SYSTEMS AND METHODS FOR BUILT IN TEST EQUIPMENT FOR A BRAKE CONTROL SYSTEM

• US 20150243113A1
• Filed: 02/25/2014
• Published: 08/27/2015
• Est. Priority Date: 02/25/2014
• Status: Active Grant

• Current Assignee: Goodrich Corporation (Rtx Corporation)
• Original Assignee: Goodrich Corporation (Rtx Corporation)
• Inventors: Cahill, Eric Daniel
• Granted Patent: US 9,280,858 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: B60T 17/221 Procedure or apparatus for checking or keeping in a correct functioning condition of brake systems hydraulic pressure systems in general F15B19/00, F15B21/04; testing structures or apparatus G01M
• CPC Class Codes: B64C 25/44 Actuating mechanisms
• CPC Class Codes: B64F 5/60 Testing or inspecting aircraft components or systems
• CPC Class Codes: G01L 5/28 for testing brakes
• CPC Class Codes: G07C 5/0808 Diagnosing performance data testing of vehicles G01M17/00; testing of electrical installation on vehicles G01R31/005

Abstract

A method is disclosed that comprises severing an I/O channel between an EMAC and an aircraft component; sending a test signal to the brake system controller; receiving, from the brake system controller, a feedback signal to the test signal; and determining an appropriateness of the feedback signal.

Claims

1. A method comprising:

establishing a safety interlock between an electromechanical actuator controller (“

EMAC”

) and an aircraft component;

severing an I/O channel between the EMAC and the aircraft component;

sending at least one test signal to the EMAC;

receiving, from the EMAC, a feedback signal to the test signal; and

determining an appropriateness of the feedback signal.

2. The method of claim 1, further comprising reestablishing the I/O channel.

3. The method of claim 1, wherein the feedback signal relates to a least one of an electromechanical actuator and a servo.

4. The method of claim 1, wherein the test signal commands an electromechanical actuator to actuate.

5. The method of claim 1, further comprising generating a test script comprising a plurality of test signals with a testing module.

6. The method of claim 1, further comprising establishing a non-severable I/O channel between the EMAC and an emergency braking system.

7. A method comprising:

disposing a selectively severable I/O channel between an electromechanical actuator controller (“

EMAC”

) and an aircraft component;

coupling the EMAC with a BITE region, wherein the BITE region comprises a testing module capable of sending a test signal to the EMAC; and

establishing a safety interlock region by disposing a non-severable I/O channel between the EMAC and the aircraft component.

8. The method of claim 7, further comprising placing the safety interlock region in electrical communication with the testing module.

9. The method of claim 8, further comprising loading a test script into the testing module.

10. The method of claim 9, further comprising loading an expected result profile into the testing module.

11. The method of claim 7, further comprising placing the BITE region in electrical communication with a signal conditioning circuit.

12. The method of claim 7, further comprising placing the BITE region in electrical communication with a sensor.

13. The method of claim 7, further comprising placing the EMAC in electrical communication with an emergency braking system.

14. The method of claim 13, receiving, at the EMAC, an emergency braking command from the emergency braking system.

15. The method of claim 14, further comprising stopping, by the EMAC, of a test in response to the emergency braking command.