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
18 pages
Report
No indication
English
Unmanned Spacecraft , Manned Spacecraft , Control simulation , Flexible spacecraft , Interactive control , Shuttle engineering simulator , Algorithms , Feedback control , Control systems design , Controllers , Cost reduction , Digital computers , Dynamic structural analysis , Rigid structures , Test facilities
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