Aircraft wing component

Patent metadata

Field	Value
Publication number	US-11919634-B2
Application number	US-202016810265-A
Country	US
Kind code	B2
Filing date	Mar 5, 2020
Priority date	Mar 13, 2019
Publication date	Mar 5, 2024
Grant date	Mar 5, 2024

Abstract

The trailing edge structure of an aircraft wing is subjected, in use, to high temperature efflux from an aircraft's engines. Such elevated temperatures can detrimentally affect the ultimate tensile strength of the trailing edge. An aircraft wing component includes composite material having a first portion including a metal matrix containing reinforcing material, and a second portion including a metal matrix containing hollow metal ceramic spheres, the second portion being adjacent a surface of the composite material. The provision of two portions, one of which contains reinforcing material and the other comprising hollow spheres means that the composite material has both structural strength and heat shielding qualities where they are needed most in the component. The portion of composite containing the hollow metal ceramic spheres acts as an embedded layer of heat insulation.

First claim

The invention claimed is:

1. An aircraft wing component comprising a composite material, wherein:
a first layer of the composite material comprises a metal matrix containing a reinforcing material;
a second layer of the composite material comprises a metal matrix containing a plurality of hollow spheres comprising alumina; and
the second layer is adjacent to an external surface of the composite material in a thickness direction of the aircraft wing component, such that the first layer is spaced apart in the thickness direction from the external surface of the composite material by the second layer.

2. The component of claim 1 , wherein the spheres have substantially similar diameters.

3. The component of claim 1 , wherein each of the spheres has one of a plurality of diameters in a predetermined range.

4. The component of claim 1 , wherein the second layer comprises less than 50% of a thickness of the composite material.

5. The component of claim 1 , wherein the second layer comprises less than 25% of a thickness of the composite material.

6. The component of claim 1 , wherein the reinforcing material comprises at least one of a plurality of fibers and particulate.

7. The component of claim 1 , wherein the reinforcing material includes alumina.

8. The component of claim 1 , wherein the metal matrix of the first layer portion is of a same material as the metal matrix of the second layer.

9. The component of claim 1 , wherein the metal matrix of at least one of the first and second layers comprises aluminum.

10. The component of claim 1 , wherein the aircraft wing component comprises at least part of a trailing edge of a wing.

11. The component of claim 1 , wherein the aircraft wing component comprises an aircraft control surface.

12. A method of manufacturing an aircraft wing component, the aircraft wing component comprising a composite material, wherein:
a first layer of the composite material comprises a metal matrix containing reinforcing material;
a second layer of the composite material comprises a metal matrix containing a plurality of hollow spheres comprising alumina; and
wherein the second layer portion is adjacent to an external surface of the composite material, such that the first layer portion is spaced apart from the external surface of the composite material by the second layer;

the method comprising:
laying up the spheres and the reinforcing material in a mold;
introducing a metal into the mold; and
solidifying the liquid metal into a solid.

13. The method of claim 12 , comprising, when laying up the spheres and the reinforcing material in the mold, vibrating the mold to distribute the spheres within the mold.

14. A wing assembly comprising:
a wing main body;
an engine; and
an aircraft wing component arranged downstream of the engine, the aircraft wing component comprising a composite material, wherein:
a first layer of the composite material comprises a metal matrix containing reinforcing material; and
a second layer of the composite material comprises a metal matrix containing a plurality of hollow spheres comprising alumina;
wherein the second layer is adjacent to an external surface of the composite material in a thickness direction of the aircraft wing component, such that the first layer is spaced apart in the thickness direction from the external surface of the composite material by the second layer.

15. An aircraft incorporating the wing assembly of claim 14 .

Assignees

• Airbus Operations Ltd

Inventors

• Tulloch William

Classifications

• B64C3/36 Primary

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

• B22D19/14

  the objects being filamentary or particulate in form (making alloys containing fibres or filaments by contacting the fibres or filaments with molten metal C22C47/08) · CPC title

• B22D27/08

  Shaking, vibrating, or turning of moulds · CPC title

• B64C3/24

  Moulded or cast structures · CPC title

• B64F5/10

  Manufacturing or assembling aircraft, e.g. jigs therefor · CPC title