Methods, systems and apparatuses for curing epoxy-containing prepreg composite assembly

Patent metadata

Field	Value
Publication number	US-9738764-B2
Application number	US-201614987988-A
Country	US
Kind code	B2
Filing date	Jan 5, 2016
Priority date	Jan 5, 2016
Publication date	Aug 22, 2017
Grant date	Aug 22, 2017

Abstract

Methods and systems and components made according to the methods and systems, are disclosed relating to improved curing methods for epoxy resin-containing composite prepreg materials, wherein the composite prepreg materials are exposed to a flow of ammonia-containing compounds to fully cure the composite prepreg materials at substantially ambient temperatures and pressures.

First claim

We claim:

1. A method for curing an epoxy-containing prepreg assembly for a composite material comprising:
positioning the epoxy-containing prepreg assembly for a composite material, in an enclosed environment, said enclosed environment comprising an inlet, said prepreg assembly comprising layers of prepregs, said layers of prepregs comprising fibers, said fibers selected from the group consisting of: carbon fibers, glass fibers, aramid fibers, boron fibers and combinations thereof;
delivering a flow of an ammonia-containing compound to the enclosed environment via the inlet, said flow delivered to the enclosed environment to a predetermined concentration;
maintaining the flow of the ammonia-containing compound to the enclosed environment at the predetermined concentration for a predetermined duration; and
curing the epoxy-containing prepreg assembly to produce the composite material;
wherein the prepreg assembly in the enclosed environment is maintained at a temperature ranging from about 60° F. to about 100° F. and at a pressure ranging from about 14 psi to about 16 psi.

2. The method of claim 1 , wherein the ammonia-containing compound is delivered to the enclosed environment in a gaseous state.

3. The method of claim 1 , wherein the ammonia-containing compound is delivered to the enclosed environment as a vapor.

4. The method of claim 1 , wherein the epoxy-containing prepreg assembly comprises an epoxy-containing compound selected from the group consisting of: digylcidyl ethers of bisphenol A; dicgycidyl ethers of bisphenol F; N,N,N′,N′-tetragylcidyl-4,4′-diaminophenylmethane; p-amino phenol triglycidyl ether; epoxy phenol novolac resins; epoxy cresol novolac resins; 1,3,5-triglycidyl isocyanurate; tris(2,3-epoxypropyl)isocyanurate; glycerol diglycidyl ether; trimethylolpropane triglycidyl ether, and combinations thereof.

5. The method of claim 1 , wherein the enclosed environment further comprises an outlet.

6. The method of claim 5 , wherein the outlet is in communication with a vacuum.

7. The method of claim 1 , wherein the epoxy-containing prepreg assembly has a viscosity ranging from about 60,000 poise to about 1000 poise.

8. The method of claim 1 , wherein the ammonia-containing compound is substantially pure ammonia.

9. A cured epoxy-containing prepreg assembly made according to the method of claim 1 .

10. A structure comprising the epoxy-containing prepreg assembly of claim 9 .

11. A vehicle comprising the epoxy-containing prepreg assembly of claim 9 .

12. The vehicle of claim 11 , wherein the vehicle is selected from the group consisting of: a manned, and unmanned aircraft, a manned spacecraft, an unmanned spacecraft, a manned rotorcraft, an unmanned rotorcraft, a rocket, a manned satellite, an unmanned satellite, a manned terrestrial vehicle, an unmanned terrestrial vehicle, a manned surface and/or sub-surface water borne vehicle, an unmanned surface and/or sub-surface waterborne vehicle, and combinations thereof.

13. A system for curing an epoxy-containing prepreg assembly for a composite material, said system comprising:
an epoxy-containing prepreg assembly for a composite material, said prepreg assembly comprising layers of prepregs, said layers of prepregs comprising fibers, said fibers selected from the group consisting of: carbon fibers, glass fibers, aramid fibers, boron fibers and combinations thereof;
an enclosed environment dimensioned to house the epoxy-containing prepreg assembly, said enclosed environment comprising an inlet; and
an amount of an ammonia-containing compound delivered to the enclosed environment to a predetermined concentration via the inlet;
wherein the ammonia-containing compound cures the epoxy-containing prepreg assembly to produce the composite material at a temperature ranging from about 60° F. to about 100° F. and at a pressure ranging from about 14 psi to about 16 psi.

14. The system of claim 13 , wherein the ammonia-containing compound is delivered to the enclosed environment in a gaseous state.

15. The system of claim 13 , wherein the epoxy-containing prepreg assembly comprises an epoxy-containing compound selected from the group consisting of: digylcidyl ethers of bisphenol A; dicgycidyl ethers of bisphenol F; N,N,N′,N′-tetragylcidyl-4,4′-diaminophenylmethane; p-amino phenol triglycidyl ether; epoxy phenol novolac resins; epoxy cresol novolac resins; 1,3,5-triglycidyl isocyanurate; tris(2,3-epoxypropyl)isocyanurate; glycerol diglycidyl ether; trimethylolpropane triglycidyl ether, and combinations thereof.

16. The system of claim 13 , wherein the enclosed environment further comprises an outlet.

17. The system of claim 16 , wherein the outlet is in communication with a vacuum.

18. The system of claim 13 , wherein the ammonia-containing compound is substantially pure ammonia.

Assignees

• Boeing Co

Inventors

• Gross Gwen M
• Thompson Michael P

Classifications

• C08J2363/00

  Characterised by the use of epoxy resins; Derivatives of epoxy resins · CPC title

• C08J2363/04

  Epoxynovolacs · CPC title

• C08J2363/06

  Triglycidylisocyanurates · CPC title

• C08J2363/02

  Polyglycidyl ethers of bis-phenols · CPC title

• C08J5/24 Primary

  Impregnating materials with prepolymers which can be polymerised in situ, e.g. manufacture of prepregs · CPC title