Landing gear system operation

Patent metadata

Field	Value
Publication number	US-11299261-B2
Application number	US-202016799896-A
Country	US
Kind code	B2
Filing date	Feb 25, 2020
Priority date	Feb 28, 2019
Publication date	Apr 12, 2022
Grant date	Apr 12, 2022

Abstract

An aircraft landing gear control system 1000 configured to be operably connected to one or more landing gear systems 30, 40 of an aircraft. The aircraft landing gear control system includes a controller 20 configured to: send at least one output for initiating operation of the one or more landing gear systems; determine whether at least one landing gear system of the one or more landing gear systems has failed to operate correctly in response to the at least one output; and determine at least one remedial action to be taken, when the controller determines that the at least one landing gear system has failed to operate correctly.

First claim

The invention claimed is:

1. An aircraft landing gear control system configured to be operably connected to one or more landing gear systems of an aircraft, the aircraft landing gear control system comprising a controller that is configured to:
send at least one output for initiating operation of the one or more landing gear systems;
determine whether at least one landing gear system of the one or more landing gear systems has failed to operate correctly in response to the at least one output; and
determine at least one remedial action to be taken when the controller determines that the at least one landing gear system has failed to operate correctly;
determine one or more reasons for the at least one landing gear system to have failed to operate correctly; and
determine the at least one remedial action to be taken, on the basis of the one or more reasons.

2. The aircraft landing gear control system according to claim 1 , wherein the controller is configured to:
determine the one or more reasons by a process comprising interrogating avionics of the aircraft.

3. The aircraft landing gear control system according to claim 1 , wherein the controller is configured to:
determine the one or more reasons by a process comprising interrogating one or more sensors of the aircraft.

4. The aircraft landing gear control system according to claim 1 , wherein the controller is configured to:
cause identification of the at least one remedial action to be output at a cockpit of the aircraft.

5. The aircraft landing gear control system according to claim 1 , wherein the controller is configured to:
cause initiation of the at least one remedial action.

6. The aircraft landing gear control system according to claim 1 , wherein the controller is configured to:
cause initiation of the at least one remedial action automatically, on the basis of the determination of the at least one remedial action to be taken.

7. The aircraft landing gear control system according to claim 1 , and further comprising:
a user interface operable by a user to manually input a request to perform the at least one remedial action;
wherein the controller is communicatively coupled to the user interface and is configured to:
receive, from the user interface, a signal indicative of user-operation of the user interface to input the request to perform the at least one remedial action; and
cause initiation of the at least remedial action, on the basis of the signal.

8. The aircraft landing gear control system according to claim 1 , wherein the at least one remedial action to be taken comprises one or more of:
determining a flight plan;
executing an aircraft manoeuvre;
reattempting operation of the at least one landing gear system; and
taking one or more actions to counteract asymmetry or pitching of the aircraft.

9. The aircraft landing gear control system of claim 1 , wherein the controller determines the one or more reasons by selecting the one or more reasons from a plurality of reasons stored in memory accessible by the controller, and
wherein the controller determines the one or more remedial actions by selecting the one or more remedial actions from a plurality of remedial actions stored in the memory accessible by the controller.

10. The aircraft landing gear control system of claim 9 , wherein, the plurality of reasons stored in the memory include a plurality of: (i) an unexpected position of a landing gear, a landing gear bay door lock, a lock and/or an actuator, (ii) a fluid pressure and/or fluid flow rate of hydraulics in the one or more landing gear systems being above or below a predetermined fluid value; (iii) electrical current drawn by the one or more landing gear systems exceeding a predetermined current value; and (iv) a failure in a sensor for the one or more landing gear systems.

11. The aircraft landing gear control system of claim 9 , wherein the plurality of remedial actions includes a plurality of: (i) recycling the one or more landing gear systems; (ii) using alterative avionics and/or mechanical systems of the one or more landing gear systems; (iii) deploying the one or more landing gear systems using gravity alone; (iv) executing a high-G aircraft manoeuver; (v) changing a flight plan of the aircraft, and (vi) deploying the one or more landing gear systems to achieve a symmetry of the landing gear systems.

12. An aircraft landing gear control system configured to be operably connected to one or more landing gear systems of an aircraft, the aircraft landing gear control system comprising a controller that is configured to:
send at least one output for initiating operation of the one or more landing gear systems;
determine whether at least one landing gear system of the one or more landing gear systems has failed to operate correctly in response to the at least one output;
determine at least one remedial action to be taken when the controller determines that the at least one landing gear system has failed to operate correctly;
send the at least one output for initiating operation of the one or more landing gear systems according to a first procedure; and
determine at least one remedial action to be taken that comprises sending at least one output for initiating operation of the at least one landing gear system according to a second procedure different to the first procedure.

13. The aircraft landing gear control system according to claim 12 , wherein the second procedure comprises one or more of:
operating at least a portion of the at least one landing gear system under the influence of gravity alone;
operating the at least one landing gear system using avionics that are different to avionics used to operate the at least one landing gear system according to the first procedure; and
actuating the at least one landing gear system using mechanics that are different to mechanics used to actuate the at least one landing gear system according to the first procedure.

14. A method of controlling one or more landing gear systems of an aircraft using a controller of the aircraft, the method comprising:
the controller issuing at least one output for causing operation of the one or more landing gear systems;
the controller determining whether at least one of the one or more landing gear systems has failed to operate correctly in response to the at least one output; and
the controller determining at least one remedial action to be taken, when the controller determines that the at least one landing gear system has failed to operate correctly in response to the at least one output;
the controller determining one or more reasons for the at least one landing gear system to have failed to have operated correctly; and
the controller determining the at least one remedial action to be taken on the basis of the one or more reasons.

15. The method according to claim 14 , further comprising:
the controller receiving signals from one or more sensors of the aircraft; and
the controller determining that the at least one landing gear system has failed to operate correctly on the basis of the one or more signals.

16. The method according to claim 14 , further comprising:
the controller determining a period of time that has elapsed, since the controller issued the at least one output, without the controller receiving an indication that the at least one landing gear system has operated correctly; and
the controller determining that the at least one landing gear system has failed to operate correctly on the basis of the period of time determined.

17. The method according to claim 14

Assignees

• Airbus Operations Ltd

Inventors

• Kerr Sean
• Marles David

Classifications

• B64C25/28

  with indicating or warning devices · CPC title

• B64C25/30 Primary

  emergency actuated · CPC title

• B64C25/26 Primary

  Control or locking systems therefor · CPC title

• B64D45/04

  Landing aids; Safety measures to prevent collision with earth's surface · CPC title

• B64C13/16

  actuated automatically, e.g. responsive to gust detectors · CPC title