航天发射火箭尾焰冲击流场三维数值研究

航天发射时火箭燃烧尾焰冲击干扰效应对发射稳定性和发射架、导流槽等地面设施有重要影响。采用压力隐式算子分裂算法,通过求解Navier-Stokes方程,对火箭外流场、发动机燃烧室内与尾焰流场进行了一体化三维数值计算。得到了火箭发射后尾焰与地面撞击产生的冲击流场。结果表明:尾焰流场计算模型、方法与结果合理;尾焰冲击干扰效应会大幅提高地面附近的压力和温度。火箭尾焰撞击地面后,高温区出现在离地面一定距离的高温层内,此时地面附近为低速区。尾焰对其正下面的地面区域产生冲击最大,主要干扰区域集中于半径为15 m的圆形区域。

Three-dimensional numerical study of impactive flowfield of liquid rocket exhaust plume while space launching

The impactive and interferential effect of rocket combustion exhaust plume has important influence on launching stability and ground equipments including of rocket launcher and flow channel.Basing on PISO algorithm,three-dimensional numerical simulation both of plume flow field of hydrogen-oxygen liquid rocket and outside flow field of rocket is conducted by solving Navier-Stokes equation.The impactive flow field while exhaust plume is impacting ground is obtained.The results show that the physical model,numerical method and flow field data herein are reasonable.The pressure and temperature increase greatly because of the impactive and interferential effect of plume.During impacting ground,plume has a high temperature zone appearing in a high temperature level near ground while the velocity in this zone is lower.The most impactive and interferential effect appears in ground area under exhaust plume,and the main interferential zone is focus on a round area with a radius of 15 m.