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astronautix.com Intelsat 5


Class: Communications. Nation: International. Agency: ITSO, Inmarsat. Manufacturer: Ford Aerospace.

The last five of the nine spacecraft in this block carry a maritime mobile payload (seven additional transponders) for lease by Inmarsat. Spacecraft: 3-axis stabilised to 0.5 deg using momentum wheels. Hydrazine propulsion system. Passive thermal control. Dual solar arrays provide 1800 W BOL, NiCd or NiH batteries. Payload: 21 C-Band and 4 Ku-Band transponders.12000 voice circuits and 2 TV channels.
Financial/Operational:
5f series


Specification

Design Life: 7 years. Total Length: 2.0 m. Maximum Diameter: 1.8 m. Total Mass: 2,000 kg.


Intelsat 5 Chronology


06 December 1980 Intelsat 5 F-2 Program: Intelsat. Launch Site: Cape Canaveral . Launch Vehicle: Atlas Centaur SLV-3D. Mass: 2,000 kg. Perigee: 35,769 km. Apogee: 35,804 km. Inclination: 4.6 deg.

Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle put payload into geosynchronous transfer orbit


23 May 1981 Intelsat 5 F-1 Program: Intelsat. Launch Site: Cape Canaveral . Launch Vehicle: Atlas Centaur SLV-3D. Mass: 1,928 kg. Perigee: 35,772 km. Apogee: 35,804 km. Inclination: 5.1 deg.

Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle put payload into geosynchronous transfer orbit


15 December 1981 Intelsat 5 F-3 Program: Intelsat. Launch Site: Cape Canaveral . Launch Vehicle: Atlas Centaur SLV-3D. Mass: 1,870 kg. Perigee: 35,770 km. Apogee: 35,802 km. Inclination: 4.1 deg.
05 March 1982 Intelsat 5 F-4 Program: Intelsat. Launch Site: Cape Canaveral . Launch Vehicle: Atlas Centaur SLV-3D. Mass: 1,928 kg. Perigee: 35,776 km. Apogee: 35,798 km. Inclination: 4.1 deg.

Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle put payload into geosynchronous transfer orbit


28 September 1982 Intelsat 5 F-5 Program: Intelsat. Launch Site: Cape Canaveral . Launch Vehicle: Atlas Centaur SLV-3D. Mass: 2,000 kg. Perigee: 35,771 km. Apogee: 35,799 km. Inclination: 3.6 deg.
19 May 1983 Intelsat 5 F-6 Program: Intelsat. Launch Site: Cape Canaveral . Launch Vehicle: Atlas Centaur SLV-3D. Mass: 1,928 kg. Perigee: 35,772 km. Apogee: 35,805 km. Inclination: 2.5 deg.

Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle put payload into geosynchronous transfer orbit


19 October 1983 Intelsat 5 F-7 Program: Intelsat. Launch Site: Kourou . Launch Vehicle: Ariane 1. Mass: 1,928 kg. Perigee: 35,759 km. Apogee: 35,814 km. Inclination: 3.0 deg.

Ariane third stage. Launched by European Space Agency. Launch time 0045:36 GMT. Launched spacecraft Intelsat V F7.


05 March 1984 Intelsat 5 F-8 Program: Intelsat. Launch Site: Kourou . Launch Vehicle: Ariane 1. Mass: 1,928 kg. Perigee: 35,773 km. Apogee: 35,800 km. Inclination: 2.4 deg.
09 June 1984 Intelsat 5 F-9 Program: Intelsat. Launch Site: Cape Canaveral . Launch Vehicle: Atlas G. FAILURE: Centaur structural failure. . Mass: 1,091 kg. Perigee: 180 km. Apogee: 1,227 km. Inclination: 29.2 deg.

Failure of Centaur upper stage left stranded in useless orbit. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle was to have put payload into geosynchronous transfer orbit



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Last update 12 March 2001.
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© Mark Wade, 2001 .