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 language | English |
|---|---|
| Title of host publication | Proceedings of The Sixteenth International Conference on Composite Materials, July 8-13, 2007: Kyoto, Japan |
| Editors | Kazuro Kageyama, Takashi Ishikawa, et al |
| Number of pages | 10 |
| Publication status | Published - 13 Jul 2007 |
| Event | 16th International Conference on Composite Materials - Kyoto, Japan Duration: 08 Jul 2007 → 13 Jul 2007 |
Conference
| Conference | 16th International Conference on Composite Materials |
|---|---|
| Country/Territory | Japan |
| City | Kyoto |
| Period | 08/07/2007 → 13/07/2007 |