Composite, aircraft or spacecraft, and method

Patent metadata

Field	Value
Publication number	US-9315252-B2
Application number	US-201313857439-A
Country	US
Kind code	B2
Filing date	Apr 5, 2013
Priority date	Oct 8, 2010
Publication date	Apr 19, 2016
Grant date	Apr 19, 2016

Abstract

The present invention provides a composite for an aircraft or spacecraft, comprising: a skin portion; a stringer which is attached to the skin portion; and a former made from fibre composite material, which is attached to the skin portion and forms an opening therewith, through which the stringer extends, substantially transverse to the former.

First claim

What is claimed is:

1. A composite for an aircraft or spacecraft, comprising:
a skin portion;
a stringer which is attached to the skin portion, wherein the stringer is constructed in a T-shape and comprises a foot portion and a web portion, wherein the foot portion and the web portion each form a closed wall; and
a former made from fibre composite material, which is attached to the skin portion and forms an opening therewith, through which the stringer extends completely with the foot portion and the web portion, substantially transverse to the former, wherein the only material disposed within the former is the transversely positioned stringer, wherein the former is constructed as a hollow Ω-profile with closed side-walls, wherein each of the closed side-walls is provided with the opening through which the stringer extends completely with its foot portion and its web portion, wherein a foot portion of the former is side by side with the foot portion of the stringer, and wherein the stringer is arranged to contact the skin portion and is riveted to the skin portion, but not fixed to the former.

2. The composite according to claim 1 , wherein the shape of the opening corresponds substantially to the external geometry of the stringer.

3. The composite according to claim 1 , wherein the stringer and the former is riveted to the skin portion.

4. The composite according to claim 1 , wherein the skin portion and/or the stringer are constructed from fibre composite material.

5. An aircraft or spacecraft, comprising a composite according to claim 1 .

6. A method for producing a composite, in particular the composite according to claim 1 , the method comprising:
joining a stringer to a skin portion, wherein the stringer is constructed in a T-shape and comprises foot portion and a web portion, wherein the foot portion and the web portion each form a closed wall, and wherein the stringer is arranged to contact the skin portion, but not fixed to the former, and is riveted to the skin portion; and
joining a former made from fibre composite material to the skin portion such that the stringer extends completely with the foot portion and the web portion through an opening formed between the former and the skin portion,
wherein the former is constructed as a hollow Ω-profile with closed side-walls, wherein each of the closed side-walls is provided with the opening through which the stringer extends completely with its foot portion and its web portion, wherein the only material disposed within the former is the transversely positioned stringer, and wherein a foot portion of the former is side by side with the foot portion of the stringer.

7. The method according to claim 6 , wherein the stringer and/or the former is riveted to the skin portion at the joining stage.

8. The method according to claim 6 , wherein the stringer and/or the skin portion is constructed from a fibre composite material and the stringer, former and/or the skin portion is at least partly cured at the joining stage.

Assignees

• Airbus Operations Gmbh

Inventors

• Dolzinski Wolf-Dietrich
• Kolax Michael

Classifications

• B64C1/064 Primary

  Stringers; Longerons · CPC title

• B64C1/061 Primary

  Frames · CPC title

• B64C1/10

  Bulkheads · CPC title

• Y10T428/24174

  including sheet or component perpendicular to plane of web or sheet · CPC title