Morphing wing leading edge

Patent metadata

Field	Value
Publication number	US-8925870-B1
Application number	US-201213417201-A
Country	US
Kind code	B1
Filing date	Mar 9, 2012
Priority date	Mar 9, 2012
Publication date	Jan 6, 2015
Grant date	Jan 6, 2015

Abstract

A wing may include a flexible leading edge skin segment having segment ends positioned adjacent to upper and lower leading edge wing skins to form a skin assembly. The upper leading edge wing skin may be positioned between the leading edge skin segment and an upper main wing skin. The lower leading edge wing skin may be positioned between the leading edge skin segment and a lower main wing skin. The wing may include a deployment device configured to flex the upper and lower leading edge wing skins thereby causing the leading edge skin segment to exhibit a rolling motion.

First claim

What is claimed is:

1. A wing having a morphing leading edge, comprising:
a flexible leading edge skin segment having segment ends positioned adjacent to upper and lower leading edge wing skins to form a skin assembly, the upper leading edge wing skin being positioned between the leading edge skin segment and an upper main wing skin, the lower leading edge wing skin being positioned between the leading edge skin segment and a lower main wing skin; and
a deployment device configured to cause the upper and lower leading edge wing skin to move between an undeployed position and a deployed position;
at least one rib mounted to a main wing structure and having a rib upper surface and/or a rib lower surface;
the upper leading edge wing skin being placed into contact with the rib upper surface when the skin assembly is in the deployed position; and
the lower leading edge wing skin being placed into contact with the rib lower surface when the skin assembly is in the undeployed position.

2. The wing of claim 1 further comprising:
the deployment device configured to flex the upper and lower leading edge wing skins thereby causing the leading edge skin segment to exhibit a rolling motion.

3. The wing of claim 1 wherein:
the upper and lower leading edge wing skins are positioned adjacent to a main wing structure.

4. The leading edge device of claim 1 further comprising:
a nose linkage interconnecting the segment upper and segment lower ends of the flexible leading edge skin segment.

5. The wing of claim 4 further comprising:
a cam configured to be rotated into engagement with the nose linkage and lock the skin assembly in an undeployed position.

6. The wing of claim 1 wherein the deployment device comprises:
an inflatable airbag captured between an airbag support and the lower leading edge wing skin for deploying the skin assembly; and
the airbag being configured to bear against the lower leading edge wing skin during inflation of the airbag.

7. The wing of claim 1 wherein:
at least one of the upper and lower leading edge wing skins being configured to bias the skin assembly toward an undeployed position.

8. The wing of claim 1 further comprising:
at least one spanwise stiffener mounted to at least one of the upper and lower leading edge wing skins.

9. The wing of claim 1 wherein:
the leading edge skin segment is formed of a thermoplastic polyamide material.

10. The wing of claim 1 wherein:
the upper and lower leading edge wing skins are formed of fiber-reinforced polymeric material.

11. The wing of claim 1 wherein:
the wing has an increase in camber of at least approximately 20 degrees when the skin assembly is in a deployed position.

12. The wing of claim 1 wherein:
the wing has a continuous outer mold line along a wing surface as the skin assembly is moved between an undeployed position and a deployed position.

13. A wing, comprising:
at least two ribs mounted to a main wing structure in spaced relation to one other, each rib having a rib upper surface and a rib lower surface;
a skin assembly, including:
a flexible upper and lower leading edge wing skin each having a forward end and an aft end, the aft ends being fixedly coupled to the main wing structure; and
a flexible leading edge skin segment interconnecting the upper and lower leading edge wing skins; and
a deployment device configured to flex the upper and lower leading edge wing skins and cause rolling motion of the leading edge skin segment to move the skin assembly from an undeployed position toward a deployed position in a manner increasing a camber of the wing;
the lower leading edge wing skin being substantially in contact with the rib lower surface when the skin assembly is in the undeployed position; and
the upper leading edge wing skin being substantially in contact with the rib upper surface when the skin assembly is in the deployed position.

14. A method of morphing a leading edge of a wing, comprising the steps of:
operating a deployment device positioned between a skin assembly and a main wing structure, the main wing structure having at least one rib mounted to the main wing structure, the rib having a rib lower surface and a rib upper surface;
causing an upper and lower leading edge wing skin of the skin assembly to flex and move between an undeployed position and a deployed position;
changing a camber angle of the wing during movement of the skin assembly;
positioning the lower leading edge wing skin substantially in contact with the rib lower surface when the skin assembly is in the undeployed position; and
positioning the upper leading edge wing skin substantially in contact with the rib upper surface when the skin assembly is in the deployed position.

15. The method of claim 14 further comprising the steps of:
causing a leading edge skin segment of the skin assembly to exhibit a rolling motion during movement of the skin assembly.

16. The method of claim 14 further comprising the steps of:
mounting at least one rib to the main wing structure, the rib having a rib lower surface; and
positioning the lower leading edge wing skin substantially in contact with the rib lower surface when the skin assembly is in the undeployed position.

17. The method of claim 14 further comprising the steps of:
mounting at least one rib to the main wing structure, the rib having a rib upper surface; and
positioning the upper leading edge wing skin substantially in contact with the rib upper surface when the skin assembly is in the deployed position.

18. The method of claim 14 further comprising the step of:
interconnecting upper and lower ends of the leading edge skin segment using a substantially rigid nose linkage.

19. The method of claim 14 further comprising the step of:
locking the skin assembly in the deployed position using a locking mechanism.

20. The method of claim 14 wherein the step of operating the deployment device comprises:
inflating an airbag in contact with a skin inner surface of the lower leading edge wing skin; and
applying pressure to the skin inner surface during inflation of the airbag.

Assignees

• Gordon Jason
• Borgstrom Carl
• Fisher Noah
• Fuhrmeister Cory
• Madigan Nathan
• Parkins Carly
• Boeing Co

Inventors

• Gordon Jason
• Borgstrom Carl
• Fisher Noah
• Fuhrmeister Cory
• Madigan Nathan
• Parkins Carly

Classifications

• B64C2003/445

  by changing shape according to the speed, e.g. by morphing · CPC title

• B64C3/28 Primary

  Leading or trailing edges attached to primary structures, e.g. forming fixed slots · CPC title