WO2003011594A1 - Moule a panneau stratifie et procede de production correspondant - Google Patents

Moule a panneau stratifie et procede de production correspondant Download PDF

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Publication number
WO2003011594A1
WO2003011594A1 PCT/NL2002/000515 NL0200515W WO03011594A1 WO 2003011594 A1 WO2003011594 A1 WO 2003011594A1 NL 0200515 W NL0200515 W NL 0200515W WO 03011594 A1 WO03011594 A1 WO 03011594A1
Authority
WO
WIPO (PCT)
Prior art keywords
mould
pack
layers
panel
fixing means
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/NL2002/000515
Other languages
English (en)
Inventor
Abdoel Faziel Rajabali
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.)
GKN Fokker Aerospace BV
Original Assignee
Fokker Aerostructures BV
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 Fokker Aerostructures BV filed Critical Fokker Aerostructures BV
Publication of WO2003011594A1 publication Critical patent/WO2003011594A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

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
    • B32B7/12—Interconnection of layers using interposed adhesives or interposed materials with bonding properties
    • 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
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/40—Shaping or impregnating by compression not applied
    • B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
    • B29C70/44—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/88—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts characterised primarily by possessing specific properties, e.g. electrically conductive or locally reinforced
    • B29C70/882—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts characterised primarily by possessing specific properties, e.g. electrically conductive or locally reinforced partly or totally electrically conductive, e.g. for EMI shielding
    • B29C70/885—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts characterised primarily by possessing specific properties, e.g. electrically conductive or locally reinforced partly or totally electrically conductive, e.g. for EMI shielding with incorporated metallic wires, nets, films or plates
    • 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
    • B32B15/14—Layered products comprising a layer of metal next to a fibrous or filamentary 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
    • 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
    • B32B38/00—Ancillary operations in connection with laminating processes
    • B32B38/18—Handling of layers or the laminate
    • B32B38/1825—Handling of layers or the laminate characterised by the control or constructional features of devices for tensioning, stretching or registration
    • B32B38/1833—Positioning, e.g. registration or centering
    • 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
    • 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
    • B32B2607/00—Walls, panels

Definitions

  • the invention relates to the production of panels having a laminated structure.
  • Such panels are used in a wide variety of fields.
  • specific characteristics can be obtained, for example with regard to the strength and rigidity.
  • a particular application is in aviation and aerospace technology.
  • the panels used in this field must, on the one hand, have a low weight and, on the other hand, have strength and rigidity characteristics such that they are able to withstand the stresses to which a self-supporting body or wing construction is exposed. Furthermore, they must meet stringent requirements with regard to fatigue strength and toughness.
  • the panels can be produced in various ways.
  • the invention relates in particular to the production of such panels under elevated pressure and temperature.
  • the panels on a mould are covered by a membrane; the pressure is lowered in the gap between the mould and the membrane.
  • the mould prepared in this way is then placed in an autoclave, after which the adhesive contained between the layers is activated.
  • the elevated pressure in the autoclave must ensure that the various layers are held pressed onto one another, such that they are not able to shift with respect to one another during the production process.
  • the adhesive becomes fluid on heating, with the consequence that the layers are able to shift with respect to one another.
  • the reinforcements concerned here can be reinforcements that have to be provided in the vicinity of openings in the panel, such as window and door openings.
  • the aim of the invention is therefore to provide a method for the production of a panel with which the position of the layers with respect to one another is determined more accurately. Said aim is achieved by means of a method for the production of a panel from a laminate that comprises at least two layers of metal and an intermediate layer consisting of an adhesive material, comprising the following steps:
  • the various layers which initially are still lying loosely on top of one another, are fixed with respect to one another by means of, for example, a pin or screw.
  • a pin or screw Such a pin per se fits in the various layers with some tolerance. Consequently, slight shifting of the layers with respect to one another is still possible, but this shifting is so slight, in any event one or more orders of magnitude smaller compared with unrestrained shifting, that an appreciably improved positional accuracy of the various layers with respect to one another is achieved.
  • the invention provides an improved method for the production of a panel from a laminate in which there is a seam with overlapping layers, comprising the following steps:
  • the position of the pack of layers itself with respect to the mould can also be determined. This is important if the mould has an irregular curved shape. Pack shifting then gives rise to an incorrect curved shape of the finished panel. According to the invention this can be prevented if the method comprises the following steps:
  • the holes that are made in the packs can be positioned such that after production of the panel they can also be used for fixing stringers and/or trusses. In this case the holes also do not have to constitute any unnecessary weakening in the panel. In some cases the positioning holes can also be made in those parts of the panel that are subsequently removed, for example at the location of the window and door openings.
  • the invention also relates to a mould for use with the method described above.
  • a known mould of this type has a mould surface onto which at least one pack of layers consisting of metal and adhesive can be placed, which pack has at least one hole through it in which a fixing means can be accommodated.
  • at least one recess for accommodating a fixing means opens at the mould surface.
  • the recess can have an internal screw thread.
  • the invention also relates to a panel produced by means of the method described above.
  • the metal layers consist of aluminium and the layer of adhesive material consists of a glass fibre matrix impregnated with an adhesive.
  • Figure 1 shows two layered packs with overlapping edges.
  • Figure 2 shows a fixing means according to the invention.
  • Figure 3 shows another fixing means.
  • Figure 4 shows a finished panel
  • a panel 1 is produced from a number of metal layers 2 between which layers 3 consisting of a glass fibre matrix with an adhesive embedded therein are accommodated. Packs of this type are accommodated on a mould 4, such as, for example, is shown in Figures 2 and 3. In a known manner a membrane (not shown) is placed over the pack 1, which membrane is joined at the edges to the mould 4 such that it is airtight.
  • a hole 11, 12 is drilled through the packs 5, 6, in which hole pin-shaped fixing means 13 are placed.
  • the individual gaps 14 in the metal layers 2, which together with the holes 15 in the layers 3 of matrix material form the hole 11 through the pack, are oversized to some extent in order to be able to fit the pin-shaped fixing means 16.
  • the tolerance that plays a role here is relatively small, such that accurate positioning of the end edges of the layers 2 is still possible.
  • the pin-shaped fixing means 16 are in the form of a screw and screwed into an insert 17 provided with an internal screw thread.
  • pin-shaped fixing means 16 are provided with a screw head 18; in the illustrative embodiment in Figure 3 pin-shaped fixing means 16 with a flat head 19, the surface of which is in the same plane as that of the stringer 20, is used.
  • the panel 1 obtained in this way can be used as the fuselage section for an aircraft.
  • the trusses 21 can be fixed in place using evenly distributed rivets without there being a relatively large, unfixed region at the location of the seam 10 as a consequence of the position of the end edges of the layers 2 not being accurately determined.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Composite Materials (AREA)
  • Mechanical Engineering (AREA)
  • Laminated Bodies (AREA)
  • Casting Or Compression Moulding Of Plastics Or The Like (AREA)

Abstract

La présente invention concerne un procédé de production d'un panneau (1) à partir d'un stratifié constitué d'au moins deux couches métalliques (2) et d'une couche intermédiaire (3) en matière adhésive. Ce procédé enchaîne les opérations suivantes: disposition d'un moule (4) pour le panneau (1) présentation d'un empilement (5, 6) faisant alterner les couches de métal (2) et de matériau adhésif (3) dans le moule; réalisation d'au moins un trou (11) traversant l'empilement (5, 6); disposition d'un organe de fixation (16) dans chaque trou (11); imposition d'une pression élevée sur l'empilement (5, 6); activation du matériau adhésif (3); enlèvement du panneau (1) du moule (4); enlèvement de chacun des organes de fixation (16).
PCT/NL2002/000515 2001-08-03 2002-07-30 Moule a panneau stratifie et procede de production correspondant Ceased WO2003011594A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
NL1018701 2001-08-03
NL1018701A NL1018701C2 (nl) 2001-08-03 2001-08-03 Werkwijze alsmede vormmal voor het vervaardigen van een gelaagd paneel.

Publications (1)

Publication Number Publication Date
WO2003011594A1 true WO2003011594A1 (fr) 2003-02-13

Family

ID=19773832

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/NL2002/000515 Ceased WO2003011594A1 (fr) 2001-08-03 2002-07-30 Moule a panneau stratifie et procede de production correspondant

Country Status (4)

Country Link
AR (1) AR034957A1 (fr)
NL (1) NL1018701C2 (fr)
TW (1) TW572830B (fr)
WO (1) WO2003011594A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102004037398A1 (de) * 2004-07-30 2006-03-23 Fritz Egger Gmbh & Co Schichtstoff, Bauteil mit einem Schichtstoff sowie Verfahren zu dessen Herstellung
RU2323090C2 (ru) * 2002-11-06 2008-04-27 Сторк Фоккер Аесп Б.В. Способ производства ламинатов из слоев металла и слоев пластика, усиленных волокнами
US20110300333A1 (en) * 2006-07-14 2011-12-08 Airbus Operatios Limited Composite manufacturing method
WO2012035184A1 (fr) * 2010-09-13 2012-03-22 Airbus Operations S.L. Disposition de liaison de pièces de matériau composite à renfort directionnel

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4118814A1 (de) * 1990-06-08 1991-12-19 Hitachi Ltd Verfahren und vorrichtung zum verkleben von mehrlagenplatten
EP1103370A1 (fr) * 1999-11-24 2001-05-30 EADS Airbus GmbH Procédé pour la fabrication d'un profile en matière hibride

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4118814A1 (de) * 1990-06-08 1991-12-19 Hitachi Ltd Verfahren und vorrichtung zum verkleben von mehrlagenplatten
EP1103370A1 (fr) * 1999-11-24 2001-05-30 EADS Airbus GmbH Procédé pour la fabrication d'un profile en matière hibride

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
A. VLOT ET AL: "Towards Application of Fibre Metal Laminates in Large Aircraft", WWW.GLARECONFERENCE.COM, 9-2001, XP002195138 *

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2323090C2 (ru) * 2002-11-06 2008-04-27 Сторк Фоккер Аесп Б.В. Способ производства ламинатов из слоев металла и слоев пластика, усиленных волокнами
DE102004037398A1 (de) * 2004-07-30 2006-03-23 Fritz Egger Gmbh & Co Schichtstoff, Bauteil mit einem Schichtstoff sowie Verfahren zu dessen Herstellung
DE102004037398B4 (de) * 2004-07-30 2011-06-22 Fritz Egger Gmbh & Co. Holzwerkstoffplatte mit einem Schichtstoff und Verfahren zur Herstellung eines Bauteils mit einer Holzwerkstoffplatte
US20110300333A1 (en) * 2006-07-14 2011-12-08 Airbus Operatios Limited Composite manufacturing method
JP2015131487A (ja) * 2006-07-14 2015-07-23 エアバス オペレーションズ リミテッドＡｉｒｂｕｓ Ｏｐｅｒａｔｉｏｎｓ Ｌｉｍｉｔｅｄ 複合パネルの製造方法、及び複合パネルの製造装置
US9764518B2 (en) * 2006-07-14 2017-09-19 Airbus Operations Limited Composite manufacturing method
WO2012035184A1 (fr) * 2010-09-13 2012-03-22 Airbus Operations S.L. Disposition de liaison de pièces de matériau composite à renfort directionnel

Also Published As

Publication number Publication date
NL1018701C2 (nl) 2003-02-04
TW572830B (en) 2004-01-21
AR034957A1 (es) 2004-03-24

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