EP0504247A1 - A composite material - Google Patents

A composite material

Info

Publication number
EP0504247A1
EP0504247A1 EP91900894A EP91900894A EP0504247A1 EP 0504247 A1 EP0504247 A1 EP 0504247A1 EP 91900894 A EP91900894 A EP 91900894A EP 91900894 A EP91900894 A EP 91900894A EP 0504247 A1 EP0504247 A1 EP 0504247A1
Authority
EP
European Patent Office
Prior art keywords
composite material
fastener
layers
vacuum bag
leg
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.)
Withdrawn
Application number
EP91900894A
Other languages
German (de)
French (fr)
Inventor
Robert Samuel Wilson
Mark Anthony Braniff
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.)
Short Brothers PLC
Original Assignee
Short Brothers PLC
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 Short Brothers PLC filed Critical Short Brothers PLC
Publication of EP0504247A1 publication Critical patent/EP0504247A1/en
Withdrawn legal-status Critical Current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
    • B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
    • B29C65/56—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using mechanical means or mechanical connections, e.g. form-fits
    • B29C65/562—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using mechanical means or mechanical connections, e.g. form-fits using extra joining elements, i.e. which are not integral with the parts to be joined
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C43/00—Compression moulding, i.e. applying external pressure to flow the moulding material; Apparatus therefor
    • B29C43/32—Component parts, details or accessories; Auxiliary operations
    • 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
    • B29C53/00—Shaping by bending, folding, twisting, straightening or flattening; Apparatus therefor
    • B29C53/02—Bending or folding
    • B29C53/04—Bending or folding of plates or sheets
    • 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
    • B29C65/5064—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 of particular form, e.g. being C-shaped, T-shaped
    • B29C65/5071—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 of particular form, e.g. being C-shaped, T-shaped and being composed by one single element
    • 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
    • B29C65/5064—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 of particular form, e.g. being C-shaped, T-shaped
    • B29C65/5078—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 of particular form, e.g. being C-shaped, T-shaped and being composed by several elements
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • 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
    • B29C65/5064—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 of particular form, e.g. being C-shaped, T-shaped
    • B29C65/5085—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 of particular form, e.g. being C-shaped, T-shaped and comprising grooves, e.g. being E-shaped, H-shaped
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
    • B29C65/56—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using mechanical means or mechanical connections, e.g. form-fits
    • B29C65/562—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using mechanical means or mechanical connections, e.g. form-fits using extra joining elements, i.e. which are not integral with the parts to be joined
    • B29C65/564—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using mechanical means or mechanical connections, e.g. form-fits using extra joining elements, i.e. which are not integral with the parts to be joined hidden in the joint, e.g. dowels or Z-pins
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
    • B29C65/72—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor by combined operations or combined techniques, e.g. welding and stitching
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/01—General aspects dealing with the joint area or with the area to be joined
    • B29C66/05—Particular design of joint configurations
    • B29C66/10—Particular design of joint configurations particular design of the joint cross-sections
    • B29C66/11—Joint cross-sections comprising a single joint-segment, i.e. one of the parts to be joined comprising a single joint-segment in the joint cross-section
    • B29C66/112—Single lapped joints
    • 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
    • B29C66/13—Single flanged joints; Fin-type joints; Single hem joints; Edge joints; Interpenetrating fingered joints; Other specific particular designs of joint cross-sections not provided for in groups B29C66/11 - B29C66/12
    • B29C66/131—Single flanged joints, i.e. one of the parts to be joined being rigid and flanged in the joint area
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/40—General aspects of joining substantially flat articles, e.g. plates, sheets or web-like materials; Making flat seams in tubular or hollow articles; Joining single elements to substantially flat surfaces
    • B29C66/41—Joining substantially flat articles ; Making flat seams in tubular or hollow articles
    • B29C66/43—Joining a relatively small portion of the surface of said articles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/40—General aspects of joining substantially flat articles, e.g. plates, sheets or web-like materials; Making flat seams in tubular or hollow articles; Joining single elements to substantially flat surfaces
    • B29C66/41—Joining substantially flat articles ; Making flat seams in tubular or hollow articles
    • B29C66/43—Joining a relatively small portion of the surface of said articles
    • B29C66/434—Joining substantially flat articles for forming corner connections, fork connections or cross connections
    • B29C66/4342—Joining substantially flat articles for forming corner connections, e.g. for making V-shaped pieces
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/40—General aspects of joining substantially flat articles, e.g. plates, sheets or web-like materials; Making flat seams in tubular or hollow articles; Joining single elements to substantially flat surfaces
    • B29C66/41—Joining substantially flat articles ; Making flat seams in tubular or hollow articles
    • B29C66/43—Joining a relatively small portion of the surface of said articles
    • B29C66/434—Joining substantially flat articles for forming corner connections, fork connections or cross connections
    • B29C66/4344—Joining substantially flat articles for forming fork connections, e.g. for making Y-shaped pieces
    • B29C66/43441—Joining substantially flat articles for forming fork connections, e.g. for making Y-shaped pieces with two right angles, e.g. for making T-shaped pieces, H-shaped pieces
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/40—General aspects of joining substantially flat articles, e.g. plates, sheets or web-like materials; Making flat seams in tubular or hollow articles; Joining single elements to substantially flat surfaces
    • B29C66/47—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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/50—General aspects of joining tubular articles; General aspects of joining long products, i.e. bars or profiled elements; General aspects of joining single elements to tubular articles, hollow articles or bars; General aspects of joining several hollow-preforms to form hollow or tubular articles
    • B29C66/51—Joining tubular articles, profiled elements or bars; Joining single elements to tubular articles, hollow articles or bars; Joining several hollow-preforms to form hollow or tubular articles
    • B29C66/52—Joining tubular articles, bars or profiled elements
    • B29C66/524—Joining profiled elements
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/72—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined
    • B29C66/721—Fibre-reinforced materials
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/80—General aspects of machine operations or constructions and parts thereof
    • B29C66/81—General aspects of the pressing elements, i.e. the elements applying pressure on the parts to be joined in the area to be joined, e.g. the welding jaws or clamps
    • B29C66/814—General aspects of the pressing elements, i.e. the elements applying pressure on the parts to be joined in the area to be joined, e.g. the welding jaws or clamps characterised by the design of the pressing elements, e.g. of the welding jaws or clamps
    • B29C66/8145—General aspects of the pressing elements, i.e. the elements applying pressure on the parts to be joined in the area to be joined, e.g. the welding jaws or clamps characterised by the design of the pressing elements, e.g. of the welding jaws or clamps characterised by the constructional aspects of the pressing elements, e.g. of the welding jaws or clamps
    • B29C66/81455—General aspects of the pressing elements, i.e. the elements applying pressure on the parts to be joined in the area to be joined, e.g. the welding jaws or clamps characterised by the design of the pressing elements, e.g. of the welding jaws or clamps characterised by the constructional aspects of the pressing elements, e.g. of the welding jaws or clamps being a fluid inflatable bag or bladder, a diaphragm or a vacuum bag for applying isostatic pressure
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/80—General aspects of machine operations or constructions and parts thereof
    • B29C66/83—General aspects of machine operations or constructions and parts thereof characterised by the movement of the joining or pressing tools
    • B29C66/832—Reciprocating joining or pressing tools
    • B29C66/8322—Joining or pressing tools reciprocating along one axis
    • 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
    • B29C66/90—Measuring or controlling the joining process
    • B29C66/91—Measuring or controlling the joining process by measuring or controlling the temperature, the heat or the thermal flux
    • B29C66/914—Measuring or controlling the joining process by measuring or controlling the temperature, the heat or the thermal flux by controlling or regulating the temperature, the heat or the thermal flux
    • B29C66/9141—Measuring or controlling the joining process by measuring or controlling the temperature, the heat or the thermal flux by controlling or regulating the temperature, the heat or the thermal flux by controlling or regulating the temperature
    • B29C66/91411—Measuring or controlling the joining process by measuring or controlling the temperature, the heat or the thermal flux by controlling or regulating the temperature, the heat or the thermal flux by controlling or regulating the temperature of the parts to be joined, e.g. the joining process taking the temperature of the parts to be joined into account
    • 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
    • B29C66/90—Measuring or controlling the joining process
    • B29C66/91—Measuring or controlling the joining process by measuring or controlling the temperature, the heat or the thermal flux
    • B29C66/914—Measuring or controlling the joining process by measuring or controlling the temperature, the heat or the thermal flux by controlling or regulating the temperature, the heat or the thermal flux
    • B29C66/9141—Measuring or controlling the joining process by measuring or controlling the temperature, the heat or the thermal flux by controlling or regulating the temperature, the heat or the thermal flux by controlling or regulating the temperature
    • B29C66/91441—Measuring or controlling the joining process by measuring or controlling the temperature, the heat or the thermal flux by controlling or regulating the temperature, the heat or the thermal flux by controlling or regulating the temperature the temperature being non-constant over time
    • B29C66/91443—Measuring or controlling the joining process by measuring or controlling the temperature, the heat or the thermal flux by controlling or regulating the temperature, the heat or the thermal flux by controlling or regulating the temperature the temperature being non-constant over time following a temperature-time profile
    • 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
    • B29C66/90—Measuring or controlling the joining process
    • B29C66/91—Measuring or controlling the joining process by measuring or controlling the temperature, the heat or the thermal flux
    • B29C66/919—Measuring or controlling the joining process by measuring or controlling the temperature, the heat or the thermal flux characterised by specific temperature, heat or thermal flux values or ranges
    • 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
    • B29C66/90—Measuring or controlling the joining process
    • B29C66/91—Measuring or controlling the joining process by measuring or controlling the temperature, the heat or the thermal flux
    • B29C66/919—Measuring or controlling the joining process by measuring or controlling the temperature, the heat or the thermal flux characterised by specific temperature, heat or thermal flux values or ranges
    • B29C66/9192—Measuring or controlling the joining process by measuring or controlling the temperature, the heat or the thermal flux characterised by specific temperature, heat or thermal flux values or ranges in explicit relation to another variable, e.g. temperature diagrams
    • B29C66/91951—Measuring or controlling the joining process by measuring or controlling the temperature, the heat or the thermal flux characterised by specific temperature, heat or thermal flux values or ranges in explicit relation to another variable, e.g. temperature diagrams in explicit relation to time, e.g. temperature-time diagrams
    • 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
    • B29C70/06—Fibrous reinforcements only
    • B29C70/10—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres
    • B29C70/16—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length
    • B29C70/24—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in at least three directions forming a three dimensional structure
    • 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
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    • B29C70/34—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
    • B29C70/345—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation using matched moulds
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    • 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
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    • B29C70/543—Fixing the position or configuration of fibrous reinforcements before or during moulding
    • B—PERFORMING OPERATIONS; TRANSPORTING
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    • 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
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    • 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
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    • B29C65/5007—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like characterised by the structure of said adhesive tape, threads or the like
    • B29C65/5021—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like characterised by the structure of said adhesive tape, threads or the like being multi-layered
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    • B29C65/50—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like
    • B29C65/5007—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like characterised by the structure of said adhesive tape, threads or the like
    • B29C65/5028—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like characterised by the structure of said adhesive tape, threads or the like being textile in woven or non-woven form
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    • B29C66/71—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 composition of the plastics material of the parts to be joined
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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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    • B29C66/737—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
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    • 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
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    • B29C66/73—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset
    • B29C66/739—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset characterised by the material of the parts to be joined being a thermoplastic or a thermoset
    • B29C66/7392—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset characterised by the material of the parts to be joined being a thermoplastic or a thermoset characterised by the material of at least one of the parts being a thermoplastic
    • B—PERFORMING OPERATIONS; TRANSPORTING
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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
    • B29C66/739—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset characterised by the material of the parts to be joined being a thermoplastic or a thermoset
    • B29C66/7392—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset characterised by the material of the parts to be joined being a thermoplastic or a thermoset characterised by the material of at least one of the parts being a thermoplastic
    • B29C66/73921—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset characterised by the material of the parts to be joined being a thermoplastic or a thermoset characterised by the material of at least one of the parts being a thermoplastic characterised by the materials of both parts being thermoplastics
    • B—PERFORMING OPERATIONS; TRANSPORTING
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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
    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
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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
    • B29C66/739—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
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    • B29K2063/00—Use of EP, i.e. epoxy resins or derivatives thereof, as moulding material
    • B—PERFORMING OPERATIONS; TRANSPORTING
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    • B29K2079/00—Use of polymers having nitrogen, with or without oxygen or carbon only, in the main chain, not provided for in groups B29K2061/00 - B29K2077/00, as moulding material
    • B29K2079/08—PI, i.e. polyimides or derivatives thereof
    • B—PERFORMING OPERATIONS; TRANSPORTING
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    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
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    • B29K2277/00—Use of PA, i.e. polyamides, e.g. polyesteramides or derivatives thereof, as reinforcement
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    • B—PERFORMING OPERATIONS; TRANSPORTING
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    • B29K2307/00—Use of elements other than metals as reinforcement
    • B—PERFORMING OPERATIONS; TRANSPORTING
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    • B29K2307/00—Use of elements other than metals as reinforcement
    • B29K2307/02—Boron
    • B—PERFORMING OPERATIONS; TRANSPORTING
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    • B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
    • B29L2031/00—Other particular articles
    • B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
    • B29L2031/3076—Aircrafts
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
    • F16B15/00—Nails; Staples
    • F16B15/0015—Staples

Definitions

  • the present invention relates to a method of manufacturing a composite material, such as for example a composite material particularly suitable for forming the outer surface material of an aircraft.
  • •• material includes any suitable component or structure, such as for example a laminate joint, depending on the application of the invention.
  • a previously proposed composite material has been manufactured by embedding high strength fibres having a high modulus of elasticity within a homogenous matrix.
  • the fibres are made cf carbon, aramid or boron, and the matrix can be formed cf material such as an epoxy, bi ⁇ malemide or polyi ide resin.
  • the fibres are supplied in a uni-directional, woven cr fibrous mat format which is pre-impregnated with slightly cured resin to form an intermediate fabric material.
  • This intermediate fabric material is flexible and tacky, and the positions of the fibre filaments therein are net fixed. Layers of these intermediate fabric materials are assembled one upon the other in a mould, and then compressed and heated. The heating action accelerates the curing of the resin, and the combination of the heating and compression joins together the intermediate fabric materials to form the composite material.
  • a method of manufacturing a composite material comprising placing together face to face a plurality of layers of intermediate- fabric material, each layer comprising high strength fibres having a high modulus of elasticity in a tacky homogeneous resin matrix, fastening together said layers at spaced locations thereon, and then compressing and heating the layer assembly to cure the resin.
  • Crimp fastening is meant a process in which each leg of a fastener is forced through at least two overlapping layers by direct pressure when the fastener is either stationary or subject to mechanical rotation. When each leg of a fastener protrudes through the overlapping layers to a required distance it is either crimped or punched in a controlled manner to produce a clamping or fastening action.
  • Crimp fasteners may have any suitable number of legs, such as for example one, two or three legs as illustrated in Figure 8 of the drawings, or may be of a spiral or helical configuration as illustrated in Figure 9 of the drawings.
  • the fastener is made of any suitable material, such as for example metal or plastics material, capable of being crimped or punched to produce the required clamping or fastening action.
  • the fasteners* may be covered by additional layers of intermediate fabric material before the assembly is heated and compressed.
  • Figs, la, lb and lc are diagrammatic illustrations of three stages in.the manufacture of a composite material
  • Fig. 2 is a perspective view showing one stage in the preparation of the composite material
  • Fig. 3 is a sectional elevation of the composite material in a mould tool
  • Fig. 4 is a detailed sectional elevation of part of the composite material located in a mould tool
  • Fig. 5 is a perspective view showing one stage in the preparation of a further composite material
  • Figs. 6 and 7 are diagrammatic illustrations of two examples of crimp fasteners for use in the preparation of the composite material
  • Figs 8 and 9 are diagrammatic illustrations of further examples of crimp fasteners for use in the preparation of the composite material
  • Fig. ⁇ o is a diagram of an operational cycle of the invention.
  • Fig. 11 is a diagrammatic illustration of examples of skin stiffening configurations which are suitable for the crimp fastening method of the invention.
  • Fig. 12 is a diagrammatic illustration of examples of composite fasteners of the invention
  • Fig. 13 is a diagrammatic illustration of stages in the manufacture of a composite material using composite fasteners.
  • transversely spaced stacks 2 and 4 of intermediate fabric material are supplied on a release film 6. These stacks have been compacted or debulked under vacuum at room temperature. This compaction or debulking gives to each stack a degree of structural rigidity which aids assembly of the proposed composite material.
  • Each stack consists of a plurality of layers of the material placed together face to face.
  • Each layer of intermediate fabric material is formed by embedding high strength fibres having a high modulus of elasticity in a homogeneous matrix which may be an epoxy, bismalemide or a polyimide resin.
  • the fibres may be uni ⁇ directional, woven or in the form of a fibrous mat, and the fibres may be made of materials such as carbon, aramid or boron.
  • Each intermediate fabric material layer is supplied with the resin matrix slightly cured to ensure that the fabric layer is tacky and flexible, and at this stage the fibres are not in a fixed position in the matrix.
  • the stacks 2 and 4 are rectangular in shape.
  • the release film 6 is removed from the stacks 2 and 4, and a film of adhesive is applied to the lower surface of the side portion 8 of the stack 2, and the upper surface of the side portion 10 of the stack 4.
  • These side portions 8 and 10 are then placed in overlapping relationship as shown in Fig. lb.
  • Each side portion is in the form of a strip running parallel to one edge of the appropriate stack 2 or .
  • These side portions 8 and 10 are then crimp fastened together by a plurality of fasteners 12 which are spaced along the side portions 8 and 10.
  • further layers 14 and 16 of intermediate fabric material are placed over the side portions 8 and 10 to cover the fasteners 12.
  • the crimp fastened stacks 2 and 4 of intermediate fabric material are placed in a mould tool comprising a base plate 18 and a top mould plate 20.
  • a vacuum bag 22 is placed over the top mould plate 20, and an airtight seal is made between the vacuum bag 22 and the base plate 18 by means of a peripheral sealer tape 24.
  • FIG. 4 provides a more detailed illustration of part of the mould tool of Fig. 3, and for clarity corresponding components in Figs. 3 and 4 have been given the same reference numerals.
  • a release film 26 is located between
  • a release agent 28 is located below the stacks 2 and 4 to prevent these stacks from adhering to the mould base plate 18.
  • An edge breather 30 extends round the base plate 18 adjacent to the edge of the vacuum bag 22, and a surface breather 32 of plate form is located near the upper portion of the vacuum bag 22.. This surface breather 32 has an area slightly less than the area of the top of the vacuum bag 22. Referring to Fig. 3, the space inside the vacuum bag 22 is evacuated* by withdrawing air through a passage 34 at one edge of the vacuum bag 22.
  • the edge breather 30 and the surface breather 32 assist in ensuring that air is withdrawn from substantially the entire region covered by the vacuum bag 22, and that the vacuum bag 22 does not wrinkle or distort unduly during evacuation.
  • the space under ' the vacuum bag 22 is evacuated, the crimp fastened stacks 2 and 4 are compressed by bringing together the mould plates 18 and 20, and the mould tool and vacuum bag assembly is then heated in an autoclave to cure the crimp fastened stacks 2 and 4 while they remain under pressure to form the required composite material.
  • the mould tool and vacuum bag assembly is removed from the autoclave, the vacuum bag 22 is removed, the mould plates 18 and 20 are separated, and the cured composite material is removed from between the separated mould plates 18 and 20.
  • the invention also includes within its scope the above- mentioned method of manufacturing a composite material in which the top mould plate 20 is not used.
  • the required degree of compression is obtained between the vacuum bag 22 and the base plate 18.
  • the top mould plate is used (1) to produce a composite material having a tool finish on both major surfaces, (2) to dissipate the autoclave pressure through the fasteners 12 and the debulked stacks 2 and 4, and (3) to form the integral stiffening or structural element where applicable.
  • crimp fastener Any suitable form of crimp fastener may be used, and Figs. 6 to 9 illustrate suitable examples of crimp fasteners.
  • crimp fasteners can be separably attached to one another in a stack to facilitate loading into a crimping machine similar to a conventional industrial stapler.
  • Fig. 5 illustrates the various stages of fastening together two stacks of * intermediate fabric material.
  • one stack 36 is in the form of a planar sheet
  • the other stack 38 is in the form cf a C section stiffener or girder.
  • the debulked C section stack 38 is crimp fastened to the debulked planar stack 36 in order to assist in correctly locating the structure onto the base plate 18.
  • the method of the described and illustrated embodiment provides a composite structure which is self sealing, and does not require expensive post jigging or drilling of the cured structure.
  • the maximum cure pressure is in the range from 5.86xl0 5 to 6.89xl0 5 N/m 2 with a maximum cure temperature of 179 ⁇ 5°C maintained over a period of 120 + 5 minutes, a heat up rate of 0.5 to 2.5°C per minute and a maximum cool down rate of 2.5°C per minute.
  • cure pressure is meant the pressure inside the autoclave, and hence the external pressure exerted on the vacuum bag 22.
  • a full vacuum is applied to the interior of the mould tool and vacuum bag assembly. This equates to an external pressure of 1.013xl0 5 N/m 2 (14.7 psig) which is produced by the column of air acting vertically above the vacuum bag 22.
  • the minimum pressure allowable on a vacuum bagged part placed in the autoclave before commencing the cure cycle is 20"Hg (0.667xl0 5 N/m 2 ) . This vacuum serves to maintain the position of the bag, breather, etc. over the crimp fastened stacks 2 and 4.
  • the vacuum line connecting the bagged part and the vacuum pump which produces the 0.667xl0 5 N/m 2 minimum pressure is vented to the atmosphere outside the autoclave once the internal autoclave pressure reaches 1.38xl0 5 N/m 2 (20psig) .
  • the reason for this action is because once the autoclave pressure exceeds 1.013xl0 5 N/m*- (I4.7psig) there is no longer any advantage in applying a vacuum.
  • joints can be used for local reinforcement, for example, at the "end” of stiffening elements to:-
  • Crimp fastening may be employed to improve the through thickness structural strength of advanced composites (i.e. prevents delamination
  • the crimp fasteners of the embodiment illustrated in Figs. 1 to 11 are made of any suitable metal or metal alloy.
  • the layers of composite material may be fastened together by means of composite fasteners.
  • composite fastener is meant a fastener made of a plurality_ of layers of woven and uni-directional material.
  • Each layer may be made of a thermosetting or thermoplastics material, including a reinforcement made of Kevlar, carbon or boron.
  • These layers are placed together face to face to form a stack which is placed in a mould tool, and cured to a desired configuration.
  • Fig. 12 illustrates several different configurations of fastener
  • Fig. 13(a) illustrates the preparation and curing of a layer stack having a Z configuration.
  • the cured stack is then cut to form a plurality of Z configuration fasteners.
  • the spacing of the cuts in the layer stack will of course define the width of each fastener.
  • first and second L-shaped stacks of layered intermediate fabric material are placed back to back on a third generally planar stack of layered intermediate fabric material.
  • the stack combination is placed on a steel base plate.
  • This base plate constitutes the base of a mould tool as illustrated in Fig. 4 and described in the corresponding part of the description.
  • a series of holes are formed in the base parts of the two L-shaped stacks and the coaxial parts of the third stack by means of a punch.
  • the Z-shaped f steners illustrated in Fig. 13 (c) are inserted through their respective holes and rotated into their fastening position as illustrated in Fig. 13(e). .
  • all or part of the stacks may be lifted from the steel base plate.
  • the fasteners are inserted manually using a suitably shaped tweezer type tool.

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Abstract

On produit un matériau composite à partir de deux piles (2 et 4) mutuellement espacées d'un tissu intermédiaire. Chaque pile est formée d'une pluralité de couches rassemblées face à face. On produit chaque couche en insérant des fibres de haute résistance, avec un module d'élasticité élevé, dans une matrice résineuse. Les piles (2 et 4) sont enlevées d'une pellicule de libération (6) et une pellicule d'adhésif est appliquée sur la surface inférieure de la partie latérale (8) de la pile (2) et sur la surface supérieure de la partie latérale (10) de la pile (4). Ces parties latérales (8 et 10) sont placées de manière à se chevaucher, puis sont reliées par gaufrage l'une à l'autre par une pluralité d'éléments de fixation (12). Des couches supplémentaires (14 et 16) de tissu intermédiaire sont placées sur les parties latérales (8 et 10) afin de recouvrir les éléments de fixation (12). Les piles reliées par gaufrage (2 et 4) sont placées dans un outil de moulage composé d'une plaque de base (18) et d'une plaque supérieure de moulage (20). Un sac sous vide (22) est placé sur la plaque supérieure de moulage (20) et un fermeture étanche à l'air est établie entre le sac sous vide (22) et la plaque de base (18) au moyen d'une bande périphérique de scellement (24). Puis l'air contenu dans le sac sous vide (22) est évacué par un passage (34) ménagé sur un bord du sac sous vide (22). On comprime les piles (2 et 4) ainsi fixées en rapprochant les plaques (18 et 20), puis en chauffant en autoclave l'outil de moulage et l'ensemble de sac sous vide afin de durcir les piles (2 et 4) pendant qu'elles sont maintenues sous pression et de former le matériau composite voulu. Une fois l'opération de durcissement achevée, l'outil de moulage et l'ensemble de sac sous vide sont enlevés de l'autoclave, le sac sous vide (22) est enlevé, les plaques de moulage (18 et 20) sont séparées et le matériau composite durci est enlevé des plaques de moulage.A composite material is produced from two piles (2 and 4) spaced apart from an intermediate fabric. Each stack is formed of a plurality of layers gathered face to face. Each layer is produced by inserting fibers of high resistance, with a high modulus of elasticity, into a resinous matrix. The batteries (2 and 4) are removed from a release film (6) and an adhesive film is applied to the lower surface of the lateral part (8) of the battery (2) and to the upper surface of the side part (10) of the stack (4). These lateral parts (8 and 10) are placed so as to overlap, and are then connected by embossing to each other by a plurality of fastening elements (12). Additional layers (14 and 16) of intermediate fabric are placed on the side portions (8 and 10) to cover the fasteners (12). The embossed stacks (2 and 4) are placed in a molding tool composed of a base plate (18) and an upper molding plate (20). A vacuum bag (22) is placed on the upper molding plate (20) and an airtight closure is established between the vacuum bag (22) and the base plate (18) by means of a strip sealing device (24). Then the air contained in the vacuum bag (22) is evacuated through a passage (34) formed on an edge of the vacuum bag (22). The stacks (2 and 4) thus fixed are compressed by bringing the plates (18 and 20) together, then by autoclaving the molding tool and the vacuum bag assembly in order to harden the stacks (2 and 4) for that they are kept under pressure and form the desired composite material. Once the curing operation is completed, the molding tool and the vacuum bag assembly are removed from the autoclave, the vacuum bag (22) is removed, the molding plates (18 and 20) are separated and the cured composite material is removed from the mold plates.

Description

A COMPOSITE MATERIAL
The present invention relates to a method of manufacturing a composite material, such as for example a composite material particularly suitable for forming the outer surface material of an aircraft.
The term ••material" includes any suitable component or structure, such as for example a laminate joint, depending on the application of the invention.
A previously proposed composite material has been manufactured by embedding high strength fibres having a high modulus of elasticity within a homogenous matrix. In one example of such a material, the fibres are made cf carbon, aramid or boron, and the matrix can be formed cf material such as an epoxy, biεmalemide or polyi ide resin.
The fibres are supplied in a uni-directional, woven cr fibrous mat format which is pre-impregnated with slightly cured resin to form an intermediate fabric material. This intermediate fabric material is flexible and tacky, and the positions of the fibre filaments therein are net fixed. Layers of these intermediate fabric materials are assembled one upon the other in a mould, and then compressed and heated. The heating action accelerates the curing of the resin, and the combination of the heating and compression joins together the intermediate fabric materials to form the composite material.
It is an aim of the invention to provide an improved method of manufacturing a composite material.
According to the present invention there is provided a method of manufacturing a composite material comprising placing together face to face a plurality of layers of intermediate- fabric material, each layer comprising high strength fibres having a high modulus of elasticity in a tacky homogeneous resin matrix, fastening together said layers at spaced locations thereon, and then compressing and heating the layer assembly to cure the resin.
One form of fastening together said layers is by the technique of crimp fastening. In the specification, by "crimp fastening" is meant a process in which each leg of a fastener is forced through at least two overlapping layers by direct pressure when the fastener is either stationary or subject to mechanical rotation. When each leg of a fastener protrudes through the overlapping layers to a required distance it is either crimped or punched in a controlled manner to produce a clamping or fastening action. Crimp fasteners may have any suitable number of legs, such as for example one, two or three legs as illustrated in Figure 8 of the drawings, or may be of a spiral or helical configuration as illustrated in Figure 9 of the drawings. The fastener is made of any suitable material, such as for example metal or plastics material, capable of being crimped or punched to produce the required clamping or fastening action.
If desired, the fasteners* may be covered by additional layers of intermediate fabric material before the assembly is heated and compressed.
Embodiments of the invention will now be described by way of example with reference to the accompanying drawings in which:-
Figs, la, lb and lc are diagrammatic illustrations of three stages in.the manufacture of a composite material;
Fig. 2 is a perspective view showing one stage in the preparation of the composite material;
Fig. 3 is a sectional elevation of the composite material in a mould tool;
Fig. 4 is a detailed sectional elevation of part of the composite material located in a mould tool;
Fig. 5 is a perspective view showing one stage in the preparation of a further composite material;
Figs. 6 and 7 are diagrammatic illustrations of two examples of crimp fasteners for use in the preparation of the composite material;
Figs 8 and 9 are diagrammatic illustrations of further examples of crimp fasteners for use in the preparation of the composite material;
Fig. ιo is a diagram of an operational cycle of the invention;
Fig. 11 is a diagrammatic illustration of examples of skin stiffening configurations which are suitable for the crimp fastening method of the invention;
Fig. 12 is a diagrammatic illustration of examples of composite fasteners of the invention, ' and Fig. 13 is a diagrammatic illustration of stages in the manufacture of a composite material using composite fasteners.
Referring to the drawings, and particularly to Fig. 1, in
one embodiment transversely spaced stacks 2 and 4 of intermediate fabric material are supplied on a release film 6. These stacks have been compacted or debulked under vacuum at room temperature. This compaction or debulking gives to each stack a degree of structural rigidity which aids assembly of the proposed composite material. Each stack consists of a plurality of layers of the material placed together face to face. Each layer of intermediate fabric material is formed by embedding high strength fibres having a high modulus of elasticity in a homogeneous matrix which may be an epoxy, bismalemide or a polyimide resin. The fibres may be uni¬ directional, woven or in the form of a fibrous mat, and the fibres may be made of materials such as carbon, aramid or boron. Each intermediate fabric material layer is supplied with the resin matrix slightly cured to ensure that the fabric layer is tacky and flexible, and at this stage the fibres are not in a fixed position in the matrix. The stacks 2 and 4 are rectangular in shape.
The release film 6 is removed from the stacks 2 and 4, and a film of adhesive is applied to the lower surface of the side portion 8 of the stack 2, and the upper surface of the side portion 10 of the stack 4. These side portions 8 and 10 are then placed in overlapping relationship as shown in Fig. lb. Each side portion is in the form of a strip running parallel to one edge of the appropriate stack 2 or . • These side portions 8 and 10 are then crimp fastened together by a plurality of fasteners 12 which are spaced along the side portions 8 and 10. As shown in Fig. lc, further layers 14 and 16 of intermediate fabric material are placed over the side portions 8 and 10 to cover the fasteners 12.
Referring to Fig. 3, the crimp fastened stacks 2 and 4 of intermediate fabric material are placed in a mould tool comprising a base plate 18 and a top mould plate 20. A vacuum bag 22 is placed over the top mould plate 20, and an airtight seal is made between the vacuum bag 22 and the base plate 18 by means of a peripheral sealer tape 24.
Fig. 4 provides a more detailed illustration of part of the mould tool of Fig. 3, and for clarity corresponding components in Figs. 3 and 4 have been given the same reference numerals. A release film 26 is located between
the crimp fastened stacks 2 and 4 and the top mould plate 20 to prevent the tacky upper surface of the stacks adhering to the plate 20. Similarly, a release agent 28 is located below the stacks 2 and 4 to prevent these stacks from adhering to the mould base plate 18. An edge breather 30 extends round the base plate 18 adjacent to the edge of the vacuum bag 22, and a surface breather 32 of plate form is located near the upper portion of the vacuum bag 22.. This surface breather 32 has an area slightly less than the area of the top of the vacuum bag 22. Referring to Fig. 3, the space inside the vacuum bag 22 is evacuated* by withdrawing air through a passage 34 at one edge of the vacuum bag 22. The edge breather 30 and the surface breather 32 assist in ensuring that air is withdrawn from substantially the entire region covered by the vacuum bag 22, and that the vacuum bag 22 does not wrinkle or distort unduly during evacuation. In operation, the space under' the vacuum bag 22 is evacuated, the crimp fastened stacks 2 and 4 are compressed by bringing together the mould plates 18 and 20, and the mould tool and vacuum bag assembly is then heated in an autoclave to cure the crimp fastened stacks 2 and 4 while they remain under pressure to form the required composite material. After the curing operation has been completed, the mould tool and vacuum bag assembly is removed from the autoclave, the vacuum bag 22 is removed, the mould plates 18 and 20 are separated, and the cured composite material is removed from between the separated mould plates 18 and 20.
The invention also includes within its scope the above- mentioned method of manufacturing a composite material in which the top mould plate 20 is not used. In this alternative method the required degree of compression is obtained between the vacuum bag 22 and the base plate 18. The top mould plate is used (1) to produce a composite material having a tool finish on both major surfaces, (2) to dissipate the autoclave pressure through the fasteners 12 and the debulked stacks 2 and 4, and (3) to form the integral stiffening or structural element where applicable.
Any suitable form of crimp fastener may be used, and Figs. 6 to 9 illustrate suitable examples of crimp fasteners.
These crimp fasteners can be separably attached to one another in a stack to facilitate loading into a crimping machine similar to a conventional industrial stapler.
Fig. 5 illustrates the various stages of fastening together two stacks of* intermediate fabric material. In the example of -Fig. 5 however one stack 36 is in the form of a planar sheet, and the other stack 38 is in the form cf a C section stiffener or girder. The debulked C section stack 38 is crimp fastened to the debulked planar stack 36 in order to assist in correctly locating the structure onto the base plate 18.
The method of the described and illustrated embodiment provides a composite structure which is self sealing, and does not require expensive post jigging or drilling of the cured structure.
In a typical cure cycle of a composite material prepared by the method of the invention the maximum cure pressure is in the range from 5.86xl05 to 6.89xl05N/m2 with a maximum cure temperature of 179 ± 5°C maintained over a period of 120 + 5 minutes, a heat up rate of 0.5 to 2.5°C per minute and a maximum cool down rate of 2.5°C per minute. By "cure pressure" is meant the pressure inside the autoclave, and hence the external pressure exerted on the vacuum bag 22.
A full vacuum is applied to the interior of the mould tool and vacuum bag assembly. This equates to an external pressure of 1.013xl05N/m2 (14.7 psig) which is produced by the column of air acting vertically above the vacuum bag 22. The minimum pressure allowable on a vacuum bagged part placed in the autoclave before commencing the cure cycle is 20"Hg (0.667xl05N/m2 ) . This vacuum serves to maintain the position of the bag, breather, etc. over the crimp fastened stacks 2 and 4.
The vacuum line connecting the bagged part and the vacuum pump which produces the 0.667xl05N/m2 minimum pressure is vented to the atmosphere outside the autoclave once the internal autoclave pressure reaches 1.38xl05N/m2 (20psig) . The reason for this action is because once the autoclave pressure exceeds 1.013xl05N/m*- (I4.7psig) there is no longer any advantage in applying a vacuum.
The statement "maintain pressure under vacuum bag of 0 to .345xl05N/m2" refers to back pressure. Pressure may be generated under the vacuum bag by volatiles emitted by the curing prepreg and by small leaks in the vacuum bag allowing autoclave pressure through to the vent line. This tolerance of 0 to .345xl05N/m2 must not be exceeded since greater back pressure produces inferior components.
The described and illustrated embodiment of the invention possesses the following advantageous features:-
(a) (i) Improved impact resistance, tensile, peel, shear strength and improved resistance to crack propagation.
(ii) The structural elements of these fasteners (staple flanges) can be placed to align more closely with the applied loads than the elements of standard mechanical fasteners.
(b) Overcomes the main problems associated with standard mechanical joints, i.e.
(i) Any increase in laminate thickness normally required for mechanical fastening is reduced to an absolute minimum (because any damage to the laminate is minimal and to a degree is self repairing) .
(ii) Typical problems associated with mechanical fastening are avoided, i.e. problems associated with drilling, jigging, counter sinking, riveting, etc.
(iii) 'The joints are self sealing and are therefore ideal for use against the environment and for containing fuel (in a wet wing) .
(iv) The joints are more weight efficient than other mechanical fastened joints.
(v) The joints are aerodynamically smooth on the air wet surfaces and therefore any filling/feathering/smoothing countersinking operations are not required.
(c) The joints can be used for local reinforcement, for example, at the "end" of stiffening elements to:-
(i) Act as anti-peel fasteners (used in a similar role for aluminium bonded stiffeners) .
(ii) Accurately secure* the structural elements in position prior to and during the cure operation.
(d) The fastening of the mechanical elements is more labour efficient than other mechanical fastening techniques because it is completed in one efficient automated operation.
(e) Any complications usually involved with fasteners in a fuel cell environment, e.g. the risk of arc plasma blow by is avoided because the fasteners can be encapsulated into the structure.
(f) Can be located in areas where extra securement is required and where fasteners would not normally be employed, e.g. blade, stiffener webs.
(g) Crimp fastening may be employed to improve the through thickness structural strength of advanced composites (i.e. prevents delamination
* of. the plies) .
Recommended cure cycles for the method of the invention are as follows:-
(a) Simple components: Apply 700 kN/m2 pressure.
Heat to 175°C at 1 to 20°C per minute.
Cure for 1' hour at 175°C.
Cool to below 60°C before pressure removal and components ejection.
(b) Optimum cycle:
Heat under vacuum only to 120°C at 1 to 20°C per minute.
When component reaches 120°C apply 700 kN/m2 pressure and vent component to atmosphere.
Continue heating to 175°C.
Cure for 1 hour at 175°C and cool to 60°C before pressure removal and component ejection.
(c) Thick components:
To avoid exotherm on thick components (>10mm) it is advisable to incorporate a dwell. of 2 to 3 hours at 130°C to 135°C in the cure cycle mentioned in (b) above.
The crimp fasteners of the embodiment illustrated in Figs. 1 to 11 are made of any suitable metal or metal alloy.
Referring to Figs. 12 and 13, in a second embodiment, the layers of composite material may be fastened together by means of composite fasteners. In the specification, by "composite fastener" is meant a fastener made of a plurality_ of layers of woven and uni-directional material. Each layer may be made of a thermosetting or thermoplastics material, including a reinforcement made of Kevlar, carbon or boron. These layers are placed together face to face to form a stack which is placed in a mould tool, and cured to a desired configuration. Fig. 12 illustrates several different configurations of fastener, and Fig. 13(a) illustrates the preparation and curing of a layer stack having a Z configuration.
Referring to Fig. 13(b) and (c) the cured stack is then cut to form a plurality of Z configuration fasteners. The spacing of the cuts in the layer stack will of course define the width of each fastener.
As shown in Fig. 13(d), first and second L-shaped stacks of layered intermediate fabric material are placed back to back on a third generally planar stack of layered intermediate fabric material. The stack combination is placed on a steel base plate. This base plate constitutes the base of a mould tool as illustrated in Fig. 4 and described in the corresponding part of the description. A series of holes are formed in the base parts of the two L-shaped stacks and the coaxial parts of the third stack by means of a punch. The Z-shaped f steners illustrated in Fig. 13 (c) are inserted through their respective holes and rotated into their fastening position as illustrated in Fig. 13(e). . In order to assist the insertion of the fasteners into the stacks, all or part of the stacks may be lifted from the steel base plate. The fasteners are inserted manually using a suitably shaped tweezer type tool.
The three stacks and the inserted composite fasteners are then compressed and heated as previously described in the specification.

Claims

CLAIMS :
1. A method of manufacturing a composite material comprising placing together face to face a plurality of layers of intermediate fabric material, each layer comprising high strength fibres having a high modulus of elasticity in a tacky homogeneous resin matrix, fastening together said layers at spaced locations thereon, and then compressing and heating the layer assembly to cure the resin.
2. A method according to claim 1, characterised i that the layers are fastened together by means of a plurality of fasteners (12) located at said spaced locations, each fastener having at least one leg.
3. A method as claimed in claim 2, characterised in that each leg of a fastener is forced through at least two overlapping layers by direct pressure exerted on the fastener.
4. A method according to claim 3, characterised in that the fastener is subjected to mechanical rotation during the leg forcing operation.
5. A method according to claim 3 or 4, characterised in that each fastener leg is deformed in a controlled manner when it protrudes through the overlapping layers to a required distance so a to provide said fastening action.
6. A method according to claim 5, characterised in that each fastener leg is deformed by crimping.
7. A method according to claim 5, characterised in that each fastener leg is deformed by punching.
8. A method according to any one of claims 2 to 4, characterised in that the fasteners are covered by at least one additional layer (14, 16) of intermediate fabric material before the layer assembly is compressed and heated.
9. A method according to any one of claims l to 4 further including applying a first film of adhesive to the lower surface of the side portion of a first stack (2) of layers of intermediate fabric material, and a second film of adhesive to the upper surface of the side portion of a second stack (4) of layers of intermediate fabric material, placing said side portions in overlapping relationship, and fastening together said overlapping side portions at spaced locations thereon.
10. A method according to claim 9, characterised in that said stacks (2,4) are located in transversely spaced relationship on a release film (6) which is removed before the adhesive is applied.
11. A method according to any one of claims 1 to 4, characterised in that the layer assembly is compressed and heated under a vacuum.
12. A method according to claim 1, characterised in that holes are made through the assembled layers at said spaced locations, a Z shaped fastener is inserted in each hole, and the fastener is then rotated into its fastening position.
13. A composite material manufactured by the method of claim 2, characterised in that at least one fastener (12) is made of metal and includes at least one leg adapted to pass through at least two overlapping layers.
14. A composite material manufactured by the method of claim 12, characterised in that each fastener is made of a plurality of layers of woven and uni-directional material.
15. A composite material according to claim 14, characterised in that each layer is made of a reinforced thermosetting material.
16 A composite material according to claim 14, characterised in that each layer is made of a reinforced thermoplastics material.
17. A method of manufacturing a composite material substantially as herein described with reference to the accompanying drawings.
18. Apparatus for manufacturing a composite material substantially as herein described and shown in the accompanying drawings.
19. A composite material substantially as herein described and shown in the accompanying drawings.
- 17 -
completed, the mould tool and vacuum bag assembly is removed from the autoclave, the vacuum bag (22) is removed, the mould plates (18) and (20) are separated, and the cured composite material is removed.
EP91900894A 1989-12-07 1990-12-06 A composite material Withdrawn EP0504247A1 (en)

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GB8927734 1989-12-07
GB898927734A GB8927734D0 (en) 1989-12-07 1989-12-07 A composite material

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GB9026576D0 (en) 1991-01-23
AU6907991A (en) 1991-07-18
CA2070830A1 (en) 1991-06-08
IL96596A0 (en) 1991-09-16
JPH05501994A (en) 1993-04-15
GB2238977A (en) 1991-06-19
WO1991008892A1 (en) 1991-06-27
FI922471A0 (en) 1992-05-29
GB8927734D0 (en) 1990-02-07
BR9007901A (en) 1992-09-22
GB2238977B (en) 1994-01-05
FI922471A (en) 1992-05-29

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