Cross-wing driveshaft channel

Patent metadata

Field	Value
Publication number	US-9981734-B2
Application number	US-201615269278-A
Country	US
Kind code	B2
Filing date	Sep 19, 2016
Priority date	Sep 19, 2016
Publication date	May 29, 2018
Grant date	May 29, 2018

Abstract

An aircraft wing including a fuel tank located in the wing, a channel defining a cavity in the fuel tank, the channel including at least two channel ends terminating at an upper or lower wing surface, a driveshaft located in the cavity; and an access panel located on the wing surface and being movable between an open position so that access to the cavity is permitted, and a closed position so that the cavity is at least partially covered by the access panel to inhibit access to the cavity.

First claim

The invention claimed is:

1. An aircraft wing having a wing surface comprising:
a fuel tank located in the wing,
a channel defining a cavity in the fuel tank, the channel comprising at least two channel ends terminating at the wing surface,
a driveshaft located in the cavity; and
an access panel located on the wing surface and being movable between an open position wherein access to the cavity is permitted, and a closed position wherein the cavity is at least partially covered by the access panel to inhibit access to the cavity.

2. The aircraft wing of claim 1 , wherein the aircraft wing is an inboard aircraft wing.

3. The aircraft wing of claim 1 , wherein the wing surface is an upper wing surface.

4. The aircraft wing of claim 1 , wherein the wing surface is a lower wing surface.

5. The aircraft wing of claim 1 , further comprising a first side surface and second side surface of the channel, the first and second side surfaces extending to the channel ends.

6. The aircraft wing of claim 5 , wherein the first and second side surfaces are substantially parallel.

7. The aircraft wing of claim 5 , wherein the first and second side surfaces are not parallel.

8. The aircraft wing of claim 5 , wherein the first and second side surfaces are substantially planar and at least one of the first or second side surfaces extends in a generally vertical direction.

9. The aircraft wing of claim 5 , wherein the first and second side surfaces are substantially planar and the first and second side surfaces extend in a generally vertical direction.

10. The aircraft wing of claim 5 , wherein the first side surface is in contact with the second side surface.

11. The aircraft wing of claim 5 , further comprising a base surface in contact with the first and second side surfaces.

12. The aircraft wing of claim 11 , wherein the base surface is curved.

13. The aircraft wing of claim 1 , wherein the channel has a U-shape.

14. The aircraft wing of claim 1 , wherein the driveshaft is located from about 20% to about 45% of the total wing chord.

15. The aircraft wing of claim 1 , wherein the driveshaft is located from about 25% to about 40% of the total wing chord.

16. The aircraft wing of claim 1 , wherein the driveshaft is located from about 25% to about 35% of the total wing chord.

17. The aircraft wing of claim 1 , wherein the channel ends are adjacent to the access panel.

18. The aircraft wing of claim 1 , further comprising a plurality of wing supports to provide primary structural support to the wing.

19. The aircraft wing of claim 18 , wherein the channel spans the plurality of wing supports.

20. The aircraft wing of claim 19 , wherein the distal end of the channel terminates at the outermost wing support.

Assignees

• Bell Helicopter Textron Inc

Inventors

• Ivans Steven
• Anderson Adam

Classifications

• B64C3/26

  Construction, shape, or attachment of separate skins, e.g. panels · CPC title

• B64C3/34 Primary

  Tanks constructed integrally with wings, e.g. for fuel or water · CPC title

• B64C3/32

  specially adapted for mounting power plant · CPC title

• B64C29/0033

  the propellers being tiltable relative to the fuselage · CPC title

• B64D37/06

  Constructional adaptations thereof · CPC title