| 摘要: |
| 对多级火箭级间热分离过程中,一级、二级发动机的分离流场进行了计算,并分析了分离机构 柱形爆炸器表面的热流分布情况;应用分区非结构化网格,进行了二维可压缩湍流流场的数值模拟,在数值计算中应用了k ε湍流模型,并考虑壁面热辐射的辐射传热模型;研究了分离过程中,级间区域的流场特性以及同柱形爆炸器的传热情况,数值结果将有助于级间分离装置的热防护结构设计。 |
| 关键词: 固体推进剂火箭发动机 级间分离 数值仿真 热流计算 |
| DOI： |
| 分类号:V435 |
| 基金项目: |
|
| Numerical simulation of flow field and thermal analysis for stage separation of multistage missile |
|
ZHANG Wen-pu, FENG Zhen-ping
|
|
Inst. of Turbomachinery, Xi’an Jiaotong Univ., Xi’an 710049, China
|
| Abstract: |
| The separation flow field for stage separation of multistage missile was studied by numerical simulation. The heat flow flux on the surface of explosive separational equipment was predicted. The unstructural grid, k-ε turbulence model and heat radiator model were applied to simulation for a unsteady axisymmetric flow field. The result can be helpful to the thermal design of stage separation equipment. |
| Key words: Solid propellant rocket engine Stage separation Numerical simulation Heat flow calculation |
