In this work, an adaptive output feedback attitude control design method is investigated for a three-axis-rotational maneuver and vibration stabilization of a spacecraft with flexible appendages. The proposed controller ensures the asymptotic fulfillment of the objectives in the case of rest-to-rest maneuvers in present of uncertain inertia parameter uncertainty and disturbances. Also, it is assumed that the modal variables describing the flexible elements are not measured. Numerical simulations demonstrate the feasibility and effectiveness of the control strategy.
Adaptive output feedback attitude control of flexible spacecraft from quaternion measurements
01.12.2008
524798 byte
Aufsatz (Konferenz)
Elektronische Ressource
Englisch
British Library Online Contents | 2004
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