导弹弹射发射分离轨迹的数值研究

The Numerical Investigation on Separation Track of Missile Ejected from Aircraft

采用弹射方式发射空空导弹会提高对导弹姿态控制的要求。将基于N-S方程求解的流动数值模拟与控制律和求解导弹运动方程相结合,进行机载导弹弹射发射分离轨迹的计算研究。结果表明无控条件下静不稳定导弹在载机干扰流场中姿态发散较快,不利于导弹与载机的安全分离,引入姿态控制后导弹离开载机过程中的姿态变化得到有效控制,提高了导弹弹射发射安全性。

Air-to-air missile launch by ejection puts higher requirement for attitude control of missile. The separation trajectories by which a missile ejected from an aircraft were computed by combination of numerical simulation based on N-S equations solver with motion equations of missile and control law. The computational results show that attitudes of static instable missile are divergent quickly due to aerodynamic interference by the aircraft and it is disadvantageous to missile＇ s separation from aircraft safely. When attitude control strategy has been in- troduced, attitudes of missile during the separation from aircraft are effectively controlled, and security of missile ejected from aircraft is greatly improved.