WO2013026801A1 - Procédé de production d'un élément structural en un matériau composite fibreux préimprégné, élément structural ainsi produit, et moule d'assemblage - Google Patents

Procédé de production d'un élément structural en un matériau composite fibreux préimprégné, élément structural ainsi produit, et moule d'assemblage Download PDF

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Publication number
WO2013026801A1
WO2013026801A1 PCT/EP2012/066131 EP2012066131W WO2013026801A1 WO 2013026801 A1 WO2013026801 A1 WO 2013026801A1 EP 2012066131 W EP2012066131 W EP 2012066131W WO 2013026801 A1 WO2013026801 A1 WO 2013026801A1
Authority
WO
WIPO (PCT)
Prior art keywords
components
component
mold
joining
prepreg
Prior art date
Application number
PCT/EP2012/066131
Other languages
German (de)
English (en)
Inventor
Gerald Possarnig
Original Assignee
C6 Gmbh
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 C6 Gmbh filed Critical C6 Gmbh
Priority to EP12753927.8A priority Critical patent/EP2744642A1/fr
Publication of WO2013026801A1 publication Critical patent/WO2013026801A1/fr

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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
    • B29C70/44—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
    • B29C70/446—Moulding structures having an axis of symmetry or at least one channel, e.g. tubular structures, frames

Definitions

  • the invention relates to a method for producing a component from hollow, semi-hollow, shell-shaped or U-shaped and similar components made of preimpregnated fiber composite material (prepreg), which is shaped and cured by means of at least one inserted sealing membrane in a mold under pressure and heat become.
  • prepreg preimpregnated fiber composite material
  • Continuous fiber-reinforced flat semi-finished products made from carbon fibers or other high-strength fibers with plastics as matrix material to form layered composite materials.
  • the largest possible proportion of the component should be formed from fibers, as these have the load-bearing function, wherein the fibers should be aligned in the direction of the load on the components. According to the state of the art, these requirements are met by the best method in which the flat semi-finished fiber products are formed by layering (lamination).
  • dry semifinished fiber products are deposited on a preform, wherein the individual layers are fixed by textile processing, such as sewing, braiding or weaving, or by a superficial application of a binder to a so-called preform, so that a transfer of the molded
  • Layer structure of the preform in the mold is possible.
  • the cavities between the reinforcing fibers are filled in the mold with a suitable liquid plastic, hereinafter solidified by crosslinking or cooling, wherein a solid composite material is formed from fibers and plastic.
  • prepregs Semi-finished fiber products in suitable molds. In most cases, prepregs with a sticky surface are used to ensure adhesion of the individual layers to one another. Separate process steps for fixing the
  • From DE 198 13 104 AI discloses a process for the production of fiber composite components located in an evacuable vacuum film, fibers comprising preform and a matrix material, wherein between the vacuum film and the fiber composite component to be produced, a porous membrane is introduced, whose pores are dimensioned such that Air can escape unhindered and the liquid matrix material is retained.
  • the preform is either as semi-finished fiber and the
  • Matrix material in liquid form or as semi-finished fiber and the matrix material used as a film or as preimpregnated with matrix material semifinished fiber products are provided.
  • Cold-formed fiber reinforcement layer is heated and the reshaped binder-provided fiber reinforcement layer is heated and then cooled.
  • prepregs Semi-finished fiber products, so-called prepregs, customary either to deposit preformed components directly in the mold, or to drape prepreg blanks directly into or onto the mold.
  • the storage of preformed components or the draping of blanks from prepreg is possible only in cooled molds, so it is necessary to the mold after each of a previous
  • Cure cooling process to complete the next component can. It is therefore also necessary to then reheat the mold.
  • the consolidation and curing process requires a mold temperature of up to 200 ° C for crosslinking matrix resins, and for thermoplastic resins up to 400 ° C, so energy consumption can be significant.
  • the component must be subjected to hydrostatic pressure and, if necessary, kept under vacuum.
  • the mold must therefore be designed so that it
  • the sealing membrane which is located on the formabgewandeten surface of the component, by air, steam, hot water, oil or the like subjected to hydrostatic pressure and at the same time the mold is heated to accelerate the consolidation and networking or perform.
  • the mold therefore needs after the end of a
  • the mold is immediately after the end of a curing process again for the production of the next component to
  • the method according to the invention uses a joining mold which
  • the joining mold is in two parts with a
  • a two-part joining form is especially advantageous for creating or joining hollow components or molded parts.
  • the sealing membrane (s) is / are already inserted into the components during preforming of the components, in particular in the case of hollow body-shaped components.
  • the components can be preformed from blanks of gelatinous prepreg.
  • the blanks of the prepreg after removal of the release films, which prevent sticking of the prepreg during storage on rollers, formed in a known manner, for example by draping, winding around a mandrel, stacking and the like to component components.
  • the components can also be preformed from blanks of dry prepreg and under the action of heat. Both when producing preformed components and when draping blanks in the mold, the components can be made from one or more layers of prepreg.
  • the method according to the invention therefore permits the production of components and components designed in many different ways.
  • Overlap shock areas As a result, the components are joined together to form the component.
  • the overlap is sufficient to easily transfer the component from the joining form into the molding tool.
  • Components made of dry prepreg can additionally be glued together at the overlapping areas.
  • components which are closed on the outside can be produced in such a way that, after the positioning of the sealing membrane, they are deposited on the joining form, open at the top and, for example, U-shaped in cross section
  • Components each have a further component with, for example, also U-shaped, semi-hollow or similar cross-section is positioned so that closed hollow components are formed.
  • components of overlapped wound prepreg can be preformed into hollow bodies.
  • the sealing membrane is inventively designed so that they
  • the invention further relates to a component which is produced by the method according to the invention and further a joining mold for assembling or draping preformed in cross-section hollow, semi-hollow, shell or U-shaped and the like components of a component of pre-impregnated fiber composite material, with recesses whose Inner contours correspond to at least portions of the outer contours of the components.
  • FIG. 1 shows a flow chart for the sequence of the method according to the invention.
  • 3 is a plan view of the joining mold with positioned component components
  • FIG. 4 is a section along the line AA of Fig. 3
  • FIGS. 5 to 7 are sectional views similar to FIG. 4 with further embodiments of the invention
  • FIG. 8 is a sectional view of a molding tool with an inserted component according to FIGS. 7 and
  • FIG. 9 shows a view of a two-part joining mold with component transfer into a molding tool.
  • the method according to the invention is suitable for producing components which are hollow, semi-hollow, U-shaped, cup-shaped and the like in cross-section
  • Components can be joined together.
  • step 1 illustrates the sequence of a preferred embodiment of the method according to the invention for the production of components from preimpregnated fiber composite material.
  • the prepreg is first of all
  • Fiber composite material usually called prepreg formed.
  • the fiber composite material consists of one layer or several layers of fiber fabric or fiber fabric and is preimpregnated with a matrix resin.
  • the fiber fabric or fiber fabric may be made
  • Glass fibers carbon fibers, synthetic fibers, natural fibers, hybrid fibers or
  • the matrix resin used for the impregnation may be solid, liquid or gel-like tacky and is an incompletely crosslinked duroplastic or a thermoplastic. Resins based on epoxides, vinyl esters, unsaturated polyesters, phenols, polyurethanes or cyanate esters are predominantly used.
  • the prepreg is thus a flat semifinished product made of reinforcing fibers and a sufficient amount of matrix resin for consolidation and curing and is provided in the form of webs, wound on rolls.
  • the matrix resin in the prepreg in liquid or gel-like sticky form before, from blanks of the prepreg, after removing the release films, which prevent sticking of the prepreg during storage on rollers, now in a known manner, for example by draping, winding around a mandrel , Stacking and the like component components are manufactured. Lies the matrix resin in an alternative embodiment of prepregs in solid form, blanks are softened from the prepreg by the action of heat such that a deformation of the sheet semifinished by bending, edge or deep drawing can take place to preformed components of the component to be produced. In either case, the blanks of the prepregs are made to have corresponding contours and the desired fiber orientation. These manufacturing capabilities of component components (step 2 in FIG. 1) are optional.
  • FIG. 2 shows, by way of example, a plurality of differently preformed components 12a to 12e which, when joined together, produce the component to be produced.
  • the preformed components 12a to 12e which consist of one or more layers of prepreg, are positioned in a joining mold 10.
  • the joining mold 10 has mold cavities whose inner contours are executed at least largely in accordance with the outer contours of the preformed components 12a to 12e.
  • the components 12a to 12e which have a U-shaped cross section or substantially in each case, form a component which has a substantially rectangular frame and a connecting part which consists of the component 12e which comprises the two
  • Components 12a and 12c connects.
  • the components 12a and 12c are with
  • All components 12a to 12e and the depressions in the joining mold 10 are adapted to one another such that the components 12a to 12e positioned in the joining form 10 can be joined together overlapping one another at their edge sections or join one another and jointly form the component.
  • the components are produced in such a way that in the joining form 10 they are the mutual ones
  • Overlap areas can form. If the tackiness of the prepreg material is insufficient to give the component the necessary stability for the subsequent transfer of the joining form 10 into the molding tool, adhesive materials in paste or film form can additionally be used. According to an alternative embodiment of the invention, in which no preforming (step 2 in FIG. 1) takes place, corresponding blanks made of prepreg are draped in one or more layers in the joining form 10 and therefore joined together when being inserted into the component.
  • the joining mold 10 is made of a material that allows easy removal of the
  • Components 12a to 12e allows, for example, plastic or aluminum.
  • the insides of the wells may be appropriately coated or treated.
  • an embodiment of the insides with ribs is also possible.
  • a flexible sealing membrane 15 is inserted into the positioned (or alternatively draped) component components 12a to 12e.
  • the sealing membrane 15 is an elongated, hose-like executed bellows made of elastic plastic or elastomer with a closed end 15 a.
  • any embodiment of the sealing membrane 15 is conceivable, which results in one or more closed chambers and which allows the formabgewandten surface of the component with a hydrostatic pressure, the sealing membrane 15 is dimensioned and designed such that they
  • the sealing membrane 15 is led out of the joining mold 10 at a cut-out 10b at the edge of the joining mold 10.
  • Sealing membrane 15 are continuously inserted into all components 12a to 12e. 4 shows, in section, the component 12b positioned in the joining mold 10 with the sealing membrane 15 inserted.
  • FIG. 5 15 additional preformed components can be positioned on the inserted components after inserting the sealing membrane.
  • a component 16a which preformed in cross-section U-shaped component 12b covers, so that a component with a closed, in FIG. 5 by way of example approximately rectangular cross section is produced.
  • FIG. 6 shows a further embodiment variant of a component component 17a in cross-section of the joining form 10 with a component component 17 already preformed in closed form.
  • the component 17 is, for example, a hollow part which is approximately rectangular in cross-section and which consists of one or more prepreg layers (n) with overlapping ones Edge sections 17a preformed by winding over a mandrel or the like and then inserted into the joining mold 10. Inside the component 17 is the introduced
  • sealing diaphragm 15 shown in section.
  • the sealing diaphragm 15 is preferably already positioned in step 2, during the formation of the component 17, or subsequently introduced into the component 17 as an elongated "bag” closed at its one end.
  • Fig. 7 shows in cross section a component component 18 as a combination of in
  • the actual design of the component to be produced determines the design and number of its individual components, taking care that the joining mold 10 can be carried out accordingly.
  • the component components are transferred as a whole or in parts from the joining mold 10 into the mold which is designed in a conventional manner. in the
  • Forming tool is the consolidation of the component by inserting a
  • Fig. 8 shows schematically a section through a closed mold with upper mold part 19 and lower mold part 20 with a trained in this Mold cavity for receiving the joined in the mold 10 component. Shown is a component 18 according to FIG. 7.
  • FIG. 9 further shows the component 21 joined in the joining form 11, which is a hollow body with several sections, analogous to the embodiment shown in FIGS. 2 and 3. Also visible is the pressure port 15b of the introduced, not visible here sealing membrane 15.
  • Fig. 9 is also a
  • the molding tool which may also have more than two parts, at least substantially coincide with the joining mold 11.
  • the two arrows in Fig. 9 illustrate the transfer of the joined component 21 of the joining mold 11 in the
  • the inventive method makes it possible to keep the time in which the mold is used for the production or curing of the component very short.
  • the mold does not need to be cooled or only slightly cooled after the end of the curing process to remove the finished component.
  • the component components or blanks already assembled in the joining form can be transferred together with the sealing membrane (s) into the molding tool without this being cooled down.
  • the invention therefore allows the mold after the end of a
  • Forming tool can be omitted.
  • the joining forms can already have a
  • Forming tool for the curing process is in use. It is therefore also the required Energy use compared to the known methods much lower, since an intermediate temperature of the mold requires a much lower energy consumption than cooling with subsequent heating.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Composite Materials (AREA)
  • Mechanical Engineering (AREA)
  • Moulding By Coating Moulds (AREA)
  • Casting Or Compression Moulding Of Plastics Or The Like (AREA)

Abstract

L'invention concerne un procédé de production d'un élément structural en un matériau composite fibreux préimprégné (Prepeg) formé de composants, de section en creux, semi-creux, en forme de coque ou en U, et analogues (12a à 12e, 16, 17, 18) qui sont moulés, et qui sont durcis dans un outil de formage, sous l'effet de la chaleur et de la pression, et au moyen d'au moins une membrane d'étanchéité (15) souple, insérée. Sur un moule d'assemblage (10, 11), soit les composants déjà préformés (12a à 12e, 16, 17, 18) de l'élément structural sont déposés, soit les pièces découpées du préimprégné sont moulées en composants, les composants (12a à 12e, 16, 17, 18) étant prélevés du moule d'assemblage (10, 11), avec la/les membrane(s) d'étanchéité insérée(s) (15), et étant transférés dans l'outil de formage.
PCT/EP2012/066131 2011-08-19 2012-08-17 Procédé de production d'un élément structural en un matériau composite fibreux préimprégné, élément structural ainsi produit, et moule d'assemblage WO2013026801A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP12753927.8A EP2744642A1 (fr) 2011-08-19 2012-08-17 Procédé de production d'un élément structural en un matériau composite fibreux préimprégné, élément structural ainsi produit, et moule d'assemblage

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
ATA1199/2011 2011-08-19
ATA1199/2011A AT511885B1 (de) 2011-08-19 2011-08-19 Verfahren zur herstellung eines bauteils aus einem vorimprägnierten verbundmaterial, derart hergestelltes bauteil und legeform

Publications (1)

Publication Number Publication Date
WO2013026801A1 true WO2013026801A1 (fr) 2013-02-28

Family

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PCT/EP2012/066131 WO2013026801A1 (fr) 2011-08-19 2012-08-17 Procédé de production d'un élément structural en un matériau composite fibreux préimprégné, élément structural ainsi produit, et moule d'assemblage

Country Status (3)

Country Link
EP (1) EP2744642A1 (fr)
AT (1) AT511885B1 (fr)
WO (1) WO2013026801A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102017100621A1 (de) 2017-01-13 2018-07-19 Teufelberger Ges.M.B.H. Formstück

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19813104A1 (de) 1998-03-25 1999-09-30 Daimler Chrysler Ag Verfahren zur Herstellung von Faserverbundbauteilen
DE60102741T2 (de) 2000-06-10 2004-08-19 Westland Helicopters Ltd., Yeovil Membran-Vakuumformen eines schichtweisen Faserverbundteils
US20070092379A1 (en) * 2005-10-21 2007-04-26 Snecma Method of manufacturing a composite turbomachine blade, and a blade obtained by the method
US20100092707A1 (en) * 2004-02-10 2010-04-15 Eurocopter Deutschland Gmbh Method for manufacturing a hollow fibre composite component and intermediate products for the manufacture
DE102009044834A1 (de) 2009-12-09 2011-06-16 Saertex Gmbh & Co. Kg Verfahren zur Herstellung eines Vorformlings für ein Faserverbundbauteil

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4415509A1 (de) * 1994-05-03 1995-11-09 Joachim Josef Nolte Hockeyschläger und Verfahren zum Herstellen eines Hockeyschlägers
CN2664891Y (zh) * 2003-11-26 2004-12-22 山河森实业股份有限公司 一种中空体状开放式或半封闭式的杆棒管体或罩壳体
FR2928294B1 (fr) * 2008-03-07 2016-12-30 Duqueine Rhone Alpes Procede et dispositif de realisation d'un profil courbe en materiau composite,et profil correspondant.

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19813104A1 (de) 1998-03-25 1999-09-30 Daimler Chrysler Ag Verfahren zur Herstellung von Faserverbundbauteilen
DE60102741T2 (de) 2000-06-10 2004-08-19 Westland Helicopters Ltd., Yeovil Membran-Vakuumformen eines schichtweisen Faserverbundteils
US20100092707A1 (en) * 2004-02-10 2010-04-15 Eurocopter Deutschland Gmbh Method for manufacturing a hollow fibre composite component and intermediate products for the manufacture
US20070092379A1 (en) * 2005-10-21 2007-04-26 Snecma Method of manufacturing a composite turbomachine blade, and a blade obtained by the method
DE102009044834A1 (de) 2009-12-09 2011-06-16 Saertex Gmbh & Co. Kg Verfahren zur Herstellung eines Vorformlings für ein Faserverbundbauteil

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102017100621A1 (de) 2017-01-13 2018-07-19 Teufelberger Ges.M.B.H. Formstück
WO2018130640A1 (fr) 2017-01-13 2018-07-19 Teufelberger Ges.M.B.H. Pièce moulée

Also Published As

Publication number Publication date
AT511885B1 (de) 2015-05-15
AT511885A2 (de) 2013-03-15
EP2744642A1 (fr) 2014-06-25
AT511885A3 (de) 2015-03-15

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