Aircraft electric braking system

Patent metadata

Field	Value
Publication number	US-9611035-B2
Application number	US-201414554572-A
Country	US
Kind code	B2
Filing date	Nov 26, 2014
Priority date	Nov 27, 2013
Publication date	Apr 4, 2017
Grant date	Apr 4, 2017

Abstract

An electrically actuated braking system for an aircraft, including: an electro-mechanical brake actuator (EMAbrake) proximate a wheel of the aircraft, the EMAbrake including a motor; an electro-mechanical actuator controller (EMAC) including a first motor controller for generating a first drive signal for the EMAbrake, and a second motor controller for generating a second drive signal for the EMAbrake, wherein the first motor controller and the second motor controller are dissimilar so as to provide protection against common mode failure of the first and second motor controllers.

First claim

The invention claimed is:

1. An electrically actuated braking system for an aircraft, comprising:
an electro-mechanical brake actuator proximate a wheel of the aircraft, the electro-mechanical brake actuator including a motor;
an electro-mechanical actuator controller (EMAC) including a first motor controller for generating a first drive signal for the electro-mechanical brake actuator, and a second motor controller for generating a second drive signal for the electro-mechanical brake actuator,
wherein the first motor controller and the second motor controller are dissimilar so as to provide protection against common mode failure of the first and second motor controllers.

2. An electrically actuated braking system according to claim 1 , further comprising a braking control unit (BCU) for generating a braking force command signal for the EMAC during a normal operating mode, and an emergency braking control unit (eBCU) for generating a braking force command signal for the EMAC during an emergency mode of operation.

3. An electrically actuated braking system according to claim 2 , wherein the BCU is operable on a normal brake channel, the eBCU is operable on an emergency brake channel, the first motor controller is operable on a normal motor control channel, and the second motor controller is operable on an emergency motor control channel.

4. An electrically actuated braking system according to claim 3 , wherein the BCU is configured to communicate with either the first motor controller or the second motor controller, and the eBCU is configured to communicate with either the first motor controller or the second motor controller.

5. An electrically actuated braking system according to claim 4 , further comprising a first switch for switching between the normal and emergency brake channels, and a second switch for switching between the normal and emergency motor control channels.

6. An electrically actuated braking system according to claim 5 , wherein the first switch and the second switch are independently switchable.

7. An electrically actuated braking system according to claim 3 , wherein the BCU is configured to communicate with the first motor controller and not the second motor controller, and the eBCU is configured to communicate with the second motor controller and not the first motor controller.

8. An electrically actuated braking system according to claim 7 , wherein the normal brake channel and the normal motor control channel are coupled so as to form a normal channel, and the emergency brake channel and the emergency motor control channel are coupled so as to form an emergency channel, and the system further comprises a switch for switching between the normal channel and the and emergency channel.

9. An electrically actuated braking system according to claim 3 , further comprising a source switch operatively coupled between the normal and emergency motor control channels and the electro-mechanical brake actuator for switching the electro-mechanical brake actuator control depending on the selected motor control channel.

10. An electrically actuated braking system according to claim 3 , further comprising an OR gate operatively coupled between the normal and emergency motor control channels and the electro-mechanical brake actuator for controlling the electro-mechanical brake actuator depending on the operative motor control channel.

11. An electrically actuated braking system according to claim 3 , wherein the BCU includes redundant brake control channels each for communicating with aircraft cockpit controls and avionics via a respective data bus.

12. An electrically actuated braking system according to claim 2 , wherein the BCU and/or the eBCU are disposed remote from the EMAC.

13. An electrically actuated braking system according to claim 12 , wherein the BCU, and optionally also the eBCU, is disposed in a remote data concentrator (RDC) configured for mounting in a wheel or axle region of landing gear of the aircraft.

14. An electrically actuated braking system according to claim 2 , wherein the BCU and/or the eBCU are disposed together with the EMAC in a common line replaceable unit (LRU).

15. An electrically actuated braking system according to claim 2 , wherein the BCU is operable to perform anti-skid brake control.

16. An electrically actuated braking system according to claim 2 , wherein the eBCU is operable to perform anti-skid brake control.

17. An electrically actuated braking system according to claim 1 , wherein the first motor controller and the second motor controller each comprise hardware for generating a pulse-width modulation signal.

18. An electrically actuated braking system according to claim 1 , wherein the first motor controller and the second motor controller each comprise a different hardware selected from the group comprising: a microprocessor, a microcontroller, a digital signal processor, an application specific integrated circuit, a programmable logic device, a complex programmable logic device, a field programmable gate array, and a transistor based discrete electronics switching circuit.

19. An electrically actuated braking system according to claim 1 , wherein the EMAC is disposed remote from the electro-mechanical brake actuator.

20. An electrically actuated braking system according to claim 1 , wherein the EMAC is disposed together with the electro-mechanical brake actuator in a common line replaceable unit (LRU).

21. An aircraft including an electrically actuated braking system according to claim 1 .

22. An electrically actuated braking system for an aircraft comprising:
an electro-mechanical brake actuator proximate a wheel of the aircraft, the electro-mechanical brake actuator including a motor;
an electro-mechanical actuator controller (EMAC) including a first motor controller configured to generate a first drive signal for the motor of the electro-mechanical brake actuator, and a second motor controller configured to generate a second drive signal for motor of the electro-mechanical brake actuator, wherein the first motor controller includes electronic hardware configured to generate the first drive signal, which is dissimilar to electronic hardware included in the second motor controller configured to generate the second drive signal, wherein the motor in the electro-mechanical brake actuator is configured to be actuated by the first and second drive signals.

23. The electrically actuated braking system of claim 22 wherein the electronic hardware in the first controller is one of a group consisting of a microprocessor, a microcontroller, a digital signal processor, an application specific integrated circuit, a programmable logic device, a complex programmable logic device, a field programmable gate array, and a transistor based discrete electronics switching circuit, and the electronic hardware in the second controller is another one of the group.

Assignees

• Airbus Operations Ltd

Inventors

• Iordanidis George
• Rees John

Classifications

• B60T13/741

  acting on an ultimate actuator · CPC title

• F16D65/14

  Actuating mechanisms for brakes; Means for initiating operation at a predetermined position (brake control systems, parts thereof B60T) · CPC title

• B64C25/44 Primary

  Actuating mechanisms · CPC title

• B60T8/885

  using electrical circuitry · CPC title

• B60T8/1703 Primary

  for aircrafts · CPC title