Planar Delamination Growth Of Composite Laminates Under Mode II Fatigue Loading

For the past few decades, research into fatigue delamination behaviour of Carbon Fibre Reinforced Polymer (CFRP) composites has predominantly relied on standard test methods. These methods typically utilize a uniaxial delamination length to quantify the fatigue delamination process. However, this approach is inadequate to describe the nature of delamination growth in a planar manner. In this work, an experimental study was conducted to gain insights into the planar delamination behaviour of CFRP composites under mode II fatigue loading. Delamination growth of two specimen configurations, each containing an embedded initial defect, was monitored through ultrasound scanning (C-scan). During load-control fatigue testing, the growth rate exhibited an initial rise, followed by a subsequent decrease as loading cycles increased. Despite the development of a larger delamination area under fatigue loading, a consistent overall stiffness was observed. Fractography revealed the presence of various fracture mechanisms ocurring at different locations near the initial delamination front. Micro matrix cracking and fibre-matrix debonding emerged as dominant mechanisms in 2D fatigue delamination growth following the fibre direction. Matrix cracking within the laminate ply occurred at the locations where the growth direction deviated from the fibre direction, consequently triggering delamination migration.