Aircraft fuselage structure

Patent metadata

Field	Value
Publication number	US-9764815-B2
Application number	US-201414487727-A
Country	US
Kind code	B2
Filing date	Sep 16, 2014
Priority date	Mar 16, 2012
Publication date	Sep 19, 2017
Grant date	Sep 19, 2017

Abstract

An aircraft fuselage structure is disclosed herein and includes an outer skin, with circumferential ribs, such that a recess is provided for receiving a wing torsion box in the outer skin, and the ribs are interrupted in the region of the recess. An object of the disclosure includes providing an aircraft fuselage structure designed such that the wing torsion box is able to extend at least partially through the upper region of the fuselage, without the stability of the fuselage being significantly reduced. This can include providing first longitudinal members which are adjacent to the recess and which extend along the longitudinal edges beyond the entire length thereof. End regions of the first longitudinal members are connected to ribs which extend circumferentially at intervals from the transverse edges of the recess along the outer skin over the vertical longitudinal central plane.

First claim

What is claimed is:

1. An aircraft fuselage structure extending along a longitudinal axis, the fuselage structure comprising an outer skin which surrounds an internal space, comprising a plurality of circumferential ribs which are spaced apart from one another and which extend in planes perpendicular to the longitudinal axis along the outer skin, wherein a recess is provided for receiving a wing torsion box in the outer skin, the recess extending in a direction of the longitudinal axis via a plurality of ribs from a front transverse edge to a rear transverse edge, wherein the recess extends in a circumferential direction from a vertical longitudinal central plane symmetrically on both sides as far as longitudinal edges extending parallel to the longitudinal axis and wherein the ribs are interrupted in a region of the recess, and wherein:
first longitudinal members are provided, the first longitudinal members being adjacent to the recess and extending along the longitudinal edges beyond an entire length of the recess,
end regions of the first longitudinal members are connected to ribs which extend circumferentially at intervals from the transverse edges of the recess along the outer skin over the vertical longitudinal central plane,
ends of the ribs facing the recess are connected to the first longitudinal members,
second longitudinal members are provided, the second longitudinal members extending parallel and at intervals from the first longitudinal members and being arranged on the side of the first longitudinal members facing away from the recess, and
end regions of the second longitudinal members are connected to ribs which extend circumferentially at intervals from the transverse edges of the recess along the outer skin over the vertical longitudinal central plane.

2. The aircraft fuselage structure according to claim 1 , wherein ribs extending in the region of the recess between the first and the second longitudinal members have rib portions extending perpendicular to the first and second longitudinal members, which connect the first and the second longitudinal members together.

3. The aircraft fuselage structure according to claim 2 , wherein two of the rib portions have first retaining tabs which extend through recesses in the first longitudinal members and which are provided for pendulum supports for retaining the wing torsion box.

4. The aircraft fuselage structure according to claim 1 , wherein the second longitudinal members have second retaining tabs for retaining support surfaces and wherein the second retaining tabs extend through the outer skin.

5. The aircraft fuselage structure according to claim 1 , wherein crossmembers extend in a linear manner along the transverse edges of the recess, and wherein oblique portions are provided between the crossmembers and the outer skin, the oblique portions extending in planes which are inclined relative to the longitudinal axis and which slope away from the outer skin towards the crossmembers.

6. The aircraft fuselage structure according to claim 5 , wherein rib elements are arranged on the inwardly facing side of the oblique portions, the rib elements extending perpendicular to the crossmembers.

7. The aircraft fuselage structure according to claim 6 , wherein additional members extending at an angle to the ribs are provided, the additional members extending along a connecting line between the oblique portions and the outer skin and ends the additional members facing a center of the fuselage are connected to an adjacent rib.

8. The aircraft fuselage structure according to claim 7 , wherein strut elements extend between the rib elements and the additional members.

Assignees

• Airbus Operations Gmbh
• Airbus Defence & Space Gmbh

Inventors

• Benthien Hermann
• Haack Cord
• Poppe Andreas
• Burrichter Michael
• Abraham Torsten
• Brinckmann Michael
• Dierker Christoph
• Werth Frank
• Bindewald Wulf

Classifications

• B64C1/26 Primary

  Attaching the wing or tail units or stabilising surfaces · CPC title

• B64C1/068 Primary

  Fuselage sections · CPC title