Proceedings

ICAF 2023
Delft, The Netherlands, 2023
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Application of continuum damage mechanics for in-service real fatigue cracking scenarios


Go-down icaf2023 Tracking Number 49

Presentation:
Session: Session 11: Digital engineering II
Room: Theatre room: plenary
Session start: 10:50 Wed 28 Jun 2023

Ismael Rivero Arevalo   ismael.rivero-arevalo@airbus.com
Affifliation: Airbus

Jorge Gonzalez Rubio   Jorge.g.gonzalez@airbus.com
Affifliation: Airbus

Rodrigo Ruiz Santos   Rodrigo.ruiz-santos@airbus.com
Affifliation: Airbus

Javier Gómez-Escalonilla Martin   Javier.gomez-escalonilla@airbus.com
Affifliation: Airbus

Sonia Blayac   Sonia.blayac@airbus.com
Affifliation: Airbus

Daniel Barroso Vloedgraven   Daniel.barroso@airbus.com
Affifliation: Airbus

Rebeca Martínez Perez   rebeca.martinez-perez@airbus.com
Affifliation: Airbus


Topics: - Fatigue crack growth and life prediction methods (Genral Topics), - Digital Engineering (Genral Topics)

Abstract:

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.