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Fatigue crack growth behavior of off-axis Ti–6Al–4V/SCS-6 metal matrix composites by A Yasmin; P Bowen is a Engineering article available to read on EtoBox.

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The fatigue crack growth (FCG) behavior of five different laminate orientations ([0/90] 2s , [90/0] 2s , [9/45] 2s , [150/60] 2s and [60/ 150] 2s ) of cross-ply Ti Á/6Al Á/4V/SCS-6 has been investigated at room temperature in air. All these tests were performed on testpieces with a similar notch depth of 0.5 mm under three-point bending (3PD). The FCG behavior was investigated as a function of initial stress intensity factor range (DK ini ), fiber orientation, surface condition and composite architecture to determine the crack arrest/ catastrophic failure (CA/CF) transition of these laminates. For a given DK ini , the laminates containing 08 (or on-axis) plies to the loading direction (e.g. [0/90] 2s and [90/0] 2s ) show higher FCG resistance than the laminates containing off-axis plies (e.g. [9/45] 2s , [150/60] 2s and [60/150] 2s ). The damaging of fibers on the surface ply due to polishing also reduces the CA/CF transition. Regarding crack propagation behavior, laminates with 08 fibers show mode-I cracking, whereas, the laminates with off-axis fibers show fatigue crack propagation at an angle to the mode-I direction. It is also found that the dominant direction of crack propagat

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Author

A Yasmin; P Bowen

Publisher

Elsevier Science; Elsevier ; Elsevier BV (ISSN 0921-5093)

Published

2003

Language

EN

Field

Engineering (Physical Sciences)