Adaptive back-stepping sliding mode attitude control of missile systems

Authors


Correspondence to: Yuanqing Xia, School of Automation, Beijing Institute of Technology, Beijing 100081, China.

E-mail: xia_yuanqing@bit.edu.cn

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.

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