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.
|Number of pages||9|
|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||AIAA/ASME/AHS/ASC 36th Structures, Structural Dynamics and Materials Conference|
|Period||10/04/1995 → 12/04/1995|