Attitude Tracking of Rigid Spacecraft With Bounded Disturbances

被引：337

作者：

Xia, Yuanqing ^{[1
]}

Zhu, Zheng ^{[1
]}

Fu, Mengyin ^{[1
]}

Wang, Shuo ^{[2
]}

机构：

[1] Beijing Inst Technol, Dept Automat Control, Beijing 100081, Peoples R China

[2] Chinese Acad Sci, Inst Automat, Key Lab Complex Syst & Intelligence Sci, Beijing 100190, Peoples R China

来源：

IEEE TRANSACTIONS ON INDUSTRIAL ELECTRONICS | 2011年 / 58卷 / 02期

基金：

中国国家自然科学基金;

关键词：

Adaptive control; attitude tracking; extended state observer (ESO); sliding-mode control (SMC); ADAPTIVE-CONTROL; REJECTION; SYSTEMS; MISSILE;

D O I：

10.1109/TIE.2010.2046611

中图分类号：

TP [自动化技术、计算机技术];

学科分类号：

0812 ;

摘要：

The problem of attitude control for a spacecraft model that is nonlinear in dynamics with inertia uncertainty and external disturbance has been investigated. Adaptive law and extended state observer are applied to estimate the disturbance, by which sliding-mode controllers are designed to combine the two approaches in order 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 strategies.

引用

页码：647 / 659

页数：13

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