| Study of aerodynamic and inertial forces of a experimental and numerical methods |
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| 作者姓名： | Xiaowu YANG Bifeng SONG Wenqing YANG Dong XUE Yang PEI Xinyu LANG |
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| 作者单位： | 1. School of Aeronautics, Northwestern Polytechnical University;2. National Key Laboratory of Science and Technology on Aerodynamic Design and Research, Northwestern Polytechnical University;3. Research & Development Institute of Northwestern Polytechnical University in Shenzhen |
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| 基金项目： | supported by the National Natural Science Foundation of China (No. 11872314)；;the Key R&D Program in Shaanxi Province of China (No. 2020GY-154)； |
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| 摘 要： | The force-generation mechanism of a dovelike flapping-wing micro air vehicle was studied by numerical simulation and experiment. To obtain the real deformation pattern of the flapping wing, the digital image correlation technology was used to measure the dynamic deformation of the wing. The dynamic deformation data were subsequently interpolated and embedded into the CFD solver to account for the aeroelastic effects. The dynamic deformation data were further used to calculate the inertial forces...
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| 收稿时间： | 12 January 2021 |
Study of aerodynamic and inertial forces of a dovelike flapping-wing MAV by combining experimental and numerical methods |
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| Xiaowu YANG,Bifeng SONG,Wenqing YANG,Dong XUE,Yang PEI,Xinyu LANG.Study of aerodynamic and inertial forces of a experimental and numerical methods[J].Chinese Journal of Aeronautics,2022,35(6):63-76. |
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| Institution: | 1. School of Aeronautics, Northwestern Polytechnical University, Xi’an 710072, China;2. National Key Laboratory of Science and Technology on Aerodynamic Design and Research, Northwestern Polytechnical University, Xi’an 710072, China;3. Research & Development Institute of Northwestern Polytechnical University in Shenzhen, Shenzhen 518057, China |
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| Abstract: | The force-generation mechanism of a dovelike flapping-wing micro air vehicle was studied by numerical simulation and experiment. To obtain the real deformation pattern of the flapping wing, the digital image correlation technology was used to measure the dynamic deformation of the wing. The dynamic deformation data were subsequently interpolated and embedded into the CFD solver to account for the aeroelastic effects. The dynamic deformation data were further used to calculate the inertial forces by regarding the wing as a system of particles to take into account the wing flexibility. The temporal variation of the forces produced by the flapping wing was measured by a miniature load cell. The numerical results provide more flow details of the unsteady aerodynamics of the flapping wing in terms of vortex formation and evolution. The calculated results of the inertial forces are analyzed and compared with the CFD results which represent the aerodynamic forces. In addition, the total forces, i.e., the sum of the CFD result and inertial result, are compared with the experimental results, and an overall good agreement is obtained. |
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| Keywords: | Aerodynamic force CFD Digital image correlation Flapping-wing micro air vehicles Inertial force |
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