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Abstract

As a consequence of their use in structural parts of supersonic aircraft, laminated composite materials have to withstand long periods at high temperature. The study presented here aims to characterize the transverse matrix cracking of a carbon/epoxy material subjected to tensile loading. Tensile tests have been performed on {0₃/90₃}_s laminates at three temperatures (20, 70 and 120°C) and three crosshead velocities (0.01, 1 and 10mm/min). Transverse matrix crack development is described for the nine corresponding experimental conditions. An LEFM approach is used to analyse the results concerning the first crack onset. After the validity of such an approach has been discussed, the focus is placed upon variations in the material resistance to transverse matrix cracking with temperature and loading rate.

Keywords

carbon/epoxy composite matrix cracking strain energy release rate temperature loading rate

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