B - Operations – Transporting – 64 – C
Patent
B - Operations, Transporting
64
C
B64C 1/00 (2006.01) B64C 1/06 (2006.01) B64C 1/12 (2006.01)
Patent
CA 2654045
An aircraft fuselage structure is described, which is constructed from a plurality of shells (11, 12) which are joined together, each form part of the aircraft fuselage (10) and comprise a support structure (13, 13a, 14, 14a) and a skin (15, 16) which is arranged on the latter and outwardly seals the aircraft fuselage (10) in a compression-proof manner. According to the invention, the aircraft fuselage structure comprises an upper and side shell (11) and a lower shell (12), of which the lower shell (12) has a radius (R2) which is essentially significantly larger than the radius (Rl) of the upper and side shell (11), the upper and side shell (11) and the lower shell (12) being joined together at transition regions (18, 19) extending in the longitudinal direction of the aircraft, and the support structure (13, 13a) of the lower shell (12) being designed in terms of its strength in such a manner that it is capable of absorbing the internal pressure loading of the lower shell (12) without the use of a main crossmember.
La présente invention concerne une structure de fuselage d'aéronef qui est construite à partir d'une pluralité de coques (11, 12) qui sont assemblées, chacune formant une partie du fuselage d'un aéronef (10) et comprenant une structure de support (13, 13a, 14, 14a) et un revêtement (15, 16) qui est disposé sur celle-ci et rend étanche vers l'extérieur le fuselage d'aéronef (10) d'une manière résistant à la compression. Selon l'invention, la structure de fuselage d'aéronef comprend une coque supérieure et latérale (11) et une coque inférieure (12), la coque inférieure (12) a un rayon (R2) qui est sensiblement considérablement supérieure au rayon (R1) de la coque supérieure et latérale (11), la coque supérieure et latérale (11) et la coque inférieure (12) étant assemblées en des régions de transition (18, 19) s'étendant dans la direction longitudinale de l'aéronef, et la structure de support (13, 13a) de la coque inférieure (12) étant conçue en fonction de sa résistance d'une telle manière qu'elle est apte à absorber la charge de pression interne de la coque inférieure (12) sans l'utilisation d'une traverse principale.
Airbus Deutschland Gmbh
Airbus Operations Gmbh
Sim & Mcburney
LandOfFree
Aircraft fuselage structure and method for its production does not yet have a rating. At this time, there are no reviews or comments for this patent.
If you have personal experience with Aircraft fuselage structure and method for its production, we encourage you to share that experience with our LandOfFree.com community. Your opinion is very important and Aircraft fuselage structure and method for its production will most certainly appreciate the feedback.
Profile ID: LFCA-PAI-O-1634243