Residual Strength Analysis of a Composite Stiffened Panel After a Stiffener Debonding Using an Industrial Numerical Damage Model

• Autorzy: Morlet Benoît , Congourdeau Fabrice , Sola Guy , Martini Dominique , Robin Alban , Jacques Vincent

Identyfikatory

DOI

10.2478/fas-2024-0004

• Języki publikacji: EN

Abstrakty

EN

The increasing demand for greener aviation technology has driven the adoption of advanced composite materials in aircraft structures, offering significant weight saving and fuel efficiency improvements. Wing structures made of torsion boxes composed of stiffened panels have shown over the decades the benefits provided by composite technology, which is able to adapt the material properties to the structural constraints to which the structure is subjected. A convenient manufacturing technology for stiffened panels consists of co-bonding stiffeners on pre-cured skin. On these structures, the certification authorities require the demonstration of the residual strength at limit load of the panel with a disbonded stiffener. This is typically a post-buckling problem where the complete failure of the panel is due to a secondary buckling mode or the failure of adjacent stiffeners due to the combination of compressive and tearing loads, the larger buckled panel bay generating pull out loads on the adjacent stiffeners. This demonstration is classically performed by tests on large stiffened panels. In a composite wing box where geometrical parameters and loading modes can vary significantly from one zone to another, the numerical simulation can bring significant benefits to reduce the number of tests. This article presents a numerical damage model able to predict the damage and disbond of a co-bonded stiffener and applicable to a large aircraft structural model that can be integrated into a post-buckling simulation. As a validation case, this model has been applied to a multi stiffened composite panel where a central stiffener has been disbonded. The simulation results gave accurate predictions for the buckling loads and modes as well as for the appearance of damages on stiffeners until the panel failure.

Słowa kluczowe

EN

composite; damage model; stiffened panel; post-bucking

• Wydawca: Wydawnictwa Naukowe Sieci Badawczej Łukasiewicz - Instytutu Lotnictwa
• Czasopismo: Fatigue of Aircraft Structures
• Rocznik: 2024
• Tom: Iss.16
• Strony: 45--56
• Opis fizyczny: Bibliogr. 4 poz., rys., wykr., wzory

Twórcy

autor

Morlet Benoît

• DASSAULT-AVIATION Saint-Cloud 78, quai Marcel Dassault, 92552 Saint-Cloud Cedex, France

• https://orcid.org/0009-0005-0566-6391

autor

Congourdeau Fabrice

• DASSAULT-AVIATION Saint-Cloud 78, quai Marcel Dassault, 92552 Saint-Cloud Cedex, France

autor

Sola Guy

• DASSAULT-AVIATION Mérignac 54 avenue Marcel Dassault, 33701 Mérignac Cedex, France

autor

Martini Dominique

• DASSAULT-AVIATION Saint-Cloud 78, quai Marcel Dassault, 92552 Saint-Cloud Cedex, France

• https://orcid.org/0000-0001-9644-990X

autor

Robin Alban

• DASSAULT-AVIATION Saint-Cloud 78, quai Marcel Dassault, 92552 Saint-Cloud Cedex, France

autor

Jacques Vincent

• DASSAULT-AVIATION Saint-Cloud 78, quai Marcel Dassault, 92552 Saint-Cloud Cedex, France

• https://orcid.org/0009-0002-6172-6481

Bibliografia

• Chaibi, S. (2022). Prévision des endommagements induits par un impact basse vitesse/basse énergie au sein de matériaux composites stratifiés carbone-epoxy de dernière génération (in French). [Thèse de doctorat]. Université de Toulouse.
• Germain, J. (2020). Évaluation des capacités prédictives d’un modèle avancé pour la prévision de la tenue de plaques stratifies perforées (in French). [Thèse de doctorat]. Université Paris-Saclay.
• Montagne, B. (2020). Effet de l’interaction fixation composite sur les modes de rupture des assemblages boulonnés composites (in French). [Thèse de doctorat - Projet MARCOS]. ISAE - Institut Supérieur de l’Aéronautique et de l’Espace .
• Sola, G., Congourdeau, F., Martini, D., & Jacques, V. (2023). Numerical approach for stiffener debonding prediction of aircraft composite structures. 11th International Conference on Composites Testing and Model Identification, Girona. http://hdl.handle.net/10256/23147

Uwagi

This article was presented at the 32nd Symposium of ICAF https://www.icaf2025.com/