Global behaviour of a composite stiffened panel in buckling. Part 1: Numerical modelling |
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Authors: | Adrien Perret,Sé bastien Mistou,Marina Fazzini |
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Affiliation: | 1. DAHER-SOCATA, Aéroport Tarbes-Lourdes-Pyrénées, 65290 Louey, France;2. ENIT-LGP, PRES Université de Toulouse, Av. Azereix, BP1629, 65016 Tarbes, France |
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Abstract: | 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. |
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Keywords: | Structural composites Fracture Buckling Failure criterion Modelling |
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