Method and apparatus for attaching a fuselage frame to a wing box

Patent metadata

Field	Value
Publication number	US-11136107-B2
Application number	US-201816152788-A
Country	US
Kind code	B2
Filing date	Oct 5, 2018
Priority date	Oct 5, 2018
Publication date	Oct 5, 2021
Grant date	Oct 5, 2021

Abstract

An aircraft includes an aircraft body including a longitudinal axis and a wing box extending through the aircraft body. The aircraft also includes an attachment assembly coupled to the aircraft body and to the wing box. The attachment assembly includes a first attachment member coupled to the aircraft body and a second attachment member coupled to the wing box. The second attachment member is configured to couple to the first attachment member. The attachment assembly also includes a plurality of fasteners extending through the first attachment member and the second attachment member such that the plurality of fasteners are loaded in shear during a wing loading condition.

First claim

What is claimed is:

1. An aircraft comprising:
an aircraft body including a longitudinal axis;
a wing box extending through the aircraft body; and
an attachment assembly coupled to said aircraft body and to said wing box, said attachment assembly comprising:
a first attachment member coupled to the aircraft body, wherein said first attachment member comprises an outer flange having a distal end;
a second attachment member coupled to said wing box, wherein said second attachment member is configured to couple to said first attachment member, wherein said second attachment member comprises a horizontally-oriented end surface spaced from said distal end to define a gap therebetween when said first attachment member is coupled to said second attachment member;
a bearing plate removably coupled to said horizontally-oriented end surface and positioned within said gap; and
a plurality of fasteners extending through said first attachment member and said second attachment member such that said plurality of fasteners are loaded in shear during a wing loading condition.

2. The aircraft of claim 1 , wherein said plurality of fasteners are oriented substantially parallel to the longitudinal axis of said aircraft body.

3. The aircraft of claim 1 , wherein the engagement member and the extension tab are both oriented substantially perpendicular to a longitudinal axis of the aircraft body.

4. The aircraft of claim 1 , wherein said first attachment member comprises an engagement member and wherein said second attachment member comprises an extension tab configured to couple to said engagement member.

5. The aircraft of claim 4 , wherein said outer flange extends from said engagement member.

6. The aircraft of claim 4 , wherein said plurality of fasteners extends through said engagement member and said extension tab.

7. The aircraft of claim 6 , wherein said extension tab extends away from said wing box.

8. The aircraft of claim 1 , wherein said first attachment member is configured to engage said bearing plate during a wing loading condition, and wherein said first attachment member is configured to be spaced from said bearing plate when the aircraft is not experiencing the wing loading condition.

9. The aircraft of claim 8 , wherein said bearing plate is coupled to said second attachment member proximate said extension tab and is configured to engage said first attachment member during the wing loading condition.

10. An attachment assembly for attaching an aircraft body to a wing box of an aircraft, the attachment assembly comprising:
a first attachment member configured to be coupled to the aircraft body and comprising an engagement member, wherein said first attachment member comprises an outer flange having a distal end;
a second attachment member configured to be coupled to the wing box and comprising an extension tab extending away from said wing box, wherein said extension tab is configured to couple to said engagement member, wherein said second attachment member comprises a body portion having a horizontally-oriented end surface spaced from said distal end to define a gap therebetween when said first attachment member is coupled to said second attachment member;
a bearing plate removably coupled to said horizontally-oriented end surface and positioned within said gap; and
a plurality of fasteners configured to extend through said extension tab and said engagement member such that said plurality of fasteners are loaded in shear during a wing loading condition.

11. The attachment assembly of claim 10 , wherein said first attachment member is configured to engage said bearing plate during a wing loading condition, and wherein said first attachment member is configured to be spaced from said bearing plate when the aircraft is not experiencing the wing loading condition.

12. The attachment assembly of claim 10 , wherein said bearing plate is coupled to said second attachment member proximate said extension tab and is configured to engage said first attachment member during the wing loading condition.

13. The attachment assembly of claim 10 , wherein said plurality of fasteners are oriented substantially parallel to a longitudinal axis of the aircraft body.

14. The attachment assembly of claim 10 , wherein said extension tab extends away from said wing box.

15. The attachment assembly of claim 10 , wherein said extension tab extends from said horizontally-oriented end surface in a direction away from said body portion.

16. The attachment assembly of claim 15 , wherein said outer flange extends from said engagement member.

17. A method of assembling an aircraft, the method comprising:
forming a wing box;
forming an aircraft body configured to be coupled to the wing box;
coupling a first attachment member to the aircraft body, wherein the first attachment member includes an outer flange having a distal end;
coupling a second attachment member to the wing box, wherein the second attachment member includes a horizontally-oriented end surface;
aligning the wing box with the aircraft body for fixed attachment;
coupling the first attachment member to the second attachment member with a plurality of fasteners such that the plurality of fasteners are loaded in shear during a wing loading condition and such that the distal end of the outer flange is spaced from the end surface to define a gap therebetween; and
coupling a bearing plate to the end surface and within the gap such that the bearing plate is configured to engage the distal end of the outer flange during the wing loading condition.

18. The method of claim 17 , wherein coupling the first attachment member of the second attachment member comprises coupling an engagement member of the first attachment member to an extension tab of the second attachment member, wherein the extension tab extends away from the wing box.

19. The method of claim 18 , wherein coupling the engagement member to the extension tab comprises inserting the fasteners in a direction substantially parallel to a longitudinal axis of the aircraft body.

20. The method of claim 18 , wherein coupling the engagement member to the extension tab comprises coupling the engagement member to the extension tab such that the engagement member and the extension tab are both oriented substantially perpendicular to a longitudinal axis of the aircraft body.

Assignees

• Boeing Co

Inventors

• Cominsky Kenneth D
• Beneke Brent Edward

Classifications

• B64C1/26 Primary

  Attaching the wing or tail units or stabilising surfaces · CPC title

• B64F5/10

  Manufacturing or assembling aircraft, e.g. jigs therefor · CPC title