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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。
Aiming at the aerodynamic heating of hypersonic flying wing, a semi-active heat protection scheme based on heat pipe is proposed. The heat pipe is a wedge-shaped cavity heat pipe, working fluid is alkali metal lithium. In order to simplify the calculation, the whole process is decoupled into convection zone, heat conduction zone and pneumatic heating zone. For the convection zone, this paper adopts the method of “hot short circuit” proposed in the literature, which means that the temperature of the inner wall of the shell is the same everywhere. For pneumatic heating zone, simplified into two sections: uniform heating section and uniform cooling section, and obtained the shell temperature distribution. The calculation results show that the temperature gradient is mainly concentrated in the leading edge, while the maximum temperature difference of the whole structure is only 500 K at a flow of 6 MW / m 2. The existence of the heat pipe greatly changes the heat flow path so that the heat flow becomes perpendicular to the wall from parallel to the wall, so that the thermal resistance is greatly reduced. Due to the high concentration of the high temperature area, the cavity heat pipe can save a great deal of heat-resistant materials.