Abstract
The FE analysis of a panel made from carbon fibre reinforced thermoplastic polymer (CFRTP) loaded in compression is introduced. The panel contains five stringers with butt joint and demonstrates the alternative to CFRP panels made from fabrics by common laminate process. The pristine and cracked (initially delaminated) panels were investigated. The advanced detailed multi-layered model was generated by ABAQUS plug-in PbPModGen so that each composite layer was represented by a layer of finite elements. Cohesive elements (CZM) were applied to join the subparts of the panel. Buckling mode shapes were documented. The explicit nonlinear solver was used to study gradual buckling development for both, the simple and the detailed models. The effect of initial delamination between the central stringer and the skin was analysed. Local skin buckling in the delaminated area was found in addition. Compared to test results, the mode of the panel failure was captured with the lower load of 3% for the pristine and 9% for the cracked panel. The collapse occurred after local debonding of one stringer from the skin with its subsequent breakage and failure extension to other stringers. The presented work introduces buckling and post-buckling behaviour assessment and shows the effect of a crack on the compressive strength.
Published Version
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