Joint assembly and method of assembling same

Patent metadata

Field	Value
Publication number	US-9315254-B2
Application number	US-201314051926-A
Country	US
Kind code	B2
Filing date	Oct 11, 2013
Priority date	Oct 11, 2013
Publication date	Apr 19, 2016
Grant date	Apr 19, 2016

Abstract

A joint assembly for an aircraft is provided. The joint assembly includes a single main fitting including a first flange, a second flange, and a third flange, an external spar component coupled to the first flange using at least one fastener, an internal spar component coupled to the second flange using at least one fastener, and a body rib coupled to the third flange using at least one fastener.

First claim

What is claimed is:

1. A joint assembly for an aircraft, said joint assembly comprising:
a single main fitting comprising a first flange, a second flange, and a third flange, wherein said main fitting is elongate in a substantially vertical direction when positioned in the aircraft with a landing gear assembly contacting a substantially horizontal ground surface;
an external spar component coupled to said first flange;
an internal spar component coupled to said second flange;
a body rib coupled to said third flange, said body rib extending away from said third flange towards a front of the aircraft; and
an intermediate fitting configured to directly couple said main fitting to the landing gear assembly.

2. A joint assembly in accordance with claim 1 , further comprising:
a side fitting coupled to said external spar component; and
said intermediate fitting coupled between said side fitting and said main fitting.

3. A joint assembly in accordance with claim 1 , wherein said second flange is substantially orthogonal to said third flange.

4. A joint assembly in accordance with claim 1 , wherein said main fitting comprises an upper portion and a base portion, and wherein said first, second, and third flanges are formed on said base portion.

5. A joint assembly in accordance with claim 4 , wherein said upper portion comprises an arcuate surface configured to couple to a skin of the aircraft.

6. A joint assembly in accordance with claim 1 , wherein said main fitting is configured to provide a substantially vertical load path when loads are applied to said joint assembly.

7. A joint assembly in accordance with claim 1 , wherein said first, second, and third flanges are elongate in the substantially vertical direction.

8. A joint for an aircraft, said joint comprising a single main fitting that comprises:
a first flange configured to couple said main fitting to an external spar component of the aircraft;
a second flange configured to couple said main fitting to an internal spar component of the aircraft;
a third flange configured to couple said main fitting to a body rib of the aircraft such that the body rib extends away from said third flange towards a front of the aircraft, wherein said main fitting is elongate in a substantially vertical direction when positioned in the aircraft with a landing gear assembly contacting a substantially horizontal ground surface; and
an intermediate fitting configured to directly couple said main fitting to the landing gear assembly.

9. A joint in accordance with claim 8 , further comprising:
a side fitting configured to couple to the external spar component; and
said intermediate fitting coupled between said side fitting and said main fitting.

10. A joint in accordance with claim 8 , wherein said second flange is substantially orthogonal to said third flange.

11. A joint in accordance with claim 8 , wherein said main fitting comprises an upper portion and a base portion, and wherein said first, second, and third flanges are formed on said base portion.

12. A joint in accordance with claim 11 , wherein said upper portion comprises an arcuate surface configured to couple to a skin of the aircraft.

13. A joint in accordance with claim 8 , wherein said main fitting is configured to provide a substantially vertical load path when loads are applied to said joint.

14. A method of assembling a joint assembly of an aircraft, said method comprising:
coupling an external spar component of the aircraft to a first flange of a single main fitting;
coupling an internal spar component of the aircraft to a second flange of the main fitting;
coupling a body rib of the aircraft to a third flange of the main fitting such that the body rib extends away from the third flange towards a front of the aircraft, wherein said main fitting is elongate in a substantially vertical direction when positioned in the aircraft with a landing gear assembly contacting a substantially horizontal ground surface; and
directly coupling the main fitting to a landing gear assembly of the aircraft using an intermediate fitting.

15. A method in accordance with claim 14 , further comprising:
coupling a side fitting to the external spar component; and
coupling the intermediate fitting between the side fitting and the main fitting.

16. A method in accordance with claim 14 , wherein coupling a body rib comprises coupling the body rib to the third flange such that the body rib is oriented substantially orthogonal to the internal spar component.

17. A method in accordance with claim 14 , wherein the main fitting includes an upper portion and a base portion, said method further comprising forming the first, second, and third flanges on the base portion of the main fitting.

18. A method in accordance with claim 17 , further comprising coupling a skin of the aircraft to an arcuate surface on the upper portion of the main fitting.

Assignees

• Boeing Co

Inventors

• Walker Steven Paul
• Veit Joanna Mara Sergiane
• Cambronero Jr Isaac G
• Davis James Donald
• Pagliarini Michael D

Classifications

• B64C1/26 Primary

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

• Y10T29/49622

  Vehicular structural member making · CPC title

• B64C3/187

  Ribs · CPC title

• B64C3/185

  Spars · CPC title

• B64F5/10 Primary

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