Aerodynamic Performance Experiments and Analysis of A Flapping-Wing Micro Aerial Vehicle

• Main Authors: Fei-Yau Lu, 路非遙
• Other Authors: Fei-Bin Hsiao
• Format: Others
• Language: zh-TW
• Published: 2001
• Online Access: http://ndltd.ncl.edu.tw/handle/90895741317435123286

碩士 === 國立成功大學 === 航空太空工程學系 === 89 === In recent years, the progress of micro-manufacturing technology has scaled down from a 1-meter UAV to a 10-cm Micro-UAV. The reduction of scale has made all the knowledge we known to face a new aspect. Designing a MAV has become a new challenge, which includes low Reynolds-number aerodynamics analysis, effective propulsion system design, effective power system design, selection of light-weighted sensor, and selection of light-weighted communication-navigation components. Every design phase is closely connected to each other. MAV can be divided into two configurations, one is fixed-wing and the other is flapping-wing. This experiment focuses on flapping-wing configuration. A four-bar linkage flapping mechanism was designed and constructed to simulate the flapping motion of a bird. The flapping mechanism was mounted on a 3-DOF, high-frequency-response force-balance in order to measure the dynamic change of lift and drag situation. The experiment result shows that the increasing of flapping frequency for 30cm-span flapping model can produce 2-8 times more lift than can be accounted for by conventional （no flapping）flight. Using by phase average method let me clearly understand that the effective lift produced is during the down-stroke of flapping motion and the result of flow visualization show us that the effective lift produced rely on the interaction of a leading-edge vortex（created by dynamic stall during flapping） and wing-tip vortex .