Leading edge device for an aerodynamic component and method for manufacturing a leading-edge device for an aerodynamic component

Patent metadata

Field	Value
Publication number	US-12466539-B2
Application number	US-202418895084-A
Country	US
Kind code	B2
Filing date	Sep 24, 2024
Priority date	Sep 25, 2023
Publication date	Nov 11, 2025
Grant date	Nov 11, 2025

Abstract

A leading-edge device for an aerodynamic component is disclosed having a first skin element having an inner surface and an aerodynamic outer surface, and further includes a second skin element having an inner surface and an aerodynamic outer surface. The leading-edge device includes a first coupling element protruding from the inner surface of the first skin element and a second coupling element protruding from the inner surface of the second skin element. The first and second coupling elements are coupled to each other in a coupling region. The first skin element and the first coupling element are formed as a single-piece structure.

First claim

The invention claimed is:

1 . A leading-edge device for an aerodynamic component, comprising:
a first skin element having an inner surface and an aerodynamic outer surface; a second skin element having an inner surface and an aerodynamic outer surface; a first coupling element protruding from the inner surface of the first skin element; a second coupling element protruding from the inner surface of the second skin element; wherein the first coupling element and the second coupling element are coupled to each other in a coupling region that is arranged between the inner surface of the first skin element and the inner surface of the second skin element; wherein the first skin element and the first coupling element are formed as a single-piece structure; and, wherein, in the coupling region, the first coupling element and the second coupling element overlap each other, thereby forming an overlapping region that is substantially perpendicular to the first and the second skin elements.

2 . The leading-edge device according claim 1 , wherein the second skin element and the second coupling element are formed as a single-piece structure.

3 . The leading-edge device according claim 1 , wherein, in the coupling region, the first coupling element and the second coupling element are bonded to each other via a bonding connection.

4 . The leading-edge device according claim 3 , wherein the bonding connection is at least one of a metal bonding connection, a thermoset bonding connection or a thermoplastic bonding connection.

5 . The leading-edge device according claim 1 , wherein, in the coupling region, the first coupling element and the second coupling element are attached to each other using at least one of an adhesive connection, a weld connection, a screw connection or a rivet connection.

6 . The leading-edge device according claim 1 , wherein the aerodynamic outer surface of the first skin element is an entirely closed surface; and/or wherein the aerodynamic outer surface of the second skin element is an entirely closed surface.

7 . The leading-edge device according claim 1 , wherein the first skin element is an integrally formed curved structure; and/or wherein the second skin element is an integrally formed curved structure.

8 . The leading-edge device according claim 1 , wherein the single-piece structure formed by the first skin element and the first coupling element includes at least one of a reinforced thermoplastic material, a thermoset material or a metallic material.

9 . The leading-edge device according claim 1 , wherein the second skin element and/or the second coupling element includes at least one of a reinforced thermoplastic material, a thermoset material or a metallic material.

10 . The leading-edge device according claim 1 , wherein the first coupling element is a longitudinal stiffening element extending on the inner surface of the first skin element and configured to stiffen at least a part of the first skin element; and/or
wherein the second coupling element is a longitudinal stiffening element extending on the inner surface of the second skin element and configured to stiffen at least a part of the second skin element.

11 . The leading-edge device according claim 1 , wherein the first skin element and the second skin element define an aerodynamic profile having a chordwise direction and a spanwise direction which is substantially perpendicular to the chordwise direction;
wherein each of the first coupling element and the second coupling element extends in the spanwise direction.

12 . An aircraft comprising the leading-edge device according to claim 1 .

13 . A method for manufacturing a leading-edge device for an aerodynamic component, comprising:
providing a first skin element with a first coupling element protruding from an inner surface of the first skin element, wherein the first skin element and the first coupling element are formed as a single-piece structure; providing a second skin element with a second coupling element protruding from an inner surface of the second skin element; arranging the first coupling element relative to the second coupling element such that the first coupling element and the second coupling element overlap each other in a coupling region that is arranged between the first skin element and the second skin element; bonding the first coupling element to the second coupling element in the coupling region; wherein, in the coupling region, the first coupling element and the second coupling element overlap each other, thereby forming an overlapping region that is substantially perpendicular to the first and the second skin elements.

14 . A leading-edge device for an aerodynamic component, comprising:
a first skin element having an inner surface and an aerodynamic outer surface; a second skin element having an inner surface and an aerodynamic outer surface; a first coupling element protruding from the inner surface of the first skin element; a second coupling element protruding from the inner surface of the second skin element; wherein the first coupling element and the second coupling element are coupled to each other in a coupling region that is arranged between the inner surface of the first skin element and the inner surface of the second skin element; wherein the first skin element and the first coupling element are formed as a single-piece structure; wherein the first coupling element is arranged substantially perpendicular with respect to the inner surface of the first skin element; and, wherein the second coupling element is arranged substantially perpendicular with respect to the inner surface of the second skin element.

Assignees

• Airbus Operations Gmbh

Inventors

• Fees Martin
• Bast Christian
• Lange Robert
• Joachim Lilian

Classifications

• B64C3/185

  Spars · CPC title

• B64C9/22

  at the front of the wing · CPC title

• B64C3/28 Primary

  Leading or trailing edges attached to primary structures, e.g. forming fixed slots · CPC title