Design of Guidance Law for Smart Missile Based on Direct Mode Configuration with Implicit Dynamic-Inverse

Abstract The design of guidance law for smart missile based on implicit dynamic-inverse direct mode configuration is described in this paper. theory and algorithm are applied to the law. pitching acceleration yaw designed pitch channel by using augmented proportional respectively. attacking time parameter attack error equation introduced as constraint criteria dynamic-inverse. According singular perturbation theory, fast slow subsystems control, then required control quantities obtained solving relative motion equations target. simulation results showed that can fully meet trajectory performance requirements missile.