An engine pylon rear secondary structure for an aircraft comprising an engine pylon (30) suspending an engine (20) to a wing (10), the engine pylon rear secondary structure comprising:
a front attachment interface (310);
an aft attachment interface (320);
a composite beam (301) connecting the front attachment interface (310) and the aft attachment interface (320);
the composite beam (301) comprising a first section (501) and a second section (502) integral with the first section;
frames (330) configured for supporting fairing panels (340) and being attached to the first section (501) of the composite beam; and
fairing panels (340) attached to outer faces of the frames;
wherein the composite beam is of a U-shaped cross-section, the frames (330) comprising three brackets (431, 432, 433) configured to be attached to the composite beam on three external faces of the U-shaped cross-section.
The invention relates to a stamping system comprising:
a trimmed thermoplastic composite blank (100);
a transfer frame (200) capable of supporting the blank;
a stamping device comprising a stamping die and a movable punch;
wherein:
the blank (100) comprises bore holes (121, 122) configured to cooperate with centering pins (212) carried by the transfer frame (200) and oblong slots (125, 126) configured to cooperate with guiding pins attached to the stamping die;
the transfer frame (200) comprises a comb-shaped supporting member (220) and holding pegs cooperating with holding slots (130); and
the transfer frame (200) comprises hinged thermally protecting flaps (214) configured to cover the blank around the positioning bore holes (121, 122, 123, 124)
B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
B29C 70/46 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs
3.
METHOD FOR RECYCLING SCRAP FROM THERMOPLASTIC COMPOSITE MATERIALS
The invention relates to a method for recycling scrap from parts made of composite material reinforced with continuous fibres in a thermoplastic polymer matrix, the method comprising the steps consisting in: i) obtaining a composite preform (110, 500) which is continuously reinforced and is suitable for obtaining a structural part; ii) obtaining the structural part (200, 400) from the composite preform which is continuously reinforced; iii) cutting out the structural part (200, 400); iv) recovering (310) the scrap (120, 220) produced in steps i) and iii); v) grinding (320) the scrap to obtain a ground material consisting of pieces of composites; vi) compounding (330) the ground material obtained in step v) to obtain a compound; vii) obtaining a second composite part (410, 600) by shaping the compound obtained in step vi).
B29C 70/00 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
B29K 105/08 - Condition, form or state of moulded material containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns
12 - Land, air and water vehicles; parts of land vehicles
14 - Precious metals and their alloys; jewelry; time-keeping instruments
17 - Rubber and plastic; packing and insulating materials
20 - Furniture and decorative products
28 - Games; toys; sports equipment
40 - Treatment of materials; recycling, air and water treatment,
Goods & Services
Hand tools and implements [hand-operated]; Cutlery; Table knives, forks and spoons of plastic; disposable tableware made of plastics. Orthopedic articles; Artificial limbs; Artificial limbs. Aeronautical apparatus, machines and appliances; Parts for vehicles; Monitor systems, for use in relation to the following goods: Aircraft; Foot pedals for aircraft; Plastic wings for use on aircraft; Head-rests for vehicle seats; Trailer hitches for vehicles; Crutches, for use in relation to the following goods: Vehicles; Wheelbarrows; Framework for vehicles; Hoods for vehicle engines; Bodies for vehicles; Trolleys; Carts; Vehicle chassis; Gears for vehicles; Hub caps; Axles for vehicles; Windshield wipers; Mudguards; Linings for vehicles; handle bars for vehicles; Rims for vehicle wheels; Vehicle joysticks; Vehicle running boards; Vehicle bumpers; Foot pedals for vehicles; Luggage carriers for vehicles; Doors for vehicles; Vehicle wheel spokes; Vehicle trailers; Tanks for vehicles; Rearview mirrors; Vehicle seats; Steering wheels for vehicles; Mine cars. Time instruments; Fittings for watches; Clock hands; Horological articles; Jewellery; Barrels (clock and watch-making); Plastic costume jewellery; Watch cases [parts of watches]; Watch straps of plastic; Dials for clock and watch making; Chronometers; Clocks; Watches; Movements for clocks and watches; Key rings. Elastomer polymers; Elastomeric polymers for use in manufacture; Carbon fibres, other than for textile use; polymeric material, based on the following products: Carbon fibre; polymeric material, For use in industry; Plastic semi-worked products, namely Plastic materials and plastic compounds for use in the following fields: Manufacturing processes; Semi-worked polymer resins; Carbon fibre reinforced synthetic resins for use in manufacture. Works of art of plastic. Sporting articles; Sporting apparatus, of plastic; Protective body wear for sport; Toys; Toys made of plastics; Sports equipment. Recycling of plastics; Treatment of materials, namely treatment of materials for the manufacture of plastic goods; Processing of plastics; Processing of plastics; Custom assembling of materials for others; Providing material treatment information; Custom 3D printing for others.
5.
METHOD FOR INTEGRATING A STIFFENER INTO A THERMOPLASTIC MATRIX COMPOSITE PART
The invention pertains to a composite part with a fibrous reinforcement and a thermoplastic polymer matrix, comprising: - a substrate part with a matrix of a first thermoplastic polymer having a first melting temperature; - a stiffener made of a composite material with a matrix of a second thermoplastic polymer having a second melting temperature; comprising the steps of: i) obtaining an unconsolidated preform of the substrate part; ii) obtaining a preform from the stiffener; iii) integrating a layer of the first thermoplastic polymer into the preform of the stiffener at the location intended to be in contact with the substrate part; iv) consolidate the preform of the stiffener integrating the layer of the first thermoplastic polymer; vi) applying a thermomechanical cycle to the substrate part and the consolidated stiffener so as to consolidate the substrate part and weld the stiffener to the substrate part.
A method for integrating a fitting (110) fitted between two wings of a composite profile (100) comprising the steps of: i) obtaining a preform of a fitting impregnated with a thermosetting resin, comprising two flanges (111) and a rib (114); ii) pre-curing the laminate preform of the fitting to obtain a partial polymerization of the preform; iii) draping a laminate preform of the profile so that fibers impregnated with a thermosetting resin included in two of the wings of the laminate preform of the profile are draped over the two flanges of the preform of the partially polymerized fitting; and iv) completely polymerizing an assembly comprising the laminate preform of the profile and the laminate preform of the partially polymerized fitting while maintaining into contact the flanges of the laminate preform of the fitting with the wings of the laminate preform of the profile. The invention also pertains to a tooling for implementing the method and a wing spar obtained by this method.
B29C 65/02 - Joining of preformed partsApparatus therefor by heating, with or without pressure
B29C 70/38 - Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
B29C 70/44 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
The invention pertains to a composite part with a fibrous reinforcement and a thermoplastic polymer matrix, comprising:
substrate part with a matrix of a first thermoplastic polymer having a first melting temperature;
stiffener made of a composite material with a matrix of a second thermoplastic polymer having a second melting temperature; comprising the steps of:
obtaining an unconsolidated preform of the substrate part;
obtaining a preform of the stiffener;
integrating a layer of the first thermoplastic polymer into the preform of the stiffener at a location configured to be in contact with the substrate part; and
subjecting the substrate part and the preform of stiffener to a thermomechanical cycle so as to consolidate the substrate part and weld the stiffener to the substrate part.
The invention relates to a tool for stamping a composite blank having a thermoplastic matrix reinforced by continuous fibres, as well as a stamping method using such a tool, the tool comprising: - a die comprising a cavity (110) having a bottom (111) and side walls (112); - a punch (120), the outer shape of which matches the cavity of the die, said punch comprising a middle portion (123) and at least two moveable side portions (121, 122) slidingly connected to the middle portion (123), such that when the side portions are blocked from moving translatably in the strike direction (190) against the bottom of the die, the movement of the middle portion (123) in the same direction causes the side portions to move translatably perpendicularly to the strike direction (190).
B29C 33/48 - Moulds or coresDetails thereof or accessories therefor with means for, or specially constructed to facilitate, the removal of articles, e.g. of undercut articles with means for collapsing or disassembling
B29C 70/46 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs
B29K 79/00 - Use of other polymers having nitrogen, with or without oxygen or carbon only, in the main chain, as moulding material
B29K 81/00 - Use of polymers having sulfur, with or without nitrogen, oxygen or carbon only, in the main chain, as moulding material
B29K 105/08 - Condition, form or state of moulded material containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns
L'invention concerne un procédé pour l'application d'un mastic polymérisable, mettant en oeuvre un dispositif comprenant : - une cartouche (210) sensiblement cylindrique comprenant un mastic polymérisable activé, ladite cartouche ayant une extrémité de distribution (211) et une extrémité de pression (212) ; - un réceptacle (110) de ladite cartouche comprenant une interface de connexion (111) avec son extrémité de distribution ; - des moyens de pression (215) agissant sur l'extrémité de pression (212) de la cartouche pour provoquer l'éjection du mastic activé par l'extrémité de distribution (211) ; - un ensemble d'application (120) comprenant une buse comportant un orifice d'application et un conduit d'amenée (122) du mastic dans ladite buse ; - ledit dispositif comprenant une aiguille (130) de fermeture, mobile en translation entre une position de fermeture où l'extrémité de l'aiguille obstrue l'orifice d'application de la buse et une position d'ouverture ou l'extrémité de l'aiguille est éloignée de l'orifice d'application, des moyens (135) pour manoeuvrer l'aiguille en translation entre ces deux positions.
B05D 1/26 - Processes for applying liquids or other fluent materials performed by applying the liquid or other fluent material from an outlet device in contact with, or almost in contact with, the surface
A leading edge slat of a wing element of an aircraft. The aircraft defining a mark including a main fuselage axis x and a spanwise axis y. The wing procuring a lift along an axis z. The wing element having a skin forming the leading edge slat, a spar linked to the skin and a stiffening structure linked on the leading edge side to the spar and to the skin. The stiffening structure being formed from a formed sheet metal having a plurality of bosses distributed according to the length of the leading edge. The bosses extending between the spar and the inner face of the skin.
A tool (200) suitable for manually or automatically applying a polymerisable sealing product to the edge of a composite part (100), said tool comprising: a. a fixed gripping portion (210) defining a grip orientation axis (201); b. an application portion (250), linked to the gripping portion so as to be able to pivot about an axis parallel to the grip orientation axis (201), and freely rotate with respect to the gripping portion, and comprising a rod (230) extending along the axis of rotation (201) of the link; c. characterised in that it comprises a cylindrical application pad (240) made up of a tubular foam sleeve (240) threaded onto the rod (230), constituted by a polyolefin foam comprising cells (241) open on the surfaces of the sleeve, capable of absorbing a product and of depositing in on a surface by contact with said surface.
B05C 1/00 - Apparatus in which liquid or other fluent material is applied to the surface of the work by contact with a member carrying the liquid or other fluent material, e.g. a porous member loaded with a liquid to be applied as a coating
B05C 7/06 - Apparatus specially designed for applying liquid or other fluent material to the inside of hollow work by devices moving in contact with the work
B05C 17/03 - Rollers with feed system for supplying material from an external source
12 - Land, air and water vehicles; parts of land vehicles
37 - Construction and mining; installation and repair services
Goods & Services
Airplanes Airplane servicing, maintenance and repair; information services in the nature of providing information regarding airplane servicing, maintenance and repair
12 - Land, air and water vehicles; parts of land vehicles
37 - Construction and mining; installation and repair services
Goods & Services
Aeroplanes. Aircraft servicing, maintenance and repair services; Providing of information relating to the repair, maintenance and servicing of aeroplanes.
12 - Land, air and water vehicles; parts of land vehicles
37 - Construction and mining; installation and repair services
Goods & Services
Aeroplanes. Aircraft servicing, maintenance and repair services; Providing of information relating to the repair, maintenance and servicing of aeroplane.
21.
Method and device for fireproofing a part in composite material
A device for fireproofing a section of a structural part made of composite material. The device includes a skin having an outer surface configured to face the flame and an inner surface. The skin is made of composite material that includes fibrous reinforcement in a polymer matrix. The skin includes a fastener to fasten the part to the structure. The device includes a layer of needled mineral felt placed between the inner surface of the skin and a surface of the structural part.
A62C 3/08 - Fire prevention, containment or extinguishing specially adapted for particular objects or places in vehicles, e.g. in road vehicles in aircraft
B64C 1/00 - FuselagesConstructional features common to fuselages, wings, stabilising surfaces or the like
B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
A method for making a first ply for laying up a fibrous preform on a tool. An attachment zone is made on the laying up surface of the tool. The zone is integral with the laying up surface of the tool. A polymer is deposited by additive manufacturing on the surface of the tool. The polymer deposit passes on the attachment zone. The first ply is laid up by activating the tackiness of the polymer deposited using additive manufacturing, so as to make the deposited fibers adhere to the material deposited by additive manufacturing.
B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
B29B 11/16 - Making preforms characterised by structure or composition comprising fillers or reinforcements
B29D 99/00 - Subject matter not provided for in other groups of this subclass
B29C 70/30 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core
A method for manufacturing a composite part with continuous fiber reinforcement and a polymer matrix from a composite preform. On one of the faces of the composite preform, a demarcated layer of thermoplastic polymer is deposited using an additive manufacturing method.
B29C 70/84 - Moulding material on preformed parts to be joined
B29C 70/68 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers
B29C 65/04 - Dielectric heating, e.g. high-frequency welding
B29C 69/00 - Combinations of shaping techniques not provided for in a single one of main groups , e.g. associations of moulding and joining techniquesApparatus therefor
A method for assembling a box structure includes elementary parts assembled along an understructure of stiffeners and skins. The understructure and skins are made of composite material with a polymer matrix. The method includes sizing the box structure for the loads to which it is subjected and for a glued assembly. A map of the loads on the structure is obtained and a first load limit is defined depending on the probability of the structure being damaged. The understructure and the skins are assembled by gluing them. An additional layer is applied that covers the assembled elementary parts to areas of the assembled box structure where the first load limit is reached.
A method for the hot stamping of a composite part with continuous fiber reinforcement in a thermoplastic matrix. A blank including a laminated structure of plies consisting in unidirectional tapes of fibers pre-impregnated with thermoplastic polymer is obtained. The blank is heated in the open to a temperature greater than or equal to the melting temperature of the polymer making up the matrix. The blank is then stamped.
B29C 70/34 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression
B29C 70/38 - Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
B29C 59/00 - Surface shaping, e.g. embossingApparatus therefor
B29C 59/02 - Surface shaping, e.g. embossingApparatus therefor by mechanical means, e.g. pressing
B29K 71/00 - Use of polyethers as moulding material
B29L 31/30 - Vehicles, e.g. ships or aircraft, or body parts thereof
26.
Device and method for forming a composite panel from a thermoplastic matrix
An apparatus and method for stamping a thermoplastic matrix composite blank, in view of heating and stamping the blank. The apparatus includes a machined blank and a frame. A plurality of cleats are fixed on the frame, extend towards the interior of the frame. The cleats delimit an internal opening surface of the frame, free from any obstacle. A locator is linked with a cleat and configured to cooperate with a hole machined in the blank. A heat sink is located near the locator and configured to maintain locally the blank temperature under the melting temperature of the polymer constituting the matrix, during the heating and transfer of the blank.
B29C 51/26 - Component parts, details or accessoriesAuxiliary operations
B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
B29C 59/02 - Surface shaping, e.g. embossingApparatus therefor by mechanical means, e.g. pressing
B29C 51/14 - Shaping by thermoforming, e.g. shaping sheets in matched moulds or by deep-drawingApparatus therefor using multilayered preforms or sheets
B29C 59/00 - Surface shaping, e.g. embossingApparatus therefor
B29C 70/42 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles
The invention relates to a device for fireproofing a section of a structural part (100) formed of a composite material. Said device is characterized in that it comprises: a. a skin (110, 210) comprising an outer surface that is intended to face the flame and an inner surface, said skin being formed of a composite material that comprises a fiber reinforcement in a polymer matrix, and comprising means (111) for attachment to the structural part; and b. an inorganic needled felt layer (120) inserted between the inner surface of the skin and a surface of the structural part (100).
A62C 3/08 - Fire prevention, containment or extinguishing specially adapted for particular objects or places in vehicles, e.g. in road vehicles in aircraft
B32B 27/04 - Layered products essentially comprising synthetic resin as impregnant, bonding, or embedding substance
The invention relates to a device for fireproofing a section of a structural part (100) formed of a composite material. Said device is characterized in that it comprises: a. a skin (110, 210) comprising an outer surface that is intended to face the flame and an inner surface, said skin being formed of a composite material that comprises a fiber reinforcement in a polymer matrix, and comprising means (111) for attachment to the structural part; and b. an inorganic needled felt layer (120) inserted between the inner surface of the skin and a surface of the structural part (100).
A62C 3/08 - Fire prevention, containment or extinguishing specially adapted for particular objects or places in vehicles, e.g. in road vehicles in aircraft
The invention concerns a method for producing a composite part having a continuous fibrous reinforcement and a polymer matrix from a composite preform, characterised in that it comprises a step consisting of: i. depositing a defined layer (110, 120) of a thermoplastic polymer on one of the faces of the preform (100), by an additive production method.
B29C 70/68 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers
30.
METHOD FOR PRODUCING A COMPLEX COMPOSITE PART, IN PARTICULAR HAVING A THERMOPLASTIC MATRIX, AND PART OBTAINED BY SUCH A METHOD
The invention concerns a method for producing a composite part having a continuous fibrous reinforcement and a polymer matrix from a composite preform, characterised in that it comprises a step consisting of: i. depositing a defined layer (110, 120) of a thermoplastic polymer on one of the faces of the preform (100), by an additive production method.
B29C 67/00 - Shaping techniques not covered by groups , or
B29C 70/68 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers
The invention relates to a method for producing a first draping ply of a fibrous preform on a mold (100), characterised in that said method includes the following steps: a) forming a so-called catching area (120) on the draping surface (101) of the mold, said area being rigidly connected to said draping surface of the mold; b) depositing a polymer (131, 132) by additive manufacturing onto the surface of the mold, the deposition process being carried out over the catching area; c) draping the first ply by activating the tack of the polymer (131, 132) deposited by additive manufacturing so as to adhere the deposited fibres to the material deposited by additive manufacturing.
The invention relates to a method for producing a first draping ply of a fibrous preform on a mold (100), characterised in that said method includes the following steps: a. forming a so-called catching area (120) on the draping surface (101) of the mold, said area being rigidly connected to said draping surface of the mold; b. depositing a polymer (131, 132) by additive manufacturing onto the surface of the mold, the deposition process being carried out over the catching area; c. draping the first ply by activating the tack of the polymer (131, 132) deposited by additive manufacturing so as to adhere the deposited fibres to the material deposited by additive manufacturing.
The invention relates to a method, and wings (100) for an aircraft obtained by said method, for assembling a casing structure (100) including basic parts (230, 240, 321) that are assembled according to a sub-structure of stiffeners (230, 240), and skins (321). The sub-structure and the skins consist of a polymer matrix composite material. Said method includes steps involving: a. sizing the casing structure on the basis of the biasing that said structure is subjected thereto, and for an adhered assembly; b. obtaining a mapping of the biasing of said structure and defining a first biasing threshold on the basis of probability of damage to the structure; c. assembling the sub-structure and the skins by adhesion; and d. applying counter-stratification (350) covering the assembled basic parts, in the areas of the assembled casing structure where the first biasing threshold is reached.
The invention relates to a method, and wings (100) for an aircraft obtained by said method, for assembling a casing structure (100) including basic parts (230, 240, 321) that are assembled according to a sub-structure of stiffeners (230, 240), and skins (321). The sub-structure and the skins consist of a polymer matrix composite material. Said method includes steps involving: a. sizing the casing structure on the basis of the biasing that said structure is subjected thereto, and for an adhered assembly; b. obtaining a mapping of the biasing of said structure and defining a first biasing threshold on the basis of probability of damage to the structure; c. assembling the sub-structure and the skins by adhesion; and d. applying counter-stratification (350) covering the assembled basic parts, in the areas of the assembled casing structure where the first biasing threshold is reached.
The invention relates to a method for manufacturing, by hot-stamping, a composite part having continuous fibrous reinforcement in a thermoplastic matrix, characterised in that said method comprises the following steps: a) obtaining a blank (160) including a stratification of folds consisting of unidirectional layers (110) of fibres pre-impregnated with a thermoplastic polymer; b) heating the blank (160) in the open air to a temperature no lower than the melting temperature of the polymer that makes up the matrix; and c) stamping the blank (160).
B29C 70/34 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression
B29C 70/38 - Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
36.
METHOD AND DEVICE FOR STAMPING A COMPOSITE BLANK WITH NON-CONSOLIDATED THERMOPLASTIC MATRIX
The invention relates to a method for manufacturing, by hot-stamping, a composite part having continuous fibrous reinforcement in a thermoplastic matrix, characterised in that said method comprises the following steps: a) obtaining a blank (160) including a stratification of folds consisting of unidirectional layers (110) of fibres pre-impregnated with a thermoplastic polymer; b) heating the blank (160) in the open air to a temperature no lower than the melting temperature of the polymer that makes up the matrix; and c) stamping the blank (160).
B29C 70/34 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression
B29C 70/38 - Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
37.
DEVICE AND METHOD FOR FORMING A COMPOSITE PANEL FROM A THERMOPLASTIC MATRIX
The invention relates to a device and a method for forming a composite panel (100) from a thermoplastic matrix, for heating and forming said panel, the device comprising a frame, a plurality of lugs (220) fixed on said frame and extending into the interior thereof and delimiting and internal opening surface of the frame, free from any obstacle, a centring device (221) rigidly connected to one lug and capable of engaging with a hole (121) machined in the panel, characterized in that near to the centring device (221) the device comprises a means (220), termed a heat sink, capable of keeping the local temperature of the panel below the melting temperature of the polymer comprising the matrix of the panel.
B29C 51/14 - Shaping by thermoforming, e.g. shaping sheets in matched moulds or by deep-drawingApparatus therefor using multilayered preforms or sheets
B29C 51/26 - Component parts, details or accessoriesAuxiliary operations
B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
The invention relates to a device and a method for forming a composite panel (100) from a thermoplastic matrix, for heating and forming said panel, the device comprising a frame, a plurality of lugs (220) fixed on said frame and extending into the interior thereof and delimiting and internal opening surface of the frame, free from any obstacle, a centring device (221) rigidly connected to one lug and capable of engaging with a hole (121) machined in the panel, characterized in that near to the centring device (221) the device comprises a means (220), termed a heat sink, capable of keeping the local temperature of the panel below the melting temperature of the polymer comprising the matrix of the panel.
B29C 51/14 - Shaping by thermoforming, e.g. shaping sheets in matched moulds or by deep-drawingApparatus therefor using multilayered preforms or sheets
B29C 51/26 - Component parts, details or accessoriesAuxiliary operations
B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
39.
Device for high-temperature welding of a stiffener on a composite panel having a thermoplastic matrix
A device for welding the bottom flange of a stiffener on the side of a skin. The stiffener and the skin are made of a composite comprising a thermoplastic polymer matrix. The device comprises a punch, an anvil and a press to make a clamping between the punch and the anvil. The punch comprises a part forming a pressure table with a cross-section width less than or equal to the width of the stiffener bottom flange and a heating element with width less than the width of the pressure table. The anvil comprises a cooling component and has a cross-section width smaller than the width of the skin. A method for implementing the device.
B32B 37/10 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the pressing technique, e.g. using direct action of vacuum or fluid pressure
B29C 65/18 - Joining of preformed partsApparatus therefor by heating, with or without pressure using heated tool
B29C 65/00 - Joining of preformed partsApparatus therefor
A method for forming a thermoplastic composite material with continuous fiber reinforcement by stamping. A flat blank comprising a pre-consolidated stack of plies by automatic fiber placement of fibers referred to as the thermoplastic pre-impregnated fibers is obtained. The flat blank is reheated to a temperature greater than or equal to the melting temperature of the thermoplastic polymer making up the matrix of the thermoplastic pre-impregnated fibers. The reheated flat blank is hot stamped and the part formed between the stamping punch and die is consolidated.
B29C 70/38 - Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
B29C 65/02 - Joining of preformed partsApparatus therefor by heating, with or without pressure
B29C 70/34 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression
B29C 70/22 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure
B29C 51/00 - Shaping by thermoforming, e.g. shaping sheets in matched moulds or by deep-drawingApparatus therefor
B29D 99/00 - Subject matter not provided for in other groups of this subclass
A device for compacting and consolidating a stack of fibrous plies pre-impregnated with a thermoplastic polymer, configured to be placed in an oven. The device comprises containment blocks, a flexible compacting plate and a vacuum pump. The containment blocks are supported by a board and demarcate the perimeter of the stack. The containment blocks comprise open grooves that open into the perimeter of the stack. The flexible compacting plate has an area equal to that of the stack but is capable of being inserted inside the perimeter demarcated by the containment blocks. The vacuum pump applies a vacuum to the wrapped volume of the stack comprising a plurality of holes in the board that open outside the perimeter of the stack. A method for implementing the device for manufacturing a thick composite panel having a thermoplastic matrix.
B29C 70/44 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
B64C 1/12 - Construction or attachment of skin panels
B29C 70/08 - Fibrous reinforcements only comprising combinations of different forms of fibrous reinforcements incorporated in matrix material, forming one or more layers, with or without non-reinforced layers
B29C 70/02 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising combinations of reinforcements and fillers incorporated in matrix material, forming one or more layers, with or without non-reinforced or non-filled layers
B32B 5/26 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer another layer also being fibrous or filamentary
B29C 43/36 - Moulds for making articles of definite length, i.e. discrete articles
B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
B32B 15/08 - Layered products essentially comprising metal comprising metal as the main or only constituent of a layer, next to another layer of a specific substance of synthetic resin
B29C 70/88 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts characterised primarily by possessing specific properties, e.g. electrically conductive or locally reinforced
B32B 15/04 - Layered products essentially comprising metal comprising metal as the main or only constituent of a layer, next to another layer of a specific substance
A method for assembling a skin and a flange of a stiffener. The periphery of the contact between the skin and the flange of the stiffener is sealed by applying a bead of adhesive on the flange of the stiffener in contact with the skin. A first and second orifices are made in the skin. The orifices open at the interface between the skin and the flange of the stiffener. The adhesive is injected through the first orifice at the interface between the skin and the flange of the stiffener while keeping the skin in contact with the stiffener until the interface between the skin and the stiffener is completely filled with the adhesive.
A method for making a structural element comprising a panel in composite material with fiber reinforcement in an organic matrix obtained by laying up and curing. The panel comprises a side likely to be exposed to contact with hydrocarbons. The required layer structure is obtained by laying up the plies of fibers pre-impregnated with resin having a curing temperature T1. A ply made of a thin film of polymer that can withstand hydrocarbons and the curing temperature T1, referred to as the protective film, is applied on the side exposed to hydrocarbons. The entire layered structure is cured under pressure at the temperature T1.
B29C 70/88 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts characterised primarily by possessing specific properties, e.g. electrically conductive or locally reinforced
B29C 70/08 - Fibrous reinforcements only comprising combinations of different forms of fibrous reinforcements incorporated in matrix material, forming one or more layers, with or without non-reinforced layers
B64C 3/34 - Tanks constructed integrally with wings, e.g. for fuel or water
2 in a direction that is locally normal to the skin, which is made up of a stack of fibrous plies in a matrix made of thermoplastic polymer. The surface of the plies that make up the patch is decreasing from the ply of the patch in contact with the skin so that the edges of the patch have a slope p greater than 0.5. The patch and the skin is joined by a weld.
B29C 65/00 - Joining of preformed partsApparatus therefor
B29C 65/02 - Joining of preformed partsApparatus therefor by heating, with or without pressure
B29C 70/34 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression
B29D 99/00 - Subject matter not provided for in other groups of this subclass
B32B 5/26 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer another layer also being fibrous or filamentary
B32B 37/10 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the pressing technique, e.g. using direct action of vacuum or fluid pressure
B32B 38/00 - Ancillary operations in connection with laminating processes
B64C 1/12 - Construction or attachment of skin panels
B29L 31/30 - Vehicles, e.g. ships or aircraft, or body parts thereof
45.
Double-sided stiffened composite panel and method for producing such a panel
A stiffened panel and method for producing such a panel comprising a laminated skin extending in two directions, made of a resin and a continuous fibers reinforcement. A first stiffener in the form of a beam is made of a resin with continuous fibers reinforcement and extends on a first side of the laminated skin in a first direction. A second stiffener in the form of a beam is made of a resin with continuous fibers reinforcement and extends on a second side of the laminated skin in a second direction. The resins which make up the skin and the stiffeners are thermoplastic in nature and the stiffeners are closely joined to the skin by welding.
B29C 65/50 - Joining of preformed partsApparatus therefor using adhesives using adhesive tape
B29C 70/34 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression
B29D 99/00 - Subject matter not provided for in other groups of this subclass
B29C 65/48 - Joining of preformed partsApparatus therefor using adhesives
B29L 31/30 - Vehicles, e.g. ships or aircraft, or body parts thereof
46.
METHOD FOR PRODUCING A WINDOW FRAME FROM A COMPOSITE MATERIAL WITH A FIBROUS REINFORCEMENT AND A WINDOW OBTAINED BY SUCH A METHOD
The invention concerns a method for producing a frame comprising a section extruded according to a guide contour, said section comprising a flange and a web extending in section in directions concurrent and perpendicular to the guide contour, characterised in that it comprises the steps consisting of: a. making a fibrous preform, called a sock, having a tubular section, by means of a braiding method; b. flattening the tubular section of said sock and applying same, as a strip (200'), according to a first portion (210) of the width of said strip, onto the first face (310) of a tool (300) comprising two concurrent faces (3120, 320) whereof the intersection is parallel to the guide contour; c. folding the second portion (220) of said strip (200') onto a face (320) of the tool concurrent with the first face; d. consolidating the preform made in this way by combining same with a polymer resin. The invention also concerns a window obtained by such a method, in particular for an aircraft.
B29C 70/22 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure
B29C 70/30 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core
B64C 1/14 - WindowsDoorsHatch covers or access panelsSurrounding frame structuresCanopiesWindscreens
The invention relates to a device for welding the base plate (125) of a stiffener (120) to the face of a skin (110), the stiffener (120) and said skin (110) being constituted of a composite comprising a thermoplastic polymer matrix, characterized in that it comprises: a. a punch (220) comprising a part that forms a press table, the cross-sectional width of which is less than or equal to the width of the base plate (125) of the stiffener and a heating element (225, 226) having a width smaller than the width of the press table; b. an anvil (210), the cross-sectional width of which is smaller than the width of the skin, which anvil comprises cooling means; c. pressing means (251, 252) capable of carrying out a clamping between the punch and the anvil. The invention also relates to a process implementing this device.
The invention relates to a device (100) for compacting and consolidating a stack (110) of fibrous plies preimpregnated with a thermoplastic polymer, which is capable of being placed in an oven, characterized in that it comprises: - spaces (130), referred to as containment spaces, resting on the surface plate (120) and delimiting the perimeter of the stack, said spaces (130) comprising open grooves (131, 132, 133) that open into the perimeter of the stack; - a flexible compacting metal plate (140) having a surface area equal to the surface area of the stack (110) but capable of being inserted inside the perimeter delimited by the containment spaces (130); - means (150, 125) for putting the volume thus enveloped under vacuum comprising a plurality of orifices (125) in the surface plate (120), said plurality consisting of orifices that open outside of the perimeter of the stack. The invention also relates to a process implementing this device for the production of a thick composite panel having a thermoplastic matrix.
B29C 43/36 - Moulds for making articles of definite length, i.e. discrete articles
B29C 70/44 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
49.
PROCESS AND DEVICE FOR THE HIGH-TEMPERATURE WELDING OF A STIFFENER TO A COMPOSITE PANEL HAVING A THERMOPLASTIC MATRIX
The invention relates to a device for welding the base plate (125) of a stiffener (120) to the face of a skin (110), the stiffener (120) and said skin (110) being constituted of a composite comprising a thermoplastic polymer matrix, characterized in that it comprises: a. a punch (220) comprising a part that forms a press table, the cross-sectional width of which is less than or equal to the width of the base plate (125) of the stiffener and a heating element (225, 226) having a width smaller than the width of the press table; b. an anvil (210), the cross-sectional width of which is smaller than the width of the skin, which anvil comprises cooling means; c. pressing means (251, 252) capable of carrying out a clamping between the punch and the anvil. The invention also relates to a process implementing this device.
The invention relates to a method of forming a thermoplastic composite material with continuous-fibre reinforcement by stamping, characterised in that it comprises the steps consisting of: a. obtaining a planar blank (230), comprising a preconsolidated stack of plies, produced by automatically positioning so-called pre-impregnated thermoplastic fibres (210, 220); b. heating said blank (230) to a temperature greater than or equal to the melting temperature of the polymer forming the matrix; c. hot-stamping the blank heated in this way and consolidating the part (250) formed in this way between the punch and the stamping die.
B29C 70/22 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure
B29C 51/00 - Shaping by thermoforming, e.g. shaping sheets in matched moulds or by deep-drawingApparatus therefor
B29C 70/34 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression
B29C 70/38 - Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
B64C 1/00 - FuselagesConstructional features common to fuselages, wings, stabilising surfaces or the like
The invention relates to a device (100) for compacting and consolidating a stack (110) of fibrous plies preimpregnated with a thermoplastic polymer, which is capable of being placed in an oven, characterized in that it comprises: - spaces (130), referred to as containment spaces, resting on the surface plate (120) and delimiting the perimeter of the stack, said spaces (130) comprising open grooves (131, 132, 133) that open into the perimeter of the stack; - a flexible compacting metal plate (140) having a surface area equal to the surface area of the stack (110) but capable of being inserted inside the perimeter delimited by the containment spaces (130); - means (150, 125) for putting the volume thus enveloped under vacuum comprising a plurality of orifices (125) in the surface plate (120), said plurality consisting of orifices that open outside of the perimeter of the stack. The invention also relates to a process implementing this device for the production of a thick composite panel having a thermoplastic matrix.
B29C 43/36 - Moulds for making articles of definite length, i.e. discrete articles
B29C 70/44 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
52.
METHOD OF FORMING A THERMOPLASTIC COMPOSITE MATERIAL WITH CONTINUOUS-FIBRE REINFORCEMENT BY STAMPING
The invention relates to a method of forming a thermoplastic composite material with continuous-fibre reinforcement by stamping, characterised in that it comprises the steps consisting of: a. obtaining a planar blank (230), comprising a preconsolidated stack of plies, produced by automatically positioning so-called pre-impregnated thermoplastic fibres (210, 220); b. heating said blank (230) to a temperature greater than or equal to the melting temperature of the polymer forming the matrix; c. hot-stamping the blank heated in this way and consolidating the part (250) formed in this way between the punch and the stamping die.
B29C 70/22 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure
B29C 70/34 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression
B29C 70/38 - Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
B29C 51/00 - Shaping by thermoforming, e.g. shaping sheets in matched moulds or by deep-drawingApparatus therefor
The invention relates to a method for creating a structural element comprising a panel (110, 121, 122) made of a composite material having a fibrous reinforcement in an organic matrix obtained by layup and curing, which panel comprises a face liable to be exposed to contact with hydrocarbons, characterized in that it comprises the steps involving: laying up the plies of fibres preimpregnated with a resin that has a first curing temperature, T1, so as to obtain the desired layering effect; applying to the face that is exposed to the hydrocarbons a ply consisting of a thin film (130, 131, 132) of a polymer that is resistant to hydrocarbons and able to withstand the curing temperature T1, referred to as the protective film (130, 131, 132); curing the entire layered structure under pressure at the temperature T1.
B29C 70/08 - Fibrous reinforcements only comprising combinations of different forms of fibrous reinforcements incorporated in matrix material, forming one or more layers, with or without non-reinforced layers
B29C 70/88 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts characterised primarily by possessing specific properties, e.g. electrically conductive or locally reinforced
The invention relates to a method for assembling a skin (102) and the flange of a stiffener, characterized in that it involves the steps consisting in: a. sealing the periphery of the contact between the skin and the flange of the stiffener by applying a bead (210, 211) of adhesive to the flange of the stiffener in contact with the skin; b. creating a first and a second orifice, known as vent orifices, in the skin, said orifices opening at the interface between the skin and the flange of the stiffener; c. injecting adhesive through the first orifice termed the injection orifice at the interface between the skin and the flange of the stiffener while keeping said skin in contact with the stiffener until adhesive has fully filled the interface between the skin and the stiffener.
The invention relates to a method for assembling a skin (102) and the flange of a stiffener, characterized in that it involves the steps consisting in: a. sealing the periphery of the contact between the skin and the flange of the stiffener by applying a bead (210, 211) of adhesive to the flange of the stiffener in contact with the skin; b. creating a first and a second orifice, known as vent orifices, in the skin, said orifices opening at the interface between the skin and the flange of the stiffener; c. injecting adhesive through the first orifice termed the injection orifice at the interface between the skin and the flange of the stiffener while keeping said skin in contact with the stiffener until adhesive has fully filled the interface between the skin and the stiffener.
Laminated composite structural panel with fibrous reinforcement comprising: a. a skin (101) of thickness e1, made up of a stack of fibrous plies in a matrix made of a thermoplastic polymer; b. a localized reinforcement or patch (102), connected to the surface of said skin (101) and rising up by a thickness e2 in a direction locally normal to the skin, made up of a stack of fibrous plies in a matrix made up of a thermoplastic polymer; c. the surface area of the plies that make up said patch decreases from the ply of the patch (102) that is in contact with the skin (101), such that the edges of said patch (102) are inclined by a slope p greater than 0.5 and such that the connection between the patch (102) and the skin (101) consists in a weld.
B29C 65/02 - Joining of preformed partsApparatus therefor by heating, with or without pressure
B29C 70/34 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression
B64C 1/12 - Construction or attachment of skin panels
57.
METHOD FOR LOCALLY STRENGTHENING A COMPOSITE PANEL WITH FIBROUS REINFORCEMENT AND PANEL OBTAINED USING SUCH A METHOD
Laminated composite structural panel with fibrous reinforcement comprising: a. a skin (101) of thickness e1, made up of a stack of fibrous plies in a matrix made of a thermoplastic polymer; b. a localized reinforcement or patch (102), connected to the surface of said skin (101) and rising up by a thickness e2 in a direction locally normal to the skin, made up of a stack of fibrous plies in a matrix made up of a thermoplastic polymer; c. the surface area of the plies that make up said patch decreases from the ply of the patch (102) that is in contact with the skin (101), such that the edges of said patch (102) are inclined by a slope p greater than 0.5 and such that the connection between the patch (102) and the skin (101) consists in a weld.
B29C 70/34 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression
B29D 99/00 - Subject matter not provided for in other groups of this subclass
B29C 65/02 - Joining of preformed partsApparatus therefor by heating, with or without pressure
B64C 1/12 - Construction or attachment of skin panels
58.
METHOD FOR LAYING UP AND CONSOLIDATING DURING LAYING THERMOPLASTIC COMPOSITE COMPONENTS CONTAINING FIBROUS REINFORCEMENTS
The invention relates to a method for laying up a strip (110) of fibres containing a thermoplastic polymer and for consolidating during laying of a component thus laid up, said method involving the steps consisting in: a. pre-consolidating a strip (115) through the pultrusion (120) of rovings (110) that have been pre-impregnated with a thermoplastic polymer through a die; b. storing said pre-consolidated strip in the form of a semifinished product; c. laying up said semifinished product on a ply (117) of the same kind, previously laid on a form (150) while pressing (165) said semifinished product (115) onto said ply (117) and heating the interface between the semifinished product and the ply (117) already laid to a temperature T capable of causing the semifinished product (115) to weld to said ply (117).
The invention relates to a stiffened panel (100) including: a) a laminated skin (110) extending in two direction and consisting of a resin and a continuous fibrous reinforcement; b) a first profiled stiffener (110) consisting of a resin reinforced by a continuous fibrous reinforcement, said first stiffener extending over a first surface of said skin (110) in a first direction; and c) a second profiled stiffener (130) consisting of a resin reinforced by a continuous fibrous reinforcement, said second stiffener extending over a second surface of said skin (110) in a second direction; d) wherein the resins constituting the skin (110) and the stiffeners (120, 130) are thermoplastic and said stiffeners (120, 130) are closely connected to the skin (110) by a weld. The invention further relates to an advantageous method for creating such a panel.
B29D 99/00 - Subject matter not provided for in other groups of this subclass
B29C 65/00 - Joining of preformed partsApparatus therefor
B29C 65/02 - Joining of preformed partsApparatus therefor by heating, with or without pressure
B29C 65/50 - Joining of preformed partsApparatus therefor using adhesives using adhesive tape
B29C 70/34 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression
60.
DOUBLE-SIDED STIFFENED COMPOSITE PANEL, AND METHOD FOR PRODUCING SUCH A PANEL
The invention relates to a stiffened panel (100) including: a) a laminated skin (110) extending in two direction and consisting of a resin and a continuous fibrous reinforcement; b) a first profiled stiffener (110) consisting of a resin reinforced by a continuous fibrous reinforcement, said first stiffener extending over a first surface of said skin (110) in a first direction; and c) a second profiled stiffener (130) consisting of a resin reinforced by a continuous fibrous reinforcement, said second stiffener extending over a second surface of said skin (110) in a second direction; d) wherein the resins constituting the skin (110) and the stiffeners (120, 130) are thermoplastic and said stiffeners (120, 130) are closely connected to the skin (110) by a weld. The invention further relates to an advantageous method for creating such a panel.
B29D 99/00 - Subject matter not provided for in other groups of this subclass
B29C 65/02 - Joining of preformed partsApparatus therefor by heating, with or without pressure
B29C 65/50 - Joining of preformed partsApparatus therefor using adhesives using adhesive tape
B29C 65/00 - Joining of preformed partsApparatus therefor
B29C 70/34 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression
61.
SELF-STIFFENED COMPOSITE PANEL, PARTICULARLY FOR AN AIRCRAFT FLOOR, AND METHOD FOR MANUFACTURING SUCH A PANEL
The invention relates to a panel (750), particularly for an aircraft floor, characterized in that it includes: a) a first plate (220) made of a composite material reinforced with continuous fibers; b) a corrugated sheet (730) made of a composite material reinforced with continuous fibers, which is coupled to a so-called lower surface of the first plate (220); and c) a local reinforcement means (751, 753, 752) which is coupled to the corrugated sheet (730).
B32B 3/28 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layerLayered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a layer with cavities or internal voids characterised by a layer comprising a deformed thin sheet, e.g. corrugated, crumpled
12 - Land, air and water vehicles; parts of land vehicles
37 - Construction and mining; installation and repair services
Goods & Services
Aeroplanes. Servicing, maintenance and repair services for aeroplanes;
information services on construction, repair and servicing
of aeroplanes, aeronautical construction.
12 - Land, air and water vehicles; parts of land vehicles
37 - Construction and mining; installation and repair services
Goods & Services
Motors and engines (except for land vehicles); Motors for airplanes; Aircraft engines; Machine couplings (non-electric) and transmission components (except for land vehicles); Aeronautical engines; Aeronautical engines; Filters for cleaning cooling air for engines; Carburetter feeders; Sparking plugs for internal combustion engines; Ignition devices for internal combustion engines; Transmission shafts (other than for land vehicles); Connecting rods for engines; Control and operating cables for machines, engines or motors; Driving chains other than for land vehicles; Transmission chains, other than for land vehicles; Control mechanisms for engines or motors; Pneumatic controls for motors and engines; conversion apparatus (fuel —) for internal combustion engines; Torque converters other than for land vehicles; Belts for motors and engines; Cylinder heads for engines; Cylinders for motors and engines; Starters for motors and engines; Heat exchangers (parts of machines); Exhausts for motors and engines; Fuel economisers for motors and engines; Ejectors; Clutches other than for land vehicles; Gears other than for land vehicles; Blowing machines for the compression and exhaustion of gases; Electric generators; Emergency power generating installations; Hydraulic controls for machines, motors and engines; Hydraulic engines and motors; Hydraulic turbines; Joints (parts of engines); Universal joints; Anti-pollution devices for motors and engines; Injectors for engines; Pistons for engines; Speed governors for machines, engines and motors; Driving motors, other than for land vehicles; Pressure reducers (parts of machines); Pressure regulators (parts of machines); Pressure valves (parts of machines); Propulsion mechanisms other than for land vehicles; Radiators (cooling) for motors and engines; Jet engines other than for land vehicles; Regulators being parts of machines; Springs (parts of machines); Valves (parts of machines); Stators; Superheaters; Superchargers; Heat exchangers (parts of machines); Transmissions other than for land vehicles; Turbines other than for land vehicles; Turbocompressors; Fans for motors and engines; Gears (other than for land vehicles). Aeronautical and aerospace apparatus, machines and devices; Component parts of aircraft, for tidying the interior of the cockpit, the cabins and the holds of aircraft, namely wall panelling, luggage compartments, luggage holds, flooring, dashboards, pylons; Structural parts of aircraft, namely, externally, leading edge, cowl, fairing, empennage, air inlet, bailer, door, girder, shutter, tail cone, and internally, avionics rack, electric furniture, firewall; Apparatus for locomotion by land; Vehicles, including lorries; Goods handling carts, fork-lift trucks; Hydraulic circuits. Building construction; Repair services, notably repair of printed circuits (logic cards); Installation, repair and maintenance of warehouses; Repair and maintenance of lorries, containers and handling apparatus and storage containers Construction, installation, maintenance and repair of technical shelters; Repair and maintenance of machines and machine tools, motors and engines (except for motors and engines for land vehicles), automatic handling machines (manipulators), robots (machines), handling apparatus (loading and unloading), lifting apparatus, goods handling carts, lifting cars (lift cars), vehicles, lorries and containers for industrial waste; Interior design services for aircraft interiors, namely installation of luggage compartments, luggage holds, wall panelling, crew rest rooms, holds, cabins and cockpits, flooring, partitions; Assembly, mounting and dismantling of factories and nuclear power stations; Assembly, mounting and dismantling of industrial assemblies and sub-assemblies.
The present invention relates to a composite material panel (1) comprising a composite material skin (2) having two generally opposite surfaces (20, 21) and first stiffeners (30) extending over one of the surfaces (20) of the skin. Said panel is characterized in that it comprises supplementary stiffeners (31) that are arranged on the surface (21) of the skin opposite the one having the first stiffeners (30), said supplementary stiffeners moreover extending in a direction separate from that of the first stiffeners (30). The skin and the stiffeners arranged on each surface are preferably secured to each other by means of co-molding.
B29C 70/00 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
B32B 5/02 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments
66.
Stamping tooling for thermoplastic parts and method
A tooling for manufacturing by stamping parts made of thermoplastic material from a blank of the material. A hollow die is delimited by a bottom, side walls and an opening opposite the bottom, and a raised punch designed to cooperate with the die via the opening. The tooling includes at least one mobile element to cooperate with at least one recess placed in the bottom and/or side walls of the die, the recess allowing the passage of one part of the blank that is to be bent using the mobile element.
09 - Scientific and electric apparatus and instruments
12 - Land, air and water vehicles; parts of land vehicles
16 - Paper, cardboard and goods made from these materials
37 - Construction and mining; installation and repair services
41 - Education, entertainment, sporting and cultural services
42 - Scientific, technological and industrial services, research and design
Goods & Services
Motors (except for motors for land vehicles); aircraft motors and their component parts; couplings (non-electrical) and transmission devices (except those for terrestrial vehicles); motors for aeronautics, motors for aerostations; filters for engine cooling air cleaning purposes; carburetor supplies; spark plugs for internal combustion engines; ignition devices for internal combustion engines; ignition magnetos; ignition magnetos for engines; transmission shafts (other than those of terrestrial vehicles); aircraft engines; ball-bearing bushes; greasing bushes (machine parts); piston bushes; engine connecting rods; ball-bearings, roller bearings, struffing boxes (machine sections); lubricating boxes (machines); machine or motor control cables; control chains other than for terrestrial vehicles; drive chains other than for terrestrial vehicles; motor control devices; pneumatic controls for motors; fuel converters for internal combustion engines; torque converters other than for terrestrial vehicles; belts for motors; motor cylinder heads; motor cylinders; motor starters; thermal exchangers (machine parts); exchange pipes for motors; fuel economizers for motors; ejectors; clutches other than for terrestrial vehicles; gears other than for terrestrial vehicles; blowers for gas compression and intake; electric generators; lubricating pumps; grease nipples (machine parts); emergency electric generator sets; hydraulic controls for machines and motors; hydraulic motors; hydraulic turbines; seals (motor parts); universal joint seals; anti-pollution devices for motors; injectors for motors; motor pistons; motor speed regulators; driving machinery other than for terrestrial vehicles; bearings (parts of machines or motors); bearing seats (machines); bearings for transmission shafts; pumps (parts of machines or motors); centrifugal pumps; pressure relief devices (machine parts); presssure regulators (machine parts); pressure valves (machine parts); propulsion mechanisms for non-terrestrial vehicles; cooling radiators for engines; jet engines other than for terrestrial vehicles; regulators (machine parts); springs (machine parts); valves (machine parts or motor parts; machine gears; roller bearings; piston rings; blowing machines; valves (machines part); stators; superheaters; boosters; thermal exchangers (machine parts); transmission mechanisms for non-terrestrial vehicles; turbines other than for terrestrial vehicles; turbo-compressors; motor fans; gearboxes other than for terrestrial vehicles. Computer programs recorded on all media; software and firmware on all media; computer and data processing and word processing software; definition of tables and graphic representations. Vehicles; locomotion vehicles by land, by air, water and rail; air transporters; airborne vehicles; hovercraft; aeronautical apparatus, machines and devices; aircraft; aerostatic balloons; aerostats; amphibious aircraft; aircraft; dirigibles; engine covers for vehicles; seatbelts for vehicle seats; brake linings for vehicles; safety harnesses for vehicle seats; propeller engines; hydraulic circuits for vehicles; seaplanes, hovercraft, jet engines for terrestrial vehicles; vehicle fuel tank plugs, vehicle brake pads, vehicle seats, ejection seats (for aircraft). Printing products; printed forms, newspapers, catalogues, magazines, periodicals, photographs, training and instruction equipment (except for apparatus); technical documentation relative to aircraft engines. Construction and repair; construction and repair of aircraft engines; vehicle servicing and repair; aircraft engine servicing and repair; aircraft servicing and repair; information in terms of construction; information concerning the construction of aircraft engines; supervision (direction) of construction works; supervision (direction) of aircraft engine construction works; information about repairs, information about aircraft engine repairs; aeronautical construction; plant construction. Practical and theoretical instruction; practical and theoretical instruction relative to aircraft engines; practical training (demonstration) and theoretical training; practical training (demonstration) and theoretical training relative to aircraft engines; publication of books, magazines, technical documentation relative to aircraft engines. Scientific and industrial research; scientific and industrial research relative to aircraft engines; work by engineers, appraisal (engineering work); study of projects relative to aircraft engines; professional consultation and establishing of drawings without any relationship to business dealings; professional consultation and production of drawings relative to aircraft engines; design and production of tooling; design and production of aircraft engines; testing of materials; laboratories; computer engineering services; computer engineering services relative to aircraft engines; programming for computers and production of computer programs relative to aircraft engines; rental of access time to database server center, legal service industrial drafting.
01 - Chemical and biological materials for industrial, scientific and agricultural use
03 - Cosmetics and toiletries; cleaning, bleaching, polishing and abrasive preparations
05 - Pharmaceutical, veterinary and sanitary products
06 - Common metals and ores; objects made of metal
07 - Machines and machine tools
10 - Medical apparatus and instruments
11 - Environmental control apparatus
16 - Paper, cardboard and goods made from these materials
17 - Rubber and plastic; packing and insulating materials
18 - Leather and imitations of leather
19 - Non-metallic building materials
20 - Furniture and decorative products
21 - HouseHold or kitchen utensils, containers and materials; glassware; porcelain; earthenware
Goods & Services
(1) Boîtes, emballages, conteneurs, récipients, boîtages, valises, malles, caisses et caissons, ces articles étant métalliques ou en matière synthétique armée, nommément conteneurs garnis d'éléments de calage pour des objets précieux et techniques; pièces en matière synthétique moulée, extrudée, ou formée, nommément, caisses et conteneurs réalisés à partir de matières plastiques diverses, telles que polyester renforcé de fibres de verre, polyethylène ou polyuréthane, et selon des techniques différentes telles que injection, moulage sous pression, thermoformage, rotomoulage; matelas d'amortissement et de calage en matière synthétique expansée.
