Leading edge flap apparatuses and associated methods

• US 20060102803A1
• Filed: 09/30/2004
• Published: 05/18/2006
• Est. Priority Date: 09/30/2004
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Wheaton, James M., Amorosi, Stephen R.
• Granted Patent: US 7,264,206 B2
• Time in Patent Office: Days
• US Class Current: 244/214
• CPC Class Codes: B64C 7/02 Nacelles
• CPC Class Codes: B64C 9/22 at the front of the wing
• CPC Class Codes: B64C 9/24 by single flap
• CPC Class Codes: Y02T 50/30 Wing lift efficiency
• CPC Class Codes: Y02T 50/40 Weight reduction

Abstract

The present invention is directed generally toward leading edge flap apparatuses and corresponding methods. One aspect of the invention is directed toward an aircraft system having an airfoil, an actuator driver, and a leading edge device with two flow surfaces and six links. In a further aspect of the invention, the flow surfaces of the leading edge device are at least approximately located in the same position when the actuator driver is in two different positions. Another aspect of the invention is directed toward an aircraft system having an airfoil and a leading edge device movable between at least a retracted position and an extended position along a motion path having two segments. The second flow surface can be positioned generally behind and/or generally above the first flow surface when the first and second flow surfaces are located in the first segment of the motion path.

Claims

1. An aircraft system, comprising:

an airfoil having a leading edge, a lower surface, and a chord line; and

a leading edge device having a first flow surface and a second flow surface,

the first flow surface being coupled to the airfoil and the second flow surface being coupled to the first flow surface, the leading edge device being movable along a motion path among;

a retracted position;

an extended position; and

an intermediate position with the first flow surface at least approximately perpendicular to the chord line of the airfoil, and wherein the motion path has;

a first segment between the retracted position and the intermediate position along which the second flow surface is positioned at least one of generally behind and generally above the first flow surface; and

a second segment between the extended position and the intermediate position.

2. The system of claim 1, further comprising a fuselage coupled to the airfoil and an engine coupled to at least one of the airfoil and the fuselage.

3. The system of claim 1, further comprising an engine having an engine nacelle, the engine nacelle being proximate to the airfoil, and wherein at least a portion of the leading edge device is at least approximately aerodynamically sealed against the engine nacelle when the leading edge device is in the extended position.

4. The system of claim 1, further comprising an engine having an engine pylon, the engine pylon being proximate to the airfoil, and wherein at least a portion of the leading edge device is at least approximately aerodynamically sealed against the engine pylon when the leading edge device is in the extended position.

5. The system of claim 1, further comprising an engine proximate to the airfoil, the engine having a thrust reverser and an engine nacelle, a portion of the engine nacelle being coupled to the thrust reverser to move when the thrust reverser is deployed, and wherein at least a portion of the leading edge device moves with the portion of the engine nacelle when the leading edge device is in the extended position.

6. The system of claim 1 wherein the leading edge device includes a first leading edge device, and wherein the method further comprises a second leading edge device laterally disposed from the first leading edge device, the second leading edge device having an extended position, wherein at least a portion of the first leading edge device is at least approximately aerodynamically sealed against a portion of a lateral edge of the second leading edge device when the first leading edge device is in the extended position and the second leading edge device is in the extended position.

7. The system of claim 1 wherein the second flow surface is discontinuous with the first flow surface while the leading edge device is in the first segment of the motion path.

8. An aircraft system, comprising:

an airfoil;

an actuator driver coupled to the airfoil; and

a leading edge device having;

a first flow surface coupled to the airfoil;

a second flow surface coupled to the first flow surface;

a first link being pivotally coupled to the actuator driver;

a second link being pivotally coupled to the airfoil and to the first link;

a third link being pivotally coupled to the second link and to the first flow surface;

a fourth link being pivotally coupled to the airfoil;

a fifth link being pivotally coupled to the fourth link and to the first flow surface, and wherein;

(a) the second link is coupled to both the first link and the third link at a first common point;

or

(b) both the third link and the fifth link are pivotally coupled to the first flow surface at a second common point;

or

both (a) and (b); and

a sixth link being coupled to the fifth link and the second flow surface.

9. The system of claim 8 wherein the actuator driver is movable among at least three stationary positions including a first position, a second position, and a third position and wherein the first and second flow surfaces of the leading edge device are located in at least approximately the same position when the actuator driver is in the first and second position.

10. The system of claim 8 wherein the actuator driver includes at least one of a mechanical actuator, a hydraulic actuator, an electric actuator, and a pneumatic actuator.

11. The system of claim 8 wherein the leading edge device includes a Krueger flap.

12. The system of claim 8 wherein the airfoil includes a lower surface and a leading edge, the actuator driver includes a torque tube having a top portion facing away from the lower surface of the airfoil, and the leading edge device is movable between at least two stationary positions, including:

a retracted position wherein the first and second flow surfaces are positioned generally behind the leading edge of the airfoil to form a portion of the lower surface of the airfoil; and

an extended position wherein the first and second flow surfaces are positioned to form an extension of the leading edge of the airfoil, and wherein the first link of the leading edge device is coupled to the actuator driver to move the leading edge device from the retracted position to the extended position when the torque tube rotates such that the top portion of the torque tube moves towards the leading edge of the airfoil.

13. The system of claim 8 wherein the airfoil includes a lower surface, a leading edge, and a chord line, and wherein the leading edge device is movable along a motion path among:

a retracted position;

an extended position; and

an intermediate position with the first flow surface at least approximately perpendicular to the chord line of the airfoil, and wherein the motion path has;

a first segment between the retracted position and the intermediate position along which the second flow surface is positioned at least one of generally behind and generally above the first flow surface; and

a second segment between the extended position and the intermediate position.

14. The system of claim 8, further comprising a fuselage coupled to the airfoil and an engine coupled to at least one of the airfoil and the fuselage.

15. The system of claim 8 wherein the airfoil includes a lower surface, and a leading edge, and wherein the system further comprises an engine pylon proximate to the airfoil, and further wherein the leading edge device is movable between at least two stationary positions, including:

a retracted position; and

an extended position wherein at least a portion of the leading edge device is at least approximately aerodynamically sealed against the engine pylon when the leading edge device is in the extended position.

16. The system of claim 8 wherein the airfoil includes a lower surface, and a leading edge, and wherein the system further comprises an engine having an engine nacelle proximate to the airfoil, and further wherein the leading edge device is movable between at least two stationary positions, including:

a retracted position; and

an extended position wherein at least a portion of the leading edge device is at least approximately aerodynamically sealed against the engine nacelle when the leading edge device is in the extended position.

17. The system of claim 8 wherein the airfoil includes a lower surface, and a leading edge, and wherein the system further comprises an engine proximate to the airfoil, the engine having an engine nacelle and a thrust reverser, a portion of the engine nacelle being coupled to the thrust reverser to move when the thrust reverser is deployed, and further wherein the leading edge device is movable between at least two stationary positions, including:

a retracted position; and

an extended position wherein at least a portion of the leading edge device moves with the portion of the engine nacelle when the leading edge device is in the extended position.

18. The system of claim 8 wherein the leading edge device includes a first leading edge device, the airfoil includes a lower surface, and a leading edge, and the system further comprises a second leading edge device laterally disposed from the first leading edge device, the second leading edge device having an extended position, and wherein the first leading edge device is movable between at least two stationary positions, including:

a retracted position; and

an extended position wherein at least a portion of the first leading edge device is at least approximately aerodynamically sealed against a portion of a lateral edge of the second leading edge device when the first leading edge device is in the extended position and the second leading edge device is in the extended position.

19. A method for making an aircraft system, comprising:

coupling a first flow surface and a second flow surface;

providing first, second, third, fourth, fifth and sixth links;

pivotally coupling the first link to the second link;

pivotally coupling the fourth link to the fifth link;

pivotally coupling the fifth link to the first flow surface, and;

(a) pivotally coupling the second link to both the first link and the third link at a first common point;

or

(b) pivotally coupling both the third link and the fifth link to the first flow surface at a second common point;

or

both (a) and (b);

pivotally coupling the sixth link to the fifth link; and

pivotally coupling the sixth link to the second flow surface.

20. The method of claim 19, further comprising:

providing an aircraft with an airfoil;

coupling the second link to the airfoil;

coupling the fourth link to the airfoil; and

coupling the first link to an actuator driver.

21. The method of claim 19, further comprising:

providing an aircraft with an airfoil, the airfoil having a lower surface and a leading edge;

coupling the second link to the airfoil;

coupling the fourth link to the airfoil; and

coupling the first link to an actuator driver, wherein the actuator driver includes a torque tube having a top portion facing away from the lower surface of the airfoil, and wherein;

the leading edge device is movable between at least two stationary positions, including;

a retracted position; and

an extended position; and

the leading edge device moves from the retracted position to the extended position when, as the torque tube rotates, a top portion of the torque tube moves toward the leading edge of the airfoil.

22. The method of claim 19, further comprising:

providing an aircraft with an airfoil, the airfoil having a lower surface and a leading edge;

coupling the second link to the airfoil; and

coupling the fourth link to the airfoil wherein the leading edge device is movable along a motion path among;

a retracted position;

an extended position; and

an intermediate position with the first flow surface at least approximately perpendicular to the chord line of the airfoil, and wherein the motion path has;

a first segment between the retracted position and the intermediate position along which the second flow surface is positioned at least one of generally behind and generally above the first flow surface; and

a second segment between the extended position and the intermediate position.

23. The method of claim 19, further comprising:

providing an aircraft with an airfoil;

coupling the second link to the airfoil;

coupling the fourth link to the airfoil; and

coupling the first link to an actuator driver, wherein the actuator driver is movable among at least three stationary positions including a first position, a second position, and a third position and wherein the first and second flow surfaces of the leading edge device are located in at least approximately the same position when the actuator driver is in the first and second position.

24. The method of claim 19, further comprising:

providing an aircraft with an airfoil and an engine pylon proximate to the airfoil, the airfoil having a lower surface and a leading edge;

coupling the second link to the airfoil; and

coupling the fourth link to the airfoil, wherein the leading edge device is movable between at least two stationary positions, including;

a retracted position; and

an extended position wherein at least a portion of the leading edge device is at least approximately aerodynamically sealed against the engine pylon when the leading edge device is in the extended position.

25. The method of claim 19, further comprising:

providing an aircraft with an airfoil and an engine proximate to the airfoil, the airfoil having a lower surface and a leading edge, the engine having an engine nacelle;

coupling the second link to the airfoil; and

coupling the fourth link to the airfoil, wherein the leading edge device is movable between at least two stationary positions, including;

a retracted position; and

an extended position wherein at least a portion of the leading edge device is at least approximately aerodynamically sealed against the engine nacelle when the leading edge device is in the extended position.

26. The method of claim 19, further comprising:

providing an aircraft with an airfoil and an engine proximate to the airfoil, the engine having an engine nacelle and a thrust reverser, a portion of the engine nacelle being coupled to the thrust reverser to move when the thrust reverser is deployed, the airfoil having a lower surface and a leading edge;

coupling the second link to the airfoil; and

coupling the fourth link to the airfoil, wherein the leading edge device is movable between at least two stationary positions, including;

a retracted position; and

an extended position wherein at least a portion of the leading edge device moves with the portion of the engine nacelle that moves with a thrust reverser when the leading edge device is in the extended position.

27. The method of claim 19 wherein the leading edge device includes a first leading edge device, and wherein the method further comprises:

providing an aircraft with an airfoil, the airfoil having a lower surface, a leading edge, and a second leading edge device laterally disposed from the first leading edge device, the second leading edge device having an extended position;

coupling the second link to the airfoil; and

coupling the fourth link to the airfoil, wherein the leading edge device is movable between at least two stationary positions, including;

a retracted position; and

an extended position wherein at least a portion of the first leading edge device is at least approximately aerodynamically sealed against a portion of a lateral edge of a second leading edge device when the first leading edge device is in the extended position and the second leading edge device is in the extended position.

28. A method of making an aircraft system, comprising:

configuring a leading edge device to be couplable to an airfoil, the airfoil having a leading edge, a lower surface, and a chord line, the leading edge device having a first flow surface and a second flow surface; and

configuring the leading edge device to be movable along a motion path among;

a retracted position;

an extended position; and

an intermediate portion with the first flow surface at least approximately perpendicular to the chord line of the airfoil, and wherein the motion path has;

a first segment between the retracted position and the intermediate position along which the second flow surface is positioned at least one of generally behind and generally above the first flow surface; and

a second segment between the extended position and the intermediate position.

29. The method of claim 28, further comprising:

providing an aircraft having an airfoil; and

coupling the leading edge device to the airfoil.

30. The method of claim 28, further comprising:

providing an aircraft having an airfoil and an engine with an engine pylon, the engine pylon being proximate to the airfoil; and

coupling the leading edge device to the airfoil wherein at least a portion of the leading edge device is at least approximately aerodynamically sealed against the engine pylon when the leading edge device is in the extended position.

31. The method of claim 28, further comprising:

providing an aircraft having an airfoil and an engine with an engine nacelle, the engine nacelle being proximate to the airfoil; and

coupling the leading edge device to the airfoil wherein at least a portion of the leading edge device is at least approximately aerodynamically sealed against the engine nacelle when the leading edge device is in the extended position.

32. The method of claim 28, further comprising:

providing an aircraft with an airfoil and an engine proximate to the airfoil, the engine having an engine nacelle and a thrust reverser, a portion of the engine nacelle being coupled to the thrust reverser to move when the thrust reverser is deployed; and

coupling the leading edge device to the airfoil wherein at least a portion of the leading edge device moves with the portion of the engine nacelle that moves with the thrust reverser when the leading edge device is in the extended position.

33. The method of claim 28 wherein the leading edge device includes a first leading edge device, and wherein the method further comprises:

providing an aircraft with an airfoil, the airfoil having a second leading edge device with a lateral edge and an extended position; and

coupling the first leading edge device to the airfoil adjacent to the second leading edge device, wherein at least a portion of the first leading edge device is at least approximately aerodynamically sealed against a portion of the lateral edge of the second leading edge device when the first leading edge device is in the extended position and the second leading edge device is in the extended position.

34. A method for configuring an aircraft for various phases of flight, comprising moving a leading edge device from a stationary retraced position to a stationary extended position, the leading edge device being coupled to an airfoil and having a first and second flow surface, and wherein the second flow surface remains positioned at least one of generally behind and generally above the first flow surface while moving from the retracted to the extended position until the first flow surface passes through an intermediate position where the first flow surface is at least approximately perpendicular to a chord line of the airfoil.

35. The method of claim 34, further comprising operating the aircraft with the leading edge device in at least one of the retracted position and the extended position.

36. An aircraft system, comprising:

an airfoil having a leading edge, a lower surface, and a chord line; and

leading edge means for forming a retractable extension of the leading edge of the airfoil, the leading edge means having a first flow surface and a second flow surface, the leading edge means coupled to the airfoil and movable along a motion path among;

a retracted position;

an extended position, and

an intermediate position with the first flow surface at least approximately perpendicular to the chord line of the airfoil, and wherein the motion path has;

a first segment between the retracted position and the intermediate position along which the second flow surface is positioned at least one of generally behind and generally above the first flow surface; and

a second segment between the extended position and the intermediate position.

37. The system of claim 36, further comprising a fuselage coupled to the airfoil and an engine coupled to at least one of the airfoil and the fuselage.

38. An aircraft system, comprising:

an airfoil;

an actuator driver coupled to the airfoil,

leading edge means for forming a retractable extension of the leading edge of the airfoil, the leading edge means having;

a first flow surface coupled to the airfoil;

a second flow surface coupled to the first flow surface;

a first link being pivotally coupled to the actuator driver;

a second link being pivotally coupled to the airfoil and to the first link;

a third link being pivotally coupled to the second link and to the first flow surface;

a fourth link being pivotally coupled to the airfoil;

a fifth link being pivotally coupled to the fourth link and to the first flow surface, and wherein;

(a) the second link is coupled to both the first link and the third link at a first common point;

or

(b) both the third link and the fifth link are pivotally coupled to the first flow surface at a second common point;

or

both (a) and (b); and

a sixth link being coupled to the fifth link and the second flow surface.

39. The system of claim 38 wherein the actuator driver is movable among at least three stationary positions including a first position, a second position, and a third position and wherein the first and second flow surfaces of the leading edge means are located in at least approximately the same position when the actuator driver is in the first and second position.

40. The system of claim 38, further comprising a fuselage coupled to the airfoil and an engine coupled to at least one of the airfoil and the fuselage.