Thickness effect on Mode I trans-laminar fracture toughness of quasi-isotropic carbon/epoxy laminates

Xiaodong Xu; Aakash Paul; Michael R. Wisnom

doi:10.1016/j.compstruct.2018.11.045

Thickness effect on Mode I trans-laminar fracture toughness of quasi-isotropic carbon/epoxy laminates

Xiaodong Xu^*, Aakash Paul, Michael R. Wisnom

^*Corresponding author for this work

Research output: Contribution to journal › Article (Academic Journal) › peer-review

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Abstract

The thickness dependency of trans-laminar fracture toughness was studied in centre-notched quasi-isotropic IM7/8552 carbon/epoxy laminates with central double 0° plies with thicknesses between 1 and 8 mm. A reduction in trans-laminar fracture toughness with thickness was measured experimentally in the specimens with a 25.4 mm notch. For specimens with a shorter 12.7 mm notch, no significant dependency on specimen thickness was found. The thickness dependency was captured in detailed Finite Element (FE) models with cohesive interface elements for sub-critical damage and a Weibull criterion for fibre breakage. The reason for the thickness dependency is explained through the damage states of the individual plies which determine whether or not premature fracture occurs before the damage process zone is fully developed.

Original language	English
Pages (from-to)	145-151
Number of pages	7
Journal	Composite Structures
Volume	210
Early online date	16 Nov 2018
DOIs	https://doi.org/10.1016/j.compstruct.2018.11.045
Publication status	Published - 15 Feb 2019

Research Groups and Themes

Bristol Composites Institute ACCIS

Keywords

Laminates
Fracture toughness
Stress concentrations
Finite element analysis (FEA)
Thickness effect

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10.1016/j.compstruct.2018.11.045

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title = "Thickness effect on Mode I trans-laminar fracture toughness of quasi-isotropic carbon/epoxy laminates",

abstract = "The thickness dependency of trans-laminar fracture toughness was studied in centre-notched quasi-isotropic IM7/8552 carbon/epoxy laminates with central double 0° plies with thicknesses between 1 and 8 mm. A reduction in trans-laminar fracture toughness with thickness was measured experimentally in the specimens with a 25.4 mm notch. For specimens with a shorter 12.7 mm notch, no significant dependency on specimen thickness was found. The thickness dependency was captured in detailed Finite Element (FE) models with cohesive interface elements for sub-critical damage and a Weibull criterion for fibre breakage. The reason for the thickness dependency is explained through the damage states of the individual plies which determine whether or not premature fracture occurs before the damage process zone is fully developed.",

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T1 - Thickness effect on Mode I trans-laminar fracture toughness of quasi-isotropic carbon/epoxy laminates

AU - Xu, Xiaodong

AU - Paul, Aakash

AU - Wisnom, Michael R.

PY - 2019/2/15

Y1 - 2019/2/15

N2 - The thickness dependency of trans-laminar fracture toughness was studied in centre-notched quasi-isotropic IM7/8552 carbon/epoxy laminates with central double 0° plies with thicknesses between 1 and 8 mm. A reduction in trans-laminar fracture toughness with thickness was measured experimentally in the specimens with a 25.4 mm notch. For specimens with a shorter 12.7 mm notch, no significant dependency on specimen thickness was found. The thickness dependency was captured in detailed Finite Element (FE) models with cohesive interface elements for sub-critical damage and a Weibull criterion for fibre breakage. The reason for the thickness dependency is explained through the damage states of the individual plies which determine whether or not premature fracture occurs before the damage process zone is fully developed.

AB - The thickness dependency of trans-laminar fracture toughness was studied in centre-notched quasi-isotropic IM7/8552 carbon/epoxy laminates with central double 0° plies with thicknesses between 1 and 8 mm. A reduction in trans-laminar fracture toughness with thickness was measured experimentally in the specimens with a 25.4 mm notch. For specimens with a shorter 12.7 mm notch, no significant dependency on specimen thickness was found. The thickness dependency was captured in detailed Finite Element (FE) models with cohesive interface elements for sub-critical damage and a Weibull criterion for fibre breakage. The reason for the thickness dependency is explained through the damage states of the individual plies which determine whether or not premature fracture occurs before the damage process zone is fully developed.

KW - Laminates

KW - Fracture toughness

KW - Stress concentrations

KW - Finite element analysis (FEA)

KW - Thickness effect

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DO - 10.1016/j.compstruct.2018.11.045

M3 - Article (Academic Journal)

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SN - 0263-8223

VL - 210

SP - 145

EP - 151

JO - Composite Structures

JF - Composite Structures

ER -

Thickness effect on Mode I trans-laminar fracture toughness of quasi-isotropic carbon/epoxy laminates

Abstract

Research Groups and Themes

Keywords

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