Attitude Tracking of Rigid Spacecraft Based on Extended State Observer

摘要：

The problem of attitude control for a spacecraft model which is nonlinear in dynamics with inertia uncertainty and external disturbance is investigated in this paper. The extended state observer is applied to estimate the disturbance, by which a sliding mode controller is designed to force the state variables of the closed loop system to converge to the reference attitude states. Also, simulation results are presented to illustrate the effectiveness of the control strategy.

关键词： Attitude tracking:Sliding mode control:Extended state observer

作者: Zheng Zhu Yuanqing Xia Mengyin Fu Shuo Wang

作者单位: Department of Automatic Control,Beijing Institute of Technology,Beijing 100081,China. Complex Systems and Intelligence Science,Institute of Automation,Chinese Academy of Sciences.

会议类型: 国际会议

会议名称: The 3rd International Symposium on Systems and Control in Aeronautics and Astronautics(第三届航空航天系统与控制国际会议 ISSCAA 2010)

会议地点: 哈尔滨

会议语种:英文

页码: 598-603

在线出版日期: 2010-01-08（万方平台首次上网日期，不代表论文的发表时间）