Optimising postbuckling composite panels for damage resistance

Andrea A. Faggiani, Brian G. Falzon

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

Abstract

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

Conference

Conference16th International Conference on Composite Materials
CountryJapan
CityKyoto
Period08/07/200713/07/2007

Bibliographical note

Proceedings published on-line and on CD-ROM

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