脉冲推力矢量控制方法及对导弹弹道的影响

Impulsive Thrust Vector Control Method and Its Effect on Missile Trajectory

针对固定倾角发射的防空导弹,建立了发射段纵平面内弹道数学模型;研究了脉冲推力矢量控制对弹道转弯特性的影响,并结合实际作战过程,利用数值方法给出了一种控制参数确定算法,该算法具有较好的工程可实现性。最后分析了脉冲推力矢量控制对导弹弹道的影响。仿真结果表明,该控制方法能扩大导弹的作战空域,减小中段飞行侧向过载,较好地消除中、末交班目标视线转率,对提高拦截精度有重要意义。

The air defense missile with a fixed launching tilt angle was investigated. Based on mathematical models in a launch-phase, the effect that impulsive thrust vector control did on trajectory property was studied. According to the practical course of battle, a feasible parameter determination algorithm of the control was also given by numerical methods. Finally, the effect on missile trajectory was analysed. Simulation results showed that this impulsive thrust vector control could enlarge the battle sky, decrease the lateral overload of midcourse flight, greatly eliminate the initial target line-of-sight rotating rate of terminal guidance and increase the intercept precision.