• 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:
    The invention relates to a sandwich structure manufacturing method including mechanical and thermal functions, monobloc and multi-materials obtained by metallurgical gradient and variation of the percentages of the components of the alloys or thermoplastic composites used. It makes it possible to obtain the skins and the core of the panel in the same operation and in a single piece, without any other contribution of material than the metal or the alloy or the thermoplastic composite which composes the structure. In addition, mechanical functions such as inserts and thermal functions such as heat pipes, are obtained in the same way, with further variations in the dosage of the metal compounds or composites used in the manufacture, so that the finished product is multi functional, monobloc and multi materials. Thus, compared to the usual technique of bonding components, core, skins, inserts, heat pipes, the overall mechanical and thermal characteristics of the sandwich structure are greatly improved. Brought locally, the variations in the percentages of the components of the alloys or thermoplastic composites used, increase the tenacity, the resistance and the conductivity of the zones in question. The proposed manufacturing method is particularly intended for satellite system and subsystem structures, aircraft structural parts and ship mast components.
    公开号:FR3029833A1
    申请号:FR1402904
    申请日:2014-12-15
    公开日:2016-06-17
    发明作者:Alain Toufine
    申请人:Alain Toufine；
    IPC主号:
    专利说明:

    [0001] The present invention relates to a process for obtaining stiffened structures such as anisotropic panels integrating mechanical and thermal functions as well as the core and the skins obtained. The use of slender anisotropic sandwich structures such as sandwich panels makes it possible to intrinsically obtain significant rigidities by limiting the mass, so that they are of particular interest to the aeronautical, space and naval industry for manufacturing primary structures such as caissons. of wings, walls of satellites, mats. The sandwich panels are generally sets of variable thickness, glued together, composed of a thin lower skin (1), a thick core (2) and a thin upper skin (3). The skins are obtained from metal sheets or materials made of carbon fibers or glass fibers. The cores are made from expanded synthetic foams or for applications with high mechanical stresses, honeycomb (NIDA) which can be micro perforated for aerospace applications. In order to provide mechanical connections to an aircraft structural or wing element or to a satellite wall or sailboat mat, metal or composite carbon fiber inserts are reported inside the sandwich panels. by hot or cold gluing as required (fig 3, 4 and 5). The equipment or the sandwich panels are assembled together with screws. These assemblies are also provided according to the needs by gluing angles made of composite materials. In certain aeronautical and space applications requiring to drain the calories from one area to another, accessories are used such as heat pipes (9) containing a heat transfer fluid or thermal braids or radiators or Pelletier cells. These said heat pipes (11) and radiators are arranged by gluing on the skins (10), either outside the panels or inside. The current manufacturing process of multi functional mechanical and thermal sandwich panels is based on the bonding of the various constituents between them: - The skins (1, 3) on the cores (2), - The inserts (6) inside the panels (8) either flush with the skin or slightly above the skin; it is then about insert flange (7), - the heat pipes (9) inside the panels (10) soul side or outside the panels on the skins, - the radiators on the skins on the faces outside the panel. These collages are, for the most part, under pressure and / or under vacuum, cold or high temperature, requiring the use of heating press or autoclave. Mechanically, the skins are intended to take up the membrane forces parallel to the plane of the panel, and the bending forces. These fluxes of forces are often important and require local reinforcement of the skins by thickening them with 5 doublers internal or external to the skins. These doublers are generally reported by gluing after assembly of the sandwich panel. Mechanically, the role of the soul is to take the shear force flows applied to the panel, to maintain the skins equidistant from each other, to avoid the buckling of the skins and the panel. However, the presence of this core is not useful on the entire panel surface. The resistance and toughness of the skins (1, 3) on the core (2) are degraded with respect to the characteristics of the metallic materials or composite carbon fibers employed by the addition of glue between the skins and the core over the entire panel surface. The zones of the sandwich panel which are very strongly stressed by the multiaxial tensile forces, the bending moments and the shear forces are located at the level of the screw / insert assemblies. This requires the densification of the core with smaller honeycomb cells and greater thickness (18) to add reinforcements of skins of variable size and thickness. The strength and toughness of these areas are degraded with respect to the characteristics of the metal or composite carbon fiber materials employed in providing the glue required for the assemblies. Thermally, the skins of a sandwich panel perform exchange functions by conduction, by radiation or, more rarely, by convection. In this case, the provision of glue to join the skins to the core, to fix the heat pipes and the radiators, strongly alter the characteristics of the materials used, so that it is necessary to use glues loaded with particles of metals. precious like gold, silver for example to allow a good thermal conductivity. Thus, it has been found that, depending on the nature of the materials that compose them, the anisotropic sandwich panels are more or less efficient with respect to mechanical stresses or thermal stresses, and that an insufficient compromise must always be found. It has been found that, for the most part, the sandwich panels manufactured for the aeronautical, space and naval fields consist of a single and homogeneous core of a uniform and repetitive geometry, including in the highly mechanically stressed areas. . It has also been found that, for the most part, sandwich panels have their overall mechanical properties degraded by the provision of adhesives necessary for the various assemblies of skins / souls, screws / inserts, heat pipes / skins, radiators / skins. It has also been found that, for the most part, sandwich panels incorporating thermal functions, the glue formulations used are difficult to implement, expensive in their composition, including precious metals or metallized NanoTube Carbons, and have many advantages. very weak mechanical resistance. It has also been found that, for the most part, the sandwich panels are flat or slightly curved and that in this case the manufacturing processes are long, delicate and complex. It has been found that, for the most part, the manufacture of sandwich panels requires stripping of manual or chemical surfaces, using very toxic products such as sulpho-chromic acid or deoxidation SOCOSURF®. It has also been found that in the case of skins made of carbon fiber composite materials as well as for the adhesives used, the traceability requirements impose great precautions in the material entry controls, the monitoring of expiry dates, the preparation controls adhesives and surfaces, the control of the time of use of these materials and adhesives. Finally for space applications it is necessary to degas the glues. The present invention is based on an initial engineering phase in numerical topological optimization of structures and functional analysis, followed by the use of additive manufacturing techniques by laser sintering or by electron beam of metal powders or synthetic materials. . The object of the present invention is to propose a process for designing, manufacturing and simultaneously obtaining, without the use of any glue: top, bottom and intermediate skins of anisotropic sandwich, metal or composite material panels as required in the recovery of mechanical forces, strong rigidities and small masses, - an anisotropic panel core, or several souls of variable natures, continuous or discontinuous, of variable geometries and variable density throughout the 30 structure, according to the needs for recovery of mechanical forces or local or global thermal drainages, - metal or composite inserts, of variable and optimized shapes, metallurgical compositions or alloys variable with respect to the skins, or density of variable metal charges in the thermoplastic, depending on the need for recovery of mechanical forces or local thermal drainages, 3029833 - 4 - - heat pipes of variable capacities, rectilinear or curved, able to snake in the manner of a network in the plane (2D) of the anisotropic panel but also able to join the upper and lower skins (3D), according to the needs of thermal drainages global and local.
    [0002] The method for manufacturing the stiffened anisotropic panel integrating the mechanical and thermal functions according to the invention is essentially characterized in that it consists in carrying out the following steps: - manufacturing the lower skin in selected dimensions in a metallic or matrix composite material thermoplastic reinforced with metallic charges, - elevating the core to chosen dimensions, in variable forms juxtaposed or not, in variable densities, in the same materials and alloys as the lower skin or in metallurgical dosages or variable components by contribution of molten metal or thermoplastic material, - simultaneously raising in the construction of the core, locally according to the mechanical functions to ensure the densified or massive zones representative of the screwed junctions (inserts), in selected dimensions, in the same materials and alloys as lower skin or in metallurgical dosages or variable components by supplying molten metal or thermoplastic material, - simultaneously raising in the construction of the core, locally according to the thermal functions to fill the heat pipes or heat drains, into selected dimensions of variable shapes in their planes and out of their planes, of the same materials and alloys as the lower skin or in metallurgical dosages or variable components by adding molten metallic or thermoplastic material, - to add the upper skin in selected dimensions, in the same materials and alloys as the In an additional feature of the process according to the invention, the core may have different shapes or profiles over the entire surface of the skin, or in metallurgical or variable metering compositions by adding molten metal or thermoplastic material. anisotropic panel (fig 12): in "coffee cup", hairpin, solid cylinder or hollow, triangle, square, hexagon like the classic honeycomb, and these sections may have varying thicknesses according to the normal to the laying plane. According to another additional characteristic of the method according to the invention, the different shapes of cores thus obtained can be arranged according to the needs of mechanical strength (FIG. 9), juxtaposed with each other or not, over the entire surface of the anisotropic panel. According to another additional feature of the method according to the invention, the densified areas able to receive and to ensure mechanical functions can be arranged according to the needs of mechanical strength (FIG. 10), locally or over the whole of the surface of the anisotropic panel, in cylindrical shapes of constant diameter (6) according to the normal to the laying plane (FIG. 4), or in forms with flanges (7) or in "X solid" shapes more or less pronounced thus making it possible to better distribute the transition of shear and traction forces to the skins of the panel. According to another additional feature of the method according to the invention, the densified zones able to receive and to ensure thermal functions can be arranged according to the global or local dissipation needs and also according to management constraints, over the entire area. the surface of the anisotropic panel, in a 2D plane network snaking on and / or under the skins, or in a 3D network snaking between the lower and upper skins or intermediate (Figure 10). According to another additional characteristic of the process according to the invention, the mechanical or thermal properties or the two sets can be adjusted in zones by means of metallurgical gradients obtained by varying during the manufacturing process the metallurgical percentages of the alloy employed. , or charged metal or thermoplastic materials, thus making the anisotropic panel multi-material. According to another additional characteristic of the process according to the invention, the surface preparations and the gluing of skins, inserts and heat pipes are eliminated. According to another additional characteristic of the method according to the invention, the 3D assemblies of sandwich-type anisotropic panels integrating the mechanical and thermal functions are carried out in a single operation without using a heating press or an autoclave.
    [0003] According to another additional characteristic of the process according to the invention, the control phases after polymerization of the glues are eliminated and replaced by a single final X-ray control. The advantages and characteristics of the process according to the invention will emerge more clearly from the description which follows and which refers to the appended drawing, which represents a non-limiting embodiment thereof. Figures (1) to (7) show the current assembly mode of a stiffened panel incorporating mechanical and thermal functions. FIGS. (8) to (13) show what becomes of the construction of a sandwich panel by the melting of alloyed metal powders, with a variation of the metallurgical percentages of the alloys according to the zone and according to the mechanical and / or thermal function at ensure, with the core of the sandwich panel of any shape and density and adapted to the need for mechanical strength. In the accompanying drawing: - Figure (1) shows an exploded view of the conventional composition of a sandwich panel with the lower skin (1), the upper skin (3) and the central core (2). There may be intermediate skins and intermediate souls not shown. Figure (2) shows the assembled sandwich anisotropic panel (4) by the conventional technique of bonding skins on the core. Figure (3) shows the sandwich panel in which one or more bores (5) and offsets are made at the locations of the structure to receive the mechanical connections to support equipment or to join an adjacent panel. Figure (4) shows an example of a cylindrical insert which is seated in the bore (5) made beforehand in the sandwich panel. The insert can be of very variable shape according to the architecture of the structure and the need for recovery of efforts. The insert is provided with a barrel (6) solid for either screw or let pass a screw, and is respectively threaded or bored. The insert may have at the bottom and / or top a flange (7) which distributes the force torsor on the skins. Figure (5) shows the insert implanted by glue injection in the sandwich panel previously manufactured and bored. The panel integrates the mechanical function (8). Figure (6) shows a rectilinear heat pipe (9) which is characterized by a flat outer geometry to allow gluing on flat areas and hollow inside to allow the passage of heat transfer fluid (usually ammonia). Figure (7) shows the rectilinear heat pipe (9) implanted in the sandwich panel (10) which then integrates the thermal function, the heat pipe being bonded to the lower skin in this figure (11). The bonding of the heat pipe takes place beforehand on the skins. Then the skins are stuck to the soul. The mechanical functions can then be added as described in FIGS. (4) and (5). The insert (12) is attached by gluing in the sandwich panel (10). Figures (8, 9, 10 and 11) show how on manufactured skin (15, 16, 17) on the spot by the additive technology of molten or pre-supplied metallic powders, relate successively by strata but simultaneously of a point From a functional point of view: the core (18, 19, 20) of geometry and density and of variable nature, the insert or inserts (21, 19, 20); 22, 23) of geometries, of variable nature, metallurgical dosage and percentage of alloy different from the skins and souls, where the heat pipe or heat pipes (24, 24bis) of variable shape in the 2D plane or out of the plane to join the lower and upper skins or join an adjacent non-coplanar or inclined sandwich panel, where the upper skin (25) is by laser melting of metal powders, or by laser welding of a previously made skin. The markers (13, 14) represent at different stages of manufacture the supply of successive layers of molten metal material or the laser beam which melts the metal powder arranged in the form of a bed of powder. - Figure (12) shows different types of non-limiting geometries that are to be envisaged to compose the core of the sandwich panel according to the results of numerical analyzes of topological optimization of structures: classical hexagon shape (29), "cup of coffee "inverted or not (30), round, triangle. The density of the core may be any and the cells which make up the core may be disjoint from each other. The heat pipe or heat pipes, or the inserts, are not shown, however their implementation is as described in Figures (8, 9, 10 and 11). - Figure (13) shows the sandwich panel with any core thus manufactured according to the method described in Figures (8, 9, 10 and 11). 20
    权利要求:
    Claims (2)
    [0001]
    CLAIMS 1 °) A method for manufacturing a stiffened anisotropic panel, lightened, incorporating mechanical and thermal functions of performing the following steps: - manufacture the lower skin (15) in selected dimensions of metal or composite material with a filled thermoplastic matrix, - to raise the soul (18) in the same materials as the lower skin, in selected dimensions, in shapes and variable geometries juxtaposed or not, and in variable densities, - to raise simultaneously in the construction of the soul the zones densified (18) or massive providing mechanical junctions (21), in selected dimensions and in variable densities, - simultaneously raising in the construction of the core and densified areas, the heat pipes or heat drains (24), in chosen dimensions, of variable shapes in their planes and out of their planes, - to add the upper skin (25), in dimensions chosen in the same material and alloys as the lower skin, in order to get the functionalized sandwich anisotropic panel.
    [0002]
    2) Method of manufacture according to claim 1, characterized in that the skins (25, 26), the core, the inserts (28), the densified zones (29), the heat pipes and the thermal drains (27) 20 are obtained by melting metal powders or alloys or thermoplastic resins charged with metal, 3 °) Manufacturing method according to claim 2, characterized in that the core, the inserts (28), the densified zones (29 ), heat pipes and heat drains (27), are obtained in a single operation without the use of adhesives, that is to say almost simultaneously, 4 °) Manufacturing method according to claim 3, characterized in that the core, the inserts (28), the densified zones (29), the heat pipes and the heat drains (27) are made of variable geometric profiles such as in the form of the inverted "cup of coffee" or no (30), hairpin, solid or hollow cylinder, triangle, square, or hexagon, 5 °) The manufacture according to any one of claims 2 to 4, characterized in that the profiles and any shapes of the core and the densified areas (29, 30) are adjacent, juxtaposed and joined or non-adjacent and disjoint according to the Resistance to be ensured, 6 °) Method of manufacture according to any one of Claims 1 to 5, characterized in that the inserts (28), the densified areas (29), the heat pipes and the thermal drains (27) are obtained by varying during the manufacture the metallurgical percentages of the alloy or metal employed or the filled thermoplastic composite, 3029833 - 9 - 7) Manufacturing method according to any one of claims 1 to 6, characterized in that that the anisotropic panel thus manufactured is functionalized, multi-material and monobloc.
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    同族专利:
    公开号 | 公开日
    ES2667967T3|2018-05-16|
    FR3029833B1|2016-12-30|
    EP3034208B1|2018-02-07|
    EP3034208A1|2016-06-22|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    DE102008041788A1|2008-09-03|2010-03-11|Airbus Deutschland Gmbh|Sandwich panel with integrated reinforcement structure and method for its production|
    DE102012020671A1|2012-08-27|2014-02-27|Fraunhofer-Gesellschaft zur Förderung der angewandten Forschung e.V.|Producing component for buildings e.g. roof tile by forming generative layer, where component comprises base layer and cover layer and a surface of component is formed with sound insulating structure, which reduces sound propagation|
    EP2730353A1|2012-11-12|2014-05-14|Airbus Operations GmbH|Additive layer manufacturing method and apparatus|RU2713678C2|2016-09-20|2020-02-06|Дженерал Электрик Компани|Reinforced shape of target location in additively manufactured part and corresponding method|
    CN106001568B|2016-07-07|2018-03-13|四川三阳激光增材制造技术有限公司|A kind of functionally gradient materialmetal die 3D printing integral preparation method|
    DE102017214340A1|2017-08-17|2019-02-21|Airbus Operations Gmbh|Process for producing a sandwich component, core for a sandwich component and sandwich component|
    US11260582B2|2018-10-16|2022-03-01|Divergent Technologies, Inc.|Methods and apparatus for manufacturing optimized panels and other composite structures|
    US20210061495A1|2019-08-28|2021-03-04|The Boeing Company|Additively manufactured spacecraft panel|
    US20220048109A1|2020-08-17|2022-02-17|Honeywell International Inc.|Lightweight stiffened panels made using additive manufacturing techniques|
    法律状态:
    2015-12-15| PLFP| Fee payment|Year of fee payment: 2 |
    2016-06-17| PLSC| Search report ready|Effective date: 20160617 |
    2016-12-19| PLFP| Fee payment|Year of fee payment: 3 |
    2017-12-18| PLFP| Fee payment|Year of fee payment: 4 |
    2019-12-24| PLFP| Fee payment|Year of fee payment: 6 |
    2021-09-10| ST| Notification of lapse|Effective date: 20210806 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1402904A|FR3029833B1|2014-12-15|2014-12-15|PROCESS FOR OBTAINING HIGHLY ANISOTROPIC SANDWICH STRUCTURES INTEGRATING MECHANICAL, THERMAL, AND SOUL FUNCTIONS AND SKINS OF STRUCTURES OBTAINED BY METALLURGIC GRADIENT OR COMPOSITE|FR1402904A| FR3029833B1|2014-12-15|2014-12-15|PROCESS FOR OBTAINING HIGHLY ANISOTROPIC SANDWICH STRUCTURES INTEGRATING MECHANICAL, THERMAL, AND SOUL FUNCTIONS AND SKINS OF STRUCTURES OBTAINED BY METALLURGIC GRADIENT OR COMPOSITE|
    ES15200033.7T| ES2667967T3|2014-12-15|2015-12-15|Procedure for obtaining highly anisotropic sandwich structure integrating mechanical, thermal and core functions and structure skins obtained by metallurgical or composite gradient|
    EP15200033.7A| EP3034208B1|2014-12-15|2015-12-15|Method for obtaining highly anisotropic sandwich structure incorporating mechanical and thermal functions, and structure core and skins obtained by metallurgical or composite gradient|
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