Title :
Sliding Mode Control of Spacecraft Attitude with Finite-time Convergence
Author :
Ding, Shihong ; Li, Shihua
Author_Institution :
Dept. of Autom. Control, Southeast Univ., Nanjing
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;
Conference_Titel :
Intelligent Control and Automation, 2006. WCICA 2006. The Sixth World Congress on
Conference_Location :
Dalian
Print_ISBN :
1-4244-0332-4
DOI :
10.1109/WCICA.2006.1712459
