子弹头部对亚音速气动特征影响数值模拟

Numerical Simulation of Influence of Submunition Nose on Aerodynamic Characteristics under Subsonic Speed

文中根据子弹气动理论对子弹外形进行了气动优化讨论。针对带药型罩子弹药可能使用的头部外形,对子弹药简化模型进行了CFD计算和风洞测试。根据计算分析结果认为:内凹、平面、外凸三种子弹头部外形对子弹气动特性的影响集中表现在子弹的阻力系数中,其对子弹升力、偏航力、阻心位置的影响较小,附于子弹侧壁的小尺寸目标探测器导致的不对称性对子弹气动特征影响较小,不带尾翼子弹阻心位置比较靠前端,这可能影响子弹飞行稳定性要求。提出增加尾翼稳定装置来保证飞行稳定。

For improving the attacking effect on spot and line goal, the figure of submunition was optimized by the theory of gas dynamics. Focused on different nose figures used in the shaped charge warhead and the target discrimination unit on side wall, the model was computed by CFD and tested by wind tunnel facilities. Except the drag coefficient, the aerodynamic response to different nose figure model was simulated. The simulation results show that the target discrimination unit has little contribution in the aerodynamic force. The pressure centre is near to the front of the submunition, so it may be unstable in the trajectory. Based on the result, the shaped charge submunition which has a target discrimination unit on side wall can satisfy the aerodynamic consistency without canceling target discrimination unit and adding wind cap, but an empennage should be added to keep the stability in the trajectory.