二维弹道修正弹静态侧向气动特性仿真研究

Static Lateral Aerodynamics Simulation of Two-Dimensional Trajectory Correction Projectiles

为研究差动舵位于攻角平面内时旋转稳定二维弹道修正弹的侧向气动特性,基于雷诺平均Navier-Stokes方程,采用有限体积法、SLAU2计算格式和标准可压SA-noft2湍流模型,建立了一套数值计算方法,并通过M910子母弹对方法进行了验证。通过对不同攻角下"+"形修正组件布局的二维修正弹进行仿真,得到了侧向气动力和力矩随攻角的变化关系,分析了修正组件对局部流动和弹丸表面压力系数分布的影响规律。结果表明,在有攻角的情况下,差动舵能使空气产生侧滑角的效果,形成侧向效应,侧向力和力矩随攻角呈线性关系。静态侧向力矩与动态侧向力矩量级相,方向由迎风区鸭舵造成的偏流所主导。

To study the lateral aerodynamics of a spin stabilized two-dimensional trajectory correction projectiles when differential rudders are in the plane of angle of attack(AOA),a numerical calculation method based on Reynolds-averaged Navier-Stokes(RANS)equations was established with finite volume method,SLAU2 scheme and Spalart-Allmaras One-Equation Model without ft2 Term(SA-noft2).And a model of M910 sub-projectile was used to verify the method.By simulating the two-dimensional trajectory correction projectile with the"+"type layout correction packages under different angles of attack,the relationship between lateral aerodynamic force and moment with the angle of attack is obtained.The effect of local flow which interfered by correction packages and the pressure coefficient on the surface of the projectile were analyzed.The results show that the differential rudder can produce the effect of the sideslip angle,and form a lateral effect.The lateral force and moment are linear with the AOA.The static lateral moment is corresponding to the dynamic lateral moment in magnitude,and the direction is dominated by the bias caused by the rudder in the windward area.