Buckling analysis of composite panels and shells with different material properties by discrete singular convolution (DSC) method

2017 ◽  
Vol 161 ◽  
pp. 93-110 ◽  
Author(s):  
Ömer Civalek
Keyword(s):  
Material Properties ◽  
Buckling Analysis ◽  
Composite Panels ◽  
Discrete Singular Convolution ◽  
Dsc Method

Thermal Post-Buckling Analysis of Functionally Graded Composite Plates with Nonlinear Aerodynamic Forces

2010 ◽  
Vol 123-125 ◽  
pp. 280-283
Author(s):  
Chang Yull Lee ◽  
Ji Hwan Kim
Keyword(s):  
Material Properties ◽  
Numerical Solutions ◽  
Virtual Work ◽  
Shear Deformation Theory ◽  
Composite Plates ◽  
Buckling Analysis ◽  
Functionally Graded ◽  
Governing Equations ◽  
Functionally Graded Composite ◽  
Post Buckling

The post-buckling of the functionally graded composite plate under thermal environment with aerodynamic loading is studied. The structural model has three layers with ceramic, FGM and metal, respectively. The outer layers of the sandwich plate are different homogeneous and isotropic material properties for ceramic and metal. Whereas the core is FGM layer, material properties vary continuously from one interface to the other in the thickness direction according to a simple power law distribution in terms of the volume fractions. Governing equations are derived by using the principle of virtual work and numerical solutions are solved through a finite element method. The first-order shear deformation theory and von-Karman strain-displacement relations are based to derive governing equations of the plate. Aerodynamic effects are dealt by adopting nonlinear third-order piston theory for structural and aerodynamic nonlinearity. The Newton-Raphson iterative method applied for solving the nonlinear equations of the thermal post-buckling analysis

Buckling analysis of piezoelectric cylindrical composite panels reinforced with carbon nanotubes

2016 ◽  
Vol 107 ◽  
pp. 69-79 ◽  
Author(s):  
Mohsen Nasihatgozar ◽  
Vahid Daghigh ◽  
Milad Eskandari ◽  
Kamran Nikbin ◽  
Andy Simoneau
Keyword(s):  
Carbon Nanotubes ◽  
Buckling Analysis ◽  
Composite Panels

Buckling and Vibration of Elastically Restrained Standing Vertical Plates

2011 ◽  
Vol 134 (1) ◽  
Author(s):  
S. K. Lai ◽  
Y. Xiang
Keyword(s):  
Numerical Technique ◽  
Eigenvalue Equation ◽  
Mode Shapes ◽  
Body Forces ◽  
Discrete Singular Convolution ◽  
Dsc Method ◽  
Elastically Restrained ◽  
Contour Mode ◽  
Elastic Edge

This paper investigates the buckling and vibration of heavy standing plates with rotational elastic edge constraints. The discrete singular convolution (DSC) method as a powerful numerical technique is applied to derive the governing eigenvalue equation. Convergence and comparison studies are conducted to authenticate the correctness and accuracy of the DSC approach. Accurate first-known vibration solutions for elastically restrained vertical plates subjecting to body forces/self-weight are presented. Some contour mode shapes for the vibration of elastically restrained vertical plates are also depicted for illustration.

Tailoring the Fundamental Frequency of Laminated Composite Panels Using Material Properties

2014 ◽  
Vol 709 ◽  
pp. 157-161
Author(s):  
Li Guo Zhang ◽  
Kang Yang ◽  
Wei Ping Zhao ◽  
Song Xiang
Keyword(s):  
Fundamental Frequency ◽  
Material Properties ◽  
Present Method ◽  
Optimization Problem ◽  
Laminated Composite ◽  
Composite Panels ◽  
Fundamental Frequencies ◽  
Laminated Panels ◽  
Frequency Optimization ◽  
Optimal Material

Optimization of material properties is performed to maximize the fundamental frequency of the laminated composite panels by means of the genetic algorithm. The global radial basis function collocation method is used to calculate the fundamental frequency of clamped laminated composite panels. In this paper, the objective function of optimization problem is the maximum fundamental frequency; optimization variables are material properties of laminated panels. The results for the optimal material properties and the maximum fundamental frequencies of the 2-layer plates are presented to verify the validity of present method.

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