摘要
针对多级火箭级间热分离这一复杂环境条件下的级间段流场进行了数值研究。计算采用AUSM+有限体积格式,针对相应的流场假设,分别求解了非定常轴对称和非定常三维Faver平均的Navier-Stokes方程。两种计算结果的比较表明,由级间排气口的分布而引起的三维效应主要集中在喷管与火箭外壳所围成的空腔内部,而喷管内部由于流速很高,排气口带来的三维效应对管内上游流动影响很小。计算结果可为级间分离段和发动机热防护的设计提供参考。
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.
出处
《推进技术》
EI
CAS
CSCD
北大核心
2007年第2期113-117,共5页
Journal of Propulsion Technology
关键词
多级火箭
级间分离
数值仿真
Multistage rocket
Stage separation
Numerical simulation
