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.
Flexible spacecraft simulator
1987-04-01
Aufsatz (Konferenz)
Keine Angabe
Englisch
NTIS | 1987
Test of a flexible spacecraft dynamics simulator
NTRS | 1998
|Test of a Flexible Spacecraft Dynamics Simulator
British Library Conference Proceedings | 1998
|SPASIM: A Spacecraft Simulator
British Library Conference Proceedings | 1997
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