Abstract We study the controlled angular motion of the Chibis-M microsatellite. Executive elements are three pairs of flywheels, whose axes are mutually perpendicular. The task of the control system is realization of a required program motion and support of its asymptotic stability. In this paper, we synthesize a control algorithm and study the evolution of the angular momentum of flywheels on long time intervals. The attitude accuracy is estimated for the case when disturbances act upon the spacecraft.
A study of angular motion of the Chibis-M microsatellite with three-axis flywheel control
Cosmic Research ; 50 , 6 ; 431-440
2012-11-01
10 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
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