Joint assembly and method of assembling the same

Patent metadata

Field	Value
Publication number	US-9441652-B2
Application number	US-201313906734-A
Country	US
Kind code	B2
Filing date	May 31, 2013
Priority date	May 31, 2013
Publication date	Sep 13, 2016
Grant date	Sep 13, 2016

Abstract

A joint assembly is that includes a first component and a second component that includes a first portion and a plurality of flexible members extending therefrom for coupling the second component to the first component. The plurality of flexible members are preloaded in a predetermined direction and are configured to flex in a direction opposite to the predetermined direction when coupling the second component to the first component.

First claim

What is claimed is:

1. A joint assembly comprising:
a first component comprising a first barrel section having a first edge portion; and
a second component comprising a second barrel section having a second edge portion with a plurality of flexible members extending longitudinally therefrom that are configured to flex when coupling said flexible members to said first edge portion of said first component, wherein said plurality of flexible members are configured to individually uncouple from said first component such that a disbond between said first component and said second component is restricted from spreading laterally to adjacent flexible members of said plurality of flexible members; and
wherein a joint formed by said first and second edge portions defines a substantially uniform thickness.

2. The assembly in accordance with claim 1 , wherein at least some of said plurality of flexible members are tapered to a tip of said second component having a reduced thickness.

3. The assembly in accordance with claim 1 , wherein said first component and said second component are each tapered such that a joint defined between said first and second components is formed with a substantially uniform thickness.

4. The assembly in accordance with claim 1 , wherein said plurality of flexible members are preloaded in a predetermined direction and are configured to flex in a direction opposite to the predetermined direction when coupling said second component to said first component.

5. The assembly in accordance with claim 4 , wherein said plurality of flexible members are bent towards said first component to be preloaded in the predetermined direction.

6. The assembly in accordance with claim 5 , wherein said plurality of flexible members are flexed in the direction opposite to the predetermined direction to apply tension to said first component.

7. The assembly in accordance with claim 4 , wherein said plurality of flexible members are bent away from said first component to be preloaded in the predetermined direction.

8. The assembly in accordance with claim 7 , wherein said plurality of flexible members are flexed in the direction opposite to the predetermined direction to apply compression to said first component.

9. The assembly in accordance with claim 1 , wherein said plurality of flexible members are separated by a gap defined between adjacent pairs of said plurality of flexible members.

10. The assembly in accordance with claim 1 , wherein said plurality of flexible members are integrally formed with said second edge portion.

11. A fuselage assembly comprising:
a first barrel section comprising a body portion extending from a first end to a second end; and
a second barrel section comprising a body portion extending from a first end to a second end and a plurality of flexible members extending longitudinally from at least one of said first end and said second end of said second barrel section, wherein said plurality of flexible members are configured to flex when coupling said flexible members to one of said first and second ends of said first barrel section, and wherein said flexible members are configured to individually uncouple from said first component such that a disbond between said first barrel section and said second barrel section is restricted from spreading laterally to adjacent flexible members of said plurality of flexible members; and
wherein a joint formed by said first and second barrel sections defines a substantially uniform thickness.

12. The assembly in accordance with claim 11 , wherein said first barrel section comprises a bond surface that is configured to mate with said plurality of flexible members.

13. The assembly in accordance with claim 11 , wherein said plurality of flexible members are fabricated from a composite material.

14. The assembly in accordance with claim 11 , wherein said plurality of flexible members are tapered to facilitate improving a gradual load transition into a joint defined between said first barrel section and said second barrel section.

15. A method of assembling a joint, said method comprising:
providing a first component comprising a first barrel section including a first edge portion and a plurality of flexible members extending longitudinally therefrom;
providing a second component comprising a second barrel section including a second edge portion; and
coupling the plurality of flexible members to said second edge portion of said second component, wherein said flexible members are configured to flex when coupling said flexible members to the second edge portion of said second component, wherein the plurality of flexible members are configured to individually uncouple from the first component such that a disbond between the first component and the second component is restricted from spreading laterally to adjacent flexible members of the plurality of flexible members, wherein a joint formed by said first and second edge portions defines a substantially uniform thickness.

16. The method in accordance with claim 15 further comprising preloading the plurality of flexible members in a predetermined direction towards the second component.

17. The method in accordance with claim 15 further comprising preloading the plurality of flexible members in a predetermined direction that is away from the second component.

18. The method in accordance with claim 15 , wherein coupling the plurality of flexible members comprises applying an adhesive material to a bond surface defined along the second component.

19. The method in accordance with claim 15 , wherein defining a gap comprises extending a slit to an edge of the first component such that the plurality of flexible members are separated from each other.

Assignees

• Boeing Co

Inventors

• Griess Kenneth H
• Georgeson Gary

Classifications

• B29C65/48 Primary

  using adhesives {, i.e. using supplementary joining material; solvent bonding} · CPC title

• B29K2307/04

  Carbon · CPC title

• B29C66/344

  Stretching or tensioning the joint area during joining · CPC title

• B29C66/54

  Joining several hollow-preforms, e.g. half-shells, to form hollow articles, e.g. for making balls, containers; Joining several hollow-preforms, e.g. half-cylinders, to form tubular articles · CPC title

• B64C1/069

  Joining arrangements therefor · CPC title