An approach to large-angle rotational maneuvers of a spacecraft-beam-tip body configuration is presented which is based on nonlinear invertibility and linear feedback stabilization. A control law is derived for the decoupled control of attitude angles, lateral elastic deflections, slopes due to bending and angular deflection due to torsion at the tip of the beam using torquers and force actuators. For the stabilization of the elastic modes, a linear feedback control law is obtained based on a linearized model augmented with a servocompensator. Simulation results are presented to show that large slewing and elastic mode stabilization can be accomplished.


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    Title :

    Robust nonlinear attitude control of flexible spacecraft


    Additional title:

    Robuste nichtlineare Lageregelung eines verformbaren Raumfahrzeugs


    Contributors:
    Singh, S.N. (author)

    Published in:

    Publication date :

    1987


    Size :

    8 Seiten, 17 Quellen



    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English







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