The switching condition of guidance laws for compound control missile

Based on the linear time-varying relative motion equation and with consideration of the lateral acceleration limitation, the necessary boundary for controllable line-of-sight angular rate is obtained. With consideration of the dynamic time-delay property of missile autopilot, the necessary boundary for controllable line-of-sight angular rate of guidance system is analyzed. Moreover, the guidance law, which can guarantee the stability of guidance system with the condition of intercepting the high maneuvering target, is put forward. Based on the working properties of the compound control missile, the switching condition to compound control, which can save more energy, is designed subsequently. The simulation results show that the guidance precision of the proposed guidance scheme is better than the existing guidance approaches, and the working time for compound control is shorter.