Link mechanisms for gapped rigid krueger flaps, and associated systems and methods

• US 20090072093A1
• Filed: 06/14/2006
• Published: 03/19/2009
• Est. Priority Date: 06/14/2006
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Fox, Stephen J., Sakurai, Seiya
• Granted Patent: US 7,578,484 B2
• Time in Patent Office: Days
• US Class Current: 244/214
• CPC Class Codes: B64C 9/22 at the front of the wing
• CPC Class Codes: Y02T 50/30 Wing lift efficiency
• CPC Class Codes: Y02T 50/40 Weight reduction

Abstract

Link mechanisms for gapped rigid Krueger flaps, and associated methods and systems are disclosed. A system in accordance with one embodiment includes a deployable leading edge assembly that in turn includes a deployable leading edge panel having a generally fixed-shape flow surface, a bullnose coupled to the panel, and a link mechanism coupled to the panel and the bullnose to move the panel between a stowed position and a deployed position. The mechanism can include a first support link, a second support link, and first, second, and third positioning links. The positioning links can be pivotably connected among the leading edge panel, the bullnose, the first support link and the second support link so that the leading edge panel forms a gap with the airfoil when in the deployed position. The positioning links can be the only positioning links coupled between the support links, the leading edge panel, and the bullnose at a particular wing span location.

Claims

1. An aircraft system, comprising:

a deployable leading edge assembly that includes;

a deployable leading edge panel having a generally fixed-shape flow surface;

a bullnose pivotably coupled to the leading edge panel;

a link mechanism coupled to the leading edge panel and the bullnose at a wing span location to move the leading edge panel between a stowed position and a deployed position, the link mechanism having;

a first support link pivotably coupleable to an airfoil;

a second support link pivotably coupleable to the airfoil and spaced apart from the first support link; and

first, second, and third positioning links pivotably connected among the leading edge panel, the bullnose, the first support link and the second support link, wherein the leading edge panel forms a gap with the airfoil when in the deployed position, and wherein the positioning links are the only positioning links coupled between the support links, the leading edge panel and the bullnose at the wing span location.

2. The system of claim 1, further comprising the airfoil, and wherein:

the first and second support links are pivotably coupled to the airfoil;

the first positioning link is pivotably connected to the first support link, the second support link and the leading edge panel;

the second positioning link is pivotably connected to the first support link, the leading edge panel and the third positioning link; and

the third positioning link is pivotably connected between the second positioning link and the bullnose.

3. The system of claim 2 wherein:

the first positioning link has a first end, a second end, and an intermediate portion between its first and second ends, the first positioning link being pivotably connected to the second support link toward its first end, pivotably connected to the leading edge panel toward its second end, and pivotably connected to the first support link at its intermediate portion to form a scissors arrangement with the first support link; and

the second positioning link has a first end, a second end, and an intermediate portion between its first and second ends, the second positioning link being pivotably connected to the first support link toward its first end, pivotably connected to the third positioning link toward its second end, and pivotably connected to the leading edge panel at its intermediate portion.

4. The system of claim 1 wherein the first support link and the first positioning link each have three pivot joints coupled to adjacent elements, and wherein the three pivot joints of the first support link are at least approximately co-linear, and wherein the three pivot joints of the first positioning link are at least approximately co-linear.

5. The system of claim 1, further comprising the airfoil, and wherein the first and second support links are pivotably coupled to the airfoil.

6. The system of claim 5 wherein the airfoil has an airfoil chord length, and wherein the leading edge panel forms a gap that is at least 2% of the airfoil chord length when in the deployed position.

7. The system of claim 1 wherein the link mechanism is a first link mechanism and the wing span location is a first wing span location, and wherein the system further comprises a second link mechanism having an arrangement of links generally the same as that of the first link mechanism, the second link mechanism being positioned at a second wing span location spaced apart in spanwise direction from the first wing span location.

8. The system of claim 1 wherein the first support link is coupled to an actuator.

9. The system of claim 1 wherein the leading edge panel has a streamwise flow surface that is exposed to freestream airflow when in both the stowed and the deployed positions.

10. The system of claim 1 wherein each of the links is generally straight.

11. The system of claim 1 wherein the first support link has three pivot locations positioned along a generally straight line.

12. The system of claim 1 wherein the first positioning link has three pivot locations positioned along a generally straight line.

13. The system of claim 1 wherein the second positioning link has three pivot locations positioned along a generally straight line.

14. The system of claim 1 wherein for each link, opposite ends of the link are offset by 20 degrees or less.

15. The system of claim 1 wherein for each link, opposite ends of the link are offset by 40 degrees or less.

16. The system of claim 1 wherein both the leading edge panel and the bullnose have generally fixed-shape, streamwise flow surfaces.

17. The system of claim 1 wherein the first support link and the first positioning link form a first scissors configuration, and wherein the leading edge panel and the second positioning link form a second scissors configuration.

18. An aircraft wing system, comprising:

an airfoil;

a deployable leading edge assembly that includes;

a deployable leading edge panel having a generally rigid, fixed-shape flow surface;

a bullnose pivotably coupled to the leading edge panel and having a generally rigid, fixed-shape flow surface;

a link mechanism coupled to the leading edge panel, the bullnose and the airfoil at a wing span location to move the leading edge panel between a stowed position and a deployed position, the link mechanism having;

a first support link pivotably coupled to the airfoil;

a second support link pivotably coupled to the airfoil and positioned aft of the first support link;

a first positioning link pivotably connected to the first support link, the second support link and the leading edge panel;

a second positioning link pivotably connected to the second support link, the leading edge panel and the third positioning link; and

a third positioning link pivotably connected between the second positioning link and the bullnose, wherein the leading edge panel forms a gap with the airfoil when in the deployed position, and wherein the positioning links are the only positioning links coupled between support links, the leading edge panel and the bullnose at the wing span location.

19. The system of claim 18 wherein each of the links is generally straight.

20. The system of claim 18 wherein for each link, opposite ends of the link are offset by 20 degrees or less.

21. The system of claim 18 wherein for each link, opposite ends of the link are offset by 40 degrees or less.

22. A method for operating an aircraft wing system, comprising:

deploying a leading edge panel and a bullnose relative to an airfoil by;

rotating a first support link pivotably coupled to the airfoil at a wing span location;

rotating a second support link pivotably coupled to the airfoil and positioned aft of the first support link;

rotating first, second, and third positioning links pivotably connected among the leading edge panel, the bullnose, the first support link and the second support link, wherein the positioning links are the only positioning links coupled between support links, the leading edge panel and the bullnose at the wing span location;

forming a gap between the airfoil and a generally fixed-shape streamwise flow surface of the leading edge panel; and

rotating the bullnose relative to the leading edge panel.

23. The method of claim 22 wherein deploying the leading edge panel includes moving the leading edge panel from a stowed position in which the panel forms a part of a lower surface of the airfoil, to a deployed position in which at least part of the panel is located forward of a leading edge of the airfoil.

24. The method of claim 22 wherein forming a gap includes forming a gap that is at least 2% of a chord length of the airfoil.

25. The method of claim 22 wherein rotating the first, second, and third positioning links includes rotating the first positioning link and the first support link relative to each other in a scissors manner, and rotating the second positioning link and the leading edge panel relative to each other in a scissors manner.