Abstract
Abstract In this study, a thermal buckling analysis of laminate composite square plate was performed with elliptical hole cutout using the finite element method. Graphite/Epoxy laminate plate used in this study is symmetrical stacking sequence plate [(0/90)2] s . This laminate square plate was subjected to temperature loading with clamped support on all edges. Moreover, the parameters considered were fiber orientation (θ), a/b ratio (elliptical hole), elliptical hole inclination (φ), thermal expansion coefficient ratio (α 1/α 2), and thickness of plates (t). The results showed that as the thermal expansion coefficient ratio changes, the elliptical hole ratio and the elliptical hole inclination have inconsequential effects on the performance of the resistance of laminate composite plates. The maximum values of thermal buckling amplification factor were obtained when the ratio a/b = 1.0, which is a circle cutout,while the minimum values were obtained when the ratio a/b = 0.5, regardless of the thickness of plates. Moreover, the plate with elliptical or circle cutout hole provides about 4% to 9% higher buckling resistance than that of the plate without hole cutout, because when subjected to temperature loading the plate with hole can release stress better than the plate without hole.
Highlights
In this study, a thermal buckling analysis of laminate composite square plate was performed with elliptical hole cutout using the finite element method
The results showed that as the thermal expansion coefficient ratio changes, the elliptical hole ratio and the elliptical hole inclination have inconsequential effects on the performance of the resistance of laminate composite plates
Chen et al [19] studied the thermal buckling of antisymmetric cross-ply laminate composite plates with circular hole
Summary
Abstract: In this study, a thermal buckling analysis of laminate composite square plate was performed with elliptical hole cutout using the finite element method. The first order shear deformation was used for the finite element analysis It demonstrated that as the aspect ratio increases, the optimum fiber orientation and critical buckling load gradually decrease. Chen et al [19] studied the thermal buckling of antisymmetric cross-ply laminate composite plates with circular hole They showed that the effects of thermal expansion and thickness ratio have no influence on the relative buckling temperature. Code developed in MATLAB software was used to analyze thermal buckling with the first order shear deformation theory It proved that the critical thermal buckling loads of symmetric plates are smaller than those of antisymmetric plates. The results presented in previous study illustrated that the effect of plate length/thickness, plate aspect ratio, cutout size, orientation of cutout, and elliptical hole aspect ratio required more detailed investigation. The parameters studied were the effect of fiber orientation (θ), ratio a/b (elliptical hole), elliptical hole inclination (φ), thermal expansion coefficient ratio (α1/α2), and thickness of plate (t)
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