Servicing of landing gear shock absorbers

Patent metadata

Field	Value
Publication number	US-10358236-B2
Application number	US-201615204548-A
Country	US
Kind code	B2
Filing date	Jul 7, 2016
Priority date	Jul 10, 2015
Publication date	Jul 23, 2019
Grant date	Jul 23, 2019

Abstract

A method and portable apparatus for servicing a shock absorber on a landing gear assembly of an aircraft in a weight-on-wheels state is disclosed. The shock absorber includes at least one chamber containing both hydraulic fluid and a gas in fluid communication with each other. The apparatus includes a source of gas and a source of hydraulic fluid. The amount of hydraulic fluid in the chamber is corrected, preferably such that the chamber is then filled with a known amount of degassed hydraulic fluid. A pre-set mass of gas is then delivered into the chamber under the control of a gas delivery system of the portable apparatus. More accurate servicing of a shock absorber may thus be provided since account is additionally taken of gas dissolved in hydraulic fluid. By delivering a pre-set mass of gas into the chamber, there is no need to rely on a measure of gas pressure or H-dimension (h) when servicing the shock absorber.

First claim

The invention claimed is:

1. A method of servicing a shock absorber on a landing gear assembly of an aircraft, the shock absorber comprising at least one chamber containing both hydraulic fluid and a gas in fluid communication with each other, wherein the method comprises the following steps all conducted whilst the weight of the aircraft is at least partially supported by the landing gear assembly:
exhausting all gas from the chamber;
degassing at least some dissolved gas from the hydraulic fluid;
ensuring that one or more set criteria, which depend on the amount of hydraulic fluid in the chamber are met;
adjusting the amount of hydraulic fluid in the chamber; and,
delivering a pre-set mass of gas into the chamber.

2. A method according to claim 1 , wherein during the step of exhausting all gas from the chamber, the volume of the chamber reduces so that the shock absorber contracts, and the method further includes a step of arranging a stop to resist further contraction of the shock absorber.

3. A method according to claim 1 , wherein before the step of exhausting all gas from the chamber is completed, arranging a collar around the landing gear assembly, the collar bearing at least some of the load that would otherwise be sustained by the shock absorber.

4. A method according to claim 1 , wherein the step of degassing at least some dissolved gas from the hydraulic fluid includes a step of actively lowering the pressure within the chamber.

5. A method according to claim 1 , wherein the step of delivering a pre-set mass of gas into the chamber includes delivering the pre-set mass via a regulator that is configured to measure or regulate the rate of injection of mass of gas per unit time.

6. A method according to claim 1 , further comprising providing a control unit which is configured to control processes effected by the method including one or more of the step of exhausting gas from the chamber, the step of degassing dissolved gas from the hydraulic fluid, the step of ensuring that said set criteria are met, and the step of delivering a pre-set mass of gas into the chamber.

7. A method according to claim 1 , further comprising providing a control unit and wherein during at least one of the steps of the method the control unit monitors inputs including inputs concerning both temperature and pressure from sensors for conditions suggestive of a fault.

8. A method of servicing a shock absorber on a landing gear assembly of an aircraft whilst the weight of the aircraft is at least partially supported by the landing gear assembly, wherein the shock absorber comprises at least one chamber containing both hydraulic fluid and a gas in fluid communication with each other, comprising:
exhausting all gas from the at least one chamber;
degassing at least some dissolved gas from the hydraulic fluid;
ensuring that one or more set criteria, which depend on the amount of hydraulic fluid in the chamber are met;
adjusting the amount of hydraulic fluid in the chamber;
providing a gas delivery system; and,
delivering a pre-set mass of gas into the chamber with the gas delivery system.

9. A method according to claim 8 , further comprising:
providing a vacuum pump; and,
exhausting gas from the at least one chamber using the vacuum pump.

10. A method according to claim 9 , further comprising:
providing a fluid trap; and,
collecting hydraulic fluid that may flow out of the at least one chamber as the gas is exhausted using the fluid trap.

11. A method according to claim 8 , further comprising:
providing a pump; and,
delivering hydraulic fluid to the shock absorber from the reservoir using the pump.

12. A method according to claim 3 , wherein the collar stops contraction by sustaining compressive loads of the same magnitude as those sustained by the shock absorber in a weight-on-wheels state.

13. A method according to claim 8 , further comprising:
providing a regulator; and,
configuring the regulator to measure or regulate the rate of injection of mass of gas per unit time.

14. A method according to claim 8 , further comprising a source of hydraulic fluid, and adding hydraulic fluid to the chamber from the source of hydraulic fluid.

Assignees

• Airbus Operations Ltd

Inventors

• Pountney Oliver
• Shepherd Alan

Classifications

• B64F5/00 Primary

  Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for · CPC title

• B64D45/0005

  Devices specially adapted to indicate the position of a movable element of the aircraft, e.g. landing gear · CPC title

• B64F5/60

  Testing or inspecting aircraft components or systems · CPC title

• B64F5/40 Primary

  Maintaining or repairing aircraft · CPC title

• F16F9/3264

  Arrangements for indicating, e.g. fluid level; Arrangements for checking dampers (F16F9/3292 takes precedence; testing of vehicle damping G01M17/04) · CPC title