Controlling aircraft using thrust differential trim

Patent metadata

Field	Value
Publication number	US-10005561-B2
Application number	US-201615184196-A
Country	US
Kind code	B2
Filing date	Jun 16, 2016
Priority date	Jun 16, 2016
Publication date	Jun 26, 2018
Grant date	Jun 26, 2018

Abstract

Systems and methods for stabilizing an aircraft in response to a yaw movement are provided. In one embodiment, a method includes detecting a yaw movement of the aircraft. The yaw movement can cause a front portion of the aircraft to move towards a first side of the aircraft. The method can further include, in response to the yaw movement, initiating a trim process resulting in a thrust differential. The trim process can include increasing thrust in one or more engines on the first side of the aircraft and decreasing thrust in one or more engines on a second side of the aircraft. The method can include controlling the trim process based at least in part on a detected yaw movement of the aircraft.

First claim

What is claimed is:

1. An aircraft comprising:
one or more first engines located on a first side of the aircraft;
one or more second engines located on a second side of the aircraft;
a rudder;
a computing system comprising one or more processors and one or more memory devices located on the aircraft, the one or more memory devices storing instructions that when executed by the one or more processors cause the one or more processors to perform operations comprising:
detecting a rudder deflection on a first side of the aircraft; and
performing a trim process in response to the rudder deflection, the trim process comprising:
determining an angle of the rudder;
controlling one or more of the one or more first engines to increase thrust;
controlling one or more of the one or more second engines to decrease thrust; and
repeating the trim process when the angle of the rudder is not within a threshold amount of zero degrees.

2. A method for controlling an aircraft in response to a yaw movement comprising:
detecting a yaw movement of the aircraft, the yaw movement causing a front portion of the aircraft to move towards a first side of the aircraft;
in response to the yaw movement, initiating a trim process resulting in a thrust differential, the trim process comprising:
increasing thrust in one or more engines on the first side of the aircraft; and
decreasing thrust in one or more engines on a second side of the aircraft; and

controlling the trim process based at least in part on a detected yaw movement of the aircraft,

wherein controlling the trim process based at least in part on a detected yaw movement comprises:
determining when the trim process negates the yaw movement;
repeating the trim process when the trim process does not negate the yaw movement; and
maintaining the thrust differential when the trim process negates the yaw movement, and
wherein a drag on the aircraft during the trim process is generally consistent with or lower than a drag on the aircraft prior to the trim process.

3. The method of claim 2 , wherein detecting the yaw movement of the aircraft comprises detecting that a rudder is deflected.

4. The method of claim 2 , wherein the determining when the trim process negates the yaw movement comprises determining when a rudder angle is within a threshold amount of zero degrees.

5. The method of claim 2 , wherein a rate of fuel consumption while the thrust differential is maintained is generally consistent with or lower than a rate of fuel consumption prior to the trim process.

6. The method of claim 2 , wherein the increase of thrust in the one or more engines on the first side of the aircraft is equal to the decrease of thrust in the one or more engines on the second side of the aircraft.

7. The method of claim 2 , wherein detecting the yaw movement of the aircraft comprises detecting that the aircraft has deviated from a flight plan by a threshold.

8. The method of claim 2 , wherein detecting the yaw movement of the aircraft comprises detecting non-responsiveness of one or more controls.

9. The method of claim 2 , wherein detecting the yaw movement of the aircraft comprises detecting a disruption in one or more of the one or more engines on the first side.

10. The method of claim 9 , wherein the disruption is in response to foreign object damage (FOD).

11. The method of claim 2 , wherein detecting the yaw movement of the aircraft comprises receiving first yaw movement data via one or more yaw movement sensors.

12. The method of claim 11 , wherein determining when the trim process negates the yaw movement comprises receiving second yaw movement data via the one or more yaw movement sensors.

13. A method for controlling an aircraft in response to a yaw movement comprising:
detecting a yaw movement of the aircraft, the yaw movement causing a front portion of the aircraft to move towards a first side of the aircraft;
in response to the yaw movement, initiating a trim process resulting in a thrust differential, the trim process comprising:
increasing thrust in one or more engines on the first side of the aircraft; and
decreasing thrust in one or more engines on a second side of the aircraft; and

controlling the trim process based at least in part on a detected yaw movement of the aircraft,
wherein controlling the trim process based at least in part on a detected yaw movement of the aircraft:
detecting that a force causing the yaw movement has ceased to act on the aircraft; and
ceasing to maintain the thrust differential in response to detecting that the force causing the yaw movement has ceased to act on the aircraft, and
wherein a rate of fuel consumption after the thrust differential is ceased to be maintained is generally consistent with the rate of fuel consumption while the thrust differential is maintained.

14. The method of claim 13 , wherein a drag on the aircraft after the thrust differential is ceased to be maintained is generally consistent with a drag on the aircraft while the thrust differential is maintained.

Assignees

• Ge Aviation Systems Llc

Inventors

• Kiebles Steven Louis
• Lax David Michael
• Darias Otto Y
• Darnell Mark Lawrence
• Hwang Sean Sanghyun
• Holbert Christopher Daniel
• Mathews Jr Harry Kirk
• Adibhatla Sridhar
• Bult Jeffrey Russell
• Swager Thomas Charles

Classifications

• B64C15/02 Primary

  the jets being propulsion jets · CPC title

• B64C17/00 Primary

  Aircraft stabilisation not otherwise provided for · CPC title

• B64D45/00

  Aircraft indicators or protectors not otherwise provided for · CPC title

• G05D1/0808

  specially adapted for aircraft · CPC title

• G05D1/0816

  to ensure stability · CPC title