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Abstract
AbstractLow‐energy instrumented falling weight impact tests were used to study the failure mechanisms in various multiangle laminates of continuous carbon‐fiber‐reinforced composites. C‐scans of impacted specimens were conducted to monitor an area for delamination damage. Photography of the tension surface during impact enabled the onset of tension surface cracking to be detected. These techniques were employed for composites based on thermoplastic, poly(ether ether ketone) (PEEK), and thermoset (epoxy system 934) matrix materials. In addition, a range of ply numbers (8 to 40) were used in preparation of the multiangle laminates. Tension surface splitting can be shown to be the first failure mechanism during impact. Initiation of a tension crack occurs at a lower absorbed impact energy than that for the onset of delamination damage.
Published Version
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