Sensor device and method for sensing gas for aircraft shock-absorber

Patent metadata

Field	Value
Publication number	US-12459670-B2
Application number	US-202318121288-A
Country	US
Kind code	B2
Filing date	Mar 14, 2023
Priority date	Mar 15, 2022
Publication date	Nov 4, 2025
Grant date	Nov 4, 2025

Abstract

A sensor and method for sensing gas absorbed in hydraulic fluid in an aircraft shock absorber are disclosed. The hydraulic fluid and a gas are in fluid communication with each other. The sensor may be incorporated in the shock absorber or in servicing apparatus such as a servicing cart. The amount of gas absorbed in the hydraulic fluid is provided as a parameter which in combination with other parameters allows a user an improved means to determine the maintenance state of the shock absorber and to derive servicing actions.

First claim

The invention claimed is:

1 . A sensor device for determining at least one parameter at an aircraft shock absorber, the aircraft shock absorber having at least one chamber containing both hydraulic fluid and a gas in fluid communication with each other, an amount of the gas being absorbed in the hydraulic fluid,
wherein the at least one chamber comprises first and second compartments separated by a restrictive opening, wherein; the sensor device comprises a total dissolved gas sensor, wherein the total dissolved gas sensor is disposed in the second compartment containing hydraulic fluid, wherein the total dissolved gas sensor directly contacts the hydraulic fluid and is configured to directly measure an absorption level of the amount of the gas absorbed in the hydraulic fluid in order to determine the at least one parameter.

2 . The sensor device of claim 1 , wherein the sensor device is mounted within the at least one chamber of the shock absorber.

3 . The sensor device of claim 1 , wherein the at least one parameter is arranged to be monitored by at least one system of an aircraft to which the shock absorber is attached.

4 . The sensor device of claim 1 , wherein the sensor device is further arranged to measure a pressure of the at least one chamber; the at least one parameter including a pressure parameter.

5 . The sensor device of claim 1 , wherein the total dissolved gas sensor comprises a pressure transducer behind a rigid gas-permeable membrane.

6 . The sensor device of claim 1 , wherein the sensor device is mounted within a servicing apparatus operably connected to at least one port of the shock absorber, and wherein the sensor device is arranged to be in contact with the hydraulic fluid via the at least one port in order to determine the at least one parameter.

7 . The sensor device of claim 6 , wherein the servicing apparatus comprises at least one probe containing the sensor device, wherein the at least one probe is engaged with the at least one port in order to determine the at least one parameter.

8 . The sensor device of claim 6 , wherein the at least one parameter includes a pressure parameter; and wherein,
the servicing apparatus and/or the sensor device is arranged to determine the pressure parameter via a port of the shock absorber.

9 . The sensor device of claim 6 , wherein the sensor device is mounted within a first sampling chamber of the servicing apparatus;
the servicing apparatus is further arranged to receive a sample of the hydraulic fluid from the shock absorber into the first sampling chamber via the at least one port; and, the sensor device is arranged to be in contact with the hydraulic fluid at the first sampling chamber in order to determine the at least one parameter.

10 . The sensor device of claim 9 , wherein the sensor device is further arranged to measure a pressure of the gas and/or hydraulic fluid;
the at least one parameter includes a pressure parameter; the servicing apparatus includes a second sampling chamber operably connected to the gas port, and wherein, the servicing apparatus is further arranged to receive a sample of the gas from the shock absorber into the second sampling chamber via the gas port in order to determine the pressure parameter.

11 . The sensor device of claim 9 , wherein the servicing apparatus is a landing gear shock absorber servicing cart.

12 . An aircraft landing gear shock absorber comprising a sensor device according to claim 1 , the sensor device being configured to provide a measurement of the amount of gas in the hydraulic fluid in the shock absorber for use by an aircraft system and/or ground maintenance system.

13 . An aircraft landing gear assembly comprising a landing gear shock absorber according to claim 12 .

14 . An aircraft comprising an aircraft landing gear shock absorber according to claim 12 .

15 . A method of determining at least one parameter at an aircraft shock absorber, comprising:
providing the sensor device of claim 1 , directly measuring an absorption level of the amount of gas absorbed in the hydraulic fluid, and using the measured absorption level to provide the at least one parameter.

16 . The method of claim 15 , wherein the at least one parameter further comprises a pressure parameter, and wherein the method further comprises the steps of;
measuring a pressure of a chamber of the shock absorber containing the hydraulic fluid and the gas; and, deriving therefrom the pressure parameter.

17 . The method of claim 15 , wherein the at least one parameter provides an indication of a maintenance state of the shock absorber.

18 . The method of claim 15 , wherein the at least one parameter is used to derive maintenance actions for servicing the aircraft shock absorber.

19 . The method of claim 15 , wherein the at least one parameter is measured after a suspected hard-landing of the aircraft to which the shock absorber is attached.

20 . A servicing cart for servicing an aircraft shock absorber, the aircraft shock absorber having:
at least one chamber containing both hydraulic fluid and a gas in fluid communication with each other, an amount of the gas being absorbed in the hydraulic fluid, the at least one chamber including a gas port and a fluid port, wherein the at least one chamber comprises first and second compartments separated by a restrictive opening, the servicing cart including: a fluid sampling chamber arranged to receive a sample of the hydraulic fluid from the at least one chamber of the aircraft shock absorber via the fluid port, a second sampling chamber arranged to receive a sample of the gas from the at least one chamber of the aircraft shock absorber via the gas port; a gas absorption sensor device coupled to the fluid sampling chamber and arranged to measure an absorption level of the amount of the gas absorbed in the sample of the hydraulic fluid for determining a gas absorption parameter, a gas sensor device coupled to the gas sampling chamber and arranged to measure a pressure of the sample of the gas for determining a pressure parameter, wherein the gas sensor device comprises a total dissolved gas sensor, wherein the total dissolved gas sensor is disposed in the second compartment containing hydraulic fluid, wherein the total dissolved gas sensor directly contacts the hydraulic fluid, and wherein the gas absorption parameter and the pressure parameter are provided to a user of the servicing cart to allow the aircraft shock absorber to be serviced.

21 . The servicing cart of claim 20 , wherein the servicing cart includes a gas reservoir and a hydraulic fluid reservoir, and wherein;
the gas port is further arranged to provide gas from the gas reservoir to replenish gas in the at least one chamber of the aircraft shock absorber; and the fluid port is further arranged to provide hydraulic fluid from the fluid reservoir to replenish hydraulic fluid in the at least one chamber of the aircraft shock absorber.

Assignees

• Airbus Operations Ltd

Inventors

• Marles David

Classifications

• B64C25/60 Primary

  Oleo legs · CPC title

• B64F5/40

  Maintaining or repairing aircraft · CPC title

• F16F2230/24

  Detecting or preventing malfunction, e.g. fail safe · CPC title

• F16F2230/08

  Sensor arrangement · CPC title

• F16F2230/0047

  Measuring, indicating · CPC title