System and method for independent braking system enablement

Patent metadata

Field	Value
Publication number	US-9376093-B2
Application number	US-201314074445-A
Country	US
Kind code	B2
Filing date	Nov 7, 2013
Priority date	Nov 7, 2013
Publication date	Jun 28, 2016
Grant date	Jun 28, 2016

Abstract

Described herein is a system and method to enable braking system operation independent of conventional aircraft signals, such as those tied to the hibernation commands. Stated another way, the present disclosure relates to the enablement of a braking system in response to an initiation signal. In this way, the crew has the ability to force the braking system out of a hibernation mode into an “emergency type” braking mode if desired. The concepts described herein may be applicable to an electric braking system and to a hydraulic braking system.

First claim

What is claimed is:

1. An aircraft braking system comprising:
a brake pedal; and
a switch configured to enable power delivery to a sensor coupled to the brake pedal, wherein the sensor is configured to measure a brake pedal displacement and duration of the brake pedal displacement above a predetermined threshold of time, wherein in response to the sensor measuring the brake pedal displacement a predetermined distance for a predetermined duration, the aircraft braking system is enabled during flight, thereby forcing the aircraft braking system out of hibernation into an operational mode.

2. The system according to claim 1 , wherein the aircraft braking system transitions from powered down mode to standby mode in response to toggling the switch.

3. The system according to claim 1 , wherein the aircraft braking system transitions from standby mode to the operational mode in response to the sensor measuring the brake pedal displacement moving the predetermined distance for the predetermined duration.

4. The system according to claim 3 , wherein in response to being in the standby mode, at least one of brake pressure is unavailable and an electromechanical brake actuator functionality is disabled.

5. The system according to claim 1 , wherein the aircraft braking system is at least one of a hydraulic braking system and an electronic braking system.

6. The system according to claim 1 , wherein in response to the aircraft braking system being enabled, at least one of brake pressure is available and an electromechanical brake actuator functionality is enabled.

7. The system according to claim 1 , wherein the predetermined duration of time is about 5 seconds.

8. The system according to claim 1 , wherein the predetermined distance is greater than about 50 percent of a total available brake pedal path of travel distance.

9. The system according to claim 1 , wherein in response to the aircraft braking system being enabled, the aircraft braking system bypasses a second braking system enablement protocol.

10. The system according to claim 1 , further comprising a brake control unit.

11. A hydraulic aircraft braking system comprising:
a brake pedal; and
a sensor coupled to the brake pedal, wherein the sensor is configured to measure a brake pedal displacement and duration of the brake pedal displacement above a predetermined threshold of time, wherein the hydraulic aircraft braking system is toggled from a disabled mode to an enabled mode in flight in response to the sensor measuring the brake pedal displacement moving the predetermined displacement for the predetermined duration, wherein in response to the hydraulic aircraft braking system toggling from the disabled mode to the enabled mode in flight, the hydraulic aircraft braking system is forced out of hibernation into an operational mode.

12. The system according to claim 11 , wherein in response to the hydraulic aircraft braking system being in the enabled mode, brake pressure is available to deliver a clamping force on a wheel of the aircraft.

13. The system according to claim 11 , wherein the predetermined duration of time is about 5 seconds.

14. The system according to claim 11 , wherein the predetermined distance is greater than about 50 percent of a total available brake pedal path of travel distance.

15. The system according to claim 11 , wherein in response to the hydraulic aircraft braking system toggling from the disabled mode to the enabled mode, the hydraulic aircraft braking system bypasses a second braking system enablement protocol.

Assignees

• Goodrich Corp

Inventors

• Cahill Eric Daniel

Classifications

• B64C25/46

  Brake regulators for preventing skidding or aircraft somersaulting · CPC title

• B64C25/42

  Arrangement or adaptation of brakes · CPC title

• B60T8/1703

  for aircrafts · CPC title

• B60T7/06 Primary

  Disposition of pedal · CPC title

• B60T2220/04

  Pedal travel sensor, stroke sensor; Sensing brake request · CPC title