The attitude stabilization and control system for the INTELSAT VI geosynchronous communications satellite is described. The dual-spin spacecraft design, the launch-to-final-orbit mission sequence, and the superspin technique developed to stabilize the spacecraft during geosynchronous transfer orbit operations are reviewed. Detailed descriptions are given of the functional design, implementation, and performance of the microprocessor-based control system. Key topics summarized include precision despun platform pointing control using either spinning sun and earth sensors or an RF beacon track receiver; active nutation stabilization using payload pointing control loops; extensive processor fault protection; and a high level of control system autonomy, including on-board spin axis attitude determination and control, on-board stationkeeping maneuver control, and the use of stored command processing.
Attitude and payload control system for INTELSAT VI
Lage- und Nutzlastkontrollsystem des Intelsat VI
Comsat Technical Review ; 21 , 1 ; 57-100
1991
44 Seiten, 7 Quellen
Aufsatz (Zeitschrift)
Englisch
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