Friction stir welded monolithic aircraft structure and method

Patent metadata

Field	Value
Publication number	US-11084569-B2
Application number	US-201816135777-A
Country	US
Kind code	B2
Filing date	Sep 19, 2018
Priority date	Sep 19, 2018
Publication date	Aug 10, 2021
Grant date	Aug 10, 2021

Abstract

A method of forming a monolithic aircraft structure having multiple aerodynamic surfaces includes forming a body component to have a body skin defining a body skin outer surface, and a body side wall integrally formed with the body skin and defining a body mating surface, the body skin outer surface providing a first aerodynamic surface. A cover component is formed to have a cover mating surface and a cover outer surface opposite the cover mating surface, the cover outer surface defining a second aerodynamic surface. The body component is positioned relative to the cover component so that the body mating surface engages the cover mating surface. At least portions of the cover mating surface are friction stir welded to the body mating surface to form friction stir welded joints between the body component and the cover component.

First claim

What is claimed is:

1. A method of forming a monolithic aircraft structure, comprising multiple aerodynamic surfaces, the method comprising steps of:
forming a body component, comprising a bottom side, a body skin, defining a body skin outer surface opposite the bottom side of the body component, a body side wall, integrally formed with the body skin and defining a body mating surface, and a stiffener, integrally formed with the body skin and the body side wall, the stiffener defining a stiffener mating surface, having a stiffener-mating-surface thickness, wherein the stiffener further comprises a boss, comprising a localized portion that has a thickness, which is greater than the stiffener-mating-surface thickness, wherein the body skin and the body side wall together define a cavity, open toward the bottom side of the body component, and wherein the body skin outer surface defines a first aerodynamic surface;
forming a cover component, sized to extend entirely over the cavity of the body component and having a cover mating surface and a cover outer surface, opposite the cover mating surface, the cover outer surface defining a second aerodynamic surface, wherein the cover mating surface of the cover component comprises a socket, sized to receive a part of the boss of the stiffener;
positioning the body component relative to the cover component so that thepart of the boss of the stiffener is inserted into the socket and the body mating surface contacts the cover mating surface, and the cover component encloses the cavity of the body component;
friction stir welding the cover component to the body component so that a friction stir welded joint extends along a portion of the cover mating surface of the cover component and a portion of the body mating surface of the body component; and
friction stir welding through the socket of the cover mating surface of the cover component and into the boss of the stiffener of the body component so that an additional friction stir welded joint is formed between the cover mating surface and the stiffener mating surface.

2. The method of claim 1 , wherein the additional friction stir welded joint extends along an entire length of the stiffener mating surface of the stiffener.

3. The method of claim 1 , further comprising heat treating the body component and the cover component.

4. The method of claim 1 , further comprising performing non-destructive inspection of the monolithic aircraft structure.

5. The method of claim 1 , further comprising applying at least one surface treatment selected from a group of surface treatments consisting of anodizing, primer coating, and topcoating to the body skin outer surface and the cover outer surface.

6. The method of claim 1 , wherein the step of forming the body component comprises machining the body component from a block of aluminum alloy material.

7. The method of claim 1 , wherein the step of forming the cover component comprises machining the cover component from a sheet of aluminum alloy material.

8. The method of claim 1 , wherein:
the step of forming the body component comprises a step of forming a spoiler body; and
the step of forming the cover component comprises a step of forming a spoiler cover.

9. The method of claim 8 , wherein the step of forming the spoiler body comprises forming lugs integrally with the body skin and the body side wall.

10. A monolithic aircraft structure, comprising:
a body component, comprising:
a bottom side;
a body skin having a body skin outer surface opposite the bottom side of the body component, wherein the body skin outer surface defines a first aerodynamic surface;
a body side wall integrally formed with the body skin and defining a body mating surface, wherein the body skin and the body side wall together define a cavity open to the bottom side of the body component; and
a stiffener, integrally formed with the body skin and the body side wall, the stiffener defining a stiffener mating surface, having a stiffener-mating-surface thickness, wherein the stiffener further comprises at least two bosses, wherein each of the at least two bosses comprises a localized portion that has a thickness, which is greater than the stiffener-mating-surface thickness;

a cover component sized to extend entirely over the cavity of the body component and having a cover mating surface and a cover outer surface opposite the cover mating surface, wherein the cover mating surface is shaped conformally with the body mating surface to enclose the cavity of the body component with the cover mating surface in contact with the body mating surface, and wherein the cover outer surface defines a second aerodynamic surface;
a friction stir welded joint, extending through the cover mating surface of the cover component and into the body mating surface, of the body component; and
additional friction stir welded joints, extending through the cover mating surface and into each of the at least two bosses of the stiffener.

11. The monolithic aircraft structure of claim 10 , wherein the additional friction stir welded joints extend along an entire length of the stiffener mating surface of the stiffener.

12. An aircraft spoiler, comprising:
a body component, comprising:
a bottom side;
a body skin having a body skin outer surface opposite the bottom side of the body component, wherein the body skin outer surface defines a first aerodynamic surface;
a body side wall integrally formed with the body skin and defining a body mating surface, the body side wall comprising first and second side panels joined by a rear panel, wherein the first and second side panels are generally triangular, and the body skin and the body side wall together define a cavity open to the bottom side of the body component; and
a stiffener, integrally formed with the body skin and the body side wall and located in the cavity of the body component between the first and second side panels to divide the cavity into sub-cavities, the stiffener defining a stiffener mating surface, having a stiffener-mating-surface thickness, wherein the stiffener further comprises at least two bosses, wherein each of the at least two bosses comprises a localized portion that has a thickness, which is greater than the stiffener-mating-surface thickness;

a cover component, sized to extend entirely over the cavity of the body component and having a cover mating surface and a cover outer surface opposite the cover mating surface, wherein the cover mating surface is shaped conformally with the body mating surface and the stiffener mating surface to enclose the sub-cavities and the stiffener of the body component with the cover mating surface in contact with the body mating surface, wherein the cover outer surface defines a second aerodynamic surface;
a friction stir welded joint, extending through the cover mating surface of the cover component and into the body mating surface of the body component; and
additional friction stir welded joints, extending through the cover mating surface of the cover component and into each of the at least two bosses of the stiffener.

13. The method of claim 1 , wherein the additional friction stir welded joint extends along a portion of a length of the stiffener mating surface of the stiffener.

14. The monolithic aircraft structure of claim 10 , wherein each of the additional friction stir welded joints extends along a portion of a length of the stiffener mating surface of the stiffener.

15. The monolithic aircraft structure of claim 10 , wherein the body component comprises aluminum alloy material.

16. The monolithic aircraft stru

Assignees

• Boeing Co

Inventors

• Shemkunas Michael P
• Schleuter Lisa G
• Dahl Bruce A
• Adjorlolo Alain A

Classifications

• Y02T50/40

  Weight reduction · CPC title

• B64C3/26 Primary

  Construction, shape, or attachment of separate skins, e.g. panels · CPC title

• B23K2101/18

  Sheet panels · CPC title

• B64C1/12

  Construction or attachment of skin panels · CPC title

• C22F1/04

  of aluminium or alloys based thereon · CPC title