Landing gear well roof

Patent metadata

Field	Value
Publication number	US-10343768-B2
Application number	US-201514973489-A
Country	US
Kind code	B2
Filing date	Dec 17, 2015
Priority date	Dec 30, 2014
Publication date	Jul 9, 2019
Grant date	Jul 9, 2019

Abstract

An aircraft landing gear well roof including a first reinforced main structure and a second reinforced main structure spaced from each other in a transverse direction of the roof and equipped with respective mounting for articulating a structural element of the first landing gear and mounting for articulating a structural element of the second landing gear. A membrane connecting the first reinforced main structure and the second reinforced main structure is disposed between them in the transverse direction.

First claim

The invention claimed is:

1. An aircraft landing gear well roof, the roof forming a pressurization barrier between a pressurized upper compartment and a gear well for accommodating a first main landing gear and a second main landing gear of an aircraft, the roof comprising:
a first reinforced main structure having a first stiffened panel extending across a landing gear well of the first main landing gear and a second reinforced main structure having a second stiffened panel extending across a second landing gear well of the second main landing gear, the first and second reinforced main structures spaced from each other in a transverse direction of the aircraft, wherein the first reinforced main structure comprises a mounting for articulating the first main landing gear and the second reinforced main structure comprises a mounting for articulating the second main landing gear; and
a flexible central membrane disposed between the first and second reinforced main structures in the transverse direction and connecting the first and second reinforced main structure along interior longitudinal edges thereof, such that the first and second reinforced main structures are mechanically decoupled from one another in the transverse direction.

2. The gear well roof according to claim 1 , wherein the central membrane has a rounded U-shape that defines a downward recess in an upper surface of the roof.

3. The gear well roof according claim 1 , wherein the membrane has a curvature with a radius between 400 and 500 mm inclusive.

4. The gear well roof according to claim 2 , wherein the membrane has a first end and a second end fixed to the first reinforced main structure and the second reinforced main structure, respectively, a main part of the membrane being arranged between the first end and the second end.

5. The gear well roof according to claim 4 , wherein the first end and the second end each have a substantially vertical tangent.

6. The gear well roof according to claim 4 , wherein the main part of the membrane has a substantially constant thickness of 0.7 to 1.5 mm.

7. The gear well roof according to claim 4 , wherein the main part of the membrane is free of transverse stiffeners.

8. The gear well roof according to claim 4 , wherein the main part of the membrane has a ratio between a width in the transverse direction and a height in a vertical direction between 0.7 and 1.3 inclusive.

9. The gear well roof according to claim 1 , wherein the membrane is made of a metal or of an elastomer-based material.

10. The gear well roof according to claim 1 , wherein the mounting for articulating a structural element of the first landing gear is substantially centered on the first reinforced main structure and the mounting for articulating a structural element of the second landing gear is substantially centered on the second reinforced main structure.

11. The gear well roof according to claim 1 , wherein a ratio between a transverse extent of the membrane and a transverse extent of the first and second reinforced main structures is between 0.1 and 0.2 inclusive.

12. The gear well roof according to claim 1 , wherein each of the first and second reinforced main structures comprises a panel or a set of stiffened panels as well as at least one additional longitudinal beam and at least one transverse beam.

13. An aircraft comprising an aircraft landing gear well roof, the roof forming a pressurization barrier between a pressurized upper compartment and a gear well for accommodating a first main landing gear and a second main landing gear of the aircraft, the roof comprising:
a first reinforced main structure having a first stiffened panel extending across a landing gear well of the first main landing gear and a second reinforced main structure having a second stiffened panel extending across a second landing gear well of the second main landing gear, the first and second reinforced main structures spaced from each other in a transverse direction of the aircraft, wherein the first reinforced main structure comprises a mounting for articulating the first main landing gear and the second reinforced main structure comprises a mounting for articulating the second main landing gear; and
a flexible central membrane disposed between the first and second reinforced main structures in the transverse direction and connecting the first and second reinforced main structure along interior longitudinal edges thereof, such that the first and second reinforced main structures are mechanically decoupled from one another in the transverse direction.

14. An assembly for an aircraft comprising:
a central wing box for connection of two wings on respective opposite sides thereof in a transverse direction;
an aircraft landing gear well roof, the roof forming a pressurization barrier between a pressurized upper compartment and a gear well for accommodating a first main landing gear and a second main landing gear, the gear roof comprising:
a first reinforced main structure and a second reinforced main structure spaced forming respective roofs above the first and second main landing gears from each other in a transverse direction of the aircraft, wherein the first reinforced main structure comprises a mounting for articulating the first main landing gear and the second reinforced main structure comprises a mounting for articulating the second main landing gear; and
a flexible central membrane disposed between the first and second reinforced main structures in the transverse direction and connecting the first and second reinforced main structure along interior longitudinal edges thereof such that the first and second reinforced main structures are mechanically decoupled from one another in the transverse direction,
wherein the central wing box and the gear roof each extend transversely a complete width of a fuselage of the aircraft, and wherein the gear roof is arranged at a rear of the central wing box and each of the first and second reinforced main structures is fixedly mounted to the central wing box;

structural elements of the first and second main landing gears articulatedly mounted on each mounting; and
systems routed longitudinally in a recess delimited by the membrane of the gear well roof.

15. The assembly according to claim 14 , wherein each of the first and second main landing gears comprises a leg articulated about an articulation axis inclined relative to the transverse direction and inclined relative to a longitudinal direction.

16. The aircraft comprising an assembly according to claim 14 .

Assignees

• Airbus Operations Sas

Inventors

• Bellet Daniel
• Gallant Guillaume
• Loyant François
• Legardez Alexandre
• Roux Simon

Classifications

• B64C2025/125

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• B64C25/04 Primary

  Arrangement or disposition on aircraft · CPC title

• B64C1/18

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• B64C1/10 Primary

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• B64C1/14 Primary

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