液体火箭燃烧尾焰冲击干扰效应数值研究

火箭发射时其燃烧尾焰的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.文章采用压力隐式算子分裂算法,通过求解 Navier-Stokes 方程,对氢氧液体火箭发动机燃烧室内燃烧过程与尾焰流场进行了一体化数值计算,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度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

Numerical study of impact and interference effect of liquid rocket combustion exhaust plume

The impact and interference effect of the rocket combustion exhaust plume is an important issue related with the launching stability and the ground equipment,including the rocket launcher and the flow channel.Based on the PISO algorithm,numerical simulations of the combustion process and the plume flow field of a hydrogen-oxygen liquid rocket are carried out by solving the Navier-Stokes equation.The impact flow field when the exhaust plume is impacting the ground is obtained.The results show that the physical model,the numerical method and the flow field are reasonable.The pressure and the temperature increase greatly because of the impact and interference effect of the plume.During its impacting ground,in the plume,a high temperature zone appears with a high temperature level near the ground and with low velocities.The most important impact and interference effect shows in the ground area under the exhaust plume,and the main interference zone is in a circular area with a radius of 15 m.