COMPOSITE AND STRUCTURE, PARTICULARLY IN THE AEROSPACE SECTOR

• US 20110095130A1
• Filed: 10/29/2010
• Published: 04/28/2011
• Est. Priority Date: 05/30/2008
• Status: Active Grant

• Current Assignee: Airbus Operations GmbH (Airbus SE)
• Original Assignee: Airbus Operations GmbH (Airbus SE)
• Inventors: Luettig, Helmut
• Granted Patent: US 8,403,263 B2
• Time in Patent Office: Days
• US Class Current: 244/119
• CPC Class Codes: B64C 1/064 Stringers; Longerons
• CPC Class Codes: B64C 2001/0072 from composite materials
• CPC Class Codes: Y02T 50/40 Weight reduction
• CPC Class Codes: Y10T 428/24008 including fastener for attaching to external surface
• CPC Class Codes: Y10T 428/24628 Nonplanar uniform thickness material

Abstract

The present invention provides a composite, in particular in the field of aviation and aerospace, comprising an omega-stringer that comprises a comb portion, and a connecting member that is connected at one end to the comb portion of the omega-stringer and can be connected at its other end to a standard coupling member. The idea underlying the present invention consists in forming omega-stringers with a connection zone that, on the one hand, is coupled to the comb portion of the omega-stringer and therefore makes it possible to transfer comparatively high loads and, on the other hand, can be connected to a standard coupling member so as to utilise the advantages of standard coupling members of this type when connecting omega-stringers to other stringers, for example T-stringers or other omega-stringers.

Claims

1. A composite, in particular in the field of aviation and aerospace, comprising:

an omega-stringer that comprises a comb portion; and

a connecting member that, at one end comprising an l-shaped cross-section, extends into the omega-stringer and is connected to the comb portion of the omega-stringer, and can be connected at its other end to a standard coupling member.

2. The composite according to claim 1, wherein the l-shaped cross-section of the one end of the connecting member comprises two flange portions and a web portion connecting them, one of the flange portions being connected to the comb portion of the omega-stringer.

3. The composite according to claim 2, wherein the comb portion of the omega-stringer is composed of a roof portion and two bevel portions connecting to opposite ends of the roof portion;

and in that the one of the flange portions is connected to the roof portion over its entire width and bevels moulded integrally on the flange portion are connected to the bevel portions, overlapping in part.

4. The composite according to claim 2, wherein the composite further comprises a planar portion;

and in that the omega-stringer is provided with two foot portions, which connect to opposite ends of the comb portion and are oriented so as to be substantially mutually opposed;

the foot portions of the omega-stringer and the other flange portion of the connecting member being connected to the planar portion, in particular by a doubler.

5. The composite according to claim 4, wherein the connecting member comprises, at its other end, an at least L-shaped cross-section with a foot portion that is connected to the planar member, and a web portion, the at least L-shaped cross-section being formed by trimming the l-shaped cross-section.

6. The composite according to claim 1, wherein the connecting member comprises a mounting portion for mounting a thrust vane or clip, in particular a former angle bracket.

7. Structure, in particular a fuselage, comprising:

a composite according to claim 1;

a stringer; and

a standard coupling member that connects the connecting member of the composite to the stringer.

8. Structure according to claim 7, wherein the standard coupling member comprises an L-, C-, Z- or T-shaped cross-section.

9. Structure according to claim 7, wherein the stringer is connected to the standard coupling member by a further connecting member, and the stringer and the further connecting member form a further composite according to claim 1.