Aircraft steering

Patent metadata

Field	Value
Publication number	US-10569864-B2
Application number	US-201816017018-A
Country	US
Kind code	B2
Filing date	Jun 25, 2018
Priority date	Jun 27, 2017
Publication date	Feb 25, 2020
Grant date	Feb 25, 2020

Abstract

A control apparatus 300 for controlling a steering system 301 of an aircraft landing gear, the aircraft landing gear being configurable in a stowed configuration and a deployed configuration. The steering system 301 includes a wheel arrangement 202 including one or more wheels. The control apparatus 300 is arranged to perform a control process which includes: receiving one or more signals from one or more sensors 302a, 302b indicating a position of the wheel arrangement 202 when the landing gear is in the stowed configuration; determining whether a predetermined condition is satisfied in relation to the position of the wheel arrangement 202; and, in response to determining that the predetermined condition is satisfied, performing an adjustment process to control the steering system 301 to adjust the position of the wheel arrangement 202.

First claim

The invention claimed is:

1. A control apparatus for controlling a steering system of an aircraft landing gear, the aircraft landing gear being configurable in a stowed configuration in which the aircraft landing gear is stowed in a landing gear bay of the aircraft, and a deployed configuration, in which the landing gear is deployed outside of the landing gear bay, the steering system comprising a wheel arrangement including one or more wheels, wherein the control apparatus is arranged to perform a control process comprising:
receiving one or more signals from one or more sensors indicating a position of the wheel arrangement while the landing gear is in the stowed configuration;
determining whether a predetermined condition is satisfied in relation to the position of the wheel arrangement, while the landing gear is in the stowed configuration; and
in response to determining that the predetermined condition is satisfied, performing an adjustment process to control the steering system to adjust the position of the wheel arrangement, while the landing gear is in the stowed configuration.

2. The control apparatus according to claim 1 , wherein the predetermined condition is that the position of the one or more wheels is greater than a threshold value away from a center position of the wheel arrangement.

3. The control apparatus according to claim 1 , wherein the adjustment process incudes moving the position of the wheel arrangement towards a center position.

4. The control apparatus according to claim 1 , wherein the control apparatus performs the control process in response to a command to deploy the landing gear from the stowed configuration to the deployed configuration.

5. The control apparatus according to claim 1 , wherein the control apparatus performs the control process continuously or intermittently during a flight period of the aircraft, during which flight period the aircraft landing gear is in the stowed configuration.

6. The control apparatus according to claim 5 , wherein the control process comprises activating the steering system in response to determining that the predetermined condition is satisfied.

7. The control apparatus according to claim 5 , wherein the control process comprises maintaining activation of the steering system during substantially the whole of the flight period.

8. An aircraft landing gear control system comprising:
a control apparatus according to claim 1 , and
the steering system being a hydraulic steering system comprising hydraulic actuators to rotate the one or more wheels.

9. The aircraft landing gear control system according to claim 8 , wherein the hydraulic steering system does not include a mechanically activated valve to isolate the hydraulic actuators from a source of hydraulic pressure to the hydraulic actuators.

10. The aircraft landing gear control system according to claim 8 , comprising the one or more sensors, wherein each of the one or more sensors comprises a variable differential transducer.

11. A method for controlling a steering system of an aircraft landing gear, the aircraft landing gear being configurable in a stowed configuration in which the aircraft landing gear is stowed into a landing gear bay of the aircraft, and a deployed configuration, in which the landing gear is deployed outside of the landing gear bay, the steering system comprising a wheel arrangement including one or more wheels, wherein the method comprises:
receiving one or more signals from one or more sensors indicating a position of the wheel arrangement;
determining whether a predetermined condition is satisfied in relation to the position of the wheel arrangement, while the landing gear is in the stowed configuration; and
in response to determining that the predetermined condition is satisfied, performing an adjustment process to control the steering system to adjust the position of the wheel arrangement, while the landing gear is in the stowed configuration.

12. The method according to claim 11 , wherein the predetermined condition is that the position of the one or more wheels is greater than a threshold value away from a center position of the wheel arrangement.

13. The method according to claim 11 , wherein the adjustment process is to move the position of the wheel arrangement towards a center position.

14. The method according to claim 11 , comprising performing the control process in response to a command to deploy the landing gear from the stowed configuration to the deployed configuration.

15. The method according to claim 11 , comprising performing the control process continuously or intermittently during a flight period of the aircraft, during which flight period the aircraft landing gear is in the stowed configuration.

16. The method according to claim 15 , wherein the control process includes activating the steering system in response to determining that the predetermined condition is satisfied.

17. The method according to claim 15 , comprising activating the steering apparatus during substantially the whole of the flight period.

18. An apparatus for maintaining a center position of a steering system of an aircraft landing gear, the apparatus being configured to:
receive one or more signals from one or more sensors indicating whether the steering system is in the center position while the landing gear is retracted in a landing gear bay of the aircraft; and
in response to the one or more signals indicating that the wheel arrangement is not in the center position, control the steering system to re-center the steering system, while the landing gear is retracted in the landing gear bay.

Assignees

• Airbus Operations Ltd

Inventors

• Tangye Robert
• Garaygay Cecile Lea Lourdes
• Crane Nicholas

Classifications

• B64C25/26

  Control or locking systems therefor · CPC title

• B64C25/14

  fore-and-aft · CPC title

• B64C25/50 Primary

  Steerable undercarriages; Shimmy-damping · CPC title

• B64C25/34

  wheeled type, e.g. multi-wheeled bogies · CPC title

• B64C25/10

  retractable, foldable, or the like · CPC title