Joints between a composite skin and a load-bearing component and methods of forming same

Patent metadata

Field	Value
Publication number	US-9399507-B2
Application number	US-201414161241-A
Country	US
Kind code	B2
Filing date	Jan 22, 2014
Priority date	Jan 22, 2014
Publication date	Jul 26, 2016
Grant date	Jul 26, 2016

Abstract

A method of forming a direct bearing joint includes providing a load bearing structure including a first structural feature having an arcuate shape and providing a composite skin including a second structural feature also having an arcuate shape. The method also includes coupling the first structural feature to the second structural feature such that the first and second structural features are mated against each other to facilitate distributing compressive loads induced into the load bearing structure into the composite skin.

First claim

What is claimed is:

1. A method of forming a direct bearing joint, said method comprising:
providing a load bearing structure including a first portion and a second portion, coupled to and extending from the first portion such that the first portion is substantially perpendicular to the second portion, the first portion including a first structural feature having an arcuate shape, wherein the load bearing structure includes one of a longeron, a keel beam, and a wing spar of an aircraft;
providing a composite skin including a second structural feature having an arcuate shape;
coupling the composite skin between a structural flange on the first portion of the load bearing structure and a bulkhead; and
coupling the first structural feature to the second structural feature such that the first and second structural features are mated against each other to facilitate distributing compressive loads induced into the load bearing structure into the composite skin.

2. The method in accordance with claim 1 , wherein providing a load bearing structure including a first structural feature further comprises providing a load bearing structure including a convex platform edge, and wherein providing a composite skin including a first structural feature further comprises providing a composite skin including a concave cutout edge.

3. The method in accordance with claim 2 , wherein coupling the first structural feature to the second structural feature further comprises mating the convex platform edge in continuous direct contact against the concave cutout edge.

4. The method in accordance with claim 1 , further comprising coupling the load bearing structure to the composite skin using a plurality of fasteners such that a first load path is defined through the first and second structural features and a second load path is defined through the plurality of fasteners.

5. The method in accordance with claim 1 , wherein providing a load bearing structure further comprises providing a bearing plate.

6. The method in accordance with claim 1 further comprising:
coupling a first inner surface of the load bearing structure in a face-to-face relationship with an outer surface of the bulkhead; and
coupling a second inner surface of the composite skin in a face-to-face relationship with the outer surface such that the first and second inner surfaces are flush.

7. A direct bearing joint comprising:
a load bearing structure comprising a first portion and a second portion, said first portion comprising a structural flange and said second portion coupled to and extending from said first portion such that said first portion is substantially perpendicular to said second portion, said first portion comprising a first structural feature that has an arcuate shape, wherein the load bearing structure comprises one of a longeron, a keel beam, and a wing spar of an aircraft; and
a composite skin coupled to said load bearing structure, said composite skin comprising a second structural feature that has an arcuate shape, said second structural feature configured to mate against said first structural feature to facilitate distributing compressive loads induced into said load bearing structure into said composite skin, wherein said composite skin is coupled between said structural flange and a bulkhead.

8. The joint in accordance with claim 7 , wherein said first structural feature is a convex platform and said second structural feature is a complementary concave cutout.

9. The joint in accordance with claim 7 , wherein said first structural feature comprises a first edge, and said second structural feature comprises a second edge that is shaped to mate against said first edge.

10. The joint in accordance with claim 7 , further comprising a plurality of fasteners configured to couple said composite skin to said load bearing structure, such that a first load path is defined through said first and second structural features, and a second load path is defined through said plurality of fasteners.

11. The joint in accordance with claim 7 , wherein said load bearing structure is a bearing plate coupled to one of the wheel well longeron, keel beam, and wing spar.

12. The joint in accordance with claim 9 , wherein said load bearing structure comprises a first inner surface coupled in a mating relationship with an outer surface of said bulkhead, said composite skin comprises a second inner surface coupled in a mating relationship with said outer surface of said bulkhead such that said first and second inner surfaces are substantially flush against each other.

13. An aircraft comprising a direct bearing joint, said aircraft comprising:
a bulkhead;
a load bearing structure coupled to said bulkhead and comprising a first portion and a second portion, said first portion comprising a structural flange and said second portion coupled to and extending from said first portion such that said first portion is substantially perpendicular to said second portion, said first portion comprising a first structural feature that has an arcuate shape, wherein the load bearing structure comprises one of a longeron, a keel beam, and a wing spar of an aircraft;
a composite skin coupled between said structural flange and said bulkhead, said composite skin comprising a second structural feature that has an arcuate shape, and said second structural feature configured to mate against said first structural feature to facilitate distributing compressive loads induced into said load bearing structure into said composite skin.

14. The aircraft in accordance with claim 13 , wherein said first structural feature comprises a first edge, said second structural feature comprises a second edge that is shaped to mate against said first edge.

15. The aircraft in accordance with claim 13 further comprising a plurality of fasteners configured to couple said composite skin to said load bearing structure, such that a first load path is defined through said first and second structural features, and a second load path is defined through said plurality of fasteners.

Assignees

• Boeing Co

Inventors

• Rosman Richard R
• Dopker Bernhard
• Chan Wallace Chi-Hua

Classifications

• B29K2307/04

  Carbon · CPC title

• B29C65/562

  using extra joining elements, i.e. which are not integral with the parts to be joined (using plastic snap elements B29C65/58; using plastic rivets B29C65/601) · CPC title

• Y10T29/49696

  Mounting · CPC title

• B29C66/721

  Fibre-reinforced materials (B29C66/729 takes precedence) · CPC title

• Y10T403/70

  Interfitted members · CPC title