Stochastic Finite Element Buckling Analysis of Laminated Plates With Circular Cutout Under Uniaxial Compression

2006 ◽  
Vol 74 (4) ◽  
pp. 798-809 ◽  
Author(s):  
A. K. Onkar ◽  
C. S. Upadhyay ◽  
D. Yadav
Keyword(s):  
Material Properties ◽  
Perturbation Technique ◽  
Compressive Loading ◽  
Laminated Composite ◽  
Composite Plates ◽  
Buckling Analysis ◽  
Laminated Plates ◽  
Buckling Strength ◽  
The Mean ◽  
Random Material Properties

A generalized stochastic buckling analysis of laminated composite plates, with and without centrally located circular cutouts having random material properties, is presented under uniaxial compressive loading. In this analysis, the layerwise plate model is used to solve both prebuckling and buckling problems. The stochastic analysis is done based on mean centered first-order perturbation technique. The mean buckling strength of composite plates is validated with results available in the literature. It has been observed that the present analysis can predict buckling load accurately even for plates with large cutouts. Micromechanics based approach is used to study the effect of variation in microlevel constituents on the effective macrolevel properties like elastic moduli. Consequently, the effect of uncertainty in these material properties on the buckling strength of the laminated plates is studied. Parametric studies are carried out to see the effect of hole size, layups, and boundary conditions on the mean and variance of plate buckling strength.

Hygrothermal Buckling Response of Laminated Composite Plates with Random Material Properties: Micro-Mechanical Model

2011 ◽  
Vol 110-116 ◽  
pp. 113-119 ◽  
Author(s):  
Rajesh Kumar ◽  
Dharamveer Singh
Keyword(s):  
Material Properties ◽  
Plate Theory ◽  
Perturbation Technique ◽  
Micromechanical Model ◽  
Laminated Composite ◽  
Composite Plates ◽  
Second Order Statistics ◽  
Operational Life ◽  
Safety And Reliability ◽  
Random Material Properties

The aim of this paper is to find out the randomness in the material properties on the buckling of laminated composite plate needed for the economy, safety and reliability of the structures and components in their operational life especially for sensitive Aerospace Engineering applications in hygrothermal environments. Micromechanical model has been taken for the analysis .The used methodology is a C0 finite element method based on higher-order shear deformation plate theory for deriving the standard eigenvalue problem. A Taylor series based mean-centered first order perturbation technique is used to find out the second order statistics of the hygrothermal buckling loads under different sets of environmental conditions..The numerical results for deterministic parameters are compared and validated with available literature and random parameters with independent Monte Carlo Simulation. The result shows that the plate is significantly affected by the hygrothermal buckling load.

EFFECT OF RANDOM SYSTEM PROPERTIES ON INITIAL BUCKLING OF COMPOSITE PLATES RESTING ON ELASTIC FOUNDATION

2008 ◽  
Vol 08 (01) ◽  
pp. 103-130 ◽  
Author(s):  
ACHCHHE LAL ◽  
B. N. SINGH ◽  
RAKESH KUMAR
Keyword(s):  
Elastic Foundation ◽  
Material Properties ◽  
Perturbation Technique ◽  
Shear Deformation Theory ◽  
Laminated Composite ◽  
Composite Plates ◽  
Material Constant ◽  
Random System ◽  
Pasternak Model ◽  
Random System Properties

In this paper, the effects of randomness in the material properties and foundation stiffness parameters on the elastic buckling of laminated composite plate resting on elastic foundation subjected to uniform in-plane edge compression are studied. Higher order shear deformation theory has been used for the plates. The interaction between the plate and foundation is included in the formulation of a two-parameter Pasternak model. A C0finite element method is used for treating the random eigenvalue problem. The uncertain lamina material properties and the foundation stiffness parameters are modeled as independent basic random variables. A mean-centered first order perturbation technique is adopted to examine the stochastic characteristics of the buckling load. From the results presented for laminated composite plates resting on elastic foundations with different boundary conditions, the influence of variation of material constant, foundation stiffness parameters, edge in-plane forces, side-to-thickness ratio, plate aspect ratio, and variation in standard deviation of material properties on the buckling response has been investigated. The results have been compared with those available in the literature and from an independent Monte Carlo simulation.

MESHFREE GALERKIN KRIGING MODEL FOR BENDING AND BUCKLING ANALYSIS OF SIMPLY SUPPORTED LAMINATED COMPOSITE PLATES

2013 ◽  
Vol 10 (03) ◽  
pp. 1350011 ◽  
Author(s):  
TINH QUOC BUI ◽  
MINH NGOC NGUYEN
Keyword(s):  
Plate Theory ◽  
Laminated Composite ◽  
Composite Plates ◽  
Kriging Model ◽  
Numerical Approach ◽  
Buckling Analysis ◽  
Laminated Plates ◽  
Kriging Interpolation ◽  
Laminated Composite Plates ◽  
Classical Plate Theory

Further development of the novel meshfree Galerkin Kriging method for bending and buckling analysis of laminated composite plates is the main objective of the present work. The present formulation follows the classical plate theory while the discrete equations are derived from the standard Galerkin weak form. The moving Kriging interpolation technique is used for constructing shape functions, which possess the delta property and thus no special techniques are required for imposing the essential boundary conditions. Various numerical examples with different geometries of plates for both bending and buckling analysis are solved to demonstrate the applicability and the effectiveness of the present approach. The calculated results are compared with reference solutions available in the literature and very good agreements are obtained. It obviously illustrates that the proposed method can be considered as an alternative numerical approach for buckling and bending of laminated plates.

THERMAL BUCKLING OF LAMINATED COMPOSITE PLATES WITH RANDOM GEOMETRIC AND MATERIAL PROPERTIES

2009 ◽  
Vol 09 (02) ◽  
pp. 187-211 ◽  
Author(s):  
VIPIN K. VERMA ◽  
B. N. SINGH
Keyword(s):  
Composite Plate ◽  
Perturbation Technique ◽  
Shear Deformation Theory ◽  
Laminated Composite ◽  
Composite Plates ◽  
Laminated Composite Plates ◽  
Geometric Properties ◽  
Various Boundary Conditions ◽  
The Mean ◽  
Standard Derivation

In this paper, a C o finite element has been employed for deriving an eigenvalue problem using higher order shear deformation theory. The uncertain material and geometric properties are modeled as basic random variables. A mean-centered first order perturbation technique is used to find the mean and standard derivation of the buckling temperature of laminated composite plates — subjected to a uniform temperature rise — with random material and geometric properties. The effects of the modulus ratio, fiber orientation, length-to-thickness ratio, aspect ratio and various boundary conditions on the critical temperature are examined. It is found that small variations in material and geometric properties of the composite plate significantly affect the buckling temperature of the laminated composite plate. The results have been validated with independent Monte Carlo simulation and those available in the literature.

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

Stochastic aeroelastic analysis of laminated composite plate with variable fiber spacing

2021 ◽  
pp. 002199832110408
Author(s):  
Narayan Sharma ◽  
Prasant Kumar Swain ◽  
Dipak Kumar Maiti ◽  
Bhrigu Nath Singh
Keyword(s):  
Perturbation Technique ◽  
Laminated Composite ◽  
Distribution Patterns ◽  
Laminated Plates ◽  
Fiber Distribution ◽  
Various Boundary Conditions ◽  
Aeroelastic Analysis ◽  
Fiber Spacing ◽  
Reliability Method ◽  
Parametric Studies

In this paper, the dynamic and aeroelastic analysis of variable fiber spacing composite (VFSC) laminated plates are carried out. The effects and benefits of changing the fiber distribution pattern on natural frequency and mode shape are explored taking various boundary conditions. Taking cantilever boundary condition flutter characteristics of VFSC plate with different fiber distribution patterns are compared. Further stochasticity of flutter velocity due to randomness in material properties that could arise due to complex manufacturing and fabrication process of VFSC laminates is investigated. The perturbation technique is implemented to perform the stochastic as well as reliability analysis. Various parametric studies are conducted to check the accuracy and efficiency of perturbation technique, by comparing the results with that of Monte Carlo simulation and the first-order reliability method.

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