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Article Number: 17F15. Code Name: Globus. Class: Communications. Nation: USSR. Manufacturer: NPO PM.
The Raduga-1 geosynchronous communications satellite was to have been the basis for the YeSSS-2 second generation Unified Satellite Communication System. Phase 1 of the system was to have consisted of three Raduga-1 spacecraft. The Raduga-1 was capable of communication not just with fixed earth stations, but mobile platforms as wel. It was equipped with the Tor C-band transponder, working at 20, 42, and 44 GHz. Communications satellite - geosynchronous. Maintenance of telephone and telegraph radio communications. Although a later generation system, Raduga-1 still used the KAUR-3 spacecraft bus. This was 3-axis stabilised using liquid propellant micro-engines to within 0.25 degrees of the earth's centre. The single-unit body was equipped with solar panels, and active liquid-gas phase-change thermoregulation system, and a corrective engine unit for making orbital adjustments. 25 square metres of solar panels provided 1280 W of power.
Total Mass: 2,000 kg.
22 June 1989
Raduga 1-1 Launch Site: Baikonur . Launch Vehicle: Proton 8K82K / 11S861. Mass: 2,000 kg. Perigee: 35,781 km. Apogee: 35,796 km. Inclination: 2.5 deg.
Stationed at 49 deg E; first launch of alternate Raduga design. Maintenance of telephone and telegraph radio communications.
27 December 1990
Raduga 1-2 Launch Site: Baikonur . Launch Vehicle: Proton 8K82K / 11S861. Mass: 2,000 kg. Perigee: 35,781 km. Apogee: 35,798 km. Inclination: 1.0 deg.
Stationed at 49 deg E; second launch of alternate Raduga design. Further expansion of the long-range telephone and telegraph radio-communications system in the territory of the USSR.
05 February 1994
Raduga 1-3 Launch Site: Baikonur . Launch Vehicle: Proton 8K82K / 11S861. Mass: 2,000 kg. Perigee: 36,513 km. Apogee: 36,513 km. Inclination: 1.4 deg.
Stationed at 48 deg E; third launch of alternate Raduga design. Extension of the telephone and telegraph radio communications system on the territory of the Russian Federation.
28 February 1999
Raduga-1 Launch Site: Baikonur . Launch Vehicle: Proton 8K82K / 11S861. Perigee: 35,778 km. Apogee: 35,794 km. Inclination: 1.2 deg.
Geosynchronous communications satellite, stationed at 35 deg E.
28 August 2000
Raduga-1 Launch Site: Baikonur . Launch Vehicle: Proton 8K82K / 11S861. Perigee: 35,765 km. Apogee: 35,797 km. Inclination: 1.2 deg.
Raduga-1 military communications satellite initially named Cosmos 2372 by the RVSN press service. Stationed at 50 deg E.
- 2 - McDowell, Jonathan, The United Nations Registry of Space Objects, Harvard University, 1997. HTML when accessed: http://hea-www.harvard.edu/QEDT/jcm/space/un/un.html
- 6 - JPL Mission and Spacecraft Library, Jet Propulsion Laboratory, 1997. HTML when accessed: http://msl.jpl.nasa.gov/home.html
- 67 - Kaesmann, Ferdinand, et. al., Journal of the British Interplanetary Society, "Proton - Development of A Russian Launch Vehicle", 1998, Volume 51, page 3.
- 102 - Voevodin, Sergey A, VSA072 - Space Apparatus, "Sergey A. Voevodin's Reports", . HTML when accessed: http://www.mcs.net/~rusaerog/sergeyv/VSA.html
- 449 - Golotyuk, S, Novosti kosmonavtiki, "Sputnikostroiteli s beregov Yeniseya", No. 10, 1999, p. 64.
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Last update 12 March 2001.
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