带微型扰流片旋转稳定弹气动特性分析

为了分析并定量描述微型扰流片在旋转稳定弹上的应用效果,采用计算流体力学方法,对带微型扰流片的旋转稳定弹在不同马赫数下的流场进行研究。通过分析扰流片和弹体表面压力分布,讨论了扰流片尺寸变化对扰流效果的影响,得出了扰流片轴向力系数、法向力系数及静力矩系数随外形参数的变化规律。结果表明:采用扰流片作为气动执行机构能产生较大的操纵力,其附加法向力方向与弹体攻角方向相同; 增加扰流片面积能有效提高弹丸的升阻比; 法向力系数、静力矩系数与扰流片高度呈良好的线性关系,该线性关系在超声速下更为明显。

Aerodynamic Characteristics of a Spin-stabilized ProjectileEquipped With Microspoiler

To analyze and quantitatively describe the application effect of the microspoiler on the spin-stabilized projectile,the flow field of the spin-stabilized projectile equipped with microspoiler was studied under different Mach number by using the computational fluid dynamics method. Based on the analysis of the pressure distribution on the surface of spoiler and projectile,the influence of the size change of the spoiler on the disturbing effect was discussed,and the change rules of axial force coefficient,normal force coefficient and static moment coefficient of the spoiler with its shape were obtained. The results show that the use of spoiler as the control actuator can produce considerable control force. The direction of the additional normal force is the same as the angle of attack.By increasing the area of the spoiler,the lift drag ratio of the projectile can be effectively improved. The normal force coefficient and static moment coefficient have a good linear relation with the height of spoiler,and the linear relation is more obvious at supersonic speed.