An analytical approach is presented for the stick-slip of the TCM (Tension Control Mechanism) by means of spacecraft attitude responses. The mathematical model utilized assumes that the spacecraft was composed of a main rigid body and flexible appendages, which consist of a number of rigid plates connected by torsional hinges. Key parameters of the hinges are determined by applying the equations of the vibration of a uniform cantilever beam with tangible physical parameters. This mathematical model was evaluated using the ADEOS (ADvanced Earth Observing Satellite) and ADEOS-II flight data and ground-based test data. It is concluded that the technical approach and mathematical model utilized have correctly represented actual spacecraft motions.


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    Title :

    Dynamic simulation of stick-slip motion of a flexible solar array


    Additional title:

    Dynamische Simulation der Stick-Slip-Bewegung einer flexiblen Solaranlage


    Contributors:

    Published in:

    Publication date :

    2008


    Size :

    12 Seiten




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English





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