Failure Prediction in Large Scale Composite Laminates Containing Bonded Repairs

Abstract

A finite element (FE) based predictive framework, incorporating NASA’s CompDam composite damage model, has been developed to simulate damage initiation and progression in large carbon fiber reinforced polymer (CFRP) composite laminates containing various scarfed hole configurations. The framework was applied to a CFRP panel with a centrally located double-sided scarf hole. The CFRP laminate is made of carbon/epoxy with layup sequences comparable to transport category aircraft wing skin panels. The experimental work was previously conducted using the Airframe Beam Structural Test (ABST) fixture at the FAA William J. Hughes Technical Center, which can apply combinations of loads simulating various service loading conditions of an aircraft. Results show good correlation between FE analysis and experiment.