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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    Title :

    Spacecraft mass property identification with torque-generating control


    Contributors:
    Bergmann, E. (author) / Dzielski, J. (author)


    Publication date :

    1990-02-01



    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English





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