The characteristics of double gimballed momentum wheels are explored with respect to their use in geostationary satellites (active and semiactive), low orbit earth pointing satellites (active and semi-active), and in astronomical satellites. Special attention is paid to the effect of control laws and gimbal suspension on the accuracy of the system. The pointing error of an active control system for a geostationary satellite can be kept low (0.05 deg) and is hardly affected by the gimbal suspension. Semi-active systems give large yaw errors due to disturbance torques; with these systems, the required accuracy cannot be maintained during station keeping, unless estimation techniques are used. The total pointing error is in the order of 0.2 deg for low orbit earth pointing satellites, due to uncertainties in the measured position of the horizon. The accuracy of astronomical satellite control systems with double gimballed momentum wheels is nearly equal to that of a system with control moment gyroscopes.


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    Titel :

    Accuracy of Attitude Control Systems for Satellites Using Double Gimballed Momentum Wheels


    Beteiligte:
    G. Boersma (Autor:in) / F. J. Sonnenschein (Autor:in)

    Erscheinungsdatum :

    1973


    Format / Umfang :

    103 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch







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