Tension-compression fatigue behavior of a H-VARTM manufactured unnotched and notched carbon/epoxy composite

S. Mall; D. W. Katwyk; R. L. Bolick; A. D. Kelkar; D. C. Davis

doi:10.1016/j.compstruct.2009.03.015

Tension-compression fatigue behavior of a H-VARTM manufactured unnotched and notched carbon/epoxy composite

S. Mall, D. W. Katwyk, R. L. Bolick, A. D. Kelkar, D. C. Davis

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

Abstract

The tension-compression fatigue behavior of a four-harness satin weave carbon fiber/epoxy (IM7/EPON 862) composite manufactured from the H-VARTM (Heated Vacuum Assisted Resin Transfer Molding) process was investigated. Unnotched and notched specimens were both tested in this study. The notch was a circular hole located at the center of specimen. The fatigue lives of the unnotched IM7/EPON 862 composites in the fully reversed tension-compression fatigue testing condition were significantly shorter than in the tension-tension fatigue testing condition. However, there was no effect of the notch on the fatigue life/strength. Damage mechanisms involved initial matrix cracking followed by delamination, microbuckling, fiber kinking and finally fiber breakage. The final failure occurred under compression in the shear mode. In the notched specimen, the damage was initially concentrated at the maximum stress concentration location (edge of hole).

Original language	English
Pages (from-to)	201-207
Number of pages	7
Journal	Composite Structures
Volume	90
Issue number	2
DOIs	https://doi.org/10.1016/j.compstruct.2009.03.015
State	Published - Sep 2009
Externally published	Yes

Keywords

Carbon/Epoxy
Circular Hole
Damage mechanisms
H- VARM
Notch
Tension-compression fatigue

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10.1016/j.compstruct.2009.03.015

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title = "Tension-compression fatigue behavior of a H-VARTM manufactured unnotched and notched carbon/epoxy composite",

abstract = "The tension-compression fatigue behavior of a four-harness satin weave carbon fiber/epoxy (IM7/EPON 862) composite manufactured from the H-VARTM (Heated Vacuum Assisted Resin Transfer Molding) process was investigated. Unnotched and notched specimens were both tested in this study. The notch was a circular hole located at the center of specimen. The fatigue lives of the unnotched IM7/EPON 862 composites in the fully reversed tension-compression fatigue testing condition were significantly shorter than in the tension-tension fatigue testing condition. However, there was no effect of the notch on the fatigue life/strength. Damage mechanisms involved initial matrix cracking followed by delamination, microbuckling, fiber kinking and finally fiber breakage. The final failure occurred under compression in the shear mode. In the notched specimen, the damage was initially concentrated at the maximum stress concentration location (edge of hole).",

keywords = "Carbon/Epoxy, Circular Hole, Damage mechanisms, H- VARM, Notch, Tension-compression fatigue",

author = "S. Mall and Katwyk, \{D. W.\} and Bolick, \{R. L.\} and Kelkar, \{A. D.\} and Davis, \{D. C.\}",

year = "2009",

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doi = "10.1016/j.compstruct.2009.03.015",

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volume = "90",

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T1 - Tension-compression fatigue behavior of a H-VARTM manufactured unnotched and notched carbon/epoxy composite

AU - Mall, S.

AU - Katwyk, D. W.

AU - Bolick, R. L.

AU - Kelkar, A. D.

AU - Davis, D. C.

PY - 2009/9

Y1 - 2009/9

N2 - The tension-compression fatigue behavior of a four-harness satin weave carbon fiber/epoxy (IM7/EPON 862) composite manufactured from the H-VARTM (Heated Vacuum Assisted Resin Transfer Molding) process was investigated. Unnotched and notched specimens were both tested in this study. The notch was a circular hole located at the center of specimen. The fatigue lives of the unnotched IM7/EPON 862 composites in the fully reversed tension-compression fatigue testing condition were significantly shorter than in the tension-tension fatigue testing condition. However, there was no effect of the notch on the fatigue life/strength. Damage mechanisms involved initial matrix cracking followed by delamination, microbuckling, fiber kinking and finally fiber breakage. The final failure occurred under compression in the shear mode. In the notched specimen, the damage was initially concentrated at the maximum stress concentration location (edge of hole).

AB - The tension-compression fatigue behavior of a four-harness satin weave carbon fiber/epoxy (IM7/EPON 862) composite manufactured from the H-VARTM (Heated Vacuum Assisted Resin Transfer Molding) process was investigated. Unnotched and notched specimens were both tested in this study. The notch was a circular hole located at the center of specimen. The fatigue lives of the unnotched IM7/EPON 862 composites in the fully reversed tension-compression fatigue testing condition were significantly shorter than in the tension-tension fatigue testing condition. However, there was no effect of the notch on the fatigue life/strength. Damage mechanisms involved initial matrix cracking followed by delamination, microbuckling, fiber kinking and finally fiber breakage. The final failure occurred under compression in the shear mode. In the notched specimen, the damage was initially concentrated at the maximum stress concentration location (edge of hole).

KW - Carbon/Epoxy

KW - Circular Hole

KW - Damage mechanisms

KW - H- VARM

KW - Notch

KW - Tension-compression fatigue

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DO - 10.1016/j.compstruct.2009.03.015

M3 - Article

SN - 0263-8223

VL - 90

SP - 201

EP - 207

JO - Composite Structures

JF - Composite Structures

IS - 2

ER -

Tension-compression fatigue behavior of a H-VARTM manufactured unnotched and notched carbon/epoxy composite

Abstract

Keywords

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