Stability and failure of composite laminates with various shaped cutouts under combined in-plane loads

Kumar, Dinesh; Singh, S. B.

doi:10.1016/j.compositesb.2011.09.005

Cited by 33 publications

(14 citation statements)

References 17 publications

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“…The details of the converged study are in Table- The commercial FEA software ANSYS has been used for the present study. In order to find the accuracy of the software results, it has been corroborated by comparing the results with those available in literatures [7][8][9][10]. [7] 17.7 18.620 Dinesh et al [8] 16.4 16.360 Dinesh et al [9] 11.7 11.615 Dinesh et al [10] 16.5 16.756 Djamel ouinas et al [12] 40 40.571…”

Section: A Convergence Studymentioning

confidence: 84%

“…Anil et al [5] have addressed the Stability effect of square symmetrical angle ply laminate with and without rectangular cutout by applying the in plane compressive and bi axial loading using Simple higher order shear deformation theory. Dinesh Kumar & Singh [6,7,8,9,10] have analysed the buckling behaviour of the square Quasi-isotropic laminate with various shaped cutouts (circle, square, diamond, horizontal ellipse and vertical ellipse) with different inplane and flexural boundary and uniaxial compression, inplane shear and combined loading conditions by computer program based on FEM using First Order Shear Deformation Theory FSDT. Hamani et al [11] have determined the effect of fibre orientation on the critical buckling load of symmetrical laminated composite plates having a crack emanating from a circular notch.…”

Section: Introductionmentioning

confidence: 99%

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Linear Buckling behaviour of Composite Laminate [(θ/-θ)] with various shaped cutout using FEM

et al. 2019

IJEAT

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In this paper, the buckling behavior has been investigated on square laminate made of Woven-glass-polyester composite with various shaped cutouts (i.e., circle, square, vertical rectangle, horizontal rectangle, vertical ellipse, horizontal ellipse) numerically. The composite laminates have been arranged in asymmetrical order as [(θ/-θ)]. The laminated plate that is subjected to uniaxial compression has been emphasized on the laminate along with the effect of layer orientation, effect of cutout ratio and effect of cutout angle. The result shows that the minimum buckling load is obtained at 45° and the maximum buckling load attained at 0° and 90°for all laminates by increasing the layer orientation. For cutout ratio, the maximum and minimum load is obtained for the smallest and largest cutout ratio in all cutout shapes. Increasing the cutout angle, the square cutout exhibits the minimum load at 60°. In elliptical cutouts, the load is decreasing and increasing gradually while they are aligned in along and perpendicular to the loading directions. The rectangular cutouts positioned vertically and horizontally the load is decreasing up to 30° and 60°and then increasing up to 90°.

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Section: A Convergence Studymentioning

confidence: 84%

Section: Introductionmentioning

confidence: 99%

Linear Buckling behaviour of Composite Laminate [(θ/-θ)] with various shaped cutout using FEM

et al. 2019

IJEAT

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“…Falzon et al [5] showed that for a quasi-isotropic panel under in-plane shear load the optimum cutout shape was a diamond rather than the conventional circular. From the results of Kumar and Singh [6], quasi-isotropic laminate under combined in-plane loads with elliptical vertical cutout has the maximum buckling load and post-buckling strengths, whereas the laminate with elliptical-horizontal cutout has the minimum strengths. With the same composite laminate and loads, the effects of flexural boundary conditions on buckling and post-buckling responses with and without a central cutout of various shapes was carried out using finite element method [7].…”

Section: Introductionmentioning

confidence: 96%

Buckling and post-buckling of a composite C-section with cutout and flange reinforcement

Guo

Zhang

et al. 2014

Composites Part B: Engineering

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a b s t r a c tThis paper presents an investigation into the effect of cutout and flange reinforcement on the buckling and post-buckling behaviour of a carbon/epoxy composite C-section structure. The C-section having a cutout in the web is clamped at one end and subjected to a shear load at the other free end. Three different stiffener reinforcements were investigated in finite element analysis by using MSC Nastran. Buckling load was predicted by using both linear and nonlinear FE analysis. Experiments were carried out to validate the numerical model and results. Subsequently post-buckling analysis was carried out by predicting the load-deflection response of the C-section beam in nonlinear analysis. Tsai-Wu failure criterion was used to detect the first-play-failure load. The effect of circular and diamond cutout shape and effective flange reinforcements were investigated. The results show that the cutout and reinforcement have little effect on the buckling stability. However an L-shape stiffener to reinforce the C-section flange can improve the critical failure load by 20.9%.

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“…The vibration processes in plates with notches and cracks are studied in [3,7]. The influence of holes of various shapes on the strain state of objects is examined in [5,9,10,13]. A nonlinear analysis of the deformation of shells with holes and rigid inclusions was carried out in [6,11].…”

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confidence: 99%

Influence of a Patch on the Deformation of an Elastic Plate with an Edge Notch Under the Action of a Shockwave

2014

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The behavior of a thin elastic plate with an edge notch under the action of a weak shock wave in air is studied experimentally. The effect of a patch placed either at the bottom or at the top of the notch on the deformation process is analyzed Keywords: thin elastic plate, edge notch, weak shock wave, deformation process Introduction. Structural members with special-purpose or process-induced inhomogeneities such as holes, notches, cracks, and cuts are widely used in various fields of engineering. The effect of such inhomogeneities on the deformation, vibration, stability, and fracture of structures or their elements is addressed in a great many studies.Let us mention some recent publications. Stress fields in beams with a different number of notches of different depth were determined in [1], where the possibility of controlled redistribution of stresses was also discussed. The vibration processes in plates with notches and cracks are studied in [3,7]. The influence of holes of various shapes on the strain state of objects is examined in [5,9,10,13]. A nonlinear analysis of the deformation of shells with holes and rigid inclusions was carried out in [6,11]. The effect of cracks on deformation and fracture is addressed in [8,14,15]. The strains in a thin elastic plate with an edge notch under the action of a shock wave recorded in [4] show that the period of vibrations depends on the length of the notch and that the notch has a strong effect on the strain state of the plate when the strains reach their maximum. Recently, there have been studies on structural repair with various patches over holes or cracks. The reinforcement of plates with circular and elliptic holes with patches tightly attached to the plate along the entire edge of holes was addressed in [2]. The behavior of loaded steel plates with a crack reinforced with a carbon fiber composite was studied in [12] using the finite-element method. A boundary-element analysis of cracked sheets repaired with bonded anisotropic patches was performed in [15].Here we will discuss experimental results on the effect of a small (compared with the notch length) patch on the maximum-strain deformation of a notched plate under the action of a normally incident long shock wave.1. Experimental Procedure. The dynamic test is schematized in Fig. 1, which shows measuring section 1 at the end of a diaphragm-type shock tube, shock wavefront 2 (arrows indicate its propagation direction), test plate 3 with resistance strain gages 4, piezoelectric transducers 5 that detect the instances (displayed on oscillograph 6) the wavefront passes them, L-1250 unit 7, and computer 8.The rectangular test plate with a thickness of 2.8 mm, width a = 139 mm, and length l = 210 mm is made from a glass-fiber laminate with density r = 1.7 g/cm 3 and elastic modulus Å = 2.6×10 10 Pa. The plate with two short edges clamped had an edge notch of width 0.5 mm and length 38 mm (which is approximately 0.27 mm of the length a of the short side) parallel to the clamped edges and originating at the middle of...

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Stability and failure of composite laminates with various shaped cutouts under combined in-plane loads

Cited by 33 publications

References 17 publications

Linear Buckling behaviour of Composite Laminate [(θ/-θ)] with various shaped cutout using FEM

Linear Buckling behaviour of Composite Laminate [(θ/-θ)] with various shaped cutout using FEM

Buckling and post-buckling of a composite C-section with cutout and flange reinforcement

Influence of a Patch on the Deformation of an Elastic Plate with an Edge Notch Under the Action of a Shockwave

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