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composite laminates
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Book Chapter
Book: Fatigue and Fracture
Series: ASM Handbook
Volume: 19
Publisher: ASM International
Published: 01 January 1996
DOI: 10.31399/asm.hb.v19.a0002415
EISBN: 978-1-62708-193-1
... Abstract Knowledge of fatigue behavior at the laminate level is essential for understanding the fatigue life of a laminated composite structure. This article describes fatigue failure of composite laminates in terms of layer cracking, delamination, and fiber break and interface debonding...
Abstract
Knowledge of fatigue behavior at the laminate level is essential for understanding the fatigue life of a laminated composite structure. This article describes fatigue failure of composite laminates in terms of layer cracking, delamination, and fiber break and interface debonding. It discusses the fatigue behavior of composite laminates in the form of a relation between applied maximum fatigue stress and fatigue life. The article explains Weibull distribution and parameters estimation for fatigue data analysis and life prediction of composite laminates. It analyzes the fatigue properties and damage tolerance of fiber-metal laminates such as ARALL and GLARE laminates. The article concludes with a discussion on the effects of fatigue on notched and unnotched specimens.
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Published: 01 January 2001
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Published: 01 January 2001
Fig. 1 Selection of lay-up pattern for fiber-reinforced composite laminates. All fibers in 0°, +45°, 90°, or–45° direction. Note: lightly loaded minimum gage structures tend to encompass a greater range of fiber patterns than indicated, because of the unavailability of thinner plies.
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Published: 01 January 2001
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Published: 01 January 2001
Fig. 9 Two-mechanism characterization of matrix failures in composite laminates. Distortion is shown at the long, circular cylinder and dilation as the flat plate cutoff perpendicular to the cylinder.
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Published: 01 January 1997
Fig. 4 Fiber arrangements. Composite laminates are generally fabricated by rotating lamina axes as shown by the twist example on the left. However, loads that are off-fiber axes cause large inter- and intralaminar matrix stresses. Safer structures can often be designed by using curved
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in Sample Preparation and Mounting for Fiber-Reinforced Composites[1]
> Metallography and Microstructures
Published: 01 December 2004
Fig. 3 Carbon fiber composite laminate labeled for sectioning using a silver ink felt-tip permanent marker. This sample with the corresponding section map was originally sent for nondestructive inspection.
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Published: 01 December 2004
Fig. 1 Microcracks in a carbon fiber composite laminate due to thermal cycling. (a) Resin-rich region in the composite. Slightly uncrossed polarized light, 10× objective. (b) Resin-rich region containing a large void. Slightly uncrossed polarized light, 10× objective
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in Analysis of the Effects of Lightning Strikes on Polymeric Composites[1]
> Metallography and Microstructures
Published: 01 December 2004
Fig. 13 Lightning strike damage in a carbon fiber composite laminate having metal foil on the surface for protection. (a) Slightly uncrossed polarized light, 4× objective. (b) Transmitted light (ultrathin section), circular polarized light, 4× objective. The impregnation outline of the epoxy
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Published: 01 January 2000
Fig. 25 Stress concentration adjacent to a hole in a composite laminate subjected to uniaxial loading
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Published: 01 November 1995
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![Delamination patterns for a [0/90/0] <span class="search-highlight">composite</span> <span class="search-highlight">laminate</span>. Adapted from Ref ...](https://asm.silverchair-cdn.com/asm/content_public/books/55/parts/a0006466/7/s_a0006466-f48.jpeg?Expires=2147483647&Signature=OVMheH3u1E4LUmP8Dbmp5SMTWKc-QP92PjPvxmSC95C0G5Uwzo9PdeMI8qMyJi0n8wqaZGgP8T1kSSEee7YN1vy2Tc53ctFIe5dKy5ETjFIHTqfmt2uHtyzjmGqe50KFiHcUCtOYvHKklqj0B5UgCY2-yZq-9Wjc-IBqdrVln4JKDyQohdGgI2FnJfLgvRfUXIVvzCccSBlCxk9SDR~fxwtGy-URnRKw1XCCbfTjRQwrQDaoMwHKOd9L5vN0IDh2LH1cjsfU~4i0EXabhvQbXEIQmfnteT6bfy3V3hqeMImw7x~hfp11VjilzUAy-HaAmli4gFhOVxdN4mOlUpGAfA__&Key-Pair-Id=APKAIE5G5CRDK6RD3PGA)
Published: 01 August 2018
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![Matrix cracks in a [0/90/0] <span class="search-highlight">composite</span> <span class="search-highlight">laminate</span>. (a) First interface delamin...](https://asm.silverchair-cdn.com/asm/content_public/books/55/parts/a0006466/7/s_a0006466-f49.jpeg?Expires=2147483647&Signature=urKeqG1uY~JxtH3SCniwdF~HyDhZHWw~GD~bsSHDoDzoeKM7EQtTkJWUY1nHJ3Vibntfvu8cwApI91SEEZC8EzH4sLKmH8Bwv~fdIfKziNQiKG3TSBmZCntpjyN8K-U7KKTmCRqpX6cO-N8WuE-fJWWOOG14ddvXRoBRvhS2sdD~MekdZ5UjsRddXU20xi10VjHKuOP6XVZCLKFtgeY-6Yb6AS06bi7hHmB7uwFI093vapRwWSMyB-S5y7nvELAbVHfmxc1PLf5lKtyO08G7CgCMv-T79FZOK7BazGdM4Yb7Pk8FB4guLudnwsIMNqNRWZj-GZvb6Da8JZ-16VtHmw__&Key-Pair-Id=APKAIE5G5CRDK6RD3PGA)
Published: 01 August 2018
Fig. 49 Matrix cracks in a [0/90/0] composite laminate. (a) First interface delamination pattern. (b) Second interface delamination pattern. Adapted from Ref 30
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Published: 01 January 2001
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Published: 01 January 2001
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Published: 01 January 2001
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Published: 01 January 2001
Fig. 6 Cross section of a composite laminate, which failed in compression, containing both delaminations and transverse fractures for examination of fracture sequence. ∼2×
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Published: 01 January 2001
Fig. 9 Fatigue striations in the resin of a carbon/fiber composite laminate that failed in mode I fatigue loading. Striations cover the surfaces of several fibers. 1000×
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Published: 01 January 2001
Fig. 10 Impact damage in a Kevlar/epoxy composite laminate depicting hackle formation indicative of shear loading; resin debris indicative of impact loading and fiber fibrillation. 120×
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Published: 01 January 1993
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