战术弹道导弹助推段拦截预测导引方法

摘要

针对弹道导弹助推段拦截的末制导问题进行研究,建立了弹道导弹助推段的运动模型,根据助推段的运动特点提出了预测导引末制导方法,通过分析零效脱靶量将比例导引的过载指令与轨控发动机工作时间进行等效.在不同的弹目速度初始夹角下分别用预测导引和比例导引法仿真并进行对比分析,仿真结果表明预测导引较比例导引在较大的末制导起始区域内具有更短的拦截时间和更少的轨控发动机燃料消耗量.%Focused on the terminal guidance law of intercepting tactical ballistic missile in boost phase, the motion model of TBM' boost-phase is established.Touse the predictive guidance as the terminal guidance law is put forward.By analyzing the zero-effort-miss, change the proportional navigation guidance (PN) command to the rail engine' working time.Separately simulated the intercepting scene with predictive guidance and PN at different initial missile velocity angle, and compared the results.The simulation results show that the predictive guidance has less intercepting time need less rail engine' working time than the PN with large terminal guidance initial area.