为了抑制甚至消除陀螺不稳定性以提高旋转弹箭的飞行稳定性和命中精度,采用耦合求解URANS方程和刚体运动方程组对M852弹丸和BasicFinner导弹模型进行了虚拟飞行的数值仿真,计算结果与试验结果吻合。不同的初始偏航角对M852子弹俯仰/偏航的周期影响不大,但初始偏航角越大,运动幅值越大,横向偏移越大,速度降低越快;对于低速旋转的BasicFinner模型,不同发射速度飞行特性差异较大,体现在速度演化、位移波动和锥动幅度等方面。

In order to suppress or eliminate gyro instability to improve the flight stability and hit accuracy of spinning projectile, the numerical simulation of virtual flight of M852 projectile and Basic Finner missile model was carried out by using coupled URANS equation and rigid motion equations. The computation results fitted well with the test results. Different initial yaw angle had little effect on the pitching / yaw cycle of M852 bullet, but the larger the initial yaw angle was, the larger the motion amplitude, and the larger the lateral deviation, the faster the speed decreased. For Basic Finner model with low speed rotation, the flight characteristics of different emission velocities were different, and it was embodied in the aspect of velocity evolution, displacement fluctuation and cone amplitude, etc..