Controller for an aircraft system

Patent metadata

Field	Value
Publication number	US-12503221-B2
Application number	US-202217679685-A
Country	US
Kind code	B2
Filing date	Feb 24, 2022
Priority date	Feb 26, 2021
Publication date	Dec 23, 2025
Grant date	Dec 23, 2025

Abstract

A controller for an aircraft system of an aircraft, the aircraft system including a first actuator and a first energy supply. The controller is configured to, when the aircraft system is configured in a first configuration, in which the first actuator is coupled to the first energy supply, determine that there is a loss of energy supplied to the first actuator from the first energy supply. The controller is configured to determine a change in performance achievable by reconfiguring the aircraft system from the first configuration to an alternative configuration, in which the first actuator is uncoupled from the first energy supply, and cause reconfiguration of the aircraft system from the first configuration to the alternative configuration, in the event that the change in performance determined by the controller is a gain in performance.

First claim

The invention claimed is:

1 . A controller for an aircraft system of an aircraft, the aircraft system comprising an actuation system and a first energy supply which provides power to the actuation system, wherein the actuation system includes a first actuator and the controller is configured to:
when the aircraft system is configured in a first configuration in which the first actuator is coupled to the first energy supply, determine that there is a loss of energy supplied to the first actuator from the first energy supply; determine a current performance of the actuation system achievable when the aircraft system is configured in the first configuration, wherein the determination of the current performance is in response to the determination of the loss of the energy supplied to the first actuator; determine, while the aircraft system is in the first configuration, a predicted performance of the actuation system achievable by the aircraft system if configured in an alternative configuration in which the first actuator is uncoupled from the first energy supply; compare, while the aircraft system is in the first configuration, the current performance to the predicted performance; determine, based on the comparison of the current performance to the predicted performance, a change in performance of the actuation system achievable by reconfiguring the aircraft system from the first configuration to the alternative configuration, and cause reconfiguration of the aircraft system from the first configuration to the alternative configuration, when the change in performance determined by the controller is a gain in performance.

2 . The controller of claim 1 , wherein the aircraft system comprises a second energy supply, and wherein the alternative configuration is either:
a first alternative configuration, in which the first actuator is coupled to the second energy supply; or a second alternative configuration, in which the first actuator is isolated from the first energy supply and the second energy supply.

3 . The controller of claim 2 , wherein the actuation system further comprises a second actuator different from the first actuator,
wherein in the first configuration, the second actuator is coupled to the first energy supply, wherein in the first alternative configuration, the second actuator is coupled to the first energy supply, and wherein in the second alternative configuration, the second actuator is coupled to the second energy supply.

4 . The controller of claim 3 , configured to determine the change in performance of the actuation system based on a change in performance associated with the first and second actuators achievable by reconfiguring the aircraft system from the first configuration to the first alternative configuration or the second alternative configuration.

5 . The controller of claim 2 , wherein the actuation system further comprises a second actuator different from the first actuator,
wherein, in the first configuration, the second actuator is coupled to the second energy supply, wherein in the first alternative configuration, the second actuator is coupled to the first energy supply, and wherein, in the second alternative configuration, the second actuator is coupled to the second energy supply.

6 . The controller of claim 5 , configured to determine the change in performance of the actuation system based on a change in performance associated with the first and second actuators achievable by reconfiguring the aircraft system from the first configuration to the first alternative configuration or the second alternative configuration.

7 . The controller of claim 2 , wherein the aircraft system comprises a third energy supply, and wherein the first actuator is coupled to the third energy supply in the second alternative configuration.

8 . The controller of claim 1 , wherein the actuation system is a brake actuation system and the first actuator is a first brake actuator configured to brake a first wheel of the aircraft, and wherein the controller is configured to:
determine a first parameter representative of a maximum reactive force able to be achieved between the first wheel and the ground; and determine the predicted performance of the brake actuation system based on the first parameter.

9 . The controller of claim 8 , wherein the brake actuation system further comprises a second actuator, wherein the second actuator is a second brake actuator configured to brake a second wheel of the aircraft, and wherein the controller is configured to:
determine a second parameter representative of a maximum reactive force able to be achieved between the second wheel and the ground; determine a second braking parameter representative of a maximum braking force able to be applied by the second brake actuator in the alternative configuration; and determine the predicted performance of the brake actuation system based on the first and second parameters and the first and second braking parameters.

10 . The controller of claim 9 , configured to determine the first and second parameters based on one or a combination of: a measured performance of the respective first and second brake actuators; an environmental condition; and a status of the aircraft.

11 . The controller of claim 10 , wherein the measured performance of each of the first and second brake actuators comprises one or more of: a measured slip between the respective first and second wheel and the ground; a measured energy supplied to the respective first and second brake actuator; and a measured braking torque, or braking force, applied by the respective first and second brake actuator to the respective first and second wheel.

12 . The controller of claim 1 , wherein the actuation system is a brake actuation system and the first actuator is a first brake actuator configured to brake a first wheel of the aircraft, and wherein the controller is configured to:
determine a first braking parameter representative of a maximum braking force able to be applied by the first brake actuator in the alternative configuration; and determine the predicted performance of the brake actuation system based on the first braking parameter.

13 . The controller of claim 1 , configured to:
determine a reconfiguration parameter representative of a loss in performance of the actuation system estimated to be incurred by an action of reconfiguring the aircraft system from the first configuration to the alternative configuration; and determine the predicted performance of the actuation system based on the reconfiguration parameter.

14 . The controller of claim 1 , wherein the predicted performance of the actuation system is included in a plurality of predicted performances of the actuation system and the alternative configuration is included in a plurality of alternative configurations, and the controller is further configured to:
determine a respective one of the predicted performances for each of the plurality of alternative configurations; if at least one of the predicted performances is a gain in performance over the current performance, select one of the alternative configurations which would result in a gain in performance; and cause reconfiguration of the aircraft system from the first configuration to the alternative configuration selected by the controller.

15 . A method of operating a controller of an aircraft system of an aircraft, the aircraft system comprising an actuation system and a first energy supply which supplies power to the actuation system, wherein the actuation system includes a first actuator and the m

Assignees

• Airbus Operations Ltd

Inventors

• Howell George

Classifications

• B60T2270/414

  Power supply failure · CPC title

• B60T2270/402

  Back-up · CPC title

• B60T2240/02

  Longitudinal grip · CPC title

• B60T17/22

  Devices for monitoring or checking brake systems; Signal devices · CPC title

• B60T8/92

  automatically taking corrective action · CPC title