Method for repairing a composite part

Patent metadata

Field	Value
Publication number	US-10406764-B2
Application number	US-201715691278-A
Country	US
Kind code	B2
Filing date	Aug 30, 2017
Priority date	Aug 30, 2017
Publication date	Sep 10, 2019
Grant date	Sep 10, 2019

Abstract

A method for repairing damage to a composite part includes creating an aperture through the composite part and preparing the surfaces surrounding the aperture on both sides of the part; inserting a plurality of resin impregnated fibers through the aperture and spreading the end portions of the plurality of fibers radially against the prepared surfaces on both sides of the part; and maintaining contact of the plurality of fibers with the prepared surfaces while the resin cures.

First claim

What is claimed is:

1. A method for repair of a composite part, comprising:
creating an aperture through the composite part;
preparing a first surface of the composite part adjacent the aperture on a first side of the composite part;
rounding or chamfering an edge between the first surface and the aperture;
preparing a second surface of the composite part adjacent the aperture on a second side of the composite part;
impregnating a plurality of fibers with a resin;
inserting the plurality of fibers through the aperture;
contacting first end portions of the plurality of fibers with the first prepared surface;
contacting second end portions of the plurality of fibers with the second prepared surface; and
maintaining the contact between the first end portions of the plurality of fibers with the first prepared surface and the contact between the second end portions of the plurality of fibers with the second prepared surface while the resin cures.

2. The method of claim 1 , wherein the preparing the first surface comprises sanding and/or spotfacing the first surface.

3. The method of claim 2 , wherein the preparing the second surface comprises sanding and/or spotfacing the second surface.

4. The method of claim 3 , wherein the plurality of fibers comprise carbon, glass, aramid, polyethylene, quartz, ceramic, or boron fibers.

5. The method of claim 4 , wherein the plurality of fibers comprises a tow, a braided tube, and/or a woven strip.

6. The method of claim 5 , wherein a ratio of fiber to resin within the aperture is between 30% fiber to 70% resin and 45% fiber to 55% resin.

7. The method of claim 6 , wherein the creating the aperture comprises drilling the aperture such that the aperture completely removes a defect.

8. The method of claim 7 , wherein the contacting the first end portions of the plurality of fibers with the first prepared surface includes spreading the first end portions radially from the aperture.

9. The method of claim 8 , wherein the contacting the second end portions of the plurality of fibers with the second prepared surface includes spreading the second end portions radially from the aperture.

10. The method of claim 9 , wherein the inserting includes inserting the plurality of fibers through a funnel, inserting the funnel into the aperture, and then removing the funnel.

11. The method of claim 9 , wherein the inserting includes using a tool to push and or pull the plurality of fibers through the aperture.

12. A method for repair of a composite part, comprising:
creating an aperture through the composite part;
preparing a first surface of the composite part adjacent the aperture on a first side of the composite part, wherein the first surface lies in a plane that is generally perpendicular to a longitudinal axis of the aperture and is recessed from an outer surface of a first side of the composite part;
preparing a second surface of the composite part adjacent the aperture on a second side of the composite part;
impregnating a plurality of fibers with a resin;
inserting the plurality of fibers through the aperture;
contacting first end portions of the plurality of fibers with the first prepared surface;
contacting second end portions of the plurality of fibers with the second prepared surface; and
maintaining the contact between the first end portions of the plurality of fibers with the first prepared surface and the contact between the second end portions of the plurality of fibers with the second prepared surface while the resin cures.

13. The method of claim 12 , further comprising:
inserting a mandrel through the aperture.

14. The method of claim 13 , further comprising:
removing the mandrel after the resin cures.

15. The method of claim 12 , wherein each of the first end portions and the second end portions of the plurality of fibers are longer than a portion of the plurality of fibers between the first end portions and the second end portions.

16. A method for repair of a composite part, comprising:
creating an aperture through the composite part;
preparing a first surface of the composite part adjacent the aperture on a first side of the composite part;
preparing a second surface of the composite part adjacent the aperture on a second side of the composite part;
impregnating a plurality of fibers with a resin;
inserting the plurality of fibers through the aperture;
contacting first end portions of the plurality of fibers with the first prepared surface;
contacting second end portions of the plurality of fibers with the second prepared surface;
maintaining the contact between the first end portions of the plurality of fibers with the first prepared surface and the contact between the second end portions of the plurality of fibers with the second prepared surface while the resin cures; and
creating a hole through at least a portion of the plurality of fibers.

17. The method of claim 16 , further comprising:
inserting a fastener through the hole.

18. The method of claim 16 , further comprising:
rounding or chamfering an edge between the first surface and the aperture.

19. The method of claim 16 , wherein each of the first end portions and the second end portions of the plurality of fibers are longer than a portion of the plurality of fibers between the first end portions and the second end portions.

Assignees

• Bell Helicopter Textron Inc

Inventors

• Whitworth Denver Ray
• Cribb Vance Newton

Classifications

• B29C70/085

  the structure being deformed in a three dimensional configuration (B29C53/805 takes precedence) · CPC title

• B29L2031/3076

  Aircrafts (blades, propellers B29L2031/08) · CPC title

• B32B17/10963

  specially adapted for repairing the layered products · CPC title

• Y10T428/20

  Patched hole or depression · CPC title

• B64F5/40

  Maintaining or repairing aircraft · CPC title