Adaptive Output Feedback Attitude Control of Flexible Spacecraft from Quaternion Measurements

摘要：

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.

作者: Yaqiu Liu Wenlong Song Liangkuan Zhu

作者单位: Northeast Forestry University Harbin,Heilongjiang Province,China,150040

会议类型: 国际会议

会议名称: The 2nd International Symposium on Systems and Control in Aeronautics and Astronautics(第二届航空航天系统与控制国际会议 ISSCAA 2008)

会议地点: 深圳

会议语种:英文

页码: 1134-1137

在线出版日期: 2008-12-10（万方平台首次上网日期，不代表论文的发表时间）