通过对比例导引的特性分析,证明了末制导时间与制导控制系统时间常数之间应满足的关系及导弹的最大可用过载能力。为了满足地地导弹大落角战技指标要求,分别研究了过重补比例导引和弹道成形制导律,并对其工程应用方案进行了分析。最后对大落角制导律在使用中应注意的问题进行了总结。研究结论对地地常规导弹末制导律的工程使用有指导意义。

Through characteristic analysis of proportional navigation (PN), the certain relationship between terminal flight time and the guidance control system time constant that should be satisfied and the missile's maximum available overload capability were proved. In order to meet the high impact angle specifications of a missile, the gravity over-compensation PN and trajectory shaping guidance law were studied, and the engineering application solutions were analyzed. Finally, points that should be paid attention to during using the high impact angle guidance law were summarized. The research conclusion has a great significance in engineering application of ground to ground conventional missile terminal guidance law.