Abstract
In order to impact the target at the expected angle, based on the integrated model of the pitch plane, the integrated design of guidance and control using backstepping control is proposed. The unknown disturbances caused by target, the missile aerodynamic coefficients, and the circumstance disturbances are estimated by the sliding mode disturbance observer. The stability of the integrated guidance and control system is proven by Lyapunov sense. The simulation results show the validity and effectiveness of the proposed guidance law.
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