Journal
INTERNATIONAL JOURNAL OF ROBUST AND NONLINEAR CONTROL
Volume 21, Issue 6, Pages 686-702Publisher
WILEY
DOI: 10.1002/rnc.1624
Keywords
attitude stabilization; sliding mode control; finite-time stability; adaptive control
Funding
- National Natural Science Foundation of China [60974011, 60904086]
- Program for New Century Excellent Talents in University of Peoples Republic of China [NCET-08-0047]
- Ministry of Education of China [20091101110023]
- Changjiang Scholars and Innovative Research Team in University
- Beijing Municipal Natural Science Foundation [4102053]
Ask authors/readers for more resources
The problem of attitude control for a spacecraft model which is nonlinear in dynamics with inertia uncertainty and external disturbance is investigated in this paper. Two sliding mode controllers are proposed to force the state variables of the closed-loop system to converge to the origin in finite time. Specially, the second control design consists of the estimation of the uncertainty and disturbance by adaptive method and thus it achieves the decrease of undesired chattering effectively. Also, simulation results are presented to illustrate the effectiveness of the control strategies. Copyright (C) 2010 John Wiley & Sons, Ltd.
Authors
I am an author on this paper
Click your name to claim this paper and add it to your profile.
Reviews
Recommended
No Data Available
Share Paper
