WO1992017331A1 - Preimpregne a base de fibres de carbone unidirectionnelles et de resines phenoliques et procede de fabrication - Google Patents

Preimpregne a base de fibres de carbone unidirectionnelles et de resines phenoliques et procede de fabrication Download PDF

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Publication number
WO1992017331A1
WO1992017331A1 PCT/US1992/002797 US9202797W WO9217331A1 WO 1992017331 A1 WO1992017331 A1 WO 1992017331A1 US 9202797 W US9202797 W US 9202797W WO 9217331 A1 WO9217331 A1 WO 9217331A1
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WO
WIPO (PCT)
Prior art keywords
carbon fibers
resin
layer
unidirectional carbon
layers
Prior art date
Application number
PCT/US1992/002797
Other languages
English (en)
Inventor
James D. Lincoln
Original Assignee
Lincoln James D
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 Lincoln James D filed Critical Lincoln James D
Priority to JP92511380A priority Critical patent/JPH05508128A/ja
Publication of WO1992017331A1 publication Critical patent/WO1992017331A1/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
    • B32B5/02—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 structural features of a fibrous or filamentary layer
    • B32B5/08—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 structural features of a fibrous or filamentary layer the fibres or filaments of a layer being of different substances, e.g. conjugate fibres, mixture of different 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
    • B32B29/00—Layered products comprising a layer of paper or cardboard
    • B32B29/02—Layered products comprising a layer of paper or cardboard next to a fibrous or filamentary layer
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29B—PREPARATION OR PRETREATMENT OF THE MATERIAL TO BE SHAPED; MAKING GRANULES OR PREFORMS; RECOVERY OF PLASTICS OR OTHER CONSTITUENTS OF WASTE MATERIAL CONTAINING PLASTICS
    • B29B15/00—Pretreatment of the material to be shaped, not covered by groups B29B7/00 - B29B13/00
    • B29B15/08—Pretreatment of the material to be shaped, not covered by groups B29B7/00 - B29B13/00 of reinforcements or fillers
    • B29B15/10—Coating or impregnating independently of the moulding or shaping step
    • B29B15/12—Coating or impregnating independently of the moulding or shaping step of reinforcements of indefinite length
    • B29B15/122—Coating or impregnating independently of the moulding or shaping step of reinforcements of indefinite length with a matrix in liquid form, e.g. as melt, solution or latex
    • B29B15/125—Coating or impregnating independently of the moulding or shaping step of reinforcements of indefinite length with a matrix in liquid form, e.g. as melt, solution or latex by dipping
    • 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
    • B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form
    • B32B3/10—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material
    • B32B3/12—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material characterised by a layer of regularly- arranged cells, e.g. a honeycomb structure
    • 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
    • B32B5/02—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 structural features of a fibrous or filamentary layer
    • B32B5/12—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 structural features of a fibrous or filamentary layer characterised by the relative arrangement of fibres or filaments of different layers, e.g. the fibres or filaments being parallel or perpendicular to each other
    • 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
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B7/00—Layered products characterised by the relation between layers; Layered products characterised by the relative orientation of features between layers, or by the relative values of a measurable parameter between layers, i.e. products comprising layers having different physical, chemical or physicochemical properties; Layered products characterised by the interconnection of layers
    • B32B7/04—Interconnection of layers
    • B32B7/12—Interconnection of layers using interposed adhesives or interposed materials with bonding properties
    • C—CHEMISTRY; METALLURGY
    • C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
    • C08J—WORKING-UP; GENERAL PROCESSES OF COMPOUNDING; AFTER-TREATMENT NOT COVERED BY SUBCLASSES C08B, C08C, C08F, C08G or C08H
    • C08J5/00—Manufacture of articles or shaped materials containing macromolecular substances
    • C08J5/24—Impregnating materials with prepolymers which can be polymerised in situ, e.g. manufacture of prepregs
    • C08J5/241—Impregnating materials with prepolymers which can be polymerised in situ, e.g. manufacture of prepregs using inorganic fibres
    • C08J5/243—Impregnating materials with prepolymers which can be polymerised in situ, e.g. manufacture of prepregs using inorganic fibres using carbon 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
    • B32B2260/00—Layered product comprising an impregnated, embedded, or bonded layer wherein the layer comprises an impregnation, embedding, or binder material
    • B32B2260/02—Composition of the impregnated, bonded or embedded layer
    • B32B2260/021—Fibrous or filamentary layer
    • 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
    • B32B2260/00—Layered product comprising an impregnated, embedded, or bonded layer wherein the layer comprises an impregnation, embedding, or binder material
    • B32B2260/04—Impregnation, embedding, or binder material
    • B32B2260/046—Synthetic resin
    • 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
    • B32B2262/101—Glass 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
    • 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
    • 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
    • B32B2307/00—Properties of the layers or laminate
    • B32B2307/50—Properties of the layers or laminate having particular mechanical properties
    • B32B2307/558—Impact strength, toughness
    • 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
    • B32B2317/00—Animal or vegetable based
    • B32B2317/12—Paper, e.g. cardboard
    • 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
    • B32B2605/00—Vehicles
    • B32B2605/18—Aircraft
    • C—CHEMISTRY; METALLURGY
    • C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
    • C08J—WORKING-UP; GENERAL PROCESSES OF COMPOUNDING; AFTER-TREATMENT NOT COVERED BY SUBCLASSES C08B, C08C, C08F, C08G or C08H
    • C08J2361/00—Characterised by the use of condensation polymers of aldehydes or ketones; Derivatives of such polymers
    • C08J2361/04—Condensation polymers of aldehydes or ketones with phenols only
    • C08J2361/06—Condensation polymers of aldehydes or ketones with phenols only of aldehydes with phenols

Definitions

  • This invention relates to laminated materials and the individual layers of which such materials are composed, and more particularly, to such materials for use in aircraft interiors.
  • desirable materials provide a high degree of strength, stiffness, and resis ⁇ tance to impact. These materials are commonly used in such applications as airplane interiors, cargo spaces and the like and are usually substantially planar, multi- layered materials which incorporate a synthetic resin. • Ideally, in addition to offering optimal strength-weight properties, the laminated material should be easy to cut, and easy to handle during installation and repair. In many cases, the laminated assemblies contain a layer or layers of molding material which incorporates a synthetic resin. These resin-impregnated materials are frequently known by the term "prepregs.” As used herein, and as used in the industry, this term refers to an intermediate product in the manufacturing process.
  • the invention disclosed herein relates to a resin- impregnated material or "prepreg," a multi-layered lami ⁇ nate assembly which incorporates the prepreg disclosed herein, and a method for making such a material.
  • prepreg resin- impregnated material
  • multi-layered lami ⁇ nate assembly which incorporates the prepreg disclosed herein, and a method for making such a material.
  • a preferred embodiment of the multi-layered laminate fea ⁇ tures superior strength, stiffness and impact resistance compared to similar materials presently known.
  • a multi-layered prepreg comprises a substantially planar core material overlaid on one or both surfaces with other materials which provide additional structural strength and may individually help to bind the layers together.
  • a cross- section of such a material would reveal an inner core material with other layers applied to one or both planar surfaces.
  • the use of certain materials as the individual layers of a multi-layered prepreg assembly is well-known in the art. For example, use of woven glass cloth, fiberglass and carbon fibers is known and the general characteristics of each are familiar to those skilled in the art.
  • Most prepreg assemblies feature one or more layers containing a type of fiber such as glass or carbon.
  • a type of fiber such as glass or carbon.
  • the properties of these layers and their methods of manufac- ture may vary.
  • common fiberglass material is a sheet comprising numerous tiny glass fibers in a random array to which a resin is added, and the resulting composition may be shaped into a desired form.
  • individual fibers may be woven in a cloth-like fashion which may provide certain advantages in strength and allows easier handling and manufacture.
  • carbon fibers utilized in prepregs have been either woven or unidirectional. Unidirectional carbon fibers are not woven such that individual fibers run perpendicular to, and pass over and under one another; rather, all the individual fibers run parallel to one another and are commercially available in ribbon form wound onto spools.
  • Characteristic of prepregs is use of a synthetic resin which aids in holding the layers together and provides structural strength and stiffness. Years ago, phenolic resins were widely used, but the phenolic-based prepregs exhibited less than ideal properties because the phenolic resins were brittle and did not bind well to the materials used as the core layer. With respect to the binding and brittleness properties, epoxy resins performed better than phenolic resins and offered advantages in the manufactur ⁇ ing process because epoxy resins could be used without first being dissolved in a solvent, which was necessary with the phenolic resins. Moreover, epoxy-based prepregs offered advantages in weight and strength and became widely used, largely phasing out the phenolic-based prepregs.
  • the type of resin used also has a bearing on the type of fiber used.
  • woven fibers are preferred because a sol ⁇ vent-based resin application system did not exist for use with unidirectional fibers.
  • the use of unidirec ⁇ tional fibers has been limited to non-solvent based, epoxy resin application systems.
  • a fabric of woven fibers is impregnated with a phenolic resin/solvent solution and dried, thus forming the pre ⁇ preg.
  • the present invention enables the use of unidirection ⁇ al carbon fibers with phenolic resin/solvent solutions.
  • a manufacturing process is described herein which produces sheets of phenolic-resin impregnated unidirectional carbon fibers which are ultimately used in forming a laminated assembly. Testing data has revealed that laminated assemblies which incorporate these prepregs have superior strength, stiffness and impact resistance properties while maintaining favorable smoke and burn characteristics.
  • most aircraft interior prepregs are comprised of woven fiber ⁇ glass or woven carbon fibers which are coated with a solution of resin and laminated to both sides of a paper honeycomb core.
  • varying thicknesses of the core and different types of fiberglass or carbon fibers may be used. Additionally different quantities, types and application processes of resin can be used.
  • the amount of carbon present in an individual type of prepreg may be described by the "Areal weight" of the prepreg which measures the grams of carbon in a square meter of the final prepreg.
  • the commercially available Amoco EXAS-33-500 epoxy-based prepreg has an Areal weight of about 150 g/m 2 and a laminated assembly featuring this prepreg has an impact resistance of approximately sixty inch-pounds.
  • an embodiment of the present invention with an Areal weight of 150 g/m 2 has an impact resistance of up to 140 inch-pounds. Similar impact-resistance properties have been achieved with embodiment of the present invention with an Areal weight as low as 120 g/m 2 .
  • Lincoln, Inc. weighs 1.6 times as much per area as that made according to the present invention and will withstand an impact of eighty-five inch-pounds.
  • Another prepreg manufactured by Fibrerite, Inc. and used in the McDon ⁇ nell-Douglas MD-80, will withstand an impact of ninety inch-pounds but weighs twice as much as that of the present invention.
  • FIGURE 1 illustrates a preferred embodiment of the present invention showing the individual layers of the final laminated assembly separated from each other to reveal the relationship of the individual layers of which the final prepreg is comprised.
  • FIGURE 2 illustrates an apparatus which may be used in the manufacturing process of an individual sheet of resin- impregnated unidirectional carbon fibers.
  • FIGURE 3 illustrates a preferred embodiment of the present invention showing a final laminated assembly with a partial cut-away of each individual layer to show one possible orientation of the individual layers.
  • the inner core material may comprise a number of materials which are low in cost and light in weight.
  • a preferred embodiment of the present invention utilizes a core 1 composed of an aramid paper pre-formed through a conventional process into a honeycomb pattern and dipped in phenolic resin.
  • the film contains a phenolic resin and, although its structural properties are unknown, the adhesive film layers facilitate binding the inner core 1 to the outer layers.
  • Sheets of unidirectional carbon fibers 3 and 3 1 are prepared by a novel process in which the fibers are immersed in a resin bath after being arranged into a sheet of uniform thickness.
  • a novel manufacturing process for preparing such resin-impregnated fibers is disclosed herein, although impregnation of fibers with a synthetic resin is a known procedure that may be accomplished in a variety of ways.
  • Layers 3 and 3' are two layers of resin- impregnated unidirectional carbon fibers which are identi- cal in manufacture and are oriented substantially perpen ⁇ dicular to one another such that the individual carbon fibers in the sheet are in a 0°/ 90 ° orientation.
  • Layers 4 are composed of a glass scrim cloth which is attached to the layers of carbon fibers 3 and 3*. Ultimately, this assem ⁇ bly is cured in a laminating press to fuse the layers together for use as the final prepreg product.
  • one preferred method is to draw strands or "ribbons" of Toray T-700 carbon fibers 12 from several spools 11.
  • the number and orientation of the individual spools is for illustra- tive purposes only; in practice the number of spools 11 may be far greater, and the spools 11 could be placed in many suitable arrangements.
  • the number of spools will vary as a function of the width and thickness of the spooled carbon fiber strands and the weight of carbon desired in the prepreg.
  • the strands of carbon fibers 12 are passed through a guide 13 or series of guides which are oriented to align and assemble the strands to form a uniform sheet 14 of the desired width and thickness.
  • Increasing the thicknesses of the sheet of the fibers thus assembled requires only the use of more spools of carbon fiber.
  • Further uniformity in thickness can be achieved by passing the strands of carbon fiber under and over a series of cylindrical bars 15 such that the bars slightly deflect the path of the strands.
  • the two cylindrical bars 15 shown in FIGURE 2 are meant to be representative of one or more of such apparatus as needed to create a continuous sheet of carbon fibers of uniform thickness.
  • the strands of carbon fibers should form a sheet of substantially uniform thickness without gaps or holes in the sheet so that after being immersed in resin the fiber sheet of carbon fibers is continuous and uniform.
  • the present invention describes a superior method of applying the resin.
  • impregnating fibers with resin through the use of a resins dissolved in a solvent in a bath 16 rather than a pre-formed resin film reduces the viscosity of the resin which is believed to increase the degree to which the resin impregnates the fibers. It is further believed that this method increases the bonding of the resins to the fiber substrate.
  • the resulting continuous sheet is then passed through a resin bath 16 to coat and impregnate the carbon fibers with phenolic resin.
  • the phenolic-resin bath solution 17 contains liquid resin dissolved in a solvent.
  • the resin is the commercially available phenolic resin Chem-Bond 6010.
  • the phenolic-resin solution con ⁇ tains 60% phenolic resin solids dissolved in methanol.
  • ethanol is added to bring the specific gravity of the resin-bath solution to approximately 0.94 g/ml.
  • the resulting resin-impregnated continuous sheet of unidirectional carbon fibers is drawn underneath an edge 18 that removes excess resin from the sheet of fibers.
  • This continuous sheet of unidirectional carbon fibers 19 is applied to a roll of silicone-coated paper 20 and passed through an oven 21 for six minutes with an ambient air temperature of approximately 210"F ⁇ 10°.
  • a first layer of the unidirectional carbon fibers is prepared in a desired shape and size by laying out a series of the sheets of resin-impregnated carbon fibers with the treated-paper backing. Additional layers of resin-impregnated carbon fibers are applied to the first layer. Taking advantage of the treated paper backing, additional layers are applied so that the carbon fibers of each layer face and contact one another and so that the treated paper backing can be peeled off in preparation for applying another layer of carbon fibers or a different component of the final laminated assembly.
  • a second layer of unidirec ⁇ tional carbon fibers is laid on top of, and substantially perpendicular to, the first layer.
  • This assembly is termed a "o°/ 90 ° unidirectional carbon fiber prepreg.”
  • the treated paper is removed from one side of this assem ⁇ bly.
  • a layer of type 108 glass scrim cloth which covers one entire surface of the resulting prepreg and thus becomes an exterior surface of the final prepreg. This layer eases handling of the resulting prepreg and prevents fraying of the prepreg and other underlying material if the prepreg is cut to fit its intended use.
  • another assembly compris ⁇ ing two layers of fibers 22 and one layer of glass scrim cloth 4, identical in size and manufacture to the one described immediately above, is prepared.
  • a layer of adhesive film 2 is attached to both sides of a honey ⁇ comb paper core material 1 of the desired shape.
  • the remaining paper backing is removed from the layers of carbon fibers and glass cloth, and the carbon fiber layer is placed most proximate to the core material so that a layer of carbon fibers directly contacts the adhesive film layer.
  • the glass cloth layer constitutes both exterior layers of the final laminated assembly.
  • the final laminated assembly is placed in a laminating press and cured for about ten minutes to two hours at a temperature of approx ⁇ imately 260-350"F at approximately 25-200 psi, preferably at about fifty psi.
  • the resulting laminated assembly is 10-12mm thick, although the thickness can be varied depending on the allowable weight and desired strength.
  • the unidirectional carbon fiber layers, the adhesive film layers and the layer of glass scrim cloth are combined without the inner core material.
  • a 0°/ 90 ° unidirectional carbon fiber prepreg is prepared as described above.
  • a layer of the glass scrim cloth is attached to one surface and the adhesive film layer is attached to the other surface.
  • This assembly is bound together by placing it in a lami ⁇ nating press at approximately 5 psi and 125-175°F for ten minutes to two hours.
  • This step may be performed under vacuum although the quality of the final prepreg does not appear to be affected by the vacuum environment.
  • the layers of the prepreg are combined without the inner core material so that the essential elements of the prepreg may be commercially available without being bound to a particular core mater ⁇ ial.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Health & Medical Sciences (AREA)
  • Inorganic Chemistry (AREA)
  • Manufacturing & Machinery (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Medicinal Chemistry (AREA)
  • Polymers & Plastics (AREA)
  • Organic Chemistry (AREA)
  • Mechanical Engineering (AREA)
  • Reinforced Plastic Materials (AREA)
  • Laminated Bodies (AREA)

Abstract

Matériaux stratifiés utilisés fréquemment comme revêtements internes d'avions, et utilisation de résines phénoliques et de fibres de carbone unidirectionnelles (14) pour former un préimprégné, comprenant la totalité des couches des matériaux stratifiés. On décrit également un nouveau procédé de fabrication d'un tel préimprégné ainsi que le produit de ce procédé. Le matériau stratifié obtenu présente des propriétés supérieures de résistance mécanique et de résilience, ainsi que des caractéristiques favorables quant à la combustion et au dégagement de fumée.
PCT/US1992/002797 1991-04-04 1992-04-01 Preimpregne a base de fibres de carbone unidirectionnelles et de resines phenoliques et procede de fabrication WO1992017331A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
JP92511380A JPH05508128A (ja) 1991-04-04 1992-04-01 単一方向配列の炭素繊維／フェノール樹脂プリプレグ材料とその製法

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US68052591A 1991-04-04 1991-04-04
US680,525 1991-04-04

Publications (1)

Publication Number Publication Date
WO1992017331A1 true WO1992017331A1 (fr) 1992-10-15

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Country Link
EP (1) EP0535214A4 (fr)
JP (1) JPH05508128A (fr)
WO (1) WO1992017331A1 (fr)

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1998034979A1 (fr) * 1997-02-06 1998-08-13 Cytec Technology Corp. Materiau fibreux partiellement impregne de resine
EP1054091A1 (fr) * 1999-05-20 2000-11-22 SA Schappe Nappe unidirectionnelle de fibres de carbone
US6242090B1 (en) 1993-07-26 2001-06-05 Hexcel Corporation Fibre reinforced resin composite products
FR2821790A1 (fr) * 2001-03-07 2002-09-13 A Chomarat Cie Ets Fils D Procede de realisation d'un nouveau produit de renforcement et de revetement et produit nouveau obtenu
US7112372B2 (en) 2003-04-02 2006-09-26 Hexcel Reinforcements Pigmented panel assembly
WO2009122354A1 (fr) * 2008-04-01 2009-10-08 Fondazione Istituto Italiano Di Tecnologia Procédé de fabrication de tissus de fibres de carbone fonctionnels
EP1927464A3 (fr) * 2006-11-30 2010-04-21 Jamco Corporation Panneau en sandwich
EP1930519A3 (fr) * 2006-11-30 2010-10-27 Jamco Corporation Panneau en sandwich
US7964052B2 (en) 2002-03-08 2011-06-21 Gurit (Uk) Limited Moulding material
DE102012101295A1 (de) * 2012-02-17 2013-08-22 Lff Composite Technology Gmbh Faserverbundwerkstoff
WO2014195884A1 (fr) * 2013-06-06 2014-12-11 Les Stratifies Panneau composite pour planchers ou éléments d'habillage de paroi, et procédé de fabrication d'un tel panneau
US20150204476A1 (en) * 2014-01-23 2015-07-23 Neptune Research, Inc. Unidirectional fiber composite system for structural repairs and reinforcement
EP2152454B2 (fr) † 2007-06-08 2017-02-22 G. Angeloni S.r.l. Renforcement fibreux, tel qu'un renforcement pour matériau composite
EP3248774A1 (fr) * 2016-05-27 2017-11-29 Airbus Operations S.L. Feuerfeste verbundstruktur in polymermatrix
JP2018162383A (ja) * 2017-03-27 2018-10-18 三菱ケミカル株式会社 耐衝撃性自動車用外板に用いられる繊維強化樹脂材料
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US6565944B1 (en) 1997-02-06 2003-05-20 Cytec Technology Corp. Resin composition, a fiber reinforced material having a partially impregnated resin and composites made therefrom
WO1998034979A1 (fr) * 1997-02-06 1998-08-13 Cytec Technology Corp. Materiau fibreux partiellement impregne de resine
EP1054091A1 (fr) * 1999-05-20 2000-11-22 SA Schappe Nappe unidirectionnelle de fibres de carbone
FR2793813A1 (fr) * 1999-05-20 2000-11-24 Schappe Sa Nappe unidirectionnelle de fibres de carbone
US6410126B1 (en) 1999-05-20 2002-06-25 Sa Schappe Unidirectional tape of carbon fibers
FR2821790A1 (fr) * 2001-03-07 2002-09-13 A Chomarat Cie Ets Fils D Procede de realisation d'un nouveau produit de renforcement et de revetement et produit nouveau obtenu
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US8383231B2 (en) 2006-11-30 2013-02-26 Jamco Corporation Sandwich panel
US8025954B2 (en) 2006-11-30 2011-09-27 Jamco Corporation Sandwich panel
EP1927464A3 (fr) * 2006-11-30 2010-04-21 Jamco Corporation Panneau en sandwich
EP1930519A3 (fr) * 2006-11-30 2010-10-27 Jamco Corporation Panneau en sandwich
EP2152454B2 (fr) † 2007-06-08 2017-02-22 G. Angeloni S.r.l. Renforcement fibreux, tel qu'un renforcement pour matériau composite
WO2009122354A1 (fr) * 2008-04-01 2009-10-08 Fondazione Istituto Italiano Di Tecnologia Procédé de fabrication de tissus de fibres de carbone fonctionnels
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WO2014195884A1 (fr) * 2013-06-06 2014-12-11 Les Stratifies Panneau composite pour planchers ou éléments d'habillage de paroi, et procédé de fabrication d'un tel panneau
FR3006625A1 (fr) * 2013-06-06 2014-12-12 Stratifies Panneau composite pour planchers ou elements d'habillage de paroi, et procede de fabrication d'un tel panneau.
US9993991B2 (en) 2013-06-06 2018-06-12 Les Stratifies Composite panel for floors or wallcovering components, and method for manufacturing such a panel
RU2706663C2 (ru) * 2014-01-23 2019-11-19 Нептун Рисёрч, Ллс Композитная система с однонаправленными волокнами для ремонта и армирования конструкций
US20150321448A1 (en) * 2014-01-23 2015-11-12 Neptune Research, Inc. Kits and methods for fiber composites including partially-cured resinous materials for the reinforcement of physical structures
WO2015112757A1 (fr) * 2014-01-23 2015-07-30 Neptune Research, Inc. Système composite à fibres unidirectionnelles pour les réparations et le renfort de structures
AU2015209285B2 (en) * 2014-01-23 2018-11-29 Neptune Research, Llc Unidirectional fiber composite system for structural repairs and reinforcement
US20150204476A1 (en) * 2014-01-23 2015-07-23 Neptune Research, Inc. Unidirectional fiber composite system for structural repairs and reinforcement
US10814584B2 (en) 2014-01-23 2020-10-27 Neptune Research, Llc Kits and methods for fiber composites including partially-cured resinous materials for the reinforcement of physical structures
US10953625B2 (en) 2014-01-23 2021-03-23 Spartan Acquisition Llc Unidirectional fiber composite system for structural repairs and reinforcement
US10266292B2 (en) 2015-01-22 2019-04-23 Neptune Research, Llc Carriers for composite reinforcement systems and methods of use
US10597182B2 (en) 2015-01-22 2020-03-24 Neptune Research, Llc. Composite reinforcement systems and methods of manufacturing the same
US11453518B2 (en) 2015-01-22 2022-09-27 Csc Operating Company, Llc Composite reinforcement systems and methods of manufacturing the same
EP3248774A1 (fr) * 2016-05-27 2017-11-29 Airbus Operations S.L. Feuerfeste verbundstruktur in polymermatrix
JP2018162383A (ja) * 2017-03-27 2018-10-18 三菱ケミカル株式会社 耐衝撃性自動車用外板に用いられる繊維強化樹脂材料

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EP0535214A1 (fr) 1993-04-07
EP0535214A4 (en) 1993-09-08

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