Aircraft pilot display system and method of use

Patent metadata

Field	Value
Publication number	US-10399696-B2
Application number	US-201615252994-A
Country	US
Kind code	B2
Filing date	Aug 31, 2016
Priority date	Aug 31, 2016
Publication date	Sep 3, 2019
Grant date	Sep 3, 2019

Abstract

A yaw feedback system for use by an aircraft is provided. The yaw feedback system includes a processor, a runway centerline indicator, and a yaw feedback indicator. The processor is configured to determine a yaw difference between a current track of the aircraft and a runway centerline. The runway centerline indicator is configured to virtually extend a runway visual range (RVR) for a pilot of the aircraft. The yaw feedback indicator is coupled to the processor and configured to prompt the pilot for a yaw input to compensate for the yaw difference.

First claim

What is claimed is:

1. A yaw feedback system ( 605 ) for use by a pilot of an aircraft ( 100 ) during takeoff, comprising:
a processor ( 615 ) configured to determine a yaw difference between a current track of the aircraft and a runway centerline ( 106 );
a runway centerline indicator ( 210 ) configured to virtually extend a runway visual range “RVR” for a pilot of the aircraft; and
a yaw feedback indicator ( 650 ) coupled to the processor and configured to prompt the pilot for a yaw input to compensate for the yaw difference, and to convey, to the pilot, a magnitude and a direction of the yaw difference.

2. The yaw feedback system ( 605 ) of claim 1 , wherein the yaw feedback indicator ( 650 ) comprises an indicator light ( 414 , 416 ) operable to illuminate in a plurality of colors, wherein an illuminated color of the indicator light is selected based on an estimated magnitude of yaw input necessary to compensate for the yaw difference.

3. The yaw feedback system ( 605 ) of claim 1 , wherein the yaw feedback indicator ( 650 ) comprises a port indicator light ( 414 ) and a starboard indicator light ( 416 ), the port indicator light configured to illuminate when prompting the pilot for port yaw input, the starboard indicator light configured to illuminate when prompting the pilot for starboard yaw input.

4. The yaw feedback system ( 605 ) of claim 1 , wherein the yaw feedback indicator ( 650 ) comprises a dial ( 508 ) defining a range of rudder input over which an indicator element ( 504 ) operates, the dial configured to move the indicator element based on the yaw difference.

5. The yaw feedback system ( 605 ) of claim 1 , wherein the processor ( 615 ) is located within a display controller ( 610 ) for a pilot display ( 208 ) on which the runway centerline indicator ( 210 ) and the yaw feedback indicator ( 650 ) are displayed.

6. The yaw feedback system ( 605 ) of claim 1 , wherein the processor ( 615 ) is located within a flight management system ( 640 ) coupled to the runway centerline indicator ( 210 ) and the yaw feedback indicator ( 650 ) through a data bus ( 620 ).

7. The yaw feedback system ( 605 ) of claim 1 , wherein the processor ( 615 ) is further configured to compute a yaw input necessary to compensate for the yaw difference based at least on an airspeed of the aircraft ( 100 ).

8. A method ( 700 ) of prompting a pilot of an aircraft ( 100 ) during takeoff, the method comprising:
receiving ( 720 ), by a processor ( 615 ), a plurality of runway centerline positions ( 214 ) defining a runway centerline ( 106 );
computing ( 730 ), by the processor, a yaw difference between a current track of the aircraft and the runway centerline;
displaying ( 740 ) a runway centerline indicator ( 210 ) to virtually extend a runway visual range “RVR” for the pilot; and
displaying ( 750 ) a yaw feedback indicator ( 650 ) to prompt the pilot for a yaw input to compensate for the yaw difference, the yaw feedback indicator configured to convey, to the pilot, a magnitude and a direction of the yaw difference.

9. The method ( 700 ) of claim 8 further comprising extrapolating, by the processor ( 615 ), the plurality of runway centerline positions ( 214 ) to render the runway centerline indicator ( 210 ) on a pilot display ( 208 ).

10. The method ( 700 ) of claim 8 further comprising receiving, by the processor ( 615 ), the current track of the aircraft from a flight management system ( 640 ).

11. The method ( 700 ) of claim 8 further comprising computing, by the processor ( 615 ), the yaw input necessary to compensate for the yaw difference.

12. The method ( 700 ) of claim 11 , wherein computing the yaw input comprises:
selecting port yaw input when the yaw difference indicates a current starboard yaw; and
selecting starboard yaw input when the yaw difference indicates a current port yaw.

13. The method ( 700 ) of claim 11 , wherein computing the yaw input comprises computing a magnitude of the yaw input based at least on an airspeed of the aircraft ( 100 ).

14. The method ( 700 ) of claim 13 , wherein the yaw feedback indicator ( 650 ) includes a numeric indicator of the magnitude of the yaw input.

15. A pilot display system ( 600 ) for an aircraft ( 100 ), the pilot display system comprising:
a display controller ( 610 ) configured to:
receive ( 720 ) a plurality of runway centerline positions ( 214 ) defining a runway centerline ( 1 . 06 ), and
compute ( 730 ) a yaw difference between a current track of the aircraft and the runway centerline; and

a pilot display ( 208 ) coupled to the display controller, the pilot display comprising:
a runway centerline indicator ( 210 ) displayed according to the plurality of runway centerline positions, and
a yaw feedback indicator ( 650 ) configured to prompt a pilot of the aircraft for a yaw input to compensate for the yaw difference, and to convey, to the pilot, a magnitude and a direction of the yaw difference.

16. The pilot display system ( 600 ) of claim 15 further comprising a data bus ( 620 ) coupled to the display controller ( 610 ) and configured to deliver the runway centerline positions ( 214 ) and the yaw difference to the display controller.

17. The pilot display system ( 600 ) of claim 16 further comprising a flight management system ( 640 ) coupled to the data bus ( 620 ) and configured to compute the yaw difference based on the plurality of runway centerline positions ( 214 ) and the current track.

18. The pilot display system ( 600 ) of claim 16 , wherein the data bus ( 620 ) is further coupled to a navigation system ( 630 ) configured to store the runway centerline positions ( 214 ).

19. The pilot display system ( 600 ) of claim 15 , wherein the pilot display ( 208 ) comprises a heads-up-display “HUD” for the aircraft ( 100 ).

20. The pilot display system ( 600 ) of claim 15 , wherein the yaw feedback indicator ( 650 ) comprises a dial ( 508 ) defining a range of rudder input over which an indicator element ( 504 ) operates, the dial configured to move the indicator element based on the yaw difference.

Assignees

• Boeing Co

Inventors

• Schwartz Samantha
• Reid Katie M

Classifications

• G01C23/00 Primary

  Combined instruments indicating more than one navigational value, e.g. for aircraft; Combined measuring devices for measuring two or more variables of movement, e.g. distance, speed or acceleration · CPC title

• B64C13/042

  operated by hand · CPC title

• B64C13/04

  actuated personally · CPC title

• B64D43/00 Primary

  Arrangements or adaptations of instruments · CPC title

• B64D45/0005

  Devices specially adapted to indicate the position of a movable element of the aircraft, e.g. landing gear · CPC title