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WO2009050651A2 - Appareil de fabrication d'éléments structurels composés d'un matériau composite à base de fibre de carbone, pour la construction d'un avion - Google Patents

Appareil de fabrication d'éléments structurels composés d'un matériau composite à base de fibre de carbone, pour la construction d'un avion Download PDF

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Publication number
WO2009050651A2
WO2009050651A2 PCT/IB2008/054229 IB2008054229W WO2009050651A2 WO 2009050651 A2 WO2009050651 A2 WO 2009050651A2 IB 2008054229 W IB2008054229 W IB 2008054229W WO 2009050651 A2 WO2009050651 A2 WO 2009050651A2
Authority
WO
WIPO (PCT)
Prior art keywords
tool
forming surface
cover
forming
extends
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/IB2008/054229
Other languages
English (en)
Other versions
WO2009050651A3 (fr
Inventor
Francesco Beneventi
Vincenzo De Vita
Vincenzo Pelusi
Giovanni Antonio Iannantuoni
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.)
Alenia Aermacchi SpA
Original Assignee
Alenia Aeronautica SpA
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 Alenia Aeronautica SpA filed Critical Alenia Aeronautica SpA
Publication of WO2009050651A2 publication Critical patent/WO2009050651A2/fr
Publication of WO2009050651A3 publication Critical patent/WO2009050651A3/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
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
    • B29C70/34—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
    • B29C70/342—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation using isostatic pressure
    • 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 an apparatus for the manufacture of structural elements made of composite material based on carbon fibre, for aircraft construction.
  • pregs the sheets
  • the sheets may be deposited already pre-impregnated with non-polymerized, thermosetting, synthetic resin which serves as binder.
  • the resin is infused after the sheets have been superimposed on the forming tool in the dry state.
  • preform which is constituted by the laminated fibre sheets with the addition of resin, is then covered by a vacuum bag to remove the air and introduced into an autoclave with the application of high temperature and pressure so as to bring about the polymerization of the thermosetting resin matrix and confer the desired shape on the laminated layers.
  • the invention has the dual objective of achieving an excellent final result in the polymerization or curing of composite structural elements, even if they are of considerable size, and of implementing the polymerization process efficiently, quickly and economically, without the use of an autoclave.
  • an apparatus comprises a forming tool 10 with an upper forming surface 11 on which the films C of a reinforcing fibre, typically carbon fibre, are deposited and superimposed, making up a preform.
  • the forming surface may of course adopt any form with various shapes, according to specific requirements.
  • one or more electrical heating resistors are incorporated in the forming tool, and are distributed appropriately so as to heat the forming surface 11 of the tool uniformly and in relatively short periods of time.
  • the tool is closed at the top by an openable or removable cover 13 which has a shape in plan that substantially matches that of the tool.
  • a sealing gasket 14 extends continuously at the interface between the cover and the tool, along the perimeter of the lower edge of the cover.
  • the gasket 14 is preferably engaged in a peripheral groove 15 which extends around the upper surface 11 of the forming tool.
  • At least one suction duct 16 extends through the tool 10 and opens in the forming surface 11 in order to withdraw the air from the carbon- fibre preform C after a vacuum bag V has been placed thereon. Depressurization is performed by means of a vacuum pump 17.
  • an inlet line 18 is provided for the supply of compressed air or other gas pressurized by a pump 19 associated with the apparatus.
  • the inlet line 18 preferably extends through the cover 13.
  • one or more resin-supply ducts 20 may also extend through the tool 10; these ducts open in the forming surface 11 in order to supply the thermosetting resin to the dry preform.
  • the heating of the resistors 12 is controlled by a processing unit, typically a PLC or programmable logic controller equipped with a personal computer, which supervises the operation of the apparatus as a whole and hence also the operation of the vacuum pump 17, of the pressurization pump 19, and of the resin infusion pump 21.
  • the resistors are controlled by the PLC in order to execute one or more tool-heating ramps, after which the carbon-fibre layers are deposited on the forming surface thereof (in the dry state or pre-impregnated with resin).
  • a vacuum bag constituted by a strong film of polymer material is then placed over the laminated layers, the vacuum pump 17 is activated, and the air is removed from the preform. If the preform is dry, the infusion of resin is activated by means of the pump 21. The space inside the cover is then pressurized and the resin is caused to polymerize at a predetermined temperature by supplying electric current to the resistors 12.
  • the PLC enables the basic quantities or parameters for the execution of a polymerization cycle, that is, the pressure, the heating and the vacuum, to be controlled better than in an autoclave.
  • the heating ramps and the pre-heating ramps can be executed with the cover open whilst manual activities are performed, for example, to reposition and adapt the carbon fibres to make them copy the shape of the tool exactly.
  • the apparatus permits working with some flexibility.
  • the resin can also be infused without pressurization, with the cover open and with the resistors switched on.
  • the resistors 12 can be arranged and distributed advantageously so as to ensure uniformity of temperature throughout the composite material. This eliminates a typical disadvantage of the processing of large composites in an autoclave in which temperature differences of more than 3 0 C between one point and another of the tool may give rise to manufacturing defects.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Composite Materials (AREA)
  • Mechanical Engineering (AREA)
  • Casting Or Compression Moulding Of Plastics Or The Like (AREA)
  • Moulding By Coating Moulds (AREA)
  • Ceramic Products (AREA)

Abstract

Cette invention se rapporte à des résistances électriques (12) incorporées dans un outil de formation (10) présentant une surface de formation supérieure (11) sur laquelle on dépose une composition superposée de feuilles de fibres de renforcement (C). Un couvercle pouvant être ouvert (13) est disposé sur l'outil afin de définir un espace hermétiquement clos (22) avec celui-ci. Une pompe à vide (16) extrait l'air de la surface de formation (11) et une conduite d'admission (18) fait entrer de l'air sous pression dans l'espace (22) à travers le couvercle (13). Des conduits d'alimentation en résine facultatifs (20) s'ouvrent dans la surface de formation (11).
PCT/IB2008/054229 2007-10-19 2008-10-15 Appareil de fabrication d'éléments structurels composés d'un matériau composite à base de fibre de carbone, pour la construction d'un avion Ceased WO2009050651A2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
ITTO20070741 ITTO20070741A1 (it) 2007-10-19 2007-10-19 Apparecchiatura per la fabbricazione di elementi strutturali di materiale composito a base di fibra di carbonio per la costruzione di aeromobili.
ITTO2007A000741 2007-10-19

Publications (2)

Publication Number Publication Date
WO2009050651A2 true WO2009050651A2 (fr) 2009-04-23
WO2009050651A3 WO2009050651A3 (fr) 2009-06-25

Family

ID=40314149

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/IB2008/054229 Ceased WO2009050651A2 (fr) 2007-10-19 2008-10-15 Appareil de fabrication d'éléments structurels composés d'un matériau composite à base de fibre de carbone, pour la construction d'un avion

Country Status (2)

Country Link
IT (1) ITTO20070741A1 (fr)
WO (1) WO2009050651A2 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9511519B2 (en) * 2014-02-04 2016-12-06 The Boeing Company System and method of vacuum bagging composite parts

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1629479A1 (de) * 1966-11-18 1971-01-28 Inst Schienenfahrzeuge Verfahren und Vorrichtung zur Herstellung eines stoss- und geraeuschdaempfenden Radkoerpers fuer schnellaufende Schienenfahrzeuge
FR2673571B1 (fr) * 1991-03-07 1994-09-16 Acb Procede de fabrication d'un stratifie constitue de renforts fibreux impregnes de resine thermodurcissable.
DE4123256C1 (fr) * 1991-07-13 1992-10-08 Saint Gobain Vitrage
FR2713979B1 (fr) * 1993-12-21 1996-03-15 Aerospatiale Procédé et dispositif de fabrication de pièces stratifiées injectées basse pression, notamment à emboutis profonds.
US6017484A (en) * 1997-01-21 2000-01-25 Harold P. Hale Method for manufacture of minimum porosity, wrinkle free composite parts
DE10150659A1 (de) * 2001-10-17 2003-05-08 Kraft Uwe Vorrichtung zur Herstellung von Kunststoffbauteilen
ITVI20060032A1 (it) * 2006-01-31 2007-08-01 Selle Royal Spa Metodo per la realizzazione di supporti elastici integrali

Also Published As

Publication number Publication date
WO2009050651A3 (fr) 2009-06-25
ITTO20070741A1 (it) 2009-04-20

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