Damage development during flexural fatigue of carbon fibre-reinforced PEEK

G. Dillon; M. Buggy

doi:10.1016/S0010-4361(06)80135-7

Damage development during flexural fatigue of carbon fibre-reinforced PEEK

G. Dillon, M. Buggy

Penn State Erie, The Behrend College

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

17 Scopus citations

Abstract

Fatigue damage growth mechanisms in [0]₁₆ and [0, 90]_4s laminates of APC-2 subjected to three-point flexure were studied using scanning electron microscopy. Building on an understanding gained from the study of statically tested samples, specific fatigue mechanisms were identified. For each laminate geometry a coherent progression of damage build-up is proposed.

Original language	English (US)
Pages (from-to)	355-370
Number of pages	16
Journal	Composites
Volume	26
Issue number	5
DOIs	https://doi.org/10.1016/S0010-4361(06)80135-7
State	Published - May 1995

All Science Journal Classification (ASJC) codes

Materials Science(all)

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10.1016/S0010-4361(06)80135-7

Cite this

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title = "Damage development during flexural fatigue of carbon fibre-reinforced PEEK",

abstract = "Fatigue damage growth mechanisms in [0]16 and [0, 90]4s laminates of APC-2 subjected to three-point flexure were studied using scanning electron microscopy. Building on an understanding gained from the study of statically tested samples, specific fatigue mechanisms were identified. For each laminate geometry a coherent progression of damage build-up is proposed.",

author = "G. Dillon and M. Buggy",

year = "1995",

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AU - Dillon, G.

AU - Buggy, M.

PY - 1995/5

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N2 - Fatigue damage growth mechanisms in [0]16 and [0, 90]4s laminates of APC-2 subjected to three-point flexure were studied using scanning electron microscopy. Building on an understanding gained from the study of statically tested samples, specific fatigue mechanisms were identified. For each laminate geometry a coherent progression of damage build-up is proposed.

AB - Fatigue damage growth mechanisms in [0]16 and [0, 90]4s laminates of APC-2 subjected to three-point flexure were studied using scanning electron microscopy. Building on an understanding gained from the study of statically tested samples, specific fatigue mechanisms were identified. For each laminate geometry a coherent progression of damage build-up is proposed.

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U2 - 10.1016/S0010-4361(06)80135-7

DO - 10.1016/S0010-4361(06)80135-7

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EP - 370

JO - Composites

JF - Composites

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ER -

Damage development during flexural fatigue of carbon fibre-reinforced PEEK

Abstract

All Science Journal Classification (ASJC) codes

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