Electric braking system with power conservation and method of operating the same

• US 10,112,704 B2
• Filed: 02/27/2014
• Issued: 10/30/2018
• Est. Priority Date: 03/06/2013
• Status: Active Grant

• Current Assignee: Bombardier Incorporated
• Original Assignee: Bombardier Incorporated
• Inventors: Di Zazzo, Marco, Plante, Bertrand
• Primary Examiner(s): Smith, Isaac G
• Application Number:
  US14/770,183
• Publication Number:
  US 20160031553A1
• Time in Patent Office: 1,706 Days
• Field of Search: 701 3
• CPC Class Codes: B60T 2270/414 Power supply failure
• CPC Class Codes: B60T 8/1703 for aircrafts
• CPC Class Codes: B60T 8/885 using electrical circuitry
• CPC Class Codes: B64C 25/34 wheeled type, e.g. multi-wheeled bogies
• CPC Class Codes: B64C 25/44 Actuating mechanisms
• CPC Class Codes: B64D 2221/00 Electric power distribution systems onboard aircraft

Abstract

A method of operating electric brakes (30, 32, 34) on an aircraft (10) in a low power mode of operation includes determining if the aircraft is in a first configuration, if the aircraft is in the first configuration, disengaging power to the electric brakes (30, 32, 34) the from all power supplies (40, 42), determining if the aircraft (10) is in a second configuration, if the aircraft is in the second configuration, engaging power to the electric brakes (30, 32, 34) from one of the power supplies (40, 42), determining if the aircraft (10) is in a third configuration, and if the aircraft (10) is in the third configuration, engaging power to the electric brakes (30, 32, 34) from at least two of the power supplies (40, 42).

Claims

1. A method of operating electric brakes on an aircraft in a low power mode of operation, comprising:

determining if the aircraft is in a first configuration in which the aircraft is in flight, wherein the first configuration is defined at least by an airspeed above a first threshold;

if the aircraft is in the first configuration, keeping a brake controller of the electric brakes powered and disengaging power to the electric brakes from all of a plurality of power supplies;

determining if the aircraft is in a second configuration;

if the aircraft is in the second configuration, engaging power to the electric brakes from only one of the power supplies;

determining if the aircraft is in a third configuration; and

if the aircraft is in the third configuration, engaging power to the electric brakes from at least two of the power supplies.

2. The method of claim 1, wherein the power supplies each are part of electrical motor control units.

3. The method of claim 1, wherein the first configuration also is defined by at least one of status information for the aircraft, landing gear position, a landing gear handle UP condition, and a landing gear retracted condition.

4. The method of claim 1, wherein the first configuration also is defined at least by a weight off wheels configuration.

5. The method of claim 1, wherein the second configuration is defined at least by the airspeed below the first threshold and above a second threshold.

6. The method of claim 5, wherein the second configuration also is defined by at least one of a status information from the RAT/ADG systems.

7. The method of claim 5, wherein the second configuration also is defined at least by a weight off wheels configuration.

8. The method of claim 1, wherein the third configuration is defined at least by the airspeed below a second threshold.

9. The method of claim 5, wherein the third configuration also is defined by a status of the airplane on the ground (WOW).

10. The method of claim 5, wherein the third configuration also is defined by a weight off wheels configuration.

11. The method of claim 5, wherein the third configuration also is defined by a wheel speed.

12. The method of claim 5, wherein the third configuration also is defined by a weight on wheels configuration.

13. The method of claim 1, wherein the power supplies comprise a plurality of batteries.

14. The method of claim 13, wherein the power supplies further comprise an air driven generator.

15. The method of claim 13, wherein the power supplies comprise a ram air turbine.

16. An aircraft operational in a low power mode of operation, comprising:

a plurality of redundant power supplies;

a plurality of landing gears;

a plurality of electrical brakes, at least one associated with each landing gear wheel; and

a brake controller operatively connected to the electrical brakes, wherein the brake controller;

determines if the aircraft is in a first configuration in which the aircraft is in flight and, if the aircraft is in the first configuration, disengages power to the electric brakes from all redundant power supplies while keeping the brake controller powered, wherein the first configuration is defined at least by an airspeed above a first threshold;

determines if the aircraft is in a second configuration and, if the aircraft is in the second configuration, engages power to the electric brakes from only one of the redundant power supplies; and

determines if the aircraft is in a third configuration and, if the aircraft is in the third configuration, engages power to the electric brakes from at least two of the redundant power supplies.

17. The aircraft of claim 16, wherein the first configuration also is defined at least by a weight off wheels configuration.

18. The aircraft of claim 16, wherein the second configuration is defined at least by the airspeed below the first threshold and above a second threshold.

19. The aircraft of claim 18, wherein the second configuration also is defined at least by a weight off wheels configuration.

20. The aircraft of claim 16, wherein the third configuration is defined at least by the airspeed below a second threshold.

21. The aircraft of claim 20, wherein the third configuration also is defined by a weight off wheels configuration.

22. The aircraft of claim 20, wherein the third configuration also is defined by a weight on wheels configuration.

23. The aircraft of claim 16, wherein the power supplies comprise a plurality of batteries.

24. A set of instructions stored in a non-transitory machine-readable medium and executable by a processor, wherein the set of instructions:

determines if the aircraft is in a first configuration in which the aircraft is in flight, wherein the first configuration is defined at least by an airspeed above a first threshold;

if the aircraft is in the first configuration, keeps a brake controller of the electric brakes powered and disengages power to the electric brakes from all of a plurality of power supplies;

determines if the aircraft is in a second configuration;

if the aircraft is in the second configuration, engages power to the electric brakes from only one of the power supplies;

determines if the aircraft is in a third configuration; and

if the aircraft is in the third configuration, engages power to the electric brakes from at least two of the power supplies.

25. An electric brake system for an aircraft in a low power mode of operation, comprising:

electric brakes;

a plurality of power supplies for supplying power to the electric brakes; and

a brake controller controlling the operation of the electric brakes, the brake controller being configured to;

disengage power to the electric brakes from all of the power supplies when the aircraft is in a first configuration in which the aircraft is in flight while keeping the brake controller powered, wherein the first configuration is defined at least by an airspeed above a first threshold; and

engage power to the electric brakes from one of the power supplies when the aircraft is in a second configuration.

26. An electric brake system for an aircraft, comprising:

electric brakes;

a plurality of redundant power supplies for supplying power to the electric brakes; and

a brake controller configured to control the operation of the electric brakes during a low power mode of operation of the aircraft, the brake controller being configured to;

disengage power to the electric brakes from all of the redundant power supplies when the aircraft is in a first configuration in which the aircraft is in flight, wherein the first configuration is defined at least by an airspeed above a first threshold;

engage power to the electric brakes from only one of the redundant power supplies when the aircraft is in a second configuration; and

engage power to the electric brakes from two of the redundant power supplies when the aircraft is in a third configuration.