Method of forming a layered composite assembly

Patent metadata

Field	Value
Publication number	US-10457017-B2
Application number	US-201414563435-A
Country	US
Kind code	B2
Filing date	Dec 8, 2014
Priority date	Dec 8, 2014
Publication date	Oct 29, 2019
Grant date	Oct 29, 2019

Abstract

A layered composite assembly may include a plurality of composite fiber layers stacked onto one another. Each of the plurality of composite fiber layers may include a main body including a plurality of composite fibers. The main body may be pre-impregnated with at least one resin. Each composite fiber layer also includes a plurality of layer-securing pins secured to the main body. The layer-securing pins are configured to mechanically connect the main body to an adjacent composite fiber layer.

First claim

What is claimed is:

1. A composite fiber layer that couples to another composite fiber layer, the composite fiber layer comprising:
a main body including a plurality of composite fibers; and
a plurality of layer-securing pins secured to the main body, wherein the plurality of layer-securing pins are separate and distinct from one another, wherein the plurality of layer-securing pins are configured to mechanically connect the main body to the other composite fiber layer, wherein each of the plurality of layer-securing pins comprises:
an annular ring; and
a plurality of legs extending from the annular ring, wherein the annular ring is exposed through an outer surface of the main body, and wherein the plurality of legs extend into the main body, wherein the annular ring adhesively bonds via curing to another annular ring of the other composite fiber layer.

2. The composite fiber layer of claim 1 , wherein the main body is pre-impregnated with at least one resin.

3. The composite fiber layer of claim 1 , wherein the main body includes first and second opposed surfaces separated by a thickness, wherein each of the plurality of layer-securing pins extends through only one of the first or second opposed surfaces.

4. The composite fiber layer of claim 1 , wherein each of the plurality of layer-securing pins comprises a linear structure.

5. The composite fiber layer of claim 1 , wherein each of the plurality of layer-securing pins further comprises a linear exposed end extending outwardly from the main body.

6. The composite fiber layer of claim 1 , wherein each of the plurality of layer-securing pins includes first and second portions that exhibit different coefficients of thermal expansion.

7. The composite fiber layer of claim 1 , wherein each of the plurality of layer-securing pins is formed of a shape memory alloy.

8. The composite fiber layer of claim 7 , wherein each of the plurality of layer-securing pins is curled at a first temperature, and wherein each of the plurality of layer-securing pins is configured to be straightened at a second temperature that differs from the first temperature.

9. The composite fiber layer of claim 1 , wherein each of the plurality of legs is formed of a bimetallic material.

10. A layered composite assembly that couples to an adjacent composite layer, the layered composite assembly comprising:
a plurality of composite fiber layers stacked onto one another, each of the plurality of composite fiber layers comprising:
a main body including a plurality of composite fibers, wherein the main body is pre-impregnated with at least one resin; and
a plurality of layer-securing pins secured to the main body, wherein the plurality of layer-securing pins are separate and distinct from one another, wherein the plurality of layer-securing pins are configured to mechanically connect the main body to the adjacent composite fiber layer, wherein each of the plurality of layer-securing pins comprises: (a) an annular ring; and (b) a plurality of legs extending from the annular ring, wherein the annular ring is exposed through an outer surface of the main body, and wherein the plurality of legs extend into the main body, and wherein the annular ring is adhesively bonded via curing to another annular ring of the adjacent composite fiber layer.

11. The layered composite assembly of claim 10 , further comprising at least one laminate layer secured around an outer one of the plurality of composite fiber layers.

12. The layered composite assembly of claim 10 , wherein each of the plurality of layer-securing pins is formed of a shape memory alloy, wherein each of the plurality of layer-securing pins is formed in a curled shaped at a first temperature, wherein each of the plurality of layer-securing pins is cooled to a second temperature that differs from the first temperature, wherein each of the plurality of layer-securing pins is mechanically straightened at a second temperature, wherein each of the plurality of layer-securing pins is secured to the main body in a straightened orientation, and wherein each of the plurality of layer-securing pins transitions to a curled orientation to hook onto one or more of the plurality of composite fibers.

13. The layered composite assembly of claim 10 , wherein each of the plurality of layer-securing pins includes an inner portion formed of a first metal and an outer portion formed of a second metal that is different than the first metal, wherein the first and second metals exhibit different coefficients of thermal expansion, wherein each of the plurality of layer-securing pins is curled at a first temperature, wherein each of the plurality of layer-securing pins is configured to be straightened at a second temperature that differs from the first temperature, wherein each of the plurality of layer-securing pins is secured to the main body in a straightened orientation, and wherein each of the plurality of layer-securing pins transitions to a curled orientation to hook onto one or more of the plurality of composite fibers.

14. A method of forming a layered composite assembly, the method comprising:
stacking a plurality of composite fiber layers, wherein each of the composite fiber layers includes a main body including a plurality of composite fibers that are pre-impregnated with at least one resin, and a plurality of layer-securing pins; and
mechanically connecting the plurality of layer-securing pins of each of the plurality of composite fiber layers with another of the plurality of composite fiber layers wherein the plurality of layer-securing pins are separate and distinct from one another, wherein the mechanically connecting operation comprises:
abutting exposed portions of rings of the plurality of layer-securing pins of the plurality of composite fiber layers together; and
adhesively bonding, via curing, the abutting exposed portions of the rings of the plurality of layer-securing pins of the plurality of composite fiber layers together.

15. The method of claim 14 , wherein the mechanically connecting operation comprises:
exposing the plurality of composite fibers layers to a change in one or both of temperature or pressure; and
transitioning the plurality of layer-securing pins between straightened and curled orientations through the exposing operation.

Assignees

• Boeing Co

Inventors

• Humfeld Keith Daniel
• Hurley Kelsi Marie

Classifications

• B29C70/543

  Fixing the position or configuration of fibrous reinforcements before or during moulding (for non-woven fabrics D04H3/08) · CPC title

• B29C66/83431

  rollers, cylinders or drums cooperating with bands or belts · CPC title

• B32B2605/18

  Aircraft · CPC title

• B32B2250/20

  All layers being fibrous or filamentary · CPC title

• B29C65/18

  using heated tools · CPC title