Abstract: The invention concerns a method for producing, by welding, a link between an element made from any material, for example metal, and an element made from a thermoplastic-matrix composite material, the second element being produced by depositing a textile yarn pre-impregnated with a thermoplastic material on the surface of the first element. The method mainly includes an operation consisting of producing an interface coating consisting of an epoxy resin filled with a thermoplastic material powder, coating the surface of the element made from any material with same, and leaving the coating to polymerise. It next includes an operation consisting simultaneously of forming the second element and welding same to the coating deposited on the surface of the first element by locally heating the two elements, when depositing the pre-impregnated textile on the first element.

Abstract: A curable composition, and a material obtained by curing the composition, in which the curable composition includes a vinylester polymerisable compound, jointly with a sulphonated polyaromatic thermoplastic polymer, and an N-vinyl lactam, and which is characterised in that it further includes, a first non-vinylester polymerisable compound which includes at least one isocyanurate group bearing at least two (meth)acrylate groups; and a second non-vinylester polymerisable compound which includes at least one carbopolycyclic or heteropolycyclic group bearing at least two (meth)acrylate groups.

Abstract: A curable composition, and a material obtained by curing the composition, in which the curable composition includes a vinylester polymerisable compound, jointly with a sulphonated polyaromatic thermoplastic polymer, and an N-vinyl lactam, and which is characterised in that it further includes, a first non-vinylester polymerisable compound which includes at least one isocyanurate group bearing at least two (meth)acrylate groups; and a second non-vinylester polymerisable compound which includes at least one carbopolycyclic or heteropolycyclic group bearing at least two (meth)acrylate groups.

Abstract: A method increases the toughness of a material obtained by curing a composition that includes at least one vinyl ester monomer. The method includes the incorporation into the composition of a sulfonated polyaromatic thermoplastic polymer, which is achieved by dissolving the vinyl ester monomer and the thermoplastic polymer in a reactive diluent in which they are both soluble. The resulting curable composition includes at least one vinyl ester monomer, and very high toughness materials can be made from it. A curable composition can include at least one vinyl ester monomer, a sulfonated polyaromatic thermoplastic polymer and a N-vinyl lactam. The compositions can be used in the aeronautical, space, railway, nautical, automotive industries, arms and other industries.

Abstract: The invention relates to a process for improving the adhesion of carbon fibers by coating a surface of the carbon fibers with a polymer film containing functional groups capable of acting as chain transfer agents during a chain transfer polymerization of a resin curable by chain transfer polymerization to obtain coated carbon fibers. The coated carbon fibers are then contacted with the curable resin, and the chain transfer polymerization of the curable resin is induced to produce an organic matrix and forming a composite material. The functional groups of the polymer film act as chain transfer agents during the chain transfer polymerization of the curable resin and thereby improve adhesion of the carbon fibers to the organic matrix. Applications of this invention include aeronautical, aerospatial, shipbuilding, railway and motor vehicle industries, armaments industry, sports and leisure articles, and the like.

Abstract: The invention relates to a process for improving the adhesion of carbon fibres with regard to an organic matrix forming a composite material with these fibres, this composite material being obtained by bringing the fibres into contact with a resin which can be cured by chain polymerization and then polymerizing the resin, which process is characterized in that it comprises the grafting, to the surface of the fibres, before they are brought into contact with the resin, of groups capable of acting as chain transfer agents during the polymerization of said resin. Fields of application: aeronautical, aerospatial, railway, ship building and automobile industries but also the armaments industry, the industry of sports and leisure articles, and the like.

Abstract: A method increases the toughness of a material obtained by curing a composition that includes at least one vinyl ester monomer. The method includes the incorporation into the composition of a sulfonated polyaromatic thermoplastic polymer, which is achieved by dissolving the vinyl ester monomer and the thermoplastic polymer in a reactive diluent in which they are both soluble. The resulting curable composition includes at least one vinyl ester monomer, and very high toughness materials can be made from it. A curable composition can include at least one vinyl ester monomer, a sulfonated polyaromatic thermoplastic polymer and a N-vinyl lactam. The compositions can be used in the aeronautical, space, railway, nautical, automotive industries, arms and other industries.

Abstract: The invention relates to a process that makes it possible to improve the mechanical strength of bonds between substrates when these bonds are produced by means of an adhesive that comprises a resin that can be cured by chain polymerization, and in particular a resin that can be cured under the effect of ionizing or light radiation. This process is characterized in that it comprises the grafting of groups capable of acting as chain transfer agents during the polymerization of said resin to the surface of the substrates, before the latter are brought into contact with the adhesive. Applications: assembling of structural, engine, passenger compartment or bodywork parts in the aeronautical, space, railway, ship-building and automotive industries.

Abstract: It relates to the use of curable resins containing a prepolymer based on glycidyl (meth)acrylate for making composite materials for use in space and, more particularly to composite materials entering the composition of structures intended to be deployed in space and to be stiffened after deployment.

Abstract: The invention relates to the stiffening of inflatably deployable structures, in particular for space use. More specifically, the invention relates to a flexible membrane for inflatably deployable structures, that comprises one layer of a composite and at least one polymer film that is permeable to visible radiation covering one of the faces of this layer, said composite being formed from a fibrous material impregnated with a composition incorporating an epoxide or epoxy/acrylate resin and a photoinitiator, and which is characterized in that the photoinitiator is an iron-arene complex salt of general formula (I): where A is an arene group, while X is a non-nucleophilic anion. Applications: manufacture of devices of the following types: radars, solar panels, reflectors, solar shields, antennas, solar mirrors or sails, intended to equip orbital vehicles or vehicles for space or planetary exploration.

Abstract: A method of using at least one polymerisable resin R1 is disclosed. According to some aspects, the resin R1 is selected from the group consisting of epoxidised polybutadiene resins, epoxidised polyisoprene resins, epoxidised polysiloxane resins, epoxidised triglyceride resins and epoxidised polyether resins. The resin R1 having at the non-polymerised state a total mass loss (TML) value lower than about 10%, a recovered mass loss (RML) value lower than about 10%, and a collected volatile condensable material (CVCM) value lower than about 1%, as determined in accordance with standard ECSS-Q-70-02A of the European Space Agency. The resin R1 also characterized by an epoxide equivalent weight of about 100 to 600 g/mole. The resin is configured for the manufacture of a composite material for use in space, and more specifically, a composite material of a Gossamer structure. Polymerisable resin compositions are also disclosed which are useful in the manufacture of composite materials for use in space.

Abstract: The invention relates to a method of assembling pre-impregnated plies by local isolated polymerization of the assembly region (30) under the action of a radiation to which the resin of the prepreg is sensitive. The assembly method makes it possible in particular to produce very large sized gossamer structures (7) in the form of a concertina-folded tube which is deployed by injecting pressurized gas once in space then stiffened by polymerization under the effect of the same radiation. The pylon concerned (7) thus comprises two structural elements (10, 20) secured end to end while at the same time maintaining its flexibility and firmness qualities.

Abstract: The invention relates to a device for controlling the deployment of an inflatable structure including, in the non-deployed state, a flexible tube (12) which is folded in zigzags and fixed to one end of a plug (13) provided with a buoyant gas admission (15), the other end of the tube being closed; means (25 to 29) for controlling the change of state of the tube from the folded state (12a) to the deployed state (30), the means being arranged inside the tube (12) and consisting of a set of interconnected flexible blades (25) which are radially arranged around the strut (16) in the form of petals, in such a way that the set can be displayed along the strut; and means (28, 29) for bringing the set of petals (25) towards the plug (13) in such a way as to press the folded part (12a) of the tube, each petal (25) being applied to a series of superimposed folds (21 to 24) of the folded part of the tube.

Abstract: The present invention relates to a process which makes it possible to improve the adhesion of carbon fibres with regard to an organic matrix forming, with these fibres, a composite material, this composite material being obtained by bringing the fibres into contact with a resin which can be cured by chain polymerization, followed by polymerization of the resin, which process consists in coating the surface of the carbon fibres, before these fibres are brought into contact with the resin, with a polymer film which comprises functional groups capable of acting as chain transfer agents during the polymerization of said resin. Applications: aeronautical, aerospatial, shipbuilding, railway and motor vehicle industries, armaments industry, sports and leisure articles, and the like.

Abstract: A multilayer wall includes Gossamer-type rigidifiable and inflatable structures, the wall including a layer of a composite material that can be rigidified by polymerisation, and is flanked, on the inside, by a gas-impermeable layer, and, on the outside, by at least one anti-adhesion and protection layer. The multilayer wall is characterised in that the external layer is partially permeable to gas and impermeable to liquid or viscous phases of the matrix of the composite material.

Abstract: The invention relates to a device for controlling the deployment of an inflatable structure including, in the non-deployed state, a flexible tube (12) which is folded in zigzags and fixed to one end of a plug (13) provided with a buoyant gas admission (15), the other end of the tube being closed; means (25 to 29) for controlling the change of state of the tube from the folded state (12a) to the deployed state (30), the means being arranged inside the tube (12) and consisting of a set of interconnected flexible blades (25) which are radially arranged around the strut (16) in the form of petals, in such a way that the set can be displayed along the strut; and means (28, 29) for bringing the set of petals (25) towards the plug (13) in such a way as to press the folded part (12a) of the tube, each petal (25) being applied to a series of superimposed folds (21 to 24) of the folded part of the tube.

Abstract: The invention relates to a material with high fracture toughness based on a vinyl ester resin and/or on an epoxide resin and to its process of manufacture. This material comprises at least one polymerized resin chosen from vinyl ester resins and epoxide resins which can be polymerized at a temperature of less than 70° C. and their blends, and a thermoplastic adjuvant present in this resin in the form of particles, and exhibits a fracture toughness (KIc) of greater than or equal to 1.2 MPa·m1/2 as determined according to Standard ISO 13586:2000. It also relates to a composite material comprising a matrix composed of said material and a reinforcement. Applications: automobile, railway, ship-building, aeronautical, aerospatial and other industries.

Abstract: The invention relates to a process that makes it possible to improve the mechanical strength of bonds between substrates when these bonds are produced by means of an adhesive that comprises a resin that can be cured by chain polymerization, and in particular a resin that can be cured under the effect of ionizing or light radiation. This process is characterized in that it comprises the grafting of groups capable of acting as chain transfer agents during the polymerization of said resin to the surface of the substrates, before the latter are brought into contact with the adhesive. Applications: assembling of structural, engine, passenger compartment or bodywork parts in the aeronautical, space, railway, ship-building and automotive industries.

Abstract: The invention relates to the stiffening of inflatably deployable structures, in particular for space use. More specifically, the invention relates to a flexible membrane for inflatably deployable structures, that comprises one layer of a composite and at least one polymer film that is permeable to visible radiation covering one of the faces of this layer, said composite being formed from a fibrous material impregnated with a composition incorporating an epoxide or epoxy/acrylate resin and a photoinitiator, and which is characterized in that the photoinitiator is an iron-arene complex salt of general formula (I): where A is an arene group, while X is a non-nucleophilic anion. Applications; manufacture of devices of the following types: radars, solar panels, reflectors, solar shields, antennas, solar mirrors or sails, intended to equip orbital vehicles or vehicles for space or planetary exploration.

Abstract: The invention relates to a process for improving the adhesion of carbon fibres with regard to an organic matrix forming a composite material with these fibres, this composite material being obtained by bringing the fibres into contact with a resin which can be cured by chain polymerization and then polymerizing the resin, which process is characterized in that it comprises the grafting, to the surface of the fibres, before they are brought into contact with the resin, of groups capable of acting as chain transfer agents during the polymerization of said resin. Fields of application: aeronautical, aerospatial, railway, ship building and automobile industries but also the armaments industry, the industry of sports and leisure articles, and the like.