Thermoplastic composition and prepreg, composite material made of said prepreg, and uses of said composite material
View Patent ↗The present invention relates to the field of thermoplastic composite materials. Specifically, the invention relates to a fluorinated, flame-retardant thermoplastic composition, to the prepreg prepared from said composition, to the composite material containing said prepreg, to the methods enabling manufacture, and to the uses of said material. The invention also relates to the use of a thermoplastic prepreg for manufacturing fire-resistant composite materials.
1. A thermoplastic prepreg consisting of a flame retardant composite composition comprising a fluorinated thermoplastic polymer grafted with a polar carboxylic function and a fibrous reinforcer consisting of at least one continuous inorganic or organic fiber, wherein the content by weight of said inorganic or organic fibers is between 40 and 80 wt %, and wherein said thermoplastic prepreg consists of one or more thermoplastic plies, each thermoplastic ply comprising a unidirectional strip of continuous fibers without any overlap between the fibers and a thermoplastic polymer as matrix impregnating the mass of said fibrous reinforcer.
2. The as claimed in claim 1 , wherein said fluorinated polymer is a poly(vinylidene fluoride) (PVDF) or a copolymer of vinylidene fluoride and of at least one other comonomer chosen from vinyl fluoride, trifluoroethylene, chlorotrifluoroethylene, 1,2-difluoroethylene, tetrafluoroethylene, hexafluoropropylene, perfluoro(methylvinyl)ether, perfluoro(ethylvinyl)ether and perfluoro(propylvinyl)ether, wherein the vinylidene fluoride represents at least 50% by weight.
3. The prepreg as claimed claim 1 wherein said inorganic or organic fiber is selected from the group consisting of: carbon fibers; silica fibers, glass fibers, E type glass, R type glass, S2 type glass; boron fibers; ceramic fibers, silicon carbide, boron carbide, boron carbonitride, silicon nitride, boron nitride; basalt fibers; fibers or filaments based on metals and alloys thereof; fibers based on metal oxides; natural fibers, flax, hemp and sisal fibers; metallized carbon fibers and metallized glass fibers, and mixtures thereof.
4. The prepreg as claimed in claim 1 , wherein said continuous inorganic or organic fiber is unidirectional and has an aspect ratio of greater than 1000.
5. The prepreg as claimed in claim 1 , wherein the flame retardant composite composition comprises one or more additives selected from the group consisting of plasticizers, dyes, antistatic agents, flame retardants and lubricants.
6. The prepreg as claimed in claim 1 , wherein said polar carboxylic function is borne by at least one polar monomer selected from the group consisting of unsaturated monocarboxylic and dicarboxylic acids having from 2 to 20 carbon atoms, acrylic acid, methacrylic acid, maleic acid, fumaric acid, itaconic acid, citraconic acid, allylsuccinic acid, cyclohex-4-ene-1,2-dicarboxylic acid, 4-methylcyclohex-4-ene-1,2-dicarboxylic acid, bicyclo(2,2,1)hept-5-ene-2,3-dicarboxylic acid and undecylenic acid and the anhydrides thereof.
7. The prepreg as claimed in any of claims 1 to 6 , wherein the content by weight of said inorganic or organic fibers is between 45 and 65%.
8. The prepreg as claimed in any one of claims 1 to 6 , wherein the content by weight of said inorganic or organic fibers is between 50 and 60%.
9. A composite material comprising the prepreg as claimed in claim 7 .
10. The composite material as claimed in claim 9 , in the form of a monolithic panel consisting of said prepreg.
11. The composite material as claimed in claim 9 , comprising a core material sandwiched between at least two of said prepregs, serving as skins.
12. The composite material as claimed in claim 11 , wherein said core material is a foam material, or a honeycomb material.
13. A process for manufacturing a composite material as claimed in claim 9 by a continuous lamination technique, under a pressure of 0.1 to 3 bar, and at a temperature ranging from 180 to 240° C.
14. The process for manufacturing a composite material as claimed in claim 9 by the vacuum molding technique using a rigid mold made of composite or made of metal, and a flexible cover, with a reduced pressure ranging from 0.1 to 900 mbar, and at a temperature ranging from 180 to 240° C.
15. The process for manufacturing a composite material as claimed in claim 9 by the thermo-compression molding technique in a metal mold, with a pressure ranging from 0.1 to 50 bar and at a temperature of from 180 to 240° C.
16. The composite material of claim 9 wherein said composite material is a part for aeronautical, naval, rail or road transportation construction, structural or semi-structural mechanical parts.