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 language | English |
|---|---|
| Title of host publication | 16th ICCM International Conference on Composite Materials |
| Place of Publication | Kyoto, japan |
| Publisher | International Committee on Composite Materials |
| Number of pages | 10 |
| Publication status | Published - 2007 |
Bibliographical note
16th ICCM International Conference on Composite MaterialsKyoto, Japan
08 -13 Jul 2007
Keywords
- Buckling Damage resistance Debonding Optimization Postbuckling Genetic algorithms Glass ceramics Iterative methods Damage mechanism Finite element packages Loading condition Optimization strategy Optimized designs Through thickness stress Structural panels