Adaptive Output Feedback Attitude Control of Flexible Spacecraft from Quaternion Measurements

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.