Composite structures with hat-stiffened panels have gained traction in modern aircraft because they help reduce weight, increase durability, and provide stability to airframe skins. For weight reduction, skins should be designed to operate in the post-buckling regime. This causes possible interlaminar and intralaminar failure. However, composite panels stiffened with multiple hat-stringers are subject to cyclic loading even in the post-buckling regime. Under the NASA Advanced Composites Project (ACP), composite panels with multiple hatstringers were subject to a cyclic loading sequence from a pre-buckling state to a post-buckling state. This effort aimed to predict interlaminar failure for cyclic compression loading with pre-existent impact-induced damage. This work uses the Abaqus FEA Virtual Crack Closure Technique (VCCT), capabilities enhanced through an empirical method to integrate fatigue R-curve effects (different from R-ratio) into the Paris Law via user-defined subroutine to simulate the fatigue response o


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    Title :

    Integration of Fatigue R-Curve Effects into VCCT for Durability Predictions, Part 2: Buckled Composite Multi-Stringer Stiffened Panels


    Contributors:

    Conference:

    AIAA SciTech 2023 ; 2023 ; National Harbor, MD, US


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English