A proposed dynamics experiment is presented on the joint U.S./Canada Communications Technology Satellite. The experiment is to excite the spacecraft in flight by means of thrusters and measure dynamic response characteristics suing accelerometers, and to compare the results with an analytical model of the flexible spacecraft dynamics. A pulse-train input is designed which is intended to be as close as possible to the spacecraft natural frequency. The response to it of the spacecraft, which is actively controlled, is explored by means of simple theory as well as a detailed digital attitude control simulation, to which flexible dynamics blocks were added. Inputs slightly off resonance are also considered. It is verified by simulation that the spacecraft attitude and structural disturbances during this experiment are acceptable with resonant excitation of twist and in-plane and out-of-plane bending modes individually, while yielding adequate data.


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    Titel :

    Near Resonant Vibration Tests of an Orbiting Flexible Spacecraft: Theory, Design and Simulation


    Beteiligte:
    S. C. Garg (Autor:in)

    Erscheinungsdatum :

    1976


    Format / Umfang :

    183 pages



    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch





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