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• W2144502318 abstract "Addressed here is the problem of designing a dynamic controller capable of performing rest-to-rest maneuvers for flexible spacecraft, by using attitude measures. This controller does not need the knowledge of modal variables and spacecraft angular velocity. The absence of measurements of these variables is compensated by appropriate dynamics of the controller, which supplies their estimates. The Lyapunov technique is applied in the design of this dynamic controller. Possible source of instability of the controlled system in real cases are the influence of the flexibility on the rigid motion, the presence of disturbances acting on the structure, and parameter variations. In order to attenuate their effects and to damp out undesirable vibrations affecting the spacecraft attitude, distributed piezoelectric actuators are used. In fact, in presence of disturbances and/or parameter variation the proposed controller ensures an approximate solution of the control problem." @default.
• W2144502318 created "2016-06-24" @default.
• W2144502318 creator A5082574385 @default.
• W2144502318 date "2003-07-01" @default.
• W2144502318 modified "2023-10-13" @default.
• W2144502318 title "Output stabilization of flexible spacecraft with active vibration suppression" @default.
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• W2144502318 doi "https://doi.org/10.1109/taes.2003.1238733" @default.
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