Buckling analysis of laminated composite plates [(θ/−θ)] containing an elliptical notch

Ouinas, Djamel; Achour, Belkacem

doi:10.1016/j.compositesb.2013.07.011

Cited by 30 publications

(21 citation statements)

References 11 publications

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“…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%

“…They have pointed out that the critical buckling loads attain important maximum values when the fibres are oriented in the range of 50ο to 90ο whereas the minimum values have been obtained when the fibres are perpendicular to the applied pressure. Djamel ouinas and Achour [12] have taken the boron epoxy laminated square plates arranged in (0°/-0°) under uniaxial compression and they identified that the buckling load decreases by increasing the geometric ratio of the elliptical cutout. From the above literature, the considerable work has been carried out for buckling behaviour of the circular, elliptical cut out under uniaxial, biaxial and combined loads.…”

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

View full text Add to dashboard Cite

show abstract

“…Shanmugam et al [10] used the FEM to develop a design formula to determine the ultimate load carrying capacity of axially compressed square plates with centrally located perforations. Ouinas and Achour [11] analysed the buckling of square plates with elliptical notch, investigated the impact of the size and location of the notch, as well as the influence of unsymmetrical layer of layout on critical force. Dinesh, Kumar and Singh [12] studied the influence of boundary conditions and post-buckling behaviour of quasiisotropic laminate [45/-45/0/90]2s with different cut shapes.…”

Section: Introductionmentioning

confidence: 99%

Stability of rectangular plates with notch using FEM

Falkowicz

2017

ITM Web Conf.

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Abstract. Buckling behaviour analysis of thin-walled composite plate under an axial compressive force is presented. The plate with central notch is made of a carbon-epoxy composite -a laminate consisting of eight symmetrically oriented plies. This paper addresses an influence of notch on buckling behaviour of laminated composite plates. In this analysis, FEM was applied to perform parametric studies on various plates based on stacking sequences, shape of notch, and its size. Buckling behaviour of laminated composite plates under an axial compression load is studied using ABAQUSS software.

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“…They indicated that the critical load of buckling reaches its maximum values when the fibers are oriented in an interval varying from 50° to 90°. Ouinas and Achour (2013) have studied the effect of the presence of an elliptical notch on the buckling of laminated boron/ epoxy plates arranged anti-symmetrically [(θ/ -θ)].…”

Section: Introductionmentioning

confidence: 99%

Numerical modeling of defective hybrid composite plates

Achour

2017

Int. j. adv. appl. sci

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It is known that the optimization of the positioning of reinforcements within a composite material is likely to increase significantly the performance of a structure. Accordingly, buckling is the most critical failure mode for notched and non-stiffened plates under axial compressive stress. In this study, the buckling response of laminated plates made of hybrid composite materials with and without elliptical notches is analyzed using finite element methods. The plates are made of carbon/epoxy/aluminum and arranged in following ordered manner [Al/ (θ/-θ) /Al]. The resistance to buckling of the hybrid plates under uniaxial compression is examined according to fiber orientations, the orientation of the notch and finally the thickness of the aluminum layer in the composite material. The results showed that when the fibers are at = 90 0 the amplification of the critical load of buckling in the hybrid notchless plate is of the order of 59% and 27.66% for a thickness of the aluminum layer tAl= 0.2mm and 0.127mm respectively. The elliptical notch oriented at 0° reduces the maximum load four times more than when oriented at 90 o .

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Buckling analysis of laminated composite plates [(θ/−θ)] containing an elliptical notch

Cited by 30 publications

References 11 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

Stability of rectangular plates with notch using FEM

Numerical modeling of defective hybrid composite plates

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