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WO1998000274A1 - Chauffage de composants - Google Patents

Chauffage de composants Download PDF

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Publication number
WO1998000274A1
WO1998000274A1 PCT/AU1997/000416 AU9700416W WO9800274A1 WO 1998000274 A1 WO1998000274 A1 WO 1998000274A1 AU 9700416 W AU9700416 W AU 9700416W WO 9800274 A1 WO9800274 A1 WO 9800274A1
Authority
WO
WIPO (PCT)
Prior art keywords
article
mould
induction heating
magnetic induction
heating
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.)
Ceased
Application number
PCT/AU1997/000416
Other languages
English (en)
Inventor
Patrick Michael William Ayres
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.)
Individual
Original Assignee
Individual
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 Individual filed Critical Individual
Priority to AU32479/97A priority Critical patent/AU3247997A/en
Publication of WO1998000274A1 publication Critical patent/WO1998000274A1/fr
Anticipated expiration legal-status Critical
Ceased 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
    • B29C33/00—Moulds or cores; Details thereof or accessories therefor
    • B29C33/02—Moulds or cores; Details thereof or accessories therefor with incorporated heating or cooling means
    • B29C33/06—Moulds or cores; Details thereof or accessories therefor with incorporated heating or cooling means using radiation, e.g. electro-magnetic waves, induction heating
    • 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
    • B29C35/00—Heating, cooling or curing, e.g. crosslinking or vulcanising; Apparatus therefor
    • B29C35/02—Heating or curing, e.g. crosslinking or vulcanizing during moulding, e.g. in a mould
    • B29C35/08—Heating or curing, e.g. crosslinking or vulcanizing during moulding, e.g. in a mould by wave energy or particle radiation
    • 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
    • B29C73/00—Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass B29D
    • B29C73/04—Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass B29D using preformed elements
    • B29C73/10—Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass B29D using preformed elements using patches sealing on the surface of the article
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
    • B64D15/16—De-icing or preventing icing on exterior surfaces of aircraft by mechanical means, e.g. pulsating mats or shoes attached to, or built into, surface
    • H—ELECTRICITY
    • H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
    • H05B—ELECTRIC HEATING; ELECTRIC LIGHT SOURCES NOT OTHERWISE PROVIDED FOR; CIRCUIT ARRANGEMENTS FOR ELECTRIC LIGHT SOURCES, IN GENERAL
    • H05B6/00—Heating by electric, magnetic or electromagnetic fields
    • H05B6/02—Induction heating
    • H05B6/10—Induction heating apparatus, other than furnaces, for specific applications
    • H05B6/105—Induction heating apparatus, other than furnaces, for specific applications using a susceptor
    • 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
    • B29C35/00—Heating, cooling or curing, e.g. crosslinking or vulcanising; Apparatus therefor
    • B29C35/02—Heating or curing, e.g. crosslinking or vulcanizing during moulding, e.g. in a mould
    • B29C2035/0211—Heating or curing, e.g. crosslinking or vulcanizing during moulding, e.g. in a mould resistance heating
    • 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
    • B29C35/00—Heating, cooling or curing, e.g. crosslinking or vulcanising; Apparatus therefor
    • B29C35/02—Heating or curing, e.g. crosslinking or vulcanizing during moulding, e.g. in a mould
    • B29C35/08—Heating or curing, e.g. crosslinking or vulcanizing during moulding, e.g. in a mould by wave energy or particle radiation
    • B29C35/0805—Heating or curing, e.g. crosslinking or vulcanizing during moulding, e.g. in a mould by wave energy or particle radiation using electromagnetic radiation
    • B29C2035/0811—Heating or curing, e.g. crosslinking or vulcanizing during moulding, e.g. in a mould by wave energy or particle radiation using electromagnetic radiation using induction
    • 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
    • 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
    • B29K2307/00—Use of elements other than metals as reinforcement
    • 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
    • B29K2707/00—Use of elements other than metals for preformed parts, e.g. for inserts
    • B29K2707/04—Carbon

Definitions

  • the present invention relates to the heating of components and relates particularly, though not exclusively, to the production of composites and methods and apparatus for their production.
  • Composites are strong and lightweight. They generally consist of a carbon, Kevlar TM, fibreglass or similar fibres which are bound together by a resin or resins. The fibres or sheet of fibres are laid up with or pre- impregnated with the resin, placed in a shaping mould and the mixture cured by heat. Typical cure temperatures are in the range of 1 20-1 80° C (250-350 ° F) .
  • Curing is the process whereby the resin used to bind and hold the fibres in place in the components, is set or hardened, usually by applying heat to the resin so that a cure temperature is reached, thus causing the resin to chemically set.
  • the process may also involve application of pressures of one atmosphere or more to the component in the mould whilst curing within an autoclave.
  • the moulds used to lay up the components have been heated, typically by passing high temperature oil or steam through pipes embedded in the mould.
  • the major disadvantages of such heating is that the area of the mould/component directly under the pipes receives the most heat/highest temperature, with areas between the pipes not being as hot. This can lead to uneven curing and in extreme cases, to sections of the components not being properly cured.
  • the differences in coefficients of expansion between the material used to build the mould and the pipes through which the heating fluid is transmitted eventually leads to delamination or structural break down of the mould.
  • An object of the present invention is to provide a method of curing composite components without requiring an autoclave or a heat blanket.
  • a further object is to reduce the time involved in curing composite components.
  • a still further object is to allow for direct heating to the composite components rather than through heat soaking of the mould.
  • the present invention in one aspect provides a method of heating an article by using magnetic induction heating and/or resistive heating.
  • said method is for heating said article having a matrix of fibres and resin and said article is formed by curing said resin through said magnetic induction heating and/or said resistive heating.
  • Said article may include an electrically conductive constituent which is heated by said magnetic induction heating.
  • said electrically conductive constituent includes carbon fibres. The natural conductivity of the fibres themselves will be used as the medium for generation of the induction heating currents. Heat build up in a mould using this method is secondary, and incidental to the cure process.
  • the article may be heated via resistive heating coils of carbon fibre or graphite laid within the matrix of the mould and its enclosing lid with said resistive heating coils located as near as possible to the working surface of the mould and the lid.
  • resistive heating coils will be laid up so that the absolute minimum of a gap exists between the resistive coils, thus obviating areas of high/low temperature in the article. Further, as the resistive heating coils are to be constructed of carbon fibre/graphite, there will be no differences in coefficients of expansion between the mould and the resistive coils, thus negating the problem of mould delamination experienced with metal or metal sheathed coils.
  • the articles being electrically conductive may alternatively be formed in moulds or parts of moulds where magnetic induction heating is used to directly induce heat into the articles themselves.
  • the moulds may incorporate a solid large plug of carbon fibre or graphite to assist "scanning" of the article using the magnetic induction heating process.
  • carbon fibre/graphite induction heating coils may be built into the moulds where appropriate for cure of certain articles.
  • the articles may be laid up in polymer/ceramic or between metal/metal surfaced moulds to contain the magnetic induction heating directly into the article. In such a process, the mould does get hot, but does not approach the curing temperature of the article, thus reducing twisting or warpage.
  • Temperature control can be accurate and quick, thus allowing much more rapid re-cycling of moulds and a lower energy usage to effect a cure.
  • electronic control of temperature it is easy to cope with exothermic heat build up as the resin cures.
  • the heating process is even over the whole surface area and internal volume of the article, ensuring even and complete curing. As the heat is induced into the article or radiated from near tool surface mounted resistive heating coils, the method avoids a progressive 4
  • the method is adaptable to accommodate vacuum bagging/pressurisation of the article during production.
  • the electronic control over the heating ensures that each article is cured within its exact specified resin cure cycle.
  • a magnetic induction heating coil including a non-conductive sheath which surrounds a conductive inner core.
  • said coil is flexible or bendable.
  • Said core may comprise carbon fibre filaments or woven metal wire rope.
  • in situ repairs can be made to damaged composite components using temporary moulds placed thereon.
  • Fig. 1 is a perspective view of a first embodiment of a mould made in accordance with the invention
  • Fig. 2 is a perspective view of a second embodiment of a further mould
  • Fig. 3 is a perspective view of a third embodiment of yet another mould
  • Fig. 4 are views of a coil strap used in the embodiment shown in Fig.3;
  • Fig. 5 are views of an alternate coil strap used in the embodiment shown in Fig.3;
  • Fig. 6 is a perspective view of a fourth embodiment of a mould
  • Fig. 7 are views of a partial section of the mould shown in Fig. 6;
  • Fig. 8 is a cross-sectional view of the bottom half of the mould shown in Fig. 6;
  • Fig. 9 is perspective view showing operation of the mould shown in Fig. 6;
  • a mould 10 comprising a top half 12 and a bottom half 14.
  • the halves 12,14 have internal surfaces or inserts/tools contoured to the desired final shape of a component or components inserted therein.
  • a carbon fibre matrix fabric is used.
  • Such fabrics are used in the aerospace industry (where most heat cured composite components are now used) and generally comprise a carbon fibre fabric, sometimes laid up with other fabrics such as fibreglass and KevlarTM .
  • a resin system is pre-impregnated onto the fabric. At other times film plies of resin are applied in a lay-up when plain fabrics (not pre-impregnated with resin) are to be used.
  • Mould 10 is not subjected to direct heat and has no embedded pipes for flow of hot oil or steam.
  • Mould 10 may be formed from any suitable material eg. metallic, metallic surfaced or non- metallic.
  • a plurality of magnetic induction heating coils 16, 18,20,22 are placed on the outside of top half 12 and linked in either a parallel or series connection. The number and shape of the magnetic induction heating coils 16,18,20,22 may vary depending on the component(s) being produced. In this embodiment each coil is a flat plate or pancake shape.
  • the use of magnetic induction heating coils are commonplace in metallurgy for surface hardening of steel but different types of coils are used.
  • a high frequency alternating current is passed through the coils 16,18,20,22 to provide a magnetic field, the intensity of which varies periodically in magnitude and direction. The frequencies to 4
  • Coils used in the process may need magnetic field concentrators where they are coupled together to ensure that effective heating of the component is achieved. Such concentrators may include connectors which also include a small inductor. If required, the flat plate coils 16, 18,20,22 may also take the form of a fixed "scanning" coil (not shown) that is robotically moved continuously to and fro across the surface of moulds 10, thus inducing the heating currents into the component.
  • Fig. 2 shows a mould 24 having a top half or lid 26 and a bottom half 28.
  • the halves 26,28 can be made of plastics or ceramic material. Again the internal surface(s) of the halves 26,28 can be contoured or include tools/inserts to provide the desired end shape of the component(s) to be moulded.
  • bottom half 28 has an magnetic induction heating coil 30 encased therein.
  • moulds/tools/inserts to be used in the manufacture of composite components are made from materials with a similar coefficient of expansion to the material to be used in the component.
  • Coil 30 may be formed of metallic or non-metallic material and may be enclosed within a non-conductive sheath. The sheath will accommodate any expansion or contraction of the coil as it heats and cools.
  • heating coil 30 may be of a different configuration in that it is constructed of carbon fibre/graphite strips, placed very near to the tooling or working surface of the mould, with minimal gaps between the strips, and heated resistively to generate heat by convection into the component.
  • a similar resistive heating coil would be inserted into the closing lid 26 of the mould 10 to ensure equal heat curing to both faces of the component.
  • Fig. 3 shows a mould 32 which may be of similar construction to that of mould 10 in Fig. 1 .
  • a flexible or bendable magnetic induction heating coil 34 is used.
  • Coil 34 may comprise a single wound coil or a plurality of coils connected together serially or in parallel. Coil 34 is wrapped around mould 32 in such a way that the coil forms a closed loop coil around the mould.
  • These coils 34 may be manufactured from metal and non-metallic conductive materials that exhibit sufficient flexibility or ductility to be wound around compound curves and tight angles, and not be subject to fatigue fracture due to constant usage. Such materials may include carbon fibres themselves.
  • Figs. 4 and 5 illustrate some examples of such materials.
  • Fig. 4 shows carbon fibres 36 laid in continuous filaments inside a non-conductive sheathing 38 to hold fibres 36 in alignment.
  • Fig. 5 shows woven metallic wire ropes 40 inside non- conductive sheathing 42 to hold ropes in alignment on mould 32.
  • moulds 10 and 32 of Figs. 1 and 3 can be extended to allow for in situ repairs of damaged composite components eg aircraft wings, without partial disassembly of the aircraft.
  • the damaged section can be dressed and prepared for the installation of a patch repair.
  • a temporary or disposable mould could be made of the outer face of the section to be repaired from another undamaged component.
  • a flexible vacuum film is inserted at the back of the damaged section and sealed against the rear of the damaged component. The vacuum film will be left inside the component.
  • the repair plies of carbon fibre (and core material, if necessary) are cut to fit the dressed damaged section and laid up to fill the damaged area.
  • the mould is laid against the outer face of the component and a vacuum drawn through the mould to compress the repair plies.
  • the magnetic induction heating coils are placed against the mould and the appropriate frequency and duration of cycle are used to induce heat in the all repair plies to effect a cure and bonding the repair material to the component.
  • Fig. 6 shows a variation of the moulds shown in Figs. 1 to 3.
  • Mould 44 has a top half 46 and bottom half 48. The halves 46,48 can be sealingly attached to one another to ensure an airtight fit.
  • An air pressurisation valve 50 is located in top half 46 to allow entry of pressurised air into mould 44.
  • a pressure relief valve 52 is also provided as a safety device in case of over- pressurisation.
  • a flexible membrane (not shown) can be moulded on top half 46 to conform to the profile of the component. Air pressure will be used to inflate the membrane, thus bearing down on the component within the mould to whatever pressure is required for that particular cure process. Air can be pumped into mould 44 via valve 50. Typical pressures would be one (1 ) atmosphere and above.
  • Such moulds 44 may incorporate a solid near surface carbon fibre/graphite plug or core 63 to assist with scanning of the component by the induction heating coil and thus generation of the heating currents within the component.
  • Fig. 7 shows a mould half 54 which has a waffle slab construction.
  • removable mould elements (not shown) are inserted in the base of the mould half 54 to be formed.
  • the mould elements When hardened the mould elements are removed to leave behind hollow ribs 58.
  • Ribs 58 will substantially increase the strength of mould half 54.
  • Such moulds will also solve the current production problem experienced with steel moulds where, under heat, they experience a positive coefficient of expansion, whereas carbon fibre has a zero or negative coefficient of expansion.
  • polymer/ceramic moulds involve a substantially reduced capital cost to build compared to steel moulds.
  • FIG. 8 there is shown a method to further assist in accurate conformance of the carbon fibre fabric 68 in mould 44 where a vacuum outlet 66 is provided which opens into lower half 48 of mould 44.
  • a vacuum pump (not shown) can be coupled to outlet 66.
  • a vacuum bag or membrane 70 is sealed to bottom half 48 by bead 72.
  • a bleed cloth 74 lies between fabric 68 and membrane 70 which provides a passage for air to escape from surface of fabric 68 to vacuum outlet 66.
  • Fig. 9 illustrates a schematic drawing of the completed process for forming components.
  • integers in Fig. 8 which correspond with integers in Figs. 1 to 8, will be given an 'A' suffix.
  • Mould half 48A has heat sensors 60 which face the component and in the membrane or adjacent the membrane from which measurements of temperatures may be recorded.
  • Heat sensors 60 may include digital silicone sensors and heat sensitive fibre optic cabling and others. Heat sensors 60 should not be conductive themselves, so that the heat measurement will properly reflect the induced temperature in the component.
  • Coil 34A preferably has sufficient depth to allow mould 44A to be able to be slipped therebetween without interference from valves 50A,52A.
  • Measurement of heat, elapsed time, air pressure, and variations thereof will be monitored by an electronic control unit or programmable processor 62 during the cure process.
  • Unit/processor 62 may control temperature/current/frequency/pressure as necessary, including varying same during the cure process, so that the desired cure cycle required for components will be controlled. Temperature, pressure, and time measurements may be recorded by the unit/processor and may be printed out on completion to provide a record of the complete cure cycle.
  • the invention provides a simpler system with substantially reduced costs and production times compared with the prior art.
  • 62 of the invention may be used for production of many different components resulting in less inventory.

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  • Engineering & Computer Science (AREA)
  • Health & Medical Sciences (AREA)
  • Mechanical Engineering (AREA)
  • Toxicology (AREA)
  • Physics & Mathematics (AREA)
  • Oral & Maxillofacial Surgery (AREA)
  • Thermal Sciences (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Electromagnetism (AREA)
  • Moulding By Coating Moulds (AREA)

Abstract

Cette invention concerne un procédé et un appareil permettant de chauffer un article en utilisant un chauffage par induction magnétique et/ou un chauffage par résistance. Ce procédé et cet appareil permettent de chauffer des articles qui comportent une matrice de fibres et de résine, l'article étant formé en solidifiant la résine grâce au chauffage par induction magnétique et/ou au chauffage par résistance. Ces articles comprennent un constituant conducteur d'électricité qui est chauffé par induction magnétique, et qui comprend des fibres de carbone. La conductivité naturelle des fibres elles-mêmes est de préférence utilisée comme un moyen permettant de générer les courants de chauffage par induction.
PCT/AU1997/000416 1996-07-01 1997-07-01 Chauffage de composants Ceased WO1998000274A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AU32479/97A AU3247997A (en) 1996-07-01 1997-07-01 Heating of components

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
AUPO0712 1996-07-01
AUPO0712A AUPO071296A0 (en) 1996-07-01 1996-07-01 Heating of components

Publications (1)

Publication Number Publication Date
WO1998000274A1 true WO1998000274A1 (fr) 1998-01-08

Family

ID=3795028

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/AU1997/000416 Ceased WO1998000274A1 (fr) 1996-07-01 1997-07-01 Chauffage de composants

Country Status (2)

Country Link
AU (1) AUPO071296A0 (fr)
WO (1) WO1998000274A1 (fr)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6717118B2 (en) 2001-06-26 2004-04-06 Husky Injection Molding Systems, Ltd Apparatus for inductive and resistive heating of an object
US6781100B2 (en) 2001-06-26 2004-08-24 Husky Injection Molding Systems, Ltd. Method for inductive and resistive heating of an object
FR2928808A1 (fr) * 2008-03-17 2009-09-18 Roctool Sa Dispositif de transformation de materiaux utilisant un chauffage par induction et des moyens de compactage deformables
EP2260993A1 (fr) * 2009-06-12 2010-12-15 Robert Bosch GmbH Outil de moulage par injection
FR3015919A1 (fr) * 2013-12-31 2015-07-03 Roctool Dispositif pour le chauffage d’un moule
WO2015108752A1 (fr) * 2014-01-17 2015-07-23 Nike Innovate C.V. Procédé de durcissement par transport ajustable
EP3278965A1 (fr) * 2016-08-05 2018-02-07 Star Leader Trading Limited Procédé et dispositif de formation de produit de fibre et carbone
US20180079112A1 (en) * 2015-06-03 2018-03-22 Mitsubishi Heavy Industries, Ltd. Curing device for resin composite material, curing method, and molded resin article
US10321524B2 (en) 2014-01-17 2019-06-11 Nike, Inc. Conveyance curing system
EP3564021A1 (fr) * 2018-05-01 2019-11-06 Rolls-Royce plc Réparation de composites à matrice polymère

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2637534A1 (fr) * 1988-10-11 1990-04-13 Pascal Roger Procede de fabrication d'une piece en materiau composite par pressage et piece obtenue par ce procede
US5248864A (en) * 1991-07-30 1993-09-28 E. I. Du Pont De Nemours And Company Method for induction heating of composite materials

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2637534A1 (fr) * 1988-10-11 1990-04-13 Pascal Roger Procede de fabrication d'une piece en materiau composite par pressage et piece obtenue par ce procede
US5248864A (en) * 1991-07-30 1993-09-28 E. I. Du Pont De Nemours And Company Method for induction heating of composite materials

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
"Chemical Engineers Handbook", Fifth Edition, 1973, Published by PERRY AND CHILTON, Part 9-30 and 9-31. *
DERWENT ABSTRACT, Accession No. 90-337825/45, Class A32; & JP,A,02 241 710 (SAKIA COMPOSITE KK), 26 September 1990. *

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6781100B2 (en) 2001-06-26 2004-08-24 Husky Injection Molding Systems, Ltd. Method for inductive and resistive heating of an object
US7041944B2 (en) 2001-06-26 2006-05-09 Husky Injection Molding Systems, Ltd. Apparatus for inductive and resistive heating of an object
US6717118B2 (en) 2001-06-26 2004-04-06 Husky Injection Molding Systems, Ltd Apparatus for inductive and resistive heating of an object
FR2928808A1 (fr) * 2008-03-17 2009-09-18 Roctool Sa Dispositif de transformation de materiaux utilisant un chauffage par induction et des moyens de compactage deformables
WO2009125079A3 (fr) * 2008-03-17 2009-11-26 Roctool Dispositif de transformation de materiaux utilisant un chauffage par induction et des moyens de compactage deformables
US8794950B2 (en) 2008-03-17 2014-08-05 Roctool Device for converting materials using induction heating and deformable compacting means
CN106079171A (zh) * 2008-03-17 2016-11-09 罗克器械公司 用于材料转化的加热设备
EP2260993A1 (fr) * 2009-06-12 2010-12-15 Robert Bosch GmbH Outil de moulage par injection
US10173379B2 (en) 2013-12-31 2019-01-08 Roctool Device for heating a mold
FR3015919A1 (fr) * 2013-12-31 2015-07-03 Roctool Dispositif pour le chauffage d’un moule
WO2015155369A1 (fr) * 2013-12-31 2015-10-15 Roctool Dispositif pour le chauffage d'un moule
WO2015108752A1 (fr) * 2014-01-17 2015-07-23 Nike Innovate C.V. Procédé de durcissement par transport ajustable
US10321524B2 (en) 2014-01-17 2019-06-11 Nike, Inc. Conveyance curing system
US11166350B2 (en) 2014-01-17 2021-11-02 Nike, Inc. Adjustable conveyance curing system
US20180079112A1 (en) * 2015-06-03 2018-03-22 Mitsubishi Heavy Industries, Ltd. Curing device for resin composite material, curing method, and molded resin article
EP3263308A4 (fr) * 2015-06-03 2018-04-04 Mitsubishi Heavy Industries, Ltd. Dispositif de durcissement pour matériau composite de résine, procédé de durcissement, et article en résine moulé
EP3278965A1 (fr) * 2016-08-05 2018-02-07 Star Leader Trading Limited Procédé et dispositif de formation de produit de fibre et carbone
EP3564021A1 (fr) * 2018-05-01 2019-11-06 Rolls-Royce plc Réparation de composites à matrice polymère
US11279100B2 (en) 2018-05-01 2022-03-22 Rolls-Royce Plc Polymer matrix composite repair

Also Published As

Publication number Publication date
AUPO071296A0 (en) 1996-07-25

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