Panel Flutter Analysis of Cylindrical Constrained Layer Damping (CLD) Panels

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Sadeghmanesh, Mostafa | 2011

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Type of Document: M.Sc. Thesis
Language: Farsi
Document No: 41895 (45)
University: Sharif University of Technology
Department: Aerospace Engineering
Advisor(s): Haddadpour, Hassan
Abstract:
The purpose of this study is to analytically study the aeroelastic characteristics of the cylindrical shells fully treated with passive constrained layer damping (PCLD) to indicate the effects of various parameters on the behavior of such structures. Constraining the viscoelastic layers increases the amount of dissipated energy and the bending stiffness of the structure without considerable change of the weight.
A thin shell theory in conjunction with the Donell assumptions is employed for the shell and the constraining layer (CL) and the first order shear deformation theory (FSDT) is used for the viscoelastic layer to construct the model. The effects of rotary inertia and shear deformations are also considered for the viscoelastic layer. The complex modulus of the viscoelastic material is taken into account by implementing the Kelvin-Voigt model. The governing partial differential equations of motion are derived by Hamilton's principle and transformed into a set of ordinary differential equations through the Galerkin Approach. The Quasi-steady Piston Theory is Used to Analyse the Supersonic Panel Flutter
Keywords:
Cylindrical Shells ; First-Order Shear Deformation Theory ; Panel Flutter ; Constrained Viscoelastic Layer ; Constrained Layer Damping (CLD) ; Kelvin-Voigt Model

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