Explicit Dynamic Simulation of Flat Nose LowVelocity Impact of Relatively Thick Composite Panels Using Built-In Failure Criteria

This work reports computational modelling of carbon fibre-reinforced composite panels subjected to flat nose drop-weight impact to predict ply-level failure using built-in failure criteria. It is widely recognised that accidental flat-nose tool (box) drop impact induce internal damage to an aircraft structure during part assembly, maintenance service and operation life. The internal damage remains undetected during routine inspections. However, the damage might cause unexpected catastrophic failure that is a major concern to aircraft industry. Extensive studies are underway on the topic to save human lives as well as capital assets by mitigating detrimental effects of the damage. Nonetheless, majority of the previous studies are experimental based, analytical studies are too complex, while simulation studies compare performance efficiencies of explicit and implicit dynamic solvers. Moreover, the predicted quantities such as load, velocity, deflection, energy, stress, and strain are further utilisation in relevant failure criteria. Thus efficient model is desired to predict ply-level failure. This study proposes reliable and efficient model consisting of mathematical formulation, ABAQUSTM/Explicit software simulation, and use of built-in mode-based failure criteria. Selected results were compared to the data results available in the literature and found in acceptable agreement. The model could be easily modified, extended, and useful to simulate similar further studies.