期刊
INFORMATION SCIENCES
卷 220, 期 -, 页码 343-366出版社
ELSEVIER SCIENCE INC
DOI: 10.1016/j.ins.2012.07.039
关键词
Attitude tracking; Sliding mode control; Extended state observer; Adaptive control; Actuator saturations
资金
- National Basic Research Program of China (973 Program) [2012CB720000]
- National Natural Science Foundation of China [60974011]
- Program for New Century Excellent Talents in University of China [NCET-08-0047]
- Ph.D. Programs Foundation of Ministry of Education of China [20091101110023, 20111101110012]
- Beijing Municipal Natural Science Foundation [4102053, 4101001]
This paper investigates the attitude tracking control problem for rigid spacecraft with actuator saturations, inertia uncertainties and external disturbances. First, based on adaptive algorithm, a sliding mode control (SMC) law is designed to achieve accurate attitude tracking, and asymptotic convergence is guaranteed by means of the Barbalat lemma. Then, the spacecraft dynamic equation is optimized, and a novel method plays a crucial role toward ensuring stability robustness to actuator saturations in the control design. Using backstepping technique (BT) associated with extended state observer (ESO) or modified differentiator (MD), the corresponding SMC approaches are appropriately designed, which not only achieve a faster and more accurate response, better transient performance, but also afford stronger capability of resistance to inertia uncertainties, external disturbances and control input saturations. Finally, simulation results are presented to illustrate effectiveness of the control strategies. (C) 2012 Elsevier Inc. All rights reserved.
作者
我是这篇论文的作者
点击您的名字以认领此论文并将其添加到您的个人资料中。
推荐
暂无数据