Joining fuselage skins using friction stir welding

Patent metadata

Field	Value
Publication number	US-9015948-B2
Application number	US-1700708-A
Country	US
Kind code	B2
Filing date	Jan 19, 2008
Priority date	Jan 19, 2008
Publication date	Apr 28, 2015
Grant date	Apr 28, 2015

Abstract

Fuselage skins of aircraft are joined using friction stir welding. A strip of cladding is removed from the skins along an abutment between the skins before the skins are welded in order to prevent the cladding from interfering with the welding process. The cladding is replaced after the welding is completed.

First claim

What is claimed is:

1. A method of joining clad metal aircraft skins, comprising:
removing a layer of clad material from an aircraft skin along an edge of the aircraft skin and from another aircraft skin along an edge of the other aircraft skin, the aircraft skin and the other aircraft skin including aluminum or aluminum alloy aside from the clad material;
placing the edge of the aircraft skin in an edge-to-edge abutment with the edge of the other aircraft skin, an upper surface of the edge of the aircraft skin substantially abutting an upper surface of the edge of the other aircraft skin;
friction stir welding the aircraft skin and the other aircraft skin along the edge-to edge abutment using a rotating pin tool, wherein removing the layer of clad material is sufficient to avoid interference with plastic deformation and recrystallization of the aluminum or aluminum alloy during the friction stir welding; and
adding clad material along the edge of the aircraft skin and along the edge of the other aircraft skin where the layer of clad material was removed.

2. The method of claim 1 , wherein the layer of clad material is removed by one of the following processes:
pickling,
chemical etching,
mechanical abrasion,
machining.

3. The method of claim 1 , wherein adding clad material is performed by one of:
air plasma spray,
combustion powder spray,
high velocity oxy fuel,
cold spray,
electric arc wire spray,
combustion wire spray,
ROKIDE® spray,
flame spray.

4. The method of claim 1 , wherein the friction stir welding includes holding the rotating pin tool against the surface of the skins in the area where the clad material has been removed.

5. The method of claim 1 , wherein said aircraft skin and said other aircraft skin comprise an aircraft fuselage.

6. The method of claim 1 , further comprising:
forming the aircraft skin and the other aircraft skin into a desired shape before the welding is performed.

7. The method of claim 1 , further comprising removing a layer of base metal from each of the skin sections beneath the layer of clad material.

8. The method of claim 1 , wherein the friction stir welding is performed by:
frictionally engaging opposite sides of the skin sections along the edge-to-edge abutment with first and second rotating shoulder tools,
moving the first and second rotating shoulder tools along the length of the edge-to-edge abutment, and
passing the rotating pin tool through the skin sections along the edge-to-edge abutment as the first and second rotating shoulder tools are moved along the length of the abutment.

9. A method of welding two clad metal fuselage skins, comprising:
forming an abutment between opposing edges of the fuselage skins;
removing a layer of cladding from one side of each of the skins along the abutment, an upper surface of each of said edges substantially abutting each other, the skins consisting of aluminum alloy aside from the layer of cladding; and,
friction stir welding the edges of the skins together along the abutment after the layer of cladding has been removed, the friction stir welding using a rotating pin tool and removing the layer of cladding being sufficient to avoid interference with plastic deformation and recrystallization of the aluminum alloy during the friction stir welding; and
adding cladding on the one side of each of the skins along the abutment where the layer of cladding was removed.

10. The method of claim 9 , further comprising removing a layer of base metal from the skins beneath the layer of cladding.

11. The method of claim 9 , wherein the friction stir welding is performed by:
frictionally engaging opposite sides of the skins along the abutment with first and second rotating shoulder tools,
moving the first and second rotating shoulder tools along the length of the abutment, and
passing the rotating pin tool through the skins along the abutment as the first and second rotating shoulder tools are moved along the length of the abutment.

12. The method of claim 9 , wherein removing the layer of cladding includes removing strips of the cladding along the opposing edges of the skins.

13. The method of claim 9 , wherein the layer of cladding is removed by one of the following processes:
pickling,
chemical etching,
mechanical abrasion,
machining.

14. The method of claim 9 , wherein adding cladding is performed using one of the following processes:
air plasma spray,
combustion powder spray,
high velocity oxy fuel,
cold spray,
electric arc wire spray,
combustion wire spray,
ROKIDE® spray,
flame spray.

15. The method of claim 9 , wherein said fuselage skins comprise an aircraft fuselage.

16. The method of claim 9 , further comprising:
forming the skin sections into a desired shape before the welding is performed.

17. A joining method comprising:
placing edges of clad metal skin sections of an aircraft fuselage in facing relationship to form an abutment between the skin sections;
removing a strip of material from one side of each of the clad metal skin sections along the abutment, including removing a layer of cladding along the strip and removing a layer of metal underlying the layer of cladding along the strip, an upper surface of each of the edges substantially abutting each other and the clad metal skin sections consisting of aluminum alloy aside from the layer of cladding; and
friction stir welding the edges of the clad metal skin sections together along the abutment after the layer of cladding has been removed, wherein friction stir welding the edges of the clad metal skin sections together includes:
frictionally engaging the opposite side of each of the skin sections along the abutment with a rotating shoulder tool,
moving the rotating shoulder tool along the length of the abutment, and
passing a rotating pin tool through the skin sections along the abutment as the rotating shoulder tool is moved along the length of the abutment, wherein removing the layer of cladding is sufficient to avoid interference with plastic deformation and recrystallization of the aluminum alloy during the friction stir welding; and

adding cladding along the length of the abutment on the one side of the skin sections in the area where the strip of material has been removed.

18. The method of claim 17 , wherein the layer of cladding is removed by one of the following processes:
pickling,
chemical etching,
mechanical abrasion,
machining.

19. The method of claim 17 , wherein adding cladding is performed using one of the following processes:
air plasma spray,
combustion powder spray,
high velocity oxy fuel,
cold spray,
electric arc wire spray,
combustion wire spray,
ROKIDE® spray,
flame spray.

20. The method of claim 17 , further comprising:
forming the skin sections into a desired shape before the welding is performed.

Assignees

• Talwar Rajesh
• Lederich Richard
• Boeing Co

Inventors

• Talwar Rajesh
• Lederich Richard

Classifications

• B23K20/1255 Primary

  Tools therefor, e.g. characterised by the shape of the probe · CPC title

• B23K2201/34

  Operations & Transport · mapped topic

• Y10T29/49728

  and by a metallurgical operation, e.g., welding, diffusion bonding, casting · CPC title

• Y10T29/49622

  Vehicular structural member making · CPC title

• B23P6/00

  Restoring or reconditioning objects (straightening or restoring form of sheet metal, metal rods, metal tubes, metal profiles, or specific articles made therefrom B21D1/00, B21D3/00; repairing defective or damaged objects by casting techniques B22D19/10) · CPC title