Described and illustrated is an aircraft fuselage structure (1) comprising a skin element (7) having an inner surface (9), a support structure (5) connected to the inner surface (9) for supporting the skin element (7), and a door opening (3) provided in the skin element (7), wherein the support structure (5) comprises an upper longitudinal element (19), a lower longitudinal element (21), a first circumferential element (23) and a second circumferential element (25) provided at the door opening (3). The object to provide an aircraft fuselage structure (1), wherein the support structure (5) around the door opening (3) is optimized for a minimum weight, is achieved in that the support structure (5) comprises a first upper angled element (33) extending from an upper first corner (49) to an upper center point (73), and a second upper angled element (53) extending from an upper second corner (69) to the upper center point (73), such that the upper longitudinal element (19), the first upper angled element (33), and the second upper angled element (53) together form a central upper triangle (87).
AIRCRAFT FUSELAGE STRUCTURE
FLUGZEUGRUMPFSTRUKTUR
STRUCTURE DE FUSELAGE D'AÉRONEF
2019-07-17
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |