WO2014121992A1 - Procédé de fabrication d'un composant en matière plastique renforcée de fibres - Google Patents

Procédé de fabrication d'un composant en matière plastique renforcée de fibres Download PDF

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Publication number
WO2014121992A1
WO2014121992A1 PCT/EP2014/050756 EP2014050756W WO2014121992A1 WO 2014121992 A1 WO2014121992 A1 WO 2014121992A1 EP 2014050756 W EP2014050756 W EP 2014050756W WO 2014121992 A1 WO2014121992 A1 WO 2014121992A1
Authority
WO
WIPO (PCT)
Prior art keywords
fiber
fiber layer
insert element
reinforced plastic
cavity
Prior art date
Application number
PCT/EP2014/050756
Other languages
German (de)
English (en)
Inventor
Jan Pfrang
Roman Sternagel
Original Assignee
Bayerische Motoren Werke Aktiengesellschaft
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 Bayerische Motoren Werke Aktiengesellschaft filed Critical Bayerische Motoren Werke Aktiengesellschaft
Publication of WO2014121992A1 publication Critical patent/WO2014121992A1/fr

Links

Classifications

    • 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
    • B29C70/48—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 and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM], e.g. by vacuum
    • 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
    • B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
    • B29C70/545—Perforating, cutting or machining during or after moulding
    • 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
    • B29C2793/00—Shaping techniques involving a cutting or machining operation
    • B29C2793/0045—Perforating

Definitions

  • the invention relates to a method for producing a fiber-reinforced plastic component with a matrix of thermoplastic or
  • thermosetting plastic are arranged in the fibers as reinforcement.
  • detachable fastening means such as screws, dowels, nails or rivets, with which fiber-reinforced plastic components can be connected to one another. From the DE
  • thermoplastic fiber composite components by means of pin-shaped functional elements.
  • the outer surface is heated at the point at which a serving for fastening purposes pin is to be introduced into the component.
  • thermoplastic matrix By heating the thermoplastic matrix, the underlying fibers in the matrix are movable and can be displaced by the penetrating pin.
  • Dodging of the fibers upon penetration of the functional element results in very little damage to the fiber composite structure.
  • the invention proposes a method for producing a fiber-reinforced plastic component, with the steps:
  • the insert element By arranging the insert element in the fiber layer, a local reorientation of the fibers can be achieved before completion of the fiber composite component, wherein the effect is exploited that the individual fibers are movable in the fiber layer.
  • the fibers In the initial state of the fiber layer, the fibers are arranged in the fiber layer, so that the fiber layer is present as a unidirectional fiber layer, as a scrim, mesh or fabric.
  • the fibers may also be arranged non-directionally in the fiber layer, so that the fiber layer is present as a nonwoven or as a random fiber mat.
  • the insert element When inserted into the fiber layer, the insert element displaces the individual fibers and thus acts as a placeholder for a connecting element to be subsequently inserted.
  • the insert element can be removed from the fiber-reinforced plastic component.
  • a recess can be produced in a simple manner in the finished fiber composite component.
  • the insert element may be formed like a mandrel, a rod or a rod and may have a circular, oval, triangular or polygonal cross-sectional shape.
  • the outer shape as a mandrel, Strft or rod has the advantage that due to the tapered end of the insert element can be particularly easily introduced between the fibers of the fiber layers.
  • the cross-sectional shape can advantageously be chosen so that it is adapted to a later connecting element, such as a screw. If insert elements are used whose cross-sectional shape is not circular, then
  • Connecting elements are selected, with the same cross-sectional shape so that the connecting elements have no rotational degrees of freedom with respect to their longitudinal axis relative to the fiber composite components to be connected.
  • the insert element may be formed as a bushing and remain after the lapse of a predetermined period of time after the infiltration of the at least one fiber layer in the fiber-reinforced plastic component.
  • a connection element such as a socket, a circular Has cross section with an inner opening, is positioned in the component. After completion of the fiber composite part screws, bolts or pins can be pushed through the socket for connecting the component with other fiber composite components.
  • thermoplastic material can be used as the matrix material, which at least partially solidifies after the lapse of the predetermined period of time or as a matrix material, a thermosetting plastic is used, which cures after the lapse of the predetermined period of time at least partially.
  • the fiber material used is in particular carbon fibers, glass fibers, aramid, basalt or a combination of these fibers.
  • the insert element can already be used in the RTM (Resin Transfer Molding) method placeholder in the fiber layer or in a plurality of fiber layers are introduced, which are removed after curing of the matrix. This can be dispensed with a subsequent machining, for example drilling, for example. During drilling, the fiber layers are usually severed and thus the mechanical properties of the component weakened.
  • the invention offers the advantage that the fiber layers or the individual fibers are not interrupted and thereby components can be achieved with high mechanical properties.
  • the fibers are displaced laterally during insertion of the insert element. As a result, in the edge regions immediately adjacent to the insert element
  • the displacement of the fiber has the advantage that the fibers are not interrupted and that at the same time in the edge region of the later recess or bore displaced fibers displace the soft material material.
  • This local increase in the fiber volume content produces a lower settling behavior, if in the region of the recess Rere fiber composite components screwed together or by equivalent non-positive fasteners, such as rivets, are connected.
  • the loss of clamping force is reduced by the flow of the matrix material and ensures a good connection of the components.
  • Increasing the mechanical characteristics of the component connection also improves the reliability of such a screw connection.
  • FIG. 1 shows a fiber layer as semi-finished product
  • Figure 2 shows a later state of the fiber layer as a semi-finished product with insert element arranged therein
  • Fiber composite components 13 are produced in a so-called resin transfer molding process, in which one or more fiber layers 10 are superimposed and introduced into a cavity of an RTM tool. Subsequently, the cavity of the tool is flooded with a liquid resin, wherein the resin infiltrates the fiber layers 10 and also wets individual fibers 11. After a sufficient degree of infiltration is ensured, a predetermined period of time is waited in which the matrix of the fiber composite component 13 its almost final shape takes on by solidifying or hardening. In this state, the cavity of the tool can be opened and the fiber composite component 13 are removed.
  • a fiber layer 10 is formed as a semi-finished product, wherein the fiber are aligned in a grid-like arrangement to each other.
  • This homogeneous structure (mesh, scrim, fabric) or inhomogeneous structure (fleece, random orientation) is changed by introducing the insertion element 12, wherein locally at the point where the insert element 12, the fiber layer 10 pierces the individual fibers are deflected.
  • the insert element 12 can be introduced into the fiber layer 10 before the fiber layer 10 is inserted into the cavity of the RTM tool or after the fiber layer has been introduced into the RTM tool.
  • one or more fiber layers 10 are first introduced into the cavity of the RTM tool and then the insert element 12 is pushed between the fibers. In this case, the insert element 12 is still in touching contact with the fiber composite component 13. Since the matrix is now dimensionally stable, the insert element 12 can be removed.
  • FIG. 2 shows schematically a fiber layer 10 with insert element 12 inserted therein
  • Insertion element 12 the fibers 11 are displaced without being interrupted. After completion of the fiber composite component and the removal of the insert element 12 remains in the fiber composite component a recess 14, as shown in Figure 3.
  • this recess is shown by way of example and not by way of limitation for the invention as a through hole 14 with a circular cross section.
  • the cross-sectional shape of the recess or the through-hole can be varied by using insert elements 12, which have a corresponding outer cross-sectional shape. Connecting elements, in particular screws, bolts, rivets or pins, can then be carried through these through holes in order to connect the fiber composite component to a further component, for example a further fiber composite component or even a component made of a different material.

Abstract

L'invention concerne un procédé de fabrication d'un composant (13) en matière plastique renforcée de fibres, comprenant les étapes suivantes : mise en place d'un élément d'insertion (12) dans au moins une couche de fibres (10), les fibres de renfort (11) de la couche de fibres (10) étant localement refoulées par l'élément d'insertion (12) ; alignement de la ou des couches de fibres (10) dans une empreinte ouverte d'un outil ; fermeture de l'empreinte de l'outil ; et infiltration d'un matériau matrice dans les couches de fibres (10) qui se trouvent dans l'empreinte.
PCT/EP2014/050756 2013-02-07 2014-01-16 Procédé de fabrication d'un composant en matière plastique renforcée de fibres WO2014121992A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102013201963.7 2013-02-07
DE102013201963.7A DE102013201963A1 (de) 2013-02-07 2013-02-07 Verfahren zur Herstellung eines faserverstärkten Kunststoffbauteils

Publications (1)

Publication Number Publication Date
WO2014121992A1 true WO2014121992A1 (fr) 2014-08-14

Family

ID=49998263

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2014/050756 WO2014121992A1 (fr) 2013-02-07 2014-01-16 Procédé de fabrication d'un composant en matière plastique renforcée de fibres

Country Status (2)

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DE (1) DE102013201963A1 (fr)
WO (1) WO2014121992A1 (fr)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102015201350A1 (de) * 2015-01-27 2016-07-28 Bayerische Motoren Werke Aktiengesellschaft Zurückhaltekörper, Verfahren zur Herstellung eines Faserverbundbauteils und Faserverbundteil
DE102016218896A1 (de) * 2016-09-29 2018-03-29 Technische Universität Dresden Verfahren und Vorrichtung zur Vorlocheinbringung für die Verbindung von Faserkunststoffverbunden untereinander und mit anderen Werkstoffen
DE102018105246B4 (de) 2017-04-25 2024-02-15 Deutsches Zentrum für Luft- und Raumfahrt e.V. Verfahren zur Herstellung eines verstärkten Faserverbundwerkstoffs, Faserverbundwerkstoff und Luft- oder Raumfahrzeug
DE102017111146B4 (de) * 2017-05-22 2020-06-18 Lisa Dräxlmaier GmbH Verfahren zum herstellen eines faserformteils mit integrierter verbindungsbuchse
FR3068912B1 (fr) * 2017-07-11 2019-08-23 Faurecia Automotive Industrie Procede de fabrication d'une piece d'equipement de vehicule automobile et piece d'equipement associee
DE102018102492A1 (de) * 2018-02-05 2019-08-08 Deutsches Zentrum für Luft- und Raumfahrt e.V. Verfahren zur Herstellung eines hybridlaminarisierten Flügelkörpers
DE102018106335B4 (de) * 2018-03-19 2021-08-12 Dr. Ing. H.C. F. Porsche Aktiengesellschaft Verfahren für die Herstellung eines Verbundbauteils aus Faserverbundmaterial und einem Metallbauteil für ein Fahrzeug sowie Verschlusseinsatz
US20240100793A1 (en) * 2022-09-28 2024-03-28 The Boeing Company Countersinks in thin gauge thermoplastic skins

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0089755A2 (fr) * 1982-03-11 1983-09-28 WESTLAND plc Méthode de perforation d'articles en fibres renforcées comme des pales d'hélicoptère
GB2239835A (en) * 1990-01-11 1991-07-17 Bp Chem Int Ltd Method for manufacturing composite material
US20030017053A1 (en) * 2001-07-18 2003-01-23 Baldwin Jack Wilbur Method for making a fiber reinforced composite article and product
EP2302166A2 (fr) * 2009-09-24 2011-03-30 Rolls-Royce plc Composant hybride metal-composite

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE458075C (de) * 1924-09-27 1928-03-29 Kirchbach Sche Werke Kirchbach Verfahren zum Lochen von aus impraegniertem Gewebe bestehenden Reibungskoerpern fuer Kupplungs- und Bremszwecke
JPS62264896A (ja) * 1986-05-12 1987-11-17 町田　輝史 接合穴を有する繊維強化複合材の製造方法
DE102009056580A1 (de) 2009-11-23 2011-05-26 Technische Universität Dresden Verfahren und Vorrichtung zum Verbinden von thermoplastischen Faserverbundbauteilen mittels stiftförmiger Funktionselemente
US8303751B2 (en) * 2010-08-30 2012-11-06 GM Global Technology Operations LLC Method for integral vent screen in molded panels
DE102011001522B4 (de) 2011-03-24 2015-03-19 Technische Universität Chemnitz Verbindungselement zur Herstellung einer Verbindung zwischen wenigstens zwei sich überlappenden Bauteilen und Verfahren zur Herstellung dieser Verbindung
DE102011107209A1 (de) * 2011-07-13 2013-01-17 Daimler Ag Faserverstärktes Kunststoffbauteil, Faser-Matrix-Halbzeug und Verfahren zu deren Herstellung

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0089755A2 (fr) * 1982-03-11 1983-09-28 WESTLAND plc Méthode de perforation d'articles en fibres renforcées comme des pales d'hélicoptère
GB2239835A (en) * 1990-01-11 1991-07-17 Bp Chem Int Ltd Method for manufacturing composite material
US20030017053A1 (en) * 2001-07-18 2003-01-23 Baldwin Jack Wilbur Method for making a fiber reinforced composite article and product
EP2302166A2 (fr) * 2009-09-24 2011-03-30 Rolls-Royce plc Composant hybride metal-composite

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Publication number Publication date
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