DISTRIBUTED PEDAL SYSTEM FOR AIRCRAFT

• US 20100280725A1
• Filed: 04/30/2009
• Published: 11/04/2010
• Est. Priority Date: 04/30/2009
• Status: Active Grant

• Current Assignee: Goodrich Corporation (Rtx Corporation)
• Original Assignee: Goodrich Corporation (Rtx Corporation)
• Inventors: Cahill, Eric D.
• Granted Patent: US 8,565,939 B2
• Time in Patent Office: Days
• US Class Current: 701/70
• CPC Class Codes: B60T 13/741 acting on an ultimate actuator
• 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 8/1703 for aircrafts

Abstract

A braking system that can reduce wiring without sacrificing performance. The system includes a data concentrator in the form of a distributed sensor processor unit for receiving braking command signals from a plurality of sensors and, based on the command signals, generating a brake control signal to be sent to a brake system control unit via a serial connection or the like.

Claims

1. An aircraft braking system including a brake assembly operative to brake at least one wheel of an aircraft, a plurality of sensors associated with one or more respective user interface devices for sensing activation of the device and generating a signal in response thereto, a distributed sensor processor unit for receiving the signals from the plurality of sensors and generating a brake control signal, and a brake system control unit for receiving the brake control signal from the distributed sensor processor unit and controlling the brake assembly in response thereto to effect braking of the at least one wheel.

2. An aircraft braking system as set forth in claim 1, wherein the brake system control unit and the distributed sensor processor unit are connected via a serial link.

3. An aircraft braking system as set forth in claim 1, wherein the brake assembly is an electromechanical brake assembly.

4. An aircraft braking system as set forth in claim 1, wherein the user interface device is a brake pedal.

5. An aircraft braking system as set forth in claim 1, wherein the brake system control unit is located remotely from the distributed sensor processor unit.

6. An aircraft braking system as set forth in claim 1, further comprising a redundant second brake system control unit for receiving the brake control signal from the distributed sensor processor unit and controlling the brake assembly in response thereby effect braking of the at least one wheel.

7. An aircraft braking system as set forth in claim 1, wherein the distributed sensor processor unit is configured to verify the health of each sensor attached thereto.

8. An aircraft braking system as set forth in claim 1, wherein the brake assembly is a hydraulic brake assembly.

9. An aircraft braking system as set forth in claim 1 having left and right braking assemblies for braking respective left and right wheels of an aircraft, wherein the distributed sensor processor unit is configured to resolve the amount of braking on the respective left and right hand brake assemblies.

10. An aircraft having a plurality of wheels and including the aircraft braking system as set forth in claim 1 for braking at least one of the wheels.

11. An aircraft as set forth in claim 10, wherein the brake system control unit is located remotely from a cockpit of the aircraft.

12. An aircraft as set forth in claim 10, wherein the distributed sensor processor unit is located within a cockpit of the aircraft.