Influence of initial heading angle for the optimal guidance law with impact angle constraint

摘要

Control of impact angle can considerably increase missile's lethality. However, large impact angle will lead to large lateral acceleration requirement during the flight. In order to avoid command saturation, one can choose initial heading angle to decrease the magnitude of the guidance command. Based on impact angle control optimal guidance law of air-to-surface missile, some more in-depth research work is showed in this paper. For a specified impact angle, the methods to select initial heading angle is presented, and, the launch envelope of initial heading angle and terminal impact angle are given. Simulation results demonstrate the obtained conclusions.