超高温热管的热防护试验验证与数值分析  

Experimental and Numerical Analysis on Ultra-high Temperature Heat Pipes Thermal Protection

作　　者：初敏 陈思员[1] 胡龙飞[1] 韩海涛[1] 陈亮[1] 艾邦成[1] CHU Min;CHEN Siyuan;HU Longfei;HAN Haitao;CHEN Liang;AI Bangcheng(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：《兵器装备工程学报》2018年第3期20-24,共5页Journal of Ordnance Equipment Engineering

摘　　要：为深入研究高超声速飞行器尖前缘部位的热防护问题,开展了铌合金-锂工质超高温热管的地面电弧风洞考核试验,并通过简化数值分析模型,对其传热能力及在不同飞行状态下的有效性进行了分析。试验结果表明,铌合金-锂工质超高温热管可有效提升尖前缘部位的防热安全性,数值结果显示其有效导热率可达1 500 W/mK。在30km、Ma7-10范围内,铌合金-锂工质超高温热管可使前缘驻点温度下降19%左右,最大温差明显下降,结构热应力显著降低,使铌合金材质的尖前缘结构可应用于更高飞行状态。In order to study the thermal protection for sharp leading edges of hypersonic vehicles,arc heated wind tunnel tests were carried out on Nb-based/lithium ultra-high temperature heat pipes.A simple numerical analysis model was established.The heat transfer performance of the ultra-high temperature heat pipe and its effectiveness under different flight conditions were analyzed.The experimental results show that Nb-based/lithium ultra-high temperature heat pipes can effectively improve the thermal protection safety.The numerical results show that the equivalent thermal conductivity of the ultra-high temperature heat pipe is up to 1 500 W/mK.When the flight conditions are 30 km,Ma7-10,the stagnation point temperature decreases by about 19%and the maximum temperature difference decreases significantly.It means the thermal stress reduces significantly and the leading edge made by niobium alloy can be applied to higher flight status.

关 键 词：超高温热管 高超声速飞行器 尖前缘 热防护 

分 类 号：TJ01[兵器科学与技术—兵器发射理论与技术]