Check-Valve Design in Enhancing Aerodynamic Performance of Flapping Wings

Applied Sciences

Balasubramanian Esakki¹  Chi-Yuan Lee²  Reshmi Waikhom³  Vivek Jabaraj Joseph³  Neethish Kumar Unnam³  Lung-Jieh Yang³  Wei-Chen Wang³  Xiuhan Li⁴ 

[1] Department of Mechanical Engineering, Vel Tech Rangarajan Dr Sagunthala R&D Institute of Science and Technology, Chennai 600062, India;Department of Mechanical Engineering, Yuan Ze Fuel Cell Center, Yuan Ze University, Taoyuan 32003, Taiwan;Department of Mechanical and Electromechanical Engineering, Tamkang University, Tamsui 251301, Taiwan;School of Electronics and Information Engineering, Beijing Jiaotong University, Beijing 100044, China;

关键词: check-valve;    flapping wing;    high lift device;   

DOI  :  10.3390/app11083416

来源: DOAJ

【 摘 要 】

A flapping wing micro air vehicle (FWMAV) demands high lift and thrust generation for a desired payload. In view of this, the present work focuses on a novel way of enhancing the lift characteristics through integrating check-valves in the flapping wing membrane. Modal analysis and static analysis are performed to determine the natural frequency and deformation of the check-valve. Based on the inference, the check-valve opens and closes during the upstroke flapping and downstroke flapping, respectively. Wind tunnel experiments were conducted by considering the two cases of wing design, i.e., with and without a check-valve for various driving voltages, wind speeds and different inclined angles. A 20 cm-wingspan polyethylene terephthalate (PET) membrane wing with two check-valves, composed of central disc-cap with radius of 7.43 mm, supported by three S-beams, actuated by Evans mechanism to have 90° stroke angle, is considered for the 10 gf (gram force) FWMAV study. The aerodynamic performances, such as lift and net thrust for these two cases, are evaluated. The experimental result demonstrates that an average lift of 17 gf is generated for the case where check-valves are attached on the wing membrane to operate at 3.7 V input voltage, 30° inclined angle and 1.5 m/s wind speed. It is inferred that sufficient aerodynamic benefit with 68% of higher lift is attained for the wing membrane incorporated with check-valve.

【 授权许可】

Unknown