Discrete sliding mode guidance law considering dynamic characteristics for autopilot

Abstract

Aiming at the related problems of discrete guidance law, the design of the dynamic delay characteristic of missile autopilots is considered as discrete finite time convergent sliding mode guidance law for the first-order inertial link. Firstly, the discrete guidance equation considering the dynamic characteristics of autopilot was derived; secondly, the discrete sliding mode variable structure guidance law was analyzed; thirdly, the finite time convergence characteristic of the designed guidance law was analyzed and proved. The simulation results show that the designed discrete sliding mode guidance law is convergent in finite time, which ensures the stability of guidance and improves the precision of guidance.