Parametric Study on Aerodynamic Performance of a Flapping Wing Rotor MAV Capable of Sustained Flight
By combining the flapping and rotary motion, a flapping wing rotor (FWR) shows unique kinematics of motion. It can produce a significantly higher aerodynamic efficiency and lift coefficient than insect-like flapping wings. However, due to the lack of controllable FWR aerial vehicles, the effect of d...
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| Format: | Article |
| Language: | English |
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MDPI AG
2022-09-01
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| Series: | Aerospace |
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| Online Access: | https://www.mdpi.com/2226-4310/9/10/551 |
| _version_ | 1797476373691891712 |
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| author | Ziyu Wang Zi Kan Huadong Li Daochun Li Shiwei Zhao Zhan Tu |
| author_facet | Ziyu Wang Zi Kan Huadong Li Daochun Li Shiwei Zhao Zhan Tu |
| author_sort | Ziyu Wang |
| collection | DOAJ |
| description | By combining the flapping and rotary motion, a flapping wing rotor (FWR) shows unique kinematics of motion. It can produce a significantly higher aerodynamic efficiency and lift coefficient than insect-like flapping wings. However, due to the lack of controllable FWR aerial vehicles, the effect of different flapping parameters of the FWR on aerodynamic characteristics and efficiency remains to be evaluated experimentally. In this work, we conduct experimental studies to investigate the FWR’s lift performance based on our previous vehicle design, which has demonstrated sustained stable hover and maneuver. In particular, by using such flyable FWR as the test platform, the changes in attack angle of the wing, the torsion of wings, different neutral positions, different up and down flapping angles, and different flapping amplitudes, were studied respectively. CFD simulation was used as an auxiliary and supplementary means for validation. As a result, design essentials to lift maximization of the FWR are proposed. The result proves that changing the attack angle and the torsion of the wing will have a certain impact on the lift. In addition, the ideal lift force can be generated when the neutral position tend to zero degrees and the up and down flapping angles tend to be equal. With the growth of the flapping amplitude, the lift force increases continuously. These experimental results provide important design cues for maximizing lift and payload capability of FWR-MAVs. |
| first_indexed | 2024-03-09T20:57:55Z |
| format | Article |
| id | doaj.art-ec47e3b6dfeb4e3ead35436e977e250b |
| institution | Directory Open Access Journal |
| issn | 2226-4310 |
| language | English |
| last_indexed | 2024-03-09T20:57:55Z |
| publishDate | 2022-09-01 |
| publisher | MDPI AG |
| record_format | Article |
| series | Aerospace |
| spelling | doaj.art-ec47e3b6dfeb4e3ead35436e977e250b2023-11-23T22:18:12ZengMDPI AGAerospace2226-43102022-09-0191055110.3390/aerospace9100551Parametric Study on Aerodynamic Performance of a Flapping Wing Rotor MAV Capable of Sustained FlightZiyu Wang0Zi Kan1Huadong Li2Daochun Li3Shiwei Zhao4Zhan Tu5School of Aeronautic Science and Engineering, Beihang University, Beijing 100083, ChinaSchool of Aeronautic Science and Engineering, Beihang University, Beijing 100083, ChinaSchool of Aeronautic Science and Engineering, Beihang University, Beijing 100083, ChinaSchool of Aeronautic Science and Engineering, Beihang University, Beijing 100083, ChinaSchool of Aeronautic Science and Engineering, Beihang University, Beijing 100083, ChinaInstitute of Unmanned System, Beihang University, Beijing 100083, ChinaBy combining the flapping and rotary motion, a flapping wing rotor (FWR) shows unique kinematics of motion. It can produce a significantly higher aerodynamic efficiency and lift coefficient than insect-like flapping wings. However, due to the lack of controllable FWR aerial vehicles, the effect of different flapping parameters of the FWR on aerodynamic characteristics and efficiency remains to be evaluated experimentally. In this work, we conduct experimental studies to investigate the FWR’s lift performance based on our previous vehicle design, which has demonstrated sustained stable hover and maneuver. In particular, by using such flyable FWR as the test platform, the changes in attack angle of the wing, the torsion of wings, different neutral positions, different up and down flapping angles, and different flapping amplitudes, were studied respectively. CFD simulation was used as an auxiliary and supplementary means for validation. As a result, design essentials to lift maximization of the FWR are proposed. The result proves that changing the attack angle and the torsion of the wing will have a certain impact on the lift. In addition, the ideal lift force can be generated when the neutral position tend to zero degrees and the up and down flapping angles tend to be equal. With the growth of the flapping amplitude, the lift force increases continuously. These experimental results provide important design cues for maximizing lift and payload capability of FWR-MAVs.https://www.mdpi.com/2226-4310/9/10/551flapping wing rotorCFD simulationflapping parameter |
| spellingShingle | Ziyu Wang Zi Kan Huadong Li Daochun Li Shiwei Zhao Zhan Tu Parametric Study on Aerodynamic Performance of a Flapping Wing Rotor MAV Capable of Sustained Flight Aerospace flapping wing rotor CFD simulation flapping parameter |
| title | Parametric Study on Aerodynamic Performance of a Flapping Wing Rotor MAV Capable of Sustained Flight |
| title_full | Parametric Study on Aerodynamic Performance of a Flapping Wing Rotor MAV Capable of Sustained Flight |
| title_fullStr | Parametric Study on Aerodynamic Performance of a Flapping Wing Rotor MAV Capable of Sustained Flight |
| title_full_unstemmed | Parametric Study on Aerodynamic Performance of a Flapping Wing Rotor MAV Capable of Sustained Flight |
| title_short | Parametric Study on Aerodynamic Performance of a Flapping Wing Rotor MAV Capable of Sustained Flight |
| title_sort | parametric study on aerodynamic performance of a flapping wing rotor mav capable of sustained flight |
| topic | flapping wing rotor CFD simulation flapping parameter |
| url | https://www.mdpi.com/2226-4310/9/10/551 |
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