| 摘要 |
Disclosed is a structural component , in particular for an aircraft, having a skin (34) and at least one stiffening element for stiffening the skin, wherein opposite to a run-out (30) of the stiffening element at least one supporting element (28a,28b) is positioned, wherein the at least one supporting element defines a supporting area (32) that is opened to the stiffening element run-out (30) in longitudinal direction of the stiffening element run-out and that is closed in transversal direction of the stiffening element run-out. |
