Aircraft control system

Patent metadata

Field	Value
Publication number	US-12319404-B2
Application number	US-202318100316-A
Country	US
Kind code	B2
Filing date	Jan 23, 2023
Priority date	Jan 24, 2022
Publication date	Jun 3, 2025
Grant date	Jun 3, 2025

Abstract

An aircraft control system 100 including a control assembly 110 having control units, including a first control unit 130 for controlling actuation of the aircraft component during a first time period, using electrical resource 512 from a first electrical resource device 510 , and a second control unit 140 for controlling actuation of the aircraft component during a second time period, and a switch mechanism 120 for switching control of the actuation of the aircraft component between the first and second control units, wherein the switch mechanism has a first electrical resource device status input 513 for indicating the status of the first electrical resource device 510 and wherein, the switch mechanism is configured to switch control between the first 130 and second 140 control units based on the first electrical resource device status input 513.

First claim

The invention claimed is:

1. An aircraft control system for controlling actuation of an aircraft component, the system comprising a control assembly including:
a first control unit configured to control actuation of the aircraft component during a first time period using an electrical resource from a first electrical resource device,
a second control unit configured to control actuation of the aircraft component during a second time period separate from the first time period, and
a switch mechanism configured to switch control of the actuation of the aircraft component between the first control unit and the second control unit,
wherein the switch mechanism has a first electrical resource device status input configured to indicate a status of the first electrical resource device, and
wherein the switch mechanism is configured to switch control, based on the first electrical resource device status input, from the first control unit to the second control unit during the first time period or from the second control unit to the first control unit during the second time period.

2. The aircraft control system as claimed in claim 1 , wherein the first control system is configured to control actuation of at least one of: a landing gear system, a braking system, or a steering system.

3. The aircraft control system as claimed in claim 1 , wherein the second control unit controls actuation of the aircraft component using an electrical resource from a second electrical resource device,
wherein the switch mechanism includes a second electrical resource device status input configured to indicate a status of the second electrical resource device, and
wherein the switch mechanism is configured to switch control between the first control unit and the second control unit based on the second electrical resource device status input.

4. The aircraft control system as claimed in claim 1 , wherein the first control unit is configured to control actuation of the aircraft component using a direct electrical resource from the first electrical resource device.

5. The aircraft control system as claimed in claim 1 , wherein the first control unit is configured to control actuation of the aircraft component using an indirect electrical resource from the first electrical resource device.

6. The aircraft control system as claimed in claim 1 , wherein the first electrical resource device status input comprises a “fault” or a “no fault” indication.

7. The aircraft control system as claimed in claim 1 , wherein the switch mechanism is part of the first control unit.

8. The aircraft control system as claimed in claim 1 , further comprising a second switch mechanism included in the second control unit.

9. The aircraft control system as claimed in claim 1 , wherein the switch mechanism is configured to switch control between the first control unit and the second control unit periodically due to repeating of the first time period and the second time period.

10. An aircraft or aircraft assembly comprising the aircraft control system of claim 1 .

11. The aircraft or aircraft assembly as claimed in claim 10 , wherein the aircraft or the aircraft assembly further comprises the aircraft component and the first electrical resource device.

12. The aircraft or aircraft assembly as claimed in claim 11 , wherein the aircraft or the aircraft assembly further comprises the second electrical resource device.

13. A method of controlling an aircraft component of an aircraft, the method comprising:
monitoring a status of a first electrical resource device,
a first control unit controlling actuation of the aircraft component during a first time period, wherein the first control unit uses an electrical resource from the first electrical resource device to actuate the aircraft component,
a second control unit controlling actuation of the aircraft component during a second time period separate from the first time period, and
based upon a status of the first electrical resource device, switching control of the actuation of the aircraft component from the first control unit to a second control unit during the first time period or switching control of the aircraft component from the second control unit to the first control unit during the second time period.

14. The method as claimed in claim 13 , further comprising the second control unit controlling actuation of the aircraft component using an electrical resource from a second electrical resource device.

15. The method as claimed in claim 13 , wherein the status of the first electrical resource device comprises a fault indication or a no-fault indication.

16. The method as claimed in claim 15 , wherein the fault indication is provided prior to the electrical resource from the first electrical resource device becoming unavailable.

17. The method as claimed in claim 13 , wherein the method includes switching control between the first control unit and the second control unit periodically due to repeating of first period and the second period.

18. The method as in claim 13 , wherein the first electrical resource device is a first aircraft engine, and the aircraft component is at least one of a landing gear bay door, landing gear extension and retraction mechanism, a wheel braking system or a wheel steering system.

19. A landing gear control system for controlling actuation of a landing gear system of an aircraft, the landing gear control system comprising a control assembly including:
a first control unit configured to control actuation of a landing gear component of the landing gear during a first period, wherein the first control unit directs electrical energy generated by a first aircraft engine to the landing gear component,
a second control unit configured to control actuation of the landing gear component during a second period separate from the first period, wherein the second control unit directs electrical energy generated by a second aircraft engine to the landing gear component,
a switch mechanism configured to switch authority for controlling the landing gear component from the first control unit to the second control unit upon expiration of the first period and from the second control unit to the first control unit upon expiration of the second period, wherein the first and second periods are sequential and repeat,
wherein the switch mechanism has an aircraft engine status input configured to indicate a status of at least the first aircraft engine, and
wherein the switch mechanism is configured to switch the authority between the first and second control units in response to a change in the status of the at least first aircraft engine and regardless of whether the switching done in the first period or the second period.

Assignees

• Airbus Operations Ltd

Inventors

• Izquierdo Civera Fernando
• Piddock Alex Robert
• Johnson Mark

Classifications

• B64C13/16

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

• B64D2221/00

  Electric power distribution systems onboard aircraft · CPC title

• B64C25/50

  Steerable undercarriages; Shimmy-damping · CPC title

• B64C25/42

  Arrangement or adaptation of brakes · CPC title

• B64C25/26 Primary

  Control or locking systems therefor · CPC title