Aircraft gap seal

Patent metadata

Field	Value
Publication number	US-10871232-B2
Application number	US-201715813516-A
Country	US
Kind code	B2
Filing date	Nov 15, 2017
Priority date	Nov 15, 2016
Publication date	Dec 22, 2020
Grant date	Dec 22, 2020

Abstract

An aircraft assembly including: first and second external skin panels having opposing edge faces separated by a gap, the gap having a width in a first direction extending between the opposing edge faces and a depth in a second direction generally orthogonal to the first direction; and a gap seal arranged in the gap to at least partially fill the gap, wherein the gap seal is formed of a material configured such that compression of the gap seal in the first direction results in substantially no expansion of the gap seal in the second direction.

First claim

The invention claimed is:

1. An aircraft assembly comprising:
first and second external skin panels having opposing edge faces separated by a gap, the gap having a width in a first direction extending between the opposing edge faces and a depth in a second direction generally orthogonal to the first direction,
a gap seal arranged in the gap to at least partially fill the gap,
wherein the first and second external skin panels are configured to move relative to one another between a first configuration in which the gap seal is arranged in the gap to at least partially fill the gap and a second configuration in which the gap seal is compressed in the first direction, and
wherein the gap seal comprises material configured such that compression of the gap seal in the first direction across the width of the gap results in substantially no expansion of the gap seal in the second direction corresponding to a depth of the gap.

2. The assembly according to claim 1 , wherein the material of the gap seal has a Poisson's ratio in at least the first direction:
equal to or less than 0.1; or
equal to or less than 0.06; or
equal to or less than 0.05.

3. The assembly according to claim 1 , wherein the material of the gap seal comprises a grid of cells.

4. The assembly according to claim 3 , wherein the material comprises a substrate and each cell comprises a uniform pattern of apertures in the substrate.

5. The assembly according to claim 1 , wherein the material is formed from at least one of the following: polyurethane; polytetrafluoroethylene; an elastomer, including silicon rubber or neoprene; or cork.

6. The assembly according to claim 1 , including a blade seal attached to the first or second external skin panel and extending across the width of the gap to obscure the gap in at least the second configuration.

7. The assembly according to claim 6 , wherein the blade seal is configured to slide relative to the other of the first or second external skin panel, respectively, during relative movement of the first and second external skin panels.

8. The assembly according to claim 1 , wherein the gap seal is fixed to the opposing edge face of a respective one of the first or second external skin panel, and is not fixed to the opposing edge face of the other of the first or second external skin panel.

9. The assembly according to claim 1 , including a friction layer between the gap seal and the opposing edge face of the other of the first or second external skin panel, wherein the friction layer has a higher coefficient of friction than the gap seal.

10. The assembly according to claim 1 , wherein a respective one of the first and second external skin panels comprises a panel of one of a movable control surface, an access door, and a landing gear bay door.

11. The assembly according to claim 1 , wherein the aircraft assembly includes an inner wing section comprising the first external skin panel, and an outer wing section comprising the second external skin panel, the outer wing being pivotable relative to the inner wing between a folded configuration in which the first and second external skin panels are separated, and a flight configuration in which the gap seal is compressed in the first direction.

12. An aircraft comprising the assembly according to claim 1 .

13. An assembly to seal a gap comprising:
a gap between opposing edges of external skin panels on an aircraft,
a gap seal in the gap wherein the gap seal has a width commensurate to a width of the gap along a direction parallel to at least one of the external skin panels,
wherein a material forming the gap seal has a Poisson's ratio of no greater than 0.1, and
wherein the external skin panels are configured to move relative to one another between a first configuration in which the gap seal is arranged in the gap to at least partially fill the gap and a second configuration in which the gap seal is compresses in the first direction.

14. The assembly of claim 13 wherein a thickness of the gap seal is commensurate with a thickness of each of the external skin panels.

15. The assembly of claim 13 wherein the gap seal is compressed by the opposing edges.

16. The assembly of claim 13 wherein the material forming the gap seal includes a substrate layer and slots in the substrate layer, wherein the slots are arranged in a pattern forming repeating cells on the layer.

17. The assembly of claim 16 wherein the cells are each hexagonal in shape.

Assignees

• Airbus Operations Ltd

Inventors

• Laverne Julien
• Jaggard Philip
• Harding Matt

Classifications

• B64C3/26 Primary

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

• F16J15/104

  characterised by structure · CPC title

• F16J15/00

  Sealings · CPC title

• B64C7/00 Primary

  Structures or fairings not otherwise provided for · CPC title

• B64C3/36

  Structures adapted to reduce effects of aerodynamic or other external heating · CPC title