1-20 of 795 Search Results for

Laminates

Follow your search
Access your saved searches in your account

Would you like to receive an alert when new items match your search?
Close Modal
Sort by
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...
Image
Published: 01 January 1994
Fig. 2 Thermal expansion characteristics of ceramics and carbon-carbon laminates. C/C, carbon-carbon laminate; L , specimen length More
Image
Published: 01 January 1996
Fig. 6 S-N curves for (a) various AS4-epoxy laminates and (b) glass-fiber polymer laminates at various ply orientations. Source: (a) Engineered Materials Handbook, Vol 1, Composites, ASM International, 1987, p 438 and (b) C. Osgood, Fatigue Design, 2nd ed., 1982, Pergamon Press, p 530 More
Image
Published: 01 January 1996
Fig. 13 Fiber-metal laminates structure, a standard 3/2 lay-up: three layers of aluminum, two layers of prepreg. Source: Ref 27 More
Image
Published: 01 January 1996
Fig. 6 Damage diameter for [45/0/−45/90] 6s IM7/8551-7 and AS4/3501-6 laminates with 12.7 mm diam indenter More
Image
Published: 01 January 1996
Fig. 24 Constant amplitude compression fatigue for [45/0/−45/90] 6s laminates with impact damage resulting in 2.54 mm dent More
Image
Published: 01 January 1996
Fig. 31 R-curves for [ + 45/0/90/ + 30/ 0 ] s AS4/938 fuselage crown laminates with various cut lengths. W ≥ 8 a o More
Image
Published: 01 January 1996
Fig. 48 Fatigue crack growth in laminates of β-21S at various temperatures between 23–760 °C. (a) da / dN -ΔK curves. (b) Data at 23–482 °C plotted as da / dN vs. (Δ K ) 2 / E σ y . The correlation using the CTOD-like parameter is good for the bcc β phase. Source: Ref 96 More
Image
Published: 01 January 2000
Fig. 38 Fiber bridging in DCB testing of unidirectional laminates More
Image
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 More
Image
Published: 01 January 1997
Fig. 12 Shape stability of right-angle laminates after cool-down from cure. All laminates are 90° before cure. (a) Symmetric laminate. The shrinkage in the matrix upon resin curing and the difference in coefficients of thermal expansion in-plane and through-plane cause a right angle to become More
Image
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. More
Image
Published: 01 January 2001
Fig. 28 Stress-concentration relief at bolt holes in composite laminates More
Image
Published: 01 January 2001
Fig. 4 Shear buckling coefficient for various graphite/ epoxy laminates More
Image
Published: 01 January 2001
Fig. 5 Normalized buckling load for [0/90] ns and [90/0] ns laminates as a function of number of ply groups More
Image
Published: 01 January 2001
Fig. 2 Carpet plots illustrating tensile modulus of laminates More
Image
Published: 01 January 2001
Fig. 3 Carpet plots illustrating tensile strength of laminates More
Image
Published: 01 January 2001
Fig. 8 Thermal expansion characteristics of ceramics and carbon-carbon laminates. 2D, two-directional; C/C, carbon-carbon laminae; L , specimen length More
Image
Published: 01 January 2001
Fig. 13 Coefficient of thermal expansion, parallel and perpendicular to laminates of two-directional weave carbon- carbon composite with final heat treatment temperature (HTT) of 1200 and 2400 °C (2190 and 4350 °F) More
Image
Published: 01 January 2001
Fig. 6 Load distribution in fasteners joining thin and thick laminates More