Composite textiles including spread filaments

Patent metadata

Field	Value
Publication number	US-10035323-B2
Application number	US-201314034456-A
Country	US
Kind code	B2
Filing date	Sep 23, 2013
Priority date	Sep 23, 2013
Publication date	Jul 31, 2018
Grant date	Jul 31, 2018

Abstract

An article comprises a multi-directional textile of first reinforcing fiber tows extending in a first direction and second reinforcing fiber tows extending in a second direction. Filaments in the first fiber tows extend past a boundary of the textile and are spread. The tows are embedded in resin.

First claim

The invention claimed is:

1. An aircraft structural element comprising a multi-directional textile including first reinforcing fiber tows extending in a first direction and second reinforcing fiber tows extending in a second direction within a boundary of the multi-directional textile, each tow of the first and second reinforcing fiber tows in the textile including an untwisted bundle of filaments arranged in a number of rows, the filaments of the first reinforcing fiber tows extending past the boundary of the multi-directional textile and being spread so that the number of rows of filaments is reduced past the boundary, the first and second reinforcing fiber tows being embedded in resin, at least some of the spread filaments extending past the boundary being straight and terminating at nonwoven sinuous wavy ends, the nonwoven sinuous wavy ends exhibiting waviness in an x-y plane and having no variation in a z-plane.

2. The aircraft structural element of claim 1 , wherein filaments in the second tows also extend past the boundary of the textile and are spread.

3. The aircraft structural element of claim 1 , wherein the filaments within the boundary of the textile provide structural strength along the first and second directions, and wherein those filaments extending past the boundary provide structural strength in only the first direction.

4. The aircraft structural element of claim 1 , wherein the spread filaments extending past the boundary are individually joined to a surface of a second part.

5. The aircraft structural element of claim 1 , wherein the textile includes a weave of the tows.

6. The aircraft structural element of claim 5 , wherein the filaments extending past the boundary have sparse to no support by cross-fibers.

7. The aircraft structural element of claim 1 , wherein the textile includes a braid of tows extending in first, second and third directions.

8. The aircraft structural element of claim 1 , wherein the textile has a circular boundary and wherein the filaments extending past the boundary are normal to the boundary.

9. The aircraft structural element of claim 1 , wherein the first and second reinforcing fiber tows of the multi-directional textile extend in the x-y plane, and wherein the sinuous wavy ends of the spread filaments exhibit waviness in the same x-y plane as the multi-directional textile.

10. The aircraft structural element of claim 1 , wherein the filaments extending past the boundary are terminated at different lengths.

11. A layup comprising a plurality of layers of reinforcing fibers and an outer layer including the multi-directional textile of claim 1 , only the outer layer of the layup including the spread filaments.

12. An aircraft structural element comprising first and second parts joined together, the first part including multiple layers of reinforcing fibers, an outer one of the layers including a multi-dimensional textile of first reinforcing fiber tows extending in a first direction and second reinforcing fiber tows extending in a second direction, the first reinforcing fiber tows and the second reinforcing fiber tows being located within a boundary of the multi-directional textile, each tow of the first and second reinforcing fiber tows in the textile including an untwisted bundle of filaments arranged in a number of rows, the filaments of the first reinforcing fiber tows extending past the boundary of the multi-directional textile and being spread so that the number of rows of filaments is reduced past the boundary, the first and second reinforcing fiber tows being embedded in a resin, the spread filaments of the first reinforcing fiber tows being joined to a surface of the second part, at least some of the spread filaments extending past the boundary being straight and terminating at nonwoven sinuous wavy ends, the nonwoven sinuous wavy ends exhibiting waviness in an x-y plane and having no variation in a z-plane.

13. The aircraft structural element of claim 12 , wherein the first and second parts are discrete parts.

14. The aircraft structural element of claim 13 , wherein the discrete parts are aircraft structural elements.

15. The aircraft structural element of claim 12 , wherein the first part is a patch for the second part.

16. The aircraft structural element of claim 15 , wherein the second part is located at an area of an aircraft that is susceptible to impact damage.

17. A method of fabricating a composite structure for an aircraft, comprising:
mating first and second parts, wherein the first part includes an outer layer having a multi-directional textile of first tows extending in a first direction and second tows extending in a second direction, the first reinforcing fiber tows and the second reinforcing fiber tows being located within a boundary of the multi-directional textile, each of the first and second tows including an untwisted bundle of filaments arranged in a number of rows, the first and second tows being embedded in a resin;
spreading filaments past a boundary of the textile by compression of the untwisted bundle of filaments so that the number of rows of filaments in each tow is reduced past the boundary, at least some of the spread filaments extending past the boundary being straight and terminating at nonwoven sinuous wavy ends, the nonwoven sinuous wavy ends exhibiting waviness in an x-y plane and having no variation in a z-plane; and
joining the spread filaments to a surface of the second part.

18. The method of claim 17 , wherein the first and second parts are aircraft structural elements.

19. The method of claim 17 , wherein the first part is a patch for the second part, which is an aircraft structural element.

Assignees

• Boeing Co

Inventors

• Griess Kenneth H
• Esposito Jack J
• Georgeson Gary E

Classifications

• Y10T428/2476

  Fabric, cloth or textile component · CPC title

• Y10T428/219

  Edge structure · CPC title

• Y10T428/20

  Patched hole or depression · CPC title

• D01D5/00 Primary

  Formation of filaments, threads, or the like · CPC title

• B64C2001/0072

  from composite materials · CPC title