Abstract:

Head pursuit guidance and control law with consideration of dynamic characteristic for missiles with blended lateral jets and aerodynamic control is researched in order to meet practical requirement for intercepting targets with high velocity and high maneuver in near space. A lateral jets control approach is given in consideration of characteristics of discrete lateral jets and continuous aerodynamic control, thus avoiding the complicated control allocation problem. In this approach, the lateral jets control is supposed to be continuous and is designed on the base of aerodynamic control, and then is discretized by impulse equivalence. According to the kinematics model of two dimensional head pursuit guidance and the dynamics model of interceptor missile, and using time-scale separation, the kinematics model of interceptor and target, together with the acceleration dynamics is treated as the slowly varying subsystem, while the pitch angular rate dynamics is treated as the fast varying subsystem. The pitch angular rate command is designed and the head pursuit guidance law considering the dynamic characteristic of blended lateral Jets and aerodynamic control is obtained by designing the tracking control law of pitch angular rate command. The simulation results show the accuracy and the effectiveness of the proposed method.

Key words: Blended lateral jets and aerodynamic control, Head pursuit, Guidance law, Dynamic characteristic of control system, Time-scale separation