25th Congress of International Council of the Aeronautical Sciences, 3 - 8 September 2006, Hamburg, Germany
Paper ICAS 2006-10.4.4


POSTBUCKLING BEHAVIOUR OF A STIFFENED PANEL SUBJECT TO COMBINED LOADING

C. A. Featherston, K. Koffi*, R. L. Burguete*
Cardiff Univ., UK; *Airbus, UK

Keywords: Postbuckling, stiffened panel, shear, in-plane bending, FEA

Aircraft wings comprise thin shells under compressive loading, potentially subject to buckling failure. In one component part, the spar, redistribution of stresses following initial buckling provides significant load carrying capability during postbuckling. The work presented aims to quantify this, to extend the design envelope and thereby reduce weight and cost.


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