Stiffened panel for fuselage in aircraft, has stiffener extending from one end to another end of panel, where trace of stiffener follows non-null geodesic curvature between ends of stiffener, over surface of skin of panel

摘要

The panel has a longitudinal stiffener (4) extending from one end to another end of the panel, where the panel is made of fiber reinforced composite material. Trace of the stiffener follows a non-null geodesic curvature between the ends of the stiffener, over a surface of a skin of the panel. The stiffener is formed of folds. The stiffener is formed by overlapping edges of the folds when the folds are draped with an intermediate ply arranged between the edges of the folds. An independent claim is also included for an aircraft comprising a fuselage.