WO2018114093A1 - Procédé de fabrication additive d'un élément structural en sandwich, élément structural en sandwich et système de levier - Google Patents

Procédé de fabrication additive d'un élément structural en sandwich, élément structural en sandwich et système de levier Download PDF

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Publication number
WO2018114093A1
WO2018114093A1 PCT/EP2017/076828 EP2017076828W WO2018114093A1 WO 2018114093 A1 WO2018114093 A1 WO 2018114093A1 EP 2017076828 W EP2017076828 W EP 2017076828W WO 2018114093 A1 WO2018114093 A1 WO 2018114093A1
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WO
WIPO (PCT)
Prior art keywords
structural component
support structure
support
construction
area
Prior art date
Application number
PCT/EP2017/076828
Other languages
German (de)
English (en)
Inventor
Andreas Nick
Original Assignee
Airbus Defence and Space GmbH
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 Defence and Space GmbH filed Critical Airbus Defence and Space GmbH
Publication of WO2018114093A1 publication Critical patent/WO2018114093A1/fr

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
    • B22F10/20—Direct sintering or melting
    • B22F10/28—Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM]
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
    • B22F10/40—Structures for supporting workpieces or articles during manufacture and removed afterwards
    • B22F10/47—Structures for supporting workpieces or articles during manufacture and removed afterwards characterised by structural features
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B33—ADDITIVE MANUFACTURING TECHNOLOGY
    • B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3-D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3-D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
    • B33Y80/00—Products made by additive manufacturing
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
    • B22F10/60—Treatment of workpieces or articles after build-up
    • B22F10/62—Treatment of workpieces or articles after build-up by chemical means
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
    • B22F10/60—Treatment of workpieces or articles after build-up
    • B22F10/66—Treatment of workpieces or articles after build-up by mechanical means
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F12/00—Apparatus or devices specially adapted for additive manufacturing; Auxiliary means for additive manufacturing; Combinations of additive manufacturing apparatus or devices with other processing apparatus or devices
    • B22F12/50—Means for feeding of material, e.g. heads
    • 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
    • B29C64/00—Additive manufacturing, i.e. manufacturing of three-dimensional [3D] objects by additive deposition, additive agglomeration or additive layering, e.g. by 3D printing, stereolithography or selective laser sintering
    • B29C64/10—Processes of additive manufacturing
    • B29C64/106—Processes of additive manufacturing using only liquids or viscous materials, e.g. depositing a continuous bead of viscous material
    • B29C64/118—Processes of additive manufacturing using only liquids or viscous materials, e.g. depositing a continuous bead of viscous material using filamentary material being melted, e.g. fused deposition modelling [FDM]
    • 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
    • B29C64/00—Additive manufacturing, i.e. manufacturing of three-dimensional [3D] objects by additive deposition, additive agglomeration or additive layering, e.g. by 3D printing, stereolithography or selective laser sintering
    • B29C64/10—Processes of additive manufacturing
    • B29C64/141—Processes of additive manufacturing using only solid materials
    • B29C64/153—Processes of additive manufacturing using only solid materials using layers of powder being selectively joined, e.g. by selective laser sintering or melting
    • 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
    • B29C64/00—Additive manufacturing, i.e. manufacturing of three-dimensional [3D] objects by additive deposition, additive agglomeration or additive layering, e.g. by 3D printing, stereolithography or selective laser sintering
    • B29C64/10—Processes of additive manufacturing
    • B29C64/165—Processes of additive manufacturing using a combination of solid and fluid materials, e.g. a powder selectively bound by a liquid binder, catalyst, inhibitor or energy absorber
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B33—ADDITIVE MANUFACTURING TECHNOLOGY
    • B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3-D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3-D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
    • B33Y10/00—Processes of additive manufacturing
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
    • Y02P10/00—Technologies related to metal processing
    • Y02P10/25—Process efficiency

Definitions

  • the present invention relates to a process for producing a
  • Structural component a structural component and a lever system.
  • Structural components of various kinds such as levers, carriers, containers, fuselage parts for vehicles or the like, are increasingly produced by generative manufacturing or manufacturing processes.
  • Manufacturing processes offer exceptional design freedom and allow, among other things, objects to be produced with manageable effort, which would not be possible to produce using conventional methods or only with considerable effort.
  • 3D printing process starting from a digitized geometric model of an object, one or more modeling materials are sequentially stacked and cured in layers.
  • Component weight can be produced.
  • a method for producing a structural component comprises carrying out a generative production method.
  • a base area of the base area extending in a planar manner takes place
  • the structure of the support elements is such that the support elements within the support structure itself
  • a generative or additive manufacturing process is thus carried out, in which first a planar, e.g. strip, plate or cup-shaped base region or a base layer is constructed in a construction direction of a modeling material.
  • the base region is accordingly produced in the construction direction with a certain thickness.
  • a grid-like support structure in the construction direction is formed from the modeling material. It is thus formed a extending in the body direction scaffold.
  • Generative manufacturing process constructed a plurality of individual support elements which are interconnected and form within the support structure repetitive elementary units, each having the same outer shape.
  • the support elements may be formed in particular rod-shaped or arcuate or generally with an elongated extension.
  • the support elements form edges of a respective elementary unit.
  • the elementary units form open cells. This structure creates a support structure with low weight and high mechanical rigidity.
  • Support structure formed a planar construction area of the modeling material.
  • the construction area and the base area thus overlap one another.
  • the support structure remains after the manufacture of the component between the
  • Base area and the construction area Due to the open-cell, grid-like Design of the support structure, the structural component produced on the one hand only a small additional weight through the support structure. On the other hand, a grid-like structure has a high mechanical strength and thus improves the mechanical strength of the component as a whole. Furthermore, the base area and the building area can be performed by the contribution of the support structure to the mechanical strength with a smaller wall thickness, whereby the component weight is reduced.
  • Support elements with a longitudinal extent in the body direction and second
  • Supporting elements are constructed with a deviating from the body direction longitudinal extent.
  • elongated, e.g. rod-shaped or arc-shaped first support elements which extend approximately in the construction direction
  • elongated, e.g. rod-shaped or arcuate second support elements which extend transversely or obliquely to the direction of construction constructed.
  • Support structure is formed with substantially direction independent high mechanical load capacity. In particular, it can be provided that a deviation from the
  • Assembly direction of the second support elements is in a range between 0.1 mm and 5 mm.
  • the deviation from the construction direction of the second support elements is in a range between 1 mm and 4 mm.
  • the support structure is produced particularly quickly and efficiently with high mechanical strength.
  • the second support elements are reliably generated in this area of the deviation from the construction direction with high quality.
  • the support elements are constructed such that the elementary units are formed as convex polyhedra.
  • a polyhedron is called convex if, for every two points of the polyhedron, the connecting distance between these points lies completely inside the polyhedron. So that support structure is thus constructed as a regular grid, which reduces the production cost and whereby a simple structural design of the structural component is achieved.
  • the elementary units can accordingly the external shape of a polyhedron on ⁇ have, for example, as polyhedron in the form of a cuboid like a hexahedron, an octahedron, a truncated octahedron, a tetrahedron, a double tetrahedron, a polygonal prism, a dodecahedron, an icosahedron, an icosidodecahedron or ,
  • the generative manufacturing process can be a selective
  • short F DM procedures include.
  • a component is built up in layers from the modeling material, for example a plastic (SLS method) or a metal (SLM method), by applying the modeling material in powder form to a substrate and passing it through local laser irradiation is liquefied, resulting in a solid, coherent component after cooling.
  • SLS method plastic
  • SLM method metal
  • EBM method a laser beam is used instead
  • Raster of points according to the component cross-section to be produced applied to a surface The points are made by the liquefaction of a
  • Extrusion produced by means of a nozzle and subsequent curing by cooling The structure of a body is carried out by repeatedly, preferably line by line, traversed a working plane with the nozzle and then the
  • Material combinations are selected for which additive methods are known.
  • a modeling material in particular a metal material, a
  • Plastic material a composite material or a ceramic material can be used.
  • the metal material used is in particular steel alloys, titanium or titanium alloys, aluminum or aluminum alloys or the like
  • plastic material in particular a polyamide or an elastomer, such as thermoplastic polyurethane, can be used.
  • composite material are in this context in particular Understand materials in which fiber material is embedded in a matrix material. These may be in particular fiber-reinforced plastics, such as, for example, carbon fiber-reinforced plastics, or carbon fibers reinforced silicon carbide.
  • fiber-reinforced plastics such as, for example, carbon fiber-reinforced plastics, or carbon fibers reinforced silicon carbide.
  • ceramic material in particular
  • Silicon carbide Al2O3 or the like can be used.
  • a structural component is provided.
  • the structural component can be produced by a method according to one of the embodiments described above.
  • Features and advantages described with reference to the method or the component thus also apply analogously to the respective other object.
  • the structural member has a planar-extending base portion and a planar-extending body portion disposed in a thickness direction spaced from the base portion.
  • the structural component has a between the
  • Base region and the construction area extending grid-like support structure, which is constructed a plurality of support elements.
  • the support elements form within the support structure repetitive elementary units each having the same outer shape.
  • Support structure are integrally formed.
  • the structural component accordingly has a planar, e.g. strip-shaped, plate-shaped or cup-shaped base region and also a flat, e.g. strip, plate or bowl-shaped construction area, wherein the base area and the
  • Build-up area are arranged opposite each other in a thickness direction opposite.
  • a support structure which is integrally formed with the base and the building area.
  • the support structure is formed like a grid.
  • a scaffold extending in the thickness direction, which extends between the base and the body region and mechanically connects them together.
  • the support structure comprises a plurality of individual ones
  • Support structure form repetitive elementary units, each having the same outer shape.
  • the support elements may be formed in particular rod-shaped or arcuate or generally with an elongated extension.
  • the support elements form edges of a respective elementary unit.
  • the elementary units form open cells.
  • This structure creates a support structure with low weight and high mechanical rigidity.
  • the described design of the component is advantageously suitable for manufacture by means of a generative manufacturing process, e.g. the method described above.
  • the grid-like support structure is constructed by first support members having a longitudinal extent in the thickness direction and second support elements with a deviating from the body direction longitudinal extent.
  • first support members having a longitudinal extent in the thickness direction and second support elements with a deviating from the body direction longitudinal extent.
  • they are each oblong, e.g. rod or arcuate first and second support members provided.
  • the first support elements extend approximately in the direction of construction or their
  • the second support elements extend transversely or obliquely to the direction of construction.
  • truss structures can be constructed in a simple manner.
  • This offers the advantage that the support structure is formed with a substantially direction-independent high mechanical load capacity.
  • a deviation from the construction direction of the second support elements is in a range between 0.1 mm and 5 mm.
  • Support elements in a range between 1 mm and 4 mm.
  • the support structure can be produced particularly quickly and efficiently with high mechanical strength by means of a generative production method, for example by the method described above.
  • the support elements may be arranged such that the elementary units are formed as convex polyhedra.
  • the elementary units accordingly have the outer shape of a polyhedron, for example as polyhedra in the form of a cuboid, a hexahedron, an octae ⁇ ders, an octahedral stump, a tetrahedron, a double tetrahedron, a polygonal prism, a dodecahedron, an icosahedron, an icosidodecahedron or similar.
  • a polyhedron for example as polyhedra in the form of a cuboid, a hexahedron, an octae ⁇ ders, an octahedral stump, a tetrahedron, a double tetrahedron, a polygonal prism, a dodecahedron, an icosahedron, an icosidodecahedron or similar.
  • lever system having at least one lever pivotally hinged to a base component, wherein the lever is formed by a structural component according to one of the embodiments described above.
  • the lever system may in particular form a movement device for moving a component mounted on the lever.
  • the lever system as part of a landing gear of an aircraft, a Adjusting device for positioning a wing flap or the like
  • the lever system may be provided as part of a kinematics of a robot.
  • the structural component forming the lever has, in particular, superstructure and base areas extending in a longitudinal direction.
  • the structural component is thus designed in particular as an elongate component.
  • direction indications and axes in particular to directions and axes which relate to the course of physical structures, herein is understood to mean a course of an axis, a direction or a structure "along" another axis, direction or structure, that these, in particular the tangents resulting in a respective position of the structures each at an angle of less than or equal to 45 degrees, preferably less than 30 degrees and
  • a progression of an axis, a direction or a structure is understood to be "transverse" to another axis, direction or structure, that In particular, the tangents resulting in a respective location of the structures each extend at an angle of greater than or equal to 45 degrees, preferably greater than or equal to 60 degrees, and most preferably perpendicular to each other "In one piece" formed components generally understood that these components are present as a single, a material unit forming part and in particular as a such are prepared, wherein one of the other component is not releasable from the other without lifting the material cohesion.
  • FIG. L schematic representation of a method according to a
  • Embodiment of the present invention during the implementation of a first method step
  • Fig. 2 is a schematic representation of the method during the
  • FIG. 3 shows a schematic illustration of the method after completion of the method step illustrated in FIG. 2;
  • FIG. Fig. 4 is a schematic representation of the method during the
  • Fig. 5 is a schematic view of a 3D printing device for
  • FIG. 6 is a perspective view of a structural component according to a
  • Embodiment of the present invention is a perspective view of a structural component according to a
  • Fig. 8 is a schematic representation of a lever system according to a
  • Fig. 9 is a schematic representation of an industrial robot with
  • Fig. 10 is a schematic representation of an aircraft with
  • Lever system according to another embodiment of the present invention.
  • FIG. 1 is a schematic and purely by way of example a sectional view of a
  • Working chamber 3 of a 3-D printing device 2 in the form of an open cavity shown.
  • the working chamber 3 has a work platform 4, which is exemplified as formed by the bottom of the cavity.
  • the method comprises, in particular, the implementation of a generative manufacturing method, for example a selective laser sintering method, an electron beam melting method or a fused deposition modeling method.
  • a surface area 10 of the structural component 1 which extends in a planar manner in a construction direction B from one is produced by means of generative production
  • the base portion 10 is exemplified as a flat layer, which in the construction direction B in layers
  • Modeling material M was produced with a thickness t10.
  • the base region 10 has, in particular, a planar extension transversely to the construction direction B and furthermore extends in a direction transverse to the construction direction
  • the base region 10 of the structural component 1 is shown by way of example as a plate-shaped, planar layer.
  • the structural component 1 shown by way of example in FIG. 5 has a curved, in particular arc-shaped, base region 10.
  • FIGS. 2 and 3 show a further step of the method.
  • a lattice-like support structure 30 is formed.
  • Support elements 31, 32 constructed in the construction direction B on the base portion 10. This is done such that the support elements 31, 32 within the support structure 30 repetitive elementary units 35, each having the same outer shape form.
  • the support members 31, 32 are symbolically represented as straight rods.
  • FIG. 3 shows the completely constructed support structure 30 with its final extent in the direction of construction B. The structure of the individual
  • Supporting elements 31, 32 thus takes place in layers along the construction direction B. This principle can be seen from a comparison of FIGS. 2 and 3.
  • the support members 31, 32 are each as elongated
  • rod-shaped supporting elements 31, 32 can be formed.
  • Fig. 6 shows exemplary support members 31, 32 which are formed as slightly curved, elongated elements.
  • first support elements 31 and second support elements 32 are constructed. As shown particularly in FIGS. 2, 6 and 7, the first
  • Supporting elements 31 constructed with a longitudinal extent in or along the mounting direction B and the second support elements 32 with a deviating from the mounting direction B by a deviation d32 longitudinal extent.
  • the first and second support members 31, 32 thus run obliquely to each other.
  • a branched support structure 30 is generated, whereby the mechanical stability of the support structure 30 is improved.
  • the deviation d32 from the mounting direction B of the second support elements 32 may in particular be in a range between 0.1 mm and 5 mm, preferably in a range between 1 mm and 4 mm.
  • the deviation d31 can be defined, in particular, by the length of an image of a respective second support element 32, which is in a Parallel projection of the respective support member 32 in the direction of construction B results in a perpendicular to the mounting direction B surface.
  • FIG. 2 shows, by way of example, a first series of elementary units 35 that repeat symbolically along the longitudinal direction L10 of the base region 10 and that are represented symbolically as pentagons and that are formed directly on the base region 10 with respect to the construction direction B. Subsequently, in FIG. 2, a further row of elementary units 35 which repeat themselves along a longitudinal direction L10 of the base region 10 and which are shown symbolically as rhombuses is shown in FIG. In Fig. 3 is another subsequent in the mounting direction B along a longitudinal direction L10 of the base portion 10 repeated
  • FIG. 4 schematically shows a final step of the method. In this case, a formation takes place in the construction direction B to the
  • the build-up area 20 also has a planar extension transverse to the mounting direction B and extends along the
  • the body portion 20 overlaps with the base member 10 with respect to the longitudinal direction L10, as shown particularly in FIGS. 4 and 7.
  • the construction area 20 is shown by way of example as a planar layer, which in the construction direction B in layers by modeling M was produced with a thickness t20.
  • the body region 20 has an areal extent transverse to the body direction B.
  • the construction area 20 of the structural component 1 is shown by way of example as a plate-shaped, planar layer.
  • the structural component 1 shown by way of example in FIG. 5 has a curved construction area 20.
  • the modeling material M is supplied to a 3D printing device 2, as shown in FIG. 5.
  • the modeling material M may be in powder form, for example. Basically, the present sees
  • Invention manifold possibilities before to liquefy the modeling material M, in which heat targeted locally introduced in stored modeling material M.
  • the use of lasers and / or particle beams, e.g. Electron beams is advantageous because this heat is generated very targeted and controlled.
  • the generative manufacturing process may be selected, for example, from the group of selective laser sintering, selective laser melting, selective electron beam sintering, and selective electron beam melting, or the like. In principle, however, any additive method can be used.
  • An energy source in the form of a laser 5A for example an Nd: YAG laser, sends a laser beam 5 in a location-selective manner to a specific part of a laser
  • Powder surface of the powdery modeling material M which in a Working chamber 3 rests on a work platform 4.
  • an optical deflection device or a scanner module such as a movable or
  • tiltable mirror 5B be provided, which the laser beam 5 depending on its tilted position on a certain part of the powder surface of the
  • Modeling material M deflects. At the point of impact of the laser beam 5, the modeling material M is heated, so that the powder particles are locally melted and form an agglomerate upon cooling. Depending on one by a computing device, e.g. in the form of a PC 6, provided digital model of the structural component 1, the laser beam 5 rasterizes the
  • Modeling material M can serve to support the previously constructed part of the structural component 1. Due to the continuous downward movement of the work platform 4, the structural component 1 is formed in layers
  • FIGS. 6 and 7 each show exemplary configurations of the structural component 1.
  • the base region 10 is designed as an arcuately extending, narrow plate which extends along a longitudinal direction LIO. The to the base region 10 in a
  • Thickness direction T spaced mounting area 20 overlaps with the base portion 10.
  • the thickness direction T corresponds to the mounting direction B.
  • the build-up area 20 is formed as a narrow plate with a stepped, arcuate course. In particular, the construction area has a first
  • Longitudinal section 20A which extends along a portion of the base portion 10, with which the first longitudinal portion 20A overlaps. With respect to the longitudinal direction L10, the first longitudinal section 20A follows
  • Step portion 20 B which extends transversely to the first longitudinal portion 20 B and along the longitudinal direction L 10 increasing distance to the base portion 10. With respect to a longitudinal direction L10 connects to the
  • Step portion 20 B an arc portion 20 C, which extends arcuately with decreasing along the longitudinal direction L 10 to the base region 10.
  • a respective functional region 41, 42 may be provided on opposite ends 1A, 1B of the structural component 1, for example as shown in FIG. 6 in the form of cylindrical sleeves, each defining recesses extending transversely to the longitudinal direction L10 ,
  • the recesses may be provided, for example, as a bearing receptacles or the like.
  • the support structure 30 of the structural component 1 shown in FIG. 6 is formed by elongated support elements 31, 32 extending in each case in a slightly curved manner. In the process, these form elementary units 35, each having the same outer shape, in particular in a central region 30A with respect to the thickness direction T along the longitudinal direction L10 within the support structure 30 out.
  • the base region 10, the construction region 20 and the support structure 30 are integrally formed, for example by means of the above-described
  • FIG. 7 shows an exemplary configuration of the structural component 1, in which the base region 10 and the mounting region 20 completely overlap each other and are arranged spaced apart in the thickness direction T.
  • the construction area 20 and the base area 10 are each formed as approximately rectangular plates.
  • the support structure 30 is arranged between the base region 10 and the construction region 20, the support structure 30 is arranged.
  • the base region 10, the construction region 20 and the support structure 30 are integrally formed,
  • FIG. 7 shows by way of example a structural component 1 which has an optional wall region 50. This extends along the thickness direction T between the base region 10 and the construction region 20.
  • the wall region 50 connects an edge region 10A of the base region 10 to an edge region 20A of the construction region 20.
  • Such a wall region 50 can also be used in the exemplary embodiment of FIG Structural component 1 may be provided.
  • a plurality of wall regions 50 may be provided, so that the wall regions 50, the base region 10 and the
  • Build-up 20 a closed cavity is formed, in which the support structure 30 is formed.
  • the wall region 50 may in particular be formed integrally with the base region 10 and the build-up region 20 and simultaneously, for example by means of a generative manufacturing process be constructed with the support structure 30 in the body direction B on the base region.
  • FIGS. 6 and 7 thus generally show a structural component 1 with a planarly extending base region 10, with a planarly extending build-up region 20, which is arranged in a thickness direction T at a distance from the base region 10 and with one between the base region 10 and Build-up area 20 extending grid-like support structure 30, which is a plurality of support members 31, 32 is constructed.
  • the form shown by way of example in FIGS. 6 and 7, the form
  • Elementarillonen 35 each having the same outer shape.
  • the base region 10, the body region 20 and the support structure 30 are integrally formed.
  • the thickness direction T corresponds to the construction direction B, along which the base region 10, the support structure 30, the build-up region 20 and optionally the optional wall region 50 are formed.
  • FIG. 8 schematically shows a lever system 100 with at least one lever 102 which is rotatably hinged to a base component 101.
  • the lever 102 is thereby moved by the structural component 1, e.g. by the structural component 1 shown in FIG. 6
  • the base component 101 shown schematically in FIG. 8 can be, for example, a further structural component 1 according to one of the design variants described above.
  • FIG. 9 shows an exemplary application of the lever system 100 to a
  • the lever 101 which is embodied in each case as a structural component 1 forms movement arms of the industrial robot 103.
  • a structural component 1 forms movement arms of the industrial robot 103.
  • an aircraft 104 is shown, the carriages 105 each have a lever system 100 according to the schematic representation of FIG. 8.
  • the lever 101 embodied as a structural component 1 can in particular form a support for a wheel of the aircraft 104.
  • the structural component 1 can be embodied, for example, as shown in FIG. 6.
  • the base part 101 can be formed, for example, by a holding structure (not shown) fastened in the fuselage of the aircraft 104.
  • T thickness direction t10 The thickness of the base layer

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Manufacturing & Machinery (AREA)
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  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
  • Powder Metallurgy (AREA)

Abstract

L'invention concerne un procédé de fabrication d'un élément structural (1), qui comprend la mise en oeuvre d'un procédé de fabrication générative. Selon l'invention, une zone de base (10) de l'élément structural (1) est d'abord formée dans une direction de fabrication (B). Ensuite, une structure de soutien (30) de type treillis, constituée d'unités élémentaires (35) se répétant à l'intérieur de la structure de soutien (30) et ayant chacune la même forme extérieure, est réalisée. Enfin, une zone supérieure (20) de l'élément structural (1), adjacente à la structure de soutien (30) dans la direction de fabrication (B), est réalisée. L'invention concerne en outre un élément structural (1) et un système de levier (100) comprenant ledit élément structural (1).
PCT/EP2017/076828 2016-12-22 2017-10-20 Procédé de fabrication additive d'un élément structural en sandwich, élément structural en sandwich et système de levier WO2018114093A1 (fr)

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DE102016226022.7 2016-12-22
DE102016226022.7A DE102016226022A1 (de) 2016-12-22 2016-12-22 Verfahren zur Herstellung eines Strukturbauteils, Strukturbauteil sowie Hebelsystem

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WO2018114093A1 true WO2018114093A1 (fr) 2018-06-28

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Cited By (1)

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EP3689501A1 (fr) * 2019-01-31 2020-08-05 CSEM Centre Suisse D'electronique Et De Microtechnique SA Procédé de fabrication d'un dispositif par la mise en uvre d'un processus de fabrication additive ne nécessitant pas de structure de support sacrificielle

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102017211627B4 (de) * 2017-07-07 2019-01-24 Zf Friedrichshafen Ag Kugelgelenk für einen Fahrwerklenker
EP3705209A1 (fr) * 2019-03-05 2020-09-09 Siemens Aktiengesellschaft Composant et procédé de fabrication d'un tel composant
CN116372189B (zh) * 2023-03-17 2023-12-15 南京航空航天大学 砂型增材制造多模型分割与图案填充打印方法

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US8512853B2 (en) * 2007-07-31 2013-08-20 The Boeing Company Composite structure having reinforced core
EP2666613A1 (fr) 2012-05-25 2013-11-27 Technische Universität Darmstadt Invention concernant des structures auxiliaires pour la fabrication de composants au moyen de procédés génératifs ou additifs
WO2015130377A2 (fr) * 2013-12-12 2015-09-03 United Technologies Corporation Panneau structural en nid d'abeille
WO2017020894A1 (fr) * 2015-08-06 2017-02-09 Cl Schutzrechtsverwaltungs Gmbh Procédé de fabrication d'un objet tridimensionnel

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Publication number Priority date Publication date Assignee Title
US8512853B2 (en) * 2007-07-31 2013-08-20 The Boeing Company Composite structure having reinforced core
EP2666613A1 (fr) 2012-05-25 2013-11-27 Technische Universität Darmstadt Invention concernant des structures auxiliaires pour la fabrication de composants au moyen de procédés génératifs ou additifs
WO2015130377A2 (fr) * 2013-12-12 2015-09-03 United Technologies Corporation Panneau structural en nid d'abeille
WO2017020894A1 (fr) * 2015-08-06 2017-02-09 Cl Schutzrechtsverwaltungs Gmbh Procédé de fabrication d'un objet tridimensionnel

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3689501A1 (fr) * 2019-01-31 2020-08-05 CSEM Centre Suisse D'electronique Et De Microtechnique SA Procédé de fabrication d'un dispositif par la mise en uvre d'un processus de fabrication additive ne nécessitant pas de structure de support sacrificielle

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