导弹直接侧向力机动突防方案设计

针对敌方不同来袭方位的拦截弹,提出了一种可用于导弹末段侧向力机动的突防方案。在建立拦截弹和导弹的相对运动模型基础上给出了脱靶量与视线转率、相对距离和机动加速度的解析表达式。以拦截弹在视线系Z向上的脱靶量达到最大值作为性能指标,对机动发动机开启时刻进行优化确定。同时通过分析机动发动机与Y向舵偏的不同组合方式对导弹的速度增量及交会角的影响,确定机动发动机的推力方向应与气动力方向一致,并使交会角明显减小。仿真结果表明,此方案能使导弹最终落入拦截弹杀伤半径10 m之外,成功实现突防。

Design on maneuver penetration of missile with direct lateral thrust

Aiming at enemy interceptor from different direction,a kind of maneuver penetration strategy used for terminal stage of missile with lateral thrust was put forward.On the basis of the relative movement model between interceptor and missile,the analytical expressions between miss distance and line-of-sight rotation rate as well as relative distance and maneuver acceleration were presented.Taking miss distance of the interceptor along line-of-sight Z direction as performance index,start-up time of the motor was optimized and determined.At the same time,through analyzing the effects of different combination modes between the motor and rudder angle along Y direction on velocity increment and contact angle,thrust direction of maneuver motor is determined to be consistent with aerodynamic force direction;and contact angle reduces obviously.Simulation results show that the strategy makes missile fall outside the 10 m kill radius range of the interceptor and successfully realize penetration.