基于需用速度增益曲面的大气层外超远程拦截导引方法

考虑拦截器使用耗尽关机固体推进系统的情况,提出需用速度增益曲面概念,设计了基于该概念的大气层外超远程拦截导引方法。根据Lambert导引,给定拦截时间就有唯一的指令推力方向与之对应,导引过程分为两个阶段:零控拦截到达阶段,选择最优拦截时间,需用速度增益曲面迅速与助推时间-拦截时间平面相切;零控拦截保持阶段,拦截时间不断减小,保持需用速度增益曲面在助推时间-拦截时间平面上滑动,消耗多余的推进剂。利用拟零控拦截概念使两个导引阶段平缓过渡,避免了导引方法切换时推力方向的跳变。导引律计及了J2项摄动对滑行段弹道的影响,导引精度对推进系统参数偏差的鲁棒性强。仿真结果表明本文制导方法用于大气层外超远程目标拦截,脱靶量仅为km量级,推进系统参数偏差对导引精度的影响很小。

Guidance Based on Velocity-to-be-gained Surface for Super-range Exoatmospheric Intercept

The concept of a velocity-to-be-gained surface and a guidance law based on it for super-range exoatmospheric intercept is proposed for an interceptor with a fuel-exhaustion-shutoff solid rocket motor.Time-tointercept determines the exclusive command thrust orientation in Lambert guidance,and the presented guidante process is composed of two stages:the optimal time-to-intercept is chosen to make the velocity-to-begained surface osculate the boost-time VS time-to-intercept plane during the zero-effort-intercept-achieving stage;then the velocity-to-be-gained surface slides on the boost-time vs time-to-intercept plane by decreasing the time-to-intercept durative to exhaust the redundant fuel.The concept of pseudo-zero-effort-intercept is used in the proposed guidance tO avoid thrust orientation break at the shift of the two guidance processes.The J2 item perturbation is considered in the guidance law,whose guidance precision is robust to motor parameter uncertainties.Simulation results demonstrate that the order of zero elfort miss magnitude is kilometer and the guidance precision is robust to motor parameter uncertainties when using the proposed guidance law for superrange exoatmospheric intercept.