Device for intermediate fastening between an aircraft fuselage and an aircraft landing gear

Patent metadata

Field	Value
Publication number	US-9272776-B2
Application number	US-201314093862-A
Country	US
Kind code	B2
Filing date	Dec 2, 2013
Priority date	Nov 30, 2012
Publication date	Mar 1, 2016
Grant date	Mar 1, 2016

Abstract

A device for intermediate fastening between an aircraft fuselage and an aircraft landing gear is provided. The device includes at least one semi-open support structure comprising a pair of webs, which are substantially parallel to each other. The webs comprise first support means intended to receive the main pivot shaft of the landing gear and second support means intended to receive the stay joint or joints of the landing gear. The device includes two support structures linked together by a central box structure. The central box structure includes a front wall, a rear wall and linking walls linking those two walls.

First claim

What is claimed is:

1. A device for intermediate fastening between an aircraft fuselage and an aircraft landing gear, the landing gear configured to pivot around at least one main shaft and to be hinged around at least one stay joint to enable the extension or the retraction of the landing gear and comprising a leg having wheels which is linked to the at least one main shaft and a stay coupling the leg to the at least one stay joint, the device comprising:
at least one support structure including a first support means configured to receive said at least one main shaft and a second support means configured to receive said at least one stay joint; and
a central box structure coupled to the at least one support structure, the central box structure including a front wall, a rear wall and linking walls connecting the front wall and the rear wall;
wherein the at least one support structure includes a right support structure and a left support structure linked together by the central box structure, the central box structure configured transverse to the longitudinal axis of the aircraft fuselage when installed on the aircraft.

2. The device according to claim 1 , wherein said at least one support structure is hollow.

3. The device according to claim 1 , wherein said at least one support structure further comprises two support structures coupled together by the central box structure, and the central box structure is made as a single piece.

4. The device according to claim 1 , wherein the central box structure is hollow.

5. The device according to claim 1 , wherein the central box structure has an internal space configured for the installation of a means for imparting motion to the leg and the stay for the extension and the retraction of the landing gear.

6. The device according to claim 1 , wherein the first and second support means are configured, when the device is mounted on the aircraft fuselage, to be situated in the immediate neighborhood of a reference datum line of the aircraft fuselage.

7. The device according to claim 1 , wherein said at least one support structure further comprises a pair of webs which are substantially parallel to each other, the first support means and the second support means being carried by the pair of webs.

8. The device according to claim 7 , wherein webs of the pair of webs are spaced from each other and configured to receive, in the space so formed, the stay and a portion of the leg.

9. The device according to claim 8 , wherein the first and second support means are bearings bored in the webs.

10. The device according to claim 6 , further comprising an interface means configured to link said at least one support structure and the aircraft fuselage, the interface means fastened substantially at the location of the reference datum line of the aircraft fuselage.

11. An assembly, comprising:
an aircraft landing gear configured to pivot around at least one main shaft and to be hinged around at least one stay joint to enable the extension or the retraction of the landing gear and comprising a leg having wheels which is linked to the at least one main shaft and a stay coupling the leg to the at least one stay joint; and
a device for intermediate fastening between an aircraft fuselage and the landing gear, comprising:
at least one support structure including a first support means configured to receive said at least one main shaft and a second support means configured to receive said at least one stay joint, the at least one support structure being hollow; and
a central box structure coupled to the at least one support structure, the central box structure including a front wall, a rear wall and linking walls connecting the front wall and the rear wall;

wherein the at least one support structure includes a right support structure and a left support structure linked together by the central box structure, the central box structure configured transverse to the longitudinal axis of the aircraft fuselage when installed on the aircraft.

12. An aircraft, comprising:
a fuselage;
a landing gear configured to pivot around at least one main shaft and to be hinged around at least one stay joint to enable the extension or the retraction of the landing gear and comprising a leg having wheels which is linked to the at least one main shaft and a stay coupling the leg to the at least one stay joint; and
a device for intermediate fastening between the fuselage and the landing gear, comprising:
two support structures, each support structure including a first support means configured to receive said at least one main shaft and a second support means configured to receive said at least one stay joint; and
a central box structure coupled to the two support structures, the central box structure including a front wall, a rear wall and linking walls connecting the front wall and the rear wall;

wherein two support structures comprise a right support structure and a left support structure linked together by the central box structure, the central box structure configured transverse to the longitudinal axis of the aircraft fuselage when installed on the aircraft.

13. The assembly according to claim 11 , wherein said at least one support structure further comprises two support structures coupled together by the central box structure, and the central box structure is made as a single piece.

14. The assembly according to claim 11 , wherein the central box structure is hollow.

15. The assembly according to claim 11 , wherein the central box structure has an internal space configured for the installation of a means for imparting motion to the leg and the stay for the extension and the retraction of the landing gear.

16. The aircraft according to claim 12 , wherein the first and second support means are configured, when the device is mounted on the fuselage, to be situated in the immediate neighborhood of a reference datum line of the fuselage.

17. The aircraft according to claim 12 , wherein at least one of the two support structures further comprises a pair of webs which are substantially parallel to each other and the first support means and the second support means are carried by the pair of webs.

18. The aircraft according to claim 16 , further comprising an interface means configured to link said at least one support structure and the fuselage, the interface means fastened substantially at the location of the reference datum line of the fuselage.

19. The aircraft according to claim 12 , wherein at least one of the two support structures is hollow.

Assignees

• Airbus Operations Sas
• Airbus Operations Sas

Inventors

• Bellet Daniel
• Gallant Guillaume

Classifications

• B64C25/20 Primary

  mechanical · CPC title

• B64C25/10 Primary

  retractable, foldable, or the like · CPC title

• B64C25/04

  Arrangement or disposition on aircraft · CPC title

• B64C2025/125

  into the fuselage, e.g. main landing gear pivotally retracting into or extending out of the fuselage · CPC title