某尾翼式火箭增程迫弹飞行失稳原因分析

Flying Unstability Research of Tail-type Extended Range shell

针对某尾翼式火箭增程迫弹弹道飞行失稳的现象,建立了火箭增程迫弹的六自由度弹道模型,仿真分析了该弹丸的摆动角变化规律、全弹道静稳定度、动态稳定度,共振转速、平衡转速等,最终确定共振为该弹飞行失稳的主要原因。为避免弹丸共振的产生,研究确定了该弹的最佳转速范围,通过最大射程及密集度试验结果表明平衡转速为8r^10r时,发动机作用对弹丸飞行影响较小,密集度最好。

Aimming at the unstable problem during the development process of tail-type extended range shell, six DOF trajectory-model of Extended Range shell is established, swing angle variation of projectile, the whole trajectorry of static stability, dynamic stability, critical speed, balancing speed is analysis by simulation. last the resonance is found which is main reasonof the instability flying bomb. In order to avoid the resonance, the optimal speed range of missile is being research, experimentshows that when the balance of speed is 8r-10r, the role of flight engine has little effect on projectile.