Strength prediction of CFRP plates with a hole under biaxial compression-tension

Soutis, C.; Filiou, C.; Pateau, V.

doi:10.2514/6.1998-1701

Cited by 4 publications

(6 citation statements)

References 8 publications

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“…The Soutis-Fleck fracture model [2] is based on the following two criteria: i) Stable crack growth: It is postulated that microbuckling occurs over a distance l from the hole when the average stress over this distance reaches the critical stress of the unnotched laminate, XQ s :…”

Section: Compressive Failure Analysismentioning

confidence: 99%

“…Ultrasonic C-scan images and X-ray shadow radiographs revealed that the shape of the impact damage is approximately circular or elliptical (equivalent to an open hole). A fracture mechanics model was developed by Soutis et al [2,3] to predict the critical buckling length and ultimate load. Using the independently measured laminate parameters of uniaxial compressive strength and mode I fracture toughness, the model successfully predicted the residual strength of various carbon fibre systems and lay-ups; in most cases the error was less than 10%.…”

Section: Introductionmentioning

confidence: 99%

“…The mechanism of in-plane failure of carbon fibre-epoxy multidirectional laminates with a stress concentrator subjected to uniaxial compression is well established [1][2][3][4]. Local microbuckling in the 0 0 plies surrounded by delamination grows laterally from the hole edge as the applied load is increased.…”

Section: Introductionmentioning

confidence: 99%

“…Using equations(2) and(4) [[ s is plotted as a function of damage length l. The failure strength of the stiffened panel with a hole and the critical microbuckling length are obtained from the point where the two curves intersect(Fig. 2).…”

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confidence: 99%

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Prediction of the Compresion-After-Impact Strength of Thin-Skin Stiffened Composite Panels

Zhuk

Soutis

Guz

2000

Advanced Composites Letters

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The compressive response of thin-skin stiffened composite panels with low velocity impact damage is examined. The finite element method together with the Soutis-Fleck fracture mechanics model is used to predict damage initiation in the form of fibre microbuckling in the 0° plies, propagation and final failure; in the model the impact damage is replaced with an equivalent circular or elliptical open hole. Theoretical results are compared to experimental data and found in good agreement.

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Section: Compressive Failure Analysismentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

mentioning

confidence: 99%

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Prediction of the Compresion-After-Impact Strength of Thin-Skin Stiffened Composite Panels

Zhuk

Soutis

Guz

2000

Advanced Composites Letters

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“…There has been a great deal of researches conducted on the characteristics of fibrous composites and their advantages over conventional materials in recent years (Joseph et al, 2002;Wang et al, 2006a;Park and Kang, 2002;Soutis et al, 2002;Wang et al, 2007). Among various fibrous composites, carbon/phenolic composites possess many excellent dynamic performances such as high dynamic strength and rigidity, superior impact absorption.…”

Section: Introductionmentioning

confidence: 98%

A study on mechanical properties of carbon/phenolic composites

Wang

Zhang

et al. 2008

Mechanics of Materials

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A Micromechanics-Based Finite Element Model for Compressive Failure of Notched Uniply Composite Laminates Under Remote Biaxial Loads

Ahn

Waas

1999

Journal of Engineering Materials and Technology

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A micromechanics based failure initiation predictive capability for analyzing notched composite laminates loaded remotely in multiaxial compression is reported. The model relies on the results from a previous experimental study that investigated compression failure mechanisms in special “uniply” composite laminates. The finite element method (FEM) was used in the solution process. The experimental results showed that the dominant mode of failure initiation was kink banding near the hole edge. The kink band was confined in extent to a distance within one half of the hole radius. The fibers within the kink band were rotated both in plane and out of the plane of the laminate. The position of the kink band with respect to the center of the notch depended on the remote biaxial load ration. In the FEM, the region in which kink banding takes place is contained within a finite size rectangular area, and is meshed as an alternatingly stacked region of fiber and matrix layers. The values of boundary loads on this rectangular area which correspond to kink banding is related to the remotely applied loads via an available closed form analysis for orthotropic laminates. Good agreement is found between experiment and analysis for a wide range of notch sizes.

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Strength prediction of CFRP plates with a hole under biaxial compression-tension

Cited by 4 publications

References 8 publications

Prediction of the Compresion-After-Impact Strength of Thin-Skin Stiffened Composite Panels

Prediction of the Compresion-After-Impact Strength of Thin-Skin Stiffened Composite Panels

A study on mechanical properties of carbon/phenolic composites

A Micromechanics-Based Finite Element Model for Compressive Failure of Notched Uniply Composite Laminates Under Remote Biaxial Loads

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