基于腔体热管的高超声速翼前缘热防护  

Thermal Protection of Leading Edge of Hypersonic Wings Based on Cavity Heat Pipes

作　　者：王焕光[1] 曲伟[2] 淮秀兰[3] 

机构地区：[1]中国矿业大学电力工程学院,徐州221116 [2]中国航天空气动力技术研究院,北京100074 [3]中国科学院工程热物理研究所,北京100190

出　　处：《工程热物理学报》2015年第10期2267-2270,共4页Journal of Engineering Thermophysics

基　　金：中央高校基本科研业务费专项资金(No.2014QNB07)

摘　　要：针对高超声速飞行翼的气动加热现象,提出了一种基于热管的半主动式热防护方案。该热管为一种楔形腔体热管,工质为碱金属锂。为简化计算,将整个过程解耦为对流区、导热区和气动加热区三个部分。对于对流区,本文采用了文献中提出的"热短路"处理方法,即假设壳体内壁面温度处处相等。对于气动加热区,简化为两段:均匀加热段和均匀散热段,并求出了壳体的温度分布。计算结果表明,温度梯度主要集中在前缘,而在6 MW/m^2的热流下,整个结构的最大温差仅为500 K。热管的存在极大地改变了热流通路,使热流由平行于壁面变成垂直于壁面,从而使热阻大为降低。由于高温区域非常集中,腔体式热管可以大幅节省耐高温材料。A semi-active thermal protection scheme based on heat pipes was proposed for the aerodynamic heating phenomenon facing hypersonic wings,in which the heat pipe used is characterized with wedge-shaped cavity,with the working fluid being the alkali metal-lithium.In order to simplify the calculation,the entire process was decoupled into three parts：the convection region,the conduction region and the aerodynamic region.For convection region,it is treated adopting the theory of ＂thermal short-circuit＂ effect,that is,the inner wall temperature of the shell is deemed as homogenous.For the aerodynamic region,it is simplified into two sections：the homogenous heating section and the homogenous cooling section,thus the temperature distribution within the shell was obtained.The calculation result shows that the temperature gradient is mainly concentrated on the leading edge,and under the heat flux of G MW/m2,the maximum temperature difference within the whole structure is just 500 K.The existence of heat pipe greatly shifted the heat flux path,from parallel to the shell wall to perpendicular to the wall,so that the thermal resistance was greatly reduced.As the high temperature region is very concentrated,cavity heat pipe can significantly save high temperature materials.

关 键 词：腔体热管 热短路效应 气动加热 高超声速 热防护 

分 类 号：TK124[动力工程及工程热物理—工程热物理]