Composite structure and method of forming thereof

Patent metadata

Field	Value
Publication number	US-10059068-B2
Application number	US-201414257663-A
Country	US
Kind code	B2
Filing date	Apr 21, 2014
Priority date	Apr 21, 2014
Publication date	Aug 28, 2018
Grant date	Aug 28, 2018

Abstract

A composite structure that includes a plurality of components coupled together forming a joint, wherein the plurality of components are oriented such that a gap is defined at least partially therebetween. The composite structure also includes a filler structure positioned in the gap. The filler structure includes a honeycomb core including side walls that define a plurality of core cells, and an amount of resin within each of the plurality of core cells. The honeycomb core side walls facilitate restricting crack propagation in the resin from spreading between adjacent pairs of the plurality of core cells.

First claim

What is claimed is:

1. A composite structure comprising:
a plurality of components coupled together forming a joint, wherein said plurality of components are oriented such that a gap is defined at least partially therebetween and wherein at least one of said plurality of components comprises a bent portion such that a radius gap is defined between said plurality of components; and
a filler structure positioned in said gap, said filler structure comprising:
a honeycomb core comprising side walls that define a plurality of core cells; and
an amount of resin within each of said plurality of core cells, wherein said side walls facilitate restricting crack propagation in the resin from spreading between adjacent pairs of said plurality of core cells.

2. The composite structure in accordance with claim 1 , wherein said plurality of components are coupled together such that said gap extends along a length of said plurality of components.

3. The composite structure in accordance with claim 1 , wherein said honeycomb core has a cross-sectional shape that substantially matches a cross-sectional shape of said gap.

4. The composite structure in accordance with claim 1 , wherein said honeycomb core side walls are fabricated from at least one ply of composite material.

5. The composite structure in accordance with claim 1 , wherein the resin comprises an epoxy material.

6. The composite structure in accordance with claim 1 , wherein the amount of resin substantially fills each of said plurality of core cells.

7. The composite structure in accordance with claim 1 , wherein the plurality of components comprises a first component having a flat surface that at least partially defines said gap, and wherein said filler structure is oriented such that said side walls of said honeycomb core extend perpendicularly relative to said flat surface.

8. A method of forming a composite structure, said method comprising:
coupling a plurality of components together forming a joint, wherein at least one of the plurality of components comprises a bent portion such that a radius gap is defined between the plurality of components, and wherein the plurality of components are oriented to form the radius gap therebetween;
forming a filler structure that includes a honeycomb core and an amount of resin, the honeycomb core including side walls that define a plurality of core cells and the resin within each of the plurality of core cells, wherein the side walls facilitate restricting crack propagation in the resin from spreading between adjacent pairs of the plurality of core cells;
positioning the filler structure in the radius gap; and
applying at least one of heat or pressure to the plurality of components and the filler structure.

9. The method in accordance with claim 8 , wherein forming a filler structure comprises:
substantially filling the plurality of core cells with the amount of resin;
curing the amount of resin within the plurality of core cells; and
forming the filler structure to have a cross-sectional shape that substantially matches a cross-sectional shape of the radius gap before being positioned in the radius gap.

10. The method in accordance with claim 8 , wherein forming a filler structure comprises:
forming the honeycomb core to have a cross-sectional shape that substantially matches a cross-sectional shape of the radius gap; and
substantially filling the plurality of core cells with the amount of resin after a geometry of the honeycomb core has been modified.

11. The method in accordance with claim 10 , wherein applying at least one of heat or pressure comprises curing the amount of resin within the plurality of core cells.

12. The method in accordance with claim 8 , wherein positioning the filler structure in the radius gap comprises positioning the filler structure in the radius gap such that the honeycomb core side walls are oriented to intersect a crack plane defined in the resin.

13. The method in accordance with claim 12 , wherein positioning the filler structure in the radius gap comprises selecting an orientation of the filler structure in the radius gap based on a predicted direction of crack propagation in the resin.

14. The method in accordance with claim 12 , wherein positioning the filler structure in the radius gap comprises orienting the filler structure within the radius gap such that core cell passages extending through the plurality of core cells extend in a substantially perpendicular direction relative to a predicted direction of crack propagation.

Assignees

• Boeing Co

Inventors

• Christensen Stephen

Classifications

• B29C70/745 Primary

  Filling cavities in the preformed part (for joining B29C70/84) · CPC title

• B29L2031/3076

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

• B32B3/02

  characterised by features of form at particular places, e.g. in edge regions {(non-uniform thickness B32B3/263)} · CPC title

• B29C70/865

  completely encapsulated · CPC title

• B32B3/12

  characterised by a layer of regularly- arranged cells, e.g. a honeycomb structure · CPC title