Landing gear controller

Patent metadata

Field	Value
Publication number	US-11345464-B2
Application number	US-201816009470-A
Country	US
Kind code	B2
Filing date	Jun 15, 2018
Priority date	Jun 16, 2017
Publication date	May 31, 2022
Grant date	May 31, 2022

Abstract

A landing gear controller (120) to control extension and retraction of a landing gear for an aircraft, the landing gear controller (120) configured to cause, during an aircraft take-off or landing procedure, a landing gear extension and retraction system (110) to perform only a first portion of a landing gear extension or retraction process, on the basis of a status of the aircraft and prior to receiving a command for the landing gear to be extended or retracted.

First claim

The invention claimed is:

1. A landing gear controller configured to control retraction of a landing gear of an aircraft, the landing gear controller configured to cause, during an aircraft take-off procedure, a landing gear retraction system to perform only a first portion of a landing gear retraction process, on the basis of a detection that the aircraft lifted off the ground and prior to receiving a command for the landing gear to be retracted,
wherein the landing gear controller is configured to cause the landing gear retraction system to perform the first portion of the landing gear retraction process immediately after the detection of the aircraft lifting off the ground.

2. The landing gear controller according to claim 1 , configured, on the basis of the command, to cause the landing gear retraction system to perform a second portion of the landing gear retraction process.

3. The landing gear controller according to claim 2 , configured to cause a landing gear bay door to move from a closed position towards an open position during the second portion of the landing gear retraction process, wherein the landing gear bay door is associated with a landing gear to which the landing gear retraction system is operatively connected.

4. The landing gear controller according to claim 1 , wherein the first portion of the landing gear retraction process comprises one or more functions involving avionics.

5. The landing gear controller according to claim 1 , wherein the detection of the aircraft lifting off the ground is based on one or more of:
ground speed, amount of lift, aircraft angle, absolute altitude, true altitude, landing gear strut length, and aircraft rotation.

6. The landing gear controller according to claim 1 , wherein the detection of lifting off the ground is based on a detection that a length of a landing gear strut has increased, during the aircraft take-off procedure, to above a predetermined threshold length, the landing gear strut being a strut of a landing gear to which the landing gear retraction system is operatively connected.

7. An aircraft landing gear system, comprising:
a landing gear retraction system; and
the landing gear controller according to claim 1 , wherein the landing gear controller is operatively connected to the landing gear retraction system.

8. The aircraft landing gear system according to claim 7 , comprising:
a landing gear bay door;
a landing gear bay door lock to retain the landing gear bay door in a closed position when locked; and
a landing gear bay door actuator to move the landing gear bay door between the closed position and an open position relative to a door frame;
wherein the first portion of the landing gear retraction process comprises the landing gear retraction system causing:
actuation of the landing gear bay door actuator to positively hold the landing gear bay door in a closed position; and
unlocking of the landing gear bay door lock to permit movement of the landing gear bay door to the open position.

9. The aircraft landing gear system according to claim 7 , comprising an isolator configured to isolate the landing gear retraction system from a power supply.

10. The aircraft landing gear system according to claim 9 , wherein the first portion of the landing gear retraction process includes actuation of the isolator to apply power from the power supply to the landing retraction system.

11. The landing gear controller according to claim 1 , configured to cause, as at least part of the first portion and during the aircraft take-off procedure and prior to receiving the command, operation of an isolator to supply power to the landing gear retraction system.

12. A method to retract a landing gear of an aircraft during an aircraft take-off procedure, the method comprising:
detecting a transition to an in-flight status of the aircraft, and
performing only a first portion of a process for retracting the landing gear immediately after the detection of the transition to the in-flight status; and
then receiving a command for the landing gear to be retracted by a landing gear retraction system configured to extend and retract the landing gear.

13. The method according to claim 12 , comprising maintaining a closed state of a landing gear bay door until after the receiving of the command, wherein the landing gear bay door is a door of a landing gear bay for accommodating the landing gear.

14. The method according to claim 12 , wherein the first portion of the process for retracting the landing gear involves the use of avionics of the aircraft.

15. The method of claim 12 , wherein the performing of the first portion includes causing operation of an isolator to supply power to the landing gear retraction system, wherein the landing gear retraction system lacked power before the operation of the isolator.

16. A method to retract a landing gear of an aircraft comprising:
automatically detecting an extension of a strut of a landing gear or rotation of the aircraft during take-off;
automatically detecting a transition of the aircraft to an in-flight condition based on the detection of the extension of the strut;
responding immediately to the determination of the transition to the in-flight condition by automatically unlocking a door lock which locks a landing gear bay door associated with the landing gear in a closed position; and
after the automatically unlocking of the door lock, receiving a command to retract the landing gear wherein the command is initiated manually.

17. The method of claim 16 , wherein the responding immediately to the determination of the transition to the in-flight condition includes operating an isolator to cause power to be supplied for retracting the landing gear; and
the method further comprises receiving the command to retract the landing gear after the isolator supplies the power; and
in response to the command, retracting the landing gear using the power supplied by the isolator.

18. The method of claim 17 , wherein the causing operation of the isolator in response to the detected extension or rotation further includes automatically opening a valve in a hydraulic system of the aircraft to pressurize hydraulic fluid in the landing gear.

Assignees

• Airbus Operations Ltd

Inventors

• Marles David

Classifications

• B64C25/26 Primary

  Control or locking systems therefor · CPC title

• B64C25/16

  Fairings movable in conjunction with undercarriage elements · CPC title

• B64C25/24

  electric · CPC title

• B64C25/22

  fluid · CPC title

• B64C25/18

  Operating mechanisms · CPC title