考虑复合控制系统动态特性的前向拦截制导律

Head Pursuit Guidance Law Considering Dynamic Characteristic of Hybrid Control System

为满足临近空间拦截高速大机动目标的实际需求,研究了考虑直接力/气动力复合控制动态特性的前向拦截制导律设计方法。在考虑连续气动力和离散直接力特点的基础上,给出了一种在气动舵控制基础上设计连续直接力、然后通过冲量等效法进行离散化的直接力设计方法,避免了复杂的控制分配问题。根据二维前向拦截导引运动学模型和拦截导弹动力学模型,利用时间尺度分离,将拦截导弹和目标的质点运动学与加速度慢变子系统构成的动态系统,看成慢变子系统,设计了俯仰角速度指令;将俯仰角速度动态子系统看成快变子系统,通过对俯仰角速度指令的跟踪控制设计得到考虑复合控制系统动态特性的前向拦截导引律。仿真结果校验了本文方法的正确性和有效性。

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.