Aerospace vehicle leading edge slat devices and corresponding methods

• US 20060169847A1
• Filed: 01/31/2005
• Published: 08/03/2006
• Est. Priority Date: 01/31/2005
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Konings, Christopher A.
• Granted Patent: US 7,322,547 B2
• Time in Patent Office: Days
• US Class Current: 244/214
• CPC Class Codes: B64C 2003/146 comprising leading edges of particular shape
• CPC Class Codes: B64C 2009/143 comprising independently adjustable elements for closing or opening the slot between the main wing and leading or trailing edge flaps
• CPC Class Codes: B64C 2230/06 by explicitly adjusting fluid flow, e.g. by using valves, variable aperture or slot areas, variable pump action or variable fluid pressure
• CPC Class Codes: B64C 3/50 by leading or trailing edge flaps
• CPC Class Codes: B64C 9/22 at the front of the wing
• CPC Class Codes: B64C 9/26 by multiple flaps
• CPC Class Codes: Y02T 50/10 Drag reduction

Abstract

Aerospace vehicle leading edge slat devices and corresponding methods are generally disclosed herein. One aspect of the invention is directed toward an aerospace vehicle system that includes an airfoil having a leading edge. The system further includes a first flow body fixedly coupled to the airfoil to form at least one gap between the leading edge of the airfoil and the first flow body. A second flow body can be coupled to the airfoil and can be movable between at least a retracted position where the second flow body is positioned to at least approximately aerodynamically seal the at least one gap, and an extended position where the second flow body is positioned to allow fluid flow through the at least one gap.

Claims

1. An aerospace vehicle system, comprising:

an airfoil having a leading edge;

a first flow body fixedly coupled to the airfoil to form at least one gap between the leading edge of the airfoil and the first flow body; and

a second flow body movably coupled to the airfoil and being movable between;

a retracted position where the second flow body is positioned to at least approximately aerodynamically seal the at least one gap; and

an extended position where the second flow body is positioned to allow fluid flow through the at least one gap.

2. The system of claim 1, further comprising an actuation device coupled to the second flow body to move the second flow body, the actuation device including at least one of a hydraulic actuator, a mechanical actuator, a pneumatic actuator, and an electric actuator.

3. The system of claim 1 wherein the at least one gap includes a tapered gap.

4. The system of claim 1 wherein the at least one gap includes at least one first gap and the extended position of the second flow body includes a first extended position, and wherein the second flow body is movable to a second extended position where the second flow body is positioned to allow fluid flow through the at least one first gap and to form at least one second gap between the second flow body and the first flow body.

5. The system of claim 1 wherein the at least one gap includes at least one first gap and the extended position of the second flow body includes a first extended position, and wherein the second flow body is movable between:

a second extended position where the second flow body is positioned to allow fluid flow through the at least one first gap and to allow fluid flow through at least one second gap between the second flow body and the first flow body, the at least one second gap having a first distance between the second flow body and the first flow body; and

a third extended position where the second flow body is positioned to allow fluid flow through the at least one first gap and the at least one second gap, the at least one second gap having a second distance between the second flow body and the first flow body, the second distance being different than the first distance.

6. The system of claim 1 wherein the at least one gap includes a first gap, and wherein the system further comprises a third flow body fixedly coupled to the leading edge of the airfoil, the third flow body positioned to form a second gap between the first flow body and the third flow body, and wherein:

in the retracted position, the second flow body is positioned to at least approximately aerodynamically seal the first gap and the second gap; and

in the extended position, the second flow body is positioned to allow fluid flow through at least one of the first gap and the second gap.

7. The system of claim 1 wherein the at least one gap includes a first gap and the extended position includes a first extended position, and wherein the system further comprises a third flow body fixedly coupled to the leading edge of the airfoil, the third flow body positioned to form a second gap between the first flow body and the third flow body, and wherein the second flow body is movable among:

the retracted position where the second flow body is positioned to at least approximately aerodynamically seal the first gap and the second gap;

the first extended position where the second flow body is positioned to allow fluid flow through at least one of the first gap and the second gap; and

a second extended position where the second flow body is positioned to allow fluid flow through the first gap and the second gap, and to form at least one third gap between the second flow body and the third flow body.

8. The system of claim 1, further comprising at least one sealing device positioned between the second flow body and the airfoil to aid in preventing fluid flow through the at least one gap when the second flow body is in the retracted position.

9. The system of claim 1 wherein the second flow body is positioned forward of, below, or both forward of and below the airfoil to form an extension of the leading edge of the airfoil when the second flow body is in the extended position.

10. The system of claim 1 wherein:

the extended position includes a first extended position where the second flow body is positioned to form a passageway with a first distance between the second flow body and the leading edge of the airfoil, the passageway being positioned to affect the air flow through the at least one gap; and

the second flow body is movable to a second extended position where the passageway has a second distance between the second flow body and the leading edge of the airfoil, the second distance being different than the first distance.

11. The system of claim 1 wherein the second flow body includes a recess, an upper trailing edge, and a lower trailing edge, and wherein when the second flow body is in the retracted position, the first flow body is located in the recess, the upper trailing edge is at least proximate to the leading edge of the airfoil, and the lower leading edge is at least proximate to the leading edge of the airfoil.

12. A method for making an aerospace vehicle system, comprising:

fixedly coupling a first flow body to an airfoil to form at least one gap between the first flow body and a leading edge of the airfoil; and

coupling a second flow body to the airfoil to be movable between;

a retracted position where the second flow body at least approximately aerodynamically seals the at least one gap; and

an extended position where the second flow body is positioned to allow fluid flow through the at least one gap.

13. The method of claim 12 wherein coupling a second flow body to the airfoil to be movable between a retracted and an extended position includes coupling a second flow body to an airfoil to be movable between a retracted position and a first extended position where the second flow body is positioned to allow fluid flow through at least one first gap, and wherein the second flow body is movable to a second extended position where the second flow body is positioned to allow fluid flow through the at least one first gap and to form at least one second gap between the second flow body and the first flow body.

14. The method of claim 12, further comprising positioning at least one sealing device between the second flow body and the leading edge of the airfoil to aid in preventing fluid flow through the at least one gap when the second flow body is in the retracted position.

15. The method of claim 12 wherein coupling a second flow body to the airfoil to be movable between a retracted and an extended position includes coupling the second flow body to the airfoil to be movable between the retracted position and the extended position wherein the second flow body is positioned forward of, below, or both forward of and below the airfoil to form an extension of the leading edge of the airfoil when the second flow body is in the extended position.

16. The method of claim 12 wherein:

coupling a second flow body includes coupling a second flow body to an airfoil to be movable between a retracted position and a first extended position where the second flow body is positioned to form a passageway having a first distance between the second flow body and the leading edge of the airfoil, the passageway being positioned to affect the air flow through the at least one gap; and

the second flow body is movable to a second extended position where the passageway has a second distance between the second flow body and the leading edge of the airfoil, the second distance being different than the first distance.

17. The method of claim 12 wherein fixedly coupling the first flow body to the airfoil to form the at least one gap includes fixedly coupling the first flow body to the airfoil to form a first gap, and wherein the method further comprises fixedly coupling a third flow body to the leading edge of the airfoil, the third flow body positioned to form a second gap between the first flow body and the third flow body, and wherein the second flow body is movable between:

the retracted position where the second flow body at least approximately aerodynamically seals the first gap and the second gap; and

the extended position where the second flow body is positioned to allow fluid flow through at least one of the first gap and the second gap.

18. The method of claim 12 wherein fixedly coupling the first flow body to the airfoil to form the at least one gap includes fixedly coupling the first flow body to the airfoil to form a first gap and wherein coupling the second flow body to the airfoil to be movable between the retracted and the extended position includes coupling the second flow body to the airfoil to be movable between the retracted position and a first extended position, and wherein the method further comprises fixedly coupling a third flow body to the leading edge of the airfoil to form a second gap between the first flow body and the third flow body, and wherein the second flow body is movable among:

the retracted position where the second flow body at least approximately aerodynamically seals the first gap and the second gap;

the first extended position where the second flow body is positioned to allow fluid flow through at least one of the first gap and the second gap; and

a second extended position where the second flow body is positioned to allow fluid flow through the first gap and the second gap, and to form at least one third gap between the second flow body and the third flow body.

19. The method of claim 12 wherein the method further comprises removing at least a portion of a leading edge device from the airfoil.

20. A method for configuring an aerospace vehicle for various phases of flight comprising:

positioning a leading edge device in a retracted position where a second flow body of the leading edge device at least approximately aerodynamically seals a gap between a portion of a first flow body of the leading edge device and a portion of a leading edge of an airfoil, wherein the first flow body is fixedly coupled to the leading edge of the airfoil; and

positioning the leading edge device in an extended position where the second flow body of the leading edge device is positioned to allow fluid flow through the gap.

21. The method of claim 20 wherein:

positioning the leading edge device in an extended position includes positioning the leading edge device in a first extended position to form a passageway having a first distance between the second flow body and the leading edge of the airfoil, the passageway being positioned to affect the air flow through the at least one gap; and

the method further comprises positioning the leading edge device in a second extended position where the passageway has a second distance between the second flow body and the leading edge of the airfoil, the second distance being different than the first distance.

22. The method of claim 20 wherein positioning the leading edge device in an extended position includes positioning the leading edge device in a first extended position to allow fluid flow through a first gap, and wherein the method further comprises positioning the leading edge device in a second extended position to allow fluid flow through the first gap and to allow fluid flow through a second gap between the first flow body and the second flow body.

23. The method of claim 20 wherein positioning the second flow body in the extended position includes positioning the second flow body at least one of forward and below the airfoil to form an extension of the leading edge of the airfoil.

24. The method of claim 20, further comprising operating the aerospace vehicle with the leading edge device in at least one of the retracted and extended positions.

25. An aerospace vehicle system, comprising:

an airfoil having a leading edge and a spanwise section;

a first flow body movably coupled to the airfoil; and

a second flow body movably coupled to the airfoil, the first flow body and the second flow body being movable between;

a retracted position where the second flow body is at least approximately aerodynamically sealed with the leading edge of the airfoil above and below the first flow body across the spanwise section; and

an extended position where the first flow body and the second flow body are positioned to interact with a fluid flow.

26. The system of claim 25 wherein the extended position includes at least one of:

the first flow body and the second flow body being positioned to allow fluid flow between the first flow body and the leading edge of the airfoil; and

the first flow body and the second flow body being positioned to allow fluid flow between the first flow body and the second flow body.