transponders can be operated in half-transponder mode.K$EE' H Transponder frequency chart (GHz)IEE#܀ . L vx HorizontalDownlinkTransponderVerticalDownlinkBandwidthE_F{#ƀ>E_FkE(,.11.55441032/D136 MHzEF{#ƀ>,.37/D211.57516036 MHz_FF{#ƀ>(,.11.59591033/D336 MHzF-F{#ƀ>,.38/D411.61666036 MHzFF{#ƀ>(,.11.65833334/D572 MHz-FaF{#ƀ>,.39/D611.65816036 MHzFF{#ƀ>,.50/E111.72748033 MHzaFF{#ƀ>(,.11.74666051/E233 MHzF/F{#ƀ>,.52/E311.76584033 MHzFF{#ƀ>(,.11.78502053/E433 MHz/FcF{#ƀ>,.54/E511.80420033 MHzFF{#ƀ>(,.11.82338055/E633 MHzcFF{#ƀ>,.56/E711.84256033 MHzF0F{#ƀ<&*,11.86174057E833 MHzFF{#ƀ>,.58/E911.88092033 MHz 0Fe F{#ƀ@*.011.90010059/E1033 MHz F F{#ƀ@.060/E1111.91928033 MHz e F F{#ƀ@*.011.93846061/E1233 MHz F6 F{#ƀ@.062/E1311.95764033 MHz F F{#ƀ@*.011.97682063/E1433 MHz 6 Fl F{#ƀ@.064/E1511.99600033 MHz F F{#ƀ@*.012.01518065/E1633 MHz l F F{#ƀ@.066/E1712.03436033 MHz  F=F{#ƀ@*.012.05354067/E1833 MHz FF{#ƀ@.068/E1912.07272033 MHz =FsF{#ƀ@*.012.09190069/E2033 MHzO+FF$ VUplink: 13.8-14.0 GHz and 17.3-18.1 GHz: sF @F1] @FR@FzFHotbird 3F @FFFFR@F5 :$xߪk" Hotbird 31 @F@F'  Generalg R@F@FG#^@") Designation24931 / 97049A[@FEAFA#R4Launch date2 Sep 1997m @FAFM#j@"N ,4"Country of originEuropeo"EAF!BFM#jD"H̀‰MissionTelecommunicationseAFBFG#^<"/ۀ0Geostationary orbit13En!!BFBFM#jB" &Launch dateplanned in 1999m WG$GM#j@"N ,4"Country of originEuropeo"GGM#jD"H̀‰MissionTelecommunications]$GGA#R8,Geostationary orbit36E\GLGG#^*" &Launch vehicleYGGG#^$Launch site&LGˋG# 8GG' "(Technical dataMˋGPG0 0:L1a契wSpecificationsKu-band1GG1WGՌGGT+PGՌG) "VȠ$To view this page you need to register&GG# 5ՌG0G1ǃ`0GeGGEUVE5 GeG, (" EUVEC 0GG# @ Extreme Ultra Violet Explorer1 eGٍG'  Generalg G@GG#^@") Designation21987 / 92031A[ٍGGA#R4Launch date7 Jun 1992t'@GGM#jN"N ,㹌לCountry of originUnited Statesr%GGM#jJ"H̀_BMissionScientific: Astronomy^GߏGA#R:"Perigee/Apogee503/527 kmVGAGA#R*ߏGAGGInclination28.4TߏGGA#R&Period94.9 minp#AGGM#jF" &p㉂Launch vehicleDelta 2 #210GG% EUVE has completed a survey of the entire celestial sphere in the extreme ultraviolet (UV) spectrum. Spectroscopic observations of individual targets are now made possible for guest observers.<G*G' *O External resourcesGG/ ,http://mahler.brera.mi.astro.it/STRUMENTI/euve.htmlhttp://cea-ftp.cea.berkeley.edu/Education/lessons/indiv/dataflow/HomePage.html8*GG' "(OTechnical dataGG. *q@ĘBased on the MultiMission Spacecraft bus. Telemetry & command via TDRS. Telemetry: 2287.5 MHz (realtime: 1/32 kbps, playback: upto 1024 kbps)Command: 2106.4 MHz (1/0.125 kbps)5G4G1r4G~GGExosJG~G5 :,G" Program: ExosA4GG# <Japanese scientific program1~GG1GoG7GoGH `n!q2q2q2q2Program: ExosExos AExos BExos CExos D7GG15oGGGExos ACoGG5 :G" Exos AM*G6G# TAlso called Kyokko which means "aurora"1 GgG'  Generalg 6GGG#^@") Designation10664 / 78014A[gG)GA#R4Launch date4 Feb 1978lGGM#j>"N ,bCountry of originJapany,)GGM#jX"H̀?vMissionScientific: ionosphere study_GmGA#R<"Perigee/Apogee634/3957 kmVGGA#R*Inclination65.4SmGGA#R$Period134 miniGGM#j8" & Launch vehicleMu 3HZGGA#R2Launch siteKagoshimaZG3GA#R2"Mass at launch103 kg&GYG# <3GG' *O External resourcesX1YGG' bhttp://www.isas.ac.jp/info/sat/kyokko-e3.html7G$G1˂G$GgGHExos BCGgG5 :G" Exos BU2$GG# dAlso called Jikiken which means "magnetosphere"1 gGG'  Generalg GTGG#^@") Designation11027 / 78087A\GGA#R6Launch date16 Sep 1978lTGGM#j>"N ,bCountry of originJapan{.GGM#j\"H̀d;plMissionScientific: magnetophere study`GGA#R>"Perigee/Apogee246/21151 kmVGMGA#R*Inclination31.4UGGA#R(Period370.2 miniMG GM#j8" & Launch vehicleMu 3HZGeGA#R2Launch siteKagoshimaY GGA#R0"Mass at launch92 kga=eG+H$ zInitial orbit: probably 230 G+HGkm x 30558 km x 31 x 525 min<GgH' * External resourcesY2+HH' dhttp://www.isas.ac.jp/info/sat/jikiken-e3.html7gHH1oH:HHExos CCH:H5 :G" Exos CJ'HH# NAlso called Ohzora which means "sky"1 :HH'  Generalg HHG#^@") Designation14722 / 84015A\HxHA#R6Launch date14 Feb 1984lHHM#j>"N ,bCountry of originJapan~1xHbHM#jb"H߲̀-MissionScientific: high atmosphere study^HHA#R:"Perigee/Apogee247/331 kmVbHHA#R*Inclination74.6THjHA#R&Period90.3 minjHHM#j:" & Launch vehicleMu 3S1ZjH.HA#R2Launch siteKagoshimaZHHA#R2"Mass at launch210 kg&.HH# 5HH'  End of lifeVH9HA#R*Decay19 Jul 1989&H_H# <9HH' *O External resourcesX1_HH' bhttp://www.isas.ac.jp/info/sat/ohzora-e3.html7H*H1}G*HmH HExos DCHmH5 :G" Exos D9*HH# ,Also called Akebono1 mHH'  Generalg H>HG#^@") Designation19822 / 89016A\HHA#R6Launch date21 Feb 1989l>H HM#j>"N ,bCountry of originJapan@H HS#v"H̀(d;pl?vMissionScientific: magnetosphere and ionosphere study_ H HA#R<"Perigee/Apogee264/8501 kmV HN HA#R*Inclination75.1U H HA#R(Period185.2 minkN H HM#j<" & Launch vehicleMu 3S 2Z Hh HA#R2Launch siteKagoshimaZ H HA#R2"Mass at launch300 kg&h H H# < H$ H' *O External resourcesY2 H} H' dhttp://www.isas.ac.jp/info/sat/akebono-e3.html<$ H H$ 0Downlink: 400.45 MHz7} H H1a`t H' HILHExosat7 H' H, (" Exosat1 HX H'  Generalg ' H HG#^@") Designation14095 / 83051A\X HHA#R6Launch date26 May 1983m HHM#j@"N ,4"Country of originEuroper%HHM#jJ"H̀_BMissionScientific: astronomya H[HA#R@"Perigee/Apogee340/191878 kmVHHA#R*Inclination72.5V[H@HA#R*Period5442.H@H H1 mins&H@HM#jL" &p㉂Launch vehicleThor Delta #169Z@H@HA#R2"Mass at launch510 kg@HAH% gAstronomy satellite designed to map the position and characteristics of cosmic X-ray sources. The observatory performed some 2000 observations during its operational lifetime.5@HAH'  End of life^AHKBHA#R:"Out of service9 Apr 1986UAHBHA#R(Decay6 May 1986&KBHBH# <BHCH' * External resourcesvBHCH. ,http://www.esoc.esa.de/external/mso/exosat.htmlhttp://astro.estec.esa.nl/SA-general/Archives/Exosat/exosat.html8CHCH' "(OTechnical data8CHDH' " SpecificationsYCHoDHA#R0&Prime contractorMBBN DHDHA#RPlatformZoDHEHA#R2"Mass at launch500 kgXDHoEHA#R.Payload mass120 kgSEHEHA#R$Diameter2.1 mRoEHFHA#R"Height1.35 m[EHoFHA#R4Solar array1.85 x 2 mYFHFHA#R0 Stabilization3 axisXoFH GHA#R.DC powerEOL: 260 W\FH|GHA#R6$Design lifetime2 yearsh' GHGHA#RN"Telemetry/dataS-band (6 W): 8 kbps&|GH HH# qDGH{HH- *  Low energy experiment: 2 grazing incidence (imaging) telescopesU HHHHA#R( Field of view1[{HH+IHA#R4$Collecting area90 cm&HHQIH# c6+IHIH- *l  Medium energy experiment: 8 proportional countersWQIH JHA#R, Field of view1.5]IHhJHA#R8$Collecting area1800 cm& JHJH# G hJHJH' @ Gas scintillator spectrometerWJH,KHA#R, Field of view1.5\JHKHA#R6$Collecting area200 cmZ,KH%LHC#V(X-ray energy ratelow energy 0.04-2 keVmedium energy 1.5-50 keVspectrometer 2-80 keV$KHILH" B%LHLH1x`LHLHHProgram: ExplorerNILHLH5 :4h" Program: ExplorerZ7LH3MH# nAmerican scientific program operated by the US Army.BLHuMH' 6 Beginning of the program+3MHNHg#V#'  (. DateLaunch dateLaunch vehicle'uMHNHX#N#'`81 Feb 1958Explorer 01Jupiter Cs!NHNHR#tB#',5 Mar 1958FailureJupiter C(NHyOHX#P#'`:26 May 1958Explorer 03Jupiter C(NH HX#P#'`:26 Jul 1958Explorer 04Jupiter CyOH HILHt"yOHHR#tD#'.24 Aug 1958FailureJupiter Ct" HHR#tD#'.22 Oct 1958FailureJupiter CqHeHR#t>#'.16 Jul 1959FailureJuno 2qHցHR#t>#'.14 Aug 1959FailureJuno 2}%eHSHX#J#'`:13 Oct 1959Explorer 07Juno 2&ցHyH# 6SHH' O Sub programsiyHH[         AD (Air Density)ADE (Atmospheric Density Explorer)AE (Atmosphere Explorer)DME (Direct Measurement Explorer)EPE (Energetic Particules Explorer)GEOS (Geodetic Earth Orbiting Satellite)IE (Ionosphere Explorer)IMP (Interplanetary Monitoring Probes)1HIH1UIHHH?HH) ",jProgram: ExplorerlIHH#>iʀ```````l`c`d`e`f`g`Āph`i`j`k``````````Āނ`````````````L``````````Explorer 01Explorer 03Explorer 04Explorer 06Explorer 07Explorer 08Explorer 09Explorer 10Explorer 11Explorer 12Explorer 13Explorer 14Explorer 15Explorer 16Explorer 17Explorer 18Explorer 19Explorer 20Explorer 21Explorer 22Explorer 23Explorer 24Explorer 25Explorer 26Explorer 27Explorer 28Explorer 29Explorer 30Explorer 31Explorer 32Explorer 33Explorer 34Explorer 36Explorer 38Explorer 39Explorer 40Explorer 41Explorer 42Explorer 43Explorer 45Explorer 46Explorer 47Explorer 48Explorer 50Explorer 51Explorer 52Explorer 53Explorer 54Explorer 55$HH" < HTH1ԀTHHAHExplorer 01HHH5 :(h" Explorer 011 TH͉H'  Generalg H4HG#^@") Designation00004 / 58001A[͉HHA#R4Launch date1 Feb 1958t'4HHM#jN"N ,㹌לCountry of originUnited Statesy,H|HM#jX"H̀?vMissionScientific: ionosphere study_HۋHA#R<"Perigee/Apogee347/1859 kmV|H1HA#R*Inclination33.2UۋHHA#R(Period107.2 minS1H HG#^" &Launch vehicleJupiter C (Juno 1 from the US Army, 18 t, 21 m tall, 4 stages)_HHA#R<Launch siteCape Canaveral[ HڍHA#R4"Mass at launch14.6 kgn?HTH/ , Rocked realized by Wernher von Braun's team, a german engineer from Peenemnde. He had been working since 1953 at the Redstone Arsenal (Huntsville, Alabama) to design a balistic missile with the help of the Army Ballistic Missile Agency and the Jet Propulsion Laboratory.First American satellite: height 1.2 m, diameter 20 cm. It was in fact the 4th stage of the rocket. Carrying 5 kg of instruments (batteries, radio transmitter, Geiger counter).Has discovered Van Allen belts (radiations beltsڍHTHH around the Earth) because the orbit was more excentric than expected.<ڍHH' *O External resourceshTHH' http://milkman.cac.psu.edu/~cooper/TourOfDC/smithsonian/Air-and-Space/MilestonesofFlight/explor.html5HTH'  End of life_HHA#R<"Out of service23 May 1958j)THHA#RRDecay31 Mar 1970 in Southern Pacific$HAH" < H}H1+}HHIHExplorer 03HAHH5 :(h" Explorer 031 }HH'  Generalg H]HG#^@") Designation00006 / 58003A\HHA#R6Launch date26 Mar 1958t']H-HM#jN"N ,㹌לCountry of originUnited Statesy,HHM#jX"H̀?vMissionScientific: ionosphere study_-HHA#R<"Perigee/Apogee186/2799 kmVH[HA#R*Inclination33.4UHHA#R(Period115.7 mine[HHG#^<" &Launch vehicleJupiter C_HtHA#R<Launch siteCape Canaveral&HH# 5tHH'  End of lifeVH%HA#R*Decay28 Jun 1958$HIH" < %HH1ԀHHQHExplorer 04HIHH5 :(h" Explorer 041 HH'  Generalg HeHG#^@") Designation00009 / 58005A\HHA#R6Launch date26 Jul 1958t'eH5HM#jN"N ,㹌לCountry of originUnited Statesy,HHM#jX"H̀?vMissionScientific: ionosphere study_5H HA#R<"Perigee/Apogee257/1352 kmVHcHA#R*Inclination50.2U HHA#R(Period100.9 minecHHG#^<" &Launch vehicleJupiter C_H|HA#R<Launch siteCape Canaveral&HH# 5|HH'  End of lifeVH-HA#R*Decay23 Oct 1959$HQH" < -HH1+fHHIExplorer 06HQHH5 :(h" Explorer 065H H# $Also called S 21 H;H'  Generalg HHG#^@") Designation00015 / 59004A[;HHA#R4Launch date7 Aug 1959t'HqHM#jN"N ,㹌לCountry of originUnited States|/HHM#j^"H̀d;plMissionScientific: magnetosphere study`qHMHA#R>"Perigee/Apogee245/42400 kmTHHA#R&Inclination47SMH IA#R$Period765 minH IQHm HyIM#j@" &=v퉂Launch vehicleThor Able_ IIA#R<Launch siteCape Canaveral&yII# 5I3I'  End of lifeVIIA#R*Decay30 Jun 1961$3II" < II1]I1I]IExplorer 07HI1I5 :(h" Explorer 071 IbI'  Generalg 1IIG#^@") Designation00022 / 59009A\bI%IA#R6Launch date13 Oct 1959t'IIM#jN"N ,㹌לCountry of originUnited States~1%IIM#jb"H߲̀-MissionScientific: high atmosphere study^IuIA#R:"Perigee/Apogee524/855 kmVIIA#R*Inclination50.3TuIIA#R&Period98.6 minbIIG#^6" &Launch vehicleJuno 2_IIA#R<Launch siteCape CanaveralYI9IA#R0"Mass at launch45 kg$I]I" < 9II1kfII IExplorer 08H]II5 :(h" Explorer 081 II'  Generalg IyIG#^@") Designation00060 / 60014A[IIA#R4Launch date3 Nov 1960t'yIHIM#jN"N ,㹌לCountry of originUnited Statesy,IIM#jX"H̀?vMissionScientific: ionosphere study_HI IA#R<"Perigee/Apogee394/1331 kmVIv IA#R*Inclination49.9U I IA#R(Period102.2 min\v I' IG#^*" &Launch vehicle_ I IA#R<Launch siteCape CanaveralY' I IA#R0"Mass at launch45 kg< I I$ 0First NASA satellite< IW I1_W I I @IExplorer 09H I I5 :(h" Explorer 091 W I I'  Generalg I7 IG#^@") Designation00081 / 61004A\ I IA#R6Launch date16 Feb 1961t'7 I IM#jN"N ,㹌לCountry of originUnited States~1 I IM#jb"H߲̀-MissionScientific: high atmosphere study_ I IA#R<"Perigee/Apogee757/2433 kmV I:IA#R*Inclination38.8S IIA#R$Period118 minl:IIM#j>" &g'KLaunch vehicleScout #4&II# 5ITI'  End of lifeUIIA#R(Decay9 Apr 1964$TI @I" I @I I< IH@I1u5H@I@IDIExplorer 10H @I@I5 :(h" Explorer 106H@I@I# &Also called P-141 @I@I'  Generalg @I^AIG#^@") Designation00098 / 61010A\@IAIA#R6Launch date25 Mar 1961t'^AI.BIM#jN"N ,㹌לCountry of originUnited StatesUAIBIG#^"H̀Missiona .BIBIA#R@"Perigee/Apogee221/181100 kmTBI8CIA#R&Inclination33VBICIA#R*Period5013.9 minq$8CICIM#jH" &p㉂Launch vehicleThor Delta #4&CI%DI# 5CIZDI'  End of lifeV%DIDIA#R*Decay30 Jun 1961$ZDIDI" < DIEI1EIXEIIIExplorer 11HDIXEI5 :(h" Explorer 111 EIEI'  Generalg XEIEIG#^@") Designation00107 / 61013A\EILFIA#R6Launch date27 Apr 1961t'EIFIM#jN"N ,㹌לCountry of originUnited States|/LFI"Perigee/Apogee790/79920 kmVpLI&MIA#R*Inclination33.4VLI|MIA#R*Period1587.3 minq$&MIMIM#jH" &p㉂Launch vehicleThor Delta #6&|MINI# 5MIHNI'  End of lifeVNINIA#R*Decay30 Sep 1963$HNINI" < NINI1NIFOIIExplorer 13HNIFOI5 :(h" Explorer 137NI}OI# (Also called S 55A1 FOIOI'  Generalg }OI!IG#^@") DesignatiOI!INIon00180 / 61022A\OI}IA#R6Launch date25 Aug 1961t'!IIM#jN"N ,㹌לCountry of originUnited States5}IsIM#jj"H̀@0pMissionScientific: observation of meteorites_IҁIA#R<"Perigee/Apogee125/1164 kmVsI(IA#R*Inclination37.7TҁI|IA#R&Period97.5 minl(IIM#j>" &g'KLaunch vehicleScout #6&|II# 5ICI'  End of lifeVIIA#R*Decay28 Aug 1961$CII" < II1dIAIIExplorer 14HIAI5 :(h" Explorer 14@II# :Also called EPE B and S 3A1 AII'  Generalg IIG#^@") Designation00432 / 62051A[ItIA#R4Launch date2 Oct 1962t'IIM#jN"N ,㹌לCountry of originUnited States|/tIdIM#j^"H̀d;plMissionScientific: magnetosphere study`IĆIA#R>"Perigee/Apogee915/96959 kmVdIIA#R*Inclination33.6VĆIpIA#R*Period2157.9 minr%IIM#jJ" &p㉂Launch vehicleThor Delta #13&pII# 5I=I'  End of lifeUIIA#R(Decay1 Jul 1966$=II" < II1I:IIExplorer 15HI:I5 :(h" Explorer 15@IzI# :Also called EPE C and S 3B1 :II'  Generalg zIIG#^@") Designation00445 / 62059A\InIA#R6Launch date27 Oct 1962t'IIM#jN"N ,㹌לCountry of originUnited StatesUnI7IG#^"H̀Mission`IIA#R>"Perigee/Apogee306/17610 kmV7IIA#R*Inclination17.9UIBIA#R(Period314.7 minr%IIM#jJ" &p㉂Launch vehicleThor Delta #14&BIڌI# 5II'  End of lifeVڌIeIA#R*Decay19 Dec 1978$II" < eIōI1dgōI IIExplorer 16HI I5 :(h" Explorer 166ōICI# &Also called S 551 ItI'  Generalg CIێIG#^@") Designation00506 / 62070A\tI7IA#R6Launch date16 Dec 1962t'ێIIM#jN"N ,㹌לCountry of originUnited States57I9IM#jj"H̀@0pMissioI9IInScientific: observation of meteorites_IIA#R<"Perigee/Apogee744/1159 kmT9IIA#R&Inclination52UIAIA#R(Period104.1 minm IIM#j@" &g'KLaunch vehicleScout #14$AII" < II1IVIIExplorer 17HIVI5 :(h" Explorer 176II# &Also called AE A1 VII'  Generalg I$IG#^@") Designation00564 / 63009A[IIA#R4Launch date3 Apr 1963t'$IIM#jN"N ,㹌לCountry of originUnited States~1IqIM#jb"H߲̀-MissionScientific: high atmosphere study^IIA#R:"Perigee/Apogee254/891 kmVqI%IA#R*Inclination57.6TIyIA#R&Period96.1 minr%%IIM#jJ" &p㉂Launch vehicleThor Delta #17&yII# 5IFI'  End of lifeVIIA#R*Decay24 Nov 1966$FII" < II1g9IDIIExplorer 18HIDI5 :(h" Explorer 18]7II& n Interplanetary Monitoring Probe, also called IMP 011 DII'  Generalg I9IG#^@") Designation00693 / 63046A\IIA#R6Launch date27 Nov 1963t'9I IM#jN"N ,㹌לCountry of originUnited States|/IIM#j^"H̀d;plMissionScientific: magnetosphere studya IIA#R@"Perigee/Apogee192/197616 kmVI"Perigee/Apogee191/95590 kmVJJA#R*Inclination33.5TJ) JA#R&Period2097 minr%J JM#jJ" &p㉂Launch vehicleThor Delta #26&) J J# 5 J J'  End of lifeV JL JA#R*Decay30 Jan 1966$ Jp J" < L J J13 J JJExplorer 22Hp J J5 :(h" Explorer 22: J. J# .Also called Beacon B1 J_ J'  Generalg . J JG#^@") Designation00899 / 64064A\_ J" JA#R6Launch date10 Oct 1964t' J JM#jN"N ,㹌לCountry of originUnited States:" J# JS#vt"H̀(CV$?vMissionScientific: Geodesy and ionosphere study_ J JA#R<"Perigee/Apogee872/1053 kmV# J JA#R*Inclination79.7U J-JA#R(Period104.3 minm JJM#j@" &g'KLaunch vehicleScout #32$-JJ" < JJ1JBJCJExplorer 23HJBJ5 :(h" Explorer 237JyJ# (Also called S 55C1 BJJ'  Generalg yJ@JG#^@") DesignationJ@JJ00924 / 64074A[Jx@JA#R4Launch date6 Nov 1964t'@J@JM#jN"N ,㹌לCountry of originUnited States5x@JnAJM#jj"H̀@0pMissionScientific: observation of meteorites^@JAJA#R:"Perigee/Apogee463/980 kmVnAJ"BJA#R*Inclination51.9TAJvBJA#R&Period99.2 minm "BJBJM#j@" &g'KLaunch vehicleScout #33&vBJ CJ# 5BJ>CJ'  End of lifeV CJCJA#R*Decay29 Jun 1983$>CJCJ" < CJCJ13CJOJ9J1MJ"Perigee/Apogee284/10043 kmVOJJA#R*Inclination19.8U9JJA#R(Period205.7 minr%JVJM#jJ" &p㉂Launch vehicleThor Delta #27$JzJ" < VJJ1уJJȅJExplorer 27HzJJ5 :(h" Explorer 27:J8J# .Also called Beacon C1 JiJ'  Generalg 8JЂJG#^@") Designation01328 / 65032A\iJ,JA#R6Launch date29 Apr 1965t'ЂJJM#jN"N ,㹌לCountry of originUnited States:,J-JS#vt"H̀(CV$?vMissionScientific: Geodesy and ionosphere study_JJA#R<"Perigee/Apogee932/1309 kmV-JJA#R*Inclination41.2UJ7JA#R(Period107.7 minm JJM#j@" &g'KLaunch vehicleScout #36$7JȅJ" < JJ1PJLJJExplorer 28HȅJLJ5 :(h" Explorer 28]7JJ& n Interplanetary Monitoring Probe, also called IMP 031 LJچJ'  Generalg JAJG#^@") Designation01388 / 65042A\چJJA#R6Launch date29 May 1965t'AJJM#jN"N ,㹌לCountry of originUnited States|/JJM#j^"H̀d;plMissionScientific: magnetosphere studya JJA#R@"Perigee/Apogee229/261206 kmVJDJA#R*Inclination30.5VJJA#R*Period8419.7 minr%DJ JM#jJ" &p㉂Launch vehicleThor Delta #31&J2J# 5 JgJ'  End of lifeU2JJA#R(Decay4 Jul 1968$gJJ" < JJ1;EJdJnJExplorer 29HJdJ5 :(h" Explorer 298JJ# *Also called Geos 11 dJ͋J'  Generalg J4JG#^@") Designation01726 / 65089A[͋JJA#R4Launch date6 Nov 1965t'4JJM#jN"N ,㹌לCountry of originUnited Statesp#JsJM#jF"H̀CV$MissionScientific: geodesy`JӍJA#R>"Perigee/Apogee1114/2273 kmVsJ)JA#R*Inclination59.4UӍJ~JA#R(Period120.3 minr%)JJM#jJ" &p㉂Launch vehicleThor Delta #34Z~JJJA#R2"Mass at launch175 kg$JnJ" < JJJ1J JJExplorer 30HnJ J5 :(h" Explorer 30J JnJ6JBJ# &Also called IQSY1 JsJ'  Generalg BJJG#^@") Designation01738 / 65093A\sJ6JA#R6Launch date19 Nov 1965t'JJM#jN"N ,㹌לCountry of originUnited StatesU6JJG#^"H̀Mission^J]JA#R:"Perigee/Apogee667/871 kmVJJA#R*Inclination59.7U]JJA#R(Period100.2 minm JuJM#j@" &g'KLaunch vehicleScout #38$JJ" < uJJ1JECJJ6JExplorer 31HJJ5 :(h" Explorer 31AJ^J# <Also called DME A or ISIS X1 JJ'  Generalg ^JJG#^@") Designation01806 / 65098B\JRJA#R6Launch date29 Nov 1965t'JJM#jN"N ,㹌לCountry of originUnited Statesy,RJ?JM#jX"H̀?vMissionScientific: ionosphere study_JJA#R<"Perigee/Apogee502/2857 kmV?JJA#R*Inclination79.8SJGJA#R$Period120 minp#JJM#jF" &#*≂Launch vehicleThor Agena B[GJJA#R4Launch siteVandenberg$J6J" < JrJ1rJJJExplorer 32H6JJ5 :(h" Explorer 32/ rJJ# Also AE B1 JJ'  Generalg JJG#^@") Designation02183 / 66044A\JJA#R6Launch date25 May 1966t'JQJM#jN"N ,㹌לCountry of originUnited States~1JJM#jb"H߲̀-MissionScientific: high atmosphere study_QJ.JA#R<"Perigee/Apogee282/2723 kmVJJA#R*Inclination64.6S.JJA#R$Period116 minr%JIJM#jJ" &p㉂Launch vehicleThor Delta #38&JoJ# 5IJJ'  End of lifeVoJJA#R*Decay22 Feb 1985$JJ" < JZJ1CRZJJmKExplorer 33HJJ5 :(h" Explorer 33]7ZJJ& n Interplanetary Monitoring Probe, also called IMP 041 J0J'  Generalg JJG#^@") Designation02258 / 66058A[0JJA#R4Launch date1 Jul 1966t'JfJM#jN"N ,㹌לCountry of originUnited StatesUJJG#^"H̀Missionc"fJ*KA#RD"PerJ*KJigee/Apogee85228/481417 kmVJKA#R*Inclination40.9W*KKA#R,Period25863.5 minr%KIKM#jJ" &p㉂Launch vehicleThor Delta #39$KmK" < IKK1KK^KExplorer 34HmKK5 :(h" Explorer 34]7KNK& n Interplanetary Monitoring Probe, also called IMP 051 KK'  Generalg NKKG#^@") Designation02817 / 67051A\KBKA#R6Launch date24 May 1967t'KKM#jN"N ,㹌לCountry of originUnited StatesUBK KG#^"H̀Missiona KlKA#R@"Perigee/Apogee242/214379 kmV KKA#R*Inclination67.1VlKKA#R*Period6358.2 minr%KKM#jJ" &p㉂Launch vehicleThor Delta #49&KK# 5KK'  End of lifeUK:KA#R(Decay3 May 1969$K^K" < :KK1RKK KExplorer 36H^KK5 :(h" Explorer 368KK# *Also called Geos 21 KKK'  Generalg KKG#^@") Designation03093 / 68002A\KKKA#R6Launch date11 Jan 1968t'KKM#jN"N ,㹌לCountry of originUnited Statesp#KKM#jF"H̀CV$MissionScientific: geodesy`KR KA#R>"Perigee/Apogee1079/1572 kmWK KA#R,Inclination105.8UR K KA#R(Period112.2 minr% Kp KM#jJ" &p㉂Launch vehicleThor Delta #56$ K K" < p K K1 K KKExplorer 38H K K5 :(h" Explorer 387 KO K# (Also called RAE 11  K K'  Generalg O K KG#^@") Designation03307 / 68055A[ KB KA#R4Launch date4 Jul 1968t' K KM#jN"N ,㹌לCountry of originUnited Statesx+B K. KM#jV"H̀_BMissionScientific: radio-astronomy` K KA#R>"Perigee/Apogee5835/5861 kmW. K KA#R,Inclination120.9U K:KA#R(Period224.3 minr% KKM#jJ" &p㉂Launch vehicleThor Delta #57$:KK" < K K11 KTKDKExplorer 39HKTK5 :(h" Explorer 39Y3 KK& f Atmospheric Density Explorer, also called ADE C1 TKK'  Generalg KQ@KG#^@KQ@KK") Designation03337 / 68066A[K@KA#R4Launch date8 Aug 1968t'Q@K AKM#jN"N ,㹌לCountry of originUnited States~1@KAKM#jb"H߲̀-MissionScientific: high atmosphere study_ AKAKA#R<"Perigee/Apogee670/2538 kmVAKSBKA#R*Inclination80.7UAKBKA#R(Period118.3 minm SBKCKM#j@" &g'KLaunch vehicleScout #63W3BKlCK$ fSphere in aluminum (3.65 m diameter, 7 to 9 kg)5CKCK'  End of lifeVlCKCKA#R*Decay22 Jun 1981$CKDK" < CKWDK1[WDKDKSHKExplorer 40HDKDK5 :(h" Explorer 409WDKDK# ,Also called Injun 51 DK EK'  Generalg DKpEKG#^@") Designation03338 / 68066B[ EKEKA#R4Launch date8 Aug 1968t'pEK?FKM#jN"N ,㹌לCountry of originUnited Statesy,EKFKM#jX"H̀?vMissionScientific: ionosphere study_?FKGKA#R<"Perigee/Apogee677/2494 kmVFKmGKA#R*Inclination80.7UGKGKA#R(Period117.9 minm mGK/HKM#j@" &g'KLaunch vehicleScout #63$GKSHK" < /HKHK11׃HKHKkMKExplorer 41HSHKHK5 :(h" Explorer 41]7HK4IK& n Interplanetary Monitoring Probe, also called IMP 071 HKeIK'  Generalg 4IKIKG#^@") Designation03990 / 69053A\eIK(JKA#R6Launch date21 Jun 1969t'IKJKM#jN"N ,㹌לCountry of originUnited States|/(JKKKM#j^"H̀d;plMissionScientific: magnetosphere studyb!JKzKKA#RB"Perigee/Apogee80374/98159 kmTKKKKA#R&Inclination86VzKK$LKA#R*Period4906.3 minr%KKLKM#jJ" &p㉂Launch vehicleThor Delta #69&$LKLK# 5LKLK'  End of lifeVLKGMKA#R*Decay23 Dec 1972$LKkMK" < GMKMK1[MKMKKExplorer 42HkMKMK5 :(h" Explorer 42@MK/NK# :Also called Uhuru or SAS 11 MK`NK'  Generalg /NKNKG#^@") Designation04797 / 70107A\`NK#OKA#R6Launch date12 Dec 1970t'NKOKM#jN"N ,㹌לCountry of originUnited Statesx+#OKKM#jV"H̀_BMissionScientific: X-rOKKkMKay astronomy^OKyKA#R:"Perigee/Apogee521/570 kmSK̀KA#R$Inclination3TyK KA#R&Period95.5 minm ̀KKM#j@" &g'KLaunch vehicleScout #71Y5 KK$ jDiscovered 200 X sources and the first black hole5KK'  End of lifeUKpKA#R(Decay5 Apr 1979$KK" < pKЂK1׃8ЂKKKExplorer 43HKK5 :(h" Explorer 43]7ЂKuK& n Interplanetary Monitoring Probe, also called IMP 081 KK'  Generalg uK KG#^@") Designation05043 / 71019A\KiKA#R6Launch date13 Mar 1971t' K݄KM#jN"N ,㹌לCountry of originUnited States|/iKYKM#j^"H̀d;plMissionScientific: magnetosphere studyb!݄KKA#RB"Perigee/Apogee1845/203130 kmVYKKA#R*Inclination31.2VKgKA#R*Period5957.9 minr%KنKM#jJ" &p㉂Launch vehicleThor Delta #83&gKK# 5نK4K'  End of lifeUKKA#R(Decay2 Oct 1974$4KK" < KK1qiK1KqKExplorer 45HK1K5 :(h" Explorer 457KhK# (Also called SSS 11 1KK'  Generalg hKKG#^@") Designation05598 / 71096A\K\KA#R6Launch date15 Nov 1971t'KЉKM#jN"N ,㹌לCountry of originUnited StatesU\K%KG#^"H̀Mission`ЉKKA#R>"Perigee/Apogee272/18149 kmU%KڊKA#R(Inclination3.2UK/KA#R(Period322.8 minm ڊKKM#j@" &g'KLaunch vehicleScout #77&/K‹K# 5KK'  End of lifeV‹KMKA#R*Decay10 Jan 1992$KqK" < MKK18GKKiKExplorer 46HqKK5 :(h" Explorer 465K*K# $Also called MTS1 K[K'  Generalg *KKG#^@") Designation06142 / 72061A\KA#R6Launch date13 Aug 1972t'KKM#jN"N ,㹌לCountry of originUnited States5KKM#jj"H̀@0pMissionScientific: observation of meteorites^KrKA#R:"Perigee/Apogee492/811 kmVKȏKA#R*Inclination37.7TrK(KA#R&ȏK(KqKPeriod97.7 minm ȏKKM#j@" &g'KLaunch vehicleScout #79&(KK# 5KK'  End of lifeUKEKA#R(Decay2 Nov 1979$KiK" < EKK1iKKKExplorer 47HiKK5 :(h" Explorer 47]7KJK& n Interplanetary Monitoring Probe, also called IMP 091 K{K'  Generalg JKKG#^@") Designation06197 / 72073A\{K>KA#R6Launch date23 Sep 1972t'KKM#jN"N ,㹌לCountry of originUnited States|/>K.KM#j^"H̀d;plMissionScientific: magnetosphere studyd#KKA#RF"Perigee/Apogee201100/235600 kmV.KKA#R*Inclination17.2UK=KA#R(Period17670 minr%KKM#jJ" &p㉂Launch vehicleThor Delta #90$=KK" < KK1G킗KWKKExplorer 48HKWK5 :(h" Explorer 487KK# (Also called SAS 21 WKK'  Generalg K&KG#^@") Designation06282 / 72091A\KKA#R6Launch date15 Nov 1972t'&KKM#jN"N ,㹌לCountry of originUnited States|/KrKM#j^"H̀_BMissionScientific: gamma-ray astronomy^KKA#R:"Perigee/Apogee526/526 kmSrK#KA#R$Inclination1TKwKA#R&Period95.2 minm #KKM#j@" &g'KLaunch vehicleScout #81&wK K# 5K?K'  End of lifeV KKA#R*Decay20 Aug 1976$?KK" < KK1K=K LExplorer 50HK=K5 :(h" Explorer 50]7KK& n Interplanetary Monitoring Probe, also called IMP 101 =KK'  Generalg K2KG#^@") Designation06893 / 73078A\KKA#R6Launch date26 Oct 1973t'2KKM#jN"N ,㹌לCountry of originUnited States|/K~KM#j^"H̀d;plMissionScientific: magnetosphere study>KKB#T|"Perigee/Apogee141185/288857 kmmid-1996: 189024/247267 kmV~KTKA#R*Inclination28.7j(KKB#TPPeriod17279 minmid-1996: 17646 minr%TK0KM#jJ" &p㉂Launch vehicleThor Delta #97&KVK# 80KK' "(OTechnical datab>VK L$ |Telemetry: 137.98 & 136.8 MHz (32 kbps)Command: 148.98 MHzK LK< KHL1킗XHLLLExplorer 51H LL5 :(h" Explorer 516HLL# &Also called AE C1 LL'  Generalg L^LG#^@") Designation06977 / 73101A\LLA#R6Launch date16 Dec 1973t'^L.LM#jN"N ,㹌לCountry of originUnited States~1LLM#jb"H߲̀-MissionScientific: high atmosphere study_.L LA#R<"Perigee/Apogee155/4306 kmVLaLA#R*Inclination68.1U LLA#R(Period132.5 minr%aL(LM#jJ" &p㉂Launch vehicleThor Delta #99&LNL# 5(LL'  End of lifeVNLLA#R*Decay12 Dec 1978$LL" < L9L1q9LL LExplorer 52HLL5 :(h" Explorer 5299LL# ,Also called Hawkeye1 LL'  Generalg LRLG#^@") Designation07325 / 74040A[LLA#R4Launch date3 Jun 1974t'RL!LM#jN"N ,㹌לCountry of originUnited StatesULvLG#^"H̀Missiona !LLA#R@"Perigee/Apogee469/125569 kmTvL+LA#R&Inclination89TLLA#R&Period3032 minm +LLM#j@" &g'KLaunch vehicleScout #87&L L# 5LG L'  End of lifeV L LA#R*Decay30 Apr 1978$G L L" < L L1X LE LLExplorer 53H LE L5 :(h" Explorer 537 L| L# (Also called SAS 31 E L L'  Generalg | L LG#^@") Designation07788 / 75037A[ Lo LA#R4Launch date7 May 1975t' L LM#jN"N ,㹌לCountry of originUnited Statesx+o L[ LM#jV"H̀_BMissionScientific: X-ray astronomy^ L LA#R:"Perigee/Apogee498/507 kmS[ L LA#R$Inclination3T L` LA#R&Period94.7 minm L LM#j@" &g'KLaunch vehicleScout #91&` L L# 5 L(L'  End of lifeU L}LA#R(Decay9 Apr 1979$(LL" < }LL1L%LCLExplorer 54HL%L5 :(h" Explorer 546L[L# &Also called AE D1 %LL'  Generalg [L @LG#^@") Designation08353 / 75096AL @LL[Lg@LA#R4Launch date6 Oct 1975t' @L@LM#jN"N ,㹌לCountry of originUnited States~1g@LYALM#jb"H߲̀-MissionScientific: high atmosphere study_@LALA#R<"Perigee/Apogee151/3819 kmVYALBLA#R*Inclination90.1UALcBLA#R(Period126.8 mins&BLBLM#jL" &p㉂Launch vehicleThor Delta #115&cBLBL# 5BL1CL'  End of lifeVBLCLA#R*Decay12 Mar 1976$1CLCL" < CLCL1CL/DLHLExplorer 55HCL/DL5 :(h" Explorer 556CLeDL# &Also called AE E1 /DLDL'  Generalg eDLDLG#^@") Designation08440 / 75107A\DLYELA#R6Launch date20 Nov 1975t'DLELM#jN"N ,㹌לCountry of originUnited States~1YELKFLM#jb"H߲̀-MissionScientific: high atmosphere study_ELFLA#R<"Perigee/Apogee154/3002 kmVKFLGLA#R*Inclination19.7UFLUGLA#R(Period117.7 mins&GLGLM#jL" &p㉂Launch vehicleThor Delta #117&UGLGL# 5GL#HL'  End of lifeVGLyHLA#R*Decay10 Jun 1981$#HLHL" AyHLHL1( tHL'ILLEXPRESS (German)IHL'IL2 40"  EXPRESS (German)E"HLlIL# DEXPeriment REentry Space System1 'ILIL'  GeneralflILJLG#^>") Designationnone assignedh'ILkJLA#RNLaunch date15 Jan 1995 at 13:45 UTn!JLJLM#jB"N , Country of originGermanyq*kJLJKLG#^T"H̀MissionExperimentation of materials^JLKLA#R:"Perigee/Apogee110/250 kmTJKLKLA#R&Inclination33L KLHLLA#RPeriodkKLLLM#j<" & Launch vehicleMu 3S 2ZHLL MLA#R2Launch siteKagoshimaZLLgMLA#R2"Mass at launch765 kg{ MLL% The payload used a Russian-built reentry vehicle and the launch was carried out by the Japanese ISAS space agency. It was due to land in the Australian desert after a five day flight, but the TVC (thrust vector control) on the second stage malfunctioned 103 seconds after launch, and the fourth stage and payload entered a 110 x 250 km x 33 deg orbit, instead of the intended 270 x 380 km one. This failure was probably due to second-stage attitude-control oscillations that exhausted attitude-control fuel. The reentry capsule decay in Ghana whereas the service module reentered over the Pacific on its second orbit of the EagMLLHLrth. gMLL% eThe reentry vehicle carried two CATEX materials processing ovens, and three German (CETEX, PYREX and RAFLEX) and one Japanese (RTEX) heat shield material reentry experiments.5LL'  End of lifeVLuLA#R*Decay15 Jan 1995$LL" AuLځL1J`焚ځL'L@LProgram: ExpressML'L5 :2c 9" Program: ExpressځLL> JuMo7U=".Also called GlavstarRussian telecommunication program replacing Gorizont. Satellite are owned by Informcosmos and operated by Intersputnik.Only the 2 first satellites are completely Russian made. New series should start with:- Express A: 1 satellite to be launched in 1999, 12 C-band and 5 Ku-band transponders, payload provided by Alcatel. 2 other satellites are planned- Express K: 3 satellites launched in 1999 & beyond: K1 should be based on a Spacebus 3000B with 52 transponders (32 C-band & 20 Ku-band); K2 should be similar to Eutelsat 3 Sesat and K3 a satellite jointly designed by NPO PM & Aerospatiale. This association of manufacturers is known ad the Troika Consortium.'LЅL( - Express 2000: 1 satellite, payload provided by Hughes, 24 transpondersThe Express slots (reservation names, not satellites) are:VL&LA#R*jExpress 0137.5WTЅLzLA#R&jExpress 0214WT&LΆLA#R&jExpress 0311WTzL"LA#R&jExpress 0440ETΆLvLA#R&jExpress 0553ET"LʇLA#R&jExpress 0680ETvLLA#R&jExpress 0790EVʇLtLA#R*jExpress 0896.5EULɈLA#R(jExpress 09103EUtLLA#R(jExpress 10140EUɈLsLA#R(jExpress 11145EULȉLA#R(jExpress 12155WTsLLA#R&jExpress 1399E$ȉL@L" 1LqL1qLيLh.@LيL: D\~wJ7J7Program: ExpressExpress 1Express 21qL L1z L\L=يLGL# 4Express' specifications\ LLA#R60&Prime contractorNPO PMs,GLLG#^X0PlatformNPO Express (similar to GALS)[LqLA#R40"Mass at launch2500 kgSLČLA#R$0 Mass in orbitSqLLA#R$0Diameter3.6 mQČLhLA#R 0Height6.1 mg&LύLA#RL0Solar arraytwin panels, 21 m spanYhL(LA#R00 Stabilization3 axisTύL|LA#R&0DC power2000 W\(L؎LA#R60$Design lifetime5 yearsxO|L\L) Equipped with an advanced Xenon ion engine that reduces the amount of propellant needed to fine-tune the initial orbit and perform station-keeping maneuvers (SPT 100 , 8 units per satellite (including redundances) produced by Fakel CIS).Beacons: 11.40؎L\LيL0 GHz (power: 0.1 W; EIRP: 14.5 dBW) and 3.800 GHz (power: 0.2 W; EIRP: 9 dBW)1؎LL1 L(LF#\LL# FExpress antenna's specificationshLL#_yxuM  : h   AntennaFrequency bandFunction / Gain maxCoverageBeam widthSteerability (degrees)'LL#N_yxu  4 North/SouthWest/East0LpL#`_yxu &6HTA1CTX / 19.0global17x17nonenone0L6L#`_yxu &2@NA2CTX / 30.0spot5x57.3/55.5/5.56pLL#l_yxu &BT`A3CTX / 20.7quasi global15x15nonenone66LL#l_yxu &>N`A4CTX / 26.5elliptical5x117.3/7.3none6LL#l_yxu &BT`A5CTX / 20.7quasi global15x15nonenone6LfL#l_yxu &>N`A6CTX / 26.5elliptical5x117.3/7.3none/L+L#^_yxu &6FRA7CRX / 19.0global17x17nonenone6fLL#l_yxu &>N`A8CRX / 26.5elliptical5x117.3/7.3none8+LL#p_yxu 6BP^A9KuRX and TX / 30.0spot5x57.3/55.5/5.5c9L(L* $raSee also the transponder/antenna connection diagram1LYL1UYLLL5(LL# $Express' C-bandYYLLA#R00(Main transponders10YL@LA#R00,Backup transpondersKLLB#T0Power9 transponders of 10.5 W (TWTA)1 transponder (#6) of 65 W (TWTA)=@LLLB#Tz0Bandwidthall transponders: 34 MHztransponder #6: 40 MHzL_Lc#a002UCoverage andEIRP maxtransponder #6:global beam (A1): 35.6 dBWspot beam (A2): 46.1 dBW2 quasi global beams (A3 & A5): 28.9 or 31 dBW2 zone beams (A4 & A6): 34.7 dBWn,LLLB#TX0Polarizationuplink: LHCPdownlink: RHCP$_LL" 1L"L1U"LMM6LXL# &Express' Ku-bandX"LLA#R.0(Main transponders2YXL LA#R00,Backup transpondersVL_LA#R*0Power60 W (TWTA)U LLA#R(0Bandwidth34 MHzs2_L3MA#Rd00Coverage aL3MLnd EIRP maxspot beam (A9): 39.2 dBWh&LMB#TL0Polarizationuplink: Vdownlink: H$3MM" 1MM1UMi M MP-M@M# ZExpress' transponder frequency chart (GHz)0 MpM'  C-band<@M2M#܀x|xx  < ^` LHCPUplinkTransponderRHCPDownlinkComments1pMM{#ƀb|xx&(6.00063.675global or spot beam, 40 MHz/2MM{#ƀ^|xx&(6.05073.725quasi global or zone beam/M2M{#ƀ^|xx&(6.10083.775quasi global or zone beam/MM{#ƀ^|xx&(6.15093.825quasi global or zone beam02MM{#ƀ`|xx(*6.200103.875quasi global or zone beam0M2M{#ƀ`|xx(*6.250113.925quasi global or zone beam(MM{#ƀP|xx(*6.300143.975zone or spot beam02MM{#ƀ`|xx(*6.350154.025quasi global or zone beam(M#M{#ƀP|xx(*6.400164.075zone or spot beam0MM{#ƀ`|xx(*6.450174.125quasi global or zone beam1 #MM'  Ku-band9M Mc#r . L HorizontalDownlinkTransponderVerticalUplinkgM MR#t*11.5251214.325g Mi MR#t*11.6752014.425$ M M" 1i M M1 M M^. M M0 0^"aExpress' transponder/antenna connections: MV M1UV M MAMExpress 1F M M5 :$c 9" Express 11 V M M'  Generalg M4 MG#^@") Designation23319 / 94067Ah' M MA#RNLaunch date13 Oct 1994 at 16:19 UTj4 M MM#j:"N , Country of originCISn Mt MP#p<(o7U=OperatorIntersputniko" M MM#jD"H̀‰MissionTelecommunicationsy,t M\MM#jX"/ۀ04Geostationary orbitExpress-02, 14Wo" MMM#jD" &㉓gLaunch vehicleProton #227E!\MM$ BTest carried out in 71E slot8MHM' "(Technical dataM@ML hPvva&Ve ꉂSpecificationsAntenna specificationsTransponder/Antenna connectionsC-bandKu-bandTransponderHM@M M Frequency Chart=HM\@M' , EIRP coverage (dBW)g@MAM> LOt|72t|70t|77t|7C-band, quasi-global (A3 & A5)C-band, hemispheric (A4)C-band, spot (A2)Ku-band, spot (A9)1\@M2AM12AMAMk5AMAM6 J7"cExpress 1's C-band EIRP: spot A2Add 7.9 dBW for transponder #61AM}BM1}BMBMe/LBMBM6 <`J7"dExpress 1's C-band EIRP: hemispheric A41}BMCM1CMrCM_)BMrCM6 C-band, quasi-global (A3)C-band, hemispheric (A4)Ku-band, spot (A9)10IMIM1IMQJMk5IMQJM6 "Perigee/Apogee222/35263 kmVMmMA#R*Inclination26.4SMMA#R$Period621 min}0mM=MM#j`" &yjLaunch vehicleAtlas Centaur #111 + IABSMM. *1SCadets and Faculty of the United States Air Force Academy, in cooperation with University of Colorado-Colorado Springs have designed this satellite=MMxM. It was attached to the upper stage.This mission, named Falcon Gold, will be responsible for sampling the Global Positioning System (GPS) signal from behind the GPS constellation and downlinking spectrum samples to ground stations for post processing.<=MKM' *O External resourcesmFMM' http://www.uccs.edu/~dasipple/masters/falcon_gold/falcon_gold.html5KMM'  End of life^MKMA#R:"Out of service9 Nov 1997n-MMA#RZCausebatteries dead (normal termination)K KMMA#RDecayZ5M^M% jEstimated lifetime: 3 weeksDownlink: 400.475 MHz?MM1 MMbMProgram: FasatK^MM5 :.o " Program: FasatMM. *Uw6"Fuerza Aerea de chile SatelliteFirst Chilean satellite program. Purpose: remote sensing and telecommunication experiments4 satellites are planned in this program<MM' *O External resourcesf?MbM' ~http://www.ee.surrey.ac.uk/EE/CSER/UOSAT/fasat/mission.html1MM1MMi/bMM: D^˝3д%=JUProgram: FasatFasat AlfaFasat Bravo; M7M1K &7M~MNFasat AlfaGM~M5 :&o " Fasat Alfa1 7MM'  GeneralA~MDMT#x")* >w|Designationn/a / 95046AFailed to separate from Sich 1h'MMA#RNLaunch date31 Aug 1995 at 06:50 UTlDMMM#j>"N ,w6"Country of originChile@MMM#j" OperatorChilean Air Force (FACH: Fuerza Aerea de Chile)kMMM#j<"H̀郉MissionRemote sensingr1MMA#Rb"Perigee/Apogeeintended: 1050 km, polar orbitQMMA#R InclinationL MMA#RPeriodr%MMM#jJ" &ቂLaunch vehicleCyclone 3 #114`MM) First Chilean satelliteInvestigation of the failure showed a British docking mechanism had been at fault.The satellite carried five grams of Chilean soil on board. It was to transmit regular information on ultraviolet radiation and the ozone layer over the antarctic. It was also to image the Chilean territory and carry out educational experiments for children with informative bulletins. The other 3 experiments, which would have been regularly carried out by Fasat Alfa, would have ment working with other satellite complexes, for the transmission and storage of data and space navigation systems.pKMM% When FACH proposed the construction of the first Chilean satellite in 1993, negotiations were arranged with Mexican, U.S. and British specialists. Surrey Satellite Technology Limited (SSTL) offered the most tempting deal to the Chileans, offering joint construction of the probe, technology transfer, and postgraduate training for the FACH technicians. The satellite was built using parts built by the Chilean National Aeronautical Company (ENAER), a branch of FACH, along with space computer technology donated by the Lockheed Company of the United States for experimental purposes.8MM' "(OTechnical data8M N' " SpecificationsM NMZMfNA#R2&Prime contractorSSTLS NNA#R$PlatformUOSATYfNNA#R0"Mass at launch50 kgSNeNA#R$ Mass in orbit^NNA#R:Dimension70 x 36 x 36 cmQeNNA#R Solar arraySNgNA#R$ StabilizationN NNA#RDC power\gNNA#R6$Design lifetime6 yearsjNN$ It has a six meters long stabilization beam with a weight in its tail which will unfold once in orbit.< NN16N#N NFasat BravoHN#N5 :(o " Fasat Bravo1 NTN'  GeneralY#NNG#^$") Designation`TN NA#R>Launch dateplanned in 1996lNyNM#j>"N ,w6"Country of originChile@ NNM#j" OperatorChilean Air Force (FACH: Fuerza Aerea de Chile)ayNgNG#^4"H̀MissionScientific: TNNA#R&"Perigee/ApogeeQgN NA#R InclinationL NXNA#RPeriod\ NNG#^*" &Launch vehicle^XNNG#^.'CMLaunch siteZenitYNkNA#R0"Mass at launch50 kgyPN N) Based on a new bus: micronsat (30 kg)approx cost of the satellite: $2 millionFASat-Bravo is designed to monitor the destruction of the ozone layer above Chile. The sophisticated satellite will also take images of the Earth's surface and will carry an educational communications experiment for universities and schools in Chile. 1kN N1W Ni N NT+ Ni N) "VȠ$To view this page you need to register& N N# @i N N1/w N N:HNProgram: FaisatL N N5 :0 K" Program: Faisat! N<N4 6wbOwbOLittle LEO satellite project from Final Analysis. It should provide global store and forward data communications.The constellation of 26 satellites (plus 4 spares) will be operated by FACS (Final Analysis Communication Services). This system is called infosat. Each of the launches can host a secondary payload. It enables experiments to be flown without financial risk (payment after orbit achievement), 25 kg max. FCC authorized on 1st April 1998.FAI plans to launch a constellation of 26 satellites 4 planes of six each at 66, plus 2 birds in individual 83 orbits for polar coverage to build a complete low data rate LEO comsat system; Russian launchers will be used throughout (Cosmos). The network should be fully deployed in 2001.A N}N' 4O Faisat-Coscon agreementr<N-AN2 2wbOwbOAlliance (Oct 1995) of Final Analysis & Polyot Enterprises for global mobile and fixed satellite communications. They intend to manufacture and launch small satellites into low earth orbit. The alliance also intends to market mobile and fixed satellite communications on a global basis with service providers to be selected. The allia}N-AN Nnce is named FAISAT(TM)-COSCON after the planned commercial satellites of the two companies.Polyot will be the service provider in Russia and the CIS countries. Final Analysis will provide training in business development, marketing and sales to Polyot for their commercial services.]}NBN' They will deliver advanced digital data services (non-voice) to include delivery of low-cost applications for SCADA, asset tracking and environmental monitoring, messaging and e-mail.The first experimental satellite is due early 1996. The launching services will be provided by Polyot: 4 dedicated Cosmos rockets (26 satellites to be launched)1 -ANBN' O Contactb4BNDCN. ,h  Polyot (Omsk, Russia)Tel/Fax: +7-3812-579-201&BNjCN# 8DCNCN' "(OTechnical data0 jCNCN' O UplinkP&CN"FN* "M148.0-149.9 MHz (shared) & 149.9-150.05 MHz with restrictions:148-148.250 MHz: shared with Leo One, Orbcomm and E-sat148.750-148.855 MHz: shared with Leo One, Orbcomm and E-sat148.855-148.905 MHz: may be used if E-sat does not use it, and if so must be shared with Leo One and Orbcomm148.905-148.955 MHz: may be used if S80-1 does not use it, and if so must be shared with Leo One and Orbcomm148.955-148.810 MHz: shared with Leo One and Orbcommexcluded: 149.585-149.635 MHz for exclusive use of Orbcomm until relocation in the 150-150.05 MHz2 CNTFN' O Downlink"FN:HN' 137.0-138.0 MHz (shared) & 400.15-401.0 MHz (shared) with restrictions:137.025-137.175 MHz & 137.825-138.00 MHz: used by NOAA, those bands can be used on a secondary basis with time-sharing with NOAA and E-sat137.333-1.4125 MHz, 137.475-137.525 MHz, 137.595-137.645 MHz, and 137.753-137.787 MHz: used by NOAA, those channels must be time-shared with NOAA and E-sat400.505-400.5517 MHz and 400.5983-400.645 MHz: time-shared with VITA's system1TFNkHN1kHNHNy8:HNHNA Rpǥ #aRaProgram: FaisatFaisat 1Faisat 1AFaisat 2V9kHNIN1wAINbINNNFaisat 1EHNbIN5 :" K" Faisat 11 ININ'  Generalg bINING#^@") Designation23465 / 95002Ch'INbJNA#RNLaunch date24 Jan 1995 at 03:54 UTt'INJNM#jN"N ,㹌לCountry of originUnited Statesq*bJNGKNG#^T"H̀MissionExperimental: communications_JNKNA#R<"Perigee/Apogee967/1021 kmVGKNKNA#R*Inclination82.9SKNOLNA#R$Period105 mineKNLNG#^<" &Launch vehicleCosmos 3C_OLNMNA#R<Launch sitePlesetsk LC132ZLNmMNA#R2"Mass at launch115 kg;MNNN' )This is a prototype of the satellites to form the infosat network. This bird was modified by FAI from an existing satellite bus whose mission was cancelled (probably a DARPA satellite). The satellite also carries a small thermal-control experiment for USAF Phillips Lab.: mMNNN19 QNN(ON9NFaisat 2vFNN(ON5 :$ K" Faisat 2V<NNdON# 2Also called Vitasat 1R1 (ONON'  Generalg dON NG#^@") Designation24954 / 97052BON NNN\ONhNA#R6Launch date23 Sep 1997t' N܀NM#jN"N ,㹌לCountry of originUnited Stateso"hNKNM#jD"H̀㓉MissionTelecommunications[܀NNA#R4"Perigee/Apogee1000 kmTKNNA#R&Inclination83SNMNA#R$Period105 mineNNG#^<" &Launch vehicleCosmos 3M_MNNA#R<Launch sitePlesetsk LC132aNN5 8n3x;Should have been launched in April 1997 with Cosmos 2341 Launch cost approx. $100,000 Power problems have been reported when operating in earth's shadowEquipped with a VHF/UHF scanner to map the use of frequencies below 1 GHz.It carries the VITA secondary payload. It enables the delivery back and forth of email through gateways around the world. The payload is based on a Loral RS 6000 Command ad Data Handling processor with 16 MB of storage. Uplink in the 148-149.9 MHz band, Downlink tunable in the 400-401 MHz band, nominal downlink: 400.55 MHz RHCP 1 active transponder (+ 1 spare) of 15 W8N߅N' "(OTechnical data8NN' " SpecificationsV߅NmNA#R*&Prime contractord#NцNA#RFPlatformpiggyback bus (100 kg)\mN-NA#R6"Mass at launch114.5 kgSцNNA#R$ Mass in orbitu4-NNA#Rh*Dimension deployed1.8 m diameter x 6.8 m lengthf%N[NA#RJ Stabilizationgradient stabilizedRNNA#R"DC power75 W\ NA#R6$Design lifetime5 years0N9N+ $ From earth mobile equipment: Uplink: 455-456 and 459-460 MHz, Downlink: 400.62 MHz and 400.55 MHz, GMSK modulation, with Forward Error Correction, 4800 and 9600 bpsCommand: 148.7 MHz ?Uplink to satellite: up to 19.2 kbps, Downlink from satellite: up to 128 kbps (256 kbps in the dedicated bus version). The satellite carries a frequency scanner to dynamically select free spectrum (1 MHz scan in 300 Hz segments every second)Has an on-board GPS receiver. Data is handled by a RISC 6000 processor, 160 MB RAM: NsN1AsNNNFaisat 1aF9NN5 :$ K" Faisat 1A1 sNN'  GeneralYNCNG#^$") Designation`NNA#R>Launch dateplanned in 2000t'CNNM#jN"N ,㹌לCountry of originUnited Statesq*NNG#^T"H̀MissionExperimental: communications[NNA#R4"Perigee/Apogee1000 kmTN7NA#R&Inclination83L NNA#RPeriode7NNG#^<" &Launch vehicleCosmos 3CYNANA#R0Launch sitePlesetsk>NN$ 4RA Ascending Node: 905ANN1 N NNFAST5 N N, (" FASTN NNX5NdN# jFast Auroral Snapshot Explorer, also called SMEX 21 NN'  Generalg dNNG#^@") Designation24285 / 96049A\NXNA#R6Launch date21 Aug 1996t'NNM#jN"N ,㹌לCountry of originUnited States|/XNHNM#j^"H̀d;plMissionScientific: magnetosphere study_NNA#R<"Perigee/Apogee350/4200 kmTHNNA#R&Inclination83SNNNA#R$Period133 mino"NNM#jD" &GKTLaunch vehiclePegasus #13NNzN% 1The spacecraft will probe the physical processes that produce auroras and add signifcantly to the understanding of our near-Earth space environment.<NN' *O External resourceszNN= Hehttp://sunland.gsfc.nasa.gov/smex/fast/http://plasma2.ssl.berkeley.edu/fast/http://www510.gsfc.nasa.gov/smex/fastpg.htmhttp://www-ssc.igpp.ucla.edu/fast/Welcome.html8NN' "(OTechnical data8NN' " SpecificationsVNkNA#R*&Prime contractorN NNA#RPlatformZkNNA#R2"Mass at launch191 kgWNjNA#R,Payload mass51 kgXNNA#R.DimensionoctogonalQjNNA#R Solar arrayj)N}NA#RR Stabilizationspin stabilized, 12 rpmRNNA#R"DC power52 W[}N*NA#R4$Design lifetime1 yearxNN, &Telemetry: 2215.0 MHz (realtime: 4 kbps, playback: 900/1500/2250 kbps)Command: 2039.65 MHz (realtime: 2 kbps)Instruments:Electric Field Experiment: to provide data on plasma density and electron temperatureMagnetic Field Experiment: 2 magnetometers Time-of-Flight Energy Angle Mass Spectrograph (TEAMS)Electrostatic Analyzers (ESA): measurements from 3 eV to 30 KeV: *NN1ww|NBNNFirewheel:NBN, (" Firewheel5NwN'  End of life_BNNA#R<"Out of service23 May 1980k$wNANG#^H&+CauseExplosed with Ariane L02G#NN$ FWas operated by Max Plank INST.EANN1l NN OProgram: FleetsatcomQNN5 :: " Program: FleetsatcomjGNN# American military geostationary telecommunications satellite program1 NN' O ContactzNN3N, (n։Operator: Naval Space CommandCommand & control: Air Force Space Command<NoN' *O External resources[3NN. ,http://www.fafb.af.mil/fltsat/http://www.fas.org/spp/military/program/com/fltsat.htmoN O, &WSFleetsatcom 7 & 8 carry an experimental EHF package for terminal applications, probably close to the one on UHF and on Milstar. The terminal is know as AN/USC-38(V)N ON1N=O1U=OOOB OO# >Fleetsatcom's specificationsY=OOA#R0&Prime contractorTRWN O&OA#RPlatform[OOA#R4"Mass at launch2250 kgZ&OOA#R2 Mass in orbit1043 kgYOvOB#TDimensionhexagonal: 2.43 m (diameter) x 1.27 m (high)With a 4.88 m diameter antennaWOOA#R,Solar array13.2 mYvO&OA#R0 Stabilization3 axisYOOA#R0DC powerBOL: 2000 W\&OOA#R6$Design lifetime5 years$OO" 1O0O10OOxOO( Fleetsatcom's UHF-band (244-263 MHz)Each satellite has 23 communications channels, 10 of which are used by the Navy for communications between its land forces, ships, and aircraft. The Air Force uses 12 of the channels as part of its satellite communications system for command and control of nuclear forces. One channel is reserved for U.S. national command authorities.10OO10OOOOe 52>>?>ቂ@>ቂA>ቂB>ቂC>ቂD>ቂE>ቂProgram: FleetsatcomFleetsatcom 1Fleetsatcom 2Fleetsatcom 3Fleetsatcom 4Fleetsatcom 5Fleetsatcom 6Fleetsatcom 7Fleetsatcom 8> O>O1&>OO OFleetsatcom 1JOO5 :, " Fleetsatcom 1:>OO# .Also called OPS 63911 OO'  Generalg OZOG#^@") Designation10669 / 78016A[OOA#R4Launch date9 Feb 1978t'ZO) OM#jN"N ,㹌לCountry of originUnited Statesy,O OM#jX"H̀‰MissionMilitary: telecommunicationsb!) O OA#RB,Geostationary orbitsee belowq$ Ou OM#jH" &yjLaunch vehicleAtlas Centaur_ O OA#R<Launch siteCape Canaveral&u O O# 2 O, O'  Location O Om#:   " BeginEndPosition, O; Oj#6"&(L: 9 Feb 1978100W' O Oj#N,.Mar 1995Dec 199615W, inclined; OU Oj#>Feb 199772E, inclined8 O O' "(Technical dataMU O O0 0:Vv8nSpecificationsPayload> OO1E߀ObOBOFleetsatcom 2J ObO5 :, " Fleetsatcom 2:OO# .Also called OPS 63921 bOO'  Generalg O4OG#^@") Designation11353 / 79038A[OOA#R4Launch date4 May 1979t'4O@OM#jN"N ,㹌לCountry of originUnited StatesO@O Oy,O@OM#jX"H̀‰MissionMilitary: telecommunications]@O@OA#R8,Geostationary orbit75Eq$@OVAOM#jH" &yjLaunch vehicleAtlas Centaur_@OAOA#R<Launch siteCape Canaveral&VAOAO# 5AOBO'  End of lifeWAOgBOA#R,"Out of serviceyes8BOBO' "(Technical dataMgBOBO0 0:Vv8nSpecificationsPayload> BO*CO1&k*COtCO0HOFleetsatcom 3JBOtCO5 :, " Fleetsatcom 3:*COCO# .Also called OPS 63931 tCOCO'  Generalg COFDOG#^@") Designation11669 / 80004A\CODOA#R6Launch date18 Jan 1980t'FDOEOM#jN"N ,㹌לCountry of originUnited Statesy,DOEOM#jX"H̀‰MissionMilitary: telecommunicationso(EOEOG#^P"/ۀ0Geostationary orbit23W, inclinedq$EOoFOM#jH" &yjLaunch vehicleAtlas Centaur_EOFOA#R<Launch siteCape Canaveral&oFOFO# 5FO)GO'  End of life\FOGOA#R6"Out of serviceSep 1995&)GOGO# 8GOGO' "(Technical dataMGO0HO0 0:Vv8nSpecificationsPayload> GOnHO17߀̃ nHOHOLOFleetsatcom 4J0HOHO5 :, " Fleetsatcom 4:nHOHO# .Also called OPS 63941 HO#IO'  Generalg HOIOG#^@") Designation12046 / 80087A\#IOIOA#R6Launch date31 Oct 1980t'IOZJOM#jN"N ,㹌לCountry of originUnited Statesy,IOJOM#jX"H̀‰MissionMilitary: telecommunicationsp)ZJOCKOG#^R"/ۀ0Geostationary orbit172E, inclinedq$JOKOM#jH" &yjLaunch vehicleAtlas Centaur_CKOLOA#R<Launch siteCape Canaveral&KO9LO# 8LOqLO' "(Technical dataM9LOLO0 0:Vv8nSpecificationsPayload> qLOLO1k_!LOJMO4OFleetsatcom 5NLOJMO8 @. " Fleetsatcom 51 LO{MO'  Generalg JMOMOG#^@") Designation12635 / 81073A[{MO=NOA#R4Launch date6 Aug 1981t'MONOM#jN"N ,㹌לCountry of originUnited Statesy,=NO*OOM#jX"H̀‰MissionMilitary: telecommunicationsYNOOOA#R0,Geostationary orbitq$*OO OM#jH" &yjLaunch vehicleAtlas CentaurOO OLO_OOkOA#R<Launch siteCape Canaveral& OO# 5kOƀO'  End of life\O"OA#R6"Out of serviceAug 1981LƀOOA#RCauseThe satellite reached GTO, but imploding payload shroud damaged it8"OO' "(Technical dataMO4O0 0:Vv8nSpecificationsPayload> OrO1_"rOOJOFleetsatcom 6N4OO8 @. " Fleetsatcom 65rOO'  End of life_OTOA#R<"Out of service26 Mar 1987q*OŃOG#^TyjCauseLaunch failure (Atlas Centaur)8TOO' "(Technical dataMŃOJO0 0:Vv8nSpecificationsPayload> OO10̃#OքOՈOFleetsatcom 7NJOքO8 @. " Fleetsatcom 79OO# ,Also called USA 0201 քO@O'  Generalg OOG#^@") Designation17181 / 86096A[@OOA#R4Launch date5 Dec 1986t'OvOM#jN"N ,㹌לCountry of originUnited Statesy,OOM#jX"H̀‰MissionMilitary: telecommunicationsp)vO_OG#^R"/ۀ0Geostationary orbit100W, inclinedq$OЇOM#jH" &yjLaunch vehicleAtlas Centaur__O/OA#R<Launch siteCape Canaveral8ЇOgO' "(Technical datan</OՈO2 4xVv8nSpecificationsPayloadHas an additional EHF payload> gOO10$OaO`OFleetsatcom 8NՈOaO8 @. " Fleetsatcom 89OO# ,Also called USA 0461 aOˉO'  Generalg O2OG#^@") Designation20253 / 89077A\ˉOOA#R6Launch date25 Sep 1989t'2OOM#jN"N ,㹌לCountry of originUnited Statesy,O{OM#jX"H̀‰MissionMilitary: telecommunicationso(OOG#^P"/ۀ0Geostationary orbit23W, inclinedq${O[OM#jH" &yjLaunch vehicleAtlas Centaur_OOA#R<Launch siteCape Canaveral8[OO' "(Technical datan<O`O2 4xVv8nSpecificationsPayloadHas an additional EHF payload6OO1| l ф%O̍O"OForte6 `O̍O, (" FortdAO0O# Fast On-orbit Recording of Transient Events, also called P94-11 ̍OaO'  Generalg 0OȎOG#^@") Designation24920 / 97047A\aO$OA#R6Launch date29 Aug 1997t'ȎOOM#jN"N ,㹌לCountry of originUnited Statesa$O OG#^4"H̀MissionScientific: O O`OZOfOA#R2"Perigee/Apogee800 kmT OOA#R&Inclination70SfO OA#R$Period101 minr%OOM#jJ" &GKTLaunch vehiclePegasus XL #17.  OO% Advanced radio frequency (RF) impulse detection and characterization experiment. Emphasis is on the measurement of electromagnetic pulses (EMP), primarily due to lightning, within a noise environment dominated by continuous wave (CW) carriers, such as TV and FM stations. Optical sensors will augment the RF system in characterizing lightning events. A principal goal is to develop a comprehensive understanding of the correlation between the optical flash and the very high frequency (VHF) emissions from lightning. <OO' *O External resourcesR+O;O' Vhttp://sst.lanl.gov/nis-projects/forte/8OsO' "(OTechnical data8;OO' " SpecificationsJsO6OA#R&Prime contractorLos Alamos National Laboratory & Sandia National Lab.N OOA#RPlatformZ6OOA#R2"Mass at launch212 kgSO1OA#R$ Mass in orbitOOOA#RDimensionQ1OOA#R Solar arrayYO*OA#R0 Stabilization3-axisRO|OA#R"DC power55 W\*OOA#R6$Design lifetime3 yearsJ|O"O+ $?First US satellite entirely made of composite materials (the 41 kg structure was built by Composite Optics). It will feature a 10.7 m antennaRF system: receiver covering 30-300 MHz and high speed digitizersOptical system: coarse imager 10 x 10 km resolution Beacon: 401.565 MHz5OWO1W9&WOOxOFR 1= "OO2 4"  FR 11 WOO'  Generalg O,OG#^@") Designation01814 / 65101A[OOA#R4Launch date6 Dec 1965m ,OOM#j@"N ,㱭+Country of originFrancey,OmOM#jX"H̀?vMissionScientific: ionosphere study^OOA#R:"Perigee/Apogee696/707 kmVmO!OA#R*Inclination75.9TOuOA#R&Period98.8 minm !OOM#j@" &g'KLaunch vehicleScout #39YuO;OA#R0"Mass at launch62 kg&OaO# 5;OO'  End of life_aOOA#R<"Out of service28 Feb 1969_OTOA#R<CauseStopped transmitting$OxO" 6TOO1 ф'OO PFreja> xOO2 4"  FrejahEOTO# In the nordic mythology Freja is the goddess of Love and fecundity1 OO'  Generalg TO PG#^@") Designation22161 / 92064AO PxO[OgPA#R4Launch date6 Oct 1992m PPM#j@"N ,ˆtCountry of originSwedeng&gP;PA#RLOperatorSwedish Space Corporation|/PPM#j^"H̀d;plMissionScientific: magnetosphere study_;PPA#R<"Perigee/Apogee586/1767 kmTPjPA#R&Inclination63UPPA#R(Period108.9 minp#jP/PM#jF" &9+SLaunch vehicleLong March 2ZPPA#R2"Mass at launch230 kg/PqP- (w1ĉSuccessor of Viking with instruments for research into the Earth's magnetosphere and the aurora. Carries magnetic particles detectors and magnetic field captors.Cost: $150 million<PP' *O External resourcesP)qPP' Rhttp://www.ssc.se/ssd/ssat/freja.html5P2P'  End of life_PPA#R<"Out of service16 Oct 1996Y2PPA#R0Causeout of control&PP# 8PHP' "(OTechnical data8PP' " Specificationsi(HPPA#RP&Prime contractorSwedish Space Corp.ZPCPA#R2"Mass at launch265 kgSPPA#R$Diameter2.2 mk*CPPA#RT StabilizationSpin stabilized (10 rpm)XPYPA#R.DC powerEOL: 130 W\PPA#R6$Design lifetime2 years&YPP# 1 P P'  PayloadUPa PA#R(Boom length15 mt3 P PA#Rf,Telemetry data rate250-500 kbps (2 Mbps burst)Za P/ PA#R2(Transmitter power2 Wt3 P PA#RfFrequencies400.55 MHz (1200 bps), 2208.163 MHz$/ P P" > P P19,( PS P PProgram: FujiN PS P8 @.G" Program: FujisN P P% Means "glycine flower"Japanese small telecommunications satellite program1S P P1) Ph Pq0 Ph PA R`ATOUO뉂J ;Program: FujiFuji 1AFuji 1BFuji 28 P P18* P PCPFuji 1AHh P P8 @"G" Fuji 1AU, P= P) "X䵟Also called JAS 1A or FO-12 or Oscar 121 Pn P'  Generalg = P PG#^@") Designation16909 / 86061B\n P1PA#R6Launch date12 Aug 1986l PPM#j>"N ,bCountry of originJapano"1P PM#jD"H̀㓉MissionTelecommunications`PlPA#R>"Perigee/Apogee1479/1497 kmT PPA#R&Inclination50UlP!@PA#R(P!@Ph PPeriod115.7 minfP@PM#j2" &JLaunch vehicleH1&!@P@P# 5@P@P'  End of life]@P?APA#R8"Out of servicefall 1989Y@PAPA#R0Causepower problemszV?APBP$ Launched with Experimental Geodetic Payload - first multi-payload launch by NASDA.8APJBP' "(OTechnical data8BPBP' " SpecificationsYJBPBPA#R0"Mass at launch50 kgc"BP>CPA#RD Stabilizationpassive magneticg&BPCPA#RLDC power8.5 W (6 Ah NiCd battery)$>CPCP" 8CPDP1;Xr+DPIDPSLPFuji 1BHCPIDP8 @"G" Fuji 1BU,DPDP) "X䵟Also called JAS 1A or FO-20 or Oscar 201 IDPDP'  Generalg DP6EPG#^@") Designation20480 / 90013C[DPEPA#R4Launch date7 Feb 1990l6EPEPM#j>"N ,bCountry of originJapano"EPlFPM#jD"H̀㓉MissionTelecommunications_EPFPA#R<"Perigee/Apogee908/1743 kmTlFPGPA#R&Inclination99UFPtGPA#R(Period112.2 minfGPGPM#j2" &JLaunch vehicleH1YtGP3HPA#R0"Mass at launch50 kgnGPHP$ Only operates in analog mode after failures. The beacon has been delimited to sending a permanent carrier.83HPHP' "(Technical datamIHPjIP$ Packet Radio Mailbox and Digipeater, and a mode J analog transponder.jHPJPB#T"Mode JD uplink1200bps Manchester coded (Biphase-L) FSK (FM) AX.25145.850 145.870 145.890 145.910 MHz&jIP"N ,bCountry of originJapano"NPNPM#jD"H̀㓉MissionTelecommunications_NPVOPA#R<"Perigee/Apogee797/1317 kmVNPOPA#R*Inclination98.6SVOP PA#R$Period106 minOP PSLPiOPuPM#j8" &JLaunch vehicleH2 #4T0 PɀP$ `Only operates in analog mode after a failure<uPP' *O External resourcesL%ɀPQP' Jhttp://www.jarl.or.jp/jarl/jas-2/8PP' "(OTechnical data8QPP' " SpecificationsVPPA#R*&Prime contractorN PePA#RPlatformYPPA#R0"Mass at launch50 kgSePPA#R$ Mass in orbit\PmPA#R6Dimension0.44 x 0.47 mQPPA#R Solar arraySmPPA#R$ StabilizationN P_PA#RDC powerUPPA#R($Design lifetimeoJ_P#P% Packet Radio Mailbox and Digipeater, and a mode J analog transponder.jPυPB#T"Mode JD uplink1200bps Manchester coded (Biphase-L) FSK (FM) AX.25145.850 145.870 145.890 145.910 MHz{9#PJPB#Tr&Mode JD downlink1200bps BPSK (SSB) AX.25435.910 MHzF"υPP$ DTotal transmitting power is 1Ws2JPPA#Rd"Mode JA uplink145.900 - 146.000 MHz (SSB, CW)?PPA#R~&Mode JA downlink435.800 - 435.900 MHz (SSB, CW, inverting)_PPA#R<"Mode JA Beacon435.795 MHz_<PAP# xTotal transmitting power is 1W, of which beacon is 100 mW5PvP1[-vPP PFUSE5 APP, (" FUSEL)vPP# RFar Ultraviolet Spectroscopic Explorer1 P(P'  GeneralYPPG#^$") Designation`(PPA#R>Launch dateplanned in 1998t'PUPM#jN"N ,㹌לCountry of originUnited Statesr%PNJPM#jJ"H̀_BMissionScientific: AstronomyZUP!PA#R2"Perigee/Apogee800 kmTNJPuPA#R&Inclination25L !PPA#RPeriodkuP,PM#j<" &p㉂Launch vehicleDelta 2QP}PA#R Launch site,PP1 0~w?vVFUSE will access the wavelength below 1180 Angstroms (the HST STIS cutoff) with high resolution astronomical spectroscopy. No long-term observatory since Copernicus (1972) has possessed this capability.8}PP' "(OTechnical data8PP' " SpecificationsVPGPA#R*&Prime contractorN PPA#RPlatformTGPPA#R&"Mass at launchSPP1Y.>PPPT+ PP) "VȠ$To view this page you need to register(>PP$ @PP1,/PJPPProgram: GalaxyPPJP8 @2qq[T" Program: Galaxy]PP/ .$Ijg?qOTelecommunication program, now operated by Panamsat. It was previously operated by HCI1JPP1}0PSPLPSP {Ӊ7up_b㉂-8up9upb㉂:up;upb㉂Program: GalaxyGalaxy 1Galaxy 1RGalaxy 1R failureGalaxy 2Galaxy 3Galaxy 3RGalaxy 4Galaxy 5Galaxy 6Galaxy 7Galaxy 8iGalaxy 9Galaxy 10Galaxy 111PP1U1P"PFPI&SPP# LGalaxy 1, 2, 3 & 6's specifications\P)PA#R60&Prime contractorHughesTP}PA#R&0PlatformHS-376[)PPA#R40"Mass at launch1200 kgY}P1PA#R00 Mass in orbit709 kgTPPA#R&0Diameter2.16 ma 1PPA#R@0Height6.6 m (2.84 m stowed)b!PHPA#RB0 StabilizationSpin stabilized};PPB#Tv0DC powerBOL: 990 WEclipse: 2 nickel-cadmium batteries]HP"PA#R80$Design lifetime10 years$PFP" 1"PwP1b2wPP>FPP# 6Galaxy 1, 2 & 3's C-bandYwPPA#R00(Main transponders24ZPhPA#R20,Backup transponders6UPPA#R(0Power9 W (TWTA)UhPPA#R(0Bandwidth36 MHzN P`PA#R0CoverageTPPA#R&0EIRP max34 dBWX`P PA#R.0PolarizationlinearxPP$ Antenna: 1.8 m diameter with two reflecting surfaces. One surface is sensitive to V polarization and the other to H.1 PP1B3P QG$P P# HGalaxy 4, 7 & 3R's specifications\P|PA#R60&Prime contractorHughesT PPA#R&0PlatformHS-601[|P+PA#R40"Mass at launch2950 kgm+PPB#TV0 Mass in orbitBOL: 1692 kgEOL: 1320 kg`+PPA#R>0Dimension2.7 x 3.6 x 3.1 m\PTPA#R60Solar array24.7 m spanYPPA#R00 Stabilization3 axisf$TPPB#TH0DC powerBOL: 6000 WEOL: 4700 W]PpPA#R80$Design lifetime15 yearszVP Q$ 2 antennas of 2.44 m x 1.83 m: C-band on the West side and Ku-band and on the EastpP QP1pP=Q1M4=QWQ? Q|Q# 8Galaxy 4, 7 & 3R's C-bandY=QQA#R00(Main transponders24Z|Q/QA#R20,Backup transponders6VQQA#R*0Power16 W (SSPA)U/QQA#R(0Bandwidth36 MHz>QrQZ#|0,.LCoverage & EIRP maxCONUS: 42 dBWAlaska, Hawaii: 33 dBWXQQA#R.0PolarizationlinearirQWQ$ Strap-crossing: transponders 18 and 24 can be feed by the Ku-band transponders 17 and 23 respectively1QQ1~5QQ<WQQ# 2Galaxy 4 & 7's Ku-bandYQQA#R00(Main transponders24ZQwQA#R20,Backup transponders6VQQA#R*0Power50 W (TWTA)@wQOQB#T0Bandwidth8 transponders of 54 MHz16 transponders of 27 MHzN QQA#R0CoverageTOQQA#R&0EIRP max45 dBWXQIQA#R.0PolarizationlinearhQQ$ Strap-crossing: transponders 17 and 23 can be feed by the C-band transponders 18 and 24 respectively1IQQ1U6Q Q QG$QMQ# HGalaxy 1R, 5 & 9's specifications\QQA#R60&Prime contractorHughesTMQQA#R&0PlatformHS-376TQQQA#R&0"Mass at launchYQQA#R00 Mass in orbit788 kgTQQQA#R&0Diameter2.16 mb!Q` QA#RB0Height7.53 m (3.11 m stowed)b!Q QA#RB0 StabilizationSpin stabilizedB` QF QB#T0DC powerBOL: 1163 WEclipse: 2 super nickel-cadmium batteries] Q QA#R80$Design lifetime10 years$F Q Q" 1 Q Q17 QKQ? Q7 Q# 8Galaxy 1R, 5 & 9's C-bandY Q QA#R00(Main transponders24Z7 Q QA#R20,Backup transponders6V Q@ QA#R*0Power16 W (TWTA)U Q QA#R(0Bandwidth36 MHzn-@ Q QA#RZ0CoverageCONUS, Alaska, Hawaii, CaribbeanT QW QA#R&0EIRP max38 dBWX Q QA#R.0PolarizationlinearxW QKQ$ Antenna: 1.8 m diameter with two reflecting surfaces. One surface is sensitive to V polarization and the other to H.9 QQ1fm8QQCQGalaxy 1IKQQ8 @$qq[T" Galaxy 11 QQ'  Generalg QeQG#^@") Designation14158 / 83065A\QQA#R6Launch date28 Jun 1983t'eQA@QM#jN"N ,QA@QKQ㹌לCountry of originUnited Stateso"Q@QM#jD"H̀‰MissionTelecommunications^A@QAQA#R:,Geostationary orbit133Ws&@QAQM#jL" &p㉂Launch vehicleThor Delta #170&AQAQ# 5AQAQ'  End of life\AQ8BQA#R6"Out of serviceApr 1994&AQ^BQ# 88BQBQ' "(Technical dataxA^BQCQ7 >#*xVھSpecificationsC-bandC-band transponder frequency chartBBQPCQ1+逤9PCQCQXGQGalaxy 1R failureRCQCQ8 @6qq[T" Galaxy 1R failure1 PCQCQ'  General\CQ/DQA#R6Launch date22 Aug 1992t'CQDQM#jN"N ,㹌לCountry of originUnited Stateso"/DQEQM#jD"H̀‰MissionTelecommunicationsq$DQEQM#jH" &yjLaunch vehicleAtlas Centaur_EQEQA#R<Launch siteCape Canaveral&EQFQ# 5EQ=FQ'  End of life_FQFQA#R<"Out of service23 Aug 1992F=FQ#GQA#RCauseFail to orbit because the launcher's 3rd stage malfunctioned5FQXGQ$ "Was an HS-376: #GQGQ1#:GQGQ]LQGalaxy 1RJXGQGQ8 @&qq[T" Galaxy 1R1 GQ HQ'  Generalg GQtHQG#^@") Designation23016 / 94013A\ HQHQA#R6Launch date19 Feb 1994t'tHQDIQM#jN"N ,㹌לCountry of originUnited Stateso"HQIQM#jD"H̀‰MissionTelecommunicationsfDIQJQG#^>"/ۀ0Geostationary orbit133Wp#IQJQM#jF" &p㉂Launch vehicleDelta 2 #225kJQKQ$ The launch was aborted on 9 Feb 1994 during main engine ignition and the vehicle did not leave the pad.8JQPKQ' "(Technical dataxAKQKQ7 >艀юھSpecificationsC-bandC-band transponder frequency chart=PKQLQ' , EIRP coverage (dBW)X(KQ]LQ0 0P!!C-band HorizontalC-band Vertical1LQLQ1;LQLQb,]LQLQ6 #*xVھSpecificationsC-bandC-band transponder frequency chart9ˁQ|Q1m>|QłQSQGalaxy 3ICQłQ8 @$qq[T" Galaxy 31 |QQ'  Generalg łQ]QG#^@") Designation15308 / 84101A\QQA#R6Launch date21 Sep 1984t']Q-QM#jN"N ,㹌לCountry of originUnited Stateso"QQM#jD"H̀‰MissionTelecommunications_-QQA#R<,Geostationary orbit93.5Ws&QnQM#jL" &p㉂Launch vehicleThor Delta #176&QQ# 5nQɅQ'  End of life\Q%QA#R6"Out of serviceOct 1995XɅQ}QA#R.Causewas deorbited&%QQ# 8}QۆQ' "(Technical dataxAQSQ7 >#*xVھSpecificationsC-bandC-band transponder frequency chart: ۆQQ1 7W?QӇQ~QGalaxy 3RFSQӇQ5 :$qq[T" Galaxy 3R1 QQ'  Generalg ӇQkQG#^@") Designation23741 / 95069A\QLjQA#R6Launch date15 Dec 1995t'kQ;QM#jN"N ,㹌לCountry of originUnited Stateso"LjQQM#jD"H̀‰MissionTelecommunicationse;QQG#^<"/ۀ0Geostationary orbit95Wp#QQM#jF" &yjLaunch vehicleAtlas 2A #97[QڊQA#R4"Mass at launch3380 kgQ̌Q/ ,c㉂Cost: $150 millionUsing a combination of digital compression and tightly focused spot beams, Galaxy 3R will used 24 Ku-band transponders to deliver as many as 144 channels of digital video and 60 channels of CD- quality audio via 24-inch (60 cm) dishes. The service was called Galaxy Latin America. In early 1998 the service was moved to Galaxy 8i. A beam of the satellite was then moved to the US in order to extend the DirecTV programming.8ڊQQ' "(Technical dataǧQQ> L⣟M+ھu"]SpecificationsC-bandC-band transponder frequency chartKu-band transponder frequency chart=QQ' , EIRP coverage (dBW)X(Q>Q0 0PB,BC-band HorizontalC-band Vertical1 QoQ'  Ku-bandY>QȎQA#R0(Main transponders24ZoQ"QA#R2,Backup transponders6VȎQxQA#R*Power63 W (TWTA)X"QQB#TBandwidth16 transponders of 27 MHz (horizontal)8 transponders of 5xQQSQ4 MHz (vertical){:xQQA#RtCoverage2 beams (12 transponders each): North AmericaTQQA#R&EIRP max49 dBWXQEQA#R.PolarizationlinearAQQB#TFrequenciesUplink: 14.0 - 14.500 GHzDownlink: 11.7-12.2 GHzEQ~Q- (c㉂Downlink frequencies where switched from 11.450 - 11.750 GHz circular (with coverage to Latin America and Brazil on 2 beams) to 11.7-12.2 GHz linear (coverage to North America) sometime in Apr 1998 after Galaxy 8i went operational. It is unclear if the uplink frequencies also changed.Strap-crossing: transponders 17 and 23 can be feed by the C-band transponders 18 and 24 respectively1QQ1@QQb,~QQ6 "/ۀ0Geostationary orbit125Wq$ RRM#jH" &yjLaunch vehicleAtlas Centaur_qRARA#R<Launch siteCape Canaveral&RgR# 8ARR' "(Technical dataxAgRR7 >艀юھSpecificationsC-bandC-band transponder frequency chart=RTR' , EIRP coverage (dBW)X(RR0 0PB)RB)RC-band HorizontalC-band Vertical1TRR1HR>Ra+R>R6 RR6 99W" R Rj#D46< Oct 1993early 1994103W#? RX Rj#F8:spring 199420 May 199874W R Rj#4"&(late May 199899W&X RR# 8 R:R' "(Technical data<RvR) "&#*xSpecifications=:RR' , EIRP coverage (dBW)JvRR0 04⣦@ⱦ@HorizontalVertical0 R-R'  C-bandYRRA#R0(Main transponders24Z-RRA#R2,Backup transponders6XRD@RA#R.RD@RRPower10.2 W (TWTA)UR@RA#R(Bandwidth36 MHzn-D@RARA#RZCoverageCONUS, Alaska, Hawaii, CaribbeanT@R[ARA#R&EIRP max39 dBWXARARA#R.PolarizationlinearR([ARBR* $PھC-band transponder frequency chart1AR6BR1K6BRBRa+BRBR6 "/ۀ0Geostationary orbit123Wp#RRM#jF" &p㉂Launch vehicleDelta 2 #236[ RRA#R4"Mass at launch1397 kgiRR, (Gb㉂Should move to 127W after Galaxy 10 is launched.43rd HS-376 launchedsatellite worth $150 million8RR' "(Technical datazBR2R8 @艀юھSpecificationsC-bandC-band transponder frequency chart=RoR' , EIRP coverage (dBW)xA2RR7 >RRRC-band HorizontalC-band VerticalC-band Alaska extended1oRR1URyRa+RyR6 BSG#^>" &Launch vehicleSea LaunchYASBSG#^$Launch site&>BSBS# 8BSBS' "(OTechnical data=BS2CS' , EIRP coverage (dBW)GBSCS> LW$ C-bandKu-band, North AmericaKu-band, BrazilKu-band, Latin82CSCS' " Specifications\CSKDSA#R6&Prime contractorHughesTCSDSA#R&PlatformHS 702TKDSDSA#R&"Mass at launchSDSFESA#R$ Mass in orbitODSESA#RDimensionw6FES FSA#RlSolar array11000 W (gallium arsenide solar cells)YESeFSA#R0 Stabilization3 axisN FSFSA#RDC power]eFSGSA#R8$Design lifetime15 yearsw6FSGSA#Rl$Station keepingXenon Ion Propulsion System (XIPS)&GSGS# 0 GSGS'  C-bandYGS6HSA#R0(Main transponders24YGSHSA#R0,Backup transpondersO6HSHSA#RPower20 WUHS3ISA#R(Bandwidth36 MHz[HSISA#R4CoverageNorth AmericaJ 3ISISA#REIRPRIS*JSA#R"Polarization&ISPJS# B*JSJS' 6 Ku-band (11.45-11.7 GHz)YPJSJSA#R0(Main transponders24YJSDKSA#R0,Backup transpondersOJSKSA#RPower75 WUDKSKSA#R(Bandwidth27 MHzBKSnLSD#XCoverageNorth AmericaCaribbeanSouth AmericaCentral AmericaN KSLSA#REIRP maxRnLSMSA#R"PolarizationZLShMSA#R2Uplink13.75-14.0 GHz\MSMSA#R6Downlink11.45-11.7 GHz&hMSMS# AMS+NS' 4 Ku-band (11.7-12.2 GHz)YMSNSA#R0(Main transponders24Y+NSNSA#R0,Backup transpondersK NS(OSA#RPowerUNS}OSA#R(Bandwidth27 MHz[(OSOSA#R4CoverageSouth AmericaN }OS2SA#ROS2SSEIRP maxROSSA#R"PolarizationY2S݀SA#R0Uplink14.0-14.5 GHz[S8SA#R4Downlink11.7-12.2 GHz&݀S^S# 18SS1W_SS ST+^SS) "VȠ$To view this page you need to register&S S# 1S:S1`:SSU SS6 <@>b"~Galaxy 11's C-band EIRP1:SS1WaSS:ST+SS) "VȠ$To view this page you need to register&S:S# 1SkS1bkSڃSo9:SڃS6 b"Galaxy 11's Ku-band EIRP (North America & Brazil)1kS S1Wc S_SST+ڃS_S) "VȠ$To view this page you need to register& SS# 1_SS1dSS^(SS6 b"Galaxy 11's Ku-band EIRP (Latin)1SES1WeESSST+SS) "VȠ$To view this page you need to register&ESS# 6SS1n [.fS+SSGalex6 S+S, (" Galex?SjS# 8Galaxy Evolution Explorer1 +SS'  GeneralYjSSG#^$") DesignationUSISA#R(Launch date2001t'SSM#jN"N ,㹌לCountry of originUnited Statesm&IS*SG#^L"H̀MissionScientific: part of SMEXZSSA#R2"Perigee/Apogee690 kmV*SڈSA#R*Inclination28.5L S&SA#RPeriodg ڈSSG#^@" &Launch vehicleOSC vehicleQ&SމSA#R Launch site[S`S' Cost: $16.5 millionGalex is a Space Ultraviolet Small Explorer mission that will map the global history and probe the causes of star formation over the redshift range 0 `SS1y hSSZSProgram: GalsNSS8 @."G" Program: GalsSS0 .o7U=Soviet direct TV-built satellites financed by The Land Group, a Chinese non-state sector company. On the 2 first satellites, 2 transponders are said to have failedIntersputnik has plans to operate Gals R12 satellites from 1997 on. (5 to 7 years lifetime, 12 Ku-band transponders (27 MHz), 2400 W.Gals R16 satellites could also be launched in 1999. 16 transponders each for DBS services<S S' *O External resourcesP)SZS' Rhttp://www.lnd.cn.net/TEXT/TEA4B1.HTM1 SS1iSS_%ZSS: DJO?O?Program: GalsGals 1Gals 21SS1jSS:SUS# .Gals' specificationsb!SSA#RB&Prime contractorInformcosmosVUS SA#R*PlatformNPO Gals[ShSA#R4"Mass at launch2500 kgS SSA#R$ Mass in orbitShSSA#R$Diameter2.5 m\SjSA#R6Solar arraytwin panelsYSSA#R0 Stabilization3 axisTjSSA#R&DC power2400 Wa SxSA#R@$Design lifetime5 to 7 yearscSS$ Xenon thrusters: SPT 100 , 8 units per satellite (including redundances) produced by Fakel CIS.1xS0S1k0SS3ScS#  Gals' ku-bandX0SSA#R.(Main transponders3YcSSA#R0,Backup transponders[SoSA#R4Power150-300 W (TWTA)USSA#R(Bandwidth27 MHzfoSmSC#VCoverage2 spot beams (steerable):A: 2.5 x 1.25 (2 transponders)B: 1.2 x 0.9 (1 transponder)TSSA#R&EIRP max57 dBWZmSSA#R2PolarizationcircularMSSB#TFrequenciesuplink: 17404.2 - 17883.7 MHzdownlink: 11804.2 - 12283.7 MHzF"SS$ DReceive antenna: spot: 2 x 27S'S1l'SnSTGals 1GSnS8 @ "G" Gals 11 'SS'  Generalg nSSG#^@") Designation22963 / 94002A\SbSA#R6Launch date20 Jan 1994jSSM#j:"N , Country of originCISo"bSGTM#jD"H̀SGTS‰MissionTelecommunicationsb!STA#RB,Geostationary orbitsee belowo"GTTM#jD" &㉓gLaunch vehicleProton #219&T>T# : TxT- */ۀ Location>TTm#:   " BeginEndPosition'xTTj#N$@BL: 20 Jan 1994mid-May 199671ETTj#, June 199636E&T9T# 8TqT' "(Technical dataQ9TT2 4>D#j⧒&SpecificationsKu-band7qTT1XmT@T TGals 2GT@T8 @ "G" Gals 21 TqT'  Generalg @TTG#^@") Designation23717 / 95063Ah'qT@TA#RNLaunch date17 Nov 1995 at 14:30 UTjTTM#j:"N , Country of originCISo"@TTM#jD"H̀‰MissionTelecommunicationsb!T{TA#RB,Geostationary orbitsee belowo"TTM#jD" &㉓gLaunch vehicleProton #237!{T T% Land has leased the satellite for $9 million a year to Global DBS Company, whose shareholders include the Loral Corp, General Instruments Co and TCI Cable TV Co, all of the United States, and British General Telecommunications Ltd/Asian TV network.: TET- */ۀ Location TTm#:   " BeginEndPosition'ET` Tj#N$@BL: 17 Nov 1995mid-Jun 199671ET Tj#*Jul 199636E&` T T# 8 T= T' "(Technical dataQ T T2 4>D#j⧒&SpecificationsKu-band7= T T1_n T T: TGals 3G T T8 @ "G" Gals 3. T: T# for 19971 Tk T1Wok T T TT+: T T) "VȠ$To view this page you need to register&k T T# 7 T T1_Xp Tc T TGals 4G Tc T8 @ "G" Gals 4.  T T# for 19981c T T1Wq T T< TT+ T T) "VȠ$To view this page you need to register& T< T# <  Tx T1 rx T Tl@TProgram: GEH< T T5 :(⧙" Program: GEtx Tl@T, &D"Telecommunication program operated by GE Americom.Another project of GE Americom: a set of satellite for global services; operated from Gibraltar. Planned orbital locations include 3E, 6.5W, 10W, 15W and 23W for Europe; 37.5E, 47E and 51E for Africa; and 97E, 100.7E, 105.3E and 108.2E for Asia and the Pacific. The proposed satellites would be used mainly for video programming distribution, including direct-to-home, cable headend and other broadcast applications. The planned spacecraft design would accommodate Tl@T< Tboth analog and digital video formats, as well as other uses including VSAT and data networks.1 T@T1s@T>ATDl@T>AT] qPdIrRUp@TrRU@TrRUrRUrRUProgram: GEGE 1GE 1AGE 2GE 2AGE 3GE 4GE 51@ToAT1toATYET9>ATAT# ,GE's specificationsq0oATBTA#R`&Prime contractorLockheed Martin Astro SpaceTATmBTA#R&PlatformA2100b[BTBTA#R4"Mass at launch2750 kgSmBTCTA#R$ Mass in orbitu4BTCTA#RhDimension1.83 x 1.85 x 2.64 m (22.2 m deployed)QCTCTA#R Solar arrayYCT:DTA#R0 Stabilization3-axisYCTDTA#R0DC powerBOL: 6000 W]:DTDTA#R8$Design lifetime15 yearsiEDTYET$ Beacon frequencies were intentionally not provided by GE Americom1DTET1UuETHT7HT1YETET# GE's C-bandYETFTA#R0(Main transponders24ZETnFTA#R2,Backup transponders8\FTFTA#R6Power12 to 18 W (SSPA)UnFTGTA#R(Bandwidth36 MHzN FTmGTA#RCoverageTGTGTA#R&EIRP max37 dBWRmGTHTA#R"Polarization$GT7HT" 1HThHT1UvhHTJTKT27HTHT# GE's Ku-bandYhHTHTA#R0(Main transponders24[HTNITA#R4,Backup transponders12VHTITA#R*Power60 W (TWTA)UNITITA#R(Bandwidth36 MHzN ITGJTA#RCoverageTITJTA#R&EIRP max49 dBWRGJTJTA#R"Polarization$JTKT" 5JTFKT1wFKTKThOTGE 1A KTKT5 :⧙" GE 11 FKTKT'  Generalg KTLTG#^@") Designation24315 / 96054A[KTzLTA#R4Launch date8 Sep 1996t'LTLTM#jN"N ,㹌לCountry of originUnited Stateso"zLT]MTM#jD"H̀‰MissionTelecommunications^LTMTA#R:,Geostationary orbit103Wu(]MT0NTM#jP" &yjLaunch vehicleAtlas 2A (AC-123)CMTsNT* $2:TGstar 1 replacement80NTNT' "(OTechnical data=sNTNT' , EIRP coverage (dBW):NThOTF \tv,[IFkviC-bandKu-bandSpecificationsC-bandKu-band1NTOT1xOT TPhOT T6 <6rRU"GE 1's C-band EIRPOT ThOT1OT=T1y=TTQ TT6 <8rRU"GE 1's Ku-band EIRP6=TĀT1 F7zĀTT]TGE 1AB TT5 :⧙" GE 1A1 ĀT7T'  GeneralYTTG#^$") Designationa 7TTA#R@Launch dateplanned for 1999t'TeTM#jN"N ,㹌לCountry of originUnited Stateso"TԂTM#jD"H̀‰MissionTelecommunicationsj#eT>TG#^F"/ۀ0Geostationary orbitover asiajԂTTM#j:" &㉓gLaunch vehicleProton&>T΃T# 8TT' "(OTechnical data8΃T>T' " Specificationsc"TTA#RD&Prime contractorAerospatiale?N >TTA#RPlatformTTCTA#R&"Mass at launchSTTA#R$ Mass in orbitOCTTA#RDimensionQT6TA#R Solar arraySTTA#R$ StabilizationN 6T׆TA#RDC powerUT,TA#R($Design lifetime&׆TRT# 1 ,TT'  Ku-bandYRT܇TA#R0(Main transponders28YT5TA#R0,Backup transpondersK ܇TTA#RPowerO5TψTA#RBandwidth{8TJTC#VpCoverageChina beamNE Asia & Philippines beamIndiaN ψTTA#REIRP maxM JTTA#RG/T maxRT7TA#R"Polarization&T]T# 17TT1W{TTTT+]TT) "VȠ$To view this page you need to register&TT# 5T=T1w܂|=T~TďTGE 2A T~T5 :⧙" GE 21 =TT'  Generalg ~TTG#^@") Designation24713 / 97002A\TrTA#R6Launch date30 Jan 1997t'TTM#jN"N ,㹌לCountry of originUnited Stateso"rTUTM#jD"H̀‰MissionTelecommunications]TTA#R8,Geostationary orbit85Wn!UT TM#jB" &6E+Launch vehicleAriane V93TώT+ $ -Satcom K1 replacement. All the Ku-band transponders have been secured for 4 years (with an option up to 15 years) by Primestar8 TT' "(OTechnical data=ώTDT' , EIRP coverage (dBW):TďTF \twPvz鉂[IFkviC-bandKu-bandSpecificationsC-bandKu-band1DT T1} T\TďT TďTPďT\T6 <6qPdI"GE 2's C-band EIRP1 TT1~TTQ\TT6 <8qPdI"GE 2's Ku-band EIRP6TT1| TVTTGE 2AB TVT5 :⧙" GE 2A1 TT'  GeneralYVTTG#^$") Designationa TATA#R@Launch dateplanned for 2000t'TTM#jN"N ,㹌לCountry of originUnited Stateso"AT$TM#jD"H̀‰MissionTelecommunicationsj#TTG#^F"/ۀ0Geostationary orbitover asia\$TTG#^*" &Launch vehicle&TT# 8THT' "(OTechnical data8TT' " Specificationsc"HTTA#RD&Prime contractorAerospatiale?N T1TA#RPlatformTTTA#R&"Mass at launchS1TTA#R$ Mass in orbitOT'TA#RDimensionQTxTA#R Solar arrayS'TTA#R$ StabilizationN xTTA#RDC powerUTnTA#R($Design lifetime&TT# 1 nTT'  Ku-bandYTTA#R0(Main transponders36YTwTA#R0,Backup transpondersK TTA#RPowerOwTTA#RBandwidth}:TTC#VtCoverageAustralia beamSouth East Asia beamSteerableN TTA#REIRP maxM T)TA#RG/T maxRT{TA#R"Polarization&)TT# 1{TT1WT&TLTT+T&T) "VȠ$To view this page you need to register&TLT# 5&TT1TT'UGE 3A LTT5 :⧙" GE 31 TT'  Generalg TZTG#^@") Designation24936 / 97050A[TTA#R4Launch date4 Sep 1997t'ZT)TM#jN"N ,㹌לCountry of originUnited Stateso"TTM#jD"H̀‰MissionTelecommunicationse)TTG#^<"/ۀ0Geostationary orbit87Wv)TsTM#jR" &yjLaunch vehicleAtlas Centaur #109aTT, (dSpacenet 3R replacement. Tested at 83W. Went operational on 1 Oct 1997Worth $100 million8sT8T' "(OTechnical data=TuT' , EIRP coverage (dBW)^8T'UH `wPvz鉂[IFkviC-bandKu-bandSpecificationsC-bandKu-bandRoyal OrduT'ULTnance Leros apogee engine5uT\U1F\UUUGE 4A 'UU5 :⧙" GE 41 \UU'  GeneralYU'UG#^$") Designationa UUA#R@Launch date3rd quarter 1999t''UUM#jN"N ,㹌לCountry of originUnited Stateso"UkUM#jD"H̀‰MissionTelecommunicationsfUUG#^>"/ۀ0Geostationary orbit101W\kU-UG#^*" &Launch vehicleEUrU* $6iSshould replace ASC 2 8-UU' "(Technical data]&rUU7 >L[IFkviSpecificationsC-bandKu-band1U8U1W8UUUT+UU) "VȠ$To view this page you need to register&8UU# 5UU1 U(UUGE 5A U(U5 :⧙" GE 51 UYU'  GeneralY(UUG#^$") DesignationQYUUA#R Launch datet'UwUM#jN"N ,㹌לCountry of originUnited Stateso"UUM#jD"H̀‰MissionTelecommunicationsewUKUG#^<"/ۀ0Geostationary orbit79WjUUM#j:" &2!Launch vehicleAriane^KU7U$ First time a US operator buys the satellite & launch services from European-only companies8UoU' "(OTechnical data87UU' " Specificationsb!oU UA#RB&Prime contractorAerospatiale[Ud UA#R4PlatformSpacebus 2000[ U UA#R4"Mass at launch1760 kgSd U UA#R$ Mass in orbitO Ua UA#RDimensionQ U UA#R Solar arraySa U UA#R$ StabilizationY U^ UA#R0DC powerEOL: 3000 W] U UA#R8$Design lifetime12 years&^ U U# 1 U U'  Ku-bandY Uk UA#R0(Main transponders16Y U UA#R0,Backup transpondersK k U UA#RPowerU Ud UA#R(Bandwidth54 MHzS U UA#R$CoverageCONUSN d UUA#REIRP maxM URUA#RG/T maxRUUA#R"Polarization&RUU# 1UU1WUOUuUT+UOU) "VȠ$To view this page you need to register&UuU# AOUU1RU @U+FUProgram: GE*StarAuU @U, (," Program: GE*StarU @UuU]-UiBU0 .[D"Telecommunication program operated by GE Americom. It is made of colocated Ka-band satellites. It was approved by the FCC in May 1997The GE*Star system will allow symmetric and asymmetric data communications transmission rates ranging from 384 Kbps to 40 Mbps.Slots: 105W, 85W, 17W, 56E and 114.5E, 2 satellites per slot except at 56E (only 1 satellite)The spacecraft will feature on-board processors that can accommodate large streams of data traffic and switch them between spot beams to provide full connectivity and worldwide coverage. 8 @UBU' "(OTechnical data1 iBUBU'  Ka-bandWBU)CUA#R,(Main transpondersYBUCUA#R0,Backup transpondersK )CUCUA#RPowerOCUDUA#RBandwidth[CUwDUA#R4Coverage44 spot beamsTDUDUA#R&EIRP max54 dBW\wDU'EUA#R6Polarizationlinear H/VMDUEUB#TFrequenciesUplink: 28.35-28.6 and 29.25-30.0 GHzDownlink: 19.7-20.2 GHzuQ'EU+FU$ 11 times frequency reuse through the use of spatially diverse satellite beams1EU\FU1W\FUFUFUT++FUFU) "VȠ$To view this page you need to register&\FUFU# @FUGU1 GUbGUQIUProgram: GeizerLFUbGU5 :0))U" Program: GeizerGUQIU' Russian military telecommunication program. The satellites composing this program are part of the Cosmos fleet. Those geostationary satellites are located on the 'Potok' slots. Potok was a telecommunication project designed in the early 80ies; was to operate in C-band. Three slots were registered with the ITU as Potok: 13.5W, 80E and 168E.Some satellites could have been leased as standard telecommunication satellites to transmit phone traffic.1bGUIU1WIUIUIUT+QIUIU) "VȠ$To view this page you need to register&IUIU# 1IU-JU1(-JU$KUIU$KUf #6vV ww!w(wfx~%x -x2xProgram: GeizerCosmos 1366Cosmos 1540Cosmos 1738Cosmos 1888Cosmos 1961Cosmos 2085Cosmos 2172Cosmos 2291Cosmos 23191-JUUKU1WUKUKUKUT+$KUKU) "VȠ$To view this page you need to register&UKUKU# 1KULU1ULU?OUcOU=KU=LU# 4Geizer's specifications\LULUA#R6&Prime contractorNPO-PMT=LULUA#R&PlatformGeizerTLUAMUA#R&"Mass at launchSLUMUA#R$ Mass in orbitOAMUMUA#RDimensionQMU4NUA#R Solar arraySMUNUA#R$ StabilizationN 4NUNUA#RDC powerj)NU?OUA#RR$Design lifetimeprobably 3 to 5 years$NUcOU" 1?OUOU1WOU U2UT+cOU U) "VȠ$To view this page you need to registerOU UcOU&OU2U# 8 UjU1' jUUUGemstar@2UU2 4"  GemstarU2jUU# dGlobal Messaging Satellite, also called Vitasat1 U0U'  General\UUA#R6Launch date15 Aug 1995t'0UUM#jN"N ,㹌לCountry of originUnited Stateso"UoUM#jD"H̀㓉MissionTelecommunicationsm U܂UM#j@" &bnW"Launch vehicleAthena #1^oU:UD#X4"Mass at launch150 kg&܂U`U# 5:UU'  End of life_`UUA#R<"Out of service15 Aug 1995YUMUA#R0CauseLaunch failure!UnU- (;Cost: between $2 million and $3 million, built by CTA Inc of Rockville, Md (base on the Gemstar bus).Was designed to provide electronic mail services and global location services for trucking fleet operators. Was also to be used by VITA<MUU' *O External resourcesO(nUU' Phttp://www.cta-space.com/s26-00.html7U0U1+' 0UoUiUGeos 3? UoU2 4"  Geos 31 0UU'  Generalg oUUG#^@") Designation07734 / 75027A[UbUA#R4Launch date9 Apr 1975t'UևUM#jN"N ,㹌לCountry of originUnited Statesp#bUFUM#jF"H̀CV$MissionScientific: geodesy^ևUUA#R:"Perigee/Apogee820/845 kmUFUUA#R(Inclination115UUNUA#R(Period101.6 mins&UUM#jL" &p㉂Launch vehicleThor Delta #109ZNUUA#R2"Mass at launch241 kgN*UiU$ TMission: Ocean and islands map-making.6UU1dJUՊU7UGFO 16 iUՊU, (" GFO 1BUU# >Also called Geosat Follow-on1 ՊUHU'  Generalg UUG#^@") Designation25157 / 98007A\HU UA#R6Launch date10 Feb 1998t'UUM#jN"N ,㹌לCountry of originUnited Statesf UUG#^>OperatorBall Corporationm&URUG#^L"H̀MissionMilitary: remote sensingZUUA#R2"Perigee/Apogee800 kmURUUA#R(Inclination108SUTUA#R$Period101 minm UUM#j@" &㻦ʼnLaunch vehicleTaurus #2[TUUA#R4Launch siteVandenbergc>UU% }Using an advanced radar altimeter (13.5 GHz), the GFO satellite is designed to provide precise information on changes in sea surface heights, eddies and warm/cold water fronts. The data wiUUiUll be used to support Navy tactical operations. The GFO contract was awarded to Ball Aerospace Systems Group in August 1992 by the U.S. Navy's Space and Naval Warfare systems command. The Navy contract calls for a "turnkey" satellite system, and contract options for two additional spacecraft. GFO will follow the successful Geosat satellite that completed service in January 1990.lEUU' Will downlink directly to vessels. For the GFO mission, Taurus will use Thiokol's Castor 120 solid rocket motor as the vehicle's first stage, and incorporate a larger, Orbital-developed payload fairing, providing a 120% increase in payload volume. Modifications to the Taurus booster, particularly a new payload fairing twice the size of the one used on the first flight, will result in a much more capable rocket. This configuration was proposed for NASA's MedLite program, and another that results in an extra 500 pounds of secondary payload capability for the GFO mission.oUU$ The initial contract worth $115 million calls for 3 GFO satellites, the last one should be launched in 2007<UU' *O External resourcespUkU5 :http://gfo.bmpcoe.org/http://osb3.wff.nasa.gov/gfo/http://www.fas.org/spp/military/program/met/gfo.htm8UU' "(Technical data8kUU' " Specificationsy8UTUA#Rp&Prime contractorBall Aerospace & Technologies Corp.VUUA#R*PlatformTechstarZTUUA#R2"Mass at launch365 kgSUWUA#R$ Mass in orbitOUUA#RDimensionQWUUA#R Solar arraySUJUA#R$ StabilizationSUUA#R$DC power126 W\JUUA#R6$Design lifetime8 years>U7U$ 496 MB on-board storage6UmU1W҅mUUUGFO 26 7UU, (" GFO 2D!mUU# BAlso called Geosat Follow-on 21 UU'  GeneralYUqUG#^$") DesignationUUUA#R(Launch date2001t'qU:UM#jN"N ,㹌לCountry of originUnited StatesUUUG#^"H̀MissionT:UUA#R&"Perigee/ApogeeQU4UA#R InclinationL UUA#RPeriod\4UUG#^*" &Launch vehicleQU-UA#R Launch sitevUU& To be built by the NRL, Washington. Will provide wave height, and wind speed. Will downlink directly to vessels.1-UU1WUNUtUT+UNU) "VȠ$To view this page you need to register&UtU# 8NUU1 JUUVGeotail@tUU2 4"  Geotail1 UU'  Generalg UUG#^@") Designation22049 / 92044Ah'U VA#RNLaunch date24 Jul 1992 at 14:26 UTU VtU3UVS#vf"N (,㹌לbCountry of originUnited States and Japant- VVG#^Z"H̀MissionScientific: lunar gravity studyb!VhVA#RB"Perigee/Apogee41363/58542 kmVVVA#R*Inclination22.4VhVVA#R*Period4750.6 minp#VVM#jF" &p㉂Launch vehicleDelta 2 #212I%VV$ JLaunched under the MELVS contract<V V' *O External resourcesVV6 : http://www.gtl.isas.ac.jp/http://spacelink.msfc.nasa.gov/NASA.Projects/Satellites/GEOTAIL/http://hurlbut.jhuapl.edu/Geotail/6 VV1 ҅KV9V VGFZ 1> V9V2 4"  GFZ 11 VjV'  Generalh!9VVG#^B") Designation23558 / 86017JEh'jV:VA#RNLaunch date19 Apr 1995 at 19:12 UTfVVG#^>"N ,Country of originGermanys2:VVA#RdOperatorGeoForschungsZentrum Postdam, Germanyp#VVM#jF"H̀CV$MissionScientific: geodesy^VVA#R:"Perigee/Apogee383/394 kmVV7VA#R*Inclination51.6TVVA#R&Period92.3 min_7VVG#^0" &Launch vehiclen/aTV>VA#R&Launch siteMirlEV V' A fake replica was launched on 17 Apr 1995 (catnr: 23557).25 observatories all over the world will execute measurements by laserreflections. Stations are among others: London, Grasse (France), Postdam, Easterisland, Graz (Austria) and even one in Kirgizie. The stations can 'catch' GFZ 1 with a beamwidth of 200 meters.<>V V' *O External resourcesW0 V= V' `http://www.gfz-potsdam.de/pb1/GFZ1/GFZ1.html8 Vu V' "(OTechnical data8= V V' " Specificationsc"u V VA#RD&Prime contractorKayser-ThredeN V^ VA#RPlatformY V VA#R0"Mass at launch20 kgS^ V VA#R$Diameter21 cmK VU VA#RWidthL V VA#RHeightSU V VA#R$ StabilizationN VB VA#RDC powerU V VA#R($Design lifetimeQ-B V V$ ZSphere covered with laser retroreflectors> V&V1_&VtVVProgram: GGSEN VtV8 @.G" Program: GGSErJ&VV( Gravity Gradient Stabilization ExperimentAmerican scientific program1tVV1VV@VVO nhAhAhAhAhAProgram: GGSEGGSE 1GGSE 2GGSE 3GGSE 4GGSE 57VV1V0@VCVGGSE 1GV0@V8 @ GV0@VV" GGSE 11 Va@V'  Generalg 0@V@VG#^@") Designation00728 / 64001B\a@V$AVA#R6Launch date11 Jan 1964t'@VAVM#jN"N ,㹌לCountry of originUnited States_$AVAVG#^0"H̀MissionScientific^AVUBVA#R:"Perigee/Apogee899/916 kmVAVBVA#R*Inclination69.9UUBVCVA#R(Period103.2 minn!BVnCVM#jB" &#*≂Launch vehicleThor Agena[CVCVA#R4Launch siteVandenberg$nCVCV" 7CV$DV1($DVkDV8HVGGSE 2GCVkDV8 @ G" GGSE 21 $DVDV'  Generalg kDVEVG#^@") Designation01244 / 65016B[DV^EVA#R4Launch date9 Mar 1965t'EVEVM#jN"N ,㹌לCountry of originUnited Statesp#^EVBFVM#jF"H̀CV$MissionScientific: geodesy^EVFVA#R:"Perigee/Apogee896/928 kmVBFVFVA#R*Inclination70.1UFVKGVA#R(Period103.2 minn!FVGVM#jB" &#*≂Launch vehicleThor Agena[KGVHVA#R4Launch siteVandenberg$GV8HV" 7HVoHV1KoHVHVLVGGSE 3G8HVHV8 @ G" GGSE 31 oHVHV'  Generalg HVNIVG#^@") Designation01292 / 65016C[HVIVA#R4Launch date9 Mar 1965t'NIVJVM#jN"N ,㹌לCountry of originUnited Statesp#IVJVM#jF"H̀CV$MissionScientific: geodesy^JVJVA#R:"Perigee/Apogee896/915 kmVJVAKVA#R*Inclination70.1UJVKVA#R(Period103.0 minp#AKVLVM#jF" &#*≂Launch vehicleThor Agena D[KVaLVA#R4Launch siteVandenberg$LVLV" 7aLVLV1(?LVMVVGGSE 4GLVMV8 @ G" GGSE 41 LV4MV'  Generalg MVMVG#^@") Designation02828 / 67053C\4MVMVA#R6Launch date31 May 1967t'MVkNVM#jN"N ,㹌לCountry of originUnited Statesp#MVNVM#jF"H̀CV$MissionScientific: geodesy^kNV9OVA#R:"Perigee/Apogee903/910 kmVNVOVA#R*Inclination70.0U9OV VA#R(Period103.1 minOV VLVp#OV|VM#jF" &#*≂Launch vehicleThor Agena D[ V׀VA#R4Launch siteVandenberg$|VV" 7׀V2V1K2VyVIVGGSE 5GVyV8 @ G" GGSE 51 2VV'  Generalg yVVG#^@") Designation02834 / 67053D\VmVA#R6Launch date31 May 1967t'VVM#jN"N ,㹌לCountry of originUnited Statesp#mVQVM#jF"H̀CV$MissionScientific: geodesy^VVA#R:"Perigee/Apogee906/913 kmVQVVA#R*Inclination70.0UVZVA#R(Period103.2 minp#VʄVM#jF" &#*≂Launch vehicleThor Agena D[ZV%VA#R4Launch siteVandenberg$ʄVIV" D%VV1 V݅V~VProgram: GlobalstarPIV݅V5 :8`" Program: GlobalstarZ.V7V, &]PGlobalstar is a low-earth orbit (LEO) satellite-based telecommunications system founded by Loral Corp. and Qualcomm Inc. that will offer low-cost, high-quality global telephony and other digital telecommunications services to areas currently underserved or not served by existing wireline and cellular telecommunications systems. Operated by Loral Qualcomm Satellite Services Inc.The satellites will be launched into eight orbital planes, with six satellites in each plane to provide continuous global coverage. Commercial service is anticipated 1999.݅V)V' Space Systems/Loral has a fixed-price contract for the construction of Globalstar's satellites, which it will perform in conjunction with various other members of the international Space Systems/Alliance, which includes Aerospatiale and Alcatel of France, Daimler-Benz Aerospace of Germany, Alenia and Finmeccanica of Italy, and with Hyundai of South Korea.Globalstar proposed next generation would be composed of 64 LEO satellites and 4 GEO satellites.87VaV' "(OTechnical data2 )VV' O LaunchesaVbV2 2;p㉂'CMThe launch of the first 4 Globalstar satellites was planned for 1997 from Cape Canaveral, aboard a two-stage Delta 2 rocket. McDonnell Douglas Corp. has been awarded a contract valued at about $50 million for the inaugural launch of the Globalstar telecommunications system. A second launch wil also take place.3 launches carring each 12 satellites will be conducted from Tyuratam in 1998 on Zenit. The 12-satellite launch configuration will be composed of three tiers of four satellites each, allowing each satellite to be dispensed sequentially. The dispensing technology will be derived from previous Multiple Independent Reentry Vehicle (MIRV) development.]VV$ 3 Soyuz-Icare vehicles will be used in 1998 (from the Starsem company), 4 satellites each@bV#V' 2 Constellation overviewSVvVA#R$ Orbit typeLEOb!#V؎VA#RB Orbit range1414 km, circularc"vV;VA#RD &Nb of satellites48 + 8 backupS؎VVA#R$ Nb of planes8T;V VA#R& Inclination52V VIV^VjVA#R: 2Nb beams per satellite16V VVA#R* Coverage5796 kmTjVVA#R& ModulationCDMAJVVB#T *Mobile frequenciesUplink: 1610-1626.5 MHzDownlink: 2483.5 - 2500 MHzGV)VB#T (Fixed frequenciesUplink: 5091 - 5250 GHzDownlink: 6875 - 7055 GHzZVVA#R2 "Satellite mass425 kgq0)VVA#R` Coverageall longitudes, 74N - 74S latitudesd#VXVA#RF &Operational date1999 (planned)&V~V# 1XVV1UVV3VA~VV) "0xProgram: GlobalstarVV#㬝QP㭝QP㮝QP㯝QP㱝QP㳝QP{}{}Globalstar 1Globalstar 2Globalstar 3Globalstar 4Globalstar 6Globalstar 8Globalstar 14Globalstar 15$V3V" 1VdV1dVVA3VV# <Globalstar's specificationsj)dVVA#RR&Prime contractorSpace Systems/Loral YVhVA#R0PlatformGlobalstar?ZVVA#R2"Mass at launch450 kgShVVA#R$ Mass in orbit`VuVA#R>Dimensiontrapezoidal shape]VVA#R8Solar array10.75 m spanx7uVJVA#Rn Stabilization3 axis (orbit determination with GPS)YVVA#R0DC powerBOL: 1100 W^JVVA#R:$Design lifetime7.5 yearsVV% eSatellites are built by Alenia Spazio in Rome. The structure and thermic control is built by Aerospatiale, the payload by Alcatel and the propulsion and solar arrays by Dasa.1V V1 VV:VCV# .Globalstar's payloada VVA#R@Capacity2800 phone circuitsSCVVA#R$Voice9600 bpsL VCVA#R FaxyesRVVA#R"Data9600 bpsGCVVA#R Mobile uplink1610 - 1626.5 MHz via 61-element phased-array antennaIVVA#R$Mobile downlink2483.5 - 2500 MHz via 91-element phased-array antennac"V VA#RD"Gateway uplink5091 - 5250 MHze$VoVA#RH&Gateway downlink6875 - 7055 MHzK' VV$ NCompatible with GSM, CDMA and AMPS.= oVV1&V@V9WGlobalstar 1IV@V5 :*`" Globalstar 11 VqV'  Generalg @VVG#^@") Designation25162 / 98008A\qV4VA#R6Launch date14 Feb 1998t'VVM#jN"N ,㹌לCountry of originUnited Stateso"4V#WM#jD"H̀㓉MissionV#WVTelecommunications[V~WA#R4"Perigee/Apogee1400 kmT#WWA#R&Inclination52L ~WWA#RPeriodp#WWM#jF" &p㉂Launch vehicleDelta 2 #254&WW# 8WW' "(Technical dataMW9W0 0:x ⍿SpecificationsPayload= WvW1'vWWWGlobalstar 2I9WW5 :*`" Globalstar 21 vWW'  Generalg WWWG#^@") Designation25163 / 98008B\WWA#R6Launch date14 Feb 1998t'WW'WM#jN"N ,㹌לCountry of originUnited Stateso"WWM#jD"H̀㓉MissionTelecommunications['WWA#R4"Perigee/Apogee1400 kmTWEWA#R&Inclination52L WWA#RPeriodp#EWWM#jF" &p㉂Launch vehicleDelta 2 #254&W'W# 8W_W' "(Technical dataM'WW0 0:x ⍿SpecificationsPayload= _WW1W2W WGlobalstar 3IW2W5 :*`" Globalstar 31 WcW'  Generalg 2WWG#^@") Designation25164 / 98008C\cW&WA#R6Launch date14 Feb 1998t'WWM#jN"N ,㹌לCountry of originUnited Stateso"&W WM#jD"H̀㓉MissionTelecommunications[Wd WA#R4"Perigee/Apogee1400 kmT W WA#R&Inclination52L d W WA#RPeriodp# Wt WM#jF" &p㉂Launch vehicleDelta 2 #254& W W# 8t W W' "(Technical dataM W W0 0:x ⍿SpecificationsPayload= W\ W1\ W WWGlobalstar 4I W W5 :*`" Globalstar 41 \ W W'  Generalg W= WG#^@") Designation25165 / 98008D\ W WA#R6Launch date14 Feb 1998t'= W WM#jN"N ,㹌לCountry of originUnited Stateso" W| WM#jD"H̀㓉MissionTelecommunications[ W WA#R4"Perigee/Apogee1400 kmT| W+WA#R&Inclination52L WwWA#RPeriodp#+WWM#jF" &p㉂Launch vehicleDelta 2 #254&wW W# 8WEW' "(Technical dataM WW0 0:x ⍿SpecificationsPayload= EWW1W$@WDWGlobalstar 6IW$@W5 :*`"W$@WW Globalstar 61 WU@W'  Generalg $@W@WG#^@") Designation25306 / 98023A\U@WAWA#R6Launch date24 Apr 1998t'@WAWM#jN"N ,㹌לCountry of originUnited Stateso"AWAWM#jD"H̀㓉MissionTelecommunications[AWVBWA#R4"Perigee/Apogee1400 kmTAWBWA#R&Inclination52L VBWBWA#RPeriodp#BWfCWM#jF" &p㉂Launch vehicleDelta 2 #257&BWCW# 8fCWCW' "(Technical dataMCWDW0 0:x ⍿SpecificationsPayload= CWNDW1INDWDWHWGlobalstar 8IDWDW5 :*`" Globalstar 81 NDWDW'  Generalg DW/EWG#^@") Designation25307 / 98023B\DWEWA#R6Launch date24 Apr 1998t'/EWEWM#jN"N ,㹌לCountry of originUnited Stateso"EWnFWM#jD"H̀㓉MissionTelecommunications[EWFWA#R4"Perigee/Apogee1400 kmTnFWGWA#R&Inclination52L FWiGWA#RPeriodp#GWGWM#jF" &p㉂Launch vehicleDelta 2 #257&iGWGW# 8GW7HW' "(Technical dataMGWHW0 0:x ⍿SpecificationsPayload> 7HWHW1yHW IWLWGlobalstar 14JHW IW5 :,`" Globalstar 141 HW=IW'  Generalg IWIWG#^@") Designation25308 / 98023C\=IWJWA#R6Launch date24 Apr 1998t'IWtJWM#jN"N ,㹌לCountry of originUnited Stateso"JWJWM#jD"H̀㓉MissionTelecommunications[tJW>KWA#R4"Perigee/Apogee1400 kmTJWKWA#R&Inclination52L >KWKWA#RPeriodp#KWNLWM#jF" &p㉂Launch vehicleDelta 2 #257&KWtLW# 8NLWLW' "(Technical dataMtLWLW0 0:x ⍿SpecificationsPayload> LW7MW1#I7MWMWzWGlobalstar 15JLWMW5 :,`" Globalstar 151 7MWMW'  Generalg MWNWG#^@") Designation25309 / 98023D\MWuNWA#R6Launch date24 Apr 1998t'NWNWM#jN"N ,㹌לCountry of originUnited Stateso"uNWXOWM#jD"H̀㓉MissionTelecommunications[NWOWA#R4"Perigee/Apogee1400 kmTXOWWA#R&InclinationOWWLW52L OW_WA#RPeriodp#WπWM#jF" &p㉂Launch vehicleDelta 2 #257&_WW# 8πW-W' "(Technical dataMWzW0 0:x ⍿SpecificationsPayloadA-WW1K0WWWProgram: GlonassIzWW2 40"  Program: GlonassW͂W/ ,5 qiGlobal'naya Navigatsionnaya Sputnikovaya SistemaRussian navigation program part of the Cosmos constellation. The satellites carry an atomic clock.:WW' &O Planes and slotsk͂WW$ The Glonass series orbit in three distinct planes that are 120 deg apart. Each plane has eight "slots".)W7Wx#RQ  & < SlotPlane 1Plane 2Plane 3WWi#:Q%x261771 (Cosmos 2179)7WCWi#:Q,x262757 (Cosmos 2235)WɅWi#:Q-x263763 (Cosmos 2294)CWOWi#:Q-x264762 (Cosmos 2296)ɅWՆWi#:Q{$x265249 (Cosmos 2111)OW[Wi#:Q-x266764 (Cosmos 2295)ՆWWi#:Q,x267759 (Cosmos 2236)[WgWi#:Q%x268769 (Cosmos 2178)5WWu#jQ. 3x3xd9776 (Cosmos 2323) / 778 (Cosmos 2324) gWWo#@Q "2x:10781 (Cosmos 2317) W/Wo#@Q "2x:11785 (Cosmos 2318)WWi#<Q ,x812767 (Cosmos 2287) /WEWo#@Q "3x:13782 (Cosmos 2325)W̋Wi#<Q ,x814770 (Cosmos 2288) EW[Wo#@Q "2x:15780 (Cosmos 2316)̋WWi#<Q ,x816775 (Cosmos 2289)[WiWi#<Q ,x17760 (Cosmos 2275)WWi#<Q ,x18758 (Cosmos 2277)iW{Wl#>Q "x4x19777 (Cosmos 2309)WWi#<Q v4x20765 (Cosmos 2307){WWi#<Q ;-x21756 (Cosmos 2205)WWi#<Q w4x22766 WWzW(Cosmos 2308)WWi#<Q ,x23761 (Cosmos 2276)W*Wi#<Q :-x24774 (Cosmos 2204)&WPW# <*WW' *O External resources|NPWW. ,http://www.rssi.ru/SFCSIC/SFCSIC_main.htmlhttp://satnav.atc.ll.mit.edu/8W@W' "(Technical dataMWWB#T$Frequency (MHz)L1 = 1602 + 0.5625 * channelL2 = 1246 + 0.4375 * channel$@WW" 1W$W1W$WxWWT+WxW) "VȠ$To view this page you need to register&$WW# = xWW1_[W(WWProgram: GMSMW(W8 @,c%" Program: GMS W5W+ $ Geostationary Meteorological Satellite, also called Himawari which means "sunflower"Japanese Meteorology Agency satellite programOriginated 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.1 (WfW' O ContactzT5WW& Ministry of Transport2-1-3 Kasumigaseki, Chiyoda-ku, TokyoTel: +81-03-3212-8341<fWW' *O External resourcesi;WW. ,vhttp://www.jwa.go.jp/gms.htmlhttp://www.kishou.go.jp1WW1W?W:W?WO ntvSTTTTTProgram: GMSGMS 1GMS 2GMS 3GMS 4GMS 51WpW1UpWoWW:?WW# .GMS's specifications`pW WA#R>0&Prime contractorHughes/NECTW^WA#R&0PlatformHS 378Z WWA#R20"Mass at launch682 kgT^W WA#R&0Diameter2.15 mRW^WA#R"0Height3.45 mb! WWA#RB0 StabilizationSpin stabilizedS^WWA#R$0DC power291 W\WoWA#R60$Design lifetime5 years$WW" 1oWW1KW X3WW#  GMS's payload]0WTW- *`  VISSR (Visible and IR Spin Scan Radiometer)w5WWB#Tj4Wavebands0.5-0.75 m (visible)10.5-12.5 m (IR)j(TW5WB#TP4Resolutionvisible: 1.25 kmIR: 5 kms2WWA#Rd42Image repeat frequency30 minutes (full Earth)&5WW# Q$WW- *HO  SEM (Space Environment Monitor)W!W< F    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.DWeW' :O Communications instrumentsy@!W X9 B    WEFAX (Weather Facsimile)DCS (Data Collection System)eW XW6eWBX1cBBXXXGMS 1F XX8 @c%" GMS 1<BXX# 2Also called Himawari 11 XX'  Generalg X\XG#^@") Designation10143 / 77065A\XXA#R6Launch date14 Jul 1977l\X$XM#j>"N ,bCountry of originJapanhXXM#j6"H̀DVMissionMeteorology^$XXA#R:,Geostationary orbit140Es&X]XM#jL" &p㉂Launch vehicleThor Delta #132&XX# 5]XX'  End of lifeWXXA#R,"Out of serviceyes&X5X# 8XmX' "(Technical dataM5XX0 0:EC(7SpecificationsPayload6mXX1VwX6X[ XGMS 2FX6X8 @c%" GMS 2<XrX# 2Also called Himawari 21 6XX'  Generalg rX XG#^@") Designation12677 / 81076A\XfXA#R6Launch date10 Aug 1981l XXM#j>"N ,bCountry of originJapanhfX:XM#j6"H̀DVMissionMeteorology^XXA#R:,Geostationary orbit140Ef:XXM#j2" &JLaunch vehicleN2&X$X# 5XYX'  End of lifeW$XXA#R,"Out of serviceyes&YXX# 8X X' "(Technical dataMX[ X0 0:EC(7SpecificationsPayload6 X X1B X X5@XGMS 3F[ X X8 @c%" GMS 3< X X# 2Also called Himawari 31 XD X'  Generalg  X XG#^@") Designation15152 / 84080A[D X XA#R4Launch date2 Aug 1984l Xr XM#j>"N ,bCountry of originJapanh X XM#j6"H̀DVMissionMeteorologyb!r X< XA#RB,Geostationary orbitsee belowf X XM#j2" &JLaunch vehicleN2&< X X# 2 X X'  Location X Xm#:   " BeginEndPosition X Xj#6"&(L: 2 Aug 1984140E XXj#<,.Feb 1995Jun 1995120E& XX# 5XX'  End of life\XHXA#R6"Out of serviceJul 1995&XnX# 8HXX' "(Technical dataQnX5@X2 4EC(7SpecificationsPayloadDownlink frX5@X[ Xequency-bands: UHF or VHF, L and S-band6Xk@X1wk@X@XbFXGMS 4F5@X@X8 @c%" GMS 4<k@X@X# 2Also called Himawari 41 @XAX'  Generalg @XAXG#^@") Designation20217 / 89070A[AXAXA#R4Launch date5 Sep 1989lAXLBXM#j>"N ,bCountry of originJapanhAXBXM#j6"H̀DVMissionMeteorologyb!LBXCXA#RB,Geostationary orbitsee belowfBX|CXM#j2" &JLaunch vehicleH1&CXCX# : |CXCX- */ۀ LocationCXfDXm#:   " BeginEndPosition'CXDXj#N">@L: 5 Sep 1989mid-Jun 1995140E fDXEXj#@Aug 1995120E, inclined&DXEX# 8EXEX' "(Technical dataQEXbFX2 4EC(7SpecificationsPayloadDownlink frequency-bands: UHF or VHF, L and S-band6EXFX1FFXFXKXGMS 5FbFXFX8 @c%" GMS 5<FXGX# 2Also called Himawari 51 FXKGX'  Generalg GXGXG#^@") Designation23522 / 95011B\KGXHXA#R6Launch date17 Mar 1995lGXzHXM#j>"N ,bCountry of originJapanhHXHXM#j6"H̀DVMissionMeteorologyp)zHXRIXG#^R"/ۀ0Geostationary orbit140E, inclinedfHXIXM#j2" &JLaunch vehicleH29RIXIX$ *Tested in 159.5E8IX)JX' "(Technical dataIXKX7 <'EC(7SpecificationsPayloadThe 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> )JX1LX10 1LXLX XProgram: GoesNKXLX8 @.G" Program: Goes1LXMMX5 83  l^gGeostationary Operational Environmental SatelliteAmerican program developed for GARP (Global Atmospheric Research Program) and operated by NOAA<LXMX' *O External resourcesMMXBNX6 :http://www.goes.noaa.gov/http://www.nnic.noaa.gov/SOCC/SOCC_Home.htmlhttp://psbsgi1.nesdis.noaa.gov:8080/EBB/ml/goes.htmlMX X% 5Notes: the imager and sounder sensors of Goes N and O (planned not before 2002) will be provided by ITT DEFENSE & ELECTRONICS (contract worth $177 million) Goes N to Q should have a solar X-ray imager built by Lockheed Martin. The Goes N and O satellites will be designed by Hughes, the contract is worth $423 million An option for Goes P and Q is available for $191 million and $185 million respectively.BNX XKX1BNX>X1>XZX XZX ހ) L......O'B...㝖.㔖.㕖.Program: GoesGoes 01Goes 02Goes 03Goes 04Goes 05Goes 06Goes GGoes 07Goes 08Goes 09Goes 10Goes 11Goes 121>XX1UXXXAZX́X# <Goes 6 & 7's specifications\X(XA#R60&Prime contractorHughesŹXXA#R20"Mass at launch835 kgR(XԂXA#R"0Length2.16 mRX&XA#R"0Height3.53 mb!ԂXXA#RB0 StabilizationSpin stabilized\&XXA#R60$Design lifetime5 years$XX" 1X9X1x9XX:XsX# .Goes 6 & 7's payloadwJ9XX- *  VAS (VISSR (Visible and IR Spin Scan Radiometer) Atmospheric Sounder)sXXE#X%Wavebands0.55-075 m (visible): 8 channels3.7-7.3 m (near IR): 2 channels7.7-14.7 m (mid IR): 2 channels6.7-14.7 m (mid IR): 2 channelsv4X7XB#ThResolutionvisible: 1, 2, 4 and 8 kmIR: 8-14 kmDXXB#T2Image repeat frequencyfull Earth: 30 minutessectors: 3 minutes7XtX% %Also equipped with 12 IR channels in a detector array for measurement of 3D structure of atmospheric temperature and water vapor distribution.Q$XŇX- *HO  SEM (Space Environment Monitor)tXLjX< F    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.DŇX X' :O Communications instrumentsu?LjXX6 <~   WEFAX (Weather Facsimile)DCS (Data Collection System)1 XX1X X[8X X# pGoes 8, 9, 10, 11 and 12's specifications (Goes Next)i(XuXA#RP0&Prime contractorSpace Systems/Loral[ XЊXA#R40"Mass at launch2300 kgYuX)XA#R00 Stabilization3 axis\ЊXXA#R60$Design lifetime5 yearsb)X X& Telemetry: 2209.086 & 2208.586 MHz (2 kbps)Command: 2034.2 MHz (250 bps)Data: 1694.0 MHz MHz1X>X1Q>XjXT1 XX# bGoes 8, 9, 10, 11 and 12's payload (Goes Next)O(>XX' P Imager (5-channel imaging radiometer)o.XPXA#R\Wavebands3.7, 6.7, 10.7, 12: visible, IRg%XXB#TJResolutionvisible: 1 kmIR: 4 km&PXݍX# DX!X' : Sounder (vertical sounder)r0ݍXXB#T`Wavebandsvisible: 1 channelIR: 18 channelsg%!XXB#TJResolutionvisible: 1 kmIR: 2 km&X X# Q$XqX- *HO  SEM (Space Environment Monitor) X[X: BI    XRS (Solar X-ray Sensor): ion chamber sensitive in 2 bandsEPS (Energetic PartqX[X Xicle Sensor): 3 detector groups for electron, proton and alpha particle fluxDqXX' :O Communications instruments[XjXE X     qWEFAX (Weather Facsimile)DCS (Data Collection System)Also equipped with SXI (Solar X-ray Imager) and a Sarsat repeter.8XX1;XXwXGoes 01HjXX8 @"G" Goes 01vXX+ &"SAlso called SMS 3 or Goes A3rd satellite of the SMS series and first operational satellite operated by the NOAA1 XX'  Generalg X#XG#^@") Designation08366 / 75100A\XXA#R6Launch date16 Oct 1975t'#XXM#jN"N ,㹌לCountry of originUnited StateshX[XM#j6"H̀DVMissionMeteorologyb!XXA#RB,Geostationary orbitsee belows&[X0XM#jL" &p㉂Launch vehicleThor Delta #116d#XXA#RF"Mass at launch627 kg (294 kg?)=0XX$ 2Visible and IR photos2 XX'  LocationXXm#:   " BeginEndPositionXXj#6$(*L: 16 Oct 197560Ew XXj# 90WxXXj# 115WxXyXj# 135W.XXj#\"$29 Jun 199181.2W; inclination: 10.5&yX7X# 5XlX'  End of lifeW7XXA#R,"Out of serviceyes&lXX# 8X!X' "(OTechnical dataV2XwX$ dBuilt by Ford AerospaceTransmits on 136.38 MHz8!XX1sXXEYGoes 02HwXX8 @"G" Goes 028X/X# *Also called Goes B1 X`X'  Generalg /XXG#^@") Designation10061 / 77048A\`X#XA#R6Launch date16 Jun 1977t'XXM#jN"N ,㹌לCountry of originUnited Statesh#XXM#j6"H̀DVMissionMeteorologyb!XaXA#RB,Geostationary orbitsee belows&XXM#jL" &p㉂Launch vehicleThor Delta #131 aXX% The satellite has been reactivated in 1995 to transmit educational programming in S-band. Used by the NSF to transmit live television broadcasts from its South Pole Station to public broadcasting facilities in the United States.: XX- */ۀ LocationXXm#:   " BeginEndPositionX7Yj#8$(X7YwX*L: 16 Oct 1975105W,XYj#X"$24 Oct 1993136W, inclination: 9.497YvYp#r /ۉ?see the Clarke Belt chart for latest location&YY# 8vYY' "(OTechnical dataqMYEY$ Built by Ford AerospaceDownlink frequency: 136.38, 1691 and 2297.5925 MHz8Y}Y1v;}YY YGoes 03HEYY8 @"G" Goes 038}YY# *Also called Goes C1 Y.Y'  Generalg YYG#^@") Designation10953 / 78062A\.YYA#R6Launch date16 Jun 1978t'YeYM#jN"N ,㹌לCountry of originUnited StateshYYM#j6"H̀DVMissionMeteorologyb!eY/YA#RB,Geostationary orbitsee belows&YYM#jL" &p㉂Launch vehicleThor Delta #142/YY% The satellite has been reactivated in 1995 to transmit educational programming in S-band. Used by the University of Hawaii to transmit educational programming throughout the Hawaiian Islands.2 YY'  LocationYFYm#:   " BeginEndPositionYYj#6$(*L: 16 Jun 197860E,FYaYj#X"$24 Oct 1993176.2W, inclination: 8'YYj#N.0~Jan 1995Jan 1996drifting East(aY Yj#PFeb 1996103W, inclination: 11&Y Y# 5 Y Y'  End of life\ Y; YA#R6"Out of serviceprobably& Ya Y# 8; Y Y' "(OTechnical dataqMa Y Y$ Built by Ford AerospaceDownlink frequency: 136.38, 1691 and 2297.5925 MHz8 YB Y1NB Y YYGoes 04H Y Y8 @"G" Goes 048B Y Y# *Also called Goes D1 Y Y'  Generalg YZ YG#^@") Designation11964 / 80074A[ Y YA#R4Launch date9 Sep 1980t'Z Y) YM#jN"N ,㹌לCountry of originUnited Statesh Y YM#j6"H̀DVMissionMeteorology^) Y YA#R:,Geostationary orbit135Ws& YbYM#jL" &p㉂Launch vehicleThor Delta #152& YY# 5bYY'  End of lifeWYYA#R,"Out of serviceyes&Y:Y# 8YrY' "(OTechnical data5:YY# $Built by Hughes8rYY1Y3@YFYGoes 05HY3@Y8 @"Y3@YYG" Goes 058Yk@Y# *Also called Goes E1 3@Y@Y'  Generalg k@YAYG#^@") Designation12472 / 81049A\@Y_AYA#R6Launch date22 May 1981t'AYAYM#jN"N ,㹌לCountry of originUnited Statesh_AY;BYM#j6"H̀DVMissionMeteorologyb!AYBYA#RB,Geostationary orbitsee belows&;BYCYM#jL" &p㉂Launch vehicleThor Delta #154ZBYjCYA#R2"Mass at launch900 kg&CYCY# 2 jCYCY'  LocationCYLDYm#:   " BeginEndPositionCYDYj#6$(*L: 22 May 198175W&LDYDY# 5DY,EY'  End of life\DYEYA#R6"Out of serviceprobably&,EYEY# 8EYEY' "(OTechnical data5EYFY# $Built by Hughes8EYSFY1vSFYFY NYGoes 06HFYFY8 @"G" Goes 068SFYFY# *Also called Goes F1 FYGY'  Generalg FYkGYG#^@") Designation14050 / 83041A\GYGYA#R6Launch date28 Apr 1983t'kGY;HYM#jN"N ,㹌לCountry of originUnited StateshGYHYM#j6"H̀DVMissionMeteorologyb!;HYIYA#RB,Geostationary orbitsee belows&HYxIYM#jL" &p㉂Launch vehicleThor Delta #168&IYIY# 2 xIYIY'  LocationIYZJYm#:   " BeginEndPositionIYJYj#8$(*L: 28 Apr 1983135W|ZJY\KYj#$1984100WxJYKYj# 110W\KYTLYj#,19891989135W&KYzLY# 5TLYLY'  End of life_zLYMYA#R<"Out of service21 Jan 1989RLY`MYA#R"CauseFailure&MYMY# 8`MYMY' "(Technical dataMMY NY0 0:YESpecificationsPayload7MYBNY1BNYNYY# 8YvY' "(Technical datag>YY8 @YEqSpecificationsPayloadTransmits in VHF-, L- and S-band. It is equipped with a Sarsat repeter8vYMY1}MYY YGoes 08HYY8 @"G" Goes 08:MYϊY# .Also known as Goes I1 YY'  Generalg ϊYgYG#^@") Designation23051 / 94022A\YËYA#R6Launch date13 Apr 1994t'gY7YM#jN"N ,㹌לCountry of originUnited StateshËYYM#j6"H̀DVMissionMeteorologye7YYG#^<"/ۀ0Geostationary orbit75Wq$YuYM#jH" &yjLaunch vehicleAtlas CentaurY\Y' On board were instruments for high resolution visible and UV imagers, and "sounders" for temperature and moisture profiles. Also on board were energetic particle detectors and a magnetometer.The satellite experienced loss of attitude control on 9 Jan 1997. One of the two momentum wheels was lost due to a tachometer failure. Goes 8 is now using its functioning momentum wheel in concert with the reaction wheel to maintain attitude control.8uYY' "(Technical dataM\Y Y0 0:kB$OASpecificationsPayloadY YY8YDY1DYY/YGoes 09H YY8 @"G" Goes 09:DYY# .Also known as Goes J1 YY'  Generalg Y^YG#^@") Designation23581 / 95025A\YYA#R6Launch date23 May 1995t'^Y.YM#jN"N ,㹌לCountry of originUnited StateshYYM#j6"H̀DVMissionMeteorologyb!.YYA#RB,Geostationary orbitsee belowq$YiYM#jH" &yjLaunch vehicleAtlas CentaurJ&YY$ LReplaced Goes 7 Cost: $220 million: iYY- */ۀ LocationYwYm#:   " BeginEndPosition#YYj#F$8:L: 23 May 1995Dec 199590WwYYj#,Feb 1996135W&YY# 8YY' "(Technical dataMY/Y3 45kB$OASpecificationsPayloadThe satellite lost a backup motor because of overheating. To cope with this problem the spacecraft, normally facing the earth all the time, will periodically be turned into another direction, and this 4 times a year when the problem is most important.8YgY1ބgYYIYGoes 10H/YY8 @"G" Goes 10D!gYY# BWas named Goes K before launch1 Y$Y'  Generalg YYG#^@") Designation24786 / 97019A^$YYA#R:Launch date25 April 1997t'Y]YM#jN"N ,㹌לCountry of originUnited StateshYYM#j6"H̀DVMissionMeteorology^]Y#YA#R:,Geostationary orbit105Wv)YYM#jR" &yjLaunch vehicleAtlas Centaur #107+#YY'  Should remain up to 2 year in in-orbit storage. worth $220 millionThe satellite has got a default: it's solar arrays cannot rotate properly. The satellite had to be put outside down to maximize solar energy reception, thus inverting the reception images.8YY' "(Technical dataMYIY0 0:kB$OASpecificationsPayload8YY1KYYfZGoes 11HIYY8 @"G" Goes 11G$YY# HNamed Goes L until it is launched1 YAY'  GeneralYYYG#^$") Designationd#AYYA#RFLaunch dateplanned in Dec 2003t'YrYM#jN"N ,㹌לCountry of originUnited StateshYYM#j6"H̀DVMissionMeteorologyd#rY>YA#RF,Geostationary orbit135 or 75Wq$YYM#jH" &yjLaunch vehicleAtlas Centaur&>YY# 8YZ' "(TecYZIYhnical dataMYfZ0 0:kB$OASpecificationsPayload1ZZ1WZZZT+fZZ) "VȠ$To view this page you need to register&ZZ# 8ZIZ1ބIZZ"ZGoes 12HZZ8 @"G" Goes 12G$IZZ# HNamed Goes M until it is launched1 Z Z'  GeneralYZbZG#^$") Designationd# ZZA#RFLaunch dateplanned in Aug 1999t'bZ:ZM#jN"N ,㹌לCountry of originUnited StateshZZM#j6"H̀DVMissionMeteorologyd#:ZZA#RF,Geostationary orbit135 or 75Wq$ZwZM#jH" &yjLaunch vehicleAtlas Centaur&ZZ# 8wZZ' "(Technical dataMZ"Z0 0:kB$OASpecificationsPayload1ZSZ1WSZZZT+"ZZ) "VȠ$To view this page you need to register&SZZ# BZZ1x ZaZZProgram: GorizontRZaZ8 @6봡" Program: GorizontGZZ8 >o7U=xxThe Gorizont satellite system is a general purpose network for communications owned by Informcosmos and operated by several firms, including Intersputnik. The network is composed of 370 ground stations.The payloads are Statsionar (C-band) and Loutch (Ku-band).1aZZ1UZ Z4 Z?ZZ) ",MProgram: GorizontZ Z3#4$o%o%o%o%o%o%o%o%o#o|#o}#o~#o#o#o#o#o#o#o#o#o#o#o#o#o#o#o#o#o#o0N#o#oGorizont 01Gorizont 02Gorizont 03Gorizont 04Gorizont 05Gorizont 06Gorizont 07Gorizont 08Gorizont 09Gorizont 10Gorizont 11Gorizont 12Gorizont 13Gorizont 14Gorizont 15Gorizont 16Gorizont 17Gorizont 18Gorizont 19Gorizont 20Gorizont 21Gorizont 22Gorizont 23Gorizont 24Gorizont 25Gorizont 26Gorizont 27Gorizont 28Gorizont 29Gorizont 30Gorizont 31Gorizont 32$Z4 Z" 1 Ze Z1e ZZ?4 Z Z# 8Gorizont's specifications\e Z ZA#R60&Prime contractorNPO PMZ ZZ ZA#R20PlatformNPO Gorizont[ Z ZA#R40"Mass at launch2120 kgWZ Z ZA#R,0Diameterabout 2 mU Za ZA#R(0Heightabout 5 mY Z ZA#R00 Stabilization3 axisTa ZZA#R&0DC power1300 Wa ZoZA#R@0$Design lifetime3 to 5 years[ZZ$ No North-South stabilisation. They also are equipped with one X- or L-band transponder.1oZZ1 ZHZ<Z[Z# 2Antenna Specifications^Zk@Z#_yxuM  : h   [Zk@ZZAntennaFrequency bandFunction / max gainCoverageBeam widthSteerability'[Z4AZ#N_yxu  4 North/SouthWest/East0k@ZAZ#`_yxu &6HTA1CTX / 19.0global17x17nonenone04AZBZ#`_yxu &6HTA2CRX / 19.0global17x17nonenoneIAZCZ#_yxu &2@LA3CTX / 30.0spot5x5noneonce West to East or East to West-BZbDZ#Z_yxu &2BNA4CTX / 22.0hemi9x18nonenone0CZ(EZ#`_yxu &6HTA5CRX / 19.0global17x17nonenone0bDZEZ#`_yxu &6HTA6CTX / 19.0global17x17nonenone3(EZFZ#f_yxu &>NZA7CRX / 25.0elliptical6x12nonenone3EZGZ#f_yxu &>NZA8CTX / 25.0elliptical6x12nonenoneQFZgHZ#_yxu 6BP\A9KuRX and TX / 30.0spot5x5noneonce East to East or East to Westc9GZHZ* $rfZSee also the transponder/antenna connection diagram1gHZHZ1UHZyLZLZ7HZ2IZ# (Gorizont's C-bandXHZIZA#R.0(Main transponders6Y2IZIZA#R00,Backup transpondersIIZnJZB#T0Power1 transponder (#6) of 40 W (TWTA)5 transponders of 15 W (TWTA)p.IZJZB#T\0Bandwidthspot (#6): 40 MHzothers: 36 MHz-nJZ LZd#002UCoverage andEIRP maxtransponder #6:global beam (A1): 35.6 dBWspot beam (A3): 46.1 dBW1 global beam(A6): 28.5 dBW1 large hemispheric beam (A4): 31 dBW1 little hemispheric beam (A8): 34 dBWn,JZyLZB#TX0Polarizationuplink: LHCPdownlink: RHCP$ LZLZ" 1yLZLZ1ULZ7OZ[OZ8LZMZ# *Gorizont's Ku-bandXLZ^MZA#R.0(Main transponders1YMZMZA#R00,Backup transpondersV^MZ NZA#R*0Power20 W (TWTA)UMZbNZA#R(0Bandwidth36 MHzg& NZNZA#RL0,Coverage & EIRP maxspot: 39.2 dBWn,bNZ7OZB#TX0Polarizationuplink: LHCPdownlink: RHCP$NZ[OZ" 17OZOZ1UOZZZR/[OZOZ# ^Gorizont's transponder frequency chart (GHz)OOZ̀Z#nxOZ̀Z[OZyj  @ ^  LHCPUplinkLHCPDownlinkTransponderRHCPDownlinkRHCPUplinkOZVZt#,nxyj(6.00063.675̀ZZt#,nxyj(6.05073.725VZjZt#,nxyj(6.10083.775ZZt#,nxyj(6.15093.825jZZt#.nxyj*6.200103.875Z Zt#.nxyj*6.250113.925ZZt#0nxyj"11.525K114325$ ZZ" 1ZZ1ZIZ^.ZIZ0 0^"Gorizont transponder/antenna connections< ZZ1pZхZ[ZGorizont 01LIZхZ8 @*봡" Gorizont 011 ZZ'  Generalg хZiZG#^@") Designation11158 / 78118A\ZņZA#R6Launch date19 Dec 1978jiZ/ZM#j:"N , Country of originCISo"ņZZM#jD"H̀‰MissionTelecommunicationst-/ZZG#^Z,4Geostationary orbitStatsionar-05, 53En!ZZM#jB" &㉓gLaunch vehicleProton #74&ZZ# 5ZۈZ'  End of lifeWZ2ZA#R,"Out of serviceyes&ۈZXZ# 82ZZ' "(Technical dataXZ[ZL h8zy,zyfZgSpecificationsAntenna specificationsTransponder/Antenna connectionsC-bandKu-bandTransponder frequency chart< ZZ1ZZlZGorizont 02L[ZZ8 @*봡" Gorizont 021 ZZ'  Generalg Z{ZG#^@") Designation11440 / 79062A[Z֋ZA#R4Launch date5 Jul 1979j{Z@ZM#j:"N , Country of originCISo"֋ZZM#jD"H̀‰MissionTelecommunicationst-@Z#ZG#^Z,4Geostationary orbitStatsionar-05, 53En!ZZM#jB" &㉓gLaunch vehicleProton #79&#ZZ# 5ZZ'  End of lifeWZCZA#R,"Out of serviceyes&ZiZ# 8CZZ' "(Technical dataiZlZL h8zy,zyfZgSpecificationsAntenna specificationsTransponder/Antenna connectionsC-bandKu-bandTransponder frequency chart< ZZ1pZ ZZGorizont 03LlZ Z8 @*봡" Gorizont 03Z ZlZ1 Z=Z'  Generalg ZZG#^@") Designation11648 / 79105A\=ZZA#R6Launch date28 Dec 1979jZjZM#j:"N , Country of originCISo"ZZM#jD"H̀‰MissionTelecommunicationst-jZMZG#^Z,4Geostationary orbitStatsionar-05, 53En!ZZM#jB" &㉓gLaunch vehicleProton #81&MZZ# 5ZZ'  End of lifeWZmZA#R,"Out of serviceyes&ZZ# 8mZZ' "(Technical dataZZL h8zy,zyfZgSpecificationsAntenna specificationsTransponder/Antenna connectionsC-bandKu-bandTransponder frequency chart< ZZ1UZZZGorizont 04LZZ8 @*봡" Gorizont 041 ZOZ'  Generalg ZZG#^@") Designation11841 / 80049A\OZZA#R6Launch date14 Jun 1980jZ|ZM#j:"N , Country of originCISo"ZZM#jD"H̀‰MissionTelecommunicationst-|Z_ZG#^Z,4Geostationary orbitStatsionar-04, 14Wn!ZZM#jB" &㉓gLaunch vehicleProton #83O+_ZZ$ VLaunched to broadcast the Olympic Games5ZQZ'  End of lifeWZZA#R,"Out of serviceyes&QZZ# 8ZZ' "(Technical dataZZL h8zy,zyfZgSpecificationsAntenna specificationsTransponder/Antenna connectionsC-bandKu-bandTransponder frequency chart< Z Z1 ZYZZGorizont 05LZYZ8 @*봡" Gorizont 051 ZZ'  Generalg YZZG#^@") Designation13092 / 82020A\ZMZA#R6Launch date15 Mar 1982jZZM#j:"N , Country of originCISo"MZ&ZM#jD"H̀‰MissionTelecommunicationsv/ZZG#^^,4Geostationary orbitStatsionar-14, 96.5En!&Z ZM#jB" &㉓gLaunch vehicleProton #95&Z0Z# 5 ZeZ'  End of lifeW0ZZA#R,"Out of serviceyes&eZZ# 8ZZ' "(Technical dataZZL h8zy,zyfZgSpecificationsAntenna specificationsTransponder/Antenna connectionsC-bandKu-bandTransponder frequency chart< Z!Z1Ud!ZmZ[Gorizont 06LZmZ8 @*봡" Gorizont 061 !ZZ'  Generalg mZ[G#^@") Designation13624 / 821Z[Z03A\Zm[A#R6Launch date20 Oct 1982j[[M#j:"N , Country of originCISo"m[F[M#jD"H̀‰MissionTelecommunicationsu.[[G#^\,4Geostationary orbitStatsionar-10, 170Wo"F[*[M#jD" &㉓gLaunch vehicleProton #101&[P[# 5*[['  End of lifeWP[[A#R,"Out of serviceyes&[[# 8[:[' "(Technical data[[L h8zy,zyfZgSpecificationsAntenna specificationsTransponder/Antenna connectionsC-bandKu-bandTransponder frequency chart< :[A[1A[[ [Gorizont 07L[[8 @*봡" Gorizont 071 A[['  Generalg [%[G#^@") Designation14160 / 83066A\[[A#R6Launch date30 Jun 1983j%[[M#j:"N , Country of originCISo"[Z[M#jD"H̀‰MissionTelecommunicationst-[[G#^Z,4Geostationary orbitStatsionar-11, 11Wo"Z[=[M#jD" &㉓gLaunch vehicleProton #110&[c[# 5=[['  End of lifeWc[[A#R,"Out of serviceyes&[[# 8[M[' "(Technical data[ [L h8zy,zyfZgSpecificationsAntenna specificationsTransponder/Antenna connectionsC-bandKu-bandTransponder frequency chart< M[T [1dT [ [+[Gorizont 08L [ [8 @*봡" Gorizont 081 T [ ['  Generalg [8 [G#^@") Designation14532 / 83118A\ [ [A#R6Launch date30 Nov 1983j8 [ [M#j:"N , Country of originCISo" [m [M#jD"H̀‰MissionTelecommunicationst- [ [G#^Z,4Geostationary orbitStatsionar-06, 90Eo"m [P [M#jD" &㉓gLaunch vehicleProton #114& [v [# 5P [ ['  End of lifeWv [ [A#R,"Out of serviceyes& [( [# 8 [` [' "(Technical data( [+[L h8zy,zyfZgSpecificationsAntenna specificationsTransponder/Antenna connectionsC-bandKu-bandTransponder frequency chart< ` [g[1+g[[JC[Gorizont 09L+[[8 @*봡" Gorizont 091 g[['  Generalg [K[G#^@") Designation14940 / 84041A\[[A#R6Launch date22 Apr 1984jK[@[M#j:"N , Country of[@[+[ originCISo"[@[M#jD"H̀‰MissionTelecommunicationst-@[A[G#^Z,4Geostationary orbitStatsionar-05, 53Eo"@[oA[M#jD" &㉓gLaunch vehicleProton #120&A[A[# 5oA[A['  End of lifeWA[!B[A#R,"Out of serviceyes&A[GB[# 8!B[B[' "(Technical dataGB[JC[L h8zy,zyfZgSpecificationsAntenna specificationsTransponder/Antenna connectionsC-bandKu-bandTransponder frequency chart< B[C[1̂C[C[\H[Gorizont 10LJC[C[8 @*봡" Gorizont 101 C[D['  Generalg C[jD[G#^@") Designation15144 / 84078A[D[D[A#R4Launch date1 Aug 1984jjD[/E[M#j:"N , Country of originCISo"D[E[M#jD"H̀‰MissionTelecommunicationst-/E[F[G#^Z,4Geostationary orbitStatsionar-13, 80Eo"E[F[M#jD" &㉓gLaunch vehicleProton #123&F[F[# 5F[F['  End of lifeWF[3G[A#R,"Out of serviceyes&F[YG[# 83G[G[' "(Technical dataYG[\H[L h8zy,zyfZgSpecificationsAntenna specificationsTransponder/Antenna connectionsC-bandKu-bandTransponder frequency chart< G[H[1+nH[H[oM[Gorizont 11L\H[H[8 @*봡" Gorizont 111 H[I['  Generalg H[|I[G#^@") Designation15484 / 85007A\I[I[A#R6Launch date18 Jan 1985j|I[BJ[M#j:"N , Country of originCISo"I[J[M#jD"H̀‰MissionTelecommunicationst-BJ[%K[G#^Z,4Geostationary orbitStatsionar-05, 53Eo"J[K[M#jD" &㉓gLaunch vehicleProton #129&%K[K[# 5K[K['  End of lifeWK[FL[A#R,"Out of serviceyes&K[lL[# 8FL[L[' "(Technical datalL[oM[L h8zy,zyfZgSpecificationsAntenna specificationsTransponder/Antenna connectionsC-bandKu-bandTransponder frequency chart< L[M[1̂M[M[[Gorizont 12LoM[M[8 @*봡" Gorizont 121 M[(N['  Generalg M[N[G#^@") Designation16769 / 86044A\(N[N[A#R6Launch date10 Jun 1986jN[UO[M#j:"N , Country of originCISo"N[O[M#jD"H̀‰MissionTelecommunicationst-UO[D[G#^Z,O[D[oM[4Geostationary orbitStatsionar-12, 40Eo"O[[M#jD" &㉓gLaunch vehicleProton #143&D[ـ[# 5[['  End of lifeWـ[e[A#R,"Out of serviceyes&[[# 8e[Á[' "(Technical data[[L h8zy,zyfZgSpecificationsAntenna specificationsTransponder/Antenna connectionsC-bandKu-bandTransponder frequency chart< Á[ʂ[1n~ʂ[[[Gorizont 13L[[8 @*봡" Gorizont 131 ʂ[G['  Generalg [[G#^@") Designation17083 / 86090A\G[ [A#R6Launch date18 Nov 1986j[t[M#j:"N , Country of originCISo" [[M#jD"H̀‰MissionTelecommunicationst-t[W[G#^Z,4Geostationary orbitStatsionar-06, 90Eo"[ƅ[M#jD" &㉓gLaunch vehicleProton #146&W[[# 5ƅ[!['  End of lifeW[x[A#R,"Out of serviceyes&![[# 8x[ֆ[' "(Technical data[[L h8zy,zyfZgSpecificationsAntenna specificationsTransponder/Antenna connectionsC-bandKu-bandTransponder frequency chart< ֆ[݇[1!݇[)[[Gorizont 14L[)[8 @*봡" Gorizont 141 ݇[Z['  Generalg )[[G#^@") Designation17969 / 87040A\Z[[A#R6Launch date11 May 1987j[[M#j:"N , Country of originCISo"[[M#jD"H̀‰MissionTelecommunicationsu.[k[G#^\,4Geostationary orbitStatsionar-07, 140Eo"[ڊ[M#jD" &㉓gLaunch vehicleProton #152&k[[# 5ڊ[5['  End of lifeW[[A#R,"Out of serviceyes&5[[# 8[[' "(Technical data[[L h8zy,zyfZgSpecificationsAntenna specificationsTransponder/Antenna connectionsC-bandKu-bandTransponder frequency chart< [[1~[=[[Gorizont 15L[=[8 @*봡" Gorizont 151 [n['  Generalg =[Ս[G#^@") Designation19017 / 88028A\n[1[A#R6Launch date30 Mar 1988jՍ[[M#j:"N , Country of originCISo"1[ [M#jD"H̀‰MissionTelecommunicationst-[~[G#^Z,4Geostationary orbitStatsionar-04, 14Wo" [ [M#jD" &㉓gLaunch vehicleProton #163~[ [[&~[2[# 5 [g['  End of lifeW2[[A#R,"Out of serviceyes&g[[# 8[[' "(Technical data[[L h8zy,zyfZgSpecificationsAntenna specificationsTransponder/Antenna connectionsC-bandKu-bandTransponder frequency chart< [#[1!\#[o[[Gorizont 16L[o[8 @*봡" Gorizont 161 #[['  Generalg o[[G#^@") Designation19397 / 88071A\[A#R6Launch date18 Aug 1988j[[M#j:"N , Country of originCISo"c[<[M#jD"H̀‰MissionTelecommunicationst-[[G#^Z,4Geostationary orbitStatsionar-13, 80Eo"<[[M#jD" &㉓gLaunch vehicleProton #170&[E[# 5[z['  End of lifeWE[[A#R,"Out of serviceyes&z[[# 8[/[' "(Technical data[[L h8zy,zyfZgSpecificationsAntenna specificationsTransponder/Antenna connectionsC-bandKu-bandTransponder frequency chart< /[6[16[[p[Gorizont 17L[[8 @*봡" Gorizont 171 6[['  Generalg [[G#^@") Designation19765 / 89004A\[A#R6Launch date26 Jan 1989j[[M#j:"N , Country of originCISo"v[O[M#jD"H̀‰MissionTelecommunicationsb![[A#RB,Geostationary orbitsee belowo"O[ [M#jD" &㉓gLaunch vehicleProton #175&[F[# : [[- */ۀ LocationF[ [m#:   " BeginEndPosition-[[p#Z$*,4L: 26 Jan 1989?Statsionar-05, 53E( [<[m#P,.Jun 1995Jan 199734E, inclined&[b[# 5<[['  End of life\b[[A#R6"Out of serviceJan 1997T[G[A#R&Causedeorbited&[m[# 8G[[' "(Technical datam[p[L h8zy,zyfZgSpecificationsAntenna specificationsTransponder/Antenna connectionsC-bandKu-bandTransponder frequency chart< [[1\[[\Gorizont 18Lp[[8 @*봡" Gorizont 181 [)['  Generalg [[G#^@") Designation20107 / 89052A[)[ \A#R4Launch date5 Jul 1989[ \p[j[v\M#j:"N , Country of originCISo" \\M#jD"H̀‰MissionTelecommunications:v\l\M#jt"/ۀ04Geostationary orbitStatsionar-07, 140E, inclinedo"\\M#jD" &㉓gLaunch vehicleProton #179&l\\# 5\6\'  End of life]\\A#R8"Out of serviceSep 1996?&6\\# 8\\' "(Technical data\\L h8zy,zyfZgSpecificationsAntenna specificationsTransponder/Antenna connectionsC-bandKu-bandTransponder frequency chart=\\' , EIRP coverage (dBW)\\F Z r̀p͉t͉o͉u͉C-band, global (A6)C-band, large hemispheric (A4)C-band, narrow hemispheric (A8)C-band, spot (A3)Ku-band, spot (A9)1\\1\\^\\7 >#o"Gorizont 18's C-band EIRP: global A6To get the EIRP of the A1 Global beam add 7.1 dBW1\\1\'\m7\'\6 \M#jD"H̀‰MissionTelecommunications; \ \M#jv"/ۀ04Geostationary orbitStatsionar-14, 96.5E, inclinedo"> \5 \M#jD" &㉓gLaunch vehicleProton #180& \[ \# 2 5 \ \'  Location[ \ \m#:q   " BeginEndPosition@ \ \p#q$8:4L: 28 Sep 1989Oct 1996Statsionar-14, 96.5E, inclined \P \j#>qDec 199634E, inclined& \v \# 8P \ \' "(Technical datav \y\L h8zy,zyfZgSpecificationsAntenna specificationsTransponder/Antenna connectionsC-bandKu-bandTransponder frequency chart1 \\1\?\^y\?\7 >#o"Gorizont 19's C-band EIRP: global A6To get the EIRP of the A1 Global beam add 7.1 dBW1\p\1p\ @\m7?\ @\6 }⁗C-band, global (A6)C-band, large hemispheric (A4)C-band, narrow hemispheric (A8)1H\]I\1]I\I\^,I\I\7 >#o"Gorizont 20's C-band EIRP: global A6To get the EIRP of the A1 Global beam add 7.1 dBW1]I\#J\1#J\J\m7I\J\6 kK\K\Ă\Gorizont 21L/K\K\8 @*봡" Gorizont 212kK\K\# Gorizont #321 K\L\'  Generalg K\L\G#^@") Designation20923 / 90094A[L\L\A#R4Launch date3 Nov 1990jL\FM\M#j:"N , Country of originCISo"L\M\M#jD"H̀‰MissionTelecommunicationsb!FM\N\A#RB,Geostationary orbitsee belowo"M\N\M#jD" &㉓gLaunch vehicleProton #191&N\N\# : N\N\- */ۀ LocationN\pO\m#:T   " BeginEndPosition+N\\p#VT"&(4L: 3 Nov 1990Statsionar-pO\\/K\06, 90E)pO\\p#RT 4Statsionar-16, 145E, inclined&\ր\# 8\\' "(Technical dataր\ف\L h8zy,zyfZgSpecificationsAntenna specificationsTransponder/Antenna connectionsC-bandKu-bandTransponder frequency chart=\\' , EIRP coverage (dBW)pف\Ă\> L****C-band, global (A6)C-band, large hemispheric (A4)C-band, narrow hemispheric (A8)Ku-band, spot (A9)1\\1\\^Ă\\7 >#o"Gorizont 21's C-band EIRP: global A6To get the EIRP of the A1 Global beam add 7.1 dBW1\\1\(\m7\(\6 \I\p#|$8:4L: 23 Nov 1990Jan 1996Statsionar-12, 40E, inclined7\\p#n$(*4mid April 1996Statsionar-07, 140E, inclined&I\\# 8\N\' "(Technical data\\L h8zy,zyfZgSpecificationsAntenna specificationsTransponder/Antenna connectionsC-bandKu-bandTransponder frequency chart=N\V\' , EIRP coverage (dBW)\ \F Z w$u$y$t$z$C-band, global (A6)C-band, large hemispheric (A4)C-band, narrow hemispheric (A8)C-band, spot (A3)Ku-band, spot (A9)1V\Q\1Q\\^ \\7 >#o"Gorizont 22's C-band EIRP: global A6To get the EIRP of the A1 Global beam add 7.1 dBW1Q\\1\\m7\\6 \\\Gorizont 23Lm\\8 @*봡" Gorizont 232\'\# Gorizont #341 \X\'  Generalg '\\G#^@") Designation21533 / 91046A[X\\A#R4Launch date2 Jul 1991j\\M#j:"N , Country of originCISo"\\M#jD"H̀‰MissionTelecommunicationsu.\h\G#^\,?4Geostationary orbitStatsionar-21, 103Eo"\\M#jD" &㉓gLaunch vehicleProton #200O+h\&\$ VThe transponder thermoregulation failed5\[\'  End of lifeW&\\A#R,"Out of serviceyes8[\\' "(Technical data\\L h8zy,zyfZgSpecificationsAntenna specificationsTransponder/Antenna connectionsC-bandKu-bandTransponder frequency chart< \\1e,\=\q\Gorizont 24L\=\8 @*봡" Gorizont 242\o\# Gorizont #351 =\\'  Generalg o\\G#^@") Designation21759 / 91074A\\c\A#R6Launch date23 Oct 1991j\\M#j:"N , Country of originCISo"c\<\M#jD"H̀‰MissionTelecommunications~7\\G#^n,4Geostationary orbitStatsionar-13, 80E, inclinedo"<\)\M#jD" &㉓gLaunch vehicleProton #202&\O\# 5)\\'  End of lifea O\\A#R@"Out of servicelate Mar 1998\\A\A#R6Causefailure/deorbited&\g\# 8A\\' "(Technical datag\j\L h8zy,zyfZgSpecificationsAntenna specificationsTransponder/Antenna connectionsC-bandKu-bandTransponder frequency chart=\\' , EIRP coverage (dBW)j\q\F Z 9AG7AG;AG6AG#o"Gorizont 24's C-band EIRP: global A6To get the EIRP of the A1 Global beam add 7.1 dBW1\h\1h\\m77\\6 \+]3]Gorizont 25L\+]8 @*봡"\+]\ Gorizont 252\]]# Gorizont #361 +]]'  Generalg ]]]G#^@") Designation21922 / 92017A[]P]A#R4Launch date2 Apr 1992j]]M#j:"N , Country of originCISo"P])]M#jD"H̀‰MissionTelecommunications:]]M#jt"/ۀ0?4Geostationary orbitStatsionar-21, 103E, inclinedo")]]M#jD" &㉓gLaunch vehicleProton #206&]E]# 8]}]' "(Technical dataE]H]L h8zy,zyfZgSpecificationsAntenna specificationsTransponder/Antenna connectionsC-bandKu-bandTransponder frequency chart=}]]' , EIRP coverage (dBW)pH]3]> L󦉂󦉂󦉂C-band, global (A6)C-band, large hemispheric (A4)C-band, narrow hemispheric (A8)Ku-band, spot (A9)1]d]1d]]^3]]7 >#o"Gorizont 25's C-band EIRP: global A6To get the EIRP of the A1 Global beam add 7.1 dBW1d]*]1*]]m7]]6 L]]]]C-band, global (A6)C-band, large hemispheric (A4)C-band, narrow hemispheric (A8)Ku-band, spot (A9)1 ] ]1 ]]^X ]]7 >#o"Gorizont 26's C-band EIRP: global A6To get the EIRP of the A1 Global beam add 7.1 dBW1 ]O]1 O]]m7]]6 C]D]p#|$8:4L: 27 Nov 1992Jul 1996Statsionar-05, 53E, inclined2ND]E]p#d4Aug 1996Statsionar-14, 96.5E, inclined&D]E]# 8E]E]' "(Technical dataE]F]L h8zy,zyfZgSpecificationsAntenna specificationsTransponder/Antenna connectionsC-bandKu-bandTransponder frequency chart=E]G]' , EIRP coverage (dBW)pF]G]> L\eZe^e_eC-band, global (A6)C-band, large hemispheric (A4)C-band, narrow hemispheric (A8)Ku-band, spot (A9)1G]G]1 G]xH]^G]xH]7 >#o"Gorizont 27's C-band EIRP: global A6To get the EIRP of the A1 Global beam add 7.1 dBW1G]H]1H]I]m7xH]I]6 #o"Gorizont 28's C-band EIRP: global A6To get the EIRP of the A1 Global beam add 7.1 dBW1m]3]13]]m7]]6 |]w]3 4}o7U=Was leased to the US-Malaysian Rimsat company to offer telecommunications services over Asia and the Pacific region. Rimsat was to use the satellite 3 years for a cost of $12 million. In September 1995 the satellite was taken over by Intersputnik after a complex disputeIn 1997, it was sold to the PASI group8]]' "(Technical dataw]z]L h8zy,zyfZgSpecificationsAntenna specificationsTransponder/Antenna connectionsC-bandKu-bandTransponder frequency chart=]]' , EIRP coverage (dBW)z]]A P7 # # #! #C-band, global (A6)C-band, large hemispheric (A4)C-band, narrow hemispheric (A8)Ku-band, spot (A9)The satellite provides slightly better performance than the standard Gorizont: at least 1 dBW more in C-band and 3 dBW in Ku-band (see footprint maps for details). This improvment could be due to a little more power available, perhaps because of the lack of auxilliary (X- or L-band) transponders.1]ď]1(ď]]]]9 @#o"Gď]]]orizont 29's C-band EIRP: global A6At BOL the satellite had 1 dBW additional powerTo get the EIRP of the A1 Global beam add 8.1 dBW1ď]]1]f]g]f]7 >#o"Gorizont 29's C-band EIRP: large hemispheric A4At BOL the satellite had 2 dBW additional power1]]1]6]hf]6]7 >#o"Gorizont 29's C-band EIRP: narrow hemispheric A8At BOL the satellite had 1 dBW additional power1]g]1g]][6]]7 >#o"Gorizont 29's Ku-band EIRP: spot A9At BOL the satellite had 3 dBW additional power< g]5]1O T\5]]]Gorizont 30L]]8 @*봡" Gorizont 30sP5]]# Gorizont #42, also called Rimsat 2 or Rimsat G2 or Statsionar R2 or Asiasat G1 ]%]'  Generalg ]]G#^@") Designation23108 / 94030Ah'%]]A#RNLaunch date20 May 1994 at 02:01 UTj]^]M#j:"N , Country of originCISo"]]M#jD"H̀‰MissionTelecommunicationsb!^]/]A#RB,Geostationary orbitsee belowo"]]M#jD" &㉓gLaunch vehicleProton #223/]T]+ $o7U=Was leased to the US-Malaysian Rimsat company. In September 1995 the satellite was taken over by Intersputnik after a complex dispute: ]]- */ۀ LocationT]]m#:   " BeginEndPosition6]]j#l$8:L: 20 May 1994Dec 1997142.5E (Statsionar-R2) ]B]j#@Jan 1998122E, inclined&]h]# 8B]]' "(Technical datah]k]L h8zy,zyfZgSpecificationsAntenna specificationsTransponder/Antenna connectionsC-bandKu-bandTransponder frequency chart=]]' , EIRP coverage (dBW)k]]H ^_ʁ.xǁ.xȁ.x́.x́.xC-band, global (A6)C-band, spot (A3)C-band, large hemispheric (A4)C-band, narrow hemispheric (A8)Ku-band, spot (A9)The satellite provides slightly better performance than the standard Gorizont: at least 1 dBW more in C-band and 3 dBW in Ku-band (see footprint maps for details). This improvment could be due to a little more power available, perhaps because of the lack of auxilliary (X- or L-band) transponders.1]]1]]]]9 @#o"Gorizont 30's C-band EIRP: global A6At BOL the satellite had 1 dBW additional powerTo get the EIRP of the A1 Global beam add 8.1 dBW1]]1]Y]Z]Y]7 >#o"Gorizont 30's C-band EIRP: spot A3At BOL the satellite had 2 dBW additional power1]]1 ](]gY](]7 >#o"Gorizont 30's C-band EIRP: large hemispheric A4At BOL the satellite had 2 dBW additional power1]Y]1!Y] ^h(] ^7 >#o"Gorizont 30's C-band EIRP: narrow hemispheric A8At BOL the satellite had 1 dBW additional powerY] ^(]1Y]=^1"=^^[ ^^7 >#o"Gorizont 30's Ku-band EIRP: spot A9At BOL the satellite had 3 dBW additional power< =^ ^1;-v# ^W^a^Gorizont 31L^W^8 @*봡" Gorizont 312 ^^# Gorizont #431 W^^'  Generalg ^!^G#^@") Designation23775 / 96005Ah'^^A#RNLaunch date25 Jan 1996 at 10:00 UTj!^^M#j:"N , Country of originCISo"^b^M#jD"H̀‰MissionTelecommunications|/^^M#j^"/ۀ04Geostationary orbitStatsionar-12, 40Eo"b^M^M#jD" &㉓gLaunch vehicleProton #239&^s^# 8M^^' "(Technical datas^v^L h8zy,zyfZgSpecificationsAntenna specificationsTransponder/Antenna connectionsC-bandKu-bandTransponder frequency chart=^^' , EIRP coverage (dBW)pv^a^> La _ c d C-band, global (A6)C-band, large hemispheric (A4)C-band, narrow hemispheric (A8)Ku-band, spot (A9)1^^1$^'^^a^'^7 >#o"Gorizont 31's C-band EIRP: global A6To get the EIRP of the A1 Global beam add 7.1 dBW1^X^1%X^^m7'^^6 #o"Gorizont 32's C-band EIRP: global A6To get the EIRP of the A1 Global beam add 7.1 dBW1^^1*^,@^m7^,@^6 I^#v  & : N b PlaneSlot 1Slot 2Slot 3Slot 4Slot 5]H^I^#ڀ< ,8A2-212-122-152-04>I^J^#ڀ>".:B2-182-07?2-022-22"I^,K^#ڀD ,8C2-242-252-192-202-13J^K^#ڀ< ,8D2-112-092-052-23",K^vL^#ڀD ,8E2-012-082-262-102-03K^M^#ڀ< ,8F2-162-142-062-17&vL^?M^# 1 M^pM^'  ContactF?M^M^* $8nրAir Force Space Command<pM^M^' *O External resourcesM^N^= H[http://www.spacecom.af.mil/usspace/gps.htmhttp://www.fas.org/spp/military/program/nav/gps.htmhttp://www.gpsy.com/gpsinfo/http://www.navcen.uscg.mil/gps/geninfo/1M^ O^1U/ O^^4^:N^GO^) ""SProgram: GPS5 O^ ^{#ƀj"cZcZ6cZPcZGPS BI-01GPS BI-02GPS BI-03GPS BI-04GO^ ^N^7GO^Ā^#Ҁn(cZ"cZ:cZTcZGPS BI-05GPS BI-06GPS BI-07GPS BI-08* ^c^u#T"cZacZ6XcZPGPS BI-09GPS BI-10GPS BI-119Ā^^{#ƀr"..:.V.GPS BII-01GPS BII-02GPS BII-03GPS BII-04@c^^#(.( .(@.(`.GPS BII-05GPS BII-06GPS BII-07GPS BII-08^i^l#,(. $(GPS BII-09D^=^#(5F݀("5F݀(D5F݀(f5F݀GPS BIIA-10GPS BIIA-11GPS BIIA-12GPS BIIA-13Di^^#(5F݀("5F݀(D5F݀(f5F݀GPS BIIA-14GPS BIIA-15GPS BIIA-16GPS BIIA-17D=^^#(5F݀("5F݀(D 6F݀(f6F݀GPS BIIA-18GPS BIIA-19GPS BIIA-20GPS BIIA-21D^^#(6F݀("6F݀(D6F݀(f6F݀GPS BIIA-22GPS BIIA-23GPS BIIA-24GPS BIIA-255^r^#؀j(6F݀("6F݀(D6F݀fGPS BIIA-26GPS BIIA-27GPS BIIA-28&^^x#L(2Z݀("3Z݀DHGPS BIIR-01GPS BIIR-02$r^4^" 1^e^10e^^4^^1 2 c%GPS frequenciesMilitary: 1227.6 MHzCivilian: 1575.42 MHzNuclear burst detection: 1381.05 MHzTelemetry on 2227.5 MHz?: e^O^1R1O^^f^GPS BI-01J^^8 @& c%" GPS BI-01Q.O^^# \Also called OPS 5111 or Navstar 1 or GPS 011 ^^'  Generalg ^^G#^@") Designation10684 / 78020A\^ފ^A#R6Launch date22 Feb 1978t'^R^M#jN"N ,㹌לCountry of originUnited Statesgފ^^M#j4"H̀シMissionNavigationb!R^^A#RB"Perigee/Apogee20230/20578 kmV^q^A#R*Inclination64.6S^Č^A#R$Period727 minkq^/^M#j<" &26Launch vehicleAtlas F[Č^^A#R4Launch siteVandenberg&/^^# 5^^'  End of life]^B^A#R8"Out of serviceJuly 1985$^f^" : B^^12^^^GPS BI-02Jf^^8 @& c%" GPS BI-02Q.^;^# \Also called OPS 5112 or Navstar 2 or GPS 021 ^l^'  Generalg ;^ӏ^G#^@") Designation10893 / 78047A\l^;^A#R6ӏ^;^f^Launch date13 May 1978t'ӏ^^M#jN"N ,㹌לCountry of originUnited Statesg;^^M#j4"H̀シMissionNavigationb!^x^A#RB"Perigee/Apogee19522/20653 kmV^^A#R*Inclination63.6Ux^#^A#R(Period714.2 mink^^M#j<" &26Launch vehicleAtlas F[#^^A#R4Launch siteVandenberg&^^# 5^D^'  End of life]^^A#R8"Out of serviceJuly 1981$D^^" : ^^1R43^I^^GPS BI-03J^I^8 @& c%" GPS BI-03Q.^^# \Also called OPS 5113 or Navstar 3 or GPS 031 I^^'  Generalg ^2^G#^@") Designation11054 / 78093A[^^A#R4Launch date7 Oct 1978t'2^^M#jN"N ,㹌לCountry of originUnited Statesg^h^M#j4"H̀シMissionNavigationb!^^A#RB"Perigee/Apogee20705/20942 kmVh^ ^A#R*Inclination63.3U^u^A#R(Period744.2 mink ^^M#j<" &26Launch vehicleAtlas F[u^;^A#R4Launch siteVandenberg^/^% Was equipped with corner-cube reflectors for satellite laser ranging (SLR). SLR tracking of the satellites permit onboard clock errors and satellite ephemeris errors in GPS tracking to be differentiated.5;^d^'  End of life\/^^A#R6"Out of serviceMay 1992$d^^" : ^^14^h^6^GPS BI-04J^h^8 @& c%" GPS BI-04Q.^^# \Also called OPS 5114 or Navstar 4 or GPS 041 h^^'  Generalg ^Q^G#^@") Designation11141 / 78112A\^^A#R6Launch date11 Dec 1978t'Q^!^M#jN"N ,㹌לCountry of originUnited Statesg^^M#j4"H̀シMissionNavigationb!!^^A#RB"Perigee/Apogee20748/21013 kmV^@^A#R*Inclination64.6U^^A#R(Period746.5 mink@^^M#j<" &26Launch vehicleAtlas F[^[^A#R4Launch siteVandenberg&^^# 5[^^'  End of life\^^A#R6"Out of serviceOct 1989$^6^" : ^p^145p^^]_GPS BI-05J6^^8 @& c%" GPS BI-05Q.p^_# \Also called OPS 5117 or Navstar 5 ^_6^or GPS 051 ^H_'  Generalg __G#^@") Designation11690 / 80011A[H_ _A#R4Launch date9 Feb 1980t'_~_M#jN"N ,㹌לCountry of originUnited Statesg __M#j4"H̀シMissionNavigationb!~_G_A#RB"Perigee/Apogee19807/20557 kmT__A#R&Inclination65SG__A#R$Period718 mink_Y_M#j<" &26Launch vehicleAtlas F[__A#R4Launch siteVandenbergY__% Was equipped with corner-cube reflectors for satellite laser ranging (SLR). SLR tracking of the satellites permit onboard clock errors and satellite ephemeris errors in GPS tracking to be differentiated.5__'  End of life\_9_A#R6"Out of serviceNov 1983$_]_" : 9__1t6__ _GPS BI-06J]__8 @& c%" GPS BI-06Q._2_# \Also called OPS 5118 or Navstar 6 or GPS 061 _c_'  Generalg 2__G#^@") Designation11783 / 80032A\c_&_A#R6Launch date26 Apr 1980t'__M#jN"N ,㹌לCountry of originUnited Statesg&__M#j4"H̀シMissionNavigationb!_c_A#RB"Perigee/Apogee19378/20480 kmV__A#R*Inclination62.7Uc_ _A#R(Period707.8 mink_y _M#j<" &26Launch vehicleAtlas F[ _ _A#R4Launch siteVandenberg&y _ _# 5 _/ _'  End of life\ _ _A#R6"Out of serviceMar 1991$/ _ _" : _ _17 _3 _ _GPS BI-07J _3 _8 @& c%" GPS BI-07E" _x _# DAlso called Navstar 7 or GPS 0753 _ _'  End of life_x _ _A#R<"Out of service18 Dec 1981k$ _w _G#^H26CauseLaunch failure (Atlas F)$ _ _" : w _ _1tڀ8 _ _B_GPS BI-08J _ _8 @& c%" GPS BI-08Q. _p _# \Also called OPS 9794 or Navstar 8 or GPS 081  _ _'  Generalg p __G#^@") Designation14189 / 83072A\ _d_A#R6Launch date14 Jul 1983t'__M#jN"N ,㹌לCountry of originUnited Statesgd_?_M#j4"H̀シMissionNavigationb!__A#RB"Perigee/Apogee20801/21183 kmV?_ @_A#R*Inclination64.3_ @_ _U_a@_A#R(Period751.1 mink @_@_M#j<" &26Launch vehicleAtlas F[a@_'A_A#R4Launch siteVandenberg&@_MA_# 5'A_A_'  End of life\MA_A_A#R6"Out of serviceMay 1993b!A_@B_A#RBCauseReplaced by GPS BIIA-20&A_fB_# 8@B_B_' "(OTechnical dataP-fB_B_# ZUsed to transmit on 1575.42 and 1227.6 MHz: B_(C_19(C_rC_H_GPS BI-09JB_rC_8 @& c%" GPS BI-09P-(C_C_# ZAlso called USA 001 or Navstar 9 or GPS 091 rC_C_'  Generalg C_ZD_G#^@") Designation15039 / 84059A\C_D_A#R6Launch date13 Jun 1984t'ZD_*E_M#jN"N ,㹌לCountry of originUnited StatesgD_E_M#j4"H̀シMissionNavigationb!*E_E_A#RB"Perigee/Apogee20032/20332 kmVE_IF_A#R*Inclination63.9SE_F_A#R$Period718 minkIF_G_M#j<" &26Launch vehicleAtlas F[F_bG_A#R4Launch siteVandenberg&G_G_# 5bG_G_'  End of life\G_H_A#R6"Out of serviceJun 1994&G_?H_# 8H_wH_' "(OTechnical dataI&?H_H_# LTransmits on 1575.42 and 1227.6 MHz: wH_H_1ڀG:H_DI_N_GPS BI-10JH_DI_8 @& c%" GPS BI-10Q.H_I_# \Also called USA 005 or Navstar 10 or GPS 101 DI_I_'  Generalg I_-J_G#^@") Designation15271 / 84097A[I_J_A#R4Launch date8 Sep 1984t'-J_J_M#jN"N ,㹌לCountry of originUnited StatesgJ_cK_M#j4"H̀シMissionNavigationb!J_K_A#RB"Perigee/Apogee19952/20411 kmVcK_L_A#R*Inclination62.2SK_nL_A#R$Period718 minm L_L_M#j@" &26Launch vehicleAtlas E14[nL_6M_A#R4Launch siteVandenberg&L_\M_# 56M_M_'  End of lifen-\M_M_A#RZ"Out of service26 Mar 1996 (orbit raised)&M_%N_# 8M_]N_' "(OTechnical dataJ'%N_N_# NTransmited on 1575.42 and 1227.6 MHz: ]N_N_1E;N_+O__GPS BI-11JN_+O_8 @& c%" GPS BI-11Q.N_|O_# \Also called USA 010 or Navstar 11 or GPS 111 +O_O_'  Generalg |O_ _G#^@") DesignatioO_ _N_n16129 / 85093A[O_{_A#R4Launch date9 Oct 1985t' __M#jN"N ,㹌לCountry of originUnited Statesg{_V_M#j4"H̀シMissionNavigationb!__A#RB"Perigee/Apogee20449/21211 kmVV__A#R*Inclination64.1U_c_A#R(Period744.4 minm _Ђ_M#j@" &26Launch vehicleAtlas E55[c_+_A#R4Launch siteVandenberg&Ђ_Q_# 5+__'  End of life\Q__A#R6"Out of serviceApr 1994&__# 8_@_' "(OTechnical dataI&__# LTransmits on 1575.42 and 1227.6 MHz; @_Ą_1fG<Ą__D_GPS BII-01K__8 @( c%" GPS BII-01R/Ą_a_# ^Also called USA 035 or Navstar 2-1 or GPS 141 __'  Generalg a__G#^@") Designation19802 / 89013A\_U_A#R6Launch date14 Feb 1989t'_Ɇ_M#jN"N ,㹌לCountry of originUnited StatesgU_0_M#j4"H̀シMissionNavigationb!Ɇ__A#RB"Perigee/Apogee20088/20274 kmV0__A#R*Inclination55.0U_=_A#R(Period717.9 minp#__M#jF" &p㉂Launch vehicleDelta 2 #183&=_ӈ_# 8_ _' "(Technical data9ӈ_D_) " Fr ̀Frequencies; __1dE=_ʉ__GPS BII-02KD_ʉ_8 @( c%" GPS BII-02R/__# ^Also called USA 038 or Navstar 2-2 or GPS 131 ʉ_M_'  Generalg __G#^@") Designation20061 / 89044A\M__A#R6Launch date10 Jun 1989t'__M#jN"N ,㹌לCountry of originUnited Statesg__M#j4"H̀シMissionNavigationb!_M_A#RB"Perigee/Apogee19847/20517 kmV__A#R*Inclination54.5SM__A#R$Period718 minp#_f_M#jF" &p㉂Launch vehicleDelta 2 #185&__# 8f_č_' "(Technical data9__) " Fr ̀Frequencies; č_8_1j>8___GPS BII-03K__8 @( c%" GPS BII-03R/8_Վ_# ^Also called USA 042 or Navstar 2-3 or GPS 161 __'  Generalg Վ_m_G#^@") Designation20185 / 89064A\_ɏ_A#R6Launch date18 Aug 1989t'm_I_M#jN"N ɏ_I__,㹌לCountry of originUnited Statesgɏ__M#j4"H̀シMissionNavigationb!I__A#RB"Perigee/Apogee20154/20207 kmV_h_A#R*Inclination55.0U__A#R(Period717.9 minp#h_-_M#jF" &p㉂Launch vehicleDelta 2 #186&_S_# 8-__' "(Technical data9S__) " Fr ̀Frequencies; __1d?_J_}_GPS BII-04K_J_8 @( c%" GPS BII-04R/__# ^Also called USA 047 or Navstar 2-4 or GPS 191 J__'  Generalg _4_G#^@") Designation20302 / 89085A\__A#R6Launch date21 Oct 1989t'4__M#jN"N ,㹌לCountry of originUnited Statesg_k_M#j4"H̀シMissionNavigationb!__A#RB"Perigee/Apogee20176/20188 kmVk_#_A#R*Inclination53.4S_v_A#R$Period718 minp##__M#jF" &p㉂Launch vehicleDelta 2 #188&v_ _# 8_D_' "(Technical data9 _}_) " Fr ̀Frequencies; D__1d[@__6_GPS BII-05K}__8 @( c%" GPS BII-05R/_U_# ^Also called USA 049 or Navstar 2-5 or GPS 171 __'  Generalg U__G#^@") Designation20361 / 89097A\_I_A#R6Launch date11 Dec 1989t'__M#jN"N ,㹌לCountry of originUnited StatesgI_$_M#j4"H̀シMissionNavigationb!__A#RB"Perigee/Apogee19995/20369 kmV$__A#R*Inclination55.7S_/_A#R$Period718 minp#__M#jF" &p㉂Launch vehicleDelta 2 #190&/__# 8__' "(Technical data9_6_) " Fr ̀Frequencies; _q_1GAq__`GPS BII-06K6__8 @( c%" GPS BII-06R/q__# ^Also called USA 050 or Navstar 2-6 or GPS 181 _?_'  Generalg __G#^@") Designation20452 / 90008A\?__A#R6Launch date24 Jan 1990t'_v_M#jN"N ,㹌לCountry of originUnited Statesg__M#j4"H̀シMissionNavigationb!v_?_A#RB"Perigee/Apogee20038/20324 kmT__A#R&Inclination54U?_ `A#R(Period717.9 min_ `6_p#_|`M#jF" &p㉂Launch vehicleDelta 2 #191& ``# 8|``' "(Technical data9``) " Fr ̀Frequencies; `N`1j[BN```GPS BII-07K``8 @( c%" GPS BII-07R/N``# ^Also called USA 054 or Navstar 2-7 or GPS 201 ``'  Generalg ``G#^@") Designation20533 / 90025A\``A#R6Launch date26 Mar 1990t'`S`M#jN"N ,㹌לCountry of originUnited Statesg``M#j4"H̀シMissionNavigationb!S``A#RB"Perigee/Apogee20071/20292 kmV`r`A#R*Inclination54.9S``A#R$Period718 minp#r`5`M#jF" &p㉂Launch vehicleDelta 2 #193&`[`# 55``'  End of life`[``A#R>"Out of service21 May 1996?K `;`A#RCause&`a`# 8;``' "(Technical data9a``) " Fr ̀Frequencies; ` `1cG0C `X` `GPS BII-08K`X`8 @( c%" GPS BII-08R/ ``# ^Also called USA 063 or Navstar 2-8 or GPS 211 X``'  Generalg `B`G#^@") Designation20724 / 90068A[``A#R4Launch date2 Aug 1990t'B` `M#jN"N ,㹌לCountry of originUnited Statesg`x `M#j4"H̀シMissionNavigationb! ` `A#RB"Perigee/Apogee19891/20473 kmVx `0 `A#R*Inclination54.7S ` `A#R$Period718 minp#0 ` `M#jF" &p㉂Launch vehicleDelta 2 #197& ` `# 8 `Q `' "(Technical data9 ` `) " Fr ̀Frequencies; Q ` `1cD ` `N@`GPS BII-09K ` `8 @( c%" GPS BII-09R/ `b `# ^Also called USA 064 or Navstar 2-9 or GPS 151  ` `'  Generalg b ` `G#^@") Designation20830 / 90088A[ `U `A#R4Launch date1 Oct 1990t' ` `M#jN"N ,㹌לCountry of originUnited StatesgU `0`M#j4"H̀シMissionNavigationb! ``A#RB"Perigee/Apogee20002/20363 kmV0``A#R*Inclination55.6S`;`A#R$Period718 minp#``M#jF" &p㉂Launch vehicleDelta 2 #199&;``# 8`@`' "(Technic`@` `al data9`N@`) " Fr ̀Frequencies< @`@`1f0kE@`@` E`GPS BIIA-10LN@`@`8 @* c%" GPS BIIA-10T1@`*A`# bAlso called USA 066 or Navstar 2A-10 or GPS 231 @`[A`'  Generalg *A`A`G#^@") Designation20959 / 90103A\`B`A#R6Launch date26 Nov 1990t'A`B`M#jN"N ,㹌לCountry of originUnited StatesgB`B`M#j4"H̀シMissionNavigationb!B`[C`A#RB"Perigee/Apogee19968/20394 kmVB`C`A#R*Inclination55.1S[C`D`A#R$Period718 minp#C`tD`M#jF" &p㉂Launch vehicleDelta 2 #201&D`D`# 8tD`D`' "(Technical data9D` E`) " Fr ̀Frequencies< D`GE`1cÂFGE`E`I`GPS BIIA-11L E`E`8 @* c%" GPS BIIA-11T1GE`E`# bAlso called USA 071 or Navstar 2A-11 or GPS 241 E`F`'  Generalg E`F`G#^@") Designation21552 / 91047A[F`F`A#R4Launch date4 Jul 1991t'F`NG`M#jN"N ,㹌לCountry of originUnited StatesgF`G`M#j4"H̀シMissionNavigationb!NG`H`A#RB"Perigee/Apogee20031/20331 kmTG`kH`A#R&Inclination56SH`H`A#R$Period718 minp#kH`.I`M#jF" &p㉂Launch vehicleDelta 2 #206&H`TI`# 8.I`I`' "(Technical data9TI`I`) " Fr ̀Frequencies< I`J`1fkGJ`MJ`N`GPS BIIA-12LI`MJ`8 @* c%" GPS BIIA-12T1J`J`# bAlso called USA 079 or Navstar 2A-12 or GPS 251 MJ`J`'  Generalg J`9K`G#^@") Designation21890 / 92009A\J`K`A#R6Launch date23 Feb 1992t'9K` L`M#jN"N ,㹌לCountry of originUnited StatesgK`pL`M#j4"H̀シMissionNavigationb! L`L`A#RB"Perigee/Apogee20031/20335 kmVpL`(M`A#R*Inclination54.2SL`{M`A#R$Period718 minp#(M`M`M#jF" &p㉂Launch vehicleDelta 2 #207&{M`N`# 8M`IN`' "(Technical data9N`N`) " Fr ̀Frequencies< IN`N`1pÂHN` O`U`GPS BIIA-13LN` O`8 @* c%" GPS BIIA-13T1N`^O`# bAlso called USA 080 or Navstar 2A-13 or GPS 281 O`O`'  Generalg ^O` `G#^@") Designation21930 / 92019AO` `N`\O`h`A#R6Launch date10 Apr 1992t' `܀`M#jN"N ,㹌לCountry of originUnited Statesgh`C`M#j4"H̀シMissionNavigationb!܀``A#RB"Perigee/Apogee20026/20338 kmVC``A#R*Inclination55.7S`N`A#R$Period718 minp#``M#jF" &p㉂Launch vehicleDelta 2 #208&N``# 8``' "(Technical data9`U`) " Fr ̀Frequencies< ``1eEI`݃``GPS BIIA-14LU`݃`8 @* c%" GPS BIIA-14T1`1`# bAlso called USA 083 or Navstar 2A-14 or GPS 261 ݃`b`'  Generalg 1`Ʉ`G#^@") Designation22014 / 92039A[b`$`A#R4Launch date7 Jul 1992t'Ʉ``M#jN"N ,㹌לCountry of originUnited Statesg$``M#j4"H̀シMissionNavigationb!`a`A#RB"Perigee/Apogee19961/20402 kmV``A#R*Inclination54.9Sa` `A#R$Period718 minp#`z`M#jF" &p㉂Launch vehicleDelta 2 #211& ``# 8z`؇`' "(Technical data9``) " Fr ̀Frequencies< ؇`M`1eJM``͌`GPS BIIA-15L``8 @* c%" GPS BIIA-15T1M``# bAlso called USA 084 or Navstar 2A-15 or GPS 271 ``'  Generalg ``G#^@") Designation22108 / 92058A[``A#R4Launch date9 Sep 1992t'`T`M#jN"N ,㹌לCountry of originUnited Statesg``M#j4"H̀シMissionNavigationb!T``A#RB"Perigee/Apogee19909/20453 kmV`s`A#R*Inclination54.2S`Ƌ`A#R$Period718 minp#s`6`M#jF" &p㉂Launch vehicleDelta 2 #214&Ƌ`\`# 86``' "(Technical data9\`͌`) " Fr ̀Frequencies< ` `1vEpK `U``GPS BIIA-16L͌`U`8 @* c%" GPS BIIA-16T1 ``# bAlso called USA 085 or Navstar 2A-16 or GPS 321 U`ڍ`'  Generalg `A`G#^@") Designation22231 / 92079Ah'ڍ``A#RNLaunch date22 Nov 1992 at 20:53 UTt'A``M#jN"N ,㹌לCountry of originUnited Statesg``M#j4"H̀シMissionNavigationb!` `A#RB"Perigee/Apogee20088/20275 km` `͌`V`b`A#R*Inclination54.7U ``A#R(Period717.9 minp#b`'`M#jF" &p㉂Launch vehicleDelta 2 #216&`M`# 8'``' "(Technical data9M``) " Fr ̀Frequencies< ``1rׁL`F``GPS BIIA-17L`F`8 @* c%" GPS BIIA-17T1``# bAlso called USA 087 or Navstar 2A-17 or GPS 291 F``'  Generalg `2`G#^@") Designation22275 / 92089Ah'``A#RNLaunch date18 Dec 1992 at 10:16 UTt'2``M#jN"N ,㹌לCountry of originUnited Statesg`u`M#j4"H̀シMissionNavigationb!``A#RB"Perigee/Apogee20044/20320 kmVu`-`A#R*Inclination54.6S``A#R$Period718 minp#-``M#jF" &p㉂Launch vehicleDelta 2 #217&``# 8`N`' "(Technical data9``) " Fr ̀Frequencies< N``1qp=M``O`GPS BIIA-18L``8 @* c%" GPS BIIA-18T1`c`# bAlso called USA 088 or Navstar 2A-18 or GPS 221 ``'  Generalg c``G#^@") Designation22446 / 93007Ag&`b`A#RLLaunch date3 Feb 1993 at 02:55 UTt'``M#jN"N ,㹌לCountry of originUnited Statesgb`=`M#j4"H̀シMissionNavigationb!``A#RB"Perigee/Apogee19995/20370 kmV=``A#R*Inclination54.5S`H`A#R$Period718 minp#``M#jF" &p㉂Launch vehicleDelta 2 #218&H``# 8``' "(Technical data9`O`) " Fr ̀Frequencies< ``1ׁN``IaGPS BIIA-19LO``8 @* c%" GPS BIIA-19T1`+`# bAlso called USA 090 or Navstar 2A-19 or GPS 311 `\`'  Generalg +``G#^@") Designation22581 / 93017Ah'\`+`A#RNLaunch date30 Mar 1993 at 03:29 UTt'``M#jN"N ,㹌לCountry of originUnited Statesg+``M#j4"H̀シMissionNavigationb!`h`A#RB"Perigee/Apogee20072/20293 kmV``A#R*Inclination55.2Sh``A#R$Period718 minp#``M#jF" &p㉂Launch vehicleDelta 2 #219K'``$ NEquipped with a Star 37 solid motor8`a' "(Technical da`aO`ta9`Ia) " Fr ̀Frequencies< aa1f=kOaaaGPS BIIA-20LIaa8 @* c%" GPS BIIA-20T1a%a# bAlso called USA 091 or Navstar 2A-20 or GPS 371 aVa'  Generalg %aaG#^@") Designation22657 / 93032A\VaaA#R6Launch date13 May 1993t'aaM#jN"N ,㹌לCountry of originUnited StatesgaaM#j4"H̀シMissionNavigationb!aVaA#RB"Perigee/Apogee20017/20345 kmVaaA#R*Inclination55.2SVaaA#R$Period718 minp#aoaM#jF" &p㉂Launch vehicleDelta 2 #220&aa# 8oaa' "(Technical data9aa) " Fr ̀Frequencies< aBa1tPBaa aGPS BIIA-21Laa8 @* c%" GPS BIIA-21T1Baa# bAlso called USA 092 or Navstar 2A-21 or GPS 391 aa'  Generalg azaG#^@") Designation22700 / 93042Ah'aaA#RNLaunch date26 Jun 1993 at 13:27 UTt'zaVaM#jN"N ,㹌לCountry of originUnited StatesgaaM#j4"H̀シMissionNavigationb!VaaA#RB"Perigee/Apogee20112/20250 kmVauaA#R*Inclination54.4UaaA#R(Period717.9 minp#ua: aM#jF" &p㉂Launch vehicleDelta 2 #221&a` a# 8: a a' "(Technical data9` a a) " Fr ̀Frequencies< a a1rk;Q aY aaGPS BIIA-22L aY a8 @* c%" GPS BIIA-22T1 a a# bAlso called USA 094 or Navstar 2A-22 or GPS 351 Y a a'  Generalg aE aG#^@") Designation22779 / 93054Ah' a aA#RNLaunch date30 Aug 1993 at 12:35 UTt'E a! aM#jN"N ,㹌לCountry of originUnited Statesg a aM#j4"H̀シMissionNavigationb!! a aA#RB"Perigee/Apogee20127/20236 kmV a@ aA#R*Inclination54.6S a aA#R$Period718 minp#@ aaM#jF" &p㉂Launch vehicleDelta 2 #222& a)a# 8aaa' "(Technical data9)aa) " Fr ̀Frequencies< aaa1|Ra"acCaGPS BIIA-23La"a8 @* c%" GPS BIIA-23T1ava# bAlso called USA 096 or Navstar 2A-23 or GPS 341 "aa'  Generalg va@aG#^@") Designation22a@aa877 / 93068A\av@aA#R6Launch date26 Oct 1993t'@a@aM#jN"N ,㹌לCountry of originUnited Statesgv@aQAaM#j4"H̀シMissionNavigationb!@aAaA#RB"Perigee/Apogee20104/20260 kmVQAa BaA#R*Inclination55.2SAa\BaA#R$Period718 minp# BaBaM#jF" &p㉂Launch vehicleDelta 2 #223&\BaBa# 8Ba*Ca' "(Technical data9BacCa) " Fr ̀Frequencies< *CaCa1i;ISCaCa#HaGPS BIIA-24LcCaCa8 @* c%" GPS BIIA-24T1Ca?Da# bAlso called USA 100 or Navstar 2A-24 or GPS 361 CapDa'  Generalg ?DaDaG#^@") Designation23027 / 94016A\pDa3EaA#R6Launch date10 Mar 1994t'DaEaM#jN"N ,㹌לCountry of originUnited Statesg3EaFaM#j4"H̀シMissionNavigationb!EapFaA#RB"Perigee/Apogee20023/20339 kmVFaFaA#R*Inclination55.1VpFaGaA#R*Period717.95 minp#FaGaM#jF" &p㉂Launch vehicleDelta 2 #226&GaGa# 8GaGa' "(Technical data9Ga#Ha) " Fr ̀Frequencies< Ga_Ha1'`T_HaHaMaGPS BIIA-25L#HaHa8 @* c%" GPS BIIA-25T1_HaHa# bAlso called USA 117 or Navstar 2A-25 or GPS 331 Ha0Ia'  Generalg HaIaG#^@") Designation23833 / 96019A\0IaIaA#R6Launch date28 Mar 1996t'IagJaM#jN"N ,㹌לCountry of originUnited StatesgIaJaM#j4"H̀シMissionNavigationb!gJa0KaA#RB"Perigee/Apogee20252/20548 kmVJaKaA#R*Inclination54.8L 0KaKaA#RPeriodp#KaBLaM#jF" &p㉂Launch vehicleDelta 2 #234KaMa' ]The satellite was worth $55 million. A solid Thiokol Star 37 apogee motor was used to circularize the orbitAfter this launch, 3 BIIA satellites are still to be launched8BLaOMa' "(Technical dataR(MaMa* $PFr ̀FrequenciesTelemetry on 2227.5 MHz< OMaMa1IUMa)NaaGPS BIIA-26LMa)Na8 @* c%" GPS BIIA-26T1Ma}Na# bAlso called USA 126 or Navstar 2A-26 or GPS 401 )NaNa'  Generalg }NaOaG#^@") Designation23953 / 96041A\NaqOaA#R6Launch date16 Jul 1996t'Oa aM#jN"N ,㹌לCountry of originUnited StatesqOa aMagqOasaM#j4"H̀シMissionNavigationb! aՀaA#RB"Perigee/Apogee20275/20368 kmVsa+aA#R*Inclination54.8SՀa~aA#R$Period723 minp#+aaM#jF" &p㉂Launch vehicleDelta 2 #237&~aa# 8aLa' "(Technical datalBaa* $Fr ̀FrequenciesTelemetry on 2227.5 MHz (telemetry number PRN 10)< Laa1f`Va@auaGPS BIIA-27La@a8 @* c%" GPS BIIA-27T1aa# bAlso called USA 128 or Navstar 2A-27 or GPS 301 @aŃa'  Generalg a,aG#^@") Designation24320 / 96056A\ŃaaA#R6Launch date12 Sep 1996t',aaM#jN"N ,㹌לCountry of originUnited StatesgacaM#j4"H̀シMissionNavigationb!aŅaA#RB"Perigee/Apogee20275/20368 kmVcaaA#R*Inclination54.8SŅanaA#R$Period723 minp#aކaM#jF" &p㉂Launch vehicleDelta 2 #238&naa# 8ކaDimension7.7 x 5.5 x 4.6 mW| b3 bA#R,Solar array21.5 mY b bA#R0 Stabilization3 axisY3 b bA#R0DC powerEOL: 3980 Wb! bGbA#RB$Design lifetime2 years (min) bb- (S@ĘRealtime acquisition via TDRS (tape recorders have failed).Telemetry: 2287.5 MHz (realtime: 1/32 kbps, playback: upto 512 kbps)Command: 2106.4 MHz (1/0.125 kbps)`3Gb}b- *f  BATSE (Burst and Transcient Source Experiment)XbbA#R.Payload mass976 kgk*}bL@bA#RTbL@bb8Industrial responsibilityMarshall SFCf%b@bA#RJ2Gamma-ray energy range20-600 keVAL@b@b$ :Equipped with 8 detectorsg:@bZAb- *t  OSSE (Oriented Scintillation Spectrometer Experiment)Y@bAbA#R0Payload mass1820 kgm,ZAb BbA#RX8Industrial responsibilityBall Aerospacej)AbBbA#RR2Gamma-ray energy range100 keV-10 MeV& BbBb# T'BbCb- *N  COMTEL (imaging COMpton TELescope)YBb]CbA#R0Payload mass1460 kgb!CbCbA#RB8Industrial responsibilityMBBd#]Cb#DbA#RF2Gamma-ray energy range1-30 MeV`CbDbA#R>*Angular resolution1.7-4.4&#DbDb# b5Db Eb- *j  EGRET (Energetic Gamma Ray Experiment Telescope)YDbdEbA#R0Payload mass1830 kgj) EbEbA#RR8Industrial responsibilityGoddard SFCi(dEb7FbA#RP2Gamma-ray energy range20 MeV-30 GeV&Eb]Fb# ?7FbFb1D_FbFbzGbProgram: GstarO]FbFb8 @0w " Program: GstarfFbzGb) "D"American telecommunication satellite program operated by GE Americom, formerly GTE Spacenet Corp.1FbGb1`Gb/Hb<zGb/HbH `x :T;Tv=;Ā=J@SpecificationsKb3bbu-bandTransponder frequency chart8bkb1L*ekbbbGstar 2H3bb8 @"w " Gstar 21 kbb'  Generalg bKbG#^@") Designation16649 / 86026A\bbA#R6Launch date28 Mar 1986t'KbbM#jN"N ,㹌לCountry of originUnited Stateso"bbM#jD"H̀‰MissionTelecommunicationsb!bbA#RB,Geostationary orbitsee belown!bZbM#jB" &C+Launch vehicleAriane V17&bb# 2 Zbb'  Locationb105W!bbj#B ;T"Gstar 2's Ku-band EIRP8bb1gbbbGstar 3HSbb8 @"w " Gstar 31 bb'  Generalg bkbG#^@") Designation19483 / 88081A[bbA#R4Launch date8 Sep 1988t'kb:bM#jN"N ,㹌לCountry of originUnited Stateso"bbM#jD"H̀‰MissionTelecommunicationsg&:bbA#RL,Geostationary orbit93W, inclinedn!b~bM#jB" & D+Launch vehicleAriane V25]9bb$ rThis satellite had a motor problem and so is inclined5~bb'  End of life\blbA#R6"Out of serviceApr 1997t3bbA#RfCausedecommissioned, inclination too important&lbb# 8b>b' "(Technical datar;bb7 >v=;Ā=J@SpecificationsKu-bandTransponder frequency chart8>bb1S*hb0bJcGstar 4Hb0b8 @"w " Gstar 41 bab'  Generalg 0bbG#^@") Designation20946 / 90100B\ab$bA#R6Launch date20 Nov 1990t'bbM#jN"N ,㹌לCountry of originUnited Stateso"$bcM#jD"H̀‰MissionTelecommunicatbcbionsb!bucA#RB,Geostationary orbitsee belown!ccM#jB" &fD+Launch vehicleAriane V40&uc c# : cCc- */ۀ Location ccm#:   " BeginEndPositionCcNcj#.$(*L: 20 Nov 1990"ccj#D46< May 1992May 1992 >125WNc[cj#. =T"Gstar 4's Ku-band EIRP7{cc12jc=c cHaruka7 c=c, (" Harukapcc# Means "far away", also called Muses B and Halca (Highly Advanced Laboratory for Communications and Astronomy)1 =cc'  Generalg chcG#^@") Designation24720 / 97005A\ccA#R6Launch date12 Feb 1997lhc0cM#j>"N ,bCountry of originJapanr%ccM#jJ"H̀_BMissionScientific: astronomyb!0ccA#RB"Perigee/Apogee565 / 21462 kmVcZcA#R*Inclination31.3SccA#R$Period374 minhZc cM#j6" & Launch vehicleMu 55 cJ c) Operated by IsasHaruka is the space segment of the VSOP (VLBI Space Observatory Programme), and will unfurl an 8-meter radiotelescope antenna to make joint observations with ground based radio observatories, simulating a telescope larger than the Earth. Haruka carries detectors operating at 1.6, 5 and 22 GHz, and will be able to make radio images with very high spatial resolution, permitting precise measurements of quasar jets and galactic maser sources.Downlinks at 128 kbps (2.2636 GHz). Lifetime: 3 to 5 years< c c' *O External resourcesRJ c c. ,http://www.vsop.isas.ac.jp/MUSES_B.htmlhttp://www.vsop.isas.ac.jp/VSOP.html: c@ c1 Dk@ c cGcHealthsatB c c2 4""  HealthsatnK@ c c# Also called Healthsat 2 because Uosat 3 provided services as Healthsat 11 c! c'  Generalg c cG#^@") Designation22827 / 93061E\! c cA#R6Launch date25 Sep 1993t' cXcM#jN"N ,㹌לCountry of originUnited Stateso" ccM#jD"H̀㓉MissionTelecommunications^Xc%cA#R:"Perigee/Apogee788/803 kmVc{cA#R*Inclination98.7U%ccA#R(Period100.8 minn!{cJ@cM#jB"cJ@c c &D+Launch vehicleAriane V59[c@cA#R4"Mass at launch47.5 kgJ@cUAc% Transmits medical data (provided by the United States, Canada and the UK) to African universities, hospitals and documentation centers.1 @cAc' O ContactUAc;Bc/ , SatelLife1360 Soldier's Field Rd., Boston, MA 02135, USATel: +1-617-789-5455Fax: +1-617-789-4771Email: hnet@usa.healthnet.org<AcwBc' *O External resourcesW;BcBc. ,http://www.healthnet.org/http://www.ee.surrey.ac.uk/CSER/UOSAT/missions/hs2.html8wBc4Cc' "(OTechnical data8BclCc' " Specifications>4CcCcG#^|& Prime contractorSSTL (Surrey Satellite Technology Ltd.)RlCcCDcA#R"PlatformSSTL[CcDcA#R4"Mass at launch50.5 kgSCDcDcA#R$ Mass in orbitRDcCEcA#R"Length352 mmQDcEcA#R Width356 mmRCEcEcA#R"Height670 mmc"EcIFcA#RD Stabilizationgravity gradientN EcFcA#RDC power\IFcFcA#R6$Design lifetime5 years&FcGc# > FcWGc1vlWGcGcIcProgram: HeaoNGcGc8 @.G" Program: HeaoEWGcIc+ $5 High Energy Astronomy ObservatoryAmerican scientific program made of 3 large observatories designed to study the "high energy universe," i.e., X-rays, gamma rays, and cosmic particles. The scientific objectives of the HEAO program were to learn more about some of the most puzzling objects in the universe: pulsars, neutron stars, black holes, quasars, radio galaxies, and supernovas. Many of these radiate only in the X-ray, gamma ray, and cosmic ray regions of the electromagnetic spectrum and cannot be studied from the ground.1GcJc1mJcJco.IcJcA R\9ڰFI۰FIܰFIProgram: HeaoHeao 1Heao 2Heao 37JcJc1VnJcKccHeao 1GJcKc8 @ G" Heao 11 Jc9Kc'  Generalg KcKcG#^@") Designation10217 / 77075A\9KcKcA#R6Launch date12 Aug 1977t'KcpLcM#jN"N ,㹌לCountry of originUnited Statesx+KcLcM#jV"H̀_BMissionScientific: X-ray astronomy^pLcFMcA#R:"Perigee/Apogee429/447 kmVLcMcA#R*Inclination22.7TFMcMcA#R&Period93.4 minq$McaNcM#jH" &yjLaunch vehicleAtlas Centaur_McNcA#R<Launch siteCape Canaveral_aNcOcA#R<"Mass at launchapprox. 3 t&NcEOc# 5OczOc'  End of lifeVEOcOcA#R*Decay15 Mar 1979&zOc c# Oc cJc<OcHc' *O External resourceshA cc' http://heasarc.gsfc.nasa.gov/docs/heasarc/missions/heao1.html7Hcc1oc.ccHeao 2Gc.c8 @ G" Heao 2H%cvc# JAlso called "Einstein observatory"1 .cc'  Generalg vccG#^@") Designation11101 / 78103A\cjcA#R6Launch date13 Nov 1978t'cނcM#jN"N ,㹌לCountry of originUnited Statesx+jcVcM#jV"H̀_BMissionScientific: X-ray astronomy^ނccA#R:"Perigee/Apogee526/548 kmVVc cA#R*Inclination23.5Tc^cA#R&Period95.4 minq$ cτcM#jH" &yjLaunch vehicleAtlas Centaur_^c.cA#R<Launch siteCape Canaveral_τccA#R<"Mass at launchapprox. 3 t.chc' iEquipped with a 58cm diameter telescope with a 3.3m focal length. The satellite also contained five other instruments, 4 of which shared the use of the telescope to make a variety of measurements of X-rays emitted by stellar objects. The fifth instrument, independent of the telescope, measured properties of X-rays beyond the telescope's energy range.Built by TRW Defense and Space Systems for NASA's Marshall Space Flight Center5cc'  End of lifeVhccA#R*Decay25 Mar 1982&cc# <cUc' *O External resourceshAcc' http://heasarc.gsfc.nasa.gov/docs/heasarc/missions/heao2.html7Ucc1Vpc;cЎcHeao 3Gc;c8 @ G" Heao 31 clc'  Generalg ;cӉcG#^@") Designation11532 / 79082A\lc/cA#R6Launch date20 Sep 1979t'ӉccM#jN"N ,㹌לCountry of originUnited States|//ccM#j^"H̀_BMissionScientific: gamma-ray astronomy^c}cA#R:"Perigee/Apogee487/503 kmVcӋcA#R*Inclination43.6T}c'cA#R&Period94.5 minq$ӋccM#jH" &yjLaunch vehicleAtlas Centaur_'ccA#R<Launch siteCape Canaveral_cVcA#R<"Mass at launchapprox. 3 t&c|c# 5Vcc'  End of lifeU|ccA#R(Decay7 Dec 1981&c,c# <chc' *O External resourceshA,cЎc' http://heasarc.gsfc.nasa.gov/docs/heasarc/missions/heao3.html@hcc1`qc\cicProgram: HliosLЎc\c5 :0/]" Program: Hlios ctc& In Greek mythology Helios was all-seeing and all-knowingFrench military observation program. The first generation is financ\ctcЎced by France (79%), Italy (14%) and Spain (7%). Operated by the DGA (Dlgation Gnrale l'Armement) and the CNES. Each country can use the satellite in proportion of its financial participation. Each country can order observations and obtain the results via its Earth station. Each country's results are cyphered so that only the orderer can use the data.D\cc' ;The second generation (Helios 2) is planned for 2002 and will be achieved by France and Spain (3%). It is supposed to cost $1.2 billion. It would be equipped with for optical and IR observation. 2 identical satellites are to be built, based on the MMS Mark 2+ bus (3600 kg) Belgium is willing to participate to the project.Other French military projects: satellite Osiris & Horus (radar/electromagnetic reconnaissance) should cost $2.4 billion (with Germany taking part). [Horus has been cancelled in April 1998 by lack of financing] tcic1 0fN5Zenon (eavesdropping satellite) and Clementine (the Cerise companion). Also for military communications see Trimilsatcom1cc1rccg-icc: DZhh휭i휭Program: HliosHlios 1AHlios 1B: c;c1s;ccTcHlios 1AFcc5 :$/]" Hlios 1A1 ;cc'  Generalg ccG#^@") Designation23605 / 95033A[ctcA#R4Launch date7 Jul 1995m ccM#j@"N ,㱭+Country of originFrancem&tcNcG#^L"H̀MissionMilitary: reconnaissance^ccA#R:"Perigee/Apogee673/676 kmVNccA#R*Inclination98.1TcVcA#R&Period98.2 minn!ccM#jB" &D+Launch vehicleAriane V75^VcFc$ Hlios 1A carries an eavesdroppring payload called Euracom, built by Dassault Electronique8c~c' "(OTechnical data8Fcc' " Specifications@~c7cA#R&Prime contractorMatra Marconi Space (under control of CNES)[ccA#R4PlatformSpot (Mark 2)[7ccA#R4"Mass at launch2537 kgSc@cA#R$ Mass in orbitOccA#RDimensionn-@ccA#RZ Stabilizationguidance by momentum wheelsTcQcA#R&DC power2200 W\ccA#R6$Design lifetime5 yearsQcTc' 2 tape recorders, only optical observationThe Hlios system downlinks in S-band at 2206.53 MHz and in X-band at 8253.0 MHz: cc1*ʂtccdHlios 1BFTcc5 :$/]" Hlios 1B1 cc'  GeneralYc^cG#^$") Designations2ccA#RdLaunch dateplanned for late 1996 / early 1997m ^c>cM#j@"N ,㱭+Country of originFrancem&ccG#^L"H̀MissionMilitary: reconnaissanceT>c dA#R&"Perigee/Apogeec dTcQc]dA#R InclinationL ddA#RPeriodj]ddM#j:" &2!Launch vehicleArianedd- ()h휭When this satellite is launched the revisit period will be about 1 day. Same orbit but 180 degrees separationProbably identical to Helios 1A1dd1WudYddT+dYd) "VȠ$To view this page you need to register&dd# > Ydd1vddpdProgram: HeosJdd5 :,G" Program: HeosiAdpd( Highly Eccentric Orbit SatelliteEuropean scientific program1dd1wdd_%pdd: DJ<WIWIProgram: HeosHeos 1Heos 27d7d1 x7d~dW dHeos 1Gd~d8 @ G" Heos 11 7dd'  Generalg ~ddG#^@") Designation03595 / 68109A[dqdA#R4Launch date5 Dec 1968m ddM#j@"N ,4"Country of originEurope{.qdYdM#j\"H̀d;plMissionScientific: magnetophere studyc"ddA#RD"Perigee/Apogee20020/202780 kmVYddA#R*Inclination60.5VdhdA#R*Period6704.3 minr%ddM#jJ" &p㉂Launch vehicleThor Delta #61Zhd4dA#R2"Mass at launch128 kgtPdd$ Study of the inter-planetary magnetic field, solar wind and space particles.54dd'  End of lifeVd3 dA#R*Decay28 Oct 1975$dW d" 73 d d1vy d ddHeos 2GW d d8 @ G" Heos 21 d d'  Generalg dm dG#^@") Designation05814 / 72005A\ d dA#R6Launch date31 Jan 1972m m d6 dM#j@"N ,4"Country of originEurope{. d dM#j\"H̀d;plMissionScientific: magnetophere studya 6 d dA#R@"Perigee/Apogee405/240164 kmV dh dA#R*Inclination89.9V d dA#R*Period7477.1 minr%h d0 dM#jJ" &p㉂Launch vehicleThor Delta #87Z d dA#R2"Mass at launch117 kgd0 dd$ Study of the high altitude magnetosphe limits and inter-planetary magnetic fields and particles.5 dGd'  End of lifeUddA#R(Decay2 Aug 1974$Gdd" 6dd1 zd,dKdHESSI6 d,d, (" HESSIL)dxd# RHigh Energy Solar Spectroscopic Imager1 ,dd'  GeneralYxd@dG#^$") Designationd@ddUdc@dA#R(Launch date2000t'@d@dM#jN"N ,㹌לCountry of originUnited Statesr%c@dIAdM#jJ"H̀jMissionScientific: Sun studyT@dAdA#R&"Perigee/ApogeeQIAdAdA#R InclinationL Ad:BdA#RPeriod\AdBdG#^*" &Launch vehicleQ:BdBdA#R Launch siteO*Bd6Fd% UHESSI will investigate the physics of particle acceleration and energy release in solar flares through an unprecedented combination of high resolution imaging and spectroscopy of X-rays and gamma rays from 2 keV to 20 MeV during the next solar maximum. It uses Fourier-transform imaging with 12 bi-grid modulation collimators and cooled germanium and silicon detectors mounted on a Sun-pointed spin-stabilized spacecraft in a low-altitude equatorial orbit. HESSI will carry out the first imaging spectroscopy in hard X-rays with 2 arcseconds angular resolution, time resolution to tens of ms, and \sim1 keV energy resolution; the first gamma-ray line spectroscopy from a spacecraft with \sim1 keV energy resolution; and the first gamma-ray line and continuum imaging with 20 arcseconds angular resolution. ABdwFd$ :Project cost: $12 million<6FdFd' *O External resourcesewFdFGd. ,http://hesperia.gsfc.nasa.gov/sftheory/hessi.htmhttp://www701.gsfc.nasa.gov/7011/imdo_HESS.htm&FdlGd# 8FGdGd' "(OTechnical data8lGdGd' " Specificationsg&GdCHdA#RL&Prime contractorSpectro Astro IncN GdHdA#RPlatformTCHdHdA#R&"Mass at launchSHd8IdA#R$ Mass in orbitOHdIdA#RDimensionQ8IdIdA#R Solar arrayb!Id:JdA#RB Stabilizationspin stabilizedN IdJdA#RDC powerU:JdJdA#R($Design lifetime&JdKd# 1Jd4Kd1W{4KdKdKdT+KdKd) "VȠ$To view this page you need to register&4KdKd# 5KdKd1|KdLddHETE5 KdLd, (" HETEJ$KdbLd& H High-Energy Transient Experiment1 LdLd'  General>bLdMdN#l|") ˓FWDesignationn/a / 96061AFailed to separate with SAC B[LdzMdA#R4Launch date4 Nov 1996t'MdMdM#jN"N ,㹌לCountry of originUnited States_zMdMNdG#^0"H̀MissionScientificTMdNdA#R&"Perigee/ApogeeQMNdNdA#R InclinationL Nd>OdA#RPeriodr%NdOdM#jJ" &GKTLaunch vehiclePegasus XL #14&>Odd% The prime objective of HETE is to carry oOddKdut 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.Odd+ $-˓FWHETE was carried inside the Dual Payload Attach Fixture on which SAC B was mounted, so it was trapped and was unable to deploy its solar panels.<d߂d' *O External resourcesyKdXd. ,http://nis-www.lanl.gov/nis-projects/hete/http://space.mit.edu/HETE/8߂dd' "(Technical dataP)Xdd' R Omnidirectional Gamma-Ray Spectrometer[d;dA#R4[Build byCESR (France)e$ddA#RH[$Instrument typeNaI(Tl); cleavedb!;ddA#RB[Energy range6 keV to > 1 MeV[d]dA#R4[(Timing resolution4 msr1dυdA#Rb[,Spectral resolution~40% @ 6 keV; ~7% @ 1 MeVq0]d@dA#R`["Effective area120 cm**2 (total for 4 units)@υddA#R[2Sensitivity (10 sigma)3 x 10**-8 erg/cm**2/s for 8-1000 keVR@ddA#R"[ FOV~ 2 pi sr^dqdA#R:[*Angular resolution~ 1 sr&dd# Bqdهd' 6 Wide Field X-ray Monitorj)dCdA#RR&ZBuild byRIKEN (Japan) and LANL (USA)>هdˆdA#R|&Z$Instrument type2 1-dim Coded aperture cameras, with PSPCs]CddA#R8&ZEnergy range2 to 25 keV[ˆdzdA#R4&Z(Timing resolution1 mse$d߉dA#RH&Z,Spectral resolution~18% @ 6 keVo.zdNdA#R\&Z"Effective area200 cm**2 (each of 2 units)>߉d͊dA#R|&Z2Sensitivity (10 sigma)8 x 10**-9 erg/cm**2/s for 2-10 keVZNd'dA#R2&Z FOV~ 2 sr (combined)U͊ddA#R&Z>Angular resolution (1 sigma)about 10 arcmin (location accuracy better than that)&'dd# L%d/d' J Ultraviolet Transient Camera ArrayWddA#R,&ZBuild byMIT (USA)}</ddA#Rx&Z$Instrument type4 UV CCD Detectors with 35 mm f/2 optics[d^dA#R4&ZEnergy range5 to 7 eV\ddA#R6&Z(Timing resolution~ 4 s{:^d5dA#Rt&Z,Spectral resolutionn/a (Broadband imaging photometer)o.ddA#R\&Z"Effective area2.5 cm**2 (each of 4 units)r15ddA#Rb&Z2Sensitivity (10 sigma)1 x 10**-9 erg/cm**2/se$d{dA#RH&Z FOV~ 1.7 sr (total for 4 units)n-d dA#RZ&Z>Angular resolution (1 sigma)+/- 3 arcsec{d dKd{dd' The spacecraft hardware and software is being developed by Aeroastro (USA).Downlink frequencies: 137.963 (300 bps) & 2272 MHz: dd1 Յ}d2ddHipparcosBd2d2 4""  Hipparcosvdd&  HIgh Precision PARallax COllecting Satellite, named as a Greek astronomer of the 2nd century before JC: Hipparkhos1 2dd'  Generalg dfdG#^@") Designation20169 / 89062B[ddA#R4Launch date8 Aug 1989m fd.dM#j@"N ,4"Country of originEuroper%ddM#jJ"H̀_BMissionScientific: astronomy`.ddA#R>"Perigee/Apogee498/35889 kmUdUdA#R(Inclination6.5UddA#R(Period638.7 minn!UddM#jB" &4D+Launch vehicleAriane V33dd' 7Was intended on geostationary 12W slot but its Mage motor didn't work. The data it provided from Nov 1989 on was recalculated to match its orbital position.Hipparcos observed 118274 stars with a precision between 0.0008 and 0.002 arcsec depending on the objects magnitude. 10000 double stars were observed including 7000 which were discovered by the satellite. It also discovered numerous variable stars.5dd'  End of life_dndA#R<"Out of service15 Aug 1993l+ddA#RVCauseStopped transmitting in June 1993&ndd# <dHispasat's direct TV missionXveeA#R.0(Main transponders3ZejeA#R20,Backup transponders1WeeA#R,0Power110 W (TWTA)UjeeA#R(0Bandwidth27 MHz\ereG#^*0"p>EIRP max58 dBW\eeA#R60Polarizationcircular LYre'eA#R00Uplink12.1-12.5 GHz[eeA#R40Downlink17.3-17.7 GHz$'ee" 1ee1Ue0 eT eT1e+e# bHispasat's telecommunication to Europe missionXeeA#R.0(Main transponders8Z+eeA#R20,Backup transponders4Ve3 eA#R*0Power50 W (TWTA)q.e eC#V\0Bandwidth4 x 36 MHz2 x 46 MHz2 x 72 MHz\3 e eG#^*0"9wEIRP max51 dBWX eX eA#R.0Polarizationlineark* e eA#RT0Uplink14.0-14.25 GHz & 14.25-14.5 GHzm,X e0 eA#RX0Downlink12.5-12.75 GHz & 11.45-11.7 GHz$ eT e" 10 e e1U e eDe_<T e e# xHispasat's telecommunication to America mission (Ku-band)X e< eA#R.0(Main transponders2Z e eA#R20,Backup transponders1W< e eA#R,0Power110 W (TWTA)U eB eA#R(0Bandwidth36 MHz= e eG#^z0"P64Coverage and EIRP maxSouth and Central America: 53 dBWZB e eA#R20Polarizationlinear V$ eDe" 1 eue1Uue Ae-Ae7Dee# (Hispasat's X-bandXueeA#R.0(Main transponders1Ze^eA#R20,Backup transponders1VeeA#R*0Power40 W (TWTA)U^e@eA#R(0Bandwidthe@eDe40 MHzN ec@eA#R0CoverageT@e@eA#R&0EIRP max42 dBWRc@e AeA#R"0Polarization$@e-Ae" 1 Ae^Ae1U^Aee eR/-AeAe# ^Hispasat's transponder frequency chart (GHz)R^AeBe#bQ]?O2JdtTransponderUplinkDownlinkBandwidthMainReserveCoverageDAeCe#,Q]?O  4<DLN1614.317 V11.517 H721B1Aswitchable Europe / America.BeDe#,\Q]?O 2:BJL714.317 H11.517 V721A1BEurope/CevEe#,^Q]?O  4<DLN1714.397 V11.597 H721A1BEurope.DeRFe#,\Q]?O 2:BJL814.397 H11.597 V721B1AEuropeBvEeBGe#,Q]?O  4<DHJ1814.464 V11.664 H461Bswitchable Europe / America,RFeHe#,XQ]?O 2:BFH914.468 H11.668 V541AEurope0BGeHe#,`Q]?O  4<DLN1514.249 V12.015 V361B1AAmerica/HeIe#,^Q]?O 2:BJL614.249 H12.078 V361A1BAmerica3HeJe#,fQ]?O *HPVZ\2317.32748 RHCP12.14944 LHCP27?DBS3IeKe#,fQ]?O *HPVZ\2717.40420 RHCP12.22616 LHCP27?DBS3JezLe#,fQ]?O *HPVZ\3117.48092 RHCP12.30288 LHCP27?DBS3Ke[Me#,fQ]?O *HPVZ\3517.55764 RHCP12.37960 LHCP27?DBS3zLe"N ,qn͉Country of originSpaino"Ke&eM#jD"H̀‰MissionTelecommunicationseeeG#^<"/ۀ0Geostationary orbit30Wn!&eeM#jB" &D+Launch vehicleAriane V53P,eIe$ XThe X-band payload failed on 18 Dec 19978ee' "(Technical dataIeQeM h-ÀLj}ŸWG@~~|SpecificationsDirect TVTelecommunication to EuropeTelecommunication to AmericaX-bandTransponder frequency chart=ee' , EIRP coverage (dBW)|QeCe9 Bp>9wP6鉂Direct TVTelecommunication to EuropeTelecommunication to AmericaBeacon: 12.7475 GHz vertical (backup in S-band)< ee1eˎeeHispasat 1BLCeˎe8 @*" Hispasat 1B1 ee'  Generalg ˎeceG#^@") Designation22723 / 93048A\eeA#R6Launch date22 Jul 1993lce7eM#j>"N ,e7eCeqn͉Country of originSpaino"eeM#jD"H̀‰MissionTelecommunicationse7e eG#^<"/ۀ0Geostationary orbit30Wn!eyeM#jB" &D+Launch vehicleAriane V58& ee# 8yee' "(Technical dataeeM h-ÀLj}ŸWG@~~|SpecificationsDirect TVTelecommunication to EuropeTelecommunication to AmericaX-bandTransponder frequency chart=ee' , EIRP coverage (dBW){ee9 Bp>9wP6鉂Direct TVTelecommunication to EuropeTelecommunication to AmericaBeacon: 12.749 GHz vertical (backup in S-band)< ee1+e efHispasat 1CLe e8 @*" Hispasat 1C1 eQe'  GeneralY eeG#^$") DesignationZQeeA#R2Launch datelate-1999lepeM#j>"N ,qn͉Country of originSpaino"eeM#jD"H̀‰MissionTelecommunicationsepeDeG#^<"/ۀ0Geostationary orbit30WaeeG#^4" &Launch vehicleAtlasK'Dee$ NSatellite worth approx. $85 million8e(e' "(Technical data;ece) "$}ʃZone coverage8(ee' " Specificationsb!ceeA#RB&Prime contractorAerospatiale[eXeA#R4PlatformSpacebus 3000[eeA#R4"Mass at launch2800 kgSXeeA#R$ Mass in orbitOeUeA#RDimensionQeeA#R Solar arrayYUeeA#R0 Stabilization3 axisl+ekeA#RVDC powerEOL: 6000 W (+ NiH2 batteries)]eeA#R8$Design lifetime15 yearslHke4e$ Command: S-band (before GEO and emergency) & Ku-band (normal status)<epe' * Ku-band to America_4eeA#R<(Main transpondersup to 12Ype(eA#R0,Backup transpondersPexeA#RPower120 WU(eeA#R(Bandwidth36 MHzxeeB#RCoverageAmerica (almost full South America excluding Portuguese speaking zones, Central America including islands and part of the US)TeeA#R&EIRP max47 dBW<eleC#VxG/T maxAmerica: +1 dB/KEurope: +3 dB/KIberia: +8 dB/KReeA#R"Polarization&lee# ;ee' ( Ku-band to Europe_e~eA#R<(Main transpondersup to 17YeeA#R0,Backup transpondersP~e3fA#Re3fePower120 WUefA#R(Bandwidth36 MHzY3ffA#R0Coveragefull EuropeTf5fA#R&EIRP max47 dBW<ffC#VxG/T maxAmerica: +1 dB/KEurope: +3 dB/KIberia: +8 dB/KR5ffA#R"Polarization&f,f# ;fgf' ( Ku-band to Iberia_,ffA#R<(Main transpondersup to 17YgffA#R0,Backup transpondersPfofA#RPower120 WUffA#R(Bandwidth36 MHzLofQfA#RCoverageIberia peninsule + Balearic, Canary, Madeira and Azores islandsTffA#R&EIRP max56 dBW<Qf$fC#VxG/T maxAmerica: +1 dB/KEurope: +3 dB/KIberia: +8 dB/KRfvfA#R"PolarizationQ-$ff$ Ztotal simultaneous transponder in use: 221vff1WfLfrfT+fLf) "VȠ$To view this page you need to register&frf# 1Lff1ffPrff6 <6c̀"Hispasat 1C's EIRP1f$f1W$fxffT+fxf) "VȠ$To view this page you need to register&$ff# 4xff1?Յff=GfHST< ff2 4"  HSTzTff&  Hubble Space Telescope, named as the American astrophysician Edwin Powell Hubble1 ff'  Generalg f fG#^@") Designation20580 / 90037B\f| fA#R6Launch date24 Apr 1990t' f fM#jN"N ,㹌לCountry of originUnited StatesR| fB fA#R"OperatorNASAr% f fM#jJ"H̀_BMissionScientific: astronomy^B f fA#R:"Perigee/Apogee589/598 kmV fh fA#R*Inclination28.5R f fA#R"Period96 minkh f% fM#j<" &JDLaunch vehicleSTS 31R f f: B]K\PThe Hubble Space Telescope (HST) was the first of the Great Observatories launched, and is exploring our universe in the visible, ultraviolet, near-infrared regions of our electromagnetic spectrum. It was designed by Lynan Spitzer and proposed to NASA in the early 60ies. It is maintained by the Shuttle: first servicing mission: STS 61. Next missions planned: Feb 1997 (STS 82) and May 2000 (STS 106)Cost: $3 billion<% fIf' *O External resourcesH! ff' Bhttp://www.stsci.edu/top.html8Iff' "(OTechnical data8ff' " SpecificationsLffB#T&Prime contractorLockheed (spacecraft)Perkin Elmer (mirror & telescope)\f @fA#R6"Mass at launch11250 kgf @ffTf`@fA#R&Diameter4.25 mR @f@fA#R"Height13.1 m\`@fAfA#R6Solar array12 x 2.83 mY@fgAfA#R0 Stabilization3 axisYAfAfA#R0DC powerBOL: 5500 W]gAfBfA#R8$Design lifetime15 yearsAfBf. *@ĘData acquisition via TDRSTelemetry: 2287.5 MHz (500 bps, 4 kbps, 32 kbps)Command: 2106 MHz (1/0.125 kbps)Data: 2255.5 MHz (1024 kbps)1 Bf Cf'  Payloadb!BflCfA#RB4Primary mirror diameter2.4 m_ CfCfA#R<,Primary mirror mass800 kgl+lCf7DfA#RV$Frequency bandsUV, visible and near IR[CfDfA#R4Resolution0.1 arcsecse$7DfDfA#RH*Pointing stability0.007 arcsecsFDf=Gf) ;Wide-Field Planetary Camera, Faint Object Camera (ESA), Faint Object Spectrograph, High Resolution Spectrograph, High Speed PhotometerThe WFPC 2 replaced the original camera on 1st servicing mission and Costar replaced the High Speed PhotometerOn the second servicing mission, the Space Telescope Imaging Spectrograph replaced both GHRS (the Goddard High Res Spectrograph) and FOS (the Faint Object Spectrograph). NICMOS, the Near Infrared Camera and Multi-Object Spectrometer was added to overs the 0.8 to 2.5 micron spectral range.= DfzGf1 spzGfGffProgram: ICO==GfGf, ($" Program: ICOBzGfIf* "1Intermediate Circular Orbit, also known as Inmarsat PGlobal mobile telephone system operated by ICO Global Communications, expected to begin service in 1999.The 12 satellites are worth: $1.3 billion. Under a separate agreement, Hughes will invest $93.8 million to become a strategic partner in ICO. The launch cost is estimated at $925 million (for 12 satellites) Cost per satellite: $275 millionTRW cancelled its Odyssey MEO satellite system and bought 7% of ICO ($150 million), becoming the largest shareholder in late 1997.<Gf5Jf' *O External resources>IfsJf' .http://www.ico.com/85JfJf' "(OTechnical datasJfoKf' ;First satellite will be launched by Atlas 2AS5 satellites will launch on Delta 33 satellites will launch on Zenit3 satellites will launch on Sea Launch2 JfKf'  OverviewSoKfKfA#R$ Orbit typeMEOc"KfWLfA#RD Orbit range10335 km, circularc"KfLfA#RD &Nb of satellites10 + 2 backupSWLf MfA#R$ Nb of planes2TLfaMfA#R& Inclination45_ MfMfA#R< 2Nb beams per satellite121WaMfNfA#R, Coverage12900 kmb!MfyNfA#RB Modulationcombined FDMA/TDMAg&NfNfA#RL *Mobile frequencies1980 - 2010 MHz[yNf;OfA#R4 "Satellite mass2300 kgWNfOfA#R, CoverageWorldwided#;Of fA#RF &Operational date2000 (planned)Of f=GfR.Of^f$ \6 satellites are needed to start operating8 ff' " Specifications\^ffA#R6&Prime contractorHughes]fOfA#R8Platformmodified HS-601[ffA#R4"Mass at launch2750 kgSOffA#R$ Mass in orbitOfLfA#RDimensionQffA#R Solar arraySLffA#R$ StabilizationYfIfA#R0DC powerEOL: 8700 W]ffA#R8$Design lifetime12 yearsIff' Will feature C- and S-band payloads. Links between terminals and satellites: 1.6/1.5 GHz, 1.6/2.4 GHz. Links between gateways and satellites: 5 and 7 GHzDesigned to work with terrestrial GSM1f„f1W„ff" &bnW"Launch vehicleAthena 2QfhfA#R Launch site^ff, (J[To be the first 1 meter commercial remote sensing satelliteOwned and operated by Eosat8hf*f' "(OTechnical data8fbf' " Specificationse$*fnjfA#RH&Prime contractorLockheed MartinN bffA#RPlatformZnjfofA#R2"Mass at launch817 kgSffA#R$ Mass in orbitOoffA#RDimensionQfbfA#R Solar arraySffA#R$ StabilizationN bffA#RDC powerUfXfA#R($Design lifetimexff' Equipped with a Kodak digital camera. This payload will enable Ikonos 1 to collect 1-meter resolution panchromatic (gray-scale)Xff=f resolution and 4-meter resolution, four-band multispectral (red, green, blue, near infrared) imagery of the Earth. The camera is comprised of a Kodak-designed and -manufactured focal plane array and a lightweight telescope using a state-of-the-art mirror fabricated with Kodaks advanced ion figuring technology. To speed the downloading of data to Space Imaging EOSATs ground receiving stations, the original 11-bit data will be compressed using Kodaks proprietary bandwidth compression technology.1Xf4f1W4fffT+ff) "VȠ$To view this page you need to register&4ff# 9ff1W.f ffIkonos 29 f f, (" Ikonos 21 fQf'  GeneralY ffG#^$") DesignationYQffA#R0Launch datemid 1998t'fwfM#jN"N ,㹌לCountry of originUnited StatescffG#^8"H̀MissionRemote sensingTwf.fA#R&"Perigee/ApogeeQffA#R InclinationL .ffA#RPeriod\f'fG#^*" &Launch vehicleQfxfA#R Launch siteG#'ff$ FWill be a duplicate of Ikonos 11xff1WfDfjfT+fDf) "VȠ$To view this page you need to register&fjf# 6Dff1{.ff,gImage6 jff, (" ImageZ7f0f# nImager for Magnetopause-to-Aurora Global Exploration1 faf'  GeneralY0ffG#^$") Designation`affA#R>Launch dateplanned in 2000t'ffM#jN"N ,㹌לCountry of originUnited States`ffG#^2"H̀MissionScientific:TfBfA#R&"Perigee/Apogee\ffA#R6Inclinationpolar orbitL BffA#RPeriodifSfM#j8" &p㉂Launch vehicleDelta[ffA#R4Launch siteVandenberg&Sff# <ff' *O External resourcesFfVf' >http://image.gsfc.nasa.gov/8ff' "(OTechnical data8Vff' " SpecificationsZf fA#R2&Prime contractorNASAN fnfA#RPlatformT ffA#R&"Mass at launchSnffA#R$ Mass in orbitOfdfA#RDimensionQffA#R Solar arraySdffA#R$ StabilizationN fVfA#RDC power\ffA#R6$Design lifetime2 yearsnJVf,g$ Will have the Far Ultraviolet Spectrograf,gjfphic Image instrument (Fuv-Si)1f]g1W]gggT+,gg) "VȠ$To view this page you need to register&]gg# ?gg1. g]g#gProgram: IMEWSGg]g2 4,"  Program: IMEWSg#g) ; Integrated Multipurpose Early Warning SatelliteAmerican military program designed to warn on rocket launch or warhead fall. Equipped with IR detectors.8]g[g1D s[gggInjun 3@#gg2 4"  Injun 31 [gg'  Generalg g3gG#^@") Designation00504 / 62067B\ggA#R6Launch date13 Dec 1962t'3ggM#jN"N ,㹌לCountry of originUnited StatesagdgG#^4"H̀MissionScientific: _ggA#R<"Perigee/Apogee240/2406 kmVdggA#R*Inclination70.3UgngA#R(Period112.1 minp#ggM#jF" &#*≂Launch vehicleThor Agena D[ng9gA#R4Launch siteVandenberg&g_g# 59gg'  End of lifeV_ggA#R*Decay25 Aug 1968&gg# <gLg' *O External resourcesb;gg' vhttp://uss-enterprise.bu.edu/BUSPACE/INJUN3/injun3.htmlBLgg1tgBggProgram: InmarsatRgBg8 @6E" Program: InmarsatXg gC T+ (I}q󉂂(I}CIxINternational MARitime SATelliteInmarsat was created by the International Maritim Organization (dependent of the United Nations) on 16 Jul 1979. It is based in London and started working on 1 Feb 1982. Inmarsat must provide links between maritime mobiles and ground networks using geostationary satellites. The services are telephone, telex, fax and an access to the emergency system Sarsat/Cospas.Inmarsat's structure is close to Intelsat's one. It isn't dominated by the United States which enabled USSR to join in. Bg g9 @ F^nCIxThe 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. gg' wInmarsat is also working on aeronautical links and a project of personnal communication medium. Inmarsat might develop low orbit satellites on polar orbits to cover Northern and Southern regions.Once the 3rd generation is fully deployed the 2nd generation satellites should be moved by 40 off their current position to allow frequency reuse. This would let Inmarsat offer new, long term services. Slots at 110E and 98W should be used.1 gg1;gg ggl =㐮):jGjGjGjG)rG*rG+rG,rG-rGProgram: InmarsatInmarsat 2F1Inmarsat 2F2Inmarsat 2F3Inmarsat 2F4Inmarsat 3F1Inmarsat 3F2Inmarsat 3F3Inmarsat 3F4Inmarsat 3F51g @g1 @g{Fgg @ggAgM@g# <Inmarsat 2's specificationsq0 @g@gA#R`&Prime contractorBritish Aerospace (now MMS)[M@gAgA#R4PlatformEurostar 1000=@gAgN#lz*"2!p㉂Mass at launch1310 kg with Ariane1385 kg with Delta^AgBgA#R: Mass in orbitBOL: 824 kgXAgZBgA#R.Payload mass132 kg`BgBgA#R>Dimension1.6 x 1.5 x 2.6 m]ZBgCgA#R8Solar array15.23 m spanYBgpCgA#R0 Stabilization3 axist3CgCgA#RfDC powerEOL: equinox: 1156 W, solstice: 1040 WXpCglIg Jg$ |This capacity is used for communications with the mobiles.1IgQJg1QJgMgG$ JgJg# HInmarsat 2's C-band (6.4/3.6 GHz)XQJgJgA#R.0(Main transponders1ZJgJKgA#R20,Backup transponders1VJgKgA#R*0Power10 W (TWTA)UJKgKgA#R(0Bandwidth18 MHzTKgILgA#R&0CoverageglobalTKgLgA#R&0EIRP max24 dBWRILgLgA#R"0 G/T14.0 dB/KRLgAMgA#R"0PolarizationeALgMg$ This capacity is used for communications with earth stations.1AMgMg1MgfgAMgNg# <Inmarsat 3's specifications>MgNgA#R|&Prime contractorLockheed Martin (formerly GE Astro Space)UNgNgA#R(PlatformGE 4000`NgLOgA#R>"Mass at launch1850-2000 kgXNgOgA#R.Payload mass208 kg`LOggA#R>Dimension2.1 x 1.8 x 1.7OggMg mWOgggA#R,Solar array16.7 mYggA#R0 Stabilization3 axisTgggA#R&DC power2300 Wt3ggA#Rf Payload powersunlight: 2138 W, eclipse: 1725 W]ggA#R8$Design lifetime13 years]gfg$ Equipped with Matra Marconi Space communications payload and a Star 37 solid apogee motor1gg1Ug2gVgG$fgނg# HInmarsat 3's L-band (1.6/1.5 GHz)Wg5gA#R,(Main transpondersYނggA#R0,Backup transpondersO5g݃gA#RPower20 Wn-gKgA#RZBandwidthforward: 29 MHz, return: 39 MHzR݃ggC#V,Coverage & EIRP maxNavigation beam: global5 spots: 47.4 dBWGlobal: 40.5 dBWRKg2gA#R"Polarization$gVg" 12gg1Ugg:gG$Vg΅g# HInmarsat 3's C-band (6.4/3.6 GHz)Wg%gA#R,(Main transpondersY΅g~gA#R0,Backup transpondersO%g͆gA#RPower15 WU~g"gA#R(Bandwidth39 MHzT͆gvgA#R&CoverageGlobalN "gćgA#REIRP maxRvggA#R"Polarization$ćg:g" = gwg1uiwgĈggInmarsat 2F1M:gĈg8 @,E" Inmarsat 2F15wgg# $Also called IOR1 Ĉg*g'  Generalg ggG#^@") Designation20918 / 90093A\*ggA#R6Launch date30 Oct 1990t'gagM#jN"N ,<Country of originInternationalo"gЊgM#jD"H̀‰MissionTelecommunicationsb!ag2gA#RB,Geostationary orbitsee belowp#ЊggM#jF" &p㉂Launch vehicleDelta 2 #200&2gȋg# : gg- */ۀ Locationȋggm#:   " BeginEndPosition%ggj#J$<>L: 30 Oct 1991> Jan 199463E)ggj#R,.Jun 1994Apr 199664.5E, inclined g8gj#@Nov 1996178E, inclined<gtg$ 0Tel: 873, Telex: 58388gg' "(Technical data\%tgg7 >J'ł'łSpecificationsL-bandC-band= gEg1Egg`gInmarsat 2F2Mgg8 @,E" Inmarsat 2F27Egɏg# (Also called AOR-E1 g g'  Generalɏg ggg ɏgsgG#^@") Designation21149 / 91018A[ ggA#R4Launch date8 Mar 1991t'sgBgM#jN"N ,<Country of originInternationalo"ggM#jD"H̀‰MissionTelecommunicationsb!BggA#RB,Geostationary orbitsee belowp#ggM#jF" &p㉂Launch vehicleDelta 2 #203<gg$ 0Tel: 871, Telex: 581: gg- */ۀ Locationggm#:   " BeginEndPosition.ggj#\"68L: 8 Mar 1991Sep 199615.5W, inclined!ggj#BJan 199755.5W, inclined&gg# 8gg' "(Technical data\%g`g7 >J'ł'łSpecificationsL-bandC-band= gg1iQgggInmarsat 2F3M`gg8 @,E" Inmarsat 2F35gg# $Also called POR1 gPg'  Generalg ggG#^@") Designation21814 / 91084B\PggA#R6Launch date16 Dec 1991t'ggM#jN"N ,<Country of originInternationalo"ggM#jD"H̀‰MissionTelecommunicationsb!gXgA#RB,Geostationary orbitsee belown!ggM#jB" &dD+Launch vehicleAriane V48<Xgg$ 0Tel: 872, Telex: 582: gMar 199765E, inclined&^g g# 8gEg' "(Technical data\% gg7 >J'ł'łSpecificationsL-bandC-band= Egg1g+ghInmarsat 2F4Mg+g8 @,E" Inmarsat 2F47gbg# (Also called AOR-W1 +gg'  Generalg bggG#^@") Designation21940 / 92021B\gVgA#R6Launch date15 Apr 1992t'ggM#jN"N ,<Country of originInternationalo"Vg9gM#jD"H̀‰MissionTelecommunicationsb!ggA#RB,Geostationary orbitsee belown!9g gM#jB" &D+Launch vehicleAriane V50&g/g# : gig- */ۀ Location/g hm#:   " BeginEndPositionig hg'ighj#N$@BL: 15 Apr 1992end of tests32W+ h2hj#V 46end of testsJul 199754W, inclinedhhj#>Oct 199717W, inclined<2hh$ 0Tel: 874, Telex: 5848h/h' "(Technical data\%hh7 >J'ł'łSpecificationsL-bandC-band= /hh1QhhhInmarsat 3F1Mhh8 @,E" Inmarsat 3F11 hFh'  Generalg hhG#^@") Designation23839 / 96020A[FhhA#R4Launch date3 Apr 1996t'h|hM#jN"N ,<Country of originInternationalo"hhM#jD"H̀‰MissionTelecommunicationse|hPhG#^<"/ۀ0Geostationary orbit64Eu(hhM#jP" &yjLaunch vehicleAtlas Centaur #996Phh$ $Tested at 27E8h3h' "(Technical data\%hh7 >JQ#0.ł.łSpecificationsL-bandC-band= 3hh1)hh hInmarsat 3F2Mhh8 @,E" Inmarsat 3F21 hJh'  Generalg hhG#^@") Designation24307 / 96053A[Jh hA#R4Launch date6 Sep 1996t'hhM#jN"N ,<Country of originInternationalo" hhM#jD"H̀‰MissionTelecommunicationsehT hG#^<"/ۀ0Geostationary orbit16Wo"h hM#jD" &㉓gLaunch vehicleProton #243D T h h$ @Was said to cost $80 million8 h? h' "(Technical data\% h h7 >JQ#0.ł.łSpecificationsL-bandC-band= ? h h1g h% hhInmarsat 3F3M h% h8 @,E" Inmarsat 3F31 hV h'  Generalg % h hG#^@") Designation24674 / 96070A\V h hA#R6Launch date18 Dec 1996t' h hM#jN"N ,<Country of originInternationalo" h hM#jD"H̀‰MissionTelecommunications^ hZ hA#R:,Geostationary orbit178Wq$ h hM#jH" &yjLaunch vehicleAtlas 2A #104G#Z hh$ FWent operational on 25 Jan 19978 hJh' "(Technical data\%hh7 >JQ#0.ł.łSpecificationsL-bandC-band= Jhh1))ǁh0h2FhInmarsat 3F4Mh0h8 @,E" Inmarsat 3F41 hah'  Generalg 0hhG#^@") Designation24819 / 97027A[ah/@hA#R4h/@hhLaunch date3 Jun 1997t'h@hM#jN"N ,<Country of originInternationalo"/@hAhM#jD"H̀‰MissionTelecommunicationse@hwAhG#^<"/ۀ0Geostationary orbit54Wn!AhAhM#jB" &:E+Launch vehicleAriane V97G#wAh,Bh$ FEntered service on 26 July 19978AhdBh' "(Technical dataD,BhBh0 0(.ł.łL-bandC-band8dBhBh' " Specificationse$BhEChA#RH&Prime contractorLockheed MartinN BhChA#RPlatform[EChChA#R4"Mass at launch2000 kgSChADhA#R$ Mass in orbit`ChDhA#R>Dimension3.2 x 2.3 x 2.1 m\ADhDhA#R6Solar array20.7 m spanYDhVEhA#R0 Stabilization3-axisYDhEhA#R0DC powerBOL: 3726 W]VEh FhA#R8$Design lifetime13 years&Eh2Fh# = FhoFh1goFhFhJhInmarsat 3F5M2FhFh8 @,E" Inmarsat 3F51 oFhFh'  Generalg FhTGhG#^@") Designation25153 / 98006B[FhGhA#R4Launch date4 Feb 1998t'TGh#HhM#jN"N ,<Country of originInternationalo"GhHhM#jD"H̀‰MissionTelecommunicationsg #HhHhG#^@"/ۀ0Geostationary orbit24.5Eo"HhhIhM#jD" &|g&\Launch vehicleAriane V105&HhIh# 8hIhIh' "(Technical dataIhJh@ NQ#0.ł.łSSpecificationsL-bandC-bandHas onboard the first payload of the GNSS 1 system, to enhance the GPS navigation system.1IhJh1WJh Kh3KhT+Jh Kh) "VȠ$To view this page you need to register&Jh3Kh# ? KhrKh1rKhKhNhProgram: InsatO3KhKh8 @0 h{h# 6Insat 1's specificationsd#=h߀hA#RF0&Prime contractorFord AerospaceS{h2hA#R$0PlatformINSAT[߀hhA#R40"Mass at launch1152 kgY2hhA#R00 Mass in orbit650 kgc"hIhA#RD0Dimension2.18 x 1.42 x 1.55 mj)hhA#RR0Solar arrayasymmetric panel, 11.5 mYIh hA#R00 Stabilization3 axisTh`hA#R&0DC power1185 W\ hhA#R60$Design lifetime7 years$`hh" 1hh1UhhɆhD!hUh# BInsat 1's S-band (2.6/5.9 GHz)XhhA#R.0(Main transponders2ZUhhA#R20,Backup transponders1Vh]hA#R*0Power50 W (TWTA)OhhA#R0BandwidthS]hhA#R$0CoverageIndiaThShA#R&0EIRP max42 dBWRhhA#R"0Polarization$ShɆh" 1hh1Uhhh6Ɇh0h# &Insat 1's C-bandYhhA#R00(Main transponders12Y0hhA#R00,Backup transpondersWh9hA#R,0Power4.5 W (TWTA)UhhA#R(0Bandwidth36 MHzS9hhA#R$0CoverageIndiaTh5hA#R&0EIRP max32 dBWRhhA#R"0Polarization$5hh" 1h܉h1U܉hh؋h7hh# (Insat 1's payloadX+܉hkh- *V  VHRR (Very High Resolution Radiometer)x6hhB#Tl4Wavebands0.55-0.75 m (visible)10.5-12.5 m (IR)k)khNhB#TR4Resolutionvisible: 2.75 kmIR: 11 kmf%hhA#RJ42Image repeat frequency30 minutes$Nh؋h" 1h h1/ hh>؋hGh# 6Insat 2's specifications_ hhA#R<0&Prime contractorISRO/ISACTGhhA#R&0PlatformINSAT2[hUhA#R40"Mass at launch1906 kgZhhA#R20 Mass in orbit1162 kgb!UhhA#RB0Dimension1.93 x 1.64 x 1.7 mb!hshA#RB0Solar arrayasymmetric pannelYh̎hA#R00 Stabilization3 axisTsh hA#R&0DC power1400 W\̎h|hA#R60$Design lifetime7 yearsa hh* $qAlso equipped with 2 single channels for data and search & rescue(Sarsat): 402.75 & 40|hh؋h6 MHz1|hDh1UDhhhD!hh# BInsat 2's S-band (2.6/5.9 GHz)XDhhA#R.0(Main transponders2Zh:hA#R20,Backup transponders1VhhA#R*0Power50 W (TWTA)U:hhA#R(0Bandwidth36 MHzSh8hA#R$0CoverageIndiaThhA#R&0EIRP max42 dBWV8hhA#R*0PolarizationLHCP$hh" 1h7h1U7hhh6hmh# &Insat 2's C-bandY7hhA#R00(Main transponders18YmhhA#R00,Backup transpondersPhohA#R0Power4.5 WUhhA#R(0Bandwidth36 MHzSohhA#R$0CoverageIndiaThkhA#R&0EIRP max32 dBW\hhA#R60PolarizationH/V linear$khh" 1hh1Uhhh7hSh# (Insat 2's payloadX+hh- *V  VHRR (Very High Resolution Radiometer)y7Sh$hB#Tn4Wave bands0.55-0.75 m (visible)10.5-12.5 m (IR)g%hhB#TJ4Resolutionvisible: 2 kmIR: 8 kmf%$hhA#RJ42Image repeat frequency30 minutes$hh" 9hNh1̓NhhdhInsat 1AIhh8 @$"N ,&‰Country of originIndia4h~hS#vh"H̀(‰DVMissionTelecommunications and meteorology]hhA#R8,Geostationary orbit74Es&~hNhM#jL" &p㉂Launch vehicleThor Delta #161R.hh$ \Insurance paid $64 million for the failure5Nhh'  End of life^h3hA#R:"Out of service4 Sep 1982f%hhA#RJCauseSolar panel didn't open out&3hh# 8hh' "(Technical datam/hdh> L^F LUSpecificationsS-bandC-bandPayload9hh1 hhiInsat 1BIdhh8 @$"N ,&‰Country of originIndia4hhS#vh"H̀(‰DVMissionTelecommunications and meteorology]Fh6iA#R8h6idh,Geostationary orbit74EjhiM#j:" &㬜Launch vehicleSTS 086iVi% #The deployment of one antenna was difficult and was not succeeded until mid Sep 1983. Went operational in Nov 1983. Became spare in Jul 1990.5ii'  End of life\ViiA#R6"Out of serviceAug 1993&i i# 8iEi' "(Technical datam/ ii> L^F LUSpecificationsS-bandC-bandPayload9Eii1]̓$i4i`iInsat 1CIi4i8 @$"N ,&‰Country of originIndia4(iiS#vh"H̀(‰DVMissionTelecommunications and meteorology_iziA#R<,Geostationary orbit93.5En!iiM#jB" & D+Launch vehicleAriane V24zii& 3It had difficulties to deloy its solar array. After a power failure, only half its payload was functional.Insurance paid $72 million for the failure5ii'  End of life_i;iA#R<"Out of service22 Nov 1989ZiiA#R2CauseEarth lock lost&;ii# 8ii' "(Technical datam/i`i> L^F LUSpecificationsS-bandC-bandPayload9ii1ZiiZ iInsat 1DI`ii8 @$"N ,&‰Country of originIndia4 i iS#vh"H̀(‰DVMissionTelecommunications and meteorologyeB i. iG#^<"/ۀ0Geostationary orbit83Es& i iM#jL" &p㉂Launch vehicleThor Delta #196. i i% Was damaged when a crane hook (34 kg) fell on it at the launch site. Damages were worth $10 million reparation. While being repared it suffered further damages (October 1989 California earthquake).8 i i' "(Technical dataM iZ iF \uF LUC-band EIRP coverage (dBW)SpecificationsS-bandC-bandPayload1 i i1 i iV Z i i6 "N ,&‰Country of originIndia4ViU@iS#vh"H̀(iU@i i‰DVMissionTelecommunications and meteorologyei@iG#^<"/ۀ0Geostationary orbit74En!U@i(AiM#jB" &D+Launch vehicleAriane V51&@iNAi# 8(AiAi' "(Technical dataMNAiBiF \w ZGUEF&XC-band EIRP coverage (dBW)SpecificationsS-bandC-bandPayload1AiJBi1JBiBi[%BiBi6 "N ,&‰Country of originIndia4DiEiS#vh"H̀(‰DVMissionTelecommunications and meteorologyg DiuEiG#^@"/ۀ0Geostationary orbit93.5En!EiEiM#jB" &D+Launch vehicleAriane V58&uEi Fi# 8EiAFi' "(Technical dataM FiFiF \w ZGUEF&XC-band EIRP coverage (dBW)SpecificationsS-bandC-bandPayload9AFi Gi1 ƀ' GiVGi9iInsat 2CIFiVGi8 @$"N ,&‰Country of originIndiao"IHi$IiM#jD"H̀‰MissionTelecommunicationsg HiIiG#^@"/ۀ0Geostationary orbit93.5En!$IiIiM#jB" & E+Launch vehicleAriane V81IiJi- (7DVUnlike other satellites of the program, Insat 2C is totally devoted to telecommunications and doesn't have any meteorology payload.Tested at 92.5E8IiJi' "(OTechnical data9Ji2Ki' $ EIRP maps (dBW)X(JiKi0 0PU؀U؉C-band, standardC-band, extended82KiKi' " Specifications_Ki!LiA#R<0&Prime contractorISRO/ISACTKiuLiA#R&0PlatformINSAT2[!LiLiA#R40"Mass at launch2020 kgSuLi#MiA#R$0 Mass in orbitb!LiMiA#RB0Dimension1.93 x 1.64 x 1.7 mb!#MiMiA#RB0Solar arrayasymmetric pannelYMi@NiA#R00 Stabilization3 axisYMiNiA#R00DC powerBOL: 1600 W]@NiNiA#R80$Design lifetime10 years#Ni%i' The internal LAM (Liquid Apogee Motor) was built by ISRO with its Indian industrial partners.The satellite will have a meteorology payload made of a VHRR with an additional water vapour channel and a 1-km resolution, 3-visiNi%iFible-channel CCD camera.>Nici' . S-band (2.6/5.9 GHz)X%iiA#R.0(Main transponders3YciiA#R00,Backup transpondersVijiA#R*0Power50 W (TWTA)UiiA#R(0Bandwidth36 MHzSjiiA#R$0CoverageIndiaTifiA#R&0EIRP max42 dBWViiA#R*0PolarizationLHCPF"fii$ DAimed at mobile communications0 i2i'  C-bando.iiA#R\(Main transponders17 + 6 (extended C-band)Y2iiA#R0,Backup transpondersPiJiA#RPower4.5 WUiiA#R(Bandwidth36 MHzx7JiiA#RnCoveragebetween the Middle East and southeast AsiaAiiN#l*U؉U؉EIRP maxstandard: 32 dBW2 extended transponders: 34 dBW\iiA#R6PolarizationH/V linear@iBi$ 8Aimed at TV broadcasting1 isi'  Ku-bandXBiˆiA#R.(Main transponders3Ysi$iA#R0,Backup transpondersK ˆioiA#RPowerO$iiA#RBandwidthN oi iA#RCoverageN iZiA#REIRP maxR iiA#R"PolarizationiZi9i$ Aimed at business communications among India's frou major cities (Delhi, Bombay, Calcutta and Madras)1iji1jiʉi`*9iʉi6 "N ,&‰Country of originIndiao"ЋiiM#jD"H̀‰MissionTelecommunications]i&i' . S-band (2.6/5.9 GHz)Xi~iA#R.0(Main transponders1Y&iiA#R00,Backup transpondersK ~i"iA#R0PowerOiqiA#R0BandwidthS"iiA#R$0CoverageIndiaN qiiA#R0EIRP maxRidiA#R"0Polarization&ii# 0 dii'  C-bandYiiA#R0(Main transponders18YiliA#R0,Backup transpondersK iiA#RPowerOliiA#RBandwidthx7i~iA#RnCoveragebetween the Middle East and southeast AsiaN iiA#REIRP maxR~iiA#R"Polarization&iDi# 1 iui'  Ku-bandXDiiA#R.(Main transponders3Yui&iA#R0,Backup transpondersK iqiA#RPowerO&iiA#RBandwidthN qiiA#RCoverageN i\iA#REIRP maxRiiA#R"Polarization&\ii# 9i i1~\X iVijInsat 2EIiVi8 @$"N ,&‰Country of originIndia4Ei8iS#vh"H̀(‰DVMissionTelecommunications and meteorology_iiA#R<,Geostationary orbit83.5Ej8iiM#j:" &2!Launch vehicleArianeQiRiA#R Launch site[iiA#R4"Mass at launch2500 kg$Rij% Intelsat will pay India's Department of Spacijie $100 million over 10 years, beginning in January 1998, for the use of 11 transponders. A special capability will be built into the satellite for use by Intelsat in addition to the INSAT system requirement.8ij' "(Technical dataEjZj) "8V#3EIRP map coverage (dBW)0 jj'  C-bandWZjjA#R,(Main transpondersYj:jA#R0,Backup transpondersK jjA#RPowerO:jjA#RBandwidthCjZjC#V,Coverage & EIRP maxQuasi globalWide beam: 36 dBWZone: 36 dBWM jjA#RG/T maxRZjjA#R"Polarization&jj# 1jPj1WPjjjT+jj) "VȠ$To view this page you need to register&Pjj# 1jj1jQjV jQj6 J)00SpecificationsS-bandC-band9j j1v ۂ j j)CjInsat 3AIV j j8 @$"N ,&‰Country of originIndia4 j jS#vh"H̀(‰DVMissionTelecommunications and meteorologyY' j jA#R0,Geostationary orbit\ jc jG#^*" &Launch vehicleQ j jA#R Launch site&c j j# 8 j j' "(OTechnical data8 jJ j' " SpecificationsV j jA#R*&Prime contractorUJ j jA#R(PlatformINSAT 3T jIjA#R&"Mass at launchS jjA#R$ Mass in orbitOIjjA#RDimensionQj<jA#R Solar arraySjjA#R$ StabilizationN <jjA#RDC powerUj>@jA#R(j>@jV j$Design lifetime&jd@j# 0 >@j@j'  C-bandWd@j@jA#R,(Main transpondersY@jDAjA#R0,Backup transpondersK @jAjA#RPowerODAjAjA#RBandwidthCAjdBjC#V,Coverage & EIRP maxQuasi globalWide beam: 36 dBWZone: 36 dBWM AjBjA#RG/T maxRdBjCjA#R"Polarization&Bj)Cj# 1CjZCj1WZCjCjCjT+)CjCj) "VȠ$To view this page you need to register&ZCjCj# 8Cj Dj1RpU DjLDjmHjIntasat@CjLDj2 4"  Intasat1 Dj}Dj'  Generalg LDjDjG#^@") Designation07531 / 74089C\}Dj@EjA#R6Launch date15 Nov 1974lDjEjM#j>"N ,qn͉Country of originSpainy,@Ej%FjM#jX"H̀?vMissionScientific: ionosphere study`EjFjA#R>"Perigee/Apogee1441/1455 kmW%FjFjA#R,Inclination101.9UFj1GjA#R(Period114.8 mins&FjGjM#jL" &p㉂Launch vehicleThor Delta #104[1GjGjA#R4"Mass at launch24.5 kgnJGjmHj$ Studies the ionosphere's density and its movement throughout the year.9GjHj1jHjHjKjIntegral9 mHjHj, (" Integral HjIj& European satellite to be launched in Apr 2001 by Proton. The launch is provided against 25% of the observation time to Russian scientists.Integral is a 4-ton gamma-astronomy satellite. It will be placed on an elliptical orbit.<Hj(Jj' * External resourcesoHIjJj' http://astro.estec.esa.nl/SA-general/Projects/Integral/integral.html8(JjJj' "(OTechnical data&JjJj# 5Jj*Kj' O InstrumentssJjKj' Spectrometer SpiImager IbisX-Ray Monitor Jem-XOptical Monitoring Camera OmcIntegral Science Data Centre Isdc1*KjKj1WKjILjoLjT+KjILj) "VȠ$To view this page you need to register&KjoLj# BILjLj1}UG LjMjTjProgram: IntelsatRoLjMj8 @6%D" Program: IntelsatLjOj6 : MiP/:INTernational TELecommunication SATelliteIntelsat was created by 11 states (leaded by the United States) on 24 Aug 1964. The Comsat (controled by the US federal government) was created to manage the system because the US had 61% of the voting part. In 1979 the structure changed so that each member can't possess more that 40% of the voting parts.Since 1966, all the continents are covered by Intelsat and nowadays numerous services are offered. Intelsat counts 142 members.*MjTj+ $The commercial arm of Intelsat, temporarily called New Skies Satellites (http://www.newskies.com/), was created in April 1998. This company is based in the Netherlands. Initially OjTjoLj6 satellites should be transfered to the new entity (703, 803, 806, K, 513 and KTV plus rights to Ka-band at 95E & 40.5W). Those satellites are worth $700 million. Intelsat should keep 10% of the company with non-voting shares. The maximum shareholder ownership was set at 17%. The ownership will be diluted through an IPO.1Ojj1Ujjj?Tjāj) ",CIxProgram: Intelsatj[j}#ʀ4(rĀ$(,0Intelsat 101Hāj>j#"Ā""ĉ(DĀ(hĀIntelsat 201Intelsat 202Intelsat 203Intelsat 204X[j=j#"Ā""ĉ(DĀ(hĀ(ĀIntelsat 301Intelsat 302Intelsat 303Intelsat 304Intelsat 3056>jj#l"Ā"ĉ"BĉdhIntelsat 306Intelsat 307Intelsat 308X=jj#"Ā""ĉ(DĀ(h Ā(!ĀIntelsat 401Intelsat 402Intelsat 403Intelsat 404Intelsat 405:jʆj#t("Ā($#Ā(H$ĀlpIntelsat 406Intelsat 407Intelsat 408]j·j#" "$ (H (n ( Intelsat 4A01Intelsat 4A02Intelsat 4A03Intelsat 4A04Intelsat 4A05ʆjbjz#Ā4" $(,0Intelsat 4A06X·jaj#"VĀ""Wĉ(DXĀ(hYĀ(ZĀIntelsat 501Intelsat 502Intelsat 503Intelsat 504Intelsat 505VbjXj#"[Ā"\ĉ"B]ĉ(d^Ā(ĀIntelsat 506Intelsat 507Intelsat 508Intelsat 509Intelsat 510XajWj#(Ā($Ā"HĀ"jĉ(ĀIntelsat 511Intelsat 512Intelsat 513Intelsat 514Intelsat 515XXjVj#" Ā"" ĉ(D Ā(h Ā( ĀIntelsat 601Intelsat 602Intelsat 603Intelsat 604Intelsat 605)Wj j#R(ƀ" 㿩ĀBHNIntelsat KIntelsat KTVRVjj#"Ā"ĉBĉbĉ"ĉIntelsat 701Intelsat 702Intelsat 703Intelsat 704Intelsat 705J jݎj#(Ā($Ā(HĀ(lĀIntelsat 706Intelsat 707Intelsat 708Intelsat 709Zj j#*(Ā($Ā(HĀ(lĀ(ĀIntelsat 801Intelsat 802Intelsat 803Intelsat 804Intelsat 805ݎj jTjݎjj#Ѐ6(Ā$(.2Intelsat 806G jj#(:#Ā($;#Ā"H<#Āj=#ĉIntelsat 901Intelsat 902Intelsat 903Intelsat 904$jj" 1jj1j|jAjj# <Intelsat 2's specificationsZjvjA#R20"Mass at launch162 kgXjjA#R.0 Mass in orbit86 kgL vjjA#R0LengthQjkjA#R 0Width1.42 mRjjA#R"0Height0.67 mb!kjjA#RB0 StabilizationSpin stabilisedb jjB#T@0DC powerBOL: 83 WEOL: 75 W\jjA#R60$Design lifetime3 years{j|j$ The antenna platform didn't counter rotate thus most of the power didn't reach the Earth. 360 omnidirectional antenna!1jj1kjj9|jj# ,Intelsat 2's C-bandXj>jA#R.0(Main transponders1OjjA#R0Power18 WV>jjA#R*0Bandwidth125 MHzVj9jA#R*0EIRP max15.5 dBWp/jjA#R^0Capacity240 phone circuits or 1 TV channel>9jj$ 4Allows multiple access1jj1UjjAjAjYj# <Intelsat 3's specificationsZjjA#R20"Mass at launch293 kgYYj jA#R00 Mass in orbit151 kgL jXjA#R0LengthQ jjA#R 0Width1.41 mRXjjA#R"0Height2.02 mb!j]jA#RB0 Stabilizationspin stabilizedd"jjB#TD0DC powerBOL: 160 WEOL: 125 W\]jjA#R60$Design lifetime5 years$jAj" 1jrj1Urjojj9Ajj# ,Intelsat 3's C-bandXrjjA#R."(Main transponders2OjRjA#R"Power11 WVjjA#R*"Bandwidth225 MHzTRjjA#R&"EIRP max23 dBWs2jojA#Rd"Capacity1500 phone circuits and 2 TV channels$jj" 1ojj1UjkkAjj# <Intelsat 4's specifications[j`jA#R40"Mass at launch1415 kgYjjA#R00 Mass in orbit700 kgL `jjA#R0LengthQjVjA#R 0Width2.38 mRjjA#R"0Height5.28 mb!VjkA#RB0 Stabilizationspin stjkjabilizedd"jzkB#TD0DC powerBOL: 600 WEOL: 400 W\kkA#R60$Design lifetime7 years$zkk" 1k+k1U+kakk9kdk# ,Intelsat 4's C-bandY+kkA#R0"(Main transponders12N dk kA#R"Power6 WUk`kA#R("Bandwidth36 MHzK kkC#V"0Coverage andEIRP maxGlobal (4 beams): 22.5 dBW2 spot beams: 33.7 dBWs2`kakA#Rd"Capacity4000 phone circuits and 2 TV channels$kk" 1akk1UkkkBkk# >Intelsat 4A's specifications[kSkA#R40"Mass at launch1515 kgYkkA#R00 Mass in orbit793 kgL SkkA#R0LengthQkIkA#R 0Width2.38 mRkkA#R"0Height6.93 mk*IkkA#RT0 StabilisationSpin stabilized (60 rpm)d"kjkB#TD0DC powerBOL: 700 WEOL: 500 W\kkA#R60$Design lifetime7 years$jkk" 1kk1k k:kUk# .Intelsat 4A's C-bandYkkA#R0"(Main transponders20XUkkA#R."Power6.5 W or 8 W?Uk[kA#R("Bandwidth36 MHzXkkD#X"0Coverage andEIRP maxGlobal: 22 dBWHemispheric (2 beams): 26 dBWSpot beam: 29 dBWs2[kj kA#Rd"Capacity6000 phone circuits and 2 TV channelstk k$ First generation with separated hemispheric beams which allowed the reuse of same frequencies on the 2 antennas.1j k3 k1U3 k?kckA kt k# <Intelsat 5's specificationsd#3 k kA#RF0&Prime contractorFord AerospaceXt k0 kA#R.0PlatformIntelsat 5[ k kA#R40"Mass at launch1900 kgZ0 k kA#R20 Mass in orbit1040 kgD kj kA#R0Payload mass233.5 kg: transponders: 174.6 kg, antennas: 58.9 kgt3 k kA#Rf0Dimension1.66 x 2 x 1.77 m (with tower: 6.4 m)]j k; kA#R80Solar array15.58 m span? k kB#T~0DC powerBOL: 1800 WEOL: equinox: 1400 W, solstice: 1288 WZ; kkA#R20 Payload power753.8 WY kokA#R00 Stabilization3 axis\kkA#R60$Design lifetime7 yearst3ok?kA#Rf0Capacity12000 phone circuits and 2 TV channels$kck" 1?kk10kBk9ckk# ,Intelsat 5's L-bandXk1@kA#R.0k1@kck(Main transponders2Yk@kA#R00,Backup transpondersK 1@k@kA#R0PowerO@k$AkA#R0BandwidthN @krAkA#R0CoverageT$AkAkA#R&0EIRP max33 dBWRrAkBkA#R"0PolarizationmCAkBk* $㐮):Only on 505 to 509. Those transponders are leased to Inmarsat1BkBk1BkFk9BkBk# ,Intelsat 5's C-bandYBkHCkA#R00(Main transponders21YBkCkA#R00,Backup transpondersKHCk.DkB#T0PowerGlobal, hemispheric and zone beams: 8.5 W (TWTA)Spot beam: 4.5 W\CkDkA#R60Bandwidth36 and 72 MHzG.DkEkC#V00Coverage andEIRP maxGlobal: 23.5 dBWHemispheric and zone: 29 dBW^DkrEkA#R:0Polarizationcircular R/L`EkEkA#R>0Beacons3.9475 & 3.9525 GHzrEkFk% First generation with orthogonal polarizations. Together with the use of 2 separated hemispheric beams more frequency space could be saved.1EkFk1UFkIkJk:FkFk# .Intelsat 5's Ku-bandXFkIGkA#R.0(Main transponders6ZFkGkA#R20,Backup transponders4VIGkGkA#R*0Power10 W (TWTA)@Gk{HkB#T0Bandwidth2 transponders of 72 MHz2 transponders of 241 MHzZGkHkA#R20Coverage2 spot beamsl*{HkAIkB#TT0EIRP maxWest: 44.4 dBWEast: 41.1 dBWXHkIkA#R.0Polarizationlinear`AIkIkA#R>"Beacons11.198 & 11.452 GHz$IkJk" 1IkNJk1UNJkOkOkBJkJk# >Intelsat 5A's specificationsd#NJkJkA#RF&Prime contractorFord AerospaceXJkLKkA#R.PlatformIntelsat 5[JkKkA#R4"Mass at launch1900 kgZLKkLkA#R2 Mass in orbit1040 kgDKkLkA#RPayload mass262.7 kg: transponders: 187.2 kg, antennas: 58.9 kg`LkLkA#R>Dimension1.66 x 2 x 1.77 m]LkCMkA#R8Solar array15.58 m span?LkMkB#T~DC powerBOL: 1800 WEOL: equinox: 1427 W, solstice: 1351 WZCMkNkA#R2 Payload power875.3 WYMkwNkA#R0 Stabilization3 axis\NkNkA#R6$Design lifetime7 yearsYwNk,OkA#R0"Phone circuits15000[NkOkA#R4.Reserved TV channels2$,OkOk" 1OkOk1UOk1kUk:Ok"k# .Ok"kOkIntelsat 5A's C-bandYOk{kA#R00(Main transponders32["kրkA#R40,Backup transponders12L{kdkB#T0PowerGlobal, hemispheric and zone beams: 8.5 W (TWTA)Spot beams: 4.5 W\րkkA#R60Bandwidth36 and 72 MHzadkekD#X00Coverage andEIRP maxGlobal: 23.5 dBWHemispheric and zone beams: 29 dBWSpot beam: 32.5 dBW^kÂkA#R:0Polarizationcircular R/Ln-ek1kA#RZ0Beacons3.9475, 3.948, 3.952 & 3.9525 GHz$ÂkUk" 11kk1UkɆkk;Ukk# 0Intelsat 5A's Ku-bandXkkA#R.0(Main transponders6ZkskA#R20,Backup transponders4VkɄkA#R*0Power10 W (TWTA)@skKkB#T0Bandwidth2 transponders of 72 MHz2 transponders of 241 MHzZɄkkA#R20Coverage2 spot beamsl*KkkB#TT0EIRP maxWest: 44.4 dBWEast: 41.1 dBWXkikA#R.0Polarizationlinear`kɆkA#R>0Beacons11.198 & 11.452 GHz$ikk" 1Ɇkk1kkAk_k# <Intelsat 6's specifications\kkA#R6&Prime contractorHughes`_kkA#R>PlatformIntelsat 6 (HS389)\kwkA#R6"Mass at launch~4300 kgZkшkA#R2 Mass in orbit2560 kg?wkQkA#R~Payload mass660 kg: transponders: 332 kg, antennas: 330 kgTшkkA#R&Diameter3.63 mb!QkkA#RBHeight6.4 m (11.84 m stowed)?kkB#T~DC powerBOL: 2600 WEOL: equinox: 2204 W, solstice: 2083 WZkkA#R2 Payload power~1600 Wb!kDkA#RB StabilizationSpin stabilized]kkA#R8$Design lifetime13 yearsl+Dk kA#RV"Phone circuits24000 (120000 with DCME)[khkA#R4.Reserved TV channels3P, kk$ X2 telemetry and remote control antennas.1hkk1Uk3kWk9k"k# ,Intelsat 6's C-band[k}kA#R40(Main transponders6+32]"kڍkA#R80,Backup transponders2+10O}kkkB#T0Power(6+2) transponders of 16 W (TWTA)(32+10) transponders of 10 W (SSPA)\ڍkǎkA#R60Bandwidth36 and 72 MHzPkk[kD#X00Coverage andEIRP maxGlobal beam: 26.5 dBWHemispheric: 29 dBWZone: 31 dBW^ǎkkA#R:0Polarizationcircular R/Ln-[k3kA#RZ0Beacok3kkns3.9475, 3.948, 3.952 & 3.9525 GHz$kWk" 13kk1Ukkk:Wkk# .Intelsat 6's Ku-bandZkkA#R2"(Main transponders8+2\kxkA#R6",Backup transponders3+1MkkB#T"Power(8+3) transponders of 20 W (TWTA)(2+1) transponders of 40 W (TWTA)Uxk\kA#R("Bandwidth36 MHzv5kkA#Rj"0Coverage and EIRP maxWest & East spots: 44.7 dBWX\k*kA#R."Polarizationlinear`kkA#R>"Beacons11.198 & 11.452 GHz$*kk" 1kk1}k+kAk k# <Intelsat 7's specificationsi(kkA#RP"&Prime contractorSpace Systems/LoralN kkA#R"PlatformIntelsat 7 (based on Ford FS 1300 and Aerospatiale Spacebus 2000)[kskA#R4""Mass at launch3750 kgZkkA#R2" Mass in orbit1800 kgUsk"kA#R("Dry mass1500 kg>kkA#R|"Payload mass446 kg: transponders: 338kg, antennas: 108 kga "kkA#R@"Dimension2.45 x 2.2 x 2.7 m\k^kA#R6"Solar array21.8 m spant3kkA#Rf"DC powerEOL: equinox: 3968 W, solstice: 3650 WY^k+kA#R0" Payload power2580 WYkkA#R0" Stabilization3 axis`+kkA#R>"$Design lifetime10-15 yearsk*kOkA#RT""Phone circuits18000 (90000 with DCME)[kkA#R4".Reserved TV channels3]Ok+k$ Cross-strapping: uplink in C-band and downlink in Ku-band (701, 702, 703, 704, 705 & 709)1k\k1\kFk9+kk# ,Intelsat 7's C-bandY\kkA#R00(Main transponders26YkGkA#R00,Backup transponders\kkA#R60Power10, 16, 20 & 30 WYGk?kC#V0Bandwidth8 transponders of 36 MHz2 transponders of 41 MHz16 transponders of 72 MHzk%kF#ZA00Coverage andEIRP maxGlobal beam: 26/29 dBWHemispheric beam: 33 dBW (2x36 MHz & 8x72 MHz)Zone beam: 33 dBW (2x36 MHz & 8x72 MHz)Spot beam: 33.3/36.3 dBW^?kkA#R:0Polarizationcircular R/L%kFk% =Four 36 MHz and the two 41 MHz transponders are either in global or in spot configuration. The two 41 MHz transponders are 3 dBW stronger than the others.1kwk1wkl:Fkk# .Intelsat 7's Ku-bandYwk kA#R00(Main transponders10YkckA#R00,Backup transpondersy7 kkB#Tn0Power5 transponders of 35 W5 transponders of 50 W@ckjlB#T0kjlFkBandwidth6 transponders of 72 MHz4 transponders of 112 MHzoklD#X00Coverage and EIRP maxSpot 1: 45.4 dBWSpot 2: 44.5 dBWSpot 3: 46 dBW(the nominal power can be increased)XjlulA#R.0PolarizationlinearxRll& 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).The downlink can be switched to 10.95-11.20 GHz, 11.45-11.70 GHz, 11.70-11.95 GHz & 12.50-12.75 GHz1ull1Nl;lBl`l# >Intelsat 7A's specificationsi(llA#RP"&Prime contractorSpace Systems/LoralU`llA#R("PlatformFS 1300[lylA#R4""Mass at launch4500 kg?llA#R~"Payload mass525 kg: transponders: 412 kg, antennas: 113 kga ylZlA#R@"Dimension2.7 x 2.2 x 2.45 m\llA#R6"Solar array25.7 m spant3Zl*lA#Rf"DC powerEOL: equinox: 5326 W, solstice: 4884 WYllA#R0" Payload power3612 WY*llA#R0" Stabilization3 axis`l<lA#R>"$Design lifetime10-15 yearsl+llA#RV""Phone circuits22500 (112500 with DCME)[<llA#R4".Reserved TV channels38l;l$ ((706, 707 & 708)1lll1ll l:;ll# .Intelsat 7A's C-bandYlllA#R00(Main transponders26YlX lA#R00,Backup transpondersXl lA#R.0Power10, 20 & 30 WAX l3 lB#T0Bandwidth10 transponders of 36 MHz16 transponders of 72 MHz l# lF#ZU00Coverage andEIRP maxGlobal beam (36 MHz): 29 dBWHemispheric beam (8x72 MHz & 2x36 MHz): 33 dBWZone beam (8x72 MHz & 2x36 MHz): 33 dBWSpot beam (36 MHz): 36.1 dBW^3 l lA#R:0Polarizationcircular R/LoK# l l$ A total of 6 transponder are switched either to global or to spot beam.1 l! l1i! lYl; l\ l# 0Intelsat 7A's Ku-bandY! l lA#R00(Main transponders14Y\ l lA#R00,Backup transpondersy7 l lB#Tn0Power5 transponders of 49 W5 transponders of 73 W@ l lB#T0Bandwidth6 transponders of 72 MHz8 transponders of 112 MHzm llD#X00Coverage and EIRP maxSpot 1: 47 dBWSpot 2: 47 dBWSpot 3: 42.8 dBW(the nominal power can be increased)X llA#R.0PolarizationlinearG#lYl$ FFive transponders max per spot.1ll1=lClAYll# <Intelsat 8's specificationsq0lH@lA#R`"lH@lYl&Prime contractorLockheed Martin Astro SpaceUl@lA#R("PlatformGE 7000[H@l@lA#R4""Mass at launch3400 kgu4@lmAlA#Rh"Dimension2.52 x 2.19 x 3.44 m (10.8 m deployed)Y@lAlA#R0" Stabilization3 axisf$mAl,BlB#TH"DC powerBOL: 6400 WEOL: 4760 W]AlBlA#R8"$Design lifetime13 yearsl+,BlBlA#RV""Phone circuits22500 (112500 with DCME)[BlPClA#R4".Reserved TV channels3F"BlCl$ D4 satellites ordered (801-804)1PClCl1UClrHlHl9ClDl# ,Intelsat 8's C-bandYClYDlA#R00(Main transponders38YDlDlA#R00,Backup transpondersZYDlNElB#T0Power7-22 W (SSPA) for zone transponders27-38W (SSPA) for hemi & global transponders\DlElA#R60Bandwidth36 and 72 MHzsNElaFlD#X0&Coverage & EIRP (beam peak to outer edge)Global: 33.1-29.0 dBWHemispheric: 40.2-34.5 dBWZone: 42.8-34.5 dBWpElGlC#V0@G/T (beam peak to outer edge)Global: -7.9 - -12.0 dB/KHemispheric: -0.5 - -9.5 dB/KZone: +5.2 - -6.5 dB/Kr1aFlGlA#Rb0 SFD-89.0 - -67.0 dBW/m (< 2 dB adjustments)i(GlGlA#RP0PolarizationCircular Right and LeftAGlrHlB#T0FrequenciesUplink: 5.850-6.425 GHzDownlink: 3.625-4.200 GHZ$GlHl" 1rHlHl1Hl!Nl:HlIl# .Intelsat 8's Ku-bandi(HljIlA#RP0(Main transponders6 (5 max per beam)YIlIlA#R00,Backup transpondersVjIlJlA#R*0Power43 W (TWTA)]IlvJlA#R80Bandwidth72 and 112 MHzeJlKlC#V0&Coverage & EIRP (beam peak to outer edge), steerableSpot 1: 52.6-44.0 dBWSpot 2: 51.6-44.0 dBWTvJlKlB#T0@G/T (beam peak to outer edge)Spot 1: +11.1 - +2.0 dB/KSpot 2: +9.5 - +2.0 dB/Kr1Kl&LlA#Rb0 SFD-89.0 - -67.0 dBW/m (< 2 dB adjustments)z9KlLlA#Rr0Polarizationlinear H/V (in-orbit switching possible)&LlMlF#ZQ0FrequenciesUplink: 14.00-14.50 GHzDownlink: each transponder can be switched into 1 of the 3 bands:10.95-11.2 GHz11.7-11.95 GHz12.5-12.75 GHz & 11.45-11.70 GHznLl!Nl% Spot 1 is circular (same as spot 3 of Intelsat 7) and spot 2 is elliptical (same as spot 1 of Intelsat 7)1MlRNl1RNl%lB!NlNl# >Intelsat 8A's specificationsq0RNlOlA#R`"&Prime contractorLockheed Martin Astro SpaceUNlZOlA#R("PlatformGE 7000TOlOlA#R&""Mass at launchOZOl lA#R"DimensionOl l!NlYOlelA#R0" Stabilization3 axisN llA#R"DC power]ellA#R8"$Design lifetime13 yearsTldlA#R&""Phone circuitsZllA#R2".Reserved TV channelsgCdl%l$ 2 satellites ordered (805-806), will be specifically customized1lVl1WVllЂlT+%ll) "VȠ$To view this page you need to register&VlЂl# 1ll1Ulll:Ђl;l# .Intelsat 8A's C-bandYllA#R00(Main transponders28Y;llA#R00,Backup transpondersUlBlA#R(0Power60W (TWTA)f$llB#TH0Bandwidth20 x 36 MHz8 x 72 MHz~<Bl&lB#Tx0&Coverage & EIRP (beam peak to outer edge)39.7-37.5 dBWs2llA#Rd0@G/T (beam peak to outer edge)-5.9 - -8.0 dB/Kr1&l lA#Rb0 SFD-89.0 - -70.0 dBW/m (< 2 dB adjustments)i(ltlA#RP0PolarizationCircular Right and LeftA llB#T0FrequenciesUplink: 5.850-6.650 GHzDownlink: 3.400-4.200 GHZ$tll" 1lLl1WLllƇlT+ll) "VȠ$To view this page you need to register&LlƇl# 1ll1]l#l;Ƈl2l# 0Intelsat 8A's Ku-bandXllA#R.0(Main transponders3Y2llA#R00,Backup transpondersWl:lA#R,0Power134 W (TWTA)]llA#R80Bandwidth72 and 112 MHzf:l@lC#V0&Coverage & EIRP (beam peak to outer edge), 1 steerable spot805: 51.7-49.7 dBW806: 50.4-48.0 dBWMlϊlB#T0@G/T (beam peak to outer edge)805: +4.2 - +2.7 dB/K806: +2.6 - +1.0 dB/Ke@lvlB#T0 SFD805: -96.0 - -74.0 dBW/m (< 2 dB adjustments)806: -95.0 - -73.0 dBW/m (< 2 dB adjustments)v3ϊllC#Vf0Polarizationlinear805: V (down)806: H (down)avllC#V0FrequenciesUplink: 14.00-14.50 GHzDownlink 806: 11.7-11.95 GHzDownlink 805: 12.5-12.75 GHznl#l% Spot 1 is circular (same as spot 3 of Intelsat 7) and spot 2 is elliptical (same as spot 1 of Intelsat 7)1lTl1WTll΍lT+#ll) "VȠ$To view this page you need to register&Tl΍l# 1ll1llA΍l@l# <Intelsat 9's specificationsi(llA#RP&Prime contractorSpace Systems/LoralN @llA#RPlatformTlKlA#R&"Mass at launchSllA#R$ Mass in orbitOKl lA#RDimensionl l΍lQl]lA#R Solar arrayS llA#R$ StabilizationN ]llA#RDC power]l[lA#R8$Design lifetime15 yearsCll$ >Payload provided by Alcatel1[ll1Wl#lIlT+l#l) "VȠ$To view this page you need to register&lIl# 1#lzl1Uzlll9Ill# ,Intelsat 9's C-bandYzl lA#R0(Main transponders44YlelA#R0,Backup transpondersK llA#RPowerAel3lB#TBandwidth32 transponders of 72 MHz12 transponders of 36 MHzN llA#RCoverageM3llC#VEIRP maxhemispheric beam: 43 dBWzone beam: 44.8 dBWglobal beam: 34 dBW^lolA#R:Polarizationcircular L/RAllB#TFrequenciesuplink: 5.850-6.425 GHzdownlink: 3.625-4.200 GHz$oll" 1lGl1WGlllT+ll) "VȠ$To view this page you need to register&Gll# 1ll1UlSlwl:l,l# .Intelsat 9's Ku-bandYllA#R0(Main transponders16Y,llA#R0,Backup transpondersK l)lA#RPower?llB#T~Bandwidth8 transponders of 72 MHz8 transponders or 36 MHzN )llA#RCoveragel*ldlB#TTEIRP maxspot 1: 52 dBWspot 2: 52 dBW\llA#R6Polarizationlinear H/VQdlSlB#TFrequenciesuplink: 14.00-14.50 GHzdownlink: 10.95-11.20 and 11.45-11.70 GHz$lwl" 1Sll1Wll"lT+wll) "VȠ$To view this page you need to register&l"l# 1lSl1zSllI""ll' Dpage intentionally left blank= Sll1 l&lmIntelsat 101Ml&l8 @,%D" Intelsat 101Dljl) "6 Also called Early Bird1 &ll'  Generalg jllG#^@") Designation01317 / 65028A[l]lA#R4Launch date6 Apr 1965t'llM#jN"N ,<Country of originInternationalo"]l@lM#jD"H̀‰MissionTelecommunicationso.llA#R\,Geostationary orbit35752/35823 km, 27.5Wr%@l!lM#jJ" &p㉂Launch vehicleThor Delta #30&lGl# 5!l|l'  End of life\GllA#R6"Out of serviceMay 1970&|l m# l ml8lDm' "(OTechnical data8 m|m' " Specifications\DmmA#R6i&Prime contractorHughesY|m1mA#R0i"Mass at launch68 kgZmmA#R2i Mass in orbit38.5 kgL 1mmA#RiLengthQm(mA#R iWidth0.72 mRmzmA#R"iHeight0.59 ml+(mmA#RVi Stabilizationspin stabilized (120 rpm)b zmHmB#T@iDC powerBOL: 45 WEOL: 33 W]mmA#R8i$Design lifetime1.5 yearHmMm% The antenna platform didn't counter rotate thus most of the power didn't reach the Earth. The antenna was 360 omnidirectional!0 m}m'  C-bandXMmmA#R.i(Main transponders2N }m#mA#RiPower6 WUmxmA#R(iBandwidth25 MHzV#mmA#R*iEIRP max11.5 dBWp/xm>mA#R^iCapacity240 phone circuits or 1 TV channelmm% aDidn't allow multiple access: the European stations: Pleumeur-Bodou (France), Goonhilly Downs (UK), Raisting (Germany) and Fucino (Italy) used to operated 1 week per month!= >mPm1ePmmP mIntelsat 201Mmm8 @,%D" Intelsat 2011 Pmm'  Generalg m5mG#^@") Designation02514 / 66096A\mmA#R6Launch date26 Oct 1966t'5m mM#jN"N ,<Country of originInternationalo"mt mM#jD"H̀‰MissionTelecommunicationsB m mA#R,Geostationary orbitn/a (3424 km x 37531 km x 17.2 x 730 min)r%t mi mM#jJ" &p㉂Launch vehicleThor Delta #42& m m# 5i m m'  End of life_ m# mA#R<"Out of service26 Oct 1966B m mA#RCauseRemained on the transfert (the apogee kick motor failed)&# m m# 8 m m' "(Technical dataL mP m0 08'kzSpecificationsC-band=  m m1CF m m AmIntelsat 202MP m m8 @,%D" Intelsat 2021 m m'  Generalg mr mG#^@") Designation02639 / 67001A\ m mA#R6Launch date11 Jan 1967t'r mBmM#jN"N ,<Country of originInternationalo" mmM#jD"H̀‰MissionTelecommunicationsm,BmmA#RX,Geostationary orbitPacific Ocean Regionr%mmM#jJ" &p㉂Launch vehicleThor Delta #44&mm# 5m @m'  End of lifem @mP mWmc@mA#R,"Out of serviceyes& @m@m# 8c@m@m' "(Technical dataL@m Am0 08'kzSpecificationsC-band= @mJAm12eJAmAmEmIntelsat 203M AmAm8 @,%D" Intelsat 2031 JAmAm'  Generalg Am/BmG#^@") Designation02717 / 67026A\AmBmA#R6Launch date23 Mar 1967t'/BmBmM#jN"N ,<Country of originInternationalo"BmnCmM#jD"H̀‰MissionTelecommunications\BmCmA#R6,Geostationary orbit4Wr%nCmn'  End of lifeW nnA#R,"Out of serviceyes&>nn# 8nn' "(Technical dataLn?n0 08n콫SpecificationsC-band= n|n1f|nn+nIntelsat 402M?nn8 @,%D" Intelsat 4021 |nn'  Generalg nanG#^@") Designation04881 / 71006A\nnA#R6Launch date26 Jan 1971t'an1nM#jN"N ,<Country of originInternationalo"nnM#jD"H̀‰MissionTelecommunications_1nnA#R<,Geostationary orbit19.5Wq$npnM#jH" &yjLaunch vehicleAtlas Centaur_nnA#R<Launch siteCape Canaveral&pnn# 5n*n'  End of lifeWnnA#R,"Out of serviceyes&*nn# 8nn' "(Technical dataLn+n0 08n콫SpecificationsC-band= nhn1Ohnn nIntelsat 403M+nn8 @,%D" Intelsat 4031 hnn'  Generalg nMnG#^@") Designation05709 / 71116A\nnA#R6Launch date20 Dec 1971t'Mn nM#jN"N ,<Country of originInternationalo"n nM#jD"H̀‰MissionTelecommunications_ n nA#R<,Geostationary orbit21.5Wq$ n\ nM#jH" &yjLaunch vehicleAtlas Centaur_ n nA#R<Launch siteCape Canaveral&\ n n# 5 n n'  End of lifeW nm nA#R,"Out of serviceyes& n n# 8m n n' "(Technical dataL n n0 08n콫SpecificationsC-band= nT n1FT n nAnIntelsat 404M n n8 @,%D" Intelsat 4041 T n n'  Generalg n9 nG#^@") Designation05775 / 72003A\ n nA#R6Launch date23 Jan 1972t'9 n nM#jN"N ,<Country of originInternationalo" nxnM#jD"H̀‰MissionTelecommunications^ nnA#R:,Geostationary orbit179Eq$xnGnM#jH" &yjLaunch vehicleAtlas Centaur_nnA#R<Launch siteCape Canaveral&Gnn# 5n @n'  End of lifen @n nWnd@nA#R,"Out of serviceyes& @n@n# 8d@n@n' "(Technical dataL@nAn0 08n콫SpecificationsC-band= @nKAn1O;KAnAnEnIntelsat 405MAnAn8 @,%D" Intelsat 4051 KAnAn'  Generalg An0BnG#^@") Designation06052 / 72041A\AnBnA#R6Launch date13 Jun 1972t'0BnCnM#jN"N ,<Country of originInternationalo"BnoCnM#jD"H̀‰MissionTelecommunications]CnCnA#R8,Geostationary orbit57Eq$oCn=DnM#jH" &yjLaunch vehicleAtlas Centaur_CnDnA#R<Launch siteCape Canaveral&=DnDn# 5DnDn'  End of lifeWDnNEnA#R,"Out of serviceyes&DntEn# 8NEnEn' "(Technical dataLtEnEn0 08n콫SpecificationsC-band= En5Fn1 5FnFn1HnIntelsat 406MEnFn8 @,%D" Intelsat 40655FnFn'  End of life_FnGnA#R<"Out of service20 Feb 1975q*FnGnG#^TyjCauseLaunch failure (Atlas Centaur)&GnGn# 8GnGn' "(Technical dataLGn1Hn0 08n콫SpecificationsC-band= GnnHn1F nHnHnMnIntelsat 407M1HnHn8 @,%D" Intelsat 4071 nHnHn'  Generalg HnSInG#^@") Designation06796 / 73058A\HnInA#R6Launch date23 Aug 1973t'SIn#JnM#jN"N ,<Country of originInternationalo"InJnM#jD"H̀‰MissionTelecommunications\#JnJnA#R6,Geostationary orbit1Wq$Jn_KnM#jH" &yjLaunch vehicleAtlas Centaur_JnKnA#R<Launch siteCape Canaveral&_KnKn# 5KnLn'  End of lifeWKnpLnA#R,"Out of serviceyes&LnLn# 8pLnLn' "(Technical dataLLnMn0 08n콫SpecificationsC-band= LnWMn1; WMnMnnIntelsat 408MMnMn8 @,%D" Intelsat 4081 WMnMn'  Generalg Mn ŁnOn1 OnnnIntelsat 4A01Nnn8 @.%D" Intelsat 4A011 On΂n'  Generalg n5nG#^@") Designation08330 / 75091A\΂nnA#R6Launch date26 Sep 1975t'5nnM#jN"N ,<Country of originInternationalo"ntnM#jD"H̀‰MissionTelecommunications_nӄnA#R<,Geostationary orbit24.5Wq$tnDnM#jH" &yjLaunch vehicleAtlas Centaur_ӄnnA#R<Launch siteCape Canaveral&DnɅn# 5nn'  End of lifeWɅnUnA#R,"Out of serviceyes&n{n# 8Unn' "(Technical dataL{nn0 08cȀSpecificationsC-band> n=n1u0 =nnnIntelsat 4A02Nnn8 @.%D" Intelsat 4A021 =nn'  Generalg n#nG#^@") Designation08620 / 76010A\nnA#R6Launch date29 Jan 1976t'#nnM#jN"N ,<Country of originInternationalo"nbnM#jD"H̀‰MissionTelecommunications_nnA#R<,Geostationary orbit27.5Wq$bn2nM#jH" &yjLaunch vehicleAtlas Centaur_nnA#R<Launch siteCape Canaveral&2nn# 5nn'  End of lifeWnCnA#R,"Out of serviceyes&nin# 8Cnn' "(Technical dataLinn0 08cȀSpecificationsC-band> n+n1?+nynnIntelsat 4A03Nnyn8 @.%D" Intelsat 4A031 +nn'  Generalg ynnG#^@") Designation10557 / 78002A[nlnA#R4Launch date7 Jan 1978t'nnM#jN"N ,<Country of originInternationalo"lnOnM#jD"H̀‰MissionTelecommunications]nnA#R8,Geostationary orbit60Eq$OnnM#jH" &yjLaunch vehicleAtlas Centaur_n|nA#R<Launch siteCape Canaveral&nn# 5|n׏n'  End of lifeWn:nA#R,׏n:nn"Out of serviceyes&׏n`n# 8:nn' "(Technical dataL`nn0 08cȀSpecificationsC-band> n"n1"npnnIntelsat 4A04Nnpn8 @.%D" Intelsat 4A041 "nn'  Generalg pnnG#^@") Designation10024 / 77041A\ndnA#R6Launch date26 May 1977t'nnM#jN"N ,<Country of originInternationalo"dnGnM#jD"H̀‰MissionTelecommunications_nnA#R<,Geostationary orbit34.5Wq$GnnM#jH" &yjLaunch vehicleAtlas Centaur_nvnA#R<Launch siteCape Canaveral&nn# 5vnn'  End of lifeWn(nA#R,"Out of serviceyes&nNn# 8(nn' "(Technical dataLNnn0 08cȀSpecificationsC-band> nn10-n^n#nIntelsat 4A05Nn^n8 @.%D" Intelsat 4A055nn'  End of life_^nnA#R<"Out of service29 Sep 1977@nynG#^yjCauseLaunch failure (Atlas Centaur): explosion after 55 s&nn# 8ynn' "(Technical dataLn#n0 08cȀSpecificationsC-band> nan1-annnIntelsat 4A06N#nn8 @.%D" Intelsat 4A061 ann'  Generalg nGnG#^@") Designation10778 / 78035A\nnA#R6Launch date31 Mar 1978t'GnnM#jN"N ,<Country of originInternationalo"nnM#jD"H̀‰MissionTelecommunications]nnA#R8,Geostationary orbit63Eq$nTnM#jH" &yjLaunch vehicleAtlas Centaur_nnA#R<Launch siteCape Canaveral&Tnn# 5nn'  End of lifeWnenA#R,"Out of serviceyes&nn# 8enn' "(Technical dataLnn0 08cȀSpecificationsC-band= nLn1rLnnIoIntelsat 501Mnn8 @,%D" Intelsat 5011 Lnn'  Generalg n1nG#^@") Designation12474 / 81050A\nnA#R6Launch date23 May 1981t'1nnM#jN"N ,<Country of originInternationalo"npnM#jD"H̀‰MissionTelecommunicationsb!nnA#RB,Geostationary orbitsee belowq$pnOoM#jH"nOon &yjLaunch vehicleAtlas Centaur_noA#R<Launch siteCape Canaveral&Ooo# 2 oo'  Locationoom#:p   " BeginEndPositionooj#.p$(*L: 23 May 1981ooj#<pMay 1988went inclined*o-oj#Tp02late 1991late 1991177W, inclinedPoop#p,.Oct 1992Jan 199691.5E, inclined (left to leave the slot to Measat 1),-ooj#Xp"68late Feb 1996Jan 199772E, inclined&oo# 5oo'  End of life\o:oA#R6"Out of serviceFeb 1997TooA#R&Causedeorbited&:oo# 8oo' "(Technical data]&oIo7 >L:뢟%ūSpecificationsC-bandKu-band= oo1 ?oo@oIntelsat 502MIoo8 @,%D" Intelsat 5021 oo'  Generalg okoG#^@") Designation12089 / 80098A[ooA#R4Launch date6 Dec 1980t'ko:oM#jN"N ,<Country of originInternationalo"ooM#jD"H̀‰MissionTelecommunicationsb!:o oA#RB,Geostationary orbitsee belowq$o| oM#jH" &yjLaunch vehicleAtlas Centaur_ o oA#R<Launch siteCape Canaveral&| o o# 2 o3 o'  Location o om#:   " BeginEndPosition3 oC oj#8"&(L: 6 Dec 198021.5W o oj#<Dec 1988went inclined&C o[ oj#L,.Jan 1991Jan 19911W, inclined) o oj#R,.Feb 1992Oct 199421.5W, inclined)[ o oj#R,.Oct 1994Apr 199840.5W, inclined& o o# 5 o o'  End of life_ o;oA#R<"Out of service14 Apr 1998T ooA#R&Causedeorbited&;oo# 8oo' "(Technical datao @o: B:뢟%ū񉂂SpecificationsC-bandKu-bandWhen in 21.5W, the antenna's platform was rotated in December 1992 to enable a direct link between Somalia and the US. The Eastern spot was pointed to Somalia.o @oIo=oI@o' , EIRP coverage (dBW)E @o@o0 0*B0}Z(C-bandKu-band1I@o@o1@oAoX"@oAo6 "Out of servicemid Jan 1998TIoyJoA#R&Causedeorbited&%JoJo# 8yJoJo' "(Technical data]&Jo4Ko7 >L:뢟%ūSpecificationsC-bandKu-band=JoqKo' , EIRP coverage (dBW)E4KoKo0 0* ǀ`C-bandKu-band1qKoKo1Ko?LoX"Ko?Lo6 L:뢟%ūSpecificationsC-bandKu-band= oHo1 kHoooIntelsat 505M oo8 @,%D" Intelsat 505@HoՇo# :Also called Intelsat MCS-A1 oo'  Generalg ՇomoG#^@") Designation13595 / 82097A\oɈoA#R6Launch date28 Sep 1982t'mo=oM#jN"N ,<Country of originInternationalo"ɈooM#jD"H̀‰MissionTelecommunicationsb!=ooA#RB,Geostationary orbitsee belowq$ooM#jH" &yjLaunch vehicleAtlas Centaur_oފoA#R<Launch siteCape Canaveral&oo# : ފo>o- */ۀ Locationoȋom#:   " BeginEndPosition>oIoj#.$(*L: 28 Sep 1982ȋoьoj#<Dec 1989went inclined*Ioeoj#T24Jan 1991end of 199163E, inclined'ьooj#N,.Feb 1992Aug 199466E, inclined'eooj#N,.Nov 1994Jun 199665E, inclined'ooj#N,.Aug 1996Nov 199633E, inclinedooj#>Apr 199772E, inclined&oǏo# 8o o' "(Technical dataǏo o om/Ǐoyo> L^:뢟.ū%ūSpecificationsL-bandC-bandKu-band= oo' , EIRP coverage (dBW)Eyoo0 0*+ZmEC-bandKu-band1o,o1,ooX"oo6 L^:뢟.ū%ūSpecificationsL-bandC-bandKu-band=oo' , EIRP coverage (dBW)E{oo0 0*ΖVtC-bandKu-band1o.o1.ooX"oo6 L^:뢟.ū%ūSpecificationsL-bandC-bandKu-band1upp1!pkpX"pkp6 L^:뢟.ū%ūSpecificationsL-bandC-bandKu-band=  p) p1z$) pv pApIntelsat 509M pv p8 @,%D" Intelsat 5091 ) p p'  Generalg v p pG#^@") Designation15034 / 84057A[ pi pA#R4Launch date9 Jun 1984t' p pM#jN"N ,<Country of originInternationalo"i pLpM#jD"H̀‰MissionTelecommunications\ ppA#R6,Geostationary orbitn/aq$LppM#jH" &yjLaunch vehicleAtlas Centaurk!ppJ#dBLaunch siteCape Canaveral&pp# 5pp'  End of life^pI@pA#R:pI@p p"Out of service9 Jun 1984c"p@pA#RDCauseLauncher partial failureVI@pApA#R*Decay24 Oct 1984&@p(Ap# 8Ap`Ap' "(Technical datam/(ApAp> L^:뢟.ū%ūSpecificationsL-bandC-bandKu-band= `Ap Bp1V% BpWBpIpIntelsat 510MApWBp8 @,%D" Intelsat 5101 BpBp'  Generalg WBpBpG#^@") Designation15629 / 85025A\BpKCpA#R6Launch date22 Mar 1985t'BpCpM#jN"N ,<Country of originInternationalo"KCp.DpM#jD"H̀‰MissionTelecommunicationsb!CpDpA#RB,Geostationary orbitsee belowq$.DpEpM#jH" &yjLaunch vehicleAtlas Centaur&Dp'Ep# : EpaEp- */ۀ Location'EpEpm#:   " BeginEndPositionaEpqFpj#8$(*L: 22 mar 1984174EEpFpj#<Aug 1992went inclined'qFpGpj#N,.Feb 1995Mar 199566E, inclined'FpHpj#N,.Apr 1995Jun 199657E, inclinedGpHpj#>Nov 199633E, inclined&HpHp# 8HpIp' "(Technical data]&Hp_Ip7 >L&р,9ᛧSpecificationsC-bandKu-band=IpIp' , EIRP coverage (dBW)E_IpIp0 0*sRyC-bandKu-band1IpJp1&JpjJpX"IpjJp6 p,.Jan 1991Jan 199127.5W ppj#<p.0late 1991Sep 199263Eppj#<p,.Oct 1992Feb 1993177E-pL&р,9ᛧSpecificationsC-bandKu-band=څptp' , EIRP coverage (dBW)E7pp0 0*6U݀Qj"C-bandKu-band1tpp1)pBpX"pBp6 ,.Jan 1991Jan 199134.5Wop~pj#8,.Mar 1991Jun 19941W+ppj#V,.Jun 1994Aug 19941W, went inclined)~ppj#R,.Sep 1994Sep 199621.5W, inclined!p1pj#BFeb 199755.5W, inclined&pWp# 81pp' "(Technical dataIWpp9 B&р,9ᛧSpecificationsC-bandKu-bandKu-band downlink: pṗp11.01-11.59 GHz1pNp1,NppX"pp6 L&р,9ᛧSpecificationsC-bandKu-band=pmp' , EIRP coverage (dBW)E0pp0 0*|bpQnwC-bandKu-band1mpp1/p;pX"p;p6 L&р,9ᛧSpecificationsC-bandKu-band= pEp1\L2EppqIntelsat 515Mpp8 @,%D" Intelsat 5151 Epp'  Generalg p*pG#^@") Designation19772 / 89006A\ppA#R6Launch date27 Jan 1989t'*ppM#jN"N ,<Country of originInternationalo"pipM#jD"H̀‰MissionTelecommunicationsb!ppA#RB,Geostationary orbitsee belown!ip9pM#jB" &D+Launch vehicleAriane V28&p_p# : 9pp- */ۀ Location_p#pm#:   " BeginEndPositionppj#.$(*L: 27 Jan 1989#p7qj#:,p7qp.Jan 1991Feb 199260Epqj#:,.Apr 1992Aug 199618W7qGqj#>,.Sep 1996Dec 199721.5Wqqj#.Mar 199837.8WkGq]q* $ur7From 1st Apr 1998 on the satellite is used by Columbia Communications Corp. and renamed Columbia 515.8qq' "(Technical data]&]qq7 >L&р,9ᛧSpecificationsC-bandKu-band1q#q13#q{qX"q{q6 Lן^̫GUSpecificationsC-bandKu-band= q q' , EIRP coverage (dBW)Ej q q0 0*@i*C-bandKu-band1 q q16 qu qX" qu q6 ,.Jan 1991Feb 199224.5W@qAqj#:,.Apr 1992Apr 199260E0Aq>Bqj#:,.Oct 1992Oct 199763EAqBqj#*Oct 199762E&>BqBq# 8BqCq' "(Technical data]&BqxCq7 >Lן^̫GUSpecificationsC-bandKu-band=CqCq' , EIRP coverage (dBW)ExCqCq0 0*t,w~C-bandKu-band1Cq+Dq19+DqDqX"CqDq6 ,.May 1992Oct 199734.5W JqKqj#.Nov 199724.5W&JqLן^̫GUSpecificationsC-bandKu-band=tKqLq' , EIRP coverage (dBW)EKqSLq0 0*0݉C-bandKu-band1LqLq1<LqLqX"SLqLq6 MqMquqIntelsat 604MfMqMq8 @,%D" Intelsat 6041 Mq!Nq'  Generalg MqNqG#^@") Designation20667 / 90056A\!NqNqA#R6Launch date23 Jun 1990t'NqXOqM#jN"N ,<Country of originInternationalo"NqOqM#jD"H̀‰MissionTelecommunicationsb!XOq5qA#RB,Oq5qfMqGeostationary orbitsee belowp#OqqM#jF" &^]Launch vehicleTitan 3 #155&5qˀq# : qq- */ۀ Locationˀqqm#:   " BeginEndPositionqqj#.$(*L: 23 Jun 1990qqj#>,.Jan 1991Feb 199227.5Wqqj#*Oct 199260E&q>q# 8qvq' "(Technical data}D>qq9 Bן^̫GU񉂂SpecificationsC-bandKu-bandKu-band used: 10.97-11.6 GHz=vq0q' , EIRP coverage (dBW)Equq0 0*]<C-bandKu-band10qq1?qqX"uqq6 ,.Jul 1992Nov 199724.5WЊqڋqj#.Dec 199727.5WYqq% YIn early September the satellite experienced an "anomaly" with telemetry. For more safety, the fleet in AOR was redeployed. The telemetry problem affects the attitude control: the satellite is not reporting its location anymore. Therefore the position has to be computed by ground stations (by measuring signal strength). Those telemetry problems were solved in Dec 1997 so that the satellite could resume normal operations.8ڋqq' "(Technical data]&q@q7 >Lן^̫GUSpecificationsC-bandKu-band=q}q' , EIRP coverage (dBW)p9@qq7 >rvQGRGRC-bandKu-band Eastern spotKu-band Western spot1}qq1BqvqX"qvq6 rA#R6Launch date22 Oct 1993t' r rM#jN"N ,<Country of originInternationalo"> r! rM#jD"H̀‰MissionTelecommunicationsb! r rA#RB,Geostationary orbitsee belown!! r rM#jB" &D+Launch vehicleAriane V60: r+ r$ ,Cost: $103 million: re r- */ۀ Location+ r rm#:   " BeginEndPosition$e r} rj#H$8:L: 22 Oct 1993Aug 1997174E r rj#,Sep 1997180E&} r#r# 8 r[r' "(Technical data]&#rr7 >L@ ӫڋSpecificationsC-bandKu-band=[rr' , EIRP coverage (dBW)Er:r0 0*5+ dCvC-bandKu-band1rkr1IkrrX":rr6 L@ ӫڋSpecificationsC-bandKu-band=FrGr' , EIRP coverage (dBW)EFrcGr0 0**jՉC-bandKu-band1GrGr1LGrGrX"cGrGr6 L?IRCSpecificationsC-bandKu-band=trr' , EIRP coverage (dBW)ErSr0 0*dkŐI )QC-bandKu-band1rr1ZrrX"Srr6 L?IRCSpecificationsC-bandKu-band=grr' , EIRP coverage (dBW)ErFr0 0*Elڀ⪙/C-bandKu-band1rwr1]wrrX"Frr6 L?IRCSpecificationsC-bandKu-band= s$s1``$sqs sIntelsat 709Msqs8 @,%D" Intelsat 7091 $ss'  Generalg qs sG#^@") Designation23915 / 96035A\sesA#R6Launch date15 Jun 1996t' ssM#jN"N ,<Country of originInternationalo"esHsM#jD"H̀‰MissionTelecommunicationsb!ssA#RB,Geostationary orbitsee belown!HssM#jB" &E+Launch vehicleAriane V87&s>s# : sxs- */ۀ Location>ssm#:   " BeginEndPosition0xssj#`$@BL: 15 Jun 1996mid-Jul 199657W, testings sj#2 $&mid-Jul 199650WjFs s$ The East Hemi beam had problems and was deactivated in early 1997.8 s s' "(Technical data]& s s7 >L@ ӫڋSpecificationsC-bandKu-band= s[ s' , EIRP coverage (dBW)E s s0 0*MmlLMk?ګmSpecificationsC-bandKu-band=CsCs' , EIRP coverage (dBW)ElCsCs0 0*b̉C-bandKu-band1CsDs1dDswDsX"CswDs6 Es1Af>EsEsIsIntelsat 802MEsEs8 @,%D" Intelsat 8021 >EsEs'  Generalg Es#FsG#^@") Designation24846 / 97031A\EsFsA#R6Launch date25 Jun 1997t'#FsFsM#jN"N ,<Country of originInternationalo"FsbGsM#jD"H̀‰MissionTelecommunicationsfFsGsG#^>"/ۀ0Geostationary orbit174En!bGs6HsM#jB" &9E+Launch vehicleAriane V96N(GsHs& PValue: $179 milliontested at 166E86HsHs' "(Technical data]&HsIs7 >LMk?ګmSpecificationsC-bandKu-band=HsVIs' , EIRP coverage (dBW)EIsIs0 0*#C`^,i+C-bandKu-band1VIsIs1gIs$JsX"Is$Js6 LMk?ګmSpecificationsC-bandKu-band=qs s' , EIRP coverage (dBW)E΀sPs0 0*ꩀ⿺oC-bandKu-band1 ss1jsفsX"Psفs6 LMk?ګmSpecificationsC-bandKu-band=%ss' , EIRP coverage (dBW)Ess0 0*i Iv鉂C-bandKu-band1s5s1m5ssX"ss6 sM#jN"N ,<Country of originInternationalo"ʉssM#jD"H̀‰MissionTelecommunications_>s sA#R<,Geostationary orbit55.5Wm sysM#j@" &yjLaunch vehicleAtlas 2ASQ sʋsA#R Launch site&yss# 8ʋs(s' "(Technical dataz<ss> Lxstp뉂DEIRP coverage (dBW)SpecificationsC-bandKu-band1(sӌs1Wpӌs'sMsT+s's) "VȠ$To view this page you need to register&ӌsMs# 1's~s1q~sύsQMsύs6 <8Ā"Intelsat 805's EIRP1~ss1WrsTszsT+ύsTs) "VȠ$To view this page you need to register&szs# = Tss1p+ssssIntelsat 806Mzss8 @,%D" Intelsat 806;s?s# 0part of the 8A series1 sps'  Generalg ?s׏sG#^@") Designation25239 / 98013A\ps?sA#R6׏s?szsLaunch date28 Feb 1998t'׏ssM#jN"N ,<Country of originInternationalo"?s"sM#jD"H̀‰MissionTelecommunications_ssA#R<,Geostationary orbit40.5Wr%"ssM#jJ" &yjLaunch vehicleAtlas 2AS #114M)s@s$ RTested at 55.5W until late Apr 1998.8sxs' "(Technical dataz<@ss> Lxي|tp뉂DEIRP coverage (dBW)SpecificationsC-bandKu-band1xs#s1t#ss^(ss6 Contract worth $100 million8s's' "(OTechnical data=sds' , EIRP coverage (dBW)xH'ss0 0hcQicQFixed 1 and Steerable 1 Ku beamsFixed 2 and Steerable 2 Ku beams8dss' " SpecificationsYsmsA#R0&Prime contractorMMS\ssA#R6PlatformEurostar 2000+[ms$sA#R4"Mass at launch3250 kgSswsA#R$ Mass in orbitO$ssA#RDimensionQwssA#R Solar arrayYspsA#R0 Stabilization3 axisTssA#R&DC power7600 W]ps!sA#R8$Design lifetime12 yearshDss$ The satellite can operate in collocation with up to 3 satellites1 !ss'  Ku-bandYssA#R0(Main transponders30YslsA#R0,Backup transpondersWssB#TPowerFixed & Steerable beam 1: 101 W (TWTA)Fixed & Steerable beam 2: 105 W (TWTA)UlsZsA#R(Bandwidth36 MHz:ss]#F$hcQicQhcQicQCoverage 1 EIRPFixed beam 1: India (dual polarization), 54.2-49 dBWFixed beam 2: China, 51.5-32 dBWSteerable beam 1: Far East (dual polarization), 55.5-50 dBWSteerable beam 2: Indonesia/Malaysia, 54-47 dBWZsZsE#X G/TFixed beam 1: +4.4 - -1 dB/KFixed beam 2: +4.8 - -3 dB/KSteerable beam 1: +8.7- 0 dB/KSteerable beam 2: +7.2 - -1 dB/KYssA#R0 SFD-91 - -73 dBW/m\ZstA#R6Polarizatiostsnlinear H/VstC#TFrequenciesUplink: 13.75-14 GHz / 14-14.25 GHz / 14.25-14.5 GHz Downlink: 12.5-12.75 GHz / 10.95-11.2 GHz / 11.45-11.7 GHz ,t t% 12 transponders for the India beam and 6 transponders for the Far East beam are permanently assigned. Additionally, there are 12 transponders that can be switched on a transponder-by-transponder basis among 18 available channels (6 per all beams except India)1t<t1Wv<tttT+ tt) "VȠ$To view this page you need to register&<tt# 1tt1wtHta+tHt6 FtG#^:" &Launch vehicleAriane 5&EtdFt# 8>FtFt' "(Technical data_'dFtFt8 @N~ 񉂂SpecificationsC-bandKu-band1Ft,Gt1W,GtGtGtT+FtGt) "VȠ$To view this page you need to register&,GtGt# 1GtGt1GtHtHt:GtHt# .Intelsat shift plansGtHt`       80164E60262E802174E701180E511157E503junk80321.3W51531.4W80429.5W80640.5W502junk?80555.5E1Ht+It1W+ItItItT+HtIt) "VȠ$To view this page you need to register&+ItIt# FItIt1@G It=JtLNtProgram: IntersputnikRIt=Jt5 :<#Ā" Program: IntersputnikOItLt\ ڀ CIx"jQv -M~wIntersputnik is an organization created in 1971 by the former USSR; started working in 1972. It was aimed to break Intelsat's monopoly (they didn't expect members not to belong to other telecommunications organizations). In 1997, 22 states belonged to the organization (Intercosmos members and other friend states). Intersputnik used Molniya satellites before turning to geostationary satellites (Raduga, Gorizont, Gals and Express). Earth stations use typical 12 m antennas. =JtLNt- ('ZӉInformcosmos is an important partnerIn June 1997 it was announced that Intersputnik and Lockheed Martin would form a joint venture to become a global satellite operator. The new company will be called Lockheed Martin Interputnik Ltd. or LMI, based in London. The new company should be operating from numerous slots around the world. The deployment should start by slots in Asia to serve the CIS.1Lt}Nt1}Nt%OtDLNtNt* $4o7U=Program: Intersputnikd-}Nt%Ot7 >Z#UM~wLMI 1see also Gorizont and Express6Nt[Ot1[OtOtitLMI 1C %OtOt6 <#Ā" LMI 11 [OtOt'  GeneralYOt4tG#^$"Ot4t%Ot) DesignationZOttA#R2Launch datelate 1998`4ttG#^2"N ,Country of origin?o"t]tM#jD"H̀‰MissionTelecommunications]ttA#R8,Geostationary orbit75Ej]t$tM#j:" &㉓gLaunch vehicleProtonYt}tG#^$Launch site&$tt# 8}tۂt' "(OTechnical data8tt' " SpecificationsXۂtktA#R.&Prime contractorLMUttA#R(PlatformA2100AXTkttA#R&"Mass at launchUtitA#R(Dry mass1730 kgOttA#RDimensionQit tA#R Solar arrayYtbtA#R0 Stabilization3-axisT ttA#R&DC power7560 W]bttA#R8$Design lifetime15 years&t9t# 0 tit'  C-bandY9t†tA#R0(Main transponders28YittA#R0,Backup transpondersK †tftA#RPowerUttA#R(Bandwidth36 MHzoftltB#TCoverageA: Africa, the Middle East, Australasia and South East Asia excluding central AsiaB: central AsiaTttA#R&EIRP max38 dBWM lt tA#RG/T max\titA#R6Polarizationlinear H/Vg ttB#TFrequenciesUplink: A: 5.725-6.025 GHz; B: 6.425-6.725 GHzDownlink: A: 3.7-4.0 GHz; B: 3.4-3.7 GHz&it8t# 1 tit'  Ku-bandY8tŠtA#R0(Main transponders16YittA#R0,Backup transpondersK ŠtftA#RPowerUttA#R(Bandwidth27 MHzfťtC#TCoverageA1: Northern part of the North hemisphere including Russia, part of China to IrakA2: Central part of the North hemisphere, including the Middle East, India, Thailand, Vietnam and most of ChinaTt tA#R&EIRP max45 dBWM ̌tmtA#RG/T maxR ttA#R"PolarizationBmtCtB#TFrequenciesUplink: 13.750-14.000 GHzDownlink: 12.5-12.75 GHz&tit# 1Ctt1WtttT+itt) "VȠ$To view this page you need to register&tt# ?tSt1B StttIntersputnik 8Htt, (:" Program: Intersputnik 8{OSt"t, &o7U=Russian telecommunication satellite program lead by Intt"ttersputnik. A special purpose company was formed with Daimler Benz Aerospace (Germany), Aerospatiale (France) and SS/L named Space Alliance.First satellite to be launched in late 1998 over the Indian Ocean. Another one will be positioned over the Atlantic Ocean in mid-1999.8tZt' "(OTechnical data8"tt' " Specificationsc"ZttA#RD&Prime contractorAerospatiale N tCtA#RPlatformTttA#R&"Mass at launchSCttA#R$ Mass in orbitOt9tA#RDimensionQttA#R Solar arrayS9ttA#R$ StabilizationTt1tA#R&DC power4000 W_ttA#R<$Design lifetime> 15 years1t^t% SSS/Loral will manufacture basic subsystems such as satellite repeaters and Daimler-Benz Aerospace will provide antennas, solar arrays and an attitude control system.0 tt'  C-bandY^ttA#R0(Main transponders24Yt@tA#R0,Backup transpondersK ttA#RPowerV@ttA#R*Bandwidth36 MHz?a tBtA#R@Coverageglobal and regionalYttA#R0EIRP max37 - 40 dBWRBttA#R"Polarization&tt# 1 tDt'  Ku-bandYttA#R0(Main transponders16YDttA#R0,Backup transpondersK tAtA#RPower`ttA#R>Bandwidth36, 54 and 72 MHza AttA#R@Coveragesteerable spot beamTtVtA#R&EIRP max50 dBWXttA#R.Polarizationlinear$Vtt" 1tt1WtWt}tT+tWt) "VȠ$To view this page you need to register&t}t# 5Wtt1Kstt uIRAS= }tt2 4"  IRASC t2t# @ Infra Red Astronomy Satellite1 tct'  Generalg 2ttG#^@") Designation13777 / 83004A\ct&tA#R6Launch date26 Jan 1983KttY#"N 4,㬹.R׉㹌לCountry of originNetherlands, United Kingdom and United Statesu(&t?tM#jP"H̀_BMissionScientific: IR astronomy^ttA#R:"Perigee/Apogee884/903 kmT?ttA#R&Inclination99UtFtA#R(Period102.9 mins&ttM#jL" &p㉂Launch vehicleThor Delta #166}YFtBu$ It mapped 250,000 IR sources in ttBu}the 300 days before its helium coolant was exhausted.5twu'  End of life_BuuA#R<"Out of service23 Nov 1983&wuu# <u8u' *O External resources]6uu' lhttp://www.gsfc.nasa.gov/astro/iras/iras_home.html88uu' "(OTechnical data8uu' " Specifications%u*uG#\<Industrial responsabilitiesNetherlands 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)[uuA#R4"Mass at launch1077 kgZ*uuA#R2"Telescope mass810 kgSu2uA#R$Diameter2.2 mQuuA#R Height3.6 m`2uuA#R>Solar array5 m (2 panels)Yu<uA#R0 Stabilization3 axisXuuA#R.DC powerEOL: 500 W^<uuA#R:$Design lifetime11 months&uu# 1 uIu'  Payloadu7u% 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.^IuuA#R:*Telescope diameter0.57 mW7uuA#R,Focal length5.5 m\uHuA#R6 Field of view30 arcmin7uu$ &Spectral range:ZHu uD#XIR Telescope(band 1) 8.5-15 m(band 2) 19-30 m(band 3) 40-80 m(band 4) 83-119 m[ux uA#R4Spectrometer7.4-23 mi( u uA#RP<Short wavelength photometer4.1-8 mK'x u, u$ NCooling system by evaporated helium\ u uA#R6,Temperature control2 Kc", u uA#RD"Telemetry/dataS-band (1 Mbps)$ u u" 8 uG u1L҃G u uHuIridiumM u u5 :2\I" Program: Iridium]1G u @u, &cN As the program was originaly though with 77 satellites, it was named after the 77th element in the periodical table: IridiumThe Iridium system is owned by Iridium LLC, an international consortium of 17 investor organizations representing telecommunications and industrial companies worldwide, with Motorola Satellite Communications Group serving as the prime contractor. The investors are: Iridium Africa Corporation, Iridium Canada, Inc., Iridium China (Hong Kong), Ltd., Iridium India Telecom Limited, Iridium Middle East Corporation, Iridium SudAmerica Corporation, Khrunichev State Research and Production Space Center of the Russian Federation, Korea Mobile Telecommunications of Korea, Lockheed Martin Corporation and Motorola, Inc. of the U.S., Nippon Iridium Corporation of Japan, o.tel.o communications GmbH of Germany, Pacific Electric Wire & Cable Co., Ltd. of Taiwan, Raytheon Company of the U.S., Sprint Corporation of the U.S., STET Group - Societa Finanziara Telefonica per Azioni of Italy, and Thai Satellite Telecommunications Co., Ltd. of Thailand. u @u uA uMAu' 5The cost of the global system is close to $4 billion. The commercial launch date is 23 Sep 1998 Cost per satellite: $62 millionIridium next generation (called MacroCell): a system with 96 satellites capable of handling 384 kbps communications (4.8 kbps with the 1st system) < @uAu' *O External resourcesMAuBBu6 :http://www.iridium.com/http://www2.satellite.eu.org/sat/vsohp/iridium.htmlhttp://www2.gsoc.dlr.de/satvis/iridiumhelp.html8AuzBu' "(OTechnical data2 BBuBu' O Launches0zBuCu8 >9+Sp㉂㉓g12 satellites in 6 launches by Long March 2C from Taiyuan with unique "smart dispenser" (option for 4 more launches); July 199640 satellites in 8 launches by Delta 2 (and 5 more between 1998 and 2001)21 satellites in 3 launches by Proton@BuDu' 2 Constellation overviewSCuoDuA#R$ Orbit typeLEOa DuDuA#R@ Orbit range780 km, circularc"oDu3EuA#RD &Nb of satellites66 + 7 backupSDuEuA#R$ Nb of planes6V3EuEuA#R* Inclination86.4^Eu:FuA#R: 2Nb beams per satellite48VEuFuA#R* Coverage4700 kmY:FuFuA#R0 ModulationFNMA/TDMAHFusGuB#T *Mobile frequenciesUplink: 1610-1626.5 MHzDownlink: 1610-1626.5 MHzZFuGuA#R2 "Satellite mass725 kgq0sGu>HuA#R` Coverageall longitudes, 80N - 80S latitudesd#GuHuA#RF &Operational date1998 (planned)&>HuHu# 1HuHu1UHuvOuOu>Hu7Iu) "*ЇProgram: Iridium?HuvOu#܄q̀mՅnՅoՅpՅqՅrՅՅՅՅՅՅՅՅƀXՅՅՅՅՅՅՅՅՅՅՅՅՅƀFՅ=Յ>Յ?Յ@ՅAՅBՅCՅDՅEՅqՅhՅiՅƀjՅkՅlՅmՅnՅoՅpՅՅՅՅՅՅՅ̀ZՅՅՅՅՅՅՅՅՅՅՅՅՅ~ՅՅՅՅՅՅՅIridium 04Iridium 05Iridium 06Iridium 07Iridium 08Iridium 09Iridium 10Iridium 11Iridium 12Iridium 13Iridium 14Iridium 15Iridium 16Iridium 17Iridium 18Iridium 19Iridium 20Iridium 21Iridium 22Iridium 23Iridium 24Iridium 25Iridium 26Iridium 27Iridium 28Iridium 29Iridium 30Iridium 31Iridium 32Iridium 33Iridium 34Iridium 35Iridium 36Iridium 37Iridium 38Iridium 39Iridium 40Iridium 41Iridium 42Iridium 43Iridium 44Iridium 45Iridium 46Iridium 47Iridium 48Iridium 49Iridium 50Iridium 51Iridium 52Iridium 53Iridium 54Iridium 55Iridium 56Iridium 57Iridium 58Iridium 59Iridium 60Iridium 61Iridium 62Iridium 63Iridium 64Iridium 65Iridium 66Iridium 67Iridium 68Iridium 69Iridium 70Iridium 71Iridium 72Iridium 73Iridium 74Iridium 75$7IuOu" 1vOuOu1UOu:u^uFOuu) ":ЇIridium'sOuuOu specificationse$OuuA#RH&Prime contractorLockheed Martina uuA#R@PlatformIridium (LM700 bus)Zu=uA#R2"Mass at launch689 kgSuuA#R$ Mass in orbitV=uuA#R*Dimension1 x 2 mQu7uA#R Solar arrayYuuA#R0 Stabilization3 axisN 7uނuA#RDC power\u:uA#R6$Design lifetime5 years$ނu^u" 1:uu1uu?^u΃u) ",ЇIridium's payloadt3uBuA#RfModulationTDMA (Time Division Multiple Access)a ΃uuA#R@Capacity3840 phone circuitsSBuuA#R$Voice4800 bpsQuGuA#R  Fax2400 bpsRuuA#R"Data2400 bps[GuuA#R4"Total Bandwith200 MHz]uQuA#R8Mobile links1.5/1.6 GHzx7uɆuA#Rn.Intersatellite linksKa-band: 18.8-20.2/27.5-30 GHz*Quu' On-board commutation. Inter satellite links, each satellite talks with its 4 neighborsCommunications between the gateways and the satellites: Uplink: 29.1-29.3 GHz, Downlink: 19.4-19.6 GHzPayload built by Motorola's Satcom division in Chandler, Arizona.; Ɇu.u1j2.uuuuIridium 04Guuu5 :&\I" Iridium 04?.uu# 8Also called Iridium SV0041 uuu'  Generalg uLuG#^@") Designation24796 / 97020E[uuA#R4Launch date5 May 1997t'LuuM#jN"N ,㹌לCountry of originUnited Stateso"uuM#jD"H̀㓉MissionTelecommunications^uuA#R:"Perigee/Apogee771/783 km^uFuG#^. Inclination86.4M uuA#RRAAN355p#FuuM#jF" &p㉂Launch vehicleDelta 2 #242&u)u# 8uau' "(Technical dataM)uu0 0:_ <ƉSpecificationsPayload; auu1m`u0uuuIridium 05Gu0u5 :&\I" Iridium 05?uou# 8Also called Iridium SV0051 0uu'  Generalg ouuG#^@") Designation24795 / 97020D[ubuA#R4Launch date5 May 1997t'u֎uM#jN"N ,㹌לCountry of originUnited Stateso"buEuM#jD"H̀㓉MissionTelecommunications^֎uuA#R:"Perigee/Apogee771/783 km^Eu uG#^. Inclination86.4u uuM uZuA#RRAAN355p# uuM#jF" &p㉂Launch vehicleDelta 2 #242&Zuu# 8u(u' "(Technical dataMuuu0 0:_ <ƉSpecificationsPayload; (uu1j2uu0uIridium 06Guuu5 :&\I" Iridium 06?u6u# 8Also called Iridium SV0061 ugu'  Generalg 6uuG#^@") Designation24794 / 97020C[gu)uA#R4Launch date5 May 1997t'uuM#jN"N ,㹌לCountry of originUnited Stateso")u uM#jD"H̀㓉MissionTelecommunications^ujuA#R:"Perigee/Apogee774/780 km^ uuG#^. Inclination86.4M juuA#RRAAN355p#uuM#jF" &p㉂Launch vehicleDelta 2 #242&uu# 8uu' "(Technical dataMu0u0 0:_ <ƉSpecificationsPayload; uku1j`kuuuIridium 07G0uu5 :&\I" Iridium 07?kuu# 8Also called Iridium SV0071 u"u'  Generalg uuG#^@") Designation24793 / 97020B["uuA#R4Launch date5 May 1997t'uXuM#jN"N ,㹌לCountry of originUnited Stateso"uuM#jD"H̀㓉MissionTelecommunications^Xu%uA#R:"Perigee/Apogee773/781 km^uuG#^. Inclination86.4M %uuA#RRAAN355p#u@uM#jF" &p㉂Launch vehicleDelta 2 #242&ufu# 8@uu' "(Technical dataMfuu0 0:_ <ƉSpecificationsPayload; u&u1jP&umuuIridium 08Gumu5 :&\I" Iridium 08?&uu# 8Also called Iridium SV0081 muu'  Generalg uDuG#^@") Designation24972 / 97020A[uuA#R4Launch date5 May 1997t'DuuM#jN"N ,㹌לCountry of originUnited Stateso"uuM#jD"H̀㓉MissionTelecommunications^uuA#R:"Perigee/Apogee776/779 km^u>uG#^. Inclination86.4M uuA#RRAAN355p#>uuM#jF" &p㉂Launch vehicleDelta 2 #242&u!u# 8uYu' "(Technical dataM!uu0 0:_ <ƉSpecificationsPayload; Yuu1b:u4vdvIridium 09Gu4v5 :&u4vu\I" Iridium 09?usv# 8Also called Iridium SV0091 4vv'  Generalg sv vG#^@") Designation24839 / 97030D\vgvA#R6Launch date18 Jun 1997t' vvM#jN"N ,㹌לCountry of originUnited Stateso"gvJvM#jD"H̀㓉MissionTelecommunications^vvA#R:"Perigee/Apogee774/778 kmVJvvA#R*Inclination86.4L vJvA#RRAAN27o"vvM#jD" &㉓gLaunch vehicleProton #249&Jvv# 8vv' "(Technical dataMvdv0 0:_ <ƉSpecificationsPayload; vv1aPvv vIridium 10Gdvv5 :&\I" Iridium 10?v%v# 8Also called Iridium SV0101 vVv'  Generalg %vvG#^@") Designation24838 / 97030C\VvvA#R6Launch date18 Jun 1997t'vvM#jN"N ,㹌לCountry of originUnited Stateso"vvM#jD"H̀㓉MissionTelecommunications^vZvA#R:"Perigee/Apogee773/780 kmVvvA#R*Inclination86.4L ZvvA#RRAAN27o"vkvM#jD" &㉓gLaunch vehicleProton #249&vv# 8kvv' "(Technical dataMv v0 0:_ <ƉSpecificationsPayload; vQ v1y:Q v v vIridium 11G v v5 :&\I" Iridium 11?Q v v# 8Also called Iridium SV0111 v v'  Generalg vo vG#^@") Designation24842 / 97030G\ v vA#R6Launch date18 Jun 1997t'o v? vM#jN"N ,㹌לCountry of originUnited Stateso" v vM#jD"H̀㓉MissionTelecommunicationsZ? v vA#R2"Perigee/Apogee770 kmV v^ vA#R*Inclination86.4L  v vA#RRAAN27o"^ v vM#jD" &㉓gLaunch vehicleProton #249B v[ v$ <Currently on reserve orbit8 v v' "(Technical dataM[ v v0 0:_ <ƉSpecificationsPayload; vv1vbvBvIridium 12G vbv5 :&\I" Iridium 12?vv# 8Also called Iridium SV0121 bvv'  Generalg v9vG#^@") Designation24837 / 97030B\vvA#R6Launch date18 Jun 1997t'9v@vM#jN"N ,㹌לCountry of originUnited v@v vStateso"v@vM#jD"H̀㓉MissionTelecommunications^@v@vA#R:"Perigee/Apogee772/781 kmV@v8AvA#R*Inclination86.4L @vAvA#RRAAN27o"8AvAvM#jD" &㉓gLaunch vehicleProton #249&AvBv# 8AvQBv' "(Technical dataMBvBv0 0:_ <ƉSpecificationsPayload; QBvBv1aBv CvPGvIridium 13GBv Cv5 :&\I" Iridium 13?Bv_Cv# 8Also called Iridium SV0131 CvCv'  Generalg _CvCvG#^@") Designation24840 / 97030E\CvSDvA#R6Launch date18 Jun 1997t'CvDvM#jN"N ,㹌לCountry of originUnited Stateso"SDv6EvM#jD"H̀㓉MissionTelecommunications^DvEvA#R:"Perigee/Apogee774/780 kmV6EvEvA#R*Inclination86.4L Ev6FvA#RRAAN27o"EvFvM#jD" &㉓gLaunch vehicleProton #249&6FvFv# 8FvGv' "(Technical dataMFvPGv0 0:_ <ƉSpecificationsPayload; GvGv1aGvGvLvIridium 14GPGvGv5 :&\I" Iridium 14?GvHv# 8Also called Iridium SV0141 GvBHv'  Generalg HvHvG#^@") Designation24836 / 97030A\BHvIvA#R6Launch date18 Jun 1997t'HvyIvM#jN"N ,㹌לCountry of originUnited Stateso"IvIvM#jD"H̀㓉MissionTelecommunications^yIvFJvA#R:"Perigee/Apogee775/778 kmVIvJvA#R*Inclination86.4L FJvJvA#RRAAN27o"JvWKvM#jD" &㉓gLaunch vehicleProton #249&Jv}Kv# 8WKvKv' "(Technical dataM}KvLv0 0:_ <ƉSpecificationsPayload; Kv=Lv1=LvLvvIridium 15GLvLv5 :&\I" Iridium 15?=LvLv# 8Also called Iridium SV0151 LvLv'  Generalg Lv[MvG#^@") Designation24869 / 97034A[LvMvA#R4Launch date9 Jul 1997t'[Mv*NvM#jN"N ,㹌לCountry of originUnited Stateso"MvNvM#jD"H̀㓉MissionTelecommunicationsZ*NvNvA#R2"Perigee/Apogee780 kmVNvIOvA#R*Inclination86.4L NvOvA#RRAAN58n!IOvvM#jB" &p㉂Launch vehicleDelta #24OvvLv4_Ovv* $㉓gWas to be launched with Proton #249 but was dropped during a loading operation in the US.8vЀv' "(Technical dataMvv0 0:_ <ƉSpecificationsPayload; ЀvXv1aLXvvυvIridium 16Gvv5 :&\I" Iridium 16?Xvށv# 8Also called Iridium SV0161 vv'  Generalg ށvvvG#^@") Designation24841 / 97030F\v҂vA#R6Launch date18 Jun 1997t'vvFvM#jN"N ,㹌לCountry of originUnited Stateso"҂vvM#jD"H̀㓉MissionTelecommunications^FvvA#R:"Perigee/Apogee775/779 kmVvivA#R*Inclination86.4L vvA#RRAAN26o"iv$vM#jD" &㉓gLaunch vehicleProton #249&vJv# 8$vv' "(Technical dataMJvυv0 0:_ <ƉSpecificationsPayload; v v1[L! vQv{vIridium 17GυvQv5 :&\I" Iridium 17? vv# 8Also called Iridium SV0171 Qvv'  Generalg v(vG#^@") Designation24870 / 97034B[vvA#R4Launch date9 Jul 1997t'(vvM#jN"N ,㹌לCountry of originUnited Stateso"vfvM#jD"H̀㓉MissionTelecommunicationsZvvA#R2"Perigee/Apogee780 kmVfvvA#R*Inclination86.4L vbvA#RRAAN58n!vЉvM#jB" &p㉂Launch vehicleDelta #244&bvv# 8Љv.v' "(Technical dataMv{v0 0:_ <ƉSpecificationsPayload; .vv1[vv'vIridium 18G{vv5 :&\I" Iridium 18?vyA#R*Inclination86.4M yyA#RRAAN292n!>yyM#jB" &p㉂Launch vehicleDelta #251&yy# 8yWy' "(Technical dataMyy0 0:_ <ƉSpecificationsPayload; Wyy1\ y&yQyIridium 50Gy&y5 :&\I" Iridium 50?yey# 8Also called Iridium SV0501 &yy'  Generalg eyyG#^@") Designation25169 / 98010A\yYyA#R6Launch date18 Feb 1998t'yyM#jN"N ,㹌לCountry of originUnited Stateso"Yy<yM#jD"H̀㓉MissionTelecommunicationsZyyA#R2"Perigee/Apogee780 kmV<yyA#R*Inclination86.4L y8yA#RRAAN26n!yyM#jB" &p㉂Launch vehicleDelta #255&8yy# 8yy' "(Technical dataMyQy0 0:_ <ƉSpecificationsPayload; yy1cyy yIridium 51GQyy5 :&\I" Iridium 51?y y# 8Also called Iridium SV0511 yC y'  Generalg  y yG#^@") Designation25262 / 98018A\C y yA#R6Launch date25 Mar 1998t' yz yM#jN"N ,㹌לCountry of originUnited Stateso" y yM#jD"H̀㓉MissionTelecommunicationsZz yC yA#R2"Perigee/Apogee780 kmV y yA#R*Inclination86.4M C y yA#RRAAN355t' yZ yM#jN" &9+SLaunch vehicleLong March 2 #48& y y# 8Z y y' "(Technical dataM y y0 0:_ <ƉSpecificationsPayload; y@ y1dr@ y yAyIridium 52G y y5 :&\I" Iridium 52?@ y y# 8Also called Iridium SV0521 y y'  Generalg y^yG#^@") Designation25171 / 98010C\ yyA#R6Launch date18 Feb 1998t'^y.yM#jN"N ,㹌לCountry of originUnited Stateso"yyM#jD"H̀㓉MissionTelecommunicationsZ.y @yA#R2"Perigee/Apogee780 kmy @y yVyb@yA#R*Inclination86.4L @y@yA#RRAAN26n!b@yAyM#jB" &p㉂Launch vehicleDelta #255&@yBAy# 8AyzAy' "(Technical dataMBAyAy0 0:_ <ƉSpecificationsPayload; zAyBy1\ByIBytFyIridium 53GAyIBy5 :&\I" Iridium 53?ByBy# 8Also called Iridium SV0531 IByBy'  Generalg By CyG#^@") Designation25172 / 98010D\By|CyA#R6Launch date18 Feb 1998t' CyCyM#jN"N ,㹌לCountry of originUnited Stateso"|Cy_DyM#jD"H̀㓉MissionTelecommunicationsZCyDyA#R2"Perigee/Apogee780 kmV_DyEyA#R*Inclination86.4L Dy[EyA#RRAAN26n!EyEyM#jB" &p㉂Launch vehicleDelta #255&[EyEy# 8Ey'Fy' "(Technical dataMEytFy0 0:_ <ƉSpecificationsPayload; 'FyFy1\r8FyFy!KyIridium 54GtFyFy5 :&\I" Iridium 54?Fy5Gy# 8Also called Iridium SV0541 FyfGy'  Generalg 5GyGyG#^@") Designation25173 / 98010E\fGy)HyA#R6Launch date18 Feb 1998t'GyHyM#jN"N ,㹌לCountry of originUnited Stateso")Hy IyM#jD"H̀㓉MissionTelecommunicationsZHyfIyA#R2"Perigee/Apogee780 kmV IyIyA#R*Inclination86.4L fIyJyA#RRAAN26n!IyvJyM#jB" &p㉂Launch vehicleDelta #255&JyJy# 8vJyJy' "(Technical dataMJy!Ky0 0:_ <ƉSpecificationsPayload; Jy\Ky1]H\KyKy yIridium 55G!KyKy5 :&\I" Iridium 55?\KyKy# 8Also called Iridium SV0551 KyLy'  Generalg KyzLyG#^@") Designation25272 / 98019A\LyLyA#R6Launch date30 Mar 1998t'zLyJMyM#jN"N ,㹌לCountry of originUnited Stateso"LyMyM#jD"H̀㓉MissionTelecommunicationsZJMyNyA#R2"Perigee/Apogee780 kmVMyiNyA#R*Inclination86.4M NyNyA#RRAAN323n!iNy$OyM#jB" &p㉂Launch vehicleDelta #256&NyJOy# 8$OyOy' "(Technical dataMJOy y0 0:_ <ƉSpecificationsPayloadOy y!Ky; OyGy1\GyyyIridium 56G yy5 :&\I" Iridium 56?Gỳy# 8Also called Iridium SV0561 yy'  Generalg ̀yeyG#^@") Designation25170 / 98010B\yyA#R6Launch date18 Feb 1998t'ey5yM#jN"N ,㹌לCountry of originUnited Stateso"yyM#jD"H̀㓉MissionTelecommunicationsZ5yyA#R2"Perigee/Apogee780 kmVyTyA#R*Inclination86.4L yyA#RRAAN26n!TyyM#jB" &p㉂Launch vehicleDelta #255&y4y# 8yly' "(Technical dataM4yy0 0:_ <ƉSpecificationsPayload; lyy1]y;ygyIridium 57Gy;y5 :&\I" Iridium 57?yzy# 8Also called Iridium SV0571 ;yy'  Generalg zyyG#^@") Designation25273 / 98019B\ynyA#R6Launch date30 Mar 1998t'yyM#jN"N ,㹌לCountry of originUnited Stateso"nyQyM#jD"H̀㓉MissionTelecommunicationsZyyA#R2"Perigee/Apogee780 kmVQyyA#R*Inclination86.4M yNyA#RRAAN323n!yyM#jB" &p㉂Launch vehicleDelta #256&Nyy# 8yy' "(Technical dataMygy0 0:_ <ƉSpecificationsPayload; yy1]HyyyIridium 58Ggyy5 :&\I" Iridium 58?y(y# 8Also called Iridium SV0581 yYy'  Generalg (yyG#^@") Designation25274 / 98019C\YyyA#R6Launch date30 Mar 1998t'yyM#jN"N ,㹌לCountry of originUnited Stateso"yyM#jD"H̀㓉MissionTelecommunicationsZyYyA#R2"Perigee/Apogee780 kmVyyA#R*Inclination86.4M YyyA#RRAAN323n!yjyM#jB" &p㉂Launch vehicleDelta #256&yy# 8jyȍy' "(Technical dataMyy0 0:_ <ƉSpecificationsPayload; ȍyPy1~PyyyIridium 59Gyy5 :&\I" Iridium 59?Py֎y# 8Also called Iridium SV0591 yy'  Generalg ֎ynyG#^@") Designation25275 / 98019D\yʏyA#R6Launch date30 Mar 1998t'nyJyM#jN"N ʏyJyy,㹌לCountry of originUnited Stateso"ʏyyM#jD"H̀㓉MissionTelecommunicationsZJyyA#R2"Perigee/Apogee780 kmVyiyA#R*Inclination86.4M yyA#RRAAN323n!iy$yM#jB" &p㉂Launch vehicleDelta #256&yJy# 8$yy' "(Technical dataMJyy0 0:_ <ƉSpecificationsPayload; y y1]F yQy}yIridium 60GyQy5 :&\I" Iridium 60? yy# 8Also called Iridium SV0601 Qyy'  Generalg y(yG#^@") Designation25276 / 98019E\yyA#R6Launch date30 Mar 1998t'(yyM#jN"N ,㹌לCountry of originUnited Stateso"ygyM#jD"H̀㓉MissionTelecommunicationsZyyA#R2"Perigee/Apogee780 kmVgyyA#R*Inclination86.4M ydyA#RRAAN323n!yyM#jB" &p㉂Launch vehicleDelta #256&dyy# 8y0y' "(Technical dataMy}y0 0:_ <ƉSpecificationsPayload; 0yy1c8yy1yIridium 61G}yy5 :&\I" Iridium 61?y>y# 8Also called Iridium SV0611 yoy'  Generalg >yyG#^@") Designation25263 / 98018B\oy2yA#R6Launch date25 Mar 1998t'yyM#jN"N ,㹌לCountry of originUnited Stateso"2yyM#jD"H̀㓉MissionTelecommunicationsZyoyA#R2"Perigee/Apogee780 kmVyyA#R*Inclination86.4M oyyA#RRAAN355t'yyM#jN" &9+SLaunch vehicleLong March 2 #48&yy# 8yy' "(Technical dataMy1y0 0:_ <ƉSpecificationsPayload; yly1]1lyyzIridium 62G1yy5 :&\I" Iridium 62?lyy# 8Also called Iridium SV0621 y#y'  Generalg yyG#^@") Designation25285 / 98021A[#yyA#R4Launch date7 Apr 1998t'yYyM#jN"N ,㹌לCountry of originUnited Stateso"yyM#jD"H̀㓉MissionTelecommunicationsZYy"yA#R2"Perigee/Apogee780 kmVyxyA#R*Inclination86.4M "yyA#RRAAN260o"xy@zM#jD" y@z1y&㉓gLaunch vehicleProton #256&yfz# 8@zz' "(Technical dataMfzz0 0:_ <ƉSpecificationsPayload; z&z1]Fz&zmzzIridium 63Gzmz5 :&\I" Iridium 63?&zz# 8Also called Iridium SV0631 mzz'  Generalg zDzG#^@") Designation25286 / 98021B[zzA#R4Launch date7 Apr 1998t'DzzM#jN"N ,㹌לCountry of originUnited Stateso"zzM#jD"H̀㓉MissionTelecommunicationsZzzA#R2"Perigee/Apogee780 kmVz2zA#R*Inclination86.4M zzA#RRAAN260o"2zzM#jD" &㉓gLaunch vehicleProton #256&zz# 8zLz' "(Technical dataMzz0 0:_ <ƉSpecificationsPayload; Lzz1]1zzG zIridium 64Gzz5 :&\I" Iridium 64?zZz# 8Also called Iridium SV0641 zz'  Generalg ZzzG#^@") Designation25287 / 98021C[zMzA#R4Launch date7 Apr 1998t'zzM#jN"N ,㹌לCountry of originUnited Stateso"Mz0zM#jD"H̀㓉MissionTelecommunicationsZzzA#R2"Perigee/Apogee780 kmV0zzA#R*Inclination86.4M z- zA#RRAAN260o"z zM#jD" &㉓gLaunch vehicleProton #256&- z z# 8 z z' "(Technical dataM zG z0 0:_ <ƉSpecificationsPayload; z z1]z  z zzIridium 65GG z z5 :&\I" Iridium 65? z z# 8Also called Iridium SV0651 z9 z'  Generalg  z zG#^@") Designation25288 / 98021D[9 z zA#R4Launch date7 Apr 1998t' zo zM#jN"N ,㹌לCountry of originUnited Stateso" z zM#jD"H̀㓉MissionTelecommunicationsZo z8 zA#R2"Perigee/Apogee780 kmV z zA#R*Inclination86.4M 8 z zA#RRAAN260o" zJzM#jD" &㉓gLaunch vehicleProton #256& zpz# 8Jzz' "(Technical dataMpzz0 0:_ <ƉSpecificationsPayload; z0z1]0zwzCzIridium 66Gzwz5 :&\I" Iridium 66?0zz# 8Also called Iridium SV0621 wz @z'  Generalz @zzg zs@zG#^@") Designation25289 / 98021E[ @z@zA#R4Launch date7 Apr 1998t's@zBAzM#jN"N ,㹌לCountry of originUnited Stateso"@zAzM#jD"H̀㓉MissionTelecommunicationsZBAz BzA#R2"Perigee/Apogee780 kmVAzaBzA#R*Inclination86.4M BzBzA#RRAAN260o"aBzCzM#jD" &㉓gLaunch vehicleProton #256&BzCCz# 8Cz{Cz' "(Technical dataMCCzCz0 0:_ <ƉSpecificationsPayload; {CzDz1] YDzJDzvHzIridium 67GCzJDz5 :&\I" Iridium 67?DzDz# 8Also called Iridium SV0671 JDzDz'  Generalg Dz!EzG#^@") Designation25290 / 98021F[Dz|EzA#R4Launch date7 Apr 1998t'!EzEzM#jN"N ,㹌לCountry of originUnited Stateso"|Ez_FzM#jD"H̀㓉MissionTelecommunicationsZEzFzA#R2"Perigee/Apogee780 kmV_FzGzA#R*Inclination86.4M Fz\GzA#RRAAN260o"GzGzM#jD" &㉓gLaunch vehicleProton #256&\GzGz# 8Gz)Hz' "(Technical dataMGzvHz0 0:_ <ƉSpecificationsPayload; )HzHz1]HzHz$MzIridium 68GvHzHz5 :&\I" Iridium 68?Hz7Iz# 8Also called Iridium SV0681 HzhIz'  Generalg 7IzIzG#^@") Designation25291 / 98021G[hIz*JzA#R4Launch date7 Apr 1998t'IzJzM#jN"N ,㹌לCountry of originUnited Stateso"*Jz KzM#jD"H̀㓉MissionTelecommunicationsZJzgKzA#R2"Perigee/Apogee780 kmV KzKzA#R*Inclination86.4M gKz LzA#RRAAN260o"KzyLzM#jD" &㉓gLaunch vehicleProton #256& LzLz# 8yLzLz' "(Technical dataMLz$Mz0 0:_ <ƉSpecificationsPayload; Lz_Mz1oY_MzMzzIridium 69G$MzMz5 :&\I" Iridium 69?_MzMz# 8Also called Iridium SV0691 MzNz'  Generalg Mz}NzG#^@") Designation25319 / 98026A[NzNzA#R4Launch date2 May 1998t'}NzLOzM#jN"N ,㹌לCountry of originUnited Stateso"NzOzM#jD"H̀㓉MissionTelecommunicationsZLOz!zA#R2"PerOz!z$Mzigee/Apogee780 kmVOzwzA#R*Inclination86.4M !zĀzA#RRAAN355t'wz8zM#jN" &9+SLaunch vehicleLong March 2 #49&Āz^z# 88zz' "(Technical dataM^zz0 0:_ <ƉSpecificationsPayload; zz1Z zezzIridium 70Gzez5 :&\I" Iridium 70?zz# 8Also called Iridium SV0701 ezՂz'  Generalg z"N ,&‰Country of originIndiak { {M#j<"H̀郉MissionRemote sensing^2 { {A#R:"Perigee/Apogee893/913 kmV {Q {A#R*Inclination98.8U { {A#R(Period103.1 minbQ {{G#^6" &Launch vehicleVostokY {a{A#R0Launch siteTyuratamZ{{A#R2"Mass at launch960 kgqMa{,{$ First commercial satellite launched by the CIS's organization Glavcosmos.8{d{' "(Technical dataM,{{0 0:ΈOB䉂SpecificationsPayload7d{ @{1l< @{S@{D{IRS 1B{ @{{G{S@{8 @ c%" IRS 1B1 @{@{'  Generalg S@{@{G#^@") Designation21688 / 91061A\@{GA{A#R6Launch date29 Aug 1991l@{A{M#j>"N ,&‰Country of originIndiakGA{B{M#j<"H̀郉MissionRemote sensing^A{|B{A#R:"Perigee/Apogee890/917 kmVB{B{A#R*Inclination99.1U|B{'C{A#R(Period103.1 minbB{C{G#^6" &Launch vehicleVostokY'C{C{A#R0Launch siteTyuratam&C{D{# 8C{@D{' "(Technical dataMD{D{0 0:ΈOB䉂SpecificationsPayload7@D{D{1Y\7D{ E{3H{IRS 1EGD{ E{8 @ c%" IRS 1E1 D{"N ,&‰Country of originIndiakE{oF{M#j<"H̀郉MissionRemote sensingkF{F{M#j<" &#Launch vehiclePSLV #1&oF{G{# 5F{5G{'  End of life_G{G{A#R<"Out of service20 Sep 1993{:5G{H{A#RtCauselauncher failure, the payload ended in the ocean$G{3H{" 7H{jH{1 <jH{H{u{IRS P2G3H{H{8 @ c%" IRS P21 jH{H{'  Generalg H{II{G#^@") Designation23323 / 94068A\H{I{A#R6Launch date15 Oct 1994lII{J{M#j>"N ,&‰Country of originIndiakI{|J{M#j<"H̀郉MissionRemote sensing^J{J{A#R:"Perigee/Apogee818/820 kmV|J{0K{A#R*Inclination98.7UJ{K{A#R(Period102.3 mink0K{K{M#j<" &#Launch vehiclePSLV #2K{L{% The spacecraft is in a Sun-synchronous orbit and carries a linear imaging self-scanner camera. The images will be marketed through a private company in the U.S.A. An X-ray telescope is also onboard for astronomical observations.8K{6M{' "(OTechnical data8L{nM{' " SpecificationsZ6M{M{A#R2&Prime contractorISROSnM{N{A#R$PlatformIRS PZM{uN{A#R2"Mass at launch870 kgSN{N{A#R$ Mass in orbitL uN{O{A#RLengthK N{_O{A#RWidthL O{O{A#RHeightY_O{{A#R0 Stabilization3 axO{{3H{isN O{^{A#RDC powerU{{A#R($Design lifetime&^{ـ{# pI{I{'  LISS 2 A & B (2 identical push-broom scanners with CCD detector arraysYـ{{E#X)Wavebands0.45-0.52 m (visible): sedimetation and coastal studies0.52-0.59 m (visible): vegetation. rock and soil discremination0.62-0.68 m (visible): chlorophyll absorption in vegetation. rock/soil0.77-0.86 m (IR): moisture in vegetation. land/water discreminationYI{{A#R0Resolution32 x 37 mV{Q{A#R*Swath width67 km${u{" 7Q{{1!7{{{IRS 1CGu{{8 @ c%" IRS 1C1 {${'  Generalg {{G#^@") Designation23751 / 95072Ah'${{A#RNLaunch date28 Dec 1995 at 06:45 UTl{_{M#j>"N ,&‰Country of originIndiak{ʅ{M#j<"H̀郉MissionRemote sensingG_{R{A#R"Perigee/Apogee816/818 km (sun-synchronous, Descending node: 10:30)Vʅ{{A#R*Inclination98.6e$R{ {A#RHPeriod101 min (revisit: 5 days)e{r{G#^<" &Launch vehicleMolniya MY {ˇ{A#R0Launch siteTyuratamr{{/ ,IJ[This was the first Russian launch into a retrograde (99 degree) orbit using the Molniya-M four stage rocket; earlier Russian retrograde launches used the Vostok rocket which has now been retired. The The Block-I third stage appears to have been suborbital, the first time such a flight profile has been used.Launched by Glavkosmos, Russia's commercial space organisation. The launch contract between Russia and India cost 60 billion roubles ($12.9 million). The American Eosat company has a contract to commercially distribute the data generated by this satellite so as the 9 other remote sensing satellites to be launched by ISRO during the 10-year period ending 2005. This contract is worth a billion dollar. Eosat has been receiving data from IRS 1B since June 1994 and from IRS-P2 since march this year on an experimental basis. Its ground station at Norman in Oklahoma was the first to receive IRS data outside India.<ˇ{ڋ{' *O External resourcesD{{' :http://www.stph.net/nrsa/8ڋ{V{' "(OTechnical data8{{' " SpecificationsZV{{A#R2&Prime contractorISRON {6{A#RPlatform[{{A#R4"Mass at launch1250 kgS6{{A#R$ Mass in orbita {E{A#R@Dimension1.65 x 1.5 x 2.1 mW{{A#R,Solar array9.6 mYE{{A#R0 Stabilization3 axisS{H{A#R$DC power809 W\{{A#R6$Design lifetime3 years&H{ʏ{# oB{E{- *  LISS 3 (ʏ{E{u{Linear Imaging Self Scanner) with CCD detector arraysiʏ{{D#X0WavebandsGreen: 0.52-0.59 mRed: 0.62-0.68 mNear Infrared: 0.77-0.86 mSW Infrared: 1.55-1.70 mo.E{a{A#R\0Resolution23.6 m except for SW IR: 70.8 mp/{{A#R^0Swath width142 km except for SW IR: 148 km&a{{# .{%{'  WiFS7{{Z#n0@WavebandsRed: 0.62-0.68 mNear IR: 0.77-0.86 mU%{ {A#R(0Resolution189 mW{b{A#R,0Swath width810 km& {{# 6b{{'  PanchromaticZ{{A#R20Wavebands0.5-0.75 mT{l{A#R&0Resolution10 mV{{A#R*0Swath width70 km&l{{# 7{{1 {f{W|IRS P3G{f{8 @ c%" IRS P31 {{'  Generalg f{{G#^@") Designation23827 / 96017A\{Z{A#R6Launch date21 Mar 1996l{{M#j>"N ,&‰Country of originIndiakZ{1{M#j<"H̀郉MissionRemote sensingF{{A#R"Perigee/Apogee802/848 km (sunsynchronous, descending node: 10:30)V1{{A#R*Inclination98.8L {Z{A#RPeriodk{{M#j<" &#Launch vehiclePSLV #3ZZ{{A#R2"Mass at launch930 kg&{E{# 8{}{' "(OTechnical data8E{{' " SpecificationsZ}{{A#R2&Prime contractorISRON {]{A#RPlatformZ{{A#R2"Mass at launch922 kgS]{ {A#R$ Mass in orbitO{Y{A#RDimensionW {{A#R,Solar array9.6 mYY{ {A#R0 Stabilization3 axisS{\{A#R$DC power817 WU {{A#R($Design lifetime&\{{# /{{'  MOS Ah'{n{A#RN0"Spectral range755-768 nm (4 bands)[{{A#R40Resolution1569x1395 mWn{ {A#R,0Swath width195 km&{F{# / {u{'  MOS Bj)F{{A#RR0"Spectral range408-1010 nm (13 bands)Yu{8{A#R00Resolution523x523 mW{{A#R,0Swath width200 km&8{{# /{ |'  MOS C{ |{i({u|A#RP0"Spectral range1500-1700 nm (1 band)Y ||A#R00Resolution523x644 mWu|%|A#R,0Swath width192 km&|K|# .%|y|'  WiFSKK||[#0@WavebandsRed: 0.62-0.68 mNear IR: 0.77-0.86 mSW IR: 1.55-1.70 mUy|t|A#R(0Resolution189 mW||A#R,0Swath width810 km&t||# fC|W|# X-ray astronomy payload: PPC range: 2-20 keV, XSM range: 2-8 keV7||1Y|| B|IRS 1DGW||8 @ c%" IRS 1D1 ||'  Generalg |m|G#^@") Designation24971 / 97057A\||A#R6Launch date29 Sep 1997lm|5|M#j>"N ,&‰Country of originIndiak||M#j<"H̀郉MissionRemote sensingF5|'|A#R"Perigee/Apogee736/825 km (sunsynchronous, descending node: 10:30)V|}|A#R*Inclination98.6h''||A#RNPeriod101.35 min (revisit: 5 days)k}|P|M#j<" &#Launch vehiclePSLV #4[||A#R4"Mass at launch1200 kgqDP| |- (YTIs a clone of IRS 1C with a few minor improvements. It will server as in-orbit replacement for IRS 1C. Should have a 5.8 m resolution and an 800 km swathWas launched in a bad orbit: 300 x 823 km The correction to the initial orbit would have consumed too much fuel so the satellite was placed in an elliptical orbit.8|T |' "(OTechnical data8 | |' " SpecificationsZT | |A#R2&Prime contractorISRON |4 |A#RPlatform[ | |A#R4"Mass at launch1250 kgS4 | |A#R$ Mass in orbita |C |A#R@Dimension1.65 x 1.5 x 2.1 mW | |A#R,Solar array9.6 mYC | |A#R0 Stabilization3 axisS |F |A#R$DC power809 W\ | |A#R6$Design lifetime3 years&F | |# oB |7 |- *  LISS 3 (Linear Imaging Self Scanner) with CCD detector arraysi | |D#X0WavebandsGreen: 0.52-0.59 mRed: 0.62-0.68 mNear Infrared: 0.77-0.86 mSW Infrared: 1.55-1.70 mk*7 |O|A#RT0Resolution23 m except for SW IR: 70 mp/ ||A#R^0Swath width142 km except for SW IR: 148 km&O||# .||'  WiFS7||Z#n0@WavebandsRed: 0.62-0.68 mNear IR: 0.77-0.86 mU| @|A#R(0Resolution189 m| @|W|W|c@|A#R,0Swath width774 km& @|@|# 6c@|@|'  PanchromaticZ@|A|A#R20Wavebands0.5-0.75 mT@|mA|A#R&0Resolution10 mVA|A|A#R*0Swath width70 kmImA| B|* $>SHas a 4.5 kg GPS receiver7A|CB|1VCB|B|F|IRS P4G B|B|8 @ c%" IRS P4;CB|B|# 0Also called Ocean Sat1 B|B|'  GeneralYB|OC|G#^$") DesignationUB|C|A#R(Launch date1997lOC|D|M#j>"N ,&‰Country of originIndiakC|{D|M#j<"H̀郉MissionRemote sensingTD|D|A#R&"Perigee/ApogeeQ{D| E|A#R InclinationL D|lE|A#RPeriodc E|E|G#^8" &Launch vehiclePSLV C2TlE|#F|A#R&"Mass at launchhE|F|$ with an Ocean sensor and LISS 3 instrument. A 100 kg piggybacked payload from Korea will be included1#F|F|1WF|4G|ZG|T+F|4G|) "VȠ$To view this page you need to register&F|ZG|# 74G|G|1vkG|G|I|IRS P5GZG|G|8 @ c%" IRS P5EG|I|( ;Also called Carto Sat or Cartosat 1planned in 1999-2000, to be launched by PSLVWould have a pan camera with 1 or 2.5 metre resolution and a 10 to 12 km swath capability and would be mainly useful for map making and terrain modelling. Other sources claim steerable swath of 30 km1G|NI|1WNI|I|I|T+I|I|) "VȠ$To view this page you need to register&NI|I|# 7I|I|1I|FJ|K|IRS P6GI|FJ|8 @ c%" IRS P6a9I|K|( sAlso called Resource Sat or Resourcesatplanned in 2000-2001, environnemental satellite, to be launched by PSLVWould have a 3-band spectral camera with a 6 m resolution and could be used for select mapping with its advance wide field sensor. It would be very effective during floods with its 1,400 km swath.1FJ|K|1WK|,L|RL|T+K|,L|) "VȠ$To view this page you need to register&K|RL|# 7,L|L|1kL|L|M|IRS 2AGRL|L|8 @ c%" IRS 2AN%L|M|) "J#to be launched in 1999 by a PSLV1L|OM|1WOM|M|M|T+M|M|) "VȠ$To view this page you need to register&OM|M|# 4M|M|1F҃MM|1N|Y|IRT4M|1N|, (" IRT1 M|bN|'  Generalg 1N|N|G#^@") Designation14689 / 84011C[bN|$O|A#R4Launch date5 Feb 1984t'N|O|M#jN"N ,㹌לCountry of originUnited States_$O| |G#^0"H̀MissionScientificO| |M|^O|j|A#R:"Perigee/Apogee279/288 kmV ||A#R*Inclination28.5Tj||A#R&Period90.2 minj|~|M#j:" &"Launch vehicleSTS 11|G|% IIRT was a inflatable balloon to be used as a rendezvous target to get practise for shuttle rendezvous manoeuvres. IRT blow appart shortly after beeing released.5~|||'  End of lifec"G|߂|A#RDCauseRetrieved by the ShuttleV||5|A#R*Decay11 Feb 1984$߂|Y|" > 5||1Ej|||Program: ISEENY||8 @.G" Program: ISEE!||+ $ International Sun Earth ExplorerInternational scientific programThe 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.<|B|' * External resources^7||' nhttp://uss-enterprise.bu.edu/BUSPACE/ISEE/isee.html1B|х|1х|0|_%|0|: DJ ֋UTVTProgram: ISEEISEE 1ISEE 27х|g|1wg|||ISEE 1G0||8 @ G" ISEE 11 g|߆|'  Generalg |F|G#^@") Designation10422 / 77102A\߆||A#R6Launch date22 Oct 1977t'F||M#jN"N ,<Country of originInternational|/||M#j^"H̀d;plMissionScientific: magnetosphere studya ||A#R@"Perigee/Apogee436/137806 kmV|I|A#R*Inclination12.7T||A#R&Period3441 mins&I||M#jL" &p㉂Launch vehicleThor Delta #1355|E|$ "Built by NASA5|z|'  End of lifeVE|Њ|A#R*Decay26 Sep 1987$z||" 7Њ|+|1x+|r||ISEE 2G|r|8 @ G" ISEE 21 +||'  Generalg r| |G#^@") Designation10423 / 77102B\|f|A#R6Launch date22 Oct 1977t' |ڌ|M#jN"N ,<Country of originInternational|/f|V|M#j^"H̀d;plMissionScientific: magnetosphere studya ڌ||A#R@"Perigee/Apogee406/137765 kmVV| |A#R*Inclination13.5V|c|A#R*Period3438.5 mins& |֎|M#jL" &p㉂Launch vehicleThor Delta #1354c| |$  Built by ESA5֎|?|'  End of lifeV ||A#R*Decay26 Sep 1987$?||" > | |1M |Z||Program: Isis| ||N|Z|8 @.ɝG" Program: IsisY6 ||# lCanadian scientific program for ionospheric studies1Z||1|C|_%|C|: DJ֋TTProgram: IsisIsis 1Isis 27|z|1}ǁz|| |Isis 1GC||8 @ ɝG" Isis 11 z||'  Generalg |Y|G#^@") Designation03669 / 69009A\||A#R6Launch date30 Jan 1969m Y|"|M#j@"N ,xW Country of originCanaday,||M#jX"H̀?vMissionScientific: ionosphere study_"||A#R<"Perigee/Apogee574/3470 kmV|P|A#R*Inclination88.4U||A#R(Period127.7 minr%P||M#jJ" &p㉂Launch vehicleThor Delta #65Z|q|A#R2"Mass at launch237 kg&||# 8q||' "(OTechnical data>| |# 6Transmits on 136.410 MHz7|D|1rD||_|Isis 2G ||8 @ ɝG" Isis 21 D||'  Generalg |#|G#^@") Designation05104 / 71024A[|~|A#R4Launch date1 Apr 1971m #||M#j@"N ,xW Country of originCanaday,~|d|M#jX"H̀?vMissionScientific: ionosphere study`||A#R>"Perigee/Apogee1353/1423 kmVd||A#R*Inclination88.5U|o|A#R(Period113.5 minr%||M#jJ" &p㉂Launch vehicleThor Delta #84Zo|;|A#R2"Mass at launch262 kg$|_|" 4;||1jF||w }ISO4_||, (" ISO@||# :Infrared Space Observatory1 |8|'  Generalg ||G#^@") Designation23715 / 95062A\8||A#R6Launch date17 Nov 1995m |h|M#j@"N ,4"Country of originEurope?||G#^~OperatorESTEC (European Space TEchnology Center) for ESAu(h|c|M#jP"H̀_BMissionScientific: IR astronomya ||A#R@"Perigee/Apogee1036/70578 kmUc||A#R(Inclination5.2T|m|A#R&Period1436 minn!||M#jB" &E+Launch vehicleAriane V804 m|}' The primary objectives of the Infrared Space Observatory are to provide spectroscopic, photometric, imaging, and polarimetric observations of selected celestial sources at infrared wavelengths from 2.3 um to 200 um with the highest possible sensitivity|}_| and spatial resolution. The instruments are cooled at -270C in a cryostat which contained 2400 liters of superfluid helium at liftoff.The satellite was initially planned for 1993 but the mission was delayed for two years while engineers worked on problems related to the temperature control system. The two-year delay added 20 percent to the project's final cost of $850 million for the satellite and launch. US astronomers will be granted 20 percent of the ISO's observation time in exchange for ground station support. R.|m}$ \The first light image was taken on Nov 28.5}}'  End of life^m}}A#R:"Out of service8 Apr 1998Y}Y}A#R0Causelack of heliumK }}A#RDecayY}m}% IThe helium consumption was smaller than planned; this enabled the satellite to operate during 28 months. The satellite was deorbited and shutoff on 16 May 1998.<}}' *O External resourcesEm}}' <http://isowww.estec.esa.nl8}&}' "(Technical data8}^}' " Specificationsb!&}}A#RB&Prime contractorAerospatialeN ^}}A#RPlatform[}i}A#R4"Mass at launch2498 kgY}}A#R0Payload mass1515 kgZi}}A#R2 Mass in orbit2418 kgc"}}A#RDDimension3.56 x 2.77 x 5.31 mQ}}A#R Solar arrayY})}A#R0 Stabilization3 axisN }w}A#RDC power^)}}A#R:$Design lifetime1.5 yearstOw}I }% Telemetry: 2266.5 MHz (4, 8, 16 & 32 kbps)Command: 2087.069 MHz (2000 bps)>} }' . Cassegrain telescopeSI } }A#R$Diameter0.6 mW }1 }A#R,Focal length9.0 mR } }A#R"CameraISOCAMd#1 } }A#RF,Temperature control3K (-270C)8 } }' "O Other payloadsi } }% Imaging photopolarimeter: ISOPHOTLong Wavelength Spectrometer: LWSShort Wavelength Spectrometer: SWS9 } }' $ Frequency bandsS }9 }A#R$ISOCAM3-17 mU } }A#R(ISOPHOT3-200 mR9 } }A#R" LWS45-180 mP }0 }A#R SWS3-45 mG# }w }$ FPointing stability: 2.7 arcsecs10 } }1W } }"}T+w } }) "VȠ$To view this page you need to register& }"}# A }c}1c}}}Program: ItalsatQ"}}8 @4cX8" Program: Italsatf<c}}* $x ƉItalian experimental satellites operated by Telespazio1}K}1K}}h.}}: D\voGoGProgram: ItalsatItalsat 1Italsat 21K} @}1 @}e@}} @}}Y)}e@}0 0T"Italsat's Ka-band National coverage1 @}@}1@}@}Z*e@}@}0 0V"Italsat's Ka-band Multibeam coverage: @}*A}1Xr*A}tA}}Italsat 1J@}tA}8 @&cX8" Italsat 11 *A}A}'  Generalg tA} B}G#^@") Designation21055 / 91003A\A}hB}A#R6Launch date15 Jan 1991l B}B}M#j>"N ,xECountry of originItalyo"hB}CC}M#jD"H̀‰MissionTelecommunicationsg B}C}G#^@"/ۀ0Geostationary orbit13.2En!CC}D}M#jB" &]D+Launch vehicleAriane V41&C}>D}# 8D}vD}' "(OTechnical data7>D}D}'   EIRP coverageY)vD}E}0 0R=$y-Ka-band NationalKa-band Multibeam8D}>E}' " Specificationsd#E}E}A#RF&Prime contractorSelenia SpazioU>E}E}A#R(PlatformItalsat[E}RF}A#R4"Mass at launch1850 kgZE}F}A#R2 Mass in orbit1122 kgCRF}0G}A#RPayload mass273.4 kg: transponders: 198 kg, antennas: 75.4 kg)`F}G}A#R>Dimension3.5 x 2.7 x 2.3 m\0G}G}A#R6Solar array21.8 m spanYG}EH}A#R0 Stabilization3 axist3G}H}A#RfDC powerEOL: equinox: 1760 W, solstice: 1633 WXEH}I}A#R. Payload power937 W\H}mI}A#R6$Design lifetime6 yearsI}J}' Equipped with 1 (+1 backup) 1 W propagation beacon, EIRP 27 dBW at 20 GHz for telemetryAlso aboard: a 40 GHz beacon phase modulated by a 505 MHz coherent subcarrier, and a polarization-switched (but otherwise unmodulated) 50 GHz beaconM&mI}J}' L Ka-band - National beam (20/30 GHz)XJ}*K}A#R.(Main transponders3YJ}K}A#R0,Backup transpondersV*K}K}A#R*Power20 W (TWTA)UK}.L}A#R(Bandwidth36 MHzm&K}L}G#^L=$CoverageItaly (1.55 x 1.06 deg)V.L}L}A#R*EIRP max46.2 dBWQL}BM}A#R  G/T5.5 dB/Ku4L}M}A#RhPolarizationlinear V (both upload and download)T0BM} N}$ `Those transponders are intended for TV feeds>M}IN}' . Ka-band - Multi beame$ N}N}A#RH(Main transponders6 in 20/60 GHzw5IN}%O}B#Tj,Backup transponders2 in 20/30 GHz4 in 20/60 GHzVN}{O}A#R*Power20 W (TWTA)V%O}O}A#R*Bandwidth120 MHzn'{O}K}G#^NO}K}@}=$CoverageItaly (6 spots of 0.49)TO}}A#R&EIRP max57 dBWRK}}A#R" G/T16.1 dB/Ku4}f}A#RhPolarizationlinear V (both upload and download)?}}% 5The spot beams carry domestic telephone traffic with a total capacity of about 12,000 voice channels. Each beam operates in the SS-TDMA mode with QPSK modulation at 147 Mbits/sec in a 100 MHz RF bandwidth. On-board regeneration (demodulation and remodulation) is provided, and the beams are fully interconnected by a space-division switching matrix. Satellite resources can be allocated on a call-by-call basis or left as assigned until changed by ground control. Reconfiguration is by ground command; the satellite is not autonomous.: f}߃}1WU߃})}X}Italsat 2J})}8 @&cX8" Italsat 21 ߃}Z}'  Generalg )}}G#^@") Designation24208 / 96044A[Z}}A#R4Launch date8 Aug 1996l}}M#j>"N ,xECountry of originItalyo"}}M#jD"H̀‰MissionTelecommunicationsg }^}G#^@"/ۀ0Geostationary orbit16.4En!}̆}M#jB" &=E+Launch vehicleAriane V90{U^}G}& Insured cost (satellite + launch): $200 millionEMS service began on 31 Oct 19968̆}}' "(OTechnical data7G}}'   EIRP coveragew@}-}7 >=$y-yKa-band NationalKa-band MultibeamEMS (L- and Ku-band)8}e}' " Specificationsd#-}Ɉ}A#RF&Prime contractorSelenia SpazioUe}}A#R(PlatformItalsat[Ɉ}y}A#R4"Mass at launch1983 kgZ}Ӊ}A#R2 Mass in orbit1185 kgXy}+}A#R.Payload mass275 kg`Ӊ}}A#R>Dimension3.5 x 2.7 x 2.3 mZ+}}A#R2Solar array24 m spanY}>}A#R0 Stabilization3 axisc"}}A#RDDC powerEOL: solstice: 1990 WY>}}A#R0 Payload power1266 W\}V}A#R6$Design lifetime8 years~<}Ԍ}B#TxBeaconsTelemetry: 18.685 & 2.202 GHzCommand: 2.028 GHz&V}}# =Ԍ}7}' , Ka-band (20/30 GHz)u4}}A#Rh(Main transponders3 national beam + 6 multi-beamY7}}A#R0,Backup transpondersV}[}A#R*Power20 W (TWTA)y7}Ԏ}B#TnBandwidthnational beam: 36 MHzmulti-beam: 110 MHzA[}c}N#l*=$y-Coveragenational beam: Italymulti-beam: Italy (6 spots)w5Ԏ}ڏ}B#TjEIRP maxnational beam: 48 dBWmulti-beam: 54 dBWRc}8}A#R"ڏ}8}}Polarization&ڏ}^}# N'8}}' N European Mobile System (EMS) payloadX^}F}B#T(Main transpondersL-band (1.5/1.6 GHz): 3 (forward)Ku-band (12/14 GHz): 12 (return)O}}A#RPower20 Wn,F}}B#TXBandwidthL-band: 4 MHzKu-band: 0.9 MHz\}_}G#^*yCoverageEuropeo-}}B#TZEIRP maxL-band: 42.5 dBWKu-band: 32 dBWf_}X}$ Payload developed by ESA. part of the capacity is leased to to Nuova Telespazio of the STET Group.1}}1}}NX}}0 0>"Italsat 2's EMS coverage8}}1 Fk}O}~Itamsat@}O}2 4"  ItamsatK"}}) "D䵟Also called IO-26 or Oscar 261 O}}'  Generalg }2}G#^@") Designation22826 / 93061D\}}A#R6Launch date26 Sep 1993l2}}M#j>"N ,xECountry of originItalyo"}i}M#jD"H̀㓉MissionTelecommunications^}}A#R:"Perigee/Apogee789/803 kmVi}}A#R*Inclination98.7U}r}A#R(Period100.8 minn!}}M#jB" &D+Launch vehicleAriane V59&r}}# <}B}' *O External resourcese>}}' |http://joshua.micronet.it/english/itamsat/itamsathome.html8B}}' "(OTechnical data8}}' " Specificationsx7}}A#Rn&Prime contractorAssociazione Radioamatori Italiani_}}A#R<PlatformAmsat-NA Microsat[}I}A#R4"Mass at launch12.5 kgS}}A#R$ Mass in orbitRI}}A#R"Length230 mmQ}?}A#R Width230 mmR}}A#R"Height235 mm[?}}A#R4 StabilizationmagneticN }:}A#RDC power_}}A#R<$Design lifetime7-10 years&:}}# ?}}' 0 Frequency chart (MHz)1}}m#b $ PR Downlink freq.Transponder/BeaconMode{}}j#"435.820?$}}j#H435.8701200 bps PSK Digital&}}# /}g}m#^   LN Uplink freq.Transponder/BeaconMode#} ~j#F145.8751200 bps FM Digitalg} ~}#g}~j#F145.9001200 bps FM Digital# ~&~j#F145.9251200 bps FM Digital#~~j#F145.9501200 bps FM Digital$&~~" 5~ ~1 ~K~~Itos? ~K~2 4"  Itos Ac= ~~& z Improved Tiros Operational Satellite, also called Tiros M1 K~~'  Generalg ~F~G#^@") Designation04320 / 70008A\~~A#R6Launch date23 Jan 1970t'F~~M#jN"N ,㹌לCountry of originUnited Statesh~~~M#j6"H̀l/MissionMeteorology`~~A#R>"Perigee/Apogee1431/1477 kmW~~5~A#R,Inclination101.4S~~A#R$Period115 minr%5~~M#jJ" &p㉂Launch vehicleThor Delta #76Z~T~A#R2"Mass at launch310 kgZ~~* $This satellite is an evolved Tiros: it enables real time observation, night and day.4T~ ~1R k׀ ~H~tB~IUE< ~H~2 4"  IUEH% ~~# J International Ultraviolet Explorer1 H~~'  Generalg ~(~G#^@") Designation10637 / 78012A\~~A#R6Launch date26 Jan 1978t'(~~M#jN"N ,<Country of originInternationalX~P ~A#R.OperatorNASA + ESAu(~ ~M#jP"H̀_BMissionScientific: UV astronomyb!P ~' ~A#RB"Perigee/Apogee30252/41315 kmV ~} ~A#R*Inclination34.5V' ~ ~A#R*Period1435.9 mins&} ~F ~M#jL" &p㉂Launch vehicleThor Delta #132Z ~ ~A#R2"Mass at launch671 kgF ~n ~' OA joint NASA/ESA/SERC (Search and Engineering Research Council) observatory satellite designed for ultraviolet spectrometry of cosmic UV sources. ESA's contribution was the construction of the spacecraft's solar panels and a ground station at Villafranca, Spain.On 1st October 1995 the primary control of the still operating spacecraft was transferred from NASA to ESA. This because of NASA's cost reduction efforts. < ~ ~' *O External resourcescn ~;~. ,http://iuewww.gsfc.nasa.gov/iuedac/iuedac_homepage.htmlhttp://www.vilspa.esa.es/iue/iue.html5 ~p~'  End of life_;~~A#R<"Out of service30 Sep 1996f%p~5~A#RJCauseplanned end of exploitation&~[~# 85~~' "(OTechnical data8[~~' " SpecificationsZ~1@~A#R2~1@~~"Mass at launch644 kgR~@~A#R"Length4.17 mQ1@~@~A#R Width1.45 mV@~*A~A#R*Solar array45 mY@~A~A#R0 Stabilization3 axis\*A~A~A#R6$Design lifetime3 yearsnA~tB~' Payload: 0.45 m diameter UV telescope + 4 spectrographsTelemetry: 138.86 & 2249.0 MHzCommand: 149.0 MHz8A~B~1+B~B~J~Jason 18 tB~B~, (" Jason 11 B~C~'  GeneralYB~nC~G#^$") Designatione$C~C~A#RHLaunch dateplanned in late 1999m nC~@D~M#j@"N ,㱭+Country of originFranceu.C~D~G#^\"H̀MissionScientific: ocean remote sensingT@D~ E~A#R&"Perigee/ApogeeQD~ZE~A#R InclinationL E~E~A#RPeriodl%ZE~F~G#^J" &Launch vehicleprovided by NASAQE~cF~A#R Launch siteTF~F~, (ueIs to replace Topex PoseidonFirst of CNES' Proteus small satellite missions.8cF~G~' "(OTechnical data8F~SG~' " Specificationsb!G~G~A#RB&Prime contractorAerospatialeXSG~ H~A#R.PlatformSpacebus-LZG~gH~A#R2"Mass at launch500 kgS H~H~A#R$ Mass in orbitOgH~ I~A#RDimensionQH~ZI~A#R Solar arrayS I~I~A#R$ StabilizationN ZI~I~A#RDC powerUI~PJ~A#R($Design lifetimejI~J~$ The Poseidon 2 (dual frequency radar altimetry) will be built by Alcatel Telecom for about $29 million1PJ~K~1WK~cK~K~T+J~cK~) "VȠ$To view this page you need to register&K~K~# ?cK~K~1U׀K~L~;M~Program: JcsatOK~L~8 @0✇}" Program: Jcsat$K~;M~, &YgJapanese telecommunication program operated by JSAT (Kabushiki-gaisha Nihon Sateraito Sisutemuzu).It is Japan's first commercial satellite system providing TV and cable distribution, telephony, business services and satellite news gathering.1L~lM~1lM~N~P;M~N~V |ㆺ2ㇺ2㈺2㉺2㊺2㋺2Program: JcsatJcsat 1Jcsat 2Jcsat 3Jcsat 4Jcsat 5Jcsat 61lM~CN~1UCN~с~~BN~N~# >Jcsat 1 & 2's specifications\CN~N~A#R60&Prime contractorHughesTN~5O~A#R&0PlatformHS-393[N~O~A#R40"Mass at launch2280 kgZ5O~ ~A#R20 Mass in orbit1376 kgO~ ~N~TO~`~A#R&0Diameter3.66 mY ~~A#R00Height10 m deployedb!`~~A#RB0 StabilizationSpin stabilizedY~t~A#R00DC powerBOL: 2240 W]~с~A#R80$Design lifetime10 years$t~~" 1с~&~1U&~ф~~;~a~# 0Jcsat 1 & 2's Ku-bandY&~~A#R00(Main transponders32Za~~A#R20,Backup transponders8V~j~A#R*0Power20 W (TWTA)U~~A#R(0Bandwidth27 MHzl+j~+~A#RV0CoverageJapan and offshore territoriesT~~A#R&0EIRP max51 dBWR+~ф~A#R"0Polarization$~~" Y(ф~N~1bN~~~ASC's C-band transponder frequency chartq7~~: Dpback()"  Jcsat 1 & 2's transponder frequency chart (GHz)cN~~# * X v  HorizontalUplinkHorizontalDownlinkTransponderVerticalDownlinkVerticalUplink~E~t#8 414.01625112.26825~Շ~t#8 $12.28325214.03125E~e~t#8 414.04625312.29825Շ~~t#8 $12.31325414.06125e~~t#8 414.07625512.32825~~t#8 $12.34325614.09125~~t#8 414.10625712.35825~5~t#8 $12.37325814.12125~ŋ~t#8 414.13625912.388255~V~t#:"&12.403251014.15125ŋ~~t#:"614.166251112.41825V~x~t#:"&12.433251214.18125~ ~t#:"614.196251312.44825x~~t#:"&12.463251414.21125 ~+~t#:"614.226251512.47825~~t#:"&12.493251614.24125+~Y~t#:~Y~~"614.256251712.50825~~t#:"&12.523251814.27125Y~{~t#:"614.286251912.53825~ ~t#:"&12.553252014.30125{~~t#:"614.316252112.56825 ~.~t#:"&12.583252214.33125~~t#:"614.346252312.59825.~P~t#:"&12.613252414.36125~~t#:"614.376252512.62825P~r~t#:"&12.643252614.39125~~t#:"614.406252712.65825r~~t#:"&12.673252814.42125~%~t#:"614.436252912.68825~~t#:"&12.703253014.45125%~G~t#:"614.466253112.71825~~t#:"&12.733253214.48125$G~~" 1~-~1-~}~P~}~6 <6✇}"Jcsat 1 & 2's EIRP8-~~1~~gJcsat 1H}~~8 @"✇}" Jcsat 11 ~.~'  Generalg ~~G#^@") Designation19874 / 89020A[.~~A#R4Launch date6 Mar 1989l~\~M#j>"N ,bCountry of originJapano"~~M#jD"H̀‰MissionTelecommunicationsb!\~-~A#RB,Geostationary orbitsee belown!~~M#jB" &D+Launch vehicleAriane V29xT-~~$ Due to a leak in the fuel tank, the satellite will reach end of life in mid-1997: ~M~- */ۀ Location~~m#:   " BeginEndPosition#M~d~j#F"68L: 6 Mar 1989Jul 1997150E~~j#<,.Sep 1997Oct 1997148Ed~l~j#,Feb 1998112E&~~# 8l~~' "(Technical dataR~g? Nu)IΉɇ~g}~Y@։EIRP coverage (dBW)SpecificationsKu-bandTransponder frequency chart8~1Ё> zJcsat 2Hg8 @"✇}" Jcsat 21 '  Generalg G#^@") Designation20402 / 90001B[A#R4Launch date1 Jan 1990lFM#j>"N ,bCountry of originJapano"M#jD"H̀‰MissionTelecommunicationsfFG#^>"/ۀ0Geostationary orbit154Ep#M#jF" &^]Launch vehicleTitan 3 #153&# 8' "(Technical dataRz? Nu)IΉɇY@։EIRP coverage (dBW)SpecificationsKu-bandTransponder frequency chart81!C Jcsat 3Hz8 @"✇}" Jcsat 31 +'  Generalg G#^@") Designation23649 / 95043A\+A#R6Launch date29 Aug 1995lZM#j>"N ,bCountry of originJapano"M#jD"H̀‰MissionTelecommunicationsfZ/G#^>"/ۀ0Geostationary orbit128Eu(M#jP" &yjLaunch vehicleAtlas Centaur #94/l' CGTO: 167 km x 81432 km x 23.5In 1995 leases were said to cost 550 million a year for 27 MHz transponders and 600 million a year for 36 MHz transponders.8' "(OTechnical data=l' , EIRP coverage (dBW)E& 0 0*^C-bandKu-band8^ ' " Specifications\&  A#R6&Prime contractorHughesT^  A#R&PlatformHS-601T b A#R&"Mass at launchS  A#R$ Mass in orbitL b  A#RLengthK L A#RWidthL   A#RHeightYL  A#R0 Stabilization3 axisT E A#R&DC power4600 W]  A#R8$Design lifetime12 yearszVE  $ NEC Corp. of Japan is a major subcontractor to Hughes for the payload electronics.0 L '  C-bandY  A#R0(Main transponders12YL  A#R0,Backup transpondersV TA#R*Power34 W (SSPA)U A#R(Bandwidth36 MHzfTG#^>CoverageAsia & AustraliaTcA#R&EIRP max37 dBWXA#R.Polarizationlinear&c# K$8@' H8@z Transponder frequency chart (GHz);@c#v . L HorizontaldownlinkTransponderVerticaldownlink`8@6AR#tC13.960`@AR#t3.980C2`6AAR#tC34.000`AVBR#t4.020C4`ABR#tC54.040`VBCR#t4.060C6`BvCR#tC74.080`CCR#t4.100C8`vC6DR#tC94.120aCDR#t4.140C10a6DDR#tC114.160aDYER#t4.180C12&DE# 1 YEE'  Ku-bandYE FA#R0(Main transponders28YEbFA#R0,Backup transpondersV FFA#R*Power60 W (TWTA)AbF;GB#TBandwidth16 transponders of 27 MHz12 transponders of 36 MHzPFGB#T,Coverage & EIRP maxJapan: 55 dBWEastern Asia, India & Australia: 43-35 dBWX;G%HA#R.PolarizationLinear&GKH# K$%HH' H Transponder frequency chart (GHz)NKH^Iz#Ā . L v HorizontaldownlinkTransponderVerticaldownlinkBandwidth (MHz)vHIc#&K112.25836v^IJJc#&12.288K236vIJc#&K312.30836vJJ6Kc#&12.328K436vJKc#&K512.34836v6K"Lc#&12.368K636vKLc#&K712.38836v"LMc#&12.408K836vLMc#&K912.42836wMMc#( 12.448K1036wMrNc#( K1112.46836wMNc#( 12.488K1236wrN`Oc#( K1312.50827wNOc#( 12.523K1427w`OZc#(OZz K1512.53827wOрc#( 12.553K1627wZHc#( K1712.56827wрc#( 12.583K1827wH6c#( K1912.59827wc#( 12.613K2027w6$c#( K2112.62827wc#( 12.643K2227w$c#( K2312.65827wc#( 12.673K2427wc#( K2512.68827wwc#( 12.703K2627wc#( K2712.71827wwec#( 12.733K2827$" 1e1  S 6 <<㈺2"Jcsat 3's C-band EIRP1>1 >T 6 <>㈺2"Jcsat 3's Ku-band EIRP8>ʇ1> ʇJcsat 4H8 @"✇}" Jcsat 4:ʇL# .Also called Jcsat 1A1 }'  Generalg LG#^@") Designation24732 / 97007A\}@A#R6Launch date17 Feb 1997lM#j>"N ,bCountry of originJapano"@M#jD"H̀‰MissionTelecommunicationsb!}A#RB,Geostationary orbitsee belowm M#j@" &yjLaunch vehicleAtlas 2AS&}# : J- */ۀ Locationԋm#:   " BeginEndPosition$Jbj#H$8:L: 17 Feb 1997Apr 1997141Eԋj#<,.May 1997Feb 1998150Ebjj#,Mar 1998124EtJލ* $ㆺ2Satellite ordered after a Jcsat 1 problem (slight leak) was detected8j' "(OTechnical data8ލN' " Specifications\A#R6&Prime contractorHughesZNA#R2PlatformHS-601 (#58)TXA#R&"Mass at launchSA#R$ Mass in orbitL X A#RLength K WA#RWidthL A#RHeightYWA#R0 Stabilization3 axisTPA#R&DC power5000 W]A#R8$Design lifetime12 yearsT0P$ `Features 4 octagonal communications antennas0 1'  C-bandYA#R0(Main transponders12Y1A#R0,Backup transpondersV9A#R*Power34 W (SSPA)UA#R(Bandwidth36 MHzf9G#^>CoverageAsia & AustraliaTHA#R&EIRP max37 dBWXA#R.Polarizationlinear&H# 1 '  Ku-bandYPA#R0(Main transponders28YA#R0,Backup transpondersBP-B#TPower60 W (TWTA)+ four 90 W (TWTA) for 4 36 MHz transpondersvB#TBandwidth8 transponders of 36 MHz16 transponders of 27 MHz (4 transponders can be switched to 54 MHz with 120 W)P-wB#T,Coverage & EIRP maxJapan: 55 dBWEastern Asia, India & Australia: 43-35 dBWXA#R.PolarizationLinear&w# 8-1 C<-usJcsat 5Hu8 @"✇}" Jcsat 51 -'  Generalg u G#^@") Designation25067 / 97075A[hA#R4Launch date2 Dec 1997l M#j>"N ,bCountry of originJapano"hCM#jD"H̀‰MissionTelecommunications^A#R:,Geostationary orbit150Eo"CM#jD" &zg&\Launch vehicleAriane V103&6# 8n' "(OTechnical data86' " Specifications\nA#R6&Prime contractorHughesTVA#R&PlatformHS-601[A#R4"Mass at launch2982 kgSVA#R$ Mass in orbitL PA#RLengthK A#RWidthL PA#RHeightY@A#R0 Stabilization3 axisTA#R&DC power5000 W]@A#R8$Design lifetime12 years&# 1 H'  Ku-bandYA#R0(Main transponders32YH A#R0,Backup transponders _B#TPower20 transponders of 60 W (TWTA)12 transponders of 90 W (TWTA) for 36 MHz transponders }D#VBandwidth16 transponders of 27 MHz12+4 transponders of 36 MHz(4 36 MHz transponders can be switched to two with 76 MHz with 90 watts)~=A#Rz,Coverage & EIRP maxJapan, Asia-Pacific region and HawaiiR}MA#R"Polarization&s# 8M1  Jcsat 6Hs8 @"✇}" Jcsat 6:-# .Also called Jcsat 4A1 ^'  GeneralY-G#^$") Designationd#^A#RFLaunch dateplanned in May 1998lM#j>"N ,bCountry of originJapano"M#jD"H̀‰MissionTelecommunications^TA#R:,Geostationary orbit124EaG#^4" &Launch vehicleAtlasg TG#^@Launch siteCape Canaveral<X$ 0Identical to Jcsat 58' "(OTechnical data8X' " Specifications\$A#R6&Prime contractorHughesTxA#R&PlatformHS-601T$A#R&"Mass at launchSxA#R$ Mass in orbitL kA#RLengthK A#RWidthL k A#RHeightY[ A#R0 Stabilization3 axisT A#R&DC power5000 WU[  A#R($Design lifetime& * # 1  [ '  Ku-bandY* A#R0(Main transponders32Y[ A#R0,Backup transpondersV c A#R*Power70 W (TWTA)U A#R(Bandwidth27 MHzYc  A#R0,Coverage & EIRP maxR c A#R"Polarization& # 1c 1W  4 T+  ) "VȠ$To view this page you need to register& 4 # 7 k 1 k {KJERS 1? 4 2 4"  JERS 1kBk ) "  Japanese Earth Resource Sensing satellite, also called Fuyo 11 F'  Generalg G#^@") Designation21867 / 92007Ah'FA#RNLaunch date11 Feb 1992 at 01:50 UTlM#j>"N ,bCountry of originJapank @M#j<"H̀郉MissionRemote sensing @4 ^j@A#R:"Perigee/Apogee567/568 kmV @@A#R*Inclination97.7Rj@AA#R"Period96 minf@xAM#j2" &JLaunch vehicleH1[AAA#R4"Mass at launch1340 kgxAB% =Had problems to open out its SAR antenna that were solved. Is working with 1 third of its power (4000 W instead of 12) thus the performance is not maximum<AB' * External resourceswBwC. ,http://hdsn.eoc.nasda.go.jp/guide/guide/satellite/satdata/jers_e.htmlhttp://www.eurimage.it/Products/JERS_1.html8BC' "(OTechnical data8wCC' " Specifications`CGDA#R>&Prime contractorMitsubishi[CDA#R4"Mass at launch1400 kgRGDDA#R"Length0.93 mQDEEA#R Width1.83 mRDEA#R"Height3.16 mZEEEA#R2Solar array7 x 3.5 m]ENFA#R8SAR Antenna11.9 x 2.4 mYEFA#R0 Stabilization3 axis\NFGA#R6$Design lifetime2 years&F)G# P#GyG- *F  SAR (Synthetic Aperture Radar)_)GGA#R<Frequency1.3 GHz (L-band)YyG1HA#R0Resolution18 x 18 mVGHA#R*Swath width75 km1H3I% Mission: high resolution monitoring of land use and type, glacier extent, snow cover, surface topography, ocean currents and waves.GHzI- *4  OPS (Optical Scanner){3I:JE#ZWavebands0.52-0.6 m (visible)0.63-0.69 m (visible)0.76-0.96 m (near IR)1.6-1.7 m (near IR)2.0-2.4 m (near IR)YzIJA#R0Resolution18 x 24 mV:JJA#R*Swath width75 kmnJ{K$ Mission: pollution monitoring in oceans and lakes, land use classification, cloud and snow discrimination.< JK1KLMProgram: KHL{KL8 @*V" Program: KHKM. *  Key HoleAmerican military reconnaissance program. The first satellites had a very limited lifetime. From 1959 to 1992: 266 launched including 50 failuresSorry, this section is under total reconstruction<L@M' *O External resourcesgMM. ,http://www.milnet.com/milnet/declass.htmhttp://www.fas.org/spp/military/program/imint/index.html1@MN1N;N 5M;N# $to be processed&NaN# ;;NN' (O Samos KH 1 seriesT-aNN' Z Satellite And Missile Observatory System5N%O' O KH 1 series~YNO% 8 satellites launchedDiscovery: kh 1, 2 & 31st generation: discovery, samos and KH 35%OO' O KH 4 seriesCO'$ >CorO'Mona8 satellites launched6O]' O KH 4A seriess'% Corona adv41 satellites launched1.5 t, launched by Thor Agena, resolution = 3 m, capsule for retrieval of data6]+' O KH 4B seriesi$ Corona adv (1966-72)1.9 t, launched by Thor Agena, resolution = 1.5 m, capsule for retrieval of data?5+큀' O KH 5 seriesmIZ$ Argonlaunched by Thor Agena, topographical camera, radio transmission5큀' O KH 6 seriesrHZ* $mO{Lanyard, samos advlaunched by Atlas Agena, program stopped in 196356' O KH 7 series냀, &mO{Gambit36 satellites launched2 tons, launched by Atlas Agena, 50 cm resolution, 1963-67, capsule retrieval, high resolution camera 56 ' O KH 8 series냀̄&  Gambit adv49 satellites launched1966-85, 3.4 tons, titan 3b, high resolution camera + topographical camera + multispectral camera5 ' O KH 9 series_8̄`' qHexagon or Big Bird19 satellites launched11.3 tons, titan 3d, 1971-86, replace KH 4B and KH 8The images were returned on film contained in capsules. The typical orbit was a 250 km sun-synchronous orbit which was maintained against drag by frequent maneuvring engine firings. Lifetime was close to 18 months6' O KH 12 series(`, &Kennan adv or Crystal adv?Intl Des Cat No Name Launch Decay Perigee--------- ------ ---------------------- --------- --------- -------1964 036B 826 KH 7-09 SUBSATELLITE 7/6/64 1/3/65 1561964 045B 851 KH 7-10 SUBSATELLITE 8/14/64 3/8/79 2721967 043B 2780 KH 4A-01 SUBSATELLITE 5/9/67 3/14/93 3991967 062B 2851 KH 4A-02 SUBSATELLITE 6/16/67 10/22/68 5011967 109B 3025 KH 4A-44 SUBSATELLITE 11/2/67 3/28/69 454Ɗ* "1968 008B 3114 KH 4A-45 SUBSATELLITE 1/24/68 3/4/70 4701968 020B 3153 KH 4A-46 SUBSATELLITE 3/14/68 1/3/70 4811968 052B 3297 KH 4A-47 SUBSATELLITE 6/20/68 1/11/70 4351968 078B 3409 KH 4A-48 SUBSATELLITE 9/18/68 9/28/69 5001968 112B 3605 KH 4A-49 SUBSATELLITE 12/12/68 13801969 010B 3673 KH 4B-06 SUBSATELLITE 2/5/69 13931969 026B 3830 KH 4A-50 SUBSATELLITE 3/19/69 12/6/71 502Ό* "1969 041B 3915 KH 4A-51 SUBSATELLITE 5/2/69 2/16/70 4071969 079B 4103 KH 4A-52 SUBSATELLITE 9/22/69 5/16/71 4901970 016B 4343 KH 4B-09 SUBSATELLITE 3/4/70 11/10/71 4411970 098B 4722 KH 4B-12 SUBSATELLITE 11/18/70 9/14/77 4931971 076B 5469 KH 4B-15 SUBSATELLITE 9/10/71 2/3/76 4891972 002D 5772 KH 9-02 SUBSATELLITE 1/20/72 4/17/79 4741972 052C 6096 KH 9-03 SUBSATELLITE 7/7/72 5/6/78 498Ɗ֎* "1972 079C 6822 KH 9-04 SUBSATELLITE 10/10/72 14201973 088D 6938 KH 9-07 SUBSATELLITE 11/10/73 14161974 085B 7498 KH 9-09 SUBSATELLITE 10/29/74 1/23/80 5211975 114B 8468 KH 9-11 SUBSATELLITE 12/4/75 5/1/78 2361976 065C 9008 KH 9-12 SUBSATELLITE 7/8/76 6281978 029B 10734 KH 9-14 SUBSATELLITE 3/16/78 6391979 025B 11306 KH 9-15 SUBSATELLITE 3/16/79 621(Ό ' 1980 052C 11852 KH 9-16 SUBSATELLITE 6/18/80 13311982 041C 13172 KH 9-17 SUBSATELLITE 5/11/82 6601983 060C 14139 KH 9-18 SUBSATELLITE 6/20/831984 065C 15071 USA 3 (KH 9-19 SUBSAT) 6/25/84 655֎ M1֎=1W=T+ ) "VȠ$To view this page you need to register&=# 11~5€M5€ a QdI%'d('dI֐҉X^z҉(҉e܌҉f܌҉g܌҉j܌҉k܌҉l܌҉҉҉҉҉Program: KHKH 1-2KH 1-5KH 4-01KH 4A-03KH 7-01KH 9-01KH 11-1KH 11-2KH 11-3KH 11-6KH 11-7KH 11-8KH 12-1KH 12-2KH 12-3KH 12-41f€1f€/ŀn65€Ā8 >m QdI@ĘKH 11 specificationsAlso called KennanThose satellites operate on a sun-synchronous orbit (250/500 km for the first satellites, from KH11-6 on 300/1000 km). Images are transmitted in real time via TDRS. Lifetime at least 4 years, variable. 13 tonsThe constellation consists of two satellites in separate planes, spaced by the angle through which the Earth rotates during two of their orbital periods, about 48.7 deg. Each satellite repeats its groundtrack every four days; and the east satellite follows the west satellite's groundtrack two days later.[7f€/ŀ$ nThey operate with CCDs, estimated resolution: 15 cm7Āfŀ1!fŀŀʀKH 1-2C/ŀŀ5 :V" KH 1-29fŀŀ# ,Also called Samos 21 ŀƀ'  Generalg ŀzƀG#^@") Designation00070 / 61001A\ƀƀA#R6Launch date31 Jan 1961t'zƀJǀM#jN"N ,㹌לCountry of originUnited Statesm&ƀǀG#^L"H̀MissionMilitary: reconnaissance^JǀȀA#R:"Perigee/Apogee474/557 kmVǀkȀA#R*Inclination97.4RȀȀA#R"Period95 minq$kȀ.ɀM#jH" &mO{Launch vehicleAtlas Agena B[ȀɀA#R4Launch siteVandenberga=.ɀɀ$ zFirst american spy satellite transmitting images by radio5ɀʀ'  End of lifeVɀuʀA#R*Decay21 Oct 1973$ʀʀ" 7uʀʀ1K8ʀˀπKH 1-5Gʀˀ8 @ V" KH 1-59ʀPˀ# ,Also called Samos 51 ˀˀ'  Generalg PˀˀG#^@") Designation00219 / 61035C\ˀD̀A#R6Launch date22 Dec 1961t'ˀ̀M#jN"N ,㹌לCountry of originUnited Statesm&D̀%̀G#^L"H̀MissionMilitary: reconnaissance^̀̀A#R:"Perigee/Apogee187/310 kmV%̀̀A#R*Inclination89.6T̀-΀A#R&Period89.4 min\̀΀G#^*" &Launch vehicle[-΀΀A#R4Launch siteVandenberg&΀ π# 5΀?π'  End of lifeU ππA#R(Decay9 Jan 1962$?ππ" 8π 1U TKH 4-01π πHπT8 @"V" KH 4-01< # 2Also called Close Look1 T'  Generalg (G#^@") Designation00256 / 62007A[A#R4Launch date7 Mar 1962t'(M#jN"N ,㹌לCountry of originUnited Statesm&dG#^L"H̀MissionMilitary: reconnaissance^A#R:"Perigee/Apogee236/686 kmVdA#R*Inclination90.9TlA#R&Period93.9 min\G#^*" &Launch vehicle[l#A#R4Launch siteVandenberg&I# 5#~'  End of lifeTIA#R&DecayMay 1963?$~" 9/18/x KH 4A-03Ix8 @$V" KH 4A-031 /'  Generalg xG#^@") Designation00578 / 63016A\lA#R6Launch date18 May 1963t'M#jN"N ,㹌לCountry of originUnited Statesm&lMG#^L"H̀MissionMilitary: reconnaissance^A#R:"Perigee/Apogee147/506 kmTMA#R&Inclination91TSA#R&Period74.5 min\G#^*" &Launch vehicle[S A#R4Launch siteVandenberg&0 # 5 e '  End of lifeV0 A#R*Decay27 May 1963$e " 8  1U _ KH 7-01H _ 8 @"V" KH 7-011  '  Generalg _ G#^@") Designation00618 / 63028A\ S A#R6Launch date12 Jul 1963t' M#jN"N ,㹌לCountry of originUnited Statesm&S 4 G#^L"H̀MissionMilitary: reconnaissance^ A#R:"Perigee/Apogee173/212 kmV4 A#R*Inclination95.3T < A#R&Period88.3 minq$ M#jH" &mO{Launch vehicleAtlas Agena D[< A#R4Launch siteVandenberg& .# 5c'  End of lifeV.A#R*Decay17 Jul 1963$c" 81]CKH 9-01H]8 @"V" KH 9-011 '  Generalg ] @G#^@") Designation05297 / 71056A @\h@A#R6Launch date15 Jun 1971t' @@M#jN"N ,㹌לCountry of originUnited Statesm&h@IAG#^L"H̀MissionMilitary: reconnaissance^@AA#R:"Perigee/Apogee180/300 kmVIAAA#R*Inclination96.4TAQBA#R&Period89.3 min\ABG#^*" &Launch vehicle[QBCA#R4Launch siteVandenberg&B.C# 5CcC'  End of lifeU.CCA#R(Decay6 Aug 1971$cCC" 8CD1BD\DHKH 11-1HC\D8 @"V" KH 11-11 DD'  Generalg \DDG#^@") Designation09627 / 76125A\DPEA#R6Launch date19 Dec 1976t'DEM#jN"N ,㹌לCountry of originUnited Statesm&PE1FG#^L"H̀MissionMilitary: reconnaissance^EFA#R:"Perigee/Apogee246/531 kmV1FFA#R*Inclination96.9TF9GA#R&Period92.3 min\FGG#^*" &Launch vehicle[9GGA#R4Launch siteVandenberg&GH# 5GKH'  End of lifeVHHA#R*Decay28 Jan 1979$KHH" 8HH1HEIMKH 11-2HHEI8 @"V" KH 11-21 HvI'  Generalg EIIG#^@") Designation10947 / 78060A\vI9JA#R6Launch date14 Jun 1978t'IJM#jN"N ,㹌לCountry of originUnited Statesm&9JKG#^L"H̀MissionMilitary: reconnaissance^JxKA#R:"Perigee/Apogee223/509 kmTKKA#R&Inclination97TxK LA#R&Period91.9 min\K|LG#^*" &Launch vehicle[ LLA#R4Launch siteVandenberg&|LL# 5L2M'  End of lifeVLMA#R*Decay23 Aug 198182MM' "(Technical data<MM) "&dSpecifications8M4N1B4N|N[KH 11-3HM|N8 @"V" KH 11-31 4NN'  Generalg |NOG#^@") Designation11687 / 80010A[NoOA#R4Launch date7 Feb 1980t'O M#jN"N ,㹌לCountry of originUnited StatesoO Mm&oOyG#^L"H̀MissionMilitary: reconnaissance^ ׀A#R:"Perigee/Apogee220/498 kmTy+A#R&Inclination97T׀A#R&Period91.7 min\+ہG#^*" &Launch vehicle[6A#R4Launch siteVandenberg&ہ\# 56'  End of lifeV\炁A#R*Decay30 Oct 19828' "(Technical data<炁[) "&dSpecifications817l ۃሁKH 11-6H[ۃ8 @"V" KH 11-69# ,Also called USA 0061 ۃE'  Generalg G#^@") Designation15423 / 84122A[EA#R4Launch date4 Dec 1984t'{M#jN"N ,㹌לCountry of originUnited Statesm&腁G#^L"H̀MissionMilitary: reconnaissance^{FA#R:"Perigee/Apogee335/758 kmT腁A#R&Inclination98L F憁A#RPeriod\BG#^*" &Launch vehicle[憁A#R4Launch siteVandenbergG#B䇁$ FWas active during the gulf war.5'  End of lifeT䇁mA#R&DecayOct 1994?8' "(Technical data<mሁ) "&dSpecifications81!aKH 11-7Hሁa8 @"V" KH 11-79# ,Also called USA 0271 aˉ'  Generalg 2G#^@") Designation18441 / 87090A\ˉA#R6Launch date26 Oct 1987t'2M#jN"N ,㹌לCountry of originUnited Statesm&oG#^L"H̀MissionMilitary: reconnaissance_΋A#R<"Perigee/Apogee300/1000 kmTo"A#R&Inclination98L ΋nA#RPeriod\"ʌG#^*" &Launch vehicleQnA#R Launch site&ʌA# 8y' "(Technical data<A) "&dSpecifications8y퍁1l"퍁5KH 11-8H58 @"V" KH 11-89퍁n# ,Also called USA 0331 5'  Generalg nG#^@") Designation19625 / 88099A[aA#R4Launch date6 Nov 1988t'ՏM#jN"N ,㹌לCountry of originUnited Statesm&aNG#^L"ՏNH̀MissionMilitary: reconnaissance_ՏA#R<"Perigee/Apogee300/1000 kmTNA#R&Inclination98L MA#RPeriod\G#^*" &Launch vehicleQMA#R Launch site& # 8X' "(Technical data< ) "&dSpecifications8X1+#ÁǁKH 12-1DÁ5 : V" KH 12-19IÁ# ,Also called USA 0531 ÁzÁ'  Generalg IÁÁG#^@") Designation20516 / 90019B\zÁ=āA#R6Launch date28 Feb 1990t'ÁāM#jN"N ,㹌לCountry of originUnited States8=ā0ŁG#^p"H̀MissionMilitary: reconnaissance (Kennan advanced)ZāŁA#R2"Perigee/Apogee800 kmT0ŁŁA#R&Inclination65L Ł*ƁA#RPeriodjŁƁM#j:" &}Launch vehicleSTS 36`*ƁƁD#X8"Mass at launch14000 kgiƁǁ* $@ĘOptical reconnaissance satellite. Believed resolution: 15 cm. Downlinks via TDRS. Built by Lockheed8Ɓǁ1$ǁȁ́KH 12-2Dǁȁ5 : V" KH 12-29ǁ<ȁ# ,Also called USA 0861 ȁmȁ'  Generalg <ȁȁG#^@") Designation22251 / 92083A\mȁ0ɁA#R6Launch date28 Nov 1992t'ȁɁM#jN"N ,㹌לCountry of originUnited States80Ɂ#ʁG#^p"H̀MissionMilitary: reconnaissance (Kennan advanced)a ɁʁA#R@"Perigee/Apogee287 / 1021 kmV#ʁʁA#R*Inclination97.8Rʁ,ˁA#R"Period97 minkʁˁM#j<" &^]Launch vehicleTitan 4\,ˁˁA#R6"Mass at launch14000 kgˁ́- (5@ĘOptical reconnaissance satellite. Believed resolution: 15 cm. Downlinks via TDRS. Built by LockheedWas found in the orbit once occupied by KH 11-78ˁ́1+%́6́KH 12-3D́6́5 : V" KH 12-39́ó# ,Also called USA 1161 6́́'  Generalg ó΁G#^@") Designation23728 / 95066Ag&́n΁A#RLLaunch date5 Dec 1995 at 21:18 UTt'΁΁M#jN"N ,㹌לCountry of originUnited StatesCn΁lρG#^"H̀MissionMilitary: reconnaissance (Kennan advanced or Crystal)^΁ρA#R:"Perigee/Apogee270/980 kmVlρ,A#R*ρ,́Inclination96.8Rρ~A#R"Period97 mink,M#j<" &^]Launch vehicleTitan 4\~EA#R6"Mass at launch14000 kgs* $@ĘOptical (and IR?) reconnaissance satellite. Believed resolution: 15 cm. Downlinks via TDRS. Built by Lockheed8E1&^KH 12-4D^5 : V" KH 12-49# ,Also called USA 1291 ^'  Generalg /G#^@") Designation24680 / 96072A\A#R6Launch date20 Dec 1996t'/M#jN"N ,㹌לCountry of originUnited States<G#^x"H̀MissionMilitary: reconnaissance (improved Crystal 4?)WA#R,"Perigee/Apogeen/aT-A#R&Inclinationn/aO|A#RPeriodn/ao"-M#jD" &^]Launch vehicleTitan 4 #19&|# AR1j;'RProgram: Kitcomm@, (*" Program: Kitcomm9R( #LEO messaging system to be operated by Kitcomm pty of Australia. Should be composed of 6 satellites for a start, to be launched with Rokot rockets. In the future a constellation of 21 satellites on 3 planes could be launched. Would orbit at 2800 km.Should use L-band11W(PvT+P) "VȠ$To view this page you need to register&v# @P1] ) 2 Program: KitsatPv 8 @2❨y" Program: Kitsat &  Also named Uribyol (Woo-Ree-Byul) which means "Our Star"Korean program operated by the Korean Institute of Science and Technology< ' *O External resourcesD 2 ' :http://satrec.kaist.ac.kr1 c 1*c e+2 : DVG.Program: KitsatKitsat AKitsat B9c  1 + J FKitsat AI J 8 @$❨y" Kitsat Aa8 ) "p䵟Also called KO-23 or Oscar 23 or Woo-Ree-Byul Ir Ho1 J '  Generalg C G#^@") Designation22077 / 92052B\ A#R6Launch date10 Aug 1992r%C  M#jJ"N ,;XJCountry of originSouth Koreao" M#jD"H̀㓉MissionTelecommunications` A#R>"Perigee/Apogee1304/1324 kmV 6A#R*Inclination66.1U A#R(Period111.9 minn!6M#jB" &D+Launch vehicleAriane V52[TA#R4"Mass at launch50.5 kg"@% ;Function: Packet Radio Mailbox, Digipeater, a CCD camera experiment and a synthesized voice experiment. The Earth Imaging System (EIST"@ ) has 2 CCD cameras.8TZ@' "(OTechnical data8"@@' " SpecificationsHZ@AA#R&Prime contractorKorean Advanced Institute of Science and Technology}6@AG#^l PlatformSSTL (Surrey Satellite Technology Ltd.)[AAA#R4"Mass at launch50.5 kgSAFBA#R$ Mass in orbitL ABA#RLengthK FBBA#RWidthL B)CA#RHeight}<BCA#Rx Stabilization3 axis (gravity gradient & magnetotorquer)N )CCA#RDC powerUCIDA#R($Design lifetime&CoD# 9IDD' $ Frequency chartKoD5EB#TUplink9600 bps K9NG/G3RUH modulated FSK (FM) AX.25145.850 145.900 MHz&D[E# E5EEB#TDownlink9600 bps K9NG/G3RUH modulated FSK (FM) AX.25435.175 MHz$[EF" 9E?F1g 7,?FFKitsat BIFF8 @$❨y" Kitsat Ba8?FF) "p䵟Also called KO-25 or Oscar 25 or Woo-Ree-Byul Ee Ho1 FG'  Generalg FGG#^@") Designation22830 / 93061H\GGA#R6Launch date26 Sep 1993r%GOHM#jJ"N ,;XJCountry of originSouth Koreao"GHM#jD"H̀㓉MissionTelecommunications^OHIA#R:"Perigee/Apogee787/803 kmVHrIA#R*Inclination98.6UIIA#R(Period100.8 minn!rI5JM#jB" &D+Launch vehicleAriane V59[IJA#R4"Mass at launch47.5 kgg5JK$ It carries CCD cameras, store/forward communication equipment (HAM radio) and a radiation detector.8JSK' "(OTechnical data8KK' " SpecificationsDSKLG#^& Prime contractorSaTRec (Satellite Technology Research Center)}6KLG#^l PlatformSSTL (Surrey Satellite Technology Ltd.)[LLA#R4"Mass at launch50.5 kgSLAMA#R$ Mass in orbitRLMA#R"Length352 mmQAMMA#R Width356 mmRM6NA#R"Height670 mm}<MNA#Rx Stabilization3 axis (gravity gradient & magnetotorquer)N 6NOA#RDC power\N]OA#R6$Design lifetime5 years&OO# ?]OO' 0 Frequency chart (MHz)1Olm#b OlF$ PR Downlink freq.Transponder/BeaconMode(Oj#P435.175T9600 bps FSK FM Digital(lj#P436.500T9600 bps FSK FM Digital&# /Rm#^   LN Uplink freq.Transponder/BeaconMode(䂂j#P145.870T9600 bps FSK FM Digital(Rvj#P145.980T9600 bps FSK FM Digital$䂂" : vԃ1 -ԃ莂Kompsat 1:, (" Kompsat 1C ԃQ# @Korea Multi Purpose Satellite1 '  GeneralYQۄG#^$") Designation`;A#R>Launch dateplanned in 1999r%ۄM#jJ"N ,;XJCountry of originSouth Korea_; G#^0"H̀MissionScientificZfA#R2"Perigee/Apogee685 kmQ A#R InclinationL fA#RPeriod\_G#^*" &Launch vehicleQA#R Launch site_d% KOMPSAT will carry remote sensing instruments to measure ocean and land as well as upper atmospheric instruments. Some experiments will focus on ionospheric and magnetic fields. Also includes an electro-optical camera with 7 meter resolution built by TRW. The camera will provide cartography data for developing digital elevation maps of the Korean peninsula for land use and planning purposes. 1 ' O Contactrd-& KARI (Korea Aerospace Research Institute)52 Eoeun Dong, Yusong Gu, Taejon 305-333, KoreaTel: +82-042-860-26118e' "(OTechnical data8-' " SpecificationsYeA#R0&Prime contractorTRWN DA#RPlatformZA#R2"Mass at launch420 kgSDA#R$ Mass in orbitO@A#RDimensionQA#R Solar arrayS@䌂A#R$ StabilizationN 2A#RDC powerU䌂A#R($Design lifetimea:2莂' uShould have Ka-band capacityDaewoo provided the attitude and orbit control subsystem; Halla and Hanwah, the propulsion subsystem; Hyundai, electrical power system components; Korean Air and Doowon, the structural and thermal subsystem; and Samsung, the on-board computer and satellite system test equipment. 11W.mT+莂m) "VȠ$To view this page you need to register&# BmՏ1c;[b/Տ3eProgram: KoreasatR38 @6 7N?"Տ3 Program: Koreasat2Տe. * $AAlso called Mugunghwa (name of the national flower)Korean geostationary telecommunication program operated by Korea Telecom. The first generation is made of 3 satellites operating in DBS & FSS band.The second generation satellites are planned for 20051310‚>e‚A R|rY Y Y Program: KoreasatKoreasat 1Koreasat 2Koreasat 31F‚1 1F‚!Ƃ?‚‚# 8Koreasat's specificationsq0F‚‚A#R`&Prime contractorLockheed Martin Astro SpaceU‚KÂA#R(PlatformGE 3000[‚ÂA#R4"Mass at launch1464 kgTKÂÂA#R&Dry mass652 kgXÂRĂA#R.Payload mass202 kgb!ÂĂA#RBDimension1.74 x 1.96 x 1.9 mYRĂ łA#R0 Stabilization3 axisYĂfłA#R0DC powerBOL: 1600 W] łłA#R8$Design lifetime12 years^:fł!Ƃ$ tBeacons would be at: 12.25125, 12.25175 & 12.74875 GHz1łRƂ1U2RƂʂʂ<!ƂƂ# 2Koreasat's Ku-band FSSYRƂƂA#R0(Main transponders12ZƂAǂA#R2,Backup transponders4OƂǂA#RPower14 WUAǂǂA#R(Bandwidth36 MHzYǂ>ȂA#R0CoverageSouth KoreaVǂȂA#R*EIRP max50.2 dBWV>ȂȂA#R*G/T max13.5 dB/KRȂ~ɂB#TPolarizationKoreasat 1: H uplink; V downlinkKoreasat 2: V uplink; H downlink@ȂʂB#TFrequenciesUplink: 14.00-14.5 GHzDownlink: 12.25-12.75 GHz>~ɂʂA#R| Beam coverage0.74 x 0.74 uplink; 0.86 x 0.86 downlink$ʂʂ" 1ʂʂ1U3ʂ΂΂<ʂ˂# 2Koreasat's Ku-band DBSXʂh˂A#R.(Main transponders3Z˂˂A#R2,Backup transponders3Ph˂̂A#RPower120 WU˂ĝA#R(Bandwidth27 MHzŶ̂A#R0CoverageSouth KoreaVĝ͂A#R*EIRP max59.4 dBWV̂l͂A#R*G/T max13.0 dB/Kd#͂͂A#RFPolarizationLHCP (up and down)=l͂O΂B#TzFrequenciesUplink: 14.5-14.8 GHzDownlink: 11.7-12.0 GHZ>͂΂A#R| Beam coverage0.82 x 0.67 uplink; 1.06 x 0.86 downlink$O΂΂" 1΂#ς14#ςzςW!΂zς6 "/ۀ0Geostationary orbit116Ep#M#jF" &p㉂Launch vehicleDelta 2 #228i<- (yp㉂The launch experienced a partial failure: a booster rocket to separate. The preliminary reports indicate that explosive lines on the Delta 2 vehicle were damaged by exposure to excessive temperatures, causing one of the solid motors not to separate. The booster separation malfunction was blamed on the heat-related failure of insulation protecting the rocket's booster separation circuits.This resulted in a wrong orbit delivery. The satellite reached GEO at the end of August on its own and used part of is propellant. Thus its lifetime was reduced to 4.5 years.[7I$ nShould move to 113E after the launch of Koreasat 38' "(Technical datan7I7 >n&`=XWSpecificationsKu-band (telecom)Ku-band (DBS)=,' , EIRP coverage (dBW)3 42JgD4w3TelecomDBSEquipped with a Star 30 solid apogee motor. Carries 625 kg of fuel for the apogee motor and 187 kg of hydrazine propellant.; ,)17)p Koreasat 2Gp5 :& 7N?" Koreasat 2A)# <Also called Mugunghwa Ee Ho1 p'  Generalg I G#^@") Designation23768 / 96003A\ A#R6Launch date14 Jan 1996r%I  M#jJ"N ,;XJCountry of originSouth Koreao" M#jD"H̀‰MissionTelecommunicationsf G#^>"/ۀ0Geostationary orbit116Ep# \ M#jF" &p㉂Launch vehicleDelta 2 #231[ A#R4"Mass at launch1608 kg&\ # 8  ' "(Technical datan7 7 >n&`=XWSpecificationsKu-band (telecom)Ku-band (DBS)= ' , EIRP coverage (dBW)B  0 0$2JgD4w3TelecomDBS; = 1j8= Koreasat 3G 5 :& 7N?" Koreasat 3C = # @Also called Mugunghwa Sahm Ho1 '  GeneralY QG#^$") Designationd# A#RFLaunch dateplanned in Aug 1999r%Q'M#jJ"N ,;XJCountry of originSouth Koreao"M#jD"H̀‰MissionTelecommunicationsf' @G#^>"/ۀ0Geostationary orbit116E @ jv@M#j:" &2!Launch vehicleArianeT @@A#R&"Mass at launchF"v@A$ Dsatellite worth US$108 million8@HA' "(OTechnical data=AA' , EIRP coverage (dBW)DHAA1 2&}D4w3TelecomDBS8AB' " Specificationse$AfBA#RH&Prime contractorLockheed MartinSBBA#R$PlatformA2100[fBCA#R4"Mass at launch2790 kgUBiCA#R(Dry mass1300 kgOCCA#RDimensionQiC DA#R Solar arraySC\DA#R$ StabilizationT DDA#R&DC power4700 W]\D EA#R8$Design lifetime12 years&D3E# 5 EhE'  Ku-band DBSX3EEA#R.(Main transponders6ZhEFA#R2,Backup transponders3PEjFA#RPower120 WUFFA#R(Bandwidth27 MHzYjFGA#R0CoverageSouth KoreaVFnGA#R*EIRP max59.4 dBWVGGA#R*G/T max14.0 dB/Kd#nG(HA#RFPolarizationLHCP (up and down)>GHA#R| Beam coverage0.82 x 0.67 uplink; 1.06 x 0.86 downlink&(HH# 5HI'  Ku-band FSSn-HpIA#RZ(Main transpondersgroup-1 12 + group-2 12ZIIA#R2,Backup transponders8OpIJA#RPower45 WUInJA#R(Bandwidth36 MHzKJJB#TCoverageG1: South KoreaG2: South Korea or South-East Asia (steerable)OnJKC#VEIRP maxG1: 50.5 dBWG2 South Korea: 55.1 dBWG2 South-East Asia: 50.2 dBWPJ LC#VG/T maxG1: 13.6 dB/KG2 South Korea: 13.7 dB/KG2 South-East Asia: 8.0 dB/KBKLB#TPolarizationG1: H uplink, V downlinkG2: V uplink, H downlinkd LJMB#T Beam CoverageG1: 0.74 x 0.74 uplink; 0.86 x 0.86 downlinkG2 South-East Asia: 3.0 circular&LpM# 1 JMM'  Ka-bandXpMMA#R.(Main transponders3ZMSNA#R2,Backup transponders2OMNA#RPower70 WVSNNA#R*Bandwidth200 MHz^NVOA#R:CoverageKorean peninsulaVNOA#R*EIRP max55.0 dBWUVO A#R(G/T max9.4 dB/KO  l+OyA#RVPolarizationRHCP uplink; LHCP downlink^ ׀A#R: Beam coverage1.2 x 1.0&y# 1׀.1W9.T+) "VȠ$To view this page you need to register&.# 1ف1:ف,S,6 << 7N?" Koreasat 3's FSS EIRP1ف]1W;]ׂT+,) "VȠ$To view this page you need to register&]ׂ# 91[b΀<IPƒL Star 19 ׂI, (" L Star 19# ,Also called LaoStar1 I'  GeneralY G#^$") Designationf%rA#RJLaunch dateplanned in early 1998o" ᄃM#jD"N ,)`Country of originThailando"rPM#jD"H̀‰MissionTelecommunications^ᄃA#R:,Geostationary orbit116EjPM#j:" &2!Launch vehicleArianeYqG#^$Launch site~Q- (sNgProgram of Asia Broadcasting and Communications Network, Ltd (ABCN) of Bangkok. ABCN is a subsidiary of Thailand's M. Group. After launch, the satellite is to be handed over to Lao-Star Co. Ltd., a company held 80 percent by ABCN and 20 percent by the government of Laos. ABCN also awarded a contract to Telesat Canada to monitor and test the L-Star program as technical advisers. Telesat will also operate the satellite during the first 24 months. Telesat is building a control center in Perth Australia. This center will be remote controlled from their main control center in Canada.(q' Japan's Itochu Corp. said it will join the project. Sondhi Satellite would also be involvedThe contract (2 satellites with launch) is worth $480 million. Options can be taken for 3rd and 4th satellites. The ground station will be located in Vientianne8O' "(Technical dataA) "0PqCEIRP coverage (dBW)8OȊ' " Specificationsi(1A#RP&Prime contractorSpace Systems/LoralXȊA#R.PlatformFS 1300 HP[1䋃A#R4"Mass at launch3500 kgS7A#R$ Mass in orbitO䋃A#RDimensionQ7׌A#R Solar arrayY0A#R0 Stabilization3-axisY׌A#R0DC powerEOL: 8200 W]0捃A#R8$Design lifetime14 years& # 1 捃='  Ku-bandY A#R0(Main transponders32Y=A#R0,Backup transpondersP?A#RPower113 WUA#R(Bandwidth33 MHzk? ]#"PqC:PqCPqCPqCCoverageE ׂast: East Asia (Taiwan, Southern and Eastern coast of China, HongKong, Korea)West: Indian subcontinent (India, Pakistan, Nepal, Bangladesh, Sri Lanka)Central: Golden Peninsula (Thailand, Laos, Cambodia, Vietnam, Malaysia Singapore)+ Japan uplinkN YA#REIRP maxR A#R"Polarization=Y*ƒB#TzFrequenciesUplink: 17.3-17.8 GHzDownlink: 11.7-12.2 GHz&Pƒ# 1*ƒƒ1W=ƒƒƒT+Pƒƒ) "VȠ$To view this page you need to register&ƒƒ# 1ƒ,Ã1t>,ÃoÃCƒoÃ0 0(" L Star's EIRP1,ÃÃ1W?ÃÃăT+oÃÃ) "VȠ$To view this page you need to register&Ãă# 9ÃSă1Z@SăăȃL Star 29 ăă, (" L Star 21 Săă'  GeneralYăŃG#^$") Designationd#ăzŃA#RFLaunch dateplanned in mid 1998o"ŃŃM#jD"N ,)`Country of originThailando"zŃXƃM#jD"H̀‰MissionTelecommunications^ŃƃA#R:,Geostationary orbit116EjXƃ ǃM#j:" &2!Launch vehicleArianeYƃyǃG#^$Launch site ǃ<ȃ- (-GC|See L Star 1 for more details... the satellites are identicalThe satellite might be delayed or cancelled because of the Asian currency crisis.8yǃtȃ' "(Technical dataA<ȃȃ) "0PqCEIRP coverage (dBW)1tȃȃ1WAȃ:Ƀ`ɃT+ȃ:Ƀ) "VȠ$To view this page you need to register&ȃ`Ƀ# B:ɃɃ1΀ABɃɃw̓Program: LacrosseR`ɃɃ8 @6Gm" Program: LacrossejɃ̃6 : QdI@ĘAlso called IndigoAmerican military reconnaissance programEquipped with a Synthetic Aperture Radar which provides 1 m resolution data. Lifetime = 5 years, 14 tons, built by Lockheed Martin. Solar pannel are believed to measure amost 50 m, which could provide 10 to 20 kW power.Can take pictures as much as 1000 km off of the ground track. The great advantage of those satellites over the KH imaging satellites is that it can view through clouds. The system probably uses high and low resolution modes and transmits large amount of data for computer processing on the ground. It probably downlinks via TDRS<Ƀ̃' *O External resourcesỹw̓. ,http://www.fas.org/spp/military/program/imint/lacrosse.htmhttp://www.fas.org/spp/military/program/imint/indigo.htm1̃̓1C̓'΃>w̓'΃A R|=Š---Program: LacrosseLacrosse 1Lacrosse 2Lacrosse 3; ̓b΃1HDb΃΃Lacrosse 1K'΃΃8 @(Gm" Lacrosse 19b΃΃# ,Also called USA 0341 ΃σ'  Generalg ΃~σG#^@") Designation19671 / 88106B[σσA#R4Launch date2 Dec 1988t'~σYM#jN"σY'΃N ,㹌לCountry of originUnited Statesm&σG#^L"H̀MissionMilitary: reconnaissance^Y$A#R:"Perigee/Apogee680/690 kmTxA#R&Inclination57L $A#RPeriodkx/M#j<" &DLaunch vehicleSTS 27R&U# 5/'  End of life^UA#R:"Out of serviceMarch 1997T<A#R&CausedeorbitedUA#R(DecayMarch 1997&<# ; 1E=Lacrosse 2K=8 @(Gm" Lacrosse 29v# ,Also called USA 0691 ='  Generalg vG#^@") Designation21147 / 91017A[iA#R4Launch date8 Mar 1991t'M#jN"N ,㹌לCountry of originUnited Statesm&iJG#^L"H̀MissionMilitary: reconnaissanceZA#R2"Perigee/Apogee700 kmTJA#R&Inclination68L DA#RPeriodkM#j<" &^]Launch vehicleTitan 4$D" ; 1FY> Lacrosse 3KY8 @(Gm" Lacrosse 39# ,Also called USA 1331 Y'  Generalg * G#^@") Designation25017 / 97064A\ A#R6Launch date24 Oct 1997t'* M#jN"N ,㹌לCountry of originUnited Statesm& g G#^L"H̀MissionMilitary: reconnaissanceZ A#R2"Perigee/Apogee700 kmTg  A#R&Inclination57L a A#RPeriodo" M#jD" &^]Launch vehicleTitan 4 #22nCa > + &-Apparently replaces Lacrosse 1has a Lockheed/Sunnyvale Bus-1A  1b nG FProgram: LadybugA> , (," Program: LadybugO  / ,A⻧u}Ka-band telecommunication program operated by KaStar Satellite Communications Corp. Was approved by the FCC in May 1997 except for the inter satellite link2 satellites planned: Ladybug 1 at 73W and Ladybug 2 at 109.2W cost: $517 millionWill provide T1 and high bandwidth pipes8 G' "(OTechnical data8' " Specificationse$GA#RH&Prime contractorLockheed MartinN 2A#RPlatform[A#R4"Mass at launch3200 kgU2 @A#R(Dry mass1690 kg @> \h@A#R6Dimension2 x 2 x 3.6 mZ @@A#R2Solar array24 m spanYh@AA#R0 Stabilization3-axisN@AA#RDC powerEOL: 6600 W (Nickel Hydrogen batteries, 100% eclipse time backup)]ABA#R8$Design lifetime10 yearsO+AVB$ VCommand and telemetry in C- and Ka-band1 BB'  Ka-bandYVBBA#R0(Main transponders48ZB:CA#R2,Backup transponders6OBCA#RPower30 WV:CCA#R*Bandwidth125 MHz{8CZDC#VpCoverageall the 50 states with:4 spotbeams1 CONUSN CDA#REIRP maxRZDDA#R"PolarizationNDEB#TFrequenciesUplink: 28.35-28.60 and 29.25-29.5 GHzDownlink: 19.7-20.2 GHz]D F& plans 60 GHz inter-satellite links (120 MHz)on-board switching12 times frequency reuse?1E>F1WH>FFFT+ FF) "VȠ$To view this page you need to register&>FF# @FF1A IFHGHProgram: LageosPFHG8 @2V%" Program: LageosFH+ $  LAser GEOdynamic SatelliteAmerican scientific program operated by CNR/PSN/NASASeries 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.1HG)I1J)IIe+HI: DV>ܝProgram: LageosLageos 1Lageos 21)II1UKI`KK=II# 4Lageos's specificationsZIVJA#R20"Mass at launch410 kgSIJA#R$0Diameter0.6 mZVJKA#R20 Stabilizationpassive]J`KA#R80$Design lifetime50 years$KK" 1`KK1ULKGNkN6KK# &Lageos's payload^7KIL' n Retroreflectors mounted on the surface of the sphereAKLA#R8Number of retroreflectors426 (422 fused silica, 4 germanium)_IL*MA#R<,Individual diameter3.8 cmhLMA#RAccuracyground transmitter position can be determined to a few cm; tectonic motion to a few mm/yeart3*MGNA#Rf.Contruction materialaluminum with a brass core$MkN" 9GNN1  MNNLageos 1IkNN8 @$V%" Lageos 11 NO'  Generalg NOG#^@") Designation08820 / 76039A[OOA#R4Launch date4 May 1976t'O`M#jNO`kN"N ,㹌לCountry of originUnited Statesp#OЀM#jF"H̀CV$MissionScientific: geodesy``0A#R>"Perigee/Apogee5836/5947 kmWЀA#R,Inclination109.8U0܁A#R(Period225.4 mins&OM#jL" &p㉂Launch vehicleThor Delta #123&܁u# <O' *O External resources\5u ' jhttp://www.dgfi.badw-muenchen.de/edc/lageos1.html8E' "(Technical dataM 0 0:4 SpecificationsPayload9E˃1N˃ÈLageos 2I8 @$V%" Lageos 21 ˃E'  Generalg G#^@") Designation22195 / 92070B\EA#R6Launch date22 Oct 1992t'|M#jN"N ,㹌לCountry of originUnited Statesp#셄M#jF"H̀CV$MissionScientific: geodesy`|LA#R>"Perigee/Apogee5615/5952 kmV셄A#R*Inclination52.6ULA#R(Period222.5 minjaM#j:" &ϛLaunch vehicleSTS 52&# <aÇ' *O External resources\5' jhttp://www.dgfi.badw-muenchen.de/edc/lageos2.html8ÇW' "(Technical datal:È2 4t4 SpecificationsPayloadPrime contractor: AeritaliaAW1'n OUQProgram: LandsatQÈU8 @4"" 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!).U%* "A In 1984 the Congress gave EOSAT (Earth Observation SATellite corporation) the right to commercialize the pictures but it didn't make Landsat self financed.:[_' &(OLandsat 1 series %j@ Nȉ  2úWMade of Landsat 1, 2 & 3. Descending node at 09:30 and 18 days orbital cycleBased on the Nimbus platform. Were equipped with the RBV (Return Beam Vidicon) TV camera and the MSS (MultiSpectral Scanner) radiometer. Such a camera had been used by the lunar observation program Ranger. The satellites transmit their data in real time to Eath stations when they are available otherwise the data is recorded on-board.Has the same MSS as Landsat 4 & 5:_' &(OLandsat 2 seriesjw; D1@Ę>=s2úWMade of Landsat 4 & 5. Descending node at 09:37 and 16 days orbital cycleThe data is transmitted by the TDRS network.SpecificationsPayload:' &(OLandsat 3 seriesMw>4 8rCeK<׉Made of Landsat 6 & 7. 16 >Èdays orbital cycleSpecificationsPayload<z' *O External resources>Q6 :Chttp://geo.arc.nasa.gov/sge/landsat/landsat.htmlhttp://edcwww.cr.usgs.gov/glis/hyper/guide/landsathttp://edcwww.cr.usgs.gov/glis/hyper/guide/landsat_tm1z1PI„jQI„]  ɀ ɉɉɉɉɉɉProgram: LandsatLandsat 1Landsat 2Landsat 3Landsat 4Landsat 5Landsat 6Landsat 71z„1UQz„Ą ńD!I„„# BLandsat 4 & 5's specifications^z„ÄA#R:0&Prime contractorGE Astrok*„ÄA#RT0PlatformMultiMission Spacecraft (MMS)[ÄÄA#R40"Mass at launch1941 kgOÄ1ĄA#R0Length4 mYÄĄA#R00 Stabilization3 axis\1ĄĄA#R60$Design lifetime3 years$Ą ń" 1Ą;ń1UR;ń|ʄʄ= ńxń# 4Landsat 4 & 5's payloadT';ńń- *N  MSS (Multispectral Scanner System)8xńDŽE#X0Wavebands0.5-0.6 m (green): mapping coastal features in sediment-laden water0.6-0.7 m (red): mapping roads and urban areas0.7-0.8 m (red to near IR): as below0.8-1.1 m (near IR): vegetation studies and mapping land/water boundariesTńXDŽA#R&0Resolution80 mWDŽDŽA#R,0Swath width185 kmFXDŽDŽ- *2  TM (Thematic Mapper)dDŽɄH#^0Wavebands0.45-0.52 m (visible): soil/vegetation differentiation & coastal water mapping0.52-0.60 m (visible): vegetation mapping0.63-0.69 m (visible): plant species differentiation0.76-0.90 m (near IR): biomass survey1.55-1.75 m (IR): snow/cloud differentiation10.4-12.5 m (thermal IR): thermal mapping2.08-1.35 m (IR): geological mappingCDŽ%ʄA#R0Resolution30 m (visible, near & middle IR); 120 m (thermal IR)WɄ|ʄA#R,0Swath width185 km$%ʄʄ" 1|ʄʄ1USʄ̈́΄D!ʄ˄# BLandsat 6 & 7's specifications^ʄs˄A#R:0&Prime contractorGE Astrol˄˄M#j>0(?9PlatformTiros N / DMSP[s˄:̄A#R40"Mass at launch2750 kgZ˄̄A#R20 Mass in orbit2000 kgQ:̄̄A#R 0Length6.4 mQ̄6̈́A#R 0Width1.22 mȲ̈́A#R00 Stabilization3 axis\6̈́̈́A#R60$Design lifetime5 years$̈́΄" 1̈́@΄1UT@΄7[i<΄΄- *x2úWLandsat 6 & 7's payloadMSS identical to Landsat 4 & 5P#@΄΄- *F  ETM (Enhanced Thematic Mapper) ΄I#`0Wavebands0.45-0.52 m (visible)0.52-0.60 m (visible)0.63-0.69 m (visible)0.76-0.90 m (near IR)1.55-1.75 m (IR)10.4-12.5 m (thermal IR)2.08-2.35 m (IR)0.5-0.9 m (panchromatic΄΄)D΄A#R0Resolution15 m (panchromatic), 30 m (visible. near & middle IR)WA#R,0Swath width185 kmY,D- *X  SeaWiFS (Sea-viewing Wide Field Sensor)kI#`0Wavebands0.43-0.45 m (visible): low chlorophyll0.49-0.51 m (visible): other pigments0.55-0.57 m (visible): baseline chlorophyll0.65-0.67 m (visible): subsurface scattering0.74-1.78 m (near IR): atmospheric correction0.84-0.89 m (near IR): atmospheric correction10.5-11.5 m (IR): sea-surface temperature11.5-12.5 m (IR): sea-surface temperatureJDB#T0Resolution1.13 km (local area coverage)4.5 km (global area coverage)XA#R.0Swath width2800 km[7A#R40&Revisit interval1 day$[" : 71 U Landsat 1J[8 @&"" Landsat 18# *Also called ERTS 11 H'  Generalg G#^@") Designation06126 / 72058A\H A#R6Launch date23 Jul 1972t'M#jN"N ,㹌לCountry of originUnited Statesk M#j<"H̀郉MissionRemote sensing^HA#R:"Perigee/Apogee895/908 kmVA#R*Inclination99.4SHA#R$Period103 minr%cM#jJ" &p㉂Launch vehicleThor Delta #89ZA#R2"Mass at launch816 kgX4c $ hHas provided over 1 million multispectral photos5J '  End of lifeX A#R."Out of service1980$J " : 1n I V J Landsat 2J J 8 @&"" Landsat 28 # *Also called ERTS 21 J '  Generalg  G#^@") Designation07615 / 75004A\ v A#R6Launch date22 Jan 1975t' M#jN"N ,㹌לCountry of originUnited Stateskv U M#j<"H̀郉MissionRemote sensing^ A#R:"Perigee/Apogee898/912 kmVU A#R*Inclination98.9U ^ A#R(Period103.1 mins& M#jL" &p㉂Launch vehicleThor Delta #107&^ # 5 ,'  End of life\ A#R6"Out of serviceFeb 1982$," : 1 ̀ W0BLandsat 3J08 @&"" Landsat 38h# *Also called ERTS 31 0'  Generalg h @G#^@") Designation10702 / 78026A @[g@A#R4Launch date5 Mar 1978t' @@M#jN"N ,㹌לCountry of originUnited Stateskg@FAM#j<"H̀郉MissionRemote sensing^@AA#R:"Perigee/Apogee895/915 kmVFAAA#R*Inclination98.9UAOBA#R(Period103.1 mins&ABM#jL" &p㉂Launch vehicleThor Delta #139$OBB" : B C1UI / X CjCGLandsat 4JBjC8 @&"" Landsat 41 CC'  Generalg jCDG#^@") Designation13367 / 82072A\C^DA#R6Launch date16 Jul 1982t'DDM#jN"N ,㹌לCountry of originUnited Statesk^D=EM#j<"H̀郉MissionRemote sensing^DEA#R:"Perigee/Apogee696/708 kmV=EEA#R*Inclination98.1TEEFA#R&Period98.8 mins&EFM#jL" &p㉂Launch vehicleThor Delta #163&EFF# 8FG' "(Technical dataxFFG2 4>=s2úWSpecificationsPayloadDownlink frequency: 2229.5 / 2265.5 MHz: GG1)̀ g YGH LLandsat 5JGH8 @&"" Landsat 51 GCH'  Generalg HHG#^@") Designation14780 / 84021A[CHIA#R4Launch date1 Mar 1984t'HyIM#jN"N ,㹌לCountry of originUnited StateskIIM#j<"H̀郉MissionRemote sensing^yIBJA#R:"Perigee/Apogee698/706 kmVIJA#R*Inclination98.1TBJJA#R&Period98.8 mins&J_KM#jL" &p㉂Launch vehicleThor Delta #174&JK# 8_KK' "(Technical dataMK L0 0:>=s2úWSpecificationsPayload: KDL1/  ZDLLLandsat 6J LL8 @&"" Landsat 61 DLL'  GeneralTLMA#R&Designationn/ag&LzMA#RLLaunch date5 Oct 1993 at 17:56 UTt'MMM#jN"N ,㹌לCountry of originUnited StateskzMYNM#j<"H̀郉MissionRemote sensingo"MNM#jD" &^]Launch vehicleTitan 2 #16&YNN# 5N#O'  End of life^NOA#R:"Out of service5 Oct 1993c"#O A#RDCauseAttitude control failureO LO' Cost: $220 millionAfter rupture of a hydrazine manifold disabled attitude control the satellite began to tumble at the start of the apogee-motor (Thiokol Star 37XFP) firing, and did not reach orbit.8 7' "(Technical dataM0 0:rCeK<׉SpecificationsPayload: 71Jg [!Landsat 7J8 @&"" Landsat 71 9'  GeneralQA#R Designationd#9A#RFLaunch dateplanned in May 1998t'bM#jN"N ,㹌לCountry of originUnited Statesk̓M#j<"H̀郉MissionRemote sensingj)b7A#RR"Perigee/Apogee705 km sun synchronousQ̓A#R Inclinationa 7鄅A#R@Period99 min (16-day cycle)kTM#j<" &p㉂Launch vehicleDelta 2[鄅A#R4Launch siteVandenbergG#T$ FLaunch under the MELVS contract<2' *O External resourcesV/' ^http://geo.arc.nasa.gov/sge/landsat/l7.html82' "(Technical dataa1!0 .c@ĘTDRS used for telemetry and command:Telemetry: 2287.5 MHz (1.216 Mbps or upto 4.864 Mbps in SSA mode)Command: 2106.4 MHz (125 kbps or upto 1 kbps in SSA mode)Data: 8212.5 & 8342.5 MHz (150 Mbps each, can be used at the same time)15 m resolution Panchromatic, 30 m resolution Multispectral modes1R1W\R̈T+!) "VȠ$To view this page you need to register&R̈# = 1  ] VProgram: LCSM̈V8 @,c%" Program: LCSQ. # \American radar calibration military program1V؉1^؉Ck*CA RTSIU IUProgram: LCSLCS 1LCS 2LCS 46؉y1` _y LCS 1FC8 @c%" LCS 11 y'  Generalg WG#^@") Designation01361 / 65034C[A#R4Launch date6 May 1965t'W&M#jN"N ,㹌לCountry of originUnited States]G#^,"H̀MissionMilitary`&㌅A#R>"Perigee/Apogee2786/2795 kmV9A#R*Inclination32.1U㌅A#R(Period145.6 minn!9M#jB" &^]Launch vehicleTitan 3 #4$ " 6V1e `V?ÅLCS 4F 8 @c%" LCS 4>Vڎ# 6Also called Gridsphere 11 '  Generalg ڎrG#^@") Designation05396 / 71067F[ ͏A#R4Launch date7 Aug 1971t'rMM#jN"N ͏M ,㹌לCountry of originUnited States]͏G#^,"H̀MissionMilitary^MA#R:"Perigee/Apogee779/910 kmV^A#R*Inclination87.6UA#R(Period101.8 min\^…G#^*" &Launch vehicle[j…A#R4Launch siteVandenberg&……# 5j……'  End of lifeV…ÅA#R*Decay11 Jun 1972$…?Å" 5ÅtÅ1Q ݂ atÅÅɅLDEF= ?ÅÅ2 4"  LDEFE"tÅÅ# D Long Duration Exposure Facility1 Å'ą'  Generalg ÅąG#^@") Designation14898 / 84034B['ąąA#R4Launch date6 Apr 1984t'ą]ŅM#jN"N ,㹌לCountry of originUnited States~1ąŅM#jb"H̀@0pMissionScientific: Meteorite observation^]Ņ9ƅA#R:"Perigee/Apogee344/348 kmVŅƅA#R*Inclination28.5T9ƅƅA#R&Period91.5 minjƅMDžM#j:" &$Launch vehicleSTS 13\ƅDž% Mass at retrieval: 10.5 t with 10000 samplesDeveloped by NASA (Langley Research Center)5MDžȅ'  End of life^DžaȅA#R:"Out of service9 Jan 1990g ȅȅG#^@uDCauseRetrieved by STS 32RVaȅɅA#R*Decay20 Jan 1990&ȅDɅ# <ɅɅ' *O External resourcesQ*DɅɅ' Thttp://dbdev.larc.nasa.gov/setas/LDEF/@Ʌʅ1] w bʅaʅͅProgram: LeasatPɅaʅ8 @2" Program: LeasatʅF̅+ $u LEAsed SATelliteAmerican military telecommunication satellite program launched in 1978 (under contract from the DoD). The satellites (Syncom 4 series) are operated by US Navy. The Leasat system is connected to the Navel Telecommunications Command Operational Center (NTCOC) in Washington, DC5 satellites were ordered, 1 initially intended as ground spare together with an operational center, 4 fixed ground stations and 2 mobile ones.1 aʅw̅' O ContactD F̅̅$ @Operator: Naval Space Command<w̅̅' *O External resourcesh̅ͅ. ,http://www.hcisat.com/sat/fleet/leasat.htmlhttp://www.fas.org/spp/military/program/com/leasat.htm1̅ͅ1cͅY΅LͅY΅O nUg!Ag"Ag#Ag$Ag%AgProgram: LeasatLeasat 1Leasat 2Leasat 3Leasat 4Leasat 51ͅ΅1d΅9CY΅΅' 8Leasat's specifications\΅)υA#R6&Prime contractorHughesT΅}υA#R&PlatformHS-3819)υ G#^r"K\Mass at launch6895 kg (after STS crade separation)}υ Y΅Z}υfA#R2 Mass in orbit1388 kgD A#RDimension4.26 m diameter x 6.17 m high deployed (4.29 m stowed)Qf<A#R Solar arraySA#R$ StabilizationD<B#TDC powerEOL: 1238 WEclipse: 3 25 A-hr nickel-cadmium batteriesUjA#R($Design lifetime~=A#Rz*Telemetry & beacon7250 to 7500 MHz, and 7975 to 8025 MHzQ'j9* $NK\Designed only for launch from STS1j1UejM&9' LLeasat's UHF-band (240 - 400 MHz)YjA#R0(Main transponders13YiA#R0,Backup transpondersK A#RPowerOiA#RBandwidthN QA#RCoverageN A#REIRP maxRQA#R"Polarization$" 9N1n  fN Leasat 1I8 @$" Leasat 1<N# 2Also called Syncom 4011 '  Generalg kG#^@") Designation15384 / 84113C\A#R6Launch date10 Nov 1984t'k;M#jN"N ,㹌לCountry of originUnited Statesy,M#jX"H̀‰MissionMilitary: telecommunicationsY; A#R0,Geostationary orbitjw M#j:" &*Launch vehicleSTS 19nJ $ It wasn't launched first because of an aborted STS launch in June 19845w  '  End of lifeW q A#R,"Out of serviceyes& # 8q ' "(Technical dataN  0 0<fSpecificationsUHF-band9 V 1i gV BLeasat 2I 8 @$" Leasat 2<V # 2Also called Syncom 4021 '  Generalg s G#^@") Designation15236 / 84093C\ A#R6Launch date30 Aug 1984t's C M#jN"N ,㹌לCountry of originUnited Statesy, M#jX"H̀‰MissionMilitary: telecommunicationsb!C A#RB,Geostationary orbitsee belowj M#j:" &OLaunch vehicleSTS 23&# : - */ۀ Locationrm#:   " BeginEndPosition @j#.$(*L: 30 Aug 1984r @ !r@j#B46early 1994early 199473E* @+Aj#T,.Feb 1995Sep 1996177.5W, inclined&@QA# 5+AA'  End of life\QAAA#R6"Out of serviceSep 1996TA6BA#R&CauseDeorbited&A\B# 86BB' "(Technical dataN\BB0 0<fSpecificationsUHF-band9BC1'  hCdCZJLeasat 3IBdC8 @$" Leasat 3<CC# 2Also called Syncom 4031 dCC'  Generalg C8DG#^@") Designation15643 / 85028C\CDA#R6Launch date12 Apr 1985t'8DEM#jN"N ,㹌לCountry of originUnited Statesy,DEM#jX"H̀‰MissionMilitary: telecommunicationsb!EEA#RB,Geostationary orbitsee belowjEMFM#j:" &'Launch vehicleSTS 16TEF1 2'SWhen released from STS 16 it failed to reach GEO and was repaired by STS 272 MFG'  LocationFGm#:   " BeginEndPositionGHj#.$(*L: 12 Apr 1985*GHj#T02early 1994Sep 1996105W, inclined&HH# 5HH'  End of life\HZIA#R6"Out of serviceSep 1996THIA#R&CauseDeorbited&ZII# 8I J' "(Technical dataNIZJ0 0<fSpecificationsUHF-band9 JJ1 u iJJOLeasat 4IZJJ8 @$" Leasat 4<JK# 2Also called Syncom 4041 JIK'  Generalg KKG#^@") Designation15995 / 85076D\IK LA#R6Launch date29 Aug 1985t'KLM#jN"N ,㹌לCountry of originUnited Statesy, LLM#jX"H̀‰MissionMilitary: telecommunications\LUMA#R6,Geostationary orbitn/ajLMM#j:" &SLaunch vehicleSTS 27&UMM# 5MN'  End of life\MvNA#R6"Out of serviceSep 1985r1NNA#RbCauseUHF downlink failed during tests in GEO&vNO# 8NFO' "(Technical dataNOO0 0<fSpecificationsUHF-band9FOO1 jO"Leasat 5IO"8 @$"O"O Leasat 5<O^# 2Also called Syncom 4051 "'  Generalg ^G#^@") Designation20410 / 90002B[QA#R4Launch date9 Jan 1990t'ŁM#jN"N ,㹌לCountry of originUnited Statesy,Q>M#jX"H̀‰MissionMilitary: telecommunicationsb!ŁA#RB,Geostationary orbitsee belowk> M#j<" &uDLaunch vehicleSTS 32R&1# : k- */ۀ Location1m#:   " BeginEndPositionkvj#.$(*L: 12 Apr 1985"j#D46early 1994early 1994177W)vj#R,.Feb 1995May 199771.5E, inclined76j#n,.May 1997Feb 1998drifting 72E - 77E, inclined j#@Apr 1998156E, inclineds6Z' In May 1998 the satellite was leased to Australian Defence Force (Royal Australian Navy) for up to 5 years. The satellite was relocated at 156E.Leasat 5 began limited service to the Australian Defence Force on Oct. 17, 1997. The PanAmSat Operations Center in Long Beach, Calif. provided the tracking, telemetry, and control capability via its Guam ground station. 8' "(Technical dataNZ0 0<fSpecificationsUHF-bandA!1݂  k!bProgram: LEO OneAb, (," Program: LEO One_!/ ,LUS program from dBX Corp. It comprises 48 LEO satellites (8 planes, 50 inclination) at 950 km for mobile messaging (vehicle tracking, pager alerts, monitoring). Worth $250 million Operator: LEO One FCC authorized.Each satellite should weigh 125 kg, lifetime: 5 to 7 yearsUplink: 148-150.05 MHz Downlink: 137-137.025 MHz and 400.15-401 MHz1b!1Wl!uT+u) "VȠ$To view this page you need to register&!# = u؋1w m؋%Program: LESM%8 @,Mc%" Program: LESb؋( Lincoln Experimental SatelliteAmerican military tactical program designed by the Lincoln lab1%1nRd ;S㿶UUU¶UöUĶUƶUǶUProgram: LESLES 1LES 2LES 3LES 4LES 5LES 6LES 8LES 96̍1L o̍LES 1F8 @Mc%" LES 11 ̍C'  Generalg G#^@") Designation01002 / 65008C\CA#R6Launch date11 Feb 1965t'zM#jN"N ,㹌לCountry of originUnited States`ڏG#^2"H̀MissionMilitary: ?`zFA#R>ڏF"Perigee/Apogee2783/2809 kmVڏA#R*Inclination32.1UFA#R(Period145.8 minn!_M#jB" &^]Launch vehicleTitan 3 #3$" 6_1 K pdņLES 2F8 @Mc%" LES 21 0†'  Generalg †G#^@") Designation01360 / 65034B[0††A#R4Launch date6 May 1965t'†fÆM#jN"N ,㹌לCountry of originUnited States`†ÆG#^2"H̀MissionMilitary: ?a fÆ'ĆA#R@"Perigee/Apogee2771/14810 kmVÆ}ĆA#R*Inclination32.2U'ĆĆA#R(Period309.9 minn!}Ć@ņM#jB" &^]Launch vehicleTitan 3 #4$Ćdņ" 6@ņņ1EL n qņņɆLES 3Fdņņ8 @Mc%" LES 31 ņƆ'  Generalg ņxƆG#^@") Designation01941 / 65108D\ƆƆA#R6Launch date21 Dec 1965t'xƆHdžM#jN"N ,㹌לCountry of originUnited States`ƆdžG#^2"H̀MissionMilitary: ?_HdžȆA#R<"Perigee/Apogee267/4829 kmVdž]ȆA#R*Inclination26.5UȆȆA#R(Period139.9 minn!]Ȇ ɆM#jB" &^]Launch vehicleTitan 3 #7&ȆFɆ# 5 Ɇ{Ɇ'  End of lifeUFɆɆA#R(Decay6 Apr 1968${ɆɆ" 6Ɇ*ʆ1FK  r*ʆpʆΆLES 4FɆpʆ8 @Mc%" LES 41 *ʆʆ'  Generalg pʆˆG#^@") Designation01870 / 65108B\ʆdˆA#R6Launch date21 Dec 1965t'ˆˆM#jN"N ,㹌לCountry of originUnited States`dˆ8̆G#^2"H̀MissionMilitary: ?`ˆ̆A#R>"Perigee/Apogee189/33632 kmV8̆̆A#R*Inclination26.6ŬC͆A#R(Period589.2 minn!̆͆M#jB" &^]Launch vehicleTitan 3 #7&C͆͆# 5͆ Ά'  End of lifeU͆aΆA#R(Decay1 Aug 1977$ ΆΆ" 6aΆΆ1n sΆφLES 5FΆφ8 @Mc%" LES 51 Ά2φ'  Generalg φφG#^@") Designation02866 / 67066E[2φ A#R4Launch date1 Jul 1967φ Άt'φM#jN"N ,㹌לCountry of originUnited States` G#^2"H̀MissionMilitary: ?b!BA#RB"Perigee/Apogee33188/33618 kmVA#R*Inclination11.6VBA#R*Period1316.1 mino"]M#jD" &^]Launch vehicleTitan 3 #19X.* $\ㅯ\&Could be equipped with a SNAP generator?6]1 t1LES 6F18 @Mc%" LES 61 b'  Generalg 1G#^@") Designation03431 / 68081D\b%A#R6Launch date26 Sep 1968t'M#jN"N ,㹌לCountry of originUnited Statesy,%M#jX"H̀‰MissionMilitary: telecommunicationsYkA#R0,Geostationary orbito"M#jD" &^]Launch vehicleTitan 3 #31&k# 55'  End of lifeWA#R,"Out of serviceyesX.5* $\ㅯ\&Could be equipped with a SNAP generator?61^u` LES 8F`8 @Mc%" LES 81 '  Generalg `G#^@") Designation08746 / 76023A\TA#R6Launch date15 Mar 1976t'M#jN"N ,㹌לCountry of originUnited Statesy,TA M#jX"H̀‰MissionMilitary: telecommunicationsb! A#RB,Geostationary orbitsee belowo"A  M#jD" &^]Launch vehicleTitan 3 #93Z l A#R2"Mass at launch450 kg \ + $ㅯ\&LES 8 & 9 were placed in geostationary orbit with 90 between each other. Equipped with a radio isotropic 238 plutonium generator, they could communicate without the help of a ground station.: l - */ۀ Location\ m#:   " BeginEndPosition j#0$(*L: 15 Mar 1976?! - j#BMar 199594.5W, inclined j#@Jan 1996103W, inclined$- " 6 1vWDLES 9F W8 @Mc%" LES 91 '  Generalg WG#^@") Designation08747 / 76023B\KA#R6Launch date15 Mar 1976t'M#jN"N ,㹌לCountry of originUnited Statesy,KD@M#jX"H̀D@ ‰MissionMilitary: telecommunicationsb!@A#RB,Geostationary orbitsee belowo"D@AM#jD" &^]Launch vehicleTitan 3 #93Z@oAA#R2"Mass at launch450 kgA_B+ $ㅯ\&LES 8 & 9 were placed in geostationary orbit with 90 between each other. Equipped with a radio isotropic 238 plutonium generator, they could communicate without the help of a ground station.: oAB- */ۀ Location_B#Cm#:   " BeginEndPositionBCj#0$(*L: 15 Mar 1976?"#C1Dj#DMar 1995105.5W, inclined CDj#@Jan 1996105W, inclined$1DD" 6DE1 wEKE$Lewis6 DKE, (" LewisV3EE# fNamed for 19th century explorer Meriwether Lewis1 KEE'  Generalg E9FG#^@") Designation24909 / 97044A\EFA#R6Launch date23 Aug 1997j9FFM#j:"N ,㹌לCountry of originUSAo(FnGG#^P"H̀MissionScientific: Remote sensingZFGA#R2"Perigee/Apogee300 kmVnGHA#R*Inclination97.5RGpHA#R"Period95 minm HHM#j@" &bnW"Launch vehicleAthena #2`pH=IA#R>Launch siteVandenberg SLC6mIHI$ Part of the Small Spacecraft Technology Initiative (SSTI), for NASA. 5=II'  End of life_I>JA#R<"Out of service26 Aug 1997t3IJA#RfCauseWent out of control after wrong maneuver V>JKA#R*Decay28 Sep 1997xQJL' It would have flown 3 imaging spectrometers to gather high resolution spectral images of the Earth's surface and atmosphere, celestial objects. 5 m resolution Panchromatic, 30 m resolution MultispectralTotal cost for NASA: $64.8 million An additional $6.2 million was spent for 1-year storage and maintenance due to delayed launch<KL' *O External resourcesYLCM. ,http://crsphome.ssc.nasa.gov/SSTI/WELCOME.HTMhttp://www.trw.com/seg/sats/SSTI.html8L{M' "(OTechnical data8CMM' " SpecificationsY{M NA#R0&Prime contractorTRWN MZNA#RPlatformZ NNA#R2"Mass at launch385 kgSZNOA#R$ Mass in orbitONVOA#RDimensionQOOA#R Solar arraySVO A#R$ StabilizationO DN OZA#RDC power\ A#R6$Design lifetime5 years_Z;& Telemetry: 2275.3 MHz (8 kbps)Command: 2095.172 MHz (2 kbps)Data: 2275.3 MHz (2.048 Mbps)1 l' O Payload;$7 <   HSI: Hyper Spectral Imager (will enable to collect data in 384 channels whereas currently standard instruments are limited to 20 channels (range 0.4 m to 2.5 m)) (built by TRW)LEISA: Linear Etalon Imaging Spectral Array (built by NASA Goddard)UCB: Ultraviolet Cosmic Background Experiment (built by Berkeley)Lewis will also carry 15 technology demonstrations experiments.9l]1p?x]ՈLightsar9 $, (" Lightsar1 ]ǃ'  GeneralY G#^$") DesignationQǃqA#R Launch datet' 儇M#jN"N ,㹌לCountry of originUnited StatesbqGM#j*"T@^gOperatorNASAo(儇G#^P"H̀MissionScientific: remote sensingTG A#R&"Perigee/ApogeeQ[A#R InclinationL A#RPeriod\[G#^*" &Launch vehicleQTA#R Launch site=% Would use advanced technologies to reduce the cost and enhance the quality of radar-based information for scientific research, commercial remote-sensing and emergency management applications. <Ty' *O External resources\5=Ո' jhttp://southport.jpl.nasa.gov/lightsar/index.html1y1WyZT+ՈZ) "VȠ$To view this page you need to register&# BZ‰1Cz‰Program: LLMSIRISB, (." Program: LLMSIRISiA‰m( Little Leo Messaging System - Intercontinental Retrieval of Information via SatelliteBelgian project for a LEO messaging system. It is supported by SAIT Systems. The total program is said to cost $33 million.Two experimental satellites (~50 kg each) are to be launched in 1997 on polar orbits by Russian launchers.8' "(OTechnical data8m݋' " Specificationsb!?A#RB&Prime contractorSAIT SystemsN ݋A#RPlatformY?指A#R0"Mass at launch60 kgS9A#R$ Mass in orbit`指A#R>Dimension0.5 x 0.5 x 0.5 mQ9ꍇA#R Solar arrayS=A#R$ StabilizationWꍇA#R,DC powerEOL: 30 W\=A#R6$Design lifetime3 years&# 1G1W{GT+) "VȠ$To view this page you need to register&G# B1? |]EÇProgram: LoralsatN]5 :4=1" Program: LoralsatP"‡. *ExTelecommunication satellite programm operated by Loral Space & Communications LtdIn Ku-band 2 satellites are planned (Loralsat 101 & 102) plus 1 ground spare. Project worth $250 million. For Ku-band there are other projects: a satellite could be located at 81W to broadcast over all america (14.0-14.5/11.7-12.2 GHz for North America, 13/75-14.0/11.45-11.7 GHz for South). At 77W yet another satellite is planned to cover all America (13.75-14.0/11.45-11.7 GHz for North and South America and 6.425-6.725/3.4-3.7 GHz for South America)`6] Ç* $l〾uFrom the same operator, in Ka-band see Cyberstar8‡EÇ' "(Technical data1 ÇvÇ1W}vÇÇÇT+EÇÇ) "VȠ$To view this page you need to register&vÇÇ# 1Ç!ć1~!ććo5Çć: Dj' p6 p6Program: LoralsatLoralsat 101Loralsat 1021!ćć1WćŇ;ŇT+ćŇ) "VȠ$To view this page you need to register&ć;Ň# 1ŇlŇ1UlŇȇȇI&;ŇŇ# LLoralsat 101 & 102's specificationsi(lŇƇA#RP&Prime contractorSpace Systems/LoralN ŇlƇA#RPlatformTƇƇA#R&"Mass at launchSlƇLJA#R$ Mass in orbitOƇbLJA#RDimensionQLJLJA#R Solar arraySbLJȇA#R$ StabilizationN LJTȇA#RDC power]ȇȇA#R8$Design lifetime12 years$Tȇȇ" 1ȇɇ1WɇZɇɇT+ȇZɇ) "VȠ$To view this page you need to register&ɇɇ# 1Zɇɇ1Uɇ0̇ṪAɇɇ# <Loralsat 101 & 102's C-bandYɇKʇA#R0(Main transponders24YɇʇA#R0,Backup transpondersOKʇʇA#RPower20 WOʇBˇA#RBandwidthN ʇˇA#RCoverageN BˇˇA#REIRP maxRˇ0̇A#R"Polarization$ˇṪ" 10̇̇1Ẇ̇̇T+Ṫ̇) "VȠ$To view this page you need to register&̇̇# 1̇0͇1U0͇ 0Ḃr͇# >Loralsat 101 & 102's Ku-bandY0͇͇A#R0(Main transponders32Yr͇$·A#R0,Backup transpondersP͇t·A#RPower110 WO$··A#RBandwidthRt·VχA#RCoverageUSA (including Hawaii and Alaska, Puerto Rico and the Virgin Islands)N ·χA#REIRP maxRVχ A#R"Polarizationχ ̇$χ0" 1 a1WaT+0) "VȠ$To view this page you need to register&a# = 1aLoralsat 101Ia5 :*=1" Loralsat 1011 '  GeneralYaG#^$") Designation`KA#R>Launch dateplanned in 1999t'M#jN"N ,㹌לCountry of originUnited Stateso"K.M#jD"H̀‰MissionTelecommunications^A#R:,Geostationary orbit129Wj.M#j:" &2!Launch vehicleAriane\8R$ pLoralsat 102 should be identical and located at 77W8' "(Technical data]&R7 >Llp"vSpecificationsC-bandKu-band11WlT+l) "VȠ$To view this page you need to register&# = l10g Loralsat 102I5 :*=1" Loralsat 1021 I'  GeneralYG#^$") Designation`IA#R>Launch dateplanned in 2000t'vM#jN"N ,㹌לCountry of originUnited Stateso"M#jD"H̀‰MissionTelecommunications]vBA#R8,Geostationary orbit77WjM#j:" &2!Launch vehicleAriane&B# 8 ' "(Technical data]&g 7 >Llp"vSpecificationsC-bandKu-band1 1W  T+g ) "VȠ$To view this page you need to register&  # 6 H 1n gH BLusat>  2 4"  LusatY0H ) "`䵟Also called Microsat 4 or LO-19 or Oscar 191  '  Generalg w G#^@") Designation20442 / 90005G\ A#R6Launch date22 Jan 1990p#w C M#jF"N ,㉕U剂Country of originArgentinao" M#jD"H̀㓉MissionTelecommunications^C  A#R:"Perigee/Apogee779/797 kmV f A#R*Inclination98.6U A#R(Period100.6 minn!f )M#jB" &6D+Launch vehicleAriane V35d J#d4$Mass at launch9 kgI%)$ JBased on an Amsat-NA Microsat bus<' *O External resources]6o' lhttp://www.amsat.org/amsat/sats/nk6k/msatmain.html8' "(OTechnical data=o @$ 2Passive stabilization @ c@B#TUplink1200 bps Manchester coded (Biphase-L) FSK (FM) AX.25145.840 145.860 145.880 145.900 MHz& @@# @AD#VDownlink1200 bps BPSK (SSB) AX.25, either one of the two frequencies below:437.154 MHz (LHCP in northern hemisphere), normal unfiltered PSK437.126 MHz (RHCP in northern hemisphere), Raised Cosine modulation&@B# h'A~BA#RNCW beacon437.126 MHz (when active)$BB" @~BB1ЂB"CpDProgram: M-Star@B"C, (*" Program: M-StarN&BpD( MPlanned global satellite network; to be designed by Motorola; total cost: $6.1 billion The company plans to earn $32 billion from the system over a 10-year period. Would be made of 72 LEO satellites. First launches planned in early 1997. throughput: 40 GbpsShould be operational in 20021"CD1WDDET+pDD) "VȠ$To view this page you need to register&DE# 4DOE1gOEEIM2A4EE, (" M2A;OEE# 0Multi-Media Asia, MA1 EE'  GeneralYEHFG#^$") Designationd#EFA#RFLaunch dateplanned in mid-1999p#HFGM#jF"N ,b#Country of originIndonesiahFGP#p0( OperatorPT PSNo"GGM#jD"H̀‰MissionTelecommunicationsg&GZHA#RL,Geostationary orbit134E or 118EjGHM#j:" &㉓gLaunch vehicleProtonYZHIG#^$Launch sitesHJ1 0>؉Project worth $350 million. To be delivered in-orbit With this order an option for 5 additional satellites was secured. See also PalapaM2A is a joint venture between Pasifik Satelit Nusantara and IndosatThe ground segment of the program is worth $115 million, granted to AlcatelThe satellite might be delayed or cancelled because of the Asian currency crisis.8IJ' "(OTechnical data8J1K' " Specificationsi(JKA#RP&Prime contractorSpace Systems/LoralV1KKA#R*PlatformFS 13000TKDLA#R&"Mass at launchSKLA#R$ Mass in orbitUDLLA#R(Dry mass1960 kgOL;MA#RDimensionQLMA#R Solar arrayY;MMA#R0 Stabilization3-axisUM:NA#R(DC power10400 W]MNA#R8$Design lifetime12 years&:NN# 0 NN'  C-bandYNFOA#R0(Main transponders24YNOA#R0,Backup transpondersK FO A#RPowerO EOO[A#RBandwidthN A#RCoverageJ [A#REIRPREA#R"Polarization\A#R6Frequencies3.7-4.2 GHz&Eǁ# 9' $ Extended C-bandYǁYA#R0(Main transponders28YA#R0,Backup transpondersK YA#RPowerOLA#RBandwidthN A#RCoverageJ L䃈A#REIRPR6A#R"Polarization\䃈A#R6Frequencies3.4-3.7 GHz&6# 0 脈'  X-bandX@A#R.(Main transponders2Y脈A#R0,Backup transpondersK @䅈A#RPowerO3A#RBandwidthN 䅈A#RCoverageJ 3ˆA#REIRPRA#R"Polarization,ˆI) Direct broadcast is planned in C-bandWill have 7 shaped spot beams and 1 global beam. Coverage of the Asia Pacific region, including Indonesia, Australia, India, China, Indochina, Korea, Japan and ASEANThe repeater module is provided by Alcatel Espace1z1WzΈT+IΈ) "VȠ$To view this page you need to register&z# AΈ51?Ђ5Program: MabuhayM5 :2A" Program: Mabuhay5F Z}m{`g {`g有Geostationary telecommunication program operated by MPSC. Mabuhay Philippines Satellite Corp. (MPSC) is controlled by PLDT (51%). Partners are Philippines Communications Satellite Corp (Philcomsat), Republic Broadcasting System, China Everbright Group, Cable Entertainment Group, PT PSN.PLDT announced they would launch 3 satellites in late 1996-1998. In mid 1996 Palapa B2P was bought in orbit to act as the first Mabuhay bird ' Agila means "Philippines Eagle" This name is a kind of brand name in the Philippines as the national satellite system. Competitors are fighting to be able to use that name...Mabuhay 2 should go to 153E (after year 2000)116u;6: Dv"Z最nProgram: MabuhayMabuhay 0 (Palapa B2P)Mabuhay 1: p1c%pBMabuhay 1F65 :$A" Mabuhay 1V3p # fShould be called Agila 2 after successful launch1 ='  Generalg G#^@") Designation24901 / 97042A\=A#R6Launch date19 Aug 1997r%rM#jJ"N ,k8{Country of originPhilippineso"ᏈM#jD"H̀‰MissionTelecommunicationsfrSG#^>ᏈS6"/ۀ0Geostationary orbit146Er%ᏈM#jJ" &9+SLaunch vehicleLong March #44Sˆ5 8C _Sk7Cost: $230 million. Two transponders are owned by PT Pasifik Satelit NusantaraWas not delivered in the exact orbit and had to burn extra fuel to move 3000 km. The lifetime is said not to have been reduced by this operation.The planned location was 144E, but there are interference problems in Ku-band with nearby Superbird C satellite. Despite the move, only 18 transponders can be activated in Ku-band.8ˆ' "(Technical dataEˆÈ) "8/<EIRP coverage map (dBW)8ˆPÈ' " Specificationsi(ÈÈA#RP&Prime contractorSpace Systems/LoralUPÈĈA#R(PlatformFS-1300[ÈiĈA#R4"Mass at launch3770 kgSĈĈA#R$ Mass in orbitOiĈ ňA#RDimensionQĈ\ňA#R Solar arrayS ňňA#R$ StabilizationN \ňňA#RDC power]ňZƈA#R8$Design lifetime12 years&ňƈ# 0 Zƈƈ'  C-bandYƈ LjA#R0(Main transponders30YƈbLjA#R0,Backup transpondersO LjLjA#RPower27 WUbLjȈA#R(Bandwidth36 MHzw5Lj}ȈB#TjCoverageentire South-East and Pacific RimHawaiiN ȈȈA#REIRP maxR}ȈɈA#R"Polarization&ȈCɈ# R+ɈɈ' V C-band Transponder frequency chart (GHz);CɈ3ʈc#v . L HorizontalDownlinkTransponderVerticalDownlink`ɈʈR#t3.58025`3ʈʈR#t263.600`ʈSˈR#t2.62027`ʈˈR#t283.640`Sˈ̈R#t3.66029`ˈs̈R#t303.680_ ̈̈R#t3.7201_ s̈1͈R#t 23.740_ ͈̈R#t3.7603_ 1͈͈R#t 43.780_ ͈NΈR#t3.8005_ ͈ΈR#t 63.820_ NΈ ψR#t3.8407_ ΈkψR#t 83.860_ ψψR#t9.8809`kψ6R#tψ66103.900`ψR#t3.92011`6R#t123.940`VR#t3.96013`R#t143.980`VR#t4.00015`vR#t164.020`R#t4.04017`v6R#t184.060`R#t4.08019`6R#t204.100`VR#t4.12021`R#t224.140`VR#t4.16023`vR#t244.177&# 1 v'  Ku-bandY&A#R0(Main transponders24YA#R0,Backup transpondersP&A#RPower110 WOA#RBandwidthDA#RCoveragePhilippines, Coastal China, Taiwan and northern VietnamN A#REIRP maxRCA#R"PolarizationO+$ VCan operate as 12 transponders at 220 WS,C' X Ku-band Transponder frequency chart (GHz); c#v . L HorizontalDownlinkTransponderVerticalDownlink` R#t 112.221` C R#t12.2212` R#t 312.261`C  R#t12.2614` c R#t 512.301` R#t12.3016`c # R#t 712.341` R#t12.3418`# R#t 912.381a D R#t12.38110a R#t1112.421aD R#t12.42112a gR#t1312.461aR#t12.46114ag)R#t1512.501aR#t12.50116a) @R#t1712.541 @6am@R#t12.54118a @@R#t1912.581am@/AR#t12.58120a@AR#t2112.621a/AAR#t12.62122aARBR#t2312.661aABR#t12.66124&RBB# 1B C1 C\CRB\C6 <:n" Mabuhay 1's coverage@ CC1CCAEProgram: MagionP\CC8 @2.舀" Program: MagionhCwD# Czech scientific program designed with the help of the Russians and other former East-bloc countries.<CD' *O External resources`wDAE. ,http://www.ufa.cas.cz/html/magion/magion.htmlhttp://www.iki.rssi.ru/interball/magion.html1DrE1rE FLAE FO n$aL$M$N$O$P$Program: MagionMagion 1Magion 2Magion 3Magion 4Magion 59rEFF1FFFJMagion 1I FF8 @$.舀" Magion 11 FFF'  Generalg F'GG#^@") Designation11110 / 78099C\FGA#R6Launch date24 Oct 1978u('GGM#jP"N ,Country of originCzechoslovakia_GWHG#^0"H̀MissionScientific^GHA#R:"Perigee/Apogee404/762 kmTWH IA#R&Inclination83TH]IA#R&Period96.4 minl IIM#j>" &s,梉Launch vehicleCosmos CY]I"JA#R0Launch sitePlesetsk&IHJ# 5"J}J'  End of lifeVHJJA#R*Decay11 Sep 1981$}JJ" 9J0K1ˁ0KyKNMagion 2IJyK8 @$.舀" Magion 21 0KK'  Generalg yKLG#^@") Designation20281 / 89080B\KmLA#R6Launch date28 Sep 1989u(LLM#jP"N ,Country of originCzechoslovakia|/mL^MM#j^"H̀d;plMissionScientific: magnetosphere study_LMA#R<"Perigee/Apogee498/2441 kmV^MNA#R*Inclination82.6UMhNA#R(Period115.3 minq$NNM#jH" &ቂLaunch vehicleCyclone 3 #79$hNN" 9N6O1O6OOMagion 3INO8 @$.舀" Magion 31 6OO'  Generalg O#G#^@") DesignaO#Ntion21835 / 91086E\OA#R6Launch date18 Dec 1991u(#M#jP"N ,Country of originCzechoslovakia|/pM#j^"H̀d;plMissionScientific: magnetosphere study_ρA#R<"Perigee/Apogee435/3045 kmVp%A#R*Inclination82.6UρzA#R(Period121.3 minq$%낉M#jH" &ቂLaunch vehicleCyclone 3 #97&z# 8낉I' "(OTechnical dataM*# TDownlink frequency: 135.150/137.850 MHz9Iσ1σMagion 4I8 @$.舀" Magion 46σN# &Also called C2-X1 '  Generalg N愉G#^@") Designation23646 / 95039Fg&MA#RLLaunch date2 Aug 1995 at 23:59 UTu(愉…M#jP"N ,Country of originCzech Republic|/M>M#j^"H̀d;plMissionScientific: magnetosphere studya …A#R@"Perigee/Apogee760/191760 kmV>A#R*Inclination63.3TIA#R&Period5454 mineG#^<" &Launch vehicleMolniya M^I A#R:Launch sitePlesetsk LC43YeA#R0"Mass at launch50 kgq * $sIt carries instruments to measure electric and magnetic fields for comparison with the Prognoz instruments.9e919oMagion 5I8 @$.舀" Magion 569# &Also called C2-A1 鉉'  Generalg PG#^@") Designation24293 / 96050Ch'鉉A#RNLaunch date29 Aug 1996 at 05:22 UTjP"M#j:"N , Country of originCISu(M#jP"H̀?vMissionScientific: aurora study`"A#R>"Perigee/Apogee782/19140 kmVMA#R*Inclination62.8L A#RPeriodeMG#^<" &Launch vehicleMolniya M^\A#R:Launch sitePlesetsk LC43YA#R0"Mass at launch58 kg\o% +Had problems to unfold one of its solar panels. In May 1998, the satellite could finally be activated (by repeatedy sending telemetry commands).91W  ᎉʉMaqsat H9 oᎉ, (" Maqsat HXb) " Also called Teamsat (Technology, science and Education experiments Added to Maqsat)1 ᎉ'  Generalg b G#^@") Designation25023 / 97066A o\hA#R6Launch date30 Oct 1997m M#j@"N ,4"Country of originEurope_h4G#^0"H̀MissionTechnology`A#R>"Perigee/Apogee554/26612 kmU4A#R(Inclination7.7S<‰A#R$Period468 mino"‰M#jD" &xg&\Launch vehicleAriane V101<‰lÉ% 9Dummy satellite full of instruments to measure environment of launch. This satellite contained the Teamsat experiment, which released the YES satellite.<‰É' *O External resourcesK$lÉÉ' Hhttp://www.estec.esa.nl/teamsat/8É+ĉ' "(OTechnical data%ÉPƉ( Built by Kayser-Threde of Munich, Germany. Teamsat was produced in 7 months at ESTEC. 2300 kgExperiments:Orbiting Debris Device(ODD) - Automation & Informatics Department, ESTEC. The MAQSAT-H satellite is painted with contrasting patterns (75% white and 25% black) to support testing and calibration of ground-based optical and radar stations in Europe. The contrasting paint should also allow detection of the rotation or tumbling of MAQSAT-H. Additionally, surface paint degradation will be studied. w+ĉȉ' Autonomous Vision System (AVS) - Technical University of Denmark. AVS is a camera which automatically recognises and tracks stars or non-stellar objects (such as satellites). AVS can be used to identify specific stars, determine the attitude of satellites for navigation purposes and acquire images.Visual Telemetry System (VTS) - MMS Bristol (UK) / IMEC and OIP (Belgium). VTS is an imaging system to monitor spacecraft activities such as the operations of critical mechanisms. TEAMSAT hosts a system of three cameras and a master unit to provide compressed image sequences of the fairing opening and satellite separations. PƉʉ% Flux Probe Experiment (FIPEX) - University of Stuttgart. FIPEX will measure the concentration of atomic oxygen at altitudes up to 1000 kilometres. Atomic oxygen is known for its erosion effect and degradation of optical surfaces and lenses. 9ȉAʉ1܈AʉzʉωMaqsat B9 ʉzʉ, (" Maqsat B1 Aʉʉ'  Generalg zʉˉG#^@") Designation25024 / 97066B\ʉnˉA#R6Launch date30 Oct 1997m ˉˉM#j@"N ,4"Country of originEurope_nˉ:̉G#^0"H̀MissionTechnology`ˉ̉A#R>"Perigee/Apogee554/26612 kmU:̉̉A#R(Inclination7.7S̉B͉A#R$Period468 mino"͉̉M#jD" &xg&\Launch vehicleAriane V101B͉~Ή% QBuilt by Kayser-Threde of Munich, Germany. It is a smaller dummy satellite stored below the SPELTRA dual launch adapter and which remains attached to the EPS stage.<͉Ή' *O External resourcesK$~Ήω' Hhttp://www.estec.esa.nl/teamsat/BΉGω1 .GωωProgram: MarathonBωω, (." Program: MarathonGω( Planned by Russian and Italian companies: system for fixed and mobile communicωωations made of 9 satellitesThe operator would be Informcosmos and the prime contractor NPO PMThe satellite could also be called Arkos1ω1WBT+) "VȠ$To view this page you need to register&B# @1܈SProgram: MarecsPB8 @2" Program: Marecs2 2 RH(㐮):European maritim telecommunication program designed from the Eutelsat platform. Operated by ESA.Satellites used by Inmarsat<' *O External resourcesaS. ,http://www.vilspa.esa.es/marecs/marecs.htmlhttp://www.esoc.esa.de/external/mso/marecs.html11y8SA RpF^nڰ_ʴU˴UProgram: MarecsMarecs AMarecs B1Marecs B21.1U.4=k# 4Marecs's specificationsq0.A#R`&Prime contractorBritish Aerospace (now MMS)Qk-A#R PlatformECS[A#R4"Mass at launch1056 kgX-A#R.Payload mass100 kga AA#R@Dimension1.9 x 1.4 x 2.56 m\A#R6Solar array13.9 m spanYAA#R0 Stabilization3 axisXNA#R.DC powerEOL: 789 W\A#R6$Design lifetime7 yearsf%NA#RJCapacity50 duplex voice channels$4" 1e1Ue  54# $Marecs's L-bandXeA#R.0(Main transponders1ZL A#R20,Backup transponders1U A#R(0Power50 to 60 WOL A#R0BandwidthT D A#R&0CoverageglobalT A#R&0EIRP max35 dBWRD A#R"0Polarization$  " 1 ? 1U? 5 t # $Marecs's C-bandX? A#R.0(Main transponders1Yt % A#R00,Backup transpondersP u A#R0Power20 W?O% A#R0BandwidthTu  A#R&0CoverageglobalN f A#R0EIRP maxR A#R"0Polarization$f " 9 1L^DMarecs AI ^8 @$" Marecs A1 '  Generalg ^G#^@") Designation13010 / 81122A\RA#R6Launch date20 Dec 1981m M#j@"N ,4"Country of originEuropeo"R:@M#jD"H̀:@ ‰MissionTelecommunicationsb!@A#RB,Geostationary orbitsee belown!:@ AM#jB" &(+Launch vehicleAriane L04&@0A# 2 AbA'  Location0AAm#:   " BeginEndPosition"bAxBj#D$(*L: 20 Dec 198115W / 26W,ACj#X2421 Mar 1993Aug 199622.8E, inclined&xB4C# 5CiC'  End of life\4CCA#R6"Out of serviceAug 1996TiCDA#R&Causedeorbited&C?D# 8DwD' "(Technical dataw>?DD9 B|&k&kSpecificationsL-bandC-bandTransmits on 137.17 MHz: wD(E1(ErE.GMarecs B1JDrE8 @&" Marecs B15(EE'  End of life_rEFA#R<"Out of service10 Sep 1982n'EtFG#^N)+CauseAriane L05's launch failure&FF# 8tFF' "(Technical data\%F.G7 >J&k&kSpecificationsL-bandC-band: FhG14LhGGMMarecs B2J.GG8 @&" Marecs B21 hGG'  Generalg GJHG#^@") Designation15386 / 84114B\GHA#R6Launch date10 Nov 1984m JHIM#j@"N ,4"Country of originEuropeo"HIM#jD"H̀‰MissionTelecommunicationsb!IIA#RB,Geostationary orbitsee belown!IRJM#jB" &C+Launch vehicleAriane V11&IxJ# : RJJ- */ۀ LocationxJMar 199726W, inclined&WLM# 8L>M' "(Technical dataw>MM9 B|&k&kSpecificationsL-bandC-bandTransmits on 137.17 MHzA>MM1.MGN Program: MarisatQMGN8 @4.P" Program: MarisatM?O2 2P/:㐮):Also called GapfillerAmerican maritim telecommunication satellite program operated by Comsat. Was first used by military forces before been used by private companies. Also used by Inmarsat.<GN{O' *O External resourcesb;?O ' vhttp://www.fas.org/spp/military/program/com/marisat.htm{O M1{O=1={: A Rt ݏ7ݏ7ݏ7Program: MarisatMarisat 1Marisat 2Marisat 3: =1 <Marisat 1J<8 @&.P" Marisat 11 m'  Generalg <ԁG#^@") Designation08697 / 76017A\m0A#R6Launch date19 Feb 1976t'ԁM#jN"N ,㹌לCountry of originUnited Stateso"0M#jD"H̀‰MissionTelecommunicationsb!uA#RB,Geostationary orbitsee belows&胊M#jL" &p㉂Launch vehicleThor Delta #120&u# 2 胊@'  Locationʄm#:   " BeginEndPosition@Pj#8$(*L: 19 Feb 1976105W(ʄ⅊j#P,.Mar 1995Mar 1997106W, inclined&P# 5⅊='  End of life^A#R:"Out of service1 Apr 1997T=A#R&Causedeorbited&# 8M' "(OTechnical dataI#& GTransmits in P- (250 MHz), L- (1.537-1.541 GHz) and C-band (4.195-4.199 GHz)The satellite uses the military aviation band in the 248.850 and 249.325 MHz (25 KHz raster): 20 channels for voice and data. They are also two 500 KHz channels for wideband transmissions (254.150-257.550 MHz).: MЈ1:Ј~Marisat 2J8 @&.P" Marisat 21 ЈK'  Generalg G#^@") Designation08882 / 76053A\KA#R6Launch date10 Jun 1976t'M#jN"N ,㹌לCountry of originUnited Stateso"M#jD"H̀‰MissionTelecommunicationsb!SA#RB,Geostationary orbitsee belows&ƋM#jL" &p㉂Launch vehicleThor Delta #124&S싊# 2 Ƌ'  Location싊m#:   " BeginEndPosition-j#6$(*L: 10 Jun 197673E)j#R,.Mar 1995Sep 199672.5E, inclined&-捊# 5'  End of life\捊wA#R6"Out of serviceSep 1996TˎA#R&Causedeorbited&w# 8ˎ)' "(OTechnical dataI#~& GTransmits in P- (250 MHz), L- (1.537-1.541 GHz) and C-band (4.195-4.199 GHz)The satellite uses the military aviation band in the 248.850 and 249.325 MHz (25 KHz raster): 20 c)~hannels for voice and data. They are also two 500 KHz channels for wideband transmissions (254.150-257.550 MHz).: )1 NJMarisat 3J~8 @&.P" Marisat 31 3'  Generalg G#^@") Designation09478 / 76101A\3A#R6Launch date14 Oct 1976t'jŠM#jN"N ,㹌לCountry of originUnited Stateso"ŠM#jD"H̀‰MissionTelecommunicationsb!jŠ;ÊA#RB,Geostationary orbitsee belows&ŠÊM#jL" &p㉂Launch vehicleThor Delta #127&;ÊÊ# : ÊĊ- */ۀ LocationÊĊm#:   " BeginEndPositionĊŊj#6$(*L: 14 Oct 197615W ĊŊj#@Mar 1995178W, inclinedŊ0Ɗj#>Oct 199672E, inclined&ŊVƊ# 80ƊƊ' "(OTechnical dataI#VƊNJ& GTransmits in P- (250 MHz), L- (1.537-1.541 GHz) and C-band (4.195-4.199 GHz)The satellite uses the military aviation band in the 248.850 and 249.325 MHz (25 KHz raster): 20 channels for voice and data. They are also two 500 KHz channels for wideband transmissions (254.150-257.550 MHz).@ƊȊ1.ȊcȊɊProgram: MeasatLNJcȊ5 :0fH" Program: MeasatMȊɊ7 < h̶-Malaysian East Asian SatelliteTelecommunication program operated by Measat Broadcast Network Systems, a subsidiary of a 1987 privatized company.Cost of the program: $235 million. Hughes also supplied equipment for a satellite control station on Malaysia's Langkawi Island and trained the Malaysian spacecraft controllers.1cȊʊ1ʊʊw6ɊʊA Rl*Program: MeasatMeasat 1Measat 2Measat 39ʊʊ18ʊ ˊMeasat 1Eʊ ˊ5 :"fH" Measat 11 ʊ>ˊ'  Generalg ˊˊG#^@") Designation23765 / 96002B\>ˊ̊A#R6Launch date12 Jan 1996o"ˊp̊M#jD"N ,-Country of originMalaysiao"̊̊M#jD"H̀‰MissionTelecommunicationsg p̊F͊G#^@"/ۀ0Geostationary orbit91.5En!̊͊M#jB" & E+Launch vehicleAriane V82&F͊͊# 8͊Ί' "(Technical dataH͊ZΊ) ">⩖~C-band EIRP coverage (dBW)8ΊΊ' " Specifications\ZΊΊA#R6&Prime contractorHughes]ΊKϊA#R8PlatformHS-376 enhanced[ΊϊA#R4"Mass at launch1450 kgYKϊ A#R0 Mass in orbit650 kgϊ ʊaϊmM#j(Diameter2.16 m[ A#R4Height7.82 m deployedo"m7M#jD"StabilizationSpin stabilizedf$B#THDC powerBOL: 1705 W?EOL: 800 W]7A#R8$Design lifetime12 years% IThe bird uses gallium arsenide solar cells instead of silicon. It also features a specially contoured surface that eliminates the need for multiple feed horns.0 '  C-bandYLA#R0(Main transponders12YA#R0,Backup transpondersVLA#R*Power12 W (SSPA)UPA#R(Bandwidth36 MHzy2G#^d"⩖~CoverageMalaysia, Philippines & South-IndiaTPA#R&EIRP max39 dBWXuA#R.Polarizationlinear@B#TFrequenciesUplink: 5.925-6.425 GHzDownlink: 3.700-4200 GHz&u# 1 N'  Ku-bandXA#R.(Main transponders4YNA#R0,Backup transpondersWVA#R,Power112 W (TWTA)UA#R(Bandwidth54 MHzAV-A#RCoveragenarrow spots: Malaysia or Philippines or South-IndiaTA#R&EIRP max57 dBWX-A#R.PolarizationlinearE` B#TFrequenciesUplink: 14.000-14.250 GHzDownlink: 10.950-11.200 GHz& # S,` ' X Ku-band transponder frequency chart (GHz)> #|  > V jl TransponderPolarizationDownlinkUplinkBeam1 o #b  021V10.98214.032Malaysia + Philippines1 , #b  022V11.04414.094Malaysia + Philippines#o #F  023V11.10614.156Malaysia#, #F  024V11.16814.218Malaysia& <#L  025V12.28413.784South-India& #L  026V12.34613.846South-India&<# 1E1ET6 <>" Measat 1's C-band EIRP9E1 A|#@zLMeasat 2E#@5 :"fH"#@ Measat 21 T@'  Generalg #@@G#^@") Designation24653 / 96063B\T@AA#R6Launch date13 Nov 1996o"@AM#jD"N ,-Country of originMalaysiao"AAM#jD"H̀‰MissionTelecommunicationsfA[BG#^>"/ۀ0Geostationary orbit148En!ABM#jB" &5E+Launch vehicleAriane V92&[BB# 8B'C' "(OTechnical data8B_C' " Specifications\'CCA#R6&Prime contractorHughesW_CDA#R,PlatformHS 376 HP[CmDA#R4"Mass at launch1520 kgSDDA#R$ Mass in orbity8mD9EA#RpDimension2.17 m diameter x 3.11 m (7.82 m deployed)QDEA#R Solar arrayb!9EEA#RB Stabilizationspin stabilizedTE@FA#R&DC power1705 W]EFA#R8$Design lifetime12 years&@FF# 0 FF'  C-bandXFKGA#R.(Main transponders6YFGA#R0,Backup transpondersK KGGA#RPowerUGDHA#R(Bandwidth72 MHzx7GHA#RnCoverageSouth-East Asia, East Australia and HawaiiN DH IA#REIRP maxRH\IA#R"Polarization& II# 1 \II'  Ku-bandXI JA#R.(Main transponders9YIdJA#R0,Backup transpondersK JJA#RPowerUdJKA#R(Bandwidth50 MHzqJKA#RCoverageswitchable (by transponder) to: Malaysia, Queensland/Australia, Indonesia, India and Vietnam +TaiwanN KLA#REIRP maxRKVLA#R"Polarization$LzL" 9VLL1BLLMeasat 3EzLL5 :"fH" Measat 31 L)M'  GeneralYLMG#^$") DesignationQ)MMA#R Launch dateo"MBNM#jD"N ,-Country of originMalaysiao"MNM#jD"H̀‰MissionTelecommunicationsaBNOG#^4"/ۀ0Geostationary orbit\NnOG#^*" &Launch vehicleuO& Bidding for this satellite: HCI, Lockheed Martin, Loral Space and AerospatialeCost expected: below $300 nOzLmillion1nOF1WFT+) "VȠ$To view this page you need to register&F# < 1 8Meteor (US)<8, ("" Meteor (US)b?# ~Multiple Experiment Transportation to Earth Orbit and Return1 8ˁ'  General\'G#^*") Designationn/a\ˁA#R6Launch date23 Oct 1995t''M#jN"N ,㹌לCountry of originUnited Statesm&dG#^L"H̀MissionScientific: MicrogravityWA#R,"Perigee/Apogeen/aTdA#R&Inclinationn/aO^A#RPeriodn/aq$τM#jH" &xLaunch vehicleConestoga #01h^7J#d<$Mass at launch~1000 kgτ) 1The satellite was a commercial microgravity recoverable spacecraft operated by EER Systems. Equipped with a Star 48 solid motorThe loss is amounted $20 million for the launcher and at least $73 million for the experiments3 commercial experiments onboard: an atomic-oxygen experiment from S-Cubed, a concentrator solar array from Able Engineering, and a Motorola payload whose details are unrevealed.57-'  End of life_A#R<"Out of service23 Oct 1995Z-懋A#R2CauseLauncher failed& # <懋H' *O External resourcesO( ' Phttp://www.cta-space.com/s23-00.htmlBHو1 و+Program: MeteosatR+8 @6_," Program: Meteosatو> Je   Series of meteorological satellites operated by Eumetsat. The satellites observe cloud formation across the full Earth disk and generate images in 3 spectral bands every 30 minutes.The 3 first satellites are experimental, the 3 next are operational: MOP (Meteosat OPerational). Then the program will use MTP (Meteosat Transition Program) and finally MSG (Meteosat Second Generation).<+1' * External resources\5' jhttp://www.esoc.esa.de/external/mso/meteosat.html111 xd 2_ϵaеaѵaҵaӵaԵaյa°SProgram: MeteosatMeteosat 1Meteosat 2Meteosat 3Meteosat 4Meteosat 5Meteosat 6Meteosat 7MSG1ˌ1Uˌ 0G$# HMeteosat 4, 5, 6's specificationsb!ˌtA#RB0&Prime contractorAerospatialeZ΍A#R20"Mass at launch681 kgYt'A#R00 Mass in orbit316 kgS΍zA#R$0Diameter2.1 mQ'ˎA#R 0Height3.1 ml+z7A#RV0 StabilizationSpin stabilized (100 rpm)d"ˎB#TD0DC powerBOL: 387 WEOL: 225 W\7 A#R60$Design lifetime5 years $0" 1 a1Uaċċ@0# :Meteosat 4, 5, 6's payloadBa' 6 Multispectral RadiometerdC#V&Wavebands0.4-1.1 m (visible)5.7-7.1 m (IR): water vapor absorption10.5-12.5 m (thermal IR)m+B#TV&Resolutionvisible: 2.5 kmothers: 5 kmp/g‹A#R^&2Image repeat frequency30 minutes (3 bands)~=‹A#Rz&&Telemetry - DataUHF- and S-band (1 transponder per band)r1g‹WËA#Rb&Data rate333 kbps (normal), 2.7 Mbps (burst)Y,‹Ë- *X  MMD (Meteorological Data Dissemination)mWË_ċB#T&,Channel frequenciesdigital high resolution (HR): 1694.5 MHzanalogue weather facsimile (WEFAX): 1691 MHzg&ËċA#RL&MDD (A & B)1.695.77 +/- 0.165 MHz$_ċċ" ; ċ%ŋ1@%ŋpŋ:ɋMeteosat 1Kċpŋ8 @(_," Meteosat 11 %ŋŋ'  Generalg pŋƋG#^@") Designation10489 / 77108A\ŋdƋA#R6Launch date23 Nov 1977m ƋƋM#j@"N ,4"Country of originEuropehdƋ9NjM#j6"H̀DVMissionMeteorologyYƋNjA#R0,Geostationary orbits&9NjȋM#jL" &p㉂Launch vehicleThor Delta #136ZNj_ȋA#R2"Mass at launch700 kg&ȋȋ# 5_ȋȋ'  End of life\ȋɋA#R6"Out of serviceOct 1984$ȋ:ɋ" ; ɋuɋ1'{uɋɋl͋Meteosat 2K:ɋɋ8 @(_," Meteosat 21 uɋɋ'  Generalg ɋXʋG#^@") Designation12544 / 81057A\ɋʋA#R6Launch date19 Jun 1981m Xʋ!ˋM#j@"N ,4"Country of originEuropehʋˋM#j6"H̀DVMissionMeteorologyY!ˋˋA#R0,Geostationary orbitn!ˋP̋M#jB" &'+Launch vehicleAriane L03Bˋ̋$ <Has provided 284000 images5P̋̋'  End of life@̋H͋A#R"Out of service6 Dec 1991 to the junk orbit (36119/36334 km)$̋l͋" ; H͋͋1/ @?͋͋Meteosat 3Kl͋͋8 @(_," Meteosat 31 ͋#΋'  Generalg ͋΋G#^@") Designation19215 / 88051A\#΋΋A#R6Launch date15 Jun 1988m ΋SϋM#j@"N ,4"Country of originEuropeh΋ϋM#j6"H̀DVMissionMeteorologyb!Sϋ)A#RB,Geoϋ)l͋stationary orbitsee belown!ϋM#jB" & D+Launch vehicleAriane V23&)# 2 '  Locationym#:   " BeginEndPosition"j#D$8:L: 15 Jun 1988Jun 19890Eyj#:,.Jun 1989Jan 199050Wj#8,.Jan 1990Apr 19900Ej#:.0Apr 1990?Nov 19905Wj#*Jul 199150Wj#, late 199275Wj#.Apr 199372.8W'j#N,.Feb 1995Nov 199570W, inclined{I$ In May 1995 Eumetsat decided it didn't need the satellite back so it remained in reserve around 70W before final burn.5~'  End of life`IA#R>"Out of servicemid Nov 1995c"~AA#RDCausepushed to the junk orbit&g# 8A' "(OTechnical dataW4g# hDownlink frequency: 137.08 & 1691 MHz + in S-band; 11{1| @Meteosat 4K|8 @(_," Meteosat 471# (Also called MOP 11 |'  Generalg K G#^@") Designation19876 / 89020B[ A#R4Launch date6 Mar 1989m K  M#j@"N ,4"Country of originEuropeh { M#j6"H̀DVMissionMeteorologyb! A#RB,Geostationary orbitsee belown!{ K M#jB" &D+Launch vehicleAriane V29C $ >First operational satellite2 K '  Location J m#:   " BeginEndPosition j#2"&(L: 6 Mar 19890EJ U j#<,.Feb 1995May 19957.7W' j#N,.Aug 1995Oct 199510E, inclined&U # 5 A'  End of lifeb! A#RB"Out of serviceEarly Nov 1995c"AA#RDCausepushed to the junk orbit&,# 8d' "(Technical data\, @2 4Ol "SpecificationsPayloadDownlink frequency: 137.08 MHz, 1691 & 1694.5 MHz + in S-bandd @; dG@1?8G@@(GMeteosat 5K @@8 @(_," Meteosat 57G@@# (Also called MOP 21 @@'  Generalg @aAG#^@") Designation21140 / 91015B[@AA#R4Launch date2 Mar 1991m aA)BM#j@"N ,4"Country of originEuropehABM#j6"H̀DVMissionMeteorologyb!)BBA#RB,Geostationary orbitsee belown!BaCM#jB" &^D+Launch vehicleAriane V42&BC# : aCC- */ۀ LocationCKDm#:   " BeginEndPositionCDj#2"&(L: 2 Mar 19910EKDTEj#8,.May 1997Feb 19989WDEj#< to indian ocean, 65EbTEbF$ Moved to 65E to take part in the INDOEX experiment (interaction between clouds and pollution)8EF' "(Technical data\bF(G2 4Ol "SpecificationsPayloadDownlink frequency: 137.08 MHz, 1691 & 1694.5 MHz + in S-band; FcG1cGGQNMeteosat 6K(GG8 @(_," Meteosat 67cGG# (Also called MOP 31 GH'  Generalg G}HG#^@") Designation22912 / 93073B\HHA#R6Launch date20 Nov 1993m }HFIM#j@"N ,4"Country of originEuropehHIM#j6"H̀DVMissionMeteorologyb!FIJA#RB,Geostationary orbitsee belown!I~JM#jB" &D+Launch vehicleAriane V61JiK' The radiometer didn't work in IR band thus temperature couldn't be measured. The problem could be solved in April 1995 after a software was developped to correct the data.Cost: $67.5 million: ~JK- */ۀ LocationiK-Lm#:   " BeginEndPosition#KLj#F$8:L: 20 Nov 1993Jan 199610W}-L7Mj#&Feb 19960&L]M# 87MM' "(Technical data]MQN4 6Ol "SpecificationsPayloadDownlink frequency: 137.08 MHz, 1691 & 1694.5 MHzEquipped with 1 S-band transponder. Data rate: 2.6 Mbps; MN18NN*Meteosat 7KQNN8 @(_," Meteosat 77NO# (Also called MTP 11 N?O'  Generalg OOG#^@") Designation24932 / 97049B[?O A#R4Launch date2 Sep 1997O QNm OzM#j@"N ,4"Country of originEuropeh ‌M#j6"H̀DVMissionMeteorology[z=A#R4,Geostationary orbit0n!‌M#jB" &njA#R6$Design lifetime2 years$ƌbnj" ?>njnj1njnj:ɌProgram: MidasKbnjnj5 :. " Program: MidasnjȌ)  MIssile Defense Alarm SystemAmerican military satellites for missile launch warning. Equipped with IR detectors and TV cameras.<njȌ' *O External resourcesd=Ȍ:Ɍ' zhttp://www.fas.org/spp/military/program/warning/midas.htm1ȌkɌ1kɌMʌw:ɌMʌk tA........c-Program: MidasMidas 02Midas 03Midas 04Midas 05Midas 06Midas 07Midas 08Midas 09Midas 109kɌʌ1ʌʌόMidas 02IMʌʌ8 @$ " Midas 02g;ʌ6ˌ, (v  Also called LASP (Low Altitude Surveillance Platform)1 ʌgˌ'  Generalg 6ˌˌG#^@") Designation00043 / 60006A\gˌ*̌A#R6Launch date24 May 1960t'ˌ̌M#jN"N ,㹌לCountry of originUnited Statesl%*̌ ͌G#^J"H̀MissionMilitary: early warning^̌h͌A#R:"Perigee/Apogee473/494 kmT ͌͌A#R&Inclination33Th͌ΌA#R&Period94.3 minq$͌ΌM#jH" &mO{Launch vehicleAtlas Agena A_ΌΌA#R<Launch siteCape Canaveral&Όό# 5Ό;ό'  End of lifeUόόA#R(Decay7 Feb 1974$;όό" 9ό 1w+ U$Midas 03ό όIόU8 @$ " Midas 031 '  Generalg UG#^@") Designation00163 / 61018A\IA#R6Launch date12 Jul 1961t'M#jN"N ,㹌לCountry of originUnited Statesl%I)G#^J"H̀MissionMilitary: early warning`A#R>"Perigee/Apogee3342/3541 kmV)A#R*Inclination91.2U4A#R(Period161.4 minq$M#jH" &mO{Launch vehicleAtlas Agena B[4A#R4Launch siteVandenberg$$" 9]1V]uMidas 04I$8 @$ " Midas 041 ]'  Generalg >G#^@") Designation00192 / 61028A\A#R6Launch date21 Oct 1961t'>M#jN"N ,㹌לCountry of originUnited Statesl%zG#^J"H̀MissionMilitary: early warning`A#R>"Perigee/Apogee3482/3763 kmVz0A#R*Inclination95.9UA#R(Period165.9 minq$0M#jH" &mO{Launch vehicleAtlas Agena B[QA#R4Launch siteVandenberg$u" 9Q1;+ Midas 05Iu8 @$ " Midas 05<3 # 2Also called Strongback1 d '  Generalg 3 G#^@") Designation00271 / 62010A[d & A#R4Launch date9 Apr 1962t' M#jN"N ,㹌לCountry of originUnited Statesl%&  G#^J"H̀MissionMilitary: early warning` f A#R>"Perigee/Apogee2784/3405 kmV A#R*Inclination86.7Uf  A#R(Period152.9 minq$ M#jH" &mO{Launch vehicleAtlas Agena B[ A#R4Launch siteVandenberg$  " 9 : 1;Vi: AMidas 06I 8 @$ " Midas 06:: # .Also called FTV 11691 '  Generalg UG#^@") Designation00574 / 63014A[ A#R4Launch date9 May 1963t'U$M#jN"N ,㹌לCountry of originUnited Statesl%G#^J"H̀MissionMilitary: early warning`$ @A#R>"Perigee/Apogee3607/3676 km @ Vb@A#R*Inclination87.3U @@A#R(Period166.4 minq$b@(AM#jH" &mO{Launch vehicleAtlas Agena B[@AA#R4Launch siteVandenberg$(AA" 9AA1?A)B7FMidas 07IA)B8 @$ " Midas 07?AhB# 8Also called ERS 10 or FTV1 )BB'  Generalg hBCG#^@") Designation00622 / 63030A\B\CA#R6Launch date18 Jul 1963t'CCM#jN"N ,㹌לCountry of originUnited Statesl%\C"Perigee/Apogee3672/3725 kmV"Perigee/Apogee3658/3708 kmVNMNA#R*Inclination89.7UMYNA#R(Period167.4 minq$NNM#jH" &mO{Launch vehicleAtlas Agena D[YN%OA#R4Launch siteVandenberg$NIO" 9%OO1HOO݃Midas 10IIOO8 @$ " Midas 10:O# .Also called OPS 1OIO9201 OB'  Generalg G#^@") Designation02481 / 66089A[BA#R4Launch date5 Oct 1966t'xM#jN"N ,㹌לCountry of originUnited Statesl%䁍G#^J"H̀MissionMilitary: early warning`xDA#R>"Perigee/Apogee3656/3721 kmT䁍A#R&Inclination90UD킍A#R(Period167.5 minq$^M#jH" &mO{Launch vehicleAtlas Agena D[킍A#R4Launch siteVandenberg$^݃" D!1A!e刍Program: MillenniumD݃e, (2" Program: Millennium^8!Æ& qProgram operated by a wholly owned subsidiary of Motorola. GEO Ka-band telecommunication system. To support residential and business communications that include: telecommuting, education, medical information access, home shopping, information services, access to on-line services and the Internet.Each satellite in the Millennium system will carry 57 transponders with 32 antenna beams, approximately 25 of which will be capable of using dual polarization. Both right- and left-hand circular polarization will be used. The system should use inter satellite linkse+ $-Based on ATM. Each satellite would have a maximum 7.5 Gbps throughput, each user could use 384 Kbps up to 51.84 Mbps. Near 60 GHz, 2000 MHz should be used for inter satellite links, 6 MHz are required in C-band for satellite control.Slots: 91W, 87W, 77W, and 75W, 1 satellite per slotDownlink: 19.7-20.2 GHzUplink: 28.35-28.6 and 29.5-30.0 GHzCost: $2.3 billion Should be operational in 20021 Æ' O Contact0 刍$ Comm, Inc11WjT+刍j) "VȠ$To view this page you need to register&# Ajщ1~щkProgram: MilstarM5 :23=F" Program: Milstarf<щ* "yUS military communication system. To provide secure worldwide wartime telecommunicationsThe project is made of 4 GEO satellites plus 2 LEO spacecraftsThe Milstar program estimated cost is $17.3 billion (1992-2011). Air Force officials said $8.8 billion of the unclassified $17.3 billion portion paid for the six satellites while another $8.5 billion will be spent on new radio gear needed by military units to use the satellites.Lockheed Martin Missiles & Space, Sunnyvale, CA, is the prime contractor for Milstar. The Milstar team is led by the MILSATCOM Joint Program Office at the Air Force Space and Missile Systems Center in El Segundo, CA. TRW Space and Electronics Group provides the low data rate payload for the satellite. Hughes Aircraft Company is providing the medium data rate payload for Milstar Block II.1 ' O ContactrM'% 50th Space Wing300 O'Malley Ave, Suite 24, Falcon AFB, CO 80912-3024, USA<c' *O External resources'k= Hhttp://www.fafb.af.mil/milstar/http://www.spacecom.af.mil/usspace/milstar1.htmhttp://www.fas.org/spp/military/program/com/milstar1.htmhttp://www.fas.org/spp/military/program/com/milstar2.htm1c1)@k)A Rc{AProgram: MilstarMilstar 1-1)kMilstar 1-2Milstar 2-11Z1Zč6)# &Milstar 1 series8Z' " Specificationse$-A#RH&Prime contractorLockheed MartinN {A#RPlatform\-A#R6"Mass at launch~4500 kgS{*A#R$ Mass in orbitOyA#RDimensionW*A#R,Solar array8000 WSy#ÍA#R$ StabilizationN qÍA#RDC powerU#ÍÍA#R($Design lifetime1 qÍÍ' O PayloadÍč) Low Data Rate payload (75 bps to 2400 bps):EHF (44.5 GHz) uplinkSHF (20 GHz) downlink4 UHF AFSATCOM transpondersThe satellites also have a 60 GHz crosslink to enable it to communicate with other Milstars< Í/ō1/ōwō[ɍMilstar 1-1Hčwō5 :(3=F" Milstar 1-19/ōō# ,Also called USA 0991 wōō'  Generalg ōHƍG#^@") Designation22988 / 94009A[ōƍA#R4Launch date7 Feb 1994t'HƍǍM#jN"N ,㹌לCountry of originUnited Statesy,ƍǍM#jX"H̀‰MissionMilitary: TelecommunicationsfǍǍG#^>"/ۀ0Geostationary orbit120WkǍaȍM#j<" &^]Launch vehicleTitan 4gǍȍJ#d:$Mass at launch4670 kg&aȍȍ# 8ȍ&ɍ' "(Technical data5 ȍ[ɍ) ";Details< &ɍɍ1<ɍɍ͍Milstar 1-2H[ɍɍ5 :(3=F" Milstar 1-29ɍʍ# ,Also called USA 1151 ɍIʍ'  Generalg ʍʍG#^@") Designation23712 / 95060A[Iʍ ˍA#R4Launch date6 Nov 1995t'ʍˍM#jN"N ,㹌לCountry of originUnited Statesy, ˍˍM#jX"H̀‰MissionMilitary: Telecommunications\ˍT̍A#R6,Geostationary orbit4Eo"ˍ̍M#jD" &^]Launch vehicleTitan 4 #14T0T͍̍$ `This satellite is estimated worth $1 billion8̍O͍' "(Technical data5 ͍͍) ";Details< O͍͍1'͍΍ Milstar 2-1H͍΍5 :(3=F" Milstar 2-11 ͍9΍'  GeneralY΍΍G#^$") Designation`9΍΍A#R>Launch dateplanned in 1998t'΍fύM#jN"N ,㹌לCountry of originUnited Statesy,΍ύM#jX"H̀‰MissionMilitary: TelecommunicationsYfύDA#R0ύD͍,Geostationary orbitkύM#j<" &^]Launch vehicleTitan 4[7D $ nMedium Data Rate payload (4.8 kbps upto 1.544 Mbps)1;1W;T+ ) "VȠ$To view this page you need to register&;# A1ACC/Program: MinisatMC5 :2B`F" Program: MinisatS', &OGKTSpanish microsatellite bus and program. Designed with low costs in mind, the bus is modular and aimed at the Pegasus launcher3 different buses are available: Minisat 0 (for varius scientific payloads), Minisat 1 (for remote sensing applications) and Minisat 2 (for communication payloads)<C' *O External resources]6/' lhttp://www.laeff.esa.es/~trapero/EURD/minisat.html1`1`V#/3 6FAK&Program: MinisatMinisat 01; `1 8Minisat 01G85 :&B`F" Minisat 011 i'  Generalg 8G#^@") Designation24779 / 97018A[i+A#R4Launch date4 Apr 1997lM#j>"N ,qn͉Country of originSpainu(+ M#jP"H̀_BMissionScientific: UV Astronomy`lA#R>"Perigee/Apogee562 / 581 kmj) A#RRInclination151 (inclination record)Tl*A#R&Period96.1 mino"M#jD" &GKTLaunch vehiclePegasus #17_*A#R<Launch siteCanary Islands>6 % 33 experiments are onboard: EURD (a spectrograph that will study the background radiation in the extreme ultraviolet range), LEGRI (will study the low energy gamma radiation from astronomic sources) and CPLM (to study the behaviour of liquid bridges in microgravity conditions).<r ' *O External resources_86 ' phttp://www.laeff.esa.es/~trapero/EURD/satellite.html8r ' "(OTechnical data8 A ' " SpecificationsZ A#R2&Prime contractorCASAWA A#R,PlatformMinisat 0Z L A#R2"Mass at launch195 kgS A#R$ Mass in orbitf%L  A#RJDimension2.487 x 2.554 x 1.170 mi( n A#RPSolar array4 panels, 45 W per panelY A#R0 Stabilization1 axisN n A#RDC powerU jA#R($Design lifetimeq% Data can be stored onboard (32 Mb) and transmitted at 1 Mbps through a 5 W S-band linkTransmits on 2.223 GHz8j81@8xCMiranda@x2 4"  Miranda48# "Also called X41 x'  Generalg P@G#^@P@") Designation07213 / 74013A[@A#R4Launch date9 Mar 1974u(P@ AM#jP"N ,R׉Country of originUnited Kingdomo(@AG#^P"H̀MissionTechnology experimentation^ AAA#R:"Perigee/Apogee677/865 kmVACBA#R*Inclination97.9UABA#R(Period100.3 minm CBCM#j@" &g'KLaunch vehicleScout #86YB^CA#R0"Mass at launch93 kg|XCC$ Built and operated by the RAE. Tested a stabilization system, solar panels and cells5^CD1KC.DDD^HMika5 CDD, (" Mika1 DuD'  Generalg DDDG#^@") Designation04345 / 70017B\uD8EA#R6Launch date10 Mar 1970m DEM#j@"N ,㱭+Country of originFranceU8EEG#^"H̀Mission_EYFA#R<"Perigee/Apogee302/1180 kmUEFA#R(Inclination5.4TYFGA#R&Period99.6 minn!FpGM#jB" &A͉Launch vehicleDiamant #5@GG$ 8First launch from Kourou5pGG'  End of lifeUG:HA#R(Decay9 Sep 1974$G^H" > :HH1.=HH]KProgram: MomoN^HH8 @.[G" Program: MomoHJ0 .3 Means "peach tree"Also called MOS (Marine Observation Satellite)Japanese remote sensing program. Mission: observethe oceans and marine/land phenomena, measure sea surface temperature and color, suspended sediment, stratospheric water vapor, ice and snow, vegetation characteristics and land use, geology, cartography, environmental monitoring, oceanography, etc.Orbital cycle: 17 days (237 periods)<HJ' * External resourcesnGJ]K' http://www.eoc.nasda.go.jp/guide/guide/satellite/satdata/mos_e.html1JK1KKa']KK: DNӔV$W$Program: MomoMomo 1AMomo 1B1K L1U LNN;K[L# 0Momo's specificationsY LLA#R00&Prime contractorNECZ[LMA#R20"Mass at launch740 kgb!LpMA#RB0Dimension1.26 x 1.48 x 2.4 mf%MMA#RJ0Solar arrayasymmetric, 2 x 5.3 mYpM/NA#R00 Stabilization3 axis\MNA#R60$Design lifetime2 years$/NN" 1NN1UNv4NO# "Momo's payloadk>NO- *|  MESSR (Multispectral Electronic Self-Scanning Radiometer) OE#X0Wavebands0.51-0.59 m (visible): water body mapping0.61-ON0.69 m (visible): vegetation differentiation0.72-0.80 m (near IR): imaging through haze0.80-1.10 m (near IR): land/water separationTOꀎA#R&0Resolution50 mWAA#R,0Swath width100 kmZ-ꀎ- *Z  VTIR (Visible and Thermal IR Radiometer)P A낎E#X0Wavebands0.50-0.70 m (visible): snow. ice and cloud6-7 m (water vapor band): upper atmosphere water vapor, cirrus10.5-11.5 m (thermal IR): ocean currents. sea surface temperature, snow10.5-12.5 m (thermal IR): ocean currents. sea surface temperature, snowo.ZA#R\0Resolutionvisible: 0.9 km; others: 2.7 kmX낎A#R.0Swath width1500 kmU(Z- *P  MSR (Microwave Scanning Radiometer)fB#T0Wavebands23.8 +/- 0.2 GHz: water vapor, rain and snowfall31.4 +/- 0.25 GHz: ice, cloud, snowfallp/A#R^0Resolution32 km in 23 GHz and 23 in 31 GHzWvA#R,0Swath width317 km$" 8v҅1 ҅ Momo 1AH8 @"[G" Momo 1A8҅R# *Also called MOS 1A1 '  Generalg RꆎG#^@") Designation17527 / 87018A\FA#R6Launch date19 Feb 1987lꆎM#j>"N ,bCountry of originJapankFM#j<"H̀郉MissionRemote sensing^{A#R:"Perigee/Apogee907/909 kmTψA#R&Inclination99U{$A#R(Period103.2 minfψM#j2" &JLaunch vehicleN2&$# 5剎'  End of lifeW<A#R,"Out of serviceyes&剎b# 8<' "(Technical datao=b 2 4zM܀n‰SpecificationsPayloadDownlink frequency: 136.12 MHz8A19{AMomo 1BH 8 @"[G" Momo 1B8A# *Also called MOS 1B1 '  Generalg YG#^@") Designation20478 / 90013A[A#R4Launch date7 Feb 1990lY M#j>"N ,bCountry of originJapankM#j<"H̀郉MissionRemote sensing^ 鍎A#R:"Perigee/Apogee907/909 kmT=A#R&Inclination99U鍎A#R(Period103.2 minf=M#j2" &JLaunch vehicleH1&# 5S'  End of life_A#R<"Out of service19 May 1996&S؏# 8' "(؏ Technical datao=؏2 4zM܀n‰SpecificationsPayloadDownlink frequency: 136.12 MHzA1 c"Program: MorelosQ8 @4{" Program: Morelos> J5'e` w퉂 Mexican telecommunication program operated by Telecomm. The program has been replaced by Solidaridad.This program is now controlled by Satmex1&Ž1&ŽŽ{:ŽA Rttz6wFFFProgram: MorelosMorelos 1Morelos 2Morelos 31&ŽŽ1UŽ9Ǝ]Ǝ>ŽÎ# 6Morelos's specifications\ŽlÎA#R60&Prime contractorHughesTÎÎA#R&0PlatformHS-376[lÎĎA#R40"Mass at launch1140 kgYÎtĎA#R00 Mass in orbit666 kgTĎĎA#R&0Diameter2.16 mZtĎ"ŎA#R20Height6.6 m deployedb!ĎŎA#RB0 StabilizationSpin stabilizedX"ŎŎA#R.0DC powerBOL: 940 W]Ŏ9ƎA#R80$Design lifetime10 years$Ŏ]Ǝ" 19ƎƎ1UƎɎɎ6]ƎƎ# &Morelos's C-band[ƎǎA#R40(Main transponders12+6\Ǝ{ǎA#R60,Backup transponders4+2aǎȎB#T0Power(6+2) transponders of 72 MHz: 10.5 W (TWTA)(12+4) transponders of 36 MHz: 7.5 W (TWTA)H{ǎȎB#T0Bandwidth(6+2) transponders of 72 MHz(12+4) transponders of 36 MHzTȎȎA#R&0CoverageMexicoTȎPɎA#R&0EIRP max39 dBWXȎɎA#R.0Polarizationlinear$PɎɎ" 1ɎɎ1UɎ̎̎7Ɏ4ʎ# (Morelos's Ku-bandXɎʎA#R.0(Main transponders4Z4ʎʎA#R20,Backup transponders2Vʎ<ˎA#R*0Power20 W (TWTA)VʎˎA#R*0Bandwidth108 MHzT<ˎˎA#R&0CoverageMexicoTˎ:̎A#R&0EIRP max40 dBWZˎ̎A#R20Polarizationlinear H$:̎̎" \+͎̎1͎͎Morelos' C-band transponder frequency charts9͎̎: Dtback()"  Morelos' C-band transponder frequency chart (GHz)&͎͎# n͎Ύ#$uxyqy * X v   HorizontalUplinkHorizontalDownlinkTransponderChannelVerticalDownlinkVerticalUplink͎fώ#ڀ8uxyqy &*3.7201W/L15.945Ύ#ڀ4uxyqy"05.9651N23.74fώ̎0fώ#ڀ8uxyqy &*3.7601W/U35.985Q#ڀ4uxyqy"06.0052N43.780#ڀ8uxyqy &*3.8003W/L56.025Q#ڀ4uxyqy"06.0453N63.8202#ڀ8uxyqy &*3.8402W/U76.065#ڀ4uxyqy"06.0854N83.8602r#ڀ8uxyqy &*3.8803W/L96.105#ڀ6uxyqy$26.1255N103.900r#ڀ:uxyqy (,3.9203W/U116.145T#ڀ6uxyqy$26.1256N123.940#ڀ:uxyqy (,3.9604W/L136.185T#ڀ6uxyqy$26.2057N143.9808#ڀ:uxyqy (,4.0004W/U156.225#ڀ6uxyqy$26.2458N164.0208z #ڀ:uxyqy (,4.0405W/L176.265 #ڀ6uxyqy$26.2859N184.060z #ڀ:uxyqy (,4.0805W/U196.305 ] #ڀ8uxyqy&46.32510N204.100 #ڀ:uxyqy (,4.1206W/L216.345] #ڀ8uxyqy&46.36511N224.140 B #ڀ:uxyqy (,4.1606W/U236.385 #ڀ8uxyqy&46.40512N244.180$B " 1 81U8AA^7' nMorelos' Ku-band transponder frequency chart (GHz)c8#uxyx * X v  HorizontalUplinkHorizontalDownlinkTransponderVerticalDownlinkVerticalUplink%@t#2uxyx"%@11.7641K14.064@t#2uxyx"11.8882K14.188%@?At#2uxyx"12.0123K14.312@At#2uxyx"12.1364K14.436$?AA" : A*B1ρ*BtBFMorelos 1JAtB8 @&{" Morelos 11 *BB'  Generalg tB CG#^@") Designation15824 / 85048B\BhCA#R6Launch date17 Jun 1985m CCM#j@"N ,Country of originMexicoo"hCDDM#jD"H̀‰MissionTelecommunications`CDA#R>,Geostationary orbit113.5WjDDEM#j:" &QLaunch vehicleSTS 25&D4E# 5EiE'  End of lifeW4EEA#R,"Out of serviceyes&iEE# 8EF' "(Technical dataqEFE Zb<rz/+loz"USpecificationsC-bandKu-bandC-band transponder frequency chartKu-band transponder frequency chart: FG1M,GXGKMorelos 2JFXG8 @&{" Morelos 21 GG'  Generalg XGGG#^@") Designation16274 / 85109B\GLHA#R6Launch date27 Nov 1985m GHM#j@"N ,Country of originMexicoo"LH(IM#jD"H̀‰MissionTelecommunicationsh!HIG#^B"/ۀ0Geostationary orbit116.8Wj(IIM#j:" &xLaunch vehicleSTS 31&I J# 8IXJ' "(Technical dataq JKE Zb<rz/+loz"USpecificationsC-bandKu-bandC-band transponder frequency chartKu-band transponder frequency chart: XJHK1 ρHKK;Morelos 3FKK5 :${" Morelos 36HKK# &Renamed SatMex 51 KK'  GeneralYKNLG#^$") DesignationZKLA#R2Launch datelate 1998m NLMM#j@"N ,Country of originMexicoo"LMM#jD"H̀‰MissionTelecommunications`MMA#R>,Geostationary orbit116.8WjMNNM#j:" &2!Launch vehicleArianeYMNG#^$Launch sited?NN O% ~coverage: from Canada to ArgentinaTotal cost: $230 million8NCO' "(OTechnical data8 O{O' " Specifications\COOA#R6&Prime contractorHughesV{O9A#R*O9KPlatformHS-601HP[OA#R4"Mass at launch3550 kgS9瀏A#R$ Mass in orbitO6A#RDimensionQ瀏A#R Solar arrayS6ځA#R$ StabilizationT.A#R&DC power7615 W]ځA#R8$Design lifetime15 years&.# 0 ႏ'  C-bandY:A#R0(Main transponders24YႏA#R0,Backup transpondersV:郏A#R*Power36 W (TWTA)O8A#RBandwidthT郏A#R&Coverage1 beamN 8ڄA#REIRP maxR,A#R"Polarization&ڄR# 1 ,'  Ku-bandYR܅A#R0(Main transponders24Y5A#R0,Backup transpondersE܅B#TPower12 transponders: 110 W (TWTA)12 transponders: 132 W (TWTA)O5 A#RBandwidthj(uB#TPCoverage2 beamsCanada to ArgentinaN ÇA#REIRP maxRuA#R"Polarization&Ç;# 1l1Wl戏T+;) "VȠ$To view this page you need to register&l戏# 71=TʏMSAT 17 戏T, (" MSAT 11 '  Generalg T쉏G#^@") Designation23846 / 96022A\HA#R6Launch date20 Apr 1996m 쉏M#j@"N ,xW Country of originCanadat$H)P#pH(OOperatorTMI Communicationso"M#jD"H̀‰MissionTelecommunicationsh!)G#^B"/ۀ0Geostationary orbit106.5Wn!nM#jB" &2!Launch vehicleAriane V8573 4-S NgThis satellite is a twin of AMSC 1. Both satellites were ordered at the same time (with separate contracts). Both operators will provide complementary mobile telephone, radio, data, and positioning service to land, aviation, and maritime users. Each operator also will provide the other with backup and restoration capacity.Should move to 101W and be jointly operated by AMSC and TMI in mid-1998<ns' *O External resourcesB7' 6http://www.msat.tmi.ca/8s펏' "(OTechnical data8%' " SpecificationsC펏B#T&Prime contractorSPARHughes (bus) and SPAR Aerospace (payload)T% A#R&PlatformHS-601 戏[gA#R4"Mass at launch2830 kgZ A#R2 Mass in orbit1600 kgd#g%A#RFDimension2.5 m x 3.5 m x 7.9 m]A#R8Solar array20.96 m spanY%A#R0 Stabilization3 axisY4A#R0DC powerBOL: 4000 W]A#R8$Design lifetime12 years4AÏ% Springback antennas: 6.7 x 4.9 m x 20 kg (for launch the 2 antennas as rolled together into a 4.9 m high cone shape atop the satellite)N'Ï' N L-band (1545-1559/1646.5-1660.5 MHz)YAÏÏA#R0(Main transponders16ZÏBďA#R2,Backup transponders4VÏďA#R*Power38 W (SSPA)OBďďA#RBandwidthWďŏC#VCoverageNorth America (4 spot beams)Alaska and Hawaii (1 beam)Carribean (1 beam)TďŏA#R&EIRP max57 dBWEŏȏ' =Total bandwith: 3200 x 5 KHzEach beam transponder is equipped with eight surface acoustic wave filters covering the 29 MHz L-band allocation, allowing selection of filters to math traffic needs and to coordinate with other international users. Frequency reuse is incorporated between the North American east and west beams. The beams are combined into two L-band power pools, one covering the east and central beams, and the other covering the remaining service areas. Each power pool is generated by a hybrid matrix amplifier assembly.1 ŏKȏ'  Ku-bandXȏȏA#R.(Main transponders1ZKȏȏA#R2,Backup transponders2WȏTɏA#R,Power100 W (TWTA)OȏɏA#RBandwidthy8TɏʏA#RpCoverageCONUS, Carribean, Canada, Alaska and HawaiiTɏpʏA#R&EIRP max37 dBWRʏʏA#R"Polarization<pʏʏ$ 0Beacon: 11.70275 MHzFʏDˏ1n"Z DˏˏProgram: Morning StarFʏˏ, (6" Program: Morning StarDˏp͏( }Morning Star is Delaware-based LLC company. It plans to launch 4 satellites to offer services such as high speed data, voice, and interactive video communications. The systems uses Ku-band as forward path and Ka-band as return path. The system should be operational in May 2002.Although FCC has granted authorization for Ka-band operations in May 1997, Ku-band operations in delayed. Cost: $847 millionGEO slots: 147W, 107.5W, 62W, 30E8ˏ͏' "(OTechnical data@p͏͏' 2 Ku-band (forward path)Y͏AΏA#R0(Main transponders16Y͏ΏA#R0,Backup transpondersK AΏΏA#RPowerUΏ:ϏA#R(Bandwidth24 MHzN ΏϏA#RCoverageJ :ϏϏA#REIRPRϏ0A#R"Ϗ0ʏPolarization&ϏV# W00' ` Ka-band (return path, up to 64 kbps channels)WVA#R,(Main transpondersY]A#R0,Backup transpondersK A#RPowerO]A#RBandwidthN EA#RCoverageN A#REIRP maxREA#R"Polarizationc!HB#TBFrequenciesUplink:Downlink:g$ a single steerable spot will be used for Ku-band uplink and Ka-band downlink to the control center.1H1WX~T+X) "VȠ$To view this page you need to register&~# > X14! Program: MSTIJ~5 :,yG" Program: MSTI;A) % Miniature Seeker Technology IntegrationUS technological program lead by the Air Force Phillips labs. Previously funded by the Ballistic Missile Defense Organization (BMDO), the MSTI program is now under the direction of USAF. It is probably mostly of military interest<}' * External resources^A . ,http://www.actgate.com/msti3/default.htmlhttp://www.plk.af.mil/PLhome/SUCCESS/msti.html1}:1:o. A R\޲xxxProgram: MSTIMSTI 1MSTI 2MSTI 37:1$ '@MSTI 1G'8 @ yG" MSTI 11 X'  Generalg 'G#^@") Designation22229 / 92078Ah'X' A#RNLaunch date21 Nov 1992 at 13:45 UTt' M#jN"N ,㹌לCountry of originUnited Stateso(' G#^P"H̀MissionTechnology experimentation^ h A#R:"Perigee/Apogee289/366 kmV A#R*Inclination96.7Th  A#R&Period91.1 minn! M#jB" &g'KLaunch vehicleScout #116Z A#R2"Mass at launch135 kg} | % Designed to test instruments for star war. Two other satellites should be launched.Cost of the 3 satellites: $19 million< ' *O External resourcesb| H . ,http://www.actgate.com/msti3/msti1.htmlhttp://www.spectrumastro.com/Programs/Msti/MSTI1.asp8 ' "(OTechnical data8H ' " Specificationsd# A#RF&Prime contractorSpectrum AstroX tA#R.PlatformARPA ASSTDTA#R&"Mass at launchStA#R$ Mass in orbitOjA#RDimensionQA#R Solar arraySj@A#R$ Sta@bilizationN h@A#RDC powerU@@A#R($Design lifetime&h@@# 7@A1#  AaAGMSTI 2G@aA8 @ yG" MSTI 21 AA'  Generalg aAAG#^@") Designation23101 / 94028Ag&A`BA#RLLaunch date9 May 1994 at 02:47 UTt'ABM#jN"N ,㹌לCountry of originUnited States_`B3CG#^0"H̀MissionTechnology^BCA#R:"Perigee/Apogee411/427 kmV3CCA#R*Inclination97.1TC;DA#R&Period92.9 minn!CDM#jB" &g'KLaunch vehicleScout #118Z;DEA#R2"Mass at launch135 kg5D8F' It was the last of the now discontinued Scout series. The satellite successfully tracked a Minuteman III ICBM on June 8, 1994, and collected over 3 million images for analysis during its mission.On 15 Sep 1997 this spacecraft passed by Mir, only at 470 m distance!5EmF'  End of life\8FFA#R6"Out of serviceSep 1994&mFF# <F+G' *O External resourcesbFG. ,http://www.actgate.com/msti3/msti2.htmlhttp://www.spectrumastro.com/Programs/Msti/MSTI2.asp7+GG1N $ G9HЀMSTI 3GG9H8 @ yG" MSTI 31 GjH'  Generalg 9HHG#^@") Designation23868 / 96031A\jH-IA#R6Launch date17 May 1996t'HIM#jN"N ,㹌לCountry of originUnited States_-IJG#^0"H̀MissionTechnologyk*IkJA#RT"Perigee/Apogee425 km (sunsynchronous)TJJA#R&Inclination97L kJ KA#RPeriodo"JzKM#jD" &GKTLaunch vehiclePegasus #11Z KKA#R2"Mass at launch211 kgH!zKN' CExperimental satellite to collect data on short- and medium-wave infrared band, radiating from ground features, bodies of water and atmospheric bodies, such as clouds. Will demonstrate more sophisticated sensors and data gathering capabilities.On 19 Oct 1997 the Army's Miracl laser was tested against it. Two beams were fired, the first of less than one second duration (in order to lock on to the satellite) and the second of about 10 seconds (in order to kill it). It is believed the experiment failed, the satellite was not destroyed.<KXN' *O External resourcesN*O6 :9http://www.actgate.com/msti3/msti3.htmlhttp://www.spectrumastro.com/Programs/Msti/MSTI3.asphttp://www.fas.org/spp/military/program/asat/miracl.htm8XNbO' "(OTechnical datab;*OЀ' wBuilt by Spectrum Astro IncMTSI 3 is about 3 m long and 1 m in diameterPayload: MWIR camera, SWIR camera, and a visbOЀGible imaging spectrometer (provided by Science Applications International Corporation (San Diego, CA)) The vehicle also has a 12 channel onboard GPS receiver for real time orbit determination. 4bO1 Z .!@MSX< Ѐ@2 4"  MSXG!& B Middlecourse Space Experiment1 @'  Generalg G#^@") Designation23851 / 96024A\{A#R6Launch date24 Apr 1996t'M#jN"N ,㹌לCountry of originUnited States<{rG#^xOperatorBallistic Missile Defense Organization (BMDO)UǃG#^"H̀Mission^r%A#R:"Perigee/Apogee896/906 kmTǃyA#R&Inclination99L %ńA#RPeriodp#y5M#jF" &p㉂Launch vehicleDelta 2 #235[ńA#R4"Mass at launch2600 kgE5Շ' =Will study the infrared, visible and ultraviolet signatures of ballistic missiles in their midcourse phase (after the launch vehicle rocket plume has shut down). MSX will also perform civilian scientific research, with atmospheric observations and astronomical studies. It will provide data on small debris in space.Johns Hopkins University's Applied Physics Laboratory built the MSX spacecraft for the BMDO. The Spirit III cryogenic-cooled infrared sensor system was supplied to BMDO by Utah State University/Space Dynamics Laboratory.J&$ LReleased a few tiny sub-satellites<Շ[' *O External resourcesn@Ɉ. ,http://msx.nrl.navy.milhttp://www.mrcnh.com/msx/index.htm8[' "(OTechnical dataM)ɈN$ RTelemetry: 2282.5 MHzData: 8475.0 MHz1 ' O Payload?ND V    _BSPIRIT III: 0.34m Spatial IR Imaging Telescope, 2.5 -28 micronsUVISI: UV and Visible Imagers and Spectrographic ImagersCIC: Contamination Instrumentation Complement (to study outgassing and contamination of optical surfaces)SBV: Space Based Visible camera, 0.15m telescope/CCDSpirit III is the first cryogenic infrared telescope to use solid hydrogen instead of the liquid helium that has been used by infrared astronomy satellites in the past. The hydrogen will maintain the dewar at 8.5K.11- # Muses BwQ& [M-5]More detail on the schedule slip of the M-5. The problem is finding welding cracks in the M-5 motor casings; such a crack is blamed for a rupture in a 1993 pressure test, and both improved materials and improved testing methods have been introduced as a result. The loss of the last M-3S-2 has put ISAS under considerable pressure to make sure the M-5 works properly. Original date for the first launch was mid-1995. It's now mid-1996, and a further six-month slip is likely due to side effects of the Kobe earthquake. ISAS is unhappy that tight funding will restrict static testing.% {Meanwhile, development is on track for the first M-5 payloads. The Muses-B VLBI radio-astronomy spacecraft (including a 10m dish antenna) will be ready for launch (into a 620x6200mi elliptical orbit) in mid-1996. The Lunar-A mission, a lunar orbiter carrying three penetrator landers, will be ready for mid-1997 launch. And early testing is underway on the Planet-B spacecraft, a fields-and-particles Mars orbiter, set to fly in winter 1998.11W,T+) "VȠ$To view this page you need to register&,# 6b1 !Ӄ!bʐMTSat6 ,, (" MTSatJ'b# NMulti-functional Transport Satellite1 '  GeneralYlG#^$") DesignationYA#R0Launch datemid 1999ll1ÐM#j>"N ,bCountry of originJapan4ÐS#vh"H̀(‰DVMissionTelecommunications and meteorology^1ÐĐA#R:,Geostationary orbit140E^ÐtĐG#^." &Launch vehicleH2YĐĐG#^$Launch site8 tĐƐ/ ,vSJapanese system for air traffic control and weather observation. Ordered by the Japanese Ministry for Transport & Meteorological agency to Space Systems/Loral ($102 million).Possible option for a second satellite in 2004Is the successor of the GMS program<ĐAƐ' *O External resourcesL%ƐƐ' Jhttp://www.mpt.go.jp/index-e.html8AƐƐ' "(OTechnical data8ƐƐ' " SpecificationsZƐWǐA#R2&Prime contractorSS/LUƐǐA#R(PlatformFS-1300TWǐȐA#R&"Mass at launchSǐSȐA#R$ Mass in orbitOȐȐA#RDimensionQSȐȐA#R Solar arraySȐFɐA#R$ StabilizationN ȐɐA#RDC powerUFɐɐA#R($Design lifetimepɐʐ& Would operate in UHF-, L-, S-, Ku- and Ka-bandWeather sensor built by ITT Aerospace/Commnucations division1ɐʐ1Wʐː*ːT+ʐː) "VȠ$To view this page you need to register&ʐ*ː# 6ː`ː1.!"`ːː+Musat6 *ːː, (" Musat?`ːː# 8Also called Microsatelite1 ː̐'  Generalg ːm̐G#^@") Designation24291 / 96050Ah'̐̐A#RNLaunch date29 Aug 1996 at 05:22 UTp#m̐E͐M#jF"N ,㉕U剂Country of originArgentina_̐͐G#^0"H̀MissionScientific_E͐ΐA#R<"Perigee/Apogee244/1192 kmV͐YΐA#R*Inclination62.8L ΐΐA#RPeriodeYΐ ϐG#^<" &Launch vehicleMolniya M^ΐhϐA#R:Launch sitePlesetsk LC43 ϐZ) {Small experimental payload from the Instituto Universitario Aeronautico de Cordoba, ArgentinaThe launch coshϐZ*ːted $200,000The satellite carries 2 CCD cameras (70 m and 2 km resolution)8hϐ' "(OTechnical data8Z' " SpecificationsV A#R*&Prime contractorN nA#RPlatform[ A#R4"Mass at launch34.5 kgXn!A#R. Mass in orbit32 kg^A#R:Dimension33 x 43 x 50 cmQ!A#R Solar arrayS#A#R$ StabilizationN qA#RDC powerU#A#R($Design lifetimee@q+% Beacon: 137.95 MHzData & telemetry: 400.95 MHz & 2260.5 MHz6a1;Ӄ!G"aMyojo> +2 4"  MyojoZ1a) "b Also called VEP (Vehicle Evaluation Payload)1 *'  Generalg G#^@") Designation22979 / 94007B[*A#R4Launch date3 Feb 1994lXM#j>"N ,bCountry of originJapan[G#^(OperatorNASDA_XG#^0"H̀MissionTechnology`rA#R>"Perigee/Apogee430/36114 kmWA#R,Inclination29.12VrA#R*Period641.95 minfM#j2" &JLaunch vehicleH2$" 81O"" 7Mysat 18  , (" Mysat 1=V $ 2Also called Tiungsat 11  '  GeneralYV G#^$") Designationd# D A#RFLaunch dateplanned in Mar 1998o" M#jD"N ,-Country of originMalaysia<D 6 G#^x"H̀MissionScientific: remote sensing & telecomunicationsT A#R&"Perigee/ApogeeQ6 A#R InclinationL ' A#RPeriodi M#j8" &'CMLaunch vehicleZenitQ' A#R Launch siteV' 7/ ,Okdgpayload includes a 1 km resolution camera for meteorology (storm alert), a 80 m multispectral camera and a telecommunication transponder (HAM)Cost: $12 million50 kgBuilt by SSTL with engineers from Astronautic Technology Sdn Bhd (ATSB). The main ground station will be in Kuala Lumpur.1 h1WhT+7) "VȠ$To view this page you need to register&h# @"1G""nAProgram: N StarLn5 :0Ǣa" Program: N Star."A4 6{O\򉂂Japanese telecommunication operated by NTT program that follows the Sakura series.The snAatellites will provide inter-orbit links, high quality DBS TV and mobile links. They will enable the use of cellular phones anywhere in Japan (in 1995 the existing cellular phone system covers 95% of Japan's populated areas but does not cover mountainous areas). This service will be provided by NTT's mobile phone unit, NTT Mobile Communications Network Inc.Designed to replace the Sakura 3A & 3B satellites1nA1A>Be+A>B: DV4) * Program: N StarN Star aN Star b1AoB1UoBVFzF=>BB# 4N Star's specificationsi(oBCA#RP0&Prime contractorSpace Systems/LoralUBjCA#R(0PlatformFS 1300[CCA#R40"Mass at launch3400 kgZjCDA#R20 Mass in orbit2050 kgUCtDA#R(0Dry mass1617 kg`DDA#R>0Dimension3.1 x 2.4 x 2.2 mWtD+EA#R,0Solar array27.3 mYDEA#R00 Stabilization3 axiso.+EEA#R\0DC power5200 W, nickel-hydrogen batteriesc"EVFA#RD0$Design lifetime10 to 12 years$EzF" 1VFF1UF'IKI5zFF# $N Star's S-bandXF8GA#R.0(Main transponders4YFGA#R00,Backup transpondersK 8GGA#R0PowerOG+HA#R0Bandwidth\GHA#R60CoverageJapan, 4 beamsN +HHA#R0EIRP maxRH'IA#R"0Polarization$HKI" 1'I|I1U|IKL5KII# $N Star's C-bandX|I JA#R.0(Main transponders6YIbJA#R00,Backup transpondersV JJA#R*0Power20 W (TWTA)ObJKA#R0BandwidthSJZKA#R$0CoverageJapanN KKA#R0EIRP maxRZKKA#R"0Polarization$KL" 1KOL1UOL8O\O6LL# &N Star's Ku-bandXOLLA#R.0(Main transponders8YL6MA#R00,Backup transpondersVLMA#R*0Power40 W (TWTA)O6MMA#R0BandwidthSM.NA#R$0CoverageJapanN M|NA#R0EIRP maxR.NNA#R"0Polarizationj)|N8OA#RR0FrequenciesDownlink: 12.19-12.91 GHz$N\O" 18OO1O6\OO# &N Star's Ka-bandYO(A#R00(O(\OMain transponders11YOA#R00,Backup transpondersV(׀A#R*0Power20 W (TWTA)O&A#R0BandwidthS׀yA#R$0CoverageJapanN &ǁA#R0EIRP maxRyA#R"0Polarizationj)ǁA#RR0FrequenciesDownlink: 17.75-19.45 GHzkG$ For military purposes & switched TDMA service on Ka-band multi-beam9'1<#'lwN Star AEl5 :"Ǣa" N Star a1 ''  Generalg lG#^@") Designation23651 / 95044A\`A#R6Launch date29 Aug 1995l̄M#j>"N ,bCountry of originJapano"`;M#jD"H̀‰MissionTelecommunicationsf̄G#^>"/ۀ0Geostationary orbit132En!;M#jB" &D+Launch vehicleAriane V77% An accident during transportation to the launch site damaged the spacecraft which delayed it. Was delivered in orbit in late October 19958' "(Technical data~9wE Zr2⢙{݉⒙{݉33SpecificationsS-bandC-bandKu-bandKa-band91#kN Star BEw5 :"Ǣa" N Star b1 &'  Generalg G#^@") Designation23781 / 96007A[&舑A#R4Launch date5 Feb 1996lTM#j>"N ,bCountry of originJapano"舑ÉM#jD"H̀‰MissionTelecommunications^T!A#R:,Geostationary orbit136En!ÉM#jB" & E+Launch vehicleAriane V83&!# 8튑' "(Technical data~9kE Zr2⢙{݉⒙{݉33SpecificationsS-bandC-bandKu-bandKa-band@튑14$Program: NahuelLk5 :0xV" Program: Nahuel-$2 2/y/yArgentine first telecommunication program operated by Nahuelsat. The broadcasting license will be for 24 years, with an extension option for an additional 6 years. Nahuelsat is owned by three leading European aerospace companies -- Deutsche Aerospace (Germany), Aerospatiale (France), and Alenia Spazio (Italy). Other private corporate and institutional equity investors, mainly from Argentina, Brazil, and Europe, have acquired stakes in Nahuelsat as well. Telecom Argentina acquired 5.57 percent.DE X/yV倉CDD"/yThe Nahuelsat control center will be collocated with the Ground Station in the Buenos Aires area. After an agreement with Embratel (the operator of Brasilsat) the system will be operated by the Brazilian company.In mid-Jan 1997 GE Americom acquired 17.25 percent of the $100-million equity of Nahuelsat S.A.1$ޏ1ޏQg-Q: DZ"%ޏQǀS_ET_EProgram: NahuelNahuel 1ANahuel 1B: ޏ1a$  Nahuel 1AFQ5 :$xV"  Nahuel 1A1 '  Generalg iG#^@") Designation24714 / 97002B\A#R6Launch date30 Jan 1997p#i5‘M#jF"N ,㉕U剂Country of originArgentinao"‘M#jD"H̀‰MissionTelecommunications_5‘ÑA#R<,Geostationary orbit71.8Wn!‘qÑM#jB" &6E+Launch vehicleAriane V93V2ÑÑ$ dThe launch was also contracted with Long March8qÑÑ' "(OTechnical data=Ñ<đ' , EIRP coverage (dBW)e.Ñđ7 >\t~t~t~Argentina beamBrazil beamLarge beam8<đđ' " SpecificationsZđ3őA#R2&Prime contractorDASA[đőA#R4PlatformSpacebus 2000[3őőA#R4"Mass at launch1780 kgTő=ƑA#R&Dry mass828 kgs2őƑA#RdDimensions1.64 x 1.46 x 2.2 m (22.3 deployed)Y=Ƒ ǑA#R0 Stabilization3-axisYƑbǑA#R0DC powerBOL: 3200 W] ǑǑA#R8$Design lifetime12 years[7bǑȑ$ ncontrol station at Benevidez, Buenos Aires province1 ǑKȑ'  Ku-bandYȑȑA#R0(Main transponders18ZKȑȑA#R2,Backup transponders6VȑTɑA#R*Power55 W (TWTA)UȑɑA#R(Bandwidth54 MHzLTɑJʑU#z8,t~t~t~Coverage & EIRP maxArgentina: 50 dBWBrazil: 51 dBWLarge: 41 dBW\ɑʑA#R6Polarizationlinear H/V&Jʑʑ# K$ʑˑ' H Transponder frequency chart (GHz)"lʑ9̑#< * X v  ƀȀ HorizontalUplinkHorizontalDownlinkTransponderVerticalDownlinkVerticalUplinkBeamˑ̑#> "24t~111.73014.030A%9̑͑#"J$*.2(4t~t~14.04311.7432B / ȂΑ#> "24t~311.79114.091A%͑Yϑ#"J$*.2(4t~t~14.10411.8044B / AΑ'#> "24t~Yϑ'Q511.85214.152A%Yϑ#"J$*.2(4t~t~14.16511.8656B / A'#> "24t~711.91314.213A%#"J$*.2(4t~t~14.22611.9268B / AG#> "24t~911.97414.274A  #@$,046t~14.28711.98710B G#@ $46t~1112.03514.335A #@$,046t~14.34812.04812B S#@ $46t~1312.09614.396A #@$,046t~14.40912.10914B S#@ $46t~1512.15714.457A #@$,046t~14.47012.17016B$c #H (<>t~1711.4886713.77700L$* #H (<>t~1911.5496713.83800L$c #H (<>t~2111.6106713.89900L$* #H (<>t~2311.6703413.95867LR. $ \Transponder 23 only has 51.3 MHz bandwidth1 ; 1 ; X" 6 S_E"Nahuel 1A's Large beam: J 1 #  HNahuel 1BF 5 :$xV"  Nahuel 1B1 O'  GeneralYG#^$") DesignationVOA#R*Launch date1998?h!fG#^B"N ,Country of originArgentinao"M#jD"H̀‰MissionTelecommunications]f>@A#R8>@ ,Geostationary orbit76Ws&@M#jL" &9+SLaunch vehicleLong March 3C ?Q>@AA#R Launch site^:@`A$ tCould be sold to GE Americom and be launched by Ariane8AA' "(OTechnical data8`AA' " Specificationsb!A2BA#RB&Prime contractorAerospatiale[ABA#R4PlatformSpacebus 2000[2BBA#R4"Mass at launch1820 kgSB;CA#R$ Mass in orbitL BCA#RLengthK ;CCA#RWidthL CDA#RHeightSCqDA#R$ StabilizationN DDA#RDC powerUqDEA#R($Design lifetime&D:E# 1 EkE'  Ku-bandY:EEA#R0(Main transponders18YkEFA#R0,Backup transpondersK EhFA#RPowerUFFA#R(Bandwidth54 MHzq0hF.GA#R`CoverageArgentina and neighboring countriesTFGA#R&EIRP max50 dBWR.GGA#R"Polarization/ GH$ 3 beams1G4H1W4HHHT+HH) "VȠ$To view this page you need to register&4HH# > HH1#j&H:IJProgram: NATONH:I8 @.{.G" Program: NatoXHI) " North Atlantic Treaty OrganizationMilitary communications satellites for the NATO<:II' *O External resourcesIJ6 :http://www.nc3a.nato.int/csdiv/satcom/index.htmhttp://www.fafb.af.mil/nato/http://www.fas.org/spp/military/program/com/nato_3.htm1IJ1JKaJKd uga }b }CdCdCdCdCdCdProgram: NatoNato 1Nato 2Nato 3ANato 3BNato 3CNato 3DNato 4ANato 4B1JK1UKLM=KL# 4Nato 3's specificationsg&KLA#RL,Downlink frequecies7.2 to 7.5 GHz\LLA#R6$Design lifetime7 years$LM" 1L4M14M=MqM# 4Nato 4's specificationsp/4MMA#R^&Prime contractorBritsh Aerospace (now MMS)QqM2NA#R PlatformECS[MNA#R4"Mass at launch1430 kgY2NNA#R0 Mass in orbit770 kgXN>OA#R.Payload mass215 kgQNOA#R Length2.2 mQ>OOA#R Height2.3 mZOFA#R2OFMSolar array16 m spanYOA#R0 Stabilization3 axisYFA#R0DC powerEOL: 1200 W\TA#R6$Design lifetime7 years^4* $hBased on the design of the Skynet 4 satellites1Tげ1Uげ&JE"(# DNato 4's UHF-band (250-315 MHz)XげA#R.0(Main transponders2Y(قA#R00,Backup transpondersV/A#R*0Power25 W (TWTA)UقA#R(0Bandwidth25 KHzT/؃A#R&0CoverageEuropeN &A#R0EIRP max$؃J" 1&{1U{,5J# $Nato 4's X-bandX{A#R.0(Main transponders3YaA#R00,Backup transpondersVA#R*0Power40 W (TWTA)]aA#R80Bandwidth60 and 135 MHzThA#R&0CoverageglobalN A#R0EIRP maxRhA#R"0Polarization$," 7c1%c#Nato 1G,8 @ {.G" Nato 11 cۇ'  Generalg BG#^@") Designation04353 / 70021A\ۇA#R6Launch date20 Mar 1970kB M#j<"N ,ķ+‰Country of originNATOy,M#jX"H̀‰MissionMilitary: telecommunicationsY ۉA#R0,Geostationary orbitr%MM#jJ" &p㉂Launch vehicleThor Delta #77&ۉs# 5M'  End of lifeWsA#R,"Out of serviceyes$#" 7Z1%%Z"Nato 2G#8 @ {.G" Nato 21 Zҋ'  Generalg 9G#^@") Designation04902 / 71009A[ҋA#R4Launch date3 Feb 1971k9M#j<"N ,ķ+‰Country of originNATOy,xM#jX"H̀‰MissionMilitary: telecommunicationsb!ڍA#RB,Geostationary orbitsee belowr%xLM#jJ" &p㉂Launch vehicleThor Delta #82&ڍr# 5L'  End of lifeWrA#R,"Out of serviceyes$"" 8Z1%%ZÒNato 3AH"8 @"{.G" Nato 3A1 Zӏ'  Generalg FG#^@"ӏF") Designation08808 / 76035A\ӏA#R6Launch date22 Apr 1976kF M#j<"N ,ķ+‰Country of originNATOy,M#jX"H̀‰MissionMilitary: telecommunications] A#R8,Geostationary orbit18Ws&V’M#jL" &p㉂Launch vehicleThor Delta #122Z’A#R2"Mass at launch376 kg&V’’# 5’ Ò'  End of lifeW’bÒA#R,"Out of serviceyes& ÒÒ# 8bÒÒ' "(Technical data<ÒÒ) "&>1Specifications8Ò4Ē1{%S%4Ē|ĒȒNato 3BHÒ|Ē8 @"{.G" Nato 3B1 4ĒĒ'  Generalg |ĒŒG#^@") Designation09785 / 77005A\ĒpŒA#R6Launch date28 Jan 1977kŒŒM#j<"N ,ķ+‰Country of originNATOy,pŒTƒM#jX"H̀‰MissionMilitary: telecommunicationsYŒƒA#R0,Geostationary orbits&Tƒ ǒM#jL" &p㉂Launch vehicleThor Delta #128ZƒzǒA#R2"Mass at launch680 kg& ǒǒ# 5zǒǒ'  End of lifeWǒ,ȒA#R,"Out of serviceyes&ǒRȒ# 8,ȒȒ' "(Technical data<RȒȒ) "&>1Specifications8ȒȒ1!%%ȒFɒ6͒Nato 3CHȒFɒ8 @"{.G" Nato 3C1 Ȓwɒ'  Generalg FɒɒG#^@") Designation11115 / 78106A\wɒ:ʒA#R6Launch date19 Nov 1978kɒʒM#j<"N ,ķ+‰Country of originNATOy,:ʒ˒M#jX"H̀‰MissionMilitary: telecommunicationsYʒw˒A#R0,Geostationary orbits&˒˒M#jL" &p㉂Launch vehicleThor Delta #146&w˒̒# 5˒E̒'  End of lifeW̒̒A#R,"Out of serviceyes&E̒̒# 8̒̒' "(Technical data<̒6͒) "&>1Specifications8̒n͒1{ S%&n͒͒Nato 3DH6͒͒8 @"{.G" Nato 3D1 n͒͒'  Generalg ͒NΒG#^@") Designation15391 / 84115A\͒ΒA#R6Launch date14 Nov 1984kNΒϒM#j<"N ,ķ+‰Country of originNATOy,ΒϒM#jX"H̀‰MissionMilitary: telecommunicationsb!ϒ A#RB,Geostationary orbitsee belowϒ 6͒s&ϒM#jL" &p㉂Launch vehicleThor Delta #177& # : - */ۀ Locationim#:   " BeginEndPositionj#.$(*L: 14 Nov 1984'i{j#N,.Feb 1995Mar 199721W, inclined!j#BApr 199718.5W, inclined&{,# 8d' "(OTechnical data8,' " Specificationsd#dA#RF&Prime contractorFord AerospaceN NA#RPlatformTA#R&"Mass at launch[NA#R4 Mass in orbit385 kg ?p/mA#R^Dimension2.13 m (diameter) x 2.74 m (high)QA#R Solar arraySmA#R$ StabilizationSdA#R$DC power500 WUA#R($Design lifetimeV2d$ dDownlinks in UHF- (250-315 MHz), C- and X-band8G1%&G Nato 4AH8 @"{.G" Nato 4A1 G'  Generalg 'G#^@") Designation21047 / 91001A[A#R4Launch date8 Jan 1991k'M#j<"N ,ķ+‰Country of originNATOy,f M#jX"H̀‰MissionMilitary: telecommunicationso( G#^P"/ۀ0Geostationary orbit18W, inclinedp#f E M#jF" &p㉂Launch vehicleDelta 2 #202& k # 8E ' "(Technical datazAk  9 Be_f◞UȉSpecificationsUHF-bandX-bandAlso downlinks in C-band8 U 1&U cANato 4BH 8 @"{.G" Nato 4B9U # ,Also called USA 0981  '  Generalg n G#^@") Designation22921 / 93076A[ A#R4Launch date8 Dec 1993kn 4 M#j<"N ,ķ+‰Country of originNATOy, M#jX"H̀‰MissionMilitary: telecommunicationsb!4 A#RB,Geostationary orbitsee belowp# M#jF" &p㉂Launch vehicleDelta 2 #224&# : - */ۀ Locationim#:   " BeginEndPosition! @j#B"68L: 8 Dec 1993Jan 19985Ei @ i@j#*Mar 199820W& @@# 8@@' "(Technical datazA@cA9 Be_f◞UȉSpecificationsUHF-bandX-bandAlso downlinks in C-band: @A1h4$&AAINetsat 28:cAA, (" Netsat 28AB$ !Netsat 28 is a Delaware LLC which plans to launch this Ka-band satellite for data communications (on-demand rates from 64 kbps to 1.544 Mbps)1 AB'  GeneralYBCG#^$") Designation`BuCA#R>Launch datebefore May 2002t'CCM#jN"N ,㹌לCountry of originUnited Stateso"uCXDM#jD"H̀‰MissionTelecommunications]CDA#R8,Geostationary orbit95W\XDEG#^*" &Launch vehicleYDjEG#^$Launch siteF"EE$ DWill provide onboard switching8jEE' "(OTechnical data1 EF'  Ka-bandYErFA#R0(Main transponders48YFFA#R0,Backup transpondersK rFGA#RPowerUFkGA#R(Bandwidth40 MHzN GGA#RCoverageN kGHA#REIRP maxRGYHA#R"PolarizationMHHB#TFrequenciesUplink: 28.35-28.6 and 29.25-30.0 GHzDownlink: 19.7-20.2 GHz&YHI# 1H?I1W?IIIT+II) "VȠ$To view this page you need to register&?II# < II1j&'I1JNilesat 101<I1J, ("" Nilesat 1011 IbJ'  Generalg 1JJG#^@") Designation25311 / 98024A\bJ%KA#R6Launch date28 Apr 1998lJKM#j>"N ,p$ Country of originEgypto"%KLM#jD"H̀‰MissionTelecommunications\K\LA#R6,Geostationary orbit7Wo"LLM#jD" &g&\Launch vehicleAriane V108S,\LN' YOn the contract: 2 satellites (1 = ground spare) + 2 earth stations on the contract: total amount: $158 million for Matra Marconi Space. The second satellite could be modified and launched to cover more of the African continentTelesat Canada provided the consultancy to setup the whole system.<LZN' * External resourcesENN' <http://www.nilesat.com.eg/8ZNN' "(Technical dataANO) "0U EIRP coverage (dBW)8NPO' " Specificationsi(OOA#RP&Prime contractorMatra Marconi Space[PO A#R4PlatfO IormEurostar 2000[O{A#R4"Mass at launch1840 kgT πA#R&Dry mass795 kg`{/A#R>Dimension2.3 x 2.4 x 1.7 mWπA#R,Solar array21.5 mS/فA#R$ StabilizationT-A#R&DC power3020 W]فA#R8$Design lifetime12 years&-# 1 ႓'  Ku-bandY:A#R0(Main transponders12Z႓A#R2,Backup transponders6P:䃓A#RPower105 WU9A#R(Bandwidth33 MHzh'䃓A#RNCoverageMiddle East & North AfricaV9A#R*EIRP max50.3 dBWRIA#R"Polarizationj)A#RRFrequenciesdownlink: 11.7 - 12.5 GHzjEI% 2.3 m diameter onboard antennaPayload provided by Alcatel EspaceK$h' H Transponder frequency chart (GHz),a#X  > TransponderPolarizationFrequencyahVR#t2H11.765aR#t3V11.785aVR#t4H11.804ayR#t5V11.823aڈR#t6H11.842ay;R#t7V11.861aڈR#t8H11.881a;R#t9V11.900b_R#t  10H11.919bR#t  11V11.938b_#R#t  12H11.957bR#t  13V11.956b#狓R#t  14H11.996bIR#t  15V12.015b狓R#t  16H12.034bI R#t  17V12.053boR#t  18H12.072& # 1oƍ1W ƍ@T+) "VȠ$To view this page you need to register&ƍ@# 1q1!qN@6 <2W"Nilesat EIRP map1q1W"DjT+D) "VȠ$To view this page you need to register&j# @D1&)# _Program: NimbusPj 8 @2[6T" Program: Nimbus j& American experimental meteorology program operated by the NOAAThose satellites have given atmosphere temperature at different altitudes< ' *O External resourcese>_' |http://thunder.met.fsu.edu/explores/Guide/nimbusindex.html11$b“n_b“d ȀQ;CR;C KS;CT;CU;CV;CW;CProgram: NimbusNimbus 1Nimbus 2Nimbus 3ANimbus 3Nimbus 4Nimbus 5Nimbus 6Nimbus 79“1'%““O˓Nimbus 1Ib““8 @$[6T" Nimbus 11 “Ó'  Generalg “|ÓG#^@") Designation00872 / 64052A\ÓÓA#R6Launch date28 Aug 1964t'|ÓLēM#jN"N ,㹌לCountry of originUnited StateshÓēM#j6"H̀l/MissionMeteorology^LēœA#R:"Perigee/Apogee429/937 kmVēhœA#R*Inclination98.7TœœA#R&Period98.4 minp#hœ,ƓM#jF" &#*≂Launch vehicleThor Agena B[œƓA#R4Launch siteVandenbergZ,ƓƓA#R2"Mass at launch376 kgƓɓ) A circular orbit was intended but a partial failure of Agena (early shutdown) caused an elliptical orbit instead.The project objectives were to provide improved photographs of local cloud conditions by an automatic picture transmission (APT) system, and to evaluate an advanced vidicon camera system for daylight coverage and a high-resolution infrared radiometer system for night-time cloud cover observation.First high resolution photos (27000 photos taken) Five hurricanes and two typhoons were spotted in photographing 70 percent of the world each day. The APT system supplied daytime photos to more than 60 low-cost ground stations. Radiometer photos were remarkably clear and covered a 12,500 square mile area.5Ɠʓ'  End of life_ɓrʓA#R<"Out of service23 Sep 1964c"ʓʓA#RDCausesolar panel drive failedVrʓ+˓A#R*Decay16 May 1974$ʓO˓" 9+˓˓1M'(&˓˓Nimbus 2IO˓˓8 @$[6T" Nimbus 21 ˓̓'  Generalg ˓i̓G#^@") Designation02173 / 66040A\̓̓A#R6Launch date15 May 1966t'i̓9͓M#jN"N ,㹌לCountry of originUnited Statesh͓̓M#j6"H̀l/MissionMeteorology`9͓ΓA#R>"Perigee/Apogee1090/1174 kmW͓XΓA#R,Inclination100.6SΓΓA#R$Period108 minp#XΓϓM#jF" &#*≂Launch vehicleThor Agena B[ΓvϓA#R4Launch siteVandenbergc<ϓ' yThe project objectives were to provide global weather photography on a 24-hour basis for meteorolvϓO˓ogical research and operational use, and provide infrared data for study of earth's heat balance.Four sensor systems weighing a total of 142 pounds were carried. The advanced vidicon camera system (AVCS) included three 1-inch cameras with 800-line resolution designed to photograph a 800,000 square mile area. A high resolution infrared radiometer provided time and was expected to yield a variety of geophysical and atmospheric data including cloud height information.: vϓ1'('i:Nimbus 3AJi8 @&[6T" Nimbus 3A:# .Also called Nimbus B1 i'  General\0G#^*") Designationn/a\A#R6Launch date18 May 1968t'0M#jN"N ,㹌לCountry of originUnited StateshhM#j6"H̀l/MissionMeteorologyp#M#jF" &#*≂Launch vehicleThor Agena D[h3A#R4Launch siteVandenberg'- (ㅯ\&Two minutes after launch, a booster malfunction forced a command destruct. The booster and spacecraft fell into the Pacific Ocean between Vandenberg Air Force Base and San Miguel Island off the coast of California.The radioactive fuel for the two generators (plutonium 238) was contained in two high-strength alloy and graphite capsules, which had been designed and tested to withstand ocean impact and seawater corrosion in case of such an abort.53\'  End of life_'A#R<"Out of service18 May 1968[\A#R4CauseLauncher failure$:" 9s1 (((sBNimbus 3I:8 @$[6T" Nimbus 31 s'  Generalg T G#^@") Designation03890 / 69037A\ A#R6Launch date14 Apr 1969t'T $ M#jN"N ,㹌לCountry of originUnited Statesh M#j6"H̀l/MissionMeteorology`$ A#R>"Perigee/Apogee1069/1128 kmU A A#R(Inclination100U A#R(Period107.2 minp#A  M#jF" &#*≂Launch vehicleThor Agena D[ a A#R4Launch siteVandenberg J+ $} KNimbus 3 was a replacement for Nimbus 3A. Nimbus 3 was the first United States satellite to make night and day global measurements from space of temperatures of the atmosphere, both over extended periods and, for the first time, at varying levels vertically. While meteorological objectives were primary, this mission also gathered vital oceanographic data for scientific purposes other than solely for weather forecasting. Another mission objective was to provide data for the first experiment of the U.S.A. portion of the Global Atmospheric Research Program (GARP), which was an international program of formulating and coordinating research for achieving long-range global weather forecasting.8a ' "(OTechnical data8J' " SpecificationsV@A#R*&Prim@:e contractorN j@A#RPlatformT@@A#R&"Mass at launchYj@AA#R0 Mass in orbit635 kgY@pAA#R0Dimension3 x 3.35 mQAAA#R Solar arrayYpABA#R0 Stabilization3 axisN AhBA#RDC powerUBBA#R($Design lifetimeAhBB* $.ㅯ\&Has a SNAP engine9B7C1(0()7CCgKNimbus 4IBC8 @$[6T" Nimbus 41 7CC'  Generalg CDG#^@") Designation04362 / 70025A[CsDA#R4Launch date8 Apr 1970t'DDM#jN"N ,㹌לCountry of originUnited StateshsDOEM#j6"H̀l/MissionMeteorology`DEA#R>"Perigee/Apogee1085/1097 kmVOEFA#R*Inclination99.9UEZFA#R(Period107.1 minp#FFM#jF" &#*≂Launch vehicleThor Agena D[ZF%GA#R4Launch siteVandenberg`FG$ It made world-wide weather observations twice a day - once in daylight and once in darkness.8%GG' "(OTechnical data8GH' " SpecificationsVGoHA#R*&Prime contractorN HHA#RPlatformToHIA#R&"Mass at launchYHjIA#R0 Mass in orbit683 kgYIIA#R0Dimension3 x 3.35 mi(jI,JA#RPSolar arraytwo panels: 0.91 x 2.44mSIJA#R$ StabilizationS,JJA#R$DC power200 WUJ'KA#R($Design lifetime@JgK$ 8Transmits on 136.500 MHz9'KK1()*KKNimbus 5IgKK8 @$[6T" Nimbus 5:K#L# .Also called Nimbus E1 KTL'  Generalg #LLG#^@") Designation06305 / 72097A\TLMA#R6Launch date11 Dec 1972t'LMM#jN"N ,㹌לCountry of originUnited StateshMMM#j6"H̀l/MissionMeteorology`MSNA#R>"Perigee/Apogee1086/1098 kmVMNA#R*Inclination99.8USNNA#R(Period107.1 minr%NpOM#jJ" &p㉂Launch vehicleThor Delta #93`N $ It was also used for testing advanced systems collecting meteorological and geological data.pO gK8pOD' "(OTechnical data8 |' " SpecificationsVDҀA#R*&Prime contractorN | A#RPlatformTҀtA#R&"Mass at launchY ́A#R0 Mass in orbit790 kgYt&A#R0Dimension3 x 3.35 mi(́A#RPSolar arraytwo panels: 0.91 x 2.44mS&ₔA#R$ StabilizationS5A#R$DC power200 WUₔA#R($Design lifetime$5" 9烔1X0(A)+烔0WNimbus 6I08 @$[6T" Nimbus 6:烔j# .Also called Nimbus F1 0'  Generalg jG#^@") Designation07924 / 75052A\^A#R6Launch date12 Jun 1975t'҅M#jN"N ,㹌לCountry of originUnited Statesh^:M#j6"H̀l/MissionMeteorology`҅A#R>"Perigee/Apogee1098/1111 kmV:A#R*Inclination99.8UEA#R(Period107.4 mins&M#jL" &p㉂Launch vehicleThor Delta #111e$EA#RH"Mass at launch829 kg or 911 kg?:W$ ,Measures sea color91V ),وĔNimbus 7IWو8 @$[6T" Nimbus 7:# .Also called Nimbus G1 وD'  Generalg G#^@") Designation11080 / 78098A\DA#R6Launch date24 Oct 1978t'{M#jN"N ,㹌לCountry of originUnited Statesh㊔M#j6"H̀l/MissionMeteorology^{AA#R:"Perigee/Apogee944/956 kmT㊔A#R&Inclination99SA苔A#R$Period104 minYAA#R0 Orbital cycle6 dayss&苔M#jL" &p㉂Launch vehicleThor Delta #145ZAA#R2"Mass at launch827 kg' Nimbus 7 was notable for providing the first daily mapping ozone concentration and the first global ocean color measurements. Data was for the first time used by ESASpacecraft and experiment data were transmitted to Earth stations immediately, or stored in an on-board high-speed tape recorder for subsequent playback when the satellite was in view of a ground acquisition station.<' *O External resourcesf' http://floeberg.colorado.edu:1733/docs/platform_documents/nimbus7_observatory_source_document.html8' "(OTechnical data8 ' " Specifications W^jA#R:&Prime contractorGE AstroY A#R0 Stabilization3 axisCjĔ ؀}                Equipped with numerous instruments: CZCS (Coastal Zone Color Scanner) out of service on 18 Dec 1986; ERBE (Earth Radiation Budget Experiment); LIMS (Limb IR Monitor of the Stratosphere) out of service mid 1989; SAM 2 (Stratospheric Aerosol Measurement 2) still working in 1992; SAMS (Stratospheric and Mesospheric Sounder) out of service in June 1983; SBUV/TOMS (Solar Backscatter Ultra-Violet/Total Ozone Mapping Spectrometer) SBUV out of service in February 1987, TOMS still working in 1992; SMMR (Scanning Multichannel Microwave Radiometer) out of service on 6 Jul 1988 and last but not least THIR (Temperature Humidity IR Radiometer) out of service in March 19856<Ĕ1: ')-<ĔrĔ{ϔNimiq6 ĔrĔ, (" Nimiq<Ĕ9Ŕ$ GNimiq is an Inuit word for any object or force that unites things or binds them together. The name Nimiq was selected through a national contest in April 1998. 1 rĔjŔ'  GeneralY9ŔŔG#^$") DesignationYjŔƔA#R0Launch dateDec 1998m ŔƔM#j@"N ,xW Country of originCanadao"ƔƔM#jD"H̀‰MissionTelecommunications]ƔUǔA#R8,Geostationary orbit91WjƔǔM#j:" &㉓gLaunch vehicleProtonYUǔȔG#^$Launch siteǔɔ3 4mIuGEO DBS satellite operated by Telesat Canada, the well known operator of Anik.The satellite should cost $240 million. ExpressVu Inc. will acquire 17 of the 32 transponders.8Ȕ9ɔ' "(OTechnical data8ɔqɔ' " Specificationsv59ɔɔA#Rj&Prime contractorLockheed Martin / Spar AerospaceSqɔ:ʔA#R$PlatformA2100TɔʔA#R&"Mass at launchS:ʔʔA#R$ Mass in orbitOʔ0˔A#RDimensionQʔ˔A#R Solar arrayS0˔˔A#R$ StabilizationN ˔"̔A#RDC powerU˔w̔A#R($Design lifetime&"̔̔# 1 w̔̔'  Ku-bandY̔'͔A#R0(Main transponders32Y͔̔A#R0,Backup transpondersK '͔͔A#RPowerO͔ΔA#RBandwidthN ͔hΔA#RCoverageN ΔΔA#REIRP maxM hΔϔA#RG/T maxRΔUϔA#R"Polarization&ϔ{ϔ# > Uϔϔ1)^-.ϔProgram: NOAAN{ϔ8 @.ZG" Program:ϔ{ϔ NOAAϔ5 8 :ܗ+l^gNational Oceanic and Atmospheric AdministrationSeries of American weather satellites which evolved from a long line of experimental and operational satellites beginning with Tiros 1. Operated by NOAA<U' *O External resourcesK= Hshttp://ns.noaa.gov/NESDIS/NESDIS_Home.htmlhttp://140.90.207.25:8080/EBB/ml/nic00.htmlhttp://www.ccrs.nrcan.gc.ca/ccrs/satsens/satellit/noaae.htmlhttp://poes2.gsfc.nasa.gov/5U'  Instruments]Kc ⑺    q wڜ Instruments on all satellitesOther instruments are used occasionnaly:SBUV (Solar Backscatter UV radiometer) [on NOAA 11 onwards]: ozone distributionERBE (Earth Radiation Budget Experiment) [on NOAA 09 & 10]: radiation gains and losses (scanning instruments and non-scanner)SARSAT [on NOAA 08 onwards]Argos for data collection on NOAA second generation: 06 onwardsThe primary command and data acquisition (CDA) stations are located in Fairbanks, Alaska, and Wallops Island, Va.11/]O] eTɑ܁ {݁ {ށ {߁ { { { { { {b {Y {Z {[ {\ {] {Program: NOAANOAA 01NOAA 02NOAA 03NOAA 04NOAA 05NOAA 06NOAA BNOAA 07NOAA 08NOAA 09NOAA 10NOAA 11NOAA 12NOAA 13NOAA 14NOAA 1511U08 \ ]4]) "h?NOAA's specifications (2nd generation: Tiros N)^IA#R:&Prime contractorGE Astron'G#^N?Platformbased on the Tiros N bus[IA#R4"Mass at launch1418 kgYkA#R0 Mass in orbit735 kgl+A#RVDimension3.71 m long x 1.88 m diameter^k5 A#R:Solar array2.37 x 4.91 mY A#R0 Stabilization3 axisN 5 A#RDC power\ 8 A#R6$Design lifetime3 years$ \ " 18 11 L)\ # RNOAA's specifications (3rd generation)^ 7 A#R:0&Prime contractorGE Astrov/ G#^^0n~Platformevolved from NOAA 2nd generation[7  A#R40"Mass at launch1420 kg[ c A#R40 Mass in orbit~1050 kgl+ A#RVDimension4.18 m long x 1.88 m diameterYc ( A#R00 Stabilization3 axis\ A#R60$Design lifetime3 years]( & Telemetry: 2247.5 MHz (8.32 or 16.64 kbps)Command: 2026.0 MHz (2 kbps)Data: (2.66 Mbps)1 81^28=CE"}# DNOAA's payload (NOAA 9 onwards)b58- *j  AVHRR (Advanced Very High Resolution Radiometer)Z}@F#Z0Wavebands0.58-0.68 m (visible): cloud, snow and ice monitoring0.725-1.10 m (near IR): water, vegetation and agriculture surveys3.55-3.93 m (near IR): sea surface temperature, volcano, forest fire activity10.3-1@1.3 m (thermal IR): sea surface temperature, soil moisture11.3-12.5 m (thermal IR): sea surface temperature, soil moistureV@A#R*0Resolution1.1 kmX@9AA#R.0Swath width3000 km[.@A- *\O  TOVS (Tiros Operational Vertical Sounder)b9A=CG \      HIRS/2 (High Resolution IR Sounder): 20 channels in the 0.69 - 14 - 95 m band; 17.4 km resolutionSSU (Stratospheric Sounding Unit): step-scanned far IR spectrometer with 3 channels in the CO absorption band (15 m);147.3km resolutionMSU (Microwave Sounding Unit): passive 4-channel radiometer operating around 55 GHz; 109 km resolution8AuC1P *3uCCGNOAA 01H=CC8 @"ZG" NOAA 018uCC# *Also called Itos B1 C&D'  Generalg CDG#^@") Designation04793 / 70106A\&DDA#R6Launch date11 Dec 1970t'D]EM#jN"N ,㹌לCountry of originUnited StateshDEM#j6"H̀l/MissionMeteorology`]E%FA#R>"Perigee/Apogee1421/1471 kmWE|FA#R,Inclination101.3U%FFA#R(Period114.8 minr%|FCGM#jJ" &p㉂Launch vehicleThor Delta #81\FGA#R6"Mass at launch306.8 kg=CGG$ 2Images 24 hours a day8GH13*?*4H\H^LNOAA 02HG\H8 @"ZG" NOAA 028HH# *Also called Itos D1 \HH'  Generalg H,IG#^@") Designation06235 / 72082A\HIA#R6Launch date15 Oct 1972t',IIM#jN"N ,㹌לCountry of originUnited StateshIdJM#j6"H̀l/MissionMeteorology`IJA#R>"Perigee/Apogee1446/1453 kmUdJKA#R(Inclination102UJnKA#R(Period114.9 minr%KKM#jJ" &p㉂Launch vehicleThor Delta #91ZnK:LA#R2"Mass at launch340 kg$K^L" 8:LL1X *@+5LLNOAA 03H^LL8 @"ZG" NOAA 038LM# *Also called Itos F1 LGM'  Generalg MMG#^@") Designation06920 / 73086A[GM NA#R4Launch date6 Nov 1973t'M}NM#jN"N ,㹌לCountry of originUnited Statesh NNM#j6"H̀l/MissionMeteorology`}NEOA#R>"Perigee/Apogee1499/1508 kmWNOA#R,Inclination102.2UEO A#R(Period116.1 minO ^Lr%O~M#jJ" &p㉂Launch vehicleThor Delta #98Z ؀A#R2"Mass at launch340 kg$~" 8؀414?*u+64|NOAA 04H|8 @"ZG" NOAA 0484# *Also called Itos G1 |偕'  Generalg LG#^@") Designation07529 / 74089A\偕A#R6Launch date15 Nov 1974t'LM#jN"N ,㹌לCountry of originUnited StateshM#j6"H̀l/MissionMeteorology`䃕A#R>"Perigee/Apogee1442/1457 kmU9A#R(Inclination102U䃕A#R(Period114.9 mins&9M#jL" &p㉂Launch vehicleThor Delta #104Z[A#R2"Mass at launch340 kg$" 8[1@++7NOAA 05H8 @"ZG" NOAA 0587# *Also called Itos H1 h'  Generalg 7φG#^@") Designation09057 / 76077A\h+A#R6Launch date29 Jul 1976t'φM#jN"N ,㹌לCountry of originUnited Statesh+M#j6"H̀l/MissionMeteorology`gA#R>"Perigee/Apogee1504/1520 kmWA#R,Inclination102.2UgA#R(Period116.3 mins&M#jL" &p㉂Launch vehicleThor Delta #126$" 8≕1u++8≕*NOAA 06H*8 @"ZG" NOAA 068≕b# *Also called NOAA A1 *'  Generalg bG#^@") Designation11416 / 79057A\VA#R6Launch date27 Jun 1979t'ʋM#jN"N ,㹌לCountry of originUnited StateshV2M#j6"H̀l/MissionMeteorology^ʋA#R:"Perigee/Apogee785/800 kmV2挕A#R*Inclination98.7U;A#R(Period100.7 mink挕M#j<" &26Launch vehicleAtlas F[;A#R4Launch siteVandenberg@A* $,?Based on Tiros N5v'  End of life_AՎA#R<"Out of service31 Mar 1987$v" 7Վ01+n+90w5ŕNOAA BGw8 @ ZG" NOAA B1 0'  Generalg wG#^@") Designation11819 / 80043A\wA#R6Launch date29 May 1980t'M#jN"N ,㹌לCountry of originUnited StateshwSM#j6"H̀l/MissionMeteorology_A#R<"Perigee/Apogee264/1445 kmVS•A#R*Inclination92.2U]•A#R(Period102.1 mink••M#j<" &26Launch vehicleAtlas F[]•#ÕA#R4Launch siteVandenberg&•IÕ# 5#Õ~Õ'  End of life_IÕÕA#R<"Out of service29 May 1980i(~ÕFĕA#RPCausefailed to reach a usable orbitUÕĕA#R(Decay3 May 1981&Fĕĕ# 8ĕĕ' "(Technical data<ĕ5ŕ) "&n~Specifications8ĕmŕ1+$+:mŕŕ˕NOAA 07H5ŕŕ8 @"ZG" NOAA 078mŕŕ# *Also called NOAA C1 ŕƕ'  Generalg ŕƕG#^@") Designation12553 / 81059A\ƕƕA#R6Launch date23 Jun 1981t'ƕUǕM#jN"N ,㹌לCountry of originUnited StateshƕǕM#j6"H̀l/MissionMeteorology^UǕȕA#R:"Perigee/Apogee828/847 kmVǕqȕA#R*Inclination98.9UȕȕA#R(Period101.7 minkqȕ1ɕM#j<" &26Launch vehicleAtlas F[ȕɕA#R4Launch siteVandenberg[1ɕɕA#R4"Mass at launch1405 kg&ɕ ʕ# 5ɕBʕ'  End of life\ ʕʕA#R6"Out of serviceJun 1986_BʕʕA#R<Causepower system failure&ʕ#˕# 8ʕ[˕' "(Technical data<#˕˕) "&n~Specifications8[˕˕1 n+,;˕̕NOAA 08H˕̕8 @"ZG" NOAA 088˕O̕# *Also called NOAA E1 ̕̕'  Generalg O̕̕G#^@") Designation13923 / 83022A\̕C͕A#R6Launch date28 Mar 1983t'͕̕M#jN"N ,㹌לCountry of originUnited StateshC͕ΕM#j6"H̀l/MissionMeteorology^͕}ΕA#R:"Perigee/Apogee792/817 kmVΕΕA#R*Inclination98.6S}Ε&ϕA#R$Period101 minkΕϕM#j<" &26Launch vehicleAtlas F[&ϕ A#R4Launch siteVandenbergϕ ˕dϕ0 0Z {qWas a longer spacecraft than NOAA D (12) and was used to carry an additional Sarsat payload.5 '  End of life_4A#R<"Out of service29 Dec 1985j)A#RRCauseclock and power system failures&4# 8' "(OTechnical data84' " Specifications^A#R:&Prime contractorGE Astrox14 G#^b?Platformbased on the Tiros N bus, extended\fA#R6"Mass at launch1418 kg?Z A#R2 Mass in orbit735 kg?k*f+A#RTDimension6.8 m long x 1.88 m diameter_A#R<Solar array2.37 x 4.91 m?Y+A#R0 Stabilization3 axisN 1A#RDC power\A#R6$Design lifetime3 years&1# 81$+,<3 NOAA 09H38 @"ZG" NOAA 098k# *Also called NOAA F1 3'  Generalg kG#^@") Designation15427 / 84123A\_A#R6Launch date12 Dec 1984t'M#jN"N ,㹌לCountry of originUnited Statesh_;M#j6"H̀l/MissionMeteorology^A#R:"Perigee/Apogee835/858 kmX;A#R.Inclination99.158UF A#R(Period101.8 mink M#j<" &26Launch vehicleAtlas E[F A#R4Launch siteVandenberg& 2 # 8 j ' "(Technical dataO2 1 2<n~⑺SpecificationsPayloadq0j * A#R`0*APT downlink freq.137.620 MHz (inoperative)c" A#RD0,HRPT downlink freq.1707.0 MHzW* A#R,0Beacon137.770 MHz$  " 8 @ 1,,=@ CCNOAA 10H 8 @"ZG" NOAA 108@ # *Also called NOAA G1 '  Generalg X G#^@") Designation16969 / 86073A\ A#R6Launch date17 Sep 1986t'X (M#jN"N ,㹌לCountry of originUnited Statesh M#j6"H̀l/MissionMeteorology^(A#R:"Perigee/Apogee799/818 kmXFA#R.Inclination98.549SA#R$Period101 minkF@M#j<" &26Launch vehicleAtlas @ E[k@A#R4Launch siteVandenbergT0@@$ `The ERBE scanner had a scan sticking anomaly5k@@'  End of lifeW@KAA#R,"Out of serviceyes&@qA# 8KAA' "(Technical dataOqAA1 2<n~⑺SpecificationsPayloadm,AeBA#RX0*APT downlink freq.137.500 MHz (standby)c"ABA#RD0,HRPT downlink freq.1698.0 MHzWeBCA#R,0Beacon136.770 MHz$BCC" 8C{C1,,>{CCJKNOAA 11HCCC8 @"ZG" NOAA 118{CC# *Also called NOAA H1 C,D'  Generalg CDG#^@") Designation19531 / 88089A\,DDA#R6Launch date24 Sep 1988t'DcEM#jN"N ,㹌לCountry of originUnited StateshDEM#j6"H̀l/MissionMeteorology^cE)FA#R:"Perigee/Apogee814/856 kmXEFA#R.Inclination99.059U)FFA#R(Period101.9 minkFAGM#j<" &26Launch vehicleAtlas E[FGA#R4Launch siteVandenbergAGPH' Studies ozoneThe attitude control subsystem lost two of its four gyros and was operated successfully with specialized onboard software.5GH'  End of life\PHHA#R6"Out of serviceearly 95^H?IA#R:Causereplaced by NOAA 14&HeI# 8?II' "(Technical dataOeII1 2<n~⑺SpecificationsPayloadq0I]JA#R`0*APT downlink freq.137.620 MHz (inoperative)c"IJA#RD0,HRPT downlink freq.1707.0 MHzf%]J&KA#RJ0Beacon137.770 MHz (inoperative?)$JJK" 8&KK1r,-?KKNOAA 12HJKK8 @"ZG" NOAA 128KL# *Also called NOAA D1 K3L'  Generalg LLG#^@") Designation21263 / 91032A\3LLA#R6Launch date14 May 1991t'LjMM#jN"N ,㹌לCountry of originUnited StateshLMM#j6"H̀l/MissionMeteorology^jM0NA#R:"Perigee/Apogee804/824 kmVMNA#R*Inclination98.6U0NNA#R(Period101.2 minr(NMOJ#dP(Equator crossing19:30 northboundkNOM#j<" &26Launch vehicleAtlas E[MOA#R4LaunchOJK siteVandenberg&OE# 8}' "(Technical dataOÈ1 2<n~⑺SpecificationsPayloadm,}9A#RX0*APT downlink freq.137.500 MHz (standby)c"̀A#RD0,HRPT downlink freq.1698.0 MHzW9A#R,0Beacon136.770 MHz$" 8O1,J-@ONOAA 13H8 @"ZG" NOAA 138Oς# *Also called NOAA I1 '  Generalg ςgG#^@") Designation22739 / 93050A[ƒA#R4Launch date9 Aug 1993t'g6M#jN"N ,㹌לCountry of originUnited StateshƒM#j6"H̀l/MissionMeteorology^6A#R:"Perigee/Apogee846/860 kmVRA#R*Inclination98.9SA#R$Period102 minkRM#j<" &26Launch vehicleAtlas E:J$ ,Cost: $100 million5'  End of life\JۆA#R6"Out of serviceAug 1993u4PA#RhCauseFailure (a screw damaged the power supply)&ۆv# 8P' "(Technical dataMv0 0:n~⑺SpecificationsPayload831i --A3{NOAA 14H{8 @"ZG" NOAA 1483# *Also called NOAA J1 {䈖'  Generalg KG#^@") Designation23455 / 94089Ah'䈖A#RNLaunch date30 Dec 1994 at 10:02 UTt'K'M#jN"N ,㹌לCountry of originUnited StateshM#j6"H̀l/MissionMeteorology^'튖A#R:"Perigee/Apogee847/861 kmVCA#R*Inclination98.9S튖A#R$Period102 minkCM#j<" &26Launch vehicleAtlas E`aA#R>Launch siteVandenberg SLC3_' 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. The motor for the Microwave Sounding Unit on the NOAA-14 spacecraft has stopped working. Records show the unit is from a delivery made to Martin Marietta dating back to 1984! The microwave sounder returned to normal operation in May 1995 after a software patch was installed to cope with any repeat failure. Its life expectancy remains uncertain.pFaϏ* $qNOAA 14 also has a power-supply problem in its Sarsat receiver. 8_' "(TechnicalϏ dataOϏb1 2<n~⑺SpecificationsPayloadm,A#RX0*APT downlink freq.137.620 MHz (standby)c"b2A#RD0,HRPT downlink freq.1698.0 MHzWA#R,0Beacon136.770 MHz$2" 81J-B-–ǖNOAA 15H-–8 @"ZG" NOAA 15@m–# :Previously known as NOAA K1 -––'  Generalg m–ÖG#^@") Designation25338 / 98030A\–aÖA#R6Launch date13 May 1998t'ÖÖM#jN"N ,㹌לCountry of originUnited StateshaÖ=ĖM#j6"H̀l/MissionMeteorologyk*ÖĖA#RT"Perigee/Apogee833 km (sunsynchronous)V=ĖĖA#R*Inclination98.7SĖQŖA#R$Period101 mino"ĖŖM#jD" &^]Launch vehicleTitan 2 #30[QŖƖA#R4Launch siteVandenbergŖƖ- (MZ {This is the first in a series of five satellites with improved imaging and sounding capabilities that will operate over the next 12 years.Will replace NOAA 12<Ɩ*ǖ' *O External resourcesM&Ɩwǖ' Lhttp://poes2.gsfc.nasa.gov/klm.htm&*ǖǖ# 1wǖǖ1CǖǖȖ*ǖǖ# NOAAǖȖ# NOAA L, M, N and N prime are still to come, built by Martin Marietta. N and N' will be launched after the end of the contury1ǖȖ1WDȖɖEɖT+Ȗɖ) "VȠ$To view this page you need to register&ȖEɖ# > ɖɖ1T)0Eɖɖ Program: NOSSJEɖɖ5 :,rG" Program: NOSSɖʖ& _Naval Ocean Surveillance System, also called ParcaeAmerican military ocean reconnaissance system. The first experimental satellite of this program could be 05678 / 71110AN'ɖʖ' N Whitecloud (1976-1987, 9 satellites)uʖ͖- ( The NOSS constellation consists of three orbital planes, each containing four satellites flying in formation; a main satellite and three sub-satellites. Some believe that the satellites periodically deploy solar sails to provide the propulsion required to maintain their precise formation flight.Another theory says the satellites would be connected by long (several km!) wires?Some of the NOSS launches carried a LIPS (Living Plume Shield) subsatellite. In those cases a jetisonable toroidal plume shield, which protected the satellite from the exhaust of the Star-37E motor, was fittet with some solar-cell experiments.ʖVΖ% ?The use of the Star-37E motor for the NOSS launches is somewhat conjectural, but is performance fits good with the published wights of the NOSS satellites.J#͖Ζ' FO Triplet (1990-..., 3 satellites)VΖPϖ% Satellites equipped with infrared sensors, built by Martin Marietta, 3600 kgThe cluster could be composed of only the 3 sub-satellites?<Ζϖ' *O External resourcesd=Pϖ ' zhttp://www.fas.org/spp/military/program/surveill/noss.htmϖ Eɖ1ϖ=1NF=Z Z ހ+l̑X~X~X~X~X~X~X~X~X~"W~#W~$W~%W~Program: NOSSNOSS 01NOSS 02NOSS 03NOSS 04NOSS 05NOSS 06NOSS 07NOSS 08NOSS 09NOSS 12NOSS 13NOSS 14NOSS 158=1<.GNOSS 01DZ5 : rG" NOSS 01:# .Also called OPS 64311 A'  Generalg G#^@") Designation08818 / 76038A\AA#R6Launch date30 Apr 1976t'xM#jN"N ,㹌לCountry of originUnited States9G#^r"H̀MissionMilitary: ocean reconnaissance (Whitecloud)`xXA#R>"Perigee/Apogee1128/1092 kmVA#R*Inclination63.5UXA#R(Period107.5 minknM#j<" &26Launch vehicleAtlas F[A#R4Launch siteVandenberg&n# 8'' "O Sub satelliteslG% SSU 1 (08835 / 76038C)SSU 2 (08836 / 76038D)SSU 3 (08884 / 76038J)8'1..H NOSS 02D5 : rG" NOSS 02:I# .Also called OPS 87811 z'  Generalg IG#^@") Designation10502 / 77112A[z<A#R4Launch date8 Dec 1977t'M#jN"N ,㹌לCountry of originUnited States9<0 G#^r"H̀MissionMilitary: ocean reconnaissance (Whitecloud)b! A#RB"Perigee/Apogee1054 / 1169 kmV0 A#R*Inclination63.4U = A#R(Period107.5 mink M#j<" &26Launch vehicleAtlas F[=  A#R4Launch siteVandenberg& ) # 8 a ' "O Sub satelliteslG) % SSU 4 (10529 / 77112D)SSU 5 (10544 / 77112E)SSU 6 (10594 / 77112F)8a  1<.X.I I ANOSS 03D I 5 : rG" NOSS 03: # .Also called OPS 72451 I '  Generalg  G#^@") Designation11720 / 80019A[ v A#R4Launch date3 Mar 1980t' M#jN"N ,㹌לCountry of originUnited States9v jG#^r"H̀MissionMilitary: ocean reconnaissance (Whitecloud)` A#R>"Perigee/Apogee1035/1150 kmVj A#R*Inclination63.0UuA#R(Period107.1 mink M#j<" &26Launch vehicleAtlas F[uG@A#R4G@ Launch siteVandenberg&m@# 8G@@' "O Sub satellitesiDm@A% EP 1 (11731 / 80019C)EP 2 (11732 / 80019D)EP 3 (11745 / 80019G)8@FA1.l.JFAAENOSS 04DAA5 : rG" NOSS 041 FAA'  General[ABA#R4Launch date9 Dec 1980t'ABM#jN"N ,㹌לCountry of originUnited States9B CG#^r"H̀MissionMilitary: ocean reconnaissance (Whitecloud)kBuCM#j<" &26Launch vehicleAtlas F[ CCA#R4Launch siteVandenberg&uCC# 5C+D'  End of life^CDA#R:"Out of service9 Dec 1980Y+DDA#R0CauseLaunch failure$DE" 8D>E1X. .K>EE8JNOSS 05DEE5 : rG" NOSS 05:>EE# .Also called OPS 02521 EE'  Generalg ETFG#^@") Designation13791 / 83008A[EFA#R4Launch date9 Feb 1983t'TF#GM#jN"N ,㹌לCountry of originUnited States9FGG#^r"H̀MissionMilitary: ocean reconnaissance (Whitecloud)`#GHA#R>"Perigee/Apogee1063/1186 kmVGYHA#R*Inclination63.4UHHA#R(Period107.8 minkYHIM#j<" &26Launch vehicleAtlas F[HtIA#R4Launch siteVandenberg&II# 8tII' "O Sub satellitesfAI8J% SSA (13844 / 83008E)SSB (13845 / 83008F)SSC (13874 / 83008H)8IpJ1l..LpJJdONOSS 06D8JJ5 : rG" NOSS 06:pJJ# .Also called OPS 64321 JK'  Generalg JKG#^@") Designation14112 / 83056A[KKA#R4Launch date9 Jun 1983t'KULM#jN"N ,㹌לCountry of originUnited States9KLG#^r"H̀MissionMilitary: ocean reconnaissance (Whitecloud)b!UL7MA#RB"Perigee/Apogee1051 / 1170 kmTLMA#R&Inclination63L 7MMA#RPeriodkMBNM#j<" &26Launch vehicleAtlas F[MNA#R4Launch siteVandenberg&BNN# 8NN' "O Sub satellitesiDNdO% GB 1 (14143 / 83056C)GB 2 (14144 / 83056D)GB 3 (14180 / 83056G)8NO1 .u/MOONOSS 07DdOO5 : rG" NOSS 07:O&# .O&dOAlso called OPS 87371 OW'  Generalg &G#^@") Designation14690 / 84012A[WA#R4Launch date5 Feb 1984t'M#jN"N ,㹌לCountry of originUnited States9 G#^r"H̀MissionMilitary: ocean reconnaissance (Whitecloud)b!oA#RB"Perigee/Apogee1052 / 1168 kmV łA#R*Inclination63.4L oA#RPeriodkł|M#j<" &26Launch vehicleAtlas F[׃A#R4Launch siteVandenberg&|# 8׃5' "O Sub satellitesiD% JD 1 (14728 / 84012C)JD 2 (14729 / 84012D)JD 3 (14795 / 84012F)85ք1./NքЉNOSS 08D5 : rG" NOSS 089քS# ,Also called USA 0151 '  Generalg S녗G#^@") Designation16591 / 86014A[FA#R4Launch date9 Feb 1986t'녗M#jN"N ,㹌לCountry of originUnited States9F:G#^r"H̀MissionMilitary: ocean reconnaissance (Whitecloud)`A#R>"Perigee/Apogee1049/1166 kmT:A#R&Inclination63L :A#RPeriodkM#j<" &26Launch vehicleAtlas F[:A#R4Launch siteVandenberg&&# 8^' "O Sub satellitesrM&Љ% USA 016 (16624 / 86014E)USA 017 (16625 / 86014F)USA 018 (16631 / 86014H)8^1u//OLNOSS 09DЉL5 : rG" NOSS 099# ,Also called USA 0221 L'  Generalg G#^@") Designation17997 / 87043A\yA#R6Launch date15 May 1987t'틗M#jN"N ,㹌לCountry of originUnited States9ymG#^r"H̀MissionMilitary: ocean reconnaissance (Whitecloud)`틗͌A#R>"Perigee/Apogee1045/1179 kmTm!A#R&Inclination63L ͌mA#RPeriodm !ڍM#j@" &26Launch vehicleAtlas E/F[m5A#R4Launch siteVandenberg&ڍ[# 85' "O Sub satellitesrM[% USA 023 (18009 / 87043E)USA 024 (18010 / 87043F)USA 025 (18025 / 87043H)8=1/v/P=$ėNOSS 12D5 : rG" NOSS 129=# ,Also called USA 0591 '  General g sG#^@") Designation20641 / 90050A[ A#R4Launch date8 Jun 1990t'sBM#jN"N ,㹌לCountry of originUnited States}6G#^l"H̀MissionMilitary: ocean reconnaissance (Triplet)[B—A#R4"Perigee/Apogee1200 kmTn—A#R&Inclination63L ——A#RPeriodkn—%×M#j<" &^]Launch vehicleTitan 4U+—z×* $VX~Could be in the same orbit as NOSS 098%××' "O Sub satellitesrMz×$ė% USA 060 (20682 / 90050B)USA 061 (20691 / 90050C)USA 062 (20692 / 90050D)8×\ė1//Q\ėėȗNOSS 13D$ėė5 : rG" NOSS 139\ėė# ,Also called USA 0721 ė ŗ'  Generalg ėqŗG#^@") Designation21775 / 91076A[ ŗŗA#R4Launch date8 Nov 1991t'qŗ@ƗM#jN"N ,㹌לCountry of originUnited States}6ŗƗG#^l"H̀MissionMilitary: ocean reconnaissance (Triplet)[@ƗǗA#R4"Perigee/Apogee1200 kmTƗlǗA#R&Inclination63L ǗǗA#RPeriodklǗ#ȗM#j<" &^]Launch vehicleTitan 4&ǗIȗ# 8#ȗȗ' "O Sub satellitesrMIȗȗ% USA 074 (21799 / 91076C)USA 076 (21808 / 91076D)USA 077 (21809 / 91076E)8ȗ+ɗ1Sv//R+ɗoɗ̗NOSS 14Dȗoɗ5 : rG" NOSS 141 +ɗɗ'  General[oɗɗA#R4Launch date2 Aug 1993t'ɗoʗM#jN"N ,㹌לCountry of originUnited States}6ɗʗG#^l"H̀MissionMilitary: ocean reconnaissance (Triplet)koʗW˗M#j<" &^]Launch vehicleTitan 4&ʗ}˗# 5W˗˗'  End of life^}˗̗A#R:"Out of service2 Aug 1993]˗m̗A#R8Causelauncher explosion$̗̗" 8m̗̗1/S̗ ͗NOSS 15D̗ ͗5 : rG" NOSS 15E"̗R͗# DAlso called NOSS 2-3 or USA 1191 ͗͗'  Generalg R͗͗G#^@") Designation23893 / 96029A\͗FΗA#R6Launch date12 May 1996t'͗ΗM#jN"N ,㹌לCountry of originUnited States}6FΗ7ϗG#^l"H̀MissionMilitary: ocean reconnaissance (Triplet)_ΗϗJ#d*Orbit1022 km?c7ϗ J#d2Inclination63.4?ϗ ̗o"ϗ{M#jD" &^]Launch vehicleTitan 4 #17& # 8{' "O Sub satellitestNM& USA 120 (23907 / 96029B)USA 121 (23908 / 96029C)USA 122 (23862 / 96029D).{'  TiPSM$ A tether satellite was carried with this launch called: Tether Physics and Survivability (TiPS) This experiment consists of 2 small end-masses connected by a 4 km nonconductuve braided tether (total mass: 53 kg). TiPS was jettisoned from its "host vehicle" on 20 June. It is aimed to test the survivability of the tether. The tether is predicted to have a mean life of 5 years before it is cut by orbital debris. The observed life of TiPS will help understand and validate these theoretical predictions.pL{ $ The two objects could be USA 123 (23936 / 96029E) & 124 (23937 / 96029F)<F' *O External resourcesO( ' Phttp://hyperspace.nrl.navy.mil/TiPS/> F1q^-0T!aProgram: NovaN!8 @.G" Program: Nova@a, &)|ۉAmerican navigation program linked to TransitEvolution 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.1!1Uo.aA R\̑wwwProgram: NovaNova 1Nova 2Nova 3781k0V8 Nova 1G8 @ G" Nova 1=8# 4Also called NNSS 30 4801 '  Generalg TG#^@") Designation12458 / 81044A\A#R6Launch date15 May 1981t'T$ M#jN"N ,㹌לCountry of originUnited Statesg M#j4"H̀シMissionNavigation`$ A#R>"Perigee/Apogee1164/1182 kmV A A#R*Inclination90.1U A#R(Period108.9 minn!A  M#jB" &g'KLaunch vehicleScout #102& * # 8 b ' "(OTechnical dataW4* # hTransmits with 3 W on 150 MHz and 5 W on 400 MHz.7b 1h0D0W 7 @Nova 2G 7 8 @ G" Nova 2= t # 4Also called NNSS 30 5001 7 '  Generalg t G#^@") Designation15362 / 84110A\ h A#R6Launch date12 Oct 1984t' M#jN"N ,㹌לCountry of originUnited Statesgh CM#j4"H̀シMissionNavigation` A#R>"Perigee/Apogee1149/1199 kmVCA#R*Inclination89.9UNA#R(Period108.9 minn!M#jB" &g'KLaunch vehicleScout #104&N @#  @ 8D@' "(OTechnical dataV3 @@# ftransmits with 3 W on 150 MHz and 5 W on 400 MHz7D@@10X@AENova 3G@A8 @ G" Nova 3=@UA# 4Also called NNSS 30 4901 AA'  Generalg UAAG#^@") Designation19223 / 88052A\AIBA#R6Launch date16 Jun 1988t'ABM#jN"N ,㹌לCountry of originUnited StatesgIB$CM#j4"H̀シMissionNavigation`BCA#R>"Perigee/Apogee1150/1198 kmT$CCA#R&Inclination90UC-DA#R(Period108.9 minn!CDM#jB" &g'KLaunch vehicleScout #111[-DDA#R4Launch siteVandenberg&DE# 8DTE' "(OTechnical dataV3EE# fTransmits with 3 W on 150 MHz and 5 W on 400 MHz@TEE1 0_0YE*FHProgram: NPOESS@E*F, (*" Program: NPOESSE/G& National Polar-orbiting Operational Environmental Satellite SystemProgram to be launched in 2006. Is the follow on of DMSP and NOAA. This unique program is designed to save $300 million. it will consist of 3 satellites<*FkG' *O External resourcesj/GH. ,http://www.laafb.af.mil/SMC/PK/NPOESS/rfp.htmhttp://www.fas.org/spp/military/program/met/npoess.htm1kG4H1[Z4HHHT+HH) "VȠ$To view this page you need to register*4HH%  = HH10[H10 cm rough Aluminum sphere5KØØ'  End of lifeUØĘA#R(Decay2 Oct 1994$Ø<Ę" ; ĘwĘ1d:1u1dwĘĘȘOderacs 1BK<ĘĘ8 @( " Oderacs 1B1 wĘĘ'  Generalg ĘZŘG#^@") Designation22991 / 94006C[ĘŘA#R4Launch date3 Feb 1994jZŘƘM#j:"N ,㹌לCountry of originUSAp)ŘƘG#^R"H̀MissionMilitary: radar calibration^ƘƘA#R:"Perigee/Apogee358/386 kmVƘCǘA#R*Inclination59.9TƘǘA#R&Period91.7 minjCǘȘM#j:" &Launch vehicleSTS 60F"ǘGȘ$ D10 cm polished Aluminum sphere5Ș|Ș'  End of lifeUGȘȘA#R(Decay4 Oct 1994$|ȘȘ" ; Ș0ɘ1Q/11e0ɘ{ɘ͘Oderacs 1CKȘ{ɘ8 @( " Oderacs 1C1 0ɘɘ'  Generalg {ɘʘG#^@") Designation22992 / 94006D[ɘnʘA#R4Launch date3 Feb 1994jʘʘM#j:"N ,㹌לCountry of originUSAp)nʘH˘G#^R"H̀MissionMilitary: radar calibration^ʘ˘A#R:"Perigee/Apogee358/386 kmVH˘˘A#R*Inclination59.9T˘P̘A#R&Period91.7 minj˘̘M#j:" &Launch vehicleSTS 60<P̘̘$ 05 cm Aluminum sphere5̘+͘'  End of lifeL ̘w͘A#RDecay?$+͘͘" ; w͘͘1Tu12f͘!Θ_Oderacs 1DK͘!Θ8 @( " Oderacs 1D1 ͘RΘ'  Generalg !ΘΘG#^@") Designation22993 / 94006E[RΘϘA#R4Launch date3 Feb 1994jΘ~ϘM#j:"N ,㹌לCountry of originUSAp)Ϙ G#^R"H̀MissionMilitary: radar calibration~Ϙ ͘^~ϘjA#R:"Perigee/Apogee358/386 kmV A#R*Inclination59.9TjA#R&Period91.7 minj~M#j:" &Launch vehicleSTS 60<$ 05 cm Aluminum sphere5~'  End of lifeL ;A#RDecay?$_" ; ;1W12g Oderacs 1EK_8 @( " Oderacs 1E1 '  Generalg }G#^@") Designation22994 / 94006F[A#R4Launch date3 Feb 1994j}BM#j:"N ,㹌לCountry of originUSAp)G#^R"H̀MissionMilitary: radar calibration^BA#R:"Perigee/Apogee223/226 kmTdA#R&Inclination57RA#R"Period89 minjd M#j:" &Launch vehicleSTS 60=]$ 215 cm Aluminum sphere5 '  End of lifeU]A#R(Decay3 Mar 1995$ " ; F1Z2 2hF Oderacs 1FK 8 @( " Oderacs 1F1 F'  Generalg )G#^@") Designation22995 / 94006G[A#R4Launch date3 Feb 1994j)M#j:"N ,㹌לCountry of originUSAp)^ G#^R"H̀MissionMilitary: radar calibration^ A#R:"Perigee/Apogee198/202 kmT^  A#R&Inclination57T d A#R&Period88.5 minj M#j:" &Launch vehicleSTS 60=d $ 215 cm Aluminum sphere5 @ '  End of lifeV A#R*Decay24 Feb 1995$@ " ; 122i @ @Oderacs 2AK @ 8 @( " Oderacs 2A1 q '  Generalg @ G#^@") Designation23471 / 95004Cg&q ? A#RLLaunch date4 Feb 1995 at 04:57 UTj M#j:"N ,㹌לCountry of originUSAp)? G#^R"H̀MissionMilitary: radar calibration^ wA#R:"Perigee/Apogee314/336 kmVA#R*Inclination51.6RwA#R"Period91 minjM#j:" &Launch vehicleSTS 63C @$ >10.16 cm diameter Al sphere @ ; G@1h 2J2jG@@DOderacs 2BK @@8 @( " Oderacs 2B1 G@@'  Generalg @*AG#^@") Designation23472 / 95004Dg&@AA#RLLaunch date4 Feb 1995 at 04:57 UTj*AAM#j:"N ,㹌לCountry of originUSAp)AkBG#^R"H̀MissionMilitary: radar calibration^ABA#R:"Perigee/Apogee314/336 kmVkBCA#R*Inclination51.6RBqCA#R"Period91 minjCCM#j:" &Launch vehicleSTS 63?qCD$ 615.24 cm dia. Al sphere5COD'  End of lifeVDDA#R*Decay29 Sep 1995$ODD" ; DE12u2kEOEHOderacs 2CKDOE8 @( " Oderacs 2C1 EE'  Generalg OEEG#^@") Designation23473 / 95004Eg&ENFA#RLLaunch date4 Feb 1995 at 04:57 UTjEFM#j:"N ,㹌לCountry of originUSAp)NF(GG#^R"H̀MissionMilitary: radar calibration^FGA#R:"Perigee/Apogee314/336 kmV(GGA#R*Inclination51.6RG.HA#R"Period91 minjGHM#j:" &Launch vehicleSTS 63E!.HH$ B5.08 cm diameter steel sphere; HI1jJ22lIcIMOderacs 2DKHcI8 @( " Oderacs 2D1 II'  Generalg cIIG#^@") Designation23474 / 95004Fg&IbJA#RLLaunch date4 Feb 1995 at 04:57 UTjIJM#j:"N ,㹌לCountry of originUSAp)bJ4.318 cm length dipole wire?<114o LJProgram: OffekO 8 @0∣" Program: OffekLJ& )Also called offeqFirst Israeli program, mainly for military experimentation purposes, especially for remote sensing and optical reconnaissance.1 1p|<LJ|H `x5ffffProgram: OffekOffek 1Offek 2Offek 3Offek 481R@3qOffek 1H|8 @"∣" Offek 173# (Means "Horizon 1"1 d'  Generalg 3ˉG#^@") Designation19519 / 88087A\d'A#R6Launch date19 Sep 1988m ˉM#j@"N ,ΝECountry of originIsrael_'G#^0"H̀MissionTechnology_RA#R<"Perigee/Apogee250/1149 kmi(A#RPInclination142.9 (retrograd orbit)TRA#R&Period98.8 minm |M#j@" &<}Launch vehicleShavit #1YՌA#R0Launch sitePalmahimZ|/A#R2"Mass at launch156 kg?Ռn$ 6First Israeli satellite5/'  End of lifeVnA#R*Decay14 Jan 1989$" 8U13π3rUTÙOffek 2H8 @"∣" Offek 27UԎ# (Means "Horizon 2"1 '  Generalg ԎlG#^@") Designation20540 / 90027A[ǏA#R4Launch date3 Apr 1990m l@M#j@"N Ǐ@,ΝECountry of originIsrael_ǏG#^0"H̀MissionTechnology^@A#R:"Perigee/Apogee149/251 kmi(fA#RPInclination143.2 (retrograd orbit)TA#R&Period88.5 minm f'™M#j@" &<}Launch vehicleShavit #2Y™A#R0Launch sitePalmahim&'™™# 5™™'  End of lifeU™0ÙA#R(Decay9 Jul 1990$™TÙ" 80ÙÙ1 @3G3sÙÙΙOffek 3HTÙÙ8 @"∣" Offek 37Ù ę# (Means "Horizon 3"1 Ù<ę'  Generalg ęęG#^@") Designation23549 / 95018Ag&<ę řA#RLLaunch date5 Apr 1995 at 11:16 UTm ęwřM#j@"N ,ΝECountry of originIsraelm& řřG#^L"H̀MissionMilitary: reconnaissance^wřBƙA#R:"Perigee/Apogee369/729 kmi(řƙA#RPInclination143.4 (retrograd orbit)TBƙƙA#R&Period95.6 minm ƙlǙM#j@" &<}Launch vehicleShavit #4YƙǙA#R0Launch sitePalmahimZlǙșA#R2"Mass at launch225 kg?Ǚ^ʙ' 1Reported by Israel's media as the first spy satellite... but it's most likely not a fullyfleged spy satellite.Offek 3 is the first of the second-generation light satellites for Israel. The system is being proposed and marketed by Israel Aircraft Industries and MLM System Engineering and Integration to carry payloads for astronomy and remote sensing purposes. The light-weight electro-optical scanner or Earth Resources Monitoring System carried aboard this mission was developed by El-Op. Equipped with a high-resolution camera.5șʙ'  End of life]^ʙʙA#R8"Out of servicelate 1997&ʙ˙# 8ʙN˙' "(OTechnical data8˙˙' " SpecificationsYN˙˙A#R0&Prime contractorIAIN ˙-̙A#RPlatformT˙̙A#R&"Mass at launchW-̙̙A#R,Payload mass36 kgO̙'͙A#RDimensionQ̙x͙A#R Solar arrayY'͙͙A#R0 Stabilization3-axisSx͙$ΙA#R$DC power180 WU͙yΙA#R($Design lifetime&$ΙΙ# 8yΙΙ1yπ3tΙϙmOffek 4HΙϙ8 @"∣" Offek 47ΙVϙ# (Means "Horizon 4"1 ϙϙ'  General\Vϙ G#^*") DesignationFTOϙ Ι\ϙhA#R6Launch date22 Jan 1998m M#j@"N ,ΝECountry of originIsraelm&hBG#^L"H̀MissionMilitary: reconnaissancem M#j@" &<}Launch vehicleShavit #5YBA#R0Launch sitePalmahimR.Z$ \The satellite was said to cost $50 million5'  End of life_ZA#R<"Out of service22 Jan 1998YGA#R0Causelaunch failure&m# 4G1@3(4uOFO< m2 4"  OFO1 '  Generalg uG#^@") Designation04690 / 70094A[A#R4Launch date9 Nov 1970t'uDM#jN"N ,㹌לCountry of originUnited States_G#^0"H̀MissionScientific^DA#R:"Perigee/Apogee304/518 kmVWA#R*Inclination37.4TA#R&Period92.6 minm WM#j@" &g'KLaunch vehicleScout #70&># 5s'  End of lifeU>A#R(Decay9 May 1971$s" = )145v)v Program: OGOMv8 @,J d%" Program: OGO)+ )  Orbiting Geophysical ObservatoryAmerican scientific program of standardized spacecraft capable of conducting many related experiments.<vg ' *O External resourcesf?+ ' ~http://heasarc.gsfc.nasa.gov/docs/heasarc/missions/ogo.html1g 1w B V |8S}V}V}V}V}V}VProgram: OGOOGO 1OGO 2OGO 3OGO 4OGO 5OGO 66 1 4x  FOGO 1F  8 @J d%" OGO 11 C '  Generalg  G#^@") Designation00879 / 64054A[C  A#R4Launch date5 Sep 1964t' y M#jN"N ,㹌לCountry of originUnited States|/ M#j^"H̀d;plMissionScientific: magnetosphere studyb!y W A#RB"Perigee/Apogee4930/144824 kmV A#R*Inclination40.7VW A#R*Period3841.9 minq$ tM#jH" &mO{Launch vehicleAtlas Agena B_A#R<Launch siteCape Canaveral_teA' OGO I carried 20 experiments, more than any previous satellite. The spacecraft's highly elliptical orbit was planned to permit correlated investigations of geophysical and solar phenomena in the Earth's atmosphere and magnetosphere, and in interplanetary spaceeA .Two experiment booms failed to deploy properly, however, and one of these booms obscured the horizon scanner's view of Earth. As a result, spacecraft attitude could not be Earth oriented and OGO I remained spin stabilized at 5 rpm. The solar panels were turned to a more favorable sun angle and all 20 experiments were able to provide data.:B+ $`OGO 1, together with data from Explorer 21, has indicated the source of much of the Van Allen belt's high-energy radiation as the solar wind - entering the magnetosphere through weak field lines in the magnetosphere's tail on the side of the Earth opposite the sun.8eAB' "(OTechnical data8BC' " SpecificationsVBeCA#R*&Prime contractorN CCA#RPlatformZeC DA#R2"Mass at launch523 kgWCdDA#R,Payload mass95 kgW DDA#R,Dimension18 x 6 m}<dD8EA#RxSolar array32000 solar cells + nickel-cadmium batteriesb!DEA#RB Stabilizationspin stabilizedN 8EEA#RDC powerUE=FA#R($Design lifetimepEF$ Spacecraft systems included a communication and data handling system to store up to 128,000 bits per second.6=FG1`4ڃ4yGMGKOGO 2FFMG8 @J d%" OGO 21 G~G'  Generalg MGGG#^@") Designation01620 / 65081A\~GAHA#R6Launch date14 Oct 1965t'GHM#jN"N ,㹌לCountry of originUnited States|/AH1IM#j^"H̀d;plMissionScientific: magnetosphere study_HIA#R<"Perigee/Apogee419/1515 kmV1IIA#R*Inclination87.4UI;JA#R(Period104.4 minn!IJM#jB" &#*≂Launch vehicleThor Agena[;JKA#R4Launch siteVandenberg&J*K# 5K_K'  End of lifeV*KKA#R*Decay17 Sep 1981$_KK" 6KL145zLULOGO 3FKUL8 @J d%" OGO 31 LL'  Generalg ULLG#^@") Designation02195 / 66049A[LHMA#R4Launch date7 Jun 1966t'LMM#jN"N ,㹌לCountry of originUnited States|/HM8NM#j^"H̀d;plMissionScientific: magnetosphere studyc"MNA#RD"Perigee/Apogee19519/102806 kmV8NNA#R*Inclination77.6VNGOA#R*Period2911.5 minq$NOM#jH" &mO{Launch vehicleAtlas Agena B\GO A#R6LaunchO K siteVandenberg?O% The orbit of this satellite remains uncertain. Other sources give 319/122173 km x 31.39 deg x 2915 min. This seems unprobable since with such a low perigee the satellite would have reentred.6 =1ڃ45{= OGO 4F8 @J d%" OGO 41 ='  Generalg G#^@") Designation02895 / 67073A\wA#R6Launch date28 Jul 1967t'낚M#jN"N ,㹌לCountry of originUnited States|/wgM#j^"H̀d;plMissionScientific: magnetosphere study^낚ŃA#R:"Perigee/Apogee422/885 kmTgA#R&Inclination86TŃmA#R&Period97.8 minp#݄M#jF" &#*≂Launch vehicleThor Agena D[m8A#R4Launch siteVandenberg&݄^# 58'  End of lifeV^酚A#R*Decay16 Aug 1972$ " 6酚C15I5|CkOGO 5F 8 @J d%" OGO 51 C'  Generalg !G#^@") Designation03138 / 68014A[|A#R4Launch date4 Mar 1968t'!M#jN"N ,㹌לCountry of originUnited States|/|lM#j^"H̀d;plMissionScientific: magnetosphere studya ͈A#R@"Perigee/Apogee271/148186 kmTl!A#R&Inclination54V͈wA#R*Period3795.9 minq$!艚M#jH" &mO{Launch vehicleAtlas Agena D_wGA#R<Launch siteCape Canaveral$艚k" 6G15}犚rOGO 6Fk犚8 @J d%" OGO 61 '  Generalg 犚G#^@") Designation03986 / 69051A[ڋA#R4Launch date5 Jun 1969t'NM#jN"N ,㹌לCountry of originUnited States|/ڋʌM#j^"H̀d;plMissionScientific: magnetosphere study_N)A#R<"Perigee/Apogee397/1089 kmTʌ}A#R&Inclination82T)эA#R&Period99.7 minq$}BM#jH" &mO{Launch vehicleAtlas Agena D[эA#R4Launch siteVandenberg&BÎ# 5'  End of lifeVÎNA#R*Decay12 Oct 1979$r" 7N1(4'5~DĚOhsumi7 r, (" Ohsumi>*# 6*rNamed as its launch site1 ['  Generalg *G#^@") Designation04330 / 70011A\[A#R6Launch date11 Feb 1970lM#j>"N ,bCountry of originJapanUG#^"H̀Mission`?šA#R>"Perigee/Apogee323/2.416 kmTšA#R&Inclination31U?ššA#R(Period113.1 ming šOÚG#^@" &Launch vehicleLambda L 4SZšÚA#R2Launch siteKagoshima[OÚĚA#R4"Mass at launch23.8 kg@ÚDĚ$ 8First Japanese satellite8Ě|Ě156|ĚĚ=Olympus@DĚĚ2 4"  OlympusQ(|Ě Ś) "P Also called L SAT (Large SATellite)1 Ě>Ś'  Generalg ŚŚG#^@") Designation20122 / 89053A\>ŚƚA#R6Launch date12 Jul 1989m ŚnƚM#j@"N ,4"Country of originEuropeo"ƚƚM#jD"H̀‰MissionTelecommunications]nƚ:ǚA#R8,Geostationary orbit19Wn!ƚǚM#jB" &3D+Launch vehicleAriane V32&:ǚǚ# 5ǚȚ'  End of life_ǚbȚA#R<"Out of service12 Aug 1993YȚȚA#R0CauseOut of control_9bȚ˚& sThe control's satellite was lost on 29 May 1991 because of a stabilization problem that caused an electric interruption. The satellite then drifted over Pacific and Atlantic. It was found by radars and the control was taken over by the ESA's station in Darmstadt on 19 Jun 1992. It was then put back into service on 7 Aug 1992.On 12 Aug 1993 it started rotating and fell in backup mode to try to stabilize (during the Perseid shower). 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.<ȚV˚' *O External resources[4˚˚' hhttp://www.esoc.esa.de/external/mso/olympus.html8V˚˚' "(OTechnical data8˚!̚' " Specificationsq0˚̚A#R`&Prime contractorBritish Aerospace (now MMS)U!̚̚A#R(PlatformOlympus[̚B͚A#R4"Mass at launch2595 kgX͚̚A#R.Payload mass359 kg`B͚͚A#R>Dimension2.9 x 2.7 x 5.6 mZ͚TΚA#R2Solar array26 m spanY͚ΚA#R0DC powerEOL: 3600 WYTΚϚA#R0 Stabilization3 axis\ΚbϚA#R6$Design lifetime7 years&ϚϚ# 1 bϚϚ'  Ku-bandb!Ϛ'A#RB(Main Ϛ'DĚtransponders2 (DBS) + 4YϚA#R0,Backup transpondersS'B#TPowerDBS: 2 transponders of 230 W (TWTA)others: 4 transponders of 30 W (TWTA)o-B#TZBandwidthDBS: 27 MHzothers: 18 & 36 MHz>B#T|CoverageDBS: Italy and Europe (steerable)others: 5 spotsk)oB#TREIRP maxDBS: 63 dBWothers: 33.3 dBWRA#R"Polarizationr0o3B#T`FrequenciesDBS: 12/18 GHzothers: 12/14 GHz&Y# =3' , Ka-band (20/30 GHz)XYA#R.(Main transponders2ZHA#R2,Backup transponders1VA#R*Power30 W (TWTA)[HA#R4Bandwidth40 & 700 MHzd#]A#RFCoverage2 steerable spot beamsVA#R*EIRP max52.1 dBWR]A#R"Polarization8=% 'Equipped with 5 steerable antennas for numerous experiments (direct TV and HDTV). Also equipped with 3 beacons at 12, 20 and 30 GHz for propagation measurements. Non Ku-band DBS transponders are designed for digital transmissions in AMRT with an on-board matrix commuter.?|1'59|^Program: OptusK=5 :.-" Program: Optusn|^) ""6]Australian telecommunication satellite system operated by Optus communications. Formerly known as Aussat.11M a^M ] ______ `Program: OptusOptus A1Optus A2Optus A3Optus B1Optus B2Optus B3Optus C11~ 1U~ l>M # 6Optus A's specifications\~  A#R60&Prime contractorHughesT l A#R&0PlatformHS-376[ A#R40"Mass at launch1250 kgTl  A#R&0Dry mass540 kgY t A#R00 Mass in orbit655 kgT A#R&0Diameter2.16 ma t ) A#R@0Height6.6 m (2.84 m stowed)b! A#RB0 StabilizationSpin stabilizedT) A#R&0DC power1000 Wl+ K A#RV0$Design lifetime7 years (10 for the A3)& q # 7K '   Video carrier^q A#R:*Receiver bandwidth30 MHzf% lA#RJ2Peak to peak deviation22.3 MHz/V$" 1l1UAA7# (Optus A's Ku-band[SA#R40(Main transponders11+4\A#R60,Backup transponders2+2NSK@B#T0Power(11+2) K@transponders of 12 W (TWTA)(4+2) transponders of 30 W (TWTA)U@A#R(0Bandwidth45 MHzs2K@AA#Rd0CoverageAustralia, New Zealand and New Guineah&@{AB#TL0EIRP max12 W: 41 dBW30 W: 51 dBWRAAA#R"0Polarization${AA" 1A"B1"BvFL%AnB' JOptus A's antenna specificationsb"BBJ#d0  BeamTransponders`nB0CA#R>National A1, 3, 4, 6 and 7m,BCA#RX4South Eastern Australia1, 3, 5, 7 and 8d#0CDA#RF(Western Australia2, 4, 7 and 8v5CwDA#RjRPapua New Guinea or South West pacific4, 6 and 7h'DDA#RNNational B9, 10, 12, 13, 14 and 15c"wDBEA#RD North Eastern9, 11, 14 and 15h'DEA#RN(Central Australia10, 12, 14 and 15BEvF% OThis chart gives the possible transponders with beams connections. Alternative selection of Papua New Guinea or South West pacific beams is possible with Optus A3.1EF1UFLpQ.vFF# \Optus A's transponder frequency chart (GHz)cFG# * X v  Horizontal uplinkHorizontal downlinkTransponderVertical downlinkVertical uplinkFvHt#0,14.025112.277GIt#0,14.089212.341vHIt#0,14.153312.405IJt#0,14.217412.469IJt#0,14.281512.553J2Kt#0,14.345612.597JKt#>*:14.4097 (30 W)12.6612KXLt#>*:14.4738 (30 W)12.725KLt#0 12.309914.057XLqMt#2"12.3731014.121LMt#2"12.4371114.185qMNt#2"12.5011214.249MOt#2"12.5651314.313 NOt#@,012.62914 (30 W)14.377 OLt#@OLvF,012.69315 (30 W)14.441$Op" 1L1WT+p) "VȠ$To view this page you need to register&# 1L1UL军># 6Optus B's specifications\L恛A#R60&Prime contractorHughesT:A#R&0PlatformHS-601[恛A#R40"Mass at launch2858 kgU:ꂛA#R(0Dry mass1270 kgZDA#R20 Mass in orbit1582 kgc"ꂛA#RD0Dimension2.27 x 2.27 x 2.27 mZDA#R20Solar array20 m spanYZA#R00 Stabilization3 axisf$B#TH0DC powerBOL: 3500 WEOL: 3000 W_ZA#R<0$Design lifetime13.7 yearsŅ% Carries a Ka-band beacon (30 GHz) and a laser retroreflector for precise satellite location and time transfer demonstrations.7'   Video carrier^ŅZA#R:*Receiver bandwidth25 MHzg&A#RL2Peak to peak deviation17.74 MHz/V$Z军" 11Uo6军L# &Optus B's L-bandn-A#RZ0(Main transponders2 (inbound and outband)YLA#R00Power150 W (8 SSPA)[nA#R40$Total bandwidth14 MHzWňA#R,0CoverageAustraliaTnA#R&0EIRP max49 dBWVňoA#R*0PolarizationRHCP$" 1oĉ1Uĉƌꌛ7# (Optus B's Ku-bandm,ĉhA#RX0(Main transponders15+1 (L-band downlink)ZŠA#R20,Backup transponders6VhA#R*0Power50 W (TWTA)UŠmA#R(0Bandwidth54 MHzYT#x06ް鉂A鉂CoverageAustralia (1 national beam and 5 regional beams)High Performance beamTmnA#R&0EIRP max47 dBWXƌA#R.0Polarizationlinear$nꌛ" 1ƌ1v›L%ꌛg' JOptus B's antenna specificationsbɍJ#d0  BeamTranspondersq*g:G#^T"ްNational A1, 2, 3, 4, 5, 6, 7 and 8j)ɍA#RRNew Zealand1, 2, 3, 4, 5, 6, 7 and 8~7:"G#^n"8South Eastern Australia1, 2, 3, 4, 5, 6, 7 and 8i"G#^D",Western Australia6, 7 and 8t-" G#^Z"ްNational B9, 10, 11, 12, 13, 14 and 15 ꌛz3G#^f"A*High performance9, 10, 11, 12, 13, 14 and 15h! G#^B"$North Eastern11, 14 and 15l%ZG#^J",Central Australia12, 14 and 15v›% This chart gives the possible transponders with beams connections. The National A, South Eastern Australia and Western Australia beams can be combined with the New Zealand beam: the power split is 20% to New Zealand and 80% for the other beam.1Z›1U›1ΛUΛQ.v››# \Optus B's transponder frequency chart (GHz)c›Û# * X v  Horizontal uplinkHorizontal downlinkTransponderVertical downlinkVertical uplink›xět#4014.0299112.2819Ûśt#4014.0925212.3445xěśt#4014.1551312.4071ś"ƛt#4014.2177412.4697śƛt#4014.2803512.5323"ƛ>Ǜt#4014.3429612.5949ƛǛt#4014.4055712.6575>ǛZțt#4014.4681812.7201Ǜțt#4"12.3132914.0612Zțwɛt#6 $12.37581014.1238țʛt#6 $12.43841114.1864wɛʛt#6 $12.50101214.2490ʛ$˛t#6 $12.56361314.3116ʛ˛t#6 $12.62621414.3742$˛B̛t#6 $12.68881514.4368@˛̛<#Hp@B̛̛0#0Mobile communication (L-band to Ku-band & Ku-band to L-band):&̛͛#ЀL*.12.2705M (16)1.6535 (RHCP)%̛1Λt#J$481.5520 (RHCP)M (16)14.0185$͛UΛ" 11ΛΛ1ΛΛ\&UΛΛ6 L♱X㉂Q#4'ASpecificationsAntenna specificationsKu-bandTransponder frequency chart9T18K8T] Optus A2E5 :"-" Optus A2;T# 0Also called Aussat A21 '  Generalg lG#^@") Designation16275 / 85109C\A#R6Launch date27 Nov 1985p#l8M#jF"N ,Country of originAustraliao"M#jD"H̀‰MissionTelecommunicationsb!8 A#RB,Geostationary orbitsee belowjsM#j:" &xLaunch vehicleSTS 31& # : s- */ۀ Location] m#:   " BeginEndPosition j#8$(*L: 27 Nov 1985156E ] m j#@Feb 1995164E, inclined& # 8m ' "(Technical dataT ] > L♱X㉂Q#4'ASpecificationsAntenna specificationsKu-bandTransponder frequency chart9 188 BOptus A3E] 5 :"-" Optus A3;  # 0Also called Aussat A31 G '  Generalg  G#^@") Designation18350 / 87078A\G A#R6Launch date16 Sep 1987p# z M#jF"N ,Country of originAustraliao" M#jD"H̀‰MissionTelecommunicationsb!z KA#RB,Geostationary orbitsee belown! M#jB" &C+Launch vehicleAriane V19&K# : - */ۀ Locationm#:   " BeginEndPosition5@j#8$(5@] *L: 16 Sep 1987164E@j#,Feb 1995156E 5@?Aj#@Aug 1995152E, inclined&@eA# 8?AA' "(Technical dataTeA/B> L♱X㉂Q#4'ASpecificationsAntenna specificationsKu-bandTransponder frequency chart=AlB' , EIRP coverage (dBW)Y)/BB0 0R4BBkCentral beamAustralian spot beams1lBB1ByCLByC7 >_"Optus A3's EIRP (National beam)Add 4 to 5 dBW for 30 W transponders1BC1C5DTyC5D7 >_"Optus A3's EIRP (Australian spot beams)Add 4 to 5 dBW for 30 W transponders9CnD1K8V8nDDIOptus B1E5DD5 :"-" Optus B11 nDD'  Generalg DKEG#^@") Designation22087 / 92054A\DEA#R6Launch date13 Aug 1992p#KEFM#jF"N ,Country of originAustraliao"EFM#jD"H̀‰MissionTelecommunicationsfFFG#^>"/ۀ0Geostationary orbit160E>FwGM#j|" &9+SLaunch vehicleLong March 2E (first commercial flight)XFGA#R.Launch siteXichang&wGG# 8G-H' "(Technical data]GHE ZJ ㉂⾮HY5PJSpecificationsAntenna specificationsL-bandKu-bandTransponder frequency chart=-H I' , EIRP coverage (dBW)xAHI7 >ް鉂A鉂Central beamAustralian spot beamsHigh Performance beam9 II189IJOptus B2EIJ5 :"-" Optus B21 I3J'  Generalg JJG#^@") Designation22278 / 92090Ah'3JKA#RNLaunch date21 Dec 1992 at 11:20 UTp#JrKM#jF"N ,Country of originAustraliao"KKM#jD"H̀‰MissionTelecommunications\rK=LA#R6,Geostationary orbitn/aq$KLM#jH" &9+SLaunch vehicleLong March 2E&=LL# 5L M'  End of life_LhMA#R<"Out of service21 Dec 1992R M D#VCauseThe satellite was destroyed when the fairing area of the launch vehicle was destroyed some 47 seconds after liftoff. The cause of the failure is still subject to some speculation and disagreement but was almost certainly due to wind shear effects encountered just after liftoff.The Optus B series of satellites have a liquid propulsion apogee engine (not solid propelled motor). They do, however, have a solid perigee stage when launched on Long March 2E. It is almost certain that this solid motor (plus a few remnants of the satellite itself) is all that was delivered into orbit.hM I&hM2# 8 j' "(Technical data]2 E ZJ ㉂⾮HY5PJSpecificationsAntenna specificationsL-bandKu-bandTransponder frequency chart=jI' , EIRP coverage (dBW)xA 7 >ް鉂A鉂Central beamAustralian spot beamsHigh Performance beam9I1`V89CrOptus B3IC8 @$-" Optus B3N+# VThis spacecraft is also called Optus B2R1 C‚'  Generalg )G#^@") Designation23227 / 94055Ah'‚A#RNLaunch date27 Aug 1994 at 21:10 UTp#)M#jF"N ,Country of originAustraliao"pM#jD"H̀‰MissionTelecommunicationsb!҄A#RB,Geostationary orbitsee belowq$pCM#jH" &9+SLaunch vehicleLong March 2E&҄i# : C- */ۀ Locationi-m#:   " BeginEndPosition$j#H$8:L: 27 Aug 1994Jul 1995152E-;j#,Aug 1995156E㇜% In mid-1998 the satellite was sold to Commonwealth Bank of Australia Ltd (CBA) for A$206 million and leased back from the bank.8;' "(Technical data]㇜E ZJ ㉂⾮HY5PJSpecificationsAntenna specificationsL-bandKu-bandTransponder frequency chart=' , EIRP coverage (dBW)xAr7 >ް鉂A鉂Central beamAustralian spot beamsHigh Performance beam; 189Optus C1/DKr8 @(-" Optus C1/D<4# 2The "/D" means defense1 e'  GeneralY4G#^$") DesignationZeA#R2Launch datelate 2000p#M#jF"N ,Country of originAustraliao"M#jD"H̀‰MissionTelecommunicationsYPA#R0,Geostationary orbit\G#^*" &Launch vehicleS/P$ ^The satellite will carry a military payload101W0T+) "VȠ$To view this page you need to register&0# A덜16u;덜8œProgram: OrbcommM85 :28" Program: Orbcommz덜8 >XdOSXdOTelecommunication program operated by Orbcomm a subsidiary of OSC. It will consist of a network of LEO satellites to relay the GPS-determined locations of cargo trucks, and data from oil pipeline monitors. Orbcomm terminal will also be able to determine their own position based upon Doppler ranging of the satellite. Initial FCC authorization: Oct 1994.Orbcomm has signed in Sep 1995 the fi8nal financing and contruction agreements for an expanded 36-Orbcomm satellite constellation, with Canada's Teleglobe investing $85 million and OSC $75 million. Technology Resources Industries Bhd. of Malaysia is also a shareholder.8œ' Full-time service will begin when 26 satellites are in orbit. The full network will be composed of 4 near-polar satellites and 32 satellites inclined at 45. Altitude: about 775 km. The global cost of the system is evaluated $330 million In Oct 1997 Orbcomm to change the inclination of some planes from 70 to 108.In April 1998 Orbcomm was granted by the FCC to operate 12 more satellites and to higher the altitude of some satellites to 815 km. 1Ü1|Ü`ĜKœ`Ĝ Ѐ㐫9_P8s:9s:s:?s:@s:rZыiZыjZыProgram: OrbcommOrbcomm XOrbcomm XP 1Orbcomm FM 1Orbcomm FM 2Orbcomm FM 5Orbcomm FM 6Orbcomm FM 7Orbcomm FM 8Orbcomm FM 9Orbcomm FM 10Orbcomm FM 11Orbcomm FM 121ÜĜ1Ĝ`ʜA`ĜĜ# <Orbcomm FM's specificationsYĜ+ŜA#R0&Prime contractorOSCWĜŜA#R,PlatformMicrostarY+ŜŜA#R0"Mass at launch40 kgSŜ.ƜA#R$ Mass in orbit[ŜƜA#R4Diameter1.04 m stowedZ.ƜƜA#R2Height0.165 m stowed\Ɯ?ǜA#R6Width2.2235 m deployedc"ƜǜA#RD Stabilizationgravity gradientN ?ǜǜA#RDC powerUǜEȜA#R($Design lifetime_ǜȜA#R<Telemetry57.6 kbps in VHF]9EȜɜ$ rDeploys a 3.28 m long VHF/UHF communications antenna.5Ȝ6ɜ' O Frequencies*ɜ`ʜ) Gateway to satellite: 148 - 149.9 MHz (57.6 kbps)Satellite to client: 137 - 138 MHz (4.8 kbps)Client to satellite: 148 - 149.9 MHz (2.4 kbps)Satellite to gateway: 137 - 138 MHz (57.6 kbps)Beacons: 400.05 - 400.15 MHzAddressing based on X400 protocol: 6ɜʜ1<^9ʜʜΜOrbcomm XJ`ʜʜ8 @&8" Orbcomm X1 ʜ˜'  Generalg ʜ|˜G#^@") Designation21576 / 91050C\˜˜A#R6Launch date17 Jul 1991t'|˜L̜M#jN"N ,㹌לCountry of originUnited Stateso"˜̜M#jD"H̀㓉MissionTelecommunications^L̜͜A#R:"Perigee/Apogee764/771 kmV̜o͜A#R*Inclination98.4U͜͜A#R(Period100.2 minn!o͜2ΜM#jB" &`D+Launch vehicleAriane V44[͜ΜA#R4"Mass at launch22.8 kgb>2ΜΜ$ |Experimental satellite. Should provide emergency services.= Μ,Ϝ19$:,ϜyϜOrbcomm XP 1MΜyϜ8 @,8" Orbcomm XP 1mJ,Ϝ # Also called OXP 1 or Orbcomm CDS (Capabilities Demonstration Satellite)yϜ Μ1 yϜ='  Generalg G#^@") Designation22489 / 93009A[=A#R4Launch date9 Feb 1993t'sM#jN"N ,㹌לCountry of originUnited Stateso"M#jD"H̀㓉MissionTelecommunications^s@A#R:"Perigee/Apogee727/790 kmTA#R&Inclination25S@A#R$Period100 minn!UM#jB" &GKTLaunch vehiclePegasus #3[A#R4Launch siteVandenberg>U$ 4Experimental satellite= +1.^9&:+xu Orbcomm FM 1Mx8 @,8" Orbcomm FM 11 +'  Generalg xG#^@") Designation23545 / 95017Ag&wA#RLLaunch date3 Apr 1995 at 13:48 UTt'M#jN"N ,㹌לCountry of originUnited Stateso"wZM#jD"H̀㓉MissionTelecommunications^A#R:"Perigee/Apogee727/756 kmTZ A#R&Inclination70L XA#RPeriodn! M#jB" &GKTLaunch vehiclePegasus #8[X!A#R4Launch siteVandenberg\$ Had stopped sending signals short after launch but control was regained in mid May 1995.8!' "(Technical datapu , (SpecificationsTransmits on 137.7075 MHz LHCP (12 W)+ satellite to gateway link at 137.56 MHz (57.6 kbps)=  1$:; POrbcomm FM 2Mu 8 @,8" Orbcomm FM 21 0 '  Generalg G#^@") Designation23546 / 95017Bg&0 A#RLLaunch date3 Apr 1995 at 13:48 UTt' r M#jN"N ,㹌לCountry of originUnited Stateso" M#jD"H̀㓉MissionTelecommunications^r ? A#R:"Perigee/Apogee727/756 kmT A#R&Inclination70L ? A#RPeriodn! M M#jB" &GKTLaunch vehiclePegasus #8[ A#R4Launch siteVandenbergM |% _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.8 ' "(Technical datap|P, (SpecificationsTransmits on 137.6775 MHz LHCP (10 W)+ satellite to gateway link at 137.56 MHz (57.6 kbps)= 1 ;:COrbcomm FM 3MP8 @,8" Orbcomm FM 31 @'  @PGeneralg ~@G#^@") Designation25158 / 98007B\@@A#R6Launch date10 Feb 1998t'~@NAM#jN"N ,㹌לCountry of originUnited Stateso"@AM#jD"H̀㓉MissionTelecommunicationsTNABA#R&"Perigee/ApogeeUAfBA#R(Inclination108L BBA#RPeriodm fBCM#j@" &㻦ʼnLaunch vehicleTaurus #2&BEC# 8C}C' "(Technical data<ECC) "&Specifications= }CC1{:CCDHOrbcomm FM 4MCCD8 @,8" Orbcomm FM 41 CtD'  Generalg CDDG#^@") Designation25159 / 98007C\tD7EA#R6Launch date10 Feb 1998t'DEM#jN"N ,㹌לCountry of originUnited Stateso"7EFM#jD"H̀㓉MissionTelecommunicationsTEnFA#R&"Perigee/ApogeeUFFA#R(Inclination108L nFGA#RPeriodm F|GM#j@" &㻦ʼnLaunch vehicleTaurus #2&GG# 8|GG' "(Technical data<GH) "&Specifications= GSH1V;~:SHHLOrbcomm FM 5MHH8 @,8" Orbcomm FM 51 SHH'  Generalg H8IG#^@") Designation25117 / 97084F\HIA#R6Launch date23 Dec 1997t'8IJM#jN"N ,㹌לCountry of originUnited Stateso"IwJM#jD"H̀㓉MissionTelecommunications`JJA#R>"Perigee/Apogee815 / 822 kmTwJ+KA#R&Inclination45L JwKA#RPeriodo"+KKM#jD" &GKTLaunch vehiclePegasus #19_wKELA#R<Launch siteWallops Island&KkL# 8ELL' "(Technical dataZ/kLL+ &^SpecificationsMain downlink: 137.200 MHz= L:M1:;:MMOrbcomm FM 6MLM8 @,8" Orbcomm FM 61 :MM'  Generalg MNG#^@") Designation25118 / 97084G\M{NA#R6Launch date23 Dec 1997t'NNM#jN"N ,㹌לCountry of originUnited Stateso"{N^OM#jD"H̀㓉MissionTelecommunications`NOA#R>"Perigee/Apogee815 / 822 kmT^OA#R&OLInclination45L OjA#RPeriodo"ـM#jD" &GKTLaunch vehiclePegasus #19_j8A#R<Launch siteWallops Island&ـ^# 88' "(Technical dataZ/^+ &^SpecificationsMain downlink: 137.225 MHz= -1~:{:-z׆Orbcomm FM 7Mz8 @,8" Orbcomm FM 71 -'  Generalg zG#^@") Designation25119 / 97084H\nA#R6Launch date23 Dec 1997t'⃝M#jN"N ,㹌לCountry of originUnited Stateso"nQM#jD"H̀㓉MissionTelecommunications`⃝A#R>"Perigee/Apogee815 / 822 kmTQA#R&Inclination45L QA#RPeriodo"M#jD" &GKTLaunch vehiclePegasus #19_QA#R<Launch siteWallops Island&E# 8}' "(Technical dataZ/E׆+ &^SpecificationsMain downlink: 137.435 MHz= }1&:D;aOrbcomm FM 8M׆a8 @,8" Orbcomm FM 81 '  Generalg aG#^@") Designation25112 / 97084A\UA#R6Launch date23 Dec 1997t'ɈM#jN"N ,㹌לCountry of originUnited Stateso"U8M#jD"H̀㓉MissionTelecommunications`ɈA#R>"Perigee/Apogee815 / 822 kmT8쉝A#R&Inclination45L 8A#RPeriodo"쉝M#jD" &GKTLaunch vehiclePegasus #19_8A#R<Launch siteWallops Island&,# 8d' "(Technical dataZ/,+ &^SpecificationsMain downlink: 137.460 MHz= d1;:HOrbcomm FM 9MH8 @,8" Orbcomm FM 91 y'  Generalg HG#^@") Designation25116 / 97084E\y<A#R6Launch date23 Dec 1997t'M#jN"N ,㹌לCountry of originUnited Stateso"<M#jD"H̀㓉MissionTelecommunications`A#R>"Perigee/Apogee815 / 822 kmTӎA#R&Inclination45L A#RPeriodo"ӎM#jD" &GKTLaunch vehiclePegasus #19_ A#R<Launch siteWallops Island &2# 8 j' "(Technical data[02+ &`SpecificationsMain downlink: 137.3125 MHz> j1;;QŝOrbcomm FM 10NQ8 @.8" Orbcomm FM 101 '  Generalg QG#^@") Designation25113 / 97084B\EA#R6Launch date23 Dec 1997t'M#jN"N ,㹌לCountry of originUnited Stateso"E(ÝM#jD"H̀㓉MissionTelecommunications`ÝA#R>"Perigee/Apogee815 / 822 kmT(ÝÝA#R&Inclination45L Ý(ĝA#RPeriodo"ÝĝM#jD" &GKTLaunch vehiclePegasus #19_(ĝĝA#R<Launch siteWallops Island&ĝŝ# 8ĝTŝ' "(Technical data[0ŝŝ+ &`SpecificationsMain downlink: 137.7375 MHz> Tŝŝ1D;;ŝ;ƝʝOrbcomm FM 11Nŝ;Ɲ8 @.8" Orbcomm FM 111 ŝlƝ'  Generalg ;ƝƝG#^@") Designation25114 / 97084C\lƝ/ǝA#R6Launch date23 Dec 1997t'ƝǝM#jN"N ,㹌לCountry of originUnited Stateso"/ǝȝM#jD"H̀㓉MissionTelecommunications`ǝrȝA#R>"Perigee/Apogee815 / 822 kmTȝȝA#R&Inclination45L rȝɝA#RPeriodo"ȝɝM#jD" &GKTLaunch vehiclePegasus #19_ɝɝA#R<Launch siteWallops Island&ɝʝ# 8ɝ>ʝ' "(Technical dataZ/ʝʝ+ &^SpecificationsMain downlink: 137.800 MHz> >ʝʝ1;V;ʝ$˝ϝOrbcomm FM 12Nʝ$˝8 @.8" Orbcomm FM 121 ʝU˝'  Generalg $˝˝G#^@") Designation25115 / 97084D\U˝̝A#R6Launch date23 Dec 1997t'˝̝M#jN"N ,㹌לCountry of originUnited Stateso"̝̝M#jD"H̀㓉MissionTelecommunications`̝[͝A#R>"Perigee/Apogee815 / 822 kmT̝͝A#R&Inclination45L [͝͝A#RPeriodo"͝jΝM#jD" &GKTLaunch vehiclePegasus #19_͝ΝA#R<Launch siteWallops Island&jΝΝ# 8Ν'ϝ' "(Technical data[0Νϝ+ &`SpecificationsMain downlink: 137.2875 MHzA'ϝϝ19<ϝ"Program: OrblinkAϝ, (," Program: Orbliϝϝnkϝ( OSC's global satellite network project to provide broadband fixed-site communications services. This program should become operational in 2002.The system is made of 7 satellites in MEO (9000 km, equatorial orbit). It should use inter-satellite links (65-71 GHz) to provide 15 Gbps links. Uplink and Downlink would take place between 37.5-38.5 GHz and 47.7-48.7 GHz. The coverage is limited to zones between 50 North and South latitudes.The satellites will be based on Orbital Starbus platform intended for GEO satellites (previously designed by CTA). Each satellite will have 4000 W of power, 100 spot beams for earth links and 2 inter-satellite links. Each should have 9 years lifetime and weigh approx 1600 kg."- (㻦ʼnThey can be launched 2 or 3 at a time on Delta 3, Atlas 2 or Ariane 4 vehicles, or 4 at a time on larger vehicles. Individual satellites also can be launched on a Taurus-derivative launch vehicle. The system cost is $900 million.1S1WST+") "VȠ$To view this page you need to register&S# : 1u;<A+DOrbview 2:A, (" Orbview 29z# ,Also called Seastar1 A'  Generalg zG#^@") Designation24883 / 97037A[mA#R4Launch date1 Aug 1997t'M#jN"N ,㹌לCountry of originUnited StateskmLM#j<"H̀郉MissionRemote sensingl+A#RV"Perigee/Apogee705 km (sun-synchronous)VLA#R*Inclination98.2a oA#R@Period99 min (16 day cycle)kM#j<" &GKTLaunch vehiclePegasuso / ,xOIt is the world's first privately owned satellite to provide multispectral (colour) images of the Earth, owned by OSC It is operated by Orbimage, a subsidiary of OSC.Carries NASA's SeaWiFS instrument as the sensor payload, also designated "Oceans Color Data Set." The objective for global ocean coverage is desired to estimate ocean color, and to derive from these measurements, various biological indicators and other useful scientific products.The SeaWiFS Team has developed, and will operate, a data system that will process, calibrate, validate, archive, and distribute SeaWiFS data for research. All other aspects of the mission -- satellite construction, launch, command and control and tracking -- are the responsibility of OSC. NASA has contracted with OSC to provide, for five years, the raw satellite data which will be used for research purposes. This contract is worth $43.5 million. OSC will own the data rights for operational and commercial purposes.< ' *O External resourcesT . ,http://seawifs.gsfc.nasa.gov/SEAWIFS.htmlhttp://www.orbimage.com/wseastar.htm8 ' "(OTechnical data8 ' " SpecificationsY `A#R0&Prime contractorOSCVA#R*PlatformOSC-madeZ`A#R2"Mass at launch309 kgScA#R$ Mass in orbitOA#RDimensionQc@A#R Solar array@Sb@A#R$ StabilizationN @@A#RDC power]b@ AA#R8$Design lifetime10 yearsd@A& Telemetry: 1702.5 MHz (665.4 kbps)Command: 2092.59 MHz (19.2 kbps)Data: 2272.5 MHz (2000 kbps)1 AA'  SeaWiFSABI#`0Wavebands412 nm (20 nm bandwidth)443 nm (20 nm bandwidth)490 nm (20 nm bandwidth)510 nm (20 nm bandwidth)555 nm (20 nm bandwidth)670 nm (20 nm bandwidth)765 nm (40 nm bandwidth)865 nm (40 nm bandwidth)QA7CA#R 0Swath widthPBCA#R0Resolution~7C+D& Has a rotating scanning telescope to achieve a scan angle > 58.3. The SeaWiFS instrument is built by Hughes Electronics; CfD1 <څ<fDDMOrbview 3A;+DD, ( " Orbview 3A1 fDD'  GeneralYD+EG#^$") Designation`DEA#R>Launch dateplanned in 1999t'+EEM#jN"N ,㹌לCountry of originUnited StatesUETFG#^"H̀Missionj)EFA#RR"Perigee/Apogee470 km sun-synchronousTTFGA#R&Inclination97L F^GA#RPeriodcGGG#^8"Orbital cycle< 3 daysk^G,HM#j<" &GKTLaunch vehiclePegasusnHGH& USAF contract worth $41.5 millionOrbview 3B should be very similar8,HH' "(OTechnical data8H I' " SpecificationsYHcIA#R0&Prime contractorOSCN IIA#RPlatformTcIJA#R&"Mass at launchSIXJA#R$ Mass in orbitOJJA#RDimensionQXJJA#R Solar arraySJKKA#R$ StabilizationN JKA#RDC power\KKKA#R6$Design lifetime3 yearsoGKdM( Will provide 1 and 2 meter resolution panchromatic, 4 m resolution multispectral imagery, and 8 m hyperspectral (Warfighter program) resolution. Swath width 8 km except for hyperspectral: 5 km.On board storage: 4 GBShould operate in the 8025-8400 MHz frequency band, TT&C communications would be in UHF-, S- and X-band. <KM' *O External resourcesO(dMM' Phttp://www.orbimage.com/worbview.htm1M N1W NtNNT+MtN) "VȠ$To view this page you need to register& NN# ?tNN1p<@N$O_Program: OrionKN$O5 :.I" Program: Orion/N_0 .ZxAmerican telecommunication program operated by Orion Networks This company was bought by Loral Space & Communications Ltd in late-1997 for approx $479 million. Other $O_Ncompanies are involved in Orion: Orion Atlantic L.P. and Orion Asia Pacific Corp.1$O1%F_%O n۴R*S*T*U*X*Program: OrionOrion 1Orion 2Orion 3Orion 4Orion 71V1Vc-%6 <\R*"Orion 1's EIRP (Broad beam to Europe)1Vꁞ1ꁞMc-M6 <\R*"Orion 1's EIRP (Spot beams to Europe)1ꁞ~1~݂_)M݂6 탞 COrion 1Hm탞8 @"I" Orion 11 '  Generalg 탞G#^@") Designation23413 / 94079A\ᄞA#R6Launch date29 Nov 1994t'UM#jN"N ,㹌לCountry of originUnited Stateso"ᄞąM#jD"H̀㓉MissionTelecommunicationsg U+G#^@"/ۀ0Geostationary orbit37.5Wq$ąM#jH" &yjLaunch vehicleAtlas CentaurhC+% The Centaur delivered Orion 1 into an unprecedented elliptical transfer orbit of 403 x 122762 km x 25.5. The orbit was then raised to 25010 km x 122766 km x 3.0. The apogee was then lowered until reaching GEO. The fuel-saving high apogee transfer technique had been used before, but never with such an extreme apogee.8<' "(OTechnical data=y' , EIRP coverage (dBW)V< > LίJ⒉Y=*{i(Broad beam to EuropeSpot beams to EuropeBroad beam to USSpot beams to US8yE' " Specificationsi( A#RP&Prime contractorMatra Marconi Space[E A#R4PlatformEurostar 2000[dA#R4"Mass at launch2350 kgX A#R.Payload mass375 kg`dA#R>Dimension1.7 x 1.6 x 2.1 mYuA#R0 Stabilization3 axisY΋A#R0DC powerEOL: 3200 Wf%u4A#RJ Payload power2500 W (in eclipse)]΋A#R8$Design lifetime12 yearsd@4$ Beacon frequency: 11.4505 GHz, LHCP (and 11.5410 GHz backup)1 &'  Ku-bandYA#R0(Main transponders34Y&؍A#R0,Backup transpondersO'A#RPower15 W@؍B#TBandwidth6 transponders of 36 MHz28 transponders of 54 MHzY'\Z#B⒉Y=ίJ(*{iCoverage3 spots and 1 zone beam to Europe4 spots and 1 zone beam to Americar0ΏB#T`EIRP maxSpot beam: 50 dBWZone beam: 45 dBWM \'A#RΏ'mG/T maxSΏzA#R$ SFD-90 dBW/m\'A#R6PolarizationLinear H/V&z# A=' 4 Transponder frequenciesb!A#RB Europe uplink14.0 - 14.5 GHzx7=žA#Rn$Europe downlink11.45 - 11.7 GHz & 12.5 - 12.75 GHze$|žA#RH&North Am. uplink14.0 - 14.5 GHzg&žžA#RL*North Am. downlink11.7 - 12.2 GHzK$|ž.Þ' H Transponder frequency chart (GHz)bžĞ#~nxjyyjj0NzĀHorizontal DownlinkTransponderVertical DownlinkBandwidth (MHz)Downlink BeamEuropean uplinkUS uplinkType@.ÞwŞ#nxjyyjj $8L`511.48354EU broad14.278 H14.278 Vtrans. or reg.GĞeƞ#nxjyyjj&:Nb11.4831454EU spots14.278 V14.278 Hnet., trans. or reg.5wŞAǞ#jnxjyyjj $8LV611.54654EU broad14.341 Hn/aregional<eƞ$Ȟ#xnxjyyjj&:DX11.5461554EU spotsn/a14.341 Htrans atlantic@AǞ ɞ#nxjyyjj $8L`711.60954EU broad14.404 H14.431 Vtrans. or reg.<$Ȟɞ#xnxjyyjj&:DX11.6091654EU spotsn/a14.404 Htrans atlantic; ɞʞ#vnxjyyjj $8BV811.67254EU broadn/a14.467 Vtrans atlantic<ɞ˞#xnxjyyjj&:DX11.6721754EU spotsn/a14.467 Htrans atlantic:ʞ̞#tnxjyyjj&:Nb11.7281854US broad14.028 H14.028 Vnetwork:˞u͞#tnxjyyjj&:Nb2611.72854US spots14.028 V14.028 Hnetwork:̞VΞ#tnxjyyjj&:Nb11.7911954US broad14.091 H14.091 Vnetwork:u͞7Ϟ#tnxjyyjj&:Nb2711.79154US spots14.091 V14.091 HnetworkAVΞ+#nxjyyjj&:Nb11.8542054US broad14.157Ϟ+m4 H14.154 Vtrans. or reg.A7Ϟ#nxjyyjj&:Nb2811.85436US spots14.145 V14.145 Htrans. or reg.=+#znxjyyjj&:PZ2911.88536US spots14.1855 Vn/atrans atlantic6#lnxjyyjj&:DX11.9172154US broadn/a14.217 VregionalA#nxjyyjj&:Nb3011.92636US spots14.226 V14.226 Htrans. or reg.A#nxjyyjj&:Nb11.9782254US broad14.278 H14.278 Vtrans. or reg.G#nxjyyjj&:Nb3111.97854US spots14.278 V14.278 Vnet., trans. or reg.6o#lnxjyyjj&:DX12.0412354US broadn/a14.341 Vregional<R#xnxjyyjj&:NX3212.04154US spots14.341 Vn/atrans atlanticAo:#nxjyyjj&:Nb12.1042454US broad14.404 H14.404 Vtrans. or reg.<R #xnxjyyjj&:NX3312.10454US spots14.404 Vn/atrans atlantic<: #xnxjyyjj&:NX12.1672554US broad14.467 Hn/atrans atlantic< #xnxjyyjj&:NX3412.16754US spots14.467 Vn/atrans atlantic9 #rnxjyyjj $8L`112.52854EU broad14.028 H14.028 Vnetwork8 #pnxjyyjj$8L^12.528954EU spots14.028 V14.028Hnetwork9 #rnxjyyjj $8L`212.59154EU broad14.091 H14.091 Vnetwork: c#tnxjyyjj&:Nb12.5911054EU spots14.091 V14.091 HnetworkA K#nxjyyjj&:Nb12.6451136EU spots14.145 V14.145 Htrans. or reg.@c>@#nxjyyjj $8L`312.654K>@m54EU broad14.154 H14.154 Vtrans. or reg.=K"A#znxjyyjj&:DZ12.6851236EU spotsn/a14.1855 Htrans atlantic5>@A#jnxjyyjj $8LV412.71754EU broad14.217 Hn/aregionalA"AB#nxjyyjj&:Nb12.7261336EU spots14.226 V14.226 Htrans. or reg.&A C# 1B=C1W=CCCT+ CC) "VȠ$To view this page you need to register&=CC# 8CC1=?C7DOrion 2HC7D8 @"I" Orion 21 ChD'  GeneralY7DDG#^$") DesignationUhDEA#R(Launch date1999t'DEM#jN"N ,㹌לCountry of originUnited Statesm#EEJ#dFOperatorOrion Atlantic L.P.o"EfFM#jD"H̀㓉MissionTelecommunicationse$EFA#RH,Geostationary orbit12W or 47WlfF7GM#j>" &yjLaunch vehicleAtlas 2AFH% U47W is the slot for which Orion got FCC's permission for Ka-band, so if the satellite carries Ka-band transponders it should be there, otherwise it should be at 12W87G>H' "(OTechnical data=H{H' , EIRP coverage (dBW)5 >HH) "MvKu-band8{HH' " SpecificationsYHAIA#R0&Prime contractorMMS\HIA#R6PlatformEurostar 2000+TAIIA#R&"Mass at launchUIFJA#R(Dry mass1380 kgOIJA#RDimensionYFJJA#R0 Stabilization3 axisYJGKA#R0DC powerEOL: 6200 W_JKA#R<$Design lifetime12.7 years&GKK# 1 KK'  Ku-bandYKVLA#R0(Main transponders30YKLA#R0,Backup transponderss1VL"MB#TbPower22 x 100 W (Europe)8 x 120 W (America)ULwMA#R(Bandwidth54 MHzo"M(NB#T,Coverage & EIRP maxEurope: 50 dBW, 22 transpondersAmerica: 48.5 dBW 8 transponders (both North and South)m+wMNB#TVG/T maxEurope: 1 dB/KAmericas: 0 dB/KR(NNA#R"PolarizationNOE#XYFrequenciesUplink Europe: 13.75-14.5 GHzUplink America: 14.0-14.5 GHzDownlink Europe: 10.950-11.200, 11.450-11.700, 12.500-12.750 GHzDownlink America: 11.7-12.2 GHzU1N9$ bTwO9Co 2.3 meter + a 1.1 meter diameter antennas1 Oj'  Ka-bandY9ÀA#R0(Main transponders24YjA#R0,Backup transpondersOÀkA#RPower60 WVA#R*Bandwidth114 MHz@kCB#TCoverage2 high-gain fixed spots2 high-gain steerable spotsN A#REIRP maxRCゟA#R"PolarizationMrB#TFrequenciesUplink: 28.35-28.6 and 29.25-30.0 GHzDownlink: 19.7-20.2 GHz&ゟ# 1rɃ1WɃCT+) "VȠ$To view this page you need to register&ɃC# 1t1tȄTCȄ6 <>S*"Orion 2's Ku-band EIRP1t1WMsT+ȄM) "VȠ$To view this page you need to register&s# 8M1> ?yɟOrion 3Hs8 @"I" Orion 31 $'  GeneralY}G#^$") Designationd#$ᆟA#RFLaunch dateplanned in Nov 1998t'}UM#jN"N ,㹌לCountry of originUnited Statesr(ᆟLJJ#dPOperatorOrion Asia Pacific Corp.o"U6M#jD"H̀㓉MissionTelecommunications^LJA#R:,Geostationary orbit139Ec6G#^8" &Launch vehicleDelta 3YPG#^$Launch siteJ& To be delivered in orbitOrion 3 will provide business communications services to users in all major Asia Pacific markets, including Korea, China, India, Japan, Australia, Southeast Asia, Oceana, and Hawaii. 8P' "(OTechnical data=J' , EIRP coverage (dBW)E0 0*YpTՉC-bandKu-band8<' " Specifications\A#R6&Prime contractorHughesW<A#R,PlatformHS 601 HPTCA#R&"Mass at launchUA#R(Dry mass1935 kgOC猟A#RDimensionQ8A#R Solar arrayY猟A#R0 Stabilization3 axisT8卟A#R&DC power6900 W]BA#R8$Design lifetime15 years&卟h# 0 B'  C-bandYhA#R0(Main transponders10YJA#R0,Backup transpondersOA#RPower55 WUJ A#R(Bandwidth36 MHz s^jA#R:CoverageAsean and HawaiiT A#R&EIRP max37 dBWTjA#R&G/T max-1 dB/K\nA#R6Polarizationlinear H/VAB#TFrequenciesUplink: 6.425 - 6.725 GHzDownlink: 3.4 - 3.7 GHz&nŸ# 1 HŸ'  Ku-bandYŸŸA#R0(Main transponders25YHŸŸA#R0,Backup transpondersXŸRßA#R.Power50, 80, 140 Wf$ŸßB#THBandwidth23 x 54 MHz2 x 27 MHz4RßğE#X,Coverage & EIRP maxNE Asia: 54 dBW, 8 transponders (horizontal)SE Asia: 51 dBW, 6 transponders (vertical, up to 9 when Oceana transponders switched)India: 54 dBW, 8 transponders (horizontal)Oceana: 45 dBW, 3 transponders (vertical)Sß?şA#R$G/T max2 dB/K\ğşA#R6Polarizationlinear H/VA?şƟB#TFrequenciesUplink: 14 - 14.5 GHzDownlink: 12.25 - 12.75 GHz&şDƟ# 3 ƟwƟ'  Ku-band 2XDƟƟA#R.(Main transponders8YwƟ(ǟA#R0,Backup transpondersK ƟsǟA#RPowerU(ǟǟA#R(Bandwidth36 MHzYsǟ!ȟA#R0,Coverage & EIRP maxSǟtȟA#R$G/T max2 dB/K\!ȟȟA#R6Polarizationlinear H/VAtȟSɟB#TFrequenciesUplink: 14 - 14.5 GHzDownlink: 12.25 - 12.75 GHz&ȟyɟ# 1Sɟɟ1Wɟɟ$ʟT+yɟɟ) "VȠ$To view this page you need to register&ɟ$ʟ# 1ɟUʟ1UʟʟS$ʟʟ6 <<T*"Orion 3's C-band EIRP1Uʟʟ1Wʟ-˟S˟T+ʟ-˟) "VȠ$To view this page you need to register&ʟS˟# 1-˟˟1˟˟TS˟˟6 <>T*"Orion 3's Ku-band EIRP1˟ ̟1W ̟]̟̟T+˟]̟) "VȠ$To view this page you need to register& ̟̟# 8]̟̟1?Ʉ?̟͟͟Orion 4H̟͟8 @"I" Orion 4j̟͟% For 1999 between 127W and 135Wtotal cost: $210 million3-axis stabilized, 16 transponders in Ku-band1͟͟1W͟Ο=ΟT+͟Ο) "VȠ$To view this page you need to register&͟=Ο# 8ΟuΟ1 ?uΟΟ Orion 7O=ΟΟ8 @0I" Orion 7, 8 & 91 uΟΟ'  GeneralYΟNϟG#^$") Designationf%ΟϟA#RJLaunch dateall 3 before May 2002t'Nϟ4M#jN"N ,㹌לϟ4=ΟCountry of originUnited Statesk$ϟG#^HOperatorOrion Network Systemso"4M#jD"H̀‰MissionTelecommunicationsj)xA#RR,Geostationary orbit89W, 81W & 78W\G#^*" &Launch vehicleYx-G#^$Launch siteh% The project is evaluated at $757 millionA fourth Ka-band satelltie for 127W is under consideration8-' "(OTechnical data8*' " SpecificationsVA#R*&Prime contractorN *A#RPlatformT"A#R&"Mass at launchSuA#R$ Mass in orbitO"A#RDimensionQuA#R Solar arrayShA#R$ StabilizationN A#RDC powerUh A#R($Design lifetime&1# 1 b'  Ka-bandY1A#R0(Main transponders32YbA#R0,Backup transpondersOcA#RPower60 WOA#RBandwidthq0c#A#R`Coverage25 fixed and 2 steerable spot beamsN qA#REIRP maxR#A#R"Polarization`qe B#TFrequenciesUplink: 28.35-28.6 and 29.25-30.0 GHz (in FDMA)Downlink: 19.7-20.2 GHz (in TDM)& # 1e 1W  6 T+  ) "VȠ$To view this page you need to register& 6 # ? u 1څ<QCu Program: OscarO6 8 @0R" Program: Oscar-u )  Orbiting Satellite Carrying Amateur RadioHAM radio satellite program. Oscar is a generical name for numerous satellites, they are often identified as #O-xx where # is the initial of an organization and xx the number of the satellite in the Oscar program.< - ' * External resources\5 ' jhttp://www.amsat.org/amsat/sats/n7hpr/satsum.html1- 1U D'D< ) "&䵟Program: Oscar7 s#n((u(FUOOscar 01AO-10: Oscar 10FO-20: Fuji 1B6 @j#l("ΓF̀Bn!Oscar 02UO-11: Uosat 2AO-21: Informator6 s#l((TO(DѓF̀Oscar 03FO-12: Fuji 1AUO-22: Uosat 53@d#f"n쉂@Oscar 04AO-13: Oscar 13KO-23: Kitsat AB>@p#((ϓF̀"D:Oscar 05>@ UO-14: Uosat 3#24 was reserved for Arsne>@s#|((*ГF̀(RAO-06: Oscar 06UO-15: Uosat 4KO-25: Kitsat B7>@Ad#n"(JKAO-07: Oscar 07AO-16: PacsatIO-26: Itamsat9@6Bs#r((*eOU(L|{3AO-08: Oscar 08DO-17: DoveAO-27: Eyesat5ABs#j(p#؀( .(FVPhase 3AWO-18: WebersatPO-28: Posat46BvCd#h"͓F̀& UFJ ;UO-09: Uosat 1LO-19: LusatFO-29: Fuji 2&BDg#L(- (,zHMO-30: Unamsat 2Phase 3D$vC'D" 9D`D1 @`DDIOscar 01I'DD8 @$R" Oscar 011 `DD'  Generalg DAEG#^@") Designation00214 / 61034B\DEA#R6Launch date12 Dec 1961t'AEFM#jN"N ,㹌לCountry of originUnited Stateso"EFM#jD"H̀㓉MissionTelecommunications^FFA#R:"Perigee/Apogee245/474 kmVF4GA#R*Inclination81.2TFGA#R&Period91.8 minp#4GGM#jF" &#*≂Launch vehicleThor Agena B[GSHA#R4Launch siteVandenbergZGHA#R2"Mass at launch4.5 kg&SHH# 5HI'  End of lifeVH^IA#R*Decay31 Jan 1962$II" 9^II1?@@IJNOscar 02IIJ8 @$R" Oscar 021 I5J'  Generalg JJG#^@") Designation00305 / 62022B[5JJA#R4Launch date2 Jun 1962t'JkKM#jN"N ,㹌לCountry of originUnited Stateso"JKM#jD"H̀㓉MissionTelecommunications^kK8LA#R:"Perigee/Apogee188/339 kmVKLA#R*Inclination74.2T8LLA#R&Period89.8 minp#LRMM#jF" &#*≂Launch vehicleThor Agena B[LMA#R4Launch siteVandenberg&RMM# 5MN'  End of lifeVM^NA#R*Decay21 Jun 1962$NN" 9^NN1@WANOOscar 03INO8 @$R" Oscar 031 N5O'  Generalg OOG#^@") Designation01293 / 65016F[5O A#R4Launch date9 Mar 1965O Nt'OM#jN"N ,㹌לCountry of originUnited Stateso" M#jD"H̀㓉MissionTelecommunications^MA#R:"Perigee/Apogee874/902 kmVA#R*Inclination70.1UMA#R(Period102.7 minp#hM#jF" &#*≂Launch vehicleThor Agena D[ÂA#R4Launch siteVandenbergh% qFirst Amateur satellite with solar power. First transponder. Transponder operational life 18 days (battery-limited). The 2 beacons operated for several months from the solar cells.8Â؃' "(OTechnical data8' " SpecificationsY؃iA#R0"Mass at launch18 kgWA#R, Stabilizationnonei(i)A#RPDC power2.5 W: solar cells; battery[$ Transponder: 1W, 50kHz bandwidth, 146 MHz uplink, 144 MHz downlink (linear translator).9)ᅠ1Z@Aᅠ*SOscar 04I*8 @$R" Oscar 041 ᅠ['  Generalg *†G#^@") Designation01902 / 65108C\[A#R6Launch date21 Dec 1965t'†M#jN"N ,㹌לCountry of originUnited Stateso"M#jD"H̀㓉MissionTelecommunications`aA#R>"Perigee/Apogee162/33549 kmVA#R*Inclination26.8Ua A#R(Period587.5 minn!zM#jB" &^]Launch vehicleTitan 3 #7& # 5zՉ'  End of lifeV+A#R*Decay12 Apr 1976eՉ$ Built by TRW radio club. Intended on a high altitude but the launch vehicle had a partial failure8+슠' "(OTechnical data8$' " SpecificationsN슠A#R StabilizationSpin generated by a spring on separation from launch vehicle[$A#R4DC power10 W, batteryE!S$ BBeacon: 432 MHz. No telemetry91WAFAՌ Oscar 05ISՌ8 @$R" Oscar 05;# 0Also called Australis1 ՌA'  Generalg G#^@") Designation04321 / 70008B\AA#R6Launch date23 Jan 1970p#tM#jF"N ,Country of originAustraliao"㎠M#jD"H̀㓉MissionTelecommunications`tCA#R>"Perigee/Apogee1431/1475 kmW㎠A#R,Inclination101.4SC A#R$Period115 min S\hG#^*" &Launch vehicle[ A#R4Launch siteVandenbergh% Built at University of Melbourne, Australia. Launched with Tiros weather satellite. Command receiver (on 2m) and hardwired decoder (first remote control of an amateur satellite). Operational life: 46 days.8' "(OTechnical data8) ' " Specificationsc" A#RD StabilizationPassive magnetic$)  " 9  1A=A 2àʠOscar 06I 2à8 @$R" Oscar 06C  uà# @Also called AO-06 or Phase 2A1 2àà'  Generalg uà ĠG#^@") Designation06236 / 72082B\àiĠA#R6Launch date15 Oct 1972t' ĠĠM#jN"N ,㹌לCountry of originUnited Stateso"iĠLŠM#jD"H̀㓉MissionTelecommunications`ĠŠA#R>"Perigee/Apogee1446/1452 kmULŠƠA#R(Inclination102UŠVƠA#R(Period114.9 min\ƠƠG#^*" &Launch vehicle[VƠ ǠA#R4Launch siteVandenbergƠ,Ƞ+ $쉂First complex control system (discrete logic). First satellite-satellite communication (via Oscar 07). Demonstrated Doppler-location of ground stations for search and rescue. Demonstrated low-cost medical data relay from remote locations.5 ǠaȠ'  End of life_,ȠȠA#R<"Out of service21 Jun 1977ZaȠɠA#R2CauseBattery failure&Ƞ@ɠ# 8ɠxɠ' "(OTechnical data8@ɠɠ' " Specificationsc"xɠʠA#RD StabilizationPassive magneticb!ɠuʠA#RBDC power5.5 W (NiCd battery)D ʠʠ$ @1 W downlink, 435 MHz beacon9uʠʠ1FABʠ<ˠOscar 07Jʠ<ˠ8 @&R" Oscar 077ʠsˠ# (Also called AO-071 <ˠˠ'  Generalg sˠ ̠G#^@") Designation07530 / 74089B\ˠg̠A#R6Launch date15 Nov 1974t' ̠̠M#jN"N ,㹌לCountry of originUnited Stateso"g̠J͠M#jD"H̀㓉MissionTelecommunications`̠͠A#R>"Perigee/Apogee1438/1456 kmWJ͠ΠA#R,Inclination101.9U͠VΠA#R(Period114.8 mins&ΠΠM#jL" &p㉂Launch vehicleThor Delta #104VΠϠ% MEarly demonstrations of low-budget medical data relay and doppler location of ground transmitters for search-and-rescue operations were done using this satellite.5ΠϠ'  End of lifeXϠ-A#R.Ϡ-ʠ"Out of service1980ZϠA#R2CauseBattery failure&-# 8' "(OTechnical data8' " Specificationsc"A#RD StabilizationPassive magnetica A#R@DC power15 W (NiCd battery)$" 9>1=AB>H Oscar 08I8 @$R" Oscar 08C ># @Also called AO-08 or Phase 2D1 '  Generalg bG#^@") Designation10703 / 78026B[A#R4Launch date5 Mar 1978t'b1M#jN"N ,㹌לCountry of originUnited Stateso"M#jD"H̀㓉MissionTelecommunications^1A#R:"Perigee/Apogee893/903 kmVTA#R*Inclination99.2SA#R$Period103 mins&TM#jL" &p㉂Launch vehicleThor Delta #139&@# 5u'  End of life_@A#R<"Out of service24 Jun 1983Zu.A#R2CauseBattery failure&T# 8.' "(OTechnical data8T' " Specifications[A#R4"Mass at launch25.8 kgc"A#RD StabilizationPassive magnetica A#R@DC power15 W (NiCd battery)eAH $ Beacons: 29.402 MHz 110mW, 435.095 MHz 100 mW, both Morse CW.9 1B2B G Phase 3AIH 8 @$R" Phase 3A5 '  End of life_ ^ A#R<"Out of service23 May 1980o( G#^P&+CauseLaunch failure of Ariane L02V^ # A#R*Decay23 May 1980$ G " 9# 1 BB BGOscar 10IG 8 @$R" Oscar 10C # @Also called AO-10 or Phase 3B1 = '  Generalg G#^@") Designation14129 / 83058B\= A#R6Launch date16 Jun 1983n! n M#jB"N , Country of originGermanyo" M#jD"H̀㓉MissionTelecommunicationsa n >A#R@"Perigee/Apogee4007/35442 kmV A#R*Inclination27.2U>A#R(Period699.5 minn!WM#jB" &*+Launch vehicleAriane L06ZA#R2"Mass at launch155 kgWA% First amateur satellite with onboard proAG pulsion. The booster bumped Oscar 10 shortly after separation which damaged one or more of its antennas and also caused other internal injuries because the second and subsequent kick motor firings never happended. This left the spacecraft in a lower inclination elliptical orbit. This meant that the bird didn't have the intended operational coverage nor enough solar panel illumination to sustain full operations.8A' "(OTechnical data8AB' " SpecificationsVArBA#R*&Prime contractorN BBA#RPlatformTrBCA#R&"Mass at launchSBgCA#R$ Mass in orbitOCCA#RDimensionQgCDA#R Solar array_CfDA#R< StabilizationMagnetorquere$DDA#RHDC power50 W (2 NiCd batteries)UfD EA#R($Design lifetime&DFE# u4 EEA#Rh0"General beacon145.809 MHz (unmodulated carrier)r1FE-FA#Rb0*Engineering beacon145.987 MHz (switched off)r1EFA#Rb0 Mode B uplink435.030 - 435.180 MHz (SSB, CW)>-FGA#R|0$Mode B downlink145.825 - 145.975 MHz (SSB, CW, inverting)$FBG" 9G{G12B{GGzOscar 13IBGG8 @$R" Oscar 13C {GH# @Also called AO-13 or Phase 3C1 G8H'  Generalg HHG#^@") Designation19216 / 88051B\8HHA#R6Launch date15 Jun 1988t'HoIM#jN"N ,㹌לCountry of originUnited Stateso"HIM#jD"H̀㓉MissionTelecommunications`oI>JA#R>"Perigee/Apogee809/37995 kmVIJA#R*Inclination57.9U>JJA#R(Period686.6 minn!JWKM#jB" & D+Launch vehicleAriane V23]JL% Much improved brother to Oscar 10: it has the ability to automatically select transponders for each mode at different points in its orbit. However problems occured: it had a RUDAK experiment onboard that failed shortly after launch. Also, in June 1993, the 70 cm downlink transmitter ceased to function, putting an end to Mode J and L operation.5WKM'  End of lifeULcMA#R(Decay6 Dec 1996&MM# 8cMM' "(OTechnical data8MM' " SpecificationsVMONA#R*&Prime contractorN MNA#RPlatformZONNA#R2"Mass at launch140 kgXNOOA#R. Mass in orbit90 kgONOA#RDimensionQOO A#R Solar arrayO BG_OkA#R< StabilizationMagnetorquera ̀A#R@DC power50 W (NiCd battery)Uk!A#R($Design lifetimekF̀% Payload power: 145 MHz - 50 W; 435 MHz - 111 W; 2350 MHz - 1.25 Wo.!A#R\0"general beacon145.812 mhz (psk, cw, rtty)s2nA#Rd0*engineering beacon145.985 mhz (psk, cw, rtty)r1A#Rb0 mode b uplink435.423 - 435.573 mhz (ssb, cw)>n_A#R|0$mode b downlink145.825 - 145.975 mhz (ssb, cw, inverting)k*ʃA#RT0"general beacon435.651 mhz (psk, rtty)o._9A#R\0*engineering beacon435.677 mhz (psk, rtty)t3ʃA#Rf0 mode l uplink1269.351 - 1269.641 mhz (ssb, cw)?9-A#R~0$mode l downlink435.715 - 436.005 mhz (ssb, cw, inverting)r1A#Rb0 mode j uplink144.423 - 144.473 mhz (ssb, cw)>-A#R|0$mode j downlink435.940 - 435.990 mhz (ssb, cw, inverting)d#A#RF0beacon2400.325 mhz (psk, rtty)d#憡A#RF0beacon2400.664 mhz (psk, rtty)w6]A#Rl0 mode s uplink435.603 - 435.639 mhz (ssb, cw, fm)z9憡ׇA#Rr0$mode s downlink2400.711 - 2400.747 mhz (ssb, cw, fm)l+]CA#RV0rudak uplink1269.710 mhz (inoperative)m,ׇA#RX0"rudak downlink435.677 mhz (inoperative)Cz% KThe beacon output alternates between CW, 50 baud RTTY and 400 bps PSK. Beacon transmissions contain satellite engineering data and bulletins from ground control.= 1@DlProgram: OSOMz8 @,N d%" Program: OSOh@l( Orbiting Solar ObservatoryAmerican Sun observation program11~vl~k OSO 4Fˡ̡8 @N d%" OSO 41 ˡ3̡'  Generalg ̡̡G#^@") Designation03000 / 67100A\3̡̡A#R6Launch date18 Oct 1967t'̡j͡M#jN"N ,㹌לCountry of originUnited Statesx+̡͡M#jV"H̀jMissionScientific: Sun observation^j͡@ΡA#R:"Perigee/Apogee552/555 kmV͡ΡA#R*Inclination32.9T@ΡΡA#R&Period95.7 minr%Ρ\ϡM#jJ" &p㉂Launch vehicleThor Delta #53&Ρϡ# 5\ϡϡ'  End of life\ϡA#R6"Out of ϡˡserviceDec 1971VϡuA#R*Decay15 Jun 1982&# <u' *O External resourcesg@>' http://heasarc.gsfc.nasa.gov/docs/heasarc/missions/oso4.html6t1^ICDtOSO 5F>8 @N d%" OSO 51 t'  Generalg RG#^@") Designation03663 / 69006A\A#R6Launch date22 Jan 1969t'R"M#jN"N ,㹌לCountry of originUnited Statesx+M#jV"H̀jMissionScientific: Sun observation^"A#R:"Perigee/Apogee538/559 kmTLA#R&Inclination33TA#R&Period95.6 minr%LM#jJ" &p㉂Launch vehicleThor Delta #64&8# 5m'  End of life\8A#R6"Out of serviceJul 1975UmA#R(Decay2 Apr 1984&D# <' *O External resourcesg@D' http://heasarc.gsfc.nasa.gov/docs/heasarc/missions/oso5.html61_mDDc OSO 6Fc8 @N d%" OSO 61 '  Generalg cG#^@") Designation04065 / 69068A[VA#R4Launch date9 Aug 1969t'M#jN"N ,㹌לCountry of originUnited Statesx+VB M#jV"H̀jMissionScientific: Sun observation^ A#R:"Perigee/Apogee489/554 kmVB A#R*Inclination32.9T J A#R&Period95.1 minr% M#jJ" &p㉂Launch vehicleThor Delta #72&J # 5  '  End of life\ s A#R6"Out of serviceJan 1972U A#R(Decay7 Mar 1981&s # < * ' *O External resourcesg@ ' http://heasarc.gsfc.nasa.gov/docs/heasarc/missions/oso6.html6* 1aDD SBOSO 7F 8 @N d%" OSO 71 > '  Generalg G#^@") Designation05491 / 71083A\> A#R6Launch date29 Sep 1971t' uM#jN"N ,㹌לCountry of originUnited Statesx+M#jV"H̀jMissionScientific: Sun observation^uKA#R:"Perigee/Apogee326/572 kmVA#R*Inclination33.1TK @A#R&Period93.5 min @ r%~@M#jJ" &p㉂Launch vehicleThor Delta #85& @@# 5~@@'  End of life\@5AA#R6"Out of serviceJul 1974U@AA#R(Decay9 Jul 1974&5AA# <AA' *O External resourcesg@ASB' http://heasarc.gsfc.nasa.gov/docs/heasarc/missions/oso7.html6AB1DBBZHOSO 8FSBB8 @N d%" OSO 81 BC'  Generalg BgCG#^@") Designation07970 / 75057A\CCA#R6Launch date21 Jun 1975t'gC7DM#jN"N ,㹌לCountry of originUnited Statesx+CDM#jV"H̀jMissionScientific: Sun observation^7D EA#R:"Perigee/Apogee539/553 kmVDcEA#R*Inclination32.9T EEA#R&Period95.6 mins&cE*FM#jL" &p㉂Launch vehicleThor Delta #112[EFA#R4"Mass at launch1064 kg&*FF# 5FF'  End of life\F0Dimension2.4 x 2.1 x 1.7 m['LLA#R40Solar array9.3 m spanYL;MA#R00 Stabilization3 axisd"LMB#TD0DC powerBOL: 750 WEOL: 555 W\;MMA#R60$Design lifetime3 yearsXMSNA#R.0"Phone circuits6000$MwN" 1SNN1UNуG$wNN# HOTS' Ku-band (downlink in 11 GHz)2 N!O'  Module AXNyOA#R.0(Main transponders4Y!OOA#R00,Backup transpondersOyO-A#R0O-wNPower20 Wh&OB#TL0Bandwidth2 of 40 MHz2 of 120 MHzy7-B#Tn0Coverage40 MHz: European beam A120 MHz: spot beam\jA#R60Polarizationlinear H/V&# 2 j'  Module BXA#R.0(Main transponders2YsA#R00,Backup transpondersO‚A#R0Power20 WTsA#R&0Bandwidth5 MHz]‚sA#R80CoverageEuropean beam B^уA#R:0Polarizationcircular L/R$s" 6у+1E+q5OTS 1Fq8 @} d%" OTS 15+'  End of lifen-qA#RZ"Out of service13 Sep 1977 (Friday 13th!)v/G#^^p㉂CauseLaunch failure of a Thor Delta #134&# 8腢' "(Technical dataM50 0:8ӉSpecificationsKu-band6腢k13EkOTS 2F58 @} d%" OTS 21 k↢'  Generalg IG#^@") Designation10855 / 78044A\↢A#R6Launch date11 May 1978m IM#j@"N ,4"Country of originEuropeo"M#jD"H̀‰MissionTelecommunications]ވA#R8,Geostationary orbit10Es&QM#jL" &p㉂Launch vehicleThor Delta #141&ވw# 5Q'  End of life\wA#R6"Out of serviceJan 1991&.# 8f' "(Technical dataM.0 0:8ӉSpecificationsKu-band< f1DH;Program: OVL;8 @*" Program: OV+ $S Orbiting VehicleAmerican programEach OV1 payload had its own propulsion module. Some OV1 missions carried also a suborbital payload (FIRE 1 & 2, ABRES 6, SSP 29)1;@1@ȍȍ @QdIoZ0qZ0rZ0uZ0vZ0Z0Z0Z0Z0Z0   0123"""Program: OVOV 1-02OV 1-04OV 1-05OV 1-08OV 1-09OV 1-10OV 1-13OV 1-14OV 1-19OV 1-21OV 2-1OV 2-3OV 2-5OV 3-1OV 3-2OV 3-3OV 3-4OV 5-5OV 5-6OV 5-98@1EHOV 1-02HȍH8 @"" OV 1-021 y'  Generalg HG#^@") Designation01613 / 65078A[y;A#R4Launch date5 Oct 1965t'M#jN"N ,㹌לCountry of originUnited StatesU;G#^"H̀Missionȍ_oA#R<"Perigee/Apogee406/2731 kmWA#R,Inclination144.2UoA#R(Period117.5 minc~G#^8" &Launch vehicleAtlas D[A#R4Launch siteVandenberg$~" 85¢1}EE5¢}¢%ƢOV 1-04H}¢8 @"" OV 1-041 5¢¢'  Generalg }¢âG#^@") Designation02121 / 66025A\¢qâA#R6Launch date30 Mar 1966t'ââM#jN"N ,㹌לCountry of originUnited StatesUqâ:ĢG#^"H̀Mission_âĢA#R<"Perigee/Apogee884/1008 kmW:ĢĢA#R,Inclination144.5SĢCŢA#R$Period104 mincĢŢG#^8" &Launch vehicleAtlas D[CŢƢA#R4Launch siteVandenberg$Ţ%Ƣ" 8Ƣ]Ƣ1EE]ƢƢOʢOV 1-05H%ƢƢ8 @"" OV 1-051 ]ƢƢ'  Generalg Ƣ=ǢG#^@") Designation02122 / 66025B\ƢǢA#R6Launch date30 Mar 1966t'=Ǣ ȢM#jN"N ,㹌לCountry of originUnited StatesUǢbȢG#^"H̀Mission_ ȢȢA#R<"Perigee/Apogee985/1055 kmWbȢɢA#R,Inclination144.6UȢmɢA#R(Period105.6 mincɢɢG#^8" &Launch vehicleAtlas D[mɢ+ʢA#R4Launch siteVandenberg$ɢOʢ" 8+ʢʢ1EăEʢʢ)ϢOV 1-08HOʢʢ8 @"" OV 1-081 ʢˢ'  Generalg ʢgˢG#^@") Designation02324 / 66063A\ˢˢA#R6Launch date14 Jul 1966t'gˢ7̢M#jN"N ,㹌לCountry of originUnited StatesUˢ̢G#^"H̀Mission_7̢̢A#R<"Perigee/Apogee985/1022 kmW̢B͢A#R,Inclination144.2U̢͢A#R(Period105.2 mincB͢͢G#^8" &Launch vehicleAtlas D[͢U΢A#R4Launch siteVandenberg&͢{΢# 5U΢΢'  End of lifeU{΢ϢA#R(Decay4 Jan 1978$΢)Ϣ" 8ϢaϢ1EFaϢϢ^OV 1-09H)ϢϢ8 @"" OV 1-091 aϢϢ'  Generalg ϢMG#^@"ϢM)Ϣ) Designation02610 / 66111A\ϢA#R6Launch date11 Dec 1966t'MM#jN"N ,㹌לCountry of originUnited StatesUrG#^"H̀Mission_A#R<"Perigee/Apogee471/4626 kmVr'A#R*Inclination99.1U|A#R(Period139.9 minc'G#^8" &Launch vehicleAtlas D[|:A#R4Launch siteVandenberg$^" 8:1ăEFOV 1-10H^8 @"" OV 1-101 '  Generalg vG#^@") Designation02611 / 66111B\A#R6Launch date11 Dec 1966t'vFM#jN"N ,㹌לCountry of originUnited StatesUG#^"H̀Mission^FA#R:"Perigee/Apogee538/604 kmVOA#R*Inclination93.4TA#R&Period96.1 mincOG#^8" &Launch vehicleAtlas D[aA#R4Launch siteVandenberg$" 8a1FF OV 1-13H8 @"" OV 1-131 6'  Generalg G#^@") Designation03173 / 68026A[6A#R4Launch date6 Apr 1968t'l M#jN"N ,㹌לCountry of originUnited StatesU G#^"H̀Mission_l A#R<"Perigee/Apogee564/9241 kmV v A#R*Inclination99.9U A#R(Period198.7 mincv . G#^8" &Launch vehicleAtlas F[ A#R4Launch siteVandenberg$. " 8 1FF - @OV 1-14H - 8 @"" OV 1-141 ^ '  Generalg - G#^@") Designation03174 / 68026B[^ A#R4Launch date6 Apr 1968t' M#jN"N ,㹌לCountry of originUnited StatesU G#^"H̀Mission_ HA#R<"Perigee/Apogee540/9892 kmU A#R(Inclination100UHA#R(Period207.1 mincUG#^8" &Launch vehicleAtlas F[A#R4Launch siteVandenberg$U @"  @ 8D@1F FD@@6DOV 1-19H @@8 @"" OV 1-191 D@@'  Generalg @$AG#^@") Designation03825 / 69025C\@AA#R6Launch date18 Mar 1969t'$AAM#jN"N ,㹌לCountry of originUnited StatesUAIBG#^"H̀Mission_ABA#R<"Perigee/Apogee482/5583 kmWIBBA#R,Inclination104.8UBTCA#R(Period151.4 mincBCG#^8" &Launch vehicleAtlas F[TCDA#R4Launch siteVandenberg$C6D" 8DnD1FFnDD]HOV 1-21H6DD8 @"" OV 1-211 nDD'  Generalg DNEG#^@") Designation05397 / 71067B[DEA#R4Launch date7 Aug 1971t'NEFM#jN"N ,㹌לCountry of originUnited StatesUErFG#^"H̀Mission^FFA#R:"Perigee/Apogee774/899 kmVrF&GA#R*Inclination87.6UF{GA#R(Period101.7 minc&GGG#^8" &Launch vehicleAtlas F[{G9HA#R4Launch siteVandenberg$G]H" 79HH1p F?FHHMOV 2-1G]HH8 @ " OV 2-17HI# (Also called LCS 21 HCI'  Generalg IIG#^@") Designation01624 / 65082A\CIJA#R6Launch date15 Oct 1965t'IzJM#jN"N ,㹌לCountry of originUnited StatesUJJG#^"H̀Mission^zJ-KA#R:"Perigee/Apogee708/791 kmVJKA#R*Inclination32.6T-KKA#R&Period99.8 minn!KELM#jB" &^]Launch vehicleTitan 3 #6&KkL# 5ELL'  End of lifeVkLLA#R*Decay27 Jul 1972$LM" 7LQM1@F]GQMMOV 2-3GMM8 @ " OV 2-31 QMM'  Generalg M0NG#^@") Designation01863 / 65108A\MNA#R6Launch date21 Dec 1965t'0NOM#jN"N ,㹌לCountry of originUnited StatesUNUOG#^"H̀Mission`OOA#R>"Perigee/Apogee167/33662 kmVUOA#R*InclinatiOMon26.4UOlA#R(Period589.3 minn!ڀM#jB" &^]Launch vehicleTitan 3 #7&l# 5ڀ5'  End of lifeVA#R*Decay17 Aug 1975$5" 7恣1?FJG恣-OV 2-5G-8 @ " OV 2-51 恣^'  Generalg -łG#^@") Designation03428 / 68081A\^!A#R6Launch date26 Sep 1968t'łM#jN"N ,㹌לCountry of originUnited StatesU!ꃣG#^"H̀MissionYCA#R0,Geostationary orbito"ꃣM#jD" &^]Launch vehicleTitan 3 #31&C؄# 5 '  End of lifeW؄dA#R,"Out of serviceyes$ " 7d1]G=G^OV 3-1G8 @ " OV 3-11 7'  Generalg G#^@") Designation02150 / 66034A\7A#R6Launch date22 Apr 1966t'nM#jN"N ,㹌לCountry of originUnited StatesUÇG#^"H̀Mission_n"A#R<"Perigee/Apogee339/4068 kmVÇxA#R*Inclination82.4U"͈A#R(Period131.9 minm x:M#j@" &g'KLaunch vehicleScout #44$͈^" 7:1:JGVG܉卣OV 3-2G^܉8 @ " OV 3-21 '  Generalg ܉tG#^@") Designation02517 / 66097A\ ЊA#R6Launch date28 Oct 1966t'tDM#jN"N ,㹌לCountry of originUnited StatesUЊG#^"H̀Mission_DA#R<"Perigee/Apogee319/1599 kmVNA#R*Inclination81.9UA#R(Period104.2 minm NM#j@" &g'KLaunch vehicleScout #49&6# 5k'  End of lifeV6A#R*Decay29 Sep 1971$k卣" 71=GiGcOV 3-3G卣c8 @ " OV 3-31 '  Generalg cG#^@") Designation02389 / 66070A[VA#R4Launch date4 Aug 1966t'ʏM#jN"N ,㹌לCountry of originUnited StatesUV+G#^"H̀ʏ+卣Mission_ʏA#R<"Perigee/Apogee348/3132 kmV+A#R*Inclination81.4U5A#R(Period121.3 minm M#j@" &g'KLaunch vehicleScout #47$5" 71VG[GD£ţOV 3-4GD£8 @ " OV 3-41 u£'  Generalg D££G#^@") Designation02201 / 66052A[u£7ãA#R4Launch date9 Jun 1966t'£ãM#jN"N ,㹌לCountry of originUnited StatesU7ãģG#^"H̀Mission_ã_ģA#R<"Perigee/Apogee643/4704 kmVģģA#R*Inclination40.9U_ģ ţA#R(Period142.9 minm ģwţM#j@" &g'KLaunch vehicleScout #44$ ţţ" 7wţţ1iGcGţƣɣOV 5-5Gţƣ8 @ " OV 5-51 ţJƣ'  Generalg ƣƣG#^@") Designation03950 / 69046A\Jƣ ǣA#R6Launch date23 May 1969t'ƣǣM#jN"N ,㹌לCountry of originUnited StatesU ǣǣG#^"H̀Missionb!ǣ8ȣA#RB"Perigee/Apogee59630/69130 kmTǣȣA#R&Inclination33V8ȣȣA#R*Period3121.9 min\ȣ>ɣG#^*" &Launch vehicle_ȣɣA#R<Launch siteCape Canaveral$>ɣɣ" 7ɣɣ1S[GGɣ?ʣaΣOV 5-6Gɣ?ʣ8 @ " OV 5-61 ɣpʣ'  Generalg ?ʣʣG#^@") Designation03951 / 69046B\pʣ3ˣA#R6Launch date23 May 1969t'ʣˣM#jN"N ,㹌לCountry of originUnited StatesU3ˣˣG#^"H̀Missionb!ˣ^̣A#RB"Perigee/Apogee59540/69022 kmVˣ̣A#R*Inclination33.6V^̣ ͣA#R*Period3115.4 min\̣fͣG#^*" &Launch vehicle_ ͣͣA#R<Launch siteCape Canaveral&fͣͣ# 8ͣ#Σ' "(OTechnical data>ͣaΣ# 6Transmits on 136.380 MHz7#ΣΣ1cGΣΣOV 5-9GaΣΣ8 @ " OV 5-91 Σϣ'  Generalg ΣwϣG#^@") Designation03952 / 69046C\ϣϣA#R6Launch date23 May 1969t'wϣSM#jN"ϣSaΣN ,㹌לCountry of originUnited StatesUϣG#^"H̀Missionb!S A#RB"Perigee/Apogee59543/69011 kmV`A#R*Inclination33.5V A#R*Period3115.1 min\`G#^*" &Launch vehicle_qA#R<Launch siteCape Canaveral$" ; q1 EH YQuick Bird; , ( " Quick Bird1 <'  GeneralY G#^$") DesignationZ<A#R2Launch datelate 1998t'cM#jN"N ,㹌לCountry of originUnited StatesUG#^"H̀Missionk*c#A#RT"Perigee/Apogee600 km, sun-synchronousTwA#R&Inclination52L #A#RPeriodlw/M#j>" &s,梉Launch vehicleCosmos CQA#R Launch siteW/* $IUS satellite operated by Earth Watch Inc. The cost of the systems is $200 million<=' *O External resourcesS,' Xhttp://www.ball.com/aerospace/qbird.html8=' "(OTechnical data8' " Specificationsd#dA#RF0&Prime contractorBall aerospaceN A#R0PlatformZd A#R20"Mass at launch900 kgXd A#R.0Payload mass300 kgO A#R0DimensionQd  A#R 0Solar arrayS W A#R$0 StabilizationS A#R$0DC power350 W\W  A#R60$Design lifetime5 years}Y $ Body-pointed spacecraft with 30 fore-and-aft, and side-to-side pointing capability= ' , Panchromatic SensorY  A#R00Wavebands450-900 nmq0 A#R`0Resolution0.82 m, image size: 22 km x 22 km& # > ' . Multispectral SensorT D#X0WavebandsBlue: 450-520 nmGreen: 520-600 nmRed: 630-690 nmNear IR: 760-900 nmq0 A#R`0Resolution3.28 m, image size: 22 km x 22 kmb: Y( uCamera provided by KodakOn-board data storage: 137 GigabitsThe uplink and downlink receivers both use NSA-approved encryption/decryption, with an emergency time-out on the uplink decryptor to allow unencrypted access in case of a system failure. Uplink: S-band (2 kbps), Downlink: X-band (4, 16 or 256 kbps)1 1W@T+Y) "VȠ$To view this page you need to register&@# @Y: J@1 HpHJ@@UIQuickscat:@@, (" Quickscat8J@@# *Quick Scattermeter1 @@'  GeneralY@FAG#^$") Designationa @AA#R@Launch dateplanned Nov 1998t'FABM#jN"N ,㹌לCountry of originUnited StatesUApBG#^"H̀Missionj)BBA#RR"Perigee/Apogee803 km sun-synchronous\pB6CA#R6Inclinationnear-polar L BCA#RPeriodf6CCG#^>" &Launch vehicleTitan 23G?QC9DA#R Launch sitepDCD, (isWorth $32 millionTo replace the NSCAT payload aboard Adeos 189DD' "(OTechnical data8DE' " Specificationsd#D}EA#RF&Prime contractorBall AerospaceVEEA#R*PlatformBCP 2000Z}E-FA#R2"Mass at launch870 kgXEFA#R.Payload mass220 kgO-FFA#RDimensionQF%GA#R Solar arraySFxGA#R$ StabilizationS%GGA#R$DC power300 W\xG'HA#R6$Design lifetime2 years.GUI* " The payload is provided by JPL. Pointing accuracy: <0.3S-band telemetry and commanddata downlink in S-band at 2 Mbps8 Gbit solid-state recorderBall will provide launch support and mission control and operations for a two-year period following launch.1'HI1WIIJT+UII) "VȠ$To view this page you need to register&IJ# 7I7J1HhI7JvJPacsat? JvJ2 4"  PacsatY07JJ) "`䵟Also called Microsat 1 or AO-16 or Oscar 161 vJK'  Generalg JgKG#^@") Designation20439 / 90005D\KKA#R6Launch date22 Jan 1990t'gK7LM#jN"N ,㹌לCountry of originUnited Stateso"KLM#jD"H̀㓉MissionTelecommunications^7LMA#R:"Perigee/Apogee781/797 kmVLZMA#R*Inclination98.6UMMA#R(Period100.6 minn!ZMNM#jB" &6D+Launch vehicleAriane V35XMuNA#R."Mass at launch9 kgH$NN$ HBased on a Amsat-NA Microsat bus<uNN' *O External resources]6NVO' lhttp://www.amsat.org/amsat/sats/nk6k/msatmain.html8NO' "(Technical data_VO A#R< S-Band beacon2401.143 MHzO JFORA#R c B#TUplink1200 bps Manchester coded (Biphase-L) FSK (FM) AX.25145.900 145.920 145.940 145.960 MHzFR=A#R P΁A#RDownlink1200 bps BPSK (SSB) AX.25, either one of the two frequencies below:=C#T437.026 MHz (LHCP in northern hemisphere), normal unfiltered PSK437.051 MHz (RHCP in northern hemisphere), Raised Cosine modulationF"΁$ DPassive magnetic stabilization71pHIV͈Pageos? V2 4"  PageosS-& Z Passive Geodetic Earth Orbiting Satellite1 Vڃ'  Generalg AG#^@") Designation02253 / 66056A\ڃA#R6Launch date24 Jun 1966t'AM#jN"N ,㹌לCountry of originUnited Statesp#M#jF"H̀CV$MissionScientific: Geodesy`ᅤA#R>"Perigee/Apogee2953/5207 kmV7A#R*Inclination84.4UᅤA#R(Period177.4 minp#7M#jF" &#*≂Launch vehicleThor Agena D[WA#R4Launch siteVandenbergvO͈' Was an inflatable 30 (or 41?) m diameter aluminum coated mylar balloon weighing 55 kg.In 1975 the satellite broke up into dozens of pieces... numerous decayed but some remain in orbit. They are of special interest for scientist studying solar radiation pressure (SRP)... because on some orbits, the debris actually gain altitude!7W1hII;Paksat7 ͈;, (" Paksat' wSatellite planned by the Pakistani government, to be ordered from Alcatel Espace. Contract worth $220 million. The satellite should carry 26 transponders and have 15 years lifetime.1;N1WNȊT+) "VȠ$To view this page you need to register&NȊ# @1QIuMTtProgram: PalapaLȊT5 :07" Program: PalapaxB RCIxDuU "Palapa" means "unity" in IndonesianIndonesian telecommunication programThe program was developped in 1975 to solve communications (phone, TV) problems between the numerous islands that compose the country. Two years after the Philippines asked to use to system for their national communications. In 1979 Intelsat recognized the system as a regional operator. Nowadays the Palapa system is operated by two companies. PT Telkom is state owned and operates (and operated) the Palapa A, B and D's. Palapa C's are operated by a private company, PT Satelindo. A third company owns and operates a few transponders: PT PSNfBTt$ PT Telkom (state-owned) and PT Satelindo should join forces...11Htz €;>؀:9:92:93:9有有5:9]:9^:9_:9:9Program: PalapaPalapa A1Palapa A2Palapa B1Palapa B2Palapa B2 PPalapa B2 RPalapa B4Palapa C1Palapa C2Palapa C3Palapa D11 1 ¤ 7C# (Palapa A's C-bandY A#R00(Main transponders12YCA#R00,Backup transpondersK @A#R0PowerUA#R(0Bandwidth36 MHzW@A#R,0CoverageIndonesiaT@¤A#R&0EIRP max34 dBWR¤A#R"0Polarization`<@¤¤$ xSatellite designed by Hughes (HS-333), lifetime: 7 years1¤#ä1U#äƤƤ?¤bä# 8Palapa B's specifications\#ääA#R60&Prime contractorHughesTbäĤA#R&0PlatformHS-376[ämĤA#R40"Mass at launch1200 kgYĤĤA#R00 Mass in orbit628 kgTmĤŤA#R&0Diameter2.16 m[ĤuŤA#R40Height6.83 m deployedb!ŤŤA#RB0 StabilizationSpin stabilizedYuŤ0ƤA#R00DC powerBOL: 1062 W\ŤƤA#R60$Design lifetime8 years$0ƤƤ" 1ƤƤ1UƤsɤɤ7ƤǤ# (Palapa B's C-bandYƤqǤA#R00(Main transponders24ZǤǤA#R20,Backup transponders6VqǤ!ȤA#R*0Power10 W (TWTA)UǤvȤA#R(0Bandwidth36 MHzW!ȤȤA#R,0CoverageIndonesiaTvȤ!ɤA#R&0EIRP max34 dBWRȤsɤA#R"0Polarization$!ɤɤ" 1sɤɤ1ɤuͤ?ɤʤ# 8Palapa C's specifications\ɤcʤA#R6&Prime contractorHughesTʤʤA#R&PlatformHS-601[cʤˤA#R4"Mass at launch2990 kgZʤlˤA#R2 Mass in orbit1800 kg`ˤˤA#R>Dimension4.5 x 3.4 x 2.8 mUlˤ!̤A#R(Solar array20 mYˤz̤A#R0 Stabilization3 axisY!̤̤A#R0DC powerEOL: 3400 W]z̤0ͤA#R8$Design lifetime14 yearsE!̤uͤ$ BFeatures 4 octogonal antennas10ͤͤ1Uͤ7uͤͤ# (Palapa C's C-bandh'ͤEΤA#RN(Main transponders24 + 6 (extended)ZͤΤA#R2,Backup transponders8FEΤ'ϤB#TPowerstandard freq.: 21.5 W (SSPA)extended freq.: 26.75 W (SSPA)UΤ|ϤA#R(Bandwidth36 Mhzv'ϤSU#z8,]>!^>!_>!Coverage & EIRP maxIndonesia and New Zealan|ϤSuͤd: 36.5 dBWIndonesia: 37 dBWAsia beam (India to Japan): 36 dBWT|ϤA#R&G/T max-1 dB/KXSA#R.PolarizationlinearAB#TFrequenciesUplink: 5.925-6.665 GHzDownlink: 3.400-4.200 GHz$" 11Uf8# *Palapa C's Ku-bandXgA#R.(Main transponders4ZA#R2,Backup transponders2PgA#RPower130 WUfA#R(Bandwidth72 MHz{/N#l*,?!?!Coverage & EIRP maxK1 (Indonesia, Thailand to HongKong): 50 dBW (horizontal)K2 (Japan & Korea): 50 dBW (vertical)TfA#R&G/T max+3 dB/K\/A#R6Polarizationlinear H/VEfB#TFrequenciesUplink: 13.750-14.490 GHzDownlink: 10.950-11.690 GHz$" 1f1UO Y6# lPalapa C's C-band transponder frequency chart (GHz)"l6#<njjkj*XnHorizontalUplinkHorizontalDownlinkChannelVerticalDownlinkVerticalUplinkCoverage'#"Nnjjkj"0(2^>!_>!3.7201H5.945C1 or C26#>njjkj,02^>!5.9651V3.740C1( #"Pnjjkj"0(2^>!]>!3.7602H5.985C1 or C1'[ #>njjkj,02^>!6.0052V3.780C1' + #"Nnjjkj"0(2^>!_>!3.8003H6.025C1 or C2[ #>njjkj,02^>!6.0453V3.820C1(+ #"Pnjjkj"0(2^>!]>!3.8404H6.065C1 or C1' #>njjkj,02^>!6.0854V3.860C1' P#"Nnjjkj"0(2^>!_>!3.8805H6.105C1 or C2 #>njjkj,02^>!6.1255V3.900C1(P @#"Pnjjkj"0(2^>!]>!3.9206H6.145C1 or C1' @@#>njjkj,02^>!6.1256V3.940C1' @A#"Nnjjkj"0(2^>!_>!3.9607H6.185C1 or C2@`B#>njjkj,02^>!6.2057V3.980C1(A1C#"Pnjjkj"0(2^>!]>!4.0008H6.225C1 or C1'`BC#>njjkj,02^>!6.2458V4.020C1'1CD#"Nnjjkj"0(2^>!_>!4.0409H6.265C1 or C2CE#>njjkj,02^>!6.2859V4.060C1)DWF#"Rnjjkj $2(4^>!]>!4.08010H6.305C1 or C1' EG#@njjkj .24^>!6.32510V4.100C1(WFG#"Pnjjkj $2(4^>!_>!4.12011H6.345C1 or C2 GH#@njjkj .24^>!6.36511V4.140C1)GI#"Rnjjkj $2(4^>!]>!4.16012H6.385C1 or C1' HCJ#@njjkj .24^>!6.40512V4.180C1IJ# njjkj (CJK#"Pnjjkj $2(4^>!_>!3.4201EH6.445C1 or C2)JL#"Rnjjkj $2(4^>!]>!3.4602EH6.485C1 or C1'(KcM#"Pnjjkj $2(4^>!_>!3.5003EH6.525C1 or C2)L5N#"Rnjjkj $2(4^>!]>!3.5404EH6.565C1 or C1'(cMO#"Pnjjkj $2(4^>!_>!3.5805EH6.605C1 or C2)5NO#"Rnjjkj $2(4^>!]>!3.6206EH6.645C1 or C1'$O " O 1O=1W =T+ ) "VȠ$To view this page you need to register&=# 1耥1 耥:Z7B# nPalapa C's Ku-band transponder frequency chart (GHz)!耥āa#B  * UplinkChannelDownlinkgB+R#t*13.7901K10.990gāR#t*13.9502K11.150g+R#t*14.2903K11.490g`R#t*14.4504K11.650:& iHorizontal downlink polarization is K1 coverage; Vertical downlink polarization is K2 coverageSignal can be uplinked in both polarization so that the 2 coverage zones are used1`k1W k儥T+:) "VȠ$To view this page you need to register&k儥# : 1K eLPalapa A1F儥e5 :$7" Palapa A11 '  Generalg eG#^@") Designation09009 / 76066A[XA#R4Launch date8 Jul 1976p#ȆM#jF"N ,b#Country of originIndonesiao"X7M#jD"H̀‰MissionTelecommunications]ȆA#R8,Geostationary orbit83Es&7M#jL" &p㉂Launch vehicleThor Delta #125&-# 5b'  End of lifeX-A#R."Out of service1985&b# 8' "(Technical data4 L) "`hC-band: 1KK ̉Palapa A2FL̉5 :$7" Palapa A21 '  Generalg ̉dG#^@") Designation09862 / 77018A\A#R6Launch date10 Mar 1977p#d0M#jF"N ,b#Country of originIndonesiao"M#jD"H̀‰MissionTelecommunications]0A#R8,Geostationary orbit77Es&oM#jL" &p㉂Launch vehicleThor Delta #129&# 5oʌ'  End of lifeX"A#R."Out of service1988&ʌH# 8"' "(Technical data4 H) "`hC-band: 1KK4ťPalapa B1F45 :$7" Palapa B1<p# 2Palapa Pacific 1 (PP1)1 4'  Generalg pG#^@") Designation14134 / 83059C\dA#R6Launch date18 Jun 1983p#ԏM#jF"N ,b#Country of originIndonesiao"dOM#jD"ԏOH̀‰MissionTelecommunicationsb!ԏA#RB,Geostationary orbitsee belowjOM#j:" &㫜Launch vehicleSTS 07+ $ This satellite was taken over in 1991 by an affiliate of Satelindo, PT Pasifik Satelit Nusantara and renamed Palapa Pacific 12 '  Location¥m#:   " BeginEndPosition+ åp#V$(*:9L: 30 Oct 1982replaced Palapa A1(¥åj#P,.Mar 1995Sep 1995134E, inclined& åå# 5å ĥ'  End of life\åiĥA#R6"Out of serviceOct 1995M ĥĥA#RCausedrifting but not removed from the belt... probably ran out of fuel!&iĥť# 8ĥUť' "(Technical dataLťť0 08 6zoSpecificationsC-band: Uťť1K>Kť!ƥʥPalapa B2Fť!ƥ5 :$7" Palapa B21 ťRƥ'  Generalg !ƥƥG#^@") Designation14692 / 84011D[RƥǥA#R4Launch date6 Feb 1984p#ƥǥM#jF"N ,b#Country of originIndonesiao"ǥǥM#jD"H̀‰MissionTelecommunicationsYǥLȥA#R0,Geostationary orbitjǥȥM#j:" &"Launch vehicleSTS 11\LȥIʥ7 <*有有Launched on a bad orbit (faulty perigee motor) it was retrieved on 12 Nov 1984 by STS 19. This retrieval was financed by the insurance companies, despite the operator's refusal to retrieve it and asked for the insurance money (then used to order Palapa B2P). Some time later the operator changed it's mind and relaunched it as Palapa B2R.8ȥʥ' "(Technical dataLIʥʥ0 08 6zoSpecificationsC-band; ʥ˥1KL˥O˥IPalapa B2PGʥO˥5 :&7" Palapa B2P;˥˥# 0Also called Mabuhay 01 O˥˥'  Generalg ˥"̥G#^@") Designation17706 / 87029A\˥~̥A#R6Launch date20 Mar 1987p#"̥̥M#jF"N ,b#Country of originIndonesiao"~̥]ͥM#jD"H̀‰MissionTelecommunicationsb!̥ͥA#RB,Geostationary orbitsee belows&]ͥ2ΥM#jL" &p㉂Launch vehicleThor Delta #181ͥΥ+ $?"ZIn mid 1996 the bird was sold to PLDT (by PT Pasifik Satelit Nusantara) for a little over $3 million to become the first satellite of the Mabuhay system.2 2Υ.ϥ'  LocationΥϥm#:   " BeginEndPosition$.ϥRj#H$ϥRʥ8:L: 20 Mar 1987May 1996113E(ϥj#P,.Aug 1996Aug 1997144E, inclined Rnj#@Sep 1997142E, inclined&# 5n'  End of life\%A#R6"Out of serviceJan 1998TyA#R&Causedeorbited&%# 8y' "(Technical datar:I8 @tſ 6zoC-band EIRP coverage (dBW)SpecificationsC-band1z1zOI6 <4最"Palapa B2P's EIRP; z1>KlLKPalapa B2RGK5 :&7" Palapa B2R1 |'  Generalg KG#^@") Designation20570 / 90034A\|?A#R6Launch date13 Apr 1990p#M#jF"N ,b#Country of originIndonesiao"?M#jD"H̀‰MissionTelecommunicationsfG#^>"/ۀ0Geostationary orbit108Ep#M#jF" &p㉂Launch vehicleDelta 2 #194c9W* $r3:9It's Palapa B2 retrieved from orbit and modernized.8' "(Technical datar:W8 @t4vKр 6zoC-band EIRP coverage (dBW)SpecificationsC-band1212O6 <4最"Palapa B2R's EIRP: 21LL Palapa B4F 5 :$7" Palapa B41 2 '  Generalg  G#^@") Designation21964 / 92027Ah'2  A#RNLaunch date14 May 1992 at 00:40 UTp# q M#jF"N ,b#Country of originIndonesiao" M#jD"H̀‰MissionTelecommunicationsfq F G#^>"/ۀ0Geostationary orbit118Ep# M#jF" &p㉂Launch vehicleDelta 2 #209;F $ .Cost: $56.4 million8 ) ' "(Technical datar: 8 @t* 6zoC-band EIRP coverage (dBW)SpecificationsC-band1) 1  N  6 <25:9"Palapa B4's EIRP: T 1* lLLT FPalapa C1F 5 :$7" Palapa C11 T '  Generalg 2G#^@") Designation23779 / 96006A[ A#R4Launch date1 Feb 1996p#2M#jF"N ,b#Country of originIndonesiao"lM#jD"H̀‰MissionTelecommunicationsb!A#RB,Geostationary orbitsee belowu(lO@M#jP" O@ &yjLaunch vehicleAtlas Centaur #98&u@# : O@@- */ۀ Locationu@9Am#:   " BeginEndPosition#@Aj#F"68L: 1 Feb 1996Mar 1996124E"9ARBj#D 46mid-Mar 1996Jun 1996113EABj#:"&(late Aug 1996150.5ERBD/ ,o GTO: 240 x 89462 km x 21.9 Launch cost: $90 million. Contract for both Hughes Palapa C: $128 millionAfter testing faulty batteries for Ku-band transponders were discovered. This could lead to the transponders not being marketed. Each transponder is worth $799,000 in revenue a year. The satellite entered service on 23 March 1996.6 of the 34 transponders are owned by PT Pasifik Satelit Nusantara, the remaining by PT Satelindo8BD' "(Technical datarDEF \ꏀvC͉ê>SpecificationsC-bandKu-bandC-band transponder frequency chartKu-band transponder frequency chart3 DE'  EIRP mapspEF> L^>!]>!_>!?!C-band: Asean beam (C1)C-band: Asean & New Zealand beam (C1')C-band: Asia beam (C2)Ku-band (K1+K2)1EF1F.Gm7F.G6 SpecificationsC-bandKu-bandC-band transponder frequency chartKu-band transponder frequency chart3 NO'  EIRP mapspOl> L^>!]>!_>!?!C-band: Asean OlHbeam (C1)C-band: Asean & New Zealand beam (C1')C-band: Asia beam (C2)Ku-band (K1+K2): O1LM쀦QPalapa C3Fl쀦5 :$7" Palapa C3eAQ$ to be launched (this was an option on the 2 Cs contract)118E1쀦1WցT+Qց) "VȠ$To view this page you need to register&# : ց61 M6|VPalapa D1F|5 :$7" Palapa D1:6# .Also called Telkom 11 |炦'  GeneralY@G#^$") Designation[炦A#R4Launch dateearly 1999_@G#^0"N ,Country of originUOG#^"H̀Mission^A#R:,Geostationary orbit108EjOM#j:" &2!Launch vehicleArianeYpG#^$Launch sitekFۅ% contract worth $140 millionlaunch is expected to cost $75 million8p' "(OTechnical data8ۅK' " Specificationse$A#RH&Prime contractorLockheed MartinN KA#RPlatform[YA#R4"Mass at launch2500 kgSA#R$ Mass in orbitOYA#RDimensionQLA#R Solar arraySA#R$ StabilizationN L툦A#RDC power]JA#R8$Design lifetime15 years&툦p# 0 J'  C-bandYpA#R0(Main transponders32YRA#R0,Backup transpondersK A#RPowerOR슦A#RBandwidthN :A#RCoverageJ 슦A#REIRPR:֋A#R"Polarization\V$ Performance is said to be close to the Palapa B series but with additional transponders.1֋1WیT+Vی) "VȠ$To view this page you need to register&# BیC1I\ CVProgram: PanamsatN5 :4" Program: PanamsatCV0 .+$Ijg?qOAmerican telecommunication program operated by Panamsat Corporation, a merger between Panamsat (Alpha Lyracom) and HCI (merger in April 1997).11m!Ï<VÏ Ѐw?J$@hAhBh8MChDhEh㩃MFhGhHhʂMProgram: PanamsatPanamsat 1Panamsat 2Panamsat 3Panamsat 3RPanamsat 4Panamsat 5Panamsat 6Panamsat 6BPanamsat 7Panamsat 8Panamsat 9Panamsat 10 & 11; 17"N" SiBPanamsat 1Ï ÏGÏS5 :&" Panamsat 17 # (Also called PAS 11 S'  Generalg "G#^@") Designation19217 / 88051C\~A#R6Launch date15 Jun 1988t'"M#jN"N ,㹌לCountry of originUnited Stateso"~a¦M#jD"H̀‰MissionTelecommunicationse¦G#^<"/ۀ0Geostationary orbit45Wn!a¦4æM#jB" & D+Launch vehicleAriane V23&¦Zæ# 84ææ' "(OTechnical data=Zææ' , EIRP coverage (dBW)f/æ5Ħ7 >^C€P&(C-bandKu-band to EuropeKu-band to US8æmĦ' " Specificationsd#5ĦĦA#RF&Prime contractorGE Astro SpaceN mĦŦA#RPlatform[ĦzŦA#R4"Mass at launch1220 kgYŦŦA#R0 Mass in orbit708 kgb!zŦ5ƦA#RBDimension1.63 x 1.32 x 1.9 mYŦƦA#R0 Stabilization3 axisY5ƦƦA#R0DC powerBOL: 1400 W]ƦDǦA#R8$Design lifetime11 yearssIƦǦ* $ZSPanamsat 1 is in fact ASC 3, a backup satellite of the ASC program.0 DǦǦ'  C-band[ǦBȦA#R4(Main transponders12+6\ǦȦA#R6,Backup transponders2+1bBȦBɦB#TPower(12+2) transponders of 36 MHz : 8.5 W (SSPA)(6+1) transponders of 72 MHz: 16.2 W (TWTA)=ȦɦB#TzBandwidth12 transponders of 36 MHz6 transponders 72 MHzBɦʦK#dw"C€,Coverage and EIRPto North America (7, 9, 11, 16 & 18): ?to Central America (8, 10, 12 & 13): 40 dBWto Latin America (1, 3, 5 & 15): 37 dBWto South America (2, 4, 6 & 14): 38 dBW\ɦe˦B#TPolarizationto Latin and South America: linear Vto Central and North America: linear H&ʦ˦# K$e˦˦' H Transponder frequency chart (GHz)n˦̦#$j * X v   HorizontalUplinkHorizontalDownlinkTransponderChannelVerticalDownlinkVerticalUplink˦ͦ#ڀ2j .5.945113.720̦*Φ#ڀ2j $3.740725.965ͦΦ#ڀ2j .5.985233.760*ΦfϦ#ڀ2j $3.780846.005Φ#ڀ2j .6.025353.800fϦÏfϦ#ڀ2j $3.820966.045L#ڀ2j .6.065473.840#ڀ4j"&3.8601086.085L#ڀ2j .6.105593.880)#ڀ6j$(3.90011106.125#ڀ4j"06.1456113.920)h#ڀ6j$(3.94012126.165 #ڀ8j&46.18513A133.960h#ڀ8j&*3.98016A146.205 K#ڀ8j&46.22513B154.000#ڀ8j&*4.02016B166.245K#ڀ8j&46.26514A174.040.#ڀ8j&*4.06017A186.285#ڀ8j&46.30514B194.080.p #ڀ8j&*4.10017B206.325 #ڀ8j&46.34516A214.120p #ڀ8j&*4.14018A226.365 S #ڀ8j&46.38516B234.160 #ڀ8j&*4.18018B246.405&S  # B \ ' 6 Ku-band (11.5-11.75 GHz)X A#R.i(Main transponders6Z\  A#R2i,Backup transponders1X f A#R.iPower16.2 W (TWTA)U A#R(iBandwidth72 MHz^f hO#ni*0P&(Coverage andEIRP maxEurope (19, 20 & 21): 47 dBWNorth America (22, 23 & 24): 45 dBWZ A#R2iPolarizationlinear H&h# K$3' H Transponder frequency chart (GHz)9c#r . L HorizontalDownlinkTransponderVerticalUplinkg3B@R#t*B@Ï11.5001914.040g@R#t*11.5802014.120gB@AR#t*11.6602114.200g@wAR#t*11.7902214.280gAAR#t*11.8202314.360gwAEBR#t*11.9002414.440$AiB" 1EBB1W#BBCT+iBB) "VȠ$To view this page you need to register&BC# 1BEC1$ECCX"CC6 "/ۀ0Geostationary orbit169En!QI%JM#jB" &D+Launch vehicleAriane V65&IKJ# 8%JJ' "(OTechnical data=KJJ' , EIRP coverage (dBW)k4J+K7 >hII=IC-band, Pacific RimC-band, OceaniaKu-band8JcK' " Specifications\+KKA#R6&Prime contractorHughesTcKLA#R&PlatformHS-601[KnLA#R4"Mass at launch2920 kgSLLA#R$ Mass in orbitOnLMA#RDimensionYLiMA#R0 Stabilization3 axisTMMA#R&DC power5400 W]iMNA#R8$Design lifetime15 yearsHMNB#TBeacons4.1985 & 4.1995 GHz (0 dBW, H)12.5 GHz (5 dBW, RHCP + LHCP)&NN# 0 NN'  C-bandYNSOA#R0(Main transponders16ZNOA#R2,Backup transponders4OSO A#RPower34 WO F>OB#T|Bandwidth12 transponder of 54 MHz4 transponder of 64 MHzL A#R0Coverage and EIRP maxOceania and Pacific Rim beams (see footprint maps)\uA#R6Polarizationlinear H/V&# K$u恧' H Transponder frequency chart (GHz)Wڂ#  . L v  HorizontalDownlinkTransponderVerticalDownlinkBandwidth (MHz)Beam恧#8$&13.72054Pacificڂ*#8$&3.720254Pacific҄#8$&33.79054Pacific*z#8$&3.790454Pacific҄"#8$&53.85054Pacificzʆ#8$&3.850654Pacific&"|#L$&73.91564Pacific / Oceaniaʆ$#8$&3.915864Pacific|̈#8$&93.98054Pacific$u#:&(3.9801054Pacific'̈(#N&(114.04054Pacific / Oceaniauъ#:&(4.0401254Pacific(z#:&(134.10054Pacificъ##:&(4.1001454Pacific'z֌#N&(154.16564Pacific / Oceania##:&(4.1651664Pacific&֌# 1 ֍'  Ku-bandY/A#R0(Main transponders16Z֍A#R2,Backup transponders4O/؎A#RPower63 W>XB#T|Bandwidth12 transponder of 54 MHz4 transponder of 64 MHzw؎$I#b"=I,Coverage and EIRPSouth Korean beam: 50 dBW and rest of Asia: 42 dBWChinese beam: 50 dBWAX$Fustralian beam: 46 dBW\XA#R6Polarizationlinear H/VJ$ B#TFrequenciesUplink: 14.000 - 14.500 GHz Downlink: 12.250 - 12.750 GHz&2# K$ }' H Transponder frequency chart (GHz)W2q§#  * H v  VerticalDownlinkTransponderHorizontalDownlinkBandwidth (MHz)Beam}ç#:&(12.281154China 1q§ç#>&(212.28154Australiaçnħ#:&(12.341354China 2çŧ#:&(412.34154NE Asianħŧ#:&(12.401554China 1ŧkƧ#>&(612.40154Australia)ŧ ǧ#R&(12.466764China 2 / AustraliakƧǧ#:&(812.46664NE Asia ǧrȧ#:&(12.531954China 1 ǧɧ#@ (*1012.53154Australia*rȧɧ#T (*12.5911154China 2 / Australiaɧ~ʧ#< (*1212.59154NE Asiaɧ(˧#< (*12.6511354China 1 ~ʧ˧#@ (*1412.65154Australia*(˧̧#T (*12.7161564China 2 / Australia˧4ͧ#< (*1612.71664NE Asia$̧Xͧ" 14ͧͧ1W+ͧͧΧT+Xͧͧ) "VȠ$To view this page you need to register&ͧΧ# 1ͧ4Χ1,4ΧΧc-ΧΧ6 <\Ah"'Panamsat 2's C-band EIRP: Pacific Rim14ΧΧ1W-ΧϧBϧT+Χϧ) "VȠ$To view this page you need to register&ΧBϧ# 1ϧsϧ1.sϧ _)Bϧ 6 XX:1OY:1O;1OC-band beam 1C-band beam 2Ku-band8^CC' " Specifications\CUDA#R6&Prime contractorHughesTCDA#R&PlatformHS-601[UDEA#R4"Mass at launch2918 kgSDWEA#R$ Mass in orbitb!EEA#RBDimension2.84 x 3.53 x 3.6 m\WEFA#R6Solar array26.5 m spanYEnFA#R0 Stabilization3 axisf$FFB#THDC powerBOL: 5400 WEOL: 4300 W]nF1GA#R8$Design lifetime15 yearsEFGB#TBeacons4.1985 & 4.1990 GHz (0 dBW)11.7 GHz (5 dBW, RHCP + LHCP)&1GH% It uses Hughes' advanced shaped-reflector technology, which concentrates the satellite's beam over targeted land areas while avoiding uninhabited oceans. Hughes' patented, highly efficient design eliminates the need for multiple feedhorn configurations.0 GI'  C-bandYHgIA#R0(Main transponders16ZIIA#R2,Backup transponders4VgIJA#R*Power34 W (SSPA)@IJB#TBandwidth12 transponders of 54 MHz4 transponders of 64 MHzLJ;KV#|80X:1OY:1OX:1OCoverage andEIRP maxPan America beam 1Pan America beam 2Africa\JKA#R6Polarizationlinear H/VA;KLB#TFrequenciesUplink: 5.925-6.425 GHzDownlink: 3.700-4.200 GHz&K@L# T-LL' Z Downlink transponder frequency chart (GHz)W@LM#  . L v  HorizontalDownlinkTransponderVerticalDownlinkBandwidth (MHz)Beam L:N#@$&Y:1O13.73054PAN AM V2 MN#@$&Y:1O3.730254PAN AM H2 :NO#@$&X:1O33.79054PAN AM V1 N\#@O\Q$&X:1O3.790454PAN AM H1 O#@$&Y:1O53.85054PAN AM V2 \#@$&Y:1O3.850654PAN AM H2*|#T$&X:1O73.91564PAN AM V1 or Africa .#@$&X:1O3.915864PAN AM H1 |#@$&Y:1O93.98054PAN AM V2!.#B&(Y:1O3.9801054PAN AM H2+P#V&(X:1O114.04054PAN AM V1 or Africa!#B&(X:1O4.0401254PAN AM H1!P#B&(Y:1O134.10054PAN AM V2!i#B&(Y:1O4.1001454PAN AM H2+&#V&(X:1O154.16564PAN AM V1 or Africa!iو#B&(X:1O4.1651664PAN AM H1&&# R+وQ' V Uplink transponder frequency chart (GHz)SA#  & D n  VerticalUplinkTransponderHorizontalUplinkBandwidth (MHz)Beam Q튨#@$&15.95554PAN America A#@$&5.955254PAN America;튨`#v$&36.01554PAN America or Africa or North America #@$&6.015454PAN America `#@$&56.07554PAN America d#@$&6.075654PAN America;+#v$&76.14064PAN America or Africa or North America d׏#@$&6.140864PAN America +#@׏Q$&96.20554PAN America!׏<#B&(6.2051054PAN America<¨#x&(116.26554PAN America or Africa or North America!<¨#B&(6.2651254PAN America!¨^è#B&(136.32554PAN America!¨ Ĩ#B&(6.3751454PAN America<^èĨ#x&(156.39064PAN America or Africa or North America! ĨŨ#B&(6.3901664PAN America&ĨŨ# 1 ŨŨ'  Ku-bandYŨ0ƨA#R0(Main transponders16ZŨƨA#R2,Backup transponders4V0ƨƨA#R*Power63 W (TWTA)@ƨbǨB#TBandwidth12 transponders of 54 MHz4 transponders of 64 MHzƨ.ȨG#\ 0Coverage andEIRP maxEurope: 50 dBWNorth-America: 50 dBWNorth South-America: 50 dBWSouth South-America: 52 dBWBrazil: 50 dBW\bǨȨA#R6PolarizationLinear H/VZ.Ȩ&ɨB#TFrequenciesUplink: 14.00-14.500 GHzDownlink: 11.700-12.200 GHz and 12.500-12.750 GHz&ȨLɨ# T-&ɨɨ' Z Downlink transponder frequency chart (GHz)YLɨʨ# * H v (;1OVerticalDownlinkTransponderHorizontalDownlinkBandwidth (MHz)Beam4ɨ_˨#h&(111.72954North South-America or Europe;ʨ)̨#v&(11.729254North-America or South South-America0_˨̨#`&(411.78954North-America (but no 4B)))̨ͨ#R (*11.7894B54Brazil (but no 4)4̨cΨ#h&(511.84954North South-America or Europe;ͨ-Ϩ#v&(11.849654North-America or South South-America0cΨ #`&(811.91464North-America (but no 8B)-Ϩ Q)-Ϩ#R (*11.9148B64Brazil (but no 8)4 #h&(911.97954North South-America or Europe@V# (*11.9791054North-America or South South-America (H)2#d (*1212.03954North-America (but no 12B)+V#V"*,12.03912B54Brazil (but no 12)5#j (*1312.09954North South-America or Europe@d# (*12.0991454North-America or South South-America (H)2%#d (*1612.16464North-America (but no 16B)+d#V"*,12.16416B64Brazil (but no 16)%|# 5@#j (*1E12.53154Europe or North South-America5| #j (*12.5319E54Europe or North South-America@ #< (*3E12.59154Europe _ #>"*,12.59111E54Europe5 # #j (*5E12.65154Europe or North South-America6_ #l"*,12.65113E54Europe or North South-America# #< (*7E12.71664Europe C #>"*,12.71615E64Europe& i # R+C ' V Uplink transponder frequency chart (GHz)Si #  & D n  VerticalUplinkTransponderHorizontalUplinkBandwidth (MHz)Beam- d#Z&(14.029154Europe or North-America$ @#H (*1S14.029d @Q54South-America-d@#Z&(214.02954Europe or North-America- @A#Z&(14.089354Europe or North-America-@KB#Z&(414.08954Europe or North-America$AB#H (*4S14.08954South-America-KBC#Z&(14.149554Europe or North-America$BdD#H (*1S14.14954South-America-CE#Z&(614.14954Europe or North-America-dDE#Z&(14.214764Europe or North-America-EF#Z&(814.21464Europe or North-America$E?G#H (*8S14.21464South-America-FG#Z&(14.279954Europe or North-America$?GH#H (*9S14.27954South-America.GbI#\ (*1014.27954Europe or North-America.HJ#\ (*14.3391154Europe or North-America.bIJ#\ (*1214.33954Europe or North-America%JK#J"*,12S14.33954South-America.JAL#\ (*14.3991354Europe or North-America%KL#J"*,13S14.39954South-America.ALM#\ (*1414.39954Europe or North-America.LfN#\ (*14.4641564Europe or North-America.M O#\ (*1614.46464Europe or North-America%fNO#J"*,16S14.46464South-America$ O " O Q1O=1W5=T+ ) "VȠ$To view this page you need to register&=# 1耩16耩F^(F6 8M",Panamsat 3R's Ku-band EIRPNAv stands for North America vertical polarization, NAh stands for North America horizontal polarization1\P1W;PʄT+) "VȠ$To view this page you need to register&Pʄ# ; 1DT~P2P<LȪPanamsat 4GʄL5 :&" Panamsat 47# (Also called PAS 41 L'  Generalg G#^@") Designation23636 / 95040A[vA#R4Launch date3 Aug 1995t'ꆩM#jN"N ,㹌לCountry of originUnited Stateso"vYM#jD"H̀‰MissionTelecommunicationsg ꆩG#^@"/ۀ0Geostationary orbit68.5En!Y.M#jB" &D+Launch vehicleAriane V76&T# 8.' "(OTechnical data=TɈ' , EIRP coverage (dBW)nu> LvvvVC-band: Africa & AsiaC-band: Asia/Middle East horizontalC-band: Asia/Middle East verticalKu-band8Ɉ' " Specifications\u A#R6&Prime contractorHughesT]A#R&PlatformHS-601[ A#R4"Mass at launch3043 kgU] A#R(Dry mass1671 kgS`A#R$ Mass in orbitb! ‹A#RBDimension2.84 x 3.53 x 3.6 m\`A#R6Solar array26.2 m spanY‹wA#R0 Stabilization3 axisf$݌B#THDC powerBOL: 5400 WEOL: 4300 W]w:A#R8$Design lifetime15 yearsE݌B#TBeacons4.1990 & 4.1995 GHz (0 dBW)12.5 GHz (5 dBW, RHCP + LHCP)&:獩# 0 '  C-bandY獩pA#R0(Main transponders16ZʎA#R2,Backup transponders4Vp A#R*Power30 W (SSPA)@ʎB#TBandwidth12 transponders of 54 MHz4 transponders of 64 MHz] g\#D2vvvvCgʄoverage and EIRP maxAfricaSouth Asia/Middle East: Horizontal or VerticalAsia\A#R6PolarizationLinear H/VAgFB#TFrequenciesUplink: 5.925-6.425 GHzDownlink: 3.700-4.200 GHz&l# T-F' Z Downlink transponder frequency chart (GHz)Wl©#  * H v  VerticalDownlinkTransponderHorizontalDownlinkBandwidth (MHz)Beam+ké#V$&13.73054South Asia/Middle East5©,ĩ#j$&3.730254Africa or South Asia/Middle East+kéĩ#V$&33.79054South Asia/Middle East,ĩũ#2$&3.790454Asia+ĩ?Ʃ#V$&53.85054South Asia/Middle East5ũǩ#j$&3.850654Africa or South Asia/Middle East+?Ʃǩ#V$&73.91564South Asia/Middle Eastǩ\ȩ#2$&3.915864Asia+ǩɩ#V$&93.98054South Asia/Middle East\ȩɩ#8&(3.9801054Africa,ɩsʩ#X&(114.04054South Asia/Middle East6ɩ5˩#l&(4.0401254Africa or South Asia/Middle East,sʩ˩#X&(134.10054South Asia/Middle East5˩̩#8&(4.1001454Africa,˩Mͩ#X&(154.16564South Asia/Middle East6̩Ω#l&(4.1651664Africa or South Asia/Middle East&Mͩ5Ω# R+ΩΩ' V Uplink transponder frequency chart (GHz)S5Ωwϩ#  * H n  HorizontalUplinkTransponderVerticalUplinkBandwidth (MHz)Beam+Ω:#V$&wϩ:ʄ15.95554South Asia/Middle East:wϩ#t$&5.955254India/Asia/Australia or Africa/Europe+:#V$&36.01554South Asia/Middle East:}#t$&6.015454India/Asia/Australia or Africa/Europe+4#V$&56.07554South Asia/Middle East:}#t$&6.075654India/Asia/Australia or Africa/Europe+4#V$&76.14064South Asia/Middle East:w#t$&6.140864India/Asia/Australia or Africa/Europe+.#V$&96.20554South Asia/Middle East*w#T&(6.2051054India/Asia/Australia,.#X&(116.26554South Asia/Middle East;c#v&(6.2651254India/Asia/Australia or Africa/Europe, #X&(136.32554South Asia/Middle East;c #v&(6.3751454India/Asia/Australia or Africa/Europe, #X&(156.39064South Asia/Middle East; a #v&(6.3901664India/Asia/Australia or Africa/Europe& # 1 a '  Ku-bandY  A#R0(Main transponders24Z k A#R2,Backup transponders6V A#R*Power60 W (TWTA)Yk ] C#VBandwidth16 transponders of 27 MHz6 transponders of 54 MHz2 transponders of 64 MHzV F#\0Coverage andEIRP maxEurope/RussiaNorth East AsiaMiddle EastIndiaSouth-Africa\] UA#R6PolarizationLinear H/VZ B#TFrequenciesUplink: 14.00-14.500 GHzDownlink: 11.450-11.700 GHz and 12.250-12.750 GHz&U# T-k' Z Downlink transponder frequency chart (GHz)Ys@# * H v (ks@ʄVVerticalDownlinkTransponderHorizontalDownlinkBandwidth (MHz)Beam3k5A#f (*1711.46427Middle East (if not Europe)*s@A#T (*11.4641727Europe (if not ME)35AB#f (*1911.52427Middle East (if not Europe)*AiC#T (*11.5241927Europe (if not ME)3B+D#f (*2111.58427Middle East (if not Europe)*iCD#T (*11.5842127Europe (if not ME)3+DE#f (*2311.64927Middle East (if not Europe)*D_F#T (*11.6492327Europe (if not ME)EF# _FG#8&(12.266927IndiaFSH#: (*1012.29627IndiaGH#: (*12.3261127IndiaSHI#: (*1212.35627IndiaHWJ#: (*12.3861327IndiaIK#: (*1412.41627IndiaWJK#: (*12.4511527IndiaKYL#6 $&12.48127IndiaKL# #YLM#F&(112.53154South-Africa-LdN#Z&(12.531554South-Africa or Europe%MO#J (*1812.54627India or Asia#dNO#F&(212.59154South-Africa-O#ZOʄ&(12.591654South-Africa or Europe%OF#J (*2012.60627India or Asia##F&(312.65154South-Africa-F#Z&(12.651754South-Africa or Europe%h#J (*2212.66627India or Asia##F&(412.71664South-Africa-hք#Z&(12.716864South-Africa or Europe%#J (*2412.73127India or Asia&ք# R+' V Uplink transponder frequency chart (GHz)S#  & D n  VerticalUplinkTransponderHorizontalUplinkBandwidth (MHz)Beam.#\&(14.029154Europe/South-Africa/Asia3k#f&(914.01427Europe/Middle East/India/Asia4+#h (*1014.04427Europe/Middle East/India/Asia.k剪#\&(14.089254Europe/South-Africa/Asia4+#h (*1114.07427Europe/Middle East/India/Asia4剪e#h (*1214.10424Europe/Middle East/India/Asia.#\&(14.149354Europe/South-Africa/Asia4eߌ#h (*1314.13427Europe/Middle East/India/Asia4#h (*1414.16427Europe/Middle East/India/Asia.ߌY#\&(14.214464Europe/South-Africa/Asia4#h (*1514.19927Europe/Middle East/India/Asia4Yُ#h (*1614.22927Europe/Middle East/India/Asia.#\ُʄ&(14.279554Europe/South-Africa/Asia4ُ_#h (*1714.26427Europe/Middle East/India/Asia4ª#h (*1814.29427Europe/Middle East/India/Asia._ª#\&(14.339654Europe/South-Africa/Asia4ªê#h (*1914.32427Europe/Middle East/India/Asia4ªYĪ#h (*2014.35427Europe/Middle East/India/Asia.êŪ#\&(14.399754Europe/South-Africa/Asia4YĪŪ#h (*2114.38427Europe/Middle East/India/Asia4Ūƪ#h (*2214.41427Europe/Middle East/India/Asia.ŪMǪ#\&(14.464864Europe/South-Africa/Asia4ƪ Ȫ#h (*2314.44927Europe/Middle East/India/Asia4MǪȪ#h (*2414.47927Europe/Middle East/India/Asia$ ȪȪ" 1Ȫ"ɪ1W="ɪvɪɪT+Ȫvɪ) "VȠ$To view this page you need to register&"ɪɪ# 1vɪɪ1>ɪ6ʪi3ɪ6ʪ6 ʪ˪6 <~Ch".Panamsat 4's C-band Asia & Middle East horizontal EIRP1˪˪1WA˪ ̪1̪T+˪ ̪) "VȠ$To view this page you need to register&˪1̪# 1 ̪b̪1Bb̪̪r<1̪̪6 V)o_2* 1*C-bandKu-band, USKu-band, Mexico8Z' " Specifications\PA#R6&Prime contractorHughesVA#R*PlatformHS-601HP[PA#R4"Mass at launch3720 kgN OA#RDry massSA#R$ Mass in orbitL OA#RLengthK 9A#RWidthL A#RHeighta 9A#R@Solar arraygallium arsenideY?A#R0 Stabilization3 axisTA#R&DC power8000 W]?A#R8$Design lifetime15 yearsgBW % Will use GaAs (gallium arsenide) solar cells, "advanced" batteries. It will be the first commercial satellite to launch with the XIPS thrusters that should provide 5 additional lifetime years. Liquid propellant thrusters provide 15 years lifetime. Some problems developped with XIPS and software patches were uploaded.0  '  C-bandYW A#R0(Main transponders24Z : A#R2,Backup transponders4O A#RPower50 WU: A#R(Bandwidth36 MHzJ w O#n,,)o艂)o艂Coverage & EIRP max1 single beam:Americas: 38 dBWEurope: 31 dBW\ A#R6Polarizationlinear H/VEw Z B#TFrequenciesUplink: 5.925 - 6.425 GHzDownlink: 3.700 - 4.200 GHzS A#R$ SFD-96 dBW/mVZ  A#R*G/T max-1.8 dB/K& ) # R+ { ' V C-band transponder frequency chart (GHz)g) u# ( T r  Vertical UplinkVertical DownlinkTransponderHorizontal DownlinkHorizontal Uplink{ t#,(5.94513.720ut#,3.72025.945@t#,(5.@Ϊ98533.760@t#,3.76045.985@3At#,(6.02553.800@At#,3.80066.0253AGBt#,(6.06573.840ABt#,3.84086.065GB[Ct#,(6.10593.880BCt#. 3.880106.105[CqDt#.*6.145113.920CDt#. 3.920126.145qDEt#.*6.185133.960DFt#. 3.960146.185EFt#.*6.225154.000F(Gt#. 4.000166.225FGt#.*6.265174.040(G>Ht#. 4.040186.265GHt#.*6.305194.080>HTIt#. 4.080206.305HIt#.*6.345214.120TIjJt#. 4.120226.345IJt#.*6.385234.160jJKt#. 4.160246.385&JK# 1 KK'  Ku-band]K4LA#R8(Main transponders18 + 6ZKLA#R2,Backup transponders4a4LLB#T>Power18 at 110 W6 at 60 WULDMA#R(Bandwidth36 MHzXLMO#n,,_2* 1*Coverage & EIRP maxUS: 49 dBWSteerable: n/aMexico (and US North-East): 49 dBW\DMGNA#R6Polarizationlinear H/VMOC#TFrequenciesUplink: 12.750 - 13.250 GHz Downlink: 10.700 - 11.450 GHzUplink: 14.000 - 14.250 GHz Downlink: 11.450 - 11.700 GHz (Spot)SGNgOA#R$ SFD-89 dBW/mVOOA#R*G/T max-2.8 dB/KVgOA#R*BOΪeacon11.454 GHz&OE# T-' Z Downlink transponder frequency chart (GHz)DEc#܀ * H vxVerticalDownlinkTransponderHorizontalDownlinkBeam~#̀2 710.727Mexicoc~#̀2 810.768Mexico(~#̀2 910.809Mexico~#̀4 "1010.850Mexico(X~#̀4 "1110.891Mexico~#̀4 "1210.932Mexico Xz~#̀ ~#̀, "11.21919USz~#̀2 111.219Mexico9~#̀, "11.26120USЇ~#̀2 211.261Mexico9d~#̀, "11.30321USЇ~#̀2 311.303Mexicod~#̀, "11.34522US&~#̀2 411.345Mexico~#̀, "11.38723US&Q~#̀2 511.387Mexico勫~#̀, "11.42924USQ|~#̀2 611.429Mexico 勫~#̀ |~#̀: "11.47613steerable<~#̀: "11.51714steerable׎~#̀: "11.55815steerable<r~#̀: "11.59916steerable׎~#̀: "11.64017rΪsteerabler~#̀: "11.68118steerable&# R+,' V Uplink transponder frequency chart (GHz)@#܀M & D np VerticalUplinkTransponderHorizontalUplinkBeam-,«{#ƀZM 112.769US / Latin America / Europe3ë{#ƀ<M "12.76919US / Europe-«ë{#ƀZM 212.811US / Latin America / Europe3ëtī{#ƀ<M "12.81120US / Europe-ëū{#ƀZM 312.853US / Latin America / Europetīū{#ƀ<M "12.85321US / Europe-ū]ƫ{#ƀZM 412.895US / Latin America / Europeūƫ{#ƀ<M "12.89522US / Europe-]ƫǫ{#ƀZM 512.937US / Latin America / Europeƫ7ȫ{#ƀ<M "12.93723US / Europe-ǫȫ{#ƀZM 612.979US / Latin America / Europe7ȫxɫ{#ƀ<M "12.97924US / Europe ȫɫ{#ƀM -xɫʫ{#ƀZM 713.026US / Latin America / Europe-ɫN˫{#ƀZM 813.067US / Latin America / Europe-ʫ˫{#ƀZM 913.108US / Latin America / Europe.N˫̫{#ƀ\M "1013.149US / Latin America / Europe.˫Hͫ{#ƀ\M "1113.190US / Latin America / Europe.̫ͫ{#ƀ\M "1213.231US / Latin America / Europe HͫwΫ{#ƀM .ͫ ϫ{#ƀ\M "1314.019US / Latin America / Europe.wΫϫ{#ƀ\M "1414.060US / Latin America / Europe. ϫ~{#ƀ\Mϫ~Ϊ "1514.101US / Latin America / Europe.ϫ'{#ƀ\M "1614.142US / Latin America / Europe.~{#ƀ\M "1714.183US / Latin America / Europe.'y{#ƀ\M "1814.224US / Latin America / Europe$" 1y1WG"HT+") "VȠ$To view this page you need to register&H# 1"y1HyV H6 " &2!Launch vehicleAriane 5QzB7CA#R Launch site\BCA#R6"Mass at launch~3500 kgc7C%E/ ,ChPanamsat gets options for more Arianespace launchesPAS-7 will expand PanAmSat's (PAS 4) southern Southern Africa satellite capacity and will extend its high-power Ku-band satellite coverage for DTH and other applications into Sub-Saharan Africa.The satellite is overweight compared to initial specifications, which cause a problem for the launch8C]E' "(OTechnical data8%EE' " Specificationsi(]EEA#RP&Prime contractorSpace Systems/LoralUESFA#R(PlatformFS 1300TEFA#R&"Mass at launchSSFFA#R$ Mass in orbitOFIGA#RDimensionQFGA#R Solar arrayYIGGA#R0 Stabilization3 axisTGGHA#R&DC power3700 W]GHA#R8$Design lifetime15 years&GHH# 0 HH'  C-bandYHSIA#R0(Main transponders14ZHIA#R2,Backup transponders4OSIIA#RPower50 WUIQJA#R(Bandwidth36 MHz@IJA#RCoverage1 single beam for Europe, Africa, Middle East, AsiaTQJ&KA#R&EIRP max36 dBWVJ|KA#R*G/T max-3.5 dB/K\&KKA#R6Polarizationlinear H/VA|K[LB#TFrequenciesuplink: 6.425-6.725 GHzdownlink: 3.400-3.700 GHzG#KL$ FBeacon: 3.698 GHz, 6 dBW globalR+[LL' V C-band transponder frequency chart (GHz)gLM# ( T r  Vertical UplinkVertical DownlinkTransponderHorizontal DownlinkHorizontal UplinkLxNt#,3.43016.455MOt#,(6.45583.430xNOt#,3.47026.495O"t#,(O"6.49593.470Ot#,3.51036.535"7t#.*6.535103.510t#,3.55046.5757Lt#.*6.575113.550ւt#,3.59056.615Lat#.*6.615123.590ւ냭t#,3.63066.655avt#.*6.655133.630냭t#,3.67076.695vt#.*6.695143.6701 '  Ku-bandYA#R0(Main transponders30[pA#R4,Backup transponders10PA#RPower100 WUpA#R(Bandwidth36 MHzm,A#RXCoverageat least South Africa and IndiaTևA#R&EIRP max54 dBWT*A#R&G/T max+2 dB/K\ևA#R6Polarizationlinear H/Va*)B#TFrequenciesuplink: 13.75-14.00 & 14.00-14.25 GHzdownlink: 10.950-11.200 & 11.450-11.700 GHz&O# 1)1WVԉT+Oԉ) "VȠ$To view this page you need to register&# ; ԉ51Z[W5|ɭPanamsat 8G|5 :&" Panamsat 875# (Also called PAS 81 |䊭'  GeneralY=G#^$") Designationf%䊭A#RJLaunch dateplanned in early-1998t'=M#jN"N ,㹌לCountry of originUnited Stateso"M#jD"H̀‰MissionTelecommunicationsg&팭A#RL,Geostationary orbit166E or 43W?jWM#j:" &㉓gLaunch vehicleProtonQ팭A#R Launch site\WA#R6"Mass at launch~3500 kg&*# 8b' "(OTechnical data8*' " Specificationsi(bA#RP&Prime contractorSpace Systems/LoralUXA#R(PlatformFS 1300TA#R&"Mass at launchSX A#R$ Mass in orbit O[A#RDimensionQ A#R Solar arrayY[A#R0 Stabilization3 axisTYA#R&DC power3700 W]A#R8$Design lifetime15 years&Y# 0 ­'  C-bandYe­A#R0(Main transponders24Z ­­A#R2,Backup transponders8Oe­íA#RPower50 WU­cíA#R(Bandwidth36 MHzN ííA#RCoverageTcíĭA#R&EIRP max40 dBWSíXĭA#R$G/T max0 dB/K\ĭĭA#R6Polarizationlinear H/V=Xĭ3ŭB#TzFrequenciesuplink: 5.925-6.425 GHzdownlink: 3.7-4.2 GHzG#ĭzŭ$ FBeacon: 3.702 GHz, 6 dBW global1 3ŭŭ'  Ku-bandYzŭƭA#R0(Main transponders24Zŭ^ƭA#R2,Backup transponders8PƭƭA#RPower100 WU^ƭǭA#R(Bandwidth36 MHzN ƭQǭA#RCoverageTǭǭA#R&EIRP max54 dBWTQǭǭA#R&G/T max-2 dB/K\ǭUȭA#R6Polarizationlinear H/VCǭȭB#TFrequenciesuplink: 14.00-14.50 GHzdownlink: 12.250-12.750 GHz&Uȭɭ# 1ȭ1ɭ1WX1ɭɭɭT+ɭɭ) "VȠ$To view this page you need to register&1ɭɭ# ; ɭɭ1l?[[Yɭ-ʭhͭPanamsat 9Gɭ-ʭ5 :&" Panamsat 9D!ɭqʭ# BAlso called Galaxy 13 or PAS 91 -ʭʭ'  GeneralYqʭʭG#^$") Designation`ʭ[˭A#R>Launch dateplanned in 1999t'ʭ˭M#jN"N ,㹌לCountry of originUnited Stateso"[˭>̭M#jD"H̀‰MissionTelecommunications]˭̭A#R8,Geostationary orbit72Wj>̭ͭM#j:" &2!Launch vehicleArianec?̭hͭ$ ~should be an HS-702 with 48 Ku- and 12 C-band transponders.1ͭͭ1WZͭͭέT+hͭͭ) "VȠ$To view this page you need to register&ͭέ# < ͭOέ1[[.Z[OέέPanamsat 10Mέέ5 :2" Panamsat 10 & 11AOέέ# <Also called PAS 10 & PAS 111 έϭ'  GeneralYέgϭG#^$") Designatione$ϭϭA#RHLaunch dateboth before May 2002t'gϭLM#jN"N ϭLέ,㹌לCountry of originUnited Stateso"ϭM#jD"H̀‰MissionTelecommunicationsg&L"A#RL,Geostationary orbit125W and 58W\~G#^*" &Launch vehicleY"G#^$Launch site&~# 85' "(OTechnical data1 f'  Ka-bandY5A#R0(Main transponders24YfA#R0,Backup transponders[sA#R4Power40 & 60 W (TWTA)UA#R(Bandwidth54 MHzf%s.A#RJCoveragemultiple steerable spotsN |A#REIRP max\.A#R6Polarizationlinear H/VM|gB#TFrequenciesUplink: 28.35-28.6 and 29.5-30.0 GHz Downlink: 19.7-20.2 GHz\8$ pOnboard switching for at least half the transponders1g1W\HnT+H) "VȠ$To view this page you need to register&n# 7H1uM\]Pansat? n2 4"  Pansat ( Petite Amateur Navy SatelliteSmall, spread-spectrum communication satellite developed by the Naval Postgraduate School (NPS) as an educational project for officer students. Will be a tumbling spacecraft with a weight of 75 kg to be completed in 1996. To be launched by the Shuttle (STS 86?).The spacecraft will supply direct-sequence, spread-spectrum modulation with an operating center frequency of 436.5 MHz, a bit rate of 9600 bits per second and 4 MB of message storage.1  % Through use by the amateur radio community PANSAT will supply a means to demonstrate spread-spectrum communications. In addition, PANSAT provides many potential applications for low-cost communications. The low probability-of-intercept would be an important feature for the military in downed-pilot-rescues. The pilot could obtain his/her location through a GPS system and uplink the information to the orbiting satellite at low risk. Examples of civilian uses include emergency rescue and communication to remote areas.hC % Upload: 435.250 -- 437.750 MHzDownload: 435.250 -- 437.750 MHz< ' *O External resourcesX1  ' bhttp://www.sp.nps.navy.mil/pansat/pansat.html8 R ' "(OTechnical data8 ' " SpecificationsVR A#R*&Prime contractorN . A#RPlatformT A#R&"Mass at launchS. A#R$ Mass in orbitO $A#RDimensionQ uA#R Solar arrayS$A#R$ StabilizationN uA#RDC power\rA#R6$Design lifetime2 years&# 1r1[^)@O@T+)@) "VȠ$To view this )@page you need to register&O@# ?)@@1\]_@@Program: Parus?O@@, ((" Program: ParusP@B2 2=  剂Means sailRussian military navigation program. The constellation is made of 1 satellite per plane on 6 planes spaced by 30. The first Parus spacecraft was Cosmos 0700, launched in 1974. The system was operational in November 1976. The Tsikada system is a civilian counterpart.B@_B' 6 Occupation of the planesBBGC#  , B X n Plane 1Plane 2Plane 3Plane 4Plane 5Plane 6_B^D#0^150.03 MHz400.08 MHz149.91 MHz399.76 MHz149.94 MHz399.84 MHz149.97 MHz399.92 MHz150.03 MHz400.08 MHz149.94 MHz399.84 MHzGCD# O^DE#ڀ6PjCosmos 0778Cosmos 0789Cosmos 0726Cosmos 0864Cosmos 0700Cosmos 0755ODF#ڀ6PjCosmos 0971Cosmos 0951Cosmos 0887Cosmos 0996Cosmos 0894Cosmos 0928OEyG#ڀ6PjCosmos 1141Cosmos 1089Cosmos 0991Cosmos 1091Cosmos 0985Cosmos 1011OFMH#ڀ6PjCosmos 1275Cosmos 1225Cosmos 1072Cosmos 1153Cosmos 1104Cosmos 1150OyG!I#ڀ6PjCosmos 1308Cosmos 1386Cosmos 1181Cosmos 1349Cosmos 1244Cosmos 1333OMHI#ڀ6PjCosmos 1417Cosmos 1531Cosmos 1295Cosmos 1459Cosmos 1344Cosmos 1428O!IJ#ڀ6PjCosmos 1513Cosmos 1610Cosmos 1464Cosmos 1605Cosmos 1577Cosmos 1535OIK#ڀ6PjCosmos 1634Cosmos 1709Cosmos 1448Cosmos 1802Cosmos 1725Cosmos 1550QJyL#怢6P (wnCosmos 1759Cosmos 1904Cosmos 1627Cosmos 1934Cosmos 1821Cosmos 1598OKMM#ڀ6PjCosmos 1891Cosmos 2074Cosmos 1745Cosmos 2016Cosmos 1864Cosmos 1704OyL!N#ڀ6PjCosmos 2004Cosmos 2184Cosmos 2026Cosmos 2100Cosmos 2034Cosmos 1808UMM O#2x:T%xrd(wCosmos 2135Cosmos 2310Cosmos 2154Cosmos 2173Cosmos 2142Cosmos 1959Y!N#",x n3x>+x\,xz ,xCosmos 2266Cosmos 2341Cosmos 2218Cosmos 2239Cosmos 2233Cosm OO@os 20612 O؀#d"3x $(H3xFJCosmos 2327Cosmos 2336Cosmos 2180'#N"F3x $(,0,xCosmos 2334Cosmos 2279؀A#:(s3x"(,04Cosmos 2346fЂ) "3xAt least Cosmos 660, 807, 1064, 2321 were Parus satellites but failed to reach the correct orbit.8A' "(OTechnical data/Ђ7'  Orbit[A#R4"Perigee/Apogee1000 kmT7惮A#R&Inclination83S9A#R$Period105 minB惮A#R Orbital cycle3 days (same ground tracks every 41 revolutions)&9℮# 8' " Specificationsg&℮A#RL&Prime contractorPO Polyot of OmskXمA#R.PlatformMusson bus[4A#R4"Mass at launch1550 kgSمA#R$ Mass in orbitu44A#RhDiameter~ 2 m (cylinder shape with a long mast)A~A#RHeight1.4 m for the first birds, then 2 m (without the mast)SчA#R$ StabilizationN ~A#RDC powerUчtA#R($Design lifetime"? L .<:n!!&Broadcast in VHF and UHF at frequencies around 150 and 400 MHzParus, Tsikada, Nadezhda, Kurs,Informator and GEO-IK all use the same basic bus, although Parus has older design systems and tends not to last as long.1tlj1W`ljAT+) "VȠ$To view this page you need to register&ljA# 7x1\]ax ʮPASI 17 A, (" PASI 1P-x# ZThe name Agila 1 will eventually remain...1 0'  GeneralYG#^$") Designationg&0A#RLLaunch dateplanned on 31 Dec 1996i"YG#^D"N ,Country of originPhilippinefP#p,(₭`gOperatorPASIo"Y.M#jD"H̀‰MissionTelecommunicationsC#T,Geostationary orbit153E or 161E (both have been coordinated)It was also reported that the 144E slot could be "shared" with Indonesiaj.hM#j:" &2!Launch vehicleAriane) The project is led by the government together with firms like: Philippine Telegraph and Telephone, Smart Communications, Globe Telecom, Eastern telecommunication Philippines, etc. Domsat Holdings Inc holds over 60%.2 satellites (identical) and 2 ground control stations (in Manila and Cebu, $16.5 million) ordered from Aerospatiale (PASI 1: $97 million, PASI 2: $hA73 million). The second satellite is a ground spare (the primary satellite will be delivered in orbit)Launch cost: $78 millionEh* $6#oPASI 0 is Gorizont 298 ' "(OTechnical data8C' " Specificationsb! A#RB&Prime contractorAerospatiale[C®A#R4PlatformSpacebus 3000[[®A#R4"Mass at launch2560 kgS®®A#R$ Mass in orbitY[®îA#R0Dimension7.3 m high\®cîA#R6Solar array26.3 m spanSîîA#R$ StabilizationYcîĮA#R0DC powerEOL: 4750 W]îlĮA#R8$Design lifetime15 years&ĮĮ# 0 lĮĮ'  C-bandYĮŮA#R0(Main transponders26YĮtŮA#R0,Backup transpondersK ŮŮA#RPowerOtŮƮA#RBandwidthq.ŮƮC#V\CoverageWest: IndiaEast: USNorth: ChinaN ƮƮA#REIRP maxRƮǮA#R"Polarization&ƮEǮ# 1 ǮvǮ'  Ku-bandYEǮǮA#R0(Main transponders12YvǮ(ȮA#R0,Backup transpondersK ǮsȮA#RPowerO(ȮȮA#RBandwidthN sȮɮA#RCoverageN Ȯ^ɮA#REIRP maxRɮɮA#R"PolarizationY5^ɮ ʮ$ jOne transponder will be donated to the government1ɮ:ʮ1Wb:ʮʮʮT+ ʮʮ) "VȠ$To view this page you need to register&:ʮʮ# Aʮʮ1r]^cʮBˮˮProgram: PegasusMʮBˮ5 :2}n" Program: PegasusAʮˮ# <American scientific program1Bˮˮ1dˮ/̮{:ˮ/̮A Rt ROPQProgram: PegasusPegasus 1Pegasus 2Pegasus 3: ˮi̮1F^ei̮̮@Pegasus 1F/̮̮5 :$}n" Pegasus 11 i̮̮'  Generalg ̮GͮG#^@") Designation01085 / 65009A\̮ͮA#R6Launch date16 Feb 1965t'GͮήM#jN"N ,㹌לCountry of originUnited States5ͮήM#jj"H̀@0pMissionScientific: observation of meteorites^ήήA#R:"Perigee/Apogee510/726 kmVήMϮA#R*Inclination31.7RήϮA#R"Period97 min\MϮ G#^*" &Launch vehicleϮ /̮_ϮkA#R<Launch siteCape Canaveral& # 5k'  End of lifeVA#R*Decay17 Sep 1978$@" : z1]^fz?Pegasus 2F@5 :$}n" Pegasus 21 z'  Generalg XG#^@") Designation01381 / 65039A\A#R6Launch date25 May 1965t'X(M#jN"N ,㹌לCountry of originUnited States5M#jj"H̀@0pMissionScientific: observation of meteorites^(A#R:"Perigee/Apogee502/740 kmV^A#R*Inclination31.7RA#R"Period97 min\^ G#^*" &Launch vehicle_kA#R<Launch siteCape Canaveral& # 5k'  End of lifeUA#R(Decay3 Nov 1979$?" : y1F^gy@ Pegasus 3F?5 :$}n" Pegasus 31 y'  Generalg WG#^@") Designation01467 / 65060A\A#R6Launch date30 Jul 1965t'W'M#jN"N ,㹌לCountry of originUnited States5M#jj"H̀@0pMissionScientific: observation of meteorites^' A#R:"Perigee/Apogee441/449 kmV] A#R*Inclination28.9T A#R&Period93.4 min\] G#^*" &Launch vehicle_ l A#R<Launch siteCape Canaveral& # 5l '  End of lifeU  A#R(Decay4 Aug 1969$ @ " 7 w 1 ]Q^hw @Pegsat7 @ , (" Pegsat1 w '  Generalg F G#^@") Designation20546 / 90028A[ A#R4Launch date5 Apr 1990t'F  M#jN"N ,㹌לCountry of originUnited States~1 M#jb"H߲̀-MissionScientific: high atmosphere study^ A#R:"Perigee/Apogee395/500 kmV GA#R*Inclination94.1T A#R&Period93.5 minn!G M#jB" &GKTLaunch vehiclePegasus #1[dA#R4Launch siteVandenbergZ A#R2"Mass at launch191 kg&d @#  @@ <H@' *O External resourcesc< @@' xhttp://uss-enterprise.bu.edu/BUSPACE/CRRES/crrespro.html6H@@1^^i@AFPole6 @A, (" PoleI @`A) "@ Means "Prliminaire EOLE"1 AA'  Generalg `AAG#^@") Designation04801 / 70109A\ATBA#R6Launch date12 Dec 1970m ABM#j@"N ,㱭+Country of originFranceRTBCA#R"OperatorCNES~1BCM#jb"H߲̀-MissionScientific: high atmosphere study^CCA#R:"Perigee/Apogee634/750 kmTCCDA#R&Inclination15TCDA#R&Period98.6 minn!CDEM#jB" &A͉Launch vehicleDiamant #6YD^EA#R0"Mass at launch58 kgW3EE$ fFirst geodetic satellite on an equatorial orbit5^EE'  End of life_EIFA#R<"Out of service23 Mar 1972VEFA#R*Decay16 Jun 1980$IFF" 9FF1Q^1_jF5GPhase 3D9 F5G, (" Phase 3D1 FfG'  GeneralY5GGG#^$") Designationd#fG#HA#RFLaunch dateplanned in Jun 1997_GHG#^0"N ,Country of origino"#HHM#jD"H̀㓉MissionTelecommunicationsc"HTIA#RD"Perigee/Apogee4000 / 47000 kmVHIA#R*Inclination63.4L TIIA#RPeriodlIbJM#j>" &2!Launch vehicleAriane 4QIJA#R Launch site&bJJ# <JK' *O External resourcesW0JlK' `http://www.amsat.org/amsat/sats/phase3d.html8KK' "(OTechnical data8lKK' " Specifications^K:LA#R:&Prime contractorAMSAT-DLN KLA#RPlatformt3:LLA#Rf"Mass at launch~ 500 kg (including 250 kg fuel)SLOMA#R$ Mass in orbitOLMA#RDimensionQOMMA#R Solar arrayYMHNA#R0 Stabilization3 axisUMNA#R(DC power~ 600 WUHNNA#R($Design lifetime{WNmO$ Orbit control with GPS (12 antennas); capable of computing it's own Kepler elementsFNO' > Uplink frequency chart (MHz)2mOix#dn  OiF* P UplinkDigitalAnalog PassbandCenter&Oc#Ln<15 mnone21.210 - 21.25021.2305ic#jn 2X2 m145.800 - 145.840145.840 - 145.990145.9157$c#nn6\70 cm435.300 - 435.550435.550 - 435.800435.675@ǂc#nBl23 cm (1)1269.000 - 1269.2501269.250 - 1269.5001269.375@$jc#nBl23 cm (2)1268.075 - 1268.3501268.325 - 1268.5751268.450@ǂ c#nBl13 cm (1)2400.100 - 2400.3502400.350 - 2400.6002400.475@jc#nBl13 cm (2)2449.200 - 2446.4502446.450 - 2446.7002446.575; Nc#vn8b6 cm5668.300 - 5668.5505668.550 - 5668.8005668.675&t# H!N' B Downlink frequency chart (MHz)4thx#hn  . T DownlinkDigitalAnalog PassbandCentervކc#&n"10 m29.3301hrc#bn .P2 m145.955-145.990145.805-145.955145.8803ކc#fn2T70 cm435.900-436.200435.475-435.725435.6008rc#pn6\13 cm2400.650-2400.9502400.225-2400.4752400.350<Bc#xn8b3 cm10451.450-10451.75010451.025-10451.27510451.150>㉯c#|n<f1.5 cm24048.450-24048.75024048.025-24048.27524048.150&B # 7㉯@'   Beacons (MHz)y ^#6n  Beacon 1Beacon 2d@R#t$n 2 mnonenonelR#t4n"70 cm435.450435.850nR#t8n$13 cm2400.2002400.600ofR#t:n$3 cm10451.00010451.400q׌R#t>n(1.5 cm24048.00024048.400&f# 1׌.1Wk.T+) "VȠ$To view this page you need to register&.# 4܍1^_l܍įPMG4, (" PMG<܍L# 2Plasma Motor Generator1 }'  Generalg L䎯G#^@") Designation22701 / 93042Bh'}LA#RNLaunch date26 Jun 1993 at 13:27 UTt'䎯M#jN"N ,㹌לCountry of originUnited StatesfL2G#^>"H̀2MissionTether experiment^A#R:"Perigee/Apogee192/850 kmT2A#R&Inclination26L 0A#RPeriodp#M#jF" &p㉂Launch vehicleDelta 2 7925_0A#R<Launch siteCape Canaveralį- (RThe PMG experiment uses somewhat different hardware from the Seds deployer, although it is for the most part built by the same groups. The PMG tether remained attached to the Delta stage.PMG was launched with a 500m conducting tether containing a copper cable. The tether deployer and end mass contained a xenon gas dispenser to complete a 0.1 kV electrical circuit through the tether with a 0.3 amp current, in a 6-hour experiment to study space tethers' electrodynamic properties.<Rį' *O External resourcese>įį' |http://liftoff.msfc.nasa.gov/academy/tether/past_uses.html8Rįį1N1__mį'ůDƯPolaire8 į'ů, (" Polaire5į\ů'  End of life^'ůůA#R:"Out of service5 Dec 1971f%\ů ƯA#RJCauseLaunch failure (Diamant B4)$ůDƯ" 6 ƯzƯ1_J`nzƯƯPolar6 DƯƯ, (" Polar1 zƯƯ'  Generalg ƯHǯG#^@") Designation23802 / 96013Ah'ƯǯA#RNLaunch date24 Feb 1996 at 11:24 UTt'Hǯ$ȯM#jN"N ,㹌לCountry of originUnited StatesZǯ~ȯG#^&OperatorNASAH$ȯɯM#j"H̀d;plMissionScientific: magnetosphere study (auroral plasma physics)T~ȯgɯA#R&"Perigee/ApogeeTɯɯA#R&Inclination86L gɯʯA#RPeriodo"ɯvʯM#jD" &p㉂Launch vehicleDelta 2 #33ʯ*ͯ- (a͉Launched under the MELVS contract (Medium Expendable Launch Vehicle Services, between NASA and McDonnell Douglas)Polar is one of two spacecraft in NASA's Global Geospace Science (GGS) mission, which is part of the International Solar-Terrestrial Physics program. Polar and a sister spacecraft, Wind 1, will perform simultaneous, coordinated measurements of key regions of Earth's space environment. Included are observations of the entry and transport of solar plasma over Earth's magnetic poles, imaging of the northern aurora (Northern Lights), and investigations of solar wind properties. Polar was built by Lockheed Martin Astro Space.<vʯfͯ' *O External resourcesh*ͯͯ. ,http://ggsfot.gsfc.nasa.gov/words/polar.htmlhttp://uss-enterprise.bu.edu/BUSPACE/POLAR/polar.html&fͯ"ί# 8ͯZί' "(Technical data:"ίH ^u      Polar carries two booms and 6 long wire antennae. In the 'equatorial' plane of the satellite are a pair of antennae spanning 130 meters and, at right angles, another pair of antennae spanning 100 meters. Along the spin axis of the satellite are another pair of antennae with a span of 14 meters. These antennae are used to study electric and magnetiZίDƯc fields for the PWI (Plasma Wave Investigation) and EFI (Electric Field Instrument) experiments. Two larger but shorter (6 m long) booms carry more PWI instruments and the MFE (Magnetic Field Experiment). nZίVq             Other instruments:TIMAS (Toroidal Imaging Mass-Angle Spectrograph) to study fluxes of ions as a function of directionTIDE (Thermal Ion Dynamics Experiment) and PSI (Plasma Source Instrument) which study connections between the polar ionosphere and the magnetotailVIS (Visible Imaging System) and UVI (Ultraviolet Imager) which measure auroral emissions.PIXIE (Polar Ionospheric X-ray Imaging Experiment) studies X-rays produced by energetic electrons in the upper atmosphere. M> J    CAMMICE (Charge and Mass Magnetospheric Ion Composition Experiment) studies the isotopic composition of energetic ions. CEPPAD (Comprehensive Energetic Particle Pitch Angle Distribution) studies high energy protons and electrons.(JSR)Telemetry: 2265.0 MHz (realtime: 55.6 kbps, playback: 512 kbps)Command: 2085.688 MHz7V1V_`oOt Pollux7 O, (" Pollux5# $Also called D5A1 O'  Generalg G#^@") Designation07801 / 75039A\xA#R6Launch date17 May 1975m M#j@"N ,㱭+Country of originFranceo(xTG#^P"H̀MissionTechnology experimentation_A#R<"Perigee/Apogee299/1256 kmTTA#R&Inclination30U\A#R(Period100.4 mino"M#jD" &A͉Launch vehicleDiamant #11Y\$ A#R0"Mass at launch37 kgx * $ )Must test a hydrazin motor. Counterpart of the first Pollux that was destroy at launch with Castor on 22 May 1973.5$ '  End of lifeU P A#R(Decay5 Aug 1975$ t " 6P 11J` p HPosat6 t , (" PosatK" + ) "D䵟Also called PO-28 or Oscar 281 \ '  Generalg + G#^@") Designation22829 / 93061G\\  A#R6Launch date25 Sep 1993o" M#jD"N ,މCountry of originPortugalk C J#d" OperatorConsorcio Po-SAT of the LNETI (Laboratorio Nacional de Engenhario e Technologia Industrial)o" M#jD"H̀㓉MissionTelecommunications^C A#R:"Perigee/Apogee787/803 kmV fA#R*Inclination98.7UA#R(Period100.8 minn!f)M#jB" &D+Launch vehicleAriane V59[A#R4"Mass at launch45.5 kgz):@0 0SFirst Portuguese satellite. Built by Surrey's University. Is very similar :@t to Kitsat B with a GPS reception system.<v@' *O External resourcesb;:@@' vhttp://www.ee.surrey.ac.uk/CSER/UOSAT/research/gps.html8v@A' "(OTechnical data8@HA' " Specifications>AAG#^|& Prime contractorSSTL (Surrey Satellite Technology Ltd.)RHABA#R"PlatformSSTL[AzBA#R4"Mass at launch50.5 kgSBBA#R$ Mass in orbitRzBCA#R"Length352 mmQBpCA#R Width356 mmRCCA#R"Height670 mmc"pC%DA#RD Stabilizationgravity gradientN CsDA#RDC power\%DDA#R6$Design lifetime5 years&sDD# K$D@E' H Transponder frequency chart (MHz),DE^#X "JLDownlink freq.Transponder/BeaconMode)@E]Fj#R145.975JD 9600 bps FSK (Primary)+EFj#V145.925JD 9600 bps FSK (Secondary)&]FG# *FG^#T FHUplink freq.Transponder/BeaconMode)G3Hj#R435.075JD 9600 bps FSK (Primary)+GHj#V435.050JD 9600 bps FSK (Secondary)$3HH" 6H"I1 aq"IXIȁProba6 HXI, (" ProbaC "II# @Project for On Board Autonomy1 XII'  GeneralYI%JG#^$") DesignationZIJA#R2Launch dateJune 2000m %JJM#j@"N ,4"Country of originEurope_JKKG#^0"H̀MissionScientificTJKA#R&"Perigee/ApogeeQKKKA#R InclinationL KDimension0.8 x 0.6 x 0.6 mO HQO^A#R Solar arrayS A#R$ StabilizationN ^A#RDC power\#R6$Design lifetime3 yearsmIȁ$ Has a 25 m resolution spectrometer and a radiation and dust detectors1[1WrMsT+ȁM) "VȠ$To view this page you need to register&s# 9M16`cs傰ꇰProspero9 s傰, (" Prospero4# "Also called X31 傰J'  Generalg G#^@") Designation05580 / 71093A\J A#R6Launch date28 Oct 1971u(M#jP"N ,R׉Country of originUnited Kingdomo( G#^P"H̀MissionTechnology experimentation_PA#R<"Perigee/Apogee531/1402 kmTA#R&Inclination82UPA#R(Period104.4 minr%kM#jJ" &XىLaunch vehicleBlack Arrow #4YĆA#R0"Mass at launch66 kgfkN$ Designed and operated by the RAE. Only satellite launched by a British rocket. Tested solar cells.8Ć' "(OTechnical datad?Nꇰ% ~Transmits on 137.56 MHzspin stabilized, 4 rpm11 m diameter9#1cat#\:ưRadarsat9 ꇰ\, (" Radarsat1 #'  Generalg \G#^@") Designation23710 / 95059A[OA#R4Launch date4 Nov 1995m M#j@"N ,xW Country of originCanadao%O+J#dJOperatorCanadian Space AgencykM#j<"H̀郉MissionRemote sensingl++A#RV"Perigee/Apogee783/787 km (polar orbit)VXA#R*Inclination98.6SA#R$Period100 minp#XM#jF" &p㉂Launch vehicleDelta 2 #229[vA#R4"Mass at launch2750 kg[7 <T@^gl^gLaunched under the MELVS contractRadarsat is a cooperative program between the Canadian Space Agency, NASA and NOAA. The Canadian Space Agency built and operated the satellite; NASA furnished the launch. In exchange, U.S. government agencies will have access to all archived Radarsat data and have approximately 15% of the satellite's observing time.The satellite is worth $640 million dollars Canadian and the launch about $50 million.Radarsat International, Inc. will be the commercial distributor of Radarsat data worldwide. Lockheed Martin has distribution rights in the United States.1 v9' O ContactjЏ- *Canadian Space AgencyTel: +1-514-926-4436Fax: +1-514-926-4973Email: coord@adro.radar1.sp-agency.ca1 9 ' O ContactЏ ꇰЏ1 05RadarSat International (RSI)275 Slater Street, Suite 1203Ottawa, Ontario K1P5H9CanadaTel: +1-613-238-6413Fax: +1-613-238-5425http://www.rsi.ca/< ' *O External resourcesQ. ,http://adro.radar1.sp-agency.ca/http://www.ball.com/aerospace/radrsat.html8' "(OTechnical data8°' " Specificationsm,p°A#RX&Prime contractorSpar Aerospace (Canada)N °°A#RPlatform\p°ðA#R6"Mass at launch3150 kg?Y°sðA#R0Payload mass1500 kgOððA#RDimensionZsðİA#R2Solar array18 m spanSðoİA#R$ StabilizationTİİA#R&DC power2200 W\oİŰA#R6$Design lifetime5 yearsİ:ư+ $15 m long x 1.5 m wide Synthetic Aperture C-band RadarResolution: between 30 m and 90 mOn-board storage: 96 MBUplink: S-band (2 kbps)Downlink: S-band (2.5, 2, 4, 32 or 128 kbps)Another downlink for science data is at: 2230.000 MHz7Űqư1+aauqưư̰Radcal7 :ưư, (" Radcal9qưư# ,Also known as P92-11 ưǰ'  Generalg ưyǰG#^@") Designation22698 / 93041Ah'ǰǰA#RNLaunch date25 Jun 1993 at 23:30 UTt'yǰUȰM#jN"N ,㹌לCountry of originUnited StatesfǰȰG#^>"H̀MissionRadar calibration^UȰɰA#R:"Perigee/Apogee751/884 kmVȰoɰA#R*Inclination89.5UɰɰA#R(Period101.2 minn!oɰ2ʰM#jB" &g'KLaunch vehicleScout #117YɰʰA#R0"Mass at launch87 kge2ʰ̰' Was built by Defense Systems Inc. for the USAF Space Test ProgramRadcal carries a C-band transponder operating on the same frequency as the radars, and a GPS navigation package so that its orbit can be precisely determined. This calibration will allow the Space Command radars to determine orbital positions of other satellites to within a few metres.<ʰS̰' *O External resourcesO(̰̰' Phttp://www.cta-space.com/s19-00.html; S̰̰1F abv̰ͰRadiosat 1;̰Ͱ, ( " Radiosat 11 ̰IͰ'  GeneralYͰͰG#^$") Designation`IͰΰA#R>Launch dateplanned in 1999t'ͰvΰM#jN"N ,㹌לCountry of originUnited Stateso"ΰΰM#jD"H̀‰MissionTelecommunications]vΰBϰA#R8,Geostationary orbit80WlΰϰM#j>" &2!Launch vehicleAriane 5.Bϰ' Program composed of 4 GEO satellites operϰ̰ated by CD Radio Inc. It will broadcast digital radio in the continental US. Was granted an FCC license ($83.3 million paid), slots: 80W & 110W. The system should cost $500 million. CD Radio acquired $105 million from Arianespace Finance S.A. to help financing the projectThe fourth satellite will serve as a ground spare. An option on a 4th satellite is also available. At the same time (Aug 1997) Loral announced to have invested $25 million in CD Radio (approx 15%)K!ϰ3* $BHIts competitor will be AMRC1 d' O ContactwJ3- *CD Radio, Inc.Washington DC, USAhttp://www.cdradio.com/NASDAQ:CDRD8d' "(OTechnical data8K' " SpecificationsZA#R2&Prime contractorSS/LUKA#R(PlatformFS-1300[UA#R4"Mass at launch3500 kgSA#R$ Mass in orbitOUA#RDimensionQHA#R Solar arrayYA#R0 Stabilization3-axisN HA#RDC power]LA#R8$Design lifetime15 yearsA$ :downlink: 2320-2332.5 MHz1L1Ww8T+) "VȠ$To view this page you need to register&8# @x1ahxxProgram: RadugaL85 :0c+" Program: Radugax, &%xMeans rainbowSoviet telecommunication program. The payloads are Statsionar (C-band), Gals (X-band, 7.25-7.75 GHz) and maybe Volna (L-band).11Uy  =) "( -Program: Raduga N#js5oހ5oމ5oމ5oމ5oމ5oމ5oމ5oމ5oމ=4oމ44oމ54oމ64oމ74oމ84oމl94oމ:4oމ;4oމ<4oމh4oމ_4oމ`4oމa4oމb4oމc4oމd4oމe4oމf4oމg4oމ4oމfւ4oމ4oމ4oމƭ\ƭ\ƭ\Raduga 01Raduga 02Raduga 03Raduga 04Raduga 05Raduga 06Raduga 07Raduga 08Raduga 09Raduga 10Raduga 11Raduga 12Raduga 13Raduga 14Raduga 15Raduga 16Raduga 17Raduga 18Raduga 19Raduga 20Raduga 21Raduga 22Raduga 23Raduga 24Raduga 25Raduga 26Raduga 27Raduga 28Raduga 29Raduga 30Raduga 31Raduga 32Raduga 33Raduga 1-1Raduga 1-2Raduga 1-3$ " 1 L 1zL = # 4Raduga's specifications\L A#R60&Prime contractorNPO PMT 9 A#R&0PlatformRaduga[ A#R40"Mass at launch1965 kgN 9 A#R0DiameterL .A#R0HeightY A#R00 Stabilization3 axisT.A#R&0DC power1300 Wa <A#R@0$Design lifetime3 to 5 yearsd@$ No North-South stabilisation. Equipped 1 X-band transponder.1<1W{1@W@T+1@) "VȠ$To vi1@ew this page you need to register&W@# 11@@1U|@C(C5W@@# $Raduga's C-bandX@AA#R.0(Main transponders3Y@nAA#R00,Backup transpondersVAAA#R*0Power15 W (TWTA)UnABA#R(0Bandwidth36 MHz};ABB#Tv00Coverage andEIRP maxhemispheric beam (9x18): 32 dBWn,BCB#TX0PolarizationRHCP: downlinkLHCP: uplink$B(C" 1CYC1W}YCCCT+(CC) "VȠ$To view this page you need to register&YCC# : C D1<?b~ DSD^HRaduga 01FCSD5 :$c+" Raduga 011 DD'  Generalg SDDG#^@") Designation08513 / 75123A\DGEA#R6Launch date22 Dec 1975jDEM#j:"N , Country of originCISo"GE FM#jD"H̀‰MissionTelecommunicationst-EFG#^Z,4Geostationary orbitStatsionar-01, 75En! FGM#jB" &㉓gLaunch vehicleProton #56&F(G# 5G]G'  End of lifeW(GGA#R,"Out of serviceyes&]GG# 8GH' "(Technical dataLG^H0 08W_'dSpecificationsC-band: HH1<bzbHHLRaduga 02F^HH5 :$c+" Raduga 021 HI'  Generalg HvIG#^@") Designation09416 / 76092A\IIA#R6Launch date11 Sep 1976jvI") Designation12618 / 81069\ȱɱA#R6Launch date30 Jul 1981jYɱʱM#j:"N , Country of originCISo"ɱʱM#jD"H̀‰MissionTelecommunicationsa ʱʱA#R@,Geostationary orbit??? 25En!ʱ]˱M#jB" &㉓gLaunch vehicleProton #90&ʱ˱# 5]˱˱'  End of lifeW˱̱A#R,"Out of serviceyes&˱5̱# 8̱m̱' "(Technical dataL5̱̱0 08W_'dSpecificationsC-band: m̱̱1?9cWḏ9ͱhRaduga 10F̱9ͱ5 :$c+" Raduga 101 ̱jͱ'  Generalg 9ͱͱG#^@") Designation12897 / 81102A[jͱ,αA#R4Launch date9 Oct 1981jͱαM#j:"N , Country of originCISo",αϱM#jD"H̀‰MissionTelecommunicationst-αyϱG#^Z,4Geostationary orbitStatsionar-02, 35En!ϱ M#jB" &㉓gLaunch vehicleProton #91yϱ ̱&yϱ2# 5 g'  End of lifeW2A#R,"Out of serviceyes&g# 8' "(Technical dataLh0 08W_'dSpecificationsC-band: 1fcdMRaduga 11Fh5 :$c+" Raduga 111 '  Generalg G#^@") Designation13669 / 82113A\A#R6Launch date26 Nov 1982jFM#j:"N , Country of originCISo"M#jD"H̀‰MissionTelecommunicationst-F)G#^Z,4Geostationary orbitStatsionar-02, 35Eo"M#jD" &㉓gLaunch vehicleProton #102Y)A#R0Launch siteTyuratam&# 5L'  End of lifeWA#R,"Out of serviceyes&L# 8' "(Technical dataLM0 08W_'dSpecificationsC-band: 1<Wdd Raduga 12FM5 :$c+" Raduga 121 '  Generalg eG#^@") Designation13974 / 83028A[A#R4Launch date8 Apr 1983je*M#j:"N , Country of originCISo"M#jD"H̀‰MissionTelecommunicationst-* G#^Z,4Geostationary orbitStatsionar-03, 85Eo"| M#jD" &㉓gLaunch vehicleProton #107& # 5| '  End of lifeW . A#R,"Out of serviceyes& T # 8. ' "(Technical dataLT 0 08W_'dSpecificationsC-band:  1=d"d X dRaduga 13F X 5 :$c+" Raduga 131  '  Generalg X G#^@") Designation14307 / 83088A\ L A#R6Launch date25 Aug 1983j M#j:"N , Country of originCISo"L % M#jD"H̀‰MissionTelecommunicationst- G#^Z,4Geostationary orbitStatsionar-09, 45Eo"% M#jD" &㉓gLaunch vehicleProton #112& .# 5c'  End of lifeW.A#R,"Out of serviceyes&c# 8' "(Technical dataLd0 08W_'dSpecificationsC-band: 1Pd*d @DRaduga 14Fd @5 :$c+" Raduga 14 @d1 =@'  Generalg @@G#^@") Designation14725 / 84016A\=@AA#R6Launch date15 Feb 1984j@jAM#j:"N , Country of originCISo"AAM#jD"H̀‰MissionTelecommunicationst-jAMBG#^Z,4Geostationary orbitStatsionar-03, 85Eo"ABM#jD" &㉓gLaunch vehicleProton #116&MBB# 5BC'  End of lifeWBnCA#R,"Out of serviceyes&CC# 8nCC' "(Technical dataLCD0 08W_'dSpecificationsC-band: CRD1>"dgdRDDHRaduga 15FDD5 :$c+" Raduga 151 RDD'  Generalg D0EG#^@") Designation15057 / 84063A\DEA#R6Launch date22 Jun 1984j0EEM#j:"N , Country of originCISo"EeFM#jD"H̀‰MissionTelecommunicationsu.EFG#^\,4Geostationary orbitStatsionar-15, 128Eo"eFIGM#jD" &㉓gLaunch vehicleProton #122&FoG# 5IGG'  End of lifeWoGGA#R,"Out of serviceyes&G!H# 8GYH' "(Technical dataL!HH0 08W_'dSpecificationsC-band: YHH1;*ddH%I/MRaduga 16FH%I5 :$c+" Raduga 161 HVI'  Generalg %IIG#^@") Designation15946 / 85070A[VIJA#R4Launch date8 Aug 1985jIJM#j:"N , Country of originCISo"JJM#jD"H̀‰MissionTelecommunicationst-JeKG#^Z,4Geostationary orbitStatsionar-09, 45En!JKM#jB" &㉓gLaunch vehicleProton#134&eKK# 5K.L'  End of lifeWKLA#R,"Out of serviceyes&.LL# 8LL' "(Technical dataLL/M0 08W_'dSpecificationsC-band: LiM1=gdyeiMMׁRaduga 17F/MM5 :$c+" Raduga 171 iMM'  Generalg MGNG#^@") Designation16250 / 85107A\MNA#R6Launch date15 Nov 1985jGN OM#j:"N , Country of originCISo"N|OM#jD"H̀‰MissionTelecommunicationst- O G#^Z,4Geostationary orbitStatsionar-02, 35E|O /Mo"|O{M#jD" &㉓gLaunch vehicleProton #137& # 5{ր'  End of lifeW-A#R,"Out of serviceyes&րS# 8-' "(Technical dataLSׁ0 08W_'dSpecificationsC-band: 1=deWcRaduga 18FׁW5 :$c+" Raduga 181 '  Generalg WG#^@") Designation16497 / 86007A\KA#R6Launch date17 Jan 1986jM#j:"N , Country of originCISo"K$M#jD"H̀‰MissionTelecommunicationst-G#^Z,4Geostationary orbitStatsionar-08, 25Wo"$M#jD" &㉓gLaunch vehicleProton #139&-# 5b'  End of lifeW-A#R,"Out of serviceyes&b߅# 8' "(Technical dataL߅c0 08W_'dSpecificationsC-band: 1>yeeㆲRaduga 19Fcㆲ5 :$c+" Raduga 191 '  Generalg ㆲ{G#^@") Designation17046 / 86082A\ׇA#R6Launch date25 Oct 1986j{AM#j:"N , Country of originCISo"ׇM#jD"H̀‰MissionTelecommunicationsu.A%G#^\,4Geostationary orbitStatsionar-10, 170Wo"M#jD" &㉓gLaunch vehicleProton #145&%# 5'  End of lifeWFA#R,"Out of serviceyes&l# 8F' "(Technical dataLl0 08W_'dSpecificationsC-band: *1=e.e*p|Raduga 20Fp5 :$c+" Raduga 201 *'  Generalg pG#^@") Designation17611 / 87028A\dA#R6Launch date19 Mar 1987jΌM#j:"N , Country of originCISo"d=M#jD"H̀‰MissionTelecommunicationst-ΌG#^Z,4Geostationary orbitStatsionar-03, 85Eo"= M#jD" &㉓gLaunch vehicleProton #149&F# 5 {'  End of lifeWFҎA#R,"Out of serviceyes&{# 8Ҏ0' "(Technical dataL|0 08W_'dSpecificationsC-band: 01ee ŲRaduga 21F| 5 :$c+" Raduga 21 |1 ='  Generalg G#^@") Designation18631 / 87100A\=A#R6Launch date10 Dec 1987jjM#j:"N , Country of originCISo"M#jD"H̀‰MissionTelecommunicationsb!j;²A#RB,Geostationary orbitsee belowo"²M#jD" &㉓gLaunch vehicleProton #159&;²²# : ² ò- */ۀ Location²òm#:   " BeginEndPosition- ò1IJp#Z$(*4L: 10 Dec 1987Statsionar-15, 128E*òIJp#T 4?Statsionar-10, 170W, inclined&1IJIJ# 8IJ)Ų' "(Technical datak3IJŲ8 @fW_'dؕ$SpecificationsC-bandEIRP coverage (dBW)1)ŲŲ1ŲƲNŲƲ6 <2_4oހ"6Raduga 21's EIRP: ŲMƲ1.efeMƲƲ̲Raduga 22FƲƲ5 :$c+" Raduga 221 MƲƲ'  Generalg Ʋ+DzG#^@") Designation19596 / 88095A\ƲDzA#R6Launch date20 Oct 1988j+DzDzM#j:"N , Country of originCISo"Dz`ȲM#jD"H̀‰MissionTelecommunicationsb!DzȲA#RB,Geostationary orbitsee belowo"`Ȳ1ɲM#jD" &㉓gLaunch vehicleProton #172&ȲWɲ# : 1ɲɲ- */ۀ LocationWɲʲm#:   " BeginEndPosition,ɲʲp#X$(*4L: 20 Oct 1988Statsionar-02, 35E)ʲP˲p#R E4?Statsionar-27, 12E, inclined&ʲv˲# 8P˲˲' "(Technical datak3v˲̲8 @fW_'dSpecificationsC-bandEIRP coverage (dBW)1˲J̲1J̲̲N̲̲6 <2`4oހ"7Raduga 22's EIRP: J̲̲1ef̲ͲORaduga 23F̲Ͳ5 :$c+" Raduga 231 ̲IͲ'  Generalg ͲͲG#^@") Designation19928 / 89030A\IͲ βA#R6Launch date14 Apr 1989jͲvβM#j:"N , Country of originCISo" ββM#jD"H̀‰MissionTelecommunicationsb!vβGϲA#RB,Geostationary orbitsee belowo"βϲM#jD" &㉓gLaunch vehicleProton #176&Gϲϲ# : ϲ"- */ϲ"̲ۀ Locationϲm#:   " BeginEndPosition4"Pp#h$8:4L: 14 Apr 1989Jul 1995Statsionar-08, 25W.p#\,.4Sep 1995Jul 1996Statsionar-09, 45E&P# 5I'  End of life\A#R6"Out of serviceJul 1996&I# 8' "(Technical dataLO0 08W_'dSpecificationsC-band; 1sfe`fRaduga 1-1GO5 :&c+" Raduga 1-11 '  Generalg iG#^@") Designation20083 / 89048A\A#R6Launch date21 Jun 1989ji/M#j:"N , Country of originCISo"M#jD"H̀‰MissionTelecommunications~7/G#^n,H4Geostationary orbitStatsionar-20, 70E, inclinedo"M#jD" &㉓gLaunch vehicleProton #178&# 5'  End of lifed#JA#RF"Out of serviceyes, early 1997?&p# 8J' "(Technical datak3p8 @fW_'dnSSpecificationsC-bandEIRP coverage (dBW)1D1DO6 <4ƭ\"8Raduga 1-1's EIRP: D1=ff  Raduga 24F 5 :$c+" Raduga 241 D '  Generalg  G#^@") Designation20367 / 89098A\D  A#R6Launch date15 Dec 1989j q M#j:"N , Country of originCISo" M#jD"H̀‰MissionTelecommunicationst-q T G#^Z,4Geostationary orbitStatsionar-09, 45Eo" M#jD" &㉓gLaunch vehicleProton #183&T # 5  '  End of lifeW u A#R,"Out of serviceyes& # 8u ' "(Technical dataL  0 08W_'dSpecificationsC-band: Y 1`f|fY BRaduga 25F 5 :$c+" Raduga 251 Y '  Generalg 7G#^@") Designation20499 / 90016A\ A#R6Launch date15 Feb 1990j7M#j:"N , Country of originCISo"lM#jD"H̀‰MissionTelecommunicationst-G#^Z,H4Geostationary orbitStatsionar-20, 70Eo"l[@M#jD[@ " &㉓gLaunch vehicleProton #185&@# 5[@@'  End of life\@AA#R6"Out of serviceMar 1995a @sAA#R@CauseSent to the junk orbit&AA# 8sAA' "(Technical dataLAB0 08W_'dSpecificationsC-band: AWB1IfāfWBBFRaduga 26FBB5 :$c+" Raduga 261 WBB'  Generalg B5CG#^@") Designation21016 / 90112A\BCA#R6Launch date20 Dec 1990j5CCM#j:"N , Country of originCISo"CjDM#jD"H̀‰MissionTelecommunicationst-CDG#^Z,4Geostationary orbitStatsionar-03, 85Eo"jDMEM#jD" &㉓gLaunch vehicleProton #194&DsE# 5MEE'  End of lifec"sE FA#RD"Out of servicebefore Feb 1995&E1F# 8 FiF' "(Technical dataL1FF0 08W_'dSpecificationsC-band; iFF1B|ffF7GHMRaduga 1-2GF7G5 :&c+" Raduga 1-21 FhG'  Generalg 7GGG#^@") Designation21038 / 90116A\hG+HA#R6Launch date27 Dec 1990jGHM#j:"N , Country of originCISo"+HIM#jD"H̀‰MissionTelecommunicationsb!HfIA#RB,Geostationary orbitsee belowo"IIM#jD" &㉓gLaunch vehicleProton #195&fII# 2 I-J'  LocationIJm#:   " BeginEndPosition>-JeKp#|$8:B4L: 27 Dec 1990Jul 1996Statsionar-24, 49E, inclined&JK# 5eKK'  End of life\KLA#R6"Out of serviceAug 1996c"KLA#RDCausedrifting out of control?&LL# 8LL' "(Technical datak3LHM8 @fW_'d)%[SpecificationsC-bandEIRP coverage (dBW)1LyM1yMMOHMM6 <4ƭ\"8Raduga 1-2's EIRP: yMN1āfgNHN#Raduga 27FMHN5 :$c+" Raduga 271 NyN'  Generalg HNNG#^@") Designation21132 / 91014A\yN LjW_'dPdSpecificationsC-bandEIRP coverage (dBW)1ij8ų18ųųOųų6 <4ƭ\";Raduga 1-3's EIRP: 8ųų1&SgOgųƳ˳Raduga 31FųƳ5 :$c+" Raduga 311 ų8Ƴ'  Generalg ƳƳG#^@") Designation23010 / 94012Ah'8ƳdzA#RNLaunch date18 Feb 1994 at 07:56 UTjƳqdzM#j:"N , Country of originCISo"dzdzM#jD"H̀‰MissionTelecommunicationsb!qdzBȳA#RB,Geostationary orbitsee belowo"dzȳM#jD" &㉓gLaunch vehicleProton #221&Bȳȳ# : ȳɳ- */ۀ Locationȳɳm#:   " BeginEndPosition4ɳ?ʳp#h$8:4L: 18 Feb 1994Jul 1995Statsionar-09, 45Eɳʳj#:,.Mar 1996May 199683E?ʳN˳j#<,.Jul 1996Aug 1996105E&ʳt˳# 8N˳˳' "(Technical dataPt˳˳3 6:W_'dSpecificationsC-band: ˳6̳1g h6̳|̳'Raduga 32F˳|̳5 :$c+" Raduga 321 6̳̳'  Generalg |̳ͳG#^@") Designation23448 / 94087Ah'̳|ͳA#RNLaunch date28 Dec 1994 at 11:31 UTjͳͳM#j:"N , Country of originCISo"|ͳUγM#jD"H̀‰MissionTelecommunications9ͳγM#jr"/ۀ0H4Geostationary orbitStatsionar-20, 70E, inclinedo"UγJϳM#jD" &㉓gLaunch vehicleProton #231&γpϳ# 8Jϳϳ' "(Technical datas5pϳ'> LjW_'dSpecificationsC-bandϳ'˳EIRP coverage (dBW)1ϳX1XU'6 <@4oހ"8Raduga 32's C-band EIRP: X1Og-Raduga 33F-5 :$c+" Raduga 331 ^'  Generalg -G#^@") Designation23794 / 96010Aa ^&A#R@Launch date19 February 1996jM#j:"N , Country of originCISo"&M#jD"H̀‰MissionTelecommunications\[A#R6,Geostationary orbitn/ao"M#jD" &㉓gLaunch vehicleProton #240k[Z% The upper stage (Block-DM2) failed to restart after first burn to circularize the orbit. Thus the satellite remained in GTO. Failure analysis determined that at second ignition of the Block DM, the main engine experienced an emergency commanded shutdown. The probable cause of the failure was a pressure leak in the engine start system. The leak was most likely caused by an inadequate lockwire installation on a start system tube joint nut, which allowed the nut to back off under vibration. Corrective actions include increasing the lockwire diameter and adding a second, redundant lockwire to the affected joint.5'  End of life_ZA#R<"Out of service19 Feb 1996&# 8L' "(Technical dataP3 6:W_'dSpecificationsC-band@L1*bWh Program: Rascom@, (*" Program: RascomsI * "Regional African Satellite Communications OrganisationTelecommunication project by a group of African countries. It is aimed to deliver telecommunication services throughout Africa. The cost of the project is approx. $1.2 billionThe first satellite, Rascom 1, is expected to be in orbit in 2001. It should cost $200 million and be operational for 10 years. It should enable telephone service inside Africa and with the rest of the world.Rascom hopes to install 456,000 fixed solar-powered telephone stations with international access across the continent over a 7-year period.| - (CIxFor the moment the wannabe operators are leasing space to the Intelsat organizationRascom is based in Abidjan (Ivory Coast), it was established in May 1992 by over 40 African countries< ' *O External resources]6|  ' lhttp://www.intelsat.int/cmc/via/via0294.htm#RASCOM1 F 1WF T+ ) "VȠ$To view this page you need to register&F # ? 1+hY J DProgram: RelayK J 5 :.!" Program: RelaygD # American experimental telecommunication program operated by NASA.<J ' *O External resourcesW0 D' `http://sulu.lerc.nasa.gov/dglover/relay.html1 u1ub(D: DP㾩AProgram: RelayRelay 1Relay 21u1UBB<D# 2Relay's specificationsVA#R*0&Prime contractorN D @A#R0Platform @Ye@A#R00"Mass at launch80 kgS @@A#R$0 Mass in orbitL e@AA#R0LengthK @OAA#R0WidthL AAA#R0HeightXOAAA#R.0 StabilizationSpin?N AABA#R0DC powerUABA#R(0$Design lifetime$ABB" 1BB1UBEEH%B3C# JRelay's C-band (upload at 1.7 GHz)XBCA#R.0(Main transponders1Y3CCA#R00,Backup transpondersOC3DA#R0Power10 Wa CDA#R@0Bandwidth600 phone circuitsN 3DDA#R0CoverageN D0EA#R0EIRP maxRDEA#R"0Polarization$0EE" 8EE1@hE"F1KRelay 1DE"F5 : !" Relay 11 ESF'  Generalg "FFG#^@") Designation00503 / 62068A\SFGA#R6Launch date13 Dec 1962t'FGM#jN"N ,㹌לCountry of originUnited Stateso"GGM#jD"H̀㓉MissionTelecommunications`GYHA#R>"Perigee/Apogee1323/7433 kmVGHA#R*Inclination47.5UYHIA#R(Period185.1 minr%HvIM#jJ" &p㉂Launch vehicleThor Delta #15{WII$ Breaks down on 3 Jan 1963 because of an important power demand but could be mended.5vI&J'  End of lifea IJA#R@"Out of serviceFebruary 1965&&JJ# 8JJ' "(Technical dataLJ1K0 08 BzSpecificationsC-band8JiK1j3hiKKRelay 2D1KK5 : !" Relay 21 iKK'  Generalg KELG#^@") Designation00737 / 64003A\KLA#R6Launch date21 Jan 1964t'ELMM#jN"N ,㹌לCountry of originUnited Stateso"LMM#jD"H̀㓉MissionTelecommunications`MMA#R>"Perigee/Apogee1960/7541 kmVM:NA#R*Inclination46.4UMNA#R(Period194.7 minr%:NOM#jJ" &p㉂Launch vehicleThor Delta #23YNZOA#R0"Mass at launch86 kgN*OO$ TEnabled 10 to 70 minutes transmissions5ZOO'  End of life_OHA#R<OH1K"Out of service26 Sep 1965&On# 8H' "(Technical dataLn0 08 BzSpecificationsC-bandD61\Yzi6zProgram: Resource21Dz, (2" Program: Resource21+6( US program for a network of 4 satellites in LEO to do remote sensing. To be operational in 2000. Agriculture is the targeted business. The satellite should provide Multispectral imaging with 10 to 100 meter resolution.Company based in Denver, Colorado.1zւ1Wւ*PT+*) "VȠ$To view this page you need to register&ւP# 6*10iiiREX 26 P, (" REX 27# (Also called P94-21 $'  Generalg G#^@") Designation23814 / 96014A[$愴A#R4Launch date9 Mar 1996t'ZM#jN"N ,㹌לCountry of originUnited Statesi"愴ÅG#^D"H̀MissionMilitary: technologyRZA#R"OperatorUSAF`ÅuA#R>"Perigee/Apogee803 x 332 kmTɆA#R&Inclination90SuA#R$Period101 mint'ɆM#jN" &GKTLaunch vehiclePegasus #10 (XL)!' The payload, sponsored by USAF Rome Lab, will study ionospheric electron density irregularities that affect radio communications. A secondary experiment will use GPS for on-orbit attitude determination and control.Built by CTA/SS (formerly DSI)<툴' *O External resources|Ni. ,http://www.cta-space.com/s27-00.htmlhttp://www.te.plk.af.mil/rexii.html@툴1zijProgram: RocsatLi5 :0;" Program: Rocsatʊ& _Republic Of China SATellitesTaiwan's satellite program. This comprises ground equipment including dynamic testing provided by TRW. 3 satellites are planned (2 LEO, 1 GEO)<' *O External resources\ʊ. ,http://www.nspo.gov.tw/english/overvw.htmlhttp://www.nspo.gov.tw/english/mission.html11W;T+) "VȠ$To view this page you need to register&;# 1l1l㌴w6;㌴A Rl&H&Hꉂ&HꉂProgram: RocsatRocsat 1Rocsat 2Rocsat 39l1 iaLƴRocsat 1E㌴a5 :";" Rocsat 11 '  GeneralYa덴G#^$") Designation{:fA#RtLaunch dateplanned in Apr 1998 (but could be delayed)e덴ˎG#^<"N ,Country of originTaiwanz3fEG#^fOperatorNSPO (National Space Program Office)y,ˎM#jX"H̀?vMissionScientific: ionosphere studyTEA#R&"㌴Perigee/ApogeeQoA#R InclinationL A#RPeriodjo%M#j:" &bnW"Launch vehicleAthenaQvA#R Launch site%9´' 9Will carry science, imaging and experimental communications payloads (Ka-band)Contract worth $61 million for the satellite, $19 million for its launch<vu´' *O External resourcesW09´´' `http://www.nspo.gov.tw/english/rocsat-1.html8u´ô' "(OTechnical data8´<ô' " SpecificationsYôôA#R0&Prime contractorTRWN <ôôA#RPlatformZô=ĴA#R2"Mass at launch425 kgSôĴA#R$ Mass in orbitO=ĴĴA#RDimensionQĴ0ŴA#R Solar arraySĴŴA#R$ StabilizationN 0ŴŴA#RDC powerUŴ&ƴA#R($Design lifetime&ŴLƴ# 1&ƴ}ƴ1W}ƴƴƴT+Lƴƴ) "VȠ$To view this page you need to register&}ƴƴ# 9ƴ0Ǵ1ii0ǴuǴʴRocsat 2EƴuǴ5 :";" Rocsat 21 0ǴǴ'  GeneralYuǴǴG#^$") Designationi(ǴhȴA#RPLaunch dateno date yet, before 2003eǴȴG#^<"N ,Country of originTaiwanUhȴ"ɴG#^"H̀Mission^ȴɴA#R:,Geostationary orbit120E\"ɴɴG#^*" &Launch vehicleYɴ5ʴG#^$Launch sitevɴʴ& A 12-month study contract for this Ka-band satellite was granted to TRW. Should have 10 transponders in Ka-band15ʴ˴1W˴V˴|˴T+ʴV˴) "VȠ$To view this page you need to register&˴|˴# 9V˴˴1i˴˴ϴRocsat 3E|˴˴5 :";" Rocsat 31 ˴+̴'  GeneralY˴̴G#^$") Designation\+̴̴A#R6Launch dateearly 2000se̴EʹG#^<"N ,Country of originTaiwanU̴ʹG#^"H̀MissionTEʹʹA#R&"Perigee/ApogeeQʹ?δA#R InclinationL ʹδA#RPeriod\?δδG#^*" &Launch vehicleYδ@ϴG#^$Launch sitec?δϴ$ ~There should be 8 such satellites to study climate changes.1@ϴϴ1Zϴ4ZT+ϴ4) "VȠ$Toϴ4ϴ view this page you need to register&ϴZ# @41pij%Program: RohiniLZ5 :0" Program: Rohini?%# 8Indian scientific program1V1V`%B T㐋 ~OaEFProgram: RohiniRohini 1A: launch failure of 10 Aug 1979Rohini 1BRohini 2Rohini 3: V212Ej2xyRohini 1BFx5 :$" Rohini 1B72# (Also called RS E21 x'  Generalg GG#^@") Designation11899 / 80062A\A#R6Launch date18 Jul 1980lGM#j>"N ,&‰Country of originIndia_nG#^0"H̀MissionScientific^A#R:"Perigee/Apogee307/921 kmVn"A#R*Inclination44.7RtA#R"Period97 minl"M#j>" &#Launch vehicleSLV 3 #2Yt9A#R0"Mass at launch35 kgm$ First Indian satellite launched by an Indian rocket. Was used to measure the performance of the launcher.59'  End of lifeVUA#R*Decay20 May 1981$y" 9U1 jj Rohini 2Ey5 :"" Rohini 27.# (Also called RS D11 _'  Generalg .G#^@") Designation12491 / 81051A\_" A#R6Launch date31 May 1981l M#j>"N ,&‰Country of originIndia_" G#^0"H̀MissionScientificA o A#R"Perigee/Apogee188/419 km (296/834 km was the intended orbit)V A#R*Inclination46.2To  A#R&Period90.6 minl M#j>" &#Launch vehicleSLV 3 #3Y A#R0"Mass at launch38 kgB $ <Carried a land-mark sensor5 U '  End of lifeV A#R*Decay31 May 1981$U " 9  1EEj M nBRohini 3E M 5 :"" Rohini 37 # (Also called RS D21 M '  Generalg G#^@") Designation14002 / 83033A\ xA#R6Launch date17 Apr 1983lM#j>"N ,&‰Country of originIndia_xCG#^0"H̀MissionScientific^A#R:"Perigee/Apogee371/861 kmVC @A#R*Inclination46.6 @ T`@A#R&Period92.7 minl @@M#j>" &#Launch vehicleSLV 3 #4[`@'AA#R4"Mass at launch41.5 kg9@`A$ *Carried 2 cameras5'AA'  End of life_`AAA#R<"Out of service24 Sep 1984VAJBA#R*Decay17 Apr 1983$AnB" 7JBB1 jLkBByRorsat@nBB, (*" Program: RorsatWBpD4 6qiㅯ\&Radar Ocean Reconnaissance SatelliteRussian program part of the Cosmos constellation. Those satellites are observation satellites using a radar powered by a nuclear engine (50 kg uranium). They are designed to monitor activity of foreign navies. They have a short lifetime (3 to 4 months).32 spacecrafts launched, 2 already decayed!ABD' 4O Rorsat first generation+pDD$ 1965BDE% :(111)Cosmos 0102 (model)+DIE$ 1966BEE% :(067)Cosmos 0125 (model)+IEE$ 1967BEE% :(127)Cosmos 0198 (model)+E#F$ 1968BEeF% :(023)Cosmos 0209 (model)+#FF$ 1970BeFF% :(079)Cosmos 0367 (model)+FF$ 1971`8F]G( p(025)Cosmos 0402 (model)(117)Cosmos 0469 (model)+FG$ 1972T/]GG% ^(066)Cosmos 0516 (Buk nuclear engine test)+GH$ 1973T/G[H% ^(108)Cosmos 0626 (Buk nuclear engine test)+HH$ 1974\[H I( (029)Cosmos 0651 (Buk nuclear engine test)(032)Cosmos 0654 (Buk nuclear engine test)+H5I$ 1975zO II+ &(024)Cosmos 0723 (first operational)(025)Cosmos 0724(116)Cosmos 0785+5II$ 1976P(I*J( P(103)Cosmos 0860(104)Cosmos 0861+IUJ$ 1977d5*JJ/ .j(088)Cosmos 0952(090)Cosmos 0954 (decayed)BUJJ' 6O Rorsat second generationhEJcK# Those satellites separate from their fuel core once out of service+JK$ 1980:cKK% *(034)Cosmos 1176+KK$ 1981f;KYL+ &v(021)Cosmos 1249(037)Cosmos 1266(081)Cosmos 1299+KL$ 1982[YLM5 :w(043)Cosmos 1365(052)Cosmos 1372(084)Cosmos 1402 (decayed)(099)Cosmos 1412ALUM' 4O Rorsat third generationhEMM# Those satellites separate from their fuel core once out of service+UMM$ 1984P(M8N( P(069)Cosmos 1579(112)Cosmos 1607+McN$ 1985P(8NN( P(064)Cosmos 1670(075)Cosmos 1677+cNN$ 1986P(N.O( P(024)Cosmos 1736(062)Cosmos 1771+NYO$ 1987p.O . ,W!w(052)Cosmos 1860(101)Cosmos 1900 (is leaking coolant (sodium potassium) from its nuclear power source)YO nB+YO7$ 1988B y+ &.(w(019)Cosmos 1932171W$T+y) "VȠ$To view this page you need to register&$# 6Z1+ jZRosat6 $, (" Rosat6ZƁ# & Rntgen SATellit1 '  Generalg Ɓ^G#^@") Designation20638 / 90049A[A#R4Launch date1 Jun 1990n!^'M#jB"N , Country of originGermany{:A#RtOperatorDLR (German aerospace research establishment)x+'M#jV"H̀_BMissionScientific: X-ray astronomy^xA#R:"Perigee/Apogee538/553 kmT̄A#R&Inclination53Tx A#R&Period95.6 minp#̄M#jF" &p㉂Launch vehicleDelta 2 #195 i% iDesigned to produce an all-sky survey of some 100,000 X-ray sources, and first all-sky survey in the extreme ultraviolet (XUV) spectrum using the UK-provided Wide Field Camera.<' *O External resourcesW0i' `http://nssdca.gsfc.nasa.gov/rosat/rosat.html84' "(OTechnical data8l' " Specifications]4ɇA#R8&Prime contractorDornier[l$A#R4"Mass at launch2426 kgYɇ}A#R0Payload mass1555 kg`$݈A#R>Dimension2.4 x 2.1 x 4.5 m\}9A#R6Solar array4.7 x 8.9 mY݈A#R0 Stabilization3 axisY9뉵A#R0DC powerEOL: 1000 W^IA#R:$Design lifetime1.5 years\뉵A#R6&Telemetry - DataS-band&Iˊ# 9' $ X-ray telescope\ˊ`A#R6&Maximum aperture835 mmWA#R,Focal length2.4 mc"`A#RD*On-axis resolution1.8 arcsecsXrA#R.Wavelength0.6-1 mL($ PIt monitors soft 0.1-2.4 keV X-rays.<r' * Wield Field Camera\VA#R6&Maximum aperture576 mmXA#R.Focal length525 mm`VA#R>*On-axis resolution1 arcminXfA#R.Wavelength0.6-3 m$" @fʎ1; 0kʎ ɵProgram: Ruslan@ , (*" Program: Ruslan,ʎB&  Russian project for GEO telecommunication proposed by NPO Mashinostroyenie (NPO Mash). The 3 satellites would be launched from 2001, would weigh 2400 kg. They would relay digital TV and data throughout CIS. BAn additional satellite could be developped for DBS8 z' "(OTechnical data8B' " Specifications^zA#R:&Prime contractorNPO MashN ^A#RPlatformTA#R&"Mass at launchX^ µA#R.Paylaod mass550 kgOYµA#RDimensionQ µµA#R Solar arrayYYµõA#R0 Stabilization3 axisTµWõA#R&DC power5200 W]õõA#R8$Design lifetime10 years&Wõõ# 0 õ ĵ'  C-bandYõcĵA#R0(Main transponders37Y ĵĵA#R0,Backup transpondersUcĵŵA#R(Powerup to 30 WUĵfŵA#R(Bandwidth36 MHzb!ŵŵA#RBCoverage3 beams (7.5 x 3.5)J fŵƵA#REIRPRŵdƵA#R"Polarization&ƵƵ# 1 dƵƵ'  Ku-bandYƵǵA#R0(Main transponders24YƵmǵA#R0,Backup transpondersOǵǵA#RPower25 WOmǵ ȵA#RBandwidthSǵ^ȵA#R$CoveragespotsJ ȵȵA#REIRPR^ȵȵA#R"Polarization&ȵ ɵ# 1ȵQɵ1WQɵɵɵT+ ɵɵ) "VȠ$To view this page you need to register&Qɵɵ# 7ɵʵ1kkʵAʵϵRyusei? ɵAʵ2 4"  Ryuseid;ʵʵ) "v Also called OREX (Orbital Re-entry Experiment vehicle)1 Aʵʵ'  Generalg ʵ=˵G#^@") Designation22978 / 94007A[ʵ˵A#R4Launch date3 Feb 1994l=˵̵M#j>"N ,bCountry of originJapan[˵_̵G#^(OperatorNASDA_̵̵G#^0"H̀MissionTechnology^_̵͵A#R:"Perigee/Apogee457/449 kmV̵r͵A#R*Inclination30.5T͵͵A#R&Period93.5 minfr͵,εM#j2" &JLaunch vehicleH2&͵Rε# 5,εε'  End of lifed#RεεA#RFDecay5 Feb 1994 in the Pacific$εϵ" 5εDϵ10klDϵyϵS80T5 ϵyϵ, (" S80T1 Dϵϵ'  Generalg yϵG#^@") Designationϵϵ22078 / 92052C\ϵyA#R6Launch date10 Aug 1992m M#j@"N ,㱭+Country of originFranceRy8A#R"OperatorCNES_G#^0"H̀MissionScientific`8A#R>"Perigee/Apogee1302/1324 kmVMA#R*Inclination66.1UA#R(Period111.9 minn!MM#jB" &D+Launch vehicleAriane V52&6# 8n' "(OTechnical data86' " Specificationsf%n A#RJ&Prime contractorClub ESIE EspaceS_A#R$PlatformUoSATY A#R0"Mass at launch50 kgV_A#R*Payload mass7 kgb!pA#RBDimension0.7 x 0.35 x 0.35 mSA#R$ Stabilization`p#A#R>DC powerConsummation: 41 W\A#R6$Design lifetime3 yearsW3#$ fFrequencies: uplink: 148 MHz, downlink: 137 MHz6 1 kl B CSAC B6 B, (" SAC BN( & P Satelite de Aplicaciones Cientificas1 B'  General?NN#l~") !SUDesignation24645 / 96061AFailed to separate with HETE[A#R4Launch date4 Nov 1996p#N M#jF"N ,㉕U剂Country of originArgentina_x G#^0"H̀MissionScientificd# A#RF"Perigee/Apogee550 km, circularTx 0 A#R&Inclination38T A#R&Period95.6 minr%0 M#jJ" &GKTLaunch vehiclePegasus XL #14T/ J % _Cooperative project between NASA and Argentinas National Commission of Space Activities (CONAE). The satellite is designed to advance the study of solar physics and astrophysics through the examination of solar flares, gamma ray bursts, diffuse X-ray cosmic background, and energetic neutral atoms. < ' *O External resourcesJ f 6 :Uhttp://www.conae.gov.ar/sac-prueba.htmlhttp://pao.gsfc.nasa.gov/gsfc/service/gallery/fact_sheets/spacesci/sacb.htmhttp://www.astro.psu.edu/xray/cubic/SAC-B.html& # 8f ' "(OTechnical data8 ' " SpecificationsV RA#R*&Prime contractors2 A#RdPlatformdesigned and constructed in ArgentinaZRA#R2"Mass at launch181 kgSrA#R$ Mass in orbitOA#RDimensionQr@A#R @Solar arraySq@A#R$ StabilizationN @@A#RDC power\q@AA#R6$Design lifetime3 years@ C( Telemetry & data: 2255.5 MHz (realtime: 0.032 kbps, playback: 50, 100 or 200 kbps)Command: 2076.9 MHz (0.992 kbps)Primary ground operations should have been performed by the Argentine Mission Operations Control Center (MOCC) located in San Miguel (just outside of Buenos Aires) which incorporates a 3.6-meter antenna system used for tracking, telemetry, telecommand and data acquisition and which is collocated and integrated with the MOCC systems.6A@C1ll@CvCGSAC C6 CvC, (" SAC C1 @CC'  GeneralYvCDG#^$") DesignationYCYDA#R0Launch datemid 1999p#DDM#jF"N ,㉕U剂Country of originArgentina_YD(EG#^0"H̀MissionScientificTD|EA#R&"Perigee/ApogeeQ(EEA#R InclinationL |EFA#RPeriodkEFM#j<" &p㉂Launch vehicleDelta 2FTG' SWill carry CCD cameras to study earth resourcesSAC A is a technological payload to be launched in July 1998 with STS 88. It might be attached to some other payload<FG' *O External resourcesU.TGG' \http://www.conae.gov.ar/sac-c/folleto.html1GH1WHjHHT+GjH) "VȠ$To view this page you need to register&HH# ?jHH1l/mHI Program: SafirKHI5 :. >P" Program: SafirHI) e Satellite For Information RelayProgram of OHB System (Bremen, Germany) with 6 satellites (3 stand-alone and 3 piggybacked). The 3 satellites are planned in 1997, 1998, 1999@I5J' 2(OStand-alone satellites1 IfJ'  General^5JJA#R:"Perigee/Apogee678/696 kmVfJKA#R*Inclination98.4RJlKA#R"Period98 minTKKA#R&Uplinks401 MHzVlKLA#R*Downlinks400 MHz&K"N ,bCountry of originJapano"ĶtŶM#jD"H̀‰MissionTelecommunications^ŶŶA#R:,Geostationary orbit135Es&tŶEƶM#jL" &p㉂Launch vehicleThor Delta #137ZŶƶA#R2"Mass at launch350 kg&Eƶƶ# 5ƶƶ'  End of lifeWƶQǶA#R,"Out of serviceyes$ƶuǶ" : QǶǶ1m6mǶǶ̶Sakura 2AFuǶǶ5 :$ր" Sakura 2A7Ƕ,ȶ# (Also called CS 2A1 Ƕ]ȶ'  Generalg ,ȶȶG#^@") Designation13782 / 83006A[]ȶɶA#R4Launch date4 Feb 1983lȶɶM#j>"N ,bCountry of originJapano"ɶɶM#jD"H̀‰MissionTelecommunications^ɶXʶA#R:,Geostationary orbit132EfɶʶM#j2" &JLaunch vehicleN2ZXʶ˶A#R2"Mass at launch350 kg&ʶ>˶# 5˶s˶'  End of lifeW>˶˶A#R,"Out of serviceyes&s˶˶# 8˶(̶' "(OTechnical data;˶c̶' ( Ka-band 20/30 GHzX(̶̶A#R.i"Phone circuits4000$c̶̶" : ̶Ͷ1$ԁmnͶ_ͶUSakura 2BF̶_Ͷ5 :$ր" Sakura 2B7ͶͶ# (Also called CS 2B1 _ͶͶ'  Generalg Ͷ.ζG#^@") Designation14248 / 83081A[ͶζA#R4Launch date5 Aug 1983l.ζζM#j>"N ,bCountry of originJapano"ζd϶M#jD"H̀‰MissionTelecommunications^ζ϶A#R:,Geostationary orbit136Efd϶4M#j2" &϶4̶JLaunch vehicleN2Z϶A#R2"Mass at launch350 kg&4# 5'  End of lifeW@A#R,"Out of serviceyes&f# 8@' "(OTechnical data;f' ( Ka-band 20/30 GHzX1A#R.i"Phone circuits4000$U" : 116mneSakura 3AFU5 :$ր" Sakura 3A7 # (Also called CS 3A1 ='  Generalg G#^@") Designation18877 / 88012A\=A#R6Launch date19 Feb 1988llM#j>"N ,bCountry of originJapano"M#jD"H̀‰MissionTelecommunications^l9A#R:,Geostationary orbit132EfM#j2" &JLaunch vehicleH1&9# 5'  End of life\VA#R6"Out of serviceSep 1996TA#R&Causedeorbited&V# 8' "(Technical data]&e7 >LWf*(dw#SpecificationsC-bandKa-band: 1nqSakura 3BFe5 :$ր" Sakura 3B7# (Also called CS 3B1 M'  Generalg G#^@") Designation19508 / 88086A\M A#R6Launch date16 Sep 1988l| M#j>"N ,bCountry of originJapano" M#jD"H̀‰MissionTelecommunicationsb!| M A#RB,Geostationary orbitsee belowf M#j2" &JLaunch vehicleH1&M # 2 '  Location m#:   " BeginEndPosition$ # j#H$8:L: 16 Sep 1988Feb 1997136E j#<,.Mar 1997Nov 1997154E&# # 5  '  End of life\ b A#R6"Out of serviceNov 1997T A#R&Causedeorbited&b # 8 ' "(Technical data]& q7 >LWf*(dw#SpecificationsC-bandKa-band71}mnGSampex7 q, (" SampexqNP# Also called Solar Anomalous and Magnetospheric Particle Explorer and SMEX 11 '  Generalg P @G#^@") Designation22012 / 92038A @q[g@A#R4Launch date3 Jul 1992t' @@M#jN"N ,㹌לCountry of originUnited Statesx+g@SAM#jV"H̀jMissionScientific: Sun observation^@AA#R:"Perigee/Apogee550/675 kmTSABA#R&Inclination82RAWBA#R"Period96 miniBBM#j8" &g'KLaunch vehicleScout]WBAC$ To conduct studies of solar, anomalous, galactic, and magnetospheric energetic particles.<B}C' *O External resourcesbAC D. ,http://sunland.gsfc.nasa.gov/smex/sampex/http://lepsam.gsfc.nasa.gov/www/public_sampex.html8}CED' "(OTechnical data8 D}D' " SpecificationsVEDDA#R*&Prime contractorN }D!EA#RPlatformZD{EA#R2"Mass at launch157 kgW!EEA#R,Payload mass40 kgO{E!FA#RDimensionQErFA#R Solar arrayS!FFA#R$ StabilizationSrFGA#R$DC power100 W[FsGA#R4$Design lifetime1 yearR-GG% ZDownlink: S-band, 900 kbpsUplink: 2 kbpsCsGH1|noHWHHProgram: San MarcoOGWH5 :6ԭYl" Program: San MarcoK(HH# PItalian high atmosphere study program1WHH1HI^HIO nrJj77777Program: San MarcoSan Marco 1San Marco 2San Marco 3San Marco 4San Marco 5< HI1nIJNSan Marco 1HIJ5 :(ԭYl" San Marco 11 I5J'  Generalg JJG#^@") Designation00957 / 64084A\5JJA#R6Launch date15 Dec 1964lJdKM#j>"N ,xECountry of originItaly~1JKM#jb"H߲̀-MissionScientific: high atmosphere study^dK@LA#R:"Perigee/Apogee200/846 kmVKLA#R*Inclination37.8T@LLA#R&Period95.1 minm LWMM#j@" &g'KLaunch vehicleScout #35ZLMA#R2"Mass at launch115 kg&WMM# 5M N'  End of lifeVMbNA#R*Decay13 Sep 1965$ NN" < bNN1:n oN OSan Marco 2HN O5 :(ԭYl" San Marco 21 N;O'  Generalg OOG#^@") Designation02761 / 67038A\;O A#R6Launch date26 Apr 1967O NlOxM#j>"N ,xECountry of originItaly~1 M#jb"H߲̀-MissionScientific: high atmosphere study^xTA#R:"Perigee/Apogee219/741 kmUA#R(Inclination2.9TTA#R&Period94.2 minm jM#j@" &g'KLaunch vehicleScout #52ZĂA#R2"Mass at launch128 kg?j$ 6First equatorial launch5Ă8'  End of lifeVA#R*Decay14 Oct 1967$8" < 1n[o6San Marco 3H65 :(ԭYl" San Marco 31 g'  Generalg 6΄G#^@") Designation05176 / 71036A\g*A#R6Launch date24 Apr 1971l΄M#j>"N ,xECountry of originItaly~1*M#jb"H߲̀-MissionScientific: high atmosphere study^rA#R:"Perigee/Apogee222/707 kmUdžA#R(Inclination3.2TrA#R&Period93.8 minm džM#j@" &g'KLaunch vehicleScout #72Z⇷A#R2"Mass at launch161 kg&# 5⇷='  End of lifeVA#R*Decay29 Nov 1971$=" < 1 oo;San Marco 4H;5 :(ԭYl" San Marco 41 l'  Generalg ;ӉG#^@") Designation07154 / 74009A\l/A#R6Launch date18 Feb 1974lӉM#j>"N ,xECountry of originItaly~1/M#jb"H߲̀-MissionScientific: high atmosphere study^wA#R:"Perigee/Apogee270/875 kmŰA#R(Inclination2.9Tw A#R&Period96.1 minm ̋M#j@" &g'KLaunch vehicleScout #85Z 猷A#R2"Mass at launch164 kg& # 5猷B'  End of lifeU A#R(Decay4 May 1976$B" < 1[o?·San Marco 5H?5 :(ԭYl" San Marco 51 p'  Generalg ?׎G#^@") Designation19013 / 88026A\p3A#R6Launch date25 Mar 1988l׎M#j>"N ,xECountry of originItaly~13)M#jb"H߲̀-MissionScientif)ic: high atmosphere study^A#R:"Perigee/Apogee268/625 kmS)A#R$Inclination3T.A#R&Period93.5 minn!M#jB" &g'KLaunch vehicleScout #109Z.A#R2"Mass at launch235 kgE!;·$ BDesigned by Rome's university5p·'  End of lifeU;··A#R(Decay6 Dec 1988$p··" 5·÷1Ono÷S÷q˷Sara5 ·S÷, (" SaraK(÷÷# PSatellite Amateur de Radio Astronomie1 S÷÷'  Generalg ÷6ķG#^@") Designation21578 / 91050E\÷ķA#R6Launch date17 Jul 1991m 6ķķM#j@"N ,㱭+Country of originFrancex+ķwŷM#jV"H̀_BMissionScientific: radio astronomy^ķŷA#R:"Perigee/Apogee755/764 kmVwŷ+ƷA#R*Inclination98.4Sŷ~ƷA#R$Period100 minn!+ƷƷM#jB" &`D+Launch vehicleAriane V44Y~ƷEǷA#R0"Mass at launch28 kgƷǷ% Must study Jupiter's radio environment by listening in the 2-15 MHz range. It is controlled and received at Nanay in France<EǷ&ȷ' *O External resourcesXǷȷ. ,http://w3.teaser.fr/~mzirnheld/sara.htmhttp://w3.teaser.fr/~mzirnheld/esieesp.htm8&ȷȷ' "(OTechnical data8ȷɷ' " Specifications{:ȷɷA#Rti&Prime contractorClub ESIEE Espace (built by students)YɷɷA#R0i"Mass at launch28 kgXɷHʷA#R.i Mass in orbit20 kgc"ɷʷA#RDiDimension0.34 x 0.34 x 0.34 m]Hʷ˷A#R8i$Design lifetime11 yearsiEʷq˷$ Telemetry beacon: 145.955 MHz, 300 bps FSK, FM, 0.5 W transmitter@˷˷1op˷˷Program: Sarsat@q˷˷, (*" Program: Sarsat ˷ηK d 㹌לxW 㱭+ SSearch And Rescue Satellite Aided TrackedInternational cooperation program with the United States, Canada, France and since 1979 the CIS which made its Cospas system compatible.Mission: search and rescue of persons and boats in distress. The service started on 1 Sep 1982. In 1995 28 earth stations and 15 control centers in 16 countries were operational.The system uses reception beacons operating at 121.5 MHz, 243 MHz and at 406 MHz. When a distress signal is received 1544.5 MHz can be heard. Polar orbiting satellites can detect and localize beacons whereas geostationary satellites can't localize them. Thus beacons to work with geostationary birds have to include a GPS receptor.U.˷SϷ' \O Satellites carrying a Sarsat-Cospas payloadη  { {.Y {R򲟉S򲟉T򲟉G@cG@c.U򲟉vEo\ {.83082NOAA 08 (EOL)8SϷq˷4123NOAA 0987022Goes 0788089NOAA 1189050Nadezhda 190017Nadezhda 291019Nadezhda 392041Insat 2A93048Insat 2B94022Goes 0894041Nadezhda 494082Luch 094089NOAA 1495025Goes 09O)SϷ8& RFuture satellites:Nadezhda 5NOAA 15<t' *O External resourcess8. ,http://psbsgi1.nesdis.noaa.gov:8080/SARSAT/homepage.htmlhttp://www.dot.gov/dotinfo/uscg/factfile/SARSAT.html@tU1oـtU,Program: SatcomL5 :0?" Program: Satcom`U,+ &D"Also called RCA (former owner)American telecommunication program operated by GE Americom.1]1q]@, ހqZ>0*-?0*-@0*-A0*q-s-t-]--Program: SatcomSatcom 1Satcom 1RSatcom 2Satcom 2RSatcom 3Satcom 3RSatcom 4Satcom C1Satcom C3Satcom C4Satcom C5 (Aurora 2)Satcom K1Satcom K21]1UOs; # 0Satcom 1 & 2's C-bandYbA#R00(Main transponders24Y A#R00,Backup transpondersK bA#R0PowerU[A#R(0Bandwidth36 MHzN A#R0CoverageT[A#R&0EIRP max32 dBWROA#R"0Polarization$s" 1O1U < ?s# 8Satcom K's specificationsd#GA#RF0&Prime contractorGE Astro SpaceUA#R(0PlatformGE 4000[GA#R40"Mass at launch1930 kgZQ A#R20 Mass in orbit1050 kgb! A#RB0Dimension1.7 x 2.13 x 1.52 mWQ A#R,0Solar array19.3 mY c A#R00 Stabilization3 axisY A#R00DC powerBOL: 3000 W\c  A#R60$Design lifetime10 year$ < " 1 m 1Um %8< # *Satcom K's Ku-bandYm A#R00(Main transponders16Z X A#R20,Backup transponders4V A#R*0Power47 W (TWTA)UX  A#R(0Bandwidth54 MHzN Q A#R0CoverageT A#R&0EIRP max48 dBW\Q A#R60Polarizationlinear H/V$ %" 1V1VS%6 <<?"<Satcom C3 & C4's EIRP9V1w=q'xCSatcom 1E'5 :"?" Satcom 11 X'  Generalg 'G#^@") Designation08479 / 75117A\X'@A#R6'@Launch date13 Dec 1975t'@M#jN"N ,㹌לCountry of originUnited Stateso"'@ AM#jD"H̀‰MissionTelecommunications]@gAA#R8,Geostationary orbit80Ws& AAM#jL" &p㉂Launch vehicleThor Delta #118ZgA4BA#R2"Mass at launch465 kg&AZB# 54BB'  End of lifeWZBBA#R,"Out of serviceyes&B C# 8BDC' "(Technical data4 CxC) "LC-band: DCC1P 0rqCC.Satcom 1RFxCC5 :$?" Satcom 1R:C2D# .Also called Satcom 61 CcD'  Generalg 2DDG#^@") Designation13984 / 83030A\cD&EA#R6Launch date11 Apr 1983t'DEM#jN"N ,㹌לCountry of originUnited Stateso"&E FM#jD"H̀‰MissionTelecommunicationsb!EkFA#RB,Geostationary orbitsee belows& FFM#jL" &p㉂Launch vehicleThor Delta #167_kF=GA#R<Launch siteCape Canaveral&FcG# 2 =GG'  LocationcGHm#:   " BeginEndPositionGHj#8$(*L: 11 Apr 1983139W"H1Ij#D46< May 1992May 1992 >131W&HWI# 51II'  End of lifeWWIIA#R,"Out of serviceyes&I J# 8IAJ' "(OTechnical data8 JyJ' " Specificationsd#AJJA#RF&Prime contractorGE Astro SpaceUyJ2KA#R(PlatformGE 3000[JKA#R4"Mass at launch1120 kga 2KKA#R@ Mass in orbitapprox. 600 kgRK@LA#R"Length1.63 mQKLA#R Width1.32 mR@LLA#R"Height0.99 m]L@MA#R8Solar array14.33 m spanYLMA#R0 Stabilization3 axisN @MMA#RDC power]MDNA#R8$Design lifetime10 years&MjN# 0 DNN'  C-bandYjNNA#R0(Main transponders24ZNMOA#R2,Backup transponders4PNOA#RPower8.5 WUMO A#R(Bandwidth36 MHzO xCN OZA#RCoverageT A#R&EIRP max36 dBW\Z A#R6Polarizationlinear H/V$." 9 g1cNpqgއSatcom 2E.5 :"?" Satcom 21 g݁'  Generalg DG#^@") Designation08774 / 76029A\݁A#R6Launch date26 Mar 1976t'DM#jN"N ,㹌לCountry of originUnited Stateso"M#jD"H̀‰MissionTelecommunicationsb!僸A#RB,Geostationary orbitsee belows&XM#jL" &p㉂Launch vehicleThor Delta #121_僸A#R<Launch siteCape Canaveral&X݄# 5'  End of lifeW݄iA#R,"Out of serviceyes&# 2 i'  LocationKm#:   " BeginEndPositionцj#8$(*L: 26 Mar 1976119W{KLj#"198472W&цr# 8L' "(Technical data4 rއ) "LC-band: 1 pt^ĸSatcom 2RFއ^5 :$?" Satcom 2R:# .Also called Satcom 71 ^Ɉ'  Generalg 0G#^@") Designation14328 / 83094A[ɈA#R4Launch date8 Sep 1983t'0M#jN"N ,㹌לCountry of originUnited Stateso"nM#jD"H̀‰MissionTelecommunications]ˊA#R8,Geostationary orbit72Ws&n>M#jL" &p㉂Launch vehicleThor Delta #172_ˊA#R<Launch siteCape Canaveral&>Ë# 5'  End of life\ËTA#R6"Out of serviceMar 1995a A#R@CauseSent to the junk orbit&Tی# 8' "(OTechnical data8یK' " Specificationsd#A#RF&Prime contractorGE Astro SpaceUKA#R(PlatformGE 3000[_A#R4"Mass at launch1120 kga A#R@ Mass in orbitapprox. 600 kgR_A#R"Length1.63 mQcA#R Width1.32 mRA#R"Height0.99 mXcA#R.Solar arrއay14.33 mYrA#R0 Stabilization3 axisN A#RDC power\rA#R6$Design lifetime10 year&B# 0 r'  C-bandYBA#R0(Main transponders24Zr%¸A#R2,Backup transponders4Pu¸A#RPower8.5 WU%¸¸A#R(Bandwidth36 MHzN u¸øA#RCoverageT¸løA#R&EIRP max36 dBW\øøA#R6Polarizationlinear H/VK!løĸ* $B#ھTransponder frequency chart9øLĸ1n=qDqLĸĸȸSatcom 3Eĸĸ5 :"?" Satcom 31 Lĸĸ'  Generalg ĸ)ŸG#^@") Designation11635 / 79101A[ĸŸA#R4Launch date7 Dec 1979t')ŸŸM#jN"N ,㹌לCountry of originUnited Stateso"ŸgƸM#jD"H̀‰MissionTelecommunications\ŸƸA#R6,Geostationary orbitn/as&gƸ6ǸM#jL" &p㉂Launch vehicleThor Delta #150_ƸǸA#R<Launch siteCape Canaveral&6ǸǸ# 5ǸǸ'  End of life^ǸNȸA#R:"Out of service7 Dec 1979\ǸȸA#R6CauseSatellite failure$Nȸȸ" : ȸɸ1Z q0rɸNɸzSatcom 3RFȸNɸ5 :$?" Satcom 3R1 ɸɸ'  Generalg NɸɸG#^@") Designation12967 / 81114A\ɸBʸA#R6Launch date20 Nov 1981t'ɸʸM#jN"N ,㹌לCountry of originUnited Stateso"Bʸ%˸M#jD"H̀‰MissionTelecommunications^ʸ˸A#R:,Geostationary orbit131Ws&%˸˸M#jL" &p㉂Launch vehicleThor Delta #158_˸U̸A#R<Launch siteCape Canaveral&˸{̸# 5U̸̸'  End of lifeW{̸͸A#R,"Out of serviceyes&̸-͸# 8͸e͸' "(OTechnical data8-͸͸' " Specificationsd#e͸θA#RF&Prime contractorGE Astro SpaceU͸VθA#R(PlatformGE 3000[θθA#R4"Mass at launch1070 kga VθϸA#R@ Mass in orbitapprox. 600 kgQθcϸA#R Length1.6 mQϸϸA#R Width1.27 mRcϸA#R"Height1.ϸȸ29 m\ϸnA#R6Solar array11.2 m spanYA#R0 Stabilization3 axisN nA#RDC power]rA#R8$Design lifetime10 years&# 0 r'  C-band[#A#R4(Main transponders18+6\A#R6,Backup transponders3+1B#B#TPower(18+3) transponders of 5.5 W(6+1) transponders of 8.5 WUXA#R(Bandwidth36 MHzN A#RCoverageTXA#R&EIRP max37 dBW\VA#R6Polarizationlinear H/V$z" 9V1J Dqp0@Satcom 4Ez5 :"?" Satcom 41 )'  Generalg G#^@") Designation13035 / 82004A\)A#R6Launch date16 Jan 1982t'`M#jN"N ,㹌לCountry of originUnited Stateso"M#jD"H̀‰MissionTelecommunications]`,A#R8,Geostationary orbit82Ws&M#jL" &p㉂Launch vehicleThor Delta #159_,A#R<Launch siteCape Canaveral&$# 5Y'  End of lifeW$A#R,"Out of serviceyes&Y# 8 ' "(OTechnical data8F ' " Specificationsd# A#RF&Prime contractorGE Astro SpaceUF A#R(PlatformGE 3000[ Z A#R4"Mass at launch1070 kga A#R@ Mass in orbitapprox. 600 kgQZ A#R Length1.6 mQ ] A#R Width1.27 mR A#R"Height1.29 m\] A#R6Solar array11.2 m spanY d A#R0 Stabilization3 axisN A#RDC power]d  A#R8$Design lifetime10 years& 5 # 0  e '  C-band[5 A#R4(Main transponders18+6\e A#R6,Backup transponders3+1~< B#TxPower(18+3) transponders 5.5 W(6+1) transponders 8.5 WUA#R(Bandwidth36 MHzN =A#RCoverageTA#R&EIRP max37 dBW\= @A#R6Polarizationlinear H/V @z$0@" : @j@1A rssj@@KSatcom C1F0@@5 :$?" Satcom C11 j@@'  Generalg @HAG#^@") Designation20945 / 90100A\@AA#R6Launch date20 Nov 1990t'HABM#jN"N ,㹌לCountry of originUnited Stateso"ABM#jD"H̀‰MissionTelecommunicationsfBBG#^>"/ۀ0Geostationary orbit137Wn!B[CM#jB" &fD+Launch vehicleAriane V40&BC# 8[CC' "(Technical dataACC) "0۠2EIRP coverage (dBW)8C2D' " Specificationsd#CDA#RF&Prime contractorGE Astro SpaceU2DDA#R(PlatformGE 3000TD?EA#R&Mass dry517 kg[DEA#R4"Mass at launch1169 kgY?EEA#R0 Mass in orbit682 kgREEFA#R"Length1.63 mQEFA#R Width1.32 mREFFA#R"Height0.99 mXF@GA#R.Solar array14.33 mYFGA#R0 Stabilization3 axisY@GGA#R0DC powerBOL: 1390 W]GOHA#R8$Design lifetime10 yearsMGHB#TBeaconstelemetry: 3.7005 GHz (H), 4.1995 GHz (V)command: 6.4235 GHz (H)&OHI# 0 H4I'  C-bandYIIA#R0(Main transponders24Z4IIA#R2,Backup transponders4WI>JA#R,Power8.5 W (SSPA)UIJA#R(Bandwidth36 MHzC>JKC#V,Coverage & EIRP maxConus: 36 dBWAlaska: 34 dBWHawaii: 32 dBW\JuKA#R6Polarizationlinear H/VK!KK* $BھTransponder frequency chart1uKK1K?LNK?L6 <2q-"=Satcom C1's EIRP: KyL10 syLLʆSatcom C3F?LL5 :$?" Satcom C31 yLL'  Generalg LWMG#^@") Designation22117 / 92060B\LMA#R6Launch date10 Sep 1992t'WM'NM#jN"N ,㹌לCountry of originUnited Stateso"MNM#jD"H̀‰MissionTelecommunicationsf'NNG#^>"/ۀ0Geostationary orbit131Wn!NjOM#jB" &D+Launch vehicleAriane V53&NO# 8jOO' "(Technical dataAO) "0A`@EIRP coverageO?L (dBW)8OM' " Specificationsd#A#RF&Prime contractorGE Astro SpaceN MA#RPlatform[ZA#R4"Mass at launch1370 kgYA#R0 Mass in orbit784 kgOZA#RLength1 mPRA#RWidth1.6 mQA#R Height1.5 m\RA#R6Solar array15.1 m spanYXA#R0 Stabilization3 axisTA#R&DC power1400 W]X A#R8$Design lifetime12 years&/# 0 _'  C-bandY/A#R0(Main transponders24Y_A#R0,Backup transpondersO`A#RPower17 WUA#R(Bandwidth36 MHzn'`#G#^N,A`@Coverage & EIRP maxsee footprint\A#R6Polarizationlinear H/VK!#ʆ* $B#ھTransponder frequency chart: 1 r|rJSatcom C4FʆJ5 :$?" Satcom C41 {'  Generalg J⇹G#^@") Designation22096 / 92057A\{>A#R6Launch date31 Aug 1992t'⇹M#jN"N ,㹌לCountry of originUnited Stateso">!M#jD"H̀‰MissionTelecommunicationsfG#^>"/ۀ0Geostationary orbit135Wp#!M#jF" &p㉂Launch vehicleDelta 2 #213_VA#R<Launch siteCape Canaveral&|# 8V' "(Technical dataA|) "0A`@EIRP coverage (dBW)8-' " Specificationsd#A#RF&Prime contractorGE Astro SpaceN -ߋA#RPlatform[:A#R4"Mass at launch1370 kgYߋA#R0 Mass in orbit784 kgO:⌹A#RLength1 mP2A#RWidth1.6 mQ⌹A#R Height1.5 m\2ߍA#R6Solar array15.1 m spanY8A#R0 Stabilization3 axisTߍA#R&DC power1400 W]8鎹A#R8$Design lifetime12 years&# 0 鎹?'  C-bandYA#R0(Main transponders24Y? A#R0,Backup transponders ʆO[A#RPower17 WO A#RBandwidthN [A#RCoverageN FA#REIRP max\A#R6Polarizationlinear H/VK!F* $B#ھTransponder frequency chart: '¹1tr'¹m¹JSatcom K1Fm¹5 :$?" Satcom K1='¹¹# 4Also called Satcom Ku 11 m¹¹'  Generalg ¹BùG#^@") Designation16482 / 86003B\¹ùA#R6Launch date12 Jan 1986t'BùĹM#jN"N ,㹌לCountry of originUnited Stateso"ùĹM#jD"H̀‰MissionTelecommunicationsb!ĹĹA#RB,Geostationary orbitsee belowjĹMŹM#j:" &yLaunch vehicleSTS 32&ĹsŹ# 2 MŹŹ'  LocationsŹ/ƹm#:   " BeginEndPosition#Źƹj#F$8:L: 12 Jan 1986Apr 199785W$/ƹJǹj#H68May 1997late-Jun 199786.5W&ƹpǹ# 5Jǹǹ'  End of life\pǹȹA#R6"Out of serviceJul 1997&ǹ'ȹ# 8ȹ_ȹ' "(Technical dataZ'ȹȹ9 Bk,ΉϕSatcom K's EIRP: {1qrsHESatcom K2FH5 :$?" Satcom K2=# 4Also called Satcom Ku 21 H'  Generalg G#^@") Designation16276 / 85109D\yA#R6Launch date28 Nov 1985t'M#jN"N ,㹌לCountry of originUnited Stateso"y\M#jD"H̀‰MissionTelecommunicationsb!A#RB,Geostationary orbitsee belowj\(M#j:" &xLaunch vehicleSTS 31&N# : (- */ۀ LocationNm#:   " BeginEndPosition#j#F$8:L: 28 Nov 1985Nov 199681W& j#:,.Nov 1996Jun 199785W j#*Jul 199781W&& # 8  ' "(Technical dataj3 m 7 >fk,Ήϕ LL' |http://astro.estec.esa.nl/SA-general/Research/Sax/sax.html8FLL' "(OTechnical data8LM' " Specificationsc"L~MA#RD&Prime contractorAlenia SpazioN MMA#RPlatform[~M'NA#R4"Mass at launch1400 kgXMNA#R.Payload mass490 kgS'NNA#R$Diameter2.7 mQN#OA#R Height3.6 ms2NOA#RdSolar array9 m span (2 panels of 2.6 x 3.5 m)Y#O A#R0 Stabilization3 axisO yGYOeA#R0DC powerEOL: 2300 W\ A#R6$Design lifetime4 years&e瀺# 1 ' O PayloadZ.瀺r, &]4 X-ray concentrators/spectrometers2 wide-field X-ray cameras (WFC)large area phoswich detector system (PDS)high-pressure gas-scintillation proportional counter HPCPC)command: 2 kbps, S-bandtelemetry/data: 2245.500 MHz (16/131/917 kbps)Other possible frequencies: 2067.5 MHz & 2245.24887 MHzm,߂A#RX>X-ray energy detection range0.1-300 keVx6rWB#Tl Field of viewWFC: 20 x 20 degothers: 0.5-1.5 degy7߂ЃB#Tn*Angular resolutionWFC: 5 arcminothers: ~ 1 arcmin$W" = Ѓ11BtRx1z^Program: SBSIz5 :*[%d%" Program: SBSC15 8   Satellite Business System, also called CNS (Communication Network Service) or USASATSatellite Business Systems was created on 15 Dec 1975 by IBM, Comsat and Aetna Life and Casualty Inc. It was the first private professional satellite digital communications network. In Jul 1984, Comsat left the consortium. In Jul 1985, Satellite Business Systems was sold to MCI; four satellites were then in orbit. Sometime around 1987, the fleet was sold off. SBS 1 and 2 were sold to Comsat, SBS 3 remained with MCI, and SBS 4 was sold to IBM's Satellite Transponder Leasing Corp (STLC) together with the SBS 5 and 6 satellites still on the ground. In Apr 1990, Hughes Communications Inc (HCI) bought STLC from IBM. Sometime later (in 1992?) SBS 3 was sold to Comsat so that currently:zz^' SBS 1, 2 & 3 are owned by ComsatSBS 4, 5 & 6 are owned by HCIAll SBS satellites are based on HS-376 buses but SBS 611'B^'V |IS=HW=HW=HW=HW=HW=HWProgram: SBSSBS 1SBS 2SBS 3SBS 4SBS 5SBS 66]1u]|SBS 1B '5 :[%d%" SBS 11 ]Љ'  Generalg 7G#^@") Designation12065 / 80091A\ЉA#R6Launch date15 Nov 1980t'7M#jN"N ,㹌לCountry of originUnited Stateso"vM#jD"H̀‰MissionTelecommunications^ԋA#R:,Geostationary orbit100Ws&vGM#jL" &p㉂Launch vehicleThor Delta #153_ԋA#R<Launch siteCape Canaveral&Ǧ# 5'  End of lifeW̌XA#R,"Out of serviceyes$|" 6X1u u ̺SBS 2B |5 :[%d%" SBS 21 %'  Generalg G#^@") Designation12855 / 81096A\%莺A#R6Launch date24 Sep 1981t'\M#jN"N ,㹌לCountry of originUnited Stateso"莺ˏM#jD"H̀‰MissionTelecommunicationsb!\9A#RBˏ9|,Geostationary orbitsee belows&ˏM#jL" &p㉂Launch vehicleThor Delta #156_9 A#R<Launch siteCape Canaveral&1# 2 c'  Location1m#:8   " BeginEndPositioncnºj#.8$(*L: 24 Sep 1981!ºj#B846< May 1992Oct 1993 >97W)nºúj#R802< Jun 1994Aug 199671W, inclined&ºú# 5úú'  End of life\úCĺA#R6"Out of serviceSep 1996TúĺA#R&CauseDeorbited&Cĺĺ# 8ĺĺ' "(OTechnical data1 ĺ&ź'  Ku-bandYĺźA#R0(Main transponders10Y&źźA#R0,Backup transpondersy7źQƺB#TnPower8 transponders of 20 W2 transponders of 40 WUźƺA#R(Bandwidth43 MHzPQƺƺA#RCoverageUSWƺMǺA#R,EIRP max43-40 dBWZƺǺA#R2Polarizationlinear H&MǺǺ# K$ǺȺ' H Transponder frequency chart (GHz)4ǺȺT#xh ,FHorizontalDownlinkTransponderVerticalUplinkfȺɺR#t(11.725114.025fȺlɺR#t(11.774214.074fɺɺR#t(11.823314.123flɺ8ʺR#t(11.872414.172fɺʺR#t(11.921514.221f8ʺ˺R#t(11.970614.270fʺj˺R#t(12.019714.319f˺˺R#t(12.068814.368fj˺6̺R#t(12.117914.417g˺̺R#t*12.1661014.466$6̺̺" 6̺̺1b ujv ̺9ͺvSBS 3B ̺9ͺ5 :[%d%" SBS 31 ̺jͺ'  Generalg 9ͺͺG#^@") Designation13651 / 82110B\jͺ-κA#R6Launch date11 Nov 1982t'ͺκM#jN"N ,㹌לCountry of originUnited Stateso"-κϺM#jD"H̀‰MissionTelecommunicationsb!κrϺA#RB,Geostationary orbitsee belowjϺϺM#j:" &㩜Launch vehicleSTS 05&rϺ# Ϻ̺: ϺH- */ۀ Locationm#:   " BeginEndPositionHSj#.$(*L: 11 Nov 1982!j#B46< May 1992May 1992 >95W!Sij#B46< May 19942 Jun 199574W&# 5i'  End of life^"A#R:"Out of service2 Jun 1995a A#R@Causemoved to the graveyard&"# 8' "(OTechnical data1 '  Ku-bandYkA#R0(Main transponders10YA#R0,Backup transpondersK kA#RPowerO^A#RBandwidthN A#RCoverageT^A#R&EIRP max46 dBWRRA#R"Polarization$v" 6R1 uv GSBS 4B v5 :[%d%" SBS 41 '  Generalg G#^@") Designation15235 / 84093B\A#R6Launch date31 Aug 1984t'VM#jN"N ,㹌לCountry of originUnited Stateso"M#jD"H̀‰MissionTelecommunicationsb!V' A#RB,Geostationary orbitsee belowj M#j:" &'Launch vehicleSTS 16&' # : - */ۀ Location { m#:   " BeginEndPosition j#0$(*L: 31 Aug 1984?!{ j#B46< May 1992Oct 1992 >91W!  j#B "< Oct 199377W, inclined& 9 # 8 q ' "(OTechnical data89 ' " Specifications\q  A#R6&Prime contractorHughesT Y A#R&PlatformHS-376[ A#R4"Mass at launch1241 kgYY A#R0 Mass in orbit725 kgT aA#R&Diameter2.16 mQ A#R Height6.6 mb!aA#RB StabilizationSpin stabilizedYmA#R0DC powerBOL: 1200 W]A#R8$Design lifetime10 years&m @#  @v1 =@'  Ku-bandY @@A#R0(Main transponders10Z=@@A#R2,Backup transponders4E@wAB#TPower5 transponders of 20 W (TWTA)5 transponders of 40 W (TWTA)U@AA#R(Bandwidth43 MHzSwABA#R$CoverageCONUSTAsBA#R&EIRP max46 dBWZBBA#R2Polarizationlinear H&sBB# K$B>C' H Transponder frequency chart (GHz)4BCT#xh ,FHorizontalDownlinkTransponderVerticalUplinkf>C,DR#t(11.725114.025fCDR#t(11.780214.080f,DDR#t(11.823314.123fD^ER#t(11.872414.172fDER#t(11.921514.221f^E*FR#t(11.970614.270fEFR#t(12.019714.319f*FFR#t(12.068814.368fF\GR#t(12.117914.417gFGR#t*12.1661014.466$\GG" 6GH1jv<w H_H݋SBS 5B G_H5 :[%d%" SBS 51 HH'  Generalg _HHG#^@") Designation19484 / 88081B[HRIA#R4Launch date8 Sep 1988t'HIM#jN"N ,㹌לCountry of originUnited Stateso"RI5JM#jD"H̀‰MissionTelecommunicationsfIJG#^>"/ۀ0Geostationary orbit123Wn!5J KM#jB" & D+Launch vehicleAriane V25&J/K# 8 KgK' "(Technical dataA/KK) "0]MEIRP coverage (dBW)8gKK' " Specifications\K99W" »j#D68< Oct 199315 Oct 199595W}»j#*Nov 199574W& »»# 8»»' "(OTechnical data=»#û' , EIRP coverage (dBW)J»mû0 04hhHorizontalVertical8#ûû' " Specifications\mûĻA#R6&Prime contractorHughesTûUĻA#R&PlatformHS-393[ĻĻA#R4"Mass at launch2478 kgZUĻ ŻA#R2 Mass in orbit1514 kgTĻ^ŻA#R&Diameter3.66 mY ŻŻA#R0Height10 m deployedk*^Ż"ƻA#RT StabilizationSpin stabilized (55 rpm)YŻ{ƻA#R0DC powerBOL: 2300 W]"ƻƻA#R8$Design lifetime10 yearsnJ{ƻFǻ$ Telemetry: 12.190-12.200 GHz H in PCM/FM and 14.495-14.500 GHz V in FM1 ƻwǻ'  Ku-bandYFǻǻA#R0(Main transponders19[wǻ+ȻA#R4,Backup transponders11VǻȻA#R*Power41 W (TWTA)U+ȻȻA#R(Bandwidth43 MHzc"Ȼ9ɻA#RDCoverageCONUS, Alaska, HawaiiTȻɻA#R&EIRP max50 dBW\9ɻɻA#R6Polarizationlinear H/V6ɻʻ$ $Antenna: 2.4 mK$ɻjʻ' H Transponder frequency chart (GHz)fʻc˻# , Z x  Horizontal UplinkHorizontalDownlinkTransponderVertical DownlinkVertical Uplinkjʻ˻t#4"11.7250114.0250c˻̻t#4014.0495211.7495˻ ͻt#4"11.7740314.0740̻ͻt#4014.0985411.7985 ͻ)λt#4"11.8230514.1230ͻλt#4014.1475611.8475)λEϻt#4"11.8720714.1720λϻt#4014.1965811.8965Eϻmt#4ϻmX"11.9210914.2210ϻt#6 214.24551011.9455mt#6 $11.97001114.2700t#6 214.29451211.9945t#6 $12.01901314.31908t#6 214.34351412.0435t#6 $12.06801514.36808Vt#6 214.39251612.0925t#6 $12.11701714.4170Vtt#6 214.44151812.1415t#6 $12.16601914.4660$t'" 1X1 XU'6 <@=HW"@SBS 6's EIRP (Vertical)1X1 5W!56 A#RDimensionQA#R Solar arrayS>₼A#R$ StabilizationN 0A#RDC powerU₼A#R($Design lifetimec>0胼% |Downlink: 2208 & 2267.515 MHzUplink: 401.635 & 2033.2 MHz61Rxy T҉Score6 胼T, (" ScoreW4# h Signal Communication by Orbiting Relay Experiment1 T܄'  Generalg CG#^@") Designation00010 / 58006A\܄A#R6Launch date18 Dec 1958t'CM#jN"N ,㹌לCountry of originUnited Stateso"M#jD"H̀㓉MissionTelecommunications_ᆼA#R<"Perigee/Apogee185/1484 kmV7A#R*Inclination32.3UᆼA#R(Period101.5 mina7퇼G#^4" &Launch vehicleAtlas_LA#R<Launch siteCape CanaveralY퇼A#R0"Mass at launch70 kg~ZL#$ Broadcast President Eisenhower Christmas wishes that had been recorded during 13 days.5X'  End of lifeV#A#R*Decay21 Jan 1959$X҉" 7 16yz @fSeasat7 ҉@, (" Seasat1 q'  Generalg @؊G#^@") Designation10967 / 78064A\q4A#R6Launch date27 Jun 1978t'؊M#jN"N ,㹌לCountry of originUnited Statesk4M#j<"H̀郉MissionRemote sensing^qA#R:"Perigee/Apogee761/764 kmUƌA#R(Inclination108UqA#R(Period100.1 minq$ƌM#jH" &mO{Launch vehicleAtlas Agena D[獼A#R4Launch siteVandenberg8+' #Seasat was designed to demonstrate techniques for global monitoring of oceanographic phenomena and features, to provide oceanographic data, and to determine key features of an operational ocean-dynamics monitoring system. The major difference between Seasat and previous Earth observation satellites was the use of active and passive microwave sensors to achieve an all-weather capability.Dedicated ocean monitoring satellite that carried the first spaceborne synthetic aperture radar (SAR) and獼+҉ other microwave instruments.5獼`'  End of life|;+A#Rv"Out of service10 Oct 1978 (106 days of returning data)>`[A#R|Causea short circuit drained all power from its batteries&# <[' *O External resourcesZ3¼' fhttp://www.belspo.be/telsat/seasat/samm_300.htm8O¼' "(OTechnical data8¼¼' " Specifications^O¼¼A#R:&Prime contractorLockheedS¼8üA#R$PlatformAgena[¼üA#R4"Mass at launch2300 kgP8üüA#RLength21 m@üdļA#R Stabilization3 axis (momentum wheel/horizon sensing system)\üļA#R6$Design lifetime2 yearsdļ}Ǽ% 1The second stage of the Atlas-Agena launch vehicle served as the satellite bus and provided attitude control, power, guidance, telemetry, and command functions. Attached to the Agena was a sensor module which carried the payload of five microwave instruments and their antennas. Together, the two modules were about 21 meters long with a maximum diameter of 1.5 m without appendages deployed. After burnout of the Agena stage and injection into orbit, Seasat-A weighed 2300 kg. In orbit the satellite appeared to stand on end with the sensor and communications antennas pointing toward Earth and the Agena rocket nozzle and solar panels pointing toward space. &ļǼ# P#}ǼǼ- *F  SAR (Synthetic Aperture Radar)a ǼTȼA#R@Frequency1.275 GHz (L-band)TǼȼA#R&Resolution25 mWTȼȼA#R,Swath width100 kmaȼɼ$ Mission: deep ocean wave pattern imaggery, coastal sea/land interaction, ice and snow imageryGȼɼ- *4  ALT (Radar Altimeter)Vɼ!ʼA#R*FrequencyKu-bandSɼtʼA#R$Accuracy10 cm!ʼ-˼% )Mission: measure satellite altitude above sea surface, significant wave height at sub-satellite point, establish characteristics of marine geoidnAtʼ˼- *  SASS (Seasat-A Satellite Scatterometer) - Wind scatterometera -˼˼A#R@Frequency1.275 GHz (L-band)|;˼x̼A#RvAccuracywindspeed +/- 2 m/s; direction better than 20H$˼̼$ HMission: windspeed and directionm@x̼-ͼ- *  SMMR (Scanning Multichannel Microwave Radiometer) (passive)?̼ͼA#R~Frequencies6.6, 18, 37, 10.7 & 21 GHz (H & V polarization)W-ͼμA#R,Swath width600 kmHͼμB#TAccuracyocean surface temperature 2 Kocean surface windspeed 2 m/sμ8ϼ%  Mission: ocean surface temperature and windspeed, water vapor, icecover, rain rate, propagation corrections for other instrumentsR%μϼ- *J  VIRR (Visible and IR Radiometer)i'8ϼ B#TNWavebands0.25-0.73 m10.5-12.5 mϼ ҉YϼeA#R0 Field of view2-5 kmX A#R.Swath width1900 kmef' Mission: image feature identification in support of other instruments, thermal images of oceanDownlink frequency: 2287.5 MHz?1yր{ Program: SecorKf5 :.U" Program: Secor2 2w  SEquential COllation of RangeAlso called EGRS (Experimental Geodetic Research Satellite)US army geodetic satellites for triangulation (early navigation). 17 to 20 kg, box shape11' s u l^{m^{n^{o^{p^{q^{r^{s^{^{Program: SecorSecor 01BSecor 02Secor 03Secor 04Secor 05Secor 06Secor 07Secor 08Secor 09Secor 13: >18@z >Secor 01BF5 :$U" Secor 01B9># ,Also called EGRS 011 '  Generalg UG#^@") Designation00729 / 64001C\A#R6Launch date11 Jan 1964t'U%M#jN"N ,㹌לCountry of originUnited Statesp#M#jF"H̀CV$MissionScientific: geodesy^%A#R:"Perigee/Apogee902/922 kmVIA#R*Inclination69.9UA#R(Period103.3 minn!I M#jB" &#*≂Launch vehicleThor Agena[gA#R4Launch siteVandenberg$ " 9g1zz  Secor 02E 5 :"U" Secor 028A # *Also called EGRS 21 r '  Generalg A G#^@") Designation01250 / 65017B\r 5 A#R6Launch date11 Mar 1965t' M#jN"N ,㹌לCountry of originUnited Statesp#5  M#jF"H̀CV$MissionScientific: geodesy_ x A#R<"Perigee/Apogee296/1014 kmT A#R&Inclination90Tx A#R&Period97.9 minq$ M#jH" &Gi4Launch vehicleThor Ablestar[ A#R4Launch siteVandenberg&  # 5 G '  End of lifeV A#R*Decay26 Feb 1968$G " 9 1G@zz ?PBSecor 03E ?5 :"U" Secor 038 w# *Also called EGRS 31 ?'  Generalg wG#^@") Designation01208 / 65016E[jA#R4Launch date9 Mar 1965t'M#jN"N ,㹌לCountry of originUnited Statesp#jZ@M#jFZ@ "H̀CV$MissionScientific: geodesy^@A#R:"Perigee/Apogee897/926 kmVZ@AA#R*Inclination70.1U@cAA#R(Period103.2 minn!AAM#jB" &#*≂Launch vehicleThor Agena[cA,BA#R4Launch siteVandenberg$APB" 9,BB1&zz BBFSecor 04EPBB5 :"U" Secor 048BC# *Also called EGRS 41 B7C'  Generalg CCG#^@") Designation01315 / 65027B[7CCA#R4Launch date3 Apr 1965t'CmDM#jN"N ,㹌לCountry of originUnited Statesp#CDM#jF"H̀CV$MissionScientific: geodesy`mD=EA#R>"Perigee/Apogee1266/1311 kmVDEA#R*Inclination90.2U=EEA#R(Period111.4 min\EDFG#^*" &Launch vehicle[EFA#R4Launch siteVandenberg$DFF" 9FF1zςz FAGJSecor 05EFAG5 :"U" Secor 058FyG# *Also called EGRS 51 AGG'  Generalg yGHG#^@") Designation01506 / 65063A\GmHA#R6Launch date10 Aug 1965t'HHM#jN"N ,㹌לCountry of originUnited Statesp#mHQIM#jF"H̀CV$MissionScientific: geodesy`HIA#R>"Perigee/Apogee1137/2416 kmVQIJA#R*Inclination69.2UI\JA#R(Period122.2 minm JJM#j@" &g'KLaunch vehicleScout #37$\JJ" 9J&K1z{ &KkK0Secor 06EJkK5 :"U" Secor 068&KK# *Also called EGRS 61 kKK'  Generalg K;LG#^@") Designation02205 / 66051B[KLA#R4Launch date9 Jun 1966t';L MM#jN"N ,㹌לCountry of originUnited Statesp#LzMM#jF"H̀CV$MissionScientific: geodesy_ MMA#R<"Perigee/Apogee168/3646 kmTzM-NA#R&Inclination90SMNA#R$Period125 min\-NNG#^*" &Launch vehicle[N7OA#R4Launch siteVandenberg&N]O# 57OO'  End of lifeU]O A#R(Decay6 Jul 1967O J$O0" 9 i1ςz]{ iSecor 07E05 :"U" Secor 078i怽# *Also called EGRS 71 '  Generalg 怽~G#^@") Designation02411 / 66077B\ځA#R6Launch date19 Aug 1966t'~NM#jN"N ,㹌לCountry of originUnited Statesp#ځM#jF"H̀CV$MissionScientific: geodesy`NA#R>"Perigee/Apogee3671/3700 kmVtA#R*Inclination89.7UɃA#R(Period167.5 min\t%G#^*" &Launch vehicle[ɃA#R4Launch siteVandenberg&%# 8ބ' "(OTechnical data># 6Transmits on 136.800 MHz9ބU1${{ USecor 08E5 :"U" Secor 088U҅# *Also called EGRS 81 '  Generalg ҅jG#^@") Designation02520 / 66089B[ņA#R4Launch date5 Oct 1966t'j9M#jN"N ,㹌לCountry of originUnited Statesp#ņM#jF"H̀CV$MissionScientific: geodesy`9 A#R>"Perigee/Apogee3673/3709 kmT]A#R&Inclination90U A#R(Period167.6 min\]G#^*" &Launch vehicle[iA#R4Launch siteVandenberg$" 9iƉ1:]{{ Ɖ Secor 09E 5 :"U" Secor 098ƉC# *Also called EGRS 91 t'  Generalg CۊG#^@") Designation02861 / 67065A\t7A#R6Launch date29 Jun 1967t'ۊM#jN"N ,㹌לCountry of originUnited Statesp#7M#jF"H̀CV$MissionScientific: geodesy`{A#R>"Perigee/Apogee3792/3946 kmVьA#R*Inclination90.1U{&A#R(Period172.2 mino"ьM#jD" &扂Launch vehicleThor Burner[&A#R4Launch siteVandenberg$" 9M1{ M ýSecor 13E5 :"U" Secor 139Mˎ# ,Also called EGRS 131 '  Generalg ˎcG#^@") Designation03891 / 69037B\A#R6Launch date14 Apr 1969t'c?M#jN"N ,?㹌לCountry of originUnited Statesp#M#jF"H̀CV$MissionScientific: geodesy`?A#R>"Perigee/Apogee1068/1126 kmUdA#R(Inclination100UA#R(Period107.2 minp#d)½M#jF" &#*≂Launch vehicleThor Agena D[½A#R4Launch siteVandenberg&)½½# 8½½' "(OTechnical data>½ ý# 6Transmits on 136.800 MHz7½Wý1(z{ Wýý˽Seds 17 ýý, (" Seds 1F#Wýý# FSmall Expendable Deployer System1 ýĽ'  Generalg ýlĽG#^@") Designation22582 / 93017Bh'ĽĽA#RNLaunch date30 Mar 1993 at 03:29 UTt'lĽHŽM#jN"N ,㹌לCountry of originUnited StatesfĽŽG#^>"H̀MissionTether experimentRHŽƽA#R"OperatorNASA^Ž^ƽA#R:"Perigee/Apogee184/746 kmTƽƽA#R&Inclination34L ^ƽƽA#RPeriodp#ƽnǽM#jF" &p㉂Launch vehicleDelta 2 #219e$ƽǽA#RHLaunch siteCape Canaveral LC17AYnǽ,ȽA#R0"Mass at launch23 kgǽHʽ' The system consisted of a small 10 kg deployer cylinder 33 cm long and a tiny 23 kg satellite (`end mass') of similar size. The satellite was connected to the cylinder by a rope made of Spectra-1000 which was 0.75 mm in diameter and 20 km long. The cylinder remained attached to the Delta second stage rocket in orbit.Seds was developed and built by NASA-Marshall, the Harvard-Smithsonian Center for Astrophysics, and Tether Applications of San Diego, CA. The end mass was built by NASA-Langley.5,Ƚ}ʽ'  End of lifeVHʽʽA#R*Decay30 Mar 1993&}ʽʽ# <ʽ5˽' *O External resourcesP)ʽ˽' Rhttp://ixeab8.larc.nasa.gov/seds.html75˽˽1 ր{| ˽˽}Seds 27 ˽˽, (" Seds 2F#˽9̽# FSmall Expendable Deployer System1 ˽j̽'  Generalg 9̽̽G#^@") Designation23028 / 94016Bh'j̽9ͽA#RNLaunch date10 Mar 1994 at 03:40 UTt'̽ͽM#jN"N ,㹌לCountry of originUnited Statesf9ͽνG#^>"H̀MissionTether experimentRͽeνA#R"OperatorNASA`ννA#R>"Perigee/Apogee347 / 352 kmVeνϽA#R*Inclination34.9L νgϽA#RPeriodp#ϽϽM#jF" &p㉂Launch vehicleDelta 2 #226d#gϽGA#RFϽG˽Launch siteCape Canaveral LC17YϽA#R0"Mass at launch23 kgG- (RIt is a package attached to the Delta second stage rocket which was to deploy a 20 km tether to compare actual tether dynamics with theoretical models. The end mass behaved as expected and unreeled in 1 h 48 min to a maximum length of 19.8 km.Unlike Seds 1 for which the tether was severed after deploy, the tether remained attached to the Delta rocket. The end mass mini-satellite transmitted for 10 hours. On 15 Mar 1995 Seds separated from the tether because of an impact and reentred.% The success of Seds 2 confirms that tether systems can be used to deploy sensors which require a particular orientation to the local vertical, such as atmospheric composition experiments.5'  End of life_6A#R<"Out of service15 Mar 1994UA#R(Decay8 May 1994&6# <' *O External resourcesb}. ,http://ixeab8.larc.nasa.gov/seds.htmlhttp://von-braun.msfc.nasa.gov/Public/Ps01/movies.html71r {| ,Sedsat7 }, (" SedsateBP# Students for the Exploration and Development of Space Satellite1 '  GeneralYPG#^$") Designationd#>A#RFLaunch dateplanned in Jul 1997_G#^0"N ,Country of originU>G#^"H̀MissionZLA#R2"Perigee/Apogee511 kmVA#R*Inclination28.5L LA#RPeriod\J G#^*" &Launch vehicleQ A#R Launch site&J # < ' *O External resourceszL w . ,http://www.seds.org/sedsat/http://seds.lpl.arizona.edu/seds/seds.html8 ' "(OTechnical data&w # <  ' * Mode A transponderL B#TUplink145.915 to 145.975 MHz (2 Meter band)Modulation: SSB, CW, FM, AM& #  D#VDownlink29.350 to 29.410 Mhz (10 Meter Band)Modulation: SSB, CW, FM, AM AFSK 300 bpsHf Packet Compatible telemetry downlink& # < ' * Mode L transpondero B#TUplink1268.250 to 1268.100 MHz (23cm band)Modulation: FSK digital data at 9.6, 19.2, 38.4 and 56 kbit/sec& # p vB#TDownlink437.850 to 438.000 MHz (70 cm band)Modulation: FSK digital data at 9.6, 19.2, 38.4 and 56 kbit/sec ,& !Data Rate: 300 bits/sec AFSK packet data 9600 bits/sec or 57,600 bits/secRF output per transponder will be 3 watts average and 15 watts max1v]1W ] @T+,) "VȠ$To view this page you need to register&] @#  @,4@@1|| @@|@HSFU< @|@2 4"  SFU:@@@& ( Space Flyer Unit1 |@@'  Generalg @NAG#^@") Designation23521 / 95011A\@AA#R6Launch date17 Mar 1995lNABM#j>"N ,bCountry of originJapan_AuBG#^0"H̀MissionScientific^BBA#R:"Perigee/Apogee467/496 kmVuB)CA#R*Inclination28.5RB{CA#R"Period92 minf)CCM#j2" &JLaunch vehicleH2[6{C%CauseRetrieved by STS 72H$F~G$ HDownlink frequency: 2263.602 MHz<6GG' *O External resourcesY2~GH' dhttp://koala.astro.isas.ac.jp/irts/irts_E.html8GKH1|| KHHMShinsei8 HH, (" Shinsei6KHH# &Means "new star"1 HH'  Generalg HQIG#^@") Designation05485 / 71080A\HIA#R6Launch date28 Sep 1971lQIJM#j>"N ,bCountry of originJapany,IJM#jX"H̀?vMissionScientific: ionosphere study_JJA#R<"Perigee/Apogee872/1866 kmVJGKA#R*Inclination32.1UJKA#R(Period113.1 miniGKLM#j8" & Launch vehicleMu 4SZK_LA#R2Launch siteKagoshimaYLLA#R0"Mass at launch66 kg&_LL# <LM' *O External resourcesY2LsM' dhttp://www.isas.ac.jp/info/sat/shinsei-e3.html8MM' "(OTechnical data>sMM# 6Transmits on 136.695 MHz7M N1r|n}! NWNSich 17 MWN, (" Sich 11 NN'  Generalg WNNG#^@") Designation23657 / 95046Ah'NWOA#RNLaunch date31 Aug 1995 at 06:50 UTn!NOM#jB"N ,eCCountry of originUkraine}6WONG#^lONMOperatorNational Space Agency of Ukraine (NKAU)~+ÒS#vV"H̀(郉뉢MissionRemote sensing (Ocean-O1)^N*A#R:"Perigee/Apogee682/651 kmV̀A#R*Inclination82.5T*ԁA#R&Period98.7 minr%FM#jJ" &ቂLaunch vehicleCyclone 3 #114ԁ- (W3д%First Ukrainian satellite (although numerous Ukrainian-made satellite were launched before under the CIS flag)Was launched with Fasat Alfa which failed to separate8FV' "(Technical dataM0 0:*; YjSpecificationsPayload7Vڃ1|}" ڃhSich 27 , (" Sich 2W4ڃh# hTo be launched in 1996 by a Zenit 2 from Tyuratam11W# 턾T+h턾) "VȠ$To view this page you need to register&# 7턾J1n}}$ J։Sicral7 , (" SICRAL_9J& r Sistema Italiana de Communicazione Riservente Allarmi1 '  GeneralYjG#^$") Designation`ʆA#R>Launch dateplanned in 1999lj6M#j>"N ,xECountry of originItalyq*ʆG#^T"H̀Missionmilitary: telecommunicationsZ6A#R2,Geostationary orbit?lmM#j>" &2!Launch vehicleAriane 5YƈG#^$Launch sitem։& Should weigh 2500 kg at lift-off. Prime contractor is Alenia Spazio It will provide secure communications for Italy's Ministry of Defense and the country's civil security forces, catering for domestic needs and operations abroad.1ƈ1W% [T+։[) "VȠ$To view this page you need to register&# 8[1 }}& Signe_3@2 4"  Signe 31 *'  Generalg G#^@") Designation10064 / 77049A\*틾A#R6Launch date17 Jun 1977m ZM#j@"N ,㱭+Country of originFrance|/틾֌M#j^"H̀_BMissionScientific: gamma-ray astronomy^Z4A#R:"Perigee/Apogee449/522 kmV֌A#R*Inclination50.7T4ލA#R&Period94.3 minlJM#j>" &s,梉Launch vehicleCosmos CYލA#R0Launch siteTyuratamZJA#R2"Mass at launch102 kg&## 5X'  End of lifeV#A#R*Decay20 Jun 1979$X "  GS1}Ƅ}' SkžProgram: Simon BolivarF , (6" Program: Simon BolivarS¾& Project of the 5 Andean Pact countries (Bolivia, Colombia, Ecuador, Peru and Venezuela) to launch telecommunication satellites. The association has also a 15-year agreement with the Intelsat system, offering them rented transponders at preferential rates.The group could first lease a satellite in orbit before launching a new model with C- and Ku-band capacity for 50 transponders. The cost would be $300 million (half of it for the equipment, its insurance and launching)kž/ ,?L2The satellite has three possible lines of orbit, at 103, 106 and 109 longitude west, but the Mexican Solidaridad 1 is in orbit at 109.2 degrees west, a path which could seriously interfere with the Simon Bolivar.The Andean telecommunications companies have been dreaming of having their own satellite for nearly 20 years. The plan produced the "Condor" project in the 1980's, but severe economic crises in several regional nations brought all this to a halt.This project was revived under the name "Simon Bolivar," with the proposal adapted as a non-governmental multinational business open to different types of international participation, especially funding.1¾ž1W( žžƾT+kžž) "VȠ$To view this page you need to register&žƾ# AžWƾ1}}~) Wƾƾ2Program: SinosatAƾƾ, (," Program: Sinosat1 Wƾƾ'  GeneralYƾ"ǾG#^$") Designationd#ƾǾA#RFLaunch dateplanned in Jun 1997l"ǾǾM#j>"N ,6"Country of originChinaUǾGȾG#^"H̀Mission^ǾȾA#R:,Geostationary orbit110Eq$GȾɾM#jH" &9+SLaunch vehicleLong March 3BYȾoɾG#^$Launch siteɾ6˾) =GEO telecom program to be operated by Sino Satellite Communications (joint venture of CASC and People's Bank of China). The satellite is insured for $350 million (by China Space Pool)EurasSpace (Munich/Beijing) in which DASA and China Aerospace Corporation (CASC) each have a 50 per cent share. Aerospatiale will also supply orbital manoeuvering operations and personnel training. 1 satellite and 2 options<oɾr˾' *O External resourcesQ*6˾˾' Thttp://www.china-web.com/science/casc/8r˾˾' "(OTechnical data8˾3̾' " Specifications|;˾̾A#Rv&Prime contractorEurasSpace (with Aerospatiale as lead)[3̾ ;A#R4PlatformSpacebus 3000[̾e;A#R4"Mass at launch2820 kgZ ;;A#R2 Mass in orbit1600 kgOe;ξA#RDimension\;jξA#R6Solar array26.3 m spanSξξA#R$ StabilizationYjξϾA#R0DC powerEOL: 5300 W]ξsϾA#R8$Design lifetime15 yearsBϾ- (+'v&Has 2 deployable 1.6 and 1.8 m diameter antennas and a fixed 1 m antenna.EurasSpace had to asϾƾsk Aerospatiale to handle the design because of the failure of EurasSpace's first satellite failure, Dong Fang Hong 41. Sinosat 2 should be the real second EurasSpace satellite.0 sϾ'  C-band_PA#R<(Main transponders16 or 24YA#R0,Backup transpondersOPA#RPower16 WUMA#R(Bandwidth36 MHzi(A#RPCoverageChina, Hong Kong and TaiwanN MA#REIRP maxRVA#R"Polarization&|# 1 V'  Ku-bandY|A#R0(Main transponders14Y_A#R0,Backup transpondersOA#RPower55 WU_A#R(Bandwidth54 MHzi(lA#RPCoverageChina, Hong Kong and TaiwanN A#REIRP maxRl A#R"Polarization&2# 1 c1W* cT+2) "VȠ$To view this page you need to register&c# ?1Ƅ}~+ gProgram: SirioKg5 :.aIZ" Program: SiriomE( Satellite Italiano Ricerca Industriale OperativaItalian program1g1, gb(g: DP_zcBdBProgram: SirioSirio 1Sirio 281I)~-  Sirio 1Dg5 : aIZ" Sirio 11  '  Generalg { G#^@") Designation10294 / 77080A\ A#R6Launch date25 Aug 1977l{ C M#j>"N ,xECountry of originItalyU G#^"H̀MissionYC A#R0,Geostationary orbits& d M#jL" &p㉂Launch vehicleThor Delta #133_ A#R<Launch siteCape Canaveralb!d % A#RB"Mass at launch218 kg or 398?& K # 5% '  End of lifeWK A#R,"Out of serviceyes$ " 8 3 1~. 3 w Sirio 2D w 5 : aIZ" Sirio 253 '  End of life_w A#R<"Out of service10 Sep 1982o( zG#^P)+CauseLaunch failure of Ariane L05N* $ T420 kg satellite aimed for meteorology@z1}~0/ TM@Program: SiriusLT5 :0pT*" Program: SiriusM@8 >kQ^gz͏tz͏tSwedish telecommunication program operated by NSAB. NSAB is owned 37.5% by Teracom, 37.5% by Rymdbolaget and TM@25% by Tele Danmark. Teracom is in charge of the exploitation1T~@10 ~@@w6M@@A RlڢProgram: SiriusSirius 1Sirius 2Sirius 39~@.A1~1 .AsACSirius 1E@sA5 :"pT*" Sirius 11 .AA'  General[sAAG#^(SOld nameBSB 1[AZBG#^(ˆtCountrySwedeno"ABM#jD"H̀‰MissionTelecommunicationsfZB/CG#^>"/ۀ0Geostationary orbit5.2E&BUC# 8/CC' "(Technical datal4UCC8 @hbٹZfܢaEIRP coverage (dBW)SpecificationsKu-band1C*D1~2 *DwDMCwD6 <0"BSirius 1's EIRP9*DD1(6~3 DDͿSirius 2EwDD5 :"pT*" Sirius 27D,E# (Also called GE 1E1 D]E'  Generalg ,EEG#^@") Designation25049 / 97071A\]E FA#R6Launch date12 Nov 1997m EFM#j@"N ,ˆtCountry of originSweden4 FGM#jh(Q^g OperatorNSAB & GE Capital Satellites-Europeo"F}GM#jD"H̀‰MissionTelecommunicationsfGGG#^>"/ۀ0Geostationary orbit4.8Eo"}GRHM#jD" &yg&\Launch vehicleAriane V102<GI9 @Q^g D"Operated by NSAB a joint venture by Teracom Svensk Rundradio and Swedish Space Corporation, and GE Capital Satellites-Europe, a subsidiary of GE Capital Satellites International itself a subsidiary of GE AmericomBecame operational in mid-Dec 1997.<RHI' *O External resourcesY2I#J' dhttp://www.ge.com/capital/americom/am5.htm#eur8I[J' "(OTechnical data=#JJ' , EIRP coverage (dBW)n7[JK7 >n\ӯWEuropeScandinaviaNorthern and Central Europe8J>K' " Specificationsb!KKA#RB&Prime contractorAerospatiale\>KKA#R6PlatformSpacebus 3000B[KWLA#R4"Mass at launch2930 kgZKLA#R2 Mass in orbit1250 kga WLMA#R@Dimension1.8 x 2.3 x 2.86 m\LnMA#R6Solar array26.3 m spanYMMA#R0 Stabilization3 axisf$nM-NB#THDC powerBOL: 6100 WEOL: 5845 W]MNA#R8$Design lifetime15 yearsZ-NNA#R2Beacon11.70685 GHz H`<NDO$ xtwo 1.8 m fixed antennas and one 1.4 m steerable antennaM&NO' L Ku-band for NSAB: Scandinavia (BSS)YDO A#R0(Main transponders13O wDb!OnA#RB,Backup transponders20-for-16O A#RPower52 WUnA#R(Bandwidth33 MHzt-G#^Z,ӯCoverage & EIRP maxScandinavia: 60 dBWZA#R2Polarizationlinear VAcB#TFrequenciesUplink: 17.3 - 18.1 GHzDownlink: 11.7 - 12.5 GHz&# Fcς' > Ku-band for GE: Europe (BSS)Y(A#R0(Main transponders13b!ςA#RB,Backup transponders20-for-16O(كA#RPower72 WU.A#R(Bandwidth33 MHzo(كG#^P,\Coverage & EIRP maxEurope: 50 dBWU.A#R(G/T max4.5 dB/KZLA#R2Polarizationlinear HAυB#TFrequenciesUplink: 17.3 - 18.1 GHzDownlink: 11.7 - 12.5 GHz&L# R+υG' V Ku-band for North & Central Europe (FSS)h'A#RN(Main transponders3 (NSAB) + 3 (GE)b!GA#RB,Backup transponders20-for-16O`A#RPower88 WUA#R(Bandwidth36 MHz=`9G#^z,WCoverage & EIRP maxNorthern and Central Europe: 48 dBWUA#R(G/T max4.5 dB/KX9房A#R.PolarizationlinearCkB#TFrequenciesUplink: 14.0 - 14.25 GHzDownlink: 12.5 - 12.75 GHz&房# K$k܉' H Transponder frequency chart (GHz)D#܀ . L vx HorizontaldownlinkTransponderVerticaldownlinkBeam܉;{#ƀ4"$11.727481EuropeЋ{#ƀ4"$211.74666Nordic;e{#ƀ4"$11.766843EuropeЋ{#ƀ6$&1011.90010Nordice{#ƀ6 $&12.0727219Europe'{#ƀ6 $&12.1110821Europe{#ƀ6$&2212.13026Nordic'S{#ƀ6 $&12.1494423Europe {#ƀ6$&2412.16862NordicS wDS{#ƀ6 $&12.1878025Europe 8{#ƀ6$&2612.20698Nordic{#ƀ6 $&12.2261627Europe8d¿{#ƀ6$&2812.24534Nordic¿{#ƀ6 $&12.2261629Europed¿ÿ{#ƀ6$&3012.28370Nordic¿&Ŀ{#ƀ6 $&12.3028831EuropeÿĿ{#ƀ6$&3212.32206Nordic&ĿRſ{#ƀ6 $&12.3412433EuropeĿſ{#ƀ6$&3412.36042NordicRſ~ƿ{#ƀ6 $&12.3796035Europeſǿ{#ƀ6$&3612.39878Nordic~ƿǿ{#ƀ6 $&12.4179637Europeǿ@ȿ{#ƀ6$&3812.43714Nordicǿȿ{#ƀ6 $&12.4563239Europe@ȿlɿ{#ƀ6$&4012.47550Nordic ȿɿ{#ƀ !lɿʿ{#ƀB"$312.60416North/Central!ɿ*˿{#ƀB"$412.64582North/Central!ʿ˿{#ƀB"$512.68748North/Central"*˿c̿{#ƀD $&12.6458210North/Central"˿Ϳ{#ƀD $&12.6874811North/Central"c̿Ϳ{#ƀD $&12.7291412North/Central$ͿͿ" 1ͿͿ1W4 ͿFοlοT+ͿFο) "VȠ$To view this page you need to register&Ϳlο# 1Fοο15 οοZ$lοο6 E F2FT+E F) "VȠ$To view this page you need to register&E2F# 8 FjF1 ~? jFFSkipper8 2FF, (" Skipper1 jFF'  Generalg F:GG#^@") Designation23752 / 95072Bh'FGA#RNLaunch date28 Dec 1995 at 06:45 UTt':GHM#jN"N ,㹌לCountry of originUnited States_GuHG#^0"H̀MissionScientific^HHA#R:"Perigee/Apogee804/813 kmVuH)IA#R*Inclination98.6SH|IA#R$Period101 mine)IIG#^<" &Launch vehicleMolniya MY|I:JA#R0Launch siteTyuratamZIJA#R2"Mass at launch257 kg&:JJ# 5JJ'  End of life_JNKA#R<"Out of service28 Dec 1995eJKA#RCauseFailed after deployment because the solar panels were wired to discharge instead of charge.X1NKLN' cJoint US-Russian satellite: Utah State University provided the forward instrument section an the Moscow Aviation Institute the satellite bus. Shape is a cylinder, 0.8 m diameter and 1.3 m long. Utah State University's Space Dynamics laboratory in Logan, Utah is the prime contractor and has already conducted similar bow shock test with sub-orbital rockets in April 1990 and February 1991: Bow Shock Ultraviolet 1 and 2. These tests showed ultraviolet light are generated by the bow shock, but tests at higher altitudes and faster speeds needs to be done.R-K% [Skipper is to investigate bow shock emissions and aerothermal chemistry reactions produced in Earth's upper atmosphere by manoeuvering and re-entering missile warheads having velocity profiles similar to those expected from the next generation of fast-burning solid propellant missiles. Skipper spacecraft is an orbital successor to the suborbital Bow Shock 1 and 2 sounding rocket missions whichLN2F revealed unexpected date on re-entering warhead signatures and which now require more extended experiment and observation time provided by an orbital test.LN' Spacecraft will carry instrumentation including three scanning spectrometers, a hydrazine thruster system and a photometer plus instrumentation support systems, attitude control and manoeuvering thrusters and science and engineering telemetry to acquire data from higher altitudes and velocities where significant changes in physical processes associated with re-entering warheads are encountered.On subsequent revolutions perigee will be gradually reduced through controlled manoeuvres to between 120 km and 130 km, spacecraft traverses through very low perigees being observed to simulate warhead re-entries into Earth's upper atmosphere. Perigee will be decreased until atmospheric drag threatens to initiate re-entry.= 10ʂ@ /Program: SkyI/5 :*&d%" Program: SkyxN* "Also called ASkyBDBS satellite system to operate from the 110W slot (the bid was won with $682.6 million). Operated by the MCI-News corporation venture called American Sky Broadcasting (ASkyB).In mid 1997 it was announced that the satellite program would join into the new Primestar Inc. comprising the former Primestar partners (TSAT, Time Warner Satellite Services, Newhouse, Cox, Comcast, MediaOne (formerly Continental) and GE Americom) plus ASkyB. The total Sky program including satellites and launch delivered in orbit and uplink facilities is valued between $400 and $500.1/؆1WA ؆,RT+,) "VȠ$To view this page you need to register&؆R# 1,1B ߇\"R߇: DDS^TSW_TSWProgram: SkySky 1Sky 211WC dT+߇d) "VȠ$To view this page you need to register&# 1d1UD :# .Sky's specificationsi(^A#RP&Prime contractorSpace Systems/LoralN A#RPlatformT^A#R&"Mass at launchSSA#R$ Mass in orbitOA#RDimensionQSA#R Solar arraySFA#R$ StabilizationTA#R&DC power7500 W]FA#R8$Design lifetime12 years$" 1L1WE LƌT+) "VȠ$To view this page you need to register&Lƌ# 11UF 3ƌ*#  Sky's Ku-bandYA#R0(Main transponders32Y*܍A#R0,Backup transpondersK 'A#RPowerO܍vA#RBandwidth{:'A#RtCoverageUnited States, Hawaii, Alaska and Puerto RicoN v?A#REIRP maxRA#R"Polarization$?" 1 1WG ` T+`) "VȠ$To view this page you need to register& # 6`1pH Sky 1B 5 :&d%" Sky 11 /'  GeneralYG#^$") Designatione$/A#RHLaunch dateplanned in late 1997t'aM#jN"N ,㹌לCountry of originUnited Stateso"M#jD"H̀‰MissionTelecommunications^a.A#R:,Geostationary orbit110WjM#j:" &㉓gLaunch vehicleProtonY.G#^$Launch site&# 8O' "(Technical dataM0 0:6)USpecificationsKu-band1O1WI !GT+!) "VȠ$To view this page you need to register&G# 6!}1 .J }Sky 2B G5 :&d%" Sky 27}# (Also called MCI 11 ''  GeneralYG#^$") Designationf%'A#RJLaunch dateplanned in early 1998t'ZM#jN"N ,㹌לCountry of originUnited Stateso"M#jD"H̀‰MissionTelecommunications^Z'A#R:,Geostationary orbit110Wm M#j@" &yjLaunch vehicleAtlas 2ASY'G#^$Launch site&# 8K' "(Technical dataM0 0:6)USpecificationsKu-band1K1WK CT+) "VȠ$To view this page you need to register&C# : }1+L }SkybridgeCC, (0" Program: Skybridge; }. *〾uFormely known as SativodProject led by Alcatel. It aims to place 64 LEO satellites in orbit to provide high speed data communications. Financing needs: $3.5 billion Partners are Loral Space & Communications, Toshiba, Spar Aerospace Ltd, Aerospatiale, Ste Regionale d'Investissements de Wallonie (Belgium), Mitsubishi Electric Corp and Sharp Corp of Japan. A strategic partnership was drawn with SS/L's Cyberstar The French space agency CNES should also join.The program should be operational in 2001 (32 satellites)(/' A unique feature of the SkyBridge system is its ability to share spectrum with existing geostationary (GEO) satellite systems in the Ku-band. Through technological and system design breakthroughs achieved by Alcatel engineers, there will be no interference to those GEO systems.The SkyBridge satellite in low earth orbit (LEO) will shut off transmissions when passing through the area where GEO satellites are transmitting. This shut-off of transmissions will not affect the user, because the traffic will be "handed" over to another satellite in the SkyBridge constellation. The use of a LEO constellation also assures real-time transmissions, without the delays that affect transmissions to GEO satellites, which are located m/Cuch farther away from the Earth. ' Orbit: 1450 km Ka-band used between the satellites and the gateways. ATM-based 16 kbps to 60 mbps for downlink, 16 kbps to 2 mbps for uplinkSatellites should weigh 800 kg. bent-pipe mode</T' *O External resourcesM&' Lhttp://www.skybridgesatellite.com/1T1WM &LT+&) "VȠ$To view this page you need to register&L# @&1RʂhN Program: SkynetLL5 :0EI" Program: Skynet!& English military programSkynet 5 is currently under study. It would be developed with the US (Lockheed Martin involved) and compatible with US communication systems. Would be based on the A2100 bus and would operate in the EHF, SHF and UHF bands.1*11O ***s  Ȁ ȉ5 ȉ6 ȉ ȉ ȉ ȉ ȉ ȉ ȉProgram: SkynetSkynet 1ASkynet 1BSkynet 2ASkynet 2BSkynet 4ASkynet 4BSkynet 4CSkynet 4DSkynet 4ESkynet 4F1*[1UP [ I&*# LSkynet 4's (A, B, C) specificationsq0[A#R`&Prime contractorBritish Aerospace (now MMS)QfA#R PlatformECS[A#R4"Mass at launch1430 kgYfA#R0 Mass in orbit770 kgXrA#R.Payload mass225 kgQA#R Length2.2 mK rA#RWidthQ_A#R Height2.3 mZA#R2Solar array16 m spanY_ A#R0 Stabilization3 axisTf A#R&DC power1500 W\ A#R6$Design lifetime7 years$f " 1  1WQ  k T+ k ) "VȠ$To view this page you need to register& # 1k 1UR . Q.  # \Skynet 4's (A, B, C) UHF-band (250-315 MHz)X k A#R.0(Main transponders2Y A#R00,Backup transpondersOk  A#R0Power40 WU h A#R(0Bandwidth25 KHzT A#R&0CoverageEuropeN h A#R0EIRP max$ . " 1 _ 1WS _ T+. ) "VȠ$To view this page you need to register&_ # 1 1UT A8AA K# <Skynet 4's (A, B, C) X-bandX A#R.0(Main transponders4YKA#R00,Backup transpondersOKA#R0Power40 W]A#R80Bandwidth60 and 135 MHzTK @A#R&0CoverageGlobal @ N Z@A#R0EIRP maxR @@A#R"0Polarizationh'Z@AA#RN0FrequenciesDownlink: 7.23-7.75 GHz$@8A" 1AiA1WU iAAAT+8AA) "VȠ$To view this page you need to register&iAA# 1AB1UV BDDL)A`B# RSkynet 4's (A, B, C) EHF-band (42 GHz)XBBA#R.0(Main transponders1Y`BCA#R00,Backup transpondersK B\CA#R0PowerOCCA#R0BandwidthN \CCA#R0CoverageN CGDA#R0EIRP maxRCDA#R"0Polarization$GDD" 1DD1WW DBEhET+DBE) "VȠ$To view this page you need to register&DhE# 1BEE1UX EI JI&hEE# LSkynet 4's (D, E, F) specificationsYE;FA#R0&Prime contractorMMSQEFA#R PlatformECS\;FFA#R6"Mass at launch1510 kg YFAGA#R0 Mass in orbit770 kgXFGA#R.Payload mass256 kgQAGGA#R Length2.2 mK G5HA#RWidthQGHA#R Height2.3 mZ5HHA#R2Solar array16 m spanYH9IA#R0 Stabilization3 axisTHIA#R&DC power1200 W\9IIA#R6$Design lifetime7 years$I J" 1I>J1WY >JJJT+ JJ) "VȠ$To view this page you need to register&>JJ# 1JJ1UZ J1MUMQ.J:K# \Skynet 4's (D, E, F) UHF-band (254-318 MHz)XJKA#R.0(Main transponders2Y:KKA#R00,Backup transpondersOK:LA#R0Power50 WUKLA#R(0Bandwidth25 KHzT:LLA#R&0CoverageEuropeN L1MA#R0EIRP max$LUM" 11MM1U[ MAUMM# <Skynet 4's (D, E, F) X-bandXMNA#R.0(Main transponders4YMxNA#R00,Backup transpondersONNA#R0Power50 W]xN$OA#R80Bandwidth60 and 125 MHzTNxOA#R&0CoverageGlobalN $OOA#R0EIRP maxRxO$A#R"0O$UMPolarizationh'OA#RN0FrequenciesDownlink: 7.23-7.75 GHz$$" 11W\ 5[T+5) "VȠ$To view this page you need to register&[# 151U] >L)[؁# RSkynet 4's (D, E, F) EHF-band (42 GHz)X0A#R.0(Main transponders1Y؁A#R00,Backup transpondersK 0ԂA#R0PowerO#A#R0BandwidthWԂzA#R,0CoveragesteerableN #ȃA#R0EIRP maxRzA#R"0Polarization$ȃ>" 1o1W^ oÄT+>Ä) "VȠ$To view this page you need to register&o# : Ä#1v|_ #iSkynet 1AFi5 :$EI" Skynet 1A1 #'  Generalg iG#^@") Designation04250 / 69101A\]A#R6Launch date22 Nov 1969u(҆M#jP"N ,R׉Country of originUnited Kingdomy,]KM#jX"H̀‰MissionMilitary: telecommunicationsb!҆A#RB,Geostationary orbitsee belowr%KM#jJ" &p㉂Launch vehicleThor Delta #74_~A#R<Launch siteCape CanaveralZ؈A#R2"Mass at launch125 kg&~# 5؈3'  End of lifeWA#R,"Out of serviceyes$3" : 1+` .Skynet 1BF.5 :$EI" Skynet 1B1 _'  Generalg .ƊG#^@") Designation04493 / 70062A\_"A#R6Launch date19 Aug 1970u(ƊM#jP"N ,R׉Country of originUnited Kingdomy,"M#jX"H̀‰MissionMilitary: telecommunications\lA#R6,Geostationary orbitn/ar%ތM#jJ" &p㉂Launch vehicleThor Delta #80_l=A#R<Launch siteCape Canaveral&ތc# 5='  End of life_cA#R<"Out of service19 Aug 1970f%]A#RJCauseRemained on transfert orbit$" : ]1|a Skynet 2AF5 :$EI" Skynet 2A1 2'  Generalg G#^@") Designation07096 / 74002A\2 A#R6Launch date19 Jan 1974 u(M#jP"N ,R׉Country of originUnited Kingdomy, M#jX"H̀‰MissionMilitary: telecommunications\VA#R6,Geostationary orbitn/as&M#jL" &p㉂Launch vehicleThor Delta #100_V(A#R<Launch siteCape Canaveral&N# 5('  End of life_NA#R<"Out of service25 Jan 1974z9\A#RrCausePlaced on a bad orbit (96 km x 3406 km x 37.6)$" : \1rjb ASkynet 2BF5 :$EI" Skynet 2B1 1'  Generalg G#^@") Designation07547 / 74094A\1A#R6Launch date23 Nov 1974u(iM#jP"N ,R׉Country of originUnited Kingdomy,M#jX"H̀‰MissionMilitary: telecommunications]i?A#R8,Geostationary orbit42Es&M#jL" &p㉂Launch vehicleThor Delta #105_?A#R<Launch siteCape CanaveralZkA#R2"Mass at launch235 kg&# 5k'  End of lifeWA#R,"Out of serviceyes$A" : {1c {8Skynet 4AFA5 :$EI" Skynet 4A1 {'  Generalg YG#^@") Designation20401 / 90001A[A#R4Launch date1 Jan 1990u(Y)M#jP"N ,R׉Country of originUnited Kingdomy,M#jX"H̀‰MissionMilitary: telecommunicationsb!)A#RB,Geostationary orbitsee belowp#tM#jF" &^]Launch vehicleTitan 3 #153&# : t- */ۀ Location^m#:   " BeginEndPositionj#2"&(L: 1 Jan 19905E^jj#>Feb 199534W, inclined&# 8j' "(Technical datap28> LdFeb 199553E, inclinedG#$ FShould be deorbited in mid-19988m' "(Technical datap2\> Ld Ld LdLaunch dateplanned in 1999u(FGM#jP"N ,R׉Country of originUnited Kingdomy,)GHM#jX"H̀‰MissionMilitary: telecommunications\GsHA#R6,Geostationary orbit1WjHHM#j:" &2!Launch vehicleArianeQsH.IA#R Launch siteHI+ $C2!Contract value: 130 million including delivery-in-orbit of the satellite, with Ariane launch and operational control and in-orbit testing before turnover.8.I2J' "(Technical datap2IJ> Ld"N ,bCountry of originJapanUI G#^"H̀Mission^hA#R:"Perigee/Apogee516/754 kmV A#R*Inclination31.3ThA#R&Period97.4 mink}M#j<" & Launch vehicleMu 3S 2ZA#R2Launch siteKagoshima&}# <9' *O External resourcesS,' Xhttp://bang.lanl.gov/solarsys/yohkoh.htmE91Xs " I Program: SolidaridadQ" 5 ::mF" Program: Solidaridad'I : B'e`tz6w Mexican telecommunication program operated by Telecomm. Replaces MorelosThe Movisat network is composed of a band L transponder and a Ku band transponder in each Solidaridad satellite.This program is now controlled by Satmex1" z 1t z t:I : DtwL2L2Program: SolidaridadSolidaridad 1Solidaridad 21z  1Uu  B a # >Solidaridad's specifications\ A#R60&Prime contractorHughesTa  A#R&0PlatformHS-601[ l A#R40"Mass at launch2740 kgZ A#R20 Mass in orbit1650 kgc"l ) A#RD0Dimension2.27 x 2.27 x 2.27 m\ A#R60Solar array18.3 m spanY) A#R00 Stabilization3 axisT 2A#R&0DC power3300 W] A#R80$Design lifetime14 years$2" 11Wv 8^T+8) "VȠ$To view this page you need to register&^# 181Uw #BGB:^# .Solidaridad's L-bandX-@A#R.0-@^(Main transponders1Y@A#R00,Backup transpondersP-@@A#R0Power100 WU@+AA#R(0Bandwidth34 MHzN @yAA#R0CoverageT+AAA#R&0EIRP max45 dBWVyA#BA#R*0PolarizationRHCP$AGB" 1#BxB1Wx xBBBT+GBB) "VȠ$To view this page you need to register&xBB# 1B#C1Uy #CE F:B]C# .Solidaridad's C-bandY#CCA#R00(Main transponders18Y]CDA#R00,Backup transpondersg%CvDB#TJ0Power10 W (36 MHz)14 W (72 MHz)LDEB#T0Bandwidth12 transponders of 36 MHz6 transponders of 72 MHz (on spot 1)JvDEC#V0,Coverage & EIRP maxSpot 1: 40.5 dBWSpot 2: 37.5 dBWSpot 3: 37.5 dBWXEEA#R.0Polarizationlinear$E F" 1E>F1Wz >FFFT+ FF) "VȠ$To view this page you need to register&>FF# 1FF1U{ F I/I;F$G# 0Solidaridad's Ku-bandYF}GA#R00(Main transponders16X$GGA#R.0Power42.5 W (TWTA)U}G*HA#R(0Bandwidth54 MHzFGHC#V0,Coverage & EIRP maxSpot 4: 47 dBWSpot 5: 46 dBWSpot 6: 45.5 dBWX*H IA#R.0Polarizationlinear$H/I" 1 I`I1W| `IIIT+/II) "VȠ$To view this page you need to register&`II# > IJ1$} JbJUNSolidaridad 1JIbJ5 :,mF" Solidaridad 11 JJ'  Generalg bJJG#^@") Designation22911 / 93073A\JVKA#R6Launch date20 Nov 1993m JKM#j@"N ,Country of originMexicoo"VK2LM#jD"H̀‰MissionTelecommunicationsh!KLG#^B"/ۀ0Geostationary orbit109.2Wn!2LMM#jB" &D+Launch vehicleAriane V61&L.M# 8MfM' "(Technical datam/.MM> L^ql'2SpecificationsL-bandC-bandKu-band=fMN' , EIRP coverage (dBW)EMUN0 0*⽱*<2.C-bandKu-band> NN1.т~ NNقSolidaridad 2JUNN5 :,mF" Solidaridad 21 NO'  Generalg NuOG#^@") Designation23313 / 94065A[OOA#R4Launch date8 Oct 1994m uOIM#j@"OIUNN ,Country of originMexicoo"OM#jD"H̀‰MissionTelecommunicationsfIG#^>"/ۀ0Geostationary orbit113Wn!M#jB" &D+Launch vehicleAriane V68&# 8' "(Technical datam/W> L^ql'2SpecificationsL-bandC-bandKu-band=' , EIRP coverage (dBW)EWق0 0*⽱*<2.C-bandKu-band1 1 aW!قa6 1y >Solrad 09J8 @&J\" Solrad 09=># 4Also called Explorer 371 '  Generalg ]G#^@") Designation03141 / 68017A[A#R4Launch date5 Mar 1968t'],M#jN"N ,㹌לCountry of originUnited States2M#jd"H̀jMissionScientific: observation if the sun^, A#R:"Perigee/Apogee353/433 kmV_A#R*Inclination59.3T A#R&Period92.4 minm _ M#j@" &g'KLaunch vehicleScout #60&F# 5 {'  End of lifeVFA#R*Decay16 Nov 1990${" : /13 /y Solrad 10Jy8 @&J\" Solrad 10=/# 4Also called Explorer 441 y'  Generalg NG#^@") Designation05317 / 71058A[A#R4Launch date8 Jul 1971t'N M#jN"N ,㹌לCountry of originUnited States2 M#jd"H̀jMissionScientific: observation if the sun^ A#R:"Perigee/Apogee433/632 kmV P A#R*Inclination51.1T A#R&Period95.2 minm P  M#j@" &g'KLaunch vehicleScout #74& 7 # 5 l '  End of lifeV7 A#R*Decay15 Dec 1979$l " ; ! 1 ! l @Solrad 11AK l 8 @(J\" Solrad 11A1 ! '  Generalg l  G#^@") Designation08748 / 76023C\ ` A#R6Launch date15 Mar 1976t' M#jN"N ,㹌לCountry of originUnited States_` 3G#^0"H̀MissionScientificd# A#RF"Perigee/Apogee118383/119180 kmV3A#R*Inclination25.7VCA#R*Period7344.3 mino"M#jD" &^]Launch vehicleTitan 3 #93$C @"  @ ; G@13 G@@CSolrad 11BK @@8 @(J\" Solrad 11B1 G@@'  Generalg @*AG#^@") Designation08749 / 76023D\@AA#R6Launch date15 Mar 1976t'*AAM#jN"N ,㹌לCountry of originUnited States_AYBG#^0"H̀MissionScientificd#ABA#RF"Perigee/Apogee115720/116645 kmVYBCA#R*Inclination25.6VBiCA#R*Period7116.7 mino"CCM#jD" &^]Launch vehicleTitan 3 #93$iCC" 8C4D1| 4DtDISolwind@CtD2 4"  Solwind74DD# (Also called P78-11 tDD'  Generalg DCEG#^@") Designation11278 / 79017A\DEA#R6Launch date24 Feb 1979t'CEFM#jN"N ,㹌לCountry of originUnited States~1EFM#jb"H߲̀-MissionScientific: high atmosphere study^FFA#R:"Perigee/Apogee310/317 kmVFEGA#R*Inclination97.8TFGA#R&Period90.8 mincEGGG#^8" &Launch vehicleAtlas F[GWHA#R4Launch siteVandenberg&G}H# 5WHH'  End of lifeV}HIA#R*Decay20 Jul 1992&H.I# <IjI' *O External resourcesU..II' \http://lasco-www.nrl.navy.mil/solwind.htmlBjIJ1 1 JFJJProgram: SpacenetEIFJ5 :"o" Spacenet\JJ) "D"American telecommunication program operated by GE Spacenet, a subsidiary of GE Americom1FJJ1 JKaJKO nv?qZIz[Iz\IzdiSProgram: SpacenetSpacenet 1Spacenet 2Spacenet 3Spacenet 3RSpacenet 4 (ASC 2)1JK1U KXO|O?KL# 8Spacenet's specificationsd#KLA#RF0&Prime contractorGE Astro SpaceULLA#R(0PlatformGE 3000[L0MA#R40"Mass at launch1195 kgYLMA#R00 Mass in orbit692 kgc"0MMA#RD0Dimension1.63 x 1.32 x 0.99 m]MINA#R80Solar array14.33 m spanYMNA#R00 Stabilization3 axisYINNA#R00DC powerBOL: 1530 W]NXOA#R80$Design lifetime10 years$N|O" 1XOO1U Oւ7|O # (Spacenet's C-bandO |O[OgA#R40(Main transponders12+6\ ÀA#R60,Backup transponders2+1OgTB#T0Power(12+2) transponders of 8.5 W (TWTA)(6+1) transponders of 16 W (TWTA)BÀ؁B#T0Bandwidth8.5 W transponders: 36 MHz16 W transponders: 72 MHzN T&A#R0CoverageT؁zA#R&0EIRP max36 dBW\&ւA#R60Polarizationlinear H/V$z" 1ւ+1U +8c# *Spacenet's Ku-bandX+A#R.0(Main transponders6ZcA#R20,Backup transponders1VkA#R*0Power16 W (TWTA)UA#R(0Bandwidth72 MHzSkA#R$0CoverageCONUSTgA#R&0EIRP max44 dBWZA#R20Polarizationlinear H$g" ; 1 F g Spacenet 1Gg5 :&o" Spacenet 11 '  Generalg gG#^@") Designation14985 / 84049A\#R6Launch date23 May 1984t'χM#jN"N ,㹌לCountry of originUnited Stateso"[>M#jD"H̀‰MissionTelecommunicationsb!χA#RB,Geostationary orbitsee belown!>M#jB" &gE+Launch vehicleAriane V09+ $ĉWas sold by GTE Spacenet to the Chinese and became Chinasat 5. Then the Chinese found an arrangement with Intelsat for 50% of it's capacity. At the same time China provided a Chinese orbital slot at 110.5E for Intelsat 805.: Y- */ۀ Locationm#:   " BeginEndPositionYij#8$(*L: 23 May 1984102W"j#D46< May 1992May 1992 >120Wiwj#0Feb 1995115.5E&# 8wՌ' "(Technical dataiF \+uEy]|UӇNC-band EIRP coverage (dBW)SpecificationsC-bandKu-bandC-band transponder frequency chartS,Ռ׍' X Ku-band transponder frequency chart (GHz)9sc#r . L HorizontalDownlinkTransponderVerticalUplinkg׍ڎR#t*11.7401914.040gsAR#t*11.8202014.120gڎR#t*11.9002114.200gAR#t*11.9802214.280gR#t*12.0602314.360gR#t*12.1402414.440$ " 1>1 >O 6 <4ZIz"ISpacenet 1's EIRP; >1 M Spacenet 2G5 :&o" Spacenet 2<K# 2Also called Satcom SN21 |'  Generalg KG#^@") Designation15385 / 84114A\|?A#R6Launch date10 Nov 1984t'M#jN"N ,㹌לCountry of originUnited Stateso"?"M#jD"H̀‰MissionTelecommunicationsb!A#RB,Geostationary orbitsee belown!"M#jB" &C+Launch vehicleAriane V11G#9$ FWent inclined after 30 Apr 1997: s- */ۀ Location9m#:   " BeginEndPosition#sj#F$8:L: 10 Nov 1984Jul 199769W j#0Sep 1997115.5E&2# 8 j' "(Technical datai2F \ὸEy]|UӇNC-band EIRP coverage (dBW)SpecificationsC-bandKu-bandC-band transponder frequency chartS,jl' X Ku-band transponder frequency chart (GHz)9c#r . L HorizontalDownlinkTransponderVerticalUplinkgloR#t*11.7401914.040gR#t*11.8202014.120go=R#t*11.9002114.200gR#t*11.9802214.280g= R#t*12.0602314.360grR#t*12.1402414.440$ " 1r1 V 6 LEy]|USpecificationsC-bandKu-band< 1 M U Spacenet 3RH[5 :(o" Spacenet 3R1 '  Generalg wG#^@") Designation18951 / 88018A\A#R6Launch date11 Mar 1988t'wSM#jN"S[N ,㹌לCountry of originUnited Stateso"M#jD"H̀‰MissionTelecommunicationsb!S$A#RB,Geostationary orbitsee belown!M#jB" &D+Launch vehicleAriane V21&$# : - */ۀ Location|m#:   " BeginEndPosition# j#F$8:L: 11 Mar 1988Sep 199787W|j#*Oct 199783W& # 8' "(OTechnical data=#' , EIRP coverage (dBW)VyW |7686rr~Ey]|UӇNC-band, 36 MHz transpondersC-band, 72 MHz transpondersKu-band, East and West spotsSpecificationsC-bandKu-bandC-band transponder frequency chartCarries at least 1 L-band transponder used by Qualcomm Inc. for a localization serviceS,#' X Ku-band transponder frequency chart (GHz)9yhc#r . L HorizontalDownlinkTransponderVerticalUplinkgR#t*11.7401914.040gh6R#t*11.8202014.120gR#t*11.9002114.200g6R#t*11.9802214.280!o#B*,12.0602314.360West spot"1 {#ƀD,.12.1402414.440East spot$U " 11 1 ^(U 6 Up to 4 satellites per slot< ' *O External resourcesBÒ' 6http://www.spaceway.com8' "(OTechnical data8̀=' " Specifications\A#R6&Prime contractorHughesT=A#R&PlatformHS-702TAA#R&"Mass at launchSA#R$ Mass in orbitOAA#RDimensionQ4A#R Solar arraySA#R$ StabilizationN 4ՃA#RDC power]2A#R8$Design lifetime15 years&ՃX# 1 2'  Ka-bandYXA#R0(Main transponders68Y;A#R0,Backup transpondersK A#RPowerK;B#TBandwidth64 x 125 MHz (user terminals)4 x 250 MHz (gateway terminals)k*~A#RTCoveragemultiple steerable spot beamsT҆A#R&EIRP max56 dBW\~.A#R6Polarizationlinear H/VN҆B#TFrequenciesUplink: 28.35-28.60 and 29.25-30.0 GHzDownlink: 19.7-20.2 GHzL%. ' KWith 48 spots (of 650 km diameter)A Time Division Multiplexed (TDM)/Frequency Division Multiple Access (FDMA) scheme is to be used on the user terminal uplinks. On user terminal downlinks, a 130 Mbps TDM signal will be transmitted in each beam from each satellite. Inter-satellite link1;1W ;T+ ) "VȠ$To view this page you need to register&;# A117 CProgram: SpartanMC5 :26lV" Program: Spartan_, &zAmerican scientific program. The satellites are reused to carry experiments in space with the Shuttle. 3-axis spacecrafts.Spartan 203 was destroyed on STS 33, Spartan 202 (UV Stellar Astronomy) and 205 (Plasma Physics) were cancelled<C' *O External resourcesI"_' Dhttp://SPARTANS.GSFC.NASA.GOV/11$ e DQ/̸~XDYDZD[DkӸ~mӸ~nӸ~Program: SpartanSpartan 101Spartan 201-1Spartan 201-2Spartan 201-3Spartan 201-4Spartan 204Spartan 206Spartan 207< D1 DBSpartan 101H5 :(6lV" Spartan 1011 D'  Generalg $G#^@") Designation15831 / 85048E\A#R6Launch date20 Jun 1985t'$M#jN"N ,㹌לCountry of originUnited Statesx+lM#jV"H̀_BMissionScientific: X-ray astronomy^ʏA#R:"Perigee/Apogee359/395 kmVl,A#R*ʏ,Inclination28.5TʏA#R&Period92.1 minj,M#j:" &QLaunch vehicleSTS 25F"0$ DHigh Energy Astrophysics (NRL)5e'  End of lifec"0A#RDCauseRetrieved by the ShuttleVeA#R*Decay24 Jun 1985$B" > 1v ,Spartan 201-1JB5 :,6lV" Spartan 201-11 '  Generalg bG#^@") Designation22623 / 93023Bh'A#RNLaunch date11 Apr 1993 at 06:11 UTt'b>M#jN"N ,㹌לCountry of originUnited States;S#vv"H̀(߲-jMissionScientific: high atmosphere and Sun study^>*A#R:"Perigee/Apogee291/298 kmT~A#R&Inclination57T*A#R&Period90.4 minj~<M#j:" &ӛLaunch vehicleSTS 56[A#R4"Mass at launch1290 kg_<$ It carried an ultraviolet coronagraph and a white light coronagraph for studies of the Sun.5O'  End of lifec"A#RDCauseRetrieved by the ShuttleVOA#R*Decay13 Apr 1993$," > j1: jSpartan 201-2J,5 :,6lV" Spartan 201-21 j'  Generalg LG#^@") Designation23253 / 94059B[A#R4Launch date9 Sep 1994t'LM#jN"N ,㹌לCountry of originUnited Statesr%M#jJ"H̀jMissionScientific: Sun study^A#R:"Perigee/Apogee259/269 kmVAA#R*Inclination56.9TA#R&Period89.5 minjAM#j:" &Launch vehicleSTS 64i$ It carried optical instruments to measure the speed and acceleration of the solar wind in the corona.5'  End of lifec"$A#RDCauseRetrieved by the ShuttleVzA#R*Decay20 Sep 1994$$" < z1 "Spartan 204H"5 :(6lV" Spartan 2041 S'  Generalg "G#^@") Designation23470 / 95004Bg&S!A#RLLaunch date7 Feb 1995 at 12:26 UTt'M#jN"N ,㹌לCountry of originUnited Statesu(!M#jP"H̀_BMissionScientific: UV astronomy^tA#R:"Perigee/Apogee310/342 kmVA#R*Inclination51.6RtA#R"Period91 minjM#j:" &Launch vehicleSTS 63jE% 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.5%'  End of lifec"A#RDCauseRetrieved by the ShuttleU%A#R(Decay9 Feb 1995$" > ?1O: ? Spartan 201-3J5 :,6lV" Spartan 201-31 ?'  Generalg !G#^@") Designation23668 / 95048Bg&A#RLLaunch date8 Sep 1995 at 16.43 UTt'!M#jN"N ,㹌לCountry of originUnited Statesr%nM#jJ"H̀jMissionScientific: Sun studyTA#R&"Perigee/ApogeeQnA#R InclinationL _A#RPeriodjM#j:" &Launch vehicleSTS 69g_0J#d:$Mass at launch2209 kgc< ' yCarried the IEH-1 (International EUV Hitchhiker) built by the Smithsonian Astrophysical Observatory. This includes a solar EUV telescope (SEH), and an Italian-US EUV telescope, UVSTAR, which will observe a variety of astronomical targets in the 500-1250A range. Prime target for this mission is Io plasma torus around Jupiter. Comet 6P/D'Arrest, currently near perihelion, may also be observed. UVSTAR has two 0.3 m telescopes. The spacecraft also carried the GLO-3 airglow experiment in a canister and the CONCAP materials processing experiment in another canister.50 '  End of lifec" + A#RDCauseRetrieved by the ShuttleX A#R.Reentry18 Sep 1995$+ " < 1I + BSpartan 206H + 5 :(6lV" Spartan 206jG # Also called OAST (Office of Aeronautical and Space Technology) Flyer1 + '  Generalg - G#^@") Designation23763 / 96001B\ A#R6Launch date11 Jan 1996t'- M#jN"N ,㹌לCountry of originUnited Statesr% oM#jJ"H̀jMissionScientific: Sun study^ A#R:"Perigee/Apogee302/311 kmVo#A#R*Inclination28.5L oA#RPeriodj#M#j:" &%Launch vehicleSTS 72oA% A Carried an experiment to measure contamination caused by spacecraft outgassing, and a test of a laser-fired explosive separation device to make sure the device doesn't go off accidentally in sunlight. It also carried an amateur radio experiment.58A'  End of lifec"AAA#RDCauseRetrieved by the ShuttleX8AAA#R.Reentry20 Sep 1994$AB" < ASB1  SBBOSpartan 207HBB5 :(6lV" Spartan 2071 SBB'  Generalg B3CG#^@") Designation23871 / 96032B\BCA#R6Launch date19 May 1996t'3CDM#jN"N ,㹌לCountry of originUnited Statesr+CuDG#^V"H̀MissionInflatable Antenna Experiment^DDA#R:"Perigee/Apogee280/290 kmTuD'EA#R&Inclination39TD{EA#R&Period90.1 minj'EEM#j:" &*Launch vehicleSTS 77{EH% uThe IAE is an inflatable antenna 14 meters in diameter which is mounted on three 28m struts. The struts are attached to the Spartan spacecraft, which were deployed and then recovered by the Shuttle. Once in low-Earth orbit, the Spartan became a platform for the antenna which, once inflated in space, was roughly the size of a tennis court. An optical system surveyed the antenna and measured the accuracy of the surface at a variety of internal pressures and thermal conditions. The antenna was developed by L'Garde Inc., of Tustin, CA, a small aerospace business, and NASA's Jet Propulsion Laboratory (JPL) of Pasadena, CA, under NASA's In-Space Technology Experiments Program., or IN-STEP.mEVL% The IAE experiment is meant to lay the groundwork for future technology development in inflatable space structures, which will be launched and then inflated like a balloon on-orbit. SP207/IAE will validate the deployment (inflation) and performance of a large inflatable antenna during a ninety-minute mission before jettisoning the antenna structure and recovering the Spartan spacecraft at mission end. The inflation process will be captured by the crew on the nearby Shuttle, using a variety of still cameras, a motion picture camera, and video cameras. The on-orbit performance of the antenna (surface accuracy) will be determined by illuminating the antenna surface with light panels mounted on the Spartan and capturing the resulting patterns on video recorders onboard the Spartan. These will be analyzed after the Spartan is returned to Earth by the Space Shuttle.HKM+ $YDIAE was ejected from Spartan once the experiment has completed (just the Spartan carrier with the experiment recorders was returned to the cargo bay). This is the same carrier as for Spartan 201-25VLM'  End of life\KMMA#R6"Out of serviceMay 1996EMbNA#RCauseRetrieved by NASA (IAE burned up into atmosphere on 22 May)&MN# <bNN' *O External resourcesO(NO' Phttp://sspp.gsfc.nasa.gov/sp207.html> NQO1mI QOOSpartan 201-4JOO5 :,6lV" Spartan 201-41 QOO'  Generalg O?G#^@")O?O Designation25062 / 97073B\OA#R6Launch date21 Nov 1997t'?M#jN"N ,㹌לCountry of originUnited States{4G#^h"H̀MissionSOHO Calibration & Spartan DevelopmentZA#R2"Perigee/Apogee296 kmV:A#R*Inclination28.5L A#RPeriodj:M#j:" &ULaunch vehicleSTS 87XHD#X($Mass at launchB' Mission duration planned: 16 days In fact the initial deployment failed (pre release activation was not done). The satellite could not be later released by lack of propellant on Columbia.Worth $10 million5Hw'  End of life_BքA#R<"Out of service21 Nov 1997[w1A#R4CauseRetrieved by STS&քW# <1' *O External resourcesM&W' Lhttp://SPARTANS.GSFC.NASA.GOV/201/> 1W lProgram: SpasNl8 @.ℨG" Program: Spas& Shuttle PAllet SatelliteReusable free-flying multi-purpose platform on which experiments can be carried into space by the space shuttle.1lP1 Po.A R\~b竀c竉d竉Program: SpasSpas 1Spas 2Spas 31P1U C3) "4~Spas's specificationsYA#R0&Prime contractorMBBY3A#R0 Stabilization3 axis^CA#R:(Total system mass3600 kgYA#R0Payload mass2000 kg`CA#R>0Length in payload bay1.7 mb!^A#RB&Mission lifetime4 to 10 daysc"A#RD(Electrical energyup to 70 kWh$^" 11U ŏ I _) "@~Astro Spas's specificationsYA#R0&Prime contractorMBBc"_A#RD(Total system mass3200-3600 kg]xA#R8Payload mass500-2000 kga ٌA#R@0Length in payload bay4.05 m`x9A#R>.Width (basic system)1.75 m_ٌA#R<.Width (with payload)2-3 mR9A#R"Height4.05 mYCA#R0 Stabilization3 axisb!A#RB&Mission lifetime4 to 10 days=C$B#Tz(Electrical energy110 kWh (batteries)30-50 kWh (payload)^ŏC#V2Frequency (to Shuttle)S-band: 2.04885/2.2250 GHzto Shuttle: 16 kbpsFrom Shuttle: 2 kbps$$ " ŏ 7ŏC1_ CkSpas 1G 8 @ ℨG" Spas 11 C'  Generalg "G#^@") Designation14142 / 83059F\~A#R6Launch date18 Jun 1983n!"M#jB"N , Country of originGermany_~KG#^0"H̀MissionScientific^A#R:"Perigee/Apogee295/300 kmVKA#R*Inclination28.5TSA#R&Period90.5 minjM#j:" &㫜Launch vehicleSTS 07&S# 5'  End of lifec"{A#RDCauseRetrieved by the ShuttleVA#R*Decay24 Jun 1983&{# 8/' "(Technical data<k) "&婦Specifications7/1KԂ Spas 2Gk8 @ ℨG" Spas 26# &Also called IBSS1 P'  Generalg G#^@") Designation21244 / 91031B\PA#R6Launch date28 Apr 1991t'M#jN"N ,㹌לCountry of originUnited States_G#^0"H̀MissionScientific^DA#R:"Perigee/Apogee245/255 kmTA#R&Inclination57TDA#R&Period89.5 minjVM#j:" &〛Launch vehicleSTS 39&|# 5V'  End of lifec"|A#RDCauseRetrieved by the ShuttleUiA#R(Decay6 May 1991&# 8i' "(Technical data<) "&婦Specifications7:1_l :Spas 3G8 @ ℨG" Spas 3sP:# Also called Orfeus (Orbiting and Retrievable Far and Extreme UV Spectrometer)1 %'  Generalg G#^@") Designation22798 / 93058C\%A#R6Launch date12 Sep 1993n!VM#jB"N , Country of originGermanyj#G#^F"H̀MissionScientific: AstronomyRVA#R"OperatorDARA^pA#R:"Perigee/Apogee301/331 kmVA#R*Inclination28.5TpA#R&Period90.9 minjM#j:" &ΛLaunch vehicleSTS 51]% The main instrument is the 1-meter Orfeus telescope with EUV (400-1150A) and far UV (900-1250A) spectrometers with high spectral resolution. A secondary experiment is the Princeton Interstellar Medium Absorption Profile Spectrograph which studied very fine structure in ultraviolet absorption lines caused by interstellar gas in stellar spectra.5G'  End of lifec"A#RDCauseRetrieved by the ShuttleVGA#R*Decay22 Sep 1993&&# 8^' "(Technical data<&) "&aSpecifications7^1Ԃ Spas 4G8 @ ℨG" Spas 48P# *Also called Crista1 '  Generalg PG#^@") Designation23341 / 94073B[CA#R4Launch date4 Nov 1994n!M#jB"N , Country of originGermany_CG#^0"H̀MissionScientific^nA#R:"Perigee/Apogee296/310 kmTA#R&Inclination57TnA#R&Period90.6 minjM#j:" &Launch vehicleSTS 66[A#R4"Mass at launch3500 kgcb$ It carried spectraphotometers to monitor gases in the middle atmosphere and lower thermosphere.5'  End of lifec"bA#RDCauseRetrieved by the ShuttleVPA#R*Decay12 Nov 1994&v# 8P' "(Technical data<v) "&aSpecifications> ( 1 7 ( r NProgram: SpotJr 5 :,ߪG" Program: Spot(( 1 0 Satellite Pour l'Observation de la TerreFrench 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 explorationr z 7 " &2!Launch vehicleAriane 5Q A#R Launch siterNx;$ The satellite and launch and associated expenses should total $400 million8s' "(OTechnical data8;' " SpecificationsYsA#R0&Prime contractorMMSUeA#R(PlatformMark 2+\A#R6"Mass at launch~3000 kgSeA#R$ Mass in orbitOcA#RDimensionQA#R Solar arrayScA#R$ StabilizationT[A#R&DC power2800 WUA#R($Design lifetime,[+ $hWill have CCDs at 12000 points providing a 5 m resolution on 60 km swath width. Will have the same onboard recorders as Helios 2 Will provide 10 m resolution in multispectral mode and 20 m in infrared mode. Should also carry the vegetation instrument.1 1W aT+a) "VȠ$To view this page you need to register& # 7a1f㆏ 6 Spot 6C5 :ߪG" Spot 645# "Also called 3S1 f'  GeneralY5G#^$") Designation`fA#R>Launch dateplanned in 2004m M#j@"N ,㱭+Country of originFranceUG#^"H̀MissionT5A#R&"Perigee/ApogeeQA#R InclinationL 5A#RPeriod\.G#^*" &Launch vehicleQA#R Launch site.6 % %Will have a 2.5 m resolution and 60 to 100 km view span. Based on a Proteus platform, this is a much smaller satellite than the other Spots. 1g 1W g T+6 ) "VȠ$To view this page you need to register&g # >  1|  i Program: SretJ i 5 :,⣷G" Program: Sret}U ( Satellite de Recherche et d'Etudes TechnologiquesFrench experimentation program1i  1  v _% v : DJITJTProgram: SretSret 1Sret 27 1% @Sret 1Cv 5 :⣷G" Sret 11 ! '  Generalg G#^@") Designation05928 / 72025B[! A#R4Launch date4 Apr 1972m P M#j@"N ,㱭+Country of originFranceo( G#^P"H̀MissionTechnology experimentation`P A#R>"Perigee/Apogee480/39248 kmV uA#R*Inclination65.6SA#R$Period735 min\u$G#^*" &Launch vehicleY}A#R0Launch sitePlesetskY$A#R0"Mass at launch15 kgR.}4@$ \Tech4@v nological satellite to test solar cell5i@'  End of lifeV4@@A#R*Decay26 Feb 1974$i@@" 7@A1l A]AESret 2C@]A5 :⣷G" Sret 21 AA'  Generalg ]AAG#^@") Designation07910 / 75049B[APBA#R4Launch date6 Jun 1975m ABM#j@"N ,㱭+Country of originFranceo(PB,CG#^P"H̀MissionTechnology experimentation`BCA#R>"Perigee/Apogee513/40825 kmV,CCA#R*Inclination62.8UC7DA#R(Period737.8 min\CDG#^*" &Launch vehicleY7DDA#R0Launch sitePlesetskYDEEA#R0"Mass at launch30 kgS/DE$ ^Tested a passive cryogenic radiative system?EEE1c E"FFProgram: SrossKE"F5 :. e" Program: Srossd<EF( x Streach ROhini Sat ServicesIndian experimental program1"FF1 F"N ,&‰Country of originIndia_EHIG#^0"H̀MissionScientifickH{IM#j<" &#Launch vehicleASLV #1[II$ Carried a measurement payload for the launch vehicle and a Gamma-ray astronomy payload.5{I/J'  End of life_IJA#R<"Out of service24 Mar 1987Y/JJA#R0Causelaunch failure$J K" 8JCK1 ] CKKNSross 2D KK5 : e" Sross 21 CKK'  General\KLA#R6Launch date12 Jul 1988lKLM#j>"N ,&‰Country of originIndia_LLG#^0"H̀MissionScientifickLJMM#j<" &#Launch vehicleASLV #2zVLM$ Carried a German (MEsOSS) remote sensing payload and a gamma-ray astronomy payload5JMM'  End of life_MXNA#R<"Out of service12 Jul 1988YMNA#R0Causelaunch failure$XNN" 8N O17 OQOăSross 3DNQO5 : e" Sross 39 OO# ,Also called Sross C1 QOO'  Generalg O.G#^@") O.NDesignation21968 / 92028A\OA#R6Launch date20 May 1992l.M#j>"N ,&‰Country of originIndiaUKG#^"H̀Mission^A#R:"Perigee/Apogee251/436 kmTKA#R&Inclination46TQA#R&Period91.4 minkM#j<" &#Launch vehicleASLV #3Y5Q$ jCarried Gamma Ray astronomy and aeronomy payload.5J'  End of lifeVA#R*Decay14 Jul 1992$Jă" 91] B Sross C2EăB5 :" e" Sross C21 s'  Generalg BڄG#^@") Designation23099 / 94027A[s5A#R4Launch date4 May 1994lڄM#j>"N ,&‰Country of originIndiay,5M#jX"H̀?vMissionScientific: ionosphere study^xA#R:"Perigee/Apogee430/619 kmT̆A#R&Inclination46Tx A#R&Period95.1 mink̆M#j<" &#Launch vehicleASLV #4Z A#R2"Mass at launch113 kg$ - (㇊D􉂂It carried a Retarding Potential Analyzer (RPA) for measuring ionospheric plasma, and a Gamma ray detector. Is identical to Sross 3Beacon freq.: 137.400 MHz It operates only on command so data reception is limited to sites close to India.5>1| >SSTPF 2 4*"  Program: SSTPyQ>( Space Spacecraft Technology Programplanned for 1995, 230 kg, remote sensing1.1W .T+) "VȠ$To view this page you need to register&.# 5݊1 ݊ST 15 , (" ST 11 ݊C'  GeneralYG#^$") Designationf%CA#RJLaunch dateplanned in early 1998q*sG#^T"N ,Country of originSingapore & Taiwan=G#^zOperatorSingapore Telecom and Chunghwa Telecom (50/50)o"sfM#jD"H̀‰MissionTelecommunications]ÍA#R8,Geostationary orbit88Ejf-M#j:" &2!Launch vehicleArianeYÍG#^$Launch site-4% To be delivered in-orbit. Contract worth $240 million (with 2 control centers in Seletar, Singapour and Taipei, Taiwan; and training)<p' *O External resourcesF4' >http://www.singtel.com/ST1/8p ' "(OTechnical data =I' , EIRP coverage (dBW)E 0 0*eptC-bandKu-band8I' " Specificationsi(/A#RP&Prime contractorMatra Marconi Space[A#R4PlatformEurostar 2000[/A#R4"Mass at launch3000 kgS8A#R$ Mass in orbitOA#RDimensionQ8A#R Solar arrayS+A#R$ StabilizationTA#R&DC power6500 W]+A#R8$Design lifetime12 years&# 0 2'  C-bandYA#R0(Main transponders14Y2A#R0,Backup transpondersK /A#RPowerO~A#RBandwidthm&/G#^LepCoveragemiddle to far East AsiaT~?A#R&EIRP max40 dBWVA#R*G/T max-2.1 dB/K\?A#R6Polarizationlinear H/V&# 1 H'  Ku-bandYA#R0(Main transponders16YHA#R0,Backup transpondersZTA#R2Power90-135 W (TWTA)OA#RBandwidthGT8N#l*ttCoverageK1: Taiwan, Philippines, Malaysia, SingaporeK2: Indiad"B#TDEIRP maxK1: 53 dBWK2: 52 dBWc!8B#TBG/T maxK1: 5 dB/KK2: 3 dB/K\#R6Polarizationlinear H/VR.$ \Transponders are switchable on either beam1[1W 2XT+2) "VȠ$To view this page you need to register&X# 121 PX6 <6maU"NST 1's C-band EIRP1 1W ^T+^) "VȠ$To view this page you need to register& # 1^1 Q6 <8maU"OST 1's Ku-band EIRP171W 7T+) "VȠ$To view this page you need to register&7# : 1Z %Starlette:%, (" StarlettepM#  Satellite de Taille Adapte avec Rflecteur Laser pour l'ETude de la TErre1 %'  Generalg -G#^@") Designation07646 / 75010A[A#R4Launch date6 Feb 1975m - M#j@"N ,㱭+Country of originFrance p#|M#jF"H̀CV$MissionScientific: geodesyR A#R"OperatorCNES_|-A#R<"Perigee/Apogee805/1108 kmVA#R*Inclination49.8U-A#R(Period104.2 mino"GM#jD" &A͉Launch vehicleDiamant #10YA#R0"Mass at launch47 kg{WG$ Sphere of 24 cm of uranium covered with reflectors. Measured the continental drift.<W' *O External resources`9' rhttp://dgfi3.dgfi.badw-muenchen.de/edc/starlette.htmlBW1 ;Program: StarliteB;, (." Program: StarliteX2& eUS military project lead by DARPA. This would be a constellation of 24 satellites configured with Synthetic Aperture Radar (SAR) to allow direct tasking control to a deployed tactical commander. The constellation would allow for a very rapid revisit rate (about 15 minutes) to most areas of the earth. The system would be capable of generating very high resolution elevation data (1 meter post spacings) and highly accurate radar imagery.Two satellite should be built in 2000 for demonstration purposes. If successful the system should be deployed in 2005.1;1W >T+) "VȠ$To view this page you need to register&># A1*Z  Program: StarsysA>, (," Program: StarsysR& , &MD"GE program made of 24 LEO satelllites to be built by Alcatel Telecom (MMS will supply the Leostar busses). Can provide tracking and monitoring services around the globe. GE Americom concluded the acquisition of an 80% interest in Starsys Global Positioning, Inc.These satellites will operate in the VHF/UHF frequency bands, and will have the capability for adaptive on-board filtering of terrestrial interference. The 80 kg (approx.) spacecraft will be used to relay short data packet bursts between a gateway site and small remote terminals.=O ) )GE Starsys will offer satellite-based data messaging services for a variety of applications, including fleet and cargo management, logistics, remote data collection and asset security. Transportation service providers will use GE Starsys to monitor their assets, increasing their fleet productivity and effectiveness.As currently envisioned, the system will consist of up to 24 orbit-controlled satellites at 965 km in altitude. Each bird should weigh 70 kg.Alcatel will aslo provide the control stations and the terminals.j@ * $ Program was abandonned in 1997, its licence is now on sale1O 1W > d T+ > ) "VȠ$To view this page you need to register& d # 7> 1?\ EStella7 d , (" Stella1 '  Generalg jG#^@") Designation22824 / 93061B\A#R6Launch date26 Sep 1993m j3M#j@"N ,㱭+Country of originFrancep#M#jF"H̀CV$MissionScientific: geodesy^3 @A#R:"Perigee/Apogee793/803 km @d Vc@A#R*Inclination98.7U @@A#R(Period100.8 minn!c@&AM#jB" &D+Launch vehicleAriane V59&@LA# 8&AA' "(OTechnical data8LAA' " SpecificationsZABA#R2&Prime contractorCNESN AdBA#RPlatformYBBA#R0"Mass at launch48 kgSdBCA#R$ Mass in orbit\BlCA#R6Diameter24 cm (sphere)SCCA#R$ StabilizationN lC DA#RDC powerUCbDA#R($Design lifetimeO DE1 0?1Its a sphere of 24 cm diameter with 20 sides and 60 laser reflectors. As Starlette or Lageos 2 Stella is designed to be tracked by laser (1 cm accuracy) by ground stations all around the world (in France: le Cergue in Grasse). It is made of impoverish uranium for the maximum stability. Will enable to make a map of the globe. > bD F1ˀ FjFIHprogram: StepJEjF5 :,G" Program: Step FG& Space Test Experiment PlatformAmerican small satellite program to test technology. The STEP program is run by the DoD Space Test Program (SMC/TEL) an office of the Space and Missile Systems Center, Test and Evaluation Directorate (SMC/TE).<jFG' *O External resources[GIH. ,http://www.te.plk.af.mil/factsheet/telfact.htmlhttp://www.te.plk.af.mil/orbital.html1GzH1 zH I@IH IO n j󼬉󼬉󼬉󼬉Program: StepStep 0Step 1Step 2Step 3Step 47zH@I16 @IIMStep 1C II5 :G" Step 17@II# (Also called P90 A1 II'  General\IGJA#R6Launch date27 Jun 1994t'IJM#jN"N ,㹌לCountry of originUnited Statesi"GJ$KG#^D"H̀MissionMilitary: technologys&JKM#jL" &GKTLaunch vehiclePegasus #6 (XL)&$KK# 5KK'  End of life_KQLA#R<"Out of service27 Jun 1994p/KLA#R^CauseDestroyed on launch with the launcher2 QLM' Operated by USAF and built by TRW from an Eagle platformIt carried radio propagation experiments, a plasma environment analyser, the CHAMPION ionosphere-magnetosphere coupling experiment, and an accelerometer and mass spectrometer to study the upper atmosphere.7L*N1C *NmNׂStep 2CMmN5 :G" Step 27*NN# (Also called P91 A1 mNN'  Generalg N|$x\v`,xCosmos 1992Cosmos 2056Cosmos 2112Cosmos 2150Cosmos 2208Cosmos 2251k#4"-x $(,0Cosmos 2298&# 2 k' (OStrela 2) 7 Those satellites were launched 8 at a time, more or less in the same plane. They were used for military radio communications.Specifications overview:VA#R*&Prime contractorN 7A#R7PlatformRA#R"Mass~ 200 kgO7A#RDimensione$=A#RH"Perigee/Apogeecircular, 1500 kmTA#R&Inclination74S=A#R$ Orbital cycle^BA#R:$Design lifetime1.5 yearsf<* $x㓉The full list of satellites launched is available here2 B' (OStrela 3/ ,ቂ Launched by 6, those satellites offer realtime and store and forward data communications between military aircraft, ships and bases. Also called Locsyst. All crafts were launched onboard Cyclone 3Specifications overview:\IA#R6&Prime contractorNPO PMN A#RPlatformPIA#RMass225 kgO6A#RDimensione$A#RH"Perigee/Apogeecircular, 1400 kmV6A#R*Inclination82.6SDA#R$ Orbital cycle\A#R6$Design lifetime2 years7D'   Satellites:Qt#"BbCosmos 1617-22Cosmos 1690-95Cosmos 1827-32Cosmos 1875-80Cosmos 1909-14Uq#Ѐ" )w&exJjCosmos 1994-99Cosmos 2038-43Cosmos 2090-95Cosmos 2114-19Cosmos 2143-48bM z#Ā"B9,xCosmos 2157-62Cosmos 2165-70Cosmos 2197, 2198, 2200, 2202Cosmos 2211-16Cosmos 2245-50aq@ #"a,x&,xJ-xr3xI3xCosmos 2252-57Cosmos 2268-73Cosmos 2299-2304Cosmos 2328-2330Cosmos 2337-2339&M f # > @ 1ˀ t Program: STRVJf 5 :,FG" Program: STRV , &o Space Technology Research VehicleEnglish experimental program operated by DRA (Defence Research Agency), the new name for the RAE (Royal Aircraft Establishment). RAE was the lead agency for all of Britain's technology(as opposed to science or communications) satellites.Designed to test spacecraft systems and technologies in orbit and investigate the effect of high radiation doses, atomic oxygen erosion and spacecraft charging.< ' *O External resourcesg@ t ' http://www.ee.surrey.ac.uk/EE/CSER/UOSAT/SSHP/data_strv.html1 1 a't : DN@djdjProgram: STRVSTRV 1ASTRV 1B1 71U 7@A;r# 0STRV's specificationsE7A#R0&Prime contractorDRA (Defense Research Agency) Aerospace Division[rSA#R40"Mass at launch~ 50 kgc"A#RD0Dimension0.45 x 0.45 x 0.47 mb!S$@A#RB0 Stabiliz$@ationSpin stabilizedb @B#T@0DC powerBOL: 27 WEOL: 24 W[$@@A#R40$Design lifetime1 year$@A" 1@6A1U 6A C0CpAA( STRV's PayloadSeveral instruments to measure radiation dose, particle fluxes, electrostatic charging, etc._6A-BA#R<0,Telemetry data rate1 kbpsa ABA#R@0(Transmitter power0.5 W, 2 W~<-B CB#Tx0FrequenciesUplink: 2.025-2.12 GHzDownlink: 2.2-2.3 GHz$B0C" 8 ChC1gX hCCHSTRV 1AD0CC5 : FG" STRV 1A1 hCC'  Generalg CDDG#^@") Designation23125 / 94034B\CDA#R6Launch date17 Jun 1994u(DDEM#jP"N ,R׉Country of originUnited Kingdomi"D~EG#^D"H̀MissionMilitary: technology`EEA#R>"Perigee/Apogee251/35518 kmU~E3FA#R(Inclination7.3SEFA#R$Period627 minn!3FFM#jB" &D+Launch vehicleAriane V64]FQGD#X2"Mass at launch50 kgFHH& Carries experiments to study surface erosion effects on spacecraft materials, a cosmic ray detector, and a gamma ray burst experiment. Will test new solar cells and measure static charge on its surfaces. 8QGH' "(Technical datab0HHH2 4`]auSpecificationsPayloadSpin rate: 10 rpm8HI1( I^INSTRV 1BDH^I5 : FG" STRV 1B1 II'  Generalg ^IIG#^@") Designation23126 / 94034C\IRJA#R6Launch date17 Jun 1994u(IJM#jP"N ,R׉Country of originUnited Kingdomi"RJ0KG#^D"H̀MissionMilitary: technology`JKA#R>"Perigee/Apogee239/35588 kmU0KKA#R(Inclination7.3SK8LA#R$Period628 minn!KLM#jB" &D+Launch vehicleAriane V64]8LMD#X2"Mass at launch53 kgeALhM$ Carries an experimental cooler, solar cells, and electronics.8MM' "(Technical dataa/hMN2 4^]auSpecificationsPayloadSpin rate: 5 rpm7M8N18  8NoN~Sunsat7 NoN, (" Sunsat1 8NN'  GeneralYoNNG#^$") Designationd#N]OA#RFLaunch dateplanned in mar 1997k$NOG#^H"N ,Country of originSouth Africak$]O?G#^H"H̀O?NMissionTelecommunication, HAM`OA#R>"Perigee/Apogee400 / 830 kmQ?A#R InclinationL <A#RPeriodkM#j<" &p㉂Launch vehicleDelta 2Q<A#R Launch siteXw' Micro satellite being designed, built and tested by students at the Electronic Systems Laboratory in the Department of Electrical and Electronic Engineering at Stellenbosch University. In exchange for a US National Aeronautics and Space Administration launch, Sunsat will carry a precision GPS receiver and a set of Laser retro-reflectors, for NASA's use.The payload includes duplicate transmitters and receivers for the 2-meter and 70-cm bands, a 24-cm (1260 Mhz) receiver and 13-cm (2400-MHz) receiver. A number of uplink and downlink frequency combinations are possible. Sunsat will offer extensive digital communication capability. One of the 2-meter receivers has four IF sections connected to 1200-baud AFSK packet modems. The satellite carries three G3RUH-compatible 9600-baud modems that can be switched to various receivers and transmitters.1 ' O Contactkw9& SED, University of Stellenbosch, Stellenbosch, 7600, South AfricaTel: +27-21-8084103Fax:+27-21-8084981<u' *O External resources~P9. ,http://esl.ee.sun.ac.za/http://www.amsat.org/amsat/sats/n7hpr/sunsat.html8u+' "(OTechnical data8c' " SpecificationsV+A#R*&Prime contractorN cA#RPlatformY`A#R0"Mass at launch60 kgSA#R$ Mass in orbit^`A#R:Dimension45 x 45 x 62 cmQbA#R Solar arraySA#R$ StabilizationN bA#RDC powerUXA#R($Design lifetime&~# 1X1W )T+~) "VȠ$To view this page you need to register&)# Cl1 lProgram: SuperbirdO)5 :6⻊f" Program: Superbird`7l) "nOJapanese telecommunication program operated by SCC1L1 LoV |Y'# OOO_Sk7`Sk7PSk7Program: SuperbirdSuperbird A1Superbird A2Superbird B1Superbird CSuperbird DSuperbird 41LB1U B@# :Superbird's specificationsz9BA#Rr0&Prime contractorFord Aerospace / Space Systems/LoralUQA#R(0PlatformFS 1300[A#R40"Mass at launch2492 kgZQA#R20 Mass in orbit1505 kgb!hA#RB0Dimension2.41 x 2.58 x 2.2 m\ďA#R60Solar array20.3 m spanYh)A#R00 ď)Stabilization3 axisTď}A#R&0DC power4460 W])A#R80$Design lifetime10 years$}" 1/1U /8g# *Superbird's X-bandX/A#R.0(Main transponders2YgA#R00,Backup transpondersVnA#R*0Power40 W (TWTA)UA#R(0Bandwidth40 MHzN nA#R0CoverageTeA#R&0EIRP max37 dBWRA#R"0Polarization$e" 1 1U A9E# ,Superbird's Ku-bandY A#R00(Main transponders23YEA#R00,Backup transpondersVMA#R*0Power50 W (TWTA)UA#R(0Bandwidth36 MHzN MA#R0CoverageTDA#R&0EIRP max53 dBWRA#R"0PolarizationEDB#T0Frequenciesuplink: 14.00 - 14.50 GHzdownlink: 12.25 - 12.75 GHz$A" 1r1U r9A# ,Superbird's Ka-bandXrA#R.0(Main transponders2Y\A#R00,Backup transpondersVA#R*0Power29 W (TWTA)V\A#R*0Bandwidth100 MHzN VA#R0Coverageo-B#TZ0EIRP maxspot beam: 59 dBWothers: 55 dBWRVA#R"0PolarizationEB#T0Frequenciesuplink: 28.40 - 28.80 GHzdownlink: 18.80 - 19.00 GHz$" 11W GmT+G) "VȠ$To view this page you need to register&m# = G10 Superbird A1Im5 :*⻊f" Superbird A11 $'  Generalg G#^@") Designation20040 / 89041A[$A#R4Launch date5 Jun 1989lRM#j>"N ,bCountry of originJapano"M#jD"H̀‰MissionTelecommunicationsk*R,A#RT,Geostationary orbitlife time in 158En!M#jB" &2D+Launch vehicleAriane V31&,# 5'  End of life\QA#R6"Out of serviceDec 1990ZA#R2CausePropellant leak&Q# 8' "(Technicmal datan0> L`8 &(4穉ՉՉSpecificationsX-bandKu-bandKa-band< 1炕 Superbird DH5 :(⻊f" Superbird D5<'  End of life_A#R<"Out of service22 Feb 1990m&<G#^L7D+CauseLaunch failure: Ariane V36&.# 8f' "(Technical datan0.> L`8 &(4穉ՉՉSpecificationsX-bandKu-bandKa-band= f10< ZSuperbird B1IZ5 :*⻊f" Superbird B11 '  Generalg ZG#^@") Designation21893 / 92010A\NA#R6Launch date26 Feb 1992lM#j>"N ,bCountry of originJapano"N)M#jD"H̀‰MissionTelecommunicationsfG#^>"/ۀ0Geostationary orbit162En!)M#jB" &eD+Launch vehicleAriane V49&## 8[' "(Technical dataO#F \8 &(4穉ՉՉ&4SpecificationsX-bandKu-bandKa-bandKu-band EIRP coverage (dBW)1[!1 !zY#z6 "N ,bCountry of originJapano" M#jD"H̀‰MissionTelecommunicationsf_ 4 G#^>"/ۀ0Geostationary orbit158En! M#jB" &D+Launch vehicleAriane V55&4 # 8 ' "(Technical datan0 n > L`8 &(4穉ՉՉSpecificationsX-bandKu-bandKa-band< 1 <* GSuperbird CHn 5 :(⻊f" Superbird C1 # '  Generalg G#^@") Designation24880 / 97036A\# A#R6Launch date28 Jul 1997l R M#j>"N ,bCountry of originJapano" M#jD"H̀‰MissionTelecommunicationsfR 'G#^>"/ۀ0Geostationary orbit144Er% M#jJ" &yjLaunch vehicleAtlas 2AS #108j''$ Investment is evaluated to $416 million including insurance. The satellite alone is worth $100 million8_' "(OTechnical data8'' " Specifications\_ @A#R6&Prime contractorHughes @n T`@A#R&PlatformHS-601[ @@A#R4"Mass at launch3130 kgS`@AA#R$ Mass in orbit`@nAA#R>Dimension2.3 x 2.3 x 2.2 m\AAA#R6Solar array26.6 m spanSnABA#R$ StabilizationTAqBA#R&DC power4500 W]BBA#R8$Design lifetime13 years&qBB# 1 B%C'  Ku-bandYB~CA#R0(Main transponders24Y%CCA#R0,Backup transpondersO~C&DA#RPower90 WUCDC#VBandwidth16 x 27 MHz4 x 36 MHz4 x 54 MHz (convertible to 2 x 114 MHz at 180 W)A&D@EA#RCoveragebeam to Japan, China, Thailand, Australia and HawaiiN DEA#REIRP maxR@EEA#R"PolarizationoEFC#VFrequenciesuplink: 14.00 - 14.50 GHzdownlink: 12.25 - 12.75 GHzdownlink: 11.70 - 12.70 GHz (Hawaii only))EG' In addition to two conventional antennas (2.16 m) the spacecraft will also feature a steerable spot beam designed and built by Mitsubishi to increase service where needed.Superbird C would have 125 MHz of X-band in the payload for mobile communication.< FG1R Z G?HYSuperbird 4HG?H5 :(⻊f" Superbird 41 GpH'  GeneralY?HHG#^$") Designationf%pH/IA#RJLaunch dateplanned in early 2000lHIM#j>"N ,bCountry of originJapano"/I JM#jD"H̀‰MissionTelecommunications^IhJA#R:,Geostationary orbit162E\ JJG#^*" &Launch vehicleIhJ K* $>OWill replace Superbird B18JEK' "(OTechnical data8 K}K' " Specifications\EKKA#R6&Prime contractorHughesV}K/LA#R*PlatformHS-601HPTKLA#R&"Mass at launchS/LLA#R$ Mass in orbitOL%MA#RDimensionQLvMA#R Solar arrayS%MMA#R$ StabilizationN vMNA#RDC powerUMlNA#R($Design lifetime&NN# 1 lNN'  Ku-bandYNOA#R0(Main transponders23YNuOA#R0,Backup transpondersK OOA#RPowerOuOA#ROGBandwidthN OiA#RCoverageN A#REIRP maxM iA#RG/T maxRVA#R"Polarization&|# 1 V'  Ka-bandX|A#R.(Main transponders6Y^A#R0,Backup transpondersK A#RPowerO^A#RBandwidthN FA#RCoverageN A#REIRP maxM FA#RG/T maxR3A#R"Polarization&Y# 131W ބT+Yބ) "VȠ$To view this page you need to register&# : ބ>1K >xSurfsat 1:x, (" Surfsat 1X5>Ѕ# jSummer Undergraduate Research Fellowship SATellite1 x'  Generalg ЅhG#^@") Designation23711 / 95060B[ÆA#R4Launch date4 Nov 1995m h0M#j@"N ,xW Country of originCanada_ÆG#^0"H̀MissionScientific_0A#R<"Perigee/Apogee934/1494 kmWEA#R,Inclination100.6SA#R$Period109 minp#EM#jF" &p㉂Launch vehicleDelta 2 #229emJ#d6$Mass at launch55 kg$' Surfsat is bolted to Delta's second stage. It has its own solar cells and is not electricaly dependent of Delta.Surfsat will be used as a test vehicle for NASA, supporting deep space communications research and training of tracking station personnel at NASA's Deep Space Network. The Deep Space Network transponders will operate in Ka-band at 32 GHz (atmospheric studies). The VLBI transponders (X- and Ku-band) will enable testing of ground equipment for VSOP (Japan) and Radioastron (Russian project).`<m$ xDesigned by Caltech undergraduates with the help of JPL.<-' *O External resourcese>' |http://sgra.jpl.nasa.gov/html_surfsat/SURFSATHomePage.html5-nj1 䄗 njSWAS5 , (" SWAS1 nj-'  GeneralYG#^$") Designatione$-A#RHLaunch dateplanned in late 1999t'_M#jN"N ,㹌לCountry of originUnited Statesr%юM#jJ"H̀_BMissionScientific: Astronomy^_/A#R:"Perigee/Apogee600/650 kmTюA#R&Inclination70L /ϏA#RPeriodn!IM#jB"ϏI &GKTLaunch vehiclePegasus XL[ϏA#R4Launch siteVandenberg&I% The SWAS mission is an outgrowth of the scientific interest in the exploration of the submillimeter wavelength region for astronomy. SWAS will be a pioneering step in submillimeter astronomy in space. The SWAS mission is designed to study molecular clouds in the galactic plane, providing a mini and full survey of the clouds, leading towards the development of maps. It will also perform quick-look chemistry on the structure and content of these molecular clouds, and will research extragalactic sources.<' *O External resources6 :http://sunland.gsfc.nasa.gov/smex/swas/http://www-astro.phast.umass.edu/swas/http://cfa-www.harvard.edu/cfa/oir/Research/swas.html8' "(OTechnical data88' " SpecificationsVA#R*&Prime contractorN 8A#RPlatformZ6A#R2"Mass at launch288 kgXA#R.Payload mass102 kgO6A#RDimensionQ.A#R Solar arrayYA#R0 Stabilization3-axisS.A#R$DC power230 W\6A#R6$Design lifetime2 yearsK#( GTelemetry: 2215 MHz (realtime: 18.75 kbps, playback: 1.8 Mbps), 5 W transmitterCommand: 2039.65 MHz (2 kbps)The instrument consists of an off-axis Cassegrain telescope, receiver, Acousto-Optical Spectrometer (AOS), instrument control electronics (ICE) and a thermal control subsystem.161W ,T+) "VȠ$To view this page you need to register&,# Co1W oProgram: SymphonieO,5 :6=" Program: SymphonieCo, &/ 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 Arospatiale, Thomson CSF, SAT and MBB, Siemens and AEG Telefunken.The program enabled the use of the SAMSON (Station Antenne Miniature pour Service Occasionnel Numrique) portable station: transportable in 2 containers containing telecommunication equipments and a 4.8 m diameter antenna.<=' *O External resourcesR+' Vhttp://www.op.dlr.de/wt-rm/symphony.htm1=1 .n4.: Dhۢ&?a׀@a׉Program: SymphonieSymphonie 1Symphonie 21_1U _@.# :Symphonie's specifications[_A#R40&Prime contractorCIFASN HA#R0PlatformZA#R20"Mass at launch400 kgYHA#R00 Mass in orbit235 kgSNA#R$0Diameter1.7 mQA#R 0Height0.5 m[N A#R40Solar array6.8 m span .FA#R0 Stabilization3 axis (first civilian satellites 3 axis stabilized)d" B#TD0DC powerBOL: 300 WEOL: 180 W\SA#R60$Design lifetime5 yearsq0A#R`0Capacity600 phone circuits or 2 TV channels$S" 11U 8Q# *Symphonie's C-bandXA#R.0(Main transponders2YQA#R00,Backup transpondersK MA#R0PowerUA#R(0Bandwidth90 MHzN MA#R0CoverageTDA#R&0EIRP max30 dBWRA#R"0Polarization$D" < 1K` >X Symphonie 1H>5 :(=" Symphonie 11 o'  Generalg >G#^@") Designation07578 / 74101A\o2A#R6Launch date19 Dec 1974.S#v\"N (, 㱭+Country of originGermany and Franceo"2"M#jD"H̀‰MissionTelecommunicationsb!A#RB,Geostationary orbitsee belows&"M#jL" &p㉂Launch vehicleThor Delta #106_VA#R<Launch siteCape Canaveral&|# 2 V'  Location|8 m#:p   " BeginEndPosition! j#Bp$02L: 19 Dec 1974197711.5W38 ` j#fp$&1977Aug 197949E (for India, STEP project)* j#Tp24Aug 197919 Feb 1983Atlantic ocean&`  # 5 O '  End of life_ A#R<"Out of service19 Feb 1983&O # 8 ' "(Technical dataL X 0 08"ЀBvJSpecificationsC-band< 1J hASymphonie 2HX 5 :(=" Symphonie 21 '  Generalg t G#^@") Designation08132 / 75077A\ A#R6Launch date27 Aug 1975.t QS#v\"N (, 㱭+Country of originGermany and Franceo" M#jD"H̀‰MissionTelecommunicationsg&Q'A#RL,Geostationary orbit26W or 11.5Ws&M#jL" &p㉂Launch vehicleThor Delta #114_' @A#R<Launch siteCape Canaveral @X &2@# 5 @g@'  End of lifeW2@@A#R,"Out of serviceyes&g@@# 8@A' "(Technical dataL@hA0 08"ЀBvJSpecificationsC-band@AA1U䄗 AACProgram: SyncomLhAA5 :0g€" Program: SyncomhAB( SYNchronous COMmunicationFirst american geostationary program. Satellites built by Hughes Aircraft<AB' *O External resourcesX1BC' bhttp://sulu.lerc.nasa.gov/dglover/syncom.html1BIC1 ICCw6CCA Rl~sHsHsHProgram: SyncomSyncom 1Syncom 2Syncom 31ICC1U CG,G=C.D# 4Syncom's specificationsVCDA#R*0&Prime contractorN .DDA#R0PlatformXD*EA#R.0 Mass in orbit40 kgL DvEA#R0LengthK *EEA#R0WidthL vE FA#R0HeightXEeFA#R.0 StabilizationSpin?N FFA#R0DC powerUeFGA#R(0$Design lifetime$F,G" 1G]G1U ]GJ3JC ,GG# @Syncom's transmission payloadX]GGA#R.0(Main transponders2YGQHA#R00,Backup transpondersN GHA#R0Power2 Wa QHIA#R@0Bandwidth300 phone circuitsN HNIA#R0CoverageN IIA#R0EIRP maxs1NIJB#Tb0Frequenciesupload: 7.4 GHzdownload: 1.8 GHz$I3J" 9JlJ1 ^ lJJOSyncom 1E3JJ5 :"g€" Syncom 11 lJJ'  Generalg JIKG#^@") Designation00553 / 63004A\JKA#R6Launch date14 Feb 1963t'IKLM#jN"N ,㹌לCountry of originUnited Statesg KLG#^@"H̀MissionTelecommunicationsYLLA#R0,Geostationary orbitr%LKMM#jJ" &p㉂Launch vehicleThor Delta #16_LMA#R<Launch siteCape Canaveral&KMM# 5MN'  End of life_MdNA#R<"Out of service14 Feb 1963q0NNA#R`CauseLost on the way to geostationary orbit&dNN# 8N3O' "(Technical dataZ*NO0 0T/_#SpecificationsTransmission payload93OO1gɂ OMSyncom 2EO5 :"g€"OO Syncom 21 OH'  Generalg G#^@") Designation00634 / 63031A\H A#R6Launch date26 Jul 1963t'M#jN"N ,㹌לCountry of originUnited Statesg G#^@"H̀MissionTelecommunicationsBiA#R,Geostationary orbit35797/35785 km, 33 inclined, above Brazilr%ۂM#jJ" &p㉂Launch vehicleThor Delta #20_i:A#R<Launch siteCape Canaveralۂ % UOn 31 Oct 1963 the president of the radiocommunications conference in Geneva, Mr Gunnar Pedersen, inaugurated a telephone link to UN's center in New York by Syncom 2.5:>'  End of lifeW A#R,"Out of serviceyes&># 8' "(Technical dataZ*M0 0T/_#SpecificationsTransmission payload91'^ ˅Syncom 3EM˅5 :"g€" Syncom 31 '  Generalg ˅cG#^@") Designation00858 / 64047A\A#R6Launch date19 Aug 1964t'c3M#jN"N ,㹌לCountry of originUnited Stateso"M#jD"H̀‰MissionTelecommunicationsY3A#R0,Geostationary orbitr%mM#jJ" &p㉂Launch vehicleThor Delta #25_̈A#R<Launch siteCape Canaveralm}% First geostationary satellite. Used to broadcast Tokyo's Olympic Games to the US in October 1964 and then for military links to Vietnam.5̈'  End of lifeW} A#R,"Out of serviceyes&/# 8 g' "(Technical dataZ*/0 0T/_#SpecificationsTransmission payload6g19W] -,Taiyo6 -, (" Taiyo~R, (  Means "sun", also called SRATS (Solar Radiation And Thermospheric Structure)1 -܋'  Generalg CG#^@") Designation07671 / 75014A\܋A#R6Launch date24 Feb 1975lC M#j>"N ,bCountry of originJapan6S#vl"H̀(?vjMissionScientific: ionosphere and Sun study_ A#R<"Perigee/Apogee250/2800 kmTGA#R&Inclination33SA#R$Period116 miniGM#j8" & Launch vehicleMu 3CZ]A#R2Launch siteKagoshimaYA#R0"Mass at launch86 kg&]܏# 5'  ܏End of lifeV܏sA#R*Decay29 Jun 1980&# <s' *O External resourcesW0,' `http://www.isas.ac.jp/info/sat/taiyo-e3.html@l1 l?Program: TanseiL,5 :0וGƀ" Program: Tanseibl?% Means "blue light necklace"Japanese program aimed at testing launchers and various technology1p1 pA?H `oCoCoCoCProgram: TanseiTansei 1Tansei 2Tansei 3Tansei 49p21  2wRTansei 1Ew5 :"וGƀ" Tansei 1<2# 2Also called Tansei MRT1 w'  Generalg KG#^@") Designation04952 / 71011A\A#R6Launch date16 Feb 1971lKM#j>"N ,bCountry of originJapan_rG#^0"H̀Missiontechnology_A#R<"Perigee/Apogee986/1106 kmVr'A#R*Inclination29.7U|A#R(Period106.1 mini'M#j8" & Launch vehicleMu 4SZ|?A#R2Launch siteKagoshimaYA#R0"Mass at launch63 kg&?# <' *O External resourcesX1R' bhttp://www.isas.ac.jp/info/sat/tansei-e3.html91- "Tansei 2ER5 :"וGƀ" Tansei 21 '  Generalg hG#^@") Designation07122 / 74008A\A#R6Launch date16 Feb 1974lh0M#j>"N ,bCountry of originJapan_G#^0"H̀Missiontechnology_0A#R<"Perigee/Apogee284/3231 kmVDA#R*Inclination31.2UA#R(Period121.7 miniDM#j8" & Launch vehicleMu 3CZ\A#R2Launch siteKagoshimaYA#R0"Mass at launch56 kg&\# 5'  End of lifeVfA#R*Decay22 Jan 1983&# <f' *O External resourcesZ3"' fhttp://www.isas.ac.jp/info/sat/tanseiII-e3.html9[1 [OTansei 3E"5 :"וGƀ" Tansei 31 ['  Generalg 8G#^@") Designation09841 / 77012A\A#R6Launch date19 Feb 1977l8 M#j>"N ,bCountry of originJapan "_kG#^0"H̀Missiontechnology_ A#R<"Perigee/Apogee796/3804 kmVk A#R*Inclination65.8UuA#R(Period134.1 mini M#j8" & Launch vehicleMu 3HZu8A#R2Launch siteKagoshimaZA#R2"Mass at launch134 kg&8# <' *O External resources[4O' hhttp://www.isas.ac.jp/info/sat/tanseiIII-e3.html91-  Tansei 4EO5 :"וGƀ" Tansei 41 '  Generalg eG#^@") Designation11706 / 80015A\A#R6Launch date17 Feb 1980le-M#j>"N ,bCountry of originJapan_G#^0"H̀Missiontechnology^-A#R:"Perigee/Apogee517/608 kmV@A#R*Inclination38.7TA#R&Period95.9 minj@M#j:" & Launch vehicleMu 3S1ZXA#R2Launch siteKagoshimaZA#R2"Mass at launch185 kg&X# 5 '  End of lifeVcA#R*Decay12 May 1983& # <c' *O External resourcesZ3 ' fhttp://www.isas.ac.jp/info/sat/tanseiIV-e3.html6U 1]< U +TD 1A6  , (" TD 1A3U #  Thor Delta 1A1 '  Generalg V G#^@") Designation05879 / 72014A\ A#R6Launch date12 Mar 1972m V  M#j@"N ,4"Country of originEuropeu( M#jP"H̀_BMissionScientific: UV astronomy^ A#R:"Perigee/Apogee523/550 kmV H A#R*Inclination97.6T A#R&Period95.4 minr%H  M#jJ" &p㉂Launch vehicleThor Delta #88[ i A#R4Launch siteVandenbergZ A#R2"Mass at launch472 kg&i # 5 '  End of lifeU sA#R(Decay9 Jan 1980&# <s' *O External resourcesV/+' ^http://www.esoc.esa.de/external/mso/td.html= h1 hb@Program: TDFI+5 :*,d%" Program: TDFwhb@. , OTldiffusion De FranceFrenchb@+ direct TV program operated by TDF. Was designed to promote the D2MAC TV standard.1@1 @@\"b@@: DDSw~Ww~WProgram: TDFTDF 1TDF 21@ A1U AEE:@ZA# .TDF's specificationsp/ AAA#R^&Prime contractorEurosatellite/AerospatialeZZA$BA#R2PlatformSpacebus 300[ABA#R4"Mass at launch2100 kgZ$BBA#R2 Mass in orbit1300 kg>BXCA#R|Payload mass206 kg: transponders: 114 kg, antennas: 92 kga BCA#R@Dimension2.4 x 1.65 x 6.4 m\XCDA#R6Solar array19.3 m spanYCnDA#R0 Stabilization3 axis?DDB#T~DC powerBOL: 4500 WEOL: equinox: 3642 W, solstice: 3311 WYnDHEA#R0 Payload power2455 W\DEA#R6$Design lifetime7 years$HEE" 1EE1U E;I_I3E,F#  TDF's Ku-bandXEFA#R."(Main transponders5Z,FFA#R2",Backup transponders1PF.GA#R"Power230 WUFGA#R("Bandwidth27 MHz=.GHG#^z"0XnCoverage and EIRP max1 beam centered on France: 63 dBWVG]HA#R*"PolarizationRHCP=HHB#Tz"FrequenciesUplink: 17.3-17.7 GHzDonwlink: 11.7-12.1 GHz_]H;IA#R<"$Video excursion13.5 MHz/v$H_I" 1;II1y IIH_II6 <&,d%"QTDF's EIRP6IJ1m JPJNTDF 1B IPJ5 :,d%" TDF 11 JJ'  Generalg PJJG#^@") Designation19621 / 88098A\JDKA#R6Launch date28 Oct 1988m JKM#j@"N ,㱭+Country of originFrancefDKLM#j2"H̀‰MissionDirect TV_KvLA#R<,Geostationary orbit18.9Wn!LLM#jB" & D+Launch vehicleAriane V26&vL M# 5L?M'  End of lifed# MMA#RF"Out of servicemid October 1996m,?MNA#RXCausedeorbited after stability problems&M6N# 8NnN' "(Technical dataP6NN2 4 a$IRSpecificationsKu-bandTransponder 1 was destroyed by a propellant leak.6nN&O1ނ &OhOTDF 2B NhO5 :,d%" TDF 21 &OO'  Generalg hO G#^@") Designation20705 / 90063AO N\OhA#R6Launch date24 Jul 1990m ՀM#j@"N ,㱭+Country of originFrancefh;M#j2"H̀‰MissionDirect TVb!ՀA#RB,Geostationary orbitsee belown!; M#jB" &8D+Launch vehicleAriane V37&1# : k- */ۀ Location1m#:   " BeginEndPosition%kj#J$8:L: 24 Jul 1990Jul 199718.9W j#:Oct 199729E (tests)xj# ?36E K+ $;RH(In August 1997 the bird joined the Eutelsat fleet. Apparently the satellite was sold. TDF 2 is expected to remain in service at least until early 1999.8' "(Technical datal4K8 @hXn a$IREIRP coverage (dBW)SpecificationsKu-band> -1e<Ղ -wProgram: TDRSJw5 :,FG" Program: TDRSE-5 8! T@^gur7Tracking and Data Relay SatelliteAmerican telecommunication program operated by NASA. Some TDRS satallites have got a so called commercial payload, operated by Columbia Communications (C-band). Provides communications, tracking, telemetry, data acquisition and command services essential to Shuttle and low-Earth orbital spacecraft missions. The TDRS system can provide communications services to orbital spacecraft over 85 percent of each orbit for most satellites, and continuous service for some orbital positions. CwW |K\plUcU~wUdPUN}PUue*The TDRS system was initiated following studies in the early 1970s which showed that a system of telecommunications satellites, operated from a single ground station, could meet the needs of NASA's mission better and more cost-effectively than the then existing network of tracking and communications ground stations located around the world.In addition to the Shuttle, TDRS customers include GRO, UARS, HST, ERBS, EUVE, Topex Poseidon, XTE and other military missions. ;_ wŘbUɉZvSɉɉvMU݌RFuture clients include: ISS, TRMM, Landsat 7, EOSRetired missions: Landsat 4, Landsat 5, SMM, COBE, SMETDRS control center is in White Sands, New Mexico.Commercial telecommunication services (C-band) are available via Columbia through 31 Dec 2001 (option to extend TDRS 5 & 6 through 2003)<Ռ' *O External resources= H3http://www.tdrss.comhttp://www530.gsfc.nasa.gov/tdrss/http://www530.gsfc.nasa.gov/TUBE/http://www.fas.org/spp/military/program/com/tdrss.htm1Ռ܍1 ܍gd @ĘOMOMOMOMOMOMOMOMProgram: TDRSTDRS 1TDRS 2TDRS 3TDRS 4TDRS 5TDRS 6TDRS 7TDRS 8-10 (or H-J)1܍؎1 ؎QB# >TDRS 1 to 7's specificationsc"؎}A#RD0&Prime contractorContel & NASAj) A#RR0PlatformTRW Space and Communications} c"}oA#RD0"Mass at launchapprox. 2200 kgZ A#R20 Mass in orbit2120 kg^o'A#R:0DimensionHexagonal shapeYA#R00 Stabilization3 axisf$'B#TH0DC powerBOL: 2000 WEOL: 1700 W]CA#R80$Design lifetime10 years & GEach satellite has 5 antenna systems: 2 for single access, multiple access, STGL and S-band omni for satellite control.For SA service, each TDRS has two dual-feed S-band, Ku-band parabolic antennas. These antennas are free to be positioned in two axes, directing the radio beam to orbiting user spacecraft below. These antennas are used primarily to relay communications to and from user spacecraft. The high data rate provided by these antennas is available to users on a time-shared basis. Each antenna is capable of supporting two-user spacecraft services simultaneously -one at S-band and one at Ku-band- provided both users are within the beam width of the antenna.E CQ% AThe MA antenna array, consisting of 30 elements, is hard-mounted on the spacecraft body on the surface of the antenna module facing the Earth.Another antenna, a 2-meter parabolic reflector, provides the prime link for relaying transmissions to and from the ground terminal at Ku-band.1 1W T+Q) "VȠ$To view this page you need to register&# 1-1U -3`#  TDRS's S-bandZ-A#R20(Main transponders2+8\`A#R60,Backup transponders2+4NB#T0Power(2+2) transponders of 26 W (TWTA)(8+4) transponders of 3.5 W (SSPA)OA#R0BandwidthN CA#R0CoverageN A#R0EIRP maxRCA#R"0Polarization$" 181 83k#  TDRS's C-bandY8A#R00(Main transponders12YkA#R00,Backup transpondersWtA#R,0Power5.5 W (TWTA)UA#R(0Bandwidth36 MHzYt"A#R00CoveragehemisphericTvA#R&0EIRP max34 dBWV"A#R*0G/T max-2.7 dB/KXv$A#R.0PolarizationlinearEB#T0FrequenciesUplink: 5.925-6.425 GHz VDownlink: 3.700-4.200 GHz HA$$ :Nominal SFD: -86.4 dBW/m11U $4Q# "TDRS's Ku-bandZA#R20(Main transponders4+2\QA#R60,Backup transponders2+2NB#T0Power(4+2) transponders of 25 W (TWTA)(2+2) transponders of 1.5 W (TWTA)[ A#R40Bandwidth50 & 225 MHz N ZA#R0CoverageT A#R&0EIRP max50 dBWRZA#R"0Polarization$$" 7[11  [ TDRS 1C$5 :FG" TDRS 11 ['  Generalg 6G#^@") Designation13969 / 83026B[A#R4Launch date4 Apr 1983t'6M#jN"N ,㹌לCountry of originUnited Stateso"tM#jD"H̀‰MissionTelecommunicationsb!A#RB,Geostationary orbitsee belowjt@M#j:" &㪜Launch vehicleSTS 06qB/ ,OMIts propulsion device (IUS) didn't work. The satellite reached the geostationary orbit by himself, using much of his propellant.Still partially operational, it is though to provide communication services with the South Pole. On 3 Feb 1997 a failure occured on 1 of the gyros. The traffic was taken over be TDRS 6: @- */ۀ Locationum#:p   " BeginEndPositionj#2p"&(L: 4 Apr 1983GTOuzj#0p"$17 Oct 198341W{j#"p198979W'zj#Np,.Feb 1995May 199585E, inclined, j#Xp46Jul 1995mid-Dec 1995139W, inclinedM j#p $&mid-Jun 199649W, inclined (to support ELVs over the South Atlantic)& # 8 1 ' "(Technical datam/ > L^ۀtataS^dSpecificationsS-bandC-bandKu-band71 1O3  6TDRS 2C  5 :FG" TDRS 21 I '  General\ A#R6Launch date28 Jan 1986t'I  M#jN"N ,㹌לCountry of originUnited Stateso" M#jD"H̀‰MissionTelecommunications\ A#R6,Geostationary orbitn/aj N M#j:" &zLaunch vehicleSTS 33& t # 5N '  End of life_t A#R<"Out of service28 Jan 1986c" kA#RDCauseExploded with Challenger&# 8k' "(Technical datam/6> L^ۀtataS^dSpecificationsS-bandC-bandKu-band7m1 muETDRS 3C65 :FG" TDRS 31 m'  Generalg T@G#^@T@6") Designation19548 / 88091B\@A#R6Launch date29 Sep 1988t'T@$AM#jN"N ,㹌לCountry of originUnited Stateso"@AM#jD"H̀‰MissionTelecommunications\$AAA#R6 Geostationarysee belowkAZBM#j<" &DLaunch vehicleSTS 26RCAB$ >Still partially operational: ZBB- */ۀ LocationBaCm#:p   " BeginEndPosition$BCj#Hp$8:L: 29 Sep 1988Apr 1995171WEaCDv#p(p~wJun 199585E, inclined: supports GRO and tested with HST&CD# 8DE' "(Technical datam/DuE> L^ۀtataS^dSpecificationsS-bandC-bandKu-band7EE1 EEJTDRS 4CuEE5 :FG" TDRS 41 E F'  Generalg EFG#^@") Designation19883 / 89021B\ FFA#R6Launch date13 Mar 1989t'FWGM#jN"N ,㹌לCountry of originUnited Stateso"FGM#jD"H̀‰MissionTelecommunicationso(WG5HG#^P"/ۀ0Geostationary orbit41W, inclinedjGHM#j:" &ULaunch vehicleSTS 295HI1 0݌RĉC-band marketed by CCC. On 15 May 1998 the C-band should not be used anymore to avoid interferences with Intelsat 806. In exchange Intelsat will use Intelsat 515 (to be renamed Columbia 515) at 37.5W.8HI' "(Technical dataIJK d? ۉtataS^dEIRP coverage in C-bandSpecificationsS-bandC-bandKu-bandKu-band downlink:13.750-15.115GHz. Beacon: 2.211GHzWent inclined on 15 Oct 19961IJ1 JFKRJFK6 <:OM"RTDRS 4's C-band EIRP7J}K1 }KKtOTDRS 5CFKK5 :FG" TDRS 51 }KK'  Generalg KXLG#^@") Designation21639 / 91054B[KLA#R4Launch date2 Aug 1991t'XL'MM#jN"N ,㹌לCountry of originUnited Stateso"LMM#jD"H̀‰MissionTelecommunicationsf'MMG#^>"/ۀ0Geostationary orbit174WjMfNM#j:" &㥛Launch vehicleSTS 43FMN* $8݌RC-band marketed by CCC8fNN' "(Technical dataJNtOF \ۉtataS^dEIRP coverage in C-bandSpecificationsS-bandC-bandKu-band1NO1 O RtO 6 <:OM"STDRS 5's C-band EIRPO tO7OC1g! CTDRS 6C 5 :FG" TDRS 68C# *Also called TDRS F1 '  Generalg VG#^@") Designation22314 / 93003B\A#R6Launch date13 Jan 1993t'V&M#jN"N ,㹌לCountry of originUnited Stateso"M#jD"H̀‰MissionTelecommunicationsb!&A#RB,Geostationary orbitsee belowjaM#j:" &ћLaunch vehicleSTS 54F* $8݌RC-band marketed by CCC: a- */ۀ Locationkm#:   " BeginEndPosition7 j#n$8:L: 13 Jan 1993Jun 199646W, inclined (reserve)kj#. "1 Jul 199647Wk #+ $ur7Columbia Communications Corp. reached an agreement with NASA for commercial operations (C-band telecommunications) on this satellite. The satellite will be marketed as COLUMBIA/TDRSS AOR-II and will join two other NASA Tracking and Data Relay Satellite System (TDRSS) satellites currently being operated by Columbia under and exclusive agreement with NASA. 8[' "(Technical dataJ#F \HY-ۉtataS^dEIRP coverage in C-bandSpecificationsS-bandC-bandKu-band1[1" nRn6 <:OM"TTDRS 6's C-band EIRP71/# yTDRS 7Cn5 :FG" TDRS 78 # *Also called TDRS G1 Q'  Generalg G#^@") Designation23613 / 95035Ah'Q A#RNLaunch date13 Jul 1995 at 19:55 UTt'M#jN"N ,㹌לCountry of originUnited Stateso" M#jD"H̀‰MissionTelecommunicationsb!eA#RB,Geostationary orbitsee belowp#ՋM#jF" &-Launch vehicleSTS 70 + IUS&e# : Ջ5- */ۀ Locationm#:   " BeginEndPosition.5Wj#\$8:L: 13 Jul 1995May 1996150W (testing)ߍj#<Jun 1996171W (spare)W& oThe IUS consists of two Solid Rocket Motors (SRM's) which inject the TDRS/IUS into geostationary orbit. The IUS SRM 1 first place the TDRS/IUS into a transfer orbit with an apogee near geosynchronous altitude (burn at 20:55 UT). At the first apogee the IUS SRM 2 fired to place the TDRS/IUS in geostationary orbit (14 Jul at 02:30 UT). The TDRS/IUS was then maneuvered to the appropriate orientation and TDRS 7 separated from the IUS.8ߍ ' "(Technical data nm/y> L^ۀtataS^dSpecificationsS-bandC-bandKu-band7 1[g$ %TDRS 8Ky5 :.FG" TDRS 8, 9 & 10mCh* "Or TDRS H, I, JThose 3 satellites will be built by Hughes and made from a modified HS-601 platform. First launch planned in July 1999 NASA required to be reimbursed for failures!TDRS 8: 147W, TDRS 9: 172EThose satellites will have S-, Ku- and Ka-band capacity with potential data rates up to 650Mb/s. No C-band.<' *O External resourcesR+h' Vhttp://www.omitron.com/tube/tdrshij.htm8.' "(OTechnical data%* "Telemetry: 2211.5 MHz (0.5, 1 or 4 kbps)Telemetry: 2206.5 MHz (0.5, 1 or 4 kbps)Telemetry: 13731 MHzTelemetry: not yet knownCommand: 2035.96 or 2031.81 MHz (2 kbps)Command: 14786 MHz (+ 15150 MHz)1.V1W% VT+%) "VȠ$To view this page you need to register&V# 81 a& @Teamsat8 @, (" Teamsat1 q'  GeneralY@G#^$") DesignationQqA#R Launch datem M#j@"N ,4"Country of originEuropeUG#^"H̀MissionW4A#R,"Perigee/ApogeeGTOQA#R InclinationL 4A#RPeriodf7G#^>" &Launch vehicleAriane 502QA#R Launch site^:7$ tWill contain 5 experiments provided by ESTEC students.8' "(OTechnical data8V' " SpecificationsVA#R*&Prime contractorN VA#RPlatformTNA#R&"Mass at launchSA#R$ Mass in orbitONA#RDimensionQAA#R Solar arraySA#R$ StabilizationN AA#RDC powerv5XA#Rj$Design lifetime1 week, duration of the batteries? L>W>WRRIt will carry a video camera to record and transmit the separation of the cap, the Speltra structure, and of the other Ariane payloads. Once in GTO the satellite might deploy a sub-satellite named Yes (160 kg) attached by a 30 km long tether. Such experiment was tested with TTS 1 & TTS 2, Seds 1 & Seds 2. This experiment is subject to controversy regarding space debris.1XJ1W' JT+) "VȠ$To view this page you need to register&J# : 1 Ղ( @ Techsat 1B@2 4""  Techsat 1:z# .Also called Gurwin 11 @'  General\zA#R6Launch date28 Mar 1995m M#j@"N ,ΝECountry of originIsraelo"M#jD"H̀㓉MissionTelecommunicationsl[M#j>" &aKLaunch vehicleStart #2&# 5['  End of lifecG#^8 CauseLauncher failureVoA#R*Decay28 Mar 1995_:% uThe 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. <o ' *O External resourcesZ3d' fhttp://www.technion.ac.il/pub/projects/techsat/8 ' "(OTechnical data8d' " SpecificationsEZA#R&Prime contractorTechnion-Israel Institute of Technology in HaifaN A#RPlatformYZA#R0"Mass at launch50 kgSTA#R$ Mass in orbitRA#R"Length0.45 mPTA#RWidth0.5 mQGA#R Height0.5 mSA#R$ StabilizationN GA#RDC powerU=A#R($Design lifetime&c# 9=' $ Frequency chart9c6 a#r $ J 145 MHz uplink1269 MHz uplink435 MHz downlinko R#t:(145.8501269.700435.225o6  R#t:(145.8901269.800435.325h | R#t,(145.9101269.900h R#t,(145.9301269.950$|  " : B 1Ya€) B BTechsat 2B 2 4""  Techsat 21 B '  GeneralY  G#^$") DesignationY g A#R0Launch datemid 1997m  M#j@"N ,ΝECountry of originIsraelo"g C M#jD"H̀㓉MissionTelecommunicationsi M#j8" &'CMLaunch vehicleZenityC K& launch cost: $400,000 The cost of the satellite is estimated at $8 millionit carries several scientific experiments< ' *O External resourcesZ3K' fhttp://www.technion.ac.il/pub/projects/techsat/8' "(OTechnical data8Q' " Specificationsz9A#Rr&Prime contractorTechnion University in Haifa, IsraelN Q%@A#R%@ PlatformY~@A#R0"Mass at launch50 kgS%@@A#R$ Mass in orbit^~@/AA#R:Dimension48 x 48 x 48 cmQ@AA#R Solar arrayS/AAA#R$ StabilizationN A!BA#RDC power\A}BA#R6$Design lifetime3 years&!BB# 1}BB1W* B(CNCT+B(C) "VȠ$To view this page you need to register&BNC# 7(CC1 + CCOTELE X7 NCC, (" TELE X1 CC'  Generalg CTDG#^@") Designation19919 / 89027A[CDA#R4Launch date2 Apr 1989m TDEM#j@"N ,ˆtCountry of originSwedenfDEP#p,(Q^gOperatorNSABfEEM#j2"H̀‰MissionDirect TVf%ENFA#RJ,Geostationary orbit5E, inclinedn!EFM#jB" &;D+Launch vehicleAriane V30&NFF# 5FG'  End of life_FvGA#R<"Out of service16 Jan 1998TGGA#R&Causedeorbited&vGG# 8G(H' "(Technical dataAGiH) "0m EIRP coverage (dBW)8(HH' " Specificationsr1iHIA#Rb&Prime contractorEurosatellite & ArospatialeZHmIA#R2PlatformSpacebus 300[IIA#R4"Mass at launch2089 kgXmI JA#R.Payload mass170 kga IJA#R@Dimension2.4 x 1.65 x 2.4 mZ JJA#R2Solar array19 m spanYJ4KA#R0 Stabilization3 axisYJKA#R0DC powerBOL: 3200 WY4KKA#R0 Payload power2000 W\KBLA#R6$Design lifetime7 years&KhL# 1 BLL'  Ku-bandXhLLA#R.(Main transponders4ZLKMA#R2,Backup transponders2WLMA#R,Power230 W (TWTA)LKM0NB#TBandwidth(2+1) transponders of 27 MHz(2+1) transponders of 40 & 86 MHzv/MNG#^^0m Coverage and EIRP maxScandinavia: 61 dBWV0NNA#R*PolarizationLHCP>N|OB#T|FrequenciesUplink: 17.7-18.1 GHzDownlink: 12.1-12.65 GHz$NO" 1|OO1|, O(KO(6 <,y"O(OUTELE X's EIRPAOi1(€`- iProgram: TelecomM(5 :2J{p" Program: Telecomi, &.3sFrench program decided on 20 Feb 1979 operated by France Telecom but designed by the CNES. Mission: telecommunication to over-sea territories, military communications and TV and data transmission.1ށ1. ށq] k eee8e9e:e;eProgram: TelecomTelecom 1ATelecom 1BTelecom 1CTelecom 2ATelecom 2BTelecom 2CTelecom 2D1ށ݂1/ ݂ć@# :Telecom 1's specificationsj)݂A#RR&Prime contractorMatra Marconi EspaceQ؃A#R PlatformECS[3A#R4"Mass at launch1210 kgY؃A#R0 Mass in orbit653 kgB3A#RPayload mass134.4 kg: transponders: 107 kg, antennas: 27.4 kga pA#R@Dimension2.06 x 1.9 x 2.2 mZʅA#R2Solar array16 m spanYp#A#R0 Stabilization3 axist3ʅA#RfDC powerEOL: equinox: 1483 W, solstice: 1450 WZ#A#R2 Payload power717.3 W\MA#R6$Design lifetime7 yearswSć$ Telemetry is transmitted in S-band in backup mode and in C-band in normal mode.1M1U0 %I8ć-# *Telecom 1's C-bandXA#R.0(Main transponders4Z-߈A#R20,Backup transponders2W6A#R,0Power8.5 W (TWTA)>߈B#T|0Bandwidth1 transponder of 36 MHz3 transponder of 120 MHzf6^B#T0,Coverage & EIRP maxHemispheric: 29.5 dBWSpot: to West Indies and Guyana (transponder #2): 35 dBWVA#R*0PolarizationLHCPK$^' H Transponder frequency chart (GHz)/c#^  < RHCPUplinkTransponderLHCPDownlinkeR#t&5.945C13.720e[R#t&6.040C23.775eR#t&6.135C33.910e[%R#t&6.360C44.135$I" 1%z11 z H%I# JTelecom 1's X-band (7.3 and 8 GHz)XzA#R.0(Main transponders2VpA#R*0Power20 W (TWTA)UŎA#R(0Bandwidth40 MHzg&p,A#RL0CoverageAtlantic and Indian oceanVŎA#R*0EIRP max31.3 dBWeA, $ Syracuse is the communication system used on the transponders I1=1U2 =&J9 v# ,Telecom 1's Ku-bandX=A#R.0(Main transponders6Zv(A#R20,Backup transponders3V~A#R*0Power20 W (TWTA)U(A#R(0Bandwidth36 MHzT~'A#R&0CoverageEuropeT{A#R&0EIRP max49 dBWZ'A#R20Polarizationlinear VK${ ' H Transponder frequency chart (GHz)9c#r * H HorizontalUplinkTransponderVerticalDownlinkg #R#t*14.022K112.522gR#t*14.064K212.564g#R#t*14.106K312.606gXR#t*14.148K412.648gR#t*14.190K512.690gX&R#t*14.232K612.732$J" 1&{1U3 {#G@J# :Telecom 2's specificationsj){%A#RR&Prime contractorMatra Marconi Espace[A#R4PlatformEurostar 2000[%A#R4"Mass at launch2225 kgZ5A#R2 Mass in orbit1005 kgCA#RPayload mass407.4 kg: transponders: 307.4 kg, antennas: 100 kg\5A#R6Dimension2 x 2.1 x 2 mZoA#R2Solar array22 m spanYA#R0 Stabilization3 axisbomC#VDC powerBOL: 3850 WEOL: equinox: 3397 W, solstice: 3143 W(nickel hydrogen 86 A/H batteries)YA#R0 Payload power2549 W]m#A#R8$Design lifetime10 years$G" 1#x1U4 x8G# *Telecom 2's C-bandYx A#R0(Main transponders10ZcA#R2,Backup transponders4Q A#R Power11.5 W?c5B#T~Bandwidth4 transponders of 90 MHz6 transponders of 50 MHz]A#R8(Coverage (uplink)Globalg5;B#T,Coverage (downlink)Spot: France, St Pierre & Miquelon, West Indies and GuyanaSemi global: Reunionq/B#T^EIRP maxSpot: 39 dBWSemi global: 32.5 dBW^; A#R:Polarizationcircular R/L[eA#R4Uplink5.925-6.425 GHzK$ ' H Transponder frequency chart (GHz)1ePc#b " PG@ LHCPDownlinkTransponderRHCPDownlinkaR#tC1A3.710aPR#tC1B3.738asR#tC2A3.768aR#tC2B3.795`s4R#t3.849C3`R#t3.907C4`4R#t3.965C5`TR#t4.019C6`R#t4.154C7$T" 1 1W5 ]T+]) "VȠ$To view this page you need to register& # 1]1U6  8# *Telecom 2's X-bandZFA#R20(Main transponders4+2\A#R60,Backup transponders2+1MF1B#T0Power(2+1) transponders of 40 W (TWTA)(4+2) transponders of 20 W (TWTA)VC#V0Bandwidth3 transponders of 40 MHz1 transponder of 60 MHz1 transponder of 80 MHzl+16A#RV0Coverageglobal: center Europe & mobileVA#R*0EIRP max31.3 dBWa6:M#j0(  AccessMRF (Multiple Rpartition en Frquence) or MRC (Multiple Rpartition par Code)YA#R00Uplink7.9-8.395 GHz\:A#R60Downlink7.25-7.745 GHz$ " 1D 1U7 D fCC9 } # ,Telecom 2's Ku-bandYD A#R00(Main transponders11Z} 0 A#R20,Backup transponders4V A#R*0Power55 W (TWTA)U0 A#R(0Bandwidth36 MHzs, N G#^X00wۉCoverage and EIRP maxEurope: 52.5 dBW\ A#R60Polarizationlinear H/VZN  A#R20Uplink14.0-14.25 GHzK$ O ' H Transponder frequency chart (GHz)g I # , \ z  Horizontal UplinkHorizontal DownlinkTransponderVertical DownlinkVertical UplinkO t#2.14.022K112.522I ct#2"12.543K714.043 t#2.14.064K212.564c}t#2"12.585K814.085@t#2.14.106K3}@ 12.606}@t#2"12.627K914.127@0At#2.14.148K412.648@At#4 $12.669K1014.1690AKBt#2.14.190K512.690ABt#4 $12.711K1114.211KBfCt#2.14.232K612.732$BC" 1fCC18 CDX"CD6 L^wJbk_bk SpecificationsC-bandX-bandKu-band; MfN1lq; fNNKTelecom 1CG+NN5 :&J{p" Telecom 1C1 fNN'  Generalg NEOG#^@") Designation18952 / 88018B\NOA#R6Launch date11 Mar 1988m EOM#j@"N ,㱭+Country of origiO+NnFranceo"OM#jD"H̀‰MissionTelecommunicationsb!A#RB,Geostationary orbitsee belown!YM#jB" &D+Launch vehicleAriane V21&# : Y- */ۀ LocationCm#:T   " BeginEndPositionǂj#4T$(*L: 11 Mar 19885W7Chj#nT,.Aug 1992Feb 19963E (inclined since fall 1995)&ǂ# 5hÃ'  End of life\A#R6"Out of serviceFeb 1996a ÃA#R@CauseMove to the junk orbit&# 8ބ' "(Technical datam/K> L^wJbk_bk SpecificationsC-bandX-bandKu-band; ބ1 ߃< ͅxTelecom 2AGKͅ5 :&J{p" Telecom 2A1 '  Generalg ͅeG#^@") Designation21813 / 91084A\A#R6Launch date16 Dec 1991m e.M#j@"N ,㱭+Country of originFranceo"M#jD"H̀‰MissionTelecommunicationsb!.A#RB,Geostationary orbitsee belown!mM#jB" &dD+Launch vehicleAriane V48&# : m͈- */ۀ LocationWm#:   " BeginEndPosition*͈j#T$HJL: 16 Dec 1991Apr 1992 (tests)3E~Wij#(Apr 19928Wc% 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 8W8i' "(Technical dataGc"@ P(ikik~ SpecificationsC-bandX-bandKu-bandBeacon: 3.816 GHz RHCP=_' , EIRP coverage (dBW)E"0 0*⅃,pwۉC-bandKu-band1 _Ռ'  Ku-bandU*A#R(iBandwidth32 MHz]ՌA#R8i$Video excursion22 MHz/v[*A#R4i"Mono bandwidth310 KHz[=A#R4i&Mono de-emphasis50 s]A#R8i&Stereo bandwidth130 KHz]=A#R8i*Stereo de-emphasis75 s]TA#R8i&Stereo expansionPanda 1$x" 1T1= V x 6 GTelecom 2BG 5 :&J{p" Telecom 2B1 G'  Generalg &G#^@") Designation21939 / 92021A\A#R6Launch date15 Apr 1992m &M#j@"N ,㱭+Country of originFranceo"^M#jD"H̀‰MissionTelecommunicationsdG#^:"/ۀ0Geostationary orbit5Wn!^0M#jB" &D+Launch vehicleAriane V50I%y$ JEntered in service on 22 Jul 199280' "(Technical dataZyK@ P(ikik~ SpecificationsC-bandX-bandKu-bandBeacon: 3.815 GHz RHCP (or 3737.500 MHz?)=' , EIRP coverage (dBW)EK0 0*(]ӹwۉC-bandKu-band1 '  Ku-bandUSA#R(iBandwidth32 MHz]A#R8i$Video excursion22 MHz/v[S A#R4i"Mono bandwidth180 KHzYdA#R0i&Mono de-emphasisJ17[ A#R4i"Mono expansionAlcatel]dA#R8i&Stereo bandwidth130 KHz[wA#R4i*Stereo de-emphasisJ17]A#R8i&Stereo expansionAlcatel$w" 1)1? )~U~6 <@J{p"XTelecom 2's C-band EIRP; )1u@ Telecom 2CG~5 :&J{p" Telecom 2C1 1'  Generalg G#^@") Designation23730 / 95067A[1A#R4Launch date6 Dec 1995m `M#j@"N ,㱭+Country of originFranceo"M#jD"H̀‰MissionTelecommunicationsd`3G#^:"/ۀ0Geostationary orbit3En!M#jB" & E+Launch vehicleAriane V8153$ "Tested at 1E8' "(Technical datam/{> L^(ikik~ SpecificationsC-bandX-bandKu-band=' , EIRP coverage (dBW){3 4U(]ӹwۉC-bandKu-bandThe spacecraft has an R-4D-12 liquid apogee engine. The mass of Telecom 2C is 1120 kg, with a fuel load of 1163 kg giving a launch mass of 2283 kg.; 1A  Telecom 2DG5 :&J{p" Telecom 2D1 H'  Generalg G#^@") Designation24209 / 96044B[H A#R4Launch date8 Aug 1996m wM#j@"N ,㱭+Country of originFranceo" M#jD"H̀‰MissionTelecommunicationsw dwpG#^:"/ۀ0Geostationary orbit5Wn! M#jB" &=E+Launch vehicleAriane V90_ph+ &3 Had interference problems with the 1 appart Amos 1 satelliteS-band beacon: 2207.130 MHz8' "(Technical data\%h7 >J(ikikSpecificationsC-bandX-band=9' , EIRP coverage (dBW)E~0 0*(]ӹwۉC-bandKu-band1 9'  Ku-bandY~A#R00(Main transponders11ZbA#R20,Backup transponders4VA#R*0Power55 W (TWTA)Ub A#R(0Bandwidth36 MHzs,G#^X00wۉCoverage and EIRP maxEurope: 52.5 dBW\ A#R60Polarizationlinear H/VZ6A#R20Uplink14.0-14.25 GHzK$' H Transponder frequency chart (GHz)c6w# * X v  HorizontalUplinkHorizontalDownlinkTransponderVerticalDownlinkVerticalUplinkt#2"11.472K114.272wt#2.14.293K711.493t#2"11.514K214.314t#2.14.335K811.5358 t#2"11.556K314.356 t#2.14.377K911.5778 R t#2"11.598K414.398 t#4 014.419K1011.619R l t#0"11.640K514440 t#4 014.461K1111.661l t#2"11.682K614.482& # C 1 WB ? GProgram: TeledesicO ? 5 :6 D" Program: Teledesic >A2 2/%1/%1Teledesic is a Delaware corporation owned by McCaw Cellular Communications Inc. and Microsoft Corporation. It was founded in 1990 and the FCC application was made in March 1994.Teledesic proposes to construct, launch, and operate a constellation consisting of 840 satellites in non-geostationary satellite orbits. The constellation is organized into 21 circular orbit planes with each plane containing a minimum of 40 active satellites spaced evenly, and up to four operational spares per orbital plane. Additional spares will be constructed to replace failed satellites so that no orbital plane contains fewer than 40 operational satellites at a? >A ny time. The orbit planes are at a sun-synchronous inclination, 98.2 degrees, which keeps them at a constant angle relative to the sun. These satellites will operate at an altitude between 695 and 700 kilometers (LEO) and will communicate with earth stations operating above a 40 degree elevation angle. ? GC+ $/%1Teledesic was authorized in March 1997 to operate in the United States in the 28.6 - 29.1 GHz (uplink) and 18.8 -19.3 GHz (downlink) band segments for its service links and 27.6-28.4 GHz bands for its "gigalink" gateway terminal uplink and the 17.8-18.6 GHz band for its "gigalink" gateway terminal downlinks. Teledesic will also use inter-satellite links (in the 65-71 GHz band) to interconnect each satellite with eight other satellites in the same and adjacent planes.B>AE% ;In late April 1997 Boeing decided to invest up to $100 million for 10 percent of the current ownership of Teledesic. As the prime contractor, Boeing will lead an international effort to design, build and launch the Teledesic Network. The estimated contract value will be $9 billion. Boeing proposed to reduce the constellation to 288 satellites using new technology. It is foreseen that Sea Launch will be a major space carrier to setup the Teledesic network. In Oct 1997 it is said that the orbit could be changed to circular, 1375 km. pCGCF- (8D9In May 1998 it was announced that Motorola would cancel its Celestri program and take a 26% stake into Teledesic. This has yet to be approved. Motorola would lead the industrial and technological team comprising Boeing, and MMS.Service is targeted to begin in 2003. Launch vehicles should include Deltas and Soyuz.<E5G' *O External resources`FG. ,http://www.teledesic.comhttp://www.fcc.gov/Bureaus/International/Orders/1997/da970527.txt15GG1C GMHY&GMH3 6LN5`1Program: TeledesicTeledesic 1< GH1D HHVTeledesic 1<MHH, ("" Teledesic 1?HI# 8Also called Batsat and T11 H5I'  Generalg IIG#^@") Designation25234 / 98012B\5IIA#R6Launch date26 Feb 1998t'IlJM#jN"N ,㹌לCountry of originUnited Stateso"IJM#jD"H̀㓉MissionTelecommunications^lJ9KA#R:"Perigee/Apogee535/581 kmVJKA#R*Inclination97.7T9KKA#R&Period95.8 minn!KQLM#jB" &GKTLaunch vehiclePegasus XL[KLA#R4Launch siteVandenbergQLM' Batsat was the name used to cover the real purpose of the satellite; it was advertised as a small technology satellite to operate in X- and Ka-band.Is reported not to operate as planned.8LM' "(OTechnical data8MN' " Specificationsf%MiNA#RJ&Prime contractorOrbital & BoeingWNNA#R,PlatformMicrostarYiNOA#R0"Mass at launch70 kgSNlOA#R$ Mass in orbitOOOA#RDimensionQlOA#R SolOMHar arraySOkA#R$ StabilizationN A#RDC powerUkA#R($Design lifetimeH$V$ HCarries a Boeing Ka-band payloadA1`E Program: TelstarMV5 :2p" Program: Telstarڂ, &IAmerican telecommunication program operated by Loral Skynet after being AT&T SkynetSkynet was sold to Loral in 1997 so the operator will become Loral Skynet. The deal was fixed at $478.1 million<' *O External resources~Pڂ. ,http://www.loralskynet.com/http://sulu.lerc.nasa.gov/dglover/telstar.html1Ń1eF Ń4 ЀgVckzzzzƵƵƵ͵͵㑑)zzzzzz zzProgram: TelstarTelstar 1Telstar 2Telstar 301Telstar 302Telstar 303Telstar 401Telstar 402Telstar 402RTelstar 5Telstar 6Telstar 7Telstar 81Ń*1UG *X|D!n# BTelstar 1 & 2's specificationsV*ąA#R*0&Prime contractorN nA#R0PlatformYąkA#R00"Mass at launch80 kgSA#R$0 Mass in orbitSkA#R$0Diameter86 cmL ]A#R0HeightXA#R.0 StabilizationSpin?N ]A#R0DC powerUXA#R(0$Design lifetime$|" 1X1UH 7[<|# 2Telstar 1 & 2's C-bandXAA#R.0(Main transponders1YA#R00,Backup transpondersN AA#R0Power2 Wa IA#R@0Bandwidth600 phone circuitsN A#R0CoverageN IA#R0EIRP maxR7A#R"0Polarization$[" 171UI &@[̋# :Telstar 3's specifications\(A#R60&Prime contractorHughesT̋|A#R&0PlatformHS-376h'(A#RN0"Mass at launch3423 kg (with PAM-D)Y|=A#R00 Mass in orbit625 kgTA#R&0Diameter2.16 mZ=A#R20Height6.8 m deployedb!MA#RB0 StabilizationSpin stabilizedXA#R.0DC powerBOL: 800 W]MA#R80$Design lifetime10 years$&" 1W1UJ W8&# *Telstar 3's C-bandYW A#R00(Main transponders24 &YeA#R00,Backup transpondersW A#R,0Power8.5 W (TWTA)UeA#R(0Bandwidth36 MHzp)G#^R00&ǵCoverage and EIRP maxCONUS: 34 dBW\A#R60Polarizationlinear H/V$" 121K 2@r# :Telstar 4's specificationsd#2A#RF0&Prime contractorGE Astro SpaceUr+A#R(0PlatformGE 7000[A#R40"Mass at launch3331 kgS+A#R$0 Mass in orbitc"<A#RD0Dimension4.08 x 2.22 x 2.54 m\A#R60Solar array24.5 m spanY<A#R00 Stabilization3 axisf$WB#TH0DC powerBOL: 6400 WEOL: 5000 W]A#R80$Design lifetime12 yearsS/W$ ^Cross-strapping possible in both directions181UL 88p# *Telstar 4's C-bandY8A#R00(Main transponders24Zp#A#R20,Backup transponders4[~A#R40Powervariable 11-21 WU#A#R(0Bandwidth36 MHzN ~!A#R0CoverageTuA#R&0EIRP max38 dBW\!A#R60Polarizationlinear H/V$u" 1&1M &9_# ,Telstar 4's Ku-bandj)&A#RR0(Main transponders16 to 24 (variable)[_$A#R40,Backup transponders12l+A#RV0Power60 W standard, up to 120 W (TWTA)^$A#R:0Bandwidth54 MHz & 27 MHzN <A#R0CoverageTA#R&0EIRP max50 dBWR<A#R"0Polarization%  8 transponders can be splited in 16 transponders of 27 MHz. The 120 W transponders are achieved by using the backup transpondersT#1N I} Telstar 4's Ku-band frequency chartj0I: Dbback()"  Telstar 4's Ku-band frequency plan (GHz)&o# #mI#< * X v  ƀȀ HorizontalUplinkHorizontalDownlinkTransponderVerticalDownlinkVerticalUplinkNotesoK# 8.2414.030111.730# 8"2411.743214.043KK# 8.2414.090311.790# 8"2411.803414.103)H# R.2414.150511.850120 W capable)# R"2411.863614.163120 W capable)H# R.2414.210711.910120 W capable)# R"2411.923814.223120 W capable:q# t*:>@14.2719 (A/B)11.971full or A: 120 W capable;I# v,0@B11.98410 (A/B)14.284full or A: 120 W capable;q!# v,<@B14.33311 (A/B)12.033full or A: 120 W capable;I# v,0@B12.04612 (A/B)14.346full or A: 120 W capable;!# v,<@B14.39513 (A/B)12.095full or A: 120 W capable; # v,0@B12.10814 (A/B)14.408full or A: 120 W capable; # v,<@B14.45715 (A/B)12.157full or A: 120 W capable; Y # v,0@B12.17016 (A/B)14.470full or A: 120 W capable$ } " 1Y 1WO  ( T+}  ) "VȠ$To view this page you need to register& ( # 1 Y 1P Y P( 6 <6p"YTelstar 30x's EIRP1Y 1Q / U / 6 <@p"ZTelstar 4's C-band EIRP1 ` 1R ` V / 6 "Perigee/Apogee966/10807 kmVFdGA#R*Inclination42.8UGGA#R(Period225.3 minr%dG+HM#jJ" &p㉂Launch vehicleThor Delta #18_GHA#R<Launch siteCape Canaveral[+HHA#R4"Mass at launch79.5 kg&H I# 5H@I'  End of life\ IIA#R6"Out of serviceMay 1965&@II# 8II' "(Technical dataLIFJ0 08utTdSpecificationsC-band< IJ1v灤U JJ+Telstar 301HFJJ5 :(p" Telstar 3011 JJ'  Generalg JbKG#^@") Designation14234 / 83077A\JKA#R6Launch date28 Jul 1983t'bK2LM#jN"N ,㹌לCountry of originUnited Stateso"KLM#jD"H̀‰MissionTelecommunicationsb!2LMA#RB,Geostationary orbitsee belows&LvMM#jL" &p㉂Launch vehicleThor Delta #171_MMA#R<Launch siteCape Canaveral&vMM# 2 M-N'  LocationMNm#:p   " BeginEndPosition-NtXڀڧ1#ھSpecificationsC-bandTransponder frequency chart< g1V gKTelstar 302H+5 :(p" Telstar 3021 g'  Generalg GG#^@") Designation15237 / 84093D[A#R4Launch date1 Sep 1984t'GM#jN"N ,㹌לCountry of originUnited Stateso"M#jD"H̀‰MissionTelecommunicationsb!A#RB,Geostationary orbitsee belowjQM#j:" &'Launch vehicleSTS 16&w# 2 Q'  Locationw3m#:   " BeginEndPosition"j#D"68L: 1 Sep 1984Jan 199785W'3Pj#N,.Feb 1997Aug 199797W, inclined&v# 5P'  End of life^v A#R:"Out of service5 Sep 1997T]A#R&Causedeorbited& # 8]' "(Technical dataQK? N&ǵXډڧ1#ھEIRP coverage (dBW)SpecificationsC-bandTransponder frequency chart< 1PW ω Telstar 303HKω5 :(p" Telstar 3031 '  Generalg ωgG#^@") Designation15826 / 85048D\ÊA#R6Launch date19 Jun 1985t'g7M#jN"N ,㹌לCountry of originUnited Stateso"ÊM#jD"H̀‰MissionTelecommunicationsb!7A#RB,Geostationary orbitsee belowjrM#j:" &QLaunch vehicleSTS 25&# : rҌ- */ۀ Location\m#:   " BeginEndPositionҌj#8$(*L: 19 Jun 1985125W*\vj#T02< May 1992May 1996123W, inclined j#@Jun 1996120W, inclined&v&# 8^' "(Technical dataQ& ? N&ǵXډڧ1#ھEIRP coverage (dBW)SpecificationsC-bandTransponder frequency chart^ K< ^H1+X H3Telstar 401H 5 :(p" Telstar 4011 H'  Generalg (G#^@") Designation22927 / 93077A\A#R6Launch date16 Dec 1993t'(M#jN"N ,㹌לCountry of originUnited Stateso"gM#jD"H̀‰MissionTelecommunications]A#R8,Geostationary orbit97Wq$g5M#jH" &yjLaunch vehicleAtlas CentaursM& Entered service on 1 Feb 1994The loss is evaluated about $132.5 million55'  End of life_<A#R<"Out of service11 Jan 1997h'A#RNCausedestroyed by a magnetic storm&<# 8' "(Technical datajE Z8ڀ1iXd#ھ@SpecificationsC-bandKu-bandTransponder frequency chartKu-band Transponder frequency chart=' , EIRP coverage (dBW)E30 0*_εr)C-bandKu-band< o1ᄥY oTelstar 402H35 :(p" Telstar 4021 o'  Generalg OG#^@") Designation23249 / 94058A[A#R4Launch date9 Sep 1994t'OM#jN"N ,㹌לCountry of originUnited Stateso"M#jD"H̀‰MissionTelecommunicationsr1A#Rb,Geostationary orbitwas expected in slot 89Wn!mM#jB" &D+Launch vehicleAriane V67:$ ,Cost: $200 million5m'  End of life^:A#R:"Out of service9 Sep 1994q*G#^T CauseExplosion after pressurisation:% The second of two pyrovalve firings to enable its propulsion system set off an explosion and a disastrous leak. A lawsuit by AT&T and a countersuit by Lockheed Martin were settled out of court in 1995 on this subject.8' "(Technical datajE Z8ڀ1iXd#ھ@SpecificationsC-bandKu-bandTransponder frequency chartKu-band Transponder frequency chart= 1+Z Telstar 402RI5 :*p" Telstar 402RJ'd# NWas renamed Telstar 4 on 28 Feb 19971 '  Generalg dG#^@") Designation23670 / 95049A\XA#R6Launch date24 Sep 1995t'M#jN"N ,㹌לCountry of originUnited Stateso"X;M#jD"H̀‰MissionTelecommunications]A#R8,Geostationary orbit89Wn!;M#jB" &D+Launch vehicleAriane V78'95 8zz͵Started serving on 1st December 1995.A Canadian company, Tee-Comm Electronics, created AlphaStar in March 1995 by leasing more than half the 24 Ku-band transponders on Telstar 402R. The new service to 61-cm home antennas, offers 110 television and 20 audio channels. It will be expanded to over 200 channels in 1997 using Telstar 5. Customers in Alaska and Hawaii will also be served via slightly larger (76-cm) antennas.The satellite was renamed Telstar 4 after the loss of Telstar 4018q' "(Technical dataq9'E Z8ڀ1iXd#ھ@SpecificationsC-bandKu-bandC-band Transponder frequency chartKu-band Transponder frequency chart=qd' , EIRP coverage (dBW)E'0 0*_εr)C-bandKu-band: d1_ᄥ[ )6BTelstar 5F)5 :$p" Telstar 51 Z'  Generalg )G#^@") Designation24812 / 97026A\ZA#R6Launch date24 May 1997t'M#jN"N ,㹌לCountry of originUnited Stateso"M#jD"H̀‰MissionTelecommunicationseeG#^<"/ۀ0Geostationary orbit97Wo"M#jD" &㉓gLaunch vehicleProton #247E!e$ BEntered service in early July8Q' "(OTechnical data=' , EIRP coverage (dBW)EQ0 0*9D4uljC-bandKu-band8 ' " Specificationsi(tA#RP&Prime contractorSpace Systems/LoralU A#R(PlatformFS-1300Tt A#R&"Mass at launchSp A#R$ Mass in orbitO A#RDimensionQp  A#R Solar arrayY i A#R0 Stabilization3 axisT A#R&DC power3200 W]i  A#R8$Design lifetime15 years& @ # 0  p '  C-bandY@ A#R0(Main transponders24Yp " A#R0,Backup transpondersO q A#RPower16 WU" A#R(Bandwidth36 MHzh'q . A#RNCoverageUS (50 states) + Caribbean^ D#XEIRP maxCONUS: 37 dBWAlaska: 32 dBWHawaii: 36 dBWPuerto Rico/US Virgin Islands: 33 dBW\. ,A#R6Polarizationlinear H/V& R# 1 ,'  Ku-bandYRA#R0(Main transponders28Y5A#R0,Backup transpondersPA#RPower100 W@5@B#TBandwidth24 transponders of 27 MHz4 transponders of 5@4 MHzC@A#RCoverageUS (50 states) + Caribbean, Mexico and Southern Canada@mAG#\EIRP maxCONUS: 46.5 dBWAlaska: 42 dBWHawaii: 45.5 dBWPuerto Rico/US Virgin Islands: 44.7 dBWMexico: 43.5 dBWSouthern Canada: 44.5 dBW\@AA#R6Polarizationlinear H/VmImA6B$ Ku-band: No variable power nor cross-strapping like on the 40x series1AgB1W\ gBBBT+6BB) "VȠ$To view this page you need to register&gBB# 1BC1] CgCUBgC6 <@zz"\Telstar 5's C-band EIRP1CC1W^ CCDT+gCC) "VȠ$To view this page you need to register&CD# 1CCD1_ CDDV DD6 JA#R$ Mass in orbitOIJA#RDimensionQ>JJA#R Solar arraySJ1KA#R$ StabilizationN JKA#RDC powerU1KKA#R($Design lifetime&KK# 0 K*L'  C-bandYKLA#R0(Main transponders24Y*LLA#R0,Backup transpondersOL+MA#RPower16 WOLzMA#RBandwidthN +MMA#RCoverageJ zMNA#REIRPRMdNA#R"Polarization&NN# 1 dNN'  Ku-bandYNOA#R0(Main transponders28YNmOA#R0,Backup transpondersPOOA#RPower100 Wg%mO0B#TJO0DEBandwidth4 x 54 Mhz 24 x 27 MHzN O~A#RCoverageJ 0ȀA#REIRPR~A#R"PolarizationmIȀ$ Ku-band: No variable power nor cross-strapping like on the 40x series11Wb 2T+ ) "VȠ$To view this page you need to register&2# : l1c laTelstar 7F25 :$p" Telstar 71 l'  GeneralY<G#^$") Designation[A#R4Launch dateearly 1999t'< M#jN"N ,㹌לCountry of originUnited Stateso"zM#jD"H̀‰MissionTelecommunications^ ؄A#R:,Geostationary orbit129WjzBM#j:" &2!Launch vehicleAriane؄a( Designed with 28 100-Watt Ku-band transponders (4 are 54 MHz and 24 are 27 MHz) and 24 16-Watt C-band transponders.Ku-band: No variable power nor cross-strapping like on the 40x seriesCould be cancelled due to FCC refusal for expansion slot1B1Wd T+a) "VȠ$To view this page you need to register& # : F1e FTelstar 8F 5 :$p" Telstar 8pMF# Should be a ground backup for satellites of the 5 to 7 series, same design1-1Wf -T+) "VȠ$To view this page you need to register&-# 8߈1Wg ߈Temisat@2 4"  Temisat@߈_# :Telespazio Micro Satellite1 '  Generalg _G#^@") Designation22783 / 93055BPG#^s kLaunch date31 Aug 1993 at 04:40 UT, released at 15:20 UT from Meteor 2-21lM#j>"N ,xECountry of originItalyXRA#R.OperatorTelespazioo"M#jD"H̀㓉MissionTelecommunications^RA#R:"Perigee/Apogee932/967 kmVuA#R*Inclination82.5SȌA#R$Period104 minr%u:M#jJ" &ቂLaunch vehicleCyclone 3 #106V2Ȍ$ dWill relay environmental data from field sites8:ȍ' "(OTechnical data8' " Specificationsc"ȍcA#RD&Prime contractorKayser-Threde_ŽA#R<"Mass at launch30 or 42 kgc"c%A#RDDimension0.35 x 0.35 x 0.35 mj)ŽA#RR Stabilization3 axis (magnetotorquer)\% A#R6$Design lifetime5 years &2# 1 c'  Payloadg%2B#TJFrequency148-150 MHz137-138 MHzu3c?B#TfUplink10 channels (9 simultaneously)1200 baudDB#TDownlink6 channels (3 simultaneously)2 x 4800 baud + 1200 baud$?" ?(1h (sProgram: TempoKs5 :.v" Program: Tempo[(. *fgDBS satellite program operated by Tempo Satellite Inc, a wholly-owned subsidiary of Tsat. Aimed at direct TV broadcasting to Conus, Alaska, Hawaii and Puerto Rico. 2 satellites planned. Since TCI couldn't get its own GEO slot, one satellite will be located at 119W and the second sold to another DBS-wannabe operator. TCI even tried to operate a DBS service from a Canadian slot, but the FCC refused.In mid-1997 a partership with Primestar was announced that would lead to the transfer of Tempo to Primestar Inc. Primestar would become the holder of the DBS licences. FCC approval still neededL(sH$ PThe 2 satellites costed $487 million<' *O External resources@H' 2http://www.tcinc.com/11i Wb(W: DPpqProgram: TempoTempo 1Tempo 211:j DW) "6Tempo's specificationsi(5A#RP&Prime contractorSpace Systems/LoralUA#R(PlatformFS 1300[5A#R4"Mass at launch3558 kgS8A#R$ Mass in orbitOA#RDimensionZ8A#R2Solar array30 m spanS4A#R$ StabilizationUA#R(DC power10000 W]4A#R8$Design lifetime10 years&  Solar pannels provided by DasaTelemetry and command: 12.201 GHz, 12.202 GHz, 12.203 GHz and 12.204 GHz, with a 450 kHz bandwidth11Wk <T+) "VȠ$To view this page you need to register&<# 1m1l mT=<) "(Tempo's Ku-bandYmA#R0(Main transponders32Y\A#R0,Backup transpondersWA#R,Power107 W (TWTA)U\A#R(Bandwidth24 MHzT\A#R&CoverageCONUS+N A#REIRP maxR\A#R"PolarizationX4T$ hCan be operated as 16 transponders of 214 W each11Wm T+T) "VȠ$To view this page you need to register&# 871vn 7{Tempo 1D{5 : v" Tempo 11 7'  GeneralY{G#^$") Designationd#uA#RFLaunch dateplanned in Jun 1996t'M#jN"N ,㹌לCountry of originUnited Stateso"uXM#jD"H̀‰MissionTelecommunications^A#R:,Geostationary orbit119WjX M#j:" &㉓gLaunch vehicleProton&F# 8 ~' "(Technical dataMF0 0:⬚GO,T(SpecificationsKu-band1~1Wo PvT+P) "VȠ$To view this page you need to register&v# 8P1w;p 8 Tempo 2Dv5 : v" Tempo 21 #'  Generalg G#^@") Designation24748 / 97011A[#A#R4Launch date8 Mar 1997t'YM#jN"N ,㹌לCountry of originUnited Stateso"M#jD"H̀‰MissionTelecommunicationsb!Y*A#RB,Geostationary orbitsee belows&M#jL" &yjLaunch vehicleAtlas 2A (#106)?*' 1The satellite experienced solar flare after launch (11 Apr 1997) and its solar arrays have experienced problems. The satellite is said to suffer from "temporary power fluctuations". It is also claimed that the satellite was not operating normally before the solar flare. Up to 4 transponders might be out of order.TSAT did not accept the satellite (as of Nov 1997) since it is believed that only 85% of the design output power can be achieved. It the satellite is not usable, SS/L has 29 months to provide a replacement satellite.:  - */ۀ Location m#:   " BeginEndPosition% / j#J"68L: 8 Mar 1997Apr 1997109.5W j#4 $&mid-Apr 1997119W8/ ' "(Technical dataM 8 0 0:⬚GO,T(SpecificationsKu-band9 q 12q q GTerriers9 8 , (" Terrierszq G # Tomographic Experiment using Radiative Recombinative Ionospheric EUV and Radio Sources, also called STEDI 2 and UNEX 021 x '  GeneralYG G#^$") DesignationUx & A#R(Launch date1997t' M#jN"N ,㹌לCountry of originUnited States`& G#^2"H̀MissionScientific:i( cA#RP"Perigee/Apogeesunsynchronous (9:00)Q A#R InclinationL cA#RPeriod\\G#^*" &Launch vehicleQA#R Launch site\C' The satellite bus is being built by AeroAsC8 tro while the instrument package is produced by the Center for Space Physics at Boston University and the University of Illinois at Urbana-Champain (UIUC). Cleveland Heights High School is also constructing a small experiment to go on the satellite.Terriers primary goal is to, for the first time, demonstrate meridional 2-D (latitude-altitude)and global 3D imaging of the ionospheric electron density and thermospheric photo-emission profiles using EUV emissions and tomographic techniques. Secondary goals of Terriers focus on the study of several ionospheric and thermospheric phenomena through the use of this novel combination of techniques and observations. As a tertiary goal, Terriers will test the utility of long term solar EUV irradiance measurements using a new technique that we have recently proven on a sounding rocket. GISSMO measures the solar EUV, one of the primary sources for the upper atmosphere.<C' *O External resourcesS,C5D' Xhttp://net.bu.edu/terriers/terriers.html8CmD' "(OTechnical data85DD' " SpecificationsVmDDA#R*&Prime contractorN DIEA#RPlatformZDEA#R2"Mass at launch121 kgSIEEA#R$ Mass in orbitOEEFA#RDimensionQEFA#R Solar arraySEFFA#R$ StabilizationN F7GA#RDC powerUFGA#R($Design lifetime&7GG# 1GG1Wr G7H]HT+G7H) "VȠ$To view this page you need to register&G]H# A7HH1`s HHIProgram: ThaicomQ]HH8 @4," Program: ThaicomxHI) "yɺThai telecommunication program operated by Shinawatra, a national operator which has secured a 30-year concession. 1HI1t IOJFIOJH `v胀FˀGˉHˉIˉProgram: ThaicomThaicom 1Thaicom 2Thaicom 3Thaicom 41IJ1Uu JONsND!OJJ# BThaicom 1 & 2's specifications\J KA#R60&Prime contractorHughesUJuKA#R(0PlatformHS-376L[ KKA#R40"Mass at launch1080 kgYuK)LA#R00 Mass in orbit629 kgTK}LA#R&0Diameter2.16 mZ)LLA#R20Height6.6 m deployedb!}L9MA#RB0 StabilizationSpin stabilizedXLMA#R.0DC powerBOL: 700 W]9MMA#R80$Design lifetime10 yearsa MONA#R@0Apogee motorThiokol Star 30$MsN" 1ONN1Uv N^<sNN# 2Thaicom 1 & 2's C-bandYN9OA#R00(Main transponders10ZNOA#R20,Backup transponders2O9O A#R0Power11 WO sNUOaA#R(0Bandwidth36 MHzQ B#T00Coverage and EIRP maxSouth Eastern Asia: 37 dBWA spot covers central Europej(a^B#TP0Polarization1: V linear2: H linear$" 1^1Uw *N=# 4Thaicom 1 & 2's Ku-bandXHA#R.0(Main transponders2ZA#R20,Backup transponders1VHA#R*0Power47 W (TWTA)UMA#R(0Bandwidth54 MHzs,G#^X00XCCoverage and EIRP maxThailand: 50 dBWj(M*B#TP0Polarization1: H linear2: V linear$N" 1*1x لZ$Nل6 LI u⬇aA>SpecificationsC-bandKu-band=>' , EIRP coverage (dBW)E0 0*o9XCC-bandKu-band1>1z U 6 <@Fˀ"_Thaicom 1's C-band EIRP: C1}K{ CThaicom 2F 5 :$," Thaicom 21 C'  Generalg !G#^@") Designation23314 / 94065B[|A#R4Launch date8 Oct 1994o"!M#jD"N ,)`Country of originThailando"|ZM#jD"H̀‰MissionTelecommunicationsg G#^@"/ۀ0Geostationary orbit78.5En!Z/M#jB" &D+Launch vehicleAriane V68&U# 8/' "(Technical data]&U 7 >LI u⬇aA>SpecificationsC-bandKu-band =I' , EIRP coverage (dBW)E 0 0*ÇXCC-bandKu-band1I1| U6 <@Gˀ"`Thaicom 2's C-band EIRP: N12(uZ} NQIThaicom 3F5 :$," Thaicom 31 N'  Generalg ,G#^@") Designation24768 / 97016A\A#R6Launch date16 Apr 1997o",M#jD"N ,)`Country of originThailando"fM#jD"H̀‰MissionTelecommunications_A#R<,Geostationary orbit78.5En!f3M#jB" &8E+Launch vehicleAriane V95k& Cost: over $200 million (including satellite, launch, ground stations and insurance)test slot: 87.5E83' "(OTechnical data=9' , EIRP coverage (dBW)i27 >d~RvRvSvC-band, quasi globalC-band, zoneKu-band89' " Specificationsb!<A#RB&Prime contractorAerospatiale\A#R6PlatformSpacebus 3000A[<A#R4"Mass at launch2650 kgUHA#R(Dry Mass1179 kgc"A#RDDimension3.25 x 2.26 x 3.48 m]HA#R8Solar array26.27 m spanYaA#R0 Stabilization3-axisYA#R0DC powerBOL: 6400 W]aA#R8$Design lifetime14 years&=# 0 m'  C-bandY=A#R0(Main transponders24YmA#R0,Backup transponders^}B#T8Power6 x 42 W18 x 19 WUA#R(Bandwidth36 MHzs}B#T,Coverage & EIRP maxQuasi global: 37.5 dBW (6 transponders in 3.4 - 3.7 GHz range)Zone (sub continent): 38 dBWXA#R.Polarizationlinear&# R+W' V C-band transponder frequency chart (GHz)D!#܀ . L vx HorizontalDownlinkTransponderVerticalDownlinkBeamW#Ҁ2 "Rv1VE3.425Zone!U#Ҁ2 "Rv2VE3.465Zone!#ҀB "~Rv3.4801HEQuasi globalU#Ҁ2 "Rv3VE3.505Zone!?#ҀB ?"~Rv3.5202HEQuasi global#Ҁ2 "Rv4VE3.545Zone!?{#ҀB "~Rv3.5603HEQuasi global#Ҁ2 "Rv5VE3.585Zone!{#ҀB "~Rv3.6004HEQuasi globalQ#Ҁ2 "Rv6VE3.625Zone!#ҀB "~Rv3.6405HEQuasi global!Q#ҀB "~Rv3.6806HEQuasi global3#؀4 ""Rv1VS3.720Zone#؀4 ""Rv2VS3.760Zone3o#؀4 ""Rv3VS3.800Zone #؀4 ""Rv4VS3.840Zoneo#؀4 ""Rv5VS3.880Zone I#؀4 ""Rv6VS3.920Zone#؀4 ""Rv7VS3.960ZoneI #؀4 ""Rv8VS4.000Zone# #؀4 ""Rv9VS4.040Zone #؀6""$Rv10VS4.080Zone# a #؀6""$Rv11VS4.120Zone #؀6""$Rv12VS4.160Zone&a & # 1 W '  Ku-bandY& A#R0(Main transponders14YW A#R0,Backup transpondersP Y A#RPower100 WU A#R(Bandwidth36 MHzBY 2B#T,Coverage & EIRP maxThailand: 55 dBWIndia (steerable): 50 dBWX A#R.Polarizationlinearb!2A#RBFrequencies12.25 - 12.75 GHzU1A$ bOnly 38 transponders can be on simultaneouslyS,' X Ku-band transponder frequency chart (GHz).AR@#؀\  2 JR@L UplinkTransponderDownlinkBeam0@{#ƀ`0214.01985512.2718Thailand or steerable0R@A{#ƀ`0214.06135612.3133Thailand or steerable0@SB{#ƀ`0214.10245712.3548Thailand or steerable0AB{#ƀ`0214.14435812.3963Thailand or steerable#SBC{#ƀF0214.18585912.4378Thailand#B:D{#ƀF0214.22736012.4793Thailand#CD{#ƀF0214.26886112.5208Thailand#:DvE{#ƀF0214.31036212.5623Thailand#DF{#ƀF0214.35136312.6038Thailand#vEF{#ƀF0214.40556412.6575Thailand#FPG{#ƀF0214.46816512.7201Thailand$FG{#ƀH0214.20666612.4586steerable$PGH{#ƀH0214.24816712.5001steerable$G-I{#ƀH0214.28966812.5416steerable$HQI" 1-II1W~ IIIT+QII) "VȠ$To view this page you need to register&II# 1I-J1 -JJf0IJ6 KT+JK) "VȠ$To view this page you need to register&J>K# 1KoK1 oKK^(>KK6 "Mass at launch2600/2700 kgSA#R$ Mass in orbitL gA#RLengthK QA#RWidthL A#RHeightSQA#R$ StabilizationN >A#RDC powerUA#R($Design lifetimesO>$ The 2 C-band and 3 Ku-band antennas are manufactured by Spar Aerospace Ltd.0 6'  C-bandYA#R0(Main transponders24Y6A#R0,Backup transpondersK 3A#RPowerOA#RBandwidthG3 B#T,Coverage & EIRP maxThailand: ?Vietnam to Western Europe: 34.5 dBWR]A#R"Polarization& # 1 ]'  Ku-bandY A#R0(Main transponders12YfA#R0,Backup transpondersK A#RPowerOfA#RBandwidthN NA#RCoverageN A#REIRP maxRNA#R"Polarization$" 1C1W CT+) "VȠ$To view this page you need to register&C# > 12 EόProgram: ThorJE5 :,⨧G" Program: Thor_ό+ &[sNamed for Norwegian explorer Thor HeyerdahlTelecommunication program operated by Telenor1E1 oo.όoA R\fOgOhOProgram: ThorThor 1Thor 2Thor 371J Thor 1Co5 :⨧G" Thor 11 '  General[uG#^(SOld nameBSB 2[ЎG#^(鉂CountryNorwayfu6M#j2"H̀‰MissionDirect TVfЎG#^>"/ۀ0Geostationary orbit0.8W>6ڏ$ 4Bought for $42 million8' "(ڏoTechnical datal4ڏ8 @h; ٹZfܢaEIRP Coverage (dBW)SpecificationsKu-band11| K6 <,fO"dThor 1's EIRP7=1V =Thor 2C5 :⨧G" Thor 21 ='  Generalg G#^@") Designation24808 / 97025A\tA#R6Launch date20 May 1997m M#j@"N ,鉂Country of originNorwayo"tPM#jD"H̀‰MissionTelecommunicationsdG#^:"/ۀ0Geostationary orbit1Wp#P$M#jF" &p㉂Launch vehicleDelta 2 #243@d$ 8To be delivered in orbit8$' "(Technical dataAd) "0ⰬEIRP Coverage (dBW)8' " Specifications\qA#R6&Prime contractorHughesi(A#RPPlatformHS-376HP (49th to be built)Tq.A#R&"Mass at launchSA#R$ Mass in orbitO.A#RDimensionc"3A#RDSolar array(gallium arsenide)b!A#RB Stabilizationspin stabilizedY3A#R0DC powerEOL: 1400 W]KA#R8$Design lifetime11 years&q# 1 K'  Ku-bandYqA#R0(Main transponders15YTA#R0,Backup transpondersVA#R*Power40 W (TWTA)UTA#R(Bandwidth26 MHzedG#^<ⰬCoverageNorthern EuropeTA#R&EIRP max52 dBW\dA#R6Polarizationlinear H/V% A wiring error in the antenna waveguides at construction time cause the polarization to be reverse. Financial compensation is expected.K$' H Transponder frequency chart (GHz),a#X  > TransponderPolarizationFrequencydR#t$1V11.215625ddR#t$2H11.228625dR#t$3V11.246875dd,R#t$4H11.260750dR#t$5V11.278125d,R#t$6H11.292875dXR#t$7V11.309375dR#t$8H11.325000dX,R#t$,9V11.340625eR#t& 10H11.357125e,R#t& 11V11.371875e[R#t& 12H11.389250eR#t& 13V11.403125e[%R#t& 14H11.421375eR#t& 15V11.434375&%# 11| ,K,6 <,gO"eThor 2's EIRP7c1 J c Thor 3C,5 :⨧G" Thor 31 c'  GeneralY0G#^$") DesignationYA#R0Launch dateAug 1998m 0M#j@"N ,鉂Country of originNorwayo"eM#jD"H̀‰MissionTelecommunications\A#R6,Geostationary orbit1Wke,M#j<" &p㉂Launch vehicleDelta 2YG#^$Launch site],% To be delivered on orbitWith this satellite comes an option for another Hughes satellite8?' "(Technical dataA) "0k؆EIRP Coverage (dBW)8?' " Specifications\A#R6&Prime contractorHughesVjA#R*PlatformHS-376HPTA#R&"Mass at launchSj A#R$ Mass in orbitO` A#RDimensionQ A#R Solar arrayS`  A#R$ StabilizationT X A#R&DC power1400 W_ A#R<$Design lifetime11.5 years&X # 1  '  Ku-bandY g A#R0(Main transponders14Y A#R0,Backup transpondersOg  A#RPower47 WO ^ A#RBandwidtht- G#^Zk؆CoverageScandinavia and central EuropeJ ^  A#REIRPR n A#R"Polarization& # 1n 1W ?T+ ) "VȠ$To view this page you need to register& ?# 1p1| pK?6 <,hO"fThor 3's EIRP1p1W @fT+@) "VȠ$To view this page you need to register&f# A@1`c  @FProgram: ThurayaAf @, (," Program: Thuraya @fB, &cThuraya means "Chandelier", a space constellationProject of Etisalat, the United Arab Emirates (UAE) telecommunications firm (60% government-owned) to launch a one billion dollar satellite system to boost its mobile telephones network. The operator will be Thuraya Satellite Telecommunications Co. Other share holders include Arabsat, Hughes, and the Abu Dhabi Investment Co. Lybia's General Post and Telecommunication has a 5% stake in the project ($25 million)q @D' The satellite system, named Thuraya, will provide services to UAE users of Two-way mobile telephones compatible with the Global System for Mobile communications (GSM). The system will make services available to remote sea and rural areas and will cover most Arab states, parts of the Indian subcontinent and Europe. Two satellites are planned, the first one expected in orbit in mid-2000. Launches via Sea Launch or Ariane or ProtonThe satellite is expected to handle between 1.75 million and 2.4 million subscribers by 2005. A second satellite would add another 40 percent capacity if demand required it (ground spare)BnE' CTotal cost for the project as planned: $1 billion Prime contractor: Hughessingle 12.25 m diameter antenna on board to be built by Astro Aerospace (Canada)<DE' *O External resourcesf8nEF. ,phttp://www.thuraya.com/http://www.etisalat.co.ae/1EAF1W AFFFT+FF) "VȠ$To view this page you need to register&AFF# 6FF1' F'GMTimed6 F'G, (" Timed^;FG# vThermosphere, Ionosphere, Mesosphere Energy and Dynamics1 'GG'  GeneralYGHG#^$") Designationd#GsHA#RFLaunch datePlanned in May 2000t'HHM#jN"N ,㹌לCountry of originUnited StatesZsHAIG#^&OperatorNASAaHIG#^4"H̀MissionScientific: ZAIIA#R2"Perigee/Apogee600 kmVIRJA#R*Inclination74.4L IJA#RPeriodkRJ KM#j<" &p㉂Launch vehicleDelta 2QJZKA#R Launch site= KL' -It will obtain global measurements of geophysical parameters of the lower thermosphere, ionosphere, and mesosphere and will be used to determine the seasonal and annual variations of these regions.Design and development: Johns Hopkins University Applied Physics Laboratory<ZKL' *O External resourcesJ#LM' Fhttp://sd-www.jhuapl.edu/TIMED/1LNM1W NMMMT+MM) "VȠ$To view this page you need to register&NMM# ?MN13 c NRNކProgram: TirosKMRN5 :.u" Program: TirosxENր3 4 :ܗ+Television and Infra Red Observation SatelliteAmerican meteorological programIn 1960, Tiros 1, the first true weather satellite, was launched. With each succeeding generation of satellites, remote sensing instruments became increasingly sophisticated and today's high quality pictures are a far cry from the first tentative trials.TIROS was a simple hatbox-shaped craftRNրM carrying special television cameras that viewed Earth's cloud cover from a 450 mile orbit. The pictures radioed back to Earth provided meteorologists with a new tool - a nephanalysis, or cloud chart.bRN_' By 1965, nine more TIROS satellites were launched. They had progressively longer operational times, carried infrared radiometers to study Earth's heat distribution, and several were placed in polar orbits to increase picture coverage over the first TIROS in its near-equatorial orbit.TIROS 8 had the first Automatic Picture Transmission (APT) equipment that allowed pictures to be sent back right after they were taken instead of having to be stored for later transmission. Eventually, APT pictures could be received on fairly simple ground stations anywhere in the world, even in high school classrooms.ր>9 @MBOUUTɑTIROS 9 and 10 were test satellites of improved configurations for the Tiros Operational Satellite (TOS) system. Operational use started in 1966. In orbit, the TOS satellites were called ESSA. TOS satellites were placed in Sun-synchronous orbits, so they passed over the same position on Earth's surface at exactly the same time each day; this allowed meteorologists to view local cloud changes on a 24-hour basis.Several ITOS (for Improved TOS satellites) have been launched since 1970 and are the workhorses of the meteorologists. In orbit they are called NOAA for the National Oceanographic and Atmospheric Administration which is responsible for their operation.<_z' *O External resourcesd=>ކ' zhttp://thunder.met.fsu.edu/explores/Guide/tirosindex.html1z17 ކz €:ܗ+;ܗ+<ܗ+=ܗ+>ܗ+?ܗ+@ܗ+Aܗ+Bܗ+ڗ+?Program: TirosTiros 01Tiros 02Tiros 03Tiros 04Tiros 05Tiros 06Tiros 07Tiros 08Tiros 09Tiros 10Tiros N9N1N NTiros 01E5 :"u" Tiros 011 NĈ'  Generalg +G#^@") Designation00029 / 60002B[ĈA#R4Launch date1 Apr 1960t'+M#jN"N ,㹌לCountry of originUnited StateshbM#j6"H̀l/MissionMeteorology^A#R:"Perigee/Apogee656/696 kmVbA#R*Inclination48.4TjA#R&Period98.3 minm ׋M#j@" &=v퉂Launch vehicleThor Able_j6A#R<Launch siteCape Canaveral\׋A#R6"Mass at launch119.5 kgW36$ fTransmits the first pictures of the cloud cover9"1W "gTTiros 02Eg5 :"u" Tiros 021 "'  Generalg gG#^@") Designation00063 / 60016A\#R6Launch date23 Nov 1960t'ώM#jN"N ,㹌לCountry of originUnited Statesh#j6"H̀l/MissionMeteorology^ώA#R:"Perigee/Apogee546/610 kmV7 A#R*Inclination48.5 T`A#R&Period96.2 minq$ M#jH" &p㉂Launch vehicleThor Delta #3_`0A#R<Launch siteCape Canaveral$T" 901Nw Tiros 03ET5 :"u" Tiros 031 '  Generalg jG#^@") Designation00162 / 61017A\A#R6Launch date12 Jul 1961t'j:M#jN"N ,㹌לCountry of originUnited StateshM#j6"H̀l/MissionMeteorology^:A#R:"Perigee/Apogee723/790 kmVVA#R*Inclination47.9SA#R$Period100 minq$VM#jH" &p㉂Launch vehicleThor Delta #5_yA#R<Launch siteCape Canaveral$" 9y1W Tiros 04E5 :"u" Tiros 041 L'  Generalg G#^@") Designation00226 / 62002A[LA#R4Launch date8 Feb 1962t'M#jN"N ,㹌לCountry of originUnited StateshM#j6"H̀l/MissionMeteorology^HA#R:"Perigee/Apogee693/811 kmVA#R*Inclination48.3THA#R&Period99.9 minq$cM#jH" &p㉂Launch vehicleThor Delta #7_A#R<Launch siteCape Canaveral$c" 91w d1Tiros 05Ed5 :"u" Tiros 051 '  Generalg dG#^@") Designation00309 / 62025A\XA#R6Launch date19 Jun 1962t'M#jN"N ,㹌לCountry of originUnited StateshX4M#j6"H̀l/MissionMeteorology^A#R:"Perigee/Apogee571/889 kmV4A#R*Inclination58.1T<A#R&Period99.4 minr%M#jJ" &p㉂Launch vehicleThor Delta #10_< A#R<Launch siteCape Canaveral$1" 9 j1 jTiros 06E15 :"u" Tiros 061 j'  Generalg GG#^@") Designation00397 / 62047A\A#R6Launch date18 Sep 1962t'G#M#jN"N ,㹌לCountry of ori#1ginUnited StateshM#j6"H̀l/MissionMeteorology^#A#R:"Perigee/Apogee639/645 kmV?A#R*Inclination58.3TA#R&Period97.6 minr%?M#jJ" &p㉂Launch vehicleThor Delta #12_dA#R<Launch siteCape Canaveral$" 9d1 Tiros 07E5 :"u" Tiros 071 7'  Generalg G#^@") Designation00604 / 63024A\7A#R6Launch date19 Jun 1963t'nM#jN"N ,㹌לCountry of originUnited StateshM#j6"H̀l/MissionMeteorology^n4A#R:"Perigee/Apogee275/281 kmVA#R*Inclination58.2T4A#R&Period90.1 minr%PM#jJ" &p㉂Launch vehicleThor Delta #19_A#R<Launch siteCape Canaveral&P# 5 '  End of lifeU_A#R(Decay3 Jun 1994$ " 9_1  Tiros 08E5 :"u" Tiros 081 2'  Generalg G#^@") Designation00716 / 63054A\2A#R6Launch date21 Dec 1963t'i M#jN"N ,㹌לCountry of originUnited Statesh M#j6"H̀l/MissionMeteorology^i / A#R:"Perigee/Apogee669/703 kmV A#R*Inclination58.5T/ A#R&Period98.5 minr% K M#jJ" &p㉂Launch vehicleThor Delta #22_ A#R<Launch siteCape Canaveral\K  A#R6"Mass at launch102.4 kgw * $ The APT (Automatic Puncture Transmission) camera enabled, for the first time, small antennas to receive pictures.9 1C % =ATiros 09E % 5 :"u" Tiros 091 V '  Generalg % G#^@") Designation00978 / 65004A\V A#R6Launch date22 Jan 1965t' M#jN"N ,㹌לCountry of originUnited StateshM#j6"H̀l/MissionMeteorology_TA#R<"Perigee/Apogee702/2563 kmVA#R*Inclination96.4UT @A#R(Period118.9 min @ r%~@M#jJ" &p㉂Launch vehicleThor Delta #28_ @@A#R<Launch siteCape Canaveral`<~@=A$ xTest satellite for the Tiros Operational Satellite (TOS)9@vA1  vAA=FTiros 10E=AA5 :"u" Tiros 101 vAA'  Generalg ASBG#^@") Designation01430 / 65051A[ABA#R4Launch date2 Jul 1965t'SB"CM#jN"N ,㹌לCountry of originUnited StateshBCM#j6"H̀l/MissionMeteorology^"CCA#R:"Perigee/Apogee721/807 kmVC>DA#R*Inclination98.8UCDA#R(Period100.1 minr%>DEM#jJ" &p㉂Launch vehicleThor Delta #32_DdEA#R<Launch siteCape Canaveral`<EE$ xTest satellite for the Tiros Operational Satellite (TOS)8dEE' "(OTechnical dataAE=F# <Can be heard at 136.235 MHz8EuF1U uFFNTiros ND=FF5 : u" Tiros N1 uFF'  Generalg FQGG#^@") Designation11060 / 78096A\FGA#R6Launch date13 Oct 1978t'QG!HM#jN"N ,㹌לCountry of originUnited StateshGHM#j6"H̀l/MissionMeteorology^!HHA#R:"Perigee/Apogee829/845 kmVH=IA#R*Inclination98.7UHIA#R(Period101.7 mink=IIM#j<" &26Launch vehicleAtlas F[IXJA#R4Launch siteVandenbergkIJ$ Was a research and development spacecraft serving as a protoflight for the operational follow-on series8XJK' "(OTechnical data8JWK' " Specificationsd#KKA#RF&Prime contractorGE Astro SpaceUWKLA#R(PlatformTiros N[KkLA#R4"Mass at launch~720 kgSLLA#R$ Mass in orbitTkLMA#R&Diameter1.88 mRLdMA#R"Heigth3.71 m_MMA#R<Solar array1 single panelSdMNA#R$ StabilizationN MdNA#RDC powerUNNA#R($Design lifetime$dNN" 6NO1  OIOۈTmsat6 NIO, (" Tmsat:OO# .Thai micro satellite1 IOO'  GeneralYOG#^$") DesONignationYOrA#R0Launch dateNov 1997o"M#jD"N ,)`Country of originThailandkrLM#j<"H̀郉MissionRemote sensingTA#R&"Perigee/ApogeeQLA#R InclinationL =A#RPeriodiM#j8" &'CMLaunch vehicleZenitY=A#R0Launch siteTyuratam' Was built by Thai engineers at the University of Surrey in Britain and it will operate in a low-earth orbit to monitor forest fires and water pollution and forecast weather.TMSAT is under funding by The Thai Micro Satellite Company Co.,Ltd.(TMSC), that is a new joint venture between Mahanakorn University of Technology (MUT) and Thai Satellite Telecommunication (TSC) of Bangkok, Thailand. <' *O External resourcesc<R' xhttp://www.ee.surrey.ac.uk/EE/CSER/UOSAT/missions/tmsat/8' "(OTechnical data8R…' " Specificationsb$G#^6&kdgPrime contractorSSTLN …rA#RPlatformZ$̆A#R2"Mass at launch150 kgSrA#R$ Mass in orbitŎnA#RDimensionQA#R Solar arraySnA#R$ StabilizationN `A#RDC powerUA#R($Design lifetime&`ۈ# 1 1W `T+ۈ`) "VȠ$To view this page you need to register& # 5`1 ́ TOMS= 2 4"  TOMSG!?& B Total Ozone Mapping Satellite1 p'  Generalg ?׊G#^@") Designation23940 / 96037A[p2A#R4Launch date2 Jul 1996t'׊M#jN"N ,㹌לCountry of originUnited Statesk2M#j<"H̀郉MissionRemote sensingk*|A#RT"Perigee/Apogee500 km (sunsynchronous)VҌA#R*Inclination97.4T|&A#R&Period96.7 minr%ҌM#jJ" &GKTLaunch vehiclePegasus XL #12&A%  TOMS will focus on tropospheric ozone, to monitor its depletion. It measures total ozone by observing both incoming solar energy and backscattered ultraviolet radiation at six wavelengths. Backscattered radiation is solar radiation that has penetrated the Earth's lower atmosphere and been reflected by air molecules and clouds back through the stratosphere to the satellite sensors. <}' *O External resourcesmA$. ,http://pao.gsfc.nasa.gov/gsfc/service/gallery/fact_sheets/earthsci/toms.htmhttp:/}$/jwocky.gsfc.nasa.gov&}J# 8$' "(OTechnical data8J' " SpecificationsYA#R0&Prime contractorTRWXkA#R.PlatformSTEP/EagleZA#R2"Mass at launch261 kgYkA#R0 Mass in orbit215 kgZxA#R2Dimension2.4 x 3.9 mQA#R Solar arrayYx"A#R0 Stabilization3 axisSuA#R$DC power128 W\"A#R6$Design lifetime2 yearsu: BW;C۫ kisSingle instrument: TOMS which already flew on Nimbus 7 (1978) and Meteor 3-05 (1991). It should also fly on Adeos 1Telemetry: 2273.50 MHz (3 downlink rates: 1.1 kbps, 50 kbps, 200 kbps)Command: 2093.51 MHz?$1 $c@Topex Poseidon?c, ((" Topex PoseidonA$# < ocean TOPography EXperiment1 c'  Generalg <G#^@") Designation22076 / 92052A\A#R6Launch date10 Aug 19924<S#vh"N (,㱭+㹌לCountry of originFrance and United StatesYxA#R0OperatorNASA & CNESkM#j<"H̀郉MissionRemote sensing`xCA#R>"Perigee/Apogee1330/1342 kmTA#R&Inclination66UCA#R(Period112.4 minfRJ#d8"Orbital cycle10 daysn!M#jB" &D+Launch vehicleAriane V52R( AMission: global ocean circulation, ocean currents, tides and surface topographyCost: $480 millionThe inclined orbit samples from 66 North to 66 South latitude: it allows the satellite to observe 90% of the ice-free oceans and all major straits. The orbit is not sun-synchronous and is prograde. The repeat-cycle is about 10 days, ie the satellite passes vertically over the same location in a 1-kilometer bandwidth every 10 days. It has been chosen to optimize the study of the temporal large scale oceanic variability. The distance between successive tracks is on the order of 310 km at the Equator. The local time of successive passes shifts by nearly two hours. <' *O External resourcesC' 8http://osb3.wff.nasa.gov8?' "(OTechnical data8w' " Specifications[?A#R&Prime contractorJet Propulsion Laboratory (+ bus: Fairchild, Poseidon: Alcatel Espace)i(w|A#RPPlatformMultiMission Spacecraft bus[A#R4"Mass at launch2100 kgT|+A#R&DC power1500 WYA#R0 Stabilization3 axis\+A#R6$Design lifetime4 years[m& mTelemetry: 2287.5 MHz (realtime 1/16 kbps)Command: 2106.5 MHz (realtime 1/0.125 kbps)P3 6   ALT (dual frequency radar altimeter) / NRA (NASA Radar Altimeter) (Topex)u3meB#TfFrequencies5.3 GHz (C-band)13.6 GHz (Ku-band)VA#R*Resolution2-3 cme+ $W㖯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.qD- *  SSALT (Single-frequency Solid-state Radar Altimeter) (Poseidon)b!dA#RBFrequency13.65 GHz (Ku-band)VA#R*Resolution2-5 cmV1d% cSSALT (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). R%b- *J  TMR (Topex Microwave Radiometer)`A#R>Frequencies18, 21 & 31 GHzF!b % CTMR (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. P#X - *FO  LRA (Laser Retroflector Array) G $ 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. {NX - *  DORIS (Doppler Orbitography and Radiopositioning Integrated by Satellite)h&G * B#TLFrequencies401.25 MHz2036.25 MHz\ A#R6(Altitude accuracy10 cm* F% 7DORIS (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. j= - *z  GPSDR (Global Positioning System Demonstration Receiver)b!FA#RBFrequencies1227.6/1574.4 MHz@= H'SSSSGPSDR (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. : (A1Ú (AbAFTournesol:@bA, (" Tournesol5(AA# $Also called D2A1 bAA'  Generalg A/BG#^@") Designation05128 / 71030A\ABA#R6Launch date15 Apr 1971m /BBM#j@"N ,㱭+Country of originFrance8BCS#vp"H̀(j_BMissionScientific: Sun study and UV astronomy^BCA#R:"Perigee/Apogee457/696 kmVC7DA#R*Inclination46.3TCDA#R&Period96.2 minn!7DDM#jB" &A͉Launch vehicleDiamant #7YDREA#R0"Mass at launch96 kg&DxE# 5REE'  End of life_xE FA#R<"Out of service22 Jul 1973VEbFA#R*Decay28 Jan 1980$ FF" 6bFF1  FFoKTraac6 FF, (" Traac1 F#G'  Generalg FGG#^@") Designation00205 / 61031B\#GGA#R6Launch date15 Nov 1961t'GZHM#jN"N ,㹌לCountry of originUnited StatesUGHG#^"H̀Mission_ZHIA#R<"Perigee/Apogee955/1108 kmVHdIA#R*Inclination32.4UIIA#R(Period105.8 minq$dI*JM#jH" &Gi4Launch vehicleThor Ablestar_IJA#R<Launch siteCape Canaveral[*JJA#R4"Mass at launch90.4 kgaJoK* $㻶؉One of the 2 first satellites launched with the same vehicle (the other one is Transit 4B).6JK1  KKTrace6 oKK, (" TraceN+K)L# VTransitional Region and Coronal Explorer1 KZL'  Generalg )LLG#^@") Designation25280 / 98020A[ZLMA#R4Launch date2 Apr 1998t'LMM#jN"N ,㹌לCountry of originUnited StatesZMMG#^&OperatorNASAx+MbNM#jV"H̀jMissionScientific: sun observationn-MNA#RZ"Perigee/Apogee602/652 km sun-synchronousVbN&OA#R*Inclination97.8RNxOA#R"Period97 minn!&O M#jB" &GKTLaunch vehiclePegasus XLxO oK[xOgA#R4Launch siteVandenbergZ A#R2"Mass at launch224 kgmFg.' Launch worth $12 millionThe TRACE satellite, designed by an international team of 13 scientists from America, Britain, Sweden and the Netherlands, will explore the connections between fine-scale magnetic fields and the associated plasma structures of the Sun. Will be built at the Lockheed Palo Alto Research Laboratory.<j' *O External resourcesa.. ,http://sunland.gsfc.nasa.gov/smex/trace/http://pore1.space.lockheed.com/TRACE/welcome.html8j1' "(OTechnical data8i' " SpecificationsX1A#R.&Prime contractorLMN iA#RPlatformZiA#R2"Mass at launch213 kgSA#R$ Mass in orbitOi A#RDimensionf%qA#RJSolar array4 panels, total: 2 mY ʅA#R0 Stabilization3-axisSqA#R$DC power220 W[ʅxA#R4$Design lifetime1 year) Telemetry: 2215 MHz (realtime: 23.4375 kpbs, playback: 1.125 or 2.25 Mbps) (5 W transmitter)Command: 2039.65 MHz (2 kbps)Field of view: 8.5 x 8.5 arcminuteTelescope: 30 cm diameter x 160 cm length, 8.66 m focal length CassegrainAx·1Z c ·DProgram: TransitM5 :2;P" Program: TransitE·`4 6#̑SAmerican navigation programFirst navigation program launched in 1959 and operational in 1964. These satellites were for the U.S. Navy and in particular, the Fleet Ballistic Missile Submarines, to accurately verify their location. This program was superseded by NOVA and finally by the Global Positioning Satellites. It was commercialized in 1967. First geodetic program to use the Doppler effect.There were 7 pre-operational Transit-5xxx satellites: 3 Transit-5A launched by Scout, 3 Transit-5BN (nuclear powered) launched by Thor Able-Star, an 1 Transit-5C launched by Scout. The Transit-5C was mostly identical with the operational Transit-O series. The first 5 Transit-O's transfered to the Thor Ablestar launch vehicle, because the Scout lacked reliability at this time.1 ' O ContactD `Ջ$ @Operator: Naval Space Command<' *O External resourcesb;Ջs' vhttp://www.fas.org/spp/military/program/nav/transit.htm8' "(Technical datavsD# Frequencies: 149.982 / 149.988 (operational channel) MHz and 399.9413 / 399.952 / 399.968 (operational channel) MHz1u1 u[DO n|ۀd؀㺶؉㻶؉ABProgram: TransitTransit 2ATransit 4ATransit 4BTransit 5BN1Transit 5BN2; uZ1  Z}Transit 2AK8 @(;P" Transit 2A1 Z֎'  Generalg =G#^@") Designation00045 / 60007A\֎A#R6Launch date22 Jun 1960t'=M#jN"N ,㹌לCountry of originUnited StatesgM#j4"H̀シMissionNavigation^A#R:"Perigee/Apogee604/988 kmV4A#R*Inclination66.7UA#R(Period100.8 minq$4M#jH" &Gi4Launch vehicleThor Ablestar_YA#R<Launch siteCape Canaveral$}" ; Y1I% uTransit 4AK}8 @(;P" Transit 4A1 4'  Generalg G#^@") Designation00116 / 61015A\4A#R6Launch date29 Jun 1961t'kM#jN"N ,㹌לCountry of originUnited StatesgM#j4"H̀シMissionNavigation^k0A#R:"Perigee/Apogee866/985 kmVA#R*Inclination66.8U0A#R(Period103.5 minq$LM#jH" &Gi4Launch vehicleThor Ablestar_A#R<Launch siteCape Canaveral[LA#R4"Mass at launch79.1 kgoEu* $ㅯ\&First satellite using a SNAP nuclear generator for power supply; 1у Transit 4BKu8 @(;P" Transit 4B1 ,'  Generalg G#^@") Designation00202 / 61031A\,A#R6Launch date15 Nov 1961t'cM#jN"N ,㹌לCountry of originUnited StatesgM#j4"H̀シMissionNavigation_c)A#R<"Perigee/Apogee953/1104 kmVA#R*Inclination32.4U)A#R(Period105.7 minq$EM#jH" &Gi4Launch vehicleThor Ablestar_A#R<Launch siteCape Canaveral[EA#R4"Mass at launch90.4 kgo2 4zPWㅯ\&Was launched with Traac: first time 2 satellites were launched with the same vehicleHas a SNAP engine= 1%@ *Transit 5BN1M*8 @,;P" Transit 5BN11 ['  Generalg *G#^@") Designation00670 / 63038B\[A#R6Launch date28 Sep 1963t'M#jN"N ,㹌לCountry of originUnited StatesgM#j4"H̀シMissionNavigation`YA#R>"Perigee/Apogee1062/1125 kmTA#R&Inclination90UYA#R(Period107.1 minq$M#jH" &Gi4Launch vehicleThor Ablestar[A#R4Launch siteVandenberg$" = ;1у ;QTransit 5BN2M8 @,;P" Transit 5BN21 ;'  Generalg  G#^@") Designation00704 / 63049B[{A#R4Launch date5 Dec 1963t' M#jN"N ,㹌לCountry of originUnited Statesg{VM#j4"H̀シMissionNavigation`A#R>"Perigee/Apogee1058/1109 kmVV A#R*Inclination90.1UaA#R(Period106.9 minq$ M#jH" &Gi4Launch vehicleThor Ablestar[a-A#R4Launch siteVandenberg$Q" 7-1" Triana7 Q, (" Triana& US satellite project. This spacecraft would be located at one of the L points to broadcasts pictures of the Earth viewed from space.This project is defended by Al Gore (US Vice president)F1m"# 1mProgram: TrimilsatcomF1, (6" Program: Trimilsatcom< m2 2kProject for 1 military telecommunication satellite shared by France, Germany and UK. Should be operational in 2005. The program should cost $2.2 billion. Belgium might join in.The system would replace UK's Skynet and France's Syracuse's payload on Telecom.111W  T+m) "VȠ$To view this page you need to register& # 5M 1<#" M GTRMM5  , (" TRMMI&M # LTropical Rainfall Measuring Mission1 '  Generalg c G#^@") Designation25063 / 97074A\ A#R6Launch date27 Nov 1997t'c 3 M#jN"N ,㹌לCountry of originUnited Statesk M#j<"H̀郉MissionRemote sensingZ3 A#R2"Perigee/Apogee350 kmT L A#R&Inclination35L A#RPeriodiL  M#j8" &JLaunch vehicleH2 #5{V |% The volume of rainfall in the tropics accounts for about two-thirds of total rainfall on the earth. Acting as the "engine" of the atmospheric cycle, this rainfall has a major influence on climate formation on a global scale. TRMM is a satellite that will measure the amount and distribution of rainfall in tropical and meta-tropical areas. Remote sensing of rainfall by the satellite will make a major contribution in predicting climatic changes on a global scale, providing long-range predictions on abnormal weather created by the E1 Nino phenomenon, and helping to prevent natural disasters.xT @$ TRMM is a joint project of Japan and the United States. It is worth $512 million| @ <|H@' *O External resources @ A6 :http://trmm.gsfc.nasa.gov/http://yyy.tksc.nasda.go.jp/Home/This/This-e/trmm_e.htmlhttp://asd-www.larc.nasa.gov/ceres/ASDceres.html8H@BA' "(OTechnical data8 AzA' " Specifications_BAAA#R<&Prime contractorNASA GSFCN zA'BA#RPlatform[ABA#R4"Mass at launch3820 kgS'BBA#R$ Mass in orbitOB$CA#RDimensionQBuCA#R Solar arrayS$CCA#R$ StabilizationN uCDA#RDC power\CrDA#R6$Design lifetime3 yearsjDE, (@ĘAcquisition via TDRSTelemetry/Data: 2255.5 MHz (upto 2 Mbps)Command: 2076.94 MHz (500 or 1024 bps)1 rD9E' O Payloadf<EG* "yPR: Precipitation Radar (Ku-band)TMI: TRMM Microwave ImagerVIRS: Visible and Infrared ScannerCERES: Clouds and the Earth's Radiant Energy SystemLIS: Lightning Imaging SensorThe CERES instrument (TRW-built) is the first of a series of 6 to fly. CERES is a scanning broadband radiometer that measures reflected sunlight and emitted thermal energy from the surface of the Earth and the atmosphere. The radiometer is made up of three sensors, each with its own telescope mounted on a gimballed platform that continuously scans across the Earth in a 6.6-second cycle. 69EG1< G HLTRSSS6 G H, (" TRSSSI&GTH# LThai Remote Sensing Small Satellite1 HH'  GeneralYTHHG#^$") Designation`H>IA#R>Launch dateplanned in 2000o"HIM#jD"N ,)`Country of originThailandc>IJG#^8"H̀MissionRemote sensingZIjJA#R2"Perigee/Apogee550 kmVJJA#R*InclinationpolarL jJ KA#RPeriod\JhKG#^*" &Launch vehicleQ KKA#R Launch site]9hKL$ rTo weigh 300 to 400 kg, to br built by Spar Aerospace1KGL1W GLLLT+LL) "VȠ$To view this page you need to register&GLL# 6LL1" L-MWTTS 16 L-M, (" TTS 1zKLM/ .   Tethered Test Satellite, also called TSS (Tethered Satellite System)1 -MM'  General[M3NA#R4Launch date6 Aug 1992lMNM#j>"N ,xECountry of originItalyZ3NNA#R2OperatorCNR/PSN/NASA_NXOG#^0"H̀MissionScientificjNOM#j:" &㨛Launch vehicleSTS 46XOz+ $㨛To test power proOzLduction (by induction). The satellite couldn't be deployed properly on STS 46 (only a few hundred meters).8O' "(OTechnical data8z' " Specifications_IA#R<&Prime contractorAeritaliaZA#R2"Mass at launch518 kgWIA#R,Payload mass66 kgSMA#R$Diameter1.6 mc"A#RD StabilizationGravity gradientWMA#R,DC power180-200 W`gA#R>$Design lifetime10 missionsW' Payload: instruments to measure electrodynamic properties of the ionosphere, magnetic fields and plasmaTether (diameter: 2.54 mm) made from Kevlar sheated in Nomex with insulated copper-wire core6g1|! ÄTTS 26 WÄ, (" TTS 2}N@/ .   Tethered Test Satellite, also called TSS 1R (Tethered Satellite System)1 Äq'  Generalg @؅G#^@") Designation23805 / 96012B\q4A#R6Launch date22 Feb 1996l؅M#j>"N ,xECountry of originItalyZ4A#R2OperatorCNR/PSN/NASA_YG#^0"H̀MissionScientificjÇM#j:" &(Launch vehicleSTS 75G"Y % EThe TSS project is a joint NASA/ASI (Italian Space Agency) effort. The 1.6 m diameter satellite is to be deployed on the end of a 20 kilometre long conductive tether to study the electrodynamic effects of moving such a tether through the Earth's magnetic field. The experiment will also test techniques for managing the tethered spacecraft at great distances. Second flight of the satellite which was worth about $200-400M (depending on whether or not you count the cost for the original satellite, modifications after the first flight, etc.) Ç% The tether broke near full deployment (19 km) on 26 Feb at 01:30 UT. The initial orbit for the satellite was 316 x 413 km; meanwhile the shuttle was at 291 x 299 km. The break was due to an electrical shortcut inside the cable.5 K'  End of lifeVA#R*Decay19 Mar 1996mIK$ Frequency downlink: 2260 MHz, uplink at 2081 MHz, 16 kbps data stream@N15́ NProgram: TubsatL5 :0&\Lʀ" Program: TubsatN, & Technische Universitt Berlin SATellitGerman small satellites program for data relay applications. 3-axis stabilized satellitesTransmissions are made on 143,075 MHz (mode: AFSK 1200 Baud, 1200/1800 Hz tones)1ύ1 ύ4e+4: DVIIProgram: TubsatTubsat ATubsat B9ύm1;ˀ mTubsat AI48 @$&\Lʀ" Tubsat A1 m'  Generalg NG#^@") Designation21577 / 91050D\A#R6Launch date17 Jul 1991n!N$M#jB"N , Country$4 of originGermanyJG#^"H̀MissionScientific: animal migration studies for Berlin's university^$A#R:"Perigee/Apogee762/772 kmViA#R*Inclination98.4UA#R(Period100.2 minn!i,M#jB" &`D+Launch vehicleAriane V44YA#R0"Mass at launch38 kg$," 91< +Tubsat BI+8 @$&\Lʀ" Tubsat B1 \'  Generalg +G#^@") Designation22970 / 94003B\\A#R6Launch date25 Jan 1994n!M#jB"N , Country of originGermany_G#^0"H̀MissionTechnology`LA#R>"Perigee/Apogee1183/1209 kmWA#R,Inclination82.55VLA#R*Period109.35 minr%kM#jJ" &ቂLaunch vehicleCyclone 3 #107$" Ak1!B !Program: TurksatQ!8 @4 " Program: Turksat`7) "nTelecommunication program operated by Turk Telekom1!1 DJDH `]cKlvmmvmnvmvmProgram: TurksatTurksat 1ATurksat 1BTurksat 1CTurksat 2A1u1U uhFD) ": Turksat's specificationsb!uA#RB0&Prime contractorAerospatiale[xA#R40PlatformSpacebus 100B[A#R40"Mass at launch1775 kgZx-A#R20 Mass in orbit1078 kg`A#R>0Dimension2.8 x 2.2 x 2.5 m\-A#R60Solar array22.4 m spanYBA#R00 Stabilization3 axisa A#R@0DC powerEOL equinox: 2900 W]BA#R80$Design lifetime12 yearsh'hA#RN0Apogee motorMBB S400 (liquid fuel)$" 1h1 c+?) ", Turksat's Ku-bandYUA#R00(Main transponders16ZA#R20,Backup transponders8VUA#R*0Power55 W (TWTA)@B#T0Bandwidth10 transponders of 36 MHz6 transponders of 72 MHztch#00*2*a5*a5Coverage andEIRP maxTurkey: 55 dBWCentral Europe: 58 dBWCentral Asia: 50 dBW (centered on Afghanistan)J O#n0G/T maxTurkey: 12 dB/KCentral Europe: 13 dB/KCentral Asia: 12 dB/Kc icuM#j80 Polarizationlinear H/VP B#T0Frequencies:uplink: 14-14.5 GHzDownlink: 10.95-11.2 GHz and 11.45-11.7 GHz$u+" 1\1 \j4+6 10.9801214.28036Turkey- #,Z|xyjy.2:<14.312511.01236Europe/Turkey' X#,N|xyjy $4<>11.0301314.33036Turkey&8@#,L|xyjy.2:<X8@14.354611.05436Turkey'X A#,N|xyjy $4<>11.0801414.38036Turkey&8@A#,L|xyjy.2:<14.396711.09636Turkey' AB#,N|xyjy $4<>11.1301514.43036Turkey-AC#,Z|xyjy.2:<14.462811.16272Europe/Turkey'BfD#,N|xyjy $4<>11.1801614.48036TurkeyC%E#,"|xyjy &fDE#,L|xyjy"2:<11.486914.03672Turkey&%EF#,L|xyjy.2:<14.040111.49072Europe'EG#,N|xyjy $4<>11.5741014.12472Turkey+F{H#,V|xyjy.2:<14.140211.59072Turkey/Asia'GPI#,N|xyjy $4<>11.6621114.21272Turkey+{H)J#,V|xyjy.2:<14.228311.67836Turkey/Asia<PIeJ$ 0beacon: 11.105 GHz V; )JJ142 JJTurksat 1CGeJJ5 :& " Turksat 1C1 JK'  Generalg JKG#^@") Designation23949 / 96040B[KKA#R4Launch date9 Jul 1996m KGLM#j@"N ,.Country of originTurkeyo"KLM#jD"H̀‰MissionTelecommunicationsb!GLMA#RB,Geostationary orbitsee belown!LMM#jB" &E+Launch vehicleAriane V89gMMJ#d:$Mass at launch1743 kg&MN# : MMN- */ۀ LocationNNm#:   " BeginEndPosition!MNbOj#B"02L: 9 Jul 1996tests31.3EN j#4"&(late Sep 199642EbO eJ&bO2# 8 j' "(Technical data<2) "&FaSpecifications8jހ' " EIRP map (dBW)d4B0 0h⪜nICentral Europe & TurkeyCentral Asia & Turkey1 ހs'  Ku-bandYB́A#R00(Main transponders16Zs&A#R20,Backup transponders8V́|A#R*0Power55 W (TWTA)X&C#V0Bandwidth9 transponders of 36 MHz2 transponders of 54 MHz5 transponders of 72 MHzg|̓O#n0*0⪜nICoverage andEIRP maxWest: Central Europe & Turkey: 53 dBWEast: Central Asia & Turkey: 53 dBWT!A#R&0G/T max11 dB/K\̓}A#R60Polarizationlinear H/VsO!$ The satellite beams were modified to have wider coverage (but only 2 beams)K$};' H Transponder frequency chart (GHz)^#h#|xyjy,\z̀Horizontal UplinkHorizontal DownlinkTransponderVertical DownlinkVertical UplinkBandwidth (MHz)Coverage (downlink)1;x#,b|xyjy8<LTV10.97012 (but not 4)14.27036East1W#,b|xyjy8HLTV14.2704 (but not 12)10.97036West$x)#,H|xyjy.2:<14.312511.01236West%W#,J|xyjy $4<>11.0301314.33036East$)Ί#,H|xyjy.2:<14.354611.05436West%#,J|xyjy $4<>11.0801414.38036East$Ίs#,H|xyjy.2:<14.396711.09636West%F#,J|xyjy $4<>11.1301514.43036East$s#,H|xyjy.2:<14.462811.16272West%F#,J|xyjy $4<>11.1801614.48036East#,"|xyjy $#,H|xyjyeJ"2:<11.486914.03672East$Z#,H|xyjy.2:<14.040111.49072West%-#,J|xyjy $4<>11.5741014.12472East$Z#,H|xyjy.2:<14.140211.59072West1-#,b|xyjy8<LTV11.66911 (but not 3)14.21954East1#,b|xyjy8HLTV14.2193 (but not 11)11.66954West$" 11 xf0x6 I# 6Also called Eurasiasat 11 '  GeneralYXG#^$") DesignationZA#R2Launch datelate 1999m XM#j@"N ,.Country of originTurkeyo"M#jD"H̀‰MissionTelecommunicationsh'A#RN,Geostationary orbit42E co-locatedbXG#^6" &Launch vehicleAriane' 3Total cost: $260 millionCapacities will be marketed by Eurasiaspace (or Eurasiasat), a Monaco-based joint venture of Aerospatiale and Turk Telecom.8XP' "(OTechnical data8' " Specificationsb!PA#RB&Prime contractorAerospatialeN 8A#RPlatform[A#R4"Mass at launch3400 kgS8A#R$ Mass in orbitO5A#RDimensionQA#R Solar arrayS5A#R$ StabilizationT-A#R&DC power9000 WUA#R($Design lifetime&-# 1 '  Ku-bandY2A#R0(Main transponders32YA#R0,Backup transpondersP2A#RPower110 WO*A#RBandwidthe$A#RHCoverageWestern Europe to ChinaN *A#REIRP maxM 6A#R6G/T maxRA#R"Polarization&6# 11W 3YT+3) "VȠ$To view this page you need to register&Y# ?31́, [Program: TvsatKY5 :.o?" Program: TvsatxO[) " German direct TV program operated by the DBP (Deutsche BundesPost Telekom)11 b([: DPmѾmԐmԐProgram: TvsatTvsat 1Tvsat 211U <[# 2Tvsat's specificationsk*A#RT&Prime contractorEurosatellite and MBBZ[ A#R2PlatformSpacebus 300[{A#R4"Mass at launch2144 kgC A#RPayload mass195.9 kg: transponders: 97.6 kg, antennas: 98.3 kga {`A#R@Dimension2.4 x 1.64 x 6.4 mYA#R0 Stabilization3 axis?`:B#T~DC powerBOL: 4500 WEOL: equinox: 3312 W, solstice: 3060 W\A#R6$Design lifetime9 years$:" 11U  % 5 # $Tvsat's Ku-bandXxA#R.0(Main transponders4Z A#R20,Backup transponders2Wx)A#R,0Power230 W (TWTA)U~A#R(0Bandwidth27 MHzT)A#R&0CoverageEuropeT~& A#R&0EIRP max65 dBW\ A#R60Polarizationcircular L=&  B#Tz0FrequenciesUplink: 17.7-18.1 GHzDownlink: 11.7-12.5 GHz$ % " 8 ] 1 ] ^Tvsat 1D% 5 : o?" Tvsat 11 ] '  Generalg 9 G#^@") Designation18570 / 87095A\ A#R6Launch date21 Nov 1987n!9  M#jB"N , Country of originGermanyf i M#j2"H̀‰MissionDirect TVt3 A#Rf,Geostationary orbitwas expected in slot 19.2Wn!i K M#jB" &D+Launch vehicleAriane V20 % [Not functional because a solar pannel remains in front of the antennas. In fact 2 bolts had been forgotten that screw the antenna tight for transportation before launch!5K R'  End of lifea A#R@"Out of serviceFebruary 1988&R# 8' "(Technical dataM^0 0: *,_SpecificationsKu-band81  }FTvsat 2D^5 : o?" Tvsat 21 @'  @^Generalg ~@G#^@") Designation20168 / 89062A[@@A#R4Launch date8 Aug 1989n!~@GAM#jB"N , Country of originGermanyf@AM#j2"H̀‰MissionDirect TVb!GABA#RB,Geostationary orbitsee belown!A}BM#jB" &4D+Launch vehicleAriane V33B/C+ $ĉWas available on 25 Aug 1989 to broadcast the Berlin's TV show. Was leased to Tele TV AS and co-located with Intelsat 702 in 1995: }BiC- */ۀ Location/CCm#:   " BeginEndPosition$iCDj#H"68L: 8 Aug 1989Feb 199519.2WCEj#,Mar 19950.6W&D'E# 8E_E' "(Technical datal4'EE8 @hi3W *,_EIRP coverage (dBW)SpecificationsKu-band/_EE'  Video_EYFA#R<i$Video excursion13.5 MHz/v$E}F" 1YFF1 FFP}FF6 <6mԐ"jTvsat 2's EIRP map5F3G1B 3GhGHUARS5 FhG, (" UARSJ'3GG# N Upper Atmospheric Research Satellite1 hGG'  Generalg GJHG#^@") Designation21701 / 91063B\GHA#R6Launch date12 Sep 1991t'JHIM#jN"N ,㹌לCountry of originUnited States~1HIM#jb"H߲̀-MissionScientific: high atmosphere study^IIA#R:"Perigee/Apogee555/586 kmVILJA#R*Inclination56.9RIJA#R"Period96 minjLJKM#j:" &㪛Launch vehicleSTS 48JK&  Mission: systematic study of Earth's stratosphere, mesosphere and lower thermosphere with specialized payloads.Cost: $630 million<KK' *O External resourcesJ#K:L' Fhttp://uarsfot08.gsfc.nasa.gov/8KrL' "(OTechnical data8:LL' " Specifications^rLMA#R:&Prime contractorGE Astroi(LqMA#RPPlatformMultiMission Spacecraft busu4MMA#Rh"Mass at launch6800 kg (2500 kg for the payload)QqM7NA#R Diameter5 mPMNA#RHeight10 m\7NNA#R6Solar array1.5 x 3.3 mYN- *|O  SOLSTICE (Solar Stellar Irradiance Comparison Experiment)C A# @Full disk solar UV irradiance^1M- *bO  SUSIM (Solar UV Spectral Irradiance Monitor)N+# Vsolar irradiance, solar flux variabilityg:M- *tO  ACRIM 2 (Active Cavity Radiometer Irradiance Monitor)F#H# Fwide band total solar irradiance= 1, ؇Program: UHFSH؇5 :>4d%" Program: UHF Follow Ony|+ &2Also called for short UHF or UFOMilitary telecommunication program composed of 10 satellites, advanced Fleetsatcom1 ؇' O ContactzN|', (n։Operator: Naval Space CommandCommand & control: Air Force Space Command% EA second generation of satellites is planned so as a 11th UHF satellite. This would cost nearly $2 billion. The new generation would be launched from 2007 on.<'*' *O External resourcesU. ,http://www.fafb.af.mil/uhf/http://www.fas.org/spp/military/program/com/ufo.htm1*ފ1 ފZk S|W|W|W|W|W|W|W|W|WProgram: UHFUHF 1UHF 2UHF 3UHF 4UHF 5UHF 6UHF 7UHF 8UHF 91ފԋ1U ԋ 0:# .UHF's specifications\ԋjA#R60&Prime contractorHughesTA#R&0PlatformHS-601e$j#A#RH0"Mass at launch3000 kg (approx.)o.A#R\0 Mass in orbit1120 kg (1360 kg from F4 on)Q#A#R 0Length3.2 mP3A#R0Width3.4 mb!A#RB0Height3.4 m (7.0 m deployed)\3A#R60Solar array18.3 m spanYJA#R00 Stabilization3 axisYA#R00DC powerEOL: 2500 WUJ A#R(0$Design lifetime $0" 1 a1W aT+0) "VȠ$To view this page you need to register&a# 1 1 . :# UHF-bandP A#R0Channels39R:A#R"0Amplifiers11K 'A#R0Power]A#R80Bandwidthtotal: 555 KHzN 'A#R0CoverageN A#R0EIRP maxRrA#R"0PolarizationoK $ Within the 39 channels: 21 narrow band, 17 relay, and 1 Fleet Broadcast1r1  . @# EHF-bandPA#R0Channels11K @A#R0PowerO*A#R0Bandwidth|:B#Tt0,Coverage & EIRP maxglobal beamsteerable 5 spot beamR*A#R"0Polarization+ $2The EHF package provides enhanced anti-jam telemetry as well as command, broadcast andfleet interconnectivity communications. It was first tested on Fleetsatcom 7 & 8 and is also used on Milstar6!1I !c{UHF 1B c5 :4d%" UHF 11 !'  Generalg cG#^@") Designation22563 / 93015A\WA#R6Launch date25 Mar 1993t'M#jN"N ,㹌לCountry of originUnited Statesy,WDM#jX"H̀‰MissionMilitary: telecommunications\A#R6,Geostationary orbitn/av)DM#jR" &!{Launch vehicleAtlas Centaur #0745K'  End of lifeHA#RCausewas delivered in a wrong orbit due to a partial launch failure&K# 82' "(Technical dataI{0 02-ₖSpecificationsUHF621<ㄷ UHF 2B {5 :4d%" UHF 29,# ,Also called USA 0951 ]'  Generalg ,G#^@") Designation22787 / 93056A[]A#R4Launch date3 Sep 1993t'M#jN"N ,㹌לCountry of originUnited Statesy, M#jX"H̀‰MissionMilitary: telecommunicationsq*}G#^T"/ۀ0Geostationary orbit71.5E, inclinedu( M#jP" &yjLaunch vehicleAtlas Centaur #79&}# 8P' "(Technical dataI0 02-ₖSpecificationsUHF6P1#d UHF 3B 5 :4d%" UHF 39V# ,Also called USA 1041 '  Generalg VG#^@") Designation23132 / 94035A\JA#R6Launch date24 Jun 1994t'M#jN"N ,㹌לCountry of originUnited Statesy,J7M#jX"H̀‰MissionMilitary: telecommunicationsq*G#^T"/ۀ0Geostationary orbit15.5W, inclinedu(7M#jP" &yjLaunch vehicleAtlas Centaur #83&C# 8{' "(Technical dataPC2 4-ₖSpecificationsUHFEquipped with an ARC 490N (liquid fuel) apogee engine6{31ㄷ 3u=UHF 4B u5 :4d%" UHF 4;3# 0Also known as USA 1081 u'  Generalg HG#^@") Designation23467 / 95003A\A#R6Launch date29 Jan 1995t'HM#jN"N ,㹌לCountry of originUnited Statesy,M#jX"H̀‰MissionMilitary: telecommunicationsp)G#^R"/ۀ0Geostationary orbit178W, inclinedu(vM#jP" &yjLaunch vehicleAtlas Centaur #889$ *Tested in 170.5W8v' "(Technical dataV=7 >>-ₖ"SpecificationsUHFEHF6s1d sC UHF 5B =5 :4d%" UHF 59s# ,Also called USA 1111  '  Generalg  G#^@") Designation23589 / 95027A\ A#R6Launch date31 May 1995t' V M#jN"N ,㹌לCountry of originUnited Statesy, M#jX"H̀‰MissionMilitary: telecommunicationsq*V @ G#^T"/ۀ0Geostationary orbit70.5E, inclinedu( M#jP" &yjLaunch vehicleAtlas Centaur #928@ ' "(Technical dataV C 7 >>-ₖ"SpecificationsUHFEHF6 y 10 y @UHF 6B C 5 :4d%" UHF 69y # ,Also called USA 1141 % '  Generalg G#^@") Designation23696 / 95057A\% A#R6Launch date22 Oct 1995t' \M#jN"N ,㹌לCountry of originUnited Statesy, M#jX"H̀‰MissionMilitary: telecommunicationsf\;G#^>"/ۀ0Geostationary orbit106Wu(M#jP" &yjLaunch vehicleAtlas Centaur #95W-;@* $Z#AgTested in 171.5W and replaced Leas@C at 38K@' "(Technical dataV@@7 >>-ₖ"SpecificationsUHFEHF6K@@1V @AEUHF 7B @A5 :4d%" UHF 71 @JA'  Generalg AAG#^@") Designation23967 / 96042A\JA BA#R6Launch date25 Jul 1996t'ABM#jN"N ,㹌לCountry of originUnited Statesy, BBM#jX"H̀‰MissionMilitary: telecommunicationseB_CG#^<"/ۀ0Geostationary orbit25Wv)BCM#jR" &yjLaunch vehicleAtlas Centaur #1010 _CE' Tested in 171.5WIt is the first of the series to have an enhanced EHF payload, adding nine more channels. This was accomplished on a very short schedule with advanced, miniaturized digital technology so that no additional spacecraft resources were required.8C=E' "(Technical dataVEE7 >>-ₖ"SpecificationsUHFEHF6=EE10 E FJUHF 8B E F5 :4d%" UHF 81 E"/ۀ0Geostationary orbit172Ev)GHM#jR" &yjLaunch vehicleAtlas Centaur #115RHwJ% First UHF satellite with the GBS (Global Broadcast System) payload. It replaces the current SHF capability with four 130 W, 24 MHz military Ka band transponders, 3 steerable downlink spot beam antennas and one steerable uplink (+ 1 fixed) receive antenna per satellite. This will provide 96 Mbps throughput. The GBS payload is provided by Hughes Information Systems (HIS, Reston, Virginia)8HJ' "(Technical dataIwJJ0 02-ₖSpecificationsUHF; J3K10V 3KzKyNUHF 9 & 10GJzK5 :&4d%" UHF 9 & 103KyN( will be launched in 1998Will have the GBS (Global Broadcast System) modification. Each satellite would provide GBS service to one of these areas: Indian Ocean, Pacific Ocean and Atlantic Ocean.The GBS payload will replace the current SHF capability with four 130 watt, 24 megahertz military Ka band transponders, 3 steerable downlink spot beam antennas and one steerable uplink (+ 1 fixed) receive antenna per satellite. The GBS augmentation would support a full range of simplex, or one-way communications, from national imagery dissemination to general news and entertainment broadcasts. Each satellite will provide 96 Mbps throughput. The GBS payload is provided by Hughes Information Systems (HIS, Reston, Virginia)1zKN1W NN$OT+yNN) "VȠ$To view this page you need to register&N$O# 6NZO1 ZOOwUme 16 $OO, (" Ume 1T1ZO # bMeans "apricot tree flower", also called ISS 1O $O1 O='  Generalg G#^@") Designation08709 / 76019A\=A#R6Launch date29 Feb 1976llM#j>"N ,bCountry of originJapany,M#jX"H̀?vMissionScientific: ionosphere study_lDA#R<"Perigee/Apogee985/1006 kmVA#R*Inclination69.7SDA#R$Period105 minfSM#j2" &JLaunch vehicleN1$w" 6S1 wUme 2> w2 4"  Ume 27"# (Also called ISS 21 S'  Generalg "G#^@") Designation10674 / 78018A\SA#R6Launch date16 Feb 1978lM#j>"N ,bCountry of originJapanaG#^4"H̀MissionScientifique_BA#R<"Perigee/Apogee970/1219 kmVA#R*Inclination69.4UBA#R(Period107.2 minfSM#j2" &JLaunch vehicleN1$w" : S1 Unamsat 1Bw2 4""  Unamsat 11 $'  General\A#R6Launch date28 mar 1995e$G#^<"N ,Country of originMexicoo"TM#jD"H̀㓉MissionTelecommunicationslM#j>" &aKLaunch vehicleStart #2&T# 5'  End of lifec~G#^8 CauseLauncher failureVԊA#R*Decay28 Mar 1995[7~/$ nBuilt by UNAM, the Autonomous University of Mexico.8Ԋg' "(OTechnical data?/' 0 Frequency chart (MHz),g0^#X "JLDownlink freq.Transponder/BeaconModej#4 "437.135TX1default}01j#& "437.179TX2s j# +19j#V  HJUplink freq.Transponder/BeaconModeĎp#6 .0145.922Channel A9Gj#2,.145.942Channel BĎʏj#2,.145.962Channel CG[j#6ʏ[w02145.872Channel E/F&ʏ# : [1J Unamsat 2B2 4""  Unamsat 2b?_# ~Autonomous University of Mexico Satellite, also called MO-301 '  Generalg _G#^@") Designation24305 / 96052B[RA#R4Launch date5 Sep 1996m M#j@"N ,Country of originMexicoo"R.M#jD"H̀㓉MissionTelecommunications_A#R<"Perigee/Apogee966/1010 kmV.A#R*Inclination82.9U8A#R(Period104.8 mineG#^<" &Launch vehicleCosmos 3MY8A#R0Launch sitePlesetsk' On board a 40.997 MHz pulse transmitter and a wide band receiver centered on the same freq. will enable the search for echoes produced on the ionized trails of meteors as they enter the atmosphere.The launch of the satellite costed $112,000<O' *O External resources]6' lhttp://serpiente.dgsca.unam.mx/unamsat/unameng.htm5O'  End of life^?A#R:"Out of service6 Sep 1996gA#RCausefailed to operate, died after 1 day The uplink receiver did not survive the launch conditions&? # 8E' "(OTechnical data8 }' " SpecificationsVEA#R*&Prime contractor\}/A#R6PlatformAmsat Microbus[A#R4"Mass at launch10.7 kgS/A#R$ Mass in orbit^;A#R:Dimension25 x 25 x 25 cmQA#R Solar arrayS;A#R$ StabilizationN -A#RDC powerUA#R($Design lifetime&-# ?' 0 Frequency chart (MHz),q^#X "JLDownlink freq.Transponder/BeaconModej#4 "437.206TX1default}qrj#& "437.138TX2s j# +rzj#V  HJUplink freq.Transponder/BeaconModep#6 .0145.815Channel Azj#2,.145.835Channel Bj#2,.145.855Channel Cj#2,.145.875Channel D&# 11W EkT+E) "VȠ$To view this page you need to register&k# ?E1 Program: UosatKk5 :." Program: Uosatw. , kdgUniversity Of Surrey sATelliteSatellites built by and operated by a unit of Surrey's university in the UK: SSTL11 rQrV |~ꠀ͓F̀ΓF̉ϓF̉ГF̉ѓF̉qOProgram: UosatUosat 1Uosat 2Uosat 3Uosat 4Uosat 5Uosat 1281 k  Uosat 1Dr5 : " Uosat 1K"9) "D䵟Also called UO-09 or Oscar 091 j'  Generalg 9G#^@") Designation12888 / 81100B[j,A#R4Launch date6 Oct 1981u(M#jP"N ,R׉Country of originUnited Kingdomo",M#jD"H̀㓉MissionTelecommunications^nA#R:"Perigee/Apogee372/374 kmVA#R*Inclination97.6RnA#R"Period92 mins&M#jL" &p㉂Launch vehicleThor Delta #157[A#R4Launch siteVandenberg& 'Cost: $38000First on-board computer (IHU - Integrated Housekeeping Unit) for battery and attitude management, remote control, and experiments.5'  End of lifeV( A#R*Decay13 Oct 1989&N # 8( ' "(OTechnical data8N ' " Specificationso. - A#R\&Prime contractorUniversity of Surrey (UK)S A#R$PlatformUoSATY- A#R0"Mass at launch52 kgc" < A#RDDimension0.74 x 0.42 x 0.42 mz9 A#Rr Stabilization3 axis (gravity gradient, magnetorquer)b <  B#T@DC powerBOL: 17 WEOL: 10 W\ t A#R6$Design lifetime3 yearsZ6 $ lEquipped with a vocal synthetisor and a TV camera.8t  1 )R  J FUosat 2D J 5 : " Uosat 2K" ) "D䵟Also called UO-11 or Oscar 111 J '  Generalg -G#^@") Designation14781 / 84021B[ A#R4Launch date1 Mar 1984u(-M#jP"N ,R׉Country of originUnited Kingdomo"lM#jD"H̀㓉MissionTelecommunications^A#R:"Perigee/Apogee651/669 kmVl,@A#R*,@ Inclination97.8R~@A#R"Period98 mins&,@@M#jL" &p㉂Launch vehicleThor Delta #174[~@LAA#R4Launch siteVandenbergv@A$ Function: Bulletin store and forward experiment, synthetic voice experiment, space dust and radiation experiments.<LA"B' *O External resources[4A}B' hhttp://www.users.zetnet.co.uk/clivew/oscar11.htm8"BB' "(OTechnical data8}BB' " Specificationso.B\CA#R\&Prime contractorUniversity of Surrey (UK)SBCA#R$PlatformUoSATY\CDA#R0"Mass at launch60 kgc"CkDA#RDDimension0.58 x 0.36 x 0.36 mz9DDA#Rr Stabilization3 axis (gravity gradient, magnetorquer)~<kDcEB#TxDC powerBOL: 25 W (12 v, 6.4 Ah NiCd battery)EOL: 10 W\DEA#R6$Design lifetime3 years&cEE# 9EF' $ Frequency chartvEFB#TDownlink1200 bps AFSK/FM (1200 and 2400 Hz tones), synthetic voice and CW.145.826 MHz, 435.025 MHz, 2401.500 MHz$FF" 8F2G1 R 2GvGUosat 3DFvG5 : " Uosat 3K"2GG) "D䵟Also called UO-14 or Oscar 141 vGG'  Generalg GYHG#^@") Designation20437 / 90005B\GHA#R6Launch date22 Jan 1990u(YH*IM#jP"N ,R׉Country of originUnited Kingdomo"HIM#jD"H̀㓉MissionTelecommunications^*IIA#R:"Perigee/Apogee781/797 kmVIMJA#R*Inclination98.6UIJA#R(Period100.7 minn!MJKM#jB" &6D+Launch vehicleAriane V35eJK, (ߎ؉Function: Packet Radio Mailbox and DigipeaterSince 1992 it is used by VITA (see also Gemstar)5KK'  End of life]K3LA#R8"Out of servicelate 1996c"KLA#RDCauseonboard computer failureK 3LLA#RDecay&LM# 8L?M' "(OTechnical data8MwM' " Specificationso.?MMA#R\&Prime contractorUniversity of Surrey (UK)SwM9NA#R$PlatformUoSATYMNA#R0"Mass at launch46 kgb!9NNA#RBDimension0.6 x 0.34 x 0.34 mYNMOA#R0 Stabilization3 axisWNOA#R,DC powerEOL: 10 W\MO A#R6$Design lifetime3 yearsO F&O2# 9 k' $ Frequency chartC2B#TUplink9600 bps K9NG/G3RUH modulated FSK (FM) AX.25145.975 MHzEkwB#TDownlink9600 bps K9NG/G3RUH modulated FSK (FM) AX.25435.070 MHzk)B#TRBeacon1200 bps AFSK NBFM435.070 MHz$w" 8>1ɂ >jUosat 4D5 : " Uosat 4K">͂) "D䵟Also called UO-15 or Oscar 151 '  Generalg ͂eG#^@") Designation20438 / 90005C\A#R6Launch date22 Jan 1990u(e6M#jP"N ,R׉Country of originUnited Kingdomo"M#jD"H̀㓉MissionTelecommunications^6A#R:"Perigee/Apogee784/799 kmVYA#R*Inclination98.6UA#R(Period100.7 minn!YM#jB" &6D+Launch vehicleAriane V35&B# 5w'  End of life_BֆA#R<"Out of service23 Jan 1990Qw'A#R CauseFailed&ֆM# 8'' "(OTechnical data8M' " Specificationso.,A#R\&Prime contractorUniversity of Surrey (UK)SA#R$PlatformUoSATY,؈A#R0"Mass at launch46 kgb!:A#RBDimension0.6 x 0.34 x 0.34 mY؈A#R0 Stabilization3 axisW:A#R,DC powerEOL: 10 W\FA#R6$Design lifetime3 years$j" 8F17  Uosat 5Dj5 : " Uosat 5K"1) "D䵟Also called UO-22 or Oscar 221 b'  Generalg 1ɋG#^@") Designation21575 / 91050B\b%A#R6Launch date17 Jul 1991u(ɋM#jP"N ,R׉Country of originUnited Kingdom7%$S#vn"H̀(㓉郉MissionTelecommunications and Remote sensing^A#R:"Perigee/Apogee759/772 kmV$؍A#R*Inclination98.4U-A#R(Period100.2 minn!؍M#jB" &`D+Launch vehicleAriane V44uQ-$ Function: Packet Radio Mailbox, Digipeater and a CCD camera experiment (EIS).8H' "(OTechnical data8' " Specificationso.H A#R\&Prime contractorUniversity of Surrey (UK) jS_A#R$PlatformUoSATY A#R0"Mass at launch49 kgc"_A#RDDimension0.68 x 0.34 x 0.34 ml+A#RV Stabilization3 axis (gravity gradient)WA#R,DC powerEOL: 10 W\:A#R6$Design lifetime3 years&`# 9:' $ Frequency chartK`&B#T0Uplink9600 bps K9NG/G3RUH modulated FSK (FM) AX.25145.900 145.975 MHz&L# E&B#T0Downlink9600 bps K9NG/G3RUH modulated FSK (FM) AX.25435.120 MHz$L" 901 kɂ 0i?Uosat 129 i, (" Uosat 121 0'  GeneralYiG#^$") DesignationVIA#R*Launch date1998?u(M#jP"N ,R׉Country of originUnited Kingdom7IHS#vn"H̀(㓉郉MissionTelecommunications and Remote sensingTA#R&"Perigee/ApogeeQHA#R InclinationL 9A#RPeriodiM#j8" &mKLaunch vehicleRokotW9A#R,Launch site300 kg+$) Equipped with 2 cameras (10 m resolution panchromatic, 40 m multispectral). CCDs are from Eastman KodakTelecommunication experiments in L- and S-band are also on board for use with Nanyang Technological University, Singapore*Estimate cost: $9 million<`' *O External resourcesb;$' vhttp://www.ee.surrey.ac.uk/EE/CSER/UOSAT/missions/uo12/8`' "(OTechnical data82' " SpecificationsVA#R*&Prime contractorN 2A#RPlatformZ0A#R2"Mass at launch300 kgSA#R$ Mass in orbitO0A#RDimensionQ#A#R Solar arraySvA#R$ StabilizationN #A#RDC powerUvA#R($Design lifetime&?# 1p1W pT+?) "VȠ$To view this page you need to register&p# 9#1J #\UPMsat 19 \, (" UPMsat 1c@## Politechnical University of Madrid (UPM in spanish) Satellite1 \'  Generalg WG#^@") Designation23607 / 95033C[A#R4Launch date7 Jul 1995lW*M#j>"N ,qn͉*Country of originSpain>G#^|"H̀MissionTechnology (microgravity and telecommunications)^* A#R:"Perigee/Apogee665/675 kmVcA#R*Inclination98.1T A#R&Period98.2 minn!c%M#jB" &D+Launch vehicleAriane V75Y~A#R0"Mass at launch47 kg$%" = ~1 $LProgram: USAE$2 4("  Program: USAX* $)Designation used by the United States since mid-1984 to name military spacecrafts.1$/X#b"cZ>USA 001USA 002 = KH 9-19USA 003 = subsat(^#P$acZ:j܌҉USA 004 = SDS 5USA 005USA 006(/;^#P"@c㷫뉂.USA 007USA 008USA 009 = SDS 6"d#D"XcZ ceM.ceMUSA 010USA 011USA 012.;GX#\$FX~USA 013 = ITV 1USA 014 = ITV 2USA 015"d#D"X~X~.X~USA 016USA 017USA 018~&GKX#LD>ቂ*USA 019USA 020USA 021 = SDS 7"d#D"X~X~.X~USA 022USA 023USA 024"KWd#D"X~㧢щ.k܌҉USA 025USA 026USA 027,X#X"cFUSA 028USA 029 = DMSP B5D2-4USA 030"Wa d#D">ㄪ뉂.l܌҉USA 031USA 032USA 033" d#D"-..USA 034USA 035USA 036"a m d#D">.. c鉂USA 037USA 038USA 039~ ^#@"㷪*.USA 040USA 041USA 042"m q d#D"*dMceM.㲪뉂USA 043USA 044USA 0454  ^#h"E>..USA 046USA 047USA 048 = Magnum 2 = Mentor'q ^#N"...USA 049USA 050USA 051 = LACE& ^#L ҉6.USA 052 = RMEUSA 053USA 0549 R#tr(TUSA 055 = GLOMR 2USA 056 = POGS & SSRUSA 057 = TEX& ^#L "W~6"W~USA 058 = SCEUSA 059USA 060" d#D""W~"W~..USA 061USA 062USA 063"'d#D". c鉂.5F݉USA 064USA 065USA 066.^#\" F-USA 067USA 068 = DMSP B5D2-5USA 069~ '=@^#@5F݉=@*#W~USA 070USA 071USA 072.@^#\0#W~F c鉂USA 073 = DMSP B5D2-6USA 074USA 075"=@OAd#D"#W~#W~.ceMUSA 076USA 077USA 078"@Ad#D"5F݀5F݉.Z뉂USA 079USA 080USA 081"OA[Bd#D"ceM5F݉.5F݉USA 082USA 083USA 084"ABd#D"5F݀҉.5F݉USA 085USA 086USA 087"[BgCd#D"5F݀b뉂.5F݉USA 088USA 089USA 090"BCd#D" 6F݀6F݉.ceMUSA 091USA 092USA 093"gCsDd#D"6F݀|W.6F݉USA 094USA 095USA 096"CDd#D"ceMCd.USA 097USA 098USA 099"sDEd#D"6F݀j뉂.j뉂USA 100USA 101USA 102"DFd#D"j|W.j뉂USA 103USA 104USA 105"EFd#D"㫢р c鉂.|WUSA 106USA 107USA 108&F!Gp#L(㬢р(5i"4|WUSA 109USA 110USA 111'FGs#N(-i(ceM(4|WUSA 112USA 113USA 114'!GUHs#N((Ҁ(46F݀USA 115USA 116USA 117'GHs#N(3i(%W~(4%W~USA 118USA 119USA 120'UHIs#N(%W~(%W~(4%W~USA 121USA 122USA 123'H#Js#N(%W~([i(46F݀USA 124USA 125USA 126'IJs#N(|W(6F݀(4ҀUSA 127USA 128USA 129'#JWKs#N( c(㭢р(43Z݀USA 130USA 131USA 132'JKs#N(-(aeM(46F݀USA 133USA 134USA 135'WKLs#N(i(i(4iUSA 136USA 137USA 139$KL" 8LL1 L+MUSA 008DL+M5 : S" USA 008:LeM# .Also called Magnum 11 +MM'  Generalg eMMG#^@") Designation15543 / 85010B\MYNA#R6Launch date24 Jan 1985t'MNM#jN"N ,㹌לCountry of originUnited Statesn'YN;OG#^N"H̀MissionMilitary: SIGINT (Magnum)\NOA#R6,Geostationary orbitn/aj;O M#j:" &VLaunch vehicleSTS 20O L&O3# 8 k' "(OTechnical data3A, &U9%Magnum type satellite, built by TRW. Carried a 76 m diameter antenna.This type of satellite (SIGINT) has seen its performance increase with the diameter of the receiving antenna. Thus the Canyon satellites (1968-72) had 10 m antennas, the Rhyolite (1973-78) and the Jumpseat (1973-78) 18 m, the Vortex (1978-89) 38 m and the Magnum 76 m. The latest generation (Jeroboam) is believed to feature a 150 m diameter antenna!<k}' *O External resourcesd=A' zhttp://www.fas.org/spp/military/program/sigint/index.html8}1e+ ]USA 032D]5 : S" USA 032=# 4Also called Singleton 11 ]˃'  Generalg 2G#^@") Designation19460 / 88078A[˃A#R4Launch date5 Sep 1988t'2M#jN"N ,㹌לCountry of originUnited Statesq*rG#^T"H̀MissionMilitary: SIGINT (Singleton)Z̅A#R2"Perigee/Apogee900 kmTr A#R&Inclination85L ̅lA#RPeriodo" ۆM#jD" &^]Launch vehicleTitan 2 #13l& !Equipped with a 10 m diameter rotating radar, built by TRW, 1500 kgpart of the Wide Area Surveillance System (WASS) of the USAF and US Navy8ۆɇ10 ɇ USA 040D 5 : S" USA 0409ɇF# ,Also called SDS 2-11 w'  Generalg FވG#^@") Designation20167 / 89061B[w9A#R4Launch date8 Aug 1989t'ވM#jN"N ,㹌לCountry of originUnited States^9 G#^."H̀MissionMilitary:WbA#R,"Perigee/Apogeen/aT A#R&Inclinationn/aObA#RPeriodn/akpM#j<" &>DLaunch vehicleSTS 28R<' *O External resources`9p ' rhttp://www.fas.org/spp/military/program/com/sds_2.htm8D1Ȁ DUSA 045D 5 : S" USA 045=DŌ# 4Also called Singleton 21 '  Generalg Ō]G#^@") Designation20220 / 89072A[A#R4Launch date5 Sep 1989t'],M#jN"N ,㹌לCountry of originUnited Statesq*G#^T"H̀MissionMilitary: SIGINT (Singleton)Z,A#R2"Perigee/Apogee900 kmTKA#R&Inclination85L A#RPeriodo"KM#jD" &^]Launch vehicleTitan 2 #14& !Equipped with a 10 m diameter rotating radar, built by TRW, 1500 kgpart of the Wide Area Surveillance System (WASS) of the USAF and US Navy5'  End of life^[A#R:"Out of service5 Sep 1989L A#RCause?$[" 812 GHUSA 048DG5 : S" USA 0488# *Also called Mentor1 G'  Generalg G#^@") Designation20355 / 89090B\sA#R6Launch date23 Nov 1989t'M#jN"N ,㹌לCountry of originUnited Statesv)s]M#jR"H̀㷫뉂MissionMilitary: SIGINT (Magnum)\A#R6,Geostationary orbitn/ak]$M#j<" &DLaunch vehicleSTS 33R$H" 8$1Ȁ `USA 067DH5 : S" USA 067N+# VAlso called AFP 658 or Orion or Magnum 31 C'  Generalg G#^@") Designation20963 / 90097B\CA#R6Launch date16 Nov 1990t'zM#jN"N ,㹌לCountry of originUnited Statesv)M#jR"H̀㷫뉂MissionMilitary: SIGINT (Magnum)\zLA#R6,Geostationary orbitn/ajM#j:" &Launch vehicleSTS 38_LD#X6"Mass at launch2700 kgK'`$ NAimed to listen to the Persian Gulf81f USA 081D`5 : S" USA 081=# 4Also called Singleton 31 J'  Generalg G#^@") Designation21949 / 92023A\J A#R6Launch date25 Apr 1992t'M#jN"N ,㹌לCountry of originUnited Statesq* G#^T"H̀MissionMilitary: SIGINT (Singleton)ZLA#R2"Perigee/Apogee900 kmTA#R&Inclination85L LA#RPeriodo"[M#jD" &^]Launch vehicleTitan 2 #15& !Equipped with a 10 m diameter rotating radar, built by TRW, 1500 kgpart of the Wide Area Surveillance System (WASS) of the USAF and US Navy8[I1 I5USA 089D5 : S" USA 0899I# ,Also called SDS 2-21 '  Generalg ^G#^@") Designation22518 / 92086B[A#R4Launch date2 Dec 1992t'^9M#jN"N ,㹌׹9Country of originUnited StatesfG#^>"H̀MissionMilitary: SIGINT?e$9A#RH"Perigee/Apogeen/a Molniya type?TXA#R&Inclinationn/aOA#RPeriodn/ajXM#j:" &ЛLaunch vehicleSTS 53$5" 8m1 mBUSA 101D55 : S" USA 101]m7) " Also called P90-5 or TAOS (Technology for Autonomous Operations Survivability) or Step 01 h'  Generalg 7G#^@") Designation23030 / 94017A\h+A#R6Launch date13 Mar 1994t'M#jN"N ,㹌לCountry of originUnited Statesi"+G#^D"H̀MissionMilitary: technology^fA#R:"Perigee/Apogee556/568 kmUA#R(Inclination105TfA#R&Period95.9 minm |M#j@" &㻦ʼnLaunch vehicleTaurus 01ZA#R2"Mass at launch500 kg|' aOperated by USAF, built by TRW from an Eagle platformIt carries autonomous navigation systems and a GPS receiver, in an attempt to reduce the need for ground controllers.<' * External resourcesY2B' dhttp://www.plk.af.mil/PLhome/SUCCESS/taos.html8z1\O z USA 102DB5 : S" USA 102:z# .Also called Darpasat1 ) '  Generalg  G#^@") Designation23031 / 94017B\) A#R6Launch date13 Mar 1994t' ` M#jN"N ,㹌לCountry of originUnited Statesi" G#^D"H̀MissionMilitary: technology`` ) A#R>"Perigee/Apogee550/550 km ?W A#R,Inclination105 ?V) A#R*Period95.9 min ?m C M#j@" &㻦ʼnLaunch vehicleTaurus 01^ D#X4"Mass at launch240 kgH$C $ HOperated by DARPA, built by Ball8 ! 14 ! e AUSA 103D e 5 : S" USA 103;! # 0Also called Trumpet 11 e '  Generalg 8G#^@") Designation23097 / 94026A[ A#R4Launch date3 May 1994t'8M#jN"N ,㹌לCountry of originUnited Stateso(vG#^P"H̀MissionMilitary: SIGINT (Trumpet)a A#R@"Perigee/Apogee1323/39034 kmVv9@A#R*9@ Inclination64.4U@A#R(Period717.9 mink9@@M#j<" &^]Launch vehicleTitan 4$@A" 8@UA1rOm UAADUSA 105DAA5 : S" USA 105<UAA# 2Also called Jeroboam 11 AB'  Generalg AmBG#^@") Designation23223 / 94054A\BBA#R6Launch date27 Aug 1994t'mB=CM#jN"N ,㹌לCountry of originUnited Statesq*BCG#^T"H̀MissionMilitary: SIGINT? (Jeroboam)V=CDA#R* Geostationaryn/akCoDM#j<" &^]Launch vehicleTitan 4kGDD$ Would feature a 150 m diameter antenna, built by Boeing and 4500 kg8oDE1x4 EVEHUSA 110DDVE5 : S" USA 110<EE# 2Also called Jeroboam 21 VEE'  Generalg E*FG#^@") Designation23567 / 95022A\EFA#R6Launch date14 May 1995t'*FFM#jN"N ,㹌לCountry of originUnited Statesq*FkGG#^T"H̀MissionMilitary: SIGINT? (Jeroboam)\FGA#R6,Geostationary orbitn/akkG2HM#j<" &^]Launch vehicleTitan 4kGGH$ Would feature a 150 m diameter antenna, built by Boeing and 4500 kg82HH1mɃ HILUSA 112DHI5 : S" USA 112;HTI# 0Also called Trumpet 21 II'  Generalg TIIG#^@") Designation23609 / 95034A\IHJA#R6Launch date10 Jul 1995t'IJM#jN"N ,㹌לCountry of originUnited Stateso(HJ+KG#^P"H̀MissionMilitary: SIGINT (Trumpet)`JKA#R>"Perigee/ApogeeMolniya-likeT+KKA#R&Inclinationn/aOK.LA#RPeriodn/akKLM#j<" &^]Launch vehicleTitan 4&.LL# 8LL1% L;M;USA 118DL;M5 : S" USA 1181 LlM'  Generalg ;MMG#^@") Designation23855 / 96026A\lM/NA#R6Launch date24 Apr 1996t'MNM#jN"N ,㹌לCountry of originUnited Statesp)/NOG#^R"H̀MissionMilitary: SIGINT (Jeroboam)ZNmOA#R2,Geostationary orbit?o"OOM#jD" &^]Launch vehicleTitan 4 #16S/mO;$ ^O;LThe orbit and mission is only a supposition8Os1Ƀ sUSA 125D;5 : S" USA 1251 s'  Generalg OG#^@") Designation23945 / 96038A[A#R4Launch date3 Jul 1996t'OM#jN"N ,㹌לCountry of originUnited States^|G#^."H̀MissionMilitary:a ݂A#R@"Perigee/ApogeeMolniya-like?T|1A#R&Inclinationn/aO݂A#RPeriodn/ao"1M#jD" &^]Launch vehicleTitan 4 #18&# 8M1!^ MUSA 136D5 : S" USA 136;M̄# 0Also called Trumpet 31 '  Generalg ̄dG#^@") Designation25034 / 97068A[A#R4Launch date8 Nov 1997t'd3M#jN"N ,㹌לCountry of originUnited Stateso(G#^P"H̀MissionMilitary: SIGINT (Trumpet)p/3A#R^"Perigee/Apogee1100/39059 km (Molniya-like)VhA#R*Inclination63.6L A#RPeriodo"h#M#jD" &^]Launch vehicleTitan 4 #23^:$ tHas a 100 m diameter antenna. Should weigh 5 to 6 tons8#1] )USA 137D5 : S" USA 137;8# 0Also called Capricorn1 i'  Generalg 8ЉG#^@") Designation25148 / 98005A\i,A#R6Launch date29 Jan 1998t'ЉM#jN"N ,㹌לCountry of originUnited States_,G#^0"H̀MissionMilitary: TSA#R&"Perigee/ApogeeTA#R&Inclination63L SA#RPeriodq$dM#jH" &yjLaunch vehicleAtlas 2A #113)' =It may be a follow-on to the SDS communications data relay satellites used to pass on spy satellite imaging data, and may also have either infrared missile warning or signals intelligence secondary payloads aboard. Another theory is that it may be the COBRA BRASS payload for infrared early warning satellite technology development, which was announced as due to fly this year.Cost: estimated at $250 million8da1q^ aUSA 139D)5 : S" USA 139<a# 2Also called Jeroboam 31 '  Generalg yG#^@") Designation25336 / 98029A[ԏA#R4Launch date9 May 1998t'yTM#jN"ԏT)N ,㹌לCountry of originUnited Statesq*ԏG#^T"H̀MissionMilitary: SIGINT? (Jeroboam)\T!A#R6,Geostationary orbitn/akM#j<" &^]Launch vehicleTitan 4M#!* $F5i뉂Would be identical to USA 11091+ TNV-StreamBT, (." Program: V-streamN( Telecommunication program planned by Panamsat. It would be made of 12 satellites operating in V-band (50/40 GHz). 3 GHz bandwidth per satellite. Planned in the 2000sEach satellite would have high power spots, on-board processing and capable of inter-satellite linksPanAmSat has requested FCC authorization to operate the global V-band network in 11 orbital slots, ranging from 99W for service over North America to 124.5E for service over the Asia-Pacific. 1T1W T+N) "VȠ$To view this page you need to register&# B;1N ;HProgram: VanguardN5 :4 &" Program: Vanguard;H* "+kQRAmerican experimental program. Eleven satellites where built but only 3 were successfully launched. See the Vanguard launch vehicle for details.1y1 y>HA R|u߀kkkProgram: VanguardVanguard 1Vanguard 2Vanguard 3; y31H 3zGVanguard 1Gz5 :& &" Vanguard 1<3# 2Also called grapefruit1 z'  Generalg NG#^@") Designation00005 / 58002B\A#R6Launch date17 Mar 1958t'NM#jN"N ,㹌לCountry of originUnited States~1M#jb"H߲̀-MissionScientific: high atmosphere study_A#R<"Perigee/Apogee656/3866 kmVQA#R*Inclination34.3UA#R(Period133.2 mino"QM#jD" &kQRLaunch vehicleVanguard #3_tA#R<Launch siteCape Canaveral[A#R4"Mass at launch1.47 kgxTtG$ Sphere of 16 cm diameter. Carries a temperature sounder and a radio transmitter.; 1  Vanguard 2GG5 :& &" Vanguard 21 '  Generalg aG#^@") Designation00011 / 59001A\A#R6Launch date17 Feb 1959t'a1M#jN"N ,㹌לCountry of originUnited States~1M#jb"H߲̀-MissionScientific: high atmosphere study_1A#R<"Perigee/Apogee559/3047 kmVdA#R*Inclination32.9UA#R(Period122.7 mino"d4M#jD" &kQ4GRLaunch vehicleVanguard #8_A#R<Launch siteCape Canaveral$4" ; 1H 9Vanguard 3G95 :& &" Vanguard 31 j'  Generalg 9G#^@") Designation00020 / 59007A\j-A#R6Launch date18 Sep 1959t'M#jN"N ,㹌לCountry of originUnited Statesr%-M#jJ"H̀jMissionScientific: Sun study_rA#R<"Perigee/Apogee512/3412 kmVA#R*Inclination33.3UrA#R(Period126.3 minp#M#jF" &kQRLaunch vehicleVanguard #11_A#R<Launch siteCape Canaveral$" > N1 NProgram: Vela5 , (" Vela{XN# American satellites to check the 1963 Moscow treaty: no atmospheric atomic explosions751 NB 5l>AViking7 l, (" Viking1 5'  Generalg lG#^@") Designation16614 / 86019B\`A#R6Launch date22 Feb 1986m M#j@"N ,ˆtCountry of originSwedena `.A#R@OperatorSwedish Space Corp.@S#v"H̀(?vd;plMissionScientific: ionosphere and magnetosphere study`.! A#R>"Perigee/Apogee818/13521 kmVw A#R*Inclination98.8U! A#R(Period261.6 minn!w : M#jB" &C+Launch vehicleAriane 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: $18 million<: k ' *O External resourcesX1/ ' bhttp://nis-www.lanl.gov/~mgh/viking_desc.html8k ' "(OTechnical data8 3 ' " Specifications` A#R>&Prime contractorSaab SpaceZ3 A#R2"Mass at launch538 kgW D A#R,Payload mass60 kgS A#R$Diameter1.9 mQD A#R Height0.5 mR :A#R"DC power80 Wk* A#RT Stabilizationmagneto-torquers (3 rpm)]:A#R8$Design lifetime8 months&(# 1 Y'  Payload(@% 2 UV imagers & instruments to measure electric and magnetic fields, charged particles, and wave/particle interaction in the magneY@tosphereZYq@A#R2"Telemetry/dataS-bandV@@A#R*Data rate55 kbpsSq@AA#R$RF power2.5 W$@>A" DAA1 M AAhNProgram: VisionstarD>AA, (2" Program: Visionstar6AC& !To operate a Ka-band GEO system. Licence granted by the FCC in May 1997.It should provide nationwide video programming in the US: over 100 national television channels plus regional and local programming. CelluarVision's Local Multipoint Distribution Service ("LMDS") system is to be used. It also proposes a broadband infrastructure offering distance learning, high-speed Internet services, interactive data and e-mail and video conferencing abilities. VisionStar proposes to offer services on a non-common carrier basis.T0APD$ `The cost is expected to reach $207.5 million1 CD' O Contact?PDD% 4Visionstar IncNew York1 DD'  GeneralYDJEG#^$") Designation`DEA#R>Launch datebefore May 2002t'JEFM#jN"N ,㹌לCountry of originUnited Stateso"EFM#jD"H̀‰MissionTelecommunications^FFA#R:,Geostationary orbit113W\FGGG#^*" &Launch vehicleYFGG#^$Launch site&GGG# 8GG' "(OTechnical data8G6H' " SpecificationsVGHA#R*&Prime contractorN 6HHA#RPlatformTH.IA#R&"Mass at launchSHIA#R$ Mass in orbitO.IIA#RDimensionQI!JA#R Solar arraySItJA#R$ StabilizationN !JJA#RDC powerUtJKA#R($Design lifetime&J=K# 1 KnK'  Ka-bandY=KKA#R0(Main transponders48YnK LA#R0,Backup transpondersUKuLA#R(Power60 or 90 WU LLA#R(Bandwidth40 MHzN uLMA#RCoverageJ LbMA#REIRPRMMA#R"PolarizationLbMBNB#TFrequenciesUplink: 28.35-28.6 and 29.25-30 GHz Downlink: 19.7-20.2 GHz&MhN# 1BNN1W NNOT+hNN) "VȠ$To view this page you need to register&NO# ANTO1B TOOProgram: VitasatAOO, (," Program: Vitasat2TO!N jeΓF̉ϓF̉VRaߎ؉BVolunteers in Technical AssiO!OstanceVITA is a non-profit private organization which uses LEO satellites for communications. In the past they have used Uosat 2, Uosat 3 and Posat. Now they use their own satellite payload: Vitasat 1R which replaces the Vitasat payload.VITA holds an FCC licence for its communications.VITA plans to setup a consortium with other LEO satellite operators. SatelLife (Healthsat) and Posat have agreed to join in. The consortium will operate a global email system dedicated to humanitarian and development purposes. 1 OR' O Contactn!' VITA1600 Wilson Boulevard (Suite 500), Arlington, VA 22209, USATel: +1-703-276-1800Fax: +1-703-243-1865<R#' *O External resources?b' 0http://www.vita.org/&## @bȃ1TM ȃ7Program: VortexL5 :0$ڀ" Program: Vortex^ȃ% Also called ChaletAmerican geostationary SIGINT satellites. Equipped with a 38 m antenna.<ӄ' *O External resourcesd=7' zhttp://www.fas.org/spp/military/program/sigint/chalet.htm1ӄh1 hW7V |9%>>>>>>Program: VortexVortex 1Vortex 2Vortex 3Vortex 4Vortex 5Vortex 69hN1 NPVortex 1E5 :"$ڀ" Vortex 11 NĆ'  Generalg +G#^@") Designation10941 / 78058A\ĆA#R6Launch date10 Jun 1978t'+M#jN"N ,㹌לCountry of originUnited Statese`G#^<"H̀MissionMilitary: SIGINT\A#R6,Geostationary orbitn/ap#`,M#jF" &^]Launch vehicleTitan 3 #111$P" 9,1| ΉVortex 2EPΉ5 :"$ڀ" Vortex 21 '  Generalg ΉfG#^@") Designation11558 / 79086A[A#R4Launch date1 Oct 1979t'f5M#jN"N ,㹌לCountry of originUnited StateseG#^<"H̀MissionMilitary: SIGINT\5A#R6,Geostationary orbitn/ap#fM#jF" &^]Launch vehicleTitan 3 #118$" 9fÌ1W ÌŏVortex 3E5 :"$ڀ" Vortex 31 Ì9'  Generalg G#^@") Designation12930 / 81107A\9A#R6Launch date31 Oct 1981t'pM#jN"N ,㹌לCountry of originUnited StateseՎG#^<"H̀MissionMilitary: SIGINT\p1A#R6,Geostationary orbitn/ap#ՎM#jF" &^]Launch vehicleTitan 3 #127$1ŏ" 9 1|ۀ QVortex 4ŏ ŏEŏQ5 :"$ڀ" Vortex 41 '  Generalg QG#^@") Designation14675 / 84009A\EA#R6Launch date31 Jan 1984t'M#jN"N ,㹌לCountry of originUnited StateseEG#^<"H̀MissionMilitary: SIGINT\zA#R6,Geostationary orbitn/ap#M#jF" &^]Launch vehicleTitan 3 #136$z" 9G1QW GVortex 5E5 :"$ڀ" Vortex 59G# ,Also called USA 0311 '  Generalg ]G#^@") Designation19458 / 88077A[A#R4Launch date2 Sep 1988t'],M#jN"N ,㹌לCountry of originUnited StateseG#^<"H̀MissionMilitary: SIGINT\,A#R6,Geostationary orbitn/ap#]M#jF" &^]Launch vehicleTitan 3 #149O+$ VThe second burn of the transtage failed9]1'ۀ * Vortex 6E*5 :"$ڀ" Vortex 69c# ,Also called USA 0371 *'  Generalg cG#^@") Designation19976 / 89035A\WA#R6Launch date10 May 1989t'M#jN"N ,㹌לCountry of originUnited StateseW0G#^<"H̀MissionMilitary: SIGINT\A#R6,Geostationary orbitn/ap#0M#jF" &^]Launch vehicleTitan 3 #151$ " 9Y1  YWebersatA 2 4 "  WebersatY0Y) "`䵟Also called Microsat 3 or WO-18 or Oscar 181 $'  Generalg G#^@") Designation20441 / 90005F\$A#R6Launch date22 Jan 1990t'[M#jN"N ,㹌לCountry of originUnited Stateso"M#jD"H̀㓉MissionTelecommunications^[(A#R:"Perigee/Apogee780/797 kmV~A#R*Inclination98.6U(A#R(Period100.6 minn!~AM#jB" &6D+Launch vehicleAriane V35}Y$ Designed at Weber State College (Ogden, Utah, USA), based on an Amsat-NA Microsat bus<A' *O External resources]6W' lhttp://www.amsat.org/amsat/sats/nk6k/msatmain.html8' "(Technical dataKW(B#TUplink1200 bps Manchester coded (Biphase-L) ( FSK (FM) AX.25145.900 MHzt2B#TdNTSC modulated ATV (not in use?)1265.000 MHz&(# D#VDownlink1200 bps BPSK (SSB) AX.25, either one of the two frequencies below:437.075 MHz (LHCP in northern hemisphere), normal unfiltered PSK437.102 MHz (RHCP in northern hemisphere), Raised Cosine modulation$" > =1 ={Program: West>{, (&" Program: WestZ=. *hOUWideband European Satellite TelecommunicationsProgram for a global satellite infrastructure, made of one or several GEO satellites and 9 MEO satellites. It is proposed to use Ka-band. It complements the East project.MMS which plans to be the prime contractor for the project is looking for investors to become the operator of the system.1{41W 4T+) "VȠ$To view this page you need to register&4# @1  :Program: WestarL:5 :0Ag" Program: Westarg# American telecommunication program operated by the Western Union Telegraph and since 1988 by Hughes.1:1 WV |`//////Program: WestarWestar 1Westar 2Westar 3Westar 4Westar 5Westar 611U  F## FWestar 1, 2 & 3's specificationsZsA#R20"Mass at launch572 kgYA#R00 Mass in orbit208 kgN sA#R0DiameterL fA#R0Heightb!A#RB0 StabilizationSpin stabilizedN f A#R0DC power\r A#R60$Design lifetime7 yearsb! A#RB0Capacity14400 phone circuits$r " 1 ) 1U ) > g # 6Westar 1, 2 & 3's C-bandY) A#R00(Main transponders12Yg  A#R00,Backup transpondersK d A#R0PowerU A#R(0Bandwidth36 MHzN d  A#R0CoverageT [ A#R&0EIRP max33 dBWR A#R"0Polarization$[ " 1  1U  @@F# H # FWestar 4, 5 & 6's specifications\ A#R60&Prime contractorHughesTH A#R&0PlatformHS-376[ SA#R40"Mass at launch1100 kgY A#R00 Mass in orbit585 kgTSA#R&0Diameter2.16 mZZA#R20Height6.6 m deployedb!A#RB0 StabilizationSpin stabilizedd"Z,@B#TD0D,@ C powerBOL: 820 WEOL: 700 W]@A#R80$Design lifetime10 years$,@@" 1@@1U @nCC>@A# 6Westar 4, 5 & 6's C-bandY@uAA#R00(Main transponders24YAAA#R00,Backup transpondersWuA%BA#R,0Power7.5 W (TWTA)UAzBA#R(0Bandwidth36 MHzN %BBA#R0CoverageTzBCA#R&0EIRP max34 dBWRBnCA#R"0Polarization$CC" 9nCC1 CDrHWestar 1ECD5 :"Ag" Westar 11 CAD'  Generalg DDG#^@") Designation07250 / 74022A\ADEA#R6Launch date13 Apr 1974t'DxEM#jN"N ,㹌לCountry of originUnited Stateso"EEM#jD"H̀‰MissionTelecommunications]xEDFA#R8,Geostationary orbit99Ws&EFM#jL" &p㉂Launch vehicleThor Delta #101_DFGA#R<Launch siteCape Canaveral&F'  End of lifeW A#R,"Out of serviceyes&># 8' "(Technical dataL?0 08pՉSpecificationsC-band9x1s# x$Westar 4E?5 :"Ag" Westar 41 x'  Generalg UG#^@") Designation13069 / 82014A\A#R6Launch date26 Feb 1982t'U%M#jN"N ,㹌לCountry of originUnited Stateso"M#jD"H̀‰MissionTelecommunications]%A#R8,Geostationary orbit99Ws&dM#jL" &p㉂Launch vehicleThor Delta #160_ÅA#R<Launch siteCape Canaveral&d# 5Å'  End of life\zA#R6"Out of serviceNov 1991&# 8z؆' "(Technical dataL$0 08rhՉSpecificationsC-band9؆]1S$ ] Westar 5E$5 :"Ag" Westar 51 ]Ӈ'  Generalg :G#^@") Designation13269 / 82058A[ӇA#R4Launch date9 Jun 1982t': M#jN"N ,㹌לCountry of originUnited Stateso"xM#jD"H̀‰MissionTelecommunications` ؉A#R>,Geostationary orbit122.5Ws&xKM#jL" &p㉂Launch vehicleThor Delta #162_؉A#R<Launch siteCape Canaveral&KЊ# 5'  End of life\ЊaA#R6"Out of serviceMay 1992&# 8a' "(Technical dataL 0 08rhՉSpecificationsC-band9D1% DXWestar 6E 5 :"Ag" Westar 61 D'  Generalg !G#^@") Designation14688 / 84011B[|A#R4Launch date3 Feb 1984t'!M#jN"N ,㹌לCountry of originUnited Stateso"|_M#jD"H̀‰MissionTelecommunications\A#R6,Geostationary orbitn/aj_%M#j:" &"Launch vehicleSTS 11c0 0*kPlaced on a bad orbit, it was retrieved on 16 Nov 1984 by STS 19. It then became Asiasat 1.8% ' "(Technical data LX0 08rhՉSpecificationsC-band: 1& NDial-Wika:X, (" Dial-Wika= # 4Wissenschaftlich Kapsel1 :'  Generalg G#^@") Designation04344 / 70017A\:A#R6Launch date10 Mar 1970n!kM#jB"N , Country of originGermany~1M#jb"H߲̀-MissionScientific: high atmosphere study_kHA#R<"Perigee/Apogee301/1631 kmUA#R(Inclination5.4UHA#R(Period104.2 minn!`M#jB" &A͉Launch vehicleDiamant #5@$ 8First launch from Kourou5`'  End of lifeU*A#R(Decay5 Oct 1978$N" 7*1' xWind 17 N, (" Wind 11 '  Generalg TG#^@") Designation23333 / 94071Ag&A#RLLaunch date1 Nov 1994 at 09:31 UTt'T/M#jN"N ,㹌לCountry of originUnited States?A#R~OperatorNASA (part of the Global Geospace Science program)u(/$M#jP"H̀jMissionScientific: study of SunW{A#R,"Perigee/Apogeen/aT$A#R&Inclinationn/aO{A#RPeriodn/ap#M#jF" &p㉂Launch vehicleDelta 2 #227[A#R4"Mass at launch1200 kg/ ,mQVCost: $173 million, Launched under the MELVS contractWind is a spacecraft in the International Solar-Terrestrial Program (ISTP). It carried instruments to measure the solar wind plasma and magnetic field, besides several instruments to measure very energetic particles and gamma rays. Operates together with PolarAfter several orbits extending to close proximity of the Moon (at about 60 Earth-radii) and involving several thrust-firings during that phase, the spacecraft will eventually reach the first Lagrangian point (L-1) located at about 275 Earth-radii in the Sun-ward direction and orbit around that point. Orbital parameters are very variable even during the first two years.L($ PBuilt by Martin Marietta Astra Space<V' *O External resourcesV/' ^http://ggsfot.gsfc.nasa.gov/words/wind.html8V' "(OTechnical datapx$ Telemetry: 2275.5 MHz (realtime: 5.56 kbps, playback: 32 or 64 kbps)Command: 2094.9 MHz (realtime: 250 kbps)51 ( = WIRE5 x, (" WIREN+0# VAlso called Wide-Field Infrared Explorer1 a'  GeneralY0G#^$") Designatione$a+A#RHLaun+xch dateplanned in late-1998t'M#jN"N ,㹌לCountry of originUnited Statesu(+M#jP"H̀_BMissionScientific: IR astronomy^rA#R:"Perigee/Apogee440/520 kmVA#R*Inclination97.2L rA#RPeriodn!M#jB" &GKTLaunch vehiclePegasus XLQA#R Launch siteqo+ $v>UUWIRE will use a single cryogenically cooled infrared telescope to survey selected target areas in two infrared bands. WIRE is specifically designed to detect the maximum number of high-red shift starburst galaxies using the smallest, simplest instrument possible. The WIRE survey will be over 500 times fainter than the IRAS Faint Source Survey at 12 and 25 m.<' *O External resources}Oo(. ,http://sunland.gsfc.nasa.gov/smex/wire/http://www.ipac.caltech.edu/wire/8`' "(OTechnical data8(' " SpecificationsV`A#R*&Prime contractorN <A#RPlatformZA#R2"Mass at launch250 kgS<A#R$ Mass in orbitO8A#RDimensionQA#R Solar arrayS8A#R$ StabilizationS/A#R$DC power160 W]A#R8$Design lifetime4 months/= ( Telemetry: 2215 MHz (realtime: 23.4375 kbpsn playback: 1.125 or 2.25 Mbps)Command: 2039.65 MHz (2 kbps)Telescope: 30 cm Cassegrain1n 1W) n T+= ) "VȠ$To view this page you need to register&n # B * 1* * y ^ Program: WordstarO y 5 :6$eT" Program: Worldstar!* , &'䉂American program operated by Worldspace to reach the third World with digital radio sent by 3 satelllites. The satellites will be constructed by a consortium led by Alcatel Espace and launched from 1998 on. They will use L-band in DAB mode. The control center will be located in Toulouse, France.The Digital Audio Broadcasting service will transmit to a new generation of receiver called Starman, which will have a satellite antenna the size of a business card. It's been developed by Motorola.y ^ % ?A fourth satellite was ordered in May 1998 from Alcatel for $57.3 million. Should be used as ground spare for the moment (will be delivered in early 2000).1 1W+ T+^ ) "VȠ$To view this page you need to register& # 1 :1, :{: A Rtu-SHgRPO}Program: WorldstarAfristarAsiastarCaribstar1:1W- :`T+:) "VȠ$To view this page you need to register&`# 1:1U. B C@`# :Worldstar's specificationsd#A@A#RFA@`&Prime contractorAlcatel Espace\@A#R6PlatformEurostar 2000+[A@@A#R4"Mass at launch2750 kgN @FAA#RDry massa @AA#R@Dimension2.6m x 1.8m x 2.3mQFAAA#R Solar arraySAKBA#R$ StabilizationTABA#R&DC power5100 W]KBBA#R8$Design lifetime12 years$B C" 1BQC1W/ QCCCT+ CC) "VȠ$To view this page you need to register&QCC# 1CC1t0 C?H8C4D# *Worldstar's L-bandYCDA#R0(Main transponders12Z4DDA#R2,Backup transponders6PD7EA#RPower150 Wb!DEA#RBBandwidth16 kbps per channelF7E!FB#TCoverageUplink: globalDownlink; 3 beams with 4 transponders eachVEwFA#R*EIRP max33.5 dBWh'!FFA#RN G/T-12.6 dB/K over the global beamKwFlGB#TFrequenciesUpload: 7.05 - 7.075 GHz (SCPC)Downlink: 1.467 - 1.492 GHzF?H) U288 channels (24 channels per transponder)a mono voice-only service requires 1 channela mono music service requires 2 channelsa stereo service requires 4 channels1lGpH1W1 pHHHT+?HH) "VȠ$To view this page you need to register&pHH# 7H!I1U=2 !IXI|MWresat7 HXI, (" Wresat1 !II'  Generalg XIIG#^@") Designation03054 / 67118A\ILJA#R6Launch date29 Nov 1967p#IJM#jF"N ,Country of originAustraliay2LJ5KG#^d"H̀MissionScientific: high atmosphere and sun?_JKA#R<"Perigee/Apogee198/1252 kmV5KKA#R*Inclination83.3TK>LA#R&Period99.3 mini"KLG#^D" &Launch vehicleRedstone (US)X>LLA#R.Launch siteWoomeraYLXMA#R0"Mass at launch50 kg$L|M" 6XMM1f3 MM%WSF 26 |MM, (" WSF 2:M"N# .Wake Shield Facility1 MSN'  Generalg "NNG#^@") Designation23669 / 95048Ch'SN"OA#RNLaunch date11 Sep 1995 at 11:25 UTt'NOM#jN"N ,㹌לCountry of originUnited Statesm&"OG#^L"H̀MissionScientific: MicrogravitO|MyZOiA#R2"Perigee/Apogee370 kmVA#R*Inclination28.4TiA#R&Period91.9 minj}M#j:" &Launch vehicleSTS 69gJ#d:$Mass at launch1979 kg}' The WSF Free Flyer generates an ultra-hard vacuum in its wake for production of semiconductors and other experiments. WSF is built and operated by the Space Vacuum Epitaxy Center in Houston.Was troubled by control problems and overheating. 56'  End of life_A#R<"Out of service14 Sep 1995l%6G#^JReentry18 Sep 1995 with STS 69$%" 4Y1=4 YJXMM4%, (" XMM8Yń# *X-ray Multi-Mirror1 '  GeneralYńOG#^$") Designationd#A#RFLaunch dateplanned in Dec 1999m O M#j@"N ,4"Country of originEuroper%M#jJ"H̀_BMissionScientific: astronomyb! A#RB"Perigee/Apogee7000/114000 kmTHA#R&Inclination60RA#R"Period2 dayslHM#j>" &2!Launch vehicleAriane 5QWA#R Launch siteqKȈ& ESA astronomy satellite worth DM 400 millionWill focus on black holes<W' *O External resourcesQ*ȈU' Thttp://astro.estec.esa.nl/XMM/xmm.html8' "(OTechnical data8Uʼn' " Specifications]"A#R8&Prime contractorDornierN ʼnpA#RPlatform]"͊A#R8"Mass at launch~ 4000 kgSp A#R$ Mass in orbitg&͊A#RLDimension10 m long x 4 m diameterQ ؋A#R Solar arrayS+A#R$ StabilizationN ؋yA#RDC power]+֌A#R8$Design lifetime10 yearstPyJ$ Will carry 3 telescopes of 70 cm diameter (with 58 overlapping mirrors each)1֌{1W5 {ύT+Jύ) "VȠ$To view this page you need to register&{# 4ύ)16 )]9 XTE4], (" XTE}T)ڎ) " X-ray Timing Explorer, Also called RXTE (Bruno B. Rossi X-ray Timing Explorer) 1 ] '  Generalg ڎrG#^@") Designation23757 / 95074Ae$ ׏A#RHLaunch date30 Dec 1995 13:48 UTt'rWM#jN"׏WN ,㹌לCountry of originUnited Statesx+׏M#jV"H̀_BMissionScientific: X-ray astronomy^W-A#R:"Perigee/Apogee565/583 kmTA#R&Inclination23T-A#R&Period96.1 minp#EM#jF" &p㉂Launch vehicleDelta 2 #230R+' WCost: $195 million, Launched under the MELVS contractDelta's new avionics system will use an array of redundant laser gyros and accelerometers to sense the vehicle's velocity and attitude movement, which includes its angular position and direction. The avionics system feeds data to onboard computers which control Delta 2's engines and power, engine start, main engine cutoff, staging and payload separation. The avionics system now has two power sources and is completely redundant. If one data system is lost, the other will complete the mission.<E' *O External resourcesQ*$' Thttp://heasarc.gsfc.nasa.gov/docs/xte/8\' "(OTechnical data8$' "O Specifications\y+ $u@ĘBuilt under coordination of NASA-Goddard Space Flight Center. It includes two high gain antennae, allowing an almost continuous telemetry stream using TDRS's Multiple Access mode. J#' FO Proportional Counter Array (PCE)R+y' WInstrument with large collecting area but low spatial resolution, for accurate timing and spectral measurements of bright X-ray sources. Built by the LHEA at GSFCThe PCA is an array of five proportional counters with a total collecting area of 6500 square cm. The instrumental properties are: ]rA#R8Energy range2 - 60 keV g&A#RL(Energy resolution&< 18% at 6 keV `r9A#R>$Time resolution1 microsec v5A#Rj*Spatial resolutioncollimator with 1 degree FWHM g&9A#RLDetectors5 proportional counters d#zA#RF$Collecting area6500 square cm LA#RLayers1 Propane veto; 3 Xenon, each split into two; 1 Xenon veto layer [zbA#R4Sensitivity0.1 mCrab XA#R.Background2 mCrab qbO$ Events detected by the PCA will be processed on board by the EDS before insertion into the telemetry stream. U.' \ High Energy X-ray Timing Experiment (HEXTE)gO0% Intrument built by CASS at UCSD which will study X-rays. HEXTE consists of two clusters each containing four phoswich scintillation counters. The clusters can rock at right angles to each other, with amplitudes of 1.5 or 3 degrees, to provide accurate background measurements. The total collecting area is 1600 square cm. The instrumental properties are: _A#R<Energy range20 - 250 keV h'0A#RN(Energy resolution&< 18% at 60 keV a XA#R@$Time resolution10 microsec v5A#Rj*Spatial resolutioncollimator with 1 degree FWHM p/XJA#R^JDetectors2 times 4 scintillation counters d#A#RF$Collecting area1600 square cm XJA#R.PhoswichNaI / CsI Z`A#R2Sensitivity10 mCrab ZA#R2Background100 mCrab `% Events detected by HEXTE will be processed on board by its own data system before insertion into the telemetry stream. It will allow event mode, histogram binned mode, multiscalar mode, PHA/PSA spectral mode, and burst mode formats. ? ' 0 All-Sky Monitor (ASM)#% ASM, built by the CSR at MIT, will spot X-ray flare stars and burst sources. It consists of three wide-angle shadow cameras equipped with proportional counters with a total collecting area of 90 square cm. The instrumental properties are: ] A#R8Energy range2 - 10 keV u4#A#Rh$Time resolution80% of the sky every 90 minutes a VA#R@*Spatial resolution3' x 15' ~=A#Rz6Number of shadow cameras3, each with 6 x 90 degrees FOV b!V6A#RB$Collecting area90 square cm }<A#RxDetectorXenon proportional counter, position-sensitive Z6 A#R2Sensitivity30 mCrab q$ Events detected by the ASM will be processed on board by the EDS before insertion into the telemetry stream. F ' >O Experiment Data System (EDS) , &The EDS consists of eight Event Analyzers (EA), of which two are dedicated to the PCA and six to the ASM. Each EA contains an Intel 80286 processor and associated memory. The EAs can be programmed independently to process incoming events from the instruments in any of the following modes: Transparent mode, using 1, 2, or 3 EAs Event mode, using 1 or 2 EAs Binned mode (time and/or energy) Burst catcher mode Fourier transform mode Pulsar fold mode Autocorrelation mode wRm % Arrival time differences histogram mode It is being built by the CSR at MIT. < ' *O Downlink frequencylm 9 $ Telemetry: 2287.5 MHz (realtime: 16/32 kbps, playback: upto 1024 kbps)Command: 2106.4 MHz (1/0.125 kbps)? x 1}O7 x LProgram: Yamal?9 , ((" Program: YamalBx ( 5Program of 2 Russian-built communication satellites operated by GasCom Corporation (Moscow). GasCom is a joint venture between RAO "Gazprom", the Russian natural gas monopoly, and RKK "Energia", the Russian aerospace company (design and operation of Mir).The first generation of satellites, called Yamal 100, are to be launched in 1997 by Proton. Slots reserved are: 19.5W and 75EA new generation called Yamal 200 is in preparation for 1999. They will use 28 C- and 16 Ku-band transponders with 35-40 and 54 dBW max respectively3 ,' (OYamal 1008 d' " Specifications|;,A#Rv&Prime contractorEnergia (payload: Space Systems/Loral)Wd7A#R,PlatformYamal 100[A#R4"Mass at launch1360 kgX7 @A#R.Payload mass315 kg @9 O[@A#RDimensionQ @@A#R Solar arrayS[@@A#R$ StabilizationT@SAA#R&DC power2200 W]@AA#R8$Design lifetime10 years&SAA# 0 AB'  C-bandWA]BA#R,(Main transpondersYBBA#R0,Backup transpondersK ]BCA#RPowerOBPCA#RBandwidthN CCA#RCoverageTPCCA#R&EIRP max40 dBWRCDDA#R"Polarization&CjD# 3 DDD' (OYamal 2008jDD' " Specifications|;DQEA#Rv&Prime contractorEnergia (payload: Space Systems/Loral)WDEA#R,PlatformYamal 200TQEEA#R&"Mass at launchRENFA#R"Payload massOEFA#RDimensionQNFFA#R Solar arraySFAGA#R$ StabilizationTFGA#R&DC power3140 W]AGGA#R8$Design lifetime12 yearsM)G?H$ R28 C-band or 16 Ku-band transponders 3 GrH' (OYamal 3008?HH' " Specifications|;rH&IA#Rv&Prime contractorEnergia (payload: Space Systems/Loral)WH}IA#R,PlatformYamal 200[&IIA#R4"Mass at launch2600 kgR}I*JA#R"Payload massOIyJA#RDimensionQ*JJA#R Solar arraySyJKA#R$ StabilizationUJrKA#R(DC power10000 W]KKA#R8$Design lifetime15 yearsM)rKL$ R28 C-band or 24 Ku-band transponders 1KML1W8 MLLLT+LL) "VȠ$To view this page you need to register&MLL# 4LL1 9 L/M3YES4L/M, (" YES@LoM# :Young Engineers' Satellite1 /MM'  Generalg oMNG#^@") Designation25025 / 97066C\McNA#R6Launch date30 Oct 1997m NNM#j@"N ,4"Country of originEurope_cN/OG#^0"H̀MissionTechnology`NOA#R>"Perigee/Apogee545/26626 kmU/O A#R(Inclination7.7O LSO_A#R$Period468 mino" ΀M#jD" &xg&\Launch vehicleAriane V101>_ - (#tYWas released by Maqsat H.Built by Delft University of Technology. YES is a sub-satellite to study the dynamics of tethered satellites. It was designed, assembled and integrated in record time by young graduates and students at ESTEC. A GPS receiver is installed to evaluate the use of GPS for navigation, especially above the GPS satellite constellation. YES also contains technology validation experiments which will measure radiation, the solar angle and acceleration in autonomous mode, after separation from MAQSAT-H.|΀$ Originally it should have been tether-attached (20 km), but this was not possible to minimize collision and debris risk.< ' *O External resourcesK$3' Hhttp://www.estec.esa.nl/teamsat/> q1Om: q!Program: YuriJ35 :,G" Program: Yuriq& GMeans "tiger lily", also called BS (Broadcast Satellite)Japanese telecommunication program operated by Telecommunication Satellite Corporation of Japan (TSCJ)<' *O External resourcesa:!' thttp://yyy.tksc.nasda.go.jp/Home/This/This-e/bs_e.html1R1; Rb!d O·㉂㉂㉂㉂㉂㉂ ㉂Program: YuriYuri 1Yuri 2AYuri 2BYuri 2XYuri 3AYuri 3BYuri 3HYuri 3N1RI1U< Ip=# 4Yuri 2's specificationsq0IA#R`0&Prime contractorToshiba with GE Astro SpaceULA#R(0PlatformGE 3000[A#R40"Mass at launch1290 kgYLA#R00 Mass in orbit760 kgb!bA#RB0Dimension1.2 x 1.32 x 2.89 mYA#R00 Stabilization3 axisYbA#R00DC powerBOL: 1400 W\pA#R60$Design lifetime5 years$" 1pŊ1U= ŊMq6# &Yuri 2's Ku-bandXŊSA#R.0(Main transponders2ZA#R20,Backup transponders1WSA#R,0Power100 W (TWTA)UYA#R(0Bandwidth27 MHzN A#R0CoverageTYA#R&0EIRP max54 dBWRMA#R"0Polarization$q" 1M1U> .R=qߍ# 4Yuri 3's specificationsm,LA#RX0&Prime contractorNEC with GE Astro SpaceUߍA#R(0PlatformGE 3000[LA#R40"Mass at launch1115 kgYUA#R00 Mass in orbit550 kgc"A#RD0Dimension1.63 x 1.32 x 0.99 m\U A#R60Solar qarray14.3 m spanYyA#R00 Stabilization3 axisY A#R00DC powerBOL: 1443 W\y.A#R60$Design lifetime7 years$R" 1.1U? /6R# &Yuri 3's Ku-bandXA#R.0(Main transponders3ZkA#R20,Backup transponders3WA#R,0Power120 W (TWTA)UkA#R(0Bandwidth27 MHzN eA#R0CoverageTA#R&0EIRP max54 dBWRe A#R"0Polarization$/" 7 f1jK@ fYuri 1C/5 :G" Yuri 16f# &Also called BS E1 '  Generalg wG#^@") Designation10792 / 78039A[A#R4Launch date7 Apr 1978lw>M#j>"N ,bCountry of originJapano"M#jD"H̀‰MissionTelecommunications^> A#R:,Geostationary orbit110Es&~M#jL" &p㉂Launch vehicleThor Delta #140_ A#R<Launch siteCape CanaveralL'~)% NBus: Toshiba/GE SatcomOwner: NASDA5^'  End of life`)A#R>"Out of serviceJanuary 1982$^" 81A ^Yuri 2AD^5 : G" Yuri 2A7# (Also called BS 2A1 ^'  Generalg -G#^@") Designation14659 / 84005A\A#R6Launch date23 Jan 1984l-M#j>"N ,bCountry of originJapano"dM#jD"H̀‰MissionTelecommunications^A#R:,Geostationary orbit110Efd(M#j2" &JLaunch vehicleN2d?% ~Suffered from in-orbit equipment failuresOwner: NASDA/TSCJ5('  End of lifeWA#R,"Out of serviceyes&># 8v' "(Technical dataM>0 0:񝉀VSpecificationsKu-band8v1KB ?Yuri 2BD?5 : G" Yuri 2B7v# (Also called BS 2B1 ?'  Generalg vG#^@") Designation16597 / 86016A\jA#R6Launch date12 Feb 1986lM#j>"N ,bCountry of originJapano"jQM#jD"QH̀‰MissionTelecommunications^A#R:,Geostationary orbit110EfQM#j2" &JLaunch vehicleN29N$ *Owner: NASDA/TSCJ5'  End of lifeWNA#R,"Out of serviceyes&# 88' "(Technical dataS2 4񝉀VSpecificationsKu-band2 out of 3 transponders failed 3 months after launch881C 9&Yuri 2XD95 : G" Yuri 2X7p# (Also called BS 2X59'  End of life_pA#R<"Out of service23 Feb 1990k$oG#^H7D+CauseExplosed with Ariane V362$ Owner: NHK8o' "(Technical dataM&0 0:񝉀VSpecificationsKu-band8^1R4D ^ Yuri 3AD&5 : G" Yuri 3A7^# (Also called BS 3A1  '  Generalg qG#^@") Designation20771 / 90077A\ A#R6Launch date28 Aug 1990lq9M#j>"N ,bCountry of originJapano"M#jD"H̀‰MissionTelecommunicationsf9G#^>"/ۀ0Geostationary orbit110EftM#j2" &JLaunch vehicleH1> , &= ㉂Started having stability problems in Sep 1995 with a peak in November. Traffic had to be taken over by Yuri 3N which is less powerful.Owner: NASDA/TSCJ8tv ' "(Technical dataM> 0 0:O҉sҍVSpecificationsKu-band8v 1*;E ? 8Yuri 3HD ? 5 : G" Yuri 3H7 v # (Also called BS 3H1 ? '  General\v  A#R6Launch date19 Apr 1991l o M#j>"N ,bCountry of originJapano" M#jD"H̀‰MissionTelecommunicationsdo B G#^:"/ۀ0Geostationary orbitn/av) M#jR" &!{Launch vehicleAtlas Centaur #0702B $ Owner: NHK5  '  End of life_ ~ A#R<"Out of service19 Apr 1991Y A#R0CauseLaunch failure~ % oThis satellite was a replacement for the Yuri 2X spacecraft which failed and was in turn a replacement for Yuri 2A spacecraft in orbit which had been suffering equipment failures.8 ' "(Technical dataM80 0:O҉sҍVSpecificationsKu-band8p14F peCYuri 3BD85 : G" Yuri 3B7p @# (Also called BS 3B @81 =@'  Generalg @@G#^@") Designation21668 / 91060A\=@AA#R6Launch date25 Aug 1991l@lAM#j>"N ,bCountry of originJapano"AAM#jD"H̀‰MissionTelecommunicationsflAABG#^>"/ۀ0Geostationary orbit110EfABM#j2" &JLaunch vehicleH19ABB$ *Owner: NASDA/TSCJ8BC' "(Technical dataMBeC0 0:O҉sҍVSpecificationsKu-band8CC1N;G CCGYuri 3NDeCC5 : G" Yuri 3N7CD# (Also called BS 3N1 CID'  Generalg DDG#^@") Designation23176 / 94040B[ID EA#R4Launch date8 Jul 1994lDwEM#j>"N ,bCountry of originJapano" EEM#jD"H̀‰MissionTelecommunicationsfwELFG#^>"/ۀ0Geostationary orbit110En!EFM#jB" &D+Launch vehicleAriane V65_LFGD#X6"Mass at launch1210 kg6FOG$ $Owner: NHK/JSB8GG' "(Technical datawEOGG2 4O҉sҍVSpecificationsKu-bandEquipped with a Star 30BP apogee motor5G3H11 H 3HhHeZeya5 GhH, (" ZeyaD!3HH# BAlso called Mozhaets and RS 161 hHH'  Generalg HDIG#^@") Designation24744 / 97010A[HIA#R4Launch date4 Mar 1997jDI JM#j:"N , Country of originCISp#IyJM#jF"H̀CV$MissionScientific: Geodesy` JJA#R>"Perigee/Apogee467 / 480 kmVyJ/KA#R*Inclination97.3RJKA#R"Period94 minn!/KKM#jB" &aKLaunch vehicleStart 1 #3&KL# <KQL' *O External resourcesY2LL' dhttp://www.users.wineasy.se/svengrahn/zeya.htm8QLL' "(OTechnical data8LM' " Specifications\LvMA#R6&Prime contractorNPO-PMi(MMA#RPPlatformpossibly based on Strela 1MYvM8NA#R0"Mass at launch87 kgSMNA#R$ Mass in orbitO8NNA#RDimensionQN+OA#R Solar arraySN~OA#R$ StabilizationN +OOA#RDC powerU~O-A#R(O-G$Design lifetimeO$3 4SThe satellite was designed by the students of the Mozhaiskiy military space engineering academy, in Saint PetersburgCarries 20 laser reflectors for geodesy and Glonass and GPS receivers.>-b' . Transponders (RS-16)A$D#XBeacons29.408 MHz29.451 MHz435.504 MHz (1.6 W)435.548 MHzFb-A#R a A#R@Uplink145.915 - 145.948 MHzF-ԂA#R g&;A#RLDownlink29.415 - 29.448 MHz (4 W)*Ԃe%  @;1b.dI Program: CosmosLe5 :0" Program: Cosmoss# Soviet denomination for satellites part of plenty of different programs. Some have a specific fact sheet in TSE:6'  Sub programscp /{!&!ְᇏ㼨ԟd퉂< 剂BionEorsatGeizerGeo-IKGlonassGonetsLuchParusRorsatStrelaTsikada< ̅1J ̅ˊCosmos 0001H5 :(qi" Cosmos 0001<̅P# 2Also called Sputnik 111 '  Generalg PG#^@") Designation00266 / 62008A\DA#R6Launch date16 Mar 1962jM#j:"N , Country of originCISy,D'M#jX"H̀?vMissionScientific: ionosphere study^A#R:"Perigee/Apogee207/649 kmT'وA#R&Inclination49T-A#R&Period93.1 minlوM#j>" &r,梉Launch vehicleCosmos B]-A#R8Launch siteKapustin Yar&# 5Q'  End of lifeVA#R*Decay25 May 1962$Qˊ" < 1nK OߎCosmos 0100HˊO5 :(qi" Cosmos 01001 '  Generalg OG#^@") Designation01843 / 65106A\CA#R6Launch date17 Dec 1965jM#j:"N , Country of originCISUCG#^"H̀Mission^`A#R:"Perigee/Apogee485/547 kmTA#R&Inclination65R`A#R"Period95 min\bG#^*" &Launch vehicleYA#R0Launch siteTyuratam$bߎ" < 1L cCosmos 0110Hߎc5 :(qi" Cosmos 01101 '  Generalg c G#^@") Designation02070 / 66015A ߎ\hA#R6Launch date22 Feb 1966j M#j:"N , Country of originCISUh'G#^"H̀Mission^A#R:"Perigee/Apogee181/887 kmV'A#R*Inclination51.8T/A#R&Period95.3 min\G#^*" &Launch vehicleY/A#R0Launch siteTyuratamN*2$ TStudy of animals and vegetals in space5g'  End of lifeV2A#R*Decay16 Mar 1966$g" < 1uM e/Cosmos 0122He5 :(qi" Cosmos 01221 '  Generalg eG#^@") Designation02254 / 66057A\YA#R6Launch date25 Jun 1966jM#j:"N , Country of originCIShY+M#j6"H̀l/MissionMeteorology^A#R:"Perigee/Apogee371/388 kmT+A#R&Inclination65T1A#R&Period92.1 min\G#^*" &Launch vehicleY1A#R0Launch siteTyuratamJ&0$ LFirst soviet meteorology satellite5e'  End of lifeV0A#R*Decay14 Nov 19898e' "(Technical data</) "&bSpecifications< k1ƒN k[Cosmos 0144H/5 :(qi" Cosmos 01441 k'  Generalg KG#^@") Designation02695 / 67018A\A#R6Launch date28 Feb 1967jKM#j:"N , Country of originCIShyM#j6"H̀l/MissionMeteorology^A#R:"Perigee/Apogee574/644 kmVy-A#R*Inclination81.3TA#R&Period96.9 min\-G#^*" &Launch vehicleY6A#R0Launch sitePlesetsk&\# 56'  End of lifeV\A#R*Decay14 Sep 19828' "(Technical data<[) "&bSpecifications< 1vuO 0Cosmos 0169H[5 :(qi" Cosmos 01691 '  Generalg wG#^@") Designation02878 / 67069A\A#R6Launch date17 Jul 1967jwIM#j:"I[N , Country of originCISUG#^"H̀Mission^IA#R:"Perigee/Apogee135/200 kmVRA#R*Inclination49.7TA#R&Period87.8 min\RG#^*" &Launch vehicleY[A#R0Launch siteTyuratam&# 5['  End of lifeV A#R*Decay17 Jul 1967$0" < l1ƒP lCosmos 0186H05 :(qi" Cosmos 01861 l'  Generalg LG#^@") Designation03014 / 67105A\A#R6Launch date27 Oct 1967jLM#j:"N , Country of originCISUgG#^"H̀Mission^A#R:"Perigee/Apogee179/223 kmVgA#R*Inclination51.6ToA#R&Period88.6 min\G#^*" &Launch vehicleYo$A#R0Launch siteTyuratamIm+ &<GځDocked with Cosmos 01885$'  End of lifeVmA#R*Decay31 Oct 1967$" < X1Q X Cosmos 0188H5 :(qi" Cosmos 01881 X'  Generalg 8 G#^@") Designation03020 / 67107A\ A#R6Launch date30 Oct 1967j8 M#j:"N , Country of originCISU S G#^"H̀Mission^ A#R:"Perigee/Apogee180/247 kmVS  A#R*Inclination51.7T [ A#R&Period88.7 min\ G#^*" &Launch vehicleY[  A#R0Launch siteTyuratamI Y + &<EځDocked with Cosmos 01865 '  End of lifeUY A#R(Decay2 Nov 1967$  " < C 1R C BCosmos 0368H 5 :(qi" Cosmos 03681 C '  Generalg #G#^@") Designation04571 / 70080A[ ~A#R4Launch date8 Oct 1970j#M#j:"N , Country of originCISU~=G#^"H̀Mission^A#R:"Perigee/Apogee202/383 kmT= @A#R&Inclination65 @ T`@A#R&Period90.4 min\ @@G#^*" &Launch vehicleY`@AA#R0Launch siteTyuratamN*@cA$ TStudy of animals and vegetals in space5AA'  End of lifeVcAAA#R*Decay14 Oct 1970$AB" < ANB1S NBBhFCosmos 0444HBB5 :(qi" Cosmos 04441 NBB'  Generalg B.CG#^@") Designation05547 / 71086A\BCA#R6Launch date13 Oct 1971j.CCM#j:"N , Country of originCIS/CvDS#v^"H̀(㓉<MissionTelecommunications (Strela-2)`CDA#R>"Perigee/Apogee1318/1507 kmTvD*EA#R&Inclination74UDEA#R(Period114.1 minl*EEM#j>" &s,梉Launch vehicleCosmos CYEDFA#R0Launch sitePlesetsk$EhF" < DFF1ׂT FFJCosmos 0445HhFF5 :(qi" Cosmos 04451 FG'  Generalg FGG#^@") Designation05548 / 71086B\GGA#R6Launch date13 Oct 1971jGJHM#j:"N , Country of originCIS/GHS#v^"H̀(㓉<MissionTelecommunications (Strela-2)`JH,IA#R>"Perigee/Apogee1348/1509 kmTHIA#R&Inclination74U,IIA#R(Period114.4 minlIAJM#j>" &s,梉Launch vehicleCosmos CYIJA#R0Launch sitePlesetsk$AJJ" < JJ1U JBKOCosmos 0446HJBK5 :(qi" Cosmos 04461 JsK'  Generalg BKKG#^@") Designation05549 / 71086C\sK6LA#R6Launch date13 Oct 1971jKLM#j:"N , Country of originCIS/6L"MS#v^"H̀(㓉<MissionTelecommunications (Strela-2)`LMA#R>"Perigee/Apogee1378/1509 kmT"MMA#R&Inclination74UM+NA#R(Period114.8 minlMNM#j>" &s,梉Launch vehicleCosmos CY+NNA#R0Launch sitePlesetsk$NO" < NPO1ׂV POOvCosmos 0447HOO5 :(qi" Cosmos 04471 POO'  Generalg O<G#^@")O<O Designation05550 / 71086D\OA#R6Launch date13 Oct 1971j<M#j:"N , Country of originCIS/S#v^"H̀(㓉<MissionTelecommunications (Strela-2)`A#R>"Perigee/Apogee1408/1512 kmT8A#R&Inclination74UA#R(Period115.1 minl8M#j>" &s,梉Launch vehicleCosmos CYRA#R0Launch sitePlesetsk$v" < R1 W ̇Cosmos 0448Hv5 :(qi" Cosmos 04481 +'  Generalg G#^@") Designation05551 / 71086E\+A#R6Launch date13 Oct 1971jXM#j:"N , Country of originCIS/څS#v^"H̀(㓉<MissionTelecommunications (Strela-2)`X:A#R>"Perigee/Apogee1438/1514 kmTڅA#R&Inclination74U:A#R(Period115.5 minlOM#j>" &s,梉Launch vehicleCosmos CYA#R0Launch sitePlesetsk$Ȯ" < 1.X P"Cosmos 0449ḢP5 :(qi" Cosmos 04491 '  Generalg PG#^@") Designation05552 / 71086F\DA#R6Launch date13 Oct 1971jM#j:"N , Country of originCIS/D0S#v^"H̀(㓉<MissionTelecommunications (Strela-2)`A#R>"Perigee/Apogee1480/1540 kmT0A#R&Inclination74U9A#R(Period116.2 minlM#j>" &s,梉Launch vehicleCosmos CY9A#R0Launch sitePlesetsk$"" < ^1 Y ^Cosmos 0450H"5 :(qi" Cosmos 04501 ^׌'  Generalg >G#^@") Designation05553 / 71086G\׌A#R6Launch date13 Oct 1971j>M#j:"N , Country of originCIS/S#v^"H̀(㓉<MissionTelecommunications (Strela-2)`A#R>"Perigee/Apogee1460/1527 kmT:A#R&Inclination74UA#R(Period115.8 minl: M#j>" &s,梉Launch vehicleCosmos C "YeA#R0Launch sitePlesetsk$ " < e1.>Z Cosmos 0451H 5 :(qi" Cosmos 04511 >'  Generalg G#^@") Designation05554 / 71086H\>A#R6Launch date13 Oct 1971jkM#j:"N , Country of originCIS/S#v^"H̀(㓉<MissionTelecommunications (Strela-2)`kMA#R>"Perigee/Apogee1487/1571 kmTA#R&Inclination74UMA#R(Period116.6 minlbM#j>" &s,梉Launch vehicleCosmos CYA#R0Launch sitePlesetsk$b" < 1[ cCosmos 0500Hc5 :(qi" Cosmos 05001 '  Generalg cG#^@") Designation06097 / 72053A\WA#R6Launch date10 Jul 1972jM#j:"N , Country of originCISw*W8M#jT"H̀_剂MissionMilitary: SIGINT (Tselina)^A#R:"Perigee/Apogee505/548 kmT8A#R&Inclination74T>A#R&Period95.2 minlM#j>" &s,梉Launch vehicleCosmos CY>A#R0Launch sitePlesetsk&)# 5^'  End of lifeV)A#R*Decay29 Mar 1980$^" < 1>\ \.Cosmos 0504H\5 :(qi" Cosmos 05041 '  Generalg \G#^@") Designation06117 / 72057A\PA#R6Launch date20 Jul 1972jM#j:"N , Country of originCIS/P<S#v^"H̀(㓉<MissionTelecommunications (Strela-2)`A#R>"Perigee/Apogee1319/1493 kmT<A#R&Inclination74UEA#R(Period113.9 minlM#j>" &s,梉Launch vehicleCosmos CYE A#R0Launch sitePlesetsk$." < j1 ] jCosmos 0505H.5 :(qi" Cosmos 05051 j'  Generalg JG#^@") Designation06118 / 72057B\A#R6Launch date20 Jul 1972jJM#j:"N , Country of .originCIS/S#v^"H̀(㓉<MissionTelecommunications (Strela-2)`A#R>"Perigee/Apogee1349/1494 kmTRA#R&Inclination74UA#R(Period114.3 minlRM#j>" &s,梉Launch vehicleCosmos CYlA#R0Launch sitePlesetsk$" < l1^ Cosmos 0506H5 :(qi" Cosmos 05061 E'  Generalg G#^@") Designation06119 / 72057C\EA#R6Launch date20 Jul 1972jrM#j:"N , Country of originCIS/S#v^"H̀(㓉<MissionTelecommunications (Strela-2)`rTA#R>"Perigee/Apogee1380/1494 kmTA#R&Inclination74UTA#R(Period114.6 minliM#j>" &s,梉Launch vehicleCosmos CYA#R0Launch sitePlesetsk$i" < "1_ "j< Cosmos 0507Hj5 :(qi" Cosmos 05071 "'  Generalg jG#^@") Designation06120 / 72057D\^A#R6Launch date20 Jul 1972jM#j:"N , Country of originCIS/^J S#v^"H̀(㓉<MissionTelecommunications (Strela-2)` A#R>"Perigee/Apogee1409/1494 kmTJ A#R&Inclination74U S A#R(Period114.9 minl M#j>" &s,梉Launch vehicleCosmos CYS  A#R0Launch sitePlesetsk$ < " <  x 1` x Cosmos 0508H< 5 :(qi" Cosmos 05081 x '  Generalg X G#^@") Designation06121 / 72057E\ A#R6Launch date20 Jul 1972jX  M#j:"N , Country of originCIS/ S#v^"H̀(㓉<MissionTelecommunications (Strela-2)` A#R>"Perigee/Apogee1441/1493 kmT TA#R&Inclination74UA#R(Period115.3 minlTM#j>" &s,梉Launch vehicleCosmos CYnA#R0Launch sitePlesetsk$" < n1a "@CCosmos 0509H"@5 :(qi""@ Cosmos 05091 S@'  Generalg "@@G#^@") Designation06122 / 72057F\S@AA#R6Launch date20 Jul 1972j@AM#j:"N , Country of originCIS/ABS#v^"H̀(㓉<MissionTelecommunications (Strela-2)`AbBA#R>"Perigee/Apogee1471/1496 kmTBBA#R&Inclination74UbB CA#R(Period115.6 minlBwCM#j>" &s,梉Launch vehicleCosmos CY CCA#R0Launch sitePlesetsk$wCC" < C0D12b 0DxDHHCosmos 0510HCxD5 :(qi" Cosmos 05101 0DD'  Generalg xDEG#^@") Designation06123 / 57057G\DlEA#R6Launch date20 Jul 1972jEEM#j:"N , Country of originCIS/lEXFS#v^"H̀(㓉<MissionTelecommunications (Strela-2)`EFA#R>"Perigee/Apogee1493/1507 kmTXF GA#R&Inclination74SF_GA#R$Period116 minl GGM#j>" &s,梉Launch vehicleCosmos CY_G$HA#R0Launch sitePlesetsk$GHH" < $HH1Vc HHLCosmos 0511HHHH5 :(qi" Cosmos 05111 HH'  Generalg HdIG#^@") Designation06124 / 72057H\HIA#R6Launch date20 Jul 1972jdI*JM#j:"N , Country of originCIS/IJS#v^"H̀(㓉<MissionTelecommunications (Strela-2)`*J KA#R>"Perigee/Apogee1493/1543 kmTJ`KA#R&Inclination74U KKA#R(Period116.4 minl`K!LM#j>" &s,梉Launch vehicleCosmos CYKzLA#R0Launch sitePlesetsk$!LL" < zLL1$29d L"MCosmos 0588HL"M5 :(qi" Cosmos 05881 LSM'  Generalg "MMG#^@") Designation06845 / 73069A[SMNA#R4Launch date2 Oct 1973jMNM#j:"N , Country of originCIS/NOS#v^"H̀(㓉<MissionTelecommunications (Strela-2)`NaOA#R>"Perigee/Apogee1446/1490 kmTOOA#R&Inclination74UaOA#R(Period1OL55.3 minlOM#j>" &s,梉Launch vehicleCosmos CYۀA#R0Launch sitePlesetsk$" < ۀ;1V\e ;TCosmos 0589H5 :(qi" Cosmos 05891 ;'  Generalg G#^@") Designation06846 / 73069B[vA#R4Launch date2 Oct 1973jM#j:"N , Country of originCIS/vbS#v^"H̀(㓉<MissionTelecommunications (Strela-2)`ƒA#R>"Perigee/Apogee1412/1486 kmTbA#R&Inclination74UƒkA#R(Period114.9 minlׄM#j>" &s,梉Launch vehicleCosmos CYk0A#R0Launch sitePlesetsk$ׄT" < 019f ؅Cosmos 0590HT؅5 :(qi" Cosmos 05901 '  Generalg ؅pG#^@") Designation06847 / 73069C[ ˆA#R4Launch date2 Oct 1973jp5M#j:"N , Country of originCIS/ˆS#v^"H̀(㓉<MissionTelecommunications (Strela-2)`5A#R>"Perigee/Apogee1431/1485 kmTkA#R&Inclination74UA#R(Period115.1 minlk,M#j>" &s,梉Launch vehicleCosmos CYA#R0Launch sitePlesetsk$," < 1\g -Cosmos 0591H-5 :(qi" Cosmos 05911 ^'  Generalg -ŊG#^@") Designation06848 / 73069D[^ A#R4Launch date2 Oct 1973jŊM#j:"N , Country of originCIS/ S#v^"H̀(㓉<MissionTelecommunications (Strela-2)`lA#R>"Perigee/Apogee1344/1483 kmT A#R&Inclination74UlA#R(Period114.4 minlM#j>" &s,梉Launch vehicleCosmos CYڍA#R0Launch sitePlesetsk$" < ڍ:1h :_Cosmos 0592H5 :(qi" Cosmos 05921 :'  Generalg G#^@") Designation06849 / 73069E[uA#R4Launch date2 Oct 1973jߏM#j:"N , Country of originCIS/umS#v^ߏm"H̀(㓉<MissionTelecommunications (Strela-2)`ߏA#R>"Perigee/Apogee1328/1482 kmTm!A#R&Inclination74UvA#R(Period133.9 minl!M#j>" &s,梉Launch vehicleCosmos CYv;A#R0Launch sitePlesetsk$_" < ;1i Cosmos 0593H_5 :(qi" Cosmos 05931 '  Generalg {G#^@") Designation06850 / 73069F[A#R4Launch date2 Oct 1973j{@M#j:"N , Country of originCIS/S#v^"H̀(㓉<MissionTelecommunications (Strela-2)`@"A#R>"Perigee/Apogee1361/1483 kmTvA#R&Inclination74U"A#R(Period114.3 minlv7M#j>" &s,梉Launch vehicleCosmos CYA#R0Launch sitePlesetsk$7" < 1łj 8 Cosmos 0594H85 :(qi" Cosmos 05941 i'  Generalg 8G#^@") Designation06851 / 73069G[i+A#R4Launch date2 Oct 1973jM#j:"N , Country of originCIS/+S#v^"H̀(㓉<MissionTelecommunications (Strela-2)`wA#R>"Perigee/Apogee1378/1484 kmTA#R&Inclination74Uw A#R(Period114.5 minlM#j>" &s,梉Launch vehicleCosmos CY A#R0Launch sitePlesetsk$ " < E1k E^Cosmos 0595H 5 :(qi" Cosmos 05951 E'  Generalg %G#^@") Designation06852 / 73069H[A#R4Launch date2 Oct 1973j%M#j:"N , Country of originCIS/lS#v^"H̀(㓉<MissionTelecommunications (Strela-2)`A#R>"Perigee/Apogee1396/1483 kmTl A#R&Inclination74UuA#R(Period114.7 minl M#j>" &s,梉Launch vehicleCosmos CYu:A#R0Launch sitePlesetsk$^" !< :1łl VCosmos 0596H^ 5 :(qi" Cosmos 0596 ^1 ='  Generalg G#^@") Designation06856 / 73070A[=A#R4Launch date3 Oct 1973jiM#j:"N , Country of originCIS\G#^*"H̀Missionspying?^i#A#R:"Perigee/Apogee206/287 kmVyA#R*Inclination65.4T#A#R&Period89.4 min\y)G#^*" &Launch vehicleYA#R0Launch sitePlesetsk&)# 5'  End of lifeU2A#R(Decay9 Oct 1973$V" < 21|3m % Cosmos 0597HV5 :(qi" Cosmos 05971  '  Generalg rG#^@") Designation06858 / 73071A[ A#R4Launch date6 Oct 1973jr7M#j:"N , Country of originCIS\G#^*"H̀Missionspying?^7A#R:"Perigee/Apogee206/290 kmVGA#R*Inclination65.4TA#R&Period89.5 min\GG#^*" &Launch vehicleYPA#R0Launch sitePlesetsk&v# 5P'  End of lifeVv A#R*Decay12 Oct 1973$% " <  a 1}Xn a Cosmos 0598H% 5 :(qi" Cosmos 05981 a '  Generalg A G#^@") Designation06862 / 73072A\ A#R6Launch date10 Oct 1973jA  M#j:"N , Country of originCIS\ c G#^*"H̀Missionspying?^ A#R:"Perigee/Apogee208/334 kmVc  A#R*Inclination72.8T k A#R&Period89.9 min\ G#^*" &Launch vehicleYk A#R0Launch sitePlesetsk& F # 5 { '  End of lifeVF A#R*Decay16 Oct 1973${ " < 113o 1yBCosmos 0599H y5 :(qi" Cosmos 05991 1'  Generalg yG#^@") Designation06867 / 73073A\mA#R6Launch date15 Oct 1973jM#j:"N , Country of originCIS\m?@G#^*"?@ H̀Missionspying?^@A#R:"Perigee/Apogee202/280 kmV?@@A#R*Inclination64.9T@GAA#R&Period89.3 min\@AG#^*" &Launch vehicleYGAAA#R0Launch sitePlesetsk&A"B# 5AWB'  End of lifeV"BBA#R*Decay28 Oct 1973$WBB" < B C1{Xp CUCGCosmos 0600HBUC5 :(qi" Cosmos 06001 CC'  Generalg UCCG#^@") Designation06873 / 73074A\CIDA#R6Launch date16 Oct 1973jCDM#j:"N , Country of originCIS\IDEG#^*"H̀Missionspying?^DmEA#R:"Perigee/Apogee205/340 kmVEEA#R*Inclination72.8RmEFA#R"Period90 min\EqFG#^*" &Launch vehicleYFFA#R0Launch sitePlesetsk&qFF# 5F%G'  End of lifeVF{GA#R*Decay23 Oct 1973$%GG" < {GG1q G#HLCosmos 0605HG#H5 :(qi" Cosmos 0605AGdH) "0Also called Bion 011 #HH'  Generalg dHHG#^@") Designation06913 / 73083A\HXIA#R6Launch date31 Oct 1973jHIM#j:"N , Country of originCISUXIJG#^"H̀Mission^IuJA#R:"Perigee/Apogee213/403 kmVJJA#R*Inclination62.8TuJKA#R&Period90.7 min\J{KG#^*" &Launch vehicleYKKA#R0Launch sitePlesetskN*{K"L$ TStudy of animals and vegetals in space5KWL'  End of lifeV"LLA#R*Decay22 Nov 1973$WLL" < L M1\r MUMCosmos 0637HLUM5 :(qi" Cosmos 06371 MM'  Generalg UMMG#^@") Designation07229 / 74017A\MINA#R6Launch date26 Mar 1974jMNM#j:"N , Country of originCISy,IN,OM#jX"H̀‰MissionMilitary: Telecommunicationsh'NOA#RN"Perigee/Apogee35475/35819 km, 65EV,O A#R*Inclination13,7O LTO`A#R&Period1429 minn! ΀M#jB" &㉓gLaunch vehicleProton #46L(`$ PFirst Soviet geostationary satellite< ΀V1s VpCosmos 0641H5 :(qi" Cosmos 06411 Vρ'  Generalg 6G#^@") Designation07265 / 74024A\ρA#R6Launch date23 Apr 1974j6M#j:"N , Country of originCIS/~S#v^"H̀(㓉<MissionTelecommunications (Strela-2)`ރA#R>"Perigee/Apogee1385/1479 kmT~2A#R&Inclination74UރA#R(Period114.5 minl2M#j>" &s,梉Launch vehicleCosmos CYLA#R0Launch sitePlesetsk$p" < L1\t ƉCosmos 0642Hp5 :(qi" Cosmos 06421 %'  Generalg G#^@") Designation07266 / 74024B\%A#R6Launch date23 Apr 1974jRM#j:"N , Country of originCIS/ԇS#v^"H̀(㓉<MissionTelecommunications (Strela-2)`R4A#R>"Perigee/Apogee1316/1478 kmTԇA#R&Inclination74U4݈A#R(Period113.7 minlIM#j>" &s,梉Launch vehicleCosmos CY݈A#R0Launch sitePlesetsk$IƉ" < 1u JCosmos 0643HƉJ5 :(qi" Cosmos 06431 {'  Generalg JG#^@") Designation07267 / 74024C\{>A#R6Launch date23 Apr 1974jM#j:"N , Country of originCIS/>*S#v^"H̀(㓉<MissionTelecommunications (Strela-2)`A#R>"Perigee/Apogee1350/1479 kmT*ތA#R&Inclination74U3A#R(Period114.4 minlތM#j>" &s,梉Launch vehicleCosmos CY3A#R0Launch sitePlesetsk$" < X1v XCosmos 0644H5 :(qi" Cosmos 06441 Xю'  Generalg 8G#^@") Designation07268 / 74024D\юA#R6Launch date23 Apr 1974j8 M#j:"N , Country of originCIS /S#v^"H̀(㓉<MissionTelecommunications (Strela-2)` A#R>"Perigee/Apogee1332/1479 kmTBA#R&Inclination74UA#R(Period113.9 minlBM#j>" &s,梉Launch vehicleCosmos CY\A#R0Launch sitePlesetsk$" < \1ҁw Cosmos 0645H5 :(qi" Cosmos 06451 5'  Generalg G#^@") Designation07269 / 74024E\5A#R6Launch date23 Apr 1974jbM#j:"N , Country of originCIS/S#v^"H̀(㓉<MissionTelecommunications (Strela-2)`bDA#R>"Perigee/Apogee1367/1479 kmTA#R&Inclination74UDA#R(Period114.3 minlYM#j>" &s,梉Launch vehicleCosmos CYA#R0Launch sitePlesetsk$Y" < 1x Z,Cosmos 0646HZ5 :(qi" Cosmos 06461 '  Generalg ZG#^@") Designation07270 / 74024F\NA#R6Launch date23 Apr 1974jM#j:"N , Country of originCIS/N:S#v^"H̀(㓉<MissionTelecommunications (Strela-2)`A#R>"Perigee/Apogee1402/1482 kmT:A#R&Inclination74UCA#R(Period114.7 minlM#j>" &s,梉Launch vehicleCosmos CYCA#R0Launch sitePlesetsk$," < h1ҁy hCosmos 0647H,5 :(qi" Cosmos 06471 h'  Generalg HG#^@") Designation07271 / 74024G\A#R6Launch date23 Apr 1974jHM#j:"N , Country of originCIS/S#v^"H̀(㓉<MissionTelecommunications (Strela-2)`A#R>"Perigee/Apogee1420/1481 kmTDA#R&Inclination74UA#R(Period114.9 minlDM#j>" &s,梉Launch vehicleCosmos CY^A#R0Launch sitePlesetsk$" < ^1z Cosmos 0648H5 :(qi" Cosmos 06481 C'  Generalg G#^@") Designation07272 / 74024H\CA#R6Launch date23 Apr 1974jpM#j:"N , Country of originCIS/S#v^"H̀(㓉<MissionTelecommunications (Strela-2)`pRA#R>"Perigee/Apogee1435/1487 kmTA#R&Inclination74URA#R(Period115.1 minlgM#j>" &s,梉Launch vehicleCosmos CYA#R0Launch sitePlesetsk$g" <  14{ h:Cosmos 0677Hh5 :(qi" Cosmos 06771 '  Generalg hG#^@") Designation07435 / 74072A\\A#R6Launch date19 Sep 1974jM#j:"N , Country of originCIS/\HS#v^"H̀(㓉<MissionTelecommunications (Strela-2)`A#R>"Perigee/Apogee1394/1464 kmTHA#R&Inclination74UQA#R(Period114.4 minlM#j>" &s,梉Launch vehicleCosmos CYQA#R0Launch sitePlesetsk$:" < v1X| v Cosmos 0678H:5 :(qi" Cosmos 06781 v'  Generalg V G#^@") Designation07436 / 74072B\ A#R6Launch date19 Sep 1974jV  M#j:"N , Country of originCIS/ S#v^"H̀(㓉<MissionTelecommunications (Strela-2)` A#R>"Perigee/Apogee1464/1530 kmT R A#R&Inclination74U A#R(Period115.9 minlR  M#j>" &s,梉Launch vehicleCosmos CY l A#R0Launch sitePlesetsk$ " < l 149}  @Cosmos 0679H  5 :(qi" Cosmos 06791 E '  Generalg  G#^@") Designation07437 / 74072C\E A#R6Launch date19 Sep 1974j rM#j:"N , Country of originCIS/S#v^"H̀(㓉<MissionTelecommunications (Strela-2)`rTA#R>"Perigee/Apogee1464/1508 kmTA#R&Inclination74UT @A#R(Period115.7 min @ lx@M#j>" &s,梉Launch vehicleCosmos CY @@A#R0Launch sitePlesetsk$x@@" < @1A1X]~ 1AyAKECosmos 0680H@yA5 :(qi" Cosmos 06801 1AA'  Generalg yABG#^@") Designation07438 / 74072D\AmBA#R6Launch date19 Sep 1974jBBM#j:"N , Country of originCIS/mBYCS#v^"H̀(㓉<MissionTelecommunications (Strela-2)`BCA#R>"Perigee/Apogee1464/1489 kmTYC DA#R&Inclination74UCbDA#R(Period115.5 minl DDM#j>" &s,梉Launch vehicleCosmos CYbD'EA#R0Launch sitePlesetsk$DKE" < 'EE19 EEICosmos 0681HKEE5 :(qi" Cosmos 06811 EF'  Generalg EgFG#^@") Designation07439 / 74072E\FFA#R6Launch date19 Sep 1974jgF-GM#j:"N , Country of originCIS/FGS#v^"H̀(㓉<MissionTelecommunications (Strela-2)`-GHA#R>"Perigee/Apogee1463/1470 kmTGcHA#R&Inclination74UHHA#R(Period115.3 minlcH$IM#j>" &s,梉Launch vehicleCosmos CYH}IA#R0Launch sitePlesetsk$$II" < }II1] I%JMCosmos 0682HI%J5 :(qi" Cosmos 06821 IVJ'  Generalg %JJG#^@") Designation07440 / 74072F\VJKA#R6Launch date19 Sep 1974jJKM#j:"N , Country of originCIS/KLS#v^"H̀(㓉<MissionTelecommunications (Strela-2)`KeLA#R>"Perigee/Apogee1450/1464 kmTLLA#R&Inclination74SeL MA#R$Period115 minlLxMM#j>" &s,梉Launch vehicleCosmos CY MMA#R0Launch sitePlesetsk$xMM" < M1N1' 1NyNWCosmos 0683HMyN5 :(qi" Cosmos 06831 1NN'  Generalg yNOG#^@") Designation07441 / 74072G\NmOA#R6Launch date19 Sep 1974jOOM#j:"N , Country of originCIS/mOeS#v^"OeMH̀(㓉<MissionTelecommunications (Strela-2)`OŀA#R>"Perigee/Apogee1432/1464 kmTeA#R&Inclination74UŀnA#R(Period114.8 minlځM#j>" &s,梉Launch vehicleCosmos CYn3A#R0Launch sitePlesetsk$ځW" < 31 ۂCosmos 0684HWۂ5 :(qi" Cosmos 06841 '  Generalg ۂsG#^@") Designation07442 / 74072H\ σA#R6Launch date19 Sep 1974js9M#j:"N , Country of originCIS/σS#v^"H̀(㓉<MissionTelecommunications (Strela-2)`9A#R>"Perigee/Apogee1413/1464 kmToA#R&Inclination74UąA#R(Period114.6 minlo0M#j>" &s,梉Launch vehicleCosmos CYąA#R0Launch sitePlesetsk$0" < 1 1Cosmos 0711H15 :(qi" Cosmos 07111 b'  Generalg 1ɇG#^@") Designation07678 / 75016A\b%A#R6Launch date28 Feb 1975jɇM#j:"N , Country of originCIS/%S#v^"H̀(㓉<MissionTelecommunications (Strela-2)`qA#R>"Perigee/Apogee1459/1490 kmTʼnA#R&Inclination74UqA#R(Period115.4 minlʼnM#j>" &s,梉Launch vehicleCosmos CYߊA#R0Launch sitePlesetsk$" < ߊ?1 ?YCosmos 0712H5 :(qi" Cosmos 07121 ?'  Generalg G#^@") Designation07679 / 75016B\{A#R6Launch date28 Feb 1975jM#j:"N , Country of originCIS/{gS#v^"H̀(㓉<MissionTelecommunications (Strela-2)`ǍA#R>"Perigee/Apogee1409/1488 kmTgA#R&Inclination74UǍpA#R(Period114.8 minl܎M#j>" &s,梉Launch vehicleCosmos CYp5A#R0Launch sitePlesetsk$܎Y" < 51% ݏCosmos 0713HYݏ5 :(qi" Cosmos 07131 ' ݏY Generalg ݏG#^@") Designation07680 / 75016C\A#R6Launch date28 Feb 1975jGM#j:"N , Country of originCIS/S#v^"H̀(㓉<MissionTelecommunications (Strela-2)`G)A#R>"Perigee/Apogee1393/1485 kmT}A#R&Inclination74U)A#R(Period114.6 minl}>M#j>" &s,梉Launch vehicleCosmos CYA#R0Launch sitePlesetsk$>" < 1* ?Cosmos 0714H?5 :(qi" Cosmos 07141 p'  Generalg ?G#^@") Designation07681 / 75016D\p3A#R6Launch date28 Feb 1975jM#j:"N , Country of originCIS/3S#v^"H̀(㓉<MissionTelecommunications (Strela-2)`A#R>"Perigee/Apogee1442/1489 kmTA#R&Inclination74U(A#R(Period115.2 minlM#j>" &s,梉Launch vehicleCosmos CY(A#R0Launch sitePlesetsk$" < M1N MgCosmos 0715H5 :(qi" Cosmos 07151 M'  Generalg -G#^@") Designation07682 / 75016E\A#R6Launch date28 Feb 1975j-M#j:"N , Country of originCIS/uS#v^"H̀(㓉<MissionTelecommunications (Strela-2)`A#R>"Perigee/Apogee1467/1502 kmTu)A#R&Inclination74U~A#R(Period115.7 minl)M#j>" &s,梉Launch vehicleCosmos CY~CA#R0Launch sitePlesetsk$g" < C1* Cosmos 0716Hg5 :(qi" Cosmos 07161 '  Generalg G#^@") Designation07683 / 75016F\A#R6Launch date28 Feb 1975jIM#j:"N , Country of originCIS/S#v^"H̀(㓉<MissionTelecommunications (Strela-2)`I+A#R>"Perigee/Apogee1477/1512 kmTA#R&Inclination74U+A#R(Period115.9 minlLM#j>"Lg &s,梉Launch vehicleCosmos CYA#R0Launch sitePlesetsk$L" < 1N> MCosmos 0717HM5 :(qi" Cosmos 07171 ~'  Generalg MG#^@") Designation07684 / 75016G\~AA#R6Launch date28 Feb 1975jM#j:"N , Country of originCIS/A-S#v^"H̀(㓉<MissionTelecommunications (Strela-2)`A#R>"Perigee/Apogee1477/1533 kmT-A#R&Inclination74U6A#R(Period116.1 minlM#j>" &s,梉Launch vehicleCosmos CY6A#R0Launch sitePlesetsk$" < [1` [s Cosmos 0718H5 :(qi" Cosmos 07181 ['  Generalg ;G#^@") Designation07685 / 75016H\A#R6Launch date28 Feb 1975j;M#j:"N , Country of originCIS/S#v^"H̀(㓉<MissionTelecommunications (Strela-2)`A#R>"Perigee/Apogee1427/1487 kmT7A#R&Inclination74SA#R$Period115 minl7M#j>" &s,梉Launch vehicleCosmos CYO A#R0Launch sitePlesetsk$s " < O 1> Cosmos 0732Hs 5 :(qi" Cosmos 07321 ( '  Generalg G#^@") Designation07820 / 75045A\( A#R6Launch date28 May 1975j U M#j:"N , Country of originCIS/ S#v^"H̀(㓉<MissionTelecommunications (Strela-2)`U 7 A#R>"Perigee/Apogee1401/1468 kmT A#R&Inclination74U7 A#R(Period114.6 minl L M#j>" &s,梉Launch vehicleCosmos CY A#R0Launch sitePlesetsk$L " < 1` M+BCosmos 0733H M5 :(qi" Cosmos 07331 ~'  Generalg MG#^@") Designation07822 / 75045B\~AA#R6Launch date28 May 1975jM#j:"N , Country of originCIS/A9@S#v^"H̀(㓉<9@ MissionTelecommunications (Strela-2)`@A#R>"Perigee/Apogee1467/1552 kmT9@@A#R&Inclination74U@BAA#R(Period116.2 minl@AM#j>" &s,梉Launch vehicleCosmos CYBABA#R0Launch sitePlesetsk$A+B" < BgB1 gBBFCosmos 0734H+BB5 :(qi" Cosmos 07341 gBB'  Generalg BGCG#^@") Designation07823 / 75045C\BCA#R6Launch date28 May 1975jGC DM#j:"N , Country of originCIS/CDS#v^"H̀(㓉<MissionTelecommunications (Strela-2)` DDA#R>"Perigee/Apogee1441/1469 kmTDCEA#R&Inclination74SDEA#R$Period115 minlCEFM#j>" &s,梉Launch vehicleCosmos CYE[FA#R0Launch sitePlesetsk$FF" < [FF1ł FGJCosmos 0735HFG5 :(qi" Cosmos 07351 F4G'  Generalg GGG#^@") Designation07824 / 75045D\4GGA#R6Launch date28 May 1975jGaHM#j:"N , Country of originCIS/GHS#v^"H̀(㓉<MissionTelecommunications (Strela-2)`aHCIA#R>"Perigee/Apogee1459/1472 kmTHIA#R&Inclination74UCIIA#R(Period115.2 minlIXJM#j>" &s,梉Launch vehicleCosmos CYIJA#R0Launch sitePlesetsk$XJJ" < JK1 KYK+OCosmos 0736HJYK5 :(qi" Cosmos 07361 KK'  Generalg YKKG#^@") Designation07825 / 75045E\KMLA#R6Launch date28 May 1975jKLM#j:"N , Country of originCIS/ML9MS#v^"H̀(㓉<MissionTelecommunications (Strela-2)`LMA#R>"Perigee/Apogee1467/1484 kmT9MMA#R&Inclination74UMBNA#R(Period115.5 minlMNM#j>" &s,梉Launch vehicleCosmos CYBNOA#R0Launch sitePlesetsk$N+O" < OgO1ł gOOCosmos 0737H+OO5 :(qi" Cosmos 07371 gOO'  Generalg OSG#^@OS+O") Designation07826 / 75045F\OA#R6Launch date28 May 1975jSM#j:"N , Country of originCIS/S#v^"H̀(㓉<MissionTelecommunications (Strela-2)`A#R>"Perigee/Apogee1468/1484 kmTOA#R&Inclination74UA#R(Period115.9 minlOM#j>" &s,梉Launch vehicleCosmos CYiA#R0Launch sitePlesetsk$" < iɃ1  ɃCosmos 0738H5 :(qi" Cosmos 07381 ɃB'  Generalg G#^@") Designation07827 / 75045G\BA#R6Launch date28 May 1975joM#j:"N , Country of originCIS/S#v^"H̀(㓉<MissionTelecommunications (Strela-2)`oQA#R>"Perigee/Apogee1467/1506 kmTA#R&Inclination74UQA#R(Period115.7 minlfM#j>" &s,梉Launch vehicleCosmos CYA#R0Launch sitePlesetsk$f" < 1. g9Cosmos 0739Hg5 :(qi" Cosmos 07391 '  Generalg gG#^@") Designation07828 / 75045H\#R6Launch date28 May 1975jʼnM#j:"N , Country of originCIS/[GS#v^"H̀(㓉<MissionTelecommunications (Strela-2)`ʼnA#R>"Perigee/Apogee1421/1506 kmTGA#R&Inclination74UPA#R(Period115.7 minlM#j>" &s,梉Launch vehicleCosmos CYPA#R0Launch sitePlesetsk$9" < u1   uCosmos 0775H95 :(qi" Cosmos 07751 u'  Generalg UG#^@") Designation08357 / 75097A[A#R4Launch date8 Oct 1975jUM#j:"N , Country of originCISSG#^"H̀MissionMilitary: early warning (Oko GEO, also called Prognoz 1st generation)]A#R8,Geostationary orbit25Wn!M#jB" &㉓gLaunch vehicleProton #54o2= HeooooFirst satellite of the Oko series for early warning put on geostat9ionary orbit. It was the same design as the Oko satellites on molnyia type orbit. Four such satellites were launched: Cosmos 0775, Cosmos 1546, Cosmos 1629 and Cosmos1894. The replacement series is called Prognoz 2nd generation.< 61s. 6~Cosmos 0777H~5 :(qi" Cosmos 07771 6'  Generalg ~G#^@") Designation08416 / 75102A\rA#R6Launch date29 Oct 1975jM#j:"N , Country of originCISUr1G#^"H̀Mission^A#R:"Perigee/Apogee425/442 kmT1A#R&Inclination65T7A#R&Period93.9 min\G#^*" &Launch vehicleY7A#R0Launch siteTyuratam&# 5G'  End of lifeUA#R(Decay3 Jun 1976$G" < 1 DCosmos 0782HD5 :(qi" Cosmos 0782A) "0Also called Bion 031 D'  Generalg G#^@") Designation08450 / 75110A\yA#R6Launch date25 Nov 1975jM#j:"N , Country of originCIS_yBG#^0"H̀MissionScientific^A#R:"Perigee/Apogee218/384 kmVBA#R*Inclination62.8TJA#R&Period90.5 min\G#^*" &Launch vehicleYJA#R0Launch sitePlesetskN*M$ TStudy of animals and vegetals in space5'  End of lifeVMA#R*Decay15 Dec 1975$" < 81 8CCosmos 0936H5 :(qi" Cosmos 0936A8) "0Also called Bion 041 '  Generalg YG#^@") Designation10172 / 77074A[A#R4Launch date3 Aug 1977jYM#j:"N , Country of originCIS_}G#^0"H̀MissionScientific^A#R:"Perigee/Apogee219/396 kmV}1A#R*Inclination62.8TA#R&Period90.6 min\1G#^*" &Launch vehicleY:A#R0Launch sitePlesetskN*$ TStudy of animals and vegetals in space5:'  End of lifeVA#R*Decay22 Aug 1977$C" < 1M Cosmos 0954HC5 :(qi" Cosmos 09541 '  Generalg _G#^@") Designation10361 / 77090A\A#R6Launch date18 Sep 1977j_%M#j:"N , Country of originCIS7M#jn"H̀d퉂MissionMilitary: ocean reconnaissance (Rorsat)^%A#R:"Perigee/Apogee251/265 kmT[A#R&Inclination65TA#R&Period89.7 min\[ G#^*" &Launch vehicleYdA#R0Launch siteTyuratam& # 5d'  End of lifeVA#R*Decay24 Jan 1978+ $Gㅯ\&Decayed in Canada. It was equipped with a 508 kg Romachka nuclear reactor for power supply with 49 kg of uranium. The CIS payed $2.55 million as compensation< 1 g1 Cosmos 1000Hg5 :(qi" Cosmos 10001 '  Generalg gG#^@") Designation10776 / 78034A\[A#R6Launch date31 Mar 1978jM#j:"N , Country of originCISy&[>S#vL"H̀(シ 剂MissionNavigation (Tsikada)_A#R<"Perigee/Apogee954/1006 kmV>A#R*Inclination82.9UH A#R(Period104.7 minl M#j>" &s,梉Launch vehicleCosmos CYH A#R0Launch sitePlesetsk$ 1 " < m 10 m Cosmos 1094H1 5 :(qi" Cosmos 10941 m '  Generalg M G#^@") Designation11333 / 79033A\ A#R6Launch date18 Apr 1979jM  M#j:"N , Country of originCISf y G#^>"H̀MissionOcean observation^ A#R:"Perigee/Apogee426/442 kmTy + A#R&Inclination65T  A#R&Period93.3 min\+ G#^*" &Launch vehicleY 4A#R0Launch siteTyuratam& Z# 54'  End of lifeUZA#R(Decay7 Nov 1979$" < D1 DDCosmos 1267H5 :(qi" Cosmos 1267GD) "<"Also called TKS Merkur #21 @'  Gener@alg w@G#^@") Designation12419 / 81039A\@@A#R6Launch date15 Apr 1981jw@=AM#j:"N , Country of originCISU@AG#^"H̀Mission^=AAA#R:"Perigee/Apogee192/259 kmVAFBA#R*Inclination51.6TABA#R&Period88.9 minn!FBCM#jB" &㉓gLaunch vehicleProton #88O+BWC$ VFirst spacecraft to dock with Salyout 65CC'  End of lifeVWCCA#R*Decay29 Jul 1982$CD" < CBD105 BDDHCosmos 1366HDD5 :(qi" Cosmos 13661 BDD'  Generalg D"EG#^@") Designation13177 / 82044A\D~EA#R6Launch date17 May 1982j"EEM#j:"N , Country of originCIS7~ErFS#vn"H̀(‰MissionMilitary: Telecommunications (Geizer)]EFA#R8,Geostationary orbit80En!rF=GM#jB" &㉓gLaunch vehicleProton #97&FcG# 5=GG'  End of life]cGGA#R8"Out of servicelate 1987$GH" < GUH1 UHH#NCosmos 1402HHH5 :(qi" Cosmos 14021 UHH'  Generalg H5IG#^@") Designation13441 / 82084A\HIA#R6Launch date30 Aug 1982j5IIM#j:"N , Country of originCIS7IJM#jn"H̀d퉂MissionMilitary: ocean reconnaissance (Rorsat)^IJA#R:"Perigee/Apogee250/266 kmVJ3KA#R*Inclination65.6TJKA#R&Period89.6 min\3KKG#^*" &Launch vehicleYK"H̀MissionMilitary: warninga A#R@"Perigee/Apogee3104/37311 kmVNA#R*Inclination67.1SXA#R$Period719 min\G#^*" &Launch vehicleYX A#R0Launch sitePlesetsk$1" < m1` mCosmos 1850H15 :(qi" Cosmos 18501 m'  Generalg MG#^@") Designation18095 / 87049A[A#R4Launch date9 Jun 1987jMM#j:"N , Country of originCIS/S#v^"H̀(㓉<MissionTelecommunications (Strela-1)^ A#R:"Perigee/Apogee775/798 km 1T`A#R&Inclination74U A#R(Period100.6 minl`!M#j>" &s,梉Launch vehicleCosmos CYzA#R0Launch sitePlesetsk$!" < z1m "Cosmos 1851H"5 :(qi" Cosmos 18511 S'  Generalg "G#^@") Designation18103 / 87050A\SA#R6Launch date12 Jun 1987jM#j:"N , Country of originCISfG#^>"H̀MissionMilitary: warninga GA#R@"Perigee/Apogee3671/36713 kmVA#R*Inclination65.5UGA#R(Period718.4 min\NG#^*" &Launch vehicleYA#R0Launch sitePlesetsk$N" < 1` O! Cosmos 1852HO5 :(qi" Cosmos 18521 '  Generalg OG#^@") Designation18113 / 87051A\CA#R6Launch date16 Jun 1987jM#j:"N , Country of originCIS/C/S#v^"H̀(㓉<MissionTelecommunications (Strela-2)`A#R>"Perigee/Apogee1471/1497 kmT/A#R&Inclination74U8 A#R(Period115.6 minl M#j>" &s,梉Launch vehicleCosmos CY8 A#R0Launch sitePlesetsk$ ! " < ] 1m ] wCosmos 1853H! 5 :(qi" Cosmos 18531 ] '  Generalg = G#^@") Designation18114 / 87051B\ A#R6Launch date16 Jun 1987j=  M#j:"N , Country of originCIS/ S#v^"H̀(㓉<MissionTelecommunications (Strela-2)` A#R>"Perigee/Apogee1470/1480 kmT 9 A#R&Inclination74U A#R(Period115.4 minl9 M#j>" &s,梉Launch vehicleCosmos CY SA#R0Launch sitePlesetsk$ w" < S1ˀ BCosmos 1854Hw5 :(qi" Cosmos 18541 ,'  Generalg G#^@") Designation18115 / 87051C\, @A#R6Launch date16 Jun 1987 @wjv@M#j:"N , Country of originCIS/ @@S#v^"H̀(㓉<MissionTelecommunications (Strela-2)`v@XAA#R>"Perigee/Apogee1456/1478 kmT@AA#R&Inclination74UXABA#R(Period115.3 minlAmBM#j>" &s,梉Launch vehicleCosmos CYBBA#R0Launch sitePlesetsk$mBB" < B&C1 &CnC@GCosmos 1855HBnC5 :(qi" Cosmos 18551 &CC'  Generalg nCDG#^@") Designation18116 / 87051D\CbDA#R6Launch date16 Jun 1987jDDM#j:"N , Country of originCIS/bDNES#v^"H̀(㓉<MissionTelecommunications (Strela-2)`DEA#R>"Perigee/Apogee1444/1475 kmTNEFA#R&Inclination74UEWFA#R(Period115.1 minlFFM#j>" &s,梉Launch vehicleCosmos CYWFGA#R0Launch sitePlesetsk$F@G" < G|G1ˀ |GGKCosmos 1856H@GG5 :(qi" Cosmos 18561 |GG'  Generalg G\HG#^@") Designation18117 / 87051E\GHA#R6Launch date16 Jun 1987j\H"IM#j:"N , Country of originCIS/HIS#v^"H̀(㓉<MissionTelecommunications (Strela-2)`"IJA#R>"Perigee/Apogee1429/1475 kmTIXJA#R&Inclination74UJJA#R(Period114.9 minlXJKM#j>" &s,梉Launch vehicleCosmos CYJrKA#R0Launch sitePlesetsk$KK" < rKK1 KL Cosmos 1857HKL5 :(qi" Cosmos 18571 KKL'  Generalg LLG#^@") Designation18118 / 87051F\KLMA#R6Launch date16 Jun 1987jLxMM#j:"N , Country of originCIS/MMS#v^"H̀(㓉<MissionTelecommunications (Strela-2)`xMZNA#R>"Perigee/Apogee1414/1475 kmTMNA#R&Inclination74UZNOA#R(Period114.8 minlNoOM#j>" &s,梉Launch vehicleCosmos CYOOA#R0Launch sitePlesetsk$oO " O K< OH1$ HbCosmos 1858H 5 :(qi" Cosmos 18581 H'  Generalg (G#^@") Designation18119 / 87051G\A#R6Launch date16 Jun 1987j(M#j:"N , Country of originCIS/pS#v^"H̀(㓉<MissionTelecommunications (Strela-2)`ЂA#R>"Perigee/Apogee1399/1476 kmTp$A#R&Inclination74UЂyA#R(Period114.6 minl$M#j>" &s,梉Launch vehicleCosmos CYy>A#R0Launch sitePlesetsk$b" < >1H Cosmos 1859Hb5 :(qi" Cosmos 18591 '  Generalg ~G#^@") Designation18120 / 87051H\څA#R6Launch date16 Jun 1987j~DM#j:"N , Country of originCIS/څƆS#v^"H̀(㓉<MissionTelecommunications (Strela-2)`D&A#R>"Perigee/Apogee1385/1474 kmTƆzA#R&Inclination74U&χA#R(Period114.4 minlz;M#j>" &s,梉Launch vehicleCosmos CYχA#R0Launch sitePlesetsk$;" < 1$ <'Cosmos 1860H<5 :(qi" Cosmos 18601 m'  Generalg <ԉG#^@") Designation18122 / 87052A\m0A#R6Launch date18 Jun 1987jԉM#j:"N , Country of originCIS70M#jn"H̀d퉂MissionMilitary: ocean reconnaissance (Rorsat)^|A#R:"Perigee/Apogee900/992 kmTЋA#R&Inclination65S|#A#R$Period104 min\ЋG#^*" &Launch vehicleY#،A#R0Launch sitePlesetskO%'* $Jㅯ\&Equipped with a nuclear reactor< ،c1!H c|Cosmos 1861H'5 :(qi" Cosmos 18611 c܍'  Generalg CG#^@") Designation18129 / 87054A\܍A#R6Launch date23 Jun 1987jC M#j:"N , Country of originCISy&S#vL"H̀(シ 剂MissionNavigation (Tsikada)^ A#R:"Perigee/Apogee996/996 kmVBA#R*B'Inclination82.9UA#R(Period104.9 minlBM#j>" &s,梉Launch vehicleCosmos CY\A#R0Launch sitePlesetsk&# 8\' "(OTechnical data. # Plane 12:"' & Radio Sputnik 10a A#R@beacon/robot29.357 Mhz (cw)a "A#R@beacon/robot29.403 Mhz (cw)q0UA#R` mode a uplink145.860 - 145.900 Mhz (ssb,cw)q0A#R`$mode a downlink29.360 - 29.400 Mhz (ssb,cw)d#U*A#RF"robot a uplink145.820 Mhz (cw)o.A#R\&robot a downlink29.357 or 29.403 Mhz (cw)a *A#R@beacon/robot29.357 Mhz (cw)a [A#R@beacon/robot29.403 Mhz (cw)o.A#R\ mode k uplink21.160 - 21.200 Mhz (ssb,cw)q0[;A#R`$mode k downlink29.360 - 29.400 Mhz (ssb,cw)c"A#RD"robot k uplink21.120 Mhz (cw)o.; A#R\&robot k downlink29.357 or 29.403 Mhz (cw)b!oA#RBbeacon/robot145.857 Mhz (cw)b! A#RBbeacon/robot145.903 Mhz (cw)o.o@A#R\ mode t uplink21.160 - 21.200 Mhz (ssb,cw)s2A#Rd$mode t downlink145.860 - 145.900 Mhz (ssb,cw)c"@A#RD"robot t uplink21.120 Mhz (cw)q0A#R`&robot t downlink145.857 or 145.903 Mhz (cw)&# :' & Radio Sputnik 11a HA#R@beacon/robot29.407 Mhz (cw)a A#R@beacon/robot29.453 Mhz (cw)q0HA#R` mode a uplink145.910 - 145.950 Mhz (ssb,cw)q0A#R`$mode a downlink29.410 - 29.450 Mhz (ssb,cw)d#A#RF"robot a uplink145.830 Mhz (cw)o.^A#R\&robot a downlink29.407 or 29.453 Mhz (cw)a A#R@beacon/robot29.407 Mhz (cw)a ^ A#R@beacon/robot29.453 Mhz (cw)o.A#R\ mode k uplink21.210 - 21.250 Mhz (ssb,cw)q0 A#R`$mode k downlink29.410 - 29.450 Mhz (ssb,cw)c"cA#RD"robot k uplink21.130 Mhz (cw)o.A#R\&robot k downlink29.407 or 29.453 Mhz (cw)b!c4A#RBbeacon/robot145.907 Mhz (cw)b!A#RBbeacon/robot145.953 Mhz (cw)o.4A#R\ mode t uplink21.210 - 21.250 Mhz (ssb,'cw)s2A#Rd$mode t downlink145.910 - 145.950 Mhz (ssb,cw)c"A#RD"robot t uplink21.130 Mhz (cw)q0XA#R`&robot t downlink145.907 or 145.953 Mhz (cw)$|" < X18R Cosmos 1870H|5 :(qi" Cosmos 18701 1'  Generalg G#^@") Designation18225 / 87064A\1A#R6Launch date25 Jul 1987j^M#j:"N , Country of originCIS-S#vZ"H̀(郉"MissionRemote sensing (Almaz-T #2)^^<A#R:"Perigee/Apogee263/278 kmVA#R*Inclination71.9T<A#R&Period89.9 mino"UM#jD" &㉓gLaunch vehicleProton #154^A#R:"Mass at launch15 to 20 tUX% Satellite developped with the United States, France, Finland and Sweden. The SAR module had a resolution of 15 to 30 meters.5'  End of lifeVXA#R*Decay29 Jul 1989$" < C1 C= Cosmos 1887H5 :(qi" Cosmos 1887AC) "0Also called Bion 081 '  Generalg dG#^@") Designation18380 / 87083A\A#R6Launch date29 Sep 1987jd* M#j:"N , Country of originCISU G#^"H̀Mission^* A#R:"Perigee/Apogee214/382 kmV 3 A#R*Inclination62.8T A#R&Period90.5 min\3 G#^*" &Launch vehicleY < A#R0Launch sitePlesetskR. $ \On board: 2 macaques, 10 rats and 6 fishes5< '  End of lifeV  A#R*Decay12 Oct 1987$ = " <  y 1FR y BCosmos 1888H= 5 :(qi" Cosmos 18881 y '  Generalg Y G#^@") Designation18384 / 87084A[ A#R4Launch date1 Oct 1987jY M#j:"N , Country of originCIS6 S#vl"H̀(‰MissionMilitary: telecommunications: Geizerb! A#RB,Geostationary orbitsee belowo"xM#jD" &㉓gLaunch vehicleProton #156& # 2 x'  Locationf@m#:f@=    " BeginEndPosition"@j#D"68L: 1 Oct 1987Aug 199080Ef@{Aj#>,.Sep 1990Dec 199413.5W&@A# 5{AA'  End of life\A2BA#R6"Out of serviceDec 1994&AXB# 82BB' "(Technical data<XBB) "&$Specifications< BC1ā CPCFCosmos 1894HBPC5 :(qi" Cosmos 18941 CC'  Generalg PCCG#^@") Designation18443 / 87091A\CDDA#R6Launch date28 Oct 1987jCDM#j:"N , Country of originCISSDDHEG#^"H̀MissionMilitary: early warning (Oko GEO, also called Prognoz 1st generation)]DEA#R8,Geostationary orbit24Wo"HEFM#jD" &㉓gLaunch vehicleProton #157&E:F# 5FoF'  End of lifeW:FFA#R,"Out of serviceyes$oFF" < F&G1. &GnGkKCosmos 1897HFnG5 :(qi" Cosmos 18971 &GG'  Generalg nGHG#^@") Designation18575 / 87096A\GbHA#R6Launch date26 Nov 1987jHHM#j:"N , Country of originCIS4bHSIS#vh"H̀(‰ᇏMissionMilitary: telecommunications: Luch]HIA#R8,Geostationary orbit95Eo"SIJM#jD" &㉓gLaunch vehicleProton #158&IEJ# 5JzJ'  End of lifeWEJJA#R,"Out of serviceyes&zJJ# 8J/K' "(Technical data<JkK) "&CGSpecifications< /KK1xā KK@Cosmos 1923HkKK5 :(qi" Cosmos 19231 K L'  Generalg KLG#^@") Designation18931 / 88015A\ LLA#R6Launch date10 Mar 1988jLMMM#j:"N , Country of originCISULMG#^"H̀Mission^MMNA#R:"Perigee/Apogee190/302 kmVMVNA#R*Inclination72.9TNNA#R&Period89.4 min\VNOG#^*" &Launch vehicleYN_OA#R0Launch sitePlesetsk&OO# 5_OO'  End of lifeVOA#R*DecaOkKy22 Mar 1988$O@" < |1& |ĀCosmos 1924H@Ā5 :(qi" Cosmos 19241 |'  Generalg Ā\G#^@") Designation18937 / 88016A\A#R6Launch date11 Mar 1988j\"M#j:"N , Country of originCIS/S#v^"H̀(㓉<MissionTelecommunications (Strela-2)`"A#R>"Perigee/Apogee1458/1512 kmTXA#R&Inclination74UA#R(Period115.7 minlXM#j>" &s,梉Launch vehicleCosmos CYrA#R0Launch sitePlesetsk$" < r҄1J ҄Cosmos 1925H5 :(qi" Cosmos 19251 ҄K'  Generalg G#^@") Designation18938 / 88016B\KA#R6Launch date11 Mar 1988jxM#j:"N , Country of originCIS/S#v^"H̀(㓉<MissionTelecommunications (Strela-2)`xZA#R>"Perigee/Apogee1457/1495 kmTA#R&Inclination74UZA#R(Period115.5 minloM#j>" &s,梉Launch vehicleCosmos CYȈA#R0Launch sitePlesetsk$o" < Ȉ(1&n (pBCosmos 1926Hp5 :(qi" Cosmos 19261 ('  Generalg pG#^@") Designation18939 / 88016C\dA#R6Launch date11 Mar 1988jΊM#j:"N , Country of originCIS/dPS#v^"H̀(㓉<MissionTelecommunications (Strela-2)`ΊA#R>"Perigee/Apogee1458/1477 kmTPA#R&Inclination74UYA#R(Period115.3 minlŌM#j>" &s,梉Launch vehicleCosmos CYYA#R0Launch sitePlesetsk$ŌB" < ~1J` ~ƍCosmos 1927HBƍ5 :(qi" Cosmos 19271 ~'  Generalg ƍ^G#^@") Designation18940 / 88016D\A#R6Launch date11 Mar 1988j^$M#j:"N , Country of originCIS/S#v^"H̀(㓉<MissionTelecommunications (Strela-2)`$A#R>"Perigee/Apogee1452/146B5 kmTfA#R&Inclination74UA#R(Period115.1 minlf'M#j>" &s,梉Launch vehicleCosmos CYA#R0Launch sitePlesetsk$'" < 1n (Cosmos 1928H(5 :(qi" Cosmos 19281 Y'  Generalg (G#^@") Designation18941 / 88016E\YA#R6Launch date11 Mar 1988jM#j:"N , Country of originCIS/S#v^"H̀(㓉<MissionTelecommunications (Strela-2)`hA#R>"Perigee/Apogee1442/1459 kmTA#R&Inclination74UhA#R(Period114.9 minl}M#j>" &s,梉Launch vehicleCosmos CYA#R0Launch sitePlesetsk$}" < 61` 6~PCosmos 1929H~5 :(qi" Cosmos 19291 6'  Generalg ~G#^@") Designation18942 / 88016F\rA#R6Launch date11 Mar 1988jM#j:"N , Country of originCIS/r^S#v^"H̀(㓉<MissionTelecommunications (Strela-2)`A#R>"Perigee/Apogee1426/1459 kmT^A#R&Inclination74UgA#R(Period114.7 minlM#j>" &s,梉Launch vehicleCosmos CYg,A#R0Launch sitePlesetsk$P" < ,1̃ Cosmos 1930HP5 :(qi" Cosmos 19301 '  Generalg lG#^@") Designation18943 / 88016G\A#R6Launch date11 Mar 1988jl2M#j:"N , Country of originCIS/S#v^"H̀(㓉<MissionTelecommunications (Strela-2)`2A#R>"Perigee/Apogee1412/1458 kmThA#R&Inclination74UA#R(Period114.6 minlh)M#j>" &s,梉Launch vehicleCosmos CYA#R0Launch sitePlesetsk$)" < 1 *Cosmos 1931H*5 :(qi" Cosmos 19311 ['  Generalg *G#^@") Designation18944 / 88016H\[*A#R6*Launch date11 Mar 1988jM#j:"N , Country of originCIS/*S#v^"H̀(㓉<MissionTelecommunications (Strela-2)`vA#R>"Perigee/Apogee1395/1459 kmTA#R&Inclination74UvA#R(Period114.4 minlM#j>" &s,梉Launch vehicleCosmos CYA#R0Launch sitePlesetsk$" < D1̃> D4Cosmos 1932H5 :(qi" Cosmos 19321 D'  Generalg $G#^@") Designation18957 / 88019A\A#R6Launch date14 Mar 1988j$M#j:"N , Country of originCIS7nM#jn"H̀d퉂MissionMilitary: ocean reconnaissance (Rorsat)_A#R<"Perigee/Apogee921/1007 kmTn!A#R&Inclination65UvA#R(Period104.4 min\!G#^*" &Launch vehicleYv+A#R0Launch siteTyuratam&Q# 5+'  End of life_QA#R<"Out of service20 May 1988O%4* $Jㅯ\&Equipped with a nuclear reactor< p1I p* Cosmos 1933H45 :(qi" Cosmos 19331 p'  Generalg P G#^@") Designation18958 / 88020A\ A#R6Launch date15 Mar 1988jP  M#j:"N , Country of originCISy, M#jX"H̀_剂MissionMilitary: SIGINT (Tselina-D)^ A#R:"Perigee/Apogee605/628 kmV C A#R*Inclination82.5R A#R"Period97 minq$C  M#jH" &ቂLaunch vehicleCyclone 3 #67$ * " <  f 1>B f >ACosmos 1934H* 5 :(qi" Cosmos 19341 f '  Generalg F G#^@") Designation18985 / 88023A\ A#R6Launch date22 Mar 1988jF M#j:"N , Country of originCIS. S#v\"H̀(シ㼨ԟMissionMilitary: Navigation (Parus)_ A#R<"Perigee/Apogee946/1005 kmT@A#R&Inclination83UA#R(Period104.6 minl@ @M#j>" &s,梉Launch vehicleCosmos C @* Yf@A#R0Launch sitePlesetsk& @@# 5f@@'  End of lifeW@AA#R,"Out of serviceyes&@>A# < AzA1Iu zAAFCosmos 1935H>AA5 :(qi" Cosmos 19351 zAA'  Generalg AZBG#^@") Designation19011 / 88025A\ABA#R6Launch date24 Mar 1988jZB CM#j:"N , Country of originCISm&BCG#^L"H̀MissionMilitary: reconnaissance^ CCA#R:"Perigee/Apogee179/356 kmTC?DA#R&Inclination67TCDA#R&Period89.5 min\?DDG#^*" &Launch vehicleYDHEA#R0Launch sitePlesetsk&DnE# 5HEE'  End of lifeUnEEA#R(Decay8 Apr 1988$EF" < EXF1B XFFKCosmos 1957HFF5 :(qi" Cosmos 19571 XFF'  Generalg F8GG#^@") Designation19276 / 88057A[FGA#R4Launch date7 Jul 1988j8GGM#j:"N , Country of originCISm&GjHG#^L"H̀MissionMilitary: reconnaissance^GHA#R:"Perigee/Apogee179/225 kmVjHIA#R*Inclination82.6THrIA#R&Period88.5 minbIIG#^6" &Launch vehicleSoyouzYrI-JA#R0Launch sitePlesetsk&ISJ# 5-JJ'  End of lifeVSJJA#R*Decay21 Jul 1988$JK" < J>K1u >KK Cosmos 1958HKK5 :(qi" Cosmos 19581 >KK'  Generalg KLG#^@") Designation19320 / 88060A\KzLA#R6Launch date14 Jul 1988jLLM#j:"N , Country of originCIS_zLCMG#^0"H̀MissionMilitary: ^LMA#R:"Perigee/Apogee360/411 kmVCMMA#R*Inclination65.8TMKNA#R&Period92.3 minlMNM#j>" &s,梉Launch vehicleCosmos CYKNOA#R0Launch sitePlesetsk&N6O# 5OkO'  End of lifeV6OOA#R*Decay21 Mar 1969$kO " O K< OH1J HCosmos 1959H 5 :(qi" Cosmos 19591 H'  Generalg (G#^@") Designation19324 / 88062A\A#R6Launch date18 Jul 1988j(M#j:"N , Country of originCIS.oS#v\"H̀(シ㼨ԟMissionMilitary: Navigation (Parus)_΂A#R<"Perigee/Apogee952/1002 kmTo"A#R&Inclination83U΂wA#R(Period104.6 minl"M#j>" &s,梉Launch vehicleCosmos CYw<A#R0Launch sitePlesetsk&b# 5<'  End of lifeWbA#R,"Out of serviceyes&# < P1w PCosmos 1960H5 :(qi" Cosmos 19601 PɅ'  Generalg 0G#^@") Designation19338 / 88065A\ɅA#R6Launch date28 Jul 1988j0M#j:"N , Country of originCIS]SG#^,"H̀MissionMilitary^A#R:"Perigee/Apogee369/379 kmVSA#R*Inclination65.8RYA#R"Period92 minlňM#j>" &s,梉Launch vehicleCosmos CYYA#R0Launch sitePlesetsk&ňD# 5y'  End of lifeUDΉA#R(Decay9 Apr 1990$y" < Ή.1-J$ .vCosmos 1961Hv5 :(qi" Cosmos 19611 .'  Generalg vG#^@") Designation19344 / 88066A[iA#R4Launch date1 Aug 1988jӋM#j:"N , Country of originCIS6i\S#vl"H̀(‰MissionMilitary: Telecommunications: Geizerb!ӋA#RB,Geostationary orbitsee belowo"\-M#jD" &㉓gLaunch vehicleProton #169&S# : -- */ۀ LocationvS^#0 BeginEndPosition$j#H"68L: 1 Aug 1988Mar 199213.5Wj#8,.Apr 1992mid 19930E&=# 5r'  End of life\=ΏA#R6"Out of servicemid 1993&r # Ώ 8ΏD' "(Technical data< ) "&$Specifications< D1w\ cCosmos 1962H5 :(qi" Cosmos 19621 5'  Generalg G#^@") Designation19372 / 88068A[5A#R4Launch date8 Aug 1988jaM#j:"N , Country of originCISm&G#^L"H̀MissionMilitary: reconnaissance^a,A#R:"Perigee/Apogee205/265 kmTA#R&Inclination70T,A#R&Period89.2 mina5G#^4" &Launch vehicleSL 16YA#R0Launch siteTyuratam&5# 5'  End of lifeV?A#R*Decay22 Aug 1988$c" < ?1$ ICosmos 1963Hc5 :(qi" Cosmos 19631 '  Generalg G#^@") Designation19384 / 88070A\A#R6Launch date16 Aug 1988jEM#j:"N , Country of originCISm&G#^L"H̀MissionMilitary: reconnaissance^EA#R:"Perigee/Apogee176/350 kmVfA#R*Inclination64.8TA#R&Period89.8 minbfG#^6" &Launch vehicleSoyouzYuA#R0Launch sitePlesetsk&# 5u'  End of lifeU%A#R(Decay2 Oct 1988$I" < %1\Ѓ -Cosmos 1964HI5 :(qi" Cosmos 19641 '  Generalg eG#^@") Designation19412 / 88072A\A#R6Launch date23 Aug 1988je+M#j:"N , Country of originCISm&G#^L"H̀MissionMilitary: reconnaissance^+A#R:"Perigee/Apogee206/271 kmTJA#R&Inclination70TA#R&Period89.3 minbJG#^6" &Launch vehicleSoyouzYYA#R0Launch siteTyuratam&# 5Y'  End of lifeU A#R(Decay7 Sep 1988$-" < i1( iHCosmos 1965H-5 :(qi" Cosmos 19651 i '  General -g sG#^@") Designation19414 / 88073A\ A#R6Launch date23 Aug 1988js9M#j:"N , Country of originCISw0G#^`"H̀MissionMilitary: remote sensing (Priroda)^9A#R:"Perigee/Apogee179/228 kmVdA#R*Inclination82.3TA#R&Period88.6 minbdG#^6" &Launch vehicleSoyouzYsA#R0Launch sitePlesetsk&# 5s'  End of lifeV$A#R*Decay22 Sep 1988$H" < $1ЃO Cosmos 1966HH5 :(qi" Cosmos 19661 '  Generalg dG#^@") Designation19445 / 88076A\A#R6Launch date30 Aug 1988jd*M#j:"N , Country of originCIS9G#^r"H̀MissionMilitary: telecommunications (experimental)a * A#R@"Perigee/Apogee2592/37777 kmVaA#R*Inclination67.4U A#R(Period718.1 min\aG#^*" &Launch vehicleYkA#R0Launch sitePlesetsk$" < k1(  u Cosmos 1967H 5 :(qi" Cosmos 19671 D '  Generalg  G#^@") Designation19462 / 88079A[D  A#R4Launch date6 Sep 1988j p M#j:"N , Country of originCISm& G#^L"H̀MissionMilitary: reconnaissance^p ; A#R:"Perigee/Apogee191/380 kmV A#R*Inclination72.9T; A#R&Period90.2 minb G G#^6" &Launch vehicleSoyouzY A#R0Launch sitePlesetsk&G # 5 '  End of lifeV Q A#R*Decay15 Sep 1988$ u " < Q 1O gBCosmos 1968Hu 5 :(qi" Cosmos 19681 *'  Generalg G#^@") Designation19488 / 88082A[*A#R4Launch date9 Sep 1988jVM#j:"N , Country of originCISm&G#^L"H̀MissionMilitary: remote sensing^V-@A#R:"-@u Perigee/Apogee177/230 kmV@A#R*Inclination82.3T-@@A#R&Period88.6 minb@9AG#^6" &Launch vehicleSoyouzY@AA#R0Launch sitePlesetsk&9AA# 5AA'  End of lifeVACBA#R*Decay23 Sep 1988$AgB" < CBB1 BBNGCosmos 1969HgBB5 :(qi" Cosmos 19691 BC'  Generalg BCG#^@") Designation19495 / 88084A\CCA#R6Launch date15 Sep 1988jCIDM#j:"N , Country of originCISm&CDG#^L"H̀MissionMilitary: reconnaissance^IDEA#R:"Perigee/Apogee165/344 kmVDjEA#R*Inclination67.1TEEA#R&Period89.6 minbjE FG#^6" &Launch vehicleSoyouzYEyFA#R0Launch sitePlesetsk& FF# 5yFF'  End of lifeVF*GA#R*Decay13 Nov 1988$FNG" < *GG1Ƃ GG@KCosmos 1970HNGG5 :(qi" Cosmos 19701 GH'  Generalg GjHG#^@") Designation19501 / 88085A\HHA#R6Launch date16 Sep 1988jjH0IM#j:"N , Country of originCISp#HIM#jF"H̀シMissionNavigation (Uragan)b!0IJA#RB"Perigee/Apogee19099/19159 kmVIXJA#R*Inclination65.7UJJA#R(Period675.7 mino"XJKM#jD" &㉓gLaunch vehicleProton #171$J@K" < K|K1̃ |KK1OCosmos 1971H@KK5 :(qi" Cosmos 19711 |KK'  Generalg K\LG#^@") Designation19502 / 88085B\KLA#R6Launch date16 Sep 1988j\L"MM#j:"N , Country of originCISp#LMM#jF"H̀シMissionNavigation (Uragan)b!"MMA#RB"Perigee/Apogee19099/19159 kmVMJNA#R*Inclination65.7TMNA#R&Period675.7 kmo"JN OM#jD" &㉓gLaunch vehicleProton #171$N1O" < OmO1Ƃ mOOICosmos 1972H1OO5 :(qi" Cosmos 19721 mO '  GeneralO 1Og OsG#^@") Designation19503 / 88085C\ πA#R6Launch date16 Sep 1988js9M#j:"N , Country of originCISp#πM#jF"H̀シMissionNavigation (Uragan)b!9 A#RB"Perigee/Apogee19113/19145 kmVaA#R*Inclination65.7U A#R(Period675.7 mino"a%M#jD" &㉓gLaunch vehicleProton #171$I" < %1̃# ̓.Cosmos 1973HI̓5 :(qi" Cosmos 19731 '  Generalg ̓eG#^@") Designation19521 / 88088A\A#R6Launch date22 Sep 1988je+M#j:"N , Country of originCISm&G#^L"H̀MissionMilitary: reconnaissance^+A#R:"Perigee/Apogee192/359 kmVLA#R*Inclination72.8RA#R"Period90 minbLG#^6" &Launch vehicleSoyouzYYA#R0Launch sitePlesetsk&# 5Y'  End of lifeV A#R*Decay10 Oct 1988$." < j16 jaCosmos 1974H.5 :(qi" Cosmos 19741 j'  Generalg JG#^@") Designation19554 / 88092A[A#R4Launch date3 Oct 1988jJM#j:"N , Country of originCISfuG#^>"H̀MissionMilitary: warninga ֊A#R@"Perigee/Apogee3323/37025 kmVu,A#R*Inclination64.7U֊A#R(Period717.7 mind,G#^:" &Launch vehiclePlesetskX=A#R.Launch siteMolniya$a" < =1# eCosmos 1975Ha5 :(qi" Cosmos 19751 '  Generalg }G#^@") Designation19573 / 88093A\ٍA#R6Launch date11 Oct 1988j}CM#j:"N , Country of originCISy,ٍM#jX"H̀_剂MissionMilitary: SIGINT (Tselina-D)^CA#R:"Perigee/Apogee604/634 kmVpA#R*Inclination82.5TďA#R&Period97.1 minq$pAM#jH" ďAa&ቂLaunch vehicleCyclone 3 #72$ďe" < A16> LCosmos 1976He5 :(qi" Cosmos 19761 '  Generalg G#^@") Designation19582 / 88094A\A#R6Launch date13 Oct 1988jGM#j:"N , Country of originCISm&G#^L"H̀MissionMilitary: reconnaissance^GA#R:"Perigee/Apogee190/366 kmVhA#R*Inclination72.9TA#R&Period90.1 minbhG#^6" &Launch vehicleSoyouzYwA#R0Launch sitePlesetsk&# 5w'  End of lifeV(A#R*Decay27 Oct 1988$L" < (1Y Cosmos 1977HL5 :(qi" Cosmos 19771 '  Generalg hG#^@") Designation19608 / 88096A\A#R6Launch date25 Oct 1988jh.M#j:"N , Country of originCISm&G#^L"H̀MissionMilitary: reconnaissancea .A#R@"Perigee/Apogee3263/37085 kmVRA#R*Inclination64.7UA#R(Period717.7 mincR G#^8" &Launch vehicleMolniyaYcA#R0Launch sitePlesetsk$ " < c1> nCosmos 1978H 5 :(qi" Cosmos 19781 <'  Generalg G#^@") Designation19612 / 88097A\<A#R6Launch date27 Oct 1988jiM#j:"N , Country of originCISm&G#^L"H̀MissionMilitary: reconnaissance^i4A#R:"Perigee/Apogee190/364 kmVA#R*Inclination72.9T4A#R&Period90.1 minb@G#^6" &Launch vehicleSoyouzYA#R0Launch sitePlesetsk&@# 5'  End of lifeVJA#R*Decay10 Nov 1988$n" < J1Y cCosmos 1979Hn5 :(qi" Cosmos 19791 #'  Generalg G#^@") Designation19647 / 88101A\# A#R6Launch date18 Nov 1988 njvM#j:"N , Country of originCIS] G#^,"H̀MissionMilitary^v1A#R:"Perigee/Apogee402/415 kmTA#R&Inclination65T1A#R&Period92.7 min\5G#^*" &Launch vehicleYA#R0Launch siteTyuratam&5# 5'  End of lifeV?A#R*Decay25 Dec 1989$c" < ?1 RCosmos 1980Hc5 :(qi" Cosmos 19801 '  Generalg G#^@") Designation19649 / 88102A\A#R6Launch date23 Nov 1988jEM#j:"N , Country of originCISy,M#jX"H̀_剂MissionMilitary: SIGINT (Tselina-2)^EA#R:"Perigee/Apogee840/850 kmTpA#R&Inclination71UA#R(Period101.8 minip.M#j8" &'CMLaunch vehicleZenit$R" < .1 D Cosmos 1982HR5 :(qi" Cosmos 19821 '  Generalg nG#^@") Designation19662 / 88105A\A#R6Launch date30 Nov 1988jn4 M#j:"N , Country of originCISy2 G#^d"H̀MissionMilitary: photography reconnaissance^4 A#R:"Perigee/Apogee204/377 kmT _ A#R&Inclination70T A#R&Period90.3 minc_  G#^8" &Launch vehicleSoyouz Y o A#R0Launch sitePlesetsk& # 5o '  End of lifeV A#R*Decay14 Dec 1988$ D " < 1@ :ACosmos 1983HD 5 :(qi" Cosmos 19831 '  Generalg ` G#^@") Designation19672 / 88107A[ A#R4Launch date8 Dec 1988j` %M#j:"N , Country of originCISm& G#^L"H̀MissionMilitary: reconnaissance^%A#R:"Perigee/Apogee243/256 kmVFA#R*Inclination62.8TA#R&Period89.5 minbF @G#^6" &Launch vehicleSoyouz @D Ye@A#R0Launch sitePlesetsk& @@# 5e@@'  End of lifeV@AA#R*Decay22 Dec 1988$@:A" < AvA1| vAA!FCosmos 1984H:AA5 :(qi" Cosmos 19841 vAA'  Generalg AVBG#^@") Designation19705 / 88110A\ABA#R6Launch date16 Dec 1988jVBCM#j:"N , Country of originCISm&BCG#^L"H̀MissionMilitary: reconnaissance^CCA#R:"Perigee/Apogee186/323 kmVC=DA#R*Inclination62.8TCDA#R&Period89.6 minb=DDG#^6" &Launch vehicleSoyouzYDLEA#R0Launch sitePlesetsk&DrE# 5LEE'  End of lifeVrEEA#R*Decay13 Feb 1989$E!F" < E]F1e@ ]FFJCosmos 1985H!FF5 :(qi" Cosmos 19851 ]FF'  Generalg F=GG#^@") Designation19720 / 88113A\FGA#R6Launch date23 Dec 1988j=GHM#j:"N , Country of originCIS<GHM#jx"H̀ MissionMilitary: radar calibration (Radar-Cal-2 #1)^HHA#R:"Perigee/Apogee206/220 kmVH@IA#R*Inclination73.5THIA#R&Period88.8 minq$@IJM#jH" &ቂLaunch vehicleCyclone 3 #73&I+J# 5J`J'  End of lifeU+JJA#R(Decay4 May 1992$`JJ" < JK1| K]KOCosmos 1986HJ]K5 :(qi" Cosmos 19861 KK'  Generalg ]KKG#^@") Designation19734 / 88116A\KQLA#R6Launch date29 Dec 1988jKLM#j:"N , Country of originCISj#QL%MG#^F"H̀MissionMilitary: observation^LMA#R:"Perigee/Apogee193/289 kmV%MMA#R*Inclination64.8TM-NA#R&Period89.3 minbMNG#^6" &Launch vehicleSoyouzY-NNA#R0Launch siteTyuratam&NO# 5NCO'  End of lifeVOOA#R*Decay11 Feb 1989$COO" < O 1I TCosmos 1987O OHOT5 :(qi" Cosmos 1987D ) "6Also called Glonass 401 Tɀ'  Generalg 0G#^@") Designation19749 / 89001A\ɀA#R6Launch date10 Jan 1989j0M#j:"N , Country of originCISp#fM#jF"H̀シMissionNavigation (Uragan)b!ȂA#RB"Perigee/Apogee19113/19145 kmVfA#R*Inclination64.9UȂsA#R(Period675.7 mino"M#jD" &㉓gLaunch vehicleProton #174&s# 5='  End of lifeWA#R,"Out of serviceyes$=" < 1 <Cosmos 1988H<5 :(qi" Cosmos 1988D) "6Also called Glonass 411 <'  Generalg G#^@") Designation19750 / 89001B\tA#R6Launch date10 Jan 1989jކM#j:"N , Country of originCISp#tNM#jF"H̀シMissionNavigation (Uragan)b!ކA#RB"Perigee/Apogee19111/19147 kmTNA#R&Inclination65UYA#R(Period675.7 mino"ȈM#jD" &㉓gLaunch vehicleProton #174&Y# 5Ȉ#'  End of lifeWzA#R,"Out of serviceyes$#" < zډ1I ډ"Cosmos 1989H"5 :(qi" Cosmos 19891 ډS'  Generalg "G#^@") Designation19751 / 89001C\SA#R6Launch date10 Jan 1989jM#j:"N , Country of originCISs&M#jL"H̀シMissionNavigation (Etalon #1)b!UA#RB"Perigee/Apogee19097/19152 kmVA#R*Inclination64.9UUA#R(Period675.5 mino"oM#jD" &㉓gLaunch vehicleProton #174$" < oύ1 ύCosmos 1990H5 :(qi" Cosmos 19901 ύH'  Generalg G#^@") Designation19756 / 89002A\H A#R6Launch date12 Jan 1989juM#j:"N , Country of originCISw0 G#^`"H̀MissionMilitary: remote sensing (Priroda)u ^ujA#R:"Perigee/Apogee177/227 kmV A#R*Inclination82.6TjA#R&Period88.5 minbvG#^6" &Launch vehicleSoyouzYA#R0Launch sitePlesetsk&v# 5*'  End of lifeVA#R*Decay11 Feb 1989$*" < 1 (Cosmos 1991H(5 :(qi" Cosmos 19911 Y'  Generalg (G#^@") Designation19758 / 89003A\YA#R6Launch date18 Jan 1989jM#j:"N , Country of originCISw0G#^`"H̀MissionMilitary: remote sensing (Priroda)^[A#R:"Perigee/Apogee204/375 kmTA#R&Inclination70T[A#R&Period90.3 minbeG#^6" &Launch vehicleSoyouzYA#R0Launch siteTyuratam&e# 5'  End of lifeUnA#R(Decay1 Feb 1989$" < n1 Cosmos 1992H5 :(qi" Cosmos 19921 G'  Generalg G#^@") Designation19769 / 89005A\G A#R6Launch date26 Jan 1989jtM#j:"N , Country of originCIS/ S#v^"H̀(㓉<MissionTelecommunications (Strela-1)^tTA#R:"Perigee/Apogee764/798 kmTA#R&Inclination74UTA#R(Period100.5 minliM#j>" &s,梉Launch vehicleCosmos CYA#R0Launch sitePlesetsk$i" < "1( "jCosmos 1993Hj5 :(qi" Cosmos 19931 "'  Generalg jG#^@") Designation19774 / 89007A\^A#R6Launch date28 Jan 1989jM#j:"N , Country of originCISm&^5G#^L"H̀MissionMilitary: reconnaissance^A#R:"Perigee/Apogee171/347 kmV5A#R*Inclination64.8T=A#R&Period89.7 minbG#^6" &Launch vehicleSoyouzY= A#R0Launch siteTyuratam &2# 5 g'  End of lifeV2A#R*Decay27 Mar 1989$g" < 1; eCosmos 1994He5 :(qi" Cosmos 19941 '  Generalg eG#^@") Designation19785 / 89009A\YA#R6Launch date10 Feb 1989jM#j:"N , Country of originCIS/YES#v^"H̀(㓉<MissionTelecommunications (Strela-3)`A#R>"Perigee/Apogee1391/1414 kmVEA#R*Inclination82.6UPA#R(Period113.9 minq$M#jH" &ቂLaunch vehicleCyclone 3 #74$P" < !1(N !iCosmos 1995Hi5 :(qi" Cosmos 19951 !'  Generalg iG#^@") Designation19786 / 89009B\]A#R6Launch date10 Feb 1989jM#j:"N , Country of originCIS/]IS#v^"H̀(㓉<MissionTelecommunications (Strela-3)`A#R>"Perigee/Apogee1409/1415 kmVIA#R*Inclination82.6UTA#R(Period114.1 minq$M#jH" &ቂLaunch vehicleCyclone 3 #74$T" < % 1;_ % m Cosmos 1996Hm 5 :(qi" Cosmos 19961 % '  Generalg m  G#^@") Designation19787 / 89009C\ a A#R6Launch date10 Feb 1989j M#j:"N , Country of originCIS/a M S#v^"H̀(㓉<MissionTelecommunications (Strela-3)` A#R>"Perigee/Apogee1403/1414 kmVM  A#R*Inclination82.6S V A#R$Period114 minq$ M#jH" &ቂLaunch vehicleCyclone 3 #74$V " < ' 1N: ' o @Cosmos 1997H o 5 :(qi" Cosmos 19971 ' '  Generalg o G#^@") Designation19788 / 89009D\ cA#R6Launch date10 Feb 1989jM#j:"N , Country of originCIS/cOS#v^"H̀(㓉<MissionTelecommunications (Strela-3)`A#R>"Perigee/Apogee1397/1414 kmVO@A#R*Inclination82@ .6Uf@A#R(Period113.9 minq$@@M#jH" &ቂLaunch vehicleCyclone 3 #74$f@@" < @7A1_M 7AADCosmos 1998H@A5 :(qi" Cosmos 19981 7AA'  Generalg ABG#^@") Designation19789 / 89009E\AsBA#R6Launch date10 Feb 1989jBBM#j:"N , Country of originCIS/sB_CS#v^"H̀(㓉<MissionTelecommunications (Strela-3)`BCA#R>"Perigee/Apogee1387/1414 kmV_CDA#R*Inclination82.6UCjDA#R(Period113.8 minq$DDM#jH" &ቂLaunch vehicleCyclone 3 #74$jDD" < D;E1:` ;EEICosmos 1999HDE5 :(qi" Cosmos 19991 ;EE'  Generalg EFG#^@") Designation19790 / 89009F\EwFA#R6Launch date10 Feb 1989jFFM#j:"N , Country of originCIS/wFcGS#v^"H̀(㓉<MissionTelecommunications (Strela-3)`FGA#R>"Perigee/Apogee1381/1414 kmVcGHA#R*Inclination82.6UGnHA#R(Period113.7 minq$HHM#jH" &ቂLaunch vehicleCyclone 3 #74$nHI" < H?I1M ?IIMCosmos 2000HII5 :(qi" Cosmos 20001 ?II'  Generalg IJG#^@") Designation19792 / 89010A\I{JA#R6Launch date10 Feb 1989jJJM#j:"N , Country of originCIS`{JEKG#^2"H̀MissionMilitary: ?^JKA#R:"Perigee/Apogee175/243 kmVEKKA#R*Inclination82.3TKMLA#R&Period88.7 mindKLG#^:" &Launch vehicleCyclone?ZML MA#R2Launch sitePlesetsk?&L1M# 5 MfM'  End of lifeU1MMA#R(Decay2 Mar 1989$fMM" < MN1`} NcNCosmos 2001HMcN5 :(qi" Cosmos 20011 NN'  Generalg cNNG#^@") Designation19796 / 89011A\NWOA#R6Launch date14 Feb 1989jNOM#j:"N , Country of originCISfWO3G#^>"H̀O3MMissionMilitary: warninga OA#R@"Perigee/Apogee2437/37977 kmV3A#R*Inclination66.5S=A#R$Period719 mincG#^8" &Launch vehicleMolniyaY=A#R0Launch sitePlesetsk$" < Y1 YCosmos 2002H5 :(qi" Cosmos 20021 Y҂'  Generalg 9G#^@") Designation19800 / 89012A\҂A#R6Launch date14 Feb 1989j9M#j:"N , Country of originCISp)oG#^R"H̀MissionMilitary: radar calibration_΄A#R<"Perigee/Apogee179/1525 kmVo$A#R*Inclination65.8S΄wA#R$Period102 minl$M#j>" &s,梉Launch vehicleCosmos CYw<A#R0Launch sitePlesetsk&b# 5<'  End of lifeVbA#R*Decay15 Oct 1989$" < M1} MCosmos 2003H5 :(qi" Cosmos 20031 MƇ'  Generalg -G#^@") Designation19818 / 89015A\ƇA#R6Launch date17 Feb 1989j-M#j:"N , Country of originCISm&`G#^L"H̀MissionMilitary: reconnaissance^A#R:"Perigee/Apogee244/255 kmV`A#R*Inclination62.8ThA#R&Period89.5 minbʊG#^6" &Launch vehicleSoyouzYh#A#R0Launch sitePlesetsk&ʊI# 5#~'  End of lifeUIӋA#R(Decay3 Mar 1989$~" < Ӌ31h6 3{Cosmos 2004H{5 :(qi" Cosmos 20041 3'  Generalg {G#^@") Designation19826 / 89017A\oA#R6Launch date22 Feb 1989jٍM#j:"N , Country of originCISgo@M#j4"H̀シMissionNavigation_ٍA#R<"Perigee/Apogee968/1015 kmV@A#R*Inclination82.9UJA#R(Period104.9 minlM#j>" &s,梉Launch vehicleCosmos CYJA#R0Launch sitePlesetsk&A# 8y' "(OTechnical dataE"A# DDownlink frequency: 149.940 MHz< y1q BCosmos 2005HB5 :(qi" Cosmos 20051 s'  Generalg BG#^@") Designation19862 / 89019A[s5A#R4Launch date2 Mar 1989jM#j:"N , Country of originCISm&5 G#^L"H̀MissionMilitary: reconnaissance^jA#R:"Perigee/Apogee188/324 kmV A#R*Inclination62.8TjA#R&Period89.6 minbvG#^6" &Launch vehicleSoyouzYA#R0Launch sitePlesetsk&v# 5*'  End of lifeVA#R*Decay25 Apr 1989$*" < 16 (Cosmos 2006H(5 :(qi" Cosmos 20061 Y'  Generalg (G#^@") Designation19893 / 89022A\YA#R6Launch date16 Mar 1989jM#j:"N , Country of originCISj#G#^F"H̀MissionMilitary: observation^NA#R:"Perigee/Apogee240/380 kmVA#R*Inclination62.8TNA#R&Period90.7 minbZG#^6" &Launch vehicleSoyouzYA#R0Launch sitePlesetsk&Z# 5'  End of lifeVdA#R*Decay31 Mar 1989$" < d1q Cosmos 2007H 5 :(qi" Cosmos 20071 ='  Generalg G#^@") Designation19900 / 89024A\=A#R6Launch date23 Mar 1989jjM#j:"N , Country of originCIS~7G#^n"H̀MissionMilitary: reconnaissance (5th generation)^jFA#R:"Perigee/Apogee224/262 kmVA#R*Inclination64.7TFA#R&Period89.4 minbRG#^6" &Launch vehicleSoyouzYA#R0Launch sitePlesetsk&R# 5'  End of lifeV\A#R*Decay22 Sep 1989$" < \1 Cosmos 2008H5 :(qi" Cosmos 20081 A'  Generalg G#^@") Designation19902 / 89025A\AA#R6Launch date24 Mar 1989jnM#j:"N , Country of originCIS/S#v^"H̀(㓉<MissionTelecommunications (Strela-2)`nPA#R>"Perigee/Apogee1391/1469 kmTA#R&Inclination74UPA#R(Period114.4 minleM#j>" &s,梉Launch vehicleCosmos CYA#R0Launch sitePlesetsk$e" < 14 f8Cosmos 2009Hf5 :(qi" Cosmos 20091 '  Generalg fG#^@") Designation19903 / 89025B\ZA#R6Launch date24 Mar 1989jM#j:"N , Country of originCIS/ZFS#v^"H̀(㓉<MissionTelecommunications (Strela-2)`A#R>"Perigee/Apogee1406/1470 kmTFA#R&Inclination74UOA#R(Period114.6 minlM#j>" &s,梉Launch vehicleCosmos CYOA#R0Launch sitePlesetsk$8" < t1X t Cosmos 2010H85 :(qi" Cosmos 20101 t'  Generalg T G#^@") Designation19904 / 89025C\ A#R6Launch date24 Mar 1989jT  M#j:"N , Country of originCIS/ S#v^"H̀(㓉<MissionTelecommunications (Strela-2)` A#R>"Perigee/Apogee1421/1470 kmT P A#R&Inclination74U A#R(Period114.8 minlP  M#j>" &s,梉Launch vehicleCosmos CY j A#R0Launch sitePlesetsk$ " < j 149  @Cosmos 2011H  5 :(qi" Cosmos 20111 C '  Generalg  G#^@") Designation19905 / 89025D\C A#R6Launch date24 Mar 1989j pM#j:"N , Country of originCIS/S#v^"H̀(㓉<MissionTelecommunications (Strela-2)`pRA#R>"Perigee/Apogee1437/1470 kmTA#R&Inclination74SR @A#R$Period115 min @ lx@M#j>" &s,梉Launch vehicleCosmos CY @@A#R0Launch sitePlesetsk$x@@" < @1A1X] 1AyAKECosmos 2012H@yA5 :(qi" Cosmos 20121 1AA'  Generalg yABG#^@") Designation19906 / 89025E\AmBA#R6Launch date24 Mar 1989jBBM#j:"N , Country of originCIS/mBYCS#v^"H̀(㓉<MissionTelecommunications (Strela-2)`BCA#R>"Perigee/Apogee1453/1470 kmTYC DA#R&Inclination74UCbDA#R(Period115.1 minl DDM#j>" &s,梉Launch vehicleCosmos CYbD'EA#R0Launch sitePlesetsk$DKE" < 'EE19 EEICosmos 2013HKEE5 :(qi" Cosmos 20131 EF'  Generalg EgFG#^@") Designation19907 / 89025F\FFA#R6Launch date24 Mar 1989jgF-GM#j:"N , Country of originCIS/FGS#v^"H̀(㓉<MissionTelecommunications (Strela-2)`-GHA#R>"Perigee/Apogee1462/1478 kmTGcHA#R&Inclination74UHHA#R(Period115.3 minlcH$IM#j>" &s,梉Launch vehicleCosmos CYH}IA#R0Launch sitePlesetsk$$II" < }II1] I%JMCosmos 2014HI%J5 :(qi" Cosmos 20141 IVJ'  Generalg %JJG#^@") Designation19908 / 89025G\VJKA#R6Launch date24 Mar 1989jJKM#j:"N , Country of originCIS/KLS#v^"H̀(㓉<MissionTelecommunications (Strela-2)`KeLA#R>"Perigee/Apogee1469/1487 kmTLLA#R&Inclination74UeLMA#R(Period115.5 minlLzMM#j>" &s,梉Launch vehicleCosmos CYMMA#R0Launch sitePlestesk$zMM" < M3N1' 3N{NYCosmos 2015HM{N5 :(qi" Cosmos 20151 3NN'  Generalg {NOG#^@") Designation19909 / 89025H\NoOA#R6Launch date24 Mar 1989jOOM#j:"N , Country of originCIS/oOgS#v^"OgMH̀(㓉<MissionTelecommunications (Strela-2)`OǀA#R>"Perigee/Apogee1467/1507 kmTgA#R&Inclination74UǀpA#R(Period115.7 minl܁M#j>" &s,梉Launch vehicleCosmos CYp5A#R0Launch sitePlesetsk$܁Y" < 51 ݂Cosmos 2016HY݂5 :(qi" Cosmos 20161 '  Generalg ݂uG#^@") Designation19921 / 89028A[ЃA#R4Launch date4 Apr 1989ju:M#j:"N , Country of originCISgЃM#j4"H̀シMissionNavigation_:A#R<"Perigee/Apogee952/1010 kmTTA#R&Inclination83UA#R(Period104.7 minlTM#j>" &s,梉Launch vehicleCosmos CYnA#R0Launch sitePlesetsk$" < nΆ1 ΆxCosmos 2017H5 :(qi" Cosmos 20171 ΆG'  Generalg G#^@") Designation19923 / 89029A[G A#R4Launch date6 Apr 1989jsM#j:"N , Country of originCISm& G#^L"H̀MissionMilitary: reconnaissance^s>A#R:"Perigee/Apogee244/260 kmVA#R*Inclination62.8T>A#R&Period89.6 minbJG#^6" &Launch vehicleSoyouzYA#R0Launch sitePlesetsk&JɊ# 5'  End of lifeVɊTA#R*Decay19 Apr 1989$x" < T1 Cosmos 2018Hx5 :(qi" Cosmos 20181 -'  Generalg G#^@") Designation19938 / 89031A\-A#R6Launch date20 Apr 1989jZM#j:"N , Country of originCISz-ԍM#jZ"H̀シMissionMilitary: Navigation (Tsigal)^Z2A#R:"Perigee/Apogee185/327 kmVԍA#R*Inclination62.9T2܎A#R&Period89.6 minb>G#^6" &Launch vehicleCosmosY܎A#R0Launch sitePlesetsk&># 5 '  End of life xVbA#R*Decay19 Jun 1989$ " < b1O iCosmos 2019H 5 :(qi" Cosmos 20191 ;'  Generalg G#^@") Designation19972 / 89034A[;A#R4Launch date5 May 1989jgM#j:"N , Country of originCISj#G#^F"H̀MissionMilitary: observation^g/A#R:"Perigee/Apogee241/256 kmVA#R*Inclination62.9T/A#R&Period89.5 minb;G#^6" &Launch vehicleSoyouzYA#R0Launch sitePlesetsk&;# 5'  End of lifeVEA#R*Decay18 May 1989$i" < E1 PCosmos 2020Hi5 :(qi" Cosmos 20201 '  Generalg G#^@") Designation19986 / 89036A\A#R6Launch date17 May 1989jKM#j:"N , Country of originCISm&G#^L"H̀MissionMilitary: reconnaissance^KA#R:"Perigee/Apogee178/280 kmVlA#R*Inclination64.8TA#R&Period89.7 minbl"G#^6" &Launch vehicleSoyouzY{A#R0Launch sitePlesetsk&"# 5{'  End of lifeV,A#R*Decay15 Jul 1989$P" < ,1Oƃ 6Cosmos 2021HP5 :(qi" Cosmos 20211 '  Generalg lG#^@") Designation20000 / 89037A\A#R6Launch date24 May 1989jl2M#j:"N , Country of originCISm&G#^L"H̀MissionMilitary: reconnaissance^2A#R:"Perigee/Apogee204/280 kmVSA#R*Inclination69.9TA#R&Period89.4 minbS G#^6" &Launch vehicleSoyouzYbA#R0Launch sitePlesetsk& # 5b'  End of lifeUA#R(Decay6 Jul 1989$6" < r1 r,Cosmos 2022H65 :(qi" Cosmos 2022Dr ) "6Also called Glonass 42 61 ='  Generalg G#^@") Designation20024 / 89039A\=A#R6Launch date31 May 1989jjM#j:"N , Country of originCISp#M#jF"H̀シMissionNavigation (Uragan)b!j<A#RB"Perigee/Apogee19119/19139 kmVA#R*Inclination65.5U<A#R(Period675.7 mino"VM#jD" &㉓gLaunch vehicleProton #177&|# 5V'  End of lifeW|A#R,"Out of serviceyes$," < h1ƃc h Cosmos 2023H,5 :(qi" Cosmos 2023Dh) "6Also called Glonass 431 %'  Generalg G#^@") Designation20025 / 89039b\%A#R6Launch date31 May 1989jRM#j:"N , Country of originCISp#M#jF"H̀シMissionNavigation (Uragan)b!R$A#RB"Perigee/Apogee19087/19170 kmVzA#R*Inclination65.5U$A#R(Period675.7 mino"z>M#jD" &㉓gLaunch vehicleProton #177&d# 5>'  End of lifeWdA#R,"Out of serviceyes$ " < P 1r P  Cosmos 2024H 5 :(qi" Cosmos 20241 P '  Generalg 0 G#^@") Designation20026 / 89039C\ A#R6Launch date31 May 1989j0 M#j:"N , Country of originCISr+ h G#^V"H̀MissionMilitary: geodesy (Etalon #2)b! A#RB"Perigee/Apogee19095/19146 kmVh A#R*Inclination65.5U u A#R(Period675.4 mino" M#jD" &㉓gLaunch vehicleProton #177$u  " < D 1cn D ACosmos 2025H 5 :(qi" Cosmos 20251 D '  Generalg $G#^@") Designation20035 / 89040A[ A#R4Launch date1 Jun 1989j$M#j:"N , Country of originCISm&VG#^L"H̀MissionMilitary: reconnaissance^A#R:"Perigee/Apogee236/256 kmVV@A#R*Inclinatio@ n62.8Tj@A#R&Period89.4 minb@@G#^6" &Launch vehicleSoyouzYj@%AA#R0Launch sitePlesetsk&@KA# 5%AA'  End of lifeVKAAA#R*Decay15 Jun 1989$AA" < A6B1fr 6B~BFCosmos 2026HA~B5 :(qi" Cosmos 20261 6BB'  Generalg ~BCG#^@") Designation20045 / 89042A[BqCA#R4Launch date7 Jun 1989jCCM#j:"N , Country of originCISgqCBDM#j4"H̀シMissionNavigation_CDA#R<"Perigee/Apogee948/1006 kmVBDDA#R*Inclination82.9UDLEA#R(Period104.6 minlDEM#j>" &s,梉Launch vehicleCosmos CYLEFA#R0Launch sitePlesetsk&E7F# 8FoF' "(OTechnical dataD!7FF# BDownlink frequency: 149.97 MHz< oFF1n F7GKCosmos 2027HF7G5 :(qi" Cosmos 20271 FhG'  Generalg 7GGG#^@") Designation20064 / 89045A\hG+HA#R6Launch date14 Jun 1989jGHM#j:"N , Country of originCISp)+HIG#^R"H̀MissionMilitary: radar calibration^HcIA#R:"Perigee/Apogee394/427 kmVIIA#R*Inclination65.8TcI JA#R&Period92.8 minlIyJM#j>" &s,梉Launch vehicleCosmos CY JJA#R0Launch sitePlesetsk&yJJ# 5J-K'  End of lifeVJKA#R*Decay14 Apr 1992$-KK" < KK1 K+LCosmos 2028HK+L5 :(qi" Cosmos 20281 K\L'  Generalg +LLG#^@") Designation20073 / 89047A\\LMA#R6Launch date16 Jun 1989jLMM#j:"N , Country of originCISm&MMG#^L"H̀MissionMilitary: reconnaissance^MTNA#R:"Perigee/Apogee204/243 kmTMNA#R&Inclination70RTNNA#R"Period89 minbN\OG#^6" &Launch vehicleSoyouzYNOA#R0Launch sitePlesetsk&\OO# 5O'  OKEnd of lifeUOqA#R(Decay6 Jul 1989$" < qр1Q р{Cosmos 2029H5 :(qi" Cosmos 20291 рJ'  Generalg G#^@") Designation20105 / 89051A[J A#R4Launch date5 Jul 1989jvM#j:"N , Country of originCISm& G#^L"H̀MissionMilitary: reconnaissance^vAA#R:"Perigee/Apogee178/238 kmVA#R*Inclination82.3TAA#R&Period88.7 minbMG#^6" &Launch vehicleSoyouzYA#R0Launch sitePlesetsk&M̄# 5'  End of lifeV̄WA#R*Decay19 Jul 1989${" < W1 \Cosmos 2030H{5 :(qi" Cosmos 20301 0'  Generalg G#^@") Designation20124 / 89054A\0A#R6Launch date12 Jul 1989j]M#j:"N , Country of originCISm&ʇG#^L"H̀MissionMilitary: reconnaissance^](A#R:"Perigee/Apogee162/349 kmVʇ~A#R*Inclination67.2T(҈A#R&Period89.6 min\~.G#^*" &Launch vehicleY҈A#R0Launch sitePlesetsk&.# 5'  End of lifeV8A#R*Decay29 Jul 1989$\" < 81Q 3Cosmos 2031H\5 :(qi" Cosmos 20311 '  Generalg xG#^@") Designation20136 / 89056A\ԋA#R6Launch date18 Jul 1989jx>M#j:"N , Country of originCIS]ԋG#^,"H̀MissionMilitary^>A#R:"Perigee/Apogee211/264 kmVOA#R*Inclination50.4TA#R&Period89.6 minbOG#^6" &Launch vehicleSoyouzY^A#R0Launch siteTyuratam&# 5^'  End of lifeVA#R*Decay15 Sep 1989$3" < o1 o=Cosmos 2032H35 :(qi" Cosmos 20321 o '  General 3g sG#^@") Designation20145 / 89057A\ A#R6Launch date20 Jul 1989js9M#j:"N , Country of originCISm&G#^L"H̀MissionMilitary: reconnaissance^9A#R:"Perigee/Apogee179/241 kmVZA#R*Inclination82.3TA#R&Period88.7 minbZG#^6" &Launch vehicleSoyouzYiA#R0Launch sitePlesetsk&# 5i'  End of lifeUA#R(Decay3 Aug 1989$=" < y1{@ y Cosmos 2033H=5 :(qi" Cosmos 20331 y'  Generalg YG#^@") Designation20147 / 89058A\A#R6Launch date24 Jul 1989jYM#j:"N , Country of originCIS]|G#^,"H̀MissionMilitary^A#R:"Perigee/Apogee196/322 kmT|.A#R&Inclination65TA#R&Period89.7 min\.G#^*" &Launch vehicleY7A#R0Launch siteTyuratam&]# 57'  End of lifeU]A#R(Decay6 Jan 1991$ " < G1P GGCosmos 2034H 5 :(qi" Cosmos 20341 G'  Generalg 'G#^@") Designation20149 / 89059A\A#R6Launch date25 Jul 1989j'M#j:"N , Country of originCISgTM#j4"H̀シMissionNavigation_A#R<"Perigee/Apogee962/1010 kmVT A#R*Inclination82.9U^A#R(Period104.8 minl M#j>" &s,梉Launch vehicleCosmos CY^#A#R0Launch sitePlesetsk$G" < #1@ FCosmos 2035HG5 :(qi" Cosmos 20351 '  Generalg cG#^@") Designation20151 / 89060A[A#R4Launch date2 Aug 1989jc(M#j:"N , Country of originCISj#G#^F"H̀MissionMilitary: observation^( A#R:"Perigee/Apogee176/306 km GVbA#R*Inclination82.6T A#R&Period88.6 minbbG#^6" &Launch vehicleSoyouzYqA#R0Launch sitePlesetsk&# 5q'  End of lifeV"A#R*Decay16 Aug 1989$F" < "1P ,Cosmos 2036HF5 :(qi" Cosmos 20361 '  Generalg bG#^@") Designation20188 / 89065A\A#R6Launch date22 Aug 1989jb(M#j:"N , Country of originCISm&G#^L"H̀MissionMilitary: reconnaissance^(A#R:"Perigee/Apogee244/259 kmVIA#R*Inclination62.8TA#R&Period89.5 minbIG#^6" &Launch vehicleSoyouzYXA#R0Launch sitePlesetsk&~# 5X'  End of lifeU~A#R(Decay5 Sep 1989$," < h1 h5 Cosmos 2037H,5 :(qi" Cosmos 20371 h'  Generalg HG#^@") Designation20196 / 89068A\A#R6Launch date28 Aug 1989jH M#j:"N , Country of originCIS0 Y#`"H̀4CV$!& MissionScientific: geodesy (Geo-IK)` A#R>"Perigee/Apogee1482/1522 kmV M A#R*Inclination73.6S A#R$Period116 minq$M  M#jH" &ቂLaunch vehicleCyclone 3 #77$ 5 " <  q 1 q 9Cosmos 2038H5 5 :(qi" Cosmos 20381 q '  Generalg Q G#^@") Designation20232 / 89074A\ A#R6Launch date14 Sep 1989jQ  M#j:"N , Country of originCIS/ S#v^"H̀(㓉<MissionTelecommunications (Strela-3)` A#R>"Perigee/Apogee1389/1408 kmV OA#R*Inclination82.6U A#R(Period113.8 minq$OM#jH" &ቂLaunch vehicleCyclone 3 #78$9" < u1 u[CCosmos 2039H95 :(qi" Cosmos 20391 u @'  General @9g s@G#^@") Designation20233 / 89074B\ @@A#R6Launch date14 Sep 1989js@9AM#j:"N , Country of originCIS/@AS#v^"H̀(㓉<MissionTelecommunications (Strela-3)`9ABA#R>"Perigee/Apogee1382/1408 kmVAqBA#R*Inclination82.6UBBA#R(Period113.7 minq$qB7CM#jH" &ቂLaunch vehicleCyclone 3 #78$B[C" < 7CC1 CC]GCosmos 2040H[CC5 :(qi" Cosmos 20401 CD'  Generalg CwDG#^@") Designation20234 / 89074C\DDA#R6Launch date14 Sep 1989jwD=EM#j:"N , Country of originCIS/DES#v^"H̀(㓉<MissionTelecommunications (Strela-3)`=EFA#R>"Perigee/Apogee1407/1413 kmVEuFA#R*Inclination82.6SFFA#R$Period114 minq$uF9GM#jH" &ቂLaunch vehicleCyclone 3 #78$F]G" < 9GG1 GGaKCosmos 2041H]GG5 :(qi" Cosmos 20411 GH'  Generalg GyHG#^@") Designation20235 / 89074D\HHA#R6Launch date14 Sep 1989jyH?IM#j:"N , Country of originCIS/HIS#v^"H̀(㓉<MissionTelecommunications (Strela-3)`?I!JA#R>"Perigee/Apogee1394/1408 kmVIwJA#R*Inclination82.6U!JJA#R(Period113.8 minq$wJ=KM#jH" &ቂLaunch vehicleCyclone 3 #78$JaK" < =KK1, KKeOCosmos 2042HaKK5 :(qi" Cosmos 20421 KL'  Generalg K}LG#^@") Designation20236 / 89074E\LLA#R6Launch date14 Sep 1989j}LCMM#j:"N , Country of originCIS/LMS#v^"H̀(㓉<MissionTelecommunications (Strela-3)`CM%NA#R>"Perigee/Apogee1398/1409 kmVM{NA#R*Inclination82.6U%NNA#R(Period113.9 minq${NAOM#jH" &ቂLaunch vehicleCyclone 3 #78$NeO" < AOO1 O Cosmos 2043HeO 5 :(qi" Cosmos 2043O eO1 O='  Generalg G#^@") Designation20237 / 89074F\=A#R6Launch date14 Sep 1989jjM#j:"N , Country of originCIS/S#v^"H̀(㓉<MissionTelecommunications (Strela-3)`jLA#R>"Perigee/Apogee1406/1407 kmVA#R*Inclination82.6ULA#R(Period113.9 minq$hM#jH" &ቂLaunch vehicleCyclone 3 #78$" < hȃ1c, ȃBCosmos 2044H5 :(qi" Cosmos 2044P'ȃ`) "NAlso called BioCosmos 9 or Bion 091 '  Generalg `G#^@") Designation20242 / 89075A\TA#R6Launch date15 Sep 1989jM#j:"N , Country of originCIS_TG#^0"H̀MissionScientific^{A#R:"Perigee/Apogee203/264 kmVцA#R*Inclination82.3T{%A#R&Period89.2 minbцG#^6" &Launch vehicleSoyouzY%A#R0Launch sitePlesetsk% Satellite with German, Austrian, Canadian, Danish, Spanish, American, French, Hungarian, Norwegian, Rumanian, Swiss and Czech experiments.5Ȉ'  End of lifeVA#R*Decay29 Sep 1989$ȈB" < ~1 ~ƉCosmos 2045HBƉ5 :(qi" Cosmos 20451 ~'  Generalg Ɖ^G#^@") Designation20244 / 89076A\A#R6Launch date22 Sep 1989j^$M#j:"N , Country of originCISj#G#^F"H̀MissionMilitary: observation^$A#R:"Perigee/Apogee205/295 kmT@A#R&Inclination70TA#R&Period89.5 min\@G#^*" &Launch vehicleYIA#R0Launch siteTyuratam&o# 5I'  End of lifeUoA#R(Decay2 Oct 1989$" < Y1 Y Cosmos 2047H5 :(qi" Cosmos 20471 YҎ'  Generalg 9G#^@") Designation20279 / 89082A[ҎA#R4Launch date3 Oct 1989j9 M#j:"N , Country of originCIS m&yG#^L"H̀MissionMilitary: reconnaissance^ A#R:"Perigee/Apogee165/330 kmVy-A#R*Inclination67.1TA#R&Period89.5 min\-G#^*" &Launch vehicleY6A#R0Launch sitePlesetsk&\# 56'  End of lifeV\A#R*Decay21 Nov 1989$ " < G1 GCosmos 2048H 5 :(qi" Cosmos 20481 G'  Generalg 'G#^@") Designation20292 / 89083A\A#R6Launch date17 Oct 1989j'M#j:"N , Country of originCISm&ZG#^L"H̀MissionMilitary: reconnaissance^A#R:"Perigee/Apogee253/269 kmVZA#R*Inclination62.6TbA#R&Period89.7 minbG#^6" &Launch vehicleSoyouzYbA#R0Launch sitePlesetsk&C# 5x'  End of lifeVCA#R*Decay26 Oct 1989$x" < .1I .vCosmos 2049Hv5 :(qi" Cosmos 20491 .'  Generalg vG#^@") Designation20320 / 89088A\jA#R6Launch date17 Nov 1989jM#j:"N , Country of originCIS~7jRG#^n"H̀MissionMilitary: reconnaissance (5th generation)^A#R:"Perigee/Apogee232/251 kmVRA#R*Inclination64.8TZA#R&Period89.3 minbG#^6" &Launch vehicleSoyouzYZA#R0Launch siteTyuratam&;# 5p'  End of lifeV;A#R*Decay19 Jun 1990$p" < &1J &nACosmos 2050Hn5 :(qi" Cosmos 20501 &'  Generalg nG#^@") Designation20330 / 89091A\bA#R6Launch date23 Nov 1989jM#j:"N , Country of originCISfb2G#^>"H̀MissionMilitary: warninga A#R@"Perigee/Apogee2273/38112 kmV2 A#R*Inclination62.7 UaA#R(Period718.4 minc G#^8" &Launch vehicleMolniyaYaA#R0Launch sitePlesetsk$A" < }1~Ip }Cosmos 2051HA5 :(qi" Cosmos 20511 }'  Generalg ]G#^@") Designation20334 / 89092A\A#R6Launch date24 Nov 1989j]#M#j:"N , Country of originCIS]G#^,"H̀MissionMilitary^#A#R:"Perigee/Apogee293/310 kmV4A#R*Inclination64.9TA#R&Period90.6 min\4G#^*" &Launch vehicleY=A#R0Launch siteTyuratam&c# 5='  End of lifeVcA#R*Decay21 Jan 1990$" < N1J N Cosmos 2052H5 :(qi" Cosmos 20521 N'  Generalg .G#^@") Designation20350 / 89095A\A#R6Launch date30 Nov 1989j.M#j:"N , Country of originCISm&aG#^L"H̀MissionMilitary: reconnaissance^A#R:"Perigee/Apogee174/320 kmVa A#R*Inclination67.1Ti A#R&Period89.5 min\ G#^*" &Launch vehicleYi  A#R0Launch sitePlesetsk& D # 5 y '  End of lifeVD A#R*Decay24 Jan 1990$y " < / 1p / w H@Cosmos 2054H w 5 :(qi" Cosmos 20541 / '  Generalg w  G#^@") Designation20391 / 89101A\ k A#R6Launch date27 Dec 1989j M#j:"N , Country of originCIS4k \ S#vh"H̀(‰ᇏMissionMilitary: Telecommunications: Luchg& A#RL,Geostationary orbit16W, inclined\\ G#^*" &Launch vehicleY xA#R0Launch siteTyuratam&# 5x'  End of life\/A#R6"Out of servicemid-1997q0A#R`Causedrifting West, probably out of control&/# 8 @' "(Technical data @ <H@) "&CGSpecifications< @@1O! @@/ECosmos 2055HH@@5 :(qi" Cosmos 20551 @@'  Generalg @dAG#^@") Designation20426 / 90003A\@AA#R6Launch date17 Jan 1990jdA*BM#j:"N , Country of originCISm&ABG#^L"H̀MissionMilitary: reconnaissance^*BBA#R:"Perigee/Apogee248/260 kmVBKCA#R*Inclination62.8TBCA#R&Period89.6 minbKCDG#^6" &Launch vehicleSoyouzYCZDA#R0Launch sitePlesetsk&DD# 5ZDD'  End of lifeVD EA#R*Decay29 Jan 1990$D/E" < EkE1q" kEEICosmos 2056H/EE5 :(qi" Cosmos 20561 kEE'  Generalg EKFG#^@") Designation20432 / 90004A\EFA#R6Launch date18 Jan 1990jKFGM#j:"N , Country of originCIS/FGS#v^"H̀(㓉<MissionTelecommunications (Strela-1)^GGA#R:"Perigee/Apogee769/802 kmTGEHA#R&Inclination74UGHA#R(Period100.6 minlEHIM#j>" &s,梉Launch vehicleCosmos CYH_IA#R0Launch sitePlesetsk$II" < _II1O# IJdNCosmos 2057HIJ5 :(qi" Cosmos 20571 I8J'  Generalg JJG#^@") Designation20457 / 90009A\8JJA#R6Launch date25 Jan 1990jJeKM#j:"N , Country of originCISm&JKG#^L"H̀MissionMilitary: reconnaissance^eK0LA#R:"Perigee/Apogee183/330 kmVKLA#R*Inclination62.8T0LLA#R&Period89.6 min\L6MG#^*" &Launch vehicleYLMA#R0Launch sitePlesetsk&6MM# 5MM'  End of lifeVM@NA#R*Decay19 Mar 1990$MdN" < @NN1q$ NNhCosmos 2058HdNN5 :(qi" Cosmos 20581 NO'  Generalg NOG#^@") Designation20465 / 90010A\OOA#R6Launch date30 Jan 1989jORM#j:ORdN"N , Country of originCISy,OˀM#jX"H̀_剂MissionMilitary: SIGINT (Tselina-D)^R)A#R:"Perigee/Apogee616/645 kmVˀA#R*Inclination82.5T)ӁA#R&Period97.3 minq$DM#jH" &ቂLaunch vehicleCyclone 3 #82$Ӂh" < D1% ]Cosmos 2059Hh5 :(qi" Cosmos 20591 '  Generalg G#^@") Designation20476 / 90012A[߃A#R4Launch date6 Feb 1990jIM#j:"N , Country of originCISp)߃G#^R"H̀MissionMilitary: radar calibration_IA#R<"Perigee/Apogee184/1585 kmVnA#R*Inclination65.8UÅA#R(Period102.7 minln/M#j>" &s,梉Launch vehicleCosmos CYÅA#R0Launch sitePlesetsk&/# 5'  End of lifeV9A#R*Decay12 Nov 1990$]" < 91& Cosmos 2061H]5 :(qi" Cosmos 20611 '  Generalg yG#^@") Designation20527 / 90023A\ՈA#R6Launch date20 Mar 1990jy?M#j:"N , Country of originCISgՈM#j4"H̀シMissionNavigation_?A#R<"Perigee/Apogee967/1015 kmV[A#R*Inclination82.9UA#R(Period104.9 minl[M#j>" &s,梉Launch vehicleCosmos CYuA#R0Launch sitePlesetsk$" < uՋ1' ՋCosmos 2062H5 :(qi" Cosmos 20621 ՋN'  Generalg G#^@") Designation20529 / 90024A\NA#R6Launch date22 Mar 1990j{M#j:"N , Country of originCISm&G#^L"H̀MissionMilitary: reconnaissance^{FA#R:"Perigee/Apogee178/221 kmVA#R*Inclination82.3TFA#R&Period88.5 minbRG#^6" &Launch vehicleSoyouzYA#R0Launch sitePlesetsk&Rя# 5'  End of яlifeUяgA#R(Decay5 Apr 1990$" < g16( Cosmos 2063H5 :(qi" Cosmos 20631 @'  Generalg G#^@") Designation20536 / 90026A\@A#R6Launch date27 Mar 1990jmM#j:"N , Country of originCISr+G#^V"H̀MissionMilitary: early warning (Oko)a m@A#R@"Perigee/Apogee1706/38633 kmVA#R*Inclination63.8U@A#R(Period717.5 mincNG#^8" &Launch vehicleMolniyaYA#R0Launch sitePlesetsk$N" < 1U) OCosmos 2064HO5 :(qi" Cosmos 20641 '  Generalg OG#^@") Designation20549 / 90029A[BA#R4Launch date6 Apr 1990jM#j:"N , Country of originCIS/B.S#v^"H̀(㓉<MissionTelecommunications (Strela-2)`A#R>"Perigee/Apogee1460/1488 kmT.A#R&Inclination74U7A#R(Period115.4 minbG#^6" &Launch vehicleCosmosY7A#R0Launch sitePlesetsk$" < R16t* RaCosmos 2065H5 :(qi" Cosmos 20651 R'  Generalg 2G#^@") Designation20550 / 90029B[A#R4Launch date6 Apr 1990j2M#j:"N , Country of originCIS/yS#v^"H̀(㓉<MissionTelecommunications (Strela-2)`A#R>"Perigee/Apogee1459/1473 kmTy-A#R&Inclination74UA#R(Period115.2 minb-G#^6" &Launch vehicleCosmosY=A#R0Launch sitePlesetsk$a" < =1U\+ Cosmos 2066Ha5 :(qi" Cosmos 20661 '  Generalg }G#^@") Designation20551 / 90029C[A#R4Launch date6 Apr 1990j}BM#j:"N , Country of originCIS/S#v^"H̀(㓉<MissionTelecommunications (Strela-2)`B0A#R>"0aPerigee/Apogee1383/1461 kmTA#R&Inclination74U0A#R(Period114.3 minb;G#^6" &Launch vehicleCosmosYA#R0Launch sitePlesetsk$;" < 1t{, <Cosmos 2067H<5 :(qi" Cosmos 20671 m'  Generalg <G#^@") Designation20552 / 90029D[m/A#R4Launch date6 Apr 1990jM#j:"N , Country of originCIS//S#v^"H̀(㓉<MissionTelecommunications (Strela-2)`{A#R>"Perigee/Apogee1398/1461 kmTA#R&Inclination74U{$A#R(Period114.4 minbG#^6" &Launch vehicleCosmosY$A#R0Launch sitePlesetsk$" < ?1\- ?N Cosmos 2068H5 :(qi" Cosmos 20681 ?'  Generalg G#^@") Designation20553 / 90029E[zA#R4Launch date6 Apr 1990jM#j:"N , Country of originCIS/zfS#v^"H̀(㓉<MissionTelecommunications (Strela-2)`A#R>"Perigee/Apogee1413/1460 kmTf A#R&Inclination74Uo A#R(Period114.6 minb G#^6" &Launch vehicleCosmosYo * A#R0Launch sitePlesetsk$ N " < * 1{. Cosmos 2069HN 5 :(qi" Cosmos 20691  '  Generalg j G#^@") Designation20554 / 90029F[ A#R4Launch date6 Apr 1990jj / M#j:"N , Country of originCIS/ S#v^"H̀(㓉<MissionTelecommunications (Strela-2)`/  A#R>"Perigee/Apogee1427/1461 kmT e A#R&Inclination74U A#R(Period114.8 minbe G#^6" &Launch vehicleCosmosY uA#R0Launch sitePlesetsk$" < u1ǀ/ BCosmos 2070H5 :(qi" Cosmos 20701 N'  Generalg G#^@") Designation20555 / 90029G[N@A#R4Launch da@te6 Apr 1990j@M#j:"N , Country of originCIS/@AS#v^"H̀(㓉<MissionTelecommunications (Strela-2)`@hAA#R>"Perigee/Apogee1441/1461 kmTAAA#R&Inclination74UhABA#R(Period114.9 minbAsBG#^6" &Launch vehicleCosmosYBBA#R0Launch sitePlesetsk$sBB" < B,C10 ,CtC;GCosmos 2071HBtC5 :(qi" Cosmos 20711 ,CC'  Generalg tC DG#^@") Designation20556 / 90029H[CgDA#R4Launch date6 Apr 1990j DDM#j:"N , Country of originCIS/gDSES#v^"H̀(㓉<MissionTelecommunications (Strela-2)`DEA#R>"Perigee/Apogee1457/1461 kmTSEFA#R&Inclination74UE\FA#R(Period115.1 minbFFG#^6" &Launch vehicleCosmosY\FGA#R0Launch sitePlesetsk$F;G" < GwG1ǀ31 wGG3LCosmos 2072H;GG5 :(qi" Cosmos 20721 wGG'  Generalg GWHG#^@") Designation20568 / 90033A\GHA#R6Launch date13 Apr 1990jWHIM#j:"N , Country of originCIS~7HIG#^n"H̀MissionMilitary: reconnaissance (5th generation)^IIA#R:"Perigee/Apogee232/270 kmVIOJA#R*Inclination64.7TIJA#R&Period89.5 minbOJKG#^6" &Launch vehicleSoyouzYJ^KA#R0Launch sitePlesetsk&KK# 5^KK'  End of lifeVKLA#R*Decay22 Nov 1990$K3L" < LoL1@2 oLL:Cosmos 2073H3LL5 :(qi" Cosmos 20731 oLL'  Generalg LOMG#^@") Designation20573 / 90035A\LMA#R6Launch date17 Apr 1990jOMNM#j:"N , Country of originCISm&MNG#^L"H̀MissionMilitary: reconnaissance^NNA#R:"Perigee/Apogee173/239 kmVN6OA#R*Inclination82.4TNOA#R&Period88.6 minb6O G#^6" &Launch vehicleSoyouzO 3LYOeA#R0Launch sitePlesetsk& # 5e'  End of lifeVA#R*Decay28 Apr 1990$:" < v1t33 vCosmos 2074H:5 :(qi" Cosmos 20741 v'  Generalg VG#^@") Designation20577 / 90036A\A#R6Launch date13 Apr 1990jVM#j:"N , Country of originCISgM#j4"H̀シMissionNavigation_A#R<"Perigee/Apogee962/1002 kmV8A#R*Inclination82.9UA#R(Period104.7 minl8M#j>" &s,梉Launch vehicleCosmos CYRA#R0Launch siteTyuratam&x# 8R' "(OTechnical dataQ.x# \Downlink frequencies: 149.910 & 399.760 MHz< =1@4 ='Cosmos 2079H5 :(qi" Cosmos 2079D=Ɇ) "6Also called Glonass 441 '  Generalg ɆaG#^@") Designation20619 / 90045A\A#R6Launch date19 May 1990ja'M#j:"N , Country of originCISp#M#jF"H̀シMissionNavigation (Uragan)b!'A#RB"Perigee/Apogee19069/19189 kmVOA#R*Inclination65.3UA#R(Period675.7 min\OG#^*" &Launch vehicleQQA#R Launch site&w# 5Q'  End of lifeWwA#R,"Out of serviceyes$'" < c15 cYCosmos 2080H'5 :(qi" Cosmos 2080Dc) "6Also called Glonass 451 '  Generalg G#^@") Designation20620 / 90045B\ A#R6Launch date19 May 1990jMM#j:"N , Country of originCISp#M#jF"H̀シMissionNavigation (Uragan)b!MA#RB"Perigee/Apogee19107/19151 kmVuA#R*Inclination65.3UʎA#R(Period675.7 min\u&G#^*" &Launch vehicleQʎwA#R Launch site&&# 5wҏ'  End of lifeW5A#R,ҏ5'"Out of serviceyes$ҏY" < 51N6 Cosmos 2081HY5 :(qi" Cosmos 2081D!) "6Also called Glonass 461 R'  Generalg !G#^@") Designation20621 / 90045C\RA#R6Launch date19 May 1990jM#j:"N , Country of originCISp#M#jF"H̀シMissionNavigation (Uragan)b!QA#RB"Perigee/Apogee19107/19151 kmVA#R*Inclination65.3UQA#R(Period675.7 min\XG#^*" &Launch vehicleQA#R Launch site&X# 5'  End of lifeW[A#R,"Out of serviceyes$" < [1|7 NCosmos 2085H5 :(qi" Cosmos 20851 4'  Generalg G#^@") Designation20693 / 90061A\4A#R6Launch date18 Jul 1990jaM#j:"N , Country of originCIS6S#vl"H̀(‰MissionMilitary: telecommunications: Geizer]aGA#R8,Geostationary orbit80E\G#^*" &Launch vehicleYGA#R0Launch siteTyuratam&"# 5W'  End of life]"A#R8"Out of servicemid 1995?&W# 8' "(Technical data<N) "&$Specifications< 1VNσ8 Cosmos 2100HN5 :(qi" Cosmos 21001 '  Generalg jG#^@") Designation20804 / 90083A\A#R6Launch date14 Sep 1990jj0M#j:"N , Country of originCISUG#^"H̀Mission_0A#R<"Perigee/Apogee957/1010 kmV:A#R*Inclination82,9UA#R(Period104.8 minl:M#j>" &s,梉Launch vehicleCosmos CYTA#R0Launch sitePlesetsk&z# 8T' "(OTechnical dataE"z# DDownlink frequency: 149.970 MHz< 319 3{Cosmos 2107H{5 :(qi" Cosmos 21071 3'  Generalg {G#^@") Designation20985 / 90108A[zA#R4Launch date4 Dec 1990jM#j:"N , Country of originCIS7zhM#jn"H̀/{MissionMilitary: ocean reconnaissance (Eorsat)^A#R:"Perigee/Apogee402/416 kmThA#R&Inclination65TnA#R&Period92.8 min\G#^*" &Launch vehicleYn#A#R0Launch sitePlesetsk&I# 5#~'  End of lifeUIA#R(Decay6 Apr 1992$~" < 31σ>: 3{Cosmos 2108H{5 :(qi" Cosmos 21081 3'  Generalg {G#^@") Designation21000 / 90109A[nA#R4Launch date4 Dec 1990jM#j:"N , Country of originCISm&nEG#^L"H̀MissionMilitary: reconnaissance^A#R:"Perigee/Apogee164/289 kmVEA#R*Inclination62.8RKA#R"Period89 minbG#^6" &Launch vehicleSoyouzYKA#R0Launch sitePlesetsk&,# 5a'  End of lifeV,A#R*Decay28 Jan 1991$a" <  1;  _ Cosmos 2109H_ 5 :(qi" Cosmos 2109D ) "6Also called Glonass 471 _ '  Generalg ; G#^@") Designation21006 / 90110A[ A#R4Launch date8 Dec 1990j; M#j:"N , Country of originCISp# p M#jF"H̀シMissionNavigation (Uragan)b! A#RB"Perigee/Apogee18975/19283 kmVp ( A#R*Inclination64.9U } A#R(Period675.7 mino"( M#jD" &㉓gLaunch vehicleProton #193&}  # 5 G '  End of lifeW A#R,"Out of serviceyes$G " < 1>< FBCosmos 2110H F5 :(qi" Cosmos 2110D ) "6Also called Glonass 481 F'  Generalg "G#^@") Designation21007 / 90110B[}A#R4Launch date8 Dec 1990j" @M#j:"N , Country of originCIS} @ p#}|@M#jF"H̀シMissionNavigation (Uragan)b! @@A#RB"Perigee/Apogee19036/19223 kmV|@4AA#R*Inclination64.9U@AA#R(Period675.7 mino"4AAM#jD" &㉓gLaunch vehicleProton #193&AB# 5ASB'  End of lifeWBBA#R,"Out of serviceyes$SBB" < B C1l= CRCHCosmos 2111HBRC5 :(qi" Cosmos 2111[, CC/ .XAlso called Glonass 49 or Glonass 2491 RCC'  Generalg CEDG#^@") Designation21008 / 90110C[CDA#R4Launch date8 Dec 1990jED EM#j:"N , Country of originCISp#DzEM#jF"H̀シMissionNavigation (Uragan)b! EEA#RB"Perigee/Apogee19110/19148 kmTzE0FA#R&Inclination65UEFA#R(Period675.7 mino"0FFM#jD" &㉓gLaunch vehicleProton #193&FG# 8FRG' "(Technical dataMGGB#T$Frequency (MHz)L1 = 1602 + 0.5625 * channelL2 = 1246 + 0.4375 * channelORG0HA#RChannel23L G|HA#RPlane1K 0HHA#RSlot5$|HH" < H'I1> 'IoI?MCosmos 2112HHoI5 :(qi" Cosmos 21121 'II'  Generalg oIJG#^@") Designation21014 / 90111A\IcJA#R6Launch date10 Dec 1990jJJM#j:"N , Country of originCIS/cJOKS#v^"H̀(㓉<MissionTelecommunications (Strela-1)^JKA#R:"Perigee/Apogee765/807 kmTOKLA#R&Inclination74UKVLA#R(Period100.6 minlLLM#j>" &s,梉Launch vehicleCosmos CYVLMA#R0Launch sitePlesetsk$L?M" < M{M1#l? {MMCosmos 2123H?MM5 :(qi" Cosmos 21231 {MM'  Generalg M[NG#^@") Designation21089 / 91007A[MNA#R4Launch date5 Feb 1991j[N OM#j:"N , Country of originCISy&NOS#vL"H̀(シ 剂MissionNavigation (Tsikada)_ O A#R<"Perigee/Apogee961/1003 kmO ?MVObA#R*Inclination82.9U A#R(Period104.7 min\bG#^*" &Launch vehicleYlA#R0Launch sitePlesetsk&# 8lʁ' "(OTechnical datapF:* $シDownlink frequencies (navigation payload): 150 & 400 MHzPlane 13:ʁt' & Radio Sputnik 12a :ՂA#R@beacon/robot29.408 mhz (cw)a t6A#R@beacon/robot29.454 mhz (cw)q0ՂA#R` mode a uplink145.910 - 145.950 mhz (ssb,cw)q06A#R`$mode a downlink29.410 - 29.450 mhz (ssb,cw)d#|A#RF"robot a uplink145.831 mhz (cw)o.A#R\&robot a downlink29.408 or 29.454 mhz (cw)a |LA#R@beacon/robot29.408 mhz (cw)a A#R@beacon/robot29.454 mhz (cw)o.LA#R\ mode k uplink21.210 - 21.250 mhz (ssb,cw)q0A#R`$mode k downlink29.410 - 29.450 mhz (ssb,cw)c"A#RD"robot k uplink21.129 mhz (cw)o._A#R\&robot k downlink29.408 or 29.454 mhz (cw)b!A#RBbeacon/robot145.912 mhz (cw)b!_#A#RBbeacon/robot145.959 mhz (cw)n-A#RZ mode t uplink21.210 - 21.250 hz (ssb,cw)s2#A#Rd$mode t downlink145.910 - 145.950 mhz (ssb,cw)c"gA#RD"robot t uplink21.129 mhz (cw)q0؉A#R`&robot t downlink145.912 or 145.959 mhz (cw)&g# :؉8' & Radio Sputnik 13a A#R@beacon/robot29.458 mhz (cw)a 8A#R@beacon/robot29.504 mhz (cw)q0kA#R` mode a uplink145.960 - 146.000 mhz (ssb,cw)q0܋A#R`$mode a downlink29.460 - 29.500 mhz (ssb,cw)d#k@A#RF"robot a uplink145.840 mhz (cw)o.܋A#R\&robot a downlink29.458 or 29.504 mhz (cw)a @A#R@beacon/robot29.458 mhz (cw)a qA#R@beacon/robot29.504 mhz (cw)o.A#R\ mode k uplink21.260 - 21.300 mhz (ssb,cw)q0qQA#R`$mode k downlink29.460 - 29.500 mhz (ssb,cw)c"A#RD"robot k uplink21.138 mhz (cw)o.Q#A#R\&robot k downlink29.458 or 29.504 mhz (cw)b!A#RBbeacon/robot145.862 mhz (cw)b!# A#RBbeacon/robot145.908 mhz (cw) ?Mo.{A#R\ mode t uplink21.260 - 21.300 mhz (ssb,cw)s2 A#Rd$mode t downlink145.960 - 146.000 mhz (ssb,cw)c"{QA#RD"robot t uplink21.138 mhz (cw)o.A#R\"robot downlink145.862 or 145.908 mhz (cw)$Q" < 1͂@ h+Cosmos 2133Hh5 :(qi" Cosmos 21331 '  Generalg hG#^@") Designation21111 / 91010A\\A#R6Launch date14 Feb 1991jM#j:"N , Country of originCIS>\KG#^|"H̀MissionMilitary: early warning (Prognoz 2nd generation)o(G#^P"/ۀ0Geostationary orbit80E, inclined\KG#^*" &Launch vehicleYoA#R0Launch siteTyuratam&# 5o'  End of life\&A#R6"Out of serviceOct 1995&L# 8&' "(OTechnical data8L' " Specificationsc"A#RD&Prime contractorNPO LavochkinN mA#RPlatform[A#R4"Mass at launch2600 kgSmA#R$ Mass in orbitL gA#RLengthK A#RWidthL gA#RHeightSQA#R$ StabilizationN A#RDC powerUQA#R($Design lifetime7+$ &S-band capacity< g1A gPCosmos 2139H+5 :(qi" Cosmos 2139Dg) "6Also called Glonass 501 $'  Generalg G#^@") Designation21216 / 91025A[$A#R4Launch date4 Apr 1991jPM#j:"N , Country of originCISp#M#jF"H̀シMissionNavigation (Uragan)b!P"A#RB"Perigee/Apogee19103/19155 kmVxA#R*Inclination65.1U"A#R(Period675.7 min\x)G#^*" &Launch vehicleQzA#R Launch site&)# 5z'  End of lifeW,A#R,"Out of serviceyes$P" < ,1͂B Cosmos 2140HP5 :(qi" Cosmos 2140D$) "6Al$Pso called Glonass 511 U'  Generalg $G#^@") Designation21217 / 91025B[UA#R4Launch date4 Apr 1991jM#j:"N , Country of originCISp#M#jF"H̀シMissionNavigation (Uragan)b!SA#RB"Perigee/Apogee19102/19156 kmVA#R*Inclination65.1USA#R(Period675.7 min\ZG#^*" &Launch vehicleQA#R Launch site&Z# 5'  End of lifeW]A#R,"Out of serviceyes$" < ]1gC  Cosmos 2141H5 :(qi" Cosmos 2141DI) "6Also called Glonass 521 z'  Generalg IG#^@") Designation21218 / 91025C[z<A#R4Launch date4 Apr 1991jM#j:"N , Country of originCISp#<M#jF"H̀シMissionNavigation (Uragan)b!xA#RB"Perigee/Apogee19109/19149 kmVA#R*Inclination65.1Ux#A#R(Period675.7 min\G#^*" &Launch vehicleQ#A#R Launch site&# 5+ '  End of lifeW A#R,"Out of serviceyes$+ " < 1`D * YCosmos 2142H * 5 :(qi" Cosmos 21421 [ '  Generalg * G#^@") Designation21230 / 91029A\[  A#R6Launch date16 Apr 1991j M#j:"N , Country of originCISU G#^"H̀Mission_ < A#R<"Perigee/Apogee958/1017 kmT A#R&Inclination83U< A#R(Period104.9 minl Q M#j>" &s,梉Launch vehicleCosmos CY A#R0Launch sitePlesetsk&Q # 8 ' "(OTechnical dataQ. Y# \Downlink frequencies: 150.030 & 400.080 MHz< 1/glE ACosmos 2155HY5 :(qi" Cosmos 21551 '  Generalg uG#^@") Designation21702 / 91064A\A#R6Launch date13 Sep 1991juG@M#j:"G@YN , Country of originCISl%@G#^J"H̀MissionMilitary: early warningYG@ AA#R0,Geostationary orbit\@hAG#^*" &Launch vehicleY AAA#R0Launch siteTyuratam$hAA" < A!B1F !BiBHCosmos 2172HAiB5 :(qi" Cosmos 21721 !BB'  Generalg iBCG#^@") Designation21789 / 91079A\B]CA#R6Launch date22 Nov 1991jCCM#j:"N , Country of originCIS6]CPDS#vl"H̀(‰MissionMilitary: telecommunications: Geizerb!CDA#RB,Geostationary orbitsee below\PDEG#^*" &Launch vehicleYDgEA#R0Launch siteTyuratam&EE# 2 gEE'  LocationvE5F^#0 BeginEndPosition/EFj#^$8:L: 22 Nov 1991Feb 199613.5W, inclined&5FF# 5F)G'  End of life\FGA#R6"Out of serviceMar 1996&)GG# 8GG' "(Technical data<GH) "&$Specifications< G[H1=lG [HHMCosmos 2173HHH5 :(qi" Cosmos 21731 [HH'  Generalg H;IG#^@") Designation21796 / 91081A\HIA#R6Launch date26 Nov 1991j;IJM#j:"N , Country of originCIS.IJS#v\"H̀(シ㼨ԟMissionMilitary: Navigation (Parus)_JJA#R<"Perigee/Apogee944/1015 kmVJ7KA#R*Inclination82.9UJKA#R(Period104.7 minl7KKM#j>" &s,梉Launch vehicleCosmos CQKILA#R Launch site&KoL# 5ILL'  End of lifeWoLLA#R,"Out of serviceyes&L!M# 8LYM' "(Technical dataV2!MM$ dDownlink frequency: 149.97 & 399.92 MHzPlane 4< YMM1H M3NCosmos 2177HM3N5 :(qi" Cosmos 2177DMwN) "6Also called Glonass 531 3NN'  Generalg wNOG#^@") Designation21853 / 92005A\NkOA#R6Launch date29 Jan 1992jOOM#j:"N , Country of originCISp#kOQM#jF"OQMH̀シMissionNavigation (Uragan)b!OA#RB"Perigee/Apogee19112/19146 kmVQ A#R*Inclination64.8U^A#R(Period675.7 min\ G#^*" &Launch vehicleQ^ A#R Launch site&1# 5 f'  End of lifeW1A#R,"Out of serviceyes$f" < 1OI e<Cosmos 2178He5 :(qi" Cosmos 2178[,/ .XAlso called Glonass 54 or Glonass 7691 e'  Generalg XG#^@") Designation21854 / 92005B\A#R6Launch date29 Jan 1992jXM#j:"N , Country of originCISp#M#jF"H̀シMissionNavigation (Uragan)b!A#RB"Perigee/Apogee19088/19170 kmTDA#R&Inclination65UA#R(Period675.7 min\DG#^*" &Launch vehicleQFA#R Launch site&l# 8F' "(Technical dataMl3B#T$Frequency (MHz)L1 = 1602 + 0.5625 * channelL2 = 1246 + 0.4375 * channelN A#RChannel2L 3͈A#RPlane1K A#RSlot8$͈<" < x1 J xCosmos 2179H<5 :(qi" Cosmos 2179[,x/ .XAlso called Glonass 55 or Glonass 7711 L'  Generalg G#^@") Designation21855 / 92005C\LA#R6Launch date29 Jan 1992jyM#j:"N , Country of originCISp#M#jF"H̀シMissionNavigation (Uragan)b!yKA#RB"Perigee/Apogee19109/19149 kmTA#R&Inclination65UKA#R(Period675.7 min\PG#^*" &Launch vehicleQA#R Launch site&PǍ# 8' "(Technical dataMǍB#T$Frequency (MHz)L1 = 1602 + 0.5625 * channelL2 = 1246 + 0.4375 * channelOݎA#RChannel23L )A#RPlane1K ݎtA#RSlot1$)" < tԏ1 OK ԏ(Cosmos 2204H(5 :(qi"ԏ( Cosmos 2204[,ԏ/ .XAlso called Glonass 56 or Glonass 7741 ('  Generalg G#^@") Designation22056 / 92047A\wA#R6Launch date30 Jul 1992jM#j:"N , Country of originCISp#wQM#jF"H̀シMissionNavigation (Uragan)b!A#RB"Perigee/Apogee19114/19144 kmTQA#R&Inclination64U\A#R(Period675.7 min\G#^*" &Launch vehicleQ\ A#R Launch site&/# 8 g' "(Technical dataM/B#T$Frequency (MHz)L1 = 1602 + 0.5625 * channelL2 = 1246 + 0.4375 * channelN gDA#RChannel1L A#RPlane3L DA#RSlot24$" < <1 ]L <]Cosmos 2205H5 :(qi" Cosmos 2205[,</ .XAlso called Glonass 57 or Glonass 7561 '  Generalg wG#^@") Designation22057 / 92047B\A#R6Launch date30 Jul 1992jw=M#j:"N , Country of originCISp#M#jF"H̀シMissionNavigation (Uragan)b!=A#RB"Perigee/Apogee19110/19148 kmTcA#R&Inclination64UA#R(Period675.7 min\cG#^*" &Launch vehicleQeA#R Launch site&# 8e' "(Technical dataMRB#T$Frequency (MHz)L1 = 1602 + 0.5625 * channelL2 = 1246 + 0.4375 * channelOA#RChannel24L RA#RPlane3L 9A#RSlot21$]" < 91VM Cosmos 2206H]5 :(qi" Cosmos 2206[,</ .XAlso called Glonass 58 or Glonass 7721 m'  Generalg <G#^@") Designation22058 / 92047C\m0A#R6Launch date30 Jul 1992jM#j:"N , Country of originCISp#0 M#jF"H̀シMissionNavigation (Uragan)b!lA#RB"Perigee/Apogee19098/19160 kmT A#R&Inclination64Ul!A#R(!]Period675.7 min\}G#^*" &Launch vehicleQ!A#R Launch site&}# 5)'  End of life_A#R<"Out of service27 Aug 1994$)" < 1J]N 0I Cosmos 2209H05 :(qi" Cosmos 22091 a'  Generalg 0G#^@") Designation22112 / 92059A\a$A#R6Launch date10 Sep 1992jM#j:"N , Country of originCIS>$G#^|"H̀MissionMilitary: early warning (Prognoz 2nd generation)o(G#^P"/ۀ0Geostationary orbit24W, inclined\G#^*" &Launch vehicleY7A#R0Launch siteTyuratam&]# 57'  End of life\]A#R6"Out of serviceOct 1996VDA#R*Cause?, drifting&j# 8D' "(OTechnical data8j' " Specificationsc"=A#RD&Prime contractorNPO LavochkinN A#RPlatform[=A#R4"Mass at launch2600 kgS9A#R$ Mass in orbitL A#RLengthK 9A#RWidthL  A#RHeightSo A#R$ StabilizationN  A#RDC powerUo  A#R($Design lifetime7 I $ &S-band capacity<  1VO )Cosmos 2218HI 5 :(qi" Cosmos 22181 '  Generalg e G#^@") Designation22207 / 92073A\ A#R6Launch date29 Oct 1992je + M#j:"N , Country of originCIS. S#v\"H̀(シ㼨ԟMissionMilitary: Navigation (Parus)_+ A#R<"Perigee/Apogee963/1013 kmV a A#R*Inclination82.9U A#R(Period104.9 minla "M#j>" &s,梉Launch vehicleCosmos CQ sA#R Launch site&"# 8s' "(OTechnical dataX4)$ hDownlink frequency: 149.940 & 399.840 MHzPlane 3< e1ƀP e$CCosmos 2219H)5 :(qi" Cosmos 22191 e'  Generalg Q@G#^@Q@)") Designation22219 / 92076A\@A#R6Launch date17 Nov 1992jQ@AM#j:"N , Country of originCISy,@AM#jX"H̀_剂MissionMilitary: SIGINT (Tselina-2)^AAA#R:"Perigee/Apogee843/855 kmTABBA#R&Inclination71UABA#R(Period101.9 miniBBCM#j8" &'CMLaunch vehicleZenit$B$C" < C`C1Q `CCGCosmos 2220H$CC5 :(qi" Cosmos 22201 `CC'  Generalg C@DG#^@") Designation22226 / 92077A\CDA#R6Launch date20 Nov 1992j@DEM#j:"N , Country of originCIS]DcEG#^,"H̀MissionMilitary^EEA#R:"Perigee/Apogee164/341 kmVcEFA#R*Inclination67.2TEkFA#R&Period89.6 minbFFG#^6" &Launch vehicleSoyouzYkF&GA#R0Launch sitePlesetsk&FLG# 5&GG'  End of lifeVLGGA#R*Decay18 Jan 1993$GG" < G7H1ƀR 7HHKCosmos 2221HGH5 :(qi" Cosmos 22211 7HH'  Generalg HIG#^@") Designation22236 / 92080A\HsIA#R6Launch date24 Nov 1992jIIM#j:"N , Country of originCISy,sIVJM#jX"H̀_剂MissionMilitary: SIGINT (Tselina-D)^IJA#R:"Perigee/Apogee629/662 kmVVJ KA#R*Inclination82.5TJ^KA#R&Period97.6 minr% KKM#jJ" &ቂLaunch vehicleCyclone 3 #100$^KK" < K0L1S 0LxL@Cosmos 2222HKxL5 :(qi" Cosmos 22221 0LL'  Generalg xLMG#^@") Designation22238 / 92081A\LlMA#R6Launch date25 Nov 1992jMMM#j:"N , Country of originCISr+lMHNG#^V"H̀MissionMilitary: early warning (Oko)a MNA#R@"Perigee/Apogee1172/39195 kmVHNNA#R*Inclination62.9UNTOA#R(Period718.1 mincNOG#^8" &Launch vehicleMolniyaYTOA#R0Launch OKsitePlesetsk$O@" < |1DT |Ā-Cosmos 2223H@Ā5 :(qi" Cosmos 22231 |'  Generalg Ā\G#^@") Designation22260 / 92087A[A#R4Launch date9 Dec 1992j\!M#j:"N , Country of originCISt-G#^Z"H̀MissionReconnaissance (5th generation)^!A#R:"Perigee/Apogee238/271 kmVIA#R*Inclination64.6TA#R&Period89.6 minbIG#^6" &Launch vehicleSoyouzYXA#R0Launch siteTyuratam&~# 5X'  End of lifeV~ A#R*Decay16 Dec 1993$-" < i1U ibCosmos 2224H-5 :(qi" Cosmos 22241 i'  Generalg IG#^@") Designation22269 / 92088A\A#R6Launch date17 Dec 1992jIM#j:"N , Country of originCIS>G#^|"H̀MissionMilitary: early warning (Prognoz 2nd generation)o(G#^P"/ۀ0Geostationary orbit12E, inclined\_G#^*" &Launch vehicleYA#R0Launch siteTyuratam[_A#R4"Mass at launch2600 kgO+b$ VBuilt by NPO Lavochkin. S-band capacity< 1DV PCosmos 2230Hb5 :(qi" Cosmos 22301 '  Generalg ~G#^@") Designation22307 / 93001A\ڊA#R6Launch date12 Jan 1993j~DM#j:"N , Country of originCISy&ڊS#vL"H̀(シ 剂MissionNavigation (Tsikada)_DA#R<"Perigee/Apogee968/1005 kmVrA#R*Inclination82.9UnjA#R(Period104.8 minlr3M#j>" &s,梉Launch vehicleCosmos CYnjA#R0Launch sitePlesetsk:3ƍ$ ,Built by PO Polyot8' "(OTechnical dataR.ƍP$ \Downlink frequency: 150 & 400 MHzPlane 11?< 1o€W ԎCosmos 2231HPԎ5 :(qi" Cosmos 22311 '  Generalg ԎlG#^@") Designation22317 / 93004A\ȏA#R6Launch date19 Jan 1993jl>M#j:"N ȏ>P, Country of originCISm&ȏG#^L"H̀MissionMilitary: Reconnaissance^> A#R:"Perigee/Apogee176/369 kmV_A#R*Inclination67.1T A#R&Period89.6 mina_G#^4" &Launch vehicleSoyuzYmA#R0Launch sitePlesetsk5'  End of lifeVmA#R*Decay25 mar 1993$" < X12%X XCosmos 2232H5 :(qi" Cosmos 22321 X'  Generalg 8G#^@") Designation22321 / 93006A\A#R6Launch date26 Jan 1993j8M#j:"N , Country of originCISl%jG#^J"H̀MissionMilitary: Early Warning`A#R>"Perigee/Apogee786/39557 kmVj A#R*Inclination62.9UuA#R(Period717.6 minc G#^8" &Launch vehicleMolniyaYu1A#R0Launch sitePlesetskpL$ Built by NPO PM, operated by the Russian Air Defense Forces (Voyska PVO)< 11€Y %Cosmos 2233H%5 :(qi" Cosmos 22331 V'  Generalg %G#^@") Designation22487 / 93008Ag&V$A#RLLaunch date9 Feb 1993 at 02:50 UTjM#j:"N , Country of originCIS.$S#v\"H̀(シ㼨ԟMissionMilitary: Navigation (Parus)_nA#R<"Perigee/Apogee949/1007 kmVA#R*Inclination82.9UnA#R(Period104.7 minlM#j>" &s,梉Launch vehicleCosmos CYA#R0Launch sitePlesetsk&# 8<' "(OTechnical dataX4$ hDownlink frequency: 150.030 & 400.075 MHzPlane 5< <1%_Z Cosmos 2234H5 :(qi" Cosmos 2234D\) "6Also called Glonass 591 '  Generalg \G#^@") Designation22512 / 93010Ah'\A#RNLaunch date17 Feb 1993 at 20:30 UTjM#j:"N , Country of originCISp#\6M#jF"H̀シMissionNavigation (Uragan)b!A#RB"Perigee/Apogee19106/19152 kmV6 A#R*Inclination64.9 UaA#R(Period675.7 mino" M#jD" &㉓gLaunch vehicleProton #213&a# 5+'  End of lifeWA#R,"Out of serviceyes$+" < 1[ *Cosmos 2235H*5 :(qi" Cosmos 2235[,/ .XAlso called Glonass 60 or Glonass 7571 *'  Generalg G#^@") Designation22513 / 93010Bh'A#RNLaunch date17 Feb 1993 at 20:30 UTjM#j:"N , Country of originCISp#_M#jF"H̀シMissionNavigation (Uragan)b!A#RB"Perigee/Apogee19111/19147 kmT_A#R&Inclination65UjA#R(Period675.7 mino"M#jD" &㉓gLaunch vehicleProton #213&j# 87' "(Technical dataMB#T$Frequency (MHz)L1 = 1602 + 0.5625 * channelL2 = 1246 + 0.4375 * channelN 7A#RChannel5L `A#RPlane1K A#RSlot2$`" <  1_\ S Cosmos 2236HS5 :(qi" Cosmos 2236[, / .XAlso called Glonass 61 or Glonass 7591 S'  Generalg F G#^@") Designation22514 / 93010Ch' A#RNLaunch date17 Feb 1993 at 20:30 UTjF  M#j:"N , Country of originCISp# M#jF"H̀シMissionNavigation (Uragan)b! A#RB"Perigee/Apogee19093/19165 kmT > A#R&Inclination65U A#R(Period675.7 mino">  M#jD" &㉓gLaunch vehicleProton #213& ( # 8 ` ' "(Technical dataM( B#T$Frequency (MHz)L1 = 1602 + 0.5625 * channelL2 = 1246 + 0.4375 * channelO` > A#RChannel21L A#RPlane1K > A#RSlot7$ " < 51] 5}BCosmos 2237H }5 :(qi" Cosmos 22371 5'  Generalg }G#^@") Designation22565 / 93016Ah'}A#RNLaunch date26 Mar 1993 at 02:25 UTj @M#j:"N , Country of originCIS} @ y,}@M#jX"H̀_剂MissionMilitary: SIGINT (Tselina-2)^ @@A#R:"Perigee/Apogee846/852 kmV@9AA#R*Inclination71.0U@AA#R(Period101.9 mini9AAM#j8" &'CMLaunch vehicleZenit$AB" < AWB1^ WBB'GCosmos 2238HBB5 :(qi" Cosmos 22381 WBB'  Generalg B7CG#^@") Designation22585 / 93018Ah'BCA#RNLaunch date30 Mar 1993 at 12:00 UTj7C DM#j:"N , Country of originCIS7CDM#jn"H̀/{MissionMilitary: ocean reconnaissance (Eorsat)^ DDA#R:"Perigee/Apogee127/143 kmVDAEA#R*Inclination65.0TDEA#R&Period87.2 mineAEEG#^<" &Launch vehicleCyclone 2YESFA#R0Launch siteTyuratam&EyF# 5SFF'  End of lifeUyFGA#R(Decay9 Dec 1994$F'G" < GcG1^_ cGGLCosmos 2239H'GG5 :(qi" Cosmos 22391 cGG'  Generalg GCHG#^@") Designation22590 / 93020Ag&GHA#RLLaunch date1 Apr 1993 at 19:00 UTjCHIM#j:"N , Country of originCIS.HIS#v\"H̀(シ㼨ԟMissionMilitary: Navigation (Parus)^IIA#R:"Perigee/Apogee963/996 kmVIIJA#R*Inclination82.9UIJA#R(Period104.7 minlIJ KM#j>" &s,梉Launch vehicleCosmos CYJcKA#R0Launch sitePlesetsk& KK# 8cKK' "(OTechnical dataW3KL$ fDownlink frequency: 149.970 & 399.92 MHzPlane 4< KTL1` TLL[Cosmos 2240HLL5 :(qi" Cosmos 22401 TLL'  Generalg L4MG#^@") Designation22592 / 93021Ag&LMA#RLLaunch date2 Apr 1993 at 14:10 UTj4MNM#j:"N , Country of originCIS?MNG#^~"H̀MissionMilitary: Reconnaissance (Yantar; 4th generation)^NNA#R:"Perigee/Apogee196/342 kmVN?OA#R*Inclination62.8TNOA#R&Period89.6 mina?O G#^4" &Launch vehicleSoyuzO LYOeA#R0Launch sitePlesetsk& # 5e'  End of lifeUA#R(Decay7 Jun 1993&;# wJ- * 2c4th generation Russian reconnaissance satellites (extracted from JSR);[$  It appears that, unlike all earlier Soviet imaging reconnaissance satellites, they do not use the 1959-vintage Vostok satellite bus, although they are probably still made by the same company, the TsSKB (Central Specialized Design Bureau), formerly a subdivision of NPO Energiya. They were introduced in 1975, and originally had a lifetime of 30 days which was a big improvement on the Vostok satellites, at that time limited to 15 day missions. Later minor improvements increased the lifetime, first to 44 days and then, in 1984, to 59 days. The two flights so far this year [1993] show a further improvement, lasting 65 and 66 days. This modest increase is nevertheless significant as the first sign of an upgrade to this satellite class in a decade. By my count [Jonathan McDowell speaking], Kosmos-2240 is the 107th in the series, although the classification of several flights is controversial.< 1^3a ߅Cosmos 2241H[߅5 :(qi" Cosmos 22411 '  Generalg ߅wG#^@") Designation22594 / 93022Ag&ކA#RLLaunch date6 Apr 1993 at 19:10 UTjwHM#j:"N , Country of originCISl%ކG#^J"H̀MissionMilitary: Early Warning`HA#R>"Perigee/Apogee832/39520 kmVjA#R*Inclination63.6UA#R(Period717.7 mincj"G#^8" &Launch vehicleMolniyaY{A#R0Launch sitePlesetsk$"" < {ۉ1Kb ۉ#Cosmos 2242H#5 :(qi" Cosmos 22421 ۉT'  Generalg #G#^@") Designation22626 / 93024Ah'T#A#RNLaunch date16 Apr 1993 at 08:00 UTjM#j:"N , Country of originCISy,#M#jX"H̀_剂MissionMilitary: SIGINT (Tselina-D)^dA#R:"Perigee/Apogee632/666 kmVA#R*Inclination82.5Rd A#R"Period97 minr%~M#jJ" &ቂLaunch vehicleCyclone 3 #103$ " < ~ލ183рc ލ&,Cosmos 2243H&5 :(qi" Cosmos 22431 ލW'  Generalg &G#^@") Designation22641 / 93028Ah'W&A#RNLaunch date27 Apr 1993 at 12:30 UTjM#j:"N , Country of originCIS?&"G#^~"H̀MissionMilitary: Reconnaissance (Kom"eta; 4th generation)^A#R:"Perigee/Apogee180/220 kmV"A#R*Inclination70.4R(A#R"Period88 minaG#^4" &Launch vehicleSoyuzY(A#R0Launch siteTyuratam&# 5='  End of lifev5A#RjCauseExploded with the 3rd stage of the launcherU=A#R(Decay6 May 1993$," < h1Kd hCosmos 2244H,5 :(qi" Cosmos 22441 h'  Generalg HG#^@") Designation22643 / 93029Ah'A#RNLaunch date28 Apr 1993 at 03:35 UTjHM#j:"N , Country of originCIS7M#jn"H̀/{MissionMilitary: ocean reconnaissance (Eorsat)^A#R:"Perigee/Apogee401/417 kmTPA#R&Inclination65TA#R&Period92.8 mineP G#^<" &Launch vehicleCyclone 2YbA#R0Launch siteTyuratam$ " < b1рe Cosmos 2245H 5 :(qi" Cosmos 22451 ;'  Generalg G#^@") Designation22646 / 93030A\;A#R6Launch date11 May 1993jhM#j:"N , Country of originCIS/S#v^"H̀(㓉<MissionTelecommunications (Strela-3)`hJA#R>"Perigee/Apogee1393/1415 kmVA#R*Inclination82.6UJA#R(Period113.9 minr%gM#jJ" &ቂLaunch vehicleCyclone 3 #104$" < g1-f Cosmos 2246H5 :(qi" Cosmos 22461 @'  Generalg G#^@") Designation22647 / 93030B\@A#R6Launch date11 May 1993jmM#j:"N , Country of originCIS/S#v^"H̀(㓉<MissionTelecommunications (Strela-3)`mOA#R>"Perigee/Apogee1397/1415 kmVA#R*Inclination82.6UOA#R(Period113.9 minr%lM#jJ" &ቂLaunch vehicleCyclone 3 #104$" < l1g Cosmos 2247H 5 :(qi" Cosmos 22471 Q'  Generalg G#^@") Designation22648 / 93030C\QA#R6Launch date11 May 1993j~M#j:"N , Country of originCIS/S#v^"H̀(㓉<MissionTelecommunications (Strela-3)`~`A#R>"Perigee/Apogee1400/1415 kmVA#R*Inclination82.6U` A#R(Period114.0 minr%}M#jJ" &ቂLaunch vehicleCyclone 3 #104$ " < }1-h %Cosmos 2248H%5 :(qi" Cosmos 22481 V'  Generalg %G#^@") Designation22649 / 93030D\VA#R6Launch date11 May 1993jM#j:"N , Country of originCIS/S#v^"H̀(㓉<MissionTelecommunications (Strela-3)`eA#R>"Perigee/Apogee1398/1415 kmVA#R*Inclination82.6UeA#R(Period113.9 minr%M#jJ" &ቂLaunch vehicleCyclone 3 #104$" < 1(i * Cosmos 2249H*5 :(qi" Cosmos 22491 ['  Generalg *G#^@") Designation22650 / 93030E\[ A#R6Launch date11 May 1993j M#j:"N , Country of originCIS/ S#v^"H̀(㓉<MissionTelecommunications (Strela-3)` j A#R>"Perigee/Apogee1400/1415 kmV A#R*Inclination82.6Uj  A#R(Period114.0 minr% M#jJ" &ቂLaunch vehicleCyclone 3 #104$ " < 1<j / Cosmos 2250H / 5 :(qi" Cosmos 22501 ` '  Generalg / G#^@") Designation22651 / 93030F\` # A#R6Launch date11 May 1993j M#j:"N , Country of originCIS/# S#v^"H̀(㓉<MissionTelecommunications (Strela-3)` oA#R>"Perigee/Apogee1400/1415 kmVA#R*Inclination82.6UoA#R(Period114.0 minr%M#jJ" &ቂLaunch vehicleCyclone 3 #104$" <  @1(0k @T@2DCosmos 2251 @HT@5 :(qi" Cosmos 22511 @@'  Generalg T@@G#^@") Designation22675 / 93036Ah'@TAA#RNLaunch date16 Jun 1993 at 04:17 UTj@AM#j:"N , Country of originCIS/TA@BS#v^"H̀(㓉<MissionTelecommunications (Strela-1)^ABA#R:"Perigee/Apogee778/803 kmV@BBA#R*Inclination74.0UBICA#R(Period100.7 minlBCM#j>" &s,梉Launch vehicleCosmos CYICDA#R0Launch sitePlesetsk$C2D" < DnD1<Pl nDDCHCosmos 2252H2DD5 :(qi" Cosmos 22521 nDD'  Generalg DNEG#^@") Designation22687 / 93038Ah'DEA#RNLaunch date24 Jun 1994 at 04:12 UTjNE FM#j:"N , Country of originCIS/EFS#v^"H̀(㓉<MissionTelecommunications (Strela-3)` FGA#R>"Perigee/Apogee1400/1415 kmVFXGA#R*Inclination82.6UGGA#R(Period114.0 minr%XGHM#jJ" &ቂLaunch vehicleCyclone 3 #105$GCH" < HH10pm HHTLCosmos 2253HCHH5 :(qi" Cosmos 22531 HH'  Generalg H_IG#^@") Designation22688 / 93038Bh'HIA#RNLaunch date24 Jun 1994 at 04:12 UTj_I1JM#j:"N , Country of originCIS/IJS#v^"H̀(㓉<MissionTelecommunications (Strela-3)`1JKA#R>"Perigee/Apogee1405/1424 kmVJiKA#R*Inclination82.6UKKA#R(Period114.1 minr%iK0LM#jJ" &ቂLaunch vehicleCyclone 3 #105$KTL" < 0LL1Pn LLqCosmos 2254HTLL5 :(qi" Cosmos 22541 L M'  Generalg LpMG#^@") Designation22689 / 93038Ch' MMA#RNLaunch date24 Jun 1994 at 04:12 UTjpMBNM#j:"N , Country of originCIS/MNS#v^"H̀(㓉<MissionTelecommunications (Strela-3)`BN$OA#R>"Perigee/Apogee1390/1412 kmVNzOA#R*Inclination82.6U$OOA#R(Period113.8 minr%zOMM#jJ"OMTL &ቂLaunch vehicleCyclone 3 #105$Oq" < M1p"o Cosmos 2255Hq5 :(qi" Cosmos 22551 &'  Generalg G#^@") Designation22690 / 93038Dh'&A#RNLaunch date24 Jun 1994 at 04:12 UTj_M#j:"N , Country of originCIS/S#v^"H̀(㓉<MissionTelecommunications (Strela-3)`_AA#R>"Perigee/Apogee1401/1413 kmVA#R*Inclination82.6UAA#R(Period113.9 minr%^M#jJ" &ቂLaunch vehicleCyclone 3 #105$" < ^1Bp Cosmos 2256H5 :(qi" Cosmos 22561 7'  Generalg G#^@") Designation22691 / 93038Eh'7A#RNLaunch date24 Jun 1994 at 04:12 UTjpM#j:"N , Country of originCIS/S#v^"H̀(㓉<MissionTelecommunications (Strela-3)`pRA#R>"Perigee/Apogee1397/1412 kmVA#R*Inclination82.6URA#R(Period113.9 minr%oM#jJ" &ቂLaunch vehicleCyclone 3 #105$" < oψ1"bq ψCosmos 2257H5 :(qi" Cosmos 22571 ψH'  Generalg G#^@") Designation22692 / 93038Fh'HA#RNLaunch date24 Jun 1994 at 04:12 UTjM#j:"N , Country of originCIS/S#v^"H̀(㓉<MissionTelecommunications (Strela-3)`cA#R>"Perigee/Apogee1404/1419 kmVA#R*Inclination82.6UcA#R(Period114.0 minr%M#jJ" &ቂLaunch vehicleCyclone 3 #105$" < 1B]r (Cosmos 2258H(5 :(qi" Cosmos 22581 Y'  Generalg (G#^@") Designation93044A / 22709g&Y'A#RLLaunch date8 Jul 1993 at 07:15 UTjM#j:"N , Country of originCIS7'M#jn"H̀/{MissionMilitary: ocean reconnaissance (Eorsat)^sA#R:"Perigee/Apogee400/417 kmTǏA#R&Inclination65Ts'A#R&Ǐ'Period92.8 mineǏG#^<" &Launch vehicleCyclone 2Y'A#R0Launch siteTyuratam& # 5@'  End of lifeU A#R(Decay8 Jun 1995$@" < 1bs =Cosmos 2259H=5 :(qi" Cosmos 22591 n'  Generalg =G#^@") Designation22716 / 93045Ah'n=A#RNLaunch date14 Jul 1993 at 16:40 UTjM#j:"N , Country of originCIS?=-G#^~"H̀MissionMilitary: Reconnaissance (Yantar; 4th generation)^A#R:"Perigee/Apogee168/349 kmV-A#R*Inclination67.1T5A#R&Period89.7 minaG#^4" &Launch vehicleSoyuzY5A#R0Launch sitePlesetsk|Xk$ It reentered after only 11 days in space. It was expected to stay up for two months.5'  End of lifeWkA#R,Landed25 Jul 1993$" < W1]et WCosmos 2260H5 :(qi" Cosmos 22601 W'  Generalg 7G#^@") Designation22721 / 93047Ah'A#RNLaunch date22 Jul 1993 at 08:56 UTj7 M#j:"N , Country of originCISx1G#^b"H̀MissionMilitary: Remote Sensing (Resurs T)^ A#R:"Perigee/Apogee177/224 kmV5A#R*Inclination82.3TA#R&Period88.5 mina5G#^4" &Launch vehicleSoyuzYCA#R0Launch sitePlesetsk&i# 5C'  End of lifeViA#R*Landed5 Aug 1993$" < T12u TCosmos 2261H5 :(qi" Cosmos 22611 T'  Generalg 4G#^@") Designation22741 / 93051Ah'A#RNLaunch date10 Aug 1993 at 15:00 UTj4M#j:"N , Country of originCISr+xG#^V"H̀MissionMilitary: Early Warning (Oko)`A#R>"Perigee/Apogee690/39674 kmTx,A#R&Inclination63SA#R$Period718 minc, G#^8" &Launch vehicleMolniya YeA#R0Launch sitePlesetsk> $ 4built by NPO Lavochkin< e1ev 'xCosmos 2262H'5 :(qi" Cosmos 22621 X'  Generalg 'G#^@") Designation22789 / 93057Ag&X&A#RLLaunch date7 Sep 1993 at 13:30 UTjM#j:"N , Country of originCIS~7&G#^n"H̀MissionMilitary: Reconnaissance (6th generation)^lA#R:"Perigee/Apogee207/323 kmTA#R&Inclination65RlA#R"Period89 minasG#^4" &Launch vehicleSoyuzYA#R0Launch siteTyuratamsx% Fifth in a new series of imaging satellites which fly two-month long missions. Previous satellites were 2031, 2101, 2163, and 2225.< 12aw  Cosmos 2263Hx5 :(qi" Cosmos 22631 -'  Generalg G#^@") Designation22802 / 93059Ah'-A#RNLaunch date16 Sep 1993 at 07:36 UTjfM#j:"N , Country of originCISy,M#jX"H̀_剂MissionMilitary: SIGINT (Tselina-2)^f=A#R:"Perigee/Apogee848/854 kmTA#R&Inclination71S=A#R$Period102 miniM M#j8" &'CMLaunch vehicleZenitq $ The program had three consecutive launch failures in 1990-1992, but the last 4 launches have been successful.< M  1"x  f Cosmos 2264H f 5 :(qi" Cosmos 22641  '  Generalg f G#^@") Designation22808 / 93060A\ Z A#R6Launch date17 Sep 1993j M#j:"N , Country of originCIS7Z H M#jn"H̀/{MissionMilitary: ocean reconnaissance (Eorsat)^ A#R:"Perigee/Apogee402/418 kmTH A#R&Inclination65T N A#R&Period92.8 mine G#^<" &Launch vehicleCyclone 2^N A#R:Launch siteTyuratam LC90 % -It carries a low thrust engine to maintain precise separation with other EORSATs and uses radio interferometry to locate transmissions from ships.< 1ay P?CCosmos 2265HP5 :(qi" Cosmos 22651 '  Generalg P @G#^@") Designation22875 / 93067A @h't@A#RNLaunch date26 Oct 1993 at 10:00 UTj @@M#j:"N , Country of originCISj#t@HAG#^F"H̀MissionMilitary: calibration_@AA#R<"Perigee/Apogee291/1573 kmTHAAA#R&Inclination83UAPBA#R(Period103.5 minlABM#j>" &s,梉Launch vehicleCosmos C_PBCA#R<Launch sitePlesetsk LC132$B?C" < C{C1H"z {CCHCosmos 2266H?CC5 :(qi" Cosmos 22661 {CC'  Generalg C[DG#^@") Designation22888 / 93070Ag&CDA#RLLaunch date2 Nov 1993 at 12:10 UTj[D,EM#j:"N , Country of originCIS.DES#v\"H̀(シ㼨ԟMissionMilitary: Navigation (Parus)_,E FA#R<"Perigee/Apogee945/1017 kmTE`FA#R&Inclination83S FFA#R$Period104 minb`FGG#^6" &Launch vehicleCosmos_FtGA#R<Launch sitePlesetsk LC132&GG# 5tGG'  End of lifeWG&HA#R,"Out of serviceyes&GLH# 8&HH' "(OTechnical dataV2LHH$ dDownlink frequency: 149.97 & 399.92 MHzPlane 1< HI1ȃ{ I^I?MCosmos 2267HH^I5 :(qi" Cosmos 22671 II'  Generalg ^IIG#^@") Designation22904 / 93071Ag&I]JA#RLLaunch date5 Nov 1993 at 08:25 UTjIJM#j:"N , Country of originCISI]JWKG#^"H̀MissionMilitary: Reconnaissance (advanced Yantar'; 5th generation)^JKA#R:"Perigee/Apogee241/282 kmVWK LA#R*Inclination70.4RK]LA#R"Period89 mina LLG#^4" &Launch vehicleSoyuz]]LMA#R8Launch siteTyuratam LC1$L?M" < M{M1Q| {MM]Cosmos 2268H?MM5 :(qi" Cosmos 22681 {MM'  Generalg M[NG#^@") Designation22999 / 94011Ah'MNA#RNLaunch date12 Feb 1994 at 08:54 UTj[N-OM#j:"N , Country of originCIS/NOS#v^"H̀(㓉<MissionTelecommunications (Strela-3)`-OA#R>"Perigee/ApogeeO?M1411/1426 kmWOrA#R,Inclination82.57UǀA#R(Period114.2 minr%r9M#jJ" &ቂLaunch vehicleCyclone 3 #108$ǀ]" < 91ȃr} oCosmos 2269H]5 :(qi" Cosmos 22691 '  Generalg yG#^@") Designation23000 / 94011Bh'A#RNLaunch date12 Feb 1994 at 08:54 UTjyKM#j:"N , Country of originCIS/̓S#v^"H̀(㓉<MissionTelecommunications (Strela-3)`K-A#R>"Perigee/Apogee1410/1421 kmW̓A#R,Inclination82.56U-لA#R(Period114.2 minr%KM#jJ" &ቂLaunch vehicleCyclone 3 #108$لo" < K1Q~ Cosmos 2270Ho5 :(qi" Cosmos 22701 $'  Generalg G#^@") Designation23001 / 94011Ch'$A#RNLaunch date12 Feb 1994 at 08:54 UTj]M#j:"N , Country of originCIS/߇S#v^"H̀(㓉<MissionTelecommunications (Strela-3)`]?A#R>"Perigee/Apogee1406/1417 kmW߇A#R,Inclination82.57V?A#R*Period114.05 minr%^M#jJ" &ቂLaunch vehicleCyclone 3 #108$" < ^1r Cosmos 2271H5 :(qi" Cosmos 22711 7'  Generalg G#^@") Designation23002 / 94011Dh'7A#RNLaunch date12 Feb 1994 at 08:54 UTjpM#j:"N , Country of originCIS/S#v^"H̀(㓉<MissionTelecommunications (Strela-3)`pRA#R>"Perigee/Apogee1403/1415 kmWA#R,Inclination82.57SRA#R$Period114 minr%nM#jJ" &ቂLaunch vehicleCyclone 3 #108$" < n΍1p ΍Cosmos 2272H5 :(qi" Cosmos 22721 ΍G'  Generalg G#^@") Designation23003 / 94011Eh'GA#RNLaunch date12 Feb 1994 at 08:54 UTjM#j:"N , Country of originCIS/S#v^"H̀(㓉<MissionTelecommunications (Strela-3)`nA#R>"Perigee/Apogee1396/1415 kmWA#R,Inclination82.57UnA#R(Period113.9 minr%M#jJ" &ቂLaunch vehicleCyclone 3 #108$" < 1 4Cosmos 2273H45 :(qi" Cosmos 22731 e'  Generalg 4G#^@") Designation23004 / 94011Fh'e4A#RNLaunch date12 Feb 1994 at 08:54 UTjM#j:"N , Country of originCIS/4 S#v^"H̀(㓉<MissionTelecommunications (Strela-3)`A#R>"Perigee/Apogee1408/1416 kmW A#R,Inclination82.57U,A#R(Period113.9 minr%M#jJ" &ቂLaunch vehicleCyclone 3 #108$," < 1%p F:Cosmos 2274HF5 :(qi" Cosmos 22741 w'  Generalg FG#^@") Designation23033 / 94018Ah'wFA#RNLaunch date17 Mar 1994 at 16:30 UTjM#j:"N , Country of originCIS@F7G#^"H̀MissionMilitary: reconnaissance (Yantar'; 4th generation)b!A#RB"Perigee/Apogee176.1/371.7 kmW7A#R,Inclination67.15UEA#R(Period89.65 mincG#^8" &Launch vehicleSoyuz U^EA#R:Launch sitePlesetsk LC43&,# 5a'  End of life_,A#R<CauseLanded in KazakhstanVaA#R*Decay21 May 1994$:" < v1& voCosmos 2275H:5 :(qi" Cosmos 2275[,v/ .XAlso called Glonass 62 or Glonass 7601 J'  Generalg G#^@") Designation23043 / 94021Ah'JA#RNLaunch date11 Apr 1994 at 08:49 UTjM#j:"N , Country of originCISp#M#jF"H̀シMissionNavigation (Uragan)b!UA#RB"Perigee/Apogee19120/19197 kmTA#R&Inclination64SUA#R$Period676 mino"kM#jD" &㉓gLaunch vehicleProton #222&# 8k' "(Technical dataMdB#Td:$Frequency (MHz)L1 = 1602 + 0.5625 * channelL2 = 1246 + 0.4375 * channelOA#RChannel24L dA#RPlane3L KA#RSlot17$o" < K1 Cosmos 2276Ho5 :(qi" Cosmos 2276[,N/ .XAlso called Glonass 63 or Glonass 7611 '  Generalg NG#^@") Designation23044 / 94021Bh'NA#RNLaunch date11 Apr 1994 at 08:49 UTjM#j:"N , Country of originCISp#N(M#jF"H̀シMissionNavigation (Uragan)b!A#RB"Perigee/Apogee19120/19197 kmT(A#R&Inclination64S1A#R$Period676 mino"M#jD" &㉓gLaunch vehicleProton #222&1# 8' "(Technical dataMB#T$Frequency (MHz)L1 = 1602 + 0.5625 * channelL2 = 1246 + 0.4375 * channelN A#RChannel3L 'A#RPlane3L sA#RSlot23$'" < s1& zCosmos 2277H5 :(qi" Cosmos 2277[,v/ .XAlso called Glonass 64 or Glonass 7581 '  Generalg v G#^@") Designation23045 / 94021Ch'v A#RNLaunch date11 Apr 1994 at 08:49 UTj M#j:"N , Country of originCISp#v P M#jF"H̀シMissionNavigation (Uragan)b! A#RB"Perigee/Apogee19120/19197 kmTP  A#R&Inclination64S Y A#R$Period676 mino" M#jD" &㉓gLaunch vehicleProton #222&Y # 5 # '  End of life_ A#R<"Out of service28 Jul 1995&# # 8 ' "(Technical dataM o B#T$Frequency (MHz)L1 = 1602 + 0.5625 * channelL2 = 1246 + 0.4375 * channelO A#RChannel10L o A#RPlane3L VA#RSlot18$ z" < V1 BCosmos 2278Hz5 :(qi" Cosmos 22781 /'  Generalg G#^@") Designation23087 / 94023Ah'/ @A#RNLaunch date23 Apr 1994 at 08:02 UT @zjv@M#j:"N , Country of originCISy, @@M#jX"H̀_剂MissionMilitary: SIGINT (Tselina-2)^v@MAA#R:"Perigee/Apogee854/858 kmT@AA#R&Inclination71SMAAA#R$Period102 miniA]BM#j8" &'CMLaunch vehicleZenit$AB" < ]BB1% BC{GCosmos 2279HBC5 :(qi" Cosmos 22791 B6C'  Generalg CCG#^@") Designation23092 / 94024Ah'6CDA#RNLaunch date26 Apr 1994 at 02:14 UTjCoDM#j:"N , Country of originCIS.DDS#v\"H̀(シ㼨ԟMissionMilitary: Navigation (Parus)_oDOEA#R<"Perigee/Apogee955/1007 kmTDEA#R&Inclination83UOEEA#R(Period104.7 minlEdFM#j>" &s,梉Launch vehicleCosmos C_EFA#R<Launch sitePlesetsk LC133&dFF# 8F!G' "(OTechnical dataZ6F{G$ lDonwlink frequencies: 149.940 & 399.840 MHzPlane 6< !GG1 GGLCosmos 2280H{GG5 :(qi" Cosmos 22801 G0H'  Generalg GHG#^@") Designation23095 / 94025A\0HHA#R6Launch date28 Apr 1994jH]IM#j:"N , Country of originCISIHIG#^"H̀MissionMilitary: reconnaissance (advanced Yantar'; 5th generation)^]IKJA#R:"Perigee/Apogee244/305 kmVIJA#R*Inclination70.3RKJJA#R"Period90 mincJVKG#^8" &Launch vehicleSoyuz U^JKA#R:Launch siteTyuratam LC31&VKK# 5KL'  End of lifeVKeLA#R*Decay22 Mar 1995$LL" < eLL1% L MfCosmos 2281HL M5 :(qi" Cosmos 22811 L>M'  Generalg MMG#^@") Designation23119 / 94032Ag&>M NA#RLLaunch date7 Jun 1994 at 07:20 UTjMvNM#j:"N , Country of originCISN N OG#^"H̀MissionMilitary: reconnaissance (Vostok/Zenit or Oblik; 4th generation)^vNiOA#R:"Perigee/Apogee192/265 kmV OOA#R*Inclination82.6TiOA#R&OLPeriod88.7 mincOG#^8" &Launch vehicleSoyuz UYۀA#R0Launch sitePlesetsk' kThe number 2281 had earlier been assigned to an identical spacecraft that was launched on May 26 but failed to attain orbit. This flight could be similar to Cosmos 2207 in 1992. The first Vostok based spy satellites were the Zenit 2 series. The first one to reach orbit, in 1962, was given the code name Cosmos 0004. The Zenit derived spy satellites have now been almost entirely phased out in favour of a newer bus called Yantar'.5ۀ'  End of lifeVBA#R*Decay29 Jun 1994$f" < B1 Cosmos 2282Hf5 :(qi" Cosmos 22821 '  Generalg G#^@") Designation23168 / 94038Ag&A#RLLaunch date6 Jul 1994 at 23:59 UTjSM#j:"N , Country of originCIS>؅G#^|"H̀MissionMilitary: early warning (Prognoz 2nd generation)g&S?A#RL,Geostationary orbit24W, inclinedo"؅M#jD" &㉓gLaunch vehicleProton #224[? A#R4"Mass at launch2600 kg&/# 5 d'  End of life]/A#R8"Out of serviceDec 1995?&d# 8' "(OTechnical datamH% Built by NPO LavochkinEquipped with a 500 kg 1 m diameter telescope< Ȉ1  ȈCosmos 2283H5 :(qi" Cosmos 22831 ȈA'  Generalg G#^@") Designation23182 / 94042A\AA#R6Launch date20 Jul 1994jnM#j:"N , Country of originCIS@G#^"H̀MissionMilitary: reconnaissance (Yantar'; 4th generation)^nSA#R:"Perigee/Apogee179/356 kmVA#R*Inclination67.1TSA#R&Period89.5 mina^G#^4" &Launch vehicleSoyuzYA#R0Launch sitePlesetsk&^݌# 5'  End of lifeV݌hA#R*Decay29 Sep 1994$" < hȍ1` ȍgCosmos 2284H5 :(qi" Cosmos 22841 ȍA'  Generalg G#^@") Designation23187 / 94044Ah'AA#RNLaunch date29 Jul 1994 at 09:29 UTjzM#j:"N , Country of originCIS? G#^~"H̀MissionMilitary: reconnaissance (Kometa; 4th generation)z ^zjA#R:"Perigee/Apogee206/296 kmV A#R*Inclination70.4TjA#R&Period89.2 mincwG#^8" &Launch vehicleSoyuz U^A#R:Launch siteTyuratam LC31w& {It is presumably the 17th in the 'Kometa' series of topographic mapping satellites, based on the Yantar' spy satellite design. Kometa satellite imagery would be commercially distributed by AO Sovinformsputnik.The last Kometa satellite, Kosmos-2243, was damaged during launch in Apr 1993. Typical mission length is 44 days. The first Kometa satellite was Kosmos-1246, in 1981. All the Kometa satellites are launched by Soyuz-U from Baykonur.5'  End of lifeVCA#R*Decay11 Sep 1994$g" < C1  Cosmos 2285Hg5 :(qi" Cosmos 22851 '  Generalg G#^@") Designation23189 / 94045Ag&A#RLLaunch date2 Aug 1994 at 20:00 UTjTM#j:"N , Country of originCISv/G#^^"H̀MissionMilitary: calibration or geodesy?_T)A#R<"Perigee/Apogee974/1013 kmT}A#R&Inclination74S)A#R$Period105 minl}<M#j>" &s,梉Launch vehicleCosmos C_A#R<Launch sitePlesetsk LC132$<" < 1H`  CZCosmos 2286HC5 :(qi" Cosmos 22861 t'  Generalg CG#^@") Designation23194 / 94048Ag&tBA#RLLaunch date5 Aug 1994 at 01:12 UTjM#j:"N , Country of originCIS8B+G#^p"H̀MissionMilitary: early warning (Oko, means "eye")`A#R>"Perigee/Apogee747/39608 kmV+A#R*Inclination63.4S4A#R$Period718 mincG#^8" &Launch vehicleMolniyaY4A#R0Launch sitePlesetskjFZ$ It carries a large telescope to detect ballistic missile launches.< 1 Cosmos 2287HZ5 :(qi" Cosmos 2287[,9/ .XAlso called Glonass 65 or Glonass 7671 j'  Generalg 9G#^@") Designation23203 / 94050Ah'j9A#RNLaunch date11 Aug 1994 at 15:27 UTjM#j:"N , Country of originCISp#9M#jF"H̀シMissionNavZigation (Uragan)b!A#RB"Perigee/Apogee19109/19150 kmTA#R&Inclination64S(A#R$Period676 mino"M#jD" &㉓gLaunch vehicleProton #225&(# 8' "(Technical dataMB#T$Frequency (MHz)L1 = 1602 + 0.5625 * channelL2 = 1246 + 0.4375 * channelOA#RChannel22L A#RPlane2L kA#RSlot12$" < k1   Cosmos 2288H5 :(qi" Cosmos 2288[,n/ .XAlso called Glonass 66 or Glonass 7701 '  Generalg nG#^@") Designation23204 / 94050B\bA#R6Launch date11 Aug 1994jM#j:"N , Country of originCISp#b<M#jF"H̀シMissionNavigation (Uragan)b!A#RB"Perigee/Apogee19091/19168 kmT<A#R&Inclination64SEA#R$Period676 mino"M#jD" &㉓gLaunch vehicleProton #225&E# 8' "(Technical dataMB#T$Frequency (MHz)L1 = 1602 + 0.5625 * channelL2 = 1246 + 0.4375 * channelN A#RChannel9L ; A#RPlane2L  A#RSlot14$; " < 1T / Cosmos 2289H / 5 :(qi" Cosmos 2289[, / .XAlso called Glonass 67 or Glonass 7751 / '  Generale G#^<") Designation23205 94050C\ | A#R6Launch date11 Aug 1994j M#j:"N , Country of originCISp#| V M#jF"H̀シMissionNavigation (Uragan)b! A#RB"Perigee/Apogee19126/19133 kmTV A#R&Inclination64S _ A#R$Period676 mino" M#jD" &㉓gLaunch vehicleProton #225&_ # 8 ,' "(Technical dataM B#T$Frequency (MHz)L1 = 1602 + 0.5625 * channelL2 = 1246 + 0.4375 * channelO, A#RChannel22L VA#RPlane2L A#RSlot16$V" < @1 H @V@ICosmos 22@90HV@5 :(qi" Cosmos 22901 @@'  Generalg V@@G#^@") Designation23218 / 94053Ah'@VAA#RNLaunch date26 Aug 1994 at 12:00 UTj@AM#j:"N , Country of originCIS>VAEBG#^|"H̀MissionMilitary: reconnaissance (Kuban; 7th generation)^ABA#R:"Perigee/Apogee211/292 kmVEBBA#R*Inclination64.8TBMCA#R&Period90.2 miniBCM#j8" &'CMLaunch vehicleZenitrMCOF' This is a 7th generation "Kuban" reconnaissance satellite. Five such satellites had been launched in 1986 and 1987. Built by the TsSKB in Samara, they were prototypes of a new spacecraft generation. Civilian applications are knowned as Nika-T (microgravity), Nika-B (medical/biology) and Nika-E (high energy particles). Are supposed to weigh 9 tons and stay in orbit 90 to 120 days. The payload which takes place in a 4.3m3 capsule weighs 1.2t. This specific satellite could be a digital imaging satellite. A commercial version should be available in September 1996; it should be equipped with a 2 m resolution imager.CI% #In late March 1995 (between Mar 24 and 29) the spacecraft raised its apogee by 200 km, from an orbit of 181 x 382 km x 64.8 to 181 x 571 km x 64.8, and four new small objects were tracked in the post-maneuver orbit. It seems likely that this marks the end of the Kosmos-2290 mission. Russian spy satellites are usually deorbited at the end of their mission, and it is not clear whether the orbit raise of Kosmos-2290 reflects a new operational regime, a new disposal strategy, a deorbit burn that went in the wrong direction, or (less likely) a tracking by US Space Command of a residual part of the spacecraft following recovery of a reentry vehicle.5OF:I'  End of lifeUIIA#R(Decay4 Apr 1995$:II" < II1xTч I7J~OCosmos 2291HI7J5 :(qi" Cosmos 22911 IhJ'  Generalg 7JJG#^@") Designation23267 / 94060Ah'hJ7KA#RNLaunch date21 Sep 1994 at 17:53 UTjJKM#j:"N , Country of originCIS67K*LS#vl"H̀(‰MissionMilitary: telecommunications: Geizerb!KLA#RB,Geostationary orbitsee belowo"*LLM#jD" &㉓gLaunch vehicleProton #226&L!M# : L[M- */ۀ Locationv!MM^#0 BeginEndPosition([McNj#P$BDL: 21 Sep 1994late-Sep 199580WMNj#.Nov 199513.5W&cN O# 8NBO' "(Technical data< O~O) "&$Specifications< BOO1 H! OCosmos 2292H~O5 :(qi" Cosmos 2292O~O1 O?'  Generalg G#^@") Designation23278 / 94061Ah'?A#RNLaunch date27 Sep 1994 at 14:00 UTjxM#j:"N , Country of originCISt-G#^Z"H̀MissionMilitary: calibration (vektor?)_xKA#R<"Perigee/Apogee400/1951 kmVA#R*Inclination82.9UKA#R(Period108.9 minlbM#j>" &s,梉Launch vehicleCosmos C_A#R<Launch sitePlesetsk LC132$b" < !1ч !iCosmos 2293Hi5 :(qi" Cosmos 22931 !'  Generalg iG#^@") Designation23336 / 94072Ah'iA#RNLaunch date2 Nov 1994 at 01:04 UTjӅM#j:"N , Country of originCIS7iWM#jn"H̀/{MissionMilitary: ocean reconnaissance (Eorsat)^ӅA#R:"Perigee/Apogee402/418 kmTW A#R&Inclination65T]A#R&Period92.8 mine ‡G#^<" &Launch vehicleCyclone 2Y]A#R0Launch siteTyuratam<‡W$ 0Replaced Cosmos 22385'  End of lifeVWA#R*Decay13 May 1996$" < B1!Q B0Cosmos 2294H5 :(qi" Cosmos 2294[,B/ .XAlso called Glonass 68 or Glonass 7631 '  Generalg }G#^@") Designation23396 / 94076Ah'A#RNLaunch date20 Nov 1994 at 00:09 UTj}OM#j:"N , Country of originCISp#M#jF"H̀シMissionNavigation (Uragan)b!O!A#RB"Perigee/Apogee19052/19207 kmVwA#R*Inclination64.9S!ʌA#R$Period675 mino"w9M#jD" &㉓gLaunch vehicleProton #229&ʌ_# 89' "(Technical dataM_&B#T$Frequency (MHz)L1 = 1602 + 0.5625 * channelL2 = 1246 + 0.4375 * channelOuA#RChannel21L &A#RPlane1K u A#RSlot3$0" < l1 lfCosmos 2295H05 :(qi" Cosmos 2295[,l/ .XAlso called Glonass 69 or 0Glonass 7641 L'  Generalg G#^@") Designation23397 / 94076Bh'LA#RNLaunch date20 Nov 1994 at 00:09 UTjM#j:"N , Country of originCISp#M#jF"H̀シMissionNavigation (Uragan)b!WA#RB"Perigee/Apogee19052/19207 kmVA#R*Inclination64.9SWA#R$Period675 mino"oM#jD" &㉓gLaunch vehicleProton #229&# 8o' "(Technical dataM\B#T$Frequency (MHz)L1 = 1602 + 0.5625 * channelL2 = 1246 + 0.4375 * channelOA#RChannel13L \A#RPlane1K BA#RSlot6$f" < B1Q@ Cosmos 2296Hf5 :(qi" Cosmos 2296[,E/ .XAlso called Glonass 70 or Glonass 7621 v'  Generalg EG#^@") Designation23398 / 94076Ch'vEA#RNLaunch date20 Nov 1994 at 00:09 UTjM#j:"N , Country of originCISp#EM#jF"H̀シMissionNavigation (Uragan)b!A#RB"Perigee/Apogee19118/19114 kmTA#R&Inclination65S(A#R$Period675 mino"M#jD" &㉓gLaunch vehicleProton #229&(# 8' "(Technical dataMB#T$Frequency (MHz)L1 = 1602 + 0.5625 * channelL2 = 1246 + 0.4375 * channelOA#RChannel12L A#RPlane1K jA#RSlot4$" < j1   Cosmos 2297H5 :(qi" Cosmos 22971 C'  Generalg G#^@") Designation23404 / 94077Ah'CA#RNLaunch date24 Nov 1994 at 09:16 UTj|M#j:"N , Country of originCISy,M#jX"H̀_剂MissionMilitary: SIGINT (Tselina-2)^|SA#R:"Perigee/Apogee845/857 kmTA#R&Inclination71SSA#R$Period102 minicM#j8" &'CMLaunch vehicleZenitc $ The satellite carries an array of electronic intelligence detectors to monitor radio emissions.c < cH1@4 HrCosmos 2298H 5 :(qi" Cosmos 22981 H'  Generalg (G#^@") Designation23431 / 94083Ah'A#RNLaunch date20 Dec 1994 at 05:11 UTj(M#j:"N , Country of originCIS/|S#v^"H̀(㓉<MissionTelecommunications (Strela-1)^A#R:"Perigee/Apogee785/810 kmT|.A#R&Inclination74UA#R(Period100.8 minl.M#j>" &s,梉Launch vehicleCosmos C_NA#R<Launch sitePlesetsk LC132$r" < N1R Cosmos 2299Hr5 :(qi" Cosmos 22991 ''  Generalg G#^@") Designation23441 / 94086Ah''A#RNLaunch date26 Dec 1994 at 22:27 UTj`M#j:"N , Country of originCIS/S#v^"H̀(㓉<MissionTelecommunications (Strela-3)``BA#R>"Perigee/Apogee1402/1415 kmVA#R*Inclination82.6SBA#R$Period114 minr%]M#jJ" &ቂLaunch vehicleCyclone 3 #113$" < ]14p  Cosmos 2300H 5 :(qi" Cosmos 23001 6 '  Generalg  G#^@") Designation23442 / 94086Bh'6  A#RNLaunch date26 Dec 1994 at 22:27 UTj o M#j:"N , Country of originCIS/ S#v^"H̀(㓉<MissionTelecommunications (Strela-3)`o Q A#R>"Perigee/Apogee1410/1414 kmV A#R*Inclination82.5SQ A#R$Period114 minr% l M#jJ" &ቂLaunch vehicleCyclone 3 #113$ " < l 1R'  @Cosmos 2301H  5 :(qi" Cosmos 23011 E '  Generalg  G#^@") Designation23443 / 94086Ch'E A#RNLaunch date26 Dec 1994 at 22:27 UTj ~M#j:"N , Country of originCIS/S#v^"H̀(㓉<MissionTelecommunications (Strela-3)`~`A#R>"Perigee/Apogee1410/1414 kmVA#R*Inclination82.5S`@A#R$Period@ 114 minr%@M#jJ" &ቂLaunch vehicleCyclone 3 #113$@@" < @@1pG @/ADCosmos 2302H@/A5 :(qi" Cosmos 23021 @`A'  Generalg /AAG#^@") Designation23444 / 94086Dh'`A/BA#RNLaunch date26 Dec 1994 at 22:27 UTjABM#j:"N , Country of originCIS//BCS#v^"H̀(㓉<MissionTelecommunications (Strela-3)`B{CA#R>"Perigee/Apogee1413/1423 kmVCCA#R*Inclination82.6U{C&DA#R(Period114.2 minr%CDM#jJ" &ቂLaunch vehicleCyclone 3 #113$&DD" < DD1'g D@EHCosmos 2303HD@E5 :(qi" Cosmos 23031 DqE'  Generalg @EEG#^@") Designation23445 / 94086Eh'qE@FA#RNLaunch date26 Dec 1994 at 22:27 UTjEFM#j:"N , Country of originCIS/@F,GS#v^"H̀(㓉<MissionTelecommunications (Strela-3)`FGA#R>"Perigee/Apogee1413/1430 kmV,GGA#R*Inclination82.6UG7HA#R(Period114.3 minr%GHM#jJ" &ቂLaunch vehicleCyclone 3 #113$7HH" < H I1G IQILCosmos 2304HHQI5 :(qi" Cosmos 23041 II'  Generalg QIIG#^@") Designation23446 / 94086Fh'IQJA#RNLaunch date26 Dec 1994 at 22:27 UTjIJM#j:"N , Country of originCIS/QJ=KS#v^"H̀(㓉<MissionTelecommunications (Strela-3)`JKA#R>"Perigee/Apogee1412/1417 kmV=KKA#R*Inclination82.6UKHLA#R(Period114.1 minr%KLM#jJ" &ቂLaunch vehicleCyclone 3 #113$HLL" < LM1Ug MbMCosmos 2305HLbM5 :(qi" Cosmos 23051 MM'  Generalg bMMG#^@") Designation23453 / 94088Ah'MbNA#RNLaunch date29 Dec 1994 at 11:31 UTjMNM#j:"N , Country of originCISIbN\OG#^"H̀MissionMilitary: reconnaissance (advanced Yantar'; 5th generation)^NOA#R:"Perigee/Apogee231/288 kmV\OA#R*InclOLination64.9TOpA#R&Period89.7 mincӀG#^8" &Launch vehicleSoyuz U^p1A#R:Launch siteTyuratam LC31U1Ӏ$ bThis spacecraft raises its orbit periodically51'  End of lifeR A#R"CausedeorbitVcA#R*Decay18 Dec 1995$ " < cÂ1iG  CCosmos 2306H 5 :(qi" Cosmos 23061 Â<'  Generalg G#^@") Designation23501 / 95008Ag&< A#RLLaunch date2 Mar 1995 at 13:00 UTjtM#j:"N , Country of originCIS|5 G#^j"H̀MissionMilitary: calibration (cosmos 816 type)^tNA#R:"Perigee/Apogee469/516 kmVA#R*Inclination65.8TNA#R&Period94.5 minldM#j>" &s,梉Launch vehicleCosmos CYA#R0Launch sitePlesetskbdC$ Releases a series of small objects at intervals, to act as calibration targets for the radars.< 1 LJdCosmos 2307HCLJ5 :(qi" Cosmos 2307[,"/ .XAlso called Glonass 71 or Glonass 7651 LJS'  Generalg "G#^@") Designation23511 / 95009Ag&S!A#RLLaunch date7 Mar 1995 at 09:23 UTjM#j:"N , Country of originCISp#!M#jF"H̀シMissionNavigation (Uragan)\WA#R6"Perigee/Apogee19132 kmTA#R&Inclination64SWA#R$Period279 mino"mM#jD" &㉓gLaunch vehicleProton #232&# 8mˋ' "(Technical dataMZB#T$Frequency (MHz)L1 = 1602 + 0.5625 * channelL2 = 1246 + 0.4375 * channelN ˋA#RChannel1L ZA#RPlane3L @A#RSlot20$d" < @1G Cosmos 2308Hd5 :(qi" Cosmos 2308[,C/ .XAlso called Glonass 72 or Glonass 7661 t'  Generalg CێG#^@") Designation23512 / 95009Bg&tBA#RLLaunch date7 Mar 1995 at 09:23 UTjێM#j:"N , Country of originCISp#B(M#jF"H̀シMissi(donNavigation (Uragan)\A#R6"Perigee/Apogee19132 kmT(A#R&Inclination64S+A#R$Period279 mino"M#jD" &㉓gLaunch vehicleProton #232&+# 8' "(Technical dataMB#T$Frequency (MHz)L1 = 1602 + 0.5625 * channelL2 = 1246 + 0.4375 * channelOA#RChannel10L "A#RPlane3L nA#RSlot22$"" < n1 Cosmos 2309H5 :(qi" Cosmos 2309[,q/ .XAlso called Glonass 73 or Glonass 7771 '  Generalg q G#^@") Designation23513 / 95009Cg&pA#RLLaunch date7 Mar 1995 at 09:23 UTj M#j:"N , Country of originCISp#pJM#jF"H̀シMissionNavigation (Uragan)\A#R6"Perigee/Apogee19132 kmTJA#R&Inclination64SMA#R$Period279 mino"M#jD" &㉓gLaunch vehicleProton #232&M# 8' "(Technical dataMB#T$Frequency (MHz)L1 = 1602 + 0.5625 * channelL2 = 1246 + 0.4375 * channelN A#RChannel3L CA#RPlane3L A#RSlot19$C" < 1 7Cosmos 2310H75 :(qi" Cosmos 23101 h'  Generalg 7G#^@") Designation23526 / 95012Ah'h7A#RNLaunch date22 Mar 1995 at 04:05 UTjM#j:"N , Country of originCIS.7"S#v\"H̀(シ㼨ԟMissionMilitary: Navigation (Parus)_A#R<"Perigee/Apogee980/1010 kmV"A#R*Inclination82.9S*A#R$Period105 minlM#j>" &s,梉Launch vehicleCosmos CY*A#R0Launch sitePlesetsk&# 8M' "(OTechnical dataZ6$ lDownlink frequencies: 149.910 & 399.760 MHzPlane 2< M1  +Cosmos 2311H+5 :(qi" Cosmos 23111 \'  Generalg +G#^@") Designation23530 / 95014Ah'\7A#RN7Launch date22 Mar 1995 at 16:45 UTjM#j:"N , Country of originCISw07G#^`"H̀MissionMilitary: reconnaissance (Yantar')^vA#R:"Perigee/Apogee169/334 kmVA#R*Inclination67.1Uv!A#R(Period89.54 mincG#^8" &Launch vehicleSoyuz UY!A#R0Launch sitePlesetskA$ :Design lifetime: 2 months5S'  End of lifeVA#R*Decay31 May 1995$S" <  1S Qs Cosmos 2312HQ5 :(qi" Cosmos 23121 '  Generalg QG#^@") Designation23584 / 95026Ah'QA#RNLaunch date24 May 1995 at 20:10 UTjM#j:"N , Country of originCISr+Q-G#^V"H̀MissionMilitary: early warning (Oko)`A#R>"Perigee/Apogee614/40166 kmV-A#R*Inclination62.8S6A#R$Period709 mineG#^<" &Launch vehicleMolniya MY6A#R0Launch sitePlesetsk}Yq$ Other birds of this program are: 2063, 2097, 2176, 2217, 2222, 2232, 2241, 2261, 22868' "(OTechnical data8q' " Specificationsd#E A#RF&Prime contractorNPO LavotchkinN  A#RPlatform[E A#R4"Mass at launch2300 kgS A A#R$ Mass in orbitL A#RLengthK A A#RWidthL $ A#RHeightS w A#R$ StabilizationT$ A#R&DC power2800 W]w ( A#R8$Design lifetime5 years?K' s $ NEquipped with an infrared telescope< ( 1' P ACosmos 2313Hs 5 :(qi" Cosmos 23131 ( '  Generalg G#^@") Designation23596 / 95028Ag&( A#RLLaunch date8 Jun 1995 at 04:30 UTj `M#j:"N , Country of originCIS7 M#jn"H̀/{MissionMilitary: ocean reconnaissance (Eorsat)^`BA#R:"Perigee/Apogee403/415 kmTA#R&Inclination65TB @A#R&Period92.7 min @s eq@G#^<" &Launch vehicleCyclone 2Y @@A#R0Launch siteTyuratamDq@A* $4g,xReplaced Cosmos 2258< @JA1UK JAAFCosmos 2314HAA5 :(qi" Cosmos 23141 JAA'  Generalg A*BG#^@") Designation23601 / 95031Ah'ABA#RNLaunch date28 Jun 1995 at 18:30 UTj*BBM#j:"N , Country of originCISw0BsCG#^`"H̀MissionMilitary: reconnaissance (Yantar')^BCA#R:"Perigee/Apogee166/339 kmVsC'DA#R*Inclination67.1TC{DA#R&Period89.6 minc'DDG#^8" &Launch vehicleSoyuz UY{D7EA#R0Launch sitePlesetskDF% YBuilt by TsSKB (Central Specialized Design Bureau) of Samara, Russia and will obtain images for the Russian GRU intelligence agency. Has the ability to raise its orbit.57E=F'  End of lifeUFFA#R(Decay6 Sep 1995$=FF" < FF1P% F:GLCosmos 2315HF:G5 :(qi" Cosmos 23151 FkG'  Generalg :GGG#^@") Designation23603 / 95032Ag&kG9HA#RLLaunch date5 Jul 1995 at 03:10 UTjGHM#j:"N , Country of originCISv#9HIS#vF"H̀(シ 剂MissionNavigation (Kurs)_HxIA#R<"Perigee/Apogee988/1027 kmVIIA#R*Inclination82.9SxI!JA#R$Period105 minlIJM#j>" &s,梉Launch vehicleCosmos Ce$!JJA#RHLaunch sitePlesetsk LC132 pad 1nJK$ Part of a new series: the Kurs system enables maritime traffic control and messages to individual vessels.8JK' "(OTechnical dataS/KL$ ^Downlink frequencies: 150 & 400 MHzPlane 11< KKL1K KLLECosmos 2316HLL5 :(qi" Cosmos 2316[,KLL/ .XAlso called Glonass 74 or Glonass 7801 LM'  Generalg LMG#^@") Designation23620 / 95037Ah'MMA#RNLaunch date24 Jul 1995 at 15:52 UTjMXNM#j:"N , Country of originCISp#MNM#jF"H̀シMissionNavigation (Uragan)b!XN*OA#RB"Perigee/Apogee19101/19134 kmVNOA#R*Inclination64.8S*OOA#R$Period675 mino"ONM#jD"ONL &㉓gLaunch vehicleProton #234&Ot# 8N' "(Technical dataMt;B#T$Frequency (MHz)L1 = 1602 + 0.5625 * channelL2 = 1246 + 0.4375 * channelN A#RChannel4L ;ՁA#RPlane2L !A#RSlot15$ՁE" < !1%G ɂoCosmos 2317HEɂ5 :(qi" Cosmos 2317[,$/ .XAlso called Glonass 75 or Glonass 7811 ɂU'  Generalg $G#^@") Designation23621 / 95037Bh'U$A#RNLaunch date24 Jul 1995 at 15:52 UTjM#j:"N , Country of originCISp#$M#jF"H̀シMissionNavigation (Uragan)b!`A#RB"Perigee/Apogee19101/19134 kmVA#R*Inclination64.8S` A#R$Period675 mino"xM#jD" &㉓gLaunch vehicleProton #234& # 8xֆ' "(Technical dataMeB#T$Frequency (MHz)L1 = 1602 + 0.5625 * channelL2 = 1246 + 0.4375 * channelN ֆA#RChannel9L eA#RPlane2L KA#RSlot10$o" < K1 Cosmos 2318Ho5 :(qi" Cosmos 2318[,N/ .XAlso called Glonass 76 or Glonass 7851 '  Generalg NG#^@") Designation23622 / 95037Ch'NA#RNLaunch date24 Jul 1995 at 15:52 UTjM#j:"N , Country of originCISp#N(M#jF"H̀シMissionNavigation (Uragan)b!A#RB"Perigee/Apogee19101/19134 kmV(A#R*Inclination64.8S3A#R$Period675 mino"M#jD" &㉓gLaunch vehicleProton #234&3Ȍ# 8' "(Technical dataMȌB#T$Frequency (MHz)L1 = 1602 + 0.5625 * channelL2 = 1246 + 0.4375 * channelN ݍA#RChannel4L )A#RPlane2L ݍuA#RSlot11$)" < uՎ1G ՎCosmos 2319H5 :(qi" Cosmos 23191 ՎN'  Generalg G#^@") Designation23653 / 95045Ah'N)A#RNLaunch da)te30 Aug 1995 at 19:33 UTjM#j:"N , Country of originCIS6)S#vl"H̀(‰MissionMilitary: Telecommunications: GeizereG#^<"/ۀ0Geostationary orbit80Eo"M#jD" &㉓gLaunch vehicleProton #235&# 8N' "(Technical data<) "&$Specifications< N1qP NCosmos 2320H5 :(qi" Cosmos 23201 ?'  Generalg G#^@") Designation23674 / 95051Ah'?A#RNLaunch date29 Sep 1995 at 04:25 UTjxM#j:"N , Country of originCISIG#^"H̀MissionMilitary: reconnaissance (advanced Yantar'; 5th generation)^xfA#R:"Perigee/Apogee189/304 kmVA#R*Inclination64.9RfA#R"Period89 mincqG#^8" &Launch vehicleSoyuz U^A#R:Launch siteTyuratam LC31&q# 5*'  End of life_A#R<"Out of service28 Sep 1996T*A#R&CausedeorbitedK (A#RDecay&N# < (1D CCosmos 2321HN5 :(qi" Cosmos 23211 '  Generalg jG#^@") Designation23676 / 95052Ag&A#RLLaunch date6 Oct 1995 at 03:23 UTjj;M#j:"N , Country of originCIS.S#v\"H̀(シ㼨ԟMissionMilitary: Navigation (Parus)^;A#R:"Perigee/Apogee257/790 kmVpA#R*Inclination82.9TA#R&Period95.1 minlp0M#j>" &s,梉Launch vehicleCosmos C_A#R<Launch sitePlesetsk LC13204% The second stage of the launcher malfunctioned; thus the satellite couldn't reach the intended 960 km x 1010 km x 83 orbit.5i'  End of life^4A#R:"Out of service6 Oct 1995ViA#R*Decay21 Aug 1997&C# < 1|P\ Cosmos 2322HC5 :(qi" Cosmos 23221 '  Generalg _G#^@") Designation23704 / 95058Ah'A#RNLaunch date31 Oct 1995 at 20:19 UTj_=M#j:"N =C, Country of originCISy,M#jX"H̀_剂MissionMilitary: SIGINT (Tselina-2)^=A#R:"Perigee/Apogee849/852 kmThA#R&Inclination71UA#R(Period101.9 minih&M#j8" &'CMLaunch vehicleZenit% The booster is said to reduce air pollution to a minimum... The Zenit rocket produced by Ukraine is fuelled by a mixture of liquid oxygen and kerosene. Zenit was fired 14 times since 1987 with 3 failures.< &W1D  W. Cosmos 2323H5 :(qi" Cosmos 2323EW) "8Also called Glonass 7761 '  Generalg |G#^@") Designation23734 / 95068Ah'A#RNLaunch date14 Dec 1995 at 06:10 UTj|NM#j:"N , Country of originCISp#M#jF"H̀シMissionNavigation (Uragan)b!N A#RB"Perigee/Apogee19114/19141 kmVvA#R*Inclination64.8S A#R$Period675 mino"v8M#jD" &㉓gLaunch vehicleProton #238&^# 88' "(Technical dataM^%B#T$Frequency (MHz)L1 = 1602 + 0.5625 * channelL2 = 1246 + 0.4375 * channelN sA#RChannel6L %A#RPlane2K s A#RSlot9$. " < j 1\ j  BCosmos 2324H.  5 :(qi" Cosmos 2324Ej  ) "8Also called Glonass 7781 ( '  Generalg  G#^@") Designation23735 / 95068Bh'(  A#RNLaunch date14 Dec 1995 at 06:10 UTj a M#j:"N , Country of originCISp#  M#jF"H̀シMissionNavigation (Uragan)b!a 3 A#RB"Perigee/Apogee19117/19139 kmV  A#R*Inclination64.8S3  A#R$Period675 mino" K M#jD" &㉓gLaunch vehicleProton #238& q # 8K  ' "(Technical dataMq 8B#T$Frequency (MHz)L1 = 1602 + 0.5625 * channelL2 = 1246 + 0.4375 * channelO A#RChannel11L 8A#RPlane2K A#RSlot9$B" < ~1  ~bECosmos 2325HB5 :(qi" Cosmos 2325E~@) "8Also called Glo@Bnass 7821 H@'  Generalg @@G#^@") Designation23736 / 95068Ch'H@AA#RNLaunch date14 Dec 1995 at 06:10 UTj@AM#j:"N , Country of originCISp#AAM#jF"H̀シMissionNavigation (Uragan)b!ASBA#RB"Perigee/Apogee19109/19148 kmVABA#R*Inclination64.8SSBBA#R$Period675 mino"BkCM#jD" &㉓gLaunch vehicleProton #238&BC# 8kCC' "(Technical dataMCXDB#T$Frequency (MHz)L1 = 1602 + 0.5625 * channelL2 = 1246 + 0.4375 * channelN CDA#RChannel6L XDDA#RPlane2L D>EA#RSlot13$DbE" < >EE1|' EE1JCosmos 2326HbEE5 :(qi" Cosmos 23261 EF'  Generalg E~FG#^@") Designation23748 / 95071Ah'FFA#RNLaunch date20 Dec 1995 at 00:52 UTj~FPGM#j:"N , Country of originCIS7FGM#jn"H̀/{MissionMilitary: ocean reconnaissance (Eorsat)TPG(HA#R&"Perigee/ApogeeQGyHA#R InclinationL (HHA#RPeriodeyH*IG#^<" &Launch vehicleCyclone 2^HIA#R:Launch siteTyuratam LC90*I1J%  It also carries 'Konus-A', a secondary science payload made in the A.F.Ioffe Physics and Technology Institute in St.Petersburg.< ImJ1X mJJ Cosmos 2327H1JJ5 :(qi" Cosmos 23271 mJJ'  Generalg JMKG#^@") Designation23773 / 96004Ah'JKA#RNLaunch date16 Jan 1996 at 15:34 UTjMKLM#j:"N , Country of originCIS.KLS#v\"H̀(シ㼨ԟMissionMilitary: Navigation (Parus)_LLA#R<"Perigee/Apogee974/1033 kmTLSMA#R&Inclination83SLMA#R$Period105 minlSMNM#j>" &s,梉Launch vehicleCosmos C_MqNA#R<Launch sitePlesetsk LC132&NN# 5qNN'  End of lifeXN$OA#R."Out of serviceyes?&NJO# 8$OO' "(OTechnical dataZ6JO $ lDownlink frequencies: 149.970 & 399.920 MHzPlane 1O 1J< OH1', H+Cosmos 2328H 5 :(qi" Cosmos 23281 H'  Generalg (G#^@") Designation23790 / 96009D\A#R6Launch date19 Feb 1996j(M#j:"N , Country of originCIS/pS#v^"H̀(㓉<MissionTelecommunications (Strela-3)\̂A#R6"Perigee/Apogee~1400 kmUp!A#R(Inclination~82L ̂mA#RPeriodr%!߃M#jJ" &ቂLaunch vehicleCyclone 3 #115L(m+$ PThis is the 3000th Russian satellite< ߃g12 g"Cosmos 2329H+5 :(qi" Cosmos 23291 g'  Generalg GG#^@") Designation23791 / 96009E\A#R6Launch date19 Feb 1996jG M#j:"N , Country of originCIS/S#v^"H̀(㓉<MissionTelecommunications (Strela-3)\ A#R6"Perigee/Apogee~1400 kmU@A#R(Inclination~82L A#RPeriodr%@M#jJ" &ቂLaunch vehicleCyclone 3 #115$"" < ^1,9 ^Cosmos 2330H"5 :(qi" Cosmos 23301 ^׈'  Generalg >G#^@") Designation23792 / 96009F\׈A#R6Launch date19 Feb 1996j>M#j:"N , Country of originCIS/S#v^"H̀(㓉<MissionTelecommunications (Strela-3)\A#R6"Perigee/Apogee~1400 kmU7A#R(Inclination~82L A#RPeriodr%7M#jJ" &ቂLaunch vehicleCyclone 3 #115&# < W112O WCosmos 2331H5 :(qi" Cosmos 23311 WЌ'  Generalg 7G#^@") Designation23818 / 96016Ah'ЌA#RNLaunch date14 Mar 1996 at 17:45 UTj7 M#j:"N , Country of originCISw0G#^`"H̀MissionMilitary: reconnaissance (Yantar')^ ގA#R:"Perigee/Apogee164/355 kmV4A#R*Inclination67.1L ގA#RPeriodc4 G#^8" &Launch vehicleSoyuz U YeA#R0Launch sitePlesetskb7 + $oY뉂This Russian Defense Ministry payload carries a US DoD secondary experiment launched as part of the Space Test Program (STP), the BINRAD package which will attempt to detect the presence of beryllium at orbital altitudes. BINRAD was flown twice before on Russian civilian Resurs F remote sensing missions.< e19] K Cosmos 2332HK5 :(qi" Cosmos 23321 |'  Generalg KG#^@") Designation23853 / 96025Ah'|KA#RNLaunch date24 Apr 1996 at 13:03 UTjM#j:"N , Country of originCISj#KG#^F"H̀MissionMilitary: calibration_~A#R<"Perigee/Apogee303/1575 kmTA#R&Inclination83L ~A#RPeriodlM#j>" &s,梉Launch vehicleCosmos CYA#R0Launch sitePlesetsk& # DM1m]3 MCosmos 2333 failureP 5 :8qi" Cosmos 2333 failure1 M'  General\*G#^*") Designationn/a\A#R6Launch date14 May 1996j*M#j:"N , Country of originCIS?vG#^~"H̀MissionMilitary: reconnaissance (Kometa; 4th generation)cG#^8" &Launch vehicleSoyuz UYv2A#R0Launch siteTyuratam@' The rocket was lost 2 minutes after launch during the burn of the first stage. The SPIN-2 payload was onboard (US mapping project) During 45 days in low orbit this satelite would have taken photos of 1.2 million square miles of the Earth's surface for American companies. In particular, the satellite was to have taken high-resolution photographs (2 m) of the United States to fulfill a contract signed last summer by Russia's Sovinformsputnik and the U.S. Aerial Images company.2\% The insurer for the satellite payed $2.7 million The experts revealed that the boosters had production errors (on the nose cones and with low quality of the latches). The report said the nose cones split apart and disintegrated during launch.<@' *O External resourcesA\' 4http://www.spin-2.com/< 1Oj ]Cosmos 2333H]5 :(qi" Cosmos 23331 '  Generalg ]G#^@") Designation24297 / 96051Ag&\A#RLLaunch date4 Sep 1996 at 09:01 UTjM#j:"N , Country of originCISy,\?M#jX"H̀_剂MissionMilitary: SIGINT (Tselina-2)^A#R:"Perigee/Apogee848/852 kmT? A#R&Inclination71 UaA#R(Period101.9 mini M#j8" &'CMLaunch vehicleZenit&a# < ,1!js ,tdCosmos 2334Ht5 :(qi" Cosmos 23341 ,'  Generalg t G#^@") Designation24304 / 96052Ag&sA#RLLaunch date5 Sep 1996 at 12:47 UTj M#j:"N , Country of originCIS.s^S#v\"H̀(シ㼨ԟMissionMilitary: Navigation (Parus)_A#R<"Perigee/Apogee968/1009 kmV^A#R*Inclination82.9UhA#R(Period104.8 minlM#j>" &s,梉Launch vehicleCosmos Ca h5A#R@Launch sitePlesetsk LC132/1/ d$ Plane 5< 513  Cosmos 2335Hd5 :(qi" Cosmos 23351 '  Generalg G#^@") Designation24670 / 96069Ah'A#RNLaunch date11 Dec 1996 at 12:00 UTjRM#j:"N , Country of originCIS7M#jn"H̀/{MissionMilitary: ocean reconnaissance (Eorsat)^R4A#R:"Perigee/Apogee403/417 kmVA#R*Inclination65.4T4A#R&Period92.7 mineC G#^<" &Launch vehicleCyclone 2^ A#R:Launch siteTyuratam LC90&C  # <  1s  K 2Cosmos 2336H K 5 :(qi" Cosmos 23361  | '  Generalg K  G#^@") Designation24677 / 96071Ah'| K A#RNLaunch date20 Dec 1996 at 06:44 UTj  M#j:"N , Country of originCIS.K 6 S#v\"H̀(シ㼨ԟMissionMilitary: Navigation (Parus)_  A#R<"Perigee/Apogee979/1012 kmV6  A#R*Inclination82.9S > A#R$Period105 minl  M#j>" &s,梉Launch vehicleCosmos CY> A#R0Launch sitePlesetsk/ 2$ Plane 4< n1 n7BCosmos 2337H25 :(qi" Cosmos 23371 n'  Generalg NG#^@") Designation24725 / 97006A\A#R6Launch date14 Feb 1997jN @M#j:"N , Country @2 of originCIS/@S#v^"H̀(㓉<MissionTelecommunications (Strela-3)\ @@A#R6"Perigee/Apogee~1400 kmU@SAA#R(Inclination~82L @AA#RPeriodr%SABM#jJ" &ቂLaunch vehicleCyclone 3 #116&A7B# < BsB1 sBB0FCosmos 2338H7BB5 :(qi" Cosmos 23381 sBB'  Generalg BSCG#^@") Designation24726 / 97006B\BCA#R6Launch date14 Feb 1997jSCDM#j:"N , Country of originCIS/CDS#v^"H̀(㓉<MissionTelecommunications (Strela-3)\DDA#R6"Perigee/Apogee~1400 kmUDLEA#R(Inclination~82L DEA#RPeriodr%LE FM#jJ" &ቂLaunch vehicleCyclone 3 #116&E0F# < FlF1 lFF)JCosmos 2339H0FF5 :(qi" Cosmos 23391 lFF'  Generalg FLGG#^@") Designation24727 / 97006C\FGA#R6Launch date14 Feb 1997jLGHM#j:"N , Country of originCIS/GHS#v^"H̀(㓉<MissionTelecommunications (Strela-3)\HHA#R6"Perigee/Apogee~1400 kmUHEIA#R(Inclination~82L HIA#RPeriodr%EIJM#jJ" &ቂLaunch vehicleCyclone 3 #116&I)J# < JeJ1 eJJNCosmos 2340H)JJ5 :(qi" Cosmos 23401 eJJ'  Generalg JEKG#^@") Designation24761 / 97015A[JKA#R4Launch date9 Apr 1997jEK LM#j:"N , Country of originCISr+K|LG#^V"H̀MissionMilitary: early warning (Oko)` LLA#R>"Perigee/Apogee527/39367 kmV|L2MA#R*Inclination62.9SLMA#R$Period708 mine2MMG#^<" &Launch vehicleMolniya MYMCNA#R0Launch sitePlesetskS)MN* $R2xPrevious bird of this program: 2312< CNN1 NOCosmos 2341HNO5 :(qi" Cosmos 23411 NKO'  Generalg OOG#^@") Designation24772 / 97017A\KOA#R6Launch dateON17 Apr 1997jOM#j:"N , Country of originCIS.S#v\"H̀(シ㼨ԟMissionMilitary: Navigation (Parus)_dA#R<"Perigee/Apogee977/1014 kmVA#R*Inclination82.9Sd A#R$Period105 minlyM#j>" &s,梉Launch vehicleCosmos CY ҂A#R0Launch sitePlesetsk&y# < ҂41 4|fCosmos 2342H|5 :(qi" Cosmos 23421 4'  Generalg |G#^@") Designation24800 / 97022A\pA#R6Launch date14 May 1997jڄM#j:"N , Country of originCISr+pLG#^V"H̀MissionMilitary: early warning (Oko)`ڄA#R>"Perigee/Apogee514/39377 kmVLA#R*Inclination62.8SUA#R$Period708 mineG#^<" &Launch vehicleMolniya MYUA#R0Launch sitePlesetskS)f* $Rw3xPrevious bird of this program: 2340< 1' mCosmos 2343Hf5 :(qi" Cosmos 23431 '  Generalg G#^@") Designation24805 / 97024A\ވA#R6Launch date15 May 1997jHM#j:"N , Country of originCIS?ވΉG#^~"H̀MissionMilitary: reconnaissance (Kuban?; 7th generation)^H,A#R:"Perigee/Apogee216/338 kmVΉA#R*Inclination64.9R,ԊA#R"Period90 minc7G#^8" &Launch vehicleSoyuz UԊ' !It was 1495th success space launch of a launcher based on the R-7 ICBM, 666th launch of Soyuz-U in total score, 250th launch of Soyuz-U from Baykonur and 350th launch in total score (including space launchers and ICBMs) from LC31 of Baykonur.The satellite caused a great deal of controversy when in burned into the atmosphere on 23 Sep 1997 from the Western Isles to the north of England (UK). 57#'  End of life_A#R<"Out of service18 Sep 1997q0#A#R`Causedeorbited and destroyed intentionally VIA#R*Decay23 Sep 1997$m" < I1π Cosmos 2344Hm5 :(qi" Cosmos 23441 "'  Generalg G#^@") Designation24827 / 97028A[" A#R4Launch date6 Jun 1997 mjvM#j:"N , Country of originCISE G#^"H̀MissionMilitary: reconnaissance (8th generation, called Arkon)`vbA#R>"Perigee/Apogee1509/2747 kmVA#R*Inclination63.4Ub A#R(Period130.1 mino"|M#jD" &㉓gLaunch vehicleProton #248& # < |1' &wCosmos 2345H&5 :(qi" Cosmos 23451 W'  Generalg &G#^@") Designation24894 / 97041A\WA#R6Launch date14 Aug 1997jM#j:"N , Country of originCIS> G#^|"H̀MissionMilitary: early warning (Prognoz 2nd generation)enG#^<"/ۀ0Geostationary orbit24Wo" M#jD" &㉓gLaunch vehicleProton #250&n# 8;' "(OTechnical data<w# 2Built by NPO Lavochkin< ;15πB Cosmos 2346Hw5 :(qi" Cosmos 23461 ,'  Generalg G#^@") Designation24953 / 97052Ah',A#RNLaunch date23 Sep 1997 at 16:44 UTjeM#j:"N , Country of originCIS.S#v\"H̀(シ㼨ԟMissionMilitary: Navigation (Parus)_eEA#R<"Perigee/Apogee968/1009 kmVA#R*Inclination82.9UEA#R(Period104.8 minl\M#j>" &s,梉Launch vehicleCosmos CYA#R0Launch sitePlesetskJ$\& H810 kg, built by NPO PMPlane 1< ;1 ;iCosmos 2347H5 :(qi" Cosmos 23471 ;'  Generalg G#^@") Designation25088 / 97079Af%A#RJLaunch date9 Dec 1997 at 7:17 UTjM#j:"N , Country of originCIS7oM#jn"H̀/{MissionMilitary: ocean reconnaissance (Eorsat)ZA#R2"Perigee/Apogee410 kmToA#R&Inclination65L iA#RPeriodeG#^<" &Launch vehicleCyclone 2^i,A#R:Launch siteTyuratam LC90=i$ 2Said to weigh 3150 kg< ,1BP  Cosmos 2348Hi 5 :(qi" Cosmos 2348 i1 ='  Generalg G#^@") Designation25095 / 97080Ah'= A#RNLaunch date15 Dec 1997 at 15:40 UTjvM#j:"N , Country of originCISH G#^"H̀MissionMilitary: reconnaissance (Yantar' 3/4, also called Kobalt)^vcA#R:"Perigee/Apogee176/370 kmVA#R*Inclination67.1L cA#RPeriodchG#^8" &Launch vehicleSoyuz UYA#R0Launch sitePlesetsk&h# 5'  End of lifeVrA#R*Decay14 Apr 1998&# < r1  Cosmos 2349H5 :(qi" Cosmos 23491 M'  Generalg G#^@") Designation25167 / 98009A\MA#R6Launch date17 Feb 1998jzM#j:"N , Country of originCIS?G#^~"H̀MissionMilitary: reconnaissance (Kometa; 4th generation)^z^A#R:"Perigee/Apogee228/286 kmVA#R*Inclination70.4R^A#R"Period90 minciG#^8" &Launch vehicleSoyuz UYA#R0Launch siteTyuratami ' The SPIN-2 payload was onboard (US mapping project) During 45 days in low orbit this satelite has taken photos of 1.2 million square miles of the Earth's surface for American companies. In particular, the satellite has taken high-resolution photographs (2 m) of the United States to fulfill a contract signed last summer by Russia's Sovinformsputnik and the U.S. Aerial Images company.The photos were properly recovered after decay. They will be on sale on the TerraServer.< ' *O External resourcesf8 l . ,phttp://www.spin-2.com/http://www.terraserver.com/5  '  End of lifee$l  A#RH"Out of servicebefore 2 Apr 1998P V A#RCausedecayU  A#R(Decay2 Apr 1998&V  # <  1P' U @Cosmos 2350H U 5 :(qi" Cosmos 23501  '  Generalg U  G#^@") Designation25315 / 98025A\ IA#R6Launch date29 Apr 1998j M#j:"N , Country of originCIS>I8G#^|"H̀MissionMilitary: early warning (Prognoz 2nd generation)aG#^4"/ۀ0Geostationary orbito"8@M#jD" &㉓gLaunch vehicleProton@  #235&:@# 8@r@' "(Technical data<:@@) "&$Specifications< r@@1 @2AECosmos 2351H@2A5 :(qi" Cosmos 23511 @cA'  Generalg 2AAG#^@") Designation25327 / 98027A[cA%BA#R4Launch date7 May 1998jABM#j:"N , Country of originCISr+%BCG#^V"H̀MissionMilitary: early warning (Oko)`BaCA#R>"Perigee/Apogee514/39377 kmVCCA#R*Inclination62.8SaC DA#R$Period708 mineCoDG#^<" &Launch vehicleMolniya MY DDA#R0Launch sitePlesetskS)oDE* $Ro3xPrevious bird of this program: 23427DRE1QR REEJAstron7 EE, (" Astron1 REE'  Generalg E!FG#^@") Designation13901 / 83020A\E}FA#R6Launch date23 Mar 1983j!FFM#j:"N , Country of originCISr%}FYGM#jJ"H̀_BMissionScientific: astronomyc"FGA#RD"Perigee/Apogee25731/178615 kmVYGHA#R*Inclination34.1VGhHA#R*Period5932.2 mino"HHM#jD" &㉓gLaunch vehicleProton #106s2hHJIA#Rd"Mass at launch3500 kg (450 kg of instruments)HJ% /Carries the French and Russian experiment UFT for UV astronomy. Payload: 1 telescope (80 cm diameter and 5 m long) and a spectrometer (1.15-3.5 m)> JIDJ1%VV DJJKProgram: BionJJJ5 :,ؽG" Program: BionDJgK& gRussian recoverable scientific satellites programThe recoverable Bion spacecraft, built by TsSKB-Progress of Samara, is based on the Zenit/Vostok spaceship in use since 1960.<JK' *O External resourcesS,gKK' Xhttp://baby.indstate.edu/asgsb/bion.html1K'L1J 'L@MK@M\ {6!wfx0pProgram: BionBion 01Bion 02 (Cosmos 0690)Bion 03Bion 04Bion 05 (Cosmos 1129)Bion 06 (Cosmos 1514)Bion 07 (Cosmos 1667)Bion 08Bion 09Bion 10 (Cosmos 2229)Bion 118'LxM1 xMMBion 11D@MM5 : ؽG" Bion 111 xMM'  Generalg MTNG#^@") Designation24702 / 96073A\MNA#R6Launch date24 Dec 1996jTNOM#j:"N , Country of originCISeNOG#^<"H̀MissionScientific: life^OOA#R:"Perigee/Apogee217/378 kmVO?A#R*O?@MInclination62.8TOA#R&Period90.4 minc?G#^8" &Launch vehicleSoyuz UYOA#R0Launch sitePlesetskC' 9It carries newts, snails, Drosophila flies and other insects, bacteria, and two macaque monkeys, Lapik and Multik. Both monkeys were safe at landing but Multik died of an heart attack during medical tests under general anaesthetic on January 8.Could downlink in the 136 MHz area5Oǂ'  End of life^%A#R:"Out of service7 Jan 1997UǂzA#R(Decay7 Jan 1997&%# 8z؃1 ؃Bion 12D5 : ؽG" Bion 121 ؃M'  GeneralYG#^$") DesignationQMA#R Launch datejaM#j:"N , Country of originCISeƅG#^<"H̀MissionScientific: life^a$A#R:"Perigee/Apogee217/378 kmVƅzA#R*Inclination62.8T$ΆA#R&Period90.4 mincz1G#^8" &Launch vehicleSoyuz UYΆA#R0Launch sitePlesetsk21- ( 0pNASA should not participate to this mission, probably because of public pressure after the monkey experimentation that went on on Bion 11. This could lead to monkey being replaced by rats for the future life experimentsCould downlink in the 136 MHz area?1oyU FProgram: EkranKF5 :._ " Program: Ekran># 6Soviet direct TV program1F1U ō<) "&~񢝀Program: Ekran1{#ƀb"eɀeɉ2eɉJeɉEkran 01Ekran 02Ekran 03Ekran 041I{#ƀb"eɀeɉ2eɉJeɉEkran 05Ekran 06Ekran 07Ekran 088#p(eɀ(xdɀ(8odɀ(TpdɀEkran 09Ekran 10Ekran 11Ekran 128Iٌ#p(qdɀ(rdɀ(8sdɀ(TtdɀEkran 13Ekran 14Ekran 15Ekran 168#p(udɀ(vdɀ(8wdɀ(TdɀEkran 17Ekran 18Ekran 19Ekran 20$ٌō" 11U x<ō2# 2Ekran's specificationsq0A#R`0&Prime contractorNPO Prikadnoy Mekaniki (PM)S2A#R$0PlatformEkran[QA#R40"Mass at launch1970 kgQA#R 0Diameter2 mOQ A#R0Height5 m ōYeA#R00 Stabilization3 axis\ A#R60$Design lifetime3 years2 e'  UHF-bandXKA#R.0(Main transponders1ZA#R20,Backup transponders1PKA#R0Power200 WUJA#R(0Bandwidth24 MHzb!A#RB0CoverageCIS and part of AsiaRJA#R"0EIRP55.5 dBWz8xB#Tp0FrequenciesUplink: C-band (6 GHz)Downlink: 714 MHz$" 9x1 Ekran 01E5 :"_ " Ekran 011 K'  Generalg G#^@") Designation09503 / 76107A\KA#R6Launch date26 Oct 1976jxM#j:"N , Country of originCISo"M#jD"H̀‰MissionTelecommunications]xDA#R8,Geostationary orbit99En!M#jB" &㉓gLaunch vehicleProton #60&D# 5 '  End of lifeWdA#R,"Out of serviceyes& # 8d' "(Technical data<) "&ƀSpecifications971x 7|Ekran 02E|5 :"_ " Ekran 021 7'  Generalg |G#^@") Designation10365 / 77092A\pA#R6Launch date20 Sep 1977jM#j:"N , Country of originCISo"pIM#jD"H̀‰MissionTelecommunicationsYA#R0,Geostationary orbitn!IM#jB" &㉓gLaunch vehicleProton #65&6# 5k'  End of lifeW6A#R,"Out of serviceyes?kDC#TCauseThe satellite broke up in GEO because of a nickel-hydrogen battery explosion on 23 Jun 1978.[The Soviets photographed the explosion accidentally. No other space power noted the explosion - the Russians revealed that the satellite had exploded at a conference in Moscow in February 1992.] &j# 8D' "(Technical data<j) "&ƀSpecifications91 \HEkran 03E\5 :"_ " Ekran 031 '  Generalg \G#^@") Designation11273 / 79015A\PA#R6Launch date21 Feb 1979jM#j:"N , Country of originCISo"P5M#jD"H̀5‰MissionTelecommunicationsYA#R0,Geostationary orbitn!5M#jB" &㉓gLaunch vehicleProton #76&"# 5W'  End of lifeW"A#R,"Out of serviceyes&W# 8 ' "(Technical data<H) "&ƀSpecifications9 1x Ekran 04IH8 @$_ " Ekran 041 '  Generalg bG#^@") Designation11561 / 79087A[A#R4Launch date3 Oct 1979jb'M#j:"N , Country of originCISo"M#jD"H̀‰MissionTelecommunicationsY'A#R0,Geostationary orbitn!]M#jB" &㉓gLaunch vehicleProton #80&# 5]'  End of lifeWA#R,"Out of serviceyes&5# 8m' "(Technical data<5) "&ƀSpecifications9m1 + Ekran 05I+8 @$_ " Ekran 051 \'  Generalg +G#^@") Designation11890 / 80060A\\A#R6Launch date14 Jul 1980jM#j:"N , Country of originCISo"M#jD"H̀‰MissionTelecommunicationsYQ A#R0,Geostationary orbitn! M#jB" &㉓gLaunch vehicleProton #84&Q  # 5  '  End of lifeW q A#R,"Out of serviceyes&  # 8q  ' "(Technical data<  ) "&ƀSpecifications9 D 1 D  mEkran 06I  8 @$_ " Ekran 061 D  '  Generalg % G#^@") Designation12120 / 80104A\  A#R6Launch date26 Dec 1980j%  M#j:"N , Country of originCISo" Z M#jD"H̀‰MissionTelecommunicationsY  A#R0,Geostationary orbitn!Z !M#jB" &㉓gLaunch vehicleProton #86& G# 5!|'  End of lifeWGA#R,"Out of serviceyes&|# 81' "(Technical data<m) "&ƀSpecifications911   @CEkran 07Im @8 @$_ " Ekran 07 @m1 =@'  Generalg @@G#^@") Designation12564 / 81061A\=@AA#R6Launch date25 Jun 1981j@jAM#j:"N , Country of originCISo"AAM#jD"H̀‰MissionTelecommunicationsYjA2BA#R0,Geostationary orbitn!ABM#jB" &㉓gLaunch vehicleProton #89&2BB# 5BB'  End of lifeWBRCA#R,"Out of serviceyes&BxC# 8RCC' "(Technical data<xCC) "&ƀSpecifications9C%D1* %DjDMHEkran 08ECjD5 :"_ " Ekran 081 %DD'  Generalg jDEG#^@") Designation13056 / 82009A[D]EA#R4Launch date5 Feb 1982jEEM#j:"N , Country of originCISo"]E6FM#jD"H̀‰MissionTelecommunications]EFA#R8,Geostationary orbit99En!6FGM#jB" &㉓gLaunch vehicleProton #94&F'G# 5G\G'  End of lifeW'GGA#R,"Out of serviceyes&\GG# 8GH' "(Technical data<GMH) "&ƀSpecifications9HH1 J HHLEkran 09EMHH5 :"_ " Ekran 091 HH'  Generalg HcIG#^@") Designation13554 / 82093A\HIA#R6Launch date16 Sep 1982jcI)JM#j:"N , Country of originCISo"IJM#jD"H̀‰MissionTelecommunications])JJA#R8,Geostationary orbit99En!JcKM#jB" &㉓gLaunch vehicleProton #99&JK# 5cKK'  End of lifeWKLA#R,"Out of serviceyes&K;L# 8LsL' "(Technical data<;LL) "&ƀSpecifications9sLL1$*K L1M2Ekran 10IL1M8 @$_ " Ekran 101 LbM'  Generalg 1MMG#^@") Designation13878 / 83016A\bM%NA#R6Launch date12 Mar 1983jMNM#j:"N , Country of originCISo"%NNM#jD"H̀‰MissionTelecommunicationsYNWOA#R0,Geostationary orbito"NOM#jD" &㉓gLaunch vehicleProton #105&WO # O L5OA'  End of lifeW A#R,"Out of serviceyes&A# 8' "(Technical data<2) "&ƀSpecifications9k1Jl kEkran 11E25 :"_ " Ekran 111 k'  Generalg HG#^@") Designation14377 / 83100A\A#R6Launch date30 Sep 1983jHM#j:"N , Country of originCISo"}M#jD"H̀‰MissionTelecommunications]ڃA#R8,Geostationary orbit99Eo"}IM#jD" &㉓gLaunch vehicleProton #113&ڃo# 5I'  End of lifeWoA#R,"Out of serviceyes&!# 8Y' "(Technical data<!) "&ƀSpecifications9Y΅1K ΅Ekran 12E5 :"_ " Ekran 121 ΅D'  Generalg G#^@") Designation14821 / 84028A\DA#R6Launch date16 Mar 1984jqM#j:"N , Country of originCISo"M#jD"H̀‰MissionTelecommunications]q=A#R8,Geostationary orbit99Eo"M#jD" &㉓gLaunch vehicleProton #118&=҈# 5'  End of lifeW҈^A#R,"Out of serviceyes&# 8^' "(Technical data<) "&ƀSpecifications911l 1v[Ekran 13Ev5 :"_ " Ekran 131 1'  Generalg vG#^@") Designation15219 / 84090A\jA#R6Launch date24 Aug 1984jԋM#j:"N , Country of originCISo"jCM#jD"H̀‰MissionTelecommunications]ԋA#R8,Geostationary orbit99Eo"CM#jD" &㉓gLaunch vehicleProton #124&5# 5j'  End of lifeW5A#R,"Out of serviceyes&j# 8' "(Technical data<[) "&ƀSpecifications91 َEkran 14E[َ5 :"_ " Ekran 141  '  Generalg َqG#^@") Designation15626 / 85024A\ ͏A#R6Launch date22 Mar 1985jqCM#j:"N ͏C[, Country of originCISo"͏M#jD"H̀‰MissionTelecommunications]CA#R8,Geostationary orbit99Eo"~M#jD" &㉓gLaunch vehicleProton #131&# 5~'  End of lifeW0A#R,"Out of serviceyes&V# 80' "(Technical data<V) "&ƀSpecifications91ρ H-Ekran 15EH5 :"_ " Ekran 151 y'  Generalg HG#^@") Designation16729 / 86038A\y<A#R6Launch date24 May 1986jM#j:"N , Country of originCISo"<M#jD"H̀‰MissionTelecommunications]rA#R8,Geostationary orbit99Eo"M#jD" &㉓gLaunch vehicleProton #142&r# 5<'  End of lifeWA#R,"Out of serviceyes&<# 8' "(Technical data<-) "&ƀSpecifications9f1 fEkran 16E-5 :"_ " Ekran 161 f'  Generalg CG#^@") Designation18328 / 87073A[A#R4Launch date4 Sep 1987jCM#j:"N , Country of originCISo"wM#jD"H̀‰MissionTelecommunications]A#R8,Geostationary orbit99Eo"wCM#jD" &㉓gLaunch vehicleProton #154&i# 5C'  End of lifeWiA#R,"Out of serviceyes&# 8S' "(Technical data<) "&ƀSpecifications9S1ρ   Ekran 17E 5 :"_ " Ekran 171 >'  Generalg G#^@") Designation18715 / 87109A\>A#R6Launch date27 Dec 1987jkM#j:"N , Country of originCISo"M#jD"H̀‰MissionTelecommunications]k7A#R8,Geostationary orbit99Eo"M#jD" &㉓gLaunch vehicleProton #160&7# 5'  End of lifeWXA#R,"Out of serviceyes&~# 8X' "(Technical data<~ ) "&ƀSpecifications 9E1  EnEkran 18E 5 :"_ " Ekran 181 E'  Generalg "G#^@") Designation19090 / 88036A[}A#R4Launch date6 May 1988j"M#j:"N , Country of originCISo"}VM#jD"H̀‰MissionTelecommunications]A#R8,Geostationary orbit99Eo"V"M#jD" &㉓gLaunch vehicleProton #165&H# 5"}'  End of lifeWHA#R,"Out of serviceyes&}# 82' "(Technical data<n) "&ƀSpecifications921$O Ekran 19En5 :"_ " Ekran 191 '  Generalg G#^@") Designation19683 / 88108A[A#R4Launch date8 Dec 1988jIM#j:"N , Country of originCISo"M#jD"H̀‰MissionTelecommunicationsg&IA#RL,Geostationary orbit99E, inclinedo"M#jD" &㉓gLaunch vehicleProton #173&# 5'  End of life\EA#R6"Out of serviceOct 1996&k# 8E' "(Technical data<k) "&ƀSpecifications9 1v   ]  Ekran 20E] 5 :"_ " Ekran 201   '  Generalg ]  G#^@") Designation22210 / 92074A\ Q A#R6Launch date30 Oct 1992j  M#j:"N , Country of originCISo"Q * M#jD"H̀‰MissionTelecommunicationso(  G#^P"/ۀ0Geostationary orbit99E, inclinedo"*  M#jD" &㉓gLaunch vehicleProton #210& . # 8 f ' "(Technical data<.  ) "&ƀSpecifications: f  1   GElectro 1:  , (" Electro 19 O # ,Also called GOMS N11   '  Generalg O  G#^@") Designation23327 / 94069A\ CA#R6Launch date31 Oct 1994j M#j:"N , Country of originCIShCM#j6"H̀DVMissionMeteorologyg |G#^@"/ۀ0Geostationary orbit76.5Eo" @M#jD" &㉓gLaunch vehicleProton #228| @ ;|GA' )It will provide cloud cover and sea temperature maps, along with the data on the upper boundaries of clouds and wind speeds, to enable hurricane, floods, and typhoon warnings.Operational since 1 Jun 1996. It broadcasts on 1691 MHz (WEFAX with a minimum filter of 50 KHz)< @A' *O External resourcesR+GAA' Vhttp://smis.iki.rssi.ru/goms/goms_1.htm8A B' "(OTechnical data8AEB' " Specifications] BBA#R8&Prime contractorVNII-EMUEBBA#R(PlatformElectro[BRCA#R4"Mass at launch2400 kgSBCA#R$ Mass in orbitL RCCA#RLengthK C"Perigee/Apogee447/66269 kmVKA#R*Inclination60.8VA#R*Period1313.8 min\KG#^*" &Launch vehicleYVA#R0Launch siteTyuratam&|# 5V'  End of lifeV|A#R*Decay10 Jul 1964$+" ?j1|W jProgram: FotonO+8 @0Iu " Program: FotonV1j% bAlso called PhotonScientific Russian program1@1 @F Z3GܝeN L L Program: FotonFoton 01 was Cosmos 1645Foton 02 was Cosmos 1744Foton 03 was Cosmos 1841Foton 08 was in Oct 1992Foton 09Foton 10Foton 119@X1  XFoton 09I8 @$Iu " Foton 091 Xҏ'  Generalg EG#^@"ҏE) Designation23122 / 94033Ah'ҏA#RNLaunch date14 Jun 1994 at 16:00 UTjEM#j:"N , Country of originCIS_vG#^0"H̀MissionScientific^A#R:"Perigee/Apogee229/385 kmVv*A#R*Inclination62.8T~A#R&Period90.4 mina*G#^4" &Launch vehicleSoyuzY~8A#R0Launch sitePlesetsk[A#R4"Mass at launch8200 kg8`% QThe spacecraft, with a research payload of 700 kg, is expected to orbit for 18 days, conducting microgravity experiments in solid state and biological disciplines. 5'  End of lifeW`A#R,Landing2 Jul 1994$" 9I1N t  IFoton 10I8 @$Iu " Foton 101 I'  Generalg *G#^@") Designation23497 / 95006Ah'A#RNLaunch date16 Feb 1995 at 17:40 UTj*M#j:"N , Country of originCISu.qG#^\"H̀MissionScientific: microgravity studies^A#R:"Perigee/Apogee228/391 kmVq%A#R*Inclination62.8RwA#R"Period94 minc%G#^8" &Launch vehicleSoyuz U^w8A#R:Launch sitePlesetsk LC43}<A#Rx"Mass at launch6300 kg (retrievable experiment: 2250 kg) 8' 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.5'  End of lifeWKA#R,Landing3 Mar 1995 % 3The descent cabin was severly damaged when it was dropped by the helicopter carrying it back for deintegration. Thus many experiments were destroyed.8KA' "(OTechnical data $ EThe Foton recoverable materials processing satellite, built by the Central Specialized Design Bureau in Samara, is based on the Vostok/Zenit spy satellite bus.9A@1  @Foton 11I8 @$Iu " Foton 111 @'  Generalg !G#^@") Designation25006 / 97060Ag&A#RLLaunch date9 Oct 1997 at 18:00 UTj! M#j:"N , Country of originCIS u.G#^\"H̀MissionScientific: microgravity studies` A#R>"Perigee/Apogee218 / 371 kmV7A#R*Inclination62.8L A#RPerioda7G#^4" &Launch vehicleSoyuzY=A#R0Launch sitePlesetsk[A#R4"Mass at launch7000 kgc>=% |Has 3 packages on board: for ESA (biobox), CNES and DARA.50'  End of life[A#RLanding23 Oct 1997 (Foton and Mirka were separated before reentry, both landed safely)&0# 8*' "(OTechnical data{0 .L The Mirka capsule built by Kayser-Threde and Jena-Optronik GmbH is a 154 kg 1m diameter sphere which contains a 40 kg payload. Onboard will be the following experiments:Heatin (Heatshield Instrumentation)Raflex (Rarefied Flow Experiment)Pyrex (Pyrometer Experiment)Mirka's re-entry capabilities were tested.IBIS 2, 75 kg (replacement for the IBIS payload on Foton 10)6* 1. I Gamma> I2 4"  Gamma1 z'  Generalg IG#^@") Designation20683 / 90058A\z=A#R6Launch date11 Jul 1990jM#j:"N , Country of originCIS|/=#M#j^"H̀_BMissionScientific: gamma-ray astronomy^A#R:"Perigee/Apogee382/387 kmV#A#R*Inclination51.6T+ A#R&Period92.3 min\ G#^*" &Launch vehicleY+  A#R0Launch siteTyuratam&  # 5 ; '  End of lifeV  A#R*Decay28 Feb 1992$;  " @  1d A :@Program: Geo-IKL A 5 :0w/U" Program: Geo-IK\*  2 2UCV$㼨ԟRussian geodesy program. It is probably military aimed, to provide precise localisation of military targets for ICBM/IRBM attacks.The satellites of this series are based on the Musson bus (see Parus for details). The satellites are all named in the Cosmos program both the most recent one.8A  ' "(OTechnical data8  ' " SpecificationsV c A#R*&Prime contractorX  A#R.PlatformMusson busTc A#R&"Mass at launchS bA#R$ Mass in orbitOA#RDimensionQbA#R Solar arrayc"eA#RD StabilizationGravity gradientN A#RDC powerUe@A#R($Design life@ time&:@# 1@k@19 k@sA:@sAA P!&-lProgram: Geo-IKCosmos (1242): FailureCosmos 1312Cosmos 1410Cosmos 1510Cosmos 1589Cosmos 1660Cosmos 1732Cosmos 1803Cosmos 1823Cosmos 1950Cosmos 2037Cosmos 2088Cosmos 2226Geo-IK 19k@A1_ AAFGeo-IK 1EsAA5 :"w/U" Geo-IK 11 A"B'  Generalg ABG#^@") Designation23411 / 94078Ah'"BBA#RNLaunch date24 Nov 1994 at 02:54 UTjB[CM#j:"N , Country of originCIS6BCS#vl"H̀(CV$!&MissionScientific: geodetic survey (Geo-IK)`[CDDA#R>"Perigee/Apogee1480/1526 kmVCDA#R*Inclination73.6SDDDA#R$Period116 minr%D_EM#jJ" &ቂLaunch vehicleCyclone 3 #112DF% 7It also carried an experimental Elekon positioning equipment to monitor movements of land and sea transportations, to optimize and increase efficiency.@_E_F1[ _FF)JProgram: GonetsLFF5 :0wP8W" Program: GonetsD_FH2 2%SRussian LEO telecommunication system, designed from the reconvertion of military technology. The system should be composed of 36 satellites on 6 orbital planes. The project was launched in 1992. The satellites are probably less than 300 kg.The system should use the GPS and GLONASS positioning systems for geolocation services. Gonets will operate in the 300-400 MHz range VHF/UHF band and the 1.5/1.6 GHz band. Uplinks will be from 312-315 MHz and 1624.5-1643.4 MHz, and downlinks from 387-390 MHz and 1541.0-1541.9 MHz.vFI* $<The system is derived from the Strela-3 military series. The Gonets-D crafts were most probably test satellites.<HI' *O External resources^7I)J' nhttp://www.wp.com/mcintosh_page_o_stuff/gonets.html1IZJ1U ZJLL=)JJ) "(!ְProgram: Gonets2 ZJJ'  Gonets D#JqK#ڀF6:>BCosmos 2199Cosmos 22013 JK'  Gonets D1[qKL#""I, J,>K,\L,zM,N,Gonets D1-1Gonets D1-2Gonets D1-3Gonets D1-4Gonets D1-5Gonets D1-6$KL" < LM13  MPMGonets D1-1HLPM5 :(wP8W" Gonets D1-11 MM'  Generalg PMMG#^@") Designation23787 / 96009A\MDNA#R6Launch date19 Feb 1996jMNM#j:"N , Country of originCIS7DN8OS#vn"H̀(㓉!ְMissionMilitary: telecommunications (Gonets)\NOA#R6"Perigee/Apogee~1400 kmU8O A#R(Inclination~82O LL OXA#RPeriodr% ʀM#jJ" &ቂLaunch vehicleCyclone 3 #115&X# < ʀ,1 B  ,tGonets D1-2Ht5 :(wP8W" Gonets D1-21 ,'  Generalg t G#^@") Designation23788 / 96009B\hA#R6Launch date19 Feb 1996j ҂M#j:"N , Country of originCIS7h\S#vn"H̀(㓉!ְMissionMilitary: telecommunications (Gonets)\҂A#R6"Perigee/Apogee~1400 kmU\ A#R(Inclination~82L YA#RPeriodr% ˄M#jJ" &ቂLaunch vehicleCyclone 3 #115&Y# < ˄-13 P  -uGonets D1-3Hu5 :(wP8W" Gonets D1-31 -'  Generalg u G#^@") Designation23789 / 96009C\iA#R6Launch date19 Feb 1996j ӆM#j:"N , Country of originCIS7i]S#vn"H̀(㓉!ְMissionMilitary: telecommunications (Gonets)\ӆA#R6"Perigee/Apogee~1400 kmU]A#R(Inclination~82L ZA#RPeriodr%̈M#jJ" &ቂLaunch vehicleCyclone 3 #115$Z" < ̈,1B e  ,tGonets D1-4Ht5 :(wP8W" Gonets D1-41 ,'  Generalg t G#^@") Designation24728 / 97006D\hA#R6Launch date14 Feb 1997j ҊM#j:"N , Country of originCIS7h\S#vn"H̀(㓉!ְMissionMilitary: telecommunications (Gonets)[ҊA#R4"Perigee/Apogee1410 kmV\ A#R*Inclination82.6S`A#R$Period114 minr% ҌM#jJ" &ቂLaunch vehicleCyclone 3 #116$`" < Ҍ21P 9  2zGonets D1-5Hz5 :(wP8W" Gonets D1-51 2'  Generalg zG#^@") Designation24729 / 97006E\nA#R6Launch date14 Feb 1997j؎M#j:"N , Country of originCIS7nbS#vn"H̀(㓉!ְMissionMilitary: telecommunications (Gonets)[؎A#R4"Perigee/Apogee1410 kmVbA#R*Inclination82.6SrA#R$Period114 minr%M#jJ" &ቂLaunch vehicleCyclone 3 #116$r" < D1e  DGonets D1-6H5 :(wP8W" Gonets D1-61 D'  Generalg $G#^@") Designation24730 / 97006F\A#R6Launch date14 Feb 1997j$M#j:"N , Country of originCIS7tS#vn"H̀(㓉!ְMissionMilitary: telecommunications (Gonets)[A#R4"Perigee/Apogee1410 kmVt%A#R*Inclination82.6SxA#R$Period114 minr%%M#jJ" &ቂLaunch vehicleCyclone 3 #116$x" 7E1 E?Granat? 2 4"  Granat1 E'  Generalg G#^@") Designation20352 / 89096A[wA#R4Launch date1 Dec 1989jM#j:"N , Country of originCISr%wSM#jJ"H̀_BMissionScientific: astronomyc"A#RD"Perigee/Apogee57435/146072 kmVS A#R*Inclination86.7VbA#R*Period5897.8 min\ G#^*" &Launch vehicleYbA#R0Launch siteTyuratam_;v$ vAstronomy satellite carrying the French Sigma telescope<' *O External resources_v?. ,http://hea.iki.rssi.ru/GRANAT/granat.htmlhttp://kisa.iki.rssi.ru/GRANAT/sigma/sigma.html; z1U. z& InformatorC?2 4$"  Informator_6z) "l䵟Also called AO-21 or RS-14 or Rudak 2 or Oscar 211 M'  Generalg G#^@") Designation21087 / 91006A\MA#R6Launch date29 Jan 1991jzM#j:"N , Country of originCISo"M#jD"H̀㓉MissionTelecommunications_zHA#R<"Perigee/Apogee955/1005 kmVA#R*Inclination82.9UHA#R(Period104.7 minl_M#j>" &s,梉Launch vehicleCosmos CYA#R0Launch sitePlesetsk&_# 5'  End of lifed#wA#RF"Out of servicemid-October 1994&# 8w' "(OTechnical data92 2?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:d#~A#RF0Mode B up435.102 - 435.022 MHzf%A#RJ0Mode B down145.852 - 145.932 MHzu4~YA#Rh0Beacons145.822 MHz CW, 145.952 MHz 1100 bps PSK>* $(Transponder 2:d#YA#RF0Mode B up435.123 - 435.043 MHzf%aA#RJ0Mode B down145.866 - 145.946 MHzu4A#Rh0Beacons145.948 MHz CW, 145.838 MHz 1100 bps PSKBa* $0RUDAK Transponder:IA#RUplink 1435.016 MHz 1200 bps Manchester FSK + FM repeater input frq.g& A#RLUplink 2435.155 MHz 2400 bps BPSKl+uA#RVUplink 3A435.193 MHz 4800 bps RSM NRZIl+ A#RVUplink 3B435.193 MHz 9600 bps RSM NRZIx7uYA#RnUplink 4435.041 MHz Digital Signal Processor input&# YYA#R0Downlink145.987 MHzu(MM#jP(UO뉂Mode 1Pacsat / FO-20 compatibleq*G#^Tn쉂Mode 2AO-13 400 bps BPSK compatiblel%M*G#^Jn쉂Mode 3AO-13 RUDAK I compatibleT~A#R&Mode 44800 bpsT*A#R&Mode 59600 bpsN ~ A#RMode 6CWq0 A#R`Mode 7FSK (F1 or F2B) RTTY, FAX, SSTV, etc.q0  A#R`Mode 8FM using D/A converter and DSP output$ & " E k 1j k  J Program: IntercosmosU&  8 @<Ƨ" Program: Intercosmosek J % 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.1 { 1 {  XJ  A R"㹧Ԁ=ԉ>㉂Program: IntercosmosIntercosmos 01Intercosmos 18Intercosmos Bulgaria 1300?{ S 1u  S  /BIntercosmos 01O  8 @0Ƨ" Intercosmos 011 S  '  Generalg :G#^@") Designation04128 / 69088A\ A#R6Launch date14 Oct 1969j:M#j:"N , Country of originCIS~1~M#jb"H߲̀-MissionScientific: high atmosphere study^A#R:"Perigee/Apogee264/617 kmV~>@A#R*>@ Inclination48.3T@A#R&Period93.4 minl>@@M#j>" &r,梉Launch vehicleCosmos B]@[AA#R8Launch siteKapustin Yar&@A# 5[AA'  End of lifeUA BA#R(Decay2 Jan 1970$A/B" ? BnB1" с  nBBNGIntercosmos 18O/BB8 @0Ƨ" Intercosmos 181 nBB'  Generalg BUCG#^@") Designation11082 / 78099A\BCA#R6Launch date24 Oct 1978jUCDM#j:"N , Country of originCIS@CDS#v"H̀(?vd;plMissionScientific: ionosphere and magnetosphere study^D EA#R:"Perigee/Apogee403/757 kmTD`EA#R&Inclination83T EEA#R&Period96.3 minl`E FM#j>" &s,梉Launch vehicleCosmos CYEyFA#R0Launch sitePlesetsk& FF# 5yFF'  End of lifeVF*GA#R*Decay17 Mar 1981$FNG" J*GG1nu  GG/LIntercosmos Bulgaria 1300Z"NGG8 @FƧ" Intercosmos Bulgaria 1300@G2H# :Also called Intercosmos 221 GcH'  Generalg 2HHG#^@") Designation12645 / 81075A[cH%IA#R4Launch date7 Aug 1981o"HIM#jD"N ,Q_tCountry of originBulgaria_%IIG#^0"H̀MissionScientific^IQJA#R:"Perigee/Apogee788/882 kmVIJA#R*Inclination81.2UQJJA#R(Period101.6 min\JXKG#^*" &Launch vehicleYJKA#R0Launch sitePlesetskZXK LA#R2"Mass at launch350 kg$K/L" > LmL1 mLLpNProgram: LuchJ/LL5 :,NG" Program: LuchmLpN. *CGMeans "beam"; also called Al'tair or SDRNRussian program for LEO communications relay (e.g. Mir). This program is also known as SDRN (Satellite Data Relay Network). The first generation satellites of this program were based on the Al'tair platform. The second generation's performance is said to increase the capacity of the channels by nearly 3 and its lifetime would be twice as long.1LN1 N?OOpN?OO nᇏw!w+fxvEomEoProgram: LuchCosmos 1700Cosmos 1897Cosmos 2054Luch 0Luch 11NpO1U pO\;?OO# 0Luch's specifications[pOA#R4&Prime contractorNO?OPOPMUOgA#R(PlatformAl'tair[€A#R4"Mass at launch2000 kg^g A#R:Dimension8.5 x 11 x 16 mm,€A#RX Stabilization3 axis, 0.5 GEO precisionT A#R&DC power1800 W\=A#R6$Design lifetime5 years@}' 2 UHF-band (0.9/0.7 GHz)X=ՂA#R.(Main transponders1Y}.A#R0Coverage6 spotbeamRՂA#R"EIRP40.7 dBW8.' " Ku-band - dataXA#R.(Main transponders1O_A#RPower30 WUA#R(Bandwidth50 MHz[_A#R4Coverage0.5 spotbeamRaA#R"EIRP55.2 dBWo.ЅA#R\Uplink15.130-15.180 GHz LHCP (16/64 kbps)u4aEA#RhDownlink13.511-13.545 GHz RHCP (16/64/256 kbps)1 Ѕv'  Ku-bandXEΆA#R.(Main transponders1v5vDA#RjCoverage1 spotbeam (1.6 m diam onboard antenna)RΆA#R"EIRP42.3 dBWb!DA#RBUplink14.591-14.625 GHz LHCPd#\A#RFDownlink10.810-10.860 GHz RHCP$" 1\1W +T+) "VȠ$To view this page you need to register&+# 7b1|  bLuch 0C+5 :NG" Luch 01 b։'  Generalg =G#^@") Designation23426 / 94082A\։A#R6Launch date16 Dec 1994j=M#j:"N , Country of originCISo"rM#jD"H̀‰MissionTelecommunicationsb!ԋA#RB,Geostationary orbitsee belowo"rCM#jD" &㉓gLaunch vehicleProton #230[ԋA#R4"Mass at launch2000 kg}SC* $qTransmits data to and from Mir station. It is equipped with a Cospas payload.: U- */ۀ Locationߍm#:   " BeginEndPosition#Ulj#F$8:L: 16 Dec 1994Mar 199795Eߍj#*May 199716W&l# 8I' "(Technical data<) "&CGSpecifications7I11    Luch 1C 5 :NG" Luch 1 1 ='  Generalg G#^@") Designation23680 / 95054Ah'= A#RNLaunch date11 Oct 1995 at 16:26 UTjvM#j:"N , Country of originCISo" M#jD"H̀‰MissionTelecommunicationsevJG#^<"/ۀ0Geostationary orbit77Eo"M#jD" &㉓gLaunch vehicleProton #236[JA#R4"Mass at launch2400 kg 3 4q󉂂CGEquipped with a Cospas payload?Its performance is said to increase the capacity of the channels by nearly 3 and its service lifetime would be twice as long compared to the Al'tair design.@L1c. LProgram: MeteorP 8 @2ȉ" Program: MeteorLv$ mSoviet meteorology satellite program. Mission: met observation: clouds, ice cover and atmospheric radiation; high speed natural phenomena: cyclone, tidal action, dust storms, etc.9' $(OMeteor 1 series?v# 830/31 satellites launched9'' $(OMeteor 2 series<c# 221 satellites launched9'' $(OMeteor 3 series2c# 6 since 198511U A=<) "(3xAProgram: Meteor7s'   Meteor-CosmosO<]#(?ف("فDbCosmos 0122Cosmos 0144Cosmos 0156Cosmos 0184Cosmos 0206st#, $(Cosmos 0226&] # 2 ?'  Meteor 1( #P(>k(">kDHLMeteor 1-01Meteor 1-02&?# 2 H'  Meteor 2(#P(Du k("s kDHLMeteor 2-01Meteor 2-21&H# 2 Q'  Meteor 37#n(٫ k("۫ k(Dܫ kfjMeteor 3-03Meteor 3-05Meteor 3-06$QA" 1r1U rC A# @Meteor-Cosmos' specificationsVr A#R*0&Prime contractor[fA#R40"Mass at launch2000 kgT A#R&0Diameter1.5 m?Pf A#R0Height5 m?_iA#R<0Solar array2 solar panelsZ A#R20 Stabilization3 axis?$i" 11U q?W# 8Meteor 1's specificationsVA#R*0&Prime contractor[WA#R40"Mass at launch2200 kgThA#R&0Diameter1.5 m?PA#R0Height5 m?_hA#R<0Solar array2 solar panelsZqA#R20 Stabilization3 axis?$" 1q1U #G?# 8Meteor 2's specificationsj)oA#RR0&Prime contractorVNII ElektromekanikiZA#R20 Mass in orbit1500 kgQoA#R 0Diameter2 mOiA#R0Height5 ma A#R@0Solar array2 panels of 10 mYi#A#R00 Stabilization3 axis$G" 1#x1U x8G# *Meteor 2's payloadR+x' V Scanning Telephotometer (direct imaging)c"eA#RD0Wavebands0.5-7.0 m (visible)~<B#Tx0Resolutionglobal coverage: 2 kmregional coverage: 1 km@e#' 2 Scanning IR Radiometer[~A#R40Wavebands8-12 m (IR)e$#A#RH0Resolutionglobal coverage: 8 kmB~%' 6 Scanning IR Spectrometerf%A#RJ0Wavelengths11, 10-18, 70 m (IR)U%A#R(0Resolution30 km$" 151U 5  ?t# 8Meteor 3's specificationsj)5A#RR0&Prime contractorVNII ElektromekanikiZt8 A#R20 Mass in orbit1500 kgQ A#R 0Diameter2 mO8  A#R0Height5 ma 9 A#R@0Solar array2 panels of 10 mY  A#R00 Stabilization3 axis$9  " 1  1 8  # *Meteor 3's payloadR+ q ' V Scanning Telephotometer (direct imaging)c"  A#RD0Wavebands0.5-7.0 m (visible)~<q R B#Tx0Resolutionglobal coverage: 2 kmregional coverage: 1 km@  ' 2 Scanning IR Radiometer[R  A#R40Wavebands8-12 m (IR)e$ R A#RH0Resolutionglobal coverage: 8 kmB  ' 6 Scanning IR Spectrometerf%R  A#RJ0Wavelengths11, 10-18, 70 m (IR)U OA#R(0Resolution30 km^ $ +TOMS (Total Ozone mapping Spectrometer): provided by the United States on some satellites< O 1 YCMeteor 1-01LY8 @*ȉ" Meteor 1-011 '  Generalg Y @G#^@") Designation03835 / 69029A @\h@A#R6Launch date26 Mar 1969j @@M#j:"N , Country of originCIShh@:AM#j6"H̀l/MissionMeteorology^@AA#R:"Perigee/Apogee548/575 kmV:AAA#R*Inclination81.2TABBA#R&Period95.9 min\ABG#^*" &Launch vehicleYBBBA#R0Launch sitePlesetsk[BRCA#R4"Mass at launch2200 kg&BxC# 8RCC' "(Technical data<xCC) "&YeSpecifications< C(D1M0 (DtDHMeteor 1-02LCtD8 @*ȉ" Meteor 1-021 (DD'  Generalg tD EG#^@") Designation04119 / 69084A[DgEA#R4Launch date6 Oct 1969j EEM#j:"N , Country of originCIShgE9FM#j6"H̀l/MissionMeteorology^EFA#R:"Perigee/Apogee514/550 kmV9FFA#R*Inclination81.2TFAGA#R&Period95.3 min\FGG#^*" &Launch vehicleYAGGA#R0Launch sitePlestesk&GH# 8GTH' "(Technical data<HH) "&YeSpecifications< THH1`f HIGMMeteor 2-01LHI8 @*ȉ" Meteor 2-011 HII'  Generalg IIG#^@") Designation08026 / 75064A\II JA#R6Launch date11 Jul 1975jIvJM#j:"N , Country of originCISh JJM#j6"H̀l/MissionMeteorology^vJ0 MMԁMeteor 2-21LGMM8 @*ȉ" Meteor 2-211 MN'  Generalg MgNG#^@") Designation22782 / 93055Ah'NNA#RNLaunch date31 Aug 1993 at 04:40 UTjgN9OM#j:"N , Country of originCIShNOM#j6"H̀l/MissionMeteorology^9O A#R:"Perigee/Apogee934/966 kmO GMVObA#R*Inclination82.5U A#R(Period104.1 minr%b)M#jJ" &ቂLaunch vehicleCyclone 3 #106&O# 8)' "(Technical dataMOԁ0 0:{e59MӉSpecificationsPayload< 1f \;Meteor 3-03Lԁ\8 @*ȉ" Meteor 3-031 '  Generalg \G#^@") Designation20305 / 89086A\PA#R6Launch date24 Oct 1989jM#j:"N , Country of originCIShP"M#j6"H̀l/MissionMeteorology`A#R>"Perigee/Apogee1235/1248 kmV"؄A#R*Inclination82.6U-A#R(Period110.3 minq$؄M#jH" &ቂLaunch vehicleCyclone 3 #80&-ą# 5'  End of lifeWąPA#R,"Out of serviceyes&v# 8P' "(Technical data[v;2 4,ߙ5SpecificationsPayloadAPT downlink frequency: 137.300 MHz (current status unknown)< w1g wÇMeteor 3-05L;Ç8 @*ȉ" Meteor 3-051 w'  Generalg Ç[G#^@") Designation21655 / 91056A\A#R6Launch date15 Aug 1991j[!M#j:"N , Country of originCIShM#j6"H̀l/MissionMeteorology`!A#R>"Perigee/Apogee1184/1203 kmW@A#R,Inclination82.55UA#R(Period109.3 minq$@M#jH" &ቂLaunch vehicleCyclone 3 #94wM}* $ bUCarried the TOMS instrument which failed in 1994. Replaced Meteor 2-218' "(OTechnical dataD!}# BTransmits on 137.850 MHz (APT)< 51! 5_Meteor 3-06L8 @*ȉ" Meteor 3-061 5'  Generalg G#^@") Designation22969 / 94003A\uA#R6Launch date25 Jan 1994jߍM#j:"N , Country of originCIShuGM#j6"H̀l/MissionMeteorology`ߍA#R>"Perigee/Apogee1184/1209 kmWGA#R,Inclination82.55VTA#R*Period109.36 minr%ƏM#jJ" &ቂLaunch vehicleCyclone 3 #107T' On board was a GeƏrman PRARE navigational system to measure parameters of spacecraft motion.The French Scarab payload for radiation budget failed in April 1995. This instrument will fly again in late-1996 and on Envisat.8Ə' "(Technical dataM_0 0:,ߙ5SpecificationsPayloadA1 @c" Program: MolniyaQ_8 @4z" Program: Molniyav( Means "flash of lightning" in RussianSoviet telecomunication program. Satellites are placed on very excentric orbits (460/40000 km, inclination: 63, satellites in 8 planes separated by 45) with a 12 hours period. Such satellites remain almost 8 hours above the CIS, slowly drifting high in the sky. Molniya satellites are used by the Orbita network equipped with 12 m antennas. Mars transportable stations could also use the network with 7 m antennas. Mission: provide long distance reliable telephone and TV links. Molniya-1 are used for government and military communications whereas Molniya-3 are used for TV programs.G. *3o7U=As the first Molniya-2 satellites were launched the system became available for Intersputnik. The first satellite operated at 1.0/0.8 GHz. C-band (6/4 GHz) was introduced from Molniya 1-07 on. Satellites also use L-band.In the future, the system could be replaced by Mayak3  ' (OMolniya 18A' " Specifications\ A#R6&Prime contractorNPO PMUAA#R(PlatformMolniyaTFA#R&"Mass at launchZA#R2 Mass in orbit1600 kgOFA#RDimensionQ@A#R Solar arraySA#R$ StabilizationY@A#R0DC powerBOL: 1000 W\HA#R6$Design lifetime2 years&n# 0 H'  X-band]nA#R8(Main transponders1 to 3YTA#R0,Backup transpondersVA#R*Power40 W (TWTA)OTA#RBandwidthN GA#RCoverageJ A#REIRPRGA#R"Polarization& # <E' *O External resourcesf? ' ~http://www.ninfinger.org/~sven/models/sovietsp/molniya.html1E1U# -Q>) "*jQvProgram: MolniyaH#(VIW($HW(HHW(lHWMolniya 1-01Molniya 1-71Molniya 1-72Molniya 1-74H#(IW($IW(HIW(lIWMolniya 1-85Molniya 1-86Molniya 1-87Molniya 1-88(jx#P(IW($4IWHLMolniya 1-89Molniya 1-90l c# jfl#0f(X$(,Molniya 2-01l c# Hf#(|Y($RY(HSY(lTYMolniya 3-01Molniya 3-34Molniya 3-35Molniya 3-36H#(UY(${Y(H}Y(l~YMolniya 3-37Molniya 3-42Molniya 3-44Molniya 3-458>#؀p(Y($〵Y(HふYlMolniya 3-46Molniya 3-47Molniya 3-48l c# >-l#.(㘜7"&*Molniya 1-S$Q" = -1# $  @Molniya 1-01MQ8 @,z" Molniya 1-011  '  Generalg sG#^@") Designation01324 / 65030A\ A#R6Launch date23 Apr 1965js9M#j:"N , Country of originCISo"M#jD"H̀㓉MissionTelecommunications`9A#R>"Perigee/Apogee538/39300 kmV^A#R*Inclination65.5UA#R(Period707.3 min\^G#^*" &Launch vehicleYhA#R0Launch siteTyuratam&# 5h'  End of lifeV A#R*Decay16 Aug 1979&? # 8 w ' "(OTechnical data8?  ' " SpecificationsVw  A#R*&Prime contractorN S A#RPlatform[  A#R4"Mass at launch1000 kgSS  A#R$ Mass in orbitL M A#RLengthK   A#RWidthL M  A#RHeightX < A#R. StabilizationSpin?N  A#RDC powerU<  A#R($Design lifetime&  # Y2 ^ ' d Transmission (upload: 0.8 GHz, download: 1 GHz)X  A#R.(Main transponders3Y^ A#R0,Backup transpondersO ^A#RPower40 Wa A#R@Bandwidth240 phone circuitsN ^ A#RCoverageJ WA#REIRPR A#R"Polarization$W @"  @Q= I@1% I@@EDMolniya 1-71M @@8 @,z" Molniya 1-711 I@@'  Generalg @.AG#^@") Designation18946 / 88017A\@AA#R6Launch date11 Mar 1988j.AAM#j:"N , Country of originCISo"AcBM#jD"H̀㓉MissionTelecommunications`ABA#R>"Perigee/Apogee491/38976 kmVcBCA#R*Inclination62.5SBlCA#R$Period699 min\CCG#^*" &Launch vehicleYlC!DA#R0Launch siteTyuratam$CED" = !DD1& DD~HMolniya 1-72MEDD8 @,z" Molniya 1-721 DE'  Generalg DgEG#^@") Designation18980 / 88022A\EEA#R6Launch date17 Mar 1988jgE-FM#j:"N , Country of originCISo"EFM#jD"H̀㓉MissionTelecommunications`-FFA#R>"Perigee/Apogee655/40584 kmVFRGA#R*Inclination62.9SFGA#R$Period735 min\RGHG#^*" &Launch vehicleYGZHA#R0Launch sitePlesetsk$H~H" = ZHH14' HILMolniya 1-74M~HI8 @,z" Molniya 1-741 H9I'  Generalg IIG#^@") Designation19730 / 88115A\9IIA#R6Launch date28 Dec 1988jIfJM#j:"N , Country of originCISo"IJM#jD"H̀㓉MissionTelecommunications`fJ5KA#R>"Perigee/Apogee654/38870 kmVJKA#R*Inclination62.8S5KKA#R$Period700 mincKALG#^8" &Launch vehicleMolniyaYKLA#R0Launch sitePlesetsk$ALL" = LL16( LHM Molniya 1-85MLHM8 @,z" Molniya 1-851 LyM'  Generalg HMMG#^@") Designation22309 / 93002A\yM"Perigee/Apogee528/39822 kmVOOA#R*Inclination63.4UuO,A#R(O,LPeriod717.7 mincOG#^8" &Launch vehicleMolniyaY,A#R0Launch sitePlesetsk$ " = I14N) INMolniya 1-86M 8 @,z" Molniya 1-861 Iǁ'  Generalg .G#^@") Designation22671 / 93035A\ǁA#R6Launch date26 May 1993j.M#j:"N , Country of originCISo"cM#jD"H̀㓉MissionTelecommunications`ÃA#R>"Perigee/Apogee681/39672 kmVcA#R*Inclination62.9UÃnA#R(Period717.8 mincфG#^8" &Launch vehicleMolniyaYn*A#R0Launch sitePlesetsk$фN" = *16q* ؅Molniya 1-87MN؅8 @,z" Molniya 1-871  '  Generalg ؅pG#^@") Designation22949 / 93079A\ ̆A#R6Launch date22 Dec 1993jp6M#j:"N , Country of originCISo"̆M#jD"H̀㓉MissionTelecommunications`6A#R>"Perigee/Apogee446/39206 kmV[A#R*Inclination62.8SA#R$Period703 minc[G#^8" &Launch vehicleMolniyaYjA#R0Launch sitePlesetsk3$ Molniya 1-T= jډ1N+ ډ'Molniya 1-88M'8 @,z" Molniya 1-881 ډX'  Generalg 'G#^@") Designation23420 / 94081A\XA#R6Launch date14 Dec 1994jM#j:"N , Country of originCISo"M#jD"H̀㓉MissionTelecommunications`TA#R>"Perigee/Apogee516/39833 kmVA#R*Inclination62.8STA#R$Period718 minebG#^<" &Launch vehicleMolniya M^A#R:Launch sitePlesetsk LC433b$ Molniya 1-T= 01Qq, 0}Molniya 1-89M}8 @,z" Molniya 1-891 0'  Generalg }G#^@") Designation24274 / 96045Ah'}A#RNLaunch date14 Aug 1996 at 22:21 UTj M#j:"N , Country of originCIS} o"}{M#jD"H̀㓉MissionTelecommunications` A#R>"Perigee/Apogee516/39833 kmV{1A#R*Inclination62.8TA#R&Period12 hourse1G#^<" &Launch vehicleMolniya M^HA#R:Launch sitePlesetsk LC43zT& Molniya 1-T seriesThis is said to be the 200th MolniyaMass at launch: 1600 kg?= H16- L,Molniya 1-90ML8 @,z" Molniya 1-901 }'  Generalg LG#^@") Designation24960 / 97054Ah'}LA#RNLaunch date24 Sep 1997 at 21:32 UTjM#j:"N , Country of originCISo"L%M#jD"H̀㓉MissionTelecommunications`A#R>"Perigee/Apogee506/39920 kmV%A#R*Inclination62.8T/A#R&Period12 hourseG#^<" &Launch vehicleMolniya M^/A#R:Launch sitePlesetsk LC43:,$ ,Molniya 1-T series= i1i. iMolniya 2-01M,8 @,z" Molniya 2-011 i'  Generalg NG#^@") Designation05620 / 71100A\A#R6Launch date25 Nov 1971jNM#j:"N , Country of originCISo"M#jD"H̀㓉MissionTelecommunications`A#R>"Perigee/Apogee516/39553 kmT7A#R&Inclination65SA#R$Period712 min\7G#^*" &Launch vehicleY?A#R0Launch sitePlesetsk&e# 5?'  End of lifeVeA#R*Decay10 May 1976$" = Q16B/ Qg Molniya 3-01M8 @,z" Molniya 3-011 Q'  Generalg 6G#^@") Designation07540 / 74092A\A#R6Launch date21 Nov 1974j6M#j:"N , Country of originCISo"kM#jD"H̀㓉MissionTelecommunications`A#R>"Perigee/Apogee250/40095 kmVk!A#R*Inclination64.1UvA#R(Period717.6 min\!G#^*" &Launch vehicleYv7 A#R07 Launch sitePlesetsk[ A#R4"Mass at launch1600 kg&7  # 5  '  End of lifeV C A#R*Decay15 May 1986$ g " = C  1iZ0    Molniya 3-34Mg  8 @,z" Molniya 3-341  " '  Generalg   G#^@") Designation19713 / 88112A\"  A#R6Launch date22 Dec 1988j O M#j:"N , Country of originCISo"  M#jD"H̀㓉MissionTelecommunications`O  A#R>"Perigee/Apogee899/39481 kmV t A#R*Inclination63.9U  A#R(Period718.3 minct , G#^8" &Launch vehicleMolniyaY  A#R0Launch sitePlesetsk$,  " =   1Br1  3  Molniya 3-35M 3 8 @,z" Molniya 3-351  d '  Generalg 3  G#^@") Designation20052 / 89043A[d & A#R4Launch date8 Jun 1989j  M#j:"N , Country of originCISo"&  M#jD"H̀㓉MissionTelecommunicationsa  ` A#R@"Perigee/Apogee1436/38918 kmV  A#R*Inclination64.8U`  A#R(Period717.8 minc n G#^8" &Launch vehicleMolniyaY  A#R0Launch sitePlesetsk$n  " = ( 1Z2 ( u - Molniya 3-36M u 8 @,z" Molniya 3-361 (  '  Generalg u  G#^@") Designation20338 / 89094A\ i A#R6Launch date28 Nov 1989j  M#j:"N , Country of originCISo"i B M#jD"H̀㓉MissionTelecommunications`  A#R>"Perigee/Apogee698/39655 kmVB  A#R*Inclination64.8U M A#R(Period717.8 minc  G#^8" &Launch vehicleMolniyaYM   A#R0Launch sitePlesetsk$ - " =  j 1r3 j  tB Molniya 3-37M-  8 @,z" Molniya 3-371 j  '  Generalg  O G#^@") Designation20444 / 90006A\  A#R6Launch date23 Jan 1990jO !@ M#j:"N , Countr !@ - y of originCISo" @ M#jD"H̀㓉MissionTelecommunications`!@ @ A#R>"Perigee/Apogee982/39367 kmV@ FA A#R*Inclination64.9U@ A A#R(Period717.7 min\FA A G#^*" &Launch vehicleYA PB A#R0Launch sitePlesetsk$A tB " = PB B 14 B B F Molniya 3-42MtB B 8 @,z" Molniya 3-421 B /C '  Generalg B C G#^@") Designation22178 / 92067A\/C C A#R6Launch date14 Oct 1992jC \D M#j:"N , Country of originCISo"C D M#jD"H̀㓉MissionTelecommunications`\D +E A#R>"Perigee/Apogee466/39103 kmVD E A#R*Inclination62.9S+E E A#R$Period701 min\E 0F G#^*" &Launch vehicleYE F A#R0Launch sitePlesetsk$0F F " = F F 1̂5 F 7G J Molniya 3-44MF 7G 8 @,z" Molniya 3-441 F hG '  Generalg 7G G G#^@") Designation22633 / 93025Ah'hG 7H A#RNLaunch date21 Apr 1993 at 00:30 UTjG H M#j:"N , Country of originCISo"7H I M#jD"H̀㓉MissionTelecommunications`H pI A#R>"Perigee/Apogee744/39603 kmVI I A#R*Inclination62.9UpI J A#R(Period717.7 mincI ~J G#^8" &Launch vehicleMolniyaYJ J A#R0Launch sitePlesetsk$~J J " = J 8K 16 8K K HO Molniya 3-45MJ K 8 @,z" Molniya 3-451 8K K '  Generalg K L G#^@") Designation22729 / 93049Ag&K L A#RLLaunch date4 Aug 1993 at 00:52 UTjL L M#j:"N , Country of originCISo"L ]M M#jD"H̀㓉MissionTelecommunications`L M A#R>"Perigee/Apogee511/39841 kmV]M N A#R*Inclination62.8UM hN A#R(Period717.7 mincN N G#^8" &Launch vehicleMolniyaYhN $O A#R0Launch sitePlesetsk$N HO " = $O O 1̂7 O O  Molniya 3-46MHO O 8 @,z" Molniya 3-461 O  '  GeneraO  HO lg O v G#^@") Designation23211 / 94051Ah' ހ A#RNLaunch date23 Aug 1994 at 14:31 UTjv H M#j:"N , Country of originCISo"ހ  M#jD"H̀㓉MissionTelecommunications`H  A#R>"Perigee/Apogee622/39726 kmT k A#R&Inclination63S  A#R$Period618 minek # G#^<" &Launch vehicleMolniya MY | A#R0Launch sitePlesetsk$#  " = | ݃ 1#8 ݃ *  Molniya 3-47M * 8 @,z" Molniya 3-471 ݃ [ '  Generalg * „ G#^@") Designation23642 / 95042Ag&[ ) A#RLLaunch date9 Aug 1995 at 01:21 UTj„  M#j:"N , Country of originCISo")  M#jD"H̀㓉MissionTelecommunications` b A#R>"Perigee/Apogee472/40851 kmV  A#R*Inclination62.3L b  A#RPeriode i G#^<" &Launch vehicleMolniya M^ LJ A#R:Launch sitePlesetsk LC43$i  " = LJ ( 1N9 ( u @ Molniya 3-48M u 8 @,z" Molniya 3-481 (  '  Generalg u  G#^@") Designation24640 / 96060Ah' u A#RNLaunch date24 Oct 1996 at 11:37 UTj ߉ M#j:"N , Country of originCISo"u N M#jD"H̀㓉MissionTelecommunications`߉  A#R>"Perigee/Apogee611/39768 kmVN  A#R*Inclination62.8U Y A#R(Period718.2 mine  G#^<" &Launch vehicleMolniya M^Y  A#R:Launch sitePlesetsk LC43$ @ " <  | 1#: | Ȍ > Molniya 1-SL@ Ȍ 8 @*z" Molniya 1-S1 |  '  Generalg Ȍ ` G#^@") Designation07392 / 74060A\  A#R6Launch date29 Jul 1974j` & M#j:"N , Country of originCISo"  M#jD"H̀‰MissionTelecommunicationsY&  A#R0,Geostationary orbitn! \ M#jB" &㉓gLaunch vehicleProton #49&  # 5\  '  End of lifeW  A#R,"Out of  @ serviceyes$ > " B  1"#;  F Program: NadezhdaR>  8 @6T" Program: Nadezhdat, F H ^Y q󉂂2xq 剂Nadezhda means 'hope'Russian navigation program using the Tsikada platform. The satellites of this program carry a Cospas receiver.The Nadezhda M generation (started with Cosmos 2315) carries hardware that can either provide Cospas or Kurs services.Designed by AO Polyot and NPO PM1 w 1< w  KF  H `.<:R򲟀S򲟉T򲟉U򲟉Program: NadezhdaNadezhda 1Nadezhda 2Nadezhda 3Nadezhda 4; w E 1= E  E Nadezhda 1K  8 @(T" Nadezhda 11 E  '  Generalg ( G#^@") Designation20103 / 89050A[  A#R4Launch date4 Jul 1989j(  M#j:"N , Country of originCISg T M#j4"H̀シMissionNavigation_  A#R<"Perigee/Apogee954/1011 kmTT  A#R&Inclination83U \ A#R(Period104.8 minl  M#j>" &s,梉Launch vehicleCosmos CY\ ! A#R0Launch sitePlesetsk$ E " ; !  1>   Nadezhda 2KE  8 @(T" Nadezhda 21  '  Generalg c G#^@") Designation20508 / 90017A\  A#R6Launch date27 Feb 1990jc ) M#j:"N , Country of originCISg  M#j4"H̀シMissionNavigation_)  A#R<"Perigee/Apogee950/1018 kmT C A#R&Inclination83U  A#R(Period104.8 minlC  M#j>" &s,梉Launch vehicleCosmos CY ] A#R0Launch sitePlesetsk&  # 8]  ' "(OTechnical data`=  # zUsed to transmit on 150 & 400 MHz (replaced by Nadezhda 4); V 1{C? V   Nadezhda 3K  8 @(T" Nadezhda 31 V  '  Generalg 9 G#^@") Designation21152 / 91019A\  A#R6Launch date12 Mar 1991j9  M#j:"N , Country of originCISg f M#j4"H̀シMissionNavigation_  A#R<"Perigee/Apogee952/1015 kmVf  A#R*Inclination82.9U p A#R(Period104.8 minl  M#j>" &s,梉Launch vehicleCosmos CYp A A#R0 A  Launch sitePlesetsk& g # 8A  ' "(OTechnical dataS/g  $ ^Downlink frequencies: 150 & 400 MHzPlane 12; - 1@ - x  Nadezhda 4K x 8 @(T" Nadezhda 41 -  '  Generalg x  G#^@") Designation23179 / 94041Ah' x A#RNLaunch date14 Jul 1994 at 06:13 UTj  M#j:"N , Country of originCISgx I M#j4"H̀シMissionNavigation_  A#R<"Perigee/Apogee951/1007 kmVI  A#R*Inclination82.9U S A#R(Period104.7 minl  M#j>" &s,梉Launch vehicleCosmos CYS  A#R0Launch sitePlesetsk& > # 8 v ' "(OTechnical dataS/>  $ ^Downlink frequencies: 150 & 400 MHzPlane 14?v  1_01A  W ; Program: OceanO W 8 @0" Program: Ocean ; & }Russian remote sensing program devoted to oceanographic applications. Mission: all-weather ice and sea monitoring, including ice floe/ice pack movements. Flood and pollution monitoring.1W l 1UB l   <;  ) "&뉢Program: Ocean1 l  '  Ocean-E! n t#B6:>Cosmos 1076Cosmos 11512   '  Ocean-OE!n 5 t#B6:>Cosmos 1500Cosmos 16022  g '  Ocean-O1<5 ) #܀x6󓋉L󓋉b󓋉Cosmos 1766Cosmos 1869Ocean 1Ocean 2Ocean 3g  #ր:"󓋀>w|,26Ocean 4Sich 1$)  " 1  1C   ? ] # 8Ocean-O1's specificationsb!  A#RB0Platformbuilt by NPO Yuzhnoe[]  A#R40"Mass at launch1400 kgS m A#R$0Diameter1.4 mO  A#R0Height3 mWm  A#R,0 Radar antenna12 mY l A#R00 Stabilization3 axis\8  $ pTransmissions: APT-like at 137.4 MHz & FM at 465 MHz1l  1UD C C 8 1 # *Ocean-O1's payloadB s ' 6 SLR (Side-Looking Radar)_1  A#R<0Frequency9.5 GHz (X-band)Vs ( A#R*0Resolution1.5 kmW  A#R,0Swath width460 kmO"(  - *D  MSU-M (Multispectral Scanner)t3 N@ A#Rf0 N@  Wavebands0.5-0.6; 0.6-0.7; 0.7-0.8; 0.8-1.1 mV @ A#R*0Resolution1.5 kmXN@ @ A#R.0Swath width2000 kmM @ IA - *@  MSU-S (Scanning Radiometer)t3@ A A#Rf0Wavebands0.5-0.6; 0.6-0.7; 0.7-0.8; 0.8-1.1 mUIA B A#R(0Resolution200 mWA iB A#R,0Swath width600 kmEB B ' < RM08 (microwave radiometer)^iB  C A#R:0Frequency36.5 - 36.8 GHzUB aC A#R(0Resolution25 kmW C C A#R,0Swath width550 km$aC C " 1C  D 1WE D aD D T+C aD ) "VȠ$To view this page you need to register& D D # 8aD D 1(sF D E H Ocean 1HD E 8 @"" Ocean 11 D 8E '  Generalg E E G#^@") Designation19274 / 88056A[8E E A#R4Launch date5 Jul 1988jE dF M#j:"N , Country of originCISv)E F M#jR"H̀郉MissionRemote sensing (Ocean-O1)^dF 8G A#R:"Perigee/Apogee606/633 kmVF G A#R*Inclination82.5T8G G A#R&Period97.1 minq$G SH M#jH" &ቂLaunch vehicleCyclone 3 #70&G yH # 8SH H ' "(Technical dataMyH H 0 0:*; YjSpecificationsPayload8H 6I 1)>G 6I ~I vM Ocean 2HH ~I 8 @"" Ocean 21 6I I '  Generalg ~I J G#^@") Designation20510 / 90018A\I rJ A#R6Launch date28 Feb 1990jJ J M#j:"N , Country of originCISv)rJ RK M#jR"H̀郉MissionRemote sensing (Ocean-O1)^J K A#R:"Perigee/Apogee618/645 kmVRK L A#R*Inclination82.5TK ZL A#R&Period97.3 minq$L L M#jH" &ቂLaunch vehicleCyclone 3 #83&ZL L # 8L )M ' "(Technical dataML vM 0 0:*; YjSpecificationsPayload8)M M 1IsH M M  Ocean 3HvM M 8 @"" Ocean 31 M 'N '  Generalg M N G#^@") Designation21397 / 91039A['N N A#R4Launch date4 Jun 1991jN SO M#j:"N , Country of originCISv)N O M#jR"H̀郉MissionRemote sensing (Ocean-O1)^SO 3 A#R:O 3 vM "Perigee/Apogee620/655 kmVO  A#R*Inclination82.5T3 ݀ A#R&Period97.5 minq$ N M#jH" &ቂLaunch vehicleCyclone 3 #92&݀ t # 8N  ' "(Technical datan<t  2 4x*; YjSpecificationsPayloadDownlink frequency: 137.4 MHz8 R 1I R   Ocean 4H  8 @"" Ocean 41 R ˂ '  Generalg 2 G#^@") Designation23317 / 94066Ah'˂  A#RNLaunch date11 Oct 1994 at 13:30 UT~12  M#jb"N , Country of originCIS (Russian/Ukrainian)v)  M#jR"H̀郉MissionRemote sensing (Ocean-O1)^  A#R:"Perigee/Apogee631/665 kmV B A#R*Inclination88.5T  A#R&Period97.7 minr%B  M#jJ" &ቂLaunch vehicleCyclone 3 #111[ c A#R4"Mass at launch1950 kg&  # 8c  ' "(Technical dataM  0 0:*; YjSpecificationsPayloadA O 1``J O  . Program: PrognozM  5 :2ގ" Program: PrognozoO . # Russian scientific program. Designed to study the Sun's activity and its influence on Earth's magnetosphere.1 _ 1dK _  3.   Ѐel?|s}s~ssssssssssProgram: PrognozPrognoz 01Prognoz 02Prognoz 03Prognoz 04Prognoz 05Prognoz 06Prognoz 07Prognoz 08Prognoz 09Prognoz 10Prognoz 11Prognoz 12; _ ͉ 1J|L ͉  - Prognoz 01G  5 :&ގ" Prognoz 011 ͉ E '  Generalg   G#^@") Designation05941 / 72029A\E  A#R6Launch date14 Apr 1972j r M#j:"N , Country of originCIS|/  M#j^"H̀d;plMissionScientific: magnetosphere studyb!r P A#RB"Perigee/Apogee1005/199667 kmT  A#R&Inclination65VP  A#R*Period5782.1 min\ V G#^*" &Launch vehicleY  A#R0Launch siteTyuratamZV  A#R2"Mass at launch845 kg$ - " ; h 1}G=M h   Prognoz 02G-  5 :&ގ" Prognoz 021 h  '  Generalg G G#^@") Designation06068 / 72046A\  A#R6Launch date29 Jun 1972jG  M#j:"N , Country of ori  - ginCIS|/  M#j^"H̀d;plMissionScientific: magnetosphere studya   A#R@"Perigee/Apogee517/201804 kmV L A#R*Inclination65.3V  A#R*Period5849.2 min\L  G#^*" &Launch vehicleY W A#R0Launch siteTyuratamZ  A#R2"Mass at launch845 kg}YW . $ Carries two French experiments (Calypso and Signe) to studies particles from the Sun.5 c '  End of lifeV.  A#R*Decay15 Dec 1982$c  " ;  1G|oN  _ u Prognoz 03G _ 5 :&ގ" Prognoz 031   '  Generalg _  G#^@") Designation06364 / 73009A\ S A#R6Launch date15 Feb 1973j  M#j:"N , Country of originCIS|/S 9 M#j^"H̀d;plMissionScientific: magnetosphere studya  A#R@"Perigee/Apogee590/200000 kmT9  A#R&Inclination65T B A#R&Period5783 min\  G#^*" &Launch vehicleYB  A#R0Launch siteTyuratamZ Q A#R2"Mass at launch845 kg$ u " ; Q  1=O   Prognoz 04Gu  5 :&ގ" Prognoz 041 ( '  Generalg  G#^@") Designation08510 / 75122A\(  A#R6Launch date22 Dec 1975j U M#j:"N , Country of originCIS|/  M#j^"H̀d;plMissionScientific: magnetosphere studya U 2 A#R@"Perigee/Apogee634/199000 kmT  A#R&Inclination65T2  A#R&Period5740 min\ 6 G#^*" &Launch vehicleY  A#R0Launch siteTyuratam$6  " ;  1o/P 5  Prognoz 05G 5 5 :&ގ" Prognoz 051 f '  Generalg 5  G#^@") Designation09557 / 76112A\f ) A#R6Launch date25 Nov 1976j  M#j:"N , Country of originCIS|/)  M#j^"H̀d;plMissionScientific: magnetosphere studya p A#R@"Perigee/Apogee777/198560 kmV  A#R*Inclination65.2Tp & A#R& &  Period5728 min\  G#^*" &Launch vehicleY&  A#R0Launch siteTyuratam$  " ; : 1HQ :  = Prognoz 06G  5 :&ގ" Prognoz 061 :  '  Generalg   G#^@") Designation10370 / 77093A\ u A#R6Launch date22 Sep 1977j  M#j:"N , Country of originCIS|/u [ M#j^"H̀d;plMissionScientific: magnetosphere studya   A#R@"Perigee/Apogee488/197867 kmT[  A#R&Inclination65T d A#R&Period5688 min\  G#^*" &Launch vehicleYd  A#R0Launch siteTyuratam$ = " ;  x 1/R x  0 Prognoz 07G=  5 :&ގ" Prognoz 071 x  '  Generalg  W G#^@") Designation11088 / 78101A\  A#R6Launch date30 Oct 1978jW  M#j:"N , Country of originCIS|/  M#j^"H̀d;plMissionScientific: magnetosphere studya   A#R@"Perigee/Apogee472/202627 kmV P A#R*Inclination64.9V  A#R*Period5881.1 min\P  G#^*" &Launch vehicleY [ A#R0Launch siteTyuratam&  # 5[  '  End of lifeV  A#R*Decay22 Oct 1980$ 0 " ; k 1HS k  r Prognoz 08G0  5 :&ގ" Prognoz 081 k  '  Generalg J G#^@") Designation12116 / 80103A\  A#R6Launch date25 Dec 1980jJ  M#j:"N , Country of originCIS|/  M#j^"H̀d;plMissionScientific: magnetosphere studya   A#R@"Perigee/Apogee978/197364 kmV C A#R*Inclination65.8V  A#R*Period5687.8 min\C  G#^*" &Launch vehicleY N A#R0Launch siteTyuratam$ r " ; N  1T   B Prognoz 09Gr  5 :&ގ" Prognoz 091  % '  Generalg   G#^@") Designation14163 / 83067A[%  @ A#R4Launch date1 Jul 1983  @ r j v@ M#j:"N , Country of originCIS; @ A S#vv"H̀(_BjMissionScientific: radio astronomy and Sun studyWv@ [A A#R,"Perigee/Apogeen/aTA A A#R&Inclinationn/aO[A A A#RPeriodn/a\A ZB G#^*" &Launch vehicleYA B A#R0Launch siteTyuratam$ZB B " ; B C 1fU C YC G Prognoz 10GB YC 5 :&ގ" Prognoz 101 C C '  Generalg YC C G#^@") Designation15661 / 85033A\C MD A#R6Launch date26 Apr 1985jC D M#j:"N , Country of originCIS_MD E G#^0"H̀MissionScientificb!D xE A#RB"Perigee/Apogee5975/194734 kmVE E A#R*Inclination76.8VxE $F A#R*Period5783.7 min\E F G#^*" &Launch vehicleY$F F A#R0Launch siteTyuratam5F G '  End of life\F jG A#R6"Out of serviceJan 1986$G G " ; jG G 1: [V G H % Prognoz 11GG H 5 :&ގ" Prognoz 11J'G ZH # NAlso called Interbol 1 or SO-M2 #5121 H H '  Generalg ZH H G#^@") Designation23633 / 95039Ag&H YI A#RLLaunch date2 Aug 1995 at 23:59 UTjH I M#j:"N , Country of originCIS<YI LJ M#jx"H̀d;plMissionScientific: magnetosphere study (Prognoz M2)a I J A#R@"Perigee/Apogee505/193064 kmVLJ K A#R*Inclination63.8TJ WK A#R&Period5472 mineK K G#^<" &Launch vehicleMolniya M^WK L A#R:Launch sitePlesetsk LC43[K uL A#R4"Mass at launch1200 kgL !M % This satellite is the Khvostovoy Zond ("Tail") satellite of Project Interbol, intended to investigate the Earth's geomagnetic tail.<uL ]M ' * External resourcesP)!M M ' Rhttp://www.iki.rssi.ru/interball.htmlF]M M ' > On-board science instrumentsm=M `N 0#0zSKA-1, PROMICS-3, VDP, AMEI-2, CORAL, ALPHA3 (plasma ions)P M N 0#0@ELECTRON, (plasma electrons) h8`N O 0#0pMONITOR-3 (solar wind ions with high time resolution)Z*N rO 0#0TIFPE (ion and electron flux variations)n>O O 0#0|MIF-M, FGS-1, FM-31 (magnetometers); OPERA (electric field)[+rO G 0#0VO G G AKR-X (solar radio emission 0.1-1.5 MHz)S#O  0#0FRF-15-1 (solar X-rays 2-240 keV)e5G  0#0jSKA-2, DOK-2, SOSNA-2, RKA-2 (energetic particles)& % # ; ` 1W `  V Prognoz 12G%  5 :&ގ" Prognoz 12J'`  # NAlso called Interbol 2 or SO-M2 #5131 " '  Generalg  G#^@") Designation24291 / 96050Bh'"  A#RNLaunch date29 Aug 1996 at 05:22 UTj [ M#j:"N , Country of originCIS5 ݃ M#jj"H̀?vMissionScientific: aurora study (Prognoz M2)`[ = A#R>"Perigee/Apogee782/19140 kmV݃  A#R*Inclination62.8L = ߄ A#RPeriode D G#^<" &Launch vehicleMolniya M^߄  A#R:Launch sitePlesetsk LC43[D  A#R4"Mass at launch1250 kg& # # < _ ' *O External resourcesU#  . ,http://www.kiam1.rssi.ru/Contents.html#BChttp://www.iki.rssi.ru/interball.html8_  ' "(OTechnical data< V # 2built by NPO Lavochkin@  1aaX  w Program: ProtonLV  5 :0+" Program: Protonp w % Soviet heavy satellite program to study cosmic radiations.Satellites have 4 solar pannels and a 9.7 m span.1  1Y 1 Aw 1 H `Ձ+܀㡄*㢄*㣄*㤄*Program: ProtonProton 1Proton 2Proton 3Proton 49 j 1qZ j  * Proton 1E1  5 :"+" Proton 11 j  '  Generalg G G#^@") Designation01466 / 65054A\  A#R6Launch date16 Jul 1965jG  M#j:"N , Country of originCISy,  M#jX"H̀?vMissionScientific: ionosphere study^  A#R:"Perigee/Apogee181/578 kmV : A#R*Inclination63.4T  A#R&Period92.2 minm :  M#j@" &㉓gLaunch vehicleProton #1Z U A#R2"Mass at launch12.2 t& { # 5U  '  End of lifeV{  A#R*Decay11 Oct 1965$ * " 9 c 1,р[ c  - Proton 2E*  5 :"+" Proton 21 c َ '  Generalg @ G#^@") Designation01701 / 65087A[َ  A#R4Launch date2 Nov 1965j@  M#j:"N , Country of originC  * ISy,  M#jX"H̀?vMissionScientific: ionosphere study^  A#R:"Perigee/Apogee189/608 kmV > A#R*Inclination63.5T  A#R&Period92.5 minm >  M#j@" &㉓gLaunch vehicleProton #2Z Y A#R2"Mass at launch12.2 t&  # 5Y  '  End of lifeU  A#R(Decay6 Feb 1966$ - " 9 f 1q\ f  % Proton 3E-  5 :"+" Proton 31 f  '  Generalg C G#^@") Designation02290 / 66060A[  A#R4Launch date6 Jul 1966jC  M#j:"N , Country of originCISy,  M#jX"H̀?vMissionScientific: ionosphere study^  A#R:"Perigee/Apogee185/594 kmV 5 A#R*Inclination63.5T  A#R&Period92.3 minm 5  M#j@" &㉓gLaunch vehicleProton #4Z P A#R2"Mass at launch12.2 t& v # 5P  '  End of lifeVv  A#R*Decay16 Sep 1966$ % " 9 ^ 1р] ^   Proton 4E%  5 :"+" Proton 41 ^  '  Generalg ; G#^@") Designation03544 / 68103A\  A#R6Launch date16 Nov 1968j;  M#j:"N , Country of originCISy, z M#jX"H̀?vMissionScientific: ionosphere study^  A#R:"Perigee/Apogee248/477 kmVz . A#R*Inclination51.6T  A#R&Period91.8 minn!.  M#jB" &㉓gLaunch vehicleProton #13X H A#R."Mass at launch17 t& n # 5H  '  End of lifeVn  A#R*Decay24 Jul 1969$  " @ ] 1cWh0i^ ]   Program: ResursL  5 :0 " Program: ResurswO] , ( Soviet remote sensing satellite program operated by the Priroda ('Nature') center of the Russian Central Geodesy and Cartography Agency (GUGK).The F2-series satellites had about 1 month lifetime while the F1 series had only half. The results of the mission (films) are sent back to earth in a reentry vehicle.A new series named Resurs DK should be launched in 1999. With 3 years lifetime this satellite will be placed in 400 km orbit by a Rus launcher. It's payload called Geoton-L will provide 2 - 2.5 m resolution panchromatic pictures, 2.5 - 3 m resol ,  ution multispectral pictures. 4 ` '  Chronology,   , &*8Resurs F20 is 60th in Resurs-F series. There were 4 types of Resurs-F spacecrafts: three of Resurs-F1 type and Resurs-F2. First Resurs-F1 named Cosmos 1127 was launched at 10:20 UTC on 5 Sep 1979 from LC41 of Plesetsk cosmodrome. First one of Resurs-F2 series (Cosmos 1906) was launched at 11:30 UTC on 26 Dec 1987 from LC16 of Plesetsk. There were a total of 50 spacecrafts of Resurs-F1 types (28 of the 1st type, 6 of the 2nd and 16 of the 3rd) and 10 of Resurs-F2 type launched. There were also two launch failures at the launch of Resurs-F1 of the 2nd and the 3rd types. So, there were 62 launch attempts of Resurs-F spacecrafts. &` 3 # &  Y # <3  ' *O External resourcesG Y  ' @http://www.ssc.se/sb/resurs/1   1U_    < I ) "&YProgram Resurs   #)2y9z9{9|9}9~99997777777777*8^!8㹾SsɉSsɉResurs F01Resurs F02Resurs F03Resurs F04Resurs F05Resurs F06Resurs F07Resurs F08Resurs F09Resurs F10Resurs F11Resurs F12Resurs F13Resurs F14Resurs F15Resurs F16Resurs F17Resurs F18Resurs F19Resurs F20Resurs F21Resurs 500Resurs O1-0 is Cosmos 1484Resurs O1-1 is Cosmos 1689Resurs O1-2 is Cosmos 1939Resurs O1-3Resurs O1-4$I  " 1 ) 1U` ) " F @ i # :Resurs F1's specifications_)  A#R<0&Prime contractorKB Photon]i % A#R80Platformmodified VostokU z A#R(0"Mass at launch?O%  A#R0Diameter?Yz " A#R00 Stabilization3 axis$ F " 1" w 1Ua w   @F  # :Resurs F2's specifications_w  A#R<0&Prime contractorKB Photon] s A#R80Platformmodified Vostoki(  A#RP0"Mass at launch6.5 t (capsule 2.5 t)Ss / A#R$0Diameter2.3 mY  A#R00 Stabilization3 axis$/  " 1  1b > 9  # ,Resurs F2's payloadE [ ' < KFA 1000 film camera system|:  B#Tt0Wavebands0.57-0.67 m (visible)0.67-0.8 m (near IR)V[ - A#R*0Resolution5-10 mV  A#R*0Swath width60 km2 -  '  KATE 200}< 2 A#Rx0Wavebands0.5-0.6, 0.6-0.7, 0.7-0.9 m (visible/near IR)W  A#R,0Resolution15-30 mW2  A#R,0Swath width180 km^: > $ tAlso equipped with an LK 1000 camera and a MK 4 camera1 o 1Uc o CB gB ?>  # 8Resurs O's specificationsj)o $@ A#RR0&Prime contractor $@ > VNII Elektromekaniki[ @ A#R40"Mass at launch1950 kgX$@ @ A#R.0Payload mass550 kgi(@ @A A#RP0Dimensions6 m long x 1.4 m diameterU@ A A#R(0Solar array10 mY@A A A#R00 Stabilization3 axisUA CB A#R(0Lifetime2 years$A gB " 1CB B 1Ud B H ;H 8gB B # *Resurs O's payloadQ*B !C ' T MSU-M (low resolution - visible and IR)}<B C A#Rx0Wavebands0.5-0.6 m, 0.6-0.7 m, 0.7-0.8 m, 0.8-1.0 mT-!C C ' Z MSU-S (medium resolution - visible and IR)f%C XD A#RJ0Wavebands0.58-0.7 m, 0.7-1.0 mS,C D ' X MSU-SK (5-channel visible and IR scanner)IXD 5E A#R0Wavebands0.5-0.6 m, 0.6-0.7 m, 0.7-08 m, 0.8-1.0 m, 10.4-12.6 mu4D E A#Rh0Resolution150 m (4 channels), 600 m (1 channel)W5E F A#R,0Swath width600 kmX1E YF ' b MSU-E (3-channel steerable push-broom scanner)s2F F A#Rd0Wavebands0.5-0.67 m, 0.65-0.8 m, 0.8-1.0 mTYF  G A#R&0Resolution30 mVF vG A#R*0Swath width85 kmH! G G ' B FRAGMENT (8-channel TV camera)YvG H A#R00Wavebands0.4-2.1 m$G ;H " 1H lH 1We lH H H T+;H H ) "VȠ$To view this page you need to register&lH H # ; H !I 1wf !I hI O Resurs F01GH hI 5 :& " Resurs F011 !I I '  Generalg hI J G#^@") Designation20006 / 89038A\I \J A#R6Launch date25 May 1989jJ J M#j:"N , Country of originCISp#\J 6K M#jF"H̀郉MissionRemote sensing (F2)^J K A#R:"Perigee/Apogee174/232 kmV6K K A#R*Inclination82.3TK >L A#R&Period88.6 minaK L G#^4" &Launch vehicleSoyuzY>L L A#R0Launch sitePlesetskL M % ACarried two Pion subsatellites aimed to air density research which were released. They were built by students at the Korolev Aviation Institute in Kubyshev.5L M '  End of lifeVM HN A#R*Decay17 Jun 1989&M nN # 7HN N '  O Subsatellites`nN )O $ PION 1 (20056 / 89038C) decayed on 23 Jul 1989PION 2 (20060 / 89038D) decayed on 24 Jul 19898N aO ' "(Technical dataM)O O 0 0:#@ⱺSpecificationsPayload; aO  1 \g S . Resurs F02O  O GO S 5 :& " Resurs F021  '  Generalg S  G#^@") Designation20095 / 89049A\ G A#R6Launch date27 Jun 1989j  M#j:"N , Country of originCISp#G ! M#jF"H̀郉MissionRemote sensing (F1)^  A#R:"Perigee/Apogee255/269 kmV! Ղ A#R*Inclination82.6T ) A#R&Period89.8 minaՂ  G#^4" &Launch vehicleSoyuzY)  A#R0Launch siteTyuratam&  # 5 > '  End of lifeV  A#R*Decay11 Jul 1989&>  # 8  ' "(Technical data< . ) "&rԓSpecifications; i 1\h i   Resurs F03G.  5 :& " Resurs F031 i  '  Generalg H G#^@") Designation20134 / 89055A\  A#R6Launch date18 Jul 1989jH  M#j:"N , Country of originCISp# ~ M#jF"H̀郉MissionRemote sensing (F2)^ ܇ A#R:"Perigee/Apogee178/214 kmV~ 2 A#R*Inclination82.6T܇  A#R&Period88.4 mina2  G#^4" &Launch vehicleSoyuzY @ A#R0Launch sitePlesetskR.  $ \Carried two Pion air density subsatellites5@ lj '  End of lifeU  A#R(Decay8 Aug 1989&lj B # 7 y '  O Subsatellites`B  $ PION 1 (20160 / 89055C) decayed on 19 Sep 1989PION 2 (20161 / 89055D) decayed on 19 Sep 19898y 5 ' "(Technical dataM  0 0:#@ⱺSpecificationsPayload; 5  1\Fi   Resurs F04G  5 :& " Resurs F041 5 '  Generalg   G#^@") Designation20175 / 89063A\5  A#R6Launch date15 Aug 1989j b M#j:"N , Country of originCISp# ҍ M#jF"H̀郉MissionRemote sensing (F2)^b 0 A#R:"Perigee/Apogee178/226 kmVҍ  A#R*Inclination82.3T0 ڎ A#R&Period88.5 min\ 6 G#^*" &Launch vehicleYڎ  A#R0Launch siteTyuratam&6  # 5  '  End of life   V b A#R*Decay14 Sep 1989&  # 8b  ' "(Technical dataM  0 0:#@ⱺSpecificationsPayload; H 1j\j H   Resurs F05G  5 :& " Resurs F051 H  '  Generalg ' G#^@") Designation20222 / 89073A[  A#R4Launch date6 Sep 1989j'  M#j:"N , Country of originCISp# \ M#jF"H̀郉MissionRemote sensing (F1)^  A#R:"Perigee/Apogee176/229 kmV\  A#R*Inclination82.3T d A#R&Period88.6 min\  G#^*" &Launch vehicleYd  A#R0Launch sitePlesetsk`  * $ Carried CAMEX (Carrier for Microgravity Experiment), a German experiment for Kayser Threde5  '  End of lifeV . A#R*Decay22 Sep 1989& T # 8.  ' "(Technical data<T  ) "&rԓSpecifications;  1 FUk  J % Resurs F06G J 5 :& " Resurs F061  { '  Generalg J  G#^@") Designation20632 / 90047A\{ > A#R6Launch date29 May 1990j  M#j:"N , Country of originCISp#>  M#jF"H̀郉MissionRemote sensing (F1)^ v A#R:"Perigee/Apogee175/231 kmV  A#R*Inclination82.4Tv  A#R&Period88.6 mina  G#^4" &Launch vehicleSoyuzY  A#R0Launch sitePlesetsk&  # 5 5 '  End of lifeV  A#R*Decay14 Jun 1990&5  # 8  ' "(Technical data< % ) "&rԓSpecifications; ` 1Wl `   Resurs F07G%  5 :& " Resurs F071 `  '  Generalg ? G#^@") Designation20687 / 90060A\  A#R6Launch date17 Jul 1990j?  M#j:"N , Country of originCISp# u M#jF"H̀郉MissionRemote sensing (F2)^  A#R:"Perigee/Apogee177/236 kmVu ) A#R*Inclination82.3T } A#R&Period88.6 min\)  G#^*" &Launch vehicleY} > A#R0 > % Launch sitePlesetsk& d # 5>  '  End of lifeVd  A#R*Decay16 Aug 1990&  # 8 M ' "(Technical dataM  0 0:#@ⱺSpecificationsPayload; M  1Um    Resurs F08G  5 :& " Resurs F081  M '  Generalg   G#^@") Designation20754 / 90073A\M  A#R6Launch date16 Aug 1990j z M#j:"N , Country of originCISp#  M#jF"H̀郉MissionRemote sensing (F1)^z H A#R:"Perigee/Apogee176/229 kmV  A#R*Inclination82.3TH  A#R&Period88.5 min\ N G#^*" &Launch vehicleY  A#R0Launch sitePlesetsk&N  # 5  '  End of lifeU W A#R(Decay1 Sep 1990& } # 8W  ' "(Technical data<}  ) "&rԓSpecifications;  , 1(W$n , s j Resurs F09G s 5 :& " Resurs F091 ,  '  Generalg s   G#^@") Designation20794 / 90082A[ f A#R4Launch date7 Sep 1990j   M#j:"N , Country of originCISp#f @ M#jF"H̀郉MissionRemote sensing (F1)^  A#R:"Perigee/Apogee177/238 kmV@  A#R*Inclination82.5T H A#R&Period88.7 mina  G#^4" &Launch vehicleSoyuzYH  A#R0Launch sitePlesetskC E $ >Carried a German experiment5 z '  End of lifeVE  A#R*Decay21 Sep 1990&z  # 8 . ' "(Technical data< j ) "&rԓSpecifications; .  1oo  A Resurs F10Gj  5 :& " Resurs F101  '  Generalg  G#^@") Designation21313 / 91035A\  A#R6Launch date21 May 1991j J M#j:"N , Country of originCISp#  M#jF"H̀郉MissionRemote sensing (F2)^J  A#R:"Perigee/Apogee178/242 kmV n A#R*Inclination82.3T  A#R&Period88.7 min\n *@ G#^*" & *@ j Launch vehicleY @ A#R0Launch sitePlesetsk&*@ @ # 5@ @ '  End of lifeV@ 4A A#R*Decay20 Jun 1991&@ ZA # 84A A ' "(Technical dataMZA A 0 0:#@ⱺSpecificationsPayload; A B 1$Ёp B aB HG Resurs F11GA aB 5 :& " Resurs F111 B B '  Generalg aB B G#^@") Designation21524 / 91044A\B UC A#R6Launch date28 Jun 1991jB C M#j:"N , Country of originCISp#UC /D M#jF"H̀郉MissionRemote sensing (F2)^C D A#R:"Perigee/Apogee253/268 kmV/D D A#R*Inclination82.3TD 7E A#R&Period89.7 min\D E G#^*" &Launch vehicleY7E E A#R0Launch sitePlesetsk&E F # 5E GF '  End of lifeVF F A#R*Decay21 Jul 1991&GF F # 8F F ' "(Technical dataMF HG 0 0:#@ⱺSpecificationsPayload; F G 1 o+q G G L Resurs F12GHG G 5 :& " Resurs F121 G G '  Generalg G bH G#^@") Designation21611 / 91052A\G H A#R6Launch date23 Jul 1991jbH (I M#j:"N , Country of originCISp#H I M#jF"H̀郉MissionRemote sensing (F1)^(I I A#R:"Perigee/Apogee178/230 kmVI LJ A#R*Inclination82.4TI J A#R&Period88.6 minaLJ K G#^4" &Launch vehicleSoyuzYJ ZK A#R0Launch sitePlesetsk&K K # 5ZK K '  End of lifeUK  L A#R(Decay8 Aug 1991&K 0L # 8 L hL ' "(Technical data<0L L ) "&rԓSpecifications; hL L 1*Ёr L &M  Resurs F13GL &M 5 :& " Resurs F131 L WM '  Generalg &M M G#^@") Designation21664 / 91058A\WM N A#R6Launch date21 Aug 1991jM N M#j:"N , Country of originCISp#N N M#jF"H̀郉MissionRemote sensing (F2)^N RO A#R:"Perigee/Apogee178/240 kmVN O A#R*Inclination82.3TRO  A#R&Period88.7 minO  L \O h G#^*" &Launch vehicleY  A#R0Launch sitePlesetsk&h  # 5  '  End of lifeV r A#R*Decay20 Sep 1991&  # 8r Ё ' "(Technical dataM  0 0:#@ⱺSpecificationsPayload; Ё X 1+s X   Resurs F14G  5 :& " Resurs F141 X Ђ '  Generalg 7 G#^@") Designation21951 / 92024A\Ђ  A#R6Launch date29 Apr 1992j7  M#j:"N , Country of originCISp# m M#jF"H̀郉MissionRemote sensing (F2)^ ˄ A#R:"Perigee/Apogee225/230 kmVm ! A#R*Inclination82.1T˄ u A#R&Period89.1 mina! օ G#^4" &Launch vehicleSoyuzYu / A#R0Launch sitePlesetsk&օ U # 5/  '  End of lifeVU  A#R*Decay29 May 1992&  # 8 > ' "(Technical dataM  0 0:#@ⱺSpecificationsPayload; > Ƈ 1 Et Ƈ   Resurs F15G  5 :& " Resurs F151 Ƈ > '  Generalg  G#^@") Designation21998 / 92033A\>  A#R6Launch date23 Jun 1992j k M#j:"N , Country of originCISp# ۉ M#jF"H̀郉MissionRemote sensing (F1)^k 9 A#R:"Perigee/Apogee177/226 kmVۉ  A#R*Inclination82.3T9  A#R&Period88.5 mina D G#^4" &Launch vehicleSoyuzY  A#R0Launch sitePlesetsk&D Ë # 5  '  End of lifeUË M A#R(Decay9 Jul 1992& s # 8M  ' "(Technical data<s  ) "&rԓSpecifications; " 1pu " i  Resurs F16G i 5 :& " Resurs F161 "  '  Generalg i  G#^@") Designation22093 / 92056A\ ] A#R6Launch date19 Aug 1992j ǎ M#j:"N , Country of originCISp#] 7 M#jF"H̀郉MissionRemote sensing (F2)^ǎ  A#R:"Perigee/Apogee178/226 kmV7  A#R*Inclination82.6   T ` A#R&Period88.6 min\  G#^*" &Launch vehicleY`  A#R0Launch sitePlesetsk  % )Two passive Pion crafts were released on 1st September. Tracking of their decay will allow studies of atmospheric density and radar calibration.5  '  End of lifeU X A#R(Decay4 Sep 1992& ~ # 7X  '  O Subsatellites`~ 9 $ PION 1 (22099 / 92056C) decayed on 25 Sep 1992PION 2 (22100 / 92056D) decayed on 24 Sep 19928 q ' "(Technical dataM9  0 0:#@ⱺSpecificationsPayload; q  1)E v @ 8 Resurs F17G @ 5 :& " Resurs F171 q '  Generalg @  G#^@") Designation22663 / 93033Ah'q @ A#RNLaunch date21 May 1993 at 09:20 UTj  M#j:"N , Country of originCISp#@  M#jF"H̀郉MissionRemote sensing (F2)^ x A#R:"Perigee/Apogee176/255 kmV  A#R*Inclination82.6Tx " A#R&Period88.8 mina  G#^4" &Launch vehicleSoyuzY"  A#R0Launch sitePlesetsk&  # 5 7 '  End of lifeV  A#R*Decay20 Jun 1993&7  # 8  ' "(Technical dataM 8 0 0:#@ⱺSpecificationsPayload; s 1qw s   Resurs F18G8  5 :& " Resurs F181 s  '  Generalg R G#^@") Designation22696 / 93040Ah'  A#RNLaunch date25 Jun 1993 at 08:20 UTjR $ M#j:"N , Country of originCISp#  M#jF"H̀郉MissionRemote sensing (F1)^$  A#R:"Perigee/Apogee173/240 kmV H A#R*Inclination82.6T  A#R&Period88.6 minaH  G#^4" &Launch vehicleSoyuzY V A#R0Launch sitePlesetsk& | # 5V  '  End of lifeV|  A#R*Decay12 Jul 1993& - # 8 e ' "(Technical data<-  ) "&rԓSpecifications; e  1? x # Resurs F19G # 5 :& " Resurs F191 T '  Generalg #  G#^@") Designation22777 / 93053Ah'T /A#RNLau / nch date24 Aug 1993 at 10:45 UTj M#j:"N , Country of originCISp#/ M#jF"H̀郉MissionRemote sensing (F1)^gA#R:"Perigee/Apogee174/236 kmV A#R*Inclination82.6TgA#R&Period88.6 minarG#^4" &Launch vehicleSoyuzYA#R0Launch sitePlesetsk&r# 5&'  End of lifeV|A#R*Decay10 Sep 1993&&# 8|' "(Technical data<) "&rԓSpecifications; Q1qy Qw Resurs F20G5 :& " Resurs F201 Q'  Generalg 0G#^@") Designation23672 / 95050Ah'A#RNLaunch date26 Sep 1995 at 11:20 UTj0M#j:"N , Country of originCISp#rM#jF"H̀郉MissionRemote sensing (F2)^A#R:"Perigee/Apogee231/233 kmVr&A#R*Inclination82.3RxA#R"Period89 minc&G#^8" &Launch vehicleSoyuz U`x;A#R>Launch sitePlesetsk LC43-4\A#R6"Mass at launch~6000 kgJ&;$ LWould be the last Resurs F mission5 '  End of life`v A#R>CauseNormal end of missionV  A#R*Decay26 Oct 1995&v  # 8 * ' "(Technical dataM w 0 0:#@ⱺSpecificationsPayload; *  1Ŝz  '@Resurs F21Gw  5 :& " Resurs F21< 5 # 2Also called Resurs F1M1 f '  Generalg 5  G#^@") Designation25059 / 97072A\f ) A#R6Launch date17 Nov 1997j  M#j:"N , Country of originCISr%)  M#jJ"H̀郉MissionRemote sensing (F1M?)^ c A#R:"Perigee/Apogee208/243 kmV  A#R*Inclination82.3L c A#RPeriodc hG#^8" &Launch vehicleSoyuz UYA#R0Launch sitePlesetskThA#R&"Mass at launch'@' It is unknown what type of satellite this is exactly, if it is a F1 or F2 or a new model.Might be equipped of 2 KFA-3000 cameras with 5 to 8 m resolution and a multispectral camera KATE-200 wi'@w th 10 to 12 m resolution.; b@1L{ b@@FResurs 500G'@@5 :& " Resurs 500\9b@A# rAlso called Zvezda Kolumba which means "Columbus Star"1 @6A'  Generalg AAG#^@") Designation22217 / 92075Ah'6ABA#RNLaunch date15 Nov 1992 at 21:50 UTjAoBM#j:"N , Country of originCISUBBG#^"H̀Mission^oB"CA#R:"Perigee/Apogee177/237 kmVBxCA#R*Inclination82.6T"CCA#R&Period88.6 minaxC-DG#^4" &Launch vehicleSoyuzYCDA#R0Launch sitePlesetskh-DF' Carries objects and messages. After a 6 day flight the capsule decayed in the Pacific. It was then moved to Seattle for thanksgiving Day. This mission is called Europe-America Space Flight 500. It celebrates the international space year, the 500th anniversary of the new world's discovery and must start a cooperation between US and Russia.Resurs F1 type5DJF'  End of lifeVFFA#R*Decay22 Nov 1992$JFF" < FG1y| GHGLResurs O1-3HFHG5 :( " Resurs O1-31 GyG'  Generalg HGGG#^@") Designation23342 / 94074Ag&yGGHA#RLLaunch date4 Nov 1994 at 05:46 UTjGHM#j:"N , Country of originCISkGHIM#j<"H̀郉MissionRemote sensing^HzIA#R:"Perigee/Apogee660/663 kmTIIA#R&Inclination98RzI JA#R"Cycle21 daysRIrJA#R"Period98 mini JJM#j8" &'CMLaunch vehicleZenityOrJTK* $ >PCarried Safir R1. The payload costed DM6 million (half financed by DARA)<JK' *O External resourcesY2TKK' dhttp://www.eurimage.it/Products/RESURS_O1.html8K!L' "(Technical datao=KL2 4z<ҏ,SpecificationsPayloadDownlink: 8.192 GHz, 7.68 mbps< !LL1̂} LMResurs O1-4HLM5 :( " Resurs O1-41 LEM'  GeneralYMMG#^$") Designation`EMMA#R>Launch dateplanned in 1998jMhNM#j:"N , Country of originCISkMNM#j<"H̀郉MissionRemote sensingZhN-OA#R2"Perigee/Apogee810 kmQN~OA#R InclinationL -OOA#RPeriodi~O?M#j8" O?L&'CMLaunch vehicleZenit&Oe# <?' *O External resourcesY2e' dhttp://www.eurimage.it/Products/RESURS_O1.html82' "(OTechnical dataS,' X MSU-SK (5-channel visible and IR scanner)U2A#R0Wavebands0.5-0.6 m, 0.6-0.7 m, 0.7-08 m, 0.8-1.0 m, 10.4-12.6 m + a 6th oneu4A#Rh0Resolution161 m (4 channels), 528 m (1 channel)WA#R,0Swath width714 kmX1?' b MSU-E (3-channel steerable push-broom scanner)s2A#Rd0Wavebands0.5-0.67 m, 0.65-0.8 m, 0.8-1.0 mT?A#R&0Resolution30 mV\A#R*0Swath width60 kmB$ <Downlink: 8.2 GHz, 16 mbps1\τ1W~ τ#IT+#) "VȠ$To view this page you need to register&τI# 6#1Lkk SRS 15> I2 4"  RS 15iI# Also called Radio-Rosto (Rosto is an acronyme for Russian Defense, Sports, and Technical Organization)1 z'  Generalg IG#^@") Designation23439 / 94085A\z=A#R6Launch date26 Dec 1994jM#j:"N , Country of originCISo"=M#jD"H̀㓉MissionTelecommunications`vA#R>"Perigee/Apogee1881/2163 kmV̈A#R*Inclination64.8SvA#R$Period128 minl̈M#j>" &mKLaunch vehicleRokot #1e#3 4N!w$xAll the electronics onboard the satellite was designed and built by a group of Radio Amateurs from the town of Kaluga (180 km SW of Moscow) under the leaderships of Aleksander Papkov. The work was coordinated and supervised by NILAKT POSTO (aero-cosmic laboratory), Moscow, under the direction of Valentin Yamnikov. Full control of RS 15 as well as RS 10/11 and RS 12/13 is implemented by the RS3A control station at Moscow (headed by Leonid Maksakov).RS-15 suffered from power supply problems, as it goes off almost immediately upon entering earth eclipse, not to return until is 'sees' sunlight again.1 T' O Contactz#. ,RS3APO Box 59, Moscow 105122, RussiaFax: +7-095-916-2949Email: rsgroup@olymp.msk.suPacket: RS3A @ RS3A.MSK.RUS.EU8T4' "(OTechnical data8l' " SpecificationsV4A#R*&Prime contractorm,l/A#RXPlatformsimilar to RS 3 to 8 satellitesYA#R0"Mass at launch70 kgS/ێA#R$ Mass in orbitb!=A#RBDiameter1 m (spherical-like)QێA#R Solar arrayW= A#R, Stabilizationnone IN ZA#RDC powerU A#R($Design lifetimeZ5Z % kOn board the satellite, there is a Mode A transponder and two CW beacons, one of which consists of a broadcast bulletin board with 2 kilobytes of storage space. A remote control system and telemetry system also exist on the satellite. RS 15 does not have not orientation or attitude stabilization systems.6?'  Transponders? B#T~Beacons29.3525 MHz (0.4 - 1.2 W)29.3987 MHz (0.4 - 1.2 W)F?A#R v5|A#RjUplink145.858 - 145.898 MHz (approx. 100 W EIRP)FA#R m,|/A#RXDownlink29.354 - 29.394 MHz (up to 5 W)$S" A/1rWc "Program: SputnikMS5 :2/Z" Program: SputnikA"# <Soviet experimental program1S1< S^ "^s 1xZU~~~~~~~~~~Program: SputnikSputnik 01Sputnik 02Sputnik 03Sputnik 04Sputnik 05Sputnik 06Sputnik 07Sputnik 09Sputnik 10Sputnik 40; S1:   Sputnik 01G^5 :&/Z" Sputnik 016# &Also called PS 11 G'  Generalg G#^@") Designation00002 / 57001B[G A#R4Launch date4 Oct 1957jsM#j:"N , Country of originCISy, M#jX"H̀?vMissionScientific: ionosphere study^sJA#R:"Perigee/Apogee227/945 kmTA#R&Inclination65TJA#R&Period96.1 minz-lM#jZ" &゜PLaunch vehicleSemiorka (R7) (8K71PS)YA#R0Launch siteTyurataml' First satellite ever launchedSphere 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.5'  End of lifeU;A#R(Decay3 Jan 19588s' "(OTechnical data8;' " SpecificationsVsA#R*&Prime contractorN OA#RPlatform[A#R4"Mass at launch83.6 kgSOA#R$ Mass in orbit]ZA#R8Dimension58 cm diameterQA#R Solar arraySZA#R$ StabilizationN LA#RDC powerUA#R($Design lifetimeH$L $ HFrequencies: 20.005 & 40.002 MHz ^; G1  Gl Sputnik 02G 5 :&/Z" Sputnik 021 G'  Generalg &G#^@") Designation00003 / 57002A[A#R4Launch date3 Nov 1957j&M#j:"N , Country of originCISx+cM#jV"H̀jMissionScientific: Sun observation_A#R<"Perigee/Apogee225/1670 kmVcA#R*Inclination65.3UmA#R(Period103.7 minq$M#jH" &゜PLaunch vehicleSemiorka (R7)Ym7A#R0Launch siteTyuratam\A#R6"Mass at launch508.3 kg7]% K1.2 m high cone that carried Laika (a dog) the first living creature in Space. Also studied X-rays and UV radiations from the Sun. The dog died after a few days.5'  End of lifeV]A#R*Decay14 Apr 19588 ' "(OTechnical data8X' " SpecificationsV A#R*&Prime contractorN XA#RPlatformZVA#R2"Mass at launch508 kgSA#R$ Mass in orbitOVA#RDimensionQIA#R Solar arraySA#R$ StabilizationN IA#RDC powerU? A#R($Design lifetime-l ) Frequencies: 20.005 & 40.002 MHz (Tral-D TM system)The satellite also featured a slow-scan TV camera (100 lines per frame, 10 frames per second), which relayed images to the ground.There was also a spectrophotometer for UV (1216 A) and Soft-X-rays (1-120 A) using a photomultiplier tube and a filterwheel. This instrument sent data through a commutated telemetry channel. The instrument was designed by the St. Peterburg physicist A. Jefremov under the direction of Academicians A. Lebedev and S. Mandelstam.; ?  1'  @Sputnik 03Gl  5 :&/Z" Sputnik 031  '  Generalg  G#^@") Designation00008 / 58004B\  A#R6Launch date15 May 1958j L M#j:"N , Country of originCISy,  M#jX"H̀?vMissionScientific: ionosphere study`L %A#R>"Perigee/Apogee217/1.864 kmV {A#R*Inclination65.2S%A#R$Period106 minq${?M#jH" &゜PLaunch vehicleSemiorka (R7)YA#R0Launch siteTyuratamm,?@A#RX"Mass at launch1327 kg (payload: 970 @l kg)&7@# 5@l@'  End of lifeU7@@A#R(Decay6 Apr 1960$l@@" ; @ A1 AgAESputnik 04G@gA5 :&/Z" Sputnik 041 AA'  Generalg gAAG#^@") Designation00034 / 60005A\A[BA#R6Launch date15 May 1960jABM#j:"N , Country of originCISU[BCG#^"H̀Mission^BxCA#R:"Perigee/Apogee284/514 kmTCCA#R&Inclination65TxC DA#R&Period92.5 minlCDM#j>" &゜PLaunch vehicleVostok LY DDA#R0Launch siteTyuratam&D E# 5D@E'  End of lifeU EEA#R(Decay5 Sep 1962$@EE" ; EE1v. E;FJSputnik 05GE;F5 :&/Z" Sputnik 051 ElF'  Generalg ;FFG#^@") Designation00055 / 60011A\lF/GA#R6Launch date19 Aug 1960jFGM#j:"N , Country of originCISU/GGG#^"H̀Mission^GLHA#R:"Perigee/Apogee281/340 kmVGHA#R*Inclination64.6TLHHA#R&Period90.7 min\HRIG#^*" &Launch vehicleYHIA#R0Launch siteTyuratam&RII# 5IJ'  End of lifeVI\JA#R*Decay20 Aug 1960$JJ" ; \JJ1r. JKCOSputnik 06GJK5 :&/Z" Sputnik 061 J3K'  Generalg KKG#^@") Designation00065 / 60017A[3KKA#R4Launch date1 Dec 1960jK_LM#j:"N , Country of originCISUKLG#^"H̀Mission^_LMA#R:"Perigee/Apogee123/269 kmTLfMA#R&Inclination65TMMA#R&Period88.4 min\fMNG#^*" &Launch vehicleYMoNA#R0Launch siteTyuratam&NN# 5oNN'  End of lifeUNOA#R(Decay2 Dec 1960$NCO" ; O~O1uh_ ~OOSputnik 07GCOO5 :&/Z" Sputnik 071 ~O '  GeneralO COg OsG#^@") Designation00071 / 61002A[ ΀A#R4Launch date4 Feb 1961js8M#j:"N , Country of originCISU΀G#^"H̀Mission^8A#R:"Perigee/Apogee212/318 kmVAA#R*Inclination64.9TA#R&Period89.8 min\AG#^*" &Launch vehicleYJA#R0Launch siteTyuratam&p# 5J'  End of lifeVpA#R*Decay26 Feb 1960$" ; Z1'K ZSputnik 09G5 :&/Z" Sputnik 091 Z҄'  Generalg 9G#^@") Designation00091 / 61008A[҄A#R4Launch date9 Mar 1961j9M#j:"N , Country of originCISUSG#^"H̀Mission^A#R:"Perigee/Apogee173/239 kmVSA#R*Inclination64.9T[A#R&Period88.6 min\G#^*" &Launch vehicleY[A#R0Launch siteTyuratam;K$ .Vostok 1 repetition5'  End of lifeUKՈA#R(Decay9 Mar 1961$" ; Ո41Kh 4{ՍSputnik 10G{5 :&/Z" Sputnik 101 4'  Generalg {G#^@") Designation00095 / 61009A\oA#R6Launch date25 Mar 1961jيM#j:"N , Country of originCISUo.G#^"H̀Mission^يA#R:"Perigee/Apogee175/175 kmV.A#R*Inclination64.9T6A#R&Period88.6 min\G#^*" &Launch vehicleY6A#R0Launch siteTyuratam;&$ .Vostok 1 repetition5['  End of lifeV&A#R*Decay25 Mar 1961$[Ս" ; 1 WSputnik 40GՍW5 :&/Z" Sputnik 40M*# TAlso called PS 2 or Sputnik Jr or RS 171 WՎ'  Generalg <G#^@") Designation24958 / 97058Cg&ՎA#RLLaunch date3 Nov 1997 at 04:05 UTj<M#j:"N , Country of oriՍginCISUnG#^"H̀Mission^A#R:"Perigee/Apogee383/391 kmVn"A#R*Inclination51.6L nA#RPeriod`"G#^2" &Launch vehiclenoneb!n0A#RBLaunch siteMir space stationY,- (Y~1/3 model of Sputnik 01 The model was built by high school students in the republic of Kabardin-Balakarsk in the Russian Federation, in the Caucasus near Chechnya. The radio transmitter payload was built by students on Reunion, a French territory in the Indian Ocean. Frequency: 145.820 MHz50'  End of life_A#R<"Out of service29 Dec 1997_|A#R<Causestopped transmittingK A#RDecay&|# 8%1 %]Start 18 ], (" Start 11 %'  Generalg ]G#^@") Designation22561 / 93014A\QA#R6Launch date25 Mar 1993jM#j:"N , Country of originCISYQG#^$"H̀MissionTest^rA#R:"Perigee/Apogee680/968 kmVA#R*Inclination75.8UrA#R(Period101.4 minlM#j>" &aKLaunch vehicleStart #1$" D1  AProgram: StatsionarPA5 :8cD" Program: Statsionar7 `1.  `Statsionar-01J"5 :,cD" Statsionar-01@`- *&/ۀ Location: 75Ewa^#2 BeginEndSatellite p#>"$5oމ22 Dec 1975Raduga 01a "s aj# $ " > 15,  +/Statsionar-02J+5 :,cD" Statsionar-02@k- *&/ۀ Location: 35Ew+^#2 BeginEndSatellitekqp#>"$5oމ11 Sep 1976Raduga 02p#>"$5oމ23 Jul 1977Raduga 03qp#>"$5oމ18 Jul 1978Raduga 04p#>"$5oމ20 Feb 1980Raduga 06p#>"$5oމ18 Mar 1981Raduga 08;p#< "=4oމ9 Oct 1981Raduga 10p#>"$44oމ26 Nov 1982Raduga 11;Yp#>"$74oމ15 Feb 1984Raduga 14p#>"$:4oމ15 Nov 1985Raduga 17 Yxp#@$&`4oމ20 Oct 1988?Raduga 22  s#@""$f4oމ19 Dec 1991Raduga 28$x/" > m1   mj Statsionar-03J/5 :,cD" Statsionar-03@m- *&/ۀ Location: 85Ewn ^#2 BeginEndSatellite p#>"$5oމ25 Apr 1979Raduga 05n  p#< "54oމ8 Apr 1983Raduga 12  p#>"$h4oމ19 Mar 1987Raduga 20)  p#R68d4oމ20 Dec 1990< Feb 1995Raduga 26  F s#@""$4oމ30 Sep 1993Raduga 30$ j " > F  1V    <@Statsionar-04c.j  5 :^cD" Statsionar-04 / Loutch-02 / Express-02@ K - *&/ۀ Location: 14Ww  ^#2 BeginEndSatellite!K Sp#B"$%o14 Jun 1980Gorizont 04! p#B"$#o30 Mar 1988Gorizont 15"Sys#D""$#o20 Jun 1990Gorizont 20 @s#@""$J713 Oct 1994Ey@j xpress 1$y<@" > @z@1 b  z@@GFStatsionar-05W"<@@5 :FcD" Statsionar-05 / Express-05@z@A- *&/ۀ Location: 53Ew@A^#2 BeginEndSatellite!ABp#B"$$o19 Dec 1978Gorizont 01 ABp#@ "%o6 Jul 1979Gorizont 02!B:Cp#B"$%o28 Dec 1979Gorizont 03"BCs#D""$%o22 Apr 1984Gorizont 09!:C`Dp#B"$|#o18 Jan 1985Gorizont 11)CDs#R0"2#o26 Jan 1989? movedGorizont 17"`DEs#D""$#o22 Nov 1992Gorizont 27D#Fs#>"#oJul 1996Gorizont 32$EGF" > #FF1_ F  FFJStatsionar-06c.GFF5 :^cD" Statsionar-06 / Loutch-03 / Express-07@F(G- *&/ۀ Location: 90EwFG^#2 BeginEndSatellite"(G4Hs#D""$%o30 Nov 1983Gorizont 08"GHs#D""$~#o18 Nov 1986Gorizont 13!4H]Is#B ""#o3 Nov 1990Gorizont 21"HIs#D""$#o28 Oct 1993Gorizont 28$]IJ" > ITJ1b   TJJTMStatsionar-07c.JJ5 :^cD" Statsionar-07 / Loutch-04 / Express-10ATJJ- *(/ۀ Location: 140EwJoK^#2 BeginEndSatellite"JLs#D""$#o11 May 1987Gorizont 14!oKLs#B ""#o6 Jul 1989Gorizont 18%L0Ms#J$("*#omid-April 1996Gorizont 22$LTM" > 0MM1F ! MMwStatsionar-08JTMM5 :,cD" Statsionar-08@MN- *&/ۀ Location: 25WwMN^#2 BeginEndSatelliteN!Op#< "5oމ5 Oct 1980Raduga 07NOp#>"$;4oމ17 Jan 1986Raduga 18'!OSp#NOSTM24a4oމ14 Apr 1989Jul 1995Raduga 23$Ow" > S1 ! Statsionar-09Jw5 :,cD" Statsionar-09@?- *&/ۀ Location: 45Ew^#2 BeginEndSatellite?Ep#>"$64oމ25 Aug 1983Raduga 13ӂp#< "94oމ8 Aug 1985Raduga 16 Ecp#@$&b4oމ15 Dec 1989?Raduga 24(ӂs#P2"44oމ18 Feb 1994Jul 1995Raduga 31cs#:"a4oމSep 1995Raduga 23$" > 1!! :Statsionar-10J:5 :,cD" Statsionar-10A{- *(/ۀ Location: 170Ww:^#2 BeginEndSatellite!{p#B"$%o20 Oct 1982Gorizont 06p#>"$<4oމ25 Oct 1986Raduga 19p#* _4oމ?Raduga 21$" > 1.!!! \YStatsionar-11c.\5 :^cD" Statsionar-11 / Loutch-06 / Express-03@- *&/ۀ Location: 11Ww\^#2 BeginEndSatellite!p#B"$%o30 Jun 1983Gorizont 07!5p#B"$#o15 Jul 1992Gorizont 26$Y" > 51!! Statsionar-12c.Y5 :^cD" Statsionar-12 / Loutch-07 / Express-04@:- *&/ۀ Location: 40Ew^#2 BeginEndSatellite!:Bp#B"$}#o10 Jun 1986Gorizont 12!ӌp#B"$#o23 Nov 1990Gorizont 22Bes#>"#oFeb 1996Gorizont 31$ӌ" > eǍ1!!C! Ǎ*VStatsionar-13c.*5 :^cD" Statsionar-13 / Loutch-08 / Express-06@Ǎj- *&/ۀ Location: 80Ew*^#2 BeginEndSatellite jqp#@ "#o1 Aug 1984Gorizont 10!p#B"$#o18 Aug 1988Gorizont 16q!qp#B"$#o23 Oct 1991Gorizont 24 2s#@""$J726 Sep 1996Express 2$V" > 21!! Statsionar-14c.V5 :^cD" Statsionar-14 / Loutch-09 / Express-08B9- **/ۀ Location: 96.5Ew^#2 BeginEndSatellite!9Ap#B"$%o15 Mar 1982Gorizont 05!p#B"$#o28 Sep 1989Gorizont 19Ads#>"#oAug 1996Gorizont 27$" > d1C!! Statsionar-15J5 :,cD" Statsionar-15AQ- *(/ۀ Location: 128Ew^#2 BeginEndSatelliteQWp#>"$84oމ22 Jun 1984Raduga 15&p#L02_4oމ10 Dec 1987? movedRaduga 21 Ws#@""$e4oމ28 Feb 1991Raduga 27$" > 1!*! EStatsionar-16c.E5 :^cD" Statsionar-16 / Loutch-10 / Express-11A- *(/ۀ Location: 145EwE^#2 BeginEndSatellitep#, #oGorizont 21s j# $" > X1!! XeStatsionar-17J5 :,cD" Statsionar-17BX- **/ۀ Location: 26.5Ww[^#2 BeginEndSatellites j# s [Aj# $e" > A1*!ׂ! Statsionar-18Je5 :,cD" Statsionar-18?,- *$/ۀ Location: 8Ew^#2 BeginEndSatellites ,j# s j# $" > 1!" 5Statsionar-19J55 :,cD" Statsionar-19@u- *&/ۀ Location: 23Ew5 ^#2 BeginEndSatelliteu s uj# s j# $" > T1ׂ!" T/Statsionar-20J5 :,cD" Statsionar-20@T- *&/ۀ Location: 70EwU^#2 BeginEndSatellite!s#B""$ƭ\21 Jun 1989Raduga 1-1Uxp#>"$c4oމ15 Feb 1990Raduga 25  s#@""$4oމ28 Dec 1994Raduga 32$x/" > m1-"V" mStatsionar-21c./5 :^cD" Statsionar-21 / Loutch-05 / Express-09Am- *(/ۀ Location: 103Ew^#2 BeginEndSatellite p#@ "#o2 Jul 1991Gorizont 23 p#@ "#o2 Apr 1992Gorizont 25$" >  1"" T Statsionar-22JT5 :,cD" Statsionar-22? - *$/ۀ Location: 1EwT ^#2 BeginEndSatellites }j# s j# $} " > R 1V"" R  ] Statsionar-23J  5 :,cD" Statsionar-23@R  - *&/ۀ Location: 15Ew S ^#2 BeginEndSatellites  j# s S 9 j# $ ] " > 9  1""  sStatsionar-24J]  5 :,cD" Statsionar-24@ % - *&/ۀ Location: 49Ew  ^#2 BeginEndSatellite % , p#@$&b4oމ22 Jun 1989?Raduga 24  p#@"$ƭ\27 Dec 1990Raduga 1-2 , Os#@ ""ƭ\5 Feb 1994Raduga 1-3$ s" > O1" " @Statsionar-25W"s5 :FcD" Statsionar-25 / Express-01BJ- **/ۀ Location: 37.5Ww^#2 BeginEndSatellites J@@j#@@s s @j# $@@@" > @A1"o" AlA.CStatsionar-26W"@lA5 :FcD" Statsionar-26 / Express-12AAA- *(/ۀ Location: 155WwlA$B^#2 BeginEndSatellites ABj# s $B Cj# $B.C" > ClC1  " lCCEStatsionar-27J.CC5 :,cD" Statsionar-27@lCC- *&/ۀ Location: 12EwCmD^#2 BeginEndSatelliteCDp#* `4oމ?Raduga 22mDEp#>"$g4oމ25 Mar 1993Raduga 29$DE" AEE1]'c/ E'F=Program: TselinaAE'F, (," Program: Tselina{XEF# Russian SIGINT program started in October 1967. It is composed of several generations8'FF' " 1st generationFG)  From 1967 to march 1982 40 satellites of the first generation were launched from Plesetsk onboard Cosmos rockets. The network was composed of 4 satellites on 45 distant planes.Specifications overview:VF(HA#R*&Prime contractorN GvHA#RPlatformP(HHA#RMass900 kgf%vH,IA#RJDimension2 m high x 1 m diametern-HIA#RZ"Perigee/Apogeecircular orbit, 500-550 kmT,IIA#R&Inclination74i(IWJA#RP Orbital cycle15 revolutions = 1 dayUIJA#R($Design lifetime7WJJ'   Satellites:OJK#ڀ6PjCosmos 0189Cosmos 0200Cosmos 0250Cosmos 0269Cosmos 0315Cosmos 0330OJL#ڀ6PjCosmos 0358Cosmos 0387Cosmos 0395Cosmos 0425Cosmos 0436Cosmos 0437QKgM#怢6TnCosmos 0460Cosmos 0479Cosmos 0500Cosmos 0536Cosmos 0544Cosmos 0549OL;N#ڀ6PjCosmos 0582Cosmos 0610Cosmos 0631Cosmos 0655Cosmos 0661Cosmos 0698OgMO#ڀ6PjCosmos 0707Cosmos 0749Cosmos 0781Cosmos 0787Cosmos 0790Cosmos 0812O;N #ڀ6PjCosmos 0845Cosmos 0870Cosmos 0899Cosmos 0924Cosmos 0960Cosmos 1008O E9Oʀ#ڀr6PjnCosmos 1062Cosmos 1114Cosmos 1215Cosmos 1345& # 8ʀ(' " 2nd generation0)  From Dec 1970 to Feb 1983 35 second generation satellites were launched from Plesetsk by Vostok vehicles. When operational the network was composed of 6 satellites orbiting in 60 apart planes.Specifications overview:V(A#R*&Prime contractorN 0ԂA#RPlatformQ%A#R Mass2500 kgh'ԂA#RNDimension5 m high x 1.5 m diameterd#%A#RF"Perigee/Apogeecircular, 650 kmVGA#R*Inclination81.2SA#R$ Orbital cycleUGA#R($Design lifetimec{) " Rainer Kracht reports a standard magnitude of 5.44 +/- 0.02 for those satellites.Satellites:OO#ڀ6PjCosmos 0389Cosmos 0405Cosmos 0476Cosmos 0542Cosmos 0604Cosmos 0673O{##ڀ6PjCosmos 0744Cosmos 0756Cosmos 0808Cosmos 0851Cosmos 0895Cosmos 0925OO#ڀ6PjCosmos 0955Cosmos 0975Cosmos 1005Cosmos 1043Cosmos 1063Cosmos 1077O#ˈ#ڀ6PjCosmos 1093Cosmos 1116Cosmos 1143Cosmos 1145Cosmos 1154Cosmos 1184O#ڀ6PjCosmos 1206Cosmos 1222Cosmos 1242Cosmos 1271Cosmos 1315Cosmos 1340Dˈh#ڀ6PjCosmos 1346Cosmos 1356Cosmos 1400Cosmos 1437Cosmos 1441&# DhҊ' : 3rd generation - Tselina D/ ,ቂ From Jun 1983 to Apr 1993 37 satellites of the third generation were launched by Cyclone 3 rockets from Plesetsk. When operational the network was composed of 6 satellites orbiting in 60 apart planes.Specifications overview:VҊ@A#R*&Prime contractorN A#RPlatformQ@ߌA#R Mass2200 kgh'GA#RNDimension5 m high x 1.5 m diameter^ߌA#R:"Perigee/Apogee635/665 kmVGA#R*Inclination82.5j)eA#RR Orbital cycle44 revolutions = 3 daysUA#R($Design lifetimee* " Those satellites are also known as Tselina-D or Ferret D. They could have a beacon at 51.140 and 51.160 MHz. Rainer Kracht reports a standard magnitude of 5.21 +/- 0.04 for those satellites.Satellites:O#ڀE6PjCosmos 1025Cosmos 1300Cosmos 1328Cosmos 1378Cosmos 1408Cosmos 1455Oh#ڀ6PjCosmos 1470Cosmos 1515Cosmos 1536Cosmos 1544Cosmos 1606Cosmos 1626O<#ڀ6PjCosmos 1633Cosmos 1666Cosmos 1674Cosmos 1703Cosmos 1707Cosmos 1726Oh#ڀ6PjCosmos 1733Cosmos 1743Cosmos 1758Cosmos 1782Cosmos 1805Cosmos 1812Q<#怢6Pj(wCosmos 1825Cosmos 1842Cosmos 1862Cosmos 1892Cosmos 1908Cosmos 1933U#(w:/fxXr+xCosmos 1953Cosmos 1975Cosmos 2058Cosmos 2151Cosmos 2221Cosmos 2228}#4"6,x $(,0Cosmos 2242&# D}' :O 4th generation - Tselina 2`1G/ ,c㉓g In 1983 a new generation was started named Tselina 2. Those heavy satellites are launched by Zenit 2 vehicles except the 2 first satellites launched on Proton. The satellites are placed on 4 planes spaced 45 apart. The system went operational with Cosmos 2227 in Dec 1992.Specifications overview:b!A#RB&Prime contractorNPO YuzhnoyeN GA#RPlatformRIA#R"Mass~9000 kgOA#RDimensionZIA#R2"Perigee/Apogee850 kmTFA#R&Inclination71SA#R$ Orbital cycle\FA#R6$Design lifetime3 yearsqHf) " Telemetry for those satellites could be around 166 MHzSatellites:O:#ڀ6PjCosmos 1603Cosmos 1656Cosmos 1697Cosmos 1714Cosmos 1833Cosmos 1844Uf&#(w:T+xr,xCosmos 1943Cosmos 1980Cosmos 2082Cosmos 2219Cosmos 2227Cosmos 2237N:#",x ,x>-x\3xzE3xCosmos 2263Cosmos 2278Cosmos 2297Cosmos 2322Cosmos 2333&&=# 1n1W nT+=) "VȠ$To view this page you need to register&n# A)11/ )vC Program: TsikadaMv5 :2⌖" Program: Tsikada)X ~} q.<:.<:qqiq2xMeans cicadaRussian navigation program operational since April 1979 (deployment started in late-1976). The satellites composing this system based on the Tsikada bus. This bus carries the Tsikada navigation transponders and optional secondary payloads, e.g. RS, etc. The Cospas (Nadezhda) package ivs carried as this secondary payload on some satellites. Lately the satellites are known as Nadezhda when they carry a Cospas receiver or part of Cosmos. A new generation is known as Kurs or Nadezhda M has just started and the satellites are in the Cosmos program (since it is still experimental). This generation is an new implementation of some equipment which can switch (on ground command) between two modes. The standard mode is Cospas for search and rescue. The other mode is the Kurs geolocation/data store-forward mode. The first use of this hardware was on Cosmos 2315. It was designed by Moscow's space instrumentation institute.lv.* $,xThe system is based on 4 planes separated by 45 covering space in order to complete the Parus system.Bp' 6 Occupation of the planes0.x#`  0 H Plane 11Plane 12Plane 13Plane 148pu#p8u0wVCosmos 0883Cosmos 0926Cosmos 1000Cosmos 10925]c#j6PCosmos 1168Cosmos 1304Cosmos 1226Cosmos 13395c#j6PCosmos 1383Cosmos 1506Cosmos 1447Cosmos 15745]c#j6PCosmos 1553Cosmos 1727Cosmos 1655Cosmos 1816:<u#tN!w:$xXS򲟉Cosmos 1791Cosmos 1861Cosmos 2123Nadezhda 28{#ƀp"R򲟀T򲟉:eL͉TU򲟉Nadezhda 1Nadezhda 3Tsikada 1Nadezhda 4w<fc#( $Cosmos 2181o#0(,x"(,Cosmos 2230fl i#,"2x $(Cosmos 2315C , &W㼨ԟNote: Cosmos 1380 failed to replace Cosmos 1168 in 1982 (placed on a wrong orbit)The satellites of this program are based on the Musson bus (see Parus for details).1l t 1W t   T+C  ) "VȠ$To view this page you need to register&t  # 1  1  t U" t 3 6D eL̀Program: TsikadaTsikada 11  1W   T+t  ) "VȠ$To view this page you need to register&  # : Y 1z Y  @Tsikada 1F  5 :$⌖" Tsikada 11 Y  '  Generalg 7 G#^@") Designation23463 / 95002Ah'  A#RNLaunch date24 Jan 1995 at 03:54 UTj7  M#j:"N , Country of originCISg pM#j4"H̀シMissionNavigation_ A#R<"Perigee/Apogee965/1020 kmVp%A#R*Inclination82.9L qA#RPeriodl%M#j>" &s,梉Launch vehicleCosmos CYqB@A#R0B@ Launch sitePlesetsk&h@# 8B@@' "(OTechnical dataS/h@@$ ^Downlink frequencies: 150 & 400 MHzPlane 131@$A1] $AxAAT+@xA) "VȠ$To view this page you need to register,$AA&  @xAA12uz( ABLaunch vehiclesLA0B5 :0NJ" Launch vehiclesU+AB* $V 㭄؉Section directed by Jean-Jacques Serra&0BB# /BC#2^'  2! #0bnW"D㰭=HVZA:ArianeASLVAthenaAtlas!BQD#B' " Xى,26:>B:Black Arrow<CDE#>x' " ቀ"$x@r,梉Xs,梉ptC:CycloneConestogaCosmos BCosmos C$QDF#&H' " p㉀" À8<@DD:DeltaDiamantDEF#6'  J"&*.2H:H1 & H22FG#&d' " "0#TX\`I:ISAS vehiclesISRO vehiclesFgH#<'  9+S,048L:Long MarchG$I#0' " $(,M:Mu/gHJ#2^' " J($JLPVZN:N1 & N2NASDA vehicles)$IJ#&R'  GKT"㉓g6#FJNP:PegasusProtonPSLVJK#6' " mK &*.2R:Rokot'IJL#' " g'K( ゜P(<<}(T#(jaK(K\S:ScoutSemiorkaShavitSLV 3StartSTS+KM#>V' " 㻦ʼn("+"6ELJNRT:TaurusThorTitan%LwN#2J' " kQR(&\8<BFV:VanguardVLSM7O#6' " 'CM $(.2Z:Zenit&wN]O# G 7OO' @ World Launch Vehicle OverviewR]O#\\6OA`VehicleFirst launchLEO capacity (kg)GTO capacity (kg)Comments O6#\\ A#\\( 248<@(BCIS (Sheldon / DoD)Detailed soviet chart hereA6#\\"゜P.0HTXZSemiorka (A / SL1)4 Oct 195713002-stage (--> 1958)EÃ#\\"゜P(*X\`bLuna (A1 / SL2)(Aug 1958)2 Jan 19593-stage (--> 1960)6#l\\"゜P,.HTXZVostok (A1 / SL3)15 May 196047003-stage jÃ#\\"゜P02fj(jQvl?Molniya (A2e / SL6)(10 Oct 1960)4 Feb 19611600 (THEO)4-stage, Molniya or Prognoz orbitPv#\\"r,梀02LVZ\Cosmos B (B1 / SL7)16 Mar 19624502-stage (--> 1977), 144 launches7?#n\\"゜P.0JVZ\Voskhod (A2 / SL4)16 Nov 196355003-stage4v#h\\(*DPTVCosmos (C1 / SL8)18 Aug 196414002-stageA?҈#\\"㉓g*,FTXZProton (D / SL9)16 Jul 1965125002-stage (--> 1968)=#z\\,.HLPRCosmos (F1r / SL11)17 Sep 19662-stage (--> 1971)5҈b#j\\"゜P*,FRVXSoyuz (A2 / SL4)28 Nov 196675003-stage>2#|\\"㉓g02LPhjProton (D1e / SL12)10 Mar 19674600 (GEO)4-stage6b#l\\,.HTXZCosmos (F1m / SL11)27 Oct 196740002-stage>2#|\\"$BFJLN1 (G / SL15?)(21 Feb 1969)Lunar vehicle launcher8#p\\"㉓g.0JX\^Proton (D1 / SL13)16 Nov 1968200003-stage:T#t\\"46P\`bCyclone 3 (F2 / SL14)24 Jun 197755003-stage7#n\\"'CM,.HVZ\Zenit (J1 / SL16)21 Jun 1985150002-stageYT#耲\\,.HXrtEnergia (K1 / SL17)15 May 198714000018000 (GEO)shuttle, 2 successful flightsA)#R\\"aK0:>@Start25 Mar 19935005-stage2#d\\"mK0<@BRokot26 Dec 199418503-stage (RS18K)4#6\\ $02Sea Launch5400 #\\ 4#:\\(㹌ל&(,046United StatesXj#\\"kQRNVZ\Vanguard(6 Dec1957)17 Mar 1958253-stage (--> 1959), 3 successful flights2(#d\\.6:<Juno 131 Jan 1958404-stage (--> 1959)Lj#\\"=vT^bdThor Able(17 Aug 1958)11 Oct 19582003-stage (--> Thor Delta)1(#b\\,48:Juno 26 Dec 1958504-stage (--> 1961)3#f\\"0<@BAtlas18 Dec 19581300Mercury launcher?Z#~\\"#* :FJLThor Agena28 Feb 195910002-stage (--> LTT Agena)8$#p\\"㰭=H >BFHAtlas Able(26 Nov 1959)3-stage (--> 1960)IZ#\\"mO{ "XdhjAtlas Agena(26 Feb 1960)24 May 196023002-stage (--> 1978)9$#r\\"Gi4$&@DHJThor Ablestar13 Apr 19602-stage (--> 1965)F#\\"p VZ^`Thor Delta(13 May 1960)18 Aug 19603-stage, (--> Delta)>u#|\\"g'KJNRTScout(4 Dec 1960)16 Feb 19614-stage (--> 1994)QY#\\"yj$&ZfrtAtlas Centaur(8 May 1962)16 Feb 1961560022504-stage (--> Atlas 2)8u#p\\2>BDSaturn 129 Jan 196468002/3-stage (--> 1965)4Y#h\\"^]4@DFTitan 208 Apr 19643500Gemini launcherB#\\"^]RVZ\Titan 3A(01 Sep 1964)10 Dec 19643-stage (--> 1965)N#\\$㏸A^]8FRTTitan 3C18 Jun 19651130045003-stage + boosters (--> Titan 34D)5#j\\4BFHSaturn 1B05 Jul 196612900Apollo launcherG_#\\$^]6BZ\Titan 3B29 Jul 19663500700 (THEO)3-stage (--> Titan 34B);3#v\\$#* "<HLNLTTAT Agena09 Aug 196620002-stage (--> 1972)<_#x\\2BFHSaturn 509 Nov 1967140000Lunar vehicle launcherI3#\\$^]6DHJTitan 3D15 Jun 1971130003-stage + boosters (--> Titan 34D)E#\\$p :FPRDelta 29xx09 Nov 197220007202/3-stage (--> Delta 39xx)?#~\\$p :>JLDelta 39xx13 Dec 197512502/3 stage (--> Delta 2)C#&\\"K\㥜2@ Titan 4)=7 #z\\"p"$>JVXDelta-2 69xx14 Feb 198940001400Interim Delta 2>h #|\\"^]4BNPTitan 414 Jun 19891770055002/3-stage + boosters67  #l\\"GKT2<@BPegasus5 Apr 1990400air launched rocket.  #\\\"p"$>JVXDelta-2 79xx26 Nov 199050001610/ P #^\\"yj2>JLAtlas 27 Dec 1991640027002-stage1  #b\\"yj6BNPAtlas 2A10 Jun 1992680029002-stage=P  #z\\"yj8DPRAtlas 2AS16 Dec 1993840036002-stage + boosters+ #V\\"㻦ŀ2>BDTaurus13 Mar 199414004-stage< m#x\\"GKT >HLNPegasus XL(27 Jun 1994)455air launched rocket/:@#^\\"bnW":FJLm:@AAthena 1(15 Aug 1995)10003-stage0m@#`\\"x<HLNConestoga(23 Oct 1995)21004-stage-:@A#Z\\2@FHTitan 4B23 Feb 199722000?4-stage!@bB#B\\$0<>Delta 31998?83463810A C#6\\ ,02Eagle1999?1300bBC#6\\ $02Atlas 2AR?4037 CRD#,\\"&(Titan 2S?CD#6\\&,02Titan 4SRMU?RDE#:\\"GKT$&,046Pegasus Turbo? DGF#\\ EF#,\\(㱭+"&(France7GFG#n\\"À8@DFDiamant A26 Nov 1965803-stage (--> 1967)9FH#r\\$À :DHJDiamant B10 Mar 19701153-stage (--> 1973)9GkI#r\\$À ":DHJDiamant BP46 Feb 19751503-stage (--> 1975)HJ#\\ kIJ#*\\(b $&JapanOJK#\\" T\`bLambda-4S(26 Sep 1966)11 Feb 1970204-stage, 1 successful flightAJrL#\\" LTXZMu-4S(25 Sep 1970)16 Feb 1971753-stage (--> 1972)3K7M#f\\" 08<>Mu-3C16 Feb 1974853-stage (--> 1976)-rLM#Z\\"J(,02N19 Sep 19753-stage (--> 1982)47MN#h\\" 0:>@Mu-3H19 Feb 19771003-stage (--> 1979)5MO#j\\" 2<@BMu-3S117 Feb 19812003-stage (--> 1984)1NR#b\\"J*.8ORA:N211 Feb 19813503-stage (--> 1987)"O#D\\" 0:>@Mu-3S28 Jan 19854006R΁#l\\"J*6BDH113 Aug 1986320011003-stage (--> 1995)D#\\"J(6^`H23 Feb 1994105004000 (2000 to GEO)2-stage + boosters/΁e#^\\" .:>@Mu 512 Feb 19971800solid 3-stage`R#\\  ",02J1exp. 1996870solid 3-stageconsist of H2 strap-on first stage + 2 stages of Mu-3S2(e#P\\ $(46H2Aexp. 19994000$85 million R#\\ I#*\\(6" $&China@#\\"9+S$&BNRTLong March 1Dno launches?1000liquid/solid 3-stageGI#\\$9+S$&\`dfLong March 1(01 Nov 1969)24 Apr 19703-stage (--> 1971)=ވ#z\\$9+S$&DHLNLong March 2A(05 Nov 1974)No successful flight6#l\\$9+S.268FB 110 Aug 19722-stage (LEO) (--> 1981)Oވ#\\"9+S&(BNfhLong March 2C26 Nov 197525001000 + PKMliquid 2-stage14 success<j#x\\"9+S"$>JVXLong March 329 Jan 198450001400liquid 3-stage73#n\\"9+S"$<HLNLong March 46 Sep 19884000liquid 3-stage[j #\\"9+S$&@LjlLong March 2E16 Jul 199092003370 with PKMliquid 2-stage + 4 liquid strap-ons:3#t\\"9+S$&@NRTLong March 2D9 Aug 19923300liquid 2-stage< #x\\"9+S$&>JVXLong March 3A8 Feb 199472002500liquid 2-stage}Џ#\\"9+S$&DHTVLong March 3B(14 Feb 1996)4800liquid 3-stage + 4 liquid strap-onsconsist of Long March 3A with 4 2E strap-ons y#\\ЏA"9+S$&<@LNLong March 3Cexp. 19973700liquid 3-stage + 2 liquid strap-onsconsist of Long March 3A with 2 2E strap-ons Џ#\\ ,#:\\*R׀*.26United KingdomO#\\$Xـ "VZ^`Black Arrow(1 Sep 1970)28 Oct 19713-stageOne successful flight,#\\ p#0\\(4" &*,Europe:I#t\\ >BFHEuropa 1 F8(30 Nov 1968)No successful flight6p#l\\6:>@Europa 2(05 Nov 1971)No successful flight;I#v\\"%+:@LNAriane 124 Dec 197917003-stage (--> 1986)9#r\\"C+6<HJAriane 34 Aug 198425803-stage + boosters/#^\\"C+8>JLAriane 230 May 198620653-stage0L#`\\"$ D+BNZ\Ariane 4, 44LP15 Jun 198883004030. #\\\ "2D+>JVXAriane 4, 44L4 Jun 1989960044605L#j\\ 6D+>JVXAriane 4, 4022 Jan 1990490020203-stage/ #^\\ "fD+@LXZAriane 4, 42P20 Nov 199061002740.T#\\\ "_D+>JVXAriane 4, 44P4 Apr 199169003290/#^\\ "D+@LXZAriane 4, 42L12 May 199374003350OT#\\8HTVAriane 5exp. Apr 1996180006800liquid 2-stage + 2 solid strap-ons #\\ 9#*\\(&€ $&IndiaA#\\"#LTXZSLV 3(10 Aug 1979)18 Jul 1980404-stage9A (--> 1983)[9#\\"#JTXZASLV(24 Mar 1987)20 May 1992150solid 4-stage + 2 solid strap-ons (--> 1994)X#\\"#JVZ\PSLV(20 Sep 1993)15 Oct 19943000solid/liquid 4-stage + 2 solid strap-ons"#D\\&2>@GSLVlate 199780002500 9#\\ #,\\(ΝE"&(Israel29#d\\"<}f6@DFShavit19 Sep 1988150solid 3-stageO#\\#0\\(7 &*,Brazil&O#L\\"\0BFHVLS(2 Nov 1997)350 kg&# G-1<+t$* -Soviet launch vehiclesS5 :> " Soviet launch vehicles;-* $" >ɀGunter Krebs&# A#6n"$46LjlSheldon / DodNameArticleDesignationComment #8n&24A / SL1R78K71B #<n.06JLA / SL1Sputnik?8K71PSfor the first 2 SputniksJ  #*n,.6DFA / SL2Sputnik?8A91for Sputnik (3) failure and Sputnik-3 C #*$n  [ K #*n@BJXZA1 / SL3Vostok L (Luna?)?8Kxxfor early Lunas and the first Korabl-SputnikGC ?#*n02:JLA1 / SL3Vostok K?8KxxKfor Korabl-Sputniks and Vostoks ZK L#6n,.6DF3xAA1 / SL3Vostok?8A92for Cosmos series (Zenit) spysats and early MeteorsC?H@#*n02:JLA1 / LH@SL3Vostok M?8A92Mfor sunsynchronous missionsLA#*$n  NH@B#*n.08LNA2 / SL4Voskhod?11A57 ?for the first missons and for Voskhod8AB#*pn*,4FHA2 / SL4Soyuz?11A511for Soyuz capsules)BC#*Rn.08LNA2 / SL4Soyuz M?11A511M ]BD#*n.08LNA2 / SL4Soyuz L?11A511Lto lift Cosmos 398 class Lunar lander tests into LEOPCE#*n.08LNA2 / SL4Soyuz U?11A511Uthe current model for unmanned missions-zDF#6n02:PR-xA2 / SL4Soyuz U2?11A511U2the current version for manned missions (and possibly for Kuban type spysats)EG#*$n  ?FH#*~n02:HJA2e / SL6Molniya?8K78was used only until 1966;GI#*vn46>NPA2e / SL6Molniya M?8K78Mthe current modelHCJ#*$n  CI3K#*n<>FVXAe / SL5Sputnik-Polyot?11A??Polyot launch vehicleCJK#*$n  C3KL#*n&(0BDA1m / SL10??11A510Cosmos 125 / 102 launch vehicleKM#*$n  2LN#*dn"$,:<B1 / SL7??63S1difference unknown:MgO#*tn02:JLB1 / SL7Cosmos 2?11K63difference unknownN2#*$n gO2 /gO#*^n"$,:<C1 / SL8??65S1Tyuratam launch72#*nn02:JLC1 / SL8Cosmos 3?11K65Tyuratam launchJ#*n24<NPC1 / SL8Cosmos 3M?11K65MKapustin Yar and Plesetsk launch#*$n  @#6n"㉓g.0@NPD / SL9ProtonUR5008K82two stage test versionK#6n"㉓g68JZ\D1 / SL13Proton KUR500K8K82Kthree stage version for LEOb#6n"㉓gHJnD1e / SL12Proton K Block DUR-500K Block D11S824for early interplanetary probesX#*n"㉓gJLp~D1e / SL12Proton K Block DMUR-500K Block DM11S86for early GEO missions `#*n"㉓gLNtD1e / SL12Proton K Block DM2UR-500K Block DM211S861uprated version of Block DM*}#*n"㉓gNPxD1e / SL12Proton K Block DM2MUR-500K Block DM2M11S861-01lightwight version of Block DM2 for higher payloads# n "j#Dn$&8>@G1e / SL15N1 / L3?IZ#n$&BHJG1e / SL15N1 / L3 (7L)LN-1 L3 (7L) had different boattailj# n +Z#Vn$&4@BF1r / SL11R36-08K69for FOBS2Ž#*dn"HJP^`F1m / SL11Cyclone M (or 2)?11K69*#*Tn"8:@NPF2 / SL14Cyclone 3?11K68Ž\# n \&)#Ln028FHJ1 / SL16Zenit 2?11K77\# n #)#Fn24:@BK1 / SL17Energiya??$" 11) RJS0R# `needs sorting! (preparing new launcher items)2 ' O Med LiteeR # made from a Taurus launcher with a Pegasus XL at the top! Should start in 1998 with SAC C and EO 13 ?'  Cosmos 3M $ Cosmos 3M, built by PO Polyot of Omsk, is derived from the R-14 (NATO designation SS-5) IRBM built originally by the Yangel design bureau.1 ?!' O Delta 3% McDonnell Douglas announced plans for private development of Delta III, based on an anchor-customer contract for 10+ launches (including the first, in early 1998) from Hughes. D3 will be capable of about 4.2 tons to GTO (roughly twice the current Delta payload). LEO payload about 9.2 tons. D3 is an odd configuration. The strap-on solids get a bit longer and fatter, and three (out of nine) acquire vectoring nozzles. The first stage mostly stays the same diameter, but shortly above the solid strap-ons, it bulges out to 13.1ft dia. The first-stage fuel tank is above the bulge. More important, the 13.1ft dia continues upward, with a completely new LH2/LOX second stage and a new wide payload fairing. The engine for the second stage has not yet been chosen, but it will be an existing Western engine. D3 design will emphasize proven technology and maximum use of existing Delta hardware.!$ Much attention on the new second stage. Some have claimed it's an H-2 second stage -- especially since McDD has a long history of work with Mitsubishi on the major Japanese launchers -- but McDD says no: "frankly, it's too expensive" (although use of some Japanese hardware is possible). Others claim it's going to be a single-engine Centaur, but McDD doesn't like Centaur's balloon tanks or its common bulkhead, and says D3 will have neither (although it will probably use Centaur's insulation scheme).0 '  ProtonT0i$ aShould be replaced by the Angara booster The first stage will use the same kerosene-LOX four-engine cluster as Zenit; the second stage will use a single Energia-derived LH2-LOX engine. The configuration is rather odd: a cylindrical center body reminiscent of a Zenit (holding the fuel), with a pair of large drop tanks slung on the outside of each stage to hold the LOX. The initial configuration will launch 26t into a 63deg orbit from Plesetsk (slightly more than Proton from Baikonur); a third stage (LH2-LOX) will be added to put 4.5t payloads into GSO.$ There is talk of an Angara offshoot using a modified second stage air-launched from an An-124, launching 6t into 51deg at about $1500/kg.0 iI'  BurlakJ$ Russian project of LEO launcher released from a bomber. Burlak will be a wingless two-stage liquid-fuel vehicle, derived from (unspecified) missile technology. Payload to LEO would be up to 800kg at perhaps $5000/kg. 1I{1W { T+J) "VȠ$To view this page you need to register&{ #  J7C1R2z(?6 CArianeC 5 :1U" ArianeDC* $4 㭄؉by Jean-Jacques Serra%2 2 /European launch vehicle program operated by Arianespace.After the failure of the Europa 1/2 program, the ELDO was to design a totally new Europa 3. This launcher was to have a first stage L150 with stockable propellant powered by 4 Viking motors from SEP and a second cryogenic stage H20 equipped with a hight pressure HM-20 motor from Cryorocket. This project was found too risky both technically and financially especially by Germany which wanted to focus on the construction of Spacelab.!% In 1972 the CNES proposed to built a launcher with the same performance but using only European tested technology like the low-pressure cryogenic propulsion. This project designed L-IIIS (substitution third generation launcher) was to use an H6 cryogenic top stage with a HM-4 motor designed by SEP. The poor performance of the H6 compared to the H20 required the use of two base stages, on L140 (reduced version of the Europa 3 L150) and an L33 (featuring a single Viking motor adapted to altitude use). ' In December 1972 the 5th European Space Conference ended on 3 agreements: creation of a European Space Agency (ESA to replace both ELDO and ESRO) and the start of the L-IIIS and Spacelab.The following year the L-IIIS project was further precised (increased propellant of the H6 to become H8 and replacement of the 4-chamber HM-4 by a single-nozzle HM-7) and changed denomination: Ariane. The CNES granted Aerospatiale as the industrial architect of the project.2 <'  Ariane 1nJ  $ The first Ariane version was a 208-ton launcher (without payload) of 47.4 m high. The first stage (L140) was 3.8 m diameter, 18.4 m high, containing 147.6 tons propellant (NTO + UDMH). It was powered by a set of 4 Viking 5 motors which fired during 146 seconds, providing 2485 kN thrust at takeoff (Isp = 247 s) and 2770 kN in vacuum (Isp = 278 s). The second stage (L33) was 2.6 m diameter for 11.6 m high. It was loaded with 34.2 tons propellant identical to first stage. It's Viking 4 motor provided 723 kN thrust (Isp = 296 s) during 138 seconds. The top stage (H8) of same diameter was 9.1 m high. It's cryogenic motor HM-7 developped 61.3 kN thrust (Isp = 441 s) and consumned 8.2 tons liquid oxygen and hydrogen in 545 seconds. The first and third stage were assembled in France by Aerospatiale, the second stage in Germany by ERNO.tP< $ Ariane was optimized for launches in GTO to which it could deliver 1750 kg. 6 T ' O Ariane 2 & 3i  4 6  As soon as 1977 the CNES started enhancing the performance of the launcher. The first derivatives named Ariane 2 & 3 had the following characteristics:- On the two first stages: enhancement of the thrust of the Viking 4 and 5 by increasing the pressure of the combustion chamber and replacement of UDMH by UH25 (75% UDMH and 25% hydrazine hydrate). The combustion duration where then respectively 135 and 123 seconds.- On the third stage: lengthening by 1.3 m of the tanks (10.7 tons propellant on this new H10) and increased specific impulsion of the motor (HM-7B). The combustion duration was then 720 s.T / ,u - Extension of the payload volumeThe Ariane 3 version had also two additional solid booster: 8 m high, 1.07 m diameter, 9.7 tons (including 7.3 tons solid propellant: Flexadyne). Each booster provided 666 kN thrust during 28 s. They were manufactured by BPD in Italy.The two launchers were 48.7 high. Ariane 2 weighed 212 tons at takeoff while Ariane 3 weighed 230 tons. The payload weights then reached 2065 kg and 2580 kg in GTO. 2 @' O @ Ariane 4":C& The construction of a series of launchers named Ariane 4 with enhanced performance was decided in 1981. Those launchers are directly derived from the previous version, retaining the 3 stages and lengthening the first one and addition solid and/or liquid boosters.The first stage of Ariane 4 named L220 is 23.2 m high. It transports 227 tons propellant identical to Ariane 2/3. It is still powered by a set of Viking 5 motors (version C) which provide during 205 seconds 2710 kN thrust at takeoff (3010 kN in vacuum, Isp = 278 s). The two other stages are those of Ariane 2/3 with a reinforced structure. The 3rd stage has been lengthened twice giving the H10+ (11 tons propellant) and H10-3 (11.8 tons propellant) versions. The latter burns during 13 minutes.jE@E% The flexibility of Ariane 4 is due to the adaptation of the payload by addition of boosters on the first stage. Those are of 2 types: PAP (solid) and PAL (liquid). The PAPs are a enhancement of the Ariane 3 boosters. They are 12 m high, weigh 12.6 tons (including 9.5 tons powder) and provide 650 kN thrust (Isp = 224 s) during 36 seconds. The PALs are built by MBB/ERNO. They are 19 m high, 2.2 m diameter, weigh 43.5 tons (39 tons of the same propellant as the first stage). Their Viking 6 motor fires during 143 seconds and provides 678 kN at ground level, 752 kN in vacuum.:CG* "The possible configurations are:- Ariane 40: no boosters- Ariane 42: 2 boosters, 42P with 2 PAP and 42L with 2 PAL- Ariane 44: 4 boosters, 44P with 4 PAP, 44L with 4 PAL, 44LP with 2 PAP and 2 PALThe launcher's height ranges from 54.1 m to 58.4 m depending on the cap used. Its mass ranges from 243 tons (Ariane 40) to 480 tons (Ariane 44L) and the GTO performance from 2020 kg to 4460 kg. Ariane 4 should remain in active service until the end of the century.2 EG' O Ariane 5{GKD VELK\J  The launch of the Ariane 5 program was decided by ESA members in November 1987 following an initial study launched in early 1985. Built with Aerospatiale as prime contractor, Ariane 5 is totally different from the previous Arianes in terms of architecture. It's configuration is closer to Titan or STS or H2. Like those launchers, Ariane 5 has got a main body with liquid propulstion and 2 large solid boosters.The EAP (Etage d'Acclration Poudre, acceleration solid stage) is composed of two MPS (Moteurs Propulsion Solide, solid propulsion motors) also named P230 built by Europropulsion (a 50/50 groupement of SEP (France) and BDP (Italy)). Each MPS is 27 m high and 3 m diameter and weighs 267 tons including 237 tons of propellant (3 PBHT segments). They provide 6 MN thrust at takeoff (ISp = 273 s) and work during 123 s before being jettisonned at 56 km altitude. GN1 0  The main body is made of an EPC (Etage Principal Cryotechnique, cryogenic main stage) and an ETS (Etage Propergols Stockables, stockable propellant stage). The EPC is 30.5 m high and 5.4 m diameter. It is propulsed by a Vulcain flux-derived motor from SEP. It's thrust is 880 kN at ground level and reaches 1130 kN in vacuum (ISp = 430 s). The MPS are ignited only after the Vulcain motor has prooved to be working properly; it then burns 131 tons of LOX and 26 tons of LH2 within 600 seconds. The EPS alias L9 uses 9.7 tons of conventional ergols (NTP and MMH-H) and care for the precise orbital release. It is equipped with a MBB-ERNO (DASA group) Aestus motor of 28 kN thrust in vacuum than can work 1150 seconds and can be re-ignited.KO% With the equipment compartment and the cap (2 different versions are available) Ariane 5 is 45.7 to 55.9 m high. It weighs 710 tons. It's capacity to GTO is 6.8 tons with one satellite or 5.9 tons with 2 satellites or 5.5 tons with 3. ;N ' ( Ariane statisticsO  XO #C  2 P  TypeFirst launchLast launchLEO/GTO capacity (kg)Number of launches= #zC %+(C+FVX124 Dec 197922 Feb 1986/ 170011 (2 failures): #tC C+(;D+DTV230 May 19862 Apr 1989/ 20656 (1 failure);#vC C+&3D+DTV34 Aug 198412 Jul 1989/ 258011 (1 failure)5R#jC  6D+*~g&\Hbd4022 Jan 199024 Mar 19984900 / 20206C-#C fD+,}g&\Jdf42P20 Nov 199027 Feb 19986100 / 274010 (1 failure)6R#lC _D+*g&\Hbd44P4 Apr 199128 Apr 19986900 / 3290136-Ɇ#lC D+,{g&\Jdf42L12 May 199322 Dec 19977400 / 33506C#C D+.|g&\Jdf44LP15 Jun 19884 Feb 19988300 / 403020 (1 failure)BɆ~#C 2D+*yg&\Hbd44L4 Jun 198912 Nov 19979600 / 446022 (1 failure)Df#C" E+((xg&\Jhj54 Jun 199630 Oct 199718000 / 68002 (1 failure)&~# ;flj' ( Motor performance #{ 4IczkOz]2zO0LȀ$ 2 ZTypeFirst launch4 Viking 54 Viking 5 Thrust (kN)4 Viking 5 Isp (s)Viking 4Viking 4 Thrust (kN)Viking 4 Isp (s)HM7HM7 Thrust (kN)HM7 Isp (s)@lj# 4IczkOz]2zO4JPZd j v11979A2485s/2770v247s/278vA723296-61.34419э#r 4IczkOz]2zO 8<BLV \ h2/31984B2690s/2980vB785296B62.8445.َ#\ 4IczkOz]2zO48>DJ P V41988C2710s/3010vB--B--&э# <َ;' *O External resourcesi;. ,vhttp://www.arianespace.com/http://www.go-ariane.com/1;Տ1U ՏKoX%93 6J2!Տ9 Ariane[launch vehicle index] ՏK#Ά% ,%+&+'+(+)+*+++,+gE+C+C+C+C+C+C+C+C+C+C+D+& D+D+ D+ D+ D+ D+ D+D+D+;D+2D+3D+4D+5D+6D+7D+8D+9D+:D+fD+&]D+^D+_D+`D+aD+bD+cD+dD+eD+D+D+D+D+D+D+D+D+D+D+D+( D+D+D+D+D+D+D+D+D+D+D+D+D+D+D+D+D+D+D+E+., E+ E+ E+ E+ E+E+E+E+E+=E+4E+5E+6E+7E+8E+9E+:E+;E+ 1056 kgr$N#lH*ڰ_vcTPayloadA: Marecs AB: Cat 4:W$ ,First night launch; >1M,, >% Ariane L05G5 :&1U" Ariane L051 >'  Generalh' A#RNLaunch date10 Sep 1982 at 01:12 UTWu A#R,Launch siteKourouK   A#RType1Yu  A#R0Payload mass1476 kgo!  N#lB*ʴUdBPayloadMarecs B1Sirio 2y5  D#Xj  Failure cause3rd stage motor turbo pump failure$ % " ;  ` 1,, `  ]Ariane L06G%  5 :&1U" Ariane L061 `  '  GeneralT , A#R&Launch id83058h'  A#RNLaunch date16 Jun 1983 at 11:59 UTW,  A#R,Launch siteKourouK 6 A#RType1Y  A#R0Payload mass1205 kgy+6 N#lV*نu쉂PayloadA: Eutelsat 1F1B: Oscar 10U1 ]$ bFirst successful launch with the Sylda system; 1,A, [AAriane L07G]5 :&1U" Ariane L071 '  GeneralTdA#R&Launch id83105h'A#RNLaunch date18 Oct 1983 at 23:54 UTWd/@A#R,/@]Launch siteKourouK z@A#RType1Y/@@A#R0Payload mass1870 kgdz@7AG#^:\ĉPayloadA: Intelsat 507$@[A" ; 7AA1,, AALDAriane L08G[AA5 :&1U" Ariane L081 AB'  GeneralTAbBA#R&Launch id84023g&BBA#RLLaunch date5 Mar 1984 at 00:50 UTWbB CA#R,Launch siteKourouK BkCA#RType1Y CCA#R0Payload mass1900 kgdkC(DG#^:]ĉPayloadA: Intelsat 508$CLD" ; (DD1A,, DDXGAriane V09GLDD5 :&1U" Ariane V091 DD'  GeneralTDSEA#R&Launch id84049\DEA#R6Launch date22 May 1984WSEFA#R,Launch siteKourouK EQFA#RType1YFFA#R0Payload mass1195 kgbQF GG#^6ZIzPayloadA: Spacenet 1L(FXG$ PFirst launch operated by Arianespace; GG1,, GG|JAriane V10GXGG5 :&1U" Ariane V101 G H'  GeneralTG_HA#R&Launch id84081j) HHA#RRLaunch date4 Aug 1984 at 11:32:54 UTW_H IA#R,Launch siteKourouK HkIA#RType3Y IIA#R0Payload mass2395 kg{-kI?JN#lZ*چ ePayloadA: Eutelsat 1F2B: Telecom 1A=I|J$ 2First Ariane 3 launch; ?JJ1#,p, JJMAriane V11G|JJ5 :&1U" Ariane V111 J/K'  GeneralTJKA#R&Launch id84114h'/KKA#RNLaunch date10 Nov 1984 at 01:14 UTWKBLA#R,Launch siteKourouK KLA#RType3YBLLA#R0Payload mass2251 kgx*L^MN#lT*[Iz˴UPayloadA: Spacenet 2B: Marecs B2n*LMD#XT GTO200/36.022 km, inclination: 7.01$^MM" ; M+N1,G- +NrNAriane V12GMrN5 :&1U" Ariane V121 +NN'  GeneralTrNNA#R&Launch id85015[NROA#R4Launch date8 Feb 1985WNOA#R,Launch siteKourouK RO A#RType3O MYOeA#R0Payload mass2310 kg{- N#lZ*4鉂bPayloadA: Arabsat 1AB: Brasilsat A1$e" ; ?1p,- ?Ariane V13G5 :&1U" Ariane V131 ?'  GeneralT A#R&Launch id85035g&rA#RLLaunch date8 May 1985 at 00:15 UTW ɂA#R,Launch siteKourouK rA#RType3YɂmA#R0Payload mass2480 kgv(N#lP*:TePayloadA: GStar 1B: Telecom 1B$m" ; B1G-- BBAriane V14G5 :&1U" Ariane V141 B'  GeneralTA#R&Launch id85056[iA#R4Launch date2 Jul 1985WA#R,Launch siteKourouK i A#RType1XcA#R.Payload mass960 kgr1 ՆA#RbPayloadESA's comet Halley interceptor GiottomIcB$ Recovery of the first stage failed because the parachutes didn't open; Ն}1 -- }ćAriane V15GBć5 :&1U" Ariane V151 }'  General\ćQA#R6Launch date13 Sep 1985WA#R,Launch siteKourouK QA#RType3YLA#R0Payload mass2380 kgu'N#lN*ۆ\IzPayloadEutelsat 1F3Spacenet 3sLxD#X  Failure causeOne of the 3rd stage motors didn't switch on. President Mitterrand was there. It was Friday 13th$" ; x׊1-- ׊Ariane V16G5 :&1U" Ariane V161 ׊O'  GeneralTA#R&Launch id86019k*OA#RTLaunch date22 Feb 1986 at 01:44:35 UTWeA#R,Launch siteKourouK A#RType1Ye A#R0Payload mass2438 kgq#zN#lF*㥇1ĉPayloadA: Spot 1B: Vikinga $ First launch towards North to put the satellites on a polar orbit. Last launch of an Ariane 1; z:1-[- :Ariane V17G5 :&1U" Ariane V171 :'  GeneralTA#R&Launch id86026\bA#R6Launch date28 Mar 1986WA#R,Launch siteKourouK bA#RType3YiA#R0Payload mass2410 kgx*N#lT*;TbPayloadA: GStar 2B: Brasilsat A2=i$ 2First launch on ELA 2; Y1-L- YXAriane V18G5 :&1U" Ariane V181 Y'  Generalh'9A#RNLaunch date30 May 1986 at 00:53 UTWA#R,Launch siteKourouK 9A#RType2Y4A#R0Payload mass1900 kgaG#^4ĉPayloadIntelsat 514<4D#Xx  Failure causeOne the 3rd stage motors didn't switch onCX$ >First launch of an Ariane 2; 1[-- SAriane V19GX5 :&1U" Ariane V191  '  GeneralT_A#R&Launch id87078\ A#R6Launch date16 Sep 1987W_A#R,Launch siteKourouK ]A#RType3YA#R0Payload mass2435 kgy+]/N#lV*_܆PayloadA: Optus A3B: Eutelsat 1F4$S" ; /1L-- 4Ariane V20GS5 :&1U" Ariane V201 '  GeneralTZA#R&Launch id87095\A#R6Launch date21 Nov 1987WZ A#R,Launch siteKourouK XA#RType2Y A#R0Payload mass2144 kg_XG#^0mԐPayloadA: Tvsat 1$4" ; o1$-- oAriane V21G45 :&1U" Ariane V211 o'  GeneralT;A#R&Launch id88018h'A#RNLaunch date11 Mar 1988 at 23:28 UTW;A#R,Launch siteKourouK EA#RType3YA#R0Payload mass2405 kgz,EN#lX*dePayloadA: Spacenet 3RB: Telecom 1Cm)D#XR GTO202/36087 km, inclination: 7.03$" ; 1-4. +Ariane V22G+5 :&1U" Ariane V221 \'  GeneralT+A#R&Launch id88040h'\A#RNLaunch date17 May 1988 at 00:58 UTWoA#R,Launch siteKourouK A#RType2YoA#R0Payload mass1978 kgdG#^:ĉPayloadA: Intelsat 513YD#X* GTO463/35948 km$" ; ;1- . ;AAriane V23G5 :&1U" Ariane V231 ;'  GeneralTA#R&Launch id88051\cA#R6Launch date15 Jun 1988WA#R,Launch siteKourouQc A#R Type4, 44LPR]A#R"Payload mass9 U#zr8ѵan쉂@hPayloadA: Meteosat 3B: Oscar 13C: Panamsat 1V1]A% bFirst launch of Ariane 4with cyclade adapter; |1 4.. |Ariane V24GA5 :&1U" Ariane V241 |'  GeneralTHA#R&Launch id88063h'A#RNLaunch date21 Jul 1988 at 23:12 UTWHA#R,Launch siteKourouK RA#RType3YA#R0Payload mass2337 kgy+R$N#lV*uG@c݆PayloadA: Insat 1CB: Eutelsat 1F5j&D#XL GTO198/35993 km, inclination: 7$$" ; 1 .. 4 Ariane V25G45 :&1U" Ariane V251 e'  GeneralT4A#R&Launch id88081g&e A#RLLaunch date8 Sep 1988 at 23:00 UTWw A#R,Launch siteKourouK  A#RType3Yw  A#R0Payload mass2511 kgq#  N#lF*FA#R,Launch siteKourouQEFA#R Type4, 44LPY>FFA#R0Payload mass2976 kgv(F^GN#lP*ㆺ2ҵaPayloadA: Jcsat 1B: Meteosat 4$FG" ; ^GG1.. GHJAriane V30GGH5 :&1U" Ariane V301 G5H'  GeneralTHHA#R&Launch id89027g&5HHA#RLLaunch date2 Apr 1989 at 02:28 UTWHGIA#R,Launch siteKourouK HIA#RType2YGIIA#R0Payload mass2089 kg^IIJG#^.yPayloadA: TELE XBIJ$ <Last launch of an Ariane 2; IJJ1ԁ.H. J KMAriane V31GJ K5 :&1U" Ariane V311 J>K'  GeneralT KKA#R&Launch id89041[>KKA#R4Launch date5 Jun 1989WKDLA#R,Launch siteKourouPKLA#RType4, 44LYDLLA#R0Payload mass3907 kgv(LcMN#lP*Oʗ>TPayloadA: Superbird A1B: DFS 1$LM" ; cMM1.L/ M NÀAriane V32GM N5 :&1U" Ariane V321 M:N'  GeneralT NNA#R&Launch id89053h':NNA#RNLaunch date12 Jul 1989 at 00:14 UTWNMOA#R,Launch siteKourouK NOA#RType3YMO A#R0Payload mass2595 kgO M_OkG#^0vtމPayloadA: OlympusX4 À$ hLast launch of an Ariane 3 and last use of ELA 1; k1H./ EAriane V33GÀE5 :&1U" Ariane V331 v'  GeneralTEʁA#R&Launch id89062[v%A#R4Launch date8 Aug 1989Wʁ|A#R,Launch siteKourouQ%͂A#R Type4, 44LPY|&A#R0Payload mass3284 kgu'͂N#lN*mԐPayloadA: Tvsat 2B: Hipparcos$&" ; 1L// AAriane V34GA5 :&1U" Ariane V341 r'  GeneralTAƄA#R&Launch id89087h'r.A#RNLaunch date27 Oct 1989 at 23:05 UTWƄA#R,Launch siteKourouQ.օA#R Type4, 44LPY/A#R0Payload mass4200 kgdօG#^: ĉPayloadA: Intelsat 602[/D#X. GTO199.6/35965 km$" ; M1/"/ MAriane V35G5 :&1U" Ariane V351 MŇ'  GeneralTA#R&Launch id90005h'ŇA#RNLaunch date22 Jan 1990 at 01:35 UTW؈A#R,Launch siteKourouO'A#RType4, 40Y؈A#R0Payload mass1990 kg`'Qq#p㦇ϓF̉ГF̉eOU . UPayloadA: Spot 2B: Uosat 3C: Uosat 4D: PacsatE: DoveF: WebersatG: Lusatg* $ The ASAP 1 (Ariane Structure for Auxiliary Payload) structure which carries up to 200kg was used; Q1// dAriane V36Gd5 :&1U" Ariane V361 '  General\dA#R6Launch date22 Feb 1990WHA#R,Launch siteKourouPA#RType4, 44LYHA#R0Payload mass3782 kgq#bN#lF*`Sk7㉂PayloadSuperbird DYuri 2XLD#X  Failure causeA rag was forgotten in a water pipe for D motor's cooling$b" ; Q1"/a/ QAriane V37G5 :&1U" Ariane V371 QɎ'  GeneralTA#R&Launch id90063\ɎyA#R6Launch date24 Jul 1990WЏA#R,Launch siteKourouPy,A#RЏ,Type4, 44LYЏA#R0Payload mass4114 kgo!,N#lB*w~W˗>TPayloadA: TDF 2B: DFS 2j&^D#XL GTO300/35933 km, inclination: 4$" ; ^1/$/ Ariane V38G5 :&1U" Ariane V381 5'  GeneralTA#R&Launch id90079h'5A#RNLaunch date30 Aug 1990 at 22:46 UTWHA#R,Launch siteKourouQA#R Type4, 44LPYHA#R0Payload mass3280 kgz,lN#lX* ȉPayloadA: Skynet 4CB: Eutelsat 2F1$" ; l1a/ҁ/ Ariane V39G5 :&1U" Ariane V391 C'  GeneralTA#R&Launch id90091\CA#R6Launch date12 Oct 1990WJA#R,Launch siteKourouPA#RType4, 44LYJA#R0Payload mass4208 kgr$eN#lH*=HW`UPayloadA: Topex PoseidonB: Kitsat AC: S80TK'"NN$ NASAP 3 carried the micro-satellites; N4O1҂01 4O{OAriane V53GN{O5 :&1U" Ariane V531 4OO'  GeneralT{O A#R&Launch id92060O N\OhA#R6Launch date10 Sep 1992W A#R,Launch siteKourouQhA#R Type4, 44LP[kA#R4Payload mass> 2120 kgy+N#lV*c͉s-PayloadA: Hispasat 1AB: Satcom C3$k" ; C1071 CAriane V54G5 :&1U" Ariane V541 C'  GeneralTA#R&Launch id92072h'wA#RNLaunch date28 Oct 1992 at 00:15 UTW΃A#R,Launch siteKourouPwA#RType4, 42PY΃wA#R0Payload mass2725 kg`ׄG#^2=upPayloadA: Galaxy 7$w" ; ׄ6111 6}Ariane V55G}5 :&1U" Ariane V551 6'  GeneralT}A#R&Launch id92084[]A#R4Launch date1 Dec 1992WA#R,Launch siteKourouP]A#RType4, 42PY]A#R0Payload mass2780 kgdG#^:OPayloadA: Superbird A2$]" ;  1711 gAriane V56Gg5 :&1U" Ariane V561 '  GeneralTgA#R&Launch id93031k*WA#RTLaunch date12 May 1993 at 00:56:32 UTWA#R,Launch siteKourouPWA#RType4, 42LYWA#R0Payload mass2854 kgs%ʊN#lJ*(~:PayloadA: Astra 1CB: ArsneD W$ @Cyclade dual payload adapter; ʊI11h1 IAriane V57G5 :&1U" Ariane V571 I'  GeneralTA#R&Launch id93039h'}A#RNLaunch date25 Jun 1993 at 00:18 UTWԌA#R,Launch siteKourouP}$A#RType4, 42PYԌ}A#R0Payload mass2988 kg`$ݍG#^2:upPayloadA: Galaxy 4$}" ; ݍ<1@1m1 <Ariane V58G5 :&1U" Ariane V581 <'  GeneralTA#R&Launch id93048k*sA#RTLaunch date22 Jul 1993 at 22:58:55 UTWʏA#R,Launch siteKourouQs'A#R ʏ'Type4, 44LPYʏA#R0Payload mass4020 kgx*'N#lT*c͉G@cPayloadA: Hispasat 1BB: Insat 2Bm)eD#XR GTO200/35957 km, inclination: 6.96$" ; e1Xh11  2Ariane V59G 5 :&1U" Ariane V591 <'  GeneralT A#R&Launch id93061h'<A#RNLaunch date26 Sep 1993 at 01:45 UTWOA#R,Launch siteKourouOA#RType4, 40YOA#R0Payload mass2117 kgxx#~㧇xټ |{3KBVPayloadA: Spot 3B: StellaC: EyesatD: ItamsatE: HealthsatF: ASAP 4 (22828)G: PosatH: Kitsat BK'2$ NASAP 4 carried the micro-satellites; m1m1S1 m*Ariane V60G25 :&1U" Ariane V601 m'  GeneralT9A#R&Launch id93066h'A#RNLaunch date22 Oct 1993 at 06:46 UTW9A#R,Launch siteKourouQIA#R Type4, 44LPYA#R0Payload mass3692 kgdIG#^:ĉPayloadA: Intelsat 701$*" ; e111 e:Ariane V61G*5 :&1U" Ariane V611 e'  GeneralT1A#R&Launch id93073h'A#RNLaunch date20 Nov 1993 at 01:17 UTW1A#R,Launch siteKourouQAA#R Type4, 44LPYA#R0Payload mass3500 kg|.AN#l\*L2ԵaPayloadA: Solidaridad 1B: Meteosat 6$:" ; u1S1Ӄ1 u@Ariane V62G:5 :&1U" Ariane V621 u'  GeneralTAA#R&Launch id93078h'A#RNLaunch date18 Dec 1993 at 01:27 UTWAA#R,Launch siteKourouPPA#RType4, 44LYA#R0Payload mass3940 kgs%PN#lJ*~9TFˉPayloadA: DBS 1B: Thaicom 1$@" ; {11}2 {Ariane V63G@5 :&1U" Ariane V631 {'  Generalh'[A#RNLaunch date24 Jan 1994 at 21:37 UTWA#R,Launch siteKourouQ[A#R Type4, 44L@PYhA#R0Payload mass3663 kgu'N#lN*lvmPayloadEutelsat 2F5Turksat 1A<h`G#^x  Failure cause3rd stage motor failure (H10+ turbopump)$" ; `1Ӄ1L2  Ariane V64K 8 @(1U" Ariane V641 ;'  GeneralT A#R&Launch id94034h';A#RNLaunch date17 Jun 1994 at 07:07 UTWNA#R,Launch siteKourouQA#R Type4, 44LPYNA#R0Payload mass3800 kg7U#zn8ĉdjdjPayloadA: Intelsat 702B: STRV 1AC: STRV 1B$" ; 1P}2]2 .MAriane V65K.8 @(1U" Ariane V651 _'  GeneralT.A#R&Launch id94040j)_A#RRLaunch date8 Jul 1994 at 23:05:32 UTWtA#R,Launch siteKourouPA#RType4, 44LYtA#R0Payload mass4035 kgv(N#lP*Ah ㉂PayloadA: Panamsat 2B: Yuri 3Nl(D#XP GTO199.6/35977 km; inclination: 7N*M$ TTotal mass boosted into orbit: 4618 kg; 1L22 Y Ariane V66KM8 @(1U" Ariane V661  '  GeneralTX A#R&Launch id94049h'  A#RNLaunch date10 Aug 1994 at 23:05 UTWX  A#R,Launch siteKourouQ h A#R Type4, 44LPR  A#R"Payload mass{-h 5 N#lZ*"cmvmPayloadA: Brasilsat B1B: Turksat 1B$ Y " ; 5  1]22  RAriane V67KY  8 @(1U" Ariane V671  '  GeneralT d A#R&Launch id94058g&  A#RLLaunch date9 Sep 1994 at 00:29 UTWd " A#R,Launch siteKourouP r A#RType4, 44PY"  A#R0Payload mass3300 kgcr .G#^8͵PayloadA: Telstar 402$ R" ; .12O2 hAAriane V68KR8 @(1U" Ariane V681  '  GeneralT]A#R&Launch id94065g& A#RLLaunch date8 Oct 1994 at 01:07 UTW]'@A#R,'@RLaunch siteKourouPw@A#RType4, 44LR'@@A#R"Payload mass{-w@DAN#lZ*L2GˉPayloadA: Solidaridad 2B: Thaicom 2$@hA" ; DAA122 AA^DAriane V69KhAA8 @(1U" Ariane V691 AB'  GeneralTAsBA#R&Launch id94070g&BBA#RLLaunch date1 Nov 1994 at 00:37 UTWsB1CA#R,Launch siteKourouPBCA#RType4, 42PY1CCA#R0Payload mass2924 kg`C:DG#^2(~PayloadA: Astra 1D$C^D" ; :DD1O22 DD?HAriane V70G^DD5 :&1U" Ariane V701 DE'  Generalg&DxEA#RLLaunch date1 Dec 1994 at 22:57 UTWEEA#R,Launch siteKourouPxEFA#RType4, 42PYExFA#R0Payload mass2985 kg_FFG#^0BhPayloadPanamsat 38xFVGG#^p  Failure cause3rd stage gave only 70% of its powerF?H% Boosters had been enhanced to transport the satellite which was 200 kilos heavier than normal maximal weight. The third stage was a H-10-3 type, first time used; this didn't cause the failure.; VGzH122zHH~KAriane V71G?HH5 :&1U" Ariane V711 zHH'  GeneralTHFIA#R&Launch id95016k*HIA#RTLaunch date28 Mar 1995 at 23:14:20 UTWFIJA#R,Launch siteKourouQIYJA#R Type4, 44LPRJJA#R"Payload mass@YJ:KO#n,#cPayloadA: Brasilsat B2B: Hotbird 1+1 meteo satellite?D J~K$ @Third stage was a H-10+ type; :KK12T2KLNAriane V72G~KL5 :&1U" Ariane V721 K1L'  GeneralTLLA#R&Launch id95021h'1LLA#RNLaunch date21 Apr 1995 at 01:44 UTWLDMA#R,Launch siteKourouOLMA#RType4, 40YDMMA#R0Payload mass2400 kgZMFNG#^&`QTPayloadERS 2O+MN$ VLast flight with a H-10+ type 3rd stage; FNN1423NOAriane V73GNO5 :&1U" Ariane V731 NHO'  GeneralTOOA#R&Launch id95023g&HOA#RLLaunch date17 May 1995 at 6:34 UONTWOfA#R,Launch siteKourouQA#R Type4, 44LPYfA#R0Payload mass4180 kgaqG#^4ĉPayloadIntelsat 706}$ Third stage was a H-10-3 type (second use) It increases the performance by 60 to 140 kg depending on the launcher version; qM1T2~3MAriane V74G5 :&1U" Ariane V741 Mł'  GeneralTA#R&Launch id95029h'łA#RNLaunch date10 Jun 1995 at 00:24 UTW؃A#R,Launch siteKourouP(A#RType4, 42PY؃A#R0Payload mass2934 kgZ(ۄG#^&〽9TPayloadDBS 3$" ; ۄ:13F3:Ariane V75G5 :&1U" Ariane V751 :'  GeneralTA#R&Launch id95033g&mA#RLLaunch date7 Jul 1995 at 16:23 UTWĆA#R,Launch siteKourouOmA#RType4, 40YĆlA#R0Payload mass2634 kg4U#zh8h휭fN#PayloadA: Hlios 1AB: CeriseC: UPMSat 1$l" ; T1~3)3TAriane V76G5 :&1U" Ariane V761 T̈'  GeneralT A#R&Launch id95040g&̈A#RLLaunch date3 Aug 1995 at 22:58 UTW މA#R,Launch siteKourouP.A#RType4, 42LYމA#R0Payload mass3043 kgb.G#^6ChPayloadA: Panamsat 4s2\A#Rd$Injection orbit485.2 km x 35934 km x 4.21 deg&# ; \1 F33܎Ariane V77G5 :&1U" Ariane V771 5'  GeneralTA#R&Launch id95044h'5A#RNLaunch date29 Aug 1995 at 06:41 UTWHA#R,Launch siteKourouPA#RType4, 44PYHA#R0Payload mass3398 kg`QG#^2) PayloadA: N Star Ae$A#RH GTO199 km x 35922 km x 6.96 deg&Q܎# ; 1))33^dAriane V78G܎^5 :&1U" Ariane V781 '  GeneralT^ A#R&Launch id95049 ܎h'tA#RNLaunch date24 Sep 1995 at 00:06 UTW A#R,Launch siteKourouPtA#RType4, 42LYtA#R0Payload mass3410 kgdG#^:㑑)PayloadA: Telstar 402Rh$t@D#XH GTO249.1 km x 35919 km x 7.03$d" ; @1 3z3Ariane V79Gd5 :&1U" Ariane V791 '  GeneralTkA#R&Launch id95055h'A#RNLaunch date19 Oct 1995 at 00:38 UTWk*A#R,Launch siteKourouPzA#RType4, 42LY*A#R0Payload mass3010 kg`z3G#^2(~PayloadA: Astra 1Eh$D#XH GTO485.5 km x 36077 km x 4.19$3" ; 1L33 A\Ariane V80GA5 :&1U" Ariane V801 r'  GeneralTAA#R&Launch id95062h'r.A#RNLaunch date17 Nov 1995 at 01:20 UTWA#R,Launch siteKourouP.A#RType4, 44PR'A#R"Payload mass[G#^(~PayloadA: ISOb!'A#RB GTO500 km x 71860 km x 5.25xT\$ Equipped with an H-10-III upper stage, but with the No. 02 type payload fairing.; 1@z33 Ariane V81G\5 :&1U" Ariane V811 '  GeneralTcA#R&Launch id95067g&A#RLLaunch date6 Dec 1995 at 23:23 UTWc!A#R,Launch siteKourouPqA#RType4, 44LY!A#R0Payload mass4296 kgw)qAN#lR*:eG@cPayloadA: Telecom 2CB: Insat 2C^A#R: GTO199.8 x 35976 km x 7N*A$ TTotal mass boosted into orbit: 4804 kg; (1!34 (oeAriane V82Go5 :&1U" Ariane V821 ('  GeneralToA#R&Launch id96002h'\A#RNLaunch date12 Jan 1996 at 23:10 UTWA#R,Launch siteKourouP\A#RType4, 44LY\A#R0Payload mass4368 kgx*N#lT*8MPayloadA: Panamsat 3RB: Measat 1a \AA#R@A GTO199.6 x 35992 km x 6.99$e" ; A134 Ariane V83Ge5 :&1U" Ariane V831 '  GeneralTlA#R&Launch id96007g&A#RLLaunch date5 Feb 1996 at 07:19 UTWl*A#R,Launch siteKourouPzA#RType4, 44PY*A#R0Payload mass3420 kg]z0G#^,* PayloadN Star B^A#R: GTO199.7 x 35952 km x 7$0" ; 144 4Ariane V84G45 :&1U" Ariane V841 e'  GeneralT4A#R&Launch id96015h'e!A#RNLaunch date14 Mar 1996 at 07:11 UTWxA#R,Launch siteKourouQ!A#R Type4, 44LPYx"A#R0Payload mass4175 kgaG#^4ĉPayloadIntelsat 707a "A#R@ GTO199.7 x 35913 km x 7.04$" ; C14d4CT Ariane V85G5 :&1U" Ariane V851 C'  GeneralTA#R&Launch id96022h'wA#RNLaunch date20 Apr 1996 at 10:36 UTWA#R,Launch siteKourouPw A#RType4, 42PYw A#R0Payload mass2855 kg[  G#^(LwPayloadMSAT 1^w 0 A#R: GTO199.5 x 35923 km x 7$ T " 10  1U  $T  " ;  14(4 +  Ariane V86G + 5 :&1U" Ariane V861 \ '  GeneralT+  A#R&Launch id96030h'\  A#RNLaunch date16 May 1996 at 01:56 UTW o A#R,Launch siteKourouP  A#RType4, 44LYo  A#R0Payload mass3952 kgt&  N#lL*^:93 PayloadA: Palapa C2B: Amos 1I  A#R GTO$  " ; 41 d4W44{]AAriane V87G {5 :&1U" Ariane V871 4'  GeneralT{A#R&Launch id96035h'hA#RNLaunch date15 Jun 1996 at 06:55 UTWA#R,Launch siteKourouPh@A#R@ Type4, 44PYt@A#R0Payload mass3420 kga@@G#^4ĉPayloadIntelsat 709d#t@9AA#RF GTO199.6 km x 35955 km x 6.99$@]A" ; 9AA1(4P4AADAriane V88G]AA5 :&1U" Ariane V881 AB'  GeneralRAbBA#R"Launch idn/ag&BBA#RLLaunch date4 Jun 1996 at 12:34 UT\bB%CA#R6Launch siteKourou ELA3K BpCA#RType5R%CCA#R"Payload mass\pCDG#^*_7ǥPayloadCluster<CZD' *O External resourceslEDD' http://www.esrin.esa.it/htdocs/tidc/Press/Press96/ariane5rep.html; ZDE1W404EHE2HAriane V89GDHE5 :&1U" Ariane V891 EyE'  GeneralTHEEA#R&Launch id96040g&yE4FA#RLLaunch date9 Jul 1996 at 11:24 UTWEFA#R,Launch siteKourouP4FFA#RType4, 44LYF4GA#R0Payload mass4360 kgy+FGN#lV*_鉂nvmPayloadA: Arabsat 2AB: Turksat 1Ca 4GHA#R@ GTO199.2 km x 35915 km x 7$G2H" ; HmH1P44mHHKAriane V90G2HH5 :&1U" Ariane V901 mHH'  GeneralTH9IA#R&Launch id96044g&HIA#RLLaunch date8 Aug 1996 at 22:49 UTW9IIA#R,Launch siteKourouPIGJA#RType4, 44LYIJA#R0Payload mass4200 kgx*GJKN#lT*oG;ePayloadA: Italsat 2B: Telecom 2Db!JzKA#RB GTO200 km x 35980 km x 5.52$KK" ; zKK104ڃ4K LNAriane V91GK L5 :&1U" Ariane V911 KQL'  GeneralT LLA#R&Launch id96054h'QL MA#RNLaunch date11 Sep 1996 at 00:00 UTWLdMA#R,Launch siteKourouP MMA#RType4, 42PRdMNA#R"Payload mass_MeNG#^0WR^ZPayloadEchostar 2d#NNA#RF GTO199.8 km x 35923 km x 6.97$eNN" ; N(O1&45(OoOmAriane V92GNoO5 :&1U" Ariane V921 (OO'  GeneralToO A#R&Launch id96063O Nh'OtA#RNLaunch date13 Nov 1996 at 22:40 UTW ˀA#R,Launch siteKourouPtA#RType4, 44LYˀtA#R0Payload mass4173 kgq#N#lF*`鉂PayloadArabsat 2BMeasat 2d#tIA#RF GTO249.6 km x 35885 km x 3.98$m" ; I1/ڃ45Ariane V93Gm5 :&1U" Ariane V931  '  GeneralTtA#R&Launch id97002h' ܃A#RNLaunch date30 Jan 1997 at 22:04 UTWt3A#R,Launch siteKourouP܃A#RType4, 44Lr13A#RbPayload mass4899 kg (4441 kg for satellites)r$gN#lH*rRUS_EPayloadA: GE 2B: Nahuel 1Ab!ɅA#RB GTO200 km x 36000 km x 7.01$g" ; Ʌ(15r5(oDAriane V94Go5 :&1U" Ariane V941 ('  GeneralToA#R&Launch id97009f%ZA#RJLaunch date1 Mar 1997 at 1:07 UTWA#R,Launch siteKourouPZA#RType4, 44PYZA#R0Payload mass3420 kgaG#^4ĉPayloadIntelsat 801e$Z A#RH GTO199.1 km x 35941 km x 6.978$D" ; 155ƉAriane V95GDƉ5 :&1U" Ariane V951 '  GeneralTƉKA#R&Launch id97016h'A#RNLaunch date16 Apr 1997 at 23:08 UTWK A#R,Launch siteKourouQ[A#R Type4, 44LPR A#R"Payload massu'["N#lN*HˉRPayloadA: Thaicom 3B: Bsat 1Ac"A#RD GTO199 km x 35,936 km x 6.99$"" ; 155+ Ariane V96G+5 :&1U" Ariane V961 \'  GeneralT+A#R&Launch id97031h'\A#RNLaunch date25 Jun 1997 at 23:44 UTWoA#R,Launch siteKourouPA#RType4, 44LRoA#R"Payload massarG#^4ĉPayloadIntelsat 802`ҏA#R> GTO200 km x 35,974 km x 7$r " ҏ ; ҏG1r5K5GxAriane V97G 5 :&1U" Ariane V971 G'  GeneralTA#R&Launch id97027g&zA#RLLaunch date3 Jun 1997 at 23:30 UTWA#R,Launch siteKourouPz!A#RType4, 44LYzA#R0Payload mass4079 kgy+!N#lV*,rGG@cPayloadA: Inmarsat 3F4B: Insat 2Da zTA#R@ GTO199.7 km x 35989 km x 7$x" ; T1K55Ariane V98Gx5 :&1U" Ariane V981 +'  GeneralTA#R&Launch id97040g&+A#RLLaunch date8 Aug 1997 at 06:45 UTW=A#R,Launch siteKourouPA#RType4, 44PY=A#R0Payload mass3420 kg_EG#^0EhPayloadPanamsat 6^A#R: GTO181 x 37143 km x 7.1$E" ; 155I.Ariane V99GI5 :&1U" Ariane V991 z'  GeneralTIA#R&Launch id97049g&z5A#RLLaunch date2 Sep 1997 at 22:21 UTWA#R,Launch siteKourouQ5A#R Type4, 44LPY6A#R0Payload mass3830 kgx*N#lT*յaPayloadA: Hotbird 3B: Meteosat 7\6 A#R6 GTO199 x 35948 km x 7$." < j15Q5jAriane V100H.5 :(1U" Ariane V1001 j'  GeneralT7A#R&Launch id97053h'A#RNLaunch date23 Sep 1997 at 23:58 UTW7A#R,Launch siteKourouPFA#RType4, 42LYA#R0Payload mass3455 kgaFG#^4ĉPayloadIntelsat 803\\A#R6 GTO249 x 35965 km x 7$" < \156Ariane V101H5 :(1U" Ariane V1011 5'  GeneralTA#R&Launch id97066h'5A#RNLaunch date30 Oct 1997 at 13:43 UT]NA#R8Launch siteKourou ELA 3K A#RType5RN A#R"Payload mass m*yC#VTPayloadA: Maqsat HB: Maqsat BC: YESz9 A#Rr GTO534 x 26631 km x 7.8 (instead of 581 x 36000 km)ry- (zPartial failure: the satellites were not injected in correct orbit. The EPC core stage shut down early (5 seconds) and had a roll control problem. The EAP solid boosters and the EPS final stage appear to have operated correctly.A dummy ballast mass replaced Phase 3D which was pulled off the mission because of a predicted rougher ride than originally specified.< 1Q56 Ariane V102H5 :(1U" Ariane V1021 G'  GeneralTA#R&Launch id97071h'GA#RNLaunch date12 Nov 1997 at 21:48 UTWZA#R,Launch siteKourouPA#RType4, 44LRZA#R"Payload massy+uN#lV*L M@PayloadA: Sirius 2B: Cakrawarta 1IA#R GTO$u" < 16t6!fM Ariane V103Hf5 :(1U" Ariane V1031 '  GeneralTfA#R&Launch id97075g&RA#RLLaunch date2 Dev 1997 at 22:53 UTWA#R,Launch siteKourouPRA#RType4, 44PRKA#R"Payload massu'N#lN*㊺2MPayloadA: Jcsat 5B: Equator SIK A#R GTOD M $ @Cyclade dual payload adapter<  16E6"   Ariane V104HM  5 :(1U" Ariane V1041  '  GeneralT V A#R&Launch id97083h'  A#RNLaunch date22 Dec 1997 at 00:16 UTWV  A#R,Launch siteKourouP e A#RType4, 42LY  A#R0Payload mass3455 kgae  G#^4ĉPayloadIntelsat 804a  A#R@ GTO249.7 x 35931 km x 6.98$  " <  1t66# ( 0@Ariane V105H ( 5 :(1U" Ariane V1051 Y '  GeneralT(  A#R&Launch id98006g&Y A#RLLaunch date4 Feb 1998 at 23:29 UTW kA#R,Launch siteKourouQA#R Type4, 44LPYkA#R0Payload mass3760 kg}/N#l^*$c-rGPayloadA: Brasilsat B3B: Inmarsat 3F5\ @A#R6 GTO199 x 36010 km x 7 @ $0@" < @l@1E66$l@@lCAriane V106H0@@5 :(1U" Ariane V1061 l@@'  GeneralT@9AA#R&Launch id98013h'@AA#RNLaunch date27 Feb 1998 at 22:38 UTW9AAA#R,Launch siteKourouPAHBA#RType4, 42PYABA#R0Payload mass2885 kg^HBBG#^.PayloadHotbird 4IBHCA#R GTO$BlC" < HCC16b6%CC[FAriane V107HlCC5 :(1U" Ariane V1071 C!D'  GeneralTCuDA#R&Launch id98017h'!DDA#RNLaunch date24 Mar 1998 at 01:46 UTWuD4EA#R,Launch siteKourouODEA#RType4, 40Y4EEA#R0Payload mass2750 kg[E7FG#^(㨇PayloadSpot 4$E[F" < 7FF16&FFIAriane V108H[FF5 :(1U" Ariane V1081 FG'  GeneralTFdGA#R&Launch id98024h'GGA#RNLaunch date28 Apr 1998 at 22:53 UTWdG#HA#R,Launch siteKourouPGsHA#RType4, 44PY#HHA#R0Payload mass3070 kgw)sHCIN#lR*WSPayloadA: Nilesat 101B: Bsat 1B^HIA#R: GTO199.4 x 35985 km x 7$CII" 7II1 *7'IJAthenaCI?J5 : " Athenae4IJ1 2h 㭄؉>ɉby Jean-Jacques Serralisting by Gunter Krebs?JM( Lockheed Launch Vehicle (LLV) or Lockheed-Martin Launch Vehicle (LMLV), later renamed AthenaThe first achievement of Lockheed Missiles & Space Co. in the large solid missiles category was in the late 50ies with the FBM (Fleet Ballistic Missile) Polaris program. Lockheed built all the US SLBM (Submarine-Launched Ballistic Missile): Polaris A1 (first fire i 1958), A2 (1960), A3 (1962), Poseidon C3 (1965), Trident-1 C4 (1977) and Trident-2 D5 (1987).In Jan 1993 Lockheed started designing a launch vehicle program aimed at light satellites (civilian and military). Those launchers are based on the existant solid boosters: Thiokol Castor 120, UTC/CSD Orbus 21 with eventually Thiokol Castor 4 boosters.\+J1 0W㻦ʼn ^ n ~ #Launch idPayloadLaunch date SiteTypeStatus (orbit in perigee x apogee x inc. x period)}i=#14]OO2  (ߎ؀ 02 PVX(^#""1n/aGemstar15 Aug 1995V1Failure: The first stage separated on time, but the rocket started oscillating a few secons earlier-Rj#4]OO2  (U02f npv"297044Lewis23 Aug 1997 at 06:51 UTV1289 x 603 km x 97.6 K=#z4]OO2  BDv "398001Lunar Prospector7 Jan 1998 at 02:28 UTC LC462`:j& t$Notes: V for Vandenberg, C for Cape Canaveral launches6 1?6C( AtlasB b5 : :" AtlasD * $4 㭄؉by Jean-Jacques SerrabW* "zOLaunchers operated by Lockheed Martin Launch Services, formerly General Dynamics. Since mid-1995 the launchers are marketed by ILS<' *O External resourcesCW։' 8http://www.lmco.com/ILS/sU z  mO{ 26 Origins of AtlasAtlas without top stageAtlas with an Agena stageAtlas with solid top stageK։, (>Oyj Atlas with a Centaur stage. * Origin: Inter Continental Ballistic Missile (ICBM) of first generationIn January 1955 the General Dynamics' Convair division was selected to build the Atlas system. In 1946 this firm was awarded a contract to design a 8000 km range ICBM: the MX-774. Three of those were launched in 1948 before the project was cancelled. Notheless those studies had lead to 3 major innovations: the engine with gimbaled nozzle, the monocoque structure and the releasable payload.ޏ+ $゜PIn the mid-50ies the problems related to high altitude ignition of liquid ergol engines were not solved. The only known solution was to ignite them all at takeoff: the Russians picked a bundle structure for their Semiorka while the Americans opted for a one-and-a-half stage vehicle. A main Rocketdyne LR105 sustainer of 670 kN was supported by 2 LR89 boosters. The propulsion bay containing 3 motors was named MA-1. Those engines consumed ergols (liquid oxygen and kerosene) provided by the same tanks. On each side a vernier LR101 rocket of 4.45 kN provided fine tuning of the thrust. The missile itself was 3.05 m diameter and 22.9 m in height (with an Mk2 Reentry Vehicle) and weighed over 110 tons.)- (ޏ'[IWOn 11 Jun 1957 for its first test, the missile was only propulsed by its lateral motors... but it failed. The first success occured at the third try, on 17 Dec 1957. On 2 Aug 1958 the first 3-motor Atlas (named version B) ranged over 4000 km and the nominal range was achieved on 28 Nov 1958 (version C). Less than a month later on 18 Dec 1958 Atlas was used for a space mission: Score.The propulsion system kept on evolving, first as a missile then as a space launcher. The first improved MA-2 was used for the Atlas-D ICBM. Then the MA-3 was introduced as a simplified version for the Atlas-E and -F ICBMs and derived launchers. The MA-5 was a civilian version of the MA-2; it was used by Atlas SLV-3 until the MA-5A version became available for Atlas-2.AޏT' 4 Atlas propulsion systemw#b[ylz  N    :< DesignationYear of first launchMain engine Thrust (kN)Main engine SI (sec.)Additional engines Thrust (kN)Additional engines SI (sec.)Application3T#,fylz&0<FHMA-119572402101335245Atlas A, B, C-#,Zylz&0<FHMA-219582552131375248Atlas D;p#,vylz&0<FHMA-319602552141470250Atlas E, F, launchers/M#,^ylz&0<FHMA-519612702201680259launchers0p+#,`ylz(2>HJMA-5A19912702201885264launchers+MV+ $=v퉂Atlas was equipped with the top stages of Thor Able -derived from those of Vanguard- in 1959. This launcher named Atlas Able was to launch the Pioneer probes to the Moon. But after 3 failures between November 1959 and December 1960 it was abandonned.4 +'  Statistics8V$ )Between 1956 and 1989, 189 MA-1/MA-2, 238 MA-3 and 213 MA-5 propulsion systems were manufactured that is 640 Atlas. The great majority of those Altas were used as ICBM. Thus the 150th Atlas was fired on 7 Nov 1962 and within those 150 rockets only 31 did launch satellites.11#)N jI mO{26yjAtlas[launch vehicle index]Origins of AtlasAtlas without top stageAtlas with an Agena stageAtlas with solid top stageAtlas with a Centaur stageH-1 8*- Atlas without top stageT5 :@ :" Atlas without top stageD-* $4 㭄؉by Jean-Jacques SerraW-* "['[IWThe Score experiment proved that Atlas could orbit payloads without any top stage. So it was decided to use it for the manned Mercury program, without major modifications. The Redstone rocket used for the first tests of this program wasn't powerful enough to orbit the 1300 kg Mercury spacecraft.P)l' R Atlas launches for the Mercury program7m#d* Y X K     $& <> l\ ln #Launch idPayloadLaunch dateTypeStatus (orbit in perigee x apogee x inc. x period)=l#:z* Y X K   24NPV1n/aMercury MA-129 Jul 1960DBallistic flight=#:z* Y X K   24NPV2n/aMercury MA-221 Feb 1961DBallistic flight=#:z* Y X K   24NPV3n/aMercury MA-325 Apr 1961DFailled to orbitF#:* Y X K   68RTZ461025Mercury MA-413 Sep 1961D161 x 256 x 32.8 x 88.4 X#:* Y X K   Z\vx~561033Mercury MA-5 (chimpanzee Enos)29 Nov 1961D150 x 242 x 32.6 x 88.3Q#:* Y X K   LNhjp662003Mercury MA-6 (J. Glenn)20 Feb 1962D161 x 263 x 32.5 x 88.6 U#:* Y X K   TVprx762019Mercury MA-7 (S. Carpenter)24 May 1962D161 x 268 x 32.5 x 88.5S#:* Y X K   PRlnt862052Mercury MA-8 (W. Schirra)03 Oct 1962D161 x 283 x 32.5 x 88.8R #:* Y X K   NPjlr963015Mercury MA-9 (G. Cooper)15 May 1963D161 x 267 x 32.5 x 88.7W- * $Z$Notes: All launches from Cape Canaveral< ? 1|7<+?  Atlas AgenaH  5 :( :" Atlas AgenaD?  * $4 㭄؉by Jean-Jacques Serra  8 >Ƿ-HǷ-HǷ-HThe Agena stage had been developped by Lockheed for the USAF. The first version featured a Bell 8096 motor (nitric acid/UDMH) of 67 kN. It couldn't be re-ignited unlike the Agena-B version introduced in 1960. Agena-D used a more powerful motor (71 kN) time double operational time. Those stages were all 1.52 m in diameter but had a variable length depending on the nature of the payload to which they were often integrated in.Most of the payloads had military missions:_ v   QdI tA7    6S8S㖯MZS- reconnaissance (Samos, KH 6 and KH 7)- early warning (Midas, Vela)- SIGINT (Canyon, Ryolithe)But Atlas Agena also launched:- lunar probes (Ranger, Lunar Orbiter) & planetary probes (Mariner)- target for the Gemini manned program (GATV, ATDA)- scientific (OAO, OGO, Seasat) and technology (Snapshot, ATS) satellites> ' . Atlas Agena launchesCzF@#b* Y ! g Y    $ : X h xz #Launch idPayloadLaunch dateSiteTypeStF@ atus (orbit in perigee x apogee x inclination x period)9EA#\r* Y ! g Y  *,FLN`1n/aMidas-0126 Feb 1960CAgena-AFailure6F@GB#hl* Y ! g Y  .24NTVh260006Midas 0224 May 1960CAgena-A1EA>C#\b* Y ! g Y  (*DJLP3n/aSamos 111 Oct 1960VFailure3GB7D#\f* Y ! g Y  ,.HNPb461001Samos 231 Jan 1961VAgena-B6>C9E#hl* Y ! g Y  .24NTVh561018Midas 0312 Jul 1961VAgena-BK7DJF#\* Y ! g Y  .0JPRd661021Ranger-123 Aug 1961CAgena-B169 x 502 x 32.9 x 90.689EHG#\p* Y ! g Y  (*DJL^7n/aSamos 309 Sep 1961VAgena-BFailure6JFJH#hl* Y ! g Y  .24NTVh861028Midas 0421 Oct 1961VAgena-BKHG[I#\* Y ! g Y  .0JPRd961032Ranger-218 Nov 1961VAgena-B158 x 237 x 33.3 x 88.39JHZJ#\r* Y ! g Y  *,FLN`10n/aSamos 422 Nov 1961VAgena-BFailureK[IkK#\* Y ! g Y  .0JPRd1161035Samos 522 Dec 1961VAgena-B244 x 702 x 89.6 x 91.1@ZJqL#\* Y ! g Y  02LRTf1262001Ranger-326 Jan 1962CAgena-BSolar orbitLkKM#\* Y ! g Y  02LRTf1362007Samos 6?07 Mar 1962VAgena-B249 x 635 x 90.9 x 93.97qLN#hn* Y ! g Y  .46PVXj1462010Midas 0509 Apr 1962VAgena-B@MO#\* Y ! g Y  02LRTf1562012Ranger-423 Apr 1962CAgena-BMoon impact GN#\* Y ! g Y  O TVpvx1662016KH 7 prototype? (FTV 2401)26 Apr 1962VAgena-B GO#\* Y ! g Y  TVpvx1762023KH 7 prototype? (FTV 2402)17 Jun 1962VAgena-B$^ւ#\* Y ! g Y  TVpvx1862030KH 7 prototype? (FTV 2403)18 Jul 1962VAgena-B184 x 236 x 96.1 x 88.7;׃#\v* Y ! g Y  .0JPRd19n/aMariner-122 Jul 1962CAgena-BFailure$^ւ#\* Y ! g Y  TVpvx2062035KH 7 prototype? (FTV 2404)05 Aug 1962VAgena-B205 x 205 x 96.3 x 88.6 D׃#\* Y ! g Y  24NTVh2162041Mariner-227 Aug 1962CAgena-BProbe to Venus@ #\* Y ! g Y  02LRTf2262055Ranger-518 Oct 1962CAgena-BSolar orbit"\-#\* Y ! g Y  TVpvx2362064KH 7 prototype? (FTV 2405)11 Nov 1962VAgena-B206 x 206 x 96 x 88.77 *#\n* Y ! g Y  &(BHJ\24n/aMidas17 Dec 1962VAgena-BFailure7--#hn* Y ! g Y  .46PVXj2563014Midas 0609 May 1963VAgena-B7**#\n* Y ! g Y  &(BHJ\26n/aMidas12 Jun 1963VAgena-DFailure6-,#hl* Y ! g Y  z҉24NTVh2763028KH 7-0112 Jul 1963VAgena-D7*/#hn* Y ! g Y  .46PVXj2863030Midas 0718 Jul 1963VAgena-BI,>#\* Y ! g Y  *,FLN`2963036KH7#206 Sep 1963VAgena-D168 x 263 x 94.4 x 89.1"\/`#\* Y ! g Y  DF`fhz3063039Vela Hotel-1/2 (+)17 Oct 1963CAgena-D107000 x 113000 x 38.3 x 6270 G>y#\* Y ! g Y  *,F`y LN`3163041KH7#325 Oct 1963VAgena-D144 x 332 x 99.1 x 89I`#\* Y ! g Y  *,FLN`3263051KH7#418 Dec 1963VAgena-D122 x 266 x 97.9 x 88.5Ay#\* Y ! g Y  02LRTf3364007Ranger-630 Jan 1964CAgena-BLunar impactT#\* Y ! g Y  @B\bdv3464009KH7#5 (OPS 2423)25 Feb 1964VAgena-D173 x 190 x 95.7 x 88.2T#\* Y ! g Y  @B\bdv3564012KH7#6 (OPS 3435)11 Mar 1964VAgena-D163 x 202 x 95.7 x 88.2U#\* Y ! g Y  @B\bdv3664020KH7#7 (OPS 3743)23 Apr 1964VAgena-D150 x 336 x 103.6 x 89.4U#\* Y ! g Y  @B\bdv3764024KH7#8 (OPS 3592)19 May 1964VAgena-D141 x 380 x 101.1 x 89.7$]#^* Y ! g Y  RTntv3864036KH7#9 (OPS 3684)OPS 492306 Jul 1964VAgena-D121 x 346 x 92.9 x 89.2;sX#`* Y ! g Y  tv3964040Vela 3 (OPS 3662)Vela 4 (OPS 3674)ERS 1317 Jul 1964CAgena-D98000 x 108000 x 39.6 x 6023@^#\* Y ! g Y  02LRTf4064041Ranger-728 Jul 1964CAgena-BMoon impact ZX~#\* Y ! g Y  PRlrt4164045KH7#10 (OPS 3802 + 3316)14 Aug 1964VAgena-D149 x 307 x 95.5 x 894^~#hh* Y ! g Y  }V.0JPRd4264054OGO 105 Sep 1964CAgena-BS~#\* Y ! g Y  BD^dfx4364058KH7#11 (OPS 4262)23 Sep 1964VAgena-D145 x 303 x 92.9 x 895~#\j* Y ! g Y  "$>DFX44n/aKH708 Oct 1964VAgena-DFailure"\#\* Y ! g Y  PRlrt4564068KH7#12 (OPS 4384 + 5063)23 Oct 1964VAgena-D139 x 271 x 95.6 x 88.6 C#\* Y ! g Y   24NTVh4664073Mariner-305 Nov 1964CAgena-DProbe to Mars C#\* Y ! g Y  24NTVh4764077Mariner-428 Nov 1964CAgena-DProbe to MarsS#\* Y ! g Y  BD^dfx4864079KH7#13 (OPS 4439)04 Dec 1964VAgena-D158 x 357 x 97 x 89.7V#\* Y ! g Y  BD^dfx4965005KH7#14 (OPS 4703)23 Jan 1965VAgena-D146 x 291 x 102.5 x 88.9@ #\* Y ! g Y  02LRTf5065010Ranger-817 Feb 1965CAgena-BMoon impactV)#\* Y ! g Y  BD^dfx5165019KH7#15 (OPS 4920)12 Mar 1965VAgena-D155 x 247 x 107.7 x 88.5@ /#\* Y ! g Y  02LRTf5265023Ranger-921 Mar 1965CAgena-BMoon impact0i)_#^* Y ! g Y  hj5365027SNAPSHOT (OPS 4682)Secor 4 (EGRS 4)03 Apr 1965VAgena-D1282 x 1313 x 90 x 111.6 Z/ #\* Y ! g Y  PRlrt5465031KH7#16 (OPS 4983 + 6717)28 Apr 1965VAgena-D180 x 259 x 95.6 x 89U_ #\* Y ! g Y  BD^dfx5565041KH7#17 (OPS 5236)27 May 1965VAgena-D149 x 267 x 95.8 x 88.7#]  #\* Y ! g Y  PRlrt5665050KH7#18 (OPS 6749 + 5501)25 Jun 1965VAgena-D151 x 283 x 107.6 x 88.85  #\j* Y ! g Y  "$>DFX57n/aKH712 Jul 1965VAgena-DFailure;s  #`* Y ! g Y  tv5865058Vela 5 (OPS 6577)Vela 6 (OPS 6564)ERS 1720 Jul 1965CAgena-D95000 x 107000 x 35.3 x 5148#] #\* Y ! g Y  PRlrt5965062KH7#19 (OPS 5698 + 6761)03 Aug 1965VAgena-D149 x 307 x 107.5 x 89.1U =@#\* Y ! g Y  BD^dfx6065076KH7#20 (OPS 6004)30=@  Sep 1965VAgena-D158 x 264 x 95.6 x 88.8<?A#\x* Y ! g Y  02LRTf61n/aAgena GATV25 Oct 1965CAgena-DFailure"\=@aB#\* Y ! g Y  PRlrt6265090KH7#21 (OPS 8293 + 6232)08 Nov 1965VAgena-D145 x 277 x 93.9 x 88.7"\?AC#\* Y ! g Y  PRlrt6366002KH7#22 (OPS 7253 + 3179)19 Jan 1966VAgena-D154 x 246 x 93.9 x 88.5'aaBD#\* Y ! g Y  ^`z6466012KH7#23 (OPS 1184 + 3011 + 3031)15 Feb 1966VAgena-D148 x 293 x 96.5 x 89PCE#\* Y ! g Y  8:TZ\n6566019Agena GATV-816 Mar 1966CAgena-D285 x 298 x 28.9 x 90.2![DF#\* Y ! g Y  PRlrt6666022KH7#24 (OPS 0879 + 0974)18 Mar 1966VAgena-D152 x 284 x 101 x 88.94EG#hh* Y ! g Y  ?vV.0JPRd6766031OAO 108 Apr 1966CAgena-DTFH#\* Y ! g Y  BD^dfx6866032KH7#25 (OPS 0910)19 Apr 1966VAgena-D145 x 398 x 117 x 89.9#]GJ#\* Y ! g Y  PRlrt6966039KH7#26 (OPS 1950 + 6785)14 May 1966VAgena-D133 x 358 x 110.6 x 89.4>H"K#\|* Y ! g Y  46PVXj70n/aAgena GATV-917 May 1966CAgena-DFailure DJ,L#\* Y ! g Y $&@FHV66046ATDA01 Jun 1966Cmodel292 x 296 x 28.9 x 90.2 Z"KLM#\* Y ! g Y  PRlrt7166048KH7#27 (OPS 1577 + 1856)03 Jun 1966VAgena-D143 x 288 x 87 x 88.94,LLN#hh* Y ! g Y  }V.0JPRd7266049OGO 307 Jun 1966CAgena-B7LMOO#hn* Y ! g Y  .46PVXj7366051Midas 0809 Jun 1966VAgena-DULNv#\* Y ! g Y  BD^dfOOv x7466062KH7#28 (OPS 1850)12 Jul 1966VAgena-D137 x 236 x 95.5 x 88.3QOO#\* Y ! g Y  :<V\^p7566065Agena GATV-1018 Jul 1966CAgena-D290 x 296 x 28.9 x 90.2 Gv#\* Y ! g Y  >@Z`bt7666073Lunar Orbiter 110 Aug 1966CAgena-DLunar orbit"\#\* Y ! g Y  PRlrt7766074KH7#29 (OPS 1832 + 6810)16 Aug 1966VAgena-D146 x 358 x 93.3 x 89.67#hn* Y ! g Y  .46PVXj7866077Midas 0919 Aug 1966VAgena-DQօ#\* Y ! g Y  :<V\^p7966080Agena GATV-1112 Sep 1966CAgena-D298 x 298 x 28.8 x 90.3 Z#\* Y ! g Y  PRlrt8066083KH7#30 (OPS 1686 + 6874)16 Sep 1966VAgena-D148 x 333 x 94 x 98.47օ#hn* Y ! g Y  c-46PVXj8160089Midas 1005 Oct 1966VAgena-D,e%#^* Y ! g Y  fh8266090KH7#31 (OPS 2055)SGLS 1 (OPS 5345)12 Oct 1966VAgena-D181 x 258 x 90.9 x 89 ZE#\* Y ! g Y  PRlrt8366098KH7#32 (OPS 2070 + 5424)02 Nov 1966VAgena-D159 x 305 x 91 x 89.2 G%R#\* Y ! g Y  >@Z`bt8466100Lunar Orbiter 206 Nov 1966CAgena-DLunar orbitQEi#\* Y ! g Y  :<V\^p8566103Agena GATV-1211 Nov 1966CAgena-D243 x 310 x 28.8 x 89.9VR#\* Y ! g Y  BD^dfx8666109KH7#33 (OPS 1890)05 Dec 1966VAgena-D137 x 388 x 104.6 x 89.84i#hh* Y ! g Y  S.0JPRd8766110ATS 107 Dec 1966CAgena-DT#\* Y ! g Y  BD^dfx8867007KH7#34 (OPS 4399)02 Feb 1967VAgena-D136 x 357 x 103 x 89.5 G#\* Y ! g Y   >@Z`bt8967008Lunar Orbiter-305 Feb 1967CAgena-DLunar orbitL#\* Y ! g Y  *,FLN`9067031ATS-206 Apr 1967CAgena-D178 x 11124 x 28.4 x 218.9 G#\* Y ! g Y  >@Z`bt9167041Lunar Orbiter 404 May 1967CAgena-DLunar orbit"\#\* Y ! g Y  PRlrt9267050KH7#35 (OPS 4321 + 5557)22 May 1967VAgena-D135 x 292 x 91.5 x 88.4V#\* Y ! g Y  BD^dfx9367055KH7#36 (OPS 4360)04 Jun 1967VAgena-D149 x 456 x 104.9 x 90.6A#\* Y ! g Y  24NTVh9467060Mariner-514 Jun 1967CAgena-DVenus probe G)#\* Y ! g Y  >@Z`bt9567075Lunar Orbiter 501 Aug 1967CAgena-DLunar probe4)#hh* Y ! g Y  S.0JPRd9667111ATS 305 Nov 1967CAgena-D4))#hh* Y ! g Y  }V.0JPRd9768014OGO 504 Mar 1968CAgena-DS)B#\* Y ! g Y  FHbhj|9868063Canyon 1 (OPS 2222)06 Aug 1968CAgena-D31680 x 39860 x 9.9S)[#\* Y ! g Y  FHbhj|9969036Canyon 2 (OPS 3148)13 Apr 1969CAgena-D31680 x 39860 x 9.9VBw#\* Y ! g Y LNhnp10070046Rhyolite 1 (OPS 5346)19 Jun 1970CAgena-D31680 x 39860 x 9.9N[#\* Y ! g Y HJdjl~10170069Canyon 3 (OPS 7329)01 Sep 1970CAgena-D31680 x 39860;w#\v* Y ! g Y .0JPRd102n/aCanyon 404 Dec 1971CAgena-DFailureA#\* Y ! g Y HJdjl~10372101Canyon 5 (OPS 9390)20 Dec 1972CAgena-DJ#\* Y ! g Y  24NTVh10473013Canyon 606 Mar 1973CAgena-D32100 x 39660 x 10.1 F#\* Y ! g Y LNhnp10575055Rhyolite 2 (OPS 4966)18 Jun 1975CAgena-DGEO D#\* Y ! g Y HJdjl~10677038Canyon 7 (OPS 9751)23 May 1977CAgena-DGEO)c#\* Y ! g Y LNhnp10777114Rhyolite 3 (OPS 4258)11 Dec 1977CAgena-DFailure: 146 x 188 x 29.9 x 87.9 F#\* Y ! g Y LNhnp10878038Rhyolite 4 (OPS 8790)07 Apr 1978CAgena-DGEOM#h* Y ! g Y 㖯24NTVh10978064Seasat26 Jul 1978VAgena-D769 x 799 x 108 x 100.7a* $$Notes: in the launcher date & site column C stands for Cape Canaveral and V for Vandenberg.11W,#IT+#) "VȠ$To view this page you need to register&I# K#1C8_>-W Atlas with solid top stage^)I5 :T :" Atlas with a solid fuel top stagee4W1 2h 㭄؉>ɉby Jean-Jacques Serralisting by Gunter Krebsg) > JS?Tɑ9l̑Some Atlas missiles were reconverted in space launchers by addition of solid fuel top stages. OV-1, the first of these programs enabled to orbit two LEO 1.2 tons satellites. 11 flights took place between 1965 and 1971, with 2 or 3 OV-1 stages.The Star-37S booster was used to launch meteorology satellites: civilians (Tiros N and 10 NOAAs) and military (8 DMSPs) between 1978 and 1995. This motor with 658 kg powder provided 43.5 KN thrust during 42 seconds. A similare motor (Star-37E ?) was used for 4 NOSS payloads between 1976 and 1980.> W 1 0SSThe 2-stage SGS-1 from McDonnell Douglas was used from 1977 to 1981 to launch 8 navigation satellites (NTS 2 and 7 of the first Navstars) SGS-1 weighed 2.5 tons and features 2 Star-37N motors providing each 68.8 kN thrust during 42 seconds. The next generation, SGS-2, weighed 4.5 tons. It featured two Star-48 motors providing each 66.7 kN during 87 seconds. It launched the 4 last preo-operational Navstars. Those two 2-stage launchers could orbit 460 and 860 kg respectively in a 250/21000 km, 63 transfert orbit. - (m&[+A few specific configurations were also reported. Thus the STP program made use of Atlas with Burner 2 twice, of the Star-17A and of the Altair-3 (Star-20). NTS 1 was launched with a PTS top stage, and Solsat & Geosat with OIS stages. No information is available on the Atlas H top stages which launched 5 payloads betwee 1983 and 1987.The last launch occured in March 1995 and Titan-2 will take over the launch of those payloads.M& ,' L Atlas with solid top stage launches,zd@#4c Y   $:Xhj#Launch idPayloadLaun,d@Ich dateTypeStatus/Comment (orbit in perigee x apogee x inclination x period)V,vA#Hc Y   "jl1, 172Dn/aOV1-1ABRES 6 (reentry experiment)21 Jan 1965D OV1Failure8d@iB#Fpc Y   .0JLZ2, 68Dn/aOV1-327 May 1965D OV1Failure QvAvC#Hc Y  "$oZ0rt3, 34D65078OV 1-02SSP 29 (reentry experiment)05 Oct 1965D OV1?iBwD#T~c Y  "*$qZ0rZ0NPjlz4, 72D66025OV 1-04OV 1-0530 Mar 1966D OV1(fvCE#Tc Y  "$uZ0FHbdr5, 58D66063OV 1-08OV1-714 Jul 1966D OV1Partial failure: OV1-7 didn't reach orbit?wDF#T~c Y  "*$vZ0Z0NPjlz6, 89D66111OV 1-09OV 1-1011 Dec 1966D OV1'lEG#Fc Y  "$PRln|7, 92D67072OV 1-11 /1-12 / 1-8627 Jul 1967D OV1Partial failure: OV1-11 didn't reach orbit@FH#Tc Y  $*&Z0Z0PRln|8, 107F68026OV 1-13OV 1-1406 Apr 1968F OV1QGI#<c Y  "$rt9, 75F68059OV1-16 (Spades)OV1-17 (Cannonball 1)11 Jul 1968F OV1HuK#Xc Y  "$" 10, 7004n/aSTP, 10 satellites:Orbiscal 1OV5-8Gridsphere 1 & 2Mylar Ballon 1Rigidsphere 1 & 2+ 3 more16 Aug 1968SLV3 Burner2Failure: the vehicle was destroyed due to a collapse of the payload fairingZIL#Lc Y  &"(Z011, 104F69025OV1-17OV1-18OV 1-19OV1-17A (Orbiscal 2)18 Mar 1969F OV1IuKM#Rc Y  $(&Z0ހ 12, 76F71067OV 1-20OV 1-21Rigidsphere 1 & 2Gridsphere 1 & 2Cannonball 2MusketballMylar Balloon07 Aug 1971F OV1^LN#:c Y  &(VXrt13, 102F72076STP (Radcat + Radsat)02 Oct 1972F Burner2530 x 750 x 98.4 x 99.5JM #:c Y  $&46PR`14, 69F74054NTS-114 Jul 1974F PTS21600 x 22200 x 63 x 720N IDN #Fc Y   "<>XZr15, 71Fn/aSTP (P72-2)12 Apr 1975F Star-17AFailure; #Fvc Y  $&X~<>XZr16, 59F76038NOSS 0130 Apr 1976F Star-37EK #:c Y  $&46PRb17, 65F77053NTS-224 Jun 1977F SGS120300 x 20300 x 63 x 720;#Fvc Y  $&X~<>XZr18, 50F77112NOSS 0208 Dec 1977F Star-37E9#Frc Y  $&cZ@B\^n19, 64F78020GPS BI-0122 Feb 1978F SGS19߅#Frc Y  $&cZ@B\^n20, 49F78047GPS BI-0213 May 1978F SGS19ӆ#Frc Y  $&cZ@B\^n21, 47F78093GPS BI-0307 Oct 1978F SGS1U߅#Fc Y  $&?<>XZz22, 29F78096Tiros N13 Oct 1978F Star-37S ISS846 x 862 x 98.9 x 1029ӆ׈#Frc Y  $&cZ@B\^n23, 39F78112GPS BI-0411 Dec 1978F SGS16ȉ#Flc Y  $&Acى<>XZh24, 27F79017Solwind24 Feb 1979F OIS>׈#F|c Y  $& {<>XZx25, 25F79057NOAA 0627 Jun 1979F Star-37SISS9ȉ#Frc Y  $&cZ@B\^n26, 35F80011GPS BI-0509 Feb 1880F SGS1;#Fvc Y  $&X~<>XZr27, 64F80019NOSS 0303 Mar 1980F Star-37E9#Frc Y  $&cZ@B\^n28, 34F80032GPS BI-0626 Apr 1980F SGS1>#F|c Y  $&:<VXx29, 19F80043NOAA B29 May 1980F Star-37S ISSB#Rc Y   "X~8:TVn30, 68En/aNOSS 0408 Dec 1980E Star-37EFailure?#F~c Y  $I& {<>XZz31, 87F81059NOAA 0723 Jun 1981F Star-37S ISS@#Rc Y   "cZ<>XZj32, 76En/aGPS BI-0718 Dec 1981E SGS1Failure^#:c Y  $&JLfh33, 60E82118DMSP/Block-5D2#121 Dec 1982E Star-37S ISS815 x 828 x 98.8 x 101.24#Fhc Y  (*X~@B\^d34, 6001H83008NOSS 0509 Feb 1983H?#F~c Y  $& {<>XZz35, 73E83022NOAA 0828 Mar 1983E Star-37S ISS4#Fhc Y  (*X~@B\^d36, 6002H83056NOSS 0609 Jun 1983H9#Frc Y  $&cZ@B\^n37, 75E83072GPS BI-0814 Jul 1983E SGS2^#:c Y  $&JLfh38, 58E83113DMSP/Block-5D2#217 Nov 1983E Star-37S ISS823 x 835 x 98.7 x 101.44#Fhc Y  (*X~@B\^d39, 6003H84012NOSS 0705 Feb 1984H9w#Frc Y  $&cZ@B\^n40, 42E84059GPS BI-0913 Jun 1984E SGS29k#Frc Y  $&acZ@B\^n41, 14E84097GPS BI-1008 Sep 1984E SGS2?we#F~c Y  $& {<>XZz42, 39E84123NOAA 0912 Dec 1984E Star-37S ISSMkg#:c Y  $&8:TVd43, 41E85021Geosat 12 Mar 1985E OIS757 x 814 x 108.1 x 100.69e[#Frc Y  $&XcZ@B\^n44, 55E85093GPS BI-1109 Oct 1985E SGS24gJ#Fhc Y  (*X~@B\^d45, 6004H86014NOSS 0809 Feb 1986H?[D#F~c Y  $&b {<>XZz46, 52E86073NOAA 1017 Sep 1986E Star-37S ISS4J?#Fhc Y  (*X~@B\^dD?I47, 6005H87043NOSS 0915 May 1987HCD=#Fc Y  $&㧢щDF`b48, 59E87053DMSP B5D2-320 Jun 1987E Star-37S ISS^?P#:c Y  $&JLfh49, 54E88006DMSP/Block-5D2#403 Feb 1988E Star-37S ISS820 x 830 x 98.7 x 101.5?=J#F~c Y  $&Y {<>XZz50, 63E88089NOAA 1124 Sep 1988E Star-37S ISS XPW#:c Y  $&NPjl51, 28E90031Stacksat/P87-2 (3)11 Apr 1990E Altair-3760 x 780 x 90 x 100^Jj#:c Y  $&JLfh52, 61E90105DMSP/Block-5D2#501 Dec 1990E Star-37S ISS730 x 850 x 98.9 x 100.7?Wd#F~c Y  $&Z {<>XZz53, 50E91032NOAA 1214 May 1991E Star-37S ISS\ju#:c Y  $&JLfh54, 53E91082DMSP/Block-5D2#628 Nov 1991E Star-37S ISS840 x 860 x 98.9 x 102?do#F~c Y  $&[ {<>XZz55, 34E93050NOAA 1309 Aug 1993E Star-37S ISSCum #Fc Y  $&㫢щDF`b56, 20E94057DMSP B5D2-729 Aug 1994E Star-37S ISS?og #F~c Y  $&\ {<>XZz57, 11E94089NOAA 1430 Dec 1994E Star-37S ISSCm e #Fc Y  $&㬢щDF`b58, 45E95015DMSP B5D2-824 Mar 1995E Star-37S ISST*g  * $T$Notes: All launches from Vandenberg.> e  1<.  J!Atlas CentaurJ A 5 :,b" Atlas Centaure4  1 2h 㭄؉>ɉby Jean-Jacques Serralisting by Gunter KrebsZA 88 > 㯃4㯃4The Atlas Centaur launchers are the most powerful versions in the Atlas familly and the only to be used since 1995. They use the Centaur top-stage which was the first cryogenic rocket stage.The Pratt & Whitney RL10 engine consuming liquid oxygen and hydrogen had a long and difficult development. Its design started in 1958. It first flew in 1962 but didn't launch a real payload before 1966. The Centaur stage was designed to be used by Atlas. It had the same diameter and was 9.1 m long. In its operational version it was equipped with two RL10 A-3-3 engines with a thrust of 66.7 kN each.6 zA3 4K\K\In the late-70ies the total height of the Atlas Centaur reached 40 m (originally 34 m) and its mass at launch increased from 132 to 150 tons. At th8zA is time the launch program was to be abandonned since NASA had decided to transfer all launches to the Shuttle. In fact STS was less available than expected and the Atlas launch program was resumed with a simplified motor: the RL10 A-3-3A with 73.4 kN thrust which first flew in 1984.During its first activity period (see chart 6) the Atlas Centaur launched:O8D[   6S9 MZSCIx\do2- probes to the Moon (Surveyor) and to other planets (Marnier, Pioneer)- heavy scientific satellites (OAO, HEAO)- geostationary telecommunication satellites (ATS, Intelsat, Comstar, Fleetsatcom)In 1987 the augmented Atlas Centaur was selected by the USAF as the MLV2 standard launcher. This new launcher is refered to as Atlas-2 and the former version as Atlas-1. The basic Atlas-2 is an Atlas Centaur which has a 2.7 m longer first stage and a 0.9 m longer second stage. Furthermore the first stage is equipped with the new MA-5A motors. Atlas-2A is different by its second stage RL10 A-4 engines with deployable nozzle. Those rockets range from 45.6 to 47.5 m high and weigh 187 tons (Atlas-1 was 42-44 m high and weigh 164 tons).zAzF- ( _ 0Atlas-2AS is still more powerful. It is made from Atlas-2A to which two pairs of Castor-4A boosters of 436 kN thrust each are added. Each pair ignites one after the other. Thus Atlas-2A weighs 234 tons and can deliver 3.6 tons in GTO compared to 2.7 and 2.9 tons for Atlas-2 and -2A, and 2.3 tons for Atlas-1.Atlas Centaur rockets are optimized for geostationary orbit satellites.4 DF' O StatisticsnKzFG# The RL-10 motor made its 100th flight on the top stage Centaur of AC-114@F\G' 2 Atlas Centaur launchesfGH# zY / u   $&<>\l|~#Launch idPayloadLaunch DateSiteTypeStatus/Comment (orbit in perigee x apogee x inclination x period)<p\GI#hzY / u  "$FHbhj~1, AC001n/asuborbital test08 May 1962CLV3C C-AFailure because of collapse of payload shroudQHK#\zY / u  &(46PVXl2, AC00263047test27 Nov 1963CLV3C C-B544 x 1699 x 30.3 x 170.5 TI5L#hzY / u  "$02LRTh3, AC003n/atest30 Jun 1964CLV3C C-CHydraulic failure in Centaur-gKbM#\zY / u  &(df4, AC00464082test (Surveyor Mass Model 1)11 Dec 1964CLV3C C-C165 x 178 x 30.7 x 87.8,`5LN#hzY / u  "$BD^dfz5, AC005n/aSurveyor SD 102 Mar 1965CLV3C C-CFailure: exploded on launch padLbMO#\zY / u  &(FHbhj~6, AC00665064Surveyor SD 211 Aug 1965CLV3C C-DSolar orbit-gNـ#\zY / u  Oـ &(df7, AC00866030test (Surveyor Mass Model 2)08 Apr 1966CLV3C C-D175 x 334 x 30.7 x 89.5XO#\zY / u  &(@B\bdx8, AC01066045Surveyor-130 May 1966CLV3C C-DPayload landed on the Moon Zـ#\zY / u  &(@B\bdx9, AC00766084Surveyor-220 Sep 1966CLV3C C-DPayload impacted on the Moon)c@#\zY / u  (*fh10, AC00966095test (Surveyor Mass Model 3)26 Oct 1966CLV3C C-D200 x 47000 x 22.9Y_#\zY / u  (*BD^dfz11, AC01267035Surveyor-317 Apr 1967CLV3C C-DPayload landed on the Moon![@#\zY / u  (*BD^dfz12, AC01167068Surveyor-414 Jul 1967CLV3C C-DPayload impacted on the Moon Z_#\zY / u  (*BD^df|13, AC01367084Surveyor-508 Sep 1967CSLV3C C-DPayload landed on the Moon Z#\zY / u  (*BD^df|14, AC01467112Surveyor-607 Nov 1967CSLV3C C-DPayload landed on the Moon Z#\zY / u  (*BD^df|15, AC01568001Surveyor-707 Jan 1968CSLV3C C-DPayload landed on the Moon3g#hzY / u  (*8:TZ\r16, AC01768068ATS-410 Aug 1968CSLV3C C-DFailure: Centaur failed on second ignition =#hzzY / u  (*?vV<>X^`v17, AC01668110OAO 207 Dec 1968CSLV3C C-DI+#\zY / u  (*@B\bdz18, AC02069014Mariner-625 Feb 1969CSLV3C C-DMars probeI:#\zY / u  (*@B\bdz19, AC01969030Mariner-727 Mar 1969CSLV3C C-DMars probe =+C#hzzY / u  (*S<>X^`v20, AC01869069ATS 512 Aug 1969CSLV3C C-D9g:#tzY / u  $&?vV8:TZ\C r21, AC021n/aOAO 330 Nov 1970CSLV3C C-DFailure: payload shroud failed to seperateDC#hzY / u  (*ĉJLfln22, AC02571006Intelsat 40226 Jan 1971CSLV3C C-D,`#hzY / u  $&<>X^`v23, AC024n/aMariner-808 May 1971CSLV3C C-DFailure: Centaur guidance failureI#\zY / u  (*@B\bdz24, AC02371051Mariner-930 May 1971CSLV3C C-DMars probeD#hzY / u  (*ĉJLfln25, AC02671116Intelsat 40320 Dec 1971CSLV3C C-DD#hzY / u  (* ĉJLfln26, AC02872003Intelsat 40423 Jan 1972CSLV3C C-DV#\zY / u  (*BD^df27, AC02772012Pioneer-1003 Mar 1972CSLV3C C-D Star-37EJupiter probeD#hzY / u  (*!ĉJLfln28, AC02972041Intelsat 40513 Jun 1972CSLV3C C-D =(#hzzY / u  (*?vV<>X^`v29, AC02272065OAO 321 Aug 1972CSLV3C C-D'aO#\zY / u  (*BD^df30, AC03073019Pioneer-1106 Apr 1973CSLV3D C-D1A Star-37EJupiter & Saturn probeF(a#hzY / u  (*#ĉJLfln31, AC03173058Intelsat 40723 Aug 1973CSLV3D C-D1AYO#\zY / u  (*BD^df32, AC03473085Mariner-1003 Nov 1973CSLV3D C-D1AVenus and Mercury probeFa#hzY / u  (*$ĉJLfln33, AC03274073Intelsat 40821 Nov 1974CSLV3D C-D1ALz#tzY / u  $&"ĉFHbhj34, AC033n/aIntelsat 40620 Feb 1975CSLV3D C-D1AFailure: 1st stage failes due to electrical shortcutF #hzY / u  (*ĉJLfln35, AC03575042Intelsat 40122 May 1975CSLV3D C-D1A  H  #hzY / u  (* LNhnp36, AC03675091Intelsat 4A0126 Sep 1975CSLV3D C-D1ARH 4 #hzY / u  (* LNhnp37, AC03776010Intelsat 4A0229 Jan 1976CSLV3D C-D1ARD  D #hzY / u  (*XLXDF`fh38, AC03876042Comstar 113 May 1976CSLV3D C-D1ARD4 T #hzY / u  (*YLXDF`fh39, AC04076073Comstar 222 Jul 1976CSLV3D C-D1ARHD h #hzY / u  (* LNhnp40, AC03977041Intelsat 4A0426 May 1977CSLV3D C-D1AR AT u #hzY / u  (*ڰFI>@Z`b~41, AC04577075Heao 112 Aug 1977CSLV3D C-D1ARHvh  #tzY / u  $& HJdjl42, AC043n/aIntelsat 4A0530 Sep 1977CSLV3D C-D1ARFailure: Atlas boostersection turbopump failedHu  #hzY / u  (* LNhnp43, AC04678002Intelsat 4A0307 Jan 1978CSLV3D C-D1ARH  #hzY / u  (*>>ቂLNhnp44, AC04478016Fleetsatcom 109 Feb 1978CSLV3D C-D1ARH  #hzY / u  (* LNhnp45, AC04878035Intelsat 4A0631 Mar 1978CSLV3D C-D1AR6p / #\zY / u  (*fh46, AC05078051Pioneer-12 (Pioneer Venus-1)20 May 1978CSLV3D C-D1ARProbe to Venus, Venus orbitD ? #hzY / u  (*ZLXDF`fh47, AC04878068Comstar 329 Jun 1978CSLV3D C-D1AR6p/ u #\zY / u  (*fh48, AC05178078Pioneer-13 (Pioneer Venus-2)08 Aug 1978CSLV3D C-D1ARProbe to Venus: soil module A?  #hzY / u  (*۰FI>@Z`b~49, AC05278103Heao 213 Nov 1978CSLV3D C-D1ARHu @ #hzY / u  (*?>ቂ @  LNhnp50, AC04779038Fleetsatcom 204 May 1979CSLV3D C-D1AR A A #hzY / u  (*ܰFI>@Z`b~51, AC05379082Heao 320 Sep 1979CSLV3D C-D1ARH@ B #hzY / u  (*@>ቂLNhnp52, AC04980004Fleetsatcom 318 Jan 1980CSLV3D C-D1ARHA C #hzY / u  (*A>ቂLNhnp53, AC05780087Fleetsatcom 431 Oct 1980CSLV3D C-D1ARGB D #hzY / u  (*WĉJLfln54, AC05480098Intelsat 50206 Dec 1980CSLV3D C-D1ARDC E #hzY / u  (*[LXDF`fh55, AC04281018Comstar 421 Feb 1981CSLV3D C-D1ARGD  G #hzY / u  (*VĉJLfln56, AC05681050Intelsat 50123 May 1981CSLV3D C-D1ARHE !H #hzY / u  (*B>ቂLNhnp57, AC05981073Fleetsatcom 506 Aug 1981CSLV3D C-D1ARG G 4I #hzY / u  (*XĉJLfln58, AC05581119Intelsat 50315 Dec 1981CSLV3D C-D1ARG!H GJ #hzY / u  (*YĉJLfln59, AC05882017Intelsat 50404 Mar 1982CSLV3D C-D1ARG4I ZK #hzY / u  (*ZĉJLfln60, AC06082097Intelsat 50528 Sep 1982CSLV3D C-D1ARGGJ mL #hzY / u  (*[ĉJLfln61, AC06183047Intelsat 50619 May 1983CSLV3D C-D1ARHvZK M #tzY / u  (*^ĉJLfln62, AC06284057Intelsat 50909 Jun 1984CG C-D1ARPartial failure: Centaur LOX-tank exploded on LEOCmL N #hzY / u  (*ĉJLfln63, AC06385025Intelsat 51022 Mar 1985CG C-D1ARCM O #hzY / u  (*ĉJLfln64, AC06485055Intelsat 51130 Jun 1985CG C-D1ARCN  #hzY / O   u  (*ĉJLfln65, AC06585087Intelsat 51229 Sep 1985CG C-D1ARDO  #hzY / u  (*D>ቂLNhnp66, AC06686096Fleetsatcom 705 Dec 1986CG C-D1AR9g 7 #tzY / u  $&C>ቂHJdjl67, AC067n/aFleetsatcom 626 Mar 1987CG C-D1ARFailure because of lightning strikeD G #hzY / u  (*E>ቂLNhnp68, AC06889077Fleetsatcom 825 Sep 1989CG C-D1ARK7 X #\zY / u  (*8:TZ\b69, AC06990065CRRES25 Jul 1990C1330 x 33600 x 18.1 x 591[G  #zY / u  "!{(*㉂PR70, AC070n/aYuri 3H (BS 3H)19 Apr 1991 at 23:30 UTC1Failure: one of the two Centaur engines didn't igniteOX · #hzY / u  (*JL~71, AC10291083Eutelsat 2F307 Dec 1991 at 22:47 UTC2 (8102)J  #hzY / u  (*ceMDFx~72, AC10192006DSCS 3-0511 Feb 1992 at 00:41 UTC2 IABS8·  #hpzY / u  (*;upBD^dfl73, AC07292013Galaxy 514 Mar 1992C1G  #hzY / u  (*ƉFHz74, AC10592032Intelsat K10 Jun 1992 at 00:00 UTC2AJ  #hzY / u  (*ceMDFx~75, AC10392037DSCS 3-0602 Jul 1992 at 21:54 UTC2 IABS6d G #tzY / u  $&-PRlrtz76, AC071n/aGalaxy 1R failure22 Jul 1992C1Failure: 3rd stage failed to ignite4V { #zY / u  "!{,.|W@Btz|(!{77, AC07493015UHF 125 Mar 1993 at 22:48 UTC1Partial failure >G  #h|zY / u  (*ceMDF`fhx78, AC10493046DSCS 3-0719 Jul 1993C2 IABS A{  #hzY / u  (*|W   <>pvx~79, AC07593056UHF 203 Sep 1993 at 11:17 UTC1 >  #h|zY / u  (*ceMDF`fhx80, AC10693074DSCS 3-0828 Nov 1993C2 IABSI  #hzY / u  (*͵HJ|81, AC10893077Telstar 40116 Dec 1993 at 00:40 UTC2ASG  #hzY / u  (*.@Bt82, AC07394022Goes 0813 Apr 1994 at 06:44 UTC 36B1E  #hzY / u  (*|W<>p~83, AC07694035UHF 324 Jun 1994 at 13:50 UTC 36B1F  #hzY / u  (*9T<>p~84, AC10794047DBS 203 Aug 1994 at 23:57 UTC 36A2AN  #hzY / u  (*ĉJL~85, AC11194064Intelsat 70306 Oct 1994 at 06:35 UTC 36B2ASH ! #hzY / u  (*R*@Bt86, AC11094079Orion 123 Nov 1994 at 10:21 UTC 36A2AJ 7 #hzY / u  (*ĉJL~87, AC11395001Intelsat 70410 Jan 1995 at 06:18 UTC2AS A! D #hzY / u  (*|W<>pvx~88, AC11295003UHF 429 Jan 1995 at 01:25 UTC2N7 ^ #hzY / u  (*ĉJL~89, AC11595013Intelsat 70522 Mar 1995 at 06:18 UTC 36B2ASGD q #hzY / u  (*S >@r90, AC11495019AMSC 107 Apr 1995 at 23:47 UTC 36A2AG^  #hzY / u  (*.@Bt91, AC07795025Goes 0923 May 1995 at 05:52 UTC 36B1Eq  #hzY / u  (*|W<>p~92, AC11695027UHF 531 May 1995 at 15:27 UTC 36A2M  #tzY / u  ("*ceMFH|93, AC11895038DSCS 3-0931 Jul 1995 at 23:30 UTC2A IABSK !#tzY / u   ! ("*㈺2BDx94, AC11795043Jcsat 329 Aug 1995 at 00:53 UTC 36B2ASG !#tzY / u  ("*|W>@t95, AC11995057UHF 622 Oct 1995 at 08:00 UTC 36B2F!!#hzY / u  (*8:n|~96, AC12195065Soho02 Dec 1995 at 08:08 UTC 36B2ASL!&!#tzY / u  ("*b㉀FH|97, AC12095069Galaxy 3R15 Dec 1995 at 00:23 UTC 36A2AL!D!#tzY / u  ("*]:9FHz98, AC12696006Palapa C11 Feb 1996 at 01:15 UTC 36B2AS N&!d!#tzY / u  ("*)rGLN99, AC12296020Inmarsat 3F13 Apr 1996 at 23:01 UTC 36A2AFD!|!#tzY / u  *",<>r100, AC07896027SAX30 Apr 1996 at 04:31 UTC 36B1Hd!!#tzY / u  *",|W@Bv101, AC12596042UHF 725 Jul 1996 at 12:42 UTC 36A2G|! !#tzY / u  *",rRU>@r102, AC12396054GE 18 Sep 1996 at 21.49 UTC 36B2A8f! !#tzY / u  *",HJ~103, AC12496067Hotbird 221 Nov 1996 at 20:47 UTC 36B2A168 km x 35784 km x 23.88f ! !#tzY / u  *",+rGNP104, AC12996070Inmarsat 3F318 Dec 1996 at 01:57 UTC2A1017 km x 35820 km x 22.77e !V !#tzY / u  *",㉺2DFz105, AC12797007Jcsat 417 Feb 1997 at 01:42 UTC 36B2AS221 km x 94251 km x 23.5J !r!#tzY / u  *",qDFx106, AC12897011Tempo 28 Mar 1997 at 06:01 UTC 36A2AFtV !!#tzY / u  *",㝖.DFz107, AC07997019Goes 1025 Apr 1997 at 05:49 UTC 36B1announced as the last launch of an Atlas 18fr!@!#tzY / u  !@! *",_Sk7LN108, AC13397036Superbird C28 Jul 1997 at 01:15 UTC 36B2AS333 x 91062 km x 25.30^!,B!#tzY / u  *",rRU>@r109, AC14697050GE 34 Sep 1997 at 12:03 UTC 36A2AS309 x 43913 km x 19.1 N@!LC!#tzY / u  *",XR^ZJL~110, AC13597059Echostar 35 Oct 1997 at 21:01 UTC 36B2AS:a,B!D!#zY / u  *0,aeM{pr111, AC13197065A: DSCS 3-10B: Falcon Gold25 Oct 1997 at 00:46 UTC 36A2A-aLC!E!#hzY / u  *,c㉂FHx112, AC14997078Galaxy 8i8 Dec 1997 at 23:52 UTC 36B2AS280 x 50607 km x 26.8KD!F!#tzY / u  *",i뉀DFz113, AC10998005USA 13729 Jan 1998 at 18:37 UTC 36A2A7eE!H!#tzY / u  *",ĉNP114, AC15198013Intelsat 80628 Feb 1998 at 00:21 UTC 36B2AS190 x 35656 km x 23&TF!-I!#tzY / u  *",|W@Bv115, AC13298016UHF 816 Mar 1998 at 21:32 UTC 36A2last Atlas 2H!J!+ $$Note: In the launch site column C stands for Cape Canaveral and may be followed by the launch pad number. In the type column the second part of the type beginning with C- stands for Centaur-1-I!MJ!1L/MJ!hK!J!hK!n [㰭=H 㰭=H mO{26yj!{!{Atlas[launch vehicle index]Origins of AtlasAtlas without top stageAtlas with an Agena stageAtlas with solid top stageAtlas CentaurAC070AC074< MJ!K!1B0K!K!N!Atlas AC070HhK!K!5 :(b" Atlas AC0701 K!L!'  Generalh'K!L!A#RNLaunch date19 Apr 1991 at 23:30 UT_L!L!A#R<Launch siteCape CanaveralK L!/M!A#RType1YL!M!A#R0Payload mass1115 kg\/M!M!G#^*㉂PayloadYuri 3H@M!kN!G#^ "Failure causeone of the two Centaur engines didn't ignite$M!N!" < kN!N!18B1N!O!!Atlas AC074HN!O!5 :(b" Atlas AC0741 N!DO!'  GeneralTO!O!A#R&Launch id93015h'DO! !A#RNLaunch date25 Mar 1993 at 22:48 UTO! !N!d#O!p!A#RFLaunch siteCape Canaveral LC36K !!A#RType1Zp!!A#R2Payload mass~3000 kg]!r!G#^,|WPayloadA: UHF 1p!!3 4㯃4㯃4The Atlas lost some power during the booster burn, and the Centaur had to burn longer to make up and get into parking orbit. As a result, the second Centaur burn to transfer orbit ran out of fuel during the burn. The payload satellite was left in a 219 x 9158 km x 27.3 deg orbit.This was the third failure of the Atlas 1 class rocket in the last 4 launches!< r!Q!1 7tC2Q!!s!Black ArrowH!!5 :( " Black Arrowe4Q!!1 2h 㭄؉>ɉby Jean-Jacques Serralisting by Gunter KrebsR+!P!' VO Origin: Black Knight experimental rocket4!!, &R׉In 1957 the UK Royal Aircraft Establishment began the development of the Black Knight rocket to study atmosphere reentry of ballistic warheads.The Black Knight was a long cylinder surmounted by a conical rounded head with 4 ribs equipped of stabilization rockets. It was powered by a Gamma 301 made by Bristol Siddeley; its thrust increased from 74 to 106 kN. On its first launch at Woomera in September 1958 it broke the world altitude record with 564 km. It was fired 22 times successfuly between 1958 and 1965.5P!!' O Black Arrow!!& MThe development of the space launcher Black Arrow began in 1964 under direction of the Royal Aircraft Establishment. It was 3-stage rocket of only 13 m high weighing 18.1 tons at takeoff time with a LEO payload capacity of nearly 100 kg.The first stage weighed 14.1 tons and measured 5.9 m high for 2 diameter. It was equipped with a Gamma-8 motor that featured 8 combustion chambers (gimbaled nozzles). It fired during 125 seconds providing 218 kN thrust and 251 kN in vacuum. Second stage was 3.55 m high per 1.37 m diameter and weighed 3.5 tons. Its Gamma-2 motor featuring 2 combustion chambes (gimbaled nozzles) consummed the same propellant and delivered 69 kN thrust during 120 seconds. The third stage was underthe 1.37 m diameter cap and layed on a spinning table. It was 1.3 m high, 71 cm diameter and 0.5 t weight. This stage was powered by a Waxwing solid fuel motor providing a mean thrust of 21 kN over 40 seconds.!D!1 0R׉'S*The first ballistic flight which occured in Jun 1969 failed but the second in March 1970 was successful. The first orbiting attempt failed in Sep 1970 when second stage shutdown 13 seconds early. In July 1971 the British government decided to drop the national program although one flight was still to be carried out. Nonetheless it was fired in Oct 1971 and orbited the Prospero satellite.>!!' . Black Arrow launches2QD!!#4\@NM   $& <> \ l |~ #Launch idPayloadLaunch DateSiteTypeStatus/Comment(\!܎!#h4\@NM :<V\^p 1n/aBallistic flight29 Jun 1969W2-stageFailure: control lost after 50 s:!܏!#\t4\@NM :<V\^p2n/aBallistic flight04 Mar 1970W2-stage![܎! !#\4\܏! !!@NM ,.HNPT3n/aOrba (X2)02 Sep 1970WFailure: 2nd stage produced unsufficient thrust4܏! !#hh4\@NM 'S*<>X^`d471093Prospero (X3)28 Oct 1971Wj@ !s!* $$Notes: All launches from Woomera Rocket Range in Australia9 !!1CH3!5!@$Cosmos BEs!!5 :" " Cosmos BD!5!* $4 㭄؉by Jean-Jacques SerrakD!!' O Origin: MRBM of first generation (Medium Range Ballistic Missile)5!!& The design of Soviet stockable liquid propellant ballistic missiles started in 1954 under management of M.K. Yangel at the SKB 586 of Dniepropetrosk (now NPO Yuzhnoye) in Ukraine. At this time the motorist V.P. Glouchko started to develop a nitric acid - kerosen 4-chamber motor, roviding 650 kN in vacuum.The first realization of Yangel was the R12 (SS-4 Sandal) of 1800 km range. This single stage rocket was 22.4 m high and 1.65 m diameter, and weighed 28 tons. It was aimed by a 4-chamber RD-214 using nitric acid & kerosen. It burned during 140 seconds providing 635 kN thrust at ground level, 730 kN in vacuum (Isp = 264 s). The tuning of the thrust vector was made with control jets but the rocket also has 4 little directional aerodynamical rudder.I!!!( CThe R12 was launched for the first time on 22 Jun 1957 from Kapustin Yar. It was declared operational in 1959. Its deployment in Cuba in 1962 cause a major international crisis.Note: the R12 without top stage was used to launch a Vertikal payload of 35 kg at 4400 km on 12 Oct 1967.=!E!' , Cosmos 1 (B1 / SL7)!9!' In 1962 the R12 rocket was transformed in a ligh launcher by addition of a top stage. This stage of same diameter as the first one was powered by a RD-119 single-nozzle motor using the unusual couple LOX/UDMH. It provided 105 kN thrust in vacuum (Isp = 352 s) during 260 seconds.This 49 tons launcher measured 32 m high and could place 0.5 tons into low earth orbit. It was used 144 times successfully between 1962 and 1977 from Kapustin Yar and Plesetsk.;E!t!' ( Launch statistics(9!!u#Pcgg & > Kapustin YarPlesetskTotalrt!!c#cgg196277r!!c#cgg196344r!g!c#cgg196477r!!c#cgg196577rg!K!c#cgg196677t!!c#"cgg19677613tK!3!c#"cgg19688816u!!c#$cgg196941014u3!!c#$cgg197051318u!!c#$cgg197111112u!"c#$cgg197221!"s!012t!"c#"cgg19731910r""c#cgg197466r"k"c#cgg197555r""c#cgg197644rk"O"c#cgg197722&"u"# ;O""' ( Cosmos B launches?uu""#d4]$OO   $& <> \ ln #Launch idPayloadLaunch dateSiteStatus/Comment (orbit in perigee x apogee x inc. x period)D""#F7`'RR" 8:TZ\162008Cosmos 000116 Mar 1962K217 x 980 km x 49.0B""#:7`'RR" 24NTV262009Cosmos-2 06 Apr 1962K212 x 1546 km x 49.0A""#:7`'RR" 24NTV362013Cosmos-3 24 Apr 1962K229 x 720 km x 49.0B""#:7`'RR" 24NTV462020Cosmos-5 28 May 1962K203 x 1600 km x 49.1A""#:7`'RR" 24NTV562028Cosmos-6 30 Jun 1962K274 x 360 km x 49.0A" "#:7`'RR" 24NTV662038Cosmos-8 18 Aug 1962K256 x 604 km x 49.0A" "#:7`'RR" 24NTV762056Cosmos-11 20 Oct 1962K245 x 921 km x 49.0A " "#:7`'RR" 24NTV863010Cosmos-14 13 Apr 1963K265 x 512 km x 49.0A " "#:7`'RR" 24NTV963017Cosmos-17 22 May 1963K260 x 788 km x 49.0B " "#:7`'RR" 46PVX1063033Cosmos-19 06 Aug 1963K270 x 519 km x 49.0B ""#:7`'RR" 46PVX1163050Cosmos-23 13 Dec 1963K240 x 613 km x 49.0B ""#:7`'RR" 46PVX1264010Cosmos-25 27 Feb 1964K272 x 526 km x 49.0B"@"#:7`'RR" 4"@"s!6PVX1364013Cosmos-26 18 Mar 1964K271 x 403 km x 49.0A"~A"#:7`'RR" 46PVX1464028Cosmos-31 06 Jun 1964K228x 508 km x 49.0A@"tB"#:7`'RR" 46PVX1564042Cosmos-36 30 Jul 1964K259x 503 km x 49.0D~A"mC"#:7`'RR" 8:TZ\1664050Cosmos-42/4322 Aug 1964K232x 1099 km x 49.0AtB"cD"#:7`'RR" 46PVX1764069Cosmos-49 24 Oct 1964K260x 490 km x 49.0AmC"YE"#:7`'RR" 46PVX1864080Cosmos-51 10 Dec 1964K264x 554 km x 48.8CcD"QF"#:7`'RR" 46PVX1965006Cosmos-53 30 Jan 1965K227 x 1192 km x 48.8CYE"IG"#:7`'RR" 46PVX2065052Cosmos-70 02 Jul 1965K229 x 1154 km x 48.8BQF"@H"#:7`'RR" 46PVX2165059Cosmos-76 23 Jul 1965K261 x 530 km x 48.8BIG"7I"#:7`'RR" 46PVX2265084Cosmos-93 19 Oct 1965K220 x 522 km x 48.4B@H".J"#:7`'RR" 46PVX2365088Cosmos-95 04 Nov 1965K207 x 521 km x 48.4C7I"&K"#:7`'RR" 46PVX2465095Cosmos-97 26 Nov 1965K220 x 2100 km x 49.0B.J"L"#:7`'RR" 46PVX2565107Cosmos-10121 Dec 1965K260 x 550 km x 49.0B&K"M"#:7`'RR" 46PVX2666004Cosmos-10625 Jan 1966K290 x 564 km x 48.4BL" N"#:7`'RR" 46PVX2766011Cosmos-10811 Feb 1966K227 x 865 km x 48.9BM"O"#:7`'RR" 46PVX2866036Cosmos-11626 Apr 1966K294 x 478 km x 48.4C N" "#:7`'RR" 46PVX2966043Cosmos-11924 May 1966K219 x 1305 km x 48.5O" "s!BO""#:7`'RR" 46PVX3066061Cosmos-12308 Jul 1966K263 x 529 km x 48.8B ""#:7`'RR" 46PVX3166112Cosmos-13512 Dec 1966K259 x 662 km x 48.5C""#:7`'RR" 46PVX3266117Cosmos-13721 Dec 1966K230 x 1720 km x 48.8C""#:7`'RR" 46PVX3367013Cosmos-14214 Feb 1967K214 x 1362 km x 48.4C""#:7`'RR" 46PVX3467019Cosmos-14503 Mar 1967K220 x 2135 km x 48.4B"م"#:7`'RR" 46PVX3567023Cosmos-14816 Mar 1967P275 x 436 km x 71.0B"І"#:7`'RR" 46PVX3667024Cosmos-14921 Mar 1967K248 x 297 km x 48.4Bم"LJ"#:7`'RR" 46PVX3767028Cosmos-15225 Mar 1967P283 x 512 km x 71.0BІ""#:7`'RR" 46PVX3867056Cosmos-16305 Jun 1967K261 x 616 km x 48.4CLJ""#:7`'RR" 46PVX3967059Cosmos-16512 Jun 1967P211 x 1542 km x 81.9B""#:7`'RR" 46PVX4067061Cosmos-16616 Jun 1967K283 x 578 km x 48.4B""#:7`'RR" 46PVX4167081Cosmos-17324 Aug 1967P280 x 528 km x 71.0C""#:7`'RR" 46PVX4267086Cosmos-17612 Sep 1967P206 x 1581 km x 81.9B""#:7`'RR" 46PVX4367115Cosmos-19121 Nov 1967P281 x 518 km x 71.0B""#:7`'RR" 46PVX4467125Cosmos-19619 Dec 1967K224 x 884 km x 49.0B""#:7`'RR" 46PVX4567126Cosmos-19726 Dec 1967K219 x 502 km x 48.5B""#:7`'RR" 4""s!6PVX4668010Cosmos-20220 Feb 1968K220 x 502 km x 48.4B"{"#:7`'RR" 46PVX4768015Cosmos-20405 Mar 1968P282 x 873 km x 71.0C"s"#:7`'RR" 46PVX4868028Cosmos-21109 Apr 1968P210 x 1574 km x 81.9B{"j"#:7`'RR" 46PVX4968033Cosmos-21519 Apr 1968K261 x 426 km x 48.5Cs"b"#:7`'RR" 46PVX5068038Cosmos-21926 Apr 1968K222 x 1770 km x 48.4Cj"Z"#:7`'RR" 46PVX5168043Cosmos-22124 May 1968K220 x 2108 km x 48.4Bb"Q"#:7`'RR" 46PVX5268044Cosmos-22230 May 1968P277 x 528 km x 71.0BZ"H"#:7`'RR" 46PVX5368048Cosmos-22512 Jun 1968K257 x 530 km x 48.4BQ"?"#:7`'RR" 46PVX5468056Cosmos-23005 Jul 1968K290 x 580 km x 48.5CH"7"#:7`'RR" 46PVX5568061Cosmos-23318 Jul 1968P210 x 2545 km x 82.0B?"."#:7`'RR" 46PVX5668079Cosmos-24220 Sep 1968P280 x 440 km x 71.0B7"%"#:7`'RR" 46PVX5768083Cosmos-24503 Oct 1968P282 x 509 km x 71.0B.""#:7`'RR" 46PVX5868107Cosmos-25703 Dec 1968P282 x 470 km x 71.0C%""#:7`'RR" 46PVX5968113Cosmos-25914 Dec 1968K219 x 1353 km x 48.5B" "#:7`'RR" 46PVX6068117Cosmos-26119 Dec 1968P217 x 670 km x 71.0B""#:7`'RR" 46PVX6168119Cosmos-26226 Dec 1968K263 x 818 km x 48.5B " ##:7`'RR" 46PVX6269012Cosmos-26507 Feb 1969P283 x 485 km x 71.0" #s!C"##:7`'RR" 46PVX6369020Cosmos-26805 Mar 1969K219 x 2186 km x 48.4B ###:7`'RR" 46PVX6469031Cosmos-27528 Mar 1969P284 x 805 km x 71.0B###:7`'RR" 46PVX6569033Cosmos-27704 Apr 1969P280 x 494 km x 71.0C###:7`'RR" 46PVX6669047Cosmos-28327 May 1969P210 x 1539 km x 82.0B###:7`'RR" 46PVX6769049Cosmos-28503 Jun 1969P279 x 518 km x 71.0B###:7`'RR" 46PVX6869073Cosmos-29522 Aug 1969P282 x 500 km x 71.0H###F7`'RR" 㹧ԉ@B\bd6969088Intercosmos 0114 Oct 1969K260 x 640 km x 48.4C###:7`'RR" 46PVX7069090Cosmos-30318 Oct 1969P282 x 4920 km x 71.0C###:7`'RR" 46PVX7169094Cosmos-30724 Oct 1969K220 x 2178 km x 48.4B# ##:7`'RR" 46PVX7269096Cosmos-30804 Nov 1969P281 x 422 km x 71.0B# ##:7`'RR" 46PVX7369102Cosmos-31124 Nov 1969P284 x 496 km x 71.0B # ##:7`'RR" 46PVX7469106Cosmos-31411 Dec 1969P282 x 491 km x 71.0F # ##:7`'RR" :<V\^7569110Intercosmos-225 Dec 1969K206 x 1200 km x 48.4C # ##:7`'RR" 46PVX7670004Cosmos-31915 Jan 1970P209 x 1537 km x 82.0B ###:7`'RR" 46PVX7770005Cosmos-32016 Jan 1970K240 x 343 km x 48.5B ###:7`'RR" 46PVX7870006Cosmos-32120 Jan 1970P280 x 507 km x 71.0B#@##:7`'RR" #@#s!46PVX7970014Cosmos-32427 Feb 1970P446 x 705 km x 71.0B#A##:7`'RR" 46PVX8070020Cosmos-32718 Mar 1970P269 x 822 km x 70.9B@#B##:7`'RR" 46PVX8170033Cosmos-33423 Apr 1970P272 x 483 km x 70.9BA#yC##:7`'RR" 46PVX8270035Cosmos-33524 Apr 1970K249 x 400 km x 48.4CB#qD##:7`'RR" 46PVX8370043Cosmos-34712 Jun 1970K215 x 2050 km x 48.4ByC#hE##:7`'RR" 46PVX8470044Cosmos-34813 Jun 1970P200 x 652 km x 71.0BqD#_F##:7`'RR" 46PVX8570051Cosmos-35127 Jun 1970P270 x 467 km x 71.0FhE#ZG##:7`'RR" :<V\^8670057Intercosmos-307 Aug 1970K200 x 1295 km x 48.4B_F#QH##:7`'RR" 46PVX8770059Cosmos-35610 Aug 1970P232 x 573 km x 81.9BZG#HI##:7`'RR" 46PVX8870063Cosmos-35719 Aug 1970P272 x 476 km x 71.0BQH#?J##:7`'RR" 46PVX8970073Cosmos-36216 Sep 1970P272 x 817 km x 71.0BHI#6K##:7`'RR" 46PVX9070081Cosmos-36908 Oct 1970P269 x 505 km x 70.9E?J#0L##:7`'RR" :<V\^9170084Intercosmos-414 Oct 1970K251 x 627 km x 48.4C6K#(M##:7`'RR" 46PVX9270100Cosmos-38024 Nov 1970P199 x 1519 km x 81.9B0L#N##:7`'RR" 46PVX9370112Cosmos-38818 Dec 1970P270 x 505 km x 71.0B(M#O##:7`'RR" 46PVX9471002Cosmos-39114 Jan 1971P267 x 803 km x 70.9BN###:7`'RR" 46PVX9571007Cosmos-39326 Jan 1971P274 x 484O##s! km x 71.0BO###:7`'RR" 46PVX9671037Cosmos-40824 Apr 1971P211 x1542 km x 81.8B###:7`'RR" 46PVX9771044Cosmos-42119 May 1971P283 x 492 km x 70.9B###:7`'RR" 46PVX9871047Cosmos-42327 May 1971P282 x 511 km x 71.0B###:7`'RR" 46PVX9971072Cosmos-43527 Aug 1971P282 x 505 km x 71.0C###:7`'RR"68RXZ10071079Cosmos-44024 Sep 1971P282 x 814 km x 71.0C###:7`'RR"68RXZ10171090Cosmos-45319 Oct 1971P281 x 522 km x 71.0C#݆##:7`'RR"68RXZ10271097Cosmos-45517 Nov 1971P282 x 516 km x 71.0C#Շ##:7`'RR"68RXZ10371101Cosmos-45829 Nov 1971P281 x 523 km x 71.0G݆#ш##:7`'RR"<>X^`10471104Intercosmos-502 Dec 1971K205 x 1200 km x 48.4CՇ#ɉ##:7`'RR"68RXZ10571113Cosmos-46717 Dec 1971P279 x 502 km x 71.0Dш#Š##:7`'RR"68RXZ10672004Cosmos-47225 Jan 1972P207 x 1568 km x 82.0Cɉ###:7`'RR"68RXZ10772020Cosmos-48125 Mar 1972P279 x 540 km x 71.0CŠ###:7`'RR"68RXZ10872023Cosmos-48511 Apr 1972P280 x 506 km x 71.0C###:7`'RR"68RXZ10972033Cosmos-48721 Apr 1972P278 x 531 km x 71.0F###:7`'RR"<>X^`11072047Intercosmos-730 Jun 1972K267 x 568 km x 48.4C###:7`'RR"68RXZ11172048Cosmos-49730 Jun 1972P282 x 812 km x 71.0C###:7`'RR"##s!68RXZ11272050Cosmos-49805 Jul 1972P282 x 511 km x 71.0D###:7`'RR"68RXZ11372054Cosmos-50112 Jul 1972K222 x 2149 km x 48.5C###:7`'RR"68RXZ11472078Cosmos-52305 Oct 1972P283 x 507 km x 71.0C###:7`'RR"68RXZ11572080Cosmos-52411 Oct 1972P277 x 537 km x 71.0C###:7`'RR"68RXZ11672084Cosmos-52625 Oct 1972P282 x 511 km x 71.0F#}##:7`'RR"<>X^`11772094Intercosmos-830 Nov 1972P214 x 679 km x 71.0C#u##:7`'RR"68RXZ11873004Cosmos-54524 Jan 1973P279 x 521 km x 71.0C}#m##:7`'RR"68RXZ11973020Cosmos-55312 Apr 1973P262 x 519 km x 71.0Gu#i##:7`'RR"<>X^`12073022Intercosmos-919 Apr 1973K202 x 1551 km x 48.4Cm#a##:7`'RR"68RXZ12173029Cosmos-55817 May 1973P279 x 526 km x 71.0Ci#Y##:7`'RR"68RXZ12273035Cosmos-56205 Jun 1973P282 x 510 km x 71.0Ca#Q##:7`'RR"68RXZ12373057Cosmos-58022 Aug 1973P283 x 518 km x 71.0DY#J##:7`'RR"68RXZ12473075Cosmos-60116 Oct 1973P210 x 1561 km x 82.0CQ#B##:7`'RR"68RXZ12573091Cosmos-60820 Nov 1973P281 x 528 km x 71.0CJ#:##:7`'RR"68RXZ12673094Cosmos-61128 Nov 1973P270 x 507 km x 71.0CB#2##:7`'RR"68RXZ12773099Cosmos-61513 Dec 1973P280 x 859 km x 71.0C:#6$#:7`'RR"68RXZ12874010Cosmos-6332#6$s!27 Feb 1974P280 x 516 km x 71.0C2#.$#:7`'RR"68RXZ12974012Cosmos-63405 Mar 1974P281 x 516 km x 71.0C6$&$#:7`'RR"68RXZ13074047Cosmos-66226 Jun 1974P290 x 795 km x 70.9C.$$#:7`'RR"68RXZ13174058Cosmos-66825 Jul 1974P281 x 519 km x 71.0C&$$#:7`'RR"68RXZ13274074Cosmos-68626 Sep 1974P281 x 515 km x 71.0C$$#:7`'RR"68RXZ13374091Cosmos-69520 Nov 1974P283 x 493 km x 71.0D$$#:7`'RR"68RXZ13475003Cosmos-70321 Jan 1975P207 x 1545 km x 82.0C$$#:7`'RR"68RXZ13575006Cosmos-70528 Jan 1975P281 x 508 km x 71.0C$$#:7`'RR"68RXZ13675026Cosmos-72508 Apr 1975P283 x 540 km x 71.0C$$#:7`'RR"68RXZ13775058Cosmos-74524 Jun 1975P274 x 540 km x 71.0C$ $#:7`'RR"68RXZ13875067Cosmos-75017 Jul 1975P281 x 830 km x 71.0C$ $#:7`'RR"68RXZ13976012Cosmos-80105 Feb 1976P290 x 723 km x 71.0C $ $#:7`'RR"68RXZ14076044Cosmos-81818 May 1976P281 x 506 km x 71.0C $ $#:7`'RR"68RXZ14176083Cosmos-84913 Aug 1976P276 x 889 km x 71.0C $ $#:7`'RR"68RXZ14276084Cosmos-85026 Aug 1976P280 x 518 km x 71.0C $$#:7`'RR"68RXZ14377025Cosmos-90105 Apr 1977P279 x 845 km x 71.0C $$#:7`'RR"68RXZ14477051Cosmos-91918 Jun 1977P278 x 847 km x 71.0\6$@$& l$Notes: K for Kapustin Yar, P for $@$s!Plesetsk launches9$X@$1tCV4X@$@$,+Cosmos CE@$@$5 :" " Cosmos CDX@$@$* $4 㭄؉by Jean-Jacques SerraJ#@$+A$' F Origin: IRBM of first generation^8@$C$& qThe second realization of M.K. Yangel at SKB-586 in Dniepropetrosk (now NPO Yuzhnoye), Ukraine, was the R14 (SS-5 Skean), 4000 kg range. This single stage rocket was 24.3 m high and 2.4 m diameter and weighed 50 tons. It was powered by 2 RD-216 motors with 2 chambers each, consuming nitric acid and UDMH. The motors provided 863 kN thrust in vacuum during 170 seconds (Isp = 291 s).The R14 was first launched in 1960 in Kapustin Yar and became operational in 1962. It was used as a probe since 1975. It can launch 1300 kg at 500 km or 860 kg at 1500 km altitude.&+A$C$# =C$C$' , Cosmos 2 (C1 / SL8)mGC$YF$& The first use of the R14 as a space launcher was in 1964. It was equipped with a top stage, same diameter as the first one, whose motor (unidentified) use NTO/UDMH. Jane's Space Directory claims it can burn for 375 seconds with 157 kN thrust. It can be re-ignited to circularize an orbit.This 106 tons launcher, approx. 32 m high. It is still used as 11K65. It can orbit 1.7 tons in LEO, but its missions generally limits to place 1 ton into 800 to 1500 km altitude orbit. This is the only launcher to have been fired from Baikonour, Plesetsk and Kapustin Yar. It was used for:iC$G$N j7㼨ԟ 剂<qi"qe- geodesy and military or civilian navigation (Parus, Tsikada, etc.)- telecommunications mainly military (Strela) but also civilian- ELINT- interception targets, radar calibration- technology (BOR-4 mini shuttles)- scientific (Cosmos, Intercosmos, Aureole, etc.);YF$G$' ( Launch statistics5G$H$#jfzy   8 X BaikonourPlesetskKapustin YarTotalG$CI$t#"fzy196411H$I$t#"fzy196566CI$LJ$t# fzy19660I$J$t#$fzy1967134LJ$XK$t#$fzy1968156J$K$t#"fzy196966XK$dL$t#&fzy19701010K$L$t#&fzy19711919dL$rM$t#&fzy19721313L$M$t#(fzy 197314115rM$N$t#(fzy 197416117M$ O$t#(fzy 197517118N$O$t#(fzy 197627128 O$&$t#(fzy O$&$@$197726228O$$t#(fzy 197820121&$6$t#(fzy 197916218$$t#(fzy 1980151166$F$t#(fzy 198117118$΂$t#(fzy 198218422F$V$t#(fzy 198318422΂$ރ$t#(fzy 198416218V$f$t#(fzy 198510111ރ$$t#&fzy19861515f$u$t#(fzy 198712113$$t#"fzy198877u$$t#"fzy198999$$t#&fzy19901010$$t#&fzy19911010$$t#"fzy199277$$t#"fzy199366$$t#"fzy199455&$B$# ;$}$' ( Cosmos C launches?uB$$#d4]$OO   $& <> \ ln #Launch idPayloadLaunch dateSiteStatus/Comment (orbit in perigee x apogee x inc. x period)C}$$#:7`'RR" 68RXZ164046Cosmos-38/4018 Aug 1964T210 x 876 km x 56.2D$$#:7`'RR" 68RXZ265011Cosmos-54/5621 Feb 1965T280 x 1856 km x 56.1D$$#:7`'RR" 68RXZ365020Cosmos-61/6315 Mar 1965T273 x 1887 km x 56.0C$$#:7`'RR" 68RXZ465053Cosmos-71/7516 Jul 1965T540 x 600 km x 56.1E$$#:7`'RR" 68RXZ565070Cosmos-80/8403 Sep 1965T1440 x 1550 km x 56.0E$$#:7`'RR" $$@$68RXZ665073Cosmos-86/9018 Sep 1965T1340 x 1670 km x 56.0A$$#:7`'RR" 24NTV765112Cosmos-10328 Dec 1965T600 x 600 km x 56.0A$$#:7`'RR" 24NTV867027Cosmos-15124 Mar 1967T630 x 630 km x 56.0A$$#:7`'RR" 24NTV967045Cosmos-15815 May 1967P850 x 850 km x 74.4B$w$#:7`'RR" 46PVX1067108Cosmos-18930 Oct 1967P535 x 600 km x 74.0C$o$#:7`'RR" 46PVX1167116Cosmos-19223 Nov 1967P755 x 7550 km x 74.0Bw$f$#:7`'RR" 46PVX1268006Cosmos-20020 Jan 1968P536 x 536 km x 74.0Do$_$#:7`'RR" 46PVX1368011Cosmos-20320 Feb 1968P1200 x 1200 km x 74.1Bf$V$#:7`'RR" 46PVX1468040Cosmos-22007 May 1968P670 x 760 km x 74.0B_$M$#:7`'RR" 46PVX1568070Cosmos-23627 Aug 1968T600 x 655 km x 56.0BV$D$#:7`'RR" 46PVX1668095Cosmos-25030 Oct 1968P523 x 556 km x 74.0DM$=$#:7`'RR" 46PVX1768106Cosmos-25630 Nov 1968P1168 x 1234 km x 74.1BD$4$#:7`'RR" 46PVX1869021Cosmos-26905 Mar 1969P526 x 558 km x 74.0D=$-$#:7`'RR" 46PVX1969024Cosmos-27217 Mar 1969P1195 x 1220 km x 74.0C4$%$#:7`'RR" 46PVX2069070Cosmos-29214 Aug 1969P747 x 7866 km x 74.0B-$$#:7`'RR" 46PVX2169091Cosmos-30421 Oct 1969P747 x 774 km x 74.0D%$!%#:7`'RR" 46PVX2269103Cosmos-31224 Nov 1969P114$!%@$5 x 1187 km x 74.0B$%#:7`'RR" 46PVX2369107Cosmos-31520 Dec 1969P521 x 556 km x 74.1B!%%#:7`'RR" 46PVX2470024Cosmos-33007 Apr 1970P512 x 549 km x 74.1B%%#:7`'RR" 46PVX2570028Cosmos-33211 Apr 1970P755 x 761 km x 74.0H%%#:7`'RR" <>X^`2670036Cosmos-336/34325 Jun 1970P1412 x 1490 km x 74.0B%%#:7`'RR" 46PVX2770064Cosmos-35820 Aug 1970P515 x 539 km x 74.0B%%#:7`'RR" 46PVX2870083Cosmos-37112 Oct 1970P746 x 761 km x 74.0B%%#:7`'RR" 46PVX2970086Cosmos-37216 Oct 1970P785 x 806 km x 74.1C%%#:7`'RR" 46PVX3070097Cosmos-37817 Nov 1970P233 x 1741 km x 74.0C%%#:7`'RR" 46PVX3170102Cosmos-38102 Dec 1970P985 x 1023 km x 74.0B% %#:7`'RR" 46PVX3270108Cosmos-38512 Dec 1970P978 x 986 km x 74.0B% %#:7`'RR" 46PVX3370111Cosmos-38716 Dec 1970P528 x 537 km x 74.0B % %#:7`'RR" 46PVX3471010Cosmos-39409 Feb 1971P574 x 619 km x 65.9B % %#:7`'RR" 46PVX3571013Cosmos-39517 Feb 1971P529 x 545 km x 74.0C % %#:7`'RR" 46PVX3671020Cosmos-40018 Mar 1971P996 x 1016 km x 65.8B %%#:7`'RR" 46PVX3771035Cosmos-40723 Apr 1971P799 x 844 km x 74.1D %%#:7`'RR" 46PVX3871038Cosmos-40928 Apr 1971P1185 x 1222 km x 74.0H%@%#:7`'RR" %@%@$<>X^`3971041Cosmos-411/41807 May 1971P1405 x 1530 km x 74.5C%A%#:7`'RR" 46PVX4071046Cosmos-42222 May 1971P994 x 1020 km x 74.0B@%B%#:7`'RR" 46PVX4171050Cosmos-42529 May 1971P511 x 556 km x 74.0DA%C%#:7`'RR" 46PVX4271052Cosmos-42604 Jun 1971P394 x 2012 km x 74.0vBB%D%#:7`'RR" 46PVX4371074Cosmos-43607 Sep 1971P514 x 550 km x 74.0BC%{E%#:7`'RR" 46PVX4471075Cosmos-43710 Sep 1971P523 x 559 km x 74.0D%)G%#7`'RR" ~BCDEFGsj.0JPR4571086A: Cosmos 0444B: Cosmos 0445C: Cosmos 0446D: Cosmos 0447E: Cosmos 0448F: Cosmos 0449G: Cosmos 0450H: Cosmos 045113 Oct 1971P1415 x 1550 km x 74.0D{E%"H%#:7`'RR" 46PVX4671099Cosmos-45720 Nov 1971P1129 x 1192 km x 74.0B)G%I%#:7`'RR" 46PVX4771102Cosmos-45929 Nov 1971P226 x 277 km x 65.8B"H%J%#:7`'RR" 46PVX4871103Cosmos-46030 Nov 1971P520 x 553 km x 74.0BI%K%#:7`'RR" 46PVX4971105Cosmos-46102 Dec 1971P490 x 524 km x 69.2CJ%K%#:7`'RR" 46PVX5071111Cosmos-46515 Dec 1971P984 x 1023 km x 74.0BK%L%#:7`'RR" 46PVX5171114Cosmos-46817 Dec 1971P788 x 830 km x 74.0DK%M%#F7`'RR" 2y`68RXZ5271119Aureole 127 Dec 1971P410 x 2500 km x 74.0CL%N%#:7`'RR" 46PVX5372009Cosmos-47525 Feb 1972P977 x 1013 km x 74.0BM% %#:7`'RR" 46PVX5472017Cosmos-47922 Mar 1972P517 x 549 km x 74.0N% %@$DN%%#:7`'RR" 46PVX5572019Cosmos-48025 Mar 1972P1183 x 1212 km x 83.0C %%#:7`'RR" 46PVX5672035Cosmos-48906 May 1972P980 x 1010 km x 74.0B%%#:7`'RR" 46PVX5772043Cosmos-49423 Jun 1972P791 x 825 km x 74.0E%%#F7`'RR" :<V\^5872053Cosmos 050010 Jul 1972P509 x 554 km x 74.0%%#7`'RR" }~02LRT5972057A: Cosmos 0504B: Cosmos 0505C: Cosmos 0506D: Cosmos 0507E: Cosmos 0508F: Cosmos 0509G: Cosmos 0510H: Cosmos 051119 Jul 1972P1425 x 1504 km x 74.0B%%#:7`'RR" 46PVX6072062Cosmos-51416 Aug 1972P959 x 999 km x 83.0C%%#:7`'RR" 46PVX6172074Cosmos-52129 Sep 1972P965 x 1192 km x 65.9H%%#:7`'RR" <>X^`6272087Cosmos-528/53501 Nov 1972P1375 x 1495 km x 74.0B%%#:7`'RR" 46PVX6372088Cosmos-53603 Nov 1972P514 x 555 km x 74.0D%%#:7`'RR" 46PVX6472102Cosmos-53921 Dec 1972P1353 x 1392 km x 74.0B%w%#:7`'RR" 46PVX6572104Cosmos-54025 Dec 1972P779 x 823 km x 74.0B%n%#:7`'RR" 46PVX6673003Cosmos-54420 Jan 1973P513 x 561 km x 74.0Bw%e%#:7`'RR" 46PVX6773005Cosmos-54626 Jan 1973K584 x 630 km x 50.7Bn%\%#:7`'RR" 46PVX6873010Cosmos-54928 Feb 1973P513 x 556 km x 74.0He%Y%#:7`'RR" <>X^`6973037Cosmos-564/57108 Jun 1973P1395 x 1485 km x 74.0C\%]%#:7`'RR" 46PVY%]%@$X7073042Cosmos-57420 Jun 1973P996 x 1026 km x 83.0BY%T%#:7`'RR" 46PVX7173060Cosmos-58228 Aug 1973P521 x 559 km x 74.0D]%M%#:7`'RR" 46PVX7273064Cosmos-58508 Sep 1973P1385 x 1416 km x 74.0CT%E%#:7`'RR" 46PVX7373065Cosmos-58614 Sep 1973P986 x 1020 km x 83.0M%%#7`'RR" ~+,XOPQRS.0JPR7473069A: Cosmos 0588B: Cosmos 0589C: Cosmos 0590D: Cosmos 0591E: Cosmos 0592F: Cosmos 0593G: Cosmos 0594H: Cosmos 059503 Oct 1973P1397 x 1512 km x 74.0GE%%#:7`'RR" <>X^`7573082Intercosmos-1030 Oct 1973P265 x 1477 km x 74.0B%%#:7`'RR" 46PVX7673093Cosmos-61027 Nov 1973P515 x 560 km x 74.0B%%#:7`'RR" 46PVX7773098Cosmos-61404 Dec 1973P770 x 830 km x 74.0H%%#:7`'RR" <>X^`7873104Cosmos-617/62419 Dec 1973P1400 x 1487 km x 74.0D%%#F7`'RR" 3y`68RXZ7973107Aureole 226 Dec 1973P407 x 1995 km x 74.0C%%#:7`'RR" 46PVX8073109Cosmos-62729 Dec 1973P974 x 1019 km x 82.9C%%#:7`'RR" 46PVX8174001Cosmos-62818 Jan 1974P975 x 1026 km x 83.0B%%#:7`'RR" 46PVX8274005Cosmos-63106 Feb 1974P522 x 656 km x 74.0%n%#7`'RR" ~.0JPR8374024A: Cosmos 0641B: Cosmos 0642C: Cosmos 0643D: Cosmos 0644E: Cosmos 0645F: Cosmos 0646G: Cosmos 0647H: Cosmos 064823 Apr 1974P1385 x 1508 km x 74.0D%g%#:7`'RR" 46PVX8474028Cosmos-65029 Apr 1974P1380 x 1413 km x 74.0Fn%n&#:7`'RR" <>Xg%n&@$^`8574034Intercosmos-1117 May 1974K483 x 511 km x 50.6Bg%e&#:7`'RR" 46PVX8674035Cosmos-65521 May 1974P520 x 549 km x 74.0Cn&]&#:7`'RR" 46PVX8774044Cosmos-66018 Jun 1974P409 x 1995 km x 83.0Be&T&#:7`'RR" 46PVX8874045Cosmos-66121 Jun 1974P514 x 544 km x 74.0C]&L&#:7`'RR" 46PVX8974048Cosmos-66327 Jun 1974P983 x 1017 km x 83.0DT&E&#:7`'RR" 46PVX9074069Cosmos-67530 Aug 1974P1370 x 1429 km x 74.0BL&<&#:7`'RR" 46PVX9174071Cosmos-67611 Sep 1974P799 x 840 km x 74.0E&&#7`'RR" ~89:f]^_`.0JPR9274072A: Cosmos 0677B: Cosmos 0678C: Cosmos 0679D: Cosmos 0680E: Cosmos 0681F: Cosmos 0682G: Cosmos 0683H: Cosmos 068419 Sep 1974P1451 x 1519 km x 74.0B<&&#:7`'RR" 46PVX9374076Cosmos-68711 Oct 1974P292 x 717 km x 74.0C& &#:7`'RR" 46PVX9474079Cosmos-68919 Oct 1974P992 x 1032 km x 83.0F& &#:7`'RR" <>X^`9574086Intercosmos-1231 Oct 1974P264 x 708 km x 74.1B & &#:7`'RR" 46PVX9674100Cosmos-69818 Dec 1974P515 x 566 km x 74.0C & &#:7`'RR" 46PVX9774105Cosmos-70026 Dec 1974P976 x 1012 km x 83.0B & &#:7`'RR" 46PVX9875008Cosmos-70705 Feb 1975P505 x 550 km x 74.0D &&#:7`'RR" 46PVX9975012Cosmos-70812 Feb 1975P1387 x 1428 km x 82.9 &n@&#7`'RR"~ijklmnop02LRT10075016A: Cosmos 0711B: Cosmos 0712C: Cosmos 0713D: Cosmos 0714E: Cosmos 07&n@&@$15F: Cosmos 0716G: Cosmos 0717H: Cosmos 071828 Feb 1975P1449 x 1530 km x 74.0H&kA&#:7`'RR">@Z`b10175022Intercosmos-1327 Mar 1975P296 x 1714 km x 83.0Dn@&dB&#:7`'RR"68RXZ10275028Cosmos-72611 Apr 1975P972 x 1008 km x 83.0DkA&cC&#F7`'RR"G8:TZ\10375033Aryabhata19 Apr 1975K569 x 610 km x 50.7DdB&\D&#:7`'RR"68RXZ10475034Cosmos-72923 Apr 1975P995 x 1023 km x 83.0cC& F&#7`'RR"~02LRT10575045A: Cosmos 0732B: Cosmos 0733C: Cosmos 0734D: Cosmos 0735E: Cosmos 0736F: Cosmos 0737G: Cosmos 0738H: Cosmos 073928 May 1975P1475 x 1532 km x 74.07\D&F&#Fn7`'RR"46PVX#"106n/aIntercosmos03 Jun 1975PfailureC F&G&#:7`'RR"68RXZ10775062Cosmos-74904 Jul 1975P511 x 557 km x 74.0CF&H&#:7`'RR"68RXZ10875069Cosmos-75224 Jul 1975P480 x 526 km x 65.9DG&I&#:7`'RR"68RXZ10975074Cosmos-75514 Aug 1975P991 x 1025 km x 82.9IH&J&#:7`'RR">@Z`b11075086Cosmos-761/76817 Sep 1975P1454 x 1537 km x 74.0EI&K&#:7`'RR"68RXZ11175089Cosmos-77024 Sep 1975P1188 x 1222 km x 83.0CJ&L&#:7`'RR"68RXZ11275094Cosmos-77330 Sep 1975P791 x 828 km x 74.1DK&M&#:7`'RR"68RXZ11375103Cosmos-77804 Nov 1975P989 x 1018 km x 83.0CL&N&#:7`'RR"68RXZ11475109Cosmos-78121 Nov 1975P508 x 557 km x 74.0CM&O&#:7`'RR"68RXZ11575112Cosmos-78328 Nov 1975P797 x 838 km x 74.0HN&Ȁ&#:7`'RRO&Ȁ&@$">@Z`b11675115Intercosmos-1411 Dec 1975P345 x 1707 km x 74.0CO&&#:7`'RR"68RXZ11776001Cosmos-78706 Jan 1976P519 x 564 km x 74.0DȀ&&#:7`'RR"68RXZ11876005Cosmos-78921 Jan 1976P993 x 1029 km x 83.0C&&#:7`'RR"68RXZ11976007Cosmos-79023 Jan 1976P513 x 559 km x 74.0I&&#:7`'RR">@Z`b12076008Cosmos-791/79828 Jan 1976P1453 x 1538 km x 74.0E&&#:7`'RR"68RXZ12176011Cosmos-80003 Feb 1976P1000 x 1027 km x 83.0C&&#:7`'RR"68RXZ12276014Cosmos-80312 Feb 1976P554 x 624 km x 66.0D&&#:7`'RR"68RXZ12376022Cosmos-80712 Mar 1976P403 x 1985 km x 83.0C&&#:7`'RR"68RXZ12476031Cosmos-81206 Apr 1976P504 x 558 km x 74.0C&&#:7`'RR"68RXZ12576037Cosmos-81628 Apr 1976P482 x 525 km x 65.9C&&#:7`'RR"68RXZ12676049Cosmos-82228 May 1976P284 x 729 km x 74.0D&{&#:7`'RR"68RXZ12776051Cosmos-82303 Jun 1976P996 x 1023 km x 83.0I&y&#:7`'RR">@Z`b12876054Cosmos-825/83215 Jun 1976P1450 x 1530 km x 74.0G{&u&#:7`'RR">@Z`b12976056Intercosmos-1519 Jun 1976P487 x 520 km x 74.0Cy&m&#:7`'RR"68RXZ13076061Cosmos-83629 Jun 1976P796 x 843 km x 74.0Du&f&#:7`'RR"68RXZ13176067Cosmos-83908 Jul 1976P984 x 2102 km x 65.9Cm&j&#:7`'RR"68Rf&j&@$XZ13276069Cosmos-84115 Jul 1976P789 x 826 km x 74.0Df&c&#:7`'RR"68RXZ13376070Cosmos-84221 Jul 1976P987 x 1023 km x 83.0Cj&[&#:7`'RR"68RXZ13476075Cosmos-84527 Jul 1976P505 x 557 km x 74.0Gc&W&#:7`'RR">@Z`b13576076Intercosmos-1627 Jul 1976K465 x 876 km x 50.6D[&P&#:7`'RR"68RXZ13676078Cosmos-84630 Jul 1976P967 x 1025 km x 83.0CW&H&#:7`'RR"68RXZ13776098Cosmos-85829 Sep 1976P792 x 833 km x 74.0DP&A&#:7`'RR"68RXZ13876108Cosmos-86429 Oct 1976P980 x 1021 km x 83.0CH&9&#:7`'RR"68RXZ13976115Cosmos-87002 Dec 1976P514 x 560 km x 74.0IA&7&#:7`'RR">@Z`b14076118Cosmos-871/87807 Dec 1976P1480 x 1520 km x 74.0C9&/&#:7`'RR"68RXZ14176120Cosmos-88009 Dec 1976P562 x 624 km x 66.0D7&(&#:7`'RR"68RXZ14276122Cosmos-88315 Dec 1976P975 x 1073 km x 83.0C/& &#:7`'RR"68RXZ14376124Cosmos-88517 Dec 1976P470 x 513 km x 66.0D(&&#:7`'RR"68RXZ14476128Cosmos-88728 Dec 1976P973 x 1030 km x 83.0E &&#:7`'RR"68RXZ14577004Cosmos-89020 Jan 1977P1000 x 1032 km x 83.0C& &#:7`'RR"68RXZ14677006Cosmos-89102 Feb 1977P466 x 518 km x 65.8D&&#:7`'RR"68RXZ14777011Cosmos-89315 Feb 1977P341 x 1703 km x 74.0D & '#:7`'RR"68RXZ14877013Cosmos-89421 Feb 1977P988 x 1026 km x 83.0& '@$C&'#:7`'RR"68RXZ14977022Cosmos-89925 Mar 1977P505 x 552 km x 74.1C ''#:7`'RR"68RXZ15077023Cosmos-90030 Mar 1977P460 x 523 km x 83.0C''#:7`'RR"68RXZ15177031Cosmos-90627 Apr 1977K466 x 523 km x 50.7D''#:7`'RR"68RXZ15277036Cosmos-90919 May 1977P991 x 2112 km x 65.8D''#:7`'RR"68RXZ15377039Cosmos-91125 May 1977P984 x 1018 km x 82.9C''#:7`'RR"68RXZ15477042Cosmos-91331 May 1977P475 x 523 km x 74.0B''#F7`'RR"o546PVX15577049Signe 317 Jun 1977K457 x 522 km x 50.6C''#:7`'RR"68RXZ15677059Cosmos-92301 Jul 1977P804 x 842 km x 74.0C''#:7`'RR"68RXZ15777060Cosmos-92405 Jul 1977P514 x 560 km x 74.0D' '#:7`'RR"68RXZ15877062Cosmos-92609 Jul 1977P997 x 1025 km x 82.9D' '#:7`'RR"68RXZ15977064Cosmos-92813 Jul 1977P977 x 1022 km x 83.0C ' '#:7`'RR"68RXZ16077067Cosmos-93019 Jul 1977P482 x 528 km x 74.0C ' '#:7`'RR"68RXZ16177070Cosmos-93322 Jul 1977P385 x 418 km x 65.8I ' '#:7`'RR">@Z`b16277079Cosmos-939/94624 Aug 1977P1448 x 1518 km x 74.0D ''#:7`'RR"68RXZ16377087Cosmos-95113 Sep 1977P989 x 1029 km x 83.0G ''#:7`'RR">@Z`b16477096Intercosmos-1724 Sep 1977P468 x 519 km x 83.0C'@'#:7`'RR"'@'@$68RXZ16577101Cosmos-95921 Oct 1977P153 x 890 km x 66.0C'A'#:7`'RR"68RXZ16677103Cosmos-96025 Oct 1977P505 x 549 km x 74.0D@'B'#:7`'RR"68RXZ16777107Cosmos-96228 Oct 1977P983 x 1022 km x 83.0EA'C'#:7`'RR"68RXZ16877109Cosmos-96323 Nov 1977P1182 x 1210 km x 82.9CB'D'#:7`'RR"68RXZ16977111Cosmos-96508 Dec 1977P469 x 520 km x 74.0DC'E'#:7`'RR"68RXZ17077116Cosmos-96713 Dec 1977P973 x 1013 km x 66.0CD'xF'#:7`'RR"68RXZ17177119Cosmos-96816 Dec 1977P783 x 822 km x 74.0DE'qG'#:7`'RR"68RXZ17277122Cosmos-97123 Dec 1977P993 x 1021 km x 83.0IxF'oH'#:7`'RR">@Z`b17378005Cosmos-976/98310 Jan 1978P1450 x 1500 km x 74.0DqG'hI'#:7`'RR"68RXZ17478007Cosmos-98517 Jan 1978P960 x 1032 km x 83.0CoH'`J'#:7`'RR"68RXZ17578019Cosmos-99017 Feb 1978P783 x 824 km x 74.0DhI'YK'#:7`'RR"68RXZ17678022Cosmos-99128 Feb 1978P972 x 1022 km x 83.0D`J'RL'#:7`'RR"68RXZ17778028Cosmos-99415 Mar 1978P996 x 1023 km x 82.9DYK'KM'#:7`'RR"68RXZ17878031Cosmos-99628 Mar 1978P970 x 1021 km x 82.9GRL'MN'#F7`'RR"u0w<>X^`17978034Cosmos 100031 Mar 1978P978 x 1024 km x 83.0DKM'FO'#:7`'RR"8:TZ\18078046Cosmos-100612 May 1978P383 x 417 km x 65.8DMN'K'#:7`'RR"8:TZ\181FO'K'@$78049Cosmos-100817 May 1978P501 x 551 km x 74.0EFO'E'#:7`'RR"8:TZ\18278053Cosmos-101123 May 1978P978 x 1026 km x 82.9KK'E'#:7`'RR"BD^df18378056Cosmos-1013/102007 Jun 1978P1456 x 1539 km x 74.0DE'>'#:7`'RR"8:TZ\18478063Cosmos-102321 Jun 1978P784 x 822 km x 74.1EE'8'#:7`'RR"8:TZ\18578074Cosmos-102727 Jul 1978P979 x 1015 km x 82.9K>'8'#:7`'RR"BD^df18678091Cosmos-1034/104104 Oct 1978P1458 x 1538 km x 74.0Z8'T'#T7`'RR"*=ԉL$df18778099A: Intercosmos 18B: Magion 125 Oct 1978P407 x 768 km x 83.0D8'M'#:7`'RR"8:TZ\18878105Cosmos-104817 Nov 1978P788 x 824 km x 74.0KT'M'#:7`'RR"BD^df18978109Cosmos-1051/105805 Dec 1978P1451 x 1530 km x 74.0DM'F'#:7`'RR"8:TZ\19078115Cosmos-106215 Dec 1978P508 x 548 km x 74.0DM'?'#:7`'RR"8:TZ\19178119Cosmos-106421 Dec 1978P435 x 991 km x 83.0DF'8'#:7`'RR"8:TZ\19278120Cosmos-106523 Dec 1978K346 x 556 km x 50.7F?'3'#:7`'RR"8:TZ\19378122Cosmos-106726 Dec 1978P1184 x 1226 km x 83.0E8'-'#:7`'RR"8:TZ\19479003Cosmos-107216 Jan 1979P983 x 1030 km x 83.0D3'&'#:7`'RR"8:TZ\19579010Cosmos-107508 Feb 1979P475 x 521 km x 65.8G-'"'#:7`'RR">@Z`b19679020Intercosmos-1928 Feb 1979P502 x 996 km x 74.0K&'.'#:7`'RR"BD^df19779026Cosmos-1081/108815 Mar "'.'@$1979P1455 x 1586 km x 74.0E"'('#:7`'RR"8:TZ\19879026Cosmos-108921 Mar 1979P986 x 1016 km x 83.0E.'"'#:7`'RR"8:TZ\19979028Cosmos-109107 Apr 1979P985 x 1024 km x 83.0E(''#:7`'RR"8:TZ\20079030Cosmos-109212 Apr 1979P983 x 1021 km x 83.0E"''#:7`'RR"8:TZ\20179046Cosmos-110431 May 1979P979 x 1022 km x 83.0E''#F7`'RR"e艂:<V\^20279051Bhaskara 107 Jun 1979K512 x 557 km x 50.7D''#:7`'RR"8:TZ\20379060Cosmos-111028 Jun 1979P792 x 833 km x 74.0D''#:7`'RR"8:TZ\20479063Cosmos-111206 Jul 1979K345 x 552 km x 50.7D''#:7`'RR"8:TZ\20579065Cosmos-111411 Jul 1979P507 x 558 km x 74.0D''#:7`'RR"8:TZ\20679078Cosmos-112528 Aug 1979P795 x 834 km x 74.0K''#:7`'RR"BD^df20779084Cosmos-1130/113726 Sep 1979P1446 x 1514 km x 74.0D''#:7`'RR"8:TZ\20879089Cosmos-114011 Oct 1979P781 x 818 km x 74.0E''#:7`'RR"8:TZ\20979090Cosmos-114116 Oct 1979P976 x 1014 km x 82.9G''#:7`'RR">@Z`b21079096Intercosmos-2001 Nov 1979P467 x 523 km x 74.0D''#:7`'RR"8:TZ\21179100Cosmos-114605 Dec 1979P441 x 497 km x 65.9E''#:7`'RR"8:TZ\21280003Cosmos-115014 Jan 1980P989 x 1023 km x 83.0E''#:7`'RR"8:TZ\21380007Cosmos-115325 Jan 1980P983 x 1031 km x 83.0K'(#:7`''(@$RR"BD^df21480012Cosmos-1156/116311 Feb 1980P1450 x 1528 km x 74.0E'(#:7`'RR"8:TZ\21580022Cosmos-116818 Mar 1980P981 x 1026 km x 82.9D((#:7`'RR"8:TZ\21680023Cosmos-116927 Mar 1980P478 x 521 km x 65.8E((#:7`'RR"8:TZ\21780026Cosmos-117103 Apr 1980P976 x 1017 km x 65.8E((#:7`'RR"8:TZ\21880037Cosmos-117914 May 1980P310 x 1570 km x 83.0E((#:7`'RR"8:TZ\21980039Cosmos-118120 May 1980P992 x 1020 km x 83.0D((#:7`'RR"8:TZ\22080047Cosmos-118606 Jun 1980P473 x 519 km x 74.0D((#:7`'RR"8:TZ\22180056Cosmos-119001 Jul 1980P792 x 829 km x 74.0K((#:7`'RR"BD^df22280058Cosmos-1192/119909 Jul 1980P1451 x 1522 km x 74.0D( (#:7`'RR"8:TZ\22380067Cosmos-120431 Jul 1980K346 x 546 km x 50.7D( (#:7`'RR"8:TZ\22480083Cosmos-121514 Oct 1980P499 x 553 km x 74.0E ( (#:7`'RR"8:TZ\22580097Cosmos-122505 Dec 1980P967 x 1041 km x 82.9E ( (#:7`'RR"8:TZ\22680099Cosmos-122610 Dec 1980P982 x 1025 km x 83.0K ( (#:7`'RR"BD^df22780102Cosmos-1228/123524 Dec 1980P1415 x 1491 km x 74.0E ((#:7`'RR"8:TZ\22881003Cosmos-123816 Jan 1981P411 x 1976 km x 83.0E ((#:7`'RR"8:TZ\22981006Cosmos-124121 Jan 1981P973 x 1009 km x 65.8G(@(#:7`'RR"(@(@$>@Z`b23081011Intercosmos-2106 Feb 1981P475 x 520 km x 74.0E(A(#:7`'RR"8:TZ\23181013Cosmos-124412 Feb 1981P975 x 1024 km x 82.9K@(B(#:7`'RR"BD^df23281022Cosmos-1250/125706 Mar 1981P1450 x 1500 km x 74.0EA(C(#:7`'RR"8:TZ\23381033Cosmos-126309 Apr 1981P430 x 1989 km x 83.0DB(D(#:7`'RR"8:TZ\23481041Cosmos-126907 May 1981P797 x 833 km x 74.0EC(~E(#:7`'RR"8:TZ\23581053Cosmos-127504 Jun 1981P983 x 1026 km x 83.0KD(~F(#:7`'RR"BD^df23681074Cosmos-1287/129406 Aug 1981P1446 x 1508 km x 74.0E~E(xG(#:7`'RR"8:TZ\23781077Cosmos-129512 Aug 1981P966 x 1026 km x 82.9D~F(qH(#:7`'RR"8:TZ\23881084Cosmos-130228 Aug 1981P783 x 824 km x 74.0DxG(jI(#:7`'RR"8:TZ\23981087Cosmos-130404 Sep 1981P917 x 984 km x 83.0EqH(dJ(#:7`'RR"8:TZ\24081091Cosmos-130818 Sep 1981P978 x 1017 km x 82.9DjI(]K(#:7`'RR"8:TZ\24181095Cosmos-131023 Sep 1981P478 x 524 km x 65.9DdJ(VL(#:7`'RR"8:TZ\24281097Cosmos-131129 Sep 1981P470 x 521 km x 83.0E]K(VM(#F7`'RR"e艂:<V\^24381115Bhaskara 220 Nov 1981K514 x 557 km x 50.7KVL(VN(#:7`'RR"BD^df24481116Cosmos-1320/132728 Nov 1981P1507 x 1632 km x 74.0GVM(RO(#:7`'RR":<V\^24581120Radio 3 to 817 Dec 1981P1685 x 1794 km x 83.0DVN(W(#:7`'RR"8:TZ\RO(W(@$24682001Cosmos-133107 Jan 1982P776 x 819 km x 74.0ERO(Q(#:7`'RR"8:TZ\24782003Cosmos-133314 Jan 1982P989 x 1029 km x 82.9DW(J(#:7`'RR"8:TZ\24882007Cosmos-133529 Jan 1982P487 x 535 km x 74.0EQ(D(#:7`'RR"8:TZ\24982012Cosmos-133918 Feb 1982P975 x 1029 km x 82.9EJ(>(#:7`'RR"8:TZ\25082024Cosmos-134424 Mar 1982P987 x 1023 km x 82.9DD(7(#:7`'RR"8:TZ\25182026Cosmos-134531 Mar 1982P507 x 550 km x 74.0E>(1(#:7`'RR"8:TZ\25282030Cosmos-134908 Apr 1982P989 x 1025 km x 83.0D7(*(#:7`'RR"8:TZ\25382034Cosmos-135121 Apr 1982K349 x 555 km x 50.7D1(#(#:7`'RR"8:TZ\25482037Cosmos-135428 Apr 1982P795 x 829 km x 74.0K*(#(#:7`'RR"BD^df25582040Cosmos-1357/136406 May 1982P1449 x 1520 km x 74.0D#((#:7`'RR"8:TZ\25682051Cosmos-137101 Jun 1982P793 x 833 km x 74.1D#((#:7`'RR"8:TZ\25782054Cosmos-137403 Jun 1982K158 x 204 km x 50.7E((#:7`'RR"8:TZ\25882055Cosmos-137506 Jun 1982P990 x 1021 km x 65.9D((#:7`'RR"8:TZ\25982061Cosmos-138018 Jun 1982P156 x 732 km x 82.9F((#:7`'RR"8:TZ\26082066Cosmos-138329 Jun 1982P1004 x 1041 km x 83.0E((#:7`'RR"8:TZ\26182069Cosmos-138607 Jul 1982P965 x 1010 km x 83.0K( (#:7`'RR"BD^df26282073Cosmos-1388/139521 Jul 1982P1448 x 1515 km x 74.0( (@$D((#:7`'RR"8:TZ\26382076Cosmos-139729 Jul 1982K346 x 549 km x 50.7E ((#:7`'RR"8:TZ\26482102Cosmos-141719 Oct 1982P978 x 1023 km x 83.0D((#:7`'RR"8:TZ\26582104Cosmos-141821 Oct 1982K362 x 417 km x 50.7D((#:7`'RR"8:TZ\26682109Cosmos-142011 Nov 1982P782 x 820 km x 74.0D((#:7`'RR"8:TZ\26782121Cosmos-142729 Dec 1982P460 x 494 km x 65.8E((#:7`'RR"8:TZ\26883001Cosmos-142812 Jan 1983P972 x 1017 km x 82.9I((#:7`'RR"BD^df26983002Cosmos-1429/143619 Jan 1983P629 x 678 km x 81.2D((#:7`'RR"8:TZ\27083017Cosmos-144515 Mar 1983K158 x 208 km x 50.7E((#:7`'RR"8:TZ\27183021Cosmos-144725 Mar 1983P975 x 1025 km x 83.0E((#:7`'RR"8:TZ\27283023Cosmos-144828 Mar 1983P977 x 1017 km x 83.0D((#:7`'RR"8:TZ\27383027Cosmos-145007 Apr 1983P474 x 515 km x 65.9D((#:7`'RR"8:TZ\27483031Cosmos-145212 Apr 1983P786 x 826 km x 74.0D((#:7`'RR"8:TZ\27583034Cosmos-145319 Apr 1983P473 x 520 km x 74.0E((#:7`'RR"8:TZ\27683042Cosmos-145906 May 1983P960 x 1028 km x 83.0E((#:7`'RR"8:TZ\27783046Cosmos-146319 May 1983P307 x 1530 km x 82.9E((#:7`'RR"8:TZ\27883048Cosmos-146424 May 1983P985 x 1022 km x 82.9D()#:7`'RR"()@$8:TZ\27983049Cosmos-146526 May 1983K349 x 551 km x 50.7K()#:7`'RR"BD^df28083069Cosmos-1473/148006 Jul 1983P1488 x 1511 km x 74.0D))#:7`'RR"8:TZ\28183079Cosmos-148603 Aug 1983P786 x 820 km x 74.1D))#:7`'RR"8:TZ\28283091Cosmos-149431 Aug 1983K341 x 561 km x 50.7D))#:7`'RR"8:TZ\28383101Cosmos-150130 Sep 1983P470 x 516 km x 82.9D))#:7`'RR"8:TZ\28483102Cosmos-150205 Oct 1983P372 x 411 km x 65.8D))#:7`'RR"8:TZ\28583103Cosmos-150312 Oct 1983P791 x 827 km x 74.0E))#:7`'RR"8:TZ\28683108Cosmos-150626 Oct 1983P969 x 1026 km x 83.0E)~)#:7`'RR"8:TZ\28783111Cosmos-150811 Nov 1983P400 x 1964 km x 83.0E)x )#:7`'RR"8:TZ\28883120Cosmos-151308 Dec 1983P977 x 1029 km x 83.0D~)q )#:7`'RR"8:TZ\28983125Cosmos-151727 Dec 1983K208 x 288 km x 50.7Kx )q )#:7`'RR"BD^df29084001Cosmos-1522/152905 Jan 1984P1449 x 1510 km x 74.0Eq )k )#:7`'RR"8:TZ\29184003Cosmos-153111 Jan 1984P994 x 1023 km x 82.9Dq )d )#:7`'RR"8:TZ\29284007Cosmos-153426 Jan 1984P470 x 519 km x 65.8Ek )^)#:7`'RR"8:TZ\29384010Cosmos-153501 Feb 1984P974 x 1029 km x 83.0Dd )W)#:7`'RR"8:TZ\29484019Cosmos-153821 Feb 1984P781 x 820 km x 74.0E^)]@)#:7`'RR"8:TZW)]@)@$\29584043Cosmos-155011 May 1984P993 x 1025 km x 83.0EW)WA)#:7`'RR"8:TZ\29684046Cosmos-155317 May 1984P997 x 1020 km x 82.9K]@)WB)#:7`'RR"BD^df29784052Cosmos-1559/156628 May 1984P1444 x 1512 km x 74.0DWA)PC)#:7`'RR"8:TZ\29884056Cosmos-157008 Jun 1984P792 x 830 km x 74.0EWB)JD)#:7`'RR"8:TZ\29984062Cosmos-157421 Jun 1984P985 x 1021 km x 83.0EPC)DE)#:7`'RR"8:TZ\30084067Cosmos-157727 Jun 1984P974 x 1023 km x 83.0EJD)>F)#:7`'RR"8:TZ\30184068Cosmos-157828 Jun 1984K296 x 1673 km x 50.7EDE)8G)#:7`'RR"8:TZ\30284100Cosmos-159813 Sep 1984P987 x 1029 km x 83.0D>F)1H)#:7`'RR"8:TZ\30384104Cosmos-160127 Sep 1984P477 x 521 km x 65.8E8G)+I)#:7`'RR"8:TZ\30484109Cosmos-160511 Oct 1984P969 x 1031 km x 82.9E1H)%J)#:7`'RR"8:TZ\30584118Cosmos-161015 Nov 1984P987 x 1027 km x 83.0D+I)K)#:7`'RR"8:TZ\30684126Cosmos-161419 Dec 1984K208 x 228 km x 50.7D%J)L)#:7`'RR"8:TZ\30784127Cosmos-161520 Dec 1984P437 x 501 km x 65.9DK)M)#:7`'RR"8:TZ\30885006Cosmos-162417 Jan 1985P787 x 825 km x 74.0EL) N)#:7`'RR"8:TZ\30985011Cosmos-162701 Feb 1985P977 x 1031 km x 82.9DM)O)#:7`'RR"8:TZ\31085018Cosmos-163127 Feb 1985T474 x 517 km x 65.9E N) )#:7`'RR"8:TZ\31185022Cosmos-163414 Mar 1985P976 x 1024 km x 82.9O) )@$KO) )#:7`'RR"BD^df31285023Cosmos-1635/164221 Mar 1985P1482 x 1526 km x 74.0E ))#:7`'RR"8:TZ\31385041Cosmos-165530 May 1985P992 x 1019 km x 82.9D ))#:7`'RR"8:TZ\31485050Cosmos-166219 Jun 1985P478 x 521 km x 65.9D))#:7`'RR"8:TZ\31585079Cosmos-168004 Sep 1985P787 x 822 km x 74.1D))#:7`'RR"8:TZ\31685089Cosmos-168802 Oct 1985K347 x 548 km x 50.7E))#:7`'RR"8:TZ\31785110Cosmos-170428 Nov 1985P986 x 1023 km x 82.9E))#:7`'RR"8:TZ\31885116Cosmos-170919 Dec 1985P982 x 1026 km x 82.9K))#:7`'RR"BD^df31986002Cosmos-1716/172309 Jan 1986P1447 x 1516 km x 74.0E)߈)#:7`'RR"8:TZ\32086005Cosmos-172516 Jan 1986P989 x 1016 km x 82.9E)ى)#:7`'RR"8:TZ\32186008Cosmos-172723 Jan 1986P982 x 1029 km x 82.9D߈)Ҋ)#:7`'RR"8:TZ\32286030Cosmos-174118 Apr 1986P784 x 824 km x 74.0Eى)̋)#:7`'RR"8:TZ\32386037Cosmos-174523 May 1986P984 x 1024 km x 83.0KҊ)̌)#:7`'RR"BD^df32486042Cosmos-1748/175506 Jun 1986P1400 x 1500 km x 74.0E̋)ƍ)#:7`'RR"8:TZ\32586047Cosmos-175918 Jun 1986P985 x 1016 km x 82.9Ď))#:7`'RR"8:TZ\32686052Cosmos-176316 Jul 1986P761 x 814 km x 74.1Dƍ))#:7`'RR"8:TZ\32786067Cosmos-177603 Sep 1986P478 x 521 km x 74.0D))#:7`'RR))@$"8:TZ\32886070Cosmos-177709 Sep 1986P781 x 819 km x 74.0D))#:7`'RR"8:TZ\32986083Cosmos-178827 Oct 1986P468 x 517 km x 65.8E))#:7`'RR"8:TZ\33086086Cosmos-179113 Nov 1986P972 x 1026 km x 83.0K))#:7`'RR"BD^df33186092Cosmos-1794/180121 Nov 1986P1500 x 1500 km x 74.0E))#:7`'RR"8:TZ\33286093Cosmos-180224 Nov 1986P985 x 1038 km x 83.0E))#:7`'RR"8:TZ\33386100Cosmos-180817 Dec 1986P995 x 1033 km x 83.0D))#:7`'RR"8:TZ\33487006Cosmos-181421 Jan 1987P775 x 815 km x 74.0D))#:7`'RR"8:TZ\33587007Cosmos-181522 Jan 1987K345 x 550 km x 50.7E))#:7`'RR"8:TZ\33687009Cosmos-181629 Jan 1987P980 x 1024 km x 82.9E))#:7`'RR"8:TZ\33787017Cosmos-182118 Feb 1987P983 x 1029 km x 82.9F))#F7`'RR",!w<>X^`33887049Cosmos 185009 Jun 1987P783 x 806 km x 74.0):)#7`'RR"~$!w%!w&!w'!w(!w)!w*!w+!w02LRT33987051A: Cosmos 1852B: Cosmos 1853C: Cosmos 1854D: Cosmos 1855E: Cosmos 1856F: Cosmos 1857G: Cosmos 1858H: Cosmos 185916 Jun 1987P1440 x 1507 km x 74.0F);)#F7`'RR"N!w<>X^`34087054Cosmos 186123 Jun 1987P982 x 997 km x 82.9E:)5)#:7`'RR"8:TZ\34187057Cosmos-186407 Jul 1987P977 x 1019 km x 83.0D;).)#:7`'RR"8:TZ\34287061Cosmos-186814 Jul 1987P279 x 726 km x 74.0E5)4*#:7`'RR"8:TZ\34387087Cosmos-1891.)4*@$14 Oct 1987P957 x 1030 km x 83.0D.)-*#:7`'RR"8:TZ\34487098Cosmos-189801 Dec 1987P777 x 810 km x 74.0D4*&*#:7`'RR"8:TZ\34587103Cosmos-190215 Dec 1987P373 x 417 km x 66.0E-* *#:7`'RR"8:TZ\34687106Cosmos-190423 Dec 1987P969 x 1008 km x 82.9&**#7`'RR"~'w'w'w'w'w'w(w(w02LRT34788016A: Cosmos 1924B: Cosmos 1925C: Cosmos 1926D: Cosmos 1927E: Cosmos 1928F: Cosmos 1929G: Cosmos 1930H: Cosmos 193111 Mar 1988P1400 x 1500 km x 74.0G **#F7`'RR" (w<>X^`34888023Cosmos 193422 Mar 1988P952 x 1009 km x 83.0D**#:7`'RR"8:TZ\34988029Cosmos-193705 Apr 1988P774 x 813 km x 74.0D**#:7`'RR"8:TZ\35088053Cosmos-195421 Jun 1988P780 x 806 km x 74.0F**#F7`'RR"c(w<>X^`35188060Cosmos 195814 Jul 1988P375 x 417 km x 65.8G* *#F7`'RR"d(w<>X^`35288062Cosmos 195918 Jul 1988P975 x 1019 km x 83.0F* *#F7`'RR"(w<>X^`35388065Cosmos 196028 Jul 1988P475 x 518 km x 65.9F * *#F7`'RR" )w<>X^`35489005Cosmos 199226 Jan 1989P777 x 814 km x 74.0G * *#F7`'RR"gx<>X^`35589012Cosmos 200214 Feb 1989P187 x 2315 km x 65.8G * *#F7`'RR"gx<>X^`35689017Cosmos 200422 Feb 1989P993 x 1031 km x 83.0 *{*#7`'RR"~gxgxex|ex}ex~exexex02LRT35789025A: Cosmos 2008B: Cosmos 2009C: Cosmos 2010D: Cosmos 2011E: Cosmos 2012F: Cosmos 2013G: Cosmos 2014H: Cosmos 201524 Mar 1989P1445 x 1510 km x 74.0G *@*#F7`'RR"ex<{*@*@$>X^`35889028Cosmos 201604 Apr 1989P970 x 1010 km x 82.9G{*A*#F7`'RR"ex<>X^`35989042Cosmos 202607 Jun 1989P970 x 1020 km x 82.9F@*B*#F7`'RR"ex<>X^`36089045Cosmos 202714 Jun 1989P480 x 510 km x 65.8FA*C*#F7`'RR"R򲟉:<V\^36189050Nadezhda 104 Jul 1989P980 x 1020 km x 83.0GB*D*#F7`'RR"ex<>X^`36289059Cosmos 203425 Jul 1989P970 x 1010 km x 82.9FC*E*#F7`'RR"-fx<>X^`36390004Cosmos 205618 Jan 1990P775 x 810 km x 74.0GD*F*#F7`'RR"0fx<>X^`36490012Cosmos 205906 Feb 1990P190 x 2280 km x 65.8FE*G*#F7`'RR"S򲟉:<V\^36590017Nadezhda 227 Feb 1990P956 x 1021 km x 83.0GF*H*#F7`'RR"Sfx<>X^`36690023Cosmos 206120 Mar 1990P973 x 1017 km x 82.9G*DJ*#7`'RR"~VfxWfxXfxYfxZfx[fxfx~fx02LRT36790029A: Cosmos 2064B: Cosmos 2065C: Cosmos 2066D: Cosmos 2067E: Cosmos 2068F: Cosmos 2069G: Cosmos 2070H: Cosmos 207106 Apr 1990P1415 x 1563 km x 74.0GH*FK*#F7`'RR"fx<>X^`36890036Cosmos 207420 Apr 1990P967 x 1006 km x 83.0DDJ*?L*#:7`'RR"8:TZ\36990038Cosmos-207525 Apr 1990P515 x 584 km x 74.0EFK*9M*#:7`'RR"8:TZ\37090078Cosmos-209828 Aug 1990P407 x 2001 km x 82.9G?L*;N*#F7`'RR"&x<>X^`37190083Cosmos 210014 Sep 1990P984 x 1027 km x 82.9F9M*X^`37290111Cosmos 211210 Dec 1990P770 x 820 km x 74.1F;N*I*#F7`'RR"n!:<V\^37391X^`37491007Cosmos 212305 Feb 1991P981 x 1019 km x 82.9KI*K*#:7`'RR"BD^df37591009Cosmos-2125/213212 Feb 1991P1452 x 1495 km x 74.0EK*E*#:7`'RR"8:TZ\37691013Cosmos-213526 Feb 1991P925 x 1020 km x 82.8FK*F*#F7`'RR"T򲟉:<V\^37791019Nadezhda 312 Mar 1991P960 x 1000 km x 82.9DE*?*#:7`'RR"8:TZ\37891021Cosmos-213719 Mar 1991T448 x 495 km x 65.8GF*A*#F7`'RR"$x<>X^`37991029Cosmos 214216 Apr 1991P983 x 1031 km x 83.0D?*:*#:7`'RR"8:TZ\38091041Cosmos-215011 Jun 1991P780 x 810 km x 74.0EA*4*#:7`'RR"8:TZ\38191059Cosmos-215422 Aug 1991P990 x 1020 km x 82.9D:*-*#:7`'RR"8:TZ\38291072Cosmos-216410 Oct 1991P290 x 720 km x 74.0G4*/*#F7`'RR"%x<>X^`38391081Cosmos 217327 Nov 1991P965 x 1030 km x 82.9E-*)*#:7`'RR"8:TZ\38492008Cosmos-218017 Feb 1992P980 x 1030 km x 82.9E/*#*#:7`'RR"8:TZ\38592012Cosmos-218109 Mar 1992P995 x 1030 km x 82.9E)**#:7`'RR"8:TZ\38692020Cosmos-218415 Apr 1992P990 x 1030 km x 82.9N#* *#:7`'RR"HJdjl38792030Cosmos-2187 to 219403 Jun 1992P1445 x 1505 km x 74.0E**#:7`'RR"8:TZ\38892036Cosmos-219501 Jul 1992P975 x 1025 km x 82.9D **#:7`'RR"8:TZ\38992053Cosmos-220812 Aug 1992P790**@$ x 810 km x 74.0G*!*#F7`'RR"+x<>X^`39092073Cosmos 221829 Oct 1992P970 x 1015 km x 82.9G*#*#F7`'RR",x<>X^`39193001Cosmos 223012 Jan 1993P990 x 1020 km x 83.0G!*%*#F7`'RR" ,x<>X^`39293008Cosmos 223309 Feb 1993P970 x 1020 km x 82.9G#*'*#F7`'RR",x<>X^`39393020Cosmos 223901 Apr 1993P980 x 1010 km x 82.9F%*(*#F7`'RR"`,x<>X^`39493036Cosmos 225116 Jun 1993P780 x 820 km x 74.0G'***#F7`'RR",x<>X^`39593067Cosmos 226526 Oct 1993P300 x 1600 km x 82.9G(*,*#F7`'RR",x<>X^`39693070Cosmos 226602 Nov 1993P960 x 1030 km x 82.9G**.*#F7`'RR",x<>X^`39794024Cosmos 227926 Apr 1994P973 x 1019 km x 82.9F,*/*#F7`'RR"U򲟉:<V\^39894041Nadezhda 414 Jul 1994P977 x 1018 km x 82.9G.*1*#F7`'RR",x<>X^`39994045Cosmos 228502 Aug 1994P974 x 1013 km x 74.0G/*3*#F7`'RR" -x<>X^`40094061Cosmos 229227 Sep 1994P400 x 1950 km x 83.0F1*4*#F7`'RR"-x<>X^`40194083Cosmos 229820 Dec 1994P785 x 810 km x 74.0E3*4*#F7`'RR"eL͉8:TZ\40295002Tsikada 124 Jan 1995P982 x 1031 km x 82.9F4*5*#F7`'RR"u4x<>X^`40395008Cosmos 230602 Mar 1995P472 x 519 km x 65.5G4*7*#F7`'RR"2x<>X^`40495012Cosmos 231022 Mar 1995P996 x 1024 km x 82.9G5*E+#F7`'RR"2x<>X^`405950327*E+@$Cosmos 231505 Jul 1995P988 x 1027 km x 82.9F7*F+#F7`'RR"3x<>X^`40695052Cosmos 232106 Oct 1995P258 x 793 km x 82.9GE+H+#F7`'RR"3x<>X^`40796004Cosmos 232716 Jan 1996P952 x 1021 km x 83.0GF+J+#F7`'RR"D3x<>X^`40896025Cosmos 233224 Apr 1996P303 x 1575 km x 83.02H+7+#Fd7`'RR"F3x<>X^`40996052Cosmos 233405 Sep 1996P2J+$+#Fd7`'RR"H3x<>X^`41096071Cosmos 233620 Dec 1996P27++#Fd7`'RR"n3x<>X^`41197017Cosmos 234117 Apr 1997P4$++#Rh7`'RR""s3x%>@"\bd41297052Cosmos 234623 Sep 1997P&+,+# 8+d+1EHZ5d+ +-CycloneD,++5 : " Cyclonee4d+ +1 2h 㭄؉>ɉby Jean-Jacques Serralisting by Gunter KrebsJ#+W+' F Origin: ICBM of third generation + +& !In the early sixties, Yangel was successful in the competition opposing the R-9 of Korolev to the UR-200 of Chelomei missiles for the providing of ICBMs of second generation. His two-stage R-16 missile (SS-7 Saddler) was 31 m in height, 3 m diameter and weighed 150 tons. Despite the important accident that occured on first test in October 1960 the R-16 was deployed in 190 silos. A space launcher project derived from the R-16 named 64S2 or Cyclone was abandonned.The second ICBM of the KB Yantel was the R-26/8K66 missile. It seems that this program did not reach the flight tests phase. (some sources state that R-26 is the ground surface of SS-8)}W++' The third ICBM of the KB Yantel (now NPO Yuzhnoye) in Ukraine was the R-36 /8K67 (SS-9 Scarp). The DoD counted 5 variants of this third generation missile: Mod 1 the original design, Mod 2 the serial model with unique payload. From Mod 3, tested as a FOBS (Fractional Orbit Bomb System), the missile was designated R-36-0/8K69. It was followed by the Mod 4 equipped with 4 MRVs and the Mod 5, an ASAT (AntiSATellite) weapon.The basic rocket had 2 stages both 3 m diameter wide. The SS-9 Mod 2 was 36 m in height and weighed 190 tons. It was the biggest known missile at that time. The first stage featured a propulsion system with 6 combustion chambers (RD-251) using NTO/UDMH. The engines burned during 120 seconds providing 2450 kN at ground level and 2750 kN in vacuum thrust (Isp = 309 seconds). Four steerable verniers enabled the flight control and the motor thrust balance during the stages separation. The second stage was powered by a two-chambers RD-252 motor burning the same propellants. It provided 883 kN thrust (Isp = 293 seconds) during 125 seconds. Moreover the missile's RV had it's own engine... making the vehicle 3 stages. +@+% AThe testings went on during several year+@+,+s (1963-65 for Mod 1 & 2, the 1969-70 and 1973 for Mod 4). A total of about 300 missiles were deployed from 1966 on.@+@+' 2 2-stage R-36 launchers]@+WC+8 >qi- In the early sixties two projects of Fractional Orbit Bombardment Systems (FOBS) launchers were being designed by the soviets: the GR-1 (SS-10 Scrag) and the Yantel R-36 in version 3. The former was cancelled after 1965.The second named F1r / SL11 in the US was tested 18 times from Tyuratam between 1966 and 1971: 2 un-official flights in 1966 and 16 Cosmos (including Cosmos 316 which decayed accidentally in the Western USA).Note: a FOBS-type RV (provided by Khrunichev/KB Saliout) was used in January 1995 for the German & Japanese EXPRESS experiment which was incorrectly orbited by Mu-3S.@+4F+9 @Iqid/{The launcher known as F1m / SL-11 was developed as antisatellite system. In a first stage (1968-1970) the same launcher was used from Tyuratam to launch target and interceptors in the Cosmos program. From February 1971 on, targets were launched by Cosmos C1 / SL8 from Plesetsk. The program stopped in 1982.Meanwhile the launcher would have been equipped on an enhanced second stage for conventional space operations. According to Jane's Space Directory the new motor would provide 956 kN in vacuum (ISp = 324 seconds) during up to 160 seconds. This launcher known as Cyclone 2 (11K79) was used to launch reconnaissance satellites from Tyuratam: Rorsat and Eorsat.J#WC+~F+' FO 3-stage R-36 launcher: Cyclone 34F+H+9 @3xA뉢"In 1977 the two-stage basic model was equipped with a S5M top stage powered by an RD-861 (NTO/UDMH) providing 78 kN thrust during 118 seconds. It could be re-ignited in orbit. In this version Cyclone 3 (11K68) weighs around 185 tons for 39.3 m heigh and a 2.7 m diameter cap.Launched from Plesetsk it can orbit 3.6 tons in LEO but it is used for satellite in circular 650, 850, 100 or 1500 km altitude:- civilian satellites: Meteor, Ocean, IntercosmosL~F+I+5 :CV$㓉!ְ- military satellites: SIGINT, geodesy, telecommunications (Gonets)<H+CI+' *O Commercial version;I+~K+& +A firmed named Satellite Delivery Systems, a subsidiary of Rockwell Aerospace (USA) and Younoye (Ukraine) was founded in 1996 to sell Cyclone launchers. This launcher which flies from Plesetsk was never used to polar-orbit satellites because is should fly over the US (all polar launches are from Tyuratam). Therefore the Cyclone launcher will get an additional top stage. This stage is built by Youjnoye. Its reignitable motor burns stockable propellant (NTO-UDMH) and was already used more than 50 times for military missions.<CI+K+' * Cyclone 3 launches m~K+L+#64]@   $& <> \^ #Launch idPayloadLaunch dateStatus/Comment (orbit in perigee x apogee x inc. x period)*K+M+#T4]@  24NP177055Cosmos 92124 Jun 1977*L+vN+#T4]@  24NP277095Cosmos 95624 Sep 1977*M+DO+#T4]@  24NP377123Cosmos 97227 Dec 19779vN+3+#$r4]@  _剂PRln478067CosmoDO+3+,+s 1025 [Tselina-D]28 Jun 1978>DO++#|4]@  Z\vx578100A: Cosmos 1045B: RS 1C: RS 226 Oct 197873++#$n4]@  뉢LNhj679011Cosmos 1076 [Ocean-E]12 Feb 19797+ق+#$n4]@  뉢LNhj780005Cosmos 1151 [Ocean-E]23 Jan 1980E+΃+#04]@  !&VXrt& 8n/aCosmos (1242) [Geo-IK #[1a]]23 Jan 1981Failure9ق++#$r4]@  _剂PRln981082Cosmos 1300 [Tselina-D]24 Aug 1981,΃++#$X4]@  4y`68RT1081093Aurole 321 Sep 19817+h+#$n4]@  !&LNhj1181098Cosmos 1312 [Geo-IK]30 Sep 1981:+L+#$t4]@  _剂RTnp1281117Cosmos 1328 [Tselina-D]03 Dec 1981+h++#V4]@  46PR1382085Meteor 2-825 Mar 1982:L++#$t4]@  _剂RTnp1482059Cosmos 1378 [Tselina-D]10 Jun 1982:++#$t4]@  _剂RTnp1582092Cosmos 1408 [Tselina-D]16 Spe 19827+Ċ+#$n4]@  !&LNhj1682096Cosmos 1410 [Geo-IK]29 Sep 1982:++#$t4]@  _剂RTnp1783037Cosmos 1455 [Tselina-D]23 Apr 1983:Ċ++#$t4]@  _剂RTnp1883061Cosmos 1470 [Tselina-D]23 Jun 19839+o+#$r4]@  뉢PRln1983099Cosmos 1500 [Ocean-OE]28 Sep 19837+P+#$n4]@  !&LNhj2083115Cosmos 1510 [Geo-IK]24 Oct 1983:o+4+#$t4]@  _剂RTnp2183122Cosmos 1515 [Tselina-D]15 Dec 1983:P+$+#$t4]@  _剂RTnp2284013Cosmos 1536 [Tselin4+$+,+a-D]08 Feb 1984:4++#$t4]@  _剂RTnp2384027Cosmos 1544 [Tselina-D]15 Mar 1984,$++#X4]@  68RT2484072Meteor 2-1105 Jul 19846++#$l4]@  !&LNfh2584084Cosmos 1589 [Geo-IK]8 Aug 19849++#$r4]@  뉢PRln2684105Cosmos 1602 [Ocean-OE]28 Sep 1984:++#$t4]@  _剂RTnp2784111Cosmos 1606 [Tselina-D]18 Oct 1984c++#04]@  VXr(t&  2884120Cosmos 1612 [Meteor (3-1a)]27 Nov 1984Failure: stage 3 failed to reignite@+|+#$4]@  <^`z|2985003Cosmos 1617 - 1622 [Strela-3]15 Jan 1985:+`+#$t4]@  _剂RTnp3085009Cosmos 1626 [Tselina-D]24 Jan 1985,|+0+#X4]@  68RT3185013Meteor 2-1206 Feb 1985:`++#$t4]@  _剂RTnp3285020Cosmos 1633 [Tselina-D]05 Mar 198570++#$n4]@  !&LNhj3385047Cosmos 1660 [Geo-IK]14 Jun 1985:++#$t4]@  _剂RTnp3485058Cosmos 1666 [Tselina-D]08 Jul 1985:++#$t4]@  _剂RTnp3585069Cosmos 1674 [Tselina-D]08 Jul 1985@++#$4]@  <^`z|3685094Cosmos 1690 - 1695 [Strela-3]09 Oct 1985++v+#V4]@  46PR3785100Meteor 3-124 Oct 1985:+Z+#$t4]@  _剂RTnp3885108Cosmos 1703 [Tselina-D]22 Nov 1985:v+>+#$t4]@  _剂RTnp3985113Cosmos 1707 [Tselina-D]12 Dec 1985,Z+,#X4]@  68RT4085119Meteor 2-1326>+,,+ Dec 1985:>+,#$t4]@  _剂RTnp4186006Cosmos 1726 [Tselina-D]17 Jan 19867,,#$n4]@  !&LNhj4286015Cosmos 1732 [Geo-IK]11 Feb 1986:,,#$t4]@  _剂RTnp4386018Cosmos 1733 [Tselina-D]19 Feb 1986:,,#$t4]@  _剂RTnp4486034Cosmos 1743 [Tselina-D]15 May 1986,,w,#X4]@  68RT4586039Meteor 2-1427 May 1986:,[,#$t4]@  _剂RTnp4686046Cosmos 1758 [Tselina-D]16 Jun 19868w,=,#$p4]@  뉢NPjl4786055Cosmos 1766 [Ocean-O]28 Jun 1986:[,!,#$t4]@  _剂RTnp4886074Cosmos 1782 [Tselina-D]30 Sep 1986L=,,#04]@  <df& 49n/aCosmos (1786) - (1791) [Strela-3]15 Oct 1986Failure7!,,#$n4]@  !&LNhj5086094Cosmos 1803 [Geo-IK]02 Dec 1986:, ,#$t4]@  _剂RTnp5186097Cosmos 1805 [Tselina-D]10 Dec 1986,, ,#X4]@  68RT5286101Cosmos 180918 Dec 1986, , ,#X4]@  68RT5387001Meteor 2-1505 Jan 1987: ,f ,#$t4]@  _剂RTnp5487003Cosmos 1812 [Tselina-D]14 Jan 19877 ,G ,#$n4]@  !&LNhj5587020Cosmos 1823 [Geo-IK]20 Feb 1987:f ,+,#$t4]@  _剂RTnp5687024Cosmos 1825 [Tselina-D]03 Mar 1987@G ,,#$4]@  <^`z|5787026Cosmos 1827 - 1832 [Strela-3]13 Mar 1987:+, @,#$t4]@  _剂RTnp5887038Cosmos 1842 [Tselina-D]27 Apr 1987, @,,+:,@,#$t4]@  _剂RTnp5987055Cosmos 1862 [Tselina-D]01 Jul 19878 @,A,#$p4]@  뉢NPjl6087062Cosmos 1869 [Ocean-O]16 Jul 1987,@,B,#X4]@  68RT6187068Meteor 2-1618 Aug 1987@A,C,#$4]@  <^`z|6287074Cosmos 1875 - 1880 [Strela-3]07 Sep 1987:B,pD,#$t4]@  _剂RTnp6387088Cosmos 1892 [Tselina-D]20 Oct 1987:C,TE,#$t4]@  _剂RTnp6488001Cosmos 1908 [Tselina-D]06 Jan 1988@pD,>F,#$4]@  <^`z|6588002Cosmos 1909 - 1914 [Strela-3]15 Jan 1988,TE,G,#X4]@  68RT6688005Meteor 2-1730 Jan 1988.>F,G,#$\4]@  (w:<VX6788020Cosmos 193315 Mar 19887G,H,#$n4]@  !&LNhj6888046Cosmos 1950 [Geo-IK]30 Apr 1988:G,I,#$t4]@  _剂RTnp6988050Cosmos 1953 [Tselina-D]14 Jun 1988)H,~J,#$R4]@  󓋉24LN7088056Ocean 15 Jul 1988+I,MK,#V4]@  46PR7188064Meteor 3-226 Jul 1988.~J,%L,#$\4]@  (w:<VX7288093Cosmos 197511 Oct 1988.MK,L,#$\4]@  (w:<VX7388113Cosmos 198523 Dec 1988T%L,QN,#j 4]@  b )w )w )w)w)w)w7489009A: Cosmos 1994B: Cosmos 1995C: Cosmos 1996D: Cosmos 1997E: Cosmos 1998F: Cosmos 199910 Feb 1989,L,!O,#X4]@  68RT7589018Meteor 2-1828 Feb 1989GQN,$,#04]@  뉢FH`b& 76n/aOcean (2) [Ocean-O]6 Jun 1989!O,$,,+Failure: 3rd stage.!O,,#$\4]@  ex:<VX7789068Cosmos 203728 Aug 1989T$,P,#j 4]@  bexexfxexexex7889074A: Cosmos 2038B: Cosmos 2039C: Cosmos 2040D: Cosmos 2041E: Cosmos 2042F: Cosmos 204314 Sep 1989M,H,#&4]@  M$xz7989080A: Intercosmos 24 (Aktivny-IK)B: Magion 228 Sep 1989.P, ,#$\4]@  ٫ k:<VX8089086Meteor 3-0324 Oct 1989=H,,#z4]@  XZtv8189100Cosmos 2053 [Radar-Cal-2 #2]26 Dec 1989. ,م,#$\4]@  /fx:<VX8290010Cosmos 205830 Jan 1990*,,#$T4]@  󓋉24NP8390018Ocean 228 Feb 1990,م,},#X4]@  68RT8490057Meteor 2-1927 Jun 19907,^,#$n4]@  !&LNhj8590066Cosmos 2088 [Geo-IK]30 Jun 1990?},G,#$~4]@  <^`xz8690070Cosmos 2090 - 2095 [Strela-3]8 Aug 1990,^,,#X4]@  68RT8790086Meteor 2-2028 Sep 1990:G,,#$t4]@  _剂RTnp8890104Cosmos 2106 [Tselina-D]28 Nov 1990@,,#$4]@  <^`z|8990114Cosmos 2114 - 2119 [Strela-3]22 Dec 1990+,,#V4]@  46PR9091030Meteor 3-424 Apr 1991@,,#$4]@  <^`z|9191033Cosmos 2143 - 2148 [Strela-3]16 May 1991),q,#$R4]@  󓋉24LN9291039Ocean 34 Jun 1991:,U,#$t4]@  _剂RTnp9391042Cosmos 2151 [Tselina-D]13 Jun 1991.q,9,#$\4]@  ۫ k:<VXU,9,,+9491056Meteor 3-0515 Aug 1991@U,#,#$4]@  <^`z|9591068Cosmos 2157 - 2162 [Strela-3]28 Sep 1991@9, ,#$4]@  <^`z|9691077Cosmos 2165 - 2170 [Strela-3]12 Nov 1991G#,,#&4]@  N$ln9791086A: Intercosmos 25 (Apex)E: Magion 318 Dec 1991i ,,#24]@  *XZ10092080Cosmos 222124 Nov 19928,,#$p4]@ !&NPjl10192092Cosmos 2226 [Geo-IK]22 Dec 1992;,,#$v4]@ _剂TVpr10292094Cosmos 2228 [Tselina-D]25 Dec 1992/,|,#$^4]@ 6,x<>XZ10393024Cosmos 224216 Apr 1993U,,#j4]@ b9,x:,x;,x<,x=,xi,x 10493030A: Cosmos 2245B: Cosmos 2246C: Cosmos 2247D: Cosmos 2248E: Cosmos 2249F: Cosmos 225011 May 1993U|,&,#j4]@ ba,xb,xc,xd,xe,xf,x 10593038A: Cosmos 2252B: Cosmos 2253C: Cosmos 2254D: Cosmos 2255E: Cosmos 2256F: Cosmos 225725 Jun 1993?,,#2~4]@ *s k4\^xz10693055A: Meteor 2-21B: Temisat31 Aug 1993@&,,#24]@ *ܫ kI^`z|10794003A: Meteor 3-06B: Tubsat B25 Jan 1994U,\,#j4]@ b,x,x,x,x,x,x 10894011A: Cosmos 2268B: Cosmos 2269C: Cosmos 2270D: Cosmos 2271E: Cosmos 2272F: Cosmos 227312 Feb 1994,,2,#$X4]@ ^8:RT10994014Coronas 12 Mar 1994j\,X-#04]@ _剂TVpr& 110n/aCosmos [2281] [T2,X-,+selina-D]25 May 1994Failure: 2nd and 3rd stage failed to separate+2,--#$V4]@ 󓋉46PR11194066Ocean 411 Oct 1994,X--#$X4]@ -l68RT11294078Geo-IK 129 Nov 1994U--X-#j4]@ b-xy4xp4xq4xr4xs4x 11394086A: Cosmos 2299B: Cosmos 2300C: Cosmos 2301D: Cosmos 2302E: Cosmos 2303F: Cosmos 230428 Dec 1994 \-e-#24]@ *>w|3д%RTnp11495046A: Sich 1Fasat Alfa31 Aug 1995Fasat failed to separate from SichiX--#v+4]@ bI,J,K,3x 3xL3x $&11596009A: Gonets-D1 1B: Gonets-D1 2C: Gonets-D1 3D: Cosmos 2328E: Cosmos 2329F: Cosmos 233019 Feb 1996 at 00:58 UTie-7-#v+4]@ bL,M,N,I3xJ3xK3x"$ 11697006A: Gonets-D1 4B: Gonets-D1 5C: Gonets-D1 6D: Cosmos 2337E: Cosmos 2338F: Cosmos 233914 Feb 1997 at 03:47 UTK%--& J$Notes: All launches from Plesetsk: 7--1VZ6-g-H-ConestogaF--5 :$ " Conestogae4-g-1 2h 㭄؉>ɉby Jean-Jacques Serralisting by Gunter Krebs-M -% The Conestoga launchers are based on a program of Space Services Inc (SSI) in the early 80ies. The company was bought by EER Systems in December 1990 and became it's Space Service Division.;g- -' ( Percheron projectsNM - -% The first achievement of SSI was a liquid rocket named Percheron. It should have been the base for a launcher series made of modules of 1.2 m diameter and 12 m high with each a motor and a propellant tank. The first Percheron rocket exploded on the first motor static test on the Matagorda island (Texas) launch pad on 5 Aug 1981.5 -0 -'  Conestoga 1~X - -& Following this failure SSI changed to solid propulsion with missile or rocket elements already operational. For it's first test on 9 Sep 1982 the Conestoga 1 (11.5 m high, 6.5 tons) was based on a single active stage: an Aerojet M56-A1 of 207 kN (the second stage of the Minuteman 1 ICBM) also used for Aries rockets. The flight was a success and the payload was ejected at apogee (313 km).Note: in the late 80ies SSI started working on commercial flights for microgravity experiments (Consort program). They used Starfire rockets (Canadian Black Brant 9 rockets with a Terrier missile booster).&0 - -# = --' ,O Conestoga launchersJ  -g@-> J_ 0_ 0_ 0_ 0EER Systems stayed with the modular concept to offer a series of light launchers based on various Thiokol boosters: Castor-4, Star-37 and Star-48.The most powerful version (Conestoga 1620) features 6 Castor-4 (4 Castor-4B and 2 Castor-4A) surrounding a Castor-4B. Four Castor are on at liftoff (first stage), two more (second stage) and the central Castor acts as the third stage. The Star 48 top stage copes with orbit in-g@--jection. This launcher is 15.7 m high, 87.3 tons and can deliver 460 km in orbit (40.5).e-@-$ The first launch was a failure. There are doubts on the ability of EER to finance another flight.8g@-(A-' " Configurations_@- B-#ڀklp 4PjDesignationLength (m)Diameter (m)Mass (tons)Thrust in vaccum (kN)Burn duration (s)<(A-B-#ڀxklp(>JXjCastor 4A (TX780)8.09-9.201,0211,58436-47653.1 3 B-C-#ڀfklp(4@NXCastor-4B (TX859)8,981,0211,4842960.9 4B->D-#ڀhklp0<HT\Star -37 FM (TEM-784)1,680,931,154863,7.C-D-#ڀ\klp(4@LTStar-48 (TEM-711)2,031,252,146684&>D-E-# <D-SE-' * Conestoga launches8nE-F-#d4]2   $& <> ^ np #Launch idPayloadLaunch date TypeStatus (orbit in perigee x apogee x inc. x period)rSE-G-#v=4]2" (4+"8:"pr(~#""1n/aMeteor (US)23 Oct 1995 at 22:03 UT1620Failure: The vehicle was destroyed 45s into the first stage burn, at an altitude of 11 kmF F-CH-& @$Notes: launches from Wallops<G-H-' *O External resourcesBCH-H-' 6http://netline.net/eer/8H-H-1(Z\7H-I-@.DiamantDH-=I-5 : " Diamante4H-I-1 2h 㭄؉>ɉby Jean-Jacques Serralisting by Gunter KrebsxK=I-J-- *O  Origin: Pierre Prcieuses (precious stones) experimental rocket series#I-=L-0 . 㱭+The SEREB (Socit pour l'Etude et la Ralisation d'Engins Balistiques, firm for the study and developpement of ballistic missiles) was founded in 1959 to support the DMA missile department which was in charge of the French strategic ballistic missile programs SSBS and MSBS. Work begin by a ballistic study program to acquire the technology necessary to development of such missiles. This program achieved several carriers in the Pierre Prcieuses series: Agate, Topaze, Emeraude and Saphir.J-AN-% The VE-110 Agate was the first of the series. It was a 1-stage solid-fuel (Isolane) non piloted carrier of 80 cm diameter. The VE-111 Topaze was similar to Agate but guided by 4 rotative nozzles. The VE-121 Emeraude was 1.40 m diameter; it was the first is the series to use liquid propellant (nitric acid and turpentine). The VE-231 Saphir had 2 stages: Emeraude + Topaze. Saphir enabled in-flight experiments of cap release, stage separation, inertial guidance and reentry.U0=L-O-% aIn December 1961 it was decided to build the Diamant launcher by replacing the payload of Saphir by a third stage. In May 1962 CNES selected DMA to manage the Diamant program, SEREB being the prime contractor. The Rubis rocket was designed to test the third stage in-flight, on top of an Agate stage.3 AN-O-'  Diamant AzVO-O-$ The diamant A launO-O-H-cher was made of a 10 m high, 1.4 m diameter Emeraude first stage weighing 14.7 tons. Its Vexin LRBA directional-nozzle motor burned during 93 seconds and delivered 269 kN thrust at sea level (304 kN in vacuum). The second stage was Topaze: 4.7 m high per 80 cm diameter and weighed 2.9 tons. It provided a mean thrust of 156 kN during 44 seconds. The P064 third stage was 2 m high and 65 cm diameter. It weighed 709 kg including 640 kg Isolane (thus its name). It burned for 45 seconds providing 27 to 53 kN thrust. With its cap Diamant was 18.95 m high and weighed 18.4 tons.3O--6 :;S  Diamant achieved orbiting at first try on 26 Nov 1965. The payload was the simple technological capsule Astrix. After this launch the 3 remaining rockets were used to orbit geodesy satellites (D1 program) between Feb 1966 and Feb 1967. All launches were carried out from the CIEES (Centre InterArmes d'Essais d'Engins Spciaux, inter-army special machine test center) in Sahara which was closed in July 1967.Once the Diamant A program ended Rubis was still used as sounding rocket: in July 1967 it delivered an experiment of the Paris-Meudon observatory's space radioastronomy department at 1560 km altitude. The third stage of Diamant A was then used twice as top stage of the Tibre launcher for the Electre experiments between Feb 1971 and Mar 1972.3 O--'  Diamant B-^-$  After Diamant numerous projects appear but CNES decides to built a launcher directly derived from Diamant A. The main evolution was the lengthened first stage which used more energy-providing propellants. This first stage called Amthyste was 14.2 m high, 1.4 m diameter, and 20.1 t weight. Its Valois motor delivered 316 kN thrust at sea level (400 kN in vacuum) during 116 seconds. The second stage was identical the Diamant A's one; The top stage (P068) was also enhanced: 1.67 m high, 80 cm diameter and 50 kN thrust during 46s. With its cap (85 cm diameter instead of 65 cm for Diamant A) Diamant B was 23.5 m high and weighed 24.6 tons.=--E X{&>8GV<_B Six Diamant B were ordered: 2 for CNES and 4 for ELDO (in single stage version) which were to be used to test the PAS (Perigee-Apogee System) for Europa 2. Finaly ELDO dropped the idea and the 5 rocket built were used by CNES.After the launch of the German Wika technological capsule Diamant B launched Peole (technology) and Tournesol (astronomy). The last 2 launches were failures. All launches occured from the CSG (Centre Spatial Guyanais, Guyana space center) which is operational since April 1968 when the first sounding rocket Veronique was launched.5^--'  Diamant BP4W-l-8 >?Xى㱭+2!Development of Diamant BP4 started in Jan 1972. It was based on the first and third stage of its ancestor. The new second stage P4 (Rita) was from the ballistic missile MSBS guided by jet deviation (freon injection). It was 2.28 m long and 1.5 m diamter; it provided a mean 180 kN thrust during 55 seconds. With the 1.38 m cap from the Black Arrow program Diamant BP4 was 21.6 m high and weighed 27 tons.After 1975 France stopped its sounding rocket and national launcher programs to devote entirely to the european Ariane launcher.E--' < Diamant launchers evolution9el--#x\yxyjkj  > X r    DesignationFirst launch1st stage2nd stage3rd stage300 km500 km1000 km*--#T\yxyjkj(8DHPA1965EmeraudeTopazeP064801--#b\yxyjkj--H-*:FPZB1970AmethysteTopazeP068160115251-w-#b\yxyjkj .:FPZBP41975AmethysteRitaP06820015345&--# :w--' & Diamant launches2Q- -#4\@NM   $& <> \ l |~ #Launch idPayloadLaunch DateSiteTypeStatus/Comment/--#h^4\@NM ;S02LRTZ165096Asterix26 Nov 1965HA2 --#td4\@NM "QS46RXZ`266013Diapason17 Feb 1966HA+S-3-#4\@NM "㦼68TZ\b 367011Diadme 108 Fab 1967HAPartial failure: orbit too low 4-<-#zh4\@NM "㧼68TZ\b 467014Diadme 215 Feb 1967HAA3-Y-#4\@NM 0&>]YUPRntv| 570017A: Dial-WikaB: Mika10 Mar 1970KB.<-V-#n\4\@NM 8GV,.HNPV 670109Pole12 Dec 1970KB 4Y-_-#zh4\@NM "<68TZ\b 771030Tournesol15 Apr 1971KB%JV--#4\@NM "cn.0JPR"X  8n/aPolaire5 Dec 1971KBFailure: 2nd stage failed%O_--#|4\@NM 68TZ\"b  9n/aCastorPollux22 May 1972KBFailure: 3rd stage failed4--#nh4\@NM ?168PVXb 1075010Starlette6 Feb 1975KBP4C--#4\@NM 0qw )PRntv 1175039A: PolluxB: Castor17 May 1975KBP40--#n`4\@NM RKU,.HNPZ 1275092Aura27 Sep 1975KBP4j@-@.* $$Notes: L-@.H-aunch site: H for Hammaguir, Algeria; K for Kourou?-.1;Z]8...ISAS launchersK@..5 :. " ISAS launchersD..* $4 㭄؉by Jean-Jacques Serra..& The first japanese sounding rockets were designed in the mid-50ies bu the TOkyo Department of Applied Industries (TODAI) to contribute to the International Geophysical Year of 1957-58.In the early sixties, university of Tokyo decided to design 3-stage rockets named Lambda while going on developping new 2-stage sounding rockets of the Kappa series. The most powerful Kappa rockets (9 & 10) weighed 1.5 to 1.7 tons and had 42 cm base stages; despite the Lambda-3 had a 73 cm diameter first stage and weighed over 7 tons. For the International Quiet Sun Year (IQSY) of 1964-65 those launchers performed 1000 km altitude orbit with 100 kg payload. The rocket workgroup at University of Tokyo then became the ISAS.3 .3.'  Lambda-4S.M.& In 1965 the TODAI started developping a satellite launcher derived from the Lambda-3 sounding rocket which in its most powerful configuration (Lambda-3H) was able to orbit 100 kg at 2000+ km. This launcher was achieved by adding a fourth stage and solid fuel boosters to Lambda-3.Four orbit injection attempts were made in Sep & Dec 1966, Apr 1967 and Sep 1969. Those launches occured from Uchinoura (31.2 North, 130.6 East) near Kagoshima on the Kyushu island. Finaly success occured in 1970.f3. .% This first Japanese launcher named Lambda-4S was 16.5 m high, weighed 9.5 tons and burned only solid fuel. The first stage was 73 cm in diameter and provided 363 kN during 28 seconds. It was assisted during the first 7 seconds by 2 solid fuel boosters of 255 kN thrust. The second stage (same diameter) provided 118 kN during 28 seconds. The third stage was 50 cm in diameter; it was capable of 64 kN during 27 seconds. The top stage was made of a 113 kg powder bloc providing 7.8 kN during 27 seconds which spherical shield made up the satellite's structure. The latter was only a technological capsule which mass at burn shutdown didn't exceed 23 kg. The vehicle was launched from an inclined ramp. It wasn't piloted; a gyroscopic system only controled the fourth stage's altitude before ignition after the ballistic phase (which follows the third stage shutdown).M. .+ $~gOOn 11 Feb 1970 the Lambda-4S number 5 orbited the first capsule named Ohsumi at 351 km x 5142 km x 31.2. This is the only object launched by a Lambda rocket... because it was abandonned as a space launcher.; . .' ( Mu series rockets . .& Seven months after the successful Lambda-4S orbiting the Japanese fired the first model of a new launcher. The Mu-4S kept the same technology but had much greater performances. It was 23.6 m high, 43.6 tons in weight and could put a 100 kg payload in a 31, 500 km circular orbit.It's first stage was 1.41 m in diameter and thrusted 834 kN during 61 seconds. It was assisted by eight 127 kN boosters during the first 5.5 seconds of the flight. The second stage had the same diameter whereas the third was 86 cm and while the 77 cm fourth stage supported a 79 cm diameter cap. The respective thrusts were: 285, 127 and 26.5 kN. The guidance system remained simplistic: only the fourth stage was piloted by jet deviation. .@.' )After a failure in September 1970 for the first flight, Mu-4S succeeded the 3 next attempts between Feb 1971 and Aug 1972.In 1974 a new version of Mu with only 3 stages was introduced. This launcher named Mu-3C was equipped with the old first stage and boosters. The second stage was modified and equipped with a radio-inertial guidance which controlled a jet deviation piloting device (freon injection) and a roll control using lateral propellers. This st .@.@.age provided 343 kN thrust during 55 seconds. The third stage was inherited from Mu-4S fourth stage; it had 65 kN thrust capability during 45 seconds. It was also under the 1.41 m diameter fuse cap. .C.) This 41.6 t launcher with its 20.2 m height had similar performances to Mu-4S although lowerer at high altitude. It was used 4 times between Feb 1974 and Feb 1979; 3 launches were successful.A more powerful launcher appeared in 1977: Mu-3H. The first stage was longer than the former one: its solid fuel engine (27 tons) provided 1080 kN during 56 seconds. The cap had been lengthened and could host a fourth stage to reach very elliptical orbits.Mu-3H was 23.8 m high for 48.7 tons at takeoff. It could orbit 100 kg at 700 km in the 3-stage version and more twice as much in the 4-stage version. It was used 3 times with success between Feb 1977 and Feb 1979 including a launch with 30500 km apogee orbit. @.G.' The fourth version of the launcher, Mu-3S, only differed from the former vehicle by the addition of a piloting system to the first stage. It was based on a nozzle freon injection device and on a roll control system provided by 4 gas generators fixed at the end of the 4 empannages. The vehicle had the same performances as Mu-3H performances. It was used to launch 4 satellites between Feb 1980 and Feb 1984.The next version was Mu-3S2; it was complety modified, only the first stage remained the same. The number of boosters was brought back to two but they mesured 74 cm in height and 285 kN (31 seconds duration). The second stage was lenghtened; it provided 490 kN during 52 seconds. The third stage's diameter was increased to 1.41 m; it provided 108 kN during 82 seconds. The launchers reached 61.2 tons in mass and 27.2 m in height. The orbitable payload which took place in an enlarged cap of 1.65 m diameter was almost twice as heavy as for Mu-3S1: 680 kg at 31, 250 km altitude.C.H.% Mu-3S2 was used 8 times (1 failure) between Jan 1985 and Jan 1995. It launched 2 interplanetary probes to the Moon and to the Halley comet.5G.H.' O Mu-5 seriesH.K.& QWhile the Mu-5 series were based on a 1.41 m diameter first stage Mu-5 uses a new first stage. It is 2.51 m in diameter and much more powerful. It enable the doublement of the payload mass in LEO.This M-14 stage is 13.7 m long and weighs 80.8 tons with over 70 tons propellant (PBHT) in 2 segments. It provides 3870 kN thrust during 49 seconds. The second stage, M-24, has the same diameter. It is 6.7 m in length and 33.2 tons in mass, including 30 tons solid fuel. It makes use of the FIH (Fire In the Hole) technology, i.e. it is linked to the first stage by a mesh structure and ignited at separation between first and second stage. It provides 1370 kN during 63 seconds.[.H.M.- (]ӊHThe third stage M-34 is 4.1 m long and 2.2 m diameter. It used advanced technologies such as a CFRP (Carbon Fiber Reinforced Plastic) envelope and a deployable nozzle which enables to shorten the 3rd stage by 1 meter and to leighten it from 300 kg. Thus is weighs 11 tons including 10 tons propellant and provides 300 kN thrust during 101 seconds.Mu-5 is 30.5 m high with the cap. It weighs 135 tons. It can place 1.8 tons in low orbit at 240 km. For its first flight on 12 Feb 1997 from Kagoshima it delivered Haruka in correct orbit (220/21000 km).?K."N.' 0 Configuration summaryHM.N.#ڀ 8NdzDesignationFirst launch1st stage2nd stage3rd stage4th stage&"N.O.#ڀL(4@Mu-4S1970M-10M-20M-30M-40"N.M.#ڀD(O.M.@.4@Mu-3C1974M-10M-22M-3A"O..#ڀD(4@Mu-3H1977M-13M-22M-3A#M..#ڀF*6BMu-3S1980M-13*M-22M-3A$.E.#ڀH,8DMu-3S21985M-13*M-23M-3AO,..# X(*) M-13 stage with thrust vector control5E.ɂ.'  Mu launches?u..#d4]y]   $& <> \ ln #Launch idPayloadLaunch dateTypeStatus/Comment (orbit in perigee x apogee x inc. x period);ɂ..#Fv4]y] $&@BP 1n/aMS-F125 Sep 1970Mu-4SFailure (61 kg)9..#Fr4]y] oCBD^`n271011Tansei 1 (MS-T1)16 Feb 1971Mu-4S8..#Fp4]y] e@B\^l371080Shinsei (MS-F2)28 Sep 1971Mu-4S5.Շ.#Fj4]y] [@=T:<VXf472064Denpa (REXS)19 Aug 1972Mu-4S9.Ɉ.#Fr4]y] oCBD^`n574008Tansei 2 (MS-T2)16 Feb 1974Mu-3C6Շ..#Fl4]y] zW<>XZh675014Taiyo (SRATS)24 Feb 1975Mu-3C=Ɉ..#Fz4]y] (*DFT 7n/aCorsa A04 Feb 1976Mu-3CFailure (86 kg) R..#F4]y] oCBD^`n877012Tansei 3 (MS-T3)19 Feb 1977Mu-3H824 x 3932 x 65.8 x 134.38..#Fp4]y] q2@B\^l978014Kyokko (Exos A)04 Feb 1978Mu-3H:..#Ft4]y] q2DF`bp1078087Jikiken (Exos B)16 Sep 1978Mu-3H;..#Fv4]y] ~NFHbdr1179014Hakucho (Corsa B)21 Feb 1979Mu-3C;..#Fv4]y] oCDF`br1280015Tansei 4 (MS-T4)17 Feb 1980Mu-3S1=..#Fz4]y] ..@.HJdfv1381017Hinotori (Astro A)21 Feb 1981Mu-3S1:..#Ft4]y] BD^`p1483011Tenma (Astro B)20 Feb 1983Mu-3S1:..#Ft4]y] q2BD^`p1584015Ohzora (Exos C)14 Feb 1984Mu-3S1 U..#:4]y] <>XZj1685001Sakigake/MS-T507 Jan 1985Mu-3S2probe to Halley comet (138 kg) V..#:4]y] >@Z\l1785073Suisei/PLANET-A18 Aug 1985Mu-3S2probe to Halley comet (140 kg):..#Ft4]y] BD^`p1887012Ginga (Astro C)05 Feb 1987Mu-3S2;..#Fv4]y] q2DF`br1989016Akebono (Exos D)21 Feb 1989Mu-3S2[..#<4]y] PRln~2090007Hiten (Muses A)Hagoromo24 Jan 1990Mu-3S2Probe to the Moon (193 kg);..#Fv4]y] ©HىDF`br2191062Yohkoh (Solar A)30 Aug 1991Mu-3S2:.}.#Ft4]y] BD^`p2293011Asuka (Astro D)20 Feb 1993Mu-3S2A..#R4]y] -.0JL\ 23n/aEXPRESS15 Jan 1995Mu-3S2Partial failure;}.{.#Rv4]y] "ӊHFHdfr2497005Haruka (Muses B)12 Feb 1997Mu-5Q'..* $N$Note: All launches from Kagoshima?{. .1!\^9 ..kM/ISRO launchersJ.U.5 :, " ISRO vehiclese4 ..1 2h 㭄؉>ɉby Jean-Jacques Serralisting by Gunter KrebsU.s.$ +Indian founded its space agency ISRO in 1969 and then a Ministry of Space in 1972. The next step was to decide to build a national space launcher.r?..3 6~O   SLV 3 (Satellite Launch Vehicle) and ASLV (Advanced SLV)s./& SLV 3 was a 4-stage solid-fuel light launcher (polybutadiene). It was 17.8 tons and 22.7 m high with a 1 m diameter max. Its payload mass in circular 500 km orbit was around 40 kg.The first stage was 9 m high; it delivered 420 kN t (sea level) thrust during 53 seconds. The second stage (80 cm diameter) operated during 42 seconds and provided 200 kN thrust. The third stage (same diameter as stage 2) was fired for 46 seconds and delivered over 60 kN thrust. The 4th stage (65 cm diameter) was fir./.ed for 30 seconds and provided about 22 kN thrust. Two ballistic phases occured during the flight: one after second stage shutdown (until 88 km altitude) and after third stage shutdown (to reach perigee altitude)../' Rockets were launched from the Sriharikota base on the Indian East coast. This site is operational since the success of a RH-125 sounding rocket in October 1971. After a first attempt which failed in August 1979 the SLV 3 rocket orbited 3 little Rohini scientific satellites in July 1980, Mai 1981 and April 1983. Then the launcher was abandonned for the ASLV.ASLV was dirived from SLV 3 by the addition of two boosters which dimensions and performances were similar to those of the first stage. Those boosters provided the takeoff of the vehicle by providing each 440 kN thrust during 49 seconds. This caused the first stage to be modified to operate in the air. ASLV was 24 m high and its capacity reached 150 kg payload in LEO (40 km).p//' The first two launches were failures in March 1987 and July 1988. Then ASLV orbited two SROSS satellites in May 1992 and May 1994.Noticeable is the fact the the first stage of the SLV 3 was used from 1989 on as first stage of the experimental Agni IRBM (2500 km range). This is perhaps a unique example of transfert of a civilian stage to a military application.W*//- *TO  PSLV (Polar Satellite Launch Vehicle)/ /, & 㱭+PSLV is a 4-stage launcher measuring 44 m high for 2.8 m diameter max, weighing 275 tons.It can orbit around 1 ton payload in sun-synchronous polar orbit.The first stage is 20 m high and weighs 129 tons. It is powered by a solid fuel motor (HTPB: Hydroxyl-Terminated PolyButadiene) which burns during 100 seconds and provides 3500 kN thrust at sea level (4600 kN in vacuum). It is supported by 6 boosters --switched on by group of two then four-- derived from the SLV 3 and ASLV first stage. Each of those deliver 440 kN thrust at sea level (660 kN in vacuum). The second stage is 11 m high for 2.8 m diameter and weighs 38 tons. Its Vikas motor --built under French SEP licence-- consumes liquid propellant (nitrogen tetraoxide and UDMH: Unsymmetrical DiMethylHydrazine). It provides 725 kN thrust during 150 seconds. The third stage is 3.5 m high and 2 m diameter; it weighs 7 tons. Its solid fuel motor (HTPB) provides 340 kN thrust. The fourth stage protected by a bulb cap is 2.6 m long by 1.34 m diameter. It is propulsed by 2 ergols motors (peroxyde d'azote and MMH: MonoMethylHydrazine) of 7.5 kN thrust each which burn during about 7 minutes./ /+ $_TThe first launch failed in Sep 1993 because of a software problem in the guidance system. The second launch in Oct 1994 orbited IRS P2. The next flights are scheduled every 12 to 18 months for the IRS remote sensing satellites.8 / /' " SLV 3 launches7m / /#dF Y  K     $& <> \ ln #Launch idPayloadLaunch dateTypeStatus (orbit in perigee x apogee x inc. x period)7 //#FnF Y  K   ,.HJX 1n/aRohini 1A10 Aug 1979SLV 3Failure2 //#FdF Y  K   ~Oa46PR`280062Rohini 1B18 Jul 1980SLV 3B/ @/#RF Y  K   E24NP^ 381051Rohini 231 May 1981SLV 3Partial failure/ @/.3/A/#RfF Y  K   "F46RTb483033Rohini 317 Apr 1983SLV 3\, @/\A/0 0X$'Notes: All launches from Sriharikota7A/A/'   ASLV launches7m\A/B/#dF Y  K     $& <> \ ln #Launch idPayloadLaunch dateTypeStatus (orbit in perigee x apogee x inc. x period):A/C/#RtF Y  K  ㅊD46PR^ 1, D1n/aSross 124 Mar 1987ASLVFailure<B/D/#^xF Y  K  "ㆊD68TVb 2, D2n/aSross 212 Jul 1988ASLVFailure FC/E/#^F Y  K   ""㇊D:<XZf 3, D392028Sross 320 May 1992ASLVPartial failureAD/F/#RF Y  K   ""_G<>pr~4, D494027Sross C24 May 1994 at 00:00 UTASLV\,E/3G/0 0X$'Notes: All launches from Sriharikota7F/jG/'   PSLV launches7m3G/H/#dF Y  K     $& <> \ ln #Launch idPayloadLaunch dateTypeStatus (orbit in perigee x apogee x inc. x period)UjG/I/#RF Y  K  YT24fht 1, D1n/aIRS 1E20 Sep 1993 at 00:12 UTPSLVFailure: computer error@H/J/#RF Y  K   ""_T8:np|2, D294068IRS P215 Oct 1994 at 05:07 UTPSLV@I/K/#RF Y  K   ""_T8:np|3, D396017IRS P321 Mar 1996 at 04:53 UTPSLV5nJ/L/#^F Y  K   ""YT8:np| 4, C197057IRS 1D29 Sep 1997 at 04:47 UTPSLVPartial failure: 822 x 306 km (not circular)}MK/kM/0 0$'Notes: All launches from Sriharikota (2100 km southeast of New Dehli); L/M/1p]lb:M/`N/ 1Long MarchU kM/M/5 :B " Long March (Chang Zheng)e4M/`N/1 2h 㭄؉>ɉby Jean-Jacques Serralisting by Gunter Krebs1M//0 .6" After the rupture between China and USSR in June 1959 the Chinese started to develop a series a ballistic missiles powered with stockable propellant. The first of these was the CSS-1: a single stage rocket very close to the Soviet SS-3 which was 22 m in length and 1.65 m in diameter that could cover 1100 km. It was tested in the sixties and entered service in 1`N//kM/970. The first Chinese IRBM, the CSS-2 was also single staged. It was 23 m long, 2.23 m diameter and ranged 2500 km. The first in-flight tests were carried out on 1969 and was deployed in 1972. The CSS-3 version with 6500 km range was made by adding a second stage to the CSS-2 (with same diameter). It never entered operational service was was used as the basis of the first Chinese launcher: CZ-1.8`N/Ձ/' " CZ-1 launchers//$ aThe CZ-1 rocket (Chang Zheng = Long March) was derived from the CSS-3 (also called DF-4 by the Chinese, Dong Feng = East Wind) which was added a solid fuel third stage. The first stage was 17.8 m long and weighed 64.1 tons including 60 tons of propellant (Nitric Acid and UDMH). It was powered by a YF-2A motor featuring 4 chambers of 1100 kN at ground level, burning during 130 seconds (ISp = 241 s). The 5.4 m second stage weighed 15.9 tons including 13.2 tons of ergols (NTO and UDMH). It used a YF-3 motor providing 294 kN thrust in vacuum during 126 seconds (ISp = 287 s). The spin-stabilized third stage required a GF=02 powder bloc weighing 1.8 tons which provides 29 kN thrust.Ձ/U/'  The full CZ-1 launcher was 29.45 m high for 81.6 tons at takeoff and could orbit a 300 kg payload at 440 km with 70 inclination. It launched the 2 first Chinese satellites from Juiquan in April 1970 and March 1971 after a failure in November 1969.Enhanced version of this launcher: CZ-1C and CZ-1D completly Chinese and CZ-1M featuring an Italian 3rd stage (IRIS) were announced... W0//' `O Second generation launchers: FB-1 and CZ-2A/DgU/E/2 2  The first Chinese ICBM CSS-3 (or DF-5 in the Chinese jargon) was over 30 m high for 3.35 m diameter. It featured two liquid fuel stages (NTO and UDMH) and ranged 11000 km. In-flight tests were carried out in 1979 and only few exemplars (8 to 12 ?) were deployed after 1980.Its development was carried out in the same time as two space launcher programs: FB-1 (Feng Bao = storm) and CZ-2. Very little is known on the FB-1 but it is probably similar to CZ-2 with lower performances (1.2 tons is LEO against 1.7 tons). Some sources believe the two launchers were developped by two different agencies (SBA (Shanghai Bureau of Astronautics) et la BWYIC (Beijing Wan Yuan Industry Corporation)) from the same specifications. It was launched successfully 4 times from Jiuquan between July 1975 and September 1981; 4 failures and 3 suborbital flights were also reported.//% KThe most important launcher of the other series is the CZ-2C. The CZ-2A was indeed only fired once in November 1974 and the B designation used for the FB-1. The CZ-2C featured a L-140 first stage of 20.5 m long which weighed 151 tons including 142 tons of propellant. It was powered by 4 YF-20 motors of 696 kN thrust at ground level (ISp = 260 s) which burned during 132 seconds. The second stage (L-35) was 7.5 m long and 39 tons (35 tons for propellant). It was equipped with an YF-22 motor providing 762 kN in vacuum (ISp = 290 s) associated with 4 deployable YF-23 verniers providing a total of 44 kN. The main engine burned 110 seconds while the verniers 300 seconds.%E/4/- (ЇThe CZ-2C launcher is 32.6 to 35.1 m high (depending on the cap) and weighed about 191 tons. It can deliver 2 to 2.5 tons in LEO. From Juiquan it orbited 9 retrievable FSW-0 (Fanhui Shi Weixing) satellites between November 1975 and August 1987 and 5 FSW-1 since September 1987. An enhanced version named CZ-2D launched two FSW-2 satellites in August 1992 and July 1994.Three-stage versions of the CZ-2C were announced (with a solid SD or CPKM stage). Only the CZ-2C/SD should be used for Iridium.8/l/' " CZ-3 launchers4//& The CZ-3 rocket is a 3-stage launcher which makes use of modified versions of the 2 first stages of CZ-2C (sal//kM/me performances) and adds a cryogenic third stage. This H-8 cryogenic stage is 7.5 m long for 2.25 m diameter. It weighs 10.5 tons including 8.5 tons of propellant (LH2 and LOX). it is equipped with a 4-chamber YF-73 motor providing 44 kN thurst in vacuum (ISp = 420 s). The reignitable motor is used for two burns during 500 and 300 seconds.This launcher is 43.2 to 43.8 m high and weighs 202 tons. It can orbit 1.4 tons in GTO. It was used from Xichang from January 1984 on to launch Chinese telecommunication satellites of foreign spacecrafts. It should still be used even after the introduction of enhanced versions designated CZ-3A and CZ-3B.]6l//' lO Third generation launchers: CZ-4, CZ-2E and CZ-3A/B//& WA new Chinese generation was introduced in the late eighties based on a streched L-180 first stage equipped with more powerful motors.The first launcher to use those new elements was CZ-4 specialy designed for sunsynchronous orbits. The first stage is thus an L-180 with 24.7 m long carrying 138 tons propellant powered during 156 seconds by 4 YF-20 motors which unitary thrust was boosted to 735 kN. The second stage is an modified L-35 with 10.4 m long. Its main engine is a YF-25 of 766 kN assisted by 4 YF-23 verniers. The third stage (L-14) specific to the CZ-4 is 6.2 m long for 2.9 m diameter. It is equipped with a pair of YF-40 engines which burn NTO and UDMH. Their total thrust is 98 kN during 321 seconds (ISp = 303 s). This CZ-4 reaches 42 m high and 250 tons. It can deliver a 1.5 ton payload on sun-synchronous orbit at 900 km. It was used to launch 2 meteorological FY satellites from Taiyuan in Sep 1988 and Sep 1990.xS/=/% The second launcher to use the L-180 and the enhanced motors is the CZ-2E devoted to heavy GEO payloads. The first stage is an L-180 with 23.7 m long (187 tons propellant) propulsed during 159 seconds by 4 YF-20 motors of 735 kN. It is assisted during 126 seconds by 4 LB-40 boosters of 15.6 m long and 2.25 m diameter (38 tons of propellant each) equipped with the same YF-20 engines. The second stage is an L-90 of 15.5 m long (86 tons ergols) with a YF-25 main engine of 831 kN. It is surrounded by 4 YF-23 verniers. The main engine burns during 300 seconds while the version 413 seconds.A/~/+ $- The CZ-2E is 49.7 to 51.2 m high. It weighs 460 tons at takeoff. Its capacity reaches 8.8 tons in LEO but it is only used for geostationary satellites with a solid perigee stage. The first version with the American Thiokol Star-63F could place 3.14 tons in GTO. With the EPKM of the Chinese HCMC (Hexi Chemical & Manufacturing Corp) company used for the first time in Nov 1995 the performance reaches 3.46 tons. After a trial launch in July 1990 the CZ-2E was used to launch several telecommunications satellites from Xichang...P+=//% WThe third launcher based on the L-180 was the CZ-3A also devoted to heavy payloads aimed at GEO. The first stage is a 23 m long L-180 (170 tons of propellant) powered by four 735 kN YF-20 motors. The second stage is a L-35 of 11.5 m long (29.6 tons ergol) with an YF-25 main engine of 766 kN which burns during 110 seconds assited by 4 YF-23 verniers. The new H-18 cryogenic third stage is 8.8 m long and 3.0 m diameter (17.6 tons propellant). It features 2 YF-75 engines providing a total thrust of 157 kN (ISp = 425 s) during 470 seconds in 2 burns.~/|/' The CZ-3A has a total of 52.3 m high and 240 tons at takeoff. It can orbit 2.3 tons in GTO. After a trial launch in Feb 1994 to launched a 3rd generation telecommunication DFH satellite in Nov 1994.The CZ-3B used the CZ-3A with 4 liquid boosters inherited from the CZ-2E. It then weighs 403 tons at takeoff and its capacity reaches 4.85 tons in GTO. It first launch failed in Feb 1996.7//'   CZ-1 launches?u|/0#d^^2  /0kM/ $& <> \ ln #Launch idPayloadLaunch dateTypeStatus/Comment (orbit in perigee x apogee x inc. x period)4/0#:h^^2  "BD^`d1, CZ-1n/aR&D suborbital10 Jan 1970000#F`^^2 $&!(v&:<VX\2, CZ-170034DFH 0124 Apr 1970/00#F^^^2 $&"(v&:<TVZ3, CZ-171018DFH 023 Mar 1971M&0 0' L$Notes: All launches from Juiquan.>0G0' . CZ-2, 3 & 4 launchesb~ 00#^^3   $& <> \ l |"~ #Launch idPayloadLaunch dateSiteTypeStatus/Comment (orbit in perigee x apogee x inc. x period)(\G00#h^^3  "02LTV^#"1, CZ-2n/aFSW 005 Nov 1974JiA?Failure: 1st stage control system failure700#nn^^3 $&$(v&<>X`bh"2, CZ-275111FSW 0-126 Nov 1975JiC700#nn^^3 $&'(v&<>X`bh"3, CZ-276116FSW 0-207 Dec 1976JiC70 0#nn^^3 $&((v&<>X`bh"4, CZ-278011FSW 0-326 Jan 1978JiC70 0#nn^^3 $&&v&<>X`bh"5, CZ-282090FSW 0-409 Sep 1982JiC7 0 0#nn^^3 $&&v&<>X`bh"6, CZ-283086FSW 0-519 Aug 1983JiC8c 0' 0#z^^3 $&&v&<>X`b"f"7, CZ-384008STTW-T129 Jan 1984XiPartial failure: 3rd stage failed to ignite6 0,0#nl^^3 $&&v&<>X`bf"8, CZ-384035STTW-T208 Apr 1984Xi7' 020#nn^^3 $&&v&<>X`bh"9, CZ-284098FSW 0-612 Sep 1984JiC8,0E@0#np^^3 &(&v&>@Zbdj"20E@0kM/10, CZ-285096FSW 0-721 Oct 1985JiC620JA0#nl^^3 &(&v&<>X`bf"11, CZ-386010STTW 101 Feb 1986Xi8E@0QB0#np^^3 &(&v&>@Zbdj"12, CZ-286076FSW 0-806 Oct 1986JiC8JA0XC0#np^^3 &(&v&>@Zbdj"13, CZ-287067FSW 0-905 Aug 1987JiC8QB0_D0#np^^3 &(&v&>@Zbdj"14, CZ-287075FSW 1-109 Sep 1987JiC6XC0dE0#nl^^3 &(&v&<>X`bf"15, CZ-388014STTW 207 Mar 1988Xi8_D0kF0#np^^3 &(&v&>@Zbdj"16, CZ-288067FSW 1-205 Aug 1988JiC6dE0pG0#nl^^3 &(&v&<>X`bf"17, CZ-488080FY 1-106 Sep 1988Ty6kF0uH0#nl^^3 &(&v&<>X`bf"18, CZ-388111STTW 322 Dec 1988Xi6pG0zI0#nl^^3 &(&v&<>X`bf"19, CZ-390011STTW 404 Feb 1990Xi9uH0J0#nr^^3 &(kBD^fhl"20, CZ-390030Asiasat 107 Apr 1990Xi2czI0K0#n^^3 &((<>X`bt"21, CZ-290059Badr A16 Jul 1990XiE (PKM)Failed to place the Optus model in GTO.QJ0L0#^^3 &8(&v&&v&&v&rt"22, CZ-490081A: FY 1-2B: DFH 31C: DFH 3203 Sep 1990Ty8K0M0#np^^3 &(&v&>@Zbdj"23, CZ-290089FSW 1-305 Oct 1990JiC8cL0!O0#z^^3 &(&v&<>X`b"f"24, CZ-391088STTW 528 Dec 1991XiPartial failure: 3rd stage failed to ignite8M040#np^^3 &(&v&>@Zbdj"25, CZ-29205!O040kM/1FSW 2-109 Aug 1992JiDD!O0G0#n^^3 &(_@B\df"26, CZ-292054Optus B113 Aug 1992XiE (Star-63F)F40c0#|^^3 &*(1T&v&Z\v~"27, CZ-292064A: FrejaB: FSW 1-406 Oct 1992JiCEpG00#z^^3 &(_@B\df""28, CZ-292090Optus B221 Dec 1992XiE (Star-63F)Partial failure: payload fairing collapsed8c00#np^^3 &(&v&>@Zbdj"29, CZ-293063FSW 1-508 Oct 1993JiCE0ʅ0#|^^3 &*(&v&&v&XZt|~"30, CZ-394010A: SJ 4B: DFH 3-008 Feb 1994XiA70І0#nn^^3 &(('v&>@X`bh"31, CZ-294037FSW 2-23 Jul 1994JiD8ʅ0ׇ0#np^^3 &(b @B\dfj"32, CZ-394043Apstar 121 Jul 1994XiDІ00#n^^3 &(_@B\df"33, CZ-294055Optus B327 Aug 1994XiE (Star-63F)8ׇ00#np^^3 &('v&>@Zbdj"34, CZ-394080DFH 3-129 Nov 1994XiAIq0:0#^^3 "$ b <>X`b(~#""35, CZ-2n/aApstar 225 Jan 1995XiE (Star-63F)Failure: vehicle destroyed due to wind shearF0U0#z^^3 &"(k(DF bjl"36, CZ-295064Asiasat 228 Nov 1995XiE (STPM-17)A:0k0#z^^3 &"(VR^Z(FH dln|"37, CZ-295073Echostar 128 Dec 1995XiE (?)^U0Ɏ0#z^^3 "$ĉDF`hj"p#"38, CZ-3n/aIntelsat 70814 Feb 1996XiBFailure: attitude control lost within seconds, due to an electrical failure&Qk0 0#z^^3 &"(i"鉀(DF bjlp"39, CZ-396039Apstar 1A03 Jul 1996Xi225 x 42184 km x 26.9Ɏ0 0kM/NsɎ0Z0#^^3 &"( 'v&(>@ t|~""40, CZ-396048DFH 4218 Aug 1996 at 10:27 UTXiPartial failure: 3rd stage shutdown 48s early8 0a0#np^^3 &(!'v&>@Zbdj"41, CZ-296059FSW 2-320 Oct 1996JiD#HZ00#^^3 &"("'v&(>"@  z"42, CZ-397021DFH 4411 May 1997 at 16:17 UTXiA/Za00#z^^3 &"(#'v&(>@ t|~"43, CZ-397029DFH 4510 Jun 1997 at 12:01 UTXi206 x 35987 km x 28.43^00#z^^3 &"(n(DF z"44, CZ-397042Mabuhay 119 Aug 1997 at 17:30 UTXiB170 x 44499 km x 24.60j0#~Y^^3 &$(Ї( Ѐ؀ڀ"45, CZ-2970482 Iridium MFS (Mass Frequency Simulators)650 kg each1 Sep 1997 at 14:00 UTTyCFirst flight from Taiyanwith Smart Dispenser upper stage+\00#n^^3 &("鉂BDv~"46, CZ-397062Apstar 2R16 Oct 1997 at 17:13 UTXiB201 x 47922 km x 24.4Xvj00#^^3 &<(iՅ kՅ(pr "47, CZ-297077A: Iridium 42B: Iridium 448 Dec 1997 at 07:16 UTTyC-3-SDWith Smart Dispenser3]0 0#|^^3 &*(ՅՅjl"48, CZ-298018A: Iridium 51B: Iridium 6125 Mar 1998 at 17:01 UTTyC-SD&P0F0#|^^3 &*(ՅՅjl"49, CZ-298026A: Iridium 69B: Iridium 712 May 1998TyC-SD < 0Q0#nx^^3 &(j)ቂFHbjlr"50, CZ-398034Chinastar 130 May 1998XiBhAF00' $Notes: Launch sites: Xi = Xichang, Ji = Jiuquan, Ty = Taiyan7Q00'   FB-1 launches?u0/0#d^^2   $& <> \ ln #Launch idPayloadLaunch dateTypeStatus/Comment (orbit in perigee x apogee x inc. x period)40$1#:h^^2  "BD^`d1, FB-1n/aR&D suborbi/0$1kM/tal10 Aug 19724/01#Fh^^2  "02LNR& 2, FB-1n/aJSSW?18 Sep 1973Failure R$1 1#F^^2  "02LNR& 3, FB-1n/aJSSW?14 Jul 1974Failure: 2nd stage engine lost thrust01 1#F`^^2 $&#(v&:<VX\4, FB-175070JSSW 126 Jul 19750 11#F`^^2 $&%(v&:<VX\5, FB-175119JSSW 216 Dec 19750 11#F`^^2 $&&(v&:<VX\6, FB-176087JSSW 330 Aug 1976411#Fh^^2  "02LNR& 7, FB-1n/aJSSW?10 Nov 1976Failure211#:d^^2  ">@Z\`8, FB-1n/a(suborbital)14 Sep 1977211#:d^^2  ">@Z\`9, FB-1n/a(suborbital)16 Apr 1978 P11#F^^2 "$.0JLP& 10, FB-1n/aSJ?27 Jul 1979Failure: 2nd stage thrusters failureH1 1#b^^2 &8()(v&&v&&v&jl11, FB-181093A: SJ 2B: SJ 3AC: SJ 3B19 Sep 1981M&1 1' L$Notes: All launches from Juiquan.? 1F 11A^1d;F 1 1 2NASDA vehiclesK 1 15 :. " NASDA vehiclese4F 1 11 2h 㭄؉>ɉby Jean-Jacques Serralisting by Gunter Krebs 1 1& The NASDA (National Space Development Agency) was founded in October 1969 by the japanese Space Activity Commission to replace the NSDC (National Space Development Center) created in 1964. The NASDA's mission was to bring the application satellite programs to life and to develop launcher capable of orbiting them.Three sounding rockets were already used by the NASDA for technological tests. Those were the single stage SB solid fuel rocket of 70 kg, the 2-stage 2.3 tons JCR solid fuel rocket and the 2-stage 2.5 tons LSC which was the only Japanese launcher with liquid propellant. The experience gained in the development of the second stage (stockable propellant) will later be used for the LE-3 motor of the N1.6 1$1' O N1 launchersJ 1zB12 21p㉂_ 0The N1 was not a Japan made rocket but a Thor-Delta rocket built under licence which second stage had been designed in Japan.The first stage was a Long Tank Thor of 2.44 m diameter built by Mitsubishi Heavy Indutries (MHI) under McDonnell Douglas licence. It was powered by a 765 kN MB-3 motor (liquid oxygen and kerosene) built by Ishikawajima-Harima Heavy Industries (IHI) under licence Rocketdyne. This first stage was$1zB1 1 on during 219 seconds with the help of 3 Castor -2 boosters designed by Nissan under Thiokol licence. The second N1 stage was built by MHI with a TRW licence for the verniers. It was 5.44 m long for 1.62 m diameter and weighed 5.8 tons. It was propulsed by a Japanese LE-3 motor (nitrogen tetraoxide and Aerozine 50) which provided 53 kN (ISp = 285 s) in vacuum during 250 seconds. The solid fuel third stage used the Thiokol TEM-364-14 (Star-37N) propulsor capable of 39 kN during 41 seconds. The launcher was radiocontrolled, the guidance and piloting device was built by Nippon Electric Co Ltd, also under licence. $1D1Q pyㅾTㆾTㇾTrWsWThe complete vehicle was then 90.4 tons for 32.6 m high. It provided 1485 kN at takeoff and could orbit 130 kg in GEO.The N1 launcher enabled to launch between 1975 and 1982 three technological satellites (Kiku 1, Kiku 2 and Kiku 4, one in GEO) and two scientific satellites (Ume 1 and Ume 2). Two other launchers ended as failures with telecommunication satellites (Ayame 1 and Ayame 2) because of the Aerojet apogee stage.6zB1D1' O N2 launcherskD1`I18 >_ 0pp㉂First launched in 1981 the N2 rocket was a enhancement of the N1 entirely built under US licence. Even though equiped with the same motor, the new first stage had enlarged tanks (23% more fuel) which enabled 269 seconds burns. Moreover it was assisted by 9 Castor -2 boosters (6 fired at takeoff and the 3 remaining at shutdown of the latters) instead of 3.The second stage used the AJ-10-118FJ motor built by IHI under Aerojet General licence. The re-ignitable motor herited from the Delta used NTO-Ax50 (Aerozine 50) as propellant and thus provided 48.3 kN (ISp = 314 s) with a total uptime of 420 seconds. The Delta inertial guidance system was installed at the top of the second stage. The third stage was the TEM-364-4 (Star-37E) capable of providing 67 kN thrust during 44 seconds, built by Nissan under Thiokol licence. N2 was 134.7 tons for 35.4 m high and developped a 2150 kN at takeoff. It could place 350 kg in GEO or 1.6 tons in 1000 km circular orbit. It was in fact some kind of clone of the Delta Straight-Eight (constant diameter of 2.44 m). It was fired 8 times between Feb 1981 and Feb 1987 to launch:2D1J1`  ㈾T TT \O V$- 1 technological satellite: Kiku 3- 2 meteorological satellites: Himawari 2 & Himawari 3- 4 telecommunication satellites: Sakura 2s and Yuri 2s- an ocean observation satellite: Momo 1A6`I1J1'  H1 launchersY5J1!N1$ kIn the mid-1970 Japan carried out researches to build a launcher more powerful than the N series with a top stage using cryogenic propulsion built in Japan. The first launcher of this new series was H1. It reused the first stage, the boosters and the cap of N2 while the 2nd and 3rd stage were developped in Japan (without US assistance) together with the ISAS and the National Aerospace Laboratory (NAL). The second stage used the LE-5, a cryogenic re-ignatable motor (liquid oxygen and hydrogren) built by MHI, IHI and NAL. It provided a 103 kN thrust (ISp = 448 s) during about 400 seconds. The stage (dry) weighed 1.1 tons and carried 8.7 tons propellant. The third stage designed by Nissan was made of a powder bloc (HTPB) of about 2 tons. It could provide a mean thrust of 92 kN (ISp = 291 s) during 62 seconds.!J1N1r _ r& A ㉾T T \O W$H1 was 138 tons and 40 m high. It could deliver 550 kg in GEO and 2.2 tons in circular 1000 km orbit (two-stage version). It was used 9 times between 1986 and 1992 for:- a geodesy satellite: Ajisai with a HAM radio satellite: Fuji- a technological satellite: Kiku 5- a meteorology satellite: Himawari 4- 4 telecommunication satellites: Sakura!N1N1 1 3s and Yuri 3s- an ocean observation satellite: Momo 1bV*!N11, (T Z- a remote sensing satellite: Fuyo 16N1ڀ1' O H2 launchers1̄1& The Japanese Space Activity Commission (SAC) decided in 1984 not to enhance the H1 as planned but to develop an new launcher called H2. This H2 is a modern rocket with combined propulsion (two large solid boosters and a cryogenic main motor) entirely designed in Japan.Each booster is 23.4 m is height, 1.81 m in diameter and weighs 70.4 tons including 60 tons powder (HTPB; ISp = 273 s) providing 1540 kN thrust during 94 seconds. The main body of 4 m diameter up to the cap has 2 stages. The first stage of 28 m heigh weighs 98.1 tons. It features a liquid oxygen and hydrogen LE-7 motor of 843 kN at ground level (1078 kN in vaccum; ISp = 446 s). The second stage weighs 19.7 tons for 10.6 m high and makes use of an enhanced version of LE-5A, the second stage motor of the H1. It provides 121.5 kN thrust (ISp = 452 s) during 610 seconds in two burns. MHI, the integrator of the launcher, also builds the cryogenic motors while Nissan provides the solid boosters.ڀ1ԅ1% H2 is nearly 50 m high and weighs 264 tons at takeoff. It can launch 4 tons in GTO, 5 to 6 tons in sun-synchronous orbit and 10 tons in LEO like for example the unmanned HOPE shuttle. It was launched 4 times since Feb 1994.4 ̄11'  N launches?uԅ1G1#d^^2   $& <> \ ln #Launch idPayloadLaunch dateTypeStatus/Comment (orbit in perigee x apogee x inc. x period)1131#Fb^^2 "$ㅾT68RT^1, N-175082ETS 109 Sep 1975N-11G11#Fb^^2 "$rW68RT^2, N-276019Ume 122 Feb 1976N-1131 1#Fb^^2 "$ㆾT68RT^3, N-377014ETS 223 Feb 1977N-1111#Fb^^2 "$sW68RT^4, N-478018Ume 216 Feb 1978N-1%a 11#X^^2 "$:<TV"`  5, N-579009Ayame 16 Feb 1979N-1Failure: 3rd stage collided with the payload31 1#Ff^^2 "$:<VXb6, N-680018Ayame 222 Feb 1980N-1;11#Fv^^2 "$㈾T68RTr7, N-781012ETS 411 Feb 1981N-2 (3 stage); 11#Fv^^2 "$T68RTr8, N-881076GMS 211 Aug 1981N-2 (3 stage)011#F`^^2 "$ㇾT68PR\9, N-982087ETS 33 Sep 1982N-1@11#F^^11 12 &(J.BD\^|10, N-1083006Sakura 2A4 Feb 1983N-2 (3 stage)@11#F^^2 &(K.BD\^|11, N-1183081Sakura 2B5 Aug 1983N-2 (3 stage)?11#F~^^2 &(㉂>@Z\z12, N-1284005Yuri 2A23 Jan 1984N-2 (3 stage)<11#Fx^^2 &(T:<TVt13, N-1384080GMS 33 Aug 1984N-2 (3 stage)?11#F~^^2 &(㉂>@Z\z14, N-1486016Yuri 2B12 Feb 1986N-2 (3 stage)?11#F~^^2 &(V$>@Z\z15, N-1587018Momo 1A19 Feb 1987N-2 (2 stage)Q*11' T$Notes: All launches from Tanegashima.51N1'  H1 launches?u11#d^^   $& <> \ ln #Launch idPayloadLaunch dateTypeStatus/Comment (orbit in perigee x apogee x inc. x period)ON11#T^^ $*&r& TO뉂Z\vx1, H-1586061A: AjisaiB: Fuji 1A12 Aug 1986H-1 (2 st,9 SO)>11#F|^^ $&㉾T8:TVx2, H-1787070ETS 527 Aug 1987H-1 (3 st,9 SO)B11#F^^ $&u.@B\^3, H-1888012Sakura 3A19 Feb 1988H-1 (3 st,9 SO)B11#F^^ $&v.@B\^4, H-1988086Sakura 3B16 Sep 1988H-1 (3 st,9 SO)=11#Fz^^ $&T8:RTv5, H-2089070GMS 45 Sep 1989H-1 (3 st,6 SO)#Z11#b^^ $8&W$XZ|7, H-2290077Yuri 3A28 Aug 1990H-1 (3 st,9 SO)@11#F^^ $&㉂<>XZ|8, H-2391060Yuri 3B25 Aug 1991H-1 (3 st,9 SO)?12#F~^^ 12 1$&Z:<VXz9, H-2492007JERS 111 Feb 1992H-1 (2 st,9 SO)}V1%2' $Notes: All launches from Tanegashima. In type column: st = stages, SO = strap-ons52Z2'  H2 launches?u%22#d^^   $& <> \ ln #Launch idPayloadLaunch dateTypeStatus/Comment (orbit in perigee x apogee x inc. x period)OZ22#l^^ $6&U +V Z\ 1, H-2694007A: RyuseiB: Myojo3 Feb 1994 at 22:20 UTH2822#Fp^^ $&㊾T8:TVl2, H-2794056ETS 628 Aug 1994H2 [LAPS]#U22#l^^ $6&T TV 3, H-2895011A: SFUB: GMS 518 Mar 1995 at 08:01 UTH2 (2 SSB)T22#`^^ 0isJ ;TV 4, 96046A: Adeos 1B: Fuji 217 Aug 1996 at 01:53 UTH2 (2 SSB)H22#`^^ 0ŘbU㋾TLN 5, 97074A: TRMMB: ETS 727 Nov 1997 at 21:27 UTH22y 2#dm^^ "ˎ46 jl"#" 6, 98011Comets21 Feb 1998 at 07:55 UTH2 [LAPS]partial failure: the second burn of the top stage failed (after 44 s); maybe caused by a combustion chamber leakQ*2 2' T$Notes: All launches from Tanegashima.8y 2 21e'lbKe< 2 22PegasusD 2F 25 : " PegasusD 2 2* $4 㭄؉by Jean-Jacques SerraF 2A2(  Orbital Science Corp. (OSC) started the design of the Air-Launched Space Booster (ASLB) alias Pegasus in April 1987. Pegasus is composed of three stages with wings, made of composit structure, powered with solif fuel and inertial guidance.In it's standard version, Pegasus is 14.8 m long by 1.27 m diameter. It has a triangular flying surface of 6.7 m span and a rear 3-drift empennage. It weighs about 18.3 tons without the payload.The carrier aircraft (B52 or L1011) jettisons Pegasus at 12000 m altitude at Mach 0.8. The launcher's propulsion is provided by 3 Hercules stages. The first stage is a fixed-nozzle Orion 50S, piloted by aerodynamical control surfaces. It provides 49.6 t thrust during 73 s. The second stage (same diameter) is a flexible-nozzle Orion 50 which delivers 12.5 t thurst during 72 s. The third stage is an Orion 38 with flexible nozzle that burns during 65 seconds providing 4.4 t thrust. The 2nd and 3rd stage mobile nozzles provide yawing and pitching guidance while rolling guidance is made with gas propellers which are also used for attitude control during the ballistic phases, and orientation and initial spin of the payload.9 2B26 :  The payload mass of the standard version ranges from 270 to 410 kg depending on the orbit inclination. OSC made enhanced versions availA2B2 2able:- additional 4th stage (liquid fuel): HAPS (Hydrazine Auxiliary Propulsion System)- lengthement of the 2 first stages (+24% propellant in the first stage, +30% in the second)This version named Pegasus XL is 16.5 m long and weighs 22.7 tons. Its performance are 60% better than the original design.Introduced in 1990 Pegasus had a difficult time obtaining a working launcher. Eight standard Pegasus were launched with success, the last one in May 1996. Nowadays only the XL version is produced. The two first launches were failures. After 3 successes the 6th model performed correctly but failed to release its payload.:A2B2' & Pegasus launchesfB2&D2# 4\N\   $& <> \ l |~ #Launch idPayloadLaunch DateSiteTypeStatus/Comment (orbit in perigee x apogee x inclination x period)/_B2UE2#p4\N\ sg^`x190028A: PegsatB: Glomr 2 (USA 055)5 Apr 1990E, B52480 km x 680 km x 941d&D2F2#j4\N\ <>Xhjv291051Microsat 1 to 717 Jul 1991E, B52HAPSPartial failure350 km x 450 km x 82=gUE2G2#|4\N\ *9_PIWVX393009A: Orbcomm XP 1B: SCD 19 Feb 1993 at 14:30 UTC, B52730 km x 790 km x 25PF2H2#n4\N\ b .0brtx493026Alexis25 Apr 1993 at 13:56 UTE, B52Satellite damagedL|G2.J2#p4\N\ 󼬉.0brt594029Step 219 May 1994 at 17:03 UTE, B52HAPSThe perigee was lower than expected600 km x 830 km x 82O}H2}K2#t4\N\ 󼬉*,FZ\d6n/aStep 127 Jun 1994V, L1011XLFailure: malfunctioned during the first stage burn, had to be destroyed!R.J2L2#n4\N\ |KU*,\lnr794046Apex3 Aug 1994 at 14:39 UTV, B52365 km x 2550 km x 70<_}K2M2#4\N\ 88s:9s:K895017A: Orbcomm FM 1B: Orbcomm FM 2C: Microlab 13 Apr 1995V, L1011FtL2 O2#t4\N\ 󼬉*,^rt|9n/aStep 322 Jun 1995 at 19:58 UTV, L1011XLFailure: interstage didn't separate from 2nd stageEM2F2#z4\N\ "W02fz|1096014 O2F2 2REX 209 Mar 1996 at 01:33 UTV, L1011XLD O2_2#z4\N\ "x24h|~1196031MSTI 317 May 1996 at 02:44 UTV, L1011DF2x2#z4\N\ " bU.0dxz1296037TOMS02 Jul 1996 at 07:48 UTV, L1011XLD_22#z4\N\ ""QU.0dxz1396049Fast21 Aug 1996 at 09:47 UTV, L1011XLZ{x22#4\N\ 0˓FW!SU>@rxz1496061SAC BHETE4 Nov 1996 at 17:09 UTWXLthe 2 payloads failed to separate from the third stageVz2A2#4\N\ 0K&H `b1597018A: Minisat 01B: Celestis 121 Apr 1997 at 11:59 UTL1011XLlaunched from the Canary islandsF2V2#n4\N\ Je68h|~1697037Orbview 21 Aug 1997 at 20:20 UTV, L1011XL>A2i2#z|4\N\ "ձT02flnv1797047Forte29 Aug 1997 at 15:00 UTVXL?V2}2#z~4\N\ "󼬉24hnpx1897063Step 422 Oct 1997 at 13:15 UTWXL!Ri22#n4\N\ 8:lrt|1997084Orbcomm FM23 Dec 1997 at 19:11 UTWXLHAPS fourth stage-Q}2ˋ2#4\N\ 0EaU5`1VX2098012A: SNOEB: Teledesic 126 Feb 1998 at 07:07 UTVXL:2Ό2#bt4\N\ *,^dfn2198020Trace02 Apr 1998 at 02:42 UTVXL:ˋ22+ $$Notes: in the launch site column C stands for Cape Canaveral and released at sea, E stands for Edwards and released at Point Arguello, V stands for Vandenberg and released at Point Arguello, and W stands for Wallops. This indication is followed by the airplane type0 Ό282' O FutureJ&22$ MOSC plans to equip Pegasus XL with two turbojets. Once released at 12000 m altitude the Pegasus Turbo will be accelerated by its turbojets to reach 30000 m altitude at over Mach 4. OSC claims the 30.8 t Pegasus Turbo will be 125% more powerful than Pegasus XL and could orbit 1000 kg in LEO.18221=2 2Q2C 2 2# @Pegasus: other future flights2 22E2Q2( ;SeaWifsForteMinisat24 Orbcomm FM xxOrbview (1m imaging satellite OSC plans to launch in late 1997. Planning is already starting on OrbView 2, which will have the same resolution over a wider swath (15km instead of 4km), longer life, and a radar system to supplement its optics.)1 221W>222T+Q22) "VȠ$To view this page you need to register&22# 72321i1dn?322/7ProtonC2v25 : " Protone43221 2h 㭄؉>ɉby Jean-Jacques Serralisting by Gunter Krebs*v22/ , The first activity of the Chelomei OKB-52 located at Reoutov near Moscow was navy missiles manufacturing. In 1959 it started producing the solid propulsion UR-96 ABM and the UR-100 (SS-11 Sego) ICBM with stockable liquid propellant. The Miassichtchev OKB-23 and the Latvotchkin OKB-301 were joined to it in 1960 and 1962 respectively.First generation ProtonChelomei started developping the heavy launcher UR-500 (SL-9/D) in 1961. The production started in 1962 in the Khrounitchev factory in Fili.i22' The first stage had a bundle structure like the US Saturn 1: 6 UDMH tanks of about 1.8 m diameter surrounder a 4.1 m diameter NTO tank. It was powered by 6 adjustable RD-253 motors (Glouchko, NPO Energomash) of 1460 kN thrust at ground level each (SI: 317 s, 1635 kN in vacuum). The thrust of the current version of those motors (modified in 1986) is 1475 kN at ground level and 1745 kN in vacuum.The second stage of 4.15 m diameter features a bloc of 4 RD-0210 motors (Kosberg, KB Khimautomatiki) consuming the same propellant. Each motor provided 583 kN thrust (Specific Impulsion: 327 s) during 210 seconds.i2628 >Ձ+܉ The UR-500 rocket (8K82) was 38.7 m high, weighed 562 tons and could place 12.5 tons payload on low Earth orbit. It was fired four times from Tyouratam: 2 in 1965 and 2 in 1966 and resulted in 3 successes (Proton).Four stages Proton (D1e / SL12)The 4-stage RU-500K was originally developped to flyby the Moon with a manned capsule. Therefore the UR-500 was equipped with 2 upper stages resulting in a 690 tons and 58 meters rocket.The third stage (Chelomei, KB Saliout) had the same diameter as the second. It was propulsed by a single 4-vernier RD-0210 motor. Its thrust was 630 kN during 250 seconds.292% The Block-D fourth stage (Korolev, NPO Energia) was derived from the Korolev's N1 lunar launcher where it was the fith stage. It consumed oxygen and kerosene with a integrated-flux motor. The latter was refirable and provided 85 kN thrust (SI = 352 s) during 600 seconds. This stage was used until 1976 for interplanetary probes. From 1974 on , a modified version called Block-DM was introduced for GEO launched, then followed by a DM2 version in 1982 and and DM3 in 1996. 62U2j e  ‰ -~񢝉Mᇏ~wDVqiNowadays it seems the motor is RD-58The 8K82K launcher introduced in 1967 was used for:- lunar probes (Zond, Luna, up to 5.7 tons) and interplanetary probes (up to 4.6 tons to Mars and 5.3 tons to Venus)- geostationary telecommunication satellites (Raduga, Ekran, Gorizont and then Luch, Gals, Express), meteorological satellite (Electro) and early warning satellite (in the Cosmos series) up to 2.4 tons.`92 3L f 㤄*  mKThree stages Proton (SL13/D1)The Proton launcher was also used in a 3-stage version to orbit payloads up to 21 tons (LEO at 200 km, 51.6 inclination)After it's first flight in 1968 to orbit Proton 4, this version launched:- the space stations of the manned programs (Saliout, Mir) and derived (Almaz)- TKS type vessels (Cosmos MerkurU2 32, Kvant, Kristall, etc...)Note: a modernized version named Proton M is announced for 1996-97. It should have new guidance systems and enhanced 2nd and 3rd stage motors. A cryogenic 4th stage is planned, so as a 5th stage derived from the Rokot Breeze.nJU2{3$ The Proton launcher is marketed by International Launch Services (ILS)9 33' $ Proton launches8n{33#d4]2   $& <> ^ np #Launch idPayloadLaunch date TypeStatus (orbit in perigee x apogee x inc. x period),33#FX4]2" 㡄*24NPT165054Proton 116 Jul 1965+33#FV4]2" 㢄*24LNR265087Proton 22 Nov 1965.33#F\4]2" 02LNR"3n/aProton (3a)24 Mar 1966F+33#FV4]2" 㣄*24LNR466060Proton 36 Jul 1966P33#L4]2" @B\^"t#"567021Cosmos 146 [L1 2]10 Mar 1967K Block-DP: Stage 4 failed O33#L4]2" @BZ\"r#"667032Cosmos 154 [L1 3]8 Apr 1967K Block-DP: Stage 4 failed M3 3#L4]2" :<VX"n#"7n/aZond (4a) [L1 4]28 Sep 1967K Block-DF: Stage 1 failed M3 3#L4]2" :<VX"n#"8n/aZond (4b) [L1 5]21 Nov 1967K Block-DF: Stage 2 failed7 3 3#:n4]2" 8:RTj968013Zond 4 [L1 6]2 Mar 1968K Block-DW 3 3#L4]2" <>XZ"p#"10n/aZond (5a) [L1 7]22 Apr 1968K Block-DF: Stage 2 failed at max Q9 3 3#:r4]2" :<VXn1168076Zond 5 [L1 9]14 Sep 1968K Block-D: 33#:t4]2" <>XZp1268101Zond 6 [L1 10]10 Nov 1968K Block-D. 33#F\4]2" 㤄*46PRX1368103Proton 416 Nov 1968K>3@3#F|4]2" >3@32@Z\r#"14n/aZond (7a) [L1 11]19 Jan 1969K Block-DFF3A3#F4]2" NPjl#"15n/aLuna (15a) (Lunokhod [1])19 Feb 1969K Block-DF6@3wB3#Fl4]2" .0JLb#"16n/aMars (2b)27 Mar 1969K Block-DF5A3gC3#Fj4]2" .0HJ`#"17n/aMars (2c)2 Apr 1969K Block-DF7wB3YD3#Fn4]2" 02LNd#"18n/aLuna (15b)14 Apr 1969K Block-DF6gC3JE3#Fl4]2" 02JLb#"19n/aLuna (15c)4 Jun 1969K Block-DF3YD32F3#:f4]2" .0JLb2069058Luna 1513 Jul 1969K Block-D9JE3 G3#:r4]2" <>VXn2169067Zond 7 [L1 12]7 Aug 1969K Block-DW2F35H3#L4]2" NPjl"#"2268080Cosmos 300 [Luna (16a)]23 Sep 1969K Block-DP: Stage 4 failedW G3JI3#L4]2" NPjl"#"2369092Cosmos 305 [Luna (16b)]22 Oct 1969K Block-DP: Stage 4 failedI5H3NJ3#F4]2" TVpr#"24n/aCosmos (311) [L1E 1, T1K #1]16 Nov 1969K Block-DF8JI3AK3#Fp4]2" 46NPf#"25n/aCosmos (323)6 Feb 1970K Block-DF'NJ3#L3#FN4]2" "$<>D#"26n/a(?)8 Aug 1970KF3AK3 M3#:f4]2" .0JLb2770072Luna 1612 Sep 1970K Block-D:#L3M3#:t4]2" <>XZp2870088Zond 8 [L1 13]20 Oct 1970K Block-D@ M3N3#:4]2" HJdf|2970095Luna 17 (Lunokhod 1)10 Nov 1970K Block-DEM3 3#:4]2" TVnp3070103Cosmos 382 [L1E 2, T1K #2]2 Dec 1970K Block-DN3 324N33#:h4]2" @B\^d3171032Salyut 1 [DOS 1]19 Apr 1971K= 323#L4]2" LNhj""3271042Cosmos 419 [Mars (2d)]10 May 1971K Block-DP: Stage 4 failed to ignite due to timer programming error233#:d4]2" ,.HJ`3371045Mars 219 May 1971K Block-D2233#:d4]2" ,.HJ`3471049Mars 328 May 1971K Block-D233#:d4]2" .0HJ`3571073Luna 182 Sep 1971K Block-D33υ3#:f4]2" .0JLb3671082Luna 1928 Sep 1971K Block-D333#:f4]2" .0JLb3772007Luna 2014 Feb 1972K Block-D]υ3҇3#L4]2" @B\^"d"38n/aSalyut (2) [DOS 2]29 Jul 1972KF: Stage 2 lost controll after 162 sec?3ƈ3#:~4]2" HJbdz3973001Luna 21 (Lunokhod 2)8 Jan 1973K Block-D3҇33#:f4]2" @BZ\b4073017Salyut 2 [OPS 1]3 Apr 1973KBƈ33#:4]2" \^xz4173026Cosmos 557 [Salyut (3), DOS 3]11 May 1973K233#:d4]2" ,.HJ`4273047Mars 421 Jul 1973K Block-D23s3#:d4]2" ,.HJ`4373049Mars 525 Jul 1973K Block-D13Y3#:b4]2" ,.FH^4473052Mars 65 Aug 1973K Block-D1s3?3#:b4]2" ,.FH^4573053Mars 79 Aug 1973K Block-D:Y343#Ft4]2" :<VXp4674017Cosmos 063726 Mar 1974K Block-DM3?3(3#:f4]2" .0JLb4774037Luna 2243(3229 May 1974K Block-D4433#:h4]2" @B\^d4874046Salyut 3 [OPS 2]24 Jun 1974K:(33#Ft4]2" 㘜7:<VXp4974060Molniya 1-S29 Jul 1974K Block-DM333#:f4]2" .0JLb5074084Luna 2328 Oct 1974K Block-D433#:h4]2" @B\^d5174104Salyut 4 [DOS 4]26 Dec 1974K333#:f4]2" 02JLb5275050Venera 98 Jun 1975K Block-D533#:j4]2" 24NPf5375054Venera 1014 Jun 1975K Block-D933#Fr4]2" o:<TVn5475097Cosmos 07758 Oct 1975K Block-DM733#Fn4]2" 02LNd#"55n/aLuna (24a)16 Oct 1975K Block-DF833#Fp4]2" 5oމ68RTl5675123Raduga 0122 Dec 1975K Block-DM43k3#:h4]2" @B\^d5776057Salyut 5 [OPS 3]22 Jun 1976K23R3#:d4]2" .0HJ`5876081Luna 249 Aug 1976K Block-D8k3E3#Fp4]2" 5oމ68RTl5976092Raduga 0211 Sep 1976K Block-DM7R373#Fn4]2" eɉ46PRj6076107Ekran 0126 Oct 1976K Block-DMIE373#>4]2" jl6176121Cosmos 881Cosmos 882[Merkur #1, #2]15 Dec 1976K>73*3#:|4]2" TVprx6277066Cosmos 929 [TKS Merkur #1]17 Jun 1977K8733#Fp4]2" 5oމ68RTl6377071Raduga 0323 Jul 1977K Block-DM O*354#J4]2" rt#"6477077Cosmos (937)Cosmos (9383542)[Merkur #3, #4]4 Aug 1977KF73'4#Fn4]2" eɉ46PRj6577092Ekran 0220 Sep 1977K Block-DM4544#:h4]2" @B\^d6677097Salyut 6 [DOS 5]29 Sep 1977KI'44#>4]2" jl6778032Cosmos 997Cosmos 998[Merkur #5, #6]30 Mar 1978K844#Fp4]2" 02LNf#"68n/aEkran (3a)27 May 1978K Block-DMF844#Fp4]2" 5oމ68RTl6978073Raduga 0418 Jul 1978K Block-DM844#Fp4]2" 02LNf#"70n/aEkran (3b)17 Aug 1978K Block-DMF544#:j4]2" 24LNf7178084Venera 119 Sep 1978K Block-DM644#:l4]2" 24NPh7278086Venera 1214 Sep 1978K Block-DM844#Fp4]2" 02LNf#"73n/aEkran (3c)17 Oct 1978K Block-DMFZ4 4#X4]2" $o:<VX"p"7478118Gorizont 0119 Dec 1978K Block-DMP: Stage 4 failed to reignite Q4 4#F4]2" vx#"75n/aCosmos (1070) / Cosmos (1071) [Merkur #7, #8]5 Jan 1979KF7 4 4#Fn4]2" eɉ46PRj7679015Ekran 0321 Feb 1979K Block-DM8 4 4#Fp4]2" 5oމ68RTl7779035Raduga 0525 Apr 1979K Block-DMN 4 4#:4]2" tv7879042Cosmos 1100 / Cosmos 1101 [Merkur #9, #10]22 May 1979K9 44#Fr4]2" %o:<TVn7979062Gorizont 025 Jul 1979K Block-DM6 44#Fl4]2" eɉ46NPh8079087Ekran 043 Oct 1979K Block-DM:4@4#Ft4]2" 4@42%o:<VXp8179105Gorizont 0328 Dec 1979K Block-DM84A4#Fp4]2" 5oމ68RTl8280016Raduga 0620 Feb 1980K Block-DM:@4B4#Ft4]2" %o:<VXp8380049Gorizont 0414 Jun 1980K Block-DM7A4C4#Fn4]2" eɉ46PRj8480060Ekran 0515 Jul 1980K Block-DM7B4uD4#Fn4]2" 5oމ68PRj8580081Raduga 075 Oct 1980K Block-DM7C4gE4#Fn4]2" eɉ46PRj8680104Ekran 0626 Dec 1980K Block-DM8uD4ZF4#Fp4]2" 5oމ68RTl8781027Raduga 0818 Mar 1981K Block-DM1gE4FG4#Fb4]2" v:<VX^8881039Cosmos 126725 Apr 1981K7ZF48H4#Fn4]2" eɉ46PRj8981061Ekran 0726 Jun 1981K Block-DM8FG4+I4#Fp4]2" 5oމ68RTl9081069Raduga 0930 Jul 1981K Block-DM78H4J4#Fn4]2" =4oމ68PRj9181102Raduga 109 Oct 1981K Block-DM6+I4K4#:l4]2" 24NPh9281106Venera 1330 Oct 1981K Block-DM5J4K4#:j4]2" 24LNf9381110Venera 144 Nov 1981K Block-DM6K4L4#Fl4]2" eɉ46NPh9482009Ekran 085 Feb 1982K Block-DM:K4M4#Ft4]2" %o:<VXp9582020Gorizont 0515 Mar 1982K Block-DM4L4N4#:h4]2" @B\^d9682033Salyut 7 [DOS 6]19 Apr 1982K:M4O4#Ft4]2" 6v:<VXp9782044Cosmos 136617 May 1982K Block-DM8N44#Fp4]2O442" 02LNf#"98n/aEkran (9a)23 Jul 1982K Block-DMF7O44#Fn4]2" eɉ46PRj9982093Ekran 0916 Sep 1982K Block-DM^44#:4]2"10082100Cosmos 1414 [Uragan #1]/Cosmos 1413,1415[Dummy]12 Oct 1982K Block-DM2<44#Fx4]2"%o<>XZt10182103Gorizont 0620 Oct 1982K Block-DM2:44#Ft4]2"44oމ8:TVp10282113Raduga 1126 Nov 1982K Block-DM2<44#Fx4]2"68RTn#"103n/aRaduga (12a)24 Dec 1982K Block-DM2F144#Fb4]2"w<>VX^10483013Cosmos 14432 Mar 1983K94}4#Fr4]2"xdɉ68RTn10583016Ekran 1012 Mar 1983K Block-DM274o4#Fn4]2""24NPj10683020Astron23 Mar 1983K Block-DM29}4c4#Fr4]2"54oމ8:RTn10783028Raduga 128 Apr 1983K Block-DM27o4O4#:n4]2"46NPj10883053Venera 152 Jun 1983K Block-DM27c4;4#:n4]2"46NPj10983054Venera 167 Jun 1983K Block-DM2;O414#Fv4]2"%o<>VXr11083066Gorizont 071 Jul 1983K Block-DM2`;4F4#:4]2"11183084Cosmos 1490-1491 [Uragan #2,3]/Cosmos 1492[Dummy]10 Aug 1983K Block-DM2:14;4#Ft4]2"64oމ8:TVp11283088Raduga 1325 Aug 1983K Block-DM29F4/4#Fr4]2"odɉ68RTn11383100Ekran 1129 Sep 1983K Block-DM2<;424#Fx4]2"%o<>XZt11483118Gorizo/4242nt 0830 Nov 1983K Block-DM2`/4G4#:4]2"11583127Cosmos 1519-1520 [Uragan #4,5]/Cosmos 1521[Dummy]29 Dec 1983K Block-DM2:24<4#Ft4]2"74oމ8:TVp11684016Raduga 1415 Feb 1984K Block-DM2;G424#Fv4]2"V w<>VXr11784022Cosmos 15402 Mar 1984K Block-DM29<4&4#Fr4]2"pdɉ68RTn11884028Ekran 1216 Mar 1984K Block-DM2<244#Fx4]2"R w<>XZt11984031Cosmos 154629 Mar 1984K Block-DM2<&44#Fx4]2"%o<>XZt12084041Gorizont 0922 Apr 1984K Block-DM2`4)4#:4]2"12184047Cosmos 1554-1555 [Uragan #6,7]/Cosmos 1556[Dummy]19 May 1984K Block-DM2:44#Ft4]2"84oމ8:TVp12284063Raduga 1522 Jun 1984K Block-DM2;)44#Fv4]2"#o<>VXr12384078Gorizont 101 Aug 1984K Block-DM2944#Fr4]2"qdɉ68RTn12484090Ekran 1324 Aug 1984K Block-DM2_44#:4]2"12584095Cosmos 1593,1595 [Uragan #8,9]/Cosmos 1594[Dummy]4 Sep 1984K Block-DM2K4"4#F4]2"_剂Z\vx12684106Cosmos 1603 [Tselina-2 #1]28 Sep 1984K Block-DM254 4#:j4]2".0JLf12784125Vega 115 Dec 1984K Block-DM25"44#:j4]2".0JLf12884128Vega 221 Dec 1984K Block-DM2< 44#Fx4]2"|#o<>XZt12985007Gorizont 1118 Jan 1985K Block-DM2<4 5#Fx4]2"8w<>XZt13085016Cosmos 162921 Feb 1985K Block-DM24 52945#Fr4]2"rdɉ68RTn13185024Ekran 1422 Mar 1985K Block-DM2b 55#:4]2"13285037Cosmos 1650-1651 [Uragan #10-11]/Cosmos-1652[Dummy]17 May 1985K Block-DM2K55#F4]2"_剂Z\vx13385042Cosmos 1656 [Tselina-2 #2]30 May 1985K Block-DM2955#Fr4]2"94oމ8:RTn13485070Raduga 168 Aug 1985K Block-DM2@55#:4]2"XZtv|13585086Cosmos 1686 [TKS Merkur #4]27 Sep 1985KO5 5#:4]2"bd~13685102Cosmos 1700 [Luch #1, Altair #1]25 Oct 1985K Block-DM2:55#Ft4]2":4oމ8:TVp13785107Raduga 1715 Nov 1985K Block-DM2b 55#:4]2"13885118Cosmos 1710-1711 [Uragan #12-13]/Cosmos-1712[Dummy]24 Dec 1985K Block-DM2:5 5#Ft4]2";4oމ8:TVp13986007Raduga 1817 Jan 1986K Block-DM225 5#:d4]2"<>XZ`14086017Mir 1 [DOS 7]19 Feb 1986K; 5 5#Fv4]2"w<>VXr14186027Cosmos 17384 Apr 1986K Block-DM29 5 5#Fr4]2"sdɉ68RTn14286038Ekran 1524 May 1986K Block-DM2< 5 5#Fx4]2"}#o<>XZt14386044Gorizont 1210 Jun 1986K Block-DM2O 5 5#:4]2"bd~14486071Cosmos 1778-1780 [Uragan #14-16]16 Sep 1986K Block-DM2: 55#Ft4]2"<4oމ8:TVp14586082Raduga 1925 Oct 1986K Block-DM2< 55#Fx4]2"~#o<>XZt14686090Gorizont 1318 Nov 1986K Block-DM2B5@5#F4]25@52"VXrtz#"14787002Cosmos [1811] [Almaz-T #1]29 Dec 1986KFa5A5#L4]2"^`z|""14887010Cosmos 1817 30 Jan 1987K Block-DM2P: Stage 4 failed:@5B5#Ft4]2"h4oމ8:TVp14987028Raduga 2019 Mar 1987K Block-DM2,A5C5#:X4]2"02LNT15087030Kvant 131 Mar 1987K-oB5D5#L4]2"bd~""15187036Cosmos 1838-1840 [Uragan #17-19]24 Apr 1987K Block-DM2P: Stage 4 failed to reignite<C5E5#Fx4]2"#o<>XZt15287040Gorizont 1411 May 1987K Block-DM22D5F5#Fd4]2"!w<>XZ`15387064Cosmos 187025 Jul 1987K8E5G5#Fp4]2"tdɉ68PRl15487073Ekran 163 Sep 1987K Block-DM2OF5H5#:4]2"bd~15587079Cosmos 1883-1885 [Uragan #20-22]16 Sep 1987K Block-DM2;G5I5#Fv4]2"!w<>VXr15687084Cosmos 18881 Oct 1987K Block-DM2<H5J5#Fx4]2"!w<>XZt15787091Cosmos 189428 Oct 1987K Block-DM2<I5K5#Fx4]2"!w<>XZt15887096Cosmos 189726 Nov 1987K Block-DM2:J5L5#Ft4]2"_4oމ8:TVp15987100Raduga 2110 Dec 1987K Block-DM29K5M5#Fr4]2"udɉ68RTn16087109Ekran 1727 Dec 1987K Block-DM2 NL5N5#L4]2"8:TV"p"161n/aGorizont [15]18 Jan 1988K Block-DM2F: Stage 3 failedbM5O5#F4]2"bd~#"16288009Cosmos 1917-1919 [Uragan #23-25]17 Feb 1988K Block-DM2P: Stage 4 failed<N5€5#Fx4]2O5€52"#o<>XZt16388028Gorizont 1531 Mar 1988K Block-DM2GO55#:4]2"RTnp16488034Cosmos 1940 [Prognoz #1]26 Apr 1988K Block-DM28€55#Fp4]2"vdɉ68PRl16588036Ekran 186 May 1988K Block-DM2O55#:4]2"bd~16688043Cosmos 1946-1948 [Uragan #26-28]21 May 1988K Block-DM2555#:j4]2"02JLf16788058Fobos 17 Jul 1988K Block-DM2655#:l4]2"02LNh16888059Fobos 212 Jul 1988K Block-DM2;55#Fv4]2"(w<>VXr16988066Cosmos 19611 Aug 1988K Block-DM2<5w5#Fx4]2"#o<>XZt17088071Gorizont 1618 Aug 1988K Block-DM2!X55#b4]2"8(w(w(wtv17188085Cosmos 1970Cosmos 1971Cosmos 197216 Sep 1988K Block-DM2:w55#Ft4]2"`4oމ8:TVp17288095Raduga 2220 Oct 1988K Block-DM2955#Fr4]2"wdɉ68RTn17388108Ekran 1910 Dec 1988K Block-DM2!X55#b4]2"8(w(w(wtv17489001Cosmos 1987Cosmos 1988Cosmos 198910 Jan 1989K Block-DM2<55#Fx4]2"#o<>XZt17589004Gorizont 1726 Jan 1989K Block-DM2:55#Ft4]2"a4oމ8:TVp17689030Raduga 2314 Apr 1989K Block-DM2!X55#b4]2"8exexextv17789039Cosmos 2022Cosmos 2023Cosmos 202431 May 1989K Block-DM2;55#Fv4]2"ƭ\:<VXr17889048Raduga 1-121 Jun 1989K Block-DM2;55#Fv4]2"552#o<>VXr17989052Gorizont 185 Jul 1989K Block-DM2<55#Fx4]2"#o<>XZt18089081Gorizont 1928 Sep 1989K Block-DM2,55#:X4]2"02LNT18189093Kvant 226 Nov 1989K65p5#Fl4]2"㲩)C24LNh18289096Granat1 Dec 1989K Block-DM2:5e5#Ft4]2"b4oމ8:TVp18389098Raduga 2415 Dec 1989K Block-DM2<p5\5#Fx4]2"+fx<>XZt18489101Cosmos 205427 Dec 1989K Block-DM2:e5Q5#Ft4]2"c4oމ8:TVp18590016Raduga 2515 Feb 1990K Block-DM2!X\5r5#b4]2"8fxfxfxtv18690045Cosmos 2079Cosmos 2080Cosmos 208119 May 1990K Block-DM2-Q5T5#:Z4]2"24NPV18790048Kristall31 May 1990K<r5K5#Fx4]2"#o<>XZt18890054Gorizont 2020 Jun 1990K Block-DM2<T5B5#Fx4]2"fx<>XZt18990061Cosmos 208518 Jul 1990K Block-DM2 bK5b5#L4]2"46"P"190?9 Aug 1990K Block-DM2F: Stage 2 failed due to forgotten rag in a fuel line;B5X5#Fv4]2"#o<>VXr19190094Gorizont 213 Nov 1990K Block-DM2<b5O5#Fx4]2"#o<>XZt19290102Gorizont 2223 Nov 1990K Block-DM2 WX5o5#b4]2"8&x$x{$xtv19390110Cosmos 2109Cosmos 2110Cosmos 21118 Dec 1990K Block-DM2:O5d5#Ft4]2"d4oމ8:TVp19490112Raduga 2620 Dec 1990K Block-DM2;o5f6#Fv4]2"ƭ\:<Vd5f62Xr19590116Raduga 1-227 Dec 1990K Block-DM2<d5]6#Fx4]2"$x<>XZt19691010Cosmos 213314 Feb 1991K Block-DM2:f6R6#Ft4]2"e4oމ8:TVp19791014Raduga 2728 Feb 1991K Block-DM29]6@6#:r4]2"JLfhn19891024Almaz 1 [Almaz-T #3]31 Mar 1991K WR6`6#b4]2"8$x%x$xtv19991025Cosmos 2139Cosmos 2140Cosmos 21414 Apr 1991K Block-DM2;@6V6#Fv4]2"#o<>VXr20091046Gorizont 232 Jul 1991K Block-DM2<`6M6#Fx4]2"+%x<>XZt20191064Cosmos 215513 Sep 1991K Block-DM2<V6D6#Fx4]2"#o<>XZt20291074Gorizont 2423 Oct 1991K Block-DM2<M6;6#Fx4]2"~%x<>XZt20391079Cosmos 217222 Nov 1991K Block-DM2:D60 6#Ft4]2"f4oމ8:TVp20491087Raduga 2819 Dec 1991K Block-DM2!X;6Q 6#b4]2"8%x%x%xtv20592005Cosmos 2177Cosmos 2178Cosmos 217929 Jan 1992K Block-DM2;0 6G 6#Fv4]2"#o<>VXr20692017Gorizont 252 Apr 1992K Block-DM2<Q 6> 6#Fx4]2"#o<>XZt20792043Gorizont 2614 Jul 1992K Block-DM2!XG 6_ 6#b4]2"8:-x;-x<-xtv20892047Cosmos 2204Cosmos 2205Cosmos 220629 Jul 1992K Block-DM2<> 6V6#Fx4]2"?-x<>XZt20992059Cosmos 220910 Sep 1992K Block-DM29_ 6J6#Fr4]2"dɉ68RTn21092074Ekran 2030 Oct 1992K Block-DM2<V6M@6#Fx4]2"#o<>XZtJ6M@6221192082Gorizont 2727 Nov 1992K Block-DM2<J6DA6#Fx4]2"+x<>XZt21292088Cosmos 222417 Dec 1992K Block-DM2!XM@6eB6#b4]2"8 ,x,x,xtv21393010Cosmos 2234Cosmos 2235Cosmos 223617 Feb 1993K Block-DM2:DA6ZC6#Ft4]2"g4oމ8:TVp21493013Raduga 2925 Mar 1993K Block-DM2A}eB6D6#X4]2"n>:<VX"r"215n/aGorizont #3927 May 1993K Block-DM2F: Stage 2 failed because contaminated UDMH destroyed an engine:ZC6E6#Ft4]2"4oމ8:TVp21693062Raduga 3030 Sep 1993K Block-DM2<D6F6#Fx4]2"#o<>XZt21793069Gorizont 2828 Oct 1993K Block-DM2<E6~G6#Fx4]2"#o<>XZt21893072Gorizont 2918 Nov 1993K Block-DM28F6qH6#Fp4]2"O?24NPl21994002Gals 120 Jan 1994K Block-DM2M:~G6fI6#Ft4]2"ƭ\:<TVp22094008Raduga 1-35 Feb 1994K Block-DM2:qH6[J6#Ft4]2"4oމ8:TVp22194012Raduga 3118 Feb 1994K Block-DM2!XfI6|K6#b4]2"8,x,x,xtv22294021Cosmos 2275Cosmos 2276Cosmos 227711 Apr 1994K Block-DM2<[J6sL6#Fx4]2"#o<>XZt22394030Gorizont 3020 May 1994K Block-DM2;|K6iM6#Fv4]2",x<>VXr22494038Cosmos 22826 Jul 1994K Block-DM2!XsL6N6#b4]2"8,x,x,xtv22594050Cosmos 2287Cosmos 2288Cosmos 228911 Aug 1994K Block-DM2<iM6O6#Fx4]2" -x<>XZt22694060Cosmos 229121 Sep 1994K Block-DM2;N66#Fv4]2"J7O6628:TVr22794067Express 113 Oct 1994K Block-DM2M;O6y6#Fv4]2"Q8:TVr22894069Electro 131 Oct 1994K Block-DM2M!X66#b4]2"8-x-x-xtv22994076Cosmos 2294Cosmos 2295Cosmos 229620 Nov 1994K Block-DM27y66#Fn4]2"vEo24NPj23094082Luch 016 Dec 1994K Block-DM2:66#Ft4]2"4oމ8:TVp23194087Raduga 3228 Dec 1994K Block-DM2 W66#b4]2"8v4xw4xx4xtv23295009Cosmos 2307Cosmos 2308Cosmos 23097 Mar 1995K Block-DM2+66#:V4]2".0JLR23395024Spektr20 May 1995K!X66#b4]2"82x2x2xtv23495037Cosmos 2316Cosmos 2317Cosmos 231824 Jul 1995K Block-DM2<66#Fx4]2"2x<>XZt23595045Cosmos 231930 Aug 1995K Block-DM2866#Fp4]2"mEo24NPl23695054Luch 111 Oct 1995K Block-DM2M966#Rr4]2""O?%46"RTn23795063Gals 217 Nov 1995K Block-DM2P66#n4]2">3x3x3x%vx"23895068Cosmos 2323Cosmos 2324Cosmos 232514 Dec 1995?>66#R|4]2""#o%>@"\^x23996005Gorizont 3125 Jan 1996K Block-DM2<66#Rx4]2""4oމ%:<"XZt24096010Raduga 3319 Feb 1996K Block-DM23r6Ԏ6#R4]2"")~%8:"ln24196021Astra 1F8 Apr 1996 at 23:09 UTK Block-DM3Cmodified DM with less mass and SAAB adapter06ŏ6#R`4]2"" "%68"TV\24296023Priroda23 Apr 1996K>Ԏ66#R|4]2ŏ662""#o%>@"\^x24396022Gorizont 3225 May 1996K Block-DM2)hŏ66#R4]2""*rG%@B"tv24496053Inmarsat 3F26 Sep 1996 at 17:37 UTK Block-DM1Csingle burn for GEO injection I66#R4]2""J7%:<"pr24596058Express 226 Sep 1996 at 17:51 UTK Block-DM2M966#Rr4]2"" "%68"TVn24696064Mars 9616 Nov 1996K Block-D2K66#^4]2"" "zz<>"tv24797026Telstar 524 May 1997 at 17.00 UTK Block-DM4CG66#F4]2"q3x<>np24897028Cosmos 23446 Jun 1997 at 17:57 UTK Block-DM566#[4]2"vՅՅՅrՅՅՅՅ%"8:V24997030A: Iridium 14B: Iridium 12C: Iridium 10D: Iridium 09E: Iridium 13F: Iridium 16G: Iridium 1118 Jun 1997 at 14:02 UTK Block-DM2C^66#R4]2"r3x<>pr"25097041Cosmos 234514 Aug 1997 at 20:49 UTK Block-DM2164 x 190 km x 53.2%a66#X4]2""Dh%<>"rt25197046Panamsat 528 Aug 1997 at 00:33 UTK Block-DM3C214 x 36018 km x 51.666#4]2"xՅ>Յ?ՅՅՅFՅ=Յ%":<X25297051A: Iridium 29B: Iridium 32C: Iridium 33D: Iridium 27E: Iridium 28F: Iridium 30G: Iridium 3114 Sep 1997 at 01:36 UTK Block-DM2C516 x 516 km x 86.6F66#L4]2"ɮ668jl25397070Coupon 112 Nov 1997 at 17:00 UTK Block-DM2 G66#X4]2"")~%8:"ln25497076Astra 1G2 Dec 1997 at 23:10 UTK Block-DM3o66#^O4]2""k%:<"pr25597086Asiasat 324 Dec 1997 at 23:19 UTK Block-DM3P: second burn of the Block DM3 failed and left the satellite in GTO (240 x 36000 km x 51.6)67#[4]2"xՅՅՅՅՅՅՅ%"8:672T25698021A: Iridium 62B: Iridium 63C: Iridium 64D: Iridium 65E: Iridium 66F: Iridium 67G: Iridium 687 Apr 1998 at 02:13 UTK Block-DM2I67#L4]2"3x<>pr25798025Cosmos 235029 Apr 1998 at 04:40 UTK Block-DM2 I77#X4]2""YR^Z%<>"pr25898028Echostar 47 May 1998 at 23:45 UTK Block-DM3S)7/7* $R$Notes: All launches from Tyouratam.67e71 Ke n@e77u7RokotB /775 : " RokotDe77* $4 㭄؉by Jean-Jacques Serra77/ ,[ The primary activity of Chelomei's OKB-52 was navy missiles production. In 1959 the firm started producing more important missiles such as the solid propulsion UR-96 ABM and the UR-100 (SS-11 Sego) ICBM with stockable liquid propellant. 1030 copies of this light ICBM (50 tons) of 3rd generation were deployed in the 60ies and 70ies.Origin: Inter Continental Ballistic Missile (ICBM) of fourth generationAfter designing the RU-200 ICBM and the UR-500 Proton space launcher Chelomei's OKB (now NPO Saliout) developped a new ICBM know as UR-100N or RS-18 (or SS-19 Stilleto) between 1964 and 1975. 360 copies of the 4th generation ICBM were manufactured in the 70ies and 80ies.7 70 . Few characteristics on this missile are known apart that it has two stages with storable liquid propellants. It uses four steerable engines (RD-0233/0234) in stage 1 and a single-chamber main engine with a four-chamber steering engine (RD-0235/0236) in stage 2. All these engines are from Kosberg (KB Khimautomatiki). The UR-100N is about 27 meters long and 2.5 meters in diameter, with a gross takeoff mass of 90 tons.The rokot launcherThe launcher is a SS-19 missile to which a Breeze 3rd stage has been added (or Briz?). Breeze weighs 6.4 tons and is 3.4 m long for 2.2 m diameter. Its in-flight refirable motor uses stockable propellant (NTO-UDMH). The launcher can orbit 1 to 2 tons of payload in LEO.o7Z 7' Two suborbital tests of Rokot were carried out on 20 Nov 1990 and 20 Dec 1991 before launching its first satellite.It should be marketed by Eurockot Launch Services GmbH (Khrunichev and DASA) in 1997. A launch should cost from 7 to 10 million dollars. The first launches should take place in Plesetsk before being transfered at Svobodny in the Russian far East.< 7 7' *O External resourcesCZ 7 7' 8http://www.eurockot.com/8 7 7' " Rokot launchesc 7 7#4]]   $ : XZ #Launch idPayloadLaunch dateStatus (orbit in perigee x apogee x inc. x period)j 7#7#$4]]  (W,.`b194085RS 1526 Dec 1994 at 03:00 UTThe spent third stage exploded a few hours after launchR( 7u7* $P$Notes: All launches from Plesetsk.6#771nGsA7R79ScoutB u775 : " Scoute47R71 2h 㭄؉>ɉby Jean-Jacques Serralisting by Gunter Krebs7}B7* "_ 0The Scout rocket was designed in 1957 by the NACA Langley center (which becamed the NASA Langley Research Center). It was mass prodR7}B7u7uced from 1959 on by Vought Corp. (to become LTV). Scout was 21 m high, weighed 16 tons and was solid fuel only. It was used as light launcher so as sounding rocket. The first stage was an Algol made by Aerojet of 1.1 m diameter which provided 52 t thrust. Algol was controlled by a jet deflector called jetavator which has been designed for the Polaris program. The second stage was a Thiokol Castor derived from the tactical Sergeant missile and provided 24 t thrust. The two upper stages were built by Alleghany Ballistics (now Hercules). The third stage was a 6.2 t thrust Antares and the fourth stage a 1.4 t Altair.R7UE7- (W`The first launches of Scout in 1960 were ballistic flights. The first orbiting attempt failed in December 1960, but on 16 February 1961 Scout successfuly delivered Explorer 09 in orbit. Since then all its stages have been improved. One USAF specific version was called Blue Scout and a Blue Scout Junior (3-stage, Algol-less) was fired 22 times on ballistic missions.Scouts were fired from 3 locations: Wallops Island, Vandenberg and San Marco. The latter is an italian oil platform at large from Kenya which only fired Scouts. Production of the Scout stopped in 1982 but the last vehicle was fired in 1994. This latter version (Scout G1) was 23 m high and weighed 21.7 tons.<}B7E7' * Evolution of ScoutpUE7G7#  mNxyxy\\k> X r   ƀ  DesignationFirst launch1st stage2nd stage3rd stage4th stageinc: 90 (1)inc: 38 (1)inc: 2.9 (1)IE7 H7#| mNxyxy\\k(<_ 0Tj~Scout X-11960Algol 1CCastor 1Antares 1Altair 14559IG7?I7#| mNxyxy\\k(<_ 0Tj~Scout X-21962Algol 1DCastor 1Antares 2Altair 15976I H7^J7#| mNxyxy\\k(<_ 0Tj~Scout X-31963Algol 2ACastor 1Antares 2Altair 16887 J?I7~K7#| mNxyxy\\k(<_ 0Tj~Scout X-41964Algol 2BCastor 1Antares 2Altair 280103 J^J7L7#| mNxyxy\\k(<_ 0Tj~Scout A-11965Algol 2BCastor 2Antares 2Altair 294122'Q~K7M7#| mNxyxy\\k(<_ 0VnScout B-11965Algol 2BCastor 2AAntares 2AAltair 3A116143151'QL7N7#| mNxyxy\\k(<_ 0VnScout D-11972Algol 3ACastor 2AAntares 2AAltair 3A148185198'QM77#| mNxyxy\\k(<_ 0VnScout F-11974Algol 3ACastor 2AAntares 2BAltair N77u73A156193203'QN7F7#| mNxyxy\\k(<_ 0VnScout G-11974Algol 3ACastor 2AAntares 3AAltair 3A166208220t77 ڀ$ 4"hڜrJjQUJPPUKU˜Yu<щD|ۉ̑QdIxNotes: (1) Payload (kg) in circular 550 km orbit; Launches from Vandenberg (90), Wallops Island (38) and San Marco (2.9)Scout was used both by NASA and USAF. It was used for:- Scientific satellites of America (Explorer program), international organizations (ESRO) and other countries (Ariel, San Marco, FR 1, Eole, Azur, Aeros, Miranda, ANS)- US satellites for military, navigation (Transit, Triad, Nova, etc.) and technology (OV3, MSTI, etc.) purposes8F77' " Scout launchesf7X7# m\@O   $& <> \ l |~ #Launch idPayloadLaunch DateSiteTypeStatus/Comment (orbit in perigee x apogee x inclination x period)O7m7#\m\@O "NPjprz1, ST-1n/aNASA radiation probe02 Sep 1960WX1Ballistic flight%XX77#jm\@O "NPhnpx 2, ST-2n/aUSAF radiation probe4 Oct 1960WX1FailureBallistic flight @m77#hm\@O ">@Z`bj 3, ST-3n/aExplorer S5604 Dec 1960WX1FailureG77#hm\@O$&`DF`fhp4, ST-461004Explorer 0916 Feb 1961WX1634x2583x38.9 @77#hm\@O ">@Z`bj 5, ST-5n/aExplorer S5530 Jun 1961WX1FailureK7ڋ7#tm\@O$&e`DF`fhp 6, ST-661022Explorer 1325 Aug 1961WX1Partial failureI77#jm\@O ".0JPRZ 7, ST-7n/aP 2119 Oct 1961WX1FailureBallistic flight Dڋ77#\m\@O "8:RXZd8, ST-8n/aReentry 11 Mar 1962WX1ABallistic flight@77#\m\@O "02LRT\9, ST-9n/aP 21A29 Mar 1962WX2Ballistic flight =77#hzm\@O "8:TZ\d 10, 111n/aSolrad 4B26 Apr 1962VX2F77u7ailure:77#htm\@O "02LRT^ 11, 112n/aP35 124 May 1962VX2MFailureJ7+7#\m\@O$&JLflnx12, 11762039P35 2 (FTV 3502)23 Aug 1962VX2M650x858x98.6 >757#h|m\@O "8:TZ\f 13, 114n/aReentry 231 Aug 1962WX3AFailure:+7;7#htm\@O$&h`DF`fhp14, 11562070Explorer 1616 Dec 1962WX3 E57F7#\m\@O$&BD^dfn15, 11862071Transit 5A-119 Dec 1962VX3698x725x90.6K;7W7#\m\@O$&JLflnx16, 12663005P35 3 (FTV 0240)19 Feb 1963VX3M505x791x100.5 @F7c7#hm\@O ">@Z`bj 17, 119n/aTransit 5A-205 Apr 1963VX3Failure:W7i7#htm\@O "02LRT^ 18, 121n/aP35 426 Apr 1963VX2MFailure@c7o7#\m\@O "02LRT\19, 116n/aRFD 122 May 1963WX3Ballistic flight Ei7z7#\m\@O$&BD^dfn20, 12063022Transit 5A-316 Jun 1963VX3727x757x90.0 Eo77#\m\@O$&@B\bdl21, 11363026GRS (CRL 1)28 Jun 1963WX4411x1311x69.7Oz77#jm\@O "8:TZ\f 22, 110n/aReentry 327 Jul 1963WX3MFailureBallistic flight:77#htm\@O "02LRT^ 23, 132n/aP35 527 Sep 1963VX2BFailure;77#hvm\@O&(k`FHbhjr24, 122R63053Explorer 1919 Dec 1963VX4777#hnm\@O&(e$t>@Z`bj25, 127R64015Ariel 227 Mar 1964WX3 F78#\m\@O78u7&(DF`fhp26, 125R64026Transit 5C-104 Jun 1964VX4854x956x90.4 A78#hm\@O"$@B\bdl 27, 128Rn/aESRS (CRL 2)25 Jun 1964VX4FailureB88#\m\@O"$46PVX`28, 124Rn/aSERT 120 Jul 1964WX4Ballistic flight G88#\m\@O"$<>X^`j29, 129Rn/aReentry 4A18 Aug 1964WX4ABallistic flight;88#hvm\@O&(`FHbhjr30, 134R64051Explorer 2025 Aug 1964VX4A88#\m\@O"$24LRT^31, 130Rn/aRFD 29 Oct 1964WX3CBallistic flight;88#hvm\@O&(`FHbhjr32, 123R64064Explorer 2210 Oct 1964VX4;88#hvm\@O&(`FHbhjr33, 133R64074Explorer 2306 Nov 1964WX4"O8) 8#vm\@O&*(``np34, 135R64076A: Explorer 24B: Explorer 2521 Nov 1964VX4;80 8#hvm\@O&(7FHbhjr35, 137R64084San Marco 115 Dec 1964WX4;) 87 8#hvm\@O&(`FHbhjr36, 136R65032Explorer 2729 Apr 1965WX470 8: 8#hnm\@O&(o^{@B\bdj37, 131R65063Secor 0510 Aug 1965WB;7 8A 8#hvm\@O&(`FHbhjr38, 138R65093Explorer 3019 Nov 1965WX44: 8A8#hhm\@O&(QU8:TZ\d39, 139R65101FR 106 Dec 1965VX4 EA 8L8#\m\@O&(BD^dfl40, 140C65109Transit-O 622 Dec 1965VA909x1086x89.1 EA8c@8#\m\@O&(BD^dfL8c@8u7l41, 142C66005Transit-O 728 Jan 1966VA861x1217x89.7 FL8oA8#\m\@O"$<>V\^h42, 141Cn/aReentry 4B9 Feb 1966WX4ABallistic flight Ec@8zB8#\m\@O&(BD^dfl43, 143C66024Transit-O 826 Mar 1966VA891x1128x89.75oA8{C8#hjm\@O&(0<>X^`f44, 145C66034OV 3-122 Apr 1966VB DzB8D8#\m\@O&(BD^dfl45, 146C66041Transit-O 919 May 1966VA863x980x90.05{C8E8#hjm\@O&(3<>X^`f46, 147C66052OV 3-410 Jun 1966WB5D8F8#hjm\@O&(2<>X^`f47, 148C66070OV 3-304 Aug 1966VB GE8G8#\m\@O&(DF`fhn48, 149C66076Transit-O 1018 Aug 1966VA1056x1101x88.95F8H8#hjm\@O&(1<>X^`f49, 150C66097OV 3-228 Oct 1966VB9G8I8#hrm\@O"$24NTV\ 50, 151Cn/aOV3-531 Jan 1967VBFailure GH8J8#\m\@O&(DF`fhn51, 154C67034Transit-O 1214 Apr 1967VA1053x1083x90.2:I8K8#htm\@O&(7FHbhjp52, 153C67038San Marco 226 Apr 1967SB6J8L8#hlm\@O&(f$t>@Z`bh53, 155C67042Ariel 305 May 1967VA GK8M8#\m\@O&(DF`fhn54, 156C67048Transit-O 1318 May 1967VA1074x1116x89.3DL8N8#hm\@O"$HJdjlr 55, 156Cn/aEsro 2A (Iris 1)29 May 1967VBFailure GM8O8#\m\@O&(DF`fhn56, 157C67092Transit-O 1425 Sep 1967VA1041x1116x89.3AN88#\m\O88u7@O"$46PVX^57, 159Cn/aRAM C119 Oct 1967WBBallistic flightIO88#\m\@O&(LNhnpv58, 158C67120OV 3-6 (Atcos 2)05 Dec 1967VB412x439x90.7 G88#\m\@O&(DF`fhn59, 162C68012Transit-O 1802 Mar 1968VA1035x1139x90.0I8#8#tm\@O&(㴎YBD^dfl 60, 160C68017Solrad 0905 Mar 1968WBPartial failureH878#hm\@O"$<>Z`bl61, 160Cn/aReentry 527 Apr 1968WX5ABallistic flight5#888#hjm\@O&(b>@Z`bf62, 164C68041Esro 2B17 may 1968V!N78Y8#vm\@O&*(``np63, 165C68066A: Explorer 39B: Explorer 4008 Aug 1968VBA88`8#\m\@O"$46PVX^64, 168Cn/aRAM C222 Aug 1968WBBallistic flight6Y8b8#hlm\@O&(ob>@Z`bh65, 167C68084Esro 1A03 Oct 1968VB6`8d8#hlm\@O&(pb>@Z`bh66, 172C69083Esro 1B01 Oct 1969VB3b8c8#hfm\@O&(KU8:TZ\b67, 169C69097Azur08 Nov 1969VB Fd8o8#\m\@O&(DF`fhn68, 176C70067Transit-O 1927 Aug 1970VA954x1221x90.2Ac8v8#\m\@O"$46PVX^69, 171Cn/aRAM C330 Sep 1970WBBallistic flight =o88#jzm\@O&(٧LNhnpv70, 174C70094A: OFOB: RM 109 Nov 1970WB:v88#htm\@O&(`FHbhjp71, 175C70107Explorer 4212 Dec 1970SB:88#htm\@O&(788u7FHbhjp72, 173C71036San Marco 324 Apr 1971SB@88#\m\@O$&24NTV\73, 144CRn/aPAET20 Jun 1971WBBallistic flight888#hpm\@O&(2YBD^dfl74, 177C71058Solrad 1008 Jul 1971WB488#hhm\@O&(JPPU8:TZ\d75, 180C71071Eole16 Aug 1971WB1?88#\~m\@O$&02LRTZ76, 166CRn/aGRP20 Sep 1971WBBallistic flight;88#hvm\@O(*`HJdjlr77, 163CR71096Explorer 4515 Nov 1971SB788#hnm\@O&(g$t>@Z`bj78, 183C71109Ariel 411 Dec 1971VB1;88#hvm\@O&(`FHbhjr79, 184C72061Explorer 4613 Aug 1972WD1I88#\m\@O&(JLflnv80, 182C72069Triad 1 (TIP 1)02 Sep 1972VB1716x863x90.1<88#hxm\@O(*`HJdjlt81, 170CR72091Explorer 4815 Nov 1972SD1688#hlm\@O&(#1<>X^`h82, 185C72092Esro 422 Nov 1972VD1788#hnm\@O&(k>@Z`bj83, 181C72100Aeros 116 Dec 1972VD1 G88#\m\@O&(DF`fhp84, 178C73081Transit-O 2030 Oct 1973VA1907x1136x90.2;88#hvm\@O&(7FHbhjr85, 190C74009San Marco 418 Feb 1974SD1788#hnm\@O&(Yu<щ>@Z`bj86, 188C74013Miranda09 Mar 1974VD1;8 9#hvm\@O&(`FHbhjr87, 191C74040Explorer 5203 Jun 1974VE18 9u7789#hnm\@O&(l>@Z`bj88, 186C74055Aeros 216 Jul 1974VD13 99#hfm\@O&(D68RXZb89, 189C74070ANS30 Aug 1974VD1799#hnm\@O&(h$t>@Z`bj90, 187C74077Ariel 515 Oct 1974SB1:99#htm\@O$&`DF`fhp91, 19475037Explorer 5307 May 1975SF1I9&9#\m\@O&(JLflnv92, 195C75099Triad 2 (TIP 2)12 Oct 1975VD1362x705x90.7P9C9#jm\@O"$^`z 93, 196Cn/aExplorer [56]Explorer [57]05 Dec 1975VF1FailureL&9U9#\m\@O(*NPjprz94, 179CR76047Wideband (P76 5)22 May 1976VB1995x1059x99.6IC9d9#\m\@O"$BD^dfn95, 193Cn/aGravity probe18 Jun 1976WD1Ballistic flightIU9s 9#\m\@O&(JLflnv96, 197C76089Triad 3 (TIP 3)01 Sep 1976VD1475x930x89.9Jd9 9#\m\@O&(HJdjlt97, 200C77106Transat (O 11)28 Oct 1977VD11000x1000x89.95s 9 9#hjm\@O&(εS:<V\^f98, 201C78041AEM 126 Apr 1978VD15 9 9#hjm\@O&(ϵS:<V\^f99, 202C79013AEM 218 Feb 1979WD18 9 9#hpm\@O(*i$t@B\bdl100, 198C79047Ariel 602 Jun 1979WD16 99#hlm\@O(*еS<>X^`h101, 203C79094AEM 330 Oct 1979VG17 99#hnm\@O(*w>@Z`bj102, 192C81044Nova 115 May 1981VG1H9@9#\m\@O(*9@9u7HJdjlt103, 205C83063Hilat (T83 1)27 Jun 1983VG1770x838x82.079A9#hnm\@O(*w>@Z`bj104, 208C84110Nova 212 Oct 1984VG1V@9B9#^m\@O(*`b|105, 209C85066Transit-O 24Transit-O 3003 Aug 1985VG11000x1260x89.8BA9C9#\m\@O(*<>X^`h106, 207C85114ITV 1/213 Dec 1985WG1316x770x37.0OB9D9#\m\@O(*RTntv~107, 199C86088Polar Bear (P87 1)14 Nov 1986VG11170x1180x90.0VC9F9#^m\@O(*`b|108, 204C87080Transit-O 27Transit-O 2916 Sep 1987VG11020x1180x90.0<D9 G9#hxm\@O(*7HJdjlt109, 209C88026San Marco 525 Mar 1988SG1VF9'H9#^m\@O(*`b|110, 211C88033Transit-O 23Transit-O 3225 Apr 1988VG11020x1300x90.07 G9*I9#hnm\@O(*w>@Z`bj111, 213C88052Nova 316 Jun 1988VG1V'H9GJ9#^m\@O(*`b|112, 214C88074Transit-O 25Transit-O 3125 Aug 1988VG11030x1180x90.0L*I9ZK9#^m\@O(*PRlrt|113, 212C90043Macsat 1Macsat 209 May 1990VG1610x770x90.0@GJ9`L9#\m\@O(*8:TZ\d114, 216C91045REX 129 Jun 1991VG1770x870x89.67ZK9cM9#hnm\@O(*~稉>@Z`bj115, 215C92038Sampex03 Jul 1992VG17`L9fN9#hnm\@O(*x>@Z`bj116, 210C92078MSTI 121 Nov 1992VG17cM9iO9#hnm\@O(*8 >@Z`bj117, 217C93041Radcal25 Jun 1993VG17fN9x9#hnm\@O(*x>@iO9x9u7Z`bj118, 218C94028MSTI 209 May 1994VG1tBiO992 2$Notes: Launch site: C for Cape Canaveral, V for Vandenberg, W for Wallops Island and S for San Marco[Gunter Krebs adds:]Although mostly neglected and not part of the "official" launch history, the Blue-Scout-1 and Blue Scout-2 versions will be included in next version of TSE. The main difference was, that the Blue-Scouts had an different aft section of the first stage as they stood on the launch pad (the "normal" Scout was suspended on a launch tower). The Blue-Scout-1 was a 3 stage version of the Scout-X1, the Blue Scout-2 was mostly identical to the Scout-X1.,x99'  The Blue-Scout-2 made one illfated attempt to launch a satellite from Cape Canaveral:01.11.1961 Mercury-MS 1The Mercury-MS 1 payload was a small communication satellite to simmulate the telemetry from a manned Mercury capsule. No replacement was launched.M9e91O nuBe99 :Semiorka and derived from R7Y$995 :J " Semiorka and derived from R7De99* $4 㭄؉by Jean-Jacques SerraX19Z9' bO Origin: ICBM of first generation (R7 Semiorka)P)99' SIn Feb 1953 the Soviet government decided to built a intercontinental rocket. The project management was affected to S.P. Korolev's OKB while V.P. Gouchko's one was in charge of the motors.Originaly the program planned to send a 3 ton payload at 8000 km. It transformed in late 1953 when the thermonuclear warheadwas found to weigh 6 tons. The modified project was accepted in August 1954 under the name R7 (or Semiorka).The R7 was a rocket made of a central body with 4 lateral boosters as the first stage. The conical boosters, were 19.8 m high and 2.68 m diameter (base). The main body, known as Block A, was 28.75 m high and a maximum diameter of 2.95 m at the upper fixation point of the boosters. The missile was known in the US as SS-6 Sapwood; it weighed 267 tons at takeoff and was 30.5 m high.sZ9D9' The first tests of the motors (static bench) took place in Sep 1956. The motors had 4 chambers consuming the couple oxygen-kerosen. The RD-107 was active during 320 seconds and provided 976 kN thrust in vacuum (Isp = 305 s). It featured two verniers. The RD-108 active 120 seconds developped 912 kN in vacuum (Isp = 308 s) and featured 4 verniers.Missiles tests started on 15 May 1957 from Tyuratam (near Bakonour), specially created for the R7. After 3 failures the first successful flight took place on 21 August the same year. A second success on 7 September set on the green light to try and achieve a satellisation.M&99' LO Usage of Semiorka without top stageD99: Bw~~~The first artifical satellite Sputnik 1 was launched on 4 Oct. 1957 from Tyuratam. Only the top stage of the R7 rocket was modified to create the rocket named 8K71 in USSR and A / SL1 in the US.This launcher was further used for 2 satellites. On 3 Nov 1957 it put the 508 kg Sputnik 2 into orbit and its Laka passenger. On 15 May 1958 after a failure in April Sputnik 3 (1327 kg) was also put onto orbit.The Semiorka configuration was such that it was a military device difficult to use. On the contrary it was a great base for a space launcher and therefore it is still used 40 years after its first launch. The constructor of this rocket is now KB Photon, a division of TsSKB Samara.9n9% The RD-107 and RD-108 motors, now built by NPO Energomash, have been enhanced. Their performance is now 1000 kN in vacuum (Isp = 314 s) for the former and 941 kN (Isp = 315 s) for the latter.V/9ď9' ^ Usage of Semiorka with a Block E third stageen9[9& The project of Lunar ď9[99probe launches required a third stage for the R7. This Block E top stage was ordered from the S.A. Kosberg KB (now KB Khimautomatiki) in Feb 1958. It was to be the first liquid stage fired up in vacuum. Its RO-7 motor (or RD-0105) using liquid onxygen and kerosen developped 49 kN thrust (Isp 316 s). It was 2.58 m diameter, 2.98 m long and weighed 8.1 tons, including 7 tons propellant. After several failures since August 1958 the first sucessful launch of the 3-stage R7 occured to send Luna 1 to the moon on 2 Jan 1959. The probe flowby 6400 km from the objective before acquiring a solar orbit. A second failure in August occured before the first moon impact with Luna 2, launched on 12 Sep 1959. Then Luna 3 launched on 4 October took the first pictures of moon's hidden side. Two failures ended the 8K72 carrier, also known as A1 / SL2.Sď99- (~The Block E will be enhanced in 1960 for a piloted launch. A new RD(448 (or RD-0109) developped 54.5 kN thrust (Isp = 324 s).The first Korabl spacecraft (Sputnik 4) was launched on 15 May 1960. It was the first of 7 tentatives including 5 successful launches which preceded the 6 Vostok flights. The Vostok rocket alias 8A92 or A1 / SL3 in the West will also be used to launch automatic satellites. In this configuration it is 38.4 m high and weighs 287 tons. It was 38.4 m high, 287 tons, and could orbit 4.7 tons in LEO or 1.1 tons in 900 km sunsynchronous orbit. This rocket launched:[990 .1  - reconnaissance satellites of first generation (Cosmos Zenith) until 1967- meteorological (Cosmos, Meteor) and observation (Cosmos, IRS) satellites until 1991Note: it seems that the Poliot satellites (1963-1964) built by OKB Chelomei were launched by a modified Vostok named SL5. The SL10 launched used to launch Cosmos 101 and Cosmos 125 (1965-1966) would also have been launched by a modified R7.V/99' ^ Usage of Semiorka with a Block I third stage99$ The 4-stage version of Semiorka was designed in 1959-1960 for interplanetary missions. The Block I third stage was built by KB S.A. Kosberg. It was 2.66 m diameter and 8.1 m long. It weighed 24 tons including 21 tons propellant. It's 4-chamber motor block RO-9 (or RD-0107) used liquid oxygen and Kerosen. It provided 298 kN (Isp = 324 s). The fourth stage, Block L, was built by OKB S.P. Korovev. It was aimed by a CI-5400 integrated flux motor developping 67 kN (Isp = 340 s) with the same propellant.9(9' The two first tentatives to Mars failed in October 1960. In Februry 1961 the first probe to Venus stayed in transfert orbit because of a Block L failure. The second launched on 12 Feb was correctly placed on solar orbit and became Venus 1. in 1962 the 3 launches towards Venus failed and only 1 launch to Mars in Oct.-Nov. succeeded on 1 Nov.After such adifficult start the 8K78 (A2e / SL6) became more reliable and launched several types of space probes (Luna, Zond, Venus and Mars).Z99- (jQvA version without fourth stage designed to launch manned vehicles was named 11A57 (or A2 / SL4). It was first tested in Nov 1963 with Cosmos 22, and then was used for the Voskhod program and to launch second generation Zenith reconnaissance satellites.In Feb 1964 the 4-stage launcher was improved by replacing the 3rd stage motor by a RD-461 (or RD-0110) giving birth to the 8K78M rocket better known an Molniya. This launcher is 42 m high and weighs 306 tons. It can orbit 1.6 tons on an elliptic 12 hours path used by the Molniya telecommunication satellites. This launcher is also used for:(9:= H  l? - space probes to the moon (1.6 tons), Venus (1.2 tons) or Mars (0.95 tons)- scientific satellites Prognoz (0.9 tons) on very eccentric orbits- early warning satellites Oko (Cosmos series) on 12 hour Molniya-type orbitsThe 3-stage version Soyuz alias 11A511 appear9:9ed in Nov 1966 for the launch of Cosmos 133, then the version Soyuz M (11A511M) in Dec 1971 for Cosmos 470. The last version Soyuz U (11A511U) was launched for the first time in Mai 1973 with Cosmos 559. c9b:% For the manned flight a Soyuz U2 version exist; it is more powerful. It's central motor (RD-118) uses cycline instead of kerosen as propellant. The thrust of each booster is 1030 kN (ground level) and 1250 kN in vacuum (Soyuz U: 1015 kN and 1240 kN respectively). The thrust of the central motor is 1010 kN (980 kN for Soyuz U). But the manned launches will from now on be made with kerosen, because the cycline plant in Oufa (Bachkirie) was closed of budget problems. NPO Energomach which produces the motors plan to compensate the performance with new injectors which enhance the combustion fo propellant.:c:L fk  YGܝ Soyuz is in fact the most launched vehicle in the world (over 700 times). It measures 45 to 50 m depending on the versions, weighs 310 tons and can orbit ~7 tons in LEO. In addition to the Soyuz spacecrafts which gave them its name, the rocket was used for:- several types of reconnaissance satellites (Zenith, Kometa, Yantar, etc.)- their civilian counterparts (Bion, Resurs F, Foton, etc.)- the Progress supply shipsI"b::' D Commercial version: Soyouz-Ikarsc:E:& The maximum capacity of the Soyuz U is only attained for launches of retrievable probes in LEO (200 km 51.8) when the cap is jettisoned early. This performance falls to 6.2 tons at 200 km when the cap is released later, as for the more fragile commercial payloads; and 5 tons at 300 km. The Molniya M can place 1.75 tons on a 500/40000 km orbit, 62.8 inclination, or 1.5 tons in sunsynchronous orbit at 800 km altitude.The Russian-French firm Starsem set up by Aerospatiale (35%), Arianespace (15%), RKA (25%) and Samara center (25%) was created in August 1996 to sell Semiorka vehicles (Soyuz, Molniya and derivatives).:. :+ $}x≂The new version is tailored for satellite constellation launches. It has an Ika stage under the cap like Molniya's Block L. This stage equipped with re-ignitable motors has already flown over 30 times with maneuverable observation satellites. The Soyuz-Ikar will be able to deliver 2.5 tons payload in 1400 km 51.8 orbits or 2.35 tons in polar orbit at the same altitude. The first use of the vehicle should be for 4 Globalstar satellites.7E:e :'  O Soyuz 2 (Rus). :_:V zIqiGܝYjQv3xA_Y뉂A enhanced Semiorka named Rus should be available in 1999. It will be used to launch the Cosmos, Foton, Bion and Resurs F satellites with a 3-stage version and Molniya, Meteor, Tselina and Resurs O satellites with a 4-stage version.This new launcher, 51.2 m high, will have the same 3 stages of Soyuz with an improved propulsion and guidance systems. The RD-0101 motor of the 3rd stage will be replaced by a RD-0124 with integrated flux of same thrust, but with a 359 s Isp and a burn duration extended at 300 s. Moreover deployable nozzle will suppress the need for the 4 vernier motors. The top stage (in 4-stage version) will be the Fregat of NPO Lavotchkine. It weighs 6.5 tons including 5.3 tons of stockable propellant (NTO-UDMH). It will be equipped with a S5-92 motor from KB KhimMach of 20 kN which can be re-ignited up to 20 times. This rocket will have 900 kg more performance than the current Soyuz.;e ::' ( Launch statisticsIa_: @:# P]l]]]lkO4Ld|A / SL1A1 / SL2A1 / SL3A2 / SL4A1 / SL5A2e / SL6A1 / SL10Total: @:9:@:#@2 P]l]]]lkO $(,195722 @:A:#@2 P]l]]]lkO $(,195811@:B:#@2 P]l]]]lkO $(,195933A:PC:#@2 P]l]]]lkO $(,196033B:"D:#@4 P]l]]]lkO $*.1961426PC:D:#@6 P]l]]]lkO $*.19627613"D:E:#@: P]l]]]lkO"(.21963811313D:F:#@< P]l]]]lkO$*0419641251422E:wG:#@> P]l]]]lkO$(06196591211133F:NH:#@> P]l]]]lkO&*06196611148134wG:#I:#@: P]l]]]lkO$(.21967821736NH:I:#@: P]l]]]lkO$(.21968234541#I:J:#@: P]l]]]lkO$(.21969237443I:K:#@: P]l]]]lkO$(.21970531743J:wL:#@: P]l]]]lkO$(.21971433340K:MM:#@< P]l]]]lkO$(0419725311147wL:#N:#@< P]l]]]lkO$(0419733401053MM:N:#@: P]l]]]lkO$(.21974636749#N:O:#@< P]l]]]lkO$(0419756401258N::#@< P]l]]]O::9lkO$(0419765381154O::#@< P]l]]]lkO$(0419777371054:[:#@: P]l]]]lkO$(.21978545959:0:#@: P]l]]]lkO$(.21979845760[::#@< P]l]]]lkO$(04198064512630:܄:#@< P]l]]]lkO$(0419816411461::#@< P]l]]]lkO$(0419825431159܄::#@< P]l]]]lkO$(0419834421157:]:#@: P]l]]]lkO"&.21984441155:3:#@< P]l]]]lkO$(0419851401657]::#@: P]l]]]lkO"&.219863614503:܉:#@8 P]l]]]lkO"&,0198743447::#@< P]l]]]lkO$(0419882421155܉::#@8 P]l]]]lkO"&,0198938644:[:#@: P]l]]]lkO"&.21990301242:0:#@: P]l]]]lkO$(.21991124530[::#@8 P]l]]]lkO"&,01992248320:؎:#@8 P]l]]]lkO"&,0199317825::#@8 P]l]]]lkO"&,0199415318&؎: :# : :97:C:1Gs!uCC::G:ShavitC ::5 : " ShavitDC::* $4 㭄؉by Jean-Jacques SerraL%::' J Origin: Jericho ballistic missiles. :D:$ The developpement of the first Israeli ballistic missile named Jericho started in the early sixties. This rocket would have been designed with the help of the French company Dassault-Breguet which was studying the MD-600 ballistic missiles at that time. After the French export embargo of armement to Israel in 1967 the developpement would have been continued by Israel Defense Industries with internal technology. Jericho 1 went operational in 1973. It was apparently a single stage solid missile range approx. 500 km.:L:% Its follow up Jericho 2 was 2-stage. It would have been designed in in seventies and first launched in 1986. The Jericho 3 was 12 m long and 1.2 m diameter. It would have been capable of launching 1 ton at 1500 km distance.BD::' 6 Shavit launchers (Comet)L::$ We still only have few details on Shavit. It is a 3-stage solid launcher whose 2 first stages are inherited from Jericho 2. The third stage was built by Raphael. The two first stages have a composit structure. They are identical and weigh approx. 13 tons. The third stage is spherical, with a titanium structure. It weighs 2 tons and its 60 kN motor burns during 92.5 seconds. The equipement case with its rotation table is located under the third stage and is jettisoned before its ignition.b)::9 @SfffThe Shavit launches take place from the Palmahim air force base, south of Tel Aviv. The launches have a 143 degrees inclination to avoid launching above neighboring countries. This conditions restricts satellisation capabilities: Offek 1 and Offek 2 launched in Sep 1988 and Apr 1990 weighed ~160 kg while Offek 3 launched in Apr 1995 weighed 225 kg.Israel had proposed, with no success, a commercial version of the Shavit named Next. Nowadays another derivative with a fourth stage for a more precise orbit injection is proposed for export.9:<:' $ Shavit launchesk:Y:#44]y]   $ : X hj #Launch idPayloadLaunch dateTypeStatus (orbit in perigee x apogee x inc. x period))<:7:#:R4]y] ,.HJN188087Offek 119 Sep 1998(Y::#:P4]y] ,.FHL290027Offek 23 Apr 199027::#Fd4]y] $&* 3FTO??unofficial launch failure4::#:h4]y] ,.^`d495018Offek 35 Apr 1995 at 11:16 UT R::#F4]y] (*\^p 5FTOOffek 422 Jan 1998 at 13:00 UT3-stageFailure: second stage?P-:G:# ZAll launches from Palamchim Air Force Base6:}:16u vD}:;m;StartB G::5 : " StartD}:;* $4 㭄؉by Jean-Jacques Serra:;G::;+ $The development of powder ballistic missiles started in 1958 in Russia. It was carried out by a division created by Korolev (today NPO Soyouz) directed by I. Sadovsky and after 1966 by A.D. Nadiradze. The first ICBM was the 3-stage RS-12 (SS-13 Savage) with metallic structure. Only 60 items were produced. Two mobile missiles were then derived from it: the SS-14 which used the 2 upper stages of the SS-13 and the SS-15 which refurbished the first and third stage.n;;/ , In the seventies the RS-14 ICBM (SS-16 Sinner) was a much improved version of the RS-12, especially for the reeled structure and the guidance. This ICBM was not deployed following the SALT agreements. The RSD-10 IRBM (SS-20 Sabre) produced to replace the aging SS-4 and SS-5 were deployed (up to 378 operational) before being retrieved with the INF agreements.Origin: Inter Continental Ballistic Missile (ICBM) of fith generationAt the beginning of the eighties the NPO Soyouz designed a new mobile ICBM named RS-12M Topol (SS-25 Sickle) to replace old launching silos. This fith generation missile which was operational in 1985 is the biggest mobile strategic missile of the CIS. According to the Russians the SS-25 is derived from the SS-13. With 3 stages it is 18.5 m long, 1.8 m diameter and weighs about 40 tons. It can send a 1 ton payload to more than 10000 km.;t;0 .- The Start launcherThe first version Start 1 is a 4-stage launcher which 3 first stages are derived from the SS-25. it is 22.7 m high, weighs 47 tons at takeoff and can deliver 300 kg on polar orbit ot 500 kg in equatorial orbit. It was tested only once in March 1993.The Start offered for commercial flights has an additional stage: an improved version of SS-20's second stage is inserted between the first and second stage. The whole is then 29 m high and 60 tons. It can put 450 kg in polar orbit. It's first launch in March 1995 failed. An agreement with Akjuit Aerospace (Canada) was signed to launch vehicles from SpacePort Canada from late 1998.8;;' " Start launcheskt; ;#44]y]   $ : X hj #Launch idPayloadLaunch dateTypeStatus (orbit in perigee x apogee x inc. x period)H; ;#F4]y] \02LN`193014Start 125 Mar 19934-stagelaunched from Plesetsk?v ; ;#b4]y] * ډ- HJdfx 2FTOTechsat 1Unamsat 128 Mar 19955-stageFailure cause: 5th stage failedlaunched from Plesetsk; ; ;#Rv4]y] "JiU,.^`r397010Zeya4 Mar 1997 at 2:00 UT4-stage< ;;#Rx4]y] "^`B8:npt497085Early Bird24 Dec 1997 at 13:32 UTiF ;m;# All launches from Svobodny (51.2 N 128.0 E) unless otherwise stated4;;1!uE;;T@;STS@ m;;5 :u@" STS;;+ ${ Space Transport SystemAmerican space Shutle programThe orbiter is 45 m long, 14.4 m wide and weights 67.5 t. It can carry 8 persons and a 29 t bay. It is launched with a 700 t tank.<;@;' *O External resour;@;m;cesC;T@;' 8http://shuttle.nasa.gov/1@;@;1UF@; G;-G;Y#T@;@;6 DUせDxJDyuDzD{|}~〛㬛(㣛㤛㥛㦛㧛㨛㩛㪛㫛כΛϛЛћқӛԛ՛֛(T-$%&'()*+,XOPQRSTUWボ}STS 01STS 02STS 03STS 04STS 05STS 06STS 07STS 08STS 09STS 11STS 13STS 16STS 17STS 19STS 20STS 23STS 24STS 25STS 26STS 26RSTS 27STS 27RSTS 28STS 28RSTS 29STS 30STS 30RSTS 31STS 31RSTS 32STS 32RSTS 33STS 33RSTS 34STS 35STS 36STS 37STS 38STS 39STS 40STS 41STS 42STS 43STS 44STS 45STS 46STS 47STS 48STS 49STS 50STS 51STS 52STS 53STS 54STS 55STS 56STS 57STS 58STS 59STS 60STS 61STS 62STS 63STS 64STS 65STS 66STS 67STS 68STS 69STS 70STS 71STS 72STS 73STS 74STS 75STS 76STS 77STS 78STS 79STS 80STS 81STS 82STS 83STS 84STS 85STS 86STS 87STS 89STS 90STS 94$@;-G;" 7 G;dG;13vGdG;G;K;STS 01C-G;G;5 :u@" STS 011 dG;G;'  GeneralTG;,H;A#R&Launch id81034\G;H;A#R6Launch date12 Apr 1981g&,H;H;A#RLLaunch siteCape Canaveral pad 39AVH;EI;A#R*TypeColumbia #01d"H;I;B#TDCrewJohn YoungRobert Crippen]EI;J;A#R8Landing date14 Apr 1981YI;_J;A#R0Landing siteEdwardsQJ;J;A#R PayloadnoneQ+_J;K;& VFlight of 54 h 20 min 52 sDFI mission<J;=K;' * External resourceslEK;K;' http://www.ksc.nasa.gov/shuttle/missions/sts-1/mission-sts-1.html7=K;K;1^~vEwHK;#L;x;STS 02CK;#L;5 :u@" STS 021 K;TL;'  GeneralT#L;L;A#R&Launch id81111\TL;M;A#R6Launch date12 Nov 1981g&L;kM;A#RLLaunch siteCape Canaveral pad 39AVM;M;A#R*TypeColumbia #02e#kM;&N;B#TFCrewRichard TrulyJoseph Engle]M;N;A#R8Landing date14 Nov 1981Y&N;N;A#R0Landing siteEdwardsQN;-O;A#R Payloadnone{UN;O;& Flight of 54 h 13 min 12 s. The flight was shortenOSTA 1 mission: 7 experiences<-O; ;' *O External resourcesO; ;K;lEO;x;' http://www.ksc.nasa.gov/shuttle/missions/sts-2/mission-sts-2.html7 ;;19vwI;;;STS 03Cx;;5 :u@" STS 031 ;#;'  GeneralT;w;A#R&Launch id82022\#;Ӂ;A#R6Launch date22 Mar 1982g&w;:;A#RLLaunch siteCape Canaveral pad 39AVӁ;;A#R*TypeColumbia #03h&:;;B#TLCrewJack LousmaCharles Fullerton];U;A#R8Landing date30 Mar 1982];;A#R8Landing siteWhite SandsQU;;A#R PayloadnoneO);R;& RFlight of 8 days 5 minOSS 1 mission<;;' * External resourceslER;;' http://www.ksc.nasa.gov/shuttle/missions/sts-3/mission-sts-3.html7;1;1DEw6wJ1;t;;STS 04C;t;5 :u@" STS 041 1;;'  GeneralTt;;A#R&Launch id82065\;U;A#R6Launch date27 Jun 1982g&;;A#RLLaunch siteCape Canaveral pad 39AVU;;A#R*TypeColumbia #04l*;~;B#TTCrewThomas MattinglyHenry Harstfield\;ڇ;A#R6Landing date4 Jul 1982Y~;3;A#R0Landing siteEdwardsQڇ;;A#R Payloadnone[53;߈;& jFlight of 7 days 1 h 9 min 39 sDoD 82-1 mission<;;' * External resourceslE߈;;' http://www.ksc.nasa.gov/shuttle/missions/sts-4/mission-sts-4.html7;;1rwwK;;B;STS 05C;;5 :u@" STS 051 ;2;'  GeneralT;;A#R&Launch id82110\2;;A#R6Launch date11 Nov 1982_;A;A#R<Launch siteCape CanaveralV;;A#R*TypeColumbia #05@A;;D#XCrewVance BrandRobert OvermyerJoseph AllenWilliam Lenoir];x;A#R8Landing date16 Nov 1982Y;ь;A#R0Landing siteEdwardsq#x;B;N#lF*=HWQQPayloadB: SBS 3C: Anik C3X4ь;;$ hFirst operational flight: 5 days 2 h 14 min 25 s<B;֍;' *O External resourceslE;B;' http://www.ksc.nasa.gov/shuttle/missions/sts-5/mission-sts-5.html7֍;y;16wbwLy;;0;STS 06CB;;5 :u@" STS 061 y;;'  GeneralT;A;A#R&Launch id83026[;;A#R4Launch date4 Apr 1983_A; ;A#R<Launch siteCape Canaveral; ;B;X;d;A#R.TypeChallenger #01> ;;D#X|CrewDonald PetersonStory MusgravePaul WeitzKarol Bobko\d;B;A#R6Landing date9 Apr 1983Y;;A#R0Landing siteEdwards^B;;G#^.OMPayloadB: TDRS 1i;;& Flight of 5 days 24 min 32 sMusgrave and Peterson worked 3 h 50 min in space to simulate repairings<;;' *O External resourceslE;0;' http://www.ksc.nasa.gov/shuttle/missions/sts-6/mission-sts-6.html7;g;1wIwMg;;;;STS 07C0;;5 :u@" STS 071 g;;'  GeneralT;/;A#R&Launch id83059\;;A#R6Launch date18 Jun 1983_/;;A#R<Launch siteCape CanaveralX;B;A#R.TypeChallenger #02m;;E#ZCrewRobert CrippenFrederik HauckSally Ride (first american woman in space)Normand ThagardJohn Fabian]B;Q;A#R8Landing date24 Jun 1983Y;;A#R0Landing siteEdwardsLQ;K;U#z8QQ2:9b竉PayloadB: Anik C2C: Palapa B1D: Spas 1 (launched and retrieved)H$;;$ HFlight of 6 days 2 h 24 min 10 s<K;;' *O External resourceslE;;;' http://www.ksc.nasa.gov/shuttle/missions/sts-7/mission-sts-7.html7;r;1ibwwNr;;;STS 08C;;;5 :u@" STS 081 r;;'  GeneralT;:;A#R&Launch id83089\;;A#R6Launch date30 Aug 1983_:;;A#R<Launch siteCape CanaveralX;M;A#R.TypeChallenger #03W;;E#ZCrewRichard TrulyDaniel BrandensteinDale GardnerGruion BlufordWilliam Thornton\M;E;A#R6Landing date5 Sep 1983Y;;A#R0Landing siteEdwards`E;;G#^2tG@cPayloadB: Insat 1BG#;E;$ FFlight of 6 days 1 h 8 min 40 s<;;' *O External resourceslEE;;' http://www.ksc.nasa.gov/shuttle/missions/sts-8/mission-sts-8.html7;$;1IwxO$;g;%<STS 09C;g;5 :u@" STS 099$;;# ,Also called STS 41A1 g;;'  GeneralT;%;A#R&Launch id83116\;;A#R6Launch date28 Nov 1983g&%;;A#RLLaunch siteCape Canaveral pad 39AV;>;A#R*TypeColumbia #06e; <F#\CrewJohn YoungBrewster ShawOwen GarriottRobert ParkerByron LichtenbergUlf Merbold (Germany)>; <;\>;h<A#R6Landing date8 Dec 1983Y <<A#R0Landing siteEdwardsQh<<A#R PayloadnonekE<}<& Flight of 10 days 7 h 47 minSpacelab 1 mission (70 experiences)<<<' *O External resourceslE}<%<' http://www.ksc.nasa.gov/shuttle/missions/sts-9/mission-sts-9.html7<\<16wxP\<<<STS 11C%<<5 :u@" STS 119\<<# ,Also called STS 41B1 < <'  GeneralT<]<A#R&Launch id84011[ <<A#R4Launch date3 Feb 1984_]<<A#R<Launch siteCape CanaveralX<o<A#R.TypeChallenger #04R<<E#ZCrewVance BrandRobert GibsonRonald Mc NairBruce Mc CandlessRobert Stewart]o<c<A#R8Landing date11 Feb 1984`<<A#R>Landing siteCape CanaveralJc<b<U#z8/~3:9PayloadB: Westar 6C: IRT (launched and retrieved)D: Palapa B2v<<& Flight of 7 days 23 h 17 minFirst free flight for Mc Candless and Stewart with the Manned Manoeuvring Unit (MMU)<b<:<' *O External resourcesjC<<' http://www.ksc.nasa.gov/shuttle/missions/41-b/mission-41-b.html7:<<1xxQ<< <STS 13C<<5 :u@" STS 139<W<# ,Also called STS 41C1 <<'  GeneralTW<<A#R&Launch id84034[<7 <A#R4Launch date6 Apr 1984_< <A#R<Launch siteCape CanaveralX7 < <A#R.TypeChallenger #05P < <E#ZCrewRobert CrippenFrancis ScobeeTerry HartGeorge NelsonJames Van Hoften] < <A#R8Landing date13 Apr 1984Y <9 <A#R0Landing siteEdwardsY < <G#^$}XUPayloadLDEFW9 < <, (Flight of 6 days 23 h 40 minReparation of SMM in orbit by Nelson and Van Hoften< <Q <' *O External resourcesjC < <' http://www.ksc.nasa.gov/shuttle/missions/41-c/mission-41-c.html7Q < <1xЀxR <5 <B<STS 16C <5 <5 :u@" STS 169 <n <# ,Also called STS 41D1 5 < <'  GeneralTn < <A#R&Launch id84093\ <O<A#R6Launch date30 Aug 1984_ <<A#R<Launch siteCape CanaveralWO<<A#R,TypeDiscovery #01x<<F#\CrewHenry HartsfieldMichael CoatsRichard MullaneSteven HawleyCharles Walker (first non astronaut)Judith Resnik\<+@<A#R6<+@< <Landing date5 Sep 1984Y<@<A#R0Landing siteEdwards5+@<A<U#zj8=HW"AgƵPayloadB: SBS 4C: Leasat 2D: Telstar 302Q+@<_A<& VFlight of 6 days 56 minOATS 1 mission<A<A<' *O External resourcesjC_A<B<' http://www.ksc.nasa.gov/shuttle/missions/41-d/mission-41-d.html7A<Landing siteCape CanaveralYE<>F<G#^$UdPUPayloadERBSL&E<F<& LFlight of 8 days 5 h 23 minSIR C<>F<F<' *O External resourcesjCF<0G<' http://www.ksc.nasa.gov/shuttle/missions/41-g/mission-41-g.html7F<gG<1NЀxxTgG<G<L<STS 19C0G<G<5 :u@" STS 199gG<G<# ,Also called STS 51A1 G<H<'  GeneralTG<hH<A#R&Launch id84113[H<H<A#R4Launch date8 Nov 1984_hH<"I<A#R<Launch siteCape CanaveralWH<yI<A#R,TypeDiscovery #02J"I<J<E#ZCrewFrederik HauckJoseph AllenDavid WalkerDale GardnerAnna Fisher]yI<eJ<A#R8Landing date16 Nov 1984`J<J<A#R>Landing siteCape Canaveralt&eJ<9K<N#lL*QQ!AgPayloadB: Anik D2C: Leasat 1J<!L<9 @_3:9/"Flight of 7 days 23 h 45 minPalapa B2 and Westar 6 are brought back on Earth (were placed on a bad orbit by STS 11). Operation financed by the insurance companies.<9K<]L<' *O External resourcesjC!L<L<' http://www.ksc.nasa.gov/shuttle/missions/51-a/mission-51-a.html7]L<L<1xyUL<AM<Ɓ<STS 20CL<AM<5 :u@" STS 209L<zM<# ,Also called STS 51C1 AM<M<'  GeneralTzM<M<A#R&Launch id85010\M<[N<A#R6Launch date24 Jan 1985_M<N<A#R<Launch siteCape CanaveralW[N<O<A#R,TypeDiscovery #03PN<O<E#ZCrewThomas MattinglyLoren ShriverEllison OnizukaJames BuchliGary Payton]O<<A#R8Landing date27 Jan 198O<<L<5`O<o<A#R>Landing siteCape Canaveral_<΀<G#^0㷫뉂PayloadB: USA 008R,o< <& XFlight of 3 days 1 h 33 minDoD mission<΀<\<' *O External resourcesjC <Ɓ<' http://www.ksc.nasa.gov/shuttle/missions/51-c/mission-51-c.html7\<<1xyV<@<<STS 23CƁ<@<5 :u@" STS 239<y<# ,Also called STS 51D1 @<<'  GeneralTy<<A#R&Launch id85028\<Z<A#R6Launch date12 Apr 1985_<<A#R<Launch siteCape CanaveralWZ<<A#R,TypeDiscovery #04u<̄<G#^CrewKarol BobkoDonald WilliamsDavid GriggsMargaret SeddonJeffrey HoffmanDavid Mc WalkerJack Garn (senator)]<)<A#R8Landing date19 Apr 1985`̄<<A#R>Landing siteCape Canaveralt&)<<N#lL*QQ#AgPayloadB: Anik C1C: Leasat 3I%<F<$ JFlight of 6 days 23 h 55 min 20 s<<<' *O External resourcesjCF<<' http://www.ksc.nasa.gov/shuttle/missions/51-d/mission-51-d.html7<#<1yyW#<f<+<STS 24C<f<5 :u@" STS 249#<<# ,Also called STS 51B1 f<Ї<'  GeneralT<$<A#R&Launch id85034\Ї<<A#R6Launch date29 Apr 1985_$<߈<A#R<Launch siteCape CanaveralX<7<A#R.TypeChallenger #07r߈<<G#^CrewRobert OvermyerFrederik GregoryDon LindWilliam ThorntonTaylor WangNorman ThagardLodewijk Vandenberg\7<L<A#R6Landing date6 May 1985Y<<A#R0Landing siteEdwardsJL<1<B#TPayloadB: Nusat 1 (radar calibration?)C: Glomr (couldn't be ejected)T.<<& \Flight of 7 days 8 minSpacelab 3 mission<1<<' *O External resourcesjC<+<' http://www.ksc.nasa.gov/shuttle/missions/51-b/mission-51-b.html7<b<1DyyXb<<<STS 25C+<<5 :u@" STS 259b<ތ<# ,Also called STS 51G1 <<'  GeneralTތ<c<A#R&Launch id85048\<<A#R6Launch date17 Jun 1985_c<<A#R<Launch siteCape CanaveralW<u<A#R,TypeDiscovery #05<D<H#^CrewDaniel BrandesteinJohn CreightonJohn FabianShannon LucidSteven NagelPatrick Baudry (France)Sultan Al Saud (Saudi Arabia)]u<<A#R8Landing date24 Jun 1985YD< <A#R0Landing siteEdwards< <+<e<<\#FF5鉂Ƶ/̸~PayloadB: Morelos 1C: Arabsat 1BD: Telstar 303E: Spartan 101 (launched and retrieved)H$ <<$ HFlight of 7 days 1 h 38 min 53 s<<Q<' *O External resourcesjC<<' http://www.ksc.nasa.gov/shuttle/missions/51-g/mission-51-g.html7Q<<1AyyY<5<E<STS 26C<5<5 :u@" STS 269<n<# ,Also called STS 51F1 5<<'  GeneralTn<<A#R&Launch id85063\<O<A#R6Launch date29 Jul 1985_<<A#R<Launch siteCape CanaveralXO<<A#R.TypeChallenger #08g<<G#^CrewStory MusgraveAntony EnglandJohn BartoeRoy BridgesKarl HeniseLoren ActonGordon Fullerton\<<A#R6Landing date6 Aug 1985Y<i<A#R0Landing siteEdwardsl+<<A#RVPayloadB: PDP (launched and retrieved)i<<' GFlight 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 orbitSpacelab 2 mission<<<' *O External resourcesjC<E<' http://www.ksc.nasa.gov/shuttle/missions/51-f/mission-51-f.html8<}<1J/{zZ}<<<STS 26RDE<<5 : u@" STS 26R9}<<# ,Also called STS 81A1 <+<'  GeneralT<<A#R&Launch id88091\+<<A#R6Launch date29 Sep 1988_<:<A#R<Launch siteCape CanaveralW<<A#R,TypeDiscovery #07G:<<E#ZCrewR. HauckRichard CoveyJohn LoungeGeorge NelsonDavid Hilmers\<y<A#R6Landing date3 Oct 1988Y<<A#R0Landing siteEdwards^y<0<G#^.OMPayloadB: TDRS 3<<l<' *O External resourcesnG0<<' http://www.ksc.nasa.gov/shuttle/missions/sts-26/mission-sts-26.html7l<<1y>z[<T<=STS 27C<T<5 :u@" STS 279<<# ,Also called STS 51I1 T<<'  GeneralT<<A#R&Launch id85076\<n<A#R6Launch date27 Aug 1985_<<A#R<Launch siteCape CanaveralWn<$<A#R,TypeDiscovery #06L<<E#ZCrewJoe EngleRichard CoveyJames Van HoftenWilliam FisherJohn Lounge\$<<A#R6Landing date3 Sep 1985Y<j<A#R0Landing siteEdwards2< =U#zd8_iS$AgPayloadB: Optus A1C: ASC 1D: Leasat 4j< =<`:j<l=& tFlight of 7 days 2 h 18 min 29 sLeasat 3 was repared< ==' *O External resourcesjCl==' http://www.ksc.nasa.gov/shuttle/missions/51-i/mission-51-i.html8=J=13yz\J===STS 27RD==5 : u@" STS 27R9J==# ,Also called STS 91A1 =='  GeneralT=L=A#R&Launch id88106[==A#R4Launch date2 Dec 1988_L==A#R<Launch siteCape CanaveralV=\=A#R*TypeAtlantis #03M==E#ZCrewRobert GibsonGuy GardnerRochard MullaneJerry RossWilliam Sheperd\\=J=A#R6Landing date6 Dec 1988Y==A#R0Landing siteEdwardsbJ==G#^6-PayloadB: Lacrosse 1K%=P=& JFlight of 4 days 9 hDoD mission<==' *O External resourcesnGP==' http://www.ksc.nasa.gov/shuttle/missions/sts-27/mission-sts-27.html7=1=1yz]1=t= =STS 28C=t=5 :u@" STS 2891==# ,Also called STS 51J1 t=='  GeneralT=2=A#R&Launch id85092[==A#R4Launch date3 Oct 1985_2==A#R<Launch siteCape CanaveralV=B=A#R*TypeAtlantis #01M==E#ZCrewKarol BobkoRonald GrabeDavid HilmersRobert StewartWilliam Pailes\B=0 =A#R6Landing date7 Oct 1985Y= =A#R0Landing siteEdwardsw)0 = =N#lR*ceMceMPayloadB: DSCS 3-03C: DSCS 3-04R, =R =& XFlight of 4 days 1 h 45 minDoD mission< = =' *O External resourcesjCR = =' http://www.ksc.nasa.gov/shuttle/missions/51-j/mission-51-j.html8 =0 =1уzv{^0 =t = @=STS 28RD =t =5 : u@" STS 28R90 = =# ,Also called STS 91D1 t = ='  GeneralT =2 =A#R&Launch id89061[ = =A#R4Launch date8 Aug 1989g&2 = =A#RLLaunch siteCape Canaveral pad 39BV =J =A#R*TypeColumbia #08N = =E#ZCrewBrewster ShawRichard RichardsDavid LeetsmaJames AdamsonMark Brown]J =:=A#R8Landing date13 Aug 1989Y ==A#R0Landing siteEdwardsj":==H#`D㷪뉂PayloadB: USA 040C: USA 413=0=$ DoD mission<=l=' *O External resourcesnG0= @=' http://www.ksc.nasa.gov/shuttle/missions/sts-28/mission-sts-28.htmll= @= =7l=C@=1Nzуz_C@=@=D=STS 29C @=@=5 :u@" STS 299C@=@=# ,Also called STS 91B1 @=@='  GeneralT@=DA=A#R&Launch id89021\@=A=A#R6Launch date13 Mar 1989_DA=A=A#R<Launch siteCape CanaveralWA=VB=A#R,TypeDiscovery #08JA=B=E#ZCrewMichel CoatsJohn BlahaJames BuchliRobert SpringerJames Bagion]VB=BC=A#R8Landing date18 Mar 1989YB=C=A#R0Landing siteEdwards^BC=C=G#^.OMPayloadB: TDRS 4<C=5D=' *O External resourcesnGC=D=' http://www.ksc.nasa.gov/shuttle/missions/sts-29/mission-sts-29.html75D=D=1?>zMz`D=E=+J=STS 30CD=E=5 :u@" STS 309D=VE=# ,Also called STS 61A1 E=E='  GeneralTVE=E=A#R&Launch id85104\E=7F=A#R6Launch date30 Oct 1985_E=F=A#R<Launch siteCape CanaveralX7F=F=A#R.TypeChallenger #09F=G=I#`GCrewHenry HartsfieldSteven NagelJames BuchliGuion BlufordBonnie DunbarErnst Messerschmidt (Germany)Reinhardt Furrer (Germany)Wubbo Ockels (Netherlands)\F=6H=A#R6Landing date6 Nov 1985YG=H=A#R0Landing siteEdwardsy86H=I=A#RpPayloadB: Glomr (Global Low Orbiting Message Relay)}WH=I=& Flight of 7 days 44 min 51 sSpacelab D1 mission (76 experiences including BIORAK)<I=I=' *O External resourcesjCI=+J=' http://www.ksc.nasa.gov/shuttle/missions/61-a/mission-61-a.html8I=cJ=1AzzacJ=J=N=STS 30RD+J=J=5 : u@" STS 30R9cJ=J=# ,Also called STS 91C1 J=K='  GeneralTJ=eK=A#R&Launch id89033[K=K=A#R4Launch date4 May 1989_eK=L=A#R<Launch siteCape CanaveralVK=uL=A#R*TypeAtlantis #04FL=M=E#ZCrewDavid WalkerRonald GrabeNorman ThagardMary CleaveMark Lee\uL=\M=A#R6Landing date8 May 1989YM=M=A#R0Landing siteEdwardsX\M= N=A#R.PayloadB: Magellan<M=IN=' *O External resourcesnG N=N=' http://www.ksc.nasa.gov/shuttle/missions/sts-30/mission-sts-30.html7IN=N=1z*{bN=1O==STS 31CN=1O=5 :u@" STS 319N=jO=# ,Also called STS 61B1 1O=O='  GeneralTjO= =A#R&Launch id85109O= =N=\O=h=A#R6Launch date27 Nov 1985_ =ǀ=A#R<Launch siteCape CanaveralVh==A#R*TypeAtlantis #02rǀ=ց=G#^CrewBrewster ShawBrian O'ConnorMary CleaveSherwood SpringsJerry RossCharles WalkerRodolfo Vela (Mexico)\=2=A#R6Landing date3 Dec 1985Yց==A#R0Landing siteEdwards72==U#zn8F_-PayloadB: Morelos 2C: Optus A2D: Satcom K2H$=_=$ HFlight of 6 days 21 h 4 min 50 s<==' *O External resourcesjC_==' http://www.ksc.nasa.gov/shuttle/missions/61-b/mission-61-b.html8===1O||c====STS 31RD==5 : u@" STS 31R8===# *Also called STS 0E1 =='  GeneralT=>=A#R&Launch id90037\==A#R6Launch date24 Apr 1990_>==A#R<Launch siteCape CanaveralW=P=A#R,TypeDiscovery #10V==E#ZCrewLoren ShriverCharles BodenSteven HawleyBruce Mc CandlessCatherin Sullivan]P=H=A#R8Landing date29 Apr 1990R==A#R"Landing site[H==G#^(~wPayloadB: HST<=1=' *O External resourcesnG==' http://www.ksc.nasa.gov/shuttle/missions/sts-31/mission-sts-31.html71=ֈ=1Mz/{dֈ===STS 32C==5 :u@" STS 329ֈ=R=# ,Also called STS 61C1 =='  GeneralTR=׉=A#R&Launch id86003\=3=A#R6Launch date12 Jan 1986g&׉==A#RLLaunch siteCape Canaveral pad 39AV3==A#R*TypeColumbia #07o==G#^CrewRobert GibsonCharles BoldenRobert CenkerSteven HawleyGeorge NelsonFranklin Chang-DiazBill Nelson]==A#R8Landing date18 Jan 1986Y=\=A#R0Landing siteEdwardsa==G#^4-PayloadB: Satcom K1O)\= =& RFlight of 6 days 1 h 4 min 9 sMSL 2<=H=' *O External resourcesjC ==' http://www.ksc.nasa.gov/shuttle/missions/61-c/mission-61-c.html8H==1؂{|e=.==STS 32RD=.=5 : u@" STS 32R8=f=# *Also called STS 0C1 .=='  GeneralTf==A#R&Launch id90002[=F=A#R4Launch date9 Jan 1990g&==A#RLLaunch siteCape Canaveral pad 39AVF==A#R*TypeColumbia #0===9Q==E#ZCrewDaniel BrandensteinJames WetherbeeBonnie DunbarDavid LowMarsha Ivins]==A#R8Landing date20 Jan 1990Y=[=A#R0Landing siteEdwards`==G#^2%AgPayloadB: Leasat 5a5[==, (j}XUFlight of 10 days 21 h 1 minRetrieval of LDEF<=X=' *O External resourcesnG==' http://www.ksc.nasa.gov/shuttle/missions/sts-32/mission-sts-32.html7X==1j*{3yf=@=y=STS 33C=@=5 :u@" STS 339=y=# ,Also called STS 51L1 @=='  General\y==A#R6Launch date28 Jan 1986_=e=A#R<Launch siteCape CanaveralX==A#R.TypeChallenger #10se=w=G#^CrewFrancis ScobeeMichael SmithGregory JarvisJudith ResnikSharon Mc AuliffeRonald Mc NairEllison OnizukaR==A#R"Landing dateRw==A#R"Landing sitep"==N#lD*OMDQPayloadTDRS 2Spartan 203H==- *6  Explosion after 73s<==' *O External resourcesjC=y=' http://www.ksc.nasa.gov/shuttle/missions/51-l/mission-51-l.html8==1v{{g==Q=STS 33RDy==5 : u@" STS 33R8=-=# *Also called STS 0B1 =^='  GeneralT-==A#R&Launch id89090\^==A#R6Launch date23 Nov 1989_=m=A#R<Launch siteCape CanaveralW==A#R,TypeDiscovery #09Wm=`=E#ZCrewFrederik GregoryDavid GriggsF. 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antenna< >>' *O External resourcesnGp>>' http://www.ksc.nasa.gov/shuttle/missions/sts-37/mission-sts-37.html7>Q>14|r|lQ>>C>STS 38C>>5 :u@" STS 381 Q>>'  GeneralT>%@>A#R&>%@>>Launch id90097\>@>A#R6Launch date15 Nov 1990_%@>@>A#R<Launch siteCape CanaveralV@>6A>A#R*TypeAtlantis #07s.@>A>E#Z\CrewCoveyCulbertsonSpringerMeadeGemar]6A>B>A#R8Landing date20 Nov 1990`A>fB>A#R>Landing siteCape Canaveral\B>B>G#^* 뉂PayloadUSA 0673fB>B>$ DoD mission<B>1C>' *O External resourcesnGB>C>' http://www.ksc.nasa.gov/shuttle/missions/sts-38/mission-sts-38.html71C>C>1l|$|mC>D>H>STS 39CC>D>5 :u@" STS 391 C>JD>'  GeneralTD>D>A#R&Launch id91031\JD>D>A#R6Launch date28 Apr 1991_D>YE>A#R<Launch siteCape CanaveralWD>E>A#R,TypeDiscovery #12qYE>hF>G#^CrewDonald Mc MonagleBlaine HammondCharles VeachGuion BlufordMichael CoatsGregory HarbaughRichard Hieb\E>F>A#R6Landing date6 May 1991`hF>$G>A#R>Landing siteCape Canaveral?F>G>H#`~c竉PayloadB: IBSS (launched and retrieved)C: Mpec (USA 70)R,$G>G>& XFlight of 8 days 7 h 26 minDoD mission<G>9H>' *O External resourcesnGG>H>' http://www.ksc.nasa.gov/shuttle/missions/sts-39/mission-sts-39.html79H>H>17|j}nH>!I>M>STS 40CH>!I>5 :u@" STS 401 H>RI>'  GeneralT!I>I>A#R&Launch id91040[RI>J>A#R4Launch date5 Jun 1991g&I>hJ>A#RLLaunch siteCape Canaveral pad 39BVJ>J>A#R*TypeColumbia #11~hJ>K>G#^CrewJames BagianBryan O'ConnorDrew GaffneySidney GutierrezMargareth Rhea SeddonMillie Hughes-FulfordTamara Jernigan]J>K>A#R8Landing date14 Jun 1991YK>9L>A#R0Landing siteEdwardsQK>L>A#R PayloadnonewK9L>M>, ( Flight of 9 days 3 h 30 minSLS 1 (Space Laboratory Science) mission<L>=M>' *O External resourcesnGM>M>' http://www.ksc.nasa.gov/shuttle/missions/sts-40/mission-sts-40.html7=M>M>1K{|oM>%N>=>STS 41CM>%N>5 :u@" STS 411 M>VN>'  GeneralT%N>N>A#R&Launch id90090[VN>O>A#R4Launch date6 Oct 1990_N>dO>A#R<Launch siteCape CanaveralWO>O>A#R,TypeDiscovery #11SdO>_>E#ZO>_>M>CrewRichard RichardsRobert ParkerBruce MelnickWilliam ShepperdThomas Akers]O>>A#R8Landing date10 Oct 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GeneralT>>A#R&Launch id92049\L>>A#R6Launch date31 Jul 1992_>[>A#R<Launch siteCape CanaveralV>>A#R*TypeAtlantis #12A[>9>G#^CrewShriverAllenNicollierIvinsChang_DiazHoffmanMalerba\>>A#R6Landing date8 Aug 1992`9>>A#R>Landing siteCape Canaveral`>U>G#^2IPayloadB: Eureca 1E>>* $6>WTried to deploy TTS 1<U>>' *O External resourcesnG>D>' http://www.ksc.nasa.gov/shuttle/missions/sts-46/mission-sts-46.html7>{>1{}~u{>>>STS 47CD>>5 :u@" STS 471 {>>'  GeneralT>C>A#R&Launch id92061h'>>A#RNLaunch date12 Sep 1992 at 14:23 UTh'C>>A#RNLaunch siteCape Canaveral, pad 39AW>j>A#R,TypeEndeavour #02Y> >G#^CrewRobert GibsonBrownLeeJerome AptJan DavisMae JemisonMamoru Mohri (Japanese)i(j>s>A#RPLanding date20 Sep 1992 at 14:53 UT` >>A#R>Landing siteCape CanaveralQs>$>A#R Payloadnone:>^>$ ,Spacelab J mission<$>>' *O External resourcesnG^>>' http://www.ksc.nasa.gov/shuttle/missions/sts-47/mission-sts-47.html7>?>1!j}}v?>>U?STS 48C>>5 :u@" STS 481 ?>>'  GeneralT>>A#R&Launch id91063\>c>A#R6Launch date12 Sep 1991_>>A#R<Launch siteCape CanaveralWc>%?A#R,>%?>TypeDiscovery #13t/>?E#Z^CrewCreightonReightlerGemarBrownBuchli]%??A#R8Landing date18 Sep 1991Y?O?A#R0Landing siteEdwards\??G#^*lUcUPayloadB: UARS<O??' *O External resourcesnG?U?' http://www.ksc.nasa.gov/shuttle/missions/sts-48/mission-sts-48.html7??1}~w??,?STS 49CU??5 :u@" STS 491 ??'  GeneralT?T?A#R&Launch id92026[??A#R4Launch date7 May 1992_T??A#R<Launch siteCape CanaveralW?e?A#R,TypeEndeavour #01T??G#^CrewBrandensteinChiltonMelnickThorntonPierre ThuotRichard HiebThomas Aker]e?]?A#R8Landing date16 May 1992Y??A#R0Landing siteEdwardsQ]??A#R Payloadnone{Q??* $ ĉAstronauts went out during 8 h 29 min on 13 May 1992 to repair Intelsat 603<??' *O External resourcesnG?,?' http://www.ksc.nasa.gov/shuttle/missions/sts-49/mission-sts-49.html7?c?1>~}xc?? ?STS 50C,??5 :u@" STS 501 c??'  GeneralT?+?A#R&Launch id92034\??A#R6Launch date25 Jun 1992g&+??A#RLLaunch siteCape Canaveral pad 39AV?D ?A#R*TypeColumbia #12;? ?G#^vCrewRichardsBowersoxDunbarBakerMeadeDelucasTrinh\D ?" ?A#R6Landing date9 Jul 1992` ? ?A#R>Landing siteCape CanaveralQ" ? ?A#R Payloadnone6 ? ?$ $USML 1 mission< ?E ?' * External resourcesnG ? ?' http://www.ksc.nasa.gov/shuttle/missions/sts-50/mission-sts-50.html7E ? ?1y ?- ?@?STS 51C ?- ?5 :u@" STS 511 ?^ ?'  GeneralT- ? ?A#R&Launch id93058\^ ? ?A#R6Launch date12 Sep 1993_ ?m ?A#R<Launch siteCape CanaveralW ? ?A#R,TypeDiscovery #17Sm ??A#R$Crew5 persons] ?t?A#R8Landing date22 Sep 1993`??A#R>Landing siteCape Canaveral?t?a?N#l~* KUd竉PayloadB: ACTSC: Orfeus-Spas (launched and retrieved)<??' *O External resourcesnGa?@?' http://www.ksc.nasa.gov/shuttle/missions/sts-51/mission-sts?@? ?-51.html7?N@?1s}~zN@?@?D?STS 52C@?@?5 :u@" STS 521 N@?@?'  GeneralT@?A?A#R&Launch id92070\@?rA?A#R6Launch date22 Oct 1992g&A?A?A#RLLaunch siteCape Canaveral pad 39BVrA?/B?A#R*TypeColumbia #139A?B?F#\rCrewWetherbeeBakerJerniganVeachShepherdMc Learn\/B? C?A#R6Landing date1 Nov 1992`B?jC?A#R>Landing siteCape Canaveral; C?C?N#lv*ySPayloadB: Lageos 2C: CTA (launched and retrieved)6jC?)D?$ $USMP 1 mission<C?eD?' *O External resourcesnG)D?D?' http://www.ksc.nasa.gov/shuttle/missions/sts-52/mission-sts-52.html7eD? E?1)~~{ E?ME?EI?STS 53CD?ME?5 :u@" STS 531 E?~E?'  GeneralTME?E?A#R&Launch id92086[~E?-F?A#R4Launch date2 Dec 1992_E?F?A#R<Launch siteCape CanaveralW-F?F?A#R,TypeDiscovery #15q,F?TG?E#ZXCrewWalkerCabanaBlufordVossClifford\F?G?A#R6Landing date9 Dec 1992YTG? H?A#R0Landing siteEdwards_G?hH?G#^0b뉂PayloadB: USA 0893 H?H?$ DoD mission<hH?H?' *O External resourcesnGH?EI?' http://www.ksc.nasa.gov/shuttle/missions/sts-53/mission-sts-53.html7H?|I?1~\||I?I?9N?STS 54CEI?I?5 :u@" STS 541 |I?I?'  GeneralTI?DJ?A#R&Launch id93003k*I?J?A#RTLaunch date13 Jan 1993 at 13:59:30 UTf%DJ?K?A#RJLaunch siteCape Canaveral, LC39BWJ?lK?A#R,TypeEndeavour #03OK?L?E#ZCrewJohn CasperDonald Mc MonagleGregory HarbaughMario RuncoSusan HelmsalK?aL?D#X:Landing date19 Jan 1993`L?L?A#R>Landing siteCape Canaveral^aL?M?G#^.OMPayloadB: TDRS 6pFL?M?* $ PARE (Physiological and Anatomical Rodent Experiment) experiment<M?M?' *O External resourcesnGM?9N?' http://www.ksc.nasa.gov/shuttle/missions/sts-54/mission-sts-54.html7M?pN?1\}pN?N?-?STS 55C9N?N?5 :u@" STS 551 pN?N?'  GeneralTN?8O?A#R&Launch id93027h'N?O?A#RNLaunch date26 Apr 1993 at 14:50 UTg&8O??A#RLLaunch siteCape Canaveral paO??9N?d 39ARO?e?A#R"TypeColumbia?6?H#^CrewSteven NagelTerence HenricksJerry RossCharles PrecourtBernard HarrisUlrich Walter (Germany)Hans William Schlegel (Germany)h'e??A#RNLanding date6 May 1993 at 14:30 UTY6??A#R0Landing siteEdwardsQ?H?A#R Payloadnone;??$ .Spacelab D2 mission<H??' *O External resourcesnG?-?' http://www.ksc.nasa.gov/shuttle/missions/sts-55/mission-sts-55.html7?d?1`~τ~~d??և?STS 56C-??5 :u@" STS 561 d?؃?'  GeneralT?,?A#R&Launch id93023[؃??A#R4Launch date8 Apr 1993_,??A#R<Launch siteCape CanaveralW?=?A#R,TypeDiscovery #16q,??E#ZXCrewCameronOswaldFoaleCockrellOchoai(=??A#RPLanding date17 Apr 1993 at 11:37 UT`?w?A#R>Landing siteCape Canaveral~7??G#^nXDPayloadB: Spartan 201-1 (launched and retrieved)7w?,?$ &ATLAS 2 mission<?h?' *O External resourcesnG,?և?' http://www.ksc.nasa.gov/shuttle/missions/sts-56/mission-sts-56.html7h? ?1jτ~~ ?P??STS 57Cև?P?5 :u@" STS 571 ??'  GeneralTP?Ո?A#R&Launch id93037h'?=?A#RNLaunch date21 Jun 1993 at 13:07 UT_Ո??A#R<Launch siteCape CanaveralW=??A#R,TypeEndeavour #04s-?f?F#\ZCrewGrabeDuffyLowSherlockWisoffVossh'?Ί?A#RNLanding date1 Jul 1993 at 12:52 UT`f?.?A#R>Landing siteCape CanaveralQΊ??A#R Payloadnone`4.?ߋ?, (hISpacehab 1 (SH 1) missionRetrieval of Eureca<??' *O External resourcesnGߋ??' http://www.ksc.nasa.gov/shuttle/missions/sts-57/mission-sts-57.html7??1G~??Landing siteCape CanaveralQ@q@A#R PayloadnoneD @@* $4~wReparation of Hubble<q@@' *O External resourcesnG@_@' http://www.ksc.nasa.gov/shuttle/missions/sts-61/mission-sts-61.html7@@1uԃ}@@ @STS 62C_@@5 :u@" STS 621 @ @'  GeneralT@^@A#R&Launch id94015[ @@A#R4Launch date4 Mar 1994_^@@A#R<Launch siteCape CanaveralV@n@A#R*TypeColumbia #16l'@@E#ZNCrewCasperAllenThuotGemanIvins]n@7@A#R8Landing date18 Mar 1994`@@A#R>Landing siteCape CanaveralM 7@@A#RPayloadj@s @% It carried a U.S. Microgravity Payload (USMP 2) and an Office of Aeronautics and Space Technology Second payload (OAST 2). Among the experiments were the Solar Array Module Plasma Interaction Experiment (SAMPIE), the Thermal Energy Storage (TES) experiment, the Experimental Investigation of Spacecraft Glow (EISG) experiment, the Spacecraft Kinetic InfraRed Test (SKIRT) experiment, the Emulsion Chamber Technology (ECT) experiment, and the CRYOgenic Two Phase (CRYOTP) experiment. A new high-speed, Ku-band communication link between mission control and the shuttle enabled transmission of 162 megabytes of data.<@ @' *O External resourcesnGs @ @' http://www.ksc.nasa.gov/shuttle/missions/sts-62/mission-sts-62.html7 @T @1 xT @ @GB@STS 63C @ @5 :u@" STS 631 T @ @'  GeneralT @ @A#R&Launch id95004j) @ @A#RRLaunch date3 Feb 1995 at 05:22:04 UTe$ @ @A#RHLaunch siteCape Canaveral LC39BW @B @A#R,TypeDiscovery #20  @M @G#\CrewJim Wetherbee (commander)Eileen Collins (pilot)Bernard Harris (mission specialist)Mike Foale (mission specialist)Janice Voss (mission specialist)Vladimir Titov (Russian Space Agency)`B @ @A#R>Landing dateCape Canaverali(M @@A#RPLanding site11 Feb 1995 at 11:50 UT @@r#pkӸ~ױBױBױBױBױBױBPayloadSpartan 204 (launched and retrieved)Oderacs 2AOderacs 2BOderacs 2COderacs 2DOderacs 2EOderacs 2F^@A@+ $Spacehab 3 (SH 03) missionThe 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@A@ @ 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. <@A@' *O External resourcesnGA@GB@' http://www.ksc.nasa.gov/shuttle/missions/sts-63/mission-sts-63.html7A@~B@1~B@B@e@STS 64CGB@B@5 :u@" STS 641 ~B@B@'  GeneralTB@FC@A#R&Launch id94059g&B@C@A#RLLaunch date9 Sep 1994 at 22:22 UTh'FC@D@A#RNLaunch siteCape Canaveral, pad 39BWC@lD@A#R,TypeDiscovery #19D@?E@G#\CrewRichard (Dick) Richards, commanderL. Blaine Hammond Jr. (KC5HBS), pilotJerry L. Linenger (KC5HBR)Susan HelmsCarl MeadeMark Lee]lD@E@A#R8Landing date20 Sep 1994R?E@E@A#R"Landing site{4E@iF@G#^hYDPayloadSpartan 201-2 (launched and retrieved)E@.I@) 9Lidar In-Space Technology Experiment (LITE 1) and SAREXAlso on board were 12 Get Away Special (GAS) experiments designed and built by high school and university students, an Orbit Stability Experiment (OSE), and a Robot Operated Materials Processing System (ROMPS).Lidar is essentially radar using an optical wavelength laser instead of microwaves. LITE consists of a Spacelab pallet with a laser transmitter and a receiver telescope. In an interesting historical note, the 96-cm receiver telescope was built in the 1960s as the engineering model for the telescope on the OAO-B satellite, lost in a 1970 launch failure. It was refurbished for the LITE mission.]iF@I@- *  LITE 1 results (made from the June 16 issue of RESEARCHER NEWS, Langley Research Center)hB.I@ M@& According to Dr. M. Patrick McCormick, LITE project scientist and branch head of Langley's Aerosol Research Branch, the LITE mission was 100 percent successful. One mission highlight was the collection of spectacular data on Super Typhoon Melissa. From the cargo bay of Space Shuttle Discovery, LITE passed directly over the eye of the typhoon and profiled the eye-wall clouds from the top to the sea surface below.Unlike passive instruments which measure the amount of heat emitted or light reflected by only the highest layer of multi-layered clouds, LITE is able to penetrate the highest clouds and provide scientists with data about clouds at many levels below. The LITE data also revealed high cirrus clouds which were not seen in the standard meteorological satellite data and are often not expressed in atmospheric models.I@ @% SUsing the three different wavelengths aboard LITE also allowed Browell [Dr. Edward Browell is a senior scientist in Langley's Chemistry and Dynamics Branch] and his team to identify the types of aerosols they were measuring. Browel said, "Remotely, we can detect whether the aerosols we're seeing are biomass burning or whether they're desert aerosols (sands)." Biomass burning generates green-house gases such as carbon dioxide, methane and ozone. Aerosols also affect the Earth's energy budget by scattering sunlight back into space, thereby cooling the Earth. Aerosols can also increase the amount of clouds present by acting as surfaces upon which water vapor can condense. M@ @GB@ M@@% The LITE system obtained a spectacular data set, demonstrating the ability of lidar remote sensing techniques to study the Earth's atmosphere. A future space-based lidar system is being studied. This future system would fly on a satellite in low-earth orbit and provide daily coverage of global cloud characteristics and aerosols created by dust storms, biomass burning and urban pollution.< @@' * External resourcesnG@e@' http://www.ksc.nasa.gov/shuttle/missions/sts-64/mission-sts-64.html7@@1]}\@߂@ @STS 65Ce@߂@5 :u@" STS 651 @@'  GeneralT߂@d@A#R&Launch id94039g&@˃@A#RLLaunch date8 Jul 1994 at 16:43 UTg&d@2@A#RLLaunch siteCape Canaveral pad 39AV˃@@A#R*TypeColumbia #172@{@H#^WCrewRobert D. Cabena (KC5HBV), commanderJames Halsell, pilotRichard HiebCarl WalzLeroy ChiaoDonald ThomasChiaki Naito, cardiolog (first Japanese woman in space)i(@@A#RPLanding date23 Jul 1994 at 10:38 UT`{@D@A#R>Landing siteCape CanaveralM @@A#RPayloadD@a@% WSpacelab 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.<@@' *O External resourcesnGa@ @' http://www.ksc.nasa.gov/shuttle/missions/sts-65/mission-sts-65.html7@B@11B@@@STS 66C @@5 :u@" STS 661 B@@'  GeneralT@ @A#R&Launch id94073g&@q@A#RLLaunch date3 Nov 1994 at 06:59 UT_ @Љ@A#R<Launch siteCape CanaveralVq@&@A#R*TypeAtlantis #13YЉ@@A#R0Crew1 ESA astronaut]&@܊@A#R8Landing date14 Nov 1994Y@5@A#R0Landing siteEdwardst-܊@@G#^Ze竉PayloadSpas 4 (launched and retrieved)2 5@ۍ@) 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.<@@' *O External resourcesnGۍ@@' http://www.ksc.nasa.gov/shuttle/missions/sts-66/mission-sts-66.html7@@1\ @@7@STS 67C@@5 :u@" STS 671 @0@'  GeneralT@@A#R&Launch id95007j)0@ @A#RRLaunch date2 Mar 1995 at 06:38:14 UT@ @@e$@q@A#RHLaunch siteCape Canaveral LC39AW @@A#R,TypeEndeavour #08^q@&@H#^-CrewSteve 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)l+@@A#RVLanding date18 Mar 1995 at 21:47:00 UTY&@@A#R0Landing siteEdwardsM @8@A#RPayload@@+ $ Ultraviolet Astronomy (ASTRO 2) missionNew endurance record: 16 days 15 hours 9 min 46 sSchool 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.8@@$ 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. <@@' *O External resourcesnG@7@' http://www.ksc.nasa.gov/shuttle/missions/sts-67/mission-sts-67.html7@n@1\xn@@P@STS 68C7@@5 :u@" STS 681 n@@'  GeneralT@6@A#R&Launch id94062\@@A#R6Launch date30 Sep 1994_6@@A#R<Launch siteCape CanaveralW@H@A#R,TypeEndeavour #07J @@A#RCrew]H@@A#R8Landing date11 Oct 1994Y@H@A#R0Landing siteEdwardsM @@A#RPayloadH@@' SRL 2 missionIt 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.<@@' *O External resourcesnG@P@' http://www.ksc.nasa.gov/shuttle/missions/sts-68/mission-sts-68.html7@@1䀂@@ASTS 69CP@@5 :u@" STS 691 @ A'  General@ AP@T@`AA#R&Launch id95048g& AAA#RLLaunch date7 Sep 1995 at 15:09 UTe$`A,AA#RHLaunch siteCape Canaveral LC39AWAAA#R,TypeEndeavour #09,AgAF#Z=CrewDavid Walker (Commander)Ken Cockrell (Pilot)James Voss (Payload Commander)James Newman (Mission Specialist)Michael Gernhardt (Mission Specialist)i(AAA#RPLanding date18 Sep 1995 at 11:37 UT`gA0AA#R>Landing siteCape Canaveralq#AAN#lF*ZD*-XPayloadSpartan 201-3WSF 2d=0AA' {WSF 2 and the IEH astronomy experimentAlso on board: a GAS Bridge Assembly with four standard GAS can experiments, plus the CAPL Hitchhiker experiment to test a cooling system for EOS satellites and the Thermal Energy Storage (TES) GAS can experiment to do research on solar dynamic power for the Space Station.<AAA' * External resourcesnGAA' http://www.ksc.nasa.gov/shuttle/missions/sts-69/mission-sts-69.html7AAA1 A)A ASTS 70CA)A5 :u@" STS 701 AZA'  GeneralT)AAA#R&Launch id95035k*ZAAA#RTLaunch date13 Jul 1995 at 13:41:55 UTe$A~AA#RHLaunch siteCape Canaveral LC39BWAAA#R,TypeDiscovery #21~AAF#ZICrewTom Henricks (commander)Kevin Kregel (pilot)Nancy Currie (mission specialist)Dr. Donald Thomas (mission specialist)May Ellen Weber (mission specialist)i(A( AA#RPLanding date22 Jul 1995 at 12:02 UT`A AA#R>Landing siteCape Canaveral^( A AG#^.OMPayloadB: TDRS 7 A A' STS-70 marked another significant milestone with the first flight of the new Block I Space Shuttle main engine. Main Engine #1 - engine 2036 - features improvements that increase the reliability and safety margins of the main engines. SSME's No. 2 and No. 3 are the current design.The Block I engine features improvements such as a new liquid oxidizer turbopump produced through a casting process that eliminates all but six of the 300 welds that exist in the current pump. A new two-duct powerhead improves fluid flows within the engine to decrease pressure and loads. A new single-coil heat exchanger in the powerhead eliminates all seven weld joints inside the engine, reducing wear, maintenance and post-flight inspections.< A& A' *O External resourcesnG A A' http://www.ksc.nasa.gov/shuttle/missions/sts-70/mission-sts-70.html7& A A1K AA%BASTS 71C AA5 :u@" STS 711 A?A'  GeneralTAAA#R&Launch id95030h'?AAA#RNLaunch date27 Jun 1995 at 19:32 UTe$A`AA#RHLaunch siteCape Canaveral LC39AVAAA#R*TypeAtlantis #14J `A @AA#RCrewA @A Ah'At@AA#RNLanding date7 Jul 1995 at 14:54 UT` @A@AA#R>Landing siteCape CanaveralM t@A!AAA#RPayloadZ6@A{AA$ lSpace Life Sciences (SL M) and first trim with Mir<!AAAA' * External resourcesnG{AA%BA' http://www.ksc.nasa.gov/shuttle/missions/sts-71/mission-sts-71.html7AA\BA1 :\BABAFASTS 73C%BABA5 :u@" STS 731 \BABA'  GeneralTBA$CAA#R&Launch id95056h'BACAA#RNLaunch date20 Oct 1995 at 13.53 UTe$$CACAA#RHLaunch siteCape Canaveral LC39BVCAGDAA#R*TypeColumbia #18J CADAA#RCrewh'GDADAA#RNLanding date5 Nov 1995 at 11:45 UT`DAYEAA#R>Landing siteCape CanaveralM DAEAA#RPayload7YEAEA$ &Spacelab USML-2<EAFA' * External resourcesnGEAFA' http://www.ksc.nasa.gov/shuttle/missions/sts-73/mission-sts-73.html7FAFA1@䀂FAGAKASTS 74CFAGA5 :u@" STS 741 FA2GA'  GeneralTGAGAA#R&Launch id95061h'2GAGAA#RNLaunch date12 Nov 1995 at 12:30 UTe$GASHAA#RHLaunch siteCape Canaveral LC39AVGAHAA#R*TypeAtlantis #15J SHAHAA#RCrewi(HA\IAA#RPLanding date20 Nov 1995 at 17:01 UT`HAIAA#R>Landing siteCape Canaverals2\IA/JAA#RdPayload316GK Mir docking modules and supplies7IAfJA$ &2nd Mir docking</JAJA' * External resourcesnGfJAKA' http://www.ksc.nasa.gov/shuttle/missions/sts-74/mission-sts-74.html7JAGKA1:GKAKA>ASTS 72CKAKA5 :u@" STS 721 GKAKA'  GeneralTKALAA#R&Launch id96001h'KAwLAA#RNLaunch date11 Jan 1996 at 09:41 UTe$LALAA#RHLaunch siteCape Canaveral LC39BWwLA3MAA#R,TypeEndeavour #10\LAMAF#\CrewBrian DuffyBrent JettLeroy ChiaoWinston ScottKoichi Wakata (NASDA)Daniel Barryi(3MA>NAA#RPLanding date20 Jan 1996 at 07:42 UT`MANAA#R>Landing siteCape Canaveral`>NANAG#^2mӸ~PayloadSpartan 206^NAOA, (SFU retrieval on 13 January2 spacewalks to test out Space Station tools and equipment.<NAOA' *O External resourcesnGOA>A' http://www.ksc.nasa.OA>AKAgov/shuttle/missions/sts-72/mission-sts-72.html7OAuA1uAAAASTS 75C>AA5 :u@" STS 751 uAA'  GeneralTA=AA#R&Launch id96012h'AAA#RNLaunch date22 Feb 1996 at 11:24 UT_=AAA#R<Launch siteCape CanaveralVAZAA#R*TypeColumbia #19YAAH#^#CrewAndrew Allen (commander)Dr. Scott Horowitz (pilot)Dr. Franklin Chang-Diaz (payload commander)Dr. Jeff Hoffmann (mission specialist)Claude Nicollier (mission specialist, ESA)Maurizio Cheli (mission specialist, ESA)Dr. Umberto Guidoni (mission specialist, ASI)\ZAAA#R6Landing date9 Mar 1996`AoAA#R>Landing siteCape CanaveralM AAA#RPayloadoAA1 0U>W㨛Deployment of the TTS 2 (first was on STS 46) also known as TSS 1R. Third flight of scientific investigations using the US Microgravity Payload (USMP) complement.<AӅA' *O External resourcesnGAAA' http://www.ksc.nasa.gov/shuttle/missions/sts-75/mission-sts-75.html7ӅAxA1xAAQASTS 76CAAA5 :u@" STS 761 xAA'  GeneralTA@AA#R&Launch id96018\AAA#R6Launch date22 Mar 1996_@AAA#R<Launch siteCape CanaveralVAQAA#R*TypeAtlantis #16AfAG#\CrewKevin Chilton (commander)Rick Searfoss (pilot)Ron Sega (payload commander)Linda Godwin (mission specialist)RichClifford (mission specialist)Shannon Lucid (mission specialist, to remain on Mir)RQAAA#R"Landing dateRfA AA#R"Landing siteM AWAA#RPayloadP, AA$ X3rd Shuttle-Mir mission, Spacehab, SAREX<WAA' *O External resourcesnGAQA' http://www.ksc.nasa.gov/shuttle/missions/sts-76/mission-sts-76.html7AA1 \AˋAASTS 77CQAˋA5 :u@" STS 771 AA'  GeneralTˋAPAA#R&Launch id96032h'AAA#RNLaunch date19 May 1996 at 10:30 UTf%PAAA#RJLaunch siteCape Canaveral LC 39BWAuAA#R,TypeEndeavour #11&AAG#\CrewJohn H. Casper: commandantCurtis L. Brown: pilotDaniel W. Bursch: mission specialistMario Runco: mission specialistMarc Garneau (Canadian space agency): mission specialistAndrew S.W. Thomas: mission specialisti(uAAA#RPLanding date29 May 1996 at 11:09 UT`AdAA#R>Landing siteCape Canaveraly2AݏAG#^dnӸ~PayloadSpartan 207 (launched and retrieved)2dAA$ ݏAAQASpacehab 4<ݏAWA' *O External resourcesnGAA' http://www.ksc.nasa.gov/shuttle/missions/sts-77/mission-sts-77.html7WAA1R䂃A?A`ASTS 78CA?A5 :u@" STS 781 ApA'  GeneralT?AAA#R&Launch id96036h'pA,AA#RNLaunch date20 Jun 1996 at 14:49 UTf%AAA#RJLaunch siteCape Canaveral LC 39BV,AAA#R*TypeColumbia #20\ADAH#^)CrewTom Henricks: commander?: pilotSusan J. Helms: mission specialistRichard M. Linnehan: mission specialistCharles E. Brady: mission specialistJean-Jacques Favier (France, CEA/CNES): payload specialistRobert Brent Thirsk (Canadian space agency): payload specialisth'AAA#RNLanding date7 Jul 1996 at 12:36 UT`DA AA#R>Landing siteCape CanaveralM AYAA#RPayload]9 AA$ rSpacelab, life and microgravity Spacehab (LMS), SAREX<YAA' *O External resourcesnGA`A' http://www.ksc.nasa.gov/shuttle/missions/sts-78/mission-sts-78.html7AA19\YAAASTS 79C`AA5 :u@" STS 791 A A'  GeneralTA_AA#R&Launch id96057h' AAA#RNLaunch date16 Sep 1996 at 08:55 UT__A&AA#R<Launch siteCape CanaveralVA|AA#R*TypeAtlantis #17v4&AAB#ThCrewBill Readdy: commander5 other crew members]|AOAA#R8Landing date26 Sep 1996`AAA#R>Landing siteCape CanaveralM OAAA#RPayload<A8A$ 0Mir docking 4, SAREX<AtA' * External resourcesnG8AA' http://www.ksc.nasa.gov/shuttle/missions/sts-79/mission-sts-79.html7tAA1䂃A\AASTS 80CA\A5 :u@" STS 801 AA'  GeneralT\AAA#R&Launch id96065k*ALAA#RTLaunch date19 Nov 1996 at 19:55:50 UTf%AAA#RJLaunch siteCape Canaveral LC 39BVLAAA#R*TypeColumbia #21w6AAA#RlCrewCockrell, Rominger, Jernigan, Jones, Musgraveh'AAA#RNLanding date7 Dec 1996 at 11:49 UT`AGAA#R>Landing siteCape CanaveralJAAB#TPayloadSpas 3 (launched and retrieved)WSF 3 (launched and retrieved)- GAA$ SAREX<ALanding siteCape CanaveralQbBBA#R Payloadnone<BOB$ 0Mir docking 5, SAREX<BB' *O External resourcesnGOBB' http://www.ksc.nasa.gov/shuttle/missions/sts-81/mission-sts-81.html7B0B1<0BsB2 BSTS 82CBsB5 :u@" STS 821 0BB'  GeneralTsBBA#R&Launch id97004h'B`BA#RNLaunch date11 Feb 1997 at 08:55 UT_BBA#R<Launch siteCape CanaveralW`BBA#R,TypeDiscovery #22BBH#^5CrewKen Bowersox (Commander)Scott Horowitz (Pilot)Mark C. Lee (Payload commander)Steve HawleyGregory J. HarbaughSteven L. SmithJoseph R. Tanneri(BaBA#RPLanding date21 Feb 1997 at 08:32 UT`BBA#R>Landing siteCape CanaveraldaB% BG#^:~wPayloadHST instrumentsc9B B* $r~wSecond flight to service the Hubble Space Telescope<% B B' *O External resourcesnG B2 B' http://www.ksc.nasa.gov/shuttle/missions/sts-82/mission-sts-82.html7 Bi B1G"\i B B@BSTS 83C2 B B5 :u@" STS 831 i B B'  GeneralT B1 BA#R&Launch id97013g& B BA#RLLaunch date4 Apr 1997 at 19:20 UTe$1 B BA#RHLaunch siteCape Canaveral LC39AV BS BA#R*TypeColumbia #22< B BH#^CrewJames D. Halsell, Commander Susan L. Still, Pilot Janice E. Voss, Payload Commander Donald A. Thomas, Mission Specialist Michael L. Gernhardt, Mission Specialist Roger Crouch, Payload Specialist Greg Linteris, Payload Specialist h'S B BA#RNLanding date8 Apr 1997 at 18:33 UT` BWBA#R>Landing siteCape CanaveralQ BBA#R Payloadnone^7WB@B' oMicrogravity Science Laboratory (MSL-1), SarexOne of the orbiter's three fuel cells malfunctioned shortly after launch, and flight rules require that all 3 must be operating. The fuel cells combine hydrogen and oxygen to make water and electricity. Therefore a Minimum Duration Flight (MDF) was perforB@B2 Bmed.<BN@B' * External resourcesnG@B@B' http://www.ksc.nasa.gov/shuttle/missions/sts-83/mission-sts-83.html7N@B@B1%<M@B6AB*FBSTS 84C@B6AB5 :u@" STS 841 @BgAB'  GeneralT6ABABA#R&Launch id97023h'gAB#BBA#RNLaunch date15 May 1997 at 08:08 UTe$ABBBA#RHLaunch siteCape Canaveral LC39AV#BBBBA#R*TypeAtlantis #19BBCBH#^OCrewCharles J. Precourt, Commander Eileen M. Collins, Pilot C. Michael FoaleCarlos I. NoriegaEdward T. LuJean-Francois Clervoy (ESA)Elena V. Kondakova (RSA)i(BB6DBA#RPLanding date24 May 1997 at 13:27 UT`CBDBA#R>Landing siteCape CanaveralQ6DBDBA#R PayloadnonemDBEB, (O6th Mir dockingMichael Foale will stay aboard Mir and Jerry Linenger (STS 81) will come back to earth<DBEB' *O External resourcesnGEB*FB' http://www.ksc.nasa.gov/shuttle/missions/sts-84/mission-sts-84.html7EBaFB1MaFBFB:KBSTS 85C*FBFB5 :u@" STS 851 aFBFB'  GeneralTFB)GBA#R&Launch id97039g&FBGBA#RLLaunch date7 Aug 1997 at 14:41 UTe$)GBGBA#RHLaunch siteCape Canaveral LC39AWGBLHBA#R,TypeDiscovery #23GBIBG#\CrewCurt Brown, commanderKent Rominger, pilotJan Davis, payload commanderBob CurbeamStephen RobinsonBjarni Tryggvason (Canada)i(LHBIBA#RPLanding date19 Aug 1997 at 11:08 UT`IBIBA#R>Landing siteCape Canaveralq0IBUJBA#R`PayloadCrista-Spas (launched and retrieved);IBJB$ .Crista-Spas mission<UJBJB' *O External resourcesnGJB:KB' http://www.ksc.nasa.gov/shuttle/missions/sts-85/mission-sts-85.html7JBqKB1YwqKBKBBSTS 86C:KBKB5 :u@" STS 861 qKBKB'  GeneralTKB9LBA#R&Launch id97055h'KBLBA#RNLaunch date26 Sep 1997 at 02:34 UTe$9LBMBA#RHLaunch siteCape Canaveral LC39AVLB\MBA#R*TypeAtlantis #20}4MBNBI#`iCrewJames Wetherbee, Commander Michael Bloomfield, Pilot Vladimar Titov, (RSA) Mission Specialist Scott Parazynski, Mission Specialist Jean-Loup Chretien, (CNES) Mission Specialist Wendy Lawrence, Mission Specialist David Wolf, Mission Specialist (left on Mir)+ Michael Foale (retrieved from Mir)h'\MBAOBA#RNLanding date6 Oct 1997 at 21:55 UT`NBOBA#R>Landing siteCape CanaveralQAOB BA#R PayloadnoneOB B:KB?OBKB$ 67th Mir docking mission< BB' *O External resourcesnGKBB' http://www.ksc.nasa.gov/shuttle/missions/sts-86/mission-sts-86.html7B,B1,BoBNBSTS 87CBoB5 :u@" STS 871 ,BB'  GeneralToBBA#R&Launch id97073\BPBA#R6Launch date19 Nov 1997e$BBA#RHLaunch siteCape Canaveral LC39AVPB BA#R*TypeColumbia #24%B0BG#\CrewKevin R. Kregel, Commander Steven W. Lindsey, Pilot Winston E. Scott, Mission Specialist Kalpana Chawla, Mission Specialist Takao Doi, (NASDA) Mission Specialist Leonid K. Kadenyuk, (NSAU) Payload Specialist \ BBA#R6Landing date5 Dec 1997`0BBA#R>Landing siteCape Canaveral{4BgBG#^h[DPayloadSpartan 201-4 (launched and retrieved)=BB$ 2Microgravity (USMP 4)<gBB' *O External resourcesnGBNB' http://www.ksc.nasa.gov/shuttle/missions/sts-87/mission-sts-87.html7BB1+wBȆB‹BSTS 89CNBȆB5 :u@" STS 891 BB'  GeneralTȆBMBA#R&Launch id98003h'BBA#RNLaunch date22 Jan 1998 at 02:48 UTf%MBBA#RJLaunch siteCape Canaveral LC 39AWBrBA#R,TypeEndeavour #12[B͉BH#^'CrewTerrence W. Wilcutt, Commander Joe F. Edwards, Jr., Pilot Bonnie J. Dunbar, Payload Commander Michael P. Anderson, Mission Specialist James F. Reilly, Mission Specialist Salizhan Shakirovich Sharipov, Mission Specialist Andrew S. W. Thomas, Mission Specialist i(rB6BA#RPLanding date31 Jan 1998 at 22:35 UT`͉BBA#R>Landing siteCape CanaveralM 6BBA#RPayload5BB$ "Mir Docking 8<BTB' *O External resourcesnGB‹B' http://www.ksc.nasa.gov/shuttle/missions/sts-89/mission-sts-89.html7TBB1BLanding siteCape CanaveralB B‹BQB]BA#R Payloadnonea= BB$ zThe Neurolab mission will carry out life science studies.7]BB1e\B8BlBSTS 94CB8B5 :u@" STS 941 BiB'  GeneralT8BBA#R&Launch id97032g&iB$BA#RLLaunch date1 Jul 1997 at 18:02 UTe$BBA#RHLaunch siteCape Canaveral LC39AV$BBA#R*TypeColumbia #23;BBH#^CrewJames D. Halsell, Commander Susan L. Still, Pilot Donald A. Thomas, Mission Specialist Greg Linteris, Payload SpecialistJanice E. Voss, Payload Commander Michael L. Gernhardt, Mission Specialist Roger Crouch, Payload Specialist i(BBA#RPLanding date17 Jul 1997 at 10:46 UT`BBA#R>Landing siteCape CanaveralQB4BA#R PayloadnonebBB, (QRe-run of the aborted STS 83 missionMicrogravity Science Laboratory replay (MSL-1R), Sarex<4BB' *O External resourcesnGBlB' http://www.ksc.nasa.gov/shuttle/missions/sts-94/mission-sts-94.html7BB1 vB*B CTaurusClBB5 : " TaurusDB*B* $4 㭄؉by Jean-Jacques Serrac7BB, &o_ 0In 1989 OSC was selected by DARPA to design the Standard Small Launch Vehicle (SSLV). This solid 4-stage rocket called Taurus is made of the first stage of the MX and the 3 stages of Pegasus. The base stage, called stage-0, is a Thiokol TU 903 of 8.4 m long, 2.34 m diameter and 48 tons. It delivers the 3 Pegasus stages at 38000 m altitude at 2030 m/s. In the future (standard type), the stage-0 will be a Thiokol Castor 120 which is a MX motor modified to provide a weaker acceleration (6.5 G max). Taurus is 27.5 m in height and can launch 1.36 tons in LEO.9*BB' $ Taurus versionsUBBA#R(PrototypeTaurusw0BBG#^`"_ 0HStandard Type (with Castor-120)Taurus-120i(BBA#RP4stretched standard typeTaurus-120XLz9BuBA#RrRstretched standard type with strap-onsTaurus-120XL/S9BB' $ Taurus launchesfuBB# 4\N\   $& <> \ l |~ #Launch idPayloadLaunch DateSiteTypeStatus/Comment (orbit in perigee x apogee x inclination x period)<fBPB#|4\N\ *j뉂j뉂PR194017A: USA 101B: USA 10213 Mar 1994 at 22:32 UTV 576E540 km x 560 km x 105jBB# 4\N\ FT:s:;s:H ΀ހ298007A: GFO 1B: Orbcomm FM 3C: Orbcomm FM 4D: Celestis 210 Feb 1998 at 13:20 UTV 576E120775 km x 108&PB C# B ClBFBRC1JRCC`ACThor (launch vehicle)A CC5 :" ThorDRCC* $4 㭄؉by Jean-Jacques SerraGCfCH ` =v퉂Gi4#*≂p㉂OriginsThor AbleThor AblestarThor AgenaThor Delta[/CC, (^O Thor with solid top stage (Altair, Burner)ofClC< F 㰭=H㰭=HOrigin: first generation of American Intermediate Range Ballistic MissilesUntil 1953 the USAF had stressed on aerodynamic missiles (while the Army was developping the Jupiter) because they believed long distance ballistic missiles would not appear before ten years. The construction of Thor wasn't awarded to Douglas Aircraft before December 1955. The program was given a very high priority and the first missile was delivered to the USAF in October 1956.The MB-1 propulsion system was made of a Rocketdyne LR79 (liquid oxygen and kerosene) engine with 670 kN derived from Jupiter and Atlas' booster. An LR101 vernier rocket on each side of the missile' base controled the roll and the final ajustement of the speed after the main engine shutdown. The missile used Atlas' Reentry Vehicle, measured 2.44 m in diameter and 19.8 m in height, and weighed over 46 tons. CxC3 4pp㉂The first four tests carried out from 25 January 1957 on were failures. The first successful launch occured on 20 September and was commissioned in 1959.Thor's propulsion system quickly evolved to an MB-3 version used by IRBMs and space launchers, especially by USAF's Thor SLV-2 and NASA's Thor Delta launchers. In the seventies the MB-3 motor was used by the Japanese N-1, N-2 and H-1 launch vehicles. An improvement program conducted between 1957 and 1959 named X-1 leaded to an H-1 version designed for Saturn-1. Later on H-1 was modified for the propulsion of Thor Deltas (39xx series) and became RS-27. The latest version RS-27A intended to Delta-2 launchers is optimized for greater performance at high altitude.&lCC# DxCC* $4 Thor propulsion systemkC C#  N   DesignationYear of first launchMain engine Thrust (kN)Main engine SI (sec.)ApplicationC C#>&02MB-11957600250IRBM: C_ C#t)FPRMB-31958670, 735, 755 (1)252IRBM, launchers6 C- C#l)>)\^RS-271973920-1030 (2)263-295 (2)Delta9_ C C#r )@)^`RS-27A1991890-1055 (2)255-305 (2)Delta-20- C.CB R$_ 0_ 0_ 0Notes: (1) Blk 1, 2 and 3; (2) values given at sea level in vacuumIn 1963 Thor's thrust became insufficient to carry out its missions. The solution (innovative at that time) found was to enhance it with 3 solid fuel strap on Thiokol Castor boosters. This resulted in TAT: Thrust Augmented Thor. Those boosters were used grouped by 3 then 6 and up to 9. After 1975 when the only Thor first stage used was the Delta the Castor-2 boosters were replaced by the 1 m-diameter Castor-4.& C`AC+ $Ƿ-HThe burn duration of Thor (160 seconds) was also enhanced by lenghtening its tanks. This gave birth to the LTT (Long Tank Thor) for which the burning time reached ab.C`AC Cout 220 seconds, used from 1966 wih Agena stages and from 1968 with Delta stages. The first stage was streched again in early 70' giving ELTT (Extended Long Tank Thor); the burning time wasn't much modified but the thrust was increased. The Delta-2 version, used since 1989, was lengthened in order to obtain a 265 seconds burning time.1.CAC1AC{BC`AC{BC[  +=v퉂Gi4#*≂p㉂扂Thor[launch vehicle index]OriginsThor AbleThor AblestarThor AgenaThor DeltaThor with solid top stage (Altair, Burner): ACBC1BC`CC͉CThor AbleF{BCBC5 :$" Thor Ablee4BC`CC1 2h 㭄؉>ɉby Jean-Jacques Serralisting by Gunter KrebsBC_FC+ $ Thor used with Vanguard top stagesIn 1958 the only top stages available for space launches were those of Vanguard. The second stage was 8.5 m long and 0.9 m in diameter. It was equipped with an adjustable Aerojet AJ10 motor (nitric acid/UDMH) capable of a 33 kN thrust during 120 seconds. The spin-stabilized third stage was equipped with a solid fuel motor of 14 kN and 30 second burn duration. The Thor Able rocket was 26.9 m high and weighed over 50 tons.Thor Able was tested in April and May 1958 with the intercontinental launch of Reentry vehicles containing a mouse. But the first 3 space launches carrying Pioneer probes to the Moon between August and November 1958 ended as 2 failures and 1 partial success.`CC-GC1 0;jThe launcher was used until 1961 to launch a scientific satellite (Explorer) a interplanetary probe (Pioneer) and a meteorological satellite (Tiros).<_FCiGC' * Thor Able launchesBx-GCHC#dP]2   :< RT r  # and serialLaunch idPayloadLaunch dateTypeStatus (orbit in perigee x apogee x inc. x period) eiGCIC#FP]2 JLfh~1, 116n/aARTV 1 (suborbital)23 Apr 1958DM18 AbleFailure: Thor exploded after 146sBHCJC#@P]2 JLfh~2, 118n/aARTV 2 (suborbital)10 Jul 1958DM18 AbleBICKC#@P]2 JLfh~3, 119n/aARTV 3 (suborbital)23 Jul 1958DM18 AblecJCLC#FP]2 DF`b|4, 127n/aPioneer 0 (Moon)17 Aug 1958DM18 Able 1Failure: Thor exploded after 17s4yKCNC#FP]2 DF`b|5, 130n/aPioneer 1 (Moon)11 Oct 1958DM18 Able 1Partial failure: 3rd stage produced unsufficient thrust[LC'OC#FP]2 DF`b|6, 129n/aPioneer 2 (Moon)08 Nov 1958DM18 Able 1Failure: 3rd stage failed;zNCnC#RP]2 NPln7, 128n/aPGRTV 1 'OCnC{BC(suborbital)23 Jan 1959DM18 Able 2Partial failure: 1st stage shut down at wrong timeE'OCkC#@P]2 LNhj8, 131n/aPGRTV 2 (suborbital)28 Feb 1959DM18 Able 2EnChC#@P]2 LNhj9, 132n/aPGRTV 3 (suborbital)21 Mar 1959DM18 Able 2EkCeC#@P]2 "NPhj10, 133n/aPGRTV 4 (suborbital)8 Mar 1959DM18 Able 2FhCcC#@P]2 "NPjl11, 135n/aPGRTV 5 (suborbital)20 May 1959DM18 Able 2FeCaC#@P]2 "NPjl12, 137n/aPGRTV 6 (suborbital)11 Jun 1959DM18 Able 2AcC`C#LP]2$&`DF`b|13, 13459004Explorer 0607 Aug 1959DM18 Able 3VaCqC#FP]2 ":<VXr14, 136n/aTransit 1A17 Sep 1959DM18 Able 2Failure: 3rd stage failed Q`CzC#@P]2$&<>XZt15, 21960001Pioneer 511 Mar 1960DM18 Able 4Probe to solar orbit>qCvC#L|P]2$&:ܗ+>@Z\v16, 14860002Tiros 0101 Apr 1960DM18 Able 2W-zC͉C* $Z$Notes: all launches from Cape Canaveral> vC C1> CCDThor AblestarJ͉CUC5 :," Thor Ablestare4 CC1 2h 㭄؉>ɉby Jean-Jacques Serralisting by Gunter KrebsUCC2 2I|ۉdThe Ablestar stage was developped for the US Navy by Space General Co. It was 5.3 m long and 1.63 m in diameter, equipped with an adjustable Aerojet AJ10-104 motor (nitric acid/UDMH). This engine could be reignited and provided a 35 kN thrust during about 300 seconds. Thor Ablestar was 24.2 m high for about 54 tons.Thor Ablestar was used to launch navigation satellites (Transit) so as numerous technologic and scientific spacecrafts (Solrad) for the US Navy. Some satellites were launched together with NASA. Thor Ablestar was used during 5 years and achieved the first in-orbit reignition in April 1960 and the first double, triple and sextuple -satellite launch.@CЍC' 2 Thor Ablestar launchesbC2C#P]$   :< RT r   # and serialLaunch idPayloadLaunch dateSiteTypeStatus (orbit in perigee x apogee x inc. x period)XЍC\C#\P]$"$<>X^`~1, 2572C\C͉C60003Transit 1B13 Apr 1960CDM21 AbleStar373 x 748 x 51.3 x 95.8"O2C~C#vP]$"*$d؉㬎YXZtz|2, 28160007Transit 2ASolrad 0122 Jun 1960CDM21 AbleStar-a\CC#hP]$ 8:TZ\z 3, 262n/aCourier 1A18 Aug 1960CDM21 AbleStarFailure: Thor failed after 134sC~CC#hP]$"$D@B\bd4, 29360013Courier 1B04 Oct 1960CDM21 AbleStar8kCC#jP]$ JLfln 5, 283n/aTransit 3ASolrad 230 Nov 1960CDM21 AbleStarFailure: Thor shud down too early^CPC#lP]$"$HJdjl 6, 31361007Transit 3BLOFTI22 Feb 1961CDM21 AbleStarPartial failure: satellites failed to separate188 x 822 x 28.4 x 96.2cCC#P]$"*$㺶؉㮎YXZtz| 7, 31561015Transit 4ASolrad 0329 Jun 1961CDM21 AbleStarPartial failure: Injun 1 and Solrad 3 failed to separateKPCC#vP]$"*$㻶؉zPWPRlrt8, 30561031Transit 4BTraac15 Nov 1961CDM21 AbleStarvCGC#pKP]$ fh 9, 311n/aLofti 2Secor 1Solrad 4Surcal 124 Jan 1962CDM21 AbleStarFailure: AbleStar produced unsufficient thrustSurcal 1 was fixed to AbleStar-aCtC#hP]$ "46PVXv 10, 314n/aAnna 1A10 May 1962CDM21 AbleStarFailure: AbleStar failed to ignite AGCC#hP]$$&WR<>X^`~11, 31962060Anna 1B31 Oct 1962CDM21 AbleStarJtCC#jP]$$&ANPjpr12, 37563038Transit 5BN15E128 Sep 1963VDM21 AbleStarJCC#jP]$$&BNPjpr13, 38563049Transit 5BN25E305 Dec 1963VDM21 AbleStar(\CC#hP]$ ">@Z`b 14, 379n/aTransit 5BN321 Apr 1964VDM21 AbleStarFailure: AbleStar failedKC.D#^P]C.D͉C$$&΀15, 25064063Transit-O 1 (OPS 5798, NNS 30010)Calsphere 1 & 206 Oct 1964VDM21 AbleStar1035 x 1080 x 89.9 x 106.6;tCiD#^P]$$&rt16, 42364083Transit-O 2 (OPS 6582 NNS 30020)5E513 Dec 1964VDM21 AbleStar1027 x 1086 x 90 x 106.30c.DD#jP]$$&l^{€17, 44065017Transit-O 3 (OPS 7087 NNS 30030)Secor 0211 Mar 1965VDM21 AbleStar7qiDD#\P]$$&ln18, 44765048Transit-O 4 (OPS 8480, NNS 30040)24 Jun 1965VDM21 AbleStar1025 x 1114 x 90 x 106.9_D/D#b+P]$$&Ѐր؀19, 45565065Transit-O 5 (OPS 8464, NNS 30050)Surcal (x3?)Dodecapole 2Tempsat 113 Aug 1965VDM21 AbleStar1089 x 1194 x 90 x 108.2aDD* $$Notes: in the launcher date & site column C stands for Cape Canaveral and V for Vandenberg.; /DD1mDDGHThor AgenaGD<D5 :&" Thor AgenaDDD* $4 㭄؉by Jean-Jacques Serra#<D D< FǷ-HǷ-HǷ-HǷ-HThe Agena stage was developped by Lockheed for the USAF. The first Thor Agena (with Discoverer1) was 23.2 m in height and weighed 48.5 tons. This version was Agena-A equipped with a Bell 8096 motor of 67 kN during 2 minutes. It couldn't be re-ignited on the contrary of the 1960 Agena-B. The Agena-D version featured a more powerful engine with 71 kN delivered during 4 minutes. All those rockets had the same diameter (1.52 m) and a variable length depending on the payload.\Dk Dl Ƿ-H  = QdI䵟  duSAgena was used from 1959 to 1987 becoming the most used American top-stage with 350 launches mainly with military payloads:- reconnaissance satellites (Discoverer, Keyhole) sometimes orbited with military payloads (Ferret) or civilian payloads (Oscar).- ELINT satellites: large ones were launched as unique payload and small size ones together with reconnaissance satellites.But Thor Agena also launched:- scientific satellites (Solrad, Starad, STP), geodesy satellites (Secor, Starflash, Topo) and technological spacecrafts (TRS, GGSE, LOFTI, Surcal, LCS, Timation, SERT).[ D DK f "`MV.Nf8Sȉ- satellites for NASA (Alouette, Explorer 31, Echo 2, Pageos, OGO, Nimbus)=k DN D' , Thor Agena launchesu DD$# 4]y^]AO  &(>@^`pʀ#Launch idPayloadLaunch dateTypePerigee (km)Apogee (km)inc. (deg)period (min)CEN D6@D#́ 4]y^]AO 68RT`blv159002Discoverer-1D6@DD28 Feb 1959T AA16396889.796EGD{AD#́ 4]y^]AO 68RT`blv259003Discoverer-213 Apr 1959T AA23934689.990.4D@6@DBD#؁ 4]y^]AO 24NP\^tx|3n/aDiscoverer-303 Jun 1959T AAfailurePL{ADDD#؁ 4]y^]AO JLfhtv4n/aDiscoverer-4 (KH-1 9001)25 Jun 1959T AAfailureOQBD^ED#́ 4]y^]AO NPjlxz559005Discoverer-5 (KH-1 9002)13 Aug 1959T AA2177398094.2OQDDFD#́ 4]y^]AO NPjlxz659006Discoverer-6 (KH-1 9003)19 Aug 1959T AA2128488495.3QS^EDGD#́ 4]y^]AO NPjlxz759010Discoverer-7 (KH-1 9004)07 Nov 1959T AA15984781.694.7TVFDRID#́ 4]y^]AO NPjlxz859011Discoverer-8 (KH-1 9005)20 Nov 1959T AA1871 67980.7103.7PLGDJD#؁ 4]y^]AO JLfhtv9n/aDiscoverer-9 (KH-1 9006)04 Feb 1960T AAfailureRNRIDKD#؁ 4]y^]AO  NPjlxz10n/aDiscoverer-10 (KH-1 9007)19 Feb 1960T AAfailureSUJDGMD#́ 4]y^]AO  RTnp|~1160004Discoverer-11 (KH-1 9008)15 Apr 1960T AA17058980.192.2FBKDND#؁ 4]y^]AO  68RT`bx|12n/aDiscoverer-1229 Jun 1960T AAfailureEGGMDOD#́ 4]y^]AO  :<VXdfpz1360008Discoverer-1310 Aug 1960T AA25970182.994SUND1D#́ 4]yOD1DD^]AO  RTnp|~1460010Discoverer-14 (KH-1 9009)18 Aug 1960T AA18680579.794.6SUODD#́ 4]y^]AO  RTnp|~1560012Discoverer-15 (KH-1 9010)13 Sep 1960T AA20972480.994.2RN1DփD#؁ 4]y^]AO  NPjlxz16n/aDiscoverer-16 (KH-1 9011)26 Oct 1960T ABfailureSUD)D#́ 4]y^]AO  RTnp|~1760015Discoverer-17 (KH-1 9012)12 Nov 1960T AB18799181.796.5SUփD|D#́ 4]y^]AO  RTnp|~1860018Discoverer-18 (KH-1 9013)07 Dec 1960T AB23366181.593.7EG)DD#́ 4]y^]AO  :<VXdfpz1960019Discoverer-1920 Dec 1960T AB20652083.493TV|DD#́ 4]y^]AO  TVpr~2061005Discoverer-20 (KH-5 9014A)17 Feb 1961T AB28878680.995.4IKD^D#́ 4]y^]AO  :<VXdfp~2161006Discoverer-2118 Feb 1961T AB2401 06980.797.9RNDD#؁ 4]y^]AO  NPjlxz22n/aDiscoverer-22 (KH-2 9015)30 Mar 1961T ABfailureTV^DD#́ 4]y^]AO  TVpr~2361011Discoverer-23 (KH-5 9016A)08 Apr 1961T AB29565182.394.1SODWD#؁ 4]y^]AO  PRlnz|24n/aDiscoverer-24 (KH-5 9018A)08 Jun 1961T ABfailureSUDD#́ 4]y^]AO  RTnp|~2561014Discoverer-25 (KH-2 9017)16 Jun 1961T AB22240982.190.9QSWDD#́ 4]y^]AO DDD RTnp|~2661016Discoverer-26 (KH-2 9019)08 Jul 1961T AB23580982.995SODZD#؁ 4]y^]AO  PRlnz|27n/aDiscoverer-27 (KH-5 9025A)21 Jul 1961T ABfailureRNDD#؁ 4]y^]AO  NPjlxz28n/aDiscoverer-28 (KH-2 9028)03 Aug 1961T ABfailureSUZDD#́ 4]y^]AO  RTnp|~2961023Discoverer-29 (KH-3 9023)30 Aug 1961T AB22555582.191.5SUDRD#́ 4]y^]AO  RTnp|~3061024Discoverer-30 (KH-3 9022)12 Sep 1961T AB23554682.792.4SUDD#́ 4]y^]AO  RTnp|~3161026Discoverer-31 (KH-3 9024)17 Sep 1961T AB23539682.790.9SURDD#́ 4]y^]AO  RTnp|~3261027Discoverer-32 (KH-3 9025)13 Oct 1961T AB23439581.790.8RNDJD#؁ 4]y^]AO  NPjlxz33n/aDiscoverer-33 (KH-3 9026)23 Oct 1961T ABfailureUWDD#́ 4]y^]AO  RTnp|~3461029Discoverer-34 (KH-3 9027)05 Nov 1961T AB2271 01182.597.1SUJDD#́ 4]y^]AO  RTnp|~3561030Discoverer-35 (KH-3 9028)15 Nov 1961T AB23827881.689.7kfD]D#ځ 4]y^]AO   쉂tv3661034A: Discoverer-36 (KH-3 9029)B: Oscar 0112 Dec 1961T AB23845081.291.8RNDD#؁ 4]y^]AO  NPjlxz37n/aDiscoverer-37 (KH-3 9030)13 Jan 1962T ABfailure79]DE#́r 4]y^]AODED  "$>@LNXbj3862004?21 Feb 1962T AB1673748290QSDCE#́ 4]y^]AO  RTnp|~3962005Discoverer-38 (KH-4 9031)27 Feb 1962T AB20834182.290JLEE#́ 4]y^]AO  @B\^jlv4062011KH-4 #2 (9032)18 Apr 1962T AB19929773.590.9JLCEE#́ 4]y^]AO  @B\^jlv4162017KH-4 #3 (9033)29 Apr 1962T AB17736473.191.1IKE E#́ 4]y^]AO  BD^`lnx4262018KH-5 #5 (9034A)15 May 1962T AB30563482.394JLEjE#́ 4]y^]AO  @B\^jlv4362021KH-4 #4 (9035)30 May 1962T AB19931974.189.7j_ EE #恾 4]y^]AO  ,쉂fh4462022A: KH-4 #5 (9036)B: Oscar 0202 Jun 1962T AB21138574.390.5CEjE E#́ 4]y^]AO  24NP\^hr~4562024ELINT 1#118 Jun 1962T AB37041182.192.4JLEa E#́ 4]y^]AO  @B\^jlv4662026KH-4 #6 (9037)23 Jun 1962T AB21329375.189.6HJ E E#́ 4]y^]AO  @B\^jlv4762027KH-4 #7 (9038)28 Jun 1962T AD2116897693.6JLa E E#́ 4]y^]AO  @B\^jlv4862031KH-4 #8 (9039)21 Jul 1962T AB20838170.990.4JL E=E#́ 4]y^]AO  @B\^jlv4962032KH-4 #9 (9040)28 Jul 1962T AB22229371.190.6IK E@E#́ 4]y^]AO  >@Z\h=E@EDjt~5062034KH-4 #10 (9041)02 Aug 1962T AD20441882.290.8IK=EAE#́ 4]y^]AO  >@Z\hjt~5162042KH-4 #11 (9044)29 Aug 1962T AD18740065.290.4KM@E&CE#́ 4]y^]AO  BD^`lnx5262044KH-5 #6 (9042A)01 Sep 1962T AB33363782.894.4QSAEwDE#́ 4]y^]AO  NPjlxz5362046KH-4 #12 (9043) + TRS-117 Sep 1962T AB20466881.893.3WM&CEEE #䁚 4]y^]AO  *H6<>XZfhr5462049Alouette 129 Sep 1962T AB9961 03280.5105.5IKwDEGE#́ 4]y^]AO  >@Z\hjt~5562050KH-4 #13 (9045)29 Sep 1962T AD20337665.490.3GIEE^HE#́ 4]y^]AO  BD^`lnx5662053KH-5 #7 (9046A)09 Oct 1962T AB2134278291EGGEIE#́ 4]y^]AO  02LNZ\ft5762058Starad 126 Oct 1962T AD1985 57071.4147.9GI^HEJE#́ 4]y^]AO  >@Z\hjt~5862063KH-4 #14 (9047)05 Nov 1962T AB2084097590.7IKIE3LE#́ 4]y^]AO  >@Z\hjt~5962065KH-4 #15 (9048)24 Nov 1962T AB20433765.189.9IKJE|ME#́ 4]y^]AO  >@Z\hjt~6062066KH-4 #16 (9049)04 Dec 1962T AD19427365.189.23LEOE# 4]y^]AO  (à΀ڀ܀6162067A: Black SphereB: Injun 3C: Surcal 1D: Surcal 1AE: Calsphere 1A13 Dec 1962T AD2352 78570.4116.3GI|MEqE#́ 4]y^]AO  >@Z\hjtOEqED~6262069KH-4 #17 (9050)14 Dec 1962T AD1993927190.5IKOEE#́ 4]y^]AO  >@Z\hjt~6363002KH-4 #18 (9051)07 Jan 1963T AD20539982.290.5FHqEE#́ 4]y^]AO  24NPbdnx6463003ELINT 1#216 Jan 1963T AB?D?45953381.994.7JFEJE#؁ 4]y^]AO  :<VXhj65n/aKH-4 #19 (9052)28 Feb 1963TAT ADfailureKGEE#؁ 4]y^]AO  <>XZjl66n/aKH-6 #1 (8001)18 Mar 1963TAT ADfailureIKJEކE#́ 4]y^]AO  >@Z\hjt~6763007KH-4 #20 (9053)01 Apr 1963T AD20140875.490.7JFE(E#؁ 4]y^]AO  >@Z\hj68n/aKH-5 #8 (9055A)26 Apr 1963T ADfailureLNކEtE#́ 4]y^]AO  @B\^npz6963016KH-6 #2 (8002)18 May 1963TAT AD15349774.591.1KM(EE#́ 4]y^]AO  >@Z\lnx7063019KH-4 #21 (9054)13 Jun 1963TAT AD19241981.990.7tEhE# 4]y^]AO  * 4ƀȀ7163021A: classifiedB: LOFTI 2AC: Solrad 06AD: Radose 112E: FTV 1292F: Surcal 1B15 Jun 1963T AD18589069.993Y[EE#́ 4]y^]AO  Z\vx7263025KH-4 #22 (9056)+ HitchHiker-127 Jun 1963TAT AD19639681.690.5CEhEE#́ 4]y^]AO  24NP\^hr~7363027ELINT 1#329 Jun 1963T AB48453682.394.8IKEYE#́ 4]y^]AO  >@Z\hjt~EYED7463029KH-4 #23 (9057)18 Jul 1963T AD19438782.990.4JLEE#́ 4]y^]AO  @B\^npz7563032KH-6 #3 (8003)31 Jul 1963TAT AD1574117590.4KMYEE#́ 4]y^]AO  BD^`pr|7663034KH-4A #1 (1001)24 Aug 1963TAT AD2253227589.4TVEBE#́ 4]y^]AO  TVpr~7763035KH-5 #9 (9058A) + Ferret29 Aug 1963T AD29232481.990.8MOEE#́ 4]y^]AO  BD^`pr|7863037KH-4A #2 (1002)24 Sep 1963TAT AD16144174.990.6UWBEE#́ 4]y^]AO  RTnp7963042KH-5 #10 (9059A) + Ferret29 Oct 1963TAT AD27934589.990.8HDE,E#؁ 4]y^]AO  :<VXdf|80n/aKH-4 #24 (9060)09 Nov 1963T ADfailureGIEsE#́ 4]y^]AO  >@Z\hjt~8163048KH-4 #25 (9061)27 Nov 1963T AD1753867090.2RT,EE#́ 4]y^]AO  PRln~8263055KH-4 #26 (9062) + Ferret21 Dec 1963TAT AD17635564.990sEE9#@ 4]y^]AO  $*PhA $ 4Ȁʀր؀8364001A: US Navy classifiedB: GGSE 1C: Secor 01BD: Solrad 07A11 Jan 1964T AD90593569.9103.5>@EE#́ 4]y^]AO  &(BDPR\fr8464002(2)19 Jan 1964T AD81082599.1101.3UKEE #䁖 4]y^]AO  *MV.46PR^`n|8564004Echo 225 Jan 1964T AB1 0921 31681.5108.9KMEkF#́ 4]y^]AO  BD^`pr|EkFD8664008KH-4A #3 (1004)15 Feb 1964TAT AD1794447590.9ACEF#́ 4]y^]AO  24NP\^hrz8764011ELINT 1#428 Feb 1964T AD4795208294.7LHkFF#؁ 4]y^]AO  >@Z\ln88n/aKH-4A #4 (1003)24 Mar 1964TAT ADfailureMOFEF#́ 4]y^]AO  BD^`pr|8964022KH-4A #5 (1005)27 Apr 1964TAT AD17844679.990.8RTFF#́ 4]y^]AO  (*PRln~9064026 or 027KH-4A #6 (1006)05 Jun 1964TAT AD1494298090.3XZEFF#́ 4]y^]AO  ^`z|9164030KH-5 #11 (9065A) + Starflash-1A13 Jun 1964T AD35036411591.7>@F-F#́ 4]y^]AO  &(BDPR\fr9264031(2)18 Jun 1964T AD82884299.8101.6KMFx F#́ 4]y^]AO  BD^`pr|9364032KH-4A #7 (1007)19 Jun 1964TAT AD1764628590.9CE-F F#́ 4]y^]AO  24NP\^hr~9464035ELINT 1#503 Jul 1964T AD50152982.194.9IKx F F#́ 4]y^]AO  BD^`pr|9564037KH-4A #8 (1008)10 Jul 1964TAT AD1804618591KM FO F#́ 4]y^]AO  BD^`pr|9664043KH-4A #9 (1009)05 Aug 1964TAT AD1824368090.7XZ FF#́ 4]y^]AO  ^`z|9764048KH-5 #11 (9065A) + Starflash-1B21 Aug 1964T AD34936311591.6RHO F @F #䁐 4]y^]AO  *Q;C8:TVbdnx9864052Nimbus 128 Aug 1964T AB42993798.498.7F @FDJLFVAF#́ 4]y^]AO  @B\^npz9964056KH-4A #10 (1010)14 Sep 1964TAT AD2384668590.9KM @FBF#́ 4]y^]AO BD^`pr|10064061KH-4A #11 (1011)05 Oct 1964TAT AD1824407890.7KMVAFCF#́ 4]y^]AO BD^`pr|10164067KH-4A #12 (1012)17 Oct 1964TAT AD1894167590.6MOBF9EF#́ 4]y^]AO BD^`pr|10264071KH-4A #13 (1013)02 Nov 1964TAT AD18044879.990.7BDCF{FF#́ 4]y^]AO 46PR^`jt|10364072ELINT 1#604 Nov 1964T AD5125268295.1KM9EFGF#́ 4]y^]AO BD^`pr|10464075KH-4A #14 (1014)18 Nov 1964TAT AD1803397089.7KM{FFIF#́ 4]y^]AO BD^`pr|10564085KH-4A #15 (1015)19 Dec 1964TAT AD1834107590.5>@GFOJF#́ 4]y^]AO $&@BRT^ht10664087?21 Dec 1964TAT AD23826470.189.5KMIFKF#́ 4]y^]AO BD^`pr|10765002KH-4A #16 (1016)15 Jan 1965TAT AD1804207590.5MOOJFLF#́ 4]y^]AO BD^`pr|10865013KH-4A #17 (1017)25 Feb 1965TAT AD17737775.190.1KFNF<#F} 4]y^]AO j 4hAhA 4m^{쉂"$>@LNXbn10965016A: Solrad 06BB: GGSE 2C: GGSE 3D: Solrad 07BE: Secor 03F: Oscar 03G: Surcal 2H: Porcupine 1 (Dodecapole 1)09 Mar 1965T AD91093970.1103.5MOLF:F#́ 4]y^]AO BD^`pr|11065026KH-4A #18 (1018)NF:FD25 Mar 1965TAT AD18626596.189.1IKNFF#́ 4]y^]AO BD^`pr|11165033KH-4A #19 (1019)29 Apr 1965TAT AD1784738591KM:F΂F#́ 4]y^]AO BD^`pr|11265037KH-4A #20 (1021)18 May 1965TAT AD1983317589.7MOFF#́ 4]y^]AO BD^`pr|11365045KH-4A #21 (1020)09 Jun 1965TAT AD17636275.189.8DF΂F_F#́ 4]y^]AO 46PR^`jt11465055ELINT 1#717 Jul 1965T AD47151270.294.5KMFF#́ 4]y^]AO BD^`pr|11565057KH-4A #22 (1022)19 Jul 1965TAT AD18246485.191KM_FF#́ 4]y^]AO BD^`pr|11665067KH-4A #23 (1023)17 Aug 1965TAT AD1804077090.4D@F9F#؁ 4]y^]AO .0JL\^tx|117n/aStarad 202 Sep 1965TAT ADfailureIKFF#́ 4]y^]AO BD^`pr|11865074KH-4A #24 (1024)22 Sep 1965TAT AD1913648090KM9F͋F#́ 4]y^]AO BD^`pr|11965079KH-4A #25 (1025)05 Oct 1965TAT AD2033237589.8EGFF#́ 4]y^]AO ,.HJZ\ft12065081OGO-214 Oct 1965TAT AD4151 51787.4104.4KM͋F]F#́ 4]y^]AO BD^`pr|12165086KH-4A #26 (1026)28 Oct 1965TAT AD1764307590.5|_FُF# 4]y^]AO "I6$<`\^xz12265098Alouette 2Explorer 3129 Nov 1965Thor A5052 98779.8121.4KM]F0F#́ 4]ُF0FDy^]AO BD^`pr|12365102KH-4A #27 (1027)09 Dec 1965TAT AD1834378090.7KMُF{F#́ 4]y^]AO BD^`pr|12465110KH-4A #28 (1028)24 Dec 1965TAT AD1784468090.8MO0FF#́ 4]y^]AO BD^`pr|12566007KH-4A #29 (1029)02 Feb 1966TAT AD18542575.190.6DF{F F#́ 4]y^]AO 46PR^`jt12666009ELINT 1#809 Feb 1966T AD50851282.194.8KMFWF#́ 4]y^]AO BD^`pr|12766018KH-4A #30 (1030)09 Mar 1966TAT AD1784327590.6MO FF#́ 4]y^]AO BD^`pr|12866029KH-4A #31 (1031)07 Apr 1966TAT AD19331275.189.6LHWFF#؁ 4]y^]AO >@Z\ln129n/aKH-4A #32 (1032)03 May 1966TAT ADfailure[QFKF #䁢 4]y^]AO *R;C:<VXhjx13066040Nimbus 215 May 1966TAT AD1 1031 179100.3108.2IKFF#́ 4]y^]AO BD^`pr|13166042KH-4A #33 (1033)24 May 1966TAT AD1792716689MOKFF#́ 4]y^]AO BD^`pr|13266055KH-4A #34 (1034)21 Jun 1966TAT AD19436780.190.2XNF9F #䁜 4]y^]AO *Nf68RTdft13366056Pageos24 Jun 1966TAT AD4 2074 27187.1181.4PRFF#́ 4]y^]AO BD^`tv13466072KH-4A #35 (1035)09 Aug 1966LTTAT AD194287100.189.4MO9FG#́ 4]y^]AO FGDBD^`pr|13566085KH-4A #36 (1036)20 Sep 1966TAT AD18844285.190.9NPF0G#́ 4]y^]AO BD^`pr|13666102KH-4A #37 (1037)08 Nov 1966TAT AD172318100.189.4BDGrG#́ 4]y^]AO 46PR^`jt|13766118ELINT 1#929 Dec 1966T AD4864967594.4MO0GG#́ 4]y^]AO BD^`pr|13867002KH-4A #38 (1038)14 Jan 1967TAT AD18038080.190.1KMrG G#́ 4]y^]AO BD^`pr|13967015KH-4A #39 (1039)22 Feb 1967TAT AD1803808090.1KMGUG#́ 4]y^]AO BD^`pr|14067029KH-4A #40 (1040)30 Mar 1967TAT AD1673268589.5XZ GG#́ 4]y^]AO TVpr14167043KH-4A #41 (1041) + Ferret09 May 1967LTTAT AD20077785.194.4UG{ G(#M 4]y^]AO BhAhAԀ ",6>14267053A: navigation satellite (OPS 5712)C: GGSE 4D: GGSE 5E: Timation 1F: Surcal 159J: Surcal 150B31 May 1967T AD91492870103.5TVG G#́ 4]y^]AO TVpr14367062KH-4A #42 (1042) + Ferret16 Jun 1967LTTAT AD1813678090EG{ G G#́ 4]y^]AO 68RT`blv14467071ELINT 1#1025 Jul 1967T AD39058275.194.3PF GdG #䁌 4]y^]AO *}V46PRbdnx14567073OGO 428 Jul 1967TAT AD4119038697.9OQ GG#́ 4]y^]AO BD^`tv14667076KH-4A #43 (1043)07 Aug 1967LTTAT AD17434679.989.7PRdGAG#́ 4]y^]AOGAGD DF`bvx14767087KH-4B #1 (1101)15 Sep 1967LTTAT AD15038980.189.9XZGgBG#́ 4]y^]AO TVpr14867109KH-4A #44 (1044) + Ferret02 Nov 1967LTTAT AD18341081.590.5PRAGCG#́ 4]y^]AO DF`bvx14967122KH-4B #2 (1102)09 Dec 1967LTTAT AD15823781.788.5EGgBGDG#́ 4]y^]AO 68RT`blv15068004ELINT 1#1117 Jan 1968T AD45057675.294.5WYCGSFG#́ 4]y^]AO RTnp15168008KH4A #45 (1045) + Ferret24 Jan 1968LTTAT AD17643081.590.6VXDGGG#́ 4]y^]AO TVpr15268020KH-4A #46 (1046) + Ferret14 Mar 1968LTTAT AD1783918390.2PRSFGHG#́ 4]y^]AO DF`bvx15368039KH-4B #3 (1103)01 May 1968LTTAT AD16424383.188.6lOGGeJG# 4]y^]AO " K6LNhjz|154n/aNimbus 3ASecor-1018 May 1968TAT ADfailureVXHGKG#́ 4]y^]AO TVpr15568052KH-4A #47 (1047) + Ferret20 Jun 1968LTTAT AD1933268589.7PReJG MG#́ 4]y^]AO DF`bvx15668065KH-4B #4 (1104)07 Aug 1968LTTAT AD15225782.188.6VXKGaNG#́ 4]y^]AO TVpr15768078KH-4A #48 (1048) + Ferret18 Sep 1968LTTAT AD1673438390.1BD MGOG#́ 4]y^]AO 46PR^`jt|15868086ELINT 2#105 Oct 1968T AD4835117594.6PRaNGG#́ 4]y^]AO OGGDDF`bvx15968098KH-4B #5 (1105)03 Nov 1968LTTAT AD15028882.288.9Z\OGYG#́ 4]y^]AO \^xz16068112KH-4A #49 (1049) + Ferret ABM12 Dec 1968LTTAT AD1692488188.7]_GG#́ 4]y^]AO ^`z|16169010KH-4B #6 (1106) + Ferret ABM05 Feb 1969LTTAT AD17823981.588.7VXYG G#́ 4]y^]AO TVpr16269026KH-4A #50 (1050) + Ferret19 Mar 1969LTTAT AD1792418388.7y\GG# 4]y^]AO "S;C$8^{RTnp16369037Nimbus 3Secor 1314 Apr 1969TAT AD1 0751 13099.9107.4VX GۇG#́ 4]y^]AO TVpr16469041KH-4A #51 (1051) + Ferret02 May 1969LTTAT AD1793266689.5RHG-G #䁐 4]y^]AO *}V46PRbdn|16569051OGO 605 Jun 1969TAT AD3971 0898299.7NPۇG{G#́ 4]y^]AO DF`bvx16669063KH-4B #7 (1107)24 Jul 1969LTTAT AD1872117588.5FH-GG#́ 4]y^]AO 46PRfhr|16769065ELINT 2#231 Jul 1969LTTAT AD1535747591.5VX{GG#́ 4]y^]AO TVpr16869079KH-4A #52 (1052) + Ferret22 Sep 1969LTTAT AD1802508588.8GԎG(#+ 4]y^]AO XҀԀ 169?Anonymous ELINT ?Timation 2Anonymous (5)Tempsat 2Soical CylinderSoical Cone30 Sep 1969TAT AD4504807093.9PRG0G#́ 4]y^]AO DF`bvx17069105KH-4B #8 (1108)04 Dec 1969ԎG0GDLTTAT AD15925181.588.6DFԎGtG#́ 4]y^]AO .0JL\^hv17170009SERT-204 Feb 1970TAT AD9951 00699.1105WY0GG#́ 4]y^]AO VXrt17270016KH-4B #9 (1109) + Ferret04 Mar 1970LTTAT AD1591678887.7u^tG@G# 4]y^]AO "T;C8Z\vx17370025Nimbus 4Topo-1 (SECOR)08 Apr 1970TAT AD1 0931 10799.8107VXGG#́ 4]y^]AO TVpr17470040KH-4B #10 (1110) + Ferret20 May 1970LTTAT AD1622468388.6KM@GG#́ 4]y^]AO BD^`tv17570054KH-4B #11 (1111)23 Jul 1970LTTAT AD1583986090FHG'G#́ 4]y^]AO 46PRfhr|17670066ELINT 2#326 Aug 1970LTTAT AD4845047594.5VXG}G#́ 4]y^]AO TVpr17770098KH-4B #12 (1112) + Ferret18 Nov 1970LTTAT AD1852328388.7PL'GG#؁ 4]y^]AO BD^`tv17871012KH-4B #13 (1113)17 Feb 1971LTTAT ADfailureOQ}GG#́ 4]y^]AO BD^`tv17971022KH-4B #14 (1114)24 Mar 1971LTTAT AD15824681.588.6FHGbG#́ 4]y^]AO 46PRfhr|18071060ELINT 2#416 Jul 1971LTTAT AD4885077594.6XZGG#́ 4]y^]AO TVpr18171076KH-4B #15 (1115) + Ferret10 Sep 1971LTTAT AD15624474.988.5MObGH#́ 4]y^]AO <>XZnpz18271089STP-1 (ASTEX)17 Oct 1971LTTAT AD77280392.7GHD100.6QSGdH#́ 4]y^]AO HJdfz|18371110NOSS (experimental)14 Dec 1971LTTAT AD98499870104.9OQHH#́ 4]y^]AO BD^`tv18472032KH-4B #16 (1116)19 Apr 1972LTTAT AD15427781.588.8OQdHH#́ 4]y^]AO BD^`tv18572039KH-4B #17 (1117)25 May 1972LTTAT AD15830596.389.2HH7 <$Ƿ-H'Notes: in the type column, AA, AB & AD stand for Agena A, B et D; T stands for Thor, TAT for Thrust Augmented Thor and LTTAT for Long Tank Thrust Augmented Thor. All launches from Vandenberg.=H?H' ,O Additional payloads HKH+ $Ferret: U.S. piggyback electronic intelligence gathering (60 kg)1) with KH-5 satellites (Thor and TAT Agena): 3 ferrets2) with KH-7 satellites (Atlas Agena): 8 ferrets3) with KH-4A/B (LTTAT Agena): 16 ferrets of which 2 ferrets ABM4) with KH-9 (Titan 3D and 34D): 14 ferrets of which 4 ferrets ABM (plus a failure on April 18, 1986)5) USA 41 (STS-28): 1 ferret ?HitchHiker 1 (80 kg) Measurement of radiation in the Earth's Van Allen belts; Returned data for three months.n?HH( Starflash 1A/B : Geodetic functionTRS 1 (Tetraedral Research Satellite) = ERS 2 (Environmental Research Satellite)Mass = 667 g; Tetraedral shape measuring 15 cm across the base; 28 solar cells producing 1.2 W; 1 m long antenna; Measurement of radiation from the Starfish nuclear detonation; ERS 2 failed to eject from the KH-4/Agena assembly and was unusable.7KH H'  O Main payloadsH H* "ELINT (1st generation) : U.S. electronic intelligence gathering (700 kg)Launched at six-months intervals, a total of eleven 1st generation ELINT satellites were flown on Thor-Agena B and Thor-Agena D.ELINT (2nd generation) : U.S. electronic intelligence gathering (900 kg)On-board processor to analyze electronic data; A total of four 2nd generation ELINT satellites were flown on LTTAT-Agena D in 1968, 1969, 1970 and 1971.NOSS (700 kg) Navy Ocean Surveillance System= H\ H* "'Three separate satellites.Starad 1 (1100 kg) Measurement of radiation from the Starfish nuclear detonationEnd of ops : 18 Jan 1963; Reentered : 5 Oct 1967STP 1 (ASTEX) : Space Test Program (Advanced Space Technology) 1185 kgTwo primary experiments : ERIS (Earth Reflecting Ionospheric Sounder, 19 separate instruments for collecting data on proton, alpha and electron particles entering the upper atmosphere) and FRUSA (Flexible Rolled-Up Solar Array, 1.7 x 5.0 m array supporting 34,000 solar cells and producing 1,500 W)C H H' 8O Multiple payload launches \ HHT vq       13 Dec 1962: 5 satellites; combined payload weighing 138 kg- Black Sphere- Injun 3 (52 kg) Radiation belt monitor (magnetic field, solar wind and particles)- Surcal 1 : Surveillance Calibration- Surcal 1A : Surveillance Calibration- Calsphere 1A : Calibration Sphere15 Jun 1963: 6 satellites; Total mass = 1628 kg- Primary : Agena D classified satellite (1500 kg) - Lofti 2A (26 kg) Low Frequency Trans Ionosphere HAHK ds     - Solrad HAHD6A (39 kg) Solar Radiation- Radose (25 kg) Radiation Dosimeter- Anonymous (35 kg) classified satellite; FTV 1292- Surcal 1C (3 kg) Surveillance Calibration11 Jan 1964: 5 satellites- Primary: US Navy classified satellite (700 kg)- GGSE 1 (39 kg) Gravity-Gradient Stabilization Experiment- Secor 1 (18 kg) Sequential Collation of Range; Beacon transmitter for geodetic function- Solrad 7A (45 kg) Solar Radiation#HCH`          - Greb (Galactic Radiation Energy Background)9 Mar 1965: 8 satellites; Total mass = 136 kg- Solrad 6B (40 kg) Solar Radiation- GGSE 2 & 3 (4 kg) Gravity-Gradient Stabilization Experiment- Solrad 7B (47 kg) Solar Radiation- Secor 3 (18 kg) Sequential Collation of Range; Geodetic monitor- Oscar 3 (14 kg) - Surcal 2 (5 kg) Surveillance Calibration- Dodecahedron (4 kg) Surveillance Calibration (or Porcupine, or Dodecapole)HAH&FHk           31 May 1967: 9 satellites- Anonymous navigation satellite (38 kg)- Timation 1 (4 kg) Test of quartz clocks for navigation equipments- Surcal (3 objects): Surveillance Calibration- Calsphere (2.4 kg, 50 cm) Calibration Sphere- Calsphere (1.5 kg, 40 cm) Calibration Sphere- GGSE 4 & 5 (4 kg) Gravity-Gradient Stabilization Experiment30 Sep 1969: 10 satellites- Anonymous ELINT ?- Timation 2 (4 kg) Test of quartz clocks for navigation equipmentsCHGH< F?    - Anonymous (5 objects)- Tempsat 2- Soical Cylinder: Space Object Identification Calibration- Soical Cone: Space Object Identification Calibration1&FH2GH1W2GHGHGHT+GHGH) "VȠ$To view this page you need to register&2GHGH# ; GHGH18<>`GHHH@MThor DeltaGGH.HH5 :&" Thor Deltae4GHHH1 2h 㭄؉>ɉby Jean-Jacques Serralisting by Gunter Krebsi3.HHJH6 :g㰭=H㯃4Ƿ-HAt the end of 1958, not long after NASA was founded, the necessity of a new civilian launcher arose. This vehicle was to be available quickly until the arrival of the Atlas and Centaur. The basic stage could only be Thor associated with one of the 3 top stages available: Able, Ablestar and Agena. Refering to the fourth letter of the Greek alphabet NASA named this new stage Delta in January 1959. Three months later the construction was granted to Douglas Aircraft (a dozen rockets were ordered) and the naming Thor Delta (or simply Delta) was adopted.HH NH- (LV.The original Delta was almost identical to Thor Able: first stage was Thor, and the second and third stage was inherited from Vanguard. The improvments were in the field of inertial guiding and active piloting during the ballistic phase between shutdown of the second stage and ignition of the third stage. This first version was 27.8 m high and weighed 51 tons; it could put 45 kg in LEO.Its first launch on 13 May 1960 ended in a failure; the third stage didn't work. But the 12 August the second Delta was successful in orbiting Echo 1; this was the first of 22 successes. NASA went on using such launchers because of their reliability and their low cost and because of the improvements made by Douglas then McDonnell Douglas.vJHсHE X_ 0   _ 0The A version (1962) resulted of the use of the MB3-3 motor; the B version (1962) of the lengthening of the second stage; the C version (1963) had a new third stage; the D version (1964) had Castor boosters added to the first stage. The TAD (Thrust Augmented Delta) could place 450 kg on a 800 km orbit.The second stage was replaced in the E version (1965) resulting in the TAID (Thrust Augmented Improved Delta). The diame NHсHGHter of the second stage changed from 0.92 m to 1.43 m. This tripled the combustion time. The LTTAD (Long Tank Thrust Augmented Delta) appeared in the M version in 1968. the M-6 version of 1969 featured 6 Castor boosters; 3 ignited at takeoff and the others burned after the first ones shutdowned. Then not 6 but 9 boosters were included which enabled Delta to deliver 350 kg in GEO and 650 kg in a 550 km circular orbit (in 2-stage configuration). NHH- (E_ 0"Straight 8" appeared in the early 70ies; this Delta version had a constant diameter: 2.44 m (8 ft). The version naming changed at the same time to become a 4-digit number: the two first digits specify the type of the first stage and the number of strap-on boosters. The two last digits refer to the type of the second and the third stage.The 2910 version featured a Rocketdyne RS-27 first stage motor burning during 225 seconds and 9 Castor-2 boosters. The second stage was made from an Aerojet AJ10-118F motor (aerozin 50 & N204) delivering 4.3 t thrust during 320 seconds or a TRW TR-201 motor derived from the Lem descent motor using the same propellants. The 2-stage 2910 Delta could deliver 2 tons in orbit. The 3-stage 2914 version launched for the first time in 1972 featured a Thiokol TE364-4 third stage motor providing 6.5 tons thrust during 44 seconds; it could launch 720 kg payloads in geosynchronous orbit.JсH)H? LK\_ 0_ 0 The 2900 series was to be the last Delta series but as the Shuttle wasn't operational before 1980 NASA ordered the development of a new series for heavier payloads.The 3914 Delta appeared in 1975. This version had its Castor-2s replaced by Castor-4s of 1 m diameter and 10 m high providing each 42 tons thrust during 56 seconds. The GEO capacity reached 930 kg. In 1980 as the third stage was replaced by a PAM-D (Payload Assist Module / Delta) equipped with a Thiokol Star 48 engine capable of 8.6 tons thrust during 85 seconds; Delta 3910 PAM peformance reached 1090 kg in GEO. In 1982 the second stage was replaced by a larger version (+30% propellant) with an Aerojet AJ10-118K (borrowed from Titan-3's Transtage) providing 4.35 tons thrust during 430 seconds. This Delta 3920 PAM of 35.5 m high could launch 1250 kg in GEO.MHH? LK\QS_ 0In 1984 NASA transfered Delta to a private company: Transpace Carrier Inc. At the end on the year it was believed that the launcher would be abandonned and replaced by the Shuttle. But after Challenger's accident in 1986 the launcher reappeared.In 1987 the improved Delta was selected by the USAF as Medium Launch Vehicle (MLV) to place in orbit the second generation of Navstar satellites. The new launched was named Delta-2 and was designed in two stages: first the 6920 series then the 7920 series. The 6925 version was derived from Delta 3920 PAM by replacing the boosters by Castor-4As and lengthening the first stage of 3.65 m, extending the burn duration to 265 seconds. The diameter of the bulb cap was upped to 2.83 m. The launcher which first flew in 1989 was 39.6 m high, weighed 215 tons and could place 1400 kg in GEO.)HH+ $? The latest version is model 7925 which first launch occured in 1991. Its first stage is equipped with a RS-27 motor which nozzle was lengthened (12:1 instead of 8:1). The Thiokol boosters were replaced by Hercules GEM (Graphite Epoxy Motors) with weight reduced structure. Those boosters are 12 m long, weigh over 12.7 tons and provide 4.8 tons thrust. Delta 7925 weighs 225 tons and can place 1610 kg in GEO.:HH' & Current versionsbHHJ#d0Q  ModelDescriptiong&HHA#RLQ7320Delta II Lite with 3 strapons@HHA#RQ7326Delta II Lite with 3 strapons and Star 37FM third stagHHGHeg&HvHA#RLQ7420Delta II Lite with 4 strapons@HHA#RQ7425Delta II Lite with 4 strapons and PAM-D (Star 48) stageu4vHlHA#RhQ7426Delta II Lite with 4 strapons and Star 37FMi(HHA#RPQ7920Delta II standard, LEO missionsDlHZHA#RQ7925Delta II with PAM-D third stage for GEO and escape missions?HHA#R~Q?Delta III with GEM LDXL strapons and LH2/LOX second stageZHHo O j牂 jUTVTr2   H͉Delta in its different Delta-1 configurations launched numerous satellites on various orbits especially scientific satellites:- with low perigee (ADE)- with high apogee (IMP, ISEE 1 & ISEE 2, Exosat)- in lunar orbit (IMP-F, RAE-B)- to the Solar-Earth Lagrange point (ISEE-3)- and interplanetary probes (Pioneer, ICE former-ISEE-3)Among the scientific mission satellites some were launched:GHH F  ֋~㖨Ԝ hڜ֋v>UU <4~WVTUXT㯃\㰃\r2H͉ BOUUTɑȉ"S L- with collaboration (ISEE, IUE, AMPTE)- for foreign states (Ariel, Isis, IRAS)- or for international organizations (Heos, TD 1A, ISEE 2, COS B, ESA-Geos 1, ESA-Geos 2, Exosat)Application missions were aimed at:- meteorology (Tiros, Essa, Itos / NOAA, Nimbus, SMS, Goes)qHdH >s 郉 Vck㾩A~`ZISӉ CIxug ۢ&S>؉kS_z:GwS- remote sensing (Landsat)Especially for telecommunication satellites such as:- American satellites (Telstar, Relay, Syncom, Westar, Satcom, SBS, Galaxy) - International satellites (Intelsat, NATO) - or foreign satellites (Skynet, Anik, Symphonie, CTS, Palapa, OTS, Sirio, Insat...)Delta-2 versions were initially developped for the Navstar-2 satellites... but is not limited to them:HtH` a vMUr#WN}PU؉ ‰JaSZug- scientific satellites (Cobe, Rosat, EUVE, Geotail)- telecommunication satellites (BSB, Satcom, NATO,...)Currently Delta is owned by McDonnell Douglas=dHH' , Thor Delta launchesVutHH#4]A]2   $& <> \ l|~#Launch idPayloadLaunch dateSiteTypeStatus (orbit in perigee x apogee x inc. x period)7H H#nn4]A]2 &(BJLX1n/aEcho 113 May 1960CDM19Failure3HH#nf4]A]2 LV.02LTVb260009Echo 1A12 Aug 1960CDM194 HH#nh4]A]2 ;ܗ+24NVXd360016Tiros 0223 Nov 1960CDM197H$I#nn4]A]2 l`8:T\^j461010Explorer 1025H$IGH Mar 1961CDM194H'I#nh4]A]2 <ܗ+24NVXd561017Tiros 0312 Jul 1961CDM197$I-I#nn4]A]2 d`8:T\^j661020Explorer 1215 Aug 1961CDM194'I0I#nh4]A]2 =ܗ+24NVXd762002Tiros 0408 Feb 1962CDM191-I0I#nb4]A]2 V,.HPR^862006OSO 107 Mar 1962CDM1930I2I#nf4]A]2 d$t02LTVb962015Ariel 126 Apr 1962CDM1950I6I#nj4]A]2 >ܗ+46PXZf1062025Tiros 0519 Jun 1962CDM1962I;I#nl4]A]2 zz68RZ\h1162029Telstar 110 Jul 1962CDM1956I?I#nj4]A]2 ?ܗ+46PXZf1262047Tiros 0618 Sep 1962CDM195;IC I#nj4]A]2 f`:<V^`f1362051Explorer 1402 Oct 1962CA5?IG I#nj4]A]2 g`:<V^`f1462059Explorer 1527 Oct 1962CA1C IG I#nb4]A]2 24NVX^1562068Relay 113 Dec 1962CB2G IH I#nd4]A]2 sH46PXZ`1663004Syncom 114 Feb 1963CB5G IL I#nj4]A]2 i`:<V^`f1763009Explorer 1703 Apr 1963CB3H INI#nf4]A]2 zz68RZ\b1863013Telstar 207 May 1963CB2L IOI#nd4]A]2 @ܗ+46PXZ`1963024Tiros 0719 Jun 1963CB2NI\@I#nd4]A]2 sH46PXOI\@IGHZ`2063031Syncom 226 Jul 1963CB5OI`AI#nj4]A]2 j`:<V^`f2163046Explorer 1827 Nov 1963CC2\@IaBI#nd4]A]2 Aܗ+46PXZ`2263054Tiros 0821 Dec 1963CB1`AIaCI#nb4]A]2 24NVX^2364003Relay 221 Jan 1964CB >aBInDI#n|4]A]2 :<V^`f24n/aExplorer (BE A)19 Mar 1964CBFailure2aCIoEI#nd4]A]2 sH46PXZ`2564047Syncom 319 Aug 1964CD5nDIsFI#nj4]A]2 `:<V^`f2664060Explorer 2104 Oct 1964CC5oEIwGI#nj4]A]2 `:<V^`f2764086Explorer 2621 Dec 1964CC2sFIxHI#nd4]A]2 Bܗ+46PXZ`2865004Tiros 0922 Jan 1965CC/wGIvII#n^4]A]2 V.0JRTZ2965007OSO 203 Feb 1965CC6xHI{JI#nl4]A]2 rĉ<>X`bh3065028Intelsat 10106 Apr 1965CD5vIIKI#nj4]A]2 `:<V^`f3165042Explorer 2829 May 1965CC2{JILI#nd4]A]2 ڗ+46PXZ`3265051Tiros 1002 Jul 1965CC4KIMI#nh4]A]2 &(BJLR33n/aOSO C25 Aug 1965CCFailure5LINI#nj4]A]2 `:<V^`f3465089Explorer 2906 Nov 1965CEEMIOI#b4]A]2 24NVX^3565105Pioneer-616 Dec 1965CEInterplanetary probe0NII#n`4]A]2 OIIGH102LTV\3666008Essa 103 Feb 1966CC0OII#n`4]A]2 102LTV\3766016Essa 228 Feb 1966CE6II#nl4]A]2 `:<V^`h3866044Explorer 3225 May 1966CC1 QIăI#n4]A]2 `:<V^`h3966058Explorer 3301 Jul 1966CE130532 x 494230 x 29 x 19488FIӄI#b4]A]2 24NVX`4066075Pioneer-717 Aug 1966CE1Interplanetary probe0ăI҅I#n`4]A]2 102LTV\4166087Essa 302 Oct 1966VEHӄII#z4]A]2 ĉ<>X`bj4266096Intelsat 20126 Oct 1966CE1Partial failureG҅II#b4]A]2 02LTV\4366114Biosat-114 Dec 1966CG295 x 309 x 33.5 x 90.47II#nn4]A]2 ĉ<>X`bj4467001Intelsat 20211 Jan 1967CE10II#n`4]A]2 102LTV\4567006Essa 426 Jan 1967VE/II#n^4]A]2 V.0JRTZ4667020OSO 308 Mar 1967CC7II#nn4]A]2 ĉ<>X`bj4767026Intelsat 20323 Mar 1967CE10II#n`4]A]2 102LTV\4867036Essa 520 Apr 1967VE6I I#nl4]A]2 `:<V^`h4967051Explorer 3424 May 1967VE1EII#b4]A]2 BD^fhp5067070Explorer 35 (IMP)19 Jul 1967CE1Lunar orbitG I6I#b4]A]2 02LTV\5167083Biosat-207 SI6IGHep 1967CG286 x 313 x 33.5 x 90.47IX`bj5267094Intelsat 20428 Sep 1967CE106I;I#n`4]A]2 V.0JRT\5367100OSO 418 Oct 1967CE11X`bh6368116Intelsat 30219 Dec 1968CM0II#n`4]A]2 V.0JRT\6469006OSO 522 Jan 1969CC11II#nb4]A]2 T02LTV^6569009Isis 130 Jan 1969VE16II#nl4]A]2 ĉ<>X`bh6669011Intelsat 30306 Feb 1969CM1IJ#nb4]A]2 IJGH102LTV^6769016Essa 926 Feb 1969CE16IJ#nl4]A]2 ĉ<>X`bh6869045Intelsat 30422 May 1969CM6JJ#nl4]A]2 `:<V^`h6969053Explorer 4121 Jun 1969VE10JJ#b`4]A]2 02LTV\7069056Biosat-329 Jun 1969CNGJJ#z4]A]2 ĉ<>X`bh7169064Intelsat 30525 Jul 1969CNPartial failure/JJ#n^4]A]2 V.0JRTZ7269068OSO 609 Aug 1969CN :JJ#nt4]A]2 24NVX^73n/aPioneer-10A28 Sep 1969CLFailure3JJ#nf4]A]2  ȉ68RZ\b7469101Skynet 1A22 Nov 1969CM6JJ#nl4]A]2 ĉ<>X`bh7570003Intelsat 30615 Jan 1970CM:J J#|t4]A]2 *BOUU쉂BD^fhp7670008ItosOscar 0523 Jan 1970VN60J J#n`4]A]2 a }02LTV\7770021Nato 120 Mar 1970CM6 J J#nl4]A]2 ĉ<>X`bh7870032Intelsat 30723 Apr 1970CM6 J J#nl4]A]2 ĉ<>X`bh7970055Intelsat 30823 Jul 1970CM3 J J#nf4]A]2  ȉ68RZ\b8070062Skynet 1B19 Aug 1970CM+[ JJ#p4]A]2 ܁ {>@Zbdl8170106NOAA 01CEP 111 Dec 1970VN6CEP 1 was attached to the 2nd stage0 J@J#n`4]A]2 b }02LTV\8271009Nato 203 FeJ@JGHb 1971CL6J#AJ#nl4]A]2 `:<V^`h8371019Explorer 4313 Mar 1971CM61@J#BJ#nb4]A]2 T02LTV^8471024Isis 201 Apr 1971VE1/#AJ!CJ#n^4]A]2 V.0JRTZ8571083OSO 729 Sep 1971CNE#BJ/DJ#b4]A]2 68RZ\d8671091ITOS-3/NOAA21 Oct 1971VN6payload exploded?0!CJ.EJ#n`4]A]2 WI02LTV\8772005Heos 231 Jan 1972VL//DJ,FJ#n^4]A]2 4~W.0JRTZ8872014TD-1A12 Mar 1972VN5.EJ0GJ#nj4]A]2  ɉ68RZ\f8972058Landsat 123 Jul 1972V9008,FJ7HJ#np4]A]2 `:<V^`l9072073Explorer 4723 Sep 1972C160430GJ9IJ#nf4]A]2 ݁ {24NVXb9172082NOAA 0215 Oct 1972V30047HJX`bn10674101Symphonie 119 Dec 1974C29147ׇJJ#nn4]A]2 ɉ8:T\^j10775004Landsat 222 Jan 1975V29103߈JJ#nf4]A]2/UW02LTVb10875011SMS 206 Feb 1975C29144JJ#nh4]A]2@24NVXd10975027Geos 309 Apr 1975V23105JJ#nj4]A]2AQQ46PXZf11075038Anik A307 May 1975C29146JJ#nl4]A]2V;C68RZ\h11175052Nimbus 612 Jun 1975V29103JJ#nf4]A]2V02LTVb11275057OSO 821 Jun 1975C29133J J#nf4]A]2UXT02LTVb11375072Cos B09 Aug 1975V2914J JGH9JJ#nr4]A]2@a׉<>X`bn11475077Symphonie 227 Aug 1975C29149 JJ#nr4]A]2`<>X`bn11575096Explorer 5406 Oct 1975V29105J J#nj4]A]2.46PXZf11675100Goes 0116 Oct 1975C29149J(J#nr4]A]2`<>X`bn11775107Explorer 5520 Nov 1975C29106 J-J#nl4]A]2>0*68RZ\h11875117Satcom 113 Dec 1975C39141(J-J#nb4]A]2S,.HPR^11976004CTS17 Jan 1976C29147-J3J#nn4]A]2ݏ78:T\^j12076017Marisat 119 Feb 1976C29146-J8J#nl4]A]2?0*68RZ\h12176029Satcom 226 Mar 1976C391453J@Zbdp14879007Scatha (P78 2)30 Jan 1979C291427800 x 42300 x 8.3 x 14416CKEK#nl4]A]2/68RZ\h14979072Westar 310 Aug 1979C29146DKFK#nl4]A]2@0*68RZ\h15079101Satcom 307 Dec 1979C39141EKGK#nb4]A]2,.HPR^15180014SMM14 Feb 1980C39105FKHK#nj4]A]2.46PXZf15280074Goes 0409 Sep 1980C39147GKIK#nn4]A]2=HW02LTVj15380091SBS 115 Nov 1980C3910/PAM5HKJK#nj4]A]2.46PXZf15481049Goes 0522 May 1981C3914DhIKLK#4]A]2*xz15581070Dynamics Explorer 1Dynamics Explorer 203 Aug 1981V3913Partial failure7JK MK#nn4]A]2=HW02LTVj15681096SBS 224 Sep 1981C3910/PAM;LKNK#|v4]A]2*͓F̉@B\dfr15781100SMEUosat 106 Oct 1981V2310 ; MK(OK#nv4]A]2-8:T\^r15881114Satcom 3R20 Nov 1981C3910/PAM :NK=K#nt4]A]2A0*68RZ\p15982(OK=KGH004Satcom 416 Jan 1982C3910/PAM :(OKFK#nt4]A]2/68RZ\p16082014Westar 426 Feb 1982C3910/PAM :=KOK#nt4]A]2sG@c68RZ\p16182031Insat 1A10 Apr 1982C3910/PAM :FKXK#nt4]A]2/68RZ\p16282058Westar 509 Jun 1982C3910/PAM7OK^K#nn4]A]2ɉ8:T\^j16382072Landsat 416 Jul 1982V39209XKfK#nr4]A]2QQ46PXZn16482082Anik D126 Aug 1982C3920/PAM6^KkK#nl4]A]2]68RZ\h16582105Aurora 128 Oct 1982C3924+[fKK#p4]A]2v>UU:<V^`l16683004IRASPIX 226 Jan 1983V3910PIX 2 was attached to the 2nd stage7kKK#nn4]A]2-8:T\^j16783030Satcom 1R11 Apr 1983C39245KK#nj4]A]2.46PXZf16883041Goes 0628 Apr 1983C39144KK#nh4]A]2r224NVXd16983051Exosat26 May 1983V3914 :KK#nt4]A]27up68RZ\p17083065Galaxy 128 Jun 1983C3920/PAM =KK#nz4]A]2Ƶ<>X`bv17183077Telstar 30128 Jul 1983C3920/PAM7KK#nn4]A]2-8:T\^j17283094Satcom 2R08 Sep 1983C3924 :KǎK#nt4]A]28up68RZ\p17383098Galaxy 222 Sep 1983C3920/PAMAKޏK#|4]A]2*ɉΓF̉LNhpr~17484021Landsat 5Uosat 201 Mar 1984V3920,OǎKK#4]ޏKKGHA]28Z=nhj17584088AMPTE CCEAMPTE IRMAMPTE UKS16 Aug 1984C3924 :ޏKK#nt4]A]29up68RZ\p17684101Galaxy 321 Sep 1984C3920/PAM5K#K#nj4]A]2Cd46PXZf17784115Nato 3D14 Nov 1984C3914;K3K#zv4]A]2O'B.0JRT`178n/aGoes G03 May 1986C3914Failure:#K6K#bt4]A]2>@Zbdp17986069USA 019 (SDIO)05 Sep 1986C392053K:K#nj4]A]2.46PXZf18087022Goes 0726 Feb 1987C3924 <6KEK#nx4]A]2有:<V^`t18187029Palapa B2P20 Mar 1987C3920/PAMV:KdK#b4]A]2<>X`b~18288008USA-30 (SDIO)08 Feb 1988C3920 or 3910220 x 340 x 28.6 x 908EKkK#np4]A]2.:<V^`l18389013GPS BII-0114 Feb 1989C69258dKrK#np4]A]2:<V^`l18489026Delta Star24 Mar 1989C39208kKyK#np4]A]2.:<V^`l18589044GPS BII-0210 Jun 1989C69258rKK#np4]A]2.:<V^`l18689064GPS BII-0318 Aug 1989C69253yKK#nf4]A]2S02LTVb18789067BSB 127 Aug 1989C49258KK#np4]A]2.:<V^`l18889085GPS BII-0421 Oct 1989C69252KK#nd4]A]2vMU.0JRT`18989089Cobe18 Nov 1989V59208KL#np4]A]2KLGH.:<V^`l19089097GPS BII-0511 Dec 1989C69258KL#np4]A]2.:<V^`l19190008GPS BII-0624 Jan 1990C6925(^LL#d4]A]2bd~19290015USA 051 + 052(LACE + RME; SDIO)14 Feb 1990C6920-8500 x 500 x 43.18LL#np4]A]2.:<V^`l19390025GPS BII-0726 Mar 1990C6925 :LL#nt4]A]2有:<V^`p19490034Palapa B2R13 Apr 1990C6925-86LL#nl4]A]2r#W02LTVh19590049Rosat01 Jun 1990C6920-106LL#nl4]A]2vG@c68RZ\h19690051Insat 1D12 Jun 1990C49258LL#np4]A]2.:<V^`l19790068GPS BII-0802 Aug 1990C69253LL#nf4]A]2S02LTVb19890074BSB 219 Aug 1990C69258L L#np4]A]2.:<V^`l19990088GPS BII-0901 Oct 1990C6925 :L L#nt4]A]2jG>@Zbdp20090093Inmarsat 2F130 Oct 1990C69259 L L#nr4]A]25F݉<>X`bn20190103GPS BIIA-1026 Nov 1990C79255 L L#nj4]A]2Cd46PXZf20291001Nato 4A08 Jan 1991C7925 : LL#nt4]A]2jG>@Zbdp20391018Inmarsat 2F208 Mar 1991C69253 LL#nf4]A]2iS02LTVb20491028ASC 213 Apr 1991C79256L'@L#nl4]A]2]68RZ\h20591037Aurora 2L'@LGH29 May 1991C7925AL8AL#p4]A]25F݉LNhpr~20691047GPS BIIA-11Losat-X04 Jul 1991C79259'@L@BL#nr4]A]25F݉<>X`bn20792009GPS BIIA-1223 Feb 1992C792598ALHCL#nr4]A]25F݉<>X`bn20892019GPS BIIA-1310 Apr 1992C79259@BLPDL#nr4]A]25:98:T\^n20992027Palapa B414 May 1992C7925-85HCLTEL#nj4]A]2N}PU.0JRTf21092031EUVE07 Jun 1992C6920-109PDL\FL#nr4]A]25F݉<>X`bn21192039GPS BIIA-1407 Jul 1992C7925,\TELGL#p4]A]2؉>@Zbdp21292044GeotailDuve24 Jul 1992C6925Duve was attached to the 2nd stage7\FLHL#nn4]A]2t-8:T\^j21392057Satcom C431 Aug 1992C79259GLIL#nr4]A]25F݉<>X`bn21492058GPS BIIA-1509 Sep 1992C79253HLJL#nf4]A]2̗>T02LTVb21592066DFS 312 Oct 1992C79259ILKL#nr4]A]25F݉<>X`bn21692079GPS BIIA-1622 Nov 1992C79259JLLL#nr4]A]25F݉<>X`bn21792089GPS BIIA-1718 Dec 1992C79259KLML#nr4]A]25F݉<>X`bn21893007GPS BIIA-1803 Feb 1993C7925DhLLNL#4]A]2*5F݉RNPjz|R21993017GPS BIIA-19Seds 130 Mar 1993C 17A7925Seds 1 was tethered to 2nd stage9ML L#nr4]A]2 6F݉<>X`bn22093032GPS BIIA-2013 May 1993C7925NL LGH*ZNL6L#p4]A]26F݉DF`hjv22193042GPS BIIA-21PMG26 Jun 1993C7925PMG was tethered to 2nd stage < LAL#nx4]A]26F݉<>Xfht22293054GPS BIIA-2230 Aug 1993C 177925 <6LLL#nx4]A]26F݉<>Xfht22393068GPS BIIA-2326 Oct 1993C 1779255ALPL#nj4]A]2Cd46PXZf22493076Nato 4B08 Dec 1993C7925 <LL[L#nx4]A]2_b㉂8:Tbdt22594013Galaxy 1R19 Feb 1994C 177925-8CgPLL#4]A]2*6F݉RNPjxzR22694016GPS BIIA-24Seds 210 Mar 1994C 177925Seds 2 was tethered to 2nd stage ;[LL#nv4]A]2a͉24N^`r22794071Wind 101 Nov 1994C 17B7925-10HmLL#4]A]2"Y <>Zjlx22895041Koreasat 105 Aug 1995C 17B7925Partial failure: a booster failed to separate`LPL#4]A]20gT㉱vPR22995059RadarsatSurfsat 104 Nov 1995 at 14:22 UTV SLC27920-10Surfsat is attached to Delta's second stageFLkL#z4]A]2"*.0dtv23095074XTE30 Dec 1995 at 13:48 UTC 17A7920-10JPLL#z4]A]2"Y <>r23196003Koreasat 214 Jan 1996 at 11:11 UTC 17B7925JkLL#n4]A]28:n~23296008NEAR probe17 Feb 1996 at 20:43 UTC 17B7925-8OLL#n4]A]2QV02L^`r23396011Polar24 Feb 1996V SLC27925-10185 x 50494 km x 866aL L#z4]A]2"6F݉>@t23496019GPS BIIA-2528 Mar 1996 at 00:21 UTC 17A7925192 x 20269 km x 34.9L LGH$IL0L#4]A]2"㟛.0dvx23596024MSX24 Apr 1996 at 12:27 UTV SLC27920-10'L LWL#4]A]2"?up8:n~23696033Galaxy 924 May 1996 at 01:10 UTC 17B7925-8(M0LL#4]A]2"6F݉>@t23796041GPS BIIA-2616 Jul 1996 at 00:50 UTC 17B7925(MWLL#4]A]2"6F݉>@t23896056GPS BIIA-2712 Sep 1996 at 08:49 UTC 17A7925CLL#z4]A]2LNhpr23996062Mars Global Surveyor7 Nov 1996C7925>LL#z|4]A]2BD^fhv24096068Mars Pathfinder4 Dec 1996C7925LL#4]A]2"2Z݉:<p241n/aGPS BIIR-0117 Jan 1997 at 16:28 UTC 17A7925Failure: was destroyed by controllers after 13 s flight. Caused damages to the launch pad. A split in the casing of one of nine solid rocket motors caused the accident. LPL#e4]A]2ZqՅpՅoՅnՅmՅ€Ā  24297020A: Iridium 08B: Iridium 07C: Iridium 06D: Iridium 05E: Iridium 045 May 1997 at 14:55 UTV SLC 27920595 x 949 km x 86.7 initial orbitELgL#t4]A]2gO24fvx24397025Thor 220 May 1997 at 22:39 UTC 17A7925PLL#4]A]2ZՅՅՅՅՅ€Ā  24497034A: Iridium 15B: Iridium 17C: Iridium 18D: Iridium 20E: Iridium 219 Jul 1997 at 13:04 UTV SLC 27920 :gLL#tt4]A]23Z݉<>Xhjp24597035GPS BIIR-0223 Jul 1997C 17AxLoL#4]A]2TՅՅՅՅՅ€24697043A: Iridium 26B: Iridium 25C: Iridium 24D: Iridium 23E: Iridium 2221 Aug 1997 at 00:38 UTV 7920DLM#t4]A]2*,oLMGH`pr24797045ACE25 Aug 1997 at 14:39 UTC 17A7920-8oLM##4]A]2TՅCՅBՅAՅ@Յ€24897056A: Iridium 19B: Iridium 37C: Iridium 36D: Iridium 35E: Iridium 3427 Sep 1997 at 01:23 UTV SLC27920-10CIM,M#t4]A]23Z݉<>n~24997067GPS BIIR-026 Nov 1997 at 00:30 UTC 17A7925MM#4]A]2ZjՅhՅqՅEՅDՅ€Ā 25097069A: Iridium 43B: Iridium 41C: Iridium 40D: Iridium 39E: Iridium 389 Nov 1997 at 01:34 UTV SLC27920|,M+M#4]A]2TlՅmՅnՅoՅpՅ€25197082A: Iridium 45B: Iridium 46C: Iridium 47D: Iridium 48E: Iridium 4920 Dec 1997 at 13:16 UTV SLC27920IMFM#t4]A]2DFx25298001Lunar Prospector7 Jan 1998 at 02:28 UTC 46H+M`M#t4]A]2 ȉ8:l|~25398002Skynet 4D10 Jan 1998 at 00:32 UTC 17B7925FM M#C4]A]2L㬝QP㭝QP㮝QP㯝QP25498008A: Globalstar 1B: Globalstar 2C: Globalstar 3D: Globalstar 414 Feb 1998 at 14:34 UTC 17A7420-10with satellite dispenser`Mw M#'4]A]2ZՅՅՅՅՅ€Ā  "25598010A: Iridium 50B: Iridium 56C: Iridium 52D: Iridium 53E: Iridium 5418 Feb 1998 at 13:58 UTV SLC27920-10C M M#'4]A]2ZՅՅՅՅՅ€Ā  "25698019A: Iridium 55B: Iridium 57C: Iridium 58D: Iridium 59E: Iridium 6030 Mar 1998 at 06:02 UTV SLC27920-10Cvw MuM#4]A]2L㱝QP㳝QP{}{} 25798023A: Globalstar 6B: Globalstar 8C: Globalstar 14D: Globalstar 1524 Apr 1998 at 22:38 UTC 17A7420~ M @M#4]A]2VՅՅՅՅՅ€Ā 25898032A: Iridium 70B: Iridium 72C: Iridium 73D: Iridium 74E: Iridium 7517 May 1998 at 21:16 UTV SLC27920uM @MGH`uM@M' $Notes: in the launcher date & site column C stands for Cape Canaveral and V for Vandenberg.J @M@M1%m@MAM MThor with solid top stage](@M:AM5 :R" Thor with a solid fuel top stagee4@MAM1 2h 㭄؉>ɉby Jean-Jacques Serralisting by Gunter Krebs8:AMCM< F&[+&[+&[+&[+The first solid fuel top stage associated with Thor in 1965 was Altair, the former third stage of Vanguard equipped with a 3-axis control by Boeing. Called Burner this top stage was also adapted on Thor and other USAF vehicles. Despite Burner 1 used an Altair motor, Burner 2 featured a Thiokol Star-37B motor (TE-M-364-2) derived from the Surveyor lunar retro-rocket. The Burner 2A was a two stage version which second stage Star-37S (TE-M-364-15) provided a slightly weaker thrust than Star-37B.AMDM+ $!&[+Thor Altair and Thor Burner were mainly used for US military meteorological programs although they also launched technological satellites.L%CMDM' J Thor with solid top stage launches/}DM FM#4T Z     : P n~# and serialLaunch idPayloadLaunch dateTypeStatus (orbit in perigee x apogee x inclination x period) QDMGM#@T Z  46PRp1, 224DMSP B4A-0119 Jan 1965LV2D Burner1471 x 822 x 98.8 x 97.7 Q FMHM#@T Z  46PRp2, 306DMSP B4A-0218 Mar 1965LV2D Burner1525 x 764 x 99.1 x 97.7 RGM)IM#@T Z  46PRp3, 282DMSP B4A-0320 May 1965LV2D Burner1567 x 953 x 98.7 x 100.1 SHM4JM#@T Z  46PRp4, 213DMSP B4A-0410 Sep 1965LV2D Burner1649 x 1054 x 98.7 x 101.9U)IMGKM#LT Z  46PRp5, 251DMSP B4A-0506 Jan 1966LV2D Burner1Failure: 2nd stage failed R4JMQLM#@T Z  46PRp6, 147DMSP B4A-0631 Mar 1966LV2D Burner1634 x 933 x 98.6 x 100.6 RGKM[MM#@T Z  46PRp7, 167DMSP B4A-0716 Sep 1966LV2D Burner2705 x 891 x 98.5 x 100.9 RQLMeNM#@T Z  46PRp8, 169DMSP B4A-0808 Feb 1967LV2D Burner2796 x 868 x 98.8 x 101.6O[MMsOM#NT Z  "$s^{^`z|9, 17167065Secor 09Aurora 1 (P67-1)29 Jun 1967LV2D Burner2 QeNMM#@T Z  68sOMM@MRTr10, 266DMSP B4A-0923 Aug 1967LV2D Burner2834 x 892 x 99 x 102.2 SsOMM#@T Z  68RTr11, 268DMSP B4A-1011 Oct 1967LV2D Burner2694 x 837 x 99.1 x 100.2 RMM#@T Z  46PRp12, 277DMSP B5A-123 May 1968LV2D Burner2817 x 904 x 98.9 x 102.2PMM#@T Z  46PRp13, 173DMSP B5A-223 Oct 1968LV2D Burner2797 x 855 x 99 x 101.4NMM#@T Z  46PRp14, 279DMSP B5A-323 Jul 1969LV2D Burner2791 x 863 x 99 x 101 RMM#@T Z  46PRp15, 287DMSP B5A-411 Feb 1970LV2D Burner2764 x 974 x 98.7 x 101.6 RMM#@T Z  46PRp16, 288DMSP B5A-503 Sep 1970LV2D Burner2764 x 874 x 98.7 x 101.3dM܇M#BT Z  XZtv17, 249DMSP B5A-6Calsphere 3, 4, 517 Feb 1971LV2D Burner2767 x 833 x 98.8 x 100.9 UMM#@T Z  <>XZx18, 210SESP-1 (P70-1)08 Jun 1971LV2D Burner2545 x 581 x 90.2 x 95.9 Q܇MM#@T Z  46PRr19, 159DMSP B5B-114 Oct 1971LV2D Burner2A796 x 877 x 99 x 101.7 SMM#@T Z  46PRr20, 153DMSP B5B-224 Mar 1972LV2D Burner2A803 x 885 x 98.8 x 101.8 SMM#@T Z  46PRr21, 294DMSP B5B-309 Nov 1972LV2D Burner2A813 x 872 x 98.6 x 101.8 SMM#@T Z  46PRr22, 291DMSP B5B-417 Aug 1973LV2D Burner2A811 x 852 x 98.9 x 101.6 SMM#@T Z  46PRr23, 207DMSP B5B-516 Mar 1974LV2D Burner2A780 x 876 x 98.9 x 101.5 SM)M#@T Z  46PRr24, 275DMSP B5B-609 Aug 1974LV2D Burner2A808 x 870 x 98.8 x 101.7 SM@M#@T Z  46PRr25, 197DMSP B5C-124 M)M@M@May 1975LV2D Burner2A830 x 904 x 98.9 x 102.2-o)MmM#LT Z  46PRr26, 182DMSP B5C-221 Feb 1976LV2D Burner2APartial failure: Thor failed, wrong orbit attainedN@MsM#@T Z  68RT|27, 172DMSP B5D1-111 Sep 1976LV2F S3B S37B-ISS820 x 845 x 99XmMM#@T Z  68RT|28, 183DMSP B5D1-205 Jun 1977LV2F S3B S37B-ISS811 x 869 x 99.2 x 101.7WsMM#@T Z  68RT|29, 143DMSP B5D1-301 May 1978LV2F S3B S37B-ISS564 x 653 x 97.6 x 96.9XMM#@T Z  68RT|30, 264DMSP B5D1-406 Jun 1979LV2F S3B S37B-ISS820 x 838 x 98.8 x 101.1]MM#LT Z  68RT|31, 304DMSP B5D1-514 Jul 1980LV2F S3B S37B-ISSFailure: 2nd stage explodedP)M M' R$Notes: All launches from Vandenberg.6MCM1UMCMMzNTitanB MM5 :F" TitanDCMM* $4 㭄؉by Jean-Jacques SerraCMOMC V ^] ^] Origins of TitanTitan without top stage (2)Titan 38 MM, (O^] Titan 4OMKM< F 㰭=H㰭=HOrigin: Inter Continental Ballistic Missile (ICBM) of second generationAs building ICBMs was a very risky venture, it was decided in 1955 to develop another two-stage missille despite Atlas. This contract was awarded to the Martin Company (then Martin Marietta, then Lockheed Martin).The first stage of 3.05 m diameter like Atlas were planned to be powered by two Aerojet LR-87 which delivered 1335 kN thrust at takeoff. The second stage of 2.44 m diameter was made of 1 Aerojet LR-91 motor of 356 kN. The two stages burned the same fuel: liquid oxygen and kerosene. The missile was 29.9 m high (with a Mk4 RV) and weighed 99.8 tons.Z3MM' gFor the first launch on 9 Feb 1959 the missile had only 1 stage active, the second was full of water. Enhancements of the motors were started the following month and the version 3 (simplified and lighter) flew in May 1960. Titan 1 was deployed in silos from 1962 to 1965 but not space launcher was derived from it.The reaction time of the Titan 1's evaluated to 15 minutes could be reducted to only 1 minute by replacing its propellant by stockable propellant. The studies started in 1960 and resulted in Titan 2. This is an enhanced vehicle with a doubled payload/range ratio. The 2 stages measuring respectivly 21.4 m and 12.2 m long had a uniform 3.05 m diameter. The motors were modified (5th version) and used Nitrogen TetraOxide and Aerozine 50. Titan 2 was 31.4 m high (with a Mk6 RV) and weighed 150 tons.zVKMM$ The missile was operational in March 1962 and deployed in silos from 1964 to 1987.AM`M' 4 Titan propulsion systemOMN#b ylz  N x  ƀ`MN M  DesignationYear of first launchLR 87 thrust (kN)LR 87 SI (sec)LR 91 thrust (kN)LR 91 SI (sec)Application9`MN#,rylz$8JT^`1-31959-19611335 (g)249 (g)356311Titan 12NN#,dylz *<FPR519621910 (g)259 (g)445315Titan 21NaN#,bylz *<FPR719641910 (g)259 (g)445315GeminiGNVN#,ylz @fpz|919641910 (g) / 2030 (v)259 (g) / 275 (v)445316Titan 3HaNLN#,ylz Bhr|~1119682045 (g) / 2350 (v)258 (g) / 302 (v)445316Titan 34VN.N#,hylz.@JTV11A19892440 (v)301 (v)467316Titan 4L(LNzN$ P(g): ground value; (v): vacuum value1.NN1N_NhzN_NL h EL^]^]^]Titan[launch vehicle index]Origins of TitanTitan 2 (without top stage)Titan 3Titan 4HNN1fN?NpNTitan without top stageT_NN5 :@F" Titan without top stageDN?N* $4 㭄؉by Jean-Jacques SerraT.N N& ]The selecting of the launcher for the manned Gemini flight was profitable to Titan 2 because of its capacity to orbit the necessary load (3.5 tons), its ease of use with stockable propellant and it's reliability. Only little modifications were made to enable it to launch manned capsules, and the motors (v7) had the same performances as v5.After a suborbital flight in 1964 and a non piloted one in early 1965 ten manned capsules from the Gemini program were launched from Cap Canaveral between March 1965 and November 1966. All were orbited correctly.?N N- (_ 0In early 1986 Martin Marietta was granted a contract to evolve some retired Titan 2 ICBM into Titan 2 SLV. The first of those was launched in September 1988 from vandenberg in G (or 23G) version. The main modifications involve the cap and the the guidance.Two other versions were proposed: Titan 2B (basic), a simplified version which keeps the original cap, and Titan 2S (Solid Thrust Augmented) which get 2 to 8 Castor 4A solid boosters.: N N' & Titan 2 launchesf NN# OZ K  $&<>\l|~#Launch idPayloadLaunch DateSiteTypeStatus/Comment (orbit in perigee x apogee x inclination x period)6 NN#\lOZ K * $&>FHh1Gemini 18 Apr 1964CCTitan-2 Gemini8N%@N#\pOZ K * $&BJLl2Gemini 219 Jan 1965*N%@N_NCCTitan-2 Gemini7N"AN#\nOZ K * $&@HJj3Gemini 323 Mar 1965CCTitan-2 Gemini6%@NBN#\lOZ K * $&>FHh4Gemini 43 Jun 1965CCTitan-2 Gemini="AN!CN#\zOZ K * 02LTVv5Gemini 5 / REP21 Aug 1965CCTitan-2 Gemini6BNDN#\lOZ K * $&>FHh6Gemini 74 Dec 1965CCTitan-2 Gemini7!CNEN#\nOZ K * $&@HJj7Gemini 615 Dec 1965CCTitan-2 Gemini7DNFN#\nOZ K * $&@HJj8Gemini 816 Mar 1966CCTitan-2 Gemini6ENGN#\lOZ K * $&>FHh9Gemini 93 Jun 1966CCTitan-2 Gemini9FNHN#\rOZ K * (*DLNn10Gemini 1018 Jul 1966CCTitan-2 Gemini9GNIN#\rOZ K * (*DLNn11Gemini 1112 Sep 1966CCTitan-2 Gemini9HNJN#\rOZ K * (*DLNn12Gemini 1211 Nov 1966CCTitan-2 GeminiIIN%KN#hOZ K *"02ㄪ뉂PRjpr13, 2B-98/-5688078Singleton 15 Sep 1988VTitan-2(23)GFJN7LN#hOZ K **,㲪뉂JLdjl14, 2B-10689072Singleton 25 Sep 1989VTitan-2(23)G ?%KNBMN#h~OZ K * Z뉂:<V\^z1592023Singleton 325 Apr 1992VTitan-2(23)Gd7LNNN# OZ K * ɉ24L*bd(+**16n/aLandsat 65 Oct 1993V SLC4WTitan-2(23)G Star-37XFP-ISSFailure: Star-37XFP-ISS kick-motor malfunctioned$XBMNON#hOZ K * ,* ln1794004Clementine 1 / DSPSE-ISA [Star-37FM]25 Jan 1994VTitan-2(23)G3UNN N#OZ K ON N_N*,$.&㭢р"*JLdjl*18, G697012DMSP B5D2-94 Apr 1997VTitan-2(23)G Star-37S-ISSAcONJN#OZ K * ,"] {"68*l~"*1998030NOAA 1513 May 1998 at 15:52 UTV SLC4WTitan-2(23)G Star 37XFP#12 ?& NpN# 8JNN1>dN0NLQTitan 3DpNN5 : F" Titan 3DN0N* $4 㭄؉by Jean-Jacques SerraH!NxN' BO Titan 3 without solid boosters0N N& The first Titan 3 vehicles were based on the 2-stage Titan 2 to which a top stage was added. The motors (version 9) had the same performance as the former versions but were qualified for in-orbit ignition. From 1968 on, the version 11 formerly developped for the MOL program was used for the Titan 3.Titan 3A was an intermediate rocket to be used for the development of the Titan 3C top stage. This third stage named Transtage was 4.5 m long and 3.05 m diameter. It could be re-ignited in orbit. It was equiped of an 2 Aerojet motor AJ10-138 propulsion bay. Those used the same propellant as the firsts stages and provided a total 71 kN.XxNN- (mO{It was not used much: only 4 launches from Sep 1964 to May 1965 from Cape Canaveral; first launch was a failure, and the following successes.Titan 3B was a military launcher exclusivly used from Vandenberg. It used an Agena top stage. It was used to launch reconnaissance satellites from the KH-8 series between 1966 and 1984. The same launcher was used for the classified SDS and Jumpseat launches to Molniya type orbits. In 1975 a version with a a longer first stage and wider cap was introduced: Titan 34B (or Titan 3B Ascent Agena). It was specifically devoted to those military launches.E NN' < Titan 3 with solid boosters6N N% #Titan 3C was made of the 3 stages of Titan 3A plus two lateral solid boosters of 3.05 m diameter. Unlike Thor's boosters, those built by UTC/CSD did not assist the first stage motors but provided alone the launcher's propulsion during about 2 minutes. With 25.5 m high and 250 tons, each (composed of 5 segments) provided 5340 kN.The Transtage which contained the full command module of the vehicle including the guidance system could deliver payloads directly in GEO. It was the first rocket to fire 4 times during a flight.r&NNL fM%k;SąoS9%㯃4Titan 3C was 39 m high and could orbit 12 tons in LEO and 1 ton in GEO. It was used from 1965 to 1982 to launch telecommunication satellites (ISDCP, LES, DSCS), early warning birds (Vela, DSP) and SIGINT (Chalet) from Cape Canaveral.Titan 3D was assembled with 3 stages from Titan 3B and the 2 lateral 5-segment boosters of Titan 3C. It was launched from Vandenberg between 1971 and 1982 with KH 9 and KH 11 on board.The Titan 3E developped for civilian applications of NASA the top stage was a cryogenic Centaur. This 9.1 m long stage had the same diameter as the 2 first stages but was under a 4.27 m diameter cap. With 48 m high and 640 tons Titan 3E could put 3.6 tons on escape orbit. It was thus used for interplanetary missions as Helios, Voyager and Viking between 1974 and 1977.H NN2 2-\l|~#Launch idPayloadLaunch DateSiteTypeStatus/Comment (orbit in perigee x apogee x inclination x period)ENN#hOZ K * "<>V^`t+*1, 3A-2n/aTranstage 12 Sep 1964CCTitan-3AFailure:NN#\tOZ K *68RZ\p2, 3A-1Transtage 210 Dec 1964CCTitan-3A;NN#hvOZ K *$&㿶U8:T\^r3, 3A-365008LES 111 Feb 1965CCTitan-3AHN"N#vOZ K *$*&UIUTVnvx4, 3A-465034B: LES 2C: LCS 16 May 1965CCTitan-3A?N'N#\~OZ K *$&@B\dfz5, 3C-765047Transtage 518 Jun 1965CCTitan-3CE"N>N#tOZ K *$& :<V^`t+*6, 3C-465082OV 2-115 Oct 1965CCTitan-3CFailure<a'NzN#OZ K *$:& ¶U쉂7, 3C-865108A: OV 2-3B: LES 4C: Oscar 04D: LES 321 Dec 1965CCTitan-3CS>NN#^OZ K *&(hj8, 3C-1166053IDCSP 1 to 7GGTS 1 (OPS 9381)16 Jun 1966CCTitan-3CMzNN#\OZ K *$&LNhpr9, 3B-166069KH-8 1 (OPS 3014)29 Jul 1966VaTitan-3B Agena-D*^NN#hOZ K *$&ln+*10, 3C-12n/aIDCSP (8) ... IDCSP (14) / GGTS 226 Aug 1966CCTitan-3CFailureNN O#\OZ K *&(NPjrt11, 3B-266086KH-8 2 (OPS 4096)28 Sep 1966VaTitan-3B Agena-DN OpNPN\O#d OZ K *&(€12, 3C-966099B: OV-4 1RC: OV-1 6D: OV-4 1TOV-4 3Gemini B3 Nov 1966CCTitan-3CGemini B was on a suborbital orbitN OpO#\OZ K *&(NPjrt13, 3B-366113KH-8 3 (OPS 8968)14 Dec 1966VaTitan-3B Agena-D C\OyO#\OZ K *(*HJdln14, 3C-1367003IDCSP 8 to 1518 Jan 1967CCTitan-3C?pO~O#\~OZ K * 02LTVz15, 3B-4?KH-8 424 Mar 1967VaTitan-3B Agena-DJyOO#hOZ K *"$46PXZ~+*16, 3B-5n/aKH-8 526 Apr 1967VaTitan-3B Agena-DFailureCy~OO#dOZ K *(*Ѐ؀ڀ17, 3C-1067040A: Vela 7B: Vela 8C: ERS 18D: OV-5 3 (ERS 20)E: OV-5 1 (ERS 27)28 Apr 1967CCTitan-3CNOO#\OZ K *&(NPjrt18, 3B-867064KH-8 6 (OPS 4282)20 Jun 1967VaTitan-3B Agena-D%WO O#lOZ K *( *öUrt19, 3C-1467066IDCSP 16 to 19E: LES 5F: Dodge1 Jul 1967CCTitan-3C CO O#\OZ K *&(8:T\^20, 3B-967079KH-8 716 Aug 1967VaTitan-3B Agena-D D O# O#\OZ K *(*:<V^`21, 3B-1067090KH-8 819 Sep 1967VaTitan-3B Agena-D? O( O#\~OZ K * 02LTVz22, 3B-11KH-8 925 Oct 1967VaTitan-3B Agena-D?# O- O#\~OZ K * 24LTVz23, 3B-12KH-8 105 Dec 1967VaTitan-3B Agena-D@( O3O#\OZ K * 24NVX|24, 3B-13KH-8 1118 Jan 1968VaTitan-3B Agena-D@- O9O#\OZ K * 24NVX|25, 3B-14KH-8 1213 Mar 1968VaTitan-3B Agena-D@3OK@O#\OZ K * 24NVX|9OK@OpN26, 3B-15KH-8 1317 Apr 1968VaTitan-3B Agena-D?9OPAO#\~OZ K * 24LTVz27, 3B-16KH-8 145 Jun 1968VaTitan-3B Agena-D DK@OZBO#\OZ K *(*JLfnp28, 3C-1668050IDCSP 19 to 2613 Jun 1968CCTitan-3CAPAOaCO#\OZ K * 24LTV~29, 3B-17KH-8 156 Aug 1968VaTitan-3B Agena-D ?BZBOiDO#\OZ K * 24NVX30, 3B-18KH-8 1610 Sep 1968VaTitan-3B Agena-D ?4_aCOEO#zOZ K *&.( ĶU31, 3C-568081A: OV 2-5B: OV-5 2C: OV-5 4D: LES 626 Sep 1968CCTitan-3CAiDOFO#\OZ K * 24LTV~32, 3B-19KH-8 176 Nov 1968VaTitan-3B Agena-D ?AEOGO#\OZ K * 24LTV~33, 3B-20KH-8 184 Dec 1968VaTitan-3B Agena-D ??FOHO#\~OZ K *02LTVz34, 3B-6KH-8 1922 Jan 1969VaTitan-3B Agena-D=GOIO#\zOZ K *(*>@X`bv35, 3C-1769013TACSAT 19 Feb 1969CCTitan-3C>HOJO#\|OZ K *02JRTx36, 3B-7KH-8 204 Mar 1969VaTitan-3B Agena-DBIOKO#\OZ K * 24NVX37, 3B-21KH-8 2115 Apr 1969VaTitan-3B Agena-D ?2hJOLO#dOZ K *(*̀38, 3C-1569046A: OV-5 5B: OV-5 6C: OV-5 9D: Vela 9E: Vela 1023 May 1969CCTitan-3CAKOMO#\OZ K * 24LTV~39, 3B-22KH-8 223 Jun 1969VaTitan-3B Agena-D ?BLOOO#\OZ K * 24NVX40, 3B-23KH-8 2322 Aug 1969VaTitan-3B Agena-D ?BMOO#\OZ K * 24NVX41, 3B-24KH-8 2424 Oct 1969VaTitan-3B AgenaOOOpN-D ?BOOO#\OZ K * 24NVX42, 3B-25KH-8 2514 Jan 1970VaTitan-3B Agena-D ?JO-O#^OZ K *(*XZrz|43, 3C-1870027A: Vela 11B: Vela 128 Apr 1970CCTitan-3CBO5O#\OZ K * 24NVX44, 3B-26KH-8 2615 Apr 1970VaTitan-3B Agena-D ?B-O=O#\OZ K * 24NVX45, 3B-27KH-8 2725 Jun 1970VaTitan-3B Agena-D ?B5OEO#\OZ K * 24NVX46, 3B-28KH-8 2818 Aug 1970VaTitan-3B Agena-D ?B=OMO#\OZ K * 24NVX47, 3B-29KH-8 2923 Oct 1970VaTitan-3B Agena-D ?OEOhO#hOZ K *(*8:RZ\x+*48, 3C-1970093DSP 16 Nov 1970CCTitan-3(23)CPartial failureBMOpO#\OZ K * 24NVX49, 3B-30KH-8 3021 Jan 1971VaTitan-3B Agena-D ?LhOO#\OZ K *(*BD^fh50, 3B-3671021Jumpseat 121 Mar 1971VaTitan-3(33)B Agena-DBpOO#\OZ K * 24NVX51, 3B-31KH-8 3122 Apr 1971VaTitan-3B Agena-D ?>OO#\|OZ K *(*8:RZ\x52, 3C-2071039DSP 25 May 1971CCTitan-3(23)C6OO#\lOZ K *.0JRTh53, 3D-1KH-9 115 Jun 1971VaTitan-3DBOO#\OZ K * 24NVX54, 3B-32KH-8 3212 Aug 1971VaTitan-3B Agena-D ?BOO#\OZ K * 24NVX55, 3B-33KH-8 3323 Oct 1971VaTitan-3B Agena-D ?)VOÏO#vOZ K *(**y,dMz,dMhj56, 3C-2171095A: DSCS 2-01B: DSCS-2 023 Nov 1971CCTitan-3(23)CIOO#\OZ K ÏOOpN*TVpxz57, 3D-2KH-9 2 / Subsat Ferret 2820 Jan 1972VaTitan-3DSÏOO#hOZ K *$&>@Zbd+*58, 3B-37n/aJumpseat 216 Feb 1972VaTitan-3(33)B Agena-DFailure9OO#\rOZ K * .0HPRn59, 3C-22DSP 31 Mar 1972CCTitan-3(23)CBOO#\OZ K * 24NVX60, 3B-34KH-8 3417 Mar 1972VaTitan-3B Agena-D ?KOO#hOZ K * 24NVX+*61, 3B-35KH-8 3520 May 1972VaTitan-3B Agena-D ?FailureHO)O#\OZ K *TVnvx62, 3D-5KH-9 3 / Subsat Ferret 297 Jul 1972VaTitan-3DAO0O#\OZ K * 24LTV~63, 3B-39KH-8 361 Sep 1972VaTitan-3B Agena-D ?I)O?O#\OZ K *TVpxz64, 3D-3KH-9 4 / Subsat Ferret 3010 Oct 1972VaTitan-3DB0OGO#\OZ K * 24NVX65, 3B-40KH-8 3721 Dec 1972VaTitan-3B Agena-D ?5?OBO#\jOZ K *.0HPRf66, 3D-6KH-9 59 Mar 1973VaTitan-3DBGOJO#\OZ K * 24NVX67, 3B-41KH-8 3816 May 1973VaTitan-3B Agena-D ?:BOJO#\tOZ K * .0JRTp68, 3C-24DSP 412 Jun 1973CCTitan-3(23)CKJOaO#hOZ K * 24NVX+*69, 3B-43KH-8 3926 Jun 1973VaTitan-3B Agena-D ?Failure6JO]O#\lOZ K *.0JRTh70, 3D-7KH-9 613 Jul 1973VaTitan-3D GaOjO#\OZ K * 8:T\^71, 3B-38Jumpseat 321 Aug 1973VaTitan-3(33)B Agena-DB]O~P#\OZ K * 24jO~PpNNVX72, 3B-42KH-8 4027 Sep 1973VaTitan-3B Agena-D ?"\jOP#\OZ K *z|73, 3D-8KH-9 7 / Subsat Ferret 31 / Subsat Ferret 3210 Nov 1973VaTitan-3D*W~PP#vOZ K *(**{,dM|,dMhj74, 3C-2673100A: DSCS 2-03B: DSCS 2-0413 Dec 1973CCTitan-3(23)CXPP#\OZ K *$.0XZt|~75, 3E-1/ TC-1n/aSphinx / Viking SD12 Feb 1974CCTitan-3E Centaur-D1TFBPP#\OZ K * 24NVX76, 3B-44KH-8 4113 Feb 1974VaTitan-3B Agena-D ?QPP#\OZ K *df77, 3D-9KH-9 8 / Subsat Ferret 33 / P73 710 Apr 1974VaTitan-3D APP#hOZ K *(*S<>X`b~78, 3C-2774039ATS 630 May 1974CCTitan-3(23)CAPP#\OZ K * 24LTV~79, 3B-45KH-8 426 Jun 1974VaTitan-3B Agena-D ?BP# P#\OZ K * 24NVX80, 3B-46KH-8 4314 Aug 1974VaTitan-3B Agena-D ?QP: P#\OZ K *df81, 3D-4KH-9 9 / Subsat Ferret 34 / P73 529 Oct 1974VaTitan-3DV# PV P#\OZ K *$24HJdln82, 3E-2/ TC-274097Helios 110 Dec 1974CCTitan-3E Centaur-D1T St-37E G: Pc P#\OZ K * 8:T\^83, 3B-50Jumpseat 410 Mar 1975VaTitan-3(34)B Agena-DBV Pk P#\OZ K * 24NVX84, 3B-48KH-8 4418 Apr 1975VaTitan-3B Agena-D ?Ahc PP#OZ K *(**},dM~,dMhj+*85, 3C-2575040A: DSCS 2-05B: DSCS 2-0620 May 1975CCTitan-3(23)CPartial failureJk PP#\OZ K * XZrz|86, 3D-10KH-9 10 / Subsat Ferret 358 Jun 1975VaTitan-3DOP@P#\OZ K P@PpN*$24HJdln87, 3E-4/ TC-475075Viking 120 Aug 1975CCTitan-3E Centaur-D1TNPAP#\OZ K *$24HJbjl88, 3E-3/ TC-375083Viking 29 Sep 1975CCTitan-3E Centaur-D1TA@PBP#\OZ K * 24LTV~89, 3B-47KH-8 459 Oct 1975VaTitan-3B Agena-D ?JAPDP#\OZ K * XZrz|90, 3D-13KH-9 11 / Subsat Ferret 364 Dec 1975VaTitan-3D:BPEP#\tOZ K * .0JRTp91, 3C-29DSP 514 Dec 1975CCTitan-3(23)CVDP$FP#\OZ K *$24HJdln92, 3E-5/ TC-576003Helios 215 Jan 1976CCTitan-3E Centaur-D1T St-37EPoEPtGP#OZ K *(F*ƶUǶU 4 4ڀ93, 3C-3076023A: LES 8B: LES 9C: Solrad 11AD: Solrad 11B15 Mar 1976CCTitan-3(23)CE$FPHP#bOZ K * 24NVX-94, 3B-52KH-8 4622 Mar 1976VaTitan-3(23)B Agena-D BtGPIP#bOZ K * .0HPR~-95, 3B-55SDS 12 Jun 1976VaTitan-3(34)B Agena-D;HPJP#bvOZ K * .0JRTp-96, 3C-28DSP 626 Jun 1976CCTitan-3(23)CSIPKP#bOZ K * hj-97, 3D-14KH-9 12 / Subsat Ferret 37 / P74 28 Jul 1976VaTitan-3D BJPLP#bOZ K * .0HPR~-98, 3B-56SDS 26 Aug 1976VaTitan-3(34)B Agena-DEKPMP#bOZ K * 24NVX-99, 3B-51KH-8 4715 Sep 1976VaTitan-3(24)B Agena-D'^LPNP#bOZ K * "|~-100, 3D-15KH-9 13 /Subsat Ferret 38 /Subsat Ferret 3919 Dec 1976VaTitan-3D;MP P#bvOZ K * "02JRTp-101, 3C-23DSP 76 Feb 1977CCTitan-3(23)CNP PpNFNPP#bOZ K * "46PXZ-102, 3B-54KH-8 4813 Mar 1977VaTitan-3(23)B Agena-D/Y PJP#|OZ K ***,,dM,dMjl-103, 3C-3277034A: DSCS 2-07B: DSCS 2-0812 May 1977CCTitan-3(23)C:PMP#btOZ K * "46PXZn-104, 3D-17KH-9 1427 Jun 1977VaTitan-3D!XJPnP#bOZ K *&*,XZt|~-105, 3E-7/ TC-7Voyager 2 [Star-37E]20 Aug 1977CCTitan-3E Centaur-D1T WMPP#bOZ K *&*,XZrz|-106, 3E-6/ TC-6Voyager 1 [Star-37E]5 Sep 1977CCTitan-3E Centaur-D1TFnPP#bOZ K * "46PXZ-107, 3B-58KH-8 4923 Sep 1977VaTitan-3(23)B Agena-DIPP#bOZ K * ":<V^`-108, 3B-49Jumpseat 525 Feb 1978VaTitan-3(34)B Agena-DMPňP#bOZ K * "Z\v~-109, 3D-20KH-9 15 / Subsat Ferret 4016 Mar 1978VaTitan-3D"VPP#hOZ K *&(TVpxz+*110, 3C-35n/aDSCS-2 9 / DSCS-2 1025 Mar 1978CCTitan-3(23)CFailureEňPP#hOZ K **,>DF`hj111, 3C-3378058Vortex 110 Jun 1978CCTitan-3(23)C9PP#\rOZ K * "46PXZn112, 3D-18KH-11 114 Jun 1978VaTitan-3DBPP#\OZ K * "02JRT113, 3B-57SDS 35 Aug 1978VaTitan-3(34)B Agena-D/YP.P#|OZ K ***,*dM*dMjl-114, 3C-3678113A: DSCS 2-11B: DSCS 2-1214 Dec 1978CCTitan-3(23)CMPDP#bOZ K * "Z\v~-115, 3D-21KH-11 2 / Subsat Ferret 4116 Mar 1979VaTitan-3DF.P_P#bOZ K * "46PXZDP_PpN-116, 3B-61KH-8 5028 May 1979VaTitan-3(24)B Agena-D<DPdP#bxOZ K * "02LTVr-117, 3C-31DSP 810 Jun 1979CCTitan-3(23)CE_PxP#nOZ K **,>DF^fh-118, 3C-3479086Vortex 21 Oct 1979CCTitan-3(23)C/YdPP#|OZ K ***,*dM*dMjl-119, 3C-3779098A: DSCS 2-13B: DSCS 2-1421 Nov 1979CCTitan-3(23)C9xPP#brOZ K * "46NVXl-120, 3D-19KH-11 37 Feb 1980VaTitan-3DMPP#bOZ K * "Z\v~-121, 3D-16KH-9 16 / Subsat Ferret 4218 Jun 1980VaTitan-3DIPP#bOZ K * ":<V^`-122, 3B-53Jumpseat 613 Dec 1980VaTitan-3(34)B Agena-DFPP#bOZ K * "46PXZ-123, 3B-59KH-8 5128 Feb 1981VaTitan-3(24)B Agena-D<PP#bxOZ K * "02LTVr-124, 3C-40DSP 916 Mar 1981CCTitan-3(23)C TPP#hOZ K * "02LTV+*125, 3B-60SDS 424 Apr 1981VaTitan-3(34)B Agena-DPartial failure8PP#\pOZ K * "46NVXl126, 3D-22KH-11 43 Sep 1981VaTitan-3DFPP#nOZ K **,>DF`hj-127, 3C-3981107Vortex 331 Oct 1981CCTitan-3(23)CUP6P#bOZ K * "RTnvx-128, 3B-62Indigo Test + 4 Subsat21 Jan 1982VaTitan-3(23)B Agena-D<P;P#bxOZ K * "24LTVr-129, 3C-38DSP 106 Mar 1982CCTitan-3(23)CM6PQP#bOZ K * "Z\v~-130, 3D-24KH-9 17 / Subsat Ferret 4311 May 1982VaTitan-3D@^;PQ#OZ K ***,*dM ceMjlQPQpN(FHbjl-136, 34D-1084009Vortex 431 Jan 1984CCTitan-34D TranstageEQQ#bOZ K *"$46PXZ-137, 34D-11DSP 1115 Apr 1984CCTitan-34D TranstageFQQ#bOZ K * "46PXZ-138, 3B-67KH-8 5317 Apr 1984VaTitan-3(24)B Agena-D;Q Q#bvOZ K * "46PXZp-139, 34D-4KH-9 1925 Jun 1984VaTitan-34D DQ# Q#bOZ K * "02LTV-140, 3B-64SDS 528 Aug 1984VaTitan-3(34)B Agena-D: Q& Q#btOZ K * "46NVXn-141, 34D-6KH-11 64 Dec 1984VaTitan-34DM# QB Q#nOZ K *,.@c鉂DF`hj-142, 34D-1384129DSP F1222 Dec 1984CCTitan-34D Transtage C& QN Q#bOZ K * "02JRT-143, 3B-69SDS 68 Feb 1985VaTitan-3(34)B Agena-DCB Q]Q#hOZ K * "46PXZp+*144, 34D-7KH-11 728 Aug 1985VaTitan-34DFailureCN QlQ#hOZ K * "46PXZp+*145, 34D-9KH-9 2018 Apr 1986VaTitan-34DFailure C]Q@Q#\OZ K * "02lQ@QpNLTV146, 3B-66SDS 712 Feb 1987VaTitan-3(34)B Agena-D<lQAQ#bxOZ K *"$68RZ\r-147, 34D-15KH-11 826 Oct 1987VaTitan-34DL@QBQ#nOZ K **,c鉂BD^fh-148, 34D-887097DSP 3-129 Nov 1987CCTitan-34D Transtage&TAQCQ#tOZ K **,>DF^fh+*149, 34D-388077Vortex 52 Sep 1988CCTitan-34D TranstageFailure?BQDQ#\~OZ K *,.@BZbdz150, 34D-1488099KH-11 96 Nov 1988VaTitan-34DNCQEQ#nOZ K *,.>FHbjl-151, 34D-1689035Vortex 610 May 1989CCTitan-34D Transtage5_DQGQ#|OZ K ***,*dMceMjl-152, 34D-289069A: DSCS 2-16B: DSCS 3-044 Sep 1989CCTitan-34D TranstageU~EQsHQ#~OZ K *(** ȉㇺ2df~-153, CT-190001A: Skynet 4AB: JCSat 21 Jan 1990CCCommercial-Titan-3Skynet 4A: PAM-D2JCSat 2: Orbus-7S>kGQIQ#vOZ K *(* ĉJLfnp+*154, CT-290021Intelsat 60314 Mar 1990CCCommercial-Titan-3Partial failure[Orbus-21S]%YsHQJQ#hOZ K *(* ĉJLfnp155, CT-390056Intelsat 60423 Jun 1990CCCommercial-Titan-3[Orbus-21S] WIQKQ#bOZ K *(*HJdln-156, CT-492063Mars Observer25 Sep 1992CCCommercial-Titan-3[TOS-21H]&JQLQ# 8KQTLQ1(%fTLQLQNRTitan 4DLQLQ5 : F" Titan 4e4TLQLQ1 2h 㭄؉>ɉby Jean-Jacques Serralisting by Gunter KrebsELQNQ2 2'㯃4\l|~#Launch idPayloadLaunch DateSiteTypeStatus/Comment (orbit in perigee x apogee x inclination x period) >FQQ#h|OZ K  " c鉂8:Tdfx1, K189046DSP 3-214 Jun 1989C LC41402 IUS:QQ#htOZ K  ""W~8:Tdfp2, K490050NOSS 1208 Jun 1990C LC41405@QΈQ#tOZ K  "" c鉀:<Xhj|3, K690095DSP 3-313 Nov 1990C LC41402 IUS@QQ#tOZ K  ""-@B^pr|4, K591017Lacrosse 208 Mar 1991V SLC4E404=ΈQQ#tzOZ K  ""#W~:<Xjlv5, K891076NOSS 1308 Nov 1991V SLC4E403AQQ#tOZ K  ""҉:<Xjl~6, K392083KH 12-228 Nov 1992V SLC4E404 TPACkQEQ#OZ K " $W~8:l~7, K11n/aNOSS 142 Aug 1993 at 19:59 UTV SLC4E403Failure: exploded after 1 min 41 s0^QuQ#tOZ K ""$DFx8, K1094009Milstar 1-17 Feb 1994 at 21:47 UTC LC40401 Centaur-G' (TC12)+YEQQ#tOZ K  ""j뉀:<n~9, K794026USA 1033 May 1994 at 15:55 UTC LC41401 Centaur-G' (TC10)-[uQQ#tOZ K QQLQ""$j뉀<>r10, K994054USA 10527 Aug 1994 at 08:58 UTC LC41401 Centaur-G' (TC11)&TQQ#tOZ K $"& c鉀>@t11, K1494084DSP 3-522 Dec 1994 at 22:19 UTC LC40402 (K14) IUS4bQ3Q#tOZ K $"&5i뉀>@t12, K2395022USA 11014 May 1995 at 13:45 UTC LC40401 (K23) Centaur-G' (TC17)FtQyQ#tOZ K $"&-i뉀>@t13, K1995034USA 11210 Jul 1995 at 12:38 UTC LC41401 (K19) Centaur-G' (TC8)26 m payload shroud9g3QQ#tOZ K $"&FH|ʀ14, K2195060Milstar 1-206 Nov 1995 at 05:15 UTC LC40401 (K21) Centaur-G' (TC-13)$RyQQ#tOZ K $&҉<pr15, K1595066KH 12-305 Dec 1995 at 21:18 UTV SLC4E404 (K15) ?mQQ#tOZ K $"&3i뉀>rt16, K1696026USA 11824 Apr 1996 at 23:37 UTC LC41401 Centaur (TC-15)23 m payload shroudKQ2Q#tOZ K $"&%W~>rt17, K2296029NOSS 1512 May 1996 at 21:32 UTV SLC4E403DQHQ#tOZ K ""$[i뉀<prxz18, K296038USA 12503 Jul 1996 at 00:31 UTC405K2QeQ#tOZ K $"&҉>rt19, K1396072KH 12-420 Dec 1996 at 06:44 UTV SLC4E403!OHQQ#tOZ K $"& c鉀>rt20, K2497008DSP 3-623 Feb 1997 at 20:20 UTC LC40402B IUS/ceQQ#hOZ K $&N21, B3397061Cassini & Huygens15 Oct 1997 at 08:43 UTC LC40401Bpayload: 5650 kgMQQ#hOZ K $&-Btv22, A1897064Lacrosse 324 Oct 1997 at 02:32 UTV SLC4E403AJQ R#tOZ K $"&i뉀>pr23, A1797068USA 1368 Nov 1997 at 02:05 UTC LC41401AQ RLQJQ(R#tOZ K $"&i뉀>pr24, K2598029USA 1399 May 1998 at 01:38 UTC LC40401B& RNR# H(RR1JwR@RRVanguard launch vehicleENRR5 :" " Vanguarde4R@R1 2h 㭄؉>ɉby Jean-Jacques Serralisting by Gunter KrebsH!RR' B Origin: sounding rocket Vikingo@RR& In 1946 the US Navy's NRL (Naval Research Laboratory) launched the study of a high performance sounding rocket named HASR-2 (High Altitude Sounding Rocket) to replace the V2s when there would be no more left. This leaded th the developement of the Neptune rocket, later renamed Viking. The Glenn L. Martin company was contacted to built 10 rockets, 4 were reordered later.The Viking propulsion was granted to Reaction Motors which already produced the Bell X1 rocket-plane. The new motor was feed with alcohol and liquid oxygen by turbopomps. It provided 91.5 kN thrust. Names XLR-10 this motor was a high technology one at the time because it used regenerating cooling system and a deployable nozzle. The rocket also had integral tanks to lighten the structure and a 3-axis stabilization with little nozzles around the it to orient it after the shutdown of the main engine.J%RgR% KThere are 2 generations in the Viking series: the models 1 to 7 that were 81 cm diameter and models 8 to 14 (shorter) that were 114 cm diameter. The heights were ranging from 14.8 m to 12.8 m and the takeoff weights were between 4.37 tons and 6.81 tons. Between May 1949 and May 1959 only one failure occured with Viking-8. All Vikings were launched from White Sands except Viking-4 which was launched from the deck of USS Norton Sound and the 2 last ones which where used as test vehicles for the Vanguard program, launched from Cape Canaveral.2 RR' O Vanguard@gR R& 5In July 1955 the United States announced their intention of launching small earth artificial satellites as their contribution to the International Geophysical Year of 1957-1958. Two months later the Vanguard project was selected to launch those satellites.The project was granted to the Glenn L. Martin Company which was to use a modified Viking rocket as first stage. In fact the differences were important: the diameter stayed the same but the length was extended to 13.4 m and the propulsion system was changed. This new motor built by General Electric was derived from the Hermes A-3B project. Named X-405 it used kerosene and LOX, had a deployable nozzle and provided 120 kN (A-3B: 100 kN) during 145 seconds. The X-405 had a re-generated cooling system and was powered by turbopomps.RR%  The second stage of Vanguard was designed by Aerojet General. It was an extrapolation of the Aerobee Hi: the diameter was extended to 81 cm. The AJ-10 motor had a deployable nozzle and its thrust was then 33 kN with a lifetime of 120 s. It was feeded with a mix a stockable propellant helium-pressurized: UDMH (Unsymmetrical DiMethyl Hydrazine) and WIFNA (White Inhibited Fuming Nitric Acid). This second stage also contained the flight control equipement and the 3rd stage table rotator. During the propulsed flight phases the rocket was controled with the nozzles and during the balistic phase after the 2nd stage shutdown by helium jets.  R@R' The third stage was equipped with a 33-KS-2800 solid booster from Grand Central Rocket Company which provided 12.5 kN thrust during 33 seconds. It was replaced for the last launch by a lighter motor developped by Alleghany Ballistics Laboratories. This glass fiber reinforced platic structure X-248 Altair engine provided 13.8 kN. FinallR@RNRy the Vanguard rocket weighed 21.6 m high with the cap. The payload was only of a few kilograms in the first version and reached 20 kg with the last model.`5R CR+ $k~After 2 test flights with a Viking first stage (TV-0 & TV-1) in Dec 1956 & May 1957 the launch of a Vanguard first stage with mockups of the top stages (TV-2) occured in Oct 1957, a few days after the launch of Sputnik 01. The successful Russian launch cause the program to be accelerated despite reliability questions. Two failures (TV-3 & TV-3A) occured before the success of Vanguard 1 in March 1958. Four failures (TV-5 & SLV-1 to -3) occured before a success in Feb 1959. The third and last success occured in Sep 1959 after 2 more failures (SLV-5 & -6).p@RDRC T=vp+㰭=Hg'KThree success out of 11 flights was not a good score especially because the Russian failures were keep secret. Worth to be noted the Vanguard top stages were used to design the Able (see Thor Able) and then the Delta (see Thor Delta) which were very reliable. Also the stages derived from Altair were used on several launchers (Thor, Atlas, Scout, etc.).; CRDR' ( Vanguard launchesF|DR=FR#dzY K u  $&<>\ln#Launch idPayloadLaunch DateSiteStatus/Comment (orbit in perigee x apogee x inclination x period) NDRFGR#FzY K u  "<>V\^1, TV-3FTOVanguard 1A6 Dec 1957CFailure: exploded after 2 sU=FRVHR#FzY K u $&@BZ`b2, TV-3BUFTOVanguard 1B5 Feb 1958CFailure: control lost after 57 s5FGRFIR#FjzY K u $&kBD^df3, TV-458002Vanguard 117 Mar 1958CWVHRXJR#FzY K u  "<>X^`4, TV-5FTOVanguard 2A28 Apr 1958CFailure: 3rd stage failed to ignite<FIROKR#FxzY K u "$>@Z`b5, SLV-1FTOVanguard 2B27 May 1958CFailure<XJRFLR#FxzY K u "$>@Z`b6, SLV-2FTOVanguard 2C26 Jun 1958CFailure<OKR=MR#FxzY K u "$>@Z`b7, SLV-3FTOVanguard 2D29 Sep 1958CFailure6FLR.NR#FlzY K u &(kDF`fh8, SLV-459001Vanguard 217 Feb 1959C<=MR%OR#FxzY K u "$>@Z`b9, SLV-5FTOVanguard 3A13 Apr 1959CFailure=.NR)R#FzzY K u $&@B\bd10, SLV-6FTOVanguard 3B%OR)RNR22 Jun 1959CFailure5t%OR^R#RzY K u *,kHJdjl11, TV-4BU59007Vanguard 318 Sep 1959CPartial failure: 3rd stage failed to separate from payload&)RR# 4^RR1xM,R \ l |~ #Launch idPayloadLaunch DateSiteTypeStatus/Comment (orbit in perigee x apogee x inclination x period))WRR#t4\N\ o\D*,\bdh1FTOSCD 2A2 Nov 1997 at 12:25 UTAFailure: 1 1-stage motor failedhBRyR& $Notes: A: Alcantara, Maranhao state Brazil (217' S, 4423' W)6RR1%wZRVR~ISZenitB yRR5 : " Zenite4RVR1 2h 㭄؉>ɉby Jean-Jacques Serralisting by Gunter Krebs:RR$ -The Zenit rockets are not derived from ballistic missiles as most of the NPO Yuzhnoye (Dniepropetrovsk, Ukraine) achievements. There ware designed from the start for space missions. The first stage of the Zenits is used as booster for the Energia launcher (known as Zenit-1).G VRR' @ Two-stage Zenit-2 (J-1/SL-16)0 RR& The Zenit 2 (11K77) has a constant diameter of 3.9 m. It is 57 m high and weighs 460 tons at liftoff with a 15-ton payload. Both stages use liquid propellant: kerosene-LOXThe first stage is equipped with a RD-170/171 motor (Glouchko, NPO Energomash) with 4 combustion chambers. It provides 7259 kN thrust at ground level and 7911 kN is vaccum (ISp = 337 s). The RD-171 version of the motor can be oriented on 2 axis, the RD-170 Energia on 1 axis. The stage contains 318.8 tons propellant and burns during 140 seconds. RR) The second stage features an RD-120 (Glouchko, NPO Energomash) with single fixed nozzle. It is joined with 4 vernier motors (NPO Yuzhnoye) for pilotage. It provides 834 kN thrust (ISp = 350 s) and can function during upto 315 seconds to match the mission's need.Zenit 2 is intended for LEO and MEO upto 1500 km altitude. The maximum payload weight is 13.74 tons in circular 200 km orbit 51 or 11.38 tons in sun-synchronous 200 km/99 from Tyuratam.Until now it has launched:YRlRV z qiY뉂 qi ㉓g - MEO: SIGINT (Cosmos series) and remote sensing (Resurs O)- LEO: Kuban photographic reconnaissance satellites (Cosmos series)Possible evolutions:- 3-stage version with a Block-DM of Proton- 3 or 4 stage version with NTO-UDMH propellant8RR' " Zenit launches8nlRR#d4]2   $& <> ^ np#Launch idPayloadLaunch date TypeStatus (orbit in perigee x apogee x inc. x period)6RR#@l4]2* 68RTf"1n/aR&D suborbital13 Apr 1985Zenit-2'oRR#@4]2* :<VXj"285053R&D suborbital21 Jun 1985Zenit-2intended to be suborbital but some debris reached orbitCR S#L4]2* _剂PRln"385097Cosmos 1697 [Tselina-2]22 Oct 1985Zenit-2R SyR+jR7S#R4]2* _剂PRln#"485121Cosmos 1714 [Tselina-2]28 Dec 1985Zenit-2Failure: second stage failed to ignite5 S$S#@j4]2* 46PRd"586056Cosmos 176730 Jul 1986Zenit-257SS#@j4]2* 46PRd"686080Cosmos 178622 Oct 1986Zenit-25$SS#@j4]2* 46PRd"787016Cosmos 182014 Feb 1987Zenit-2CSS#L4]2* _剂PRln"887027Cosmos 1833 [Tselina-2]18 Mar 1987Zenit-2CSS#L4]2* _剂PRln"987041Cosmos 1844 [Tselina-2]13 May 1987Zenit-25SS#@j4]2* 68PRd"1087065Cosmos 18711 Aug 1987Zenit-26SS#@l4]2* 68RTf"1187071Cosmos 187328 Aug 1987Zenit-2DSS#L4]2* _剂RTnp"1288039Cosmos 1943 [Tselina-2]15 May 1988Zenit-28S S#Lp4]2* (w:<VXj"1388102Cosmos 198023 Nov 1988Zenit-2DS S#L4]2* _剂RTnp"1490046Cosmos 2082 [Tselina-2]22 May 1990Zenit-25n S S#^4]2* _剂:<TV(h#""15n/a[Tselina-2 ?]4 Oct 1990Zenit-2Failure: first stage engine exploded after 3 seconds Y S* S#^4]2* _剂:<VX(j#""16n/a[Tselina-2 ?]30 Aug 1991Zenit-2Failure: second stage exploded"[ SLS#^4]2* _剂:<TV(h#""17n/a[Tselina-2 ?]5 Feb 1992Zenit-2Failure: second stage malfunction8* SBS#Lp4]2* +x:<VXj"1892076Cosmos 221917 Nov 1992Zenit-2DLSP@S#L4]2* _剂RTnp"BSP@SyR1992093Cosmos 2227 [Tselina-2]25 Dec 1992Zenit-28BSFAS#Lp4]2* ,x:<VXj"2093016Cosmos 223726 Mar 1993Zenit-28P@SLVCastor 4 (TX526)9.071.0210.5342853.9:qSS#ڀt(<HVhCastor 4A (TX780)8.09-9201.0211.58436-47653.12'SS#ڀd(4@NXCastor 4B (TX859)8.981.0211.4842960.9{<S$S? Ly+#*pJFrom 1963 on, the Thor first-stage-based launchers were equipped with Castor solid boosters to get the TAT (Thrust Augmented Thor). The TAT Agena was launched in 1963, the TAT Delta (or TAD) in 1964. Those Castor-1 & Castor-2 boosters were then used by groups of 3, 6 (Delta M6) and fS$S(Sinally 9 (Delta 900). The last models were used from 1975 on by the Japanese N1, N2 and H1 rockets.The boosters of Sergeant missiles are still used by OSC for Starbird (targets for the ERINT program), LCLV (Low Cost Launch Vehicle) and Storm (targets for the THAAD program).7S[S'  O Castor 4 & 4Ag)$SS> JSpp㰭=HxAfter 1975, when the only Thor first stage-based was the Delta (3900 series) the Castor-2 were replaced by Castor-4 (TX526) of 1.02 m diameter that we herited from the Athena-H sounding rocket. In 1989 an enhanced version was introduced on the Delta 2 (6900 series): Castor-4A (TX780) weighing 11.6 tons. Two pairs of Castor-4A boosters also equip the Atlas 2 (2AS version) since 1993.The light launcher Conestoga was designed from associated Castor-4. The most powerful version, Conestoga 1620, is made of 6 Castor-4 (4 Castor-4B with deployable nozzle and 2 Castor-4A with fixed nozzle) surrounding a Castor-4B. Four Castors are fired at launch time (1st stage), 2 are ignited then (2nd stage) and the central Castor-4 acts as the third stage. The top stage is a Star-48, also built by Thiokol."[SS% The Castor-4A boosters are also used by OSC for Prospector sounding rockets since 1991. The Maxus rocket (German & Swedish) is the largest sounding rocket fired from Europe (Kiruna). It is also made of a Castor-4B; with 12.3 tons and 500 kg payload.7SS'   Castor 120 GTSS8 >a㻦ʼnGKTbnW"The Castor-120 is a large solid fuel booster derived from the MX Peacekeeper (TU 903) missile. This booster is 8.89 m long and 2.34 m diameter. It weighs about 54 tons. Castor-120 was modified to provide a smaller acceleration than the TU 903: 1546 kN (in vacuum) during 86 seconds.Two light launchers are based on it: Taurus from OSC (with the 3 Hercules stages of Pegasus) and Athena from LM (with an Orbus 21 UTC/CSD).CSFS1LoFSSI TCentaur top stagesOSS5 :6 " Centaur top stagesDFSS* $4 㭄؉by Jean-Jacques Serra:SS' &O Centaur on AtlasX.SkS* "]㰭=HThe Centaur top-stage was the first cryogenic rocket stage. The Pratt & Whitney RL10 engine consuming liquid oxygen and hydrogen had a long and difficult development. Its design started in 1958. It first flew in 1962 but didn't launch a real payload before 1966. The Centaur stage was designed to be used by Atlas. It was 3.05 m in diameter and 9.1 m in length. In its operational version it was equipped with two RL10 A-3-3 engines with a thrust of 66.7 kN each. It carried 13.8 tons propellant and could burn during 450 seconds with several ignitions.NSSI ` yjK\K\㰭=HCIxyjIn the late-70ies the Atlas Centaur program was to be abandonned since NASA had decided to transfer all launches to the Shuttle. In fact STS was less available than expected and the Atlas launch program was resumed (with the help of Intelsat finances) with a simplified motor. On the RL10 A-3-3A (73.4 kN thrust) the turbopump feeding was replaced by a pressurized tank system. This new Centaur was first launched in 1984 with an Atlas-G (streched by 2 meters). The GTO capacity then reached 2.3 tons.jkSrTC Tyjyjyjyj_ 0In 1987 the augmented Atlas Centaur was selected by the USAF as the MLV2 standard launcher. This new launcher is refered to as Atlas-2. The first stage was streched by 2.7 m and the second stage by 0.9 m. This new Centaur takes 16.8 tons of propellant and can burn up to 473 seconds. Atlas-2A is different by its second stage RL10 A-4 engines with deployable nozzle. Atlas-2AS is still more powerful. It is made from Atlas-2A to which two pairs of Castor-4A boosters are added. Each pair ignites one afteSrTSr the other. Thus GTO capacity raises to 2.8, 3.1 and 3.7 tons respectively for Atlas 2, 2A and 2AS.&ST# R+rTT' V Evolution of Centaur's propulsion system dTT#    @ v  DesignationFirst launchMain engine Thrust (kN)Main engineSI (sec.)Applications%TT#J $0:<RL10 A-1196266.7425Tests/TaT#^ (4>@RL10 A-3-1196366.7431Atlas Centaur/TT#^ (4>@RL10 A-3-3196666.7444Atlas Centaur/aTT#^ *6@BRL10 A-3-3A198473.4446Atlas-1 & -2/TT#^ $0:<RL10 A-4199192.6449Atlas-2A & -2AS~YTT% Statistics: the RL-10 motor made its 100th flight on the top stage Centaur of AC-114:TJT' &O Centaur on Titan*Tt T> J^]K\K\zBetween 1974 and 1977, seven Centaur were used as top stages for Titan 3 rockets, designated as Titan 3E with no major transformation. In this configuration the Centaur was placed into the cap (4.1 m diameter) which provided the thermic protection. Those launchers were devoted to US and German probles and could send 3.6 tons to Mars or Venus.In 1983 an agreement between NASA and USAF was reached to finance the development of a stage derived from Centaur to launch military satellites and probes from the Shuttle. This new cryogenic stage was a wide body of the Centaur to optimize the volume into the Shuttle's bay. The same motors remained so as the 3.05 m diamater liquid oxygen tank while the hydrogen tank was enhanced to 4.3 m diameter. Two versions of this new stage were developped: Centaur G of 6.1 m long for the USAF and a longer version named Centaur G-prime of 9.1 m long for NASA. After the Challenger accident usage of a cryogenic stage was prohibited for security reasons.JTI T1 0I^]^]The Centaur G-prime was then adapted to the Titan 4. This version is 4.5 m diameter and about 9 m long. It weighs 26 tons including 23 tons propellant. The motors are RL10-3-3A of 73.4 kN which can operate for up to 617 seconds. The Titan 4 with Centaur top stage is designated Titan 401. It can orbit 4.5 tons in GEO. An enhanced version with Hercules SRMU boosters will enable to place 5.8 tons on such orbits.4t T} T1 } T T(GTIUSKI T T5 :. " IUS top stagesD} T T* $4 㭄؉by Jean-Jacques Serra( T4T2 2K\ELAt first called Interim Upper Stage since it was devoted to fill the gap until the Space Tug shuttle became available, it became the Intertial Upper Stage when the project was stopped.Boeing developped the IUS from 1976 to 1981. The vehicle was aimed to act as a top stage for STS but also for the Titan military launchers. IUS is a 2-stage solid fuel vehicle featuring UTC/CSD boosters with deployable nozzles. The propellant load (HTPB) can be adjusted depending of the mission (up to -50%).f TBT3 4K\^]Note: a 3-stage version designed for NASA was dropped, but some of the launches did required a third stage (probes).The whole vehicle is 5.17 m high 4TBTI Tfor 2.9 m diameter and weighs 14.76 tons (Shuttle version) or 13.1 tons (Titan 34D version). The first stage (SRM 1) is 3.52 m long and 2.34 m diameter. It used the Orbus-21 motor (up to 9.7 tons propellant) providing a mean thrust of 196 kN during 154 seconds (ISp = 295 seconds). This motor is also used for the TOS perigee stages, and those (spinned) of Intelsat 6 series and for the LLV top stage. The second stage (SRM 2) is 2.1 m long and 1.61 m diameter. It features an Orbus motor (up to 2.75 tons of propellant) available in 2 versions: 6 or 6E depending on the presence of an extensible nozzle. It provides 80 kN during 103 seconds (ISp = 289 seconds or 303 seconds respectively for version 6 and 6E).4TCTL f K\ ^] ^]This 3-axis stabilized vehicle is very reliable. Its launch capacity to GEO is:- 2.27 tons from STS- 1.82 tons from Titan 34D- 2.36 tons or 2.86 tons from Titan 4 (CSD or Hercules boosters)3 BT(DT' O Titan IUS3CT[ET= H^]ą^]oSIUS was used twice on Titan 34D: in Octiber 1982 (1st IUS launch) and in September 1989 to launch DSCS satellites.The Titan 4 + IUS configuration is named Titan 402. It was introduced in June 1989 and is used to launch DSP satellites.1 (DTET' O STS IUSL[ET(GTP nz㯃4K\K\@ĘąoSIUS succeeded all its missions from the Shuttle except the first one (partial failure). After the Challenger accident the Centaur was banned from STS so IUS became the only available vehicle. Late 1995 the missions carried out by STS IUS were: TDRS, Magnum, DSCS, DSP and probes such as Magellan, Galileo, Ulysses9ETaGT1 aGTGTKKTMissionsE(GTGT5 :"NJ" Missions4 aGTGT'  ScientificGTHTT vS_BCV$?v߲-d;pl@0pjAstronomyGeodesyObservation of ionosphereObservation of high atmosphereObservation of magnetosphereObservation of meteoritesObservation of the SunBGTIT' 6O Observation of the EarthdHTIT7 >DVl/郉Meteorology: Geostationary satellitesMeteorology: LEO satellitesRemote sensing satellites<ITIT' * Telecommunications^.ITNJT0 0\€㓉Geostationary satellitesLEO satellites4 ITJT'  NavigationENJTJT* $6シNavigation satellites8JTJT' " Special topicsL#JTKKT) "Fㅯ\&Radioactive payload and debris: JTKT1(9KTKTTTAstronomyJKKTKT8 @&H̀" Astronomy=KT LT' ,O Gamma-ray astronomy+KT7LT$ 1961B LTyLT+ &.c`(014)Explorer 11+7LTLT$ 19647yLTLT& "Cosmos 0051+LTMT$ 1968]/LTcMT. ,^Cosmos 0208Cosmos 0251Cosmos 0264+MTMT$ 1972BcMTMT+ &.`(090)Explorer 48+MTMT$ 19737MT2NT& "Cosmos 0561+MT]NT$ 1975<2NTNT+ &"UXT(072)Cos B+]NTNT$ 1977>NTOT+ &&o5(049)Signe 3+NT-OT$ 1979=OTjOT+ &$ܰFI(082)Heao 3+-OTOT$ 1987>jOTOT+ &&(012)Astro C+OT T$ 1989OT TKKT=OTIT+ &$㲩)C(096)Granat+ TtT$ 1990<ITT+ &"hT(058)Gamma+tTۀT$ 1991:TT+ &p(027)GRO6ۀTKT' O IR astronomy+TvT$ 1983;KTT+ & v>UU(004)Iras+vT܁T$ 1989;TT+ & vMU(089)Cobe+܁TBT$ 1995:T|T+ &~(062)ISO>BTT' .O Multi-band astronomy+|TT$ 1989@T%T+ &*(062)Hipparcos+TPT$ 1990:%TT+ &~w(037)HST6PTT' O UV astronomy+TT$ 19647T"T& "Cosmos 0051+TMT$ 1966<"TT+ &"?vV(031)OAO 1+MTT$ 1968<TT+ &"?vV(110)OAO 2+TT$ 1971@T[T+ &*<(030)Tournesol+TT$ 1972T [TڅT4 8@4~W?vV(014)TD 1A(065)OAO 3+TT$ 1974:څT?T+ &D(070)ANS+TjT$ 1975;?TT+ & RKU(092)Aura+jTІT$ 1977:T T+ &~(012)IUE+ІT5T$ 1983= TrT+ &$"(020)Astron+5TT$ 1992;rT؇T+ & N}PU(031)EUVE+TT$ 1993=؇T@T+ &$b (062)Alexis+TkT$ 1995b.@T͈T4 8\kӸ~ZD(004)Spartan 204(048)Spartan 201-3+kTT$ 1997A͈T9T+ &,K&(018)Minisat 019TrT' $O X-ray astronomy+9TT$ 19687rTԉT& "Cosmos 0208+TT$ 1970BԉTAT+ &.`(107)Explorer 42+TlT$ 1972<ATT+ &"?vV(065)OAO 3+lTӊT$ 1974T T'T4 8@Dh$t(070)ANS(077)Ariel 5+ӊTRT$ 1975B'TT+ &.`(037)Explorer 53+RTT$ 1977=TT+ &$ڰFI(075)Heao 1+T'T$ 1978=TdT+ &$۰FI(103)Heao 2+'TT$ 1979X$dTT4 8H~Ni$t(014)Corsa B(047)Ariel 6+TT$ 1983W#TiT4 8Fr2(011)Astro B(051)Exosat+TT$ 1985BiT֍T+ &./̸~(048)Spartan 101+TT$ 1987>֍T?T+ &&(012)Astro C+TjT$ 1989=?TT+ &$㲩)C(096)Granat+jTҎT$ 1990T T&T4 8@r#WhT(049)Rosat(058)Gamma+ҎTQT$ 1993>&TT+ &&(011)Astro D+QTT$ 1995:T T+ &*(074)XTET TKKT+T7T$ 1996: TqT+ &(027)SAX97TT' $O Radio astronomy+qTT$ 1968BTT+ &.`(055)Explorer 38+TBT$ 1983ATT+ &,s(067)Prognoz 09+BTT$ 1991;TT+ & 4`U(050)Sara+TT$ 1997=TQT+ &$ӊH(005)Haruka<TT' *O External resourcesQTTT6 :#http://heasarc.gsfc.nasa.gov/http://cossc.gsfc.nasa.gov/code661/code661.htmlhttp://lheawww.gsfc.nasa.gov/docs/xray/branch/homepage.html8TT1 TTUGeodesyHTTT8 @"H̀" Geodesy+TT$ 1960=T Lue!&(052)Topex Poseidon(070)Lageos 2Cosmos 2226 (Geo-IK)+UzU$ 1993=OUU+ &$xټ(061)Stella+zUU$ 1994PU2U1 2>-l!&(078)Geo-IK 1 (Geo-IK)+U]U$ 19957 2UU+ &lJTGFZ 1+]UU$ 19976 UU+ &JiUZeya<U1U' *O External resources_8UU' phttp://www.dgfi.badw-muenchen.de/edc/satellites.htmlJ1UU19U4U%GUObservation of ionosphereZ"U4U8 @FH̀" Observation of ionosphere+U_U$ 1957A4UU+ &,~(001)Sputnik 01+_UU$ 1958UUfUF \``~`(001)Explorer 01(003)Explorer 03(004)Sputnik 03(005)Explorer 04+UU$ 1960BfUU+ &.`(014)Explorer 08+UU$ 1961@U>U+ &*㮎Y(015)Solrad 03+UiU$ 1962>UU UV z-d$tH6(008)Cosmos 0001Cosmos 0002Cosmos 0003(015)Ariel 1Cosmos 0007Cosmos 0008(049)Alouette 1Cosmos 0010Cosmos 0012+iU U$ 1963\U U U: DCosmos 0013Cosmos 0015Cosmos 0016Cosmos 0017Cosmos 0018Cosmos 0019+ UA U$ 1964 U2 Ub e$t````(006)Elektron 1(015)Ariel 2(038)Elektron 3(051)Explorer 20(064)Explorer 22(076)Explorer 25(086)Explorer 26+A U] U$ 1965r2 U' UX `㡄*㢄*`I6QU(031)Explorer 27(054)Proton 1(087)Proton 2(098)Explorer 31(098)Alouette 2(101)FR 1+] UR U$ 1966?' U U+ &(㣄*(060)Proton 3+R U U$ 1967Q" U U/ .Df$t(042)Ariel 3Cosmos 0163+ U8 U$ 1968Y U UJ db`ob㤄*(041)Esro 2B(66)Explorer 40(084)Esro 1A(103)Proton 4Cosmos 0255+8 UU$ 1969C UUA RTpbKU(009)Isis 1(083)Esro 1B(097)AzurIntercosmos 02+UU$ 1970`2UU. ,dCosmos 0321Intercosmos 03Cosmos 0381+U@U$ 1971YU @UJ dTeg$t2y`(024)Isis 2(080)ShinseiIntercosmos 05(109)Ariel 4(119)Aurole 1@U @UU+@U7@U$ 1972 @U AUR r[@=T#1kCosmos 0477Cosmos 0484Intercosmos 06Cosmos 0490(064)Denpa(092)Esro 4Intercosmos 08(100)Aeros 1+7@U7AU$ 1973l9 AUAU3 6r3y`Intercosmos 09Intercosmos 10(107)Aurole 2+7AUAU$ 1974X$AU&BU4 8HlmgS(055)Aeros 2(089)Intasat+AUQBU$ 1975H&BUBU< HzWG(014)TaiyoIntercosmos 13(033)AryabhataIntercosmos 14+QBUCU$ 1976R#BURCU/ .FrW(019)Ume 1Intercosmos 15+CU}CU$ 1977M#RCUCU* $FCosmos 0900Intercosmos 17+}CUCU$ 1978^*CUSDU4 8Tq2=ԉ(014)Exos A(099)Intercosmos 18+CU~DU$ 1979:SDUDU& (Intercosmos 19+~DUDU$ 1981MDUmEU= J)(v&4y`(070)Dynamics Explorer 2(093)Dong Fang Hong 09(094)Aurole 3+DUEU$ 19847mEUEU& "Cosmos 1543+EUEU$ 1986=EU7FU+ &$1ĉ(019)Viking+EUbFU$ 1989=7FUFU+ &$q2(016)Exos D+bFUFU$ 1994['FU%GU4 8N^_G(014)Coronas 1(027)Sross C2OFUtGU1B itGUGUUObservation of high atmosphere_'%GUGU8 @PH̀" Observation of high atmosphere+tGUGU$ 1958AGU?HU+ &,k(002)Vanguard 1+GUjHU$ 1959_+?HUHU4 8Vk`(001)Vanguard 2(009)Explorer 07+jHUHU$ 1961BHU6IU+ &.`(004)Explorer 09+HUaIU$ 1963`,6IUIU4 8Xi`k`(009)Explorer 17(053)Explorer 19+aIUIU$ 1964LIUyJUA Re$t`7(015)Ariel 2Cosmos 0049(076)Explorer 24(084)San Marco 1+IUJU$ 1966ByJUJU+ &.`(043)Explorer 32+JUKU$ 1967\(JUmKU4 8P7f$t(038)San Marco 2(042)Ariel 3+KUKU$ 1968h5mKULU3 6j`(066)Explorer 39Cosmos 0261Cosmos 0262+KU+LU$ 1969ELUpLU+ &4㹧ԉ(088)Intercosmos 01++LULU$ 1970EpLUMU< H&>8GV(017)Dial-WikaCosmos 0348Intercosmos 04(109)Pole+LUGMU$ 1971s6MUMU= Jl7JPPUg$t(036)San Marco 3(071)Eole(109)Ariel 4+GMUMU$ 1972:MUNU& (Intercosmos 07+MUJNU$ 1973BNUNU+ &.`(101)Explorer 51+JNUNU$ 1974n;NU%OU3 6v7(009)San Marco 4Intercosmos 11Intercosmos 12+NUPOU$ 1975`,%OUOU4 8X``(096)Explorer 54(107)Explorer 55+POUOU$ 1979V"OU=U4 8DOU=U%GUSAcى(013)AEM 2(017)Solwind+OUhU$ 1981:=UU+ &(100)SME+hÙU$ 1984T U!U4 8@q2UdPU(015)Exos C(108)ERBS+̀ULU$ 1988B!UU+ &.7(026)San Marco 5+LUU$ 1989\*UU2 4TPion 1Pion 2Pion 3Pion 4+U@U$ 1990QU҂UA Rsg&v&&v&(028)PegsatCRRES(081)Dong Fang Hong 31(081)Dong Fang Hong 32+@UU$ 1991;҂U8U+ & lUcU(063)UARS+UcU$ 1992@8UU* $,Pion 5Pion 6+cU΃U$ 1993DUU+ &2XD(023)Spartan 201-1+΃U=U$ 1994>U{U+ &&쉂(006)Bremsat+=UU$ 1996;{UU+ &  bU(037)TOMSMU.U1 .UUbUObservation of magnetosphere]%UU8 @LH̀" Observation of magnetosphere+.UU$ 1959BUU+ &.`(004)Explorer 06+U#U$ 1961BUeU+ &.d`(020)Explorer 12+#UU$ 1962BeU҆U+ &.f`(050)Explorer 14+UU$ 1963B҆U?U+ &.j`(046)Explorer 18+UjU$ 1964?ULU] }V`(006)Elektron 1(006)Elektron 2(038)Elektron 3(038)Elektron 4Cosmos 0041(054)OGO 1(060)Explorer 21+jUwU$ 1965Z&LUшU4 8L`}V(042)Explorer 28(081)OGO 2+wUU$ 1966<шU8U+ &"}V(049)OGO 3+UcU$ 1967<8UU+ &"}V(073)OGO 4+cUʉU$ 1968U!UU4 8B}VWI(014)OGO 5(109)Heos 1+ʉUJU$ 1969Z&UU4 8L}V`(051)OGO 6(053)Explorer 41+JUϊU$ 1971`,U/U4 8X``(019)Explorer 43(096)Explorer 45+ϊUZU$ 1972O/UUF \WI|s}s`(005)Heos 2(029)Prognoz 01(046)Prognoz 02(073)Explorer 47+ZUU$ 1973_+UyU4 8V~s`(009)Prognoz 03(078)Explorer 50+UU$ 1974ByUU+ &.`(040)Explorer 52+UU$ 1975W(UhU/ .PsIntercosmos 14(122)Prognoz 04+UU$ 1976AhUԍU+ &,s(112)Prognoz 05+UU$ 1977YԍUUJ d㯃\sUTVTCosmos 0900(029)ESA-Geos 1(093)Prognoz 06(102)ISEE 1(102)ISEE 2+U͎U$ 1978bU~UO n㰃\ ֋q2=ԉs(071)ESA-Geos 2(079)ISEE 3(087)Exos B(099)Intercosmos 18(101)Prognoz 07+͎UU$ 1980A~U U+ &,s(103)Prognoz 08U UU+U7U$ 1981O UU= J4y`(070)Dynamics Explorer 1(070)Dynamics Explorer 2(094)Aurole 3+7UU$ 1984x;UfU= JvZ=n(088)AMPTE CCE(088)AMPTE IRM(088)AMPTE UKS+UU$ 1986=fUU+ &$1ĉ(019)Viking+UU$ 1989g/U`U8 @^q2M$(016)Exos DAktivny(080)Magion 2+UU$ 1991?`UU+ &(N$(086)Magion 3+UU$ 1992o2UdU= Jd~稉؉1T(038)Sampex(044)Geotail(064)Freja+UU$ 1994{>dU U= J|&v&^|KU(010)Dong Fang Hong 38(014)Coronas 1(046)Apex+U5U$ 1995w: UU= Jt ~sO$(002)Astrid 1(039)Prognoz 11(039)Magion 4+5UU$ 1996EUbUF \QV"QUsP$(013)Polar(049)Fast(050)Prognoz 12(050)Magion 5JUU1WiUU,UObservation of meteoritesZ"bUU8 @FH̀" Observation of meteorites+U1U$ 1961BUsU+ &.e`(022)Explorer 13+1UU$ 1962BsUU+ &.h`(070)Explorer 16+U U$ 1964BUMU+ &.`(074)Explorer 23+ UxU$ 1965x;MUU= JvOPQ(009)Pegasus 1(039)Pegasus 2(060)Pegasus 3+xUU$ 1972BU]U+ &.`(061)Explorer 46+UU$ 1984;]UU+ & }XU(034)LDEF+UU$ 1994>U,U+ &&쉂(006)BremsatGUsU1Q 'sUUVObservation of the SunW,UU8 @@H̀" Observation of the Sun+sUU$ 1957AU6U+ &,~(002)Sputnik 02+UaU$ 1959A6UU+ &,k(007)Vanguard 3+aUU$ 1962<U U+ &"V(006)OSO 1+U4U$ 1965M UU/ .<V(007)OSO 2Solrad 08+4UU$ 1967f.UU8 @\VV(020)OSO 3Cosmos 166(100)OSO 4+U=U$ 1968c0UU3 6`㴎Y(17)Solrad 09Cosmos 215Cosmos 230+=UU$ 1969T UU4 8@VV(006)OSO 5(068)OSO 6+UJU$ 19706UU&  Cosmos 381+JUU$ 1971t7UU= Jn<2YV(030)Tournesol(058)Solrad 10(083)OSO 7+UJU$ 19726UU&  Cosmos 484+JUU$ 1975k.UU= J\zWVRKU(014)Taiyo(057)OSO 8(092)Aura+UAU$ 1976:U{U& (Intercosmos 16+AUU$ 1978={U V+ &$ ֋(079)ISEE 3U V,U+U7V$ 1980: VqV+ &(014)SMM+7VV$ 1981>qVV+ &&(017)Astro A+VV$ 1983AVFV+ &,s(067)Prognoz 09+VqV$ 1991>FVV+ &&©Hى(062)Solar A+qVV$ 1992=VV+ &$~稉(038)Sampex+VBV$ 1993DVV+ &2XD(023)Spartan 201-1+BVV$ 1994y<V*V= Jx^YDa͉(014)Coronas 1(059)Spartan 201-2(071)Wind 1+VUV$ 1995S%*VV. ,JZD(048)Spartan 201-3(065)Soho+UVV$ 1998<VV+ &"PW(020)TraceX'VgV1 gVVVMeteorological geostationary satellitesh0VV8 @bH̀" Meteorological geostationary satellites+gVV$ 1966<V6V+ &"S(110)ATS 1+VaV$ 1967<6VV+ &"S(111)ATS 3+aVV$ 1974<VV+ &".UW(033)SMS 1+V/V$ 1975V"VV4 8D/UW.(011)SMS 2(100)Goes 01+/VV$ 1977s6V#V= Jl.Tϵa(048)Goes 02(065)GMS 1(108)Meteosat 1+VNV$ 1978>#VV+ &&.(062)Goes 03+NVV$ 1980>VV+ &&.(074)Goes 04+V V$ 1981s6VV= Jl.еaT(049)Goes 05(057)Meteosat 2(076)GMS 2+ VV$ 1982Y%V V4 8JsG@c.(031)Insat 1A(041)Goes 06+VB V$ 1983? V V+ &(tG@c(089)Insat 1B+B V V$ 1984< V V+ &"T(080)GMS 3+ V V$ 1987> VQ V+ &&.(022)Goes 07+ V| V$ 1988o7Q V V8 @nѵauG@cCosmos 1940(051)Meteosat 3(063)Insat 1C+| V V$ 1989Y% Vo V4 8JҵaT(020)Meteosat 4(070)GMS 4+ V V$ 1990?o V V+ &(vG@c(051)Insat 1D+ V V$ 1991A VE V+ &,ӵa(015)Meteosat 5+ Vp V$ 1992?E V V+ &(G@c(041)Insat 2A+p V V$ 1993\( V6 V4 8PG@cԵa(048)Insat 2B(073)Meteosat 6+ Va V$ 1994Z&6 V V4 8L.Q(022)Goes 08(069)Electro 1+a V V$ 1995V" V<V4 8DT.(011)GMS 5(025)Goes 09+ VgV$ 1997t7<VV= Jn㝖.#'v&յa(019)Goes 10(029)DFH 45(049)Meteosat 7<gVV' *O External resourcesrVV. ,http://www.met.fsu.edu/explores/Guide/satguide.htmlhttp://climate.gsfc.nasa.gov/~chesters/text/geonews.htmlNV@V1'@Vo@VVMeteorological LEO satelV@VVlites^&Vo@V8 @NH̀" Meteorological LEO satellites+@V@V$ 1959Bo@V@V+ &.`(009)Explorer 07+@VAV$ 1960Z&@VaAV4 8L:ܗ+;ܗ+(002)Tiros 01(016)Tiros 02+AVAV$ 1961?aAVAV+ &(<ܗ+(017)Tiros 03+AVAV$ 1962u8AVkBV= Jp=ܗ+>ܗ+?ܗ+(002)Tiros 04(025)Tiros 05(047)Tiros 06+AVBV$ 1963Z&kBVBV4 8L@ܗ+Aܗ+(024)Tiros 07(054)Tiros 08+BVCV$ 1964?BVZCV+ &(Q;C(052)Nimbus 1+CVCV$ 1965k3ZCVCV8 @fBܗ+ڗ+(004)Tiros 09(051)Tiros 10DMSP B2-1+CVDV$ 1966sCVDVW ~11R;C?ف1(008)Essa 1(016)Essa 2DMSP B2-2(040)Nimbus 2DMSP B4-1(057)Cosmos 0122(087)Essa 3+DVEV$ 1967nDVEVR t1ف11(006)Essa 4DMSP B4-2(018)Cosmos 0144(036)Essa 5DMSP B4-3DMSP B4-4(114)Essa 6+EVEV$ 1968x<EVsFV< Hx11DMSP B4-5(069)Essa 7DMSP B4-6(114)Essa 8+EVFV$ 1969[sFVCGVJ d1>kS;C>k(016)Essa 9(029)Meteor 1-01(037)Nimbus 3DMSP B4-7(084)Meteor 1-02+FVnGV$ 1970CGVQHVV zBOUUT;C܁ {(008)ItosDMSP B5A-01Meteor 1-03(025)Nimbus 4Meteor 1-04Meteor 1-05DMSP B5A-02Meteor 1-06(106)NOAA 01+nGV|HV$ 1971\QHVIV: DMeteor 1-07DMSP B5A-03Meteor 1-08Meteor 1-09DMSP B5A-04Meteor 1-10+|HV=IV$ 1972pIVIVH `݁ {U;CDMSP B5B-05Meteor 1-11Meteor 1-12(082)NOAA 02Meteor 1-13DMSP B5C-06(097)Nimbus 5+=IV JV$ 1973w@IVJV7 >ށ {Meteor 1-14Meteor 1-15DMSP B5C-07(086)NOAA 03+ JVJV$ 1974|JVKVG ^߁ {Meteor 1-16DMSP B5C-08Meteor 1-17Meteor 1-18DMSP B5C-09Meteor 1-19(089)NOAA 04Meteor 1-20+JVKV$ 1975_KVNLV? NV;CMeteor 1-21DMSP B5C-10(052)Nimbus 6Meteor 2-01Meteor 1-22Meteor 1-23+KVyLV$ 1976fNLVMV? N {DMSP B5C-11Meteor 1-24Meteor 1-25(077)NOAA 05DMSP B5D1-1 (AMS 1)Meteor 1-26+yLVIMV$ 1977UMVMV6 <Meteor 2-02Meteor 1-27DMSP B5D1-2 (AMS 2)Meteor 1-28Meteor 2-03+IMVMV$ 1978t<MVsNV8 @x?W;CDMSP B5D1-3 (AMS 3)(096)Tiros N(098)Nimbus 7+MVNV$ 1979WsNV0OV; F {Meteor 1-29Meteor 2-04DMSP B5D1-4 (AMS 4)(057)NOAA 06Meteor 2-05+NV[OV$ 1980c00OVOV3 6`(043)NOAA BMeteor 1-30Meteor 2-06+[OV V$ 1981OV VVd1OVpV3 6b {Meteor 2-07(059)NOAA 07Meteor 1-31+ VV$ 1982e7pVV. ,nMeteor 2-08Meteor 2-09DMSP B5D2-1 (AMS 5)+V+V$ 1983d1VV3 6b {(022)NOAA 08Meteor 2-10DMSP B5D2-2++VV$ 1984Q"V V/ .D {Meteor 2-11(123)NOAA 09+V6V$ 1985]/ VV. ,^Meteor 2-12Meteor 3-01Meteor 2-13+6VV$ 1986Q"VV/ .Db {Meteor 2-14(073)NOAA 10+V:V$ 1987h5VV3 6j㧢щMeteor 2-15(053)DMSP B5D2-3Meteor 2-16+:V̓V$ 1988rVV@ P&v&Y {Meteor 2-17DMSP B5D2-4 (USA 29)Meteor 3-02(080)Dong Fang Hong 24(Feng Yun 1-1)(089)NOAA 11+̓VV$ 1989U&VV/ .L٫ kMeteor 2-18(086)Meteor 3-03+V*V$ 1990aV…V7 >&v&Meteor 2-19(081)Dong Fang Hong 30(Feng Yun 1-2)Meteor 2-20DMSP B5D2-5 (USA 68)+*VV$ 1991O…VxV< HZ {۫ kMeteor 3-04(032)NOAA 12(056)Meteor 3-05DMSP B5D2-6 (USA 73)+VV$ 19937xVچV& "Meteor 2-21+VV$ 1994z=چVV= Jzܫ k㫢щ\ {(003)Meteor 3-06(057)DMSP B5D2-7(089)NOAA 14+VV$ 1995BVV+ &.㬢щ(015)DMSP B5D2-8+VV$ 1998>VUV+ &&] {(030)NOAA 15<VV' *O External resources^7UVV' nhttp://www.met.fsu.edu/explores/Guide/satguide.htmlJV9V19VVWRemote sensing satellitesZ"VV8 @FH̀" Remote sensing satellites4 9VljV' O Chronology+VV$ 1972@ljV2V+ &* ɉ(058)Landsat 1+V]V$ 1975f2V VF \ ɉ#(v&$(v&%(v&(004)Landsat 2(070)Dong Fang Hong 03(110)Dong Fang Hong 04(119)Dong Fang Hong 05+]V4V$ 1976l8 VV4 8p&(v&'(v&(087)Dong Fang Hong 06(117)Dong Fang Hong 07+4VˋV$ 19777VV& "Meteor 1-28+ˋV-V$ 1978aV݌VO n((v&ɉεS㖯W;C(011)Dong Fang Hong 08(026)Landsat 3(041)AEM 1(064)Seasat(098)Nimbus 7+-VV$ 1979P݌VV7 >e艂Meteor 1-29Cosmos 1076 (Ocean-E)(051)Bhaskara 1Intercosmos 20+VV$ 1980T*VV* $TCosmos 1151 (Ocean-E)Meteor 1-30+V9V$ 1981j7VV3 6ne艂Intercosmos 21Meteor 1-31(115)Bhaskara 2+9VΎV$ 1982d0V2V4 8`ɉ&v&(072)Landsat 4(090)Dong Fang Hong 12+ΎV]V$ 1983yF2V֏V3 6&v&(086)Dong Fang Hong 13Cosmos 1484Cosmos 1500 (Ocean-OE)+]V V$ 1984֏V VVJ֏VV8 @ɉ&v&(021)Landsat 5(098)Dong Fang Hong 16Cosmos 1602 (Ocean-OE)+ VV$ 1985[,VV/ .X&v&(096)Dong Fang Hong 17Cosmos 1689+V@V$ 1986IVV> L㥇뉢&v&(019)Spot 1Cosmos 1766 (Ocean-O1)(076)Dong Fang Hong 19+@VV$ 1987zVVP pV$뉢!w&v&&v&(018)Momo 1ACosmos 1869 (Ocean-O1)(064)Cosmos 1870(067)Dong Fang Hong 20(075)Dong Fang Hong 21+VV$ 1988ZVVG ^YT󓋉뉢&v&(021)IRS 1A(056)Ocean 1 (Ocean-O1)Cosmos 1939(067)Dong Fang Hong 23+VV$ 1989fVhVO ny9z9{9|9}9(038)Resurs F01(047)Resurs F02(055)Resurs F03(063)Resurs F04(073)Resurs F05+VV$ 1990hVVq Y㦇W$󓋉뉢~9999&v&(005)Spot 2(013)Momo 1B(018)Ocean 2 (Ocean-O1)(047)Resurs F06(060)Resurs F07(073)Resurs F08(082)Resurs F09(089)Dong Fang Hong 33+VV$ 1991VVu S7󓋉뉢7_QTѓF̉77YTAlmaz(035)Resurs F10(039)Ocean 3 (Ocean-O1)(044)Resurs F11(050)ERS 1(050)Uosat 5(052)Resurs F12(058)Resurs F13(061)IRS 1B+V$V$ 1992V"Vb 9Z77ue7&v&&v&(007)JERS 1(024)Resurs F14(033)Resurs F15(052)Topex Poseidon(056)Resurs F16(051)Dong Fang Hong 35(064)Dong Fang Hong 36+$VMV$ 1993x"VVX IW777㧇&v&(009)SCD 1(033)Resurs F17(040)Resurs F18(053)Resurs F19(061)Spot 3(063)Dong Fang Hong 37+MVHV$ 1994`VVL h('v&󓋉뉢_TSsɉ(037)Dong Fang Hong 40(066)Ocean 4 (Ocean-O1)(068)IRS P2(074)Resurs O1-3+HVV$ 1995WVVO n`QT>w|*8gTYT(021)ERS 2(046)Sich 1(050)Resurs F20(059)Radarsat(072)IRS 1C+VV$ 1996LVVF \_T bUis!'v&(017)IRS P3(037)TOMS(046)Adeos 1(059)Dong Fang Hong 43+VV$ 1997jVoVX JeUYT!8ŘbU^`B(037)Orbview 2(044)Lewis(057)IRS 1D(072)Resurs F21(074)TRMM(085)Early Bird+VV$ 1998=oVV+ &$㨇(017)Spot 4:VV' & SAR performances*VVa#T  8 SatelliteLaunch dateResolutions VVj# VVs#2(㹌ל (*.United StatesV$Vp#2"㖯&Seasat197825 ms VVj# $V%Ws#( V%WVCIS$VWp#H"!w"$0Cosmos 1870198715 to 30 m!%WJWp#B*Almaz 1A199110 to 15 ms WWj# JWBWs#$(4"  EuropeWWp#0"_QT$ERS 1199126 mBWZWv#4(`QT(ERS 2199526 mWWv#2(7&Envisat?30 ms ZW\Wj# WWv#$(b  Japan\WpWp#8"Z&JERS 1199225-30 ms WWj# pWlWv#&(xW "CanadaWWv#8(gT .Radarsat19959 m&lW$W# <W`W' *O External resourcesS$WW. ,http://midas.ac.uk/rs/http://www.ccrs.nrcan.gc.ca/ccrs/satsens/satsense.htmlR!`W3W1x3WW YTelecommunications LEO satellitesa)WW8 @TH̀" LEO Telecommunication satellites+3WW$ 1958<WW+ &"'[IW(006)Score+W& W$ 1960Z&W W4 8LLV.D(009)Echo 1(013)Courier 1B+& W W$ 1961? W W+ &(쉂(???)Oscar 01+ W W$ 1962u8 W W= Jp쉂zz(022)Oscar 02(029)Telstar 1(068)Relay 1+ W W$ 1963@ W W+ &*zz(013)Telstar 2+ W W$ 1964W# Ww W4 8FMV.(003)Relay 2(004)Echo 2+ W W$ 1965Lw W/ WA R쉂VIW쉂(016)Oscar 03(030)Molniya 1-01Molniya 1-02(108)Oscar 04+ WZ W$ 1966/ W0 WK dCosmos 103Molniya 1-03IDSCP 1-1IDSCP 1-2IDSCP 1-3IDSCP 1-4IDSCP 1-5IDSCP 1-6IDSCP 1-7Molniya 1-04+Z W[ W$ 1967?0 WWc IDSCP 2-1IDSCP 2-2IDSCP 2-3IDSCP 2-4IDSCP 2-5IDSCP 2-6IDSCP 2-7IDSCP 2-8Cosmos 151Molniya 1-05IDSCP 3-1IDSCP 3-2IDSCP 3-3IDSCP 3-4Molniya 1-06Molniya 1-07+[ WW$ 1968WWS tQMolniya 1-08IDSCP 4-1IDSCP 4-2IDSCP 4-3IDSCP 4-4IDSCP 4-5IDSCP 4-6IDSCP 4-7IDSCP 4-8Molniya 1-09Cosmos 236Molniya 1-10+W @W$ 1969W @WWbW@W> L<<Molniya 1-11Molniya 1-12Cosmos 292 (exp. Strela-1)Cosmos 304 (exp. Strela-1)+ @W@W$ 1970"|@WBW 쉂<<<<<<<<<<<(008)Oscar 05Molniya 1-13Cosmos 332 (exp. Strela-1)Cosmos 336 (Strela-2)Cosmos 337 (Strela-2)Cosmos 338 (Strela-2)Cosmos 339 (Strela-2)Cosmos 340 (Strela-2)Cosmos 341 (Strela-2)Cosmos 342 (Strela-2)Cosmos 343 (Strela-2)Molniya 1-14Molniya 1-15Cosmos 371 (exp. Strela-1)(086)Cosmos 372 (Strela-1)L"@WECW* $DMolniya 1-16Molniya 1-17+BWpCW$ 1971&tECWEW 2<<<<<<<< LexXX :}b,xՅRa4IWՅ@ՅAՅBՅ(043)Iridium 22(043)Iridium 23(043)Iridium 24(043)Iridium 25(043)Iridium 26(051)Iridium 27(051)Iridium 28(051)Iridium 29(051)Iridium 30(051)Iridium 31(051)Iridium 32(052)Faisat 2V(054)Molniya 1-90(056)Iridium 19(056)Iridium 34(056)Iridium 35(056)Iridium 36^'YTY FCՅjՅhՅqՅEՅDՅiՅkՅlՅmՅnՅoՅpՅs:?s:(056)Iridium 37(069)Iridium 43(069)Iridium 41(069)Iridium 40(069)Iridium 39(069)Iridium 38(077)Iridium 42(077)Iridium 44(082)Iridium 45(082)Iridium 46(082)Iridium 47(082)Iridium 48(082)Iridium 49(085)Orbcomm FM 5(085)Orbcomm FM 6(085)Orbcomm FM 7(085)Orbcomm FM 8]:YYF \@s:rZыiZыjZы(085)Orbcomm FM 9(085)Orbcomm FM 10(085)Orbcomm FM 11(085)Orbcomm FM 12+TY"Y$ 1998OY$ Y 4:s:;s:㬝QP㭝QP㮝QP㯝QPՅՅՅՅՅ5`1ՅՅՅՅ(007)Orbcomm FM 3(007)Orbcomm FM 4(008)Globalstar 1(008)Globalstar 2(008)Globalstar 3(008)Globalstar 4(010)Iridium 50(010)Iridium 52(010)Iridium 53(010)Iridium 54(010)Iridium 56(012)Teledesic 1(018)Iridium 51(018)Iridium 61(019)Iridium 55(019)Iridium 57`"Y@ Y FՅՅՅՅՅՅՅՅՅՅ㱝QP㳝QP{}{}ՅՅՅ(019)Iridium 58(019)Iridium 59(019)Iridium 60(021)Iridium 62(021)Iridium 63(021)Iridium 64(021)Iridium 65(021)Iridium 66(021)Iridium 67(021)Iridium 68(023)Globalstar 6(023)Globalstar 8(023)Globalstar 14(023)Globalstar 15(026)Iridium 69(026)Iridium 71(032)Iridium 70S$ Y YG ^ՅՅՅՅ(032)Iridium 72(032)Iridium 73(032)Iridium 74(032)Iridium 75\+@ Y6 Y1$B6 Y YIZTelecommunications geostationary satellitesk3 Y Y8 @hH̀" Geostationary telecommunication satellitesK"6 Y Y) "D/ۉSee also the Clarke Belt list* YY' O + YAY$ 1964?YY+ &(sH(047)Syncom 3+AYY$ 1965CYY+ &0rĉ(028)Intelsat 101+YY$ 1966<YUY+ &"S(110)ATS 1+YY$ 1967SUY%@YF \ĉĉĉS(001)Intelsat 202(026)Intelsat 203(094)IntelY%@Y Ysat 204(111)ATS 3+YP@Y$ 1968['%@Y@Y4 8NĶUĉ(081)LES 6(116)Intelsat 302+P@Y@Y$ 1969P@YlAYF \ĉĉS ȉ(011)Intelsat 303(045)Intelsat 304(069)ATS 5(101)Skynet 1A+@YAY$ 1970TlAY1BYF \ĉa }ĉĉ(003)Intelsat 306(021)Nato 1(032)Intelsat 307(055)Intelsat 308+AY\BY$ 1971d1BYCYO nĉb }y,dMz,dMĉ(006)Intelsat 402(009)Nato 2(095)DSCS 2-01(095)DSCS 2-02(116)Intelsat 403+\BY:CY$ 1972|?CYCY= J~ ĉ!ĉ?QQ(003)Intelsat 404(041)Intelsat 405(090)Anik A1+:CYCY$ 1973OCYvDYF \@QQ#ĉ{,dM|,dM(023)Anik A2(058)Intelsat 407(100)DSCS 2-03(100)DSCS 2-04+CYDY$ 1974vDYEYk 9/S㘜7/$ĉ6 ȉ?a׉(014)Cosmos 0637(022)Westar 1(039)ATS 6(060)Molniya 1S(075)Westar 2(093)Intelsat 408(094)Skynet 2B(101)Symphonie 1+DYEY$ 1975zEYFYX AQQĉ@a׉ >0*5oމ(038)Anik A3(042)Intelsat 401(077)Symphonie 2(091)Intelsat 4A01(117)Satcom 1(123)Raduga 01+EYFY$ 1976FYoHY S ݏ7ƶUǶU?0*CdXLXݏ7:9YLX5oމݏ7eɉ(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+FYHY$ 1977oHYIYk 1ㆾT:9,dM,dM 5oމeɉ*߉(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+HYIY$ 1978xIY@KY  >>ቂ ·ቂpiVZLX5oމCd*dM*dMjQQ$o(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+IYkKY$ 1979&@KYLYt eeɉ5oމ?>ቂ%o/eɉ*dM*dM%o(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+kKYLY$ 1980(LYMYt i@>ቂ5oމ%oeɉ5oމA>ቂ=HWWĉeɉ(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+LYNY$ 1981uMYOY [LX5oމVĉc&Seɉ5oމB>ቂ=HW=4oމ-Xĉڰ_(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+NYOY$ 1982UOYՁY XA0*eɉ/Yĉ%oOYՁY YsG@c6v/QQeɉZĉ%o]*dM ceM=HWQQ44oމ(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+OYY$ 1983FՁYY FJ.xdɉOM54oމ-[ĉنQQ2:97up%oƵK.64oމtG@c-8up(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|?Y~Y= J~odɉ\ĉ%o(100)Ekran 11(105)Intelsat 507(118)Gorizont 08+YY$ 1984S~YY F㉂74oމV w]ĉpdɉ&v&%oZIz84oމ#oچ eqdɉ=HW"AgƵ9up(005)Yuri 2A(016)Raduga 14(022)Cosmos 1540(023)Intelsat 508(028)Ekran 12(035)Dong Fang Hong 15(041)Gorizont 09(049)Spacenet 1(063)Raduga 15(078)Gorizont 10(081)Eutelsat 1F2(081)Telecom 1A(090)Ekran 13(093)SBS 4(093)Leasat 2(093)Telstar 302(101)Galaxy 3]YdYO nQQ!Ag[Iz˴UCd(113)Anik D2(113)Leasat 1(114)Spacenet 2(114)Marecs B2(115)Nato 3D+YY$ 1985IdYY F|#o4鉂b􉂃rdɉĉQQ#Ag:TeF5鉂Ƶĉ94oމ_iS$Ag(007)Gorizont 11(015)Arabsat 1A(015)Brasilsat A1(024)Ekran 14(025)Intelsat 510(028)Anik C1(028)Leasat 3(035)Gstar 1(035)Telecom 1B(048)Morelos 1(048)Arabsat 1B(048)Telstar 303(055)Intelsat 511(070)Raduga 16(076)Optus A1(076)ASC 1(076)Leasat 4 YYk =ĉ ceMceMw:4oމF_-(087)Intelsat 512(092)DSCS 3-02(092)DSCS 3-03(102)Cosmos 1700(107)Raduga 17(109)Morelos 2(109)Optus A2(109)Satcom K2+YȊY$ 1986YMY -;4oމ&v&㉂;Tb􉂃wsdɉ}#o<4oމ~#oD>ቂ(003)Satcom K1(007)Raduga 18(010)Dong Fang Hong 18(016)Yuri 2B(026)Gstar 2(026)Brasilsat A2(027)Cosmos 1738(038)Ekran 15(044)Gorizont 12(082)Raduga 19(090)Gorizont 13(096)Fleetsatcom 7+ȊYxY$ 1987\MYԍY ڀh4oމ有#o㉾Ttdɉ_܆!w!w_4oމudɉ(028)Raduga 20(029)Palapa B2P(040)Gorizont 14(070)ETS 5(073)Ekran 16(078)Optus A3(078)Eutelsat 1F4(084)Cosmos 1888(096)Cosmos 1897(100)Raduga 21(109)Ekran 17+xYY$ 1988RԍYY Fu.&v&de#ovdɉĉ@huG@c݆(w#oTƭ\#ovtމmԐS*dMceME>ቂ#o ĉ(004)Gorizont 17(006)Intelsat 515(020)Jcsat 1(021)TDRS 4(027)TELE X(030)Raduga 23(041)Superbird A1(041)DFS 1(048)Raduga 1-1(052)Gorizont 18(053)Olympus(062)Tvsat 2(067)BSB 1(069)DSCS 2-16(069)DSCS 3-04(077)Fleetsatcom 8(081)Gorizont 19(087)Intelsat 602^*YqY4 8Tb4oމ+fx(098)Raduga 24(101)Cosmos 2054+YY$ 1990FqYY F ȉㇺ2%Ag&v&c4oމ ĉk有vG@c#o ĉfxw~W˗>TS㉂ ȉ(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 4CAYY} Ȁ=HWT=updɉ#oO(066)DFS 3(072)Galaxy 7(074)Ekran 20(082)Gorizont 27(084)Superbird A2+YY$ 1993JYY XOMg4oމ|W(~:upceMc͉G@c|W KU4oމĉ#o#oceMCd͵~9T(003)TDRS 6(029)Raduga 29(015)UHF 1(031)Astra 1C(039)Galaxy 4(046)DSCS 3-07(048)Hispasat 1B(048)Insat 2B(056)UHF 2(058)ACTS(062)Raduga 30(066)Intelsat 701(069)Gorizont 28(072)Gorizont 29(074)DSCS 3-08(076)Nato 4B(077)Telstar 401(078)DBS 1@Y Y+ &*Fˉ(078)Thaicom 1+Y6Y$ 1994H YFZ FO?ƭ\4oމ_b㉂#oĉ|WAh ㉂b 9T"c􉂃mvm_ -xĉ(002)Gals 6YFZ Y1(008)Raduga 1-3(009)Milstar 1-1(012)Raduga 31(013)Galaxy 1R(030)Gorizont 30(034)Intelsat 702(035)UHF 3(040)Panamsat 2(040)Yuri 3N(043)Apstar 1(047)DBS 2(049)Brasilsat B1(049)Turksat 1B(055)Optus B3(060)Cosmos 2291(064)Intelsat 703 6YQZk AL2GˉJ7(~R*'v&vEo4oމ(065)Solidaridad 2(065)Thaicom 2(067)Express 1(070)Astra 1D(079)Orion 1(080)Dong Fang Hong 41(082)Luch 0(087)Raduga 32+FZ|Z$ 1995SQZZ Xĉ|Wĉ#c􉂃S ĉ|W〽9TOMceMChY ㈺2) 2x㑑)mEo(001)Intelsat 704(003)UHF 4(013)Intelsat 705(016)Brasilsat B2(016)Hotbird 1(019)AMSC 1(023)Intelsat 706(027)UHF 5(029)DBS 3(035)TDRS 7(038)DSCS 3-09(040)Panamsat 4(041)Koreasat 1(043)Jcsat 3(044)N Star A(045)Cosmos 2319(049)Telstar 402R(054)Luch 1|ZZk +(~|WO?:eG@cb㉂VR^Z(055)Astra 1E(057)UHF 6(060)Milstar 1-2(063)Gals 2(067)Telecom 2C(067)Insat 2C(069)Galaxy 3R(073)Echostar 1+ZZ$ 1996LZZ F8MY #o]:9* ĉ)rG)~Lw^:93 ?up#oĉi"鉂_鉂(002)Panamsat 3R(002)Measat 1(003)Koreasat 2(005)Gorizont 31(006)Palapa C1(007)N Star B(015)Intelsat 707(020)Inmarsat 3F1(021)Astra 1F(022)MSAT 1(030)Palapa C2(030)Amos 1(033)Galaxy 9(034)Gorizont 32(035)Intelsat 709(039)Apstar 1A(040)Arabsat 2AuZ< Z nvm|WoG;e*rGrRUWR^ZJ7`鉂+rG(040)Turksat 1C(042)UHF 7(044)Italsat 2(044)Telecom 2D(053)Inmarsat 3F2(054)GE 1(055)Echostar 2(058)Express 2(063)Arabsat 2B(063)Measat 2(067)Hotbird 2(070)Inmarsat 3F3+Zg Z$ 1997M< Zy Z XrRUS_E㉺2ĉqHˉR􉂃"'v&gOzz,rGG@cĉ_Sk7EhnrRU(002)GE 2(002)Nahuel 1A(007)Jcsat 4(009)Intelsat 801(011)Tempo 2(016)Thaicom 3(016)Bsat 1A(021)DFH 44(025)Thor 2(026)Telstar 5(027)Inmarsat 3F4(027)Insat 2D(031)Intelsat 802(036)Superbird C(040)Panamsat 6(041)Mabuhay 1(049)Hotbird 3(050)GE 3^g Z Z ڀĉXR^Z"鉂aeMɮ6L M@㊺2)~c㉂ĉ(053)Intelsat 803(059)Echostar 3(062)Apstar 2R(065)DSCS 3-10(070)Coupon 1(071)Sirius 2(071)Cakrawarta 1(075)Jcsat 5(076)Astra 1G(078)Galaxy 8i(083)Intelsat 804+y Z Z$ 1998G ZIZ~ ʀ ȉ$c􉂃-rGĉ|WW􉂃S􉂃YR^Zj)ቂ(002)Skynet 4D(006)Brasilsat B3(006)Inmarsat 3F5(013)Hotbird 4(014)Intelsat 806(016)UHF 8(024)Nilesat 101(024)Bsat 1B(028)Echostar 4(033)Chinastar 1F ZZ16xZZl[Navigation satellitesVIZZ8 @>H̀" Navigation satellites+ZZ$ 1960S$ZcZ/ .Hd؉Transit 1B(007)Transit 2A+ZZ$ 1961yAcZ@Z8 @㺶؉㻶؉Transit 3B (loft 1)(015)Transit 4A(031)TransiZ@ZIZt 4B+Z>@Z$ 19626@Zt@Z&  Transit 5A+>@Z@Z$ 1963yAt@ZAZ8 @ABTransit 7 (5A3)(038)Transit 5BN1(049)Transit 5BN2+@ZCAZ$ 1964d6AZAZ. ,lTransit 9 (5C 1)Transit 5B 4Transit 5B 5+CAZAZ$ 1965ZAZZBZ. ,NNSS 30 030 (Transit 5B 6)NNSS 30 040 (Transit 5B 7)NNSS 30 050 (Transit 10)+AZBZ$ 1966rZBZ)CZ2 4NNSS 30 060 (Transit 11)NNSS 30 070 (Transit 12)NNSS 30 080 (Transit 13)NNSS 30 090 (Transit 14)+BZTCZ$ 1967r)CZCZ6 <NNSS 30 120 (Transit 15)NNSS 30 130 (Transit 16)Timation 1NNSS 30 140 (Transit 17)Cosmos 192+TCZ'DZ$ 1968V,CZ}DZ* $XNNSS 30 180 (Transit 18)Cosmos 220+'DZDZ$ 1969g9}DZEZ. ,rCosmos 292Timation 2 (+ 6 ss sat)Cosmos 304+DZ:EZ$ 1970IEZEZ6 <Cosmos 332NNSS 30 190Cosmos 371Cosmos 381Cosmos 385+:EZEZ$ 1971HEZ,FZ* $<Cosmos 422Cosmos 465+EZWFZ$ 1972i7,FZFZ2 4nCosmos 475Cosmos 489Cosmos 514Triad 1+WFZFZ$ 1973m;FZXGZ2 4vCosmos 574Cosmos 586NNSS 30 200Cosmos 627+FZGZ$ 1974hXGZ+HZ@ P㼨ԟCosmos 628Cosmos 660Cosmos 663Timation 3 (NTS 1)Cosmos 689Cosmos 700 (Parus)+GZVHZ$ 1975k+HZ IZH `㼨ԟ㼨ԟ㼨ԟCosmos 726 (Parus)Cosmos 729Cosmos 755 (Parus)Triad 2 (TIP 2)Cosmos 778 (Parus)+VHZ4IZ$ 1976  IZTJZc {㼨ԟ㼨ԟ 剂㼨ԟCosmos 789 (Parus)Cosmos 800Cosmos 807Cosmos 823Cosmos 842Cosmos 846Triad 3 (TIP 3)Cosmos 864 (Parus)Cosmos 883 (Tsikada)Cosmos 887 (Parus)+4IZJZ$ 1977TJZKZe k㼨ԟ 剂㼨ԟ㼨ԟ㼨ԟCosmos 890Cosmos 894 (Parus)Cosmos 911Cosmos 926 (Tsikada)Cosmos 928 (Parus)Cosmos 951 (Parus)NNSS 30 110Cosmos 962Cosmos 971 (Parus)+JZKZ$ 1978KZJMZ 㼨ԟcZ㼨ԟ㼨ԟu0w 剂cZ㼨ԟcZcZCosmos 985 (Parus)(020)GPS BI-01Cosmos 991 (Parus)Cosmos 994Cosmos 996 (Parus)(034)Cosmos 1000 (Tsikada)(047)GPS BI-02Cosmos 1011 (Parus)Cosmos 1027(093)GPS BI-03(112)GPS BI-04Cosmos 1064+KZuMZ$ 1979JMZnNZ_ 5㼨ԟ㼨ԟ㼨ԟ 剂㼨ԟ㼨ԟCosmos 1072 (Parus)Cosmos 1089 (Parus)Cosmos 1091 (Parus)Cosmos 1092 (Tsikada)Cosmos 1104 (Parus)Cosmos 1141 (Parus)+uMZNZ$ 19803nNZOZq 㼨ԟ㼨ԟcZ 剂cZ㼨ԟ㼨ԟ 剂Cosmos 1150 (Parus)Cosmos 1153 (Parus)(011)GPS BI-05Cosmos 1168 (Tsikada)(032)GPS BI-06Cosmos 1181 (Parus)Cosmos 1225 (Parus)Cosmos 1226 (Tsikada)+NZ Z$ 1981OZ ZIZOZZ^ #㼨ԟw㼨ԟ㼨ԟ 剂㼨ԟCosmos 1244 (Parus)(044)Nova 1Cosmos 1275 (Parus)Cosmos 1295 (Parus)Cosmos 1304 (Tsikada)Cosmos 1308 (Parus)+ Z&Z$ 1982 ZZ ̀㼨ԟ 剂㼨ԟ㼨ԟ 剂㼨ԟ㼨ԟCosmos 1333 (Parus)Cosmos 1339 (Tsikada)Cosmos 1344 (Parus)Cosmos 1349 (Parus)Cosmos 1380Cosmos 1383 (Tsikada)Cosmos 1386 (Parus)Cosmos 1413 (dummy)Cosmos 1414 (Glonass)Cosmos 1415 (dummy)Cosmos 1417 (Parus)+&Z݂Z$ 1983bZZ 㼨ԟ 剂㼨ԟ㼨ԟ㼨ԟcZ 剂㼨ԟCosmos 1428 (Parus)Cosmos 1447 (Tsikada)Cosmos 1448 (Parus)Cosmos 1459 (Parus)Cosmos 1464 (Parus)(072)GPS BI-08Cosmos 1490 (Glonass)Cosmos 1491 (Glonass)Cosmos 1492 (dummy)Cosmos 1506 (Tsikada)Cosmos 1513 (Parus)Cosmos 1519 (Glonass)Cosmos 1520 (Glonass)Cosmos 1521 (dummy)+݂Z Z$ 1984kZZ 㼨ԟ㼨ԟ㼨ԟ 剂cZ 剂acZ㼨ԟCosmos 1531 (Parus)Cosmos 1535 (Parus)Cosmos 1550 (Parus)Cosmos 1553 (Tsikada)Cosmos 1554 (Glonass)Cosmos 1555 (Glonass)Cosmos 1556 (dummy)(059)GPS BI-09Cosmos 1574 (Tsikada)Cosmos 1577Cosmos 1593 (Glonass)Cosmos 1594 (dummy)Cosmos 1595 (Glonass)(097)GPS BI-10Cosmos 1598 (Parus)D ZZ? N㼨ԟw㼨ԟCosmos 1605 (Parus)(110)Nova 2Cosmos 1610 (Parus)+ZʇZ$ 1985hZȉZ 㼨ԟ㼨ԟ 剂XcZ㼨ԟ㼨ԟCosmos 1627 (Parus)Cosmos 1634 (Parus)Cosmos 1650 (Glonass)Cosmos 1651 (Glonass)Cosmos 1652 (dummy)Cosmos 1655 (Tsikada)(095)GPS BI-11SOOS ? Transit 19 (SOOS 240 - 300)SOOS ?Transit 20Cosmos 1704 (Parus)Cosmos 1709 (Parus)Cosmos 1710 (Glonass)Cosmos 1711 (Glonass)Cosmos 1712 (dummy)+ʇZZ$ 1986ȉZZ 9㼨ԟ 剂㼨ԟ㼨ԟ 剂㼨ԟ㼨ԟCosmos 1725 (Parus)Cosmos 1727 (Tsikada)Cosmos 1745 (Parus)Cosmos 1759 (Parus)Cosmos 1778 (Glonass)Cosmos 1779 (Glonass)Cosmos 1780 (Glonass)Cosmos 1791 (Tsikada)Polar Bear (17070)Cosmos 1802 (Parus)Cosmos 1808 (Parus)+ZŋZ$ 1987rZߍZ  剂㼨ԟN!w 剂㼨ԟ㼨ԟ㼨ԟCosmos 1816 (Tsikada)Cosmos 1821 (Parus)Cosmos 1838 (Glonass)Cosmos 1839 (Glonass)Cosmos 1840 (Glonass)(054)Cosmos 1861 (Tsikada)Cosmos 1864 (Parus)Cosmos 1883 (Glonass)Cosmos 1884 (Glonass)Cosmos 1885 (Glonass)SOOS 270 (Oscar 27)SOOS 290 (Oscar 29)Cosmos 1891 (Parus)Cosmos 1904 (Parus)+ŋZ Z$ 1988oߍZ*Z  (w㼨ԟwd(w㼨ԟ(wCosmos 1917 (Glonass)Cosmos 1918 (Glonass)Cosmos 1919 (Glonass)(023)Cosmos 1934 (Parus)SOOS 230 (Oscar 23)SOOS 320 (Oscar 32)Cosmos 1946 (Glonass)Cosmos 1947 (Glonass)Cosmos 1948 (Glonass)(052)Nova 3(062)Cosmos 1959 (Parus)SOOS 250 (Oscar 25)SOOS 310 (Oscar 31)(08 Z*ZIZ5)Cosmos 1970 (Glonass)D ZZ@ P(w(w(085)Cosmos 1971 (Glonass)(085)Cosmos 1972 (Glonass)+*ZZ$ 1989VZZ L(w(w(w.gx㼨ԟex㼨ԟexexexexex㼨ԟ.(001)Cosmos 1987 (Glonass)(001)Cosmos 1988 (Glonass)(001)Cosmos 1989(013)GPS BII-01(017)Cosmos 2004 (Parus)(028)Cosmos 2016 (Parus)(031)Cosmos 2018(039)Cosmos 2022 (Glonass)(039)Cosmos 2023 (Glonass)(039)Cosmos 2024 (Glonass)(042)Cosmos 2026 (Parus)(044)GPS BII-02qZZU zR򲟉ex㼨ԟ...(050)Nadezhda 1(059)Cosmos 2034 (Parus)(064)GPS BII-03(085)GPS BII-04(097)GPS BII-05+ZZ$ 1990VZZ H.S򲟉Sfx㼨ԟ.fx㼨ԟfxfxfx.㼨ԟ.5F݉&x(008)GPS BII-06(017)Nadezhda 2(023)Cosmos 2061 (Parus)(025)GPS BII-07(036)Cosmos 2074 (Parus)(045)Cosmos 2079 (Glonass)(045)Cosmos 2080 (Glonass)(045)Cosmos 2081 (Glonass)(068)GPS BII-08Cosmos 2100 (Parus)(088)GPS BII-09(103)GPS BIIA-10(110)Cosmos 2109 (Glonass)DZvZ@ P$x{$x(110)Cosmos 2110 (Glonass)(110)Cosmos 2111 (Glonass)+ZZ$ 1991vZXZ 3$x 剂㼨ԟT򲟉$x%x$x㼨ԟ5F݉㼨ԟ%x㼨ԟ(007)Cosmos 2123 (Tsikada)Cosmos 2135 (Parus)(019)Nadezhda 3(025)Cosmos 2139 (Glonass)(025)Cosmos 2140 (Glonass)(025)Cosmos 2141 (Glonass)Cosmos 2142 (Parus)(047)GPS BIIA-11Cosmos 2154 (Parus)(081)Cosmos 2173 (Parus)+ZZ$ 1992cXZZ B%x%x%x㼨ԟ 剂5F݉5F݉㼨ԟ5F݉:-x;-x<-x(005)Cosmos 2177 (Glonass)(005)Cosmos 2178 (Glonass)(005)Cosmos 2179 (Glonass)Cosmos 2180 (Parus)Cosmos 2181 (Tsikada)(009)GPS BIIA-12(019)GPS BIIA-13Cosmos 2184 (Parus)Cosmos 2195(039)GPS BIIA-14(047)Cosmos 2204 (Glonass)(047)Cosmos 2205 (Glonass)(047)Cosmos 2206 (Glonass)`ZLZL h5F݉+x㼨ԟ5F݉5F݉(058)GPS BIIA-15(073)Cosmos 2218 (Parus)(079)GPS BIIA-16(089)GPS BIIA-17+ZwZ$ 1993#aLZZ R,x 剂5F݉ ,x㼨ԟ ,x,x,x5F݉,x㼨ԟ 6F݉6F݉6F݉6F݉,x㼨ԟ(001)Cosmos 2230 (Tsikada)(007)GPS BIIA-18(008)Cosmos 2233 (Parus)(010)Cosmos 2234 (Glonass)(010)Cosmos 2235 (Glonass)(010)Cosmos 2236 (Glonass)(017)GPS BIIA-19(020)Cosmos 2239 (Parus)(032)GPS BIIA-20(042)GPS BIIA-21(054)GPS BIIA-22(068)GPS BIIA-23(070)Cosmos 2266 (Parus)+wZZ$ 1994RZZ F6F݉,x,x,x,x㼨ԟU򲟉,x,x,x-x-x(016)GPS BIIA-24(021)Cosmos 2275 (Glonass)(021)Cosmos 2276 (Glonass)(021)Cosmos 2277 (Glonass)(024)Cosmos 2279 (Parus)(041)Nadezhda 4(050)Cosmos 2287 (Glonass)(050)Cosmos 2288 (Glonass)(050)Cosmos 2289 (Glonass)(076)Cosmos 2294 (Glonass)(076)Cosmos 2295 (Glonass)T#Z3[1 2F-xZ3[IZ(076)Cosmos 2296 (Glonass)+Z^[$ 1995.f3[[ ^v4xw4xx4x2x㼨ԟ2x 剂2x2x2x3x㼨ԟ3x3x(009)Cosmos 2307 (Glonass)(009)Cosmos 2308 (Glonass)(009)Cosmos 2309 (Glonass)(012)Cosmos 2310 (Parus)(032)Cosmos 2315 (Kurs)(037)Cosmos 2316 (Glonass)(037)Cosmos 2317 (Glonass)(037)Cosmos 2318 (Glonass)(052)Cosmos 2321 (Parus)(068)Cosmos 2323 (Glonass)(068)Cosmos 2324 (Glonass)T#^[[1 2F3x(068)Cosmos 2325 (Glonass)+[ [$ 1996[[[ 3x㼨ԟ6F݉6F݉E3x㼨ԟ6F݉(004)Cosmos 2327 (Parus)(019)GPS BIIA-25(041)GPS BIIA-26(051)Cosmos 2333 (Parus)(056)GPS BIIA-27+ [[$ 1997j[[R tE3x㼨ԟ3Z݉s3x㼨ԟ6F݉(017)Cosmos 2333 (Parus)(035)GPS BIIR-02(052)Cosmos 2346 (Parus)(067)GPS BIIA-28<[[' *O External resourcesd=[l[' zhttp://doradus.einet.net/editors/john-beadles/sum_pre.htmO[[1[[G[Radioactive payload and debris[&l[[5 :NH̀" Radioactive payload and debrisD [Z[8 >_B_BRadioactive payloads have been a concern for the community ever since radioactive debris decayed on Earth and contaminated entire regions. The first such event was in Jan 1978 when Cosmos 0954 decayed. Since then radioactive debris are closely monitored.Those nuclear reactors which are to remain in orbit for a hundred years or so also caused problems to scientists. "Nuclear noise" as it is called cause gamma ray disturbances to astronomers. Indeed those reactors interfere periodically with gamma-ray surveys.&[[# <Z[[' *O Russian satellitesV"[ [4 6E d퉂The Russian Rorsat program is the most important program with nuclear reactor equipped satellites (32 spacecrafts). This engine (named Topol or Topaz) contains 50 kg of uranium and provides about 2000 W.Two other Russian satellites are known to have a Topaz 1 reactor (also named Buk): Cosmos 1818 (87011A) and Cosmos 1867 (87060A), probably for test missions. This reactor provides around 5-6 kW power. It weighs 1350 kg.A third engine named Enissei or Topaz 2 was built but has never been launched. It provides 6 kW and weighs 1 ton.7[I ['  O US satellites [ [< F㹌ל  The United States also used nuclear power on space missions. Two types of engines were used: - Nuclear reactors which produce energy by nuclear fission (space based reactors use Uranium-235).- RTGs (Radioisotope Thermoelectric Generator) which use the energy of radioactive decay (current SNAPs use Plutonium-238).The SNAP (Systems for Nuclear Auxiliary Power) series include:0I [ [a#`  F RTG enginesNuclear reactorsUncertainC [P[p#(㺶؀"vTransit 4AOPS 4682 also called SNAPSHOT (65027A)LES 5x [[^#4(㻶؀ &Transit 4BLES 67P[][^#n(S;C"Nimbus 3OPS 0757 also called Tacsat (69013A)n[[^# (ƶULES 8n][E@[^# (Ƕ[E@[l[ULES 9[A[' MOther missions required nuclear power such as the Apollo moon missions experiments, the Viking Mars Landers, Pioneer and Voyager missions and the Galileo probe: E@[A[a#@n  . LAUNRSpacecraftOrbityA[ B[^#6n*69-099APOLLO 12MoonlA[xB[R#t4n(71-008APOLLO 14Moonl B[B[R#t4n(71-063APOLLO 15Moon~,xB[bC[R#tXn,72-012APIONEER 10escaped solar systemlB[C[R#t4n(72-031APOLLO 16MoonlbC[:D[R#t4n(72-096APOLLO 17Moon~,C[D[R#tXn,73-019APIONEER 11escaped solar systemr :D[*E[R#t@n475-075VIKING 1 LANDERMarsr D[E[R#t@n475-083VIKING 2 LANDERMars}+*E[F[R#tVn*77-076AVOYAGER 2escaped solar system}+E[F[R#tVn*77-084AVOYAGER 1escaped solar system-F[G[R#tZn&89-084BGALILEOheliocentric orbit (Sun)F[G[; D? Gi4 KFinally 3 missions failed:Transit 5BN3 on 21 Apr 1964 aboard Thor AblestarNimbus 3AApollo 13 (70029A) on 11 Apr 1970 which decayed on 17 Apr 1970: G[)H[1)H[oH[ [AddressesFG[oH[5 :$NJ" AddressesY)H[J[ Xn։apCNgF}(@O=H%쉂/품H;eur7P/:ѤRgI=V倉J[eQH≂wbO.3sD" Air Force Space CommandAlascom Inc.Alcatel TelecomAMSCAntrixAPTArabsatArianespaceAsiasatAstrolinkColumbia Communications Corp.Comsat CorporationDTAGEarth Watch Inc.Echostar Satellite Corp.EmbratelEosatEumetsatEutelsatFAIFrance TelecomGE AmericomGE Capital Satellites-EuropeQoH[L[ HP?qOv FzOZӉ(I}MiډN ZXgYg⻧u}$ALIxmh̶R@/yT@^gl^gGlobalstar L.P.HCIHispasat S.A.ILSInformcosmosInmarsat LtdIntelsatIntersputnikIridium LLCISROJSATKaStar Satellite Communications Corp.Korea TelecomLEO OneLoral SkynetLoral Space & Communications LtdMabuhayMeasatMobile Communications Holdings, Inc.Nahuelsat S.A.NASANOAAfJ[N[ ,Q^g{OZf"6]XdOxOZ$Ijg(㼉₭`g{`g UDuWOOyɺ9 B扂NSABNTTOdyssey TelecommunicationsOptus CommunicationsOrbcommOrbital Science CorporationOrion Network Systems Inc.Panamsat CorporationParacomsatPASIPLDTPT Pasifik Satelit NusantaraPT SatelindoPT TelkomRadarSat International (RSI)SCCSESShinawatra Satellite Company LtdSingapore TelecomSpacecom Ltd.HL[ [ ڀkdgO'e`/%1[sIu Ɖz͏tcOfg\@gg'䉂SSTLTDFTelecommTeledesicTelenorTelesat CanadaTelespazioTeracomThuraya Satellite Telecommunications CoTMI CommunicationsTsatTurk TelekomUSSBWorldspaceN[ [G[c2N[o[1go[H[Asia Broadcasting and Communications Network, Ltd. [H[+ $]Asia Broadcasting and Communications Network, Ltd.(ABCN)SM Tower, 979/66-70 Phaholyothin Road, Phayathai, Bangkok, 10400, ThailandTel: +662-298-0044Fax: +662-271-3076Ho[[1Mj[[Air Force Space CommandH[[I `y92SSAir Force Space Command50th Space Wing, 300 O'Malley Ave, Suite 24, Falcon AFB, CO 80912-3024, USAhttp://www.spacecom.af.mil/hqafspc/Programs: DMSP, Fleetsatcom, GPS, UHF8[͂[1͂[[Alascom[[4 65[YAlascom Inc.210 Bluff Road, Box 6607, Anchorage, AK99502-7649, USATel: +1-907-264-7000Fax: +1-907-264-7704Program: Auroraa subsidiary of AT&T@͂[ۃ[16jۃ[ф[Alcatel Telecom[ф[9 @{㋗hPAlcatel Telecom10, Rue Latcore, BP 57, 78141 VELIZY CEDEX, FranceTel: +33-1-3077-8010Fax: +33-1-3077-8066http://www.alcatel.com/our_bus/telecom/content.htmProgram: SkybridgeV%ۃ['[1`'[1[American Mobile Satellite Corporation ф[1[G \//S American Mobile Satellite Corporation(AMSC)10802 Parkridge Blvd., Reston, VA 22091, USATel: +1-703-758-6000Fax: +1-703-758-6111http://www.ammobile.com/NASDAQ:SKYCProgram: AMSCK'[|[1|[#[Antrix Corporation Limited~1[#[) "Antrix Corporation LimitedAntrix Complex, New BEL Road, Bangalore, 560 094, IndiaTel: +91-80-3415474Fax: +91-80-3418981f5|[[1[[Asia Pacific Telecommunication Satellites Company Ltd#[[; DttXXAsia Pacific Telecommunication Satellites Company Ltd(APT)Room 3111-2, 31st floor, One Pacific Plaza, 88 Queens way, Hong KongTel: +852-2-526-2281Fax: +852-2-522-0419http://www.apstar.comNYSE:ATSProgram: Apstar8[ވ[1"ވ[ȉ[Arabsat[ȉ[@ NUu䉂ArabsatPO Box 1038, Riyadh 11431, Saudi ArabiaTel: +966-1-464-6666Fax: +966-1-465-6983Email: arabsat@arab.nethttp://www.arab.net/arabsat/Program: Arabsat< ވ[[1[Ȋ[Arianespaceȉ[Ȋ[8 >2!ArianespaceBoulevard de l'Europe, BP 177, 91006 EVRY cedex, FranceFax: +33-1-6087-6217http://www.arianespace.comProgram: Ariane^-[&[1!&[[Asia Satellite Telecommunications Company LtdȊ[[= H %Asia Satellite Telecommunications Company Ltd(Asiasat)23-24/F, East Exchange Tower, 38-40 Leighton Road, Causeway Bay, Hong KongTel: +852-2-805-6666Fax: +852-2-504-3875http://www.asiasat.com.hkNYSE:SATProgram: AsiasatAsiasat is owned by Hong Kong's Hutchison Whampoa Ltd, Beijing's China International Trust and Investment Corp (CITIC) and Britain's Cable and Wireless Plc: &[#[1"O#[ [Astrolink[ [9 @_jAstrolinkLockheed Martin Telecommunications Astrolink1272 Borregas Avenue, Sunnyvale, CA 94089, USATel: +1-888-278-7565http://www.astrolink.comProgram: AstrolinkN#[Y[1R Y[][Columbia Communications Corp. [][@ N݌RColumbia Communications Corp.7200 Wisconsin Ave., Suite 701, Bethesda, MD 20814, USATel: +1-301-907-8800Fax: +1-301-907-2420columbia@tdrss.comhttp://www.tdrss.comProgram: ColumbiaCY[[1O[[Comsat Corporation][[L f\doCIx ISComsat Corporation[[][6560 Rock Spring Drive, Bethesda, MD 20817, USATel: +1-301-214-3658Fax: +1-301-214-7130http://www.comsat.comNYSE:CQPrograms: Comstar, Intelsat, Marisat, SBSD[[14 [[Deutsche Telekom AG[[@ Na0`mѾDeutsche Telekom AG(DTAG)Godesberger Alle 87-91, 53175 Bonn, GermanyTel: +49-228-181-1211Fax: +49-228-181-8872http://www.dtag.dePrograms: DFS Kopernikus, TvsatA[0[12h0[![Earth Watch Inc.[![9 @qEarth Watch Inc.1900 Pike Road, Longmont, CO 80501, USATel: +1-800-496-1225Tel: +1-303-702-5561Fax: +1-303-702-5562Email: info@digitalglobe.comhttp://www.digitalglobe.comI0[j[1_Bj[[Echostar Satellite Corp.![[< FR4Echostar Satellite Corp.5701 S. Santa Fe Drive, Littleton, CO 80120, USATel: +1-303-723-1000Fax: +1-303-723-1499http://www.echostar.comNASDAQ:DISHProgram: EchostarEchostar is owned at 50% by News Corp.U$j[[1hj[@[Mobile Communications Holdings, Inc.k([@[C TQSMobile Communications Holdings, Inc.(MCHI)1120 19th Street, N.W., Suite 460, Washington, DC 20036, USATel +1-202-466-4488Fax +1-202-466-4493Email: jtedino@mchi.comhttp://www.ellipso.comProgram: EllipsatPrincipal Subsidiaries: Ellipsat International Inc. & Ellipsat Corporation\+[[1JB%[[Empresa Brasileira de Telecomunicaes S.A.@[[3 4wCDEmpresa Brasileira de Telecomunicaes S.A.(Embratel)Avenida Presidente Vargas 1012, Rio de Janeiro 20279-900, BrazilTel: +55-21-216-7535Fax: +55-21-216-8831Program: Brasilsat6[[1j„[[Eosat[[2 2;EOSATSpace Imaging4300 Forbes Boulevard, Lanham, MD 20706, USATel: +1-301-552-0537 or +1-800-344-9933Fax: +1-301-552-3762http://www.spaceimage.comP[[1%ن[[European Meteorologic Satellite<[[x 2_㱭+ xE㬹.މqn͉ˆt.R׉European Meteorologic SatelliteEumetsatAm Kavalleriesand 31, D-64295 Darmstadt, GermanyTel: +49-6151-807-7Fax: +49-6151-807-555http://www.eumetsat.de/Program: MeteosatOrganization created in May 1983 based at Darmstadt, Germany, that counts 17 members: Austria, Belgium, Denmark, Finland, France, Germany, Greece, Ireland, Italy, Netherlands, Norway, Portugal, Spain, Sweden, Switzerland, Turkey and United Kingdom.vS[[# Funding: $4.5 million (1985-1995); Germany 24%, France 18%, Italy 15% and UK 14%U$[[1„͉[Y[EUropean TELecommunication SATellites[Y[ ̀RH(㱭+ xEL> 㬹.މ qn͉ˆtR׉EUropean TELecommunication SATelliteEutelsat70 rue Balard, 75502 Paris cedex 15, FranceTel: +33-1-5398-4747Fax: +33-1-5398-3700Fax on demand: +33-1-5398-2338http://www.eutelsat.orgProgram: EutelsatWhen 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, YugosloviaD[[1uن[\Final Analysis Inc.Y[\: BYǥ Final Analysis, Inc.(FAI)9701-E Phila[\Y[delphia Court, Lanham, MD 20706, USATel: +1-301-459-0100Fax: +1-301-459-0101http://www.finalanalysis.com/Program: Faisat?[\1R͉\\France Telecom\\G \ kFrance Telecom21 rue de la vanne, BP 800, 92542 Montrouge cedex, FranceTel: +33-1-5595-2600Fax: +33-1-5595-2700FTE.PAhttp://www.francetelecom.frhttp://www.globecast.comProgram: TelecomQ \2\1Sf2\4\GE American Communications, Inc.\4\h 5qPdIeF ZSv?qㄋQtGE American Communications, Inc.GE Americom4 Research Way, Princeton, NJ 08540-6684, USATel: +1-800-273-0329Tel: +1-609-987-4000Fax: +1-609-987-4312Email: americom.info@capital.ge.comhttp://www.ge.com/capital/americom/Programs: GE, GE*Star, Gstar, Satcom, Sky, Spacenet, StarsysCompany formed in 1975. Wholly-owned subsidiary of GE Capital Services, a General Electric company.M2\\1oG\\GE Capital Satellites-Europe"4\\A PD"GE Capital Satellites-EuropeSweden House, 2nd floor, 20 St. James' Street, London SW1A 1ES, UKTel: +44-171-302-6302Fax: +44-171-302-6352Email: satellites@ge.geis.comProgram: Sirius 2Subsidiary of GE Americom@\\1Uf!\\Globalstar L.P.\\; Dx≂Globalstar L.P.3200 Zanker Road, P.O. Box 640670, San Jose, CA 95164-0670, USATel +1-408-473-5550Fax +1-408-473-5750http://www.globalstar.com/Program: GlobalstarFounded by Loral Corp. and Qualcomm Inc. K\C\1GC\x\Hughes Communications Inc.5\x\N jlSӉ?J$qHughes Communications Inc.(HCI)PO Box 9712, Long Beach, CA 90810, USATel: +1-310-525-5211Fax: +1-310-525-5220http://www.hcisat.comPrograms: DBS, Galaxy, Panamsat, Spacewaya subsidiary of GM Hughes Electronics> C\\1!\ \Hispasat S.A.x\ \9 @1&̉Hispasat S.A.Apartado P.O. Box: 95.000, 28080 Madrid, SpainTel: +34-1-372-9000Fax: +34-1-307-7705http://www.hispasat.es/Programs: HispasatN\ \1$D \ \International Launch Services \ \2 2IInternational Launch Services(ILS)101 West Broadway, Suite 2000, San Diego, CA 92101, USATel: +1-619-645-6400Fax: +1-619-645-6500http://www.lmco.com/ILS/= \ \1 \t \Informcosmosc \t \) "Informcosmos16 Kazakova Street, Moscow 103064 RussiaTel: +7-095-261-5494Fax: +7-095-261-0090= \ \1DH \ \Inmarsat Ltdt \ \? LC㐮):6SInmarsat Ltd99 City Road, London EC1Y 1AX, United KingdomTel: +44-171-728-1000Fax: +44-171-728-1044http://www.inmarsat.orgPrograms: Inmarsat, ICO9 \ \1 \ \Intelsat \ \9 @ICIxIntelsat3400 International drive NW, Box 63, Washington DC, 20008, USATel: +1-202-944-7500Fax: +1-202-944-7890http://www.intelsat.intProgram: Intelsat= \ \1H \?@\IntersputnikO \?@\f ~wMo7U=Q_t Intersputnik2 Smolensky Lane 1/4, Moscow, 121099, CISTel: +7-095-244-0333Fax: +7-095-253-9906Email: dir@intersputnik.comhttp://www.intersputnik.comPrograms: Express, Gorizont, IntersputnikToday Intersputnik has the following 22 members: Afghanistan, Belarus, Bulgaria, Cuba, Czechoslovakia, Georgia, Germany, Hungary, Kazakhstan, Kirghistan, North-Korea, Laos, Mongolia, Nicaragua, Poland, Tajikistan, Turkmenis \?@\ \tan, Romania, Russia, Syria, Yemen and Vietnam.< \{@\1v{@\'A\Iridium LLCv?@\'A\6 <ЇIridium LLC1575 Eye Street, NW, Suite 500, Washington, DC 20005, USAhttp://www.iridium.comProgram: Iridium5{@\\A\1\A\:B\ISRO'A\:B\? L?:Gw㿓SISROAntariksh Bhavan, New B.E.L. road, Bangalore 560 094, IndiaTel: +91-80-333-4474Fax: +91-80-333-2292http://www.isro.org/Programs: Insat, IRS5\A\oB\1voB\MD\JSAT:B\MD\< FEJSATJapan Satellite Systems Inc. - Kabushiki-gaisha Nihon Sateraito SisutemuzuToranomon 17 Mori Bldg. 5th Fl., 1-26-5 Toranomon, Minato-ku, Tokyo 105 JapanTel: +81-3-5511-7778Fax: +81-3-3597-0601http://www.iijnet.or.jp/JSAT/Program: JcsatJSAT was formed in 1993 by the merger of Japan Communications Satellite Co (JCSAT, which operated the first two JCSAT satellites) and Satellite Japan Corp (SAJAC).V%oB\D\1$GD\qE\KaStar Satellite Communications Corp.MD\qE\> J![dKaStar Satellite Communications Corp.P.O. Box 1471, Evergreen, CO 80437, USADMDTV@aol.comhttp://www.kastarcom.comProgram: Ladybug> D\E\1v>E\F\Korea Telecom8qE\F\A PrKorea TelecomSatellite Business Group, Korea Telecom680-63, Jayang-dong, Kwangjin-gu, Seoul, KoreaTel: +82-2-201-0082Fax: +82-2-458-6430Email: koreasat@ktweb.kotel.co.krhttp://koreasat.nc.kotel.co.kr/welcome.htmlProgram: Koreasat?E\&G\11G&G\H\LEO One (firm)F\H\@ NeM(LEO One150 North Meramec Avenue, #620, St Louis, MO 63105, USATel: +1-314-746-0567Fax: +1-314-721-3410Email: info@leoone.comhttp://www.leoone.comProgram: LEO One= &G\UH\1>UH\.I\Loral SkynetH\.I\9 @ALoral Skynet500 Hills Drive, Box 7018, Bedminster, NJ 07921, USATel: +1 908 470-2328Fax: +1 908 470-2459http://www.loralskynet.com/Program: SkynetQ UH\I\1_SI\J\Loral Space & Communications Ltd.I\J\K d'tz6w۴w퉂Loral Space & Communications Ltd600 Third Ave., New York, NY 10016, USATel: +1-212-697-1105Fax: +1-212-661-8988http://ssloral.comProgram: Loralsat, Morelos, Orion, SolidaridadT#I\J\1IJ\K\Mabuhay Philippines Satellite Corp.J\K\3 4"ZMabuhay Philippines Satellite Corp.(MPSC)21/F Pacific Star Bldg., Makati corner Sen. Gil Puyat Avenues, Makati 1200, PhilippinesTel: +63-2-811-5636Fax: +63-2-811-5639Program: Mabuhay7J\ L\1S L\L\MeasatK\L\9 @K*MeasatP.O.Box 12202, Kuala Lumpur, 50770, MalaysiaTel : +60-3-244-3388Fax : +60-3-242-7510 or +60-3-202-5520http://www.jaring.my/measat/Program: Measat? L\*M\1J*M\M\Nahuelsat S.A.L\M\9 @!"%ljNahuelsat S.A.Lavalle 472, Piso 3, 1047 Buenos Aires, ArgentinaTel: +54-1-327-2292Fax: +54-1-327-2319nsat@ba.netProgram: Nahuelsat5*M\(N\1(N\N\NASAdM\N\/ .NASA600 Independence Avenue, SW, Washington DC 20546Tel: +1-202-453-1000http://www.nasa.gov5(N\N\1TJN\\NOAAN\\Q p LȉTɑWi<ʉNOAAOffice of Satellite OperationsFederal Building 4, Room 135, 4401 Suitland Road, Suitland, MD 20233Tel: +1-301-457-5130http://www.noaa.govPrograms: Goes, Nimbus, NOAA, NPON\\N\ESS, TirosNN\i\1i\6\Nordiska Satellitaktiebolaget\6\9 @)ڢyNordiska Satellitaktiebolaget(NSAB)Box 17666, 118 92 Stockholm, SwedenTel: +46-8-671 25 90Fax: +46-8-671 21 81Programs: Sirius, Tele X[*i\\1ha\\Nippon Telegraph and Telephone Corporation 6\\@ N4\Nippon Telegraph and Telephone Corporation(NTT)1-6 Uchisaiwai-cho, 1-chome, Chiyoda-Ku, Tokyo 100, JapanTel: +81-3-3509-3101Fax: +81-3-3509-4290http://www.ntt.co.jpPrograms: N Star, SakuraK\\1\\Odyssey Telecommunications\\1 0?Odyssey TelecommunicationsOne Space Park, Redondo Beach, CA 90278, USATel: +1-310-814-8888 Fax: +1-310-814-1400 http://www.trw.com/seg/sats/ODY.html E\\1xa\1\Optus Communications3\1\; DOptus Communications101 Miller Street, North Sydney, NSW 2060, AustraliaTel: +61-2-342-7800Fax: +61-2-342-7100http://www.optus.net.auProgram: Optus49% of the firm is owned by Cable & Wireless, 25% by Mayne Nickless Ltd of Australia.8\i\1$i\ކ\Orbcommu,1\ކ\I `Y㐫xOOrbcomm21700 Atlantic Boulevard, Dulles, Virginia 20166-6801 USATel: 1-800-orbcommTel: +1-703-406-6000Fax: +1-703-406-3504Email: orbcomm@orbital.comhttp://www.orbcomm.netPrograms: OrbcommParent companies are Orbital Sciences Corp. (50%), Teleglobe Inc. and TRI Inc. of Malaysia.Li\*\1m *\K\Orbital Science Corporation!ކ\K\< FXdOOrbital Science Corporation(OSC)21700 Atlantic Boulevard, Dulles, Virginia 20166-6801, USATel: 1-800-orbcommTel: +1-703-406-5000Fax: +1-703-406-5511http://www.orbital.comNASDAQ:ORBISubsidiaries: Orbcomm, OrbimageK*\\1$ \މ\Orion Network Systems Inc.HK\މ\F Z۴xOrion Network Systems Inc.2440 Research Boulevard, Rockville, MD 20850, USATel:US: 1-800-786-7466Int: +1-301-258-8101Fax:+1-301-258-3222http://www.OrionNetworks.netNASDAQ:ONSIProgram: OrionWas bought by Loral Space & Communications LtdE\#\1h #\F\Panamsat Corporation#މ\F\< F?J$Panamsat CorporationOne Pichwick Plaza, Greenwich, CT 06830, USATel: +1-203-622-6664Fax: +1-203-861-8688http://www.panamsat.comNASDAQ: SPOTProgram: Panamsat81% of the firm is owned by Hughes Electronics Corporation; #\\1 w\0\ParacomsatF\0\* " Paracomsat25 de Mayo 516, 6 Piso, (1002) Buenos Aires, ArgentinaTel: +54-1-313-5058 or 313-5158 or 313-9829Fax: +54-1-311-1852O\\1:6\j\Philippine Agila Satellite Inc0\j\, &Philippine Agila Satellite Inc (PASI)Domsat Holdings Inc18th floor Pearlbank Center, 146 Valero St., Salcedo Village, City of Makati, PhilippineTel: +632-840-30-21Fax: +632-750-57-64V%\\1Fw\\Philippine Long Distance Telephone Coj\\4 6y"ZPhilippine Long Distance Telephone Co(PLDT)7/F Ramon Cojuangco Building, Makati Ave., Makati, Metro Manila, PhilippineTel: +632-816-8911Fax +632-818-6800TEL.PSProgram: MabuhayH\\16\M\PT Media Citra IndostarI\M\3 4-PT Media Citra IndostarElektrindo Building, 8/F, Jl. Kuningan Barat No. 8, Jakarta 12710 IndonesiaTel: +62-21-526-9380Fax: +62-21-526-9389http://www.indovision.co.id/Media Citra is owned by Matahari Lint\M\\as Cakrawala which is 61 percent controlled by PT Datakom Asia.M\\1~ꀹ\\PT Pasifik Satelit Nusantara1M\\G \>؉PT Pasifik Satelit NusantaraMulia Centre # 1201, Jl. Rasuna Said Kav X/6 No. 8, Jakarta 12940, IndonesiaTel: +62-21-5229292Fax: +62-21-5229293Email: psn@psn.co.idhttp://www.psn.co.idNASDAQ:PSNRYProgram: M2A, Palapa= \\1>\ \PT Satelindo\ \: B>؉PT SatelindoPT Satellit Palapa Indonesia (Satelindo)Ji Daan Mogot KM 11, Jakarta Barat 11710, IndonesiaTel: +62-21-545-1745Fax: +62-21-545-1746http://www.satelindo.co.idProgram: Palapa: \C\1ꀹC\\PT Telkomn \\1 2>؉PT TelkomJl. Japati No. 1, Bandung, IndonesiaTel: +62-22-452-2330Fax: +62-22-706-225Program: PalapaGC\)\1@ނ)\"\RadarSat International\"\: BgTRadarSat International(RSI)275 Slater Street, Suite 1203, Ottawa, Ontario K1P5H9, CanadaTel: +1-613-238-6413Fax: +1-613-238-5425http://adro.radar1.sp-agency.caProgram: RadarsatQ )\s\1Qs\s\Space Communications Corporation"\s\: BY'# Space Communications Corporation(SCC)2-8, Higashi-shinagawa 2-chome, Shinagawa-ku,Tokyo 140, JapanTel: +81-3-5462-1350 Fax: +81-3-5462-1390http://www.superbird.co.jpProgram: SuperbirdQ s\\14ނM\\Socit Europenne de Satellitess\\: BS ܜSocit Europenne de Satellites(SES)Chteau de Betzdorf, 6815 Betzdorf, LuxembourgTel: +352-710-7251Fax: +352-710-725324http://www.astra.luProgram: AstraB\\1Ԅ\\Singapore Telecom\\1 0Singapore Telecom31 Exeter Road, Comcentre, Singapore 0923, SingaporeTel: +65-838-3388Fax: +65-734-8119http://www.singtel.comQ \\1JM\\Shinawatra Satellite Company Ltd\\9 @v胉Shinawatra Satellite Company Ltd41/103 Rattanathibet Road, Nonthaburi 11000, ThailandTel: +662-591-0736Fax: +662-591-0706http://www.shinawatra.co.th/ssa/satel.htmProgram: Thaicom> \)\1Ԅ߆ )\\Spacecom Ltd.K\\; D3 Spacecom Ltd.Twin Towers II, suite 917, 35 Jabotinsky St., Ramat Gan 52511, ISRAELTel: +972-3-6134720Fax: +972-3-6134723Email: spacecom@netvision.net.ilProgram: AmosSpacecom is a joint venture of Gilat Communication Engineering, Israel Aircraft Industries, General Satellite Services Company and MER Services Group.T#)\\1Շ \3\Surrey Satellite Technology Limited0\3\: B~ꠉSurrey Satellite Technology Limited(SSTL)Centre for Satellite Engineering Research, University of Surrey, Guildford, Surrey GU2 5XH, UKTel: +44-1483-259143 Fax: +44-1483-259503http://www.ee.surrey.ac.uk/EE/CSER/UOSAT/Program: UosatH\{\1߆Z {\3\Tldiffusion De France3\3\3 4 STldiffusion De France(TDF)21-27 rue Barbs, 92120 Montrouge, FranceTel: +33-1-4965-1000Fax: +33-1-4657-4850Program: TDFM{\\1]Շ1 \\Telecomunicaciones de Mexico3\\9 @tz6ww퉂Telecomunicaciones de Mexico(Telecomm)Eje Central Lazaro Cardenas No. 567, P.B., Ala Norte, Col. Narvarte, 03020 Mexico, D.F., MexicoTel: +52-5-629-1392Fax: +52-5-538-8505Programs: Morelos, Solidaridad: \\1Z \]Teledesic\]@ Na\]\NꉂTeledesic2300 Carillon Point, Kirkland, WA 98033, USATel +1-425-602-0000Fax: +1-425-602-0001Email: info@teledesic.comhttp://www.teledesic.comProgram: TeledesicK\]131]]Telenor Satellite Services]]9 @_Telenor Satellite ServicesP.O.Box 6914, St. Olavs pl., Olso, 0130, NorwayTel: +47-22-77-79-50Fax: +47-22-77-79-80http://www.international.telenor.noProgram: Thor?]8]1|8]u]Telesat Canada=]u]B RTelesat Canada1601 Telesat Court, Gloucester K1B 5P4, Ontario, CanadaTel: +1-613-748-0123Fax: +1-613-748-8712Email: info@telesat.cahttp://www.telesat.caProgram: AnikTelesat Canada belongs for half to the State and private companies.; 8]]1Q]]Telespaziou]]; DvTelespazioVia Alberto Bergamini 50, Roma 00159, ItalyTel: +39-6-4987-2240Fax: +39-6-4987-2743http://www.Telespazio.itProgram: ItalsatOn 31 Dec 1993 Telespazio was equally owned by STET, ITALCABLE and RAI8]]1%]]Teracom]]@ NAڢTeracomAgnesfridsvgen 113 C, S-202 50 Malm, SwedenTel: +46-40-14-18-00Fax: +46-40-14-18-12info@teracom.sehttp://www.teracom.seProgram: SiriusX']6]1O6]-]Thuraya Satellite Telecommunications Co]-]@ NoThuraya Satellite Telecommunications CoPO Box 33344, Abu Dhabi, UAETel: +971 2 2084235Fax: +971 2 330064thuraya@emirates.net.aehttp://www.thuraya.com/Program: ThurayaC6]p]1%]p]#]TMI Communications-]#]2 2LwTMI CommunicationsP.O. Box 9826, Ottawa, Ontario, K1G 5M2, CanadaTel: +1-613-742-0000Fax: +1-613-742-4100Program: MSATR!p]u]1<u]_ ]TCI Satellite Entertainment, Inc.#]_ ]4 6mTCI Satellite Entertainment, Inc.(TSAT)4100 East Dry Creek Road, Littleton, CO 80122, USATel: +1-303-486-3800Fax: +1-303-486-3891NASDAQ:TSATA, NASDAQ:TSATBProgram: Tempo= u] ]1] ]C ]Turk Telekomv_ ]C ]1 2]cKTurk TelekomAydinlikevler, Ankara 06103, TurkeyTel: +90-312-313-15 71Fax: +90-312-313-15 98Program: TurksatU$ ] ]1tk ] ]United States Satellite BroadcastingC ] ]= HlSUnited States Satellite BroadcastingUSSB3415 University Avenue, St Paul, NM 55114, USATel: +1-612-646-5555Fax: +1-612-642-4103http://www.ussbtv.comNASDAQ:USSBProgram: DBSA division of Hubbard Broadcasting Inc; ] ]1W ] ]# ]Worldspace  ] ]A PuWorldspace11 Dupont Circle, N.W., 9th Floor, Washington, DC 20036, USATel: +1-202-884-7800Fax: +1-202-884-7900Email: gene@mail.worldspace.comhttp://www.worldspace.comProgram: Worldstar& ]# ]# 1 ]1/0Helvtlp[6Times New Roman~hc1SymbolC:\TEMP\Arial Courier MS SerifttttMS Sans SerifvTimes LHelvetica펔SystemCourier NewłāArial Narrow҂Century GothicŴŴClearface Gothic MTLucida Sans TypewriOptimumc1255 SwitzerlandtSwitzerlandBlackSwitzerlandCondBlacSwitzerlandCondenseBodoni-DTCBodoni MT Bold CondBodoni MT Ultra BolLucida Sans UnicodeLucida ConsoleLotusLineDrawMonotype SortsMT ExtraNWingdingst uGaramonduuEnglish157 BTuUmbra BTuFranceuuu Mural ScripttMS DialogQTBlackForestBook AntiquauLucida FaxCarrKeysNew Berolina MTBalloonDomCasual BTuBlippo-HeavyuuDesdemonauSmall FontsQLetter Gothic 6 PitTms Rmnuu (       @  GsGsGsGsGsGsGsGsGsGsGsGGsGsGsGsX )o),%%/.*t%t9*+tgC+L+[,,',,,/,S,Z8ZZ]S,-n% Tjʂ----f.uM4ý Zn~B.C/g//l/Ё/.X/f///}0#0߂2Z333ހ3΃3A444}4+4555҃FA=AB2BBpH .iQi56%%n%6!6d7B7T88^:!6o:o:<<<<<<<!=== Ӄ!#llm>*=++s,M,,,,A,,,5Q566t6E666b6,p,G-----[-L----4. ....B..ԁ..H.L///"//a/$/ҁ//9/+000k0 000[00҂0017111h1m11S11Ӄ1}2L2]222O2222T23~3F3)333z333444d4(4W4P4044ڃ455r5K5555'>>>P>Ă>>?<?܈Z??@o@AكAQo:V!6B GBMBhCuD,F;G- G1d]SGGHHHIIaJK+L.L$MrN&NOOOPTPr|PwQQQQQ l QRW?6z>zуzMzv{|l||j}}}}}x7_>}_>\_>_>xBB8<<_><<<<7GnnaRARRSwSn~S SSSЃST:TT688K88V89<?6AA)T<UUUUtCUU%P?BtVVV] 9 6RzCC:%0%V{VRxVWcW WXZZZ]qRxVlZK;4Z|[Z|[[-[[[N%rс ' (b%HJ\-#0dd")a^\b%Ƅ}G\Lb\\I]]]d%dԀ+yH f'wIRyK.dNhK.5W+%?@wCnV>@?-d53hɂg灤Ui^у@9z^hxy> + XM'`43:nуlC ]z@z7y(@zPL e F^,^z}E4FqEGf.ф?Fn WAK ogEE0JG'Cڃ4iGςzhIрEVG{0=G]{ARăEFegguCF nP>RK?{ ƒ5ICR$5FF1>]Gv1[mDrFF({[GcGGI5[DS" U+^kA5@%((jf|4*׃Q^%jǁ o`  FA||Dׂ .a^rms86Ă>SOGF|>2n i;f1G *FA߂250(',=Z3;V9\ł3X킗?*ssS[oCƀ\ҁ^wSX,N54X9]>@+=AiJ *N>d@3J`G\s s`ł %)D0ajb`uS.jNptjobd:^3=q%...b .KVbu+j?bk%-=Kqss0;}zb~/'<.m<.<.-<.k˂EI B?+ERBybBWco A)u HVˁS%4Kt{t3UL+4bx c&?V+ps[,ttq\߀'cU....+jckuPbc0h0Ej@6]n+9cxx̃с BoklkkЃSuh)fc|DqVr]0r kU ̀ 45ӂk*:TtK~////`mˀ$H5h mJρSmK8Rl āقv.enm&Jn`̃색߃>IBo!G{BMD0>uJw܀m$\Ѓ(ۀO#m*vƂ̃n3,#6e>Yނ H@nB|I\(;N_:M`}E6Ё?q4X9])e€feOƃcr炕fnZvf'5Q\@P\\\[tuF,L`IJrpN Ȁ`fju O넎ɂpHq[qBn3e8fs1G@3^6Ut\{ǀMBL3@LLk/$e/ UU//Nm|gW[: nGnn0n<wƒEwr>σ>l|fāf&U$ fIi͂+4كAg_,$To,kn~9<oЁe+;,}4<v/lv/tjwv/v/qgoOuÂ<+QlL]3junZ҅][ó7k8EsEEEV|r9og  逤Odƀ# +<DpV8Cp4€ׁ%^9x_Qg<=ր{^3-Kр-(IZ?60Pp"B akb]u+ƀ̂-eqf2.*Ԃa.`xgo";:Tт8u&e}Nˀ0k"Sg:1/1u1122olZȃQrp2og7[b{&%O$ 6-N $(XㄷoNCd7 `i5e W4 49h+HчKu7UaJ!l̂Q@ʀ =Ipq w4Rp'GgOgJ-k$Od: 22J2u223 G|hX$:&:π3/m ePKʂ.^g%GdvS>#|=ᄥP| KDahC\ #0y2PAj'\vL 3 B ,2 h_9I+L"!OɃBtLB. #IW///;B7<ၴ`0ru*rwӃ![]38z܂Up#l!=sB)#DP e 9 CwmiK|[11^`2 pJg''q:P<L!a\Z<Xπ^9UW13{_hs[@zt 88v6GKc~J\P.LՃ?A1z ;D;;;V;:~:;wuD^Zǁ{::^'raoم<c8H F1z YIy&[' z-y F_PZ]]/wa%]1^^^D.^C/wbwIwxxЀxy/{^cZ]i^mnBno pCpcq_Z[b|bjqlUƄl  ' N  G   . cY"#z(n!u,%P_`. u`0`~vvEww6wwzz*{{r|$|~~τ~6`Oc`a:%Haj HabVbbbl{Z^%1[b4bbqnuƒׂ .>2V9\ł3X\ҁ4X9]*N>`ł .05#SE`mˀ$HRā&Jn`̃>IBuJw$\Ѓ(OƂ̃#6>Y@|I(;N_:M`}6q4X9]OƃcrnQ@P,IJpOq6Ut\{ǀ3@Nσ>l͂glO]VƀD€%_^3Kр-(0Pp"Bb]e2a"ȃQrp&% ` Hч!Q@4Rp'GgG PK%GPD\ ',29O]j3s'πBP'tCHos s KccEc.d%l6}mmԁm6mnndddV^^^^A)AKegggKeSJ`G\Na df%Ideeee@z%W%%%0xx3e%%mm)e;ffijjajjtjjkkoklkkӂk%lnl llflll mSmm܀m#mnBn2oIp pnGnnnooooo2ooIpCpp pqcq~vff|ggggZg8zIdhxxxyy3yyz{؂{7||}~~\ԃ\Zh5hhhhhi5hhhiqww]ijjajjtjjkkoklkkӂk%lnl llflll mSmm܀m#mnBnnGnnnooooo2ooIpCpp pqcq́q%́@r^rmssss sqssKt{tttttc6=JPff„ʂڂ2Ƅ}[n?b\b{~B[ǃU.'5D`*„ن0ǃن̂e $t ]k`˂oGtԀ+f5dg9X3уPECR1[׃8iG킗X`U" !!! !b C!"F ! 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qCATNR 23444CATNR 23445CATNR 23446CATNR 23448 CATNR 23455CATNR 23461CATNR 23463CATNR 23464CATNR 23465 CATNR 23467$CATNR 23470(CATNR 23471,CATNR 234720CATNR 234734CATNR 234748CATNR 23475<CATNR 23476@CATNR 23497DCATNR 23501HCATNR 23511LCATNR 23512PCATNR 23513TCATNR 23519XCATNR 23521\CATNR 23526`CATNR 23528dCATNR 23530hCATNR 23533lCATNR 23536pCATNR 23537tCATNR 23545xCATNR 23546|CATNR 23547CATNR 23549CATNR 23553CATNR 23558CATNR 23560CATNR 23567CATNR 23571CATNR 23581CATNR 23584CATNR 23589CATNR 23596CATNR 23598CATNR 23601CATNR 23603CATNR 23605CATNR 23606CATNR 23607CATNR 23609CATNR 23613CATNR 23620CATNR 23621CATNR 23622CATNR 23628CATNR 23633CATNR 23636CATNR 23639CATNR 23642CATNR 23646CATNR 23649CATNR 23651CATNR 23653CATNR 23657CATNR 23668CATNR 23669CATNR 23670CATNR 23672 CATNR 23674CATNR 23676CATNR 23680CATNR 23686CATNR 23696 CATNR 23704$CATNR 23710(CATNR 23711,CATNR 237120CATNR 237174CATNR 237238CATNR 23728<CATNR 23730@CATNR 23731DCATNR 23734HCATNR 23735LCATNR 23736PCATNR 23741TCATNR 23748XCATNR 23751\CATNR 23752`CATNR 23754dCATNR 23757hCATNR 23763lCATNR 23764pCATNR 23765tCATNR 23768xCATNR 2377|CATNR 23775CATNR 23779CATNR 23787CATNR 23788CATNR 23789CATNR 23790CATNR 23791CATNR 23792CATNR 23794CATNR 23802CATNR 23816CATNR 23818CATNR 23827CATNR 23833CATNR 23839CATNR 23842CATNR 23846 qCATNR 23851CATNR 23853CATNR 23855CATNR 23857CATNR 23864CATNR 23865CATNR 23868CATNR 23871CATNR 23877CATNR 23893CATNR 23907CATNR 23908CATNR 23915CATNR 23940 CATNR 23943 CATNR 23945 CATNR 23948 CATNR 23949 CATNR 23953 CATNR 23967 CATNR 24208 CATNR 24209 CATNR 24274$ CATNR 24277( CATNR 24278, CATNR 242850 CATNR 242914 CATNR 24293< CATNR 24297@ CATNR 24304D CATNR 24305H CATNR 24307L CATNR 24313P CATNR 24315T CATNR 24320X CATNR 24435\ CATNR 24634` CATNR 24640d CATNR 24645h CATNR 24652l CATNR 24653p CATNR 24665t CATNR 24670x CATNR 24674 CATNR 24677 CATNR 24680 CATNR 24702 CATNR 24713 CATNR 24714 CATNR 24720 CATNR 24725 CATNR 24726 CATNR 24727 CATNR 24728 CATNR 24729 CATNR 24730 CATNR 24732 CATNR 24737 CATNR 24742 CATNR 24744 CATNR 24748 CATNR 24753 CATNR 24761 CATNR 24768 CATNR 24769 CATNR 24772 CATNR 24779 CATNR 24780 CATNR 24786 CATNR 24792 CATNR 24793 CATNR 24794 CATNR 24795 CATNR 24798 CATNR 24800 CATNR 24805!CATNR 24808!CATNR 24812!CATNR 24819 !CATNR 24820!CATNR 24827!CATNR 24834!CATNR 24837!CATNR 24838$!CATNR 24839(!CATNR 248400!CATNR 248414!CATNR 248468!CATNR 24869Intelsat 202>Intelsat 203>Intelsat 204 >Intelsat 301>Intelsat 302>Intelsat 303>Intelsat 304>Intelsat 305 >Intelsat 306$>Intelsat 307(>Intelsat 308,>Intelsat 4010>Intelsat 4024>Intelsat 4038>Intelsat 404<>Intelsat 405@>Intelsat 406D>Intelsat 407H>Intelsat 408L>Intelsat 4A01P>Intelsat 4A02T>Intelsat 4A03X>Intelsat 4A04\>Intelsat 4A05`>Intelsat 4A06d>p Intelsat 501h>Intelsat 502l>Intelsat 503p>Intelsat 504t>Intelsat 505x>Intelsat 506|>Intelsat 507>Intelsat 508>Intelsat 509>Intelsat 510>Intelsat 511>Intelsat 512>Intelsat 513>Intelsat 514>Intelsat 515>Intelsat 601>Intelsat 602>Intelsat 603>Intelsat 604>Intelsat 605>Intelsat 701>Intelsat 702>Intelsat 703>Intelsat 704>Intelsat 705>Intelsat 706>Intelsat 707>Intelsat 708>Intelsat 709>Intelsat 801>Intelsat 802>Intelsat 803>Intelsat 804>Intelsat 805>Intelsat 806>Intelsat 901>Intelsat 902>Intelsat 903>Intelsat 904?Intelsat K?Intelsat KTV?Intelsat MCS-A ?Intelsat MCS-B?Intelsat MCS-C?Intelsat MCS-D?Intelsat Star?Interball 2 ?Interbol 1$?Interbol 2(?Intercosmos,?Intercosmos 010?Intercosmos 184?Intercosmos 228?Intercosmos Bulgaria 1300RS 108uRS 10/11@Spas 3ySpas 4ySPIN 2ySPIN-2ySPLAVySpotySpot 1ySpot 2ySpot 3ySpot 4ySpot 5ySpot 6ySputnikzSputnik 01zSputnik 02zSputnik 03 zSputnik 04zSputnik 05zSputnik 06zSputnik 07zSputnik 09 zSputnik 10$zSputnik 11(zSputnik 40,zSputnik Jr0zSRATS4zSret8zSret 1Spas 3?STS #28@STS 82ATelstar 7BUHF 7CUSA 134DGMS 2-#HO6VLO-#  I6O6چO-# IpO6O B3O OC:\TEMP\~hc88J#D-#5?GFO7zO-#e5S6O8OJO5LO a_laQ)5LOncWM-#E  IO)78O-#a_laq yL4Od7Onc-#deltPO7LO a_lang2057lanc_atlas_centaur lang2057}O-#tro EpO`O-#& .IO66O!-# JO6O -#S6q/ zOC*O,OGals 3 prog-#{ IO5Oԍ-#a_la KO 6Oa-#48@SBOD6O cosm8NO3_-#-F/&;)Lz#Main index4Alphabetical satellite indexdDesignationX TSE World Satellite CD WSCD Subscription order form7 WSCD Single order forms License Agreement Order form Order form with VAT] BibliographyAcknowlegdmentIVersionsCompatible softwareHow to use this encyclopedia?TSE (franais)Licence d'utilisationJJean-Jacques SerraGunter KrebsCountries of origin' ArgentinaAustraliaBrazilrBulgariaCanadacChileChinaCISACzechoslovakiaEgypt.FranceNGermany#Hong KongIndiaIndonesiaIsraelVItalyJapanKorea (South)xLuxemburgLMalaysia MexicoǀNetherlands~Norway5Pakistan˂PhilippinesWPortugalSpainRSweden-ThailandTurkeyUkraineUnited KingdomMUnited StatesArab StatesEurope9InternationalNATOThe Clarke BeltO!}!!To be launched%%%Glossary%Printing'C-band US frequency chart (starting horizontal) (C-band US frequency chart (starting vertical)߁(First in History)AbrixasA)o)ACeS*.*ACTS*Adeos 1+Adeos 2++AEM 1L+AEM 2[,AEM 3,Program: Aeros,',Aeros 1,Aeros 2,Afristar%,S,Program: Agrani,-Ajisai-Alexis-Alos~--Program: Alouette--Alouette 1f.Alouette 2..B.Amos 1/#/C/Amos 29/g/Program: AMPTEo//AMPTE CCEl/AMPTE IRMЁ/AMPTE UKSX/Program: AMRC8/f/Program: AMS/AMSC 10Program: Andesat0#0Program: Anik0B011?11e1111h1k22222Anik's Ku-band transponder frequency chart߂2Anik A1Z3Anik A23Anik A33Anik B1ހ3Anik C1΃3Anik C2A4Anik C34Anik D14Anik D2}4Anik E1+4Anik E25Anik F155Anna 1B5ANSi5Apex6APMT66Apple!6Program: Apstar~6́6d7Apstar 1#7B7Apstar 1A8+8IIIIIIIIT8Apstar 28Apstar 2R: :^:Apstar 3A:o:Program: Arabsat::::i:x:X;;ۀ;;];<Arabsat 1A<Arabsat 1B<Arabsat 1C<ڀ<<Arabsat 1D<Arabsat 1E<Arabsat 2A!=Arabsat 2B=Arabsat 3A<>?>m>Program: Argos'>Program: Ariel\>>Ariel 1>Ariel 2P>Ariel 3Ă>Ariel 4>Ariel 5?Ariel 6<?Aries 1,?Z?Arsne?Artemis@@Aryabhatao@Program: ASC3@U@I@ASC's C-band transponder frequency chartAAASC 1كAASC 2B BCBBProgram: AsiasatBMBAsiasat 1CBChCAsiasat 24DTDuDAsiasat 3MEmEF,FAsiasat 3S G;GAsiasat 4݀G GAsiastar%GSGProgram: AsterGGAstrixHHProgram: AstraoHHAstra 1AHGHwHHIAstra 1BIIIIyIIAstra 1CJJJ1JaJAstra 1D'KWKKKKAstra 1EkLLLL+LAstra 1FnLL΂LL.LAstra 1G M$MAstra 1HN,NDNrNAstra 1KXNNNւNN&NAstra 2A/O]O~OOOOAstra 2BЁOOAstrid 1OPAstrid 2&PTPProgram: AstroPPAstro AwQAstro BQAstro CQAstro DQAstro EQQProgram: AstrolinkRRAsusat 13RaRProgram: ATSRARATS 1RATS 3SATS 5wSATS 6SAura SProgram: AuroleRSSAurole 1SAurole 2ЃSAurole 3TProgram: Aurora'TRT:TAurora_1TAurora 2wTTAXAFUUProgram: AyameUUAyame 1UAyame 2kUAzurUBadr AUBadr B[VVProgram: BhaskaraVVBhaskara 1VBhaskara 2%VBonum 1VVProgram: Brasilsat4WWWWWvWBrasilsat A1cWBrasilsat A2 WBrasilsat B1XɁXXBrasilsat B2YZ8ZmZZBrasilsat B3ZBrasilsat B4>ZlZBremsatZProgram: BSAT˃ZZ Z|[Bsat 1A[Bsat 1B-[Program: BSB[[$[[BSB 1[BSB 2J\Cakrawarta 1G\Castor\Caribstar4\b\Program: Cat\\Cat 1III]Cat 2]Cat 3]Cat 4Z]Program: CBERSZ]]CBERS 1a]]Program: Celestis^1^Celestis 1^Celestis 2^Program: Celestri^.^Cerise^Champ__Chinastar 1P_Program: Cluster`Program: Cluster 2``Cobe`Program: Columbia`+```Columbia AOR``5`c`Columbia POREasaaaaaCometsHaProgram: ComstarÂa a^a.aComstar 1VbComstar 2bComstar 3bComstar 4[bCoronas 14bCorsa BbCos B)cKcCoupon 1cCoupon 2cEcCoupon 3d.dCourier 1BdCTAdCTSdProgram: Cyberstarބd dProgram: DashIdProgram: DBS deSe|eeDBS 1eDBS 2eDBS 3eDBS 4e3eDebut)eDelta Star;fDenpafProgram: DFS KopernikusaffkffffDFS 1|gDFS 2gDFS 3+ggProgram: DiadmefggDiadme 1gDiadme 2gDiapasonhProgram: DiscovererhProgram: DMSPhhh5hDMSP B5D2-3hDMSP B5D2-7hDMSP B5D2-8iDMSP B5D2-9iProgram: Dong Fang Hongiiii2iiijjDong Fang Hong 01jDong Fang Hong 02ajDong Fang Hong 03jDong Fang Hong 04tjDong Fang Hong 05jDong Fang Hong 06kDong Fang Hong 07kDong Fang Hong 08okDong Fang Hong 09lkDong Fang Hong 10kDong Fang Hong 11ӂkDong Fang Hong 12%lDong Fang Hong 13nlDong Fang Hong 14 lDong Fang Hong 15lDong Fang Hong 16flDong Fang Hong 17lDong Fang Hong 18lDong Fang Hong 19 mDong Fang Hong 20SmDong Fang Hong 21mDong Fang Hong 22܀mDong Fang Hong 23#mDong Fang Hong 24nDong Fang Hong 25BnDong Fang Hong 26nDong Fang Hong 30GnDong Fang Hong 31nDong Fang Hong 32nDong Fang Hong 33oDong Fang Hong 34oDong Fang Hong 35oDong Fang Hong 36oDong Fang Hong 37oDong Fang Hong 382oDong Fang Hong 39oDong Fang Hong 40IpDong Fang Hong 41CpDong Fang Hong 42pDong Fang Hong 43 pDong Fang Hong 44qDong Fang Hong 45t\\Cat 1IIcqDong Fang Hong 46ҁqqDove@rProgram: DSCSr rrr^rDSCS 2-01msDSCS 2-02sDSCS 2-03sDSCS 2-04sDSCS 2-05 sDSCS 2-06qsDSCS 2-07sDSCS 2-08KtDSCS 2-11{tDSCS 2-12tDSCS 2-13tDSCS 2-14tDSCS 2-15tDSCS 2-16Essa 7Essa 8Essa 96Program: ETSEETS 1=ETS 2ETS 3ETS 4JETS 5ETS 6PETS 7fETS 8ڂProgram: Eurasiasat-[Eureca 1Program: Europe*Star0Program: EuroskywayǃProgram: Eutelsat8₆ ++VEutelsat 1F1̂Eutelsat 1F2eEutelsat 1F3Eutelsat 1F4lEutelsat 1F5え Eutelsat 2F1$Eutelsat 2F2tEutelsat 2F3Eutelsat 2F4 Eutelsat 2F5Hotbird 1&T}Hotbird 2<Hotbird 3Hotbird 4Hotbird 5ZEutelsat 3F1/]Eutelsat 3 SESAT=kEutelsat 3F2Eutelsat 3F3lEutelsat 3F4EUVE`Exos˂Exos AoExos BGExos CExos DExosattProgram: ExplorerIExplorer 01ԀExplorer 03+Explorer 04Explorer 06fExplorer 07Explorer 08Explorer 09Explorer 105Explorer 11Explorer 12Explorer 13Explorer 14dExplorer 15Explorer 16gExplorer 17Explorer 189Explorer 19XExplorer 20Explorer 21Explorer 223Explorer 23Explorer 24Explorer 25уExplorer 26PExplorer 27Explorer 28Explorer 29EExplorer 30Explorer 31CExplorer 32Explorer 33RExplorer 34Explorer 36Explorer 38Explorer 391Explorer 40[Explorer 41׃Explorer 42Explorer 438Explorer 45iExplorer 46GExplorer 47Explorer 48킗Explorer 50Explorer 51XExplorer 52Explorer 53Explorer 54Explorer 55`EXPRESS (German)Program: Express4bh(Express 1}+UExpress 2W焚Program: Expressway.EyesatFalcon GoldProgram: Fasat6Fasat Alfa&Fasat BravoProgram: FaisatFaisat 1AFaisat 2vQFaisat 1awFASTFirewheel|Program: Fleetsatcom3EFleetsatcom 1&Fleetsatcom 2߀Fleetsatcom 3kFleetsatcom 4̃Fleetsatcom 5Fleetsatcom 6_Fleetsatcom 7Fleetsatcom 8WForteфFR 19FrejaProgram: Fuji(XFuji 1A8Fuji 1BrFuji 2,FUSE,[Program: Galaxyр䃡4rGalaxy 1怢Galaxy 1R failure7Galaxy 1RBmGalaxy 2Galaxy 3#Galaxy 3R.[Galaxy 4.X+Galaxy 5Galaxy 6逤Galaxy 7oGalaxy Ku-band frequency chart?Galaxy 8iWGalaxy 9f䄥Galaxy 10>`Galaxy 11Ft*SGalex.Program: Gals4Gals 1Gals 2XGals 3sGals 4Program: GED?܂GE 15GE 1AsrIGE 2^7GE 2AGE 3GE 4FGE 5Program: GE*StartProgram: GeizerAoDGemstardGeos 3GFO 1JGFO 2҅GeotailGFZ 1KProgram: GGSEGGSE 1GGSE 2(GGSE 3KGGSE 4?GGSE 5cProgram: GlobalstarEŃ'Globalstar 1Globalstar 2Globalstar 3Globalstar 4Globalstar 6Globalstar 8IGlobalstar 14yGlobalstar 15_Program: Glonass0Program: GMSփ愯GMS 1BGMS 2wGMS 3GMS 4GMS 5[Program: GoesFGoes 01;Goes 02Goes 03Goes 04Goes 05Goes 06vGoes GGoes 07Goes 08Goes 09Goes 10ބGoes 11KGoes 12yProgram: GorizontMGorizont 01pGorizont 02Gorizont 03Gorizont 04UGorizont 05Gorizont 06dGorizont 07Gorizont 08Gorizont 09+Gorizont 10̂Gorizont 11nGorizont 12Gorizont 13~Gorizont 14!Gorizont 15Gorizont 16\Gorizont 17Gorizont 18TGorizont 19/9eGorizont 20QƒGorizont 21B>Gorizont 22W,Gorizont 23Gorizont 24|ۄLwGorizont 25fGorizont 26~Gorizont 278qGorizont #39:Gorizont 28-(TGorizont 29yhр-Gorizont 30ȅW\Gorizont 31zJvGorizont 329dProgram: GPS]GPS BI-01RGPS BI-02GPS BI-034GPS BI-04GPS BI-05GPS BI-06tGPS BI-07GPS BI-08ڀGPS BI-09GPS BI-10GGPS BI-11EGPS BII-01GPS BII-02GPS BII-03GPS BII-04GPS BII-05[GPS BII-06GGPS BII-07GPS BII-080GPS BII-09GPS BIIA-10kGPS BIIA-11ÂGPS BIIA-12IGPS BIIA-13GPS BIIA-14EGPS BIIA-15GPS BIIA-16pGPS BIIA-17ׁGPS BIIA-18=GPS BIIA-19GPS BIIA-20kGPS BIIA-21GPS BIIA-22;GPS BIIA-23GPS BIIA-24IGPS BIIA-25`GPS BIIA-26GPS BIIA-276GPS BIIA-28GPS BIIR-01\GPS BIIR-02Program: GracezProgram: GramsatGRO2Program: Gstar Gstar 1Gstar 2 *Gstar 3Gstar 4%DHarukaHealthsatProgram: HeaoHeao 1VHeao 2Heao 3Program: HliosʂHlios 1AHlios 1BProgram: HeosQvHeos 1Heos 2HESSITHETEHipparcosՅProgram: Hispasat+l7<*3nHispasat 1A+Hispasat 1BHispasat 1CLHSTProgram: ICOProgram: IDSCPIkonos 1.Ikonos 2)WImage.Program: IMEWSInjun 3sProgram: Inmarsat. 06Inmarsat 2F1iInmarsat 2F2Inmarsat 2F3QInmarsat 2F4Inmarsat 3F1Inmarsat 3F2)Inmarsat 3F3gInmarsat 3F4ǁInmarsat 3F5BpProgram: Insatf+^ Insat 1A̓Insat 1BInsat 1C$Insat 1D9ZInsat 2AƀInsat 2BInsat 2C'Insat 2DۂInsat 2E .\Insat 2RXInsat 3AIntasatUIntegral<jProgram: Intelsatdc>Ճ? K)byCF^cS![g(VjFtIntelsat 101Intelsat 201eIntelsat 202FIntelsat 203Intelsat 204Intelsat 301[Intelsat 302FIntelsat 303Intelsat 304Intelsat 305^Intelsat 306(Intelsat 307fIntelsat 308Intelsat 401Intelsat 402Intelsat 403OIntelsat 404FIntelsat 405Intelsat 406;Intelsat 407Intelsat 408uIntelsat 4A01GPS BIIA-12IIntelsat 4A02-Intelsat 4A030Intelsat 4A04Intelsat 4A05?Intelsat 4A06Intelsat 501Intelsat 502+NrIntelsat 503$GkIntelsat 504Intelsat 505Z}Intelsat 506_Intelsat 507Intelsat 508VIntelsat 509zIntelsat 510Intelsat 511UxIntelsat 512#GIntelsat 5138\Intelsat 514Intelsat 515<Intelsat 601(LIntelsat 602 1Intelsat 603RuIntelsat 604AeIntelsat 6058[3Intelsat KIntelsat 701$Intelsat 702'KIntelsat 703>Intelsat 704Intelsat 705ĀIntelsat 706iIntelsat 707dIntelsat 708;Intelsat 709?bIntelsat 801<Intelsat 802͂Intelsat 803eIntelsat 804)LpIntelsat 805<Intelsat 806+Intelsat KTV<jIntelsat 901 Intelsat 902BIntelsat 903Intelsat 904 Program: IntersputnikنLMI 1Intersputnik 8ӂIRASsIridium[*Iridium 042Iridium 05`Iridium 06Iridium 07Iridium 08PIridium 09:Iridium 10Iridium 11Iridium 12Iridium 13Iridium 14LIridium 15Iridium 16Iridium 17!Iridium 18hIridium 19Iridium 20aIridium 21Iridium 22Iridium 239Iridium 24Iridium 25^Iridium 26Iridium 273Iridium 281Iridium 29{Iridium 30Iridium 31Iridium 32Iridium 33[Iridium 34Iridium 35sIridium 36Iridium 37Iridium 38Iridium 39GIridium 40Iridium 41ՃIridium 42Iridium 43Iridium 44AIridium 451Iridium 46zIridium 47ÂIridium 48 Iridium 49Iridium 508Iridium 51Iridium 52rIridium 53Iridium 54GPS BIIA-12I Iridium 55Iridium 56HIridium 57Iridium 58Iridium 59Iridium 60Iridium 61FIridium 621Iridium 63zIridium 64Iridium 65 Iridium 66Iridium 67YIridium 68Iridium 69yIridium 70Iridium 71 Iridium 72Iridium 73FIridium 74Iridium 75҃Program: IRSFIRS 1A\IRS 1B<IRS 1E7IRS P2IRS 1CIRS P3IRS 1DIRS P4IRS P5=kIRS P6IRS 2AEIRTMProgram: ISEEISEE 1ISEE 2jProgram: IsisMrIsis 1ǁIsis 2ISOFProgram: Italsat*UItalsat 1rItalsat 2dItamsatkItosIUE׀Jason 1iProgram: JcsatEASC's C-band transponder frequency chartЁJcsat 1Jcsat 2>Jcsat 3$CJcsat 4Jcsat 5<Jcsat 6JERS 1Program: KH!.ހKKH 1-2KH 1-58KH 4-01UKH 4A-03KH 7-01KH 9-01KH 11-1BKH 11-2KH 11-3KH 11-6lKH 11-7KH 11-8KH 12-1+KH 12-2KH 12-3KH 12-4Program: Kitcomm ;Program: Kitsat 7Kitsat AKitsat BKompsat 1 Program: KoreasatB [}Koreasat 1jKoreasat 2Koreasat 3KyL Star 1^΀L Star 2jProgram: LacrosseLacrosse 1Lacrosse 2Lacrosse 3AProgram: Ladybug@nProgram: Lageos 7Lageos 1  Lageos 2 Program: Landsat     n Landsat 1 Landsat 2I Landsat 3̀ Landsat 4/ Landsat 5g Landsat 6 Landsat 7  Program: LCS; e LCS 1` LCS 4 LDEF݂ Program: LeasatW  ;  Leasat 1n Leasat 2 Leasat 3 Leasat 4u Leasat 5w Program: LEO One  Program: LES  LES 1L LES 2K LES 3n LES 4 LES 5LES 6LES 8^LES 9LewisLightsar?Program: LLMSIRISium 54GPS BIIA-12I Program: Loralsat0Loralsat 101rLoralsat 102LusatgProgram: M-StarЂM2AlProgram: MabuhayTMabuhay 1lProgram: MagionˁMagion 1Magion 2Magion 3Magion 4Magion 5Maqsat H Maqsat B܈Program: Marathon.Program: MarecsAyMMarecs ALMarecs B1Marecs B2Program: Marisat:Marisat 1 Marisat 2Marisat 3Program: Measat AMeasat 1Measat 2|Measat 3.Meteor (US)Program: Meteosat'Meteosat 1@Meteosat 2{Meteosat 3?Meteosat 4Meteosat 58Meteosat 6Meteosat 7Program: MSGProgram: MetopMicrolab 1Program: MidaswMidas 02Midas 03+Midas 04VMidas 05Midas 06iMidas 07Midas 08Midas 090Midas 10Program: MillenniumAProgram: Milstar Milstar 1-1Milstar 1-2<Milstar 2-1UProgram: Minisat1Minisat 01CMiranda@MikacProgram: MomooZ{Momo 1AMomo 1B=Program: Morelos+(XMorelos' C-band transponder frequency chartfMMorelos 1ρMorelos 2,Morelos 3"MSAT 1Program: Morning Star, Z Program: MSTI # MSTI 1$ MSTI 2 MSTI 3!MSX2!!.!MTSat!Ӄ!Musat"MyojoG"Mysat 1""Program: N Star"+"g"""Q"#N Star A#N Star B#Program: Nahuel##Nahuel 1A&$I$i$$Nahuel 1B$4$Program: NATOC$$$%%%Nato 1%Nato 2%Nato 3A%Nato 3BS%Nato 3C%Nato 3D&Nato 4A&Nato 4Bj&Netsat 28ւ&&Nilesat 101'H'a''Program: Nimbus߀'M'Nimbus 1'Nimbus 2(Nimbus 3A(Nimbus 3(Nimbus 40(Nimbus 5)Nimbus 6A)Nimbus 7)Nimiq)Program: NOAA*Y****NOAA 01 *NOAA 02?*NOAA 03@+NOAA 04A-12I u+NOAA 05+NOAA 06+NOAA Bn+NOAA 07$+NOAA 08,NOAA 09,NOAA 10,NOAA 11,NOAA 12-NOAA 13J-NOAA 14-NOAA 15-0-^-Program: NOSS..NOSS 01<.NOSS 02.NOSS 03X.NOSS 04l.NOSS 05 .NOSS 06.NOSS 07u/NOSS 08/NOSS 09/NOSS 12v/NOSS 13/NOSS 14/NOSS 150Program: Nova:0h0Nova 10Nova 2D0Nova 30Program: NPOESS/0_0Program: OAO00OAO 1W0OAO 2)1OAO B1OAO 31Oderacs1:1Oderacs 1A/1Oderacs 1Bu1Oderacs 1C1Oderacs 1D2Oderacs 1E2Oderacs 1F 2Oderacs 2A2Oderacs 2BJ2Oderacs 2Cu2Oderacs 2D2Oderacs 2E3Oderacs 2F3Program: Offekx33Offek 1@3Offek 2π3Offek 3G3Offek 44OFO(4Program: OGO4`4OGO 14OGO 2ڃ4OGO 35OGO 45OGO 5I5OGO 65Ohsumi'5Olympus6Program: Optus66q66v6707+777p77E7t78Optus A18Optus A2K8Optus A3݀8*88Optus B1V8Optus B29Optus B39Optus C1/D99Program: Orbcommǁ999Orbcomm X^9Orbcomm XP 1$:Orbcomm FM 1&:Orbcomm FM 2{:Orbcomm FM 3:Orbcomm FM 4:Orbcomm FM 5~:Orbcomm FM 6;Orbcomm FM 7;Orbcomm FM 8V;Orbcomm FM 9D;Orbcomm FM 10;Orbcomm FM 11;Orbcomm FM 12u;Program: Orblink<<Orbview 2<Orbview 3A<څ<Program: Orion=F=t====Orion 1>>Orion 2 ?9?X??Orion 3Y???Ӄ?? ?Orion 4?Ʉ?Orion 7@@Program: OscarV@?@Oscar 01@Oscar 02@Oscar 03WAOscar 04AOscar 05FAOscar 06=AOscar 07BOscar 08BPhase 3A2BOscar 10BOscar 13QCProgram: OSOCCOSO 1lCOSO 2COSO 3ICOSO 4mDOSO 5DOSO 6DOSO 7DOSO 8DProgram: OTS>D`DDEOTS 1EOTS 2EProgram: OVE}EOV 1-02EOV 1-04EOV 1-05EOV 1-08ăEOV 1-09FOV 1-10FOV 1-13FOV 1-14FOV 1-19 FOV 1-21FOV 2-1?FOV 2-3]GOV 2-5I JGOV 3-1=GOV 3-2VGOV 3-3iGOV 3-4[GOV 5-5cGOV 5-6GOV 5-9HQuick BirdHHQuickscatBHpHPacsathIPageosIPaksatIIProgram: PalapaIjI؀IׁIIImJJK.KKKPalapa A1KPalapa A2KPalapa B1KPalapa B2>KPalapa B2PLLPalapa B2RRLlLPalapa B4LLPalapa C1EL}LL΃LLPalapa C2MPalapa C3SMMPalapa D1GMuMProgram: Panamsat$MMPanamsat 1kNNNNNFNpNNPanamsat 2OODOrOP.PPP~PPanamsat 3P2PPanamsat 3RS.SWSSSShSSPanamsat 4,UZUUUU)UfUUUUPanamsat 5XXX X3XaXXXPanamsat 6>ZlZZZZ.ZPanamsat 6BZPanamsat 7[?[Panamsat 8c[[Panamsat 9[[Panamsat 10\\Pansat3\\Program: Parus~]]PASI 1r]]Program: Pegasusׂ]]Pegasus 1F^Pegasus 2^Pegasus 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0596Cosmos 05973Cosmos 0598XCosmos 0599Cosmos 0600Cosmos 0605Cosmos 0637\Cosmos 0641Cosmos 0642Cosmos 0643Cosmos 0644Cosmos 0645ҁCosmos 0646Cosmos 0647Cosmos 0648Cosmos 06774Cosmos 0678XCosmos 06799Cosmos 0680]Cosmos 0681Cosmos 0682Cosmos 0683Cosmos 0684Cosmos 0711Cosmos 0712Cosmos 0713Cosmos 0714*Cosmos 0715NCosmos 0716Cosmos 0717>Cosmos 0718`Cosmos 0732Cosmos 0733Cosmos 0734Cosmos 0735łCosmos 0736Cosmos 0737Cosmos 0738 Cosmos 0739.Cosmos 0775Cosmos 0777Cosmos 0782Cosmos 0936Cosmos 0954Cosmos 1000Cosmos 10940Cosmos 1267Cosmos 13665Cosmos 1402Cosmos 1443Cosmos 1540Cosmos 1546#Cosmos 1629SCosmos 1700ECosmos 1738Cosmos 1849Cosmos 1850`Cosmos 1851mCosmos 1852indCosmos 1853Cosmos 1854ˀCosmos 1855Cosmos 1856Cosmos 1857Cosmos 1858$Cosmos 1859HCosmos 1860Cosmos 1861Cosmos 1870RCosmos 1887Cosmos 1888Cosmos 1894āCosmos 1897Cosmos 1923Cosmos 1924&Cosmos 1925JCosmos 1926nCosmos 1927`Cosmos 1928Cosmos 1929Cosmos 1930̃Cosmos 1931Cosmos 1932>Cosmos 1933ICosmos 1934BCosmos 1935uCosmos 1957Cosmos 1958Cosmos 1959JCosmos 1960wCosmos 1961$Cosmos 1962\Cosmos 1963Cosmos 1964ЃCosmos 1965(Cosmos 1966OCosmos 1967Cosmos 1968Cosmos 1969Cosmos 1970ƂCosmos 1971̃Cosmos 1972Cosmos 1973#Cosmos 19746Cosmos 1975Cosmos 1976>Cosmos 1977YCosmos 1978Cosmos 1979Cosmos 1980Cosmos 1982Cosmos 1983@Cosmos 1984|Cosmos 1985Cosmos 1986Cosmos 1987ICosmos 1988Cosmos 1989Cosmos 1990Cosmos 1991Cosmos 1992Cosmos 1993(Cosmos 1994;Cosmos 1995NCosmos 1996_Cosmos 1997:Cosmos 1998MCosmos 1999`Cosmos 2000Cosmos 2001}Cosmos 2002Cosmos 2003Cosmos 20046Cosmos 2005qCosmos 2006Cosmos 2007Cosmos 2008Cosmos 20094Cosmos 2010XCosmos 20119Cosmos 2012]Cosmos 2013Cosmos 2014Cosmos 2015Cosmos 2016Cosmos 2017Cosmos 2018Cosmos 2019OCosmos 2020Cosmos 2021ƃCosmos 2022Cosmos 2023cCosmos 2024rCosmos 2025nCosmos 2026Cosmos 2027Cosmos 2028Cosmos 2029QCosmos 2030Cosmos 2031Cosmos 2032Cosmos 2033@Cosmos 2034PCosmos 2035Cosmos 2036Cosmos 2037Cosmos 2038Cosmos 2039Cosmos 2040Cosmos 2041Cosmos 2042,Cosmos 2043Cosmos 2044Cosmos 2045Cosmos 2047Cosmos 2048Cosmos 2049ICosmos 2050JCosmos 2051pCosmos 2052Cosmos 2054Cosmos 2055OCosmos 2056qCosmos 2057Cosmos 2058Cosmos 2059852indCosmos 2061Cosmos 2062Cosmos 20636Cosmos 2064UCosmos 2065tCosmos 2066\Cosmos 2067{Cosmos 2068Cosmos 2069Cosmos 2070ǀCosmos 2071Cosmos 20723Cosmos 2073@Cosmos 2074Cosmos 2079Cosmos 2080Cosmos 2081NCosmos 2085Cosmos 2100σCosmos 2107Cosmos 2108>Cosmos 2109Cosmos 2110Cosmos 2111lCosmos 2112Cosmos 2123Cosmos 2133͂Cosmos 2139Cosmos 2140Cosmos 2141gCosmos 2142Cosmos 2155lCosmos 2172Cosmos 2173Cosmos 2177Cosmos 2178OCosmos 2179Cosmos 2204Cosmos 2205]Cosmos 2206VCosmos 2209Cosmos 2218Cosmos 2219ƀCosmos 2220Cosmos 2221Cosmos 2222Cosmos 2223DCosmos 2224Cosmos 2230Cosmos 2231€Cosmos 2232%Cosmos 2233Cosmos 2234_Cosmos 2235Cosmos 2236Cosmos 2237Cosmos 2238Cosmos 2239^Cosmos 2240Cosmos 22413Cosmos 2242KCosmos 2243рCosmos 2244Cosmos 2245Cosmos 2246-Cosmos 2247Cosmos 2248Cosmos 2249(Cosmos 2250<Cosmos 22510Cosmos 2252PCosmos 2253pCosmos 2254Cosmos 2255"Cosmos 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Comsat CorporationDeutsche Telekom AGEarth Watch Inc.hEchostar Satellite Corp.BMobile Communications Holdings, Inc.jEmpresa Brasileira de Telecomunicaes S.A.%Eosat„European Meteorologic SatelliteنEUropean TELecommunication SATellite͉Final Analysis Inc.France TelecomGE American Communications, Inc.fGE Capital Satellites-EuropeGGlobalstar L.P.!Hughes Communications Inc.Hispasat S.A.International Launch ServicesDInformcosmosInmarsat LtdHIntelsatIntersputnikIridium LLCvISROJSATKaStar Satellite Communications Corp.GKorea Telecom>LEO One (firm)Loral SkynetLoral Space & Communications LtdSMabuhay Philippines Satellite Corp.MeasatNahuelsat S.A.JNASANOAANordiska SatellitaktiebolagetNippon Telegraph and Telephone CorporationaOdyssey TelecommunicationsOptus CommunicationsOrbcomm$Orbital Science Corporation Orion Network Systems Inc. Panamsat CorporationParacomsatwPhilippine Agila Satellite Inc6Philippine Long Distance Telephone CoPT Media Citra IndostarPT Pasifik Satelit NusantaraꀹPT SatelindoPT TelkomRadarSat InternationalނSpace Communications CorporationSocit Europenne de SatellitesMSingapore TelecomԄShinawatra Satellite Company LtdSpacecom Ltd.߆Surrey Satellite Technology LimitedՇTldiffusion De FranceZTelecomunicaciones de Mexico1TeledesicTelenor Satellite ServicesTelesat CanadaTelespazioTeracom%Thuraya Satellite Telecommunications CoTMI Communications]TCI Satellite Entertainment, Inc.Turk TelekomUnited States Satellite BroadcastingkWorldspace8American Mobile Satellite CorporationAntrix Corporation LimitedAsia Pacific Telecommunication Satellites Company LtdArabsatArianespaceAsia Satellite Telecommunications Company LtdAstrolink36vT8I]cq u+ JG k  灤|,xOInmarsat Ltd 2B806A7 Intelsat 2B80748 Intersputnik 2B807EC Iridium LLC 2B88000 ISRO 2B88076 JSAT 2B88115 )Japan Satellite Systems Inc. 2B88115 2KaStar Satellite Communications Corp. 2B882B7 Korea Telecom 2B88347 LEO One 2B8843E Loral Skynet 2B884F0 -Loral Space & Communications Ltd 2B88590 0Mabuhay Philippines Satellite Corp. 2B88653 MPSC 2B88653 Measat 2B88715 Binariang Sdn. 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