Abstract
In the present work, the fracture resistance of a carbon fiber composite under mode I and mode II loading have been experimentally determined. For the mode I and II, the energy release rate G has been determinate for each material. In some cases, only a single estimation of G was possible due to problems in the propagation such as extensive fiber bridging and loss of planarity of the running crack. The experimental results relative to DCB tests have been analyzed in order to derive statistical trends. Only the samples for which more than three crack advance data points have been collected are considered in the analysis. The G values are those obtained with the compliance calibration method (CC). For ENF test, determination of critical GII, in addition to the value calculated with the relationship given in the prescription EN6034, other two values, the non linear and visual non linear, are also given. The crack propagation resulted to be unstable for all specimens tested and only a single value of GII could be determined.
Highlights
Composites based on carbon fiber are widely used in the field of automobiles, aircrafts, and spacecrafts
Interlaminar flaws, or delaminations, can be generated in the composite material during the production process, as a consequence of the contamination of the prepeg which may result in regions with poor adhesion between plies, or they can start from regions of the composite with an elevated void volume fraction
Double Cantilever Beam (DCB) and End Notched Flexure (ENF) testing mainly measured the fracture toughness for Mode I and Mode II
Summary
Composites based on carbon fiber are widely used in the field of automobiles, aircrafts, and spacecrafts. The fracture resistance of carbon fiber based laminates under mode I and mode II loading have been experimentally determined.
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