ELECTRIC BRAKING SYSTEM WITH POWER CONSERVATION AND METHOD OF OPERATING THE SAME

• US 20160031553A1
• Filed: 02/27/2014
• Published: 02/04/2016
• Est. Priority Date: 03/06/2013
• Status: Active Grant

• Current Assignee: Bombardier Incorporated
• Original Assignee: Bombardier Incorporated
• Inventors: DI ZAZZO, Marco, PLANTE, Bertrand
• Granted Patent: US 10,112,704 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• 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;

if the aircraft is in the first configuration, disengaging power to the electric brakes from all 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 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 is defined at least by an airspeed above a first threshold.

4. The method of claim 3, 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.

5. The method of claim 3, wherein the first configuration also is defined at least by a weight off wheels configuration.

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

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

8. The method of claim 6, wherein the second configuration also is defined at least by a weight off wheels configuration.

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

10. The method of claim 6, wherein the third configuration also is defined by a status of the airplane on the ground (WOW).

12. The method of claim 6, wherein the third configuration also is defined by a wheel speed.

13. The method of claim 6, wherein the third configuration also is defined by a weight on wheels configuration.

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

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

16. The method of claim 14, wherein the power supplies comprise a ram air turbine.

11. The method of clam 6, wherein the third configuration also is defined by a weight off wheels configuration.

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

a plurality of redundant power systems;

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 and, if the aircraft is in the first configuration, disengages power to the electric brakes from all power supplies, 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 one of the 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 power supplies.

18. The aircraft of claim 17, wherein the first configuration is defined at least by an airspeed above a first threshold.

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

20. The aircraft of claim 17, wherein the second configuration is defined at least by an airspeed below a first threshold and above a second threshold.

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

22. The aircraft of claim 17, wherein the third configuration is defined at least by an airspeed below a second threshold.

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

25. The aircraft of claim 17, wherein the power supplies comprise a plurality of batteries.

23. The aircraft of clam 22, wherein the third configuration also is defined by a weight off wheels configuration.

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

electric brakes;

at least one power supply connected to the electric brakes; and

a brake controller controlling the operation of the electric brakes, wherein

if the aircraft is in a first configuration, power to the electric brakes is disengaged from all power supplies,

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

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

27. A set of instructions executable by a processor, wherein the set of instructions:

determines if the aircraft is in a first configuration;

if the aircraft is in the first configuration, disengages power to the electric brakes the from all 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 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.