Fig. 1 Percent gains in weight of ASTM C 581 laminates of a high- and low-styrene-containing vinyl ester exposed at 66 °C (150 °F) to a distilled and saturated sodium chloride solution for 120 days More

Fig. 10 Degradation of glass laminates in water at 100 °C (212 °F) for different polyester-resin matrices. BPA, bisphenol A More

Fig. 21 Auger electron spectroscopy-ion milling depth profiles comparing laminates. (a) X laminate, 5 nm (50 Å)/min. (b) Y laminate, 10 nm (100 Å)/min More

Fig. 7.4 Young’s modulus for graphite/epoxy laminates. f v , fiber volume More

Fig. 12.53 Two 8-ply laminates. (a) Symmetric. (b) Nonsymmetric More

Fig. 12.54 Defining plies, orientation, loads, and stresses and strains in laminates of continuous fiber-reinforced matrix material. Source: Ref 12.24 More

Fig. 7.20 Horizontal flow laminates. Source: Ref 4 More

Fig. 12.6 Ultrasonic C-scans of composite laminates More

Fig. 14.13 S / N fatigue curves for carbon/epoxy laminates. Source: Ref 15 More

Fig. 17.5 Stress concentration reduction in composite laminates. Source: Ref 3 More

Fig. 17.8 Stress concentration relief at bolt holes in composite laminates. Source: Ref 3 More

Fig. 21 S - N curves for T300/934 carbon/epoxy laminates, R = –1. A, unidirectional [0] 16 ; B, cross-ply [0/90] 4S ; C, quasi-isotropic [0/45/90] 2S ; D, angle-ply [45] 4S . Source: Ref 11 More

Fig. 23 S - N curve for T300/5209 carbon/epoxy laminates and residual strength of specimens after fatigue cycling. Source: Ref 13 More

Fig. 8.17 S-N curves for T300/934 graphite/epoxy laminates, R = −1. A, unidirectional [0] 16 ; B, cross-ply [0/90] 4S ; C, quasi-isotropic [0/±45/90] 2S ; D, angle-ply [±45] 4S . Source: Ref 8.16 More

Fig. 8.19 S-N curve for T300/5209 graphite/epoxy laminates and residual strength of specimens after fatigue cycling. Source: Ref 8.18 More

Fig. 8.26 Two types of delamination in unnotched laminates. Only two 90° plies and four angle plies ( n = 4, t = 6) are shown in these models. Source: Ref 8.28 More

Figure 12.3 The conventional notation for uniaxial (a) and crossply (b) laminates. The crossply laminate is designated [0/±45/0] T . More

Figure 12.20 Temperature dependence of thermal conductivity of uniaxial laminates. L = longitudinal, T = transverse. Transverse conductivity of the aramid laminate assumed from fabric-reinforced data. Vol.% = fiber volumefraction. Refs.: (1) Hust and Arvidson (1978) ; (2) Dahlerup-Petersen More

Figure 12.36 Tensile grip assembly for testing laminates at cryogenic temperature. More

Figure 12.37 Grip system for tensile fatigue testing of laminates at cryogenic temperatures. Example is a waisted specimen used with [0/±45/0] S , 140- μ m (5.6-mil) boron-epoxy. More