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Book: Composites
Series: ASM Handbook Archive
Volume: 21
Publisher: ASM International
Published: 01 January 2001
DOI: 10.31399/asm.hb.v21.a0003442
EISBN: 978-1-62708-195-5
... of thermal expansion and coefficient of moisture expansion; glass transition temperature; thermal conductivity, diffusivity, and specific heat. lamina nonmechanical testing laminate nonmechanical testing nonmechanical properties composite materials ply thickness density coefficient of thermal...
Abstract
Characterization of nonmechanical properties is performed in the testing and certification of composite materials. This article focuses on the properties of composites that are commonly investigated. The properties include: per ply thickness; constituent content; density; coefficient of thermal expansion and coefficient of moisture expansion; glass transition temperature; thermal conductivity, diffusivity, and specific heat.
Book: Composites
Series: ASM Handbook Archive
Volume: 21
Publisher: ASM International
Published: 01 January 2001
DOI: 10.31399/asm.hb.v21.a0003443
EISBN: 978-1-62708-195-5
... Abstract This article provides the general mechanical testing guidelines for the characterization of lamina and laminate properties. Guidelines are provided for tensile property, compressive property, shear property, flexure property, fracture toughness, and fatigue property test methods...
Abstract
This article provides the general mechanical testing guidelines for the characterization of lamina and laminate properties. Guidelines are provided for tensile property, compressive property, shear property, flexure property, fracture toughness, and fatigue property test methods. The article also tabulates selected standards for lamina and laminate mechanical testing.
Book Chapter
Macromechanics Analysis of Laminate Properties
Available to PurchaseBook: Composites
Series: ASM Handbook Archive
Volume: 21
Publisher: ASM International
Published: 01 January 2001
DOI: 10.31399/asm.hb.v21.a0003378
EISBN: 978-1-62708-195-5
... the development of the relations between mid-surface strains and curvatures and membrane stress and moment resultants. The article discusses the properties, such as thermal expansion, moisture expansion, and conductivity, of symmetric laminates and unsymmetric laminates. It describes the distribution...
Abstract
The properties of unidirectional composite (UDC) materials are quite different from those of conventional, metallic materials. This article provides information on the treatment of UDC stress-strain relations in the forms appropriate for analysis of thin plies of material. It explains the development of the relations between mid-surface strains and curvatures and membrane stress and moment resultants. The article discusses the properties, such as thermal expansion, moisture expansion, and conductivity, of symmetric laminates and unsymmetric laminates. It describes the distribution of temperature and moisture through the thickness of a laminate. Stresses caused due to mechanical loads, temperature, and moisture on the laminate are analyzed. The article concludes with information on interlaminar cracking, free-edge delamination, and transverse cracks of laminates.
Book Chapter
Fatigue of Composite Laminates
Available to PurchaseBook: 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 1996
Fig. 2 Increase of number of cracks for [0°/90°/±45°] s laminate subjected to static loading
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Published: 01 January 1996
Fig. 3 Increase of number of cracks for [0°/90°/±45°] s laminate subjected to fatigue loading
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Notch fatigue behavior of 3/2 ARALL-1 laminate, nominally 0.053 in. (1.3 mm...
Available to PurchasePublished: 01 January 1996
Fig. 16 Notch fatigue behavior of 3/2 ARALL-1 laminate, nominally 0.053 in. (1.3 mm) thick. Source: Ref 27
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Crack growth behavior of GLARE fiber-metal laminate and 2024-T3 aluminum al...
Available to PurchasePublished: 01 January 1996
Fig. 17 Crack growth behavior of GLARE fiber-metal laminate and 2024-T3 aluminum alloy. S max = 120 MPa (17.4 ksi). R = 0.05. Frequency = 10 Hz.
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Effect of fiber orientation on 3/2 ARALL-1 laminate (0.053 in.) fatigue cra...
Available to PurchasePublished: 01 January 1996
Fig. 18 Effect of fiber orientation on 3/2 ARALL-1 laminate (0.053 in.) fatigue crack growth. Source: Ref 27
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Published: 01 January 1996
Fig. 3 Compressive strength versus defect size for AS4/3501-6 wing skin laminate
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Published: 01 January 1996
Fig. 28 R-curve for [ + 45/0/90/ + 30/ 0 ] s AS4/938 fuselage crown laminate (2 a o = 23 cm and W = 91 cm)
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Amorphous iron (Metglas) cut with a wire saw. Each laminate is 0.1 mm (0.00...
Available to PurchasePublished: 01 December 2004
Fig. 15 Amorphous iron (Metglas) cut with a wire saw. Each laminate is 0.1 mm (0.004 in.) thick.
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Carbon fiber composite laminate labeled for sectioning using a silver ink f...
Available to Purchase
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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Laminate made with unidirectional carbon fiber prepreg and woven carbon fab...
Available to PurchasePublished: 01 December 2004
Fig. 2 Laminate made with unidirectional carbon fiber prepreg and woven carbon fabric prepreg plies. Voids are shown in the woven fabric area at the bottom of the composite part that was against the tool surface during cure. Bright-field illumination, 65 mm macrophotograph
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Microcracks in a carbon fiber composite laminate due to thermal cycling. (a...
Available to PurchasePublished: 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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Lightning strike damage in a carbon fiber composite laminate having metal f...
Available to Purchase
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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Stress concentration adjacent to a hole in a composite laminate subjected t...
Available to PurchasePublished: 01 January 2000
Fig. 25 Stress concentration adjacent to a hole in a composite laminate subjected to uniaxial loading
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Schmatic of the laminate code (0/90/±45), for a composite material. The lam...
Available to PurchasePublished: 01 January 2000
Fig. 29 Schmatic of the laminate code (0/90/±45), for a composite material. The laminate code follows an ascending order from the bottom ply. The numerals are ply (or fiber) orientation with respect to the x-axis. The subscript s denotes that the laminate is symmetric with respect
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