In this paper, we demonstrate that, in fact, two momentum wheel actuators can be used to control the attitude of a rigid spacecraft and that arbitrary reorientation maneuvers of the spacecraft can be accomplished in a specific sense. The complete spacecraft dynamics cannot be stabilized to an equilibrium attitude. However, the spacecraft equations are small time locally controllable in a reduced nonlinear sense. The reduced spacecraft dynamics cannot be asymptotically stabilized to an equilibrium attitude using a time-invariant continuous feedback control law, but a discontinuous feedback control strategy is constructed which asymptotically stabilizes an equilibrium attitude of the spacecraft. Consequently, arbitrary reorientation of the spacecraft can be accomplished using this discontinuous feedback control strategy.


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    Title :

    Attitude stabilization of a rigid spacecraft using momentum wheel actuators operating in a failure mode


    Contributors:

    Publication date :

    1992-08-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English





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