Fatigue testing and buckling characteristics impacted composite specimens

摘要

Fatigue testing has been performed in constant amplitude tension-compression loading on impact damaged carbon fibre/epoxy composite laminates. Two layups were tested. The shape and the amplitude of the buckles were measured using an optical whole field measurement technique. The experimental conditions were chosen to be representative of damages in aircraft structures. The R-value was found to have a small influence on the fatigue life indicating that the compressive part of the load cycle has more Importance than the tensile part, this because the compressive load caused local bucking around the damage zone.