• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    A method of repairing sandwich panels made of composite materials after an impact having damaged the core of this panel, characterized in that it comprises the acquisition of a digital model of the shape of the damaged zone, and then the realization by a method stereolithography from the digital model, a replacement core (14), or a mold (10) in which this replacement core is to be molded, then the production of a replacement part (18) comprising this soul, then the establishment of this piece which is fitted inside an opening (6) cut in the sandwich panel around the damage, and finally the attachment of the replacement part on the panel.
    公开号:FR3013634A1
    申请号:FR1361761
    申请日:2013-11-28
    公开日:2015-05-29
    发明作者:Arnaud Delehouze；Jean-Philippe Mucherie
    申请人:Aircelle SA；
    IPC主号:
    专利说明:

    [0001] The present invention relates to a method for repairing sandwich panels made of composite materials, as well as a sandwich panel and a turbojet engine nacelle repaired with such a method. Composite sandwich panels, having a central core covered by two outer skins, constitute a reduced mass assembly having a high rigidity. Any form of panels can be made which are more and more used, especially in the aeronautical field. This type of panel is particularly used in nacelles containing a turbojet engine, in order to produce rigid structures comprising good aerodynamic profiling. The production of these panels generally comprises the manufacture of a core which may be a rigid foam, or a structure having transverse honeycomb-shaped cells, made of plastic or aluminum alloy in particular, which is draped in fold-forming resin-impregnated fibers constituting a skin on each side. This set is then pressed into a mold and baked in an oven to cure the resin. Panels of any shape having a particular strength which can be adjusted by defining the thickness of the core as well as the nature and the number of pleats arranged locally on each face are obtained. In the event of a major impact on this type of sandwich panel, used in particular in the aeronautical field, causing damage to the core, in particular a through perforation of the panel, then the complete panel is usually replaced in order to have a piece of Replacement with similar strength, shape and appearance characteristics. However, these replacements may require a delay in the supply of the new parts, which must then be manufactured if no parts are available in stock. In addition, the cost of a new part can be relatively expensive, the environmental impact of a discarded whole part is important, and the complete change of the part can give a bad image to the customers.
    [0002] The present invention is intended to avoid these disadvantages of the prior art. To this end, it proposes a process for repairing sandwich panels made of composite materials comprising a core receiving a skin on each face, after a shock having damaged the core or a skin of this panel, which is remarkable in that it comprises the acquisition a numerical model of the shape of the damaged zone, then the realization by a method of stereolithography from the numerical model, a soul and / or a replacement skin, or a mold in which one goes mold this replacement soul and / or a mold in which one will mold this replacement skin on which will be glued a soul, then the realization of a replacement part including this soul and / or this skin, then the setting place this piece which is fitted inside an opening cut in the sandwich panel around the damage, and finally fixing the replacement part on the panel. An advantage of this repair method is that from a digital model of the form received from the manufacturer of the panel, or acquired directly by measurements on the damaged panel, it is possible to carry out in a simple and rapid manner by the stereolithography method. , without delay of supply of particular parts, a mold or a soul corresponding exactly to the shape of the damaged zone. This mold or core then makes it possible to produce the replacement part comprising the original shapes, which will economically replace only the area of the damaged panel.
    [0003] The repair method according to the invention may further comprise one or more of the following features, which may be combined with one another. In one embodiment, stereolithography provides a mold or core and / or replacement skin from resin polymerization under the effect of light and heat.
    [0004] According to another embodiment, the stereolithography produces a mold, or a core and / or a metal or ceramic skin, from powder mixtures with a paste composed of photosensitive resin. In particular, the repair method may provide a porous core and / or metal skin. This soul and / or skin may advantageously have similar characteristics to those of the soul and / or skin of origin. Advantageously, the method according to the invention can produce a porous metal replacement core. Advantageously, the repair method realizes the replacement part by covering the replacement core with first layers of folds which are draped over it, the set of folds constituting at least a part of at least one of the two skins of the sandwich panel to repair. This soul can be reinforced to prepare the replacement piece. The ply layers can be draped directly onto the mold. The replacement part is fixed by mechanical splicing on the panel to be repaired, that is to say it is fixed via at least one metal or composite junction piece fixed on the replacement part and on the sandwich panel to be repaired by fasteners passing right through the sandwich panel or not. Advantageously, the repair method realizes the attachment of the replacement part in the opening of the panel, by the removal of cover folds on both sides of the panel. We thus obtain a continuity of the two skins of the panel which gives it its rigidity. The invention also relates to a sandwich panel made of composite materials comprising a core receiving a skin on each face, this panel having received a replacement part fitted into an opening to carry out a repair, with a repair method comprising one Any of the foregoing features. The invention furthermore relates to a turbojet engine nacelle provided for an aircraft, comprising sandwich panels made of composite materials comprising a core receiving a skin on each face, this panel having received a replacement part fitted into an opening to carry out a repair. , with a repair method comprising any of the preceding features.
    [0005] The invention will be better understood and other features and advantages will appear more clearly on reading the following description given by way of example, with reference to the appended FIG. 1 which is a diagram showing a method of repair according to FIG. 'invention. FIG. 1 presents in a first step A a sandwich panel having a core 2 comprising on each face a skin 4 made of composite materials. The sandwich panel has a particular curvature made by molding before the firing of the composite materials, this molding also giving a smooth and regular surface condition. In particular, it is possible to form panels constituting ferrules 15 forming external or internal surfaces of aircraft nacelles, which have neat aerodynamic shapes providing good efficiency. The panel received in a curvature a significant shock, forming a damaged area with a bore 6 through it completely. In a second step B is made around the damaged area 20 a cutout over the entire thickness of the panel to retain only the healthy and undistorted part of this panel, to form an opening 6 comprising a contour of simple shape, with cutting edges perpendicular to the surface 8 which are net. A subsequent step C which can be carried out in parallel comprises the production of a digital file which can be the recovery of digital plans from the original manufacturer of the panel, such as a CAD model used in drawing or manufacturing this panel. panel, or reconstitution 24 of a digital plane from measurements made directly on the damaged panel. According to a first embodiment, a following step D comprises the production of a mold 10 from the digital file, made by a stereolithography method, which comprises a smooth inner surface 12 having a curvature corresponding to that of the panel in its damaged part. A next step E comprises the production of a core 14 and / or a repair skin in the mold 10, from known materials and molding methods, covering a surface at least equal to the opening of the panel 6 to be replaced; the repair skin 4 is intended to be glued to a core (2, 14). According to a second embodiment, as a variant of these last two steps D, E, a core 14 and / or a skin 4 obtained also by the stereolithography process is produced directly in another step F, and likewise comprising a curvature corresponding to that of the panel in its damaged part. Stereolithography is a technique also called rapid prototyping, which makes it possible to manufacture solid objects from a digital model, by superimposing thin slices of material. The three-dimensional numerical model is cut into thin slices of constant thickness, including a two-dimensional contour. This thickness chosen by the operator determines the resolution of the restitution, and therefore the accuracy of the object that will be produced. There are several methods of stereolithography. The oldest method is photopolymerization, based on the properties of some resins to be polymerized under the effect of light and heat. The resin used is generally a mixture of acrylate or epoxy monomers, and a photoinitiator which initiates the polymerization of the material under the effect of light. In this process a mobile platform immersed in a liquid resin tank, supports the model being manufactured. A fixed laser has a beam control device, and another orientation of this beam to direct it to any point of the platform. The slices constituting the model are then processed one by one. The laser beam scans the liquid resin surface according to the shape of the software defined wafer to solidify a wafer by making a solid polymer. The platform then descends from a height corresponding to the thickness of the slice according to the chosen resolution, and the process is renewed to form a new slice fully integral with the previous one.
    [0006] After rinsing the obtained pattern to remove the unpolymerized resin, the last step involves baking the object to harden it. A method developed more recently makes it possible to produce metal or ceramic parts by mixing the corresponding powders with a paste composed of photosensitive resin.
    [0007] The mixture, once insolated by the laser radiation, forms a polymer network that traps the mineral particles. At the end, a heat treatment of the object makes it possible to obtain a dense ceramic. With this latter method it is thus possible to carry out directly in step F a core 14 made of metallic or ceramic materials, which may be porous or non-porous, precisely reproducing the original part of the core of the panel which has been removed. After one of the two embodiments of the core 14, a subsequent step G comprises the preparation of a replacement part 18 comprising this core, which is covered if necessary with first layers of folds 16 which are draped over it and undergo a first firing, in order to give this piece some resistance. If necessary, the cutout of the contour of the replacement part 18 is touched up to ensure its fit in the opening of the panel 6.
    [0008] The last step H comprises the adjustment of the replacement part 18 in the opening of the panel 6, then the fixing of this part by a known connection means, comprising for example the removal of cover plies 20 on both sides. of the panel to obtain maximum strength of the assembly.
    [0009] A repaired panel is thus obtained which has regained the integrity of its inner core and / or external skin (s), and which may have characteristics similar to those of the original panel, particularly with regard to the properties mechanical, aerodynamic and acoustic. In particular for panels undergoing different types of specific constraints, such as panels of a turbojet engine nacelle for which the mass, and aerodynamic performance as well as acoustics given by particular forms that must be respected, are important, this type of quick and economical repair is particularly suitable.
    权利要求:
    Claims (10)
    [0001]
    CLAIMS1 - Process for repairing sandwich panels made of composite materials comprising a core (2) receiving a skin (4) on each face, after an impact having damaged the core of this panel, characterized in that it comprises the acquisition of a numerical model of the shape of the damaged area, then the realization by a stereolithography method from the numerical model, a core (14) and / or a replacement skin, or a mold (10). ) in which we will mold this replacement core and / or a mold in which we will mold this replacement skin, then producing a replacement part (18) comprising the core (14) and / or this skin replacing, then the establishment of this piece which is fitted inside an opening (6) cut in the sandwich panel around the damage, and finally the attachment of the replacement part on the panel.
    [0002]
    2 - A repair method according to claim 1, characterized in that the stereolithography produces a mold (10) or a core (14) and / or a replacement skin from a polymerization of resins under the effect of light and heat.
    [0003]
    3 - A repair method according to claim 1, characterized in that the stereolithography produces a mold (10), or a core (14) and / or a metal or ceramic skin, from mixtures of powders with a paste composed of resin photosensitive.
    [0004]
    4 - A method of repair according to claim 3, characterized in that it 25 carries a core (14) of porous metal replacement.
    [0005]
    5 - A method of repair according to claim 4, characterized in that it realizes the replacement part (18) covering the core (14) of replacement first layers of folds (16) which are draped over, all plies constituting at least a portion of at least one of the two skins of the sandwich panel to be repaired.
    [0006]
    6 - Repair method according to claim 5, characterized in that the ply layers (16) are draped directly on the mold (10) of the core (14) replacement.
    [0007]
    7 - Repair method according to any one of the preceding claims, characterized in that the replacement part is fixed by mechanical splicing on the panel to be repaired.
    [0008]
    8 - Repair method according to any one of the preceding claims, characterized in that it carries out the attachment of the replacement part (18) in the opening of the panel (6), by the removal of plies 10 overlap ( 20) on both sides of the panel.
    [0009]
    9 - Composite sandwich panel comprising a core (2) receiving a skin (4) on each face, this panel having received a replacement part (18) fitted into an opening (6) to carry out a repair, characterized in that the repair method is carried out according to any one of the preceding claims.
    [0010]
    10 -Nacelle turbojet provided for an aircraft, comprising composite sandwich panels comprising a core (2) receiving a skin (4) on each side, this panel having received a replacement part (18) fitted into an opening (6). ) for performing a repair, characterized in that the repair method is carried out according to any one of claims 1 to 8.
    类似技术:
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    同族专利:
    公开号 | 公开日
    FR3013634B1|2020-02-28|
    WO2015079146A1|2015-06-04|
    EP3074210A1|2016-10-05|
    CA2930372A1|2015-06-04|
    US20160263845A1|2016-09-15|
    CN105764676A|2016-07-13|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    EP1985538A2|2007-04-24|2008-10-29|United Technologies Corporation|Using a stiffener to repair a part for an aircraft engine.|
    US20090188748A1|2008-01-24|2009-07-30|Honeywell International Inc.|Noise suppression panels and repair methods therefor|
    WO2012062253A2|2010-09-25|2012-05-18|Mtu Aero Engines Gmbh|Device for producing, repairing, and/or replacing a component by means of a powder that can be solidified by energy radiation, and a method and a component produced according to the method|FR3075690A1|2017-12-22|2019-06-28|Safran Nacelles|PROCESS FOR REPAIRING SANDWICH PANELS OF COMPOSITE OR METAL MATERIALS WITH AN ADDITIVE PRODUCTION PROCESS|
    FR3091495A1|2019-01-07|2020-07-10|Safran Nacelles|Method for repairing an acoustic attenuation panel and acoustic attenuation panel repaired with such a method|
    FR3101808A1|2019-10-09|2021-04-16|Safran Nacelles|Repair by suture of a sandwich panel|
    ES2870479T3|2016-11-11|2021-10-27|Airbus Operations Gmbh|Method for reconditioning a damaged part of a component and insert for it|
    RU2664620C1|2017-10-20|2018-08-21|Российская Федерация, От Имени Которой Выступает Министерство Промышленности И Торговли Российской Федерации|Polymer composite materials three-layer panels repairing method|
    FR3073448B1|2017-11-16|2022-02-04|Safran Nacelles|METHOD FOR REPAIRING A COMPOSITE PROFILE|
    法律状态:
    2015-10-30| PLFP| Fee payment|Year of fee payment: 3 |
    2016-09-29| PLFP| Fee payment|Year of fee payment: 4 |
    2017-11-09| PLFP| Fee payment|Year of fee payment: 5 |
    2018-03-02| CD| Change of name or company name|Owner name: SAFRAN NACELLES, FR Effective date: 20180125 |
    2019-10-22| PLFP| Fee payment|Year of fee payment: 7 |
    2020-10-21| PLFP| Fee payment|Year of fee payment: 8 |
    2021-10-20| PLFP| Fee payment|Year of fee payment: 9 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1361761|2013-11-28|
    FR1361761A|FR3013634B1|2013-11-28|2013-11-28|METHOD FOR REPAIRING SANDWICH PANELS IN COMPOSITE MATERIALS COMPRISING THE REALIZATION OF A CORE OR MOLD BY STEREOLITHOGRAPHY|FR1361761A| FR3013634B1|2013-11-28|2013-11-28|METHOD FOR REPAIRING SANDWICH PANELS IN COMPOSITE MATERIALS COMPRISING THE REALIZATION OF A CORE OR MOLD BY STEREOLITHOGRAPHY|
    EP14821730.0A| EP3074210A1|2013-11-28|2014-11-21|Method for repairing sandwich panels made of composite materials involving the creation of a core or of a mould using stereolithography|
    CA2930372A| CA2930372A1|2013-11-28|2014-11-21|Method for repairing sandwich panels made of composite materials involving the creation of a core or of a mould using stereolithography|
    CN201480064377.1A| CN105764676A|2013-11-28|2014-11-21|Method for repairing sandwich panels made of composite materials involving the creation of core or of mould using stereolithography|
    PCT/FR2014/052994| WO2015079146A1|2013-11-28|2014-11-21|Method for repairing sandwich panels made of composite materials involving the creation of a core or of a mould using stereolithography|
    US15/164,913| US20160263845A1|2013-11-28|2016-05-26|Method for repairing sandwich panels made of composite materials involving the creation of a core or of a mould using stereolithography|
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