Experimental and numerical results of a flapping wing four bar mechanism

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2017

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American Institute of Aeronautics and Astronautics Inc.

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Department of Mechatronics Engineering
Our purpose in the program is to educate our students for contributing to universal knowledge by doing research on contemporary mechatronics engineering problems and provide them with design, production and publication skills. To reach this goal our post graduate students are offered courses in various areas of mechatronics engineering, encouraged to do research to develop their expertise and their creative side, as well as develop analysis and design skills.

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Abstract

This paper explores the design and testing of a flapping wing four-bar mechanism. A four-bar linkage system kinematic analysis is introduced for flapping wing motion. Four-bar mechanism is activated by a servo motor which is driven by microcontroller. The wing undergoes a pure flapping motion at a fixed pitch angle. Force measurements are performed for hover mode by using a force transducer. In addition, 3D numerical analyses are performed and the results are compared with the experimental measurements. Overall, CFD results show good agreement with the experimental data. © 2017 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

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AIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting -- 55th AIAA Aerospace Sciences Meeting -- 9 January 2017 through 13 January 2017 -- Grapevine -- 126423

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https://doi.org/10.2514/6.2017-0498
 https://hdl.handle.net/20.500.14411/3839

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Scopus