Rigid spacecraft attitude control using adaptive integral second order sliding mode

被引：94
|
作者：
Tiwari, Pyare Mohan [1 ]
Janardhanan, S. [2 ]
Nabi, Mashuq Un [2 ]
机构：
[1] Amity Univ Uttar Pradesh, Dept Elect Engn, Noida, India
[2] Indian Inst Technol, Dept Elect Engn, New Delhi 110016, India
来源：
AEROSPACE SCIENCE AND TECHNOLOGY | 2015年 / 42卷
关键词：
Attitude control; Second order sliding mode; Integral sliding mode; Finite-time convergence; Adaptive gain; VARIABLE-STRUCTURE CONTROL; FINITE-TIME STABILITY; SYSTEMS; DESIGN; ORDER; TRACKING;
D O I：
10.1016/j.ast.2014.11.017
中图分类号：
V [航空、航天];
学科分类号：
08 ; 0825 ;
摘要：
The aim of this paper is to design a globally robust and globally finite-time convergent attitude controller for a rigid spacecraft. Second order sliding mode control in integral sliding mode is proposed to design the controller. To eliminate the need of advance information about uncertainty and external disturbance bounds, the gains of the proposed controller are calculated using the adaptive laws. The second order sliding mode controller applied is based on geometric homogeneity approach. The finite-time stability is proved by using both the Lyapunov stability and negative homogeneity approach. Simulations are conducted for the attitude tracking and attitude stabilization under the effect of spacecraft mass inertia uncertainty and external disturbances; and the outcomes reveal the effectiveness of the proposed control method. (C) 2015 Elsevier Masson SAS. All rights reserved.
引用
收藏
页码：50 / 57
页数：8
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