高超声速飞行器翼面前缘半主动金属热防护系统设计与分析

Design and analysis of semi-active thermal protection system for the leading edges of hypersonic vehicles

针对高超声速飞行器翼面前缘的热防护,文章设计了一种基于热管的半主动金属热防护系统。设计中使用工程估算方法预测了翼面前缘的气动热环境,并采用有限元法对高温合金翼面前缘结构进行了热固耦合分析和强度考核。分析结果表明:在马赫数为5～8的飞行状态下,热管可以有效地降低高超声速飞行器翼面前缘峰值温度达23%～31%,且呈现飞行马赫数越高则峰值温度降低幅度越大的趋势;同时热管还可以降低翼面前缘结构温差达90%以上,从而极大地减小由于温差而导致的热应变和内部应力。因此,将基于热管的半主动金属热防护系统应用于高超声速飞行器翼面前缘可以真正实现结构防热一体化,有助于获得较好的防热和减重效果。

A semi-active metallic thermal protection system based upon heat pipes is designed for the leading edge structure of a hypersonic vehicle in this paper. The engineering estimation method is adopted to predict the aerodynamic heating environment of the structure. The finite element method is used for the thermal-solid coupling analysis and the strength evaluation. The calculated results show that： for a hypersonic vehicle under a cruise Mach number of 5-8, the peak temperature of the leading edge would reduce 23%-31%, with the use of heat pipes, and the reduction increases with the increase of the Mach number. The maximum temperature difference also decreases by at least 90%, with significantly reduced thermal strain and stress level. Consequently, it is possible to reduce the weight of the structure. The semi-active thermal protection system based upon heat pipes is a promising solution for the leading edges of hypersonic vehicles in terms of both thermal protection and structural efficiency.