NASA - NSSDC - Master Catalog - Spacecraft Query · 2011-05-31 · Cronología de Lanzamientos Espaciales . Año 1991 . Recopilación de datos Ing. Eladio Miranda Batlle. Los textos,

Cronología de Lanzamientos Espaciales

Año 1991 Recopilación de datos Ing. Eladio Miranda Batlle. Los textos, imágenes y tablas fueron obtenidos de la National Space Science. Data Center. NASA

NASA - NSSDC - Spacecraft - Query Results

http://nssdc.gsfc.nasa.gov/nmc/spacecraftSearch.do[27/03/2011 0:35:58]

Sunday, 27 March 2011

Spacecraft Query Results

There were 141 spacecraft returned.

Spacecraft Name NSSDC ID Launch Date

Almaz 1 1991-024A 1991-03-31

Anik E1 1991-067A 1991-09-26

Anik E2 1991-026A 1991-04-04

APEX-MAIN 1991-086A 1991-12-18

ASC-2 1991-028A 1991-04-13

Astra 1B 1991-015A 1991-03-02

Aurora 2 1991-037A 1991-05-29

BS-3B 1991-060A 1991-08-25

Compton Gamma-Ray Observatory 1991-027B 1991-04-05

Cosmos 2107 1990-108A 1991-12-04

Cosmos 2109 1990-110A 1991-12-08

Cosmos 2121 1991-004A 1991-01-17

Cosmos 2122 1991-005A 1991-01-18

Cosmos 2123 1991-007A 1991-02-07

Cosmos 2124 1991-008A 1991-02-07

Cosmos 2125 1991-009A 1991-02-12

Cosmos 2126 1991-009B 1991-02-12

Cosmos 2127 1991-009C 1991-02-12

Cosmos 2128 1991-009D 1991-02-12

Cosmos 2129 1991-009E 1991-02-12

Cosmos 2130 1991-009F 1991-02-12

Cosmos 2131 1991-009G 1991-02-12

Cosmos 2132 1991-009H 1991-02-12

Cosmos 2133 1991-010A 1991-02-14

Cosmos 2134 1991-011A 1991-02-15

Cosmos 2135 1991-013A 1991-02-26

Cosmos 2136 1991-016A 1991-03-06

Cosmos 2137 1991-021A 1991-03-19

Cosmos 2138 1991-023A 1991-03-26

Cosmos 2139 1991-025A 1991-04-04

Cosmos 2140 1991-025B 1991-04-04

Cosmos 2141 1991-025C 1991-04-04

Cosmos 2142 1991-029A 1991-04-16

Cosmos 2143 1991-033A 1991-05-16

Cosmos 2144 1991-033B 1991-05-16

Cosmos 2145 1991-033C 1991-05-16

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Cosmos 2146 1991-033D 1991-05-16

Cosmos 2147 1991-033E 1991-05-16

Cosmos 2148 1991-033F 1991-05-16

Cosmos 2149 1991-036A 1991-05-24

Cosmos 2150 1991-041A 1991-06-11

Cosmos 2151 1991-042A 1991-06-13

Cosmos 2152 1991-048A 1991-07-10

Cosmos 2153 1991-049A 1991-07-10

Cosmos 2154 1991-059A 1991-08-22

Cosmos 2155 1991-064A 1991-09-13

Cosmos 2156 1991-066A 1991-09-19

Cosmos 2157 1991-068A 1991-09-28

Cosmos 2158 1991-068B 1991-09-28

Cosmos 2159 1991-068C 1991-09-28

Cosmos 2160 1991-068D 1991-09-28

Cosmos 2161 1991-068E 1991-09-28

Cosmos 2162 1991-068F 1991-09-28

Cosmos 2163 1991-071A 1991-10-09

Cosmos 2164 1991-072A 1991-10-10

Cosmos 2165 1991-077A 1991-11-12

Cosmos 2166 1991-077B 1991-11-12

Cosmos 2167 1991-077C 1991-11-12

Cosmos 2168 1991-077D 1991-11-12

Cosmos 2169 1991-077E 1991-11-12

Cosmos 2170 1991-077F 1991-11-12

Cosmos 2171 1991-078A 1991-11-20

Cosmos 2172 1991-079A 1991-11-22

Cosmos 2173 1991-081A 1991-11-27

Cosmos 2174 1991-085A 1991-12-17

DMSP 5D-2/F11 1991-082A 1991-11-28

ERS 1 1991-050A 1991-07-17

EUTELSAT-II F2 1991-003B 1991-01-15

EUTELSAT-II F3 1991-083A 1991-12-07

Foton 7 1991-070A 1991-10-04

GOES-X GOES-X 1991-06-01

Gorizont 23 1991-046A 1991-07-01

Gorizont 24 1991-074A 1991-10-23

IBSS 1991-031B 1991-04-28

Informator-1 1991-006A 1991-01-29

Inmarsat 2-F2 1991-018A 1991-03-08

Inmarsat 2-F3 1991-084B 1991-12-16

INTELSAT 6 F-1 1991-075A 1991-10-29

INTELSAT 6 F-5 1991-055A 1991-08-14

IRS-1B 1991-061A 1991-08-29

Italsat 1 1991-003A 1991-01-15

LOSAT-X 1991-047B 1991-07-04

Magion 3 1991-086E 1991-12-28

Meteor 3-4 1991-030A 1991-04-24

Meteor 3/TOMS 1991-056A 1991-08-15



Microsat 1 1991-051A 1991-07-17

Microsat 2 1991-051B 1991-07-17

Microsat 3 1991-051C 1991-07-17

Microsat 4 1991-051D 1991-07-17

Microsat 5 1991-051E 1991-07-17

Microsat 6 1991-051F 1991-07-17

Microsat 7 1991-051G 1991-07-17

Molniya 1-80 1991-012A 1991-02-15

Molniya 1-81 1991-043A 1991-06-18

Molniya 1-82 1991-053A 1991-08-01

Molniya 3-40 1991-022A 1991-03-22

Molniya 3-41 1991-065A 1991-09-17

MOP 2 1991-015B 1991-03-02

Nadezhda-3 1991-019A 1991-03-12

NATO 4A 1991-001A 1991-01-08

Navstar 2A-02 1991-047A 1991-07-04

NOAA 12 1991-032A 1991-05-14

NOSS 10 1991-076A 1991-11-08

Okean 3 1991-039A 1991-06-04

Orbcomm-X 1991-050C 1991-07-17

PRC 34 1991-088A 1991-12-28

Progress M- 6 1991-002A 1991-01-14

Progress M- 7 1991-020A 1991-03-19

Progress M- 8 1991-038A 1991-05-30

Progress M- 9 1991-057A 1991-08-20

Progress M-10 1991-073A 1991-10-17

Raduga 27 1991-014A 1991-02-28

Raduga 28 1991-087A 1991-12-19

Resurs-F10 1991-035A 1991-05-21

Resurs-F11 1991-044A 1991-06-28

Resurs-F12 1991-052A 1991-07-23

Resurs-F13 1991-058A 1991-08-21

REX 1991-045A 1991-06-29

SARA 1991-050E 1991-07-17

SLS 1 SLABLS1 1991-06-05

Solar Optical Telescope SOT-1 1991-03-01

Soyuz TM-12 1991-034A 1991-05-18

Soyuz TM-13 1991-069A 1991-10-02

STS 37 1991-027A 1991-04-05

STS 39 1991-031A 1991-04-28

STS 40/SLS 1 1991-040A 1991-06-05

STS 43/SSBUV03 1991-054A 1991-08-02

STS 44 1991-080A 1991-11-24

STS 48 1991-063A 1991-09-12

TDRS-E 1991-054B 1991-08-02

TELECOM 2A 1991-084A 1991-12-16

TUBSAT-1 1991-050D 1991-07-17

UARS 1991-063B 1991-09-12

UOSAT 5 1991-050B 1991-07-17



USA 69 1991-017A 1991-03-08

USA 70 1991-031C 1991-04-28

USA 74 1991-076C 1991-11-08

USA 75 1991-080B 1991-11-24

USA 76 1991-076D 1991-11-08

USA 77 1991-076E 1991-11-08

Yohkoh 1991-062A 1991-08-30

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NASA - NSSDC - Spacecraft - Details

http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1991-024A[02/04/2011 23:33:10]

Sunday, 03 April 2011

Description

The Almaz-1 was a satellite dedicated to providing radarimaging capabilities used in geophysical, agricultural,geological and environmental applications. The Almaz("diamond") spacecraft design was based on the MIR/Salyutmanned orbital station and a class of Heavy Cosmos militaryspacecraft (Cosmos 929). The Almaz-1 spacecraft had two100 m**2 solar panels and batteries to provide power. Thespacecraft used reaction wheels to maintain attitude and 3-axis stabilization. The interior was pressurized by nitrogen tosea level. The Almaz program had its origins in 1981, when thespaceraft was originally designed as a military reconnaissancecraft. Almaz-1 was designed and manufactured and operatedby NPO Machinostroenye. The sensor was a 3 GHz (10 cm) S-band Synthetic Aperature Radar (SAR) that used two 1.5 x 15m slotted waveguide antennas to obtain a resolution of 15meters per pixel. Data was temporarily stored on board usingvideo tape recorders, and subsequently down-linked to theground stations via the Luch GEO satellite. Almaz-1 alsocarried a radiometric scanner system (RMS) for infraredsounding of the Earth's surface. The Almaz-1 spacecraftreentered the Earth's atmosphere on October 17, 1992 after 18months in orbit out of an expected 30-month mission. Thespacecraft exectuted a controlled descent over the PacificOcean after the maneuvering fuel was unexpectedly exhaustedbecause of frequent orbit re-positioning due to increased solaractivity. Almaz-1 was preceded by Cosmos 1870 whichsuccesfully carried the Almaz SAR prototype.

Almaz 1

NSSDC ID: 1991-024A

Alternate Names

21213

Facts in Brief

Launch Date: 1991-03-31Launch Vehicle: ProtonLaunch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.RMass: 18550.0 kgNominalPower: 2400.0 W

Funding Agency

Russian Space Agency(U.S.S.R)

Discipline

Earth Science

AdditionalInformation

Launch/Orbitalinformation for Almaz 1

Experiments on Almaz 1

Data collections fromAlmaz 1

Questions or commentsabout this spacecraft canbe directed to: CoordinatedRequest and User SupportOffice.

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Name Role Original Affiliation E-mail


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http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=1991-024A


http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Almaz 1

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Almaz 1

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Almaz 1

mailto:[email protected]?Subject=NMC Comment/Question: Almaz 1 (1991-024A)













Mr. William Wirin GeneralContact

Almaz Corporation

Dr. AlexanderDunaev

GeneralContact

Russian SpaceAgency

Mr. William A.Kennedy

GeneralContact

Raytheon ITSS [email protected]

Selected References

Clark, P. S., From whence Almaz?, Space, Dec. 1992.


http://www.usa.gov/








Description

Anik-E1 was a Canadian communications satellite launchedfrom the Kourou Space Center in French Guiana by an Arianebooster rocket. It was placed in a geostationary orbit at 111.1deg W over the eastern part of the Pacific ocean.

Anik E1 was used primarily for business telecommunicationsservices, while Anik E2 was a broadcast communicationssatellite carrying the bulk of Canada's television signals.

Anik E1

NSSDC ID: 1991-067A

Alternate Names

21716

Facts in Brief

Launch Date: 1991-09-26Launch Vehicle: Ariane44PLaunch Site: Kourou,French GuianaMass: 2932.0 kg

Funding Agency

Telesat Canada Ltd.,Ottawa (Canada)

Discipline

Communications


Launch/Orbitalinformation for Anik E1

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Data collections from AnikE1



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http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Anik E1

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mailto:[email protected]?Subject=NMC Comment/Question: Anik E1 (1991-067A)











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Description

A fifth-generation Canadian telecommunications satellite, AnikE2 was launched via an Ariane 44P booster from Kourou,French Guiana. The satellite was the largest North Americandomestic commsat launched to date and required the extra liftof 4 Ariane solid propellant strap-on boosters. The Anik Eseries carried two dozen 12-W C-band transponders plus sixspares, and sixteen 50-W Ku-band transponders, with twospares. Coverage extended throughout Canada and a largeportion of the US. The satellite was manufactured by SparAerospace for TELESAT Canada. The bus was provided byGE Astro-Space. The main body measured 2.8 by 2.3 by 2.4m; solar arrays, generating 3888 W, spanned 21.5 m. Anik E2arrived on station at 107.3 deg. w as planned, but its orbitaldebut was dampened when the C-band antenna did notdeploy. With earth sensors covered by the stuck antenna,operations were impossible. For nearly three months, thesatellite was spun up, slowed down, heated and cooled inrepeated attempts to free the antenna. Telsat was prepared towrite the bird off. Relentless engineers tried a series of dualspin turn maneuvers, with the satellite spinning up the 4.5 rpm.On July 3, the C-band antenna swung free. Although therescue maneuvers used about a year's worth of fuel, Anik E2still had a 12-year life expectancy. After a two month testphase, Ku-band service was transferred to the new satellitefrom Anik C1, and C-band service from Anik D1 and D2.

Anik E2

NSSDC ID: 1991-026A

Alternate Names

21222

Facts in Brief

Launch Date: 1991-04-04Launch Vehicle: Ariane44PLaunch Site: Kourou,French GuianaMass: 2923.0 kgNominalPower: 3888.0 W

Funding Agency

Telesat Canada Ltd.,Ottawa (Canada)

Discipline

Communications


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Data collections from AnikE2



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Description

The lone dedicated Soviet science mission of the year lifted offfrom Plesetsk aboard a Tsyklon (SL-14) booster. Intercosmos25 was part of the APEX (Active Plasma Experiment) programto investigate the effects of streams of electrons and beams ofplasma on the ionosphere and magnetosphere. The spacecraftwas cylindrical, measuring 1.8 m long, 1.5 m in diameter. Eightsolar panels extended in petal-like fashion from one end. Itweighed about one metric ton at launch. A Czechoslovakiansubsatellite, Magion 3, was deployed from Intercosmos 25 onDecember 28.

APEX-MAIN

NSSDC ID: 1991-086A

Alternate Names

Intercosmos 25

21819

Facts in Brief

Launch Date: 1991-12-18LaunchVehicle: Tsiklon-3Launch Site: Plesetsk,U.S.S.RMass: 1000.0 kg

Funding Agency

Institut KosmicheskichIssledovaniy(Inst. ofCosmophysicalResearch) (U.S.S.R)

Discipline

Space Physics


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http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=APEX-MAIN

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=APEX-MAIN

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mailto:[email protected]?Subject=NMC Comment/Question: APEX-MAIN (1991-086A)














Prof. Victor N.Oraevsky

ProgramScientist

IZMIRAN [email protected]

Dr. G. A. Avanesov ProjectScientist

Soviet Academy ofSciences


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Description

A commercial communications satellite serving the US andPuerto Rico was launched aboard a Delta 2 rocket from CapeCanaveral. The commsat carried 18 C-band and 6 Ku-bandtransponders for TV news and interactive data transmissionsto private networks and small terminals. ASC 2 was thesecond of 2 satellites built by GE Astro-Space for Contel ASC.A subsequent merger between Contel and GTE Spacenetbrought the satellite into the GTE fold; its name was changedto Spacenet 4 after launch. Stationed above 101 deg. w, itjoined 3 Spacenet satellites, 4 GStars and ASC 1 to completethe merged GTE/Contel constellation. The existing fleet wascovering for 3 Ku-band transponders aboard Spacenet 4 thatfailed on orbit. Spacenet 4 was box-shaped, measuring 1 by1.3 by 1.6 m. Solar arrays spanned 14.1 m. It has a 10-yeardesign life.

ASC-2

NSSDC ID: 1991-028A

Alternate Names

Spacenet 4

21227

Facts in Brief

Launch Date: 1991-04-13LaunchVehicle: ShuttleLaunch Site: CapeCanaveral, United StatesMass: 1350.0 kg

Funding Agency

GTE/GTE Spacenet(United States)

Discipline

Communications


Launch/Orbitalinformation for ASC-2

Experiments on ASC-2

Data collections from ASC-2



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http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=ASC-2

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http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=ASC-2

mailto:[email protected]?Subject=NMC Comment/Question: ASC-2 (1991-028A)











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Description

ASTRA 1-B, a direct television satellite, was launched forLuxembourg by the European Space Agency on March 2,1991, using an Ariane booster rocket. It provided TVprogramming to some 90 percent of the metropolitan andurban areas of Western Europe and the Canary Islands. Itscommunications payload consisted of 16 active 60-watt Ku-band transponders and six spares. Signals could be receivedon small 60-cm dishes. Colocated with ASTRA 1-A above 19.2deg. e, ASTRA 1-B boosted system capability to 32 TVchannels and radio braodcasts. It was built by GE Astro-Spacefor Societe Europeenne des Satellites (SES), Luxembourg. Itwas box-shaped, measuring 2.9 by 2.3 by 2.2 m. Solar arrays,supplying 3,700 W at end of life, spanned 24.4 m. It had a 10-year design life.

Astra 1B

NSSDC ID: 1991-015A

Alternate Names

21139

Facts in Brief

Launch Date: 1991-03-02Launch Vehicle: Ariane44LPLaunch Site: Kourou,French GuianaMass: 1582.0 kgNominalPower: 3700.0 W

Funding Agency

Societe Europeenne desSatellites (Luxembourg)(Luxembourg)

Discipline

Communications


Launch/Orbitalinformation for Astra 1B

Experiments on Astra 1B

Data collections from Astra1B



Spacecraft

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http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Astra 1B

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http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Astra 1B

mailto:[email protected]?Subject=NMC Comment/Question: Astra 1B (1991-015A)











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Description

Aurora 2, an Alaskan-owned telecommunications satellite, waslaunched from Cape Canaveral aboard a Delta booster rocket.It provided telephone, television, maritime, radio andemergency communications service for the northern state'slong distance carrier, Alascom, as well as radio and dataservices for GE Americom. The satellite carried 32 C-bandtransponders (24 primary and 6 redundant) operating at 6/4GHz. Sixteen of the 24 channels served Alaskan customers, 8served US business. Built by GE Astro-Space for Alascom,Aurora 2 was box-shaped, measuring 1 by 1.64 by 1.4 m. Twothree-panel solar arrays, totalling 13 sq. m, extended fromeither side of the main body. The fixed dual-polarizationreflector antenna covered the continental US, Alaska andHawaii. It replaced Aurora 1, retired after 9 years of service.Stationed above 139 deg. w, Aurora 2 became operational inJuly. It has a 12-year life expectancy.

Aurora 2

NSSDC ID: 1991-037A

Alternate Names

21392

Facts in Brief

Launch Date: 1991-05-29Launch Vehicle: DeltaLaunch Site: CapeCanaveral, United StatesMass: 1336.0 kg

Funding Agency

GE AmericanCommunications, Inc.(United States)

Discipline

Communications


Launch/Orbitalinformation for Aurora 2

Experiments on Aurora 2

Data collections fromAurora 2



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Aurora 2

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Aurora 2

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Aurora 2

mailto:[email protected]?Subject=NMC Comment/Question: Aurora 2 (1991-037A)











http://www.usa.gov/








Description

BS-3B (Broadcasting Satellite-3B) was launched utilizing theH-I launch vehicle from the Tanegashima Space Center inJapan. It was equipped with three 120 W transpondersoperating at 12/14 GHz for direct-to-home TV broadcast. Twotransponders were used by the Japanese nationalbroadcasting network, Nippon Hoso Kyokai (NHK), the otherby privately owned Japan Satellite Broadcasting Co. BS-3Balso hosted a full redundant backup channel, and a 20-Wwideband transponder for experimental transmissions of highdefinition TV. Manufactured by Nippon Electric Co (NEC), thesatellite was based on GE's SATCOM 3000 bus. It measured1.3 by 1.6 by 1.6 m, with solar arrays spanning 15 m tip to tip.Once in space, the satellite's name was changed to Yuir 3B(Lily). Operational above 110 deg. e, it has a 7 to 9-year lifeexpectancy.

BS-3B

NSSDC ID: 1991-060A

Alternate Names

Yuri 3B

21668

Facts in Brief

Launch Date: 1991-08-25Launch Vehicle: H-ILaunchSite: Tanegashima, JapanMass: 550.0 kgNominalPower: 1093.0 W

Funding Agency

National SpaceDevelopment Agency(NASDA) (Japan)

Discipline

Communications


Launch/Orbitalinformation for BS-3B

Experiments on BS-3B

Data collections from BS-3B



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=BS-3B

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=BS-3B

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=BS-3B

mailto:[email protected]?Subject=NMC Comment/Question: BS-3B (1991-060A)











http://www.usa.gov/






http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1991-027B[02/04/2011 23:36:22]


Description

The Compton Gamma-Ray Observatory (GRO) is one ofNASA's four "Great Observatories". GRO's specific mission isto study the sources and astrophysical processes (e.g.,nuclear reactions, electron bremsstrahlung, matter-antimatterannihilation, elementary particle producation and decay,Compton scattering, and synchrotron radiation) that producethat highest energy electromagnetic radiation from the cosmos.GRO carries a complement of four instruments that providesimultaneous observations covering over five decades ofenergy from 0.1 MeV to 30 GeV: the Burst and TransientSource Experiment (BATSE), the Oriented ScintillationSpectrometer Experiment (OSSE), the Imaging ComptonTelescope (COMPEL), and the Energetic Gamma-RayExperiment Telescope (EGRET). The initial phase of thescience program consists of a near-uniform survey of thecomplete celestial sky followed by specific concentrations inlater phases; a 6 to 10-year mission lifetime is anticipated. TheGRO spacecraft is a 3-axis stabilized, free-flying spacecraftthat is capable of pointing at any celestial target for a period of14 days or more with an accuracy of 0.5 degree. Attitudedetermination accuracy is 2 arc minutes. If a significantcelestial event should occur at some other location, GRO iscapable of maneuvering to any orientation, by groundcommand, within 36 hours. Absolute timing is accurate to 0.1ms. The observatory has an onboard propulsion system, withapproximately 1860 kg of monopropellant hydrazine, for orbitmaintenance. Fuel is reserved for a controlled reentry, into adefined area of the Pacific Ocean at mission demise.

Compton Gamma-Ray Observatory

NSSDC ID: 1991-027B

Alternate Names

GRO

CGRO

21225

Facts in Brief

Launch Date: 1991-04-05LaunchVehicle: ShuttleLaunch Site: CapeCanaveral, United StatesMass: 16329.0 kgNominalPower: 2000.0 W

Funding Agency

NASA-Office of SpaceScience Applications(United States)

Discipline

Astronomy


Launch/Orbitalinformation for ComptonGamma-Ray Observatory

PDMP information forCompton Gamma-RayObservatory

Telecommunicationsinformation for ComptonGamma-Ray Observatory

Experiments on ComptonGamma-Ray Observatory

Data collections fromCompton Gamma-RayObservatory


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


Compton Gamma-RayObservatory


http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=1991-027B



http://nssdc.gsfc.nasa.gov/nmc/spacecraftPdmp.do?id=1991-027B



http://nssdc.gsfc.nasa.gov/nmc/spacecraftTelemetry.do?id=1991-027B



http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Compton Gamma-Ray Observatory

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Compton Gamma-Ray Observatory

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Compton Gamma-Ray Observatory











http://nssdc.gsfc.nasa.gov/image/spacecraft/cgro.jpg



Questions or commentsabout this spacecraft canbe directed to: Dr. CynthiaY. Cheung.

Personnel


Dr. Alan N.Bunner

ProgramScientist

NASA Headquarters

Mr. Robert E.Wilson

ProjectDirector

NASA Goddard Space FlightCenter

Dr. Neil Gehrels ProjectScientist


[email protected]

Dr. Guenter R.Reigler

ProgramManager

NASA Headquarters [email protected]

Selected References

Kniffen, D. A., Gamma-Ray Observatory overview, NASA-GSFC, Proceedings of the GammaRay Observatory Science Workshop, edited by W. N. Johnson, Greenbelt, MD, Apr. 1989.

Cameron, R. A., et al., Operation and performance of the OSSE instrument, In--The ComptonObservatory Science Workshop, NASA Conference Publication 3137, edited by C. R. Shrader,N. Gehrels and B. Dennis, p. 3, 1992.

Related Information/Data at NSSDC

STS 37 (CGRO Deployment mission)

US Active Archive for CGRO Information/Data

The CGRO Science Support Center at HEASARC


mailto:[email protected]?Subject=NMC Comment/Question: Compton Gamma-Ray Observatory (1991-027B)

mailto:[email protected]?Subject=NMC Comment/Question: Compton Gamma-Ray Observatory (1991-027B)

http://cossc.gsfc.nasa.gov/archive/index.html

http://www.usa.gov/








Description

Cosmos 2107 was a Soviet naval reconnaisance satellitelaunched from the Baikonur cosmodrome aboard a Tsyklon 2rocket. This naval forces monitoring spacecraft was used todetermine the position of enemy naval forces through detectionand triangulation of their electromagnetic emissions (radio,radar, etc).

Cosmos 2107

NSSDC ID: 1990-108A

Alternate Names

20985

Facts in Brief

Launch Date: 1991-12-04LaunchVehicle: Tsiklon-2Launch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.RMass: 3000.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline

Surveillance and OtherMilitary


Launch/Orbitalinformation for Cosmos2107

Experiments on Cosmos2107

Data collections fromCosmos 2107



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Cosmos 2107


http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Cosmos 2107


mailto:[email protected]?Subject=NMC Comment/Question: Cosmos 2107 (1990-108A)











http://www.usa.gov/








Description

Cosmos 2109 was a Soviet Global Navigation Satellite System(GLONASS) satellite launched from the Baikonur cosmodromeaboard a Proton rocket. Originally established in order tolocate the Soviet Union's civil aircraft and its merchant andfishing vessels, the signals were used by many American GPSsystem receivers as a complement/backup to the GPS systemitself. The operational system contained 21 satellites in 3orbital planes, with 3 on-orbit backups. Each satellite wasidentified by its slot number, which defined the orbital plane (1-8, 9-16, 17-24) and the location within the plane. The 3 orbitalplanes were separated 120 degrees, and the satellites withinthe same orbit plane by 45 degrees. The orbits were roughlycircular with an inclination of about 64.8 degrees, a semi-axisof 25,440 km, and a period of 11h 15m 44s.

The 3-axis stabilized spacecraft possessed a mass of about1,400 kg, a slight increase over the 1,250 original model. Thediameter and height of the satellite bus were approximately 2.4m and 3.7 m, respectively, with a solar array span of 7.2 m foran electrical power generation capability of 1.6 kW atbeginning of life. The aft payload structure housed 12 primaryantennas for L-band transmissions. Laser corner-cubereflectors were also carried to aid in precise orbit determinationand gedetic research.

Cosmos 2109

NSSDC ID: 1990-110A

Alternate Names

21006

Facts in Brief


Funding Agency

Scientific ProductionAssociation(Russia)(U.S.S.R)

Discipline

Navigation & GlobalPositioning







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


+ Privacy Policy and Important Notices NASA Official: Dr. Ed Grayzeck

























Description

Cosmos 2121 was a Soviet military cartographic photo-surveillance satellite launched from the Plesetsk Cosmodromeaboard a Soyuz-U rocket. It conducted an investigation of thenatural resources of the earth in the interests of variousbranches of the national economy of the USSR andinternational cooperation. Typical orbital profile: inclination 70degrees with altitude of 350-420 km. Designed duration: 15days. Transmission frequencies observed in West: 19.989FSK; 39.978 FSK; 232.0 PPM-AM.

Cosmos 2121

NSSDC ID: 1991-004A

Alternate Names

21059

Facts in Brief

Launch Date: 1991-01-17LaunchVehicle: Soyuz-ULaunch Site: Plesetsk,U.S.S.RMass: 6300.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

Cosmos 2122 was a Soviet naval reconnaisance satellitelaunched from the Baikonur cosmodrome aboard a Tsyklon 2rocket. This naval forces monitoring spacecraft was used todetermine the position of enemy naval forces through detectionand triangulation of their electromagnetic emissions (radio,radar, etc).

Cosmos 2122

NSSDC ID: 1991-005A

Alternate Names

21065

Facts in Brief

Launch Date: 1991-01-18LaunchVehicle: Tsiklon-2Launch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.RMass: 3000.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

Cosmos 2123 was a Soviet navigation satellite launched fromthe Plesetsk cosmodrome aboard a Kosmos 11 rocket. It waspositioned in plane 13 of the constellation. It was used fortesting of components and equipment of a space navigationsystem being set up to determine the position of civil aircraftand ships of the USSR merchant marine and fishing fleet atany point on the oceans and seas.

Development of this second generation Soviet navigationsatellite system represented a collaboration between the Navy,Academy of Sciences, and Ministry of Shipping. The basiswas the Parus / Tsiklon-B doppler navigation system, butallowing asynchronous operation of on-board equipment withonly essential equipment receiving a timer interrupt.Development began in 1974 with some preliminary workalready accomplished. The Tsikada system provided globalnavigation for both the Soviet Navy and commercial shipping.Prime contractor was KBPM/Reshetnev. PO Polyot, A SKlinyshkov provided synchronisation equipment. NIIRadiopribor under N Ye Ivanov provided cryptography andspacecraft navigation systems. Flight trials began in 1976under Admiral A I Rassokho. The system was accepted intomilitary service in 1979.

Cosmos 2123

NSSDC ID: 1991-007A

Alternate Names

21089

Facts in Brief

Launch Date: 1991-02-07LaunchVehicle: CosmosLaunch Site: Plesetsk,U.S.S.RMass: 810.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

Cosmos 2124 was a Soviet photo surveillance satellitelaunched from the Plesetsk cosmodrome aboard a Soyuzrocket. Two small film capsules were recovered in flight andthe main re-entry capsule with remaining film, camera, andcomputer systems at end of flight.

Cosmos 2124

NSSDC ID: 1991-008A

Alternate Names

21092

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

The lowest level of the three-tier communications satelliteconstellation was populated with two distinct systems devotedto military and government communications. Both systemswere assessed to be simple store-dump repeaters which wereparticularly useful in relaying traffic between the RussianFederation and overseas stations or forces. These Strela(which means "Arrow" in Russian) satellites recorded radiomessages transmitted by Russian intelligence agentsworldwide and relayed them when flying over Moscow.Debuting in 1970 was a system of small (61 kg, 0.80 m by0.75 m) relay satellites launched from Plesetsk by the Kosmosbooster in groups of eight. Although the mean altitude of thisconstellation was near 1500 km, each set of eight Strela 1satellites was normally dispersed into slightly elliptical orbitswith mean altitudes between 1430 and 1490 km. Theintentional orbital period differences of about 0.15 min ensuredthat the satellites would become randomly spaced about theorbital plane shortly after launch. Unlike the lower altitudeconstellation, this network relied on a single orbital plane withan inclination of 74 deg which was replenished on the averageof once each year. The last mission in this network was inJune 1992, and the network has now been superseded by themore modern and capable Strela 3 system.

Cosmos 2125

NSSDC ID: 1991-009A

Alternate Names

21100

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

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Maps

New/Updated Data






















http://www.usa.gov/








Description


Cosmos 2126

NSSDC ID: 1991-009B

Alternate Names

21101

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data











mailto:[email protected]?Subject=NMC Comment/Question: Cosmos 2126 (1991-009B)











http://www.usa.gov/






http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1991-009C[02/04/2011 23:41:16]


Description


Cosmos 2127

NSSDC ID: 1991-009C

Alternate Names

21102

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=1991-009C







mailto:[email protected]?Subject=NMC Comment/Question: Cosmos 2127 (1991-009C)











http://www.usa.gov/






http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1991-009D[02/04/2011 23:41:45]


Description


Cosmos 2128

NSSDC ID: 1991-009D

Alternate Names

21103

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=1991-009D







mailto:[email protected]?Subject=NMC Comment/Question: Cosmos 2128 (1991-009D)











http://www.usa.gov/






http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1991-009E[02/04/2011 23:42:06]


Description


Cosmos 2129

NSSDC ID: 1991-009E

Alternate Names

21104

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=1991-009E







mailto:[email protected]?Subject=NMC Comment/Question: Cosmos 2129 (1991-009E)











http://www.usa.gov/






http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1991-009F[02/04/2011 23:42:27]


Description


Cosmos 2130

NSSDC ID: 1991-009F

Alternate Names

21105

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=1991-009F







mailto:[email protected]?Subject=NMC Comment/Question: Cosmos 2130 (1991-009F)











http://www.usa.gov/






http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1991-009G[02/04/2011 23:42:49]


Description


Cosmos 2131

NSSDC ID: 1991-009G

Alternate Names

21106

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=1991-009G







mailto:[email protected]?Subject=NMC Comment/Question: Cosmos 2131 (1991-009G)











http://www.usa.gov/






http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1991-009H[02/04/2011 23:43:19]


Description


Cosmos 2132

NSSDC ID: 1991-009H

Alternate Names

21107

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=1991-009H







mailto:[email protected]?Subject=NMC Comment/Question: Cosmos 2132 (1991-009H)











http://www.usa.gov/








Description

Cosmos 2133 was part of a Soviet constellation of satellitescomprised of an echelon of the Missile Attack Warning System(SPRN), which was operated by the Air Defense Forces of theMinistry of Defense. According to Soviet officials, the earlywarning satellites could detect missile launches within 20seconds of lift-off.

Each satellite possessed a perigee of about 600 km, anapogee of nearly 40,000 km, and an inclination of 63 degrees.This orbit was superfically similar to that employed by theMolniya communications satellites but was distinguished byinitial argument of perigee 316-319 degrees, including to theMolniya 280-288 degree arguments of perigee. The seeminglyminor difference significantly affected the shape of thesatellite's groundtrack in the Northern Hemisphere.

Russian early warning spacecraft were more affected bygravitational perturbations due to their higher argument ofperigee and, therefore, performed periodic station-keepingmaneuvers to maintain an acceptable groundtrack. In addition,the argument of perigee migrated slightly over time (due toinclination variations), causing an alteration in the shape of thegroundtrack. Instead of expending additional propellant toprevent the argument of perigee shift, Russian spacecraftcontrollers altered the satellite's ascending node. This had theeffect of "stabilizing" the apogee point about which surveillanceoperations were performed.

Cosmos 2133

NSSDC ID: 1991-010A

Alternate Names

21111

Facts in Brief

Launch Date: 1991-02-14Launch Vehicle: ProtonLaunch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.RMass: 2150.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline

Earth Science







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

Cosmos 2134 was a variation of the Yantar-class spacecraftused to conduct high-precision topographic surveys. Thesespacecraft, now referred to as Kometa, typically remained inorbit for 44-45 days and were distinguished by their relativelycircular orbits between 210 and 280 km. These missions werealways launched from the Baikonur cosmodrome intoinclinations of 65 degrees or 70 degrees at the rate of one ortwo per year.

Cosmos 2134

NSSDC ID: 1991-011A

Alternate Names

21116

Facts in Brief

Launch Date: 1991-02-15Launch Vehicle: SoyuzLaunch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.RMass: 6600.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

Cosmos 2135 was part of a 6-satellite Russian militarynavigation system distributed in orbital planes spaced 30degrees apart, and launched from the Plesetsk cosmodromeaboard a Cosmos rocket. Navigation information was derivedfrom Doppler-shifted VHF transmissions (approximately 150and 400 MHz) of the satellite position and orbital data. Byacquiring fixes from several satellite, a user's location could becalculated with an accuracy of 100 m. The time needed toascertain a position was dependent upon the user's latitudeand the number of operational spacecraft in orbit. Normally,accurate location determination could be made within 1-2hours.

Cosmos 2135

NSSDC ID: 1991-013A

Alternate Names

21130

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

Cosmos 2136 was a Russian military cartographic photo-surveillance satellite launched from the Plesetsk Cosmodromeaboard a Soyuz-U rocket. It conducted an investigation of thenatural resources of the earth in the interests of variousbranches of the national economy of the USSR andinternational cooperation. Typical orbital profile: inclination 70degrees with altitude of 350-420 km. Designed duration: 15days. Transmission frequencies observed in West: 19.989FSK; 39.978 FSK; 232.0 PPM-AM.

Cosmos 2136

NSSDC ID: 1991-016A

Alternate Names

21143

Facts in Brief

Launch Date: 1991-03-06LaunchVehicle: Soyuz-ULaunch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.RMass: 6300.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

In 1969 KB Yuzhnoye introduced targets for exercise and testof PVO air defence and space tracking systems. The secondgeneration consisted of Taifun-1 and Taifun-2 satellites, whichdiffered in the type of equipment installed. In 1972 KB-3 underB E Khimrov, with the co-operation of assisting organisationsand the Ministry of Defence, completed the draft project. Thefirst Taifun-2 was completed in 1976. Flight trials wereconducted in the second half of the 1970's using Kosmos-3Mlaunch vehicles from Plesetsk and Kapustin Yar. The heads ofthe State Trials Commission were B N Karpov, N N Zhukov,and B G Zudin. Taifun-2 satellites were spherical in shape, 2m in diameter, with no external solar cells or antennae.

Cosmos 2137

NSSDC ID: 1991-021A

Alternate Names

21190

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

Cosmos 2138 was a Russian photo surveillance satellitelaunched from the Plesetsk cosmodrome aboard a Soyuzrocket. Two small film capsules were recovered in flight andthe main re-entry capsule with remaining film, camera, andcomputer systems at end of flight.

Cosmos 2138

NSSDC ID: 1991-023A

Alternate Names

21203

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

Cosmos 2139 was a Russian Global Navigation SatelliteSystem (GLONASS) satellite launched from the Baikonurcosmodrome aboard a Proton rocket. Originally established inorder to locate the Soviet Union's civil aircraft and its merchantand fishing vessels, the signals were used by many AmericanGPS system receivers as a complement/backup to the GPSsystem itself. The operational system contained 21 satellites in3 orbital planes, with 3 on-orbit backups. Each satellite wasidentified by its slot number, which defined the orbital plane (1-8, 9-16, 17-24) and the location within the plane. The 3 orbitalplanes were separated 120 degrees, and the satellites withinthe same orbit plane by 45 degrees. The orbits were roughlycircular with an inclination of about 64.8 degrees, a semi-axisof 25,440 km, and a period of 11h 15m 44s.


Cosmos 2139

NSSDC ID: 1991-025A

Alternate Names

21216

Facts in Brief


Funding Agency


Discipline








Spacecraft

Experiments

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Description



Cosmos 2140

NSSDC ID: 1991-025B

Alternate Names

21217

Facts in Brief


Funding Agency


Discipline








Spacecraft

Experiments

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Personnel

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New/Updated Data



























Description



Cosmos 2141

NSSDC ID: 1991-025C

Alternate Names

21218

Facts in Brief


Funding Agency


Discipline








Spacecraft

Experiments

Data Collections

Personnel

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Maps

New/Updated Data


























Curator: E. Bell, IIVersion 4.0.14, 08 October 2010

http://www.usa.gov/






Description


Cosmos 2142

NSSDC ID: 1991-029A

Alternate Names

21230

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/







Cosmos 2143

NSSDC ID: 1991-033A

Description

The Strela 3 system was a communications satellite constellation devoted to military and government communications.It was a simple store-dump repeater system which were particulatly useful in relaying non-essential traffic between theRussian Federation and overseas stations or forces. The Strela 3 system, which began in 1985, was launched by theTsyklon-3 booster from the Plesetsk cosmodrome into orbits near 1400 km at inclinations of 82.6 degrees with sixspacecraft stacked atop each launch vehicle. Two orbital planes were spaced 90 degrees apart, apparently eachcontained 10-12 operational spacecraft. Normally, two missions were conducted per year, suggesting an averagespacecraft life-time of approximately 24 months. The 220 kg spacecraft had a diameter of 1.0 m and a main bus heightof 1.5 m. A gravity-gradient beam was extended on-orbit to provide attitude stabilization.

Alternate Names21299

Facts in Brief

Launch Date: 1991-05-16Launch Vehicle: Tsiklon-3Launch Site: Plesetsk, U.S.S.RMass: 220.0 kg

Funding AgencyUnknown (U.S.S.R)

DisciplineCommunications

Additional InformationLaunch/Orbital information for Cosmos 2143

Experiments on Cosmos 2143

Data collections from Cosmos 2143

Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.


SpacecraftExperimentsData CollectionsPersonnelPublicationsMapsNew/Updated DataLunar/Planetary Events


















Description

The Strela 3 system was a communications satelliteconstellation devoted to military and governmentcommunications. It was a simple store-dump repeater systemwhich were particulatly useful in relaying non-essential trafficbetween the Russian Federation and overseas stations orforces. The Strela 3 system, which began in 1985, waslaunched by the Tsyklon-3 booster from the Plesetskcosmodrome into orbits near 1400 km at inclinations of 82.6degrees with six spacecraft stacked atop each launch vehicle.Two orbital planes were spaced 90 degrees apart, apparentlyeach contained 10-12 operational spacecraft. Normally, twomissions were conducted per year, suggesting an averagespacecraft life-time of approximately 24 months. The 220 kgspacecraft had a diameter of 1.0 m and a main bus height of1.5 m. A gravity-gradient beam was extended on-orbit toprovide attitude stabilization.

Cosmos 2144

NSSDC ID: 1991-033B

Alternate Names

21300

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Cosmos 2145

NSSDC ID: 1991-033C

Alternate Names

21301

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Cosmos 2146

NSSDC ID: 1991-033D

Alternate Names

21302

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Cosmos 2147

NSSDC ID: 1991-033E

Alternate Names

21303

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Cosmos 2148

NSSDC ID: 1991-033F

Alternate Names

21304

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

Cosmos 2149 was a Soviet photo surveillance satellitelaunched from the Plesetsk cosmodrome aboard a Soyuzrocket. Two small film capsules were recovered in flight andthe main re-entry capsule with remaining film, camera, andcomputer systems at end of flight.

Cosmos 2149

NSSDC ID: 1991-036A

Alternate Names

21315

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

The lowest level of the three-tier communications satelliteconstellation is now populated with two distinct systemsdevoted to military and government communications. Bothsystems are assessed to be simple store-dump repeaterswhich were particularly useful in relaying non-essential trafficbetween the Russian Federation and overseas stations offorces. The first Strela (which means "Arrow" in Russian)system debuted in 1970 and consisted of 750 - 1000 kgsatellites deployed at mean altitudes of 800 km in three orbitalplanes inclined 74 degrees to the equator and spaced 120degrees apart. These Strela 2 spacecraft were launchedseparately by the Kosmos launch vehicle from the Plesetskcosmodrome into each orbital plane at intervals of 24-36months. The activity of these satellites could be monitored viaa characteristic CW beacon emitted on a frequency of 153.660MHz.

Cosmos 2150

NSSDC ID: 1991-041A

Alternate Names

21418

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

Cosmos 2151 was a Russian ELINT (Electronic and SignalsIntelligence) satellite launched from the Plesetsk cosmodrome.

From 1965 to 1967 two dedicated ELINT systems were tested:the Tselina and the Navy's US. Both reached service, since theMinistry of Defence could not force a single system on themilitary services.

Tselina was developed by Yuzhnoye and consisted of twosatellites: Tselina-O for general observations and Tselina-D fordetailed observations. ELINT systems for Tselina were firsttested under the Cosmos designation in 1962 to 1965. The firstTselina-O was launched in 1970. The Tselina-D took a longtime to enter service due to delays in payload developmentand weight growth. The whole Tselina system was notoperational until 1976. Constant improvement resulted inTselina-O being abandoned in 1984 and all systems being puton Tselina-D.

Cosmos 2151

NSSDC ID: 1991-042A

Alternate Names

21422

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

Cosmos 2152 was a Russian military cartographic photo-surveillance satellite launched from the Plesetsk Cosmodromeaboard a Soyuz-U rocket. It conducted an investigation of thenatural resources of the earth in the interests of variousbranches of the national economy of the USSR andinternational cooperation. Typical orbital profile: inclination 70degrees with altitude of 350-420 km. Designed duration: 15days. Transmission frequencies observed in West: 19.989FSK; 39.978 FSK; 232.0 PPM-AM.

Cosmos 2152

NSSDC ID: 1991-048A

Alternate Names

21558

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

Cosmos 2153 was a Russian digital photo surveillance satellitelaunched from the Baikonur cosmodrome aboard a Soyuz-Urocket. It remained in orbit for 247 days.

Cosmos 2153

NSSDC ID: 1991-049A

Alternate Names

21560

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Cosmos 2154

NSSDC ID: 1991-059A

Alternate Names

21666

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

Cosmos 2155 was part of a Russian constellation of satellitescomprised of an echelon of the Missile Attack Warning System(SPRN), which was operated by the Air Defense Forces of theMinistry of Defense. According to Soviet officials, the earlywarning satellites could detect missile launches within 20seconds of lift-off.

Each satellite possessed a perigee of about 600 km, anapogee of nearly 40,000 km, and an inclination of 63 degrees.This orbit was superfically similar to that employed by theMolniya communications satellites but was distinguished byinitial argument of perigee 316-319 degrees, including to theMolniya 280-288 degree arguments of perigee. The seeminglyminor difference significantly affected the shape of thesatellite's groundtrack in the Northern Hemisphere.

Russian early warning spacecraft were more affected bygravitational perturbations due to their higher argument ofperigee and, therefore, performed periodic station-keepingmaneuvers to maintain an acceptable groundtrack. In addition,the argument of perigee migrated slightly over time (due toinclination variations), causing an alteration in the shape of thegroundtrack. Instead of expending additional propellant toprevent the argument of perigee shift, Russian spacecraftcontrollers altered the satellite's ascending node. This had theeffect of "stabilizing" the apogee point about which surveillanceoperations were performed.

Cosmos 2155

NSSDC ID: 1991-064A

Alternate Names

21702

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Cosmos 2156

NSSDC ID: 1991-066A

Alternate Names

21713

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Cosmos 2157

NSSDC ID: 1991-068A

Alternate Names

21728

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Cosmos 2158

NSSDC ID: 1991-068B

Alternate Names

21729

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Cosmos 2159

NSSDC ID: 1991-068C

Alternate Names

21730

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Cosmos 2160

NSSDC ID: 1991-068D

Alternate Names

21731

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Cosmos 2161

NSSDC ID: 1991-068E

Alternate Names

21732

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Cosmos 2162

NSSDC ID: 1991-068F

Alternate Names

21733

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

Cosmos 2163 was the third of the sixth generation photoreconnaisance satellites launched from the Baikonurcosmodrome using the Soyuz-U2 launch vehicle, which hadotherwise been restricted to supporting Soyuz-TM andProgress-M missions. The spacecraft was inserted into anorbital inclination of 64.8 degrees with mean operationalaltitudes normally between 240 and 260 km. The sixthgeneration spacecraft, believed to carry both film returncapsules and digital transmission capabilities, have only flownsix times; once each year during 1989-1993 and once in 1997.

Cosmos 2163

NSSDC ID: 1991-071A

Alternate Names

21741

Facts in Brief

Launch Date: 1991-10-09LaunchVehicle: Soyuz-U2Launch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.RMass: 6500.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

In 1969 KB Yuzhnoye introduced targets for exercise and testof PVO air defence and space tracking systems. The secondgeneration consisted of Taifun-1 and Taifun-2 satellites, whichdiffered in the type of equipment installed. In 1972 KB-3 underB E Khimrov, with the co-operation of assisting organisationsand the Ministry of Defence, completed the draft project. Thefirst Taifun-2 was completed in 1976. Flight trials wereconducted in the second half of the 1970's using Kosmos-3Mlaunch vehicles from Plesetsk and Kapustin Yar. The heads ofthe State Trials Commission were B N Karpov, N N Zhukov,and B G Zudin. Taifun-2 satellites were spherical in shape, 2m in diameter, with no external solar cells or antennae.

Cosmos 2164

NSSDC ID: 1991-072A

Alternate Names

21743

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Cosmos 2165

NSSDC ID: 1991-077A

Alternate Names

21779

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Cosmos 2166

NSSDC ID: 1991-077B

Alternate Names

21780

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Cosmos 2167

NSSDC ID: 1991-077C

Alternate Names

21781

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Cosmos 2168

NSSDC ID: 1991-077D

Alternate Names

21782

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Cosmos 2169

NSSDC ID: 1991-077E

Alternate Names

21783

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Cosmos 2170

NSSDC ID: 1991-077F

Alternate Names

21784

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Cosmos 2171

NSSDC ID: 1991-078A

Alternate Names

21787

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

Cosmos 2172 was a Russian military second generation globalcommand and control system (GKKRS) satellite launched fromthe Baiknour cosmodrome aboard a Proton K rocket. Thesesatellites were integrated with the Luch geostationary systemand featured retransmission of high rate data retransmission inthe centimetre wavelength range. While Luch handledcommunications between spacecraft and ground stations,Potok handled communications between fixed points anddigital data from the Yantar-4KS1 electroptical reconnaissancesatellite. Potok was the first communications spacecraft built bythe Lavochkin design bureau and used the Splav-2transponder by NPO Elas.

Potok is said by one account to have utilized the KAUR-4spacecraft bus. This had an active 3-axis orientation system,with a single central body from which extended 40 squaremetres of solar panels. Its basic structure was that of theKAUR-3, but it was equipped with completely new systems: adigital computer, plasma station-keeping engines, hydrazinemonopropellant orientation engines, and actively-scannedantennae arrays with 0.5 degrees antenna and 0.1 degreespacecraft pointing accuracy. Cosmos 2172 was stationed at13 deg W.

Cosmos 2172

NSSDC ID: 1991-079A

Alternate Names

21789

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Cosmos 2173

NSSDC ID: 1991-081A

Alternate Names

21796

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

Cosmos 2174 was a variation of the Yantar-class spacecraftthat conducted high-precision topographic surveys. ThisKometa spacecraft was distinguished by its relatively circularorbit between 210 and 280 km. It was launched from theBaikonur cosmodrome into an inclination of 60 - 70 degrees. Itwas believed to carry the TK-35010-m resolution stereocamera system, produced by the Belarus Optical CameraCompany, with an Earth's surface field-of-view of 180 km by270 km, and the KVR-1002-m resolution camera system withan image field-of view of 40 km by 40 km.

Cosmos 2174

NSSDC ID: 1991-085A

Alternate Names

21816

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

DMSP 5D-2/F11 is one of a series of meteorological satellitesdeveloped and operated by the Air Force under the DefenseMeteorological Satellite Program (DMSP). This program,previously known as DAPP (Data Acquisition and ProcessingProgram), was classified until March 1973. The objective ofthis program is to provide global visual and infrared cloudcoverdata and specialized environmental data to supportDepartment of Defense operational weather analysis andforecasting requirements. Operationally, the program consistsof two satellites in sun-synchronous polar orbits, with theascending node of one satellite in early morning and the otherat local noon. The 6.4-m-long spacecraft is separated into foursections: (1) a precision mounting platform for sensors andequipment requiring precise alignment; (2) an equipmentsupport module containing the electronics, reaction wheels,and some meteorological sensors; (3) a reaction controlequipment support structure containing the third-stage rocketmotor and supporting the ascent phase reaction controlequipment; and (4) a 9.29-sq-m solar cell panel. Thespacecraft stabilization is controlled by a combination flywheeland magnetic control coil system so that sensors aremaintained in the desired earth-looking mode. One feature isthe precision-pointing accuracy of the primary imager to 0.01deg provided by a star sensor and an updated ephemerisnavigation system. This allows automatic geographicalmapping of the digital imagery to the nearest picture element.The operational linescan system is the primary data acquisitionsystem that provides real-time or stored, multi-orbit, day-and-night, visual and infrared imagery of clouds. A supplementarysensor package contains five special sensors: (1) a microwavetemperature sounder, (2) an X-ray spectrometer, (3) anionospheric/scintillation monitor, (4) a precipitating electron/ionspectrometer, and (5) a microwave imager. Either recorded orreal-time data are transmitted to ground-receiving sites by tworedundant S-band transmitters. Recorded data are read out totracking sites located at Fairchild AFB, Washington, and atLoring AFB, Maine, and relayed by SATCOM to Air ForceGlobal Weather Central, Offutt AFB, Nebraska. Real-time dataare read out at mobile tactical sites located around the world.Additional information concerning this satellite can be found inthe report by D. A. Nichols, "The Defense MeteorologicalSatellite Program," Optical Engineering, v. 14, n. 4, p. 273,July-August 1975.

DMSP 5D-2/F11

NSSDC ID: 1991-082A

Alternate Names

DMSP-F11

USA 73

21798

Facts in Brief

Launch Date: 1991-11-28Launch Vehicle: AtlasELaunchSite: Vandenberg AFB,United StatesMass: 470.0 kg

Funding Agency

Department of Defense-Department of the AirForce (United States)

Disciplines

Astronomy

Earth Science

Space Physics


Launch/Orbitalinformation for DMSP 5D-2/F11

Experiments on DMSP 5D-2/F11

Data collections fromDMSP 5D-2/F11

Questions or commentsabout this spacecraft canbe directed to: Dr. Dieter K.Bilitza.


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=DMSP 5D-2/F11

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=DMSP 5D-2/F11

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=DMSP 5D-2/F11

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=DMSP 5D-2/F11

mailto:[email protected]?Subject=NMC Comment/Question: DMSP 5D-2/F11 (1991-082A)

mailto:[email protected]?Subject=NMC Comment/Question: DMSP 5D-2/F11 (1991-082A)











Personnel


Col J. Rivers Program Manager US Air Force Space Division

Other Sources of DMSP Data/Information

SSIES ion data (U. Texas - Dallas)DMSP data (National Geophysical Data Center)SSMI sea ice data (National Snow and Ice Data Center)DMSP F11 summary (NASA MSFC)


http://cindispace.utdallas.edu/DMSP/

http://dmsp.ngdc.noaa.gov/dmsp.html

http://nsidc.org/

http://microwave.msfc.nasa.gov:5721/source_documents/dmsp_f11.html

http://www.usa.gov/








Description

The first European Remote Sensing Satellite (ERS 1) was amajor element of the European Earth Observation Programcovering a number of disciplines including meteorology,climatology, oceanography, land resource inventory andmonitoring, geodesy and geodynamics. The objectives of ERS1 were primarily oriented towards ice and ocean monitoringwith all-weather high resolution active microwave imaging overland and coastal areas. The primary objectives were to meeteconomic and scientific needs to (1) develop and promoteapplications to further knowledge of ocean parameters, seastate and ice conditions and (2) increase the scientificunderstanding of coastal zones and ocean processes. TheERS 1 carried the following instruments: (1) Active MicrowaveInstrumentation (AMI), which combined a Synthetic ApertureRadar (SAR) and a wind scatterometer to acquire all-weatherimages over polar ice, coastal zones and land area and tomeasure wind field and wave spectra over oceans; (2) a RadarAltimeter (RA) to measure wave height, ocean surface windspeed and ice parameters; (3) the Along-Track ScanningRadiometer (ATSR), which consisted of two instruments:infrared radiometer (IRR) for measuring sea surface and cloudtop temperature and a microwave sounder (MWS) formeasuring total precipitable liquid and vapor water; (4) thePrecise Range and Range-rate Equipment (PRARE) toprovide accurate altitude measurements for geodeticapplications, sea surface topography, crustal dynamics andocean circulation; and (5) the Laser Retroreflector (LRR),which was a passive optical device used to assist satellitetracking. The ERS 1 spacecraft was based on the FrenchSPOT platform with a three axis stabilized earth pointedattitude control and a bias of 0.11 deg with an absolute errorrate of less than 0.0015 deg/s. The spacecraft consisted of thefollowing modules: Service Module (SM), Reaction ControlModule (RCM), Solar Array, PFM Thermal Control, PowerSupply Subsystem (PSS), Communications and Data HandlingSubsystem (CDHS), Attitude and Orbit Control Subsystem(AOCS), Flight Software, and Reaction and Self-mode ControlUnit. Power was supplied by two 5.8 x 2.4 m solar array panelsbacked up by four NiCd 24-Ah batteries. Attitude and orbitcontrol was maintained by horizon and Sun sensors andgyroscopes. Primary attitude control was provided by a set ofmomentum wheels and hydrazine thrusters. The ERS 1thermal control system was of a passive design complementedby an active heater system. The On-Board Computer (OBC)ran the flight software. All instrument computers were linked bythe On-Board Data-Handling (OBDH) system. All of theonboard processors were programmable during flight. Thespacecraft orbital orientation permitted a 3-day repeatcycle.The Payload Module consisted of the Payload

ERS 1

NSSDC ID: 1991-050A

Alternate Names

European Rem Sens Sat-1

21574

Facts in Brief

Launch Date: 1991-07-17Launch Vehicle: Ariane40Launch Site: Kourou,French GuianaMass: 2157.0 kgNominalPower: 2000.0 W

Funding Agency

European Space Agency(International)

Discipline

Earth Science


Launch/Orbitalinformation for ERS 1

PDMP information forERS 1

Telecommunicationsinformation for ERS 1

Experiments on ERS 1

Data collections from ERS1



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





http://nssdc.gsfc.nasa.gov/nmc/spacecraftPdmp.do?id=1991-050A


http://nssdc.gsfc.nasa.gov/nmc/spacecraftTelemetry.do?id=1991-050A


http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=ERS 1

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=ERS 1

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=ERS 1

mailto:[email protected]?Subject=NMC Comment/Question: ERS 1 (1991-050A)













Electronics Module (PEM) and the Antenna Support Structure(ASS). The PEM was a honeycomb structure that facilitatedthe integration of the ERS 1 instruments. The ASS assemblyprovided support for the SAR antenna. See "UK ERS-1Reference Manual",DC-MA-EOS-ED-0001,January 1991.

Personnel


Dr. Jan J.Burger

ProjectManager

ESA-European Space Research and TechnologyCentre


http://www.usa.gov/








Description

EUTELSAT-II F2 was launched for the European SpaceAgency from the Kourou Space Center in French Guiana bythe same Ariane rocket that launched ITALSAT 1. It was thesecond in a series of new-generation EuropeanTelecommunications Satellite Organization (EUTELSAT) andprovided TV, telephone, telex and data transmission servicesto the European Community. It carried sixteen 50-W Ku-bandtransponders; signals could be received on small 60 to 70-cmantennas. Built by a consortium led by Aerospatiale, thesatellite measured 1.3 by 1.3 by 2.7 m. Solar arrays spanned22.4 m when deployed and provided 3,000 W of power. It hadan eight-year design life. The Ariane-launched satellite wascolocated with EUTELSAT-I F5 above 10 deg. E. Traffic wastransferred from the elder satellite and commercial service viathe new craft commenced in March. EUTELSAT-I F5 was thenmoved to 21.5 E.

EUTELSAT-II F2

NSSDC ID: 1991-003B

Alternate Names

21056

Facts in Brief

Launch Date: 1991-01-15Launch Vehicle: Ariane44LLaunch Site: Kourou,French GuianaMass: 1877.0 kgNominalPower: 3000.0 W

Funding Agency

EuropeanTelecommunicationsSatellite Consortium(International)

Discipline

Communications


Launch/Orbitalinformation forEUTELSAT-II F2

Experiments onEUTELSAT-II F2

Data collections fromEUTELSAT-II F2



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=EUTELSAT-II F2


http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=EUTELSAT-II F2


mailto:[email protected]?Subject=NMC Comment/Question: EUTELSAT-II F2 (1991-003B)















Curator: E. Bell, IIVersion 4.0.14, 08 October 2010

http://www.usa.gov/






Description

EUTELSAT-II F3 was launched by the EuropeanTelecommunications Satellite Organization from the KourouSpace Center in French Guiana. It was one of 5 EUTELSAT IIcommunications satellites that were successfully put into orbit.The satellites were basically identical. With the arrival of the Wseries of satellites at the orbital positions until now used byEUTELSAT-II F1, F2, F3 and F4, these satellites weregradually relocated to new positions where they could continueto be used for a full rqange of telecommunications andtelevision services.

EUTELSAT-II F3

NSSDC ID: 1991-083A

Alternate Names

21803

Facts in Brief

Launch Date: 1991-12-07Launch Vehicle: Atlas 2Launch Site: CapeCanaveral, United StatesMass: 1874.0 kg

Funding Agency

EuropeanTelecommunicationsSatellite Consortium(International)

Discipline

Communications


Launch/Orbitalinformation forEUTELSAT-II F3

Experiments onEUTELSAT-II F3

Data collections fromEUTELSAT-II F3



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data











mailto:[email protected]?Subject=NMC Comment/Question: EUTELSAT-II F3 (1991-083A)











http://www.usa.gov/








Description

Beginning in 1985 the USSR/CIS conducted annual unmannedspace missions dedicated to materials science research. ThePhoton (Foton) spacecraft used for these flights was aderivative of the 1960's era Vostok/Voskhod mannedspacecraft and the Zenit military reconnaissance satellites andwere very similar to the operational Bion and Resurs-Fsatellites. Prototype Photon satellites were launched during1985-1987 as Cosmos 1645, Cosmos 1744, and Cosmos1841. Since 1988, the spacecraft have been officiallydesignated as Photon.

The 6,200-kg spacecraft was 6.2 m in length with a maximumdiameter of 2.5 m and was divided into three major sections:the service/retro module, the payload capsule, and anequipment block. The 2.3 m diameter recoverable capsulehandled a payload of up to 700 kg and a volume of 4.7 mcubed. Electrical power was supplied entirely by storagebatteries with 400 W average per day allocated to the payload(up to 700 W for 90 minutes each day). Mission durations forthe 8 Photon flights to the end of 1992 were 13-16 days.

To minimize perturbation forces, thereby maximizingmicrogravity conditions, Photon spacecraft were placed in amildly eccentric orbit at 62.8 degrees inclination and were notmaneuvered during the mission. Prior to 1991 the annualPhoton missions had always been launched in April or May.Launches were performed by the Soyuz booster from thePlesetsk cosmodrome, and recoveries made in Kazakhstan inthe primary manned recovery region northeast of the Baikonurcosmodrome.

The planned 16-day Photon 7 flight was scheduled toexperiment on obtaining protein crystals and semiconductormaterials under microgravity conditions. The spacecraft alsocarried scientific apparatus devised by German and Frenchspecialists.

Foton 7

NSSDC ID: 1991-070A

Alternate Names

Photon 7

21737

Facts in Brief

Launch Date: 1991-10-04Launch Vehicle: SoyuzLaunch Site: Plesetsk,U.S.S.RMass: 6200.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline

Microgravity


Launch/Orbitalinformation for Foton 7

Experiments on Foton 7

Data collections from Foton7



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Foton 7

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Foton 7

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Foton 7

mailto:[email protected]?Subject=NMC Comment/Question: Foton 7 (1991-070A)











http://www.usa.gov/






http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=GOES-X[03/04/2011 0:23:46]


Description

GOES-X is a collective name assigned by NSSDC to the nextseries of geostationary and operational environmentalsatellites (GOES-I, -J, -K, -L, -M). This three-axis bodystabilized spacecraft carries: (1) a visible infrared spin-scanradiometer (VISSR) atmospheric sounder (VAS) for collectingradiance, cloudcover, atmospheric temperature and watervapor data; (2) a space environment monitor (SEM) thatincludes a three-axis magnetometer, an X-ray Sensor (XRS),an Energy Particle Sensor (EPS), and a High Energy Protonand Alpha Detector (HEPAD); and (3) a Data CollectionSystem (DCS) to relay data between ground based platformsand the NOAA Command and Data Acquision (CDA) Station.Weather Facsimile (WEFAX) data are transmitted between theCDA and various small users at S-Band. A Search andRescue (SAR) system receives distress signals at UHF andretransmits the signals to SARSAT ground stations at L-Band.In addition to the telemetry link, GOES-X uses a Multiuse/DataLink (MDL), for transmission of diagnostic data for ImageNavigation and Registration. The system has been improvedover previous GOES systems in that the imager and sounderequipment of the VAS are separate and independentlyoperated. The imager allows simultaneous imaging from visibleand infrared channels, has increased sensitivity, and provideshigher resolution (4 km) data in the cloud detection and surfacechannels. The sounder is improved because of additionalspectral channels, higher resolution (8 km) and increasedsensitivity. The scan control of both parts is more flexible,providing small area coverage for frequent severe stormobservations. Image navigation utilizes Image MotionCompensation and Mirror Rotation Compensation so imagerycan be accurately registered with respect to a fixed grid thatcan remain unchanged for one to several days.

GOES-X

NSSDC ID: GOES-X

Alternate Names

GOES-I

GOES-J

GOES-K

GOES-L

GOES-M

Facts in Brief

Launch Date: 1991-06-01Launch Vehicle: AtlasLaunch Site: CapeCanaveral, United StatesMass: 980.0 kg

Funding Agency

NOAA NationalEnvironmental SatelliteService (United States)

Disciplines

Communications

Earth Science

Solar Physics

Space Physics


Launch/Orbitalinformation for GOES-X

Experiments on GOES-X

Data collections fromGOES-X

Questions or commentsabout this spacecraft canbe directed to: CoordinatedRequest and User Support


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data



http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=GOES-X

http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=GOES-X

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=GOES-X

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=GOES-X

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=GOES-X

mailto:[email protected]?Subject=NMC Comment/Question: GOES-X (GOES-X)











http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=GOES-X[03/04/2011 0:23:46]

Office.

Personnel


Mr. Robert H.Pickard

ProjectManager

NASA Goddard SpaceFlight Center

Mr. James R.Greaves

ProgramManager


Mr. William E.Shenk

ProjectScientist




http://www.usa.gov/







Thursday, 07 April 2011

Description

Gorizont 23 was a Soviet geosynchronous communicationssatellite. It was launched to provide telephone, telegraph andfax communications services, in addition to relaying TV andradio broadcasts. It was stationed at 103 deg E.

The Gorizont spacecraft possessed an initial mass in excess of2.1 metric tons and have demonstrated a lifetime of nearly 10years, although a 5-year service life was more common. The3-axis stabilized satellite was approximately 2 m in diameterand 5 m long with two large solar arrays capable of generating1.3 kW of electrical power for the first 3 years. Seven separatetransmission antennas allowed a variety of reception patternsfor both broad and localized terrestrial regions.

A typical Gorizont communications payload included sixgeneral purpose (TV, audio, facsimile) 6/4 GHz transponders(five 12.5 W and one 60 W), one Luch 14/11 GHz transponder(15 W), and one Volna 1.6/1.5 GHz transponder (20 W). TheVolna transponders were INMARSAT-compatible and wereextensively used by the Russian merchant marine fleet via theprimary GEO television rebroadcasting system, supporting allfive Federation time zones: Zone 1 from 140 deg E, Zone 2from 90 deg E, Zone 3 from 80 deg E, Zone 4 from 53 deg E,and Zone 5 from 14 deg W. These transmissions were handledby Orbita (12-m receiving antenna) and Moskva (2.5-mreceiving antenna) ground stations in the 6/4 GHz band. TheMoskva Globalnaya system was inaugurated in 1989 using 4-m receiving antennas and serviced by Gorizonts at 96.5 deg Eand 11 deg W.

Gorizont 23

NSSDC ID: 1991-046A

Alternate Names

21533

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications

Additional Information

Launch/Orbitalinformation for Gorizont23

Experiments on Gorizont23

Data collections fromGorizont 23



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Gorizont 23


http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Gorizont 23


mailto:[email protected]?Subject=NMC Comment/Question: Gorizont 23 (1991-046A)











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Description

Gorizont 24 was a Soviet geosynchronous communicationssatellite. It was launched to provide telephone, telegraph andfax communications services, in addition to relaying TV andradio broadcasts. It was stationed at 80 deg E.

The Gorizont spacecraft possessed an initial mass in excess of2.1 metric tons and have demonstrated a lifetime of nearly 10years, although a 5-year service life was more common. The3-axis stabilized satellite was approximately 2 m in diameterand 5 m long with two large solar arrays capable of generating1.3 kW of electrical power for the first 3 years. Seven separatetransmission antennas allowed a variety of reception patternsfor both broad and localized terrestrial regions.

A typical Gorizont communications payload included sixgeneral purpose (TV, audio, facsimile) 6/4 GHz transponders(five 12.5 W and one 60 W), one Luch 14/11 GHz transponder(15 W), and one Volna 1.6/1.5 GHz transponder (20 W). TheVolna transponders were INMARSAT-compatible and wereextensively used by the Russian merchant marine fleet via theprimary GEO television rebroadcasting system, supporting allfive Federation time zones: Zone 1 from 140 deg E, Zone 2from 90 deg E, Zone 3 from 80 deg E, Zone 4 from 53 deg E,and Zone 5 from 14 deg W. These transmissions were handledby Orbita (12-m receiving antenna) and Moskva (2.5-mreceiving antenna) ground stations in the 6/4 GHz band. TheMoskva Globalnaya system was inaugurated in 1989 using 4-m receiving antennas and serviced by Gorizonts at 96.5 deg Eand 11 deg W.

Gorizont 24

NSSDC ID: 1991-074A

Alternate Names

21759

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications


Launch/Orbitalinformation for Gorizont24

Experiments on Gorizont24

Data collections fromGorizont 24



Spacecraft

Experiments

Data Collections

Personnel

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Maps

New/Updated Data






















http://www.usa.gov/








Description

IBSS (Infrared Background Signature Survey) satellite wasdeployed from the orbiting STS-39 mission. This US Air Forceastronomy mission was retrieved by the shuttle on May 2,1991.

IBSS

NSSDC ID: 1991-031B

Alternate Names

Infrared BackgroundSignature Survey

21244

Facts in Brief

Launch Date: 1991-04-28Launch Vehicle: ShuttleLaunch Site: CapeCanaveral, United StatesMass: 1901.0 kg

Funding Agency


Disciplines

Astronomy



Launch/Orbitalinformation for IBSS

Experiments on IBSS

Data collections from IBSS



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=IBSS

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=IBSS

mailto:[email protected]?Subject=NMC Comment/Question: IBSS (1991-031B)











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Description

Informator was a prototype satellite for the Koskon (SpaceConversion) Global Space Communication Systems. It waslaunched from the Plesetsk cosmodrome by a Kosmos launchvehicle. The 600 kg satellite was inserted into an orbit of 960km by 1,010 km at an inclination of 83 degrees under thesponsorship of the Ministry of Geology. It was developed bythe Polet Production Association and the Elas ScientificProduction Association and was cylindrical in nature (1.8 m indiameter, 4 m in height) with two solar panels designed toproduce 1kW average power. Like Gonets, Informator 1 reliedon gravity gradient stabilization as was projected to have anoperational lifetime of 5 years or more. It also carried theSoviet RS14 and the German RUDAK 2 amateur satellitetransponders as piggy-back payloads. Exactly one week afterthe launch of these amsat transponders, two more, RS12 andRS13, were placed in a virtually identical orbit as secondarypayloads to the Kosmos 2123 navigation satellite.

Informator-1

NSSDC ID: 1991-006A

Alternate Names

Oscar 21

21087

Facts in Brief

Launch Date: 1991-01-29Launch Vehicle: CosmosLaunch Site: Plesetsk,U.S.S.RMass: 800.0 kg

Funding Agency

Unknown (U.S.S.R)

Disciplines

Communications

Earth Science


Launch/Orbitalinformation for Informator-1

Experiments on Informator-1

Data collections fromInformator-1



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Informator-1

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Informator-1

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Informator-1

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Informator-1

mailto:[email protected]?Subject=NMC Comment/Question: Informator-1 (1991-006A)











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Description

Inmarsat 2-F2 was a maritime satellite launched using a Deltalaunch vehicle from Cape Canaveral Air Force Base for theInternational Maritime Satellite Organization. It operated a totalof four INMARSAT-2 satellites. Launched between 1990-92,they each had a capacity equivalent to about 250 INMARSAT-A voice circuits.

The spacecraft was built by an international consortiumheaded by British Aerospace. Subcontractors included HughesAircraft Company, Fokker (The Netherlands), Matra (France),MBB (Germany), NEC (Japan), and Spar (Canada). Satelliteground control operations contractors included CLTC (China),CNES (France), SED (Canada), Telespazio (Italy) and Intelsat.

The INMARSAT-2s were three-axis-stabilized spacecraftbased on the Matra/B Ae Eurostar platform. With a ten-yeardesign life, each satellite has a 1,300 kg launch mass,reducing to an initial 800 kg in orbit. Initial power rating was1,200 W.

The communications payload comprised two transponderssupporting satellite- to-mobile (service) links in L-band(1.6GHz uplink, 1.5GHz downlink) and satellite-to-earth station(feeder) links in C-band (6.4GHz uplink, 3.6GHz downlink).Effective L-band isotropic radiated power (EIRP) was 39dBW.Each satellite's global beam covered roughly one-third of theearth's surface.

INMARSAT 2 F2 is now being used as a spare back-up toINMARSAT 3 F4 in the Atlantic Ocean Region.

Inmarsat 2-F2

NSSDC ID: 1991-018A

Alternate Names

INMARSAT 2

21149

Facts in Brief

Launch Date: 1991-03-08Launch Vehicle: DeltaLaunch Site: CapeCanaveral, United StatesMass: 800.0 kg

Funding Agency

Inmarsat (International)

Discipline

Communications


Launch/Orbitalinformation for Inmarsat2-F2

Experiments on Inmarsat2-F2

Data collections fromInmarsat 2-F2



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Inmarsat 2-F2


http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Inmarsat 2-F2


mailto:[email protected]?Subject=NMC Comment/Question: Inmarsat 2-F2 (1991-018A)











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Description

Inmarsat 2-F3 was a maritime satellite launched using anAriane launch vehicle from the Kourou Space Center for theInternational Maritime Satellite Organization. It operated a totalof four INMARSAT-2 satellites. Launched between 1990-92,they each had a capacity equivalent to about 250 INMARSAT-A voice circuits.

The spacecraft was built by an international consortiumheaded by British Aerospace. Subcontractors included HughesAircraft Company, Fokker (The Netherlands), Matra (France),MBB (Germany), NEC (Japan), and Spar (Canada). Satelliteground control operations contractors included CLTC (China),CNES (France), SED (Canada), Telespazio (Italy) and Intelsat.

The INMARSAT-2s were three-axis-stabilized spacecraftbased on the Matra/B Ae Eurostar platform. With a ten-yeardesign life, each satellite has a 1,300 kg launch mass,reducing to an initial 800 kg in orbit. Initial power rating was1,200 W.

The communications payload comprised two transponderssupporting satellite- to-mobile (service) links in L-band(1.6GHz uplink, 1.5GHz downlink) and satellite-to-earth station(feeder) links in C-band (6.4GHz uplink, 3.6GHz downlink).Effective L-band isotropic radiated power (EIRP) was 39dBW.Each satellite's global beam covered roughly one-third of theearth's surface.

INMARSAT 2 F3 is now being used as a spare back-up toINMARSAT 3 F1 in the Indian Ocean Region.

Inmarsat 2-F3

NSSDC ID: 1991-084B

Alternate Names

21814

Facts in Brief

Launch Date: 1991-12-16Launch Vehicle: Ariane44LLaunch Site: Kourou,French GuianaMass: 800.0 kg

Funding Agency

Inmarsat (International)

Discipline

Communications


Launch/Orbitalinformation for Inmarsat2-F3

Experiments on Inmarsat2-F3

Data collections fromInmarsat 2-F3



Spacecraft

Experiments

Data Collections

Personnel

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Maps

New/Updated Data











mailto:[email protected]?Subject=NMC Comment/Question: Inmarsat 2-F3 (1991-084B)











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Description

INTELSAT 6 F-1 was a telecommunications satellite launchedfrom the Kourou Space Center in French Guiana using theAriane booster rocket. The spacecraft was capable of handling120,000 telephone, 3 television broadcasts, and other servicessimultaneously. Its system of directional antennas allowed thesatellite to cover the entire American, European, and Africancontinents by means of a reconfiguration. Owned by the 121-member International Telecommunications SatelliteOrganization (INTELSAT), it carried 38 C-band and 10 K-bandtransponders. The massive commsat, built by Hughes Spaceand Communications Group, stood 11.7 m tall, 3.6 m indiameter. Body mounted solar cells generated 2,250 w at endof life.

INTELSAT 6 F-1

NSSDC ID: 1991-075A

Alternate Names

21765

Facts in Brief

Launch Date: 1991-10-29Launch Vehicle: Ariane44LLaunch Site: Kourou,French GuianaMass: 4259.2 kgNominal Power: 2250.0 W

Funding Agency

InternationalTelecommunicationsSatellite Corporation(International)

Discipline

Communications


Launch/Orbitalinformation for INTELSAT6 F-1

Experiments on INTELSAT6 F-1

Data collections fromINTELSAT 6 F-1



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=INTELSAT 6 F-1


http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=INTELSAT 6 F-1


mailto:[email protected]?Subject=NMC Comment/Question: INTELSAT 6 F-1 (1991-075A)











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Description

INTELSAT 6 F-5 was an international mammothcommunications satellite launched from the Kourou SpaceCenter in French Guiana using the Ariane booster rocket. Itwas placed at an altitude of 36,000 km above the equator, at14.5 deg W over the Atlantic ocean. Owned by the 121-member International Telecommunications SatelliteOrganization (INTELSAT), it carried 38 C-band and 10 K-bandtransponders providing telephone, TV and data services tolarge ground stations and small terminals. It could handle120,000 telephone calls and 3 color TV broadcastssimultaneously. Built by Hughes Space and CommunicationsGroup, the satellite stood 11.7 m tall, 3.6 m in diameter. Bodymounted solar cells generated 2,250 w at end of life. It had a10 year design life but is expected to achieve 14 years ofservice.

INTELSAT 6 F-5

NSSDC ID: 1991-055A

Alternate Names

21653

Facts in Brief


Funding Agency

InternationalTelecommunicationsSatellite Corporation(International)

Discipline

Communications


Launch/Orbitalinformation for INTELSAT6 F-5

Experiments on INTELSAT6 F-5

Data collections fromINTELSAT 6 F-5



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Experiments

Data Collections

Personnel

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Maps

New/Updated Data






















http://www.usa.gov/








Description

The Indian Remote Sensing Satellite-1B (IRS-1B) continuedthe series of Earth resources remote sensing satellitesdeveloped by India for land-based applications such asagriculture, forestry, geology, and hydrology. The spacecraftwas a box-shaped 1.6 x 1.56 x 1.1 meter bus with two Sun-tracking solar arrays of 8.5 square meters each. Two nickelcadmium batteries provided power during eclipses. The three-axis stabilized sun-synchronous satellite had a 0.4 degreepitch/roll and 0.5 degree yaw pointing accuracy provided by azero-momentum reaction wheel system utilizing Earth/Sun/starsensors and gyros. The satellite carried three Linear ImagingSelf-Scanning (LISS) push-broom CCD sensors operating infour spectral bands compatible with Landsat Thematic Mapperand Spor HRV data. The bands were 0.45 - 0.52, 0.52 - 0.59,0.62 - 0.68, and 0.77 - 0.86 microns. The LISS 1 sensor hadfour 2048-element CCD imagers with a focal length of 162.2cm generating a resolution of 72.5 meters and a 148 km swathwidth. The LISS 2A/B sensors had eight 2048-element CCDimagers with a focal length of 324.4 mm generating a groundresolution of 36.25 meters and a 74 km swath width. The twoLISS 2 imagers bracketed the LISS 1 imager providing a 3 kmoverlap. Data from the LISS 1 were downlinked on S-band at5.2 Mbps and from the LISS 2 A/B at 10.4 Mbps to the groundstation at Shandnager, India. The satellite was controlled fromBangalore, India.

IRS-1B

NSSDC ID: 1991-061A

Alternate Names

Indian Remote SensingSatellite 1B

21688

Facts in Brief

Launch Date: 1991-08-29Launch Vehicle: SLV-3Launch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.RMass: 975.0 kgNominal Power: 620.0 W

Funding Agency

Indian Space ResearchOrganization (India)

Discipline

Earth Science


Launch/Orbitalinformation for IRS-1B

Experiments on IRS-1B

Data collections from IRS-1B


Personnel


Dr. K. General Indian Space Research [email protected]


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=IRS-1B

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=IRS-1B

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=IRS-1B

mailto:[email protected]?Subject=NMC Comment/Question: IRS-1B (1991-061A)













Kasturirangan Contact Organization

Dr. P. N.Jayaraman

ProjectScientist

Indian Space ResearchOrganization


http://www.usa.gov/








Description

Italy's first national communications satellite, ITALSAT 1 wasdual launched aboard an Ariane 44L booster from Kourou,French Guiana. Placed in geosynchronous orbit above 13.2deg. e, the satellite served as a spaceborne telephoneswitchboard, redirecting up to 12,000 calls at once. ITALSATwas experimental in nature, a pre-operational component of aproposed digital satellite network for Italy. Built by SeleniaSpazio for Agenzia Spaziale Italiana (the Italian SpaceAgency), ITALSAT 1 was box-shaped, measuring 2.72 by 2.22by 3.48 m. It was 6.1 m tall with its two 2-m reflector antennasdeployed. Solar arrays spanned 21 m and provided 1,600 Wof power. Its communications package housed six 20/30 GHzmultibeam transponders, three 20/30 GHz global beamtransponders and a propagation experiment operating at 40/50GHz. The multibeam system, using advanced time divisionmultiple access (TDMA) techniques, was expected to undergotwo years of testing; the global beam system was consideredoperational from the start and was used to test new services.ITALSAT 1 had a 5-year design life, but the accuracy of itsorbital insertion saved maneuvering fuel, giving it a predicted 2-year life extension.

Italsat 1

NSSDC ID: 1991-003A

Alternate Names

21055

Facts in Brief


Funding Agency

Agenzia Spaziale Italiana(Italy)

Discipline

Communications


Launch/Orbitalinformation for Italsat 1

Experiments on Italsat 1

Data collections fromItalsat 1



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Italsat 1

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Italsat 1

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Italsat 1

mailto:[email protected]?Subject=NMC Comment/Question: Italsat 1 (1991-003A)











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Description

This spacecraft, for SDIO, was to gather multi-spectral data onground-launched rocket plumes and the space environment. Italso was used for development and testing of othertechnologies. The spacecraft was spring-ejected from a Delta2nd stage.

LOSAT-X

NSSDC ID: 1991-047B

Alternate Names

21553

Facts in Brief

Launch Date: 1991-07-04Launch Vehicle: Delta IILaunch Site: CapeCanaveral, United StatesMass: 73.0 kg

Funding Agency

Unknown (United States)

Disciplines

Engineering



Launch/Orbitalinformation for LOSAT-X

Experiments on LOSAT-X

Data collections fromLOSAT-X



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=LOSAT-X

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=LOSAT-X

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=LOSAT-X

mailto:[email protected]?Subject=NMC Comment/Question: LOSAT-X (1991-047B)











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Description

The Magion 3 spacecraft was manufactured as the subsatelliteof the APEX spacecraft. The APEX project had the followingprimary objectives: Simulation and initiation of aurora andradio frequency radiation in the auroral area; study of thedinamics of modulated beams and plasmoids in the near -earth plasma; study of the nature of electrodinamic relationshipof electromagnetic waves in magnetosphere and ionosphere;determination of radio emission characteristics of modulatedbeams of charged particles and plasmoids; search for non-linear wave structures of the electromagnetic soliton type indisturbed environment.

The Magion 3 scientific payload was almost the same as forMagion 2.

Magion 3

NSSDC ID: 1991-086E

Alternate Names

21835

Facts in Brief

Launch Date: 1991-12-28Launch Vehicle: Tsiklon-3Launch Site: Plesetsk,U.S.S.RMass: 52.0 kg

Funding Agency

Institut KosmicheskichIssledovaniy(Inst. ofCosmophysicalResearch) (U.S.S.R)

Discipline

Space Physics


Launch/Orbitalinformation for Magion 3

Experiments on Magion 3

Data collections fromMagion 3


Personnel


Dr. G. A. Avanesov Project Scientist Soviet Academy of Sciences


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Magion 3

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Magion 3

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Magion 3

mailto:[email protected]?Subject=NMC Comment/Question: Magion 3 (1991-086E)
















Description

The Meteor-3 series of meteorological satellites providedtwice-daily weather information including data on clouds, iceand snow cover, atmospheric radiation and humidity sounding.The Meteor-3 class of satellites orbited in a higher altitude thanthe Meteor-2 class of satellites and thus provided morecomplete coverage of the Earth's surface. The Meteor-3 hadthe same payload as the Meteor-2 but also included anadvanced scanning radiometer with better spectral and spatialresolution and a spectrometer for determining total ozonecontent. The spacecraft incorporated three-axis stabilization(0.5 deg accuracy) and twin 10-m span solar panels. The orbitwas adjusted by ion thrusters. Meteorological data wastransmitted to four primary sites in the former Soviet Union inconjunction with about 80 other smaller sites. Internationallycompatible Automatic Picture Transmission (APT) was madeavailable on 137 - 138 MHz channels to ground workstations.The Meteor-3 had two 0.5 - 0.7 micron radiometers. The firstprovided direct relay with a swath width of 2600 km and aresolution of 1 x 2 km. The second stored data on an on-boarddata recorder which provided global coverage with a swathwidth of 3100 km and a resolution of 0.7 x 1.4 km. The payloadalso included a scanning IR radiometer at 10.5 - 12.5 micronswith a swath width of 3100 km and a resolution of 3 x 3 km,and an 8-channel IR radiometer for atmospheric sounding at9.65 - 18.7 microns with a swath width of 2000 km and aresolution of 32 x 32 km. The Meteor-3 also included a 4channel UV ozone monitor (0.25 - 1.03 micron) at 2 km altituderesolution and a particle radiation detector (0.15 - 90 MeV).

Meteor 3-4

NSSDC ID: 1991-030A

Alternate Names

21232

Facts in Brief

Launch Date: 1991-04-24Launch Vehicle: TsiklonLaunch Site: Plesetsk,U.S.S.RMass: 2150.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline

Earth Science


Launch/Orbitalinformation for Meteor 3-4

Experiments on Meteor 3-4

Data collections fromMeteor 3-4



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Meteor 3-4

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Meteor 3-4

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Meteor 3-4

mailto:[email protected]?Subject=NMC Comment/Question: Meteor 3-4 (1991-030A)











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Description

The objective of this cooperative space mission between theUS and the former USSR was to map global ozone from spacewith the goal of studying global and regional changes in theozone. The Meteor-3, a series of meteorological observationspacecraft, had a three-axis stabilized system to provide anadir-pointing fixed-yaw attitude. The attitude system consistedof a combination of gyros and a horizon sensor similar to USsatellites. Attitude was controlled by momentum wheels. Solarenergy was collected by twin solar panels and electrical powerwas provided by solar-charged nickel-cadmium batteries. TheMeteor-3 normal instrumentation included twin TV camera formonitoring earth cloud cover and ice conditions, an infraredradiometer (IRR) for determining sea-surface temperature andobtaining cloud information, and a multichannel spectrometer(MCS) for providing thermal atmospheric sounding data. TheMeteor 3-5 spacecraft incorporated a Total Ozone MappingSpectrometer (TOMS), designed and operated by NASA, asthe first foreign sensor to fly on the Meteor series. The Meteor-3 had a continuous telemetry format, and a 24-hour storagecapacity on board for the TOMS operation. With a downlinkdata rate of 80 kbs, observational data were downlinked toreceiving stations in both the US and the Russia.

Meteor 3/TOMS

NSSDC ID: 1991-056A

Alternate Names

Meteor 3-5

21655

Facts in Brief

Launch Date: 1991-08-15Launch Vehicle: Tsiklon-3Launch Site: Plesetsk,U.S.S.RMass: 2150.0 kgNominal Power: 500.0 W

Funding Agencies

National Aeronautics andSpace Administration(United States)

SovietHydrometeorologicalService (U.S.S.R)

Discipline

Earth Science


Launch/Orbitalinformation for Meteor3/TOMS

PDMP information forMeteor 3/TOMS

Telecommunicationsinformation for Meteor3/TOMS

Experiments on Meteor3/TOMS

Data collections fromMeteor 3/TOMS

Questions or commentsabout this spacecraft can


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data











http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Meteor 3/TOMS

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Meteor 3/TOMS

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Meteor 3/TOMS

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Meteor 3/TOMS











be directed to: CoordinatedRequest and User SupportOffice.

Personnel


Mr. Charles E.Cote

ProjectDirector


[email protected]

Dr. RobertDouglas Hudson

ProjectScientist


Dr. George F.Esenwein, Jr.

ProgramManager

NASA Headquarters


mailto:[email protected]?Subject=NMC Comment/Question: Meteor 3/TOMS (1991-056A)



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Description

Microsat 1 was launched using a Pegasus booster rocket. Thepayload was delivered to orbit by vehicle released from a B-52.About an hour after take off from Edwards AFB, the 15-m long,1.2-m-diameter 19,026-kg Pegasus was dropped from theaircraft and its engines ignited. A stage separation malfunction,however, cast the 7-satellite payload into a lower thananticipated orbit. Ground controllers could not make contactwith the satellites and it appeared that they were lost. Some 9hours after launch, telemetry was acquired as the Microsatspassed over the main control station. Apparently, a new fourthstage guidance system compensated for the separation glitchand modified the trajectory. Subsequent passes verified that all7 satellite were operating. Built by Defense Systems Inc. forthe Defense Advanced Research Projects Agency (DARPA),the 12-sided Microsats measured 10 cm by 48 cm andweighed 22 kg each. They were designed to assess the use oflow-earth orbit for global communications. Each satelliteoperated in UHF, using an analog transponder for FM radiorelay of voice communications and a digital transponder torelay data, message, facsimile and modest video traffic.Although the 359 by 457-km orbit fell short of the planned 719km, the inclination was on target, allowing mission objectivesto be met.

Microsat 1

NSSDC ID: 1991-051A

Alternate Names

21580

Facts in Brief

Launch Date: 1991-07-17Launch Vehicle: PegasusLaunch Site: VandenbergAFB, United StatesMass: 22.0 kg

Funding Agency

Defense AdvancedResearch ProjectsAgency (United States)

Disciplines

Communications

Engineering


Launch/Orbitalinformation for Microsat 1

Experiments on Microsat 1

Data collections fromMicrosat 1



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Microsat 1

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Microsat 1


mailto:[email protected]?Subject=NMC Comment/Question: Microsat 1 (1991-051A)











http://www.usa.gov/








Description

Microsat 2 was launched using a Pegasus booster rocket. Thepayload was delivered into orbit by a vehicle released from aB-52 along with Microsats 1, and 3 through 7. They weredesigned to assess the use of low-earh orbit for globalcommunications. Each satellite operated in UHF, using ananalog transponder for FM radio, relay of voicecommunications and a digital transponder to relay data,message, facsimile and modest video traffic. For a fulldescription of the mission see Microsat 1 (1991-051A).

Microsat 2

NSSDC ID: 1991-051B

Alternate Names

21581

Facts in Brief


Funding Agency


Disciplines

Communications

Engineering







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data









mailto:[email protected]?Subject=NMC Comment/Question: Microsat 2 (1991-051B)











http://www.usa.gov/








Description

Microsat 3 was launched using a Pegasus booster rocket. Thepayload was delivered into orbit by a vehicle released from aB-52 along with Microsats 1, 2 and 4 through 7. They weredesigned to assess the use of low-earth orbit for globalcommunications. Each satellite operated in UHF, using ananalog transponder for FM radio relay of voicecommunications and a digital transponder to relay data,message, facsimile and modest video traffic. For a fulldescription of this satellite see Microsat 1 (1991-051A).

Microsat 3

NSSDC ID: 1991-051C

Alternate Names

21582

Facts in Brief


Funding Agency


Disciplines

Communications

Engineering







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data









mailto:[email protected]?Subject=NMC Comment/Question: Microsat 3 (1991-051C)











http://www.usa.gov/








Description

Microsat 4 was launched using a Pegasus booster rocket. Thepayload was delivered into orbit by a vehicle released from aB-52. It was launched along with Microsats 1-3 and 5-7. Theywere designed to assess the use of low-earth orbit for globalcommunications. Each satellite operated in UHF, using ananalog transponder for FM radio relay of voicecommunications and a digital transponder to relay data,message, facsimile and modest video traffic. For a fulldescription of this satellite see Microsat 1 (91-051A).

Microsat 4

NSSDC ID: 1991-051D

Alternate Names

21583

Facts in Brief


Funding Agency


Disciplines

Communications

Engineering







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data









mailto:[email protected]?Subject=NMC Comment/Question: Microsat 4 (1991-051D)











http://www.usa.gov/








Description

Microsat 5 was launched using a Pegasus booster rocket. Thepayload was delivered into orbit by a vehicle released from aB-52. It was launched along with Microsats 1-4 and 6-7. Theywere designed to assess the use of low-earth orbit for globalcommunications. Each satellite operated in UHF, using ananalog transponder for FM radio relay of voicecommunications and a digital transponder to relay data,message, facsimile and modest video traffic. For a fulldescription of this satellite see Microsat 1 (91-051A).

Microsat 5

NSSDC ID: 1991-051E

Alternate Names

21584

Facts in Brief


Funding Agency


Disciplines

Communications

Engineering







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data









mailto:[email protected]?Subject=NMC Comment/Question: Microsat 5 (1991-051E)











http://www.usa.gov/








Description

Microsat 6 was launched using a Pegasus booster rocket. Thepayload was delivered into orbit by a vehicle released from aB-52. It was launched along with Microsats 1-5 and 7. Theywere designed to assess the use of low-earth orbit for globalcommunications. Each satellite operated in UHF, using ananalog transponder for FM radio relay of voicecommunications and a digital transponder to relay data,message, facsimile and modest video traffic. For a fulldescription of this satellite see Microsat 1 (91-051A).

Microsat 6

NSSDC ID: 1991-051F

Alternate Names

21585

Facts in Brief


Funding Agency


Disciplines

Communications

Engineering







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data









mailto:[email protected]?Subject=NMC Comment/Question: Microsat 6 (1991-051F)











http://www.usa.gov/






http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1991-051G[06/04/2011 23:24:42]


Description

Microsat 7 was launched using a Pegasus booster rocket. Thepayload was delivered into orbit by a vehicle released from aB-52. It was launched along with Microsats 1-6. They weredesigned to assess the use of low-earth orbit for globalcommunications. Each satellite operated in UHF, using ananalog transponder for FM radio relay of voicecommunications and a digital transponder to relay data,message, facsimile and modest video traffic. For a fulldescription of this satellite see Microsat 1 (91-051A).

Microsat 7

NSSDC ID: 1991-051G

Alternate Names

21586

Facts in Brief


Funding Agency


Disciplines

Communications

Engineering







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data









mailto:[email protected]?Subject=NMC Comment/Question: Microsat 7 (1991-051G)











http://www.usa.gov/








Description

Molniya 1/80 was a first-generation Russian communicationssatellite (COMSAT) orbited to test and perfect a system ofradio communications and television broadcasting using earthsatellites as active transponders and to experiment with thesystem in practical use. The basic function of the satellite wasto relay television programs and long-distance two-waymultichannel telephone, phototelephone, and telegraph linksfrom Moscow to the various standard ground receiving stationsin the 'Orbita' system. The satellite was in the form of ahermetically sealed cylinder with conical ends -- one endcontained the orbital correcting engine and a system ofmicrojets, and the other end contained externally mountedsolar and earth sensors. Inside the cylinder were (1) a high-sensitivity receiver and three 800-MHz 40-w transmitters (oneoperational and two in reserve), (2) telemetering devices thatmonitored equipment operation, (3) chemical batteries thatwere constantly recharged by solar cells, and (4) an electroniccomputer that controlled all equipment on board. Mountedaround the central cylinder were six large solar battery panelsand two directional, high-gain parabolic aerials, 180 deg apart.One of the aerials was directed continually toward the earth bythe highly sensitive earth sensors. The second aerial was heldin reserve. Signals were transmitted in a fairly narrow beamensuring a strong reception at the earth's surface. The satellitereceived telemetry at 1000 MHz. Television service wasprovided in a frequency range of 3.4 to 4.1 GHz at 40 w.Molniya 1/80, whose cylindrical body was 3.4 m long and 1.6 min diameter, was much heavier than corresponding U.S.COMSATs, and it had about 10 times the power output of theEarly Bird COMSAT. In addition, it did not employ ageosynchronous equatorial orbit as have most U.S. COMSATsbecause such an orbit would not provide coverage for areasnorth of 70 deg n latitude. Instead, the satellite was boostedfrom a low-altitude parking orbit into a highly elliptical orbit withtwo high apogees daily over the northern hemisphere -- oneover Russia and one over North America -- and relatively lowperigees over the southern hemisphere. During its apogee,Molniya 1/80 remained relatively stationary with respect to theearth below for nearly 8 of every 12 hr. By placing three ofmore Molniya 1 satellites in this type of orbit, spacing themsuitably, and shifting their orbital planes relative to each otherby 120 deg, a 24-hr/day communication system could beobtained.

Molniya 1-80

NSSDC ID: 1991-012A

Alternate Names

21118

Facts in Brief

Launch Date: 1991-02-15Launch Vehicle: MolniyaLaunch Site: Plesetsk,U.S.S.RMass: 1600.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline

Communications


Launch/Orbitalinformation for Molniya 1-80

Experiments on Molniya 1-80

Data collections fromMolniya 1-80



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Molniya 1-80


http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Molniya 1-80


mailto:[email protected]?Subject=NMC Comment/Question: Molniya 1-80 (1991-012A)











http://www.usa.gov/








Description

Molniya 1/81 was a first-generation Russian communicationssatellite (COMSAT) orbited to test and perfect a system ofradio communications and television broadcasting using earthsatellites as active transponders and to experiment with thesystem in practical use. The basic function of the satellite wasto relay television programs and long-distance two-waymultichannel telephone, phototelephone, and telegraph linksfrom Moscow to the various standard ground receiving stationsin the 'Orbita' system. The satellite was in the form of ahermetically sealed cylinder with conical ends -- one endcontained the orbital correcting engine and a system ofmicrojets, and the other end contained externally mountedsolar and earth sensors. Inside the cylinder were (1) a high-sensitivity receiver and three 800-MHz 40-w transmitters (oneoperational and two in reserve), (2) telemetering devices thatmonitored equipment operation, (3) chemical batteries thatwere constantly recharged by solar cells, and (4) an electroniccomputer that contorlled all equipment on board. Mountedaround the central cylinder were six large solar battery panelsand two directional, high-gain parabolic aerials, 180 deg apart.One of the aerials was directed continually toward the earth bythe highly sensitive earth sensors. The second aerial was heldin reserve. Signals were transmitted in a fairly narrow beamensuring a strong reception at the earth's surface. The satellitereceived telemetry at 1000 MHz. Television service wasprovided in a frequency range of 3.4 to 4.1 GHz at 40 w.Molniya 1/81, whose cylindrical body was 3.4 m long and 1.6 min diameter, was much heavier than corresponding U.S.COMSATS, and it had about 10 times the power output of theEarly Bird COMSAT. In addition, it did not employ ageosynchronous equatorial orbit as have most U.S. COMSATsbecause such an orbit would not provide coverage for areasnorth of 70 deg n latitude. Instead, the satellite was boostedfrom a low-altitude parking orbit into a highly elliptical orbit withtwo high apogees daily over the northern hemisphere -- oneover Russia and one over North America -- and relatively lowperigees over the southern hemisphere. During its apogee,Molniya 1/81 remained relatively staionary with respect to theearth below for nearly 8 of every 12 hr. By placing three ormore Molniya 1 satellites in this type of orbit, spacing themsuitably, and shifting their orbital planes relative to each otherby 120 deg, a 24-hr/day communication system could beobtained.

Molniya 1-81

NSSDC ID: 1991-043A

Alternate Names

21426

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

Molniya 1/82 was a first-generation Russian communicationssatellite (COMSAT) orbited to test and perfect a system ofradio communications and television broadcasting using earthsatellites as active transponders and to experiment with thesystem in practical use. The basic function of the satellite wasto relay television programs and long-distance two-waymultichannel telephone, phototelephone, and telegraph linksfrom Moscow to the various standard ground receiving stationsin the 'Orbita' system. The satellite was in the form of ahermetically sealed cylinder with conical ends -- one endcontained the orbital correcting engine and a system ofmicrojets, and the other end contained externally mountedsolar and earth sensors. Inside the cylinder were (1) a high-sensitivity receiver and three 800-MHz 40-w transmitters (oneoperational and two in reserve), (2) telemetering devices thatmonitored equipment operation, (3) chemical batteries thatwere constantly recharged by solar cells, and (4) an electroniccomputer that controlled all equipment on board. Mountedaround the central cylinder were six large solar battery panelsand two directional, high-gain parabolic aerials, 180 deg apart.One of the aerials was directed continually toward the earth bythe highly sensitive earth sensors. The second aerial was heldin reserve. Signals were transmitted in a fairly narrow beamensuring a strong reception at the earth's surface. The satellitereceived telemetry at 1000 MHz. Television service wasprovided in a frequency range of 3.4 to 4.1 GHz at 40 w.Molniya 1/82, whose cylindrical body was 3.4 m long and 1.6 min diameter, was much heavier than corresponding U.S.COMSATs, and it had about 10 times the power output of theEarly Bird COMSAT. In addition, it did not employ ageosynchronous equatorial orbit as have most U.S. COMSATsbecause such an orbit would not provide coverage for areasnorth of 70 deg n latitude. Instead, the satellite was boostedfrom a low-altitude parking orbit into a highly elliptical orbit withtwo high apogees daily over the northern hemisphere -- oneover Russia and one over North America -- and relatively lowperigees over the southern hemisphere. During its apogee,Molniya 1/82 remained relatively stationary with respect to theearth below for nearly 8 of every 12 hr. By placing three ormore Molniya 1 satellites in this type of orbit, spacing themsuitably, and shifting their orbital planes relative to each otherby 120 deg, a 24-hr/day communication system could beobtained.

Molniya 1-82

NSSDC ID: 1991-053A

Alternate Names

21630

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

The Molniya-3 Soviet communications satellites were used tocreate the 'Orbita' communications system for northernregions, with groups of four satellites. The first Molniya 3spacecraft appeared in 1974, primarily to support civilcommunications (domestic and international), with a slightlyenhanced electrical power system and a communicationspayload of three 6/4 GHz transponders with power outputs of40 W or 80 W. The land segment used a 12 m diameterparabolic antenna, which was pointed automatically at thesatellite using autonomous electromechanical equipment. Laterversions were to be part of the YeSSS Unified SatelliteCommunications System. Trials of this version began in the1980's, with the system being accepted by the Russian militaryin 1983-1985.

Molniya 3-40

NSSDC ID: 1991-022A

Alternate Names

21196

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

The Molniya-3 Russian communications satellites were used tocreate the 'Orbita' communications system for northernregions, with groups of four satellites. The first Molniya 3spacecraft appeared in 1974, primarily to support civilcommunications (domestic and international), with a slightlyenhanced electrical power system and a communicationspayload of three 6/4 GHz transponders with power outputs of40 W or 80 W. The land segment used a 12 m diameterparabolic antenna, which was pointed automatically at thesatellite using autonomous electromechanical equipment. Laterversions were to be part of the YeSSS Unified SatelliteCommunications System. Trials of this version began in the1980's, with the system being accepted by the Russian militaryin 1983-1985.

Molniya 3-41

NSSDC ID: 1991-065A

Alternate Names

21706

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

The Meteosat Operational Programme (MOP-2) satellite wasthe second operational geostationary Meteosat satellitefollowing 3 pre-operational Meteosat satellites (Meteosat-1,-2,-3/P2). The primary goals of the MOP satellites were (1) toprovide visible and IR day/night cloudcover data and radiancesand (2) to disseminate image data to users through the DataCollection Platform (DCP). MOP-2 (or Meteosat 5) was a 2.1 mdiameter, 3.195 m high stepped cylindrical body with solarcells on six main body panels. The spacecraft was spin-stabilized at 100 rpm around the main axis aligned almostparallel to the Earth's axis with spin regulated by two smallhydrazine thrusters. Spin access control and east-weststationkeeping were provided by two pairs of large thrusters.Attitude information was provided by Earth horizon and Sun-litsensors. A radiating dipole antenna directed S-band (333 kbs)transmission of DCP image data to the Data Acquisition,Telemetry, and Tracking Station at Odenwald, Germany forrelay to the Meteosat Ground Computer System and MeteosatOperations Control center at ESA's European SpaceOperations Center (ESOC). The MOP-2 carried a singleimaging radiometer in visible/infrared wavelengths in additionto the Data Collection Platform.

MOP 2

NSSDC ID: 1991-015B

Alternate Names

Meteosat 5

21140

Facts in Brief

Launch Date: 1991-03-02Launch Vehicle: Ariane44LPLaunch Site: Kourou,French GuianaMass: 316.0 kg

Funding Agency

European MeteorologicalSatellite Agency(International)

Discipline

Earth Science


Launch/Orbitalinformation for MOP 2

Experiments on MOP 2

Data collections from MOP2


Personnel


Mr. J. Project ESA-European Space Research and Technology


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=MOP 2

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=MOP 2

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=MOP 2

mailto:[email protected]?Subject=NMC Comment/Question: MOP 2 (1991-015B)













Aasted Manager Centre


http://www.usa.gov/








Description

Nadezhda-3 was a Soviet navigation satellite launched using aCosmos booster rocket. This civilian satellite carried anCOSPAS search and rescue package. It was used to locatevessels in the Soviet merchant marine and fishing fleet.

Nadezhda-3

NSSDC ID: 1991-019A

Alternate Names

21152

Facts in Brief

Launch Date: 1991-03-12Launch Vehicle: CosmosLaunch Site: Plesetsk,U.S.S.RMass: 825.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline



Launch/Orbitalinformation for Nadezhda-3

Experiments on Nadezhda-3

Data collections fromNadezhda-3



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Nadezhda-3

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Nadezhda-3

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Nadezhda-3

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Nadezhda-3

mailto:[email protected]?Subject=NMC Comment/Question: Nadezhda-3 (1991-019A)











http://www.usa.gov/








Description

A communnications satellite serving the North Atlantic TreatyOrganization (NATO) and British Ministry of Defense waslaunched from Cape Canaveral by a Delta 2 rocket. NATO 4Awas the first of two new-generation commsats offering securemilitary and diplomatic voice and data communications toNATO member nations and troops in the field. The satelliteoffered spot beam and global coverage to reach a wide rangeof ground stations and ships at sea. The communicationspackage housed four SHF and two UHF channels. Thepayload was provided by Marconi Space Systems; the satellitewas built by British Aerospace. Based on the Skynet 4 design,it was box-shaped, measuring 2.1 m high by 1.9 m long by 1.4m wide. Solar arrays spanned 16 m and provided 1,200 W atend of life. The satellite was operational above 18 deg. w andhad a 7-year design life. NATO 4B is scheduled to fly in 1993or 94.

NATO 4A

NSSDC ID: 1991-001A

Alternate Names

21047

Facts in Brief

Launch Date: 1991-01-08Launch Vehicle: Delta IILaunch Site: CapeCanaveral, United StatesMass: 1433.0 kgNominal Power: 1200.0 W

Funding Agency

North Atlantic TreatyOrganization(International)

Discipline

Communications


Launch/Orbitalinformation for NATO 4A

Experiments on NATO 4A

Data collections fromNATO 4A



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=NATO 4A

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=NATO 4A

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=NATO 4A

mailto:[email protected]?Subject=NMC Comment/Question: NATO 4A (1991-001A)











http://www.usa.gov/








Description

Global Positioning System (GPS) was developed by the USDepartment of Defense to provide all-weather round-the-clocknavigation capabilities for military ground, sea, and air forces.Since its implementation, GPS has also become an integralasset in numerous civilian applications and industries aroundthe globe, including recreational used (e.g., boating, aircraft,hiking), corporate vehicle fleet tracking, and surveying. GPSemploys 24 spacecraft in 20,200 km circular orbits inclined at55 degrees. These vehicles are placed in 6 orbit planes withfour operational satellites in each plane.

GPS Block 2 was the operational system, following thedemonstration system comprised of Block 1 (Navstar 1 - 11)spacecraft. These spacecraft were 3-axis stabilized, nadirpointing using reaction wheels. Dual solar arrays supplied 710watts of power. They used S-band (SGLS) communications forcontrol and telemetry and UHF cross-link between spacecraft.The payload consisted of two L-band navigation signals at1575.42 MHz (L1) and 1227.60 MHz (L2). Each spacecraftcarried 2 rubidium and 2 cesium clocks and nuclear detonationdetection sensors. Built by Rockwell Space Systems for theUS Air Force, the spacecraft measured 5.3 m across with solarpanels deployed and had a design life of 7.5 years.

Navstar 2A-02

NSSDC ID: 1991-047A

Alternate Names

USA 71

GPS 2-11

21552

Facts in Brief

Launch Date: 1991-07-04Launch Vehicle: Delta IILaunch Site: CapeCanaveral, United StatesMass: 840.0 kgNominal Power: 710.0 W

Funding Agency


Discipline



Launch/Orbitalinformation for Navstar2A-02

Experiments on Navstar2A-02

Data collections fromNavstar 2A-02



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, II





http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Navstar 2A-02

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Navstar 2A-02

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Navstar 2A-02

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Navstar 2A-02

mailto:[email protected]?Subject=NMC Comment/Question: Navstar 2A-02 (1991-047A)











http://www.usa.gov/







Description

NOAA-12 (NOAA-D before launch) is a third-generationoperational meteorological satellite for use in the NationalEnvironmental Satellite, Data, and Information Service(NESDIS). The satellite design provides an economical andstable sun-synchronous (morning equator-crossing) platformfor advanced operational instruments to measure the earth'satmosphere, its surface and cloud cover, and the near-spaceenvironment. Primary sensors include an Advanced Very HighResolution Radiometer (AVHRR) for observing daytime andnighttime global radiances and temperatures and a TIROSOperational Vertical Sounder (TOVS) for obtaining temperatureand water vapor profiles through the earth's atmosphere.Secondary experiments consist of a Space EnvironmentMonitor (SEM), which measures the proton and electron fluxesnear the earth, and an ARGOS Data Collection and LocationSystem, which processes and relays to central data acquisitionstations the various meteorological data received from free-floating balloons and ocean buoys distributed around theglobe. The satellite is based upon the Block 5D spacecraft busdeveloped for the U.S. Air Force, and it is capable ofmaintaining an earth-pointing accuracy of better than plus orminus 0.1 deg with a motion rate of less than 0.035 deg/s.NOAA 12 operations were closed as of April 2001.

NOAA 12

NSSDC ID: 1991-032A

Alternate Names

NOAA-D

21263

Facts in Brief

Launch Date: 1991-05-14Launch Vehicle: Atlas ELaunch Site: VandenbergAFB, United StatesMass: 588.9 kg

Funding Agencies

NOAA NationalEnvironmental SatelliteService (United States)


Disciplines

Communications

Earth Science

Space Physics


Launch/Orbitalinformation for NOAA 12

Experiments on NOAA 12

Data collections fromNOAA 12


Personnel


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data





http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=NOAA 12

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=NOAA 12

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=NOAA 12

mailto:[email protected]?Subject=NMC Comment/Question: NOAA 12 (1991-032A)














Dr. Albert Arking ProjectScientist


[email protected]

Mr. Gerald W.Longanecker

ProjectManager


Mr. James R.Greaves

ProgramManager



http://www.usa.gov/








Description

This US Navy Ocean Surveillance Satellite (NOSS) waslaunched from Vandenberg AFB aboard a Titan 4 rocket. Itplaced a cluster of one primary satellite and three smaller sub-satellites (that trailed along at distances of several hundredkilometers) into low polar orbit. This satellite array determinedthe location of radio and radars transmitters, usingtriangulation, and the identity of naval units, by analysis of theoperating frequencies and transmission patterns.

In external appearance, the sub-satellites were reminiscent ofthe Navy's Transit navigational satellites. The had gravitygradient orientation booms 10-15 meters long. These ensuredthat the side of the satellite body where the signal antennaswere mounted was constantly oriented toward the Earth. Thesatellites maintained an assigned position in a group atdistances of 30 to 240 km one from the other by using on-board low-thrust engines. As a result of ground processing ofdirection-finding data on the signals from target emittersprovided by a group of satellites, and also sequentially byseveral groups of satellites, the coordinates, direction andspeed of travel were obtained.

NOSS 10

NSSDC ID: 1991-076A

Alternate Names

USA 72

Naval Ocean SurveillanceSatellite 10

21775

Facts in Brief

Launch Date: 1991-11-08Launch Vehicle: Titan IVLaunch Site: VandenbergAFB, United States

Funding Agency

Department of Defense-Department of the Navy(United States)

Discipline



Launch/Orbitalinformation for NOSS 10

Experiments on NOSS 10

Data collections fromNOSS 10



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=NOSS 10

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=NOSS 10

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=NOSS 10

mailto:[email protected]?Subject=NMC Comment/Question: NOSS 10 (1991-076A)











http://www.usa.gov/








Description

The Okean series of satellites are all-weather radaroceanographic systems primarily designed to monitor sea-iceconditions in the Arctic Seas. The payload includes a side-looking radar, a scanning microwave radiometer, nadir-viewingmicrowave spectrometer, optical scanners and a datacollection platform. The spacecraft is a stepped cylindricalpressurized bus 3 m high and 1.4 m diameter. The spacecraftis 3-axis stabilized (nadir pointing, aided by a gravity gradientboom), has twin solar arrays spanning 4.82 m and an 11.8 mradar antenna mounted on the Earth-facing base. A primaryfeature of the Okean-series is direct Automatic PictureTransmission (APT) on 137.4 MHz of imagery to APT stationsas well as to foreign users. The on-board recorder has 6.5minute capacity and permits coverage and transmission of a470 x 2750 km image by side-looking radar (SLR) and 1930 x2750 km image by the multispectral scanner during a pass overan APT station. The Okean payload was flown on Cosmos1500, Cosmos 1602, Cosmos 1766, and Cosmos 1869 (radarfailed), as well as Okean-1 and Okean-2. See Karpov, A.,"Hydrometeorological, Oceanographic and Earth-ResourcesSatellite Systems Operated by the U.S.S.R.", Adv Space Res.,Vol. 11, No. 3, pp. 183-190, 1991.

Okean 3

NSSDC ID: 1991-039A

Alternate Names

21397

Facts in Brief

Launch Date: 1991-06-04Launch Vehicle: TsiklonLaunch Site: Plesetsk,U.S.S.RMass: 1950.0 kg

Funding Agency

Russian Space Agency(Russia)

Discipline

Earth Science


Launch/Orbitalinformation for Okean 3

Experiments on Okean 3

Data collections fromOkean 3



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Okean 3

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Okean 3

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Okean 3

mailto:[email protected]?Subject=NMC Comment/Question: Okean 3 (1991-039A)











http://www.usa.gov/








Description

ORBCOMM-X was launched from the Kourou Space Center inFrench Guiana on the same Ariane rocket with UOSAT 5,TUBSAT, and SARA. Built by Orbital Sciences Corporation, itwas a forerunner of a proposed network of low-earth-orbitingmobile communications satellites. The 0.46 by 0.66 by 0.2-morbiter was powered by body mounted solar cells generating27 W. It was flown to evaluate the ORBCOMMcommunications system, explore possible store and forwardservices and test location determination capability. Initialground contact with ORBCOMM-X indicated the satellite washealthy, but communications were lost following a scheduledshut down of the VHF transmitter.

Orbcomm-X

NSSDC ID: 1991-050C

Alternate Names

21576

Facts in Brief

Launch Date: 1991-07-17Launch Vehicle: Ariane40Launch Site: Kourou,French GuianaMass: 22.1 kgNominal Power: 27.0 W

Funding Agency

Orbital Sciences Corp(United States)

Discipline

Communications


Launch/Orbitalinformation for Orbcomm-X

Experiments on Orbcomm-X

Data collections fromOrbcomm-X



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Orbcomm-X

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Orbcomm-X

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Orbcomm-X

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Orbcomm-X

mailto:[email protected]?Subject=NMC Comment/Question: Orbcomm-X (1991-050C)











http://www.usa.gov/








Description

This Chinese domestic communications satellite was strandedin an unusable orbit when the CZ-3 launch vehicle's third stagefailed 135 seconds after ignition. The satellite was placed intoa satisfactory parking orbit; the subsequent boost to transferorbit failed. The following day, the satellite's apogee kick motorraised its flight path, allowing it to perform limitedcommunications work from a highly elliptical orbit. ShiyongTongbu Weixing, or Operational GeostationaryCommunications Satellite, was part of the Chinese Dong FangHong 2 series. It was cylindrical, measuring about 2 m indiameter and 2.4 m high. The third stage failure was notexpected to affect the scheduled 1992 launches of 2 Australianpayloads.

PRC 34

NSSDC ID: 1991-088A

Alternate Names

STTW 5

21833

Facts in Brief

Launch Date: 1991-12-28Launch Vehicle: LongMarch 3Launch Site: Xichang,Peoples Republic of ChinaMass: 1025.0 kg

Funding Agency

Unknown (PeoplesRepublic of China)

Discipline

Communications


Launch/Orbitalinformation for PRC 34

Experiments on PRC 34

Data collections from PRC34



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=PRC 34

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=PRC 34

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=PRC 34

mailto:[email protected]?Subject=NMC Comment/Question: PRC 34 (1991-088A)











http://www.usa.gov/








Description

An improved version of cargo freighters used to supply the Mirspace station, the Progress M series had greater cargocapacity, a modernized approach/docking system and carried 2solar panels to generate electrical power. Progress M can flyfor 30 days independently and 108 days docked with Mir.Spare propellent in Progress M's tanks can be transferred toMir before it is consigned to burn up in reentry. In the past,extra fuel was abandoned with the craft. Future Progressvehicles will carry a recoverable reentry capsule for the speedyreturn of up to 150 kg of material from Mir to earth.

Progress M-6 docked with Mir on January 16, 1991.

Progress M- 6

NSSDC ID: 1991-002A

Alternate Names

21053

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Resupply/Refurbishment/Repair


Launch/Orbitalinformation for ProgressM- 6

Experiments on ProgressM- 6

Data collections fromProgress M- 6



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Progress M- 6


http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Progress M- 6


mailto:[email protected]?Subject=NMC Comment/Question: Progress M- 6 (1991-002A)











http://www.usa.gov/








Description


Progress M- 7

NSSDC ID: 1991-020A

Alternate Names

21188

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Progress M-8 docked with Mir on June 1, 1991.

Progress M- 8

NSSDC ID: 1991-038A

Alternate Names

21395

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Progress M- 9

NSSDC ID: 1991-057A

Alternate Names

21662

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Progress M-10

NSSDC ID: 1991-073A

Alternate Names

21746

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline



Launch/Orbitalinformation for ProgressM-10

Experiments on ProgressM-10

Data collections fromProgress M-10



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Progress M-10

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Progress M-10

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Progress M-10

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Progress M-10

mailto:[email protected]?Subject=NMC Comment/Question: Progress M-10 (1991-073A)











http://www.usa.gov/








Description

Raduga 27 was a Soviet communications satellite launchedfrom the Baikonur cosmodrome aboard a Proton 8K82K/BlockDM rocket. It provided uninterrupted round the clock telephoneand telegraph radio communications in the USSR andsimultaneous transmission of color and black and white USSRcentral television programs to stations in the Orbita network.

Raduga 27

NSSDC ID: 1991-014A

Alternate Names

21132

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications


Launch/Orbitalinformation for Raduga27

Experiments on Raduga 27

Data collections fromRaduga 27



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Raduga 27

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Raduga 27


mailto:[email protected]?Subject=NMC Comment/Question: Raduga 27 (1991-014A)











http://www.usa.gov/








Description

Raduga 28 was a Soviet communications satellite launchedfrom the Baikonur cosmodrome aboard a Proton 8K82K/BlockDM rocket. It provided uninterrupted round the clock telephoneand telegraph radio communications in the USSR andsimultaneous transmission of color and black and white USSRcentral television programs to stations in the Orbita network.

Raduga 28

NSSDC ID: 1991-087A

Alternate Names

21821

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Communications


Launch/Orbitalinformation for Raduga28

Experiments on Raduga 28

Data collections fromRaduga 28



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Raduga 28














http://www.usa.gov/








Description

The Resurs-F was a photoreconnaissance spacecraft used tomonitor Earth's natural resources (primarily those of theUSSR). The spacecraft flew two types of missionconfigurations: (1) F1, which typically lasted two weeks andused three Kate-200 and two KFA-1000 camera systems, and(2) F2, which flew in a lower orbit than F1, typically lasted 3-4weeks, and used the MK-4 camera system. The MK-4 was amultispectral visible wavelength camera which provided 5 to 8meter resolution. The MK-4 operated at six wavelengths:0.635-0.69, 0.81-0.9, 0.515-0.565, 0.46-0.505, 0.58-0.8, and0.4-0.7 micrometers. The Kate-200 was a 200 mm focal lengthcamera which operated at three wavelengths (0.5-0.6, 0.6-0.70.7-0.85 micrometers) with a resolution of 15 to 30 m. TheKFA-1000 was a 1000 mm focal length camera with twowavelengths (0.57-0.68 and 0.67-0.81 micrometers) at 2 to 5m resolution. The film camera systems were returned in 2.321diameter spherical descent capsules, which were re-usedapproximately three times. The F2 mission was supported bysolar panels which backed up the standard battery powersupply. A stellar camera was provided on each mission forpointing. The data will be available in the U.S. through CentralTrading Systems of Fort Worth, TX.

Resurs-F10

NSSDC ID: 1991-035A

Alternate Names

21313

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Earth Science


Launch/Orbitalinformation for Resurs-F10

Experiments on Resurs-F10

Data collections fromResurs-F10



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Resurs-F10


http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Resurs-F10


mailto:[email protected]?Subject=NMC Comment/Question: Resurs-F10 (1991-035A)











http://www.usa.gov/








Description

The Resurs-F was a photoreconnaissance spacecraft used tomonitor Earth's natural resources (primarily those of theUSSR). The spacecraft flew two types of missionconfigurations: (1) F1, which typically lasted two weeks andused three Kate-200 and two KFA-1000 camera systems, and(2) F2, which flew in a lower orbit than F1, typically lasted 3-4weeks, and used the MK-4 camera system. The MK-4 was amultispectral visible wavelength camera which provided 5 to 8meter resolution. The MK-4 operated at six wavelengths:0.635-0.69, 0.81-0.9, 0.515-0.565, 0.46-0.505, 0.58-0.8, and0.4-0.7 micrometers. The Kate-200 was a 200 mm focal lengthcamera which operated at three wavelengths (0.5-0.6, 0.6-0.70.7-0.85 micrometers) with a resolution of 15 to 30 m. TheKFA-1000 was a 1000 mm focal length camera with twowavelengths (0.57-0.68 and 0.67-0.81 micrometers) at 2 to 5m resolution. The film camera systems were returned in 2.321diameter spherical descent capsules, which were re-usedapproximately three times. The F2 mission was supported bysolar panels which backed up the standard battery powersupply. A stellar camera was provided on each mission forpointing.

Resurs-F11

NSSDC ID: 1991-044A

Alternate Names

21524

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Earth Science







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Resurs-F12

NSSDC ID: 1991-052A

Alternate Names

21611

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Earth Science







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description


Resurs-F13

NSSDC ID: 1991-058A

Alternate Names

21664

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Earth Science







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/








Description

REX was a US Air Force radiation experiment satellitelaunched using a Scout booster rocket. It performedexperiments to study scintillation effects of the Earth'satmosphere on RF transmissions. Built by Defense SystemsInc (DSI), the spacecraft was gravity gradient stabilized(approx. 5 degrees control) using a 6 m boom and 2.5 kg tipmass. Minor control was provided by three axis torque coils.

REX

NSSDC ID: 1991-045A

Alternate Names

Radiation Experiment

21527

Facts in Brief

Launch Date: 1991-06-29Launch Vehicle: ScoutLaunch Site: VandenbergAFB, United StatesMass: 85.0 kg

Funding Agency


Discipline



Launch/Orbitalinformation for REX

Experiments on REX

Data collections from REX



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=REX

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=REX

mailto:[email protected]?Subject=NMC Comment/Question: REX (1991-045A)











http://www.usa.gov/








Description

SARA was launched from the Kourou Space Center in FrenchGuiana on the same Ariane rocket with UOSAT 5, ORBCOMM-X, and TUBSAT. It carried a radio astronomy experimentdesigned to survey radioelectric emissions from Jupiter. It wasan 0.45-m cube built by the French Club ESIEESPACE. Withantennas deployed its height grew to 10 m. During its projected11-year mission, SARA will supplement information gatheredby the Ulysses and Galileo spacecraft.

SARA

NSSDC ID: 1991-050E

Alternate Names

21578

Facts in Brief

Launch Date: 1991-07-17Launch Vehicle: Ariane40Launch Site: Kourou,French GuianaMass: 36.0 kg

Funding Agency

Unknown (France)

Disciplines

Astronomy

Planetary Science


Launch/Orbitalinformation for SARA

Experiments on SARA

Data collections fromSARA



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=SARA

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=SARA

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=SARA

mailto:[email protected]?Subject=NMC Comment/Question: SARA (1991-050E)











http://www.usa.gov/






http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=SLABLS1[06/04/2011 23:36:32]


Description

The Spacelab Life Sciences-1 mission is devoted to lifesciences research related to the future health, safety, andproductivity of humans in space. A set of coordinated andcomplementary investigations focused on observations of earlyphysiological responses to weightlessness. In addition, thismission contains several materials science, environmentalmonitoring, and hardware verification tests. The SLS-1 missionis the first Space Shuttle Spacelab mission dedicated to lifesciences research. Proposed by an international team ofinvestigators, 18 primary and 11 secondary inflight payloadelements have been selected for flight. The scientific objectivesof the mission require data and specimen samples to begathered from animal and human subjects. The crew will alsobe involved in the acquisition and evaluation of data. Lifesciences hardware planned for this flight includes: the SmallMass Measurement Instrument (SMMI), Refrigerator/IncubatorModule (R/IM), General Purpose Work Station (GPWS),General Purpose Transfer Unit (GPTU), PhysiologicalMonitoring System (PMS), cardiovascular andcardiopulmonary testing apparatus, and the echocardiograph.An upgraded version of the Research Animal Holding facility(RAHF) is planned too.

SLS 1

NSSDC ID: SLABLS1

Alternate Names

Spacelab Life Sciences 1

Spacelab 4

Facts in Brief


Funding Agency


Discipline

Life Science


Launch/Orbitalinformation for SLS 1

Telecommunicationsinformation for SLS 1

Experiments on SLS 1

Data collections from SLS1


Personnel


Dr. Ronald J. Program NASA Headquarters


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data



http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=SLABLS1

http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=SLABLS1

http://nssdc.gsfc.nasa.gov/nmc/spacecraftTelemetry.do?id=SLABLS1

http://nssdc.gsfc.nasa.gov/nmc/spacecraftTelemetry.do?id=SLABLS1

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=SLS 1

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=SLS 1

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=SLS 1

mailto:[email protected]?Subject=NMC Comment/Question: SLS 1 (SLABLS1)












http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=SLABLS1[06/04/2011 23:36:32]

White Scientist

Mr. William P.Gilbreath

ProgramManager

NASA Headquarters

Dr. Howard J.Schneider

MissionScientist

NASA Johnson SpaceCenter

Mr. Gary W.McCollum

ProgramManager



http://www.usa.gov/






http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=SOT-1[06/04/2011 23:37:44]


Description

The main objective of the Space Optical Telescope (SOT) is toachieve the high spatial resolution required for thedetermination of density, temperature, magnetic field, and non-thermal velocity field in solar features on the scale at whichmany basic physical processes occur. Such processes includechanges in magnetic field strength, waves, single pulses, andsystematic mass flows. To understand the flow of energy andmass on a global scale over the surface of the sun, it isnecessary to investigate structures only slightly larger than thephoton mean free path. SOT consists of two major parts: thetelescope facility, which remains essentially unchanged frommission to mission; and the scientific instruments (SIs) which,depending upon the objectives, may vary from mission tomission. The telescope uses an on-axis Gregorianconfiguration with primary mirror 1.3 m in diameter. Theparaboloidal primary mirror focuses light through a hole in aheat-rejection mirror allowing only 3 arc-min of the sun's 32-arc-min disk to be seen by the secondary mirror. Theellipsoidal secondary mirror reflects the image onto a flattertiary mirror that directs the light beam off axis. Focal planeinstruments, such as those selected for the SOT-1 mission, arepositioned at the final or Gregorian focus. The telescope facilityhas an effective focal length of 31.25 m and a 151-micrometerarc-s plate scale. The SOT Observatory remains Shuttle-attached throughout the mission. It utilizes the Spacelab-provided instrument pointing system during on-orbitoperations, and is mounted via launch locks directly to theShuttle cargo bay during launch and landing. Missionoperations are conducted by dual interactive control, eitherfrom the payload specialist station in the Shuttle aft flight deckor from ground-based stations in the payload operationscontrol center.

Solar Optical Telescope

NSSDC ID: SOT-1

Alternate Names

SOT-1

Sunlab

HRSO

Facts in Brief


Funding Agency


Discipline

Solar Physics


Launch/Orbitalinformation for SolarOptical Telescope

Experiments on SolarOptical Telescope

Data collections from SolarOptical Telescope


Personnel



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data



http://nssdc.gsfc.nasa.gov/nmc/spacecraftOrbit.do?id=SOT-1



http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Solar Optical Telescope

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Solar Optical Telescope

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Solar Optical Telescope

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Solar Optical Telescope

mailto:[email protected]?Subject=NMC Comment/Question: Solar Optical Telescope (SOT-1)












http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=SOT-1[06/04/2011 23:37:44]

Dr. Stuart D.Jordan

ProjectScientist


[email protected]

Mr. George D.Hogan

ProjectManager


Dr. Eric G.Chipman

ProgramScientist

NASA Headquarters

Dr. Edmond M.Reeves

ProgramManager

NASA Headquarters


http://www.usa.gov/








Description

British cosmonaut Helen Sharman joined Anatoli Artsebarskiand Sergei Krikalev aboard Soyuz TM-12. She became thefirst woman to visit the Mir space station and conductedmedical experiments on behalf of her Soviet hosts. She alsotook pictures and made radio contact with Britishschoolchildren. Her 7-day, 21-hr, 14-mn mission ended May26, when she returned to earth with the TM-11 crew.Artsebarski and Krikalev settled into the Mir regimen ofexeriments and maintenance. An atmosphereic researchsubsatellite released June 17 failed when its antenna did notdeploy. A balloon deployment on August 15 also failed. During6 EVAs, taking place between June 25 and July 27, thecosmonauts installed outdoor experiments, retrieved others,repaired the Kvant docking antenna and erected a 14-mplatform to host an attitude control thruster for the growingstation. Total time outside Mir was 31 hrs, 58 mns. WhileArtsebarski and Krikalev orbited earth, their homeland suffereda failed coup d'etat and political turmoil that would lead to thebreakup of the Soviet Union. Mir activities, however, proceedednormally; Progress M-9 was launched on schedule on August20th. The cosmonauts were more affected by a decision madea month earlier to combine two upcoming Mir flights into one.The shuffle bumped Krikalev's replacement, requiring him tospend 5 more months in space. Soyuz TM-13, bringingArtsebarski's relief, arrived October 4. He returned to earthOctober 10 after 144 days, 15 hrs, 22 mns in space.

Soyuz TM-12

NSSDC ID: 1991-034A

Alternate Names

21311

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Human Crew


Launch/Orbitalinformation for Soyuz TM-12

Experiments on Soyuz TM-12

Data collections fromSoyuz TM-12



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Soyuz TM-12


http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Soyuz TM-12


mailto:[email protected]?Subject=NMC Comment/Question: Soyuz TM-12 (1991-034A)











http://www.usa.gov/





Soyuz TM-12

Launch, orbit and landing data Launch date: 18.05.1991 Launch time: 12:50 UT Launch site: Baikonur Launch pad: 1 Altitude: 350 km Inclination: 51,6° Landing date: 10.10.1991 Landing time: 04:12 UT Landing site: 67 km SE of Arkalyk

Crew

No. Surname Given name Job

1 Artsebarsky Anatoli Pavlovich Commander

2 Krikalyov Sergei Konstantinovich Flight Engineer

3 Sharman Helen Patricia "Lenochka" Research Cosmonaut

Flight Launch from Baikonur; landing 67 km southeast of Arkalyk. Docking on Soyuz TM-11-Quant1-MIR-Kristall-Quant2 complex; scientific experiments together

http://www.spacefacts.de/maps/english/e_bai_ussr_1.htm�

http://www.spacefacts.de/maps/english/e_soyuz-tm-12.htm�

http://www.spacefacts.de/bios/cosmonauts/english/artsebarsky_anatoli.htm�

http://www.spacefacts.de/bios/cosmonauts/english/krikalyov_sergei.htm�

http://www.spacefacts.de/bios/international/english/sharman_helen.htm�

http://www.spacefacts.de/mission/english/soyuz-tm11.htm�

with the eighth resident crew; Artsebarsky and Krikalyov became ninth MIR resident crew; both cosmonauts performed six EVA's on 24.06.1991 (4h 58m), 28.06.1991 (3h 24m), 15.07.1991 (5h 45m), 19.07.1991 (5h 28m), 23.07.1991 (5h 34m) and 27.07.1991 (6h 49m) (assembly of Sofora).

Photos / Drawings

http://www.spacefacts.de/mir/english/mir-8.htm�

http://www.spacefacts.de/bios/cosmonauts/english/artsebarsky_anatoli.htm�






Description

A crew representing Austria, the Republic of Kazakhstan, andthe Soviet states, was lofted to Mir aboard Soyuz TM-13.Austrian Franz Viehbock and Kazakh Toktar Aubakirov werepaying passengers. Aubakirov, from the home of the Tyuratamlaunch site, was the first commercial cosmonaut from insidethe USSR. Commander Aleksander Volkov, a Ukranian livingin Moscow, would reside on Mir for the next few months.Viehbock and Aubakirov spent their 6-day visit completing arigorous slate of medical, biological and technical experiments.Each also made photo surveys of their respective lands. Theresearchers returned to earth October 10, joining AnatoliArtsebarski aboard Soyuz TM-12. Both had logged 7 days, 22hrs, 13 mns in space. Volkov remained at Mir with veteranSergei Krikalev. On October 15, the team tested the Kvant portdocking antenna during a 1-hr, 44-mn flight around the stationaboard TM-13. Progress M-10 arrived October 21, docking twodays after an initial rendezvous was aborted by a computermalfunction. In contrast to the daily upheavals that wereshattering the Soviet Union, the Mir flight remained markedlyroutine. The cosmonauts devoted their working hours toastrophysical and geophysical experiments, medical studiesand smelting operations.

Soyuz TM-13

NSSDC ID: 1991-069A

Alternate Names

21735

Facts in Brief


Funding Agency

Unknown (U.S.S.R)

Discipline

Human Crew


Launch/Orbitalinformation for Soyuz TM-13

Experiments on Soyuz TM-13

Data collections fromSoyuz TM-13



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






















http://www.usa.gov/





Soyuz TM-13

Launch, orbit and landing data Launch date: 02.10.1991 Launch time: 05:59 UT Launch site: Baikonur Launch pad: 1 Altitude: 350 km Inclination: 51,6° Landing date: 25.03.1992 Landing time: 08:52 UT Landing site: 85 km NE of Arkalyk

Crew


1 Volkov Aleksandr Aleksandrovich Commander

2 Aubakirov Toktar Ongarbayevich Research Cosmonaut

3 Viehböck Franz Artur Research Cosmonaut

http://www.spacefacts.de/maps/english/e_bai_ussr_1.htm�

http://www.spacefacts.de/maps/english/e_soyuz-tm-13.htm�

http://www.spacefacts.de/bios/cosmonauts/english/volkov_aleksandr.htm�

http://www.spacefacts.de/bios/cosmonauts/english/aubakirov_toktar.htm�

http://www.spacefacts.de/bios/international/english/viehboeck_franz.htm�

Flight Launch from Baikonur; landing 85 km northeast of Arkalyk; docking on Soyuz TM-12-Quant1-MIR-Quant2-Kristall spacestation; scientific experiments with ninth resident crew; resident crew partly exchanged; Volkov and Krikalyov became tenth MIR-resident crew; both cosmonauts performed an EVA on 20.02.1992 (4h 12m).

Photos / Drawings

http://www.spacefacts.de/mission/english/soyuz-tm12.htm�


http://www.spacefacts.de/bios/cosmonauts/english/volkov_aleksandr.htm�






Description

STS-37 was the eighth flight of the shuttle Atlantis and the39th shuttle flight. The orbiter weighed 115,502 kg at launch;total vehicle weight was 2,047,178 kg. Much of the load wasthe Gamma Ray Observatory (GRO), at 15, 620 kg theheaviest shuttle-launched payload to date. STS 37 was staffedby Commander Steven R. Nagel, Pilot Kenneth D. Cameron,Mission Specialists Linda M. Godwin, Jerry L. Ross and JayApt. GRO deployment was scheduled from mission day three;an EVA to test conveyance carts and construction aids forlarge space structures was on the docket for day four. As ithappened, GRO deployment was delayed and the firstspacewalk since 1985 commenced a day early. Plans werechanged by a stubborn antenna. Midway though GRO'sdeployment sequence, while still attached to the remotemanipulator arm, the satellite's high gain antenna boom stuckin its stowed position. Repeated maneuvers to free it failed.Astronauts Ross and Apt were called on to free the boom byhand. Seventeen minutes after the pair exited Atlantis, Rossreleased the boom. GRO was ultimately cast into orbit only 4.5hr later than planned. While outside the shuttle, Ross and Aptbegan the scheduled equipment tests, evaluating hand railsand foot restrains. They reentered the shuttle after 4 hrs, 38mns. Outdoor activities resumed the next day, with the teamtesting manual and electric personnel carts during a 6-hr, 11-mn EVA. Several times during the flight, Atlantis passed withinview of the Mir station. The crew attempted to contact theirSoviet conterparts via ham radio, but were unsuccessful.Landing was delayed one day by gusty winds at Edwards AFB.The 5-day, 23-hr, 33-mn mission concluded on Edward'srunway 33 at 13:55, April 11.

STS 37

NSSDC ID: 1991-027A

Alternate Names

21224

Facts in Brief


Funding Agency

NASA-Office of SpaceFlight (United States)

Discipline

Human Crew


Launch/Orbitalinformation for STS 37

Telecommunicationsinformation for STS 37

Experiments on STS 37

Data collections from STS37



The Compton Gamma Ray Observatory

Other Sources of STS 37 Information/Data

STS 37 information (NASA KSC)


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Maps

New/Updated Data


STS 37






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=STS 37

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http://www.ksc.nasa.gov/shuttle/missions/sts-37/mission-sts-37.html









http://nssdc.gsfc.nasa.gov/image/spacecraft/sts-37.jpg



STS 37 Press Release images (NASA JSC)


http://images.jsc.nasa.gov/iams/html/pao/STS37.htm

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STS-37

Launch, orbit and landing data Launch date: 05.04.1991 Launch time: 14:22 UT Launch site: Cape Canaveral (KSC) Launch pad: 39-B Altitude: 459 km Inclination: 28,45° Landing date: 11.04.1991 Landing time: 13:55 UT Landing site: Edwards AFB

Crew


1 Nagel Steven Ray CDR

2 Cameron Kenneth Donald PLT

3 Godwin Linda Maxine MSP

4 Ross Jerry Lynn MSP

5 Apt Jerome "Jay" MSP

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http://www.spacefacts.de/bios/astronauts/english/cameron_kenneth.htm�

http://www.spacefacts.de/bios/astronauts/english/godwin_linda.htm�

http://www.spacefacts.de/bios/astronauts/english/ross_jerry.htm�

http://www.spacefacts.de/bios/astronauts/english/apt_jerome.htm�

Flight Launch from Cape Canaveral (KSC); landing on Edwards AFB. Deploying of the Gamma Ray Observatory (GRO) weight: 17,5 t; unscheduled EVA by Ross and Apt on 05.04.1991 (4h 24m) to free and deploy the failed GRO high-gain antenna; second (scheduled) EVA by Ross and Apt on 06.04.1991 (6h 11m) to test to move themselves and equipment for planned ISS; several other experiments.

Photos / Drawings








Description

STS-39 was the 12th shuttle Discovery flight and the firstunclassified military mission. The purpose of the flight was togather data needed to develop spaceborne sensors andsoftware that could recognize missile or reentry vehiclesignatures as they flew through or above the atmosphere. Tothat end, Discovery carried Air Force and Strategic DefenseInitiative-sponsored instruments to observe gases in the upperatmosphere, emissions from the shuttle engines, andchemicals released from co-orbiting subsatellites. Thescheduled observations required the crew to work around theclock in 12-hour shifts. Mission Commander was Michael L.Coats, the Pilot was Blaine Hammond Jr., and MissionSpecialists were Gregory L. Harbaugh, Donald R. McMonagle,Guion S. Buford, C. Lacy Veach and Richard J. Hieb. Theprimary Air Force payload -- a CIRRIS infrared telescope,secondary sensors and an ultraviolet camera -- was activated3 hours into the flight. Two failed tape recorders curtailed datacollection until the crew rigged a bypass on mission day 7. TheInfrared Background Signature Survey (IBSS) instrument,mounted on the Shuttle Pallet Satellite (SPAS), was deployedon May 1. A pointing error stalled the experiment for 9 hours.With IBSS/SPAS in position, the shuttle undertook a series offast Orbital Maneuvering System (OMS) and Reaction ControlSystem (RCS) burns. During the 27-mn sequence, and 3encores, the IBSS photographed Discovery's exhaust plumes.The free-flyer subsequently observed chemicals released fromthree subsatellites ejected from the cargo bay. A fifth satellitewas deployed several hours before landing. Discovery's returnto earth was rerouted to KSC due to high winds at EdwardsAFB. It touched down on the concrete runway at 18:55 May 6,after 8 days, 7 hrs, 22 mns in orbit. Despite the technicalproblems, the returns from STS 39 surpassed expectationsand will serve as a database for missile defense systemdevelopment.

STS 39

NSSDC ID: 1991-031A

Alternate Names

21242

Facts in Brief


Funding Agency


Discipline

Human Crew





Questions or commentsabout this spacecraft canbe directed to: Dr. Dieter K.Bilitza.


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data



















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STS-39

Launch, orbit and landing data Launch date: 28.04.1991 Launch time: 11:33 UT Launch site: Cape Canaveral (KSC) Launch pad: 39-A Altitude: 259 km Inclination: 57,0° Landing date: 06.05.1991 Landing time: 18:55 UT Landing site: Cape Canaveral (KSC)

Crew


1 Coats Michael Lloyd CDR

2 Hammond Lloyd Blaine, Jr. PLT

3 Harbaugh Gregory Jordan MSP

4 McMonagle Donald Ray MSP

5 Bluford Guion Stewart, Jr. "Guy" MSP

6 Veach Charles Lacy MSP

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http://www.spacefacts.de/bios/astronauts/english/hammond_blaine.htm�

http://www.spacefacts.de/bios/astronauts/english/harbaugh_gregory.htm�

http://www.spacefacts.de/bios/astronauts/english/mcmonagle_donald.htm�

http://www.spacefacts.de/bios/astronauts/english/bluford_guion.htm�

http://www.spacefacts.de/bios/astronauts/english/veach_charles.htm�

7 Hieb Richard James MSP

Flight Launch from Cape Canaveral (KSC); landing on Cape Canaveral (KSC). Dedicated Department of Defense mission, but first time not secret; SDI-experiments including AFP-675-payload and research complex IBSS (included deploying and retrieval of SPAS II and deploying of three CRO-satellites); also deploying SDI-satellite MPEC.

Photos / Drawings

http://www.spacefacts.de/bios/astronauts/english/hieb_richard.htm�




Description

The first shuttle mission dedicated to life sciences began at13:25, June 5, when Columbia lifted off from the KennedySpace Center Pad 39B. The orbiter also carried 12 Get AwaySpecials and 7 NASA Orbiter Experiments. The crew itself wasthe focal point for the Spacelab Life Science (SLS-1) researchto determine the causes of space sickness and note physicalchanges in microgravity conditions. The crew consisted ofCommander Bryan D. O'Connor, Pilot Sidney M. Gutierrez,Mission Specialists James P. Bagian, Tamara E. Jernigan,Margaret R. Seddon, and Payload Specialists F. Drew Gaffneyand Millie Highes-Fulford. The human crew was accompaniedby 29 white rats and 2,500 jellyfish. The astronauts entered theSpacelab module 3 hrs, 44 mns into the flight, kicking off arigorous work schedule in which they poked, prodded, spun,weighed, sampled, squeezed and monitored. It was the mostconcentrated life science research conducted in orbit sinceSkylab; the crew achieved 140% of mission goals. On flightday 2, concern was raised that torn insulation in the cargo baymight prevent the doors from closing. That unease wasdispelled and a proposed spacewalk to make repairs was notneeded. The 9-day, 2-hr, 14-mn mission ended on EdwardsAFB runway 22 at 15:39, June 14.

STS 40/SLS 1

NSSDC ID: 1991-040A

Alternate Names

21399

Facts in Brief


Funding Agency


Disciplines

Human Crew

Life Science


Launch/Orbitalinformation for STS40/SLS 1

Experiments on STS40/SLS 1

Data collections from STS40/SLS 1



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=STS 40/SLS 1

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=STS 40/SLS 1

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=STS 40/SLS 1

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=STS 40/SLS 1

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STS-40

Launch, orbit and landing data Launch date: 05.06.1991 Launch time: 13:24 UT Launch site: Cape Canaveral (KSC) Launch pad: 39-B Altitude: 290 km Inclination: 39° Landing date: 14.06.1991 Landing time: 15:39 UT Landing site: Edwards AFB

hi res version (783 KB)

Crew


1 O'Connor Bryan Daniel "O.C." CDR 2 Gutierrez Sidney McNeill "Sid" PLT 3 Bagian James Philipp MSP

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4 Jernigan Tamara Elizabeth "Tammy" MSP 5 Seddon Margaret Rhea MSP 6 Gaffney Francis Andrew "Drew" PSP 7 Hughes-Fulford Millie Elizabeth PSP

Flight Launch from Cape Canaveral (KSC); landing on Edwards AFB. Spacelab Life Science-Mission SLS-1; interrelated physological measurement in space; subjects were humans, rodents and jelly-fishes and their blood, bones, muscles, heart, lungs, inner-ear, brain and more; Hughes-Fulford was first female Payload Specialist.

Photos / Drawings

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Description

STS-43 was the ninth shuttle Atlantis flight. It's mission was todeploy a NASA communications satellite and to conduct abevy of scientific experiments. The five-person crew consistedof John E. Blaha, Commander; Michael A Baker, pilot;Shannon W. Lucid, G. David Low and James C. Adamson,mission specialists. The cargo bay held the Tracking and DataRelay Satellite (TDRS), and experimental heat pipe element,an ultraviolet experiment and instruments for opticalcommunications. Eight commercial crystal growth, materialsprocessing, photographic, fluids and microgravity experimentswere housed on the middeck. TDRS was dispatched from thecargo bay on orbit five, 6 hrs, 13 mns into the flight. The crewspent the remaining seven days conducting technologyexperiments and biomedical research. The entire flight fromliftoff to landing progressed like virtual clockwork. Atlantisreturned to earth on KSC's 15,00-ft concrete runway 15, at12:23, August 11, to end the 8-day, 21-hr, 21-mn mission.

STS 43/SSBUV03

NSSDC ID: 1991-054A

Alternate Names

21638

Facts in Brief


Funding Agency


Disciplines

Earth Science

Human Crew

Solar Physics


Launch/Orbitalinformation for STS43/SSBUV03

Experiments on STS43/SSBUV03

Data collections from STS43/SSBUV03



TDRS-E

Other Sources of STS 43 Information/Data


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Maps

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STS 43/SSBUV03





http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=STS 43/SSBUV03

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=STS 43/SSBUV03

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=STS 43/SSBUV03

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=STS 43/SSBUV03

mailto:[email protected]?Subject=NMC Comment/Question: STS 43/SSBUV03 (1991-054A)











http://nssdc.gsfc.nasa.gov/image/spacecraft/sts-43.jpg



STS 43 information (NASA KSC)STS 43 Press Release images (NASA JSC)


http://www.ksc.nasa.gov/shuttle/missions/sts-43/mission-sts-43.html

http://images.jsc.nasa.gov/iams/html/pao/STS43.htm

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STS-43

Launch, orbit and landing data Launch date: 02.08.1991 Launch time: 15:02 UT Launch site: Cape Canaveral (KSC) Launch pad: 39-A Altitude: 322 km Inclination: 28,45° Landing date: 11.08.1991 Landing time: 12:23 UT Landing site: Cape Canaveral (KSC)

Crew


1 Blaha John Elmer CDR

2 Baker Michael Allen PLT

3 Lucid Matilda Shannon Wells MSP

4 Low George David MSP

5 Adamson James Craig MSP


http://www.spacefacts.de/maps/english/ksc_landing.htm�

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http://www.spacefacts.de/bios/astronauts/english/baker_michael.htm�

http://www.spacefacts.de/bios/astronauts/english/lucid_shannon.htm�

http://www.spacefacts.de/bios/astronauts/english/low_david.htm�

http://www.spacefacts.de/bios/astronauts/english/adamson_james.htm�

Flight Launch from Cape Canaveral (KSC); landing on Cape Canaveral (KSC). Deploying of communications satellite TDRS-E; 32 physical, material and life sciences experiments were conducted.

Photos / Drawings




Description

STS-44 was the tenth shuttle Atlantis flight. On board wereAsrtonauts Frederick Gregory, Terence Henricks, StoryMusgrave, Mario Runco, James Voss, and Thomas Hennen.This was a dedicated mission for the US Department ofDefense to gather data for their programs. The DefenseSupport Program (DSP) satellite was deployed. The Cargo bayand middeck payloadsincluded: Interim OperationalContamination Monitor(IOCM); Terra Scout; Military Man inSpace (M88-1); Air Force Maui Optical System (AMOS);Cosmic Radiation Effects and Activation Monitor (CREAM);Shuttle Activation Monitor (SAM); Radiation MonitoringEquipment III (RME III); Visual Function Tester-1 (VFT-1);Ultraviolet Plume Instrument (UVPI). Bioreactor Flow andParticle Trajectory experiment; and Extended Duration OrbiterMedical Project, a series of investigations in support ofExtended Duration Orbiter. The mission was shortened whenan inertial measurement unit failed on the sixth day of themission. The mission duration was 166 hours 52 minutes 27seconds.

STS 44

NSSDC ID: 1991-080A

Alternate Names

21795

Facts in Brief


Funding Agency


Discipline

Human Crew






Personnel



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




















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STS-44

Launch, orbit and landing data Launch date: 24.11.1991 Launch time: 23:44 UT Launch site: Cape Canaveral (KSC) Launch pad: 39-A Altitude: 365 km Inclination: 28,5° Landing date: 01.12.1991 Landing time: 22:34 UT Landing site: Edwards AFB



Crew


1 Gregory Frederick Drew CDR

2 Henricks Terence Thomas "Tom" PLT

3 Voss James Shelton MSP

4 Musgrave Franklin Story MSP

5 Runco Mario, Jr. "Trooper" MSP

6 Hennen Thomas John MSE

Flight Launch from Cape Canaveral (KSC); landing on Edwards AFB. Dedicated Department of Defense mission; deploying of DSP-16-satellite; COLA-maneuver to fly in save distance to Kosmos 851-launch rocket; premature return to Earth due of to technical problems.

Photos / Drawings

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http://www.spacefacts.de/bios/astronauts/english/henricks_terence.htm�

http://www.spacefacts.de/bios/astronauts/english/voss_james.htm�

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Description

STS 48 was the thirteenth Discovery flight. On board wereAstronauts John Creighton, Kenneth Reightler, Mark Brown,James Buchli, and Charles Gemar. The mid-deck payloadconsisted of the Physiological and Anatomical RodentExperiment (PARE) wad the Protein Crystal Growth (PCG)experiment. The Upper Atmosphere Research Satellite (UARS)was launched to study physical processes acting within andupon the stratosphere, mesosphere, and lower thermosphere.Discovery landed in California on September 18, 1991. Themission duration was 128 hours, 27 minutes, 51 seconds.

STS 48

NSSDC ID: 1991-063A

Alternate Names

21700

Facts in Brief


Funding Agency


Discipline

Human Crew







Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data




















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STS-48

Launch, orbit and landing data Launch date: 12.09.1991 Launch time: 23:11 UT Launch site: Cape Canaveral (KSC) Launch pad: 39-A Altitute: 579 km Inclination: 57,0° Landing date: 18.09.1991 Landing time: 07:38 UT Landing site: Edwards AFB

Crew


1 Creighton John Oliver CDR

2 Reightler Kenneth Stanley, Jr. PLT

3 Gemar Charles Donald "Sam" MSP

4 Buchli James Frederick MSP

5 Brown Mark Neil MSP



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Flight Launch from Cape Canaveral (KSC); landing on Edwards AFB. Primary payload: Upper Atmosphere Research Satellite (UARS); several secondary payloads; crew performed the first Collision Avoidance Maneuver (COLA) to fly in save distance to a Kosmos 955-satellite segment.

Photos / Drawings




Description

TDRS-E was the fourth successful launch of the Tracking andData Relay Satellite series. TDRS-E was used in combinationwith other TDRS spacecraft and a ground communicationssystem to form the Tracking and Data Relay Satellite System(TDRSS).

The objective of the TDRSS program is to provide andmaintain improved tracking and data acquisition services tospacecraft in low-Earth orbit. In order to fulfill this objective,TDRSS requires at least two fully operational TDRS in orbitwith one or more additional spacecraft serving as systemspares.

Each TDRS is a three-axis, momentum-biased satellite. Thebus section of the spacecraft is hexagonal with an approximatediameter of 3 m. Power is provided by two opposing, three-section solar array panels, 4.0 x 3.8 m in dimension, at the endof 3.25 m booms. Perpendicular to the solar arrays are the two4.9 m diameter, K- and S-band, single-access (SA) antennae.With the solar panels and SA antennae deployed, TDRSmeasures 17.3 x 14.2 m.

TDRS is comprised of three functional modules: payload,spacecraft, and antenna. The payload module consists of twosingle-access compartments, the multiple access antennaplatform, and a main payload module. The main payloadmodule has six panels which form an integral part of the mainbus structure and house the principle elements of the TDRSpayload. The spacecraft module contains the thermal control,electrical power, attitude control, propulsion, and tracking,telemetry, and command systems. The antenna moduleconsists of the two SA dish antennae, the 2.0 m K-bandSpace-to-Ground Link (SGL) antenna, and, on the bus of thespacecraft, the 30 helical element, multiple access (MA)antenna array, a C-band antenna, and an S-bandomnidirectional SGL antenna.

In addition to changes made to previous TDRS spacecraftsubsequent to TDRS-A, TDRS-E was modified to providemultiple fusing of critical coaxial and waveguide switches ineach single access compartment as a result of on-orbitexperience with TDRS-C.

TDRS-E

NSSDC ID: 1991-054B

Alternate Names

TDRS 5

Tracking and Data RelaySatellite 5

21639

Facts in Brief

Launch Date: 1991-08-02Launch Vehicle: ShuttleLaunch Site: CapeCanaveral, United StatesMass: 2108.0 kgNominal Power: 1700.0 W

Funding Agency

NASA-Office of Trackingand Data Acquisition(United States)

Discipline

Communications


Launch/Orbitalinformation for TDRS-E

Experiments on TDRS-E

Data collections fromTDRS-E


Personnel



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


TDRS-E




http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=TDRS-E

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=TDRS-E

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=TDRS-E

mailto:[email protected]?Subject=NMC Comment/Question: TDRS-E (1991-054B)











http://nssdc.gsfc.nasa.gov/image/spacecraft/tdrse_deploy.jpg




NSSDC TDRS pageSTS 43

Other Sources of TDRS Information/Data

TDRS program


http://nssdc.gsfc.nasa.gov/multi/tdrs.html

http://esc.gsfc.nasa.gov/space-communications/tdrs.html

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Description

TELECOM-2A was a family of three communications satellites:A, B, and C. The objectives of TELECOM-2A were (1) tosucceed the TELECOM-1 family (which reached the end of itslife) which provided for telephone, FAX, TV and data transferservices between mainland and French overseas departments;(2) to provide government communications; (3) to transfer highrate data for professional apoplications of French industrialfirms; and (4) to transmit commercial TV channels.

TELECOM 2A

NSSDC ID: 1991-084A

Alternate Names

21813

Facts in Brief


Funding Agency

France Telecom (France)

Discipline

Communications


Launch/Orbitalinformation for TELECOM2A

Experiments on TELECOM2A

Data collections fromTELECOM 2A



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=TELECOM 2A

http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=TELECOM 2A

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=TELECOM 2A

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=TELECOM 2A

mailto:[email protected]?Subject=NMC Comment/Question: TELECOM 2A (1991-084A)











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Description

TUBSAT-1 was launched from the Kourou Space Center inFrench Guiana as a secondary payload on the same Arianerocket with three other secondary payloads UOSAT-F,ORBCOMM-X, and SARA, and the primary payload ERS-1.The TUBSAT microsatellites are designed and built at theTechnical University of Berlin (TUB). The primary objective ofTUBSAT-1 is academic research, particularly in the field ofattitude determination. It was financed by the German BMFT.The orbit is 10:30am sun-synchronous, circular, with aninclination of 98.5 degrees and a height of 780km. Tubsatweighs 35kg, and has a cubical shape with 380mm sides. Ithas a three axis star sensor, a fixed momentum wheel andmagnetorquer coil, a two axis sun-sensor and three axismagnetometer. The communication systems employfrequencies in the amateur satellite service VHF and UHFbands.

TUBSAT-1

NSSDC ID: 1991-050D

Alternate Names

21577

Facts in Brief


Funding Agency

Technical University ofBerlin (Federal Republicof Germany)

Discipline

Communications


Launch/Orbitalinformation for TUBSAT-1

Experiments on TUBSAT-1

Data collections fromTUBSAT-1



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=TUBSAT-1

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=TUBSAT-1

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=TUBSAT-1

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Description

The Upper Atmosphere Research Satellite (UARS), an elementin NASA's Mission to Planet Earth, was launched from theShuttle (STS 48) to provide data for better understanding ofthe Earth's upper atmosphere and the effects of natural andhuman interactions on the atmosphere. The objectives of theUARS mission were to conduct research in the atmosphereabove the tropopause by measuring the global budget ofconstituent trace gases and their chemical, dynamic,andradiative behavior.

UARS had two major components: an instrument modulecontaining the ten instruments and mission uniquecomponents, and a multimission modular spacecraft (MMS).The MMS included the Communications and Data Handling(C&DH) subsystem, the Modular Attitude Control Subsystem(MACS), the Modular Power Subsystem (MPS), the SignalConditioning and Control Unit (SC&CU), and the PropulsionModule. The C&DH provided communications, command andcontrol of the spacecraft and instruments, acquistion andstorage of science and housekeeping data, and centralcomputation facilities. The MACS provided attitudedetermination and control. The MACS subsystem maintainedthe Earth-oriented three-axis stability of the spacecraft throughthe use of star trackers, an inertial reference unit, three-axismagnetometers, a Fine Sun Sensor assembly, an EarthSensor Assembly, and a Coarse Sun Sensor assembly, aswell as momentum wheels, magnetic torquers, and attitudecontrol thrusters.

Power was maintained by a six-panel solar array and three 50A-hour batteries. The power subsystem also consisted of theMPS, regulators, solar array drive (which had some problemsduring summer 1992), solar array drive electronics, and powertransfer assemblies.

The instrument complement for UARS consisted of nineinstruments devoted to the primary atmospheric mission plusone announcement-of-opportunity instrument, the ActiveCavity Radiometer Irradiance Monitor II (ACRIM II). The nineprimary instruments were: (1) Cryogenic Limb Array EtalonSpectrometer (CLAES); (2) Improved Stratospheric andMesospheric Sounder (ISAMS); (3) Microwave Limb Sounder(MLS); (4) Halogen Occultation Experiment (HALOE); (5) HighResolution Doppler Imager (HRDI); (6) Wind ImagingInterferometer (WINDII); (7) Solar Ultraviolet SpectralIrradiance (SUSIM); (8) Solar Stellar Irradiance ComparisonExperiment (SOLSTICE); and, (9) Particle EnvironmentMonitor (PEM). There were also ten UARS investigatorsperforming theoretical investigations.

National Space Science Data Center Header

UARS

NSSDC ID: 1991-063B

Alternate Names

Upper AtmosphereResearch Satellite

21701

Facts in Brief

Launch Date: 1991-09-12Launch Vehicle: ShuttleLaunch Site: CapeCanaveral, United StatesMass: 6540.0 kgNominal Power: 1600.0 W

Funding Agency


Disciplines

Astronomy

Earth Science

Solar Physics

Space Physics


Launch/Orbitalinformation for UARS

PDMP information forUARS

Telecommunicationsinformation for UARS

Experiments on UARS

Data collections fromUARS

Questions or commentsabout this spacecraft canbe directed to: CoordinatedRequest and User Support


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data









http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=UARS

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=UARS

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=UARS

mailto:[email protected]?Subject=NMC Comment/Question: UARS (1991-063B)












Office.

Personnel


Mr. Michael R.Luther

ProgramManager

NASA Headquarters

Dr. LuisGonzales

ProjectManager


[email protected]

Dr. Robert J.McNeal

ProgramScientist

NASA Headquarters

Dr. Mark R.Schoeberl

ProjectScientist


[email protected]

Selected References

Reber, C. A., Upper Atmosphere Research Satellite, EOS, 71, No. 51, 1867-1868, 1873-1874,1878, Dec. 1990.

Other sources of UARS information

UARS Project (NASA GSFC)Goddard Earch Science Data and Information Services (GES DISC) (NASA GSFC)



http://umpgal.gsfc.nasa.gov/

http://daac.gsfc.nasa.gov/

http://www.usa.gov/








Description

UOSAT 5 was launched from the Kourou Space Center inFrench Guiana on the same Ariane rocket with ORBCOMM-X,TUBSAT and SARA. Built by the University of Surrey, UOSAT5 was a 50-kg commsat that stored and forwarded electronicmail messages. The rectangular craft measured 0.35 by 0.35by 0.6 m and was topped with a 6-m antenna. It also hostedradiation effects experiments and a CCD camera for 2-kmresolution imaging.

UOSAT 5

NSSDC ID: 1991-050B

Alternate Names

UOSAT-F

Oscar 22

21575

Facts in Brief


Funding Agency

University of Surrey(United Kingdom)

Discipline

Communications


Launch/Orbitalinformation for UOSAT 5

Experiments on UOSAT 5

Data collections fromUOSAT 5



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=UOSAT 5

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=UOSAT 5

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=UOSAT 5

mailto:[email protected]?Subject=NMC Comment/Question: UOSAT 5 (1991-050B)











http://www.usa.gov/








Description

USA 69 was launched by the US Department of Defense.

USA 69

NSSDC ID: 1991-017A

Alternate Names

Lacrosse 2

21147

Facts in Brief


Funding Agency

National ReconnaissanceOffice (United States)

Discipline



Launch/Orbitalinformation for USA 69

Experiments on USA 69

Data collections from USA69



Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data






http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=USA 69

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=USA 69


mailto:[email protected]?Subject=NMC Comment/Question: USA 69 (1991-017A)











http://www.usa.gov/








Description

USA-70 was deployed from the STS-39 mission for the USDepartment of Defense.

USA 70

NSSDC ID: 1991-031C

Alternate Names

21262

Facts in Brief

Launch Date: 1991-04-28Launch Vehicle: ShuttleLaunch Site: CapeCanaveral, United States

Funding Agency


Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data









mailto:[email protected]?Subject=NMC Comment/Question: USA 70 (1991-031C)











http://www.usa.gov/








Description



USA 74

NSSDC ID: 1991-076C

Alternate Names

21799

Facts in Brief


Funding Agency


Discipline








Spacecraft

Experiments

Data Collections

Personnel

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Maps

New/Updated Data




















http://www.usa.gov/








Description

This spacecraft is part of a continuing series of classifiedspacecraft. The three spacecraft USA 39 (1989-046A), USA 65(1990-095A), and USA 75 (1991-080B) replace an earlierconstellation of geosynchronous orbit spacecraft. These threewere positioned at longitudes of approximately 195, 8, and 72degrees, respectively, as of February 20, 1992. Eachspacecraft carries two instruments whose data are availablefor magnetospheric research: the Magnetospheric PlasmaAnalyzer (MPA) and the Synchronous Orbit Particle Analyzer(SOPA). The article by McComas et al., "Magnetosphericplasma analyzer: Initial three-spacecraft observations fromgeosynchronous orbit,'' (J. Geophys. Res., 98, No. A8, p.13453, 1993) gives more information. It also declares:"Recently, the MPA and SOPA data sets have become part ofthe International Solar Terrestrial Physics (ISTP) program withthe inclusion of key parameter data in the ISTP Central DataHandling Facility (CDHF). These data should provide avaluable adjunct to ISTP science, particularly in light of thelack of a dedicated `Equator' spacecraft, in addition toproviding new information about the geosynchronousenvironment in their own right.''

USA 75

NSSDC ID: 1991-080B

Alternate Names

DSP F16

Defense SupportProgram

21805

Facts in Brief


Funding Agency

Department of Defense(United States)

Disciplines


Space Physics






Selected References

McComas, D. J., et al., Magnetospheric plasma analyzer: Initial three-spacecraft observationsfrom geosynchronous orbit, J. Geophys. Res., 98, No. A8, 13453-13465, Aug. 1993.


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data


USA 75







mailto:[email protected]?Subject=NMC Comment/Question: USA 75 (1991-080B)











http://nssdc.gsfc.nasa.gov/image/spacecraft/dsp_f16.jpg



Image courtesy of the USAF Defense Support Program.


http://www.usa.gov/








Description



USA 76

NSSDC ID: 1991-076D

Alternate Names

21808

Facts in Brief


Funding Agency


Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data









mailto:[email protected]?Subject=NMC Comment/Question: USA 76 (1991-076D)











http://www.usa.gov/








Description



USA 77

NSSDC ID: 1991-076E

Alternate Names

21809

Facts in Brief


Funding Agency


Discipline








Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data









mailto:[email protected]?Subject=NMC Comment/Question: USA 77 (1991-076E)











http://www.usa.gov/








Description

The objective of Yohkoh (Japanese for sunbeam) is to studythe high-energy radiations from solar flares (hard and soft X-rays and energetic neutrons) as well as quiet structures andpre-flare conditions. The mission is a successor to Hinotori, aprevious Japanese spacecraft flown at the previous solaractivity maximum in 1981.

Yohkoh is a three-axis stabilized observatory-type satellite in anearly-circular Earth orbit, carrying four instruments: twoimagers and two spectrometers. The spacecraft is arectangular solid about 2 m square and 4 m long. The imaginginstruments have almost full-Sun fields of view, to avoidmissing any flares on the visible disk of the Sun. The hard X-ray telescope is a multi-grid synthesis type with a spatialresolution of 7 arcsec, operating in the 20 - 80 keV range. Thesoft X-ray telescope uses grazing-incidence optics andachieves 4 arcsec spatial resolution, operating in the 0.1 - 4keV range and using 1024 x 1024-pixel CCDs. US solarphysicists at Lockheed Palo Alto Research Laboratory arecollaborating in the soft X-ray telescope production and dataanalysis. There is also a continuum spectrometer for X-raysand gamma-rays from 3 keV to 20 MeV (also sensitive toneutrons) and a Bragg crystal spectrometer for the X-ray linesFe XXV, Fe XXVI, Ca XIX, and S XV.

Approximately 50 MB of data are accumulated per day, andstored on an on-board tape recorder with 10.5 Mbyte capacity.The Yohkoh mission is a cooperative mission of Japan, theUS, and the United Kingdom.

The Solar Data Analysis Center (SDAC) at NASA/GSFC canprovide small quantities of data, by request [email protected]. Sample data from the SXTimages may be obtained via the World Wide Web from theSDAC at:

http://umbra.nascom.nasa.gov/The Yohkoh analysis guide is available in PostScript form inthree parts from:

ftp://umbra.nascom.nasa.gov/pub/yohkoh/doc/iguide.ps

ftp://umbra.nascom.nasa.gov/pub/yohkoh/doc/rguide.ps

ftp://umbra.nascom.nasa.gov/pub/yohkoh/doc/uguide.ps

Yohkoh

NSSDC ID: 1991-062A

Alternate Names

Solar-A

21694

Facts in Brief

Launch Date: 1991-08-30Launch Vehicle: M-3SIILaunch Site: UchinouraSpace Center, JapanMass: 390.0 kgNominal Power: 200.0 W

Funding Agencies

Institute of Space andAeronautical Science, Uof Tokyo (Japan)


Discipline

Solar Physics


Launch/Orbitalinformation for Yohkoh

PDMP information forYohkoh

Telecommunicationsinformation for Yohkoh

Experiments on Yohkoh

Data collections fromYohkoh

Questions or commentsabout this spacecraft canbe directed to: Dr. H. KentHills.


Spacecraft

Experiments

Data Collections

Personnel

Publications

Maps

New/Updated Data



http://umbra.nascom.nasa.gov/







http://nssdc.gsfc.nasa.gov/nmc/experimentSearch.do?spacecraft=Yohkoh

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Yohkoh

http://nssdc.gsfc.nasa.gov/nmc/datasetSearch.do?spacecraft=Yohkoh

mailto:[email protected]?Subject=NMC Comment/Question: Yohkoh (1991-062A)

mailto:[email protected]?Subject=NMC Comment/Question: Yohkoh (1991-062A)











Personnel


Dr. YutakaUchida

Project Scientist University of Tokyo

Prof. Keizo Kai Mission PrincipalInvestigator

National Astronomical Observatory ofJapan

Dr. YoshiakiOgawara

Project Manager Institute of Space and AeronauticalScience

Selected References

The launching of M-3SII-6 rocket and ``Yohkoh'' satellite, Institute of Space and AstronauticalScience, Dec. 1991.

Kai, K., Rapid fluctuations in solar flares, NASA, Conference Pub. 2449, p. 647, 1986.


http://www.usa.gov/





Documents

NASA - NSSDC - Master Catalog - Spacecraft Query · 2011-05-31 · Cronología de Lanzamientos Espaciales . Año 1991 . Recopilación de datos Ing. Eladio Miranda Batlle. Los textos,