弹道导弹飞行时间偏差修正方法

Method for Correcting Flight Time Deviation of Ballistic Missile

为实现弹道导弹精确时间协同作战,需要对出现的飞行时间偏差进行控制。根据摄动理论将飞行时间偏差在末修段预定点展开成速度和位置的线性形式,建立修正飞行时间偏差所需速度增量方程组,求出修正所需速度增量、推力作用时间和方向,利用末修发动机对飞行时间偏差进行修正。仿真计算表明:该方法可有效修正导弹飞行时间偏差。

In order to realize the coordinated operation of ballistic missile, it is necessary to control the flight time deviation. According to perturbation theory, the flight time deviation is expanded into the linear form of velocity and position at the scheduled point of terminal correction phase, and the required velocity increment equations are established to correct the flight time deviation. The flight time deviation is modified by terminal correction thruster based on the required velocity increment, thrust time and di- rection which are derived from the equations. The simulation results show that the method can effectively correct the missile flight time deviation.