Aircraft fuselage frame in composite material with stabilising ribs which, in at least a first sector (31), comprises a frame (9) with an omega-shaped cross-section (11) formed by a top element (23), two webs (25, 25'), two feet (27, 27') which includes at least one internal rib (41) formed by a top element (43) joined to the top element (23) of the frame (9), a web (45), two flanges (49, 49') joined to the webs (25, 25') of the frame (9) and a foot (47) aligned with the feet (27, 27') of the frame (9). The invention also relates to a manufacturing procedure for the first sector (31) of the frame with stabilised web (10) comprising steps for: a) providing a frame (9) and at least one internal rib (41) with the configurations indicated; b) joining at least said internal rib (41) to the frame (9).
AIRCRAFT FUSELAGE FRAME OF COMPOSITE MATERIAL WITH STABILISING RIBS
STRUCTURE DE FUSELAGE D'AERONEF EN MATERIAU COMPOSITE A NERVURES DE STABILISATION
2018-02-13
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |
AIRCRAFT FUSELAGE FRAME IN COMPOSITE MATERIAL WITH STABILIZED WEB
Europäisches Patentamt | 2017
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