Aerodynamic and inertial characterization of a generic flapping wing mechanism

Beker , Can
The primary focus of this thesis is to conduct an aerodynamical and inertial characterization of a generic flapping wing mechanism. Firstly, a CAD model of the utilized flapping mechanism is created, and a custom test platform is developed for the performed flapping-wing test sequence. Experimental validation of the modal analysis performed for the developed test platform is presented. In the inertial force characterization study, the standalone effect of the inertial forces that occur during flapping motion on the produced total aerodynamic lift force is aimed to investigate. In this framework, the wing membrane is eliminated, and a flapping wing test is performed to measure the inertial force generated due to the motion of the prescribed kinematics in the lift direction. The dynamic calibration of the utilized sensor is carried out to ensure the fidelity of the acquired data during the flapping test. Verification studies regarding to the experimental inertial force investigation are conducted by performing theoretical and dynamic finite element analysis approaches. For the aerodynamic characterization of the proposed system, a nylon wing membrane is attached to the utilized flapping wing mechanism, and a flapping wing experiment is performed in the air medium. To verify the experimental results, a numerical validation study is conducted and, a fluid-structure interaction analysis model is presented for the corresponding model. Besides, the effect of wing-flexion on aerodynamic performance is investigated for the corresponding model. In this regard, a distinct fluid-structure interaction analysis model, including a flapping wing with high-rigidity material properties, is created to minimize the deflection that occurs on the wing structure. Experimental, theoretical, and numerical approaches conducted for the inertial and aerodynamic characterization of the utilized flapping mechanism showed great resemblance to each other. A comparative study performed for the effect of wing-flexion shows that wing elasticity enhances the thrust force for the proposed model.


Aeroelastic Analysis of a Flapping Blow Fly Wing
Beker, Can; Turgut, Ali Emre; ARIKAN, KUTLUK BİLGE; Kurtuluş, Dilek Funda (2020-06-01)
In this study, a 3D model of the bio-inspired blowfly wing Callphere Erytrocephala is created and aeroelastic analysis is performed to calculate its aerodynamical characteristics by use of numerical methods. To perform the flapping motion, a sinusoidal input function is created. The scope of this study is to perform aeroelastic analysis by synchronizing computational fluid dynamics (CFD) and structural dynamic analysis models and to investigate the unsteady lift formation on the aeroelastic flapping wing fo...
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...
Beker, Can; Turgut, Ali Emre; Arıkan, Kutluk Bilge; Kurtuluş, Dilek Funda (2019-07-11)
In this paper, it is introduced to find net aerodynamic lift capacity of proposed flapping-wing micro air vehicle (FWMAV) by performing dynamical calculation and FSI (Fluid Structure Interaction) analysis of a flapping wing test system. In the flapping system, a single degree of freedom type four-bar mechanism which was used as a piezo-driven flapping wing mechanism in previous literature studies is implemented to create beating motion of the wings. For the wing structure, Calliphora Erythocephala’s wing is...
Aerodynamic characteristics of flapping motion in hover
Kurtuluş, Dilek Funda; FARCY, A.; ALEMDAROGLU, N. (Springer Science and Business Media LLC, 2008-01-01)
The aim of the present work is to understand the aerodynamic phenomena and the vortex topology of an unsteady flapping motion by means of numerical and experimental methods. Instead of the use of real insect/bird wing geometries and kinematics which are highly complex and difficult to imitate by an exact modeling, a simplified model is used in order to understand the unsteady aerodynamics and vortex formation mechanisms during the different phases of the flapping motion. The flow is assumed to be laminar wi...
Development and testing of a 3 DOF tandem flapping wing mechanism
Mutlu, Talha; Kurtuluş, Dilek Funda; Department of Aerospace Engineering (2014)
Scope of the thesis is to develop a tandem flapping wing mechanism, capable of mimicking the insect flight, in order to investigate the 3-D complex nature of the flow around the flapping wings. Thus, valuable data about the unsteady aerodynamics of such flow can be obtained in order to provide necessary knowledge for development of future Micro Air Vehicles (MAVs). The mechanism is equipped with a state of art multi axial force and torque sensor. By placing the sensor to the root chord of the wing, any forc...
Citation Formats
C. Beker, “Aerodynamic and inertial characterization of a generic flapping wing mechanism,” M.S. - Master of Science, Middle East Technical University, 2020.