| Article ID | Journal | Published Year | Pages | File Type |
|---|---|---|---|---|
| 1719165 | Progress in Aerospace Sciences | 2015 | 33 Pages |
Abstract
The buckling and post-buckling behavior of curved cylindrical stringer-stiffened laminated composite and metal panels had been investigated both numerically and experimentally. The results were compared to those of cylindrical stringer-stiffened laminated composite shells to yield a way of determining the optimal structure to be used for axial compression loading. For the present tested structures, the composite panels showed the best load-weight ratio.
Related Topics
Physical Sciences and Engineering
Engineering
Aerospace Engineering
Authors
H. Abramovich, C. Bisagni,