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

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-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

Keywords

  • Buckling
  • Damage resistance
  • Debonding
  • Optimization
  • Postbuckling

ASJC Scopus subject areas

  • Engineering(all)
  • Ceramics and Composites

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