Aircraft wing

Patent metadata

Field	Value
Publication number	US-2023257099-A1
Application number	US-202318105627-A
Country	US
Kind code	A1
Filing date	Feb 3, 2023
Priority date	Feb 11, 2022
Publication date	Aug 17, 2023
Grant date	—

Abstract

An aircraft wing including: a main wing portion with a tip end, and a wing tip device rotatably coupled to the tip end of the main wing portion at a joint, the wing tip device rotatable at the joint about a first axis between a flight configuration and a ground configuration; and a seal panel assembly including: a seal panel extending across the joint; a first connecting element having a first end non-rotatably coupled to the seal panel and a second end rotatably coupled to the main wing portion such that the seal panel is rotatable about a second axis; and a second connecting element having a first end rotatably coupled to the seal panel and a second end rotatably coupled to the wing tip device, such that rotation of the wing tip device about the first axis causes the seal panel to rotate about the second axis.

First claim

1 . An aircraft wing comprising:
a main wing portion with a tip end; a wing tip device rotatably coupled to the tip end of the main wing portion at a joint, the wing tip device rotatable at the joint about a first axis between a flight configuration and a ground configuration; and a seal panel assembly comprising:
a seal panel extending across the joint;
a first connecting element including a first end non-rotatably coupled to the seal panel and a second end rotatably coupled to the main wing portion, such that the seal panel is rotatable about a second axis; and
a second connecting element including a first end rotatably coupled to the seal panel and a second end rotatably coupled to the wing tip device, such that rotation of the wing tip device about the first axis causes the seal panel to rotate about the second axis.

2 . The aircraft wing of claim 1 , wherein the first axis and the second axis are substantially parallel, and the seal panel and wing tip device are configured to rotate in the same direction.

3 . The aircraft wing of claim 1 , wherein the second end of the first connecting element is inboard of the seal panel.

4 . The aircraft wing of claim 1 , wherein the first connecting element comprises a first arm portion and a second arm portion that meet at an elbow.

5 . The aircraft wing of claim 4 , wherein a central axis of the first arm portion extends at an angle less than 135 degrees with respect to a central axis of the second arm portion.

6 . The aircraft wing of claim 1 , wherein the seal panel further includes a side panel including a face portion substantially perpendicular to the first axis, wherein the side panel is configured to extend over at least a portion of the first connecting element and the second connecting element while the wing tip device is in a ground configuration.

7 . The aircraft wing of claim 6 , wherein an inboard edge of the side panel is arcuate.

8 . The aircraft wing of claim 6 , wherein the side panel is a first side panel located towards a first end of the joint, and the seal panel includes a second side panel located towards a second end of the joint.

9 . The aircraft wing of claim 8 , wherein the first connecting element and the second connecting element are located between the first side panel and the second side panel.

10 . The aircraft wing of claim 1 , wherein the seal panel has a perimeter edge, and substantially an entirely of the perimeter edge is adjacent one of an outer skin of the main wing portion and an outer skin of the wing tip device, while the wing tip device is in a flight configuration.

11 . The aircraft wing of claim 1 , further comprising a seal configured to seal a gap between the seal panel and a surrounding structure of the main wing portion while the wing tip device in a flight configuration, wherein the seal extends along substantially an entire perimeter of the seal panel.

12 . The aircraft wing of claim 1 , further comprising a power system extending across the joint at a chordwise position, wherein the seal panel assembly is located at a chordwise position of the power system extending across the joint such that the seal panel is arranged to cover the power systems.

13 . The aircraft wing of claim 1 , wherein the wing tip device is rotatable coupled to the main wing portion by a plurality of lugs, and wherein the seal panel assembly is located at a chordwise position of the lugs such that the seal panel covers the plurality of lugs.

14 . The aircraft wing of claim 1 , wherein the seal panel assembly is a first seal panel assembly arranged to cover a first portion of the joint, and the aircraft wing comprises a second seal panel assembly arranged to cover a second portion of the joint.

15 . The aircraft wing of claim 1 , wherein the seal panel extends across the joint on an upper surface of the aircraft wing.

16 . An aircraft comprising the aircraft wing of claim 1 .

Assignees

• Airbus Operations Ltd

Inventors

• Walega Janusz
• Harding Matt

Classifications

• B64C7/00

  Structures or fairings not otherwise provided for · CPC title

• B64C3/56 Primary

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

• B64C3/26 Primary

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

• B64C23/072 Primary

  the wing tip airfoil devices being moveable in their entirety · CPC title

• B64C3/546 Primary

  by foldable elements · CPC title