An existing compression after impact (CAI) model was used as the fitness function in an optimization routine to produce a damage tolerance optimized composite layup. This laminate was tested in a CAI strength experiment, alongside a baseline quasi-isotropic layup. Although a 13% improvement in CAI strength was observed, the analytical model was shown to overpredict the strength of the damage tolerance optimized laminate. It was found that the optimization process eliminated localized failure due to Mode-I buckling-induced propagation, and that the impacted laminate failed instead through globally driven, in-plane effects.
|Title of host publication
|51st AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
|Place of Publication
|American Institute of Aeronautics and Astronautics
|Published - 2010