The despin maneuver of a Satellite Business Systems (SBS) spacecraft is unique because the effective spin-to-transverse inertia ratio is greater than unity in the all-spinning configuration and less than unity in the despin configuration. Thus, the vehicle changes from a passively stable to a passively unstable configuration. For a brief period during this transition, the effective spin inertia ratio is intermediate and the nutation angle diverges exponentially. A successful despin maneuver depends on certain spacecraft mass properties. Digital simulations have been used to determine the sufficient constraints on spacecraft mass properties for acceptable despin operations. The performance and characteristics of platform despin can also be investigated based on the simulation results. Several runs using the expected worst-case mass properties of the SBS F-3 spacecraft were also conducted. The results can be used to predict the spacecraft despin maneuver.
Digital simulations of SBS spacecraft despin operation
Digitalsimulationen der Stabilisierung des kommerziellen Satellitensystems
Comsat Technical Review ; 12 , 1 ; 213-229
1982
17 Seiten, 6 Quellen
Aufsatz (Zeitschrift)
Englisch
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