Aircraft having a simplified general section

Patent metadata

Field	Value
Publication number	US-10071797-B2
Application number	US-201615133758-A
Country	US
Kind code	B2
Filing date	Apr 20, 2016
Priority date	Apr 20, 2015
Publication date	Sep 11, 2018
Grant date	Sep 11, 2018

Abstract

An aircraft comprising a fuselage which has a central part with a cross section of constant geometry which comprises a floor. The floor comprises two lateral portions which are fixed respectively to two opposite lateral edges of the fuselage and which enclose a central portion to which they are fixed. One of the lateral floor portions is fixed to the central portion so as to allow a relative lateral movement between the two portions in the event of a modification in pressure inside the fuselage. The cross section thus deforms homogeneously when the fuselage is pressurized and the floor is not involved in maintaining the shape of the fuselage.

First claim

The invention claimed is:

1. An aircraft comprising a fuselage having a central part with a cross section of constant geometry and which comprises a floor, the floor comprising:
two lateral portions which are fixed respectively to two opposite lateral edges of the fuselage and which enclose a central portion to which the two lateral portions are fixed,
one of the two lateral floor portions being fixed to the central portion so as to allow a relative lateral movement between the two portions in the event of a modification in pressure inside the fuselage without transferring mechanical loads from the one of the lateral floor portions of the central portion.

2. The aircraft according to claim 1 , wherein the fuselage comprises, arranged in succession along a longitudinal axis of the aircraft, a nose, the central part with a cross section of constant geometry and a tail, the nose and the tail being each of non-constant cross section.

3. The aircraft according to claim 1 , wherein the central part has a circular cross section.

4. The aircraft according to claim 1 , further comprising, for each lateral floor portion, arranged along a longitudinal axis of the aircraft, a plurality of force-transmitting elements which extend between each lateral floor portion and the fuselage, each force-transmitting element extending obliquely from an end of a lateral floor portion fixed to the central floor portion to a lower edge of the fuselage located beneath the lateral floor portion and set back with respect to a projection formed by the end of said lateral floor portion.

5. The aircraft according to claim 1 , further comprising, above each lateral floor portion, a plurality of rows of passenger seats, the passenger seats of each row being mounted on a common tube whose longitudinal extent is parallel to the floor, the tube being itself fixed to the corresponding lateral floor portion by a single foot.

6. The aircraft according to claim 4 , further comprising, above each lateral floor portion, a plurality of rows of passenger seats, the passenger seats of each row being mounted on a common tube whose longitudinal extent is parallel to the floor, the tube being itself fixed to the corresponding lateral floor portion by a single foot.

7. The aircraft according to claim 6 , wherein the single foot of each row of passenger seats is fixed at the end of the lateral floor portion which is fixed to the central floor portion so as to transmit the vertical forces passing through said foot through the force-transmitting elements located beneath the floor.

8. The aircraft according to claim 1 , wherein the central part is reserved for receiving passenger seats.

9. The aircraft according to claim 1 , further comprising, integrated into the lateral floor portions so as to extend longitudinally in the central part of the aircraft, bundles of electric cables and air supply and removal ducts.

10. The aircraft according to claim 1 , wherein the one of the two lateral floor portions is slideably fixed to the central portion.

11. The aircraft according to claim 10 , wherein both lateral floor portions are slideably fixed to the central portion to allow a relative lateral movement between the two portions in the event of a modification in pressure inside the fuselage without transferring mechanical loads from the lateral portions to the central portion.

12. The aircraft according to claim 11 , wherein the two lateral floor portions are each slideably fixed to the central portion via a sliding connection comprising a pin within an oblong hole.

13. The aircraft according to claim 10 , wherein the one of the two lateral floor portions is slideably fixed to the central portion via a sliding connection comprising a pin within an oblong hole.

14. The aircraft according to claim 1 , wherein each lateral floor portion comprises a box divided into multiple parallel hollow compartments.

Assignees

• Airbus Operations Sas

Inventors

• Guering Bernard
• Saint-Marc Laurent

Classifications

• B64D27/02

  Aircraft characterised by the type or position of power plants · CPC title

• B64C1/20 Primary

  specially adapted for freight · CPC title

• B64C5/02

  Tailplanes · CPC title

• B64C1/18 Primary

  Floors · CPC title

• B64D11/04

  Galleys · CPC title