Aircraft landing gear assembly

Patent metadata

Field	Value
Publication number	US-9919793-B2
Application number	US-201514882599-A
Country	US
Kind code	B2
Filing date	Oct 14, 2015
Priority date	Oct 16, 2014
Publication date	Mar 20, 2018
Grant date	Mar 20, 2018

Abstract

An aircraft landing gear assembly having a main strut and an axle on which wheel and brake assemblies are mounted. An adaptor member is mounted on a mounting pin and arranged to define a brake rod anchor point. The adaptor member is coupled to a part of the landing gear assembly so as to react brake torque and can be formed from a different material than a portion of the main strut.

First claim

The invention claimed is:

1. An aircraft landing gear assembly comprising:
a main strut arranged to be coupled to an aircraft;
an elongate axle movably coupled to the main strut;
a wheel assembly mounted on the axle;
a brake assembly mounted on the axle;
a first brake rod coupled at a first location on the first brake rod to the brake assembly; and
a first adaptor member distinct from the main strut and mounted on a mounting pin to be rotatable relative to the main strut, the first adaptor member comprising a first arm that defines a first anchor point to which the first brake rod is coupled at a second location on the first brake rod, the first adaptor member being coupled to a first part of the landing gear assembly distinct from the first adaptor member in a manner inhibiting relative rotation between the first adaptor member and the mounting pin;
wherein the first adaptor member includes a second arm defining a first auxiliary anchor point via which the first adaptor member is coupled to a second part of the landing gear assembly distinct from the first adaptor member and distinct from the first part of the landing gear assembly so as to inhibit relative rotation between the first adaptor member and the mounting pin.

2. The aircraft landing gear assembly of claim 1 , wherein the mounting pin is arranged to inhibit movement of the first adaptor member relative to the main strut in degrees of freedom other than rotation.

3. The aircraft landing gear assembly of claim 1 , wherein the mounting pin comprises a pin joint between first and second elements of the landing gear assembly, the first and second elements each being distinct from the first adaptor member.

4. The aircraft landing gear assembly of claim 3 , wherein: the first element comprises the main strut and the second element comprises a bogie beam; the bogie beam is pivotally coupled to the main strut via a bogie hinge pin; and the mounting pin comprises the bogie hinge pin.

5. The aircraft landing gear assembly of claim 1 , wherein the first arm and/or the second arm is elongate.

6. The aircraft landing gear assembly of claim 1 , further comprising a second adaptor member having a third arm arranged in a spaced parallel relationship with respect to the first arm, and defining a second anchor point for at least a second brake rod.

7. The aircraft landing gear assembly of claim 6 , wherein the second anchor point is coaxial with the first anchor point.

8. The aircraft landing gear assembly of claim 6 , wherein the third arm is coupled to the landing gear assembly via the mounting pin, the first adaptor member and the second adaptor member each being coupled to the mounting pin via engagement formations arranged to prevent relative rotation between the first adaptor member, the second adaptor member and the mounting pin.

9. The aircraft landing gear assembly of claim 6 , wherein the second adaptor member includes a fourth arm arranged defining a second auxiliary anchor point via which the second adaptor member is coupled to the landing gear assembly.

10. The aircraft landing gear assembly of claim 1 , wherein the main strut comprises a main fitting and a slider coupled to one another via a torque link, and the first auxiliary anchor point is coupled to a torque link mounting pin.

11. The aircraft landing gear assembly of claim 6 , wherein the first arm and/or third arm extends generally parallel with respect to the longitudinal axis of the main strut.

12. The aircraft landing gear assembly of claim 1 , wherein the first auxiliary anchor point includes a lost motion device.

13. The aircraft landing gear assembly of claim 1 , wherein the first adaptor member is formed from a different material than a lower portion of the main strut.

14. The aircraft landing gear assembly of claim 1 , wherein the mounting pin connects the first adapter member to a lower portion of the main strut.

15. The aircraft landing gear assembly of claim 14 , wherein the mounting pin is coaxial with a bogie hinge pin connecting the bogie beam to the main strut.

16. The aircraft landing gear assembly of claim 14 , wherein the main strut comprises a main fitting and a slider coupled to one another via a torque link, and the mounting pin connects the first adapter member to the slider.

17. An aircraft landing gear assembly comprising:
a main strut arranged to be coupled to an aircraft;
an elongate axle movably coupled to the main strut;
a wheel assembly mounted on the axle;
a brake assembly mounted on the axle;
a brake rod coupled to brake assembly; and
an adaptor member distinct from the main strut and mounted on a mounting pin to be rotatable relative to the main strut, the adaptor member comprising a first arm which defines an anchor point to which the brake rod is coupled, the adaptor member being coupled to an anchor region of the landing gear assembly distinct from the adaptor member in a manner inhibiting relative rotation between the adaptor member and the mounting pin, wherein the adaptor member includes a second arm defining an auxiliary anchor point via which the adaptor member is coupled to the anchor region of the landing gear assembly so as to inhibit relative rotation between the adaptor member and the mounting pin.

18. An aircraft including one or more landing gear assemblies of claim 1 .

19. The aircraft landing gear assembly according to claim 17 , wherein the anchor region of the landing gear assembly is part of the main strut.

20. The aircraft landing gear assembly according to claim 17 , wherein the first adaptor member is coupled to the main strut.

Assignees

• Messier Dowty Ltd
• Safran Landing Systems Uk Ltd

Inventors

• Sexton Matthew
• Schmidt Robert Kyle

Classifications

• B64C25/08

  non-fixed, e.g. jettisonable · CPC title

• B64C25/36 Primary

  Arrangements or adaptations of wheels, tyres or axles in general · CPC title

• B64C25/42 Primary

  Arrangement or adaptation of brakes · CPC title