Cronología de Lanzamientos Espaciales

Año 1992

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

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Publications There were 140 spacecraft returned.

Maps Spacecraft Name NSSDC ID Launch Date New/Updated Data Arabsat 1C 1992-010B 1992-02-25

Lunar/Planetary Events Atlas 1 / STS 45 ATLAS1 1992-03-23 AUSSAT B1 1992-054A 1992-08-12 AUSSAT B2 1992-090A 1992-12-20 Bion 10 1992-095A 1992-12-28 CANEX-2 CANEX-2 1992-10-14 Cosmos 2175 1992-001A 1992-01-20 Cosmos 2176 1992-003A 1992-01-23 Cosmos 2177 1992-005A 1992-01-28 Cosmos 2178 1992-005B 1992-01-28 Cosmos 2179 1992-005C 1992-01-28 Cosmos 2180 1992-008A 1992-02-16 Cosmos 2181 1992-012A 1992-03-08 Cosmos 2182 1992-016A 1992-03-31 Cosmos 2183 1992-018A 1992-04-07 Cosmos 2184 1992-020A 1992-04-14 Cosmos 2185 1992-025A 1992-04-28 Cosmos 2186 1992-029A 1992-05-27 Cosmos 2187 1992-030A 1992-06-02 Cosmos 2188 1992-030B 1992-06-02 Cosmos 2189 1992-030C 1992-06-02 Cosmos 2190 1992-030D 1992-06-02 Cosmos 2191 1992-030E 1992-06-02 Cosmos 2192 1992-030F 1992-06-02 Cosmos 2193 1992-030G 1992-06-02 Cosmos 2194 1992-030H 1992-06-02 Cosmos 2195 1992-036A 1992-06-30 Cosmos 2196 1992-040A 1992-07-07 Cosmos 2197 1992-042A 1992-07-12 Cosmos 2198 1992-042B 1992-07-12 Cosmos 2199 1992-042C 1992-07-12 Cosmos 2200 1992-042D 1992-07-12 Cosmos 2201 1992-042E 1992-07-12 Cosmos 2202 1992-042F 1992-07-12 Cosmos 2203 1992-045A 1992-07-23 Cosmos 2204 1992-047A 1992-07-29

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Cosmos 2205 1992-047B 1992-07-29 Cosmos 2206 1992-047C 1992-07-29 Cosmos 2207 1992-048A 1992-07-29 Cosmos 2208 1992-053A 1992-08-11 Cosmos 2209 1992-059A 1992-09-09 Cosmos 2210 1992-062A 1992-09-21 Cosmos 2211 1992-068A 1992-10-19 Cosmos 2212 1992-068B 1992-10-19 Cosmos 2213 1992-068C 1992-10-19 Cosmos 2214 1992-068D 1992-10-19 Cosmos 2215 1992-068E 1992-10-19 Cosmos 2216 1992-068F 1992-10-19 Cosmos 2217 1992-069A 1992-10-20 Cosmos 2218 1992-073A 1992-10-28 Cosmos 2219 1992-076A 1992-11-16 Cosmos 2220 1992-077A 1992-11-19 Cosmos 2221 1992-080A 1992-11-23 Cosmos 2222 1992-081A 1992-11-24 Cosmos 2223 1992-087A 1992-12-08 Cosmos 2224 1992-088A 1992-12-16 Cosmos 2225 1992-091A 1992-12-21 Cosmos 2226 1992-092A 1992-12-21 Cosmos 2227 1992-093A 1992-12-24 Cosmos 2228 1992-094A 1992-12-24 CTA 1992-070C 1992-10-21 DFS Kopernikus 3 1992-066A 1992-10-11 DoD-1 STSDOD1 1992-12-01 DSCS III-08 1992-006A 1992-02-09 DSCS III-09 1992-037A 1992-07-01 Ekran 20 1992-074A 1992-10-29 EURECA 1 1992-049B 1992-08-01 EUTELSAT-II F4 1992-041B 1992-07-08 EUVE 1992-031A 1992-06-06 Foton 8 1992-065A 1992-10-07 Freja 1992-064A 1992-10-05 FSW-1 4 1992-064B 1992-10-05 Galaxy 5 1992-013A 1992-03-13 Galaxy 7 1992-072A 1992-10-27 Geotail 1992-044A 1992-07-23 Gorizont 25 1992-017A 1992-04-01 Gorizont 26 1992-043A 1992-07-13 Gorizont 27 1992-082A 1992-11-26 Hispasat 1A 1992-060A 1992-09-09 IML 1 IMGLAB1 1992-01-21 Inmarsat 2-F4 1992-021B 1992-04-14 INSAT 2A 1992-041A 1992-07-08 INTELSAT K 1992-032A 1992-06-09 Japanese Earth Resource Satellite 1 1992-007A 1992-02-10 KH 12-1 1992-083A 1992-11-27

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KITSAT-A 1992-052B 1992-08-09 LAGEOS II 1992-070B 1992-10-21 Mars Observer 1992-063A 1992-09-24 Molniya 1-83 1992-011A 1992-03-03 Molniya 1-84 1992-050A 1992-08-05 Molniya 3-42 1992-067A 1992-10-13 Molniya 3-43 1992-085A 1992-12-01 MSTI 1 1992-078A 1992-11-20 Navstar 2A-03 1992-009A 1992-02-22 Navstar 2A-04 1992-019A 1992-04-09 Navstar 2A-05 1992-039A 1992-07-06 Navstar 2A-06 1992-058A 1992-09-08 Navstar 2A-07 1992-079A 1992-11-21 Navstar 2A-08 1992-089A 1992-12-17 Palapa B-4 1992-027A 1992-05-13 Pion 5 1992-056C 1992-08-18 Pion 6 1992-056D 1992-08-18 PRC 35 1992-051A 1992-08-08 Progress M-11 1992-004A 1992-01-24 Progress M-12 1992-022A 1992-04-18 Progress M-13 1992-035A 1992-06-29 Progress M-14 1992-055A 1992-08-14 Progress M-15 1992-071A 1992-10-26 Resurs 500 1992-075A 1992-11-14 Resurs-F14 1992-024A 1992-04-28 Resurs-F15 1992-033A 1992-06-22 Resurs-F16 1992-056A 1992-08-18 S 80/T 1992-052C 1992-08-09 SAMPEX 1992-038A 1992-07-02 SATCOM C3 1992-060B 1992-09-09 SATCOM C4 1992-057A 1992-08-30 SHEAL-A OSS-2 1992-09-02 Soyuz TM-14 1992-014A 1992-03-16 Soyuz TM-15 1992-046A 1992-07-26 Spacelab-J SPLABJ 1992-09-11 Spartan-B SPATN-B 1992-07-08 SROSS 3 1992-028A 1992-05-19 SSBUV04 SSBUV04 1992-03-23 STS 42/IML 1 1992-002A 1992-01-21 STS 45 1992-015A 1992-03-23 STS 46 1992-049A 1992-07-30 STS 47 1992-061A 1992-09-11 STS 49 1992-026A 1992-05-06 STS 50/USML 1 1992-034A 1992-06-24 STS 52/USMP 1 1992-070A 1992-10-21 STS 53 1992-086A 1992-12-01 Superbird A-1 1992-084A 1992-11-30 Superbird B1 1992-010A 1992-02-25 TELECOM 2B 1992-021A 1992-04-14

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Topex/Poseidon 1992-052A 1992-08-09 TSS-1 TSS-1 1992-06-25 UMSP-1 USMP-1 1992-10-21 USA 81 1992-023A 1992-04-24 USA 89 1992-086B 1992-12-01 USML 1 USMLAB1 1992-06-24

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Wednesday, 20 April 2011

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Personnel Arabsat 1C

Publications NSSDC ID: 1992-010B Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Arabsat-1C was a Saudi Arabian communications satellite 21894 launched using the same Ariane-44L vehicle that launched Superbird B1 from the Kourou Space Center in French Guiana. Facts in Brief

Launch Date: 1992-02- 26 Launch Vehicle: Ariane 44L Launch Site: Kourou, French Guiana Mass: 1310.0 kg

Funding Agency

Arabsat Satellite Communications (International)

Discipline

Communications

Additional Information

Launch/Orbital information for Arabsat 1C

Experiments on Arabsat 1C

Data collections from Arabsat 1C

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

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Personnel Atlas 1 / STS 45

Publications NSSDC ID: ATLAS1 Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Telemetry and raw data are received by the ATLAS PIs. STS 45 / Atlas 1 Science data sets are produced by individual PIs. The EOSDIS STS/Atlas 1 DAAC at NASA/GSFC has had several meetings with ATLAS Project management and has met with the PIs at workshops to discuss archiving data from the solar and atmospheric ATLAS Facts in Brief experiments. The ATLAS Project is coordinating with the ATLAS PIs on an archival plan. Launch Date: 1992-03- 24 Launch Vehicle: Shuttle Launch Site: Cape Canaveral, United States Mass: 93007.0 kg

Funding Agency

NASA-Office of Space Science Applications (United States)

Disciplines

Astronomy Earth Science Solar Physics Space Physics

Additional Information

Launch/Orbital information for Atlas 1 / STS 45 PDMP information for Atlas 1 / STS 45 Telecommunications information for Atlas 1 / STS 45

Experiments on Atlas 1 / STS 45

Data collections from Atlas 1 / STS 45

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

Personnel

Name Role Original Affiliation E-mail Dr. Jack A. Program NASA Goddard Space Kaye Scientist Flight Center Dr. Earl J. Program NASA Headquarters Montoya Manager Dr. Marsha R. Mission NASA Marshall Space Torr Scientist Flight Center Mr. Anthony M Mission NASA Marshall Space [email protected] O'Neil Manager Flight Center

Selected References

Torr, M. R., and K. D. Sullivan, Atlas-1 Shuttle mission, EOS, 73, No. 10, Mar. 1992.

Shea, C., and T. McMahan, Atlas 1: Encountering planet earth, NASA-MSFC, Payload Projects Office, Huntsville, Alabama, 1992.

Atmospheric Laboratory for Applications and Science mission 1, NASA-MSFC, TM-4101, edited by P. D. Craven and M. R. Torr, Huntsville, Alabama, 1988.

Mission operation report, Atmospheric Laboratory for Applications and Science 1, NASA-OSSA, S-420-45-92-01, Flight Systems Division, Washington, D.C., 1992.

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Personnel AUSSAT B1

Publications NSSDC ID: 1992-054A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events AUSSAT B-1 (also known as OPTUS B-1) was an Australian OPTUS B1 communications spacecraft launched from Xichang site by a 22087 Long March 2-E rocket. It was placed in a geostationary orbit at 160 deg E. Facts in Brief

Launch Date: 1992-08- 13 Launch Vehicle: Long March 2E Launch Site: Xichang, Australia Mass: 1600.0 kg

Funding Agency

AUSSAT Proprietary Ltd. (Australia)

Discipline

Communications

Additional Information

Launch/Orbital information for AUSSAT B1 Telecommunications information for AUSSAT B1

Experiments on AUSSAT B1

Data collections from AUSSAT B1

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

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Personnel AUSSAT B2

Publications NSSDC ID: 1992-090A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events AUSSAT B-2, also known as Optus B-2, was an Australian OPTUS B2 geostationary communications spacecraft launched by a Long 22278 March booster from the Xichang center in the People's Republic of China. Tracking stations had been unable to receive any signals from the spacecraft, at least for several Facts in Brief days after its launch, because the launch rocket exploded 45 seconds after launch. Launch Date: 1992-12- 21 Launch Vehicle: Long March 2E Launch Site: Xichang, Peoples Republic of China Mass: 3000.0 kg

Funding Agency

AUSSAT Proprietary Ltd. (Australia)

Discipline

Communications

Additional Information

Launch/Orbital information for AUSSAT B2

Experiments on AUSSAT B2

Data collections from AUSSAT B2

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

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Personnel Bion 10

Publications NSSDC ID: 1992-095A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Bion 10 (Cosmos 2229), a C.I.S. spacecraft, was launched by Cosmos 2229 a Soyuz rocket from the Plesetsk cosmodrome. It carried two Biocosmos 10 monkeys and several insects, amphibians, plants, and cell cultures. Participating scientists were from nine countries and 22300 ESA. Facts in Brief The spacecraft was based on the Zenit reconnaissance satellite and launches began in 1973 with primary emphasis on Launch Date: 1992-12- the problems of radiation effects on human beings. Launches 29 in the program included Cosmos 110, 605, 670, 782, plus Launch Nauka modules flown on Zenit-2M reconnaissance satellites. Vehicle: Soyuz-U 90 kg of equipment could be contained in the external Nauka Launch Site: Plesetsk, module. Russia Mass: 6000.0 kg

Funding Agency

Institute of Biomedical Problems, Moscow (U.S.S.R)

Discipline

Life Science

Additional Information

Launch/Orbital information for Bion 10

Experiments on Bion 10

Data collections from Bion 10

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

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Personnel CANEX-2

Publications NSSDC ID: CANEX-2 Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The Canadian Experiments (CANEX-2) is a group of space Canadian Experiments-2 technology, space science, materials processing and life sciences experiments flown in the Space Shuttle cargo bay on STS-52. The experiments will be performed by Payload Facts in Brief Mission Specialist Dr. Steve MacLean of the Canadian Space Launch Date: 1992-10- Agency. Potential applications include machine vision systems 14 using robotics in space and in other environments (mines, Launch nuclear reactors). Other potential applications include the Vehicle: Shuttle manufacture of goods, materials processing, ozone layer Launch Site: Cape studies, and human adaptation to microgravity. CANEX-1 was Canaveral, United States flown on a Space Shuttle mission in 1984. The current list of Mass: 136.0 kg experiments are: (1) Space Vision System Experiment (SVS), (2) Materials Exposure in Low-Earth Orbit (MELEO), (3) Orbiter Glow-2 (OGLOW-2), (4) Queen's University Experiment in Funding Agency Liquid Metal Diffusion (QUELD), (5) Sun Photo Spectrometer Earth Atmosphere Measurement (SPEAM-2), (6) Phase Canadian Space Agency Partitioning in Liquids (PARLIQ), (7) Space Adaptation Tests (Canada) and Observations (SATO), (8) Vestibular-Ocular Reflex Check, (9) Body Water Changes in Microgravity, (10) Assessment of Disciplines Back Pain in Astronauts, and (11) Illusions During Movement. Engineering Earth Science Life Science Microgravity

Additional Information

Launch/Orbital information for CANEX-2 PDMP information for CANEX-2 Telecommunications information for CANEX-2

Experiments on CANEX-2

Data collections from CANEX-2

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

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Personnel

Name Role Original Affiliation E-mail Dr. Bob Aikenhead Program Manager Canadian Space Agency

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Personnel Cosmos 2175

Publications NSSDC ID: 1992-001A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Cosmos 2175 was a Russian photo surveillance satellite 21844 launched from the Plesetsk cosmodrome aboard a Soyuz rocket. Two small film capsules were recovered in flight and the main re-entry capsule with remaining film, camera, and Facts in Brief computer systems at end of flight. Launch Date: 1992-01- 21 Launch Vehicle: Soyuz-U Launch Site: Plesetsk, Russia Mass: 6600.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline

Surveillance and Other Military

Additional Information

Launch/Orbital information for Cosmos 2175

Experiments on Cosmos 2175

Data collections from Cosmos 2175

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

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Personnel Cosmos 2176

Publications NSSDC ID: 1992-003A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Cosmos 2176 was a Russian missile early warning satellite 21847 launched from the Plesetsk cosmodrome aboard a Molniya rocket. It was part of the Oko constellation of satellites and covered the plane 6 - 119 degree longitude of ascending node. Facts in Brief Launch Date: 1992-01- 23 Launch Vehicle: Molniya-M Launch Site: Plesetsk, Russia Mass: 1900.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline

Surveillance and Other Military

Additional Information

Launch/Orbital information for Cosmos 2176

Experiments on Cosmos 2176

Data collections from Cosmos 2176

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

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Personnel Cosmos 2177

Publications NSSDC ID: 1992-005A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Cosmos 2177 was a Russian Global Navigation Satellite 21853 System (GLONASS) satellite launched from the Baikonur cosmodrome aboard a Proton rocket. Originally established in order to locate the Soviet Union's civil aircraft and its merchant Facts in Brief and fishing vessels, the signals were used by many American Launch Date: 1992-01- GPS system receivers as a complement/backup to the GPS 29 system itself. The operational system contained 21 satellites in Launch Vehicle: Proton 3 orbital planes, with 3 on-orbit backups. Each satellite was Launch Site: Tyuratam identified by its slot number, which defined the orbital plane (1- (Baikonur Cosmodrome), 8, 9-16, 17-24) and the location within the plane. The 3 orbital Kazakhstan planes were separated 120 degrees, and the satellites within Mass: 1400.0 kg the same orbit plane by 45 degrees. The orbits were roughly Nominal circular with an inclination of about 64.8 degrees, a semi-axis Power: 1600.0 W of 25,440 km, and a period of 11h 15m 44s.

The 3-axis stabilized spacecraft possessed a mass of about Funding Agency 1,400 kg, a slight increase over the 1,250 original model. The diameter and height of the satellite bus were approximately 2.4 Scientific Production m and 3.7 m, respectively, with a solar array span of 7.2 m for Association(Russia) an electrical power generation capability of 1.6 kW at (U.S.S.R) beginning of life. The aft payload structure housed 12 primary antennas for L-band transmissions. Laser corner-cube Discipline reflectors were also carried to aid in precise orbit determination and gedetic research. Navigation & Global Positioning

Additional Information

Launch/Orbital information for Cosmos 2177

Experiments on Cosmos 2177

Data collections from Cosmos 2177

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

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Personnel Cosmos 2178

Publications NSSDC ID: 1992-005B Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Cosmos 2178 was a Russian Global Navigation Satellite 21854 System (GLONASS) satellite launched from the Baikonur cosmodrome aboard a Proton rocket. Originally established in order to locate the Soviet Union's civil aircraft and its merchant Facts in Brief and fishing vessels, the signals were used by many American Launch Date: 1992-01- GPS system receivers as a complement/backup to the GPS 29 system itself. The operational system contained 21 satellites in Launch Vehicle: Proton 3 orbital planes, with 3 on-orbit backups. Each satellite was Launch Site: Tyuratam identified by its slot number, which defined the orbital plane (1- (Baikonur Cosmodrome), 8, 9-16, 17-24) and the location within the plane. The 3 orbital Kazakhstan planes were separated 120 degrees, and the satellites within Mass: 1400.0 kg the same orbit plane by 45 degrees. The orbits were roughly Nominal circular with an inclination of about 64.8 degrees, a semi-axis Power: 1600.0 W of 25,440 km, and a period of 11h 15m 44s.

The 3-axis stabilized spacecraft possessed a mass of about Funding Agency 1,400 kg, a slight increase over the 1,250 original model. The diameter and height of the satellite bus were approximately 2.4 Scientific Production m and 3.7 m, respectively, with a solar array span of 7.2 m for Association(Russia) an electrical power generation capability of 1.6 kW at (U.S.S.R) beginning of life. The aft payload structure housed 12 primary antennas for L-band transmissions. Laser corner-cube Discipline reflectors were also carried to aid in precise orbit determination and gedetic research. Navigation & Global Positioning

Additional Information

Launch/Orbital information for Cosmos 2178

Experiments on Cosmos 2178

Data collections from Cosmos 2178

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

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Personnel Cosmos 2179

Publications NSSDC ID: 1992-005C Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Cosmos 2179 was a Russian Global Navigation Satellite 21855 System (GLONASS) satellite launched from the Baikonur cosmodrome aboard a Proton rocket. Originally established in order to locate the Soviet Union's civil aircraft and its merchant Facts in Brief and fishing vessels, the signals were used by many American Launch Date: 1992-01- GPS system receivers as a complement/backup to the GPS 29 system itself. The operational system contained 21 satellites in Launch Vehicle: Proton 3 orbital planes, with 3 on-orbit backups. Each satellite was Launch Site: Tyuratam identified by its slot number, which defined the orbital plane (1- (Baikonur Cosmodrome), 8, 9-16, 17-24) and the location within the plane. The 3 orbital Kazakhstan planes were separated 120 degrees, and the satellites within Mass: 1400.0 kg the same orbit plane by 45 degrees. The orbits were roughly Nominal circular with an inclination of about 64.8 degrees, a semi-axis Power: 1600.0 W of 25,440 km, and a period of 11h 15m 44s.

The 3-axis stabilized spacecraft possessed a mass of about Funding Agency 1,400 kg, a slight increase over the 1,250 original model. The diameter and height of the satellite bus were approximately 2.4 Scientific Production m and 3.7 m, respectively, with a solar array span of 7.2 m for Association(Russia) an electrical power generation capability of 1.6 kW at (U.S.S.R) beginning of life. The aft payload structure housed 12 primary antennas for L-band transmissions. Laser corner-cube Discipline reflectors were also carried to aid in precise orbit determination and gedetic research. Navigation & Global Positioning

Additional Information

Launch/Orbital information for Cosmos 2179

Experiments on Cosmos 2179

Data collections from Cosmos 2179

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

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Personnel Cosmos 2180

Publications NSSDC ID: 1992-008A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Cosmos 2180 was part of a 6-satellite Russian military 21875 navigation system distributed in orbital planes spaced 30 degrees apart, and launched from the Plesetsk cosmodrome aboard a Cosmos rocket. Navigation information was derived Facts in Brief from Doppler-shifted VHF transmissions (approximately 150 Launch Date: 1992-02- and 400 MHz) of the satellite position and orbital data. By 17 acquiring fixes from several satellite, a user's location could be Launch calculated with an accuracy of 100 m. The time needed to Vehicle: Cosmos ascertain a position was dependent upon the user's latitude Launch Site: Plesetsk, and the number of operational spacecraft in orbit. Normally, Russia accurate location determination could be made within 1-2 Mass: 825.0 kg hours.

Funding Agency

Unknown (U.S.S.R)

Discipline

Navigation & Global Positioning

Additional Information

Launch/Orbital information for Cosmos 2180

Experiments on Cosmos 2180

Data collections from Cosmos 2180

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

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Personnel Cosmos 2181

Publications NSSDC ID: 1992-012A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Cosmos 2181 was a Russian navigation satellite launched from 21902 the Plesetsk cosmodrome aboard a Kosmos 11 rocket. It was positioned in plane 13 of the constellation. It was used for testing of components and equipment of a space navigation Facts in Brief system being set up to determine the position of civil aircraft Launch Date: 1992-03- and ships of the USSR merchant marine and fishing fleet at 09 any point on the oceans and seas. Launch Vehicle: Cosmos Development of this second generation Soviet navigation Launch Site: Plesetsk, satellite system represented a collaboration between the Navy, Russia Academy of Sciences, and Ministry of Shipping. The basis Mass: 825.0 kg was the Parus / Tsiklon-B doppler navigation system, but allowing asynchronous operation of on-board equipment with only essential equipment receiving a timer interrupt. Funding Agency Development began in 1974 with some preliminary work already accomplished. The Tsikada system provided global Unknown (U.S.S.R) navigation for both the Soviet Navy and commercial shipping. Prime contractor was KBPM/Reshetnev. PO Polyot, A S Discipline Klinyshkov provided synchronisation equipment. NII Radiopribor under N Ye Ivanov provided cryptography and Navigation & Global spacecraft navigation systems. Flight trials began in 1976 Positioning under Admiral A I Rassokho. The system was accepted into military service in 1979. Additional Information

Launch/Orbital information for Cosmos 2181

Experiments on Cosmos 2181

Data collections from Cosmos 2181

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

+ Privacy Policy and Important Notices NASA Official: Dr. Ed Grayzeck Curator: E. Bell, II Version 4.0.15, 15 April 2011

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Personnel Cosmos 2182

Publications NSSDC ID: 1992-016A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Cosmos 2182 was a Russian photo surveillance satellite 21920 launched from the Plesetsk cosmodrome aboard a Soyuz rocket. Two small film capsules were recovered in flight and the main re-entry capsule with remaining film, camera, and Facts in Brief computer systems at end of flight. Launch Date: 1992-04- 01 Launch Vehicle: Soyuz-U Launch Site: Plesetsk, Russia Mass: 6600.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline

Surveillance and Other Military

Additional Information

Launch/Orbital information for Cosmos 2182

Experiments on Cosmos 2182

Data collections from Cosmos 2182

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

+ Privacy Policy and Important Notices NASA Official: Dr. Ed Grayzeck Curator: E. Bell, II Version 4.0.15, 15 April 2011

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Personnel Cosmos 2183

Publications NSSDC ID: 1992-018A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Cosmos 2183 was a Russian digital photo surveillance satellite 21928 launched from the Baikonur cosmodrome aboard a Soyuz-U rocket. It remained in orbit for 314 days. Facts in Brief

Launch Date: 1992-04- 08 Launch Vehicle: Soyuz-U Launch Site: Tyuratam (Baikonur Cosmodrome), Kazakhstan Mass: 6600.0 kg

Funding Agency

Russian Space Agency (Russia)

Discipline

Surveillance and Other Military

Additional Information

Launch/Orbital information for Cosmos 2183

Experiments on Cosmos 2183

Data collections from Cosmos 2183

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

+ Privacy Policy and Important Notices NASA Official: Dr. Ed Grayzeck Curator: E. Bell, II Version 4.0.15, 15 April 2011

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Personnel Cosmos 2184

Publications NSSDC ID: 1992-020A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Cosmos 2184 was part of a 6-satellite Russian military 21937 navigation system distributed in orbital planes spaced 30 degrees apart, and launched from the Plesetsk cosmodrome aboard a Cosmos rocket. Navigation information was derived Facts in Brief from Doppler-shifted VHF transmissions (approximately 150 Launch Date: 1992-04- and 400 MHz) of the satellite position and orbital data. By 15 acquiring fixes from several satellite, a user's location could be Launch calculated with an accuracy of 100 m. The time needed to Vehicle: Cosmos ascertain a position was dependent upon the user's latitude Launch Site: Plesetsk, and the number of operational spacecraft in orbit. Normally, Russia accurate location determination could be made within 1-2 Mass: 825.0 kg hours.

Funding Agency

Unknown (U.S.S.R)

Discipline

Navigation & Global Positioning

Additional Information

Launch/Orbital information for Cosmos 2184

Experiments on Cosmos 2184

Data collections from Cosmos 2184

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

+ Privacy Policy and Important Notices NASA Official: Dr. Ed Grayzeck Curator: E. Bell, II Version 4.0.15, 15 April 2011

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Personnel Cosmos 2185

Publications NSSDC ID: 1992-025A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Cosmos 2185 was a variation of the Yantar-class spacecraft 21953 used to conduct high-precision topographic surveys. These spacecraft, now referred to as Kometa, typically remained in orbit for 44-45 days and were distinguished by their relatively Facts in Brief circular orbits between 210 and 280 km. These missions were Launch Date: 1992-04- always launched from the Baikonur cosmodrome into 29 inclinations of 65 degrees or 70 degrees at the rate of one or Launch two per year. Vehicle: Soyuz-U Launch Site: Tyuratam (Baikonur Cosmodrome), Kazakhstan Mass: 6600.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline

Surveillance and Other Military

Additional Information

Launch/Orbital information for Cosmos 2185

Experiments on Cosmos 2185

Data collections from Cosmos 2185

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

+ Privacy Policy and Important Notices NASA Official: Dr. Ed Grayzeck Curator: E. Bell, II Version 4.0.15, 15 April 2011

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Personnel Cosmos 2186

Publications NSSDC ID: 1992-029A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Cosmos 2186 was a Russian photo surveillance satellite 21975 launched from the Plesetsk cosmodrome aboard a Soyuz rocket. Two small film capsules were recovered in flight and the main re-entry capsule with remaining film, camera, and Facts in Brief computer systems at end of flight. Launch Date: 1992-05- 28 Launch Vehicle: Soyuz-U Launch Site: Plesetsk, Russia Mass: 6600.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline

Surveillance and Other Military

Additional Information

Launch/Orbital information for Cosmos 2186

Experiments on Cosmos 2186

Data collections from Cosmos 2186

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

+ Privacy Policy and Important Notices NASA Official: Dr. Ed Grayzeck Curator: E. Bell, II Version 4.0.15, 15 April 2011

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Personnel Cosmos 2187

Publications NSSDC ID: 1992-030A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The lowest level of the three-tier communications satellite 21976 constellation was populated with two distinct systems devoted to military and government communications. Both systems were assessed to be simple store-dump repeaters which were Facts in Brief particularly useful in relaying traffic between the Russian Launch Date: 1992-06- Federation and overseas stations or forces. These Strela 02 (which means "Arrow" in Russian) satellites recorded radio Launch messages transmitted by Russian intelligence agents Vehicle: Cosmos worldwide and relayed them when flying over Moscow. Launch Site: Plesetsk, Debuting in 1970 was a system of small (61 kg, 0.80 m by Russia 0.75 m) relay satellites launched from Plesetsk by the Kosmos Mass: 45.0 kg booster in groups of eight. Although the mean altitude of this constellation was near 1500 km, each set of eight Strela 1 satellites was normally dispersed into slightly elliptical orbits Funding Agency with mean altitudes between 1430 and 1490 km. The intentional orbital period differences of about 0.15 min ensured Unknown (U.S.S.R) that the satellites would become randomly spaced about the orbital plane shortly after launch. Unlike the lower altitude Discipline constellation, this network relied on a single orbital plane with an inclination of 74 deg which was replenished on the average Communications of once each year. The last mission in this network was in June 1992, and the network has now been superseded by the more modern and capable Strela 3 system. Additional Information

Launch/Orbital information for Cosmos 2187

Experiments on Cosmos 2187

Data collections from Cosmos 2187

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

+ Privacy Policy and Important Notices NASA Official: Dr. Ed Grayzeck Curator: E. Bell, II Version 4.0.15, 15 April 2011

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Personnel Cosmos 2188

Publications NSSDC ID: 1992-030B Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The lowest level of the three-tier communications satellite 21977 constellation was populated with two distinct systems devoted to military and government communications. Both systems were assessed to be simple store-dump repeaters which were Facts in Brief particularly useful in relaying traffic between the Russian Launch Date: 1992-06- Federation and overseas stations or forces. These Strela 02 (which means "Arrow" in Russian) satellites recorded radio Launch messages transmitted by Russian intelligence agents Vehicle: Cosmos worldwide and relayed them when flying over Moscow. Launch Site: Plesetsk, Debuting in 1970 was a system of small (61 kg, 0.80 m by Russia 0.75 m) relay satellites launched from Plesetsk by the Kosmos Mass: 45.0 kg booster in groups of eight. Although the mean altitude of this constellation was near 1500 km, each set of eight Strela 1 satellites was normally dispersed into slightly elliptical orbits Funding Agency with mean altitudes between 1430 and 1490 km. The intentional orbital period differences of about 0.15 min ensured Unknown (U.S.S.R) that the satellites would become randomly spaced about the orbital plane shortly after launch. Unlike the lower altitude Discipline constellation, this network relied on a single orbital plane with an inclination of 74 deg which was replenished on the average Communications of once each year. The last mission in this network was in June 1992, and the network has now been superseded by the more modern and capable Strela 3 system. Additional Information

Launch/Orbital information for Cosmos 2188

Experiments on Cosmos 2188

Data collections from Cosmos 2188

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

+ Privacy Policy and Important Notices NASA Official: Dr. Ed Grayzeck Curator: E. Bell, II Version 4.0.15, 15 April 2011

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Personnel Cosmos 2189

Publications NSSDC ID: 1992-030C Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The lowest level of the three-tier communications satellite 21978 constellation was populated with two distinct systems devoted to military and government communications. Both systems were assessed to be simple store-dump repeaters which were Facts in Brief particularly useful in relaying traffic between the Russian Launch Date: 1992-06- Federation and overseas stations or forces. These Strela 02 (which means "Arrow" in Russian) satellites recorded radio Launch messages transmitted by Russian intelligence agents Vehicle: Cosmos worldwide and relayed them when flying over Moscow. Launch Site: Plesetsk, Debuting in 1970 was a system of small (61 kg, 0.80 m by Russia 0.75 m) relay satellites launched from Plesetsk by the Kosmos Mass: 45.0 kg booster in groups of eight. Although the mean altitude of this constellation was near 1500 km, each set of eight Strela 1 satellites was normally dispersed into slightly elliptical orbits Funding Agency with mean altitudes between 1430 and 1490 km. The intentional orbital period differences of about 0.15 min ensured Unknown (U.S.S.R) that the satellites would become randomly spaced about the orbital plane shortly after launch. Unlike the lower altitude Discipline constellation, this network relied on a single orbital plane with an inclination of 74 deg which was replenished on the average Communications of once each year. The last mission in this network was in June 1992, and the network has now been superseded by the more modern and capable Strela 3 system. Additional Information

Launch/Orbital information for Cosmos 2189

Experiments on Cosmos 2189

Data collections from Cosmos 2189

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

+ Privacy Policy and Important Notices NASA Official: Dr. Ed Grayzeck Curator: E. Bell, II Version 4.0.15, 15 April 2011

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Personnel Cosmos 2190

Publications NSSDC ID: 1992-030D Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The lowest level of the three-tier communications satellite 21979 constellation was populated with two distinct systems devoted to military and government communications. Both systems were assessed to be simple store-dump repeaters which were Facts in Brief particularly useful in relaying traffic between the Russian Launch Date: 1992-06- Federation and overseas stations or forces. These Strela 02 (which means "Arrow" in Russian) satellites recorded radio Launch messages transmitted by Russian intelligence agents Vehicle: Cosmos worldwide and relayed them when flying over Moscow. Launch Site: Plesetsk, Debuting in 1970 was a system of small (61 kg, 0.80 m by Russia 0.75 m) relay satellites launched from Plesetsk by the Kosmos Mass: 45.0 kg booster in groups of eight. Although the mean altitude of this constellation was near 1500 km, each set of eight Strela 1 satellites was normally dispersed into slightly elliptical orbits Funding Agency with mean altitudes between 1430 and 1490 km. The intentional orbital period differences of about 0.15 min ensured Unknown (U.S.S.R) that the satellites would become randomly spaced about the orbital plane shortly after launch. Unlike the lower altitude Discipline constellation, this network relied on a single orbital plane with an inclination of 74 deg which was replenished on the average Communications of once each year. The last mission in this network was in June 1992, and the network has now been superseded by the more modern and capable Strela 3 system. Additional Information

Launch/Orbital information for Cosmos 2190

Experiments on Cosmos 2190

Data collections from Cosmos 2190

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

+ Privacy Policy and Important Notices NASA Official: Dr. Ed Grayzeck Curator: E. Bell, II Version 4.0.15, 15 April 2011

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Personnel Cosmos 2191

Publications NSSDC ID: 1992-030E Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The lowest level of the three-tier communications satellite 21980 constellation was populated with two distinct systems devoted to military and government communications. Both systems were assessed to be simple store-dump repeaters which were Facts in Brief particularly useful in relaying traffic between the Russian Launch Date: 1992-06- Federation and overseas stations or forces. These Strela 02 (which means "Arrow" in Russian) satellites recorded radio Launch messages transmitted by Russian intelligence agents Vehicle: Cosmos worldwide and relayed them when flying over Moscow. Launch Site: Plesetsk, Debuting in 1970 was a system of small (61 kg, 0.80 m by Russia 0.75 m) relay satellites launched from Plesetsk by the Kosmos Mass: 45.0 kg booster in groups of eight. Although the mean altitude of this constellation was near 1500 km, each set of eight Strela 1 satellites was normally dispersed into slightly elliptical orbits Funding Agency with mean altitudes between 1430 and 1490 km. The intentional orbital period differences of about 0.15 min ensured Unknown (U.S.S.R) that the satellites would become randomly spaced about the orbital plane shortly after launch. Unlike the lower altitude Discipline constellation, this network relied on a single orbital plane with an inclination of 74 deg which was replenished on the average Communications of once each year. The last mission in this network was in June 1992, and the network has now been superseded by the more modern and capable Strela 3 system. Additional Information

Launch/Orbital information for Cosmos 2191

Experiments on Cosmos 2191

Data collections from Cosmos 2191

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

+ Privacy Policy and Important Notices NASA Official: Dr. Ed Grayzeck Curator: E. Bell, II Version 4.0.15, 15 April 2011

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Personnel Cosmos 2192

Publications NSSDC ID: 1992-030F Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The lowest level of the three-tier communications satellite 21981 constellation was populated with two distinct systems devoted to military and government communications. Both systems were assessed to be simple store-dump repeaters which were Facts in Brief particularly useful in relaying traffic between the Russian Launch Date: 1992-06- Federation and overseas stations or forces. These Strela 02 (which means "Arrow" in Russian) satellites recorded radio Launch messages transmitted by Russian intelligence agents Vehicle: Cosmos worldwide and relayed them when flying over Moscow. Launch Site: Plesetsk, Debuting in 1970 was a system of small (61 kg, 0.80 m by Russia 0.75 m) relay satellites launched from Plesetsk by the Kosmos Mass: 45.0 kg booster in groups of eight. Although the mean altitude of this constellation was near 1500 km, each set of eight Strela 1 satellites was normally dispersed into slightly elliptical orbits Funding Agency with mean altitudes between 1430 and 1490 km. The intentional orbital period differences of about 0.15 min ensured Unknown (U.S.S.R) that the satellites would become randomly spaced about the orbital plane shortly after launch. Unlike the lower altitude Discipline constellation, this network relied on a single orbital plane with an inclination of 74 deg which was replenished on the average Communications of once each year. The last mission in this network was in June 1992, and the network has now been superseded by the more modern and capable Strela 3 system. Additional Information

Launch/Orbital information for Cosmos 2192

Experiments on Cosmos 2192

Data collections from Cosmos 2192

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

+ Privacy Policy and Important Notices NASA Official: Dr. Ed Grayzeck Curator: E. Bell, II Version 4.0.15, 15 April 2011

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Personnel Cosmos 2193

Publications NSSDC ID: 1992-030G Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The lowest level of the three-tier communications satellite 21982 constellation was populated with two distinct systems devoted to military and government communications. Both systems were assessed to be simple store-dump repeaters which were Facts in Brief particularly useful in relaying traffic between the Russian Launch Date: 1992-06- Federation and overseas stations or forces. These Strela 02 (which means "Arrow" in Russian) satellites recorded radio Launch messages transmitted by Russian intelligence agents Vehicle: Cosmos worldwide and relayed them when flying over Moscow. Launch Site: Plesetsk, Debuting in 1970 was a system of small (61 kg, 0.80 m by Russia 0.75 m) relay satellites launched from Plesetsk by the Kosmos Mass: 45.0 kg booster in groups of eight. Although the mean altitude of this constellation was near 1500 km, each set of eight Strela 1 satellites was normally dispersed into slightly elliptical orbits Funding Agency with mean altitudes between 1430 and 1490 km. The intentional orbital period differences of about 0.15 min ensured Unknown (U.S.S.R) that the satellites would become randomly spaced about the orbital plane shortly after launch. Unlike the lower altitude Discipline constellation, this network relied on a single orbital plane with an inclination of 74 deg which was replenished on the average Communications of once each year. The last mission in this network was in June 1992, and the network has now been superseded by the more modern and capable Strela 3 system. Additional Information

Launch/Orbital information for Cosmos 2193

Experiments on Cosmos 2193

Data collections from Cosmos 2193

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

+ Privacy Policy and Important Notices NASA Official: Dr. Ed Grayzeck Curator: E. Bell, II Version 4.0.15, 15 April 2011

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Personnel Cosmos 2194

Publications NSSDC ID: 1992-030H Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The lowest level of the three-tier communications satellite 21983 constellation was populated with two distinct systems devoted to military and government communications. Both systems were assessed to be simple store-dump repeaters which were Facts in Brief particularly useful in relaying traffic between the Russian Launch Date: 1992-06- Federation and overseas stations or forces. These Strela 02 (which means "Arrow" in Russian) satellites recorded radio Launch messages transmitted by Russian intelligence agents Vehicle: Cosmos worldwide and relayed them when flying over Moscow. Launch Site: Plesetsk, Debuting in 1970 was a system of small (61 kg, 0.80 m by Russia 0.75 m) relay satellites launched from Plesetsk by the Kosmos Mass: 45.0 kg booster in groups of eight. Although the mean altitude of this constellation was near 1500 km, each set of eight Strela 1 satellites was normally dispersed into slightly elliptical orbits Funding Agency with mean altitudes between 1430 and 1490 km. The intentional orbital period differences of about 0.15 min ensured Unknown (U.S.S.R) that the satellites would become randomly spaced about the orbital plane shortly after launch. Unlike the lower altitude Discipline constellation, this network relied on a single orbital plane with an inclination of 74 deg which was replenished on the average Communications of once each year. The last mission in this network was in June 1992, and the network has now been superseded by the more modern and capable Strela 3 system. Additional Information

Launch/Orbital information for Cosmos 2194

Experiments on Cosmos 2194

Data collections from Cosmos 2194

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

+ Privacy Policy and Important Notices NASA Official: Dr. Ed Grayzeck Curator: E. Bell, II Version 4.0.15, 15 April 2011

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Personnel Cosmos 2195

Publications NSSDC ID: 1992-036A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Cosmos 2195 was part of a 6-satellite Russian military 22006 navigation system distributed in orbital planes spaced 30 degrees apart, and launched from the Plesetsk cosmodrome aboard a Cosmos rocket. Navigation information was derived Facts in Brief from Doppler-shifted VHF transmissions (approximately 150 Launch Date: 1992-07- and 400 MHz) of the satellite position and orbital data. By 01 acquiring fixes from several satellite, a user's location could be Launch calculated with an accuracy of 100 m. The time needed to Vehicle: Cosmos ascertain a position was dependent upon the user's latitude Launch Site: Plesetsk, and the number of operational spacecraft in orbit. Normally, Russia accurate location determination could be made within 1-2 Mass: 825.0 kg hours.

Funding Agency

Unknown (U.S.S.R)

Discipline

Navigation & Global Positioning

Additional Information

Launch/Orbital information for Cosmos 2195

Experiments on Cosmos 2195

Data collections from Cosmos 2195

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

+ Privacy Policy and Important Notices NASA Official: Dr. Ed Grayzeck Curator: E. Bell, II Version 4.0.15, 15 April 2011

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Personnel Cosmos 2196

Publications NSSDC ID: 1992-040A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Cosmos 2196 was a Russian missile early warning satellite 22017 launched from the Plesetsk cosmodrome aboard a Molniya rocket. It was part of the Oko constellation of satellites and covered the plane 5 - 75 degree longitude of ascending node. Facts in Brief Launch Date: 1992-07- 08 Launch Vehicle: Molniya-M Launch Site: Plesetsk, Russia Mass: 1900.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline

Surveillance and Other Military

Additional Information

Launch/Orbital information for Cosmos 2196

Experiments on Cosmos 2196

Data collections from Cosmos 2196

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

+ Privacy Policy and Important Notices NASA Official: Dr. Ed Grayzeck Curator: E. Bell, II Version 4.0.15, 15 April 2011

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Personnel Cosmos 2197

Publications NSSDC ID: 1992-042A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The Strela 3 system was a communications satellite 22034 constellation devoted to military and government communications. It was a simple store-dump repeater system which were particulatly useful in relaying non-essential traffic Facts in Brief between the Russian Federation and overseas stations or Launch Date: 1992-07- forces. The Strela 3 system, which began in 1985, was 13 launched by the Tsyklon-3 booster from the Plesetsk Launch cosmodrome into orbits near 1400 km at inclinations of 82.6 Vehicle: Tsiklon-3 degrees with six spacecraft stacked atop each launch vehicle. Launch Site: Plesetsk, Two orbital planes were spaced 90 degrees apart, apparently Russia each contained 10-12 operational spacecraft. Normally, two Mass: 220.0 kg missions were conducted per year, suggesting an average spacecraft life-time of approximately 24 months. The 220 kg spacecraft had a diameter of 1.0 m and a main bus height of Funding Agency 1.5 m. A gravity-gradient beam was extended on-orbit to provide attitude stabilization. Unknown (U.S.S.R)

Discipline

Communications

Additional Information

Launch/Orbital information for Cosmos 2197

Experiments on Cosmos 2197

Data collections from Cosmos 2197

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

+ Privacy Policy and Important Notices NASA Official: Dr. Ed Grayzeck Curator: E. Bell, II Version 4.0.15, 15 April 2011

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Personnel Cosmos 2198

Publications NSSDC ID: 1992-042B Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The Strela 3 system was a communications satellite 22035 constellation devoted to military and government communications. It was a simple store-dump repeater system which were particulatly useful in relaying non-essential traffic Facts in Brief between the Russian Federation and overseas stations or Launch Date: 1992-07- forces. The Strela 3 system, which began in 1985, was 13 launched by the Tsyklon-3 booster from the Plesetsk Launch cosmodrome into orbits near 1400 km at inclinations of 82.6 Vehicle: Tsiklon-3 degrees with six spacecraft stacked atop each launch vehicle. Launch Site: Plesetsk, Two orbital planes were spaced 90 degrees apart, apparently Russia each contained 10-12 operational spacecraft. Normally, two Mass: 220.0 kg missions were conducted per year, suggesting an average spacecraft life-time of approximately 24 months. The 220 kg spacecraft had a diameter of 1.0 m and a main bus height of Funding Agency 1.5 m. A gravity-gradient beam was extended on-orbit to provide attitude stabilization. Unknown (U.S.S.R)

Discipline

Communications

Additional Information

Launch/Orbital information for Cosmos 2198

Experiments on Cosmos 2198

Data collections from Cosmos 2198

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

+ Privacy Policy and Important Notices NASA Official: Dr. Ed Grayzeck Curator: E. Bell, II Version 4.0.15, 15 April 2011

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Personnel Cosmos 2199

Publications NSSDC ID: 1992-042C Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The Strela 3 system was a communications satellite 22036 constellation devoted to military and government communications. It was a simple store-dump repeater system which were particulatly useful in relaying non-essential traffic Facts in Brief between the Russian Federation and overseas stations or Launch Date: 1992-07- forces. The Strela 3 system, which began in 1985, was 13 launched by the Tsyklon-3 booster from the Plesetsk Launch cosmodrome into orbits near 1400 km at inclinations of 82.6 Vehicle: Tsiklon-3 degrees with six spacecraft stacked atop each launch vehicle. Launch Site: Plesetsk, Two orbital planes were spaced 90 degrees apart, apparently Russia each contained 10-12 operational spacecraft. Normally, two Mass: 220.0 kg missions were conducted per year, suggesting an average spacecraft life-time of approximately 24 months. The 220 kg spacecraft had a diameter of 1.0 m and a main bus height of Funding Agency 1.5 m. A gravity-gradient beam was extended on-orbit to provide attitude stabilization. Unknown (U.S.S.R)

Discipline

Communications

Additional Information

Launch/Orbital information for Cosmos 2199

Experiments on Cosmos 2199

Data collections from Cosmos 2199

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

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Personnel Cosmos 2200

Publications NSSDC ID: 1992-042D Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The Strela 3 system was a communications satellite 22037 constellation devoted to military and government communications. It was a simple store-dump repeater system which were particulatly useful in relaying non-essential traffic Facts in Brief between the Russian Federation and overseas stations or Launch Date: 1992-07- forces. The Strela 3 system, which began in 1985, was 13 launched by the Tsyklon-3 booster from the Plesetsk Launch cosmodrome into orbits near 1400 km at inclinations of 82.6 Vehicle: Tsiklon-3 degrees with six spacecraft stacked atop each launch vehicle. Launch Site: Plesetsk, Two orbital planes were spaced 90 degrees apart, apparently Russia each contained 10-12 operational spacecraft. Normally, two Mass: 220.0 kg missions were conducted per year, suggesting an average spacecraft life-time of approximately 24 months. The 220 kg spacecraft had a diameter of 1.0 m and a main bus height of Funding Agency 1.5 m. A gravity-gradient beam was extended on-orbit to provide attitude stabilization. Unknown (U.S.S.R)

Discipline

Communications

Additional Information

Launch/Orbital information for Cosmos 2200

Experiments on Cosmos 2200

Data collections from Cosmos 2200

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

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Personnel Cosmos 2201

Publications NSSDC ID: 1992-042E Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The Strela 3 system was a communications satellite 22038 constellation devoted to military and government communications. It was a simple store-dump repeater system which were particulatly useful in relaying non-essential traffic Facts in Brief between the Russian Federation and overseas stations or Launch Date: 1992-07- forces. The Strela 3 system, which began in 1985, was 13 launched by the Tsyklon-3 booster from the Plesetsk Launch cosmodrome into orbits near 1400 km at inclinations of 82.6 Vehicle: Tsiklon-3 degrees with six spacecraft stacked atop each launch vehicle. Launch Site: Plesetsk, Two orbital planes were spaced 90 degrees apart, apparently Russia each contained 10-12 operational spacecraft. Normally, two Mass: 220.0 kg missions were conducted per year, suggesting an average spacecraft life-time of approximately 24 months. The 220 kg spacecraft had a diameter of 1.0 m and a main bus height of Funding Agency 1.5 m. A gravity-gradient beam was extended on-orbit to provide attitude stabilization. Unknown (U.S.S.R)

Discipline

Communications

Additional Information

Launch/Orbital information for Cosmos 2201

Experiments on Cosmos 2201

Data collections from Cosmos 2201

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

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Personnel Cosmos 2202

Publications NSSDC ID: 1992-042F Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The Strela 3 system was a communications satellite 22039 constellation devoted to military and government communications. It was a simple store-dump repeater system which were particulatly useful in relaying non-essential traffic Facts in Brief between the Russian Federation and overseas stations or Launch Date: 1992-07- forces. The Strela 3 system, which began in 1985, was 13 launched by the Tsyklon-3 booster from the Plesetsk Launch cosmodrome into orbits near 1400 km at inclinations of 82.6 Vehicle: Tsiklon-3 degrees with six spacecraft stacked atop each launch vehicle. Launch Site: Plesetsk, Two orbital planes were spaced 90 degrees apart, apparently Russia each contained 10-12 operational spacecraft. Normally, two Mass: 220.0 kg missions were conducted per year, suggesting an average spacecraft life-time of approximately 24 months. The 220 kg spacecraft had a diameter of 1.0 m and a main bus height of Funding Agency 1.5 m. A gravity-gradient beam was extended on-orbit to provide attitude stabilization. Unknown (U.S.S.R)

Discipline

Communications

Additional Information

Launch/Orbital information for Cosmos 2202

Experiments on Cosmos 2202

Data collections from Cosmos 2202

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

+ Privacy Policy and Important Notices NASA Official: Dr. Ed Grayzeck Curator: E. Bell, II Version 4.0.15, 15 April 2011

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Personnel Cosmos 2203

Publications NSSDC ID: 1992-045A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Cosmos 2203 was a Russian photo surveillance satellite 22052 launched from the Plesetsk cosmodrome aboard a Soyuz rocket. Two small film capsules were recovered in flight and the main re-entry capsule with remaining film, camera, and Facts in Brief computer systems at end of flight. Launch Date: 1992-07- 24 Launch Vehicle: Soyuz-U Launch Site: Plesetsk, Russia Mass: 6600.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline

Surveillance and Other Military

Additional Information

Launch/Orbital information for Cosmos 2203

Experiments on Cosmos 2203

Data collections from Cosmos 2203

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

+ Privacy Policy and Important Notices NASA Official: Dr. Ed Grayzeck Curator: E. Bell, II Version 4.0.15, 15 April 2011

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Personnel Cosmos 2204

Publications NSSDC ID: 1992-047A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Cosmos 2204 was a Russian Global Navigation Satellite 22056 System (GLONASS) satellite launched from the Baikonur cosmodrome aboard a Proton rocket. Originally established in order to locate the Soviet Union's civil aircraft and its merchant Facts in Brief and fishing vessels, the signals were used by many American Launch Date: 1992-07- GPS system receivers as a complement/backup to the GPS 29 system itself. The operational system contained 21 satellites in Launch Vehicle: Proton 3 orbital planes, with 3 on-orbit backups. Each satellite was Launch Site: Tyuratam identified by its slot number, which defined the orbital plane (1- (Baikonur Cosmodrome), 8, 9-16, 17-24) and the location within the plane. The 3 orbital Kazakhstan planes were separated 120 degrees, and the satellites within Mass: 1400.0 kg the same orbit plane by 45 degrees. The orbits were roughly Nominal circular with an inclination of about 64.8 degrees, a semi-axis Power: 1600.0 W of 25,440 km, and a period of 11h 15m 44s.

The 3-axis stabilized spacecraft possessed a mass of about Funding Agency 1,400 kg, a slight increase over the 1,250 original model. The diameter and height of the satellite bus were approximately 2.4 Scientific Production m and 3.7 m, respectively, with a solar array span of 7.2 m for Association(Russia) an electrical power generation capability of 1.6 kW at (Russia) beginning of life. The aft payload structure housed 12 primary antennas for L-band transmissions. Laser corner-cube Discipline reflectors were also carried to aid in precise orbit determination and gedetic research. Navigation & Global Positioning

Additional Information

Launch/Orbital information for Cosmos 2204

Experiments on Cosmos 2204

Data collections from Cosmos 2204

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

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Personnel Cosmos 2205

Publications NSSDC ID: 1992-047B Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Cosmos 2205 was a Russian Global Navigation Satellite 22057 System (GLONASS) satellite launched from the Baikonur cosmodrome aboard a Proton rocket. Originally established in order to locate the Soviet Union's civil aircraft and its merchant Facts in Brief and fishing vessels, the signals were used by many American Launch Date: 1992-07- GPS system receivers as a complement/backup to the GPS 29 system itself. The operational system contained 21 satellites in Launch Vehicle: Proton 3 orbital planes, with 3 on-orbit backups. Each satellite was Launch Site: Tyuratam identified by its slot number, which defined the orbital plane (1- (Baikonur Cosmodrome), 8, 9-16, 17-24) and the location within the plane. The 3 orbital Kazakhstan planes were separated 120 degrees, and the satellites within Mass: 1400.0 kg the same orbit plane by 45 degrees. The orbits were roughly Nominal circular with an inclination of about 64.8 degrees, a semi-axis Power: 1600.0 W of 25,440 km, and a period of 11h 15m 44s.

The 3-axis stabilized spacecraft possessed a mass of about Funding Agency 1,400 kg, a slight increase over the 1,250 original model. The diameter and height of the satellite bus were approximately 2.4 Scientific Production m and 3.7 m, respectively, with a solar array span of 7.2 m for Association(Russia) an electrical power generation capability of 1.6 kW at (Russia) beginning of life. The aft payload structure housed 12 primary antennas for L-band transmissions. Laser corner-cube Discipline reflectors were also carried to aid in precise orbit determination and gedetic research. Navigation & Global Positioning

Additional Information

Launch/Orbital information for Cosmos 2205

Experiments on Cosmos 2205

Data collections from Cosmos 2205

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

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Personnel Cosmos 2206

Publications NSSDC ID: 1992-047C Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Cosmos 2206 was a Russian Global Navigation Satellite 22058 System (GLONASS) satellite launched from the Baikonur cosmodrome aboard a Proton rocket. Originally established in order to locate the Soviet Union's civil aircraft and its merchant Facts in Brief and fishing vessels, the signals were used by many American Launch Date: 1992-07- GPS system receivers as a complement/backup to the GPS 29 system itself. The operational system contained 21 satellites in Launch Vehicle: Proton 3 orbital planes, with 3 on-orbit backups. Each satellite was Launch Site: Tyuratam identified by its slot number, which defined the orbital plane (1- (Baikonur Cosmodrome), 8, 9-16, 17-24) and the location within the plane. The 3 orbital Kazakhstan planes were separated 120 degrees, and the satellites within Mass: 1400.0 kg the same orbit plane by 45 degrees. The orbits were roughly Nominal circular with an inclination of about 64.8 degrees, a semi-axis Power: 1600.0 W of 25,440 km, and a period of 11h 15m 44s.

The 3-axis stabilized spacecraft possessed a mass of about Funding Agency 1,400 kg, a slight increase over the 1,250 original model. The diameter and height of the satellite bus were approximately 2.4 Scientific Production m and 3.7 m, respectively, with a solar array span of 7.2 m for Association(Russia) an electrical power generation capability of 1.6 kW at (Russia) beginning of life. The aft payload structure housed 12 primary antennas for L-band transmissions. Laser corner-cube Discipline reflectors were also carried to aid in precise orbit determination and gedetic research. Navigation & Global Positioning

Additional Information

Launch/Orbital information for Cosmos 2206

Experiments on Cosmos 2206

Data collections from Cosmos 2206

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

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

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Personnel Cosmos 2207

Publications NSSDC ID: 1992-048A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Cosmos 2207 was a Russian military cartographic photo- 22062 surveillance satellite launched from the Plesetsk Cosmodrome aboard a Soyuz-U rocket. It conducted an investigation of the natural resources of the earth in the interests of various Facts in Brief branches of the national economy of the USSR and Launch Date: 1992-07- international cooperation. Typical orbital profile: inclination 70 30 degrees with altitude of 350-420 km. Designed duration: 15 Launch days. Transmission frequencies observed in West: 19.989 Vehicle: Soyuz-U FSK; 39.978 FSK; 232.0 PPM-AM. Launch Site: Plesetsk, Russia Mass: 6300.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline

Surveillance and Other Military

Additional Information

Launch/Orbital information for Cosmos 2207

Experiments on Cosmos 2207

Data collections from Cosmos 2207

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

+ Privacy Policy and Important Notices NASA Official: Dr. Ed Grayzeck Curator: E. Bell, II Version 4.0.15, 15 April 2011

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Personnel Cosmos 2208

Publications NSSDC ID: 1992-053A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The lowest level of the three-tier communications satellite 22080 constellation is now populated with two distinct systems devoted to military and government communications. Both systems are assessed to be simple store-dump repeaters Facts in Brief which were particularly useful in relaying non-essential traffic Launch Date: 1992-08- between the Russian Federation and overseas stations of 12 forces. The first Strela (which means "Arrow" in Russian) Launch system debuted in 1970 and consisted of 750 - 1000 kg Vehicle: Cosmos satellites deployed at mean altitudes of 800 km in three orbital Launch Site: Plesetsk, planes inclined 74 degrees to the equator and spaced 120 Russia degrees apart. These Strela 2 spacecraft were launched Mass: 900.0 kg separately by the Kosmos launch vehicle from the Plesetsk cosmodrome into each orbital plane at intervals of 24-36 months. The activity of these satellites could be monitored via Funding Agency a characteristic CW beacon emitted on a frequency of 153.660 MHz. Unknown (U.S.S.R)

Discipline

Communications

Additional Information

Launch/Orbital information for Cosmos 2208

Experiments on Cosmos 2208

Data collections from Cosmos 2208

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

+ Privacy Policy and Important Notices NASA Official: Dr. Ed Grayzeck Curator: E. Bell, II Version 4.0.15, 15 April 2011

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Personnel Cosmos 2209

Publications NSSDC ID: 1992-059A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Cosmos 2209 was part of a Russian constellation of satellites 22112 comprised of an echelon of the Missile Attack Warning System (SPRN), which was operated by the Air Defense Forces of the Ministry of Defense. According to Soviet officials, the early Facts in Brief warning satellites could detect missile launches within 20 Launch Date: 1992-09- seconds of lift-off. 10 Launch Vehicle: Proton Each satellite possessed a perigee of about 600 km, an Launch Site: Tyuratam apogee of nearly 40,000 km, and an inclination of 63 degrees. (Baikonur Cosmodrome), This orbit was superfically similar to that employed by the Kazakhstan Molniya communications satellites but was distinguished by Mass: 2200.0 kg initial argument of perigee 316-319 degrees, including to the Molniya 280-288 degree arguments of perigee. The seemingly minor difference significantly affected the shape of the Funding Agency satellite's groundtrack in the Northern Hemisphere. Unknown (U.S.S.R) Russian early warning spacecraft were more affected by gravitational perturbations due to their higher argument of Discipline perigee and, therefore, performed periodic station-keeping maneuvers to maintain an acceptable groundtrack. In addition, Surveillance and Other the argument of perigee migrated slightly over time (due to Military inclination variations), causing an alteration in the shape of the groundtrack. Instead of expending additional propellant to prevent the argument of perigee shift, Russian spacecraft Additional controllers altered the satellite's ascending node. This had the Information effect of "stabilizing" the apogee point about which surveillance Launch/Orbital operations were performed. information for Cosmos 2209

Experiments on Cosmos 2209

Data collections from Cosmos 2209

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

+ Privacy Policy and Important Notices NASA Official: Dr. Ed Grayzeck Curator: E. Bell, II Version 4.0.15, 15 April 2011

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Personnel Cosmos 2210

Publications NSSDC ID: 1992-062A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Cosmos 2210 was a Russian photo surveillance satellite 22133 launched from the Plesetsk cosmodrome aboard a Soyuz rocket. Two small film capsules were recovered in flight and the main re-entry capsule with remaining film, camera, and Facts in Brief computer systems at end of flight. Launch Date: 1992-09- 22 Launch Vehicle: Soyuz-U Launch Site: Plesetsk, Russia Mass: 6600.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline

Surveillance and Other Military

Additional Information

Launch/Orbital information for Cosmos 2210

Experiments on Cosmos 2210

Data collections from Cosmos 2210

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

+ Privacy Policy and Important Notices NASA Official: Dr. Ed Grayzeck Curator: E. Bell, II Version 4.0.15, 15 April 2011

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Sunday, 24 April 2011

National Space Science Data Center Header

Cosmos 2211

NSSDC ID: 1992-068A Description

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

22182 Facts in Brief

Launch Date: 1992-10-20 Launch Vehicle: Tsiklon-3 Launch Site: Plesetsk, Russia Mass: 220.0 kg Funding Agency

Unknown (U.S.S.R) Discipline

Communications Additional Information

Launch/Orbital information for Cosmos 2211

http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1992-068A[23/04/2011 23:50:13] NASA - NSSDC - Spacecraft - Details

Experiments on Cosmos 2211

Data collections from Cosmos 2211

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

Spacecraft Experiments Data Collections Personnel Publications Maps New/Updated Data Lunar/Planetary Events

+ Privacy Policy and Important Notices

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Personnel Cosmos 2212

Publications NSSDC ID: 1992-068B Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The Strela 3 system was a communications satellite 22183 constellation devoted to military and government communications. It was a simple store-dump repeater system which were particulatly useful in relaying non-essential traffic Facts in Brief between the Russian Federation and overseas stations or Launch Date: 1992-10- forces. The Strela 3 system, which began in 1985, was 20 launched by the Tsyklon-3 booster from the Plesetsk Launch cosmodrome into orbits near 1400 km at inclinations of 82.6 Vehicle: Tsiklon-3 degrees with six spacecraft stacked atop each launch vehicle. Launch Site: Plesetsk, Two orbital planes were spaced 90 degrees apart, apparently Russia each contained 10-12 operational spacecraft. Normally, two Mass: 220.0 kg missions were conducted per year, suggesting an average spacecraft life-time of approximately 24 months. The 220 kg spacecraft had a diameter of 1.0 m and a main bus height of Funding Agency 1.5 m. A gravity-gradient beam was extended on-orbit to provide attitude stabilization. Unknown (U.S.S.R)

Discipline

Communications

Additional Information

Launch/Orbital information for Cosmos 2212

Experiments on Cosmos 2212

Data collections from Cosmos 2212

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

+ Privacy Policy and Important Notices NASA Official: Dr. Ed Grayzeck Curator: E. Bell, II Version 4.0.15, 15 April 2011

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Personnel Cosmos 2213

Publications NSSDC ID: 1992-068C Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The Strela 3 system was a communications satellite 22184 constellation devoted to military and government communications. It was a simple store-dump repeater system which were particulatly useful in relaying non-essential traffic Facts in Brief between the Russian Federation and overseas stations or Launch Date: 1992-10- forces. The Strela 3 system, which began in 1985, was 20 launched by the Tsyklon-3 booster from the Plesetsk Launch cosmodrome into orbits near 1400 km at inclinations of 82.6 Vehicle: Tsiklon-3 degrees with six spacecraft stacked atop each launch vehicle. Launch Site: Plesetsk, Two orbital planes were spaced 90 degrees apart, apparently Russia each contained 10-12 operational spacecraft. Normally, two Mass: 220.0 kg missions were conducted per year, suggesting an average spacecraft life-time of approximately 24 months. The 220 kg spacecraft had a diameter of 1.0 m and a main bus height of Funding Agency 1.5 m. A gravity-gradient beam was extended on-orbit to provide attitude stabilization. Unknown (U.S.S.R)

Discipline

Communications

Additional Information

Launch/Orbital information for Cosmos 2213

Experiments on Cosmos 2213

Data collections from Cosmos 2213

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

+ Privacy Policy and Important Notices NASA Official: Dr. Ed Grayzeck Curator: E. Bell, II Version 4.0.15, 15 April 2011

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Personnel Cosmos 2214

Publications NSSDC ID: 1992-068D Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The Strela 3 system was a communications satellite 22185 constellation devoted to military and government communications. It was a simple store-dump repeater system which were particulatly useful in relaying non-essential traffic Facts in Brief between the Russian Federation and overseas stations or Launch Date: 1992-10- forces. The Strela 3 system, which began in 1985, was 20 launched by the Tsyklon-3 booster from the Plesetsk Launch cosmodrome into orbits near 1400 km at inclinations of 82.6 Vehicle: Tsiklon-3 degrees with six spacecraft stacked atop each launch vehicle. Launch Site: Plesetsk, Two orbital planes were spaced 90 degrees apart, apparently Russia each contained 10-12 operational spacecraft. Normally, two Mass: 220.0 kg missions were conducted per year, suggesting an average spacecraft life-time of approximately 24 months. The 220 kg spacecraft had a diameter of 1.0 m and a main bus height of Funding Agency 1.5 m. A gravity-gradient beam was extended on-orbit to provide attitude stabilization. Unknown (U.S.S.R)

Discipline

Communications

Additional Information

Launch/Orbital information for Cosmos 2214

Experiments on Cosmos 2214

Data collections from Cosmos 2214

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

+ Privacy Policy and Important Notices NASA Official: Dr. Ed Grayzeck Curator: E. Bell, II Version 4.0.15, 15 April 2011

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Personnel Cosmos 2215

Publications NSSDC ID: 1992-068E Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The Strela 3 system was a communications satellite 22186 constellation devoted to military and government communications. It was a simple store-dump repeater system which were particulatly useful in relaying non-essential traffic Facts in Brief between the Russian Federation and overseas stations or Launch Date: 1992-10- forces. The Strela 3 system, which began in 1985, was 20 launched by the Tsyklon-3 booster from the Plesetsk Launch cosmodrome into orbits near 1400 km at inclinations of 82.6 Vehicle: Tsiklon-3 degrees with six spacecraft stacked atop each launch vehicle. Launch Site: Plesetsk, Two orbital planes were spaced 90 degrees apart, apparently Russia each contained 10-12 operational spacecraft. Normally, two Mass: 220.0 kg missions were conducted per year, suggesting an average spacecraft life-time of approximately 24 months. The 220 kg spacecraft had a diameter of 1.0 m and a main bus height of Funding Agency 1.5 m. A gravity-gradient beam was extended on-orbit to provide attitude stabilization. Unknown (U.S.S.R)

Discipline

Communications

Additional Information

Launch/Orbital information for Cosmos 2215

Experiments on Cosmos 2215

Data collections from Cosmos 2215

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

+ Privacy Policy and Important Notices NASA Official: Dr. Ed Grayzeck Curator: E. Bell, II Version 4.0.15, 15 April 2011

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Personnel Cosmos 2216

Publications NSSDC ID: 1992-068F Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The Strela 3 system was a communications satellite 22187 constellation devoted to military and government communications. It was a simple store-dump repeater system which were particulatly useful in relaying non-essential traffic Facts in Brief between the Russian Federation and overseas stations or Launch Date: 1992-10- forces. The Strela 3 system, which began in 1985, was 20 launched by the Tsyklon-3 booster from the Plesetsk Launch cosmodrome into orbits near 1400 km at inclinations of 82.6 Vehicle: Tsiklon-3 degrees with six spacecraft stacked atop each launch vehicle. Launch Site: Plesetsk, Two orbital planes were spaced 90 degrees apart, apparently Russia each contained 10-12 operational spacecraft. Normally, two Mass: 220.0 kg missions were conducted per year, suggesting an average spacecraft life-time of approximately 24 months. The 220 kg spacecraft had a diameter of 1.0 m and a main bus height of Funding Agency 1.5 m. A gravity-gradient beam was extended on-orbit to provide attitude stabilization. Unknown (U.S.S.R)

Discipline

Communications

Additional Information

Launch/Orbital information for Cosmos 2216

Experiments on Cosmos 2216

Data collections from Cosmos 2216

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

+ Privacy Policy and Important Notices NASA Official: Dr. Ed Grayzeck Curator: E. Bell, II Version 4.0.15, 15 April 2011

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Personnel Cosmos 2217

Publications NSSDC ID: 1992-069A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Cosmos 2217 was a Russian missile early warning satellite 22189 launched from the Plesetsk cosmodrome aboard a Molniya rocket. It was part of the Oko constellation of satellites and covered the plane 8 - 201 degree longitude of ascending node. Facts in Brief Launch Date: 1992-10- 21 Launch Vehicle: Molniya-M Launch Site: Plesetsk, Russia Mass: 1900.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline

Surveillance and Other Military

Additional Information

Launch/Orbital information for Cosmos 2217

Experiments on Cosmos 2217

Data collections from Cosmos 2217

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

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Personnel Cosmos 2218

Publications NSSDC ID: 1992-073A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Cosmos 2218 was part of a 6-satellite Russian military 22207 navigation system distributed in orbital planes spaced 30 degrees apart, and launched from the Plesetsk cosmodrome aboard a Cosmos rocket. Navigation information was derived Facts in Brief from Doppler-shifted VHF transmissions (approximately 150 Launch Date: 1992-10- and 400 MHz) of the satellite position and orbital data. By 29 acquiring fixes from several satellite, a user's location could be Launch calculated with an accuracy of 100 m. The time needed to Vehicle: Cosmos ascertain a position was dependent upon the user's latitude Launch Site: Plesetsk, and the number of operational spacecraft in orbit. Normally, Russia accurate location determination could be made within 1-2 Mass: 825.0 kg hours.

Funding Agency

Unknown (U.S.S.R)

Discipline

Navigation & Global Positioning

Additional Information

Launch/Orbital information for Cosmos 2218

Experiments on Cosmos 2218

Data collections from Cosmos 2218

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

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Personnel Cosmos 2219

Publications NSSDC ID: 1992-076A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Cosmos 2219 was a Russian ELINT (Electronic and Signals 22219 Intelligence) satellite launched from the Baikonur cosmodrome aboard a Zenit 2 rocket. Facts in Brief

Based on the first generation Tselina ELINT, TSNII-KS at the Launch Date: 1992-11- beginning of the 1970's developed the specifications for an 17 improved model with increased frequency range and on-board Launch Vehicle: Zenit method of determining the position of fixed transmitters. The Launch Site: Tyuratam Tselina-2 was authorised in March 1973 and handled by prime (Baikonur Cosmodrome), contractor TsNIRTI Minradioprom (M E Zaslovskiy) for the Kazakhstan ELINT equipment and KB Yuzhnoye (KB-3, B S Khimrov) for Mass: 6600.0 kg the spacecraft bus. The launch vehicle was by OKB MEI Minvuza (A F Bogomolov) and the encrypted communications system by 0-TsNII KS MO. The draft project was drawn up in Funding Agency the first quarter of 1974 and the MO approved the TTZ in May 1974. After a long review process the VPK issued the project Unknown (U.S.S.R) plan for development of the system in December 1976. It would now use the new Zenit launch vehicle. The first flight Discipline trials system was completed in December 1980, but delays in the development of the Zenit launch vehicle meant that the first Surveillance and Other two trials flights had to be aboard Proton boosters in 1984 and Military 1985. Zenit-boosted flights began in 1985 and the system was accepted into service in 1987. Additional Information

Launch/Orbital information for Cosmos 2219

Experiments on Cosmos 2219

Data collections from Cosmos 2219

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

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Personnel Cosmos 2220

Publications NSSDC ID: 1992-077A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Cosmos 2220 was a Russian photo surveillance satellite 22226 launched from the Plesetsk cosmodrome aboard a Soyuz rocket. Two small film capsules were recovered in flight and the main re-entry capsule with remaining film, camera, and Facts in Brief computer systems at end of flight. Launch Date: 1992-11- 20 Launch Vehicle: Soyuz-U Launch Site: Plesetsk, Russia Mass: 6600.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline

Surveillance and Other Military

Additional Information

Launch/Orbital information for Cosmos 2220

Experiments on Cosmos 2220

Data collections from Cosmos 2220

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

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Personnel Cosmos 2221

Publications NSSDC ID: 1992-080A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Cosmos 2221 was a Russian ELINT (Electronic and Signals 22236 Intelligence) satellite launched from the Plesetsk cosmodrome.

From 1965 to 1967 two dedicated ELINT systems were tested: Facts in Brief the Tselina and the Navy's US. Both reached service, since the Launch Date: 1992-11- Ministry of Defence could not force a single system on the 23 military services. Launch Vehicle: Tsiklon-3 Tselina was developed by Yuzhnoye and consisted of two Launch Site: Plesetsk, satellites: Tselina-O for general observations and Tselina-D for Russia detailed observations. ELINT systems for Tselina were first Mass: 2000.0 kg tested under the Cosmos designation in 1962 to 1965. The first Tselina-O was launched in 1970. The Tselina-D took a long time to enter service due to delays in payload development Funding Agency and weight growth. The whole Tselina system was not operational until 1976. Constant improvement resulted in Unknown (U.S.S.R) Tselina-O being abandoned in 1984 and all systems being put on Tselina-D. Discipline

Surveillance and Other Military

Additional Information

Launch/Orbital information for Cosmos 2221

Experiments on Cosmos 2221

Data collections from Cosmos 2221

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

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Personnel Cosmos 2222

Publications NSSDC ID: 1992-081A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Cosmos 2222 was a Russian missile early warning satellite 22238 launched from the Plesetsk cosmodrome aboard a Molniya rocket. It was part of the Oko constellation of satellites and covered the plane 1 - 270 degree longitude of ascending node. Facts in Brief Launch Date: 1992-11- 25 Launch Vehicle: Molniya-M Launch Site: Plesetsk, Russia Mass: 1900.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline

Surveillance and Other Military

Additional Information

Launch/Orbital information for Cosmos 2222

Experiments on Cosmos 2222

Data collections from Cosmos 2222

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

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Personnel Cosmos 2223

Publications NSSDC ID: 1992-087A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Cosmos 2223 was a Russian digital photo surveillance satellite 22260 launched from the Baikonur cosmodrome aboard a Soyuz-U rocket. It remained in orbit for 372 days. Facts in Brief

Launch Date: 1992-12- 09 Launch Vehicle: Soyuz-U Launch Site: Tyuratam (Baikonur Cosmodrome), Kazakhstan Mass: 6600.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline

Surveillance and Other Military

Additional Information

Launch/Orbital information for Cosmos 2223

Experiments on Cosmos 2223

Data collections from Cosmos 2223

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

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Personnel Cosmos 2224

Publications NSSDC ID: 1992-088A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Cosmos 2224 was part of a Russian constellation of satellites 22269 comprised of an echelon of the Missile Attack Warning System (SPRN), which was operated by the Air Defense Forces of the Ministry of Defense. According to Soviet officials, the early Facts in Brief warning satellites could detect missile launches within 20 Launch Date: 1992-12- seconds of lift-off. 17 Launch Vehicle: Proton Each satellite possessed a perigee of about 600 km, an Launch Site: Tyuratam apogee of nearly 40,000 km, and an inclination of 63 degrees. (Baikonur Cosmodrome), This orbit was superfically similar to that employed by the Kazakhstan Molniya communications satellites but was distinguished by Mass: 2200.0 kg initial argument of perigee 316-319 degrees, including to the Molniya 280-288 degree arguments of perigee. The seemingly minor difference significantly affected the shape of the Funding Agency satellite's groundtrack in the Northern Hemisphere. Unknown (U.S.S.R) Russian early warning spacecraft were more affected by gravitational perturbations due to their higher argument of Discipline perigee and, therefore, performed periodic station-keeping maneuvers to maintain an acceptable groundtrack. In addition, Earth Science the argument of perigee migrated slightly over time (due to inclination variations), causing an alteration in the shape of the groundtrack. Instead of expending additional propellant to Additional prevent the argument of perigee shift, Russian spacecraft Information controllers altered the satellite's ascending node. This had the Launch/Orbital effect of "stabilizing" the apogee point about which surveillance information for Cosmos operations were performed. 2224

Experiments on Cosmos 2224

Data collections from Cosmos 2224

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

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Personnel Cosmos 2225

Publications NSSDC ID: 1992-091A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Cosmos 2225 was the fourth of the sixth generation photo 22280 reconnaisance satellites launched from the Baikonur cosmodrome using the Soyuz-U2 launch vehicle, which had otherwise been restricted to supporting Soyuz-TM and Facts in Brief Progress-M missions. The spacecraft was inserted into an Launch Date: 1992-12- orbital inclination of 64.8 degrees with mean operational 22 altitudes normally between 240 and 260 km. The sixth Launch generation spacecraft, believed to carry both film return Vehicle: Soyuz-U capsules and digital transmission capabilities, have only flown Launch Site: Tyuratam six times; once each year during 1989-1993 and once in 1997. (Baikonur Cosmodrome), Kazakhstan Mass: 6500.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline

Surveillance and Other Military

Additional Information

Launch/Orbital information for Cosmos 2225

Experiments on Cosmos 2225

Data collections from Cosmos 2225

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

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Personnel Cosmos 2226

Publications NSSDC ID: 1992-092A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Cosmos 2226 was a Russian geodetic satellite launched from 22282 the Plesetsk cosmodrome aboard a Tsyklon 3 rocket. It provided five ways for determining satellite position: Facts in Brief

1. Doppler system working at 150 and 400 MHz and providing Launch Date: 1992-12- 3 cm accuracy 2. High intensity lights flashing 3 times per 22 second, allowing precise location by ground observatories 3. Launch Radio transponder working at 5.7/3.4 GHz and providing 5 m Vehicle: Tsiklon-3 accuracy 4. Laser reflector providing 1.5 m accuracy 5. Radar Launch Site: Plesetsk, reflector working at 9.4 GHz providing 5 m altitude accuracy. Russia Mass: 1500.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline

Earth Science

Additional Information

Launch/Orbital information for Cosmos 2226

Experiments on Cosmos 2226

Data collections from Cosmos 2226

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

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Personnel Cosmos 2227

Publications NSSDC ID: 1992-093A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Cosmos 2227 was a Russian ELINT (Electronic and Signals 22284 Intelligence) satellite launched from the Baikonur cosmodrome aboard a Zenit 2 rocket. Facts in Brief

Based on the first generation Tselina ELINT, TSNII-KS at the Launch Date: 1992-12- beginning of the 1970's developed the specifications for an 25 improved model with increased frequency range and on-board Launch Vehicle: Zenit method of determining the position of fixed transmitters. The Launch Site: Tyuratam Tselina-2 was authorised in March 1973 and handled by prime (Baikonur Cosmodrome), contractor TsNIRTI Minradioprom (M E Zaslovskiy) for the Kazakhstan ELINT equipment and KB Yuzhnoye (KB-3, B S Khimrov) for Mass: 6000.0 kg the spacecraft bus. The launch vehicle was by OKB MEI Minvuza (A F Bogomolov) and the encrypted communications system by 0-TsNII KS MO. The draft project was drawn up in Funding Agency the first quarter of 1974 and the MO approved the TTZ in May 1974. After a long review process the VPK issued the project Unknown (U.S.S.R) plan for development of the system in December 1976. It would now use the new Zenit launch vehicle. The first flight Discipline trials system was completed in December 1980, but delays in the development of the Zenit launch vehicle meant that the first Surveillance and Other two trials flights had to be aboard Proton boosters in 1984 and Military 1985. Zenit-boosted flights began in 1985 and the system was accepted into service in 1987. Additional Information

Launch/Orbital information for Cosmos 2227

Experiments on Cosmos 2227

Data collections from Cosmos 2227

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

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Personnel Cosmos 2228

Publications NSSDC ID: 1992-094A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Cosmos 2228 was a Russian ELINT (Electronic and Signals 22286 Intelligence) satellite launched from the Plesetsk cosmodrome.

From 1965 to 1967 two dedicated ELINT systems were tested: Facts in Brief the Tselina and the Navy's US. Both reached service, since the Launch Date: 1992-12- Ministry of Defence could not force a single system on the 25 military services. Launch Vehicle: Tsiklon-3 Tselina was developed by Yuzhnoye and consisted of two Launch Site: Plesetsk, satellites: Tselina-O for general observations and Tselina-D for Russia detailed observations. ELINT systems for Tselina were first Mass: 2000.0 kg tested under the Cosmos designation in 1962 to 1965. The first Tselina-O was launched in 1970. The Tselina-D took a long time to enter service due to delays in payload development Funding Agency and weight growth. The whole Tselina system was not operational until 1976. Constant improvement resulted in Unknown (U.S.S.R) Tselina-O being abandoned in 1984 and all systems being put on Tselina-D. Discipline

Surveillance and Other Military

Additional Information

Launch/Orbital information for Cosmos 2228

Experiments on Cosmos 2228

Data collections from Cosmos 2228

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

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Personnel CTA

Publications NSSDC ID: 1992-070C Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events CTA (Canadian Target Assembly), a Canadian spacecraft, was Canadian Target released from STS 52. Assembly 22214

Facts in Brief

Launch Date: 1992-10- 22 Launch Vehicle: Shuttle Launch Site: Cape Canaveral, United States Mass: 82.0 kg

Funding Agency

Unknown (Canada)

Disciplines

Engineering Surveillance and Other Military

Additional Information

Launch/Orbital information for CTA

Experiments on CTA

Data collections from CTA

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

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Personnel DFS Kopernikus 3

Publications NSSDC ID: 1992-066A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events DFS 3 was a German geostationary communications 22175 spacecraft launched by a Delta 2/7925 rocket from Cape Canaveral. It had 10 carrier frequencies. Facts in Brief

Launch Date: 1992-10- 12 Launch Vehicle: Delta II 7925 Launch Site: Cape Canaveral, United States Mass: 1400.0 kg

Funding Agency

Deutsche Bundespost (Federal Republic of Germany)

Discipline

Communications

Additional Information

Launch/Orbital information for DFS Kopernikus 3

Experiments on DFS Kopernikus 3

Data collections from DFS Kopernikus 3

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

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Personnel DoD-1

Publications NSSDC ID: STSDOD1 Maps Description Facts in Brief New/Updated Data

Lunar/Planetary Events The DoD-1 spacecraft is a classified Department of Defense Launch Date: 1992-12- satellite and represents the last major military payload currenly 02 planned for the shuttle fleet. Due to national security concerns, Launch no public discussion of the identification and purpose of DoD-1 Vehicle: Shuttle will take place. Launch Site: Cape Canaveral, United States Mass: 10552.0 kg

Funding Agency

Department of Defense (United States)

Discipline

Surveillance and Other Military

Additional Information

Launch/Orbital information for DoD-1 PDMP information for DoD-1 Telecommunications information for DoD-1

Experiments on DoD-1

Data collections from DoD- 1

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

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Personnel DSCS III-08

Publications NSSDC ID: 1992-006A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Defense Satellite Communications System (DSCS III-08) was USA 78 part of a US military satellite constellation placed in 21873 geosynchronous orbit to provide high-volume, secure voice and data communications. Phase II was a successor to the IDSCS (Initial Defense Satellite Communications System) Facts in Brief program which began in 1966 with the launch of the first 8 satellites of this constellation. The DSCS III system was used Launch Date: 1992-02- for high priority communications such as the exchange of 09 wartime information between defense officials and battlefield Launch Vehicle: Atlas 2 commanders. The military also used DSCS to transmit space Launch Site: Cape operations and early warning data to various systems and Canaveral, United States users. Funding Agency Each satellite orbits the earth at an altitude of more than 23,000 miles. They carried a single channel transponder used Department of Defense- for disseminating emergency action and force direction Department of the Air messages to nuclear capable forces. Each satellite utilized six Force (United States) super high frequency transponder channels capable of providing worldwide secure voice and high rate data communications. Discipline Communications

Additional Information

Launch/Orbital information for DSCS III- 08

Experiments on DSCS III- 08

Data collections from DSCS III-08

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

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Personnel DSCS III-09

Publications NSSDC ID: 1992-037A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Defense Satellite Communications System (DSCS III-09) was USA 82 part of a US military satellite constellation placed in 22009 geosynchronous orbit to provide high-volume, secure voice and data communications. Phase II was a successor to the IDSCS (Initial Defense Satellite Communications System) Facts in Brief program which began in 1966 with the launch of the first 8 satellites of this constellation. The DSCS III system was used Launch Date: 1992-07- for high priority communications such as the exchange of 02 wartime information between defense officials and battlefield Launch Vehicle: Atlas 2 commanders. The military also used DSCS to transmit space Launch Site: Cape operations and early warning data to various systems and Canaveral, United States users. Funding Agency Each satellite orbits the earth at an altitude of more than 23,000 miles. They carried a single channel transponder used Department of Defense- for disseminating emergency action and force direction Department of the Air messages to nuclear capable forces. Each satellite utilized six Force (United States) super high frequency transponder channels capable of providing worldwide secure voice and high rate data communications. Discipline Surveillance and Other Military

Additional Information

Launch/Orbital information for DSCS III- 09

Experiments on DSCS III- 09

Data collections from DSCS III-09

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

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Personnel Ekran 20

Publications NSSDC ID: 1992-074A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Ekran 1 was a Russian communications satellite launched from 22210 the Baikonur Cosmodrome aboard a Proton 8K82K/Block DM rocket. It transmitted color and black-and-white USSR central television programs to the network of public receiving units Facts in Brief located in population centers in Siberia and the Far North. The Launch Date: 1992-10- single-unit body was equipped with solar panels, and active 30 liquid-gas phase-change thermoregulation system, and a Launch Vehicle: Proton corrective engine unit for making orbital adjustments. Twenty- Launch Site: Tyuratam five square metres of solar panels provided 1280 W of power. (Baikonur Cosmodrome), Kazakhstan Mass: 1970.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline

Communications

Additional Information

Launch/Orbital information for Ekran 20

Experiments on Ekran 20

Data collections from Ekran 20

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

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Personnel EURECA 1

Publications NSSDC ID: 1992-049B Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The European Space Agency's (ESA) European Retrievable European Retrievable Car Carrier (EURECA) was designed to be launched from the USA 22065 Space Shuttle, retrieved from another space shuttle flight 6 to 9 months later, refurbished on the ground and re-flown on another shuttle flight. The first mission (EURECA-1), launched Facts in Brief from STS 46 and retrieved by STS 57, was primarily devoted to research in materials and life sciences and radiobiology, all Launch Date: 1992-08- requiring a controlled microgravity environment. Experiments 02 were also conducted in earth science, solar physics, space Launch physics and astrophysics. Vehicle: Shuttle Launch Site: Cape EURECA was made of high-strength carbon-fibre struts and Canaveral, United States titanium nadal points joined together to form a framework of Mass: 4491.0 kg cubic elements. Thermal control on EURECA combined both EURECA 1 active and passive heat transfer and radiation systems. Active Funding Agency heat transfer was achieved by means of a freon cooling loop which dissipitated the thermal load through two radiators into European Space Agency space. The passive system made use of multilayer insulation (International) blankets combined with electrical heaters.

The electrical subsystem was powered by deployable and Disciplines retractable solar arrays together with four 40 amp-hour nickel- Astronomy cadmium batteries. When EURECA was in the Shuttle cargo bay, power was supplied by the Shuttle. The modular attitude Engineering and orbit control subsystem (AOCS) maintained attitude and Earth Science spacecraft orientation and stabilization. An orbit transfer Life Science assembly, consisting of four thrusters, was used to boost EURECA to its operational attitude (515 km) and return it to Microgravity retrievable orbit (about 300 km). Planetary Science Solar Physics EURECA was three-axis stabilized by means of a magnetic torque assembly together with a nitrogen reaction contral Space Physics assembly (RCA). Data handling was carried out by EURECAs data handling subsystem (DHS) supported by telemetry and Additional telecommand subsystems providing the link to the ground Information station. Launch/Orbital EURECA was attached to the Shuttle cargo bay by means of a information for EURECA three-point latching system. EURECA operations were 1 controlled by ESA's Space Operations Centre (ESOC) in Germany. The EURECA project was sponsored by the Italian Experiments on EURECA Space Agency (ASI). EURECA was developed under ESA 1 contracts with aerospace firms in Germany, Italy, the UK, Belgium, the Netherlands, and France. Data collections from EURECA 1 EURECA consisted of 15 experiments: (1) Solution Growth Facility (SGF) (Belgium); (2) Protein Crystallization Facility (PCF) (Germany); (3) Exobiology and Radiation Assembly (ERA) (Germany); (4) Multi-Furnace Assembly (MFA) (Italy); Questions or comments http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1992-049B[24/04/2011 0:13:54] NASA - NSSDC - Spacecraft - Details

(5) Automatic Mirror Furnace (AMF) (Germany); (6) Surface about this spacecraft can Forces Adhesion Instrument (SFA) (Italy); (7) High Precision be directed to: Coordinated Thermostat Instrument(HPT) (Germany); (8) Solar Constant Request and User Support and Variability Instrument (SOVA) (Belgium); (9) Solar Office. Spectrum Instrument (SOSP) (France); (10) Occultation Radiometer Instrument (ORI) (Belgium); (11) Wide Angle Telescope (WATCH) (Denmark); (12) Timeband Capture Cell Experiment (TICCE) (Great Britian); (13) Radio Frequency Ionization Thruster Assembly (RITA) (Germany); (14) Inter- Orbit Communications (IOC) (France/the Netherlands); (15) Advanced Solar Gallium Arsenide Array (ASGA) (Italy). See Longdon, N. in "Spaceflight", Vol. 34, July and August 1992.

Related Information/Data at NSSDC

STS 46 STS 57

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Personnel EUTELSAT-II F4

Publications NSSDC ID: 1992-041B Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events EUTELSAT-II F-4 was a communications geostationary 22028 satellite launched by an Ariane booster from the Kourou Space Center in French Guiana. It was originally stationed at 7 deg E. It was part of a constellation of 5 satellites that were basically Facts in Brief identical. With the arrival of the W series of satellites at the Launch Date: 1992-07- orbital positions until now used by EUTELSAT-II F1, F2, F3 09 and F4, these satellites were gradually relocated to new Launch Vehicle: Ariane positions where they could continue to be used for a full range Launch Site: Kourou, of telecommunications and television services. EUTELSAT-II French Guiana F4 was slightly modified by stretching its Widebeam in order to Mass: 1877.0 kg provide improved coverage of Eastern Europe, as far as Moscow. Funding Agency

European Telecommunications Satellite Consortium (International)

Discipline

Communications

Additional Information

Launch/Orbital information for EUTELSAT-II F4

Experiments on EUTELSAT-II F4

Data collections from EUTELSAT-II F4

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Personnel EUVE

Publications NSSDC ID: 1992-031A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The Extreme-Ultraviolet Explorer (EUVE) was a spinning BERKSAT spacecraft designed to rotate about the earth/sun line. EUVE Extreme Ultraviolet was a part of NASA's Explorer spacecraft series, and designed Explorer to operate in the extreme ultraviolet (EUV) range of the spectrum, from 70 - 760 Angstroms. This spacecraft's objective Explorer 67 was to carry out a full-sky survey, and subsequently, a deep- 21987 survey and pointed observations. Science objectives included discovering and studying UV sources radiating in this spectral region, and analyzing effects of the interstellar medium on the Facts in Brief radiation from these sources. Launch Date: 1992-06- EUVE 07 The full-sky survey was accomplished by three Wolter- Launch Vehicle: Delta Schwarzschild grazing-incidence telescopes. During the sky II survey, the satellite was spun three times per orbit to image a Launch Site: Cape 2 degree wide band of sky in each of four EUV passbands. Canaveral, United States The deep-survey was accomplished with a fourth Wolter- Mass: 3275.0 kg Schwarzschild grazing-incidence telescope, within a 2x180 Nominal degree region of sky. This telescope was also used for three- Power: 1100.0 W EUV bandpass spectroscopy of individual sources, providing ~ 1-2 Angstrom resolution spectra. The science instruments were attached to a Multi-mission Modular spacecraft (MMS). Funding Agency The MMS was 3-axis stabilized, with a stellar reference control system and solar arrays. NASA-Office of Space Science Applications The EUVE mission was extended twice, but cost and scientific (United States) merit issues led NASA to a decision to terminate the mission in 2000. EUVE satellite operations ended on January 31, 2001 Discipline when the spacecraft was placed in a safehold. Transmitters were commanded off on February 2, 2001. EUVE re-entered Astronomy the Earth's atmosphere over central Egypt at approximately 11:15pm EST on January 30, 2002. The mission is considered a success since it accomplished its scientific, technological, Additional and outreach goals. Information Launch/Orbital information for EUVE PDMP information for EUVE Telecommunications information for EUVE

Experiments on EUVE

Data collections from EUVE

Questions or comments

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

Personnel

Name Role Original Affiliation E-mail Dr. Llewellyn Mission NASA Goddard Space W. Operations Flight Center Nicholson Manager Mr. Marius Program NASA Headquarters B. Weinreb Manager Dr. Edward Program NASA Headquarters [email protected] J. Weiler Scientist Dr. Yoji Project NASA Goddard Space [email protected] Kondo Scientist Flight Center Mr. Hector Mission NASA Goddard Space [email protected] A. Zayas- Operations Flight Center Aguiar Manager Mr. James Project NASA Goddard Space [email protected] S. Manager Flight Center Barrowman

Selected References

EUVE guest observer program handbook, EUVE Guest Observer Center, NASA NRA 92-OSSA- 5, Appendix G, Jan. 1992.

US Active Archive for EUVE Information/Data

EUVE Archive at MAST(STScI) EUVE Archive at HEASARC

Other Sources of EUVE Information/Data

The EUVE home page

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Personnel Foton 8

Publications NSSDC ID: 1992-065A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Beginning in 1985 the USSR/CIS conducted annual unmanned Photon 8 space missions dedicated to materials science research. The 22173 Photon (Foton) spacecraft used for these flights was a derivative of the 1960's era Vostok/Voskhod manned spacecraft and the Zenit military reconnaissance satellites and Facts in Brief were very similar to the operational Bion and Resurs-F satellites. Prototype Photon satellites were launched during Launch Date: 1992-10- 1985-1987 as Cosmos 1645, Cosmos 1744, and Cosmos 08 1841. Since 1988, the spacecraft have been officially Launch Vehicle: Soyuz designated as Photon. Photon 8 conducted space materials Launch Site: Plesetsk, research jointly with Germany. Russia Mass: 6200.0 kg The 6,200-kg spacecraft was 6.2 m in length with a maximum diameter of 2.5 m and was divided into three major sections: Funding Agency the service/retro module, the payload capsule, and an equipment block. The 2.3 m diameter recoverable capsule Unknown (U.S.S.R) handled a payload of up to 700 kg and a volume of 4.7 m cubed. Electrical power was supplied entirely by storage batteries with 400 W average per day allocated to the payload Discipline (up to 700 W for 90 minutes each day). Mission durations for Microgravity the 8 Photon flights to the end of 1992 were 13-16 days.

To minimize perturbation forces, thereby maximizing Additional microgravity conditions, Photon spacecraft were placed in a Information mildly eccentric orbit at 62.8 degrees inclination and were not maneuvered during the mission. Prior to 1991 the annual Launch/Orbital Photon missions had always been launched in April or May. information for Foton 8 Launches were performed by the Soyuz booster from the Plesetsk cosmodrome, and recoveries made in Kazakhstan in Experiments on Foton 8 the primary manned recovery region northeast of the Baikonur cosmodrome. Data collections from Foton 8

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Personnel Freja

Publications NSSDC ID: 1992-064A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The Freja spacecraft carried instruments to better understand: 22161 the processes responsible for transverse energization of ions over the auroral oval; the nature of plasma cavities and their consequences to hot/cold plasma insteractions; low-altitude Facts in Brief electron/ion acceleration; the processes that germinate fine Launch Date: 1992-10- structures over the oval; wave phenomena and wave-particle 06 interactions. The mission was jointly sponsored by Sweden Launch Vehicle: Long and Germany, as a follow up to the Viking mission. It carried March eight instruments to monitor the auroral phenomeno and Launch Site: Jiuquan, processes. The spacecraft's spin axis was maintained with Freja Peoples Republic of China about 10 degrees from the Sun, with the spin period varied in Mass: 214.0 kg the range of 1-5 s. Nominal Power: 168.0 W

Funding Agencies

Max-Planck-Institut (Federal Republic of Germany) Swedish Board for Space Activities (Sweden)

Discipline

Space Physics

Additional Information

Launch/Orbital information for Freja PDMP information for Freja Telecommunications information for Freja

Experiments on Freja

Data collections from Freja

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Personnel

Name Role Original Affiliation E-mail Dr. Gerhard Project Max-Planck-Institut fur [email protected] Haerendel Scientist Extraterrestrische Physik Mr. Sven Grahn Project Swedish Space Corporation Manager Prof. Rickard Project Swedish Institute for Space Physics [email protected] Lundin Scientist

Selected References

Andre, M., The Freja scientific satellite, Swedish Inst. of Space Phys., Oct. 1992.

Lundin, R., et al., The Freja project, Geophys. Res. Lett., 21, No. 17, 1823-1826, Aug. 1994.

Data from Freja Hot Plasma (F3H) experiment (Institute for Space Physics, Kiruna, Sweden) Magnetic Field Experiment team page (APL/JHU) Cold Plasma Analyzer page (U. Calgary) Hot Plasma Experiment page (Institute for Space Physics, Kiruna, Sweden) UV Imager page (U. Calgary)

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Personnel FSW-1 4

Publications NSSDC ID: 1992-064B Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events PRC 36, a People's Republic of China spacecraft, was PRC 36 launched from the Jiuquan Center by a Long March rocket. It 22162 was a retrievable spacecraft.

Facts in Brief

Launch Date: 1992-10- 06 Launch Vehicle: Long March Launch Site: Jiuquan, Peoples Republic of China Mass: 2100.0 kg

Funding Agency

Unknown (Peoples Republic of China)

Discipline

Earth Science

Additional Information

Launch/Orbital information for FSW-1 4

Experiments on FSW-1 4

Data collections from FSW- 1 4

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Personnel Galaxy 5

Publications NSSDC ID: 1992-013A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Galaxy 5 was a US commercial communications satellite 21906 launched from Cape Canaveral by an Atlas rocket.

The spacecraft was used for general communications services, Facts in Brief such as television relay, voice and data. It was dedicated to Launch Date: 1992-03- cable television transmission across the United States. The 13 fleet's ground control station is in Long Beach, CA, with Launch Vehicle: Atlas telemetry and command terminals in Brooklyn, NY, and Launch Site: Cape Fillmore, CA. Canaveral, United States Mass: 1412.0 kg Galaxy 5 carried a McDonnell Douglas payload assist module that performed the conventional third-stage rocket function of insertion into an elliptical transfer orbit. The apogee motor, Funding Agency which placed the satellite in near-synchronous orbit above the equator, was a Thiokol Star 30 solid propellant rocket motor. Pan American Satellite (United States)

Discipline

Communications

Additional Information

Launch/Orbital information for Galaxy 5

Experiments on Galaxy 5

Data collections from Galaxy 5

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Personnel Galaxy 7

Publications NSSDC ID: 1992-072A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The Galaxy VII satellite brought C-band and Ku--band services 22205 together for the first time on the same spacecraft for American customers of PanAmSat Corp. The spacecraft was a version of the three-axis, body-stabilized HS 601 model built by Hughes Facts in Brief Space and Communications Company (HSC). It was launched Launch Date: 1992-10- aboard an Ariane 42P rocket from Kourou, French Guiana. 27 With 24 C-band and 24 Ku-band transponders, the satellite Launch Vehicle: Ariane offered double the capacity of the satellite it replaced. It was 42P configured to provide coverage to all 50 United States plus the Launch Site: Kourou, Caribbean basin, with a signal strength of 36 dBW in C-band French Guiana and 45 dBW in Ku-band across the contiguous US. It was Mass: 1683.0 kg positioned in a geostationary orbit at 91 degrees W and had an expected lifetime of 12 years. Funding Agency

Pan American Satellite (United States)

Discipline

Communications

Additional Information

Launch/Orbital information for Galaxy 7

Experiments on Galaxy 7

Data collections from Galaxy 7

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Personnel Geotail

Publications NSSDC ID: 1992-044A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The solar wind draws the Earth's magnetic field into a long tail GTL on the nightside of the Earth and stores energy in the stretched ISTP/Geotail field lines of the magnetotail. During active periods, the tail couples with the near-Earth magnetosphere, sometimes GGS/Geotail releasing energy stored in the tail and activating auroras in the Geomagnetic Tail Lab polar ionosphere. 22049

The Geotail mission measures global energy flow and transformation in the magnetotail to increase understanding of Facts in Brief fundamental magnetospheric processes. This includes the physics of the magnetopause magnetospheric boundary Launch Date: 1992-07- regions, the lobe and plasma sheet, and reconnection and 24 neutral line formation, i.e., the mechanisms processes of input, Launch Vehicle: Delta transport, storage, release and conversion of mass, II momentum and energy in the magnetotail. Launch Site: Cape Canaveral, United States Geotail, together with Wind, Polar, SOHO, and Cluster Mass: 980.0 kg projects, constitute a cooperative scientific satellite project Nominal Geotail designated the International Solar Terrestrial Physics (ISTP) Power: 273.0 W program which aims at gaining improved understanding of the physics of solar-terrestrial relations. Funding Agencies

Geotail is a spin-stabilized spacecraft utilizing mechanically Institute of Space and despun antennas with a design lifetime of about four years. Aeronautical Science, U The nominal spin rate of the spacecraft is about 20 rpm around of Tokyo (Japan) a spin axis maintained between 85-89 degrees to the ecliptic NASA-Office of Space plane. Geotail is cylindrical, approximately 2.2 m in diameter, Science Applications and 1.6 m high. with It has body-mounted solar cells. Geotail (United States) also has and a back-up battery subsystem which that operates when the spacecraft is in the Earth's shadow (limited to 2 hrs). Real-time telemetry data transmitted in X-band are received at Discipline the Usuda Deep Space Center (UDSC) in Japan. There are two tape recorders on board, each with a capacity of 450 Mb, Space Physics which allows daily 24-hour data coverage and are collected in playback mode by the NASA Deep Space Network (DSN). Additional Information The Geotail mission is divided into two phases. During the two- year initial phase, the orbit apogee was kept on the nightside Launch/Orbital of the Earth by using the Moon's gravity in a series of double- information for Geotail lunar swing-by maneuvers that result in the spacecraft PDMP information for spending most of its time in the distant magnetotail (maximum Geotail apogee about 200 Earth radii) with a period varying from one to four months. Then, starting in November 1994, there were a Telecommunications series of maneuvers to bring the spacecraft into its near-Earth information for Geotail orbit. This transition orbit lasted about three months with the apogee varying from 50 RE to 30 RE. The second phase is Experiments on Geotail dedicated to the study of near-Earth magnetospheric processes, including neutral line formation. Data collections from Geotail http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1992-044A[24/04/2011 0:17:26] NASA - NSSDC - Spacecraft - Details

Details on the Geotail mission and instrumentation are given in the Journal of Geomagnetism and Geoelectricity (Vol. 46, No. 1, 1994); online from JGG at Questions or comments about this spacecraft can http://www.terrapub.co.jp/journals/EPS/JGG be directed to: Dr. Timothy E. Eastman.

Personnel

Name Role Original Affiliation E-mail Dr. Kunginori Project Institute of Space and Tono Uesugi Manager Aeronautical Science Dr. Donald H. Project NASA Goddard Space [email protected] Fairfield Scientist Flight Center Dr. Charles Program NASA Headquarters [email protected] P. Holmes Scientist Dr. Atsuhiro Program NASA Goddard Space [email protected] Nishida Manager Flight Center Dr. Toshifumi General Institute of Space and [email protected] Mukai Contact Aeronautical Science Mr. Kenneth Project NASA Goddard Space [email protected] O. Sizemore Manager Flight Center

Selected References

Dunham, D. W., et al., Double-lunar swingby trajectories for the spacecraft of the International Solar Terrestrial Physics program, In--Orbital Mechanics and Mission Design, Volume 69, Advances in the Astronautical Sciences, edited by J. Teles, p. 285, 1989.

Nishida, A., et al., Geotail mission to explore earth's magnetotail, EOS, 73, No. 40, Oct. 1992.

Other Sources of Geotail Data/Information

Geotail project (JAXA) ISTP page (NASA)

Comprehensive Plasma Instrument (CPI) Energetic Particles and Ion Composition (EPIC) DARTS

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Personnel Gorizont 25

Publications NSSDC ID: 1992-017A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Gorizont 25 was a Russian geosynchronous communications 21922 satellite. It was launched to provide telephone, telegraph and fax communications services, in addition to relaying TV and radio broadcasts, and supported maritime and international Facts in Brief communications. It was stationed at 103 deg E. It transmitted Launch Date: 1992-04- in Siberia and was the solution to the communications 01 problems in Russia's earther region. Launch Vehicle: Proton Launch Site: Tyuratam The Gorizont spacecraft possessed an initial mass in excess of (Baikonur Cosmodrome), 2.1 metric tons and have demonstrated a lifetime of nearly 10 Kazakhstan years, although a 5-year service life was more common. The Mass: 2125.0 kg 3-axis stabilized satellite was approximately 2 m in diameter and 5 m long with two large solar arrays capable of generating 1.3 kW of electrical power for the first 3 years. Seven separate Funding Agency transmission antennas allowed a variety of reception patterns for both broad and localized terrestrial regions. Russian Space Agency (Russia) A typical Gorizont communications payload included six general purpose (TV, audio, facsimile) 6/4 GHz transponders Discipline (five 12.5 W and one 60 W), one Luch 14/11 GHz transponder (15 W), and one Volna 1.6/1.5 GHz transponder (20 W). The Communications Volna transponders were INMARSAT-compatible and were extensively used by the Russian merchant marine fleet via the primary GEO television rebroadcasting system, supporting all Additional five Federation time zones: Zone 1 from 140 deg E, Zone 2 Information from 90 deg E, Zone 3 from 80 deg E, Zone 4 from 53 deg E, Launch/Orbital and Zone 5 from 14 deg W. These transmissions were handled information for Gorizont by Orbita (12-m receiving antenna) and Moskva (2.5-m 25 receiving antenna) ground stations in the 6/4 GHz band. The Moskva Globalnaya system was inaugurated in 1989 using 4- Experiments on Gorizont m receiving antennas and serviced by Gorizonts at 96.5 deg E 25 and 11 deg W. Data collections from Gorizont 25

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Personnel Gorizont 26

Publications NSSDC ID: 1992-043A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Gorizont 26 was a Russian geosynchronous communications 22041 satellite. It was launched to provide telephone, telegraph and fax communications services, in addition to relaying TV and radio broadcasts, as well as supporting maritime and Facts in Brief international communications. It was stationed at 349 deg E. Launch Date: 1992-07- 14 The Gorizont spacecraft possessed an initial mass in excess of Launch Vehicle: Proton 2.1 metric tons and have demonstrated a lifetime of nearly 10 Launch Site: Tyuratam years, although a 5-year service life was more common. The (Baikonur Cosmodrome), 3-axis stabilized satellite was approximately 2 m in diameter Kazakhstan and 5 m long with two large solar arrays capable of generating Mass: 2125.0 kg 1.3 kW of electrical power for the first 3 years. Seven separate transmission antennas allowed a variety of reception patterns for both broad and localized terrestrial regions. Funding Agency

A typical Gorizont communications payload included six Unknown (U.S.S.R) general purpose (TV, audio, facsimile) 6/4 GHz transponders (five 12.5 W and one 60 W), one Luch 14/11 GHz transponder Discipline (15 W), and one Volna 1.6/1.5 GHz transponder (20 W). The Volna transponders were INMARSAT-compatible and were Communications extensively used by the Russian merchant marine fleet via the primary GEO television rebroadcasting system, supporting all five Federation time zones: Zone 1 from 140 deg E, Zone 2 Additional from 90 deg E, Zone 3 from 80 deg E, Zone 4 from 53 deg E, Information and Zone 5 from 14 deg W. These transmissions were handled Launch/Orbital by Orbita (12-m receiving antenna) and Moskva (2.5-m information for Gorizont receiving antenna) ground stations in the 6/4 GHz band. The 26 Moskva Globalnaya system was inaugurated in 1989 using 4- m receiving antennas and serviced by Gorizonts at 96.5 deg E Experiments on Gorizont and 11 deg W. 26

Data collections from Gorizont 26

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Personnel Gorizont 27

Publications NSSDC ID: 1992-082A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Gorizont 27 was a Russian geosynchronous communications 22245 satellite. It was launched to provide telephone, telegraph and fax communications services, in addition to relaying TV and radio broadcasts, as well as support maritime and international Facts in Brief communications. It was stationed at 53 deg E. Launch Date: 1992-11- 27 The Gorizont spacecraft possessed an initial mass in excess of Launch Vehicle: Proton 2.1 metric tons and have demonstrated a lifetime of nearly 10 Launch Site: Tyuratam years, although a 5-year service life was more common. The (Baikonur Cosmodrome), 3-axis stabilized satellite was approximately 2 m in diameter Kazakhstan and 5 m long with two large solar arrays capable of generating Mass: 2125.0 kg 1.3 kW of electrical power for the first 3 years. Seven separate transmission antennas allowed a variety of reception patterns for both broad and localized terrestrial regions. Funding Agency

A typical Gorizont communications payload included six Unknown (U.S.S.R) general purpose (TV, audio, facsimile) 6/4 GHz transponders (five 12.5 W and one 60 W), one Luch 14/11 GHz transponder Discipline (15 W), and one Volna 1.6/1.5 GHz transponder (20 W). The Volna transponders were INMARSAT-compatible and were Communications extensively used by the Russian merchant marine fleet via the primary GEO television rebroadcasting system, supporting all five Federation time zones: Zone 1 from 140 deg E, Zone 2 Additional from 90 deg E, Zone 3 from 80 deg E, Zone 4 from 53 deg E, Information and Zone 5 from 14 deg W. These transmissions were handled Launch/Orbital by Orbita (12-m receiving antenna) and Moskva (2.5-m information for Gorizont receiving antenna) ground stations in the 6/4 GHz band. The 27 Moskva Globalnaya system was inaugurated in 1989 using 4- m receiving antennas and serviced by Gorizonts at 96.5 deg E Experiments on Gorizont and 11 deg W. 27

Data collections from Gorizont 27

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Personnel Hispasat 1A

Publications NSSDC ID: 1992-060A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Hispasat 1A, Spain's communications satellite, was launched 22116 by an Ariane-4 rocket from the Kourou Space Center in French Guiana. Based on the Eurostar spacecraft bus developed by British Aerospace and Matra Marconi, Hispasat was designed Facts in Brief to support civil, military and government communications Launch Date: 1992-09- requirements through an array of multi-frequency 10 transponders. Positioned at 30 degrees W, it carried 15 active Launch Vehicle: Ariane transponders: three X-band with one space and 12 Ku-band (8 4 at 55 W, 4 at 110 W) with six spares. The Hispasat bus Launch Site: Kourou, measured 1.7 m by 1.9 m by 2.1 m with a solar array span of French Guiana 22 m and an initial power capacity of 3.2 kW. A problem with Mass: 2194.0 kg the Spanish-manufactured primary antenna led Matra Marconi Nominal to procure an Aerospatiale antenna for Hispasat 1B. The Power: 3200.0 W spacecraft design life was 10 years. From its position over the Atlantic Ocean, it was capable of servicing not only Europe but also North and South America. Funding Agency

Unknown (Spain)

Discipline

Communications

Additional Information

Launch/Orbital information for Hispasat 1A

Experiments on Hispasat 1A

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Personnel IML 1

Publications NSSDC ID: IMGLAB1 Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The First International Microgravity Mission (IML-1) was the International Microgravity first in a series of missions with payloads dedicated to life Laboratory 1 science and microgravity science research. It was flown aboard Space Shuttle Discovery, STS-42; it was the 45th Shuttle flight and the 15th flight of Discovery. The primary Facts in Brief objective of IML-1 was to conduct science and technology Launch Date: 1992-01- investigations that required the low-gravity environment of 22 space, with emphasis on experiments that studied the effects Launch of microgravity on materials and processes and living Vehicle: Shuttle organisms. IML-1 was a cooperative effort involving six space Launch Site: Cape research institutions: the National Aeronautics and Space Canaveral, United States Administration (NASA), the Canadian Space Agency (CSA), Mass: 10440.0 kg the European Space Agency (ESA), the West German Research and Development Institute for Air and Spacecraft (DLR), the French National Center for Space Studies (CNES), Funding Agencies and the Japanese National Development Agency (NASDA). More than 200 scientists from 16 countries participated in the National Aeronautics and investigations. The crew aboard STS-42 consisted of a flight Space Administration crew composed of the commander, pilot, and a mission (United States) specialist; a payload crew composed of two mission Centre National d'Etudes specialists; and two payload specialists. The IML-1 payload Spatiales (France) consisted of 9 materials science investigations and 7 life European Space Agency science experiments most of which were maintained in the (International) onboard Spacelab Long Module. The Long Module, which measured 7 m in length and was connected to the middeck of Canadian Space Agency Discovery by a 5.8 m long tunnel, contained 12 Spacelab racks (Canada) (10 of which held experiments and stowage containers), and Deutsche 14 overhead stowage lockers. The Orbiter middeck lockers Forschunganstalt fuer housed additional experiments and ancillary equipment. Luft- und Raumfahrt (DLR, nee DFVLR) (Federal Republic of Germany) National Space Development Agency (NASDA) (Japan)

Disciplines

Life Science Microgravity

Additional Information

Launch/Orbital information for IML 1 PDMP information for IML http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=IMGLAB1[24/04/2011 0:19:38] NASA - NSSDC - Spacecraft - Details

1 Telecommunications information for IML 1

Experiments on IML 1

Data collections from IML 1

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Personnel

Name Role Original Affiliation E- mail Dr. Ronald J. White Program Scientist NASA Headquarters Mr. Robert O. Mission Manager NASA Marshall Space Flight McBrayer Center Mr. R. Wayne Richie Program Manager NASA Headquarters Dr. Robert S. Program Scientist NASA Headquarters Sokolowski Dr. Robert S. Snyder Mission Scientist NASA Marshall Space Flight Center Mr. John L. Frazier Deputy Mission NASA Marshall Space Flight Manager Center

Selected References

First International Microgravity Laboratory experiment descriptions, NASA TM-4353, First Edition, edited by T. Y. Miller, Marshall SFC, Alabama, Feb. 1992.

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Personnel Inmarsat 2-F4

Publications NSSDC ID: 1992-021B Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Inmarsat 2-F4 was a maritime satellite launched using an 21940 Ariane launch vehicle from the Kourou Space Center for the International Maritime Satellite Organization. It operated a total of four INMARSAT-2 satellites. Launched between 1990-92, Facts in Brief they each had a capacity equivalent to about 250 INMARSAT- Launch Date: 1992-04- A voice circuits. 15 Launch Vehicle: Ariane The spacecraft was built by an international consortium 44L headed by British Aerospace. Subcontractors included Hughes Launch Site: Kourou, Aircraft Company, Fokker (The Netherlands), Matra (France), French Guiana MBB (Germany), NEC (Japan), and Spar (Canada). Satellite Mass: 800.0 kg ground control operations contractors included CLTC (China), CNES (France), SED (Canada), Telespazio (Italy) and Intelsat. Funding Agency The INMARSAT-2s were three-axis-stabilized spacecraft based on the Matra/B Ae Eurostar platform. With a ten-year Inmarsat (International) design life, each satellite has a 1,300 kg launch mass, reducing to an initial 800 kg in orbit. Initial power rating was Discipline 1,200 W. Communications The communications payload comprised two transponders supporting satellite- to-mobile (service) links in L-band (1.6GHz uplink, 1.5GHz downlink) and satellite-to-earth station Additional (feeder) links in C-band (6.4GHz uplink, 3.6GHz downlink). Information Effective L-band isotropic radiated power (EIRP) was 39dBW. Launch/Orbital Each satellite's global beam covered roughly one-third of the information for Inmarsat earth's surface. 2-F4

Experiments on Inmarsat 2-F4

Data collections from Inmarsat 2-F4

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Personnel INSAT 2A

Publications NSSDC ID: 1992-041A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Stationed at 74 deg E, INSAT 2A performed communications Indian National Satellite functions for India as well as providing domestic long distance 2A telecommunications, meteorological earth observation and 22027 data collection services, direct satellite TV broadcasting to community TV receivers in rural and remote areas, radio and TV program distribution, and Satellite Aided Search and Facts in Brief Rescue services. Launch Date: 1992-07- 09 Launch Vehicle: Ariane Launch Site: Kourou, French Guiana Mass: 1900.0 kg

Funding Agency

Indian Space Research Organization (India)

Disciplines

Communications Earth Science

Additional Information

Launch/Orbital information for INSAT 2A

Experiments on INSAT 2A

Data collections from INSAT 2A

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

Personnel

Name Role Original Affiliation E-mail

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Personnel INTELSAT K

Publications NSSDC ID: 1992-032A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Intelsat K was an ITSO geostationary communications satellite 21989 launched by an Atlas-Centaur rocket from Cape Canaveral, Florida. Facts in Brief

Launch Date: 1992-06- 09 Launch Vehicle: Atlas- Centaur Launch Site: Cape Canaveral, United States Mass: 2928.0 kg

Funding Agency

International Telecommunications Satellite Corporation (International)

Discipline

Communications

Additional Information

Launch/Orbital information for INTELSAT K

Experiments on INTELSAT K

Data collections from INTELSAT K

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Personnel Japanese Earth Resource Satellite 1

Publications NSSDC ID: 1992-007A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The main purposes of this Japanese Earth Resources FUYO 1 Satellite-1 (JERS-1) are to check functions and performance of Fuyo 1 optical sensors and synthetic aperture radar and to establish an integrated system for observing earth resources. Other 21867 objectives include making surveys of Japanese land, monitoring agriculture and forestry, preserving the Facts in Brief environment, preventing disaster, and monitoring the coasts. With a box type shape, the JERS-1 has a body approximately Launch Date: 1992-02- 1 by 1.8 by 3.1 meters in size. The solar cell paddle measures 10 8 by 3.4 meters. A Mission Data Transmitter (MDT) and a Launch Vehicle: H-1 Mission Data Recorder (MDR) are equipped on the JERS-1. Launch The spacecraft uses a zero-momentum, strap-down, three-axis Site: Tanegashima, Japan control mode for high precision attitude control. Experiments Mass: 1400.0 kg on board the JERS-1 are Synthetic Aperture Radar (SAR) and Optical Sensors (OPS). The SAR is an active microwave imaging sensor achieving high resolution and having capability Funding Agency of operating all day and in all weather. The Optical Sensors National Space are multispectral imaging radiometers with high geometric Development Agency resolution and having capability of taking stereoscopic image. (NASDA) (Japan) The minimum lifetime of this mission is two years. The JERS-1 program is a joint development between the Ministry of International Trade and Industry (MITI) and the Science and Discipline Technology Agency (STA/National Space Development Agency of Japan (NASDA). See Tanaka, T.,"Japanese Earth Earth Science Observing Systems in the 1990's",Adv.Space Res., Vol. 11, No. 3, pp 201-211, 1991. Additional Information

Launch/Orbital information for Japanese Earth Resource Satellite 1

Experiments on Japanese Earth Resource Satellite 1

Data collections from Japanese Earth Resource Satellite 1

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Name Role Original Affiliation E-mail

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Personnel KH 12-1

Publications NSSDC ID: 1992-083A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events KH 12-1 was launched from Vandenberg AFB aboard a Titan 4 USA 86 rocket for the US Department of Defense. It was an electro- 22251 optical reconnaisance satellite that succedded the KH-11 series. It was heavier and believed to include a signals intelligence payload, it had wider spectral band sensitivity, Facts in Brief perhaps "real time" television capability, and other improvements compared to the KH-11 satellites. Data were Launch Date: 1992-11- transmitted via the SDS military relay satellites. 28 Launch Vehicle: Titan IV Launch Site: Vandenberg AFB, United States Mass: 19600.0 kg

Funding Agency

Department of Defense- Department of the Air Force (United States)

Discipline

Surveillance and Other Military

Additional Information

Launch/Orbital information for KH 12-1

Experiments on KH 12-1

Data collections from KH 12-1

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

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Personnel KITSAT-A

Publications NSSDC ID: 1992-052B Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events KITSAT-A, also known as Uribyol (meaning "our star"), a Uribyol South Korean spacecraft, was launched from Kourou in French Oscar 23 Guiana by an Ariane booster. It carried an electronic mail system, an earth-picture camera, and a device to measure 22077 cosmic rays. Facts in Brief

Launch Date: 1992-08- 10 Launch Vehicle: Ariane Launch Site: Kourou, French Guiana Mass: 50.0 kg

Funding Agency

University of Surrey (United Kingdom)

Disciplines

Communications Earth Science Space Physics

Additional Information

Launch/Orbital information for KITSAT-A

Experiments on KITSAT-A

Data collections from KITSAT-A

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

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Personnel LAGEOS II

Publications NSSDC ID: 1992-070B Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events LAGEOS II (LAser GEOdetic Satellite) was a very dense (high LAGEOS 2 mass-to-area ratio) laser retroreflector satellite that provided a 22195 permanent reference point in a very stable orbit for precision Earth dynamics measurements such as crustal motions, regional strains, fault motions, and polar motion. The satellite Facts in Brief also provided a reference point for measurement of Earth rotation variations, solid earth tides, and other kinematic and Launch Date: 1992-10- dynamic parameters associated with earthquake assessment 22 and alleviation. LAGEOS II, launched from the Shuttle STS 52, Launch was a joint project between NASA and the Italian Space Vehicle: Shuttle Agency (ASI). LAGEOS II was a passive satellite consisting of Launch Site: Cape 426 reflectors designed to return a laser beam to the Canaveral, United States originating station. Of the 426 reflectors (called ``cube corner Mass: 911.0 kg retroreflectors''), 422 were made of fused silica and four of germanium. Each reflector was 3.8 cm in diameter, and had a Funding Agencies flat, circular front face with three faces in the back that formed a solid right angle. The satellite was only 60 cm in diameter NASA-Office of Space and weighed only 405 Kg. Its compact and dense design was Science Applications to insure the orbit was as stable as possible. In conjunction (United States) with appropriate laser-tracking systems (about 16 mobile and Agenzia Spaziale Italiana 10 fixed laser-ranging facilities), LAGEOS II permitted extreme (Italy) precision ranging measurements for both geometric mode (multilateration) and orbital dynamic mode determinations of positions of points on the Earth. The high-accuracy range Discipline measurements from LAGEOS II's reference point were used to accomplish many extreme precision earth-dynamics Earth Science measurements required by the earthquake hazard assessment and alleviation objectives of the Crustal Dynamics Project Additional (CDP). The performance of LAGEOS II in orbit was limited only Information by degradation of the retroreflectors, so many decades of useful life can be expected. LAGEOS II was carried into its Launch/Orbital parking orbit by the Italian Research Interim Stage (IRIS) solid- information for LAGEOS fueled booster from the Shuttle payload bay. The apogee kick II motor (AKM), aboard LAGEOS II, placed the satellite in a PDMP information for circular orbit. The IRIS system consisted of the IRIS Spinning LAGEOS II Stage (ISS) and the Airborne Support Equipment (ASE). The ISS was a spin-stabilizing expendable stage that lifted Telecommunications LAGEOS II to its parking orbit. The ASE contained reusable information for LAGEOS structures and electrical equipment that controlled the payload II until deployment and returned with the Shuttle. The IRIS provided power while in the Shuttle payload bay while six Experiments on LAGEOS II batteries from the AKM provided power during orbit insertion. The power supply was carried in the LAGEOS Apogee Stage Data collections from (LAS), which contained all of the satellite's subsystems. LAGEOS II LAGEOS II was identical to LAGEOS I.

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Personnel

Name Role Original Affiliation E-mail Mr. Gilbert W. Project NASA Goddard Space Ousley, Sr. Manager Flight Center Dr. Miriam Program NASA Headquarters Baltuck Scientist Ing. Cesare Project Italian Space Agency Albanesi Manager Mr. James P. Deputy Project NASA Headquarters Murphy Manager Dr. Louis Caudill Program NASA Headquarters Manager Mr. Ronald Project NASA Goddard Space [email protected] Kolenkiewicz Scientist Flight Center Dr. Roberto Ibba Mission Italian Space Agency [email protected] Manager

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Personnel Mars Observer

Publications NSSDC ID: 1992-063A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Mars Observer, the first of the Observer series of planetary Mars missions, was designed to study the geoscience and climate of Geoscience/Climatology Mars. The primary science objectives for the mission were to: Orbiter (1) determine the global elemental and mineralogical character MGCO of the surface material; (2) define globally the topography and gravitational field; (3) establish the nature of the Martian 22136 magnetic field; (4) determine the temporal and spatial distribution, abundance, sources, and sinks of volatiles and Facts in Brief dust over a seasonal cycle; and, (5) explore the structure and circulation of the atmosphere. Launch Date: 1992-09- 25 The bus and electronics of the Observer series of spacecraft, Launch Vehicle: Titan Mars Observer used to study the terrestrial planets and near-Earth asteroids, III were derived from the Satcom-K and DMSP/TIROS spacecraft. Launch Site: Cape The rectangular bus section was 2.1 x 1.5 x 1.1 m. During the Canaveral, United States cruise phase of the mission, the high-gain antenna and the Mass: 1018.0 kg booms for the magnetometer (MAG/ER) and gamma-ray Nominal spectrometer (GRS) were partially deployed. When fully Power: 1147.0 W deployed, the two booms were each 6 m long. The 1.5 m diameter high-gain antenna was, when fully deployed, on a 5.5 m boom to allow for clearance over the solar array when the Funding Agencies antenna was pointed toward Earth. Centre National d'Etudes Spatiales (France) Pointing control for the spacecraft was maintained through the use of four reaction wheels. Attitude information was provided Russian Space Agency by a horizon sensor (which defined the direction of the nadir), a (U.S.S.R) star mapper (for inertial attitude), gyros and accelerometers NASA-Office of Space (for measuring angular rates and linear accelerations), and Science Applications multiple Sun sensors. Power was provided through a six-panel (United States) solar array which, when fully deployed, measured 7.0 x 3.7 m. During the cruise phase, however, only four panels were deployed (due to the proximity of the spacecraft to the sun) to Disciplines reduce the amount of power generated. During periods when Astronomy the spacecraft was in Mars' shadow, energy was to be provided by two Ni-Cd batteries, each with a capacity of 43 Planetary Science amp-hours. Additional The interplanetary cruise phase of the mission was intended Information primarily for spacecraft and instrument checkout and calibration. Two periods of data collection for the MAG/ER and Launch/Orbital GRS and one for the gravity wave experiment were planned information for Mars for this phase as well. During the four month period from Mars Observer orbital insertion until the spacecraft was to achieve its final PDMP information for mapping orbit, only data collection for the MAG/ER, GRS, and Mars Observer thermal emission spectrometer (TES) were scheduled. The mapping phase of the mission was scheduled to nominally last Telecommunications one Martian year. Mars Observer was also to support the information for Mars acquisition of data from the Russian Mars 1994 mission Observer through the use of the joint French-Russian-American Mars http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1992-063A[24/04/2011 0:25:22] NASA - NSSDC - Spacecraft - Details

Balloon Relay instrument. Experiments on Mars Observer Contact with Mars Observer was lost on August 21, 1993, three days before scheduled orbit insertion, for unknown Data collections from Mars reasons and has not been re-established. It is not known Observer whether the spacecraft was able to follow its automatic programming and go into Mars orbit or if it flew by Mars and is now in a heliocentric orbit. Later investigation concluded the Questions or comments most probable cause of the mishap was a fuel line rupture about this spacecraft can during fuel tank pressurization which would have caused the be directed to: Dr. David R. spacecraft to spin uncontrollably. Although none of the primary Williams. objectives of the mission were achieved, cruise mode data were collected up to loss of contact. The total cost of the Mars Observer mission including development, construction, launch, and ground support is estimated at $813 million.

Personnel

Name Role Original Affiliation E-mail Mr. David D. Project NASA Jet Propulsion Evans Manager Laboratory Dr. Arden L. Project Scientist California Institute of [email protected] Albee Technology Mr. Frank D. Deputy Project NASA Jet Propulsion [email protected] Palluconi Scientist Laboratory Dr. William L. Program NASA Headquarters Piotrowski Manager Dr. Bevan M. Program NASA Headquarters French Scientist

Selected References

Palocz, S., Mars Observer mission and systems overview, J. Spacecr. Rockets, 28, No. 5, 491- 497, Sep.-Oct. 1991.

Potts, D. L., Mars Observer spacecraft description, J. Spacecr. Rockets, 28, No. 5, 507-514, Sep.-Oct. 1991.

Blume, W. H., et al., Mars Observer mission plan, J. Spacecr. Rockets, 28, No. 5, 522-529, Sep.-Oct. 1991.

Albee, A. L., et al., Mars Observer mission, J. Geophys. Res., 97, No. E5, 7665-7680, May 1992.

Other Mars Observer Information Reports on the loss of Mars Observer What Happened to the Mars Observer? - from the FAQ

Related Information at NSSDC Mars Global Surveyor - the Mars Observer replacement Mars Home Page

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La Mars Observer fue una sonda lanzada el 22 de agosto de 1992 por los Estados Unidos a estudiar el planeta Marte. Se trató de la primera misión marciana de la NASA tras el lanzamiento de las Viking en 1975- 76. Mars Observer Debía haber permanecido en órbita durante un año marciano para estudiar el planeta. Sin embargo, Dibujo artístico de la sonda se perdió contacto con la sonda tres días antes de entrar en órbita de Marte.

Objetivos

Los objetivos básicos de la sonda eran:

1. Determinar la composición mineralógica de la superficie de Marte. 2. Definir la topografía y campo gravitatorio del planeta. Datos de la misión 3. Establecer la naturaleza del campo magnético Nombre: Mars Observer marciano. 4. Determinar la distribución Organización: NASA espacial y temporal de los elementos volátiles y el Constructor: Malin Space Science Systems polvo en la atmósfera, así como sus fuentes y Coste: entre 813 y 980 millones de $ sumideros. 5. Explorar la estructura y Cohete lanzador: Titan 34D circulación de la atmósfera planetaria. Tipo de misión: Orbitador 6. Servir como relé de comunicaciones para el Masa: 2.573 kg (1.018 kg sin combustible) globo franco-ruso de la misión Marshnik 94 (rebautizada después 25 de septiembre de 1992 00:35 UTC como Marsnik 96). Lanzamiento: Cabo Cañaveral LC40 28°33′43″N 80°34′38″O Diseño básico Último contacto: 22 de agosto de 1993 La Mars Observer debía haber sido la primera de una nueva clase de Llegada a Marte: (prevista) 25 de agosto sondas llamadas genéricamente Planetary Observer. Además de la Mars Observer se propuso el lanzamiento de la Lunar Observer y la Mercury Observer. Los asteroides cercanos a la Tierra entraban en la lista de posibles objetivos.

Preparativos para el lanzamiento de la Mars Observer.

Los principales elementos de la sonda eran:

1. Cuerpo principal (bus): tanto el bus como la electrónica de la sonda se basó en satélites terrestres como los Satcom y los DMSP/TIROS. El bus era poliédrico y medía 2,1 * 1,5 * 1,1 metros. 2. Pértigas: llevaba dos pértigas para ubicar el magnetómetro y el espectómetro de rayos gamma. Durante el tránsito Tierra-Marte estas pértigas se mantuvieron sólo parcialmente desplegadas. Una vez desplegadas medían 6 metros cada una. 3. Estabilización: se conseguía en los 3 ejes, mediante cuatro volantes de reacción. 4. Orientación: se conseguía mediante un sensor de horizonte, un rastreador de estrellas, giroscopios, acelerómetros y diversos sensores del Sol. 5. Comunicaciones: la sonda se comunicaba con tierra utilizando una antena de 1,5 metros de diámetro ubicada en el extremo de un mástil de 5,5 y que no se desplegaba hasta que no se hubiese llegado a Marte. 6. Energía: la energía se conseguía mediante paneles solares, que proporcionaban un potencia de entre 1.100 y 1.500 vatios. Durante la fase de crucero había desplegados sólo cuatro, al llegar a Marte se desplegarían otros dos. En total, los seis medían 7 * 3,7 metros. Para abastecerse en los períodos en los que se sumergía en la sombra del planeta, llevaba dos baterías de níquel-cadmio, cada una con capacidad de 43 amperios/hora. 7. Motores: tanto los principales como los de posición utilizaban monometilhidracina como combustible y tetróxido de nitrógeno como comburente. Los tanques estaban presurizados con helio.

Instrumental científico

La sonda contaba con el siguiente instrumental científico a bordo:

1. Espectrómetro de rayos gamma (GRS): diseñado para determinar la abundancia de elementos químicos en la superficie de Marte. 2. Espectrómetro de emisión termal (TES): escogido para mapear el contenido mineral de las rocas, hielos y nubes. 3. Cámara (MOC): constaba en realidad de dos cámaras. Una era de baja resolución, para estudiar el clima, y la otra era de alta resolución, para estudiar áreas selectas del planeta. 4. Altímetro láser: embarcado para determinar el relieve superficial. 5. Radiómetro infrarrojo de modulación por presión (PMIRR): diseñado para medir las características del polvo y condensaciones en la atmósfera. 6. Experimento de radio: empleo del transmisor-receptor de la sonda para investigar cómo las ondas de radio atravesaban la atmósfera y para determinar el campo gravitatorio. 7. Magnetómetro y relfector de electrones: diseñado para determinar la naturaleza del campo magnético marciano y su interacción con el viento solar.

Desarrollo de la misión

Lanzamiento y fase de crucero

La sonda se lanzó sin incidentes el 25 de septiembre de 1992 mediante un cohete Titan 34D. Durante la fase de crucero la misión se desarrolló con normalidad, aprovechándose para calibrar la sonda y su instrumental.

Pérdida [editar]

El 21 de agosto de 1993, tres días antes de que se realizara la maniobra de inserción orbital en torno a Marte, se ordenó a la sonda que presurizara sus tanques de combustible. Tras ello, debía ponerse en contacto con la Tierra. Sin embargo nunca se recibió de nuevo señal de la sonda.

Investigación posterior

Se creó el Coffey Board para determinar las causas de la pérdida de la sonda. Debido a que ningún datos transmitido previamente por la sonda hacía sospechar la existencia de un problema y que la comunicación nunca se restableció, no se pudo determinar la causa con total exactitud, aunque se llegó a determinar cuál era el motivo más probable.

Se comprobó que una válvula de combustible que llevaba la Mars Observer había sido adoptada de satélites en órbita terrestre. Sin embargo en estos satélites la presurización de los tanques de combustible se realiza poco después del lanzamiento y no meses después (como se intentó hacer con la Mars Observer). Se considera que la válvula habría fallado y se habría producido una fuga de combustible (hidracina) y presurizante helio. Esto habría llevado a una serie de problemas, todos ellos potencialmente fatales:

1. La hidracina utilizada como combustible es altamente corrosiva, por lo que una fuga de ésta habría dañado fatalmente los equipos. 2. La fuga habría hecho girar a la sonda de forma incontrolada, lo que habría desorientado la antena respecto la Tierra, imposibilitando restablecer comunicación. 3. El giro, además, habría desorientado los paneles solares respecto al Sol, por lo que la sonda no habría tardado en quedarse sin energía.

Otras posibles fuentes del error fueron:

1. Pérdida de energía eléctrica por cortocircuito. 2. Sobrepresurización del tanque de combustible por fallo del regulador, con la consiguiente rotura. 3. Eyección accidental de un iniciador pirotécnico en el interior de algún elemento de la sonda.

Además se identificaron otros dos posibles escenarios:

1. Fallo de la computadora de a bordo, así como de su reserva. 2. Fallo del transmisor principal y el de reserva. El Jet Propulsion Laboratory de la NASA, aunque concordó básicamente con las conclusiones de la Comisión Coffey, apuntó también a que el fallo de una válvula podría haber permitido al oxidante haberse introducido en el depósito del combustible, produciéndose una explosión.

Consecuencias

El fracaso de la Mars Observer marcó el final de una etapa en la que la NASA lanzaba pocas sondas pero de alta calidad y elevado presupuesto. En adelante la política a seguir sería la de faster, cheaper, better (más rápido, más barato y mejor).

Los intrumentos de reserva de la Mars Observer terminarían volando en otras misiones de la NASA como la Mars Global Surveyor, la Mars Odyssey y la Mars Reconnaissance Orbiter.

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Personnel Molniya 1-83

Publications NSSDC ID: 1992-011A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Molniya 1/83 was a first-generation Russian communications 21897 satellite (COMSAT) orbited to test and perfect a system of radio communications and television broadcasting using earth satellites as active transponders and to experiment with the Facts in Brief system in practical use. The basic function of the satellite was Launch Date: 1992-03- to relay television programs and long-distance two-way 03 multichannel telephone, phototelephone, and telegraph links Launch from Moscow to the various standard ground receiving stations Vehicle: Molniya in the 'Orbita' system. The satellite was in the form of a Launch Site: Plesetsk, hermetically sealed cylinder with conical ends -- one end Russia contained the orbital correcting engine and a system of Mass: 1600.0 kg microjets, and the other end contained externally mounted solar and earth sensors. Inside the cylinder were (1) a high- sensitivity receiver and three 800-MHz 40-w transmitters (one Funding Agency operational and two in reserve), (2) telemetering devices that monitored equipment operation, (3) chemical batteries that Unknown (Russia) were constantly recharged by solar cells, and (4) an electronic computer that controlled all equipment on board. Mounted Discipline around the central cylinder were six large solar battery panels and two directional, high-gain parabolic aerials, 180 deg apart. Communications One of the aerials was directed continually toward the earth by the highly sensitive earth sensors. The second aerial was held in reserve. Signals were transmitted in a fairly narrow beam Additional ensuring a strong reception at the earth's surface. The satellite Information received telemetry at 1000 MHz. Television service was Launch/Orbital provided in a frequency range of 3.4 to 4.1 GHz at 40 w. information for Molniya 1- Molniya 1/83, whose cylindrical body was 3.4 m long and 1.6 m 83 in diameter, was much heavier than corresponding U.S. COMSATs, and it had about 10 times the power output of the Experiments on Molniya 1- Early Bird COMSAT. In addition, it did not employ a 83 geosynchronous equatorial orbit as have most U.S. COMSATs because such an orbit would not provide coverage for areas Data collections from north of 70 deg n latitude. Instead, the satellite was boosted Molniya 1-83 from a low-altitude parking orbit into a highly elliptical orbit with two high apogees daily over the northern hemisphere -- one over Russia and one over North America -- and relatively low perigees over the southern hemisphere. During its apogee, Questions or comments Molniya 1/83 remained relatively stationary with respect to the about this spacecraft can earth below for nearly 8 of every 12 hr. By placing three or be directed to: Coordinated more Molniya 1 satellites in this type of orbit, spacing them Request and User Support suitably, and shifting their orbital planes relative to each other Office. by 120 deg, a 24-hr/day communication system could be obtained.

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Personnel Molniya 1-84

Publications NSSDC ID: 1992-050A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Molniya 1/84 was a first-generation Russian communications 22068 satellite (COMSAT) orbited to test and perfect a system of radio communications and television broadcasting using earth satellites as active transponders and to experiment with the Facts in Brief system in practical use. The basic function of the satellite was Launch Date: 1992-08- to relay television programs and long-distance two-way 06 multichannel telephone, phototelephone, and telegraph links Launch from Moscow to the various standard ground receiving stations Vehicle: Molniya in the 'Orbita' system. The satellite was in the form of a Launch Site: Plesetsk, hermetically sealed cylinder with conical ends -- one end Russia contained the orbital correcting engine and a system of Mass: 1600.0 kg microjets, and the other end contained externally mounted solar and earth sensors. Inside the cylinder were (1) a high- sensitivity receiver and three 800-MHz 40-w transmitters (one Funding Agency operational and two in reserve), (2) telemetering devices that monitored equipment operation, (3) chemical batteries that Unknown (Russia) were constantly recharged by solar cells, and (4) an electronic computer that controlled all equipment on board. Mounted Discipline around the central cylinder were six large solar battery panels and two directional, high-gain parabolic aerials, 180 deg apart. Communications One of the aerials was directed continually toward the earth by the highly sensitive earth sensors. The second aerial was held in reserve. Signals were transmitted in a fairly narrow beam Additional ensuring a strong reception at the earth's surface. The satellite Information received telemetry at 1000 MHz. Television service was Launch/Orbital provided in a frequency range of 3.4 to 4.1 GHz at 40 w. information for Molniya 1- Molniya 1/84, whose cylindrical body was 3.4 m long and 1.6 m 84 in diameter, was much heavier than corresponding U.S. COMSATs, and it had about 10 times the power output of the Experiments on Molniya 1- Early Bird COMSAT. In addition, it did not employ a 84 geosynchronous equatorial orbit as have most U.S. COMSATs because such an orbit would not provide coverage for areas Data collections from north of 70 deg n latitude. Instead, the satellite was boosted Molniya 1-84 from a low-altitude parking orbit into a highly elliptical orbit with two high apogees daily over the northern hemisphere -- one over Russia and one over North America -- and relatively low perigees over the southern hemisphere. During its apogee, Questions or comments Molniya 1/84 remained relatively stationary with respect to the about this spacecraft can earth below for nearly 8 of every 12 hr. By placing three or be directed to: Coordinated more Molniya 1 satellites in this type of orbit, spacing them Request and User Support suitably, and shifting their orbital planes relative to each other Office. by 120 deg, a 24-hr/day communication system could be obtained.

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Personnel Molniya 3-42

Publications NSSDC ID: 1992-067A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The Molniya-3 Russian communications satellites were used to 22178 create the 'Orbita' communications system for northern regions, with groups of four satellites. The first Molniya 3 spacecraft appeared in 1974, primarily to support civil Facts in Brief communications (domestic and international), with a slightly Launch Date: 1992-10- enhanced electrical power system and a communications 14 payload of three 6/4 GHz transponders with power outputs of Launch 40 W or 80 W. The land segment used a 12 m diameter Vehicle: Molniya parabolic antenna, which was pointed automatically at the Launch Site: Plesetsk, satellite using autonomous electromechanical equipment. Later Russia versions were to be part of the YeSSS Unified Satellite Mass: 1600.0 kg Communications System. Trials of this version began in the 1980's, with the system being accepted by the Russian military in 1983-1985. Funding Agency

Unknown (U.S.S.R)

Discipline

Communications

Additional Information

Launch/Orbital information for Molniya 3- 42

Experiments on Molniya 3- 42

Data collections from Molniya 3-42

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Monday, 25 April 2011

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Personnel Molniya 3-43

Publications NSSDC ID: 1992-085A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events he Molniya-3 Russian communications satellites were used to 22255 create the 'Orbita' communications system for northern regions, with groups of four satellites. The first Molniya 3 spacecraft appeared in 1974, primarily to support civil Facts in Brief communications (domestic and international), with a slightly Launch Date: 1992-12- enhanced electrical power system and a communications 01 payload of three 6/4 GHz transponders with power outputs of Launch 40 W or 80 W. The land segment used a 12 m diameter Vehicle: Molniya parabolic antenna, which was pointed automatically at the Launch Site: Plesetsk, satellite using autonomous electromechanical equipment. Later Russia versions were to be part of the YeSSS Unified Satellite Mass: 1600.0 kg Communications System. Trials of this version began in the 1980's, with the system being accepted by the Russian military in 1983-1985. Funding Agency

Unknown (U.S.S.R)

Discipline

Communications

Additional Information

Launch/Orbital information for Molniya 3- 43

Experiments on Molniya 3- 43

Data collections from Molniya 3-43

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

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Personnel MSTI 1

Publications NSSDC ID: 1992-078A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The Miniature Sensor Technology Integration (MSTI) Miniature Sensor spacecraft had a four day mission to photograph infrared Technology Integration 1 images of islands in the eastern Pacific Ocean. It was the first 22229 of a series of low-cost satellites which were intended to assist the Air Force's Strategic Defense Initiative Organization in its missile sensor technology. It was stabilized by a sold-gas Facts in Brief reaction system. An FM transmitter relayed the infrared camera data to Air Force tracking stations. Launch Date: 1992-11- 21 Launch Vehicle: Scout Launch Site: Vandenberg AFB, United States Mass: 157.0 kg

Funding Agency

Department of Defense- Department of the Air Force (United States)

Discipline

Surveillance and Other Military

Additional Information

Launch/Orbital information for MSTI 1 PDMP information for MSTI 1

Experiments on MSTI 1

Data collections from MSTI 1

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

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Monday, 25 April 2011

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Personnel Navstar 2A-03

Publications NSSDC ID: 1992-009A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Global Positioning System (GPS) was developed by the US GPS 2A-2 Department of Defense to provide all-weather round-the-clock GPS 2-12 navigation capabilities for military ground, sea, and air forces. Since its implementation, GPS has also become an integral USA 79 asset in numerous civilian applications and industries around Navstar 25 the globe, including recreational used (e.g., boating, aircraft, 21890 hiking), corporate vehicle fleet tracking, and surveying. GPS employs 24 spacecraft in 20,200 km circular orbits inclined at 55 degrees. These vehicles are placed in 6 orbit planes with Facts in Brief four operational satellites in each plane. Launch Date: 1992-02- GPS Block 2 was the operational system, following the 23 demonstration system comprised of Block 1 (Navstar 1 - 11) Launch Vehicle: Delta spacecraft. These spacecraft were 3-axis stabilized, nadir II 7925 pointing using reaction wheels. Dual solar arrays supplied 710 Launch Site: Cape watts of power. They used S-band (SGLS) communications for Canaveral, United States control and telemetry and UHF cross-link between spacecraft. Mass: 840.0 kg The payload consisted of two L-band navigation signals at Nominal 1575.42 MHz (L1) and 1227.60 MHz (L2). Each spacecraft Power: 710.0 W carried 2 rubidium and 2 cesium clocks and nuclear detonation detection sensors. Built by Rockwell Space Systems for the Funding Agency US Air Force, the spacecraft measured 5.3 m across with solar panels deployed and had a design life of 7.5 years. Department of Defense- Department of the Air Force (United States)

Discipline

Navigation & Global Positioning

Additional Information

Launch/Orbital information for Navstar 2A-03

Experiments on Navstar 2A-03

Data collections from Navstar 2A-03

Questions or comments about this spacecraft can

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Personnel Navstar 2A-04

Publications NSSDC ID: 1992-019A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Global Positioning System (GPS) was developed by the US USA 80 Department of Defense to provide all-weather round-the-clock GPS 2-13 navigation capabilities for military ground, sea, and air forces. Since its implementation, GPS has also become an integral 21930 asset in numerous civilian applications and industries around the globe, including recreational used (e.g., boating, aircraft, Facts in Brief hiking), corporate vehicle fleet tracking, and surveying. GPS employs 24 spacecraft in 20,200 km circular orbits inclined at Launch Date: 1992-04- 55 degrees. These vehicles are placed in 6 orbit planes with 09 four operational satellites in each plane. Launch Vehicle: Delta II 7925 GPS Block 2 was the operational system, following the Launch Site: Cape demonstration system comprised of Block 1 (Navstar 1 - 11) Canaveral, United States spacecraft. These spacecraft were 3-axis stabilized, nadir Mass: 840.0 kg pointing using reaction wheels. Dual solar arrays supplied 710 Nominal watts of power. They used S-band (SGLS) communications for Power: 710.0 W control and telemetry and UHF cross-link between spacecraft. The payload consisted of two L-band navigation signals at 1575.42 MHz (L1) and 1227.60 MHz (L2). Each spacecraft Funding Agency carried 2 rubidium and 2 cesium clocks and nuclear detonation Department of Defense- detection sensors. Built by Rockwell Space Systems for the Department of the Air US Air Force, the spacecraft measured 5.3 m across with solar Force (United States) panels deployed and had a design life of 7.5 years.

Discipline

Navigation & Global Positioning

Additional Information

Launch/Orbital information for Navstar 2A-04

Experiments on Navstar 2A-04

Data collections from Navstar 2A-04

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

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Monday, 25 April 2011

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Personnel Navstar 2A-05

Publications NSSDC ID: 1992-039A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Global Positioning System (GPS) was developed by the US USA 83 Department of Defense to provide all-weather round-the-clock GPS 2-14 navigation capabilities for military ground, sea, and air forces. Since its implementation, GPS has also become an integral 22014 asset in numerous civilian applications and industries around the globe, including recreational used (e.g., boating, aircraft, Facts in Brief hiking), corporate vehicle fleet tracking, and surveying. GPS employs 24 spacecraft in 20,200 km circular orbits inclined at Launch Date: 1992-07- 55 degrees. These vehicles are placed in 6 orbit planes with 07 four operational satellites in each plane. Launch Vehicle: Delta II 7925 GPS Block 2 was the operational system, following the Launch Site: Cape demonstration system comprised of Block 1 (Navstar 1 - 11) Canaveral, United States spacecraft. These spacecraft were 3-axis stabilized, nadir Mass: 840.0 kg pointing using reaction wheels. Dual solar arrays supplied 710 Nominal watts of power. They used S-band (SGLS) communications for Power: 710.0 W control and telemetry and UHF cross-link between spacecraft. The payload consisted of two L-band navigation signals at 1575.42 MHz (L1) and 1227.60 MHz (L2). Each spacecraft Funding Agency carried 2 rubidium and 2 cesium clocks and nuclear detonation Department of Defense- detection sensors. Built by Rockwell Space Systems for the Department of the Air US Air Force, the spacecraft measured 5.3 m across with solar Force (United States) panels deployed and had a design life of 7.5 years.

Discipline

Navigation & Global Positioning

Additional Information

Launch/Orbital information for Navstar 2A-05

Experiments on Navstar 2A-05

Data collections from Navstar 2A-05

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

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Personnel Navstar 2A-06

Publications NSSDC ID: 1992-058A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Global Positioning System (GPS) was developed by the US GPS 2-15 Department of Defense to provide all-weather round-the-clock USA 84 navigation capabilities for military ground, sea, and air forces. Since its implementation, GPS has also become an integral 22108 asset in numerous civilian applications and industries around the globe, including recreational used (e.g., boating, aircraft, Facts in Brief hiking), corporate vehicle fleet tracking, and surveying. GPS employs 24 spacecraft in 20,200 km circular orbits inclined at Launch Date: 1992-09- 55 degrees. These vehicles are placed in 6 orbit planes with 09 four operational satellites in each plane. Launch Vehicle: Delta II 7925 GPS Block 2 was the operational system, following the Launch Site: Cape demonstration system comprised of Block 1 (Navstar 1 - 11) Canaveral, United States spacecraft. These spacecraft were 3-axis stabilized, nadir Mass: 840.0 kg pointing using reaction wheels. Dual solar arrays supplied 710 Nominal watts of power. They used S-band (SGLS) communications for Power: 710.0 W control and telemetry and UHF cross-link between spacecraft. The payload consisted of two L-band navigation signals at 1575.42 MHz (L1) and 1227.60 MHz (L2). Each spacecraft Funding Agency carried 2 rubidium and 2 cesium clocks and nuclear detonation Department of Defense- detection sensors. Built by Rockwell Space Systems for the Department of the Air US Air Force, the spacecraft measured 5.3 m across with solar Force (United States) panels deployed and had a design life of 7.5 years.

Discipline

Navigation & Global Positioning

Additional Information

Launch/Orbital information for Navstar 2A-06

Experiments on Navstar 2A-06

Data collections from Navstar 2A-06

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

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Personnel Navstar 2A-07

Publications NSSDC ID: 1992-079A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Global Positioning System (GPS) was developed by the US USA 85 Department of Defense to provide all-weather round-the-clock GPS 2-16 navigation capabilities for military ground, sea, and air forces. Since its implementation, GPS has also become an integral 22231 asset in numerous civilian applications and industries around the globe, including recreational used (e.g., boating, aircraft, Facts in Brief hiking), corporate vehicle fleet tracking, and surveying. GPS employs 24 spacecraft in 20,200 km circular orbits inclined at Launch Date: 1992-11- 55 degrees. These vehicles are placed in 6 orbit planes with 22 four operational satellites in each plane. Launch Vehicle: Delta II 7925 GPS Block 2 was the operational system, following the Launch Site: Cape demonstration system comprised of Block 1 (Navstar 1 - 11) Canaveral, United States spacecraft. These spacecraft were 3-axis stabilized, nadir Mass: 840.0 kg pointing using reaction wheels. Dual solar arrays supplied 710 Nominal watts of power. They used S-band (SGLS) communications for Power: 710.0 W control and telemetry and UHF cross-link between spacecraft. The payload consisted of two L-band navigation signals at 1575.42 MHz (L1) and 1227.60 MHz (L2). Each spacecraft Funding Agency carried 2 rubidium and 2 cesium clocks and nuclear detonation Department of Defense- detection sensors. Built by Rockwell Space Systems for the Department of the Air US Air Force, the spacecraft measured 5.3 m across with solar Force (United States) panels deployed and had a design life of 7.5 years.

Discipline

Navigation & Global Positioning

Additional Information

Launch/Orbital information for Navstar 2A-07

Experiments on Navstar 2A-07

Data collections from Navstar 2A-07

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

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Personnel Navstar 2A-08

Publications NSSDC ID: 1992-089A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Global Positioning System (GPS) was developed by the US USA 87 Department of Defense to provide all-weather round-the-clock GPS 2-17 navigation capabilities for military ground, sea, and air forces. Since its implementation, GPS has also become an integral 22275 asset in numerous civilian applications and industries around the globe, including recreational used (e.g., boating, aircraft, Facts in Brief hiking), corporate vehicle fleet tracking, and surveying. GPS employs 24 spacecraft in 20,200 km circular orbits inclined at Launch Date: 1992-12- 55 degrees. These vehicles are placed in 6 orbit planes with 18 four operational satellites in each plane. Launch Vehicle: Delta II 7925 GPS Block 2 was the operational system, following the Launch Site: Cape demonstration system comprised of Block 1 (Navstar 1 - 11) Canaveral, United States spacecraft. These spacecraft were 3-axis stabilized, nadir Mass: 840.0 kg pointing using reaction wheels. Dual solar arrays supplied 710 Nominal watts of power. They used S-band (SGLS) communications for Power: 710.0 W control and telemetry and UHF cross-link between spacecraft. The payload consisted of two L-band navigation signals at 1575.42 MHz (L1) and 1227.60 MHz (L2). Each spacecraft Funding Agency carried 2 rubidium and 2 cesium clocks and nuclear detonation Department of Defense- detection sensors. Built by Rockwell Space Systems for the Department of the Air US Air Force, the spacecraft measured 5.3 m across with solar Force (United States) panels deployed and had a design life of 7.5 years.

Discipline

Navigation & Global Positioning

Additional Information

Launch/Orbital information for Navstar 2A-08

Experiments on Navstar 2A-08

Data collections from Navstar 2A-08

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

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Tuesday, 26 April 2011

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Personnel Palapa B-4

Publications NSSDC ID: 1992-027A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Palapa B-4 was an Indonesian communications spacecraft 21964 launched by a Delta rocket.

Facts in Brief

Launch Date: 1992-05- 13 Launch Vehicle: Delta II 7925 Launch Site: Cape Canaveral, United States Mass: 1254.0 kg

Funding Agency

Unknown (Indonesia)

Discipline

Communications

Additional Information

Launch/Orbital information for Palapa B- 4

Experiments on Palapa B- 4

Data collections from Palapa B-4

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

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Personnel Pion 5

Publications NSSDC ID: 1992-056C Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Pion 1 was a passive atmospheric research spacecraft ejected 22099 from the Resurs F-16 spacecraft after its launch on August 19, 1992. It was launched along with Pion 2 to investigate the upper atmosphere density. Facts in Brief Launch Date: 1992-08- 19 Launch Vehicle: Soyuz Launch Site: Plesetsk, Russia Mass: 50.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline

Earth Science

Additional Information

Launch/Orbital information for Pion 5

Experiments on Pion 5

Data collections from Pion 5

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Personnel Pion 6

Publications NSSDC ID: 1992-056D Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Pion 2 was a passive atmospheric research spacecraft ejected 22100 from the Resurs F-16 spacecraft after its launch on August 19, 1992. It was launched along with Pion 1 to investigate upper atmospheric density. Facts in Brief Launch Date: 1992-08- 19 Launch Vehicle: Soyuz Launch Site: Plesetsk, Russia Mass: 50.0 kg

Funding Agency

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

Discipline

Earth Science

Additional Information

Launch/Orbital information for Pion 6

Experiments on Pion 6

Data collections from Pion 6

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Personnel PRC 35

Publications NSSDC ID: 1992-051A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events FSW-2 1 was a People's Republic of China Earth resources FSW-2 1 satellite launched from the Shuang Cheng Tzu site aboard a 22072 CZ-2D rocket. This Fanhui Shi Weixing (Recoverable Satellite) performed photo imaging and microgravity experiments. The film capsule was recovered on August 25, 1992. Facts in Brief

Launch Date: 1992-08- 09 Launch Vehicle: Long March 2D Launch Site: Jiuquan, Peoples Republic of China Mass: 2500.0 kg

Funding Agency

Unknown (Peoples Republic of China)

Disciplines

Earth Science Microgravity

Additional Information

Launch/Orbital information for PRC 35

Experiments on PRC 35

Data collections from PRC 35

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Tuesday, 26 April 2011

Progress M-11

NSSDC ID: 1992-004A Description

Automatic cargo ship Progress M-11 was launched from the Baikonur cosmodrome aboard a Soyuz rocket. An improved version of cargo freighters used to supply the Mir space station, the Progress M series had greater cargo capacity, a modernized approach/docking system and carried 2 solar panels to generate electrical power. Progress M can fly for 30 days independently and 108 days docked with Mir. Spare propellent in Progress M's tanks can be transferred to Mir before it is consigned to burn up in reentry. In the past, extra fuel was abandoned with the craft. Future Progress vehicles will carry a recoverable reentry capsule for the speedy return of up to 150 kg of material from Mir to earth. Alternate Names

21851

Facts in Brief

Launch Date: 1992-01-25 Launch Vehicle: Soyuz Launch Site: Tyuratam (Baikonur Cosmodrome), Kazakhstan Mass: 7250.0 kg Funding Agency

Unknown (U.S.S.R)

Discipline

Resupply/Refurbishment/Repair

Additional Information

Launch/Orbital information for Progress M-11

Experiments on Progress M-11

Data collections from Progress M-11

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

NSSDC Master Catalog Search

Spacecraft Experiments Data Collections Personnel Publications Maps New/Updated Data Lunar/Planetary Events

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Personnel Progress M-12

Publications NSSDC ID: 1992-022A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events An improved version of cargo freighters used to supply the Mir 21946 space station, the Progress M series had greater cargo capacity, a modernized approach/docking system and carried 2 solar panels to generate electrical power. Progress M can fly Facts in Brief for 30 days independently and 108 days docked with Mir. Launch Date: 1992-04- Spare propellent in Progress M's tanks can be transferred to 19 Mir before it is consigned to burn up in reentry. In the past, Launch Vehicle: Soyuz extra fuel was abandoned with the craft. Future Progress Launch Site: Tyuratam vehicles will carry a recoverable reentry capsule for the speedy (Baikonur Cosmodrome), return of up to 150 kg of material from Mir to earth. Kazakhstan Mass: 7250.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline

Resupply/Refurbishment/Repair

Additional Information

Launch/Orbital information for Progress M-12

Experiments on Progress M-12

Data collections from Progress M-12

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

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Personnel Progress M-13

Publications NSSDC ID: 1992-035A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events An improved version of cargo freighters used to supply the Mir 22004 space station, the Progress M series had greater cargo capacity, a modernized approach/docking system and carried 2 solar panels to generate electrical power. Progress M can fly Facts in Brief for 30 days independently and 108 days docked with Mir. Launch Date: 1992-06- Spare propellent in Progress M's tanks can be transferred to 30 Mir before it is consigned to burn up in reentry. In the past, Launch Vehicle: Soyuz extra fuel was abandoned with the craft. Future Progress Launch Site: Tyuratam vehicles will carry a recoverable reentry capsule for the speedy (Baikonur Cosmodrome), return of up to 150 kg of material from Mir to earth. Kazakhstan Mass: 7250.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline

Resupply/Refurbishment/Repair

Additional Information

Launch/Orbital information for Progress M-13

Experiments on Progress M-13

Data collections from Progress M-13

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

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Progress M-14

NSSDC ID: 1992-055A Description

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

Progress M-14 was launched from Baykonur launch site to deliver a capsule for returning research output materials from Mir. Alternate Names

22090

Facts in Brief

Launch Date: 1992-08-15 Launch Vehicle: Soyuz Launch Site: Tyuratam (Baikonur Cosmodrome), Kazakhstan Mass: 7250.0 kg Funding Agency

Unknown (U.S.S.R)

Discipline

Resupply/Refurbishment/Repair

Additional Information

Launch/Orbital information for Progress M-14

Experiments on Progress M-14

Data collections from Progress M-14

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

NSSDC Master Catalog Search

Spacecraft Experiments Data Collections Personnel Publications Maps New/Updated Data Lunar/Planetary Events http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1992-055A[26/04/2011 22:51:47] NASA - NSSDC - Spacecraft - Details

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Personnel Progress M-15

Publications NSSDC ID: 1992-071A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events An improved version of cargo freighters used to supply the Mir 22203 space station, the Progress M series had greater cargo capacity, a modernized approach/docking system and carried 2 solar panels to generate electrical power. Progress M can fly Facts in Brief for 30 days independently and 108 days docked with Mir. Launch Date: 1992-10- Spare propellent in Progress M's tanks can be transferred to 27 Mir before it is consigned to burn up in reentry. In the past, Launch Vehicle: Soyuz extra fuel was abandoned with the craft. Future Progress Launch Site: Tyuratam vehicles will carry a recoverable reentry capsule for the speedy (Baikonur Cosmodrome), return of up to 150 kg of material from Mir to earth. Kazakhstan Mass: 7250.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline

Resupply/Refurbishment/Repair

Additional Information

Launch/Orbital information for Progress M-15

Experiments on Progress M-15

Data collections from Progress M-15

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

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Personnel Resurs 500

Publications NSSDC ID: 1992-075A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Resurs 500 was a Russian spacecraft launched from the 22217 Plesetsk Cosmodrome. It carried a descent module containing greetings, etc., to the American people on the 500th anniversary of Columbus' landing, and was to soft-land west of Facts in Brief Seattle, WA and be retrieved. Launch Date: 1992-11- 15 Launch Vehicle: Soyuz Launch Site: Plesetsk, Russia Mass: 6300.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline

Earth Science

Additional Information

Launch/Orbital information for Resurs 500

Experiments on Resurs 500

Data collections from Resurs 500

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

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Personnel Resurs-F14

Publications NSSDC ID: 1992-024A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Resurs F-14 was a Russian remote sensing spacecraft 21951 launched by a Soyuz vehicle from the Plesetsk Cosmodrome. Upon completion of the mission, the exposed film was handed over to the Priroda center for processing and distribution to Facts in Brief customers. Launch Date: 1992-04- 29 Launch Vehicle: Soyuz Launch Site: Plesetsk, Russia Mass: 6300.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline

Earth Science

Additional Information

Launch/Orbital information for Resurs- F14

Experiments on Resurs- F14

Data collections from Resurs-F14

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

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Personnel Resurs-F15

Publications NSSDC ID: 1992-033A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Resurs F-15 was a Russian remote sensing spacecraft 21998 launched from the Plesetsk Cosmodrome.

Facts in Brief

Launch Date: 1992-06- 23 Launch Vehicle: Soyuz Launch Site: Plesetsk, Russia Mass: 6300.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline

Earth Science

Additional Information

Launch/Orbital information for Resurs- F15

Experiments on Resurs- F15

Data collections from Resurs-F15

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

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Personnel Resurs-F16

Publications NSSDC ID: 1992-056A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Resurs F-16 was a Russian remote sensing spacecraft 22093 launched from the Plesetsk Cosmodrome by a Soyuz rocket.

Facts in Brief

Launch Date: 1992-08- 19 Launch Vehicle: Soyuz Launch Site: Plesetsk, Russia Mass: 6300.0 kg

Funding Agency

Unknown (U.S.S.R)

Discipline

Earth Science

Additional Information

Launch/Orbital information for Resurs- F16

Experiments on Resurs- F16

Data collections from Resurs-F16

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

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Personnel S 80/T

Publications NSSDC ID: 1992-052C Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events S 80/T was a French experimental communications spacecraft 22078 launched from the Kourou Space Center in French Guiana by an Ariane rocket. Matra Marconi's S80/T microsatellite, based on the UK UoSat bus, was placed into a nearly circular orbit of Facts in Brief 1,315 km at an inclination of 66.1 degrees as a piggyback on Launch Date: 1992-08- the Topex/Poseidon mission. Sponsored by CNES, the 50 kg 10 satellite was gravity gradient stabilized with a 25 W power Launch Vehicle: Ariane supply. The primary objectives were analysis of the VHF Launch Site: Kourou, frequency band between 148 and 149.9 MHz and transmission French Guiana of data to prepare the future operational S80 system, a Mass: 50.0 kg constellation of small satellites in low, inclined orbits providing Nominal Power: 25.0 W positioning and short message service.

Funding Agency

Centre National d'Etudes Spatiales (France)

Discipline

Communications

Additional Information

Launch/Orbital information for S 80/T

Experiments on S 80/T

Data collections from S 80/T

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

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Personnel SAMPEX

Publications NSSDC ID: 1992-038A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The Solar Anomalous and Magnetospheric Particle Explorer Small Explorer/SAMPEX (SAMPEX) is the first of a series of spacecraft that was Explorer 68 launched under the Small Explorer (SMEX) mission of program for low cost spacecraft. The main objectives of SAMPEX SMEX/SAMPEX experiments was to obtained data for several continuous years Solar Anomalous and on the anomalous components of cosmic rays, on solar Magnetospheric Particle energetic particles emissions from the sun, and on the Explorer precipitating magnetospheric relativistic electrons. The orbit of 22012 SAMPEX has an altitude of 512 by 687 km and an 81.7 degree inclination. The spacecraft uses an on-board 3-axis stabilized solar pointed/momentum bias system with the pitch Facts in Brief axis pointed to towards the sun. Solar panels provide power Launch Date: 1992-07- SAMPEX for operations, including 16.7 W for science instruments. An on-board DPU preprocesses the science and other data and 03 stores them in a RPP unit of about 65 Mb, before transmitting Launch Vehicle: Scout in the S-band at a rate of 1.5 Mb/s over Wallops (or a back-up) Launch station. The command memory can store at least a thousand Site: Vandenberg AFB, commands. The science instruments generally point toward United States local zenith, especially over the terrestrial poles, for optimal Mass: 158.0 kg sampling of galactic and solar cosmic ray flux. Energetic magnetospheric particle precipitation is monitored at lower Funding Agency geomagnetic latitudes. It carries four science instruments: (1) low energy ion composition analyzer (LICA); (2) heavy ion NASA-Office of Space large telescope (HILT); (3) mass spectrometer telescope Science Applications (MAST); and (4) proton electron telescope (PET). Estimated (United States) useful lifetime of the spacecraft was about three years; however, the data stream continue to July, 2004. In 1997, NASA Goddard transferred operation of SAMPEX to the Flight Disciplines Dynamics and Control Laboratory (FDCL) housed within the Astronomy Aerospace Engineering Department of the University of Maryland. For more details, see IEEE Transactions on Solar Physics Geoscience and Remote Sensing (Vol 31, Issue 3, May 1993, Space Physics pp. 531-574).

Additional Information

Launch/Orbital information for SAMPEX PDMP information for SAMPEX Telecommunications information for SAMPEX

Experiments on SAMPEX

Data collections from SAMPEX

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Questions or comments about this spacecraft can be directed to: Dr. Timothy E. Eastman.

Personnel

Name Role Original Affiliation E-mail Dr. Charles Program NASA Headquarters [email protected] P. Holmes Scientist Mr. Maureen Project Manager NASA Goddard Space [email protected] P. Madden Flight Center Dr. Glenn M. Mission Principal University of Maryland [email protected] Mason Investigator

Selected References

Baker, D. N., et al., An overview of the Solar, Anomalous, and Magnetospheric Particle Explorer (SAMPEX) mission, IEEE Trans. Geosci. Rem. Sens., 31, No. 3, 531-541, May 1993.

Other Sources of SAMPEX Data/Information SAMPEX

Small Explorer program

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Personnel SATCOM C3

Publications NSSDC ID: 1992-060B Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events SATCOM C3 was a commercial communications satellite 22117 launched by an Ariane-4 rocket from the Kourou Space Center in French Guiana. Built and operated by GE Americom, it provided uplink, downlink, tape playback, terrestrial Facts in Brief interconnections, and end-to-end turnkey solutions to Launch Date: 1992-09- commercial and government users in the continental US, 10 Alaska and Hawaii. It was placed in a geosynchronous orbit at Launch Vehicle: Ariane 131 degrees W. 4 Launch Site: Kourou, French Guiana Mass: 1375.0 kg

Funding Agency

GE American Communications, Inc. (United States)

Discipline

Communications

Additional Information

Launch/Orbital information for SATCOM C3

Experiments on SATCOM C3

Data collections from SATCOM C3

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

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Personnel SATCOM C4

Publications NSSDC ID: 1992-057A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events SATCOM C4 was a GE Americom commercial 22096 communications satellite launched from Cape Canaveral aboard a Delta rocket. It provided uplink, downlink, tape playback, terrestrial interconnections, and end-to-end turnkey Facts in Brief solutions to commercial and government users in the Launch Date: 1992-08- continental US, Alaska, Hawaii and the Caribbean. It was 31 placed in a geosynchronous orbit at 135 degrees W. Launch Vehicle: Delta II 7925 Launch Site: Cape Canaveral, United States Mass: 2000.0 kg

Funding Agency

GE American Communications, Inc. (United States)

Discipline

Communications

Additional Information

Launch/Orbital information for SATCOM C4

Experiments on SATCOM C4

Data collections from SATCOM C4

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

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Personnel SHEAL-A

Publications NSSDC ID: OSS-2 Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The Shuttle High Energy Astrophysics Laboratory-A (SHEAL- OSS-2 A) system consists of the space segment and the ground segment. The space segment includes the Shuttle, Shuttle Payload of Opportunity Carrier (SPOC) avionics, and individual Facts in Brief corners for the instruments. The ground segment consists of Launch Date: 1992-09- the Tracking and Data Relay Satellite System (TDRSS) for 02 data acquisition, the Payload Operations Control Center Launch (POCC) for payload control, the Spacelab Data Processing Vehicle: Shuttle Facility (SLDPF) for data capture and processing, and the data Launch Site: Cape analysis facilities at various principal investigators' institutions. Canaveral, United States The investigations study the temperature and composition of Mass: 3700.0 kg high-temperature astrophysical plasmas on a scale of sizes and distances ranging from our own galaxy to clusters of galaxies. These investigations are part of the high-energy Funding Agency astrophysics program of multiple spacelab flights and extended space platform observations. The first flight in this series will NASA-Office of Space contain only the Diffuse X-Ray Spectrometer (DXS) Science Applications investigation and will be launched earlier. The other (United States) investigations described below will fly on subsequent flights. The SHEAL-A was destroyed in the Challenger disaster. Discipline

Astronomy

Additional Information

Launch/Orbital information for SHEAL-A

Experiments on SHEAL-A

Data collections from SHEAL-A

Questions or comments about this spacecraft can be directed to: Dr. H. Kent Hills.

Personnel

Name Role Original Affiliation E-mail Mr. Frank G. Mission NASA Goddard Space [email protected] Volpe Manager Flight Center

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Dr. Francis E. Mission NASA Goddard Space [email protected] Marshall Scientist Flight Center

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Personnel Soyuz TM-14

Publications NSSDC ID: 1992-014A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Soyuz TM-14 was a Russian spacecraft launched from the 21908 Baykonur Cosmodrome with 3 cosmonauts on board, and docked with the Mir space station on March 19, 1992. They conducted zero-gravity biological experiments. Designed and Facts in Brief manufactured by RKK Energiya, the Soyuz TM was capable of Launch Date: 1992-03- carrying three cosmonauts and has a gross weight of just over 17 seven metric tons, a length of seven meters, and a maximum Launch Vehicle: Soyuz diameter of 2.7 m. The spacecraft consisted of three main Launch Site: Tyuratam sections: the orbital module, the command and reentry module, (Baikonur Cosmodrome), and the service module. Two solar arrays (10.6 m span) Kazakhstan provided electrical power for the typical 50-hour journey to Mir Mass: 7150.0 kg and could be interconnected with the space station's electrical system to furnish additional 1.3 kW. The nominal flight time for Soyuz TM spaceship was 5-6 months. Funding Agency

Unknown (U.S.S.R)

Disciplines

Human Crew Life Science

Additional Information

Launch/Orbital information for Soyuz TM- 14

Experiments on Soyuz TM- 14

Data collections from Soyuz TM-14

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

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Launch, orbit and landing data Launch date: 17.03.1992 Launch time: 10:54 UT Launch site: Baikonur Launch pad: 1 Altitude: 350 km Inclination: 51,6° Landing date: 10.08.1992 Landing time: 01:05 UT Landing site: 47° 25' N, 69° 21' E

alternate crew photo

Crew

No. Surname Given name Job

1 Viktorenko Aleksandr Stepanovich Commander

2 Kaleri Aleksandr Yuriyevich Flight Engineer

3 Flade Klaus-Dietrich Research Cosmonaut

Flight Launch from Baikonur; landing 136 km east of Dzheskasgan; Mission MIR`92.

Docking on Soyuz TM-13-Quant1-MIR-Kristall-Quant2 complex; scientific experiments with the tenth MIR resident crew; Viktorenko and Kaleri became the eleventh resident crew; first mission after disolution of the USSR; first Russian spaceflight; first joined spaceflight Russia-Germany; Viktorenko and Kaleri performed an EVA on 08.07.1992 (2h 03m), inspecting gyrodyne orientation flywheels.

Photos / Drawings

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Personnel Soyuz TM-15

Publications NSSDC ID: 1992-046A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Soyuz TM-15 was launched from Baykonur cosmodrome on its 22054 way to dock with the Mir station. It carried on French and two Russian cosmonauts. Designed and manufactured by RKK Energiya, the Soyuz TM was capable of carrying three Facts in Brief cosmonauts and has a gross weight of just over seven metric Launch Date: 1992-07- tons, a length of seven meters, and a maximum diameter of 27 2.7 m. The spacecraft consisted of three main sections: the Launch Vehicle: Soyuz orbital module, the command and reentry module, and the Launch Site: Tyuratam service module. Two solar arrays (10.6 m span) provided (Baikonur Cosmodrome), electrical power for the typical 50-hour journey to Mir and Kazakhstan could be interconnected with the space station's electrical Mass: 7150.0 kg system to furnish additional 1.3 kW. The nominal flight time for Soyuz TM spaceship was 5-6 months. Funding Agency

Unknown (U.S.S.R)

Discipline

Human Crew

Additional Information

Launch/Orbital information for Soyuz TM- 15

Experiments on Soyuz TM- 15

Data collections from Soyuz TM-15

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

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Launch, orbit and landing data Launch date: 27.07.1992 Launch time: 06:08 UT Launch site: Baikonur Launch pad: 1 Altitude: 350 km Inclination: 51,6° Landing date: 01.02.1993 Landing time: 03:49 UT Landing site: 100 km NW of Arkalyk

Crew

No. Surname Given name Job

1 Soloviyov Anatoli Yakovlevich Commander

2 Avdeyev Sergei Vasiliyevich Flight Engineer

3 Tognini Michel Ange-Charles Research Cosmonaut

Flight Launch from Baikonur; landing 100 km northwest of Arkalyk.

Docking on MIR space station; joint work with eleventh resident crew; Soloviyov and Avdeyev became then twelfth MIR-resident crew; both cosmonauts performed four EVA's on 03.09.1992 (3h 56m), 07.09.1992 (5h 08m), 11.09.1992 (5h 44m) and 15.09.1992 (3h 33m), to install the VDU thruster pod on the Sofora girder and to install the Kurs docking system antenna on the Kristall module.

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Personnel Spacelab-J

Publications NSSDC ID: SPLABJ Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The Spacelab-J mission was a joint project for life science and SL-J microgravity research between Japan and the United States. STS 47/Spacelab-J Within the spacelab was Japan's ``First Materials Processing Test'', a collection of 34 material and life science investigations, seven U.S. experiments, and two collaborative Facts in Brief experiments. The long spacelab module was used for the mission. The materials science experiments examined Launch Date: 1992-09- phenomena in biotechnology, electronic materials, fluid 11 dynamics and transport, glasses and ceramics, and metals Launch and alloys. The life science experiments included Vehicle: Shuttle investigations in cell separation, cell biology, developmental Launch Site: Cape biology, animal and human physiology and behavior, space Canaveral, United States radiation, biological rhythms, and medical technology. Funding Agencies

National Space Development Agency (NASDA) (Japan) NASA-Office of Space Science Applications (United States)

Disciplines

Life Science Microgravity

Additional Information

Launch/Orbital information for Spacelab- J PDMP information for Spacelab-J Telecommunications information for Spacelab- J

Experiments on Spacelab- J

Data collections from Spacelab-J

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Personnel

Name Role Original Affiliation E-mail Mr. Norio Project National Space Development Soichi Manager Agency of Japan Mr. J. Aubray Mission NASA Marshall Space Flight King Manager Center Dr. Yoshinori Project National Space Development [email protected] Fujimori Scientist Agency of Japan Mr. Fred W. Mission NASA Marshall Space Flight Leslie Scientist Center Dr. Robert S. Program NASA Headquarters Sokolowski Scientist Mr. Gary W. Program NASA Headquarters [email protected] McCollum Manager Dr. Thora Program NASA Headquarters Halstead Scientist

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Personnel Spartan-B

Publications NSSDC ID: SPATN-B Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Spartan consists of low-cost, Shuttle-launched, short-duration, Spartan 2 sounding-rocket-type payloads. The payloads are retrievable and reusable with a turnaround time of approximately 6 to 9 months. Spartan has relatively few operational interfaces with Facts in Brief STS. It operates as an autonomous sub-satellite, and the data Launch Date: 1992-07- are stored on an internal tape recorder. Pointing and 08 stabilization are achieved by an Attitude Control System (ACS) Launch capable of plus or minus 30 arcsec accuracy. Spartan-B Vehicle: Shuttle carries instruments that are used (1) to probe the physics of Launch Site: Cape the acceleration of the solar wind by measuring temperatures, Canaveral, United States particle densities, and velocities between 1.5 and 6 solar radii; Mass: 1100.0 kg (2) to map X-rays emanating from clusters of galaxies and explore the center of our galaxy; and (3) conduct a far ultraviolet survey of selected star fields such as the Magellanic Funding Agency Clouds and the Andromeda Galaxy. Network support of Spartan-B will consist of C-band radar tracking from various NASA-Office of Space ground stations. For detailed information, see Mission Science Applications Requirements and Data Systems Support Forecast, STDN No. (United States) 803, Dec/Jan 1989-1990, GSFC, NASA. Discipline

Solar Physics

Additional Information

Launch/Orbital information for Spartan-B

Experiments on Spartan-B

Data collections from Spartan-B

Questions or comments about this spacecraft can be directed to: Dr. H. Kent Hills.

Personnel

Name Role Original Affiliation E-mail Mr. John H. Mission NASA Goddard Space Flight Lane Manager Center

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Dr. J. David Program NASA Headquarters Bohlin Scientist Dr. Werner M. Project NASA Goddard Space Flight [email protected] Neupert Scientist Center Mr. John L. Mission Harvard College [email protected] Kohl Scientist Observatory Dr. Richard H. Mission High Altitude Observatory [email protected] Munro Scientist Mr. John A. Program NASA Headquarters Glaab Manager

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Personnel SROSS 3

Publications NSSDC ID: 1992-028A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events SROSS 3 was an Indian remote sensing spacecraft launched 21968 by an ASLV booster from the Sriharikota Center in India. This Stretche Rohini Satellite Series spacecraft provided India with its first astrophysics observatory, albeit temporarily. The Facts in Brief primary purpose of the flight was to test the ASLV launch Launch Date: 1992-05- vehicle which had failed on the two previous attempts. The 19 SROSS 3 was a payload of opportunity which carried a Launch Vehicle: ASLV geophysics package and a gamma ray burst detector. The (Indian) latter was tuned to the energy range of 20 keV-3 MeV and Launch Site: Sriharikota, consisted of high voltage scintillation detectors. The India observational program was concentrated on the southern Mass: 106.0 kg celestial sky. Unfortunately, the 106-kg spacecraft decayed after only 55 days instead of an anticipated one year due to the less-than-nominal performance of the launch vehicle. Funding Agency

Indian Space Research Organization (India)

Disciplines

Astronomy Earth Science Space Physics

Additional Information

Launch/Orbital information for SROSS 3

Experiments on SROSS 3

Data collections from SROSS 3

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

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Personnel SSBUV04

Publications NSSDC ID: SSBUV04 Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The fourth Shuttle Solar Backscatter Ultraviolet (SSBUV04) STS/SSBUV04 payload was co-manifested with the ATLAS 1 payload. The SSBUV was physically separated from the ATLAS 1 payload and consisted of two Get Away Special (GAS) canisters Facts in Brief mounted on one standard GAS adapter beam assembly with Launch Date: 1992-03- an interconnecting cable to provide communication and power 24 between the two canisters. The canister containing the SSBUV Launch instrument was equipped with a motorized door assembly. The Vehicle: Shuttle adjacent support canister contained data, command and Launch Site: Cape avionics systems. The light sources, quartz-halogen, Canaveral, United States deuterium, and mercury lamps, and a diffuser plate assembly were all contained in the instrument canister. SSBUV commands were sent directly from the Johnson Payload Funding Agency Operations Control Center (POCC) in Houston, TX. The payload was managed by Goddard Space Flight Center. The NASA-Office of Space SSBUV was flown on three previous shuttle flights and is Science Applications expected to be co-manifested with subsequent ATLAS Shuttle (United States) flights. Disciplines

Earth Science Solar Physics

Additional Information

Launch/Orbital information for SSBUV04 PDMP information for SSBUV04 Telecommunications information for SSBUV04

Experiments on SSBUV04

Data collections from SSBUV04

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

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Personnel

Name Role Original Affiliation E-mail Mr. Ernest Mission Principal NASA Goddard Space [email protected] Hilsenrath Investigator Flight Center

Selected References

Torr, M. R., and K. D. Sullivan, Atlas-1 Shuttle mission, EOS, 73, No. 10, Mar. 1992.

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Personnel STS 42/IML 1

Publications NSSDC ID: 1992-002A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Space Shuttle Mission STS-42 was the 45th Shuttle flight and 21846 the 15th flight of Discovery. Commanding the mission was Ronald J. Grabe, Col., USAF. Stephen S. Oswald served as his pilot. Mission Specialists included Dr. Norman E. Thagard, Facts in Brief M.D.; David C. Hilmers, Lt. Col., USMC; and William F. Launch Date: 1992-01- Readdy. Dr. Roberta L. Bondar, M.D. and Ph.D., of the 22 Canadian Space Agency and Ulf D. Merbold, Ph.D., of the Launch European Space Agency, served as Payload Specialists. The Vehicle: Shuttle main objective of STS-42 was to carry out the International Launch Site: Cape Microgravity Laboratory-1 (IML-1) mission, a collection of life Canaveral, United States science and microgravity experiments developed by more than Mass: 13001.0 kg 200 scientists from 16 countries. The IML-1 was the first in a series of IML missions planned to fly aboard the Space Shuttle this decade. In addition the the IML-1 module, STS-42 also Funding Agency carried 12 Get Away Special containers containing experiments ranging from materials processing work to NASA-Office of Space investigations into the development of animal life in Flight (United States) weightlessness. Two experiments from the Space Shuttle Student Involvement Program, Convection in Zero Gravity and Disciplines Zero-G Capillary Rise of Liquid Through Granular Porous Media, were also flown. On Discovery's lower deck, the Human Crew Investigation into Polymer Membrane Processing investigated Life Science advances in filtering technologies in microgravity, and the Radiation Monitoring Equipment-III recorded radiation levels in Microgravity the crew cabin. The spacecraft maintained a gravity gradient orientation with its nose pointed to space and its tail to Earth in Additional order to minimize firings of the Shuttle's small steering Information thrusters, thus avoiding disturbances to onboard experiments. Launch/Orbital information for STS 42/IML 1

Experiments on STS 42/IML 1

Data collections from STS 42/IML 1

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Discovery (14)

Launch, orbit and landing data Launch date: 22.01.1992 Launch time: 14:52 UT Launch site: Cape Canaveral (KSC) Launch pad: 39-A Altitude: 302 km Inclination: 57,0° Landing date: 30.01.1992 Landing time: 16:07 UT Landing site: Edwards AFB

Crew

No. Surname Given name Job

1 Grabe Ronald John CDR

2 Oswald Stephen Scot PLT

3 Thagard Norman Earl MSP

4 Readdy William Francis "Bill" MSP

5 Hilmers David Carl MSP

6 Bondar Roberta Lynn PSP

7 Merbold Ulf Dietrich PSP

hi res version (755 KB) Flight Launch from Cape Canaveral (KSC); landing on Edwards AFB.

First fl ight o f I nternational M icrogravity Laboratory IML-1, t o ex plore t he co mplex e ffects of weightlessness on living organism and materials processing; the crew performed 55 experiments on t he ar eas of lif e sciences, l ow gravity m aterials pr ocessing and f luid-physics; Oswald made a f ilm from the s urface o f Africa and E urope; this f ilm s hould be u sed f or the movie "Destiny in Space".

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Personnel STS 45

Publications NSSDC ID: 1992-015A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The Space Shuttle ``Atlantis'' was a ten day mission primarily 21915 to operate the Atmospheric Laboratory for Applications and Science 1 (ATLAS 1) payload. ATLAS 1 (see entry) consisted of twelve instruments and thirteen experiments to study the Facts in Brief Sun and Earth's atmosphere. Several more ATLAS flights are Launch Date: 1992-03- planned for studying solar inputs and atmospheric responses 24 over an eleven year solar cycle. Additional payloads on the Launch shuttle included the Shuttle Solar Backscatter Ultraviolet Vehicle: Shuttle (SSBUV) (its fourth shuttle flight), and several Get Away Launch Site: Cape Specials (GAS). Science experiment payloads included Space Canaveral, United States Tissue Loss (STL 1), an Investigations into Polymer Mass: 8020.0 kg Membrane Processing (IPMP) Experiment, the Shuttle Amateur Radio Experiment II (SAREX II), Visual Function Tester (VFT 2), Radiation Monitoring Equipment III (RME III), Funding Agency and the Cloud Logic to Optimize Use of Defense Systems (CLOUDS-1A) Experiment. The Shuttle flight carried a crew of NASA-Office of Space seven, including three mission specialists and two payload Flight (United States) specialists. Disciplines

Astronomy Human Crew Solar Physics Space Physics

Additional Information

Launch/Orbital information for STS 45

Experiments on STS 45

Data collections from STS 45

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

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Atlantis (11)

Launch, orbit and landing data Launch date: 24.03.1992 Launch time: 13:13 UT Launch site: Cape Canaveral (KSC) Launch pad: 39-A Altitude: 296 km Inclination: 57,0° Landing date: 02.04.1992 Landing time: 11:23 UT Landing site: Cape Canaveral (KSC)

Crew

No. Surname Given name Job Charles Frank, Jr. 1 Bolden CDR "Charlie" 2 Duffy Brian PLT

3 Sullivan Kathryn Dwyer MSP

4 Leestma David Cornell MSP

5 Foale Colin Michael MSP Dirk Dries David 6 Frimout PSP Damiaan 7 Lichtenberg Byron Kurt PSP

Flight Launch from Cape Canaveral (KSC); landing on Cape Canaveral (KSC).

First mission of Atmospheric Laboratory for Applications and Science (ATLAS-01) on Spacelab- pallets; photographic work; the pilots had to fly more than 250 manoeuvres to bring Atlantis in the right position for the different experiments.

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Personnel STS 46

Publications NSSDC ID: 1992-049A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events STS 46 was the 49th shuttle mission and the 12th flight of the 22064 Atlantis orbiter. It carried a crew of seven.

The Shuttle was to deploy the Tethered Satellite System-1 Facts in Brief (TSS-1), an Italian Space Agency-developed satellite. The Launch Date: 1992-07- satellite was to have been attached by a 12.5 mile cable to the 31 Shuttle cargo bay to explore the dynamics of electricity- Launch generating systems. However, attempts by the crew to release Vehicle: Shuttle the cable failed and the experiment was unsuccessful. Launch Site: Cape Canaveral, United States The European Retrievable Carrier (EURECA), developed by Mass: 12965.0 kg the European Space Agency (ESA), was deployed. The satellite, carrying 15 experiments in material science, life science and space physics and upper atmosphere research, Funding Agency was retrieved by STS 57 a year later. NASA-Office of Space The following experiments were also carried by STS-46: (1) Flight (United States) Evaluation of Oxygen Interaction with Materials III (EOIM); (2) Thermal Energy Management (TEMP 2A); (3) IMAX camera Discipline production; (4) materials processing experiments; (5) Limited Duration Space Environment Candidate Materials Exposure Human Crew (LDCE); (6) Pituitary Growth Hormone Cell Function (PHCF); (7) Air Force Maui Optical System (AMOS); and, (8) Ultraviolet Plume Experiment (UVPI). Additional STS 46 Information The orbiter landed at Kennedy Space Center after completing Launch/Orbital 127 orbits. The mission duration was 7 days, 23 hours, 15 information for STS 46 minutes, and 3 seconds. Experiments on STS 46

Data collections from STS 46

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

Related Information/Data at NSSDC

TSS-1 Eureca 1

Other Sources of STS 46 Information/Data

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STS 46 information (NASA KSC) STS 46 Press Release images (NASA JSC)

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Atlantis (12)

Launch, orbit and landing data

Launch date: 31.07.1992 Launch time: 13:56 UT Launch site: Cape Canaveral (KSC) Launch pad: 39-B Altitude: 426 km Inclination: 28,45° Landing date: 08.08.1992 Landing time: 13:11 UT Landing site: Cape Canaveral (KSC)

Crew

No. Surname Given name Job Flight No. Duration Orbits

1 Shriver Loren James CDR 3 7d 23h 15m 127

2 Allen Andrew Michael "Andy" PLT 1 7d 23h 15m 127

3 Nicollier Claude MSP 1 7d 23h 15m 127

4 Ivins Marsha Sue MSP 2 7d 23h 15m 127

5 Hoffman Jeffrey Alan MSP 3 7d 23h 15m 127

6 Chang-Diaz Franklin Ramon MSP 3 7d 23h 15m 127

7 Malerba Franco Egidio PSP 1 7d 23h 15m 127

Crew seating arrangement Landing 1 Shriver 2 Allen 3 Hoffman 4 Ivins 5 Nicollier 6 Chang-Diaz 7 Malerba

Launch 1 Shriver 2 Allen 3 Nicollier 4 Ivins 5 Hoffman 6 Chang-Diaz 7 Malerba

Backup Crew

No. Surname Given name Job

7 Guidoni Umberto PSP

Flight Launch from Cape Canaveral (KSC); landing on Cape Canaveral (KSC).

Deployment of ESA's European Retrievable Carrier (EURECA) was successfull after a few problems; deployment of joint NASA-Italian Space Agency Tethered Satellite System (TSS- 1); maximum distance only 860 feet because of jammed tether line; TSS-operations were then stopped and the satellite was succesful stowed for return to Earth; several secondary payloads.

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Personnel STS 47

Publications NSSDC ID: 1992-061A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events STS 47 was the 50th Shuttle mission and flew as its primary Spacelab-J/STS 47 payload Spacelab-J (SL-J), utilized pressurized Spacelab 22120 module. Jointly sponsored by NASA and the National Space Development Agency (NASDA) of Japan, SL-J included 24 material science and 19 life sciences experiments, of which 34 Facts in Brief were sponsored by NASDA, seven by NASA, and two collaborative efforts. The mission was extended one day to Launch Date: 1992-09- further science objectives. The materials science investigations 12 covered such fields as biotechnology, electronic materials, fluid Launch dynamics and transport phenomena, glasses and ceramics, Vehicle: Shuttle metals and alloys, and acceleration measurements. The life Launch Site: Cape sciences investigations covered human health, cell separation Canaveral, United States and biology, development biology, animal and human Mass: 12772.0 kg physiology and behavior, space radiation, and biological rhythms. Test subjects included the crew, Japanese koi fish, Funding Agencies cultured animal and plant cells, chicken embryos, fruit flies, fungi and plant seeds, and frogs and frog eggs. NASA-Office of Space Flight (United States) Also flown in the payload bay were 12 Get Away Special National Space (GAS) canisters (10 holding experiments, two for ballast) Development Agency attached to a GAS Bridge Assembly. Middeck experiments (NASDA) (Japan) included Israeli Space Agency Investigation about Hornets (USAIAH); Solid Surface Combustion Experiment (SSCE); Shuttle Amateur Radio Experiment (SAREX II); Air Force Maui Disciplines Optical Site (AMOS); and Ultraviolet Plume Instrument (UVPI). Human Crew The crew consisted of mission commander Robert L Gibson, Life Science pilot Curtis L. Brown Jr., payload commander Mark C. Lee, Microgravity mission specialist N. Jan Davis, science mission specialist Mae C. Jemison, and payload specialist Mamoru C. Mohri. Jemison became the first African-American woman to fly in space, Lee Additional and Davis were the first married couple, and Mohri the first Information Japanese to fly on the Shuttle. Launch/Orbital The mission duration was 7 days, 22 hours, 30 minutes, and information for STS 47 23 seconds. Telecommunications information for STS 47

Experiments on STS 47

Data collections from STS 47

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Endeavour (2)

USA

Launch, orbit and landing data

Launch date: 12.09.1992 Launch time: 14:23 UT Launch site: Cape Canaveral (KSC) Launch pad: 39-B Altitude: 307 km

Inclination: 57,0° Landing date: 20.09.1992 Landing time: 12:53 UT Landing site: Cape Canaveral (KSC)

Crew

No. Surname Given name Job Flight No. Duration Orbits

1 Gibson Robert Lee "Hoot" CDR 4 7d 22h 30m 126

2 Brown Curtis Lee, Jr. "Curt" PLT 1 7d 22h 30m 126

3 Lee Mark Charles MSP 2 7d 22h 30m 126

4 Apt Jerome "Jay" MSP 2 7d 22h 30m 126

5 Davis Nancy Jan MSP 1 7d 22h 30m 126

6 Jemison Mae Carol MSP 1 7d 22h 30m 126

7 Mohri Mamoru PSP 1 7d 22h 30m 126

Crew seating arrangement

Launch 1 Gibson 2 Brown 3 Lee 4 Apt 5 Davis Jemiso 6 n 7 Mohri

Landing 1 Gibson 2 Brown

3 Davis 4 Apt

5 Lee 6 Jemison 7 Mohri Backup Crew

No. Surname Given name Job

7 Mukai Chiaki PSP

7 Doi Takao PSP

7 Koszelak Stanley Norbert, Jr. PSP

Flight Launch from Cape Canaveral (KSC); landing on Cape Canaveral (KSC).

Mission Spacelab J with 43 experiments; first mission of Japanese Space Agency NASDA; Davis and Lee became first married couple at the same time in space; experiments with frogs; life science experiments conducted by Mohri; hornets were unable to built honeycombs in weightlessness; experiments in materials science. Photos / Drawings

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Personnel STS 49

Publications NSSDC ID: 1992-026A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events STS 49 was the first flight of the space shuttle Endeavour. On 21963 board were Astronauts Daniel Brandenstein, Kevin Chilton, Richard Hieb, Bruce Melnick, Pierre Thout, Kathryn Thornton, and Thomas Akers. Facts in Brief Launch Date: 1992-05- INTELSAT VI (F-3) satellite, stranded in an unusable orbit 07 since launch aboard a Titan vehicle in March 1990, was Launch captured by crew members during an EVA (extravehicular Vehicle: Shuttle activity) and equipped with a new perigee kick motor. The Launch Site: Cape Satellite was subsequently released into orbit and the new Canaveral, United States motor fired to put the spacecraft into a geosynchronous orbit Mass: 14786.0 kg for operational use.

The capture required three EVAs: a planned one by astronaut Funding Agency Pierre J. Thuot and Richard J. Hieb who were unable to attach a capture bar to the satellite from a position on the RMS; a NASA-Office of Space second unscheduled but identical attempt the following day; Flight (United States) and finally an unscheduled but successful hand capture by Pierre J. Thuot and fellow crewmen Richard J. Hieb and Discipline Thomas D. Akers as commander Daniel C. Brandenstein delicately maneuvered the orbiter to within a few feet of the Human Crew 4.5-ton communications satellite. An ASEM structure was erected in the cargo bay by the crew to serve as a platform to aid in the hand capture and subsequent attachment of the Additional capture bar. Information Launch/Orbital A planned EVA also was performed by astronauts Kathryn C. information for STS 49 Thornton and Thomas D. Akers as part of the Assembly of Station by EVA Methods (ASEM) experiment to demonstrate Experiments on STS 49 and verify maintenance and assembly capabilities for Space Station Freedom. The ASEM space walk, originally scheduled Data collections from STS for two successive days, was cut to one day because of the 49 lengthy INTELSAT retrieval operation.

Other "payloads of opportunity" experiments conducted included: Commercial Protein Crystal Growth (CPCG), Questions or comments Ultraviolet Plume Imager (UVPI) and the Air Force Maui about this spacecraft can Optical Station (AMOS) investigation. Mission was extended be directed to: Coordinated two days to complete objectives. Request and User Support Office. The following records were set during the STS-49 mission:

* First EVA involving three astronauts. * First and second longest EVA to date: 8 hours and 29 minutes and 7 hours and 45 minutes. * First Shuttle mission to feature four EVAs. * EVA time for a single Shuttle mission: 25 hours and 27 minutes, or 59:23 person hours. * First Shuttle mission requiring three rendezvous with an orbiting spacecraft. attached a live rocket motor to an orbiting satellite. * First use of a-drag chute during http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1992-026A[26/04/2011 23:03:34] NASA - NSSDC - Spacecraft - Details

a Shuttle landing.

The mission duration was 213 hours 17 minutes 38 seconds.

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Endeavour (1)

Launch, orbit and landing data Launch date: 07.05.1992 Launch time: 23:40 UT Launch site: Cape Canaveral (KSC) Launch pad: 39-B Altitude: 361 km Inclination: 28,35° Landing date: 16.05.1992 Landing time: 20:57 UT Landing site: Edwards AFB

Crew

No. Surname Given name Job

1 Brandenstein Daniel Charles CDR

2 Chilton Kevin Patrick "Chily" PLT

3 Hieb Richard James MSP

4 Melnick Bruce Edward "Mel" MSP

5 Thuot Pierre Joseph MSP

6 Thornton Kathryn Cordell Ryan MSP

7 Akers Thomas Dale MSP

Flight Launch from Cape Canaveral (KSC); landing on Edwards AFB.

First mission with orbiter Endeavour; first EVA by Thuot and Hieb on 10.05.1992 (3h 43m) to capture the stranded Intelsat VI-F3-satellite (failed); second EVA again by Thuot and Hieb on 11.05.1992 (5h 26m) for the same work, but again failed; third EVA by Akers, Thuot and Hieb on 13.05.1992 (8h 29m) and this time the astronauts were succesful, when they captured Intelsat with their hands and not with the capture bar; it was the first time, that three astronauts performed an EVA at the same time; the satellite was repaired (new perigee kick motor) and then again released into orbit; fourth EVA by Akers and Thornton on 14.05.1992 (7h 45m) to test EVA-tools and structures.

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Personnel STS 50/USML 1

Publications NSSDC ID: 1992-034A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Space Shuttle Mission STS 50 was the 48th Shuttle flight and 22000 the 12th flight of Columbia. Commanding the mission was Richard N. Richards, Capt. USN. Kenneth D. Bowersox served as his pilot. Mission specialists included Bonnie Dunbar, who Facts in Brief also served as Payload Commander, Ellen Baker, and Carl Launch Date: 1992-06- Meade, col. USAF. Payload specialists included Lawrence J. 25 DeLucas and Eugene H. Trinh. STS 50 carried the United Launch States Microgravity Laboratory (USML 1), a Spacelab long Vehicle: Shuttle module with an Extended Duration Orbiter (EDO) pallet in the Launch Site: Cape aft cargo bay. The USML 1 consisted of 31 experiments Canaveral, United States ranging from the manufacture of crystals for possible Mass: 11153.0 kg semiconductor use to the study of the behavior of weightless fluids. STS 50 also carried the Investigations into Polymer Membrane Processing experiment and the Space Shuttle Funding Agencies Amature Radio Experiment-II. Columbia landed July 9, 1992, at 11:43 a.m. UT on KSC's Shuttle Landing Facility Runway NASA-Office of Space 33. It completed 221 revolutions around the Earth and logged Science Applications 5,758,000 miles during the flight. (United States) NASA-Office of Space Flight (United States)

Disciplines

Human Crew Life Science Microgravity

Additional Information

Launch/Orbital information for STS 50/USML 1 PDMP information for STS 50/USML 1 Telecommunications information for STS 50/USML 1

Experiments on STS 50/USML 1

Data collections from STS 50/USML 1

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Columbia (12)

Launch, orbit and landing data Launch date: 25.06.1992 Launch time: 16:12 UT Launch site: Cape Canaveral (KSC) Launch pad: 39-A Altitude: 296 km Inclination: 28,45° Landing date: 09.07.1992 Landing time: 11:43 UT Landing site: Cape Canaveral (KSC)

Crew

No. Surname Given name Job

1 Richards Richard Noel "Dick" CDR

2 Bowersox Kenneth Dwane "Sox" PLT

3 Dunbar Bonnie Jeanne MSP

4 Baker Ellen Louise Shulman MSP

5 Meade Carl Joseph MSP

6 DeLucas Lawrence James PSP

7 Trinh Eugene Huu-Chau PSP

Flight Launch from Cape Canaveral (KSC); landing on Cape Canaveral (KSC).

Primary payload: United States Microgravity Laboratory-1 (USML-1); 31 experiments as crystal growth experiments; life science and biological experiments; investigation of fluid dynamics in microgravity; longest Shuttle-flight to date.

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Personnel STS 52/USMP 1

Publications NSSDC ID: 1992-070A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events STS 52 was the 13th space shuttle Columbia mission launched 22194 from Cape Canaveral. On board were Astronauts James Wetherbee, Michael Baker, William Sheperd, Tamara Jernigan, and Charles Veach. It carried the US Microgravity Payload-2 Facts in Brief (USMP-2) which contained several microgravity experimental Launch Date: 1992-10- packages. Among them were the growth of cadmium telluride 22 crystals from vapor phase, growth of protein/enzyme crystals, Launch and a number of high school experiments such as the clotting Vehicle: Shuttle action of snake venom on blood plasma proteins, germination Launch Site: Cape of Florida's official flower seeds, and microgravity effect on dry Canaveral, United States mustard seeds that were germinated after return. Also on- Mass: 9106.0 kg board were 6 rats that had been given anti-osteoporotic treatment with an experimental drug. The mission duration was 236 hours 56 minutes 13 seconds. Funding Agency

NASA-Office of Space Flight (United States)

Discipline

Human Crew

Additional Information

Launch/Orbital information for STS 52/USMP 1 Telecommunications information for STS 52/USMP 1

Experiments on STS 52/USMP 1

Data collections from STS 52/USMP 1

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Columbia (13)

USA

Launch, orbit and landing data

Launch date: 22.10.1992 Launch time: 17:09 UT Launch site: Cape Canaveral (KSC) Launch pad: 39-B Altitude: 302 km Inclination: 28,45° Landing date: 01.11.1992 Landing time: 14:05 UT Landing site: Cape Canaveral (KSC)

Crew No Orbit Surname Given name Job Flight No. Duration . s Wetherbe CD 1 James Donald "Wexbee" 2 9d 20h 56m 159 e R 2 Baker Michael Allen PLT 2 9d 20h 56m 159

MS 3 Veach Charles Lacy 2 9d 20h 56m 159 P MS 4 Shepherd William McMichael 3 9d 20h 56m 159 P Tamara Elizabeth MS 5 Jernigan 2 9d 20h 56m 159 "Tammy" P 6 MacLean Steven Glenwood PSP 1 9d 20h 56m 159

Crew seating arrangement

Launch Wetherb 1 ee 2 Baker 3 Veach Shepher 4 d 5 Jernigan

Landing 1 Wetherbee 2 Baker 3 Jernigan 4 Shepherd 5 Veach

6 MacLean

6 MacLean

Backup Crew

No Given Surname Job . name Bjarni Tryggvaso PS 6 Valdima n P r

hi res version (828 KB) Flight Launch from Cape Canaveral (KSC); landing on Cape Canaveral (KSC).

Deploying of Laser Geodynamic Satellite II (LAGEOS-II); second primary objective was the operation of U.S. Microgravity Payload 1 (USMP-1) with three experiments; heat pipe experiments; Canadian experiment "CANEX-2 (with Space Vision System).

Photos / Drawings

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Personnel STS 53

Publications NSSDC ID: 1992-086A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The STS-53 Space Shuttle "Discovery" mission is a dedicated STS/DoD 1 Department of Defense (DoD) mission and carried the DoD-1 STS 53/DoD 1 classified payload. In addition, several non-classified DoD experiments were carried out. The Space Shuttle "Discovery" 22259 had been completely refurbished and modified. The secondary unclassified experiments include: (1) Shuttle Glow (GLO), to Facts in Brief investigate Shuttle/space environment interactions; (2) Cryogenic Heat Pipe Experiment (CRYOHP), a joint DoD and Launch Date: 1992-12- NASA Hitchhiker experiment to test advanced technology to 02 regect excess heat generated by infrared sensors; (3) Orbital Launch Debris Radar Calibration System (ODERACS), an experiment Vehicle: Shuttle which will release 6 calibrated spheres into orbit in order to Launch Site: Cape provide a source for fine-tuning ground-based radar facilities Canaveral, United States around the world; (4) Battlefield Laser Acquisition Sensor Test Mass: 11868.0 kg (BLAST), an Army space project to demonstrate the use of spaceborne laser receivers to detect laser energy from ground test locations; (5) Cloud Logic to Optimize Use of Defense Funding Agencies System (CLOUDS), a meteorological experiment to quantify NASA-Office of Space the variation in apparent cloud cover as a function of orbital Flight (United States) view angle; (6) Cosmic Radiation Effects and Activation Monitor (CREAM), an experiment designed to collect cosmic Department of Defense- ray energy loss spectra, neutron fluxes, and induced Department of the Air radioactivity; (7) Fluid Acquisition and Resupply Equipment Force (United States) (FARE), an experimen t to investigate the dynamics of fluid transfer in space; (8) Hand-held, earth-oriented, Real-time, Disciplines Cooperative, User-friendly, Location-targeting and Environmental System (HERCULES), a Naval Research Lab Earth Science (NRL) experiment to enable a Shuttle astrionaut to point a Human Crew camera at an Earth feature, record the image and determine the latitude and longitude of the feature; (10) Microencapsulation In Space (MIS), designed to incresae the Additional knowledge of microencapsulated drug technology; (11) Information Radiation Monitoring Equipment -III (RME-III), an instrument to measure the exposure to ionizing radiation on the Shuttle; (12) Launch/Orbital Space Tissue Loss (STL), to study the effects of space on information for STS 53 fragile life systems; and (13) Visual Function Tester - Model II PDMP information for (VFT-2), a series of vision performance experiments in space. STS 53 Telecommunications information for STS 53

Experiments on STS 53

Data collections from STS 53

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Personnel

Name Role Original Affiliation E-mail Dr. Robert Mission US Air Force Space Ballard Manager Division Mr. Leonard Program NASA Johnson Space [email protected] Nicholson Manager Center

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Discovery (15)

USA

Launch, orbit and landing data

Launch date: 02.12.1992 Launch time: 13:24 UT Launch site: Cape Canaveral (KSC) Launch pad: 39-A Altitude: 322 km Inclination: 57° Landing date: 09.12.1992 Landing time: 20:43 UT Landing site: Edwards AFB

Crew No Surnam Orbit Given name Job Flight No. Duration . e s CD 1 Walker David Mathieson 3 7d 07h 19m 116 R 2 Cabana Robert Donald PLT 2 7d 07h 19m 116

MS 3 Bluford Guion Stewart, Jr. "Guy" 4 7d 07h 19m 116 P Michael Richard Uram MS 4 Clifford 1 7d 07h 19m 116 "Rich" P MS 5 Voss James Shelton 2 7d 07h 19m 116 P

Crew seating arrangement

Launch 1 Walker Caban 2 a 3 Bluford 4 Clifford 5 Voss

Landing 1 Walker 2 Cabana 3 Voss 4 Clifford 5 Bluford

Flight Launch from Cape Canaveral (KSC); landing on Edwards AFB.

Final dedicated Department of Defense mission; deploying primary payload DoD-1-satellite (Imaging Radar Satellite "Lacrosse" or "Keyhole-Satellite" - not clarified); several scientific experiments on the area of materials science. Photos / Drawings

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Personnel Superbird A-1

Publications NSSDC ID: 1992-084A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Superbird A-1 was a Japanese geostaionary communications 22253 satellite launched by an Ariane 42-P booster from the Kourou Space Center in French Guiana. The final parking longitude was 158 deg E longitude. Facts in Brief Launch Date: 1992-12- 01 Launch Vehicle: Ariane 42P Launch Site: Kourou, French Guiana Mass: 2780.0 kg

Funding Agency

Space Communication Corporation (SCC) (Japan)

Discipline

Communications

Additional Information

Launch/Orbital information for Superbird A-1

Experiments on Superbird A-1

Data collections from Superbird A-1

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Personnel Superbird B1

Publications NSSDC ID: 1992-010A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events Superbird B1 was a Japanese communications satellite 21893 launched using the Ariane-44L vehicle from the Kourou Space Center in French Guiana. Facts in Brief

Launch Date: 1992-02- 26 Launch Vehicle: Ariane 44L Launch Site: Kourou, French Guiana Mass: 2560.0 kg

Funding Agency

Space Communication Corporation (SCC) (Japan)

Discipline

Communications

Additional Information

Launch/Orbital information for Superbird B1

Experiments on Superbird B1

Data collections from Superbird B1

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Personnel TELECOM 2B

Publications NSSDC ID: 1992-021A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events TELCOM 2B was a French geostationary communications 21939 satellite launched by an Ariane booster rocket from the Kourou Space Center in French Guiana. Facts in Brief

Launch Date: 1992-04- 15 Launch Vehicle: Ariane 44L Launch Site: Kourou, French Guiana Mass: 2200.0 kg

Funding Agency

France Telecom (France)

Discipline

Communications

Additional Information

Launch/Orbital information for TELECOM 2B

Experiments on TELECOM 2B

Data collections from TELECOM 2B

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Personnel Topex/Poseidon

Publications NSSDC ID: 1992-052A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The Ocean Topography Experiment (TOPEX/Poseidon) 22076 mission was a collaboration between NASA and the Centre National d'Etudes Spatiales (CNES) of France to obtain global measurements of sea-surface heights using radar altimetry. Facts in Brief Topex/Poseidon was a core element of the World Ocean Launch Date: 1992-08- Circulation Experiment (WOCE), an international study 10 designed to improve our understanding of global climate Launch Vehicle: Ariane predictions conducted in the early 1990's. TOPEX/Poseidon, 42P the second element in NASA's Mission to Planet Earth (MTPE) Launch Site: Kourou, program, was designed to measure shifts in the global climate French Guiana system that account for global warming or cooling, and the El Mass: 2402.0 kg Nino phenomena in the Pacific basin. The TOPEX/Poseidon Nominal spacecraft design was based on the existing Multimission Power: 2100.0 W Modular Satellite (MMS) bus flown on the French/CNES SPOT 2 spacecraft. The TOPEX/Poseidon spacecraft consisted of the MMS and the instrument module housing the sensors. The Funding Agencies MMS consisted of: (1) a command and data handling subsystem which contained the main on-board computer; (2) National Aeronautics and the attitude determination and control subsystem, for Space Administration maintaining the spacecraft attitude; and, (3) the electrical (United States) power subsystem, which contained the solar array and three Centre National d'Etudes batteries. The command and data handling subsystem housed Spatiales (France) three tape recorders for collecting engineering telemetry and instrument data. This subsystem also provided telecommunications using a steerable high-gain antenna dish Disciplines and two omni antennas. During normal operations, the satellite Engineering communicated with the Tracking and Data Relay Satellite System (TDRSS). The 8.7 m by 3.3 m solar array was Earth Science deployed about two minutes after separation from the launch vehicle. The batteries provided power before deployment of Additional the solar array and during the nighttime part of the orbit. The Information TOPEX/Poseidon spacecraft carried the following instruments: (1) the Dual-Frequency TOPEX Radar Altimeter (ALT), Launch/Orbital provided by NASA, the first 2-channel radar altimeter to be information for used in space and a follow-on to the radar altimeter flown on Topex/Poseidon Seasat in 1978; (2) the TOPEX Microwave Radiometer (TMR), PDMP information for provided by NASA, a three-channel passive microwave Topex/Poseidon radiometer for the detection of atmospheric water vapor to correct the altimeter data; (3) the Single-Frequency Poseidon Telecommunications Altimeter (SSALT), provided by CNES, an experiment to information for validate improved radar altimetry technology; (4) the Doppler Topex/Poseidon Orbitography and Radiopositioning Integrated by Satellite (DORIS) experiment, provided by CNES, for precise orbit Experiments on determination (a DORIS system was also on the French/CNES Topex/Poseidon SPOT 2 spacecraft); and, (5) the Global Positioning System Demonstration Receiver (GPSDR), an experimental receiver Data collections from provided by NASA for continuous orbit determination. The Topex/Poseidon spacecraft also carried a ring of laser corner-reflectors (LRA) around the altimeter antenna for precise satellite tracking by a http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1992-052A[26/04/2011 23:08:32] NASA - NSSDC - Spacecraft - Details

network of twelve ground stations. The spacecraft orbit was Questions or comments designed to cover 90% of the global ocean every 11 days. The about this spacecraft can lifetime of TOPEX/Poseidon is expected to be 3 to 5 years. be directed to: Dr. Dieter K. Bilitza.

Personnel

Name Role Original Affiliation E-mail Dr. Jean Louis Program Centre National d'Etudes Fellous Manager Spatiales Mr. Charles A. Project NASA Jet Propulsion [email protected] Yamarone, Jr. Manager Laboratory Dr. Michel Project NASA Jet Propulsion Lefebvre Scientist Laboratory Dr. William C. Program NASA Headquarters [email protected] Patzert Scientist Dr. Alain Ratier Program Centre National d'Etudes Scientist Spatiales Mr. Michel Dorrer Project Centre National d'Etudes Manager Spatiales Dr. W. Linwood Project NASA Headquarters Jones, Jr. Manager Mr. Lee-Lueng Fu Project NASA Jet Propulsion [email protected] Scientist Laboratory

Selected References

Born, G. H., et al., Topex: Observing the oceans from space, EOS, 65, No. 28, 433-434, July 1984.

Topex/Poseidon mission description, In--1633-5, Rev. B, JPL D-601, Rev. B, JPL/NASA, Dec. 1985.

TOPEX/Poseidon Sci Work Team, Topex/Poseidon science investigations plan, In--JPL/NASA, Sep. 1991.

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Personnel TSS-1

Publications NSSDC ID: TSS-1 Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The Tethered Satellite System (TSS) consists of a satellite, a Tethered Satellite System conducting tether, and a tether deployment/retrieval system to 1 be flown on the Space Shuttle. The objectives of the TSS-1 mission were to: (1) verify engineering performance of the Tethered Satellite System (TSS); (2) determine and Facts in Brief understand the electro-magnetic interaction between the Launch Date: 1992-06- tether/satellite/orbiter system and the ambient space plasma; 25 (3) investigate and understand the dynamical forces acting Launch upon a tethered satellite; and, (4) develop the capability for Vehicle: Shuttle future tether applications on the Shuttle and Space Station. Launch Site: Cape Canaveral, United States The TSS released a satellite while remaining attached to a reel Mass: 518.0 kg in the orbiter payload bay. This mission was intended to demonstrate control of the satellite during deployment, aerodynamic stability at flight altitude, and the ability of the Funding Agencies TSS-1 system to collect meaningful scientific data and to return the data to the Orbiter, and then to the Payload Operations Control NASA-Office of Space Center (POCC). The satellite was to be deployed 20 Km (12.5 Science Applications miles) above the Orbiter. The deploying equipment consisted (United States) of a Spacelab pallet, a reel for tether deployment, an Piano Spaziale Nazionale extendible/retractable boom for initial deployment and final of CNR (Italy) retrieval of the satellite, an electrical power and distribution subsystem, a communications and data management subsystem, and a tether control capability. A separate support Disciplines structure carried science instrumentation. Engineering The spherical satellite was 1.6 meters in diameter, with the Space Physics upper hemisphere containing some of the scientific payload, and the lower hemisphere containing the support equipment. Additional The satellite contained cold gas (nitrogen) thrusters used for Information deployment, retrieval, and attitude control. The 2.54 mm diameter conducting tether cowas constructed using Kevlar Launch/Orbital and Nomex with 10 strands of 34 AWG copper wire and a information for TSS-1 Teflon sheath. PDMP information for TSS-1 NASA was reponsible for the TSS deployer and systems integration, and Italy for building the satellite. Five Telecommunications investigations from Italy and five from the USA were selected information for TSS-1 for the first mission. Experiments on TSS-1 Because of a technical problem (a protruding bolt) the tether could only be released to about 840 feet. A reflight of the Data collections from TSS- tether system (TSS-1R) is now scheduled for February 1996. 1

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Bilitza.

Personnel

Name Role Original Affiliation E-mail Dr. Michael A. Program NASA Headquarters [email protected] Calabrese Manager Prof. Franco Program Consiglio Nazionale delle [email protected] Mariani Scientist Ricerche Mr. Nobie H. Mission NASA Marshall Space Stone Scientist Flight Center Mr. James M. Mission NASA Marshall Space Sisson Manager Flight Center Prof. Marino Program Consiglio Nazionale delle [email protected] Dobrowolny Scientist Ricerche Dr. G. Manarini Program Consiglio Nazionale delle Manager Ricerche Dr. Stanley D. Program NASA Headquarters Shawhan Scientist

Other TSS 1 Data/Information at NSSDC

Read about the final report regarding the TSS 1 malfunction

Related Information/Data at NSSDC

STS 46 TSS-1R

Other Sources of TSS 1 Information/Data

TSS home page

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Personnel UMSP-1

Publications NSSDC ID: USMP-1 Maps Description Facts in Brief New/Updated Data

Lunar/Planetary Events Launch Date: 1992-10- 21 Launch Vehicle: Shuttle Launch Site: Cape Canaveral, United States

Funding Agency

National Aeronautics and Space Administration (United States)

Discipline

Microgravity

Additional Information

Launch/Orbital information for UMSP-1 Telecommunications information for UMSP-1

Experiments on UMSP-1

Data collections from UMSP-1

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Personnel USA 81

Publications NSSDC ID: 1992-023A Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events USA 81 was a US Air Force signals intelligence satellite 21949 launched from Vandenberg AFB aboard a Titan 2 rocket. It probably performed some kind of imaging also. Onboard propulsion boosted the spacecraft to an 800 km operating Facts in Brief orbit. Launch Date: 1992-04- 25 Launch Vehicle: Titan II Launch Site: Vandenberg AFB, United States Mass: 1700.0 kg

Funding Agency

Department of Defense- Department of the Air Force (United States)

Discipline

Surveillance and Other Military

Additional Information

Launch/Orbital information for USA 81

Experiments on USA 81

Data collections from USA 81

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Personnel USA 89

Publications NSSDC ID: 1992-086B Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The US Air Force's second generation classified Satellite Data SDS-2 System (SDS-2) replaced the SDS-1 system starting with its 22518 second launch in 1992 of USA 89. Like its predecessors, the SDS-2 spacecraft had high apogee and low perigee, enabling it to cover the polar regions for Air Force communications in Facts in Brief those areas. The SDS-2, however, had an additional package, the Heritage (Radiant Agate) infrared early warning system for Launch Date: 1992-12- detection of ballistic missile launches. The Shuttle payload 02 envelope defined the satellite's design. It featured two 15-foot Launch diameter dish antennas adapted by Hughes from its TDRSS-3 Vehicle: Shuttle satellite design. It also had a third dish (6.6 feet in diameter) Launch Site: Cape that served as a k-band antenna downlink. It had two more Canaveral, United States antennas, one that was used for uplink communications, and Mass: 700.0 kg another that was a telemetry and command antenna, which was used as a backup. The body itself, based on LEASAT, Funding Agency was cylindrical and was 14 feet in diameter and 9.5 feet long. Its solar arrays generated 1238 watts of power with support Department of Defense- from three 25-amp-hour nickel-cadium batteries. Department of the Air Force (United States)

Discipline

Surveillance and Other Military

Additional Information

Launch/Orbital information for USA 89

Experiments on USA 89

Data collections from USA 89

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Personnel USML 1

Publications NSSDC ID: USMLAB1 Maps Description Alternate Names New/Updated Data

Lunar/Planetary Events The United States Microgravity Laboratory (USML-1) was a US Microgravity Lab 1 Spacelab long module with an Extended Duration Orbiter (EDO) pallet in the aft cargo bay. It carried 31 investigations from five basic areas: 1) The fluid dynamics experiments Facts in Brief examined basic fluid phenomena, from movement caused by Launch Date: 1992-06- heating to the dyanmics of individual liquid drops; 2) The 25 Crystal Growth experiments grew a variety of inorganic and Launch organic crystals; 3) The Combustion Science experiments Vehicle: Shuttle examined the differences in the shapes of flames and how Launch Site: Cape these spread in microgravity versus gravity; 4) The Biological Canaveral, United States experiments examined the production of various products and Mass: 9988.0 kg monitored the changes to human physiology as a result of extended exposure to microgravity; and 5) the Technology Demonstrations tested experimental concepts and facilities for Funding Agency use on future missions. Four new experiment facilities were flown on the USML-1: the Crystal Growth Furnace which was NASA-Office of Space used to grow high-quality semiconductor and infrared detector Science Applications crystals using both directional solidification and vapor growth (United States) techniques; the Glovebox which was used for direct manipulation of experiments while keeping the crew isolated Disciplines from the materials involved; the Surface Tension Driven Convection Experiment apparatus which conducted studies of Life Science fluid mechanics and heat transfer; and the Drop Physics Microgravity Module which used acoustic force (sound waves) to position and manipulate liquid drops so that their physical and chemical properties could be examined. Additional Information

Launch/Orbital information for USML 1 PDMP information for USML 1 Telecommunications information for USML 1

Experiments on USML 1

Data collections from USML 1

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