FR3009515A1 - THERMOFORMED COMPOSITE STRUCTURE AND METHOD OF MANUFACTURING THE SAME - Google Patents

THERMOFORMED COMPOSITE STRUCTURE AND METHOD OF MANUFACTURING THE SAME Download PDF

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Publication number
FR3009515A1
FR3009515A1 FR1357862A FR1357862A FR3009515A1 FR 3009515 A1 FR3009515 A1 FR 3009515A1 FR 1357862 A FR1357862 A FR 1357862A FR 1357862 A FR1357862 A FR 1357862A FR 3009515 A1 FR3009515 A1 FR 3009515A1
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FR
France
Prior art keywords
composite structure
plate
upper plate
lower plate
plates
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.)
Granted
Application number
FR1357862A
Other languages
French (fr)
Other versions
FR3009515B1 (en
Inventor
Magalie Menard
Didier Imbert
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.)
Flex N Gate France SAS
Original Assignee
Faurecia Bloc Avant SAS
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Filing date
Publication date
Application filed by Faurecia Bloc Avant SAS filed Critical Faurecia Bloc Avant SAS
Priority to FR1357862A priority Critical patent/FR3009515B1/en
Publication of FR3009515A1 publication Critical patent/FR3009515A1/en
Application granted granted Critical
Publication of FR3009515B1 publication Critical patent/FR3009515B1/en
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
    • B29C65/56—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using mechanical means or mechanical connections, e.g. form-fits
    • B29C65/562—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using mechanical means or mechanical connections, e.g. form-fits using extra joining elements, i.e. which are not integral with the parts to be joined
    • 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
    • B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
    • B29C65/02—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor by heating, with or without pressure
    • B29C65/10—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor by heating, with or without pressure using hot gases (e.g. combustion gases) or flames coming in contact with at least one of the parts to be joined
    • B29C65/103—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor by heating, with or without pressure using hot gases (e.g. combustion gases) or flames coming in contact with at least one of the parts to be joined direct heating both surfaces to be joined
    • 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
    • B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
    • B29C65/02—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor by heating, with or without pressure
    • B29C65/14—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor by heating, with or without pressure using wave energy, i.e. electromagnetic radiation, or particle radiation
    • B29C65/1429—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor by heating, with or without pressure using wave energy, i.e. electromagnetic radiation, or particle radiation characterised by the way of heating the interface
    • B29C65/1432—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor by heating, with or without pressure using wave energy, i.e. electromagnetic radiation, or particle radiation characterised by the way of heating the interface direct heating of the surfaces to be joined
    • 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
    • B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
    • B29C65/02—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor by heating, with or without pressure
    • B29C65/14—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor by heating, with or without pressure using wave energy, i.e. electromagnetic radiation, or particle radiation
    • B29C65/1429—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor by heating, with or without pressure using wave energy, i.e. electromagnetic radiation, or particle radiation characterised by the way of heating the interface
    • B29C65/1445—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor by heating, with or without pressure using wave energy, i.e. electromagnetic radiation, or particle radiation characterised by the way of heating the interface heating both sides of the joint
    • 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
    • B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
    • B29C65/56—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using mechanical means or mechanical connections, e.g. form-fits
    • 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
    • B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
    • B29C65/72—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor by combined operations or combined techniques, e.g. welding and stitching
    • 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
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/01—General aspects dealing with the joint area or with the area to be joined
    • B29C66/05—Particular design of joint configurations
    • B29C66/10—Particular design of joint configurations particular design of the joint cross-sections
    • B29C66/11—Joint cross-sections comprising a single joint-segment, i.e. one of the parts to be joined comprising a single joint-segment in the joint cross-section
    • B29C66/112—Single lapped joints
    • B29C66/1122—Single lap to lap joints, i.e. overlap joints
    • 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
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/01—General aspects dealing with the joint area or with the area to be joined
    • B29C66/05—Particular design of joint configurations
    • B29C66/20—Particular design of joint configurations particular design of the joint lines, e.g. of the weld lines
    • B29C66/21—Particular design of joint configurations particular design of the joint lines, e.g. of the weld lines said joint lines being formed by a single dot or dash or by several dots or dashes, i.e. spot joining or spot 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
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/01—General aspects dealing with the joint area or with the area to be joined
    • B29C66/05—Particular design of joint configurations
    • B29C66/303—Particular design of joint configurations the joint involving an anchoring effect
    • 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
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/01—General aspects dealing with the joint area or with the area to be joined
    • B29C66/05—Particular design of joint configurations
    • B29C66/303—Particular design of joint configurations the joint involving an anchoring effect
    • B29C66/3034—Particular design of joint configurations the joint involving an anchoring effect making use of additional elements, e.g. meshes
    • 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
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/40—General aspects of joining substantially flat articles, e.g. plates, sheets or web-like materials; Making flat seams in tubular or hollow articles; Joining single elements to substantially flat surfaces
    • B29C66/41—Joining substantially flat articles ; Making flat seams in tubular or hollow articles
    • B29C66/43—Joining a relatively small portion of the surface of said articles
    • B29C66/434—Joining substantially flat articles for forming corner connections, fork connections or cross connections
    • B29C66/4342—Joining substantially flat articles for forming corner connections, e.g. for making V-shaped pieces
    • B29C66/43421—Joining substantially flat articles for forming corner connections, e.g. for making V-shaped pieces with a right angle, e.g. for making L-shaped pieces
    • 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
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/40—General aspects of joining substantially flat articles, e.g. plates, sheets or web-like materials; Making flat seams in tubular or hollow articles; Joining single elements to substantially flat surfaces
    • B29C66/41—Joining substantially flat articles ; Making flat seams in tubular or hollow articles
    • B29C66/45—Joining of substantially the whole surface of the 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
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/72—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined
    • B29C66/721—Fibre-reinforced materials
    • B29C66/7212—Fibre-reinforced materials characterised by the composition of the fibres
    • 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
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/72—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined
    • B29C66/721—Fibre-reinforced materials
    • B29C66/7214—Fibre-reinforced materials characterised by the length of the fibres
    • B29C66/72141—Fibres of continuous length
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/73—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset
    • B29C66/739—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset characterised by the material of the parts to be joined being a thermoplastic or a thermoset
    • B29C66/7392—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset characterised by the material of the parts to be joined being a thermoplastic or a thermoset characterised by the material of at least one of the parts being a thermoplastic
    • B29C66/73921—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset characterised by the material of the parts to be joined being a thermoplastic or a thermoset characterised by the material of at least one of the parts being a thermoplastic characterised by the materials of both parts being thermoplastics
    • 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
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/80—General aspects of machine operations or constructions and parts thereof
    • B29C66/81—General aspects of the pressing elements, i.e. the elements applying pressure on the parts to be joined in the area to be joined, e.g. the welding jaws or clamps
    • B29C66/814—General aspects of the pressing elements, i.e. the elements applying pressure on the parts to be joined in the area to be joined, e.g. the welding jaws or clamps characterised by the design of the pressing elements, e.g. of the welding jaws or clamps
    • B29C66/8141—General aspects of the pressing elements, i.e. the elements applying pressure on the parts to be joined in the area to be joined, e.g. the welding jaws or clamps characterised by the design of the pressing elements, e.g. of the welding jaws or clamps characterised by the surface geometry of the part of the pressing elements, e.g. welding jaws or clamps, coming into contact with the parts to be joined
    • B29C66/81411—General aspects of the pressing elements, i.e. the elements applying pressure on the parts to be joined in the area to be joined, e.g. the welding jaws or clamps characterised by the design of the pressing elements, e.g. of the welding jaws or clamps characterised by the surface geometry of the part of the pressing elements, e.g. welding jaws or clamps, coming into contact with the parts to be joined characterised by its cross-section, e.g. transversal or longitudinal, being non-flat
    • B29C66/81415—General aspects of the pressing elements, i.e. the elements applying pressure on the parts to be joined in the area to be joined, e.g. the welding jaws or clamps characterised by the design of the pressing elements, e.g. of the welding jaws or clamps characterised by the surface geometry of the part of the pressing elements, e.g. welding jaws or clamps, coming into contact with the parts to be joined characterised by its cross-section, e.g. transversal or longitudinal, being non-flat being bevelled
    • B29C66/81419—General aspects of the pressing elements, i.e. the elements applying pressure on the parts to be joined in the area to be joined, e.g. the welding jaws or clamps characterised by the design of the pressing elements, e.g. of the welding jaws or clamps characterised by the surface geometry of the part of the pressing elements, e.g. welding jaws or clamps, coming into contact with the parts to be joined characterised by its cross-section, e.g. transversal or longitudinal, being non-flat being bevelled and flat
    • 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
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/80—General aspects of machine operations or constructions and parts thereof
    • B29C66/81—General aspects of the pressing elements, i.e. the elements applying pressure on the parts to be joined in the area to be joined, e.g. the welding jaws or clamps
    • B29C66/814—General aspects of the pressing elements, i.e. the elements applying pressure on the parts to be joined in the area to be joined, e.g. the welding jaws or clamps characterised by the design of the pressing elements, e.g. of the welding jaws or clamps
    • B29C66/8141—General aspects of the pressing elements, i.e. the elements applying pressure on the parts to be joined in the area to be joined, e.g. the welding jaws or clamps characterised by the design of the pressing elements, e.g. of the welding jaws or clamps characterised by the surface geometry of the part of the pressing elements, e.g. welding jaws or clamps, coming into contact with the parts to be joined
    • B29C66/81427—General aspects of the pressing elements, i.e. the elements applying pressure on the parts to be joined in the area to be joined, e.g. the welding jaws or clamps characterised by the design of the pressing elements, e.g. of the welding jaws or clamps characterised by the surface geometry of the part of the pressing elements, e.g. welding jaws or clamps, coming into contact with the parts to be joined comprising a single ridge, e.g. for making a weakening line; comprising a single tooth
    • 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
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/80—General aspects of machine operations or constructions and parts thereof
    • B29C66/81—General aspects of the pressing elements, i.e. the elements applying pressure on the parts to be joined in the area to be joined, e.g. the welding jaws or clamps
    • B29C66/814—General aspects of the pressing elements, i.e. the elements applying pressure on the parts to be joined in the area to be joined, e.g. the welding jaws or clamps characterised by the design of the pressing elements, e.g. of the welding jaws or clamps
    • B29C66/8141—General aspects of the pressing elements, i.e. the elements applying pressure on the parts to be joined in the area to be joined, e.g. the welding jaws or clamps characterised by the design of the pressing elements, e.g. of the welding jaws or clamps characterised by the surface geometry of the part of the pressing elements, e.g. welding jaws or clamps, coming into contact with the parts to be joined
    • B29C66/81427—General aspects of the pressing elements, i.e. the elements applying pressure on the parts to be joined in the area to be joined, e.g. the welding jaws or clamps characterised by the design of the pressing elements, e.g. of the welding jaws or clamps characterised by the surface geometry of the part of the pressing elements, e.g. welding jaws or clamps, coming into contact with the parts to be joined comprising a single ridge, e.g. for making a weakening line; comprising a single tooth
    • B29C66/81429—General aspects of the pressing elements, i.e. the elements applying pressure on the parts to be joined in the area to be joined, e.g. the welding jaws or clamps characterised by the design of the pressing elements, e.g. of the welding jaws or clamps characterised by the surface geometry of the part of the pressing elements, e.g. welding jaws or clamps, coming into contact with the parts to be joined comprising a single ridge, e.g. for making a weakening line; comprising a single tooth comprising a single tooth
    • 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
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/80—General aspects of machine operations or constructions and parts thereof
    • B29C66/83—General aspects of machine operations or constructions and parts thereof characterised by the movement of the joining or pressing tools
    • B29C66/832—Reciprocating joining or pressing tools
    • B29C66/8322—Joining or pressing tools reciprocating along one axis
    • B29C66/83221—Joining or pressing tools reciprocating along one axis cooperating reciprocating tools, each tool reciprocating along one axis
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
    • B29C70/34—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
    • B29C70/345—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation using matched moulds
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
    • B29L2031/00—Other particular articles
    • B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
    • B29L2031/3055—Cars

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Health & Medical Sciences (AREA)
  • Electromagnetism (AREA)
  • Toxicology (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Laminated Bodies (AREA)

Abstract

La structure composite renforcée (2; 202; 302) comprend une plaque supérieure (4 ; 204 ; 304 ; 404) et une plaque inférieure (5 ; 205 ; 305 ; 406), la plaque supérieure étant réalisée en un matériau composite comportant une matrice thermoplastique (8 ; 308 ; 408) et des fibres continues (10 ; 310 ; 410), la plaque inférieure étant réalisée en un matériau composite comportant une matrice thermoplastique et des fibres continues, une partie de la plaque supérieure étant fixée sur une partie de la plaque inférieure par thermocompression. La structure composite comprend au moins une zone dans laquelle la plaque supérieure est partiellement enchâssée dans la plaque inférieure.The reinforced composite structure (2; 202; 302) comprises an upper plate (4; 204; 304; 404) and a lower plate (5; 205; 305; 406), the upper plate being made of a composite material comprising a matrix thermoplastic (8; 308; 408) and continuous fibers (10; 310; 410), the lower plate being made of a composite material comprising a thermoplastic matrix and continuous fibers, a part of the upper plate being attached to a portion of the lower plate by thermocompression. The composite structure comprises at least one zone in which the upper plate is partially embedded in the lower plate.

Description

Structure composite thermoformée et son procédé de fabrication La présente invention concerne une structure composite renforcée comprenant au moins une plaque supérieure et une plaque inférieure, la plaque supérieure étant réalisée en un matériau composite comportant une matrice thermoplastique et des fibres continues, la plaque inférieure étant réalisée en un matériau composite comportant une matrice thermoplastique et des fibres continues, une partie de la plaque supérieure étant fixée sur une partie de la plaque inférieure par thermocompression. La présente invention concerne également un procédé de fabrication d'une telle structure composite renforcée.The present invention relates to a reinforced composite structure comprising at least one upper plate and one lower plate, the upper plate being made of a composite material comprising a thermoplastic matrix and continuous fibers, the lower plate being made in a composite material comprising a thermoplastic matrix and continuous fibers, a portion of the upper plate being fixed to a portion of the lower plate by thermocompression. The present invention also relates to a method of manufacturing such a reinforced composite structure.

L'invention s'applique en particulier dans l'industrie automobile, dans la fabrication des pièces composites obtenues par thermocompression de deux plaques réalisées en un matériau composite comprenant une matrice en résine thermoplastique et des fibres continues. Or, si les plaques renforcées de fibres de verre utilisées sont chacune mécaniquement résistantes, l'association par thermocompression de deux telles plaques conduit à la fabrication d'une structure composite présentant une résistance mécanique équivalente uniquement à celle de la résine thermoplastique. Effectivement, lors de l'étape de thermocompression, les résines des deux plaques ne fusionnent qu'en surface car les matériaux utilisés ne sont pas prévus pour fluer d'une plaque à l'autre par atteinte d'une fluidité suffisante. Ainsi, une telle structure n'est pas appropriée pour supporter de fortes contraintes. L'invention vise ainsi à proposer une structure composite utilisant les mêmes matériaux et dont la résistance mécanique de l'assemblage est augmentée. A cet effet, l'invention a pour objet une structure composite renforcée du type précité dans laquelle la structure composite comprend au moins une zone dans laquelle la plaque supérieure est partiellement enchâssée dans la plaque inférieure. Suivant d'autres aspects avantageux de l'invention, la structure composite comporte l'une ou plusieurs des caractéristiques suivantes, prise(s) isolément ou suivant toutes les combinaisons techniquement possibles : - la structure composite renforcée comprend au moins un renfoncement comportant une portion de la plaque supérieure et une portion associée de la plaque inférieure compressées ensembles, ladite portion associée de la plaque inférieure étant en regard de ladite portion de la plaque supérieure ; - la structure composite renforcée comprend au moins un rivet inséré dans le renfoncement ; - les fibres continues de la plaque supérieure sont partiellement insérées dans la matrice thermoplastique de la plaque inférieure ; - les fibres continues de la plaque inférieure sont partiellement insérées dans la matrice thermoplastique de la plaque supérieure ; et - les fibres continues des plaques supérieure et inférieure sont des tissés de fibres de verre.The invention applies in particular in the automotive industry, in the manufacture of composite parts obtained by thermocompression of two plates made of a composite material comprising a thermoplastic resin matrix and continuous fibers. However, if the glass fiber reinforced plates used are each mechanically resistant, the combination by thermocompression of two such plates leads to the manufacture of a composite structure having a mechanical strength equivalent only to that of the thermoplastic resin. Indeed, during the thermocompression step, the resins of the two plates merge only on the surface because the materials used are not intended to flow from one plate to another by achieving sufficient fluidity. Thus, such a structure is not appropriate to withstand strong constraints. The invention thus aims to provide a composite structure using the same materials and whose mechanical strength of the assembly is increased. For this purpose, the subject of the invention is a reinforced composite structure of the aforementioned type in which the composite structure comprises at least one zone in which the upper plate is partially embedded in the lower plate. According to other advantageous aspects of the invention, the composite structure comprises one or more of the following characteristics, taken in isolation or in any technically possible combination: the reinforced composite structure comprises at least one recess comprising a portion the upper plate and an associated portion of the lower plate compressed together, said associated portion of the lower plate facing said portion of the upper plate; the reinforced composite structure comprises at least one rivet inserted into the recess; the continuous fibers of the upper plate are partially inserted into the thermoplastic matrix of the lower plate; the continuous fibers of the lower plate are partially inserted into the thermoplastic matrix of the upper plate; and the continuous fibers of the upper and lower plates are glass fiber woven fabrics.

L'invention a également pour objet un procédé de fabrication d'une structure composite renforcée, telle que définie ci-dessus, le procédé comportant l'une ou plusieurs des caractéristiques suivantes, prise(s) isolément ou suivant toutes les combinaisons techniquement possibles : . fourniture de d'une plaque supérieure et d'une plaque inférieure, les deux plaques supérieure et inférieure étant réalisées en des matériaux composites thermoplastiques à fibres continues, . thermocompression d'une partie de la plaque supérieure sur une partie de la plaque inférieure, l'ensemble formant la structure composite, . renforcement de la structure composite, . l'étape de thermocompression et l'étape de renforcement sont réalisées en même temps ; - au cours de l'étape de thermocompression, une partie des fibres de la plaque supérieure, respectivement inférieure, sont aiguilletées dans une partie de la plaque inférieure, respectivement supérieure ; - l'étape de thermocompression comprend les étapes suivantes : . chauffage des plaques supérieure et inférieure par rayonnement ou air chaud . positionnement de la plaque supérieure au-dessus de la plaque inférieure, les deux plaques étant positionnées entre un moule et un contre-moule comprenant au moins un poinçon de renfoncement, . moulage par enfoncement du contre-moule à l'intérieur du moule. - le procédé de fabrication comprend une étape de rivetage des plaques supérieure et inférieure dans laquelle un rivet est inséré dans le renfoncement. L'invention sera mieux comprise à la lecture de la description détaillée qui va suivre, donnée uniquement à titre d'exemple, faite en référence aux dessins annexés sur lesquels : - la figure 1 est une vue en coupe d'une première structure composite selon l'invention, - la figure 2 est une vue en coupe d'une variante de la première structure composite selon l'invention, - la figure 3 est une vue en coupe d'une deuxième structure composite selon l'invention, - la figure 4 est une vue en coupe d'une troisième structure composite selon l'invention, - les figures 5 à 8 sont des vues schématiques en coupe des étapes du procédé de fabrication d'une structure composite selon l'invention, - les figures 9 et 10 sont des vues schématiques en coupe des étapes du procédé de fabrication selon une variante de l'invention, et - la figure 11 est une vue du dessus de la structure composite selon l'invention. Une première structure composite renforcée 2 est illustrée par les figures 1 et 2. La structure composite 2 est destinée à être utilisée dans la fabrication de pièces automobiles comportant des liaisons entre deux plaques réalisées en matériaux composites. La structure composite 2 comprend une plaque supérieure 4 thermocompressée sur une plaque inférieure 5, c'est-à-dire fixée à celle-ci au moins par thermocompression. La structure composite 2 se divise en une première zone I appelée renfoncement, comprise entre un premier plan A et un deuxième plan B, le plan B étant parallèle au plan A, et une seconde zone II située à l'extérieur des plans A et B. Dans le renfoncement I, la somme des densités des plaques supérieure 4 et inférieure 5 est plus élevée que la somme des densités des plaques supérieure 4 et inférieure 5 situées dans la seconde zone II. Autrement dit, dans le renfoncement I, la plaque supérieure 4 est enchâssée dans la plaque inférieure 5. Par « enchâssé », on doit comprendre que la plaque supérieure 4 est mise en forme de façon à ce qu'elle soit partiellement dans la plaque inférieure 5. Dans ce cas, l'enchâssement de la plaque supérieure 4 dans la plaque inférieure 5 entraîne une augmentation locale de la densité de l'ensemble. La plaque supérieure 4 est réalisée en un matériau composite comportant une matrice thermoplastique 8 et un renfort 10 de fibres continues. Par exemple la matrice 8 est une résine thermoplastique et le renfort 10 est un tissé en fibres de verre noyé dans la matrice. La plaque inférieure 5 est réalisée en un matériau composite comportant une matrice thermoplastique 12 et un renfort 14 en fibres continues. Par exemple la matrice 12 est la même résine thermoplastique que celle utilisée pour la plaque supérieure 4 et le renfort 14 est un tissé en fibres de verre. La plaque inférieure 5 est fixée sous la plaque supérieure 4 par thermocompression des deux plaques l'une au-dessus de l'autre. Ce procédé crée une interface 16 comportant un mélange des résines 8 et 12.The invention also relates to a method of manufacturing a reinforced composite structure, as defined above, the method comprising one or more of the following characteristics, taken separately or in any technically possible combination: . providing an upper plate and a lower plate, the two upper and lower plates being made of continuous fiber thermoplastic composite materials,. thermocompression of a portion of the upper plate on a portion of the lower plate, the assembly forming the composite structure, reinforcement of the composite structure,. the thermocompression step and the reinforcing step are performed at the same time; during the thermocompression step, part of the fibers of the upper plate, respectively lower, are needled in a part of the lower plate, respectively upper; the thermocompression step comprises the following steps: heating of the upper and lower plates by radiation or hot air. positioning the upper plate above the lower plate, the two plates being positioned between a mold and a counter-mold comprising at least one recess punch, casting mold against the mold inside the mold. - The manufacturing method comprises a riveting step of the upper and lower plates in which a rivet is inserted into the recess. The invention will be better understood on reading the detailed description which follows, given solely by way of example, with reference to the appended drawings, in which: FIG. 1 is a sectional view of a first composite structure according to the invention, - Figure 2 is a sectional view of a variant of the first composite structure according to the invention, - Figure 3 is a sectional view of a second composite structure according to the invention, - the figure 4 is a sectional view of a third composite structure according to the invention; FIGS. 5 to 8 are diagrammatic cross-sectional views of the steps of the method of manufacturing a composite structure according to the invention, FIGS. 10 are schematic sectional views of the steps of the manufacturing method according to a variant of the invention, and - Figure 11 is a top view of the composite structure according to the invention. A first reinforced composite structure 2 is illustrated by FIGS. 1 and 2. The composite structure 2 is intended to be used in the manufacture of automobile parts comprising connections between two plates made of composite materials. The composite structure 2 comprises an upper plate 4 thermocompressed on a lower plate 5, that is to say fixed thereto at least by thermocompression. The composite structure 2 is divided into a first zone I called recess, between a first plane A and a second plane B, the plane B being parallel to the plane A, and a second zone II located outside the planes A and B In the recess I, the sum of the densities of the upper 4 and lower 5 plates is greater than the sum of the densities of the upper 4 and lower 5 plates located in the second zone II. In other words, in the recess I, the upper plate 4 is embedded in the lower plate 5. By "encased" it should be understood that the upper plate 4 is shaped so that it is partially in the lower plate 5. In this case, the embedding of the upper plate 4 in the lower plate 5 causes a local increase in the density of the assembly. The upper plate 4 is made of a composite material comprising a thermoplastic matrix 8 and a reinforcement 10 of continuous fibers. For example, the matrix 8 is a thermoplastic resin and the reinforcement 10 is a fiberglass woven embedded in the matrix. The lower plate 5 is made of a composite material comprising a thermoplastic matrix 12 and a reinforcement 14 of continuous fibers. For example, the matrix 12 is the same thermoplastic resin used for the upper plate 4 and the reinforcement 14 is a fiberglass woven fabric. The lower plate 5 is fixed under the upper plate 4 by thermocompression of the two plates one above the other. This process creates an interface 16 comprising a mixture of resins 8 and 12.

Une deuxième structure 202 selon l'invention est représentée sur la figure 3.A second structure 202 according to the invention is shown in FIG.

Tout comme la structure composite 2, la structure composite 202 comprend une plaque supérieure 204 réalisée en un matériau composite comprenant une résine thermoplastique et des fibres continues, fixée sur une plaque inférieure 205 réalisée en un matériau composite comprenant une résine thermoplastique et des fibres continues. En particulier, la structure composite 204 se divise en une première zone l' appelée renfoncement, comprise entre un premier plan AA et un deuxième plan BB, le plan BB étant parallèle au plan AA, et une seconde zone Il' située à l'extérieur des plans AA et BB. Toutefois, à la différence de la structure composite 2, la structure composite 202 comprend également un moyen de fixation supplémentaire 206 qui est par exemple, un rivet métallique. Le rivet 206 est inséré dans le renfoncement l' et s'étend selon une direction sensiblement parallèle aux plans AA et BB. Une troisième structure composite 302 selon l'invention est représentée sur la figure 4. La structure 302 comprend une plaque supérieure 304 fixée sur une plaque inférieure 305. La plaque supérieure 304 est réalisée dans un matériau composite comprenant une résine thermoplastique 308 et des fibres continues 310 telles que des fibres de verre ou de carbone. La plaque inférieure 305 est réalisée dans un matériau composite comprenant une résine thermoplastique 312 et des fibres continues 314 telles que des fibres de verre. Les fibres de verre 310 de la plaque supérieure 304 sont aiguilletées verticalement vers le bas de façon à ce qu'elles soient partiellement insérées dans la résine 312 de la plaque inférieure 305. Par « aiguilleté verticalement vers le bas », on comprend qu'une aiguille est insérée dans la résine 308, dans laquelle elle rentre en contact avec une fibre de verre 310. Par le mouvement vertical vers le bas de l'aiguille, la portion de la fibre 310 en contact avec l'aiguille est entraînée vers le bas dans la résine 312, entraînant ainsi toute une partie de la fibre 310 dans la résine 312, le reste de la fibre 310 restant horizontal. De même, les fibres de verre 314 de la plaque inférieure 305 sont aiguilletées verticalement vers le haut de façon à ce qu'elles soient partiellement insérées dans la résine 308 de la plaque supérieure 304. La plaque supérieure 304 est donc enchâssée dans la plaque inférieure 305. Le procédé de fabrication de telles structures composites va maintenant être explicité en regard des figures 5 à 8.Like the composite structure 2, the composite structure 202 comprises an upper plate 204 made of a composite material comprising a thermoplastic resin and continuous fibers, fixed on a lower plate 205 made of a composite material comprising a thermoplastic resin and continuous fibers. In particular, the composite structure 204 is divided into a first zone called the recess, between a first plane AA and a second plane BB, the plane BB being parallel to the plane AA, and a second zone Il 'located outside. AA and BB plans. However, unlike the composite structure 2, the composite structure 202 also comprises additional fastening means 206 which is for example a metal rivet. The rivet 206 is inserted into the recess 1 'and extends in a direction substantially parallel to the planes AA and BB. A third composite structure 302 according to the invention is shown in FIG. 4. The structure 302 comprises an upper plate 304 fixed on a lower plate 305. The upper plate 304 is made of a composite material comprising a thermoplastic resin 308 and continuous fibers. 310 such as glass or carbon fibers. The bottom plate 305 is made of a composite material comprising a thermoplastic resin 312 and continuous fibers 314 such as glass fibers. The glass fibers 310 of the top plate 304 are needled vertically downward so that they are partially inserted into the resin 312 of the bottom plate 305. By "needled vertically downward", it will be understood that needle is inserted into the resin 308, in which it comes into contact with a fiberglass 310. By the vertical movement down the needle, the portion of the fiber 310 in contact with the needle is driven downwards in the resin 312, thereby driving a portion of the fiber 310 into the resin 312, the remainder of the fiber 310 remaining horizontal. Similarly, the glass fibers 314 of the bottom plate 305 are needled vertically upward so that they are partially inserted into the resin 308 of the upper plate 304. The upper plate 304 is thus embedded in the lower plate. 305. The method of manufacturing such composite structures will now be explained with reference to FIGS. 5 to 8.

Tout d'abord, on dispose dans deux fours 402A et 402B, ou dans un seul four, à rayonnement infrarouge ou à air chaud par exemple, une première plaque supérieure 404 et une seconde plaque inférieure 406. La plaque supérieure 404 est réalisée dans un matériau composite comprenant une résine thermoplastique 408 et des fibres de verre 410. La plaque inférieure 406 est réalisée dans un matériau composite comprenant une résine thermoplastique 412 et des fibres de verre 414. Les résines 408 et 412 sont telles qu'elles ne fluent pas complètement car elles n'atteignent pas une fluidité suffisante. En variante, les deux plaques 404 et 406 peuvent être disposées en même temps dans un seul four agencé pour réaliser le traitement thermique des deux plaques en même temps. Ensuite, on positionne la plaque inférieure chauffée 406 en-dessous de la plaque supérieure chauffée 404, entre un moule 416 et un contre-moule 418. Un poinçon 420 fait saillie hors du contre-moule 418. Un ensemble d'aiguilles 422 fait saillie verticalement par rapport au poinçon 420 et un ensemble d'aiguilles 424 fait saillie verticalement par rapport au moule 416. Avantageusement, les aiguilles 422 sont décalées horizontalement par rapport aux aiguilles 424, de sorte que lorsque le contre-moule 418 est déplacé verticalement vers le moule 416, les aiguilles 422 et 424 ne peuvent pas entrer en contact. Le contre-moule 418 est par la suite déplacé verticalement vers le moule 416, de façon à compresser la plaque supérieure 404 sur la plaque inférieure 406. Les résines 408 et 412 fusionnent alors en surface des plaques afin que l'ensemble des plaques 404 et 406 soient solidaires pour former une structure composite 430. Le poinçon 420 permet la réalisation d'un renfoncement. Les aiguilles 422 aiguillètent verticalement vers le bas les fibres 410 dans la résine 412. De même, les aiguilles 424 aiguillètent verticalement vers le haut les fibres 414 dans la résine 408. Les aiguilles sont de forme adéquate afin de « repousser » les fibres et ainsi réaliser cette opération d'aiguilletage. Enfin, le contre-moule 418 est déplacé verticalement vers le haut, et la structure 430 possédant un renfoncement, les fibres 410 de la plaque supérieure étant partiellement insérées dans la résine 412 de la plaque inférieure 406 et les fibres 414 étant partiellement insérées dans la résine 408 de la plaque supérieure est retirée du moule 416. En variante, représentée sur les figures 9 et 10, le poinçon 420 ne fait pas saillie hors du contre moule, par exemple pour réaliser une structure dans laquelle les fibres de l'une des plaques sont insérées dans la résine de l'autre plaque. Alternativement, la réalisation d'un renfoncement peut être réalisée ultérieurement. La structure composite 2 est donc particulièrement simple de fabrication car elle peut être réalisée dans l'étape de thermocompression et n'engendre donc aucun coût supplémentaire dans le processus de fabrication actuellement mis en place. De plus, le renfoncement I permet une continuité des transferts d'efforts et donc une meilleure tenue mécanique des liaisons entre deux matériaux composites thermoplastique. La structure composite 202 présente les mêmes avantages que la structure composite 2, à ceci près qu'une étape de rivetage est à ajouter au processus de fabrication. Toutefois, la présence du rivet 206 permet d'augmenter encore davantage la tenue mécanique de l'assemblage. Enfin, la structure composite 302 est également particulièrement simple de fabrication car elle peut être réalisée dans l'étape de thermocompression. L'enchevêtrement des fibres permet la création d'un réseau tridimensionnel de fibres à l'interface entre les deux plaques, ce qui augmente la résistance mécanique de l'assemblage. Selon d'autres modes de réalisation, les plaques supérieure et inférieure ne sont que partiellement superposées l'une sur l'autre. Par exemple, la figure 11 présente une structure comprenant deux plaques 505 et 506 en composite de forme rectangulaire dont les extrémités se superposent de façon à former un coin 508 en angle droit. De plus, la structure composite, selon d'autres modes de réalisation, comprend plusieurs renfoncements. Par exemple, la figure 11 illustre une structure comprenant deux renfoncements 510 et 512 présentant, dans un plan perpendiculaire aux plans A et B, une section en forme de croissant de lune. La concavité des sections des renforcements est dirigée vers le coin 508 en angle droit formé par les deux plaques superposées 505 et 506. Les deux tels renfoncements 510 et 512 s'étendent sensiblement parallèlement l'un à l'autre. Une telle structure permet une solide fixation des plaques et présente une résistance mécanique aux cisaillements et à l'arrachement. D'autres formes de renfoncements communément appelés « bulldozers » sont également réalisables afin de renforcer l'ensemble des 2 plaques composites dans leurs zones superposées. De même, la structure composite peut comprendre plusieurs rivets, de différents types.Firstly, two furnaces 402A and 402B, or a single furnace, with infrared radiation or hot air, for example, have a first upper plate 404 and a second lower plate 406. The upper plate 404 is made in one composite material comprising a thermoplastic resin 408 and glass fibers 410. The lower plate 406 is made of a composite material comprising a thermoplastic resin 412 and glass fibers 414. The resins 408 and 412 are such that they do not completely flow. because they do not reach a sufficient fluidity. Alternatively, the two plates 404 and 406 can be arranged at the same time in a single oven arranged to perform the heat treatment of the two plates at the same time. Then, the heated bottom plate 406 is positioned below the heated upper plate 404, between a mold 416 and a counter-mold 418. A punch 420 projects out of the counter-mold 418. A set of needles 422 protrude vertically relative to the punch 420 and a set of needles 424 protrudes vertically relative to the mold 416. Advantageously, the needles 422 are offset horizontally relative to the needles 424, so that when the counter-mold 418 is moved vertically towards the mold 416, the needles 422 and 424 can not come into contact. Against the mold 418 is subsequently moved vertically towards the mold 416, so as to compress the upper plate 404 on the lower plate 406. The resins 408 and 412 then merge at the surface of the plates so that all the plates 404 and 404 406 are integral to form a composite structure 430. The punch 420 allows the realization of a recess. The needles 422 vertically point down the fibers 410 in the resin 412. Similarly, the needles 424 vertically point up the fibers 414 in the resin 408. The needles are of adequate shape to "push" the fibers and thus perform this needling operation. Finally, counter-mold 418 is moved vertically upwards, and structure 430 having a recess, the fibers 410 of the upper plate being partially inserted into resin 412 of lower plate 406 and fibers 414 being partially inserted into the resin 408 of the upper plate is removed from the mold 416. Alternatively, shown in Figures 9 and 10, the punch 420 does not protrude out of the counter mold, for example to achieve a structure in which the fibers of one of the plates are inserted into the resin of the other plate. Alternatively, the realization of a recess can be performed later. The composite structure 2 is therefore particularly simple to manufacture because it can be performed in the thermocompression step and therefore does not generate any additional cost in the manufacturing process currently in place. In addition, the recess I allows a continuity of the transfer of forces and therefore a better mechanical strength of the connections between two thermoplastic composite materials. The composite structure 202 has the same advantages as the composite structure 2, except that a riveting step is to be added to the manufacturing process. However, the presence of the rivet 206 makes it possible to further increase the mechanical strength of the assembly. Finally, the composite structure 302 is also particularly simple to manufacture because it can be performed in the thermocompression step. The entanglement of the fibers allows the creation of a three-dimensional network of fibers at the interface between the two plates, which increases the mechanical strength of the assembly. In other embodiments, the upper and lower plates are only partially superimposed on each other. For example, FIG. 11 shows a structure comprising two rectangular-shaped composite plates 505 and 506, the ends of which are superimposed so as to form a wedge 508 at right angles. In addition, the composite structure, according to other embodiments, comprises several recesses. For example, Figure 11 illustrates a structure comprising two recesses 510 and 512 having, in a plane perpendicular to the planes A and B, a crescent-shaped section. The concavity of the reinforcement sections is directed towards the right-angled corner 508 formed by the two superposed plates 505 and 506. The two such recesses 510 and 512 extend substantially parallel to each other. Such a structure allows a strong fixing of the plates and has a mechanical resistance to shearing and tearing. Other forms of recesses commonly called "bulldozers" are also feasible to strengthen all 2 composite plates in their overlapping areas. Similarly, the composite structure may comprise several rivets, of different types.

Claims (10)

REVENDICATIONS1.- Structure composite renforcée (2; 202; 302; 402) comprenant au moins une plaque supérieure (4 ; 204 ; 304 ; 404) et une plaque inférieure (5 ; 205 ; 305 ; 406), la plaque supérieure étant réalisée en un matériau composite comportant une matrice thermoplastique (8 ; 308 ; 408) et des fibres continues (10 ; 310 ; 410), la plaque inférieure étant réalisée en un matériau composite comportant une matrice thermoplastique et des fibres continues, une partie de la plaque supérieure étant fixée sur une partie de la plaque inférieure par thermocompression, caractérisée en ce que la structure composite comprend au moins une zone dans laquelle la plaque supérieure est partiellement enchâssée dans la plaque inférieure.1. Reinforced composite structure (2; 202; 302; 402) comprising at least one upper plate (4; 204; 304; 404) and a lower plate (5; 205; 305; 406), the upper plate being made of a composite material comprising a thermoplastic matrix (8; 308; 408) and continuous fibers (10; 310; 410), the lower plate being made of a composite material comprising a thermoplastic matrix and continuous fibers, a part of the upper plate being fixed to a portion of the lower plate by thermocompression, characterized in that the composite structure comprises at least one zone in which the upper plate is partially embedded in the lower plate. 2.- Structure composite renforcée (2; 202; 302) selon la revendication 1, caractérisée en ce qu'elle comprend au moins un renfoncement (1 ; 1') comportant une portion de la plaque supérieure (4; 204; 404) et une portion associée de la plaque inférieure (5 ; 205 ; 406) compressées ensembles, ladite portion associée de la plaque inférieure étant en regard de ladite portion de la plaque supérieure.2. Reinforced composite structure (2; 202; 302) according to claim 1, characterized in that it comprises at least one recess (1; 1 ') comprising a portion of the upper plate (4; 204; 404) and an associated portion of the bottom plate (5; 205; 406) compressed together, said associated portion of the bottom plate facing said portion of the top plate. 3.- Structure composite renforcée (202) selon la revendication 2, caractérisée en ce qu'elle comprend au moins un rivet (206) inséré dans le renfoncement (1').3. Reinforced composite structure (202) according to claim 2, characterized in that it comprises at least one rivet (206) inserted into the recess (1 '). 4.- Structure composite renforcée (302) selon l'une quelconque des revendications précédentes, caractérisée en ce que les fibres continues (310; 410) de la plaque supérieure (304 ; 404) sont partiellement insérées dans la matrice thermoplastique (312 ; 412) de la plaque inférieure (305 ; 406).4. Reinforced composite structure (302) according to any one of the preceding claims, characterized in that the continuous fibers (310; 410) of the upper plate (304; 404) are partially inserted into the thermoplastic matrix (312; ) of the lower plate (305; 406). 5.- Structure composite renforcée (302) selon l'une quelconque des revendications précédentes, caractérisée en ce que les fibres continues (314; 414) de la plaque inférieure (305 ; 406) sont partiellement insérées dans la matrice thermoplastique (308; 408) de la plaque supérieure (304 ; 404).5. Reinforced composite structure (302) according to any one of the preceding claims, characterized in that the continuous fibers (314; 414) of the lower plate (305; 406) are partially inserted into the thermoplastic matrix (308; 408). ) of the upper plate (304; 404). 6.- Structure composite renforcée (2; 202; 302) selon l'une quelconque des revendications précédentes, caractérisée en ce que les fibres continues des plaques supérieure (4 ; 204 ; 304 ; 404) et inférieure (5 ; 205 ; 305 ; 406) sont des tissés de fibres de verre.6. Reinforced composite structure (2; 202; 302) according to any one of the preceding claims, characterized in that the continuous fibers of the upper (4; 204; 304; 404) and lower (5; 205; 305; 406) are woven glass fibers. 7.- Procédé de fabrication d'une structure composite (2; 202; 302) selon la revendication 1, procédé comprenant les étapes suivantes : - fourniture de d'une plaque supérieure (404) et d'une plaque inférieure (406), les deux plaques supérieure et inférieure étant réalisées en des matériaux composites thermoplastiques à fibres continues (410 ; 414),- thermocompression d'une partie de la plaque supérieure sur une partie de la plaque inférieure, l'ensemble formant la structure composite, - renforcement de la structure composite, caractérisé en ce que l'étape de thermocompression et l'étape de renforcement sont réalisées en même temps.7. A method of manufacturing a composite structure (2; 202; 302) according to claim 1, the method comprising the following steps: - providing an upper plate (404) and a lower plate (406), the two upper and lower plates being made of continuous fiber thermoplastic composite materials (410; 414); thermocompression of a portion of the upper plate on a portion of the lower plate, the assembly forming the composite structure; of the composite structure, characterized in that the thermocompression step and the reinforcing step are performed at the same time. 8.- Procédé de fabrication selon la revendication 7, caractérisé en ce qu'au cours de l'étape de thermocompression, une partie des fibres (410 ;414) de la plaque supérieure (404), respectivement inférieure (406), sont aiguilletées dans une partie de la plaque inférieure, respectivement supérieure.8. A manufacturing method according to claim 7, characterized in that during the thermocompression step, a portion of the fibers (410; 414) of the upper plate (404), respectively lower (406), are needled in a part of the lower plate, respectively upper. 9.- Procédé de fabrication selon la revendication 7 ou 8, caractérisé en ce que l'étape de thermocompression comprend les étapes suivantes : - chauffage des plaques supérieure et inférieure par rayonnement ou air chaud - positionnement de la plaque supérieure au-dessus de la plaque inférieure, les deux plaques étant positionnées entre un moule (416) et un contre-moule (418) comprenant au moins un poinçon de renfoncement (420), - moulage par enfoncement du contre-moule à l'intérieur du moule.9. A manufacturing method according to claim 7 or 8, characterized in that the thermocompression step comprises the following steps: - heating of the upper and lower plates by radiation or hot air - positioning of the upper plate above the lower plate, the two plates being positioned between a mold (416) and a counter-mold (418) comprising at least one recess punch (420), - molding by pressing the counter-mold inside the mold. 10.- Procédé de fabrication selon la revendication 9, caractérisé en ce qu'il comprend une étape de rivetage des plaques supérieure et inférieure dans laquelle un rivet (206) est inséré dans le renfoncement (1').2010. A manufacturing method according to claim 9, characterized in that it comprises a step of riveting the upper and lower plates in which a rivet (206) is inserted into the recess (1 ').
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FR3074080A1 (en) * 2017-11-30 2019-05-31 Francois Geli SOLID ASSEMBLY OF THERMOPLASTIC COMPOSITE MATERIAL PARTS

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JPH1190986A (en) * 1997-09-25 1999-04-06 Press Kogyo Co Ltd Method for welding fiber-reinforced resin molding
WO2006089534A1 (en) * 2005-02-21 2006-08-31 Airbus Deutschland Gmbh Fiber composite component and method for the production of a fiber composite component
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JPH04135720A (en) * 1990-09-27 1992-05-11 Mazda Motor Corp Manufacture of fiber-reinforced resin molded object
JPH1190986A (en) * 1997-09-25 1999-04-06 Press Kogyo Co Ltd Method for welding fiber-reinforced resin molding
WO2006089534A1 (en) * 2005-02-21 2006-08-31 Airbus Deutschland Gmbh Fiber composite component and method for the production of a fiber composite component
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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3074080A1 (en) * 2017-11-30 2019-05-31 Francois Geli SOLID ASSEMBLY OF THERMOPLASTIC COMPOSITE MATERIAL PARTS

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