Cronología de Lanzamientos Espaciales
Año 1988
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 144 spacecraft returned.
Maps Spacecraft Name NSSDC ID Launch Date New/Updated Data Astra 1A 1988-109B 1988-12-11
Lunar/Planetary Events Buran 1988-100A 1988-11-15 Cosmos 1908 1988-001A 1988-01-06 Cosmos 1909 1988-002A 1988-01-15 Cosmos 1910 1988-002B 1988-01-15 Cosmos 1911 1988-002C 1988-01-15 Cosmos 1912 1988-002D 1988-01-15 Cosmos 1913 1988-002E 1988-01-15 Cosmos 1914 1988-002F 1988-01-15 Cosmos 1915 1988-004A 1988-01-26 Cosmos 1916 1988-007A 1988-02-03 Cosmos 1917 1988-009A 1988-02-18 Cosmos 1918 1988-009B 1988-02-18 Cosmos 1919 1988-009C 1988-02-18 Cosmos 1920 1988-010A 1988-02-18 Cosmos 1921 1988-011A 1988-02-19 Cosmos 1922 1988-013A 1988-02-26 Cosmos 1923 1988-015A 1988-03-10 Cosmos 1924 1988-016A 1988-03-11 Cosmos 1925 1988-016B 1988-03-11 Cosmos 1926 1988-016C 1988-03-11 Cosmos 1927 1988-016D 1988-03-11 Cosmos 1928 1988-016E 1988-03-11 Cosmos 1929 1988-016F 1988-03-11 Cosmos 1930 1988-016G 1988-03-11 Cosmos 1931 1988-016H 1988-03-11 Cosmos 1932 1988-019A 1988-03-14 Cosmos 1933 1988-020A 1988-03-15 Cosmos 1934 1988-023A 1988-03-22 Cosmos 1935 1988-025A 1988-03-24 Cosmos 1936 1988-027A 1988-03-30 Cosmos 1937 1988-029A 1988-04-05 Cosmos 1938 1988-030A 1988-04-11 Cosmos 1939 1988-032A 1988-04-20 Cosmos 1940 1988-034A 1988-04-26 Cosmos 1941 1988-035A 1988-04-27
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Cosmos 1942 1988-037A 1988-05-12 Cosmos 1943 1988-039A 1988-05-15 Cosmos 1944 1988-041A 1988-05-18 Cosmos 1945 1988-042A 1988-05-19 Cosmos 1946 1988-043A 1988-05-21 Cosmos 1947 1988-043B 1988-05-21 Cosmos 1948 1988-043C 1988-05-21 Cosmos 1949 1988-045A 1988-05-28 Cosmos 1950 1988-046A 1988-05-30 Cosmos 1951 1988-047A 1988-05-31 Cosmos 1952 1988-049A 1988-06-11 Cosmos 1953 1988-050A 1988-06-14 Cosmos 1954 1988-053A 1988-06-21 Cosmos 1955 1988-054A 1988-06-22 Cosmos 1956 1988-055A 1988-06-23 Cosmos 1957 1988-057A 1988-07-07 Cosmos 1958 1988-060A 1988-07-14 Cosmos 1959 1988-062A 1988-07-18 Cosmos 1960 1988-065A 1988-07-28 Cosmos 1961 1988-066A 1988-08-01 Cosmos 1962 1988-068A 1988-08-08 Cosmos 1963 1988-070A 1988-08-16 Cosmos 1964 1988-072A 1988-08-23 Cosmos 1965 1988-073A 1988-08-23 Cosmos 1966 1988-076A 1988-08-30 Cosmos 1967 1988-079A 1988-09-06 Cosmos 1968 1988-082A 1988-09-09 Cosmos 1969 1988-084A 1988-09-15 Cosmos 1970 1988-085A 1988-09-16 Cosmos 1971 1988-085B 1988-09-16 Cosmos 1972 1988-085C 1988-09-16 Cosmos 1973 1988-088A 1988-09-22 Cosmos 1974 1988-092A 1988-10-03 Cosmos 1975 1988-093A 1988-10-11 Cosmos 1976 1988-094A 1988-10-13 Cosmos 1977 1988-096A 1988-10-25 Cosmos 1978 1988-097A 1988-10-27 Cosmos 1979 1988-101A 1988-11-18 Cosmos 1980 1988-102A 1988-11-23 Cosmos 1981 1988-103A 1988-11-24 Cosmos 1982 1988-105A 1988-11-30 Cosmos 1983 1988-107A 1988-12-08 Cosmos 1984 1988-110A 1988-12-16 Cosmos 1985 1988-113A 1988-12-23 Cosmos 1986 1988-116A 1988-12-29 DMSP 5D-2/F09 1988-006A 1988-02-03 Ekran 18 1988-036A 1988-05-06 Ekran 19 1988-108A 1988-12-10 EUTELSAT 5 1988-063B 1988-07-21
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Fengyun 1A 1988-080A 1988-09-06 Foton 4 1988-031A 1988-04-14 Gorizont 15 1988-028A 1988-03-31 Gorizont 16 1988-071A 1988-08-18 GSTAR 3 1988-081A 1988-09-08 INSAT 1C 1988-063A 1988-07-21 INTELSAT 5A F-13 1988-040A 1988-05-17 IRS-1A 1988-021A 1988-03-17 KH 11-9 1988-099A 1988-11-06 Lacrosse 1 1988-106B 1988-12-02 Meteor 2-17 1988-005A 1988-01-30 Meteor 3-2 1988-064A 1988-07-26 Meteosat 3 1988-051A 1988-06-15 Molniya 1-71 1988-017A 1988-03-11 Molniya 1-72 1988-022A 1988-03-17 Molniya 1-73 1988-069A 1988-08-12 Molniya 1-74 1988-115A 1988-12-28 Molniya 3-32 1988-044A 1988-05-26 Molniya 3-33 1988-090A 1988-09-29 Molniya 3-34 1988-112A 1988-12-22 NOAA 11 1988-089A 1988-09-24 NOSS 9 1988-078A 1988-09-05 NOVA II 1988-052A 1988-06-16 Ofeq 1 1988-087A 1988-09-19 Okean 1 1988-056A 1988-07-05 OSCAR 13 1988-051B 1988-06-15 PANAMSAT 1 1988-051C 1988-06-15 Phobos 1 1988-058A 1988-07-07 Phobos 2 1988-059A 1988-07-12 PRC 22 1988-014A 1988-03-07 PRC 23 1988-067A 1988-08-05 PRC 25 1988-111A 1988-12-22 Progress 34 1988-003A 1988-01-20 Progress 35 1988-024A 1988-03-23 Progress 36 1988-038A 1988-05-13 Progress 37 1988-061A 1988-07-18 Progress 38 1988-083A 1988-09-09 Progress 39 1988-114A 1988-12-25 Raduga 22 1988-095A 1988-10-20 Sakura-3A 1988-012A 1988-02-19 Sakura-3B 1988-086A 1988-09-16 San Marco-D/L 1988-026A 1988-03-25 SBS 5 1988-081B 1988-09-08 Skynet 4B 1988-109A 1988-12-11 Soyuz TM- 5 1988-048A 1988-06-07 Soyuz TM- 6 1988-075A 1988-08-29 Soyuz TM- 7 1988-104A 1988-11-26 Spacenet 3 1988-018A 1988-03-11 STS 26 1988-091A 1988-09-29
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STS 27 1988-106A 1988-12-02 TDF 1 1988-098A 1988-10-28 TDRS-C 1988-091B 1988-09-29 TELECOM 1C 1988-018B 1988-03-11 Transit-O 23 1988-033A 1988-04-26 Transit-O 25 1988-074A 1988-08-25 Transit-O 31 1988-074B 1988-08-25 Transit-O 32 1988-033B 1988-04-26 USA 30 1988-008A 1988-02-08 USA 31 1988-077A 1988-09-02
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Personnel Astra 1A
Publications NSSDC ID: 1988-109B Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events ASTRA 1 was a Luxembourg television satellite launched from 19688 Kourou, French Guiana. It was owned and operated by Societe Europienne des Satellites (SES), a private company formed in 1985. It carried 16 Ku-band transponders (with six Facts in Brief spares) and had a design life of 12 years. Launch Date: 1988-12- 11 Launch Vehicle: Ariane 44LP Launch Site: Kourou, French Guiana Mass: 1767.7 kg
Funding Agency
Societe Europeenne des Satellites (Luxembourg) (Luxembourg)
Discipline
Communications
Additional Information
Launch/Orbital information for Astra 1A
Experiments on Astra 1A
Data collections from Astra 1A
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Buran
Publications NSSDC ID: 1988-100A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Buran was launched by the USSR. It was a reusable orbital 19637 spacecraft placed in near-earth orbit by the Energiya rocket. After circling the earth twice, it re-entered the atmosphere and landed successfully. Facts in Brief Launch Date: 1988-11- 15 Launch Vehicle: Energia Launch Site: Tyuratam (Baikonur Cosmodrome), U.S.S.R Mass: 73000.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Engineering
Additional Information
Launch/Orbital information for Buran
Experiments on Buran
Data collections from Buran
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Cosmos 1908
Publications NSSDC ID: 1988-001A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 1908 was a Soviet ELINT (Electronic and Signals 18748 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: 1988-01- Ministry of Defence could not force a single system on the 06 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 U.S.S.R detailed observations. ELINT systems for Tselina were first Mass: 1600.0 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 1908
Experiments on Cosmos 1908
Data collections from Cosmos 1908
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 4.0.14, 08 October 2010
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Personnel Cosmos 1909
Publications NSSDC ID: 1988-002A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events The Strela 3 system was a communications satellite 18788 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: 1988-01- forces. The Strela 3 system, which began in 1985, was 15 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 U.S.S.R 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 1909
Experiments on Cosmos 1909
Data collections from Cosmos 1909
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Cosmos 1910
Publications NSSDC ID: 1988-002B Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events The Strela 3 system was a communications satellite 18789 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: 1988-01- forces. The Strela 3 system, which began in 1985, was 15 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 U.S.S.R 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 1910
Experiments on Cosmos 1910
Data collections from Cosmos 1910
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Cosmos 1911
Publications NSSDC ID: 1988-002C Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events The Strela 3 system was a communications satellite 18790 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: 1988-01- forces. The Strela 3 system, which began in 1985, was 15 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 U.S.S.R 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 1911
Experiments on Cosmos 1911
Data collections from Cosmos 1911
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 4.0.14, 08 October 2010
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Personnel Cosmos 1912
Publications NSSDC ID: 1988-002D Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events The Strela 3 system was a communications satellite 18791 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: 1988-01- forces. The Strela 3 system, which began in 1985, was 15 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 U.S.S.R 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 1912
Experiments on Cosmos 1912
Data collections from Cosmos 1912
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 4.0.14, 08 October 2010
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Personnel Cosmos 1913
Publications NSSDC ID: 1988-002E Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events The Strela 3 system was a communications satellite 18792 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: 1988-01- forces. The Strela 3 system, which began in 1985, was 15 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 U.S.S.R 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 1913
Experiments on Cosmos 1913
Data collections from Cosmos 1913
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 4.0.14, 08 October 2010
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Personnel Cosmos 1914
Publications NSSDC ID: 1988-002F Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events The Strela 3 system was a communications satellite 18793 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: 1988-01- forces. The Strela 3 system, which began in 1985, was 15 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 U.S.S.R 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 1914
Experiments on Cosmos 1914
Data collections from Cosmos 1914
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 4.0.14, 08 October 2010
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Personnel Cosmos 1915
Publications NSSDC ID: 1988-004A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 1915 was a Soviet military cartographic photo- 18809 surveillance satellite launched from the Plesetsk Cosmodrome aboard a Soyuz 11 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: 1988-01- international cooperation. Typical orbital profile: inclination 70 26 degrees with altitude of 350-420 km. Designed duration: 15 Launch Vehicle: Soyuz days. Transmission frequencies observed in West: 19.989 Launch Site: Plesetsk, FSK; 39.978 FSK; 232.0 PPM-AM. U.S.S.R Mass: 6300.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for Cosmos 1915
Experiments on Cosmos 1915
Data collections from Cosmos 1915
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 4.0.14, 08 October 2010
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Personnel Cosmos 1916
Publications NSSDC ID: 1988-007A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 1916 was a Soviet photo surveillance satellite 18823 launched from the Baikonur cosmodrome aboard a Soyuz rocket. Two small film capsules were recovered in flight and the main reentry capsule with remaining film, camera, and Facts in Brief computer systems at end of flight. Launch Date: 1988-02- 03 Launch Vehicle: Soyuz Launch Site: Tyuratam (Baikonur Cosmodrome), U.S.S.R Mass: 6600.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for Cosmos 1916
Experiments on Cosmos 1916
Data collections from Cosmos 1916
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Cosmos 1917
Publications NSSDC ID: 1988-009A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 1917 was launched with Cosmos 1918 and Cosmos 18857 1919 to test the elements and equipment of a space navigation system. The separation unit containing the satellites failed to reach the required orbit, entered dense layers of the Facts in Brief atmosphere, and ceased to function. Launch Date: 1988-02- 18 Launch Vehicle: Proton-K Launch Site: Tyuratam (Baikonur Cosmodrome), U.S.S.R Mass: 1400.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Navigation & Global Positioning
Additional Information
Launch/Orbital information for Cosmos 1917
Experiments on Cosmos 1917
Data collections from Cosmos 1917
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Cosmos 1918
Publications NSSDC ID: 1988-009B Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 1918 was launched with Cosmos 1917 and Cosmos 18856 1919 to test the elements and equipment of a space navigation system. The separation unit containing the satellites failed to reach the required orbit, entered dense layers of the Facts in Brief atmosphere, and ceased to function. Launch Date: 1988-02- 18 Launch Vehicle: Proton-K Launch Site: Tyuratam (Baikonur Cosmodrome), U.S.S.R Mass: 1400.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Navigation & Global Positioning
Additional Information
Launch/Orbital information for Cosmos 1918
Experiments on Cosmos 1918
Data collections from Cosmos 1918
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 4.0.14, 08 October 2010
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Personnel Cosmos 1919
Publications NSSDC ID: 1988-009C Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 1919 was launched with Cosmos 1917 and Cosmos 18855 1918 to test the elements and equipment of a space navigation system. The separation unit containing the satellites failed to reach the required orbit, entered dense layers of the Facts in Brief atmosphere, and ceased to function. Launch Date: 1988-02- 18 Launch Vehicle: Proton-K Launch Site: Tyuratam (Baikonur Cosmodrome), U.S.S.R Mass: 1400.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Navigation & Global Positioning
Additional Information
Launch/Orbital information for Cosmos 1919
Experiments on Cosmos 1919
Data collections from Cosmos 1919
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 4.0.14, 08 October 2010
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Personnel Cosmos 1920
Publications NSSDC ID: 1988-010A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 1920 was a Soviet remote sensing satellite launched 18860 from the Plesetsk cosmodrome aboard a Soyuz rocket. Its purpose was to investigate the natural resources of the earth in the interests of various branches of the national economy of Facts in Brief the USSR and international cooperation. It remained Launch Date: 1988-02- operational for 20 days. 18 Launch Vehicle: Soyuz Launch Site: Plesetsk, U.S.S.R Mass: 6300.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Earth Science
Additional Information
Launch/Orbital information for Cosmos 1920
Experiments on Cosmos 1920
Data collections from Cosmos 1920
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 4.0.14, 08 October 2010
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Personnel Cosmos 1921
Publications NSSDC ID: 1988-011A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 1921 was a Soviet military cartographic photo- 18875 surveillance satellite launched from the Baikonur Cosmodrome aboard a Soyuz 11 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: 1988-02- international cooperation. Typical orbital profile: inclination 70 19 degrees with altitude of 350-420 km. Designed duration: 15 Launch Vehicle: Soyuz days. Transmission frequencies observed in West: 19.989 Launch Site: Tyuratam FSK; 39.978 FSK; 232.0 PPM-AM. (Baikonur Cosmodrome), U.S.S.R Mass: 6300.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for Cosmos 1921
Experiments on Cosmos 1921
Data collections from Cosmos 1921
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 4.0.14, 08 October 2010
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Personnel Cosmos 1922
Publications NSSDC ID: 1988-013A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 1922 was a Soviet missile early warning satellite 18881 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: 1988-02- 26 Launch Vehicle: Molniya-M Launch Site: Plesetsk, U.S.S.R Mass: 1800.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for Cosmos 1922
Experiments on Cosmos 1922
Data collections from Cosmos 1922
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 4.0.14, 08 October 2010
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Personnel Cosmos 1923
Publications NSSDC ID: 1988-015A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 1923 was a Soviet military cartographic photo- 18931 surveillance satellite launched from the Plesetsk Cosmodrome aboard a Soyuz 11 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: 1988-03- international cooperation. Typical orbital profile: inclination 70 10 degrees with altitude of 350-420 km. Designed duration: 15 Launch Vehicle: Soyuz days. Transmission frequencies observed in West: 19.989 Launch Site: Plesetsk, FSK; 39.978 FSK; 232.0 PPM-AM. U.S.S.R Mass: 6300.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for Cosmos 1923
Experiments on Cosmos 1923
Data collections from Cosmos 1923
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 4.0.14, 08 October 2010
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Personnel Cosmos 1924
Publications NSSDC ID: 1988-016A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events The lowest level of the three-tier communications satellite 18937 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: 1988-03- Federation and overseas stations or forces. These Strela 11 (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 U.S.S.R 0.75 m) relay satellites launched from Plesetsk by the Kosmos Mass: 40.0 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 1924
Experiments on Cosmos 1924
Data collections from Cosmos 1924
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 4.0.14, 08 October 2010
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Personnel Cosmos 1925
Publications NSSDC ID: 1988-016B Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events The lowest level of the three-tier communications satellite 18938 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: 1988-03- Federation and overseas stations or forces. These Strela 11 (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 U.S.S.R 0.75 m) relay satellites launched from Plesetsk by the Kosmos Mass: 40.0 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 1925
Experiments on Cosmos 1925
Data collections from Cosmos 1925
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 4.0.14, 08 October 2010
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Personnel Cosmos 1926
Publications NSSDC ID: 1988-016C Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events The lowest level of the three-tier communications satellite 18939 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: 1988-03- Federation and overseas stations or forces. These Strela 11 (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 U.S.S.R 0.75 m) relay satellites launched from Plesetsk by the Kosmos Mass: 40.0 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 1926
Experiments on Cosmos 1926
Data collections from Cosmos 1926
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 4.0.14, 08 October 2010
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1988-016C[05/02/2011 23:07:58] NASA - NSSDC - Spacecraft - Details
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Personnel Cosmos 1927
Publications NSSDC ID: 1988-016D Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events The lowest level of the three-tier communications satellite 18940 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: 1988-03- Federation and overseas stations or forces. These Strela 11 (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 U.S.S.R 0.75 m) relay satellites launched from Plesetsk by the Kosmos Mass: 40.0 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 1927
Experiments on Cosmos 1927
Data collections from Cosmos 1927
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 4.0.14, 08 October 2010
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1988-016D[05/02/2011 23:08:20] NASA - NSSDC - Spacecraft - Details
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Personnel Cosmos 1928
Publications NSSDC ID: 1988-016E Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events The lowest level of the three-tier communications satellite 18941 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: 1988-03- Federation and overseas stations or forces. These Strela 11 (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 U.S.S.R 0.75 m) relay satellites launched from Plesetsk by the Kosmos Mass: 40.0 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 1928
Experiments on Cosmos 1928
Data collections from Cosmos 1928
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 4.0.14, 08 October 2010
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1988-016E[05/02/2011 23:08:41] NASA - NSSDC - Spacecraft - Details
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Personnel Cosmos 1929
Publications NSSDC ID: 1988-016F Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events The lowest level of the three-tier communications satellite 18942 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: 1988-03- Federation and overseas stations or forces. These Strela 11 (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 U.S.S.R 0.75 m) relay satellites launched from Plesetsk by the Kosmos Mass: 40.0 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 1929
Experiments on Cosmos 1929
Data collections from Cosmos 1929
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 4.0.14, 08 October 2010
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1988-016F[05/02/2011 23:09:15] NASA - NSSDC - Spacecraft - Details
Sunday, 06 February 2011
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Personnel Cosmos 1930
Publications NSSDC ID: 1988-016G Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events The lowest level of the three-tier communications satellite 18943 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: 1988-03- Federation and overseas stations or forces. These Strela 11 (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 U.S.S.R 0.75 m) relay satellites launched from Plesetsk by the Kosmos Mass: 40.0 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 1930
Experiments on Cosmos 1930
Data collections from Cosmos 1930
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 4.0.14, 08 October 2010
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1988-016G[05/02/2011 23:10:44] NASA - NSSDC - Spacecraft - Details
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Personnel Cosmos 1931
Publications NSSDC ID: 1988-016H Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events The lowest level of the three-tier communications satellite 18944 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: 1988-03- Federation and overseas stations or forces. These Strela 11 (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 U.S.S.R 0.75 m) relay satellites launched from Plesetsk by the Kosmos Mass: 40.0 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 1931
Experiments on Cosmos 1931
Data collections from Cosmos 1931
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 4.0.14, 08 October 2010
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Personnel Cosmos 1932
Publications NSSDC ID: 1988-019A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 1932 was a Soviet nuclear powered Radar Ocean 18957 Reconnaissance Satellite (RORSAT) launched from the Baikonur cosmodrome aboard a Tsyklon 2 rocket. The RORSATs were designed to search the oceans for US Navy Facts in Brief task forces and other shipping. Launch Date: 1988-03- 14 Launch Vehicle: Tsiklon-2 Launch Site: Tyuratam (Baikonur Cosmodrome), U.S.S.R Mass: 1500.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for Cosmos 1932
Experiments on Cosmos 1932
Data collections from Cosmos 1932
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 4.0.14, 08 October 2010
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Personnel Cosmos 1933
Publications NSSDC ID: 1988-020A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 1933 was a Soviet ELINT (Electronic and Signals 18958 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: 1988-03- Ministry of Defence could not force a single system on the 15 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 U.S.S.R detailed observations. ELINT systems for Tselina were first Mass: 1600.0 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 1933
Experiments on Cosmos 1933
Data collections from Cosmos 1933
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 4.0.14, 08 October 2010
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Personnel Cosmos 1934
Publications NSSDC ID: 1988-023A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 1934 was part of a 6-satellite Soviet military 18985 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: 1988-03- and 400 MHz) of the satellite position and orbital data. By 22 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, U.S.S.R accurate location determination could be made within 1-2 Mass: 700.0 kg hours.
Funding Agency
Unknown (U.S.S.R)
Discipline
Navigation & Global Positioning
Additional Information
Launch/Orbital information for Cosmos 1934
Experiments on Cosmos 1934
Data collections from Cosmos 1934
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 4.0.14, 08 October 2010
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Personnel Cosmos 1935
Publications NSSDC ID: 1988-025A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 1935 was a Soviet photo surveillance satellite 19011 launched from the Plesetsk cosmodrome aboard a Soyuz rocket. Two small film capsules were recovered in flight and the main reentry capsule with remaining film, camera, and Facts in Brief computer systems at end of flight. Launch Date: 1988-03- 24 Launch Vehicle: Soyuz Launch Site: Plesetsk, U.S.S.R Mass: 6600.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for Cosmos 1935
Experiments on Cosmos 1935
Data collections from Cosmos 1935
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 4.0.14, 08 October 2010
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Personnel Cosmos 1936
Publications NSSDC ID: 1988-027A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 1936 was a Soviet digital photo surveillance satellite 19015 launched from the Baikonur cosmodrome aboard a Soyuz 11 rocket. It remained in orbit for 49 days. Facts in Brief
Launch Date: 1988-03- 30 Launch Vehicle: Soyuz Launch Site: Tyuratam (Baikonur Cosmodrome), U.S.S.R Mass: 6600.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for Cosmos 1936
Experiments on Cosmos 1936
Data collections from Cosmos 1936
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 4.0.14, 08 October 2010
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Personnel Cosmos 1937
Publications NSSDC ID: 1988-029A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events The lowest level of the three-tier communications satellite 19038 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: 1988-04- between the Russian Federation and overseas stations of 05 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 U.S.S.R degrees apart. These Strela 2 spacecraft were launched Mass: 700.0 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
Surveillance and Other Military
Additional Information
Launch/Orbital information for Cosmos 1937
Experiments on Cosmos 1937
Data collections from Cosmos 1937
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 4.0.14, 08 October 2010
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Personnel Cosmos 1938
Publications NSSDC ID: 1988-030A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 1938 was a Soviet military cartographic photo- 19041 surveillance satellite launched from the Plesetsk Cosmodrome aboard a Soyuz 11 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: 1988-04- international cooperation. Typical orbital profile: inclination 70 11 degrees with altitude of 350-420 km. Designed duration: 15 Launch Vehicle: Soyuz days. Transmission frequencies observed in West: 19.989 Launch Site: Plesetsk, FSK; 39.978 FSK; 232.0 PPM-AM. U.S.S.R Mass: 6300.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for Cosmos 1938
Experiments on Cosmos 1938
Data collections from Cosmos 1938
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 4.0.14, 08 October 2010
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1988-030A[05/02/2011 23:16:09] NASA - NSSDC - Spacecraft - Details
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Personnel Cosmos 1939
Publications NSSDC ID: 1988-032A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 1939 was the fifth satellite in the Resurs-O1 series Resurs-01 and the first to become operational. The Cosmos 1939/Resurs- 19045 O1 spacecraft was similar to the USA Landsat series and was designed to provide data for geologic applications, cartography, fire detection, ice monitoring, agriculutre and Facts in Brief hydrology. The Resurs-O spacecraft was based on the Meteor- 3 design and is three-axis stabilized. The spacecraft is about 5 Launch Date: 1988-04- m high and consists of 10 m solar pannels. Cosmos 1939 20 consists of 2 multispectral imaging systems: MSU-SK, a 5- Launch Vehicle: SLV-3 channel multispectral conical scanner, and two MSU-E 3- Launch Site: Tyuratam channel pushbroom CCD imagers. The Resurs-O1 spacecraft (Baikonur Cosmodrome), were built by VNII Elecktromekaniki. The Resurs-O/Cosmos U.S.S.R 1939 was preceeded by Meteor 1-30, Meteor 1-31, Cosmos Mass: 1900.0 kg 1484, and Cosmos 1689. See Kozoderov,V.V., etal,"Cosmos Nominal 1939 Data Processing for FIFE 1989",JGR,V.97,No.D17,pp. Power: 500.0 W 18,779-18,784, November 30, 1992. Funding Agency
Soviet Hydrometeorological Service (U.S.S.R)
Discipline
Earth Science
Additional Information
Launch/Orbital information for Cosmos 1939
Experiments on Cosmos 1939
Data collections from Cosmos 1939
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
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Personnel Cosmos 1940
Publications NSSDC ID: 1988-034A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 1940 was part of a Soviet constellation of satellites 19073 comprised of the first 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, Facts in Brief the early warning satellites could detect missile launches within Launch Date: 1988-04- 20 seconds of lift-off. 26 Launch Each satellite possessed a perigee of about 600 km, an Vehicle: Proton-K apogee of nearly 40,000 km, and an inclination of 63 degrees. Launch Site: Tyuratam This orbit was superfically similar to that employed by the (Baikonur Cosmodrome), Molniya communications satellites but was distinguished by U.S.S.R initial argument of perigee 316-319 degrees, including to the Mass: 2000.0 kg Molniya 280-288 degree arguments of perigee. The seemingly minor difference significantly affected the shape of the satellite's groundtrack in the Northern Hemisphere. Funding Agency
Russian early warning spacecraft were more affected by Unknown (U.S.S.R) gravitational perturbations due to their higher argument of perigee and, therefore, performed periodic station-keeping Discipline maneuvers to maintain an acceptable groundtrack. In addition, the argument of perigee migrated slightly over time (due to Surveillance and Other inclination variations), causing an alteration in the shape of the Military groundtrack. Instead of expending additional propellant to prevent the argument of perigee shift, Russian spacecraft controllers altered the satellite's ascending node. This had the Additional effect of "stabilizing" the apogee point about which surveillance Information operations were performed. Launch/Orbital information for Cosmos 1940
Experiments on Cosmos 1940
Data collections from Cosmos 1940
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Cosmos 1941
Publications NSSDC ID: 1988-035A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 1941 was a Soviet military cartographic photo- 19079 surveillance satellite launched from the Baikonur Cosmodrome aboard a Soyuz 11 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: 1988-04- international cooperation. Typical orbital profile: inclination 70 27 degrees with altitude of 350-420 km. Designed duration: 15 Launch Vehicle: Soyuz days. Transmission frequencies observed in West: 19.989 Launch Site: Tyuratam FSK; 39.978 FSK; 232.0 PPM-AM. (Baikonur Cosmodrome), U.S.S.R Mass: 6300.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for Cosmos 1941
Experiments on Cosmos 1941
Data collections from Cosmos 1941
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Cosmos 1942
Publications NSSDC ID: 1988-037A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 1942 was a Soviet photo surveillance satellite 19115 launched from the Plesetsk cosmodrome aboard a Soyuz rocket. Two small film capsules were recovered in flight and the main reentry capsule with remaining film, camera, and Facts in Brief computer systems at end of flight. Launch Date: 1988-05- 12 Launch Vehicle: Soyuz Launch Site: Plesetsk, U.S.S.R Mass: 6600.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for Cosmos 1942
Experiments on Cosmos 1942
Data collections from Cosmos 1942
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Cosmos 1943
Publications NSSDC ID: 1988-039A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 1943 was a Soviet ELINT (Electronic and Signals 19119 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: 1988-05- beginning of the 1970's developed the specifications for an 15 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 U.S.S.R 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 1943
Experiments on Cosmos 1943
Data collections from Cosmos 1943
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Cosmos 1944
Publications NSSDC ID: 1988-041A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 1944 was a variation of the Yantar-class spacecraft 19123 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: 1988-05- always launched from the Baikonur cosmodrome into 18 inclinations of 65 degrees or 70 degrees at the rate of one or Launch Vehicle: Soyuz two per ye Launch Site: Tyuratam (Baikonur Cosmodrome), U.S.S.R Mass: 6600.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for Cosmos 1944
Experiments on Cosmos 1944
Data collections from Cosmos 1944
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Cosmos 1945
Publications NSSDC ID: 1988-042A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 1945 was a Soviet military cartographic photo- 19131 surveillance satellite launched from the Baikonur Cosmodrome aboard a Soyuz 11 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: 1988-05- international cooperation. Typical orbital profile: inclination 70 19 degrees with altitude of 350-420 km. Designed duration: 15 Launch Vehicle: Soyuz days. Transmission frequencies observed in West: 19.989 Launch Site: Tyuratam FSK; 39.978 FSK; 232.0 PPM-AM. (Baikonur Cosmodrome), U.S.S.R Mass: 6300.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for Cosmos 1945
Experiments on Cosmos 1945
Data collections from Cosmos 1945
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Cosmos 1946
Publications NSSDC ID: 1988-043A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 1946 was a Soviet Global Navigation Satellite System 19163 (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 and Facts in Brief fishing vessels, the signals were used by many American GPS Launch Date: 1988-05- system receivers as a complement/backup to the GPS system 21 itself. The operational system contained 21 satellites in 3 Launch orbital planes, with 3 on-orbit backups. Each satellite was Vehicle: Proton-K identified by its slot number, which defined the orbital plane (1- Launch Site: Tyuratam 8, 9-16, 17-24) and the location within the plane. The 3 orbital (Baikonur Cosmodrome), planes were separated 120 degrees, and the satellites within U.S.S.R the same orbit plane by 45 degrees. The orbits were roughly Mass: 1400.0 kg circular with an inclination of about 64.8 degrees, a semi-axis Nominal of 25,440 km, and a period of 11h 15m 44s. Power: 1600.0 W
The 3-axis stabilized spacecraft possessed a mass of about 1,400 kg, a slight increase over the 1,250 original model. The Funding Agency diameter and height of the satellite bus were approximately 2.4 m and 3.7 m, respectively, with a solar array span of 7.2 m for Scientific Production an electrical power generation capability of 1.6 kW at Association(Russia) beginning of life. The aft payload structure housed 12 primary (U.S.S.R) antennas for L-band transmissions. Laser corner-cube reflectors were also carried to aid in precise orbit determination Discipline and gedetic research. Navigation & Global Positioning
Additional Information
Launch/Orbital information for Cosmos 1946
Experiments on Cosmos 1946
Data collections from Cosmos 1946
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Cosmos 1947
Publications NSSDC ID: 1988-043B Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 1947 was a Soviet Global Navigation Satellite System 19164 (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 and Facts in Brief fishing vessels, the signals were used by many American GPS Launch Date: 1988-05- system receivers as a complement/backup to the GPS system 21 itself. The operational system contained 21 satellites in 3 Launch orbital planes, with 3 on-orbit backups. Each satellite was Vehicle: Proton-K identified by its slot number, which defined the orbital plane (1- Launch Site: Tyuratam 8, 9-16, 17-24) and the location within the plane. The 3 orbital (Baikonur Cosmodrome), planes were separated 120 degrees, and the satellites within U.S.S.R the same orbit plane by 45 degrees. The orbits were roughly Mass: 1400.0 kg circular with an inclination of about 64.8 degrees, a semi-axis Nominal of 25,440 km, and a period of 11h 15m 44s. Power: 1600.0 W
The 3-axis stabilized spacecraft possessed a mass of about 1,400 kg, a slight increase over the 1,250 original model. The Funding Agency diameter and height of the satellite bus were approximately 2.4 m and 3.7 m, respectively, with a solar array span of 7.2 m for Scientific Production an electrical power generation capability of 1.6 kW at Association(Russia) beginning of life. The aft payload structure housed 12 primary (U.S.S.R) antennas for L-band transmissions. Laser corner-cube reflectors were also carried to aid in precise orbit determination Discipline and gedetic research. Navigation & Global Positioning
Additional Information
Launch/Orbital information for Cosmos 1947
Experiments on Cosmos 1947
Data collections from Cosmos 1947
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Cosmos 1948
Publications NSSDC ID: 1988-043C Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 1948 was a Soviet Global Navigation Satellite System 19165 (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 and Facts in Brief fishing vessels, the signals were used by many American GPS Launch Date: 1988-05- system receivers as a complement/backup to the GPS system 21 itself. The operational system contained 21 satellites in 3 Launch orbital planes, with 3 on-orbit backups. Each satellite was Vehicle: Proton-K identified by its slot number, which defined the orbital plane (1- Launch Site: Tyuratam 8, 9-16, 17-24) and the location within the plane. The 3 orbital (Baikonur Cosmodrome), planes were separated 120 degrees, and the satellites within U.S.S.R the same orbit plane by 45 degrees. The orbits were roughly Mass: 1400.0 kg circular with an inclination of about 64.8 degrees, a semi-axis Nominal of 25,440 km, and a period of 11h 15m 44s. Power: 1600.0 W
The 3-axis stabilized spacecraft possessed a mass of about 1,400 kg, a slight increase over the 1,250 original model. The Funding Agency diameter and height of the satellite bus were approximately 2.4 m and 3.7 m, respectively, with a solar array span of 7.2 m for Scientific Production an electrical power generation capability of 1.6 kW at Association(Russia) beginning of life. The aft payload structure housed 12 primary (U.S.S.R) antennas for L-band transmissions. Laser corner-cube reflectors were also carried to aid in precise orbit determination Discipline and gedetic research. Navigation & Global Positioning
Additional Information
Launch/Orbital information for Cosmos 1948
Experiments on Cosmos 1948
Data collections from Cosmos 1948
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Cosmos 1949
Publications NSSDC ID: 1988-045A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 1949 was a Soviet naval reconnaisance satellite 19193 launched from the Baikonur cosmodrome aboard a Tsyklon 2 rocket. This naval forces monitoring spacecraft was used to determine the position of enemy naval forces through detection Facts in Brief and triangulation of their electromagnetic emissions (radio, Launch Date: 1988-05- radar, etc). 28 Launch Vehicle: Tsiklon-2 Launch Site: Tyuratam (Baikonur Cosmodrome), U.S.S.R Mass: 3000.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for Cosmos 1949
Experiments on Cosmos 1949
Data collections from Cosmos 1949
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Cosmos 1950
Publications NSSDC ID: 1988-046A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 1950 was a Soviet geodetic satellite launched from 19195 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: 1988-05- 3 cm accuracy 2. High intensity lights flashing 3 times per 30 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. U.S.S.R Mass: 1500.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Earth Science
Additional Information
Launch/Orbital information for Cosmos 1950
Experiments on Cosmos 1950
Data collections from Cosmos 1950
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Cosmos 1951
Publications NSSDC ID: 1988-047A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 1951 was a Soviet remote sensing satellite launched 19197 from the Plesetsk cosmodrome aboard a Soyuz rocket. Its purpose was to investigate the natural resources of the earth in the interests of various branches of the national economy of Facts in Brief the USSR and international cooperation. Launch Date: 1988-05- 31 Launch Vehicle: Soyuz Launch Site: Plesetsk, U.S.S.R Mass: 6300.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Earth Science
Additional Information
Launch/Orbital information for Cosmos 1951
Experiments on Cosmos 1951
Data collections from Cosmos 1951
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Cosmos 1952
Publications NSSDC ID: 1988-049A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 1952 was a Soviet military cartographic photo- 19206 surveillance satellite launched from the Baikonur Cosmodrome aboard a Soyuz 11 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: 1988-06- international cooperation. Typical orbital profile: inclination 70 11 degrees with altitude of 350-420 km. Designed duration: 15 Launch Vehicle: Soyuz days. Transmission frequencies observed in West: 19.989 Launch Site: Tyuratam FSK; 39.978 FSK; 232.0 PPM-AM. (Baikonur Cosmodrome), U.S.S.R Mass: 6300.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for Cosmos 1952
Experiments on Cosmos 1952
Data collections from Cosmos 1952
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Cosmos 1953
Publications NSSDC ID: 1988-050A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 1953 was a Soviet ELINT (Electronic and Signals 19210 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: 1988-06- Ministry of Defence could not force a single system on the 14 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 U.S.S.R detailed observations. ELINT systems for Tselina were first Mass: 1600.0 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 1953
Experiments on Cosmos 1953
Data collections from Cosmos 1953
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Cosmos 1954
Publications NSSDC ID: 1988-053A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events The lowest level of the three-tier communications satellite 19256 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: 1988-06- between the Russian Federation and overseas stations of 21 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 U.S.S.R degrees apart. These Strela 2 spacecraft were launched Mass: 700.0 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 1954
Experiments on Cosmos 1954
Data collections from Cosmos 1954
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Cosmos 1955
Publications NSSDC ID: 1988-054A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 1955 was a Soviet photo surveillance satellite 19258 launched from the Baikonur cosmodrome aboard a Soyuz rocket. Two small film capsules were recovered in flight and the main reentry capsule with remaining film, camera, and Facts in Brief computer systems at end of flight. Launch Date: 1988-06- 22 Launch Vehicle: Soyuz Launch Site: Tyuratam (Baikonur Cosmodrome), U.S.S.R Mass: 6600.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for Cosmos 1955
Experiments on Cosmos 1955
Data collections from Cosmos 1955
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Cosmos 1956
Publications NSSDC ID: 1988-055A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 1956 was a Soviet military cartographic photo- 19263 surveillance satellite launched from the Plesetsk Cosmodrome aboard a Soyuz 11 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: 1988-06- international cooperation. Typical orbital profile: inclination 70 23 degrees with altitude of 350-420 km. Designed duration: 15 Launch Vehicle: Soyuz days. Transmission frequencies observed in West: 19.989 Launch Site: Plesetsk, FSK; 39.978 FSK; 232.0 PPM-AM. U.S.S.R Mass: 6300.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for Cosmos 1956
Experiments on Cosmos 1956
Data collections from Cosmos 1956
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Cosmos 1957
Publications NSSDC ID: 1988-057A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 1957 was a Soviet remote sensing satellite launched 19276 from the Plesetsk cosmodrome aboard a Soyuz rocket. Its purpose was to investigate the natural resources of the earth in the interests of various branches of the national economy of Facts in Brief the USSR and international cooperation. Launch Date: 1988-07- 07 Launch Vehicle: Soyuz Launch Site: Plesetsk, U.S.S.R Mass: 6300.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Earth Science
Additional Information
Launch/Orbital information for Cosmos 1957
Experiments on Cosmos 1957
Data collections from Cosmos 1957
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Cosmos 1958
Publications NSSDC ID: 1988-060A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 1958 was a Soviet atmospheric research satellite 19320 launched from the Plesetsk cosmodrome aboard a Kosmos 11 rocket. It was part of a series of Vektor spacecraft. Facts in Brief
Launch Date: 1988-07- 14 Launch Vehicle: Cosmos Launch Site: Plesetsk, U.S.S.R
Funding Agency
Unknown (U.S.S.R)
Discipline
Earth Science
Additional Information
Launch/Orbital information for Cosmos 1958
Experiments on Cosmos 1958
Data collections from Cosmos 1958
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Cosmos 1959
Publications NSSDC ID: 1988-062A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 1959 was part of a 6-satellite Soviet military 19324 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: 1988-07- and 400 MHz) of the satellite position and orbital data. By 18 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, U.S.S.R accurate location determination could be made within 1-2 Mass: 700.0 kg hours.
Funding Agency
Unknown (U.S.S.R)
Discipline
Navigation & Global Positioning
Additional Information
Launch/Orbital information for Cosmos 1959
Experiments on Cosmos 1959
Data collections from Cosmos 1959
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Cosmos 1960
Publications NSSDC ID: 1988-065A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events From 1969 KB Yuzhnoye built the Lira targets for exercise and 19338 test of PVO air defence and space tracking systems. The second generation consisted of Taifun-1 and Taifun-2 satellites, which differed in the type of equipment installed. Facts in Brief Taifun-1 would release up to 25 Romb sub-satellites, while Launch Date: 1988-07- Taifun-2 did not. In 1972 KB-3 under B E Khimrov, with the co- 28 operation of assisting organisations and the Ministry of Launch Defence, completed the draft project. The first Taifun-1 was Vehicle: Cosmos completed in 1974, and flight trials were conducted in the Launch Site: Plesetsk, second half of the 1970's using Kosmos-3M launch vehicles U.S.S.R from Plesetsk and Kapustin Yar. The heads of the State Trials Commission were B N Karpov, N N Zhukov, and B G Zudin. Taifun-1 normally released 25 Romb subsatellites into an orbit Funding Agency of 300 to 500 km altitude, at inclinations of 50.7 degrees (from Kapustin Yar) and 65.9 74, or 82.9 degrees (from Plesetsk). Unknown (U.S.S.R) Two unique missions in 1989-1990 were put into 180 km x 1550 km orbits at 65.8 degrees. With this higher apogee the Discipline payload was reduced to 10 Romb subsatellites. Vektor satellites were spherical in shape, about 2 m in diameter, the Surveillance and Other surface covered with solar cells and equipped with four Military antennae.
Additional Information
Launch/Orbital information for Cosmos 1960
Experiments on Cosmos 1960
Data collections from Cosmos 1960
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Cosmos 1961
Publications NSSDC ID: 1988-066A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 1961 was a Soviet military second generation global 19344 command and control system (GKKRS) satellite launched from the Baiknour cosmodrome aboard a Proton K rocket. These satellites were integrated with the Luch geostationary system Facts in Brief and featured retransmission of high rate data retransmission in Launch Date: 1988-08- the centimetre wavelength range. While Luch handled 01 communications between spacecraft and ground stations, Launch Potok handled communications between fixed points and Vehicle: Proton-K digital data from the Yantar-4KS1 electroptical reconnaissance Launch Site: Tyuratam satellite. Potok was the first communications spacecraft built by (Baikonur Cosmodrome), the Lavochkin design bureau and used the Splav-2 U.S.S.R transponder by NPO Elas. Mass: 2000.0 kg
Potok is said by one account to have utilized the KAUR-4 spacecraft bus. This had an active 3-axis orientation system, Funding Agency with a single central body from which extended 40 square metres of solar panels. Its basic structure was that of the Unknown (U.S.S.R) KAUR-3, but it was equipped with completely new systems: a digital computer, plasma station-keeping engines, hydrazine Discipline monopropellant orientation engines, and actively-scanned antennae arrays with 0.5 degrees antenna and 0.1 degree Communications spacecraft pointing accuracy. Cosmos 1961 was stationed at 13.5 deg W and later moved to 80 deg E. Additional Information
Launch/Orbital information for Cosmos 1961
Experiments on Cosmos 1961
Data collections from Cosmos 1961
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Cosmos 1962
Publications NSSDC ID: 1988-068A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 1962 was a Soviet military cartographic photo- 19372 surveillance satellite launched from the Baikonur Cosmodrome aboard a Soyuz 11 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: 1988-08- international cooperation. Typical orbital profile: inclination 70 08 degrees with altitude of 350-420 km. Designed duration: 15 Launch Vehicle: Soyuz days. Transmission frequencies observed in West: 19.989 Launch Site: Tyuratam FSK; 39.978 FSK; 232.0 PPM-AM. (Baikonur Cosmodrome), U.S.S.R Mass: 6300.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for Cosmos 1962
Experiments on Cosmos 1962
Data collections from Cosmos 1962
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Cosmos 1963
Publications NSSDC ID: 1988-070A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 1963 was a Soviet photo surveillance satellite 19384 launched from the Baikonur cosmodrome aboard a Soyuz rocket. Two small film capsules were recovered in flight and the main reentry capsule with remaining film, camera, and Facts in Brief computer systems at end of flight. Launch Date: 1988-08- 16 Launch Vehicle: Soyuz Launch Site: Tyuratam (Baikonur Cosmodrome), U.S.S.R Mass: 6600.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for Cosmos 1963
Experiments on Cosmos 1963
Data collections from Cosmos 1963
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 4.0.14, 08 October 2010
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Personnel Cosmos 1964
Publications NSSDC ID: 1988-072A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 1964 was a Soviet military cartographic photo- 19412 surveillance satellite launched from the Baikonur Cosmodrome aboard a Soyuz 11 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: 1988-08- international cooperation. Typical orbital profile: inclination 70 23 degrees with altitude of 350-420 km. Designed duration: 15 Launch Vehicle: Soyuz days. Transmission frequencies observed in West: 19.989 Launch Site: Tyuratam FSK; 39.978 FSK; 232.0 PPM-AM. (Baikonur Cosmodrome), U.S.S.R Mass: 6300.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for Cosmos 1964
Experiments on Cosmos 1964
Data collections from Cosmos 1964
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 4.0.14, 08 October 2010
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Personnel Cosmos 1965
Publications NSSDC ID: 1988-073A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 1965 was a Soviet remote sensing satellite launched 19414 from the Plesetsk cosmodrome aboard a Soyuz rocket. Its purpose was to investigate the natural resources of the earth in the interests of various branches of the national economy of Facts in Brief the USSR and international cooperation. Launch Date: 1988-08- 23 Launch Vehicle: Soyuz Launch Site: Plesetsk, U.S.S.R Mass: 6300.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Earth Science
Additional Information
Launch/Orbital information for Cosmos 1965
Experiments on Cosmos 1965
Data collections from Cosmos 1965
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 4.0.14, 08 October 2010
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Personnel Cosmos 1966
Publications NSSDC ID: 1988-076A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 1966 was a Soviet missile early warning satellite 19445 launched from the Plesetsk cosmodrome aboard a Molniya rocket. It was part of the Oko constellation and covered the plane 3 - 355 degree longitude of ascending node. Facts in Brief Launch Date: 1988-08- 30 Launch Vehicle: Molniya-M Launch Site: Plesetsk, U.S.S.R Mass: 1250.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for Cosmos 1966
Experiments on Cosmos 1966
Data collections from Cosmos 1966
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 4.0.14, 08 October 2010
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Personnel Cosmos 1967
Publications NSSDC ID: 1988-079A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 1967 was a Soviet military cartographic photo- 19462 surveillance satellite launched from the Plesetsk Cosmodrome aboard a Soyuz 11 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: 1988-09- international cooperation. Typical orbital profile: inclination 70 06 degrees with altitude of 350-420 km. Designed duration: 15 Launch Vehicle: Soyuz days. Transmission frequencies observed in West: 19.989 Launch Site: Plesetsk, FSK; 39.978 FSK; 232.0 PPM-AM. U.S.S.R Mass: 6300.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for Cosmos 1967
Experiments on Cosmos 1967
Data collections from Cosmos 1967
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 4.0.14, 08 October 2010
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Personnel Cosmos 1968
Publications NSSDC ID: 1988-082A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 1968 was a Soviet remote sensing satellite launched 19488 from the Plesetsk cosmodrome aboard a Soyuz rocket. Its purpose was to investigate the natural resources of the earth in the interests of various branches of the national economy of Facts in Brief the USSR and international cooperation. Launch Date: 1988-09- 09 Launch Vehicle: Soyuz Launch Site: Plesetsk, U.S.S.R Mass: 6300.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Earth Science
Additional Information
Launch/Orbital information for Cosmos 1968
Experiments on Cosmos 1968
Data collections from Cosmos 1968
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 4.0.14, 08 October 2010
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Personnel Cosmos 1969
Publications NSSDC ID: 1988-084A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 1969 was a Soviet photo surveillance satellite 19495 launched from the Plesetsk cosmodrome aboard a Soyuz rocket. Two small film capsules were recovered in flight and the main reentry capsule with remaining film, camera, and Facts in Brief computer systems at end of flight. Launch Date: 1988-09- 15 Launch Vehicle: Soyuz Launch Site: Plesetsk, U.S.S.R Mass: 6600.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for Cosmos 1969
Experiments on Cosmos 1969
Data collections from Cosmos 1969
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 4.0.14, 08 October 2010
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Personnel Cosmos 1970
Publications NSSDC ID: 1988-085A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 1970 was a Soviet Global Navigation Satellite System 19501 (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 and Facts in Brief fishing vessels, the signals were used by many American GPS Launch Date: 1988-09- system receivers as a complement/backup to the GPS system 16 itself. The operational system contained 21 satellites in 3 Launch orbital planes, with 3 on-orbit backups. Each satellite was Vehicle: Proton-K identified by its slot number, which defined the orbital plane (1- Launch Site: Tyuratam 8, 9-16, 17-24) and the location within the plane. The 3 orbital (Baikonur Cosmodrome), planes were separated 120 degrees, and the satellites within U.S.S.R the same orbit plane by 45 degrees. The orbits were roughly Mass: 1400.0 kg circular with an inclination of about 64.8 degrees, a semi-axis Nominal of 25,440 km, and a period of 11h 15m 44s. Power: 1600.0 W
The 3-axis stabilized spacecraft possessed a mass of about 1,400 kg, a slight increase over the 1,250 original model. The Funding Agency diameter and height of the satellite bus were approximately 2.4 m and 3.7 m, respectively, with a solar array span of 7.2 m for Scientific Production an electrical power generation capability of 1.6 kW at Association(Russia) beginning of life. The aft payload structure housed 12 primary (U.S.S.R) antennas for L-band transmissions. Laser corner-cube reflectors were also carried to aid in precise orbit determination Discipline and gedetic research. Navigation & Global Positioning
Additional Information
Launch/Orbital information for Cosmos 1970
Experiments on Cosmos 1970
Data collections from Cosmos 1970
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Cosmos 1971
Publications NSSDC ID: 1988-085B Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 1971 was a Soviet Global Navigation Satellite System 19502 (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 and Facts in Brief fishing vessels, the signals were used by many American GPS Launch Date: 1988-09- system receivers as a complement/backup to the GPS system 16 itself. The operational system contained 21 satellites in 3 Launch orbital planes, with 3 on-orbit backups. Each satellite was Vehicle: Proton-K identified by its slot number, which defined the orbital plane (1- Launch Site: Tyuratam 8, 9-16, 17-24) and the location within the plane. The 3 orbital (Baikonur Cosmodrome), planes were separated 120 degrees, and the satellites within U.S.S.R the same orbit plane by 45 degrees. The orbits were roughly Mass: 1400.0 kg circular with an inclination of about 64.8 degrees, a semi-axis Nominal of 25,440 km, and a period of 11h 15m 44s. Power: 1600.0 W
The 3-axis stabilized spacecraft possessed a mass of about 1,400 kg, a slight increase over the 1,250 original model. The Funding Agency diameter and height of the satellite bus were approximately 2.4 m and 3.7 m, respectively, with a solar array span of 7.2 m for Scientific Production an electrical power generation capability of 1.6 kW at Association(Russia) beginning of life. The aft payload structure housed 12 primary (U.S.S.R) antennas for L-band transmissions. Laser corner-cube reflectors were also carried to aid in precise orbit determination Discipline and gedetic research. Navigation & Global Positioning
Additional Information
Launch/Orbital information for Cosmos 1971
Experiments on Cosmos 1971
Data collections from Cosmos 1971
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Cosmos 1972
Publications NSSDC ID: 1988-085C Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 1972 was a Soviet Global Navigation Satellite System 19503 (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 and Facts in Brief fishing vessels, the signals were used by many American GPS Launch Date: 1988-09- system receivers as a complement/backup to the GPS system 16 itself. The operational system contained 21 satellites in 3 Launch orbital planes, with 3 on-orbit backups. Each satellite was Vehicle: Proton-K identified by its slot number, which defined the orbital plane (1- Launch Site: Tyuratam 8, 9-16, 17-24) and the location within the plane. The 3 orbital (Baikonur Cosmodrome), planes were separated 120 degrees, and the satellites within U.S.S.R the same orbit plane by 45 degrees. The orbits were roughly Mass: 1400.0 kg circular with an inclination of about 64.8 degrees, a semi-axis Nominal of 25,440 km, and a period of 11h 15m 44s. Power: 1600.0 W
The 3-axis stabilized spacecraft possessed a mass of about 1,400 kg, a slight increase over the 1,250 original model. The Funding Agency diameter and height of the satellite bus were approximately 2.4 m and 3.7 m, respectively, with a solar array span of 7.2 m for Scientific Production an electrical power generation capability of 1.6 kW at Association(Russia) beginning of life. The aft payload structure housed 12 primary (U.S.S.R) antennas for L-band transmissions. Laser corner-cube reflectors were also carried to aid in precise orbit determination Discipline and gedetic research. Navigation & Global Positioning
Additional Information
Launch/Orbital information for Cosmos 1972
Experiments on Cosmos 1972
Data collections from Cosmos 1972
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Cosmos 1973
Publications NSSDC ID: 1988-088A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 1973 was a Soviet military cartographic photo- 19521 surveillance satellite launched from the Plesetsk Cosmodrome aboard a Soyuz 11 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: 1988-09- international cooperation. Typical orbital profile: inclination 70 22 degrees with altitude of 350-420 km. Designed duration: 15 Launch Vehicle: Soyuz days. Transmission frequencies observed in West: 19.989 Launch Site: Plesetsk, FSK; 39.978 FSK; 232.0 PPM-AM. U.S.S.R Mass: 6300.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for Cosmos 1973
Experiments on Cosmos 1973
Data collections from Cosmos 1973
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 4.0.14, 08 October 2010
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Personnel Cosmos 1974
Publications NSSDC ID: 1988-092A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 1974 was a Soviet missile early warning satellite 19554 launched from the Plesetsk cosmodrome aboard a Molniya rocket. It was part of the Oko constellation of satellites and covered the plane 7 - 157 degree longitude of ascending node. Facts in Brief Launch Date: 1988-10- 03 Launch Vehicle: Molniya-M Launch Site: Plesetsk, U.S.S.R Mass: 1250.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for Cosmos 1974
Experiments on Cosmos 1974
Data collections from Cosmos 1974
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 4.0.14, 08 October 2010
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Personnel Cosmos 1975
Publications NSSDC ID: 1988-093A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 1975 was a Soviet ELINT (Electronic and Signals 19573 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: 1988-10- Ministry of Defence could not force a single system on the 11 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 U.S.S.R detailed observations. ELINT systems for Tselina were first tested under the Cosmos designation in 1962 to 1965. The first Tselina-O was launched in 1970. The Tselina-D took a long Funding Agency time to enter service due to delays in payload development and weight growth. The whole Tselina system was not Unknown (U.S.S.R) operational until 1976. Constant improvement resulted in Tselina-O being abandoned in 1984 and all systems being put Discipline on Tselina-D. Surveillance and Other Military
Additional Information
Launch/Orbital information for Cosmos 1975
Experiments on Cosmos 1975
Data collections from Cosmos 1975
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 4.0.14, 08 October 2010
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Personnel Cosmos 1976
Publications NSSDC ID: 1988-094A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 1976 was a Soviet military cartographic photo- 19582 surveillance satellite launched from the Plesetsk Cosmodrome aboard a Soyuz 11 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: 1988-10- international cooperation. Typical orbital profile: inclination 70 13 degrees with altitude of 350-420 km. Designed duration: 15 Launch Vehicle: Soyuz days. Transmission frequencies observed in West: 19.989 Launch Site: Plesetsk, FSK; 39.978 FSK; 232.0 PPM-AM. U.S.S.R Mass: 6300.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for Cosmos 1976
Experiments on Cosmos 1976
Data collections from Cosmos 1976
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 4.0.14, 08 October 2010
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Personnel Cosmos 1977
Publications NSSDC ID: 1988-096A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 1977 was a Soviet missile early warning satellite 19608 launched from the Plesetsk cosmodrome aboard a Molniya rocket. It was part of the Oko constellation of satellites and covered the plane 6 - 116 degree longitude of ascending node. Facts in Brief Launch Date: 1988-10- 25 Launch Vehicle: Molniya-M Launch Site: Plesetsk, U.S.S.R Mass: 1250.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for Cosmos 1977
Experiments on Cosmos 1977
Data collections from Cosmos 1977
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 4.0.14, 08 October 2010
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Personnel Cosmos 1978
Publications NSSDC ID: 1988-097A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 1978 was a Soviet military cartographic photo- 19612 surveillance satellite launched from the Plesetsk Cosmodrome aboard a Soyuz 11 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: 1988-10- international cooperation. Typical orbital profile: inclination 70 27 degrees with altitude of 350-420 km. Designed duration: 15 Launch Vehicle: Soyuz days. Transmission frequencies observed in West: 19.989 Launch Site: Plesetsk, FSK; 39.978 FSK; 232.0 PPM-AM. U.S.S.R Mass: 6300.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for Cosmos 1978
Experiments on Cosmos 1978
Data collections from Cosmos 1978
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Cosmos 1979
Publications NSSDC ID: 1988-101A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 1979 was a Soviet naval reconnaisance satellite 19647 launched from the Baikonur cosmodrome aboard a Tsyklon 2 rocket. This naval forces monitoring spacecraft was used to determine the position of enemy naval forces through detection Facts in Brief and triangulation of their electromagnetic emissions (radio, Launch Date: 1988-11- radar, etc). 18 Launch Vehicle: Tsiklon-3 Launch Site: Tyuratam (Baikonur Cosmodrome), U.S.S.R Mass: 3000.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for Cosmos 1979
Experiments on Cosmos 1979
Data collections from Cosmos 1979
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Cosmos 1980
Publications NSSDC ID: 1988-102A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 1980 was a Soviet ELINT (Electronic and Signals 19649 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: 1988-11- beginning of the 1970's developed the specifications for an 23 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 U.S.S.R 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 1980
Experiments on Cosmos 1980
Data collections from Cosmos 1980
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Cosmos 1981
Publications NSSDC ID: 1988-103A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 1981 was a Soviet military cartographic photo- 19651 surveillance satellite launched from the Plesetsk Cosmodrome aboard a Soyuz 11 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: 1988-11- international cooperation. Typical orbital profile: inclination 70 24 degrees with altitude of 350-420 km. Designed duration: 15 Launch Vehicle: Soyuz days. Transmission frequencies observed in West: 19.989 Launch Site: Plesetsk, FSK; 39.978 FSK; 232.0 PPM-AM. U.S.S.R Mass: 6300.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for Cosmos 1981
Experiments on Cosmos 1981
Data collections from Cosmos 1981
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Cosmos 1982
Publications NSSDC ID: 1988-105A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 1982 was a Soviet military cartographic photo- 19662 surveillance satellite launched from the Baikonur Cosmodrome aboard a Soyuz 11 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: 1988-11- international cooperation. Typical orbital profile: inclination 70 30 degrees with altitude of 350-420 km. Designed duration: 15 Launch Vehicle: Soyuz days. Transmission frequencies observed in West: 19.989 Launch Site: Tyuratam FSK; 39.978 FSK; 232.0 PPM-AM. (Baikonur Cosmodrome), U.S.S.R Mass: 6300.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for Cosmos 1982
Experiments on Cosmos 1982
Data collections from Cosmos 1982
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Cosmos 1983
Publications NSSDC ID: 1988-107A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 1983 was a Soviet military cartographic photo- 19672 surveillance satellite launched from the Plesetsk Cosmodrome aboard a Soyuz 11 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: 1988-12- international cooperation. Typical orbital profile: inclination 70 08 degrees with altitude of 350-420 km. Designed duration: 15 Launch Vehicle: Soyuz days. Transmission frequencies observed in West: 19.989 Launch Site: Plesetsk, FSK; 39.978 FSK; 232.0 PPM-AM. U.S.S.R Mass: 6300.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for Cosmos 1983
Experiments on Cosmos 1983
Data collections from Cosmos 1983
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 4.0.14, 08 October 2010
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Personnel Cosmos 1984
Publications NSSDC ID: 1988-110A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 1984 was a Soviet photo surveillance satellite 19705 launched from the Plesetsk cosmodrome aboard a Soyuz rocket. Two small film capsules were recovered in flight and the main reentry capsule with remaining film, camera, and Facts in Brief computer systems at end of flight. Launch Date: 1988-12- 16 Launch Vehicle: Soyuz Launch Site: Plesetsk, U.S.S.R Mass: 6600.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for Cosmos 1984
Experiments on Cosmos 1984
Data collections from Cosmos 1984
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Cosmos 1985
Publications NSSDC ID: 1988-113A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 1985 was a Soviet military calibration mission 19720 launched from the Plesetsk cosmodrome aboard a Tsyklon 3 rocket. It was believed to be a modernised version of the Taifun-1 satellite, built by NPO Yuzhnoe. The satellite carried Facts in Brief 36 small Calibration Spherical Object subsatellites to test Launch Date: 1988-12- Russian radars. These were released between December 27, 23 1989 and November 1, 1991. Launch Vehicle: Tsiklon-3 Launch Site: Plesetsk, U.S.S.R
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for Cosmos 1985
Experiments on Cosmos 1985
Data collections from Cosmos 1985
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Cosmos 1986
Publications NSSDC ID: 1988-116A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Cosmos 1986 was a variation of the Yantar-class spacecraft 19734 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: 1988-12- always launched from the Baikonur cosmodrome into 29 inclinations of 65 degrees or 70 degrees at the rate of one or Launch Vehicle: Soyuz two per year. Launch Site: Tyuratam (Baikonur Cosmodrome), U.S.S.R Mass: 6600.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for Cosmos 1986
Experiments on Cosmos 1986
Data collections from Cosmos 1986
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel DMSP 5D-2/F09
Publications NSSDC ID: 1988-006A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events DMSP 5D-2/F9 is one of a series of meteorological satellites USA 29 developed and operated by the Air Force under the Defense DMSP-F9 Meteorological Satellite Program (DMSP). This program, previously known as DAPP (Data Acquisition and Processing 18822 Program), was classified until March 1973. The objective of this program is to provide global visual and infrared cloudcover Facts in Brief data and specialized environmental data to support Department of Defense operational weather analysis and Launch Date: 1988-02- forecasting requirements. Operationally, the program consists 03 of two satellites in planned 830-km, sun-synchronous polar Launch Vehicle: Atlas orbits, with the ascending node of one satellite in early morning E and the other at local noon. The 6.4-m-long spacecraft is Launch separated into four sections: (1) a precision mounting platform Site: Vandenberg AFB, for sensors and equipment requiring precise alignment; (2) an United States equipment support module containing the electronics, reaction Mass: 468.0 kg wheels, and some meteorological sensors; (3) a reaction control equipment support structure containing the third-stage rocket motor and supporting the ascent phase reaction control Funding Agency equipment; and (4) a 9.29-sq-m solar cell panel. The Department of Defense- spacecraft stabilization is controlled by a combination flywheel Department of the Air and magnetic control coil system so sensors are maintained in Force (United States) the desired "earth-looking" mode. One feature is the precision- pointing accuracy of the primary imager to 0.01 deg provided by a star sensor and an updated ephemeris navigation system. Disciplines This allows automatic geographical mapping of the digital imagery to the nearest picture element. The operational Astronomy linescan system is the primary data acquisition system that Earth Science provides real-time or stored, multi-orbit, day-and-night visual Space Physics and infrared imagery of clouds. A supplementary sensor package contains four special sensors: (1) an advanced X-ray spectrometer, (2) an ionospheric/scintillation monitor, (3) a Additional precipitating electron/ion spectrometer, and (4) an infrared Information temperature and moisture sounder. Either recorded or real- time data are transmitted to ground-receiving sites by two Launch/Orbital redundant S-band transmitters. Recorded data are read out to information for DMSP 5D- tracking sites located at Fairchild AFB, Washington, and at 2/F09 Loring AFB, Maine, and relayed by SATCOM to Air Force Global Weather Center, Offutt AFB, Nebraska. Real-time data Experiments on DMSP 5D- are read out at mobile tactical sites located around the world. 2/F09 Additional information concerning this satellite program can be found in the report by D.A. Nichols, "The Defense Data collections from Meteorological Satellite Program," Optical Engineering, v. 14, DMSP 5D-2/F09 n. 4, p. 273, July-August 1975.
Questions or comments about this spacecraft can be directed to: Dr. Dieter K. Bilitza.
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Personnel
Name Role Original Affiliation E-mail Col J. Rivers Program Manager US Air Force Space Division
Other Sources of DMSP Data/Information
SSIES ion data (U. Texas - Dallas)
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Personnel Ekran 18
Publications NSSDC ID: 1988-036A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Ekran 18 was a Soviet communications satellite launched from 19090 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: 1988-05- single-unit body was equipped with solar panels, and active 06 liquid-gas phase-change thermoregulation system, and a Launch corrective engine unit for making orbital adjustments. Twenty- Vehicle: Proton-K five square metres of solar panels provided 1280 W of power. Launch Site: Tyuratam (Baikonur Cosmodrome), U.S.S.R Mass: 1970.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Communications
Additional Information
Launch/Orbital information for Ekran 18
Experiments on Ekran 18
Data collections from Ekran 18
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Ekran 19
Publications NSSDC ID: 1988-108A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Ekran 19 was a Soviet communications satellite launched from 19683 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: 1988-12- single-unit body was equipped with solar panels, and active 10 liquid-gas phase-change thermoregulation system, and a Launch corrective engine unit for making orbital adjustments. Twenty- Vehicle: Proton-K five square metres of solar panels provided 1280 W of power. Launch Site: Tyuratam (Baikonur Cosmodrome), U.S.S.R Mass: 1970.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Communications
Additional Information
Launch/Orbital information for Ekran 19
Experiments on Ekran 19
Data collections from Ekran 19
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 4.0.14, 08 October 2010
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Personnel EUTELSAT 5
Publications NSSDC ID: 1988-063B Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events The EUTELSAT I series of satellites was developed by the ECS 5 European Space Agency (ESA) as part of the European 19331 Communications Satellite (ECS) program. Once launched and checked out in a geostationary orbit over Europe, each satellite was handed to EUTELSAT for commercial operations. Four Facts in Brief EUTELSAT I satellites were successfully launched between 1983-1988. They served both public and private traffic, Launch Date: 1988-07- including telephone services, fax, data, land mobile service, 21 and television and radio programming. Each had a design life Launch Vehicle: Ariane of 7 years and a bandwidth of 72 MHz. EUTELSAT 5 was 3 positioned at 12.5 degrees E. Launch Site: Kourou, French Guiana Mass: 1185.4 kg
Funding Agency
European Telecommunications Satellite Consortium (International)
Discipline
Communications
Additional Information
Launch/Orbital information for EUTELSAT 5
Experiments on EUTELSAT 5
Data collections from EUTELSAT 5
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Fengyun 1A
Publications NSSDC ID: 1988-080A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events In 1988 and again in 1990 the People's Republic of China FY-1A launched FY-1 (Feng Yun - Wind and Cloud) meterological PRC 24 satellites into approximately 900 km, 99 degree inclination orbits by CZ-4 boosters from the Taiyuan space center. The Fengyuan 1A spacecraft were designed to be comparable to existing 19467 international LEO meteorological and remote sensing systems, including APT transmissions in the 137 MHz band. The satellite structure and support systems were created by the Facts in Brief Shanghai Satellite Engineering and Research Center of the Launch Date: 1988-09- China Space Technology Institute, whereas the payload was 06 developed by the Shanghai Technical Physics Institute of the Launch Vehicle: Long Chinese Academy of Sciences. March 4 Launch Site: Taiyuan, Both satellites were experimental to test systems prior to the Peoples Republic of China launch of operational Feng Yun 1 spacecraft and were similar Mass: 750.0 kg in design, although technical characteristics differed. The height of the cubical spacecraft bus (1.4 m by 1.4 m base) of Feng Yun 1A was apparently increased from 1.2 m to nearly Funding Agency 1.8 m for Feng Yun 1B. Likewise, total spacecraft mass increased from 750 kg to about 880 kg. Both satellites were Chinese Meteorological powered by two solar arrays (about 3.5 m long each) with a Administration (Peoples combined rating of more than 800 W. Nickel- cadmium Republic of China) batteries were used for electrical power storage. Attitude control was maintained by a combination of nitrogen cold gas Discipline thrusters and reaction wheels, although both spacecraft suffered serious malfunctions in this system. Feng Yun 1A was Earth Science lost after only 38 days, but Feng Yun 1B operated for more than a year. Additional The Feng Yun 1 primary payload consisted of two Very High Information Resolution Scanning Radiometers (VHRSR) with a combined Launch/Orbital mass of 95 kg. These optical-mechanical scanners operated at information for Fengyun 360 rpm with a 20-cm diameter primary mirror. The five 1A spectral bands used were 0.58-0.68 um, 0.725-1.1 um, 0.48- 0.53 um, 053-0.58 um, and 10.5-12.5 um. The system swath Experiments on Fengyun was 2,860 km with a 1.08-km resolution in the High Resolution 1A Picture Transmission (HRPT) mode and 4-km resolution in the Automatic Picture Transmission (APT) mode. Data collections from Fengyun 1A
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Foton 4
Publications NSSDC ID: 1988-031A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Beginning in 1985 the USSR/CIS conducted annual unmanned Photon 4 space missions dedicated to materials science research. The 19043 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: 1988-04- 1985-1987 as Cosmos 1645, Cosmos 1744, and Cosmos 14 1841. Since 1988, the spacecraft have been officially Launch Vehicle: Soyuz designated as Photon. Launch Site: Plesetsk, U.S.S.R The 6,200-kg spacecraft was 6.2 m in length with a maximum Mass: 6200.0 kg diameter of 2.5 m and was divided into three major sections: the service/retro module, the payload capsule, and an Funding Agency equipment block. The 2.3 m diameter recoverable capsule handled a payload of up to 700 kg and a volume of 4.7 m Unknown (U.S.S.R) cubed. Electrical power was supplied entirely by storage batteries with 400 W average per day allocated to the payload (up to 700 W for 90 minutes each day). Mission durations for Discipline the 8 Photon flights to the end of 1992 were 13-16 days. Microgravity To minimize perturbation forces, thereby maximizing microgravity conditions, Photon spacecraft were placed in a Additional mildly eccentric orbit at 62.8 degrees inclination and were not Information maneuvered during the mission. Prior to 1991 the annual Photon missions had always been launched in April or May. Launch/Orbital Launches were performed by the Soyuz booster from the information for Foton 4 Plesetsk cosmodrome, and recoveries made in Kazakhstan in the primary manned recovery region northeast of the Baikonur Experiments on Foton 4 cosmodrome. Data collections from Foton 4
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Gorizont 15
Publications NSSDC ID: 1988-028A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Gorizont 15 was a Soviet geosynchronous communications 19017 satellite. It was launched to provide telephone, telegraph and fax communications services, in addition to relaying TV and radio broadcasts. It was stationed at 346 deg E. Facts in Brief Launch Date: 1988-03- The Gorizont spacecraft possessed an initial mass in excess of 31 2.1 metric tons and have demonstrated a lifetime of nearly 10 Launch years, although a 5-year service life was more common. The Vehicle: Proton-K 3-axis stabilized satellite was approximately 2 m in diameter Launch Site: Tyuratam and 5 m long with two large solar arrays capable of generating (Baikonur Cosmodrome), 1.3 kW of electrical power for the first 3 years. Seven separate U.S.S.R transmission antennas allowed a variety of reception patterns Mass: 2100.0 kg for both broad and localized terrestrial regions.
A typical Gorizont communications payload included six Funding Agency general purpose (TV, audio, facsimile) 6/4 GHz transponders (five 12.5 W and one 60 W), one Luch 14/11 GHz transponder Unknown (U.S.S.R) (15 W), and one Volna 1.6/1.5 GHz transponder (20 W). The Volna transponders were INMARSAT-compatible and were Discipline extensively used by the Russian merchant marine fleet via the primary GEO television rebroadcasting system, supporting all Communications five Federation time zones: Zone 1 from 140 deg E, Zone 2 from 90 deg E, Zone 3 from 80 deg E, Zone 4 from 53 deg E, and Zone 5 from 14 deg W. These transmissions were handled Additional by Orbita (12-m receiving antenna) and Moskva (2.5-m Information receiving antenna) ground stations in the 6/4 GHz band. The Launch/Orbital Moskva Globalnaya system was inaugurated in 1989 using 4- information for Gorizont m receiving antennas and serviced by Gorizonts at 96.5 deg E 15 and 11 deg W. Experiments on Gorizont 15
Data collections from Gorizont 15
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Gorizont 16
Publications NSSDC ID: 1988-071A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Gorizont 16 was a Soviet geosynchronous communications 19397 satellite. It was launched to provide telephone, telegraph and fax communications services, in addition to relaying TV and radio broadcasts. It was stationed at 80 deg E. Facts in Brief Launch Date: 1988-08- The Gorizont spacecraft possessed an initial mass in excess of 18 2.1 metric tons and have demonstrated a lifetime of nearly 10 Launch years, although a 5-year service life was more common. The Vehicle: Proton-K 3-axis stabilized satellite was approximately 2 m in diameter Launch Site: Tyuratam and 5 m long with two large solar arrays capable of generating (Baikonur Cosmodrome), 1.3 kW of electrical power for the first 3 years. Seven separate U.S.S.R transmission antennas allowed a variety of reception patterns Mass: 2100.0 kg for both broad and localized terrestrial regions.
A typical Gorizont communications payload included six Funding Agency general purpose (TV, audio, facsimile) 6/4 GHz transponders (five 12.5 W and one 60 W), one Luch 14/11 GHz transponder Unknown (U.S.S.R) (15 W), and one Volna 1.6/1.5 GHz transponder (20 W). The Volna transponders were INMARSAT-compatible and were Discipline extensively used by the Russian merchant marine fleet via the primary GEO television rebroadcasting system, supporting all Communications five Federation time zones: Zone 1 from 140 deg E, Zone 2 from 90 deg E, Zone 3 from 80 deg E, Zone 4 from 53 deg E, and Zone 5 from 14 deg W. These transmissions were handled Additional by Orbita (12-m receiving antenna) and Moskva (2.5-m Information receiving antenna) ground stations in the 6/4 GHz band. The Launch/Orbital Moskva Globalnaya system was inaugurated in 1989 using 4- information for Gorizont m receiving antennas and serviced by Gorizonts at 96.5 deg E 16 and 11 deg W. Experiments on Gorizont 16
Data collections from Gorizont 16
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel GSTAR 3
Publications NSSDC ID: 1988-081A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events GSTAR 3, a telecommunications satellite, was launched from Geostar R02 Kourou, French Guiana, for the United States. 19483
Facts in Brief
Launch Date: 1988-09- 08 Launch Vehicle: Ariane 3 Launch Site: Kourou, French Guiana Mass: 1271.5 kg
Funding Agency
GE American Communications, Inc. (United States)
Discipline
Communications
Additional Information
Launch/Orbital information for GSTAR 3
Experiments on GSTAR 3
Data collections from GSTAR 3
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Personnel INSAT 1C
Publications NSSDC ID: 1988-063A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events The INSAT-1C was the third spacecraft in the first generation Indian National Satellite Indian National Satellite system. The geostationary (at 94 deg 1C E), three-axis stabilized spacecraft was functionally identical to 19330 INSAT 1A and 1B, and was designed to provide combined telecommunications, direct TV broadcast, and meteorological service to India's civilian community over a 7-year-in-orbit life Facts in Brief span. The telecommunications package provided two-way, long-distance telephone circuits and direct radio and TV Launch Date: 1988-07- broadcasting to the remotest areas of India. The meteorology 21 package was comprised of a scanning very-high-resolution, Launch Vehicle: Ariane two-channel radiometer (VHRR) to provide full-frame, full-earth 3 coverage every 30 min. The visual channel (0.55-0.75 Launch Site: Kourou, micrometer) had a 2.75-km resolution while the IR channel French Guiana (10.5-12.5 micrometers) had an 11-km resolution. Using the Mass: 1152.0 kg INSAT TV capability, early warnings of impending disasters (i.e., floods, storms, etc.) can directly reach the civilian Funding Agency population, even in remote areas. The INSAT-1C also had a data channel for relaying meteorological, hydrological, and Indian Space Research oceanographic data from unattended land-based or ocean- Organization (India) based data collection and transmission platforms.
Disciplines
Communications Earth Science
Additional Information
Launch/Orbital information for INSAT 1C
Experiments on INSAT 1C
Data collections from INSAT 1C
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Personnel
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Name Role Original Affiliation E-mail Dr. P. P. Kale Project Manager India Department of Space Dr. J. P. Singh Program Manager ISRO Satellite Center
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Personnel INTELSAT 5A F-13
Publications NSSDC ID: 1988-040A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Intelsat 5A F-13 was a geostationary communications satellite 19121 launched from Kourou, French Guiana, for ITSO.
Facts in Brief
Launch Date: 1988-05- 17 Launch Vehicle: Ariane 2 Launch Site: Kourou, French Guiana Mass: 1978.0 kg
Funding Agency
International Telecommunications Satellite Corporation (International)
Discipline
Communications
Additional Information
Launch/Orbital information for INTELSAT 5A F-13
Experiments on INTELSAT 5A F-13
Data collections from INTELSAT 5A F-13
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Personnel IRS-1A
Publications NSSDC ID: 1988-021A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events The Indian Remote Sensing Satellite-1A (IRS-1A) was the first Indian Remoste Sensing of a series of semi-operational/operational remote sensing Satellite 1A satellites developed by India for land-based applications such 18960 as agriculture, forestry, geology, and hydrology. The three- axis-stabilized sun-synchronous satellite carried two linear imaging self-scanned sensors (LISS) which performed Facts in Brief "pushbroom" scanning in visible and near IR bands to acquire images of the earth. Local equatorial crossing time was fixed at Launch Date: 1988-03- around 10 a.m. The spacecraft platform, measuring 1.56 m x 17 1.66 m x 1.10 m, had the payload module attached on the top Launch Vehicle: Vostok and a deployable solar array stowed on either side. Attitude Launch Site: Tyuratam control was provided by four momentum wheels, two magnetic (Baikonur Cosmodrome), torques, and a thruster system. Together they gave an U.S.S.R estimated accuracy of better than plus or minus 0.10 deg in all Mass: 850.0 kg three axes. Further information can be found in "The Indian Remote Sensing Satellite: a Program Overview," Proc. Indian Funding Agency Acad. Sci, v. 6, pp. 313-336, 1983, by R. R. Navalgund and K. Kasturirangan. Indian Space Research Organization (India)
Discipline
Earth Science
Additional Information
Launch/Orbital information for IRS-1A
Experiments on IRS-1A
Data collections from IRS- 1A
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Personnel
Name Role Original Affiliation E-mail
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Mr. K. Navalgund Project Scientist Space Applications Center Dr. K. Kasturirangan General Contact ISRO Satellite Center [email protected] Dr. P. N. Jayaraman Project Scientist ISRO Satellite Center
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Personnel KH 11-9
Publications NSSDC ID: 1988-099A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events USA 33 was launched by the United States Department of USA 33 Defense. 19625
Facts in Brief
Launch Date: 1988-11- 06 Launch Vehicle: Titan 34D Launch Site: Vandenberg AFB, United States
Funding Agency
Department of Defense- Department of the Air Force (United States)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for KH 11-9
Experiments on KH 11-9
Data collections from KH 11-9
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Personnel Lacrosse 1
Publications NSSDC ID: 1988-106B Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Lacrosse 1 was a side-looking radar, all weather surveillance USA 34 satellite launched from the shuttle mission STS-27 for the US 19671 National Reconnaisance Office and the CIA. It was manufactured by Lockheed Martin Aeronautics, Denver and completed operations in March 1997. Facts in Brief
Launch Date: 1988-12- 02 Launch Vehicle: Shuttle Launch Site: Cape Canaveral, United States
Funding Agency
National Reconnaissance Office (United States)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for Lacrosse 1
Experiments on Lacrosse 1
Data collections from Lacrosse 1
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Meteor 2-17
Publications NSSDC ID: 1988-005A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Meteor 2-17 carried scientific instruments for continuing space 18820 research, radio systems for precise orbital measurements, and a radio telemetry system. It also carried equipment for obtaining global images of cloud cover and the underlying Facts in Brief surface in the visible and infrared bands of the spectrum using Launch Date: 1988-01- either the tape recording mode or direct transmission, and 30 radiometric equipment for continuous observations of fluxes of Launch penetrating radiation in the near-earth space. Vehicle: Tsiklon-3 Launch Site: Plesetsk, U.S.S.R Mass: 2750.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Earth Science
Additional Information
Launch/Orbital information for Meteor 2- 17
Experiments on Meteor 2- 17
Data collections from Meteor 2-17
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Personnel Meteor 3-2
Publications NSSDC ID: 1988-064A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Meteor 3-2 was launched by the USSR and carried complex 19336 optical and mechanical scanning, television and radiometric equipment; and instruments for geophysical exploration. Facts in Brief
Launch Date: 1988-07- 26 Launch Vehicle: Tsiklon-3 Launch Site: Plesetsk, U.S.S.R Mass: 2150.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Earth Science
Additional Information
Launch/Orbital information for Meteor 3-2
Experiments on Meteor 3-2
Data collections from Meteor 3-2
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Personnel Meteosat 3
Publications NSSDC ID: 1988-051A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Meteosat P2 was a refurbished prototype of Meteosat 2. In Meteosat-P2 general, the spacecraft design, instrumentation, and operation MPSATP2 were similar to SMS/GOES. The spin-stabilized, geostationary spacecraft carried (1) a visible-IR radiometer to provide high- 19215 quality, day/night cloud-cover data and to take radiance temperatures of the earth/atmosphere system; (2) a Facts in Brief meteorological data collection system to disseminate image data to user stations, to collect data from various earth-based Launch Date: 1988-06- platforms, and to relay data from polar-orbiting satellites; (3) a 15 LASSO retro-reflector; and (4) an SEM-2 electron Launch Vehicle: Ariane spectrometer, provided by LANL, to investigate the link 44LP between deep dielectric charging and the spacecraft anomalies Launch Site: Kourou, seen on Meteosat 1 and 2. The cylindrically shaped spacecraft French Guiana measured 210 cm in diameter and 430 cm in length, including Mass: 625.0 kg the apogee boost motor. The primary structural members were an equipment platform and a central tube. The radiometer telescope was mounted on the equipment platform and viewed Funding Agency the earth through a special aperture in the side of the European Meteorological spacecraft. A support structure extended radially out from the Satellite Agency central tube and was affixed to the solar panels, which formed (International) the outer walls of the spacecraft and provided the primary source of electrical power. Located in the annulus-shaped space between the central tube and the solar panels were Disciplines station-keeping and dynamics control equipment and batteries. Proper spacecraft attitude and spin rate (approximately parallel Engineering to the Earth's spin axis and approximately 100 rpm) were Earth Science maintained by jet thrusters mounted on the spacecraft and Space Physics activated by ground command. The spacecraft used both UHF- band and S-band frequencies in its telemetry and command systems. A lower power VHF transponder provided telemetry Additional and command during launch and then served as a backup for Information the primary subsystem once the spacecraft attained synchronous orbit. Launch/Orbital information for Meteosat 3
Experiments on Meteosat 3
Data collections from Meteosat 3
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Personnel
Name Role Original Affiliation E-mail Mr. J. Aasted Project Manager European Space Agency - Toulouse
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Personnel Molniya 1-71
Publications NSSDC ID: 1988-017A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Molniya 1/71 was a first-generation Russian communications 18946 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: 1988-03- to relay television programs and long-distance two-way 11 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: Tyuratam hermetically sealed cylinder with conical ends -- one end (Baikonur Cosmodrome), contained the orbital correcting engine and a system of U.S.S.R microjets, and the other end contained externally mounted Mass: 1800.0 kg solar and earth sensors. Inside the cylinder were (1) a high- sensitivity receiver and three 800-MHz 40-w transmitters (one operational and two in reserve), (2) telemetering devices that Funding Agency monitored equipment operation, (3) chemical batteries that were constantly recharged by solar cells, and (4) an electronic Unknown (U.S.S.R) computer that contorlled all equipment on board. Mounted around the central cylinder were six large solar battery panels Discipline and two directional, high-gain parabolic aerials, 180 deg apart. One of the aerials was directed continually toward the earth by Communications the highly sensitive earth sensors. The second aerial was held in reserve. Signals were transmitted in a fairly narrow beam ensuring a strong reception at the earth's surface. The satellite Additional received telemetry at 1000 MHz. Television service was Information provided in a frequency range of 3.4 to 4.1 GHz at 40 w. Launch/Orbital Molniya 1/71, whose cylindrical body was 3.4 m long and 1.6 m information for Molniya 1- in diameter, was much heavier than corresponding U.S. 71 COMSATS, and it had about 10 times the power output of the Early Bird COMSAT. In addition, it did not employ a Experiments on Molniya 1- geosynchronous equatorial orbit as have most U.S. COMSATs 71 because such an orbit would not provide coverage for areas north of 70 deg n latitude. Instead, the satellite was boosted Data collections from from a low-altitude parking orbit into a highly elliptical orbit with Molniya 1-71 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, Molniya 1/71 remained relatively staionary with respect to the Questions or comments earth below for nearly 8 of every 12 hr. By placing three or about this spacecraft can more Molniya 1 satellites in this type of orbit, spacing them be directed to: Coordinated suitably, and shifting their orbital planes relative to each other Request and User Support by 120 deg, a 24-hr/day communication system could be Office. obtained.
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Personnel Molniya 1-72
Publications NSSDC ID: 1988-022A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Molniya 1/72 was a first-generation Russian communications 18980 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: 1988-03- to relay television programs and long-distance two-way 17 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 U.S.S.R contained the orbital correcting engine and a system of Mass: 1800.0 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 (U.S.S.R) 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 1/72, whose cylindrical body was 3.4 m long and 1.6 m 72 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 72 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 1-72 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 1/72 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 1-73
Publications NSSDC ID: 1988-069A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Molniya 1/73 was a first-generation Russian communications 19377 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: 1988-08- to relay television programs and long-distance two-way 12 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 U.S.S.R contained the orbital correcting engine and a system of Mass: 1800.0 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 (U.S.S.R) 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 1/73, whose cylindrical body was 3.4 m long and 1.6 m 73 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 73 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 1-73 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 1/73 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 1-74
Publications NSSDC ID: 1988-115A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Molniya 1/74 was a first-generation Russian communications 19730 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: 1988-12- to relay television programs and long-distance two-way 28 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 U.S.S.R contained the orbital correcting engine and a system of Mass: 1800.0 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 (U.S.S.R) 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 1/74, whose cylindrical body was 3.4 m long and 1.6 m 74 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 74 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 1-74 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 1/74 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 3-32
Publications NSSDC ID: 1988-044A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events The Molniya-3 Soviet communications satellites were used to 19189 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: 1988-05- enhanced electrical power system and a communications 26 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 U.S.S.R 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- 32
Experiments on Molniya 3- 32
Data collections from Molniya 3-32
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Molniya 3-33
Publications NSSDC ID: 1988-090A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events The Molniya-3 Soviet communications satellites were used to 19541 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: 1988-09- enhanced electrical power system and a communications 29 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 U.S.S.R 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- 33
Experiments on Molniya 3- 33
Data collections from Molniya 3-33
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Molniya 3-34
Publications NSSDC ID: 1988-112A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events The Molniya-3 Soviet communications satellites were used to 19713 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: 1988-12- enhanced electrical power system and a communications 22 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 U.S.S.R 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- 34
Experiments on Molniya 3- 34
Data collections from Molniya 3-34
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Personnel NOAA 11
Publications NSSDC ID: 1988-089A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events NOAA 11 was a third-generation operational meteorological NOAA-H satellite for use in the National Operational Environmental 19531 Satellite System (NOESS) and for support of the Global Atmospheric Research Program (GARP) during 1978-84. The satellite design provided an economical and stable sun- Facts in Brief synchronous platform for advanced operational instruments to measure the earth's atmosphere, its surface and cloud cover, Launch Date: 1988-09- and the near-space environment. Primary sensors included (1) 24 an advanced very high resolution radiometer (AVHRR) for Launch Vehicle: Atlas observing daytime and nighttime global cloud cover, (2) a E TIROS operational vertical sounder (TOVS) for obtaining Launch temperature and water vapor profiles through the earth's Site: Vandenberg AFB, atmosphere, and (3) a solar backscatter ultraviolet United States spectrometer (SBUV/2) for providing ozone distributions in the Mass: 386.0 kg atmosphere. The secondary experiment was a data collection system (DCS), which processed and relayed to central data Funding Agencies acquisition stations the various meteorological data received from free-floating balloons and ocean buoys distributed around NASA-Office of Space the globe. A search and rescue (SAR) system was also carried Science Applications on NOAA-H to receive, process, and relay distress signals (United States) transmitted by beacons carried by civil aircraft and some NOAA National classes of marine vessels. The satellite was based upon the Environmental Satellite Block 5D spacecraft bus developed for the U.S. Air Force, and Service (United States) was capable of maintaining an earth-pointing accuracy of better than plus or minus 0.1 deg with a motion rate of less than 0.035 deg/s. Disciplines
Communications Earth Science Solar Physics
Additional Information
Launch/Orbital information for NOAA 11
Experiments on NOAA 11
Data collections from NOAA 11
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Office.
Personnel
Name Role Original Affiliation E-mail Mr. Gerald W. Project NASA Goddard Space Longanecker Manager Flight Center Mr. James R. Program NASA Headquarters [email protected] Greaves Manager
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Personnel NOSS 9
Publications NSSDC ID: 1988-078A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events This US Navy Ocean Surveillance Satellite (NOSS) was USA 32 launched from Vandenberg AFB aboard an Atlas E/F rocket. It Naval Ocean Surveillance placed a cluster of one primary satellite and three smaller sub- Satellite 9 satellites (that trailed along at distances of several hundred kilometers) into low polar orbit. This satellite array determined 19460 the location of radio and radars transmitters, using triangulation, and the identity of naval units, by analysis of the Facts in Brief operating frequencies and transmission patterns. Launch Date: 1988-09- In external appearance, the sub-satellites were reminiscent of 05 the Navy's Transit navigational satellites. The had gravity Launch Vehicle: Atlas gradient orientation booms 10-15 meters long. These ensured Launch that the side of the satellite body where the signal antennas Site: Vandenberg AFB, were mounted was constantly oriented toward the Earth. The United States satellites maintained an assigned position in a group at Mass: 1700.0 kg distances of 30 to 240 km one from the other by using on- board low-thrust engines. As a result of ground processing of direction-finding data on the signals from target emitters Funding Agency provided by a group of satellites, and also sequentially by Department of Defense- several groups of satellites, the coordinates, direction and Department of the Navy speed of travel were obtained. (United States)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for NOSS 9
Experiments on NOSS 9
Data collections from NOSS 9
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Personnel NOVA II
Publications NSSDC ID: 1988-052A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events NOVA 1 was an improved Transit satellite launched by NASA NNSS 30490 for the US Navy's operational navigation system. 19223
Facts in Brief
Launch Date: 1988-06- 16 Launch Vehicle: Scout Launch Site: Vandenberg AFB, United States Mass: 174.0 kg
Funding Agency
Department of Defense- Department of the Navy (United States)
NOVA II Discipline
Navigation & Global Positioning
Additional Information
Launch/Orbital information for NOVA II
Experiments on NOVA II
Data collections from NOVA II
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Ofeq 1
Publications NSSDC ID: 1988-087A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Ofeq 1 (Horizon 1) was an experimental satellite launched by Horizon 1 Israel to demonstrate its capability to launch small satellites. 19519 Launch was from a site in the Negev desert. The spacecraft operated successfully for nearly four months, until re-entry on January 14, 1989. Solar panels provided a power capability of Facts in Brief 246 watts, but the average power consumption of the spacecraft was 53 watts. Spin period was one second. Launch Date: 1988-09- Telemetry was in the S-band, at 2.5 kbits/sec. This launch on 19 a Shavit booster made Israel the eighth nation to launch a Launch Vehicle: Shavit satellite on its own rocket. Launch Site: Palmahim, Israel Mass: 157.0 kg
Funding Agency
Israeli Space Agency (Israel)
Discipline
Engineering
Additional Information
Launch/Orbital information for Ofeq 1
Experiments on Ofeq 1
Data collections from Ofeq 1
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Okean 1
Publications NSSDC ID: 1988-056A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events The Okean series of satellites were all-weather radar 19274 oceanographic systems primarily designed to monitor sea-ice conditions in the Arctic seas. The payload included a side- looking radar, a scanning microwave radiometer, a nadir- Facts in Brief viewing microwave spectrometer, optical scanners and a data Launch Date: 1988-07- collection platform. The spacecraft was a stepped cylindrical 05 pressurized bus 3 m high and 1.4 m diameter. It was 3-axis Launch stabilized (nadir pointing, aided by a gravity gradient boom), Vehicle: Tsiklon-3 had twin solar array spanning 4.82 m and an 11.8 m radar Launch Site: Plesetsk, antenna mounted on the Earth-facing base. A primary feature U.S.S.R of the Okean-series was direct Automatic Picture Transmission Mass: 1950.0 kg (APT) on 137.4 MHz of imagery to CIS APT stations as well as to foreign users. The on-board recorder had 6.5 minute capacity and permitted coverage and transmission of a 470 x Funding Agency 2750 km image by side-looking radar (SRL) and a 1930 x 2750 km image by the multispectral scanner during a pass over an Unknown (U.S.S.R) APT station. The SRL operated at 3.2 cm with a swath width of 450 km and ground resolution of 1200 x 1500 meters. The Discipline MSU-M visible/near-IR multispectral scanner operated at 0.5 - 0.6, 0.6 - 0.7, 0.7 - 0.8, and 0.8 - 1.1 microns with a swath Earth Science width of 1900 km and ground resolution of 1900 meters. The MSU-S visible/near-IR scanner operated at 0.6 - 0.7 and 0.8 - 1.1 microns with a swath width of 1100 km and a ground Additional resolution of 370 m. The MSU-SK operated at 0.8 - 1.1 Information microns with a swath width of 1150 km and ground resolution Launch/Orbital of 500 m. The non-scanning microwave instrument operated information for Okean 1 at a frequency of 3 cm with a ground resolution of 12 m along orbit and 6 m perpendicular to the orbit track. The Okean Experiments on Okean 1 payload was flown on Cosmos 1500, Cosmos 1602, Cosmos 1766, and Cosmos 1869 (radar failed), as well as Okean-1 Data collections from and Okean-2. See Karpov, A., "Hydrometeorological, Okean 1 Oceanographic and Earth-Resources Satellite Systems Operated by the U.S.S.R.", Adv. Space Res., Vol. 11, No. 3, pp. 183-190, 1991. 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 OSCAR 13
Publications NSSDC ID: 1988-051B Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Oscar 13 was launched from Kourou, French Guiana, for the AMSAT 3C United States. It was an international amateur radio satellite 19216 launched into geosynchronous orbit.
Facts in Brief
Launch Date: 1988-06- 15 Launch Vehicle: Ariane 44LP Launch Site: Kourou, French Guiana Mass: 144.0 kg
Funding Agency
Radio Amateur Satellite Corporation (International)
Discipline
Communications
Additional Information
Launch/Orbital information for OSCAR 13
Experiments on OSCAR 13
Data collections from OSCAR 13
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel PANAMSAT 1
Publications NSSDC ID: 1988-051C Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events PAS 1 was launched from Kourou, French Guiana, for the Pan American Satellite 1 United States. PAS 1 19217
Facts in Brief
Launch Date: 1988-06- 15 Launch Vehicle: Ariane 44LP Launch Site: Kourou, French Guiana Mass: 1220.0 kg
Funding Agency
Pan American Satellite (United States)
Discipline
Communications
Additional Information
Launch/Orbital information for PANAMSAT 1
Experiments on PANAMSAT 1
Data collections from PANAMSAT 1
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Phobos 1
Publications NSSDC ID: 1988-058A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Phobos 1, and its companion spacecraft Phobos 2, were the 19281 next-generation in the Venera-type planetary missions, succeeding those last used during the Vega 1 and 2 missions to comet P/Halley. The objectives of the Phobos missions were Facts in Brief to: (1) conduct studies of the interplanetary environment; (2) Launch Date: 1988-07- perform observations of the Sun; (3) characterize the plasma 07 environment in the Martian vicinity; (4) conduct surface and Launch atmospheric studies of Mars; and, (5) study the surface Vehicle: Proton-K composition of the Martian satellite Phobos. The main section Launch Site: Tyuratam of the spacecraft consisted of a pressurized toroidal electronics (Baikonur Cosmodrome), section surrounding a modular cylindrical experiment section. U.S.S.R Phobos 1 Below these were mounted four spherical tanks containing Mass: 6220.0 kg hydrazine for attitude control and, after the main propulsion module was to be jettisoned, orbit adjustment. A total of 28 thrusters (twenty-four 50 N thrusters and four 10 N thrusters) Funding Agency were mounted on the spherical tanks with additional thrusters mounted on the spacecraft body and solar panels. Attitude was Institut Kosmicheskich maintained through the use of a three-axis control system with Issledovaniy(Inst. of pointing maintained with sun and star sensors. Phobos 1 Cosmophysical operated nominally until an expected communications session Research) (U.S.S.R) on 2 September 1979 failed to occur. The failure of controllers to regain contact with the spacecraft was traced to an error in Disciplines the software uploaded on 29/30 August which had deactivated the attitude thrusters. This resulted in a loss of lock on the Sun, Planetary Science resulting in the spacecraft orienting the solar arrays away from Solar Physics the Sun, thus depleting the batteries. Space Physics
Additional Information
Launch/Orbital information for Phobos 1 Telecommunications information for Phobos 1
Experiments on Phobos 1
Data collections from Phobos 1
Questions or comments about this spacecraft can be directed to: Dr. Edwin V. Bell, II.
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Personnel
Name Role Original Affiliation E-mail Dr. Andrej I. Project Institut Kosmicheskich [email protected] Zakharov Scientist Issledovaniya (IKI)
Selected References
Sagdeev, R. Z., et al., The Phobos project: Scientific objectives and experimental methods, Sov. Sci. Rev. E. Astrophys. Space Phys., 6, Pt. 1, 1-60, Aug. 1988.
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Personnel Phobos 2
Publications NSSDC ID: 1988-059A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Phobos 2, and its companion spacecraft Phobos 1, were the 19287 next-generation in the Venera-type planetary missions, succeeding those last used during the Vega 1 and 2 missions to comet P/Halley. The objectives of the Phobos missions were Facts in Brief to: (1) conduct studies of the interplanetary environment; (2) Launch Date: 1988-07- perform observations of the Sun; (3) characterize the plasma 12 environment in the Martian vicinity; (4) conduct surface and Launch atmospheric studies of Mars; and, (5) study the surface Vehicle: Proton-K composition of the Martian satellite Phobos. Launch Site: Tyuratam (Baikonur Cosmodrome), The main section of the spacecraft consisted of a pressurized U.S.S.R Phobos 2 toroidal electronics section surrounding a modular cylindrical Mass: 2600.0 kg experiment section. Below these were mounted four spherical tanks containing hydrazine for attitude control and, once the main propulsion module had been jettisoned, orbit adjustment. Funding Agency A total of 28 thrusters (twenty-four 50 N thrusters and four 10 N thrusters) were mounted on the spherical tanks with Institut Kosmicheskich additional thrusters mounted on the spacecraft body and solar Issledovaniy(Inst. of panels. Attitude was maintained through the use of a three-axis Cosmophysical control system with pointing maintained with sun and star Research) (U.S.S.R) sensors. Disciplines Phobos 2 operated nominally throughout its cruise and Mars orbital insertion phases, gathering data on the Sun, Planetary Science interplanetary medium, Mars, and Phobos. Shortly before the Solar Physics final phase of the mission, during which the spacecraft was to approach within 50 m of Phobos' surface and release two Space Physics landers, one a mobile `hopper', the other a stationary platform, contact with Phobos 2 was lost. The mission ended when the Additional spacecraft signal failed to be successfully reacquired on 27 Information March 1989. The cause of the failure was determined to be a malfunction of the on-board computer. Launch/Orbital information for Phobos 2 Telecommunications information for Phobos 2
Experiments on Phobos 2
Data collections from Phobos 2
Questions or comments about this spacecraft can be directed to: Dr. Edwin V. Bell, II.
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Personnel
Name Role Original Affiliation E-mail Dr. Andrej I. Project Institut Kosmicheskich [email protected] Zakharov Scientist Issledovaniya (IKI)
Selected References
Sagdeev, R. Z., et al., The Phobos project: Scientific objectives and experimental methods, Sov. Sci. Rev. E. Astrophys. Space Phys., 6, Pt. 1, 1-60, Aug. 1988.
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DATOS DE LA MISIÓN:
Este proyecto estaba formado por dos naves idénticas, construidas por el Institut Kosmicheskich Issledovaniy (Instituto de Investigación Cosmofísica) de la Unión Soviética en cooperación con otros 14 países incluyendo Estados Unidos, Francia, Alemania Occidental y Suiza. El objetivo principal de la misión era conseguir el primer acercamiento y aterrizaje en una luna de otro planeta, en este caso la luna marciana Fobos. Cada nave además de sus propios instrumentos científicos llevaba abordo dos aterrizadores que tenían que descender a la superficie de Fobos para tomar imágenes, datos y muestras de la superficie.
El primer aterrizador era una plataforma de observación fija con instrumentos llamada 'DAS' y al segundo aterrizador se le denominó 'Hopper' (saltador), el cual debía posarse en un lugar de la luna, tomar datos y pegar un pequeño salto que lo llevaría hasta otra zona del satélite para seguir midiendo el campo de gravedad, la química y el campo magnético de cada lugar.
Ambas sondas fueron lanzadas en dos cohetes Proton-K y formaban una nueva generación mejorada de sondas tipo Venera para la exploración del Sistema Solar, muy similares a las usadas en las misiones Vega 1 y Vega 2 al cometa Halley. Otros objetivos de esta misión era realizar estudios del ambiente interplanetario, observaciones del Sol, estudiar el plasma en las cercanías de Marte y realizar estudios atmosféricos y de la superficie de Marte. La parte principal de la sonda consistía en un módulo presurizado con forma toroidal donde se encuentran los aparatos electrónicos, con un módulo cilíndrico con los experimentos en la parte superior. Debajo se encuentran cuatro tanques esféricos que contienen hidrazina para mantener la orientación de la nave y para ajustar la órbita una vez que el motor principal de propulsión ha sido expulsado. Un total de 28 toberas (24 de 50 Newtons de potencia y 4 de 10 N), fueron colocadas en los tanques esféricos, el cuerpo de la nave y los paneles solares. La orientación era mantenida a través de un sistema de control de tres ejes conectado a varios sensores de estrellas. La energía la obtenían a través de dos paneles solares.
La memoria para almacenar los datos en la nave llegaba a los 30 MB y eran transmitidos a la Tierra con una parabólica a la velocidad de 4 kbits/seg. Los aterrizadores estáticos podían transmitir los datos directamente a Tierra a la velocidad de entre 4 y 20 bits/seg. y eran recogidos por las antenas de 70m. de la Unión Soviética. Los datos del 'Hopper' se transmitían a través del orbitador.
Entre los instrumentos científicos destacaban el Sistema de Televisión llamado VSK, un espectrómetro infrarrojo, un espectrómetro de infrarrojo cercano, una cámara de imágenes termales, un magnetómetro, un espectrómetro de rayos gamma, un telescopio de rayos-X, detector de radiaciones, un altímetro por radar y por láser y por último el experimento por láser llamado 'Lima-D' consistente en vaporizar material de la superficie de Fobos para realizar análisis con los espectrómetros.
El sistema de imágenes VSK fue creado en colaboración de instituciones de la URSS, Bulgaria y Alemania del Este. Era capaz de tomar imágenes en tres bandas distintas del espectro y realizar análisis espectrales de las fotografías. Todos los datos eran procesados por un equipo internacional de la URSS, Bulgaria, Alemania, Finlandia, Gran Bretaña y los Estados Unidos.
La plataforma de observación fija 'DAS' llevaba abordo cámaras panorámicas en estéreo, sismómetro, magnetómetro, espectrómetro de rayos-X, detector de partículas alfa y penetrador para tomar muestras.
Phobos 1. Otros nombres: 1988-058A. Lanzamiento: 7 de julio de 1.988 a las 17:38:04 GMT. Masa seca en órbita: 2.600 kg.
La sonda Phobos 1 funcionó perfectamente hasta el día 2 de septiembre de 1.988, cuando en el transcurso de una sesión de comunicaciones con la nave, la conexión desapareció. Ningún intento posterior por contactar con la nave tuvo éxito y el fallo fue debido a un error en los comandos enviados a la nave los días 29 y 30 de agosto, en el que entre los miles de bits enviados se confundió un signo 'menos' con un sigo 'mas' y esto provocó la desactivación de las toberas encargadas de mantener la orientación. A raíz de esto, la nave perdió el contacto con el Sol en el sensor de estrellas y los paneles solares se quedaron sin electricidad, descargando las baterías.
Originalmente ambas sondas iban a llevar los mismos instrumentos, sin embargo debido a limitaciones de peso, algunos de ellos sólo viajaron en una de las naves. Phobos 1 llevaba 25 instrumentos, pero no llevaba el Hopper.
Phobos 2. Otros nombres: 1988-059A. Lanzamiento: 12 de julio de 1.988 a las 17:01:43 GMT. Masa seca en órbita: 2.600 kg.
La sonda funcionó con normalidad a lo largo de su viaje hasta la llegada a Marte y su fase de inserción orbital alrededor del planeta (el 29 de enero de 1.989), consiguiendo numerosos datos del Sol, el medio interplanetario, Marte y Fobos.
Justo antes de la fase final de la misión, cuando la nave debía de acercarse a sólo 50 metros de la superficie de Fobos y soltar dos aterrizadores, uno de ellos móvil y el otro una plataforma estacionaria, se perdió el contacto con la nave (27 de marzo de 1.989). Como causa de la pérdida se determinó un fallo en la computadora de la sonda.
Antes de llegar a Marte, la sonda tenía ya numerosos problemas. A finales de 1.988 la nave había perdido dos de los tres canales de televisión (del Sistema VSK) y los datos los mandaba por el transmisor de repuesto.
El experimento de plasma desarrollado en los Estados Unidos y Bulgaria estaba sobrecalentado continuamente y afectaba a otros equipos. En un total de 52 órbitas a Marte nos mandó un total de 37 fotografías. Los resultados científicos obtenidos no llegaron a completarse por lo que la misión no se puede considerar un éxito.
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Personnel PRC 22
Publications NSSDC ID: 1988-014A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events PRC 22 was launched March 7, 1988, by the People's STTW-2 Republic of China. The final position of this quasi-synchronous 18922 communications satellite was fixed at 87.5 deg east longitude above the equator in early April, 1988. Facts in Brief
Launch Date: 1988-03- 07 Launch Vehicle: Long March 3 Launch Site: Xichang, Peoples Republic of China Mass: 900.0 kg
Funding Agency
Unknown (Peoples Republic of China)
Discipline
Communications
Additional Information
Launch/Orbital information for PRC 22
Experiments on PRC 22
Data collections from PRC 22
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel PRC 23
Publications NSSDC ID: 1988-067A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events PRC 23, a retrievable satellite with experimental devices from FSW-1 2 The Federal Republic of Germany on board, conducted 19368 scientific exploration and technological experiments and then returned to earth. Facts in Brief
Launch Date: 1988-08- 05 Launch Vehicle: Long March 2C Launch Site: Jiuquan, Peoples Republic of China Mass: 1700.0 kg
Funding Agency
Unknown (Peoples Republic of China)
Discipline
Microgravity
Additional Information
Launch/Orbital information for PRC 23
Experiments on PRC 23
Data collections from PRC 23
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Personnel PRC 25
Publications NSSDC ID: 1988-111A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events PRC 25 was launched by the People's Republic of China. The STTW-3 quasi-geosynchronous telecommunications satellite was 19710 expected to be fixed over the equator at 110.5 deg east longitude. Facts in Brief
Launch Date: 1988-12- 22 Launch Vehicle: Long March 3 Launch Site: Xichang, Peoples Republic of China Mass: 900.0 kg
Funding Agency
Unknown (Peoples Republic of China)
Discipline
Communications
Additional Information
Launch/Orbital information for PRC 25
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Data collections from PRC 25
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Progress 34
Publications NSSDC ID: 1988-003A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Progress 34 carried expendable materials and various other 18795 loads for the orbit station Mir.
Facts in Brief
Launch Date: 1988-01- 20 Launch Vehicle: Proton-K Launch Site: Tyuratam (Baikonur Cosmodrome), U.S.S.R Mass: 7240.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Resupply/Refurbishment/Repair
Additional Information
Launch/Orbital information for Progress 34
Experiments on Progress 34
Data collections from Progress 34
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 4.0.14, 08 October 2010
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Personnel Progress 35
Publications NSSDC ID: 1988-024A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Progress 35 carried expendable materials and various other 18992 loads for the orbit station Mir.
Facts in Brief
Launch Date: 1988-03- 23 Launch Vehicle: Soyuz Launch Site: Tyuratam (Baikonur Cosmodrome), U.S.S.R Mass: 7240.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Resupply/Refurbishment/Repair
Additional Information
Launch/Orbital information for Progress 35
Experiments on Progress 35
Data collections from Progress 35
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Progress 36
Publications NSSDC ID: 1988-038A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Progress 36 carried expendable materials and various loads 19117 for the orbit station Mir.
Facts in Brief
Launch Date: 1988-05- 13 Launch Vehicle: Soyuz Launch Site: Tyuratam (Baikonur Cosmodrome), U.S.S.R Mass: 7240.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Resupply/Refurbishment/Repair
Additional Information
Launch/Orbital information for Progress 36
Experiments on Progress 36
Data collections from Progress 36
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Progress 37
Publications NSSDC ID: 1988-061A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Progress 37 carried expendable materials and various loads 19322 for the orbital station Mir.
Facts in Brief
Launch Date: 1988-07- 18 Launch Vehicle: Soyuz Launch Site: Tyuratam (Baikonur Cosmodrome), U.S.S.R Mass: 7240.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Resupply/Refurbishment/Repair
Additional Information
Launch/Orbital information for Progress 37
Experiments on Progress 37
Data collections from Progress 37
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Progress 38
Publications NSSDC ID: 1988-083A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Progress 38 was launched by the USSR and carried 19486 expendable material and various cargos for the orbital station Mir. Facts in Brief
Launch Date: 1988-09- 09 Launch Vehicle: Soyuz Launch Site: Tyuratam (Baikonur Cosmodrome), U.S.S.R Mass: 7240.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Resupply/Refurbishment/Repair
Additional Information
Launch/Orbital information for Progress 38
Experiments on Progress 38
Data collections from Progress 38
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Progress 39
Publications NSSDC ID: 1988-114A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Progress 39 was launched by the USSR and carried 19728 expendable material and various cargo for the orbital space station Mir. Facts in Brief
Launch Date: 1988-12- 25 Launch Vehicle: Soyuz Launch Site: Tyuratam (Baikonur Cosmodrome), U.S.S.R Mass: 7240.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Resupply/Refurbishment/Repair
Additional Information
Launch/Orbital information for Progress 39
Experiments on Progress 39
Data collections from Progress 39
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Raduga 22
Publications NSSDC ID: 1988-095A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Raduga 22 was a Soviet communications satellite launched 19596 from the Baikonur cosmodrome aboard a Proton 8K82K/Block DM rocket. It provided uninterrupted round the clock telephone and telegraph radio communications in the USSR and Facts in Brief simultaneous transmission of color and black and white USSR Launch Date: 1988-10- central television programs to stations in the Orbita network. It 20 was placed in a geostationary orbit at 35 deg E. Launch Vehicle: Proton Launch Site: Tyuratam (Baikonur Cosmodrome), U.S.S.R Mass: 1965.0 kg
Funding Agency
Unknown (U.S.S.R)
Discipline
Communications
Additional Information
Launch/Orbital information for Raduga 22
Experiments on Raduga 22
Data collections from Raduga 22
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Sakura-3A
Publications NSSDC ID: 1988-012A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events CS-3A (Communications Satellite-3A) was launched by the H-I CS-3A launch vehicle (H18F) from the Tanegashima Space Center of 18877 the National Space Development Agency of Japan. The satellite was nicknamed "Sakura 3-A". Facts in Brief
Launch Date: 1988-02- 19 Launch Vehicle: H-1 Launch Site: Tanegashima, Japan Mass: 550.0 kg
Funding Agency
National Space Development Agency (NASDA) (Japan)
Discipline
Communications
Additional Information
Launch/Orbital information for Sakura-3A
Experiments on Sakura-3A
Data collections from Sakura-3A
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Sakura-3B
Publications NSSDC ID: 1988-086A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events CS-3B (Communications Satellite 3B) was launched from the CS-3B Tanegashima Space Center, Japan. It was placed in an 19508 elliptical orbit and was moved at a later stage to a stationary orbit above the equator at 136 deg east longitude over the western part of New Guinea. Facts in Brief
Launch Date: 1988-09- 16 Launch Vehicle: H-1 Launch Site: Tanegashima, Japan Mass: 550.0 kg
Funding Agency
National Space Development Agency (NASDA) (Japan)
Discipline
Communications
Additional Information
Launch/Orbital information for Sakura-3B
Experiments on Sakura-3B
Data collections from Sakura-3B
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel San Marco-D/L
Publications NSSDC ID: 1988-026A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events The primary purpose of the San Marco-D/L Spacecraft was to 19013 explore the relationship between solar activity and thermosphere-ionosphere phenomena. The spacecraft had a planned lifetime of one year. The science investigations used Facts in Brief the following five flight sensors: a Drag Balance Instrument Launch Date: 1988-03- (DBI) for determining neutral density, a Wind and Temperature 25 Spectrometer (WATI), an Ion Velocity Instrument (IVI), an Launch Vehicle: Scout Airglow-Solar Spectrometer (ASSI), and an Electric Field Launch Site: San Marco Meter (EFI). The satellite was a 96.5 cm-diameter sphere with Platform, Kenya four 48 cm canted monopole telemetry antennas and three Mass: 273.0 kg orthogonal pairs of electric field probe sensors (one pair oriented along the spacecraft spin axis). An internal structural cylinder (26 cm diameter) extends slightly through the sphere Funding Agencies and was coincident with the satellite spin axis. The power supply consisted of a solar-cell array split into two sections, Centro Ricerche two rechargeable NiCd batteries, and associated circuitry. The Aerospaziali, Italy (Italy) satellite attitude data were provided by a triaxial NASA-Office of Space magnetometer, a horizon sensor, a digital sun sensor, and a Science Applications star tracker for calibration. A magnetic torquing system was (United States) used to control spin rate and spacecraft attitude. The spacecraft reentered on schedule on December 6, 1988. All instruments operated as planned, except WATI which failed to Disciplines respond to commands after 20 days (fuse failure). The Communications spacecraft performed nominally throughout its lifetime. Final data were acquired at 150 Km during re-entry. Earth Science Solar Physics Space Physics
Additional Information
Launch/Orbital information for San Marco-D/L PDMP information for San Marco-D/L Telecommunications information for San Marco-D/L
Experiments on San Marco-D/L
Data collections from San Marco-D/L
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Questions or comments about this spacecraft can be directed to: Dr. Dieter K. Bilitza.
Personnel
Name Role Original Affiliation E-mail Mr. Ronald E. Adkins Project Manager NASA Goddard Space Flight Center Dr. Nelson W. Spencer Project Scientist NASA Goddard Space Flight Center Dr. M. Diruscio General Contact Universita degli Studi di Roma
Other Sources of San Marco D/L Data/Information
San Marco D/L Project page
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Personnel SBS 5
Publications NSSDC ID: 1988-081B Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events SBS 5, a telecommunications satellite, was launched from Satellite Business Kourou, French Guiana, for the United States. Systems 5 19484
Facts in Brief
Launch Date: 1988-09- 08 Launch Vehicle: Ariane 3 Launch Site: Kourou, French Guiana Mass: 1239.0 kg
Funding Agency
Pan American Satellite (United States)
Discipline
Communications
Additional Information
Launch/Orbital information for SBS 5
Experiments on SBS 5
Data collections from SBS 5
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Skynet 4B
Publications NSSDC ID: 1988-109A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events SKYNET 4B was a British military telecommunications satellite 19687 launched from Kourou, French Guiana.
Facts in Brief
Launch Date: 1988-12- 11 Launch Vehicle: Ariane 44LP Launch Site: Kourou, French Guiana Mass: 1429.1 kg
Funding Agency
Ministry of Defence, UK (United Kingdom)
Discipline
Communications
Additional Information
Launch/Orbital information for Skynet 4B
Experiments on Skynet 4B
Data collections from Skynet 4B
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Soyuz TM- 5
Publications NSSDC ID: 1988-048A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events The Soyuz TM-5 flight program provided for 46 projects 19204 involving astrophysical experiments, remote probing of the earth's surface, and studies in space biology and medicine. It carried cosmonauts Anatoliy Solovev, Viktor Savinykh, and Facts in Brief Aleksandr Aleksandrov and docked with MIR on June 9, 1988. Launch Date: 1988-06- Designed and manufactured by RKK Energiya, the Soyuz TM 07 was capable of carrying three cosmonauts and had a gross Launch Vehicle: Soyuz weight of just over seven metric tons, a length of seven Launch Site: Tyuratam meters, and a maximum diameter of 2.7 m. The spacecraft (Baikonur Cosmodrome), consisted of three main sections: the orbital module, the U.S.S.R command and reentry module, and the service module. Two Mass: 7000.0 kg solar arrays (10.6 m span) provided electrical power for the typical 50-hour journey to Mir and could be interconnected with the space station's electrical system to furnish additional 1.3 Funding Agency kW. The nominal flight time for Soyuz TM spaceship was 5-6 months. Unknown (U.S.S.R)
Discipline
Human Crew
Additional Information
Launch/Orbital information for Soyuz TM- 5
Experiments on Soyuz TM- 5
Data collections from Soyuz TM- 5
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: 07.06.1988 Launch time: 14:03 UT Launch site: Baikonur Launch pad: 1 Altitude: 350 km Inclination: 51,6° Landing date: 17.06.1988 Landing time: 10:13 UT Landing site: 202 km SE of Dzheskaskan
Crew
No. Surname Given name Job
1 Soloviyov Anatoli Yakovlevich Commander
2 Savinykh Viktor Petrovich Flight Engineer
3 Alexandrov Alexandr Panayatov "Sasha" Research Cosmonaut
Flight Launch from Baikonur; landing 202 km southeast of Dzheskaskan; docking on MIR-Quant- Soyuz TM-4-complex; conducting joint scientific work with the third resident crew.
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Personnel Soyuz TM- 6
Publications NSSDC ID: 1988-075A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Soyuz TM-6 carried cosmonauts Vladimir Lyakhov, Physician 19443 Valeriy Polyakov, and Afghan Research Cosmonaut Abdul Ahad Mohmand to a docking with the MIR orbital station where they performed several joint scientific studies. Facts in Brief Launch Date: 1988-08- Designed and manufactured by RKK Energiya, the Soyuz TM 29 was capable of carrying three cosmonauts and had a gross Launch Vehicle: Soyuz weight of just over seven metric tons, a length of seven Launch Site: Tyuratam meters, and a maximum diameter of 2.7 m. The spacecraft (Baikonur Cosmodrome), consisted of three main sections: the orbital module, the U.S.S.R command and reentry module, and the service module. Two Mass: 7070.0 kg solar arrays (10.6 m span) provided electrical power for the typical 50-hour journey to Mir and could be interconnected with the space station's electrical system to furnish additional 1.3 Funding Agency kW. The nominal flight time for Soyuz TM spaceship was 5-6 months. Unknown (U.S.S.R)
Discipline
Human Crew
Additional Information
Launch/Orbital information for Soyuz TM- 6
Experiments on Soyuz TM- 6
Data collections from Soyuz TM- 6
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: 29.08.1988 Launch time: 04:23 UT Launch site: Baikonur Launch pad: 1 Altitude: 350 km Inclination: 51,6° Landing date: 07.09.1988 Landing time: 00:49 UT Landing site: 160 km SE of Dzheskasgan
Crew
No. Surname Given name Job
1 Lyakhov Vladimir Afanasiyevich Commander
2 Polyakov Valeri Vladimirovich Research Doctor
3 Mohmand Abdul Ahad "Abdulah" Research Cosmonaut
Flight Launch from Baikonur; landing with Soyuz TM-5-spacecraft 160 km southeast of Dzheskasgan; docking on MIR-Quant-Soyuz TM-5; scientific work with the third resident crew; Polyakov stayed on board and became member of the third resident crew; landing at third attempt because of a computer error.
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Personnel Soyuz TM- 7
Publications NSSDC ID: 1988-104A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Soyuz TM-7 was launched by the USSR and carried a French- 19660 Soviet crew. The flight program provided for the craft's linkup with the orbital complex Mir, and joint scientific studies and experiments with the cosmonauts on board. Designed and Facts in Brief manufactured by RKK Energiya, the Soyuz TM was capable of Launch Date: 1988-11- carrying three cosmonauts and had a gross weight of just over 26 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) U.S.S.R provided electrical power for the typical 50-hour journey to Mir Mass: 7000.0 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)
Discipline
Human Crew
Additional Information
Launch/Orbital information for Soyuz TM- 7
Experiments on Soyuz TM- 7
Data collections from Soyuz TM- 7
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: 26.11.1988 Launch time: 15:49 UT Launch site: Baikonur Launch pad: 1 Altitude: 350 km Inclination: 51,6° Landing date: 27.04.1989 Landing time: 02:57 UT Landing site: 140 km NE of Dzhezkasgan
Crew
No. Surname Given name Job
1 Volkov Aleksandr Aleksandrovich Commander
2 Krikalyov Sergei Konstantinovich Flight Engineer
3 Chrétien Jean-Loup Jacques Marie Research Cosmonaut
Flight Launch from Baikonur; landing 140 km northeast of Dzhezkasgan.
Second joined mission USSR - France; docking on MIR-Quant-complex; scientific work with third resident crew; Volkov and Krikalyov together with Polyakov became the fourth resident crew; EVA by Volkov and Chrétien on 09.12.1988 (5h 57m), installing the French ERA experimental deployable structure and a panel of material samples; Chrétien became the first non-American and non-Soviet cosmonaut to perform a spacewalk. Photos / Drawings
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Personnel Spacenet 3
Publications NSSDC ID: 1988-018A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Spacenet 3-R was launched from Kourou, French Guiana, on Geostar R01 an Ariane 3 launch vehicle, for the United States. 18951
Facts in Brief
Launch Date: 1988-03- 11 Launch Vehicle: Ariane 3 Launch Site: Kourou, French Guiana Mass: 1216.8 kg
Funding Agency
GE American Communications, Inc. (United States)
Discipline
Communications
Additional Information
Launch/Orbital information for Spacenet 3
Experiments on Spacenet 3
Data collections from Spacenet 3
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel STS 26
Publications NSSDC ID: 1988-091A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events STS-26 was launched from the Kennedy Space Center 19547 utilizing the Shuttle vehicle Discovery. The primary objective of the mission was to deploy the TDRS-C, and to conduct seven mid-deck experiments that were part of NASA's microgravity Facts in Brief science and applications program. Launch Date: 1988-09- 29 This mission marked resumption of Shuttle flights after 1986 Launch 51-L accident. The primary payload, NASA Tracking and Data Vehicle: Shuttle Relay Satellite-3 (TDRS-3) attached to an Inertial Upper Stage Launch Site: Cape (IUS), became second TDRS deployed. After deployment, IUS Canaveral, United States propelled satellite to geosynchronous orbit. Secondary Mass: 21082.0 kg payloads: Physical Vapor Transport of Organic Solids (PVTOS); Protein Crystal Growth (PCG); Infrared Communications Flight Experiment (IRCFE); Aggregation of Funding Agency Red Blood Cells (ARC); Isoelectric Focusing Experiment (IFE); Mesoscale Lightning Experiment (MLE); Phase Partitioning NASA-Office of Space STS 26 Experiment (PPE); Earth-Limb Radiance Experiment (ELRAD); Flight (United States) Automated Directional Solidification Furnace (ADSF); and two Shuttle Student Involvement Program (SSIP) experiments. Discipline Orbiter Experiments Autonomous Supporting Instrumentation System-1 (OASIS-1) recorded variety of environmental Human Crew measurements during various inflight phases of orbiter.
The Ku-band antenna in the payload bay was deployed; Additional however, a dish antenna command and actual telemetry did Information not correspond. Also, the orbiter cabin Flash Evaporator Launch/Orbital System iced up, raising crew cabin temperature to mid-80s. information for STS 26
Experiments on STS 26
Data collections from STS 26
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
Related Information/Data at NSSDC
TDRS-C
Other Sources of STS 26 Information/Data
STS 26 information (NASA KSC) http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1988-091A[19/02/2011 23:21:59] NASA - NSSDC - Spacecraft - Details
STS 26 Press Release images (NASA JSC)
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Personnel STS 27
Publications NSSDC ID: 1988-106A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events STS-27 (Space Transportation System-27) was launched from 19670 the Kennedy Space Center utilizing the Shuttle vehicle Atlantis. It carried a five-member All were military personnel, and three were veterans of previous Shuttle flights. STS-27 Mission Facts in Brief Commander Robert L. Gibson (Cdr., USN) was pilot on STS Launch Date: 1988-12- 41-B in February 1984 and commander on 61-C in January 02 1986. Mission Specialists Richard M. Mullane (Col., USAF) Launch and Jerry L. Ross (Lt. Col., USAF) flew on 41-D in August Vehicle: Shuttle 1984 and 61-B in November 1985, respectively. STS-27 will Launch Site: Cape be the first space flight for Pilot Guy S. Gardner (Lt. Col., Canaveral, United States USAF) and Mission Specialist William M. Shepherd (Cdr., USN). Funding Agencies
Department of Defense (United States) NASA-Office of Space Flight (United States)
Discipline
Human Crew
Additional Information
Launch/Orbital information for STS 27
Experiments on STS 27
Data collections from STS 27
Questions or comments about this spacecraft can be directed to: Dr. H. Kent Hills.
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Personnel TDF 1
Publications NSSDC ID: 1988-098A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events TDF 1, a French telecommunications satellite, was launched 19621 from Kourou, French Guiana.
Facts in Brief
Launch Date: 1988-10- 28 Launch Vehicle: Ariane 2 Launch Site: Kourou, French Guiana Mass: 2076.7 kg
Funding Agency
European Telecommunications Satellite Consortium (France)
Discipline
Communications
Additional Information
Launch/Orbital information for TDF 1
Experiments on TDF 1
Data collections from TDF 1
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel TDRS-C
Publications NSSDC ID: 1988-091B Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events TDRS-C was the second successful launch of the Tracking TDRS 3 and Data Relay Satellite series. TDRS-C was used in Tracking and Data Relay combination with other TDRS spacecraft and a ground Satellite 3 communications system to form the Tracking and Data Relay Satellite System (TDRSS). 19548
The objective of the TDRSS program is to provide and Facts in Brief maintain improved tracking and data acquisition services to spacecraft in low-Earth orbit. In order to fulfill this objective, Launch Date: 1988-09- TDRSS requires at least two fully operational TDRS in orbit 29 with one or more additional spacecraft serving as system Launch spares. Vehicle: Shuttle TDRS-C Launch Site: Cape Each TDRS is a three-axis, momentum-biased satellite. The Canaveral, United States bus section of the spacecraft is hexagonal with an approximate Mass: 2224.9 kg diameter of 3 m. Power is provided by two opposing, three- Nominal section solar array panels, 4.0 x 3.8 m in dimension, at the end Power: 1700.0 W of 3.25 m booms. Perpendicular to the solar arrays are the two 4.9 m diameter, K- and S-band, single-access (SA) antennae. With the solar panels and SA antennae deployed, TDRS Funding Agency measures 17.3 x 14.2 m. NASA-Office of Tracking and Data Acquisition TDRS is comprised of three functional modules: payload, (United States) spacecraft, and antenna. The payload module consists of two single-access compartments, the multiple access antenna platform, and a main payload module. The main payload Discipline module has six panels which form an integral part of the main bus structure and house the principle elements of the TDRS Communications payload. The spacecraft module contains the thermal control, electrical power, attitude control, propulsion, and tracking, Additional telemetry, and command systems. The antenna module Information consists of the two SA dish antennae, the 2.0 m K-band Space-to-Ground Link (SGL) antenna, and, on the bus of the Launch/Orbital spacecraft, the 30 helical element, multiple access (MA) information for TDRS-C antenna array, a C-band antenna, and an S-band omnidirectional SGL antenna. Experiments on TDRS-C
Data collections from TDRS-C
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. George Q. Clark Project Manager NASA Goddard Space Flight Center
Related Information/Data at NSSDC
NSSDC TDRS page STS 26
Other Sources of TDRS Information/Data
TDRS program
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Personnel TELECOM 1C
Publications NSSDC ID: 1988-018B Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Telecom-1C was launched from Kourou, French Guiana on an 18952 Ariane 3 launch vehicle, for France.
Facts in Brief
Launch Date: 1988-03- 11 Launch Vehicle: Ariane 3 Launch Site: Kourou, French Guiana Mass: 690.0 kg
Funding Agency
France Telecom (France)
Discipline
Communications
Additional Information
Launch/Orbital information for TELECOM 1C
Experiments on TELECOM 1C
Data collections from TELECOM 1C
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Transit-O 23
Publications NSSDC ID: 1988-033A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Transit-O 23 was a US Navy navigation satellite launched by a NNSS 30230 Scout G rocket. Transit, one of the first operational satellite OSCAR(NAV) 23 systems, was also know as the Navy Navigation Satellite (NNS). 19070
The Transit spacecraft were developed for updating the inertial Facts in Brief navigation systems on board US Navy Polaris submarines, and later for civilian use. Transit receivers used the known Launch Date: 1988-04- characteristics of the satellite's orbit, measured the Doppler 26 shift of the satellite's radio signal, and thereby calculated the Launch Vehicle: Scout receivers position on the earth. As a single spacecraft travelled Launch overhead, the user measured the Doppler shift over a 15 Site: Vandenberg AFB, minute period by receiving timing marks and satellite orbital United States information on two separate frequencies, 149.99 and 399.97 Mass: 64.0 kg MHz. These signals were corrected for ionospheric refraction and the information was then fed into the users navigation system. Funding Agency Department of Defense- Individual Transit satellites operated for over 10 years. Department of the Navy Technical break- throughs during the program included gravity (United States) gradient stabilization, the use of radio-isotope thermoelectic generators (RTG), and navigation satellite technologies later used in the GPS system. Transit was superseded by the Discipline Navstar global positioning system. The use of the satellites for navigation was discontinued at the end of 1996 but the Navigation & Global satellites continued transmitting and became the Navy Positioning Ionospheric Monitoring System (NIMS). Additional Information
Launch/Orbital information for Transit-O 23
Experiments on Transit-O 23
Data collections from Transit-O 23
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Transit-O 25
Publications NSSDC ID: 1988-074A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Transit-O 25 was a US Navy navigation satellite launched by a OSCAR(NAV) 25 Scout G rocket. Transit, one of the first operational satellite 19419 systems, was also know as the Navy Navigation Satellite (NNS). Facts in Brief The Transit spacecraft were developed for updating the inertial navigation systems on board US Navy Polaris submarines, and Launch Date: 1988-08- later for civilian use. Transit receivers used the known 25 characteristics of the satellite's orbit, measured the Doppler Launch Vehicle: Scout shift of the satellite's radio signal, and thereby calculated the Launch receivers position on the earth. As a single spacecraft travelled Site: Vandenberg AFB, overhead, the user measured the Doppler shift over a 15 United States minute period by receiving timing marks and satellite orbital Mass: 59.0 kg information on two separate frequencies, 149.99 and 399.97 MHz. These signals were corrected for ionospheric refraction Funding Agency and the information was then fed into the users navigation system. Department of Defense- Department of the Navy Individual Transit satellites operated for over 10 years. (United States) Technical break- throughs during the program included gravity gradient stabilization, the use of radio-isotope thermoelectic generators (RTG), and navigation satellite technologies later Discipline used in the GPS system. Transit was superseded by the Navigation & Global Navstar global positioning system. The use of the satellites for Positioning navigation was discontinued at the end of 1996 but the satellites continued transmitting and became the Navy Ionospheric Monitoring System (NIMS). Additional Information
Launch/Orbital information for Transit-O 25
Experiments on Transit-O 25
Data collections from Transit-O 25
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Transit-O 31
Publications NSSDC ID: 1988-074B Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Transit-O 31 was a US Navy navigation satellite launched by a NNSS 30310 Scout G rocket. Transit, one of the first operational satellite OSCAR(NAV) 31 systems, was also known as the Navy Navigation Satellite (NNS). 19420
The Transit spacecraft were developed for updating the inertial Facts in Brief navigation systems on board US Navy Polaris submarines, and later for civilian use. Transit receivers used the known Launch Date: 1988-08- characteristics of the satellite's orbit, measured the Doppler 25 shift of the satellite's radio signal, and thereby calculated the Launch Vehicle: Scout receivers position on the earth. As a single spacecraft travelled Launch overhead, the user measured the Doppler shift over a 15 Site: Vandenberg AFB, minute period by receiving timing marks and satellite orbital United States information on two separate frequencies, 149.99 and 399.97 Mass: 59.0 kg MHz. These signals were corrected for ionospheric refraction and the information was then fed into the users navigation system. Funding Agency Department of Defense- Individual Transit satellites operated for over 10 years. Department of the Navy Technical break- throughs during the program included gravity (United States) gradient stabilization, the use of radio-isotope thermoelectic generators (RTG), and navigation satellite technologies later used in the GPS system. Transit was superseded by the Discipline Navstar global positioning system. The use of the satellites for navigation was discontinued at the end of 1996 but the Navigation & Global satellites continued transmitting and became the Navy Positioning Ionospheric Monitoring System (NIMS). Additional Information
Launch/Orbital information for Transit-O 31
Experiments on Transit-O 31
Data collections from Transit-O 31
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel Transit-O 32
Publications NSSDC ID: 1988-033B Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events Transit-O 32 was a US Navy navigation satellite launched by a OSCAR(NAV) 32 Scout G rocket. Transit, one of the first operational satellite NNSS 30320 systems, was also known as the Navy Navigation Satellite (NNS). 19071
The Transit spacecraft were developed for updating the inertial Facts in Brief navigation systems on board US Navy Polaris submarines, and later for civilian use. Transit receivers used the known Launch Date: 1988-04- characteristics of the satellite's orbit, measured the Doppler 26 shift of the satellite's radio signal, and thereby calculated the Launch Vehicle: Scout receivers position on the earth. As a single spacecraft travelled Launch overhead, the user measured the Doppler shift over a 15 Site: Vandenberg AFB, minute period by receiving timing marks and satellite orbital United States information on two separate frequencies, 149.99 and 399.97 Mass: 64.0 kg MHz. These signals were corrected for ionospheric refraction and the information was then fed into the users navigation system. Funding Agency Department of Defense- Individual Transit satellites operated for over 10 years. Department of the Navy Technical break- throughs during the program included gravity (United States) gradient stabilization, the use of radio-isotope thermoelectic generators (RTG), and navigation satellite technologies later used in the GPS system. Transit was superseded by the Discipline Navstar global positioning system. The use of the satellites for navigation was discontinued at the end of 1996 but the Navigation & Global satellites continued transmitting and became the Navy Positioning Ionospheric Monitoring System (NIMS). Additional Information
Launch/Orbital information for Transit-O 32
Experiments on Transit-O 32
Data collections from Transit-O 32
Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.
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Personnel USA 30
Publications NSSDC ID: 1988-008A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events USA 30 was launched by the United States Department of 18847 Defense.
Facts in Brief
Launch Date: 1988-02- 08 Launch Vehicle: Delta 3924 Launch Site: Cape Canaveral, United States Mass: 6000.0 kg
Funding Agency
Unknown (United States)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for USA 30
Experiments on USA 30
Data collections from USA 30
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 4.0.14, 08 October 2010
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Personnel USA 31
Publications NSSDC ID: 1988-077A Maps Description Alternate Names New/Updated Data
Lunar/Planetary Events USA 31 was launched by the United States Department of 19458 Defense.
Facts in Brief
Launch Date: 1988-09- 02 Launch Vehicle: Titan 34D Launch Site: Cape Canaveral, United States Mass: 1045.0 kg
Funding Agency
Department of Defense (United States)
Discipline
Surveillance and Other Military
Additional Information
Launch/Orbital information for USA 31
Experiments on USA 31
Data collections from USA 31
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 4.0.14, 08 October 2010
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1988-077A[19/02/2011 23:28:31]