EP3860835A2 - Produit semi-fini et procédé de fabrication d'un composant structural - Google Patents

Produit semi-fini et procédé de fabrication d'un composant structural

Info

Publication number
EP3860835A2
EP3860835A2 EP19779842.4A EP19779842A EP3860835A2 EP 3860835 A2 EP3860835 A2 EP 3860835A2 EP 19779842 A EP19779842 A EP 19779842A EP 3860835 A2 EP3860835 A2 EP 3860835A2
Authority
EP
European Patent Office
Prior art keywords
semi
prepreg
finished product
layer structure
layers
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.)
Pending
Application number
EP19779842.4A
Other languages
German (de)
English (en)
Inventor
Julian Kuntz
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.)
Premium Aerotec GmbH
Original Assignee
Premium Aerotec 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 Premium Aerotec GmbH filed Critical Premium Aerotec GmbH
Publication of EP3860835A2 publication Critical patent/EP3860835A2/fr
Pending 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
    • B29C70/04—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
    • B29C70/22—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure
    • B29C70/222—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure the structure being shaped to form a three dimensional configuration
    • 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
    • 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
    • B29C35/00—Heating, cooling or curing, e.g. crosslinking or vulcanising; Apparatus therefor
    • B29C35/02—Heating or curing, e.g. crosslinking or vulcanizing during moulding, e.g. in a mould
    • B29C35/08—Heating or curing, e.g. crosslinking or vulcanizing during moulding, e.g. in a mould by wave energy or particle radiation
    • B29C35/0805—Heating or curing, e.g. crosslinking or vulcanizing during moulding, e.g. in a mould by wave energy or particle radiation using electromagnetic radiation
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/40—Shaping or impregnating by compression not applied
    • B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
    • B29C70/46—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs
    • B29C70/465—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating by melting a solid material, e.g. sheets, powders of fibres
    • 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
    • B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
    • B32B5/02—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer
    • 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
    • B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
    • B32B5/22—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed
    • B32B5/24—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer
    • B32B5/26—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer another layer next to it also being fibrous or filamentary
    • 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
    • B32B7/00—Layered products characterised by the relation between layers; Layered products characterised by the relative orientation of features between layers, or by the relative values of a measurable parameter between layers, i.e. products comprising layers having different physical, chemical or physicochemical properties; Layered products characterised by the interconnection of layers
    • B32B7/04—Interconnection of layers
    • B32B7/08—Interconnection of layers by mechanical means
    • B32B7/09—Interconnection of layers by mechanical means by stitching, needling or sewing
    • C—CHEMISTRY; METALLURGY
    • C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
    • C08J—WORKING-UP; GENERAL PROCESSES OF COMPOUNDING; AFTER-TREATMENT NOT COVERED BY SUBCLASSES C08B, C08C, C08F, C08G or C08H
    • C08J5/00—Manufacture of articles or shaped materials containing macromolecular substances
    • C08J5/04—Reinforcing macromolecular compounds with loose or coherent fibrous material
    • C—CHEMISTRY; METALLURGY
    • C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
    • C08J—WORKING-UP; GENERAL PROCESSES OF COMPOUNDING; AFTER-TREATMENT NOT COVERED BY SUBCLASSES C08B, C08C, C08F, C08G or C08H
    • C08J5/00—Manufacture of articles or shaped materials containing macromolecular substances
    • C08J5/24—Impregnating materials with prepolymers which can be polymerised in situ, e.g. manufacture of prepregs
    • D—TEXTILES; PAPER
    • D03—WEAVING
    • D03D—WOVEN FABRICS; METHODS OF WEAVING; LOOMS
    • D03D1/00—Woven fabrics designed to make specified articles
    • D—TEXTILES; PAPER
    • D03—WEAVING
    • D03D—WOVEN FABRICS; METHODS OF WEAVING; LOOMS
    • D03D15/00—Woven fabrics characterised by the material, structure or properties of the fibres, filaments, yarns, threads or other warp or weft elements used
    • D03D15/40—Woven fabrics characterised by the material, structure or properties of the fibres, filaments, yarns, threads or other warp or weft elements used characterised by the structure of the yarns or threads
    • D03D15/44—Woven fabrics characterised by the material, structure or properties of the fibres, filaments, yarns, threads or other warp or weft elements used characterised by the structure of the yarns or threads with specific cross-section or surface shape
    • D03D15/46—Flat yarns, e.g. tapes or films
    • D—TEXTILES; PAPER
    • D03—WEAVING
    • D03D—WOVEN FABRICS; METHODS OF WEAVING; LOOMS
    • D03D15/00—Woven fabrics characterised by the material, structure or properties of the fibres, filaments, yarns, threads or other warp or weft elements used
    • D03D15/40—Woven fabrics characterised by the material, structure or properties of the fibres, filaments, yarns, threads or other warp or weft elements used characterised by the structure of the yarns or threads
    • D03D15/47—Woven fabrics characterised by the material, structure or properties of the fibres, filaments, yarns, threads or other warp or weft elements used characterised by the structure of the yarns or threads multicomponent, e.g. blended yarns or threads
    • D—TEXTILES; PAPER
    • D03—WEAVING
    • D03D—WOVEN FABRICS; METHODS OF WEAVING; LOOMS
    • D03D15/00—Woven fabrics characterised by the material, structure or properties of the fibres, filaments, yarns, threads or other warp or weft elements used
    • D03D15/50—Woven fabrics characterised by the material, structure or properties of the fibres, filaments, yarns, threads or other warp or weft elements used characterised by the properties of the yarns or threads
    • D03D15/587—Woven fabrics characterised by the material, structure or properties of the fibres, filaments, yarns, threads or other warp or weft elements used characterised by the properties of the yarns or threads adhesive; fusible
    • D—TEXTILES; PAPER
    • D04—BRAIDING; LACE-MAKING; KNITTING; TRIMMINGS; NON-WOVEN FABRICS
    • D04H—MAKING TEXTILE FABRICS, e.g. FROM FIBRES OR FILAMENTARY MATERIAL; FABRICS MADE BY SUCH PROCESSES OR APPARATUS, e.g. FELTS, NON-WOVEN FABRICS; COTTON-WOOL; WADDING ; NON-WOVEN FABRICS FROM STAPLE FIBRES, FILAMENTS OR YARNS, BONDED WITH AT LEAST ONE WEB-LIKE MATERIAL DURING THEIR CONSOLIDATION
    • D04H3/00—Non-woven fabrics formed wholly or mainly of yarns or like filamentary material of substantial length
    • D04H3/02—Non-woven fabrics formed wholly or mainly of yarns or like filamentary material of substantial length characterised by the method of forming fleeces or layers, e.g. reorientation of yarns or filaments
    • D04H3/04—Non-woven fabrics formed wholly or mainly of yarns or like filamentary material of substantial length characterised by the method of forming fleeces or layers, e.g. reorientation of yarns or filaments in rectilinear paths, e.g. crossing at right angles
    • D—TEXTILES; PAPER
    • D04—BRAIDING; LACE-MAKING; KNITTING; TRIMMINGS; NON-WOVEN FABRICS
    • D04H—MAKING TEXTILE FABRICS, e.g. FROM FIBRES OR FILAMENTARY MATERIAL; FABRICS MADE BY SUCH PROCESSES OR APPARATUS, e.g. FELTS, NON-WOVEN FABRICS; COTTON-WOOL; WADDING ; NON-WOVEN FABRICS FROM STAPLE FIBRES, FILAMENTS OR YARNS, BONDED WITH AT LEAST ONE WEB-LIKE MATERIAL DURING THEIR CONSOLIDATION
    • D04H3/00—Non-woven fabrics formed wholly or mainly of yarns or like filamentary material of substantial length
    • D04H3/08—Non-woven fabrics formed wholly or mainly of yarns or like filamentary material of substantial length characterised by the method of strengthening or consolidating
    • D04H3/14—Non-woven fabrics formed wholly or mainly of yarns or like filamentary material of substantial length characterised by the method of strengthening or consolidating with bonds between thermoplastic yarns or filaments produced by welding
    • 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
    • B29C35/00—Heating, cooling or curing, e.g. crosslinking or vulcanising; Apparatus therefor
    • B29C35/02—Heating or curing, e.g. crosslinking or vulcanizing during moulding, e.g. in a mould
    • B29C35/08—Heating or curing, e.g. crosslinking or vulcanizing during moulding, e.g. in a mould by wave energy or particle radiation
    • B29C35/0805—Heating or curing, e.g. crosslinking or vulcanizing during moulding, e.g. in a mould by wave energy or particle radiation using electromagnetic radiation
    • B29C2035/0811—Heating or curing, e.g. crosslinking or vulcanizing during moulding, e.g. in a mould by wave energy or particle radiation using electromagnetic radiation using induction
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
    • B29K2101/00—Use of unspecified macromolecular compounds as moulding material
    • B29K2101/12—Thermoplastic materials
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
    • B29K2105/00—Condition, form or state of moulded material or of the material to be shaped
    • B29K2105/06—Condition, form or state of moulded material or of the material to be shaped containing reinforcements, fillers or inserts
    • B29K2105/08—Condition, form or state of moulded material or of the material to be shaped containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns
    • B29K2105/0809—Fabrics
    • B29K2105/0845—Woven fabrics
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
    • B29K2105/00—Condition, form or state of moulded material or of the material to be shaped
    • B29K2105/06—Condition, form or state of moulded material or of the material to be shaped containing reinforcements, fillers or inserts
    • B29K2105/08—Condition, form or state of moulded material or of the material to be shaped containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns
    • B29K2105/0872—Prepregs
    • B29K2105/0881—Prepregs unidirectional
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
    • B29K2995/00—Properties of moulding materials, reinforcements, fillers, preformed parts or moulds
    • B29K2995/0037—Other properties
    • B29K2995/0046—Elastic
    • 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
    • B32B2260/00—Layered product comprising an impregnated, embedded, or bonded layer wherein the layer comprises an impregnation, embedding, or binder material
    • B32B2260/02—Composition of the impregnated, bonded or embedded layer
    • B32B2260/021—Fibrous or filamentary layer
    • B32B2260/023—Two or more layers
    • 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
    • B32B2260/00—Layered product comprising an impregnated, embedded, or bonded layer wherein the layer comprises an impregnation, embedding, or binder material
    • B32B2260/04—Impregnation, embedding, or binder material
    • B32B2260/046—Synthetic resin
    • 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
    • B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
    • B32B2262/02—Synthetic macromolecular fibres
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    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
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    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
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    • B32B2605/00—Vehicles
    • B32B2605/18—Aircraft
    • C—CHEMISTRY; METALLURGY
    • C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
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    • D10B2505/00—Industrial
    • D10B2505/02—Reinforcing materials; Prepregs

Definitions

  • the present invention relates to a semi-finished product and a method for producing a structural component, in particular a structural component, which has a curved or double-curved shape or shape.
  • Structural components made of fiber composite material which have a dome-shaped or dome-shaped or otherwise spherical shape that is curved in at least two directions. Such components are used in aircraft construction e.g. used as a pressure frame or as a fuselage shell.
  • Fiber composite components wherein a layer structure, which has reinforcing fiber layers embedded in thermoplastic matrix material, between
  • Structural component wherein a plurality of semifinished layers from one
  • fiber-reinforced thermoplastic material are stacked and selectively connected to each other to fix a position of the semifinished layers relative to each other. Wrinkling during subsequent press forming is to be avoided by the type of connection.
  • a semifinished product for producing a structural component.
  • the semifinished product comprises a multiplicity of prepreg tapes which extend along one another and each have unidirectionally arranged reinforcing fibers embedded in a thermoplastic matrix material and a multiplicity of connecting strands comprising a thermoplastic material.
  • Prepreg tapes are connected to form a textile fabric in which each of the connecting strands crosses several of the prepreg tapes.
  • Connecting strands and the prepreg bands are in a first end region of the Flat structure and a second end region of the flat structure lying opposite to it, each along a connecting line
  • thermoplastic material of the connecting strands can be the same thermoplastic material as the matrix material contained in the prepreg tapes or at least have a similar composition.
  • the textile structure i.e. a structure made up of intersecting strands, offers the advantage that the semi-finished product is anisotropic
  • the textile structure allows the prepreg tapes to slide along one another, which prevents wrinkling when deforming.
  • the formation of wrinkles is further prevented by the fact that a cohesive connection of the strands, that is to say a cohesive connection between prepreg tapes and thermoplastic connecting strands, only along connecting lines lying opposite one another
  • the unidirectional thermoplastic prepreg tapes are elongated, single-ply tape material, in which continuous, unidirectional reinforcing fibers are embedded in a thermoplastic matrix material.
  • Prepreg tapes of this type have the advantage that they are easily deformable but are not very susceptible to the formation of undulations.
  • Matrix material more to produce a structural component from the semi-finished product.
  • a semifinished product for producing a structural component.
  • the semi-finished product includes a variety of
  • Prepreg tapes each in a thermoplastic matrix material
  • thermoplastic materials have embedded, unidirectionally arranged reinforcing fibers.
  • thermoplastic materials are also optional
  • the prepreg tapes are arranged to form a multiaxial fabric which comprises a plurality of layers of prepreg tapes lying one above the other, the prepreg tapes running parallel to one another within one layer, and the layers being connected at individual points relative to one another, in particular sewn, knitted, woven, welded or through another textile process connected, preferably by means of the connecting strands.
  • a multi-layer semifinished product is provided, the individual layers being formed from parallel prepreg strips and the individual layers being connected only selectively by the connecting strands.
  • connection points can be provided along parallel lines. Due to the only selective connection of the layers and the parallel
  • the individual layers can slide relative to one another and the fibers within the individual layers can slide relative to one another, as a result of which one
  • a method for producing a structural component having a curved shape is provided. According to this method, a layer structure is first formed from a plurality of layers, the layers each having at least one semi-finished product which is designed as described above. The layers can optionally be on one
  • Connection point which is located in the area of an apex of the arched shape to be produced, can be thermoplastic connected, e.g. by welding, in particular ultrasonic welding. So there is a discrete, e.g. punctiform material connection of the layers of the layer structure is produced at a point at which no or only slight relative movements of the individual layers to one another occur during the forming in order to produce the curved shape.
  • Layer structure in the curved shape at a forming temperature that is less than a melting point of the thermoplastic materials of the semi-finished product. After the forming, the formed layer structure is heated to one
  • thermoplastic materials of the semi-finished product that is, greater than the melting point of the thermoplastic matrix material of the prepreg tapes and greater than the melting point of the thermoplastic material of the connecting strands of the semi-finished product.
  • Cooled solidification temperature which is less than the melting point of the thermoplastic materials of the semi-finished product. Another idea of the invention is therefore to create wrinkles
  • Prevents reinforcement fibers By fixing the layers or layers relative to one another in an area of the layer structure which after the forming contains an apex of the curved shape of the structural component, sliding of the layers to one another in more deformed areas is facilitated.
  • the mechanical strength of the components is improved by reducing the formation of folds. Thanks to the textile structure made of prepreg tapes and
  • Connecting strands which each have one, preferably the same thermoplastic material, can be produced in a very simple and quick manner after the shaping, a large flat component.
  • the prepreg tapes can in particular have a width between 3 mm and 15 mm. In particular, it can also be provided that a width is between 0.001 percent and 5 percent of a length of the prepreg edges.
  • a width is between 0.001 percent and 5 percent of a length of the prepreg edges.
  • Prepreg tapes extend in a first direction and the
  • Connecting strands extend in a second direction running transversely to the first direction, and a first prepreg tape that is outermost in relation to the second direction and an extreme second prepreg tape that is located opposite to the first prepreg tape, in order to form the connecting lines each integrally with the Connecting strands are connected.
  • the connecting lines run along opposite, outermost prepreg bands of the semi-finished textile product. This prevents fraying or disintegration of the semi-finished product, while the sliding of the individual strips relative to one another is prevented as little as possible.
  • the prepreg strips and the connecting strands are woven together. Accordingly, the prepreg tapes run parallel to each other, e.g. in a first direction, and the connecting strands extend transversely to the prepreg bands, e.g. in a second direction, and also run parallel to each other.
  • the prepreg tapes can be provided as warp strands and the connecting strands as weft strands or vice versa. The are optional
  • Connecting strands and the prepreg tapes are woven in an atlas weave, in which the weft strand passes under a warp strand and then over more than two warp strands.
  • Connecting rods offers the particular advantage that within the The reinforcing fibers are approximately parallel to one another. Furthermore, weaving can be carried out automatically in a simple manner.
  • Connecting strands each have a first end section and opposite to this second end section, the first and second end sections each projecting beyond the connecting lines. Accordingly, the connecting strands form protrusions or a kind of tabs which protrude over an edge or edge area of the fabric. These tabs can be used for cohesive coupling to other semi-finished products of the same or similar construction, which facilitates the processing of the semi-finished product.
  • Foil tapes or as threads made of the thermoplastic material are or as threads made of the thermoplastic material. Ribbons, i.e. strands with flat, rectangular cross sections, have a small cross section thickness, so that a very thin semi-finished product can be realized. Threads, i.e. strands with several filaments twisted into an approximately circular cross section, offer the advantage of a larger one
  • the connecting strands are optionally made of thermoplastic
  • Plastic material preferably the thermoplastic matrix material of the prepreg tapes.
  • the connecting strands loosen when the semi-finished product is heated to a temperature greater than the melting temperature of the thermoplastic materials to a certain extent and also improve the cohesion between the reinforcing fibers.
  • the individual layers of the layer structure are each formed from a plurality of semi-finished products in which the connecting strands protrude beyond the connecting lines, as was described above.
  • Prepreg tapes of a respective further semi-finished product thermoplastic bonded.
  • Connecting strands of the further semi-finished product are connected to prepreg tapes of the first semi-finished product in a thermoplastic manner. This makes it easy to produce large flat layers.
  • a welding process e.g. Ultrasonic welding can be used.
  • the layer structure is formed in such a way that the prepreg strips extend in different layers in different directions.
  • the layers are stacked one on top of the other in such a way that the prepreg strips of two adjacent layers or layers each extend in different directions.
  • the reinforcing fibers thus also extend in different layers in different directions, which improves the mechanical strength of the structural component.
  • the layer structure is formed by sequentially stacking the layers on a flat storage surface, and the forming is carried out in a further step, for example in a cavity Molding tool, wherein the cavity is formed by a molded part with a contour surface corresponding to the curved shape of the structural component and a flat contact part.
  • Stacking on a flat surface has the advantage that a large number of layers can be deposited quickly, and the risk of wrinkles is low.
  • the forming takes place in a separate (press) forming step.
  • the layer structure is formed by sequential stacking of the layers on a curved storage surface and thereby simultaneously deformed into the curved shape, whereby the
  • Storage area is formed a contour surface of a molded part of a mold corresponding to the curved shape of the structural component, the molded tool additionally having a flat contact part for forming a cavity with the molded part.
  • Each layer is placed on a curved surface and thereby at least partially already formed into the desired shape. This offers the advantage that the individual layers do not have to slide against one another, or only slide to a small extent, which further reduces the risk of wrinkles. It can optionally be provided that layers of the layer structure deposited on the curved contour surface of the molded part are in addition to those in the area of the
  • connection point located at the apex at further points
  • Connection points are connected thermoplastic. This fixes the layers in their position.
  • the layer structure is heated in the cavity of the molding tool. if the Layers have already been deposited on the molded part, the cavity is first closed by the deposit part, thereby compacting the individual layers.
  • the molded part of the molding tool is designed as a flat, first molded sheet, the contact part being designed as a flat, second molded sheet.
  • the molded part and the plant part are therefore each designed as flat, curved metal plates.
  • the molded parts have a low heat capacity. As a result, the cavity can be heated up quickly and with little energy expenditure.
  • the molded part can also be designed as a partially solid form, e.g. with a surface section, which forms the contour surface, and with a base section, which is designed as a stiffening structure and supports the surface section.
  • a magnetic field is generated to apply the compression pressure by means of a magnetic device, which magnetic field is coupled into a magnetizable material assigned to the first shaped plate and / or into a magnetizable material assigned to the second shaped plate in such a way that the layer structure is subjected to the compression pressure through the shaped plates .
  • a magnetic field directed transversely to the contour surface is generated.
  • the compression pressure is generated by means of a magnetic force which, for example, can act directly on the shaped sheets, e.g. if the first and / or the second shaped sheet is formed from a magnetizable metal material and the magnetizable material is assigned to the respective shaped sheet in this way.
  • the first and / or the second shaped sheet is formed from a magnetizable metal material and the magnetizable material is assigned to the respective shaped sheet in this way.
  • Magnet device also coupled to the mold plates magnetizable elements have as a magnetic material, which press the molded sheets relative to one another by the action of the magnetic field. Due to their planar extent, the shaped sheets allow the formation of a shape extending through the cavity in which the layer structure is located
  • the molding tool for heating and cooling or consolidating is placed on one mold half, the compression pressure being applied by the molding tool during cooling.
  • the mold half can in particular serve as a kind of support for the
  • the mold half can also serve as a heat sink.
  • Molding tool in the cavity of which the layer structure is accommodated, is pressed together between two mold halves adapted to an outer contour of the molding tool. In this way, the final desired curved shape of the structural component can be produced very precisely.
  • Press tool also serves as a heat sink for cooling the layer structure.
  • a heating of the layer composite in the cavity of the mold and one Cooling the layer composite in the cavity of a separate pressing tool speeds up the process and saves energy.
  • the layer structure is heated by inductive heating of the shaped sheets or by means of
  • Infrared radiation Infrared radiation.
  • Inductive heating that is to say heating by generating alternating magnetic fields by means of an alternating electrical voltage, offers the advantage that the shaped plates themselves act as a heating device. This enables the cavity to be heated up efficiently. Infrared radiation can advantageously be generated with little design effort. Since the shaped sheets have a low heat capacity, both heating is by means of
  • Infrared radiation as well as inductive heating of the mold plates are suitable for generating rapid temperature changes in the cavity, which accelerates both the heating and the cooling of the layer structure.
  • a vacuum is created in the cavity of the molding tool.
  • air that may be present between or in the layers of the layer structure becomes from the layer structure
  • the vacuum can be used at least partially to generate the compression pressure or the pressure for forming. This further speeds up the process.
  • a “curved component” or a “curved shape” is generally understood to mean a geometric body that has at least a first one
  • a domed body is understood here to mean an at least partially dome-shaped, spherical, parabolic or bowl-shaped body.
  • a vertex of the arched shape of the component can, for example, by the center of gravity of one of the body forming the arched shape
  • the vertex can be on a
  • directions and axes which relate to the course of physical structures, a course of an axis, a direction or a structure “along” another axis, direction or structure is understood here to mean that these, in particular the tangents resulting in a respective location of the structures at an angle of less than or equal to 45 degrees, preferably less than 30 degrees and
  • a course of an axis, a direction or a structure “transverse” to another axis, direction or structure is understood here to mean that these, in particular, the tangents resulting in a respective location of the structures each run at an angle of greater than or equal to 45 degrees, preferably greater than or equal to 60 degrees and particularly preferably perpendicular to one another.
  • Reinforcing fibers herein may be generally filamentary or filamentary fibers, such as carbon, glass, ceramic, aramid, boron, mineral, natural, or plastic fibers, or mixtures thereof.
  • a “melting point” or a “melting temperature” in relation to a thermoplastic material is understood here to mean a temperature above which the material is in a flowable, viscous state. Above the
  • Melting temperature can be a component made of thermoplastic material with another component made of thermoplastic material, which is also above the
  • Melting temperature is present, cohesively connected, in particular fused.
  • Fig. 1 is a plan view of a semi-finished product according to one
  • Fig. 2 is a plan view of a semi-finished product according to another
  • Fig. 3 is a schematic sectional view of a prepreg tape
  • Fig. 4 is a schematic sectional view of a connecting strand
  • FIG. 5 is a schematic sectional view of a connecting strand
  • Fig. 6 is a plan view of a location for generating a
  • Fig. 7 is a plan view of a location for generating a
  • Fig. 8 is a plan view of the position of Fig. 7 after performing a
  • FIG. 9 shows a schematic exploded view of a layer structure composed of several layers
  • FIG. 10 shows a plan view of a layer structure composed of several layers after the creation of an optional connection point in one step of a method according to an exemplary embodiment of the present invention
  • Fig. 1 1 is a schematic sectional view of a layer structure
  • Fig. 12 is a schematic sectional view of a layer structure from
  • FIG. 13 shows a forming and heating of a layer structure in a cavity of a molding tool in steps of a method according to an exemplary embodiment of the present invention
  • FIG. 16 shows a schematic partial sectional view of a semifinished product according to a further exemplary embodiment of the present invention.
  • FIG. 17 shows a structural component produced by means of a method according to an exemplary embodiment of the present invention.
  • the same reference numerals designate identical or functionally identical components, unless stated otherwise.
  • the figures 1, 2 and 16 each show a semi-finished product 1 for producing a
  • Structural component B As shown in FIGS. 1, 2 and 16, the semifinished product has a multiplicity of prepreg strips 2 and a multiplicity of connecting strands 3.
  • the prepreg tape 2 has a plurality of reinforcing fibers 21 which extend in one direction or unidirectionally.
  • the reinforcing fibers 21 can be present, for example, as fiber bundles.
  • the reinforcing fibers 21 are in one
  • the prepreg tapes 2 are realized as narrow, strip-shaped tapes. As shown in Fig. 3, the prepreg tapes 2 can have a width b2, e.g. in a range between 1 mm and 15 mm, and a length I2, e.g. have in a range between 0.5 m and 100 m.
  • the connecting strands 3 can each consist of a thermoplastic material or have a thermoplastic material.
  • 4 shows, by way of example, a reinforcing strand 3 in cross section, which is realized as a film strip 33 consisting of thermoplastic material 30.
  • the film strip 33 can be realized with a rectangular cross section.
  • 5 shows, by way of example, a reinforcement strand 3 in cross section, which is designed as a thread 34 consisting of thermoplastic material 30.
  • the thread 34 can consist of several twisted filaments 35 may be formed, which form an approximately circular cross section of the thread 34.
  • the reinforcing strands 3 contain the same thermoplastic material that is used as the matrix material of the prepreg tapes.
  • Connecting strands 3 crosses several of the prepreg strips 2.
  • each connecting strand 3 runs in sections on opposite sides of the prepreg strips 2.
  • the prepreg strips 2 run along one another and do not cross one another within the flat structure 4.
  • Fig. 1 are the
  • the prepreg tapes 2 extend in a first direction R1 and the connecting strands 3 extend in a second direction R2 running transverse to the first direction R1.
  • a first prepreg tape 2A which is outermost in relation to the second direction R2 and an extreme second prepreg tape 2B which is situated opposite to the first prepreg tape are integrally connected to the connecting strands 3 in FIG. 1.
  • the connecting strands 3 are in the region of a first end section 31 with the first prepreg tape 2A and in the region of a second end section 32, which is opposite to the first end section 31 with respect to the second direction R2 second prepreg tape 2A integrally connected.
  • the first and the second prepreg tape 2A, 2B each define opposite edges of the textile fabric 4.
  • each of the connecting strands 3 with the first and the second prepreg tape 2A, 2B be integrally connected.
  • the connecting strands 3 and the prepreg strips 2 are integrally connected to one another in a first end region 41 of the flat structure 4 and in a second end region 42 of the flat structure 4 lying opposite this, along a connecting line 5A, 5B.
  • the connecting lines 5A, 5B each run along the first direction R1 or along the first and second prepreg bands 2A, 2B.
  • the cohesive connection can be produced, for example, by ultrasonic welding.
  • first end section 31 of the connecting strands 3 protrudes or projects beyond the first prepreg band 2A and the second end section 32 of the connecting strands 3 extends beyond the second prepreg band 2B and thus, and thus forms a protruding tab.
  • the first end section 31 of the connecting strands 3 protrudes or projects beyond the first prepreg band 2A and the second end section 32 of the connecting strands 3 extends beyond the second prepreg band 2B and thus, and thus forms a protruding tab.
  • the prepreg strips 2 and the connecting strands 3 are intertwined and thereby form a textile, single-layer flat structure 4.
  • the connecting strands 3 run transversely to the prepreg bands 2, each of the
  • Connecting strands 3 crosses several of the prepreg strips 2.
  • each connecting strand 3 runs in sections on opposite sides of the prepreg strips 2.
  • the connecting strands 3 are exemplary as
  • the connecting strands 3 in the area of a first end section 31 and in the area of a second end section 32, which is opposite to the first end section 31 with respect to the second direction R2, are each materially bonded to one of the prepreg strips 2 connected.
  • the connecting strands 3 and the prepreg strips 2 are integrally connected to one another in a first end region 41 of the flat structure 4 and in a second end region 42 of the flat structure 4 lying opposite to this, along a connecting line 5A, 5B.
  • connection lines 5A, 5B each run along intersections of the prepreg strips 2 and the connecting strands 3 and obliquely to a longitudinal extent of the prepreg strips 2 and the connecting strips 3.
  • the integral connection can, for example, by
  • Connection line 5B protrudes and thus forms a protruding tab.
  • the in Figs. 1, 2 semi-finished products 3 shown by way of example allow the prepreg tapes to slide against one another due to their textile structure, thereby reducing the risk of wrinkles when the semi-finished product is deformed.
  • the semi-finished product 1 shown schematically and by way of example in FIG. 16 is constructed in several layers.
  • the prepreg tapes 2 are arranged to form a surface-extending multiaxial fabric 6, which comprises a plurality of layers 60 of prepreg tapes 2 lying one above the other. As shown schematically in FIG. 16, the prepreg strips 2 extend parallel within a respective layer 60 to each other. In adjacent layers 60 the extend
  • Prepreg tapes 2 in different directions, e.g. across from each other. 16 shows only two layers or layers 60 for the sake of simplicity.
  • the individual layers 60 are relative to one another on individual, preferably discrete, e.g. periodically repeating places or stitched at points or
  • a connecting strand 3 can be used to connect the individual layers 60.
  • the connecting strand 3 wraps around, for example, two intersecting prepreg bands 2 at an intersection.
  • the connecting strand 3 is preferably designed as a thread 34.
  • the prepreg strips 2 can slide within one layer 60 and the layers 60 against one another, as a result of which the
  • FIG. 17 shows an example of a curved structural component B in the form of a
  • the structural component B can in particular have a circular peripheral edge E.
  • the structural component can, for example, be dome-shaped or dome-shaped and thus curved in several directions of curvature. 17 is a
  • the apex P of the arched shape of the structural component B is shown, which is given by an intersection of lines of symmetry S1, S2 of the structural component B.
  • a layer structure 100 is first formed, which has a plurality of layers 110 lying one above the other, the layers 110 each containing at least one semifinished product 1, as is exemplified by FIGS. 1, 2 and 16.
  • the layers 1 10 realized as flat mats.
  • the figures 6 to 8 show an example of the production of a single layer 1 10 from several of the semi-finished products 1 shown in FIG thermoplastic or cohesively connected, e.g. by ultrasonic welding.
  • End sections 32 of the connecting strands 3 of the further semifinished product 12 are also thermoplastic bonded to prepreg strips 2 of the first semifinished product 1 1, for example also by ultrasonic welding. As shown in FIG. 6, the first end sections 31 of the connecting strands 3 of the first semifinished product 1 1 overlap the outermost second prepreg band 2B of the second semifinished product 12 and the second end sections 32 of the connecting strands 3 of the first
  • Semi-finished products 12 overlap the outermost first prepreg tape 2A of the first
  • the semifinished product 1 shown in FIG. 2 can be connected in the same way to other such semifinished products 1.
  • FIG. 7 shows a layer 110, which was formed by several semi-finished products 1 as described above.
  • the individual semi-finished products 1 before connecting them to a layer 1 10 each at opposite ends 1A, 1 B.
  • different circumferential shapes of the layers 110 can be generated, for example an approximately circular circumference, as is shown by way of example in FIG.
  • a further cut can be made by the
  • one layer contains 1 10 of the
  • Layer structure 100 a plurality of layers 60 of the semi-finished product 1.
  • the layer structure 100 is generally formed by stacking or depositing a plurality of layers 110 one on top of the other, as exemplified in FIG. 9 in one
  • the layer structure 100 can in particular be designed such that the
  • the prepreg strips 2 extend from mutually adjacent layers 110 of the layer structure 100 in intersecting directions R1 10.
  • the layer structure 100 is shown by way of example in FIG. 1 1, the layer structure 100
  • Storage area 150a are formed.
  • the layer structure 100 can also be formed by stacking the layers 110 on a curved storage surface 150a are as shown schematically in Fig. 12. In the latter case, due to the slack nature of the textile fabric 4 or the multiaxial scrim 6, there is at least partial deformation of the individual layers 110 in accordance with the curved storage surface 150a. The arched
  • Storage surface 150a can be provided, for example, by a contour surface 210a of a molding tool 200 which corresponds to the curved shape of structural component B.
  • the molding tool 200 is explained in detail below.
  • the layers 110 are optionally thermoplastic bonded, for example in the region of the vertex P of the arched shape to be produced, at a connection point 120, e.g. by ultrasonic welding.
  • the connection point is selected such that no or only a very slight displacement of the layers 110 relative to one another is necessary in the corresponding region during the subsequent deformation.
  • there is optionally also a thermoplastic connection at further connection points 121 away from the apex P e.g. also by
  • Ultrasonic welding. 10 is a schematic plan view of a
  • Layer structure 100 shown which is formed from layers 1 10 with a circular circumference.
  • the connection point 120 is formed with respect to a radial direction in the area of the center. This is the area that the
  • the layer structure 100 is deformed into the curved shape.
  • This forming step takes place at a forming temperature which is lower than a melting point of the thermoplastic materials 20, 30 des Semifinished product 1.
  • the forming temperature is thus less than a melting point of the matrix material 20 of the prepreg strips 2 and less than a melting point of the thermoplastic material 30 of the connecting strands 3.
  • the prepreg strips 2 and the reinforcing strands 3 of the semifinished products 1 contained in the layers 110 are in one solid state, which reduces the friction or the viscous adhesion between and within the layers 1 10.
  • the reinforcing fibers within the individual prepreg bands are still supported by solid matrix material, so that the fibers are better protected from dents even in the event of a pressure load in the longitudinal direction of the fibers due to the forming process. This prevents the formation of wrinkles, waviness or undulations in the fiber layers.
  • Forming can take place, for example, in a cavity 205 of a molding tool 200, as is shown schematically in FIG. 13.
  • the molding tool 200 has a molded part 210 with a contour surface 210a corresponding to the curved shape of the structural component B and an abutment part 220.
  • the contact part 220 and the molded part 210 can be positioned relative to one another in a closed position, as is shown by way of example in FIG. 13.
  • a cavity 205 is formed between the contour surface 210a and an inner surface 220a of the contact part 220.
  • a seal 215 can be arranged between the contact part 220 and the molded part 210, which seals the cavity 205 hermetically in the closed position of the molding tool 200.
  • the molded part 210 can be designed as a flatly extending first molded sheet 21 1 and the contact part 220 as a flatly extending second molded sheet 221.
  • the inner surface 220a of the plant part 220 can correspond to the shape of the Structural component B or complementary to the contour surface 210a of the molded part 210.
  • the shaped part 210 and the abutment part 220 are subjected to a force F such that the Layer structure 100 is pressed between molded part 210 and plant part 220.
  • the force F can be generated, for example, by creating a vacuum in the cavity 205 of the molding tool 200 by means of a fluidically conductive to the cavity 205
  • coupled evacuation device or pump 230 can be applied, as shown in FIG. 13 as an example. At the same time, this ensures that 100 air pockets possibly present in the layer structure are removed or reduced.
  • the force F can also be generated by generating a magnetic field which is coupled into a magnetizable material assigned to the first shaped plate 21 1 and / or into a magnetizable material assigned to the second shaped plate 221 in such a way that the layer structure is formed by the compression pressure is applied to the mold plates.
  • the first and / or the second shaped plate 21 1, 221 and / or a substructure, such as the mold half 310 is formed from a magnetizable metal material and a magnetic field is generated which the first and the second shaped plate 21 1, 221 contracts or compresses relative to each other.
  • the magnetizable material is assigned to the shaped sheets 21 1, 221 in that they are themselves formed from or contain a magnetizable material.
  • the first mold plates 21 1 can be magnetized Material can also be assigned in that the mold half 310 is formed from or has a magnetizable material.
  • a magnetic device 240 can be provided with a plurality of electrical induction coils 241, which are distributed along the contour surface 210 a of the molded part 210. Instead of electrical induction coils 241, permanent magnets (not shown) can also be provided. In general, the magnetic device 240 can be set up to generate a magnetic field
  • Induction coils 241 are referred to as magnetic field generators, the features disclosed for this also apply in an analogous manner to other magnetic field generators.
  • the magnet device 240 can be located in the substructure of the mold half 310 or, for example, on the other side, above the upper mold plate 221.
  • the magnet device 240 can be at least partially flexible or articulated have designed support structure which is coupled to the second shaped plate 221, so that the induction elements 241 are flexibly connected to one another and can adapt to the shaped plate 221 in order to transmit the pressure as uniformly as possible.
  • the magnet device 240 is in particular set up to generate a magnetic field directed transversely to the contour surface 210a.
  • the reinforcement profiles 130 can, for example, have a double-T-shaped cross section, as is shown schematically in FIG. 13, and also have a thermoplastic material.
  • the reinforcement profiles 130 can be formed from a fiber-reinforced thermoplastic material be.
  • the molding tool 200 is then brought into the closed position, as shown in FIG. 13.
  • the contact part 220 or the second shaped plate 221 is provided with recesses 223 through which a web of the reinforcing profile 223 extends.
  • the second shaped plate 221 can be formed, for example, in two parts, a first part having the recesses 223 in the form of slots which are open on one side and are closed by a second part.
  • the stiffening profiles 130 can also be inserted into enveloping bulges or depressions (not shown) of the second shaped plate 221 or of the contact part 220. This improves the tightness of the cavity 205.
  • the stiffening profile 130 can generally be pressed against the layer structure 100 in the cavity 205 by means of the contact part 220.
  • the formed layer structure 100 is heated to a temperature which is greater than the melting point of the thermoplastic materials 20, 30 of the semifinished product 1.
  • the thermoplastic matrix material 20 of the prepreg strips 2 and the thermoplastic material 30 of the connecting strands 3 are melted, as a result of which the individual layers 110 of the layer structure 100 fuse with one another and are thereby connected.
  • the optional stiffening profiles 130 are thereby also fused to the uppermost layer 110.
  • the heating is preferably carried out in the cavity 205 of the molding tool 200.
  • a vacuum is also created in the cavity 205 by means of the pump 205.
  • a heater 250 can be used to heat the cavity 205
  • heater 250 is exemplified as one
  • Induction heater 252 executed which one or more
  • Induction coils 253 has in at least one of the shaped plates 21 1, 221 to induce an alternating magnetic field, which inductively heats the shaped plate 21 1, 221, so that the cavity 205 is heated. 13 is the
  • the first shaped sheet 21 1 is preferably excited thereby, so that the layer structure 100 heats up from this and the optional ones
  • Stiffening profiles 130 are primarily heated in the area in which they rest on the layer structure 100.
  • the heating device 250 is exemplified as an infrared radiator 251
  • a further infrared radiator (not shown) can optionally be arranged on the part of the molded part 210.
  • the infrared radiator 251 is used to generate
  • Heat radiation is set up to heat the cavity 205.
  • an induction heating device 252 can also be provided in FIG. 15, as was explained with reference to FIG. 13. It is also conceivable that the
  • Magnetic device 240 which is provided per se for applying the compression pressure, is also used as a heating device. For this purpose, it can be provided that a direct current flows through the induction coils 241 to generate the direct magnetic field for applying the compression pressure and an alternating current flows through the cavity 205 for heating.
  • the molding tool 200 can be placed on a mold half 310 during the heating, as is shown by way of example in FIG. 15.
  • the mold half 310 can have a mold surface 310a, which
  • Molding tool 200 may be shaped.
  • an insulation layer 31 1 between the mold surface 310a of the mold half 310 and the rear surface is advantageous 210b of the molded part 210 arranged to largely avoid heating the mold half 310.
  • the mold half 310 serves in particular as a support for the molding tool 200.
  • the molding plates 21 1, 221 can thus be made relatively thin. This speeds up the heating of the cavity 205 and reduces the tool costs.
  • the magnet device 240 can be integrated into the mold half 310, for example.
  • a further process step a
  • Compression pressure is a consolidation of the layer structure 100 by cooling to a solidification temperature that is less than the melting point of the
  • the layer structure 100 cools down or heat is removed from the
  • thermoplastic material 20, 30 solidifies and the structural component B is formed.
  • the consolidation can also take place in the cavity 205 of the molding tool 200.
  • the heating device 250 is switched off and / or the molding tool 205 and the heating device 250 are spatially separated from one another. As shown by way of example in FIG. 15, the consolidation or
  • the compression pressure can be generated by the vacuum device 205 and / or by the magnet device 240.
  • compression pressure 200 can be applied by molding tool 200.
  • the molding tool 200 for consolidation or cooling can be formed in one by two mold halves 310, 320 of a pressing tool 300 Cavity 305 arranged and the compression pressure can be applied through the mold halves 310, 320, as shown schematically in Fig. 14.
  • the pressing tool 300 shown by way of example in FIG. 14 has a first mold half 310 and a second mold half 320.
  • the first mold half 310 can be designed analogously to the mold half described with reference to FIG. 15 with a first mold surface 310a.
  • the second molding surface 320 has a second molding surface 320a which is designed to correspond to an outer surface 220b of the contact part 220.
  • the mold halves 310, 320 can be moved relative to one another between an open position and a closed position by means of a movement device 330, for example in the form of a hydraulic drive.
  • Fig. 14 shows that
  • Press tool 300 in a closed position or position in which the second mold surface 320a faces the first mold surface 310a and the
  • Mold halves 310, 320 or the mold surfaces 310a, 320a of the mold halves 310, 320 define the cavity 305.
  • the mold halves 310, 320 press the molded part 210 and the contact part 220 and thus the layer structure 100, which is located in the cavity 205 of the molding tool 200, together.
  • the compression pressure is thus applied by the pressing tool 300.
  • Cavity 305 of the pressing tool 300 and / or the cavity 205 of the molding tool 200 can be evacuated. If the layer structure 100 together with the
  • the cavity 205 of the forming tool 200 can optionally be evacuated before being inserted into the cavity 305 of the pressing tool 300, which facilitates the holding together of the layer structure 100 and the form plates 21 1, 221 and in the layer structure 100 beforehand air is removed before melting.
  • the mold halves 310, 320 have when consolidating or cooling the
  • Layer structure 100 has a temperature that is lower than the melting temperature of the thermoplastic materials 20, 30.
  • the mold halves 310, 320 form heat sinks, which accelerates the cooling of the cavity 205.
  • the cooling can be further accelerated in that the mold halves 310, 320 from one
  • the heat capacity of the mold halves 310, 320 is advantageously a multiple, e.g. ten times the heat capacity of the mold plates 21 1, 212 of the mold 200.
  • thermoplastic matrix material 20 thermoplastic matrix material

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  • Engineering & Computer Science (AREA)
  • Textile Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • Health & Medical Sciences (AREA)
  • Composite Materials (AREA)
  • Materials Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Polymers & Plastics (AREA)
  • Organic Chemistry (AREA)
  • Medicinal Chemistry (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Manufacturing & Machinery (AREA)
  • Electromagnetism (AREA)
  • Toxicology (AREA)
  • Oral & Maxillofacial Surgery (AREA)
  • Thermal Sciences (AREA)
  • Moulding By Coating Moulds (AREA)

Abstract

La présente invention concerne un produit semi-fini (1) destiné à la fabrication d'un composant structural (B) comprenant une pluralité de bandes préimprégnées (2), lesquelles possèdent respectivement des fibres de renforcement (21) disposées de manière unidirectionnelle et enrobées dans un matériau matriciel thermoplastique (20), et une pluralité de brins de liaison (3) contenant une matière thermoplastique (30). Les bandes de préimprégnés (2) et les brins de liaison (3) sont soit reliés pour former un produit plat textile (4), soit les bandes de préimprégnés (2) sont disposées pour former un non-tissé multiaxial (6), les couches individuelles (60) du non-tissé (6) étant reliées par les brins de liaison (3). L'invention concerne en outre un procédé de fabrication d'un composant structural (B) courbe à partir d'un tel produit semi-fini (1).
EP19779842.4A 2018-10-04 2019-09-26 Produit semi-fini et procédé de fabrication d'un composant structural Pending EP3860835A2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102018217018.5A DE102018217018A1 (de) 2018-10-04 2018-10-04 Halbzeug und verfahren zur herstellung eines strukturbauteils
PCT/EP2019/076079 WO2020069978A2 (fr) 2018-10-04 2019-09-26 Produit semi-fini et procédé de fabrication d'un composant structural

Publications (1)

Publication Number Publication Date
EP3860835A2 true EP3860835A2 (fr) 2021-08-11

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Application Number Title Priority Date Filing Date
EP19779842.4A Pending EP3860835A2 (fr) 2018-10-04 2019-09-26 Produit semi-fini et procédé de fabrication d'un composant structural

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US (1) US20210370620A1 (fr)
EP (1) EP3860835A2 (fr)
DE (1) DE102018217018A1 (fr)
WO (1) WO2020069978A2 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2013036848A1 (fr) * 2011-09-09 2013-03-14 Nicolon Corporation, doing business as TenCate Geosynthetics North America Tissu multiaxial
EP3812118B1 (fr) 2018-06-20 2023-07-26 Mitsubishi Chemical Corporation Feuille préimprégnée et son procédé de fabrication, article moulé en matériau composite renforcé de fibres et son procédé de fabrication, et procédé de fabrication d'une préforme
CN116017908A (zh) * 2022-08-03 2023-04-25 上海敏博锐传感器有限公司 防水器件半成品以及防水器件成品

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US5808281A (en) * 1991-04-05 1998-09-15 The Boeing Company Multilayer susceptors for achieving thermal uniformity in induction processing of organic matrix composites or metals
US5591369A (en) 1991-04-05 1997-01-07 The Boeing Company Method and apparatus for consolidating organic matrix composites using induction heating
US5633074A (en) * 1993-06-07 1997-05-27 Yamaha Corporation Prepreg available for fiber reinforced thermoplastic resin and process of producing sporting goods using the same
US5952067A (en) * 1996-12-02 1999-09-14 A&P Technology, Inc. Braided structure having uncrimped strands
US6846548B2 (en) * 1999-02-19 2005-01-25 Honeywell International Inc. Flexible fabric from fibrous web and discontinuous domain matrix
DE19910201A1 (de) * 1999-03-09 2000-09-14 Richard Pott Kettfaden-Faserschicht
EP1321282B1 (fr) * 2001-12-20 2004-06-30 epo GmbH Prepreg
US6979807B2 (en) 2003-08-13 2005-12-27 The Boeing Company Forming apparatus and method
US20080260954A1 (en) * 2005-10-11 2008-10-23 Rowan Johnson Paton Method of Binding Dry Reinforcement Fibres
JP2008240667A (ja) * 2007-03-28 2008-10-09 Fujitsu General Ltd ロータリ圧縮機
DE102010050740B4 (de) 2010-11-08 2012-12-06 Airbus Operations Gmbh Verfahren und Vorrichtung zur Herstellung eines Flugzeugstrukturbauteils
JP6757581B2 (ja) * 2016-03-24 2020-09-23 美津濃株式会社 繊維強化部材
EP3251821B1 (fr) * 2016-06-03 2019-03-13 Airbus Operations GmbH Presse pour composant, en particulier de consolidation thermoplastique et/ou presse de formage et procédé de pressage d'un tel composant
TR201618336A2 (tr) * 2016-12-12 2018-06-21 Kordsa Teknik Tekstil As Sabi̇tlenmi̇ş güçlendi̇ri̇ci̇ teksti̇l kumaş ve bunun üreti̇m yöntemi̇
DE102018217017A1 (de) * 2018-10-04 2020-04-09 Premium Aerotec Gmbh Verfahren zur herstellung eines strukturbauteils

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US20210370620A1 (en) 2021-12-02
DE102018217018A1 (de) 2020-04-09
WO2020069978A2 (fr) 2020-04-09
WO2020069978A3 (fr) 2020-05-28

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