Abstract: A design of stage separation of multi stage rocket is discussed Detailed numerical investigation of the interaction between an engine jet and the supersonic external flow was preformed for several models Numerical predication of the flow was obtained using an existing 3 D TLA N S computational technique The flow structures for different models of the design were compared,the results show the model with inducing holes is better The drag on the aft body changed nonlinerly with different separation distance The result can provide basis for the design of the stage separation part

Key words: Multistage rocket;Stage separation;Jet flow;Numerical simulation;Navier Stokes equation

摘要： 针对某型号研制提出一种级间分离设计方案 ,从三维薄层近似N S方程出发 ,对多级火箭级间分离发动机喷流与超声速外流形成的复杂流动进行了数值模拟 ,比较了栅栏构架和排焰孔两种设计方案级间段流场 ,从流动形态分析三维排焰孔模型更为稳定。研究给出不同分离距离下火箭的轴向力系数 ,发现在较近分离距离内 ,后体受到的作用力随距离不是单调减小 ,与分离喷流参数有密切关系。计算结果可作为分离段设计的参考

关键词: 多级火箭;级间分离;射流;数值仿真;纳维尔-斯托克斯方程