Adaptive Output Feedback Attitude Control of Flexible Spacecraft from Quaternion Measurements

被引：0
|
作者：
Liu, Yaqiu [1 ]
Song, Wenlong [1 ]
Zhu, Liangkuan [1 ]
机构：
[1] NE Forestry Univ, Harbin 150040, Heilongjiang Pr, Peoples R China
来源：
2008 2ND INTERNATIONAL SYMPOSIUM ON SYSTEMS AND CONTROL IN AEROSPACE AND ASTRONAUTICS, VOLS 1 AND 2 | 2008年
关键词：
D O I：
暂无
中图分类号：
TP [自动化技术、计算机技术];
学科分类号：
0812 ;
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.
引用
收藏
页码：1007 / 1010
页数：4
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