Abstract
The fatigue crack propagation behavior of [0/90]s and [0/±45]sSCS-6/Ti-15-3 laminates at room temperature was studied and compared with that of a [0]6 laminate. The testing was conducted in a tension-tension mode on specimens with a chevron notch perpendicular to the 0° surface layer. The maximum applied stress intensity ranged from 20 to 30 MPam1/2. The fatigue crack growth rates at various applied stress intensity levels were measured and the fatigue damage mechanisms were examined. It was found that fatigue crack damage in angle-ply SCS-6/Ti-15-3 laminates is much more complex than that identified in their unidirectional counterparts. The primary crack which originated from the notch interacted with secondary cracks, resulting in catastrophic failure of the laminate. Also, the direction of fatigue crack growth and the final crack length differed in each layer of the angle-ply laminates.
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