助推器分离过程动态流场数值模拟

Numerical Simulation of Dynamic Flow Field in Booster Detaching Process

利用三维N-S方程,采用NND2M有限差分格式作为数值离散方法,对助推器与上面级分离过程的动态流场进行了数值模拟,分析了反作用推力火箭发动机的喷流对上面级弹体底部轴向作用力的影响。根据计算得到的变化规律发现,在分离距离较小的情况下,反推火箭喷流对上面级弹体的干扰作用明显,产生较大轴向作用力,对于上面级飞行稳定性有影响。

The 3D N-S equations are numerically solved, while NND2M scheme is used for the discrctization of the equations, aimed to simulate the dynamic flow about the process in which booster takes apart from upper stage. The effect that the jet of the counterthrust rocket motor exerts on the axial force on the base of upper stage body is analyzed. The results of the simulation show a law that counter-thrust rocket jet has a great effect on the upper stage body while the distance between them is short, which produces a big axial force doing harm to the flight stability of upper stage.