Method of recycling a structure or at least a portion thereof, and component for an aircraft or spacecraft

Patent metadata

Field	Value
Publication number	US-12485482-B2
Application number	US-202318188714-A
Country	US
Kind code	B2
Filing date	Mar 23, 2023
Priority date	Mar 31, 2022
Publication date	Dec 2, 2025
Grant date	Dec 2, 2025

Abstract

A method of recycling a structure or at least a portion thereof, and component for an aircraft or spacecraft. The structure comprises components connected to each other and each made from a metal alloy. The method includes producing, at least from a plurality of the components, including components made from at least two different metal alloys, a powder adapted to being used as a starting material in an additive manufacturing process. Also, a component for an aircraft or spacecraft, made using additive manufacturing, the component being produced a powder obtained in accordance with the method.

First claim

The invention claimed is:

1 . A method of recycling a structure, or at least a portion thereof, wherein the structure comprises components connected to each other and each made from a metal alloy, wherein the method comprises:
producing, at least from material of a plurality of components including components made from at least two different metal alloys, a powder configured to be utilized as a starting material in an additive manufacturing process, wherein producing the powder comprises:
melting the material of the plurality of components to form a homogeneous melt;
melt atomizing the homogenous melt in order to obtain the powder; and
nano-decorating the powder with at least one additive.

2 . The method according to claim 1 , wherein the melt is formed by:
subjecting at least some of the components from the plurality of the components, or sections thereof, which are still connected to each other to melting, or mechanically reducing at least some of the components from the plurality of the components, or sections thereof, which are still connected to each other to smaller pieces and subjecting the smaller pieces to melting.

3 . The method according to claim 1 , wherein the producing comprises:
mechanically reducing the material of the plurality of components to powder, by cutting, or chopping, or shredding, or chipping, or grinding, or a combination thereof.

4 . The method according to claim 3 , wherein the mechanically reducing the material to powder comprises subjecting at least some of the components from the plurality of the components, or sections thereof, which are still connected to each other to cutting, or chopping, or shredding, or chipping, or grinding, or a combination thereof.

5 . The method according to claim 1 , wherein producing the powder further comprises subjecting the powder to a plasma treatment.

6 . The method according to claim 1 , wherein the at least one additive is selected from consisting of: titanium, silicon, a zirconium hydride, a titanium diboride, a calcium hexaboride, a lanthanum hexaboride, and mixtures thereof.

7 . The method according to claim 1 , wherein the additive manufacturing process is a powder bed process.

8 . The method according to claim 1 , wherein the components from the plurality of components includes components each made from an aluminum alloy.

9 . The method according to claim 1 , wherein the components from the plurality of components includes components made from alloys classified in at least two different alloy series, and
the method further comprising: producing a new component with the additive manufacturing process, wherein the new component comprises a cross-over alloy can be additively made.

10 . The method according to claim 1 , wherein the components from the plurality of components comprises one or more of at least a portion of an outer fuselage skin, a wing cover, a fuselage stringer, a wing stringer, a fuselage frame, an internal structural element of a fuselage, a bracket or a fastening element.

11 . The method according to claim 1 , wherein the components from the plurality of components comprises components connected to each other using rivets or using a bolted connection or welded to each other or adhesively bonded to each other.

12 . The method according to claim 1 , wherein at least some of the components from the plurality of components are connected to each other via connecting elements, in particular rivets or bolts, the connecting elements being formed with a material different from an aluminum alloy, wherein during production of the powder, the connecting elements are processed together with the components from the plurality of components.

13 . The method according to claim 1 , wherein the method further comprises:
selecting, based on documentation available of the structure to be recycled, components of the structure or sections thereof to be used for the production of a batch of a pre-defined powder.

14 . The method according to claim 1 , wherein the method further comprises:
producing a new component for an aircraft or spacecraft, wherein the producing of the new component includes the additive manufacturing process and the powder is used as the starting material in the additive manufacturing process for producing the new component.

15 . The method according to claim 1 , wherein the component is an aircraft or spacecraft structure.

16 . The method according to claim 1 , wherein the additive manufacturing process comprises locally melting the powder to form a melt and cooling the melt resulting therefrom at a cooling rate of at least 10,000 Kelvin per second.

17 . The method according to claim 1 , wherein the components from the plurality of components includes components each made from an aluminum alloy classified in a 2xxx aluminum alloy series, a 5xxx aluminum alloy series, a 6xxx aluminum alloy series, and a 7xxx aluminum alloy series.

18 . A component for an aircraft or spacecraft made using additive manufacturing, wherein the component is produced with the powder obtained in accordance with the method of claim 1 .

19 . A method of recycling a structure, or at least a portion thereof, wherein the structure comprises components connected to each other and each made from an aluminum alloy, wherein the method comprises:
producing, at least from material of a plurality of components including components made from at least two different aluminum alloys, a powder configured to be utilized as a starting material in an additive manufacturing process; wherein the additive manufacturing process comprises locally melting the powder as part of a laser powder bed fusion process to form a melt and cooling the melt resulting therefrom at a cooling rate of at least 10,000 Kelvin per second; wherein producing the powder comprises nano-decorating the powder with at least one additive which is an additive capable of acting as a grain refiner and nucleating agent, the additive being a fine powder nano-additive comprising particles having a particle size of <1000 nm.

Assignees

• Airbus Sas

Inventors

• Palm Frank
• Schimbäck David

Classifications

• B22F2301/052

  Aluminium · CPC title

• B22F2009/001

  from scrap particles · CPC title

• B22F9/04

  starting from solid material, e.g. by crushing, grinding or milling ({C22C1/1084 takes precedence}; crushing, grinding or milling, in general, see the relevant subclasses, e.g. B02C) · CPC title

• B22F1/14

  Treatment of metallic powder (mixing with lubricating or binding agents or with organic material B22F1/10) · CPC title

• B22F10/28

  Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM] · CPC title