International Journal of Scientific Engineering and Technology

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Buckling Behavior of an Orthotropic Composite Laminate Using Finite Element Analysis


Affiliations
1 Department of Applied Mechanics, Maulana Azad National Institute of Technology, Bhopal, India
 

The effect of fibre orientation on buckling behaviour in a rectangular composite laminate with central circular hole under uniform in-plane loading has been studied by using finite element method. The critical buckling loads with different fibre orientation in an orthotropic composite laminate (E-glass/epoxy) were obtained. The deformation behaviour of the plate is shown for modes, i=1,2. Studies are carried out for three D/A ratio (where D is hole diameter and A is plate width) with different plate thickness (number of layers). The finite element formulation is carried out in the analysis section of the ANSYS software.

Keywords

Orthotropic Composite Laminates, Fibre Orientation, Buckling Analysis, Eigen Value, ANSYS.
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  • Buckling Behavior of an Orthotropic Composite Laminate Using Finite Element Analysis

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Authors

Priyanka Dhurvey
Department of Applied Mechanics, Maulana Azad National Institute of Technology, Bhopal, India
N. D. Mittal
Department of Applied Mechanics, Maulana Azad National Institute of Technology, Bhopal, India

Abstract


The effect of fibre orientation on buckling behaviour in a rectangular composite laminate with central circular hole under uniform in-plane loading has been studied by using finite element method. The critical buckling loads with different fibre orientation in an orthotropic composite laminate (E-glass/epoxy) were obtained. The deformation behaviour of the plate is shown for modes, i=1,2. Studies are carried out for three D/A ratio (where D is hole diameter and A is plate width) with different plate thickness (number of layers). The finite element formulation is carried out in the analysis section of the ANSYS software.

Keywords


Orthotropic Composite Laminates, Fibre Orientation, Buckling Analysis, Eigen Value, ANSYS.