导弹高空级间分离过程反向喷流流场数值模拟研究

Numerical simulation research of high altitude reverse jet flow for stage separation of missile

采用有限体积法求解三维守恒N-S方程组,按准静态处理,对导弹130km高空头体级间分离过程反向喷流流场进行了数值模拟,并分析了N-S方程的有效性。分析了流场参数分布、气动力分布特性及轴向力随分离距离变化情况。计算结果为头体分离方案提供一定的参考依据。

With the applying of finite volume method and quasi-static state idea, the numerical simulation research of reverse jet flow in the course of stage separation of missile at an altitude of 130kin has been done. The validity of N-S equations, the distribution of flow parameters and aerodynamic force and the relation between axial force and separation distance have been analyzed. The results can be a reference for the project of head-body separation.