Behaviour of fibre-metal laminates subjected to localised blast loading: Part I-Experimental observations

G. S. Langdon; S. L. Lemanski; G. N. Nurick; M. C. Simmons; W. J. Cantwell; G. K. Schleyer

doi:10.1016/j.ijimpeng.2006.05.008

Behaviour of fibre-metal laminates subjected to localised blast loading: Part I-Experimental observations

G. S. Langdon, S. L. Lemanski, G. N. Nurick, M. C. Simmons, W. J. Cantwell, G. K. Schleyer

Aerospace Engineering

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

121 Scopus citations

Abstract

This two-part article examines the behaviour of aluminium alloy-glass fibre-reinforced polypropylene-based fibre-metal laminates (FMLs) subjected to localised explosive blast loading. Part I presents observations from the experiments on samples of varying thickness and material distribution, and investigates the influence of stacking configuration. This extensive study examines panels which have between two and five layers of aluminium, and up to eight plies of composite between each pair of aluminium layers. Diamond and cross-shaped back face damage is observed and varies according to panel thickness. Pitting, global displacement and ring buckling of the front face are also discerned. Some observations are related to wave propagation effects. Part II reports a quantitative analysis of the experimental data. Expressed in terms of non-dimensional parameters, front and back face displacements fall within one plate thickness of a linear trend line. The threshold impulse for the onset of tearing is found to increase linearly with panel thickness.

Original language	British English
Pages (from-to)	1202-1222
Number of pages	21
Journal	International Journal of Impact Engineering
Volume	34
Issue number	7
DOIs	https://doi.org/10.1016/j.ijimpeng.2006.05.008
State	Published - Jul 2007

Keywords

Blast loading
Composite
Failure
Fibre-metal laminate
Panel

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10.1016/j.ijimpeng.2006.05.008

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@article{1a5e0160a2b14fcbaf3a172c84045a1c,

title = "Behaviour of fibre-metal laminates subjected to localised blast loading: Part I-Experimental observations",

abstract = "This two-part article examines the behaviour of aluminium alloy-glass fibre-reinforced polypropylene-based fibre-metal laminates (FMLs) subjected to localised explosive blast loading. Part I presents observations from the experiments on samples of varying thickness and material distribution, and investigates the influence of stacking configuration. This extensive study examines panels which have between two and five layers of aluminium, and up to eight plies of composite between each pair of aluminium layers. Diamond and cross-shaped back face damage is observed and varies according to panel thickness. Pitting, global displacement and ring buckling of the front face are also discerned. Some observations are related to wave propagation effects. Part II reports a quantitative analysis of the experimental data. Expressed in terms of non-dimensional parameters, front and back face displacements fall within one plate thickness of a linear trend line. The threshold impulse for the onset of tearing is found to increase linearly with panel thickness.",

keywords = "Blast loading, Composite, Failure, Fibre-metal laminate, Panel",

author = "Langdon, {G. S.} and Lemanski, {S. L.} and Nurick, {G. N.} and Simmons, {M. C.} and Cantwell, {W. J.} and Schleyer, {G. K.}",

note = "Funding Information: The authors wish to thank the 1851 Royal Commission (UK), the Leverhulme Trust (UK) and the Engineering and Physical Sciences Research Council (UK) for financial support, and acknowledge BP, Gluco, Linpac and the Royal Mail for their professional support. This material is also based upon work supported by the National Research Foundation (South Africa). ",

year = "2007",

month = jul,

doi = "10.1016/j.ijimpeng.2006.05.008",

language = "British English",

volume = "34",

pages = "1202--1222",

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T2 - Part I-Experimental observations

AU - Langdon, G. S.

AU - Lemanski, S. L.

AU - Nurick, G. N.

AU - Simmons, M. C.

AU - Cantwell, W. J.

AU - Schleyer, G. K.

N1 - Funding Information: The authors wish to thank the 1851 Royal Commission (UK), the Leverhulme Trust (UK) and the Engineering and Physical Sciences Research Council (UK) for financial support, and acknowledge BP, Gluco, Linpac and the Royal Mail for their professional support. This material is also based upon work supported by the National Research Foundation (South Africa).

PY - 2007/7

Y1 - 2007/7

N2 - This two-part article examines the behaviour of aluminium alloy-glass fibre-reinforced polypropylene-based fibre-metal laminates (FMLs) subjected to localised explosive blast loading. Part I presents observations from the experiments on samples of varying thickness and material distribution, and investigates the influence of stacking configuration. This extensive study examines panels which have between two and five layers of aluminium, and up to eight plies of composite between each pair of aluminium layers. Diamond and cross-shaped back face damage is observed and varies according to panel thickness. Pitting, global displacement and ring buckling of the front face are also discerned. Some observations are related to wave propagation effects. Part II reports a quantitative analysis of the experimental data. Expressed in terms of non-dimensional parameters, front and back face displacements fall within one plate thickness of a linear trend line. The threshold impulse for the onset of tearing is found to increase linearly with panel thickness.

AB - This two-part article examines the behaviour of aluminium alloy-glass fibre-reinforced polypropylene-based fibre-metal laminates (FMLs) subjected to localised explosive blast loading. Part I presents observations from the experiments on samples of varying thickness and material distribution, and investigates the influence of stacking configuration. This extensive study examines panels which have between two and five layers of aluminium, and up to eight plies of composite between each pair of aluminium layers. Diamond and cross-shaped back face damage is observed and varies according to panel thickness. Pitting, global displacement and ring buckling of the front face are also discerned. Some observations are related to wave propagation effects. Part II reports a quantitative analysis of the experimental data. Expressed in terms of non-dimensional parameters, front and back face displacements fall within one plate thickness of a linear trend line. The threshold impulse for the onset of tearing is found to increase linearly with panel thickness.

KW - Blast loading

KW - Composite

KW - Failure

KW - Fibre-metal laminate

KW - Panel

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JO - International Journal of Impact Engineering

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ER -

Behaviour of fibre-metal laminates subjected to localised blast loading: Part I-Experimental observations

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Keywords

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