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

• US 20110214496A1
• Filed: 03/08/2010
• Published: 09/08/2011
• Est. Priority Date: 03/08/2010
• Status: Active Grant

• Current Assignee: Goodrich Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: Goodrich Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Cahill, Eric D.
• Granted Patent: US 8,393,203 B2
• Time in Patent Office: Days
• US Class Current: 73/121
• 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 25/42 Arrangement or adaptation of brakes
• CPC Class Codes: B64F 5/60 Testing or inspecting aircraft components or systems

Abstract

A method is disclosed that comprises severing an I/O channel between a brake system controller 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. A system is disclosed that comprises a brake system controller wrapped in a BITE region, wherein the BITE region comprises a testing module, a safety interlock region having an I/O channel between the brake system controller and another system, and a testing module capable of sending a test signal to the brake system controller.

Claims

1. A method comprising:

severing an I/O channel between a brake system controller 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.

2. The method of claim 1, further comprising establishing a safety interlock between the brake system controller and the aircraft component.

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

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

5. The method of claim 2, further comprising sending a command signal from the brake system controller through the safety interlock to the aircraft component.

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

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

8. A system comprising:

a brake system controller wrapped in a BITE region, wherein the BITE region comprises a testing module; and

a safety interlock region having an I/O channel between the brake system controller and another system,

wherein the testing module is capable of sending a test signal to the brake system controller.

9. The system of claim 8, wherein the safety interlock region is in electrical communication with the testing module.

10. The system of claim 9, wherein the testing module creates a test script.

11. The system of claim 8, wherein the BITE region reversibly severs an I/O channel between the brake system controller and another aircraft component.

12. The system of claim 11, wherein the severing of the I/O channel is responsive to a weight on wheels signal.

13. The system of claim 11, wherein the severing of the I/O channel is responsive to at least one of a landing gear downlock signal and a throttle position signal.

14. The system of claim 8, wherein the testing module receives a signal from a component of the brake system controller.

15. A method comprising:

disposing a selectively severable I/O channel between a brake system controller and an aircraft component;

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

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

16. The method of claim 15, further comprising placing the safety interlock region in electrical communication with the testing module.

17. The method of claim 15, further comprising loading a test script into the testing module.

18. The method of claim 15, further comprising loading an expected result profile into the testing module.

19. The method of claim 15, further comprising placing the BITE region in electrical communication with a signal conditioning circuit.

20. The method of claim 15, further comprising placing the BITE region in electrical communication with a sensor.