摘要
在分析尖化前缘热环境特性的基础上,给出了尖化前缘相应的热结构特性的计算和分析,分析结果表明：尖化前缘热流密度在2～3个自由程内下降到原来的1/3,而表面温度仅有10%的下降;高热导率的防热材料可降低前缘的最高表面温度,对非烧蚀热防护十分有利,它还可提高后部的表面温度,增加辐射散热的力度,这是非烧蚀热防护的重要机制.
According to the analysis of aeroheating property for sharp leading edge, the thermal structure property is calculated and analyzed. The analysis results show that heat flux is decreased to one third of that on stagnation, but the surface temperature is only decreased by 10% at 2 - 3 mean free path distance. The maximum surface temperature of sharp leading edges can be decreased and sureface temperature of rear regions can be increased for high thermal conductivity materials. This is an important therrmal protection mechanism for non-ablation thermal protection.
出处
《宇航材料工艺》
CAS
CSCD
北大核心
2007年第4期8-11,共4页
Aerospace Materials & Technology
基金
国家自然科学基金资助项目(90505015)
关键词
高超声速飞行器
尖化前缘
热结构
Spacecraft, Sharp leading edge, Thermal structure
