Verification of control algorithms for flexible spacecraft can be done only through simulation and test; these are necessary to understand control/structure interaction (C/SI) sufficiently to design robust controllers for future spacecraft. The objective persued is to develop a low-cost facility which simulates the fundamental problem of C/SI; and to provide accessibility for designs so that experience can be gained in applying various multivariable control design methods to an actual structure. A test facility is being constructed with test elements that provide 3 rigid body and 6 flexible modes, all in the horizontal plane, with frequencies below 2.5 Hz. The control force actuator are on/off air jets with sensing by optical displacement sensors. Loop closure is provided by a digital computer with control algorithms designed using the IAC and MATRIX-X.


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    Test of a flexible spacecraft dynamics simulator

    Dichmann, Donald / Sedlak, Joseph | NTRS | 1998


    Test of a Flexible Spacecraft Dynamics Simulator

    Dichmann, D. / Sedlak, J. / American Astronautical Society et al. | British Library Conference Proceedings | 1998


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