固体弹道导弹大气层外弹道飞行时间控制方法

Control Method for Extra-atmospheric Flight Time of Solid Ballistic Missiles

针对固体弹道导弹发动机推力大小无法调节与被动关机的特点,为满足大气层外导弹时间协同需求,开展耗尽关机的弹道飞行时间控制算法研究,设计了一种可以满足固体弹道导弹中段时间协同的飞行时间控制方法。通过设计导弹增速方向交替变换规律实现固体发动机能量管理,推导了能量管理对终端状态造成耦合影响的相关速度与位置解析式,并采用修正补偿的思路设计了相应的制导律,对能量管理造成的耦合影响进行了修正补偿,使导弹发动机关机时刻速度矢量与位置矢量达到满足飞行时间约束与位置约束的零控状态。仿真结果表明,该算法可以有效地降低能量管理造成的耦合影响且保持较高的时间控制精度,并满足多枚固体弹道导弹在大气层外的时间协同需求。

Considering the characteristics that the thrust of solid ballistic missile engine cannot be adjusted and passive shutdown,the research on multi-missile time coordination flight time control method of depletion shutdown is carried out to meet the related requirements outside the atmosphere.A guidance method that can meet the midcourse time coordination of solid ballistic missiles is proposed.The energy management is realized by designing the alternating transformation law of missile velocity increasing direction,and the analytical equation of velocity and position related to the coupling effect of energy management on the terminal state is derived.Moreover,the coupling effect is corrected and compensated by a designed guidance law,so that the velocity vector and position vector at the shutdown time of each missile engine can reach the zero control state that meets the time coordination of multiple missiles.The simulation results show that the coupling effect caused by energy management is reduced effectively,and a high time constraint accuracy is maintained to meet the time coordination requirements of multiple solid ballistic missiles outside the atmosphere.