摘要
高温合金前缘热防护结构由高温合金蜂窝和隔热毡、连接件构成,同时具有承载和隔热作用,易于拆卸和维修,具有经济性和安全性。通过分析高温合金前缘热防护结构隔热性能和承载能力,对前缘结构进行设计。高温合金蜂窝隔热效果良好,并可以承受1 200℃高温。隔热毡所用的隔热材料在高温试验下保持良好的隔热效果,验证了本文传热分析方法的正确性。建立了传热迭代分析算例,确认结构各项参数满足某型高速临近空间飞行器的热环境和承载使用要求,完成了前缘结构隔热一体化初步设计。
Leading edge using metallic thermal protection system consists of super alloy honeycomb and thermal insulation felt,duct fastening,which has the function of loading and thermal insulation capacity.The leading edge is easy to be disassembled and maintained,with economic efficiency and safety.The leading edge's loading and thermal insulation capacity are analyzed,then the final structure design is obtained.Super alloy honeycomb has good thermal insulation effect,and has high temperature resistance at 1 200℃.The material of thermal insulation felt maintains excellent thermal insulation effect in high temperature test,so the correctness of heat transfer analysis method is verified.By modeling local heat transfer analysis structure,the leading edge design parameters can be iteratively fixed to achieve the leading edge structure-thermal integrative design.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2016年第S1期53-58,共6页
Acta Aeronautica et Astronautica Sinica
关键词
高温合金
前缘
热防护
隔热
结构隔热一体化设计
super alloy
leading edge
thermal protection
thermal insulation
structure-thermal integrative design
