WO2002081790A1 - Fibre composite melangee et diffusee - Google Patents

Fibre composite melangee et diffusee Download PDF

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Publication number
WO2002081790A1
WO2002081790A1 PCT/NO2002/000125 NO0200125W WO02081790A1 WO 2002081790 A1 WO2002081790 A1 WO 2002081790A1 NO 0200125 W NO0200125 W NO 0200125W WO 02081790 A1 WO02081790 A1 WO 02081790A1
Authority
WO
WIPO (PCT)
Prior art keywords
filaments
band
matrix
structural
composite
Prior art date
Application number
PCT/NO2002/000125
Other languages
English (en)
Inventor
Gard Alexander Antonsen
Original Assignee
Hiform As
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 Hiform As filed Critical Hiform As
Priority to EP02713326A priority Critical patent/EP1383946A1/fr
Publication of WO2002081790A1 publication Critical patent/WO2002081790A1/fr

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Classifications

    • 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
    • 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

Definitions

  • the invention relates to a method for producing composite fibres having an improved distribution of structural fibres, e.g. filaments of carbon, boron, aramide or similar, and matrix fibres, e.g. filaments of thermoplastic.
  • structural fibres e.g. filaments of carbon, boron, aramide or similar
  • matrix fibres e.g. filaments of thermoplastic.
  • a method for vacuum injecting resin into structural fibres is called the ⁇ Scrimp"-method, in which by means of vacuum resin is suctioned into a layup of structural fibres, e.g. glass fibres or carbon fibres, under a vacuum bag, requires that the resin is in the fluid phase before it comes into contact with the structural fibres.
  • a more advanced and cleaner solution is to apply a commingled fibre fabric consisting of structural fibres and melting fibres e.g. of thermoplastic, and laying this mat directly into the mould form and vacuum melt the entire layup in order for the melting fibres melt and envelop the structural fibres, whereby a fibre composite blank is formed and may be cooled or in other ways hardened and then removed from the mould form.
  • EPP 0 033 244 applies a matrix on the outside of a fibre by letting the fibre pass through an extrusion press or a bath of molten thermoplastic material.
  • US-Patent 5 425 796 and US 5 Oil 523 both relate to production of glass fibre filaments and thermoplastic filaments that run together to form a yarn having relatively poor distribution of glass fibre having an enveloping cover of thermoplastic filaments, see Fig. 3a, b, and c in the actual U.S. -Patent.
  • US 5 Oil 523 shows also that the final composite fibre yarn is cut into short pieces, making the fibre structure of the string inapplicable for forming composite blanks for load-bearing designs which require highest possible strength-to-weight ratio.
  • Carbon fibres, as opposed to the illustrated U. S. -patents may not be pulled directly from a bath, but must be formed through a somewhat more complex process in which a precursor thread, e.g. an acryl fibre, is pulled through a high temperature furnace in which it is carbonized to a non-melting carbon fibre, being one of the desired points of origin for the present invention
  • PCT/FR97/01184 shows extrusion of glass and formation of thermoplastic covered glass fibre filament, and winding of the final material onto a bobin.
  • US 3 091 018 also covers a glass fibre thread with resin fibre by heating, in which a coat of resin fibre is applied on the glass fibre thread.
  • the purpose is not to obtain a homogenous distribution of glass and resin fibres, but a core of one of the materials.
  • DE 20 19019 assembles two filaments of two different fibre types being cpllected at a comb and are then run over to rollers being arranged 90 degrees across the comb's plane, and as such collect the plane to one yarn.
  • EP 0 182 335 describes two yarns being twisted and, as such, thus do not provide the desired properties for the present invention' s broad band which shall be generally without twisting to avoid weaknesses in the carbon-, boron-, or aramide filaments in the final composite material, and which must to a highest possible degree be free of twisting to avoid crossed structural fibre filaments and matrix filaments before joining in order to achieve a best possible distribution and mixing of these two kinds of filaments .
  • DE 36 34904 shows glass fibres being pulled from a melt, whereby glass fibre filaments run in onto a roller from which a seize is applied, and then the seized glass fibre yarn runs into a rotation chamber in which the fibre is slung and given a twist, whereby the twisted yarn of several filaments is wound onto a bobin.
  • US 4 539 249 first twines a graphite fibre and then winds this thread of graphite fibre with a resin fibre so one single yarn is formed which may be woven to hybrid fabrics for use in a form in which the melting material may be heated and for a resin-graphite laminate.
  • the undesired twining of the graphite fibre weakens the graphite filaments in a composite fibre laminate blank that is being built from a thread formed according to the US-Patent.
  • the structural fibre may be present as a rather loose bundle of e.g. 1000 to 100 000 filaments, e.g. of carbon, boron, aramide, ceramic material, or metal, in which the bundle is available wound without twisting ("non-twisted") onto a bobin.
  • the diameter of each single filament may be 5 to 20 ⁇ .
  • the structural fibre shall be used in a process in which is it is lead adjacent to a corresponding bundle of matrix fibre of thermoplastic material as PP, PET, PBT, PEN, PEEK or others.
  • the number of filaments in the bundle may be 1000 to 100 000 filaments having a diameter of about 10 to 40 ⁇ .
  • the first problem is, that if one joins the bundle having structural fibres with the bundle having matrix fibres, a composite bundle arises in which no even distribution of structural fibres and matrix fibres necessarily exists, but that the materials respectively lie in thinner bundles of structural filaments and matrix filaments which are badly distributed when seen on a " filament level.
  • Carbon fibre bundles in particular, may have very thin filaments lying closely and which may be difficult to separate for slotting matrix fibres in between or for intrusion of molten matrix material.
  • One reason for this incapability of matrix filaments to lie themselves between the carbon fibre filaments may be the smaller diameter of the carbon fibre filaments and their higher stiffness.
  • the other problem particularly associated with the use of carbon fibres is that the filaments should lye straightest possible, without kinks on the fibres.
  • a deviation in straightness for one single fibre filaments being more than the half filament diameter may incur an essential reduction of the filament's compression module and compression strength, and other compression properties, and also the tensile module, the tensile strength and strain at rupture, both the compression strain at rupture and the tensile strength at rupture.
  • One solution to the above mentioned problems is a method for producing composite fibres having an improved distribution of non- melting structural fibres of carbon, boron or aramide, and matrix fibre filaments of thermoplastics, e.e. PET, PP, PCB, PEEK, in which the novelty by the invention comprises the following steps: a) spreading of at least one bundle of structural filaments to at least one first broad band having at least one flat surface and having a thickness corresponding to one or a small number of structural filaments, in which the spreading of the bundle of structural fibres form generally parallel running and continuous structural filaments; b) spreading of at least one bundle of matrix filaments to at least one second broad band having at least one flat surface and having a thickness corresponding to one or a small number of matrix filaments, in which the spreading of the bundle of matrix filaments form generally parallel and continuous running matrix filaments; that one locally, e.g.
  • first band and the second band preferably in parallel and in the same direction, and that one in the local parallel position, e.g. on a roller's surface, join or let run together the first band with the at least one flat surface against the other band' s at least one flat surface to a composite band, in which one lets the composite band maintain a large width with respect to the thickness in the further winding or use of the composite band.
  • the invention is also a composite fibre having an improved distribution of non-melting structural fibres of carbon, boron or aramide, and matrix fibre ' filaments of thermoplastic, e.g. of PET, PP, PCB, PEEK, in which the novel features of the invention are as follows: that it is produced by running together in a common direction of a first structure filament band's at least one flat surface adjacent to at least a second thermoplastic matrix filament band's at least one flat surface to a composite band, in which one lets the composite band maintain a large width relative to the thickness in the further winding-up or use of the composite band; that at least one bundle of structural filaments are spread by letting it run over rollers to at least a first broad band having the at least one flat surface and having a thickness corresponding to one or a small number of structural filaments, in which the spreading of the bundle of structural fibres form mainly parallel running and continuous structural filaments; in which at least one bundle of matrix filaments are spread to at least a second broad band having its at least one flat surface
  • the method of the invention it is possible to achieve that particularly the structural filaments lye straight to avoid kinks on the filaments, and that the baked-in filaments compression strength as seen on a micro-level add up to a compression strength corresponding to their number also as seen on a macro-level for the composite material.
  • the filaments lye straight and in parallel also the distribution and mixing of structural fibres and matrix fibres will take place more easily, and one achieves a band having very well distributed structural filaments and matrix filaments also down to a filament scale. This gives good laminate properties.
  • Figures 1 and 2 illustrate a side elevation view and a vertical view of the invention having a sef-up with a rack of bobins with structural fibre bundles and matrix fibre bundles each separately rolled off the bobins and rolled over broad rollers and spread to separate broad bands until the two bands are joined in a process according to the invention to a broad band which will then be a composite fibre.
  • Figure 3 is a side elevation view of the two spread bands running in onto the roller that may be called a collector or joiner or mixing station, on which a composite fibre band is formed.
  • Figure 4 is an imagined section through such a composite fibre band, in which one flat surface of the first band lye adjacent to one flat surface of the other band.
  • Figure 5 is an imagined enlarged section through such a composite fibre band in the beginning of the joining process in which one will see structural filaments 1 lying above matrix filaments 2,
  • Figure 6 is an imagined enlarged section through such a composite fibre band at the end of, or after, the joining process in which one may see structural filaments lying distributed between matrix filaments .
  • the figures 1 and 2 illustrate, in a side elevation view and in a vertical view, the invention with a set-up with a rack 16 with bobins 11, 12 with structural fibre bundles 9, and bobins 13, 14, 15 with matrix fibre bundles 10 separately being rolled off the bundles and rolled over broad rollers 122, 121, 213, 221, 222, 223 for structural fibres, and bobins 231, 232, 241, 242, 243, 244 until each on their own have been spread to broad flat bands which are joined in a process according to the invention to a broad band 8 of composite fibre.
  • Structural filament 1 contained in the at least one structural fibre bundle 9.
  • Rollers 211 to 223 shape the bundle 9 to a broader band 6 comprising spread structural fibres or fibre filaments 1.
  • Matrix filaments 2 are contained in a matrix fibre bundle 10.
  • the rollers 231 to 244 shape the bundle 10 to a broader band 7 . of spread matrix fibres or matrix filaments 2.
  • Fig. 3 is a side elevation view of the spread bands 6 and 7 running in on a collector roller 3 on which a composite band 8 is formed.
  • the collector roller 3 is included as a central element in the method of the invention and may also be called a collector or mixing station 3.
  • the collector roller joins the bands 6 and 7 to a composite fibre band 8, composed of structural fibres or structural filaments 1 and matrix fibres or matrix filaments 2.
  • band 6 with the structural fibres may be guided in from the outside of the band 7 containing matrix fibres because the structural fibres 1 often will be stiffer than the matrix fibres 2 and thus force themselves down between these due to the difference in stiffness.
  • a stabiliser 4 which is not strictly required, may be used for leading the spread- mixed composite fibre band 8 in onto a composite fibre bobin 5 for the produced composite fibre band 8, or the composite fibre band 8 may be lead directly into a process in which a composite product is built.
  • Fig. 4 is an imagined longitudinal section, early in the joining process, through such a composite fibre band 8, in which a flat surface 18 of the band 6 lye adjacent to a flat surface 19 of the band 7.
  • Fig. 5 is an enlarged section across a part of such a composite fibre band 8, here seen at the beginning of the joining process in which one may see structural filaments 1 lying side to side with matrix filaments 2.
  • Fig. 6 is an imagined enlarged section through a part of such a composite fibre band 8 in the end of or after the joining process in which one see structural filaments 1 lye distributed between matrix filaments 2. in the joined state the composite fibre band may be consolidated by a partial melting of the matrix filaments so that these have adhesive properties to the structural fibre filaments, or the band may be unconsolidated.
  • the structural fibre bundle 9 is delivered from the manufacturer as a bobin in which the structural fibre bundle is not spread.
  • the matrix fibre bundle 10 is delivered from the manufacturers side as non-spread on a matrix fibre bobin.
  • the manufacturer shall produce structural filaments 1 as a broad band wound up in crossed layers on a bobin by the production of the structural filaments, so that the in situ spreading of the bundle 9 is avoided when it shall be joined in the present process.
  • matrix fibre filaments 2 may be imagined provided as a broad band 7 on a bobin in order to avoid the step of spreading the bundle 10 to a broad band 7 before the collector roller 3.
  • the invention is thus a method to produce composite fibre having an improved distribution of non-melting structural fibres of carbon, boron or aramide, and matrix fibre filaments of thermoplastic, e.g. PET, PP, PCB and PEEK.
  • Particular to the method are the following steps: a) spreading of at least one bundle (9) of structural filaments (1) to at least one first broad band (6) having at least one flat surface (18) and having a thickness corresponding to one or a small number of structural filaments (1) , in which the spreading of the bundle (9) of structural fibres for generally parallel running and continuous structural filaments (1) ; b) spreading of at least one bundle (10) of matrix filaments (2) to at least one second broad band (7) having at least one flat surface (19) and having a thickness corresponding to one or a small number of matrix filaments (2) , in which the spreading of the bundle
  • matrix filaments (2) form generally parallel and continuously running matrix filaments (2) ; c) that one guide the first band (6) and the second band (7) in parallel and in the same direction; d) that one in this parallel position join or let run together the first band (6) with the at least one flat surface (18) against the second band's (7) at least one flat surface (19) to a composite band (8) , in which one lets the composite band (8) maintain a large width with respect to the thickness in the further winding or use of the composite band (8) .
  • the composite band (8) maintain a large width with respect to the thickness before it is wound up flat onto the bobin (5) .
  • the main purpose of the process only is to have an even distribution of the composite fibres (1,2) and desires to have a thick bundle having a round cross-section out of the process, it may be imagined to gather the band (8) again to a bundle, e.g. in the stabiliser 4 and guide for spread-mixed composite fibres.
  • the band is guided flat-lying in and onto the roller 5.
  • generally parallel running structural filaments (1) will be formed during spreading of the bundle (9) of structural fibres.
  • generally parallel running matrix filaments (2) will be formed during spreading of the bundle (10) of matrix filaments (2) .
  • the thickness of the structural filaments (1) and the matrix filaments (2) is preferably of the same order of size, and usually such that the structural filaments are somewhat more numerous and thinner than the fewer and melting matrix filaments, but this is not a prerequisite for the method to work.
  • at least one of the bands (6) with structural filaments (1) or the band (7) with matrix filaments (2) may be heated before the joining of the bands (6, 7) so that the bands adhere entirely or partly after the joining.
  • the band (7) having matrix filaments (2) may be supplied with heat so that it achieves partial melting or in other ways gets adhesion properties to the band ( ⁇ ) of structural filaments (1).
  • (1) bay be supplied with head to that it, on joining with the band (7) , transfers heat and partially melts the band (7) of matrix filaments (2) or in other way supplies adhesion properties before the structural filaments (1) .
  • the advantage in heating the band (6) of structural fibres is that this band is non-melting, and one will thus not run any risk that any of the bands are entirely or partially broken before the joining on the collector roller (3) . If heat is supplied to the band (7) of melting filaments (2) before the collector roller (3) , there is a risk that one or more of the filaments (2) are locally weakened and may break, which would disturb the process.
  • the bands (6, 7) of structural filaments (1) and with matrix filaments (2) may be charged with opposite signs of their charges so that the at least two bands (6, 7) attract each other during the joining to one composite fibre band (8) .
  • the bundle (9) of structural filaments (1) is without twist. This is entirely essential for avoid kinks in the structural filaments, particularly carbon filaments.
  • the bundle (10) of matrix filaments (2) should also be without twists, but this is less essential than the fact that the structural filaments should be without twisting, because the matrix filaments shall anyway be melted totally or partially in the end.
  • Sensors may be arranged to check if the bands (6, 7) have obtained the desired least width before the collector roller (3) .
  • the collector roller (3) there may be arranged rollers (not shown) to maintain the distribution and to obtain additional mixing of structural filaments (1) and matrix filaments (2) .
  • These rollers may contribute to better guiding of the band (8) in onto the composite fibre bobin (5) or to a larger bobin, or for guiding the band (8) into a desired process which utilizes such a composite band being better distributed internally.
  • the composite fibre band (8) may also be narrowed again to a bundle, then having strongly improved distribution of matrix filaments (2) and structural filaments (1) .
  • the filament diameter quotient between the structural fibre and the matrix fibre is included in the determination of numbers of bobins of different types.
  • the weight relationship between the fibres may be defined within narrow tolerances based on tex in each of the coils.
  • Carbpn fibre yarn which is spread or is pre-spread may in a preferred embodiment of the invention be guided through a plasma treatment in which original seizing is burned away, an by means of the plasma treatment replaced with thermoplastic molecules of e.g. the same kind as the carbon fibre later to be mixed with. This results in chemical bonding between carbon fibre and matrix fibre, which will result in a considerable increase of the strength of such composite fibres consolidated into final laminates.
  • composite fibres composed of structural fibres or filaments 1 and matrix fibres or -filaments 2.
  • rotating axle for holding bobin for composite fibre 5. rack for composite fibre bobins.
  • sixth roller main spreader unit for the structural fibres.
  • roller for guiding spread matrix fibres towards the collector roller 5.

Abstract

La présente invention concerne un procédé servant à produire des fibres composites ayant une répartition améliorée de fibres structurelles (par ex. filaments de carbone, bore, aramide ou analogue) et de fibres matricielles (par ex. filaments de thermoplastique). Le procédé de l'invention se caractérise par les étapes suivantes: a) diffusion d'au moins un faisceau (9) de filaments structurels (1) pour former au moins une large bande (6) ayant au moins une surface plane (18) et ayant une épaisseur correspondant à un ou à un nombre limité de filaments structurels (1); b) diffusion d'au moins un faisceau (10) de filaments matriciels (2) pour former au moins une seconde large bande (7) ayant au moins une surface plane (19) et ayant une épaisseur correspondant à un ou à un nombre limité de filaments matriciels (2); c) guidage local de la première bande (6) et de la seconde bande (7) en parallèle et dans la même direction; d) jonction en position parallèle ou déplacement simultané de la première bande (6) présentant au moins une surface plane (18) de manière adjacente à la/aux surface(s) plane(s) (19) de la seconde bande (7) pour former une bande composite (8).
PCT/NO2002/000125 2001-03-27 2002-03-26 Fibre composite melangee et diffusee WO2002081790A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP02713326A EP1383946A1 (fr) 2001-03-27 2002-03-26 Fibre composite melangee et diffusee

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
NO2001.1568 2001-03-27
NO20011568A NO316324B1 (no) 2001-03-27 2001-03-27 Spredemikset komposittfiber

Publications (1)

Publication Number Publication Date
WO2002081790A1 true WO2002081790A1 (fr) 2002-10-17

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Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/NO2002/000125 WO2002081790A1 (fr) 2001-03-27 2002-03-26 Fibre composite melangee et diffusee

Country Status (3)

Country Link
EP (1) EP1383946A1 (fr)
NO (1) NO316324B1 (fr)
WO (1) WO2002081790A1 (fr)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2338667A4 (fr) * 2008-10-22 2016-11-30 Lg Hausys Ltd Procede de production de complexe hybride fibreux thermoplastique/continue
EP2152454B2 (fr) † 2007-06-08 2017-02-22 G. Angeloni S.r.l. Renforcement fibreux, tel qu'un renforcement pour matériau composite
CN109385083A (zh) * 2018-10-19 2019-02-26 江苏苏能新材料科技有限公司 连续玄武岩纤维增强聚酰胺单向预浸带及其制备方法
CN109467809A (zh) * 2018-10-19 2019-03-15 江苏苏能新材料科技有限公司 连续玻璃纤维增强聚丙烯单向预浸带及其制备方法
CN109485999A (zh) * 2018-10-19 2019-03-19 江苏苏能新材料科技有限公司 连续凯芙拉纤维增强聚丙烯单向预浸带及其制备方法
EP3738753A1 (fr) * 2019-05-14 2020-11-18 Cetex Institut gGmbH Procédé de fabrication d'un faisceau de fibres hybrides, faisceau de fibres hybrides et dispositif de fabrication d'un faisceau de fibres hybrides

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106987914A (zh) * 2017-04-21 2017-07-28 常熟涤纶有限公司 一种高网络免浆丝的加工工艺

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2106484A (en) * 1981-06-19 1983-04-13 John Maurice Curry Carbon fibres
US5454846A (en) * 1992-11-19 1995-10-03 Vetrotex France S.A. Process and device for making up a composite thread
US6004650A (en) * 1996-12-31 1999-12-21 Owens Corning Fiberglas Technology, Inc. Fiber reinforced composite part and method of making same

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2106484A (en) * 1981-06-19 1983-04-13 John Maurice Curry Carbon fibres
US5454846A (en) * 1992-11-19 1995-10-03 Vetrotex France S.A. Process and device for making up a composite thread
US6004650A (en) * 1996-12-31 1999-12-21 Owens Corning Fiberglas Technology, Inc. Fiber reinforced composite part and method of making same

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2152454B2 (fr) † 2007-06-08 2017-02-22 G. Angeloni S.r.l. Renforcement fibreux, tel qu'un renforcement pour matériau composite
EP2338667A4 (fr) * 2008-10-22 2016-11-30 Lg Hausys Ltd Procede de production de complexe hybride fibreux thermoplastique/continue
CN109385083A (zh) * 2018-10-19 2019-02-26 江苏苏能新材料科技有限公司 连续玄武岩纤维增强聚酰胺单向预浸带及其制备方法
CN109467809A (zh) * 2018-10-19 2019-03-15 江苏苏能新材料科技有限公司 连续玻璃纤维增强聚丙烯单向预浸带及其制备方法
CN109485999A (zh) * 2018-10-19 2019-03-19 江苏苏能新材料科技有限公司 连续凯芙拉纤维增强聚丙烯单向预浸带及其制备方法
CN109485999B (zh) * 2018-10-19 2021-08-03 江苏苏能新材料科技有限公司 连续凯芙拉纤维增强聚丙烯单向预浸带及其制备方法
CN109467809B (zh) * 2018-10-19 2021-08-03 江苏苏能新材料科技有限公司 连续玻璃纤维增强聚丙烯单向预浸带及其制备方法
CN109385083B (zh) * 2018-10-19 2021-08-31 江苏苏能新材料科技有限公司 连续玄武岩纤维增强聚酰胺单向预浸带及其制备方法
EP3738753A1 (fr) * 2019-05-14 2020-11-18 Cetex Institut gGmbH Procédé de fabrication d'un faisceau de fibres hybrides, faisceau de fibres hybrides et dispositif de fabrication d'un faisceau de fibres hybrides

Also Published As

Publication number Publication date
NO316324B1 (no) 2004-01-12
NO20011568D0 (no) 2001-03-27
EP1383946A1 (fr) 2004-01-28
NO20011568L (no) 2002-09-30

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