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Book Chapter

By John Moylan
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...
Book Chapter

By Rod Wishart
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...
Book Chapter

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...
Book Chapter

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...
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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 More
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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 More
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Published: 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 More
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Published: 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. More
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Published: 01 January 1996
Fig. 18 Effect of fiber orientation on 3/2 ARALL-1 laminate (0.053 in.) fatigue crack growth. Source: Ref 27 More
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Published: 01 January 1996
Fig. 19 Fracture toughness of GLARE fiber-metal laminate More
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Published: 01 January 1996
Fig. 3 Compressive strength versus defect size for AS4/3501-6 wing skin laminate More
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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) More
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Published: 01 December 2004
Fig. 15 Amorphous iron (Metglas) cut with a wire saw. Each laminate is 0.1 mm (0.004 in.) thick. More
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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. More
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Published: 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 More
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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 More
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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 More
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Published: 01 January 2000
Fig. 25 Stress concentration adjacent to a hole in a composite laminate subjected to uniaxial loading More
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Published: 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 More
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Published: 01 November 1995
Fig. 12 Typical composite laminate configurations More