Previous studies indicated that an applied force was necessary to perform in-flight identification of the mass and center of mass of a spacecraft. This paper shows that the mass and center of mass of a rigid spacecraft can be determined using only torque-producing actuators such as control-moment gyros or reaction wheels, and commonly available sensors, e.g., rate gyros and accelerometers. A space-station application is presented.


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    Titel :

    Spacecraft mass property identification with torque-generating control


    Beteiligte:
    Bergmann, E. (Autor:in) / Dzielski, J. (Autor:in)


    Erscheinungsdatum :

    1990-02-01



    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch





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