A numerical Approach for analyzing post-impact behaviour of composite laminate plate under in-plane compression
Résumé
A numerical approach is presented to estimate the compressive behaviors of 150x100mm² composite laminate specimen made from T800/M21S with impact damage and served as a guide for compression after impact (CAI) measurements. A continuum damage model has been developed at ICA-ISAE which gives as a result the impact damage by a reduction of material moduli through six damage variables, and the contribution of different ruin modes on each one. Each damage variable is obtained by summing the contribution of 5 different ruin modes (fiber breakage in tension or compression, spherical crush, perpendicular and parallel matrix cracking). This model was used to predict impact damage [1]. The numerical computation of CAI is performed with this damage model based on the computed realistic impact damage. The evolution and competition of different impact damage and ruin modes during CAI can be monitored and analyzed to determine which is predominant in the final rupture of the sample. At the same time, CAI tests are conducted on specimens impacted at 15J 20J and 30J with the purpose of validation. In order to compare with numerical conclusions, during CAI tests, some specimens are tried to be unloaded just before the final rupture for preservation of first initiated damage mechanisms to be identified by X-ray and Cscan examination.