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
  • B29C65/48—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding
• • 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
  • B29C33/00—Moulds or cores; Details thereof or accessories therefor
  • B29C33/0038—Moulds or cores; Details thereof or accessories therefor with sealing means or the like
  • B29C33/0044—Moulds or cores; Details thereof or accessories therefor with sealing means or the like for sealing off parts of inserts projecting into the mould cavity
• • 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
  • B29C65/48—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding
  • B29C65/50—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like
  • B29C65/5007—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like characterised by the structure of said adhesive tape, threads or the like
  • B29C65/5028—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like characterised by the structure of said adhesive tape, threads or the like being textile in woven or non-woven form
• • 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
  • B29C65/48—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding
  • B29C65/50—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like
  • B29C65/5057—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like positioned between 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
  • 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
  • B29C66/02—Preparation of the material, in the area to be joined, prior to joining or welding
  • B29C66/022—Mechanical pre-treatments, e.g. reshaping
• • 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
• • 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
  • B29C66/13—Single flanged joints; Fin-type joints; Single hem joints; Edge joints; Interpenetrating fingered joints; Other specific particular designs of joint cross-sections not provided for in groups B29C66/11 - B29C66/12
  • B29C66/131—Single flanged joints, i.e. one of the parts to be joined being rigid and flanged in the joint area
• • 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
  • B29C66/301—Three-dimensional joints, i.e. the joined area being substantially non-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
  • B29C66/01—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
  • B29C66/30341—Particular design of joint configurations the joint involving an anchoring effect making use of additional elements, e.g. meshes non-integral with the parts to be joined, e.g. making use of extra elements
• • 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
  • B29C66/50—General aspects of joining tubular articles; General aspects of joining long products, i.e. bars or profiled elements; General aspects of joining single elements to tubular articles, hollow articles or bars; General aspects of joining several hollow-preforms to form hollow or tubular articles
  • B29C66/51—Joining tubular articles, profiled elements or bars; Joining single elements to tubular articles, hollow articles or bars; Joining several hollow-preforms to form hollow or tubular articles
  • B29C66/52—Joining tubular articles, bars or profiled elements
  • B29C66/524—Joining profiled elements
• • 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
  • B29C66/50—General aspects of joining tubular articles; General aspects of joining long products, i.e. bars or profiled elements; General aspects of joining single elements to tubular articles, hollow articles or bars; General aspects of joining several hollow-preforms to form hollow or tubular articles
  • B29C66/51—Joining tubular articles, profiled elements or bars; Joining single elements to tubular articles, hollow articles or bars; Joining several hollow-preforms to form hollow or tubular articles
  • B29C66/53—Joining single elements to tubular articles, hollow articles or bars
  • B29C66/532—Joining single elements to the wall of tubular articles, hollow articles or bars
• • 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
  • B29C66/50—General aspects of joining tubular articles; General aspects of joining long products, i.e. bars or profiled elements; General aspects of joining single elements to tubular articles, hollow articles or bars; General aspects of joining several hollow-preforms to form hollow or tubular articles
  • B29C66/61—Joining from or joining on the inside
• • 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
• • 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
  • B29C66/74—Joining plastics material to non-plastics material
  • B29C66/742—Joining plastics material to non-plastics material to metals or their alloys
• • 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
  • B29C65/48—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding
  • B29C65/4805—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding characterised by the type of adhesives
  • B29C65/483—Reactive adhesives, e.g. chemically curing adhesives
  • B29C65/4835—Heat curing adhesives
• • 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
  • B29C65/48—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding
  • B29C65/50—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like
  • B29C65/5007—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like characterised by the structure of said adhesive tape, threads or the like
  • B29C65/5014—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like characterised by the structure of said adhesive tape, threads or the like being fibre-reinforced
• • 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
• • 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
  • B29L2031/3076—Aircrafts
• • 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
  • B29L2031/3097—Cosmonautical vehicles; Rockets

Definitions

• the present invention relates to a structural bonding method of structural parts of which at least a first structural part is a composite material part and a second structural part is a composite material part or a metal part, each piece of structure of material composite consisting of a reinforcing preform based on fibers impregnated with a matrix based on polymers, the two structural parts being assembled together during a bonding operation in which an adhesive seal is deposited in a zone defined junction of at least one of said structural parts, said structural parts are pressed against each other and held in position until hardened said glue joint to obtain a rigid structural assembly.
• the invention also relates to a textured surface insert for implementing said method of structural bonding, a tool for manufacturing a structural part made of composite material comprising at least one mold and a counter mold defining the three-dimensional footprint of said piece of composite material structure to be manufactured, and allowing the shaping of a fiber-reinforced reinforcement preform, the impregnation of the preform with a matrix based on polymers, then the hardening of the part thus obtained, an assembly of at least two structural parts obtained according to said bonding method, and a use of said assembly obtained.
• the parts to be assembled can be made of identical or different materials.
• the present invention is more particularly concerned on the one hand with an assembly by bonding two pieces of composite material, and secondly to a bonding assembly of a composite material part and a metal part. Indeed, a bonding assembly of two metal parts is of little interest compared to other existing assembly techniques, such as welding or the like.
• a car seat is manufactured from a sandwich panel consisting of a sheet of composite material superimposed on a metal sheet by an adhesive intermediate layer consisting of a nonwoven impregnated with a thermosetting resin. It is specified that the metal foil can undergo a plasma treatment to increase the adhesion.
• the publication WO 03/039851 A1 describes an assembly process by gluing for aircraft of an outer skin made of metal or of composite material on a structural part by means of a pre-cut glue joint and disposed in the zones of junction.
• This glue joint consists of a layer of glass fibers impregnated with polymerized resin sandwiched between two layers of binder, one polymerized and the other partially polymerized to adjust the thickness of said glue joint by variation. pressure during assembly.
• the publication EP 2 944 456 A1 relates to a method of repairing a composite material part, such as the outer surface of an aircraft wing, by bonding a repair patch made of the same composite material as the part. to be repaired by means of a bonding interface consisting of a thermosetting adhesive layer sandwiched between two sheets of fabric reinforcement.
• the publication FR 2 960 881 B1 proposes a reinforced structural bonding method of two pieces made of composite material, in which the adhesive seal is loaded with so-called solid particles. Under the action of a strong pressure on the glue joint, the solid particles penetrate partially into the composite parts to obtain additional mechanical anchoring in their junction zone.
• the publication US 2016/0265570 A1 proposes to etch the resin on the surface of a composite material part by a laser beam in order to expose the carbon or glass fibers of said part to an adhesive material.
• This same publication proposes to machine with a laser beam the surface of a metal part to make grooves.
• the combination of these two surface treatments by removal of material makes it possible to improve the mechanical anchoring of the parts to be assembled.
• this bonding process is slow to implement, requires immobilization of the parts, and ensures only a mechanical surface anchoring of 0.1 to 0.2 mm which may be insufficient in terms of mechanical strength.
• the present invention aims to overcome these disadvantages by proposing an industrializable bonding process between two structural parts to produce a composite / composite or composite / metal assembly by means of a conventional glue joint, allowing further improve the mechanical strength in the bonded junction zone, by greatly increasing the specific surface area of the structural parts in their junction zones to create an interpenetration of the materials in the presence, also making it possible to control the thickness of the glue joint added, in particular in a composite / metal assembly, while reducing the surface preparation times of the structural parts to be assembled, which makes it possible to adapt said method to an assembly line, this method being moreover compatible with a large part of the manufacturing processes current composite structural parts and may be suitable for assemblies small and large dimensions and / or simple and complex shapes.
• the invention relates to a method of the kind indicated in the preamble, characterized in that, prior to the bonding operation, a surface texturing of the junction zone of the two composite material structural parts is performed in a composite / composite assembly or at least the composite structure part in a composite / metal assembly by adding material to increase the specific surface area of said structural parts in their junction zone, in that, to perform said texturing of surface, we add fibers in said junction zone of each structural component part made of composite material which will not be or only partially impregnated during the manufacture of said composite part, and in that, during the gluing operation, when said structural parts are pressed against each other, said textured junction zones interpenetrate and intimately bond each other with said glue joint to increase their mechanical anchorage.
• a textured surface insert based on textile fibers is manufactured whose shape and dimensions are adapted to those of said zone of junction, and integrates said textured surface insert in each composite material structure part during its manufacture in a tool adapted by orienting said textured surface insert outside said composite material structure part, in said area of joining, and isolating the textile fibers of said textured surface insert to remain dry, to give a specific texture to said junction area and to be exposed to said glue joint during the operation of bonding.
• said textured surface insert it is possible to produce a complex comprising a first sheet of textile fibers superimposed on a barrier film, said first sheet of textile fibers constituting an outer face of said textured surface insert arranged for being oriented outside said composite material structure part, to remain dry and to give texture to said junction area, and said barrier film being arranged to isolate the outer face of said textured surface insert from said part structure of composite material and to prevent the impregnation of said first sheet of textile fibers by the matrix of said composite material for said textile fibers to remain dry.
• said barrier film is advantageously dimensioned so that it has a surface greater than the surface of said first textile fiber web in order to create a peripheral rim all around said textured surface insert, this peripheral rim being arranged to cooperate with a seal provided on said adapted tooling.
• said textured surface insert can be assembled to the reinforcing preform of said composite material by a sewing, needling or tufting technique.
• said second sheet of textile fibers is advantageously dimensioned so that it has a surface at least equal to the surface of said barrier film.
• said barrier film is produced in thermoplastic or thermoset sand materials, and said barrier film is intimately joined to said first sheet of textile fibers and / or said second sheet of textile fibers by a heat-bonding, polymerization or cross-linking process. under pressure, to cause interpenetration of said barrier film in said webs of textile fibers binding the components together after curing said barrier film, but without completely impregnating said webs of textile fibers.
• said first web of textile fibers and / or said second web of textile fibers is produced in two-dimensional webs. obtained from a woven fabric or a nonwoven web, and / or in three-dimensional webs obtained from a smooth or ribbed velvet, a knit, a needle-punched nonwoven, a tufted fabric, scraped fabric, or a combination of these tablecloths.
• the three-dimensional plies can be produced from a pile whose pile tufts are oriented predominantly orthogonal to the plane of said ply so as to increase the specific surface area of said structural parts in their junction zone and / or or anchoring said insert in said structural parts of composite material.
• a composite / metal assembly it is also possible to perform a surface texturing of the junction area of said structural piece of metal material by producing a three-dimensional relief by adding deposited material according to a three-dimensional printing process.
• the surface texturing of the junction areas of said structural parts to be assembled can be performed by choosing compatible or complementary texturing patterns.
• the invention also relates to a textured surface insert for implementing the structural bonding method defined above, characterized in that it comprises a complex provided with a first layer of textile fibers superimposed on a barrier film, said first web of textile fibers constituting an outer face of said textured surface insert and being arranged to be oriented outside of said composite material structure part, to remain dry and to give the texture to the junction zone of each piece of composite material structure, and said barrier film being arranged to isolate said first sheet of textile fibers and to prevent its impregnation by the matrix of said composite material to remain dry.
• said barrier film has a surface greater than the surface of said first web of textile fibers to create a peripheral rim all around said textured surface insert.
• said textured surface insert may further comprise a second layer of textile fibers superimposed on said barrier film opposite said first sheet of textile fibers, said second sheet of textile fibers constituting an inner face of said textile insert. textured surface and being arranged to be oriented within said composite material structure part, to be impregnated by the matrix of said composite material and to intimately bond said textured surface insert to said composite material part.
• said second web of textile fibers preferably has a surface at least equal to the surface of said barrier film.
• the object of the invention is also achieved by a tool as defined in the preamble, characterized in that it is adapted for the implementation of the bonding method defined above, and in that it comprises in said mold at least one recess whose shape and dimensions correspond to those of said determined junction zone and whose depth corresponds to the thickness of said textured surface insert, and a peripheral groove disposed around said recess for receiving a seal for cooperating with the peripheral rim of said textured surface insert to isolate its outer face and prevent the impregnation of said first sheet of textile fibers by the matrix of said composite material injected into said tool so that the textile fibers of said first sheet remain dry during the manufacture of said structural part composite material and give a specific texture to said junction area.
• the invention relates to an assembly of structural parts obtained by the structural bonding method defined above, and a use of such an assembly as a subassembly or structural assembly for aeronautics, the aerospace, transportation, construction and energy.
• FIG. 1 is a perspective view of a textured surface insert for implementing the bonding method according to the invention
• FIG. 2 is a sectional view along the AA section plane of the textured surface insert of FIG. 1,
• FIG. 3 is a sectional view of a tool for manufacturing a composite part in which the textured surface insert of FIG. 1 has been positioned before the introduction of the preform to produce said composite part,
• FIG. 4 is a perspective view of a metal part provided in its junction regions with a pattern of reliefs obtained by surface treatment in accordance with the method of the invention
• FIGS. 5A and 5B are other examples of patterns obtained by surface treatment of the metal part of FIG. 4,
• FIG. 6 is a perspective view of a structural subassembly obtained by bonding a composite part and a metal part according to the method of the invention
• Figures 7 and 8 are enlarged views of details VII and Vin of Figure 6
• Figure 9 is an enlarged sectional view of the composite / metal assembly of Figure 8, and
• Figure 10 is an enlarged sectional view of a composite / composite assembly.
• the method of structural bonding of structural parts 1, 2 according to the invention can be applied on the one hand to an assembly between two parts made of composite material, the composite materials in the presence which may be identical or different, and on the other hand to an assembly between a composite material part and a metal part.
• composite material part must be understood to mean any type of composite parts that can be manufactured and that generally comprise a reinforcing preform based on fibers impregnated with a matrix based on polymers, fibers which may be carbon, glass or any other type commonly used in composite materials, and polymers which may be thermoplastic or thermoset sands resins commonly used in composite materials.
• a bonding operation consists of depositing an adhesive joint 5 in a junction zone 3, 4 determined from at least one of the parts 1, 2 to be assembled, to press the parts 1, 2 against each other and hold them in position until hardening of the glue joint 5 to obtain a rigid structural assembly.
• junction zone and “glue joint” used in this application may also be used in the plural.
• the method according to the invention is distinguished in that, prior to the bonding operation, a surface texturing of the junction zone 3, 4 of each of the pieces 1, 2 is carried out by adding material for the purpose. to increase the specific surface area of the structural parts 1, 2 in their junction zone 3, 4.
• texturing covers any action aimed at creating a drawing, a pattern, a figure or the like, two-dimensional or three-dimensional, or a combination of the two, the technical effect of which is the increase of the specific surface area of the structural parts 1, 2 in their junction zone 3, 4.
• This phenomenon necessarily generates a significant increase in the mechanical anchoring of the parts between they allow to reach a high level of mechanical performance that can reach, for example, a gain of at least 50% in resistance to shear stresses compared to a conventional bonding, and depending on the choice chosen to perform the surface texturing.
• a textured surface insert 6 based on textile fibers is manufactured whose shape and dimensions are adapted to those of each junction zone 3, this textured surface insert 6 is integrated with the structural part 1 made of material composite during its manufacture, by orienting textured surface insert 6 outside of said workpiece 1, isolating the fibers of said textured surface insert 6 to remain dry and thereby provide a texture specific to the junction zone 3 for increasing its specific surface area.
• FIGS. 1-10 A first example of a textured surface insert 6 is shown in detail in FIGS.
• first ply 7 of textile fibers constitutes an outer face the textured surface insert 6, arranged to be oriented outside the structural part 1 of composite material, remain dry and give the texture to said junction zone 3.
• the second ply 9 of textile fibers constitutes a face inside of the textured surface insert 6, arranged to be oriented inside the structural part 1 made of composite material, impregnated by the matrix of said composite material and intimately bonded to said insert
• the function of the barrier film 8 is to isolate the first ply 7 from the second ply 9 in order to prevent impregnation of the first ply 7 with the matrix of said composite material and to keep dry fibers.
• the first ply 7 of textile fibers and the second ply 9 of textile fibers may be of construction and of identical or different nature, and may be made in two or three dimensions depending on the desired mechanical performance.
• the sheets are two-dimensional, they can be obtained from a woven fabric, a nonwoven web, without these examples being limiting.
• they when they are three-dimensional, they can be obtained from a smooth or ribbed velvet, a knit, a needle-punched nonwoven, a tufted fabric, a scraped fabric, or a combination of these layers, without these examples being limiting.
• the fibers protrude transversely to the surface of the ply and form either bristles 7 ', 9' or loops.
• the tufts of bristles are oriented mainly orthogonally with respect to the plane of the sheet and contribute more to the increase of the specific surface of the junction zones and / or the anchoring of the insert in structural parts made of composite material.
• any interleaving method of textile fibers may be suitable.
• any type of design or interlacing pattern of the fibers may be suitable, such as a chevron weave, a jersey knit, a striped or checkered velvet, or the like for the simple purpose of creating an anchor on more efficient possible.
• the fibers that make up the first and second plies 7 and 9 may be chosen from natural, synthetic, artificial, inorganic textile fibers, such as, for example, aramid, carbon fiber, glass or flax fibers. and any other fiber having in particular a high tensile strength.
• the barrier film 8 can be made in any type of thermoplastic or thermoset sand, such as for example an epoxy resin or a polyurethane, without these examples being limiting. It should preferably have a glass transition temperature (Tg) greater than the melting temperature of the matrix to preserve its integrity and barrier function at least during manufacture of the composite part. For example, a difference between +10 and + 20 ° C may suffice. This choice remains in the domain of the person skilled in the art.
• Tg glass transition temperature
• the barrier film 8 protrudes from this first ply 7 to form a periphery flange 10 on this outer face.
• the thickness E8 of the barrier film 8 the more the textured surface insert 6 will remain discrete on the surface of the composite structure part 1 and have no influence on the technical characteristics. of the structural part 1 of composite material.
• the thicknesses of the three components may be between 0.05 and 0.5 mm for the barrier film 8 and between 0.1 and 1 mm for the plies 7 and 9, without these examples being limiting.
• the three components of the textured surface insert 6, namely the first ply 7, the barrier film 8 and the second ply 9, are joined together intimately by any compatible method, such as a mechanical method by sewing, stapling, or the like, a thermal process by heat sealing, polymerization, crosslinking or the like, or a combination of both.
• a thermal process will be favored to cause the material of the barrier film 8 to flow towards the plies 7 and 8 (such as schematically illustrated in Figure 2), and thus the interpenetration of the barrier film 8 in each of the layers 7 and 9, binding the components together after curing the barrier film 8.
• the conditions of this thermal process in terms of temperature, pressure and time are determined by the skilled person according to the nature of the barrier film 8 and are part of his knowledge.
• the viscosity of the barrier film 8 is important. Viscosity too low would cause capillary effects that would completely impregnate the two layers 7 and 9. It must be high enough to avoid this capillary phenomenon, and for example greater than 10OPa.s without this example being limiting. It depends at the same time on the nature of the barrier film 8 and the temperature of implementation, and the values indicated are not limiting.
• textured surface insert 6 which has just been described is not limiting, but has the advantage of being easy to industrialize because it can be prepared in advance and outside the production line of parts of structure 1 in composite material. Similarly, it can be easily integrated into the structural part 1 during its manufacture. However, it requires slightly modifying the manufacturing tooling of these parts with reference to FIG. 3.
• Another variant of embodiment that is not illustrated consists in producing a textured surface insert without the second sheet 9 of textile fibers and in directly bonding it to the reinforcing preform of the future structural part 1 made of composite material.
• This textured surface insert would comprise only the barrier film and the first ply of textile fibers and would be assembled to said reinforcing preform by any suitable assembly method, such as stitching, needling, tufting, or the like, traversing all or part of the thickness of the reinforcing preform, or by a thermal process as textured surface insert 6 described above.
• the first web of textile fibers may or may not be completed by reinforcement threads used for needling or tufting. This method of construction can provide extreme mechanical performance, but increases considerably the time of realization. It may, however, have an interest in structural parts with high added value for demanding areas such as aerospace or aeronautics.
• a tooling 20 allowing the manufacture of a piece 1 of composite material must be slightly modified to be able to integrate textured surface insert 6 in said piece 1 during its manufacture so that it is an integral part of this piece and can not get away from it.
• a tooling 20 generally comprises at least one rigid mold 21 and a flexible or rigid counter mold 22 (symbolized by an arrow) defining the three-dimensional impression of the component 1 made of composite material to be manufactured, and allowing the forming a reinforcing preform 11 based on fibers, impregnating the preform 11 with a matrix based on polymers, and then hardening the part 1 thus obtained.
• the bottom of the mold 21 is machined to create a recess 23 whose shape and dimensions correspond to those of the junction zone 3 determined and whose depth P23 corresponds substantially to the thickness of the textured surface insert 6.
• a throat 24 device is machined around the recess 23 to receive a seal 25, for example elastomer or the like, or any equivalent sealing system.
• This seal 25 is arranged to create with the peripheral rim 10 of the textured surface insert 6, when the counter mold 22 is closed under pressure, a peripheral sealing zone for isolating the textile fibers of the first 7.
• the tooling 20 can thus be adapted without much extra cost to the bonding method according to the invention and makes it possible to easily integrate one or more textured surface inserts 6 in the part 1 to be manufactured, the textured surface insert 6 being not limited in size or surface that can range from a few mm 2 to several m 2 .
• a piece 1 of composite material is obtained in its strict definition, that is to say a solid piece made of a matrix and of a reinforcing preform 11. Only the outer face of the textured surface insert 6 is not or only partially impregnated by the matrix, leaving the dry fibers of the first sheet 7 appear in the junction zone 3.
• the metal structure part 2 can be prepared specifically by performing a surface texturizing of one or more junction zones 4 by adding material. It may not undergo a texturing step before gluing. We would still obtain a resistance gain through the texturing of the composite part.
• an additive manufacturing technique is preferably used, by a three-dimensional printing method of the LMD type (Laser Metal Deposition) or the like. This method makes it possible to add a material that is chemically and physically compatible with the metal constituting the structural part 2 to enable it to adhere intimately to the surface of said part.
• the added material may preferably be metallic, or in some cases synthetic, depending on the chosen three-dimensional printing method and the part 2 to be textured.
• FIG. 4 represents an example of a piece of metal structure 2 in the form of an omega section, the end flanges of which comprise two longitudinal and parallel bearing zones forming said junction zones 4.
• junction areas 4 comprise a surface topography formed by pins 12 in relief, obtained by adding material by means of a three-dimensional printing process, these pins 12 being distributed uniformly.
• the surface topography can have a variable thickness, between 0.1mm and some millimeters, without these values being limiting.
• the "pin" pattern illustrated is not limiting and extends to any other pattern, which can be determined according to the mechanical stresses of the junction areas 4.
• the three-dimensional printing pattern can also be chosen according to the drawing or the pattern of the first ply 7 of textile fibers, so that they are compatible or even complementary in part or in whole to further improve the interpenetration of the two junction areas 3 and 4 during the bonding operation of the parts 1 and
• Figs. 5A and 5B illustrate two further exemplary patterns, one in the form of S-shaped parallel corrugated ribs 13 and the other in the form of parallel straight ribs 14. These patterns may also be uniformly distributed or not in the junction areas 4 to distribute the best constraints according to the solicitation modes encountered.
• FIG. 6 shows the advantage of the bonding method according to the invention in a concrete application, between a first piece of structure 1 made of composite material in the form of a skin, and several second pieces of metal structure 2 in the form of stiffeners, common assembly in the field of aeronautics and rail for example.
• the second pieces of metal structure 2 have been texturized from their junction areas 4 by three-dimensional printing, in accordance with FIG. 4.
• the assembly of these parts 1 and 2 by gluing consists in depositing an adhesive joint 5 in the junction zone or zones 3 and 4 of one or both pieces 1 and 2, pressing them against each other, keeping them in position until the adhesive seam (s) 5 are hardened.
• the result obtained is illustrated in FIG. 9 in a very enlarged manner and shows an adhesive joint 5 between the two parts 1 and 2, and the interpenetration of the pins 12 of the zone of textured junction 4 of the metal part 2 in the bristles 7 'of the textured junction zone 3 of the piece 1 made of composite material.
• the invention achieves the goals set, namely a simple bonding process to industrialize to achieve a high level of mechanical performance, and particularly suitable for composite / composite and composite / metal, thus covering a wide range of market assemblies.
• the present invention is not limited to the embodiments described but extends to any modification and variation obvious to a person skilled in the art.

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• Engineering & Computer Science (AREA)
• Mechanical Engineering (AREA)
• Textile Engineering (AREA)
• Laminated Bodies (AREA)
• Adhesives Or Adhesive Processes (AREA)

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• 2017
  • 2017-10-23 FR FR1759955A patent/FR3072604B1/fr active Active
• 2018
  • 2018-10-22 EP EP18796858.1A patent/EP3700740A1/de active Pending
  • 2018-10-22 WO PCT/EP2018/078921 patent/WO2019081441A1/fr unknown

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