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Attitude stabilization of rigid spacecraft with finite‐time convergence
Author(s) -
Zhu Zheng,
Xia Yuanqing,
Fu Mengyin
Publication year - 2011
Publication title -
international journal of robust and nonlinear control
Language(s) - English
Resource type - Journals
SCImago Journal Rank - 1.361
H-Index - 106
eISSN - 1099-1239
pISSN - 1049-8923
DOI - 10.1002/rnc.1624
Subject(s) - control theory (sociology) , spacecraft , inertia , convergence (economics) , nonlinear system , attitude control , computer science , disturbance (geology) , control (management) , mode (computer interface) , controller (irrigation) , control engineering , engineering , physics , aerospace engineering , agronomy , classical mechanics , quantum mechanics , artificial intelligence , economic growth , economics , biology , operating system , paleontology
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 © 2010 John Wiley & Sons, Ltd.