Experimental and numerical results of a flapping wing four bar mechanism

Senol M., Arıkan K. B., KURTULUŞ D. F.

55th AIAA Aerospace Sciences Meeting, Texas, United States Of America, 9 - 13 January 2017 identifier

  • Publication Type: Conference Paper / Full Text
  • Doi Number: 10.2514/6.2017-0498
  • City: Texas
  • Country: United States Of America
  • TED University Affiliated: No

Abstract

© 2017 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.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.