磁浮飞行风洞试验技术及应用需求分析

倪章松; 张军; 符澄; 王邦毅; 李宇

doi:10.7638/kqdlxxb-2021.0206

磁浮飞行风洞试验技术及应用需求分析

doi: 10.7638/kqdlxxb-2021.0206

倪章松^1,,
张军^1, ,,
符澄²,
王邦毅¹,
李宇¹

1.
成都流体动力创新中心，成都　610072
2.
中国空气动力研究与发展中心设备设计与测试技术研究所，绵阳　621000

基金项目: 国家重点研发计划（2020YFA0710901）

详细信息

作者简介:
倪章松（1973-），男，安徽太湖人，正高级工程师，研究方向：低速实验流体力学,结冰空气动力学. E-mail：nzscczx@163.com

通讯作者:
张军^*，副研究员，研究方向：飞行器、地面高速交通气动噪声产生机理与控制方法. E-mail：jzhang@nudt.edu.cn

中图分类号: TB79
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- 文章访问数: 820
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- 被引次数: 0
出版历程
- 收稿日期: 2021-08-15
- 修回日期: 2021-10-14
- 录用日期: 2021-10-20
- 网络出版日期: 2021-10-25
- 刊出日期: 2021-11-05

Analyses of the test techniques and applications of maglev flight tunnels

NI Zhangsong^1
,,
ZHANG Jun^{1
, ,},
FU Cheng²,
WANG Bangyi¹,
LI Yu¹

1.
Chengdu Fluid Dynamics Innovation Center, Chengdu　610072, China
2.
Institute of Equipment Design and Test Technology of China Aerodynamics Research and Development Center, Mianyang　621000, China

摘要

摘要: 随着高速、超高速轨道交通的快速发展，需要发展新型的风洞设备，实现风洞性能和试验能力的突破。磁浮飞行风洞是利用真空管道列车概念结合动模型试验技术提出的一种新概念风洞设备，可以构建出更加接近真实状态的测试环境。本文从磁浮飞行风洞基本概念、国内外研究现状及发展趋势、试验技术、应用需求等几个方面开展论述。首先论述了国内外传统风洞和动模型设备的现状及发展趋势，指出了发展磁浮飞行风洞的必要性；其次，重点对磁浮飞行风洞需要发展的试验技术进行了分析；最后，对磁浮飞行风洞在超高速轨道交通及其他领域的应用需求进行了展望。
- 磁悬浮 /
- 电磁推进 /
- 飞行风洞 /
- 试验技术 /
- 高速轨道交通
Abstract: With the rapid development of high-speed and ultra-high-speed rail transportation, it is necessary to develop new wind tunnel equipment to achieve breakthroughs in the performance and test capabilities of wind tunnels. The maglev flight tunnel, which is a new concept combining vacuum pipeline train and the dynamic model test technology, can construct a test environment closer to the real state. This paper discusses basic concepts of the maglev flight tunnel, the research status and the development trend, as well as test techniques and application requirements. Firstly, the current status and development trend of traditional wind tunnels and dynamic model equipment are introduced, and the necessity of developing maglev flight tunnels is pointed out. Secondly, test techniques need to be developed in maglev flight tunnels are analyzed. Finally, perspectives on the application requirements of maglev flying wind tunnels in the field of ultra-high-speed rail transit and other fields are proposed.
- magnetic levitation /
- electromagnetic propulsion /
- flying tunnel /
- test technology /
- high-speed rail transit

HTML全文

图 1 600 km/h高速磁浮下线^[1]

Figure 1. A 600 km/h high-speed maglev train^[1]

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图 2 美国霍洛曼空军基地火箭橇滑轨^[19]

Figure 2. The rocket sled at Holloman Air Force Base^[19]

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图 3 德国宇航中心TSG平台隧道试验^[30]

Figure 3. TSG platform at the German Aerospace Center^[30]

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图 4 气动活塞牵引加速方法^[32]

Figure 4. An accelerator using air piston^[32]

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图 5 中南大学列车动模型试验装置^[33]

Figure 5. Train-model test device at Central South University^[33]

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图 6 美国HiLiFT高升力飞行风洞概念图^[36]

Figure 6. A conceptual sketch of HiLiFT ^[36]

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图 7 Hyperloop全尺寸真空管道^[37]

Figure 7. A full-size vacuum pipe of Hyperloop^[37]

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图 8 高温超导磁悬浮试验平台^[41]

Figure 8. A high temperature superconducting maglev test platform ^[41]

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图 9 F-P光纤应变计原理图^[48]

Figure 9. A sketch of the F-P optical fiber strain gauge^[48]

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图 10 光束干涉现象^[49]

Figure 10. A sketch of the optical fiber interference phenomenon^[49]

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图 11 基于F-P应变计的光纤天平^[49]

Figure 11. An optical fiber balance based on F-P strain gauge^[49]

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图 12 PIV测量原理图^[54]

Figure 12. A sketch of the PIV measurement^[54]

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图 13 MEMS传感器^[56]

Figure 13. A MEMS sensor^[56]

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图 14 半球油膜法流显图^[59]

Figure 14. A flow field displayed by the hemispherical oil film method^[59]

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图 15 纹影法原理图^[66]

Figure 15. A sketch of the schlieren method^[66]

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图 16 纹影法测量图^[67]

Figure 16. Flow visualizations by the schlieren method^[67]

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图 17 NASA 太空发射系统载人飞船瞬态压敏漆测试图^[69]

Figure 17. A SLS crew vehicle painted with uPSP^[69]

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图 18 高速列车车内外气动噪声测试^[71]

Figure 18. Noise measurements inside and outside a high-speed train ^[71]

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图 19 CRH-0503标准动车组420 km会车试验^[81]

Figure 19. A passing test of CRH-0503 standard EMU with a relative velocity 840 km/h^[81]

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图 20 地面效应中的气动干扰示意^[84]

Figure 20. A sketch of aerodynamic interference induced by the ground effect^[84]

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图 21 美国NFAC风洞开展的全尺寸火星降落伞风洞试验^[88]

Figure 21. A full-scale Mars parachute test in the NFAC (National Full-Scale Aerodynamics Complex) wind tunnel^[88]

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表 1 国外部分引导性动模型风洞及试验平台参数

Table 1. Parameters of foreign moving-model wind tunnels

所属机构	布置方式	尺寸/m	弹射方式	模型缩比	最高速度 /(km·h^–1)
伯明翰大学铁路研究与教育中心	双向复线布置	全长150 测试段50	橡筋弹射	1∶25	270
日本Kobayasi物理研究所	单向轨道布置	全长61 测试段35 加速段10	压缩空气炮弹射	1∶30	500
德国宇航中心哥根廷隧道试验平台	单向轨道布置	全长60 隧道段8	液压驱动弹射	1∶25	360
韩国建筑技术研究院	单向轨道布置	全长39 测试段33	电动机带传动弹射	1∶20	10.8

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表 2 国内部分引导性动模型风洞及试验平台参数

Table 2. Parameters of domestic moving-model wind tunnels

所属机构	布置方式	尺寸/m	弹射方式	模型缩比	最高速度 /(km·h^–1)
西南交通大学试验中心	环形单轨道布置	全长20 直径6.5	压缩空气	1∶80	360
中国科学院力学研究所	单向轨道布置	全长180 测试段50	压缩空气	1∶8	400
中南大学高速列车研究中心	双向复线布置	全长164 测试段60 加速段52	橡筋弹射	1∶20	500

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