Failure analysis in postbuckled composite T-sections

• Published in: Composite structures Vol. 86; no. 1; pp. 146 - 153
• Main Authors: Orifici, A.C., Shah, S.A., Herszberg, I., Kotler, A., Weller, T.
• Format: Journal Article Conference Proceeding
• Language: English
• Published: Oxford Elsevier Ltd 01.11.2008; Elsevier Science
• Subjects: Buckling; COCOMAT; Exact sciences and technology; Fracture mechanics (crack, fatigue, damage...); Fundamental areas of phenomenology (including applications); Physics; Postbuckling; Skin-stiffener damage; Solid mechanics; Stiffened panels; Structural and continuum mechanics; Skin-stiffener damage; Stiffened panels; Buckling; COCOMAT; Postbuckling; Rupture; Fracture criterion; Experimental study; Layer thickness; Modeling; Composite material; Reinforced structure; Global local method; Reinforced shell; Finite element method; Dimensional analysis; Antisymmetric load; Delamination; Fuselage; Strength; Crack initiation; Damaging; Stiffener
• ISSN: 0263-8223; 1879-1085
• DOI: 10.1016/j.compstruct.2008.03.022

Blade-stiffened skin designs made of composite materials have the potential to produce highly efficient structures, when the large strength reserves in the postbuckling range are utilised. This paper investigates the failure under postbuckling deformations of T-section specimens cut from a blade-stiffened panel, by comparing experimental results to finite element models. In the experimental work, T-section specimens with a particular lay-up and geometry were tested to failure in antisymmetric and symmetric loading rigs. These loading rigs simulate deformations on skin-stiffener interfaces during panel postbuckling. For the numerical analysis, two-dimensional models of the interface cross-section were used with a strength-based criterion that monitored failure within each ply. The use of a zero-thickness layer of cohesive elements has also been investigated in order to simulate the delamination behaviour. The numerical predictions are compared to the experimental results in terms of the failure load, specimen stiffness and specimen behaviour. The analysis approach is shown to be capable of predicting the critical damage locations and initiation loads for both antisymmetric and symmetric loadings. The successful prediction of failure in skin-stiffener interfaces can be linked to a global-local approach for efficient analysis of large, fuselage-representative composite structures.