根据飞航导弹对面攻击的需要， 针对可以获取的信息，设计了视线角信息 框架下的双平面导引规律，以实现指定入射角的攻击，并从理论上进行了分析。以 此为基础，考虑到弹体和控制回路的特性， 完成了一种便于工程实施的综合制导律， 改善了制导性能。通过充分利用飞航导弹 中制导阶段的弹道特性，解决了计算弹道 倾角时光滑低延迟垂速获取的难题。数学 仿真结果显示了所设计方法的有效性。

]To meet the cruise missile's air-to-surface attack requirement,  specified impact angle guidance law is presented based on line of sight (LOS) information framework.  Theoretical analysis proves its property.  Considering the missile autopilot's dynamics,  a simple engineering version of integrated guidance and control synthesis is deduced to improve performance.  Mid-course trajectory characteristic is utilized to obtain smooth and low-delay vertical velocity to calculate trajectory angle.  Finally mathematical simulation demonstrates their effectiveness.