Aeroelastic Analysis of Sandwich Plates with Viscoelastic Core and Functionally Graded Materials in Supersonic Flow

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Gholamalizadeh, Vajiheh | 2020

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Type of Document: M.Sc. Thesis
Language: Farsi
Document No: 53923 (45)
University: Sharif University of Technology
Department: Aerospace Engineering
Advisor(s): Haddadpour, Hassan
Abstract:
This study investigates the aeroelastic instability of functionally graded sandwich plate with viscoelastic core in supersonic airflow. The classical plate theory, first order shear deformation theory, Hamilton's principle and linear first-order piston theory have been employed to extract the governing equations of motion of the structure. The Ritz method and State space notation is used to solve the derived equations and identify the instability boundary of the sandwich plate with simply-supported boundary conditions. The derived are solved using a computer program which is validated and verified by comparing the results with available literature. Our attention is focused on analyzing the effects of different parameters such as geometric aspect ratio, core layer thickness and constrained layer on the stability of the two type of sandwich plates. The results show that the critical non-dimensional aerodynamic pressure of the sandwich panel is influenced by geometric aspect ratio, core layer thickness and constrained layer thickness
Keywords:
Sandwich Panel ; Aeroelasticity ; Constrained Layer Damping (CLD) ; Functionally Graded Materials (FGM) ; Piston Theory ; Flutter

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