An aircraft structural component, such as a fuselage or wing stringer 3, comprises a flange 31 and a web 32 having a first end 33 extending from the flange, and a second end 34 distal from the first end and from the flange. The web has a non-planar shape that deviates from a plane 36 which is normal to the flange and extends in a longitudinal direction of the component so that a deviation of the non-planar shape of the web from the plane increases with distance along the web in a direction from one of the first and second ends to the other of the first and second ends. The deviation extends over at least 10cm of a length of the component. The non-planar shape of the web may deviate from the plane by a constantly increasing amount from a first point to a second point along the length of the component and may define at least one sine wave. The first and second ends of the web may be of equal length. A method of fabricating the component may comprise use of a tool with a non-planar profile to impart the non-planar shape to the web.
Aircraft structural component and a method of fabricating an aircraft structural component
2024-05-22
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
AIRCRAFT STRUCTURAL COMPONENT AND A METHOD OF FABRICATING AN AIRCRAFT STRUCTURAL COMPONENT
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