航天器环境工程2013，Vol.30Issue(1)：1-7,7.DOI:10.3969/j.issn.1673-1379.2013.01.001
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
谢宗蕻 1孙俊峰1
作者信息
- 1. 西北工业大学航天学院先进结构与复合材料实验室,西安710072
- 折叠
摘要
Abstract
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.
关键词
半主动金属热防护系统/热管/翼面前缘/高超声速飞行器Key words
semi-active metallic thermal protection system/ heat pipes/ leading edge/ hypersonic vehicle分类
航空航天引用本文复制引用
谢宗蕻,孙俊峰..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[J].航天器环境工程,2013,30(1):1-7,7.
