仿生撲翼飛行器風洞實驗研究進展

付強; 張祥; 趙民; 張春華; 賀威

doi:10.13374/j.issn2095-9389.2021.04.30.004

仿生撲翼飛行器風洞實驗研究進展

doi: 10.13374/j.issn2095-9389.2021.04.30.004

付強^{1, 2},
張祥^{1, 2},
趙民^{1, 2},
張春華³,
賀威^{1, 2, ,}

1.
北京科技大學自動化學院，北京 100083
2.
北京科技大學人工智能研究院，北京 100083
3.
中國兵器裝備集團自動化研究所有限公司，綿陽 621000

基金項目: 裝備預研教育部聯合基金資助項目（6141A02033339）；北京科技大學青年教師學科交叉研究資助項目（FRF-IDRY-19-010）；國家自然科學基金資助項目（61803025，62073031）

詳細信息

通訊作者:
E-mail: weihe@ieee.org

中圖分類號: TP242.6
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- 被引次數: 0
出版歷程
- 收稿日期: 2021-04-30
- 網絡出版日期: 2021-07-01
- 刊出日期: 2022-04-02

Research progress on the wind tunnel experiment of a bionic flapping-wing aerial vehicle

FU Qiang^{1, 2},
ZHANG Xiang^{1, 2},
ZHAO Min^{1, 2},
ZHANG Chun-hua³,
HE Wei^{1, 2
, ,}

1.
School of Automation and Electrical Engineering, University of Science and Technology Beijing, Beijing 100083, China
2.
Institute of Artificial Intelligence, University of Science and Technology Beijing, Beijing 100083, China
3.
Automation Research Institute Co., Ltd., China South Industries Group Corporation, Mianyang 621000, China

More Information

Corresponding author: E-mail: weihe@ieee.org

摘要

摘要: 仿生撲翼飛行器的設計靈感來源于自然界中的鳥類、昆蟲和蝙蝠的飛行模式，通過機翼的主動運動來產生飛行所需要的升力和推力。仿生撲翼飛行器具有隱蔽性好、機動性強等優點，成為近年來國內外飛行器研究的重點。但是仿生撲翼飛行器研究涉及到低雷諾數、非定常空氣動力學等問題，與常規固定翼飛行器有很大的不同。仿生撲翼飛行器的研究方法一般分三種：氣動計算、風洞實驗和外場試飛。氣動計算方面，非定常氣動設計優化理論與方法目前仍存在不足；外場試飛的方法無法精確測量出飛行器復雜的氣動力，難以對飛行器進行定量分析研究；風洞實驗由于可以模擬飛行時的真實情況，獲得的數據較為真實可靠，且可以定量分析研究，成為目前研究仿生撲翼飛行器非常有效的方法。國內外研究人員利用風洞進行了大量針對仿生撲翼飛行器的實驗研究。在介紹了風洞組成和分類的基礎上，詳細闡述了仿鳥和仿昆蟲撲翼飛行器風洞實驗的研究現狀，最后對仿生撲翼飛行器風洞實驗未來可能的研究方向給出了建議。
- 仿生撲翼飛行器 /
- 風洞實驗 /
- 氣動特性 /
- 翼型設計 /
- 雷諾數
Abstract: “Flapping wing” is a mechanism observed in the flight of birds, insects, and bats. The lift and thrust for a flight are generated by the active movement of wings. It was first specifically designed by Da Vinci. With good concealment and maneuverability advantages, the bionic flapping wing has become the hotspot in the field of aerial vehicles at home and abroad in recent years. Due to its high degree of bionic appearance and ultra-low flight noise, the bionic flapping-wing aerial vehicle has important applications in the military and civilian fields. Because of a low Reynolds number, unsteady aerodynamics, and other issues, such as flexible deformation of the wing and so on, the study of a bionic flapping-wing aerial vehicle is quite different from that of a conventional fixed-wing aerial vehicle. The three methods used in the study of a flapping-wing aerial vehicle are aerodynamic calculations, wind tunnel experiments, and outside flight tests. In terms of aerodynamic calculation, the theory and method of an unsteady aerodynamic design and optimization are still inadequate at present. The outside flight test cannot accurately measure the complex aerodynamic force of the aerial vehicle and cannot conduct quantitative analysis as well as research on the aerial vehicle. As the wind tunnel experiment can simulate a real flight, the data obtained is more reliable, can be analyzed, and studied quantitatively. Therefore, the wind tunnel experiment has become an effective method to study a flapping-wing aerial vehicle. Researchers at home and abroad have conducted several experimental studies on a bionic flapping-wing aerial vehicle using a wind tunnel. This paper first introduced the composition and classification of a wind tunnel and then introduced the research status of the wind tunnel experiment, covering the bird-like and insect-like flapping-wing aerial vehicles in detail. Finally, this paper provided suggestions on the possible research directions to the wind tunnel experiment of the bionic flapping-wing aerial vehicle, such as research on how the multi-wing and the feather structure of the wings affect the performance of the bionic flapping-wing aerial vehicle.
- bionic flapping-wing aerial vehicle /
- wind tunnel experiment /
- aerodynamic characteristics /
- airfoil design /
- Reynolds number

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圖 1 開口回流式低速風洞結構示意圖

Figure 1. Wind tunnel structure of a flapping-wing aerial vehicle

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圖 2 北京科技大學微型飛行器專用風洞

Figure 2. Special wind tunnel for a microair vehicle of University of Science and Technology Beijing

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圖 3 歐姆龍VTE?18?4N4212 漫反射光電開關

Figure 3. OMRON VTE?18?4N4212 diffuse reflection photoelectric switch

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圖 4 數字式粒子圖像測速系統

Figure 4. Digital particle image velocimetry system

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圖 5 DIC系統^[6]

Figure 5. Digital image correlation^[6]

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圖 6 ATI nano17

Figure 6. ATI nano17

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圖 7 煙流法下顯示的流場

Figure 7. Flow field under the smoke flow method

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圖 8 鳥類翅膀結構

Figure 8. Structure of a bird wing

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圖 9 熊超和宋筆鋒所用仿生撲翼飛行器和實驗機翼。（a）實驗用仿生撲翼飛行器；（b）實驗機翼^[3]

Figure 9. Flapping-wing aerial vehicle and the experimental wing used by Xiong C and Song B F: (a) experimental flapping-wing aerial vehicle；(b) experimental wing^[3]

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圖 10 昂海松等實驗所用撲翼飛行器^[19]

Figure 10. Flapping-wing aerial vehicle used by Ang H S’s team^[19]

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圖 11 仿生撲翼飛行器翼肋及機翼形狀平面圖。（a）翼肋結構；（b）機翼形狀平面圖

Figure 11. Plan view of wing rib and wing shape of bionic flapping-wing aerial vehicle: (a) structure of the wing rib; (b) schematic of the planform view of the wing shape

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圖 12 仿生撲翼飛行器整機及撲翼系統示意圖。（a）仿生撲翼飛行器整機；（b）開放試驗段風洞中的撲翼系統^[20]

Figure 12. Schematic of the whole bionic flapping-wing aerial vehicle: (a) the whole bionic flapping-wing aerial vehicle; (b) flapping wing system in the open test section of a wind tunnel^[20]

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圖 13 橢圓形和燕尾形尾翼。（a）橢圓形；（b）燕尾形^[25]

Figure 13. The oval and dovetail tails: (a) oval tail； (b) dovetail^[25]

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圖 14 試驗用仿生撲翼飛行器整機圖^[26]

Figure 14. The whole bionic flapping-wing aerial vehicle for testing^[26]

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圖 15 翼展處的翼型截面圖。（a）10%翼長；（b）20%翼長；（c）30%翼長；（d）40%翼長；（e）50%翼長；（f）60%翼長；（g）70%翼長；（h）80%翼長；（i）90%翼長^[32]

Figure 15. Airfoil section at wingspan: (a) 10% chord; (b) 20% chord; (c) 30% chord; (d) 40% chord; (e) 50% chord; (f) 60% chord; (g) 70% chord; (h) 80% chord; (i) 90% chord^[32]

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圖 16 具有上彎和前凸特征的海鷗翅膀

Figure 16. Wings of a seagull characterized by upper bending and anterior protrusion

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圖 17 昆翅的結構

Figure 17. Structure of an insect wing

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圖 18 實驗所用4種翼面形狀

Figure 18. Four wing shapes used in the experiment

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圖 19 RoboBee X-Wing

Figure 19. RoboBee X-Wing

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圖 20 千葉大學四翼撲翼飛行器^[47]

Figure 20. Chiba University’s four-wing flapping-wing aerial vehicle^[47]

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圖 21 翅膀設計輪廓^[48]

Figure 21. Contour of a wing design^[48]

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圖 22 變剛度翅膀^[39]

Figure 22. Variable stiffness wing^[39]

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表 1 熊超團隊和昂海松團隊實驗結果展示

Table 1. Experimental results of Xiong C’s team and Ang H S’s team

Team	Variable	Change of the angle of attack	Change of flapping frequency	Change of wind speed
Xiong C	Lift	Increase	Basically constant	Increase
Xiong C	Thrust	Decrease	Increase	Decrease
Ang H S	Lift	Increase	Increase	Increase
Ang H S	Thrust	Basically constant	Increase	Decrease

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