Flapping Wing Micro Air Vehicle Bench Test Set-up

2009 ◽  
Author(s):  
Craig Svanberg ◽  
Mark Reeder ◽  
David Curtis ◽  
Richard Cobb
Keyword(s):  
Flapping Wing ◽  
Micro Air Vehicle ◽  
Bench Test ◽  
Test Set ◽  
Air Vehicle ◽  
Set Up

scholarly journals Flapping Wing Micro Air Vehicle Bench Test Setup

2012 ◽  
Vol 4 (1) ◽  
pp. 51-77 ◽  
Author(s):  
David H. Curtis ◽  
Mark F. Reeder ◽  
Craig E. Svanberg ◽  
Richard G. Cobb ◽  
Gregory H. Parker
Keyword(s):  
Flapping Wing ◽  
Micro Air Vehicle ◽  
Bench Test ◽  
Test Setup ◽  
Air Vehicle

scholarly journals Experimental investigation of wing flexibility on force generation of a hovering flapping wing micro air vehicle with double wing clap-and-fling effects

2017 ◽  
Vol 9 (3) ◽  
pp. 187-197 ◽  
Author(s):  
Quoc V Nguyen ◽  
Woei L Chan ◽  
Marco Debiasi
Keyword(s):  
Experimental Investigation ◽  
Power Consumption ◽  
High Speed ◽  
Electrical Power ◽  
Leading Edge ◽  
Flapping Wing ◽  
Micro Air Vehicle ◽  
Custom Made ◽  
Air Vehicle ◽  
Set Up

Experimental investigation of wing flexibility on vertical thrust generation and power consumption in hovering condition for a hovering Flapping-Wing Micro Air Vehicle, namely FlowerFly, weighing 14.5 g with a 3 g onboard battery and having four wings with double wing clap-and-fling effects, was conducted for several wing configurations with the same shape, area, and weight. A data acquisition system was set up to simultaneously record aerodynamic forces, electrical power consumption, and wing motions at various flapping frequencies. The forces and power consumption were measured with a loadcell and a custom-made shunt circuit, respectively, and the wing motion was captured by high-speed cameras. The results show a phase delay of the wing tip displacement observed for wings with high flexible leading edge at high frequency, resulting in less vertical thrust produced when compared with the wings with less leading edge flexibility at the same flapping frequency. Positive wing camber was observed during wing flapping motion by arranging the wing supporting ribs. Comparison of thrust-to-power ratios between the wing configurations was undertaken to figure out a wing configuration for high vertical thrust production but less power consumption.

Design and Fabrication of an SU-8 Biomimetic Flapping-wing Micro Air Vehicle by MEMS Technology

ROBOT ◽  
2011 ◽  
Vol 33 (3) ◽  
pp. 366-370 ◽  
Author(s):  
Pengcheng CHI ◽  
Weiping ZHANG ◽  
Wenyuan CHEN ◽  
Hongyi LI ◽  
Kun MENG ◽  
...  
Keyword(s):  
Flapping Wing ◽  
Micro Air Vehicle ◽  
Air Vehicle ◽  
Mems Technology

scholarly journals Dove: A biomimetic flapping-wing micro air vehicle

2017 ◽  
Vol 10 (1) ◽  
pp. 70-84 ◽  
Author(s):  
Wenqing Yang ◽  
Liguang Wang ◽  
Bifeng Song
Keyword(s):  
Mechanism Design ◽  
Flapping Wing ◽  
Micro Air Vehicle ◽  
Flexible Wing ◽  
The Past ◽  
Ground Station ◽  
Air Vehicle ◽  
Research Goal ◽  
Color Video ◽  
Flapping Mechanism

This paper describes the design and development of the Dove, a flapping-wing micro air vehicle (FWMAV), which was developed in Northwestern Polytechnical University. FWMAVs have attracted international attentions since the past two decades. Since some achievements have been obtained, such as the capability of supporting an air vehicle to fly, our research goal was to design an FWMAV that has the ability to accomplish a task. Main investigations were presented in this paper, including the flexible wing design, the flapping mechanism design, and the on-board avionics development. The current Dove has a mass of 220 g, a wingspan of 50 cm, and the ability of operating fully autonomously, flying lasts half an hour, and transmitting live stabilized color video to a ground station over 4 km away.

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