• 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 present invention relates to a method of manufacturing a filler body of a blade (5, 15) of a rotor (9, 19). According to the invention, such a method is remarkable in that it comprises a succession of layer-by-layer additions of material, each step consisting in producing a new layer of material on a previous layer of material produced in step previous.
    公开号:FR3069481A1
    申请号:FR1770806
    申请日:2017-07-28
    公开日:2019-02-01
    发明作者:Andre Amari；Jacques Gaffiero；Jean Francois Piccone
    申请人:Airbus Helicopters SAS；
    IPC主号:
    专利说明:

    Method for manufacturing a filling body for a rotor blade and filling body for a rotor blade comprising at least one closed cell honeycomb assembly
    The present invention relates to the field of methods for manufacturing a filler body for a blade of a rotor. Such a blade filling body can in particular be used to equip a main rotor blade and / or rear rotor of a rotorcraft or any rotary wing such as that of a multirotor drone or even a propeller in particular.
    Once produced, such a filling body is then generally covered with a reinforcing composite material comprising at least one woven ply impregnated with a resinous matrix or a mineral or even metallic matrix, serving as a binder between the various fibers of the (or) woven fold (s), two or more folds forming a laminate by definition.
    In addition, the invention also relates to a body for filling a blade of a rotor comprising at least one alveolar assembly with closed cells.
    In known manner, the filling bodies of rotorcraft blades can be formed of polyurethane foams for example or of structures known as honeycombs based for example on impregnated cardboard or on paper coated with a varnish, of kevlar impregnated with resin, expanded aluminum or also extruded plastic such as polypropylene in particular. Such filling bodies then form a core intended to be arranged between two coatings (laminates, metal, etc.) impregnated with a matrix. For example, such a material is known under the name NOMEX®, registered trademark of the company Dupont de Nemours. It consists of sheets made from aramid fibers, these sheets also being impregnated with a phenolic resin.
    For example, the density of honeycomb structures can be of the order of 25 kg / m 3 (kilogram per cubic meter) while the density of polyurethane foams is rather between 65 and 120 kg / m 3 (kilogram per cubic meter).
    A sandwich thus produced by a lower coating, a filling body and an upper coating can then make it possible to produce a rotorcraft blade having a high flexural strength as well as a great lightness thanks to a vacuum rate close to 95%.
    However, taking into account the geometric configuration of the honeycomb structures, such filling bodies have mechanical characteristics in compression which are highly variable along the three axes of an orthonormal reference frame comprising a transverse axis X oriented along the chord of the profiles aerodynamics of the sections of the blade, a longitudinal axis Y oriented substantially along the span of the blade (generally the direction of expansion of the honeycombs) and an axis in elevation Z perpendicular both to the transverse axis X and to the longitudinal axis Y.
    Indeed, the filling bodies having a honeycomb structure have important characteristics of resistance to compression along the axis in elevation Z which can correspond to the direction of the generatrices of the cells of the honeycomb. Such a positioning of the honeycomb cells is in particular advantageous in order to counteract the compressive forces which can cause crushing of the aerodynamic profile of the sections along this axis in elevation Z.
    On the other hand, along the other two axes, transverse X and longitudinal Y, the compressive strength of the honeycomb structures is lower. Such a characteristic is then penalizing, and at the very least constraining, for achieving the positioning of the other structural components of the blade such as in particular the longitudinal members, the boxes or the ribs in particular which must be arranged in the blade before positioning the woven fold. reinforcement forming all or part of its outer shell and at a molding phase of this outer shell.
    In fact, during the molding phase of a rotorcraft blade, when all the elements are placed in the mold in the non-polymerized state and the mold is closed, it appears in the blade section and therefore in the body. filling thereof significant compressive forces which tend to deform and move during polymerization the various structural constituents of the blade along the three axes X, Y and Z. Displacements of sub-assemblies such as torsion boxes can then be generated along the transverse axis X in the direction for example of a trailing edge of the aerodynamic profile of the sections due in particular to the low resistance to compression (or more exactly the stiffness in compression) along the transverse axis X of the honeycomb structures forming the filling body of the blade. .
    In addition, the upper and lower faces of the honeycomb structures are opened by construction and covered by the woven reinforcing pleats. Due to this discontinuity in localized maintenance of sharp edges and the intrinsic flexibility of the woven reinforcing plies, we then observe, after manufacture or operation in the center of each honeycomb cell, a phenomenon of local collapse causing a multifaceted surface effect like a "golf ball". This localized degradation of the shape of the blade at the level of the honeycomb filling bodies is known in English as "telegraphing" with reference to the paths of cables suspended between pylons.
    Such a surface effect then requires significant finishing operations such as puttying and sanding in order to obtain a satisfactory surface condition. The cost and the technical characteristics of the blades thus formed are then penalized by these limits of the honeycomb structures.
    If the foam filling bodies, for example of the polyurethane type, do not have these drawbacks, they in turn have densities generally greater than those of the honeycomb structure. They are in fact typically greater than 65 kg / m 3 (kilogram per cubic meter). In addition, their manufacturing cost is relatively high because it is first necessary to pour foam bars, to steam them, to listen, then in a second step, to machine in these blocks complex shapes in three dimensions constituting the bodies of filling as such.
    Finally, foams comprising, for example organic compounds such as polyols or iso-cyanates and the significant drop rates which can be 80% non-recyclable, since they are linked to the process for manufacturing these filling bodies, have an ecological footprint. important.
    The object of the present invention is therefore to propose a method for manufacturing the filling bodies for rotor blades which makes it possible to overcome the limitations mentioned above. In addition, the manufacturing process makes it possible to produce filling bodies without falling material.
    In addition, the filling bodies thus produced are very light and have stiffness and compressive strength characteristics which can be substantially similar along the three axes X, Y and Z.
    The invention therefore relates to a method for manufacturing a filler body for a blade of a rotor.
    Such a manufacturing process is remarkable in that it comprises a succession of steps of adding material layer by layer, each step consisting in producing a new layer of material on a previous layer of material produced in the previous step, at least one of the steps consisting in producing a layer of perforated material having a plurality of openings.
    In other words, such a manufacturing process makes it possible to produce a filling body in three dimensions, ie along the axes X, Y, Z and can implement steps of printing in three dimensions by depositing a material by means of a nozzle on a support or by stereo lithography using a laser making it possible either to locally polymerize a bath of material in the liquid phase, or to selectively sinter a material in the powder state. Such a process for manufacturing a blade filling body then corresponds to the ALM type processes corresponding, in English, to the acronym of the expression Additive Layer Manufacturing.
    Such a method can in particular make it possible to confer on the filling body variable densities in three dimensions along the axes X, Y, Z. Consequently, for each cross section along a plane XZ of a filling body, the precise positioning of the center of gravity of the section in the XZ plane of the blade filling body can be determined during the design of the internal structure of the blade filling body, this internal structure being obtained for example by the successive superposition of the different layers of material wholly perforated along the axis in elevation Z.
    Furthermore, independently of the density of the filling bodies which it is possible to adjust, such a manufacturing method also also makes it possible to adjust the stiffness and / or the mechanical properties of the blade, in particular when buckling or in compression.
    Advantageously, the succession of steps of adding material layer by layer can generate layers of openwork material each having a closed contour, such closed contours respectively of these layers of openwork material being two to two joined together and forming an envelope. closed of the blade filling body.
    As a result, the succession of steps makes it possible to directly generate a filling body provided with a substantially smooth envelope with an external surface. Such a method thus makes it possible to avoid the phenomenon of telegraphing during the covering of the filling body with one (or more) woven ply (s) of reinforcement or a laminate and consequently also additional steps of puttying and sanding. .
    In practice, the succession of steps of adding material layer by layer can generate layers of perforated material each comprising a plurality of geometric shapes arranged inside the closed contour and making it possible to delimit the plurality of openings in the layer. of perforated material, the pluralities of respective geometric shapes of the layers of perforated material being two to two contiguous with each other and forming a cellular assembly of closed cells arranged inside the closed envelope of the filling body of the blade.
    In other words, the alveolar assembly makes it possible, by modifying the geometric shapes for example in planes parallel to the XY plane, to modify the density, the stiffness and / or the mechanical strength characteristics of the filling body. Of course, the density, the stiffness and the mechanical resistance characteristics of the filling body are modified by adapting the number, the size and the shape of the closed cells constituting it but also the thickness of the geometric shapes making it possible to generate these closed cells.
    Furthermore and according to a first embodiment, the succession of steps of adding material layer by layer can generate layers of openwork material formed from the same material.
    However, according to a second advantageous embodiment, the succession of steps of adding material layer by layer can also generate layers of openwork material formed in at least two distinct materials one from the other.
    These at least two distinct materials can thus advantageously comprise densities distinct from one another, stiffnesses and / or mechanical resistance characteristics, in particular in buckling or in compression, different from each other in order to 'Adapt the positioning of the mass center of gravity of the blade, the stiffness and / or the characteristics of overall mechanical resistance of the blade thus formed with such a filling body.
    In this case and according to a first variant of the invention, the succession of steps of adding material layer by layer can generate at least two layers of perforated material distinct from each other, a first layer being formed in a first material and a second layer being formed in a second material distinct from the first material.
    According to this first variant, it is then for example envisaged to produce layers formed in a first material near a middle portion of the filling body along the axis in elevation Z and then to produce other layers in a second material to from a predetermined distance along the axis in elevation Z relative to this middle portion. In addition, such a middle portion of the filling body can form a left surface in which the strings of the different aerodynamic profiles of the sections of a blade formed from such a filling body are inscribed.
    It can thus be envisaged that the first material close to the middle portion has a density greater than that of the second material remote from the middle portion. Such a process can in fact be carried out by means of a three-dimensional printing machine comprising at least two printing heads, each head making it possible to print in a predetermined material.
    According to a second variant of the invention, the succession of steps of adding material layer by layer can generate at least one layer of perforated material formed in the at least two distinct materials one from the other.
    In this case, it is then envisaged to modify the density of the material of the filling body in the same plane parallel to the XY plane and in the same layer of material. At least two printheads can then be used simultaneously on the same layer of material.
    Thus, a first print head can print a first zone located in a plane parallel to the XY plane while a second print head can print, for example simultaneously, a second zone also located in the same plane parallel to the XY plane.
    The present invention also relates to a body for filling a blade of a rotor comprising at least one alveolar assembly with closed cells.
    Such a filling body is remarkable in that it is produced by a manufacturing process as described above.
    In other words, such a filling body is produced by means of a manufacturing method of the ALM type, that is to say a method comprising a succession of steps of adding material layer by layer, each step consisting in make a new layer of material on a previous layer of material produced in the previous step.
    Advantageously, the honeycomb assembly can be formed by cells with at least four faces, each face of these cells being formed respectively by a polygon with at least three sides.
    In other words, the alveoli can form polyhedra chosen from the group comprising in particular tetrahedra, hexahedra, octahedra, dodecahedra and icosahedra.
    In practice, the alveolar assembly can comprise at least two groups of alveoli distinct from each other.
    Indeed, the shape and size of the cells can vary depending on their respective location in the filling body.
    According to a first embodiment of the invention, the honeycomb assembly may comprise a first group of cells whose at least three sides each have a first length respectively and a second group of cells whose at least three sides have respectively each a second length distinct from the first length.
    In this case, it is the size of the cells which is changed between the first group and the second group of cells. In addition, the larger the size of the cells and the lower the density of the filling body compared to cells of the same shape but of smaller size. In addition to modifying the density of the filling body, such a first exemplary embodiment also makes it possible to modify the stiffness and / or the mechanical strength characteristics of the filling body.
    In addition, the first group and the second group of cells can be arranged in the same plane parallel to the XY plane. Alternatively or simultaneously, the first group and the second group of cells can also be arranged along the same axis parallel to the axis in elevation Z.
    According to a second embodiment of the invention, the honeycomb assembly may comprise a third group of cells, the at least three sides of which each have a first thickness, and a fourth group of cells, the said at least three sides of which respectively have each a second thickness distinct from said first thickness.
    According to this second embodiment, the thickness of the faces of the cells is changed between the third group and the fourth group of cells. It is also immediate that for the same size and the same shape of cells, the greater the thickness of the faces and the higher the density of the filling body. Regardless of the density of the filling body, such a second embodiment also allows the stiffness and / or the mechanical strength characteristics of the filling body to be modified.
    In addition, the third group and the fourth group of cells can be arranged in the same plane parallel to the XY plane. Alternatively or simultaneously, the third group and the fourth group of cells can also be arranged along the same axis parallel to the axis in elevation Z.
    According to a third embodiment of the invention, the honeycomb assembly may include a fifth group of cells, the polygons of which form the at least four faces, each respectively have a first shape and a sixth group of cells, the polygons of which form the at least four faces respectively each have a second shape distinct from the first shape.
    As a result, the shape of the cells can be changed between the fifth group and the sixth group of cells of the filling body. In addition, the larger the polygons, the lower the density of the filling body because it contains less material per unit area in the same layer. As previously, such a third exemplary embodiment also makes it possible to modify the characteristics of stiffness and / or mechanical resistance of the filling body.
    In addition, the fifth group and the sixth group of cells can be arranged in the same plane parallel to the XY plane. Alternatively or simultaneously, the fifth group and the sixth group of cells can also be arranged along the same axis parallel to the axis in elevation Z.
    According to a fourth embodiment of the invention, the honeycomb assembly may comprise a seventh group of cells formed in a first material and an eighth group of cells formed in a second material distinct from the first material.
    In this case, the density of the material chosen to form the seventh group and the eighth group of cells respectively makes it possible directly to modify the density of the filling body, the stiffness and / or its mechanical strength characteristics.
    In addition, the seventh group and the eighth group of cells can be arranged in the same plane parallel to the XY plane. Alternatively or simultaneously, the seventh group and the eighth group of cells can also be arranged along an axis parallel to the axis in elevation Z.
    Advantageously, the filling body may comprise a closed envelope, this closed envelope completely covering the cellular assembly.
    As a result, this closed envelope can be smooth and continuous so as to avoid the phenomenon of telegraphing during the covering of the filling body with one (or more) woven ply (s) of reinforcement or laminates and consequently also additional puttying and sanding steps.
    The invention and its advantages will appear in more detail in the context of the description which follows with examples given by way of illustration with reference to the appended figures which represent:
    FIG. 1, a diagram in side view of a rotorcraft equipped with blades, in accordance with the invention,
    - Figures 2, 3 and 5, cross-sectional views of different embodiments of filling bodies according to the invention,
    FIG. 4a, two perspective views of two distinct groups of cells forming a honeycomb assembly of a filling body according to the invention,
    FIG. 4b, projections in a plane of two polygons illustrating the shape of two distinct groups of cells forming a cellular assembly of a filling body according to the invention,
    - Figure 6, two perspective views of two other separate groups of cells forming a honeycomb assembly of a filling body according to the invention, and.
    - Figures 7 and 8, two block diagrams illustrating two manufacturing methods according to the invention
    The elements present in several separate figures are assigned a single reference.
    Note that three axes X, Y and Z orthogonal to each other are shown in Figures 2, 3 and 5.
    The X axis is said to be transverse in so far as it extends transversely along a chord of the airfoil of the sections of a blade between a leading edge and a trailing edge,
    this blade comprising the invention. a body of filling conform to Another axis Y East said longitudinal and spreads perpendicularly by compared to the next X axis sensibly the span of the blade.Finally, a third axis Z is said in elevation and matches
    the thickness dimensions of the aerodynamic profile of the sections of the blade between a surface of the upper surface and a face of the lower surface of this aerodynamic profile.
    As already mentioned the invention therefore relates to a body for filling a blade of a rotor, or even a propeller, for example of rotorcraft.
    As shown in FIG. 1, such a filling body can be arranged at a blade 5 of a main rotor 9 and / or at a blade 15 of a rear rotor 19 of a rotorcraft 6.
    As already indicated, such a filling body is remarkable in that it is manufactured by an ALM type process by making a superposition of layers of material one above the other, for example in stereo lithography or by three-dimensional printing.
    As shown in FIG. 2 and according to a first exemplary embodiment, the filling body 1 is produced by a superposition of openwork layers of material 2 each comprising a plurality of geometric shapes 7 inscribed in each of the planes parallel to the XY plane. In addition, these geometric shapes 7 each define an opening 101 made in the openwork layers of material 2.
    Furthermore, these geometric shapes 7 are delimited by a closed contour 3 in each plane parallel to the XY plane and making it possible to generate a closed envelope 4 in three dimensions of the filling body 1. For example, it is envisaged to print a layer of openwork material by moving a print head along a plane parallel to the XY plane, then moving the print head along the Z axis and printing a new layer of openwork material on the previous layer parallel to the XY plane.
    Such a combined displacement of the print head along the axes X, Y and Z therefore makes it possible to produce a blade filling body extending in three dimensions along the three axes X, Y and Z.
    Of course, such an orientation of the layers is given as an indication and not limiting. In addition, the openwork material layers can also be deposited in planes parallel to the XZ plane and the print head can be moved along the Y axis between two operations of depositing an openwork material layer.
    Furthermore, such a closed envelope 4 thus contains a cellular assembly 8 of different cells 50, 60 with closed cells extending in three dimensions along the three axes X, Y, Z and in particular making it possible to vary the density of the body of filling 1 along the three axes X, Y and Z, the stiffness and / or the mechanical strength characteristics along the three axes X, Y and Z of such a filling body 1.
    More particularly, these different variations in the density of the filling body 1 along the three axes X, Y and Z, the stiffness and / or the mechanical strength characteristics along the three axes X, Y and Z can be achieved by means of different groups of cells 50, 60.
    Thus, a first group 71 of cells 50 can be formed by tetrahedra and thus have four faces 51-54, as illustrated in FIG. 4a, these faces 51-54 being formed by points defined by their coordinates according to the axes X, Y, Z. Similarly, a second group 72 of cells 60 can be formed by tetrahedrons having four faces 61-64 defined by other points with coordinates along the axes X, Y, Z ..
    In accordance with FIG. 4b, each face 51-54 of the cells 50 of the first group 71 may have sides 55-57 each having a length L1 respectively. Likewise, each face 61-64 of the cells 60 of the second group 72 may have sides 65-67 each having a length L2 respectively. In this case, the length L1 relating to the cells 50 is then distinct from the length L2 relating to the cells 60.
    Similarly and as shown in FIG. 3, the filling body 11 is produced by a superposition of layers of material 12, 12 ’each comprising a plurality of geometric shapes 17 inscribed in each of the planes parallel to the XY plane. In addition, these geometric shapes 17 are delimited by a closed contour 13, 13 ′ in each plane parallel to the XY plane making it possible to generate a closed envelope 14 in three dimensions of the filling body 11 by the displacement along the axis Z of the head printing.
    Such a filling body 11 can then comprise at least two layers 12 and 12 ′ distinct from each other. A first layer 12 can then be formed from a first material while the second layer 12 ’is formed from a second material separate from the first material.
    Furthermore, each closed envelope 14 may also contain a cellular assembly 18 of different cells 50, 60 with closed cells, in particular making it possible to vary the density of the filling body 11 along the three axes X, Y and Z, the stiffness and / or the mechanical strength characteristics along the three axes X, Y and Z of such a filling body 11.
    However, in accordance with FIG. 4b, each face 51-54 of the cells 50 of a third group 73 may have sides 5557 each having a thickness e1 respectively. Likewise, each face 61-64 of the cells 60 of the fourth group 74 may have sides 65-67 each having a thickness e2 respectively. In this case, the thickness e1 relating to the cells 50 is then distinct from the thickness e2 relating to the cells 60.
    As shown in Figures 5 and 6, the honeycomb assembly 28 includes a fifth group 75 of cells 150 whose polygons forming the four faces 151-154 each have a first shape 155 such as a tetrahedron and a sixth group 76 of cells 160, the polygons of which form the six faces 161-164 each have a second shape 165, such as a cube or hexahedron.
    In addition, the honeycomb assembly 28 can also include a seventh group 77 of cells 150 formed in a first material and an eighth group 78 of cells 160 formed in a second material distinct from the first material.
    In addition, the same layer 22 of material of the filling body 21 can thus be formed in two separate materials from one another.
    Consequently, such a honeycomb assembly 28 comprises different cells 150, 160 with closed cells allowing in particular to vary the density of the filling body 21 along the three axes X, Y and Z, the stiffness and / or the mechanical strength characteristics. along the three axes X, Y and Z of such a filling body 21.
    As shown in Figures 7 and 8, the invention also relates to a method of manufacturing such a filling body 1, 11, 21. As already mentioned, this manufacturing method 30, 40 comprises a succession of steps 31, 32, 41, 42 of additions of material layer by layer, each step 32, 42 consisting in producing a new layer of material on a previous layer of material produced in the previous step 31, 41.
    According to a first manufacturing method 30 as shown in FIG. 7, the succession of steps 31, 32 of adding material layer by layer can then generate layers of openwork material 2 formed from the same material.
    However, according to a second manufacturing method 40 as shown in FIG. 8, the succession of steps 41, 42 of adding material layer by layer can generate layers of perforated material 12, 12 ′, 22 formed in at least two materials separate from each other.
    Naturally, the present invention is subject to numerous variations and combinations as to its implementation. Although several embodiments have been described, it is understood that it is not conceivable to identify exhaustively all the possible modes. It is of course conceivable to replace a means described by an equivalent means without departing from the scope of the present invention.
    权利要求:
    Claims (15)
    [1" id="c-fr-0001]
    1. Method of manufacturing (30, 40) of a filling body (1, 11, 21) of a blade (5, 15) of a rotor (9, 19), characterized in that said method (30 , 40) comprises a succession of steps (31, 32, 41, 42) of additions of material layer by layer, each step (32, 42) consisting in producing a new layer of material on a previous layer of material produced at the previous step (31, 41), at least one of the said steps (31, 32, 41, 42) consisting in producing a layer of openwork material (2, 12, 22) having a plurality of openings (101) .
    [2" id="c-fr-0002]
    2. The manufacturing method according to claim 1, characterized in that said succession of steps (31, 32, 41, 42) of additions of material layer by layer generates layers of perforated material (2, 12, 22) comprising each a closed contour (3, 13, 23), said closed contours (3, 13, 23) respective of said layers of perforated material (2, 12, 22) being two to two joined together and forming a closed envelope (4, 14, 24) of said filling body (1, 11, 21) of said blade (5, 15).
    [3" id="c-fr-0003]
    3. The manufacturing method according to claim 2, characterized in that said succession of steps (31, 32, 41, 42) of additions of material layer by layer generates layers of perforated material (2, 12, 22) comprising each a plurality of geometric shapes (7, 17, 27) arranged inside said closed contour (3, 13, 23) and making it possible to delimit said plurality of openings (101) of said layer of perforated material (2, 12 , 22), said pluralities of geometric shapes (7, 17, 27) respective to said layers of perforated material (2, 12, 22) being two to two contiguous with each other and forming a cellular unit (8, 18, 28) closed arranged inside said closed casing (4, 14, 24) of said filling body (1, 11, 21) of said blade (5, 15).
    [4" id="c-fr-0004]
    4. Manufacturing method according to any one of claims 1 to 3, characterized in that said succession of steps (31, 32) of additions of material layer by layer generates layers of perforated material (2) formed in a same material.
    [5" id="c-fr-0005]
    5. Manufacturing method according to any one of claims 1 to 3, characterized in that said succession of steps (41, 42) of additions of material layer by layer generates layers of perforated material (12, 12 ', 22) formed from at least two materials which are distinct from each other.
    [6" id="c-fr-0006]
    6. The manufacturing method according to claim 5, characterized in that said succession of steps (41, 42) of adding material layer by layer generates at least two layers of perforated material (12) and (12 ') distinct l 'from each other, a first layer (12) being formed in a first material and a second layer (12') being formed in a second material distinct from said first material.
    [7" id="c-fr-0007]
    7. Manufacturing method according to any one of claims 5 to 6, characterized in that said succession of steps (41, 42) of material additions layer by layer generates at least one layer of perforated material (22) formed in said at least two materials distinct from each other.
    [8" id="c-fr-0008]
    8. Filling body (1, 11, 21) of a blade (5, 15) of a rotor (9, 19) comprising at least one alveolar assembly with closed cells, characterized in that said filling body (1 , 11, 21) is produced by a manufacturing method according to any one of claims 1 to 7.
    [9" id="c-fr-0009]
    9. Filling body according to claim 8, characterized in that said honeycomb assembly (8, 18, 28) is formed by cells (50, 60, 150, 160) with at least four faces (51-54, 61- 64, 151-154, 161-164), each face (51-54, 6164, 151-154, 161-164) of said cells (50, 60, 150, 160) being respectively formed by a polygon with at least three sides (5557, 65-67).
    [10" id="c-fr-0010]
    10. Filling body according to claim 9, characterized in that said cellular assembly (8, 18, 28) comprises at least two groups (71, 73, 75, 77) and (72, 74, 76, 78) of cells (50, 60, 150, 160) distinct from each other.
    [11" id="c-fr-0011]
    11. Filling body according to claim 10, characterized in that said honeycomb assembly (8) comprises a first group (71) of cells (50) whose said at least three sides (55-57) each have a first length respectively L1 and a second group (72) of cells (60), said at least three sides (65-67) of which each have a second length L2 distinct from said first length L1, respectively.
    [12" id="c-fr-0012]
    12. Filling body according to any one of claims 10 to 11, characterized in that said cellular assembly (18) comprises a third group (73) of cells (50) of which said at least three sides (55-57) each have a first thickness e1 and a fourth group (74) of cells (60) each of which said at least three sides (65-67) each have a second thickness e2 respectively distinct from said first thickness e1.
    [13" id="c-fr-0013]
    13. Filling body according to any one of claims 10 to 12, characterized in that said honeycomb assembly (28) comprises a fifth group (75) of cells (150) whose said polygons forming said at least four faces (151 -154) each have a first shape (155) and a sixth group (76) of cells (160) of which said polygons forming said at least four faces (161-164) each have a second shape (165) each distinct from said first form (155).
    [14" id="c-fr-0014]
    14. Filler body according to any one of claims 10 to 13, characterized in that said cellular assembly (28) comprises a seventh group (77) of cells (150) formed in a first material and an eighth group (78 ) cells (160) formed from a second material separate from said first material.
    [15" id="c-fr-0015]
    15. Filling body according to any one of claims 8 to 14, characterized in that said filling body (1, 11, 21) comprises a closed envelope (4, 14, 24), said closed envelope (4, 14 , 24) completely covering said cellular assembly (8, 18, 28).
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    同族专利:
    公开号 | 公开日
    KR102171748B1|2020-10-29|
    CA3007901A1|2018-08-14|
    RU2684999C1|2019-04-16|
    US10967966B2|2021-04-06|
    EP3434464B1|2020-12-02|
    CN109305358B|2021-10-08|
    CA3007901C|2019-09-17|
    KR20190013614A|2019-02-11|
    EP3434464A1|2019-01-30|
    CN109305358A|2019-02-05|
    US20190031329A1|2019-01-31|
    FR3069481B1|2021-05-28|
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    法律状态:
    2019-02-01| PLSC| Search report ready|Effective date: 20190201 |
    2019-07-19| PLFP| Fee payment|Year of fee payment: 3 |
    2020-07-21| PLFP| Fee payment|Year of fee payment: 4 |
    2021-07-28| PLFP| Fee payment|Year of fee payment: 5 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1770806|2017-07-28|
    FR1770806A|FR3069481B1|2017-07-28|2017-07-28|METHOD OF MANUFACTURING A BODY FOR FILLING A ROTOR BLADE AND FILLING BODY OF A ROTOR BLADE CONTAINING AT LEAST ONE CLOSED CELL ALVEOLAR ASSEMBLY|FR1770806A| FR3069481B1|2017-07-28|2017-07-28|METHOD OF MANUFACTURING A BODY FOR FILLING A ROTOR BLADE AND FILLING BODY OF A ROTOR BLADE CONTAINING AT LEAST ONE CLOSED CELL ALVEOLAR ASSEMBLY|
    EP18177075.1A| EP3434464B1|2017-07-28|2018-06-11|A method of fabricating a rotor blade filler body, and a rotor blade filler body comprising at least one cellular assembly having closed cells|
    CA3007901A| CA3007901C|2017-07-28|2018-06-11|Procede de fabrication d'un corps de remplissage d'une pale d'un rotor et corps de remplissage d'une pale de rotor comportant au moins un ensemble alveolaire a cellules fermees|
    RU2018122090A| RU2684999C1|2017-07-28|2018-06-18|Method of manufacturing a propeller blade filling body and a propeller blade filling body comprising at least one cellular system with closed cells|
    CN201810804397.8A| CN109305358B|2017-07-28|2018-07-20|Rotor wing panel infill and method of making same|
    US16/044,793| US10967966B2|2017-07-28|2018-07-25|Method of fabricating a rotor blade filler body, and a rotor blade filler body comprising at least one cellular assembly having closed cells|
    KR1020180087973A| KR102171748B1|2017-07-28|2018-07-27|A method of fabricating a rotor blade filler body, and a rotor blade filler body comprising at least one cellular assembly having closed cells|
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