Antilock braking system with directional control

Patent metadata

Field	Value
Publication number	US-9315177-B2
Application number	US-201213419493-A
Country	US
Kind code	B2
Filing date	Mar 14, 2012
Priority date	Mar 14, 2012
Publication date	Apr 19, 2016
Grant date	Apr 19, 2016

Abstract

A system and method for adjusting a yaw of an aircraft having an antilock braking system is disclosed. The antilock braking system includes a controller configured to receive a directional input from a rudder. The controller is further configured to deliver a braking output to at least one of a left wheel brake and a right wheel brake. A position of the rudder indicates a pilot's desired steering response, and to allow for braking optimization by the antilock braking system, the pilot depresses fully the left wheel brake pedal and the right wheel brake pedal. The controller receives the directional input after both the right wheel brake pedal and the left wheel brake pedal have been fully depressed. The controller then delivers the braking output and a pressure on one of the left wheel brake and the right wheel brake is reduced in accordance with the directional input.

First claim

The invention claimed is:

1. A method for adjusting an unintended yaw of an aircraft having a free-castering nose wheel, a left wheel, a right wheel, an antilock braking system, a left brake pedal for operating a left wheel brake associated with the left wheel, a right brake pedal for operating a right wheel brake associated with the right wheel, a controller for executing a computer implemented routine, and a rudder, the method comprising steps:
automatically triggering the routine when:
one of a left rudder pedal and a right rudder pedal is depressed to cause the rudder to deflect off-center; and
the left brake pedal and the right brake pedal are each fully depressed to cause the antilock braking system to respectively apply an optimal retarding force with each of the left wheel brake and the right wheel brake

receiving by the controller a directional input from the rudder upon the triggering of the routine; and
using the routine to deliver a braking output by the controller to automatically reduce an actual braking pressure of one of the left wheel brake and the right wheel brake in line with the directional input until the depressed rudder pedal is released and the unintended yaw is corrected, wherein the routine artificially increases a calculated ground speed of the aircraft used to compute a slip of one of a left and right wheel, causing the slip of one of the left and right wheels to also artificially increase.

2. The method of claim 1 , wherein a right speed sensor is coupled to the right wheel, and a left speed sensor is coupled to the left wheel.

3. The method of claim 2 , wherein an original slip target of at least one of the right wheel and the left wheel is reinstated after the aircraft has steered in accordance with the directional input.

4. The method of claim 1 , wherein the optimal retarding force generally maintains a wheel slip ratio of about fifteen percent.

5. The method of claim 4 , wherein the braking output is proportional to the directional input.

6. A method for correcting a yaw of an aircraft traveling on a runway, the method comprising:
triggering a computer implemented routine by:
fully depressing each of a left wheel brake pedal associated with a left hand wheel brake and a right wheel brake pedal associated with a right hand wheel brake; and
deflecting a rudder off-center using a rudder pedal;

receiving a directional input upon the triggering of the routine;
imposing by a controller a pulsing cycle wherein an intermittent and automatic release of both of the left and right hand wheel brakes occurs; and
using the routine to reduce a pressure on one of the left hand wheel brake and the right hand wheel brake according to the directional input, wherein the routine artificially increases a calculated ground speed of the aircraft used to compute a slip of one of a left and right wheel, causing the slip of one of the left and right wheels to also artificially increase, thereby inducing an antilock braking system to subsequently reduce the slip of one of the left and right wheels to a target slip by reducing the braking pressure on one of the left hand wheel brake and the right hand wheel brake.

7. The method of claim 6 , wherein the aircraft has a free-castering no sewheel.

8. The method of claim 7 , wherein the reduction in the pressure on one of the left hand wheel brake and the right hand wheel brake is proportional to the directional input.

9. A method for adjusting an unintended yaw of an aircraft having a nose wheel, a left wheel, a right wheel, an antilock braking system, a left brake pedal for operating a left wheel brake associated with the left wheel, a right brake pedal for operating a right wheel brake associated with the right wheel, a controller for executing a computer implemented routine, and a rudder, the method comprising steps:
triggering the routine by:
depressing one of a left rudder pedal and a right rudder pedal to cause the rudder to deflect off-center; and
depressing fully the left brake pedal and the right brake pedal to cause the antilock braking system to respectively apply an optimal retarding force with each of the left wheel brake and the right wheel brake;

receiving by the controller a directional input from the rudder after the routine has been triggered; and
using the routine to deliver a braking output by the controller to automatically reduce an actual braking pressure of one of the left wheel brake and the right wheel brake in line with the directional input until the depressed rudder pedal is released, wherein the routine artificially increases a calculated ground speed of the aircraft used to compute a slip of one of the left and right wheels, causing the slip of one of the left and right wheels to also artificially increase, thereby inducing the antilock braking system to subsequently reduce the slip of one of the left and right wheels to a target slip by reducing the braking pressure on one of the left hand wheel brake and the right hand wheel brake.

10. The method of claim 9 wherein the nose wheel is a free castering nosewheel.

11. The method of claim 10 , wherein a right speed sensor is coupled to the right wheel, and a left speed sensor is coupled to the left wheel.

12. The method of claim 11 , wherein an original slip target of at least one of the right wheel and the left wheel is reinstated after the aircraft has steered in accordance with the directional input.

13. The method of claim 9 , wherein:
the aircraft has a nosewheel steering; and
the routine serves as a backup to the nosewheel steering and is triggered when the nosewheel steering fails.

14. A method for adjusting the yaw of an aircraft, the aircraft having a no sewheel, a left wheel, a right wheel, a left wheel brake for applying a retarding force to the left wheel, a right wheel brake for applying a retarding force to the right wheel, a left brake pedal associated with the left wheel brake, a right brake pedal associated with the right wheel brake, a rudder and a rudder pedal associated therewith, and a braking system having a controller and non-transitory memory for implementing a routine, the method comprising steps:
triggering the routine when each of:
the left wheel brake is applying a retarding force to the left wheel and the right wheel brake is applying a retarding force to the right wheel; and
the rudder is off center;

receiving a directional input upon the triggering of the routine;
imposing by a controller a pulsing cycle wherein an intermittent and automatic release of both of the left and right wheel brakes occurs; and
using the routine to reduce a pressure on one of the left wheel brake and the right wheel brake according to the directional input;
wherein the routine artificially modifies a calculated ground speed of the aircraft used to compute a slip of one of the left wheel and the right wheel, causing the slip of one of the left and right wheels to also artificially increase, thereby inducing the controller to subsequently reduce the slip of one of the left and right wheels to a target slip by reducing the retarding force being applied by one of the left wheel brake and the right wheel brake.

Assignees

• Mckay Gary E
• Textron Innovations Inc

Inventors

• Mckay Gary E

Classifications

• B64C25/46

  Brake regulators for preventing skidding or aircraft somersaulting · CPC title

• B60T8/1703 Primary

  for aircrafts · CPC title

• B64C25/48

  differentially operated for steering purposes · CPC title