Active vibration suppression of a large flexible space structure is addressed. The system (experimental test bed), performance requirements, and system simulations and models are described. The structures is a 60-m truss beam attached to the Shuttle orbiter. A baseline control system is required to provide 5% structural damping for the first ten structural (flexible) modes of the truss beam. The control design approach used to achieve the damping is a decentralized velocity feedback type. Collocated actuator and sensor locations are given, with details of the model for the proof-mass actuating device, the linear DC motor.


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    Title :

    Active vibration suppression for the mast flight system


    Additional title:

    Aktive Schwingungsunterdrueckung fuer ein grosses flexibles Raumfahrtsystem


    Contributors:
    Ham, F.M. (author) / Greeley, S.W. (author) / Henniges, B.L. (author)

    Published in:

    Publication date :

    1989


    Size :

    6 Seiten, 4 Quellen



    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English





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