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Global behaviour of a composite stiffened panel in buckling. Part 1: Numerical modelling

Perret, Adrien and Mistou, Sébastien and Fazzini, Marina Global behaviour of a composite stiffened panel in buckling. Part 1: Numerical modelling. (2011) Composite Structures, 93 (10). 2610-2618. ISSN 0263-8223

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Official URL: http://dx.doi.org/10.1016/j.compstruct.2011.04.026


The present study analyses an aircraft composite fuselage structure manufactured by the Liquid Resin Infusion (LRI) process and subjected to a compressive load. LRI is based on the moulding of high performance composite parts by infusing liquid resin on dry fibres instead of prepreg fabrics or Resin Transfer Moulding (RTM). Actual industrial projects face composite integrated structure issues as a number of structures (stiffeners, …) are more and more integrated onto the skins of aircraft fuselage. A representative panel of a composite fuselage to be tested in buckling is studied numerically. This paper studies which of the real behaviours of the integrated structures are to be observed during this test. Numerical models are studied at a global scale of the composite stiffened panel. Linear and non linear analyses are conducted. The Tsai–Wu criterion with a progressive failure analysis is implemented, to describe the global behaviour of the panel up to collapse. Also, three stiffener connection methods are compared at the intersection between two types of integrated structures. Load shortening curves permit to estimate the expected load and displacements.

Item Type:Article
Additional Information:Thanks to Elsevier editor. The definitive version is available at http://dx.doi.org/10.1016/j.compstruct.2011.04.026
HAL Id:hal-00812133
Audience (journal):International peer-reviewed journal
Uncontrolled Keywords:
Institution:Other partners > DAHER (FRANCE)
Université de Toulouse > Institut National Polytechnique de Toulouse - Toulouse INP (FRANCE)
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Deposited On:11 Apr 2013 14:55

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