WO2011070204A1 - Procédé de compactage d'une pièce de matériaux composites - Google Patents

Procédé de compactage d'une pièce de matériaux composites Download PDF

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Publication number
WO2011070204A1
WO2011070204A1 PCT/ES2010/070690 ES2010070690W WO2011070204A1 WO 2011070204 A1 WO2011070204 A1 WO 2011070204A1 ES 2010070690 W ES2010070690 W ES 2010070690W WO 2011070204 A1 WO2011070204 A1 WO 2011070204A1
Authority
WO
WIPO (PCT)
Prior art keywords
layer
properties
membrane
double
sided tape
Prior art date
Application number
PCT/ES2010/070690
Other languages
English (en)
Spanish (es)
Inventor
Gerardo GONZÁLEZ FERNÁNDEZ
Víctor SÁNCHEZ MONTES
Original Assignee
Airbus Operations, S.L.
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 Airbus Operations, S.L. filed Critical Airbus Operations, S.L.
Priority to ES10835527T priority Critical patent/ES2908947T3/es
Priority to EP10835527.2A priority patent/EP2511079B1/fr
Priority to CN201080063553.1A priority patent/CN102741040B/zh
Priority to RU2012128931/05A priority patent/RU2540657C2/ru
Publication of WO2011070204A1 publication Critical patent/WO2011070204A1/fr
Priority to US13/493,637 priority patent/US8932427B2/en

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
    • B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
    • B29C70/544—Details of vacuum bags, e.g. materials or shape
    • 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
    • B32B37/10—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the pressing technique, e.g. using action of vacuum or fluid pressure
    • B32B37/1009—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the pressing technique, e.g. using action of vacuum or fluid pressure using vacuum and fluid pressure
    • 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
    • B32B37/02—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by a sequence of laminating steps, e.g. by adding new layers at consecutive laminating stations
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/80—General aspects of machine operations or constructions and parts thereof
    • B29C66/82—Pressure application arrangements, e.g. transmission or actuating mechanisms for joining tools or clamps
    • B29C66/826—Pressure application arrangements, e.g. transmission or actuating mechanisms for joining tools or clamps without using a separate pressure application tool, e.g. the own weight of the parts to be joined
    • B29C66/8266—Pressure application arrangements, e.g. transmission or actuating mechanisms for joining tools or clamps without using a separate pressure application tool, e.g. the own weight of the parts to be joined using fluid pressure directly acting on the parts to be joined
    • B29C66/82661—Pressure application arrangements, e.g. transmission or actuating mechanisms for joining tools or clamps without using a separate pressure application tool, e.g. the own weight of the parts to be joined using fluid pressure directly acting on the parts to be joined by means of vacuum
    • 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
    • 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
    • B32B37/10—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the pressing technique, e.g. using action of vacuum or fluid pressure
    • B32B37/1018—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the pressing technique, e.g. using action of vacuum or fluid pressure using only vacuum

Definitions

  • the present invention refers to a process of compacting a piece of composite materials, which aims to simplify the compaction process by reducing the number of necessary phases that are required to make compaction, which also has a lower cost in obtaining the product.
  • the invention is applicable in any process in which it is required to carry out the compaction of a piece of composite materials, and more particularly in the aeronautical industry in obtaining parts, which determine the coating of many of the parts of the aircraft.
  • Said covering consists of a base piece constituted by a laminate called leather and a set of pieces that stiffen said skin, and which are called elementary pieces, such as rib ties, stringers, cords, etc.
  • the laminate that constitutes the skin is obtained by stacking several layers of composite materials, either manually or in an automatic machine. Likewise, different elementary pieces are obtained: rib ties, stringers, cords, etc., which together with each other and together with the base skin, form a complete lining.
  • a compaction process of several layers of composite materials on a tool, also called a cradle, to allow the correct stacking, also known as curb or laminated, of the different layers that constitute the skin.
  • a tool also called a cradle
  • curb or laminated the correct stacking
  • a release agent is first applied to the skin manufacturing tool to prevent the piece of skin from sticking to it.
  • the curing of the release agent is then carried out by applying heat.
  • the remains of cured release agent are cleaned from the tool and then another layer of release agent is applied.
  • a layer with adhesive properties is spread over the tool over the entire surface corresponding to the dimensions of the leather piece, for which the layer with adhesive properties must have dimensions at least slightly greater than those of said piece of skin.
  • the objective of this layer is to fill the pores that could remain on the exposed face of the coating and thus leave a completely smooth surface.
  • a first compaction is made in which a vacuum paste is glued around the tool and then an air blanket formed by a separating film and a aerator fabric The blanket is used for the vacuum to circulate equally at all points and should have dimensions greater than the area of compaction of the leather piece.
  • the compaction bag is lifted leaving the plastic attached to one of the sides of the tool and the aerated blanket is removed. Once the interior of the bag has been discovered, all those patterns of composite materials that must be introduced in the preparation prior to the curb of the laminate are positioned where, for mechanical and / or design needs, it corresponds, such as areas that must incorporate rivets.
  • a layer with conductive properties is mounted on the entire surface of the leather piece to give electrical continuity to it.
  • This layer can have a pre-impregnated mesh configuration, in which case the protective paper that incorporates said layer with conductive properties on the opposite side of the tool is left, that is, facing upwards, and a new compaction is performed.
  • the aerator blanket must be extended again and the vacuum bag must be closed and then the vacuum valve must be connected to the compressor.
  • the conductive layer can also have a pattern-shaped configuration or any other geometry, in which case it is positioned in the corresponding place and following the assembly specifications specified by the manufacturer and compaction is performed by applying the vacuum in the bag.
  • the compaction bag is lifted leaving the plastic attached to one of the sides of the tool and the aerated blanket is removed, then detach the protective paper from the layer with conductive properties and the cut is made if it proceeds from it according to the contour presented by the piece of leather, for which the entire contour is fastened with American tape.
  • sheets are positioned that stiffen certain areas, which are located in those points where you need greater structural rigidity, such as the ribs that assemble one piece of lining with another through the rib ties. Finally, these sheets are covered if appropriate with a new layer with adhesive properties of similar dimensions.
  • the aerated blanket is replaced and the bag is closed and then applied vacuum and compacted the last layers. Then the curb is performed, of the skin on the tool. If the taping of the layers that constitute the skin is done by hand, the compacting bag is removed after approximately 10 minutes as well as the aerated blanket and the wrapping process begins. Since this process takes several compacted, the steps in which the aerator blanket is placed are repeated and the bag is closed to subsequently apply vacuum and compact the last layers, as well as remove the compacting bag and the aerator blanket after approximately 10 minutes . If the layer wrapping process occurs in an automatic machine, the tool remains connected to the compressor until the wrapping machine is laminated onto the previously compacted layers on the compacted layers.
  • the plastic layer is used which together with the vacuum rubber constitutes a vacuum bag.
  • This configuration determines that punctures or cracks may appear in the plastic that cause the bag to lose its emptiness, so it is necessary to search for the location of the puncture to repair it, and in the event that there are multiple or multiple slits. punctures, it is necessary to remove the bag and put a new one.
  • the invention provides a new compaction process that avoids the placement of the vacuum paste and the use of plastic, for which once the layer with adhesive properties has been applied on the release agent, the invention avoid applying the paste of vacuum, for which instead of a plastic bag uses a membrane with elastic properties that has high vacuum stability and maximum durability so it can be reused almost unlimited number of times which prevents generation of waste materials.
  • the process of the invention presents the novelty that after applying a layer with adhesive properties on the release agent, an aerated blanket is spread along the layer with adhesive properties, with dimensions greater than said layer with adhesive properties, and then an elastic membrane is spread over the entire surface of the tool, so that this membrane includes a vacuum valve to remove the air between the membrane and the tool and the layer is compacted with adhesive properties, maintaining the vacuum for the time required to effect the compaction of said layer with adhesive properties.
  • the compaction process is simplified, apart from the fact that the generation of waste materials is avoided, as well as the logistic expenses originated for transporting materials, both for their new use, and for their subsequent recycling.
  • the invention comprises a subsequent phase in which the removal of the membrane and the aerator blanket is carried out, so that then patterns of composite materials are positioned in areas where the piece of skin to be obtained needs greater rigidity.
  • a layer with conductive properties (8) is then mounted, which can be a standard layer, a prepreg layer, a prepreg pattern layer or a prepreg mesh layer.
  • a mesh-shaped layer In the case where a mesh-shaped layer is mounted, one of its faces is protected by a protective paper, which is mounted on the surface of the layer with compacted adhesive properties, leaving the protective paper arranged on the opposite side of the tool. , leaving the mesh protruding an excess part with respect to the contour of the double-sided tape.
  • a double-sided tape with protective plastic is placed throughout the contour that defines the piece to be obtained, overlapping it with the layer with adhesive properties, so that the double-sided tape does not fit within the contour of the piece to be obtained.
  • the overlapping of the double-sided tape with the layer with adhesive properties is made between 2 and 5 mm.
  • the aerated blanket is then extended again and the protective plastic is removed from the double-sided, to then extend the membrane and perform a second compaction by removing the air between the membrane and the tool, so that the compaction is maintained until adhesion of the mesh to the layer with adhesive properties occurs, to the patterns of composite materials and double-sided tape.
  • the membrane and the air blanket are then removed and the protective paper is removed from the mesh so that the excess of the mesh is then cut according to the contour of the double-sided tape and with the aid of said contour of the tape double sided
  • the phases of removal of the membrane are carried out by winding it in a cylindrical tubular body, so that the removal of the elastic sheet is facilitated, as well as its subsequent location to effect a new compaction.
  • Figure 1. Shows a schematic perspective view of a tool, in which after applying the release agent the layer with adhesive properties with dimensions greater than those of the piece has been applied of coating to obtain.
  • Figure 2. Shows a view equivalent to the previous figure in which the aeration blanket has been arranged.
  • Figure 3. Shows a view equivalent to the previous figure in which the vacuum is applied to effect the compaction of the layer of adhesive properties by incorporating the membrane onto the aeration blanket.
  • Figure 4.- Shows the phase in which after removing the aeration blanket and the membrane, the double-sided tape overlapped with the layer with compacted adhesive properties is arranged.
  • Figure 5. Shows the phase in which the layer with conductive properties in the form of a mesh is arranged.
  • Figure 6.- Shows the phase in which the mesh is compacted.
  • Figure 7.- Shows the phase in which the mesh has been compacted and the sheet of paper that covers it is removed.
  • Figure 8.- Shows a view in which the cutting of the excess of the compacted mesh begins.
  • Figure 9. Shows a view in which the complete cutting of the excess of the mesh has been made, according to the contour of the double-sided tape.
  • Figure 10. Shows a view according to section A-B of the previous figure.
  • a release agent is applied on the surface of the tool 1.
  • the most commonly used release agents are Frekote 33, Relay All 75, Ram 225, water, etc., the application of the release agent is carried out in a manner homogeneous, uniform and in accordance with the following instructions:
  • the tool 1 is rubbed with a clean cloth, until the possible roughness and opaque appearance of it are eliminated.
  • a layer with adhesive properties 2 is applied.
  • the layer 2 is applied on a surface that exceeds the limits of the skin part of the coating 3, which has been represented by an imaginary line of dashes and dots. . Therefore, before applying layer 2, the contour to be adopted by the final coating piece must be known.
  • This layer 2 has the function of filling the pores that may remain on the face of the piece and thus leave a completely smooth surface.
  • a first compaction is carried out, for which an air blanket 4 formed by a separating film and an aerator fabric is extended along the tool.
  • Blanket 4 has the function of allowing the vacuum circulate equally in all the points of the tool 1 and must have dimensions greater than those of the compaction zone, in this case the one constituted by the previous layer 2.
  • a membrane with elastic properties 5 is then extended over the entire surface of the tool 1, which by means of a vacuum valve 6 is connected to a vacuum rubber 11 which in turn is connected to a compressor (not shown), so The air is then removed from the inside of the membrane 5, comprised between it and the tool 1 and the layer 2 and the aeration blanket 4 assembled previously are compacted. To achieve an optimum vacuum, make sure that there are no folds in the membrane 5 and no elements protrude inside the tool 1.
  • the vacuum is applied for approximately 10 minutes at -600 mm / Hg, to achieve the correct compaction of layer 2.
  • the membrane 5 is then wound in a cardboard strip 12 for later storage and the aerated blanket 4 is removed by folding it and leaving it in a clean place.
  • composite material patterns (not shown) are positioned, which are mounted in the areas where it is required due to mechanical and / or design needs, such as in the assembly areas with the adjacent cladding pieces.
  • the process continues by placing a double-sided tape 7 around the contour of layer 2, overlapping with it between 2 and 5 mm.
  • the double-sided tape 7 should never fit within the contour 3 that constitutes the skin part of the skin.
  • a layer with conductive properties 8 is then mounted, for example in the form of a mesh with dimensions that exceed the contour of the double-sided tape 7, leaving the protective paper 9 of the mesh 8 on the opposite side of the tool 1.
  • the aerator blanket 4 is extended again and removed the protective plastic of the double-sided tape 7, to then extend the membrane with elastic properties 5 again by unwinding it from the cardboard strip 12 and the vacuum valve 6 is connected to the compressor by means of the hose 11. As in the previous case to achieve an optimal vacuum, make sure that there are no folds in the membrane 5 and no elements protrude inside the tool 1.
  • the compacting is applied on the mesh 8 for approximately 10 minutes at -600 mm / Hg, and then the membrane 5 is rewound in the cardboard strip 12 for later storage and the aerator blanket 4 is removed.
  • sheets that stiffen certain areas of the skin are positioned, normally their situation coincides with the assembly of elements such as the pieces that assemble one piece of lining with another, through the joining elements, and finally these sheets are covered with a new layer of adhesive properties of similar dimensions.
  • the membrane 5 When the skin is laminated by hand, the membrane 5 is wound, for example in a cardboard strip and the aerated blanket 4 is removed, to hand laminate the layers that constitute the laminate of the skin. Once finished, the aerator blanket 4 is extended as well as the membrane 5, applying the vacuum that allows the compaction of the last stacked layers. Since the manufacture of the skin by hand requires more compaction between layers, the steps described above are repeated. However, if the skin laminate is stacked in an automatic machine, the tool 1 remains continuously connected to the vacuum net until it enters said machine, which encloses a laminate constituting the skin of the skin above the previously compacted layers. coating, which will be reheated later.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Chemical & Material Sciences (AREA)
  • Composite Materials (AREA)
  • Laminated Bodies (AREA)
  • Lining Or Joining Of Plastics Or The Like (AREA)

Abstract

L'invention porte sur un procédé de compactage d'une pièce de matériaux composites. Ce procédé comprend l'application d'un agent de démoulage sur un dispositif (1) de compactage, la réalisation de son séchage et l'application d'une couche à propriétés adhésives (2) sur l'agent de démoulage. Le procédé est caractérisé en ce qu'il consiste en outre à étendre le long de la couche (2) une couverture aératrice (4) de dimensions supérieures à celles de la couche d'adhésif (2), et à étendre une membrane à propriétés élastiques (5) sur toute la surface du dispositif (1) en appliquant le vide à la membrane (5) pour compacter la couche d'adhésif. Ce procédé permet de réduire le nombre d'étapes requises pour effectuer le compactage et d'éviter la production de matériaux de rebut, le coût dudit procédé étant par conséquent réduit.
PCT/ES2010/070690 2009-12-11 2010-10-26 Procédé de compactage d'une pièce de matériaux composites WO2011070204A1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
ES10835527T ES2908947T3 (es) 2009-12-11 2010-10-26 Proceso de compactación de una pieza de materiales compuestos
EP10835527.2A EP2511079B1 (fr) 2009-12-11 2010-10-26 Procédé de compactage d'une pièce de matériaux composites
CN201080063553.1A CN102741040B (zh) 2009-12-11 2010-10-26 一块复合材料的压紧方法
RU2012128931/05A RU2540657C2 (ru) 2009-12-11 2010-10-26 Способ уплотнения изделия из композиционных материалов
US13/493,637 US8932427B2 (en) 2009-12-11 2012-06-11 Compaction process of a piece of composite materials

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
ESP200931151 2009-12-11
ES200931151A ES2371623B1 (es) 2009-12-11 2009-12-11 Proceso de compactación de una pieza de materiales compuestos.

Related Child Applications (1)

Application Number Title Priority Date Filing Date
US13/493,637 Continuation US8932427B2 (en) 2009-12-11 2012-06-11 Compaction process of a piece of composite materials

Publications (1)

Publication Number Publication Date
WO2011070204A1 true WO2011070204A1 (fr) 2011-06-16

Family

ID=44145133

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/ES2010/070690 WO2011070204A1 (fr) 2009-12-11 2010-10-26 Procédé de compactage d'une pièce de matériaux composites

Country Status (6)

Country Link
US (1) US8932427B2 (fr)
EP (1) EP2511079B1 (fr)
CN (1) CN102741040B (fr)
ES (2) ES2371623B1 (fr)
RU (1) RU2540657C2 (fr)
WO (1) WO2011070204A1 (fr)

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US11097524B2 (en) * 2017-05-26 2021-08-24 The Boeing Company Flexible vacuum securement of objects to complex surfaces
US11312026B2 (en) 2019-10-10 2022-04-26 The Boeing Company Placement and compaction of objects via vacuum
US11904558B2 (en) 2020-10-09 2024-02-20 The Boeing Company Placement and compaction of multiple objects via vacuum heads with floating end effectors

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ES2326542T3 (es) * 2004-06-24 2009-10-14 Meier Solar Solutions Gmbh Laminador.
US20060108058A1 (en) * 2004-11-24 2006-05-25 Chapman Michael R Composite sections for aircraft fuselages and other structures, and methods and systems for manufacturing such sections
DE102006050579B3 (de) * 2006-10-26 2008-03-06 Deutsches Zentrum für Luft- und Raumfahrt e.V. Verfahren zur Herstellung von Faserverbundbauteilen

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Also Published As

Publication number Publication date
CN102741040A (zh) 2012-10-17
EP2511079A1 (fr) 2012-10-17
US8932427B2 (en) 2015-01-13
ES2371623B1 (es) 2012-11-22
EP2511079B1 (fr) 2021-12-29
CN102741040B (zh) 2014-11-26
RU2540657C2 (ru) 2015-02-10
EP2511079A4 (fr) 2017-11-29
ES2908947T3 (es) 2022-05-04
RU2012128931A (ru) 2014-01-20
ES2371623A1 (es) 2012-01-05
US20130153140A1 (en) 2013-06-20

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