Composites 27B, 59-69, 1996
I.C. Skrna-Jakl, M.A. Stiftinger and F.G. Rammerstorfer
Institute of Lightweight Structures and Aerospace
TU Wien, Vienna, Austria
Computational investigations of the buckling and post-buckling
behavior of a stringer-stiffened composite wing torsion box employing
the finite element method are presented. Perfect and imperfect
configurations - considering geometrical imperfections as well as
initial stresses - are discussed. The determination of load-deflection curves
and first-ply-failure calculations for the skin are performed
for two different loadcases.
In addition, in a global-local approach, the interlaminar stresses, the risk of delamination and first ply failure in the stiffener sections in the prebuckled and the postbuckled ranges are examined. This approach combining nonlinear global and linear local investigations represents an analysis concept for stiffened composite structures, which considers the stability behavior of the structure as well as ply failure and onset of delamination in the skin, the stringers and the skin-stringer transitions.