Monitor for uncommanded braking

• US 6,134,956 A
• Filed: 05/12/1999
• Issued: 10/24/2000
• Est. Priority Date: 03/12/1996
• Status: Expired due to Term

• Current Assignee: Hydro-Aire Division of Crane Company
• Original Assignee: Hydro-Aire Division of Crane Company
• Inventors: Kwong, Raymond, Cook, Robert D., Salamat, Bijan
• Primary Examiner(s): DOMBROSKE, GEORGE M
• Application Number:
  US09/310,636
• Time in Patent Office: 531 Days
• Field of Search: 73/121, 73/123, 73/126, 73/129, 73/118.1, 73/132, 340/453, 340/454
• 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: B60T 7/12 for automatic initiation; for initiation not subject to will of driver or passenger limiting speed of vehicles other than rail vehicles B60K31/00
• CPC Class Codes: B60T 8/1703 for aircrafts

Abstract

The monitor for uncommanded braking controls uncommanded brake application on one or more wheels during takeoff of an aircraft. Brake pedal application is determined, brake pressure is measured, and brake pressure is compared with a selected threshold brake pressure. A brake pressure applied signal is generated when the brake pressure exceeds the threshold brake pressure. The pedal application signal and brake pressure applied signal are received by a fault latch logic circuit that generates a fault latch output signal when uncommanded braking has occurred. A test inhibit signal is also generated when weight is not applied on the wheel. The test inhibit signal is also input to the fault latch logic circuit so that uncommanded braking can occur when the aircraft is in the air and weight is off the wheel. The monitor disables or latches off the shutoff valve when pressure is detected without pedal application. A fail-safe feature re-enables the shutoff valve to allow it to turn on, and monitoring is stopped, when pedal application is detected.

Claims

1. Apparatus for monitoring uncommanded braking for an aircraft having landing gear that can move between a retracted position and an actuated position, the landing gear having a wheel and a hydraulically operated wheel braking system with a brake pedal for controlling operation of said wheel braking system, comprising:

a pedal application monitoring circuit for determining brake pedal application and for generating a pedal application signal indicating actuation of the wheel braking system when said brake pedal has been applied;

a brake pressure monitoring circuit for measuring brake pressure communicated to said wheel braking system;

a brake pressure monitoring circuit for comparing said brake pressure with a selected threshold brake pressure and for generating a brake pressure signal when said brake pressure exceeds said threshold brake pressure;

a gear handle position switch for generating a gear handle up signal to indicate that the landing gear is retracted;

a gear test inhibit logic circuit for receiving said gear handle up signal and for generating a test inhibit signal responsive to said gear handle up signal for inhibiting the apparatus for monitoring uncommanded braking when the landing gear is actuated and permitting operation of the apparatus for monitoring uncommanded braking when the landing gear is retracted;

a shut off valve connected to said wheel braking system for preventing communication of brake pressure to said wheel braking system, in order to prevent braking; and

a fault latch logic circuit for receiving said pedal application signal, said brake pressure signal, and said gear test inhibit signal, and for generating a fault latch output signal for controlling said shut off valve responsive to said pedal application signal, said brake pressure signal, and said gear test inhibit signal.

2. The apparatus of claim 1, further comprising a microcontroller for generating a shut off valve control signal received by said fault latch means.

3. The apparatus of claim 1, wherein said gear test inhibit logic circuit further comprises a weight on wheel switch for sensing weight on said wheel and for generating a test inhibit signal when weight is not applied on said wheel.

4. The apparatus of claim 1, further comprising a built-in-test enable logic circuit for testing functionality of said apparatus for monitoring uncommanded braking and for generating a test enable signal that is received by said fault latch means to reset said fault latch means to allow testing of the apparatus for monitoring uncommanded braking with a test pressure pulse.

5. The apparatus of claim 1, further comprising a microcontroller for controlling brake functions of the wheel braking system.

6. The apparatus of claim 1, further comprising a microcontroller for controlling brake torque of the wheel braking system.

7. A method for monitoring uncommanded braking for an aircraft having landing gear that can move between a retracted position and an actuated position, the landing gear having a wheel and a hydraulically operated wheel braking system with a brake pedal for controlling operation of said wheel braking system, and a shut off valve connected to the wheel braking system for preventing communication of brake pressure to said wheel braking system in order to prevent braking, the steps of the method comprising:

detecting application of a brake pedal and generating a pedal application signal indicating actuation of the wheel braking system when said brake pedal has been applied;

measuring brake pressure communicated to said wheel braking system;

comparing said brake pressure with a selected threshold brake pressure and generating a brake pressure signal when said brake pressure exceeds said threshold brake pressure;

generating a gear handle up signal to indicate that the landing gear is retracted;

generating a test inhibit signal responsive to said gear handle up signal for inhibiting the apparatus for monitoring uncommanded braking when the landing gear is actuated and permitting operation of the apparatus for monitoring uncommanded braking when the landing gear is retracted; and

generating a fault latch output signal for controlling said shut off valve responsive to said pedal application signal, said brake pressure signal, and said gear test inhibit signal.

8. The method of claim 7, further comprising generating a shut off valve control signal received by said fault latch means.

9. The method of claim 7, further comprising sensing weight on said wheel and for generating a test inhibit signal when weight is not applied on said wheel.

10. The method of claim 7, further comprising generating a test enable signal that is received by said fault latch means to reset said fault latch means.

11. The method of claim 7, further comprising controlling brake functions of the wheel braking system responsive to said fault latch output signal.

12. The method of claim 7, further comprising controlling brake torque of the wheel braking system responsive to said fault latch output signal.