Aircraft monitoring system

• US 9,156,563 B2
• Filed: 10/01/2014
• Issued: 10/13/2015
• Est. Priority Date: 02/18/2013
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Pennell, Sean M., Aaron, Noah Eric, McDonald, Darren Gordon
• Primary Examiner(s): Swarthout, Brent
• Application Number:
  US14/504,127
• Publication Number:
  US 20150054663A1
• Time in Patent Office: 377 Days
• Field of Search: 340/967, 340/973, 340/975, 244/87, 701/3, 701/9, 701/120.EAS
• US Class Current: 1/1
• CPC Class Codes: B64C 13/503 Fly-by-Wire
• CPC Class Codes: B64D 45/00 Aircraft indicators or protectors not otherwise provided for camouflage F41H3/00
• CPC Class Codes: B64D 45/0005 Devices specially adapted to indicate the position of a movable element of the aircraft, e.g. landing gear
• CPC Class Codes: B64F 5/60 Testing or inspecting aircraft components or systems
• CPC Class Codes: G05D 1/0055 with safety arrangements
• CPC Class Codes: G05D 1/0816 to ensure stability
• CPC Class Codes: G08B 23/00 Alarms responsive to unspecified undesired or abnormal conditions

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

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 (413, 469, or 490) on the graphical user interface (236), a response of the aircraft.

2. The method of claim 1 further comprising:

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

3. 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.

4. The method of claim 1 further comprising:

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

5. The method of claim 1 further comprising:

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

6. The method of claim 1 further comprising:

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

7. The method of claim 1 further comprising:

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

8. The method of claim 1 further comprising:

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

9. 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.

10. The method of claim 1 further comprising:

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

11. The method of claim 1 further comprising:

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

12. 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).

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

14. 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 (413, 469, or 490) on the graphical user interface (236), a response of the aircraft.

15. The method of claim 14 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.

16. 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 (413, 469, or 490) on the graphical user interface (236), a response of the aircraft.

17. The apparatus of claim 16, wherein the aircraft (202) is a fly-by-wire aircraft (216).

18. The apparatus of claim 17, 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.

19. The apparatus of claim 16, wherein the flight monitor (204) is further configured to display a level of saturation (310) for a roll control surface.

20. The apparatus of claim 16, wherein the flight monitor (204) is further configured to display a level of saturation (310) for a yaw control surface.

21. The apparatus of claim 16, wherein the flight monitor (204) is further configured to display a level of saturation (310) for of a pitch control surface.

22. The apparatus of claim 16, wherein the flight monitor (204) is further configured to display an indication of the control surface system (206) approaching the threshold (241).

23. The apparatus of claim 16, 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.

24. The apparatus of claim 16, 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).

25. The apparatus of claim 16, wherein the flight monitor (204) is further configured to display a sideslip for the aircraft (202) as a function of a pedal input (460).

26. The apparatus of claim 16, 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).

27. 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 (413, 469, or 490) on the graphical user interface, a response of the aircraft.

28. The apparatus of claim 27, 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.