Fracture Criterion for Notched Thin Composite Laminates

Vaidya, Rajesh S.; Sun, C. T.

doi:10.2514/2.93

Cited by 40 publications

(14 citation statements)

References 6 publications

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“…Published work in the literature [4,6,[9][10][11] suggest that the translaminar fracture toughness of cross-ply laminates and of 0 • ply-block depends on the thickness of that ply-block. While it can be speculated that delamination may play a meaningful role in this (the extent of delamination in thick ply-block laminates is larger [10]), the analysis of the 20 translaminar fracture surfaces of 0 • plies of different thicknesses reveals significant differences [10].…”

Section: Introductionmentioning

confidence: 99%

“…The ply-block thickness effect on the onset of micro-cracking and delamination has been extensively analysed [1][2][3][4][5][6]. Kim and Soni [7] investigated several quasi-isotropic layups, with different layups sequences while keeping the same ratio of each constituent ply; the authors showed that the delamination 5 threshold decreased with increasing ply-block thickness.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Thickness-dependence of the translaminar fracture toughness: Experimental study using thin-ply composites

Teixeira

Pinho

Robinson

2016

Composites Part A: Applied Science and Manufacturing

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Thickness-dependence of the translaminar fracture toughness: Experimental study using thin-ply composites

Teixeira

Pinho

Robinson

2016

Composites Part A: Applied Science and Manufacturing

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“…For the purpose of demonstrating numerically the aforementioned concepts, the material selected for generating the necessary simulated experimental data is a typical laminate constructed from an epoxy resin/fiber laminae system of type AS4/3506-1. The elastic moduli of this material are listed in Table 2 according to several sources [3,54,[57][58][59][60][61][62].…”

Section: Numerical Resultsmentioning

confidence: 99%

Data-Driven Design Optimization for Composite Material Characterization

Michopoulos

Hermanson

Iliopoulos³

et al. 2011

Journal of Computing and Information Science in Engineering

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The main goal of the present paper is to demonstrate the value of design optimization beyond its use for structural shape determination in the realm of the constitutive characterization of anisotropic material systems such as polymer matrix composites with or without damage. The approaches discussed are based on the availability of massive experimental data representing the excitation and response behavior of specimens tested by automated mechatronic material testing systems capable of applying multiaxial loading. Material constitutive characterization is achieved by minimizing the difference between experimentally measured and analytically computed system responses as described by surface strain and strain energy density fields. Small and large strain formulations based on additive strain energy density decompositions are introduced and utilized for constructing the necessary objective functions and their subsequent minimization. Numerical examples based on both synthetic (for one-dimensional systems) and actual data (for realistic 3D material systems) demonstrate the successful application of design optimization for constitutive characterization.

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“…A number of studies (4-9) have been carried out on the fracture toughness associated with fibre-dominated tensile failure. Vaidya and Sun (10) studied the fracture characteristics of composite laminates and developed a fracture criterion which showed that the critical stress intensity factor for fibre failure is a material constant. Blanco et al (11) investigated different geometric configurations of the CT specimen for the characterisation of the tensile intralaminar fracture toughness of woven composite laminates.…”

Section: Introductionmentioning

confidence: 99%

An experimental method to determine the intralaminar fracture toughness of high-strength carbon-fibre reinforced composite aerostructures

et al. 2018

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Carbon fibres with high tensile strength are being increasingly utilised in the manufacture of advanced composite aerostructures. A Modified Compact Tension (MCT) specimen is often deployed to measure the longitudinal intralaminar fracture toughness but a high tensile strength often leads to premature damage away from the crack tip. We present an approach whereby the MCT specimen is supported by external fixtures to prevent premature damage. In addition, we have developed a novel measurement technique, based on the fibre failure strain and C-scanning, to determine the crack length in the presence of surface sublaminate delamination which masks the crack tip location. A set of cross-ply specimens, with a ((90/0)s)4 layup, were manufactured from an IMS60/epoxy composite system Two different data reduction schemes, compliance calibration and the area method, are used to determine the fibre-dominated initiation and propagation intralaminar fracture toughness values. Propagation values of fracture toughness were measured at 774.9 ± 5.2% kJ/m2 and 768.5 ± 4.1% kJ/m2, when using the compliance calibration method and the area method, respectively. Scanning Electron Microscopy (SEM) is carried out on the fracture surface to obtain insight into the damage mechanism of high-tensile-strength fibre-reinforced unidirectional composites. The measured tensile fracture toughness value is used in a fully validated computational model to simulate the physical test.

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Fracture Criterion for Notched Thin Composite Laminates

Cited by 40 publications

References 6 publications

Thickness-dependence of the translaminar fracture toughness: Experimental study using thin-ply composites

Thickness-dependence of the translaminar fracture toughness: Experimental study using thin-ply composites

Data-Driven Design Optimization for Composite Material Characterization

An experimental method to determine the intralaminar fracture toughness of high-strength carbon-fibre reinforced composite aerostructures

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