Bang-Bang控制方式旋转导弹气动特性数值分析

为研究Bang-Bang控制式鸭舵对旋转导弹气动特性的影响,在CFD软件中采用嵌套网格方法模拟导弹的旋转和鸭舵的偏转,对Bang-Bang控制式旋转导弹在不同攻角、马赫数和转速下的气动特性进行了数值模拟,得到了气动特性变化规律。研究表明,因鸭舵洗流方向的改变,耦合导弹自旋会导致弹体和尾翼的侧向力发生突变。通过与不控鸭舵的旋转导弹进行对比,采用Bang-Bang控制式鸭舵的旋转导弹的周期平均侧向力系数变小,周期平均法向力系数变大。由于侧向力的存在,导弹在一个周期内的合力会偏离竖直方向,合力偏离竖直方向的角度随着马赫数、自旋速率和攻角的增大而减小。

Numerical study on the aerodynamic characteristics of the rotating projectile based on Bang-Bang control method

To study the effect of Bang-Bang controlled canard on aerodynamic characteristics of the rotating projectile, the nested grid in CFD software was used to simulate the spinning of missile and the deflection of canard. By this method, aerodynamic characteristics of the Bang-Bang controlled rotating missile at different angles, Mach numbers and rotation speeds were numerically simulated, and the aerodynamic law of the rotating missile was obtained. The research shows that the immediate change of lateral forces will take place in projectile body and tail fin, due to the variation in canard washing current direction which coupled the missile spin. Compared with those without canard control, the periodic average lateral force coefficient under control decreases, while the normal force coefficient increases. Due to lateral force, the net force in a period deviates from the vertical direction, and the deviation angle of which decreases with the increase of Mach number, spin rate and attack angle.