A Theoretical Model for Predicting Fatigue Crack Growth Rates in Fibre‐reinforced Metal Laminates

Guo, Y. J.; Wu, X.R.

doi:10.1046/j.1460-2695.1998.00076.x

Cited by 52 publications

(39 citation statements)

References 4 publications

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“…56,57 Characterization of the delamination shape and growth of GLARE under cyclic loading is a diffi cult issue that is not yet well understood. In addition, the existing models for predicting crack growth still have a large error with experimental data.…”

Section: Fatigue Behaviormentioning

confidence: 99%

The mechanical behavior of GLARE laminates for aircraft structures

Yang

2005

JOM

288

156

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GLARE (glass-reinforced aluminum laminate) is a new class of fi ber metal laminates for advanced aerospace structural applications. It consists of thin aluminum sheets bonded together with unidirectional or biaxially reinforced adhesive prepreg of high-strength glass fi bers. GLARE laminates offer a unique combination of properties such as outstanding fatigue resistance, high specific static properties, excellent impact resistance, good residual and blunt notch strength, fl ame resistance and corrosion properties, and ease of manufacture and repair. GLARE laminates can be tailored to suit a wide variety of applications by varying the fi ber/resin system, the alloy type and thickness, stacking sequence, fi ber orientation, surface pretreatment technique, etc. This article presents a comprehensive overview of the mechanical properties of various GLARE laminates under different loading conditions.

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Section: Fatigue Behaviormentioning

confidence: 99%

The mechanical behavior of GLARE laminates for aircraft structures

Yang

2005

JOM

288

156

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“…Composite materials are generally regarded as an orthotropic anisotropic body in macrostructure according to their fibrous directions [2]. Their statics problems have been researched in the literature [3][4][5][6][7][8][9][10]. However, the fractures of composite materials often arise in dynamic conditions, so it is extremely significant to study their fracture dynamics problems.…”

Section: Introductionmentioning

confidence: 99%

An Asymmetrical Self-Similar Dynamic Crack Model of Bridging Fiber Pull-Out in Unidirectional Composite Materials

Cheng

2008

International Journal for Computational Methods in Engineering

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When composite materials produce a crack, their fibrous position will form bridges, moreover the crack usually propagates in the modality of asymmetrical self-similarity. In this paper an asymmetrical self-similar dynamic crack model of bridging fiber pull-out in unidirectional composite materials is built. Analytical solutions of the stresses, displacements, stress intensity factors and bridging fiber fracture speeds for this model under the action of moving loads and homogeneous loads, respectively, are acquired by self-similar measures. After those analytical solutions were utilized by superposition theorem, the solutions of arbitrary complex problems could be gained.

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“…Using ultrasonic scanning of specimens, several studies revealed an elliptical delamination shape, Lin and Kao (1996), Marissen (1991), and Takamatsu, et al (1999). A triangular shape was considered by Guo and Wu (1998) in their work with CCT specimens made of GLARE. In another study, Guo and Wu (1999) stated that the delamination shapes are irregular during fatigue and not elliptical in most cases but closer to a triangle.…”

Section: Analysis Model For Fibre-bridgingmentioning

confidence: 99%

“…Under fatigue loading, the cyclic load transfer causes cyclic adhesive shear stresses to initiate fatigue delamination of the adhesive between the fibres and the metal sheets. The effect of the adhesive shear on the bridging stresses has been investigated in recent work by Guo and Wu (1999), Guo and Wu (1998), and Takamatsu, et al (1999). This adhesive deformation is a necessary component for the bridging mechanism in fibremetal laminates.…”

Section: Analysis Model For Fibre-bridgingmentioning

confidence: 99%

Numerical Fracture Mechanics Analysis of Cracked Fibre-Metal Laminates with Cut-Outs

Cudzilo

Tan

2007

EJBE

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The boundary element method (BEM) for two-dimensional numerical stress analysis is employed to investigate crack-face bridging of cracked fibre-metal laminates (FML) with cut-outs in this study. The fracture mechanics prediction of crack growth in these perforated laminates involves the interaction of the geometry and crack size, the delamination between the pre-peg and metal layers, and the extent of fibre-bridging of the crack flanks with the stress field caused by the cut-out. The present work investigates the effects of a stress concentration on the fibre-bridging stress and the stress intensity factor of a bridged crack in fibre-metal laminates. A number of cracked configurations are analyzed and the FML, ARALL2, is considered. The bridging stresses on the crack flanks are modeled in the 2 -D analysis using power-law expressions and with the mechanical properties of the laminate homogenized through the thickness. An iterative scheme is employed to solve for the bridging stresses as they are not known a priori. Three dimensional finite element method (FEM) analyses are also carried out to confirm the validity of the 2-D BEM models.FML's with circular cut-outs will contain high bridging stresses near the cutout resulting in fibre failure there, causing a reduction of the extent of fibre bridging of the crack. Results of the study show a likelihood of fibre failure near the edge of the cut-out and this could lead to a reduction of the bridging length. Comparison of the BEM with the FEM stress intensity factors for the range of problems analyzed reveals that the percentage difference is generally less than about 6%, except for a few cases when the power-law index of 0.5 is assumed. The BEM results indicate an increasing bridging stress and stress intensity factor with decreasing bridging length and the benefits of the fibre bridging of the crack are clearly demonstrated. This numerical study confirms that the 2-D BEM models employed can indeed be used to provide a quick and reasonable estimate of the stress intensity factor for a bridged crack in a FML with a circular cut-out.

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A Theoretical Model for Predicting Fatigue Crack Growth Rates in Fibre‐reinforced Metal Laminates

Cited by 52 publications

References 4 publications

The mechanical behavior of GLARE laminates for aircraft structures

The mechanical behavior of GLARE laminates for aircraft structures

An Asymmetrical Self-Similar Dynamic Crack Model of Bridging Fiber Pull-Out in Unidirectional Composite Materials

Numerical Fracture Mechanics Analysis of Cracked Fibre-Metal Laminates with Cut-Outs

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