Sliding mode control of spacecraft attitude with finite-time convergence

被引：0

作者：

Ding, Shihong ^{[1
]}

Li, Shihua ^{[1
]}

机构：

[1] SE Univ, Dept Automat Control, Nanjing 210096, Peoples R China

来源：

WCICA 2006: SIXTH WORLD CONGRESS ON INTELLIGENT CONTROL AND AUTOMATION, VOLS 1-12, CONFERENCE PROCEEDINGS | 2006年

关键词：

spacecraft; attitude control; finite-time convergence; sliding mode control;

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：

A sliding mode control method based on finite-time control technology is designed to the spacecraft-attitude output tracking control system in the presence of external disturbances. The states of the tracking error system can not only be controlled to the sliding mode manifold from any initial states in finite-time but also converge to zero along the sliding mode manifold in finite-time. Rigorous mathematical proof is also given. Meanwhile, based on sliding mode control method, a finite-time control law for stabilizing the spacecraft attitude is also given. Numerical simulation results are presented to validate the effectiveness of the system.

引用

页码：830 / 834

页数：5

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