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WO2009033559A1 - Procédé de production d'élément composite renforcé par fibres - Google Patents

Procédé de production d'élément composite renforcé par fibres Download PDF

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Publication number
WO2009033559A1
WO2009033559A1 PCT/EP2008/006935 EP2008006935W WO2009033559A1 WO 2009033559 A1 WO2009033559 A1 WO 2009033559A1 EP 2008006935 W EP2008006935 W EP 2008006935W WO 2009033559 A1 WO2009033559 A1 WO 2009033559A1
Authority
WO
WIPO (PCT)
Prior art keywords
fiber
nonwoven
material layers
layers
fiber composite
Prior art date
Legal status (The legal status 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 status listed.)
Ceased
Application number
PCT/EP2008/006935
Other languages
German (de)
English (en)
Inventor
Christoph Breu
Andreas Gessler
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Airbus Defence and Space GmbH
Original Assignee
EADS Deutschland 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 EADS Deutschland GmbH filed Critical EADS Deutschland GmbH
Publication of WO2009033559A1 publication Critical patent/WO2009033559A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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
    • B29C70/68—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks
    • B29C70/86—Incorporated in coherent impregnated reinforcing layers, e.g. by winding
    • B29C70/865—Incorporated in coherent impregnated reinforcing layers, e.g. by winding completely encapsulated
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
    • B29D99/00—Subject matter not provided for in other groups of this subclass
    • B29D99/0003—Producing profiled members, e.g. beams
    • B29D99/0005—Producing noodles, i.e. composite gap fillers, characterised by their construction
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
    • B29D99/00—Subject matter not provided for in other groups of this subclass
    • B29D99/001—Producing wall or panel-like structures, e.g. for hulls, fuselages, or buildings
    • B29D99/0014—Producing wall or panel-like structures, e.g. for hulls, fuselages, or buildings provided with ridges or ribs, e.g. joined ribs
    • 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
    • B29C70/12—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of short length, e.g. in the form of a mat
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
    • B29L2031/00—Other particular articles
    • B29L2031/001—Profiled members, e.g. beams, sections
    • B29L2031/003—Profiled members, e.g. beams, sections having a profiled transverse cross-section

Definitions

  • the invention relates to a method for producing a fiber composite component.
  • a fiber composite material is a composite material, which generally consists of two components, namely a matrix and fibers embedded therein. By mutual interactions of these components, the material receives higher quality properties than either of the two components involved individually.
  • a plurality of each two-dimensional fiber material layers, the z. B. each as a semi-finished fiber such.
  • a fabric or a scrim may be provided, stacked flat side on flat side over one another and embedded in a matrix (by infiltration with a resin and subsequent curing).
  • plate-flat component structures can thus relatively easily produce plate-shaped curved component structures.
  • a method for producing a fiber composite component which comprises the following steps:
  • nonwoven material as a material for filling one or more spaces remaining when the fiber material layers are joined together makes it possible, in a simple and cost-effective manner, to produce the relevant fiber composite component in a consistent and high quality.
  • nonwoven material here refers to a material of loosely folded fibers whose strength is based essentially on the fiber's inherent adhesion. The fibers are confused in the nonwoven material.
  • nonwoven material with one or more preferred directions of fiber orientation
  • the nonwoven material is substantially isotropic.
  • the fibers are completely stochastically oriented, such. B. in a random nonwoven fabric.
  • the use of such a filling body, in which the fibers contained have no preferred fiber direction is particularly advantageous. This not only because of the resulting, often particularly favorable mechanical component properties, but also with regard to the production of the packing and its introduction into the space in question. Because of the isotropy, the material orientation does not have to be considered in these process steps.
  • the nonwoven material is a consolidated nonwoven web.
  • This can z. B. its processing or packaging to a suitable filler can be considerably simplified.
  • the term "consolidated nonwoven” in particular includes any type of felt.
  • the fibers were characterized by a mostly mechanical processing such.
  • wet felting or “dry felts 1 " brought into a solidified form.
  • the production method according to the invention is suitable for any fibrous materials and matrix materials. Particularly advantageous is the method for the production of components with relatively highly curved component sections.
  • the fibers used for the fiber material layers are, for example, glass fibers, carbon fibers, synthetic synthetic fibers, steel fibers or natural fibers.
  • plastics such as thermosetting plastics (resins) interesting.
  • these lists are only to be understood as examples.
  • fillers or additives can be added in a manner known per se.
  • the same type of fiber is provided for the nonwoven material as for the fiber material layers to be assembled.
  • the nonwoven material may in particular z. B. made of wool fibers and / or other textile fibers including synthetic fibers.
  • the nonwoven material to be used has previously been separated from a flat structure of a consolidated nonwoven.
  • the solidified web structure can be particularly advantageous for. B. in the form of a nonwoven sheet or, with sufficient flexibility, rolled up in the form of a nonwoven material roll be kept.
  • a required filler can be separated in a suitable form from the consolidated web form, z. B. cut by a knife, and optionally placed in a desired final contour.
  • the filler to be inserted into the at least one intermediate space is formed in one piece from solidified nonwoven material.
  • this nonwoven fabric should therefore be dimensioned sufficiently (large) with regard to the required filler dimensions.
  • the stock held as solidified sheet nonwoven material having a thickness of at least 1 cm.
  • the required material thickness depends on the dimensions of the fiber composite component to be produced or the interspaces contained therein, so that in larger fiber composite components a dimensioning of prepared nonwoven or felt materials in many cases with a thickness of at least 0.1 m may be appropriate.
  • fillers of greatly varying size and / or geometry are required in the production of the fiber composite components, then it is also advantageous to provide an assortment of differently sized, stockpiled solidified nonwoven materials. In this case, material waste can be considerably reduced in practice.
  • the infiltration of the fiber material layers as well as the nonwoven material can be carried out in the invention quite generally before or after the joining of the fiber material layers.
  • initially dry semi-finished fiber products such. As tissues, braids, scrim, fiber mats, etc., and then infiltrated with a resin.
  • design of semifinished fiber products their assembly and infiltration, as well as in terms of the final curing process (eg thermal), can be used advantageously on the knowledge and methods well-known in the field of fiber composite technology.
  • the invention is also compatible for the production of fiber composite components by means of textile preform technology and vacuum infusion process ("open mold”). Also, so-called prepregs (pre-impregnated fiber semi-finished products) can be processed as the required flat fiber material layers.
  • At least one of the fiber material layers represents an angled profile and the bending region forms the curved surface section adjoining the intermediate space.
  • a simple example of such a profile is z.
  • a preferred field of application of the method according to the invention is the production of structural components, in particular for vehicles, for example aircraft.
  • An advantageous application is z.
  • Such elements or fittings are of particular interest as structural components in aircraft construction (eg with dimensions of the order of magnitude of a few 10 cm to a few m).
  • the method according to the invention it is possible in particular to manufacture components of reproducible quality, in which one or more bending regions of the two-dimensional fiber material layers inevitably form at least one wedge-like tapered intermediate space (gusset) during the assembly of the fiber material layers.
  • a felt is made in sufficient thickness with a suitable fibrous material (eg, same fibers as the fibrous material layers). The density of the felt and the resulting fiber content can be variably adjusted to the application.
  • a prefabricated felt or felt web can z. B. be made with the help of knives and placed in any desired shape for the filler.
  • a felt plate can be used for many Golf stressesgeometrien.
  • a particularly reproducible result in the production of the filling body can be achieved.
  • Various geometries are possible.
  • As the cutting out of a gusset, can advantageously be made immediately before the need. Often particularly advantageous mechanical properties of the component as well as a simplification of the processing Processing of the nonwoven or felt material results when using material with fibers without preferred direction.
  • FIG. 3 is a view corresponding to FIG. 2, after infiltration and curing,
  • FIG. 4 shows a representation to illustrate the provision of a filling body by separation from a felt web
  • FIG. 5 shows a separated from the web in Fig. 4 felt body
  • Fig. 6 is a view corresponding to FIG. 2 for a further component geometry
  • Fig. 7 is a view corresponding to FIG. 2 for a still further component geometry.
  • FIGS. 1 to 3 illustrate a method for producing a fiber composite component 10 '(FIG. 3) comprising three successively performed steps: a) joining three respective sheet-like fiber material layers 12-1, 12-2 and 12-3, wherein a felting roll 14 is inserted into a gap formed by two curved surface portions 16-1 and 16-2 of the fiber material layers 12-1 and 12- 2 is limited.
  • the suitably shaped Filzzwickel 14 is placed with a flat base on top of the fiber material layer 12-3. Then, as shown in FIG. 2, the two further fiber material layers 12-1 and 12-2 are added, so that the felt winding 14 is inserted in the intermediate space between the several (here: 3) fiber material layers. This results in a construct 10.
  • the cured and firmly interconnected fiber layers, including interposed Filzzwickel are designated in Fig. 3 with 12'-1, 12'-2, 12'-3 and 14 '.
  • the component 10 ' is in this embodiment, as shown in FIG. 3, a profile component with T-shaped cross-section and has due to the integration of the tethered and cured Filzzwickels 14' despite ease of manufacture, a high mechanical strength.
  • the length of the profile member 10 'for the sake of simplicity of the presentation is relatively short (compared to the dimensions of the Pofilqueritess) drawn.
  • the method is particularly suitable for producing elongated, straight or curved profile components.
  • Figures 4 and 5 illustrate a particularly advantageous manner in practice of producing a filling body 14a ( Figure 5).
  • Fig. 4 shows a felt plate (eg needle felt) 20a held as a supply.
  • the felt panel 20a consists of an isotropic felt having a thickness d dimensioned sufficiently to separate required fillers therefrom.
  • FIG. 4 shows sectional lines for the separation of packing of the shape of the filling body 14a shown in dashed lines.
  • the corresponding processing of the Fiizplatte 20a is preferably automated, z. B. by means of a computer-controlled cutting apparatus.
  • the wedge-shaped, prismatic shape of the filling body 14a shown in FIG. 5 is to be understood as an example only and to be described with the description given in FIG. NEN method also filler of a different geometry from the felt plate 20a can be separated or separated out (for example, the Filzzwickel 14 shown in Fig. 1).
  • FIGS. 6 and 7 illustrate further examples of assembled fiber material constructs 10b and 10c for producing fiber composite components 10b 1 and 10c 1, respectively.
  • the third fiber material layer 12c-3 with a bulged profile region has been provided so that the interposed filler 14c is attached to three curved surface sections 16c-1 to 16c -3 adjacent.
  • fiber material layer is intended to include in particular so-called textile semi-finished products as they are well known in fiber composite technology. In this case, it is by no means impossible and even expedient, in particular for comparatively thick-walled fiber material layers, that these are each formed by superimposing a plurality of individual layers.
  • Such a multi-layer fiber material layer can, for. B. during the assembly step described above. Alternatively, it is z.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Architecture (AREA)
  • Civil Engineering (AREA)
  • Structural Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Composite Materials (AREA)
  • Moulding By Coating Moulds (AREA)
  • Laminated Bodies (AREA)
  • Reinforced Plastic Materials (AREA)

Abstract

L'invention concerne un procédé permettant de produire un élément composite renforcé par fibres (10'), qui comprend les étapes suivantes: a) réunir plusieurs couches de matériau fibreux (12-1 à 12-3), dans chaque cas planes, un matériau non tissé (14) étant inséré dans au moins un interstice, qui est délimité par au moins une section superficielle (16-1, 16-2) cintrée d'une des couches de matériau fibreux, b) infiltrer les couches de matériau fibreux (12-1 à 12-3) et le matériau non tissé (14) avec un matériau matriciel et c) durcir les couches de matériau fibreux (12-1 à 12-3) réunies et infiltrées, conjointement avec le matériau non tissé.
PCT/EP2008/006935 2007-09-06 2008-08-22 Procédé de production d'élément composite renforcé par fibres Ceased WO2009033559A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102007042287.5 2007-09-06
DE102007042287A DE102007042287B4 (de) 2007-09-06 2007-09-06 Verfahren zur Herstellung eines Faserverbundbauteils

Publications (1)

Publication Number Publication Date
WO2009033559A1 true WO2009033559A1 (fr) 2009-03-19

Family

ID=40185010

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2008/006935 Ceased WO2009033559A1 (fr) 2007-09-06 2008-08-22 Procédé de production d'élément composite renforcé par fibres

Country Status (2)

Country Link
DE (1) DE102007042287B4 (fr)
WO (1) WO2009033559A1 (fr)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102011119856B4 (de) 2011-11-24 2014-09-04 Christoph Erbelding Verfahren zur Herstellung von Faserverbundbauteilen
DE102015109855A1 (de) 2015-06-19 2016-12-22 Airbus Operations Gmbh Verfahren zur Herstellung von Bauteilen, insbesondere länglichen Profilen aus bandförmigen, vorimprägnierten Fasern (Prepreg)
CN105082561B (zh) * 2015-09-18 2020-12-29 中航复合材料有限责任公司 复合材料三角填充区双圆弧结构的制造方法
DE102016211899B4 (de) 2016-06-30 2023-10-26 Airbus Operations Gmbh Verfahren zum Verwerten von Resten von vorimprägnierten Verstärkungsfasern

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2246320A (en) * 1990-07-17 1992-01-29 Europ Propulsion Preform insert
JPH0825386A (ja) * 1994-07-19 1996-01-30 Fuji Heavy Ind Ltd 繊維強化プラスチック構造部材の成形方法
US5650229A (en) * 1994-12-13 1997-07-22 Dow-United Technologies Composite Products Inc. Shaped unidirectional fiber preforms
WO2008125150A1 (fr) * 2007-04-17 2008-10-23 Airbus Operations Gmbh Procédé d'extrusion par étirage pour la réalisation d'un profil continu
EP2006074A1 (fr) * 2006-03-15 2008-12-24 Toray Industries, Inc. Procédé et appareil de fabrication d'une préforme

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4789594A (en) * 1987-04-15 1988-12-06 The Boeing Company Method of forming composite radius fillers

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2246320A (en) * 1990-07-17 1992-01-29 Europ Propulsion Preform insert
JPH0825386A (ja) * 1994-07-19 1996-01-30 Fuji Heavy Ind Ltd 繊維強化プラスチック構造部材の成形方法
US5650229A (en) * 1994-12-13 1997-07-22 Dow-United Technologies Composite Products Inc. Shaped unidirectional fiber preforms
EP2006074A1 (fr) * 2006-03-15 2008-12-24 Toray Industries, Inc. Procédé et appareil de fabrication d'une préforme
WO2008125150A1 (fr) * 2007-04-17 2008-10-23 Airbus Operations Gmbh Procédé d'extrusion par étirage pour la réalisation d'un profil continu

Also Published As

Publication number Publication date
DE102007042287A1 (de) 2009-03-12
DE102007042287B4 (de) 2012-11-22

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