【摘要】 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。更多还原

【Abstract】 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.更多还原