Effect of Wing Kinematics Modulation on Aerodynamic Force Generation in Hovering Insect-mimicking Flapping-wing Micro Air Vehicle
详细信息 查看全文
- 作者：Hoang Vu Phana ; b ; c ; Quang Tri Truongd ; Thi Kim Loan Aua ; b ; c ; Hoon Cheol Parka ; b ; c ; hcpark@konkuk.ac.kr" class="auth_mail" title="E-mail the corresponding author
- 关键词：wing kinematics ; flapping-wing MAV ; biomimetics ; beetle-mimicking ; insect flight ; linear extrapolation
- 刊名：Journal of Bionic Engineering
- 出版年：2015
- 出版时间：October 2015
- 年：2015
- 卷：12
- 期：4
- 页码：539-554
- 全文大小：7285 K
文摘
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 insect-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
was about 4% less, its force-to-input-power ratio was about 30% and 10% higher than those with the offsets of 0.10 and 0.15 , 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 ; can be regarded as an optimal twist configuration for the development of the FW-MAV.
was about 4% less, its force-to-input-power ratio was about 30% and 10% higher than those with the offsets of 0.10 and 0.15 , 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 ; can be regarded as an optimal twist configuration for the development of the FW-MAV.