固体火箭技术2011，Vol.34Issue(5)：579-583,5.
固体火箭发动机喉衬流场及热结构耦合分析
Coupled fluid, thermal and structural analysis of nozzle inserts in solid rocket motors
张晓光 1王长辉 1刘宇 1任军学1
作者信息
- 1. 北京航空航天大学宇航学院,北京100191
- 折叠
摘要
Abstract
In order to accurately predict the thermal and structural behavior of throat inserts in solid rocket-motor environments, a fluid-thermal-structural coupling model was established based on CFD code FLUENT and FEM code ANSYS. Fully coupled fluid-solid analysis was performed first to simulate the heat transfer and material erosion process, using the method of whole-field discretization and solution in FLUENT. Subsequently, the structural analysis was carried out in ANSYS based on the resulting pressure and thermal loading. In such a procedure, two-way coupling was considered between flow and heat transfer while one-way coupling method was employed in structural analysis. Numerical results show that the convective heat transfer coefficient gradually decreases with increase of wall temperature during the motor firing. The wall temperature and erosion rate follow the trend exhibited by the heat flux distribution, and attain peak at upstream of the throat. The stress is most severe in the throat region due to the steep temperature gradient.关键词
固体火箭发动机/喉衬/流场及热结构耦合/烧蚀Key words
solid rocket motor/throat insert/fluid-thermal-structural coupling/erosion分类
航空航天引用本文复制引用
张晓光,王长辉,刘宇,任军学..固体火箭发动机喉衬流场及热结构耦合分析[J].固体火箭技术,2011,34(5):579-583,5.
