System and method for securely connecting portions of a composite structure together

Patent metadata

Field	Value
Publication number	US-2016293153-A1
Application number	US-201514940397-A
Country	US
Kind code	A1
Filing date	Nov 13, 2015
Priority date	Apr 3, 2015
Publication date	Oct 6, 2016
Grant date	—

Abstract

A composite component assembly may include a composite core including a plurality of core cells between first and second ends. A connection joint is formed between the first and second ends. An adhesive layer is disposed within the connection joint between the first and second ends. The adhesive layer is configured to bond the first and second ends through a curing process. A peg splice securing joint securely connects the first and second ends together before and during the curing process.

First claim

What is claimed is:

1 . A composite component assembly, comprising:
a composite core including a plurality of core cells between first and second ends, wherein a connection joint is formed between the first and second ends; an adhesive layer disposed within the connection joint between the first and second ends, wherein the adhesive layer is configured to bond the first and second ends through a curing process; and a peg splice securing joint that securely connects the first and second ends together before and during the curing process.

2 . The composite component assembly of claim 1 , wherein the composite core has a first height, and wherein the peg splice securing joint has a second height that is less than the first height.

3 . The composite component assembly of claim 1 , wherein the second height is less than 50% of the first height.

4 . The composite component assembly of claim 1 , wherein the peg splice securing joint is urged into outer surfaces of the first and second ends, and wherein an outer surface of the peg splice securing joint is flush with the outer surfaces of the first and second ends.

5 . The composite component assembly of claim 1 , wherein the adhesive layer is spaced apart from the peg splice securing joint.

6 . The composite component assembly of claim 1 , wherein the adhesive layer comprises a foaming adhesive layer that is configured to react at and above a particular temperature.

7 . The composite component assembly of claim 1 , wherein each of the plurality of core cells comprises a septum having acoustic properties.

8 . The composite component assembly of claim 7 , wherein the peg splice securing joint is spaced apart from the septum of each of the plurality of core cells.

9 . The composite component assembly of claim 1 , wherein the composite core and the peg splice securing joint are formed of the same material, wherein the peg splice securing assembly includes a plurality of peg splice cells.

10 . A method of forming a composite component assembly, comprising:
laying-up a composite core having a plurality of core cells in relation to a mandrel; disposing an adhesive layer within a connection joint between first and second ends of the composite core; securely connecting the first and second ends together with a peg splice securing joint; and curing the composite component assembly, wherein the securely connecting operation securely fastens and stabilizes the first and second ends together before and during the curing process, and wherein the curing operation causes the adhesive layer to securely bond the first and second ends together.

11 . The method of claim 10 , wherein the composite core has a first height, wherein the peg splice securing joint has a second height that is less than the first height.

12 . The method of claim 10 , wherein the second height is less than 50% of the first height.

13 . The method of claim 10 , wherein the securely connecting operation comprises urging the peg splice securing joint into outer surfaces of the first and second ends until an outer surface of the peg splice securing joint is flush with the outer surfaces of the first and second ends.

14 . The method of claim 13 , wherein the securely connecting operation comprises spacing the adhesive layer apart from the peg splice securing joint.

15 . The method of claim 10 , wherein the curing operation comprises causing the adhesive layer to adhere to portions of the first and second ends.

16 . The method of claim 10 , wherein each of the plurality of core cells comprises a septum having acoustic properties.

17 . The method of claim 16 , wherein the securely connecting operation comprises spacing the peg splice securing joint apart from the septum of each of the plurality of core cells.

18 . The method of claim 10 , further comprising forming the composite core and the peg splice securing joint of the same material.

19 . A composite component assembly, comprising:
a composite core including a plurality of honeycomb core cells between first and second ends, wherein a connection joint is formed between the first and second ends, wherein the composite core has a first height, wherein each of the plurality of honeycomb core cells comprises a septum having acoustic properties; a foaming adhesive layer disposed within the connection joint between the first and second ends, wherein the foaming adhesive layer is configured to bond the first and second ends through a curing process; and a peg splice securing joint that securely connects the first and second ends together before and during the curing process, wherein the peg splice securing joint has a second height that is less than 50% of the first height, wherein the peg splice securing joint is urged into outer surfaces of the first and second ends, and wherein an outer surface of the peg splice securing joint is flush with the outer surfaces of the first and second ends.

20 . The composite component assembly of claim 1 , wherein the adhesive layer is spaced apart from the peg splice securing joint, and wherein the peg splice securing joint is spaced apart from the septum of each of the plurality of core cells.

Assignees

• Boeing Co

Inventors

• Taylor Jr Bruce
• Gibbings Geoffrey
• Braun Rudy
• Advent Kyle Christopher

Classifications

• G10K11/168 Primary

  Plural layers of different materials, e.g. sandwiches · CPC title

• B32B2605/18

  Aircraft · CPC title

• B32B7/08

  by mechanical means · CPC title

• B32B2307/102

  Insulating · CPC title

• B32B7/12 Primary

  using interposed adhesives or interposed materials with bonding properties · CPC title