| 飞行器尖化前缘的热结构特性 |
| |
| 引用本文： | 姜贵庆%张学军%王淑华%艾邦成%俞继军. 飞行器尖化前缘的热结构特性[J]. 宇航材料工艺, 2007, 37(4): 8-11 |
| |
| 作者姓名： | 姜贵庆%张学军%王淑华%艾邦成%俞继军 |
| |
| 作者单位： | 航天空气动力技术研究院,北京,100074 |
| |
| 摘 要： | 在分析尖化前缘热环境特性的基础上,给出了尖化前缘相应的热结构特性的计算和分析,分析结果表明：尖化前缘热流密度在2～3个自由程内下降到原来的1/3,而表面温度仅有10%的下降;高热导率的防热材料可降低前缘的最高表面温度,对非烧蚀热防护十分有利,它还可提高后部的表面温度,增加辐射散热的力度,这是非烧蚀热防护的重要机制.
|
| 关 键 词： | 高超声速飞行器 尖化前缘 热结构 |
| 修稿时间： | 2006-09-262006-12-25 |
Thermal Structure Properties of Sharp Leading Edges for Spacecraft |
| |
| Jiang Guiqing,Zhang Xuejun,Wang Shuhua,Ai Bangcheng,Yu Jijun. Thermal Structure Properties of Sharp Leading Edges for Spacecraft[J]. Aerospace Materials & Technology, 2007, 37(4): 8-11 |
| |
| Authors: | Jiang Guiqing Zhang Xuejun Wang Shuhua Ai Bangcheng Yu Jijun |
| |
| Affiliation: | China Academy of Aerospace Aerodynamics, Beijing 100074 |
| |
| Abstract: | According to the analysis of aeroheating property for sharp leading edge, the thermal structure property is calculated and analyzed. The analysis results show that heat flux is decreased to one third of that on stagnation, but the surface temperature is only decreased by 10% at 2 - 3 mean free path distance. The maximum surface temperature of sharp leading edges can be decreased and sureface temperature of rear regions can be increased for high thermal conductivity materials. This is an important therrmal protection mechanism for non-ablation thermal protection. |
| |
| Keywords: | Spacecraft Sharp leading edge Thermal structure |
| 本文献已被 CNKI 维普 万方数据 等数据库收录！ |
| 点击此处可从《宇航材料工艺》浏览原始摘要信息 |
|
点击此处可从《宇航材料工艺》下载免费的PDF全文 |
|
