Systems and methods for built in test equipment for a brake control system

• US 8,393,203 B2
• Filed: 03/08/2010
• Issued: 03/12/2013
• Est. Priority Date: 03/08/2010
• Status: Active Grant

• Current Assignee: Goodrich Corporation (Rtx Corporation)
• Original Assignee: Goodrich Corporation (Rtx Corporation)
• Inventors: Cahill, Eric D.
• Primary Examiner(s): MCCALL, ERIC SCOTT
• Application Number:
  US12/719,644
• Publication Number:
  US 20110214496A1
• Time in Patent Office: 1,100 Days
• Field of Search: 731/21, 731/28, 731/29, 731/30
• 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:

establishing a safety interlock between a brake system controller and an aircraft component;

severing an I/O channel between the brake system controller and the 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 reestablishing the I/O channel.

3. 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.

4. The method of claim 1, further comprising sending a command signal from the brake system controller through the safety interlock to the aircraft component.

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

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