尾流对超声速导弹后弹体的影响规律

Investigation in the Impact of Rocket Plume on the Aft Missile under Supersonic Condition

针对超声速飞行条件下尾流对轴对称导弹后弹体的影响,采用CFD流场仿真方法,对后弹体在不同飞行状态、落压比、喷管扩张半角及后弹体外形情况下的内外流干扰流场进行了数值计算,研究了发动机尾喷流对后弹体附近压强分布的影响规律。结果表明:尾喷流作用范围随发射高度的增大而增大,随发射马赫数的增大而减小;尾喷流作用范围与落压比呈分段线性关系,与喷管扩张半角呈线性增大关系;后弹体外形对尾喷流作用范围的影响很小。

Aiming at the impact of rocket plume on the axisymmetric aft missile under supersonic condition,the interaction flow field between inner and external flow around aft missile was studied comprehensively under different factors,including flight conditions,nozzle pressure ratio,nozzle expansion cone half angle and the shape of aft missile,using CFD method,and the incidence of the rocket plume was investigated performing as the pressure distribution around the aft missile.The results show that:the effective range of plume enlarges and diminishes with the increase of altitude and Ma respectively;the incidence of plume enhances in a piecewise linear way with the raise of NPR;the incidence of plume linearly grows with the rise of nozzle expansion cone half angle;the shape of aft missile hardly affect the incidence of plume.