Abstract
A study was performed to determine the fatigue crack growth (FCG) behaviour and the associated fatigue damage processes in a [0] 8- and [90] 8-oriented SCS6/Ti-15-3 composite. Companion testing was also done on identically processed Ti-15-3 unreinforced material. The active fatigue crack growth failure processes were very similar for both composite orientations tested. For both orientations, fatigue crack growth was along the fibre direction. It was found that the composite constituent most susceptible to fatigue damage was the interface region and in particular the carbon coating surrounding the fibre. The failure of the interface region led to crack initiation and also strongly influenced the FCG behaviour in this composite. The failure of the interface region was apparently driven by normal stresses perpendicular to the fibre direction. The FCG rates were considerably higher for the [90] 8-oriented CT specimens in comparison to the unreinforced material. This is consistent with the scenario in which the interface has a lower fatigue resistance than the matrix, causing lower composite fatigue resistance. The FCG rates of the [0] 8 composite could not be directly compared to the [90] 8 composite but were shown to increase with an increase in the crack length.
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