Design and testing of a four-bar flapping wing mechanism

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2016
Şenol, Münire Gülay
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The purpose of this thesis is to design and test a flapping wing four-bar mechanism. A four-bar linkage system kinematic analysis is introduced for flapping wing motion. The type of mechanism is double rocker and the motion has a single-degree of freedom. Four-bar mechanism is activated by a servo motor which is driven by microcontroller. From the design of four bar mechanism, two different simulations result two different flapping angles and flapping frequencies. This thesis provides a detailed description of the design and manufacturing of the flapping mechanism and its experimental setup. The wing has pure flapping motion with fixed incidence angle. Force measurements are performed for hover modes by using a force transducer. CFD analyses are performed for both hover and forward flight cases. The numerical and experimental results are discussed and compared.
Aerofoils., Flaps (Airplanes)., Airplanes, Micro air vehicles., Computational fluid dynamics.
http://etd.lib.metu.edu.tr/upload/12619748/index.pdf
https://hdl.handle.net/11511/25436
Graduate School of Natural and Applied Sciences, Thesis

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Citation Formats
M. G. Şenol, “Design and testing of a four-bar flapping wing mechanism,” M.S. - Master of Science, Middle East Technical University, 2016.
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