On the Relationship between Engineering Properties and Delamination of Composite Materials

Herakovich, Carl T.

doi:10.1177/002199838101500404

Cited by 110 publications

(48 citation statements)

References 17 publications

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“…It is shown that the strength of a composite is strongly dependent on its stacking sequence [24,25]. For unidirectional continuous carbon/glass fibre-reinforced hybrid composites under flexural loading, it was shown that partial substitution of glass fibres for carbon fibres on the compressive face resulted in improved flexural strength, i.e.…”

Section: Introductionmentioning

confidence: 99%

Effect of stacking sequence on the flexural properties of carbon and glass fibre-reinforced hybrid composites

Dong

Davies

2018

Adv Compos Hybrid Mater

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A study on the flexural properties of carbon and glass fibre-reinforced epoxy hybrid composites is presented in this paper. For the purpose of understanding the effect of stacking sequence on the flexural properties, test specimens of both glass/carbon and sandwich stacking sequences were studied both experimentally and by simulation. The experimental flexural properties were obtained by three-point bend test in accordance with ASTM D7264/D7264M-15. Simulation was achieved with the aid of finite element analysis (FEA) and classical lamination theory (CLT). From the experimental and simulation results, it is concluded that for the hybrid composites with glass/carbon stacking sequences, when glass/epoxy laminas are placed on the compressive face, positive hybrid effects are present. When glass/epoxy laminas are placed on the tensile face, the hybrid effect is dominantly negative. For the sandwich-type hybrid composites, carbon/epoxy laminas should be the skin and glass/epoxy laminas should be the core.

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Section: Introductionmentioning

confidence: 99%

Effect of stacking sequence on the flexural properties of carbon and glass fibre-reinforced hybrid composites

Dong

Davies

2018

Adv Compos Hybrid Mater

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“…10). More delamination was present in the 10 0 specimen in which the mismatch in coefficient of mutual influence is largest [9]. The alternating 45 1 specimens failed in a mode similar to the clustered laminate (Fig.…”

Section: Failure Mechanismsmentioning

confidence: 88%

“…The influence of interlaminar stresses on the prediction of initial failure using the tensor polynomial failure criterion was considered by this author and his colleagues in two previous papers [6,7] where it was shown that the interlaminar shear stress TZx dominates the initiation of failure in graphite-epoxy for fiber angles smaller than 370. The relationship between engineering properties and delamination of finite-width graphite-epoxy laminates was recently studied by this author [9]. It was shown that there is a close correspondence between the mismatch in coefficient of mutual influence of adjacent layers and delamination of angle-ply laminates.…”

Section: Introductionmentioning

confidence: 97%

Influence of Layer Thickness on the Strength of Angle-Ply Laminates

Herakovich

1982

Journal of Composite Materials

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Experimental results are presented showing that the strength and toughness of finite-width angle-ply laminates can be increased significantly by using an alternating layer stacking sequence as opposed to a clustered con figuration. The ultimate tensile stress of an alternating plus/minus θ laminate of the form [(±θ)2] s can be as much as 1.5 times that a clustered configura tion of the form [θ2/—θ2] s. Further, the toughness of the alternating layer configuration can be as much as 2.7 times that of the clustered configuration. These differences are explained analytically through consideration of the in fluence of layer thickness on the magnitude of the interlaminare shear stress and by examination of failed specimens. It is shown that the two laminate configurations exhibit distinctly different failure modes for some fiber angles. Both laminate configurations exhibit catastrophic failure with the damage limited essentially to a small region defined by the length of a single crack across the face of the specimen, parallel to the fiber direction. Results are presented for T300/5208 graphite-epoxy for fiber orientations of 10°, 30 °, and 45 °.

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“…Interlaminar shear stresses (zxz) have been shown to vary qualitatively with the magnitude of mis-match in the 'coefficient of mutual influence' between adjacent layers, which can be reduced by altering the stacking sequence [8]. Similarly, the interlaminar normal stress (az) at any interface varies with the magnitude of the moment due to cry of the lamina about the laminate surface.…”

Section: Laminates: Stacking Sequencementioning

confidence: 99%

“…Herakovich [8] performed a finite element analysis to determine the distribution of interlaminar shear stresses for various stacking sequences of a (0/+ 45/90) laminate and observed that the resistance to delamintion varied with the various stacking sequences.…”

Section: Laminates: Stacking Sequencementioning

confidence: 99%