Graphite-epoxy laminate

Ishai O., Rosenthal H., Sela N. and Drukker E. (1988). Effect of selective adhesive interleaving on interlaminar fracture toughness of graphite/epoxy composite laminates. Composites 19, 49-54. [Pg.362]

Figure 11. Log (1/ct) vs. time for a thick graphite laminate (192 ply) catalyzed epoxy monitored during cure in the autoclave.

Figure 4.12 The lay up of a thick TGDDM epoxy (Hercules 3501-6) graphite laminate autoclave run showing the positions of the dielectric sensors and thermocouples...

Preston. J. L., and Ccok. T. S. (1975). Impact response of graphite-epoxy flat laminates using projectiles that simulate aircraft engine encounters. Foreign Object Impact Damage to Compo.sites. ASTM STP 568, pp. 49-71. [Pg.834]

Minguet PJ, Gunther CK. A comparison of graphite/epoxy tape laminates and 2-D braided composites mechanical properties. NASA CR 4610 July 1994. [Pg.151]

The trend is similar to that discussed on page 345 for short fiber composites, but at the same time it is opposite to the general behavior of plain samples of both short fiber and continuous fiber composites, where the fatigue strength decreases when the biaxiality ratio A2 increases. However, on the basis of the limited amount of data available, it is impossible to justify the experimental evidence and further research is indeed needed to clarify the mechanisms responsible for this peculiar behavior. Results on [0/ 45]2s, [0/ 45/90]s, and [02/ 45]s graphite/epoxy cruciform laminates reported by Jones et al. [16] are less clear than those just discussed—in some cases increasing the biaxiality ratio Ai decreased the fatigue life, and for others the life was increased. [Pg.168]

Hirano Y, Katsumata S, Iwahori Y, Todoroki A. Artificial lightning testing on graphite/ epoxy composite laminates. Compos Part A Appl Sci Manuf 2010 41 1461-70. http // dx.doi.org/10.1016/j.compositesa.2010.06.008. [Pg.229]

Whitworth, H.A. Modeling Stiffness Reduction of Graphite/Epoxy Composite Laminates, Journal of Composite Materials, 21 (1987), p. 362-372... [Pg.1353]

High performance composites may be laminates wherein veils of carbon fiber ate treated with an epoxy resin, stacked up to the desired final product thickness, and then laminated together under heat and pressure (see Composite materials Carbon and graphite fibers). Simply mixing together carbon or glass fibers and polymeric resins to form a reinforced plastic leads to a composite material, but this is not a laminate if not constmcted from discrete phes. [Pg.531]

Maximum deflection results for a graphite-epoxy laminate for which... [Pg.300]

As for the deflection problem in Section 5.3.3, the effect of the number of layers on the buckling load is found by dividing a constantthickness, equal-weight cross-ply laminate into more and more laminae as in Figure 5-12. Results for graphite-epoxy antisymmetric cross-ply laminated plates for which Ei/E2 = 40, Gi2/E2 = - - v,2 = -25 are... [Pg.310]

Unsymmetric Cross-Ply Laminated Graphite-Epoxy Plates (After Jones and Morgan [5-23])... [Pg.324]

Example Unsymmetric Cross-Ply Graphite-Epoxy Laminate (After Jones [5-19])... [Pg.325]

Normalized fundamental natural frequencies for the exampie un-symmetrical cross-piy laminated graphite-epoxy piates are shown in Figure 5-40. The vibration resuits are analogous to the buckling resuits in the same manner as explained for antisymmetric iaminates, nameiy, iesser differences for vibration frequencies because of the square-root factor. [Pg.327]

Pagano presented numerical results for several laminates made of a high-modulus graphite-epoxy composite material with... [Pg.347]

Whitney solved Equations (6.44) for a square four-layered symmetric cross-ply [0 /90 /90 /0 ] laminated graphite-epoxy plate under the transverse load p = Po sin(7tx/a) sin(jiy/a) [6-30], The material properties are typical of a high-modulus graphite-epoxy ... [Pg.354]

Square Graphite-Epoxy Laminates (After Hyer [6-38])... [Pg.358]

Russell, A.J. and Street, K.N. (1984). Factors affecting the interlaminar fracture energy of graphite/epoxy laminates. In Proc. 4th Intern. Conf. on Composite Materials. (T. Hayashi, K. Kawata and S. Umekawa eds.), Japan Society of Composites Materials, Tokyo, p. 129. [Pg.91]

Fig. 6.22. Comparisons of the longitudinal splitting length, Z,p, between analysis and finite element method for graphite fiber-epoxy matrix orthotropic laminates. After Tirosh (1973).

Bathias, C., Esnault, R. and Bellas, J. (1983). On the increasing fracture toughness at increasing notch length of 0/90 and 0/ 45/0 graphite/epoxy laminates. Composites 14, 365-369. [Pg.274]

Caprino, G. Halpin, J.C. and Nicolais, L. (1980). Fracture toughness of graphite/epoxy laminates. Composites 11, 105-107. [Pg.274]

Ishikawa. T, Fukunaga, H. and Ono, K.I. (1989) Graphite-epoxy laminates with almost null coefficient of thermal expansion under a wide range of temperature. J. Mater. Sci. 24,2011-2017. [Pg.323]

Jordan W.M. and Bradley W.L. (1987). Microniechanisms of fracture in toughened graphite-epoxy laminates. In Toughened Composites (N.J. Johnston ed.), ASTM STP 937, ASTM, Philadelphia, PA, pp. 95-114. [Pg.362]

Masters. J.E. (1987b). Characterisation of impact damage development in graphite/epoxy laminates. In Fractography of Modern Engineering Materials Composites and Metals, ASTM STP 948, ASTM. Philadelphia, PA, pp. 238-258. [Pg.363]

Sun. C.T. and Luo, J. (1988). Failure loads for notched graphite/epoxy laminates with a softening strip. Composites Sci. Techno . 22, 121-133. [Pg.365]

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