Free Vibration of Composite Conical Sandwich Panel with a Flexible Core

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Najafi, Babak | 2014

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Type of Document: M.Sc. Thesis
Language: Farsi
Document No: 45366 (45)
University: Sharif University of Technology
Department: Aerospace Engineering
Advisor(s): Kouchakzadeh, Mohammad Ali
Abstract:
In this thesis, free vibration of composite conical sandwich panel with a flexible is presented. Simply supported boundary condition are applied on the face’s edge only. Hamilton principle and energy method are used to derive equilibrium equations. In the mathematical formulation higher-order sandwich panel theory (HSAPT) was used. First shear deformation theory (FSDT) is used for faces.
Core displacement in various directions is modeled by polynomial function with indeterminate coefficient. It is assumed that the core is able to sustain shear and in-plane stresses. Temprature and humidity effects are neglected. Equations solved using generalized differential quadrature (GDQ) method. Results are compared and validated with cylindrical sandwich panel and composite laminated conical shell. The ten first natural frequencies calculated. Finally, the effects of length to radius ratio, radius to total thickness ratio, core modulus to faces modulus ratio, core thickness to total thickness ratio, on natural frequencies are investigated
Keywords:
Free Vibration ; High Order Shear Theory ; Conical Sandwich Panel ; Flexible Core ; Generalized Quadrature