Hinged raked wing tip

Patent metadata

Field	Value
Publication number	US-10538307-B2
Application number	US-201213664416-A
Country	US
Kind code	B2
Filing date	Oct 30, 2012
Priority date	Oct 1, 2011
Publication date	Jan 21, 2020
Grant date	Jan 21, 2020

Abstract

A wing assembly comprises a raked wing tip having an outboard portion hinged to one of a main wing having at least one moveable control surface and an inboard raked wing tip portion. The outboard portion of the raked wing tip does not carry any moveable flight control surfaces.

First claim

The invention claimed is:

1. A wing assembly comprising:
one of a main wing having at least one moveable control surface and an inboard raked wing tip portion, wherein the main wing or the inboard raked wing tip portion includes an upper skin panel and a lower skin panel, and a stub spar door is formed in one of the upper skin panel and the lower skin panel;
an outboard raked wing tip portion rotatably coupled to the main wing or the inboard raked wing tip portion by a hinge defining a hinge line about which the outboard raked wing tip portion rotates relative to the main wing or the inboard raked wing tip portion, the outboard raked wing tip portion being rotatable about the hinge line between a folded position and an extended position, in which the outboard raked wing tip portion is approximately co-planar with the main wing or the inboard raked wing tip portion;
a stub spar coupled to the outboard raked wing tip portion, the stub spar extending from an end of the outboard raked wing tip portion and positioned to pass through the stub spar door as the outboard raked wing tip portion rotates about the hinge line between the folded position and the extended position, the stub spar being configured for insertion into the main wing or the inboard raked wing tip portion when the outboard raked wing tip portion is in the extended position, wherein a free end of the stub spar defines a locking location for coupling to the main wing;
the main wing or the inboard raked wing tip portion including a main wing spar;
a locking device for locking the free end of the stub spar to the spar of the main wing or the inboard raked wing tip portion, thereby to secure the outboard raked wing tip portion in the extended position; and
an actuator coupled to the free end of the stub spar and configured to rotate the outboard raked wing tip portion about the hinge line between the folded position and the extended position.

2. The wing assembly of claim 1 , wherein the outboard raked wing tip portion is hinged to the main wing.

3. The wing assembly of claim 1 , wherein the outboard raked wing tip portion is hinged to the inboard raked wing tip portion, the inboard raked wing tip portion having at least one moveable flight control surface.

4. The wing assembly of claim 1 , wherein the wing assembly is swept.

5. The wing assembly of claim 4 , wherein the outboard raked wing tip portion forms a leading edge sweep angle that is greater than the leading edge sweep angle of the main wing, and chord length that decreases significantly in a spanwise direction.

6. The wing assembly of claim 1 , wherein the hinge line is oriented in a streamwise direction.

7. The wing assembly of claim 1 , wherein the hinge line is parallel to a ribwise direction.

8. The wing assembly of claim 1 , wherein the hinge line is oriented at an angle between streamwise and ribwise directions.

9. The wing assembly of claim 1 , wherein the hinge line is coincident with one of the upper skin panel and lower skin panel.

10. The wing assembly of claim 1 , wherein the wing assembly has a wingspan greater than 65 meters when the outboard raked wing tip portion is in the extended position, and wherein the wing assembly has a wingspan less than 65 meters when the outboard raked wing tip portion is in the folded position.

11. The wing assembly of claim 1 , wherein the outboard raked wing tip portion, and the one of the inboard raked wing tip portion and the main wing are configured for a commercial aircraft.

12. An aircraft comprising:
a fuselage;
wing assemblies attached to the fuselage, each wing assembly including:
an inboard section with moveable flight control surfaces, the inboard section including a main wing spar, an upper skin panel and a lower skin panel, and a stub spar door is formed in one of the upper skin panel and the lower skin panel;
a raked wing tip rotatably coupled to the inboard section by a hinge defining a hinge line about which the raked wing tip rotates relative to the inboard section, the raked wing tip having no moveable flight control surfaces and being rotatable about the hinge line between a folded position and an extended position, in which the raked wing tip is approximately co-planar with the inboard section;
a stub spar coupled to the raked wing tip, the stub spar extending from an end of the raked wing tip and positioned to pass through the stub spar door as the wing tip rotates about the hinge line between the folded position and the extended position, the stub spar being configured for insertion into the inboard section and alignment with the main wing spar when the raked wing tip is in the extended position, wherein a free end of the stub spar defines a locking location for coupling to the main wing;
a locking assembly for locking the free end of the stub spar to the main wing spar, thereby to secure the wing tip in the extended position; and
an actuator coupled to the free end of the stub spar and configured to rotate the outboard raked wing tip portion about the hinge line between the folded position and the extended position.

13. The method of claim 12 , wherein the aircraft has a wingspan greater than 65 meters when the raked wing tips are in the extended position, and wherein the wing assembly has a wingspan less than 65 meters when the raked wing tips are in the folded position.

14. The aircraft of claim 12 , wherein the hinge line of each wing assembly is coincident with one of the upper skin panel and lower skin panel.

15. The aircraft of claim 12 , wherein the hinge line of each wing assembly is oriented in a streamwise direction.

16. A method of enhancing performance of an aircraft including wings with raked wing tips, the method comprising folding outboard portions of the raked wing tips in a folded position for taxiing, extending the outboard portions in an extended position, in which the raked wing tips are approximately co-planar with associated main wings, to increase wingspan for flight; wherein each of the outboard portions is rotatably coupled to the associated main wing by a hinge defining a hinge line about which the outboard raked wing tip portion rotates relative to the associated main wing; wherein each of the outboard portions further includes a stub spar extending from an end of the outboard portion and positioned to pass through a stub spar door formed in one of an upper skin panel and a lower skin panel provided on an associated main wing as the outboard portion rotates about the hinge line between the folded position and the extended position, wherein each stub spar is configured for insertion into the main wing when the outboard portion is in the extended position; wherein a free end of each stub spar defines a locking location for coupling to a main wing spar of the main wing; wherein a locking assembly locks the free end of the stub spar to the main wing spar to secure each wing tip in the extended position; and wherein an actuator is coupled to the free end of each stub spar and configured to rotate the associated outboard portion about the hinge line between the folded position and the extended position.

17. The aircraft of claim 16 , wherein the hinge line is oriented in a streamwise direction.

18. The aircraft of claim 16 , wherein the hinge line is parallel to a ribwise direction.

19. The aircraft of claim 16 , wherein the hinge line is oriented at an angle between streamwise and ribwise directions.

20. The aircraft of claim 16 , wherein the aircraft has a wingspan greater than 65 meters when the raked wing tip

Assignees

• Boeing Co

Inventors

• Dees Paul W
• Good Mark S
• Sakurai Seiya
• Kordel Jan A
• Fox Stephen J
• Lassen Matthew A
• Fox Bruce Robert
• Walker Steven Paul
• Santini Gregory M

Classifications

• B64C3/58

  provided with fences or spoilers (adjustable for control purposes B64C9/00) · CPC title

• Y02T50/14

  Cross-Sectional Technologies · mapped topic

• B64C3/56 Primary

  Folding or collapsing to reduce overall dimensions of aircraft · CPC title

• Y02T50/10

  Drag reduction · CPC title