| 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。 |
| 关键词: 多级火箭 级间分离 数值仿真 |
| DOI： |
| 分类号:V430 |
| 基金项目: |
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| Numerical simulation of the initial stage flowfields for the stage separation of the multi-stage rocket |
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HUANG Si-yuan,QUAN Xiao-bo,GUO Feng-mei,FU Song
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1.School of Aerospace,Tsinghua Univ.,Beijing 100084,China;2.Beijing Inst.of Space System Engineering,Beijing 100076,China
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| 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 |
