• 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:
    In a rotor blade coupling device (2) for coupling to a rotor mast, comprising a rotor head center piece (7), at least three rotor blade holders (4) fastened to the rotor head center piece (7) for accommodating at least three rotor blades lying in a rotor plane (RE) and at least one connection means between adjacent rotor blade holders (4), wherein the rotor blade holders (4) in each case about a vertically to the rotor plane (RE) standing pivot axis (RLL) are pivotally movable, wherein the at least one connecting means by a damping device (D) is formed, and wherein the rotor blade coupling device (2) a plate-shaped transfer element (10), which in each case crosses a rotor blade holder (4) and is coupled to at least one damping device (D), is to be provided with a rotor blade coupling device of a simplified construction which ensures improved damping against lead-lag movements. This is achieved in that the plate-shaped transfer element (10) crossing each rotor blade holder (4) forms part of two adjacent damping devices (D) and is in direct operative connection with the two adjacent damping devices (D).
    公开号:CH711754A2
    申请号:CH01360/16
    申请日:2016-10-11
    公开日:2017-05-15
    发明作者:Stucki Martin；Caminada Mario；Reginald Moser Patrick；Leibbrandt Riekert
    申请人:Marenco Swisshelicopter Ag；
    IPC主号:
    专利说明:

    Description TECHNICAL FIELD The present invention describes a rotor blade coupling device of a rotor head for a rotorcraft such as a helicopter or a helicopter according to the preamble of the first claim.
    The rotor blade coupling device according to the present invention is particularly concerned with the occurring during rotation of the rotor blades whipping and pivoting movements.
    Typically, rotor blade coupling devices comprise a vertical to the rotor level rotary joint with adjustable Winkelverstellwiderstand between individual rotor blade holders and a respective associated, buoyancy generating rotor blade. In the horizontal rotor plane occurs depending on the position of the respective rotor blade occurring pivotal movement. This pivotal movement is backward, i. against the direction of rotation ("lag") of a rotor blade, or forward, i. directed in the direction of rotation ("lead") of a rotor blade. Usually, the Winkelverstellwiderstand is adjustable by means of hydraulic damping elements which slow down or dampen such so-called lead-hunting movements. Hydraulic damping elements are particularly cumbersome in terms of assembly, inspection and maintenance. Such lead-hunt moves are mainly caused by Coriolis forces and air resistance, with centrifugal forces and inertial forces influencing the lead-jaw movements.
    PRIOR ART US 2008/0 159 862 A1 discloses, for example, rotor blade coupling devices in which a multiplicity of damping elements (resilient in the direction of rotation of the rotating rotor blades) are arranged as connecting elements between in each case two adjacent rotor blades and dampen the lead-hunting movements.
    Such known from US 2008/0 159 862 A1 damping elements between each two adjacent rotor blades are commonly referred to as "interblade" damper. The rotor blade coupling device known from US 2008/0159 862 A1 with damping elements between in each case two adjacent rotor blades corresponds to a complex construction. Thus, an additional arrangement of two joints and connecting tabs is necessary in the transition region between the individual damping elements and rotor blade holders, which require a particularly large amount of maintenance. Furthermore, it has been found that such two joints articulated by the blade-pitch axis can produce negative, dynamic effects.
    Below are further known from the prior art rotor blade coupling devices are named, which have connecting elements in the transverse region of the rotor blade mounts and damping means to dampen the lead hunting movements.
    From US 2010/0 215 496 A1 discloses a rotor blade coupling device is known, which has a similar structure as the rotor blade coupling device of US 2008/0 159 862 A1.
    The rotor blade coupling device known from US 2010/0 215 496 A1 comprises, as a region which traverses the rotor blade holder, a damping device, wherein this damping device comprises an elastomeric component. The damping is based on an elastic rotation of the elastomeric component. Between the damping devices are formed as connecting elements between the rotor blades preferably made of rigid material rods.
    The known from US 2010/0 215 496 A1 rotor blade coupling device is expensive to install and maintain.
    From US 4 915 585 a further rotor blade coupling device is known with a plurality of rotor blades each arranged on a rotor blades and damping means for damping of lead hunting movements. Furthermore, US Pat. No. 4,915,585 discloses damping devices as connecting means between adjacent rotor blade holders, so-called "interblade" dampers. In addition, according to a preferred variant, the rotor blade coupling device of US Pat. No. 4,915,585 each comprises the rotor blade holder crossing, V-shaped and rigidly formed lever elements, one lever arm of the lever element being articulated and the other lever arm being rigidly connected to a damping device.
    SUMMARY OF THE INVENTION It is an object of the present invention to provide a rotor blade coupling device of a simpler, low-articulation rotor blade coupling device which is simpler in construction and which ensures improved damping against lead-hauling movements compared with the rotor blade coupling devices known from the prior art.
    These objects are achieved by a rotor blade coupling device with the features of claim 1.
    According to the invention forms a respective rotor blade holder transverse plate-shaped transfer element is a component of two adjacent damping devices and is in direct operative connection with the two adjacent damping devices.
    The entirety of the transverse, plate-shaped transfer elements and damping devices form a split ring or a ring assembly. The split ring forms in coupled to the rotor head state of the rotor blade coupling device according to the invention no direct mechanical and rigid operative connection between the split ring and rotor mast, so that the split ring is mounted, so to speak, completely gimbal. The ring arrangement of the entirety of the transverse, plate-shaped transfer elements and damping devices may be substantially circular or polygonal, in particular pentagonal, formed.
    In other words, the split ring or the ring assembly of the rotor blade coupling device according to the invention can be regarded as a ring assembly with flexible sections, wherein the flexible sections are formed by the damping devices.
    It has been found advantageous that a particularly good damping is achieved by such a ring arrangement of the rotor blade coupling device according to the invention with respect to the so-called "regressive mode" with respect to ground resonance.
    Furthermore, it was surprisingly found that in the ring assembly of the rotor blade coupling device according to the invention, occurring during the rotation of the rotor blades, collective and cyclic impact movements have a reduced influence on the damping devices in comparison with the lead-lag damping systems known rotor blade coupling devices. In this context, it can also be mentioned as advantageous that in the rotor blade coupling device according to the invention such striking movements are already aerodynamically damped to a high degree, whereby an additional undesirable load on the components of the damping devices of the rotor blade coupling device according to the invention is reduced and thereby the life of the components of the damping devices is increased.
    According to a preferred embodiment, the rotor blade holder crossing, plate-shaped transfer element is designed angularly or circular segment-shaped with two arms, wherein two arms of each two adjacent transfer elements are indirectly connected to each other via the damping device designed as a plate damper. A sufficiently rigid design of the rotor blade holder crossing transfer elements can be achieved by the choice of material and / or geometry, in particular the thickness of the transfer element. Particularly preferred materials for achieving the required rigidity of the transfer elements in aircraft construction are conventional materials such as aluminum, steel, titanium or their alloys, or fiber composites, e.g. Carbon and / or glass fiber used.
    Preferably, the transverse, plate-shaped transfer elements are integrally formed, but it is also conceivable that the transverse, plate-shaped transfer elements are formed in several pieces. In the context of the present invention, in this context, in the case of a one-piece, plate-shaped transfer element as well as a multi-part, plate-shaped transfer element, this is a structurally rigid element without articulated sections.
    According to the invention, the transfer elements crossing the blade holders forms an integral part of two adjacent damping devices and is thus in direct operative connection with the two adjacent damping devices, an improved, direct distribution of the forces acting on one rotor blade on two damping devices, resulting in an improved Damping the lead-jaw movements results. According to the present invention, operative connection is understood to mean that the transverse transfer element is integrated into the damping device in such a way that a relative movement can take place between the transverse plate-shaped transfer element and the other components of the damping device. For the purposes of the present invention, a direct operative connection between the plate-shaped transfer element and the damping device is understood to mean that no additional joints are arranged between the transfer element and the damping device, in contrast to the rotor blade coupling device of US Pat. No. 4,915,585.
    For the purposes of the present invention, the rotor blade coupling device according to the invention can preferably be coupled to the rotor mast of a main rotor. Alternatively, however, it is also conceivable that the rotor blade coupling device according to the invention can be attached to the tail rotor. In addition, the application of the rotor blade coupling device according to the invention can relate to manned and unmanned rotorcraft.
    Preferably, the rotor blade coupling device according to the invention in each case comprises an elastomeric, spherical bearing element for a rotor blade holder in order to allow pivoting movements and impact movements. Particularly preferably, the spherical bearing elements are configured and arranged in the rotor blade coupling device, that the at least three rotor blade holders behave flexibly during rotation in the circumferential direction and the at least three rotor blade holders relative to the rotor head central piece with respect to a rotor longitudinal axis are pivotable about a pivot axis substantially vertical to the rotor plane and thereby allow "Iead-Jay" movements. Furthermore, the elastomeric, spherical bearing element is configured such that the elastomeric, spherical bearing element behaves flexibly in the direction of the impact movements. In addition, the elastomeric, spherical
    Bearing element designed so as to behave flexibly against «blade-pitch» rotations. Such configured bearing elements are known in professional circles as so-called "laminated spherical thrust hearing".
    Preferably, the rotor head central piece has at least two openings, wherein in each case an elastomeric, spherical bearing element is arranged in a breakthrough. Alternatively, it is conceivable that instead of a elastome-ren, spherical bearing element at this point, a mechanical bearing element is arranged.
    Such elastomeric spherical bearing elements advantageously effect a transmission of the centrifugal load of one rotor blade holder to the rotor mast. In particular, such elastomeric spherical bearing elements transmit the centrifugal force (under pressure) and allow for whipping, pivoting and so-called blade-pitch rotational motions. For the purposes of the present invention, the term "elastomeric" is understood to mean that rubber is preferably used as the material and that thereby the spherical bearings deform elastically under tensile and compressive loads, but then return to their original, undeformed shape.
    Further advantageous embodiments are specified in the dependent claims.
    Preferably, the transverse, plate-shaped transfer elements are tiltably mounted to the blade holders, for example by means of a sliding bearing, in particular ball joint bearing with a sliding layer, and / or by means of an elastomeric bearing, in particular ball joint bearing with one or more elastomer layers. Such a tilting bearing allows unhindered rotational movements between rotor blade holders and transfer elements.
    Preferably, the damping device is designed as a plate damper, wherein particularly preferably the plate damper comprises at least two spaced, each adjacent rotor blade holders transverse, plate-shaped transfer elements and at least partially receives. In other words, as cushioning devices, it is conceivable to use any desired design of plate dampers or any other "interblade" dampers, such as, for example, hydraulic dampers, which make it possible to accommodate the transverse, plate-shaped transfer elements.
    In other words, in the damping device designed as a plate damper, the damping takes place by a shear of elastomer plates as active units of the plate damper. The elastomeric sheets preferably behave viscoelastically, i. elastic for energy storage and viscous for energy absorption or energy conversion (damping).
    Preferably, the elastomer plates of the plate damper are rubber elements containing, for example, natural rubber, silicone rubber, ethylene-propylene-diene rubber (EPDM), polyurethane, butyl rubber, urethane rubber, polyvinyl acetate, polyvinyl chloride and the like. Ideally, a material with a loss factor of at least 0.1 is selected for the elastomer plates.
    Preferably, the plate-shaped transfer elements contain as materials metals, for example aluminum, steel or titanium, or fiber composites, e.g. Carbon, kevlar, aramid and / or glass fiber.
    According to the present invention, the plate-shaped transfer elements each crossing a rotor blade holder are understood to be part of two adjacent damping devices in that the transverse, plate-shaped transfer elements are at least partially received by the damping devices and in other words are integrated in the damping device. As a result of the integration of the plate-shaped transfer elements crossing the rotor blade holders in two adjacent damping devices, the transverse, plate-shaped transfer element is in direct operative connection with the two adjacent damping devices.
    Preferably, the tilting bearings in the transverse region of the rotor blade holders, in particular linear acting in the direction of rotation of the rotor blades and / or along the Blattanstellwinkelachse, stiffer than the arranged between the rotor blade holders, designed as a plate damper damping devices. For the purposes of the present invention, the stiffness of the dampening device designed as a plate damper is understood to mean a rigidity resulting from the choice of its components in combination with its geometry or shape and the formable fixing of the components.
    Preferably designed as a plate damper damper device of the inventive rotor blade coupling device to a stiffness between 0.5 kN / mm to 10 kN / mm, especially preferably between 1 kN / mm to 4 kN / mm, can be formed or formed. In other words, the stiffness is adjustable by damping device in the form of a plate damper in a simple manner specifically for the particular application, and in particular the natural frequencies of the rotor can be adjusted.
    Particularly preferably, the tilting bearings are formed at least three times, more preferably at least five times, in particular linear in the direction of rotation of the rotor blades and / or along the Blattanstellwinkelachse, stiffer than the arranged between the rotor blade holders, designed as a plate damper damping devices. The higher the rigidity of the tilting bearing is compared to the stiffness of the damping device, the less lossy are movements of the rotor blade holders to the split ring or the ring arrangement of the rotor blade coupling device according to the invention. Another aspect of the present invention relates to a rotor head comprising a rotor blade coupling device according to the invention for coupling to a rotor mast.
    According to a preferred development of the rotor blade coupling device according to the invention, the tilting bearings can be constructed from a tilt bearing mounting bolt and a spherical tilt bearing ball element, wherein the tilt bearing mounting bolt as the rotor blade holders radially outwardly substantially in the direction of Blattanstellwinkelachse be arranged extending.
    Alternatively, according to a further preferred embodiment of the rotor blade coupling device according to the invention, the tilting bearings can be inserted perpendicular to the ring plane of the split ring or the ring assembly in each case a transfer element.
    Brief Description of the Drawings A preferred embodiment of the subject invention will now be described in conjunction with the accompanying drawings. Show it:
    1 shows a perspective view of a preferred embodiment of the rotor blade coupling device according to the invention;
    2 shows a detailed view of the rotor blade coupling device 2 according to the invention with an enlarged view of a damping device D;
    3 shows a section along A-A in FIG. 1 through a rotor blade holder of the rotor blade coupling device according to the invention;
    4 shows a section along B-B in FIG. 1 between a rotor blade holder, tilting bearing and transfer element of the rotor blade coupling device according to the invention;
    5 shows a section along C-C in Figure 1 through a designed as a plate damper damping device D of the inventive rotor blade coupling device.
    6 shows a perspective view of a further preferred embodiment of the rotor blade coupling device according to the invention;
    7a shows a longitudinal section along A'-A 'in FIG. 6 through a rotor blade holder of the further preferred embodiment of the rotor blade coupling device according to the invention;
    FIG. 7b shows a longitudinal section along A'-A 'in FIG. 6 through a rotor blade holder of the further preferred embodiment of the rotor blade coupling device according to the invention with radially deflected tilting bearing fastening bolt;
    8a shows a cross section along B'-B 'in FIG. 6 through a rotor blade holder of the further preferred embodiment of the rotor blade coupling device according to the invention;
    8b shows a cross section along B'-B 'in FIG. 6 through a rotor blade holder of the rotor blade coupling device according to the invention with a tilting bearing fastening bolt deflected in the direction of rotation.
    Description: [0038] FIG. 1 shows a perspective view, obliquely from above, of a preferred embodiment of the rotor blade coupling device 2 of a rotor head 1. On the rotor head 1, five rotor blades (not illustrated here) can be fastened by means of the rotor blade coupling device 2 according to the invention. The rotor blade coupling device 2 comprises a rotor head center piece 7 and five rotor blade holders 4 fastened thereto for receiving five rotor blades. Rotorkopfzentralstück 7 is rotatably coupled to a rotor mast (not shown in Fig. 1), wherein the rotor mast by means of a drive not shown here is set in rotation and upon rotation in a direction of rotation U necessary for flying buoyancy force is effected.
    The rotor blade holders 4 each comprise an upper rotor blade holder plate 5 and a lower rotor blade holder plate 6. The rotor blade holder plates 5 and 6 have in an outer, radial region openings 33 for receiving elastically mounted bolts 34 for fixing rotor blades. In addition, in Fig. 1, a Blattverstellstange 35 can be seen coupled to a rotor blade holder 4, based on the Blattverstellstange 35 a coupled rotor blade holder 4 about a Blattanstellwinkelachse Rbp (also called blade-pitch axis) is rotatable and thereby the Blattanstellwinkel a rotor blade against the adjustable air is adjustable and the rotorcraft rises or falls (so-called "blade pitch").
    1, designed as a disk rotor head central piece 7 openings 8, wherein in the openings 8 each have an elastomeric spherical bearing element 20 is arranged. As indicated in FIG. 1 by a double arrow LL, the elastic, spherical bearing elements 20 each permit a spatial pivoting movement LL about a vertical axis of rotation RLL in relation to the described, depending on the orientation of a rotor blade 3 occurring Lead Jag movements. The pivoting movement LL can take place in the rotor plane RE in the circumferential direction U ("lead") or in the opposite direction to the rotational direction U ("lag").
    1, the entirety of the rotor blade holders 4 crossing transfer elements 10 and damping devices D is a split ring or a ring assembly, wherein - as shown in Fig. 1 - in coupled to the rotor head state of the inventive rotor blade coupling device no direct mechanical operative connection between the split ring and rotor mast, so that the split ring thanks to articulated connections between the upper and lower rotor blade mounts 5; 6 is completely gimbaled.
    From this and the following, like reference numerals designate like components in the figures.
    2 shows a detailed view of the rotor blade coupling device 2 according to the invention, namely an enlarged view of a damping device D, which is arranged as a so-called "interblade" damper between two adjacent blade holders 4 and designed as a plate damper.
    On a first arm 11 of a ring segment forming, plate-shaped transfer element 10, an upper damping element 15 'and a lower damping element 16' is mounted and thereby operatively integrated into the damping device D to form a first damping portion D1. In addition, an upper damping element 15 "and a lower damping element 16" are attached to a second arm 12 of an adjacent, plate-shaped transfer element 10 of an adjacent rotor blade holder 4 and are thereby integrated into the damping device in an actively connected manner to form a second damping section D 2. Here, the articulated connection advantageously becomes advantageous the adjacent ring segments forming, plate-shaped transfer elements 10 laid in the damping device D.
    As can be seen further in FIG. 2, the damping elements 15 '; 15 ", 16 ', 16" each have an elastomer plate 18 enclosed between two plates 17. The damping elements 15 '; 15 ", 16 ', 16" can be fixed to one another, for example, by vulcanization and / or by gluing. The plates 17 may be made of metals such as steel, aluminum or titanium, or fiber composites, for example.
    The damping device D comprises an upper connecting plate 28 and a lower connecting plate 29, which produce a connection between the first damping portion D1 and the second damping portion D2. By means of screws 30, the connecting plates 28; 29 and the other components of the damping sections D1; D2 fixed together and biased to a defined compression displacement.
    According to an alternative embodiment of the damping device D, it is conceivable that the damping elements 15 '; 15 "is firmly fixed to the upper connecting plate 28, for example by means of vulcanization, and thereby forms an upper damping unit forming a unit, advantageously on the side facing away from the arms 11, 12 (ie between the connecting plate 28 and the damping elements 15 ', 15") omitted a plate 17 and thereby weight can be saved. In an analogous manner, a lower, a unit forming damping member by a fixed fixation of the damping elements 16 '; 16 "may be formed with the lower connecting plate 29. For example, by means of screwing, the upper and lower damping components with the arms 11, 12 are fixed together.
    During operation of the rotor head takes place in the damping device D shown in Figure 2, a relative movement between the first arm 11 of a transfer member 10 and the other components in the first damping portion D1 by shearing the elastomer plates 18 of the damping elements 15 '; 16 'or a relative movement between the second arm 12 of a further transfer element 10 and the other components in the second damping section D2 by shearing the elastomer plates 18 of the damping elements 15 "; 16". Each damping element 15 '; 15 ", 16 ', 16" is sandwiched by two plates 17 and an elastomer plate 18 arranged therebetween, while the plate-shaped transfer elements 10 are each arranged between two damping elements 15'; 15 ", 16 ', 16" lie.
    3 shows a section along AA in FIG. 1 through a rotor blade holder 4 of the rotor blade coupling device according to the invention with an upper rotor blade holder plate 5 and a lower rotor blade holder plate 6. As shown in FIG. 3, a tilting bearing 25 is located in the region of the transfer element 10 arranged, which is composed of a tilting bearing mounting bolt 26 and a spherical Kipplagerkugelelement 27, wherein the Kipplagerbefestigungsbolzen 26 as the rotor blade holders 4 are arranged radially outwardly substantially in the direction of Blattanstellwinkelachse Rbp, wherein such an arrangement of the Kipplagerbefestigungsbolzen 26 at the rotation of the Blattanstellwinkelachse Rbp proves to be particularly advantageous. Furthermore, the tilting bearing 25 comprises a tilting bearing housing 40, which on the side facing the tilting bearing ball element 27 has a ball shape corresponding to the tilting bearing ball element 27. In the area between tilting bearing housing 40 and the tilting bearing ball element 27, a sliding layer, for example a Teflongleitschicht, or elastomer layer 41 is formed. The tilting bearing 25 is in a spacer 19 between the rotor blade mounting plates 5; 6 attached and fixed by means of fixing 42. Optionally, it is conceivable that the tilting bearing housing 40 and the spacer 19 is formed by an integrated, one-piece component, whereby advantageously the installation and maintenance costs can be minimized.
    An elastomeric, spherical bearing element 20 can be seen in an opening 8 of the rotor head center piece 7. The elastomeric, spherical bearing element 20 comprises a trained bearing component 21, a bearing component 22 designed as a spherical segment, and a bearing component 23 which receives the rotor head central portion 7 in sections.
    The bearing member 21 is substantially rigid with the rotor blade mounting plates 5; 6 connected. In addition, the bearing component 22 is a layered rubber-metal element which, by virtue of its flexible design, permits the pivot, impact and blade pitch adjustment.
    4 shows a section along BB in FIG. 1 between a rotor blade holder 4, tilting bearing 25 and transfer element 10 of the rotor blade coupling device 2 in the region of a recess 13 of the transfer element 10. As shown in FIG. 4, the tilting bearing 25 is in a spacer 19 is disposed between the upper rotor blade mounting plate 5 and the lower rotor blade mounting plate 6, whereby the transfer element 10 is tiltably mounted to the rotor blade holder 4 in connection with the "blade-pitch" setting. The tilting bearing 25 comprises a tilting bearing fastening bolt 26, which is surrounded by an outer tilting ball bearing element 27, with which the tilting bearing 25 is designed as a ball and socket joint. The tilt bearing ball element 27 is preferably made of higher strength metals such as steel or titanium or the like.
    In the following, FIG. 5 shows a section along C-C in FIG. 1 through a damping device D of the rotor blade coupling device designed as a plate damper.
    As can be seen in FIG. 5, the damping device D has four through bores 32. In each case a bore 32, a sleeve 31 is arranged, wherein the bias of the selected length of the sleeve 32 to a defined compression displacement is adjustable. In other words, the components of the damping device D are adjusted in a shift-controlled manner to the defined compression displacement.
    As can be seen in Fig. 5, damping elements 15 '; 15 ", 16 ', 16", which in each case comprise an elastomer plate 18 enclosed between two plates 17, in sections into the connecting plates 28; 29 and opposite in the arms 11; 12 arranged positively. By such an arrangement of the damping elements 15 '; 15 ", 16 ', 16" can advantageously be a relative movement, for example, of the arm 11 of the plate-shaped transfer element 10 in the direction x relative to the other components such as the connecting plates 28; 29 of the damping device D are damped.
    A relative movement, for example, of the arm 11 of a plate-shaped transfer element 10 in the direction x resulting from the lead-hunting movements of a rotor blade is in other words effected by shearing the elastomer plate 18 of the damping elements 15 '; 16 'attenuated via a damping section D1. As can be seen in Fig. 5, there are a space d1 (damping portion D1) and d2 (damping portion D2) in the region of the passage of the screws 30 through the arms 11 and arms 12 and the outer diameter of a sleeve 31, said gaps d1; Define d2 maximum displacement distances. Furthermore, between the first arm 11 of a plate-shaped transfer element 10 and the second arm 12 of a further plate-shaped transfer element 10, a further shift distance d3 is defined, this shift distance d3 ideally corresponding approximately to the sum of the shift distances d1 + d2.
    The plate-shaped transfer elements 10, or their arms 11; 12 can thanks to the spaces d1 and d2 in the x, y direction on the one hand elastic shear deformations and thanks to the elastic deformability to pressure in the damping elements 15 '; 16 'and 15 "; 16" also certain deformations in z-direction movements are absorbed.
    Fig. 6 shows a perspective view of another preferred embodiment of the inventive rotor blade coupling device 2, wherein the tilting bearing 25 is embedded in each case a transfer element 10 perpendicular to the ring plane of the split ring or the ring assembly.
    On a first arm 11 of a ring segment forming, plate-shaped transfer element 10, an upper damping element 15v and a lower damping element 161 is mounted and thereby operatively integrated into the damping device D to form a first damping portion D1.
    The tilting bearing 25 here comprises a tilting bearing housing 40, which on the tilting ball bearing element 27 side facing a Kipplagerkugelelement 27 corresponding spherical shape. The tilting bearing housing 40 is here received and secured in a recess of the plate-shaped transfer element 10. In the area between the tilting bearing housing 40 and the tilting bearing ball element 27 is a sliding layer, for example a Teflongleitschicht or a sliding layer of aluminum bronze or suitable plastics, or elastomer layer 41 is formed, which may be here with hardened and polished steel, ceramic or tungsten carbide in combination.
    In this embodiment, the tilting bearing fastening bolt 26 extends substantially between the upper rotor blade mounting plate 5 and the lower rotor blade mounting plate 6 of the rotor blade mounting 4.
    FIG. 7a shows a longitudinal section along A'-A 'in FIG. 6 through a rotor blade holder 4 of the rotor blade coupling device according to the invention.
    The rotor head central piece 7 here has openings 8, wherein in the apertures 8 each have an elastomeric, spherical bearing element 20 is arranged. In this case, the bearing element 20 comprises a designed bearing component 21, a bearing component 22 configured as a spherical segment, and a bearing component 23 which receives the rotor head centerpiece 7 in sections.
    The tilting bearing 25 includes a tilting bearing mounting bolt 26 which is surrounded by an outer Kipplagerkugelelement 27, whereby the tilting bearing 25 is formed as a ball joint bearing. The tilting bearing fastening bolt 26 extending between the upper rotor blade mounting plate 5 and the lower rotor blade mounting plate 6 is, as shown in FIG. 7a, received in an upper guide cylinder 43 and a lower guide cylinder 44, in which case the upper guide cylinder 43 is attached to the upper rotor blade mounting plate 5 and the lower guide cylinder 44 are integrally formed on the lower rotor blade mounting plate 6. Alternatively, it is conceivable, the guide cylinder 43; 44 form as independent components and to the rotor blade mounting plates 5; 6 to fix.
    As can be seen in Fig. 7a, the tilting bearing 25 is arranged in the region of the transfer element 10, which is composed of a tilt bearing mounting bolt 26 and a spherical Kipplagerkugelelement 27, wherein the Kipplagerbefestigungsbolzen 26 in the idle state or non-operating state of the rotor perpendicular to the ring plane standing or vertical to the Blattanstellwinkelachse Rbp standing arranged or aligned. In addition, here the tilt bearing mounting bolt 26 is arranged to extend parallel to a longitudinal axis of the bolt 34.
    In this context, Fig. 7b, the rotor blade coupling device 2 in the operating state of the rotor with rotating rotor blades, the tilting bearing mounting bolt 26 by a tilt angle a preferably of up to 20 °, more preferably tilted or deflected to 1 ° to 5 ° can.
    FIG. 7b shows by way of example a tilting bearing fastening bolt 26 deflected radially outward in the direction of the pitch angle axis Rbp by a tilt angle α.
    In the following, FIG. 8a shows a cross section along B'-B 'in FIG. 6 through a rotor blade holder of the further embodiment of the rotor blade coupling device according to the invention.
    Here, the tilting bearing mounting bolt 26 is arranged or aligned perpendicular to the ring plane in the idle state or non-operating state of the rotor.
    8b shows here by way of example a tilt bearing mounting bolt 26 deflected in the direction of rotation of the rotating rotor blades. In this case, the tilting bearing fastening bolt 26 can also be inclined in this direction by a tilt angle β of up to 20 °, particularly preferably up to 5 ° to 15 °, be tilted or deflected about the Blattanstellwinkelachse Rbp.
    Due to the design of the tilting bearing 25 as a ball and socket joint, the tilting bearing mounting bolt 26 can be rotated about all axes, i. E. in any intermediate positions or superimpositions of the deflections shown in FIGS. 7b and 8b to tilt or deflect the tilting angles a and ß.
    Such an arrangement and orientation of the tilting bearing mounting bolt 26 of the ball bearing formed as a tilting bearing 25 (as shown in FIGS. 6 to 8b) advantageously ensures a particularly good clearance and collision freedom. Typically, the deflections or tilting movements of the tilting bearing mounting bolt 26 are induced by the "biaditch" about a blade pitch axis Rbp, pivotal movements about the pivot axis RLL, and impact (also referred to as "flapping").
    REFERENCE SIGNS LIST 1 rotor head 2 rotor blade coupling device 4 rotor blade holder 5 upper rotor blade holder plate 6 lower rotor blade holder plate 7 rotor head centerpiece 8 aperture 10 transfer element 11 first arm 12 second arm 13 recess 15 ', 15 "upper damper element (of plate damper) 16', 16" lower damper element (of Plate damper) 17 plate (damping element) 18 elastomer plate (damping element)
    权利要求:
    Claims (7)
    [1]
    A rotor blade coupling device (2) for coupling to a rotor mast for forming a rotor head (1) of a rotorcraft, in particular a helicopter or helicopter, comprising - a rotor head center piece (7) - at least three rotor blade holders (4) fastened to the rotor head center piece (7) at least three rotor blades lying in a rotor plane (RE), and at least one connecting means between adjacent rotor blade holders (4), the rotor blade holders (4) each being pivotable about a pivot axis (RLL) vertical to the rotor plane (RE), the at least one Connecting means by a damping device (D) is formed, and wherein the rotor blade coupling device (2) each having a rotor blade holder (4) transversely, plate-shaped transfer element (10) coupled to at least one damping device (D), characterized in that each one rotor blade holder (4) Transverse transfer ement (10) forms part of two adjacent damping devices (D) and thereby is in direct operative connection with the two adjacent damping devices (D).
    [2]
    2. rotor blade coupling device (2) according to claim 1, characterized in that the transverse, transfer elements (10) to the rotor blade holders (4) by means of a tilting bearing (25) are tiltably mounted, for example by means of a sliding bearing, in particular ball joint bearing with a sliding layer (41). , and / or by means of an elastomer bearing, in particular ball joint bearing with one or more elastomer layers (41).
    [3]
    3. rotor blade coupling device (2) according to claim 1 or 2, characterized in that the damping device (D) is designed as a plate damper, wherein the plate damper comprises two spaced apart, each adjacent rotor blade holders (4) crossing, transfer elements (10) and at least partially receives ,
    [4]
    4. rotor blade coupling device (2) according to claim 3, characterized in that the tilting bearings (25) in the transverse region of the rotor blade holders (4), in particular linear in the direction of rotation of the rotor blades and / or along the Blattanstellwinkelachse (Rbp) acting, are stiffer than that arranged between the rotor blade holders (4), designed as a plate damper damping devices (D).
    [5]
    5. Rotor blade coupling device (2) according to claim 4, characterized in that designed as a plate damper damping device (D) to a stiffness between 0.5 kN / mm to 10 kN / mm, more preferably between 1 kN / mm to 4 kN / mm, can be formed or is formed.
    [6]
    6. rotor blade coupling device (2) according to claim 4 or 5, characterized in that the tilting bearing (25) at least three times, more preferably at least five times, in particular linear in the direction of rotation of the rotor blades and / or along the Blattanstellwinkelachse (Rbp) acting, stiffer than the arranged between the rotor blade holders (4), designed as a plate damper damping devices (D).
    [7]
    7. rotor head (1) comprising a rotor blade coupling device (2) for coupling with a rotor mast (9) according to one of the preceding claims.
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    同族专利:
    公开号 | 公开日
    CN106965927A|2017-07-21|
    RU2016144174A|2018-05-10|
    CH711738A1|2017-05-15|
    BR102016026434A2|2018-05-02|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US3842945A|1971-05-13|1974-10-22|J Potter|Viscoelastic damper|
    FR2516891B1|1981-11-25|1984-02-17|Aerospatiale|
    FR2630703B1|1988-04-29|1990-08-24|Aerospatiale|ROTOR HEAD OF A GIRAVION WITH ELASTIC RETURN INTERPAL DRAWERS WITH BUILT-IN DAMPING|
    FR2929675B1|2008-04-07|2013-02-22|Eurocopter France|IMPROVED VISCOELASTIC DAMPING DEVICE|
    CN202244082U|2011-08-29|2012-05-30|湖南山河科技股份有限公司|Shimmy damper for rotor wing of helicopter|
    CN102501970B|2011-11-15|2014-12-24|中国航空工业集团公司北京航空材料研究院|Band type damper and preparation method thereof|
    US9777788B2|2012-01-10|2017-10-03|Bell Helicopter Textron Inc.|Rotorcraft vibration suppression system in a four corner pylon mount configuration|
    法律状态:
    2018-10-31| PFA| Name/firm changed|Owner name: KOPTER GROUP AG, CH Free format text: FORMER OWNER: MARENCO SWISSHELICOPTER AG, CH |
    2020-09-15| AZW| Rejection (application)|
    优先权:
    申请号 | 申请日 | 专利标题
    CH01639/15A|CH711738A1|2015-11-11|2015-11-11|Blade coupling device for coupling with a rotor mast for forming a rotor head of a rotorcraft.|EP16197094.2A| EP3168146B1|2015-11-11|2016-11-03|Rotor blade coupling device of a rotor head for a rotorcraft|
    JP2016219841A| JP2017100706A|2015-11-11|2016-11-10|Rotor blade coupling device of rotor head for rotorcraft|
    RU2016144174A| RU2016144174A|2015-11-11|2016-11-10|Rotor head rotor blades communication device for rotor with rotor|
    CN201610998393.9A| CN106965927A|2015-11-11|2016-11-11|Rotor blade coupling arrangement for the rotor head of gyroplane|
    US15/349,273| US10759529B2|2015-11-11|2016-11-11|Rotor blade coupling device of a rotor head for a rotorcraft|
    BR102016026434-0A| BR102016026434A2|2015-11-11|2016-11-11|ROTATING WINGS AIRCRAFT HEAD ROTOR BLADES BLOCKING DEVICE|
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