EP4168243A1 - Stiffened part formed from a thermoset composite material with a boxed structure and manufacturing method - Google Patents

Stiffened part formed from a thermoset composite material with a boxed structure and manufacturing method

Info

Publication number
EP4168243A1
EP4168243A1 EP21758400.2A EP21758400A EP4168243A1 EP 4168243 A1 EP4168243 A1 EP 4168243A1 EP 21758400 A EP21758400 A EP 21758400A EP 4168243 A1 EP4168243 A1 EP 4168243A1
Authority
EP
European Patent Office
Prior art keywords
bodies
mandrel
stiffened
composite material
juxtaposed
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
EP21758400.2A
Other languages
German (de)
French (fr)
Inventor
Frederick Cavaliere
Remi CROSSONNEAU
Francisque BICEP
Joseph THAY-NAM
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
ArianeGroup SAS
Original Assignee
ArianeGroup SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by ArianeGroup SAS filed Critical ArianeGroup SAS
Publication of EP4168243A1 publication Critical patent/EP4168243A1/en
Pending legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
    • B29C70/32—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core on a rotating mould, former or core
    • 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
    • B29C33/44—Moulds or cores; Details thereof or accessories therefor with means for, or specially constructed to facilitate, the removal of articles, e.g. of undercut articles
    • B29C33/48—Moulds or cores; Details 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
    • 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
    • B29C33/44—Moulds or cores; Details thereof or accessories therefor with means for, or specially constructed to facilitate, the removal of articles, e.g. of undercut articles
    • B29C33/48—Moulds or cores; Details 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
    • B29C33/50—Moulds or cores; Details 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 elastic or flexible
    • B29C33/505—Moulds or cores; Details 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 elastic or flexible cores or mandrels, e.g. inflatable
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/02—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising combinations of reinforcements, e.g. non-specified reinforcements, fibrous reinforcing inserts and fillers, e.g. particulate fillers, incorporated in matrix material, forming one or more layers and with or without non-reinforced or non-filled layers
    • B29C70/026—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising combinations of reinforcements, e.g. non-specified reinforcements, fibrous reinforcing inserts and fillers, e.g. particulate fillers, incorporated in matrix material, forming one or more layers and with or without non-reinforced or non-filled layers and with one or more layers of pure plastics material, e.g. foam layers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/68—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, e.g. foam blocks
    • B29C70/681—Component parts, details or accessories; Auxiliary operations
    • B29C70/682—Preformed parts characterised by their structure, e.g. 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
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/68—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, e.g. foam blocks
    • B29C70/685—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, e.g. foam blocks by laminating inserts between two plastic films or plates
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/68—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, e.g. foam blocks
    • B29C70/70—Completely encapsulating inserts
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/68—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, e.g. foam blocks
    • B29C70/74—Moulding material on a relatively small portion of the preformed part, e.g. outsert moulding
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/68—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, e.g. foam blocks
    • B29C70/74—Moulding material on a relatively small portion of the preformed part, e.g. outsert moulding
    • B29C70/76—Moulding on edges or extremities of the preformed part
    • B29C70/763—Moulding on edges or extremities of the preformed part the edges being disposed in a substantial flat plane
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/68—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, e.g. foam blocks
    • B29C70/86—Incorporated in coherent impregnated reinforcing layers, e.g. by winding
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
    • B29D24/00—Producing articles with hollow walls
    • B29D24/002—Producing articles with hollow walls formed with structures, e.g. cores placed between two plates or sheets, e.g. partially filled
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
    • B29D24/00—Producing articles with hollow walls
    • B29D24/002—Producing articles with hollow walls formed with structures, e.g. cores placed between two plates or sheets, e.g. partially filled
    • B29D24/005—Producing articles with hollow walls formed with structures, e.g. cores placed between two plates or sheets, e.g. partially filled the structure having joined ribs, e.g. honeycomb
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
    • B29D99/00—Subject matter not provided for in other groups of this subclass
    • B29D99/001—Producing wall or panel-like structures, e.g. for hulls, fuselages, or buildings
    • B29D99/0014—Producing wall or panel-like structures, e.g. for hulls, fuselages, or buildings provided with ridges or ribs, e.g. joined ribs
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q1/00—Details of, or arrangements associated with, antennas
    • H01Q1/27—Adaptation for use in or on movable bodies
    • H01Q1/28—Adaptation for use in or on aircraft, missiles, satellites, or balloons
    • H01Q1/288—Satellite antennas
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q15/00—Devices for reflection, refraction, diffraction or polarisation of waves radiated from an antenna, e.g. quasi-optical devices
    • H01Q15/14—Reflecting surfaces; Equivalent structures
    • H01Q15/141—Apparatus or processes specially adapted for manufacturing reflecting surfaces
    • H01Q15/142—Apparatus or processes specially adapted for manufacturing reflecting surfaces using insulating material for supporting the reflecting surface
    • 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
    • B29C65/5057—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
    • B29C66/05—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
    • B29C66/11—Joint cross-sections comprising a single joint-segment, i.e. one of the parts to be joined comprising a single joint-segment in the joint cross-section
    • B29C66/112—Single lapped joints
    • B29C66/1122—Single lap to lap joints, i.e. overlap joints
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/01—General aspects dealing with the joint area or with the area to be joined
    • B29C66/05—Particular design of joint configurations
    • B29C66/10—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
    • B29C66/114—Single butt 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
    • B29C66/11—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
    • B29C66/114—Single butt joints
    • B29C66/1142—Single butt to butt 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
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    • 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
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    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/40—General aspects of joining substantially flat articles, e.g. plates, sheets or web-like materials; Making flat seams in tubular or hollow articles; Joining single elements to substantially flat surfaces
    • B29C66/47—Joining single elements to sheets, plates or other substantially flat surfaces
    • B29C66/474—Joining single elements to sheets, plates or other substantially flat surfaces said single elements being substantially non-flat
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    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
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    • 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
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    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
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    • 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
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    • B29C66/53—Joining single elements to tubular articles, hollow articles or bars
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    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
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    • 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
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    • 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
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
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    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/73—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset
    • B29C66/737—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset characterised by the state of the material of the parts to be joined
    • B29C66/7375—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset characterised by the state of the material of the parts to be joined uncured, partially cured or fully cured
    • B29C66/73751—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset characterised by the state of the material of the parts to be joined uncured, partially cured or fully cured the to-be-joined area of at least one of the parts to be joined being uncured, i.e. non cross-linked, non vulcanized
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/73—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset
    • B29C66/737—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset characterised by the state of the material of the parts to be joined
    • B29C66/7375—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset characterised by the state of the material of the parts to be joined uncured, partially cured or fully cured
    • B29C66/73753—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset characterised by the state of the material of the parts to be joined uncured, partially cured or fully cured the to-be-joined area of at least one of the parts to be joined being partially cured, i.e. partially cross-linked, partially vulcanized
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/73—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset
    • B29C66/737—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset characterised by the state of the material of the parts to be joined
    • B29C66/7375—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset characterised by the state of the material of the parts to be joined uncured, partially cured or fully cured
    • B29C66/73753—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset characterised by the state of the material of the parts to be joined uncured, partially cured or fully cured the to-be-joined area of at least one of the parts to be joined being partially cured, i.e. partially cross-linked, partially vulcanized
    • B29C66/73754—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset characterised by the state of the material of the parts to be joined uncured, partially cured or fully cured the to-be-joined area of at least one of the parts to be joined being partially cured, i.e. partially cross-linked, partially vulcanized the to-be-joined areas of both parts to be joined being partially cured
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/73—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset
    • B29C66/737—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset characterised by the state of the material of the parts to be joined
    • B29C66/7375—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset characterised by the state of the material of the parts to be joined uncured, partially cured or fully cured
    • B29C66/73755—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset characterised by the state of the material of the parts to be joined uncured, partially cured or fully cured the to-be-joined area of at least one of the parts to be joined being fully cured, i.e. fully cross-linked, fully vulcanized
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/73—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset
    • B29C66/737—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset characterised by the state of the material of the parts to be joined
    • B29C66/7375—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset characterised by the state of the material of the parts to be joined uncured, partially cured or fully cured
    • B29C66/73755—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset characterised by the state of the material of the parts to be joined uncured, partially cured or fully cured the to-be-joined area of at least one of the parts to be joined being fully cured, i.e. fully cross-linked, fully vulcanized
    • B29C66/73756—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset characterised by the state of the material of the parts to be joined uncured, partially cured or fully cured the to-be-joined area of at least one of the parts to be joined being fully cured, i.e. fully cross-linked, fully vulcanized the to-be-joined areas of both parts to be joined being fully cured
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/73—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset
    • B29C66/739—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset characterised by the material of the parts to be joined being a thermoplastic or a thermoset
    • B29C66/7394—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset characterised by the material of the parts to be joined being a thermoplastic or a thermoset characterised by the material of at least one of the parts being a thermoset
    • B29C66/73941—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset characterised by the material of the parts to be joined being a thermoplastic or a thermoset characterised by the material of at least one of the parts being a thermoset characterised by the materials of both parts being thermosets
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/40—Shaping or impregnating by compression not applied
    • B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
    • B29C70/46—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs
    • B29C70/48—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM], e.g. by vacuum
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
    • B29K2101/00—Use of unspecified macromolecular compounds as moulding material
    • B29K2101/10—Thermosetting resins
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
    • B29K2105/00—Condition, form or state of moulded material or of the material to be shaped
    • B29K2105/06—Condition, form or state of moulded material or of the material to be shaped containing reinforcements, fillers or inserts
    • B29K2105/08—Condition, form or state of moulded material or of the material to be shaped containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns
    • B29K2105/0809—Fabrics
    • 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
    • B29L2031/34—Electrical apparatus, e.g. sparking plugs or parts thereof
    • B29L2031/3456—Antennas, e.g. radomes

Definitions

  • the invention relates to a stiffened part, in which the stiffening mode is integrated on at least one of the faces of the part made of thermosetting composite material.
  • the invention can find application for the stiffening of all parts made of thermosetting composite material which must have great dimensional stability under mechanical or thermal stresses and/or great rigidity.
  • the invention thus applies to all technical fields which require stiffened parts of complex shapes; it can for example be structural parts in the space field (for example, satellite antenna reflector, satellite platform structure, distributor ("dispenser" in English, structure which serves as a support for several satellites at the same time and ejection of these satellites once in orbit according to a predefined order), composite interstage structures, composite tanks, etc.) or aeronautical (for example, fuselage panels, wing panels, undercarriage doors landing, access hatches, etc.) and can be applied to the fields of road, air, rail and maritime transport.
  • space field for example, satellite antenna reflector, satellite platform structure, distributor ("dispenser" in English, structure which serves as a support for several satellites at the same time and ejection of these satellites once in orbit according to a predefined order
  • composite interstage structures composite interstage structures
  • satellite antenna reflectors comprise a composite material shell which is assembled, after polymerization, to a rigid rear structure.
  • the shell has a complex double curvature shape; the rear structure, for its part, is made up of an assembly of tubes, sleeves (allowing a junction between the tubes) and fitting type connecting means (allowing a junction between the rear structure and the satellite).
  • connection means of the angle type made of composite material having an L shape The rear structure has a different shape from the shell and is therefore not directly in contact with the hull during the assembly operation.
  • One end of the angles is glued to the rear structure and the other end is glued to the shell.
  • the angle and width of the angles must be chosen so as to allow good contact with the rear face of the hull (double curvature).
  • Each angle type connecting piece must therefore be adapted, in particular to the curvature at the interface with the shell, which implies having a large number of different connecting pieces available and a lot of time for the choice of the piece. adequate connection.
  • this mode of stiffening and assembly is particularly complex and time-consuming, since it requires the manufacture of many elements (tubes, sleeves, very many types of angles) and requires many and meticulous assembly operations by manual gluing. at ambient temperature (assembly of the tubes/sleeves for the production of the rear structure, and assembly of the shell/structure using the angles), which has an impact on the cost of the stiffened structural parts thus obtained.
  • the object of the invention is to propose a mode of stiffening which makes it possible to easily adapt to complex specific shapes of structural parts to be stiffened, while reducing manufacturing costs by drastically reducing the number of elements necessary for stiffening. of a structural part and by reducing the various bonding operations of these elements on the part.
  • the invention proposes a stiffened part comprising at least a first structure made of thermoset composite material, which first structure comprises at least one hollow longitudinal body having at least one open end.
  • the first structure is a box-section structure formed from one or more hollow bodies.
  • Each hollow body can be a tubular component with a circular, rectangular, triangular section, or any other shape whatsoever.
  • stiffened part Some preferred but non-limiting aspects of the stiffened part are:
  • the first structure comprises at least two bodies, said bodies being juxtaposed and/or stacked, the contact between two adjacent bodies taking place via their side wall;
  • the first structure comprises a first row of juxtaposed bodies and a second row of juxtaposed bodies, the first and second rows being stacked with an offset between the bodies of the first row and the bodies of the second row;
  • the stiffened part further comprises a second structure made of thermoset composite material, distinct from the first structure, the first structure being at least partly integrated into the second structure and/or juxtaposed on a surface of the second structure;
  • the second structure can be of the monolithic type (for example a monolithic plate) or of the sandwich type with a cellular core of the type honeycomb or foam with closed or open pores, and two outer skins arranged on either side of the core;
  • the part can be a satellite antenna reflector.
  • the invention also relates to a method of manufacturing a stiffened part as described above, the stiffened part being formed of at least two elements of thermoset composite material including at least one body of the first structure and the optional second structure, the method comprising the following successive steps:
  • thermosetting resin for each body of the first structure, either making a fibrous preform of the body by draping a fabric around a mandrel and impregnating the fibrous preform with a thermosetting resin, or making a preimpregnated fibrous preform by draping a fabric pre-impregnated with a thermosetting resin around a mandrel, whereby a body of unpolymerized thermosetting composite material supported by a mandrel is obtained;
  • thermosetting composite material supported by a mandrel
  • the stiffened part comprises a second structure, provision of the second structure, the second structure being made of unpolymerized, partially polymerized or completely polymerized thermosetting composite material;
  • thermosetting composite material depositing a layer of unpolymerized thermosetting adhesive on a zone of contact of said element with another element of the part;
  • the method further comprises, before the assembly step, depositing an adhesive film between two unpolymerized and/or partially polymerized elements. This keeps these two elements together during assembly; this can also make it possible to improve the mechanical strength of the assembly interface, once the two elements have completely polymerized.
  • the optional step of complete polymerization of at least one body of thermosetting composite material supported by a mandrel is not carried out. Indeed, it is preferable for the body or bodies of the first structure to be completely polymerized during assembly with the second structure, which makes it possible to correctly position the bodies by following the out-of-plane curvatures and the in-plane curvatures at the level assembly interfaces with the second structure.
  • the polymerization of two adjacent elements will be done by co-firing or by co-bonding depending on whether or not one of the two elements is in a completely polymerized state before assembly.
  • thermosetting resin there is also at least one sheet or fabric preimpregnated with thermosetting resin or which is subsequently impregnated with thermosetting resin, this sheet or this fabric being applied, during of the assembly step, on at least one body, preferably on several stacked and/or juxtaposed bodies, and/or on the possible second structure.
  • the mandrel is a grouping of at least two mandrels of smaller sections, either stacked or juxtaposed laterally.
  • each mandrel is made of flexible elastomer.
  • the mandrel can be hollow or solid; preferably, a solid mandrel is chosen.
  • At least one mandrel has a polygonal section, for example of the triangular or parallelepipedal type. Section can be constant or variable
  • the mandrels can have a constant section or a variable section which increases from one end of the mandrel to the other.
  • the invention has many advantages.
  • the body or bodies of the first structure make it possible to produce a boxed assembly which can easily adapt to complex specific shapes in the plane or out of the plane, making it possible to adapt to the surface of a part to be stiffened (the part can for example, have a double curvature surface).
  • the hollow body or bodies forming the first structure are capable of following the in-plane and out-of-plane curvatures at the assembly interfaces with the second structure.
  • the hollow body(s) can be straight or else take any necessary curvature in the plane of assembly with the second structure.
  • the invention makes it possible to ensure good mechanical strength and high reliability of the bonded connections.
  • FIG. 1 shows an example according to the invention of a body obtained by draping a sheet or a preimpregnated fabric around a mandrel of rectangular section, the body having two open ends;
  • FIG. 2 shows another example according to the invention of a body obtained by draping a sheet or a preimpregnated fabric around a mandrel of triangular section, the body having two open ends;
  • FIG. 3 shows another example according to the invention of a body obtained by draping a sheet or a preimpregnated fabric around a mandrel of rectangular section, the body having only one open end;
  • FIG. 4 shows another example according to the invention of a body obtained by draping a sheet or a preimpregnated fabric around a mandrel of variable section, the body having two open ends;
  • FIG. 5a shows, in a cross-sectional view, an example of draping a fabric or a sheet around a mandrel of rectangular section;
  • FIG. 5b shows, in a cross-sectional view, another example of draping a fabric or a sheet around a mandrel of rectangular section
  • - Figure 5c shows, in a cross-sectional view, another example of draping a fabric or a sheet around a mandrel of rectangular section
  • FIG. 5d shows, in a cross-sectional view, an example of draping several fabrics or layers around a mandrel of rectangular section;
  • FIG. 5e shows, in a cross-sectional view, another example of draping several fabrics or layers around a mandrel of rectangular section;
  • FIG. 5f shows, in a cross-sectional view, another example of draping a fabric or a sheet around a mandrel of rectangular section;
  • FIG. 6 shows, in a perspective view, a body formed by draping a fabric around a mandrel formed of a plurality of mandrels of smaller sections which are stacked and / or juxtaposed longitudinally;
  • FIG. 8 shows, in a cross-sectional view, an embodiment of a stiffened part according to the invention
  • FIG. 9 shows, in a cross-sectional view, another embodiment of a stiffened part according to the invention.
  • FIG. 10 shows, in a cross-sectional view, another embodiment of a stiffened part according to the invention.
  • FIG. 11 shows, in a cross-sectional view, another embodiment of a stiffened part according to the invention.
  • FIG. 12 shows, in a cross-sectional view, another embodiment of a stiffened part according to the invention.
  • FIG. 13 shows, in a perspective view, an example of placement of a body (supported by a mandrel) on a surface of a second structure (for example a part to be stiffened), the body being placed in a direction radial of the second structure;
  • FIG. 14 shows, in a perspective view, an example of placement of a body (supported by several mandrels) on a surface of a second structure (for example a part to be stiffened), the body being placed in a direction radial of the second structure and protruding from the second structure, the contact surface between the first structure and the second structure not being over the entire length of the body;
  • - Figure 15 shows, in a perspective view, another example of placement of a body (supported by several mandrels) on a surface of a second structure (for example a part to be stiffened), the body being placed according to a radial direction of the second structure and protruding from the second structure, the contact surface between the first structure and the second structure not being over the entire length of the body and a gap being left between the body and the second structure;
  • - Figure 16 shows, in a perspective view, an example of placement of a body (supported by a mandrel) on a surface of a second structure (for example a part to be stiffened), the body being placed in a direction circumferential of the second structure;
  • - Figure 17 shows, in a perspective view, an example of a stiffened part obtained by placing, on a surface of a second structure (here the part to be stiffened), a first structure formed of a first body arranged in a first radial direction of the second structure, and a second and a third body arranged on either side of the first body in a second radial direction of the second structure, which may be perpendicular to the first direction ;
  • - Figure 18 shows, in a perspective view, another example of a stiffened part obtained by placing, on a surface of a second structure (here the part to be stiffened), a first structure formed of a row of bodies juxtaposed and arranged in radial directions of the second structure;
  • - Figure 19 shows, in a perspective view, another example of a stiffened part obtained by placing a first structure formed of several bodies on a surface of a second structure (here the part to be stiffened), some bodies being positioned in radial directions of the second structure and others in circumferential directions of the second structure, the bodies being joined to each other in contact zones;
  • - Figure 20 shows, in a perspective view, another example of a stiffened part, comprising a first structure formed of a first body arranged in a radial direction of a second structure (here the part to be stiffened) and a second body disposed astride the first body and the second structure, in a circumferential direction of the second structure;
  • FIG. 21 shows, in a perspective view, another example of a stiffened part, made only from bodies assembled to each other and forming the first structure
  • FIG. 22 shows, in a top view, an example of six bodies arranged radially and at equal distances from each other on the surface of a second structure (part to be stiffened);
  • FIG. 23 shows, in a top view, an example of three bodies arranged on the surface of a second structure (part to be stiffened), each body having one end which protrudes from the second structure and the other end joining a side wall of one of the other bodies, the junction of the three bodies forming a triangle at the center of the second structure;
  • FIG. 24 shows, in a top view, another example of four bodies arranged on the surface of a second structure (part to be stiffened), each body having one end which protrudes from the second structure and the other end joining a side wall of one of the other bodies, the junction of the four bodies forming a square in the center of the second structure;
  • FIG. 25 shows, in a top view, another example of four bodies arranged on the surface of a second structure (part to be stiffened), each body having an end which comes to a place at the periphery of the second structure and the other end which comes to another place, diametrically opposite, at the periphery of the second structure, each body overlapping one of the three other bodies and being overlapped by another of the three other bodies;
  • FIG. 26 shows, in a top view, another example of four bodies arranged on the surface of a second structure (part to be stiffened), one end of each body running along the periphery of the second structure and the other end joining a side wall of one of the other bodies near the center of the second structure, the junction of the four bodies forming a circle in the center of the second structure.
  • the stiffened part according to the invention comprises a first structure 6 and a possible second structure 7, the first and second structures being made of thermoset composite material, and the first structure comprising at least one hollow longitudinal body 2 having at least one open end 3.
  • thermoset composite material is a composite material of the fibrous reinforcement type impregnated with a thermosetting matrix which is thermoset by heat treatment. This is what will make it possible to assemble the different elements forming the piece by co-curing (or “co-curing” in English) or by co-gluing (or “co-bonding” in English), as we see further.
  • the fibrous reinforcement can be made of carbon fibers and/or glass and/or KevlarTM fibers; it can also be a combination of several types of fibers, for example a mixture of glass/carbon fibers, or carbon/KevIarTM fibers
  • the matrix is a resin binder that permeates the reinforcement and solidifies when cured.
  • the matrix is a thermosetting resin.
  • the base monomer of the epoxy resin can for example be of the DGEBA (DiGlycidyl Ether of Bisphenol A), TGPAP (TriGlycidyl ParaAminoPhenol) or TGMDA (TetraGlycidyl Methylene DiAniline) type.
  • the hardener can be of the amine type, for example DDS (DiaminoDiphenyl Sulfone).
  • thermosetting resins used and described in this document polymerize completely at a temperature generally between 120° C. and 220° C. for a period of two hours at the polymerization temperature. More specifically, the resins most used in space and aeronautics are so-called 180°C class resins, for which complete polymerization is achieved after 2 hours at 180°C.
  • fabrics or webs can be used and stacked to form strata.
  • the fibrous reinforcement impregnated with resin can optionally be compacted before undergoing polymerization.
  • the assembly of two elements corresponds either to bonding by "co-curing", when the two elements to be assembled are unpolymerized or partially polymerized and are brought to a state of complete polymerization during the same heating cycle, or to bonding by "co-bonding", when one of the two elements is already completely polymerized, with the need to prepare the surface of the polymerized element and to place a layer of resin adhesive at the interface of the two elements thermosetting, adhesive preferably in the form of a film.
  • a layer of adhesive be deposited at the bonding interface of the two elements.
  • the bonding interface will generally be prepared, for example by sanding and cleaning with a solvent, then depositing a film of adhesive.
  • co-bonding there are two heating cycles, a first cycle during which one of the two elements is completely polymerized and a second cycle during which the second element, as well as adhesive, are fully cured. In the end, whether by bonding by "co-curing" or by "co-bonding", a bond is obtained between the two elements by hot bonding which has great reliability and very good mechanical strength.
  • draping is carried out by winding a fabric or a sheet 5 around a mandrel 1 in order to form a preform.
  • the fabric or sheet 5 can be preimpregnated with thermosetting resin, or else be dry and the fabric or sheet is impregnated with a thermosetting resin subsequently, for example by injection or infusion of the resin into the dry preform already shaped.
  • the injection/infusion phase occurs when the preform is placed in a closed mould. This phase is followed by polymerization of the injected resin.
  • the mandrel 1 can have a constant section, for example rectangular (Figure 1) or triangular (Figure 2) or a variable section ( Figure 4).
  • section is variable, it must nevertheless allow the extraction of the mandrel from the body once the resin has polymerized. In this case, particular attention will be paid to ensuring that the variation in section or the deformation of the mandrel during extraction allows the moldability (extraction), from the open end 3, of the mandrel placed inside the body.
  • the body 2 must have at least one open end 3 (in Figure 3 the body has a closed end 4); it can have two open ends 3 (FIGS. 1, 2, 4), in order to allow the mandrel to come out.
  • One or more layers of fabric or ply 5 can be wound around the same mandrel 1.
  • the winding of each layer can be done:
  • the part to be stiffened comprises a first structure 6, composed of one or more bodies 2, and of a possible second structure 7.
  • the stiffened part may only comprise a first structure 6, as illustrated in figure 21, but it generally comprises a second structure 7, which is generally the part to be stiffened.
  • This structure 7 can be a sandwich structure consisting of 2 skins and a core material of the honeycomb type; usually this will be a honeycomb cell core, but it can also be a closed or open pore foam core.
  • the second structure 7 is the sandwich shell of the reflector which it is desired to stiffen.
  • the mandrel is made of flexible elastomer so as to:
  • the second structure 7 can be of the monolithic type or of the sandwich type.
  • the second structure is of the sandwich type.
  • the unpolymerized or partially polymerized body or bodies are placed on the second unpolymerized or partially polymerized structure 7 polymerized taking care to follow the shape of the surface of the second structure and the defined location.
  • the second structure 7 can be completely polymerized. In this case, it will be necessary, before placing the body or bodies 2 on the second structure 7, to prepare the surface of the second structure in the assembly zone (for example, degreasing, sanding, cleaning), then depositing a layer of thermosetting adhesive before draping the bodies 2. After polymerization of the assembly, an assembly by co-bonding is thus obtained.
  • the bodies can be assembled directly on the draping mold of the second structure.
  • the bodies are then partially polymerized (half-cured), they are separated from the mold and the assembly produced is stored without removing the mandrels from the mould.
  • the degree of polymerization measured by differential scanning calorimetry (DSC) according to standard ISO 11357-1:2016, is between 10% and 75%, and preferably between 15% and 40 %.
  • DSC differential scanning calorimetry
  • this assembly can be placed on the surface of the second structure to be stiffened, and complete polymerization can be carried out. Assembly will be by co-firing if the second structure is uncured or partially cured, or by co-bonding, if the second structure is cured (in this case, it will first be necessary to deposit a layer of adhesive, as described previously).
  • the second structure 7 can be produced by draping the second structure on a draping mold with pre-impregnated fabrics or sheets, then assembling the first structure, already constituted, forming a boxed assembly, on the second unpolymerized structure. If the first structure is partially polymerized, there is no need to perform surface preparation at the bonding interface, nor need for an adhesive film at the interface (the assembly being similar to co -cooking). On the contrary, if the first structure is completely polymerized, it is necessary to carry out a preliminary surface treatment of the surface at the location of the bonding (degreasing, sanding, cleaning), then adding an adhesive film (in order to to obtain an assembly by co-bonding).
  • partial polymerization of the first structure is preferred; thus, during the final polymerization, the viscosity of the partially polymerized resin of the first structure will decrease (softening of the resin) and allow, on the one hand, a good conformation of the first structure on the surface of the second structure, and, on the other hand, the creation of bonds between the polymer chains of the two resins (first and second structures).
  • the behavior of the resins of each structure will be similar during the final polymerization.
  • the viscosity of each resin will decrease, allowing a good conformation of the structures at the location of the assembly interfaces, accompanied by the creation of bonds between the polymer chains of the two resins.
  • the assembly configurations of the body or bodies are multiple.
  • the bodies 2 forming the first structure 6 can be assembled on the second structure (FIG. 8), both on and in the second structure (FIG. 12) or even in the second structure (FIGS. 9, 10, 11). It is also possible that there is no second structure 7 and that the first structure 6 alone forms the stiffened part (FIG. 21).
  • the first structure 6 comprises a first row of juxtaposed bodies and a second row of juxtaposed bodies, the first and second rows being stacked and the bodies of the first row being offset with respect to the bodies of the second row.
  • the first and second rows can be offset by a half-width offset of a body.
  • This figure 21 illustrates one of the many possible examples of a stiffened part. By changing the number of rows, shapes of the bodies, as well as the position of the bodies between them, it is possible to obtain multiple configurations, not detailed in this description.
  • the stiffened part comprises a first structure 6 and a second structure 7.
  • the first structure 6 is a stack of four bodies 2; the first structure is assembled on the surface of the second structure 7 with a fold 9.
  • the first structure 6 is a grouping of four bodies 2, while in Figure 10, the first structure 6 comprises a single body 2.
  • the first structure 6 is partly incorporated into the second structure 7.
  • the contact may be a partial contact.
  • the body or bodies 2 can go beyond the surface of the second structure 7 (as illustrated, for example, in FIG. 14) or else locally present a gap between the two surfaces so that they no longer assembled (as shown, for example, in Figure 15).
  • the first structure 6 comprises two juxtaposed bodies 2 and is completely incorporated into the second structure 7.
  • the contact between the adjacent bodies is made by their side wall.
  • the first structure 6 comprises seven stacked and juxtaposed bodies 2 and is partly incorporated into the second structure 7; here, one of the seven bodies is completely integrated into the second structure 7, and the other six bodies are located above the surface of the second structure 7.
  • two or more adjacent bodies may not be in contact with each other, since a ply 9 may be placed between two adjacent bodies.
  • the stiffened part comprises a first and a second structure
  • different assembly configurations are possible.
  • the body or bodies 2 of the first structure 6 can be arranged in any direction on the surface of the structure 7.
  • the positioning of the body or bodies 2 on the surface of the structure 7 can be rectilinear (for example, the figures 22, 23, 24) or curved (for example, figures 25 and 26).
  • the body or bodies 2 of the first structure 6 can be arranged on the surface of the second structure 7 in a radial direction of the second structure (FIG. 13), in a circumferential direction of the second structure (FIG. 16) or well again according to a configuration combining radial and circumferential directions (FIG. 19).
  • the body or bodies 2 may protrude from the second structure 7, as illustrated for example in figure 14, where it can be seen that the contact surface between the body 2 of the first structure and the second structure is not on the entire length of the body. There may also be a gap between the body or bodies 2 and the surface of the second structure 7, as illustrated for example in figure 15.
  • FIGS. 22 to 26 Other configurations are illustrated in FIGS. 22 to 26, where the part to be stiffened (the second structure 7) is a circular peripheral plate.
  • FIG. 17 there is a configuration where the first structure 6 has the shape of a cross, with a first long body 2 positioned in a first radial direction of the second structure 7 and two shorter bodies, which are positioned on either side. other of the first body, in a radial direction of the second structure, perpendicular to the first direction.
  • the two shorter bodies preferably have one end open (for exit from the chuck) and a closed end, the side wall of the closed end allowing assembly with the side wall of the first body.
  • the stiffened part is represented after the extraction of the mandrels 1.
  • the first structure 6 comprises a row of seven juxtaposed bodies 2 of different lengths; contact between adjacent bodies is through their side wall.
  • a few folds 9 can cover the body or bodies 2 of the first structure 6 and/or of the second structure 7.
  • a few folds 9 come to cover the first structure, with a return on the surface of the second framework; an omega-shaped draping (W) is obtained.
  • a first draping covers the four bodies of the first structure, and a second and third draping respectively covers the upper surface and the lower surface of the second structure, as well as the first structure 6.
  • a first and a second layup respectively cover the upper surface and the lower surface of the second structure.
  • a first and second ply 9 respectively covers the lower and upper surface of the second structure 7, as well as the body integrated into the second structure 7.
  • a third ply 9 covers the surface of the structure 6 and part of the upper surface of the structure 7.
  • a few folds 9 can be draped over the front and rear faces of the first structure 6, or between the rows of bodies 2, to finalize the draping.

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Abstract

The invention relates to a stiffened part formed from at least two members of thermoset composite material including at least one body of a first structure and optionally a second structure, and the manufacturing method thereof, which comprises: for each body of the first structure, forming a fibre preform of the body and impregnating said body with a thermosetting resin or forming a pre-impregnated fibre preform, whereby a body formed from an uncured thermosetting composite material supported by a mandrel is obtained; optionally partially or fully polymerising at least one body supported by a mandrel; if the stiffened part comprises a second structure, providing the second structure formed from an uncured, partially uncured or fully uncured thermosetting composite material; if there is at least one member formed from a fully cured thermosetting composite material, depositing a layer of uncured thermosetting adhesive on an area where ​​the member makes contact with another member of the part; joining the members forming the part, each member being juxtaposed with, or stacked upon, at least one other member; fully curing the assembly by heat treatment; removing the mandrel from each fully cured body.

Description

Description Description
PIECE RAIDIE EN MATERIAU COMPOSITE THERMODURCI A STRUCTURE CAISSONNEE ETSTIFFERED PART IN THERMODURED COMPOSITE MATERIAL WITH BOXED STRUCTURE AND
PROCEDE DE FABRICATION MANUFACTURING PROCESS
DOMAINE TECHNIQUE L'invention se rapporte à une pièce raidie, dans laquelle le mode de raidissage est intégré sur au moins l'une des faces de la pièce en matériau composite thermodurcissable. TECHNICAL FIELD The invention relates to a stiffened part, in which the stiffening mode is integrated on at least one of the faces of the part made of thermosetting composite material.
L'invention peut trouver application pour le raidissage de toutes pièces en matériau composite thermodurcissable devant présenter une grande stabilité dimensionnelle sous sollicitations mécaniques ou thermiques et/ou une grande rigidité. L'invention s'applique ainsi à tous les domaines techniques qui requièrent des pièces raidies de formes complexes ; il peut par exemple s'agir de pièces structurales dans le domaine spatial (par exemple, réflecteur d'antenne de satellite, structure plateforme satellite, distributeur (« dispenser » en anglais, structure qui sert de support de plusieurs satellites en même temps et d'éjection de ces satellites une fois en orbite selon un ordre défini à l'avance), structures inter-étages composites, réservoirs composites, etc.) ou aéronautique (par exemple, panneaux de fuselage, panneaux de voilure, trappes de train d'atterrissage, trappes d'accès, etc.) et peut s'appliquer aux domaines des transports routier, aérien, ferroviaire et maritime. ÉTAT DE LA TECHNIQUE ANTÉRIEURE The invention can find application for the stiffening of all parts made of thermosetting composite material which must have great dimensional stability under mechanical or thermal stresses and/or great rigidity. The invention thus applies to all technical fields which require stiffened parts of complex shapes; it can for example be structural parts in the space field (for example, satellite antenna reflector, satellite platform structure, distributor ("dispenser" in English, structure which serves as a support for several satellites at the same time and ejection of these satellites once in orbit according to a predefined order), composite interstage structures, composite tanks, etc.) or aeronautical (for example, fuselage panels, wing panels, undercarriage doors landing, access hatches, etc.) and can be applied to the fields of road, air, rail and maritime transport. PRIOR ART
Certaines pièces nécessitent d'être raidies. Pour illustrer la problématique qui se pose au cours de la réalisation de telles pièces, nous allons décrire le cas particulier de la réalisation d'une pièce de type réflecteur d'antenne de satellite. Some parts need to be stiffened. To illustrate the problem that arises during the production of such parts, we will describe the particular case of the production of a part of the satellite antenna reflector type.
Actuellement, les réflecteurs d'antenne de satellite comportent une coque en matériau composite qui est assemblée, après polymérisation, à une structure arrière rigide. La coque présente une forme complexe en double courbure ; la structure arrière, quant à elle, est composée d'un assemblage de tubes, de manchons (permettant une jonction entre les tubes) et de moyens de liaison de type ferrure (permettant une jonction entre la structure arrière et le satellite). Currently, satellite antenna reflectors comprise a composite material shell which is assembled, after polymerization, to a rigid rear structure. The shell has a complex double curvature shape; the rear structure, for its part, is made up of an assembly of tubes, sleeves (allowing a junction between the tubes) and fitting type connecting means (allowing a junction between the rear structure and the satellite).
L'assemblage de la structure arrière rigide avec la coque est réalisé par l'intermédiaire de moyens de liaison de type cornière en matériau composite ayant une forme en L. La structure arrière présente une forme différente de la coque et n'est donc pas directement en contact avec la coque lors de l'opération d'assemblage. Une extrémité des cornières est collée à la structure arrière et l'autre extrémité est collée à la coque. L'angle et la largeur des cornières doivent être choisis de manière à permettre un bon contact avec la face arrière de la coque (double courbure). Chaque pièce de liaison de type cornière doit donc être adaptée, notamment à la courbure à l'interface avec la coque, ce qui implique d'avoir à disposition un grand nombre de pièces de liaison différentes et beaucoup de temps pour le choix de la pièce de liaison adéquate. The assembly of the rigid rear structure with the shell is carried out by means of connection means of the angle type made of composite material having an L shape. The rear structure has a different shape from the shell and is therefore not directly in contact with the hull during the assembly operation. One end of the angles is glued to the rear structure and the other end is glued to the shell. The angle and width of the angles must be chosen so as to allow good contact with the rear face of the hull (double curvature). Each angle type connecting piece must therefore be adapted, in particular to the curvature at the interface with the shell, which implies having a large number of different connecting pieces available and a lot of time for the choice of the piece. adequate connection.
En outre, tous les collages sont réalisés manuellement, en utilisant un adhésif en pâte, à température ambiante (on effectue ce que l'on appelle communément un collage à froid). In addition, all the bondings are done manually, using a paste adhesive, at room temperature (what is commonly called cold bonding is performed).
Au final, ce mode de raidissage et d'assemblage est particulièrement complexe et chronophage, puisqu'il nécessite la fabrication de nombreux éléments (tubes, manchons, très nombreux types de cornières) et nécessite de nombreuses et minutieuses opérations d'assemblage par collage manuel à température ambiante (assemblage des tubes/manchons pour la réalisation de la structure arrière, et assemblage de la coque/structure à l'aide des cornières), ce qui a un impact sur le coût des pièces structurales raidies ainsi obtenues. In the end, this mode of stiffening and assembly is particularly complex and time-consuming, since it requires the manufacture of many elements (tubes, sleeves, very many types of angles) and requires many and meticulous assembly operations by manual gluing. at ambient temperature (assembly of the tubes/sleeves for the production of the rear structure, and assembly of the shell/structure using the angles), which has an impact on the cost of the stiffened structural parts thus obtained.
Il y a donc un besoin de simplification des opérations de raidissage de la coque et d'assemblage des différents éléments, tout en conservant une grande fiabilité des liaisons collées. There is therefore a need to simplify the operations of stiffening the hull and of assembling the various elements, while maintaining high reliability of the bonded connections.
On rappelle que cette problématique a été décrite dans le cas particulier des réflecteurs d'antenne de satellites, mais se pose de manière générale à toute pièce structurale devant être raidie en étant assemblée avec un ensemble de raidisseurs et présentant une interface de collage variable (du fait d'une interface de collage à courbure variable, le plus souvent à double courbure, et qui peut être différente selon les positions d'assemblage). It is recalled that this problem has been described in the particular case of satellite antenna reflectors, but generally arises for any structural part that must be stiffened by being assembled with a set of stiffeners and having a variable bonding interface (from made of curvature bonding interface variable, most often with double curvature, and which can be different according to the assembly positions).
L'invention a pour objectif de proposer un mode de raidissage qui permette de s'adapter facilement à des formes spécifiques complexes de pièces structurales à raidir, tout en diminuant les coûts de fabrication en diminuant de manière drastique le nombre d'éléments nécessaires au raidissage d'une pièce structurale et en diminuant les différentes opérations de collage de ces éléments sur la pièce. The object of the invention is to propose a mode of stiffening which makes it possible to easily adapt to complex specific shapes of structural parts to be stiffened, while reducing manufacturing costs by drastically reducing the number of elements necessary for stiffening. of a structural part and by reducing the various bonding operations of these elements on the part.
EXPOSÉ DE L'INVENTION DISCLOSURE OF THE INVENTION
À cet effet, l'invention propose une pièce raidie comprenant au moins une première structure en matériau composite thermodurci, laquelle première structure comporte au moins un corps longitudinal creux ayant au moins une extrémité ouverte. To this end, the invention proposes a stiffened part comprising at least a first structure made of thermoset composite material, which first structure comprises at least one hollow longitudinal body having at least one open end.
La première structure est une structure caissonnée formée d'un ou plusieurs corps creux. Chaque corps creux peut être un composant tubulaire à section circulaire, rectangulaire, triangulaire, ou toute autre forme quelconque. The first structure is a box-section structure formed from one or more hollow bodies. Each hollow body can be a tubular component with a circular, rectangular, triangular section, or any other shape whatsoever.
Certains aspects préférés mais non limitatifs de la pièce raidie sont les suivants :Some preferred but non-limiting aspects of the stiffened part are:
- la première structure comprend au moins deux corps, lesdits corps étant juxtaposés et/ou empilés, le contact entre deux corps adjacents se faisant par leur paroi latérale ; - the first structure comprises at least two bodies, said bodies being juxtaposed and/or stacked, the contact between two adjacent bodies taking place via their side wall;
- la première structure comporte une première rangée de corps juxtaposés et une deuxième rangée de corps juxtaposés, les première et deuxième rangées étant empilées avec un décalage entre les corps de la première rangée et les corps de la deuxième rangée ; - The first structure comprises a first row of juxtaposed bodies and a second row of juxtaposed bodies, the first and second rows being stacked with an offset between the bodies of the first row and the bodies of the second row;
- la première structure forme à elle seule la pièce raidie ; - The first structure alone forms the stiffened part;
- la pièce raidie comprend en outre une deuxième structure en matériau composite thermodurci, distincte de la première structure, la première structure étant au moins en partie intégrée dans la deuxième structure et/ou juxtaposée sur une surface de la deuxième structure ; la deuxième structure peut être de type monolithique (par exemple une plaque monolithique) ou de type sandwich avec une âme alvéolaire de type nid d'abeille ou mousse à pores fermés ou ouverts, et deux peaux extérieures disposées de part et d'autre de l'âme ; - the stiffened part further comprises a second structure made of thermoset composite material, distinct from the first structure, the first structure being at least partly integrated into the second structure and/or juxtaposed on a surface of the second structure; the second structure can be of the monolithic type (for example a monolithic plate) or of the sandwich type with a cellular core of the type honeycomb or foam with closed or open pores, and two outer skins arranged on either side of the core;
- la pièce peut être un réflecteur d'antenne de satellite. - the part can be a satellite antenna reflector.
L'invention concerne également un procédé de fabrication d'une pièce raidie telle que décrite ci-dessus, la pièce raidie étant formée d'au moins deux éléments en matériau composite thermodurci dont au moins un corps de la première structure et l'éventuelle deuxième structure, le procédé comprenant les étapes successives suivantes : The invention also relates to a method of manufacturing a stiffened part as described above, the stiffened part being formed of at least two elements of thermoset composite material including at least one body of the first structure and the optional second structure, the method comprising the following successive steps:
- pour chaque corps de la première structure, soit réalisation d'une préforme fibreuse du corps par drapage d'un tissu autour d'un mandrin et imprégnation de la préforme fibreuse avec une résine thermodurcissable, soit réalisation d'une préforme fibreuse préimprégnée par drapage d'un tissu préimprégné d'une résine thermodurcissable autour d'un mandrin, moyennant quoi on obtient un corps en matériau composite thermodurcissable non polymérisé supporté par un mandrin ; - for each body of the first structure, either making a fibrous preform of the body by draping a fabric around a mandrel and impregnating the fibrous preform with a thermosetting resin, or making a preimpregnated fibrous preform by draping a fabric pre-impregnated with a thermosetting resin around a mandrel, whereby a body of unpolymerized thermosetting composite material supported by a mandrel is obtained;
- éventuelle polymérisation partielle ou complète d'au moins un corps en matériau composite thermodurcissable supporté par un mandrin ; - possible partial or complete polymerization of at least one body of thermosetting composite material supported by a mandrel;
- si la pièce raidie comporte une deuxième structure, fourniture de la deuxième structure, la deuxième structure étant en matériau composite thermodurcissable non polymérisé, partiellement polymérisé ou complètement polymérisé ; - if the stiffened part comprises a second structure, provision of the second structure, the second structure being made of unpolymerized, partially polymerized or completely polymerized thermosetting composite material;
- s'il y a au moins un élément en matériau composite thermodurcissable complètement polymérisé, dépôt d'une couche d'adhésif thermodurcissable non polymérisé sur une zone de contact dudit élément avec un autre élément de la pièce ; - if there is at least one element made of completely polymerized thermosetting composite material, depositing a layer of unpolymerized thermosetting adhesive on a zone of contact of said element with another element of the part;
- assemblage des éléments formant la pièce, chaque élément étant juxtaposé avec, ou empilé sur, au moins un autre élément ; - assembly of the elements forming the part, each element being juxtaposed with, or stacked on, at least one other element;
- polymérisation complète de l'assemblage par traitement thermique ; - complete polymerization of the assembly by heat treatment;
- retrait du mandrin de chaque corps complètement polymérisé. - removal of the mandrel from each fully cured body.
Selon une variante, le procédé comprend en outre, avant l'étape d'assemblage, un dépôt d'un film adhésif entre deux éléments non polymérisés et/ou partiellement polymérisés. Cela permet de maintenir ensemble ces deux éléments pendant l'assemblage ; cela peut également permettre d'améliorer la tenue mécanique de l'interface d'assemblage, une fois les deux éléments complètement polymérisés. De préférence, l'éventuelle étape de polymérisation complète d'au moins un corps en matériau composite thermodurcissable supporté par un mandrin n'est pas réalisée. En effet, il est préférable que le ou les corps de la première structure soient complètement polymérisés lors de l'assemblage avec la deuxième structure, ce qui permet de correctement positionner les corps en suivant les courbures hors plan et les courbures dans le plan au niveau des interfaces d'assemblage avec la deuxième structure. According to a variant, the method further comprises, before the assembly step, depositing an adhesive film between two unpolymerized and/or partially polymerized elements. This keeps these two elements together during assembly; this can also make it possible to improve the mechanical strength of the assembly interface, once the two elements have completely polymerized. Preferably, the optional step of complete polymerization of at least one body of thermosetting composite material supported by a mandrel is not carried out. Indeed, it is preferable for the body or bodies of the first structure to be completely polymerized during assembly with the second structure, which makes it possible to correctly position the bodies by following the out-of-plane curvatures and the in-plane curvatures at the level assembly interfaces with the second structure.
La polymérisation de deux éléments adjacents se fera par co-cuisson ou par co- bonding selon que l'un des deux éléments sera ou non dans un état complètement polymérisé avant l'assemblage. The polymerization of two adjacent elements will be done by co-firing or by co-bonding depending on whether or not one of the two elements is in a completely polymerized state before assembly.
Selon un mode de réalisation, parmi les éléments formant la pièce, il y a en outre au moins une nappe ou un tissu préimprégné de résine thermodurcissable ou qui est imprégné par la suite de résine thermodurcissable, cette nappe ou ce tissu étant appliqué, au cours de l'étape d'assemblage, sur au moins un corps, de préférence sur plusieurs corps empilés et/ou juxtaposés, et/ou sur l'éventuelle deuxième structure.According to one embodiment, among the elements forming the part, there is also at least one sheet or fabric preimpregnated with thermosetting resin or which is subsequently impregnated with thermosetting resin, this sheet or this fabric being applied, during of the assembly step, on at least one body, preferably on several stacked and/or juxtaposed bodies, and/or on the possible second structure.
Selon un autre mode de réalisation, pour au moins un corps, le mandrin est un regroupement d'au moins deux mandrins de plus petites sections, soit empilés, soit juxtaposés latéralement. According to another embodiment, for at least one body, the mandrel is a grouping of at least two mandrels of smaller sections, either stacked or juxtaposed laterally.
Avantageusement, chaque mandrin est en élastomère souple. Le mandrin peut être creux ou plein ; de préférence, on choisit un mandrin plein. Advantageously, each mandrel is made of flexible elastomer. The mandrel can be hollow or solid; preferably, a solid mandrel is chosen.
Selon une variante, au moins un mandrin a une section polygonale, par exemple de type triangulaire ou parallélépipédique. La section peut être constante ou variableAccording to a variant, at least one mandrel has a polygonal section, for example of the triangular or parallelepipedal type. Section can be constant or variable
Les mandrins peuvent avoir une section constante ou une section variable qui augmente d'une extrémité à l'autre du mandrin. The mandrels can have a constant section or a variable section which increases from one end of the mandrel to the other.
L'invention présente de nombreux avantages. Le ou les corps de la première structure permettent de réaliser un ensemble caissonné qui peut s'adapter facilement à des formes spécifiques complexes dans le plan ou hors plan, permettant de s'adapter à la surface d'une pièce à raidir (la pièce peut par exemple présenter une surface en double courbure). En d'autres termes, le ou les corps creux formant la première structure sont capables de suivre les courbures dans le plan et hors plan au niveau des interfaces d'assemblage avec la deuxième structure. Le ou les corps creux peuvent être rectilignes ou bien prendre toute courbure nécessaire dans le plan d'assemblage avec la deuxième structure. The invention has many advantages. The body or bodies of the first structure make it possible to produce a boxed assembly which can easily adapt to complex specific shapes in the plane or out of the plane, making it possible to adapt to the surface of a part to be stiffened (the part can for example, have a double curvature surface). In other words, the hollow body or bodies forming the first structure are capable of following the in-plane and out-of-plane curvatures at the assembly interfaces with the second structure. The hollow body(s) can be straight or else take any necessary curvature in the plane of assembly with the second structure.
Cela permet également de diminuer les coûts de fabrication (notamment par une diminution drastique du nombre d'éléments nécessaires au raidissage, une simplification de leur positionnement sur la pièce à raidir et une diminution des différentes opérations de collage de la structure de raidissage par rapport à l'art antérieur). This also makes it possible to reduce manufacturing costs (in particular by drastically reducing the number of elements required for stiffening, simplifying their positioning on the part to be stiffened and reducing the various bonding operations of the stiffening structure compared to prior art).
Enfin, l'invention permet d'assurer une bonne tenue mécanique et une grande fiabilité des liaisons collées. Finally, the invention makes it possible to ensure good mechanical strength and high reliability of the bonded connections.
BRÈVE DESCRIPTION DES DESSINS BRIEF DESCRIPTION OF DRAWINGS
La présente invention sera mieux comprise à la lecture de la description qui va suivre, donnée à titre purement indicatif et nullement limitatif, en faisant référence aux dessins annexés sur lesquels : The present invention will be better understood on reading the following description, given for information only and in no way limiting, with reference to the appended drawings in which:
- la figure 1 représente un exemple selon l'invention d'un corps obtenu par drapage d'une nappe ou d'un tissu préimprégné autour d'un mandrin de section rectangulaire, le corps ayant deux extrémités ouvertes ; - Figure 1 shows an example according to the invention of a body obtained by draping a sheet or a preimpregnated fabric around a mandrel of rectangular section, the body having two open ends;
- la figure 2 représente un autre exemple selon l'invention d'un corps obtenu par drapage d'une nappe ou d'un tissu préimprégné autour d'un mandrin de section triangulaire, le corps ayant deux extrémités ouvertes ; - Figure 2 shows another example according to the invention of a body obtained by draping a sheet or a preimpregnated fabric around a mandrel of triangular section, the body having two open ends;
- la figure 3 représente un autre exemple selon l'invention d'un corps obtenu par drapage d'une nappe ou d'un tissu préimprégné autour d'un mandrin de section rectangulaire, le corps ayant une seule extrémité ouverte ; - Figure 3 shows another example according to the invention of a body obtained by draping a sheet or a preimpregnated fabric around a mandrel of rectangular section, the body having only one open end;
- la figure 4 représente un autre exemple selon l'invention d'un corps obtenu par drapage d'une nappe ou d'un tissu préimprégné autour d'un mandrin de section variable, le corps ayant deux extrémités ouvertes ; - Figure 4 shows another example according to the invention of a body obtained by draping a sheet or a preimpregnated fabric around a mandrel of variable section, the body having two open ends;
- la figure 5a représente, selon une vue en coupe transversale, un exemple de drapage d'un tissu ou d'une nappe autour d'un mandrin de section rectangulaire ; - Figure 5a shows, in a cross-sectional view, an example of draping a fabric or a sheet around a mandrel of rectangular section;
- la figure 5b représente, selon une vue en coupe transversale, un autre exemple de drapage d'un tissu ou d'une nappe autour d'un mandrin de section rectangulaire ; - la figure 5c représente, selon une vue en coupe transversale, un autre exemple de drapage d'un tissu ou d'une nappe autour d'un mandrin de section rectangulaire ; - Figure 5b shows, in a cross-sectional view, another example of draping a fabric or a sheet around a mandrel of rectangular section; - Figure 5c shows, in a cross-sectional view, another example of draping a fabric or a sheet around a mandrel of rectangular section;
- la figure 5d représente, selon une vue en coupe transversale, un exemple de drapage de plusieurs tissus ou nappes autour d'un mandrin de section rectangulaire ; - Figure 5d shows, in a cross-sectional view, an example of draping several fabrics or layers around a mandrel of rectangular section;
- la figure 5e représente, selon une vue en coupe transversale, un autre exemple de drapage de plusieurs tissus ou nappes autour d'un mandrin de section rectangulaire ; - Figure 5e shows, in a cross-sectional view, another example of draping several fabrics or layers around a mandrel of rectangular section;
- la figure 5f représente, selon une vue en coupe transversale, un autre exemple de drapage d'un tissu ou d'une nappe autour d'un mandrin de section rectangulaire ; - Figure 5f shows, in a cross-sectional view, another example of draping a fabric or a sheet around a mandrel of rectangular section;
- la figure 6 représente, selon une vue en perspective, un corps formé par drapage d'un tissu autour d'un mandrin formé d'une pluralité de mandrins de plus petites sections qui sont empilés et/ou juxtaposés longitudinalement ; - Figure 6 shows, in a perspective view, a body formed by draping a fabric around a mandrel formed of a plurality of mandrels of smaller sections which are stacked and / or juxtaposed longitudinally;
- la figure 7 représente une vue en coupe transversale dans le plan A de la figure- Figure 7 shows a cross-sectional view in plane A of Figure
6 ; 6;
- la figure 8 représente, selon une vue en coupe transversale, un exemple de réalisation d'une pièce raidie selon l'invention ; - Figure 8 shows, in a cross-sectional view, an embodiment of a stiffened part according to the invention;
- la figure 9 représente, selon une vue en coupe transversale, un autre exemple de réalisation d'une pièce raidie selon l'invention ; - Figure 9 shows, in a cross-sectional view, another embodiment of a stiffened part according to the invention;
- la figure 10 représente, selon une vue en coupe transversale, un autre exemple de réalisation d'une pièce raidie selon l'invention ; - Figure 10 shows, in a cross-sectional view, another embodiment of a stiffened part according to the invention;
- la figure 11 représente, selon une vue en coupe transversale, un autre exemple de réalisation d'une pièce raidie selon l'invention ; - Figure 11 shows, in a cross-sectional view, another embodiment of a stiffened part according to the invention;
- la figure 12 représente, selon une vue en coupe transversale, un autre exemple de réalisation d'une pièce raidie selon l'invention ; - Figure 12 shows, in a cross-sectional view, another embodiment of a stiffened part according to the invention;
- la figure 13 représente, selon une vue en perspective, un exemple de placement d'un corps (supporté par un mandrin) sur une surface d'une deuxième structure (par exemple une pièce à raidir), le corps étant placé selon une direction radiale de la deuxième structure; - Figure 13 shows, in a perspective view, an example of placement of a body (supported by a mandrel) on a surface of a second structure (for example a part to be stiffened), the body being placed in a direction radial of the second structure;
- la figure 14 représente, selon une vue en perspective, un exemple de placement d'un corps (supporté par plusieurs mandrins) sur une surface d'une deuxième structure (par exemple une pièce à raidir), le corps étant placé selon une direction radiale de la deuxième structure et dépassant de la deuxième structure, la surface de contact entre la première structure et la deuxième structure n'étant pas sur la totalité de la longueur du corps; - Figure 14 shows, in a perspective view, an example of placement of a body (supported by several mandrels) on a surface of a second structure (for example a part to be stiffened), the body being placed in a direction radial of the second structure and protruding from the second structure, the contact surface between the first structure and the second structure not being over the entire length of the body;
- la figure 15 représente, selon une vue en perspective, un autre exemple de placement d'un corps (supporté par plusieurs mandrins) sur une surface d'une deuxième structure (par exemple une pièce à raidir), le corps étant placé selon une direction radiale de la deuxième structure et dépassant de la deuxième structure, la surface de contact entre la première structure et la deuxième structure n'étant pas sur la totalité de la longueur du corps et un écart étant laissé entre le corps et la deuxième structure ; - la figure 16 représente, selon une vue en perspective, un exemple de placement d'un corps (supporté par un mandrin) sur une surface d'une deuxième structure (par exemple une pièce à raidir), le corps étant placé selon une direction circonférentielle de la deuxième structure ; - Figure 15 shows, in a perspective view, another example of placement of a body (supported by several mandrels) on a surface of a second structure (for example a part to be stiffened), the body being placed according to a radial direction of the second structure and protruding from the second structure, the contact surface between the first structure and the second structure not being over the entire length of the body and a gap being left between the body and the second structure; - Figure 16 shows, in a perspective view, an example of placement of a body (supported by a mandrel) on a surface of a second structure (for example a part to be stiffened), the body being placed in a direction circumferential of the second structure;
- la figure 17 représente, selon une vue en perspective, un exemple d'une pièce raidie obtenue par le placement, sur une surface d'une deuxième structure (ici la pièce à raidir), d'une première structure formée d'un premier corps disposé selon une première direction radiale de la deuxième structure, et d'un deuxième et d'un troisième corps disposés de part et d'autre du premier corps selon une deuxième direction radiale de la deuxième structure, pouvant être perpendiculaire à la première direction ; - la figure 18 représente, selon une vue en perspective, un autre exemple d'une pièce raidie obtenue par le placement, sur une surface d'une deuxième structure (ici la pièce à raidir), d'une première structure formée d'une rangée de corps juxtaposés et disposés selon des directions radiales de la deuxième structure ; - Figure 17 shows, in a perspective view, an example of a stiffened part obtained by placing, on a surface of a second structure (here the part to be stiffened), a first structure formed of a first body arranged in a first radial direction of the second structure, and a second and a third body arranged on either side of the first body in a second radial direction of the second structure, which may be perpendicular to the first direction ; - Figure 18 shows, in a perspective view, another example of a stiffened part obtained by placing, on a surface of a second structure (here the part to be stiffened), a first structure formed of a row of bodies juxtaposed and arranged in radial directions of the second structure;
- la figure 19 représente, selon une vue en perspective, un autre exemple d'une pièce raidie obtenue par le placement d'une première structure formée de plusieurs corps sur une surface d'une deuxième structure (ici la pièce à raidir), certains corps étant positionnés dans des directions radiales de la deuxième structure et d'autres dans des directions circonférentielles de la deuxième structure, les corps étant joints les uns aux autres dans des zones de contact ; - la figure 20 représente, selon une vue en perspective, un autre exemple d'une pièce raidie, comprenant une première structure formée d'un premier corps disposé selon une direction radiale d'une deuxième structure (ici la pièce à raidir) et d'un deuxième corps disposé à cheval sur le premier corps et la deuxième structure, selon une direction circonférentielle de la deuxième structure ; - Figure 19 shows, in a perspective view, another example of a stiffened part obtained by placing a first structure formed of several bodies on a surface of a second structure (here the part to be stiffened), some bodies being positioned in radial directions of the second structure and others in circumferential directions of the second structure, the bodies being joined to each other in contact zones; - Figure 20 shows, in a perspective view, another example of a stiffened part, comprising a first structure formed of a first body arranged in a radial direction of a second structure (here the part to be stiffened) and a second body disposed astride the first body and the second structure, in a circumferential direction of the second structure;
- la figure 21 représente, selon une vue en perspective, un autre exemple d'une pièce raidie, réalisée uniquement à partir de corps assemblés les uns aux autres et formant la première structure ; - Figure 21 shows, in a perspective view, another example of a stiffened part, made only from bodies assembled to each other and forming the first structure;
- la figure 22 représente, selon une vue de dessus, un exemple de six corps disposés radialement et à égales distances les uns des autres sur la surface d'une deuxième structure (pièce à raidir) ; - Figure 22 shows, in a top view, an example of six bodies arranged radially and at equal distances from each other on the surface of a second structure (part to be stiffened);
- la figure 23 représente, selon une vue de dessus, un exemple de trois corps disposés sur la surface d'une deuxième structure (pièce à raidir), chaque corps ayant une extrémité qui dépasse de la deuxième structure et l'autre extrémité rejoignant une paroi latérale d'un des autres corps, la jonction des trois corps formant un triangle au centre de la deuxième structure ; - Figure 23 shows, in a top view, an example of three bodies arranged on the surface of a second structure (part to be stiffened), each body having one end which protrudes from the second structure and the other end joining a side wall of one of the other bodies, the junction of the three bodies forming a triangle at the center of the second structure;
- la figure 24 représente, selon une vue de dessus, un autre exemple de quatre corps disposés sur la surface d'une deuxième structure (pièce à raidir), chaque corps ayant une extrémité qui dépasse de la deuxième structure et l'autre extrémité rejoignant une paroi latérale d'un des autres corps, la jonction des quatre corps formant un carré au centre de la deuxième structure ; - Figure 24 shows, in a top view, another example of four bodies arranged on the surface of a second structure (part to be stiffened), each body having one end which protrudes from the second structure and the other end joining a side wall of one of the other bodies, the junction of the four bodies forming a square in the center of the second structure;
- la figure 25 représente, selon une vue de dessus, un autre exemple de quatre corps disposés sur la surface d'une deuxième structure (pièce à raidir), chaque corps ayant une extrémité qui vient à un endroit à la périphérie de la deuxième structure et l'autre extrémité qui vient à un autre endroit, diamétralement opposé, à la périphérie de la deuxième structure, chaque corps chevauchant un des trois autres corps et étant chevauché par un autre des trois autre corps ; - Figure 25 shows, in a top view, another example of four bodies arranged on the surface of a second structure (part to be stiffened), each body having an end which comes to a place at the periphery of the second structure and the other end which comes to another place, diametrically opposite, at the periphery of the second structure, each body overlapping one of the three other bodies and being overlapped by another of the three other bodies;
- la figure 26 représente, selon une vue de dessus, un autre exemple de quatre corps disposés sur la surface d'une deuxième structure (pièce à raidir), une extrémité de chaque corps longeant la périphérie de la deuxième structure et l'autre extrémité rejoignant une paroi latérale d'un des autres corps à proximité du centre de la deuxième structure, la jonction des quatre corps formant un cercle au centre de la deuxième structure. - Figure 26 shows, in a top view, another example of four bodies arranged on the surface of a second structure (part to be stiffened), one end of each body running along the periphery of the second structure and the other end joining a side wall of one of the other bodies near the center of the second structure, the junction of the four bodies forming a circle in the center of the second structure.
EXPOSÉ DÉTAILLÉ DE MODES DE RÉALISATION PARTICULIERS DETAILED DISCUSSION OF PARTICULAR EMBODIMENTS
La pièce raidie selon l'invention comporte une première structure 6 et une éventuelle deuxième structure 7, les première et deuxième structures étant en matériau composite thermodurci, et la première structure comprenant au moins un corps 2 longitudinal creux ayant au moins une extrémité ouverte 3. The stiffened part according to the invention comprises a first structure 6 and a possible second structure 7, the first and second structures being made of thermoset composite material, and the first structure comprising at least one hollow longitudinal body 2 having at least one open end 3.
Le matériau composite thermodurci est un matériau composite du type à renfort fibreux imprégné par une matrice thermodurcissable qui est thermodurcie par traitement thermique. C'est notamment ce qui va permettre d'assembler les différents éléments formant la pièce par co-cuisson (ou « co-curing » en anglais) ou par co-collage (ou « co- bonding » en anglais), comme nous le verrons plus loin. The thermoset composite material is a composite material of the fibrous reinforcement type impregnated with a thermosetting matrix which is thermoset by heat treatment. This is what will make it possible to assemble the different elements forming the piece by co-curing (or "co-curing" in English) or by co-gluing (or "co-bonding" in English), as we see further.
Le renfort fibreux peut être en fibres de carbone et/ou de verre et/ou de fibres de Kevlar™ ; il peut aussi s'agir d'une combinaison de plusieurs types de fibres, par exemple un mélange de fibres verre/carbone, ou de fibres carbone/KevIar™ The fibrous reinforcement can be made of carbon fibers and/or glass and/or Kevlar™ fibers; it can also be a combination of several types of fibers, for example a mixture of glass/carbon fibers, or carbon/KevIar™ fibers
La matrice est un liant en résine qui imprègne le renfort et se solidifie lorsqu'elle est polymérisée. Dans l'invention, la matrice est une résine thermodurcissable. Le monomère de base de la résine époxy peut par exemple être de type DGEBA (DiGlycidyl Éther de Bisphénol A), TGPAP (TriGlycidyl ParaAminoPhénol) ou TGMDA (TétraGlycidyl Méthylène DiAniline). Le durcisseur peut être de type amine, par exemple du DDS (DiaminoDiphényl Sulfone). The matrix is a resin binder that permeates the reinforcement and solidifies when cured. In the invention, the matrix is a thermosetting resin. The base monomer of the epoxy resin can for example be of the DGEBA (DiGlycidyl Ether of Bisphenol A), TGPAP (TriGlycidyl ParaAminoPhenol) or TGMDA (TetraGlycidyl Methylene DiAniline) type. The hardener can be of the amine type, for example DDS (DiaminoDiphenyl Sulfone).
Les résines thermodurcissables utilisées et décrites dans ce document polymérisent complètement à une température généralement comprise entre 120°C et 220°C pendant une durée de deux heures à température de polymérisation. Plus précisément, les résines les plus employées dans le spatial et l'aéronautique sont des résines dites de classe 180°C, pour lesquelles la polymérisation complète est atteinte au bout de 2h à 180°C. The thermosetting resins used and described in this document polymerize completely at a temperature generally between 120° C. and 220° C. for a period of two hours at the polymerization temperature. More specifically, the resins most used in space and aeronautics are so-called 180°C class resins, for which complete polymerization is achieved after 2 hours at 180°C.
Pour le renfort fibreux, on peut utiliser des tissus ou des nappes et les empiler pour former des strates. On peut utiliser un renfort fibreux pré-imprégné de résine thermodurcissable (également appelé « prepreg » en anglais) ou imprégner avec la résine un renfort fibreux après mise en forme de ce renfort fibreux. Le renfort fibreux imprégné de résine peut éventuellement être compacté avant de subir une polymérisation. For the fibrous reinforcement, fabrics or webs can be used and stacked to form strata. You can use a fibrous reinforcement pre-impregnated with resin thermosetting (also called "prepreg" in English) or impregnate with the resin a fibrous reinforcement after shaping this fibrous reinforcement. The fibrous reinforcement impregnated with resin can optionally be compacted before undergoing polymerization.
De manière générale, dans le cadre de la présente invention, l'assemblage de deux éléments (qu'il s'agisse par exemple de l'assemblage de deux corps 2 de la première structure 6 ou de l'assemblage de la première structure 6 avec la deuxième structure 7) correspond soit à un collage par« co-curing », lorsque les deux éléments à assembler sont non polymérisés ou partiellement polymérisés et sont amenés à un état de polymérisation complète lors du même cycle de chauffage, soit à un collage par « co- bonding », lorsque l'un des deux éléments est déjà complètement polymérisé, avec la nécessité de réaliser une préparation de surface de l'élément polymérisé et de disposer à l'interface des deux éléments une couche d'adhésif en résine thermodurcissable, adhésif préférentiellement sous la forme d'un film. En d'autres termes, dès lors qu'un élément est totalement polymérisé, il est nécessaire, pour qu'il soit assemblé à un autre élément, qu'on dépose une couche d'adhésif à l'interface de collage des deux éléments. On fera généralement une préparation de l'interface de collage par exemple par ponçage et nettoyage avec un solvant, pour ensuite déposer un film d'adhésif. Dans le cas d'un collage par « co-bonding », il y a deux cycles de chauffage, un premier cycle au cours duquel l'un des deux éléments est complètement polymérisé et un second cycle au cours duquel le deuxième élément, ainsi que l'adhésif, sont complètement polymérisés. Au final, que ce soit par collage par « co-curing » ou par « co-bonding », on obtient une liaison entre les deux éléments par collage à chaud qui présente une grande fiabilité et une très bonne tenue mécanique. In general, in the context of the present invention, the assembly of two elements (whether for example the assembly of two bodies 2 of the first structure 6 or the assembly of the first structure 6 with the second structure 7) corresponds either to bonding by "co-curing", when the two elements to be assembled are unpolymerized or partially polymerized and are brought to a state of complete polymerization during the same heating cycle, or to bonding by "co-bonding", when one of the two elements is already completely polymerized, with the need to prepare the surface of the polymerized element and to place a layer of resin adhesive at the interface of the two elements thermosetting, adhesive preferably in the form of a film. In other words, once an element is completely polymerized, it is necessary, in order for it to be assembled to another element, that a layer of adhesive be deposited at the bonding interface of the two elements. The bonding interface will generally be prepared, for example by sanding and cleaning with a solvent, then depositing a film of adhesive. In the case of "co-bonding" bonding, there are two heating cycles, a first cycle during which one of the two elements is completely polymerized and a second cycle during which the second element, as well as adhesive, are fully cured. In the end, whether by bonding by "co-curing" or by "co-bonding", a bond is obtained between the two elements by hot bonding which has great reliability and very good mechanical strength.
Nous allons à présent décrire en détails le procédé de réalisation d'une pièce raidie selon l'invention. We will now describe in detail the process for producing a stiffened part according to the invention.
Réalisation du ou des corps : Realization of the body(ies):
On commence par réaliser un ou plusieurs corps 2 longitudinaux creux. Pour ce faire, on procède au drapage par enroulement d'un tissu ou d'une nappe 5 autour d'un mandrin 1 afin de former une préforme. Le tissu ou la nappe 5 peut être préimprégné de résine thermodurcissable, ou bien être sec et le tissu ou la nappe est imprégné avec une résine thermodurcissable par la suite, par exemple par injection ou infusion de la résine dans la préforme sèche déjà mise en forme. La phase d'injection/infusion intervient lorsque la préforme est placée dans un moule fermé. Cette phase est suivie d'une polymérisation de la résine injectée. Comme illustré dans les figures 1 et 2, le mandrin 1 peut avoir une section constante, par exemple rectangulaire (figure 1) ou triangulaire (figure 2) ou une section variable (figure 4). Si la section est variable, elle doit néanmoins permettre l'extraction du mandrin hors du corps une fois la résine polymérisée. On apportera dans ce cas une attention particulière à ce que la variation de section ou la déformation du mandrin lors de l'extraction autorise la démoulabilité (extraction), depuis l'extrémité ouverte 3, du mandrin placé à l'intérieur du corps. We start by making one or more hollow longitudinal bodies 2. To do this, draping is carried out by winding a fabric or a sheet 5 around a mandrel 1 in order to form a preform. The fabric or sheet 5 can be preimpregnated with thermosetting resin, or else be dry and the fabric or sheet is impregnated with a thermosetting resin subsequently, for example by injection or infusion of the resin into the dry preform already shaped. The injection/infusion phase occurs when the preform is placed in a closed mould. This phase is followed by polymerization of the injected resin. As illustrated in Figures 1 and 2, the mandrel 1 can have a constant section, for example rectangular (Figure 1) or triangular (Figure 2) or a variable section (Figure 4). If the section is variable, it must nevertheless allow the extraction of the mandrel from the body once the resin has polymerized. In this case, particular attention will be paid to ensuring that the variation in section or the deformation of the mandrel during extraction allows the moldability (extraction), from the open end 3, of the mandrel placed inside the body.
Le corps 2 doit avoir au moins une extrémité ouverte 3 (dans la figure 3, le corps possède une extrémité fermée 4) ; il peut avoir deux extrémités ouvertes 3 (figures 1, 2, 4), afin de permettre la sortie du mandrin. The body 2 must have at least one open end 3 (in Figure 3 the body has a closed end 4); it can have two open ends 3 (FIGS. 1, 2, 4), in order to allow the mandrel to come out.
Une ou plusieurs couches de tissu ou de nappe 5 peuvent être enroulées autour d'un même mandrin 1. L'enroulement de chaque couche peut se faire : One or more layers of fabric or ply 5 can be wound around the same mandrel 1. The winding of each layer can be done:
- par recouvrement (le tissu se replie sur lui-même) (figure 5a) ; - by covering (the fabric folds back on itself) (figure 5a);
- par jonction jointive (le tissu se touche sans recouvrement) (figure 5b) ; - by contiguous junction (the fabric touches without covering) (figure 5b);
- par jonction non jointive (par exemple, enroulement partiellement tubulaire (figure 5c) ou enroulement partiel (figure 5f)). - By non-adjoining junction (for example, partially tubular winding (Figure 5c) or partial winding (Figure 5f)).
Il est également possible d'utiliser au moins deux couches jointives ou non (figures 5d et 5e) pour former un corps 2. It is also possible to use at least two layers which may or may not be contiguous (FIGS. 5d and 5e) to form a body 2.
Il est également possible d'enrouler une (ou plusieurs) couche(s) de tissu ou nappe 5 autour d'un mandrin 1 formé de plusieurs mandrins 10, 11, 12, 13, 14, 15 de plus petites sections regroupés latéralement, tel qu'illustré dans les figures 6 et 7. Cela peut s'avérer nécessaire lorsque la forme de la deuxième structure 7, à laquelle doit s'adapter le corps 2, est très courbée et/ou que la hauteur du corps 2 est importante. Là encore, le drapage peut être réalisé sur toute la périphérie du mandrin ou seulement sur une partie (drapage partiel). It is also possible to wrap one (or more) layer(s) of fabric or sheet 5 around a mandrel 1 formed of several mandrels 10, 11, 12, 13, 14, 15 of smaller sections grouped laterally, such illustrated in Figures 6 and 7. This may prove necessary when the shape of the second structure 7, to which the body 2 must adapt, is very curved and/or the height of the body 2 is significant. Here again, the draping can be carried out over the entire periphery of the mandrel or only over a part (partial draping).
Comme nous l'avons déjà dit, la pièce à raidir comporte une première structure 6, composée d'un ou plusieurs corps 2, et d'une éventuelle deuxième structure 7. Étant donné que la pièce raidie comporte forcément deux éléments dont un corps, alors si la première structure 6 ne comporte qu'un seul corps 2, il y aura forcément une deuxième structure 7. La pièce raidie peut ne comporter qu'une première structure 6, comme illustré dans la figure 21, mais elle comporte généralement une deuxième structure 7, qui est généralement la pièce à raidir. Cette structure 7 peut être une structure sandwich constituée de 2 peaux et d'un matériau d'âme du type alvéolaire ; généralement, il s'agira d'une âme alvéolaire en nid d'abeille, mais il peut également s'agir d'une âme en mousse à pores fermés ou ouverts. Dans le cas d'un réflecteur d'antenne de satellite, la deuxième structure 7 est la coque sandwich du réflecteur que l'on souhaite raidir. As we have already said, the part to be stiffened comprises a first structure 6, composed of one or more bodies 2, and of a possible second structure 7. Being given that the stiffened part necessarily comprises two elements including a body, then if the first structure 6 only comprises a single body 2, there will necessarily be a second structure 7. The stiffened part may only comprise a first structure 6, as illustrated in figure 21, but it generally comprises a second structure 7, which is generally the part to be stiffened. This structure 7 can be a sandwich structure consisting of 2 skins and a core material of the honeycomb type; usually this will be a honeycomb cell core, but it can also be a closed or open pore foam core. In the case of a satellite antenna reflector, the second structure 7 is the sandwich shell of the reflector which it is desired to stiffen.
Selon une variante de l'invention, il est possible de draper les tissus ou nappes 5 sur la surface de la deuxième structure 7 au niveau de l'interface d'assemblage entre la deuxième structure 7 et un corps 2, puis de placer le mandrin 1, ou plusieurs mandrins 1, sur les tissus ou nappes, et enfin venir enrouler les tissus ou nappes autour du ou des mandrins. Cela peut être utile dans le cas où il y aurait beaucoup de couches à enrouler autour du ou des mandrins et/ou lorsque la forme de la deuxième structure est très courbée. According to a variant of the invention, it is possible to drape the fabrics or webs 5 on the surface of the second structure 7 at the level of the assembly interface between the second structure 7 and a body 2, then to place the mandrel 1, or several mandrels 1, on the fabrics or webs, and finally come to wrap the fabrics or webs around the mandrel(s). This can be useful in cases where there are many layers to wrap around the core(s) and/or where the shape of the second structure is very curved.
De préférence, le mandrin est en élastomère souple de manière à : Preferably, the mandrel is made of flexible elastomer so as to:
- pouvoir s'adapter facilement à la forme de la deuxième structure sur laquelle il est destiné à être positionné ; - Being able to adapt easily to the shape of the second structure on which it is intended to be positioned;
- pouvoir extraire le mandrin facilement de l'intérieur du corps par striction (traction élongation de l'élastomère, accompagnée d'une diminution de la section lors de l'élongation). - be able to extract the mandrel easily from inside the body by necking (elongation traction of the elastomer, accompanied by a reduction in section during elongation).
Assemblage du ou des corps de la première structure et de l'éventuelle deuxième structure : Assembly of the body or bodies of the first structure and any second structure:
La deuxième structure 7 peut être de type monolithique ou de type sandwich. De manière préférentielle, dans le cas de l'application au réflecteur d'antenne, la deuxième structure est de type sandwich. The second structure 7 can be of the monolithic type or of the sandwich type. Preferably, in the case of the application to the antenna reflector, the second structure is of the sandwich type.
Selon un mode de réalisation, le ou les corps non polymérisés ou partiellement polymérisés sont posés sur la deuxième structure 7 non polymérisée ou partiellement polymérisée en prenant garde de bien suivre la forme de la surface de la deuxième structure et l'emplacement défini. According to one embodiment, the unpolymerized or partially polymerized body or bodies are placed on the second unpolymerized or partially polymerized structure 7 polymerized taking care to follow the shape of the surface of the second structure and the defined location.
Il est possible d'utiliser la projection laser de l'emplacement de chaque corps sur la deuxième structure pour aider au positionnement et améliorer la précision de la pose. It is possible to use the laser projection of the location of each body on the second structure to help positioning and improve the precision of the pose.
Des compactages intermédiaires sous dépression peuvent être employés au fur et à mesure de la dépose des corps, afin d'assurer un meilleur maintien sur la deuxième structure 7 et une meilleure conformation de chaque corps. Intermediate compactions under depression can be used as the bodies are removed, in order to ensure better support on the second structure 7 and better conformation of each body.
Il est également possible de réaliser une dépose de plis 9 supplémentaires en tissus ou nappes préimprégnés de résine thermodurcissable venant recouvrir un ou plusieurs corps, ainsi qu'une partie de la surface de la deuxième structure (comme illustré notamment dans les figures 8, 9, 10, 11, 12, 19). It is also possible to deposit additional plies 9 in fabrics or layers preimpregnated with thermosetting resin covering one or more bodies, as well as part of the surface of the second structure (as illustrated in particular in Figures 8, 9, 10, 11, 12, 19).
Une fois tous les éléments positionnés, on procède à la polymérisation de l'ensemble. On obtiendra alors un assemblage par co-cuisson. Once all the elements have been positioned, the whole assembly is polymerized. We will then obtain an assembly by co-firing.
En variante, la deuxième structure 7 peut être complètement polymérisée. Dans ce cas, il faudra, avant de placer le ou les corps 2 sur la deuxième structure 7, préparer la surface de la deuxième structure dans la zone d'assemblage (par exemple, dégraissage, ponçage, nettoyage), puis y déposer une couche d'adhésif thermodurcissable avant drapage des corps 2. Après polymérisation de l'ensemble, on obtient ainsi un assemblage par co-bonding. As a variant, the second structure 7 can be completely polymerized. In this case, it will be necessary, before placing the body or bodies 2 on the second structure 7, to prepare the surface of the second structure in the assembly zone (for example, degreasing, sanding, cleaning), then depositing a layer of thermosetting adhesive before draping the bodies 2. After polymerization of the assembly, an assembly by co-bonding is thus obtained.
En variante, on peut réaliser l'assemblage des corps directement sur le moule de drapage de la deuxième structure. On procède ensuite à une polymérisation partielle des corps (mi-cuisson), on les sépare du moule et on procède au stockage de l'ensemble réalisé sans démoulage des mandrins. Lors de l'étape de polymérisation partielle, le taux de polymérisation, mesuré par calorimétrie différentielle à balayage (DSC) suivant la norme ISO 11357-1 :2016, est compris entre 10% et 75%, et préférentiellement compris entre 15% et 40%. Par la suite, cet ensemble pourra être placé sur la surface de la deuxième structure à raidir, et on pourra procéder à la polymérisation complète. L'assemblage sera par co-cuisson si la deuxième structure est non polymérisée ou partiellement polymérisée, ou par co-bonding, si la deuxième structure est polymérisée (dans ce cas, il faudra au préalable déposer une couche d'adhésif, comme décrit précédemment). As a variant, the bodies can be assembled directly on the draping mold of the second structure. The bodies are then partially polymerized (half-cured), they are separated from the mold and the assembly produced is stored without removing the mandrels from the mould. During the partial polymerization step, the degree of polymerization, measured by differential scanning calorimetry (DSC) according to standard ISO 11357-1:2016, is between 10% and 75%, and preferably between 15% and 40 %. Subsequently, this assembly can be placed on the surface of the second structure to be stiffened, and complete polymerization can be carried out. Assembly will be by co-firing if the second structure is uncured or partially cured, or by co-bonding, if the second structure is cured (in this case, it will first be necessary to deposit a layer of adhesive, as described previously).
En variante, on peut réaliser la deuxième structure 7 en procédant au drapage de la deuxième structure sur un moule de drapage avec des tissus ou nappes préimprégnés, puis on procède à l'assemblage de la première structure, déjà constituée, formant un ensemble caissonné, sur la deuxième structure non polymérisée. Si la première structure est partiellement polymérisée, il n'y a pas besoin de réaliser une préparation de surface à l'interface de collage, ni besoin d'un film adhésif à l'interface (l'assemblage s'apparentant à de la co-cuisson). Au contraire, si la première structure est complètement polymérisée, il est nécessaire de réaliser un traitement de surface préliminaire de la surface à l'emplacement du collage (dégraissage, ponçage, nettoyage), puis ajout d'un film d'adhésif (afin d'obtenir un assemblage par co-bonding). As a variant, the second structure 7 can be produced by draping the second structure on a draping mold with pre-impregnated fabrics or sheets, then assembling the first structure, already constituted, forming a boxed assembly, on the second unpolymerized structure. If the first structure is partially polymerized, there is no need to perform surface preparation at the bonding interface, nor need for an adhesive film at the interface (the assembly being similar to co -cooking). On the contrary, if the first structure is completely polymerized, it is necessary to carry out a preliminary surface treatment of the surface at the location of the bonding (degreasing, sanding, cleaning), then adding an adhesive film (in order to to obtain an assembly by co-bonding).
Dans cette variante, on préfère une polymérisation partielle de la première structure ; ainsi, lors de la polymérisation finale, la viscosité de la résine partiellement polymérisée de la première structure va diminuer (ramollissement de la résine) et permettre, d'une part, une bonne conformation de la première structure à la surface de la deuxième structure, et, d'autre part, la création de liaisons entre les chaînes polymères des deux résines (première et deuxième structures). In this variant, partial polymerization of the first structure is preferred; thus, during the final polymerization, the viscosity of the partially polymerized resin of the first structure will decrease (softening of the resin) and allow, on the one hand, a good conformation of the first structure on the surface of the second structure, and, on the other hand, the creation of bonds between the polymer chains of the two resins (first and second structures).
Dans le cas où les deux structures 6 et 7 sont partiellement polymérisées, le comportement des résines de chaque structure sera similaire lors de la polymérisation finale. Lors de la montée en température, la viscosité de chaque résine va diminuer, permettant une bonne conformation des structures à l'emplacement des interfaces d'assemblage, assortie d'une création de liaisons entre les chaînes polymères des deux résines. In the case where the two structures 6 and 7 are partially polymerized, the behavior of the resins of each structure will be similar during the final polymerization. During the rise in temperature, the viscosity of each resin will decrease, allowing a good conformation of the structures at the location of the assembly interfaces, accompanied by the creation of bonds between the polymer chains of the two resins.
On pourra également positionner un film adhésif à l'interface entre les deux structures 6 et 7 crues, entre une structure crue et une structure partiellement polymérisée, ou bien entre deux structures 6 et 7 partiellement polymérisées pour des raisons de maintien en position lors du drapage et/ou des raisons de tenue mécanique de la liaison collée une fois complètement polymérisée. It is also possible to position an adhesive film at the interface between the two raw structures 6 and 7, between a raw structure and a partially polymerized structure, or else between two partially polymerized structures 6 and 7 for reasons of holding in position during draping and/or reasons of mechanical strength of the bonded bond once completely polymerized.
Les configurations d'assemblage du ou des corps sont multiples. Les corps 2 formant la première structure 6 peuvent être assemblés sur la deuxième structure (figure 8), à la fois sur et dans la deuxième structure (figure 12) ou bien encore dans la deuxième structure (figures 9, 10, 11). Il est également possible qu'il n'y ait pas de deuxième structure 7 et que la première structure 6 forme à elle seule la pièce raidie (figure 21). The assembly configurations of the body or bodies are multiple. The bodies 2 forming the first structure 6 can be assembled on the second structure (FIG. 8), both on and in the second structure (FIG. 12) or even in the second structure (FIGS. 9, 10, 11). It is also possible that there is no second structure 7 and that the first structure 6 alone forms the stiffened part (FIG. 21).
Dans la figure 21, la première structure 6 comporte une première rangée de corps juxtaposés et une deuxième rangée de corps juxtaposés, les première et deuxième rangées étant empilées et les corps de la première rangée étant décalés par rapport aux corps de la deuxième rangée. Par exemple, comme illustré dans la figure 21, les première et deuxième rangées peuvent être décalées d'un décalage à mi-largeur d'un corps. Cette figure 21 illustre un des nombreux exemples possibles de pièce raidie. En changeant le nombre de rangées, de formes des corps, ainsi que la position des corps entre eux, il est possible d'obtenir de multiples configurations, non détaillées dans cette description. In FIG. 21, the first structure 6 comprises a first row of juxtaposed bodies and a second row of juxtaposed bodies, the first and second rows being stacked and the bodies of the first row being offset with respect to the bodies of the second row. For example, as shown in Figure 21, the first and second rows can be offset by a half-width offset of a body. This figure 21 illustrates one of the many possible examples of a stiffened part. By changing the number of rows, shapes of the bodies, as well as the position of the bodies between them, it is possible to obtain multiple configurations, not detailed in this description.
Dans les figures 8 à 12, la pièce raidie comporte une première structure 6 et une deuxième structure 7. In figures 8 to 12, the stiffened part comprises a first structure 6 and a second structure 7.
Dans la figure 8, la première structure 6 est un empilement de quatre corps 2 ; la première structure est assemblée sur la surface de la deuxième structure 7 avec un pli 9. In FIG. 8, the first structure 6 is a stack of four bodies 2; the first structure is assembled on the surface of the second structure 7 with a fold 9.
Dans la figure 9, la première structure 6 est un regroupement de quatre corps 2, tandis que dans la figure 10, la première structure 6 comporte un seul corps 2. In Figure 9, the first structure 6 is a grouping of four bodies 2, while in Figure 10, the first structure 6 comprises a single body 2.
Dans les figures 9 et 10, la première structure 6 est en partie incorporée dans la deuxième structure 7. Pour le ou les corps 2 qui sont en contact avec la deuxième structure 7, le contact peut être un contact partiel. En cela, le ou les corps 2 peuvent aller au-delà de la surface de la deuxième structure 7 (comme illustré, par exemple, dans la figure 14) ou bien présenter localement un écart entre les deux surfaces de manière à ce qu'elles ne soient plus assemblées (comme illustré, par exemple, dans la figure 15). In FIGS. 9 and 10, the first structure 6 is partly incorporated into the second structure 7. For the body or bodies 2 which are in contact with the second structure 7, the contact may be a partial contact. In this, the body or bodies 2 can go beyond the surface of the second structure 7 (as illustrated, for example, in FIG. 14) or else locally present a gap between the two surfaces so that they no longer assembled (as shown, for example, in Figure 15).
Dans la figure 11, la première structure 6 comporte deux corps 2 juxtaposés et est totalement incorporée dans la deuxième structure 7. In figure 11, the first structure 6 comprises two juxtaposed bodies 2 and is completely incorporated into the second structure 7.
Il est à noter que dans les figures 8, 9, 11 et 12, le contact entre les corps adjacents se fait par leur paroi latérale. Dans la figure 12, la première structure 6 comporte sept corps 2 empilés et juxtaposés et est en partie incorporée dans la deuxième structure 7 ; ici, l'un des sept corps est complètement intégré dans la deuxième structure 7 et les six autres corps sont situés au-dessus de la surface de la deuxième structure 7. It should be noted that in FIGS. 8, 9, 11 and 12, the contact between the adjacent bodies is made by their side wall. In FIG. 12, the first structure 6 comprises seven stacked and juxtaposed bodies 2 and is partly incorporated into the second structure 7; here, one of the seven bodies is completely integrated into the second structure 7, and the other six bodies are located above the surface of the second structure 7.
Il est à noter que, parmi les corps 2 formant la première structure, deux ou plusieurs corps adjacents peuvent ne pas être en contact entre eux, car on peut disposer un pli 9 entre deux corps adjacents. It should be noted that, among the bodies 2 forming the first structure, two or more adjacent bodies may not be in contact with each other, since a ply 9 may be placed between two adjacent bodies.
Lorsque la pièce raidie comporte une première et une deuxième structure, différentes configurations d'assemblage sont possibles. When the stiffened part comprises a first and a second structure, different assembly configurations are possible.
Le ou les corps 2 de la première structure 6 peuvent être agencés suivant n'importe quelle direction sur la surface de la structure 7. Le positionnement du ou des corps 2 sur la surface de la structure 7 peut être rectiligne (par exemple, les figures 22, 23, 24) ou bien courbe (par exemple, les figures 25 et 26). The body or bodies 2 of the first structure 6 can be arranged in any direction on the surface of the structure 7. The positioning of the body or bodies 2 on the surface of the structure 7 can be rectilinear (for example, the figures 22, 23, 24) or curved (for example, figures 25 and 26).
Par exemple, le ou les corps 2 de la première structure 6 peuvent être agencés sur la surface de la deuxième structure 7 suivant une direction radiale de la deuxième structure (figure 13), selon une direction circonférentielle de la deuxième structure (figure 16) ou bien encore selon une configuration combinant des directions radiales et circonférentielles (figure 19). For example, the body or bodies 2 of the first structure 6 can be arranged on the surface of the second structure 7 in a radial direction of the second structure (FIG. 13), in a circumferential direction of the second structure (FIG. 16) or well again according to a configuration combining radial and circumferential directions (FIG. 19).
Le ou les corps 2 peuvent dépasser de la deuxième structure 7, comme illustré par exemple dans la figure 14, où l'on peut voir que la surface de contact entre le corps 2 de la première structure et la deuxième structure n'est pas sur la totalité de la longueur du corps. Il peut également y avoir un écart entre le ou les corps 2 et la surface de la deuxième structure 7, comme illustré par exemple dans la figure 15. The body or bodies 2 may protrude from the second structure 7, as illustrated for example in figure 14, where it can be seen that the contact surface between the body 2 of the first structure and the second structure is not on the entire length of the body. There may also be a gap between the body or bodies 2 and the surface of the second structure 7, as illustrated for example in figure 15.
D'autres configurations sont illustrées dans les figures 22 à 26, où la pièce à raidir (la deuxième structure 7) est une plaque de périphérie circulaire. Other configurations are illustrated in FIGS. 22 to 26, where the part to be stiffened (the second structure 7) is a circular peripheral plate.
Dans la figure 17, on a une configuration où la première structure 6 a une forme de croix, avec un premier long corps 2 positionné dans une première direction radiale de la deuxième structure 7 et deux corps moins longs, qui sont positionnés de part et d'autre du premier corps, selon une direction radiale de la deuxième structure, perpendiculaire à la première direction. Ici, les deux corps moins longs ont de préférence une extrémité ouverte (pour la sortie du mandrin) et une extrémité fermée, la paroi latérale de l'extrémité fermée permettant l'assemblage avec la paroi latérale du premier corps. Dans la figure 17, contrairement à la figure 16, la pièce raidie est représentée après l'extraction des mandrins 1. In FIG. 17, there is a configuration where the first structure 6 has the shape of a cross, with a first long body 2 positioned in a first radial direction of the second structure 7 and two shorter bodies, which are positioned on either side. other of the first body, in a radial direction of the second structure, perpendicular to the first direction. Here, the two shorter bodies preferably have one end open (for exit from the chuck) and a closed end, the side wall of the closed end allowing assembly with the side wall of the first body. In figure 17, contrary to figure 16, the stiffened part is represented after the extraction of the mandrels 1.
Dans la figure 18, la première structure 6 comporte une rangée de sept corps 2 juxtaposés et de longueurs différentes ; le contact entre les corps adjacents se fait par leur paroi latérale. In FIG. 18, the first structure 6 comprises a row of seven juxtaposed bodies 2 of different lengths; contact between adjacent bodies is through their side wall.
On peut également avoir un chevauchement des corps 2, comme représenté dans la figure 20 ; ici, un des deux corps 2 est disposé selon une direction radiale de la deuxième structure 7 et l'autre selon une direction circonférentielle, ce dernier corps étant disposé à la fois sur la surface de la deuxième structure et sur une partie du premier corps et il se conforme à la forme de la surface de la deuxième structure, ainsi qu'à celle du corps qu'il chevauche. One can also have an overlap of the bodies 2, as shown in Figure 20; here, one of the two bodies 2 is arranged in a radial direction of the second structure 7 and the other in a circumferential direction, this latter body being arranged both on the surface of the second structure and on a part of the first body and it conforms to the shape of the surface of the second structure, as well as that of the body it overlaps.
Quelques plis 9 peuvent recouvrir le ou les corps 2 de la première structure 6 et/ou de la deuxième structure 7. Par exemple, dans la figure 8, quelques plis 9 viennent recouvrir la première structure, avec un retour sur la surface de la deuxième structure ; on obtient un drapage en forme de oméga (W). Dans la figure 9, un premier drapage recouvre les quatre corps de la première structure, et un deuxième et troisième drapage recouvrent respectivement la surface supérieure et la surface inférieure de la deuxième structure, ainsi que la première structure 6. Dans les figures 10 et 11, un premier et un deuxième drapage recouvrent respectivement la surface supérieure et la surface inférieure de la deuxième structure. Dans la figure 12, un premier et deuxième pli 9 recouvre respectivement la surface inférieure et supérieure de la deuxième structure 7, ainsi que le corps intégré à la deuxième structure 7. Un troisième pli 9 recouvre la surface de la structure 6 et une partie de la surface supérieure de la structure 7. Dans la figure 21, quelques plis 9 peuvent être drapés sur les faces avant et arrière de la première structure 6, ou entre les rangées de corps 2, pour finaliser le drapage. A few folds 9 can cover the body or bodies 2 of the first structure 6 and/or of the second structure 7. For example, in FIG. 8, a few folds 9 come to cover the first structure, with a return on the surface of the second framework; an omega-shaped draping (W) is obtained. In FIG. 9, a first draping covers the four bodies of the first structure, and a second and third draping respectively covers the upper surface and the lower surface of the second structure, as well as the first structure 6. In FIGS. 10 and 11 , a first and a second layup respectively cover the upper surface and the lower surface of the second structure. In FIG. 12, a first and second ply 9 respectively covers the lower and upper surface of the second structure 7, as well as the body integrated into the second structure 7. A third ply 9 covers the surface of the structure 6 and part of the upper surface of the structure 7. In FIG. 21, a few folds 9 can be draped over the front and rear faces of the first structure 6, or between the rows of bodies 2, to finalize the draping.

Claims

Revendications Claims
1. Pièce raidie comprenant au moins une première structure (6) en matériau composite thermodurci, laquelle première structure comporte au moins un corps (2) longitudinal creux ayant au moins une extrémité ouverte (3). 1. Stiffened part comprising at least a first structure (6) of thermoset composite material, which first structure comprises at least one hollow longitudinal body (2) having at least one open end (3).
2. Pièce raidie selon la revendication 1, dans laquelle la première structure (6) comprend au moins deux corps (2), lesdits corps étant juxtaposés et/ou empilés, le contact entre deux corps adjacents se faisant par leur paroi latérale. 2. Stiffened part according to claim 1, in which the first structure (6) comprises at least two bodies (2), said bodies being juxtaposed and/or stacked, the contact between two adjacent bodies taking place via their side wall.
3. Pièce raidie selon la revendication 2, dans laquelle la première structure (6) comporte une première rangée de corps juxtaposés et une deuxième rangée de corps juxtaposés, les première et deuxième rangées étant empilées avec un décalage entre les corps de la première rangée et les corps de la deuxième rangée. 3. Stiffened part according to claim 2, in which the first structure (6) comprises a first row of juxtaposed bodies and a second row of juxtaposed bodies, the first and second rows being stacked with an offset between the bodies of the first row and the bodies in the second row.
4. Pièce raidie selon la revendication 2 ou la revendication 3, dans laquelle la première structure (6) forme à elle seule la pièce raidie. 4. Stiffened part according to claim 2 or claim 3, wherein the first structure (6) alone forms the stiffened part.
5. Pièce raidie selon l'une quelconque des revendications 1 à 3, comprenant en outre une deuxième structure (7) en matériau composite thermodurci, distincte de la première structure (6), la première structure étant au moins en partie intégrée dans la deuxième structure et/ou juxtaposée sur une surface de la deuxième structure. 5. Stiffened part according to any one of claims 1 to 3, further comprising a second structure (7) of thermoset composite material, separate from the first structure (6), the first structure being at least partly integrated into the second structure and/or juxtaposed on a surface of the second structure.
6. Pièce raidie selon l'une quelconque des revendications 1 à 5, ladite pièce étant un réflecteur d'antenne de satellite. 6. stiffened part according to any one of claims 1 to 5, said part being a satellite antenna reflector.
7. Procédé de fabrication d'une pièce raidie selon l'une quelconque des revendications 1 à 6, la pièce raidie étant formée d'au moins deux éléments en matériau composite thermodurci dont au moins un corps (2) de la première structure et l'éventuelle deuxième structure, le procédé comprenant les étapes successives suivantes : - pour chaque corps (2) de la première structure, soit réalisation d'une préforme fibreuse du corps par drapage d'un tissu autour d'un mandrin et imprégnation de la préforme fibreuse avec une résine thermodurcissable, soit réalisation d'une préforme fibreuse préimprégnée par drapage d'un tissu préimprégné d'une résine thermodurcissable autour d'un mandrin, moyennant quoi on obtient un corps en matériau composite thermodurcissable non polymérisé supporté par un mandrin (1) ; 7. A method of manufacturing a stiffened part according to any one of claims 1 to 6, the stiffened part being formed of at least two elements of thermoset composite material including at least one body (2) of the first structure and the possible second structure, the method comprising the following successive steps: - for each body (2) of the first structure, either production of a fiber preform of the body by draping a fabric around a mandrel and impregnation of the fiber preform with a thermosetting resin, or production of a fiber preform preimpregnated by draping a fabric preimpregnated with a thermosetting resin around a mandrel, whereby a body of uncured thermosetting composite material is obtained supported by a mandrel (1);
- éventuelle polymérisation partielle ou complète d'au moins un corps en matériau composite thermodurcissable supporté par un mandrin ; - possible partial or complete polymerization of at least one body of thermosetting composite material supported by a mandrel;
- si la pièce raidie comporte une deuxième structure, fourniture de la deuxième structure, la deuxième structure étant en matériau composite thermodurcissable non polymérisé, partiellement polymérisé ou complètement polymérisé, ; - if the stiffened part comprises a second structure, provision of the second structure, the second structure being made of unpolymerized, partially polymerized or completely polymerized thermosetting composite material;
- s'il y a au moins un élément en matériau composite thermodurcissable complètement polymérisé, dépôt d'une couche d'adhésif thermodurcissable non polymérisé sur une zone de contact dudit élément avec un autre élément de la pièce ; - if there is at least one element made of completely polymerized thermosetting composite material, depositing a layer of unpolymerized thermosetting adhesive on a zone of contact of said element with another element of the part;
- assemblage des éléments formant la pièce, chaque élément étant juxtaposé avec, ou empilé sur, au moins un autre élément ; - assembly of the elements forming the part, each element being juxtaposed with, or stacked on, at least one other element;
- polymérisation complète de l'assemblage par traitement thermique ; - complete polymerization of the assembly by heat treatment;
- retrait du mandrin (1) de chaque corps complètement polymérisé. - removal of the mandrel (1) from each completely polymerized body.
8. Procédé selon la revendication 7, comprenant en outre, avant l'étape d'assemblage, un dépôt d'un film adhésif entre deux éléments non polymérisés et/ou partiellement polymérisés. 8. Method according to claim 7, further comprising, before the assembly step, depositing an adhesive film between two unpolymerized and/or partially polymerized elements.
9. Procédé selon la revendication 7 ou la revendication 8, dans lequel, parmi les éléments formant la pièce, il y a en outre au moins une nappe (9) ou un tissu (9) préimprégné de résine thermodurcissable ou imprégné par la suite de résine thermodurcissable, cette nappe ou ce tissu étant appliqué, au cours de l'étape d'assemblage, sur au moins un corps, de préférence sur plusieurs corps empilés et/ou juxtaposés, et/ou sur l'éventuelle deuxième structure. 9. Method according to claim 7 or claim 8, in which, among the elements forming the part, there is also at least one sheet (9) or a fabric (9) preimpregnated with thermosetting resin or subsequently impregnated with thermosetting resin, this ply or this fabric being applied, during the assembly step, to at least one body, preferably to several stacked and/or juxtaposed bodies, and/or to the optional second structure.
10. Procédé selon l'une quelconque des revendications 7 à 9, dans lequel, pour au moins un corps, le mandrin (1) est un regroupement d'au moins deux mandrins (10 ; 11 ; 12 ; 13 ; 14 ; 15) de plus petites sections, soit empilés, soit juxtaposés latéralement. 10. Method according to any one of claims 7 to 9, in which, for at least one body, the mandrel (1) is a combination of at least two mandrels (10; 11; 12; 13; 14; 15) smaller sections, either stacked or juxtaposed laterally.
11. Procédé selon l'une quelconque des revendications 7 à 10, dans lequel chaque mandrin est en élastomère souple. 11. Method according to any one of claims 7 to 10, in which each mandrel is made of flexible elastomer.
EP21758400.2A 2020-07-17 2021-07-16 Stiffened part formed from a thermoset composite material with a boxed structure and manufacturing method Pending EP4168243A1 (en)

Applications Claiming Priority (2)

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FR2007522A FR3112506B1 (en) 2020-07-17 2020-07-17 STIFFENED PART IN THERMODSET COMPOSITE MATERIAL WITH BOXED STRUCTURE AND METHOD OF MANUFACTURING
PCT/FR2021/051340 WO2022013513A1 (en) 2020-07-17 2021-07-16 Stiffened part formed from a thermoset composite material with a boxed structure and manufacturing method

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GB2122939B (en) * 1982-06-25 1986-01-08 British Aerospace Jointed composite articles
JP5763206B2 (en) * 2010-11-11 2015-08-12 スピリット アエロシステムズ，アイエヌシー． Method and system for interconnecting or mutually curing composite parts using a rigid / malleable SMP apparatus
US9365022B2 (en) * 2013-06-11 2016-06-14 Bell Helicopter Textron Inc. System and method of post-cure processing of composite core
GB2555657A (en) * 2016-11-08 2018-05-09 Oxford Space Systems Deployable mast structure

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FR3112506B1 (en) 2023-05-12
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US20230264440A1 (en) 2023-08-24

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