SYSTEM AND METHODS FOR AN ELECTRIC BRAKE ACTUATION OVERDRIVE FEATURE IN AN AIRCRAFT ELECTRIC BRAKE SYSTEM

• US 20080154470A1
• Filed: 12/21/2006
• Published: 06/26/2008
• Est. Priority Date: 12/21/2006
• Status: Abandoned Application

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Adkinson, Daniel W., Anacker, Gregory T., Goranson, Pete T.
• Application Number:
  US11/614,951
• Publication Number:
  US 20080154470A1
• Time in Patent Office: Days
• US Class Current: 701/70
• CPC Class Codes: B60T 13/746 and mechanical transmission of the braking action
• CPC Class Codes: B60T 2270/402 Back-up
• CPC Class Codes: B60T 2270/404 Brake-by-wire or X-by-wire failsafe
• 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 8/885 using electrical circuitry

Abstract

An electric brake system for an aircraft includes an electric brake actuator overdrive feature that preserves full braking performance even with a failed or intentionally-deactivated electric brake actuator. The electric brake actuator (EBA) overdrive feature monitors EBA parameters, detects a failed or deactivated EBA, deactivates the failed EBA if needed, and proportionally overdrives the remaining functional EBAs by an amount equivalent to the lost clamping force of the failed EBA. This technique effectively provides a clamping force for the wheel-brake that is fully or partially equivalent to the clamping force of a complement of functional EBAs on any wheel-brake of the electric brake system. Use of the overdrive technique provides airplane braking performance that is equivalent to a normal braking condition; therefore, the airplane can be dispatched with a failed or deactivated EBA without the standard operational-performance restriction.

Claims

1. An electric brake system for an aircraft, the electric brake system comprising:

a wheel-brake configured to produce brake torque in response to a clamping force;

a plurality of electric brake actuators (EBAs) configured to provide the clamping force for the wheel-brake;

a plurality of sensors coupled to the EBAs and configured to sense EBA parameters;

an EBA motor controller coupled to the EBAs, wherein the EBA motor controller is configured to;

monitor the EBA parameters for occurrence of a failure condition;

detect at least one failed EBA based upon the failure condition;

disable the at least one failed EBA; and

proportionally overdrive remaining functional EBAs by an amount partially or fully equivalent to a lost clamping force of the at least one failed EBA on any wheel-brake.

2. A system according to claim 1, wherein the failure condition comprises a pending failure.

3. A system according to claim 1, wherein the failure condition comprises a partial failure.

4. A system according to claim 1, wherein the EBA parameters comprise an EBA electric current.

5. A system according to claim 1, wherein the EBA parameters comprise an EBA voltage.

6. A system according to claim 1, wherein the EBA parameters comprise an EBA position.

7. A system according to claim 1, wherein the EBA parameters comprise an EBA load.

8. A system according to claim 1, wherein the actuator motor controller is configured to monitor the EBA parameters by:

receiving EBA parameter signals; and

scanning the EBA parameter signals for occurrence of the failure condition.

9. A method for providing an electric brake actuation overdrive for an aircraft, the method comprising:

monitoring electric brake actuator (EBA) parameters for occurrence of a failure condition;

detecting at least one failed EBA based upon the failure condition;

disabling the at least one failed EBA; and

proportionally overdriving remaining functional EBAs by an amount partially or fully equivalent to a lost clamping force of the at least one failed EBA.

10. A method according to claim 9, wherein the monitoring step further comprises:

receiving EBA parameters signals; and

scanning the EBA parameters signals for occurrence of the failure condition.

11. A method according to claim 10, wherein the EBA parameters signals comprise an EBA electric current signal and an EBA voltage signal.

12. A method according to claim 10, wherein the EBA parameters signals comprise an EBA position signal.

13. A method according to claim 10, wherein the EBA parameters signals comprise an EBA load signal.

14. A method according to claim 9, wherein the failure condition comprises a partial failure.

15. A method according to claim 9, wherein the failure condition comprises a pending failure.

16. An overdrive system for providing an electric brake actuation overdrive for an aircraft having an electric brake system, the overdrive system comprising:

means for monitoring electric brake actuator (EBA) parameters for occurrence of a failure condition;

means for detecting at least one failed EBA based upon the failure condition;

means for disabling the at least one failed EBA; and

means for proportionally overdriving remaining functional EBAs by an amount partially or fully equivalent to a lost clamping force of the at least one failed EBA.