Aerospace vehicle leading edge slat devices and corresponding methods

• US 7,322,547 B2
• Filed: 01/31/2005
• Issued: 01/29/2008
• Est. Priority Date: 01/31/2005
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Konings, Christopher A.
• Primary Examiner(s): Collins; Timothy D.
• Application Number:
  US11/048,320
• Publication Number:
  US 20060169847A1
• Time in Patent Office: 1,093 Days
• Field of Search: 244/35.R, 244/198, 244/201, 244/213, 244/214
• 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 having a recess, an upper trailing edge, and a lower trailing edge, the second flow body being movably coupled to the airfoil to move between;

a retracted position wherein the second flow body is positioned to at least approximately aerodynamically seal the at least one gap, and wherein the first flow body is located in the recess, the upper trailing edge is positioned proximate to the leading edge of the airfoil to at least approximately aerodynamically seal with the airfoil, and the lower trailing edge is positioned proximate to the leading edge of the airfoil to at least approximately aerodynamically seal with the airfoil; 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.

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.

6. An aerospace vehicle system, comprising:

an airfoil having a leading edge;

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

a second flow body movably coupled to the airfoil; and

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, wherein the second flow body is movable between;

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

an 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.

7. The system of claim 6 wherein the extended position includes a first extended position, and wherein the second flow body is movable among:

the retracted position;

the first extended position; 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.

11. 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

movably coupling a second flow body to the airfoil, the second flow body having a recess, an upper trailing edge, and a lower trailing edge, the second flow body being movable between;

a retracted position wherein the second flow body at least approximately aerodynamically seals the at least one gap, and wherein the first flow body is located in the recess, the upper trailing edge is positioned proximate to the leading edae of the airfoil to at least approximately aerodynamically seal with the airfoil, and the lower trailing edge is positioned proximate to the leading edge of the airfoil to at least approximately aerodynamically seal with the airfoil; and

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

12. The method of claim 11 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.

13. The method of claim 11, 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.

14. The method of claim 11 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.

15. The method of claim 11 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.

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

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

movably coupling a second flow body to the airfoil;

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, wherein the second flow body is movable between;

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

an 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.

17. The method of claim 16 wherein the extended position includes a first extended postion, and wherein the second flow body is movable among:

the retracted position;

the first extended position; 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.

18. A method for configuring an aerospace vehicle system, comprising:

removing at least a portion of a pre-existing leading edge device from an airfoil;

fixedly coupling a first flow body to the 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.

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

positioning a leading edge device in a retracted position wherein;

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

the first flow body is located in a recess of the second flow body, an upper trailing edge of the second flow body is positioned proximate to the leading edge of the airfoil to at least approximately aerodynamically seal with the airfoil, and a lower trailing edge of the second flow body is positioned proximate to the leading edge of the airfoil to at least approximately aerodynamically seal with the airfoil; and

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

20. The method of claim 19 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 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.

21. The method of claim 19 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.

22. The method of claim 19 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.

23. The method of claim 19, further comprising operating the aerospace vehicle with the leading edge device in at least one of the retracted and extended positions.

24. 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 second flow body having a recess, an upper trailing edge, and a lower trailing edge, the first flow body and the second flow body being movable between;

a retracted position where the first flow body is located in the recess, the upper trailing edae of the second flow body is proximate to and at least approximately aerodynamically sealed with the leading edge of the airfoil above the first flow body across the spanwise section, and the lower trailing edge of the second flow body is proximate to and at least approximately aerodynamically sealed with the leading edge of the airfoil 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.

25. The system of claim 24 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.