Buckling Behavior of Laminated Composite Plates

Baba, Buket Okutan

doi:10.1177/0731684407079515

Cited by 53 publications

(26 citation statements)

References 13 publications

(19 reference statements)

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“…Baba [19] and Baba and Baltaci [20] studied the effect of support conditions on the buckling load laminated plates with circular in semicircular cutouts under axial compression. They found that the buckling load of clamped-clamped plates is 75% higher than the buckling load of simply supported plates, and 50% for the case of clamped-pinned boundary condition.…”

Section: Introductionmentioning

confidence: 99%

Influence of cut-out hole on multi-layer Kevlar-29/epoxy composite laminated plates

et al. 2013

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a b s t r a c tThis paper presented the effect of cutout hole on multi layer of Kevlar-29/epoxy composite laminated plates this effect occurred and fiber orientation angle. An experimental procedure was developed to study the performance of these effects under quasi-static compressive and tensile load using a servo-hydraulic testing machine. The work involved investigation on the variety of orientation angles of Kevlar-29 fiber. The ultimate load of failure for each Kevlar-29/epoxy laminated plates had been determined and specified the optimum angle orientation and the load reduction due to the effect of fiber orientation angle (+45°/À45°) was low in the case for compared (0°/90°) orientation angle of fiber. To simulate this problem the researcher used Explicit Mesh for AUTODYN under ANSYS-12.1 software, where the researcher found that the results obtained via this simulation agreed reasonably well with the experimental results and the maximum difference between the experimental conditions and the simulation was 5.8%.

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Section: Introductionmentioning

confidence: 99%

Influence of cut-out hole on multi-layer Kevlar-29/epoxy composite laminated plates

et al. 2013

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“…Throughout operation the composite laminate plates are generally subjected to compression loads that may basis buckling if overloaded. Consequently their buckling behaviors are significant factors in safe and reliable design of these structures [3]. For predicting the buckling load and buckling mode form of a structure in the finite element program, the linear (or eigenvalue) buckling analysis is an existing technique for estimation [4].…”

Section: Introductionmentioning

confidence: 99%

Buckling analysis of laminated composite plates with an elliptical/circular cutout using FEM

Komur

Şen

Ataş

et al. 2010

Advances in Engineering Software

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“…The thin walled composite structures which are widely used become unstable when they are subjected to mechanical or thermal loads leading to buckling. Accordingly, their behaviors in buckling are significant factors in safe and reliable design (Baba, 2007). Baba and Baltaci (2007) have performed a buckling analysis of a laminated composite rectangular plate having a circular hole at the center.…”

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 Behavior of Laminated Composite Plates

Cited by 53 publications

References 13 publications

Influence of cut-out hole on multi-layer Kevlar-29/epoxy composite laminated plates

Influence of cut-out hole on multi-layer Kevlar-29/epoxy composite laminated plates

Buckling analysis of laminated composite plates with an elliptical/circular cutout using FEM

Numerical modeling of defective hybrid composite plates

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