Systems and methods for brake actuator operation sensor error compensation

• US 9,663,078 B1
• Filed: 12/28/2015
• Issued: 05/30/2017
• Est. Priority Date: 12/28/2015
• Status: Active Grant

• Current Assignee: Goodrich Corporation (Rtx Corporation)
• Original Assignee: Goodrich Corporation (Rtx Corporation)
• Inventors: Rook, Todd
• Primary Examiner(s): Tarcza, Thomas
• Assistant Examiner(s): Dunn, Alex C
• Application Number:
  US14/980,053
• Time in Patent Office: 519 Days
• CPC Class Codes: B60T 2270/406 Test-mode; Self-diagnosis
• CPC Class Codes: B60T 2270/413 Plausibility monitoring, cross check, redundancy
• CPC Class Codes: B60T 8/1703 for aircrafts
• CPC Class Codes: B60T 8/171 Detecting parameters used in the regulation; Measuring values used in the regulation
• CPC Class Codes: B60T 8/885 using electrical circuitry
• CPC Class Codes: B64C 25/44 Actuating mechanisms

Abstract

The present disclosure provides systems and methods for brake actuator operation sensor error compensation. In various embodiments, a system for brake actuator operation sensor error compensation determines the existence of potential sensor errors and compensates for the effects of such errors.

Claims

1. A method of brake actuator operation sensor error compensation comprising:

polling, by an aircraft electro-mechanical brake actuator controller, a plurality of inputs comprising at least one of;

a plurality of load cell forces;

a plurality of current sensor currents; and

a plurality of position sensor positions;

performing, by the controller, a conformance test in response to the polling;

rejecting, by the controller, non-conforming inputs in response to the conformance test; and

outputting, by the controller, a compensation signal to a command force controller,

wherein the command force controller comprises the aircraft electro-mechanical brake actuator controller,

wherein the conformance test comprises performing a least squares fit of the plurality of inputs whereby non-conforming inputs are identified for rejection.

2. The method according to claim 1, wherein the conformance test further comprises:

performing a Euclidean fit of the plurality of inputs whereby non-conforming inputs are identified for rejection.

3. The method according to claim 2, wherein the conformance test further comprises:

performing a medial least squares fit of the plurality of inputs whereby non-conforming inputs are identified for rejection.

4. The method according to claim 3, wherein the conformance test further comprises:

performing a planar fit of subsets of the plurality of inputs, wherein median calculations are performed of coefficients, whereby non-conforming inputs are identified for rejection.

5. The method according to claim 4, wherein the plurality of inputs comprises four inputs, and wherein the subsets comprise three of the four inputs.

6. The method according to claim 5, wherein the compensation signal comprises an indication to increase or decrease a braking force.

7. A tangible, non-transitory memory configured to communicate with a controller, the tangible, non-transitory memory having instructions stored thereon that, in response to execution by the controller, cause the controller to perform operations comprising:

polling, by an aircraft electro-mechanical brake actuator controller, a plurality of inputs comprising at least one of;

a plurality of load cell forces;

a plurality of current sensor currents; and

a plurality of position sensor positions;

performing, by the controller, a conformance test in response to the polling;

rejecting, by the controller, non-conforming inputs in response to the conformance test; and

outputting, by the controller, a compensation signal to a command force controller,

wherein the command force controller comprises the aircraft electro-mechanical brake actuator controller,

wherein the conformance test comprises performing a least squares fit of the plurality of inputs whereby non-conforming inputs are identified for rejection.

8. The tangible, non-transitory memory according to claim 7, wherein the conformance test further comprises:

performing a Euclidean fit of the plurality of inputs whereby non-conforming inputs are identified for rejection.

9. The tangible, non-transitory memory according to claim 8, wherein the conformance test further comprises:

performing a medial least squares fit of the plurality of inputs whereby non-conforming inputs are identified for rejection.

10. The tangible, non-transitory memory according to claim 9, wherein the conformance test further comprises:

performing a planar fit of subsets of the plurality of inputs, wherein median calculations are performed of coefficients, whereby non-conforming inputs are identified for rejection.

11. The tangible, non-transitory memory according to claim 10, wherein the plurality of inputs comprises four inputs, and wherein the subsets comprise three of the four inputs.

12. The tangible, non-transitory memory according to claim 11, wherein the compensation signal comprises an indication to increase or decrease a braking force.

13. The tangible, non-transitory memory according to claim 7, wherein the polling, by the aircraft electro-mechanical brake actuator controller, is performed by at least one of a measured current error detector, a measured position error detector, and a measured force error detector logically partitioned within the electro-mechanical brake actuator controller.

14. A system for brake actuator operation sensor error compensation,

wherein the system comprises at least one of:

a first load cell, a second load cell, a third load cell, and a fourth load cell each in communication with a command force controller and a measured force error detector;

a first current sensor, a second sensor, a third current sensor, and a fourth current sensor each in communication with the command force controller and a measured current error detector; and

a first position sensor, a second position sensor, and a third position sensor, each in communication with the command force controller and a measured position error detector,

wherein an output compensation signal is output to the command force controller by the at least one of;

the measured current error detector,

the measured position error detector, and

the measured force error detector,

wherein the command force controller commands an electric brake actuator to actuate an actuator motor,

whereby a pressure plate exerts a force on a disc in response to the output compensation signal.

15. A method of brake actuator operation sensor error compensation comprising:

polling, by an aircraft electro-mechanical brake actuator controller, a plurality of inputs comprising at least one of;

a plurality of load cell forces;

a plurality of current sensor currents; and

a plurality of position sensor positions;

performing, by the controller, a conformance test in response to the polling;

rejecting, by the controller, non-conforming inputs in response to the conformance test; and

outputting, by the controller, a compensation signal to a command force controller,

wherein the polling, by the aircraft electro-mechanical brake actuator controller, is performed by at least one of a measured current error detector, a measured position error detector, and a measured force error detector logically partitioned within the electro-mechanical brake actuator controller.