NL1018120C2 - Method for manufacturing a molded laminate. - Google Patents
Method for manufacturing a molded laminate. Download PDFInfo
- Publication number
- NL1018120C2 NL1018120C2 NL1018120A NL1018120A NL1018120C2 NL 1018120 C2 NL1018120 C2 NL 1018120C2 NL 1018120 A NL1018120 A NL 1018120A NL 1018120 A NL1018120 A NL 1018120A NL 1018120 C2 NL1018120 C2 NL 1018120C2
- Authority
- NL
- Netherlands
- Prior art keywords
- laminate
- laminates
- heating
- molded portion
- deforming
- Prior art date
Links
- 238000004519 manufacturing process Methods 0.000 title claims abstract description 12
- 238000000034 method Methods 0.000 title claims description 34
- 229910052751 metal Inorganic materials 0.000 claims abstract description 22
- 239000002184 metal Substances 0.000 claims abstract description 22
- 239000004033 plastic Substances 0.000 claims abstract description 17
- 229920003023 plastic Polymers 0.000 claims abstract description 17
- 238000010438 heat treatment Methods 0.000 claims abstract description 14
- 238000001816 cooling Methods 0.000 claims abstract description 10
- 239000003292 glue Substances 0.000 claims description 4
- 239000004848 polyfunctional curative Substances 0.000 claims 1
- 239000010410 layer Substances 0.000 description 46
- 239000000463 material Substances 0.000 description 5
- 230000003014 reinforcing effect Effects 0.000 description 5
- 239000000853 adhesive Substances 0.000 description 4
- 230000001070 adhesive effect Effects 0.000 description 4
- 229920001187 thermosetting polymer Polymers 0.000 description 4
- 229910000881 Cu alloy Inorganic materials 0.000 description 3
- 239000012790 adhesive layer Substances 0.000 description 3
- -1 aluminum-manganese Chemical compound 0.000 description 3
- 238000010276 construction Methods 0.000 description 3
- 239000003365 glass fiber Substances 0.000 description 3
- 230000002787 reinforcement Effects 0.000 description 3
- 229920001169 thermoplastic Polymers 0.000 description 3
- 229910000861 Mg alloy Inorganic materials 0.000 description 2
- 239000004696 Poly ether ether ketone Substances 0.000 description 2
- 229910000676 Si alloy Inorganic materials 0.000 description 2
- UCKMPCXJQFINFW-UHFFFAOYSA-N Sulphide Chemical compound [S-2] UCKMPCXJQFINFW-UHFFFAOYSA-N 0.000 description 2
- 229910001297 Zn alloy Inorganic materials 0.000 description 2
- WPPDFTBPZNZZRP-UHFFFAOYSA-N aluminum copper Chemical compound [Al].[Cu] WPPDFTBPZNZZRP-UHFFFAOYSA-N 0.000 description 2
- FJMNNXLGOUYVHO-UHFFFAOYSA-N aluminum zinc Chemical compound [Al].[Zn] FJMNNXLGOUYVHO-UHFFFAOYSA-N 0.000 description 2
- 230000007423 decrease Effects 0.000 description 2
- 230000004313 glare Effects 0.000 description 2
- 239000011521 glass Substances 0.000 description 2
- 150000002739 metals Chemical class 0.000 description 2
- 229920001643 poly(ether ketone) Polymers 0.000 description 2
- 229920001652 poly(etherketoneketone) Polymers 0.000 description 2
- 229920002492 poly(sulfone) Polymers 0.000 description 2
- 229920001230 polyarylate Polymers 0.000 description 2
- 229920006393 polyether sulfone Polymers 0.000 description 2
- 229920002530 polyetherether ketone Polymers 0.000 description 2
- 229920001601 polyetherimide Polymers 0.000 description 2
- 238000003825 pressing Methods 0.000 description 2
- 239000004416 thermosoftening plastic Substances 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 229910000851 Alloy steel Inorganic materials 0.000 description 1
- 241000531908 Aramides Species 0.000 description 1
- 229910000914 Mn alloy Inorganic materials 0.000 description 1
- 229910001069 Ti alloy Inorganic materials 0.000 description 1
- 238000004026 adhesive bonding Methods 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 150000004645 aluminates Chemical class 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- PNEYBMLMFCGWSK-UHFFFAOYSA-N aluminium oxide Inorganic materials [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 0.000 description 1
- SNAAJJQQZSMGQD-UHFFFAOYSA-N aluminum magnesium Chemical compound [Mg].[Al] SNAAJJQQZSMGQD-UHFFFAOYSA-N 0.000 description 1
- 229920006231 aramid fiber Polymers 0.000 description 1
- 229920003235 aromatic polyamide Polymers 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 239000007795 chemical reaction product Substances 0.000 description 1
- 230000001427 coherent effect Effects 0.000 description 1
- 229910052593 corundum Inorganic materials 0.000 description 1
- 230000032798 delamination Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000003822 epoxy resin Substances 0.000 description 1
- 230000003628 erosive effect Effects 0.000 description 1
- 150000002170 ethers Chemical class 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 239000002657 fibrous material Substances 0.000 description 1
- 239000000945 filler Substances 0.000 description 1
- LNEPOXFFQSENCJ-UHFFFAOYSA-N haloperidol Chemical compound C1CC(O)(C=2C=CC(Cl)=CC=2)CCN1CCCC(=O)C1=CC=C(F)C=C1 LNEPOXFFQSENCJ-UHFFFAOYSA-N 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 230000035515 penetration Effects 0.000 description 1
- 230000002085 persistent effect Effects 0.000 description 1
- 150000002989 phenols Chemical class 0.000 description 1
- 229920000647 polyepoxide Polymers 0.000 description 1
- 229920001470 polyketone Polymers 0.000 description 1
- 239000000047 product Substances 0.000 description 1
- 229920005989 resin Polymers 0.000 description 1
- 239000011347 resin Substances 0.000 description 1
- 229920003002 synthetic resin Polymers 0.000 description 1
- 239000000057 synthetic resin Substances 0.000 description 1
- MHSKRLJMQQNJNC-UHFFFAOYSA-N terephthalamide Chemical compound NC(=O)C1=CC=C(C(N)=O)C=C1 MHSKRLJMQQNJNC-UHFFFAOYSA-N 0.000 description 1
- 229920006305 unsaturated polyester Polymers 0.000 description 1
- 229920001567 vinyl ester resin Polymers 0.000 description 1
- 125000000391 vinyl group Chemical group [H]C([*])=C([H])[H] 0.000 description 1
- 229910001845 yogo sapphire Inorganic materials 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B7/00—Layered products characterised by the relation between layers; Layered products characterised by the relative orientation of features between layers, or by the relative values of a measurable parameter between layers, i.e. products comprising layers having different physical, chemical or physicochemical properties; Layered products characterised by the interconnection of layers
- B32B7/04—Interconnection of 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
- 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
- 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
- B29C66/40—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
- B29C66/70—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
- B29C66/723—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 being multi-layered
-
- 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
- B29C66/723—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 being multi-layered
- B29C66/7232—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 being multi-layered comprising a non-plastics layer
- B29C66/72321—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 being multi-layered comprising a non-plastics layer consisting of metals or their alloys
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- 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
- B29C70/08—Fibrous reinforcements only comprising combinations of different forms of fibrous reinforcements incorporated in matrix material, forming one or more layers, and with or without non-reinforced layers
- B29C70/088—Fibrous reinforcements only comprising combinations of different forms of fibrous reinforcements incorporated in matrix material, forming one or more layers, and with or without non-reinforced layers and with one or more layers of non-plastics material or non-specified material, e.g. supports
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B15/00—Layered products comprising a layer of metal
- B32B15/04—Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different material
- B32B15/08—Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different material of synthetic resin
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B15/00—Layered products comprising a layer of metal
- B32B15/04—Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different material
- B32B15/08—Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different material of synthetic resin
- B32B15/092—Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different material of synthetic resin comprising epoxy resins
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B15/00—Layered products comprising a layer of metal
- B32B15/20—Layered products comprising a layer of metal comprising aluminium or copper
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B27/00—Layered products comprising a layer of synthetic resin
- B32B27/36—Layered products comprising a layer of synthetic resin comprising polyesters
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B27/00—Layered products comprising a layer of synthetic resin
- B32B27/38—Layered products comprising a layer of synthetic resin comprising epoxy resins
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
- B32B37/06—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the heating method
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B43/00—Operations specially adapted for layered products and not otherwise provided for, e.g. repairing; Apparatus therefor
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B7/00—Layered products characterised by the relation between layers; Layered products characterised by the relative orientation of features between layers, or by the relative values of a measurable parameter between layers, i.e. products comprising layers having different physical, chemical or physicochemical properties; Layered products characterised by the interconnection of layers
- B32B7/04—Interconnection of layers
- B32B7/12—Interconnection of layers using interposed adhesives or interposed materials with bonding properties
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
-
- 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
- B29C66/70—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
- B29C66/71—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
-
- 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
- B29C66/7392—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
- 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
-
- 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
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2009/00—Layered products
- B29L2009/003—Layered products comprising a metal layer
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2250/00—Layers arrangement
- B32B2250/05—5 or more layers
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2311/00—Metals, their alloys or their compounds
- B32B2311/24—Aluminium
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2363/00—Epoxy resins
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2367/00—Polyesters, e.g. PET, i.e. polyethylene terephthalate
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2398/00—Unspecified macromolecular compounds
- B32B2398/10—Thermosetting resins
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C2001/0054—Fuselage structures substantially made from particular materials
- B64C2001/0072—Fuselage structures substantially made from particular materials from composite materials
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Abstract
Description
Werkwijze voor het vervaardigen van een gevormd laminaat.Method for manufacturing a molded laminate.
De uitvinding betreft het vervaardigen van gelamineerde delen die bestaan uit afwisselende lagen uit een metaal en lagen uit een kunststof. De kunststoflagen kunnen 5 een hechtmiddel bevatten, en kunnen zijn versterkt met vezelmateriaal. Dergelijke gelamineerde delen vinden bijvoorbeeld toepassing in de luchtvaart- en ruimtevaartindustrie. Als voorbeelden worden genoemd het materiaal Glare d) (glass reinforced) en het materiaal ARALL ® (aramide aluminate laminate). Zij bezitten een relatief laag gewicht, gepaard aan een vrij hoge sterkte en stijfheid. Deze 10 eigenschappen hangen samen met de stijve verbindingen tussen de metaallagen, die verkregen worden door de hechting via de kunststoflagen.The invention relates to the production of laminated parts consisting of alternating layers of a metal and layers of a plastic. The plastic layers may contain an adhesive, and may be reinforced with fiber material. Such laminated parts find application, for example, in the aerospace industry. Examples are the material Glare d) (glass reinforced) and the material ARALL ® (aramide aluminate laminate). They have a relatively low weight, coupled with a relatively high strength and stiffness. These properties are related to the rigid connections between the metal layers that are obtained by the adhesion via the plastic layers.
Uit WO-A-9853989 is een werkwijze bekend voor het vervaardigen van dergelijke gelamineerde delen. De metalen platen met daartussen een lijmlaag, al dan niet voorzien van een versterking, worden geplaatst in een mal, waardoor een bepaalde 15 gewenste vorm wordt verkregen. Het geheel wordt vervolgens blootgesteld aan een verhoogde temperatuur en druk voor het tot stand brengen van de lijmverbinding. Na afkoelen van de lagen is een samenhangend, gevormd deel verkregen met de wenste mechanische eigenschappen betreffende stijfheid, sterkte en dergelijke.From WO-A-9853989 a method is known for manufacturing such laminated parts. The metal plates with a layer of glue between them, whether or not provided with a reinforcement, are placed in a mold, whereby a certain desired shape is obtained. The whole is then exposed to an elevated temperature and pressure for establishing the glue connection. After cooling of the layers, a coherent, shaped part has been obtained with the desired mechanical properties regarding stiffness, strength and the like.
Op dezelfde wijze kunnen verbindingen tot stand gebracht worden in dergelijke 20 gelamineerde delen. Daartoe kunnen een of meerdere metaallagen secties bezitten die elkaar overlappen. Bij een deel ter vorming van de huid van een vliegtuig bijvoorbeeld kan een sectie van een bepaalde buitenste metaallaagstuk zijn doorgezet, zodanig dat dit onder de aangrenzende sectie van een ander buitenste metaallaagstuk komt te liggen. De secties kunnen vervolgens op de hierboven beschreven wijze aan elkaar 25 worden bevestigd.In the same way, connections can be made in such laminated parts. To this end, one or more metal layers may have sections that overlap each other. In a part for forming the skin of an aircraft, for example, a section of a certain outer metal layer piece can be continued, such that it comes to lie below the adjacent section of another outer metal layer piece. The sections can then be attached to each other in the manner described above.
Het doorgezette gebied vormt een verstoring van het oppervlak van het gevormde deel. Bij toepassing in een vliegtuigconstructie moet dat oppervlak inwendig zijn, omdat anders het aërodynamisch gevormde, uitwendige oppervlak verstoord zou worden.The persistent area forms a disturbance of the surface of the formed part. When used in an aircraft construction, that surface must be internal, because otherwise the aerodynamically formed external surface would be disturbed.
30 In bepaalde gevallen kan het wenselijk zijn om het gevormde deel al of niet plaatselijk te versterken. Daartoe moeten extra lagen op het reeds gevormde deel worden bevestigd. Bij de doorgezette gebieden doet zich dan een probleem voor. De op het reeds gevormde deel aan te brengen lagen sluiten dan niet goed aan, omdat die 1018120 2 lagen een vlakke vorm bezitten. In de praktijk wordt dat opgelost door opvullagen toe te passen die het door de doorzetting veroorzaakte hoogteverschil moeten compenseren.In certain cases, it may be desirable to reinforce the formed portion locally or not. To this end, additional layers must be attached to the already formed part. A problem then occurs in the persevered areas. The layers to be applied to the already formed part then do not fit well, because those 1018120 2 layers have a flat shape. In practice, this is solved by applying filler layers to compensate for the height difference caused by the perseverance.
Een dergelijke oplossing heeft echter nadelen. Allereerst is de toepassing daarvan arbeidsintensief, omdat de opvullagen apart op maat moeten worden vervaardigd en 5 vervolgens in een aparte arbeidsstap moeten worden aangebracht. Bovendien werken zij gewichtsverhogend, hetgeen vooral bij toepassing in de luchtvaart- en ruimtevaart-industrie een groot nadeel is.However, such a solution has disadvantages. First of all, the application thereof is labor-intensive, because the filling layers must be produced separately to size and then have to be applied in a separate working step. Moreover, they have a weight-increasing effect, which is a major disadvantage, especially when used in the aerospace industry.
Vooral het aanbrengen van een vooraf reeds vervaardigd laminaat als extra versterkend element op een dergelijke niet-vlakke constructie blijkt problematisch. Een 10 dergelijk laminaat bezit een zodanig grote stijfheid, dat het aanpassen daarvan aan de contour van de niet-vlakke constructie gecompliceerd is.The application of a laminate already manufactured in advance as an additional reinforcing element on such a non-flat construction appears to be problematic. Such a laminate has such a high rigidity that it is complicated to adapt it to the contour of the non-planar construction.
Het aanbrengen van een aanvullende versterking in de vorm van extra lagen metaal is daardoor lastig en kostbaar. Doel van de uitvinding is een werkwijze te verschaffen waarbij deze problemen zich niet of in mindere mate voordoen. Dat doel 15 wordt bereikt door middel van een werkwijze voor het vervaardigen van een gevormd deel uit ten minste een vooraf vervaardigd laminaat dat ten minste twee metaallagen alsmede ten minste een zich daartussen bevindende, een thermoharder omvattende kunststoflaag omvat, welke werkwijze de stappen omvat van: het verschaffen van ten minste een vooraf vervaardigd, uitgehard laminaat, 20 - het verwarmen van dat laminaat, het vervormen van het verwarmde laminaat ter verschaffing van een gevormd deel, het afkoelen van het gevormde deel.Making an additional reinforcement in the form of additional layers of metal is therefore difficult and expensive. The object of the invention is to provide a method in which these problems do not occur or occur to a lesser extent. That object is achieved by means of a method for manufacturing a molded part from at least one prefabricated laminate which comprises at least two metal layers and at least one plastic layer between them, comprising a thermoset comprising a layer of synthetic resin, which method comprises the steps of: providing at least one prefabricated, cured laminate, heating said laminate, distorting the heated laminate to provide a molded portion, cooling the molded portion.
Volgens de uitvinding kan een reeds gevormd deel uit verschillende metaallagen, 25 die onderling zijn verbonden door een hechtende kunststoflaag die een thermoharder omvat, toch in een bepaalde gewenste vorm worden gebracht door toepassing van warmte en druk. Ondanks het feit dat het gerede laminaat een behoorlijke stijfheid bezit, kan het onder die omstandigheden toch goed worden vervormd. Dit is mogelijk doordat de kunststoflaag vervormbaar blijkt te worden bij hogere temperaturen, 30 mogelijk als gevolg van het zich strekken van de moleculen daarin. De metaallagen kunnen daardoor gemakkelijker langs elkaar glijden bij het aanbrengen van een buigbelasting, hetgeen de goede vervormbaarheid verklaart. Bij het afkoelen van het laminaat herstelt de oorspronkelijke stijfheid zich. Uiteraard moeten de vervormingen 1018120 3 niet zodanig groot worden dat loslating of delaminatie optreedt. Afhankelijk van de toegepaste materialen kan een optimaal temperatuurgebied worden gekozen bij het uitvoeren van de werkwijze volgens de uitvinding bijvoorbeeld van 100°C-250°C, bij voorkeur tussen 100°C - 180°C. De toe te passen druk kan bijvoorbeeld liggen tussen 1 5 en 10 bar, bij voorkeur tussen 2 en 6 bar. Dergelijke temperaturen en drukken kunnen worden verkregen door de werkwijze uit te voeren met behulp van een autoclaaf.According to the invention, an already formed part from different metal layers, which are interconnected by an adhesive plastic layer comprising a thermoset, can nevertheless be brought into a specific desired shape by applying heat and pressure. Despite the fact that the finished laminate has a considerable rigidity, it can still be properly deformed under those circumstances. This is possible because the plastic layer appears to become deformable at higher temperatures, possibly due to the stretching of the molecules therein. As a result, the metal layers can more easily slide past each other when applying a bending load, which explains the good formability. The original stiffness recovers upon cooling of the laminate. Of course, the deformations 1018120 3 should not become so large that release or delamination occurs. Depending on the materials used, an optimum temperature range can be selected when carrying out the method according to the invention, for example from 100 ° C to 250 ° C, preferably between 100 ° C to 180 ° C. The pressure to be applied can for instance be between 15 and 10 bar, preferably between 2 and 6 bar. Such temperatures and pressures can be obtained by carrying out the process with the aid of an autoclave.
Zowel thermoharders als thermoplasten kunnen worden toegepast.Both thermosets and thermoplastics can be used.
Zoals reeds genoemd kan de werkwijze volgens de uitvinding op verschillende manieren worden toegepast. Volgens een eerste mogelijkheid wordt de werkwijze 10 toegepast voor het verstevigen van een reeds gevormd, gelamineerd deel. De uitvinding betreft daarom eveneens het vervaardigen van een gevormd deel uit ten minste twee vooraf vervaardigde, uitgeharde laminaten die geheel of gedeeltelijk op elkaar liggen, welke laminaten aan hun naar elkaar gekeerde oppervlakken een ongelijke contour bezitten, omvattende: 15 - het verschaffen van ten minste twee laminaten met een ongelijke oppervlaktecontour, het ten minste gedeeltelijk op elkaar plaatsen van die laminaten onder insluiting van een te verharden lijmlaag, het verwarmen van die laminaten, 20 - het vervormen van ten minste een van die laminaten voor het onderling aanpassen van de oppervlaktecontouren daarvan, het aan elkaar hechten van de laminaten met onderling aangepaste oppervlaktecontouren ter verschaffing van het gevormde deel, het afkoelen van het gevormde deel.As already mentioned, the method according to the invention can be applied in various ways. According to a first possibility, the method 10 is used for reinforcing an already formed, laminated part. The invention therefore also relates to the production of a molded part from at least two prefabricated, cured laminates which lie wholly or partly on top of each other, which laminates have an uneven contour on their faces facing each other, comprising: - providing at least two laminates with an uneven surface contour, placing those laminates at least partially on top of each other while enclosing a layer of glue to be cured, heating those laminates, - deforming at least one of those laminates to mutually adjust their surface contours bonding the laminates with mutually matched surface contours to provide the molded part, cooling the molded part.
25 In het bijzonder kan het eerste laminaat een verbindingsconstructie omvatten die ten minste een metaallaag met overlappende secties heeft, zodanig dat ter plaatse van die overlappende secties een der oppervlakken van dat laminaat een diktesprong heeft die een afwijking vormt van het vlakke oppervlak van dat laminaat en het andere oppervlak daarvan vlak is, omvattende de stappen van: 30 - het op elkaar plaatsen van de beide laminaten, het plaatsen van het eerste laminaat met het vlakke oppervlak daarvan op een mal met een overeenkomstig vlak oppervlak, het verwarmen van die laminaten, » 1018120 4 het vervormen van het tweede laminaat voor het aanpassen daarvan aan het oppervlak van het eerste laminaat met de diktesprong ter verschaffing van het gevormde deel, het afkoelen van het gevormde deel.In particular, the first laminate may comprise a connecting structure that has at least one metal layer with overlapping sections, such that at the location of those overlapping sections one of the surfaces of said laminate has a thickness jump that forms a deviation from the flat surface of said laminate and the other surface thereof is flat, comprising the steps of: - placing the two laminates on top of each other, placing the first laminate with its flat surface on a mold with a corresponding flat surface, heating said laminates, 1018120 4 deforming the second laminate for adapting it to the surface of the first laminate with the thickness jump to provide the molded portion, cooling the molded portion.
5 De hiervoor genoemde diktesprong kan ook worden veroorzaakt door bijvoorbeeld een verbindingstrip ("doubler") die is gelijmd over de randen van twee kops tegen elkaar geplaatste lagen. De grootte van de diktesprong kan ongeveer 2 mm bedragen.The aforementioned thickness jump can also be caused by, for example, a connecting strip ("doubler") that is glued over the edges of two layers placed against each other. The size of the thickness jump can be around 2 mm.
De werkwijze volgens de uitvinding kan zowel worden toegepast bij platte, 10 vlakke delen, als bij gekromde delen. Ook dubbel gekromde delen kunnen verwerkt worden met de wijze volgens de uitvinding. Voordeel van vooral deze laatste variant is dat het versterkende laminaat, dat aangebracht wordt op een reeds vervaardigd, ander laminaat, niet nauwkeurig behoeft te worden afgestemd op de vorm van dat andere laminaat. Als gevolg van het verwarmen kan het versterkende laminaat zich vrij 15 eenvoudig "zetten", waardoor de productie van dubbel gekromde delen aanzienlijk goedkoper en eenvoudiger wordt.The method according to the invention can be applied to flat, flat parts as well as to curved parts. Double-curved parts can also be processed with the method according to the invention. The advantage of this latter variant, in particular, is that the reinforcing laminate, which is applied to a different laminate already manufactured, does not have to be precisely matched to the shape of that other laminate. As a result of the heating, the reinforcing laminate can quite easily "set", making the production of double-curved parts considerably cheaper and simpler.
Gewezen wordt op EP-A-547664, waaruit een werkwijze bekend is voor het vormen van een laminaat uit twee aluminiumlagen met daartussen een kunststoflaag. Bij deze bekende werkwijze bestaat de kunststoflaag echter uit een thermoplast.Reference is made to EP-A-547664, from which a method is known for forming a laminate from two aluminum layers with a plastic layer between them. In this known method, however, the plastic layer consists of a thermoplastic.
20 Vervolgens zal de uitvinding nader worden toegelicht aan de hand van de figuren.The invention will be explained in more detail below with reference to the figures.
Figuur 1 toont een eerste stap bij het uitvoeren van de werkwijze volgens de uitvinding.Figure 1 shows a first step in carrying out the method according to the invention.
Figuur 2 toont de tweede stap van de werkwijze.Figure 2 shows the second step of the method.
De werkwijze volgens de uitvinding betreft het vervaardigen van gevormde delen 25 uit een aantal metaallagen die onderling zijn verbonden door een hechtende kunststof laag. De in de figuren 1 en 2 weergegeven werkwij zestappen betreffen het versterken van het in zijn geheel met 21 weergegeven eerste gelamineerde deel door middel van het met 22 weergegeven, tweede gelamineerde deel.The method according to the invention relates to the production of molded parts from a number of metal layers which are mutually connected by an adhesive plastic layer. The method steps shown in Figs. 1 and 2 relate to reinforcing the first laminated part shown in its entirety by 21 by means of the second laminated part shown by 22.
Het eerste gelamineerde deel 21 omvat een drietal metalen lagen 1 tot 3 elk 30 bestaande uit twee secties 4', 5', respectievelijk 4", 5", respectievelijk 4'", 5'". Tussen de metalen lagen 1, 2 en 3 zijn respectievelijk de lagen kunststof materiaal 6, 7 aangebracht, die bijvoorbeeld bestaan uit een matrix van glasvezels ingebed in een hars.The first laminated part 21 comprises three metal layers 1 to 3, each consisting of two sections 4 ', 5', 4 ", 5", 4 "", 5 "", respectively. Arranged between the metal layers 1, 2 and 3 are the layers of plastic material 6, 7, which consist, for example, of a matrix of glass fibers embedded in a resin.
1018120 51018120 5
De secties 4', 5' respectievelijk 4", 5", respectievelijk 4"', 5'" overlappen elkaar ter plaatse van de overlap 8 respectievelijk 9 respectievelijk 10. Sectie 4' van de buitenste metalen laag 1 bezit daartoe een doorgezet gedeelte 11', sectie 4" van de metalen laag 2 een doorgezet gedeelte 11" en sectie 4'" van de metalen laag een doorgezet gedeelte 5 1Γ". Deze doorgezette gedeelten 11', respectievelijk 11", respectievelijk 1Γ" strekken zich uit tot onder de andere bijbehorende sectie 5', respectievelijk 5", respectievelijk 5'". Door middel van de lijmlagen 12', respectievelijk 12", respectievelijk 12'" zijn deze doorgezette delen en secties aan elkaar gelijmd. De kunststof lagen 6, 7 lopen door tussen deze overlappingen 8, 9 en 10.The sections 4 ', 5' and 4 ", 5" and 4 "', 5'", respectively, overlap each other at the location of the overlap 8, 9 and 10, respectively. Section 4 'of the outer metal layer 1 has a continuous portion 11 for this purpose. ", section 4" of the metal layer 2 a continuous portion 11 "and section 4" "of the metal layer a continuous portion 5". These extended portions 11 ', 11 ", and 1Γ", respectively, extend below the other associated sections 5', 5 ", and 5", respectively. By means of the adhesive layers 12 ', 12 "and 12" respectively, these stuck parts and sections are glued together. The plastic layers 6, 7 continue between these overlaps 8, 9 and 10.
10 In bepaalde gevallen kan het wenselijk zijn om het gelamineerde deel 21 te verstevigen door het aanbrengen van één of meerdere extra lagen. Die extra lagen kunnen bijvoorbeeld zijn samengesteld tot een tweede gelamineerde deel 22, dat in het weergegeven uitvoeringsvoorbeeld de lagen 13,14 en 15 omvat. Deze zijn aan elkaar bevestigd door de kunststof lagen 16 respectievelijk 17. Aangezien het tweede 15 gelamineerde deel 22 vlak is, is het niet direct mogelijk om dit door lijmen te verbinden aan het eerste gelamineerde deel 21. In de praktijk werden daarom tot nu toe vulplaten toegepast, die de grotere afstand tussen de lagen 3 en 13, buiten het doorgezette gedeelte 11'" moesten opvullen. Een dergelijke gang van zaken is echter arbeidsintensief, en leidt ook tot gewichtsverhoging als gevolg van de aanwezigheid 20 van de opvulplaten.In certain cases it may be desirable to reinforce the laminated part 21 by applying one or more additional layers. These additional layers can for instance be assembled into a second laminated part 22, which comprises the layers 13, 14 and 15 in the exemplary embodiment shown. These are attached to each other by the plastic layers 16 and 17, respectively. Since the second laminated part 22 is flat, it is not directly possible to connect this to the first laminated part 21 by gluing. which had to fill the greater distance between the layers 3 and 13 outside the protruded portion 11 '. However, such a course of action is labor-intensive and also leads to an increase in weight due to the presence of the shims.
Volgens de uitvinding kan het tweede gelamineerde deel 2 direct aan het niet vlakke oppervlak, veroorzaakt door de doorzetting 1Γ", worden gelijmd door de vooraf vervaardigde gelamineerde delen 21, 22 te verwarmen. Daardoor neemt de afschuifstijfheid in de kunststof lagen 16,17 af. Deze afname is zodanig, dat door het 25 met voldoende hoge druk op elkaar drukken van de gelamineerde delen 21,22, in het weergegeven uitvoeringsvoorbeeld de lagen 13,14 en 15 daarvan, gevormd kunnen worden volgens de contour van het gelamineerde deel 1, in het bijzonder de contour ter plekke en in de nabijheid van het doorgezette deel 11'". Bij het verwarmen wordt de vooraf op het eerste gelamineerde deel 21 aangebrachte Iijmlaag 18 geactiveerd, welke 30 Iijmlaag 18 na afkoelen voor de verbinding zorgt tussen de twee gelamineerde delen 21,22.According to the invention, the second laminated part 2 can be glued directly to the non-flat surface caused by the penetration 1Γ "by heating the prefabricated laminated parts 21, 22. As a result, the shear stiffness in the plastic layers 16, 17 decreases. This decrease is such that by pressing the laminated parts 21,22 together with sufficient pressure, the layers 13,14 and 15 thereof in the illustrated embodiment can be formed according to the contour of the laminated part 1 in in particular the contour on the spot and in the vicinity of the extended part 11 '". During heating, the adhesive layer 18 previously applied to the first laminated part 21 is activated, which adhesive layer 18, after cooling, provides the connection between the two laminated parts 21,22.
Voordeel van de werkwijze volgens de uitvinding is dat, vóór het aan elkaar hechten van gelamineerde delen 21, 22, deze niet voor wat betreft him vorm precies op 1018120 6 elkaar behoeven te worden afgestemd. Dat vereenvoudigt en versnelt het vervaardigingsproces aanzienlijk.The advantage of the method according to the invention is that, prior to the bonding of laminated parts 21, 22, they do not have to be precisely matched to each other with regard to their shape. This considerably simplifies and speeds up the manufacturing process.
Het in figuur 2 weergegeven eindproduct wordt verkregen doordat het eerste gelamineerde deel 21 aan zijn vrije oppervlak is ondersteund in een vlakke mal.The end product shown in Figure 2 is obtained in that the first laminated part 21 is supported on its free surface in a flat mold.
5 Daardoor wordt het tweede gelamineerde deel 22 bij aandrukken gedwongen de getoonde vorm aan te nemen. Overigens kunnen met de werkwijze volgens de uitvinding ook dubbel gekromde vormen worden vervaardigd. Zo kan in een vooraf vervaardigd, dubbel gekromd deel 1 een overeenkomstig dubbel gekromd deel 2 worden geplaatst. Hoewel deze aanvankelijk niet goed tegen elkaar aansluiten, kan 10 door toepassing van warmte en druk toch de gewenste aanligging verkregen worden.As a result, the second laminated part 22 is forced, upon pressing, to assume the shape shown. Incidentally, with the method according to the invention, double-curved shapes can also be produced. Thus, a corresponding double-curved part 2 can be placed in a prefabricated, double-curved part 1. Although these do not initially fit well together, the desired contact can still be obtained by applying heat and pressure.
Indien het eerste gekromde deel 1 in een dubbel gekromde mal wordt ondersteund, wordt als gevolg van de warmte en druk het tweede dubbel gekromde deel 2 gedwongen zijn vorm aan te passen aan de krommingen van het eerste dubbel gekromde deel 1. Ook hierbij worden aanzienlijke vereenvoudigingen van de 15 werkwijze verkregen, aangezien ook in dit geval het tweede dubbel gekromde deel niet nauwkeurig behoeft te worden aangepast aan het eerste gekromde deel.If the first curved part 1 is supported in a double-curved mold, as a result of the heat and pressure the second double-curved part 2 is forced to adapt its shape to the curves of the first double-curved part 1. Here too considerable simplifications are made obtained from the method, since in this case also the second double-curved part does not have to be accurately adapted to the first curved part.
Voor de metalen en kunststoffen kunnen allerlei verschillende producten worden gekozen. Voorbeelden van geschikte metalen zijn aluminium legeringen, staal legeringen, titanium legeringen, koper legeringen, magnesium legeringen. In het 20 bijzonder kunnen worden genoemd aluminium-koper legeringen (AA 2000), aluminium-mangaan legeringen (AA 3000), aluminium-magnesium legering (AA 5000), aluminium-zink legeringen (AA 7000), en aluminium-magnesium-silicium legeringen (AA 6000).All kinds of different products can be chosen for metals and plastics. Examples of suitable metals are aluminum alloys, steel alloys, titanium alloys, copper alloys, magnesium alloys. Mention may be made in particular of aluminum-copper alloys (AA 2000), aluminum-manganese alloys (AA 3000), aluminum-magnesium alloys (AA 5000), aluminum-zinc alloys (AA 7000), and aluminum-magnesium-silicon alloys (AA 6000).
In het bijzonder de voorkeur genieten de aluminium-koper legering (AA 2224), 25 de aluminium-zink legering (AA 7075) en de aluminium-magnesium-silicium legering (AA 6013). Datzelfde geldt voor AA 2X24-23 en AA 7X75-26. Indien een hoge bestendigheid tegen erosie gewenst is, kan een AA 50525 legering in het laminaat worden opgenomen.The aluminum-copper alloy (AA 2224), the aluminum-zinc alloy (AA 7075) and the aluminum-magnesium-silicon alloy (AA 6013) are particularly preferred. The same applies to AA 2X24-23 and AA 7X75-26. If a high erosion resistance is desired, an AA 50525 alloy can be incorporated into the laminate.
Voorbeelden van geschikte thermohardende kunststoffen zijn epoxyharsen, 30 onverzadigde polyesters, vinylesters, en fenolesters. Geschikte thermoplastische kunststoffen zijn bijvoorbeeld polyarylaten (PAR), polysulfonen (PSO), polyethersulfonen (PES), polyetherimiden (PEI), of polyphenileenethers (PEE), 1018120 7 polyphenileensulfide (PPS), polyamide-4,6, polyketonsulfide (PKS), polyetherketonen (PEK), polyetheretherketon (PEEK) en polyetherketonketon (PEKK).Examples of suitable thermosetting plastics are epoxy resins, unsaturated polyesters, vinyl esters, and phenol esters. Suitable thermoplastic plastics are, for example, polyarylates (PAR), polysulfones (PSO), polyether sulfones (PES), polyetherimides (PEI), or polyphenilene ethers (PEE), 1018120 7 polyphenilene sulfide (PPS), polyamide-4,6, polyketone sulfide (PKS), polyetherketones (PEK), polyether ether ketone (PEEK) and polyether ketone ketone (PEKK).
De hechtende kunststoflaag kan zijn voorzien van een wapening in de vorm van continue vezels, bijvoorbeeld zoals het geval is bij de hiervoor genoemde materialen 5 Glare ® en ARALL ®. De voorkeur gaat daarbij uit naar S-2 glas of R-glasvezels, die elk ongeveer 58 - 69 gew.% S1O2,18-29 gew.% AI2O3 en 7 -19 gew.% MgO omvatten. Ook geschikt zijn E-glasvezels, met ongeveer 55 gew.% S1O2,15 gew.% AI2O3,19 gew.% CaO, 7 gew.% B2O3 en 3 gew.% MgO. Een geschikte aramidevezel is vervaardigd uit polyparafinileentereftalamide.The adhesive plastic layer can be provided with a reinforcement in the form of continuous fibers, for example as is the case with the aforementioned materials Glare ® and ARALL ®. Preference is given to S-2 glass or R-glass fibers, which each comprise approximately 58 - 69% by weight of S102.18-29% by weight of Al2O3 and 7 -19% by weight of MgO. Also suitable are E-glass fibers, with approximately 55% by weight of SO2.15% by weight of Al2O3.19% by weight of CaO, 7% by weight of B2O3 and 3% by weight of MgO. A suitable aramid fiber is made from polyparafinile terephthalamide.
10181201018120
Claims (12)
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
NL1018120A NL1018120C2 (en) | 2001-05-21 | 2001-05-21 | Method for manufacturing a molded laminate. |
PCT/NL2002/000251 WO2002094565A1 (en) | 2001-05-21 | 2002-05-15 | Method for producing a shaped laminate |
ARP020101880A AR033904A1 (en) | 2001-05-21 | 2002-05-21 | METHOD FOR PRODUCING A CONFORMED LAMINATE |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
NL1018120 | 2001-05-21 | ||
NL1018120A NL1018120C2 (en) | 2001-05-21 | 2001-05-21 | Method for manufacturing a molded laminate. |
Publications (1)
Publication Number | Publication Date |
---|---|
NL1018120C2 true NL1018120C2 (en) | 2002-12-03 |
Family
ID=19773432
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
NL1018120A NL1018120C2 (en) | 2001-05-21 | 2001-05-21 | Method for manufacturing a molded laminate. |
Country Status (3)
Country | Link |
---|---|
AR (1) | AR033904A1 (en) |
NL (1) | NL1018120C2 (en) |
WO (1) | WO2002094565A1 (en) |
Families Citing this family (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
NL1025744C2 (en) * | 2004-03-16 | 2005-01-18 | Stork Fokker Aesp Bv | Laminate with metal layers, used for aerospace applications, contains electrical heating layer |
DE102007019716A1 (en) | 2007-04-26 | 2008-10-30 | Airbus Deutschland Gmbh | Fiber metal laminate panel |
NL2007603C2 (en) * | 2011-10-14 | 2013-04-16 | Univ Delft Tech | Fiber metal laminate. |
WO2015049509A1 (en) * | 2013-10-02 | 2015-04-09 | Bae Systems Plc | Flexible tooling |
EP2857168A1 (en) * | 2013-10-02 | 2015-04-08 | BAE Systems PLC | Flexible tooling |
WO2017139536A1 (en) * | 2016-02-11 | 2017-08-17 | Durez Corporation | Molded polymer and metal articles |
NL2017062B1 (en) * | 2016-06-28 | 2018-01-05 | Fokker Aerostructures Bv | Method for manufacturing a panel with thickening |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5160771A (en) * | 1990-09-27 | 1992-11-03 | Structural Laminates Company | Joining metal-polymer-metal laminate sections |
EP0547664A2 (en) * | 1991-12-19 | 1993-06-23 | Hoogovens Groep B.V. | Method of hot-forming a component by shaping a laminated metal and plastics material sheet |
WO1994001277A1 (en) * | 1992-07-09 | 1994-01-20 | Structural Laminates Company | Spliced laminate for aircraft fuselage |
WO1998053989A1 (en) * | 1997-05-28 | 1998-12-03 | Akzo Nobel N.V. | Method for making a laminate and laminate obtainable by said method |
US5951800A (en) * | 1992-11-18 | 1999-09-14 | Mcdonnell Douglas Corp. | Fiber/metal laminate splice |
-
2001
- 2001-05-21 NL NL1018120A patent/NL1018120C2/en not_active IP Right Cessation
-
2002
- 2002-05-15 WO PCT/NL2002/000251 patent/WO2002094565A1/en not_active Application Discontinuation
- 2002-05-21 AR ARP020101880A patent/AR033904A1/en not_active Application Discontinuation
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5160771A (en) * | 1990-09-27 | 1992-11-03 | Structural Laminates Company | Joining metal-polymer-metal laminate sections |
EP0547664A2 (en) * | 1991-12-19 | 1993-06-23 | Hoogovens Groep B.V. | Method of hot-forming a component by shaping a laminated metal and plastics material sheet |
WO1994001277A1 (en) * | 1992-07-09 | 1994-01-20 | Structural Laminates Company | Spliced laminate for aircraft fuselage |
US5951800A (en) * | 1992-11-18 | 1999-09-14 | Mcdonnell Douglas Corp. | Fiber/metal laminate splice |
WO1998053989A1 (en) * | 1997-05-28 | 1998-12-03 | Akzo Nobel N.V. | Method for making a laminate and laminate obtainable by said method |
Also Published As
Publication number | Publication date |
---|---|
WO2002094565A1 (en) | 2002-11-28 |
AR033904A1 (en) | 2004-01-07 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
JP4262782B2 (en) | LAMINATE MANUFACTURING METHOD AND LAMINATE OBTAINED BY THE METHOD | |
EP1474287B1 (en) | Laminated panel with discontinuous internal layer | |
EP1031409B1 (en) | Method of manufacturing lightweight glazing by multilayer glass/plastic sheets | |
NL1024076C2 (en) | Method for forming a laminate with a recess. | |
EP1963091B1 (en) | Composite panel | |
NL2012458B1 (en) | Laminate of mutually bonded adhesive layers and metal sheets, and method to obtain such laminate. | |
CN1081534C (en) | Composite panel | |
JP2838966B2 (en) | Metal-polypropylene-metal laminates and methods of making sheet articles in the form of such laminates | |
NL1018120C2 (en) | Method for manufacturing a molded laminate. | |
US20010017336A1 (en) | Composite airfoil structures and their forming methods | |
JP2003312590A (en) | Reinforcement body for aircraft skin panel and manufacturing method for skin panel provided with reinforcement body | |
GB2133342A (en) | Lightweight core for laminate constructions | |
CN103568446A (en) | Laminated composite bending and stiffening members with reinforcement by inter-laminar metal sheets | |
NL2015437B1 (en) | Laminate of mutually bonded adhesive layers and metal sheets, and method to obtain such laminate. | |
JP6583966B2 (en) | Panel made of laminate and method for producing the same | |
CN106394702B (en) | The connection structure of car engine room longeron and front wall crossbeam | |
US20170165904A1 (en) | Composite steel | |
JP2000038139A (en) | Steering wheel and its manufacture | |
NL1019575C2 (en) | Honeycomb material and methods for manufacturing it. | |
FI119282B (en) | Process for manufacturing a molded piece | |
JP2022078876A (en) | Metal-fiber reinforced resin laminate | |
KR20230069942A (en) | Forming method of container for vehicle battery | |
NL8900125A (en) | Method for mfg. strip-like heat deformable laminate - has short spring-steel strips in outermost layer, partly overlapping connected by heating under pressure and covered on both sides |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PD2B | A search report has been drawn up | ||
VD1 | Lapsed due to non-payment of the annual fee |
Effective date: 20051201 |