WO2009049737A1 - Procédé de production d'une ébauche en un semi-produit textile pour l'obtention d'un profilé de cadre annulaire en un matériau composite fibreux - Google Patents

Procédé de production d'une ébauche en un semi-produit textile pour l'obtention d'un profilé de cadre annulaire en un matériau composite fibreux Download PDF

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Publication number
WO2009049737A1
WO2009049737A1 PCT/EP2008/007734 EP2008007734W WO2009049737A1 WO 2009049737 A1 WO2009049737 A1 WO 2009049737A1 EP 2008007734 W EP2008007734 W EP 2008007734W WO 2009049737 A1 WO2009049737 A1 WO 2009049737A1
Authority
WO
WIPO (PCT)
Prior art keywords
tape
preform
frame profile
producing
profile
Prior art date
Application number
PCT/EP2008/007734
Other languages
German (de)
English (en)
Inventor
Brian Bautz
Jürgen FILSINGER
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 WO2009049737A1 publication Critical patent/WO2009049737A1/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
    • B29C70/06—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
    • 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
    • B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
    • B29C70/32—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core on a rotating mould, former or core
    • 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
    • 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
    • B29L2031/005—Profiled members, e.g. beams, sections having a profiled transverse cross-section for making window frames

Definitions

  • the present invention relates generally to the production of preforms from textile semi-finished products for the production of fiber composite components.
  • a fiber composite material is a composite material which generally consists of two major 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 component can be economically produced in practice as a fiber composite component or not depends on a large number of factors. In addition to the required properties in terms of mechanical strength and weight of the component plays in particular the desired shape of the component or geometry a major role. In particular, for complicated or very specially shaped components an industrial production in fiber composite technology due to the associated effort is often out of the question.
  • window frames for commercial aircraft in series production.
  • window frames are typically formed by an annular window frame profile which is milled from aluminum.
  • window frame profiles have, for example, an L-shaped or U-shaped profile cross-section with at least one radial cross-sectional section, which forms a radial flange on the window frame profile.
  • a method for producing a preform made of textile semifinished product for producing an annular frame profile having at least one radial flange from the semi-finished product impregnated with a matrix material and hardened, wherein the preform is produced by winding the semifinished product fed as strip onto a core will, and wherein the wound tape is cut from a band edge, which is provided for forming the radial flange on the frame profile.
  • the invention advantageously makes possible a comparatively cost-effective, in particular easily automatable production of annular frame structures in fiber composite technology, which are suitable for numerous applications.
  • Essential for the invention is the use of a winding process to produce the preform for the annular frame profile.
  • a winding process is simple and, in particular, inexpensive to implement and can be automated and to a certain extent provides "automatically" an annularity of the preform.
  • the provision of special cuts of the semifinished product strip used for the winding process is essential for the invention. As will be more fully understood below, particularly in the description of exemplary embodiments, such cuts have particular significance with regard to the formation of the (at least one) radial flange on a curved and / or angled portion of the frame profile. In some cases, these cuts enable the formation of the required radial flanges on the finished profile component.
  • the band contains fibers in different orientations. This can be achieved for many applications, particularly advantageous strength properties of the frame profile.
  • both identical and different proportions of fibers can be provided in different orientations.
  • the proportions of fibers in different orientations can be selected in particular adapted to the requirements of the particular application.
  • the band is a multiaxial fabric, a fabric or a braid.
  • a semifinished product strip of the aforementioned type (with several different fiber orientations) can be provided in a simple manner.
  • the band contains fibers in 0 ° orientation.
  • the "0 ° orientation" is intended here to mean that the respective fibers are oriented in the circumferential direction (based on the annularity of the preform or the frame profile to be produced therewith).
  • the band contains fibers oriented in 0 °, which completely revolve (at least once) in the finished frame profile, i. H. are not interrupted in the ring.
  • the band contains fibers in 45 ° orientation and / or 90 ° orientation.
  • the band contains fiber orientations in 0 °, 90 ° and +/- 45 °.
  • the band represents a so-called "pre-preg" (preimpregnated fiber material).
  • pre-preg preimpregnated fiber material
  • Such prepregs are known per se in various embodiments and therefore need no further explanation.
  • particularly advantageously usable prepregs z. B. contain continuous fibers which are embedded in an uncured thermosetting plastic matrix.
  • Such prepregs are mostly commercially available wound on rolls commercially available and can, for.
  • the production method according to the invention is suitable for any fibrous materials and matrix materials.
  • fibers come for example Glass fibers, carbon fibers, synthetic plastic fibers, steel fibers or natural fibers into consideration.
  • a matrix material in particular plastics such.
  • the method according to the invention produces a preform which is used to produce an annular frame profile made of CFRP.
  • annular frame profile is to be understood in the context of the invention very broad and is intended to include each at least partially curved and / or angled running, total annularly extending element.
  • a frame profile over the entire circumferential course may be curved more or less, for example, to form a circular or oval frame profile.
  • one or more rectilinear portions are provided in the ring profile of the frame profile, such as for the formation of a polygonal frame profile, optionally with rounded polygon corners.
  • the frame profile may form a frame to be manufactured (eg, window frames for an aerospace vehicle).
  • the strip is fed as a quasi-endless strip whose length is sufficiently dimensioned for producing a plurality of preforms.
  • This measure is particularly interesting for a series production of preforms, for example for the production of identical preforms (eg more than ten), for example when it comes to the series production of corresponding frame profiles.
  • the incisions or center lines of the incisions each extend substantially orthogonally to the relevant band edge.
  • the locations at which the tape to be wound is cut are selected such that the incisions of adjacent winding layers are circumferentially offset zueinan- arranged on the wound tape. If the incisions are arranged equidistantly viewed at an edge of the supplied tape in the feed direction, the mutual distance of the incisions z. B. be sized so that a circumferential length of the wound on the core band is not an integer multiple of this distance. Depending on the desired shape design of the produced annular frame profile, this geometric condition can usually be realized in many ways.
  • each incision on the wound strip viewed in the circumferential direction is at least approximately in the middle between two circumferentially adjacent incisions of an underlying (or overlying) winding layer of the tape.
  • the mutual distances of adjacent incisions can be adapted to a particular band edge of the relevant shape design or dimensioning of the relevant core, preferably taking into account the gradually increasing during the winding process peripheral length.
  • the cuts do not have to be arranged equidistantly.
  • a preferred use of the method according to the invention is the production of a preform for producing a window frame element for an airframe. or spacecraft.
  • low-cost semi-finished products eg, multiaxial covers, woven fabrics, braids etc. in the form of straight strips
  • the semifinished product strip used contains endless fibers in the 0 ° orientation
  • continuous fibers (apart from the beginning and the end of the strip) can be realized in a simple manner at least in one web region of the frame profile in the circumferential direction.
  • preforms may be made for annular CFRP frames or frame members having L, Z or U profile cross sections, e.g. For example, window frames or window frame elements for aircraft, in particular commercial aircraft.
  • Fig. 1 is a plan view of an annular frame profile for enclosing a window for a commercial aircraft
  • Fig. 2 is a sectional view taken along line H-II in Fig. 1 and illustrating a Z-shaped profile cross-section of the annular frame profile of Fig. 1,
  • FIG. 3 is an illustration for illustrating a winding process for producing an annular preform from which the frame profile of FIG. 1 is manufactured;
  • FIG. 4 to 7 are the corresponding sectional views of FIG. 2 for modified embodiments of frame profiles
  • Fig. 8 is a sectional view illustrating a profile cross section in an annular frame member which is composed of two annular frame profiles each having an L-shaped profile cross-section, and
  • Fig. 9 is a sectional view illustrating a profile cross section in an annular frame member composed of a Z-section frame profile and a L-section frame profile.
  • Fig. 1 shows a plan view of an annular closed, here as an oval frame profile 10 for enclosing a window for the passenger area of a commercial aircraft.
  • the frame profile 10 comprises two radial flanges, namely a radially inner flange 12 and a radially outer flange 14 interconnected by an axial web 16 ( Figure 2).
  • Fig. 2 shows the total Z-shaped profile cross-section of the frame profile 10, which is composed in the illustrated embodiment by each rectangular profile regions of the two flanges 12, 14 and the connecting web 16.
  • transition from the radially inner flange 12 to the axial web 16 and the transition from the radially outer flange 14 to the axial web 16 takes place at respective bends 18 and 20, respectively.
  • FIG. 3 illustrates how, by winding a textile semifinished product (here: a prepreg for producing a CFRP composite) fed onto a forming core 32, a preform 34 is produced by means of which a hardening process of a type known per se is produced (eg, thermally), the annular frame profile 10 (Figure 1) can be created.
  • a textile semifinished product here: a prepreg for producing a CFRP composite
  • a preform 34 is produced by means of which a hardening process of a type known per se is produced (eg, thermally)
  • the annular frame profile 10 Figure 1
  • the semifinished product strip 30 is withdrawn in the illustrated embodiment by a braked belt spool 36 in the direction of an arrow 38 or supplied to the rotationally driven core 32.
  • the axis of rotation of the core 32 is indicated at 40.
  • An arrow 42 symbolizes the direction of rotation.
  • the preform 34 (FIG. 2) therefore likewise has a radially inner flange 44, a radially outer flange 46 and an axial web region 48 connecting these two radial flanges.
  • the semi-finished semi-finished product to be wound 30 is a flexible, but practically non-stretchable prepreg of pre-impregnated carbon fibers with different orientations (here: 0 °, 90 ° and +/- 45 °).
  • the flanges 44 and 46 which are to be oriented on the preform 34 in the radial direction, can be easily formed, the tape 30 is cut at appropriate locations from the edge before it is wound on the core 32.
  • An accomplishing this cutting or punching device can, for. B. be arranged in the course of the tape reel 36 to the core 32, but not shown in Fig. 3.
  • the radial flanges 44 and 46 of the preform 34 are formed by the lateral edge regions of the band 30 are accordingly angled out of the axial plane of the central web region 48 out.
  • suitable pressure rollers are preferably used on the outer circumference of the core 32, which bring the supplied strip material into the desired profile shape during winding.
  • That edge of the band 30 which is intended to form the radially inner flange 44 is provided with V-shaped cuts 50, which taper in the direction of the center of the band.
  • the other edge of the band 30, which is used to form the outer flange 46 is provided with "simple" (linear) cuts 52.
  • the V-shape of the cuts 50 is in this case dimensioned such that due to the curvature of the band 30 produced during winding, the V-shape "just closes", so that for the inner radial flange 40 an overlap of band areas resulting using simple incisions a winding layer is advantageously avoided.
  • the corresponding recesses 52 are not “compressed” during the formation of the flange, but “spread apart", so that the curvature of the band 30 produced in the area of the outer flange 46 when the band 30 is wound up V-shaped recesses of the strip material arise.
  • the core 32 is wrapped some 10 times with the tape 30 for the production of the preform 34.
  • the cuts 50 and 52 are in this case provided so that they are not arranged directly above one another after winding, but offset from each other. Another peculiarity of the illustrated embodiment is that the mutual incisions 50 and 52 are also offset from each other (viewed in the tape running direction 38, the incisions 50 are each in the space between two adjacent of the incisions 52).
  • the preform 34 thus formed is thermally cured, preferably in a molding tool.
  • the semifinished product used Volume 30
  • other special manufacturing steps for the production of the final product frame profile 10
  • a prior infiltration of the matrix material before the curing process may be required.
  • FIG. 4 to 7 illustrate by way of example further design options with regard to the profile cross-section in a frame profile of the type shown in Fig. 1.
  • Fig. 4 shows an L-shaped profile with a radially outwardly directed flange 14a.
  • Fig. 5 shows an L-shaped profile with a radially inwardly directed flange 12b.
  • Fig. 6 shows a U-shaped profile with two radially outwardly directed flanges 14c-1 and 14c-2, which are interconnected by an axial web 16c.
  • Fig. 7 shows a U-shaped profile with two radially inwardly directed flanges 12d-1 and 12d-2, which are interconnected by an axial web 16d.
  • the profiles according to FIGS. 4 to 7 can each be produced by a corresponding modification of the core used for winding as well as the cuts.
  • the profiles of Figs. 4 and 5 each comprising only a radial flange, it is sufficient to provide the winding process supplied to the Haizeugband only at a band edge with cuts.
  • FIGS. 8 and 9 illustrate that a frame profile element to be produced, for example a window frame of the type already explained above, can also be assembled from a plurality of annular frame profiles.
  • the two figures each show the profile of a frame 60 composed of two frame profiles produced by the method described above (FIG. 8) and 62 (FIG. 9).
  • annular frame profiles components are created that are interesting due to the use of fiber composite technology "despite difficult geometry” for many applications.

Abstract

L'invention concerne un procédé de production d'une ébauche (34) en un semi-produit textile, en vue d'obtenir un profilé de cadre annulaire (10) présentant au moins une bride radiale (12, 14), à partir du semi-produit durci et imprégné d'un matériau matriciel, procédé caractérisé en ce que l'ébauche (34) est produite par enroulement du semi-produit, amené sous la forme d'une bande (30), sur un noyau (32), et en ce que la bande à enrouler est entaillée (50, 52) à partir d'un bord de bande qui est prévu pour la formation de la bride radiale (12, 14) sur le profilé du cadre.
PCT/EP2008/007734 2007-10-12 2008-09-16 Procédé de production d'une ébauche en un semi-produit textile pour l'obtention d'un profilé de cadre annulaire en un matériau composite fibreux WO2009049737A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102007049347A DE102007049347B8 (de) 2007-10-12 2007-10-12 Verfahren zur Herstellung eines Vorformlings aus Halbzeug, zur Herstellung eines ringförmigen Rahmenprofils, Verwendung des Vefahrens, sowie Rahmenprofil
DE102007049347.0 2007-10-12

Publications (1)

Publication Number Publication Date
WO2009049737A1 true WO2009049737A1 (fr) 2009-04-23

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PCT/EP2008/007734 WO2009049737A1 (fr) 2007-10-12 2008-09-16 Procédé de production d'une ébauche en un semi-produit textile pour l'obtention d'un profilé de cadre annulaire en un matériau composite fibreux

Country Status (2)

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DE (1) DE102007049347B8 (fr)
WO (1) WO2009049737A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2319682A1 (fr) * 2009-11-10 2011-05-11 Alliant Techsystems Inc. Formage automatique de structure annulaire composite
US8226787B2 (en) 2003-08-01 2012-07-24 Alliant Techsystems Inc. Methods for forming composite stiffeners and reinforcing structures
US9662841B2 (en) 2009-11-10 2017-05-30 Orbital Atk, Inc. Radially extending composite structures
US10173380B2 (en) 2016-05-20 2019-01-08 Cotesa Gmbh Arcuate fiber composite plastic preform and method for production of curved profiles

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JP5697506B2 (ja) * 2011-03-25 2015-04-08 シキボウ株式会社 ドライプリフォーム、複合材料からなる環状構造体、及びその製造方法
DE102015204490A1 (de) 2015-03-12 2016-09-15 Wobben Properties Gmbh Verfahren und Vorrichtung zum Herstellen eines Vorformlings
DE102015004232B4 (de) * 2015-03-31 2018-12-20 Audi Ag Verfahren zur Umformung eines flächigen Halbzeugs zu einer dreidimensionalen Hohlkörperkontur
DE102015013775A1 (de) 2015-10-24 2016-04-14 Daimler Ag Verfahren zum Herstellen eines Hybridbauteils
DE102016110848A1 (de) 2016-06-14 2017-12-14 Wobben Properties Gmbh Verfahren und Vorrichtung zum Herstellen eines Vorformlings
CN113752588B (zh) * 2020-06-03 2022-07-01 上海飞机制造有限公司 一种飞机隔框的制造方法

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DE831302C (de) * 1949-03-17 1952-02-11 Fischer Stahlbau Maschinen Wer Fenster, Tueren, Tore, Drehtueren und aehnliche Konstruktionen aus Metall oder Kunststoffen
DE10326422A1 (de) * 2003-06-10 2005-01-05 Eads Deutschland Gmbh Verfahren zur Herstellung von sich in einer Längsrichtung erstreckenden FVK-Hohlprofilen

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8226787B2 (en) 2003-08-01 2012-07-24 Alliant Techsystems Inc. Methods for forming composite stiffeners and reinforcing structures
US10525641B2 (en) 2003-08-01 2020-01-07 Northrop Grumman Innovation Systems, Inc. Composite structures, forming apparatuses and related systems and methods
US10525640B2 (en) 2003-08-01 2020-01-07 Northrop Grumman Innovation Systems, Inc. Composite structures including an elongated member exhibiting a curved shape
EP2319682A1 (fr) * 2009-11-10 2011-05-11 Alliant Techsystems Inc. Formage automatique de structure annulaire composite
US8282757B2 (en) 2009-11-10 2012-10-09 Alliant Techsystems Inc. Automated composite annular structure forming
US8512497B2 (en) 2009-11-10 2013-08-20 Alliant Techsystems Inc. Automated composite annular structure forming
US9662841B2 (en) 2009-11-10 2017-05-30 Orbital Atk, Inc. Radially extending composite structures
US10668672B2 (en) 2009-11-10 2020-06-02 Northrop Grumman Innovation Systems, Inc. Radially extending composite structures
US10173380B2 (en) 2016-05-20 2019-01-08 Cotesa Gmbh Arcuate fiber composite plastic preform and method for production of curved profiles

Also Published As

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DE102007049347B8 (de) 2011-02-03
DE102007049347A1 (de) 2009-04-23
DE102007049347B4 (de) 2010-09-30

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