为解决鸭式布局双旋弹控制飞行时的飞行稳定性问题,基于建立的七自由度刚体运动模型,推导得到该弹的攻角运动微分方程、陀螺稳定性、动态稳定性与追随稳定性判据,对其弹道特性和运动稳定性进行子数值计算与分析。结果表明,鸭舵启控时刻与最大舵偏角对控制通道的修正效果影响较大,同时会引起其他通道的附带控制偏差;过大的舵偏角会引起攻角发散,破坏飞行稳定;鸭舵启动控制后,得益于后体高速旋转,攻角剧烈震荡但不发散,高转速、低初速和小静力矩系数是鸭式布局双旋弹维持陀螺稳定性和动态稳定性的必要条件;增大升阻比有利于保证弹体的动态稳定性。

In order to solve the problem of flight stability of the projectiles equipped with canards in controlled flight, based on the established seven degree of freedom rigid body motion model, the differential equation of attack angle motion, gyro stability, dynamic stability and following stability criteria of the projectile are derived, and its ballistic characteristics and kinematic stability are calculated numerically and analyzed. The results show that the time to start control and the maximum rudder deflection angle have a great influence on the correction effect of the control channel, and will cause the incidental control deviation of other channels. Excessive rudder deflection causes angle of attack divergence and destroys flight stability. After the canards control was started, thanks to the high-speed rotation of the rear body, the angle of attack oscillates violently but do not diverge. High speed, low initial velocity and small static moment coefficient are the necessary conditions for the projectile to maintain gyro stability and dynamic stability. Increasing the lift drag ratio is helpful to ensure the dynamic stability of the projectile.