Application of continuum damage mechanics for in-service real fatigue cracking scenarios

icaf2023 Tracking Number 49

F&DT evaluation for aeronautical structures is a complex process able to produce robust designs and ensure high safety standards. Nevertheless fatigue cracking events are still happening in any aircraft fleet, in most of the cases due to an interaction of several causes that cannot be properly combined in the standard F&DT evaluations. The evaluation and correlation of in-service findings is essential to ensure that root cause is identified and adequate corrective actions are taken. However this is not an easy task as these events are usually associated with complex structural and material behaviours that are difficult to be properly predicted under certain conditions by current F&DT certification methods. This paper presents an Airbus real practical application in the context of an in-service cracking scenario using more sophisticated state-of-the-art F&DT prediction methods techniques combining a highly refined detailed finite element model with a fatigue damage model based on the Continuum Damage Mechanics framework. Details of the overall process followed as a result of an in service crack finding will be provided. This process includes a full damage correlation against a specific subcomponent test and in service experience as part of the Continuous Airworthiness verification, validation and acceptance criteria.