AIRCRAFT WING BOX JOINT

• US 20130062467A1
• Filed: 01/21/2011
• Published: 03/14/2013
• Est. Priority Date: 06/14/2010
• Status: Active Grant

• Current Assignee: Airbus Operations Limited (Airbus SE)
• Original Assignee: Airbus Operations Limited (Airbus SE)
• Inventors: Soenarjo, Mochamad Agoes
• Granted Patent: US 9,004,406 B2
• Time in Patent Office: Days
• US Class Current: 244/123.1
• CPC Class Codes: B64C 1/26 Attaching the wing or tail units or stabilising surfaces
• CPC Class Codes: B64C 3/187 Ribs
• CPC Class Codes: C08K 3/04 Carbon
• CPC Class Codes: C08K 5/14 Peroxides
• CPC Class Codes: C08K 5/34924 containing cyanurate groups; Tautomers thereof
• CPC Class Codes: C08L 23/02 not modified by chemical after-treatment
• CPC Class Codes: C08L 2666/02 Organic macromolecular compounds, natural resins, waxes or and bituminous materials
• CPC Class Codes: Y10T 29/49622 Vehicular structural member making

Abstract

An aircraft wing box spanwise joint, comprising a rib having a web, and a pair of rib fittings joined together, each rib fitting forming a closed loop around the periphery of the rib, wherein the rib is integrally formed with one of the rib fittings. Also, an aircraft wing including two or more of the joints. Also, a method of forming an aircraft wing box spanwise joint, the method comprising forming a pair of rib fittings, wherein one of the rib fittings is integrally formed with a rib having a web, each rib fitting forming a closed loop around the periphery of the rib, bringing the rib fittings together, and joining the rib fittings together.

Claims

1. An aircraft wing box spanwise joint comprising a rib having a web, and a pair of rib fittings joined together, each rib fitting forming a closed loop around the periphery of the rib, wherein the rib is integrally formed with one of the rib fittings.

2. A joint according to claim 1, wherein each rib fitting includes a spanwise projecting flange.

3. A joint according to claim 2, wherein the flange forms a closed loop around the periphery of the rib.

4. A joint according to claim 1, wherein each rib fitting has a substantially L-shaped cross-section extending around the rib to form the closed loop.

5. A joint according to claim 4, wherein the rib fittings are joined back-to-back.

6. A joint according to claim 1, wherein the rib fittings are joined together by fastening.

7. A joint according to claim 1, wherein the other rib fitting has a central void.

8. A joint according to claim 1, further comprising stiffeners supporting the rib web.

9. A joint according to claim 8, wherein the stiffeners are integrally formed with the rib web.

10. A joint according to claim 1, which joins two wing box structures, wherein each rib fitting forms part of a respective one of the wing box structures.

11. A joint according to claim 10, wherein each wing box structure is a centre or lateral wing box structure, or part thereof.

12. A joint according to claim 11, wherein the joint is a root joint between a centre wing box structure and a lateral wing box structure.

13. A joint according to claim 10, wherein each wing box structure includes wing box covers, and the rib fittings are attached to the covers of their respective wing box structure.

14. A joint according to claim 10, wherein each wing box structure includes wing box spars, and the rib fittings are attached to the spars of their respective wing box structure.

15. An aircraft wing including two or more joints in accordance with claim 1.

16. A method of forming an aircraft wing box spanwise joint, the method comprising forming a pair of rib fittings, wherein one of the rib fittings is integrally formed with a rib having a web, each rib fitting forming a closed loop around the periphery of the rib, bringing the rib fittings together, and joining the rib fittings together.

17. A method according to claim 16, wherein each rib fitting forms part of a wing box structure, and the method further comprises attaching each rib fitting to the remainder of its wing box structure.

18. A method according to claim 17, wherein each rib fitting is attached to the remainder of its wing box structure prior to joining the rib fittings together.