Aircraft brake system testing methods

• US 9,227,617 B2
• Filed: 05/29/2014
• Issued: 01/05/2016
• Est. Priority Date: 05/29/2014
• 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, Georgin, Marc
• Primary Examiner(s): Shaawat, Mussa A
• Assistant Examiner(s): JHA, ABDHESH K
• Application Number:
  US14/290,521
• Publication Number:
  US 20150344017A1
• Time in Patent Office: 586 Days
• Field of Search: None
• 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: B60T 2270/406 Test-mode; Self-diagnosis
• CPC Class Codes: B60T 8/1703 for aircrafts
• CPC Class Codes: B60T 8/885 using electrical circuitry
• CPC Class Codes: B64C 25/42 Arrangement or adaptation of brakes
• CPC Class Codes: B64C 25/44 Actuating mechanisms

Abstract

Methods for testing the operation of an aircraft braking system utilize the steps of applying a predetermined electrical energy level to an electromechanical actuator attached to a brake assembly, followed by discontinuing electrical energy to the electromechanical actuator. In some test methods, an actuation level of the electromechanical actuator is determined and used to evaluate braking performance. In other tests, a voltage generated by an electric motor in an actuator is measured and used to evaluate braking performance.

Claims

1. A method for testing the operation of an aircraft braking system comprising:

at least partially actuating a brake actuator attached to a brake assembly, wherein the brake assembly comprises a brake stack and the brake actuator comprises a ram;

discontinuing actuating the brake actuator,

determining an actuation level of the brake actuator by determining a position of the ram after discontinuing actuation of the brake actuator; and

evaluating braking performance by comparing the position of the ram after discontinuing actuation to a predetermined desired position of the ram.

2. The testing method of claim 1, wherein the brake actuator is an electromechanical actuator.

3. The testing method of claim 2, wherein the aircraft braking system comprises four electromechanical actuators.

4. The testing method of claim 1, wherein determining the actuation level of the brake actuator comprises receiving a signal from a position detector of the brake actuator.

5. The testing method of claim 1, wherein evaluating the braking performance comprises comparing the actuation level of the brake actuator to a predetermined value, the actuation level comprising the position of the ram after discontinuing actuation and the predetermined value comprising the predetermined desired position of the ram.

6. The testing method of claim 1, wherein the testing method is performed on an aircraft as it is in flight.