Front landing-gear well

Patent metadata

Field	Value
Publication number	US-9505483-B2
Application number	US-201214348093-A
Country	US
Kind code	B2
Filing date	Sep 27, 2012
Priority date	Sep 30, 2011
Publication date	Nov 29, 2016
Grant date	Nov 29, 2016

Abstract

A forward part of an aircraft comprising a fuselage and a landing gear well housing a forward landing gear comprising a breaker strut designed to adopt an extended configuration when the landing gear is extended, configuration in which said breaker strut lies in a strut plane parallel to the transverse direction of the forward part. The forward part comprises a transverse beam resisting strut reactions located above the landing gear well and mounted on the fuselage at its two ends, the beam having a globally rectangular cross-section, in which the median plane parallel to the length of the rectangle is coincident with said strut plane.

First claim

The invention claimed is:

1. A forward part of an aircraft comprising:
a fuselage extending lengthwise along a longitudinal direction of the aircraft,
a landing gear well and
a forward landing gear housed in the landing gear well and comprising a breaker strut designed to adopt an extended configuration when the landing gear is extended, and in the extended configuration, said breaker strut lies in a strut plane and extends along a direction parallel to a transverse direction of the forward part, the transverse direction being orthogonal to the longitudinal direction of the aircraft,
the forward part of an aircraft further comprising a transverse beam resisting breaker strut reactions located above the landing gear well and the transverse beam having opposing ends mounted orthogonal to the longitudinal direction of the aircraft on horizontally opposing sides of the fuselage, said transverse beam having a globally rectangular cross-section, in which a median plane parallel to a length of the globally rectangular cross-section is coincident with said strut plane.

2. The forward part of an aircraft according to claim 1 , wherein a ratio between a length of the beam extending in the transverse direction to the length of the globally rectangular cross-section of the beam is between 3 to 1 and 6 to 1.

3. The forward part of an aircraft according to claim 1 , wherein a ratio between a length of the beam extending in the transverse direction to the length of the globally rectangular cross-section of the beam is between 4 to 1 and 5 to 1.

4. The forward part of an aircraft according to claim 1 , wherein a ratio between the length and a width of the globally rectangular cross-section is between 8 to 1 and 12 to 1.

5. The forward part of an aircraft according to claim 1 , wherein a ratio between the length and a width of the globally rectangular cross-section is between 9 to 1 and 11 to 1.

6. The forward part of an aircraft according to claim 1 , wherein said beam extends from a top partition of the landing gear well to a floor of said forward part of the aircraft.

7. The forward part of an aircraft according to claim 1 , wherein said opposing ends of the beam are mounted on a skin of said fuselage.

8. The forward part of an aircraft according to claim 1 , wherein said beam has a lower longitudinal edge provided with means of assembly of said breaker strut.

9. The forward part of an aircraft according to claim 1 , wherein said beam is made of a composite material.

10. A forward part of an aircraft comprising:
a forward partition separating a forward landing gear well from a radome zone which houses a radar equipment;
a forward landing gear well located aft of said forward partition and housing a forward landing gear; and
an upper partition, below which the forward landing gear well is located, having at least one removable cover closing off a manhole for accessing the forward landing gear well.

11. The forward part of the aircraft according to claim 10 , further comprising two opposite lateral partitions, each partition forming an integral part of a lateral box formed jointly with an upper panel connected firstly to an upper longitudinal edge of each lateral partition, and secondly to a fuselage of the aircraft.

12. The forward part of the aircraft according to claim 10 , wherein the removable cover is in the form of a honeycomb sandwich structure.

13. The forward part of the aircraft according to claim 10 , further comprising one or more transverse stiffeners having opposing ends connected to a fuselage of the aircraft and routed adjacent to the upper partition.

14. The forward part of the aircraft according to claim 10 , wherein the forward landing gear comprises a deployment jack and a breaker strut both mounted on lateral partitions of the landing gear well.

15. The forward part of the aircraft according to claim 10 , wherein said forward landing gear comprises a breaker strut designed to adopt an extended configuration when the forward landing gear is extended, wherein said breaker strut lies in a strut plane parallel to a transverse direction of the aircraft, and in that the breaker strut comprises a transverse beam to resist strut forces arranged above the landing gear well and the transverse beam mounted at opposing ends to a fuselage of the aircraft, said transverse beam having a globally rectangular cross-section, in which a median plane parallel to a length of the globally rectangular cross-section is coincident with said strut plane.

Assignees

• Airbus Operations Sas

Inventors

• Guering Bernard
• Durand Yves

Classifications

• B64C25/10

  retractable, foldable, or the like · CPC title

• B64C25/04

  Arrangement or disposition on aircraft · CPC title

• B64C1/10

  Bulkheads · CPC title

• B64C25/14

  fore-and-aft · CPC title

• B64C1/36

  adapted to receive antennas or radomes · CPC title