Optimizing postbuckling composite panels for damage resistance

Andrea A. Faggiani*, Brian G. Falzon

*Corresponding author for this work

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-element-based 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 16th International Conference on Composite Materials, ICCM-16 - "A Giant Step Towards Environmental Awareness
Subtitle of host publicationFrom Green Composites to Aerospace"
PublisherInternational Committee on Composite Materials
ISBN (Print)9784931136052
Publication statusPublished - 01 Jan 2007
Externally publishedYes

Publication series

NameICCM International Conferences on Composite Materials


  • Buckling
  • Damage resistance
  • Debonding
  • Optimization
  • Postbuckling

ASJC Scopus subject areas

  • Engineering(all)
  • Ceramics and Composites

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