前缘一体化高温热管结构防热效果的实验研究  

Experimental Study on the Thermal Protection Effect of the Leading Edge Integrated High-Temperature Heat Pipe Structure

作　　者：朱晓军 刘祥[1] 李锋[1] 欧东斌[1] 陈连忠[1] ZHU Xiao-jun;LIU Xiang;LI Feng;OU Dong-bin;CHEN Lian-zhong(China Academy of Aerospace Aerodynamics,Beijing 100074,China)

机构地区：[1]中国航天空气动力技术研究院,北京100074

出　　处：《气体物理》2022年第5期78-88,共11页Physics of Gases

摘　　要：为了研究复杂构型前缘一体化高温热管结构在高热流密度状态下的防热效果,设计了飞行器气动加热轨道,实现了高温热管低状态完全启动、高状态极限考核。然后采用超声速电弧风洞驻点自由射流结合轨道模拟技术,模拟乘波体飞行器的前缘疏导构件的气动加热环境,开展了前缘一体化高温热管结构防热效果研究。实验结果表明,一体化高温热管结构能够多次使用,低状态下高温热管的启动时间约为115 s,在高状态下结构依然有效,降温系数达到24.5%,验证了前缘疏导式防热结构的防热效果,可为未来新型高超声速飞行器非烧蚀热防护系统的设计提供指导。In order to study the thermal protection effect of the integrated high-temperature heat pipe structure with a complex leading edge under high heat flux,the aerodynamic heating track of the aircraft was designed to realize the complete start-up of high-temperature heat pipe in a low state and the limit assessment in a high state.The stagnation point free jet in the supersonic arc wind tunnel combined with orbital simulation technology was used to simulate the aerodynamic heating environment of the leading-edge dredging component of the wave-riding vehicle.The thermal protection effect of the integrated high-temperature heat pipe structure was investigated.The experimental results show that the integrated high-temperature heat pipe structure is reusable.The startup time of the high-temperature heat pipe is about 115 s in a low state,and the structure is still effective in a high state,with a cooling coefficient of 24.5%.The results verify the thermal protection effect of the heat-pipe-cooled leading edge thermal protection structure,which can provide guidance for the design of the non-ablation thermal protection system of the new hypersonic aircraft in the future.

关 键 词：一体化高温热管 防热效果 电弧风洞 气动加热 非烧蚀 

分 类 号：V416[航空宇航科学与技术—航空宇航推进理论与工程]