Command equation for inertia wheel control system which results in desirable dynamic response and precise control is derived; three degree of freedom study indicates that inertia coupling and precession coupling have only small effects on results; single degree of freedom bench tests verified dynamic response predicted and demonstrated control within plus or minus 9 arc-sec of reference attitude.


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    Titel :

    Satellite attitude control using combination of inertia wheels and bar magnet


    Weitere Titelangaben:

    NASA -- Tech Note


    Beteiligte:
    Adams, J.J. (Autor:in) / Brissenden, R.F. (Autor:in)


    Erscheinungsdatum :

    1960


    Format / Umfang :

    42 pages


    Medientyp :

    Report


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :


    SIMULATOR STUDY OF A SATELLITE ATTITUDE CONTROL SYSTEM USING INERTIA WHEELS AND A MAGNET

    Adams, J. J. / Bergeron, H. P. / Howell, W. E. | NTRS | 1963




    Study of systems using inertia wheels for precise attitude control of satellite

    White, J.S. / Hansen, Q.M. | Engineering Index Backfile | 1961