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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Basic Finner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Basic Finner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 even eliminate the gyro instability and improve the flight stability and hit accuracy of the projectile, the numerical simulation of the M852 projectile and the Basic Finner missile model using the coupled solution of URANS equations and rigid body motion equations was carried out. The test results match. Different initial yaw angles have little effect on the pitch / yaw cycle of the M852. However, the larger the initial yaw angle, the larger the amplitude of movement and the greater the lateral offset, the faster the speed reduction. For the low-rotation Basic Finner Model, different launch speed flight characteristics vary greatly, reflected in the speed of evolution, displacement fluctuations and cone motion amplitude and so on.