Cutting wire for removal of expanded material after curing of a composite part

Patent metadata

Field	Value
Publication number	US-11292208-B2
Application number	US-201916448576-A
Country	US
Kind code	B2
Filing date	Jun 21, 2019
Priority date	Jun 21, 2019
Publication date	Apr 5, 2022
Grant date	Apr 5, 2022

Abstract

Composite fabrication system and associated methods. In one embodiment, a composite fabrication system comprises a molding tool that includes a forming surface at least partially disposed within a constrained space, and a foamable material that expands inside of the constrained space to form an expanded material that presses a layup of one or more composite layers against the molding tool. The composite fabrication system further comprises a curing device configured to cure the layup to form a composite part, and a cutting wire embedded in the constrained space that is heated and configured to cut the expanded material into pieces that are removable from the constrained space.

First claim

The invention claimed is:

1. A method of fabricating a composite part, the method comprising:
placing one or more composite layers on a molding tool to form a layup, wherein at least a portion of the layup is within a constrained space;
inserting a foamable material in the constrained space;
embedding a cutting wire in the constrained space before curing;
activating the foamable material to expand into an expanded material within the constrained space;
curing the layup while the expanded material presses the layup against the molding tool to form the composite part;
heating the cutting wire after curing;
moving the cutting wire to cut the expanded material into pieces; and
removing the pieces from the constrained space.

2. The method of claim 1 wherein activating the foamable material comprises:
heating the foamable material.

3. The method of claim 1 wherein heating the cutting wire comprises:
applying a current through the cutting wire.

4. The method of claim 1 wherein moving the cutting wire comprises:
moving the cutting wire within the constrained space with a manipulator.

5. The method of claim 4 wherein heating the cutting wire comprises:
applying a current through the cutting wire with end effectors of the manipulator.

6. The method of claim 4 wherein removing the pieces from the constrained space comprises:
grasping the pieces with the manipulator; and
pulling the pieces from the constrained space with the manipulator.

7. The method of claim 1 wherein:
the foamable material comprises foamable pellets.

8. The method of claim 1 wherein removing the pieces from the constrained space comprises:
applying suction with a vacuum device to remove the pieces.

9. The method of claim 1 wherein:
the composite part is manufactured for an aircraft.

10. A method of fabricating a composite part, the method comprising:
placing composite layers on a molding tool to form a layup, wherein at least a portion of the layup is within a constrained space created by a shape of the molding tool;
inserting a foamable material in the constrained space with the layup disposed between the foamable material and forming surfaces of the molding tool;
embedding, before curing the layup, a cutting wire along with the foamable material within the constrained space;
heating the molding tool and the layup in a curing device, wherein the heating activates the foamable material to expand within the constrained space into an expanded material that presses the layup against the forming surfaces of the molding tool, and cures the layup to form the composite part;
heating the cutting wire after curing;
moving the cutting wire while heated within the constrained space to cut the expanded material into pieces; and
removing the pieces from the constrained space.

11. The method of claim 10 wherein heating the molding tool and the layup comprises:
heating the molding tool and the layup in an oven.

12. The method of claim 10 wherein heating the molding tool and the layup comprises:
heating the molding tool and the layup in an autoclave.

13. The method of claim 10 wherein moving the cutting wire comprises:
moving the cutting wire within the constrained space with a manipulator.

14. The method of claim 13 wherein heating the cutting wire comprises:
applying a current through the cutting wire with end effectors of the manipulator.

15. The method of claim 13 wherein removing the pieces from the constrained space comprises:
grasping the pieces with the manipulator; and
pulling the pieces from the constrained space with the manipulator.

16. A method of fabricating a composite part, the method comprising:
placing composite layers on a molding tool to form a layup, wherein at least a portion of the layup is within a constrained space created by a shape of the molding tool;
inserting a foamable material in the constrained space with the layup disposed between the foamable material and forming surfaces of the molding tool;
embedding, before curing the layup, a cutting wire along with the foamable material within the constrained space;
activating, before curing the layup, the foamable material to expand within the constrained space into an expanded material that presses the layup against the forming surfaces of the molding tool;
curing the layup to form the composite part;
heating the cutting wire after curing;
moving the cutting wire while heated within the constrained space to cut the expanded material into pieces; and
removing the pieces from the constrained space.

17. The method of claim 16 wherein activating the foamable material comprises:
activating the foamable material by a chemical reaction.

18. The method of claim 16 wherein moving the cutting wire comprises:
moving the cutting wire within the constrained space with a manipulator.

19. The method of claim 18 wherein heating the cutting wire comprises:
applying a current through the cutting wire with end effectors of the manipulator.

20. The method of claim 18 wherein removing the pieces from the constrained space comprises:
grasping the pieces with the manipulator; and
pulling the pieces from the constrained space with the manipulator.

Assignees

• Boeing Co

Inventors

• Georgeson Gary E
• Wang Xiaoxi
• Santiago Jonathan

Classifications

• B29C70/446 Primary

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

• B29C70/54

  Component parts, details or accessories; Auxiliary operations {, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing} · CPC title

• B29C66/0326 Primary

  Cutting, e.g. by using waterjets, or perforating (using heat B29C66/0346) · CPC title

• B29C65/02

  by heating, with or without pressure · CPC title

• B29C66/112

  Single lapped joints · CPC title