Attitude stabilization of rigid spacecraft with finite-time convergence

被引：779
|
作者：
Zhu, Zheng [1 ]
Xia, Yuanqing [1 ]
Fu, Mengyin [1 ]
机构：
[1] Beijing Inst Technol, Dept Automat Control, Beijing 100081, Peoples R China
来源：
INTERNATIONAL JOURNAL OF ROBUST AND NONLINEAR CONTROL | 2011年 / 21卷 / 06期
基金：
中国国家自然科学基金;
关键词：
attitude stabilization; sliding mode control; finite-time stability; adaptive control; SLIDING-MODE CONTROL; ADAPTIVE-CONTROL; TRACKING; ROBUST; DESIGN; CONTROLLER; SYSTEMS;
D O I：
10.1002/rnc.1624
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 which is nonlinear in dynamics with inertia uncertainty and external disturbance is investigated in this paper. Two sliding mode controllers are proposed to force the state variables of the closed-loop system to converge to the origin in finite time. Specially, the second control design consists of the estimation of the uncertainty and disturbance by adaptive method and thus it achieves the decrease of undesired chattering effectively. Also, simulation results are presented to illustrate the effectiveness of the control strategies. Copyright (C) 2010 John Wiley & Sons, Ltd.
引用
收藏
页码：686 / 702
页数：17
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