Carbon epoxy

Acoustic Emission to Model the Fatigue Behaviour of Quasi-Isotropic Carbon-Epoxy Laminate Composites. [Pg.45]

Lafarie-Frenot, M.C. and Henaff-Gardin, C., Formation and Growth of 90° Ply Fatigue Cracks in Carbon/Epoxy Laminates , Composites Science and Technology Vol. 40, p. 307-324, 1991... [Pg.52]

Vitahium FHS ahoy is a cobalt—chromium—molybdenum ahoy having a high modulus of elasticity. This ahoy is also a preferred material. When combiaed with a properly designed stem, the properties of this ahoy provide protection for the cement mantle by decreasing proximal cement stress. This ahoy also exhibits high yields and tensile strength, is corrosion resistant, and biocompatible. Composites used ia orthopedics include carbon—carbon, carbon—epoxy, hydroxyapatite, ceramics, etc. [Pg.190]

Thus the addition of the stiff carbon fibers has a very great effect in stiffening the epoxy matrix. Eor the commonly used fiber volume fraction of 0.6 the unidirectional carbon—epoxy lamina has a predicted extensional stiffness E = 145 GPa (2.1 x 10 psi)-... [Pg.10]

Fig. 3.24 Variation of elastic properties for a single ply of carbon/epoxy composite...

Fig. 3.25 Variation of elastic properties for a (+/ — 45) symmetric laminate of carbon/epoxy...

A single ply of carbon/epoxy composite has the properties listed below and the fibres are aligned at 25° to the x-direction. If stresses of... [Pg.242]

A carbon/epoxy composite with the stacking arrangement [0/ - 30/30]j has the properties listed below. Determine the value of in-plane stress which would cause failure according to the (a) Maximum Strain (b) Maximum Stress and (c) Tsai-Hill criteria. [Pg.243]

Detroit, Mi., 9th-l 1th Nov. 1999, p.275-81 CATALYTIC PROCESS FOR THE RECLAMATION OF CARBON FIBRES FROM CARBON/EPOXY COMPOSITES Allred R E Busselle L D Shoemaker J M Adherent Technologies Inc. [Pg.45]

Garton, A. and Daly, J.H. (1985). Characterization of the aramid-epoxy and carbon-epoxy interphases. Polym. Composites 6, 195-200. [Pg.39]

Scherf, J. and Wagner, H.D, (1992). Interpretation of fiber fragmentation in carbon/epoxy single fiber composites Possible fiber pre-tension effects. Polym. Eng. Sci. 32, 298-304. [Pg.91]

Fig. 6.3. A theoretical plot of fracture toughness, R, with variation of frictional shear stress, Tf, compared with experimental fracture toughness values (A) Charpy impact and (A) slow bend tests for carbon-epoxy composites ( ) Charpy impact and (O) slow bend tests for carbon polyester composites. After...

$Fig. 6.3. A theoretical plot of fracture toughness, R, with variation of frictional shear stress, Tf, compared with experimental fracture toughness values (A) Charpy impact and (A) slow bend tests for carbon-epoxy composites ( ) Charpy impact and (O) slow bend tests for carbon polyester composites. After...$

Energy Carbon-epoxy Silicon rubber 140 nil-60 Izod impact... [Pg.281]

Delamination Carbon-epoxy Nylon films 270 25 Charpy impact... [Pg.281]

Reduction of Carbon-epoxy Spiro monomer 50 15 Izod impact... [Pg.281]

In particular, the techniques based on the termination of certain plies within the laminate has also shown promise. Static tensile tests of [30°/-30°/30°/90°]s carbon-epoxy laminates containing terminals of [90°] layers at the mid-plane show that premature delamination is completely suppressed with a remarkable 20% improvement in tensile strength, compared to those without a ply terminal. Cyclic fatigue on the same laminates confirms similar results in that the laminate without a ply terminal has delamination equivalent to about 40% of the laminate width after 2x10 cycles, whereas the laminates with a ply terminal exhibit no evidence of delamination even after 9x10 cycles. All these observations are in agreement with the substantially lower interlaminar normal and shear stresses for the latter laminates, as calculated from finite element analysis. A combination of the adhesive interleaf and the tapered layer end has also been explored by Llanos and Vizzini, (1992). [Pg.347]

Herszberg, I., Weller, T., Leong, K.H. and Bannister, M.K. (1996). The residual tensile strength of stitched and unstitched carbon/epoxy laminates impacted under tensile load. In Proc. 1st Australasian Congre.ss on Applied Mechanics. Melbourne, pp. 309-314. [Pg.362]

Ogo, Y. (1987). The effect of stitching on in-plane interlaminar properties of carbon-epoxy fabric laminates, M.S. Thesis, University of Delaware, Delaware, USA. [Pg.364]

Carbon-epoxy plates are now used in bone surgery replacing the titanium plates that had been employed. Usually a layer of connective tissue forms around the composite plate. [Pg.245]

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