| 高超声速飞行器主动气膜冷却热防护数值仿真研究 |
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| 引用本文： | 郭春海,张文武,向树红,张敏捷,童靖宇.高超声速飞行器主动气膜冷却热防护数值仿真研究[J].航天器环境工程,2017,34(2):132-137. |
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| 作者姓名： | 郭春海 张文武 向树红 张敏捷 童靖宇 |
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| 作者单位： | 中国科学院 宁波材料技术与工程研究所, 宁波 315201;中国科学院 宁波材料技术与工程研究所, 宁波 315201;北京卫星环境工程研究所 可靠性与环境工程技术重点实验室, 北京 100094;北京卫星环境工程研究所 可靠性与环境工程技术重点实验室, 北京 100094;北京卫星环境工程研究所 可靠性与环境工程技术重点实验室, 北京 100094 |
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| 基金项目： | 可靠性与环境工程技术重点实验室开放基金；宁波市自然科学基金（编号：2015A610102；2015A610105） |
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| 摘 要： | 为研究高超声速飞行器头部全覆盖保护情况下的气动热分布特征,文章提出一种微孔射流的主动气膜热防护方案,并对射流微孔分布进行优化;通过数值求解N-S方程,得到高超声速飞行器头部的驻点压力及表面、附近温度分布。研究结果表明,在主动气膜冷却热防护下,高超声速飞行器壁面温度可以降到1000 K以下。该方案可为未来高超声速飞行器的外壳设计提供参考。
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| 关 键 词： | 高超声速 微孔射流 气膜冷却 数值模拟 |
| 收稿时间： | 2016/10/24 0:00:00 |
| 修稿时间： | 2017/3/5 0:00:00 |
Numerical simulation of hypersonic vehicle thermal protection with active film cooling |
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| GUO Chunhai,ZHANG Wenwu,XIANG Shuhong,ZHANG Minjie and TONG Jingyu.Numerical simulation of hypersonic vehicle thermal protection with active film cooling[J].Spacecraft Environment Engineering,2017,34(2):132-137. |
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| Authors: | GUO Chunhai ZHANG Wenwu XIANG Shuhong ZHANG Minjie and TONG Jingyu |
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| Institution: | Ningbo Institute of Materials Technology and Engineering, Chinese Academy of Sciences, Ningbo 315201, China;Ningbo Institute of Materials Technology and Engineering, Chinese Academy of Sciences, Ningbo 315201, China;Science and Technology on Reliability and Environmental Engineering Laboratory, Beijing Institute of Spacecraft Environment Engineering, Beijing 100094, China;Science and Technology on Reliability and Environmental Engineering Laboratory, Beijing Institute of Spacecraft Environment Engineering, Beijing 100094, China;Science and Technology on Reliability and Environmental Engineering Laboratory, Beijing Institute of Spacecraft Environment Engineering, Beijing 100094, China |
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| Abstract: | For studying the thermal distribution on the hypersonic vehicle head in the case of full cover protection, this paper proposes a thermal protection scheme with the active film cooling based on micro jet, and an optimization of the distribution of the film holes. By solving the Navier-Stokes equations, the hypersonic stagnation pressure and the surface temperature distribution of the vehicle front are obtained. It is shown that the temperature at the wall of the hypersonic vehicle could be below 1000 K under the active thermal protection. This scheme provides a new idea for the future hypersonic vehicle design. |
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| Keywords: | hypersonic micro jet film-cooling numerical simulation |
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