前缘一体化高温热管结构防热效果的实验研究

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。 

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

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.