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针对高超声速飞行器工作时前缘恶劣的气动加热环境,为了保证飞行器前缘的尖锐外形,提出内嵌高温热管前缘结构.针对热管内部复杂流动与换热情况,对内嵌高温热管前缘结构进行一体化建模,将模型的核心部件液态金属热管工作状况的计算与实验进行对比以验证模型的可靠性.本文还分析了给定工况下内嵌高温热管前缘结构的热防护效果,其中壁面最高温度下降了11.6%,最低温度上升了8%,高温区和低温区均被封闭在前缘外层区域,内层温度更加均匀,实现了热流由高温区向低温区的转移,削弱了高温区的热负荷.本文还分析了接触热阻对热管冷却前缘结构效果的影响.
Aiming at the harsh aerodynamic heating environment of hypersonic vehicle, in order to ensure the sharp shape of aircraft front, the structure of leading edge of high-temperature heat pipe embedded is put forward. In view of the complex flow and heat transfer inside heat pipe, The model of the core components of the liquid metal heat pipe calculations and experiments to verify the reliability of the model.This paper also analyzes the thermal protection effect of the embedded high temperature heat pipe front structure under given conditions, The maximum wall temperature decreased by 11.6% and the minimum temperature increased by 8%. Both the high temperature and the low temperature were enclosed in the outer layer of the front edge, and the temperature of the inner layer was more uniform. The heat transfer from the high temperature zone to the low temperature zone was weakened The heat load in the high temperature zone.This paper also analyzed the impact of contact resistance on the structure of the cooling front of the heat pipe.