Landing gear well roof

Patent metadata

Field	Value
Publication number	US-2016185451-A1
Application number	US-201514973489-A
Country	US
Kind code	A1
Filing date	Dec 17, 2015
Priority date	Dec 30, 2014
Publication date	Jun 30, 2016
Grant date	—

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 bear. A membrane connecting the first reinforced main structure and the second reinforced main structure is disposed between them in the transverse direction.

First claim

1 . An aircraft landing gear well roof, the roof being intended to form 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 roof comprising:
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 a respective mounting articulating a structural element of the first main landing gear and mounting articulating a structural element of the second main landing bear; and a membrane connecting the first reinforced main structure and the second reinforced main structure disposed between them in the transverse direction.

2 . The gear well roof according to claim 1 , wherein the membrane has a rounded shape so as to define a recess in the upper surface of the roof.

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

4 . The gear well roof according to claim 1 , 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 articulating a structural element of the first landing gear is substantially centered on the first reinforced main structure and the mounting 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 the 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 longitudinal beam and at least one transverse beam.

13 . An aircraft comprising a gear well roof according to claim 1 .

14 . An assembly for 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 being intended to form 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 from each other in a transverse direction of the roof and equipped with a respective mounting articulating a structural element of the first main landing gear and mounting articulating a structural element of the second main landing bear; and a membrane connecting the first reinforced main structure and the second reinforced main structure disposed between them in the transverse direction, the gear roof arranged at a rear of the central wing box and each of the first and second reinforced main structures of which being fixedly mounted on the central wing box; structural elements of the first and second main landing gears being articulatedly mounted on the mounting equipping the first and second reinforced main structures of the roof; 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 the longitudinal direction.

16 . An assembly according to claim 14 .

Assignees

• Airbus Operations Sas

Inventors

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

Classifications

• B64C25/04 Primary

  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

• B64C1/18

  Floors · CPC title

• B64C1/10 Primary

  Bulkheads · CPC title

• B64C1/14 Primary

  Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens {accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers}(fairings movable in conjunction with undercarriage elements B64C25/16; bomb doors B64D1/06) · CPC title