Aircraft movement control system

Patent metadata

Field	Value
Publication number	US-11053016-B1
Application number	US-201916259231-A
Country	US
Kind code	B1
Filing date	Jan 28, 2019
Priority date	Jan 28, 2019
Publication date	Jul 6, 2021
Grant date	Jul 6, 2021

Abstract

Controlling a movement of an aircraft. A computer system detects a position of a group of integrated control levers for the aircraft. The computer system controls a forward thrust, a drag, and a reverse thrust generated by the aircraft based on the position of the group of integrated control levers.

First claim

What is claimed is:

1. An aircraft control system that comprises:
an engine configured to generate a forward thrust for an aircraft;
a speed brake configured to generate a drag for the aircraft;
an integrated control lever for the aircraft, wherein the integrated control lever is configured to move to different positions that comprise: a first range of positions, a second range of positions adjacent to the first range of positions, and a third range of positions adjacent the second range of positions;
an interlock at the third range of positions, wherein the interlock is configured to prevent a movement of the integrated control lever within the third range of positions when the aircraft is in air;
a thrust reverser on the engine and configured to generate a reverse thrust from the engine; and
a computer system located in the aircraft and configured to control:
the forward thrust, the drag, and the reverse thrust based on a position of the integrated control lever in the different positions; and
a removal of the interlock when the aircraft is on a ground.

2. The aircraft control system of claim 1 , wherein the computer system is further configured to control:
the forward thrust as a variable forward thrust without a generation of the drag from the speed brake and the reverse thrust from the thrust reverser based on the position of the integrated control lever within the first range of positions;
the drag as a variable drag with the forward thrust as an idle forward thrust and without the reverse thrust based on the position of the integrated control lever within the second range of positions; and
the drag as a full drag and the reverser thrust as a variable reverse thrust without the forward thrust based on the position of the integrated control lever within the third range of positions.

3. The aircraft control system of claim 2 further comprising:
a lockout at the third range of positions and configured to prevent a movement of the integrated control lever into the third range of positions when the aircraft is in air; and
a switch configured to remove the lockout when the aircraft is on ground.

4. The aircraft control system of claim 2 , wherein a first tactile detent is present for the second range of positions, and a second tactile detent is present for the third range of positions.

5. The aircraft control system of claim 1 , wherein the computer system is further configured to control a braking friction generated by wheel brakes for the aircraft based on the position of the integrated control lever.

6. The aircraft control system of claim 5 , wherein a tactile detent is located at an entrance to the second range of positions.

7. The aircraft control system of claim 1 , wherein the computer system comprises a group of flight control systems that generate commands for: a group of engines, air brakes, and a number of thrust revers in the group of engines based on the position of the integrated control lever.

8. The aircraft control system of claim 1 , wherein the speed brake is selected from at least one of a control surface, a spoiler, a hydraulic tail cone clamshell air brake, a deceleron, a rudder configured to vertically split, a wing leading edge device, a flap, or an air brake panel.

9. The aircraft control system of claim 1 , wherein the thrust reverser is located in the engine.

10. The aircraft control system of claim 1 , wherein the aircraft is selected from a group that consists of: an airplane, a jet, a passenger jet airplane, a military jet aircraft, a propeller airplane, an unmanned aerial vehicle, and a refueling tanker.

11. An aircraft control system that comprises a computer system located in an aircraft and configured to:
detect a position of an integrated control lever configured to control the following:
a forward thrust, a drag, and a reverse thrust of the aircraft based on the position of the integrated control lever; and
a movement of the integrated control lever to different positions within a first range of positions, a second range of positions adjacent to the first range of positions, and a third range of positions adjacent the second range of positions, wherein a first tactile detent is located at an entrance of the second range of positions and second tactile detent is present in the third range of positions.

12. The aircraft control system of claim 11 , wherein the computer system is configured to control the aircraft to generate the following:
the forward thrust as a variable thrust without the drag and without the reverse thrust based on the position of the integrated control lever within the first range of positions;
a variable drag with the forward thrust as an idle forward thrust and the reverse thrust based on the position of the integrated control lever within the second range of positions; and
a full drag and generate the reverse thrust as a variable reverse thrust without the forward thrust based on the position of the integrated control lever within the third range of positions.

13. The aircraft control system of claim 12 further comprising an interlock located at the third range of positions and configured to:
prevent the movement of the integrated control lever within the third range of positions when the aircraft is in air; and
be removed when a group of conditions is present.

14. The aircraft control system of claim 11 , wherein the computer system is configured to control the aircraft to generate the following:
the forward thrust as a variable forward thrust without the drag and without the reverse thrust based on the position of the integrated control lever within the first range of positions;
the drag as a variable drag with the forward thrust as an idle forward thrust and without the reverse thrust based on the position of the integrated control lever within the second range of positions when the aircraft is in air; and
a full drag and generate the reverse thrust as a variable reverse thrust with the idle forward thrust based on the position of the integrated control lever within the second range of positions when the aircraft is on ground.

15. The aircraft control system of claim 11 , further comprising:
an engine configured to respond to the computer system to generate the forward thrust; and
a thrust reverser in the engine and configured to respond to the computer system to generate the reverse thrust from the engine.

16. The aircraft control system of claim 15 , wherein the thrust reverser is located in the engine.

17. The aircraft control system of claim 11 , further comprising:
a flight control surface system configured to respond to the computer system to generate the drag for the aircraft, wherein the flight control surface system is selected from at least one of: a control surface, a spoiler, a hydraulic tail cone clamshell air brake, a fuselage-mounted air brake, a deceleron, a rudder configured to vertically split, a wing leading edge device, a flap, or an air brake panel.

18. The aircraft control system of claim 11 , wherein the aircraft is selected from a group consisting of: an airplane, a jet, a passenger jet airplane, a military jet aircraft, a propeller airplane, an unmanned aerial vehicle, and a refueling tanker.

19. The aircraft control system of claim 11 , wherein the computer system is further configured to control the forward thrust, the drag, the reverse thrust, and a braking friction generated by wheel brakes for the aircraft based on the position of the integrated control lever.

20. A method for controlling

Assignees

• Boeing Co

Inventors

• Lassen Matthew August
• Elliott Joseph E
• Burrington Stephen Todd
• Myers Robert James
• Karnofski Kent E
• Staggs Thomas Jenkins

Classifications

• Y02T50/40

  Weight reduction · CPC title

• B64D31/04 Primary

  actuated personally · CPC title

• B64C13/14

  lockable · CPC title

• B64C13/042

  operated by hand · CPC title

• G05G2505/00

  Means for preventing, limiting or returning the movements of parts of a control mechanism, e.g. locking controlling member · CPC title