Compressive strength of composite laminates following free edge impact

Andrew T Rhead; D Marchant; Richard Butler

doi:10.1016/j.compositesa.2009.10.024

Compressive strength of composite laminates following free edge impact

Andrew T Rhead, D Marchant, Richard Butler

Department of Mechanical Engineering

Research output: Contribution to journal › Article › peer-review

48 Citations (SciVal)

Abstract

Barely Visible Impact Damage (BVID) can occur when laminated composite material is subject to free edge Impact loads in the plane of the laminate and can result in a significant reduction in compressive strength caused by buckle-driven delamination. This paper will report on a semi-analytical fracture mechanics model that predicts the Compression After Impact (CAI) strength of composite laminates subject to in-plane free edge Impact. Compression testing has been undertaken on three impacted coupons in order to validate the theoretical results. Analytical results are shown to be on average within 10% of experimental values for the strain at which propagation of damage occurs.

Original language	English
Pages (from-to)	1056-1065
Number of pages	10
Journal	Composites Part A Applied Science and Manufacturing
Volume	41
Issue number	9
DOIs	https://doi.org/10.1016/j.compositesa.2009.10.024
Publication status	Published - Sept 2010
Event	10th International Conference on Deformation and Fracture of Composites (DFC-10) - Sheffield, UK United Kingdom Duration: 15 Apr 2009 → 17 Apr 2009

Keywords

free edge impact
laminates
damage tolerance
analytical modelling

Access to Document

10.1016/j.compositesa.2009.10.024

Cite this

@article{6c8ebf2486ec431596668472b5b9fa65,

title = "Compressive strength of composite laminates following free edge impact",

abstract = "Barely Visible Impact Damage (BVID) can occur when laminated composite material is subject to free edge Impact loads in the plane of the laminate and can result in a significant reduction in compressive strength caused by buckle-driven delamination. This paper will report on a semi-analytical fracture mechanics model that predicts the Compression After Impact (CAI) strength of composite laminates subject to in-plane free edge Impact. Compression testing has been undertaken on three impacted coupons in order to validate the theoretical results. Analytical results are shown to be on average within 10\% of experimental values for the strain at which propagation of damage occurs.",

keywords = "free edge impact, laminates, damage tolerance, analytical modelling",

author = "Rhead, \{Andrew T\} and D Marchant and Richard Butler",

year = "2010",

month = sep,

doi = "10.1016/j.compositesa.2009.10.024",

language = "English",

volume = "41",

pages = "1056--1065",

journal = "Composites Part A Applied Science and Manufacturing",

issn = "1359-835X",

publisher = "Elsevier",

number = "9",

note = "10th International Conference on Deformation and Fracture of Composites (DFC-10) ; Conference date: 15-04-2009 Through 17-04-2009",

}

TY - JOUR

T1 - Compressive strength of composite laminates following free edge impact

AU - Rhead, Andrew T

AU - Marchant, D

AU - Butler, Richard

PY - 2010/9

Y1 - 2010/9

N2 - Barely Visible Impact Damage (BVID) can occur when laminated composite material is subject to free edge Impact loads in the plane of the laminate and can result in a significant reduction in compressive strength caused by buckle-driven delamination. This paper will report on a semi-analytical fracture mechanics model that predicts the Compression After Impact (CAI) strength of composite laminates subject to in-plane free edge Impact. Compression testing has been undertaken on three impacted coupons in order to validate the theoretical results. Analytical results are shown to be on average within 10% of experimental values for the strain at which propagation of damage occurs.

AB - Barely Visible Impact Damage (BVID) can occur when laminated composite material is subject to free edge Impact loads in the plane of the laminate and can result in a significant reduction in compressive strength caused by buckle-driven delamination. This paper will report on a semi-analytical fracture mechanics model that predicts the Compression After Impact (CAI) strength of composite laminates subject to in-plane free edge Impact. Compression testing has been undertaken on three impacted coupons in order to validate the theoretical results. Analytical results are shown to be on average within 10% of experimental values for the strain at which propagation of damage occurs.

KW - free edge impact

KW - laminates

KW - damage tolerance

KW - analytical modelling

UR - https://www.scopus.com/pages/publications/77955429877

UR - http://dx.doi.org/10.1016/j.compositesa.2009.10.024

U2 - 10.1016/j.compositesa.2009.10.024

DO - 10.1016/j.compositesa.2009.10.024

M3 - Article

SN - 1359-835X

VL - 41

SP - 1056

EP - 1065

JO - Composites Part A Applied Science and Manufacturing

JF - Composites Part A Applied Science and Manufacturing

IS - 9

T2 - 10th International Conference on Deformation and Fracture of Composites (DFC-10)

Y2 - 15 April 2009 through 17 April 2009

ER -

Compressive strength of composite laminates following free edge impact

Abstract

Keywords

Access to Document

Other files and links

Fingerprint

Aerostructural Efficiency

EQUIPMENT FOR MULTIPLE PROJECTS: TESTING AND VISUALIZATION FOR AEROSPACE RESEARCH

Cite this

Compressive strength of composite laminates following free edge impact

Abstract

Keywords

Access to Document

Other files and links

Fingerprint

Projects

Aerostructural Efficiency

EQUIPMENT FOR MULTIPLE PROJECTS: TESTING AND VISUALIZATION FOR AEROSPACE RESEARCH

Cite this