IP Library › Granted Patent US 8,878,700
Granted Patent B2
US 8,878,700 · App. 13/769,674 · Granted Nov 4, 2014

Aircraft monitoring system

Inventors: Sean M. Pennell (Seattle, WA); Noah Eric Aaron (Seattle, WA); Darren Gordon McDonald (Federal Way, WA)
Assignee: The Boeing Company
G08B23/00
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Quick Facts
Patent No.
US 8,878,700
App. No.
13/769,674
Granted
Nov 4, 2014
Kind
B2
Abstract

A method and apparatus for monitoring an aircraft. A pilot control input signal is received. A response of a control surface system controlled by a flight control model is identified using the pilot control input signal. An alert is generated when the control surface system reaches a threshold with respect to the control surface system becoming saturated.

Claims (73)

1. A method for monitoring an aircraft ( 202 ), the method comprising:

receiving a pilot control input signal ( 224 );

identifying a response of a control surface system ( 206 ) controlled by a flight control model ( 230 ) using the pilot control input signal ( 224 );

generating an alert ( 240 ) when the control surface system ( 206 ) reaches a threshold ( 241 ) with respect to the control surface system ( 206 ) becoming saturated; and

displaying, via a first indicator ( 408 , 436 , or 464 ) on a graphical user interface ( 236 ), the pilot control input signal ( 224 );

displaying, via a second indicator ( 412 ) on the graphical user interface ( 236 ), a command sent to the control surface system ( 206 ) in response to the pilot control input signal ( 224 ); and

displaying, via a third indicator ( 442 , 468 , or 444 ) on the graphical user interface ( 236 ), the response of the control surface system ( 206 ) to the command.

2. The method of claim 1 further comprising:

modifying a display of the response of the control surface system ( 206 ) based on a range for a position of a control surface prior to displaying the response on the graphical user interface ( 236 );

wherein the pilot control input signal ( 224 ) is displayed via a first graphical element ( 408 , 436 , or 464 ) and a second graphical element ( 422 , 454 , or 478 ) and the second graphical element ( 422 , 454 , or 478 ) displays the pilot control input signal ( 224 ) as a numerical value; and

wherein the command is displayed via a third graphical element ( 412 , 442 , 444 , or 468 ) and a fourth graphical element ( 423 , 456 , 457 , and 480 ) and the fourth graphical element ( 423 , 456 , 457 , and 480 ) displays the command as a numerical value.

3. The method of claim 1 further comprising:

displaying a level of saturation ( 310 ) for a roll control surface.

4. The method of claim 1 further comprising:

displaying a level of saturation ( 310 ) for a yaw control surface.

5. The method of claim 1 further comprising:

displaying a level of saturation ( 310 ) for a pitch control surface.

6. The method of claim 1 further comprising:

modifying a display of the response based on a range for a position of a control surface.

7. The method of claim 1 further comprising:

displaying an indication of the control surface system ( 206 ) approaching the threshold ( 241 ).

8. The method of claim 1 further comprising:

displaying a roll rate ( 406 ) for the aircraft ( 202 ) as a function of a wheel input command in a circumference display.

9. The method of claim 1 further comprising:

displaying an angle of attack for the aircraft ( 202 ) correlating to a column input ( 432 ).

10. The method of claim 1 further comprising:

displaying a slideslip for the aircraft ( 202 ) correlating to a pedal input ( 460 ).

11. The method of claim 1 , wherein the pilot control input signal ( 224 ) is generated by a control ( 212 ) located in one of the aircraft ( 202 ) and a simulator for the aircraft ( 202 ).

12. The method of claim 1 , wherein the aircraft ( 202 ) is a fly-by-wire aircraft ( 216 ).

13. A method for monitoring an aircraft ( 202 ), the method comprising:

receiving a pilot control input signal ( 224 );

identifying a response of a control surface system ( 206 ) controlled by a flight control model ( 230 ) using the pilot control input signal ( 224 );

modifying a display of the response of the control surface system ( 206 ) based on a range for a position of the control surface system ( 206 );

displaying, via a first indicator ( 408 , 436 , or 464 ) on a graphical user interface ( 236 ), the pilot control input signal ( 224 );

displaying, via a second indicator ( 412 ) on the graphical user interface ( 236 ), a command sent to the control surface system ( 206 ) in response to the pilot control input signal ( 224 ); and

displaying, via a third indicator ( 442 , 468 , or 444 ) on the graphical user interface ( 236 ), the response of the control surface system ( 206 ) to the command.

14. The method of claim 13 further comprising:

generating an alert ( 240 ) as the response indicates that the control surface system ( 206 ) is approaching a full deflection capability for the control surface system ( 206 );

wherein the pilot control input signal ( 224 ) is displayed via a first graphical element ( 408 , 436 , or 464 ) and a second graphical element ( 422 , 454 , or 478 ) and the second graphical element ( 422 , 454 , or 478 ) displays the pilot control input signal ( 224 ) as a numerical value; and

wherein the command is displayed via a third graphical element ( 412 , 442 , 444 , or 468 ) and a fourth graphical element ( 423 , 456 , 457 , and 480 ) and the fourth graphical element ( 423 , 456 , 457 , and 480 ) displays the command as a numerical value.

15. An apparatus comprising:

a flight monitor ( 204 ) configured to:

receive a pilot control input signal ( 224 ) for an aircraft ( 202 );

identify a response of a control surface system ( 206 ) controlled by a flight control model ( 230 ) using the pilot control input signal ( 224 );

generate an alert ( 240 ) when the control surface system ( 206 ) reaches a threshold ( 241 ) with respect to the control surface system ( 206 ) becoming saturated;

display, via a first indicator ( 408 , 436 , or 464 ) on a graphical user interface ( 236 ), the pilot control input signal ( 224 );

display, via a second indicator ( 412 ) on the graphical user interface ( 236 ), a command sent to the control surface system ( 206 ) in response to the pilot control input signal ( 224 ); and

display, via a third indicator ( 442 , 468 , or 444 ) on the graphical user interface ( 236 ), the response of the control surface system ( 206 ).

16. The apparatus of claim 15 ,

wherein the aircraft ( 202 ) is a fly-by-wire aircraft ( 216 ).

17. The apparatus of claim 16 , wherein the flight monitor ( 204 ) is further configured to modify a display of the response of the control surface system ( 206 ) based on a range for a position of a control surface prior to displaying the response on the graphical user interface ( 236 );

wherein the pilot control input signal ( 224 ) is displayed via a first graphical element ( 408 , 436 , or 464 ) and a second graphical element ( 422 , 454 , or 478 ) and the second graphical element ( 422 , 454 , or 478 ) displays the pilot control input signal ( 224 ) as a numerical value; and

wherein the command is displayed via a third graphical element ( 412 , 442 , 444 , or 468 ) and a fourth graphical element ( 423 , 456 , 457 , and 480 ) and the fourth graphical element ( 423 , 456 , 457 , and 480 ) displays the command as a numerical value.

18. The apparatus of claim 15 , wherein the flight monitor ( 204 ) is further configured to display a level of saturation ( 310 ) for a roll control surface.

19. The apparatus of claim 15 , wherein the flight monitor ( 204 ) is further configured to display a level of saturation ( 310 ) for a yaw control surface.

20. The apparatus of claim 15 , wherein the flight monitor ( 204 ) is further configured to display a level of saturation ( 310 ) for of a pitch control surface.

21. The apparatus of claim 15 , wherein the flight monitor ( 204 ) is further configured to display an indication of the control surface system ( 206 ) approaching the threshold ( 241 ).

22. The apparatus of claim 15 , wherein the flight monitor ( 204 ) is further configured to display a roll rate ( 406 ) for the aircraft ( 202 ) correlating to a wheel input command in a circumference display.

23. The apparatus of claim 15 , wherein the flight monitor ( 204 ) is further configured to display an angle of attack for the aircraft ( 202 ) as a function of a column input ( 432 ).

24. The apparatus of claim 15 , wherein the flight monitor ( 204 ) is further configured to display a slideslip for the aircraft ( 202 ) as a function of a pedal input ( 460 ).

25. The apparatus of claim 15 , wherein the pilot control input signal ( 224 ) is generated by a control ( 212 ) located in one of the aircraft ( 202 ) and a simulator for the aircraft ( 202 ).

26. An apparatus comprising:

a flight monitor ( 204 ) configured to:

receive a pilot control input signal ( 224 ) for an aircraft ( 202 );

identify a response of a control surface system ( 206 ) controlled by a flight control model ( 230 ) using the pilot control input signal ( 224 );

modify a display of the response of the control surface system ( 206 ) based on a range for a position of a control surface;

display, via a first indicator ( 408 , 436 , or 464 ) on a graphical user interface ( 236 ), the pilot control input signal ( 224 );

display, via a second indicator ( 412 ) on the graphical user interface ( 236 ), a command sent to the control surface system ( 206 ) in response to the pilot control input signal ( 224 ); and

display, via a third indicator ( 442 , 468 , or 444 ) on the graphical user interface, the response of the control surface system ( 206 ) to the command.

27. The apparatus of claim 26 , wherein the flight monitor ( 204 ) is further configured to:

generate an alert ( 240 ) as the response indicated that the control surface system ( 206 ) is approaching a saturation limit for the control surface system ( 206 );

wherein the pilot control input signal ( 224 ) is displayed via a first graphical element ( 408 , 436 , or 464 ) and a second graphical element ( 422 , 454 , or 478 ) and the second graphical element ( 422 , 454 , or 478 ) displays the pilot control input signal ( 224 ) as a numerical value; and

wherein the command is displayed via a third graphical element ( 412 , 442 , 468 , or 444 ) and a fourth graphical element ( 423 , 456 , 457 , and 480 ) and the fourth graphical element ( 423 , 456 , 457 , and 480 ) displays the command as a numerical value.

Assignments (1)
ASSIGNMENT OF ASSIGNOR'S INTEREST Recorded Mar 1, 2013
From: PENNELL, SEAN M.; AARON, NOAH ERIC; MCDONALD, DARREN GORDON
To: THE BOEING COMPANY
Reel/Frame 029906/0923 →
Continuity (1)
Related Publication 20140232568A1 · Aug 21, 2014