Abstract
The results of a combined experimental and numerical
study of hat-stiffened co-cured carbon-fibre composite
panels loaded in uniaxial compression are presented.
All panels consisted of two integrated stiffeners
separated by an eight-ply thick skin bay of lay-up
[*45/0190], . The effects of a 100 mm circular cutout in
the skin was also investigated. The ultimate strength of
all panels was governed by the load carrying capacity of
the stiffeners. A change in the skin's buckling
mode-shape was also observed for all panels loaded
deep in the postbuckling region. The strains induced at
the interior free-edge were not found to be critical.
Non-linear finite element results correlated well with
the prebuckling and initial postbuckling strain and
displacements results obtained by experiment.
| Original language | English |
|---|---|
| Pages | 2663-71 |
| Number of pages | 9 |
| DOIs | |
| Publication status | Published - 12 Apr 1995 |
| Event | AIAA/ASME/AHS/ASC 36th Structures, Structural Dynamics and Materials Conference - New Orleans, United States Duration: 10 Apr 1995 → 12 Apr 1995 |
Conference
| Conference | AIAA/ASME/AHS/ASC 36th Structures, Structural Dynamics and Materials Conference |
|---|---|
| Country/Territory | United States |
| City | New Orleans |
| Period | 10/04/1995 → 12/04/1995 |