Sliding Mode Control of Spacecraft Attitude with Finite-time Convergence

Author

Ding, Shihong ; Li, Shihua

Author_Institution

Dept. of Autom. Control, Southeast Univ., Nanjing

Volume

1

fYear

0

fDate

0-0 0

Firstpage

830

Lastpage

834

Abstract

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

Keywords

attitude control; position control; space vehicles; variable structure systems; external disturbances; finite-time control technology; finite-time convergence; numerical simulation; sliding mode control; sliding mode manifold; spacecraft attitude stability; spacecraft-attitude output tracking control system; tracking error system; Attitude control; Automatic control; Control systems; Convergence; Error correction; Numerical simulation; Roentgenium; Sliding mode control; Space technology; Space vehicles; attitude control; finite-time convergence; sliding mode control; spacecraft;

fLanguage

English

Publisher

ieee

Conference_Titel

Intelligent Control and Automation, 2006. WCICA 2006. The Sixth World Congress on

Conference_Location

Dalian

Print_ISBN

1-4244-0332-4

Type

conf

DOI

10.1109/WCICA.2006.1712459

Filename

1712459