Method for fabricating a central caisson of an aircraft wing made from composite material

Patent metadata

Field	Value
Publication number	US-11919259-B2
Application number	US-202117161062-A
Country	US
Kind code	B2
Filing date	Jan 28, 2021
Priority date	Jan 29, 2020
Publication date	Mar 5, 2024
Grant date	Mar 5, 2024

Abstract

A method for fabricating a central caisson of an aircraft wing including a frame formed from U-section crossmembers. Formation of at least one crossmember includes forming a stack comprising at least one layer of resin film applied to a layer of dry fibers, pressing this stack to confer on it a U-section form and such as to compress the layers thereof, and pre-polymerization and/or polymerization of the resin of the stack. The manipulated fiber layers are layers of dry fibers, such that manipulation thereof by an automated machine may be effected for a reasonable cost and at a high throughput. Deposition of resin films carried by removable leaves, i.e., of which one of the faces is not adhesive, likewise facilitates manipulation by an automated installation.

First claim

The invention claimed is:

1. A method for fabricating a central caisson of an aircraft wing, the central caisson comprising a frame formed from U-section crossmembers, wherein formation of at least one of the U-section crossmembers comprises:
providing one or more layers of dry fibers;
providing a layer of a resin, which is in a form of a resin film and comprises a removable leaf that bears the resin film;
applying the layer of the resin to the one or more layers of the dry fibers to form a stack;
removing, when the layer of the resin is in place on the one or more layers of the dry fibers, the removable leaf from the resin film; and
hot-pressing the stack using a press to conjointly confer on the stack a U-section form and to compress the layers of the stack.

2. The method of claim 1 , comprising pre-polymerizing and/or polymerizing the resin present in the stack.

3. The method of claim 2 , wherein the pre-polymerizing of the resin is integrated into using the press.

4. The method of claim 1 , wherein at least one of the one or more layers of the dry fibers is a layer of fabric made of woven fibers.

5. The method of claim 1 , wherein the stack is a planar stack, the method comprising cutting the planar stack into multiple strips, each strip of the multiple strips corresponding to one crossmember.

6. The method of claim 1 , comprising:
installing a plurality of the U-section crossmembers onto a support mandrel;
winding fibers around the plurality of the U-section crossmembers installed on the mandrel;
impregnating the fibers and the plurality of the U-section crossmembers with a resin to form an outer skin of the caisson; and
carrying out conjoined polymerization of the resin in the outer skin and of the resin in the plurality of the U-section crossmembers.

7. The method of claim 6 , wherein the fibers wound around the plurality of the U-section crossmembers are composite fibers and/or carbon fibers.

8. The method of claim 1 , wherein the dry fibers are carbon fibers.

9. The method of claim 4 , wherein the woven fibers of the fabric are carbon fibers.

10. A method for fabricating a central caisson of an aircraft wing, the central caisson comprising a frame formed from U-section crossmembers, wherein formation of at least one of the U-section crossmembers comprises:
providing layers of dry fibers;
providing layers of a resin, each of which are in a form of a resin film;
assembling the layers of the dry fibers with the layers of the resin to form a stack;
arranging the stack on a lower part of a press, the lower part of the press having a first cavity formed therein;
arranging an upper part of the press above the lower part of the press, the upper part of the press having a second cavity formed therein;
actuating the press to sandwich the stack between the upper part of the press and the lower part of the press, such that the stack has a U-section shape.

11. The method of claim 10 , wherein the stack comprises the layers of dry fibers and the layers of the resin that are assembled in an alternating sequence.

12. The method of claim 10 , comprising controlling a pressure exerted on the stack within the press to compress the layers of dry fibers and the layers of the resin within the stack to form a U-section crossmember that is essentially devoid of air bubbles.

13. The method of claim 10 , comprising heating the press to pre-polymerize and/or polymerize the resin within the stack to aid in penetration of the resin within the layers of the dry fabric.

14. The method of claim 10 , wherein each layer of the resin comprises, when being assembled with the layers of the dry fibers, the resin film and a removable leaf, the method comprising removing the removable leaf of each of the layers of the resin before a subsequent one of the layers of the dry fibers is deposited thereon.

15. The method of claim 10 , wherein the stack is a planar structure.

16. The method of claim 10 , wherein the stack comprises one of the layers of the resin between each of the layers of the dry fibers.

17. The method of claim 10 , wherein one or more of the layers of the dry fibers are in a form of a fabric comprising woven carbon fibers.

18. The method of claim 10 , wherein the dry fibers are carbon fibers.

19. The method of claim 10 , comprising:
forming a plurality of the U-section crossmembers;
installing the plurality of the U-section crossmembers onto a support mandrel;
winding fibers around the plurality of the U-section crossmembers installed on the mandrel;
impregnating the fibers and the plurality of the U-section crossmembers with a resin to form an outer skin of the caisson; and
carrying out conjoined polymerization of the resin in the outer skin and of the resin in the plurality of the U-section crossmembers.

20. The method of claim 19 , wherein the fibers wound around the plurality of the U-section crossmembers are composite fibers and/or carbon fibers.

Assignees

• Airbus Operations Sas

Inventors

• Pridie Jago

Classifications

• B64C1/26

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

• B29C70/462 Primary

  Moulding structures having an axis of symmetry or at least one channel, e.g. tubular structures, frames · CPC title

• B29K2105/089

  fabric · CPC title

• B29K2307/04

  Carbon · CPC title

• B29L2031/3085

  Wings · CPC title