Aircraft landing gear assembly

Patent metadata

Field	Value
Publication number	US-11235867-B2
Application number	US-201916511579-A
Country	US
Kind code	B2
Filing date	Jul 15, 2019
Priority date	Jul 16, 2018
Publication date	Feb 1, 2022
Grant date	Feb 1, 2022

Abstract

An aircraft landing gear assembly comprising: an axle having an axis, a wheel rotatably mounted on the axle to rotate about the axis, a brake arranged to selectively exert a braking torque on the wheel about the axis, a brake anchor structure having a substantially fixed position relative to the axle, a brake reaction linkage that mechanically couples the brake to the brake anchor structure, and a sensor comprising a sensor element arranged to detect a change in one or more physical properties of a component of the brake reaction linkage in order to determine a stress in the component due to the braking torque, wherein the sensor element does not contact the component.

First claim

The invention claimed is:

1. An aircraft landing gear assembly comprising:
an axle having an axis;
a wheel rotatably mounted on the axle to rotate about the axis;
a brake arranged to selectively exert a braking torque on the wheel about the axis;
a brake anchor structure comprising a first structural component of the aircraft landing gear assembly which is arranged so as to have a substantially fixed position relative to the axle;
a brake reaction linkage comprising one or more second structural components of the aircraft landing gear assembly that mechanically couple the brake to the brake anchor structure such that the one or more second structural components react the braking torque; and
a sensor comprising a sensor element arranged and configured to detect a change in one or more physical properties of at least one of the second structural components of the brake reaction linkage in order to determine a stress in the at least one of the second structural components due to the braking torque, wherein the sensor element does not contact the component, and wherein the sensor element is arranged and configured to directly observe the at least one of the second structural components of the brake reaction linkage in order to detect the change in one or more physical properties of the at least one of the second structural components of the brake reaction linkage.

2. The landing gear assembly of claim 1 , wherein the sensor element is configured to convert an electromagnetic property to an electrical signal.

3. The landing gear assembly of claim 2 , wherein the sensor element is a light transducer.

4. The landing gear assembly of claim 2 , wherein the sensor element is configured to detect a magnetic field.

5. The landing gear assembly of claim 1 , wherein the sensor is an interferometer.

6. The landing gear assembly of claim 1 , wherein the at least one of the second components is a torque tube, which surrounds and extends along the axle, and wherein the brake comprises stationary brake discs that are coupled to the torque tube.

7. The landing gear assembly of claim 6 , wherein the sensor is arranged on a radially inner or radially outer surface of the torque tube.

8. The landing gear assembly of claim 6 , wherein the sensor is arranged proximate to an end of the torque tube where the torque tube connects to a brake housing.

9. The landing gear assembly of claim 6 , wherein the sensor is arranged on a bracket arranged adjacent to the torque tube.

10. The landing gear assembly of claim 1 , wherein the component is a flanged adapter arranged to mechanically couple a brake housing of the landing gear to the axle, the flanged adapter extending around the axle and having an annular shape, which is L-shaped in cross section.

11. The landing gear assembly of claim 10 , wherein the flanged adapter is a spoked flanged adapter, which has a plurality of spokes extending radially between the axle and the brake housing.

12. The landing gear assembly of claim 1 , wherein the brake comprises a stack of brake discs.

13. The landing gear assembly of claim 12 , wherein the brake discs are formed from carbon.

14. The landing gear assembly of claim 1 , wherein the one or more second structural components are formed from metal.

15. The landing gear assembly of claim 1 , wherein the sensor element is arranged and configured to directly observe a surface of the one or more second structural components, wherein the surface is an integral, unitary part of the one or more second structural components.

16. The landing gear assembly of claim 1 , wherein the sensor element is not arranged and configured to directly observe a layer or sleeve applied to the one or more second structural components in order to detect the change in one or more physical properties of the one or more second structural components.

17. An aircraft including one or more landing gear assemblies, each landing gear assembly comprising:
an axle having an axis,
a wheel rotatably mounted on the axle to rotate about the axis,
a brake arranged to selectively exert a braking torque on the wheel about the axis,
a brake anchor structure comprising a first structural component of the aircraft landing gear assembly which is arranged so as to have a substantially fixed position relative to the axle,
a brake reaction linkage comprising one or more second structural components of the aircraft landing gear assembly that mechanically couple the brake to the brake anchor structure such that the one or more second structural components react the braking torque, and

a sensor comprising a sensor element arranged and configured to detect a change in one or more physical properties of at least one of the second structural components of the brake reaction linkage in order to determine a stress in the at least one of the second structural components due to the braking torque, wherein the sensor element does not contact the component, and wherein the sensor element is arranged and configured to directly observe the at least one of the second structural components of the brake reaction linkage in order to detect the change in one or more physical properties of the at least one of the second structural components of the brake reaction linkage.

Assignees

• Safran Landing Systems Uk Ltd
• Safran Landing Systems

Inventors

• Price Neil
• Coq Marie

Classifications

• G01L5/28

  for testing brakes · CPC title

• F16D55/36

  Brakes with a plurality of rotating discs all lying side by side · CPC title

• B60T17/22

  Devices for monitoring or checking brake systems; Signal devices · CPC title

• B60T8/52

  Torque sensing, i.e. wherein the braking action is controlled by forces producing or tending to produce a twisting or rotating motion on a braked rotating member · CPC title

• B60T8/171

  Detecting parameters used in the regulation; Measuring values used in the regulation · CPC title