A frame component for a frame of a fuselage structure of an aircraft includes a central web extending along a longitudinal direction and having an inner edge region with respect to a radial direction running transversely with respect to the longitudinal direction and an outer edge region with respect to the radial direction. An inner web is bent from the inner edge region of the central web towards a first side. An outer web is bent from the outer edge region of the central web towards the first side. The central web, the outer web and the inner web are produced integrally from a metal sheet and together define a C-shaped cross section of the frame component. At least one stringer recess is formed in the outer web and in the outer edge region of the central web. The central web has, in the region of the stringer recess, a first reinforcing formation which forms a protrusion on the first side of the central web.
SPANTKOMPONENTE UND VERFAHREN ZUR HERSTELLUNG EINER SPANTKOMPONENTE, SPANT UND RUMPFSTRUKTUR FÜR EIN LUFTFAHRZEUG
FRAME COMPONENT AND METHOD FOR MANUFACTURING A FRAME COMPONENT, FRAME AND FUSELAGE STRUCTURE FOR AN AIRCRAFT
COMPOSANT DE CADRE ET PROCÉDÉ DE FABRICATION D'UN COMPOSANT DE CADRE, CADRE ET STRUCTURE DE FUSELAGE POUR UN AÉRONEF
2022-10-26
Patent
Electronic Resource
German
European Patent Office | 2021
|European Patent Office | 2020
|European Patent Office | 2017
|