Landing gear assembly

Patent metadata

Field	Value
Publication number	US-11945575-B2
Application number	US-202017296788-A
Country	US
Kind code	B2
Filing date	May 19, 2020
Priority date	May 20, 2019
Publication date	Apr 2, 2024
Grant date	Apr 2, 2024

Abstract

A retractable fuselage mounted landing gear assembly is disclosed. The landing gear assembly includes a main strut, a drag stay and a landing gear main fitting. A first end of the drag stay is attached to the main strut and a second end of the drag stay is connected to the fuselage. A first end of the landing main fitting is attached to the main strut and a second end of the main fitting is connected to the fuselage. When the landing gear is extended, substantially all the landing gear loads are transferred from the landing gear to the fuselage via one or more of the drag stay and the main fitting.

First claim

The invention claimed is:

1. An aircraft comprising a fuselage and a retractable landing gear assembly mounted on the fuselage, the landing gear assembly comprising:
a main strut
a drag stay, a first end of the drag stay being attached to the main strut and a second end of the drag stay being connected to the fuselage such that landing gear loads can be transferred into the fuselage of the aircraft from the drag stay;
a landing gear main fitting, a first end of the landing gear main fitting being attached to the main strut and a second end of the main fitting being connected to the fuselage such that landing gear loads can be transferred into the fuselage of the aircraft from the landing gear main fitting;
and wherein, in use, when the landing gear assembly is in an extended configuration relative to the fuselage, the landing gear loads experienced by the landing gear are only transferred from the landing gear to the fuselage via one or more of the drag stay and the main fitting.

2. An aircraft according to claim 1 , the aircraft comprising a wing having a rear spar and the fuselage comprising a fuselage airframe, and wherein the main strut is located aft of the rear spar and/or outboard of the fuselage airframe when the landing gear is in the extended configuration.

3. An aircraft according to claim 1 , the fuselage comprising a fuselage airframe and a wheel assembly mounted to a distal end of the main strut and wherein at least part of the wheel assembly is received within a recess formed in the fuselage airframe when the landing gear assembly is in a retracted configuration relative to the fuselage.

4. An aircraft according to claim 1 , the landing gear main fitting being pivotally connected to the fuselage for rotation about a landing gear axis such that the main strut can be rotated between an extended position and a retracted position relative to the fuselage and wherein the landing gear axis is inclined with respect to both a longitudinal axis and a lateral axis of the aircraft.

5. An aircraft according to claim 4 , wherein the inclination of the landing gear axis causes a distal end of the main strut to move inboard, forward and upward as the main strut moves from the extended position towards the retracted position.

6. An aircraft according to claim 4 , wherein the landing gear axis is inclined at an angle of 45 degrees with respect to both the longitudinal axis and the lateral axis of the aircraft.

7. An aircraft according to claim 1 , the aircraft comprising a wing and wherein the second end of the drag stay is connected to the fuselage in the region where the wing joins the fuselage.

8. An aircraft according to claim 7 , the wing comprising a rear spar and wherein the drag stay is attached to a point on the aircraft located aft of the rear spar.

9. An aircraft according to claim 7 , the wing comprising a plurality of ribs and wherein the drag stay is connected to the fuselage via one of said ribs, located at the interface between the fuselage and the wing.

10. An aircraft according to claim 7 , wherein the drag stay extends forward from the main strut so that the second end of the drag stay is located forward of the first end of the drag stay.

11. An aircraft according to claim 1 , the aircraft comprising a bulkhead, and wherein the landing gear main fitting is connected to the fuselage via an aircraft main fitting attached to the bulkhead.

12. A method of operating a landing gear assembly mounted on an aircraft fuselage, the landing gear assembly comprising a main strut connected to the fuselage by a drag stay and a main fitting,
the method comprising the steps of:
rotating the main strut about a landing gear axis to move the landing gear assembly from an extended configuration to a retracted configuration relative to the fuselage, and while the landing gear is in extended configuration, all the landing gear loads experienced by the landing gear are transferred to the fuselage by one, or at most both, of the drag stay and main fitting.

13. A method according to claim 12 , wherein the landing gear axis is inclined relative to a lateral and a longitudinal axis of the aircraft and the step of rotating the main strut about the landing gear axis comprises the distal end of the main strut moving inboard, forward and upward.

14. A landing gear assembly comprising:
a main strut having at least one pair of wheels mounted at a first end, each pair of wheels being arranged to rotate about a wheel axis;
a drag stay, a first end of the drag stay being attached to the main strut and a second end of the drag stay for connecting to the fuselage of an aircraft;
a landing gear main fitting for connecting the landing gear to the fuselage of an aircraft, the landing gear main fitting being attached to the main strut and defining a pivot axis about which the main strut can rotate;
and wherein the pivot axis is inclined an angle of at least 20 degrees with respect to each wheel axis such that the first end of the main strut moves forward and inboard as the main strut rotates about the pivot axis from an extended position to a retracted position.

15. An aircraft comprising a fuselage and a retractable landing gear assembly mounted on the fuselage, the landing gear assembly comprising:
a main strut
a drag stay, a first end of the drag stay being attached to the main strut and a second end of the drag stay being connected to the fuselage such that landing gear loads can be transferred into the fuselage of the aircraft from the drag stay;
a landing gear main fitting, a first end of the landing gear main fitting being attached to the main strut and a second end of the main fitting being connected to the fuselage such that landing gear loads can be transferred into the fuselage of the aircraft from the landing gear main fitting;
and wherein, in use, when the landing gear assembly is in an extended configuration relative to the fuselage, the landing gear has at most two load-bearing elements via which the landing gear loads experienced by the landing gear are transferred from the landing gear to the fuselage, a first one of said load-bearing elements being the drag stay and a second one of said load-bearing elements being the main fitting.

Assignees

• Airbus Operations Ltd
• Airbus Operations Sas

Inventors

• Perkins Christopher James
• Boscolo Marco
• White Nicholas
• Matheis Xavier
• Legardez Alexandre
• Roux Simon
• Crouzet Sébastien

Classifications

• B64C25/14

  fore-and-aft · CPC title

• B64C25/12

  sideways · CPC title

• B64C25/10 Primary

  retractable, foldable, or the like · CPC title

• 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