Methods and apparatus to extend a leading-edge vortex of a highly-swept aircraft wing

Patent metadata

Field	Value
Publication number	US-10967957-B2
Application number	US-201615385444-A
Country	US
Kind code	B2
Filing date	Dec 20, 2016
Priority date	Dec 20, 2016
Publication date	Apr 6, 2021
Grant date	Apr 6, 2021

Abstract

Methods, apparatus, and articles of manufacture to extend a leading-edge vortex of a highly-swept wing aircraft wing are disclosed. An example apparatus includes a shoulder wing coupled to a fuselage of an aircraft above a highly-swept wing of the aircraft, the shoulder wing operative in a first position to extend a leading-edge vortex spanwise along the highly-swept wing of the aircraft.

First claim

What is claimed is:

1. An apparatus comprising:
a shoulder wing coupled to a fuselage of an aircraft, the aircraft including a first highly-swept wing on a first side of the aircraft and a second highly-swept wing on a second side of the aircraft opposite the first side, the shoulder wing coupled to the fuselage on the first side of the aircraft above the first highly-swept wing, the shoulder wing operative to move from a first position to a second position to extend a leading-edge vortex spanwise along the first highly-swept wing of the aircraft;
a shoulder wing housing coupled to the fuselage, the shoulder wing housing to stow the shoulder wing in the first position; and
a door coupled to the shoulder wing housing, the door operative to move from a third position to a fourth position in response to the shoulder wing moving from the first position to the second position, the door operative to return to the third position in response to the shoulder wing moving to the second position.

2. The apparatus of claim 1 , further including an actuator to operatively couple the shoulder wing to the fuselage to move the shoulder wing from the first position to the second position in a counter-clockwise direction.

3. The apparatus of claim 2 , wherein the shoulder wing is behind a leading-edge of the first highly-swept wing, and the first position is at a first angle relative to a longitudinal axis of the fuselage and the second position is at a second angle relative to the longitudinal axis of the fuselage, the second angle different than the first angle.

4. The apparatus of claim 1 , further including a slat coupled to the shoulder wing facing a first direction of the aircraft and a flap coupled to the shoulder wing facing a second direction of the aircraft.

5. The apparatus of claim 4 , wherein the slat is operatively coupled to the shoulder wing via a slat actuator to further extend the leading-edge vortex spanwise along the first highly-swept wing of the aircraft.

6. The apparatus of claim 4 , wherein the flap is operatively coupled to the shoulder wing via a flap actuator to further extend the leading-edge vortex spanwise along the first highly-swept wing of the aircraft.

7. The apparatus of claim 4 , further including at least one of a second slat, a second slat actuator, a second flap, or a second flap actuator.

8. The apparatus of claim 1 , further including at least one perforation on the shoulder wing, the perforation enabling an expulsion of pressurized air to further extend the leading-edge vortex spanwise along the first highly-swept wing of the aircraft.

9. The apparatus of claim 1 , wherein the aircraft is a tailless aircraft.

10. The apparatus of claim 1 , wherein the shoulder wing in the second position delays a burst of the leading-edge vortex to increase a lift-to-drag ratio of the aircraft.

11. The apparatus of claim 1 , further including an actuator to operatively couple the shoulder wing to the fuselage to move the shoulder wing from the first position to the second position in a counter-clockwise direction and to move the shoulder wing from the second position to the first position in a clockwise direction.

12. A non-transitory computer readable storage medium comprising instructions that, when executed, cause at least one processor to at least:
control a housing door operatively coupled to a shoulder wing housing of an aircraft to move from a first position to a second position, the shoulder wing housing to stow a shoulder wing of the aircraft in a third position, the aircraft including a first highly-swept wing on a first side of the aircraft and a second highly-swept wing on a second side of the aircraft, the second side opposite the first side, the shoulder wing coupled to a fuselage of the aircraft on the first side above the first highly-swept wing, the shoulder wing housing coupled to the fuselage;
in response to the housing door moving to the second position, control the shoulder wing to move from the third position to a fourth position, the shoulder wing in the fourth position to extend a leading-edge vortex spanwise along a leading-edge of the first highly-swept wing of the aircraft; and
in response to the shoulder wing moving to the fourth position, control the housing door to move from the second position to the first position.

13. The non-transitory computer readable storage medium of claim 12 , wherein the instructions, when executed, cause the at least one processor to:
obtain a flight condition associated with the aircraft from a sensor;
determine to increase a first quantity of lift being generated by the first highly-swept wing of the aircraft to a second quantity of lift greater than the first quantity of lift based on the flight condition; and
determine to move the shoulder wing to the fourth position to generate the second quantity of lift.

14. The non-transitory computer readable storage medium of claim 13 , wherein the flight condition is a first flight condition, and the instructions, when executed, cause the at least one processor to:
determine to increase the second quantity of lift to a third quantity of lift greater than the second quantity of lift based on a second flight condition associated with the aircraft obtained from the sensor; and
deploy at least one of a slat or a flap operatively coupled to the shoulder wing to move from a fifth position to a sixth position, the at least one of the slat or the flap in the sixth position to generate the third quantity of lift by further extending the leading-edge vortex spanwise along the leading-edge of the first highly-swept wing.

15. The non-transitory computer readable storage medium of claim 12 , wherein the instructions, when executed, cause the shoulder wing to move to the fourth position to adjust the leading-edge vortex from moving above the leading edge of the first highly-swept wing at a first angle relative to a longitudinal axis of the aircraft to moving spanwise along the leading edge at a second angle relative to the longitudinal axis, the second angle greater than the first angle.

16. A method comprising:
controlling a housing door operatively coupled to a shoulder wing housing of an aircraft to move from a first position to a second position, the shoulder wing housing to stow a shoulder wing of the aircraft in a third position, the aircraft including a first highly-swept wing on a first side of the aircraft and a second highly-swept wing on a second side of the aircraft, the second side opposite the first side, the shoulder wing coupled to a fuselage of the aircraft on the first side above the first highly-swept wing, the shoulder wing housing coupled to the fuselage;
in response to the housing door moving to the second position, controlling the shoulder wing to move from the third position to a fourth position, the shoulder wing in the fourth position to extend a leading-edge vortex spanwise along a leading-edge of the first highly-swept wing of the aircraft; and
in response to the shoulder wing moving to the fourth position, controlling the housing door to move from the second position to the first position.

17. The method of claim 16 , further including:
obtaining a flight condition associated with the aircraft from a sensor;
determining to increase a first quantity of lift being generated by the first highly-swept wing of the aircraft to a second quantity of lift greater than the first quantity of lift based on the flight condition; and
determining to move the shoulder wing to the fourth position to generate the second quantity of lift.

18. Th

Assignees

• Boeing Co

Inventors

• Harrison Neal A
• Sclafani Anthony J
• Gea Lie-Mine

Classifications

• B64C1/0009

  Aerodynamic aspects · CPC title

• B64C3/10

  Shape of wings · CPC title

• Y02T50/10

  Drag reduction · CPC title

• Y02T50/40

  Weight reduction · CPC title

• B64C23/06 Primary

  by generating vortices · CPC title