In the present work, the fatigue delamination growth of a 2-ply off-axis cord rubber composite was tracked to failure. The 2-ply cord rubber laminate was fatigued under load control and the modulus was defined as the slope of the stress- strain curve. Delamination initiated at the free edges of the laminate and propagated inward between the cords until coalescence and failure. The delaminated area of the composite was measured using ultrasonic C-scan. In order to accurately capture the delaminated regions the laminate was discretized into thirteen layers. Reduction in the modulus of the laminate was tracked in conjunction with the increase in the delamination area. Using the change in the delamination area, the strain energy release rate for the delamination growth, G, and the crack growth rates were calculated [1-5]. The slopes of the calculated crack growth rate versus G were identical to those experimentally obtained from a modified double cantilever beam [6] fatigue crack growth experiment.
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