Elongate aircraft structural component and method of fabricating an elongate aircraft structural component

Patent metadata

Field	Value
Publication number	US-2025171130-A1
Application number	US-202418948803-A
Country	US
Kind code	A1
Filing date	Nov 15, 2024
Priority date	Nov 29, 2023
Publication date	May 29, 2025
Grant date	—

Abstract

An elongate aircraft structural component for an aircraft, the structural component comprising a web and a flange, wherein the flange extends from the web, comprises layers of composite material, and has a length in a direction of a length of the elongate aircraft structural component, a width perpendicular to the length of the flange and a thickness smaller than, and perpendicular to, both the width and the length of the flange, wherein the width of the flange varies along the length of the flange, whereby the flange comprises a wide flange region and a narrow flange region, the narrow flange region having a smaller width than the wide flange region, and wherein the wide flange region comprises stitching interconnecting the layers of composite material, the stitching extending along a path in a direction with at least a component parallel to the width of the flange.

First claim

Claimed is:

1 . An elongate aircraft structural component for an aircraft, the elongate aircraft structural component comprising:
a web and a flange, wherein the flange extends from the web and comprises layers of composite material, a length in a direction of a length of the elongate aircraft structural component, a width perpendicular to the length of the flange, and a thickness smaller than, and perpendicular to, both the width and the length of the flange, wherein the width of the flange varies along the length of the flange, whereby the flange comprises a wide flange region and a narrow flange region, the narrow flange region having a smaller width than the wide flange region, and wherein the wide flange region comprises stitching interconnecting the layers of composite material, the stitching extending along a path in a direction with at least a component parallel to the width of the flange.

2 . The elongate aircraft structural component according to claim 1 , wherein the layers of composite material comprise layers of fiber composite material.

3 . The elongate aircraft structural component according to claim 2 , wherein the layers of fiber composite material comprise carbon fibers.

4 . The elongate aircraft structural component according to claim 2 , wherein the layers of fiber composite material comprise unidirectional-fiber layers, having continuous fibers orientated along the length of the flange, and chopped strand layers, having discontinuous fibers orientated in a plurality of directions within a plane of each respective chopped strand layer.

5 . The elongate aircraft structural component according to claim 4 , wherein at least 50% of the layers of composite material in the flange are the unidirectional-fiber layers.

6 . The elongate aircraft structural component according to claim 1 , wherein the wide flange region comprises a hole for receiving a fastener for fastening the flange to a skin section of the aircraft.

7 . The elongate aircraft structural component according to claim 6 , wherein the hole does not interrupt the stitching.

8 . The elongate aircraft structural component according to claim 6 , wherein the stitching surrounds the hole.

9 . The elongate aircraft structural component according to claim 1 , wherein the stitching comprises a plurality of parallel stitchings interconnecting the layers of composite material.

10 . The elongate aircraft structural component according to claim 1 , wherein the stitching comprises a plurality of intersecting stitchings.

11 . The elongate aircraft structural component according to claim 1 , wherein the direction of the path has equal components in a direction of the width of the flange and a direction of the thickness of the flange.

12 . The elongate aircraft structural component according to claim 1 , wherein the direction of the path has a component parallel to the length of the flange.

13 . The elongate aircraft structural component according to claim 1 , wherein the elongate structural component is an aircraft stringer.

14 . The elongate aircraft structural component according to claim 1 , wherein the narrow flange region also comprises stitching interconnecting the layers of composite material.

15 . An aircraft structural assembly, comprising:
the elongate aircraft structural component according to claim 1 ; and a skin section affixed to the flange of the elongate aircraft structural component.

16 . An aircraft comprising:
the aircraft structural assembly according to claim 15 .

17 . A method of fabricating an elongate aircraft structural component for an aircraft, the method comprising:
providing a web; providing a flange extending from the web and comprising layers of composite material, a length in a direction of a length of the elongate aircraft structural component, a width perpendicular to the length of the flange, and a thickness smaller than, and perpendicular to, both the width and the length of the flange, wherein the width of the flange varies along the length of the flange, whereby the flange comprises a wide flange region and a narrow flange region, the narrow flange region having a smaller width than the wide flange region; and providing stitching interconnecting the layers of composite material in the wide flange region, the stitching extending along a path in a direction with at least a component parallel to the width of the flange.

18 . The method according to claim 17 , wherein the layers of composite material comprise unidirectional-fiber layers, having continuous fibers orientated along the length of the flange, and chopped-strand layers, having discontinuous fibers orientated in a plurality of directions within a plane of each of the respective chopped-strand layers.

19 . The method according to claim 17 , wherein the method comprises providing the wide flange region with a hole for receiving a fastener for fastening the flange to a skin section of the aircraft.

20 . The method according to claim 19 , wherein the providing the wide flange region with a hole comprises providing the hole such that the hole does not interrupt the stitching.

Assignees

• Airbus Operations Ltd

Inventors

• Bryant Stuart
• Barnett Thomas

Classifications

• B64C1/12

  Construction or attachment of skin panels · CPC title

• B64C1/068

  Fuselage sections · CPC title

• B64C3/187

  Ribs · CPC title

• B64C3/00 Primary

  Wings (ornithopter wings B64C33/02) · CPC title

• B32B2262/106

  Carbon fibres, e.g. graphite fibres · CPC title