Most of the attitude control tests of flexible spacecraft have been made by numerical simulation, a static closed loop test or a dynamic closed loop test. However, the dynamic closed loop test is required to check hardware compatibilities with an actual spacecraft control system. This paper describes a new dynamic closed loop test system and verification of a new attitude controller using this dynamic test system. The problem peculiar to this test system is a physical model, how to realize spacecraft flexibility parameters and how to remove residual disturbance torque on the ground. In this test system, it is possible to obtain the dynamic characteristics of the physical spacecraft model, equivalent to that which the real flexible spacecraft indicates. Using this test system, the dynamic closed loop tests of flexible spacecraft attitude controller have been carried out on the ground. Its tests have been made to evaluate the performance of the newly developed attitude controller for flexible spacecraft. This new controller has the ability to improve the attitude control bandwidth for disturbance in comparison with a conventional controller. Moreover, this controller can be easily realized by existing hardwares. A numerical simulation results and test results of this attitude controller are presented.


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    Title :

    Attitude control test of flexible spacecraft


    Additional title:

    Prüfung der Lageregelungseinrichtung bei flexiblen Raumfahrzeugen


    Contributors:
    Yamashita, T. (author) / Kurii, T. (author)

    Published in:

    Publication date :

    1993


    Size :

    9 Seiten, 6 Bilder, 2 Tabellen, 5 Quellen



    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English




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