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

[+] Author and Article Information
A. K. Onkar, C. S. Upadhyay

Department of Aerospace Engineering, Indian Institute of Technology, Kanpur 208016, India

D. Yadav1

Department of Aerospace Engineering, Indian Institute of Technology, Kanpur 208016, Indiady@iitk.ac.in


Corresponding author.

J. Appl. Mech 74(4), 798-809 (Sep 19, 2006) (12 pages) doi:10.1115/1.2711230 History: Received March 06, 2006; Revised September 19, 2006

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.

Copyright © 2007 by American Society of Mechanical Engineers
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Figure 1

Periodic fiber reinforced composite

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Figure 2

Geometry of a laminated composite plate with centrally located cutout

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Figure 3

Representation of transverse function over the thickness of plate: (a) equivalent layer; and (b) layer by layer

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Figure 4

Distribution of the intensity of stress (σ¯11) for [θ∕−θ∕−θ∕θ] square plates with SSSS boundary condition and having different ply orientation: (a)0deg; (b)15deg; (c)30deg; (d)45deg; (e)60deg; (f)75deg; and (g)90deg

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Figure 5

The effect of hole size and ply orientation on the mean critical load parameter for [θ∕−θ∕−θ∕θ] square plates with different boundary conditions: (a) SSSS; (b) SCSC; and (c) SFSF

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Figure 6

The first eigen modes for [θ∕−θ∕−θ∕θ] square plates under SSSS boundary condition with different, (a)0deg; (b)15deg; (c)30deg; (d)45deg; (e)60deg; (f)75deg; and (g)90deg

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Figure 7

Influence of dispersion in all material properties changing simultaneously on the COV of critical load parameter for [θ∕−θ∕−θ∕θ] square laminates with various hole size and different boundary conditions: (a) SSSS; (b) SCSC; and (c) SFSF




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