The invention refers to an aircraft fuselage frame (2) that comprises a central element (3) adapted to be located within the perimeter of the fuselage, and two lateral extensions (4) projecting outside the perimeter of the fuselage from both sides of the central element (3) that are a portion of a longitudinal structure of a lifting surface (1). Additionally the central element (3) and the two lateral extensions (4) being configured as an integrated piece.
AIRCRAFT FUSELAGE FRAME
CHASSIS DE FUSELAGE D'AERONEF
2016-05-27
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
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