摘要
可重复使用的空天飞行器再入过程中关键热结构的热分析可为结构设计、选材等提供参考依据。本文针对全C/SiC复合材料襟翼结构,考虑传导与辐射耦合换热,建立了其再入过程热分析的有限元模型。由有限元计算结果的分析发现:辐射换热在整个温度场中起主导作用,并且对于采用防热-结构一体化设计的可重复使用的空天飞行器,C/SiC是比较理想的结构材料。
The thermal analysis of the primary hot structure is necessary to the structure design and material selection for re-entry space vehicle. The finite element model, considering the coupled conduction-radiation heat transfer, was established for the thermal analysis of the all-ceramic body flap. It is found that the radiation heat transfer has dominant influence on the temperature distribution. It could be conclude that the carbon fiber reinforced silicon carbide （C/SiC） is an ideal material for the primary hot structure of re-entry space vehicle.
出处
《强度与环境》
2006年第2期17-22,共6页
Structure & Environment Engineering
基金
航空基金(04B53012)
国家自然科学基金(10372081)
关键词
空天飞行器
热分析
有限元
辐射
C/SIC
re-entry space vehicle
thermal analysis
finite element
radiation
C/SiC
