飞航导弹双平面纵向综合制导技术

Synthesis of Bi-planar Vertical Guidance and Control for Cruise Missile

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.