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TRANSCRIPT
Cronología de Lanzamientos Espaciales
Año 1981 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[03/11/2010 0:05:38]
Wednesday, 03 November 2010
Spacecraft Query Results
There were 159 spacecraft returned.
Spacecraft Name NSSDC ID Launch Date
APPLE 1981-057B 1981-06-19
Aureol 3 1981-094A 1981-09-21
Bhaskara 2 1981-115A 1981-11-20
Chalet 3 1981-107A 1981-10-31
COMSTAR 4 1981-018A 1981-02-21
Cosmos 1237 1981-001A 1981-01-06
Cosmos 1238 1981-003A 1981-01-16
Cosmos 1239 1981-004A 1981-01-16
Cosmos 1240 1981-005A 1981-01-20
Cosmos 1241 1981-006A 1981-01-21
Cosmos 1242 1981-008A 1981-01-27
Cosmos 1243 1981-010A 1981-02-02
Cosmos 1244 1981-013A 1981-02-12
Cosmos 1245 1981-014A 1981-02-13
Cosmos 1246 1981-015A 1981-02-18
Cosmos 1247 1981-016A 1981-02-19
Cosmos 1248 1981-020A 1981-03-05
Cosmos 1249 1981-021A 1981-03-05
Cosmos 1250 1981-022A 1981-03-06
Cosmos 1251 1981-022B 1981-03-06
Cosmos 1252 1981-022C 1981-03-06
Cosmos 1253 1981-022D 1981-03-06
Cosmos 1254 1981-022E 1981-03-06
Cosmos 1255 1981-022F 1981-03-06
Cosmos 1256 1981-022G 1981-03-06
Cosmos 1257 1981-022H 1981-03-06
Cosmos 1258 1981-024A 1981-03-14
Cosmos 1259 1981-026A 1981-03-17
Cosmos 1260 1981-028A 1981-03-20
Cosmos 1261 1981-031A 1981-04-01
Cosmos 1262 1981-032A 1981-04-07
Cosmos 1263 1981-033A 1981-04-09
Cosmos 1264 1981-035A 1981-04-15
Cosmos 1265 1981-036A 1981-04-16
Cosmos 1266 1981-037A 1981-04-21
Cosmos 1267 1981-039A 1981-04-25
NSSDC MasterCatalog Search
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http://nssdc.gsfc.nasa.gov/nmc/spacecraftSearch.do[03/11/2010 0:05:38]
Cosmos 1268 1981-040A 1981-04-28
Cosmos 1269 1981-041A 1981-05-07
Cosmos 1270 1981-045A 1981-05-18
Cosmos 1271 1981-046A 1981-05-19
Cosmos 1272 1981-047A 1981-05-21
Cosmos 1273 1981-048A 1981-05-22
Cosmos 1274 1981-052A 1981-06-03
Cosmos 1275 1981-053A 1981-06-04
Cosmos 1276 1981-055A 1981-06-16
Cosmos 1277 1981-056A 1981-06-17
Cosmos 1278 1981-058A 1981-06-19
Cosmos 1279 1981-062A 1981-07-01
Cosmos 1280 1981-063A 1981-07-02
Cosmos 1281 1981-064A 1981-07-07
Cosmos 1282 1981-066A 1981-07-15
Cosmos 1283 1981-067A 1981-07-17
Cosmos 1284 1981-068A 1981-07-29
Cosmos 1285 1981-071A 1981-08-04
Cosmos 1286 1981-072A 1981-08-04
Cosmos 1287 1981-074A 1981-08-06
Cosmos 1288 1981-074B 1981-08-06
Cosmos 1289 1981-074C 1981-08-06
Cosmos 1290 1981-074D 1981-08-06
Cosmos 1291 1981-074E 1981-08-06
Cosmos 1292 1981-074F 1981-08-06
Cosmos 1293 1981-074G 1981-08-06
Cosmos 1294 1981-074H 1981-08-06
Cosmos 1295 1981-077A 1981-08-12
Cosmos 1296 1981-078A 1981-08-13
Cosmos 1297 1981-079A 1981-08-18
Cosmos 1298 1981-080A 1981-08-21
Cosmos 1299 1981-081A 1981-08-24
Cosmos 1300 1981-082A 1981-08-24
Cosmos 1301 1981-083A 1981-08-27
Cosmos 1302 1981-084A 1981-08-28
Cosmos 1303 1981-086A 1981-09-04
Cosmos 1304 1981-087A 1981-09-04
Cosmos 1305 1981-088A 1981-09-11
Cosmos 1306 1981-089A 1981-09-14
Cosmos 1307 1981-090A 1981-09-15
Cosmos 1308 1981-091A 1981-09-18
Cosmos 1309 1981-092A 1981-09-18
Cosmos 1310 1981-095A 1981-09-23
Cosmos 1311 1981-097A 1981-09-28
Cosmos 1312 1981-098A 1981-09-30
Cosmos 1313 1981-099A 1981-10-01
Cosmos 1314 1981-101A 1981-10-09
Cosmos 1315 1981-103A 1981-10-14
Cosmos 1316 1981-104A 1981-10-15
NASA - NSSDC - Spacecraft - Query Results
http://nssdc.gsfc.nasa.gov/nmc/spacecraftSearch.do[03/11/2010 0:05:38]
Cosmos 1317 1981-108A 1981-10-31
Cosmos 1318 1981-109A 1981-11-03
Cosmos 1319 1981-112A 1981-11-13
Cosmos 1320 1981-116A 1981-11-28
Cosmos 1321 1981-116B 1981-11-28
Cosmos 1322 1981-116C 1981-11-28
Cosmos 1323 1981-116D 1981-11-28
Cosmos 1324 1981-116E 1981-11-28
Cosmos 1325 1981-116F 1981-11-28
Cosmos 1326 1981-116G 1981-11-28
Cosmos 1327 1981-116H 1981-11-28
Cosmos 1328 1981-117A 1981-12-03
Cosmos 1329 1981-118A 1981-12-04
Cosmos 1330 1981-121A 1981-12-19
DSP F9 1981-025A 1981-03-16
Dynamics Explorer 1 1981-070A 1981-08-03
Dynamics Explorer 2 1981-070B 1981-08-03
Ekran 7 1981-061A 1981-06-26
ETS 4 1981-012A 1981-02-11
FLTSATCOM 5 1981-073A 1981-08-06
GMS 2 1981-076A 1981-08-10
GOES 5 1981-049A 1981-05-22
Hinotori 1981-017A 1981-02-21
IK Bulgaria 1300 1981-075A 1981-08-07
INTELSAT 5 F-3 1981-119A 1981-12-15
INTELSAT 5B F-1 1981-050A 1981-05-23
Intercosmos 21 1981-011A 1981-02-06
ISKRA 1981-065C 1981-07-10
KH 11-4 1981-085A 1981-09-03
KH 8-51 1981-019A 1981-02-28
Marecs-A 1981-122A 1981-12-20
Meteor 1-31 1981-065A 1981-07-10
Meteor 2-7 1981-043A 1981-05-14
Meteosat 2 1981-057A 1981-06-19
Molniya 1-49 1981-009A 1981-01-30
Molniya 1-50 1981-060A 1981-06-24
Molniya 1-51 1981-113A 1981-11-17
Molniya 1-52 1981-123A 1981-12-23
Molniya 3-14 1981-002A 1981-01-09
Molniya 3-15 1981-030A 1981-03-24
Molniya 3-16 1981-054A 1981-06-09
Molniya 3-17 1981-105A 1981-10-17
NOAA 7 1981-059A 1981-06-23
NOVA I 1981-044A 1981-05-15
Progress 12 1981-007A 1981-01-24
Radio 3 1981-120A 1981-12-17
Radio 4 1981-120B 1981-12-17
Radio 5 1981-120C 1981-12-17
Radio 6 1981-120D 1981-12-17
NASA - NSSDC - Spacecraft - Query Results
http://nssdc.gsfc.nasa.gov/nmc/spacecraftSearch.do[03/11/2010 0:05:38]
Radio 7 1981-120E 1981-12-17
Radio 8 1981-120F 1981-12-17
Raduga 8 1981-027A 1981-03-18
Raduga 9 1981-069A 1981-07-30
Raduga 10 1981-102A 1981-10-09
RCA-SATCOM 3R 1981-114A 1981-11-20
Rohini 2 1981-051A 1981-05-31
SBS 2 1981-096A 1981-09-24
SDS F-4 1981-038A 1981-04-24
Shijian 2A 1981-093D 1981-09-19
Shijian 2B 1981-093A 1981-09-19
Shijian 2C 1981-093B 1981-09-19
SME 1981-100A 1981-10-06
Soyuz 39 1981-029A 1981-03-22
Soyuz 40 1981-042A 1981-05-14
Soyuz T-4 1981-023A 1981-03-12
Sphinx-B SPHNX-B 1981-11-01
STP P80-2 P80-2 1981-01-01
STS 1 1981-034A 1981-04-12
STS 2/OSTA 1 1981-111A 1981-11-12
UOSAT 1 1981-100B 1981-10-06
Venera 13 1981-106A 1981-10-30
Venera 13 Descent Craft 1981-106D 1981-10-30
Venera 14 1981-110A 1981-11-04
Venera 14 Descent Craft 1981-110D 1981-11-04
+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-057B[03/11/2010 0:18:09]
Wednesday, 03 November 2010
Description
The Ariane Passenger PayLoad Experiment (APPLE)spacecraft was launched via an Ariane L03 rocket from theKourou Space Center in French Guiana. Built by the IndianSpace Research Organization (ISRO), it was India's firstexperimental communications satellite. It provided experiencein building and operating a three-axis stabilizedcommunications satellite.
APPLE
NSSDC ID: 1981-057B
Alternate Names
Ariane Pass Payload Exp
12545
Facts in Brief
Launch Date: 1981-06-19Launch Vehicle: ArianeLaunch Site: Kourou,French GuianaMass: 670.0 kg
Funding Agency
Indian Space ResearchOrganization (India)
Discipline
Communications
AdditionalInformation
Launch/Orbitalinformation for APPLE
Experiments on APPLE
Data collections fromAPPLE
Questions or commentsabout this spacecraft canbe directed to: CoordinatedRequest and User SupportOffice.
NSSDC MasterCatalog Search
Spacecraft
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Lunar/Planetary Events
+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-094A[03/11/2010 0:18:45]
Wednesday, 03 November 2010
Description
Aureol 3 was a Soviet satellite that was part of the IntercosmosSeries, subset AUOS-T (automatic universal orbital stationterrestrial studies). The spacecraft was launched September21, 1981, in a near-polar orbit. The center portion of thespacecraft was a pressurized cylinder 1.6 m in diameter and2.7 m in height. Extending from the central body and deployedafter launch were the telemetry and command antennas, thesolar panels, and six booms holding various sensors awayfrom the spacecraft. Magnetic torquing and gravity gradientwere utilized to achieve three-axis stabilization. The Z axis ofthe spacecraft was aimed toward the center of the earth, the Xaxis was the direction of the spacecraft velocity vector. Bothpassive and active thermal control were used. Eight solarpanels and 28-V batteries provided a maximum power of 250W, and an average power of 50 W. The spacecraft carried atotal of 12 experiments (4 from the USSR, 7 from France, and1 done jointly by France and the USSR). The overall objectiveswere to provide some answers to the numerous questionsrelated to magnetosphere-ionosphere coupling at highlatitudes. The phenomena of interest included aurorae,magnetospheric substorms, origin and transport of plasmas,associated energies, electric currents, and electric fields. Theexperiments planned to meet these objectives includedmeasurements of ambient electron density, electrontemperature, and plasma velocity; of charged particles over therange 0.1 eV to 255 keV, plus electrons with energies above40 keV and protons with energies above 500 keV; of dcelectric and magnetic fields (0 to 10 Hz); of ELF and VLFwaves in the range 0.01 to 16 kHz; of electric fields atfrequencies from 0.1 to 16 MHz; and of auroral photometry at4278 A, 4861 A, and 6300 A. Commands were either carriedout in real time or stored on a weekly basis. Two instrumentswere used for onboard processing of experimental data. Thecorrelometer provided cross-correlation and autocorrelationdata for the measurement from either the four Kukushkadetectors (81-094A-01) or two Kukushka and two Pietstchanka(81-094A-02) detectors. The ONTCH-2ME instrument providedonboard processing of the data from the ISO F (81-094A-09)and ISO M (81-094A-10) experiments. Two telemetry systemswere used, a direct read-out system used over Frenchtelemetry stations and a delayed read-out system that usedtape-recording and play back over the Soviet telemetrystations. The routine scheduling of operations for the Frenchexperiments was initiated weekly (on Fridays), 24 days inadvance. It was coordinated through the French Centred'Operations Specialise ARCAD 3 (COS A3) and forwarded tothe Institute for Space Research (IKI), Moscow, where it wasmerged with the input from the Russian experimenters. It wasthen returned to France for concurrence and returned to IKI
Aureol 3
NSSDC ID: 1981-094A
Alternate Names
Aureole 3
ARCAD 3
Oreol 3
12848
Facts in Brief
Launch Date: 1981-09-21LaunchVehicle: Modified SS-6(Sapwood) with 2ndGeneration (Longer) UpperStageLaunch Site: Plesetsk,U.S.S.RMass: 1000.0 kg
Funding Agency
Soviet Academy ofSciences (U.S.S.R)
Discipline
Space Physics
AdditionalInformation
Launch/Orbitalinformation for Aureol 3
Experiments on Aureol 3
Data collections fromAureol 3
Questions or commentsabout this spacecraft canbe directed to: Dr. H. KentHills.
NSSDC MasterCatalog Search
Spacecraft
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New/Updated Data
Lunar/Planetary Events
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-094A[03/11/2010 0:18:45]
Moscow 11 days prior to the beginning of operations. Theschedule was then finalized and distributed 5 days prior to thebeginning of operations.
Personnel
Name Role Original Affiliation E-mail
Dr. M. G.Charles
ProjectManager
CNRS Centre d'Etudes Spatiale desRayonments
Prof. HenriReme
ProjectScientist
CNRS Centre d'Etudes Spatiale desRayonments
Prof. Yuri I.Galperin
ProjectScientist
Institut Kosmicheskich Issledovaniya(Institute of Space Research)
+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-115A[03/11/2010 0:19:21]
Wednesday, 03 November 2010
Description
Bhaskara 2 was launched as part of India's Satellite-for-Earth-Observations (SEO) program. It was placed in orbit by a Sovietvehicle launched from a Cosmodrome in the U.S.S.R. Themain objectives were to conduct earth observationexperiments for applications related to hydrology, forestry, andgeology using a two-TV-camera system, and to conductocean-surface studies using a three-frequency satellitemicrowave radiometer (SAMIR) system. Secondary objectiveswere to test engineering and data processing systems, and tocollect limited meteorological data from remote platforms.Bhaskara 2 was a 26-faced quasi-spherical polyhedron. It hada height of 1.66 m, and a diameter of 1.55 m. The satellite wasnamed after the two "Bhaskaracharyas," astronomer-mathematicians of ancient India. Information and data areavailable from the Space Application Centre, Ahmedabad,India.
Bhaskara 2
NSSDC ID: 1981-115A
Alternate Names
SEO 2
Sat. for Earth Obs. 2
12968
Facts in Brief
Launch Date: 1981-11-20LaunchVehicle: Modified SS-5(SKean IRBM) plus UpperStageLaunch Site: KapustinYar, U.S.S.RMass: 444.0 kg
Funding Agency
Indian Space ResearchOrganization (India)
Disciplines
Engineering
Earth Science
AdditionalInformation
Launch/Orbitalinformation for Bhaskara2
Experiments on Bhaskara2
Data collections fromBhaskara 2
Questions or commentsabout this spacecraft canbe directed to: CoordinatedRequest and User SupportOffice.
NSSDC MasterCatalog Search
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NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-115A[03/11/2010 0:19:21]
Personnel
Name Role Original Affiliation E-mail
Dr. K. Kasturirangan ProjectDirector
ISRO Satellite Center [email protected]
Mr. Om P. N. Calla ProjectScientist
Space ApplicationsCenter
Prof. UdipiRamachandra Rao
ProgramManager
ISRO Satellite Center [email protected]
Dr. G. Joseph ProjectScientist
Space ApplicationsCenter
+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-107A[03/11/2010 0:19:56]
Wednesday, 03 November 2010
Description
Chalet 3
NSSDC ID: 1981-107A
Alternate Names
12930
Facts in Brief
Launch Date: 1981-10-31Launch Vehicle: TitanIII-CLaunch Site: CapeCanaveral, United StatesMass: 820.0 kg
Funding Agency
Department of Defense-Department of the AirForce (United States)
Discipline
Surveillance and OtherMilitary
AdditionalInformation
Launch/Orbitalinformation for Chalet 3
Experiments on Chalet 3
Data collections fromChalet 3
Questions or commentsabout this spacecraft canbe directed to: CoordinatedRequest and User SupportOffice.
NSSDC MasterCatalog Search
Spacecraft
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Personnel
Publications
Maps
New/Updated Data
Lunar/Planetary Events
+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-018A[03/11/2010 0:20:32]
Wednesday, 03 November 2010
Description
COMSTAR 4 was the fourth in the series of four domesticcommunications launched by NASA from Cape Canaveral forCOMSAT.
COMSTAR 4
NSSDC ID: 1981-018A
Alternate Names
12309
Facts in Brief
Launch Date: 1981-02-21Launch Vehicle: Atlas-CentaurLaunch Site: CapeCanaveral, United StatesMass: 1520.0 kg
Funding Agency
Unknown (United States)
Discipline
Communications
AdditionalInformation
Launch/Orbitalinformation forCOMSTAR 4
Experiments on COMSTAR4
Data collections fromCOMSTAR 4
Questions or commentsabout this spacecraft canbe directed to: CoordinatedRequest and User SupportOffice.
NSSDC MasterCatalog Search
Spacecraft
Experiments
Data Collections
Personnel
Publications
Maps
New/Updated Data
Lunar/Planetary Events
+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-001A[03/11/2010 0:21:10]
Wednesday, 03 November 2010
Description
Cosmos 1237 was a Soviet photo surveillance satellitelaunched from the Plesetsk cosmodrome aboard a Soyuzrocket.
Cosmos 1237
NSSDC ID: 1981-001A
Alternate Names
12130
Facts in Brief
Launch Date: 1981-01-06LaunchVehicle: Soyuz-ULaunch Site: Plesetsk,U.S.S.RMass: 600.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and OtherMilitary
AdditionalInformation
Launch/Orbitalinformation for Cosmos1237
Experiments on Cosmos1237
Data collections fromCosmos 1237
Questions or commentsabout this spacecraft canbe directed to: CoordinatedRequest and User SupportOffice.
NSSDC MasterCatalog Search
Spacecraft
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Maps
New/Updated Data
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-003A[03/11/2010 0:21:45]
Wednesday, 03 November 2010
Description
Cosmos 1238 was a Soviet atmospheric research satellitelaunched from the Plesetsk cosmodrome aboard a Kosmos 11rocket. It was the 12th in a series of Vektor spacecraft.
Cosmos 1238
NSSDC ID: 1981-003A
Alternate Names
12138
Facts in Brief
Launch Date: 1981-01-16LaunchVehicle: Modified SS-5(SKean IRBM) plus UpperStageLaunch Site: Plesetsk,U.S.S.RMass: 550.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Earth Science
AdditionalInformation
Launch/Orbitalinformation for Cosmos1238
Experiments on Cosmos1238
Data collections fromCosmos 1238
Questions or commentsabout this spacecraft canbe directed to: CoordinatedRequest and User SupportOffice.
NSSDC MasterCatalog Search
Spacecraft
Experiments
Data Collections
Personnel
Publications
Maps
New/Updated Data
Lunar/Planetary Events
+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-004A[03/11/2010 0:22:11]
Wednesday, 03 November 2010
Description
Cosmos 1239 was a Soviet photo surveillance satellitelaunched from the Plesetsk cosmodrome aboard a Soyuzrocket. The spacecraft also performed mapping, geodesy.
Cosmos 1239
NSSDC ID: 1981-004A
Alternate Names
12140
Facts in Brief
Launch Date: 1981-01-16LaunchVehicle: Soyuz-ULaunch Site: Plesetsk,U.S.S.RMass: 5700.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and OtherMilitary
AdditionalInformation
Launch/Orbitalinformation for Cosmos1239
Experiments on Cosmos1239
Data collections fromCosmos 1239
Questions or commentsabout this spacecraft canbe directed to: CoordinatedRequest and User SupportOffice.
NSSDC MasterCatalog Search
Spacecraft
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-005A[03/11/2010 0:22:40]
Wednesday, 03 November 2010
Description
Cosmos 1240 was a Soviet photo surveillance satellitelaunched from the Baikonur cosmodrome aboard a Soyuzrocket. Returned film in two small SpK capsules during missionand in the main cabin at completion of the mission.
Cosmos 1240
NSSDC ID: 1981-005A
Alternate Names
12143
Facts in Brief
Launch Date: 1981-01-20LaunchVehicle: Modified SS-6(Sapwood) with 2ndGeneration (Longer) UpperStageLaunch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.RMass: 6700.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and OtherMilitary
AdditionalInformation
Launch/Orbitalinformation for Cosmos1240
Experiments on Cosmos1240
Data collections fromCosmos 1240
Questions or commentsabout this spacecraft canbe directed to: CoordinatedRequest and User SupportOffice.
NSSDC MasterCatalog Search
Spacecraft
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New/Updated Data
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed Grayzeck
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-006A[07/11/2010 0:04:32]
Sunday, 07 November 2010
Description
Cosmos 1241 was a Soviet satellite launched from thePlesetsk cosmodrome aboard a Kosmos rocket. It was anASAT (anti-satellite) target for the Cosmos 1243 and 1258interceptors. It was part of a series of tests to validatefunctioning of system after extended storage.
It was designated the IS ("Istrebitel Sputnikov", fightersatellite). The orbital parameters of the target satellite wouldalready be known before launch, and the interceptor would bepre-programmed with those parameters. After being placedinto an initial parking orbit by the launch vehicle, theinterceptor's engine would make a number of manoeuvres tointercept with the target, and at the appropriate moment, blowitself up together with the target. The interception was intendedto take place on the first to third orbit, although it would bepossible to make repeated attempts in case the target wasmissed.
The Istrebitel Sputnikov was approximately spherical in formand had a total mass of 1,400 kg. It consisted of two sections:the main section, which contained the guidance and targeting,computational and optical homing systems, and the 300 kgexplosive charge; and the engine section. The body of theinterceptor was designed so that after the explosion it wouldfragment into 12 groups of shrapnel. The specified radius ofguaranteed target destruction was 1 km. However in a head-onintercept, only 400 m radius was guaranteed, while in a chaseintercept, a 2 km radius of destruction could be achieved. Theengine was capable of numerous quick starts and restarts,with a total operating time of 300 seconds.
Cosmos 1241
NSSDC ID: 1981-006A
Alternate Names
12149
Facts in Brief
Launch Date: 1981-01-21LaunchVehicle: Modified SS-5(SKean IRBM) plus UpperStageLaunch Site: Plesetsk,U.S.S.RMass: 650.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and OtherMilitary
AdditionalInformation
Launch/Orbitalinformation for Cosmos1241
Experiments on Cosmos1241
Data collections fromCosmos 1241
Questions or commentsabout this spacecraft canbe directed to: CoordinatedRequest and User SupportOffice.
NSSDC MasterCatalog Search
Spacecraft
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Data Collections
Personnel
Publications
Maps
New/Updated Data
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-008A[07/11/2010 0:05:13]
Sunday, 07 November 2010
Description
Cosmos 1242 was a Soviet 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 1242
NSSDC ID: 1981-008A
Alternate Names
12154
Facts in Brief
Launch Date: 1981-01-27LaunchVehicle: Modified SS-6(Sapwood) with 1stGeneration Upper StageLaunch Site: Plesetsk,U.S.S.RMass: 2500.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and OtherMilitary
AdditionalInformation
Launch/Orbitalinformation for Cosmos1242
Experiments on Cosmos1242
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-010A[07/11/2010 0:05:52]
Sunday, 07 November 2010
Description
Cosmos 1243 was a Soviet ASAT interceptor launched fromthe Baikonur cosmodrome aboard a Tsyklon 2 rocket. Itapproached within 50 m of the target (Cosmos 1241), but anexplosive charge did not go off as planned. It deorbited todestructive re-entry in the atmosphere.
Cosmos 1243
NSSDC ID: 1981-010A
Alternate Names
12160
Facts in Brief
Launch Date: 1981-02-02LaunchVehicle: Modified SS-9(SCARP) or SS-13(SCRAG) with Orbital andManeuverableLaunch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.RMass: 1400.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and OtherMilitary
AdditionalInformation
Launch/Orbitalinformation for Cosmos1243
Experiments on Cosmos1243
Data collections fromCosmos 1243
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed Grayzeck
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-013A[07/11/2010 0:06:35]
Sunday, 07 November 2010
Description
Cosmos 1244 was part of a 6-satellite Soviet 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 1244
NSSDC ID: 1981-013A
Alternate Names
12297
Facts in Brief
Launch Date: 1981-02-12LaunchVehicle: Modified SS-5(SKean IRBM) plus UpperStageLaunch Site: Plesetsk,U.S.S.RMass: 810.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Communications
AdditionalInformation
Launch/Orbitalinformation for Cosmos1244
Experiments on Cosmos1244
Data collections fromCosmos 1244
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-014A[07/11/2010 0:07:56]
Sunday, 07 November 2010
Description
Cosmos 1245 was a Soviet photo surveillance satellitelaunched from the Plesetsk cosmodrome aboard a Soyuzrocket.
Cosmos 1245
NSSDC ID: 1981-014A
Alternate Names
12299
Facts in Brief
Launch Date: 1981-02-13LaunchVehicle: Soyuz-ULaunch Site: Plesetsk,U.S.S.RMass: 6300.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and OtherMilitary
AdditionalInformation
Launch/Orbitalinformation for Cosmos1245
Experiments on Cosmos1245
Data collections fromCosmos 1245
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-015A[07/11/2010 0:08:48]
Sunday, 07 November 2010
Description
A variation of the Yantar-class spacecraft appeared in 1981(Cosmos 1246) to conduct high-precision topographic surveys.These spacecraft, now referred to as Kometa, typicallyremained in orbit for 44-45 days and were distinguished bytheir relatively circular orbits between 210 and 280 km. Thesemissions were always launched from the Baikonurcosmodrome into inclinations of 65 degrees or 70 degrees atthe rate of one or two per year.
Cosmos 1246
NSSDC ID: 1981-015A
Alternate Names
12301
Facts in Brief
Launch Date: 1981-02-18LaunchVehicle: Soyuz-ULaunch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.RMass: 6700.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Earth Science
AdditionalInformation
Launch/Orbitalinformation for Cosmos1246
Experiments on Cosmos1246
Data collections fromCosmos 1246
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-016A[07/11/2010 0:09:56]
Sunday, 07 November 2010
Description
Cosmos 1247 was a Soviet missile early warning satellitelaunched from the Plesetsk cosmodrome aboard a Molniyarocket. It was part of the Oko constellation of satellites andcovered the plane 5 - 77 degree longitude of ascending node.
Cosmos 1247
NSSDC ID: 1981-016A
Alternate Names
12303
Facts in Brief
Launch Date: 1981-02-19LaunchVehicle: Modified SS-6(Sapwood) with 2ndGeneration Upper Stage +Escape StageLaunch Site: Plesetsk,U.S.S.RMass: 1250.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and OtherMilitary
AdditionalInformation
Launch/Orbitalinformation for Cosmos1247
Experiments on Cosmos1247
Data collections fromCosmos 1247
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, II
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-020A[07/11/2010 0:11:05]
Sunday, 07 November 2010
Description
Cosmos 1248 was a Soviet photo surveillance satellitelaunched from the Plesetsk cosmodrome aboard a Soyuzrocket. Returned film in two small SpK capsules during missionand in the main cabin at completion of the mission.
Cosmos 1248
NSSDC ID: 1981-020A
Alternate Names
12317
Facts in Brief
Launch Date: 1981-03-05LaunchVehicle: Modified SS-6(Sapwood) with 2ndGeneration (Longer) UpperStageLaunch Site: Plesetsk,U.S.S.RMass: 6700.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and OtherMilitary
AdditionalInformation
Launch/Orbitalinformation for Cosmos1248
Experiments on Cosmos1248
Data collections fromCosmos 1248
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, II
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-021A[07/11/2010 0:11:31]
Sunday, 07 November 2010
Description
Cosmos 1249 was a Soviet nuclear powered Radar OceanReconnaissance Satellite (RORSAT) launched from theBaikonur cosmodrome aboard a Tsyklon 2 rocket. TheRORSATs were designed to search the oceans for US Navytask forces and other shipping.
Cosmos 1249
NSSDC ID: 1981-021A
Alternate Names
12319
Facts in Brief
Launch Date: 1981-03-05LaunchVehicle: Tsiklon-2Launch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.RMass: 3800.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and OtherMilitary
AdditionalInformation
Launch/Orbitalinformation for Cosmos1249
Experiments on Cosmos1249
Data collections fromCosmos 1249
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-022A[07/11/2010 0:11:55]
Sunday, 07 November 2010
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 1250
NSSDC ID: 1981-022A
Alternate Names
12320
Facts in Brief
Launch Date: 1981-03-06LaunchVehicle: Modified SS-5(SKean IRBM) plus UpperStageLaunch Site: Plesetsk,U.S.S.RMass: 40.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Communications
AdditionalInformation
Launch/Orbitalinformation for Cosmos1250
Experiments on Cosmos1250
Data collections fromCosmos 1250
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-022B[07/11/2010 0:12:21]
Sunday, 07 November 2010
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 1251
NSSDC ID: 1981-022B
Alternate Names
12321
Facts in Brief
Launch Date: 1981-03-06LaunchVehicle: Modified SS-5(SKean IRBM) plus UpperStageLaunch Site: Plesetsk,U.S.S.RMass: 40.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Communications
AdditionalInformation
Launch/Orbitalinformation for Cosmos1251
Experiments on Cosmos1251
Data collections fromCosmos 1251
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-022C[07/11/2010 0:12:46]
Sunday, 07 November 2010
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 1252
NSSDC ID: 1981-022C
Alternate Names
12322
Facts in Brief
Launch Date: 1981-03-06LaunchVehicle: Modified SS-5(SKean IRBM) plus UpperStageLaunch Site: Plesetsk,U.S.S.RMass: 40.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Communications
AdditionalInformation
Launch/Orbitalinformation for Cosmos1252
Experiments on Cosmos1252
Data collections fromCosmos 1252
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-022D[07/11/2010 0:13:24]
Sunday, 07 November 2010
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 1253
NSSDC ID: 1981-022D
Alternate Names
12323
Facts in Brief
Launch Date: 1981-03-06LaunchVehicle: Modified SS-5(SKean IRBM) plus UpperStageLaunch Site: Plesetsk,U.S.S.RMass: 40.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Communications
AdditionalInformation
Launch/Orbitalinformation for Cosmos1253
Experiments on Cosmos1253
Data collections fromCosmos 1253
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-022E[07/11/2010 0:14:04]
Sunday, 07 November 2010
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 1254
NSSDC ID: 1981-022E
Alternate Names
12324
Facts in Brief
Launch Date: 1981-03-06LaunchVehicle: Modified SS-5(SKean IRBM) plus UpperStageLaunch Site: Plesetsk,U.S.S.RMass: 40.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Communications
AdditionalInformation
Launch/Orbitalinformation for Cosmos1254
Experiments on Cosmos1254
Data collections fromCosmos 1254
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-022F[07/11/2010 0:15:18]
Sunday, 07 November 2010
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 1255
NSSDC ID: 1981-022F
Alternate Names
12325
Facts in Brief
Launch Date: 1981-03-06LaunchVehicle: Modified SS-5(SKean IRBM) plus UpperStageLaunch Site: Plesetsk,U.S.S.RMass: 40.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Communications
AdditionalInformation
Launch/Orbitalinformation for Cosmos1255
Experiments on Cosmos1255
Data collections fromCosmos 1255
Questions or commentsabout this spacecraft canbe directed to: CoordinatedRequest and User SupportOffice.
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-022G[07/11/2010 0:16:53]
Sunday, 07 November 2010
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 1256
NSSDC ID: 1981-022G
Alternate Names
12326
Facts in Brief
Launch Date: 1981-03-06LaunchVehicle: Modified SS-5(SKean IRBM) plus UpperStageLaunch Site: Plesetsk,U.S.S.RMass: 40.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Communications
AdditionalInformation
Launch/Orbitalinformation for Cosmos1256
Experiments on Cosmos1256
Data collections fromCosmos 1256
Questions or commentsabout this spacecraft canbe directed to: CoordinatedRequest and User SupportOffice.
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-022H[07/11/2010 0:17:43]
Sunday, 07 November 2010
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 1257
NSSDC ID: 1981-022H
Alternate Names
12327
Facts in Brief
Launch Date: 1981-03-06LaunchVehicle: Modified SS-5(SKean IRBM) plus UpperStageLaunch Site: Plesetsk,U.S.S.RMass: 40.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Communications
AdditionalInformation
Launch/Orbitalinformation for Cosmos1257
Experiments on Cosmos1257
Data collections fromCosmos 1257
Questions or commentsabout this spacecraft canbe directed to: CoordinatedRequest and User SupportOffice.
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-024A[07/11/2010 0:18:42]
Sunday, 07 November 2010
Description
Cosmos 1258 was a Soviet ASAT interceptor launched fromthe Baikonur cosmodrome aboard a Tsyklon 2 rocket. It failedto intercept the intended target (Cosmos 1241). It deorbited todestructive re-entry in the atmosphere.
Cosmos 1258
NSSDC ID: 1981-024A
Alternate Names
12337
Facts in Brief
Launch Date: 1981-03-14LaunchVehicle: Modified SS-9(SCARP) or SS-13(SCRAG) with Orbital andManeuverableLaunch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.RMass: 1400.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and OtherMilitary
AdditionalInformation
Launch/Orbitalinformation for Cosmos1258
Experiments on Cosmos1258
Data collections fromCosmos 1258
Questions or commentsabout this spacecraft canbe directed to: CoordinatedRequest and User SupportOffice.
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed Grayzeck
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-026A[07/11/2010 0:19:55]
Sunday, 07 November 2010
Description
Cosmos 1259 was a Soviet photo surveillance satellitelaunched from the Baikonur cosmodrome aboard a Soyuzrocket.
Cosmos 1259
NSSDC ID: 1981-026A
Alternate Names
12341
Facts in Brief
Launch Date: 1981-03-17LaunchVehicle: Soyuz-ULaunch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.RMass: 6300.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and OtherMilitary
AdditionalInformation
Launch/Orbitalinformation for Cosmos1259
Experiments on Cosmos1259
Data collections fromCosmos 1259
Questions or commentsabout this spacecraft canbe directed to: CoordinatedRequest and User SupportOffice.
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http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-028A[07/11/2010 0:20:33]
Sunday, 07 November 2010
Description
Cosmos 1260 was a Soviet naval reconnaisance satellitelaunched from the Baiknour 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 1260
NSSDC ID: 1981-028A
Alternate Names
12364
Facts in Brief
Launch Date: 1981-03-20LaunchVehicle: Modified SS-9(SCARP) or SS-13(SCRAG) with Orbital andManeuverableLaunch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.RMass: 3000.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Human Crew
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Launch/Orbitalinformation for Cosmos1260
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http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-031A[07/11/2010 0:21:09]
Sunday, 07 November 2010
Description
Cosmos 1261 was a Soviet missile early warning satellitelaunched from the Plesetsk cosmodrome aboard a Molniyarocket. It was part of the Oko constellation of satellites andcovered the plane 6 - 115 degree longitude of ascending node.
Cosmos 1261
NSSDC ID: 1981-031A
Alternate Names
12376
Facts in Brief
Launch Date: 1981-04-01LaunchVehicle: Molniya-MLaunch Site: Plesetsk,U.S.S.RMass: 1250.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and OtherMilitary
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http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-032A[07/11/2010 0:21:34]
Sunday, 07 November 2010
Description
Cosmos 1262 was a Soviet photo surveillance satellitelaunched from the Plesetsk cosmodrome aboard a Soyuzrocket. The spacecraft was maneuverable.
Cosmos 1262
NSSDC ID: 1981-032A
Alternate Names
12385
Facts in Brief
Launch Date: 1981-04-07LaunchVehicle: Soyuz-ULaunch Site: Plesetsk,U.S.S.RMass: 6300.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and OtherMilitary
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http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-033A[07/11/2010 0:22:04]
Sunday, 07 November 2010
Description
Cosmos 1263 was a Soviet atmospheric research satellitelaunched from the Plesetsk cosmodrome aboard a Kosmos 11rocket. It was the 13th in a series of Vektor spacecraft.
Cosmos 1263
NSSDC ID: 1981-033A
Alternate Names
12388
Facts in Brief
Launch Date: 1981-04-09LaunchVehicle: Modified SS-5(SKean IRBM) plus UpperStageLaunch Site: Plesetsk,U.S.S.RMass: 550.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Earth Science
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http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-035A[07/11/2010 0:22:28]
Sunday, 07 November 2010
Description
Cosmos 1264 was a Soviet photo surveillance satellitelaunched from the Baikonur cosmodrome aboard a Soyuzrocket.
Cosmos 1264
NSSDC ID: 1981-035A
Alternate Names
12400
Facts in Brief
Launch Date: 1981-04-15LaunchVehicle: Soyuz-ULaunch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.RMass: 6300.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and OtherMilitary
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http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-036A[07/11/2010 0:23:51]
Sunday, 07 November 2010
Description
Cosmos 1265 was a Soviet photo surveillance satellitelaunched from the Plesetsk cosmodrome aboard a Soyuzrocket. The spacecraft was maneuverable.
Cosmos 1265
NSSDC ID: 1981-036A
Alternate Names
12402
Facts in Brief
Launch Date: 1981-04-16LaunchVehicle: Soyuz-ULaunch Site: Plesetsk,U.S.S.RMass: 6300.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and OtherMilitary
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http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-037A[07/11/2010 0:24:47]
Sunday, 07 November 2010
Description
Cosmos 1266 was a Soviet nuclear powered Radar OceanReconnaissance Satellite (RORSAT) launched from theBaikonur cosmodrome aboard a Tsyklon 2 rocket. TheRORSATs were designed to search the oceans for US Navytask forces and other shipping.
Cosmos 1266
NSSDC ID: 1981-037A
Alternate Names
12409
Facts in Brief
Launch Date: 1981-04-21LaunchVehicle: Tsiklon-2Launch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.RMass: 3800.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and OtherMilitary
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http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-039A[07/11/2010 0:25:19]
Sunday, 07 November 2010
Description
Cosmos 1267 was a Soviet spacecraft launched from theBaikonur cosmodrome aboard a Proton rocket. It was a TKSspace station ferry. It was flown unmanned to the Salyut 6space station after the Almaz military station program wascancelled. It docked with Salyut 6 on June 19 at 10:52 AM MTafter 57 days of autonomous flight. It deorbited and wasdestroyed with Salyut on July 29, 1982.
Cosmos 1267
NSSDC ID: 1981-039A
Alternate Names
12419
Facts in Brief
Launch Date: 1981-04-25Launch Vehicle: ProtonBooster Plus Upper StageLaunch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.RMass: 15100.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Engineering
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http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-040A[07/11/2010 0:31:38]
Sunday, 07 November 2010
Description
Cosmos 1268 was a Soviet photo surveillance satellitelaunched from the Baikonur cosmodrome aboard a Soyuzrocket. The spacecraft was maneuverable.
Cosmos 1268
NSSDC ID: 1981-040A
Alternate Names
12423
Facts in Brief
Launch Date: 1981-04-28LaunchVehicle: Soyuz-ULaunch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.RMass: 6300.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and OtherMilitary
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NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-041A[07/11/2010 0:32:23]
Sunday, 07 November 2010
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 1269
NSSDC ID: 1981-041A
Alternate Names
12442
Facts in Brief
Launch Date: 1981-05-07LaunchVehicle: Modified SS-5(SKean IRBM) plus UpperStageLaunch Site: Plesetsk,U.S.S.RMass: 750.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Communications
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http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-045A[07/11/2010 0:33:18]
Sunday, 07 November 2010
Description
Cosmos 1270 was a Soviet area survey photo reconnaissancesatellite launched from the Baikonur cosmodrome aboard aSoyuz-U rocket.
Yantar was the Soviet Union's second series of photoreconnaissance satellites, succeeding the Zenit series in theprimary film reconnaissance role. Yantars were identified in theWest as 'Fourth Generation Photo Reconnaissance Satellite'.In comparison with the Zenit series, the Yantar was equippedwith maneuvering engines to change the spacecrafts orbit,thereby providing more flexibility and surprise in photographingtargets of interest. In common with the Zenit it was equippedwith a large re-entry capsule which returned the camera andprimary electronics for re-use. However it also had two smallcapsules for return of film before return of the main capsule.The design lifetime of Yantar was 30 days, as opposed to the12 days of the Zenit. The SpK capsules would typically makeinterim film deliveries on the tenth and eighteenth days offlight.
Cosmos 1270
NSSDC ID: 1981-045A
Alternate Names
12461
Facts in Brief
Launch Date: 1981-05-18LaunchVehicle: Soyuz-ULaunch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.RMass: 6700.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and OtherMilitary
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http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-046A[07/11/2010 0:33:39]
Sunday, 07 November 2010
Description
Cosmos 1271 was a Soviet ELINT (Electronic and SignalsIntelligence) satellite launched from the Plesetsk cosmodrome.It replaced Cosmos 1077.
From 1965 to 1967 two dedicated ELINT systems were tested:the Tselina and the Navy's US. Both reached service, since theMinistry of Defense 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 1271
NSSDC ID: 1981-046A
Alternate Names
12464
Facts in Brief
Launch Date: 1981-05-19Launch Vehicle: Vostok2MLaunch Site: Plesetsk,U.S.S.RMass: 2500.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and OtherMilitary
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http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-047A[07/11/2010 0:34:04]
Sunday, 07 November 2010
Description
Cosmos 1272 was a Soviet photo surveillance satellitelaunched from the Baikonur cosmodrome aboard a Soyuzrocket.
Cosmos 1272
NSSDC ID: 1981-047A
Alternate Names
12466
Facts in Brief
Launch Date: 1981-05-21LaunchVehicle: Soyuz-ULaunch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.RMass: 6300.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and OtherMilitary
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http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-048A[07/11/2010 0:34:25]
Sunday, 07 November 2010
Description
Cosmos 1273 was a Soviet photo surveillance satellitelaunched from the Plesetsk cosmodrome aboard a Soyuzrocket. The spacecraft was maneuverable and also performedearth resources tasks. Investigation of the natural resources ofthe earth in the interests of various branches of the nationaleconomy of the USSR and international cooperation.
Cosmos 1273
NSSDC ID: 1981-048A
Alternate Names
12469
Facts in Brief
Launch Date: 1981-05-22LaunchVehicle: Soyuz-ULaunch Site: Plesetsk,U.S.S.RMass: 5900.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and OtherMilitary
AdditionalInformation
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NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-052A[07/11/2010 0:34:53]
Sunday, 07 November 2010
Description
Cosmos 1274 was a Soviet photo surveillance satellitelaunched from the Plesetsk cosmodrome aboard a Soyuzrocket. Returned film in two small SpK capsules during missionand in the main cabin at completion of the mission.
Cosmos 1274
NSSDC ID: 1981-052A
Alternate Names
12495
Facts in Brief
Launch Date: 1981-06-03LaunchVehicle: Soyuz-ULaunch Site: Plesetsk,U.S.S.RMass: 6700.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and OtherMilitary
AdditionalInformation
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NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-053A[07/11/2010 0:35:37]
Sunday, 07 November 2010
Description
Cosmos 1275 was part of a 6-satellite Soviet 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.
National Space Science Data Center Header
Cosmos 1275
NSSDC ID: 1981-053A
Alternate Names
12504
Facts in Brief
Launch Date: 1981-06-04LaunchVehicle: Modified SS-5(SKean IRBM) plus UpperStageLaunch Site: Plesetsk,U.S.S.RMass: 810.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Navigation & GlobalPositioning
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http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-055A[07/11/2010 0:37:59]
Sunday, 07 November 2010
Description
Cosmos 1276 was a Soviet photo sureillance satellite launchedfrom the Plesetsk cosmodrome aboard a Soyuz rocket. Thespacecraft was maneuverable and also performed earthresources tasks. Investigation of the natural resources of theearth in the interests of various branches of the nationaleconomy of the USSR and international cooperation.
Cosmos 1276
NSSDC ID: 1981-055A
Alternate Names
12517
Facts in Brief
Launch Date: 1981-06-16LaunchVehicle: Soyuz-ULaunch Site: Plesetsk,U.S.S.RMass: 5900.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and OtherMilitary
AdditionalInformation
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http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-056A[07/11/2010 0:38:26]
Sunday, 07 November 2010
Description
Cosmos 1277 was a Soviet photo surveillance satellitelaunched from the Baikonur cosmodrome aboard a Soyuzrocket.
Cosmos 1277
NSSDC ID: 1981-056A
Alternate Names
12520
Facts in Brief
Launch Date: 1981-06-17LaunchVehicle: Soyuz-ULaunch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.RMass: 6300.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and OtherMilitary
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http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-058A[07/11/2010 0:38:55]
Sunday, 07 November 2010
Description
Cosmos 1278 was a Soviet missile early warning satellitelaunched from the Plesetsk cosmodrome aboard a Molniyarocket. It was part of the Oko constellation and covered theplane 3 - 357 degree longitude of ascending node.
Cosmos 1278
NSSDC ID: 1981-058A
Alternate Names
12547
Facts in Brief
Launch Date: 1981-06-19LaunchVehicle: Molniya-MLaunch Site: Plesetsk,U.S.S.RMass: 1250.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and OtherMilitary
AdditionalInformation
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http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-062A[07/11/2010 0:39:19]
Sunday, 07 November 2010
Description
Cosmos 1279 was a Soviet photo surveillance satellitelaunched from the Baikonur cosmodrome aboard a Soyuzrocket. The spacecraft was maneuverable.
Cosmos 1279
NSSDC ID: 1981-062A
Alternate Names
12571
Facts in Brief
Launch Date: 1981-07-01LaunchVehicle: Soyuz-ULaunch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.RMass: 6300.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and OtherMilitary
AdditionalInformation
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NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-063A[07/11/2010 0:40:49]
Sunday, 07 November 2010
Description
Cosmos 1280 was a third generation, high resolution Sovietphoto surveillance satellite launched from the Plesetskcosmodrome aboard a Soyuz rocket. The spacecraft wasmaneuverable and also performed earth resources tasks.Investigation of the natural resources of the earth in theinterests of various branches of the national economy of theUSSR and international cooperation.
Cosmos 1280
NSSDC ID: 1981-063A
Alternate Names
12577
Facts in Brief
Launch Date: 1981-07-02LaunchVehicle: Soyuz-ULaunch Site: Plesetsk,U.S.S.RMass: 6300.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Earth Science
AdditionalInformation
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Experiments on Cosmos1280
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-064A[07/11/2010 0:41:32]
Sunday, 07 November 2010
Description
Cosmos 1281 was a Soviet photo surveillance satellitelaunched from the Plesetsk cosmodrome aboard a Soyuzrocket.
Cosmos 1281
NSSDC ID: 1981-064A
Alternate Names
12583
Facts in Brief
Launch Date: 1981-07-07LaunchVehicle: Soyuz-ULaunch Site: Plesetsk,U.S.S.RMass: 6300.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and OtherMilitary
AdditionalInformation
Launch/Orbitalinformation for Cosmos1281
Experiments on Cosmos1281
Data collections fromCosmos 1281
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-066A[07/11/2010 0:42:45]
Sunday, 07 November 2010
Description
Cosmos 1282 was a Soviet photo surveillance satellitelaunched from the Plesetsk cosmodrome aboard a Soyuzrocket. Returned film in two small SpK capsules during missionand in the main cabin at completion of the mission.
Cosmos 1282
NSSDC ID: 1981-066A
Alternate Names
12588
Facts in Brief
Launch Date: 1981-07-15LaunchVehicle: Soyuz-ULaunch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.RMass: 6700.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and OtherMilitary
AdditionalInformation
Launch/Orbitalinformation for Cosmos1282
Experiments on Cosmos1282
Data collections fromCosmos 1282
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-067A[07/11/2010 0:43:12]
Sunday, 07 November 2010
Description
Cosmos 1283 was a third generation, high resolution Sovietphoto surveillance satellite launched from the Plesetskcosmodrome aboard a Soyuz rocket. The spacecraft wasmaneuverable and also performed earth resources tasks.Investigation of the natural resources of the earth in theinterests of various branches of the national economy of theUSSR and international cooperation.
Cosmos 1283
NSSDC ID: 1981-067A
Alternate Names
12598
Facts in Brief
Launch Date: 1981-07-17LaunchVehicle: Soyuz-ULaunch Site: Plesetsk,U.S.S.RMass: 6300.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and OtherMilitary
AdditionalInformation
Launch/Orbitalinformation for Cosmos1283
Experiments on Cosmos1283
Data collections fromCosmos 1283
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-068A[07/11/2010 0:43:33]
Sunday, 07 November 2010
Description
Cosmos 1284 was a third generation, medium resolutionSoviet photo surveillance satellite launched from the Plesetskcosmodrome aboard a Soyuz rocket. The spacecraftperformed earth resources tasks. Investigation of the naturalresources of the earth in the interests of various branches ofthe national economy of the USSR and internationalcooperation.
Cosmos 1284
NSSDC ID: 1981-068A
Alternate Names
12614
Facts in Brief
Launch Date: 1981-07-29LaunchVehicle: Soyuz-ULaunch Site: Plesetsk,U.S.S.RMass: 6300.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and OtherMilitary
AdditionalInformation
Launch/Orbitalinformation for Cosmos1284
Experiments on Cosmos1284
Data collections fromCosmos 1284
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-071A[07/11/2010 0:43:57]
Sunday, 07 November 2010
Description
Cosmos 1285 was a Soviet missile early warning satellitelaunched from the Plesetsk cosmodrome aboard a Molniyarocket. It replaced Cosmos 1261 in the Oko constellation ofsatellites and covered the plane 6 - 116 degree longitude planeof ascending node.
Cosmos 1285
NSSDC ID: 1981-071A
Alternate Names
12627
Facts in Brief
Launch Date: 1981-08-04LaunchVehicle: Molniya-MLaunch Site: Plesetsk,U.S.S.RMass: 1250.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and OtherMilitary
AdditionalInformation
Launch/Orbitalinformation for Cosmos1285
Experiments on Cosmos1285
Data collections fromCosmos 1285
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-072A[07/11/2010 0:44:49]
Sunday, 07 November 2010
Description
Cosmos 1286 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 1286
NSSDC ID: 1981-072A
Alternate Names
12631
Facts in Brief
Launch Date: 1981-08-04LaunchVehicle: Modified SS-9(SCARP) or SS-13(SCRAG) with Orbital andManeuverableLaunch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.RMass: 3000.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and OtherMilitary
AdditionalInformation
Launch/Orbitalinformation for Cosmos1286
Experiments on Cosmos1286
Data collections fromCosmos 1286
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed Grayzeck
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-074A[07/11/2010 0:45:24]
Sunday, 07 November 2010
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 1287
NSSDC ID: 1981-074A
Alternate Names
12636
Facts in Brief
Launch Date: 1981-08-06LaunchVehicle: Modified SS-5(SKean IRBM) plus UpperStageLaunch Site: Plesetsk,U.S.S.RMass: 40.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Communications
AdditionalInformation
Launch/Orbitalinformation for Cosmos1287
Experiments on Cosmos1287
Data collections fromCosmos 1287
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-074B[07/11/2010 0:45:55]
Sunday, 07 November 2010
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 1288
NSSDC ID: 1981-074B
Alternate Names
12637
Facts in Brief
Launch Date: 1981-08-06LaunchVehicle: Modified SS-5(SKean IRBM) plus UpperStageLaunch Site: Plesetsk,U.S.S.RMass: 40.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Communications
AdditionalInformation
Launch/Orbitalinformation for Cosmos1288
Experiments on Cosmos1288
Data collections fromCosmos 1288
Questions or commentsabout this spacecraft canbe directed to: CoordinatedRequest and User SupportOffice.
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-074C[07/11/2010 0:46:25]
Sunday, 07 November 2010
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 1289
NSSDC ID: 1981-074C
Alternate Names
12638
Facts in Brief
Launch Date: 1981-08-06LaunchVehicle: Modified SS-5(SKean IRBM) plus UpperStageLaunch Site: Plesetsk,U.S.S.RMass: 40.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Communications
AdditionalInformation
Launch/Orbitalinformation for Cosmos1289
Experiments on Cosmos1289
Data collections fromCosmos 1289
Questions or commentsabout this spacecraft canbe directed to: CoordinatedRequest and User SupportOffice.
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-074D[07/11/2010 0:46:46]
Sunday, 07 November 2010
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 1290
NSSDC ID: 1981-074D
Alternate Names
12639
Facts in Brief
Launch Date: 1981-08-06LaunchVehicle: Modified SS-5(SKean IRBM) plus UpperStageLaunch Site: Plesetsk,U.S.S.RMass: 40.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Communications
AdditionalInformation
Launch/Orbitalinformation for Cosmos1290
Experiments on Cosmos1290
Data collections fromCosmos 1290
Questions or commentsabout this spacecraft canbe directed to: CoordinatedRequest and User SupportOffice.
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-074E[07/11/2010 0:47:18]
Sunday, 07 November 2010
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 1291
NSSDC ID: 1981-074E
Alternate Names
12640
Facts in Brief
Launch Date: 1981-08-06LaunchVehicle: Modified SS-5(SKean IRBM) plus UpperStageLaunch Site: Plesetsk,U.S.S.RMass: 40.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Communications
AdditionalInformation
Launch/Orbitalinformation for Cosmos1291
Experiments on Cosmos1291
Data collections fromCosmos 1291
Questions or commentsabout this spacecraft canbe directed to: CoordinatedRequest and User SupportOffice.
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-074F[07/11/2010 0:47:49]
Sunday, 07 November 2010
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 1292
NSSDC ID: 1981-074F
Alternate Names
12641
Facts in Brief
Launch Date: 1981-08-06LaunchVehicle: Modified SS-5(SKean IRBM) plus UpperStageLaunch Site: Plesetsk,U.S.S.RMass: 40.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Communications
AdditionalInformation
Launch/Orbitalinformation for Cosmos1292
Experiments on Cosmos1292
Data collections fromCosmos 1292
Questions or commentsabout this spacecraft canbe directed to: CoordinatedRequest and User SupportOffice.
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Spacecraft
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-074G[07/11/2010 0:48:18]
Sunday, 07 November 2010
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 1293
NSSDC ID: 1981-074G
Alternate Names
12642
Facts in Brief
Launch Date: 1981-08-06LaunchVehicle: Modified SS-5(SKean IRBM) plus UpperStageLaunch Site: Plesetsk,U.S.S.RMass: 40.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Communications
AdditionalInformation
Launch/Orbitalinformation for Cosmos1293
Experiments on Cosmos1293
Data collections fromCosmos 1293
Questions or commentsabout this spacecraft canbe directed to: CoordinatedRequest and User SupportOffice.
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Spacecraft
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-074H[07/11/2010 0:48:48]
Sunday, 07 November 2010
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 1294
NSSDC ID: 1981-074H
Alternate Names
12643
Facts in Brief
Launch Date: 1981-08-06LaunchVehicle: Modified SS-5(SKean IRBM) plus UpperStageLaunch Site: Plesetsk,U.S.S.RMass: 40.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Communications
AdditionalInformation
Launch/Orbitalinformation for Cosmos1294
Experiments on Cosmos1294
Data collections fromCosmos 1294
Questions or commentsabout this spacecraft canbe directed to: CoordinatedRequest and User SupportOffice.
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Spacecraft
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-077A[07/11/2010 0:49:54]
Sunday, 07 November 2010
Description
Cosmos 1295 was part of a 6-satellite Soviet 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 1295
NSSDC ID: 1981-077A
Alternate Names
12681
Facts in Brief
Launch Date: 1981-08-12LaunchVehicle: Modified SS-5(SKean IRBM) plus UpperStageLaunch Site: Plesetsk,U.S.S.RMass: 700.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Navigation & GlobalPositioning
AdditionalInformation
Launch/Orbitalinformation for Cosmos1295
Experiments on Cosmos1295
Data collections fromCosmos 1295
Questions or commentsabout this spacecraft canbe directed to: CoordinatedRequest and User SupportOffice.
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-078A[07/11/2010 0:51:24]
Sunday, 07 November 2010
Description
Cosmos 1296 was a Soviet photo surveillance satellitelaunched from the Plesetsk cosmodrome aboard a Soyuzrocket. Returned film in two small SpK capsules during missionand in the main cabin at completion of the mission.
Cosmos 1296
NSSDC ID: 1981-078A
Alternate Names
12687
Facts in Brief
Launch Date: 1981-08-13LaunchVehicle: Soyuz-ULaunch Site: Plesetsk,U.S.S.RMass: 6700.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and OtherMilitary
AdditionalInformation
Launch/Orbitalinformation for Cosmos1296
Experiments on Cosmos1296
Data collections fromCosmos 1296
Questions or commentsabout this spacecraft canbe directed to: CoordinatedRequest and User SupportOffice.
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Spacecraft
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-079A[07/11/2010 0:53:13]
Sunday, 07 November 2010
Description
Cosmos 1297 was a Soviet photo surveillance satellitelaunched from the Plesetsk cosmodrome aboard a Soyuzrocket. The spacecraft was maneuverable.
Cosmos 1297
NSSDC ID: 1981-079A
Alternate Names
12716
Facts in Brief
Launch Date: 1981-08-18LaunchVehicle: Soyuz-ULaunch Site: Plesetsk,U.S.S.RMass: 6300.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and OtherMilitary
AdditionalInformation
Launch/Orbitalinformation for Cosmos1297
Experiments on Cosmos1297
Data collections fromCosmos 1297
Questions or commentsabout this spacecraft canbe directed to: CoordinatedRequest and User SupportOffice.
NSSDC MasterCatalog Search
Spacecraft
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New/Updated Data
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-080A[07/11/2010 0:54:13]
Sunday, 07 November 2010
Description
Cosmos 1218 was a Soviet high resolution photo surveillancesatellite launched from the Baikonur cosmodrome aboard aSoyuz rocket. It returned film in two small SpK capsules duringthe mission and with the main capsule at completion of themission.
Cosmos 1298
NSSDC ID: 1981-080A
Alternate Names
12776
Facts in Brief
Launch Date: 1981-08-21LaunchVehicle: Soyuz-ULaunch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.RMass: 6700.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and OtherMilitary
AdditionalInformation
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http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-081A[07/11/2010 0:54:58]
Sunday, 07 November 2010
Description
Cosmos 1299 was a Soviet nuclear powered Radar OceanReconnaissance Satellite (RORSAT) launched from theBaikonur cosmodrome aboard a Tsyklon 2 rocket. TheRORSATs were designed to search the oceans for US Navytask forces and other shipping.
Cosmos 1299
NSSDC ID: 1981-081A
Alternate Names
12783
Facts in Brief
Launch Date: 1981-08-24LaunchVehicle: Tsiklon-2Launch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.RMass: 3800.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and OtherMilitary
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http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-082A[07/11/2010 0:55:55]
Sunday, 07 November 2010
Description
Cosmos 1300 was a Soviet 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 1300
NSSDC ID: 1981-082A
Alternate Names
12785
Facts in Brief
Launch Date: 1981-08-24LaunchVehicle: Tsiklon-3Launch Site: Plesetsk,U.S.S.R
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and OtherMilitary
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http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-083A[07/11/2010 0:56:24]
Sunday, 07 November 2010
Description
Cosmos 1301 was a third generation, high resolution Sovietphoto surveillance satellite launched from the Plesetskcosmodrome aboard a Soyuz rocket. The spacecraft wasmaneuverable and also performed earth resources tasks.Investigation of the natural resources of the earth in theinterests of various branches of the national economy of theUSSR and international cooperation.
Cosmos 1301
NSSDC ID: 1981-083A
Alternate Names
12788
Facts in Brief
Launch Date: 1981-08-27LaunchVehicle: Soyuz-ULaunch Site: Plesetsk,U.S.S.RMass: 6300.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and OtherMilitary
AdditionalInformation
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http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-084A[07/11/2010 0:56:53]
Sunday, 07 November 2010
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 1302 replaced Cosmos 1269.
Cosmos 1302
NSSDC ID: 1981-084A
Alternate Names
12791
Facts in Brief
Launch Date: 1981-08-28LaunchVehicle: Modified SS-5(SKean IRBM) plus UpperStageLaunch Site: Plesetsk,U.S.S.RMass: 750.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Communications
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http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-086A[07/11/2010 0:57:28]
Sunday, 07 November 2010
Description
Cosmos 1303 was a Soviet photo surveillance satellitelaunched from the Baikonur cosmodrome aboard a Soyuzrocket.
Cosmos 1303
NSSDC ID: 1981-086A
Alternate Names
12801
Facts in Brief
Launch Date: 1981-09-04LaunchVehicle: Soyuz-ULaunch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.RMass: 6300.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and OtherMilitary
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http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-087A[07/11/2010 0:58:05]
Sunday, 07 November 2010
Description
Cosmos 1304 was part of a 6-satellite Soviet 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 1304
NSSDC ID: 1981-087A
Alternate Names
12803
Facts in Brief
Launch Date: 1981-09-04LaunchVehicle: Modified SS-5(SKean IRBM) plus UpperStageLaunch Site: Plesetsk,U.S.S.RMass: 810.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Navigation & GlobalPositioning
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NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-088A[07/11/2010 0:58:45]
Sunday, 07 November 2010
Description
Cosmos 1305
NSSDC ID: 1981-088A
Alternate Names
12818
Facts in Brief
Launch Date: 1981-09-11LaunchVehicle: Molniya-MLaunch Site: Plesetsk,U.S.S.RMass: 1000.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Communications
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http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-089A[07/11/2010 0:59:21]
Sunday, 07 November 2010
Description
Cosmos 1306 was a Soviet military naval reconnaisance,ocean monitoring satellite launched from the Baikonurcosmodrome aboard a Tsyklon 2 rocket. This naval forcesmonitoring spacecraft was used to determine the position ofenemy naval forces through detection and triangulation of theirelectromagnetic emissions (radio, radar, etc).
Cosmos 1306
NSSDC ID: 1981-089A
Alternate Names
12828
Facts in Brief
Launch Date: 1981-09-14LaunchVehicle: Modified SS-9(SCARP) or SS-13(SCRAG) with Orbital andManeuverableLaunch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.RMass: 3000.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and OtherMilitary
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http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-090A[07/11/2010 0:59:48]
Sunday, 07 November 2010
Description
Cosmos 1307 was a Soviet photo surveillance satellitelaunched from the Plesetsk cosmodrome aboard a Soyuzrocket.
Cosmos 1307
NSSDC ID: 1981-090A
Alternate Names
12830
Facts in Brief
Launch Date: 1981-09-15LaunchVehicle: Soyuz-ULaunch Site: Plesetsk,U.S.S.RMass: 6300.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and OtherMilitary
AdditionalInformation
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http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-091A[09/11/2010 23:56:51]
Wednesday, 10 November 2010
Description
Cosmos 1308 was part of a 6-satellite Soviet 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 1308
NSSDC ID: 1981-091A
Alternate Names
12835
Facts in Brief
Launch Date: 1981-09-18LaunchVehicle: Modified SS-5(SKean IRBM) plus UpperStageLaunch Site: Plesetsk,U.S.S.RMass: 7000.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Navigation & GlobalPositioning
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NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-092A[09/11/2010 23:58:56]
Wednesday, 10 November 2010
Description
Cosmos 1309 was a Soviet photo surveillance satellitelaunched from the Plesetsk cosmodrome aboard a Soyuzrocket. The spacecraft performed mapping, geodesy.
Cosmos 1309
NSSDC ID: 1981-092A
Alternate Names
12837
Facts in Brief
Launch Date: 1981-09-18LaunchVehicle: Soyuz-ULaunch Site: Plesetsk,U.S.S.RMass: 5700.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and OtherMilitary
AdditionalInformation
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Experiments on Cosmos1309
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NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-095A[10/11/2010 0:00:28]
Wednesday, 10 November 2010
Description
Cosmos 1310 was a Soviet atmospheric research satellitelaunched from the Plesetsk cosmodrome aboard a Kosmos 11rocket. It was the 14th in a series of Vektor spacecraft.
Cosmos 1310
NSSDC ID: 1981-095A
Alternate Names
12852
Facts in Brief
Launch Date: 1981-09-23LaunchVehicle: Modified SS-5(SKean IRBM) plus UpperStageLaunch Site: Plesetsk,U.S.S.R
Funding Agency
Unknown (U.S.S.R)
Discipline
Earth Science
AdditionalInformation
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http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-097A[10/11/2010 0:00:56]
Wednesday, 10 November 2010
Description
From 1969 KB Yuzhnoye built the Lira targets for exercise andtest of PVO air defence and space tracking systems. Thesecond generation consisted of Taifun-1 and Taifun-2satellites, which differed in the type of equipment installed.Taifun-1 would release up to 25 Romb sub-satellites, whileTaifun-2 did not. In 1972 KB-3 under B E Khimrov, with the co-operation of assisting organisations and the Ministry ofDefence, completed the draft project. The first Taifun-1 wascompleted in 1974, and flight trials were conducted in thesecond half of the 1970's using Kosmos-3M launch vehiclesfrom Plesetsk and Kapustin Yar. The heads of the State TrialsCommission were B N Karpov, N N Zhukov, and B G Zudin.Taifun-1 normally released 25 Romb subsatellites into an orbitof 300 to 500 km altitude, at inclinations of 50.7 degrees (fromKapustin Yar) and 65.9 74, or 82.9 degrees (from Plesetsk).Two unique missions in 1989-1990 were put into 180 km x1550 km orbits at 65.8 degrees. With this higher apogee thepayload was reduced to 10 Romb subsatellites. Vektorsatellites were spherical in shape, about 2 m in diameter, thesurface covered with solar cells and equipped with fourantennae.
Cosmos 1311
NSSDC ID: 1981-097A
Alternate Names
12871
Facts in Brief
Launch Date: 1981-09-28LaunchVehicle: Modified SS-5(SKean IRBM) plus UpperStageLaunch Site: Plesetsk,U.S.S.R
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and OtherMilitary
AdditionalInformation
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Experiments on Cosmos1311
Data collections fromCosmos 1311
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NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-098A[10/11/2010 0:01:17]
Wednesday, 10 November 2010
Description
Cosmos 1312 was a Soviet geodetic satellite launched fromthe Plesetsk cosmodrome aboard a Tsyklon 3 rocket. Itprovided five ways for determining satellite position:
1. Doppler system working at 150 and 400 MHz and providing3 cm accuracy 2. High intensity lights flashing 3 times persecond, allowing precise location by ground observatories 3.Radio transponder working at 5.7/3.4 GHz and providing 5 maccuracy 4. Laser reflector providing 1.5 m accuracy 5. Radarreflector working at 9.4 GHz providing 5 m altitude accuracy.
Cosmos 1312
NSSDC ID: 1981-098A
Alternate Names
12879
Facts in Brief
Launch Date: 1981-09-30LaunchVehicle: Tsiklon-3Launch Site: Plesetsk,U.S.S.RMass: 1500.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Earth Science
AdditionalInformation
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Experiments on Cosmos1312
Data collections fromCosmos 1312
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NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-099A[10/11/2010 0:01:38]
Wednesday, 10 November 2010
Description
Cosmos 1313 was a Soviet photo surveillance satellitelaunched from the Baikonur cosmodrome aboard a Soyuzrocket. The spacecraft was maneuverable.
Cosmos 1313
NSSDC ID: 1981-099A
Alternate Names
12881
Facts in Brief
Launch Date: 1981-10-01LaunchVehicle: Soyuz-ULaunch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.RMass: 6300.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and OtherMilitary
AdditionalInformation
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http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-101A[10/11/2010 0:01:59]
Wednesday, 10 November 2010
Description
Cosmos 1314 was a Soviet photo surveillance satellitelaunched from the Plesetsk cosmodrome aboard a Soyuzrocket. The spacecraft was maneuverable and also performedearth resources tasks. Investigation of the natural resources ofthe earth in the interests of various branches of the nationaleconomy of the USSR and international cooperation.
Cosmos 1314
NSSDC ID: 1981-101A
Alternate Names
12895
Facts in Brief
Launch Date: 1981-10-09LaunchVehicle: Soyuz-ULaunch Site: Plesetsk,U.S.S.RMass: 6300.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and OtherMilitary
AdditionalInformation
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Experiments on Cosmos1314
Data collections fromCosmos 1314
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NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-103A[10/11/2010 0:02:31]
Wednesday, 10 November 2010
Description
Cosmos 1315 was a Soviet 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 Defense 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 1315
NSSDC ID: 1981-103A
Alternate Names
12903
Facts in Brief
Launch Date: 1981-10-14Launch Vehicle: Vostok2MLaunch Site: Plesetsk,U.S.S.RMass: 2500.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and OtherMilitary
AdditionalInformation
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Experiments on Cosmos1315
Data collections fromCosmos 1315
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NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-104A[10/11/2010 0:03:08]
Wednesday, 10 November 2010
Description
Cosmos 1316 was a Soviet photo surveillance satellitelaunched from the Baikonur cosmodrome aboard a Soyuzrocket. The spacecraft was maneuverable.
Cosmos 1316
NSSDC ID: 1981-104A
Alternate Names
12905
Facts in Brief
Launch Date: 1981-10-15LaunchVehicle: Soyuz-ULaunch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.RMass: 6300.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and OtherMilitary
AdditionalInformation
Launch/Orbitalinformation for Cosmos1316
Experiments on Cosmos1316
Data collections fromCosmos 1316
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NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-108A[10/11/2010 0:03:44]
Wednesday, 10 November 2010
Description
Cosmos 1317 was a Soviet missile early warning satellitelaunched from the Plesetsk cosmodrome aboard a Molniyarocket. It was part of the Oko constellation of satellites andcovered the plane 8 - 196 degree longitude of ascending node.
Cosmos 1317
NSSDC ID: 1981-108A
Alternate Names
12933
Facts in Brief
Launch Date: 1981-10-31LaunchVehicle: Molniya-MLaunch Site: Plesetsk,U.S.S.RMass: 1250.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and OtherMilitary
AdditionalInformation
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Data collections fromCosmos 1317
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
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http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-109A[10/11/2010 0:04:25]
Wednesday, 10 November 2010
Description
Cosmos 1318 was a Soviet photo surveillance satellitelaunched from the Plesetsk cosmodrome aboard a Soyuzrocket. Returned film in two small SpK capsules during missionand in the main cabin at completion of the mission.
Cosmos 1318
NSSDC ID: 1981-109A
Alternate Names
12936
Facts in Brief
Launch Date: 1981-11-03LaunchVehicle: Soyuz-ULaunch Site: Plesetsk,U.S.S.RMass: 6700.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and OtherMilitary
AdditionalInformation
Launch/Orbitalinformation for Cosmos1318
Experiments on Cosmos1318
Data collections fromCosmos 1318
Questions or commentsabout this spacecraft canbe directed to: CoordinatedRequest and User SupportOffice.
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-112A[10/11/2010 0:04:45]
Wednesday, 10 November 2010
Description
Cosmos 1319 was a Soviet photo surveillance satellitelaunched from the Baikonur cosmodrome aboard a Soyuzrocket.
Cosmos 1319
NSSDC ID: 1981-112A
Alternate Names
12954
Facts in Brief
Launch Date: 1981-11-13LaunchVehicle: Soyuz-ULaunch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.RMass: 6300.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and OtherMilitary
AdditionalInformation
Launch/Orbitalinformation for Cosmos1319
Experiments on Cosmos1319
Data collections fromCosmos 1319
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-116A[10/11/2010 0:05:14]
Wednesday, 10 November 2010
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 1320
NSSDC ID: 1981-116A
Alternate Names
12975
Facts in Brief
Launch Date: 1981-11-28LaunchVehicle: Modified SS-5(SKean IRBM) plus UpperStageLaunch Site: Plesetsk,U.S.S.RMass: 40.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Communications
AdditionalInformation
Launch/Orbitalinformation for Cosmos1320
Experiments on Cosmos1320
Data collections fromCosmos 1320
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-116B[10/11/2010 0:06:38]
Wednesday, 10 November 2010
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 1321
NSSDC ID: 1981-116B
Alternate Names
12976
Facts in Brief
Launch Date: 1981-11-28LaunchVehicle: Modified SS-5(SKean IRBM) plus UpperStageLaunch Site: Plesetsk,U.S.S.RMass: 40.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Communications
AdditionalInformation
Launch/Orbitalinformation for Cosmos1321
Experiments on Cosmos1321
Data collections fromCosmos 1321
Questions or commentsabout this spacecraft canbe directed to: CoordinatedRequest and User SupportOffice.
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-116C[10/11/2010 0:07:38]
Wednesday, 10 November 2010
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 1322
NSSDC ID: 1981-116C
Alternate Names
12977
Facts in Brief
Launch Date: 1981-11-28LaunchVehicle: Modified SS-5(SKean IRBM) plus UpperStageLaunch Site: Plesetsk,U.S.S.RMass: 40.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Communications
AdditionalInformation
Launch/Orbitalinformation for Cosmos1322
Experiments on Cosmos1322
Data collections fromCosmos 1322
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-116D[10/11/2010 0:08:09]
Wednesday, 10 November 2010
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 1323
NSSDC ID: 1981-116D
Alternate Names
12978
Facts in Brief
Launch Date: 1981-11-28LaunchVehicle: Modified SS-5(SKean IRBM) plus UpperStageLaunch Site: Plesetsk,U.S.S.RMass: 40.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Communications
AdditionalInformation
Launch/Orbitalinformation for Cosmos1323
Experiments on Cosmos1323
Data collections fromCosmos 1323
Questions or commentsabout this spacecraft canbe directed to: CoordinatedRequest and User SupportOffice.
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-116E[10/11/2010 0:08:53]
Wednesday, 10 November 2010
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 1324
NSSDC ID: 1981-116E
Alternate Names
12979
Facts in Brief
Launch Date: 1981-11-28LaunchVehicle: Modified SS-5(SKean IRBM) plus UpperStageLaunch Site: Plesetsk,U.S.S.RMass: 40.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Communications
AdditionalInformation
Launch/Orbitalinformation for Cosmos1324
Experiments on Cosmos1324
Data collections fromCosmos 1324
Questions or commentsabout this spacecraft canbe directed to: CoordinatedRequest and User SupportOffice.
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-116F[10/11/2010 0:09:51]
Wednesday, 10 November 2010
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 1325
NSSDC ID: 1981-116F
Alternate Names
12980
Facts in Brief
Launch Date: 1981-11-28LaunchVehicle: Modified SS-5(SKean IRBM) plus UpperStageLaunch Site: Plesetsk,U.S.S.RMass: 40.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Communications
AdditionalInformation
Launch/Orbitalinformation for Cosmos1325
Experiments on Cosmos1325
Data collections fromCosmos 1325
Questions or commentsabout this spacecraft canbe directed to: CoordinatedRequest and User SupportOffice.
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-116G[10/11/2010 0:10:41]
Wednesday, 10 November 2010
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 1326
NSSDC ID: 1981-116G
Alternate Names
12981
Facts in Brief
Launch Date: 1981-11-28LaunchVehicle: Modified SS-5(SKean IRBM) plus UpperStageLaunch Site: Plesetsk,U.S.S.RMass: 40.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Communications
AdditionalInformation
Launch/Orbitalinformation for Cosmos1326
Experiments on Cosmos1326
Data collections fromCosmos 1326
Questions or commentsabout this spacecraft canbe directed to: CoordinatedRequest and User SupportOffice.
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-116H[10/11/2010 0:12:02]
Wednesday, 10 November 2010
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 1327
NSSDC ID: 1981-116H
Alternate Names
12982
Facts in Brief
Launch Date: 1981-11-28LaunchVehicle: Modified SS-5(SKean IRBM) plus UpperStageLaunch Site: Plesetsk,U.S.S.RMass: 40.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Communications
AdditionalInformation
Launch/Orbitalinformation for Cosmos1327
Experiments on Cosmos1327
Data collections fromCosmos 1327
Questions or commentsabout this spacecraft canbe directed to: CoordinatedRequest and User SupportOffice.
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-117A[10/11/2010 0:12:55]
Wednesday, 10 November 2010
Description
Cosmos 1328 was a Soviet 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 1328
NSSDC ID: 1981-117A
Alternate Names
12987
Facts in Brief
Launch Date: 1981-12-03LaunchVehicle: Tsiklon-3Launch Site: Plesetsk,U.S.S.R
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and OtherMilitary
AdditionalInformation
Launch/Orbitalinformation for Cosmos1328
Experiments on Cosmos1328
Data collections fromCosmos 1328
Questions or commentsabout this spacecraft canbe directed to: CoordinatedRequest and User SupportOffice.
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-118A[10/11/2010 0:13:40]
Wednesday, 10 November 2010
Description
Cosmos 1329 was a Soviet photo surveillance satellitelaunched from the Baikonur cosmodrome aboard a Soyuzrocket. The spacecraft was maneuverable.
Cosmos 1329
NSSDC ID: 1981-118A
Alternate Names
12989
Facts in Brief
Launch Date: 1981-12-04LaunchVehicle: Soyuz-ULaunch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.RMass: 6300.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and OtherMilitary
AdditionalInformation
Launch/Orbitalinformation for Cosmos1329
Experiments on Cosmos1329
Data collections fromCosmos 1329
Questions or commentsabout this spacecraft canbe directed to: CoordinatedRequest and User SupportOffice.
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-121A[10/11/2010 0:14:42]
Wednesday, 10 November 2010
Description
Cosmos 1330 was a Soviet photo surveillance satellitelaunched from the Baikonur cosmodrome aboard a Soyuzrocket. Returned film in two small SpK capsules during missionand in the main cabin at completion of the mission.
Cosmos 1330
NSSDC ID: 1981-121A
Alternate Names
13008
Facts in Brief
Launch Date: 1981-12-19LaunchVehicle: Soyuz-ULaunch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.RMass: 6700.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and OtherMilitary
AdditionalInformation
Launch/Orbitalinformation for Cosmos1330
Experiments on Cosmos1330
Data collections fromCosmos 1330
Questions or commentsabout this spacecraft canbe directed to: CoordinatedRequest and User SupportOffice.
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-025A[10/11/2010 0:15:38]
Wednesday, 10 November 2010
Description
DSP F9 was part of the oldest segments of North America'searly warning system. These Defense Support Systemsatellites were the space-based segment of a 2-tiered ballisticmissile launch detection and warning system. Orbiting 23,000mile above Earth, these satellites provided the first look atpotentially hostile ballistic missiles launched from land or sea,anywhere in the world, in near-real time. For tactical missilewarning, satellite data could be transmitted directly to thetheater commander via the Tactical Event System. DSPsensors also detected nuclear detonations. The speed andaccuracy have greatly reduced the potential for surprise attackand is vital to effective deterrance to war. The DSP sytem hasone satellite watching the eastern hemisphere and twospacecraft watching the western hemisphere for missilelaunches. Since there was less time associated with asubmarine launch from a Soviet boat at the US mainland,these was a great concern that this type of missile must bedetected.
The satellite's infrared sensors detected and tracked exhaustheat generated by balistic missiles. The data were thenrelayed almost instantaneously to USSPACECOM MissileWarning Center in the Cheyenne Mountain Complex. DSPsatellites were used during the Persian Gulf War to detect IragiScud missile launches.
DSP F9
NSSDC ID: 1981-025A
Alternate Names
12339
Facts in Brief
Launch Date: 1981-03-16Launch Vehicle: TitanIII-CLaunch Site: CapeCanaveral, United StatesMass: 1670.0 kg
Funding Agency
Department of Defense-Department of the AirForce (United States)
Disciplines
Surveillance and OtherMilitary
Space Physics
AdditionalInformation
Launch/Orbitalinformation for DSP F9
Experiments on DSP F9
Data collections from DSPF9
Questions or commentsabout this spacecraft canbe directed to: Dr. H. KentHills.
Personnel
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DSP F9
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-025A[10/11/2010 0:15:38]
Dr. W. Doyle Evans Project Scientist Los Alamos National Laboratory
Project Manager US Air Force Space Division
Image courtesy of the USAF Defense Support Program.
+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-070A[10/11/2010 0:16:51]
Wednesday, 10 November 2010
Description
The Dynamics Explorer (DE) mission's general objective is toinvestigate the strong interactive processes coupling the hot,tenuous, convecting plasmas of the magnetosphere and thecooler, denser plasmas and gases corotating in the earth'sionosphere, upper atmosphere, and plasmasphere. Twosatellites, DE 1 and DE 2, were launched together and wereplaced in polar coplanar orbits, permitting simultaneousmeasurements at high and low altitudes in the same field-lineregion. The DE 1 spacecraft (high-altitude mission) uses anelliptical orbit selected to allow (1) measurements extendingfrom the hot magnetospheric plasma through the plasmasphereto the cool ionosphere; (2) global auroral imaging, wavemeasurements in the heart of the magnetosphere, andcrossing of auroral field lines at several earth radii; and (3)measurements for significant periods along a magnetic fieldflux tube. The spacecraft approximated a short polygon 137 cmin diameter and 115 cm high. The antennas in the X-Y planemeasured 200-m tip-to-tip, and on the Z-axis are 9 meters tip-to-tip. Two six-meter booms are provided for remotemeasurements. Power is supplied by a solar cell array,mounted on the side and end panels. The spacecraft is spinstabilized, with the spin axis normal to the orbital plane, andthe spin rate at ten plus or minus 0.1 rpm. A pulse codemodulation (PCM) telemetry data system is used that operatesin real time or in a tape-recorder mode. Data have beenacquired on a science-problem-oriented basis, with closelycoordinated operations of the various instruments, bothsatellites, and supportive experiments. Data acquired from theinstruments are temporarily stored on tape recorders beforetransmission at an 8:1 playback-to-record ratio. Additionaloperational flexibility allows a playback-to-record ratio of 4:1.The primary data rate is 16,384 bits per second. Sincecommands are stored in a command memory unit, spacecraftoperations are not real time, except for the transmission of thewideband analog data from the Plasma Wave Instrument (81-070A-02). On October 22, 1990 science operations wereterminated. On February 28, 1991 Dynamics Explorer 1operations were offically terminated. Additional details may befound in R. A. Hoffman et al., Space Sci. Instrum., v. 5, n. 4, p.349, 1981.
Dynamics Explorer 1
NSSDC ID: 1981-070A
Alternate Names
DE-A
DE 1
Dynamics Explorer-A
Explorer 62
12624
Facts in Brief
Launch Date: 1981-08-03Launch Vehicle: DeltaLaunchSite: Vandenberg AFB,United StatesMass: 424.0 kgNominal Power: 86.0 W
Funding Agency
NASA-Office of SpaceScience Applications(United States)
Discipline
Space Physics
AdditionalInformation
Launch/Orbitalinformation for DynamicsExplorer 1
PDMP information forDynamics Explorer 1
Telecommunicationsinformation for DynamicsExplorer 1
Experiments on DynamicsExplorer 1
Data collections fromDynamics Explorer 1
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NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-070A[10/11/2010 0:16:51]
Questions or commentsabout this spacecraft canbe directed to: Dr. Dieter K.Bilitza.
Personnel
Name Role Original Affiliation E-mail
Dr. Michael A.Calabrese
ProgramManager
NASA Headquarters [email protected]
Mr. Paul J.Pashby
ProjectManager
NASA Goddard SpaceFlight Center
Dr. Robert A.Hoffman
ProjectScientist
NASA Goddard SpaceFlight Center
Dr. Mary M.Mellott
ProgramScientist
NASA Headquarters [email protected]
Other DE 1 Data/Information at NSSDC
CDAWeb (Browse and retrieve DE in CDAW)
Related Data/Information at NSSDC
Dynamics Explorer 2
Other Sources of DE 1 Data/Information
General DE page (Los Alamos)
PWI page (U. Iowa) Access to dataSAI page (U. Iowa) Access to dataRIMS page (NASA/MSFC) Access to dataEICS page (Lockheed-Martin) Access to data
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NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-070B[10/11/2010 0:17:52]
Wednesday, 10 November 2010
Description
The DE 2 spacecraft (low-altitude mission) complemented thehigh-altitude mission DE 1 and was placed into an orbit with aperigee sufficiently low to permit measurements of neutralcomposition, temperature, and wind. The apogee was highenough to permit measurements above the interaction regionsof suprathermal ions, and also plasma flow measurements atthe feet of the magnetospheric field lines. The general form ofthe spacecraft was a short polygon 137 cm in diameter and115 cm high. The triaxial antennas were 23 m tip-to-tip. One 6-m boom was provided for remote measurements. Thespacecraft weight was 403 kg. Power was supplied by a solarcell array, which charged two 6-ampere-hour nickel-cadmiumbatteries. The spacecraft was three-axis stabilized with theyaw axis aligned toward the center of the earth to within 1 deg.The spin axis was normal to the orbit plane within 1 deg with aspin rate of one revolution per orbit. A single-axis scanplatform was included in order to mount the low-altitudeplasma instrument (81-070B-08). The platform rotated aboutthe spin axis. A pulse code modulation telemetry data systemwas used that operated in real time or in a tape-recordermode. Data were acquired on a science-problem-orientedbasis, with closely coordinated operations of the variousinstruments, both satellites, and supportive experiments.Measurements were temporarily stored on tape recordersbefore transmission at an 8:1 playback-to-record ratio. Sincecommands were also stored in a command memory unit,spacecraft operations were not real time. Additional details canbe found in R. A. Hoffman et al., Space Sci. Instrum., v. 5, n.4, p. 349, 1981. DE-2 reentered the atmosphere on February19, 1983.
Dynamics Explorer 2
NSSDC ID: 1981-070B
Alternate Names
Explorer 63
DE-B
DE 2
Dynamics Explorer-B
12625
Facts in Brief
Launch Date: 1981-08-03Launch Vehicle: DeltaLaunchSite: Vandenberg AFB,United StatesMass: 420.0 kgNominalPower: 115.0 W
Funding Agency
NASA-Office of SpaceScience Applications(United States)
Disciplines
Earth Science
Space Physics
AdditionalInformation
Launch/Orbitalinformation for DynamicsExplorer 2
PDMP information forDynamics Explorer 2
Telecommunicationsinformation for DynamicsExplorer 2
Experiments on DynamicsExplorer 2
Data collections from
NSSDC MasterCatalog Search
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NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-070B[10/11/2010 0:17:52]
Dynamics Explorer 2
Questions or commentsabout this spacecraft canbe directed to: Dr. Dieter K.Bilitza.
Personnel
Name Role Original Affiliation E-mail
Dr. Michael A.Calabrese
ProgramManager
NASA Headquarters [email protected]
Mr. J. PatrickCorrigan, III
ProjectManager
NASA Goddard SpaceFlight Center
Dr. Robert A.Hoffman
ProjectScientist
NASA Goddard SpaceFlight Center
Dr. John T.Lynch
ProgramScientist
NASA Headquarters [email protected]
Other DE 2 Data/Information at NSSDC
CDAWeb (Browse and retrieve DE in CDAW)
Related Data/Information at NSSDC
Dynamics Explorer 1
Other Sources of DE 2 Data/Information
General DE page (Los Alamos)
+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-061A[10/11/2010 0:18:13]
Wednesday, 10 November 2010
Description
Ekran 7 was a Soviet communications satellite launched fromthe Baikonur Cosmodrome aboard a Proton 8K82K/Block DMrocket. It transmitted color and black-and-white USSR centraltelevision programs to the network of public receiving unitslocated in population centers in Siberia and the Far North. Thesingle-unit body was equipped with solar panels, and activeliquid-gas phase-change thermoregulation system, and acorrective engine unit for making orbital adjustments. Twenty-five square metres of solar panels provided 1280 W of power.
Ekran 7
NSSDC ID: 1981-061A
Alternate Names
12564
Facts in Brief
Launch Date: 1981-06-26Launch Vehicle: ProtonBooster Plus Upper Stageand Escape StagesLaunch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.RMass: 1970.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Communications
AdditionalInformation
Launch/Orbitalinformation for Ekran 7
Experiments on Ekran 7
Data collections fromEkran 7
Questions or commentsabout this spacecraft canbe directed to: CoordinatedRequest and User SupportOffice.
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-012A[10/11/2010 0:18:37]
Wednesday, 10 November 2010
Description
Engineering Test Satellite-4 (ETS-4) was launched by theNational Space Development Agency of Japan from theTanegashima Space Center using the N-2 launch vehicle. Thesatellite's national name was Kiku-3.
ETS 4
NSSDC ID: 1981-012A
Alternate Names
Kiku-3
Engineering Test Sat-4
12295
Facts in Brief
Launch Date: 1981-02-11Launch Vehicle: N-2LaunchSite: Tanegashima, JapanMass: 640.0 kg
Funding Agency
National SpaceDevelopment Agency(NASDA) (Japan)
Disciplines
Engineering
Earth Science
AdditionalInformation
Launch/Orbitalinformation for ETS 4
Experiments on ETS 4
Data collections from ETS4
Questions or commentsabout this spacecraft canbe directed to: Dr. Dieter K.Bilitza.
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-073A[10/11/2010 0:19:13]
Wednesday, 10 November 2010
Description
The FLTSATCOM (Fleet Satellite Communications)communications satellite system served as a world-wide UHFcommunications link among USN aircraft, ships, submarines,and ground stations. This high-capacity spacebornecommunications system gave the Navy both shore-to-fleet andsingle-way communication among ships, aircraft, andsubmarines separated by distances exceeding line-of-sightUHF ranges. The satellite provided 30 voice channels and 12teletypewriter channels simultaneously in UHF. The UHF uplinkwas in the 290- to 320-MHz range, while UHF downlink was inthe 240- to 270-MHz range. Transmissions in the s-band wereused for commands and beacons. A number of these channelswere reserved for high-priority USAF ground-to-aircommunications with SAC aircraft, the E-3A airborne warningand control system, and elements of the presidential commandstructure. The satellite was hexagonal in shape andapproximately 1.7 m high and 2.7 m in diameter. An erectable5.3-m wire mesh parabolic communications antenna with a 2-msolid-center section extended from one end of the satellite.Protruding from the opposite end was the nozzle of thesatellite's off-loaded apogee motor. Unlike most military andcommercial communications satellites, the FLTSATCOMsatellites used a triaxial stabilization system utilizing a reactioncontrol wheel assembly instead of spin stabilization. Electricalpower (1.1 kw dc) was provided by 2 three-section solarpanels mounted on booms extending from the satellite bodyand unfolded in space. Nickel-cadmium batteries providedpower during solar eclipses. The USN and USAF plan to orbitfour satellites, including one as an on-station spare, positionedaround the world in near-equatorial geosynchronous orbits toprovide near-global coverage. The FSC satellite was theheaviest communications satellite the United States hadattemped to orbit, exceeding the previous leader, TACSAT-1,by over 250 lbs.
FLTSATCOM 5
NSSDC ID: 1981-073A
Alternate Names
FSC-5
FLEETSATCOM 5
12635
Facts in Brief
Launch Date: 1981-08-06Launch Vehicle: Atlas-CentaurLaunch Site: CapeCanaveral, United StatesMass: 1842.0 kg
Funding Agency
Department of Defense-Department of the Navy(United States)
Discipline
Communications
AdditionalInformation
Launch/Orbitalinformation forFLTSATCOM 5
Experiments onFLTSATCOM 5
Data collections fromFLTSATCOM 5
Questions or commentsabout this spacecraft canbe directed to: CoordinatedRequest and User SupportOffice.
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NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-073A[10/11/2010 0:19:13]
Personnel
Name Role Original Affiliation E-mail
Mr. Henry O. Slone Project Manager NASA Lewis Research Center
+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-076A[10/11/2010 0:19:41]
Wednesday, 10 November 2010
Description
The Geostationary Meteorological Satellites (GMS) wereJapan's contribution to the international Global AtmosphericResearch Program (GARP). The spacecraft was roughlycylindrical with a height of 345 cm and a diameter of 216 cm.The cylindrical surface was covered with solar cells whichprovided 225 W. The satellite was spin-stabilized with adespun earth-pointing antenna. The satellite was positionednear 140 deg E and was designed to operate for 5 years. Thiswas a follow-on GMS type spacecraft launched and controlledby NASDA of Japan. The spacecraft was turned off inSeptember 1984.
GMS 2
NSSDC ID: 1981-076A
Alternate Names
Geostation Meteoro Sat 2
Himawari 2
12677
Facts in Brief
Launch Date: 1981-08-10Launch Vehicle: N-2LaunchSite: Tanegashima, JapanMass: 653.0 kg
Funding Agency
National SpaceDevelopment Agency(NASDA) (Japan)
Disciplines
Earth Science
Space Physics
AdditionalInformation
Launch/Orbitalinformation for GMS 2
Experiments on GMS 2
Data collections from GMS2
Questions or commentsabout this spacecraft canbe directed to: CoordinatedRequest and User SupportOffice.
Personnel
NSSDC MasterCatalog Search
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New/Updated Data
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NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-076A[10/11/2010 0:19:41]
Name Role Original Affiliation E-mail
Project Scientist Japanese Meteorological Agency
Dr. Nobuhiko Kodaira Project Manager Meteorological Satellite Center
+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-049A[10/11/2010 0:20:02]
Wednesday, 10 November 2010
Description
GOES 5 was the seventh in a series of NASA-developed,NOAA-operated, geosynchronous, and operational spacecraft.The spin-stabilized spacecraft was stationed at 75 deg W, andcarried (1) an infrared spin-scan radiometer (VISSR)atmospheric sounder (VAS) to provide high-quality day/nightcloudcover data, to take radiance-derived temperatures of theearth/atmosphere system, and to determine atmospherictemperature and water vapor content at various levels, (2) ameteorological data collection and transmission system torelay processed data from central weather facilities to APT-equipped regional stations and to collect and retransmit datafrom remotely located earth-based platforms, and (3) a spaceenvironment monitor (SEM) system to measure proton,electron, and solar X-ray fluxes and magnetic fields. Thecylindrically shaped spacecraft measured 190.5 cm in diameterand 230 cm in length, exclusive of a magnetometer thatextended an additional 83 cm beyond the cylindrical shell. Theprimary structural members were a honeycombed equipmentshelf and thrust tube. The VISSR telescope was mounted onthe equipment shelf and viewed the earth through a specialaperture in the side of the spacecraft. A support structureextended radially from the thrust tube and was affixed to thesolar panels, which formed the outer walls of the spacecraft toprovide the primary source of electrical power. Located in theannulus-shaped space between the thrust tube and the solarpanels were stationkeeping and dynamics control equipment,batteries, and most of the SEM equipment. Proper spacecraftattitude and spin rate (approximately 100 rpm) weremaintained by two separate sets of jet thrusters mountedaround the spacecraft equator and activated by groundcommand. The spacecraft used both UHF-band and S-bandfrequencies in its telemetry and command subsystem. A low-power VHF transponder provided telemetry and commandduring launch and then served as a backup for the primarysubsystem once the spacecraft had attained synchronousorbit. On July 30, 1984, GOES 5 VAS experienced a failure,thus NOAA was prompted to reactivate GOES 1 and 4, torelocate GOES 6 to a more central 98 deg W position, and toreactivate GOES 1 and GOES 4 for the acquisition and relayof VISSR information, respectively, from the western UnitedStates.
GOES 5
NSSDC ID: 1981-049A
Alternate Names
GOES-E
12472
Facts in Brief
Launch Date: 1981-05-22Launch Vehicle: DeltaLaunch Site: CapeCanaveral, United StatesMass: 660.0 kg
Funding Agency
NOAA NationalEnvironmental SatelliteService (United States)
Disciplines
Earth Science
Solar Physics
Space Physics
AdditionalInformation
Launch/Orbitalinformation for GOES 5
Experiments on GOES 5
Data collections fromGOES 5
Questions or commentsabout this spacecraft canbe directed to: CoordinatedRequest and User SupportOffice.
Personnel
NSSDC MasterCatalog Search
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NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-049A[10/11/2010 0:20:02]
Name Role Original Affiliation E-mail
Mr. James R.Greaves
ProgramManager
NASA Headquarters [email protected]
Mr. William E.Shenk
ProjectScientist
NASA Goddard SpaceFlight Center
+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-017A[10/11/2010 0:20:39]
Wednesday, 10 November 2010
Description
The main objective of the HINOTORI mission was the detailedstudy of solar flares during solar maximum. Principalinvestigations were (1) imaging of solar flare X rays in therange 10 to 40 keV by means of rotating modulationcollimators and (2) spectroscopy of X-ray emission lines fromhighly ionized iron in solar flares in the range 1.7 to 2.0 A bymeans of a Bragg spectrometer. Wavelength scanning wasachieved by the spacecraft revolution, with an offset pointing ofthe spin axis with respect to the sun. Investigations (1) and (2)each had a time resolution of 6 s. In addition, the followinginvestigations were included: three solar flare X-ray monitorsthat recorded the time profile and spectrum of the X-ray flaresin the range 2 to 20 keV, a solar flare gamma-ray detector forthe range 0.2 to 9.0 MeV, a particle detector that monitoredelectron flux above 100 keV, and plasma probes for themeasurement of electron density and temperature.
Hinotori
NSSDC ID: 1981-017A
Alternate Names
Astronomical Satellite-A
ASTRO-A
12307
Facts in Brief
Launch Date: 1981-02-21Launch Vehicle: M-3SLaunch Site: UchinouraSpace Center, JapanMass: 188.0 kg
Funding Agency
Institute of Space andAeronautical Science, Uof Tokyo (Japan)
Disciplines
Solar Physics
Space Physics
AdditionalInformation
Launch/Orbitalinformation for Hinotori
Experiments on Hinotori
Data collections fromHinotori
Questions or commentsabout this spacecraft canbe directed to: Dr. H. KentHills.
Personnel
Name Role Original Affiliation E-
NSSDC MasterCatalog Search
Spacecraft
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New/Updated Data
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NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-017A[10/11/2010 0:20:39]
Mr. Katsuo Tanaka ProjectScientist
Institute of Space and AeronauticalScience
Prof. YasuoTanaka
ProjectManager
Institute of Space and AeronauticalScience
+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-075A[10/11/2010 0:21:24]
Wednesday, 10 November 2010
Description
The spacecraft contained a set of plasma, particles, fields, andoptical experiments that were designed and constructed inBulgaria. The spacecraft was three-axis stabilized with thenegative Z-axis pointing toward the center of the earth and theX-axis pointing along the velocity vector. The outer skin of thespacecraft, including the solar panels, was coated with aconducting material in order to allow the proper measurementof electric fields and low energy plasma. Both active andpassive thermal control were employed. The solar panelssupplied 2 kW and batteries were used during eclipse periods.There were two tape recorders, each with a capacity of 60megabits. The transmitter radiated about 10 W in the 130-MHzband.
IK Bulgaria 1300
NSSDC ID: 1981-075A
Alternate Names
ICB1300
Intercosmos Bulgar 1300
12645
Facts in Brief
Launch Date: 1981-08-07LaunchVehicle: Modified SS-6(Sapwood) with 1stGeneration Upper StageLaunch Site: Plesetsk,U.S.S.RMass: 1500.0 kg
Funding Agencies
Bulgarian Academy ofSciences (Bulgaria)
Intercosmos (U.S.S.R)
Discipline
Space Physics
AdditionalInformation
Launch/Orbitalinformation for IKBulgaria 1300
Experiments on IK Bulgaria1300
Data collections from IKBulgaria 1300
Questions or commentsabout this spacecraft canbe directed to: Dr. Dieter K.Bilitza.
NSSDC MasterCatalog Search
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NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-075A[10/11/2010 0:21:24]
Personnel
Name Role Original Affiliation E-mail
Dr. Ivan S.Kutiev
ProjectScientist
Central Laboratory for SpaceResearch, Bulgarian Academy ofScience
Mr. A. G.Iosiphian
ProjectManager
Intercosmos
Prof. KirilBorissovSerafimov
ProjectManager
Central Laboratory for SpaceResearch, Bulgarian Academy ofScience
Dr. MitkoMarinovGogoshev
ProjectScientist
Central Laboratory for SpaceResearch, Astronomical Observatory
Dr. V. M.Balebanov
ProjectScientist
Institut Kosmicheskich Issledovaniya(Institute of Space Research)
+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-119A[10/11/2010 0:22:01]
Wednesday, 10 November 2010
Description
Intelsat 5D F-3 was a COMSAT Corporation commercialcommunications satellite. It was part of an advanced series ofspacecraft used to provide increased telecommunicationscapacity for Intelsat's global network.
INTELSAT 5 F-3
NSSDC ID: 1981-119A
Alternate Names
12994
Facts in Brief
Launch Date: 1981-12-15Launch Vehicle: Atlas-CentaurLaunch Site: CapeCanaveral, United StatesMass: 1870.0 kg
Funding Agency
InternationalTelecommunicationsSatellite Corporation(United States)
Discipline
Communications
AdditionalInformation
Launch/Orbitalinformation for INTELSAT5 F-3
Experiments on INTELSAT5 F-3
Data collections fromINTELSAT 5 F-3
Questions or commentsabout this spacecraft canbe directed to: CoordinatedRequest and User SupportOffice.
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-050A[10/11/2010 0:22:30]
Wednesday, 10 November 2010
Description
Intelsat 5B F-1 was a COMSAT commercial communicationssatellite. It was part of an advanced series of spacecraft toprovide telecommunications capacity for Intelsat's globalnetwork.
INTELSAT 5B F-1
NSSDC ID: 1981-050A
Alternate Names
12474
Facts in Brief
Launch Date: 1981-05-23Launch Vehicle: Atlas-CentaurLaunch Site: CapeCanaveral, United StatesMass: 1928.0 kg
Funding Agency
InternationalTelecommunicationsSatellite Corporation(United States)
Discipline
Communications
AdditionalInformation
Launch/Orbitalinformation for INTELSAT5B F-1
Experiments on INTELSAT5B F-1
Data collections fromINTELSAT 5B F-1
Questions or commentsabout this spacecraft canbe directed to: CoordinatedRequest and User SupportOffice.
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-011A[10/11/2010 0:22:50]
Wednesday, 10 November 2010
Description
Intercosmos 21 was launched by the USSR. It carried scientificinstruments.
Intercosmos 21
NSSDC ID: 1981-011A
Alternate Names
12162
Facts in Brief
Launch Date: 1981-02-06LaunchVehicle: Modified SS-5(SKean IRBM) plus UpperStageLaunch Site: Plesetsk,U.S.S.RMass: 550.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Earth Science
AdditionalInformation
Launch/Orbitalinformation forIntercosmos 21
Experiments onIntercosmos 21
Data collections fromIntercosmos 21
Questions or commentsabout this spacecraft canbe directed to: CoordinatedRequest and User SupportOffice.
NSSDC MasterCatalog Search
Spacecraft
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Personnel
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-065C[10/11/2010 0:23:36]
Wednesday, 10 November 2010
Description
Iskra 1 was a development satellite built by the MoscowAviation Institute, launched on July 10th 1968 with Meteor 31into a 638 x 663 km orbit. It weighed 28kg and measured 0.6min diameter.
ISKRA
NSSDC ID: 1981-065C
Facts in Brief
Launch Date: 1981-07-10LaunchVehicle: Modified SS-6(Sapwood) with 1stGeneration Upper StageLaunch Site: Plesetsk,U.S.S.RMass: 2200.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Microgravity
AdditionalInformation
Launch/Orbitalinformation for ISKRA
Experiments on ISKRA
Data collections fromISKRA
Questions or commentsabout this spacecraft canbe directed to: CoordinatedRequest and User SupportOffice.
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-085A[10/11/2010 0:24:38]
Wednesday, 10 November 2010
Description
This US Air Force photo surveillance satellite was launchedfrom Vandenberg AFB aboard a Titan 3D rocket. It was a KH-11 (Key Hole-11) type spacecraft. Spacecraft engaged inpractical applications and uses of space technology such asweather or communication.
KH 11-4
NSSDC ID: 1981-085A
Alternate Names
1981-085A
12799
Facts in Brief
Launch Date: 1981-09-03Launch Vehicle: TitanIII-DLaunchSite: Vandenberg AFB,United StatesMass: 13300.0 kg
Funding Agency
Unknown (United States)
Discipline
Surveillance and OtherMilitary
AdditionalInformation
Launch/Orbitalinformation for KH 11-4
Experiments on KH 11-4
Data collections from KH11-4
Questions or commentsabout this spacecraft canbe directed to: CoordinatedRequest and User SupportOffice.
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-019A[10/11/2010 0:25:30]
Wednesday, 10 November 2010
Description
This US Air Force photo surveillance satellite was launchedfrom Vandenberg AFB aboard a Titan 3B rocket. It was a KH-8(Key Hole-8) type spacecraft. Spacecraft engaged in practicalapplication and uses of space technology such as weather orcommunications.
KH 8-51
NSSDC ID: 1981-019A
Alternate Names
1981-019A
12315
Facts in Brief
Launch Date: 1981-02-28Launch Vehicle: TitanIII-BLaunchSite: Vandenberg AFB,United StatesMass: 3000.0 kg
Funding Agency
Department of Defense-Department of the AirForce (United States)
Discipline
Surveillance and OtherMilitary
AdditionalInformation
Launch/Orbitalinformation for KH 8-51
Experiments on KH 8-51
Data collections from KH 8-51
Questions or commentsabout this spacecraft canbe directed to: CoordinatedRequest and User SupportOffice.
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-122A[10/11/2010 0:26:41]
Wednesday, 10 November 2010
Description
MARECS 1 was a geostationary communications satellite,which formed part of INMARSATs world-wide maritimecommunications satellite network. The program began as theexperimental Maritime Orbital Test Satellite (MAROTS) in1973, but was subsequently changed to an operational systemresulting in a name change, a satellite redesign, and delayeddevelopment. MARECS was operated by ESA for INMARSAT.The spacecraft was based on the British Aerospace ECSplatform, 3-axis stabilized to 0.2 deg (pitch, roll) using fullyredundant momentum wheels, thrusters, and nutationdampers. Redundant sun sensors provided 0.04 degknowledge. Two sun-tracking solar arrays provided 955 W(BOL) with 2 NiCd batteries for eclipse power. It had ahydrozine propulsion system for station-keeping. The payloadconsisted of 3 repeaters: shore-to-ship with 5 MHz bandwidth,ship-to-shore with 6 MHz bandwidth, and shore-to-shore with0.5 MHZ bandwidth. These provided 35 two-way voicechannels plus search and rescue capabilities. It had one 2 mdiameter L-Band antenna and 2 horns (one transmit, onereceive) for 4/6 GHz channels. All antennas had full Earthcoverage.
Marecs-A
NSSDC ID: 1981-122A
Alternate Names
13010
Facts in Brief
Launch Date: 1981-12-20Launch Vehicle: ArianeLaunch Site: Kourou,French GuianaMass: 582.0 kg
Funding Agency
European Space Agency(International)
Discipline
Communications
AdditionalInformation
Launch/Orbitalinformation for Marecs-A
Experiments on Marecs-A
Data collections fromMarecs-A
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NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-065A[10/11/2010 0:27:34]
Wednesday, 10 November 2010
Description
Meteor 1-31
NSSDC ID: 1981-065A
Alternate Names
12585
Facts in Brief
Launch Date: 1981-07-10LaunchVehicle: Modified SS-6(Sapwood) with 1stGeneration Upper StageLaunch Site: Plesetsk,U.S.S.RMass: 2200.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Earth Science
AdditionalInformation
Launch/Orbitalinformation for Meteor 1-31
Experiments on Meteor 1-31
Data collections fromMeteor 1-31
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NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-043A[10/11/2010 0:28:25]
Wednesday, 10 November 2010
Description
Meteor 2 was launched by the USSR. It carried scientific andmeteorological instruments, an electrosupply system, a radiosystem for precise measurement of orbit elements, an orbitcorrection system, and a radio telemetry system.
Meteor 2-7
NSSDC ID: 1981-043A
Alternate Names
12456
Facts in Brief
Launch Date: 1981-05-14LaunchVehicle: Modified SS-6(Sapwood) with 1stGeneration Upper StageLaunch Site: Plesetsk,U.S.S.RMass: 2750.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Earth Science
AdditionalInformation
Launch/Orbitalinformation for Meteor 2-7
Experiments on Meteor 2-7
Data collections fromMeteor 2-7
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http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-057A[10/11/2010 0:29:20]
Wednesday, 10 November 2010
Description
Meteosat 2 was a geostationary spacecraft which served aspart of the European Space Agency's (ESA) contribution to theGlobal Atmospheric Research Program (GARP). As part ofGARP, the satellite helped to supply data required for globaldata sets used in improvement of machine weather forecasts.In general, the spacecraft design, instrumentation, andoperation were similar to SMS/GOES. The spin-stabilizedspacecraft carried (1) a visible-IR radiometer that providedhigh-quality day/night cloudcover data and that took radiancetemperatures of the earth/atmosphere system; (2) ameteorological data collection system that disseminated imagedata to user stations, collected data from various earth-basedplatforms, and relayed data from polar-orbiting satellites; and(3) an AFGL electron spectrometer to investigate the linkbetween surface charging and the spacecraft anomalies seenon Meteosat 1. The cylindrically shaped spacecraft measured210 cm in diameter and 430 cm in length, including the apogeeboost motor. The primary structural members were anequipment platform and a central tube. The radiometertelescope was mounted on the equipment platform and viewedthe earth through a special aperture in the side of thespacecraft. A support structure extended radially out from thecentral tube and was affixed to the solar panels, which formedthe outer walls of the spacecraft and provided the primarysource of electrical power. Located in the annulus-shapedspace between the central tube and the solar panels werestationkeeping and dynamics control equipment and batteries.Proper spacecraft attitude and spin rate (approximately 100rpm) were maintained by jet thrusters mounted on thespacecraft and activated by ground command. The spacecraftused both UHF-band and S-band frequencies in its telemetryand command subsystems. A low-power VHF transponderprovided telemetry and command during launch and thenserved as a backup for the primary subsystem after thespacecraft had attained synchronous orbit. Meteosat 2 wasmaintained on station between 1 deg E and 1 deg W.
National Space Science Data Center Header
Meteosat 2
NSSDC ID: 1981-057A
Alternate Names
Meteorological Sat-B
12544
Facts in Brief
Launch Date: 1981-06-19Launch Vehicle: ArianeLaunch Site: Kourou,French GuianaMass: 625.8 kg
Funding Agency
European MeteorologicalSatellite Agency(International)
Disciplines
Earth Science
Space Physics
AdditionalInformation
Launch/Orbitalinformation for Meteosat2
Experiments on Meteosat 2
Data collections fromMeteosat 2
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http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-057A[10/11/2010 0:29:20]
Name Role Original Affiliation E-mail
Mr. J. Aasted Project Manager European Space Agency - Toulouse
+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-009A[10/11/2010 0:30:10]
Wednesday, 10 November 2010
Description
Molniya 1/49 was a first-generation Russian communicationsatellite orbited to test and perfect a system of radiocommunications 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 orbtial 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 at 1000 MHz. Television service was provided in afrequency range of 3.4 to 4.1 GHz at 40 w. Molniya 1/49,whose cylindrical body was 3.4 m long and 1.6 m in diameter,was much heavier than corresponding U.S. COMSATs, and ithad about 10 times the power output of the Early BirdCOMSAT. In addition, it did not employ a synchronousequatorial orbit as do most U.S. COMSATs because such anorbit would not provide coverage for areas north of 70 deg nlatitude. Instead, the satellite was boosted from a low-altitudeparking orbit into a highly elliptical orbit with two high apogeesdaily over the northern hemisphere -- one over Russia and oneover North America -- and relatively low perigees over thesouthern hemipshere. During its apogee, Molniya 1/49remained relatively stationary with respect to the earth belowfor nearly 8 of every 12 hr. By placing three or more Molniya 1satellites in this type of orbit, spacing them suitably, andshifting their orbital planes relative to each other by 120 deg, a24-hr/day communication system could be obtained.
Molniya 1-49
NSSDC ID: 1981-009A
Alternate Names
12156
Facts in Brief
Launch Date: 1981-01-30LaunchVehicle: Modified SS-6(Sapwood) with 2ndGeneration Upper Stage +Escape StageLaunch Site: Plesetsk,U.S.S.RMass: 1000.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Communications
AdditionalInformation
Launch/Orbitalinformation for Molniya 1-49
Experiments on Molniya 1-49
Data collections fromMolniya 1-49
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NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-060A[10/11/2010 0:31:01]
Wednesday, 10 November 2010
Description
Molniya 1/50 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 1/50, 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 1/50 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 1-50
NSSDC ID: 1981-060A
Alternate Names
12556
Facts in Brief
Launch Date: 1981-06-24LaunchVehicle: Modified SS-6(Sapwood) with 2ndGeneration Upper Stage +Escape StageLaunch Site: Plesetsk,U.S.S.RMass: 1000.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Communications
AdditionalInformation
Launch/Orbitalinformation for Molniya 1-50
Experiments on Molniya 1-50
Data collections fromMolniya 1-50
Questions or commentsabout this spacecraft canbe directed to: CoordinatedRequest and User SupportOffice.
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NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-113A[10/11/2010 0:31:46]
Wednesday, 10 November 2010
Description
Molniya 1/51 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 1/51, 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 1/51 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 1-51
NSSDC ID: 1981-113A
Alternate Names
12959
Facts in Brief
Launch Date: 1981-11-17LaunchVehicle: Modified SS-6(Sapwood) with 2ndGeneration Upper Stage +Escape StageLaunch Site: Plesetsk,U.S.S.RMass: 1000.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Communications
AdditionalInformation
Launch/Orbitalinformation for Molniya 1-51
Experiments on Molniya 1-51
Data collections fromMolniya 1-51
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-123A[10/11/2010 0:32:54]
Wednesday, 10 November 2010
Description
Molniya 1/52 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 1/52, 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 1/52 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 1-52
NSSDC ID: 1981-123A
Alternate Names
13027
Facts in Brief
Launch Date: 1981-12-23LaunchVehicle: Modified SS-6(Sapwood) with 2ndGeneration Upper Stage +Escape StageLaunch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.RMass: 1000.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Communications
AdditionalInformation
Launch/Orbitalinformation for Molniya 1-52
Experiments on Molniya 1-52
Data collections fromMolniya 1-52
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NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-002A[10/11/2010 0:34:24]
Wednesday, 10 November 2010
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 3-14
NSSDC ID: 1981-002A
Alternate Names
12133
Facts in Brief
Launch Date: 1981-01-09LaunchVehicle: Modified SS-6(Sapwood) with 2ndGeneration Upper Stage +Escape StageLaunch Site: Plesetsk,U.S.S.RMass: 1500.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Communications
AdditionalInformation
Launch/Orbitalinformation for Molniya 3-14
Experiments on Molniya 3-14
Data collections fromMolniya 3-14
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NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-030A[10/11/2010 0:36:02]
Wednesday, 10 November 2010
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 3-15
NSSDC ID: 1981-030A
Alternate Names
12368
Facts in Brief
Launch Date: 1981-03-24LaunchVehicle: Modified SS-6(Sapwood) with 2ndGeneration Upper Stage +Escape StageLaunch Site: Plesetsk,U.S.S.RMass: 1500.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Communications
AdditionalInformation
Launch/Orbitalinformation for Molniya 3-15
Experiments on Molniya 3-15
Data collections fromMolniya 3-15
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NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-054A[10/11/2010 0:37:17]
Wednesday, 10 November 2010
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 3-16
NSSDC ID: 1981-054A
Alternate Names
12512
Facts in Brief
Launch Date: 1981-06-09LaunchVehicle: Modified SS-6(Sapwood) with 2ndGeneration Upper Stage +Escape StageLaunch Site: Plesetsk,U.S.S.RMass: 1500.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Communications
AdditionalInformation
Launch/Orbitalinformation for Molniya 3-16
Experiments on Molniya 3-16
Data collections fromMolniya 3-16
Questions or commentsabout this spacecraft canbe directed to: CoordinatedRequest and User SupportOffice.
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-105A[10/11/2010 0:38:42]
Wednesday, 10 November 2010
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 3-17
NSSDC ID: 1981-105A
Alternate Names
12915
Facts in Brief
Launch Date: 1981-10-17LaunchVehicle: Modified SS-6(Sapwood) with 2ndGeneration Upper Stage +Escape StageLaunch Site: Plesetsk,U.S.S.RMass: 1500.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Communications
AdditionalInformation
Launch/Orbitalinformation for Molniya 3-17
Experiments on Molniya 3-17
Data collections fromMolniya 3-17
Questions or commentsabout this spacecraft canbe directed to: CoordinatedRequest and User SupportOffice.
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-059A[10/11/2010 0:39:54]
Wednesday, 10 November 2010
Description
NOAA 7 was an operational meteorological satellite for use inthe National Operational Environmental Satellite System(NOESS) and for the support of the Global AtmosphericResearch Program (GARP) during 1978-84. The satellitedesign provided an economical and stable sun-synchronousplatform for advanced operational instruments to measure theearth's atmosphere, its surface and cloud cover, and the near-space environment. Primary sensors included an advancedvery high resolution radiometer (AVHRR) and a TIROSoperational vertical sounder (TOVS). Secondary experimentsconsisted of a space environment monitor (SEM) and a datacollection and platform location system (DCPLS). Acontamination monitor was provided by USAF to assesscontamination sources, levels, and effects for consideration onfuture spacecraft. The satellite was based upon the Block 5Dspacecraft bus developed for the U.S. Air Force, and it wascapable of maintaining an earth-pointing accuracy of betterthan plus or minus 0.1 deg with a motion rate of less than0.035 deg/s. For a more detailed description, see A. Schwalb,"The TIROS-N/NOAA A-G Satellite Series," NOAA Tech. Mem.NESS 95, 1978.
NOAA 7
NSSDC ID: 1981-059A
Alternate Names
NOAA-C
12553
Facts in Brief
Launch Date: 1981-06-23Launch Vehicle: AtlasFLaunchSite: Vandenberg AFB,United StatesMass: 588.9 kg
Funding Agency
NOAA NationalEnvironmental SatelliteService (United States)
Disciplines
Communications
Earth Science
Space Physics
AdditionalInformation
Launch/Orbitalinformation for NOAA 7
Experiments on NOAA 7
Data collections fromNOAA 7
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NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-059A[10/11/2010 0:39:54]
Personnel
Name Role Original Affiliation E-mail
Dr. Joel Susskind ProjectScientist
NASA Goddard SpaceFlight Center
Mr. Gerald W.Longanecker
ProjectManager
NASA Goddard SpaceFlight Center
Dr. Ray J. Arnold ProgramManager
NASA Headquarters
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NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-044A[10/11/2010 0:41:18]
Wednesday, 10 November 2010
Description
NOVA 1 was an improved Transit satellite launched by NASAfor the US Navy's operational navigation system.
NOVA I
NSSDC ID: 1981-044A
Alternate Names
NNSS 30480
NOVA
12458
Facts in Brief
Launch Date: 1981-05-15Launch Vehicle: ScoutLaunchSite: Vandenberg AFB,United States
Funding Agency
Unknown (United States)
Discipline
Navigation & GlobalPositioning
AdditionalInformation
Launch/Orbitalinformation for NOVA I
Experiments on NOVA I
Data collections fromNOVA I
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NOVA I
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http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-007A[10/11/2010 0:42:40]
Wednesday, 10 November 2010
Description
Automatic cargo ship Progress 12 was launched by theSoviets from the Baikonur cosmodrome aboard a Soyuzrocket. It delivered various cargos to the Salyut 6 space stationand deorbited on March 29, 1981 at 16:59 GMT.
Progress 12
NSSDC ID: 1981-007A
Alternate Names
12152
Facts in Brief
Launch Date: 1981-01-24LaunchVehicle: Modified SS-6(Sapwood) with 2ndGeneration (Longer) UpperStageLaunch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.RMass: 7020.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Resupply/Refurbishment/Repair
AdditionalInformation
Launch/Orbitalinformation for Progress12
Experiments on Progress12
Data collections fromProgress 12
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NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-120A[10/11/2010 0:44:50]
Wednesday, 10 November 2010
Description
Radio 3 was launched by the USSR. It carried amateur radioinstruments and a telemetry system.
Radio 3
NSSDC ID: 1981-120A
Alternate Names
12997
Facts in Brief
Launch Date: 1981-12-17LaunchVehicle: Modified SS-5(SKean IRBM) plus UpperStageLaunch Site: Plesetsk,U.S.S.R
Funding Agency
Unknown (U.S.S.R)
Discipline
Communications
AdditionalInformation
Launch/Orbitalinformation for Radio 3
Experiments on Radio 3
Data collections fromRadio 3
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NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-120B[11/11/2010 22:53:31]
Friday, 12 November 2010
Description
Radio 4 was launched by the USSR. It carried amateur radioinstruments and a radio telemetry system.
Radio 4
NSSDC ID: 1981-120B
Alternate Names
12998
Facts in Brief
Launch Date: 1981-12-17LaunchVehicle: Modified SS-5(SKean IRBM) plus UpperStageLaunch Site: Plesetsk,U.S.S.R
Funding Agency
Unknown (U.S.S.R)
Discipline
Communications
AdditionalInformation
Launch/Orbitalinformation for Radio 4
Experiments on Radio 4
Data collections fromRadio 4
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NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-120C[11/11/2010 22:54:25]
Friday, 12 November 2010
Description
Radio 5 was launched by the USSR. It carried amateur radioinstruments and a radio telemetry system.
Radio 5
NSSDC ID: 1981-120C
Alternate Names
12999
Facts in Brief
Launch Date: 1981-12-17LaunchVehicle: Modified SS-5(SKean IRBM) plus UpperStageLaunch Site: Plesetsk,U.S.S.R
Funding Agency
Unknown (U.S.S.R)
Discipline
Communications
AdditionalInformation
Launch/Orbitalinformation for Radio 5
Experiments on Radio 5
Data collections fromRadio 5
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NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-120D[11/11/2010 22:55:01]
Friday, 12 November 2010
Description
Radio 6 was launched by the USSR. It carried amateur radioinstruments and a radio telemetry system.
Radio 6
NSSDC ID: 1981-120D
Alternate Names
13000
Facts in Brief
Launch Date: 1981-12-17LaunchVehicle: Modified SS-5(SKean IRBM) plus UpperStageLaunch Site: Plesetsk,U.S.S.R
Funding Agency
Unknown (U.S.S.R)
Discipline
Communications
AdditionalInformation
Launch/Orbitalinformation for Radio 6
Experiments on Radio 6
Data collections fromRadio 6
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NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-120E[11/11/2010 22:55:41]
Friday, 12 November 2010
Description
Radio 7 was launched by the USSR. It carried amateur radioinstruments and a radio telemetry system.
Radio 7
NSSDC ID: 1981-120E
Alternate Names
13001
Facts in Brief
Launch Date: 1981-12-17LaunchVehicle: Modified SS-5(SKean IRBM) plus UpperStageLaunch Site: Plesetsk,U.S.S.R
Funding Agency
Unknown (U.S.S.R)
Discipline
Communications
AdditionalInformation
Launch/Orbitalinformation for Radio 7
Experiments on Radio 7
Data collections fromRadio 7
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NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-120F[11/11/2010 22:56:23]
Friday, 12 November 2010
Description
Radio 8 was launched by the USSR. It carried amateur radioinstruments and a radio telemetry system.
Radio 8
NSSDC ID: 1981-120F
Alternate Names
13002
Facts in Brief
Launch Date: 1981-12-17LaunchVehicle: Modified SS-5(SKean IRBM) plus UpperStageLaunch Site: Plesetsk,U.S.S.R
Funding Agency
Unknown (U.S.S.R)
Discipline
Communications
AdditionalInformation
Launch/Orbitalinformation for Radio 8
Experiments on Radio 8
Data collections fromRadio 8
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-027A[11/11/2010 22:57:04]
Friday, 12 November 2010
Description
Raduga 8 was launched by the USSR into a circular orbit. Itcarried instruments for telephone and telegraphiccommunication and TV transmission.
Raduga 8
NSSDC ID: 1981-027A
Alternate Names
12351
Facts in Brief
Launch Date: 1981-03-18Launch Vehicle: ProtonBooster Plus Upper Stageand Escape StagesLaunch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.R
Funding Agency
Unknown (U.S.S.R)
Discipline
Communications
AdditionalInformation
Launch/Orbitalinformation for Raduga 8
Experiments on Raduga 8
Data collections fromRaduga 8
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-069A[11/11/2010 22:57:48]
Friday, 12 November 2010
Description
Raduga 9 was a Soviet communications satellite launched fromthe Baikonur cosmodrome aboard a Proton 8K82K/Block DMrocket. It provided uninterrupted round the clock telelphoneand telegraph radio communications in the USSR andsimultaneous transmission of color and black and white USSRcentral television programs to stations in the Orbita network.
Raduga 9
NSSDC ID: 1981-069A
Alternate Names
12618
Facts in Brief
Launch Date: 1981-07-30Launch Vehicle: ProtonBooster Plus Upper Stageand Escape StagesLaunch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.R
Funding Agency
Unknown (U.S.S.R)
Discipline
Communications
AdditionalInformation
Launch/Orbitalinformation for Raduga 9
Experiments on Raduga 9
Data collections fromRaduga 9
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NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-102A[11/11/2010 22:58:42]
Friday, 12 November 2010
Description
Raduga 10 was a Soviet communications satellite launchedinto a geosynchronous orbit from the Baikonur cosmodromeaboard a Proton 8K82K/Block DM rocket. It provideduninterrupted round the clock telephone and telegraph radiocommunication in the USSR and simultaneous transmission ofcolor and black and white USSR central television programs tostations in the Orbita network.
Raduga 10
NSSDC ID: 1981-102A
Alternate Names
12897
Facts in Brief
Launch Date: 1981-10-09Launch Vehicle: ProtonLaunch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.R
Funding Agency
Unknown (U.S.S.R)
Discipline
Communications
AdditionalInformation
Launch/Orbitalinformation for Raduga10
Experiments on Raduga 10
Data collections fromRaduga 10
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NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-114A[11/11/2010 22:59:18]
Friday, 12 November 2010
Description
RCA-SATCOM 3R was the fourth in a series of RCA-GLOBCOM commercial communications satellites launchedinto a geosynchronous transfer orbit from Cape Canaveral. TheDelta rocket performed nominally, placing the spacecraft andits apogee boost motor (ABM) into the desired transfer orbitthat permitted the propulsion systems to meet the mission'sobjectives.
RCA-SATCOM 3R
NSSDC ID: 1981-114A
Alternate Names
RCA-SATCOM IIIR
12967
Facts in Brief
Launch Date: 1981-11-20Launch Vehicle: DeltaLaunch Site: CapeCanaveral, United StatesMass: 1078.0 kg
Funding Agency
GE AmericanCommunications, Inc.(United States)
Discipline
Communications
AdditionalInformation
Launch/Orbitalinformation for RCA-SATCOM 3R
Experiments on RCA-SATCOM 3R
Data collections from RCA-SATCOM 3R
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NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-051A[11/11/2010 23:00:04]
Friday, 12 November 2010
Description
Rohini 2 was the second Indian national launch. It waslaunched using a SLV-3 rocket from the Sriharikota SpaceCenter in the Bengal Bay into a 186 x 418km (intended 296 x834) orbit. The satellite was spherical with a 0.6 m diameterand weighed 38 kg. It carried a landmark tracker payload foraccurate orbit and attitude determination.
Rohini 2
NSSDC ID: 1981-051A
Alternate Names
12491
Facts in Brief
Launch Date: 1981-05-31Launch Vehicle: Indian-Designed LaunchComparable to the Atlas-AgenaLaunch Site: Sriharikota,IndiaMass: 38.0 kg
Funding Agency
Unknown (India)
Discipline
Earth Science
AdditionalInformation
Launch/Orbitalinformation for Rohini 2
Experiments on Rohini 2
Data collections fromRohini 2
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NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-096A[11/11/2010 23:01:01]
Friday, 12 November 2010
Description
SBS 2 (Satellite Business Systems 2) was launched by NASAto provide fully switched private networks to businesses,government agencies, and other organizations with large,varied communications requirements.
SBS 2
NSSDC ID: 1981-096A
Alternate Names
Satellite BusinessSystems 2
12855
Facts in Brief
Launch Date: 1981-09-24Launch Vehicle: DeltaLaunch Site: CapeCanaveral, United StatesMass: 550.0 kg
Funding Agency
Satellite BusinessSystems (United States)
Discipline
Communications
AdditionalInformation
Launch/Orbitalinformation for SBS 2
Experiments on SBS 2
Data collections from SBS2
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Personnel
Name Role Original Affiliation E-mail
Mr. Robert J. Goss Project Manager NASA Goddard Space Flight Center
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http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-038A[11/11/2010 23:01:36]
Friday, 12 November 2010
Description
The Satellite Data System (SDS-1) was composed of twooperational satellites that had supported near-real timecommunications between low altitude photographic intelligencesatellites and ground control stations, making it a critical part ofthe US Air Force Satellite Communications (AFSATCOM)System. In particular, SDS-1 served as a communications linkbetween the Air Force Satellite Control Facility at Sunnyvale,CA, and 7 remote tracking stations located at VandenbergAFB, Hawaii, Guam, Nahe Island, Greenland, the UK, andBoston. Furthermore, the SDS-1 enabled almost two-way real-time command, control, and UHF communications in the polarregion for Strategic Air Command (SAC) forces. The Northpolar region was not covered by communications satellites ingeostationary orbit, and therefore the SDS-1 filled the gap. Athird and unacknowledged function was to provide a relay forinformation from the KH-11 photo reconnaisance satellite to aground station, which was probably the Defense SpecialMissile and Astronautics Center at Fort Meade, MD. It flew in63 deg orbits, having high apogees over the North Pole andlow perigees. This gave it a long stay time over the polarregion, enabling it to relay communications to aircraft in thoseareas. Two of the SDS-1 satellites had to be in orbit for thecommunications to be constant. Each had 12 communicationschannels in the UHF band. The main transmitting antenna wasover 10 feet in diameter. The body itself, based on the designof the TACSAT, was cylindrical and about 13 feet long and 10feet in diameter. The outside cylinder, call the solar array, wasmade of a silicon skin and spun for thermal distribution of theheat load. The primary electrical power was provided by solarcharged batteries with a total of 980 watts of power.
SDS F-4
NSSDC ID: 1981-038A
Alternate Names
Satellite Data System F-4
12418
Facts in Brief
Launch Date: 1981-04-24Launch Vehicle: TitanIII-BLaunchSite: Vandenberg AFB,United StatesMass: 700.0 kg
Funding Agency
Department of Defense-Department of the AirForce (United States)
Discipline
Surveillance and OtherMilitary
AdditionalInformation
Launch/Orbitalinformation for SDS F-4
Experiments on SDS F-4
Data collections from SDSF-4
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NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-093D[11/11/2010 23:02:19]
Friday, 12 November 2010
Description
The announced missions of the three SJ-2 (Shi Jian - Practice)spacecraft launched on a single booster included ionosphericand atmospheric studies. This cover story was frequently usedby early American electronic intelligence satellites launched bythe US Navy, and the mass and orbital parameters (200 by1600 km orbits at 59.4 deg inclination) of the SJ-2 spacecraftwere consistent both with the announced missions as well aswith electronic intelligence (ELINT) applications.
Shijian 2A
NSSDC ID: 1981-093D
Alternate Names
SJ 2A
China 11
PRC 11
12845
Facts in Brief
Launch Date: 1981-09-19Launch Vehicle: FB-1Launch Site: ShuangCheng-Tzu, PeoplesRepublic of ChinaMass: 483.0 kg
Funding Agency
Unknown (PeoplesRepublic of China)
Discipline
Space Physics
AdditionalInformation
Launch/Orbitalinformation for Shijian 2A
Experiments on Shijian 2A
Data collections fromShijian 2A
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-093A[11/11/2010 23:03:01]
Friday, 12 November 2010
Description
The announced missions of the three SJ-2 (Shi Jian - Practice)spacecraft launched on a single booster included ionosphericand atmospheric studies. This cover story was frequently usedby early American electronic intelligence satellites launched bythe US Navy, and the mass and orbital parameters (200 by1600 km orbits at 59.4 deg inclination) of the SJ-2 spacecraftwere consistent both with the announced missions as well aswith electronic intelligence (ELINT) applications.
Shijian 2B
NSSDC ID: 1981-093A
Alternate Names
China 9
SJ 2B
PRC 9
12842
Facts in Brief
Launch Date: 1981-09-19Launch Vehicle: FB-1Launch Site: ShuangCheng-Tzu, PeoplesRepublic of ChinaMass: 257.0 kg
Funding Agency
Unknown (PeoplesRepublic of China)
Discipline
Earth Science
AdditionalInformation
Launch/Orbitalinformation for Shijian 2B
Experiments on Shijian 2B
Data collections fromShijian 2B
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NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-093B[11/11/2010 23:03:48]
Friday, 12 November 2010
Description
The announced missions of the three SJ-2 (Shi Jian - Practice)spacecraft launched on a single booster included ionosphericand atmospheric studies. This cover story was frequently usedby early American electronic intelligence satellites launched bythe US Navy, and the mass and orbital parameters (200 by1600 km orbits at 59.4 deg inclination) of the SJ-2 spacecraftwere consistent both with the announced missions as well aswith electronic intelligence (ELINT) applications.
Shijian 2C
NSSDC ID: 1981-093B
Alternate Names
China 10
SJ 2C
PRC 10
12843
Facts in Brief
Launch Date: 1981-09-19Launch Vehicle: FB-1Launch Site: ShuangCheng-Tzu, PeoplesRepublic of ChinaMass: 28.0 kg
Funding Agency
Unknown (PeoplesRepublic of China)
Discipline
Space Physics
AdditionalInformation
Launch/Orbitalinformation for Shijian 2C
Experiments on Shijian 2C
Data collections fromShijian 2C
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http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-100A[11/11/2010 23:04:40]
Friday, 12 November 2010
Description
The Solar Mesosphere Explorer (SME) mission objective wasprimarily to investigate the processes that create and destroyozone in the Earth's mesosphere and upper stratosphere.Some specific goals were to: (1) determine the nature andmagnitude of changes in mesospheric ozone densitiesresulting from changes in the solar ultraviolet flux; (2)determine the interrelationship between solar flux, ozone, andthe temperature of the upper stratosphere and mesosphere; (3)determine the interrelationship between ozone and watervapor; and (4) determine the interrelationship between nitrogendioxide and ozone.
The satellite experiment complement consisted of a solarultraviolet spectrometer, an ultraviolet ozone spectrometer, aninfrared radiometer, a 1.27-micrometer spectrometer, and anitrogen dioxide spectrometer. In addition, a solar proton alarmdetector was carried on-board to measure the integrated solarflux in the range 30-500 MeV.
Spin stabilized at 5 rpm, the satellite moved in a 3 a.m. to 3p.m. sun-synchronous orbit. The spacecraft body was acylinder approximately 1.7 m x 1.25 m and consisted of twomajor modules: the observatory module that housed thescientific instruments, and the spacecraft bus. The spin axiswas oriented normal to the orbital plane. The command systemwas capable of executing commands in real time or fromstored program control. Power was supplied by a solar cellarray. The telemetry system was used either in a real-time orin a tape-recorder mode.
All instruments on-board the SME were turned off inDecember 1988 because of energy considerations.
SME
NSSDC ID: 1981-100A
Alternate Names
Solar MesosphereExplorer
Explorer 64
12887
Facts in Brief
Launch Date: 1981-10-06Launch Vehicle: DeltaLaunchSite: Vandenberg AFB,United StatesMass: 145.0 kg
Funding Agency
NASA-Office of SpaceScience Applications(United States)
Disciplines
Earth Science
Solar Physics
Space Physics
AdditionalInformation
Launch/Orbitalinformation for SME
Experiments on SME
Data collections from SME
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http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-100A[11/11/2010 23:04:40]
Personnel
Name Role Original Affiliation E-mail
Dr. Charles A.Barth
ProjectScientist
University of Colorado [email protected]
Mr. Marius B.Weinreb
ProgramManager
NASA Headquarters
Dr. Shelby G.Tilford
ProgramScientist
NASA Headquarters
Dr. George F.Esenwein, Jr.
ProgramManager
NASA Headquarters
Mr. John J.Paulson
ProjectManager
NASA Jet PropulsionLaboratory
Selected References
Barth, C. A., et al., Solar Mesosphere Explorer: Scientific objectives and results, Geophys. Res.Lett., 10, No. 4, 237-240, Apr. 1983.
+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-029A[11/11/2010 23:05:44]
Friday, 12 November 2010
Description
Soyuz 39 was a manned Soviet mission launched from theBaikonur cosmodrome and docked with the Salyut 6 spacestation. Its two man crew of of Vladimir Dzhanibekov (USSR)and Jugderdemidiyn Girragcha (Mongolia) was the eighthinternational crew in the Intercosmos program. It wasrecovered on March 30, 1981 at 11:42 GMT.
Soyuz 39
NSSDC ID: 1981-029A
Alternate Names
12366
Facts in Brief
Launch Date: 1981-03-22LaunchVehicle: Modified SS-6(Sapwood) with 2ndGeneration (Longer) UpperStageLaunch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.RMass: 6800.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Human Crew
AdditionalInformation
Launch/Orbitalinformation for Soyuz 39
Experiments on Soyuz 39
Data collections fromSoyuz 39
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
Soyuz 39
Launch, orbit and landing data Launch date: 22.03.1981 Launch time: 14:58 UT Launch site: Baikonur Launch pad: 31 Altitude: 195 - 261 km Inclination: 51,68° Landing date: 30.03.1981 Landing time: 11:40 UT Landing site: 170 km SE of Dzheskasgan
Crew
No. Surname Given name Job
1 Dzhanibekov Vladimir Aleksandrovich Commander
2 Gurragcha Zhugderdemidiyn "Gurr" Research Cosmonaut(Mongolia)
Flight Launch from Baikonur; landing 170 km southeast of Dzheskasgan; eighth Interkosmos-mission. Docking on Salyut 6 space station. The cosmonauts installed cosmic ray detectors in the work and transfer compartments. They also performed the Illyuminator ("viewing port") experiment, which studied the degradation of the station's viewports. Kovalyonok and Savinykh also used the Gologramma ("hologram") apparatus to image a viewing port damaged by micrometeoroids. They also collected samples of the station's air and microflora and removed the cosmic ray detectors for return to Earth. Experiments of Earth science were also performed, especially studies of Mongolia from space.
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-042A[11/11/2010 23:06:38]
Friday, 12 November 2010
Description
Soyuz 40 was a manned Soviet mission launched from theBaikonur cosmodrome and docked with the Salyut 6 spacestation. Its two man crew of Leonid Popov (USSR) andDumitru Prinariu (Romania) was the ninth international crew ofthe Intercosmos program. It was recovered on May 22, 1981 at13:58 GMT.
Soyuz 40
NSSDC ID: 1981-042A
Alternate Names
12454
Facts in Brief
Launch Date: 1981-05-14LaunchVehicle: Modified SS-6(Sapwood) with 2ndGeneration (Longer) UpperStageLaunch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.RMass: 6800.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Human Crew
AdditionalInformation
Launch/Orbitalinformation for Soyuz 40
Experiments on Soyuz 40
Data collections fromSoyuz 40
Questions or commentsabout this spacecraft canbe directed to: CoordinatedRequest and User SupportOffice.
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
Soyuz 40
Launch, orbit and landing data Launch date: 14.05.1981 Launch time: 18:16 UT Launch site: Baikonur Launch pad: 1 Altitude: 191 - 269 km Inclination: 51,62° Landing date: 22.05.1981 Landing time: 14:59 UT Landing site: 225 km SE of Dzheskasgan
Crew
No. Surname Given name Job
1 Popov Leonid Ivanovich Commander
2 Prunariu Dumitru Dorin Research Cosmonaut
Flight Launch from Baikonur; landing 225 km southeast of Dzheskasgan. Ninth Interkosmos-mission. Docking on Salyut 6 spacestation as final spacecraft. Scientific research and experiments including exploration of Earth magnetic field. Earth observations had to be delayed until the last day of this mission, when Salyut 6 at last passed over Romania in daylight. During this time the crew also tested the station's orientation system.
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-023A[11/11/2010 23:07:21]
Friday, 12 November 2010
Description
Soyuz T-4 was a manned Soviet mission launched from theBaikonur cosmodrome with cosmonauts Vladimir Kovalyonokand Viktor Savinykh on board to carry out repairs andpreventive maintenance aboard the Salyut 6 space station. Itwas recovered on June 10, 1981 at 12:38 GMT.
Soyuz T-4
NSSDC ID: 1981-023A
Alternate Names
12334
Facts in Brief
Launch Date: 1981-03-12LaunchVehicle: Modified SS-6(Sapwood) with 2ndGeneration (Longer) UpperStageLaunch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.RMass: 7000.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Human Crew
AdditionalInformation
Launch/Orbitalinformation for Soyuz T-4
Experiments on Soyuz T-4
Data collections fromSoyuz T-4
Questions or commentsabout this spacecraft canbe directed to: CoordinatedRequest and User SupportOffice.
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+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
Soyuz T-4
Launch, orbit and landing data Launch date: 12.03.1981 Launch time: 19:00 UT Launch site: Baikonur Launch pad: 1 Altitude: 245 - 315 km Inclination: 51,61° Landing date: 26.05.1981 Landing time: 12:37 UT Landing site: 125 km E of Dzheskasgan
Crew
No. Surname Given name Job
1 Kovalyonok Vladimir Vasiliyevich Commander
2 Savinykh Viktor Petrovich Flight Engineer
Flight Launch from Baikonur; landing 125 km east of Dzheskasgan. Docking on Salyut 6; fifth and final resident crew of the Salyut 6 spacestation. Visiting crews: Interkosmos-missions Soyuz 39 on 23.03.1981 and Soyuz 40 on 15.05.1981; resulting in common science research onboard the station. One of the first mission objectives of this crew was, to unload the earlier launched Progress 12-spacecraft. Meteorological studies from the Bermuda-Triangle were conducted too.
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=SPHNX-B[11/11/2010 23:08:12]
Friday, 12 November 2010
Description
The Sphinx satellites mission is to provide spaceflightexperiment data at or near geosynchronous spacecraftaltitudes to determine interaction between space plasma andhigh-voltage system components required for future spaceflightmissions. The Sphinx satellites will be spin-stabilized with spinaxis oriented towards the sun. As presently proposed, a singleauxillary spacecraft would accompany a primary (Shuttle)interim upper stage (IUS) launch and payload delivery system.As a primary Delta payload, the Sphinx would consist of a dualspacecraft mission. The spacecraft will be launched intoparking and transfer orbits to achieve a highly elliptical orbitwith apogee near-geosynchronous altitude.
Sphinx-B
NSSDC ID: SPHNX-B
Alternate Names
Sp Plasma hi-Volt Int Ex
Facts in Brief
Launch Date: 1981-11-01LaunchVehicle: UnknownLaunch Site: CapeCanaveral, United States
Funding Agency
NASA-Office of Spaceand TerrestrialApplications (UnitedStates)
Discipline
Engineering
AdditionalInformation
Launch/Orbitalinformation for Sphinx-B
Experiments on Sphinx-B
Data collections fromSphinx-B
Questions or commentsabout this spacecraft canbe directed to: CoordinatedRequest and User SupportOffice.
Personnel
Name Role Original Affiliation E-mail
Mr. R. R. Lovell Project Manager NASA Lewis Research Center
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NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=P80-2[11/11/2010 23:09:16]
Friday, 12 November 2010
Description
The space test program P80-2 spacecraft is an ascent Agena(similar to SEASAT) which is modified to carry orbitalexperiments on the forward structure. High electric powerrequirements are met by flexible roll-out solar array panelswhich extend from the Agena. The twilight sun-synchronousorbit allows deployment of the array perpendicular to theinsolation vector. Experiment data may be read out by groundstations or may be recorded for subsequent transmission tothe ground stations. The investigations will test a deep-space-viewing infrared telescope with active cryogenic refrigeration,and measure solar flare iostopic composition.
STP P80-2
NSSDC ID: P80-2
Alternate Names
P80-2
Space Test ProgramP80-2
Facts in Brief
Launch Date: 1981-01-01Launch Vehicle: AtlasFLaunchSite: Vandenberg AFB,United StatesMass: 2430.0 kg
Funding Agency
Department of Defense-Department of the AirForce (United States)
Disciplines
Astronomy
Solar Physics
AdditionalInformation
Launch/Orbitalinformation for STP P80-2
Experiments on STP P80-2
Data collections from STPP80-2
Questions or commentsabout this spacecraft canbe directed to: CoordinatedRequest and User SupportOffice.
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NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=P80-2[11/11/2010 23:09:16]
Personnel
Name Role Original Affiliation E-mail
Maj William J. Niemann Project Manager US Air Force Space Division
Dr. John R. Stevens Project Scientist Aerospace Corporation
+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-034A[11/11/2010 23:10:17]
Friday, 12 November 2010
Description
STS-1 was the first manned orbital test flight of the SpaceTransportation System with astronauts John Young andRobert Crippen on board to verify the combined performanceof the Space Shuttle vehicle. Mission duration was 54 hours 20minutes 53 seconds.
STS 1
NSSDC ID: 1981-034A
Alternate Names
12399
Facts in Brief
Launch Date: 1981-04-12LaunchVehicle: ShuttleLaunch Site: CapeCanaveral, United StatesMass: 4908.0 kg
Funding Agency
NASA-Office of SpaceFlight (United States)
Discipline
Human Crew
AdditionalInformation
Launch/Orbitalinformation for STS 1
Experiments on STS 1
Data collections from STS1
Questions or commentsabout this spacecraft canbe directed to: CoordinatedRequest and User SupportOffice.
Personnel
Name Role Original Affiliation E-mail
Mr. Richard E. Thompson Project Manager NASA Johnson Space Center
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STS-1(Columbia)
Insignia de la misión
Datos de la misión Misión STS-1 Transbordador Columbia Tripulación 2 Plataforma de lanzamiento 39-A Lanzamiento 12 de abril de 1981 6:00:03 a.m. CST (12:00:03 UTC) Aterrizaje 14 de abril de 1981 12:20:57 p.m. CST (18:20:57 UTC), Base de la Fuerza Aérea de Edwards, Pista 23 Duración2 dias 6:20:53 Número de órbitas 36 Tripulación
Los miembros de la tripulación John W. Young y Robert L. Crippen posan con el traje de eyección (EES) con un pequeño modelo del transbordador Espacial. La primera misión del Transbordador Espacial, la STS-1, fue lanzada el 12 de abril de 1981, y regresó el 14 de abril. Transbordador espacial Columbia orbitó la tierra 36 veces en su misión de 54 horas y media. Fue el primer vuelo espacial tripulado de los EE.UU desde el proyecto de prueba Apollo-Soyuz el 15 de julio de 1975.
Tripulación
•
John W. Young (5), Comandante • Robert Crippen (1), Piloto
(1) número de vuelos espaciales hechos por cada miembro de la tripulación, hasta la fecha inclusive esta misión.
El primer lanzamiento del transbordador espacial sucedió el 12 de abril de 1981, exactamente 20 años después del primer vuelo espacial triupulado, cuando el orbitador Columbia, con sus dos miembros de la triupulación, los astronautas John W. Young, comandante, y Robert L. Crippen, piloto, despegó de la
plataforma de lanzamiento A, Complejo 39, en el centro espacial John F. Kennedy — el primero de 24 lanzamientos desde la plataforma A. Fue exactamente a las 7 a.m. EST. Dos dias antes un intento de lanzamiento se aborto a causa de problemas de encendido en uno de los ordenadores de proposito general del Columbia.
No solo fue este el primer lanzamiento del transbordador espacial, sino que también marcó la primera vez que se usaron en lanzamientos triupulados los cohetes de combustible sólido en los EE.UU.. También fue el primer vehiculo espacial que los EE.UU. lanzaron sin un vuelo de prueba propulsado sin tripulación. El tranbordador de la misión STS-1, el Columbia, además tiene el récord del mayor tiempo empleado en la fábrica de procesamiento del transbordador (OPF) antes del lanzamiento — 610 dias, fue el tiempo necesitado para el reemplazo de muchos de sus losetas de protección térmica.
Los objetivos principales de la misión del vuelo inagural fueron verificar el sistema del transbordador en conjunto, conseguir un ascenso sin percances hasta la órbita y regresar a la tierra para aterrizar sin problemas. Todos los objetivos se cumplieron, y se comprobó la navegabilidad del transbordador como vehículo espacial.
La única carga que llevó en la misión fue un paquete de instrumentación de desarrollo del vuelo (DFI) que contenía sensores y dispositivos de medida para registrar el rendimiento del orbiter y las tensiones que ocurrieron durante el lanzamiento, asceso, vuelo orbital, desceso y aterrizaje.
En la órbita 36, después de 933.757 millas de vuelo durante 2 dias, 6 horas, 20 minutos y 32 segundos. Tubo lugar el aterrizaje en la pista 23 en la base de la Fuerza Aérea de Edwards, California el 14 de abril a las 10:21 a.m. PST.
El Columbia regresó al centro espacial John F. Kennedy desde California el 28 de abril sobre un 747, uno de los aviones portadores del transbordador.
Programa del transbordador espacial
El Transbordador espacial Discovery en la plataforma de lanzamiento
El transbordador espacial o lanzadera espacial (en inglés Space Shuttle) de la NASA, llamado oficialmente Space Transportation System (STS), traducido "Sistema de Transporte Espacial", es el único vehículo espacial utilizado actualmente para el transporte de astronautas por parte de Estados Unidos. En particular lo destacable de él es que es parcialmente reutilizable.
Desde el despegue de la primera misión del transbordador espacial (STS-1) se ha utilizado para el transporte de grandes cargas hacia varias órbitas, para el abastecimiento y colocación de módulos orbítales en la Estación Espacial Internacional (ISS) y para realizar misiones del mantenimiento (como por ejemplo en el Telescopio espacial Hubble). Visto de antemano, uno de sus aprovechamientos originales y que todavía no se ha aprovechado, es la posibilidad de traer de nuevo a la Tierra satélites en su bodega para ser reparados. Aunque desde la ISS en ella si se han traido grandes cargas, ya que las Soyuz no puede traerlas de regreso por tener una capacidad más limitada.
El vehículo está programado inicialmente para realizar aproximadamente 100 vuelos.
El programa del transbordador espacial comienza a finales de los años 60 y se convierte en prioridad principal de la NASA en los 70. En enero de 2004, la NASA anuncio que retirará la flota entera de transbordadores y los sustituirá en 2010. Después del desastre del Columbia en 2003, no hubo más vuelos. El regreso de los vuelos con la misión STS-114 fue programado inicialmente en julio de 2005, pero debido a problemas en un sensor del tanque externo se descartó. Después de más de dos años de suspensión, el 26 de julio de 2005 el Discovery reanudó las operaciones con la Estación Espacial Internacional (ISS) para la transferencia de material y abastecimiento. En la reentrada a la Tierra hubo problemas técnicos con el seguimiento de la nave a causa del mal tiempo sucedido el 9 de agosto.
Puesto que en una sola misión el orbitador no puede compaginar el transporte de módulos a la ISS y continuar el mantenimiento del telescopio espacial Hubble, y de previamente haber cancelado estas misiones, la NASA aunció que realizaria una misión, la cúal es la última que dará servicio al Hubble el próximo octubre de 2008 en la misión STS-125.
Según el discurso que sostuvo el presidente estadounidense George W. Bush el 14 de enero de 2004, el uso del transbordador espacial será concentrado totalmente en el ensamblaje de la ISS hasta 2010, año en el cual tendría que ser substituido por el vehículo Orión, todavía en fase de desarrollo.
Diseño
El Programa del transbordador espacial fue ideado principalmente como sucesor de las
misiones Apolo para dotar a la NASA de un programa espacial tripulado en la década de los 80.
La NASA quería abaratar los costos y necesitaba una nave multifuncional. Uno de sus usos sería traer los satélites que eran lanzados al espacio para su reparación en caso de algún fallo. Otra función sería que fuera reutilizable para evitar la pérdida de miles de millones de dólares en cohetes que se iban separando en fases menores y una vez desechados se quemaban durante la reentrada a la atmósfera. Por último se usaría como transporte a la estación espacial que tenía planeada construir la NASA.
Con todos estos principios durante la década de los 60, la NASA había delineado una serie de proyectos en papel sobre vehículos espaciales reusables para reemplazar los sistemas de uso único como el Proyecto Mercury, el Proyecto Gemini y el Programa Apollo. La Fuerza Aérea de los Estados Unidos
En la segunda mitad de la década de los 60, el esfuerzo para mejorar el Apollo se estaba diluyendo, y la NASA empezó a buscar el futuro del programa espacial. Su visión fue la de un programa ambicioso que contemplaba el desarrollo de una enorme estación espacial que se lanzara con grandes cohetes, y que fuera mantenida por un "transbordador espacial" reutilizable que pudiera dar servicio a una colonia lunar permanente y que eventualmente pudiera transportar personas a
(USAF) también tenía interés en sistemas más pequeños, con mayor capacidad de maniobrabilidad y estaba realizando su propio proyecto de avión espacial, llamado X-20 Dyna-Soar. Para poder elaborar un estado del arte en la materia, ambos equipos trabajaron juntos.
Marte.
Sin embargo, la realidad era otra, ya que el presupuesto de la NASA disminuyó rápidamente. En lugar de retroceder y reorganizar su futuro en función de su nueva situación económica, la agencia intentó salvar tanto como fuera posible de sus proyectos. Se descartó la misión a Marte, pero tanto la estación espacial como el transbordador todavía estaban en pie. Eventualmente solo se pudo salvar uno de ellos, que fue el transbordador por razones económicas y logísticas, ya que sin ese sistema no se podría construir una estación espacial.
A continuación se propusieron una cantidad de diseños, muchos de ellos complejos y diferentes entre ellos. Maxime Faget, diseñador de la cápsula del Mercury, entre otros, creó el "DC-3", un pequeño avión capaz de llevar una carga de 9.070 kg o menos, cuatro tripulantes, aunque con maniobrabilidad limitada. El DC-3 se constituyó en la plataforma básica con la cual se compararían los demás diseños.
Con la desesperación de ver su último proyecto salvado, la NASA pidió la bendición de la Fuerza Aérea de los Estados Unidos (USAF). La agencia hizo la solicitud de que los futuros lanzamientos de la USAF se hicieran con el transbordador en vez de los lanzadores descartables que se estaban usando, como el cohete Titan II. Como retribución, la USAF vería ahorros significativos en la construcción y actualización de sus lanzadores, puesto que el transbordador tendría capacidad más que suficiente para lograr los objetivos.
Sin mucho entusiasmo, la USAF asintió, no sin antes pedir un incremento significativo en la capacidad para permitirle lanzar sus satélites espías proyectados. Estos eran grandes, con un peso aproximado de 18.144 kg, y tendrían que ponerse en órbitas polares, lo cual necesita más energía que la que se requiere para poner un objeto en órbita baja (LEO). El vehículo también tendría que tener la habilidad de maniobrar hacia cualquier lado de su huella orbital para ajustarse a la deriva rotacional del punto de lanzamiento mientras estuviera en la órbita polar - por ejemplo, en una órbita de 90 minutos, el punto Vandenberg AFB en California, EE.UU. tendría una deriva de 1.600 km, mientras que en órbitas más alineadas con el ecuador, la deriva sería de menos de 400 km. Para lograr lo anterior, el vehículo debería tener alas más grandes y pesadas.
Con ello, el sencillo DC-3 quedaba fuera de la ecuación debido a su reducida capacidad de carga y habilidad de maniobra. De hecho, todos los diseños eran insuficientes. Todos los nuevos dibujos tendrían que incorporar un ala delta. Y ese no era el único inconveniente, con el incremento de la capacidad del vehículo, los propulsores también debían ser mucho más poderosos. De pronto, el sistema había crecido hasta ser más alto que el cohete Saturno V y sus costos y complejidad se salieron de todos los pronósticos.
Mientras todo esto sucedía, otras personas sugirieron un enfoque diferente: que la NASA utilizara el Saturno existente para lanzar la estación espacial, la cual sería mantenida por cápsulas Gemini modificadas que irían en cohetes Titan II-M, de la USAF. El costo sería probablemente menor, y alcanzaría el objetivo de la estación internacional más pronto.
La respuesta no se hizo esperar: un transbordador reutilizable pagaría con creces el costo de su desarrollo, si se comparaba con el gasto de lanzar cohetes de uso único. Otro factor en el análisis fue la inflación, que fue tan alta en la década de los 70 que cualquier reposición del costo del desarrollo tenía que ser rápida. Se necesitaba entonces una tasa de lanzamientos para hacer que el sistema fuera plausible desde el punto de vista económico. Estas condiciones no las cumplían ni la estación espacial, ni las cargas de la USAF. La recomendación fue, entonces, hacer los lanzamientos desde el transbordador, una vez construido. El costo de lanzar el transbordador tendría que ser menor que cualquier otro sistema, exceptuando los cohetes pequeños y los muy grandes.
Con el tema de la plausibilidad solucionado, la NASA se dedicó a obtener fondos para los cinco años que tardaría el desarrollo del proyecto, empresa que no resultó para nada fácil. La inflación y la Guerra de Vietnam amenazaban con dar al traste con el transbordador, pero era el único proyecto viable, y suspenderlo significaba que EE.UU. no tendría un programa espacial tripulado en la década de los 80. Sin embargo, los presupuestos debían ajustarse, lo cual llevó otra vez a la mesa de dibujo. Se abandonó el proyecto de cohete reutilizable en favor de un cohete sencillo que se desprendiera y fuera recuperado posteriormente. El combustible se sacó del orbitador a un tanque externo, lo cual permitió aumentar la capacidad de carga a costa de desechar el tanque.
El último escollo de diseño fue la naturaleza de los propulsores. Por lo menos cuatro soluciones se propusieron, y se optó finalmente por la que contemplaba dos cohetes sólidos (en vez de uno grande), debido a menores costos de diseño (aspecto que estuvo permanentemente presente en el diseño del transbordador).
Desarrollo
El desarrollo del transbordador se hizo oficial el
5 de enero de 1972, cuando el presidente Richard Nixon anunció que la NASA comenzaría a crear un sistema de transbordador reusable, de bajo coste. Debido a los topes de presupuesto, el proyecto ya estaba condenado a durar más de lo que se había anticipado originalmente. Sin embargo, el trabajo empezó rápidamente, y un par de años después ya había varios artículos de prueba.
De estos, el más notable era el primer Orbitador completo, que originalmente se conocería como "Constitution". Sin embargo, una campaña masiva de cartas de fanáticos de la serie Star Trek convenció a la Casa Blanca de rebautizar al orbitador como "Enterprise". Con bombo y platillos, el Enterprise hizo su
primer carreteo el 17 de septiembre de 1976 y empezó una serie de pruebas exitosas que fueron la primera validación real del diseño.
Lanzamiento del Columbia (1981)
El primer orbitador completamente funcional, el Columbia, fue construido en Palmdale, California, y enviado al Centro Espacial Kennedy el 25 de marzo de 1979. Dos tripulantes iban en el primer viaje del Columbia, el 12 de abril de 1981. En julio de 1982 el CEK vio llegar al Challenger. En Noviembre de 1983 llegó el Discovery, y el Atlantis en Abril de 1985. Con el tiempo las tripulaciones fueron creciendo: la primera tripulación de cinco astronautas fue en el STS-7 en 1983 y la de seis fue en el STS-9 a finales del mismo año. La primera tripulación de 7 personas fue en STS 41-C en 1984 y el récord de ocho fue en 1985 a bordo del STS 61-A.
Debido a las grandes tripulaciones, los astronautas fueron divididos en dos grupos: pilotos, responsables del vuelo y mantenimiento del orbitador; y los especialistas de misión, encargados de los experimentos y de la carga útil. Finalmente se creó otra categoría: los especialistas de carga, los cuales no tienen que hacer necesariamente un curso de astronauta. Éstos se ocupan de experimentos de abordo.
La segunda parte del proyecto, la llamada Estación Espacial Libertad, anunciada en 1984, se convirtió, con modificaciones y reducciones, en la Estación Espacial Internacional. En la mañana del 28 de junio de 1986 el Challenger explotó 73 segundos después del despegue (misión STS-51-L). El problema se debió a un escape en una junta de sellado de los cohetes auxiliares. La tripulación de siete personas perdió la vida. Para reemplazarlo se construyó el Endeavour, que llegó en Mayo de 1991.
En 1995 el transbordador espacial fue preparado para la concepción de la Estación Espacial Internacional, motivo por el cual realizó una serie de acoplamientos con los rusos en la estación Mir. Finalmente y debido a los retrasos por presupuesto de la agencia espacial rusa se dio comienzo a la construcción de la ISS en 1998.
Último despegue del Columbia
El 1 de febrero de 2003 otro trágico accidente sacudió a la familia de transbordadores espaciales de la NASA al desintegrarse el Columbia en los cielos durante su reentrada, cuando regresaba tras finalizar con éxito la misión STS-107.
La NASA suspendió todos los vuelos de transbordadores programados mientras investigaba lo sucedido. El resultado fue que el desastre del Columbia se produjo por un pedazo de espuma que
recubre el tanque externo que se desprendió y choco el ala del transbordador a unos 800 km/h, este golpeó y produjo un orificio que luego resultaría fatal ya que por este entraría el plasma producido por el rozamiento con la atmósfera lo que la fundió.
Los vuelos se reiniciaron con el despegue del Discovery dos años y medio después, el 26 de julio de 2005, para llevar a cabo la misión STS-114, esta se realizó sin haber solucionado por completo el problema del tanque externo, el Discovery regreso a casa el 9 de agosto de 2005 en la Base Edwards en California. La siguiente misión del Transbordador se realizó en julio de 2006 con el lanzamiento del Discovery. La misión comprendió un viaje a la Estación Espacial Internacional y pruebas de seguridad.
Conclusión
El transbordador ha requerido de importantes avances tecnológicos para su desarrollo, incluyendo miles de
losetas de protección térmica, capaces de resistir el calor de la reentrada en el curso de varias misiones, además de sofisticados motores que pudieran ser usados una y otra vez sin ser desechados. El orbitador con forma de avión tiene tres de estos motores principales, los cuales queman hidrógeno y oxígeno líquido que están almacenados en el tanque externo. Fijados al tanque externo se encuentran dos cohetes de combustible sólido ó aceleradores llamados SRB, en inglés Solid Rocket Boosters, los cuales proveen la mayor parte del empuje durante el despegue. Los “boosters” se apagan y son arrojados al océano para ser recuperados, rellenados y preparados para el próximo uso. Una vez que los cohetes de combustible
sólido han sido desechados, los tres motores principales del orbitador siguen quemando el combustible del tanque externo hasta aproximadamente los ocho minutos de vuelo.
El STS introdujo muchas herramientas que son utilizadas en el espacio: el sistema de manipulación remota, un brazo de 15,24 metros de longitud construido por la Agencia Espacial Canadiense, es capaz de mover grandes y pesados objetos desde y hacia la bahía de carga del transbordador la cual tiene unos 18,29 metros de largo. El módulo Spacelab construido por la Agencia Espacial Europea (ESA), provee un laboratorio presurizado y completamente equipado para que los científicos puedan realizar diversos experimentos, cubriendo un amplio espectro de la investigación: desde la astronomía, la creación de nuevos materiales, la observación de la Tierra, el estudio de fenómenos físicos y hasta la investigación biomédica. La Unidad de Vuelo Maniobrable (MMU) permite a los astronautas moverse libremente en el espacio sin estar conectado al Transbordador valiéndose de unos pequeños cohetes fijados a la estructura en forma de silla para el desplazamiento.
La mayoría de las misiones han sido científicas y de defensa. Entre los proyectos científicos más importantes se destaca la puesta en órbita del Telescopio Espacial Hubble, la nave espacial Galileo que realizó importantes descubrimientos, el Observatorio de Rayos Gamma y el transporte de módulos y abastecimiento para la construcción de la Estación Espacial Internacional (ISS).
Flota de transbordadores espaciales de la NASA [editar]
Los cinco transbordadores funcionales de la NASA durante algunos lanzamientos
Perdidos en accidentes:
Artículo principal: Transbordador espacial Challenger Artículo principal: Transbordador espacial Columbia
• Actualmente en servicio:
Artículo principal: Transbordador espacial Discovery Artículo principal: Transbordador espacial Atlantis Artículo principal: Transbordador espacial Endeavour
El Transbordador tiene dos fuentes de combustible: el Tanque Externo y dos Cohetes Aceleradores Sólidos, en inglés Solid Rocket Boosters (SRB). El orbitador también almacena combustibles hipergólicos que son usados durante la estadía en el espacio.
El impulso combinado es tal que en un lapso de 0 a 8,5 s el Transbordador alcanza una velocidad de 250 m/s. Esto equivale a unos 3 G, es decir, más de 3 veces la fuerza ejercida por la tierra.
Fuente de combustibles
El Tanque externo
Lancha a remolque trasladando el tanque externo a Cabo Cañaveral
El Tanque externo llega hasta el Edificio de Ensamblaje de Vehículo en una enorme barca. Una vez en esta instalación, es procesado y colocado en posición vertical para ser unido al orbitador.
El Tanque Externo es el elemento más grande y más pesado del transbordador espacial. Además de alimentar a los tres motores principales del Orbitador, el Tanque cumple la función de espina dorsal del Transbordador al absorber las cargas de empuje durante el lanzamiento. Es eyectado a los 10 s del apagado de los motores principales del transbordador, reentrando en la atmósfera terrestre e impactando sobre el océano índico o pacífico, en función del tipo de misión. No es reutilizable.
En las dos primeras misiones iba pintado de blanco pero a partir de la STS-3 dejó de pintarse para reducir peso. Desde entonces presenta ese color naranja tan característico.
Los Motores Principales
Motores principales del Columbia
Son tres, y proveen del empuje necesario para alcanzar la velocidad de escape. Los motores principales están ubicados en la parte inferior del orbitador y antes de ser instalados en el mismo han de haber pasado por una prueba de encendido en el Centro Espacial Dennis en Misisipi de donde son transportados en camión hasta el edificio de ensamblaje del vehículo.
Los motores miden unos 4,2 m de altura y cada uno pesa unas 2 t. La potencia que producen es tremenda: 12 millones de CV de potencia, lo necesario para proveer de energía a 10.000 hogares. El elemento principal de los motores es la turbobomba la cual se encarga de alimentar de propelente a la cámara de combustión. La potencia de la turbobomba también es descomunal, ya que con sólo el tamaño de un motor V-8 tiene la fuerza de 28 locomotoras, por lo que si llegara a explotar enviaría una columna de hidrógeno a 58 km a la redonda. Cuando se enciende, la turbobomba consume 1 t/s de combustible.
Los motores principales utilizan LOX y LH2 que se encienden en la cámara de combustión que no mide más de 25 cm de diámetro a una temperatura de 3.300 °C lo que le da una gran presión. Una vez que son liberados, los gases calientes son expulsados por la tobera. Después de la separación de los boosters, los motores principales siguen encendidos por varios minutos. Los motores principales son reutilizables para 55 despegues y operan con un rendimiento máximo de 104%
Cohetes Aceleradores Sólidos
Cohete acelerador sólido de la misión STS-114 recuperado y transportado a Cabo Cañaveral.
El transbordador espacial usa el cohete de propulsión sólida más grande del mundo. Cada cohete acelerador contiene 453.600 kg de propelente en la forma de una sustancia sólida de consistencia similar a la goma de borrar. El Cohete Acelerador Sólido (SRB) tiene cuatro secciones centrales que contienen el propelente. La parte superior tiene un hueco en
forma de estrella que se extiende hasta dos tercios hacia abajo hasta tomar la forma de un cilindro. Cuando entran en ignición todas las superficies expuestas reaccionan violentamente proveyendo el impulso necesario. Una vez que entran en ignición, no es posible su apagado. Debido a la forma de estrella del segmento superior, la eficiencia de impulso es mucho mayor que con una forma cilíndrica.
Después de proveer un empuje equivalente a un tercio del total, los SRBs se separan a los 2:12 min de vuelo. Caen en el océano Atlántico, con ayuda de unos paracaídas, de donde son rescatados y posteriormente reutilizados.
Propelentes
El combustible utilizado por el transbordador espacial proviene del Tanque Externo y de los cohetes aceleradores o también conocidos como Boosters. El propelente empleado en los boosters es
perclorato de amonio y tiene una consistencia sólida; respecto al Tanque Externo, aquí sucede lo contrario ya que está dividido en dos tanques el superior contiene oxígeno líquido (LOX) y el segundo tanque contiene hidrógeno líquido (LH2) los cuales se mezclan en la cámara de combustión de los motores principales del transbordador espacial proveyendo la combustión.
Una característica importante de los combustibles es su impulso específico, el cual es utilizado para medir la eficiencia de los propelentes de los cohetes en términos de segundos. Cuanto más alto es el número, más “caliente” es el propelente.
La NASA utiliza cuatro tipos de propelentes: petróleo, criogénicos, hipergólicos y sólidos.
El petróleo es en realidad un tipo de kerosén similar al quemado en las lámparas y estufas. Sin embargo, en este caso se trata de un tipo llamado RP-1 (Petróleo Refinado) que es quemado con oxígeno líquido (oxidante) para proveer de impulso. El RP-1 sólo se utiliza en los cohetes Delta, Atlas-Centauro y también fue utilizado en las primeras etapas del Saturn IB y el Saturn 5.
En el programa del Transbordador no se utiliza el petróleo, salvo para etapas de satélites. En el despegue, el transbordador espacial utiliza el tipo criogénico y sólido, mientras que en órbita hace uso de los tipos hipergólicos.
Criogénicos
Los motores
criogénicos se basan en la unión de oxígeno líquido (LOX), que es utilizado como oxidante, e hidrógeno líquido (LH2) que es el combustible. El LOX permanece en estado líquido a –183 °C y el LH2 a –253 °C.
En su estado gaseoso, el oxígeno y el hidrógeno tienen densidades tan bajas que serían necesarios enormes tanque para su almacenamiento, por ello deben ser enfriados y comprimidos para ser almacenados en los tanques de los cohetes. Debido a la continua tendencia de los criogénicos a volver a su estado natural, es decir, gaseoso, su uso es menos frecuente en los cohetes militares debido a que éstos deben permanecer en las bases de lanzamiento por largos períodos de tiempo.
A pesar de las dificultades que acarrean para su almacenamiento, la combinación LOX-LH2 tiene una gran eficiencia. El hidrógeno tiene una potencia un 40% mayor que otros combustibles y es muy liviano pesando cerca de 0,45 kg por cada 3,8 L. El oxígeno es mucho más pesado, con 4,5 kg por cada 3,8 litros.
Los motores de alta eficiencia a bordo del orbitador utilizan hidrógeno y oxígeno líquido logrando un impulso específico de 455 segundos, lo cual es un gran avance respecto a los motores F-1 del Saturno 5, que llegaban a 260 s. Las células de combustible a bordo del orbitador usan estos dos líquidos para producir energía eléctrica en un proceso conocido como electrólisis inversa. La quema del LOX con LH2 se produce sin producir gases tóxicos dejando sólo como subproducto vapor de agua.
Hipergólicos [editar
Los hipergólicos son combustibles y oxidantes que entran en ignición cuando entran en contacto, por lo que no necesitan de una fuente de ignición. Esta capacidad de encendido los hace especialmente útiles en sistemas de maniobramiento, tanto tripulados como no tripulados. Otra de sus ventajas es el almacenamiento, ya que no necesitan
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temperaturas extremamente bajas como los criogénicos.
El combustible es monometilhidracina (MMH) y el oxidante es tetróxido de nitrógeno (N2O4). La hidracina es un compuesto de nitrógeno e hidrógeno con un olor muy fuerte similar al amoníaco. El tetróxido de nitrógeno es de color rojizo y tiene un olor repugnante. Debido a que ambos son altamente tóxicos, su tratamiento se realiza bajo condiciones de seguridad extrema.
El orbitador usa hipergólicos para el Sistema de Maniobramiento Orbital (OMS) para la inserción en órbita, maniobras orbitales y salida de órbita. El sistema de control de reacción usa hipergólicos para el control de actitud.
La eficiencia de la combinación MMH/N2O4 en el orbitador es de 260 a 280 segundos en el SCR y 313 segundos en el OMS. La mayor eficiencia del OMS se explica por la mayor expansión de las toberas y las elevadas presiones en las cámaras de combustión.
Sólido [editar
Los propelentes sólidos son los más simples de todos. Su uso no requiere de turbobombas o complejos sistemas de alimentación de propelentes. Su ignición se produce con un largo chorro de llamas producido desde la punta del cohete lo cual produce el encendido inmediato. Los combustibles sólidos, compuestos por un
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metal y diferentes mezclas químicas son más estables y permiten un mejor almacenamiento. Por otra parte, la gran desventaja que presentan es que los propelentes sólidos una vez encendidos no pueden apagarse.
Los propelentes sólidos se usan en una gran variedad de naves y sistemas como el Módulo de Asistencia de Carga (PAM) y en la Etapa Superior Inercial (IUS) que proveen el impulso necesario para que satélites alcancen órbitas geosincrónicas o para entrar en órbitas planetarias. El IUS se utiliza en el transbordador espacial.
Un propelente sólido siempre posee su propia fuente de oxígeno. El oxidante del propelente sólido del transbordador espacial es perclorato de amonio, que constituye el 63,93% de la mezcla. El combustible es una forma de aluminio en polvo (16%) con un oxidante de hierro en polvo (0,07%) como catalizador. El fijador que mantiene a la mezcla unida es ácido acrilonitril polibutadieno (12,04%). Además, la mezcla contiene un agente de protección epoxy (1,96%). Tanto el fijador como el agente epoxy se queman junto con el resto del propelente, contribuyendo al empuje.
El impulso específico de los SRB del transbordador espacial es de 242 segundos a nivel del mar y 268,6 segundos en el vacío.
Instalaciones de la NASA para el programa del transbordador espacial
Despegue del transbordador espacial
El Centro Espacial Kennedy es el centro principal de la NASA para las pruebas, chequeos y lanzamientos del transbordador espacial y sus cargas. El centro también es uno de los sitios de aterrizaje del Transbordador.
Los Transbordadores despegan del Complejo de Lanzamiento 39 ubicado sobre Merrit Island, Florida, al norte de Cabo Cañaveral. Las instalaciones del complejo
39 han sufrido modificaciones desde la época de las misiones Apollo para poder adaptarse a la tecnología del Programa del transbordador espacial.
Instalación de aterrizaje del Transbordador [editar
La pista de aterrizaje para el transbordador espacial es una de las más grandes del mundo. La pista del Centro Espacial Kennedy está ubicada a unos tres kilómetros al noroeste del edificio de ensamblaje, en un alineamiento noroeste/sudeste. La pista de aterrizaje tiene el doble de longitud que las pistas de los aeropuertos comerciales. Mide aproximadamente unos 4.752 m de largo y 91,4 metros de ancho, y tiene 406 milímetros de espesor en el centro. En cada extremo hay un espacio de 305 metros para propósitos de seguridad. A cada lado de la pista corren unos pequeños surcos de 0,63
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cm de ancho y profundidad.
Debido a que el orbitador, una vez que ha reentrado en la atmósfera, carece de un sistema de propulsión propio, tiene que valerse de la suspensión aerodinámica provista por el aire. La velocidad de aterrizaje varía entre 343 y 364 kilómetros por hora.
Para lograr un aterrizaje perfecto, el orbitador necesita de ayuda de navegación, que se encuentra tanto en tierra como a bordo de la misma nave. El escáner de rayos microondas del sistema de aterrizaje sirve para el acercamiento final y dirige al orbitador a un punto determinado de la pista.
Aterrizaje del transbordador Atlantis
Los aterrizajes se realizan de noroeste a sudeste (Pista 15) o de sudeste a noreste (Pista 33). La pista no es perfectamente plana, ya que tiene una pendiente de 61 cm desde la línea central hasta el borde. Esta pendiente junto con los surcos constituyen un efectivo método de dispersión del agua. Los surcos además son de utilidad para la resistencia al deslizamiento superficial. Modificaciones posteriores de la pista de aterrizaje
aumentaron su longitud, por lo que actualmente mide unos 5.182 metros de largo.
Instalación de procesamiento del orbitador [editar
Horas después de haber aterrizado el orbitador es transportado hasta el edificio de procesamiento en el centro espacial. El edificio tiene tres bahías, cada una de 60 m de largo, 46 m de ancho y 29 m de alto, que ocupan un área de 2.694 m². La bahía inferior conecta a las bahías 1 y 2. Tiene 71 m de largo, 30 de ancho y cerca de 8 m de altura. La bahía 3 está ubicada al norte y al este de las dos primeras; tiene además una bahía inferior adyacente.
Otros anexos y estructuras proveen del espacio necesario para realizar el mantenimiento del orbitador. Cada bahía superior está acompañada de un brazo grúa de 27 t de peso con una altura aproximada de 20 m. Una serie de plataformas, un puente de acceso principal y dos puentes móviles motorizados proveen los accesos al orbitador. Las bahías superiores tienen un sistema de escape de emergencia en caso de que se produzca el escape de hipergólicos. La bahía inferior tiene equipos eléctricos, mecánicos una sala de comunicaciones, oficinas y salas de supervisión del control. Todas las bahías tienen sistemas de protección en caso de incendio.
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El control post-vuelo y mejoras, además de la instalación de cargas en posición horizontal, se realizan en este edificio. Los satélites colocados en posición vertical normalmente son instalados en la plataforma de lanzamiento.
Después del procesamiento, el orbitador es remolcado hasta el edificio de ensamblaje a través de la gran puerta al extremo norte de la bahía superior.
Instalación del sistema de protección térmica [editar
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Endeavour. Se puede apreciar el recubrimiento de losetas térmicas del transbordador.
Un Sistema de Protección Térmica, compuesto de una red de losetas, filtros y mantas de aislamiento, protegen el interior de cada orbitador del calor producido en el despegue y durante la reentrada, además de las bajas temperaturas del espacio. Estos materiales pueden resistir algún daño dentro del tiempo de vuelo y deben ser inspeccionados, reparados o algunas veces reemplazados para la próxima misión.
La reparación y la elaboración final de los materiales del sistema de protección térmica toma lugar en la instalación de dicho sistema, un edificio de 2 pisos con un área de 4.088 metros cuadrados. El edificio está ubicado cruzando la calle desde el complejo de procesamiento del orbitador.
Instalación de Logística [editar
El Complejo de Logística, con un área de 30.159 metros cuadrados está ubicado al sur del edificio de ensamblaje. Contiene cerca de 160.000 partes de repuestos del transbordador espacial y más de 500 trabajadores de la NASA y de empresas contratadas. Una de las características destacables de este edificio es la existencia del sistema de recuperación de partes, el cual automáticamente encuentra y retira partes específicas del Transbordador.
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Instalaciones de procesamiento de los Cohetes Aceleradores Sólidos [editar
Después de 2 minutos del lanzamiento, los SRB se separan del tanque externo gracias al encendido de retrocohetes y abren sus paracaídas para caer al norte del
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Océano Atlántico en donde son rescatados por barcos especiales que los transportan hasta la estación de la Fuerza Aérea de Cabo Cañaveral.
Instalación para el desarmado del Cohete Acelerador Sólido [editar
Corresponde al área en y alrededor del hangar AF que junto al edificio forman la instalación del desarmado del Cohete Acelerador. Elevadores especiales detrás del hangar AF elevan a los SRB del agua. Allí pasan por un lavado inicial y cada cohete es separado en sus cuatro secciones y los ensamblajes superiores e inferiores. Los segmentos principales son devueltos al complejo de lanzamiento en el Centro Espacial Kennedy a bordo de vehículos sobre rieles para ser enviados al manufacturero y la recarga del propelente.
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Instalación para el reacondicionamiento y ensamblaje del Cohete Acelerador Sólido [editar
El reacondicionamiento y la instalación de las secciones superior e inferior se lleva a cabo en este edificio ubicado al sur del edificio de ensamblaje. Este complejo está formado por cinco edificios: construcción, ingeniería, servicio, prueba de la sección inferior o prueba de fuego y la instalación de enfriamiento. El edificio de tres pisos para la construcción cuenta con sistema de control automático, una grúa de 24 X 61 metros en la bahía superior y tres robots grúas, estando estos últimos entre los más grandes del mundo.
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Instalación para el proceso de rotación y salida [editar
Ubicada al norte del edificio de ensamblaje, esta instalación recibe los segmentos de los SRB cargados con propelente a través de un sistema férreo desde el manufacturero. El complejo incluye un edificio de procesamiento y dos edificios de despacho. La inspección, rotación y el armado de la parte inferior del booster ocurre en el edificio de procesamiento. Los otros dos edificios de despacho sirven para el almacenamiento de los segmentos cargados con propelentes y permanecen allí hasta ser transportados al edificio de ensamblaje para ser integrados a las otras partes del booster listas para el siguiente vuelo.
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Instalación para el reacondicionamiento del paracaídas [editar
Después de que los dos boosters caigan en el Océano Atlántico, dos embarcaciones los recuperan y también retiran los paracaídas que son enrollados en enormes rodillos los cuales son enviados a esta instalación. Una vez allí, los paracaídas son lavados, secados y almacenados en tanques para un uso futuro.
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Edificio de ensamblaje de vehículos [editarArtículo principal:
] Edificio de ensamblaje de vehículos
Edificio de ensamblaje de vehículos
Aquí, los boosters son unidos al tanque externo y al orbitador para ser transportados hasta la plataforma de lanzamiento.
Ubicado en el centro del complejo de lanzamiento 39, el edificio de ensamblaje del vehículo es uno de los más grandes del mundo cubriendo un área de 3,24 ha y con un volumen de aproximadamente 3.884.460 m³. El edificio
tiene 160 m de altura, 218 m de largo y 158 m de ancho.
La estructura puede resistir vientos de 125 km/h y está reforzada con vigas de acero de 406 mm de diámetro hasta una profundidad de 49 m.
La bahía superior tiene una altura de 160 m y la bahía inferior, 64 m. Al este se encuentran las bahías superiores 1 y 3 donde se unen los componentes del transbordador espacial en posición vertical en la plataforma lanzadora. Al oeste están las bahías 2 y 4 donde se chequea el tanque externo y es también donde se realiza el almacenamiento.
Este edificio tiene más de 70 dispositivos de elevación incluyendo dos grúas de 227 t.
Una vez que el ensamblaje del transbordador espacial está completo, se abren las enormes puertas del edificio para permitir la entrada del transportador oruga que se desplaza debajo de la Plataforma Lanzadora Móvil y los lleva –con el Transbordador ensamblado- hasta el lugar de lanzamiento.
Centro de control de lanzamiento [editar]
Centro de control de lanzamiento
Es un edificio de cuatro pisos conectado a la parte oriental del edificio de ensamblaje a través de un elevado puente cerrado. El centro de control cuenta con dos salas de operaciones y otras dos de apoyo cada una equipada con el sistema de procesamiento de lanzamiento –un sistema automático de operación computarizada– el cual monitorea y controla en ensamblaje del transbordador espacial, el control y las operaciones de lanzamiento.
La cuenta regresiva para el transbordador espacial toma cerca de 43 h gracias al sistema de procesamiento de lanzamiento, de otra manera, llevaría más de 80 h, como en las misiones Apollo.
Por otro lado, el uso del sistema de procesamiento de lanzamiento requiere la presencia de 225 a 230 personas en la sala de lanzamiento, a diferencia de las misiones Apollo que requerían de cerca de 450 personas.
Una vez que los cohetes de propulsión sólida se encienden en el despegue, el control pasa automáticamente al centro de control de misión en el Centro Espacial Johnson en Houston, Texas.
Detalle (sin inscripciones)
Equipo transportable e instalaciones
Plataforma Lanzadora Móvil
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El transbordador espacial Discovery sobre la Plataforma de Lanzadora Móvil
Es una estructura de acero de dos pisos que provee de una base de lanzamiento transportable para el transbordador espacial. El cuerpo principal de la plataforma tiene 7,6 m de altura, 49 m de largo y 41 m de ancho. La plataforma descansa sobre seis pedestales de 6,7 m de altura.
Sin ser cargada, una plataforma pesa cerca de 3.730 t. Con un Transbordador sin combustible, pesa unas 5.000 t.
El cuerpo principal de la plataforma tiene tres salidas: una para los gases expelidos por los cohetes de propulsión sólida y otra ubicada en el medio, para los tres motores principales. Sobre la estructura hay dos dispositivos de tamaño
considerable a cada lado del hueco de escape de los motores principales. Estos dispositivos denominados "mástiles de servicio trasero" proveen de varias conexiones umbilicales al orbitador incluyendo una línea de oxígeno líquido a través de uno y una línea de hidrógeno líquido a través del otro. Estos combustibles criogénicos son alimentados al tanque externo a través de estas conexiones desde la plataforma. En el momento de lanzamiento estos umbilicales son retraídos hasta los mástiles donde son protegidos de las llamas de los motores por una cubierta giratoria.
Cada mástil tiene 4,5 m de largo, 2,7 m de ancho y se elevan a unos 9,4 m de altura sobre el piso de la plataforma.
Otros umbilicales transportan helio y nitrógeno, además de energía eléctrica y enlaces de comunicación. Ocho pernos, cuatro en cada base del los SRB sostienen al transbordador espacial sobre la plataforma lanzadora. Estos pernos encajan con otros pernos opuestos sobre los dos huecos de escape de los SRB. La nave se desconecta de la plataforma mediante pirotecnia que rompe los enlaces de estos pernos.
Cada plataforma lanzadora contiene dos niveles internos que proveen de equipos eléctricos, de prueba y de carga de propelentes.
Transportador Oruga [editar
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Transportador oruga
Estos vehículos especiales transportan al transbordador espacial montado sobre la plataforma lanzadora desde el edificio de ensamblaje hasta la zona de lanzamiento. Se trata de dos orugas (nombre dado a los vehículo cuya tracción se da sobre correas móviles como la de los tanques de guerra) que tienen 6,1 metros de altura, 40 m de largo y 34,7 m de ancho. Cada una pesa unos 2.700 t sin carga. Un vehículo de este tipo tiene seis orugas con 57 secciones cada una. Cada conjunto de ruedas
contenido en la oruga pesa unos 907 kg.
La velocidad máxima de la oruga con el transbordador a bordo es de 1,6 km/h, mientras que sin carga tiene una velocidad máxima de 3,2 km/h.
La oruga tiene un sistema de nivelación para contrarrestar los 5 grados de inclinación hasta el sitio de lanzamiento y posee además, un sistema de rayos láser que le permite ubicarse en una posición precisa.
Cada oruga es impulsada por dos motores diésel de 2.750 CV. Los motores controlan unos generadores de 1.000 kW que proveen de energía eléctrica a los 16 motores de tracción.
Camino del transportador oruga [editar
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Camino del Transportador Oruga
Una carretera de 39,6 m de ancho es usada por el transportador oruga en un trayecto desde el edificio de ensamblaje hasta la plataforma de lanzamiento que están separados por unos 4,8 km.
El camino consiste en dos carriles de 12 metros separados por una franja central de 15 m. Para soportar el peso de la carga total (unas 7.700 t) el camino está compuesto por cuatro capas. La parte superior es una
capa de grava de río de 20,3 cm en las curvas y 10,2 cm en los trayectos rectos. Las otras capas —en sentido descendiente— son: 1,2 m de roca comprimida, 76 cm de un relleno selecto y 30 cm de un relleno compacto.
La distancia desde el edificio de ensamblaje a la Plataforma 39A es unos 5,5 km y a la Plataforma 39B, unos 6,8 km.
Contenedor de carga [editar
Este contenedor instala las cargas útiles en sentido vertical y opera en varias instalaciones. En la instalación de procesamiento del orbitador sirve para las cargas de posición horizontal.
Cada contenedor está sellado herméticamente y puede llevar cargas de hasta 4,5 m de diámetro y 18,3 m de longitud. El peso máximo que permite es de aproximadamente 22,68 t.
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Transportador del contenedor de carga [editar
Es un camión de 48 ruedas que puede transportar el contenedor ya sea en posición vertical u horizontal. El Transportador tiene unos 19,8 m de largo y 7 m de ancho, con una plataforma que puede ser elevada o bajada desde 1,5 m hasta 2,1 m.
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Cada rueda tiene un eje independiente lo que le permite desplazarse libremente en cualquier dirección. Un motor diésel impulsa al transportador en las actividades exteriores, pero cuando está dentro de una instalación funciona con un motor eléctrico.
Cuando está completamente cargado tiene una velocidad máxima de 8 km/h, pero también se puede desplazar a velocidades del orden de 0,636 centímetros por segundo (o lo que es lo mismo: 0,022 km/h) para las cargas que necesitan un movimiento de precisión.
Plataformas de lanzamiento 39A y 39B
Las plataformas A y B del Complejo de Lanzamiento tienen un tamaño casi
octogonal. Cada una cubre un área de 0,65 km². La parte central de la Plataforma A está situada a unos 14,6 metros sobre el nivel del mar, y la Plataforma B a 16,8 m. Antes del retorno a vuelos en 1988 después de la trágica misión del Challenger, el Complejo sufrió 105 modificaciones. Las modificaciones fueron realizadas para mejorar la inspección de los sistemas.
La parte superior de cada Plataforma mide 119 X 99 m. Las dos estructuras principales de cada plataforma de lanzamiento son la Estructura de Servicio Fija y la Estructura de Servicio Giratoria.
Estructura de servicio fija
Está ubicada al norte de cada plataforma de lanzamiento. Es una estructura abierta de cerca de 12,2 metros cuadrados. Una grúa en la parte superior provee de acceso para las operaciones pro-lanzamiento. La estructura tiene 12 pisos de trabajo a intervalos de 6,1 m cada uno. La altura de la estructura es de 75 m. Mientras que la altura hasta la grúa superior es de 81 m por encima de todo se encuentra el
pararrayos: una estructura cilíndrica de fibra de vidrio con una longitud de 24 m. Con el pararrayos, la estructura tiene una altura de 106 m.
La estructura fija tiene tres brazos de servicio:
Ingenieros en la escotilla del orbitador
• Brazo de acceso al orbitador: este brazo se extiende para permitir el acceso de personal especializado al compartimiento de la tripulación en el orbitador. La parte extrema de este brazo comprende una sección llamada “cuarto blanco”. Este pequeño cuarto permite el acceso de un
máximo de seis personas y permite el acceso a la escotilla a través de la cual los astronautas se ubican en sus posiciones.
El brazo de acceso permanece en posición extendida hasta los 7 min 24 s previos al lanzamiento para proveer una salida de emergencia a la tripulación. Mide 19,8 m de largo, 1,5 m de ancho y 2,4 m de altura. Este brazo está fijado a la Estructura de Servicio Fija a un nivel de 44,8 m sobre la superficie.
En caso de emergencia, el brazo puede ser extendido mecánica o manualmente en cerca de 15 s.
Conexión umbilical al tanque externo
• Brazo de línea de acceso para la ventilación de hidrógeno del tanque externo: este brazo permite la unión de las líneas umbilicales del tanque externo con las instalaciones de la plataforma además de proveer acceso para el trabajo en el área del tanque. Este brazo se retrae varias horas antes del lanzamiento dejando los cables umbilicales unidos al tanque los cuales son cortados en el instante en el que los boosters se encienden. Los cables vuelven a la torre de la estructura donde son protegidos de la llamas de los motores gracias a una cortina de agua.
El brazo de línea de acceso para la ventilación de hidrógeno del tanque externo mide 48 m de largo y está unido a la estructura de servicio fija a un nivel de 51 m.
• Brazo de ventilación de oxígeno gaseoso del tanque externo: este brazo se extiende hasta la parte superior del tanque exterior donde baja un cobertor o capullo en la punta del tanque. El capullo contiene nitrógeno gaseoso calentado que corre a través de esta cubierta para evitar que los vapores de la abertura de ventilación se condensen formando hielo que puede desprenderse y por lo tanto dañar a la nave durante el despegue. El sistema del brazo de ventilación tiene 24,4 m de largo, 1,5 m de ancho y 2,4 m de alto. Este brazo está adherido a la Estructura de Servicio Fija entre los niveles correspondientes a los 63 y 69 m.
El cobertor es retirado de la abertura de ventilación a los 2 min y 30 s previos al lanzamiento y el brazo es retraído hasta la estructura de la torre y puede ser vuelto a su posición extendida si se detiene la cuenta regresiva.
Estructura de servicio giratoria
Estructura de servicio giratoria
Provee de protección al transbordador y acceso a la bahía de carga para la instalación y servicio de cargas en la plataforma. La estructura gira de un tercio de círculo a 120° para que las puertas de la sala de cambio de carga se acoplen a la bahía de carga del orbitador. El cuerpo de
esta estructura empieza a un nivel de 18 metros y se extiende hasta un nivel de 57,6 m proveyendo el acceso a cinco niveles. La estructura giratoria, se desplaza en 8 carros sobre rieles. El cuerpo giratorio mide 31 m de largo, 15 m de ancho y 40 m de alto.
El propósito principal de la estructura giratoria es la de instalar cargas en la bahía del orbitador. Solamente se encarga de la instalación de cargas livianas, para los casos más pesados como compartimentos, laboratorios, etc. se realizan en la instalación de procesamiento del orbitador.
Cuarto de intercambio de carga
El cuarto de intercambio de carga se encuentra en la parte central de esta estructura y constituye un cuarto sellado que recibe las cargas del contenedor de carga. La limpieza de estas cargas se mantiene gracias a cobertores que impiden que los dispositivos sean expuestos al aire libre.
Unidad umbilical central del orbitador [editar
Esta unidad permite el acceso y trabajo en el área central del orbitador. La misma se extiende desde la Estructura de Servicio Giratoria desde los niveles de 48 a 53,6 m. Esta unidad tiene 6,7 m de largo, 4 m de ancho y 6 m de alto. Una plataforma de extensión y un mecanismo manual de desplazamiento horizontal permite el acceso a
la puerta del cuerpo central del orbitador.
]
Esta unidad sirve para la alimentación de hidrógeno y oxígeno líquido de las células de combustible, y gases como el nitrógeno y helio.
Sistema umbilical de hipergólicos [editar
El sistema transporta el combustible hipergólico y el oxidante, además de líneas de servicio para el hidrógeno y helio desde la estructura de servicio fija hasta el transbordador espacial. Es sistema también permite la rápida conexión de las líneas y su desconexión del vehículo. Seis unidades umbilicales son operadas manualmente en la plataforma. Estas unidades están ubicadas a cada lado de la parte inferior del orbitador. Estas unidades sirven al sistema de maniobramiento orbital y el sistema de reacción de control, además de la bahía de carga y el área del morro del orbitador.
]
Sistema de protección climática [editar
Este sistema ubicado en las plataformas A y B sirve para proteger al orbitador de las inclemencias del tiempo como
]
granizo, chaparrones y escombros transportados por el viento que podrían dañar al sistema de protección térmica y las mantas de aislamiento.
La estructura giratoria al cerrarse cubre la mayor parte del orbitador, el sistema de protección climática cubre los espacios libres.
Puertas corredizas que se desplazan entre la panza del orbitador y el tanque externo proveen protección para la parte inferior del orbitador. Estas puertas que miden 16 m de largo y 11,6 m de alto pesan unos 20.866 kg. Las puertas están conectadas a la estructura giratoria y la Estructura de Servicio Fija. Las puertas se mueven en lados opuestos sobre rieles.
Un sello inflable que protege la parte superior del orbitador se extiende desde el cuarto de intercambio de carga, formando un semicírculo que cubre 90 grados de arco entre el vehículo y el tanque externo. Una serie de 20 o más puertas metálicas dobles de 24,4 por 1,2 metros se extienden desde el cuarto de intercambio de carga en la Estructura de Servicio Giratoria para cubrir las áreas laterales entre el tanque externo y el orbitador.
Sistema deflector de llamas [editar
El sistema sirve para proteger del fuego del lanzamiento al vehículo y las estructuras de la plataforma.
Un deflector de llamas es una estructura en forma de V invertida que sirve para desviar las llamas del lanzamiento y dirigirlas a través de las aberturas de la plataforma lanzadora hasta las fosas ubicadas debajo. Las paredes de esta estructura se curvan a medida que se apartan de la zona central y alcanzan una pendiente casi horizontal.
Esta estructura deflectora mide 149 m de largo, 18 de ancho y 12 m de alto. El sistema deflector que utiliza el transbordador espacial es doble ya que un lado de la V invertida recibe las llamas de los motores principales, mientras que el lado opuesto recibe las llamas de los cohetes de propulsión sólida.
]
Los deflectores del orbitador y los cohetes aceleradores están construidos con acero y cubiertos con un material de ablación con un espesor de 127 mm. Cada deflector pesa más de 453,6 t.
Además de los deflectores fijos, también hay otros dos que se desplazan sobre la fosa para proveer de protección adicional de las llamas de los cohetes aceleradores.
Sistema de escape [editar
Provee una ruta de escape para los astronautas del orbitador y los técnicos en la Estructura de Servicio Fija hasta los últimos 30 segundos de la cuenta regresiva. El sistema está compuesto por siete cables que se extienden desde la Estructura de Servicio Fija al nivel del Brazo de Acceso al Orbitador cuyos trayectos terminan en el suelo.
]
En caso de emergencia los astronautas se introducen en una estructura en forma de balde hecho de acero y rodeado de una red. Cada balde puede servir para tres personas. El cable se extiende unos 366 m hasta un
búnker de refugio ubicado al oeste de la Estructura de Servicio Fija. El descenso dura unos 35 s y el frenado se lleva a cabo gracias a una red y a un sistema de frenado por cadenas.
Pararrayos
Imagen de un rayo durante el Huracán Ernesto antes del despegue de la STS-115
El pararrayos se extiende desde la parte superior de la estructura fija y provee la protección al vehículo y las estructuras de la plataforma. El pararrayos está conectado a un cable que se fija a un ancla a 335 m al sur de la estructura y otro cable se extiende la misma distancia hacia el norte. El rayo que golpee la punta corre por este cable hasta el suelo, de esta manera, el mástil del pararrayos funciona como un aislador eléctrico manteniendo el cable aislado de la estructura fija. El mástil junto a la estructura acompañante eleva al cable unos 30,5 m sobre la estructura.
Sistema de agua para supresión sonora [editar
]
En el Centro Espacial Kennedy, el agua es vertida en la plataforma de lanzamiento al comienzo de un test de supresión de sonido.
Este sistema instalado en las plataformas protege al orbitador y sus cargas del daño producido por la energía acústica y las llamaradas expulsadas por los cohetes sólidos en la fosa deflectora y la plataforma lanzadora.
El sistema de supresión sonora incluye un tanque de agua con una capacidad de 1.135.620 L. El tanque tiene 88 m de alto y está ubicado a una posición elevada adyacente a cada plataforma. El agua es liberada justo antes de la ignición de los motores del transbordador espacial y fluye a través de cañerías de un diámetro de 2,1 m.
El trayecto lo realiza en cerca de 20 s. El agua es expulsada a través de 16 boquillas encima de los deflectores de llamas y a través de unas aberturas en el hueco de la plataforma lanzadora para los motores principales del orbitador, comenzando a T menos 6,6 s (T corresponde a tiempo (time, en inglés) que define el preciso momento del lanzamiento).
Para el momento en que los SRB entren en ignición, un torrente de agua cubre la plataforma lanzadora gracias a seis enormes toberas o rociadores fijados en su superficie. Los rociadores miden 3,7 m de altura. Los dos centrales miden 107 cm de diámetro; los restantes cuatro tienen 76 cm de diámetro.
El punto de mayor flujo de agua se da a los 9 segundos después del despegue con 3.406.860 L desde todas las fuentes.
Los niveles acústicos llegan a su máximo cuando el transbordador está a unos 300 m sobre la plataforma de lanzamiento. El peligro disminuye a una altitud de 305 m.
Sistema de supresión de la tensión del Cohete Acelerador Sólido [editar
Este sistema pertenece al sistema de supresión sonora. En este caso, se encarga de disminuir los efectos de las presiones reflejadas que ocurren cuando los cohetes aceleradores entran en ignición. Sin el sistema de supresión la presión ejercería mucha tensión en las alas y las superficies de control de orbitador.
]
Hay dos componentes principales para este sistema de supresión de energía acústica:
• Un sistema de rociadores de agua que provee un colchón de agua el cual es dirigido a la fosa de llamas directamente debajo de cada booster.
• Una serie de bolsas de aguas distribuidas alrededor de los huecos de llamas proveen de una masa de agua que facilita la absorción del pulso de presión reflejado.
Usados juntos, esta barrera de agua impide el paso de las ondas de presión de los boosters, disminuyendo su intensidad. En caso de una misión abortada, un sistema de inundación post-apagado se encargaría de enfriar la parte inferior del orbitador. También controla la quema del gas de hidrógeno residual después de que los motores hayan sido apagados con el vehículo en la plataforma. Hay 22 bocas de agua alrededor del hueco de escape para los motores principales dentro de la plataforma lanzadora. El agua es alimentada por una línea de abastecimiento con un diámetro de 15 cm, logrando que el agua fluya a 9.463,5 L/min.
Sistema de eliminación de hidrógeno del motor principal [editar
Los vapores de hidrógeno que se producen durante el comienzo de la secuencia de ignición son expelidos en las toberas de los motores justo antes de la ignición. Como resultado se obtiene una atmósfera rica en hidrógeno dentro de las toberas. Para evitar daños a los motores, seis preiniciadores de remoción están instalados en el mástil trasero. Justo antes de la ignición de los motores principales estos preiniciadores son activados y producen la ignición de cualquier remanente de hidrógeno en el área debajo de las toberas. Este proceso evita una brusca combustión en el encendido de los motores principales.
]
Instalaciones de almacenamiento de propelentes [editar
Estas instalaciones están ubicadas en las dos plataformas de lanzamiento. Un tanque de 3.406.860 L situado en el extremo noroeste de cada plataforma almacena el oxígeno líquido (LOX) que es usado como el oxidante de los motores principales del orbitador.
]
En realidad estos tanques son enormes botellas al vacío. Éstas mantienen al LOX a temperaturas de –183°C. Dos bombas que abastece 4.540 L oxidante/min (cada una) transfieren el LOX desde el tanque de almacenamiento hasta el tanque externo del orbitador.
Botellas al vacío similares con una capacidad de 3.217.590 L y ubicadas en el extremo noreste de las plataformas, almacenan el hidrógeno para los tres motores principales del orbitador. En este caso, no se necesitan bombas para mover el LH2 hasta el tanque externo durante las operaciones de abastecimiento, ya que primero un poco de hidrógeno se evaporiza y esta acción crea un presión de gas en la parte superior del tanque que mueve al liviano combustible a través de las líneas de transferencia.
Las líneas de transferencia llevan a los propelentes súper enfriados hasta la plataforma lanzadora y alimentan al tanque externo a través de los mástiles traseros.
Los propelentes hipergólicos usados por los motores de maniobramiento orbital y los cohetes de control de actitud también están almacenados en las plataformas, en áreas bien separadas. Una instalación ubicada en el extremo sudeste de cada plataforma contiene el combustible monometil hidracina. Una instalación en el extremo sudoeste almacena el oxidante, tetróxido de nitrógeno. Estos propelentes son almacenados por líneas de transferencia hasta la estructura fija y continúan hasta el sistema umbilical de hipergólicos de la estructura giratoria, con sus tres pares de líneas umbilicales conectadas al orbitador.
Interfase de la plataforma de lanzamiento y el sistema de procesamiento del lanzamiento [editar
Los elementos ubicados en la Sala de Conexión Terminal de la plataforma proveen los enlaces vitales entre el sistema de procesamiento de lanzamiento en el centro de control de lanzamiento, el equipo de apoyo terrestre, y los dispositivos de vuelo del transbordador. Esta sala reside debajo de la elevada posición de la plataforma.
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NASA - NSSDC - Spacecraft - Details
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Friday, 12 November 2010
Description
The second flight of the Space Shuttle (STS-2) carried the firstscientific payload OSTA-1 (Office of Space and TerrestrialApplication 1). The instruments from the OSTA-1 payload weredesigned to perform remote sensing of the earth's atmosphere,oceans, and land resources. During its time in orbit, the Shuttleassumed an earth-viewing orientation, thus accommodatingthe experiments of the OSTA-1 payload. In this attitude, calledZ-axis local vertical (ZLV), the Shuttle's payload bay faces theearth on a line perpendicular to the earth's surface. The OSTA-1 payload consisted of (1) a shuttle imaging radar-A (SIR-A),(2) a shuttle multispectral infrared radiometer (SMIRR), (3) afeature identification and location experiment (FILE), (4) ameasurement of air pollution from satellites (MAPS), (5) anocean color experiment (OCE), (6) a night/day optical survey oflightning (NOSL), and (7) a helfex bioengineering test (HBT).The first five instruments were located in the payload bay. Apallet, supplied by the European Space Agency, made theinterface between the payload bay and these five experiments.The NOSL and HBT instruments were located in the crewcompartment. Due to the loss of one of three fuel cells, theSTS-2 mission was shortened from the planned 124-h to a 54-h minimum mission. The OSTA-1 payload was activatedapproximately 4.5 h after launch. The earth-viewing time wasreduced from the planned 88 h to 36 h. The STS-2 missionsuccessfully demonstrated the capability of the Space Shuttleto conduct scientific research. For more detailed descriptionsof the OSTA-1 payload, see "OSTA-1 Experiments," JSC17059, NASA-JSC, and Science, v. 218, n. 4576, pp. 993-1033, 1982.
STS 2/OSTA 1
NSSDC ID: 1981-111A
Alternate Names
Shuttle OFT 2
OSTA 1/STS 2
12953
Facts in Brief
Launch Date: 1981-11-12LaunchVehicle: ShuttleLaunch Site: CapeCanaveral, United StatesMass: 2542.0 kg
Funding Agencies
NASA-Office of SpaceFlight (United States)
NASA-Office of SpaceScience Applications(United States)
Disciplines
Earth Science
Human Crew
Life Science
AdditionalInformation
Launch/Orbitalinformation for STS2/OSTA 1
Experiments on STS2/OSTA 1
Data collections from STS2/OSTA 1
Questions or commentsabout this spacecraft canbe directed to: Coordinated
NSSDC MasterCatalog Search
Spacecraft
Experiments
Data Collections
Personnel
Publications
Maps
New/Updated Data
Lunar/Planetary Events
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-111A[11/11/2010 23:11:35]
Request and User SupportOffice.
Personnel
Name Role Original Affiliation E-mail
Dr. Mark Settle Program Scientist NASA Headquarters
Dr. Glynn S. Lunney Project Manager NASA Johnson Space Center
Mr. Louis J. Demas Program Manager NASA Headquarters
+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-100B[11/11/2010 23:12:55]
Friday, 12 November 2010
Description
The experiments selected to be part of the UOSAT payloadhad several objectives which included the following: to providethe educational community with an operational scientificsatellite which could be utilized with a minimal ground station;to provide the scientific community with a new source of datato aid in the understanding of the electro-magnetic propertiesof the near earth environment; and to provide the amateurradio community with a full complement of instruments for thestudy and monitoring of radio propagation conditions from thehigh frequency to microwave. In order to meet these objectivesthe following instruments comprised the UOSAT payload: atriaxial fluxgate magnetometer with a resolution of plus orminus 2 nT and maximum vector sample rate of 6.25 per s;two charged particle counters with threshold energies of 20and 60 keV; four phase-referenced high-frequency beacons at7, 14, 21, and 28 MHz; two microwave beacons at 2.4 and10.47 GHz; and a CCD earth-imaging camera with 2 kmresolution, and spectral response of 0.4 -1.0 micrometers. OneVHF and one UHF telemetry channel provided data instandard FSK ASCII at a variety of baud rates, as well asMorse code and synthesized voice formats.
UOSAT 1
NSSDC ID: 1981-100B
Alternate Names
OSCAR 9
12888
Facts in Brief
Launch Date: 1981-10-06Launch Vehicle: Delta2310LaunchSite: Vandenberg AFB,United StatesMass: 54.0 kg
Funding Agencies
Radio Amateur SatelliteCorporation (UnitedStates)
University of Surrey(United Kingdom)
Disciplines
Communications
Engineering
Earth Science
Space Physics
AdditionalInformation
Launch/Orbitalinformation for UOSAT 1
Experiments on UOSAT 1
Data collections fromUOSAT 1
Questions or commentsabout this spacecraft canbe directed to: CoordinatedRequest and User Support
NSSDC MasterCatalog Search
Spacecraft
Experiments
Data Collections
Personnel
Publications
Maps
New/Updated Data
Lunar/Planetary Events
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-100B[11/11/2010 23:12:55]
Office.
Personnel
Name Role Original Affiliation E-mail
Dr. M. N. Sweeting ProjectManager
University of Surrey
Mr. Richard L.Daniels
ProgramManager
NASA Headquarters
Dr. Ronald A.Parise
ProjectScientist
AMSAT Corporation [email protected]
Dr. J. A. King ProgramScientist
AMSAT Corporation
+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-106A[11/11/2010 23:14:36]
Friday, 12 November 2010
Description
Venera 13 and 14 were identical spacecraft built to takeadvantage of the 1981 Venus launch opportunity and launched5 days apart. The Venera 13 mission consisted of a bus (81-106A) and an attached descent craft (81-106D). After launchand a four month cruise to Venus, the descent vehicleseparated and plunged into the Venus atmosphere on 1 March1982. As it flew by Venus the bus acted as a data relay for thebrief life of the descent vehicle, and then continued on into aheliocentric orbit. The bus was equipped with instrumentationincluding a gamma-ray spectrometer, retarding potential traps,UV grating monochromator, electron and protonspectrometers, gamma-ray burst detectors, solar wind plasmadetectors, and two-frequency transmitters which mademeasurements before, during, and after the Venus flyby.
Venera 13
NSSDC ID: 1981-106A
Alternate Names
Venera 13 Flight Platform
12927
Facts in Brief
Launch Date: 1981-10-30Launch Vehicle: ProtonBooster Plus Upper Stageand Escape StagesLaunch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.R
Funding Agency
Unknown (U.S.S.R)
Discipline
Planetary Science
AdditionalInformation
Launch/Orbitalinformation for Venera 13
Experiments on Venera 13
Data collections fromVenera 13
Questions or commentsabout this spacecraft canbe directed to: Dr. David R.Williams.
Personnel
Name Role Original Affiliation E-mail
Mr. Artem Ivankov General Contact Lavochkin Association [email protected]
NSSDC MasterCatalog Search
Spacecraft
Experiments
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Personnel
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Venera 13
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-106A[11/11/2010 23:14:36]
Selected References
Harvey, B., The new Russian space programme from competition to collaboration, John Wiley &Sons, Chichester, England, 1996.
Venera 13 Orbiter
Venera 13 Descent Craft/LanderVenera 14 Orbiter
Venus Home PageVenera Home PageVenera lander images of the surface of Venus - and other Venus images
+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-106D[11/11/2010 23:16:52]
Friday, 12 November 2010
Description
Venera 13 and 14 were identical spacecraft built to takeadvantage of the 1981 Venus launch opportunity and launched5 days apart. The Venera 13 mission consisted of a bus (81-106A) and an attached descent craft (81-106D). The Venera13 descent craft/lander was a hermetically sealed pressurevessel, which contained most of the instrumentation andelectronics, mounted on a ring-shaped landing platform andtopped by an antenna. The design was similar to the earlierVenera 9-12 landers. It carried instruments to take chemicaland isotopic measurements, monitor the spectrum of scatteredsunlight, and record electric discharges during its descentphase through the Venusian atmosphere. The spacecraftutilized a camera system, an X-ray fluorescence spectrometer,a screw drill and surface sampler, a dynamic penetrometer,and a seismometer to conduct investigations on the surface.
After launch and a four month cruise to Venus, the descentvehicle separated from the bus and plunged into the Venusatmosphere on 1 March 1982. After entering the atmosphere aparachute was deployed. At an altitude of 47 km the parachutewas released and simple airbraking was used the rest of theway to the surface. Venera 13 landed about 950 km northeastof Venera 14 at 7 deg 30 min S, 303 E, just east of the easternextension of an elevated region known as Phoebe Regio. Thearea was composed of bedrock outcrops surrounded by dark,fine-grained soil. After landing an imaging panorama wasstarted and a mechanical drilling arm reached to the surfaceand obtained a sample, which was deposited in a hermeticallysealed chamber, maintained at 30 degrees C and a pressureof about .05 atmospheres. The composition of the sampledetermined by the X-ray flourescence spectrometer put it in theclass of weakly differentiated melanocratic alkaline gabbroids.The lander survived for 127 minutes (the planned design lifewas 32 minutes) in an environment with a temperature of 457degrees C and a pressure of 84 Earth atmospheres. Thedescent vehicle transmitted data to the bus, which acted as adata relay as it flew by Venus.
Venera 13 Descent Craft
NSSDC ID: 1981-106D
Alternate Names
Venera 13 Lander
Facts in Brief
Launch Date: 1981-10-30Launch Vehicle: ProtonBooster Plus Upper Stageand Escape StagesLaunch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.RMass: 760.0 kg
Funding Agency
Soviet Academy ofSciences (U.S.S.R)
Discipline
Planetary Science
AdditionalInformation
Launch/Orbitalinformation for Venera 13Descent Craft
Experiments on Venera 13Descent Craft
Data collections fromVenera 13 Descent Craft
Questions or commentsabout this spacecraft canbe directed to: Dr. David R.Williams.
Personnel
Name Role Original Affiliation E-mail
Mr. Artem Ivankov General Contact Lavochkin Association [email protected]
Selected References
Harvey, B., The new Russian space programme from competition to collaboration, John Wiley &Sons, Chichester, England, 1996.
NSSDC MasterCatalog Search
Spacecraft
Experiments
Data Collections
Personnel
Publications
Maps
New/Updated Data
Lunar/Planetary Events
Venera 13 Descent Craft
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-106D[11/11/2010 23:16:52]
Surkov, Yu. A., et al., New data on the composition, structure, and properties of Venus rockobtained by Venera 13 and Venera 14, J. Geophys. Res., 89, 8393-8402, Feb. 1984.
Venera 13 BusVenera 14 Descent Craft/Lander
Venus Home PageVenera Home PageVenera lander images of the surface of Venus - and other Venus images
+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
Venera 13
Venera 13 and 14 were identical spacecraft built to take advantage of the 1981 Venus launch opportunity and launched 5 days apart. The Venera 13 mission consisted of a bus (81-106A) and an attached descent craft (81-106D). The Venera 13 descent craft/lander was a hermetically sealed pressure vessel, which contained most of the instrumentation and electronics, mounted on a ring-shaped landing platform and topped by an antenna. The design was similar to the earlier Venera 9-12 landers. It carried instruments to take chemical and isotopic measurements, monitor the spectrum of scattered sunlight, and record electric discharges during its descent phase through the Venusian atmosphere. The spacecraft utilized a camera system, an X-ray fluorescence spectrometer, a screw drill and surface sampler, a dynamic penetrometer, and a seismometer to conduct investigations on the surface.
After launch and a four month cruise to Venus, the descent vehicle separated from the bus and plunged into the Venus atmosphere on 1 March 1982. After entering the atmosphere a parachute was deployed. At an altitude of 47 km the parachute was released and simple airbraking was used the rest of the way to the surface. Venera 13 landed about 950 km northeast of Venera 14 at 7 deg 30 min S, 303 E, just east of the eastern extension of an elevated region known as Phoebe Regio. The area was composed of bedrock outcrops surrounded by dark, fine-grained soil. After landing an imaging panorama was started and a mechanical drilling arm reached to the surface and obtained a sample, which was deposited in a hermetically sealed chamber, maintained at 30 degrees C and a pressure of about .05 atmospheres. The composition of the sample determined by the X-ray flourescence spectrometer put it in the class of weakly differentiated melanocratic alkaline gabbroids. The lander survived for 127 minutes (the planned design life was 32 minutes) in an environment with a temperature of 457 degrees C and a pressure of 84 Earth atmospheres. The descent vehicle transmitted data to the bus, which acted as a data relay as it flew by Venus.
Alternate Names
• Venera 13 Lander
Facts in Brief
Launch Date: 1981-10-30
Launch Vehicle: Proton Booster Plus Upper
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-110A[11/11/2010 23:19:15]
Friday, 12 November 2010
Description
Venera 13 and 14 were identical spacecraft built to takeadvantage of the 1981 Venus launch opportunity and launched5 days apart. The Venera 14 mission consisted of a bus (81-110A) and an attached descent craft (81-110D). After launchand a four month cruise to Venus, the descent vehicleseparated and plunged into the Venus atmosphere on 5 March1982. As it flew by Venus the bus acted as a data relay for thebrief life of the descent vehicle, and then continued on into aheliocentric orbit. The bus was equipped with instrumentationincluding a gamma-ray spectrometer, retarding potential traps,UV grating monochromator, electron and protonspectrometers, gamma-ray burst detectors, solar wind plasmadetectors, and two-frequency transmitters which mademeasurements before, during, and after the Venus flyby.
Venera 14
NSSDC ID: 1981-110A
Alternate Names
Venera 14 Flight Platform
12939
Facts in Brief
Launch Date: 1981-11-04Launch Vehicle: ProtonBooster Plus Upper Stageand Escape StagesLaunch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.R
Funding Agency
Unknown (U.S.S.R)
Discipline
Planetary Science
AdditionalInformation
Launch/Orbitalinformation for Venera 14
Experiments on Venera 14
Data collections fromVenera 14
Questions or commentsabout this spacecraft canbe directed to: Dr. David R.Williams.
Personnel
Name Role Original Affiliation E-mail
Mr. Artem Ivankov General Contact Lavochkin Association [email protected]
NSSDC MasterCatalog Search
Spacecraft
Experiments
Data Collections
Personnel
Publications
Maps
New/Updated Data
Lunar/Planetary Events
Venera 14
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-110A[11/11/2010 23:19:15]
Selected References
Harvey, B., The new Russian space programme from competition to collaboration, John Wiley &Sons, Chichester, England, 1996.
Venera 14 Orbiter
Venera 14 Descent Craft/LanderVenera 13 Orbiter
Venus Home PageVenera Home PageVenera lander images of the surface of Venus - and other Venus images
+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-110D[11/11/2010 23:20:51]
Friday, 12 November 2010
Description
Venera 13 and 14 were identical spacecraft built to takeadvantage of the 1981 Venus launch opportunity and launched5 days apart. The Venera 14 mission consisted of a bus (81-110A) and an attached descent craft (81-110D). The Venera14 descent craft/lander was a hermetically sealed pressurevessel, which contained most of the instrumentation andelectronics, mounted on a ring-shaped landing platform andtopped by an antenna. The design was similar to the earlierVenera 9-12 landers. It carried instruments to take chemicaland isotopic measurements, monitor the spectrum of scatteredsunlight, and record electric discharges during its descentphase through the Venusian atmosphere. The spacecraftutilized a camera system, an X-ray fluorescence spectrometer,a screw drill and surface sampler, a dynamic penetrometer,and a seismometer to conduct investigations on the surface.
After launch and a four month cruise to Venus, the descentvehicle separated from the bus and plunged into the Venusatmosphere on 5 March 1982. After entering the atmosphere aparachute was deployed. At an altitude of about 50 km theparachute was released and simple airbraking was used therest of the way to the surface. Venera 14 landed about 950 kmsouthwest of Venera 13 near the eastern flank of PhoebeRegio at 13 deg 15 min S by 310 E on a basaltic plain. Afterlanding an imaging panorama was started and a mechanicaldrilling arm reached to the surface and obtained a sample,which was deposited in a hermetically sealed chamber,maintained at 30 degrees C and a pressure of about .05atmospheres. The composition of the sample was determinedby the X-ray flourescence spectrometer, showing it to besimilar to oceanic tholeiitic basalts. The lander survived for 57minutes (the planned design life was 32 minutes) in anenvironment with a temperature of 465 degrees C and apressure of 94 Earth atmospheres. The descent vehicletransmitted data to the bus, which acted as a data relay as itflew by Venus.
Venera 14 Descent Craft
NSSDC ID: 1981-110D
Alternate Names
Venera 14 Lander
Facts in Brief
Launch Date: 1981-11-04Launch Vehicle: ProtonBooster Plus Upper Stageand Escape StagesLaunch Site: Tyuratam(Baikonur Cosmodrome),U.S.S.RMass: 760.0 kg
Funding Agency
Soviet Academy ofSciences (U.S.S.R)
Discipline
Planetary Science
AdditionalInformation
Launch/Orbitalinformation for Venera 14Descent Craft
Experiments on Venera 14Descent Craft
Data collections fromVenera 14 Descent Craft
Questions or commentsabout this spacecraft canbe directed to: Dr. David R.Williams.
Personnel
Name Role Original Affiliation E-mail
NSSDC MasterCatalog Search
Spacecraft
Experiments
Data Collections
Personnel
Publications
Maps
New/Updated Data
Lunar/Planetary Events
Venera 14 Descent Craft
NASA - NSSDC - Spacecraft - Details
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1981-110D[11/11/2010 23:20:51]
Mr. Artem Ivankov General Contact Lavochkin Association [email protected]
Selected References
Harvey, B., The new Russian space programme from competition to collaboration, John Wiley &Sons, Chichester, England, 1996.
Surkov, Yu. A., et al., New data on the composition, structure, and properties of Venus rockobtained by Venera 13 and Venera 14, J. Geophys. Res., 89, 8393-8402, Feb. 1984.
Venera 14 BusVenera 13 Descent Craft/Lander
Venus Home PageVenera Home PageVenera lander images of the surface of Venus - and other Venus images
+ Privacy Policy and Important Notices NASA Official: Dr. Ed GrayzeckCurator: E. Bell, IIVersion 4.0.14, 08 October 2010
Venera 14
Venera 13 and 14 were identical spacecraft built to take advantage of the 1981 Venus launch opportunity and launched 5 days apart. The Venera 14 mission consisted of a bus (81-110A) and an attached descent craft (81-110D). The Venera 14 descent craft/lander was a hermetically sealed pressure vessel, which contained most of the instrumentation and electronics, mounted on a ring-shaped landing platform and topped by an antenna. The design was similar to the earlier Venera 9-12 landers. It carried instruments to take chemical and isotopic measurements, monitor the spectrum of scattered sunlight, and record electric discharges during its descent phase through the Venusian atmosphere. The spacecraft utilized a camera system, an X-ray fluorescence spectrometer, a screw drill and surface sampler, a dynamic penetrometer, and a seismometer to conduct investigations on the surface.
After launch and a four month cruise to Venus, the descent vehicle separated from the bus and plunged into the Venus atmosphere on 5 March 1982. After entering the atmosphere a parachute was deployed. At an altitude of about 50 km the parachute was released and simple airbraking was used the rest of the way to the surface. Venera 14 landed about 950 km southwest of Venera 13 near the eastern flank of Phoebe Regio at 13 deg 15 min S by 310 E on a basaltic plain. After landing an imaging panorama was started and a mechanical drilling arm reached to the surface and obtained a sample, which was deposited in a hermetically sealed chamber, maintained at 30 degrees C and a pressure of about .05 atmospheres. The composition of the sample was determined by the X-ray flourescence spectrometer, showing it to be similar to oceanic tholeiitic basalts. The lander survived for 57 minutes (the planned design life was 32 minutes) in an environment with a temperature of 465 degrees C and a pressure of 94 Earth atmospheres. The descent vehicle transmitted data to the bus, which acted as a data relay as it flew by Venus.
Alternate Names
• Venera 14 Lander
Facts in Brief
Launch Date: 1981-11-04 Launch Vehicle: Proton Booster Plus Upper Stage and Escape Stages Launch Site: Tyuratam (Baikonur Cosmodrome), U.S.S.R Mass: 760.0 kg