AERODYNAMIC ANALYSIS OF FLAPPING WING ACTUATED WITH PZT MATERIAL INCLUDING AEROELASTIC DEFORMATION

Date

2024-1-15

Author

ÇÖMEZ ÖZGÜN, FADİLE YUDUM

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In this thesis, both experimental and computational methods are proposed as a solution to understand how aerodynamic forces and structural deformations of flexible flapping wings interact utilizing unsteady conditions. In the first part of the experiments, the structural properties (e.g., Young’s modulus, Poisson’s ratio, density) of the wing material are investigated and the wing models are fabricated from thin aluminum material. To conduct the experiments, one flexible rectangular wing and one Rufous hummingbird wing are selected. These wings are manufactured from a flat aluminum plate without replicating the vasculature structure found in flying creatures of nature. Throughout these experiments, the wings are induced to flapping motion using piezoelectric actuators. Force measurements are obtained by the ATI Nano 17 force/torque sensor and the wing deformations are collected by the DIC high-speed camera system. The displacement values obtained from the Digital Image Correlation (DIC) system provided inputs to the numerical model. The simulations of the laminar flow conditions at low Reynolds numbers are conducted using Ansys Fluent software. Consequently, the impact of deformations captured by the high-speed camera system on the wing's flow is observed. Thus, the effect of structural deformations on the flow is observed, and their impacts on the flow due to structural deformations are determined. The combined use of experimental and numerical methods was facilitated rather than employing lengthy and intricate analysis methods.

Subject Keywords

Butterfly Flapping Wings, PZT Material, Aeroelastic Analysis, Experimental Methods, Computational Methods

URI

https://hdl.handle.net/11511/108335

Collections

Graduate School of Natural and Applied Sciences, Thesis