AIRCRAFT ELECTRICAL BRAKE CONTROL SYSTEM ARCHITECTURE

• US 20080030069A1
• Filed: 08/04/2006
• Published: 02/07/2008
• Est. Priority Date: 08/04/2006
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Godo, Erik L., Nguyen, Tu-Luc H., Griffith, T. Todd, Yamamoto, David T.
• Granted Patent: US 9,656,641 B2
• Time in Patent Office: Days
• US Class Current: 303/20
• CPC Class Codes: B60T 13/741 acting on an ultimate actuator
• CPC Class Codes: B60T 2270/404 Brake-by-wire or X-by-wire failsafe
• CPC Class Codes: B60T 2270/82 Brake-by-Wire, EHB
• CPC Class Codes: B60T 7/042 by electrical means, e.g. using travel or force sensors
• CPC Class Codes: B60T 8/1703 for aircrafts
• CPC Class Codes: B60T 8/325 Systems specially adapted for aircraft

Abstract

An electric brake system architecture for an aircraft with two or more electrical braking subsystems including brake system controls configured to communicate pilot pedal commands to electric brake actuator controllers that apply or release brakes in wheel groups. The system allows independent brake activation of wheel groups through a plurality of brake system controls and electric brake actuator controllers. The electric braking system further includes remote data consolidators to collect and transmit wheel data to brake system controls through a digital data communication bus. The system reduces aircraft weight, prevents inadvertent braking, and prevents error propagation between subsystems.

Claims

1. An electric brake system for an aircraft having at least one left landing gear wheel and at least one right landing gear wheel, the system comprising:

a right brake system control unit configured to generate brake control signals for the at least one right landing gear wheel in response to pilot input;

a left brake system control unit configured to generate brake control signals for the at least one left landing gear wheel in response to pilot input;

at least one right electric brake actuator control coupled to and controlled by the right brake system control unit, the at least one right electric brake actuator control unit being configured to generate brake mechanism control signals for the at least one right landing gear wheel; and

at least one left electric brake actuator control coupled to and controlled by the left brake system control unit, the at least one left electric brake actuator control unit being configured to generate brake mechanism control signals for the at least one left landing gear wheel.

2. An electric brake system according to claim 1, wherein:

the at least one left landing gear wheel includes N left wheel groups;

the at least one left electric brake actuator control includes N left electric brake actuator controls respectively coupled to the N left wheel groups;

the at least one right landing gear wheel includes N right wheel groups; and

the at least one right electric brake actuator control includes N right electric brake actuator controls respectively coupled to the N right wheel groups.

3. An electric brake system according to claim 2, further comprising:

a plurality of right sensors each coupled to a wheel in the N right wheel groups and configured to measure data corresponding to the wheel in the N right wheel groups; and

a plurality of left sensors each coupled to a wheel in the N left wheel groups and configured to measure data corresponding to the wheel in the N left wheel groups.

4. An electric brake system according to claim 2, wherein each wheel group has a fore wheel and an aft wheel.

5. An electric brake system according to claim 1, further comprising:

the at least one left landing gear wheel includes a left inboard and a left outboard wheel groups;

the at least one left electric brake actuator control includes a left outboard and a left inboard electric brake actuator controls respectively coupled to the left outboard and the left inboard wheel groups;

the at least one right landing gear wheel includes a right inboard and a right outboard wheel groups; and

the at least one right electric brake actuator control includes a right outboard and a right inboard electric brake actuator controls respectively coupled to the right outboard and the right inboard wheel groups.

6. An electric brake system according to claim 1, further comprising:

a left pilot pedal configured to construct the pilot input to generate the brake control signals for the at least one left landing gear wheel; and

a right pilot pedal to construct the pilot input to generate the brake control signals for the at least one right landing gear wheel group.

7. An electric brake system according to claim 1, further comprising:

at least one left electric brake power supply unit configured to supply power to the left brake system control unit and to the at least one left electric brake actuator control; and

at least one right electric brake power supply unit configured to supply power to the right brake system control unit and to the at least one right electric brake actuator control.

8. An electric brake system according to claim 1, further comprising a plurality of remote data concentrators (“

RDCs”

), a respective RDC being coupled to each of the at least one left landing gear wheel and the at least one right landing gear wheel, and each RDC being configured to collect and transmit wheel data for its respective landing gear wheel.

9. An electric brake system according to claim 8, wherein:

the plurality of RDCs include at least one left RDC corresponding to the at least one left landing gear wheel, and at least one right RDC corresponding to the at least one right landing gear wheel;

the electric brake system further comprises a first digital data communication bus configured to communicate wheel data from the at least one left RDC to the left brake system control unit; and

the electric brake system further comprises a second digital data communication bus configured to communicate wheel data from the at least one right RDC to the right brake system control unit.

10. An electric brake system according to claim 8, wherein:

the at least one right RDC is, further, configured to receive power from the right brake system control unit; and

the at least one left RDC is, further, configured to receive power from the left brake system control unit.

11. An electric brake system according to claim 1, further comprising:

at least one right electric brake power supply unit, configured to supply power to the right brake system control unit and to the at least one right electric brake actuator control unit; and

at least one left electric brake power supply unit, configured to supply power to the left brake system control unit and to at least one left electric brake actuator control unit.

12. An electric brake system for an aircraft having at least one left landing gear wheel and at least one right landing gear wheel, the system comprising:

at least one left remote data concentrator (“

RDC”

) for the at least one left landing gear wheel, the at least one left RDC being configured to collect wheel data for the at least one left landing gear wheel;

at least one right RDC for the at least one right landing gear wheel, the at least one right RDC being configured to collect wheel data for the at least one right landing gear wheel;

at least one left electric brake actuator control configured to generate brake control signals for the at least one left landing gear wheel in response to wheel data collected by the at least one left RDC; and

at least one right electric brake actuator control configured to generate brake control signals for the at least one right landing gear wheel in response to wheel data collected by the at least one right RDC.

13. An electric brake system according to claim 12, wherein:

the at least one right landing gear wheel includes a first right inboard wheel, a second right inboard wheel, a first right outboard wheel, and a second right outboard wheel; and

the at least one left landing gear wheel includes a first left inboard wheel, a second left inboard wheel, a first left outboard wheel, and a second left outboard wheel.

14. An electric brake system according to claim 13, wherein:

the at least one right RDC includes a first right inboard RDC coupled to the first right inboard wheel, a second right inboard RDC coupled to the second right inboard wheel, a first right outboard RDC coupled to the first right outboard wheel, and a second right outboard RDC coupled to the second right outboard wheel; and

the at least one left RDC includes a first left inboard RDC coupled to the first left inboard wheel, a second left inboard RDC coupled to the second left inboard wheel, a first left outboard RDC coupled to the first left outboard wheel, and a second left outboard RDC coupled to the second left outboard wheel.

15. An electric brake system according to claim 14, further comprising:

a right outboard electric brake actuator control coupled to the first and the second right outboard RDCs and being configured to generate brake control signals for the first and the second right outboard landing gear wheels in response to wheel data collected by the right outboard RDCs; and

a right inboard electric brake actuator control coupled to the first and the second right inboard RDCs and being configured to generate brake control signals for the first and the second right inboard landing gear wheels in response to wheel data collected by the right inboard RDCs;

a left outboard electric brake actuator control coupled to the first and the second left outboard RDCs and being configured to generate brake control signals for the first and the second left outboard landing gear wheels in response to wheel data collected by the left outboard RDCs; and

a left inboard electric brake actuator control coupled to the first and the second left inboard RDCs and being configured to generate brake control signals for the first and the second left inboard landing gear wheels in response to wheel data collected by the left inboard RDCs.

16. An electric brake system according to claim 12, further comprising:

at least one right electric brake power supply unit, configured to supply power to a right brake system control unit and to the at least one right electric brake actuator control unit; and

at least one left electric brake power supply unit, configured to supply power to a left brake system control unit and to the at least one left electric brake actuator control unit.

17. An electric brake system according to claim 16, wherein:

the at least one left RDC is, further, configured to receive power from the left brake system control unit; and

the at least one right RDC is, further, configured to receive power from the right brake system control unit.

18. An electric brake system for an aircraft having at least one landing gear wheel, the system comprising:

a brake system control unit configured to generate brake control signals for at least one landing gear wheel in response to pilot input; and

at least one electric brake actuator control coupled to and controlled by the brake system control unit, the at least one electric brake actuator control unit being configured to generate brake mechanism control signals for the at least one landing gear wheel.

19. An electric brake system according to claim 18, further comprising:

the at least one landing gear wheel includes inboard and outboard wheel groups; and

the at least one electric brake actuator control includes outboard and inboard electric brake actuator controls respectively coupled to the outboard and the inboard wheel groups.

20. An electric brake system according to claim 18, wherein the brake system control unit is, further, configured to generate the brake control signals using a digital data transmission protocol.

21. An electric brake system according to claim 18, wherein the at least one electric brake actuator control unit is, further, configured to generate the brake mechanism control signals using a digital data transmission protocol.