Hydraulic actuator and accumulator arrangement

Patent metadata

Field	Value
Publication number	US-10919642-B2
Application number	US-201815888120-A
Country	US
Kind code	B2
Filing date	Feb 5, 2018
Priority date	Feb 6, 2017
Publication date	Feb 16, 2021
Grant date	Feb 16, 2021

Abstract

A landing gear system for an aircraft includes a retractable landing gear assembly, a hydraulic actuator for actuating movement part, for example a bogie of the landing gear assembly, and an accumulator associated with the actuator. The accumulator comprises a volume of pressurised gas separated from hydraulic fluid by a separator piston. Travel of the separator piston beyond a certain position is indicative of a fault. The accumulator includes a snubbing device that acts to slow movement of the separator piston beyond that position. A monitoring system measures the time taken for the movement of the landing gear part effected by the hydraulic actuator. If the measured time is longer than a threshold time, that is indicative of a possible fault in the accumulator, that might, without the snubbing, remain undetected and/or hidden from view.

First claim

The invention claimed is:

1. A landing gear system for an aircraft including
a retractable landing gear assembly,
a hydraulic actuator for actuating movement of at least a part of the landing gear assembly from a first configuration to a second configuration,
an accumulator associated with the actuator, the accumulator comprising a first space for a volume of pressurised gas, and a second space for a volume of hydraulic fluid, the first and second spaces being separated by a separator piston,
and a monitoring system,
wherein
the separator piston is configured to travel to a first stroke limit position during said movement from the first configuration to the second configuration,
travel of the separator piston beyond the first stroke limit position is indicative of a fault,
the accumulator includes a snubbing device that acts to slow movement of the separator piston only once the separator piston has traveled beyond the first stroke limit position, and
the monitoring system is arranged to measure the time taken for movement of said part from the first configuration to the second configuration, and to compare the time taken with a threshold time, such that the measured time being longer than the threshold time is indicative of a possible fault.

2. A landing gear system according to claim 1 , wherein the landing gear monitoring system is configured to output an alert signal in the event that the measured time is longer than the threshold time.

3. A landing gear system according to claim 1 , wherein the hydraulic actuator is configured for moving a bogie of the landing gear assembly.

4. A landing gear system according to claim 3 , wherein the hydraulic actuator is configured to position the bogie into a bias position.

5. A landing gear system according to claim 1 , wherein the monitoring system is provided by a landing gear monitoring system which is arranged to measure the time taken for the landing gear assembly to move between a deployed configuration and a retracted configuration.

6. A landing gear system according to claim 4 , wherein the monitoring system is provided by a bogie pitch monitoring system which is arranged to measure the time taken for the bogie to be moved from a prior pre-set state to the bias position.

7. A landing gear system according to claim 1 , wherein the landing gear system includes one or more sensors that are connected to the monitoring system to enable the monitoring system to detect when the landing gear assembly has moved to the second configuration.

8. A landing gear system according to claim 7 , wherein the one or more sensors are located externally of the accumulator.

9. A method of detecting a fault in an accumulator of a landing gear system according to claim 1 , the method comprising the following steps:
measuring the time taken for the said part of the landing gear assembly to move between two positions under operation of the hydraulic system including the accumulator, and
in dependence on a comparison between that measured time and an expected time, deeming whether or not there might be a fault in the accumulator.

10. A method according to claim 9 , wherein the said part of the landing gear assembly is a bogie.

11. A method according to claim 9 , wherein the method includes successfully moving the said part from or to one of either a fully deployed position or a fully retracted position, despite a fault being present in the accumulator, and nevertheless detecting the fault by comparing the measured time and the expected time.

12. A kit of parts comprising a hydraulic actuator, a snubbed accumulator, and a monitoring system, the kit of parts being arranged so as to be suitable for use in converting an aircraft landing gear assembly into a landing gear system according to claim 1 .

13. A kit of parts comprising a hydraulic actuator, a snubbed accumulator, and a monitoring system, the kit of parts being arranged so as to be suitable either for use in performing the method of claim 9 .

14. An aircraft on which the apparatus of claim 1 has been installed.

15. A monitoring system for use as the monitoring system of claim 1 .

16. A monitoring system comprising computer hardware programmed with suitable software for performing the function of the monitoring system of claim 1 .

17. A monitoring system comprising computer hardware programmed with suitable software for performing the function of the monitoring method of claim 9 .

18. A computer program product configured to cause, when the computer program is executed, computer hardware to perform the function of the monitoring system according to claim 16 .

19. An accumulator including a snubbing device, wherein the accumulator is configured for use as the snubbed accumulator of the kit of parts of claim 12 .

20. A method of detecting a fault in an accumulator of a hydraulic system associated with a moving part of an aircraft, the accumulator being so configured that there is snubbing of movement of a part of the accumulator beyond the extreme position that accumulator part would reach during movement without such a fault, the method comprising the following steps:
moving a moving part of the aircraft from or to one of either a fully deployed position or a fully retracted position under operation of the hydraulic system including the accumulator, despite a fault being present in the accumulator,
measuring the time taken for the moving part of the aircraft to move from or to the one of either the fully deployed position or the fully retracted position, and
detecting the fault by comparing the measured time and an expected time.

Assignees

• Airbus Operations Ltd

Inventors

• Papadopoulos Christopher
• Marples Matthew
• Mounty Andy
• Fanourakis Costas
• King Graham

Classifications

• B64C13/48 Primary

  characterised by the fluid being gaseous · CPC title

• F15B15/14

  of the straight-cylinder type · CPC title

• F15B1/24

  with rigid separating means, e.g. pistons · CPC title

• F15B2201/205

  using gas · CPC title

• F15B1/08

  using a gas cushion; Gas charging devices; Indicators or floats therefor · CPC title