A rotor hub and rotor with a flexible hub axial hinge

Abstract

This invention relates to a rotor hub and rotor with a flexible hub axial hinge, belonging to the field of helicopter technology, and solves the problem of poor aeroelastic stability of helicopter rotors caused by the inefficient absorption of rotor shimmy. The rotor hub with a flexible hub axial hinge of this invention includes a central component assembly and a flexible hub axial hinge; the flexible hub axial hinge includes a functional part and a limiting part, with the limiting part disposed between the central component assembly and the functional part; the limiting part includes a support shaft assembly and a lower limit motion assembly; the functional part includes a sleeve, a tension / torsion plate assembly, and a stacked shimmy damping assembly. The rotor hub of this invention has composite damping, which can efficiently absorb the centrifugal force and shimmy of the blades, ensuring both maneuverability and responsiveness while maintaining stable flight; the rotor of this invention can improve the flight performance of helicopters.

Description

Technical Field

[0001] This invention relates to the field of helicopter technology, and more specifically to a rotor hub and rotor with a flexible hub axial hinge. Background Technology

[0002] The rotor system is the core of a helicopter, providing lift for flight. The development of helicopter rotor systems has gone through three stages: the first generation used articulated hubs and metal blades; the second generation used star-shaped flexible hubs, titanium alloy spherical flexible hubs, and all-composite blades; and the third generation adopted large composite blades, spherical flexible hubs, and bearingless tail rotors. Most third-generation rotor systems are now widely used in helicopters.

[0003] Currently, the development of fourth-generation helicopters is in the process of technological advancement. The research and development of fourth-generation helicopters focuses on bearingless rotor technology, rotor anti-icing technology, tilt rotor technology, and intelligent rotor technology, reaching a scale of collaborative research and development.

[0004] Bearingless rotor technology significantly reduces flapping, wobbling, and pitch-changing motions in helicopter rotor blades caused by various forces, objectively improving the helicopter's maneuverability, agility, reliability, survivability, and maintainability. It also enhances the helicopter's piloting qualities, maneuverability, and responsiveness. Bearingless rotors are gradually becoming one of the preferred rotor configurations for advanced helicopters.

[0005] During helicopter flight, the vibration of the bearingless rotor has a significant impact on the helicopter's flight performance. Especially at low speeds or when hovering, aerodynamic damping is minimal, and the direction of rotor oscillation becomes a crucial factor affecting rotor aeroelastic stability. To reduce the impact of blade oscillation on the overall flight performance of the helicopter, bearingless rotors are equipped with structural damping devices.

[0006] In existing technologies, helicopters typically employ stacked oscillation dampers. These dampers primarily utilize the shear deformation of high-damping silicone rubber materials to generate elasticity and damping stiffness, absorbing rotor oscillation energy to minimize the risk of resonance in the helicopter on the ground and in the air.

[0007] Existing stacked oscillation dampers are typically located at the junction of the rotor blades and the central assembly. Because the blades are directly connected to the periphery of the central assembly, the flapping pitch oscillation motion of a conventional bearingless rotor is entirely borne by the root of the junction, making it highly susceptible to cracking or breakage due to torque. Therefore, not only are the lifespans of the rotor hub assembly and blades affected, but the helicopter's flight safety is also threatened, increasing maintenance costs.

[0008] One of the technical challenges is to provide suitable damping devices for bearingless rotors to improve the service life of the rotor hub, reduce maintenance costs, and meet the requirements of long-term high-performance helicopter flight. Summary of the Invention

[0009] Based on the above analysis, the present invention aims to provide a rotor hub and rotor with a flexible rotor hub axial hinge, in order to solve the technical problem that the rotor oscillation of helicopters cannot be efficiently absorbed, resulting in poor aeroelastic stability of helicopter rotors.

[0010] This invention is achieved through the following technical solution:

[0011] A propeller hub with a flexible hub axial hinge includes a central component assembly and a flexible hub axial hinge; the flexible hub axial hinge includes a functional part and a limiting part; the limiting part is disposed between the functional part and the central component assembly; the limiting part includes a support shaft assembly and a lower limit motion assembly; the functional part includes a sleeve, a tension / torsion plate assembly and a stacked oscillation damping assembly.

[0012] Furthermore, the support shaft assembly is connected to the balance shaft and the central component assembly at both ends, and the lower limit motion assembly is connected to the lower part of the central component assembly and located below the support shaft assembly.

[0013] Furthermore, the central component assembly includes a central component body, a central component cover plate, a limiting ring, and a limiting ring stop block; the central component cover plate is connected to the upper part of the central component body, and the limiting ring stop block is limited and connected to the lower periphery of the central component body; the central component body and the limiting ring stop block limit the limiting ring from both the upper and lower directions.

[0014] Furthermore, the central component body includes an integrally formed rotor shaft mounting bushing, a central component body mounting part, and a central component limiting ring positioning platform; the central component cover plate includes an integrally formed cover plate positioning sleeve and a cover plate mounting part.

[0015] Furthermore, the central component body mounting part is plate-shaped, and the central component body mounting part is symmetrically arranged on the outer side of the middle part of the rotor shaft mounting bushing and extends to both sides; the central component lower limit moving connection part is provided in the middle of both sides of the central component body mounting part.

[0016] Furthermore, the lower limit motion assembly includes a lower limit motion fixing body, a lower limit motion support shaft, a spring, a lower limit motion elastic body, and a lower limit motion elastic body fixing member.

[0017] Furthermore, the lower limit moving support shaft is movably connected in the lower limit moving fixed body, and the spring is disposed between the lower limit moving support shaft and the lower limit moving fixed body; the lower limit moving elastic body is connected to the distal end of the lower limit moving support shaft through a lower limit moving elastic body fixing member.

[0018] Furthermore, the sleeve is an elliptical sleeve structure; the sleeve is provided with a sleeve damper mounting part, a sleeve paddle clamp mounting part, and a sleeve observation hole.

[0019] Furthermore, the sleeve is made of a composite material.

[0020] Furthermore, the pull-torsion plate assembly includes a pull-torsion strip and pull-torsion strip clips; the distal end of the pull-torsion strip is clamped between two pull-torsion strip clips and connected to the sleeve via the paddle clip; the proximal end of the pull-torsion strip is connected to the central component assembly.

[0021] Furthermore, the proximal end of the pull-torsion bar clip is configured as an arc-shaped flange facing away from the pull-torsion bar.

[0022] Furthermore, the tension bar has a Y-shaped structure, and the proximal end of the tension bar has two branch structures.

[0023] Furthermore, the tension bar is made of stainless steel.

[0024] Furthermore, the stacked oscillation damping assembly includes a stacked oscillation damper, a balance shaft, and a joint bearing; both ends of the balance shaft extend out of the sleeve at the sleeve damper mounting part and are respectively connected to a stacked oscillation damper on the outer side of the sleeve; the joint bearing is installed in the middle of the balance shaft.

[0025] Furthermore, the support shaft assembly includes a support shaft and a rubber pad; the support shaft includes a support shaft positioning part; and the rubber pad is connected to the support shaft positioning part.

[0026] Furthermore, the distal end face of the rubber pad can contact the proximal end of the balance shaft.

[0027] Furthermore, the functional unit also includes a paddle clip and a baffle; the paddle clip is connected to the distal end of the sleeve, and the stacked oscillation damping assembly and the baffle are connected to the proximal end of the sleeve.

[0028] Furthermore, the paddle clip is connected to the distal end of the sleeve, and the stacked oscillation damping assembly and baffle are connected to the proximal end of the sleeve.

[0029] Furthermore, the propeller clamp includes a propeller clamp tension / torsion plate mounting portion and a propeller clamp blade mounting portion; the propeller clamp blade mounting portion is connected to the proximal end of the propeller blade; the propeller clamp tension / torsion plate mounting portion is connected to the tension / torsion plate assembly.

[0030] Furthermore, the baffle includes a baffle body and a baffle mounting ear; the baffle mounting ear is located in the middle of the far end plane of the baffle body, forming a T-shaped structure with the baffle body; the baffle mounting ear (282) is connected to the outer edge of the lower proximal part of the sleeve (21).

[0031] Furthermore, the support shaft also includes a support shaft baffle, a support shaft mounting part, and a support shaft positioning part, with the support shaft mounting part and the support shaft positioning part located on both sides of the support shaft baffle.

[0032] Furthermore, the cross-section of the limiting ring has a non-uniform wall thickness structure, and the wall thickness of the limiting ring in the long axis direction is greater than that in the short axis direction.

[0033] A rotor with a flexible hub axial hinge includes a hub and blades with the flexible hub axial hinge.

[0034] Furthermore, the central components of the plurality of said propeller hubs are connected vertically along an axis; the central component of each said propeller hub is connected to the proximal end of the plurality of flexible propeller hub axial hinges; and the distal end of each flexible propeller hub axial hinge is connected to one of the propeller blades.

[0035] Compared with the prior art, the present invention can achieve at least the following beneficial effects:

[0036] The rotor hub of the present invention has a flexible rotor hub axial hinge between the central component assembly and the rotor blade. The flexible rotor hub axial hinge absorbs the oscillation from the rotor blade through the vibration absorption and movement limitation of the sleeve, tension and torsion plate assembly, stacked oscillation damper, support shaft assembly, lower limit movement assembly, etc., effectively ensuring the stiffness and dynamic flexibility of the helicopter rotor hub, optimizing the flight characteristics of the helicopter, and improving the service life of the rotor hub and rotor.

[0037] The above-described technical solutions can also be combined with each other to achieve more preferred combinations. Other features and advantages of the present invention will be set forth in the following description, and some advantages may become apparent from the description or be learned by practicing the invention. The objects and other advantages of the invention can be realized and obtained from what is particularly pointed out in the description and drawings. Attached Figure Description

[0038] The accompanying drawings are for illustrative purposes only and are not intended to limit the invention. Throughout the drawings, the same reference numerals denote the same parts.

[0039] Figure 1 This is a schematic diagram of the overall structure of the propeller hub with a flexible hub axial hinge according to the present invention.

[0040] Figure 2 for Figure 1 A sectional view along the axis;

[0041] Figure 3 This is a partial perspective view of the axial hinge of the flexible propeller hub of the present invention;

[0042] Figure 4 This is a schematic diagram of the sleeve structure of the present invention;

[0043] Figure 5 This is a schematic diagram of the propeller clamp structure of the present invention;

[0044] Figure 6 This is a schematic diagram of the tension-torsion plate assembly structure of the present invention;

[0045] Figure 7 This is a cross-sectional view of the axial hinge portion of the flexible propeller hub of the present invention along the balance shaft axis.

[0046] Figure 8 This is a schematic diagram of the balance shaft structure of the present invention;

[0047] Figure 9 This is a schematic diagram of the stacked oscillation damper structure of the present invention;

[0048] Figure 10 This is a schematic diagram of the lower limit motion component structure of the present invention;

[0049] Figure 11 for Figure 10 Sectional view along the BB direction;

[0050] Figure 12 This is a schematic diagram of the baffle structure of the present invention;

[0051] Figure 13 This is a schematic diagram of the overall structure of the central component assembly of the present invention;

[0052] Figure 14 This is a front half-sectional view of the central component assembly of the present invention;

[0053] Figure 15 This is a schematic diagram of the central component body structure of the present invention;

[0054] Figure 16 This is a schematic diagram of the central component cover plate structure of the present invention;

[0055] Figure 17 This is a schematic diagram of the support shaft structure of the present invention;

[0056] Figure 18 This is a schematic diagram of the rubber pad structure of the present invention;

[0057] Figure 19 This is a schematic diagram of the limiting ring structure of the present invention;

[0058] Figure 20 for Figure 19 Cross-sectional view of the preferred embodiment of the limiting ring of the present invention;

[0059] Figure 21 This is a schematic diagram of the rotor with a flexible hub axial hinge according to the present invention.

[0060] Figure label:

[0061] 1. Central component assembly; 11. Central component body; 111. Rotor shaft mounting bushing; 1111. Spline; 112. Central component body mounting part; 1121. Central component lower limit moving mounting part; 1122. Central component tension / torsion plate mounting part; 113. Central component limiting ring limiting platform; 1131. Central component upper limit platform; 1132. Central component limiting ring stop block mounting part; 12. Central component cover plate; 121. Cover plate positioning sleeve; 122. Cover plate mounting part; 1221. Cover plate support shaft mounting part; 1222. Cover plate tension / torsion plate mounting part; 13. Limiting ring; 14. Limiting... 1. Moving ring stop; 2. Flexible propeller hub axial hinge; 21. Sleeve sleeve; 211. Sleeve sleeve damper mounting part; 212. Sleeve sleeve propeller clamp mounting part; 213. Sleeve sleeve rocker arm mounting position; 214. Sleeve sleeve observation hole; 22. Torsion plate assembly; 221. Torsion bar; 222. Torsion bar clamp; 223. Torsion plate sleeve; 23. Stacked oscillation damping assembly; 231. Stacked oscillation damper; 2311. Damper circumferential positioning part; 232. Balance shaft; 2321. Balance shaft spherical bearing hole; 2322. Balance shaft circumferential positioning part; 2323. Balance shaft fastening part; 233. Spherical plain bearing; 24. Support shaft assembly; 241. Support shaft; 2411. Support shaft baffle; 2412. Support shaft mounting part; 2413. Support shaft positioning part; 242. Rubber pad; 2421. Rubber pad positioning hole; 25. Rocker arm assembly; 26. Lower limit moving assembly; 261. Lower limit moving fixing body; 2611. Lower limit moving fixing body mounting end; 26111. Lower limit moving fixing body mounting hole; 2612. Lower limit moving outer sleeve; 26121. Lower limit moving outer sleeve inner hole; 262. Lower limit moving support shaft; 2621. Support shaft sliding shaft part; 2622 2623. Support shaft spring positioning part; 26231. Support shaft limiting ring limiting part; 2624. Support shaft limiting ring limiting port; 2625. Support shaft spherical part limiting part; 26261. Support shaft spherical part locking part; 263. Spring; 264. Lower limit moving elastic body; 265. Lower limit moving elastic body fixing part; 27. Paddle clamp assembly; 271. Paddle clamp; 2711. Paddle clamp tension plate mounting part; 2712. Paddle clamp blade mounting part; 272. Paddle blade pin; 28. Baffle; 281. Baffle body; 282. Baffle mounting ear; 2821. Baffle mounting hole; 3. Paddle blade. Detailed Implementation

[0062] The preferred embodiments of the present invention will now be described in detail with reference to the accompanying drawings, which constitute a part of the present invention and are used together with the embodiments of the present invention to illustrate the principles of the present invention, but are not intended to limit the scope of the present invention.

[0063] Combination Figures 1-21 The technical solution of the present invention will be described in more detail below:

[0064] In this embodiment, the central axis of the central component 1 is defined as the center position. The ends of each component that are close to the center position of the invention are called the near ends, and the ends of each component that are far from the center position of the invention are called the far ends. The upper and lower directions of the invention are defined as the upper part when the helicopter is in a landing state or hovering in a positive position, and the lower part is called the lower part. The fastener assembly of the invention is a combination of bolts, spline nuts and dovetail pins or a combination of similar functions.

[0065] It should also be noted that the accompanying drawings do not show the rotor blades involved in the invention; the rotor blades involved in the invention are mounted at the distal end of the flexible rotor hub axial hinge 2 via a rotor clamp assembly 27.

[0066] like Figure 1 As shown, the flexible rotor hub axial hinge 2 of the present invention is used to bridge the rotor blades of a helicopter to the central component assembly 1. The proximal end of the flexible rotor hub axial hinge 2 is connected to the central component assembly 1, and the distal end of the flexible rotor hub axial hinge 2 is connected to the rotor blade bridge.

[0067] Multiple flexible hub axial hinges 2 and central component assembly 1 together constitute a hub with flexible hub axial hinges 2.

[0068] At least one of these hubs, together with multiple blades, constitutes a UAV rotor with a flexible hub axial hinge.

[0069] Example 1

[0070] A propeller hub with a flexible hub axial hinge.

[0071] Below, in conjunction with Figures 1-20 This invention introduces the technical solution of a propeller hub with a flexible hub axial hinge:

[0072] like Figure 1 As shown, the propeller hub with flexible hub axial hinge of the present invention includes a central component assembly 1 and a flexible hub axial hinge 2.

[0073] The flexible propeller hub axial hinge 2 includes a functional part and a limiting part.

[0074] The remote end of the functional part is connected to the propeller blade; the limiting part is disposed between the central component assembly and the functional part; the limiting part is disposed between the functional part and the central component assembly 1.

[0075] The limiting part includes a support shaft assembly 24 and a lower limit moving assembly 26; the limiting part of the flexible propeller hub axial hinge 2 is used to limit the extreme positional relationship between the functional part of the flexible propeller hub axial hinge 2 and the central component assembly 1, so that the swinging and oscillating motion of the flexible propeller hub axial hinge 2 can be controlled within the relevant range.

[0076] The functional components include a sleeve 21, a tension / torsion plate assembly 22, and a stacked oscillation damping assembly 23. The functional components of the flexible rotor hub axial hinge 2 are used to realize three motions: blade flapping, oscillation, and pitch variation.

[0077] In this embodiment 1, multiple flexible rotor hub axial hinges 2 can be installed on the central component assembly 1, and the number of flexible rotor hub axial hinges 2 corresponds to the number of rotor blades.

[0078] Multiple flexible propeller hub axial hinges 2 are evenly distributed around the periphery of the central component assembly 1.

[0079] Preferred, such as Figure 1 As shown, the propeller hub with flexible hub axial hinge in this embodiment 1 includes a central component assembly 1 and two flexible hub axial hinges 2 symmetrically installed on both sides of the central component assembly 1.

[0080] The technical solution for the functional part of the flexible rotor hub axial hinge 2 is described below:

[0081] like Figure 2 and Figure 3 As shown, the functional parts of the flexible propeller hub axial hinge 2 include a sleeve 21, a tension / torsion plate assembly 22, a stacked oscillation damping assembly 23, a propeller clamp 271, and a baffle 28.

[0082] Specifically, such as Figure 4 As shown, sleeve 21 is a sleeve-type thin-walled piece.

[0083] Preferably, the sleeve 21 has an elliptical sleeve structure with the minor axis in the vertical direction, which is an irregular shape. The sleeve 21 is made of composite material, preferably with ±45° carbon fiber reinforced composite material layup. The structure and material of the sleeve 21 enable it to have sufficient strength to meet the structural design requirements for torsional stiffness.

[0084] Specifically, such as Figure 2 As shown, the sleeve of the sleeve 21 has a sleeve rocker arm mounting position 213 at the proximal end.

[0085] The sleeve of the sleeve 21 has a partial planar structure in the upper and lower parts of the proximal end, and a sleeve damper mounting part 211 is provided in the planar structure. The sleeve damper mounting part 211 is a set of through holes in the upper and lower parts of the sleeve of the sleeve 21, including balance shaft through holes in the upper and lower parts, damper mounting holes around the balance shaft through holes, and sleeve baffle mounting holes close to the proximal end of the sleeve 21 and located below the sleeve 21.

[0086] like Figure 4 As shown, the sleeve arm mounting position 213 is located on one side near the proximal end of the sleeve 21, and is used to connect the arm device that provides force input for the variable pitch motion of the UAV rotor hub. Specifically, the sleeve arm mounting position 213 is a through-hole structure.

[0087] Specifically, such as Figure 2As shown, the sleeve of the sleeve 21 has a sleeve paddle clamp mounting part 212 with upper and lower through mounting holes at the distal end of the sleeve. The paddle clamp 271 is connected to the sleeve paddle clamp mounting part 212 of the sleeve 21 by a fastener assembly. The sleeve paddle clamp mounting part 212 is a set of upper and lower through mounting holes provided at the distal end of the sleeve of the sleeve 21.

[0088] Specifically, such as Figure 4 As shown, the sleeve structure of the sleeve 21 is provided with multiple sleeve observation holes 214 on both sides. On the one hand, the sleeve observation holes 214 facilitate the observation of the usage status of the internal tension-torsion plate assembly 22 of the flexible propeller hub axial hinge 2, which is convenient for timely maintenance; on the other hand, it helps to reduce the torsional stiffness of the sleeve 21 and maintain the flexibility of the propeller hub to meet the design requirements. Preferably, in this embodiment 1, two pairs of sleeve observation holes 214 are provided on the sleeve 21.

[0089] The sleeve 21 can be waved and oscillated around the joint bearing 233. The joint bearing 233 extends outward without structural restraint because the torsion bar 221 is slightly deformed in the length direction under the centrifugal force of the rotating blade, allowing the joint bearing 233 to move slightly on the support shaft 241.

[0090] like Figure 5 As shown, the propeller clip 271 has a double-sided lug structure. Each lug has a mounting hole structure.

[0091] Among them, such as Figure 2 As shown, the lugs on the near end of the paddle clip 271 are the paddle clip tension plate mounting part 2711; the tension plate assembly 22 is disposed between the lugs of the paddle clip tension plate mounting part 2711; the paddle clip 271 and the tension plate assembly 22 are fastened to the sleeve paddle clip mounting part 212 of the sleeve 21 by fastener assembly.

[0092] Among them, such as Figure 2 As shown, the lug on the far side of the propeller clamp 271 is the propeller clamp blade mounting part 2712. The proximal end of the blade is installed between the lugs of the propeller clamp blade mounting part 2712, and the blade is fastened to the propeller clamp 271 by a blade pin.

[0093] Preferably, in this embodiment 1, the propeller clamp torsion plate mounting part 2711 and the propeller clamp blade mounting part 2712 are each provided with two through mounting holes for fasteners to pass through.

[0094] like Figure 1 and Figure 2 As shown, the pull-twist plate assembly 22 is installed inside the sleeve 21; the distal end of the pull-twist plate assembly 22 is connected to the distal end of the sleeve 21 via the paddle clip 271; the proximal end of the pull-twist plate assembly 22 is connected to the central component assembly 1.

[0095] like Figure 6As shown, specifically, the tension-torsion plate assembly 22 of this embodiment 1 includes a tension-torsion strip 221 and a tension-torsion strip clamp 222.

[0096] The distal end of the torsion bar 221 is clamped between two torsion bar clips 222. A torsion bar distal end mounting hole is provided at the distal end of the torsion bar 221, and a torsion bar clip distal end mounting hole is provided on the torsion bar clip 222.

[0097] The positions of the distal end mounting holes of the torsion bar and the distal end mounting holes of the torsion bar clip correspond to each other, forming a distal end torsion bar mounting hole system. This distal end torsion bar mounting hole system corresponds to the position of the sleeve paddle clamp mounting hole of the sleeve paddle clamp mounting part 212, allowing the fastener bolts to pass through the distal end torsion bar mounting hole system and the sleeve paddle clamp mounting hole.

[0098] The proximal end of the torsion bar 221 is provided with a torsion plate proximal mounting hole for connection with the central component assembly 1.

[0099] In this way, the two ends of the tension-torsion plate assembly 22 are respectively connected to the central component assembly 1 and the blade.

[0100] Preferably, the tension / torsion bar 221 is made of stainless steel 301, which has the characteristics of improved strength and hardness under cold deformation processing while retaining sufficient plasticity and toughness. When subjected to external impact, the tension / torsion bar 221 can undergo slight elastic deformation, and can absorb more impact energy during the deformation process.

[0101] Preferably, the proximal end of the tension strip 221 is divided into two to form a symmetrical tension strip proximal end, and at least one tension strip proximal end mounting hole is provided on the Y-shaped structure of the two proximal branches of the tension strip 221.

[0102] The Y-shaped structure and material properties of the torsion bar 221 can withstand the centrifugal force from the blades well, and through the two branches at the near end, it further disperses the concentrated transmission of centrifugal force to the central component 1, effectively reducing the torsional stiffness of the rotor.

[0103] Preferably, a torsion plate sleeve 223 is installed in the distal torsion plate mounting hole system of the torsion plate assembly 22. The torsion plate sleeve 223 penetrates the distal torsion plate mounting hole system.

[0104] Preferably, in this embodiment 1, two sets of distal tension / torsion plate mounting hole systems are provided.

[0105] Preferably, the tension bar 221 and tension bar clip 222 are interference-fitted with the outer wall of the tension bar sleeve 223, so that the tension bar assembly 22 can have structural consistency after installation, which is beneficial to better transmit centrifugal force and oscillation.

[0106] Preferred, such as Figure 6As shown, the near end of the torsion bar clip 222 is configured with an arc-shaped flange facing away from the torsion bar 221. The arc-shaped flange of the torsion bar clip 222 reserves a possible deformation area of ​​the torsion bar 221 caused by the blade flapping process, so that the torsion bar clip 222 does not hinder the deformation of the torsion bar 221. The torsion bar 221 can deform freely, better absorb and withstand the centrifugal force from the blade, and thus better reduce the impact on the central component assembly 1, which helps to reduce the torsional stiffness of the rotor.

[0107] like Figure 7 As shown, the stacked oscillation damping assembly 23 includes a stacked oscillation damper 231, a balance shaft 232, and a spherical bearing 233; one stacked oscillation damper 231 is connected to each end of the balance shaft 232, and the spherical bearing 233 is installed in the middle of the balance shaft 232.

[0108] Specifically, the balance shaft 232 is disposed in the middle of the proximal end of the sleeve 21 in the upward and downward direction. Both ends of the balance shaft 232 extend out of the sleeve 21 through the balance shaft through-holes in the middle of the sleeve damper mounting part 211. A stacked oscillation damper 231 is installed at each end of the balance shaft 232 outside the sleeve 21, and the two stacked oscillation dampers 231 are fixed to both ends of the balance shaft 232 by fasteners, preferably spline nuts, forming a symmetrical structure relative to the sleeve 21. Simultaneously, the stacked oscillation dampers 231 are connected to the proximal end of the sleeve 21 through damper mounting holes around the sleeve damper mounting part 211 via a fastener assembly.

[0109] Specifically, such as Figure 8 As shown, the balance shaft 232 has a balance shaft spherical bearing hole 2321 in the middle, and balance shaft fastening parts 2323 for connecting spline nuts are respectively provided at both ends. The outer ring of the spherical bearing 233 is pressed and connected to the balance shaft spherical bearing hole 2321.

[0110] Preferably, a circumferential positioning part 2322 for the balance shaft is provided at the root of the balance shaft fastening part 2323 for axially positioning the sleeve damper mounting part 211. Preferably, the circumferential positioning part 2322 for the balance shaft has a stepped structure. The vertical plane of the step has a unique direction.

[0111] like Figure 9 As shown, corresponding to the circumferential positioning part 2322 of the balance shaft, the circumferential positioning part 2311 of the damper is matched and provided on the shaft platform of the central mounting hole of the stacked oscillation damper 231. This mechanism design can stably fix the stacked oscillation damper 231 relative to the balance shaft 232 in the circumferential direction, ensuring the consistency of the damping effect of the two stacked oscillation dampers 231 symmetrically arranged with respect to the sleeve 21.

[0112] like Figure 2As shown, the baffle 28 is connected to the outer edge of the lower part of the near end of the sleeve 21 and is connected to the sleeve baffle mounting hole of the sleeve 21 by a fastener assembly.

[0113] like Figure 12 As shown, the baffle 28 includes a baffle body 281 and a baffle mounting ear 282. The baffle mounting ear 282 is located in the middle of the far end plane of the baffle body 281, forming a T-shaped structure with the baffle body 281.

[0114] The baffle mounting ear 282 has a baffle mounting hole 2821, the position of which corresponds to the baffle mounting hole at the lower part of the sleeve 21. The baffle mounting ear 282 is located on the inner side of the lower proximal part of the sleeve 21. The baffle 28 is fastened to the sleeve 21 by a fastener assembly. After connection, the distal plane of the baffle body 281 abuts against the proximal end face of the sleeve 21.

[0115] The following describes the technical solution for the limiting part of the flexible propeller hub axial hinge 2:

[0116] like Figure 2 As shown, the limiting part is connected between the flexible rotor hub axial hinge 2 and the central component assembly 1 to limit the positional relationship between the flexible rotor hub axial hinge 2 and the central component assembly 1, including the support shaft assembly 24 and the lower limit moving assembly 26.

[0117] The support shaft assembly 24, the lower limit motion assembly 26, and the balance shaft 232 are all located on the vertical center line in the upper and lower directions of the sleeve 21.

[0118] like Figure 2 As shown, the support shaft assembly 24 includes a support shaft 241 and a rubber pad 242.

[0119] like Figure 17 As shown, the support shaft 241 includes an integrally formed support shaft baffle 2411, a support shaft mounting part 2412, and a support shaft positioning part 2413. The support shaft mounting part 2412 and the support shaft positioning part 2413 are respectively disposed on both sides of the support shaft baffle 2411.

[0120] The support shaft positioning part 2413 is a cylinder located at the far end of the support shaft 241 and serves as a functional part for connecting the flexible propeller hub axial hinge 2. The cylinder of the support shaft positioning part 2413 is positioned and pressed against the inner ring of the spherical bearing 233, thus shielding the transmission of the rotational movement of the flexible propeller hub axial hinge 2 along the cylindrical axis of the support shaft positioning part 2413 to the central component assembly 1, thereby protecting the structural stability of the central component assembly 1.

[0121] The support shaft mounting part 2412 is located near the end of the support shaft 241, and the support shaft mounting part 2412 is provided with at least two support shaft mounting holes for connecting the support shaft 241 to the central component assembly 1 through the fastener assembly.

[0122] like Figure 18 As shown, the rubber pad 242 is an elastomer with a rubber pad positioning hole 2421 in the middle. The rubber pad 242 is interference-fitted to the cylinder of the support shaft positioning part 2413 through the rubber pad positioning hole 2421. The proximal end of the rubber pad 242 is attached to the distal end of the support shaft baffle 2411, and the distal end of the rubber pad 242 is attached to the center of the proximal end of the balance shaft 232, specifically the opposite surface of the surface where the spherical bearing 233 is located.

[0123] The structure in which the rubber pad positioning hole 2421 is interference-fitted onto the cylinder of the support shaft positioning part 2413 can also be replaced by a technical solution in which the rubber pad 242 is fixedly connected to the support shaft 241.

[0124] A rubber pad 242 is installed between the balance shaft 232 and the support shaft 241. When the sleeve 21 is raised, the rubber pad 242 can provide cushioning against the collision between the balance shaft 232 and the support shaft 241.

[0125] like Figure 2 As shown, the lower limit moving component 26 is disposed at the lower part of the support shaft assembly 24. The upper part of the lower limit moving component 26 is fixedly connected to the central component assembly 1, and the two ends of the lower part of the lower limit moving component 26 flexibly contact the proximal planes of the central component assembly 1 and the baffle body 281, respectively.

[0126] like Figure 10 and 11 As shown, the lower limit moving assembly 26 includes a lower limit moving fixed body 261, a lower limit moving support shaft 262, a spring 263, a lower limit moving elastic body 264, and a lower limit moving elastic body fixing member 265. The lower limit moving support shaft 262 is movably connected in the lower limit moving fixed body 261, the spring 263 is disposed between the lower limit moving support shaft 262 and the lower limit moving fixed body 261, and the lower limit moving elastic body 264 is connected to the distal end of the lower limit moving support shaft 262 through the lower limit moving elastic body fixing member 265.

[0127] Specifically, the lower limit movable fixing body 261 includes an integrally formed lower limit movable fixing body mounting end 2611 and a lower limit movable outer sleeve 2612.

[0128] The lower limit moving body mounting end 2611 is provided with at least two lower limit moving body mounting holes 26111, which are used to fasten the lower limit moving component 26 to the central component component 1 through the fastener assembly.

[0129] like Figure 11 As shown, the lower limit moving sleeve 2612 is a sleeve structure with a central hole. The upper part of the lower limit moving sleeve 2612 is integrally formed on the lower part of the lower limit moving fixed body 261. In addition to the through lower limit moving sleeve central hole, the sleeve structure of the lower limit moving sleeve 2612 also has a lower limit moving sleeve inner hole 26121.

[0130] The lower limit moving support shaft 262 has a stepped shaft structure, which includes, from the near end to the far end, a support shaft limiting ring limiting part 2623, a support shaft sliding shaft part 2621, a support shaft spring positioning part 2622, and a support shaft spherical part limiting part 2624.

[0131] The support shaft limiting ring limiting part 2623 is provided with a support shaft limiting ring limiting port 26231. The support shaft limiting ring limiting port 26231 is used to limit the limiting ring 13 of the central component assembly 1. The limiting ring 13 is an elastic ring that surrounds the functional components of the central component assembly 1.

[0132] The support shaft spherical component limiting part 2624 is provided with a support shaft spherical component bayonet 26241, and the two side ends of the support shaft spherical component bayonet 26241 are provided with support shaft spherical component limiting part mounting holes.

[0133] The spherical support jaw 26241 is used to limit the lower limit of the dynamic elastic body 264.

[0134] The lower limit movable elastic body 264 is an elastic sphere with a through hole in the middle. The lower limit movable elastic body fastener 265 is used to fasten the lower limit movable elastic body 264 to the lower limit movable support shaft 262. The lower limit movable elastic body fastener 265 passes through the mounting hole of the spherical part limiting part of the support shaft and the through hole of the lower limit movable elastic body 264, and is a fastener assembly.

[0135] Preferably, the lower limit kinetic elastic body 264 in this embodiment 1 is a rigid metal sphere.

[0136] like Figure 11 As shown, the spring 263 is limited between the inner hole 26121 of the lower limit moving sleeve and the spring positioning part 2622 of the support shaft, and the two ends of the spring 263 are limited by the shaft platform.

[0137] Preferably, the lower limit moving sleeve inner hole 26121 and the support shaft sliding shaft portion 2621 are close to a transition fit clearance fit, and the surface machining accuracy and dimensional fit of the two allow the lower limit moving support shaft 262 to generate axial sliding displacement in the inner hole of the lower limit moving sleeve 2612 after being subjected to force.

[0138] The lower limit moving support shaft 262 is used to increase the clearance between the rotor blade central component assembly 1 (in other words, the helicopter fuselage). During low-speed operation, hovering, and when encountering gusts of wind, the lower limit moving support shaft 262 can prevent the rotor blade from colliding with the fuselage.

[0139] The working process of the lower limit moving support shaft 262 is as follows:

[0140] like Figure 1As shown, a lower limit moving component 26 is installed on each side of the central component assembly 1. The lower limit moving component 26 has a lower limit moving fixing body 261 through at least two fasteners, preferably two in this embodiment 1. The fastener assembly is fixedly connected to the central component assembly 1. The lower limit moving support shaft 262 can move left and right at the center hole of the lower limit moving fixing body 261 and the inner hole 26121 of the lower limit moving outer sleeve.

[0141] When the blades are at low speed and in a hovering state, the lower limit support shafts 262 on both sides drive the surrounding limiting ring 13 of the central component assembly 1 to compress the central spring 263 and swing left and right. The distance that the limiting ring 13 can move left and right is related to the results of dynamic calculations.

[0142] If the flexible rotor hub axial hinge 2 on the first side causes the limiting ring 13 to move beyond its limit, the spring 263 on the second side will be compressed to its shortest length to prevent the limiting ring 13 on the first side from colliding with the central component body 11. Conversely, the same applies.

[0143] At large aggregate distances, the lower limit moving component 26 does not contact the collision baffle body 281.

[0144] In this embodiment 1, when the blade on one side swings, causing the lower limit moving support shaft 262 of the flexible hub axial hinge 2 on the same side to move backward under force, the lower limit moving elastic body 264 will elastically collide with the baffle body 281 and restrict the flexible hub axial hinge 2 driven by the blade to continue swinging downward; when the lower limit moving support shaft 262 moves forward under force, the elastic limiting ring 13 elastically collides with the central component assembly 1 on the opposite side, protecting the central component assembly 1 while limiting the flexible hub axial hinge 2 on that side to no longer swing upward.

[0145] Therefore, the design of the lower limit motion component 26 and the elastic limit ring 13 of the present invention can effectively control the flapping amplitude of the rotor blades, so that the helicopter can be stable throughout the flight process, especially during low speed processes, hovering, and when encountering gusts, thereby improving the flight performance of the helicopter.

[0146] Central component 1 is a key component of the helicopter fuselage.

[0147] like Figure 13 and Figure 14 As shown, the central component assembly 1 includes a central component body 11, a central component cover 12, a limiting ring 13, and a limiting ring stop 14. The central component cover 12 is connected to the upper part of the central component body 11, specifically by sleeve; the limiting ring stop 14 is connected to the lower periphery of the central component body 11 for limiting; the central component body 11 and the limiting ring stop 14 limit the limiting ring 13 from both the upper and lower directions.

[0148] like Figure 15As shown, the central component body 11 includes an integrally formed rotor shaft mounting bushing 111, a central component body mounting part 112, and a central component limiting ring limiting platform 113.

[0149] The central component mounting part 112 is plate-shaped and is symmetrically arranged on the outer side of the middle part of the rotor shaft mounting sleeve 111 and extends to both sides.

[0150] The central component body mounting part 112 has a central component lower limit moving connection part 1122 provided in the middle of both sides.

[0151] Preferably, in this embodiment 1, the lower limit moving connection part 1122 of the central component has two through holes, which match the lower limit moving fixing body mounting holes 26111 on the lower limit moving assembly 26; the lower limit moving assembly 26 is connected to the central component assembly 1 by a fastener assembly.

[0152] Preferably, central component tension tab mounting portions 1121 are symmetrically provided on the outer sides of both sides of the central component body mounting portion 112. The central component tension tab mounting portion 1121 has at least one central component tension tab mounting through hole, and the proximal end of the tension tab 221 is connected to the central component assembly 1 by fastener assembly.

[0153] In a further preferred embodiment, a central component mounting section 112 is provided in the middle of both sides of the central component body mounting section 112, and the central component lower limit moving connection section 1122 is located within the central component body mounting section. This arrangement enables the central component body mounting section 112 to have an irregular shape, increasing the overall rigidity of the central component body 11. This ensures that key components such as the rotor shaft connected to the rotor shaft mounting bushing 111, the support shaft 241 connected to the periphery, and the lower limit moving assembly 26 are firmly positioned, resulting in a stable structure and contributing to good flight performance of the helicopter.

[0154] Specifically, a pair of central component limiting ring positioning platforms 113 are respectively mirror-symmetrically arranged on the outer periphery of the lower part of the rotor shaft mounting bushing 111 and in the direction perpendicular to the long axis of the central component body mounting part 112.

[0155] Preferably, in this embodiment 1, the central component limiting ring positioning platform 113 is a stepped platform structure; the higher platform is on top, which is the central component upper positioning platform 1131; the lower platform is on the bottom, which is the central component limiting ring block mounting part 1132; the central component limiting ring block mounting part 1132 is a screw hole structure, used to install the limiting ring block 14.

[0156] like Figure 19 As shown, the overall structure of the limiting ring 13 is an elastic ring with a near-elliptical cross section, which surrounds the functional components of the central component assembly 1.

[0157] like Figure 20As shown, preferably, the limiting ring 13 has a non-uniform wall thickness cross-section. The wall thickness of the limiting ring 13 in the long axis direction is C, and the wall thickness of the limiting ring 13 in the short axis direction is B, where C>B. This configuration allows the limiting ring 13 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 limiting ring 13.

[0158] like Figure 13 As shown, the limiting ring block 14 is a strip structure with limiting ring block mounting holes at both ends. The positions of the limiting ring block mounting holes correspond to the screw hole positions of the two central component limiting ring block mounting parts 1132 on the paired central component limiting ring limiting platform 113, and are used to connect the limiting ring block 14 to the central component body 11 by screw fasteners.

[0159] In the installed state, the upper end of the limiting ring stop 14 and the shaft platform on the lower side of the central component upper limit platform 1131 jointly limit the upper and lower positions of the limiting ring 13, so that the limiting ring 13 is always in the working position.

[0160] like Figure 16 As shown, the central cover plate 12 includes an integrally formed cover plate positioning sleeve 121 and a cover plate mounting part 122.

[0161] The inner hole of the cover plate positioning sleeve 121 is interference-fitted, specifically sleeved, and connected as a whole in the middle of the outer wall surface of the rotor shaft mounting sleeve 111.

[0162] The cover plate mounting part 122 is plate-shaped, with a flange at the lower end of the cover plate positioning sleeve 121 and extending to both sides to form a symmetrical structure.

[0163] A cover plate support shaft mounting part 1221 is provided in the middle of both sides of the cover plate mounting part 122.

[0164] Preferably, in this embodiment 1, the support shaft mounting part 1221 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 part 1221 corresponds to the position of the support shaft mounting part mounting hole of the support shaft mounting part 2412; the fastener assembly here fastens the support shaft 241 to the central component assembly 1 together.

[0165] Cover plate torsion plate mounting portions 1222 are symmetrically arranged on the exterior of both sides of the cover plate mounting portion 122.

[0166] Preferably, in this embodiment 1, the cover plate torsion plate mounting part 1222 consists of two symmetrically arranged cover plate torsion plate mounting holes, and the cover plate torsion plate mounting holes of the cover plate torsion plate mounting part 1222 match the central component torsion plate mounting holes of the central component torsion plate mounting part 1121; the front ends of the two branches of the torsion bar 221 are clamped between the central component cover plate 12 and the central component body 11 by the fastener assembly, and are fastened together to form a whole, thereby realizing the fastening connection between the torsion bar 221 and the central component assembly 1.

[0167] Preferably, a cover plate recess is provided in the middle of both sides of the cover plate mounting portion 122, and the cover plate support shaft mounting portion 1221 is located in the cover plate recess. This arrangement enables the cover plate mounting portion 122 of the central component cover plate 12 to have an irregular shape, increasing the overall rigidity of the central component cover plate 12. This ensures that key components such as the rotor shaft connected in the rotor shaft mounting bushing 111, the support shaft 241 connected to the periphery, and the lower limit moving assembly 26 are firmly positioned, resulting in a stable structure and contributing to good flight performance of the helicopter.

[0168] Example 2

[0169] A type of rotor.

[0170] The following is a combination of Example 1 and... Figure 21 The technical solution of the rotor in Embodiment 2 of the present invention is introduced as follows:

[0171] The rotor of this embodiment 2 includes at least one hub and blade 3 of embodiment 1.

[0172] Multiple central component assemblies 1 of a rotor with flexible hub axial hinges are stacked and fastened together along the axis. Each central component assembly 1 has multiple flexible hub axial hinges 2 evenly distributed around its circumference. The far end of each flexible hub axial hinge 2 is connected to a blade 3.

[0173] All central component assemblies 1 have the same number of flexible hub axial hinges 2 within their respective propeller disks; correspondingly, all propeller disks have the same number of blades 3.

[0174] This configuration ensures that rotor shimmy is efficiently absorbed, while also guaranteeing aerodynamic and torque balance of the helicopter in flight, thus optimizing flight performance.

[0175] like Figure 21 As shown, preferably, the central component of this embodiment 2 includes two central component assemblies 1 that are fastened together vertically along the axis. Each central component assembly 1 is connected to two radially symmetrical flexible propeller hub axial hinges 2, specifically connected to the proximal end of the flexible propeller hub axial hinge 2; the distal end of each flexible propeller hub axial hinge 2 is connected to a propeller blade 3.

[0176] The above are merely preferred embodiments of the present invention, but the scope of protection of the present invention is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in the present invention should be included within the scope of protection of the present invention. Furthermore, any equipment or facilities equipped with this device to expand the application field and produce combined technical effects are within the scope of protection of this invention.

Claims

1. A propeller hub with a flexible hub axial hinge, characterized in that, Includes a central component assembly (1) and a flexible hub axial hinge (2); The flexible propeller hub axial hinge (2) includes a functional part and a limiting part; the limiting part is disposed between the functional part and the central component assembly (1); The limiting part includes a support shaft assembly (24) and a lower limit moving assembly (26). The lower limit motion assembly (26) includes a lower limit motion fixing body (261), a lower limit motion support shaft (262), a spring (263), a lower limit motion elastic body (264), and a lower limit motion elastic body fixing member (265); the lower limit motion support shaft (262) is movably connected in the lower limit motion fixing body (261), and the spring (263) is disposed between the lower limit motion support shaft (262) and the lower limit motion fixing body (261); the lower limit motion elastic body (264) is connected to the distal end of the lower limit motion support shaft (262) through the lower limit motion elastic body fixing member (265); the functional part includes a sleeve (21), a tension and torsion plate assembly (22), and a stacked swing damping assembly (23).

2. The propeller hub with a flexible hub axial hinge according to claim 1, characterized in that, The central component assembly (1) includes a central component body (11), a central component cover plate (12), a limiting ring (13), and a limiting ring stop (14); the central component cover plate (12) is connected to the upper part of the central component body (11), and the limiting ring stop (14) is connected to the lower periphery of the central component body (11); the central component body (11) and the limiting ring stop (14) limit the limiting ring (13) from the upper and lower directions.

3. The propeller hub with a flexible hub axial hinge according to claim 2, characterized in that, The central component body (11) includes an integrally formed rotor shaft mounting bushing (111), a central component body mounting part (112), and a central component limiting ring limiting platform (113); the central component cover plate (12) includes an integrally formed cover plate positioning sleeve (121) and a cover plate mounting part (122).

4. The propeller hub with a flexible hub axial hinge according to claim 1, characterized in that, The support shaft assembly (24) includes a support shaft (241) and a rubber pad (242); the support shaft (241) includes a support shaft positioning part (2413); the rubber pad (242) is connected to the support shaft positioning part (2413).

5. The propeller hub with a flexible hub axial hinge according to any one of claims 1-4, characterized in that, The functional unit also includes a paddle clip (271) and a baffle (28); the paddle clip (271) is connected to the far end of the sleeve (21), and the stacked oscillation damping assembly (23) and the baffle (28) are connected to the near end of the sleeve (21).

6. The propeller hub with a flexible hub axial hinge according to claim 5, characterized in that, The propeller clamp (271) includes a propeller clamp tension plate mounting part (2711) and a propeller clamp blade mounting part (2712).

7. The propeller hub with a flexible hub axial hinge according to claim 5, characterized in that, The baffle (28) includes a baffle body (281) and a baffle mounting ear (282); the baffle mounting ear (282) is connected to the outer edge of the lower proximal part of the sleeve (21).

8. A rotor, characterized in that, The rotor hub with a flexible rotor hub axial hinge as described in any one of claims 1-7 further includes rotor blades (3).

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