Backstepping Sliding Mode Control for Missile Attitude System

This paper is devoted to the attitude control of a quaternion described missile model, which is nonlinear in aerodynamics with atmospheric moment uncertainties, inertia uncertainties, bounded disturbances and actuator failures. One backstepping 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. The variable structure control including sliding mode control has the valuable features of anti-interference and resisting parameter distortion, providing a useful solution for designing control law. Also, simulation results are presented to illustrate the effectiveness of the control strategy.