Effect of Wing Kinematics Modulation on Aerodynamic Force Generation in Hovering Insect-mimicking Flapping-wing Micro Air Vehicle

作     者：Hoang Vu Phan Quang Tri Truong Thi Kim Loan Au Hoon Cheol Park 

作者机构：Artificial Muscle Research Center Konkuk University Seoul 143-701 South Korea National Research Laboratory for Biomimetics and Intelligent Microsystems Konkuk University Seoul 143-701 South Korea Department of Advanced Technology Fusion Konkuk University Seoul 143-701 South Korea Laboratory of Applied Mechanics Faculty of Applied Science Ho Chi Minh City University of Technology Ho Chi Minh 740-128 Vietnam 

出 版 物：《Journal of Bionic Engineering》 (仿生工程学报（英文版）)

年 卷 期：2015年第12卷第4期

页      面：539-554页

核心收录：

学科分类：08[工学] 0825[工学-航空宇航科学与技术] 080101[工学-一般力学与力学基础] 0801[工学-力学（可授工学、理学学位）] 

基　　金：supported by a grant to the Bio-Mimetic Robot Research Center funded by the Defense Acquisition Program Administration supported by the Basic Science Research Program through the National Research Foundation of Korea (NRF) funded by the Ministry of Science, ICT and Future Planning 

主　　题：wing kinematics flapping-wing MAV biomimetics beetle-mimicking insect flight linear extrapolation 

摘      要：We investigated the effect of wing kinematics modulation, which was achieved by adjusting the location of trailing-edge constraint at the wing-root, i.e., by adjusting the wing-root offset, on the generation of aerodynamic forces in a hovering in- sect-mimicking Flapping-Wing Micro Air Vehicle （FW-MAV） by numerical and experimental studies. Three-dimensional wing kinematics measured using three synchronized high-speed cameras revealed a clear difference in the wing rotation angle of a wing section for different wing-root offsets. The extrapolated wing kinematics were in good agreement with the measured ones for various wing-root offsets. The Unsteady Blade Element Theory （UBET） was used to estimate the forces generated by the flapping wings and validated by comparison with results of measurements performed using a load cell. Although the thrust produced by a flapping wing with a wing-root offset of 0.20 c was about 4% less, its force-to-input-power ratio was about 30% and 10% higher than those with the offsets of 0.10 c and 0.15 c, respectively. This result could be explained by analyzing the effective Angle of Attack （AoA） and the force components computed by the UBET. Thus, a flapping wing with a wing-root offset of 0.20 c can be regarded as an optimal twist configuration for the development of the FW-MAV.