WO2015049114A1 - Procédé de production d'un composant structural et composant structural constitué d'un matériau composite comportant une couche supérieure métallique - Google Patents

Procédé de production d'un composant structural et composant structural constitué d'un matériau composite comportant une couche supérieure métallique Download PDF

Info

Publication number
WO2015049114A1
WO2015049114A1 PCT/EP2014/070076 EP2014070076W WO2015049114A1 WO 2015049114 A1 WO2015049114 A1 WO 2015049114A1 EP 2014070076 W EP2014070076 W EP 2014070076W WO 2015049114 A1 WO2015049114 A1 WO 2015049114A1
Authority
WO
WIPO (PCT)
Prior art keywords
imparting layer
layer
metallic
structural component
top layer
Prior art date
Application number
PCT/EP2014/070076
Other languages
English (en)
Inventor
Thomas Mathias HERKNER
Stefan Koch
Matthias Manfred MEINEL
Original Assignee
Gkn Aerospace Services Limited
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 Gkn Aerospace Services Limited filed Critical Gkn Aerospace Services Limited
Publication of WO2015049114A1 publication Critical patent/WO2015049114A1/fr

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B15/00—Layered products comprising a layer of metal
    • B32B15/04—Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different material
    • B32B15/08—Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different material of synthetic resin

Definitions

  • the present invention relates to a method for producing a structural component, in particular a structural component in which a base carrier made of a nonmetallic composite material is provided with a metallic top layer. Similarly, the present invention relates to a corresponding structural component.
  • the invention is employed in particular for structural components which are produced substantially from a fibre reinforced plastic.
  • Structural components of this type are characterized in particular by a high rigidity and strength combined with a low weight. In addition, these materials also have a high load-bearing capacity in terms of compressive stresses and/or tensile stresses. Structural components of this type can be used in many applications, for example in tools, aircraft components, satellites, floor-bound vehicles, etc.
  • Fibre reinforced, nonmetallic composite materials of this type generally comprise two essential components, specifically on the one hand the fibre and on the other hand a polymer matrix surrounding the fibre.
  • the matrix encloses the fibres and is cured by a thermal treatment (polymerization), such that three-dimensional crosslinking takes place.
  • This polymerization has the effect that the fibres are bonded firmly to one another and forces can be introduced into the fibres, specifically predominantly by way of shear stresses.
  • glass fibres may also be suitable as fibres.
  • the fibre diameter is, for example, 4.5 to 8 ⁇ [micrometres].
  • the properties of such carbon fibres are anisotropic.
  • glass fibres have an amorphous structure and isotropic properties. They consist predominantly of silicon oxide, where further oxides can be admixed if appropriate. Whereas the glass fibres are relatively inexpensive, the carbon fibres are distinguished by their high strength and rigidity.
  • prepreg technique is often used for producing corresponding components.
  • preimpreg- nated fabrics or other fibre forms preform
  • synthetic resins such as polystyrene
  • thermally treated merely until they solidify slightly (gel formation), such that they can be handled in layers.
  • a prepreg material of this type exhibits a small degree of adhesion and can therefore readily be arranged in appropriate moulds or one on top of another in layers until the desired component form is formed. If the desired layers of the prepreg material are pro- vided, they can be (thermally) cured.
  • prepreg component use is presently made of what are known as autoclaves, i.e. ovens which if appropriate are heated with an overpressure (up to 10 bar) over many hours in order to achieve complete curing of the components.
  • autoclaves i.e. ovens which if appropriate are heated with an overpressure (up to 10 bar) over many hours in order to achieve complete curing of the components.
  • prepreg materials which can be cured by means of microwave radiation are also known.
  • dielectric heating and resistive heating When heating the prepreg material using microwaves, the following active mechanisms may set in depending on the material used: dielectric heating and resistive heating.
  • Long-chain hydrocarbon molecules e.g. in epoxy resin
  • dipoles i.e. have an irregular charge distribution
  • the material can thus be heated to temperatures above 130°C or even above 160°C, a temperature at which the polymerization and/or the curing of the prepreg materials regu- larly sets in.
  • structural components of this type often have a complex, three-dimensional shape, it being the case that these structural components should not only be producible easily and quickly, but also, despite their complex shape, should scarcely have differences on their surface and/or in the surface properties thereof.
  • a further objective which is the subject of particular focus here is that of providing structural components of this type made of a nonmetallic composite material which, at least on an outer side or surface, are provided with a closed top layer with the greatest possible homogeneity which affords at least a protective function or an additional function for the composite material.
  • the protective function can consist in particular in making the surface or the composite material resistant to environmental influences, such as mechanical contact, weathering influences (sun, moisture, etc.) or the like.
  • An additional function is considered to be, for example, when the structural component is equipped with electrical functions, such that in particular an at least partially electrically conductive surface is created.
  • the intention is to specify a method for producing a structural component, with which a (fibre reinforced) nonmetallic composite material is provided with a metallic top layer, where this production method should be easily imple- mentable, the bond between the nonmetallic composite material and the metallic top layer should prove to be particularly resistant with a high load- bearing capacity, and a variable formation of the metallic top layer should be achieved without any problem.
  • a base carrier with a surface, comprising a nonmetallic composite material
  • the outer shape of the structural component is in principle not limited.
  • the structural component will in many cases form a surface or a body which can be used in a multiplicity of applications. The preferred fields of use of such structural components will be mentioned later.
  • the structural component is in particular a three-dimensional component possibly of complex shape.
  • a base carrier is provided with a surface.
  • the base carrier can in particular already form the shape of the ultimately desired structural component and/or a part thereof.
  • the base carrier will regularly also account for the greatest proportion by volume for the final structural component, and therefore in particular will also be responsi- ble for the significant proportion of weight, strength, etc. of the structural component.
  • the base carrier is made virtually exclusively from a nonmetallic composite material, i.e. in particular all outer surfaces of the base carrier are also formed with the nonmetallic composite material.
  • a base carrier use can be made in particular of the preparation methods of the prepreg technique as outlined in the introduction, and therefore reference is made at this point to these explanations.
  • a subsequent step b) (at least) one imparting layer is then formed on at least one surface or on at least part of a surface. It is preferable that only a single imparting layer is formed.
  • the imparting layer can be applied to the surface of the base carrier and/or introduced (partially) into the surface.
  • the imparting layer is distinguished in particular by the fact that it comprises a metallic material.
  • the metallic material is present in distributed form, in particular i.e. no surface layer closed with the metallic material is formed with the imparting layer. Instead, the metallic material is present in the imparting layer at least partially spaced apart (e.g.
  • step b) it may be the case in particular that the imparting layer is bonded to the base carrier (in particular so that it can be detached again virtually non- destructively) or firmly (in particular so that it can no longer be detached non-destructively) .
  • step c) a metallic top layer is then formed on the imparting layer.
  • the top layer penetrates at least partially into the imparting layer or enters into a strong integral bond with the imparting layer. It is very particularly preferable that, after the formation of the metal- lie top layer, a firm bond is formed between the base carrier, the imparting layer and the top layer.
  • the metallic top layer extends in particular as a closed top layer over the entire region of the imparting layer. In this case, the metallic top layer preferably forms a constant top layer thickness. Steps a), b) and c) are regularly performed in the order given here, where if appropriate further steps or processes can be performed therebetween and/or at the same time. Some of these steps and processes will be explained below in detail. According to one development of the method, it is proposed that step a) comprises the production of an at least partially cured base carrier comprising at least one of the following constituents: carbon fibre reinforced plastic, glass fibre reinforced plastic, aramid fibre reinforced plastic, natural fibre reinforced plastic.
  • the base carrier can also be produced and/or (partially) cured using the prepreg technique. It will often be expedient to provide the base carrier with the desired (final) contour already in the completely cured state. For this purpose, it is possible to use the manufacturing methods mentioned in the introduction. After the base carrier has been produced, conventional processes can be effected for reworking and/or preparing the following steps, for example cleaning, a surface treatment (smoothing and/or roughening), deformation, etc. According to one development, it is also proposed that the metallic material of the imparting layer is provided with at least one of the following metallic constituents: fibres, particles, sheet-like structure. In particular, the imparting layer is produced separately and then applied to the base carrier.
  • the imparting layer can likewise be produced using the prepreg technique.
  • the imparting layer to be applied can be provided in layers or as a fluid. It is preferable that the metallic constituents presented here are embedded at least partially in a matrix material of the imparting layer. In other words, this means that the imparting layer can be produced with the metallic constituents remote from the base carrier and/or else firstly in step b), i.e. in particular on the base carrier itself.
  • the metallic fibres present can be introduced in particular in the form of wires, chips or the like.
  • the fibres can have, for example, a fibre length in the range of 0.1 to 5.0 mm [millimetres] and a fibre diameter in the range of
  • metallic particles can also be provided.
  • the particles can have in principle a use-oriented form
  • the particles have, for example, a (mean) particle diameter in the range of 5 to 15 ⁇ [micrometres].
  • At least one metallic sheet-like structure can be provided in the imparting layer.
  • the sheet-like structure can be configured, for example, in the form of a mesh, a woven fabric, a knitted fabric, a nonwoven or the like.
  • the sheet-like structure itself should be configured in such a way that the metallic material can be provided as a structural component with apertures, openings, pores, etc., i.e. virtually itself (alone) can form an imparting layer.
  • the imparting layer comprises at least one constituent of the nonmetallic composite material.
  • the imparting layer is enriched with at least one constituent of the nonmetallic composite material.
  • This can be provided in the form of the matrix material and/or as an additive material.
  • the imparting layer comprises one of the following constituents: carbon fibres, glass fibres, aramid fibres, natural fibres. These fibres are provided in particular with a fibre length in the range of 0.1 to 3.0 mm [millimetres] and/or a fibre diameter in the range of 7 to 24 ⁇ [micrometres].
  • the proportion of the constituents of the nonmetallic composite material is preferably 40 to 60% by weight of the imparting layer.
  • constituents can be provided to an increased extent in an outer boundary region to at least one neighbouring layer or the base body or else in a uniform distribution in the imparting layer. If a concentrated arrangement is desired at at least one boundary region, the constituents of the non- metallic composite material can also be added separately (subsequently) to the surface of the base carrier (before step b)) and/or to the surface of the applied imparting layer (after step b)). According to a development of the method, the imparting layer is formed with an at least porous or nonmetallic matrix material.
  • This matrix material can in particular form similar chemical and/or physical properties or a similar material composition to the top layer and/or the base carrier.
  • a porosity of the imparting layer is greater, for example, during application to the base carrier than later in the finished structural component.
  • the porosity should express the fact that provision is made of cavities and/or passages which promote in particular the incorporation or the accumulation of adjacent material components and/or the integration of the metallic constituents and/or of the nonmetallic constituents in the imparting layer.
  • the matrix material has an electrically insulating property. It is preferable in this respect that the matrix material is porous and nonmetallic.
  • this comprises at least one of the following components: paper, foam, resin.
  • the components are in such a form in particular that the metallic constituents of the imparting layer are fixed therein and/or thereon with a dispersed distribution.
  • the paper has in particular a weight per unit area in the range of 80 to 1000 g/m 2 or a paper thickness in the range of 0.2 to 3 mm [millimetres].
  • the foam can form open and/or closed pores and preferably have a porosity in the range of 20% to 75%.
  • this resin can be formed with (small) cavities, e.g. like micropores, which extend preferably from an outer surface (partially) inwards. This can be achieved, for example, by postmachining.
  • step b) comprises at least the following processes:
  • the imparting layer is applied in an at least partially deformable form and is thermally solidified in process b.2).
  • the base carrier may be pretreated, for example roughened, cleaned or the like.
  • the surface of the base carrier is still (slightly) deformable, in particular if for example an imparting layer in the form of a sheet-like structure (wire mesh) is pressed into the surface of the base carrier.
  • process b.2) the base carrier together with the imparting layers are then subjected to a heat treatment, in which in particular curing of at least one of the materials and(or constituents of the base carrier and imparting layer sets in, such that the imparting layer is permanently fixed or integrated on the surface of the base carrier.
  • a heat treatment in which in particular curing of at least one of the materials and(or constituents of the base carrier and imparting layer sets in, such that the imparting layer is permanently fixed or integrated on the surface of the base carrier.
  • process b.2) can also be carried out at an elevated ambient pressure or as a sintering process.
  • Process b.3) has the effect in particular that the surface of the imparting layer is machined, in order to expose (in a targeted manner) metallic materials which are integrated in the imparting layer or are included in the imparting layer after process b.2). This can be effected, for example, using mechanical and/or thermal material removal methods.
  • process b.3) comprises laser machining the imparting layer.
  • a high-energy laser is directed onto the imparting layer, where in particular the further constituents of the imparting layer, which form the outer surface of the imparting layer and are nonmetallic materials, are removed and/or evaporated.
  • the laser is to be operated in particular in such a way that the metallic materials (in part) obtain an exposed or protruding position with respect to the imparting layer, i.e. in particular pro- trade beyond the outer surface or form it (in the manner of a ragged surface).
  • Process b.3 performs the task in particular of making it possible to achieve a good metal-to-metal bond with the metallic top layer to be applied later.
  • the exposure of the metallic material also has the effect that clearances are created around the metallic materials, into which clearances the metallic top layer can subsequently penetrate and thus a good mechanical and also integral bond between the (two or three) layers is made possible.
  • further processes can of course follow between process b.3) and step c), for example cleaning processes, surface shaping processes (dimensional accuracy, roughness, etc.), etc.
  • material removal in process b.3) is compensated for by corresponding material application in step c).
  • the base carrier (together with the imparting layer) to be finished already with a near net shape and for the material removals from the processes of the production method proposed here to be compensated for by corresponding material applications of the metallic top layer. Since the material removal and the material application can be controlled exactly, it is possible in particular to reuse already existing tools to produce the structural components and/or to employ the production method presented here also as a repair method.
  • step c) comprises at least one of the following processes:
  • Electroplating generally involves the provision of an electrolytic bath, in which a cathode and an anode are formed, such that an electric current can flow.
  • the metal which is to be applied to the substrate is provided on the anode.
  • the cathode is formed with the substrate to be coated.
  • the applied electric current in this process detaches metal ions from the anode (consumer electrode) and deposits them by reduction on the substrate (cathode).
  • the substrate to be coated is thus provided uniformly with a metallic top layer in the intended regions.
  • the layer thickness of the metal layer also increases with the duration of the electroplating.
  • the provision of the imparting layer with its different characteristics is selected notably to the effect that the electroplating process is particularly suitable for producing a metallic, homogeneous top layer.
  • the metallic top layer is (also) applied by means of vapour deposition.
  • a gaseous carrier medium guides the metallic material onto the imparting layer.
  • CVD chemical vapour deposition
  • C-CVD flame coatings
  • PVD physi- cal vapour depositions
  • sputtering can usually be considered.
  • Vapour deposition is suitable particularly when a very thin, homogeneous top layer is to be provided, for example with a top layer thickness in the nanometre range or (at most) up to the micrometre range.
  • the metallic top layer comprises at least one of the following constituents: nickel, chromium, titanium, copper, steel.
  • alloys can also of course be em- braced by the metallic top layer, where for example the aforementioned constituents nickel, chromium, titanium, copper represent the basis or the predominant proportion by weight.
  • nickel is suitable, for example, when the corrosion protec- tion properties and/or the scratch resistance is to be improved.
  • Chromium is used in particular when at least one of the factors surface hardness, sliding property and abrasion resistance are to be adapted.
  • a top layer comprising titanium can be expedient when an anti-corrosion action is required at rela- tively high temperatures, and/or fitting components made of carbon fibre reinforced plastic are permanently in contact with the surface (electrochemical series).
  • the formation of a top layer comprising copper makes it possible for the workpieces to have an increased thermal conductivity and electrical conductivity, which achieves functionality determined merely thereby or makes further refining possible.
  • Further constituents of a metallic top layer can also be, for example, Invar® or a similar iron-nickel alloy with low thermal expansion.
  • a structural component which has at least a base carrier made of a nonmetallic composite material, an imparting layer made of a matrix material with a metallic material integrated therein, and a metallic top layer, wherein the imparting layer is arranged between the base carrier and the top layer.
  • the structural component can be produced in particular by the method described here according to the invention. In this respect, it should also be stated that, in terms of the characteristics and/or of the constituents, reference can be made comprehensively (also independently of the production process) to the features indicated here.
  • the structural component is preferably one of the following components: outer skin element of an aircraft, antenna, tool for producing an outer skin component of an aircraft, satellite component, regions of the aircraft outer skin at risk of erosion, an engine casing or engine blades made of carbon fibre reinforced plastic, elements which require local heat dissipation, regions at risk of corrosion, e.g. in the bilge of an aircraft fuselage, defined sliding surfaces in the case of drive shafts made of carbon fibre reinforced plastic, surfaces for deicing or to be kept free of ice during operation of the aircraft.
  • the layer structure of the structural component close to the outer surface can easily be identified by a corresponding consideration of a cross section through the structural component.
  • the layer structure revealed here can be ascertained without any problem on account of the different constituents of base carrier, imparting layer and top layer.
  • the imparting layer has an increased proportion of metallic material in a boundary region towards the top layer.
  • the metallic top layer is applied by means of electroplating.
  • This increased proportion of metallic materials in the boundary region is notably the consequence of the fact that this me- tallic material has been exposed from the imparting layer during a production process, i.e. in particular is provided by subsequent removal of a matrix material and/or compression of the matrix material.
  • the increased proportion of the metallic material in the boundary region ensures a durable bond to the metallic top layer, for example by direct metal-metal contact and/or the possibility that the material of the top layer can penetrate deep into the imparting layer in the boundary region. This prevents in particular undesirable shearing of the top layer away from the imparting layer in the structural component.
  • the top layer forms at least part of an outer surface of the structural component.
  • Fig. 1 shows a method sequence for producing the structural component
  • Fig. 2 shows a first embodiment variant of the imparting layer
  • Fig. 3 shows a second embodiment variant of the imparting layer
  • Fig. 4 shows a third embodiment variant of the imparting layer
  • Fig. 5 shows a fourth embodiment variant of the imparting layer
  • Fig. 6 shows a fifth embodiment variant of the imparting layer
  • Fig. 7 shows an embodiment variant of the method for shaping an im- parting layer
  • Fig. 8 shows a detailed view of a structural component. It is to be noted that identical components in the figures are provided with the same reference signs hereinbelow. Furthermore, it is noted that the combinations of technical features shown in the figures are not generally compulsory. Thus, technical features of a figure or of a shown component can be combined with other technical features of a further figure or of a further shown component and/or of the general description. Something different shall apply only if the combination of features has been declared explicitly as a necessity here and/or a person skilled in the art identifies that the production process is impossible without this combination.
  • Fig. 1 illustrates substantially the superordinate steps a), b) and c), which are to be carried out at least for producing the structural component 1.
  • a base carrier 2 is provided, which on the outside forms a surface 3.
  • the base body 2 regularly consists of a nonmetallic com- posite material 4, in particular a fibre reinforced plastic. Even if here the base carrier 2 is shown by way of example in one piece, this is not absolutely necessary.
  • the area of the surface 3 which is ultimately to be equipped with a metallic top layer can be freely selected, and in particular can also comprise corners, edges, non-planar sur- faces, etc.
  • an imparting layer 5 is formed on the surface 3 of the base carrier 2.
  • This imparting layer 5 here comprises a metallic material 6.
  • the metallic material 6 is embedded in a matrix material, such that (with the possible exception of the shaping of an imparting layer 5 in the manner of a sheet-like structure) no purely metallic bonding layer 5 is usually present.
  • a metallic top layer 7 is to be formed on the imparting layer 5 (cf. step c)).
  • a two-layer system is thus produced on the base carrier 2, whereupon the metallic top layer 7 in particular provides the desired functions for the struc- rural component 1 and the imparting layer 5 ensures the reliable and permanent bond between the metallic top layer 7 and the base carrier 2.
  • Fig. 2 - 6 show different embodiment variants of the imparting layer 5 comprising the metallic material 6. These figures also reveal various com- binations of matrix material 11 and metallic material 6, but these are only intended to be exemplary here.
  • Fig. 2 shows (e.g. in cross section) a detail of the imparting layer comprising a matrix material 11, here resin 14 for example, in which the metallic material 6 is provided in the form of (platelet- like and/or planar) particles 9 having a predefined particle diameter 21.
  • the particle diameters 21 of the particles 9 can be different, but this is not absolutely necessary.
  • Fig. 3 shows a similar system to Fig. 2, but here the metallic material 6 is provided with fibres 8 of a predefined fibre length 22 and a predefined fibre diameter 23.
  • the fibre length and/or fibre diameter of the fibres 8 in the matrix material 11 can vary, but this is not absolutely necessary.
  • Fig. 4 shows that the metallic material 6 can also be in the form of a sheetlike structure 10.
  • a woven fabric is formed from metallic fibres 8, which then sufficiently forms openings in order to realize a good integral bond with the nonmetallic composite material of the base carrier.
  • Fig. 5 shows a refinement of the imparting layer 5 in which the metallic material 6 is integrated in paper 12. If appropriate, it is possible that the paper 12 is thermally treated, in particular sintered, in the course of the process for producing the structural component.
  • Fig. 6 is intended to illustrate that the imparting layer 5 can also be formed with a foam 13, where the metallic material 6 is introduced at least partially into the pores of the foam 13.
  • Fig. 7 schematically illustrates how the imparting layer 5 is applied and if appropriate prepared for step c).
  • process b.l firstly the con- stituents of the imparting layer 5 are applied to the surface 3 of the base carrier 2.
  • the imparting layer 5 can be applied, for example, with a plurality of at least partially deformable layers, although superimposed, layered application, spraying on or the like is also possible.
  • process b.2) shown the imparting layer 5 is then fixed on the base carrier 2. This can be effected, for example, by virtue of the fact that the two components are baked to one another and/or the imparting layer 5 cures.
  • the base carrier 2 together with the imparting layer 5 can be treated in an oven 25, for example, if appropriate at an excess pressure.
  • the then cured, at least partially no longer deformable imparting layer 5 is fastened securely on the base carrier, it can be machined in process b.3) in such a way that the metallic material 6 of the imparting layer 5 is exposed.
  • laser machining is carried out on the surface by means of a laser 24 (if appropriate operated in pulsed fashion). This has the effect in particular that the matrix material, which otherwise at least partially also surrounds or covers the metallic material 6 of the imparting layer 5, is removed, and therefore a greater proportion of metallic material 6 is then exposed in the boundary region 17. There is therefore a specific material removal 15, in particular in terms of the matrix material of the imparting layer 5.
  • Fig. 8 also shows how the material removal 15 effected, for example, ac- cording to process b.3) is applied again by a metallic top layer 7 (see material application 16).
  • the detail illustrated in Fig. 8 in section through a structural component 1 shows the following layers proceeding from the outer side 18:
  • the outer surface 18 is formed by the metallic top layer 7 having a predefined top layer thickness 20.
  • This is adjoined underneath by the (remaining) imparting layer 5 having an imparting layer thickness 19, the imparting layer 5 in this example comprising not only metallic materials 6 (e.g. in the form of particles), but also in addition nonmetallic composite material 4, for exam- pie in the form of fibres (carbon fibres, glass fibres, etc.).
  • the imparting layer 5 in this example comprising not only metallic materials 6 (e.g. in the form of particles), but also in addition nonmetallic composite material 4, for exam- pie in the form of fibres (carbon fibres, glass fibres, etc.).
  • the transition region between the top layer 7 and the imparting layer 5 there is formed a boundary region, in which there is a good integral and mechanical bond between the constituents of top layer and imparting layer.
  • the base carrier 2 which likewise comprises nonmetallic composite material 4.
  • the base carrier 2 has a relatively rough surface 3, which likewise promotes the bond between the imparting layer 5 and the base carrier 2.

Landscapes

  • Laminated Bodies (AREA)

Abstract

La présente invention concerne un procédé de production d'un composant structural (1), comprenant au moins les étapes suivantes consistant à : a) fournir un support de base (2) comportant une surface (3), comprenant un matériau composite non métallique (4), b) former une couche de transmission (5) sur la surface (3), comprenant un matériau métallique (6), c) former une couche supérieure métallique (7) sur la couche de transmission (5). De plus, l'invention concerne un composant structural (1) comprenant un support de base (2) constitué d'un matériau composite non métallique (4), d'une couche de transmission (5) constituée d'un matériau de matrice (11) intégrant un matériau métallique (6) en son sein, et d'une couche supérieure métallique (7), la couche de transmission (5) étant disposée entre le support de base (2) et la couche supérieure (7).
PCT/EP2014/070076 2013-10-01 2014-09-22 Procédé de production d'un composant structural et composant structural constitué d'un matériau composite comportant une couche supérieure métallique WO2015049114A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102013110921.7A DE102013110921A1 (de) 2013-10-01 2013-10-01 Verfahren zur Herstellung eines Strukturbauteils sowie Strukturbauteil aus Verbundwerkstoff mit metallischer Deckschicht
DE102013110921.7 2013-10-01

Publications (1)

Publication Number Publication Date
WO2015049114A1 true WO2015049114A1 (fr) 2015-04-09

Family

ID=51660445

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2014/070076 WO2015049114A1 (fr) 2013-10-01 2014-09-22 Procédé de production d'un composant structural et composant structural constitué d'un matériau composite comportant une couche supérieure métallique

Country Status (2)

Country Link
DE (1) DE102013110921A1 (fr)
WO (1) WO2015049114A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3181731A1 (fr) * 2015-12-09 2017-06-21 Rolls-Royce plc Procédé d'application d'une couche électrodéposée sur un matériau composite polymère
CN113400669A (zh) * 2021-05-27 2021-09-17 航天辰马(宁波)新材料有限公司 一种防雷车辆地板用高吸能蜂窝板的制作方法

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1323844A1 (fr) * 2001-12-20 2003-07-02 CENTRO SVILUPPO MATERIALI S.p.A. Composite démontrant une faible émissivité dans l'infrarouge moyen et lointain et une faible réflectivité dans le visible et l'infrarouge proche
WO2012110383A2 (fr) * 2011-02-15 2012-08-23 Integran Technologies Articles hybrides en polymère-métal légers ayant une limite d'élasticité élevée

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1323844A1 (fr) * 2001-12-20 2003-07-02 CENTRO SVILUPPO MATERIALI S.p.A. Composite démontrant une faible émissivité dans l'infrarouge moyen et lointain et une faible réflectivité dans le visible et l'infrarouge proche
WO2012110383A2 (fr) * 2011-02-15 2012-08-23 Integran Technologies Articles hybrides en polymère-métal légers ayant une limite d'élasticité élevée

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3181731A1 (fr) * 2015-12-09 2017-06-21 Rolls-Royce plc Procédé d'application d'une couche électrodéposée sur un matériau composite polymère
US10221704B2 (en) 2015-12-09 2019-03-05 Rolls-Royce Plc Method of applying an electroplated layer to a polymeric composite material
CN113400669A (zh) * 2021-05-27 2021-09-17 航天辰马(宁波)新材料有限公司 一种防雷车辆地板用高吸能蜂窝板的制作方法

Also Published As

Publication number Publication date
DE102013110921A1 (de) 2015-04-02

Similar Documents

Publication Publication Date Title
EP3019711B1 (fr) Nosecône en polymère plaqué pour turbine à gas
JP5139426B2 (ja) 鋼材複合体及びその製造方法
JP5008040B2 (ja) チタン合金複合体とその接合方法
US20130271891A1 (en) Metallic Mesh and Lightning Strike Protection System
WO2007138619A1 (fr) Procédé de production rapide d'objets de forme quelconque
EP3285994B1 (fr) Objet comprenant une matière plastique renforcée par des fibres et un matériau céramique et procédé de fabrication de l'objet
US20110091709A1 (en) Method for coating a fiber composite component for an aircraft or spacecraft and fiber composite component produced by said method
US20170165906A1 (en) Method of making a composite article
CA2917955A1 (fr) Placage d'un composite pour renforcer le collage d'elements metalliques
JP2011508715A (ja) 望ましい形状に注型し次いで金属又は高特性セラミック層で被覆することによるコンクリートのような低コストのセラミック又はポリマーから高度に機械的に要求される部品および特殊工具の製造方法
JPWO2008126812A1 (ja) 銅合金複合体とその製造方法
CA2676731C (fr) Materiau composite renforce par des fibres et a matrice metallique et procede de fabrication dudit materiau
EP3285935B1 (fr) Procédé de production d'un composite protégé thermiquement
US20080311374A1 (en) Metallized skin panels and methods of making
Qaiser et al. Optimization of interlaminar shear strength behavior of anodized and unanodized ARALL composites fabricated through VARTM process
WO2015049114A1 (fr) Procédé de production d'un composant structural et composant structural constitué d'un matériau composite comportant une couche supérieure métallique
JP2019130895A (ja) マンドレルの上のカウルを有する誘導加熱セル、及びそれを使用する方法
US11453147B2 (en) Method for producing a composite component formed with a fibre-reinforced plastic component on which at least one surface with a coating is formed
GB2509754A (en) Ferromagnetic fibre composites
DK2676993T3 (en) Component with a layer which reduces the adhesion and method of making it
EP3181731B1 (fr) Procédé d'application d'une couche électrodéposée sur un matériau composite polymère
Ostapiuk Behavior of microcapsules in FML under different pressure of manufacturing in autoclave
Faudree et al. Advances in Titanium/Polymer Hybrid Joints by Carbon Fiber Plug Insert: Current Status and Review. Materials 2022, 15, 3220
US11377750B1 (en) Ductile coatings on additive manufactured components
JP2018009241A (ja) 金属基複合材料形成のためのシステムおよび方法

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 14780786

Country of ref document: EP

Kind code of ref document: A1

NENP Non-entry into the national phase

Ref country code: DE

122 Ep: pct application non-entry in european phase

Ref document number: 14780786

Country of ref document: EP

Kind code of ref document: A1