A flexible hub axial hinge, hub and rotor

Abstract

The present invention relates to a flexible hub axial hinge, a hub and a rotor, belonging to the technical field of helicopters, and is used to solve the problem that the flapping of the rotor cannot be efficiently absorbed, resulting in poor aeroelastic stability of the helicopter rotor. The flexible hub axial hinge of the present invention is used to bridge the central component assembly and the blade, and includes a functional part and a limiting part; the limiting part is arranged between the central component assembly and the functional part; the functional part includes a sleeve, a tension-torsion plate assembly and a laminated flapping damping assembly; the limiting part includes a support shaft assembly; the support shaft assembly includes a support shaft and a rubber pad; the rubber pad is arranged between the support shaft and the laminated flapping damping assembly. The flexible hub axial hinge of the present invention can produce a composite damping effect, efficiently absorb the centrifugal force and flapping of the blade, and ensure the smooth flight of the helicopter; the hub of the present invention can ensure the maneuverability and followability of the helicopter; the rotor of the present invention can improve the flight performance of the helicopter.

Description

Technical Field

[0001] The present invention relates to the technical field of helicopters, and particularly relates to a flexible hub axial hinge, a hub and a rotor blade. Background Art

[0002] The rotor system is the core of a helicopter and is used to provide the lift for the helicopter to fly. The development of the rotor system of a helicopter has gone through three stages: the first generation is a rotor system that selects a hinged hub and metal rotor blades; the second generation is a rotor system that selects a star flexible hub, a titanium alloy ball flexible hub, and all-composite rotor blades; the third generation of rotor systems adopts large composite rotor blades, ball flexible hubs, bearingless tail rotors, etc. Most of the third-generation rotor systems have been widely installed and applied.

[0003] Currently, the research and development of the fourth-generation helicopter is in the process of technological advancement. The research and development technologies of the fourth-generation helicopter focus on bearingless rotor technology, rotor anti-icing technology, tiltrotor technology, smart rotor technology, etc., and have reached the scale of collective wisdom research and development.

[0004] Among them, because the bearingless rotor technology can significantly reduce the flapping, lead-lag, and pitch change motions of the helicopter rotor blades due to the action of various forces, objectively improving the maneuverability, agility, reliability, survivability, and maintenance supportability of the helicopter, and improving the flight quality of the helicopter, as well as the maneuverability and followability of the helicopter. The bearingless rotor is gradually becoming one of the preferred rotor configurations for advanced helicopters.

[0005] During the flight of a helicopter, the vibration of the bearingless rotor has a great impact on the flight performance of the helicopter. Especially when the flight speed is small or hovering, the aerodynamic damping is very small, and the lead-lag direction of the rotor will become an important factor affecting the aeroelastic stability of the rotor. In order to reduce the influence of the 300 swing of the rotor blade on the overall flight performance of the helicopter, a structural damping device is provided for the bearingless rotor.

[0006] In the prior art, a laminated lead-lag damper is usually adopted on a helicopter. The laminated lead-lag damper mainly generates elastic and damping stiffness through the shear deformation of a high-damping silicone rubber material, absorbs the lead-lag energy of the rotor, so as to meet the requirement of preventing the helicopter from resonating on the ground and in the air as much as possible.

[0007] The laminated lead-lag damper of the prior art is usually arranged at the connection between the rotor blade and the central component. Since the rotor blade is directly connected to the periphery of the central component, the flapping, pitch change, and lead-lag motions of the conventional bearingless rotor are all borne by the root of the connection, and the connection is extremely vulnerable to torque and cracks or fractures are likely to occur. Therefore, not only the life cycles of the hub central component and the rotor blade are affected, but also the flight safety of the helicopter is threatened, and the maintenance cost of the helicopter is increased.

[0008] How to provide a suitable damping device for a bearingless rotor to improve the service life of the hub, reduce maintenance costs, and meet the requirements of long-term high-performance flight of the helicopter is one of the technical problems. Summary of the Invention

[0009] In view of the above analysis, the present invention aims to provide a flexible hub axial hinge, a hub, and a rotor to solve the technical problems of low service life of the helicopter hub, high maintenance costs, and inability to meet the requirements of long-term high-performance flight of the helicopter.

[0010] The present invention is realized through the following technical solutions:

[0011] A flexible hub axial hinge for bridging a central component assembly and a blade, comprising a functional part and a limiting part; the distal end of the functional part is connected to the blade, and the limiting part is arranged between the central component assembly and the functional part; the functional part includes a sleeve, a tension-torsion plate assembly, and a laminated flapping damping assembly; the limiting part includes a support shaft assembly.

[0012] The laminated flapping damping assembly includes a balance shaft and a spherical plain bearing; a balance shaft spherical plain bearing hole is arranged in the middle of the balance shaft, and the outer ring of the spherical plain bearing is tightly connected in the balance shaft spherical plain bearing hole.

[0013] The support shaft includes an integrally formed support shaft baffle, a support shaft mounting part, and a support shaft positioning part; the support shaft mounting part and the support shaft positioning part are arranged on both sides of the support shaft baffle; the support shaft positioning part is a cylinder, and the cylinder of the support shaft positioning part is positioned and pressed at the inner ring of the spherical plain bearing.

[0014] The support shaft assembly includes a support shaft and a rubber pad; the rubber pad is arranged between the support shaft and the balance shaft of the laminated flapping damping assembly.

[0015] Further, the sleeve is an oval sleeve structure; a sleeve damper mounting part, a sleeve blade clamp mounting part, and a sleeve observation hole are arranged on the sleeve; the distal end of the sleeve is connected to a blade clamp assembly; the proximal end of the sleeve is connected to a baffle and a laminated flapping damping assembly.

[0016] Further, the tension-torsion plate assembly includes a tension-torsion bar and tension-torsion bar clips; the distal end of the tension-torsion bar is clamped between two tension-torsion bar clips and connected to the sleeve through the blade clamp assembly; the proximal end of the tension-torsion bar is connected to the central component assembly.

[0017] Further, the proximal end of the tension-torsion bar clip is provided with an arc-shaped flange deviating from the tension-torsion bar.

[0018] Further, the tension-torsion bar is in a Y-shaped structure, and the proximal end of the tension-torsion bar is two branch structures.

[0019] Furthermore, the sleeve is made of a composite material; and the torsion strip is made of 301 stainless steel.

[0020] Furthermore, the stacked shimmy damping assembly includes a stacked shimmy damper; the balancing shaft is arranged through the proximal end of the sleeve, and both ends of the balancing shaft extend out of the sleeve at the sleeve damper mounting portion and are respectively connected to a stacked shimmy damper on the outside of the sleeve; the spherical bearing is installed in the middle of the balancing shaft.

[0021] Furthermore, the limiting portion includes a support shaft assembly; two ends of the support shaft assembly are respectively connected to the balancing shaft and the central piece assembly.

[0022] Furthermore, the support shaft mounting portion and the support shaft positioning portion are arranged on both sides of the support shaft baffle.

[0023] Furthermore, the rubber pad is connected to the support shaft positioning portion of the support shaft, and the distal end surface of the rubber pad can contact the proximal end of the balancing shaft.

[0024] Furthermore, the baffle is arranged at the outer edge of the lower proximal end of the sleeve and is connected to the sleeve via a fastener assembly.

[0025] Furthermore, the baffle includes a baffle body and a baffle mounting ear, and the baffle mounting ear is arranged in the middle of the distal end plane of the baffle body to form a T-shaped structure with the baffle body.

[0026] A hub comprises a plurality of the flexible hub axial hinges and a central piece assembly; the plurality of the flexible hub axial hinges are evenly distributed around the central piece assembly; the support shaft of each of the flexible hub axial hinges is connected to the central piece assembly.

[0027] Furthermore, the propeller hub also includes a lower limit assembly; the lower limit assembly is connected to the central component assembly; the lower limit assembly is located on the mid-vertical line of the upper and lower directions of the sleeve, and is located below the support shaft assembly.

[0028] A rotor comprises one or more propeller hubs; wherein, in the case of comprising a plurality of propeller hubs, the central component assemblies in the plurality of propeller hubs are connected up and down along an axis; and a blade is connected to the distal end of the axial hinge of each flexible propeller hub.

[0029] Compared with the prior art, the present invention can at least achieve the following beneficial effects:

[0030] The hub of the present invention is provided with a flexible hub axial hinge between the central component assembly and the blade. Through the vibration absorption of the laminated flapping damper, support shaft assembly, etc., the flexible hub axial hinge can well absorb the flapping from the blade, effectively ensuring the stiffness and dynamic flexibility of the helicopter hub, optimizing the flight characteristics of the helicopter, and at the same time increasing the service life of the hub and the rotor.

[0031] The above technical solutions can also be combined with each other to achieve more preferred combined solutions. Other features and advantages of the present invention will be described in the subsequent specification, and some advantages can be made obvious from the specification or understood by implementing the present invention. The objectives and other advantages of the present invention can be realized and obtained from the content specifically pointed out in the specification and the drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] The drawings are only for the purpose of showing specific embodiments and are not considered as limitations of the present invention. Throughout the drawings, the same reference signs denote the same components.

[0033] Figure 1 Partial perspective view of the flexible hub axial hinge of Embodiment 1 of the present invention;

[0034] Figure 2 is Figure 1 Cross-sectional view along the vertical center line;

[0035] Figure 3 Schematic diagram of the sleeve structure of Embodiment 1 of the present invention;

[0036] Figure 4 Schematic diagram of the tension-torsion plate assembly structure of Embodiment 1 of the present invention;

[0037] Figure 5 Cross-sectional view of a part of the structure of Embodiment 1 of the present invention along the axis of the balance shaft;

[0038] Figure 6 Schematic diagram of the balance shaft structure of Embodiment 1 of the present invention;

[0039] Figure 7 Partial structure schematic diagram of the laminated flapping damper of Embodiment 1 of the present invention;

[0040] Figure 8 Schematic diagram of the support shaft structure of Embodiment 1 of the present invention;

[0041] Figure 9 Schematic diagram of the rubber pad structure of Embodiment 1 of the present invention;

[0042] Figure 10 Schematic diagram of the baffle structure of Embodiment 1 of the present invention;

[0043] Figure 11Schematic diagram of the central component cover plate according to Embodiment 1 of the present invention;

[0044] Figure 12 Schematic diagram of the paddle clip structure according to Embodiment 1 of the present invention;

[0045] Figure 13 Schematic diagram of the overall structure according to Embodiment 2 of the present invention;

[0046] Figure 14 is Figure 13 Half-sectional view along the vertical center line;

[0047] Figure 15 Partial perspective view of a part of the structure according to Embodiment 2 of the present invention;

[0048] Figure 16 Schematic diagram of the lower limit movement component structure according to Embodiment 2 of the present invention;

[0049] Figure 17 is Figure 16 Cross-sectional view taken along line B-B in;

[0050] Figure 18 Schematic diagram of the overall structure of the central component assembly according to Embodiment 2 of the present invention;

[0051] Figure 19 Front view semi-sectional schematic diagram of the central component assembly according to Embodiment 2 of the present invention;

[0052] Figure 20 Schematic diagram of the central component body structure according to Embodiment 2 of the present invention;

[0053] Figure 21 Schematic diagram of the limit ring structure according to Embodiment 2 of the present invention;

[0054] Figure 22 is Figure 21 Cross-sectional view of the preferred scheme of the limit ring according to Embodiment 2 of the present invention;

[0055] Figure 23 Schematic diagram of the structure of the rotor with a flexible hub axial hinge according to Embodiment 2 of the present invention.

[0056] Reference numerals:

[0057] 1. Sleeve; 11. Sleeve damper mounting part; 12. Sleeve paddle clip mounting part; 13. Sleeve rocker arm mounting position; 214. Sleeve observation hole; 2. Pull-twist piece assembly; 21. Pull-twist bar; 22. Pull-twist bar clip; 23. Pull-twist piece sleeve; 3. Stacked flapping damper assembly; 31. Stacked flapping damper; 311. Damper circumferential positioning part; 32. Balance shaft; 321. Balance shaft joint bearing hole; 322. Balance shaft circumferential positioning part; 323. Balance shaft fastening part; 33. Joint bearing; 4. Support shaft assembly; 41. Support shaft; 411. Support shaft baffle; 412. Support shaft mounting part; 413. Support shaft positioning part; 42. Rubber pad; 421. Rubber pad positioning hole; 5. Baffle; 51. Baffle body; 52. Baffle mounting ear; 521. Baffle mounting hole; 6. Central part assembly; 61. Central part body; 611. Rotor shaft mounting bushing; 6111. Spline; 612. Central part body mounting part; 6121. Central part lower stop mounting part; 6122. Central part pull-twist piece mounting part; 613. Central part stop ring limiting platform; 6131. Central part upper limiting platform; 6132. Central part stop ring block mounting part; 62. Central part cover plate; 621. Cover plate positioning sleeve; 622. Cover plate mounting part; 6221. Cover plate support shaft mounting part; 6222. Cover plate pull-twist piece mounting part; 63. Stop ring; 64. Stop ring block; 7. Paddle clip assembly; 71. Paddle clip; 711. Paddle clip pull-twist piece mounting part; 712. Paddle clip blade 300 mounting part; 72. Blade pin; 8. Lower stop assembly; 81. Lower stop fixed body; 811. Lower stop fixed body mounting end; 8111. Lower stop fixed body mounting hole; 812. Lower stop outer sleeve; 8121. Lower stop outer sleeve inner hole; 82. Lower stop support shaft; 821. Support shaft sliding shaft part; 822. Support shaft spring positioning part; 823. Support shaft stop ring limiting part; 8231. Support shaft stop ring limiting port; 824. Support shaft spherical part limiting part; 8241. Support shaft spherical part bayonet; 83. Spring; 84. Lower stop elastic body; 85. Lower stop elastic body fixing part; 9. Rocker arm assembly; 100. Flexible hub axial hinge; 200. Central part component; 300. Blade. Detailed implementation manners

[0058] The following will specifically describe the preferred embodiments of the present invention in conjunction with the accompanying drawings. Among them, the accompanying drawings form a part of the present invention and are used together with the embodiments of the present invention to explain the principle of the present invention, rather than to limit the scope of the present invention.

[0059] In conjunction with Figures 1 - 23 , the technical solution of the present invention will be described in more detail:

[0060] Definition of this embodiment: The present invention takes the central axis of the central component 6 as the central position. The end of each component close to the central position of the present invention is the proximal end, and the end of each component far from the central position of the present invention is the distal end. The up and down directions of the present invention are defined as the upper part when the helicopter is in the landing state or in the upright hovering state and the lower part as the lower. The fastener assembly of the present invention is a combination of a bolt, a spline nut and a dovetail pin or a combination with similar functions.

[0061] Meanwhile, it is noted that the blade 300 involved in the present invention is installed at the distal end of the flexible hub axial hinge 100 through the blade grip assembly 7.

[0062] As Figure 1 shown, the flexible hub axial hinge 100 of the present invention is used to bridge the blade 300 of the helicopter on the central component 6. The proximal end of the flexible hub axial hinge 100 is connected to the central component 6, and the distal end of the flexible hub axial hinge 100 is connected to the blade 300.

[0063] Multiple flexible hub axial hinges 100 and the central component 6 together form a hub with a flexible hub axial hinge.

[0064] At least one such hub and multiple blades 300 together form a drone rotor with a flexible hub axial hinge 100.

[0065] Embodiment 1

[0066] A flexible hub axial hinge.

[0067] The functional part of the flexible hub axial hinge 100 is used to realize the three motions of the blade 300: flapping, lead-lag and pitch change.

[0068] Next, in combination with Figures 1 - 12 , Figure 23 , the technical solution of the flexible hub axial hinge 100 of the present invention will be introduced:

[0069] As Figure 1 and Figure 2 shown, the flexible hub axial hinge 100 includes a functional part and a limiting part. The functional part includes a sleeve 1, a tension-torsion plate assembly 2, a laminated lead-lag damping assembly 3, a baffle 5 and a blade grip 71. The limiting part includes a support shaft assembly 4.

[0070] The proximal end of the blade grip 71 is used to connect the tension-torsion plate assembly 2 to the sleeve 1, and the proximal end of the blade grip 71 is used to connect the blade 300 to the flexible hub axial hinge 100.

[0071] The proximal end of the support shaft assembly 4 is used to connect to the central component 6. Specifically, the proximal end of the support shaft assembly 4 is connected to the central component cover plate 62. The distal end of the support shaft assembly 4 is used to connect to the laminated lead-lag damping assembly 3. Specifically, the distal end of the support shaft assembly 4 is connected to the balance shaft 32.

[0072] The limiting part of the flexible hub axial hinge 100 includes a support shaft assembly 4, which is used to define the positional relationship between the functional part of the flexible hub axial hinge 100 and the central part assembly 6. The limiting functional part for defining the extreme positional relationship between the functional part of the flexible hub axial hinge 100 and the central part assembly 6 further includes a lower stop assembly 8.

[0073] The support shaft assembly 4 and the lower stop assembly 8 enable the flapping and pitching motions of the flexible hub axial hinge 100 to be controlled within the involved range.

[0074] Among them, the lower stop assembly 8 is connected to the central part assembly 6, and the technical solution of the lower stop assembly 8 is introduced in Embodiment 2.

[0075] Next, the technical solution of the functional part of the flexible hub axial hinge 100 in Embodiment 1 will be introduced:

[0076] As Figure 3 shown, the sleeve 1 is a sleeve-type thin-walled part. Preferably: the structure of the sleeve 1 is an oval sleeve structure with a short axis in the up-down direction, which is a special-shaped structure, and the sleeve 1 is made of a composite material. Preferably, the sleeve 1 is laid with ±45° carbon fiber reinforced composite material. The structure and material of the sleeve 1 can enable itself to have sufficient strength to meet the structural design requirements of torsional stiffness.

[0077] Specifically, as Figure 3 shown, the sleeve of the sleeve 1 is provided with a sleeve rocker arm mounting position 13 at the proximal end.

[0078] The sleeve of the sleeve 1 has a local planar structure at the upper and lower parts of the proximal end, and a sleeve damper mounting part 11 is provided at the planar structure. The sleeve damper mounting part 11 is a set of through-hole structures penetrating up and down at the proximal end of the sleeve 1, including balance shaft through-holes located on the upper and lower surfaces, damper mounting holes located around the balance shaft through-holes, and sleeve baffle mounting holes close to the proximal end of the sleeve 1 and located on the lower surface of the sleeve 1.

[0079] As Figure 3 shown, the sleeve rocker arm mounting position 13 is arranged at one side of the proximal end of the sleeve 1 and is used to connect the rocker arm assembly 9 that provides the input force for the pitch change movement of the drone hub. Specifically, the sleeve rocker arm mounting position 13 is a through-hole structure.

[0080] Specifically, as Figure 3 shown, the sleeve of the sleeve 1 is provided with a sleeve paddle clip mounting part 12 with upper and lower through-mounted holes at the distal end, and the paddle clip 71 is connected to the sleeve paddle clip mounting part 12 of the sleeve 1 through a fastener assembly. The sleeve paddle clip mounting part 12 is a set of sleeve paddle clip mounting holes penetrating up and down at the distal end of the sleeve 1.

[0081] Specifically, asFigure 3 As shown, a plurality of sleeve observation holes 14 are further provided on both sides of the sleeve structure of the sleeve 1. On the one hand, the sleeve observation holes 14 facilitate observing the usage condition of the tension-torsion sheet assembly 2 in the flexible hub axial hinge 100, which is convenient for timely maintenance; on the other hand, it is beneficial to reduce the torsional stiffness of the sleeve 1 and maintain the flexibility of the hub to meet the design requirements. Preferably, in this embodiment 1, 2 pairs of sleeve observation holes 14 are provided on the sleeve 1.

[0082] The sleeve 1 can perform flapping and pitching motions around the spherical plain bearing 33. There is no structural limit on the outboard side in the span direction of the spherical plain bearing 33 because under the centrifugal force of the rotating blade 300, the tension-torsion bar 21 has a slight deformation in the length direction, allowing the spherical plain bearing 33 to make a small displacement movement on the support shaft 41.

[0083] As Figure 12 shown, the blade clamp 71 has a bilateral opposed-ear structure. Mounting hole structures are provided on each side of the opposed ears.

[0084] As Figure 12 shown, one of the opposed ears on the proximal side of the blade clamp 71 is the blade clamp tension-torsion sheet mounting portion 711.

[0085] Combined with Figure 1 , Figure 2 and Figure 12 shown, the tension-torsion sheet assembly 2 is arranged between the opposed ears of the blade clamp tension-torsion sheet mounting portion 711; the blade clamp 71 and the tension-torsion sheet assembly 2 are fixedly connected to the sleeve blade clamp mounting portion 12 of the sleeve 1 through a fastener combination.

[0086] As Figure 12 shown, one of the opposed ears on the distal side of the blade clamp 71 is the blade clamp blade mounting portion 712.

[0087] Combined with Figure 1 , Figure 2 , Figure 12 and Figure 23 shown, the proximal end of the blade 300 is mounted between the opposed ears of the blade clamp blade mounting portion 712, and the blade 300 is fixedly connected to the blade clamp 71 through a blade pin.

[0088] Preferably, the blade clamp tension-torsion sheet mounting portion 711 and the blade clamp blade mounting portion 712 of this embodiment 1 are respectively provided with 2 through mounting holes for the fasteners to pass through.

[0089] As Figure 1 and Figure 2 shown, the tension-torsion sheet assembly 2 is installed inside the sleeve 1; the distal end of the tension-torsion sheet assembly 2 is connected to the distal end of the sleeve 1 through the blade clamp 71; the proximal end of the tension-torsion sheet assembly 2 is connected to the central part cover plate 62.

[0090] As Figure 4As shown, specifically, the pull-twist piece assembly 2 of Embodiment 1 includes a pull-twist bar 21 and a pull-twist bar clip 22.

[0091] The distal end of the pull-twist bar 21 is clamped between two pull-twist bar clips 22. A pull-twist bar distal end bar mounting hole is provided at the distal end of the pull-twist bar 21, and a pull-twist bar clip distal end mounting hole is provided on the pull-twist bar clip 22.

[0092] The pull-twist bar distal end bar mounting hole and the pull-twist bar clip distal end mounting hole are in corresponding positions, jointly forming a distal pull-twist piece mounting hole system. This distal pull-twist piece mounting hole system is in corresponding position with the sleeve paddle clip mounting hole of the sleeve paddle clip mounting part 12, allowing a fastener bolt to pass through the distal pull-twist piece mounting hole system and the sleeve paddle clip mounting hole.

[0093] A pull-twist piece proximal end mounting hole is provided at the proximal end of the pull-twist bar 21 for connecting with the central part assembly 6.

[0094] In this way, both ends of the pull-twist piece assembly 2 are respectively connected to the central part assembly 6 and the paddle 300.

[0095] Preferably, the pull-twist bar 21 is made of stainless steel 301 material, having the characteristics that the strength and hardness are increased under good cold deformation processing and sufficient plasticity and toughness are retained. When the pull-twist bar 21 is impacted by an external force, it can elastically deform slightly and absorb more impact energy during the deformation process.

[0096] Preferably, the proximal end of the pull-twist bar 21 is bifurcated to form a symmetric pull-twist piece proximal end. At least one pull-twist piece proximal end mounting hole is provided on the Y-shaped structures of the two branches at the proximal end of the pull-twist bar 21.

[0097] The Y-shaped structure and material characteristics of the pull-twist bar 21 can well withstand the centrifugal force from the paddle 300, and through the two branches at the proximal end, further disperse the concentrated transmission of the centrifugal force to the central part assembly 6, effectively reducing the torsional stiffness of the rotor.

[0098] Preferably, a pull-twist piece sleeve 23 is installed in the distal pull-twist piece mounting hole system of the pull-twist piece assembly 2. The pull-twist piece sleeve 23 penetrates through the distal pull-twist piece mounting hole system.

[0099] Preferably, two groups of distal pull-twist piece mounting hole systems are provided in Embodiment 1.

[0100] Preferably, the pull-twist bar 21, the pull-twist bar clip 22 and the outer wall of the pull-twist piece sleeve 23 are in interference fit, so that after installation, the pull-twist piece assembly 2 can have structural consistency, which is beneficial to better transmit the centrifugal force and flapping.

[0101] Preferably, as Figure 4As shown, the proximal end of the tension-torsion bar clip 22 is provided with an arc-shaped flanging that deviates from the tension-torsion bar 21. The arc-shaped flanging of the tension-torsion bar clip 22 reserves a possible deformation area of the tension-torsion bar 21 caused during the flapping of the blade 300, so that the tension-torsion bar clip 22 does not hinder the deformation of the tension-torsion bar 21, and the tension-torsion bar 21 can deform freely, better absorb and bear the centrifugal force from the blade 300, and further better reduce the impact on the central component assembly 6, which helps to reduce the torsional stiffness of the rotor.

[0102] As Figure 2 and Figure 5 shown, the laminated flapping damper assembly 3 includes a laminated flapping damper 31, a balance shaft 32, and a spherical plain bearing 33; both ends of the balance shaft 32 are respectively connected to one laminated flapping damper 31, and the spherical plain bearing 33 is installed in the middle of the balance shaft 32.

[0103] Specifically, the balance shaft 32 is disposed through the middle position of the proximal end of the sleeve 1 in the up-down direction, and both ends of the balance shaft 32 pass through the sleeve 1 from the balance shaft through holes in the middle of the sleeve damper mounting portion 11; one laminated flapping damper 31 is respectively installed at both ends of the balance shaft 32 outside the sleeve 1, and the two laminated flapping dampers 31 are respectively fixed to both ends of the balance shaft 32 through fasteners, preferably spline nuts, to form a symmetrical structure relative to the sleeve 1. At the same time, the laminated flapping damper 31 is connected to the proximal end of the sleeve 1 through the damper mounting holes around the sleeve damper mounting portion 11 via a fastener assembly.

[0104] Specifically, as Figure 6 shown, a balance shaft spherical plain bearing hole 321 is provided in the middle of the balance shaft 32, and balance shaft fastening portions 323 for connecting spline nuts are respectively provided at both ends. The outer ring of the spherical plain bearing 33 is press-fitted and connected in the balance shaft spherical plain bearing hole 321.

[0105] Preferably, a balance shaft circumferential positioning portion 322 is provided at the root of the balance shaft fastening portion 323 for axially positioning the sleeve damper mounting portion 11. Preferably, the balance shaft circumferential positioning portion 322 is a stepped structure. The vertical plane of the step has a unique direction.

[0106] As Figure 7 shown, corresponding to the balance shaft circumferential positioning portion 322, a damper circumferential positioning portion 311 is matched and provided on the shaft table of the central mounting hole of the laminated flapping damper 31. This mechanism design can stably fix the laminated flapping damper 31 relative to the balance shaft 32 in the circumferential direction, ensuring the consistency of the damping effect of the two laminated flapping dampers 31 symmetrically arranged with respect to the sleeve 1.

[0107] As Figure 1 and Figure 2As shown, the baffle 5 is arranged at the outer edge of the lower part of the proximal end of the sleeve 1 and is connected to the baffle mounting hole of the sleeve 1 through a fastener assembly.

[0108] As Figure 10 shown, the baffle 5 includes a baffle body 51 and baffle mounting ears 52. The baffle mounting ears 52 are arranged in the middle of the distal plane of the baffle body 51 and form a T-shaped structure with the baffle body 51.

[0109] Among them, baffle mounting holes 521 are arranged on the baffle mounting ears 52. The positions of the baffle mounting holes 521 correspond to the baffle mounting holes in the lower part of the sleeve 1. The baffle mounting ears 52 are arranged inside the lower part of the proximal end of the sleeve 1. The baffle 5 is fixedly connected to the sleeve 1 through a fastener assembly. After connection. At this time, the distal plane of the baffle body 51 abuts against the proximal end face of the sleeve 1.

[0110] The following introduces the limiting part technical solution of the flexible hub axial hinge 100 of Embodiment 1:

[0111] As Figure 1 and Figure 2 shown, the limiting part of the flexible hub axial hinge 100 is connected between the flexible hub axial hinge 100 and the central component assembly 6 and is used to limit the positional relationship between the flexible hub axial hinge 100 and the central component assembly 6, including a support shaft assembly 4.

[0112] Both the support shaft assembly 4 and the balance shaft 32 are located on the vertical bisector in the up and down direction of the sleeve 1.

[0113] As Figure 8 shown, the support shaft assembly 4 includes a support shaft 41 and a rubber pad 42.

[0114] Specifically, the support shaft 41 includes an integrally formed support shaft baffle 411, a support shaft mounting portion 412, and a support shaft positioning portion 413. The support shaft mounting portion 412 and the support shaft positioning portion 413 are respectively arranged on both sides of the support shaft baffle 411.

[0115] Among them, the support shaft positioning portion 413 is a cylinder and is located at the distal end of the support shaft 41 and is used to connect the functional part of the flexible hub axial hinge 100. The cylinder of the support shaft positioning portion 413 is positioned and pressed at the inner ring of the spherical plain bearing 33. Here, the rotational movement of the flexible hub axial hinge 100 along the axis of the cylinder of the support shaft positioning portion 413 is shielded from being transmitted to the central component assembly 6, protecting the structural stability of the central component assembly 6.

[0116] Among them, the support shaft mounting portion 412 is located at the proximal end of the support shaft 41. At least two support shaft mounting holes are arranged on the support shaft mounting portion 412 and are used to connect the support shaft 41 to the central component assembly 6 through a fastener assembly.

[0117] AsFigure 9 As shown, the rubber pad 42 is an elastomer, and a rubber pad positioning hole 421 is provided in the middle; the rubber pad 42 is interference-fitted on the cylinder of the support shaft positioning portion 413 through the rubber pad positioning hole 421.

[0118] The rubber pad 42 is arranged between the laminated pendulum damping assembly 3 and the support shaft 41, and is specifically arranged between the support shaft baffle 411 of the support shaft 41 and the balance shaft 32 of the laminated pendulum damping assembly 3.

[0119] Specifically, the proximal end of the rubber pad 42 abuts against the distal end of the support shaft baffle 411, and the distal end of the rubber pad 42 abuts against the central portion of the proximal end of the balance shaft 32, specifically, the opposite surface of the surface where the joint bearing 33 is located.

[0120] The structure in which the rubber pad positioning hole 421 is interference-fitted on the cylinder of the support shaft positioning portion 413 can also be replaced by a technical solution in which the rubber pad 42 is limited and fixedly connected to the support shaft 41.

[0121] The rubber pad 42 is installed between the balance shaft 32 and the support shaft 41. When the sleeve 1 swings upward, the rubber pad 42 can provide buffering for the collision between the balance shaft 32 and the support shaft 41.

[0122] Embodiment 2

[0123] A hub.

[0124] The following combines Embodiment 1 and Figures 13 - 22 , and introduces the technical solution of the hub of Embodiment 2 of the present invention:

[0125] The hub of the present invention may include a plurality of flexible hub axial hinges 100 as described in Embodiment 1, and further includes a central member assembly 6 and a lower stop assembly 8. Each flexible hub axial hinge 100 is matched and connected with one lower stop assembly 8 to form a combination of a plurality of flexible hub axial hinges 100 and lower stop assemblies 8; a plurality of such combinations are circumferentially and evenly connected to the outer peripheral side of the central member assembly 6, and the support shaft 41 of the flexible hub axial hinge 100 is connected to the central member assembly 6.

[0126] Specifically in this Embodiment 2, the hub of Embodiment 2 includes two flexible hub axial hinges 100 as described in Embodiment 1, and further includes a central member assembly 6 and a lower stop assembly 8.

[0127] The lower stop assembly 8 is connected to the central member assembly 6 and cooperates with the baffle 5 in the flexible hub axial hinge 100 to limit the vibration amplitude of the flexible hub axial hinge 100 and the connected blade 300 relative to the central member assembly 6.

[0128] The lower stop assembly 8 of this Embodiment 2 is located on the vertical bisector in the up and down directions of the sleeve 1 and is located below the support shaft assembly 4.

[0129] As Figure 13 and Figure 14 shown, and in combination with Figure 15 shown, the lower limit moving component 8 is arranged at the lower part of the support shaft component 4. The upper part of the lower limit moving component 8 is fixedly connected upward to the central component assembly 6, and the two ends of the lower part of the lower limit moving component 8 are respectively in flexible contact with the central component assembly 6 and the proximal plane of the baffle body 51.

[0130] As Figure 16 and Figure 17 shown, the lower limit moving component 8 includes a lower limit moving fixed body 81, a lower limit moving support shaft 82, a spring 83, a lower limit moving elastic body 84 and a lower limit moving elastic body fixing member 85. The lower limit moving support shaft 82 is movably connected in the lower limit moving fixed body 81, the spring 83 is arranged between the lower limit moving support shaft 82 and the lower limit moving fixed body 81, and the lower limit moving elastic body 84 is connected to the distal end of the lower limit moving support shaft 82 through the lower limit moving elastic body fixing member 85.

[0131] Specifically, the lower limit moving fixed body 81 includes an integrally formed lower limit moving fixed body mounting end 811 and a lower limit moving outer sleeve 812.

[0132] At least two lower limit moving fixed body mounting holes 8111 are provided on the lower limit moving fixed body mounting end 811 for fastening and connecting the lower limit moving component 8 to the central component assembly 6 through a fastener combination.

[0133] As Figure 17 shown, the lower limit moving outer sleeve 812 is a sleeve structure with a central hole. The upper outer part of the lower limit moving outer sleeve 812 is integrally formed on the lower part of the lower limit moving fixed body 81. In addition to the through lower limit moving outer sleeve central hole, the sleeve structure of the lower limit moving outer sleeve 812 also has a lower limit moving outer sleeve inner hole 8121.

[0134] The lower limit moving support shaft 82 is a stepped shaft structure, and successively includes a support shaft limit ring limiting part 823, a support shaft sliding shaft part 821, a support shaft spring positioning part 822 and a support shaft spherical part limiting part 824 from the proximal end to the distal end.

[0135] Among them, a support shaft limit ring limiting opening 8231 is provided on the support shaft limit ring limiting part 823. The support shaft limit ring limiting opening 8231 is used for limiting the limit ring 63 of the central component assembly 6 therein. The limit ring 63 is an elastic ring that surrounds the periphery of the functional components of the central component assembly 6.

[0136] Among them, a support shaft spherical part bayonet 8241 is provided on the support shaft spherical part limiting part 824, and support shaft spherical part limiting part mounting holes are provided at both side ends of the support shaft spherical part bayonet 8241.

[0137] The support shaft spherical part bayonet 8241 is used for limiting the lower limit moving elastic body 84.

[0138] The lower limit elastic body 84 is an elastic sphere with a through hole in the middle. The lower limit elastic body fixing piece 85 is used to fasten the lower limit elastic body 84 to the lower limit support shaft 82. The lower limit elastic body fixing piece 85 passes through the mounting hole of the support shaft spherical piece limit portion and the through hole of the lower limit elastic body 84, and is a fastener assembly.

[0139] Preferably, the lower motion-limiting elastic body 84 of this embodiment 2 is a rigid metal ball.

[0140] like Figure 17 As shown, the spring 83 is limited between the inner hole 8121 of the lower limit sleeve and the support shaft spring positioning portion 822, and both ends of the spring 83 are limited by the pillow block.

[0141] Preferably, the inner hole 8121 of the lower limit sleeve and the sliding shaft portion 821 of the support shaft have a clearance fit close to a transition fit, and the surface processing accuracy and dimensional fit of the two allow the lower limit support shaft 82 to produce an axial sliding displacement at the inner hole of the lower limit sleeve 812 after being subjected to force.

[0142] The lower limit support shaft 82 is used to increase the gap between the central component 6 of the blade 300 (in other words, it can also be said to be the helicopter fuselage). When the blade 300 is in a low speed process, hovering state, or encountering a gust of wind, the lower limit support shaft 82 can prevent the blade 300 from colliding with the fuselage.

[0143] The working process of the lower limit support shaft 82 is:

[0144] Combination Figure 13 and Figure 17 As shown, a lower limit assembly 8 is installed on each side of the central component 6, and the lower limit fixing body 81 of the lower limit assembly 8 is fixedly connected to the central component 6 through at least 2, preferably 2 in this embodiment 2, fastener assemblies, and the lower limit support shaft 82 can move left and right at the center hole of the lower limit fixing body 81 and the inner hole 8121 of the lower limit sleeve.

[0145] When the blade 300 is in a low speed process and hovering state, the lower limit support shafts 82 on both sides drive the surrounding limit ring 63 of the central component 6 to squeeze the middle spring 83 to swing left and right. The distance that the limit ring 63 can move left and right is related to the result of dynamic calculation.

[0146] If the flexible hub axial hinge 100 on the first side drives the stop ring 63 to move beyond the limit, the spring 83 on the second side will be compressed to the shortest to prevent the stop ring 63 on the first side from colliding with the central component body 61. The reverse is also true.

[0147] When the total distance is large, the lower limit assembly 8 does not contact the collision baffle body 51.

[0148] In the second embodiment, when the blade 300 on one side flaps and the lower limit stop support shaft 82 of the flexible hub axial hinge 100 on the same side moves backward under force, the lower limit stop elastomer 84 will elastically collide with the baffle body 51 and limit the further downward flapping of the flexible hub axial hinge 100 driven by the blade 300; when the lower limit stop support shaft 82 moves forward under force, the elastic limit ring 63 elastically collides with the central component assembly 6 on the opposite side, protecting the central component assembly 6 while limiting the further upward flapping of the flexible hub axial hinge 100 on this side.

[0149] Therefore, the design of the lower limit stop assembly 8 and the elastic limit ring 63 of the present invention can effectively control the flapping amplitude of the blade 300, making the helicopter flight process, especially during the low rotational speed process, hovering state, and encountering sudden gusts, overall stable, and improving the flight performance of the helicopter.

[0150] The central component assembly 6 is a key component of the helicopter fuselage.

[0151] As Figure 18 and Figure 19 shown, the central component assembly 6 includes a central component body 61, a central component cover plate 62, a limit ring 63, and a limit ring stop block 64. The central component cover plate 62 is sleeved on the upper part of the central component body 61, and the limit ring stop block 64 is connected in a limited position on the circumferential side of the lower part of the central component body 61; the central component body 61 and the limit ring stop block 64 limit the limit ring 63 from above and below.

[0152] As Figure 20 shown, the central component body 61 includes a rotor shaft mounting bushing 611, a central component body mounting part 612, and a central component limit ring limiting platform 613 that are integrally formed.

[0153] The central component body mounting part 612 is plate-shaped and is symmetrically arranged on the outer side of the middle of the rotor shaft mounting bushing 611 and extends to both sides.

[0154] Central component lower limit stop connection parts 6122 are provided in the middle of both sides of the central component body mounting part 612.

[0155] Preferably, the central component lower limit stop connection parts 6122 in the second embodiment are 2 through holes, which match the lower limit stop fixed body mounting holes 8111 on the lower limit stop assembly 8; the lower limit stop assembly 8 is connected to the central component assembly 6 through a fastener combination.

[0156] Preferably, central component pull and torsion sheet mounting parts 6121 are symmetrically arranged on the outside of both sides of the central component body mounting part 612. The central component pull and torsion sheet mounting parts 6121 are at least 1 central component pull and torsion sheet mounting through hole, and the proximal ends of the pull and torsion bars 21 are respectively connected to the central component assembly 6 through a fastener combination.

[0157] Further preferably, central part body sinking slots are arranged in the middle parts on both sides of the central part body installation part 612, and the central part lower limit connection part 6122 is arranged in the central part body sinking slots. This setting can make the central part body installation part 612 as a whole an irregular structure, increasing the overall stiffness of the central part body 61, making the positioning of key parts such as the rotor shaft connected in the rotor shaft installation bushing 611, the support shaft 41 connected to the periphery, and the lower limit movement assembly 8 firm, and the structure stable, which is beneficial for the helicopter to have good flight performance.

[0158] Preferably, a spline 6111 is arranged in the rotor shaft installation bushing 611, and the spline 6111 is used for accurately positioning and connecting the rotor shaft and driving it through the rotor shaft.

[0159] Specifically, a pair of central part limit ring limit platforms 613 are symmetrically arranged in a mirror image on the outer periphery of the lower part of the rotor shaft installation bushing 611 and perpendicular to the long axis direction of the central part body installation part 612.

[0160] Preferably, the central part limit ring limit platform 613 of the second embodiment is a stepped platform structure; the higher platform is on the upper part, which is the central part upper limit platform 6131; the lower platform is on the lower part, which is the central part limit ring stopper installation part 6132; the central part limit ring stopper installation part 6132 is a threaded hole structure for installing the limit ring stopper 64.

[0161] As Figure 21 shown, the overall structure of the limit ring 63 is an elastic ring with a quasi-elliptical cross-section, which surrounds the periphery of the functional parts of the central part assembly 6.

[0162] As Figure 22 shown, preferably, the cross-section of the limit ring 63 is a non-uniform wall thickness structure. The wall thickness of the limit ring 63 in the long axis direction is C, and the wall thickness of the limit ring 63 in the short axis direction is B, and C > B. This setting enables the limit ring 63 to generate greater elasticity or damping when bearing pressure and tension in the long axis direction and is not easily damaged, further optimizing the elastic effect and service life of the limit ring 63.

[0163] As Figure 18 and Figure 19 shown, the limit ring stopper 64 is a strip structure, and limit ring stopper installation holes are respectively arranged at both ends. The positions of the limit ring stopper installation holes correspond to the threaded hole positions of the 2 central part limit ring stopper installation parts 6132 on the paired central part limit ring limit platforms 613, and are used to connect the limit ring stopper 64 to the central part body 61 through screw fasteners respectively.

[0164] In the installation state, the upper end of the limit ring stopper 64 and the shaft platform on the lower side of the central part upper limit platform 6131 jointly limit the upper and lower positions of the limit ring 63, so that the limit ring 63 is always in the working position.

[0165] AsFigure 11 As shown, the central component cover plate 62 includes an integrally formed cover plate positioning sleeve 621 and a cover plate mounting portion 622.

[0166] The inner hole of the cover plate positioning sleeve 621 is in interference fit with the outer wall surface in the middle of the rotor shaft mounting sleeve 611, and they are connected into a whole.

[0167] The cover plate mounting portion 622 is plate-shaped, flanged at the lower end of the cover plate positioning sleeve 621 and extends to both sides, forming a symmetrical structure.

[0168] Cover plate support shaft mounting portions 6221 are provided in the middle of both sides of the cover plate mounting portion 622.

[0169] Preferably, the support shaft mounting portion 1221 of the second embodiment is at least one cover plate support shaft mounting through hole, and the cover plate support shaft mounting through hole of the cover plate support shaft mounting portion 6221 corresponds to the support shaft mounting hole of the support shaft mounting portion 412; the fastener assembly fastens and connects the support shaft 41 and the central component assembly 6 together here.

[0170] Cover plate pull-twist tab mounting portions 6222 are symmetrically provided on the outer sides of both sides of the cover plate mounting portion 622.

[0171] Preferably, the cover plate pull-twist tab mounting portions 6222 of the second embodiment are 2 symmetrically arranged cover plate pull-twist tab mounting through holes, and the cover plate pull-twist tab mounting through holes of the cover plate pull-twist tab mounting portions 6222 match the central component pull-twist tab mounting through holes of the central component pull-twist tab mounting portion 6121; the front ends of the 2 branches of the pull-twist bar 21 are clamped between the central component cover plate 62 and the central component body 61 by the fastener assembly and are fastened and connected into a whole, realizing the fastening connection between the pull-twist bar 21 and the central component assembly 6.

[0172] Further preferably, cover plate sink notches are provided in the middle of both sides of the cover plate mounting portion 622, and the cover plate support shaft mounting portions 6221 are arranged in the cover plate sink notches. This setting can make the cover plate mounting portion 622 of the central component cover plate 62 as a whole an irregular structure, increasing the overall stiffness of the central component cover plate 62, making the rotor shaft connected in the rotor shaft mounting sleeve 611, the support shaft 41 connected to the periphery, the lower limit stop assembly 8 and other key parts firmly positioned and the structure stable, which is beneficial for the helicopter to have good flight performance.

[0173] A plurality of flexible hub axial hinges 100 can be installed on the central component assembly 6 of the second embodiment, and the number of the flexible hub axial hinges 100 corresponds to the number of the blade 300.

[0174] Preferably, the plurality of flexible hub axial hinges 100 are circumferentially and evenly distributed and connected to the peripheral side of the central component assembly 6.

[0175] Such as Figure 1As shown in the figure, the hub with a flexible hub axial hinge in Embodiment 2 includes a central component assembly 6 and two flexible hub axial hinges 100 symmetrically installed on both sides of the central component assembly 6.

[0176] Embodiment 3

[0177] A rotor.

[0178] The following combines Embodiment 1, Embodiment 2 and Figure 23 introduces the technical solution of the rotor in Embodiment 3 of the present invention:

[0179] The rotor of the present invention may include one hub as in Embodiment 2, or may include a plurality of hubs arranged in the up and down directions. In the case of including a plurality of hubs, the central component assemblies 6 in the plurality of hubs are sequentially connected along the axial direction, and the plurality of central component assemblies 6 constitute a central component part 200. One blade 300 is connected to the distal end of each flexible hub axial hinge of the hub.

[0180] Preferably, the rotor in Embodiment 3 includes two hubs as in Embodiment 2. The central component assemblies 6 of the two hubs are sequentially connected along the axial direction of the central component assembly 6, specifically coaxially connected in the up and down directions. The two central component assemblies 6 constitute a central component part 200. The hub and the blade 300 together constitute the rotor of the unmanned aerial vehicle with the flexible hub axial hinge of Embodiment 1.

[0181] Specifically, the central component part 200 includes two central component assemblies 6 connected up and down along the axis. Each central component assembly 6 is connected to a plurality of circumferentially evenly distributed flexible hub axial hinges 100, and one blade 300 is connected to the distal end of each flexible hub axial hinge 100.

[0182] As Figure 23 shown, preferably in Embodiment 3, two radially arranged flexible hub axial hinges 100 are circumferentially evenly distributed and connected within the blade disc where each central component assembly 6 is located, specifically connecting the proximal end of the flexible hub axial hinge 100; one blade 300 is connected to the distal end of each flexible hub axial hinge 100.

[0183] The same number of flexible hub axial hinges 100 are provided within the blade discs where all central component assemblies 6 are located; correspondingly, the same number of blades 300 are provided within all blade discs.

[0184] This setting can ensure that while the rotor flapping is efficiently absorbed, it further ensures the aerodynamic balance and torque balance of the helicopter in the flight state from the overall structure, thereby optimizing the flight performance.

[0185] The above are only the preferred specific embodiments of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that can be easily thought of by those skilled in the art within the technical scope disclosed by the present invention should be covered within the protection scope of the present invention. At the same time, any equipment or facility equipped with this device to expand the application field and produce compound technical effects belongs to the protection scope of the method invention of the present invention.

Claims

1. A flexible hub axial hinge, characterized in that, For bridging the central component assembly (6) and the blade (300), including a functional part and a limiting part; the limiting part is arranged between the central component assembly (6) and the functional part; The functional part includes a sleeve (1), a tension-torsion plate assembly (2) and a laminated flap damping assembly (3); The limiting part includes a support shaft assembly (4); the support shaft assembly (4) includes a support shaft (41) and a rubber pad (42); The laminated flap damping assembly (3) includes a balance shaft (32) and a spherical plain bearing (33); a balance shaft spherical plain bearing hole (321) is arranged in the middle of the balance shaft (32), and the outer ring of the spherical plain bearing (33) is tightly connected in the balance shaft spherical plain bearing hole (321); The support shaft (41) includes a support shaft baffle (411), a support shaft mounting part (412) and a support shaft positioning part (413) which are integrally formed; the support shaft mounting part (412) and the support shaft positioning part (413) are respectively arranged on both sides of the support shaft baffle (411); the support shaft positioning part (413) is a cylinder, and the cylinder of the support shaft positioning part (413) is positioned and pressed on the inner ring of the spherical plain bearing (33); The rubber pad (42) is arranged between the support shaft (41) and the balance shaft (32) of the laminated flap damping assembly (3).

2. The flexible hub axial hinge according to claim 1, wherein The sleeve (1) is an elliptical sleeve structure; a sleeve damper mounting part (11), a sleeve blade clamp mounting part (12) and a sleeve observation hole (14) are arranged on the sleeve (1); a blade clamp assembly (7) is connected to the distal end of the sleeve (1); a baffle (5) and the laminated flap damping assembly (3) are connected to the proximal end of the sleeve (1).

3. The flexible hub axial hinge according to claim 2, characterized in that, The tension-torsion plate assembly (2) includes a tension-torsion bar (21) and a tension-torsion bar clip (22); the distal end of the tension-torsion bar (21) is clamped between the two tension-torsion bar clips (22) and is connected to the sleeve (1) through the blade clamp assembly (7), and the proximal end of the tension-torsion bar (21) is connected to the central component assembly (6).

4. The flexible hub axial hinge according to claim 3, wherein The tension-torsion bar (21) is in a Y-shaped structure, and the proximal end of the tension-torsion bar (21) is the two branch structures of the Y-shaped structure.

5. The flexible hub axial hinge according to claim 3, wherein The sleeve (1) is made of a composite material, and the tension-torsion bar (21) is made of a stainless steel material.

6. The flexible hub axial hinge according to claim 1, characterized in that, The laminated flap damping assembly (3) includes a laminated flap damper (31); both ends of the balance shaft (32) extend out of the sleeve (1) at the sleeve damper mounting part (11) and are respectively connected with a laminated flap damper (31) on the outer side surface of the sleeve (1); the spherical plain bearing (33) is installed in the middle of the balance shaft (32).

7. A hub, characterized in that, Including a plurality of flexible hub axial hinges as described in any one of claims 1-6, and further including a central component assembly (6); a plurality of the flexible hub axial hinges are circumferentially and evenly distributed on the periphery of the central component assembly (6); the support shaft (41) of each flexible hub axial hinge is connected to the central component assembly (6).

8. A rotor, characterized in that, Comprising one or more hub as claimed in claim 7; wherein, in the case of comprising a plurality of said hubs, the central member assemblies (6) in the plurality of said hubs are sequentially connected in the axial direction; Each flexible hub axial hinge distal end of the hub is connected with one blade (300).

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