高速飞行器减阻降热研究进展

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doi:10.6052/1000-0992-23-021

潘利生^{1, 2,,},
郝亨隆^{1, 2},
姚子康^{1, 2},
郭媛³,
慕浩凡³,
李敏³,
魏小林^{1, 2}

1.
中国科学院力学研究所高温气体动力学国家重点实验室, 北京 100190
2.
中国科学院大学工程科学学院, 北京 100049
3.
北京建筑大学环境与能源工程学院, 北京 100044

详细信息

作者简介:
潘利生, 中国科学院力学研究所副研究员, 长期从事热能的高效传递、转化与利用研究. 聚焦CO₂热力循环体系, 提出了自冷凝CO₂跨临界动力循环、CO₂跨临界热力循环综合储能系统和飞行器CO₂综合热管理系统. 先后主持国家自然科学基金项目3项、北京市自然科学基金项目1项, 获得授权发明专利20余项, 发表学术论文70余篇

通讯作者:
panlisheng@imech.ac.cn

中图分类号:V37
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- 被引次数:0
出版历程
- 收稿日期:2023-06-20
- 录用日期:2023-12-19
- 网络出版日期:2023-12-22
- 刊出日期:2023-12-30

Current status of research on reducing drag and cooling of high-speed aircraft

PAN Lisheng^{1, 2,,},
HAO Henglong^{1, 2},
YAO Zikang^{1, 2},
GUO Yuan³,
MU Haofan³,
LI Min³,
WEI Xiaolin^{1, 2}

1.
State Key Laboratory of High-temperature Gas Dynamics, Institute of Mechanics, Chinese Academy of Sciences, Beijing 100190, China
2.
School of Environment and Energy Engineering, Beijing University of Civil Engineering and Architecture, Beijing 100049, China
3.
School of Engineering Science, University of Chinese Academy of Science, Beijing 100044, China

More Information

Corresponding author:panlisheng@imech.ac.cn

摘要

摘要:降低飞行阻力、探索更高效的热防护系统是研发高速飞行器过程中至关重要的课题. 目前, 国内外学者在飞行器减阻降热的机理及应用技术方面进行了大量研究, 取得了丰富的成果. 本文系统地梳理了在高速飞行器减阻降热领域的研究进展, 阐述了主动热防护机理的研究结果, 介绍了应用于高速飞行器的前沿减阻降热技术, 并简述了基于余热利用的整体热防护系统的发展情况. 基于对研究现状的分析, 归纳总结了高速飞行器减阻降热技术的发展趋势与实际研究需求; 最后针对这些实际研究需求, 提出了一些研究思路上的建议.
- 飞行器主动冷却技术/
- 主动流动控制/
- 减阻降热/
- 综合热管理系统
Abstract:Reducing flight resistance and exploring more efficient thermal protection systems are crucial issues in the development of high-speed aircraft. Domestic and foreign scholars have conducted extensive research on the mechanism and application technology of aircraft cooling and drag reduction, and have achieved rich results. This article systematically reviews the research progress in the field of cooling and drag reduction for hypersonic aircraft, elaborates on the research results of active thermal protection mechanisms, introduces cooling and drag reduction technologies applied to high-speed aircraft, And briefly described the development of overall thermal protection systems based on waste heat utilization. Based on the analysis of the current research status, the development trend and practical research needs of drag and heat reduction technology for high-speed aircraft were summarized and summarized. Finally, in response to these practical research needs, some suggestions on research ideas were proposed.
- Active cooling technology for aircraft/
- Active control of flow/
- Reduce drag and heat/
- Integrated thermal management system

HTML全文

图 1飞行器气动热(Glass 2008). (a) 前缘热流随飞行速度变化, (b) 马赫数7.8时飞行器各部位温度 (℃)

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图 2二维切向气膜物理模型(Stollery 1965)

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图 3结合可压缩混合层与湍流边界层区物理模型(Kanda et al. 1994)

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图 4主动减阻降热方法(卓长飞等 2014)

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图 5减阻杆头部横向射流纹影图(Jiang et al. 2009)

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图 6逆向射流实验模型(Shang et al. 2001)

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图 7Hyper-X前体吹气模型(Berry et al. 2008)

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图 8不同逆向射流总压比时流场纹影(Sriram & Jagadeesh 2009)

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图 9等离子体逆向喷流实验中球头受控流场演化(马正雪等 2022)

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图 10MHD原理示意图(梁伟等 2021)

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图 11典型主动热防护法示意图

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图 12超燃冲压发动机再生冷却示意图(袁鑫等2017)

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图 13射流预冷工作原理图(陆禹铭 2022)

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图 14前缘发汗冷却结构与液态水发汗冷却实验过程(Wang et al. 2014,Shen et al. 2016)

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图 15综合热管理系统(唐玫等 2022)

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图 16Qin等建立的热能利用系统(Qin et al. 2010)

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图 17带回热的超临界布雷顿循环一体化系统(姜培学等 2021)

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图 18热电发电机制(Cheng et al. 2018)

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图 19新型热管理系统(Guo et al. 2023)

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