Output Feedback Attitude Tracking Control for a Rigid Spacecraft with Dynamic Uncertainty

被引：5
|
作者：
Xian Bin [1 ]
Huang Mu [1 ]
Li Dong [1 ]
Cui Cuijie [1 ]
Yang Kaiyan [1 ]
机构：
[1] Tianjin Univ, Sch Elect Engn & Automat, Tianjin 300072, Peoples R China
来源：
PROCEEDINGS OF THE 27TH CHINESE CONTROL CONFERENCE, VOL 2 | 2008年
关键词：
Spacecraft; Output feedback; Attitude control; Quaternion; uncertainty;
D O I：
10.1109/CHICC.2008.4605788
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 paper, a nonlinear output feedback control mechanism is developed to address the attitude tracking problem of a rigid spacecraft system which contains uncertainty associated with dynamic model and is under the effect of external disturbance. The control strategy is based on limited assumption on the system dynamics. A set of filters are developed to compensate for the unmeasurable spacecraft's angular velocity. A semi-global asymptotic attitude tracking result is achieved while all the closed-loop states remain bounded.
引用
收藏
页码：464 / 468
页数：5
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