WO2005033393A1 - Materiaux composites thermoplastiques renforces par des fibres et leur procede de fabrication - Google Patents

Materiaux composites thermoplastiques renforces par des fibres et leur procede de fabrication Download PDF

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Publication number
WO2005033393A1
WO2005033393A1 PCT/US2004/032266 US2004032266W WO2005033393A1 WO 2005033393 A1 WO2005033393 A1 WO 2005033393A1 US 2004032266 W US2004032266 W US 2004032266W WO 2005033393 A1 WO2005033393 A1 WO 2005033393A1
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WO
WIPO (PCT)
Prior art keywords
matrix material
stack
thermoplastic prepreg
product
fiber
Prior art date
Application number
PCT/US2004/032266
Other languages
English (en)
Inventor
Joe Grasty
Original Assignee
Fabrics Technologies Llc
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Fabrics Technologies Llc filed Critical Fabrics Technologies Llc
Publication of WO2005033393A1 publication Critical patent/WO2005033393A1/fr

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
    • B32B5/22—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed
    • B32B5/24—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer
    • B32B5/26—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer another layer next to it also being fibrous or filamentary
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/06—Fibrous reinforcements only
    • B29C70/10—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres
    • B29C70/16—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length
    • B29C70/20—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in a single direction, e.g. roofing or other parallel fibres
    • B29C70/202—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in a single direction, e.g. roofing or other parallel fibres arranged in parallel planes or structures of fibres crossing at substantial angles, e.g. cross-moulding compound [XMC]
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
    • B29C70/32—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core on a rotating mould, former or core
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/40—Shaping or impregnating by compression not applied
    • B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
    • B29C70/46—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/40—Shaping or impregnating by compression not applied
    • B29C70/50—Shaping or impregnating by compression not applied for producing articles of indefinite length, e.g. prepregs, sheet moulding compounds [SMC] or cross moulding compounds [XMC]
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/40—Shaping or impregnating by compression not applied
    • B29C70/50—Shaping or impregnating by compression not applied for producing articles of indefinite length, e.g. prepregs, sheet moulding compounds [SMC] or cross moulding compounds [XMC]
    • B29C70/504—Shaping or impregnating by compression not applied for producing articles of indefinite length, e.g. prepregs, sheet moulding compounds [SMC] or cross moulding compounds [XMC] using rollers or pressure bands
    • B29C70/506—Shaping or impregnating by compression not applied for producing articles of indefinite length, e.g. prepregs, sheet moulding compounds [SMC] or cross moulding compounds [XMC] using rollers or pressure bands and impregnating by melting a solid material, e.g. sheet, powder, fibres
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B38/00—Ancillary operations in connection with laminating processes
    • B32B38/0004—Cutting, tearing or severing, e.g. bursting; Cutter details
    • D—TEXTILES; PAPER
    • D04—BRAIDING; LACE-MAKING; KNITTING; TRIMMINGS; NON-WOVEN FABRICS
    • D04H—MAKING TEXTILE FABRICS, e.g. FROM FIBRES OR FILAMENTARY MATERIAL; FABRICS MADE BY SUCH PROCESSES OR APPARATUS, e.g. FELTS, NON-WOVEN FABRICS; COTTON-WOOL; WADDING ; NON-WOVEN FABRICS FROM STAPLE FIBRES, FILAMENTS OR YARNS, BONDED WITH AT LEAST ONE WEB-LIKE MATERIAL DURING THEIR CONSOLIDATION
    • D04H3/00—Non-woven fabrics formed wholly or mainly of yarns or like filamentary material of substantial length
    • D04H3/02—Non-woven fabrics formed wholly or mainly of yarns or like filamentary material of substantial length characterised by the method of forming fleeces or layers, e.g. reorientation of yarns or filaments
    • D04H3/04—Non-woven fabrics formed wholly or mainly of yarns or like filamentary material of substantial length characterised by the method of forming fleeces or layers, e.g. reorientation of yarns or filaments in rectilinear paths, e.g. crossing at right angles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
    • B32B2262/10—Inorganic fibres
    • B32B2262/106—Carbon fibres, e.g. graphite fibres

Definitions

  • This invention relates to composite fabric materials made of reinforcing fibers and a matrix material, and a manufacturing process thereof.
  • Composite fabric materials, or fiber-reinforced plastic materials have been widely used as component materials of aircrafts, boats, sporting goods and other items.
  • composite fabric materials made of fibers such as carbon fibers
  • fiber bundles (yarns, also referred to as tows when the fibers are unidirectional) may be held together by an adhesive material.
  • One existing method of producing such a material uses a "prepreg" formed by impregnating carbon fiber bundles with an epoxy resin composition or other adhesive material.
  • prepreg formed by impregnating carbon fiber bundles with an epoxy resin composition or other adhesive material.
  • One disadvantage of composite fabric materials made by conventional methods is that they tend to be stiff and difficult to work with and thus unsuitable for certain applications.
  • One type of known product is staple fiber based blended thermoplastic composite materials.
  • Another known type of products, referred to as co-mingled materials is made with a process continuous reinforcement fibers are co-mingled with matrix fibers to yield a mixed total which can be converted into woven fabrics, braids, etc.
  • the disadvantages of this method are poor wet-out at other than high pressures (25 bars plus) when processing, the expense of converting into usable form (fabrics) and the limitation of multiaxial fiber orientations.
  • Another known method referred to as co-weaving and co-braiding, is a process where continuous reinforcement fibers are co-woven or braided with matrix fibers to yield fabrics, braids, etc.
  • the disadvantages of this method are even poorer wet-out and fiber/matrix uniformity even when formed at high pressures (25 bars plus).
  • the lack of uniformity in fiber/matrix yields poor physical properties.
  • the expense of converting into usable form and multiaxial fiber also limit its applications.
  • Another known method referred to as hot melt process, is a process where continuous reinforcement fibers are collimated to desired area weights and mated or impregnated with a molten thermoplastic matrix to yield a true prepreg.
  • the disadvantages of this method are that the uniaxial tape or fabric is very stiff, boardy, and difficult to place and orient in forming molds. High pressure must be used to overpower the inherent lack of pliability, thereby resulting in poor fiber orientation in the formed parts. Multiaxial configurations must be orientated and welded in place by hand. This form of uniaxial prepreg can also be slit into narrow tapes and converted into woven or braided constructions. These constructions still exhibit the difficult handling problems stated above.
  • the present invention is directed to a metho of manufacturing a composite fabric material and such a material that substantially obviate one or more of the problems due to limitations and disadvantages of the related art.
  • Objects of the present invention include to advance the state of the art with regards to fiber reinforced thermoplastic raw materials, to facilitate less labor intensive process parameters, to facilitate superior methods of establishing and maintaining desired proper fiber orientation in the formed (molded) parts, to offer a viable alternative true engineering thermoplastic composite to compete with the thermoset composites, and to reduce the industry dependency on the toxic thermoset materials and their inherent hazardous waste disposal problems. Additional features and advantages of the invention will be set forth in the descriptions that follow and in part will be apparent from the description, or may be learned by practice of the invention.
  • the present invention provides a method of making a multiaxial continuoiis filament thermoplastic prepreg including a step (a) of producing a unidirectional thermoplastic prepreg material, and a step (b) of producing a multiaxial thermoplastic prepreg.
  • Step (a) includes (al) placing one or more layers of a thermoplastic matrix material over and/or under a bundle of continuous fibers; (a2) heating the layers of matrix material and the fiber bundle, the heating being sufficient to melt the matrix material; (a3) applying a pressure on the heated layers of matrix material and the fiber bundle; and (a4) cooling the resulting product of step (a3).
  • Step (b) includes: (bl) layering a plurahty of the unidirectional thermoplastic prepreg materials into a stack, wherein the unidirectional thermoplastic prepreg materials in the stack have a plurality of fiber orientations; (b2) heating the stack of unidirectional thermoplastic prepreg materials, the heating being" sufficient to melt the matrix material; (b3) applying a pressure on the heated stack of unidirectional thermoplastic prepreg materials; and (b4) cooling the resulting product of step (b3).
  • a step (c) may be performed to cut the product of step (b) into pieces having sizes smaller than one inch.
  • the above steps (a) and (b) may be practiced independently.
  • step (a) may be useful in processes other than step (b); and the starting materials for step (b) may other materials than those produced by step (a).
  • the present invention provides a composite fabric products made by the above-described process or processes. It is to be understood that both the foregoing general description and the following detailed description are exemplary and explanatory and are intended to provide further explanation of the invention as claimed.
  • Figure 1 illustrates method steps of making a fiber-reinforced thermoplastic composite material according to an embodiment of the present invention.
  • Figure 2 schematically illustrates a process of making a unidirectional product according to an embodiment of the present invention.
  • Figures 3(a) and 3(B) schematically illustrate a product made by a method according to an embodiment of the present invention.
  • Figure 4 schematically illustrates a process of making a multiaxial product according to an embodiment of the present invention.
  • Embodiments of the present provides a method of combining, prepregging, or converting of continuous reinforcing fibers with thermoplastic matrix resins in such a manner or process to achieve a supple, highly flexible, easily preformed and user friendly uniaxial or multiaxial true engineering thermoplastic raw material.
  • products made by methods according to embodiments of the present invention are continuous fiber reinforcement with thermoplastic matrix tapes or fabrics which exhibit uniaxial or multiaxial fiber orientations. These tapes and fabrics may be supplied as such or reduced to specific or random cut sizes such as 0.5 inch x 0.5 inch pieces. The latter type of product is typically classified as molding compounds.
  • a method of making a fiber-reinforced thermoplastic composite material generally includes the following processes.
  • the first process is the preparation of a tape or fabric product using a heat and pressure method. This step includes collimating uniaxial continuous fiber reinforcements into suitable widths and area weights, then mating, combine prepregging or converting these reinforcements with various thermoplastic matrix materials using a selective heat and pressure continuous process. This yields a tape or fabric product with sufficient structural integrity to be secondarily processed.
  • the product of Step 1 may be referred to as a prepreg.
  • the second process takes the resulting product from Step 1, and by mating, combining, or converting, cross plying it into multiaxial fabric product with the desired ply count and fiber angle orientations using one or more of the suitable processes more fully described below.
  • the product of Step 2 may be characterized as continuous filament, thermoplastic prepreg.
  • the third process takes the resulting products from Step 2 and by slitting, cutting or chopping, reducing the products into specific or random cut sizes such as 0.5 inch x 0.5 inch pieces.
  • the third process achieves an engineering thermoplastic molding compound.
  • the product of the Step 2 may be treated as an end product in itself, useful in the uncut form.
  • Step 1 and Step 2 individually are new and unique may be used separately.
  • the process of Step 1 may be practiced to produce a commercial product, which may be subsequently used in a process described in Step 2 or other suitable processes.
  • suitable processes and products made by such processes include woven fabric, uniaxial fabric, multiaxial fabric, stitch bonded fabric, spun bonded fabric, heat bonded fabric, braid, and molding Compound.
  • Such processes are conventional and no further description is necessary here.
  • the Step 2 may be practiced using a prepreg product made by the process of Step 1, or a prepreg made by other processes.
  • Step 3 is optional; the product of Step 2 may be a separate commercial product.
  • the fiber reinforcements may be continuous filament carbon fibers, continuous filament aramid fibers, continuous filament glass fibers, hybrids of these fibers, or other suitable fibers.
  • the matrix material may be various amorphous thermoplastic resins or copolymers thereof, various crystalline thermoplastic resins or copolymers thereof, or hybrids of the above.
  • the composite ratio combinations of the reinforcements and the matrix material may range from 70/30 to 30/70 percent by volume of the product.
  • Step 1 collimated continuous reinforcing fibers at a desired area weight are combined with a spun bonded thermoplastic matrix resin (often referred to as a web or veil by those skilled in the art) using a heat and pressure process whereby the product yield is a uniaxial tape or fabric composite raw material.
  • a spun bonded thermoplastic matrix resin often referred to as a web or veil by those skilled in the art
  • this uniaxial product itself exhibits advantageous and desirable physical properties described in this specification. It is supple, pliable, flexible, and thereby easily preformed into difficult geometric shapes while maintaining the desired fiber orientations. This results in fabricated parts that can be lighter in weight and exhibit more uniformity in the translation of physical properties.
  • Step 1 to convert the continuous fibers reinforcements using a thermoplastic matrix into a prepreg may be achieved using machines with the sophisticated specific capabilities outlined below, with reference to Fig. 2.
  • the step of collimating the fibers (20) may be performed using conventional spool creels (21) through graduated gates or combs (22) and over and around mandrels (23) to achieve tension and present a uniform oriented web of the desired fiber area weight to the mating zones of the machine.
  • the next process step which is to separately mate the spun bonded thermoplastic matrix (24) of the desired formulation and weight to yield the combined weight or volume percent desired in prepreg fabric, may be performed in a minimum three zone mating area in the machine.
  • Zone one (25) is a heat area
  • zone two (26) includes pressure rolls or plates
  • zone three (27) is the cooling zone.
  • the fiber and matrix are preferably sandwiched between heat resistant release films (not shown). Commonly available products may be used as the release film.
  • the time, heat and pressure applied by the machine process depend on the nature of the matrix material (data developed and supplied by the matrix manufacturer may be used to determine these parameters).
  • Step 2 The production process (Step 2) to convert the resultant unidirectional prepreg fabric from Step 1 above into multiaxial quasi-isotropic constructions may be achieved by using a different set of sophisticated machine capabilities. In Step 2, multiple rolls of the prepreg product of Step 1 of a desired width may be cross plied at various angles to achieve a desired quasi-isotropic construction. Fig.
  • Step 2 schematically illustrates a product 31 having four plies PI through P4 at fiber angles of 90 degrees, -45 degrees, +45 degrees, and 0 degrees, respectively.
  • Fig. 3(b) is an exploded view illustrating the four plies and the respective fiber orientations.
  • the machine to accomplish this task (Step 2) preferably accepts two or more rolls of the prepreg product at various angles and is capable of cutting and delivering to a carrier (prepreg or release film) continuously traveling through the machine precisely orientated and placed cut sizes.
  • This multiaxial quasi-isotropic stacked build-up continues to the ancillary film mating stage and through the same or similar heat, compaction and cooling process described above with reference to Step
  • Step 2 illustrates an example of how the multiple layers are laid down.
  • the product yielded by Step 2 is a fiber/thermoplastic multiaxial prepreg with desirable physical properties described in this specification.
  • the machines used in Step 1 and Step 2 may be separate machines, or one machine with combined capabilities for both steps described above.
  • An application extension of the resultant product from Step 2 is the further processing of the product into molding compound (Step 3). Because of the ease of achieving a multiaxial tape or fabric using the process of Step 2, the product of Step

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Composite Materials (AREA)
  • Mechanical Engineering (AREA)
  • Textile Engineering (AREA)
  • Reinforced Plastic Materials (AREA)

Abstract

L'invention concerne un procédé de fabrication de préimprégnés thermoplastiques à filaments continus multiaxiaux. Ledit procédé comprend une étape (a) de production d'un préimprégné thermoplastique unidirectionnel et une étape (b) de production d'un préimprégné thermoplastique multiaxial. L'étape (a) consiste (a1) à placer une ou plusieurs couches d'un matériau matrice thermoplastique sur et/ou sous un faisceau de fibres continues ; (a2) à chauffer les couches de matériau matrice et le faisceau de fibres, le chauffage étant suffisant pour faire fondre le matériau matrice ; (a3) à appliquer une pression sur les couches chauffées du matériau matrice et sur le faisceau de fibres ; et (a4) à refroidir le produit obtenu lors de l'étape (a3). L'étape (b) consiste (b1) à disposer en couches une pluralité des matériaux préimprégnés thermoplastiques unidirectionnels de manière à former un empilement, les matériaux de l'empilement présentant une pluralité d'orientations de fibres ; (b2) à chauffer l'empilement de matériaux, le chauffage étant suffisant pour faire fondre le matériau matrice ; (b3) à appliquer une pression sur l'empilement chauffé de matériaux préimprégnés thermoplastiques unidirectionnels ; et (b4) à refroidir le produit obtenu lors de l'étape (b3).
PCT/US2004/032266 2003-09-30 2004-09-30 Materiaux composites thermoplastiques renforces par des fibres et leur procede de fabrication WO2005033393A1 (fr)

Applications Claiming Priority (2)

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US50758103P 2003-09-30 2003-09-30
US60/507,581 2003-09-30

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Cited By (16)

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Publication number Priority date Publication date Assignee Title
WO2008045248A1 (fr) * 2006-10-05 2008-04-17 Ocv Intellectual Capital, Llc Textile traité par infusion permettant des vitesses d'infusion de résine élevées
WO2008014784A3 (fr) * 2006-08-04 2008-11-20 Md Fibertech Corp Procédé de fabrication continue d'une bande de canevas multiaxiale
CN101516612A (zh) * 2006-08-04 2009-08-26 Md光纤技术公司 用于连续制造多轴向织物幅的方法
WO2012152242A1 (fr) * 2011-05-12 2012-11-15 Skl Schwergewebekonfektion Lichtenstein Gmbh Structure textile de renforcement multicouche intégrant une matrice thermoplastique pour la fabrication de structures façonnables de demi-produits composites renforcés par des fibres
US20130213571A1 (en) * 2012-02-22 2013-08-22 Karl Mayer Malimo Textilmaschinenfabrik Gmbh Method and device for producing a composite material
WO2014062900A1 (fr) * 2012-10-18 2014-04-24 Cytec Industries Inc. Ingénierie de surface de matières thermoplastiques et outillage
US8921692B2 (en) 2011-04-12 2014-12-30 Ticona Llc Umbilical for use in subsea applications
US9190184B2 (en) 2011-04-12 2015-11-17 Ticona Llc Composite core for electrical transmission cables
WO2015191354A1 (fr) 2014-06-09 2015-12-17 Dow Global Technologies Llc Procédé de fabrication de pré-imprégné renforcé par des fibres, multicouche, durcissable
CN106003876A (zh) * 2016-05-18 2016-10-12 中国电子科技集团公司电子科学研究院 一种防拉铆撕裂的复合材料及敷设方法
WO2019155013A1 (fr) * 2018-02-09 2019-08-15 Institut De Recherche Technologique Jules Verne Procédé de fabrication d'une pièce préimprégnée en matériau composite
WO2020072009A1 (fr) * 2018-10-04 2020-04-09 B Preg Kompozit Ve Tekstil Muhendislik Danismanlik Sanayi Ticaret Anonim Şirketi Matériaux composites semi-finis contenant des fibres naturelles et leur production
US10676845B2 (en) 2011-04-12 2020-06-09 Ticona Llc Continuous fiber reinforced thermoplastic rod and pultrusion method for its manufacture
US20200238659A1 (en) * 2012-02-08 2020-07-30 Mitsubishi Chemical Advanced Materials Composites Ag Planar composite material
EP3789190A1 (fr) * 2019-09-04 2021-03-10 Corex Materials Corporation Procédé de fabrication de matériau composite
EP4317265A1 (fr) 2022-08-04 2024-02-07 Kuraray Europe GmbH Procédé de production d'une feuille organique

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US5445693A (en) * 1988-09-26 1995-08-29 Vane; Jeffrey A. Method of producing a formable composite material
US6139942A (en) * 1997-02-06 2000-10-31 Cytec Technology, Inc. Resin composition, a fiber reinforced material having a partially impregnated resin and composites made therefrom
US6399199B1 (en) * 1999-12-28 2002-06-04 Toray Industries Inc. Prepeg and carbon fiber reinforced composite materials
US6599610B2 (en) * 2000-02-28 2003-07-29 Toray Industries, Inc. Multiaxially stitched base material for reinforcing and fiber reinforced plastic, and method for preparing them

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Publication number Priority date Publication date Assignee Title
US4244765A (en) * 1978-06-27 1981-01-13 Tomotoshi Tokuno Method for manufacturing a resin-reinforced carbon fiber product
US5445693A (en) * 1988-09-26 1995-08-29 Vane; Jeffrey A. Method of producing a formable composite material
US6139942A (en) * 1997-02-06 2000-10-31 Cytec Technology, Inc. Resin composition, a fiber reinforced material having a partially impregnated resin and composites made therefrom
US6399199B1 (en) * 1999-12-28 2002-06-04 Toray Industries Inc. Prepeg and carbon fiber reinforced composite materials
US6599610B2 (en) * 2000-02-28 2003-07-29 Toray Industries, Inc. Multiaxially stitched base material for reinforcing and fiber reinforced plastic, and method for preparing them

Cited By (28)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2008014784A3 (fr) * 2006-08-04 2008-11-20 Md Fibertech Corp Procédé de fabrication continue d'une bande de canevas multiaxiale
CN101516612A (zh) * 2006-08-04 2009-08-26 Md光纤技术公司 用于连续制造多轴向织物幅的方法
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