关键词: 多级火箭;级间分离;数值仿真

Abstract: The thermal and flow conditions between two separating stages of a rocket are investigated numerically using finite volume method.The AUSM+ scheme is employed to solve the unsteady axisymmetric three-dimensional Faver-averaged Navier-Stokes equations.The results demonstrated that the effects of the vent deployment on the thermal and flow field are mainly appeared in the chamber surrounded by the rocket shell and the vents.Because the high velocity of the jet in the nozzle,the three dimensional effects caused by the vents have little influence on the flows in the nozzles.This can provide basis for the design of the stage separation part for a rocket and the thermal protection of the engine.

Key words: Multistage rocket;Stage separation;Numerical simulation