Finite time attitude control for over-activated spacecraft with reaction wheel misalignment

被引：0
|
作者：
Zhang, Ai-Hua [1 ,2 ]
Hu, Qing-Lei [1 ]
Huo, Xing [1 ,2 ]
机构：
[1] School of Astronautics, Harbin Institute of Technology, Harbin 150001, China
[2] College of Engineering, Bohai University, Jinzhou 121001, China
来源：
Kongzhi yu Juece/Control and Decision | 2014年 / 29卷 / 01期
关键词：
Navigation - Sliding mode control - Spacecraft - Wheels - Tracking (position) - Alignment;
D O I：
10.13195/j.kzyjc.2012.1316
中图分类号：
学科分类号：
摘要：
A finite-time control scheme is presented to address the attitude tracking problem of over-actuated spacecraft, in which reaction wheel misalignment, external disturbance and uncertain mass of moment inertia are considered. A finite time controller using adaptive sliding mode control technique is developed. It can guarantee finite-time reachability of the given attitude motion even in the presence of external disturbances, and uncertainties in the configuration matrix due to reaction wheel misalignment and mass of moment inertia. Numerical simulation results of an application to spacecraft show the effectiveness of the proposed attitude tracking control law.
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页码：27 / 32
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