Impact Damage Analysis of Layered Composite Plates
Material and geometrical parameters affecting structural response of impacted aircraft structures have been defined. Numerical model for the prediction of damage in layered composite panels under low velocity impact has been presented. The model takes into account matrix cracks and delaminations. All necessary numerical procedures have been performed within the frame of ABAQUS finite element software with the addition of user subroutines. Numerical effectiveness of the method has been demonstrated by the example of impact on the carbon/epoxy simply supported square plate.