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.


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    Titel :

    A study of angular motion of the Chibis-M microsatellite with three-axis flywheel control


    Beteiligte:

    Erschienen in:

    Cosmic Research ; 50 , 6 ; 431-440


    Erscheinungsdatum :

    2012-11-01


    Format / Umfang :

    10 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch




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