Frequency Domain Analysis of Aeroelastic Flutter Problem of Planar Structures Using Generalized Differential Quadrature Method

Date

2025-01-01

Author

Kılıçarslan, Doğuhan
Kösterit, Güneş
Ciğeroğlu, Ender

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This work is licensed under a Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License.

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Flutter instability occurs when the modal damping of the system becomes negative while the natural frequency is nonzero, in which the energy of the system increases while the structure is undergoing vibrations. As an aeroelastic problem, flutter occurs when wing-like or panel structures undergo self-excited vibrations where the vibration amplitude increases greatly while the fluid flow speed is at or higher than a critical threshold. Structural system is generally modeled using finite element or the Rayleigh-Ritz method; one other alternative is the generalized differential quadrature method (GDQM), where the derivative in the domain is approximated by the function values in the domain. In this work, the aeroelastic flutter problem of simply supported and cantilever plates under supersonic flow is modeled using linear Kirchhoff-Love plate theory and first-order piston theory to model the fluid-structure interaction. Equation of motion is discretized using GDQM in the spatial domain to transform differential equations into algebraic equations. Resulting algebraic equations are solved as a state space eigenvalue problem to obtain complex mode shapes and complex eigenvalues. Results are compared with those found in the literature, and the ability of GDQM to be applied to aeroelastic flutter analysis is assessed.

Subject Keywords

Aeroelastic flutter, Frequency domain, Generalized differential quadrature method, Instability, Kirchoff-Love plate theory

URI

https://www.scopus.com/inward/record.uri?partnerID=HzOxMe3b&scp=85208531820&origin=inward
https://hdl.handle.net/11511/113151

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Department of Mechanical Engineering, Conference / Seminar