| 摘要 |
<p>The invention relates to a structural element (1,12,30) for reinforcing a fuselage of an aircraft, wherein the structural element comprises a reinforcement profile (2,13) which is made of a metallic material, particularly an aluminum alloy material or a titanium alloy material, as a single piece. According to the invention, the reinforcement profile is provided with a tab (5,14,24) at least in some areas. As a result of the tab, which is made of a fiber-reinforced layer material (7) or a fiber metal laminate and glued to a flange (20, 32) of the reinforcement profile at least in some areas, the structural element has a high damage tolerance and advantageous fatigue properties. The fiber metal laminate or the layer material comprises a plurality of metal layers (8,34,43) and fiber-reinforced plastic layers (9,35,41) stacked in alternating fashion, said layers being glued to each other over the entire area. The reinforcement profile is joined to the tab through a joining layer (6,15,36). Said joining layer is constructed with preferably two prepreg layers (20,23,37,38) and a non-fiber-reinforced adhesive layer (21). The reinforcement profile is, for example, a curved rib segment (31) or a straight beam, both of which can be used particularly to brace a central and highly loaded fuselage section of a high wing aircraft. A crack (16) which forms in the area of an inner flange or an outer flange of the rib segment or of a reinforcement profile is bridged by the effect of the tab so that further propagation, if not completely prevented, is at least greatly slowed.</p> |
