Testing of Flapping Wing Four Bar Mechanism

Date

2015-10-29

Author

Şenol, Münier Gülay
Cömez, F Yudum
Kurtuluş, Dilek Funda
Arıkan, Kutluk Bilge

Metadata

Show full item record

Item Usage Stats

175
views

0
downloads

The purpose of this paper is to do preliminary work to design and test a flapping wing four-bar mechanism. A four-bar linkage system kinematic analysis is introduced forequation of motion of flapping wing. A validation case is selected upon the works of Konkuk University [4]. 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 (ART-TECH AS-100) which is driven by Arduino Uno. Two different deflections (10° and 20°) for input angle θ1is analyzed and instantaneous aerodynamic forces are obtained in hover mode. From the design of four bar mechanism input angle of 10° result a flapping angle (φ) of 41.5° at 11.2 Hz flapping frequency. The maximum flapping deflection of the current mechanism is found to be 85.9° with 20° input angle and the flapping frequency attained with the servo motor is 5.85Hz. This paper provides a detailed description of the design and manufacture of the mechanism and experimental setup. A CFD analysis is also performed for 10° deflection angle of the flapping wing mechanism designed and tested.

URI

https://hdl.handle.net/11511/86447

Conference Name

Workshop on Non-Intrusive Measurements of Unsteady Flows and Aerodynamics,27 - 29 Ekim 2015

Collections

Department of Aerospace Engineering, Conference / Seminar

Suggestions

OpenMETU
Core

Design and testing of a four-bar flapping wing mechanism Şenol, Münire Gülay; Kurtuluş, Dilek Funda; Department of Aerospace Engineering (2016) 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...
DEVELOPMENT OF AN AUTOMATIC DESIGN AND ANALYSIS TOOL FOR AXIAL FLOW COMPRESSORS Kundes, Necmettin Anil; Aksel, Mehmet Haluk; Baran, Özgür Uğraş (2019-01-01) This paper presents a new design and analysis tool that is developed to be employed during the design process of axial flow compressors. The tool chain implemented by this design tool consists of five parts: a mean-line design tool, followed by a blade geometry parametrization tool. Then 3D blade geometry is created, next a high quality structured mesh is generated and completed by Computational Fluid Dynamics (CFD) solution. All components employed in the new tool are either new developments, or achieved b...
Development of a sabot design tool for aeroballistic range testing Kafdağlı, Karaca Efe; Kayran, Altan; Department of Aerospace Engineering (2006) The aim of this thesis is to investigate the general design and analysis principles of sabots and to develop a sabot design tool. Structures which support and align the models in gun bore, and separate without disturbing the flight path of models are called sabots. In the scope of this study, structurally critical regions and loads acting on sabots due to acceleration in the gun are determined. To calculate the loads acting and to size the sabots, approximate relations are derived by the help of strength of...
Experimental and Numerical Results of a Flapping Wing Four Bar Mechanism Şenol, Münire Gülay; Arıkan, Kutlu Bilge; Kurtuluş, Dilek Funda (2017-01-13) This paper exploresthedesign and testing ofa 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 apure flapping motion at afixed pitchangle. Force measurements are performed for hover modeby using a force transducer. In addition, 3D numericalanalyses are performed and the results are compared with the experim...
Development of PDMS-based micromachining process for microfluidic reconfigurable antennas / Seyedpour Esmaeilzad, SeyedehNasim; Külah, Haluk; Topallı, Kağan; Department of Electrical and Electronics Engineering (2015) The objective of this thesis is to develop fabrication methods to implement microfluidic-based reconfigurable antennas. As the initial structure, a microfluidic based reconfigurable antenna is developed for transmitarrays, which consists of a multi-layered structure incorporating a microfluidic channel to confine liquid metal. The microfluidic channels are fabricated using soft lithography techniques where the channel material is PDMS. PDMS-to-glass and PDMS-to-PDMS bonding processes are optimized to achiev...

Citation Formats

M. G. Şenol, F. Y. Cömez, D. F. Kurtuluş, and K. B. Arıkan, “Testing of Flapping Wing Four Bar Mechanism,” Poitiers, France, 2015, p. 114, Accessed: 00, 2021. [Online]. Available: https://hdl.handle.net/11511/86447.