空间直接碰撞末制导的制导与控制

Guidance and Control in Terminal Homing Phase of a Space Interceptor

根据空间直接碰撞末制导的总体设计思想和空间交会的具体情况，本文探讨了大侧向过载修偏条件下的制导与控制问题并将末制导段分为两段，即末制导前段和未制导末端。由于末制导前段占有末制导的大部分时间，选用最优导引律以实现能量最省和剩余偏差尽可能小；在末制导的末端，转用预测遭遇点的最大侧向力开关时间控制方法（即预测强力开关律）。该控制律特点是要预知精确的碰撞时刻和导引律与控制律合一，本文叙述了这种控制律和一种简单的推测相对距离的方法。

On the basis of the System design for terminal homing of a space interceptor and the special condition in a space interception,the guidance and control using larger lateral acceleration control(LLAC)are discussed and the terminal homing phase is divided into two sections,that is,the forward section and the terminal section.Since the forward section will occupy the greater part of the time in terminal phase,the optimal guidance law (OGL) will be chosen so that the least energy is con-sumed and the cross range error(CRE) is as small as possible.In the terminal section,the terminal encounter point predicted strong force on off control(TESOC)method is used so that the error at encounter point can be efficiently corrected. The conceptions for TESOC and relative range predic-tion is mainly discussed in the paper.