Structured thermoplastic in composite interleaves

Patent metadata

Field	Value
Publication number	US-9868265-B2
Application number	US-201113166646-A
Country	US
Kind code	B2
Filing date	Jun 22, 2011
Priority date	May 27, 2010
Publication date	Jan 16, 2018
Grant date	Jan 16, 2018

Abstract

One or more layers of structured thermoplastic polymer, such as a light weight veil of thermoplastic polymer fibers, are located within the interleaf zone of laminates that are composed of fibrous layers and thermosetting resin. The thermoplastic veils are used in the interleaf zones as a replacement for thermoplastic toughening particles. The structured thermoplastic polymer may be coated with a conductive material to improve electrical conductivity through the laminate.

First claim

What is claimed is:

1. A method for making a laminate comprising a plurality of electrically conductive fibrous layers and an uncured thermosetting resin wherein said fibrous layers comprise structural conductive fibres and are separated by an interleaf zone located between adjacent fibrous layers, said method providing spacing between said fibrous layers and providing electrical conductance between said fibrous layers across said interleaf zone, said method comprising the steps of:
providing an electrically conductive nonwoven veil comprising polyamide fibers that have been coated with a coating of conductive metal, said nonwoven veil weighing from 5 to 20 grams per square meter;
compressing said electrically conductive nonwoven veil to form an electrically conductive calendared open-structured polymeric sheet which is from 5 microns to 30 microns thick, said calendared open-structured polymeric sheet having a maximum thickness and a minimum thickness, said nonwoven veil being compressed a sufficient amount to form said calendared open-structured polymeric sheet wherein the difference between said maximum thickness and said minimum thickness is less than 1 micron;
providing two fibrous layers comprising electrically conductive structural fibres and an uncured thermosetting resin;
locating the two fibrous layers adjacent to each other to form an interleaf zone between the two fibrous layers; and
forming said laminate by locating said calendared open-structured polymeric sheet within the interleaf zone, said calendared open-structured polymeric sheet acting as a spacer to provide spacing between said fibrous layers and also providing electrical conductance between said fibrous layers across said interleaf zone.

2. A method for making a laminate according to claim 1 wherein said metal is selected from the group consisting of silver, copper, nickel, gold, platinum, aluminum and mixtures thereof.

3. A method for making a cured laminate comprising the method according to claim 1 which comprises the additional step of curing said uncured thermosetting resin.

4. A method for making a cured laminate according to claim 3 wherein a pressure of about 1 atmosphere or less is applied to said laminate during said step of curing said uncured thermosetting resin.

5. A method for making a composite part comprising the method according to claim 3 which includes the additional step of forming said laminate into a composite part prior to curing of said uncured thermosetting resin.

6. A method for making a composite part according to claim 5 wherein said composite part is an aerospace vehicle part.

7. A method for making a laminate according to claim 1 wherein said calendered are open-structured polymeric sheet is from 10 microns to 20 microns thick.

8. A method for making a laminate according to claim 1 wherein said polyamide fibers have a thickness of from 10 microns to 20 microns and wherein said coating of conductive metal is from 0.01 micron to 1.0 micron thick.

9. A method for making a laminate comprising a plurality of electrically conductive fibrous layers and an uncured thermosetting resin wherein said fibrous layers comprise structural conductive fibres and are separated by an interleaf zone located between adjacent fibrous layers, said method providing spacing between said fibrous layers and providing electrical conductance between said fibrous layers across said interleaf zone, said method comprising the steps of:
providing an electrically conductive nonwoven veil comprising polyamide fibers that have been coated with a coating of conductive metal;
compressing said electrically conductive nonwoven veil to form an electrically conductive calendared open-structured polymeric sheet which is from 5 microns to 30 microns thick and weighs from 5 to 20 grams per square meter, said calendared open-structured polymeric sheet having a maximum thickness and a minimum thickness, said nonwoven veil being compressed a sufficient amount to form said calendared open-structured polymeric sheet wherein the difference between said maximum thickness and said minimum thickness is less than 1 micron;
providing a first fibrous layer comprising electrically conductive structural fibres and an uncured thermosetting resin;
locating said calendared open-structured polymeric sheet on said fibrous layer to form a prepreg;
providing a second fibrous layer comprising electrically conductive structural fibres and an uncured thermosetting resin; and
locating said prepreg and second fibrous layers adjacent to each other to form a laminate having an interleaf zone located between said first and second fibrous layers wherein said calendared open-structured polymeric, sheet is located within the interleaf zone, said calendared open-structured polymeric sheet acting as a spacer to provide spacing between said first and second fibrous layers and also providing electrical conductance between said first and second fibrous layers across said interleaf zone.

10. A method for making a laminate according to claim 9 wherein said metal is selected from the group consisting of silver, copper, nickel, gold, platinum, aluminum and mixtures thereof.

11. A method for making a composite part comprising the method according to claim 9 which comprises the additional step of curing said uncured thermosetting resin located in said first and second fibrous layers.

12. A method for making a composite part according to claim 11 wherein a pressure of about 1 atmosphere or less is applied to said prepreg during said curing step of curing said uncured thermosetting resin.

13. A method for making a composite part comprising the method according to claim 11 which includes the additional step of forming said laminate into a portion of said composite part prior to curing of said uncured thermosetting resin.

14. A method far making a composite part according to claim 13 wherein said composite part is an aerospace vehicle part.

15. A method for making a laminate according to claim 9 wherein said calendared open-structured polymeric sheet is from 10 microns to 20 microns thick.

16. A method for making a laminate according to claim 9 wherein said polyamide fibers have a thickness of from 10 microns to 20 microns and wherein said coating of conductive metal is from 0.01 micron to 1.0 micron thick.

Assignees

• Simmons Martin
• Blair Dana
• Mortimer Steve
• Hexcel Composites Ltd

Inventors

• Simmons Martin
• Blair Dana
• Mortimer Steve

Classifications

• Y10T428/269

  including synthetic resin or polymer layer or component · CPC title

• B32B2262/0261

  Polyamide fibres · CPC title

• Y10T442/654

  Including a free metal or alloy constituent · CPC title

• B32B5/26

  another layer {next to it} also being fibrous or filamentary {(relative arrangement of fibres or filaments of different layers B32B5/12)} · CPC title

• B32B2605/18

  Aircraft · CPC title