Optimising postbuckling composite panels for damage resistance

Andrea A. Faggiani, Brian G. Falzon

Research output: Chapter in Book/Report/Conference proceedingConference contribution


The design of current composite primary aerostructures, such as fuselage or wing stiffened panels, tends to be conservative due to the susceptibility of the relatively weak skin-stiffener interface. This weakness is due to through-thickness stresses which are exacerbated by deformations due to buckling. This paper presents a finite-elementbased optimization strategy, utilizing a global-local modelling approach, for postbuckling stiffened panels which takes into account damage mechanisms which may lead to delamination and subsequent failure of the panel due to stiffener debonding. A genetic algorithm was linked to a finite element package to automate the iterative procedure and maximize the damage resistance of the panel in postbuckling. For a given loading condition, the procedure optimized the panel’s skin layup leading to a design displaying superior damage resistance compared to non-optimized designs
Original languageEnglish
Title of host publicationProceedings of The Sixteenth International Conference on Composite Materials, July 8-13, 2007: Kyoto, Japan
EditorsKazuro Kageyama, Takashi Ishikawa, et al
Number of pages10
Publication statusPublished - 13 Jul 2007
Event16th International Conference on Composite Materials - Kyoto, Japan
Duration: 08 Jul 200713 Jul 2007


Conference16th International Conference on Composite Materials

Bibliographical note

Proceedings published on-line and on CD-ROM

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