后射空空导弹稳定性问题研究

Study on stability of air-to-air missile in firing-back attack

提出了解决空空导弹后射速度过零姿态角不稳问题的速度快速过零法 .方法的思路是增大加速器推力 ,使速度快速由负变为正 ,使发散的姿态角限制于允许范围内 .进而 ,姿态角扰动因导弹姿态变稳而收敛 .进行了导弹后射姿态角变化动态过程的定性分析 .采用仿真方法 ,定量分析了方法原理上的可行性 ,分析了静态稳定系数、起始攻角扰动、后射速度初值对姿态角运动的影响 .结果证明方法有效 .

A method to solve the instability of an air-to-air missile s attitude angle motion during its velocity pass through zero in case of that the missile fires back was proposed. The idea of the method is to increase the thrust of the missile's booster. It results in that the velocity of the missile transforms from negative into positive quickly, and it constrains the divergent attitude angle of the missile in an allowable margin. The attitude perturbation convergent since the missile's attitude motion becomes stable. The qualitative analysis of the dynamic procedure of the missile's attitude angle changing was made in the same case. The principle feasibility of the method and the effects of steady stability coefficient, initial perturbation of the angle of attack and initial value of back-firing velocity on the missile's attitude motion were analyzed quantitatively by simulation.