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astronautix.com AS 4000

AS 4000 satellite
AS 4000 satellite -

Credit: Lockheed-Martin. 10,912 bytes. 300 x 304 pixels.



Class: Communications. Nation: USA. Manufacturer: Lockheed Martin.

3-axis stabilisation with momentum wheels, magnetic torquers, Earth sensors and 16 blowdown monopropellant hydrazine thrusters. Solar arrays provide 2800 W, 3 x 50 Ahr NiH batteries. GEO insertion by Star 37XFP solid rocket motor. 16 Ku-band transponders (with six spares) .


Specification

Design Life: 12 years. Total Length: 2.1 m. Maximum Diameter: 1.7 m. Total Mass: 1,021 kg.


AS 4000 Chronology


27 November 1985 Satcom K2 Program: Satcom. Launch Site: Cape Canaveral . Launch Vehicle: Shuttle. Mass: 1,812 kg. Perigee: 35,786 km. Apogee: 35,790 km. Inclination: 0.0 deg.

Released by STS 61B 11/28/85; 81 deg W.


12 January 1986 Satcom K1 Program: Satcom. Launch Site: Cape Canaveral . Launch Vehicle: Shuttle. Mass: 1,923 kg. Perigee: 35,783 km. Apogee: 35,792 km. Inclination: 0.0 deg.

Stationed at 81 deg W.


11 December 1988 Astra 1A Program: Astra. Launch Site: Kourou . Launch Vehicle: Ariane 44LP. Mass: 1,780 kg. Perigee: 35,741 km. Apogee: 35,831 km. Inclination: 0.0 deg.

European TV broadcast; 19.2 deg W. Astra 1A provides TV coverage to Western Europe. The satellite is owned and operated by Société Europíenne des Satellites (SES), a private company formed in 1985. Astra 1A is based in the GE 4000 series platform, and was the first in a network of four satellites. Spacecraft: GE 4000 platform.3-axis stabilisation with momentum wheels, magnetic torquers, Earth sensors and 16 blowdown monopropellant hydrazine thrusters. Solar arrays provide 2800 W BOL, 3 50 Ahr NiH batteries. GEO insertion by Star 37XFP solid rocket motor. Payload: 16 Ku-band transponders (with six spares) .


03 April 1996 Inmarsat 3 F1 Program: Inmarsat. Launch Site: Cape Canaveral . Launch Vehicle: Atlas IIA. Mass: 2,068 kg. Perigee: 35,765 km. Apogee: 35,805 km. Inclination: 2.2 deg.

Geostationary at 64.1E. Launch vehicle put payload into geosynchronous transfer orbit with RAAN Cntl trajectory option.


06 September 1996 Inmarsat 3 F2 Program: Inmarsat. Launch Site: Baikonur . Launch Vehicle: Proton 8K82K / DM1. Mass: 1,021 kg. Perigee: 35,766 km. Apogee: 35,807 km. Inclination: 2.5 deg.

Geostationary at 15.5W.


18 December 1996 Inmarsat 3 F3 Program: Inmarsat. Launch Site: Cape Canaveral . Launch Vehicle: Atlas IIA. Mass: 1,021 kg. Perigee: 35,698 km. Apogee: 35,877 km. Inclination: 2.6 deg.

Geostationary at 157.6E. Launch vehicle put payload into geosynchronous transfer orbit with RAAN Cntl trajectory option.


03 June 1997 Inmarsat 3 F4 Program: Inmarsat. Launch Site: Kourou . Launch Vehicle: Ariane 44L . Mass: 1,021 kg. Perigee: 35,770 km. Apogee: 35,805 km. Inclination: 0.0 deg.

Geosynchronous. Stationed over 54.0W


04 February 1998 Inmarsat 3 F5 Program: Inmarsat. Launch Site: Kourou . Launch Vehicle: Ariane 44LP . Mass: 1,021 kg. Perigee: 35,773 km. Apogee: 35,799 km. Inclination: 2.6 deg.

Geostationary at 25.0 degrees E.



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Last update 12 March 2001.
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