Quaternion Based Sliding Mode Attitude Control Design for Spacecraft

被引：0
|
作者：
Tian Ye [1 ]
Cai Yuanli [1 ]
机构：
[1] Xi An Jiao Tong Univ, Inst Control Engn, Xian, Shaanxi, Peoples R China
来源：
CONFERENCE PROCEEDINGS OF 2017 3RD IEEE INTERNATIONAL CONFERENCE ON CONTROL SCIENCE AND SYSTEMS ENGINEERING (ICCSSE) | 2017年
关键词：
sliding-mode control; quaternion; atitude tracking error; attitude control; VARIABLE-STRUCTURE CONTROL; MANEUVERS;
D O I：
暂无
中图分类号：
TP [自动化技术、计算机技术];
学科分类号：
0812 ;
摘要：
In this paper, the attitude tracking control problem is investigated for a rigid spacecraft. Robust controllers based on the quaternion model are proposed to solve this problem with external perturbations. An exponential reaching law-based sliding mode control approach is proposed for the problem. The controller guarantees the convergence of attitude tracking errors in finite time, where the settling time can be set in advance, for spacecraft attitude tracking problem. Finally, simulation results are given to demonstrate the efficiency of the proposed methods.
引用
收藏
页码：110 / 114
页数：5
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