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Adaptive back‐stepping sliding mode attitude control of missile systems
Author(s) -
Xia Yuanqing,
Lu Kunfeng,
Zhu Zheng,
Fu Mengyin
Publication year - 2013
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.2952
Subject(s) - control theory (sociology) , missile , quaternion , nonlinear system , actuator , sliding mode control , controller (irrigation) , attitude control , aerodynamics , computer science , mode (computer interface) , inertia , control engineering , bounded function , control (management) , engineering , mathematics , aerospace engineering , artificial intelligence , physics , mathematical analysis , agronomy , geometry , classical mechanics , quantum mechanics , biology , operating system
SUMMARY This paper is devoted to the attitude control of a quaternion missile model, which is nonlinear in aerodynamics with atmospheric moment uncertainties, inertia uncertainties, bounded disturbances and actuator failures. By employing the back‐stepping technique, the corresponding sliding mode controller is designed to guarantee the state variables of the closed loop system to converge to a small region of the reference states with the help of the adaptive law by estimating the total uncertainties, and be chatter‐free. Also, simulation results are presented to illustrate the effectiveness of the control strategy. Copyright © 2013 John Wiley & Sons, Ltd.