• 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 monolithic blade (21) of a rotorcraft rotor, said blade (21) comprising at least locally a profiled zone (30) having a lower face and an extrados face. The invention is remarkable in that said blade (21) comprises a root zone (3) comprising a spherical bearing finger (24) arranged at a root end (33) of said blade (21). a recess (23) adapted to receive a laminated spherical abutment and a flexible portion (26) having a preferred bending deformation direction along a beat axis of said blade (21), said flexible portion (26) being arranged between said finger (24) and said recess (23).
    公开号:FR3051439A1
    申请号:FR1600782
    申请日:2016-05-17
    公开日:2017-11-24
    发明作者:Andre Amari；Jacques Gaffiero
    申请人:Airbus Helicopters SAS；
    IPC主号:
    专利说明:

    Monolithic blade, rotorcraft rotor equipped with such a monolithic blade and associated rotorcraft.
    The present invention relates to the field of aeronautics and more particularly to the manufacture of monolithic blades intended to form a rotary wing aircraft rotor, a rotor provided with at least two blades of this type and a rotary wing aircraft equipped with such a rotor.
    Indeed, a rotary wing aircraft such as a rotorcraft generally comprises at least one lift rotor or propulsion. Such a lift rotor then comprises a central hub with which blades are secured and arranged substantially radially relative to an axis of rotation of this hub.
    These blades may in certain cases be secured to sleeves arranged at the interface with a central hub. In this case, these blades are not then directly secured to a central hub.
    The monolithic blades are each formed respectively by a single piece directly connected to the central hub of a rotor. Such a type of rotor having monolithic blades thus has a reduced number of parts and is generally lighter than a rotor comprising both non-monolithic blades and sleeves reported on a central hub.
    This type of rotor equipped with monolithic blades can then comprise laminated stops to directly articulate each monolithic blade with respect to the hub along a beat axis, a drag axis and a pitch variation axis. Such a type of rotor has in particular been described by the Applicant in the document FR 2 984 849.
    However, in this case, a laminated spherical abutment serves both to articulate a monolithic blade with respect to the hub and to play, at least partially, the drag damping role for example to avoid sol and air resonance phenomena. Such a drag damper damps the oscillations of each blade relative to the hub about its drag axis.
    Such laminated spherical abutments are therefore both subject to radial compression forces generated by the centrifugal force of the rotor during its rotation and vibratory shearing forces during oscillations of the blade along the beat axis, the axis of drag and the axis of variation of step. The combination of these compressive forces and shear thus makes the design of these laminated spherical abutments very complex and difficult to achieve, which requires to adapt accordingly the dimensioning of these laminated spherical abutments to support these different stresses. As a result, a rotor equipped with such blades and laminated spherical abutments is heavy and complex to manufacture.
    The present invention therefore aims to provide monolithic blades having a particular shape and an associated rotor to overcome the limitations mentioned above. This is achieved in particular by a new design of a monolithic blade to use laminated spherical stops performing only the hinge function according to a ball-type connection between the blade and the hub of the rotor. The invention thus relates to a monolithic blade of a rotorcraft rotor. Such a blade conventionally comprises an aerodynamically profiled zone, hereinafter profiled area, comprising an extrados face and a lower surface face, that is to say whose contours sections are aerodynamic profiles formed by an extrados and a lower surface.
    According to the invention the blade is remarkable in that it comprises a root zone comprising: a spherical bearing finger arranged at a root end of the blade, such finger being intended to cooperate according to a annular linear type connection with a cylindrical bore, a recess opening on either side of a rigid portion of the root zone of the blade between a first face and a second face respectively extending the intrados face and the extrados face of the profiled zone of the blade towards said root end, such a recess being able to receive a laminated spherical abutment, and • a flexible portion having a direction of preferred bending deformation along a beat axis of the blade, said flexible portion being arranged between said finger and said recess adapted to receive said laminated spherical stop.
    In other words, such a blade, forming a one-piece assembly, is intended to be directly secured to the hub of a rotorcraft rotor via a laminated spherical abutment inserted in the recess emerging from the root of this blade. . Given its particular design, such a monolithic blade can also cooperate directly with a drag damper annex and independent of the laminated spherical stop. Such a drag damper is then specifically designed to cooperate with the spherical bearing finger arranged at the root end of the blade. This root end of the blade is intended to be positioned closest to the axis of rotation of the rotor.
    As a result, such a monolithic blade comprises a root zone designed to cooperate with a central hub and a profiled zone. The particular shape of the root zone of this blade then makes it possible to simplify the design of the laminated spherical abutments and thus to reduce the dimensions and the associated mass due in part to no contribution to any function of damping the movement of the blades and on the other hand the removal of heavy hinge masses such as a sleeve and the associated fasteners in particular. Indeed, these swinging masses with high inertia induce significant dynamic loads and high vibration levels resulting in oversized lamination spherical abutments.
    In addition, the flexible portion of the blade in a preferred direction of deformation beat may allow this root zone extending from the finger to beyond the recess to participate in the beat movements of said blade.
    The annular linear type connection between the spherical bearing pin of the blade and the cylindrical bore of the drag damper furthermore makes it possible to confer four degrees of freedom between the finger and the bore. These four degrees of freedom can be broken down into three rotations along three axes forming an orthonormal coordinate system and a translation in a direction parallel to the span of the blade allowing the beat and drag movements of a blade and its setting in step.
    Advantageously, the recess can be arranged at a narrowing of the strings of the blade in the root zone, such a narrowing corresponding to a decrease of the rope of the blade relative to the rope of the profiled zone of the blade. blade.
    In other words, the cord of the root zone at the level of the recess for receiving the laminated abutment is less than the cord of the profiled zone of the blade.
    In practice, the flexible portion may comprise all or part of a plate form.
    As a result, such a flexible portion has a cross section, that is to say substantially perpendicular to the pitch axis of the blade, having a constant thickness as opposed to the thickness of the blade at the contoured zone. , the thickness being expressed perpendicularly to the chord of the sections of the root zone or to the chord of the aerodynamic profiles according to the zone concerned. Such a thickness at the level of the flexible portion is also less than the maximum thickness of the blade measured at the level of the profiled zone. In addition, such a flexible portion of the blade may have several cross sections having different thicknesses.
    For example, the flexible portion may comprise all or part of a first form of plate having a first predetermined thickness and a second form of plate having a second predetermined thickness. The first form of plate is then integral with the spherical finger while the second form of plate is arranged near the recess. The first form of plate is otherwise continuous coplanar with the second form of plate.
    The first and second predetermined thicknesses are therefore advantageously chosen different from each other. For example, the first predetermined thickness of the first plate shape may then be chosen smaller than the second predetermined thickness of the second plate shape. The first predetermined thickness of the first plate shape may be of the order of 10 to 20 mm and the second predetermined thickness of the second plate shape may be in the range of 20 to 40 mm.
    According to another embodiment according to the invention, the flexible portion of the blade may comprise a plurality of transverse sections having a thickness varying progressively from a minimum thickness e1 'to a maximum thickness e2' in the direction of the span of the blade .
    Advantageously, the flexible portion may be arranged symmetrically on either side of a median plane of the root zone of the blade.
    In this way, the flexible portion extends symmetrically with respect to the median plane passing through the center of the spherical finger and the center of the laminated spherical stop. In a particular case, such a median plane may be substantially perpendicular to the axis of rotation of a rotor having a plurality of blades.
    According to a first exemplary embodiment, the flexible portion may comprise at least locally an I-shaped cross-section, the median plane defining an axis of symmetry of the central core of this section, such a flexible portion having two edges of part and else of the central core forming symmetrical excrescences on both sides of the median plane of the root zone of the blade.
    Such an I-shaped cross-sectional shape is thus optimal to guarantee both a low mass of the flexible portion and a stiffness in drag greater than the stiffness in flapping. Furthermore, such an I-shape can in particular be achieved when the flexible portion of the blade is obtained by a molding process of a thermoplastic material.
    According to a second exemplary embodiment, the flexible portion may comprise at least locally a cross section of rectangular shape arranged symmetrically with respect to the median plane of the root zone of the blade.
    Such a rectangular cross-sectional shape is easier to make than a cross-section I-shaped and can for example be made with laminated composite materials obtained by the superposition of textile webs comprising reinforcing fibers, such as in particular glass, carbon and aramid fibers, pre-impregnated with a matrix such as an epoxy resin for example, these fibers being judiciously oriented. Indeed, the preferred orientation of the fibers gives them properties of anisotropy to adjust the characteristics of the module, so rigidity and strength in the desired direction.
    Advantageously, the root zone of the blade may be formed in at least one composite material chosen especially from the group comprising epoxy polymers, epoxy resins, epoxy resins loaded with reinforcing fibers, textile mats based on reinforcing fibers, and embedded in an epoxy matrix and woven, knitted or braided textile plies based on reinforcing fibers and then embedded in an epoxy matrix.
    These composite materials have, with respect to metal materials, better specific mechanical characteristics, that is to say related to their density, such as, for example, static and fatigue tensile strengths as well as modules also knowing that the Young's modulus of metals can be matched by some of these composite materials.
    In other words, such materials are well suited for the manufacture of rotorcraft rotor blades whose mass must be as low as possible. In fact, these materials have, as previously seen, a high specific modulus and therefore a low density for a modulus of elasticity or maximum Young's modulus. In particular, it is possible to obtain a Young's modulus greater than or equal to 70000 MPa for a density of less than 2000 kg / m3.
    In practice, the rigid portion of the root zone of the blade may comprise a "roving" strap embedded within the material or materials forming all or part of the blade, the roving strap forming a loop to form at least one portion of the periphery of the recess of the blade, this loop being extended by two rectilinear portions disposed respectively on either side of the recess and then in the profiled zone of the blade to the outer end, also called free end of the blade, that is to say the end intended to be positioned furthest from the axis of rotation of the rotor.
    More specifically, the roving strap, adhering to the composite materials forming the blade and the rigid portion of the root zone, is a spar that transmits to the laminated spherical stop the centrifugal force generated by the rotation of the corresponding blade. It is an essential resistant element that simultaneously strengthens the blade and the rigid portion of the root zone comprising the recess.
    Such a roving strap is in particular in the form of skeins or in the form of rovings, each of its forms being for example based on R glass fibers impregnated in a matrix of thermoplastic or thermosetting resin type. The realization of this roving strap is either manual or mechanized and consists of stacking roving ribbons on tooling mandrels or filling the blade and after additional constitution of the blade, perform a polymerization phase of all by application of a heating cycle.
    The present invention also relates to a rotorcraft rotor having at least two monolithic blades, a hub for driving in rotation the at least two blades around an axis of rotation of the rotor and at least two laminated spherical abutments respectively forming each a ball-type connection between each blade and the hub.
    Such a rotorcraft rotor is remarkable in that the at least two blades are as previously described.
    Such a rotor thus comprises a plurality of blades as described above allowing the use of specific laminated spherical stops less loaded and reduce the number of hinge masses resulting in a reduction in mass and a better vibratory level.
    Advantageously, the rotor may comprise at least one drag damper secured in type connection with the hub, each spherical finger of the at least two blades cooperating in a linear annular type of connection with a corresponding cylindrical bore formed in the damper of trail.
    Such a drag damper is then arranged near the axis of rotation of the rotor. The cylindrical bore cooperating with the finger is in turn arranged substantially radially with respect to the axis of rotation of the rotor to enable an annular linear type connection to be made with this finger.
    According to a first variant of the invention, the trailing damper (s) may be composed of a plurality of disjoint members, arranged circumferentially around the axis of rotation of the hub, and each having a cylindrical bore cooperating with each spherical finger of the at least two blades.
    In this case, the various disjoint members are secured independently in connection with the type embedded with the hub of the rotor.
    According to a second variant of the invention, the trailing damper (s) may be composed of a monolithic ring disposed circumferentially around the axis of rotation of the hub, and comprising at least two cylindrical bores respectively cooperating respectively with a spherical finger of the at least two blades.
    In this case, the monolithic ring cooperates with the different blades and thus comprises several cylindrical bores oriented radially.
    In practice, the (or) drag damper (s) can (may) be laminated type (s).
    In other words, such drag dampers then comprise an inner armature forming the cylindrical bores, then on either side a stack of flexible main layers interposed between rigid secondary layers and an outer armature covering the assembly thus formed. . The inner and outer armatures may be formed of a metallic material, for example aluminum alloy or steel. The main flexible layers can in turn be formed from an elastomeric material of the polyurethane or rubber type, stacked alternately with rigid secondary layers for example of metal material, for example aluminum alloy or steel. The stacking of the main flexible layers and rigid secondary layers is carried out either along a vertical axis or along a radial axis. Such elastomeric damper configurations and technologies are commonly used today.
    In addition, the invention also relates to a rotorcraft comprising a rotor as described above.
    Thus, the invention relates to a rotorcraft equipped for example with a main rotor and / or an anti-torque rotor equipped with monolithic blades as previously described. The invention and its advantages will appear in more detail in the context of the following description with examples given by way of illustration with reference to the appended figures which represent: FIG. 1, a perspective view from above of a compliant rotorcraft according to the invention equipped with a rotor according to a first variant of the invention, - Figure 2, a perspective view from above of a rotor according to a second variant of the invention, - Figure 3, a view of bottom view of the rotor according to the first variant of the invention, - Figure 4, a perspective view of a blade according to a second embodiment, in accordance with the invention, - Figure 5, a partial section in view the face of said blade according to a second embodiment, - Figure 6, a sectional view AA as indicated in Figure 5 of said blade according to the second embodiment, - Figure 7, a section for side of a gir rotor aircraft equipped with said blade according to the second embodiment, - Figure 8, a sectional side view of a blade according to another embodiment according to the invention, - Figure 9, a sectional view BB such that indicated in Figure 7 of a blade according to a first embodiment, and - Figures 10 and 11, sectional views BB as shown in Figure 7 of two alternatives corresponding to said blade according to the second embodiment .
    The elements present in several distinct figures can be assigned a single reference.
    As already mentioned, the invention relates to the field of rotary wing aircraft such as rotorcraft.
    As represented in FIG. 1, a rotorcraft 1 according to the invention is equipped with a rotor 10 comprising a hub 15 and monolithic blades 21 each respectively connected with such a hub 15 by their root zone 3.
    According to a first variant of the invention, the rotor 10 also comprises a drag damper 16 cooperating with the ends of the blades 21. The drag damper 16 is secured to the hub 15 in a connection-type connection and therefore has no degree of freedom with respect to this hub 15.
    In addition according to this first variant of the invention, the drag damper 16 is composed of a plurality of disjoint members 18 each cooperating individually with the root end of a blade 21 and in particular with a finger such as described later.
    As represented in FIG. 2 and according to a second variant of the invention, a rotorcraft according to the invention can be equipped with a rotor 11 comprising a hub 15, blades 21 and a drag damper 17 formed by a ring monolithic 19.
    Such drag dampers 16, 17 cooperating with the root ends of the blades 21 then make it possible to damp the drag oscillations of the blades 21.
    As represented in FIGS. 3 to 6, such a rotor 10 may for example comprise hubs 15 at the hub 15 which are hinged relative to a lower flange 6 of this hub 15. Such return arms 52 may be controlled collectively or cyclically and then make it possible to transmit a rotational movement in steps to the different blades 21 each equipped respectively with a pitch lever 50, rotated by a connecting rod 61 connected to a return beam 52, the pitch lever 50 forming an outgrowth in a direction parallel to a transverse direction 41, itself perpendicular to a longitudinal direction 49 according to the span of the blade 21. Moreover, the transverse direction 41 forms with the longitudinal direction 49 a median plane 45 of symmetry for all or part of the root zone 3 of the blade 21.
    According to FIG. 4, the blade 21 comprises at the root end 33 of the root zone 3 a spherical finger 24 intended to cooperate with the drag damper 16, 17. The root zone 3 of the blade 21 also comprises a flexible portion 26 and a recess 23 formed in a rigid portion 64 for accommodating a laminated spherical abutment 22.
    Such a flexible portion 26 is remarkable in that it comprises a preferred flexural deformation direction along a beat axis 40 with respect to a bending deformation direction along a drag axis 53. Such a flexible portion 26 is thus flexible. in flexion along the beat axis 40 but is rigidly opposed in flexion along the drag axis 53.
    Advantageously, the finger 24 may be formed in the same material as that used to form the flexible portion 26 but such a finger 24 may also be attached at the root end 33 of the blade 21 and be formed in another material than that of the flexible portion 26.
    As shown in FIGS. 5 and 7, the flexible portion 26 of the blade 21 may comprise a first form of plate 28 having a first predetermined thickness e1 and a second form of plate 29 having a second predetermined thickness e2.
    The first form of plate 28 is integral with the spherical finger 24 while the second form of plate 29 is arranged close to the recess 23. The first form of plate 28 is otherwise continuous coplanar with the second form plate 29.
    According to another embodiment according to the invention as shown in FIG. 8, the flexible portion 125 of the blade 121 may also comprise a plate shape 128 whose cross-sectional thickness varies continuously between a minimum thickness e1 and a maximum thickness e2 'in the direction of the span of the blade 121. The thickness of the cross section can thus grow continuously along the flexible portion 125 between the finger 24 and the rigid portion 64 comprising the obviously 23 of the root zone 3.
    As shown in FIG. 5, the blade 21 comprises a narrowing 27 arranged at a transverse direction 41 distant and parallel with respect to a transverse direction 42 of the sections at a zone 30 of the blade 21 having a shape aerodynamically profiled, said profiled zone 30 as seen above.
    As shown in FIG. 7, at the narrowing 27 is the recess 23 opening on either side of the rigid portion 64 of the root zone 3 of the blade 21 between a first face 34 extending one face extrados 31 of the profiled zone 30 and a second face 35 extending a lower face 32 of the profiled zone 30.
    According to FIGS. 5 and 6, the blade 21 also comprises a roving strap 38 embedded in the materials forming the blade 21. Such a roving strap 38 is therefore in the form of skeins or in the form of rovings, each of its forms being for example based on fiberglass R.
    The "roving" strap 38 allows at least partially surround the periphery 39 of the recess 23 with a curved portion 43 and two straight portions 44 on either side of the recess 23 extending into the profiled zone 30 until at the free end of the blade 21. This "roving" strap 38 thus makes it possible to form the spar of the blade 21 and consequently guarantees the mechanical strength of a blade 21 biased by a large centrifugal force during the rotation of the blade. rotor 10.
    In addition, as shown in FIG. 7, the hub 15 comprises a lower flange 6 and an upper flange 5 secured on the one hand with the laminated spherical abutments 22 and on the other hand with the trailing damper 16.
    The connection between the lower flange 6, the upper flange 5 and the laminated spherical abutments 22 is of the recessed type and comprises, for example, clamping members 63 such as screws, bolts or the like. Similarly, the connection between the blade 21 and the laminated spherical abutment 22 is of the embedding type and may comprise a connecting piece 22 'attached to the inside of the recess 23 and secured to the blade 21 by clamping members 62 such as than screws, bolts or the like. Such a connecting piece 22 'then makes it possible to form an internal protrusion to the recess 23 with which the laminated spherical abutment 22 can be secured in a mechanical connection of the embedding type obtained for example by a gluing process.
    Moreover, as already indicated, such a drag damper 16 may comprise several disjointed members 18 each having a cylindrical bore 14 cooperating in a linear annular type connection with the finger 24.
    As shown, the flexible portion 26 of the blade 21 is arranged symmetrically on either side of the median plane 45. However, such a flexible portion 26 may have different shapes of cross sections.
    Thus, according to a first exemplary embodiment shown in FIG. 9, the root zone 2 of the blade 20 has a flexible portion 25 which has a cross-section 36 in the form of I. In this case, the flexible portion 25 comprises two edges 46, 47 forming symmetrical excrescences on either side of the median plane 45.
    According to Figures 10 and 11 and according to a second embodiment, the root zone 3 of the blade 21, 51 comprises a flexible portion 26, 56 having a rectangular cross section 37, 57.
    A first alternative is illustrated in FIG. 10. In this case, the cross section 37 of the flexible portion 26 of the blade 21 has an internal structure 55 in the shape of an I, ensuring the resistance of this flexible portion 26 and filling layers. 58, 59 disposed symmetrically on either side of the median plane 45. Such filling layers 58, 59 can thus be made in a material different from that used to form the internal structure 55 in the form of I.
    For example, the internal structure 55 can be made by a stack of glass or carbon rovings whose fibers are oriented parallel to the longitudinal direction 49 of the blade 21. The filling layers 58 and 59 can be made by stacks of tissue of glass or carbon oriented in a balanced manner to plus or minus 45 degrees relative to the longitudinal direction 49 of the blade 21. The assembly formed by the internal structure 55 and the filling layers 58, 59 is covered with a coating based on twill fabrics consisting of R-weighted glass fibers balanced in the warp and weft directions.
    A second alternative is illustrated in FIG. 11. In this case, the transverse section 57 of the flexible portion 56 of the blade 51 can be formed by the superposition of textile plies 60. The flexible portion 56 is then formed by laminated composite materials. to form a plurality of textile plies 60 embedded in a matrix. For example, the textile plies 60 make it possible to form a stack of glass fabrics oriented in a balanced manner at plus or minus 45 degrees with respect to the longitudinal direction 49 (span) of the blade 51.
    Under these conditions, the transition relative to the materials in the root zone 2, 3 of the blade 20, 21, 51 is specified below. The transition between the finger 24, which may be metallic, and the first form of plate 28 is ensured, for example, by screws implanted in threaded metal inserts arranged in the thickness of the flexible portion 26.
    In another embodiment of the invention in which the finger 24 is formed in a composite material, the connection with the flexible portion 28 may be provided by an extension of the reinforcing fibers constituting the flexible portion 28 possibly being supplemented by fibers additional reinforcement positioned near the finger 24 spherical scope.
    Moreover, the transition of the materials between the second form of plate 28, 29 and the rigid portion 64 of the root zone 2, 3 of blade 20, 21, 51 can be ensured at the surface by an extension of the reinforcing cloths. the root zone 2, 3 of the blade 20, 21, 51. Likewise at the core, unidirectional reinforcing fibers may be arranged against the roving strap 38 at the level of the rigid portion 64.
    Finally, the transition of the materials between the rigid portion 64 and the profiled zone 30 of the blade 20, 21, 51 is made in such a way as to ensure a continuity of the reinforcing fibers arranged at the level of the narrowing 27 between, on the one hand, the roving strap. 38 and secondly reinforcements of the root zone 2, 3. The two rectilinear portions 44 of the roving strap 38 are disposed on either side of the recess 23 and extend to the common portion 48 of the blade 21. The surface reinforcing fabrics originating from the running portion 48 of the blade are, for example, partially cut and folded inside the recess 23 in order to ensure better attachment of the edge fabrics of the blade. recess 23.
    Naturally, the present invention is subject to many variations as to its implementation. Although several embodiments have been described, it is well understood that it is not conceivable to exhaustively identify all the possible modes. It is of course conceivable to replace a means described by equivalent means without departing from the scope of the present invention.
    权利要求:
    Claims (16)
    [1" id="c-fr-0001]
    Monolithic blade (20, 21, 51, 121) of a rotorcraft rotor (1, 11, 11), said blade (20, 21, 51, 121) comprising at least locally a profiled zone (30) comprising a lower face (32) and an extrados face (31), characterized in that said blade (20, 21, 51, 121) comprises a root zone (2, 3) comprising: • a finger ( 24) having a spherical bearing arranged at a root end (33) of said blade (20, 21, 51, 121), said finger (24) being intended to cooperate in an annular linear type connection with a bore cylindrical (14), • a recess (23) opening on either side of a rigid portion (64) of the blade (20, 21, 51, 121) between a first face (34) and a second face ( 35) respectively extending said extrados face (31) and said intrados face (32) of said profiled zone (30) towards said root end (33), said recess (23) being able to receive a spherical stop l amifiée (22), and • a flexible portion (25, 26) having a direction of flexural deformation preferred along a beat axis (40) of said blade (20, 21, 51, 121), said flexible portion (25, 26) being arranged between said finger (24) and said recess (23) adapted to receive said laminated spherical stop (22).
    [2" id="c-fr-0002]
    2. blade according to claim 1, characterized in that said recess (23) is arranged at a narrowing (27) of a rope of said blade (20, 21, 51, 121) in said root zone (2, 3), said narrowing (27) corresponding to a reduction of the chord of said blade (20, 21, 51, 121) relative to the chord of the profiled zone (30) of said blade (20, 21, 51, 121).
    [3" id="c-fr-0003]
    3. blade according to any one of claims 1 to 2, characterized in that said flexible portion (25, 26, 125) comprises all or part of a plate form (28, 29, 128).
    [4" id="c-fr-0004]
    4. Blade according to claim 3, characterized in that said flexible portion (25, 26) comprises wholly or partly a first form of plate (28) having a first predetermined thickness e1 and a second form of plate (29) having a second predetermined thickness e2, said first plate form (28) being integral with said spherical bearing finger (24), said second plate form (29) being arranged proximate said recess (23), said first plate form (28) being coplanarly juxtaposed with said second plate form (29).
    [5" id="c-fr-0005]
    5. blade according to claim 3, characterized in that the flexible portion (125) comprises a plurality of cross sections having a thickness gradually varying from a minimum thickness e1 'to a maximum thickness e2' in the direction of the span of the blade (121).
    [6" id="c-fr-0006]
    6. blade according to any one of claims 1 to 5, characterized in that said flexible portion (25, 26, 125) is arranged symmetrically on either side of a median plane (45) for said zone of root (2, 3) of said blade (20, 21, 51, 121).
    [7" id="c-fr-0007]
    7. blade (20) according to claim 6, characterized in that said flexible portion (25) comprises at least locally a cross section (36) I-shaped and has two borders (46, 47) forming symmetrical excrescences from and other of said median plane (45) of said root zone (2) of said blade (20).
    [8" id="c-fr-0008]
    8. blade (21, 51) according to claim 6, characterized in that said flexible portion (26, 56) comprises at least locally a cross section (37, 57) of rectangular shape arranged symmetrically with respect to said median plane (45) said root zone (3) of said blade (21, 51).
    [9" id="c-fr-0009]
    9. blade according to any one of claims 1 to 8, characterized in that at least said root zone (2, 3) of said blade (20, 21, 51, 121) is formed in at least one selected composite material among the group comprising epoxidized polymers, epoxy resins, epoxy resins filled with reinforcing fibers, textile mats based on reinforcing fibers and then embedded in an epoxy matrix and woven, knitted or braided textile webs based on reinforcement and then embedded in an epoxy matrix.
    [10" id="c-fr-0010]
    10. blade according to any one of claims 1 to 9, characterized in that said rigid portion (64) of the root zone (3) of said blade (20, 21, 51, 121) comprises a strap " roving "(38) embedded within at least one material forming all or part of said blade (20, 21, 51, 121), said roving strap (38) forming a loop to form at least a portion of the periphery (39) of said recess (23) of said blade (20, 21, 51, 121) comprising a curved portion (43) and two rectilinear portions (44) on either side of the recess (23), a such loop extending from said recess (23) in said profiled zone (30) of said blade (20, 21, 51, 121) to its free end.
    [11" id="c-fr-0011]
    11. Rotorcraft rotor (10, 11) having at least two monolithic blades (20, 21, 51), a hub (15) for rotating said at least two blades (20, 21, 51, 121) about an axis of rotation (12) of said rotor (10, 11) and at least two laminated spherical abutments (22) each respectively forming a ball-type connection between each blade (20, 21, 51, 121) and said hub (15), characterized in that said at least two blades (20, 21, 51, 121) are according to any one of claims 1 to 10.
    [12" id="c-fr-0012]
    12. Rotor according to claim 11, characterized in that said rotor (10, 11) comprises at least one drag damper (16, 17) secured in type connection with said hub (15), each finger (24) to spherical bearing surface of said at least two blades (20, 21, 51, 121) cooperating in an annular linear type connection with a cylindrical bore (14) formed in said drag damper (16, 17).
    [13" id="c-fr-0013]
    13. Rotor (10) according to claim 12, characterized in that said at least one drag damper (16) is composed of a plurality of disjoint members (18) each having a cylindrical bore (14) cooperating with each finger (24) spherical bearing of said at least two blades (20, 21, 51, 121).
    [14" id="c-fr-0014]
    14. Rotor (11) according to claim 12, characterized in that said at least one drag damper (17) is formed by a monolithic ring (19) having at least two cylindrical bores (14) each cooperating respectively with a finger ( 24) with a spherical bearing surface of said at least two blades (20, 21, 51, 121).
    [15" id="c-fr-0015]
    15. Rotor (10, 11) according to any one of claims 12 to 14, characterized in that said at least one drag damper (16, 17) is of laminated type.
    [16" id="c-fr-0016]
    16. Giravion (1), characterized in that it comprises a rotor (10) according to any one of claims 11 to 15.
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    EP2540620B1|2015-02-25|Rotor blade and aircraft, equipped therewith
    EP0080920B1|1985-07-31|Rotor for rotor craft with articulated joints incorporated in the blade root
    EP2070819B1|2010-02-17|Rotorcraft blade, rotorcraft rotor equipped with said blade and method of manufacturing this blade
    US8272841B2|2012-09-25|Propeller blade retention
    EP0213016B1|1990-12-27|Mast hub unit and rotor head for a rotor craft incorporating it
    US5621967A|1997-04-22|Method of making a leading edge weight retention assembly for a helicopter rotor
    US9365285B2|2016-06-14|Propeller blade with reinforcing spars and boxes, and propeller comprising at least one such blade
    EP2481670B1|2014-06-04|Blade and method for manufacturing said blade
    EP0521792B1|1995-09-06|Rotary wing aircraft rotor head, rigid in drag and articulated in pitch and flapping
    EP0211740B1|1989-09-13|Mast hub unit and rotor head for a rotor craft incorporating it
    EP2818408A1|2014-12-31|Blade with reduced torsional rigidity and rotor provided with such a blade
    FR2689483A1|1993-10-08|Gyroplane rotor hub
    US20210062661A1|2021-03-04|Composite propulsor blade retention structure and method for constructing same
    同族专利:
    公开号 | 公开日
    US10301014B2|2019-05-28|
    CA2963655A1|2017-06-12|
    KR101958948B1|2019-03-18|
    FR3051439B1|2018-06-01|
    KR20170129634A|2017-11-27|
    CN107380429B|2020-04-21|
    US20170334555A1|2017-11-23|
    EP3246250A1|2017-11-22|
    PL3246250T3|2019-05-31|
    CN107380429A|2017-11-24|
    CA2963655C|2018-07-17|
    EP3246250B1|2018-11-28|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    DE2712706A1|1977-03-23|1978-10-19|Messerschmitt Boelkow Blohm|Rotary wing aircraft rotor head - has fibre reinforced plastics construction with hub disc sandwiched between two cover plates with spokes and assembly cured as unit|
    EP0034210A2|1980-02-19|1981-08-26|Messerschmitt-Bölkow-Blohm Gesellschaft mit beschränkter Haftung|Helicopter rotor|
    FR2616409A1|1987-06-09|1988-12-16|Aerospatiale|BLADE OF COMPOSITE MATERIALS AND METHOD FOR MANUFACTURING THE SAME|
    FR2984849A1|2011-12-27|2013-06-28|Eurocopter France|LAMINATED TOGETHER, ROTOR WITH SUCH A ROCKET, AND AIRCRAFT|
    DE2806119C3|1978-02-14|1981-02-05|Messerschmitt-Boelkow-Blohm Gmbh, 8000 Muenchen|
    IT1196800B|1986-11-25|1988-11-25|Agusta Aeronaut Costr|ANTICOPE ROTOR FOR HELICOPTERS|
    US5738494A|1996-07-18|1998-04-14|Sikorsky Aircraft Corporation|Optimized composite flexbeam for helicopter rotors|US10457380B2|2017-06-28|2019-10-29|Bell Textron Inc.|Articulated rotor systems with pitch independent damping|
    US10597150B2|2018-04-24|2020-03-24|Textron Innovations Inc.|Articulated rotor systems with blade-to-blade damping|
    CN113247243B|2021-06-29|2021-09-28|四川腾盾科技有限公司|Seesaw type unmanned helicopter rotor wing structure and chord direction dynamic balance balancing method|
    法律状态:
    2017-05-23| PLFP| Fee payment|Year of fee payment: 2 |
    2017-11-24| PLSC| Search report ready|Effective date: 20171124 |
    2018-05-22| PLFP| Fee payment|Year of fee payment: 3 |
    2019-05-23| PLFP| Fee payment|Year of fee payment: 4 |
    2020-05-22| PLFP| Fee payment|Year of fee payment: 5 |
    2021-05-20| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1600782A|FR3051439B1|2016-05-17|2016-05-17|MONOLITHIC BLADE, ROTOR OF GIRAVION EQUIPPED WITH SUCH A MONOLITHIC BLADE AND ASSOCIATED GIRAVION|
    FR1600782|2016-05-17|FR1600782A| FR3051439B1|2016-05-17|2016-05-17|MONOLITHIC BLADE, ROTOR OF GIRAVION EQUIPPED WITH SUCH A MONOLITHIC BLADE AND ASSOCIATED GIRAVION|
    PL17165044T| PL3246250T3|2016-05-17|2017-04-05|A monolithic blade, a rotorcraft rotor fitted with such a monolithic blade, and an associated rotorcraft|
    EP17165044.3A| EP3246250B1|2016-05-17|2017-04-05|A monolithic blade, a rotorcraft rotor fitted with such a monolithic blade, and an associated rotorcraft|
    CA2963655A| CA2963655C|2016-05-17|2017-04-06|Monolithic blade, rotorcraft rotor equipped with such a monolithic blade and associated rotorcraft|
    CN201710329281.9A| CN107380429B|2016-05-17|2017-05-11|Integrated blade, rotorcraft rotor equipped with such an integrated blade, and associated rotorcraft|
    US15/594,961| US10301014B2|2016-05-17|2017-05-15|Monolithic blade, a rotorcraft rotor fitted with such a monolithic blade, and an associated rotorcraft|
    KR1020170061155A| KR101958948B1|2016-05-17|2017-05-17|A monolithic blade, a rotorcraft rotor fitted with such a monolithic blade, and an associated rotorcraft|
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