CN117104503A

CN117104503A - Hingeless pitch-changing hub, helicopter rotor wing and helicopter

Info

Publication number: CN117104503A
Application number: CN202311334511.2A
Authority: CN
Inventors: 韩述宏; 张瑞芳; 孟程; 张亚军; 田刚印
Original assignee: Beijing Zhz Technology Co ltd
Current assignee: Beijing Zhz Technology Co ltd
Priority date: 2023-10-16
Filing date: 2023-10-16
Publication date: 2023-11-24

Abstract

The invention relates to a hingeless pitch-variable hub, a helicopter rotor wing and a helicopter, belongs to the technical field of helicopters, and solves the problems that in the flight process of the helicopter, the shimmy of the rotor wing cannot be absorbed efficiently, and a blade stalls, so that the flight speed of the helicopter is restricted. The hingeless pitch-changing hub comprises a hub central shell and a hub pitch-changing component; the hub variable-pitch component is connected to the outer periphery of the hub central shell; the pitch-changing component of the propeller hub comprises a propeller clamp shell, a torque-changing transmission assembly, a pitch-changing hinge support piece and a pitch-changing pull rod assembly; the torque conversion transmission assembly is limited between the paddle clamp shell and the variable-pitch hinge support piece; the proximal end of the paddle unit is connected inside the variable-pitch hinge support; the variable-pitch pull rod assembly is arranged in the hub central shell and drives the variable-pitch hinge support piece to rotate, and the blade unit performs variable-pitch motion along with the variable-pitch pull rod assembly. The helicopter rotor and the helicopter can efficiently absorb the centrifugal force and the shimmy of the blade unit, reduce the rigidity of the hub and avoid the resonance risk of the helicopter rotor and the helicopter.

Description

Hingeless pitch-changing hub, helicopter rotor wing and helicopter

Technical Field

The invention relates to the technical field of helicopters, in particular to a hingeless pitch-variable hub, a helicopter rotor wing and a helicopter.

Background

The rotor system is the core of a helicopter for providing the helicopter with flight lift. Helicopter rotor system development has undergone three phases: the first generation is a rotor system which selects an articulated hub and metal blades, the second generation is a rotor system which selects a star-shaped flexible hub, a titanium alloy ball flexible hub and full composite blades, and the third generation rotor system adopts large composite blades, ball flexible hubs, bearingless tail paddles and the like. Third generation rotor systems have been widely installed in most applications.

The hingeless or bearingless rotor wing is widely researched, popularized and applied because the actuation efficiency is high, the maneuvering performance and the following performance of the helicopter can be improved to a certain extent, and the hingeless or bearingless rotor wing has better driving quality.

Currently, many manufacturers at home and abroad choose either a hingeless rotor (such as BO105 or a cat) or a bearingless rotor (such as EC 135) at the beginning of the aircraft design.

However, the existing hingeless rotor and hingeless pitch-variable hub have no flapping hinge and no shimmy hinge, and only the pitch-variable hinge is used for realizing the flapping and shimmy movements of the rotor blade by the elastic deformation of the structure. This presents the following technical problems:

1. the coaxial rigid rotor wing in the prior art adopts a rigid hingeless rotor wing configuration, the flapping and shimmy hinges are eliminated, only the variable-pitch hinges are reserved, and the blade root is rigidly connected with the hub; because the rigidity of the blade is required to meet the requirement that the advancing edge bears most of lift force and the distance between the upper rotor blade tip and the lower rotor blade tip is required to be kept, the blade is stiffer than the conventional blade in the flapping, shimmy and torsion directions, and the dynamics characteristics of the blade are different from those of the conventional rotor blade, so that the rigidity of the conventional hingeless pitch-variable hub is high, the resonance risk of the rotor blade exists, and the flight safety and the service life of the helicopter are influenced.

2. In the prior art, a hinged-free hub and blade connection mode generally adopts a double-pin method, a blade wing profile starts at the root of a blade, and the root of the blade is connected with the hub through a blade pin, so that the blade wing profile which truly generates lift force is not maximally close to the hub, the starting position of the rotor wing profile deviates from the rotation center of a rotor wing, and the improvement of the aerodynamic efficiency of a helicopter and the reduction of aerodynamic resistance are not facilitated;

3. the axial locking of the bearing of the hingeless hub in the prior art generally adopts a large nut mode. On one hand, the larger nut has large volume and needs special tools for locking operation, and cannot be finished by conventional tools, so that the installation cost is increased; on the other hand, the moment loaded by the large nut is larger, when the bearing is axially fixed, the wall thickness of the metal part to be fixed reaches a certain degree (the thickness of a single side is usually not less than 6-8 mm), so that the rigidity of the hub is increased greatly, the rotor wing is caused to resonate, and the flight safety and the service life of the helicopter are affected.

Therefore, how to optimize the variable-pitch hinge structure to reduce rigidity and solve the technical problem that helicopter resonance is possibly caused in the process of transmitting hub power to the blades is one of the technical problems.

Disclosure of Invention

In view of the above analysis, the invention aims to provide a hingeless pitch-variable hub, a helicopter rotor wing and a helicopter, so as to solve the technical problems that the existing rotor hub is unreasonable in structure, rotor wing resonance is easy to generate, and the aerodynamic efficiency and flight safety of the helicopter are affected.

The specific technical scheme is as follows:

a hingeless pitch change hub includes a hub center housing and a plurality of hub pitch change members; the plurality of hub variable-pitch components are uniformly distributed on the outer peripheral side of the hub central shell; each hub variable-pitch component is provided with a variable-pitch hinge support piece capable of penetrating through the blade connecting unit; the pitch-changing component of the propeller hub further comprises a propeller clamp shell, a torque-changing transmission assembly and a pitch-changing pull rod assembly; the variable-pitch hinge support piece is rotatably arranged in the paddle clamp shell, and the variable-pitch transmission assembly is limited and arranged between the paddle clamp shell and the variable-pitch hinge support piece; the proximal end of the paddle unit is connected inside the variable-pitch hinge support; the pitch change pull rod assembly is arranged inside the hub central shell; one end of the variable-pitch pull rod assembly is connected with the proximal end of the variable-pitch hinge support piece and is positioned in the hub central shell.

Further, the proximal end of the paddle unit is connected with the inside of the variable-pitch hinge support in a penetrating manner; the inside of the variable-pitch hinge support piece is sequentially provided with a support piece inner cavity positioning part, a support piece inner cavity transition part and a support piece inner cavity cone part along the axial direction; the support member inner cavity cone portion is a conical cavity with a distal end diameter larger than a proximal end diameter.

Further, the paddle clamp shell comprises a paddle clamp shell cylinder; the inside of the paddle clamp shell barrel is sequentially provided with a cylindrical roller bearing outer mounting part, a thrust cylindrical bearing outer mounting part, a paddle clamp shell limiting table and an angle bearing outer mounting part along the axial direction.

Further, the outer part of the variable-pitch hinge support piece is sequentially provided with a cylindrical roller bearing inner mounting part, a thrust cylindrical bearing inner mounting part, an angular bearing inner mounting part, a support piece axial positioning groove, an axial positioning block positioning ring table and a support piece barrel tail along the axial direction; the axial positioning block locating ring table is radially provided with an axial positioning block ring table locking part.

Further, the torque transmission assembly includes a torque transmission unit; the torque transmission unit comprises a cylindrical roller bearing, a thrust cylindrical bearing unit and an angular bearing which are sequentially arranged along the axial direction; the thrust cylindrical bearing unit comprises 2 thrust cylindrical bearings which are axially and continuously arranged.

Further, a second baffle ring is arranged between the cylindrical roller bearing and the thrust cylindrical bearing unit, and a first baffle ring is arranged at the far end surface of the angle bearing;

an axial positioning unit is arranged at the distal end face of the first baffle ring; the axial positioning unit comprises at least 2 axial positioning blocks.

Further, the axial positioning block is provided with an axial positioning table, a positioning locking part, an anti-rotation limiting groove and an axial adjustment installation part; the axial position adjusting member is connected to the axial position adjusting mounting portion.

Further, the axial positioning table is arranged at the proximal end of the axial positioning block; the anti-rotation limiting groove is axially and penetratingly arranged in the middle of the inner ring of the axial positioning block; the axial positioning block is provided with a positioning locking part, and the positioning locking part is connected with a radial compression bolt.

A helicopter rotor comprising at least 1 of said hingeless pitch hubs, further comprising blade units and rotor hub connection units; the rotor hub connection unit comprises an anti-rotation pin and a blade lock nut; the blade unit includes a blade mount and a blade airfoil; the blade mounting part is arranged in the variable-pitch hinge support in a penetrating manner and is connected to the proximal end of the variable-pitch hinge support through the blade locking nut; the anti-rotation pin is arranged at the joint of the blade mounting part and the blade airfoil part and is used for radially limiting the blade unit on the variable-pitch hinge support.

A helicopter comprising the helicopter rotor and a helicopter body; the helicopter body is provided with a control system; the control system is positioned in the hub central shell and is connected with the variable-pitch pull rod assembly; the control system can drive the blade unit to do variable-pitch motion through the variable-pitch pull rod assembly and the variable-pitch hinge support piece.

Compared with the prior art, the invention has at least the following beneficial effects:

1. the hingeless pitch-variable hub has the advantages that the proximal end of the blade unit is connected inside the pitch-variable hinge support piece and the pitch-variable pull rod assembly is arranged inside the central shell of the hub, so that the overall structure of the hingeless pitch-variable hub is compact, and the starting position of the blade unit is as close to the rotation center of the hingeless pitch-variable hub as possible; the connection mode can effectively reduce the pneumatic waste resistance of the control system of the helicopter, improve the pneumatic efficiency of the helicopter and reduce the pneumatic resistance of the helicopter.

2. According to the hingeless pitch-changing hub, the blade units are compressed in the installation process and loaded by the blade locking nuts, and the supporting positions of the blade units are arranged between the blade installation parts and the conical surfaces of the pitch-changing hinge supporting pieces, so that the requirement of rotor wing installation on special tools is avoided, and the installation efficiency is effectively improved.

3. The variable-pitch propeller hub has the advantages that the thickness of the proximal end of the variable-pitch propeller support is larger, the design of thinness is adopted at the distal end, the integral rigidity of the non-hinged variable-pitch propeller hub is effectively reduced, the service life of the non-hinged variable-pitch propeller hub is prolonged, the occurrence of rotor resonance phenomenon is avoided, and the pneumatic efficiency and the flight safety of a helicopter are effectively improved.

Additional features and advantages of the invention will be set forth in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. The objectives and other advantages of the invention may be realized and attained by the structure particularly pointed out in the written description and drawings.

Drawings

The drawings are only for purposes of illustrating the embodiments and are not to be construed as limiting the invention, and like reference numerals refer to like parts throughout the several views.

FIG. 1 is a schematic view of a structure of a hingeless pitch hub according to embodiment 1 of the present invention after mounting a blade unit;

FIG. 2 is a cross-sectional view taken along line A-A of FIG. 1;

FIG. 3 is a schematic view of a variable pitch hinge support member according to embodiment 1 of the present invention;

FIG. 4 is a cross-sectional view taken along B-B in FIG. 3;

FIG. 5 is a schematic view of a hub flange structure according to embodiment 1 of the present invention;

FIG. 6 is a cross-sectional view taken along line C-C of FIG. 5;

FIG. 7 is a schematic view of an axial positioning block according to embodiment 1 of the present invention;

fig. 8 is a schematic view of a rotor swing arm according to embodiment 1 of the present invention;

FIG. 9 is a schematic view of a hub center housing structure according to embodiment 1 of the present invention;

FIG. 10 is a sectional view taken along the direction D-D in FIG. 9;

FIG. 11 is a schematic view of a helicopter rotor configuration according to embodiment 2 of the present invention;

fig. 12 is a schematic view of the structure of the blade unit of the present invention.

Reference numerals:

1. a hub center housing; 11. a mounting table on the housing; 111. a housing upper mounting portion; 12. a mounting table under the shell; 121. a housing lower mounting portion; 13. a housing-side mounting portion; 131. a housing-variable-distance-portion mounting surface; 1311. a housing hub mounting location; 132. a housing hub yielding portion; 2. a hub component; 21. a paddle clamp housing; 211. a paddle clip housing cylinder; 2111. an angular bearing outer mounting portion; 2112. a paddle clamp shell limiting table; 21121. the limiting table passes through the oil hole; 2113. an outer mounting part of the thrust cylindrical bearing; 2114. an outer mounting part of the cylindrical roller bearing; 212. a paddle clamp housing flange; 2121. the flange mounting position of the paddle clamp shell; 213. a first oil filler hole; 214. a second oil filling hole; 2151. a first clamping groove; 2152. a second clamping groove; 22. a torque conversion transmission assembly; 2211. an axial positioning block; 22111. an axial positioning table; 22112. positioning and locking parts; 22113. an anti-rotation limit groove; 22114. reserving an installation part; 22115. an axial adjustment mounting portion; 2212. a first baffle ring; 2213. a second baffle ring; 2221. a first retainer ring; 2222. the second check ring; 2231. a first oil seal; 2232. a second oil seal; 224. an angular bearing; 225. a thrust cylindrical bearing; 226. cylindrical roller bearings; 23. a variable-pitch hinge support; 231. a support member lumen; 2311. a support member lumen cone portion; 2312. a support member lumen transition; 2313. a support member inner cavity positioning portion; 232. the support piece is provided with an axial positioning groove; 233. an angular bearing inner mounting portion; 234. an inner mounting part of the thrust cylindrical bearing; 235. an inner mounting portion of the cylindrical roller bearing; 236. positioning the annular table by an axial positioning block; 2361. an axial positioning block annular table locking part; 2362. axial positioning block annular table circumferential limit part; 237. an anti-slip pin passing portion; 238. a support flange; 2381. a support flange connection location; 2382. a support flange mounting location; 239. a support piece tail; 24. an oiling unit; 241. a first oil filler plug; 242. a second oil filling plug; 25. a variable-pitch pull rod assembly; 251. rotor swing arms; 2511. a rotor swing arm mounting table; 25111. a rotor swing arm mounting portion; 2512. a rotor swing arm connecting arm; 25121. a rotor swing arm connection; 252. a variable-pitch pull rod unit; 2521. a power input part of the variable-pitch pull rod; 26. a radial compression bolt; 27. balancing weight; 3. a blade unit; 31. a blade mounting portion; 311. blade locking part; 312. a blade locking support; 313. a paddle transition portion; 314. a blade anti-slip pin connection; 315. blade damping cavity; 32. blade airfoil; 4. a rotor hub connection unit; 41. an anti-rotation pin; 42. blade lock nuts; 100. an upper rotor section; 200. a lower rotor section.

Detailed Description

The technical scheme of the invention is specifically described below with reference to fig. 1-12. Wherein the showings are for the purpose of illustrating the principles of the invention and together with the description of the embodiments thereof are not intended to limit the scope of the invention.

The present embodiment sets:

(1) All components, units, parts are proximal at their ends close to the hub center housing 1 center and distal at their ends remote from the hub center housing 1 center.

(2) The up and down direction setting is marked by taking the position of the helicopter in a stopped landing state as a setting.

Example 1

Embodiment 1 of the invention shows a hingeless pitch hub.

The technical solution of the hingeless pitch hub according to embodiment 1 will be described with reference to fig. 1 to 10.

As shown in fig. 1, the hingeless pitch hub of this embodiment 1 includes a hub center housing 1 and a hub pitch change member 2; the hub central shell 1 is used for connecting the hub variable-pitch component 2 and a helicopter body; the plurality of the hub variable-pitch components 2 are uniformly and circumferentially connected to the outer peripheral side of the hub central shell 1. The blade unit 3 of the helicopter is connected through to said hub pitch change member 2. The central hub shell 1 is axially connected with the helicopter body, and the central axis of the central hub shell 1 is the rotation center of a rotor wing of the helicopter.

Specifically, this embodiment 1 includes four of the hub pitch change members 2; the four hub variable-pitch parts 2 are circumferentially and uniformly distributed in the middle of the outer peripheral side of the hub central shell 1. Four of said hub pitch members 2 are adapted to be correspondingly connected to said blade units 3 of four of said helicopters.

The hub center housing 1 is open at both ends, and includes a housing upper mounting table 11, a housing lower mounting table 12, and a housing side mounting portion 13. The housing-side mounting portion 13 is provided on the outer peripheral side of the hub center housing 1.

As shown in fig. 9 and 10, in the preferred embodiment 1, the hub central housing 1 has an overall structure of a rotary housing with an arc-shaped bus bar and open ends, and a through hole formed in the middle is used for through connection with the helicopter body.

The upper shell mounting table 11 and the lower shell mounting table 12 are distributed at the upper end and the lower end of the hub central shell 1; the upper shell mounting table 11 and the lower shell mounting table 12 are provided with an upper shell mounting part 111 on the periphery of the upper end surface through hole of the upper shell mounting table 11, and a lower shell mounting part 121 on the periphery of the lower end surface through hole of the lower shell mounting table 12.

The upper housing mounting part 111 and the lower housing mounting part 121 are specifically screw holes for mounting the helicopter body; the control system in the helicopter body is accommodated in the inner cavity of the rotary shell of the hub central shell 1. The control system is provided with a power output part, and the output power drives the blade unit 3 to perform variable-pitch motion through the hub variable-pitch component 2.

Specifically, in the embodiment 1, four housing-side mounting portions 13 are uniformly distributed on the circumference of the middle portion of the outer peripheral side of the hub central housing 1; each of the housing-side mounting portions 13 is connected to 1 of the hub pitch members 2.

As shown in fig. 9 and 10, each of the housing-side mounting portions 13 includes a housing-pitch-changing-portion mounting surface 131 and a housing hub relief portion 132. The housing hub relief 132 is provided at an end face of the housing variable-pitch portion mounting surface 131 and penetrates the housing of the hub center housing 1.

Specifically, the housing hub relief 132 of the embodiment 1 is located in the middle of the housing pitch-changing-portion mounting surface 131 and penetrates through the rotary-type housing sidewall of the hub center housing 1; the steering system of the helicopter is able to connect the hub pitch change member 2 through the space of the housing hub relief 132.

A plurality of housing hub mounting positions 1311 are arranged on the housing variable-pitch portion mounting surface 131; the hub pitch member 2 is attached to the housing pitch-changing portion mounting surface 131, and the hub center housing 1 is connected to the housing pitch-changing portion mounting surface 131. Preferably, the housing hub mounting location 1311 is a screw hole.

The hub pitch member 2 and the helicopter blade unit 3 to which it is attached are attached to the hub center housing 1 in the direction normal to the housing pitch change mounting surface 131.

As shown in fig. 2 and 10, the housing torque converter mounting surface 131 of embodiment 1 is preferably inclined with respect to the center axis of the hub center housing 1.

Specifically, in embodiment 1, a pre-taper angle a exists between the normal line of the housing torque converter mounting surface 131 and the end surface of the hub center housing 1. The pre-taper angle a can enable the position of the distal end of the hub variable-pitch component 2 and the blade unit 3 connected with the hub variable-pitch component to be higher than the position of the proximal end of the hub variable-pitch component (the ground position state), the unloading effect of the blade unit 3 on centrifugal force can be increased, the static bending moment of the proximal end of the blade unit 3 is reduced, and the service life of the integral structure of the blade unit 3 is prolonged.

The pre-taper angle a is related to the helicopter take-off weight, overload design parameters, the centrifugal force of the blade unit 3, the number of blades of the blade unit 3 and the like.

Preferably, in this embodiment 1, a is 5 °.

As shown in fig. 1 and 2, the hub pitch block 2 includes a pitch clamp housing 21, a torque transmission assembly 22, a pitch hinge support 23, and a pitch link assembly 25.

The paddle clip housing 21 is connected to the housing pitch change portion mounting surface 131 of the housing side mounting portion 13 at a proximal end thereof by a fastener; the variable-pitch hinge support piece 23 is arranged inside the paddle clamp shell 21, and the torque conversion transmission assembly 22 is arranged between the paddle clamp shell 21 and the torque conversion transmission assembly 22 in a limiting mode; the pitch hinge support 23 is rotatable relative to the blade holder housing 21 by the torque converter transmission assembly 22.

As shown in fig. 1, in this embodiment 1, the pitch link assembly 25 is located in the inner cavity of the hub central housing 1, a first end of the pitch link assembly 25 is connected to the proximal end of the pitch hinge support 23, and a second end of the pitch link assembly 25 can be connected to the steering system of the helicopter. The control system of the helicopter is positioned on the helicopter body in the inner cavity of the hub central housing 1.

The blade unit 3 is connected in a penetrating manner to the pitch-varying hinge support 23, is fixedly connected to the pitch-varying hinge support 23 through the rotor hub connection unit 4, and rotates with the rotation of the pitch-varying hinge support 23.

The control system drives the variable-pitch hinge support piece 23 to rotate by taking the central axis of the paddle clamp shell 21 as a central line through the variable-pitch pull rod assembly 25, so that the variable-pitch motion of the paddle unit 3 under the control of the control system is realized, the purpose of adjusting the lifting force and the direction is achieved, and the purpose of controlling the helicopter to realize various flight attitudes is achieved.

As shown in fig. 5 and 6, the paddle holder housing 21 of the embodiment 1 has a cylindrical structure with two open ends, and includes a paddle holder housing cylinder 211 and a paddle holder housing flange 212 that are integrally formed. The inside of the blade holder housing cylinder 211 is provided with a cylindrical roller bearing outer mounting portion 2114, a thrust cylindrical bearing outer mounting portion 2113, a blade holder housing limit table 2112 and the blade holder housing cylinder 211 for connecting the torque converter transmission assembly 22 in order along the axial direction.

The blade clamp housing flange 212 is a flanging flange plate arranged at the proximal end of the blade clamp housing cylinder 211, and is provided with a blade clamp housing flange mounting position 2121 which is matched with the housing blade hub mounting position 1311 in position and size; the outer end surface of the blade holder housing flange 212 is attached to the housing pitch change portion mounting surface 131. The blade clamp housing flange mounting locations 2121 of this embodiment are through holes that match the housing hub mounting locations 1311 in position and size.

Fasteners pass through the rotor clamp housing flange mounting locations 2121 and are threaded onto the housing hub mounting locations 1311 to securely attach the hub pitch change member 2 to the hub center housing 1.

The outer part of the paddle clamp shell cylinder 211 is in a stepped shaft shape, and is in arc transition connection with the paddle clamp shell flange 212 at the proximal end. The inside of the paddle clamp shell body 211 is provided with a stepped hole, and the stepped hole is used for being matched with the outer structure of the variable-pitch hinge support 213 to axially limit and connect with the torque conversion transmission assembly 22.

Such a special-shaped cylindrical structure of the blade holder housing flange 212 can increase the structural rigidity of the blade holder housing 21 while achieving light weight.

As shown in fig. 6, specifically, a paddle clip housing limit table 2112 is provided in the paddle clip housing cylinder 211 of embodiment 1 at a position near the distal end; the paddle clamp housing limit table 2112 is provided with a paddle clamp housing cylinder 211 in a distal direction, and the paddle clamp housing limit table 2112 is provided with a thrust cylindrical bearing outer mounting portion 2113 and a cylindrical roller bearing outer mounting portion 2114 in sequence in a proximal direction. The paddle holder housing limit table 2112 is provided with a limit table oil hole 21121 which is axially penetrated.

The paddle clamp housing 21 of this embodiment 1 is further provided with a first clip groove 2151 and a second clip groove 2152 at both ends inside. The first clamping groove 2151 and the second clamping groove 2152 have a ring groove structure.

The variable pitch hinge support 23 of embodiment 1 has a cylindrical structure, is rotatably provided inside the paddle clamp housing 21, and is rotatable with respect to the paddle clamp housing 21 by the torque converter transmission assembly 22; the proximal end of the blade unit 3 is connected inside the pitch hinge support 23; the pitch link assembly 25 is attached to the proximal end of the pitch hinge support 23.

As shown in fig. 3 and 4, in particular, the proximal end of the variable pitch hinge support 23 is provided with a support flange 238. A plurality of support flange connection positions 2381 are uniformly distributed on the periphery of the support flange 238; the support flange connection location 2381 is used to connect the torque rod assembly 25.

Preferably, the support flange connection position 2381 is a screw hole.

A support flange mounting location 2382 is provided at the center of the proximal end face of the support flange 238; the support flange mounting locations 2382 are used to connect the blade units 3. Preferably, the support flange mounting location 2382 is a counter sink structure.

The whole outside of the variable-pitch hinge support 23 is of a stepped shaft structure, and a cylindrical roller bearing inner mounting part 235, a thrust cylindrical bearing inner mounting part 234, an angular bearing inner mounting part 233, a support axial positioning groove 232 and an axial positioning block positioning annular table 236 are sequentially arranged from the proximal end to the distal end along the axial direction and are used for connecting the variable-pitch transmission assembly 22; the furthest end of the variable-pitch hinge support 23 is a support barrel tail 239.

A plurality of radially arranged axial positioning block annular table locking parts 2361 are uniformly distributed on the circumference of the axial positioning block positioning annular table 236. Preferably, the axial positioning block annular table locking portion 2361 of embodiment 1 is a screw hole.

The axial positioning block positioning ring 236 is further provided with a plurality of raised axial positioning block ring circumferential limiting portions 2362. The axial positioning block annular table circumferential limiting part 2362 is arranged along the direction of the bus.

The support barrel 239 is provided with an anti-slip pin passing portion 237 penetrating in the radial direction. The anti-slip pin passing portion 237 is used for installing an anti-slip pin 41 for restricting the rotation of the blade unit 3.

In embodiment 1, a weight 27 is preferably further connected to the anti-skid pin passing portion 237; the weight 27 is preferably mounted on the outer periphery of the blade holder housing 21 by the anti-rotation pin 41.

When the dynamic balance of the helicopter rotor needs to be adjusted, the balancing weight 27 can be increased or decreased to perform balancing work.

As shown in fig. 4, inside the variable-pitch hinge support 23, a support lumen positioning portion 2313, a support lumen transition portion 2312, and a support lumen cone portion 2311 are sequentially provided along the axis from the proximal end to the distal end. The buttress lumen taper 2311 is a tapered cavity having a distal diameter greater than a proximal diameter.

The support lumen locating portion 2313 is used to locate the proximal end of the blade unit 3.

As shown in fig. 4, the whole structure of the variable-pitch hinge support 23 is a special-shaped cylinder, and the proximal end is thicker; the distal end of the support member lumen taper 2311 is a tapered lumen with a taper angle that opens distally and a tapered distal wall thickness. The structure has the technical effects that:

(1) The wall thickness of the variable-pitch hinge support 23 is gradually thinned towards the distal end of the support barrel tail 239, the diameter of the inner cavity is gradually increased, the variable-pitch hinge support can adapt to the gradual increase of the appearance of the blade unit 3 towards the distal end, and the variable-pitch hinge support is convenient for carrying out strength enhancement structural design on the blade unit 3.

(2) The rigidity of the blade unit 3 in the flight process of the helicopter is required to meet the requirement that the advancing edge bears most of the lifting force and the distance between the upper rotor blade tip and the lower rotor blade tip is kept, so that the blade unit 3 is stiffer than a conventional blade in the flapping, shimmy and torsion directions; the rotor hub stiffness is reduced, avoiding the risk of rotor resonance; the variable-pitch hinge support 23 has larger proximal end thickness and thinner distal end, can effectively reduce the integral rigidity of the hingeless variable-pitch hub, and meets the requirement of the helicopter on the rigidity of the hingeless variable-pitch hub in the flight process.

As shown in fig. 2, the torque converter transmission assembly 22 of the present embodiment 1 is mounted between the inner wall surface of the blade holder housing 21 and the outer wall surface of the pitch hinge support 23.

The torque converter transmission assembly 22 includes a torque transmission unit, a torque transmission axial limit unit, an oil seal unit, and a retainer ring unit.

In particular, the torque transmission unit includes a cylindrical roller bearing 226, a thrust cylindrical bearing unit, and an angular bearing 224, which are disposed in axial order from the proximal end to the distal end. Wherein the thrust cylindrical bearing unit comprises 2 thrust cylindrical bearings 225 arranged axially in succession.

As shown in fig. 2, 4 and 6, the cylindrical roller bearing 226 is disposed between the cylindrical roller bearing inner mounting portion 235 and the cylindrical roller bearing outer mounting portion 2114; the angular bearing 224 is disposed between the angular bearing inner mount 233 and the angular bearing outer mount 2111. The cylindrical roller bearing 226 and the angular bearing 224 receive the swing bending moment of the blade unit 3 to form radial damping.

Specifically, the thrust cylindrical bearing unit is disposed between the thrust cylindrical bearing inner mounting portion 234 and the thrust cylindrical bearing outer mounting portion 2113; the two thrust cylindrical bearings 225 of the thrust cylindrical bearing unit bear the axial centrifugal load of the blade unit 3, forming tangential damping.

The torque transmission axial limiting unit comprises an axial positioning unit, a first baffle ring 2212 and a second baffle ring 2213. The axial positioning unit comprises at least two axial positioning blocks 2211.

As shown in fig. 2, the axial positioning unit of the present embodiment 1 includes two axial positioning blocks 2211 of semi-circular arc plates, and the two axial positioning blocks 2211 are circumferentially connected to the outer periphery of the variable-pitch hinge support 23, specifically located at the support axial positioning groove 232 and the axial positioning block positioning annular table 236.

As shown in fig. 7, the axial positioning blocks 2211 are preferably arc plates with less semicircle, so that two axial positioning blocks 2211 are connected to the variable-pitch hinge support 23 without interference.

Specifically, an axial positioning table 22111 of an inner ring table is disposed at the proximal end of the axial positioning block 2211, and an anti-rotation limiting groove 22113 penetrating along the bus is disposed in the middle of the inner ring of the axial positioning block 2211. The axial positioning table 22111 is mounted within the support axial positioning slot 232. The anti-rotation limiting groove 22113 is configured to receive the axial positioning block annular table circumferential limiting portion 2362 to limit circumferential rotation of the axial positioning block annular table 236. The anti-rotation limiting groove 22113 and the axial positioning table 22111 can prevent the axial positioning unit from rotating circumferentially and axially on the variable-pitch hinge support 23, and ensure that the positions of the anti-rotation limiting groove 22113 and the axial positioning table 22111 are relatively fixed so as to keep the consistency of movement.

Specifically, the axial positioning block 2211 is circumferentially provided with a plurality of positioning locking parts 22112; preferably, the positioning and locking portion 22112 is a radial through hole symmetrically arranged at two sides of the anti-rotation limiting groove 22113, the positioning and locking portion 22112 is connected with a radial compression bolt 26, and the radial compression bolt 26 can further fasten the axial positioning unit to the outer periphery of the variable-pitch hinge support 23.

Specifically, the axial positioning block 2211 is further provided with an axial adjustment mounting portion 22115 for mounting an axial position adjustment member for adjusting an axial position of the internal structure of the torque converter transmission assembly 22.

Preferably, the axial direction adjustment mounting portion 22115 of the present embodiment 1 is a plurality of screw hole structures that are circumferentially arranged and pass through, and the axial direction position adjustment member is an axial direction position adjustment screw.

Specifically, the axial positioning block 2211 is further provided with an axial positioning block connection ear, and the axial positioning block connection ear is provided with a reserved mounting portion 22114. Preferably, the reserved installation part 22114 is a screw hole structure and is used for being screwed with the peripheral equipment.

Wherein the first stop ring 2212 is disposed between the proximal end of the axial positioning unit and the distal end of the angular bearing 224. Tightening the axial position adjustment screw of the axial position adjustment member can push the first stop ring 2212 in a proximal direction, thereby adjusting the axial position of the angular bearing 224, axially fastening the angular bearing 224 at the distal end face of the paddle clamp housing stop table 2112, ensuring that the angular bearing 224 is free from axial play, ensuring that the angular bearing 224 is subjected to a minimal radial load and no slippage occurs during operation.

Wherein the second stop ring 2213 is disposed between the distal end of the cylindrical roller bearing 226 and the proximal end of the thrust cylindrical bearing unit. By selecting a proper axial height dimension, on one hand, the second baffle ring 2213 can be matched with the proximal end surface of the paddle clamp shell limiting table 2112 to clamp the thrust cylindrical bearing unit, so that the thrust cylindrical bearing unit is ensured to have no axial play; on the other hand, the second stop ring 2213 is disposed between the cylindrical roller bearing 226 and the thrust cylindrical bearing unit, so that the force transmission direction can be effectively ensured (because the inner ring of the cylindrical roller bearing 226 is relatively narrow, and the load and the service life of the thrust cylindrical bearing 225 are affected by the point load when centrifugal force is transmitted, and the second stop ring 2213 can convert the point load into a surface load and then apply pressure to the thrust cylindrical bearing 225, so that the thrust cylindrical bearing unit is prevented from bearing unbalanced load).

Specifically, the oil seal unit and the first and second oil seals 2231 and 2232 are included.

Specifically, the collar unit includes a first collar 2221 and a second collar 2222.

The first oil seal 2231 is disposed at a proximal end of the first retainer 2221 and the second oil seal 2232 is disposed at a distal end of the second retainer 2222 in an overall structural layout of the torque converter transmission assembly 22. The retainer ring unit axially positions the oil seal unit, and the oil seal unit is used for locking lubricating grease in the torque conversion transmission assembly 22, so that the lubricating grease is prevented from being thrown out under the action of centrifugal force.

Specifically, the first retainer ring 2221 is disposed in a first clamping groove 2151 at a distal end inside the paddle clamp housing 21, and the first oil seal 2231 is axially installed at a proximal end of the first clamping groove 2151 and radially installed between an outer periphery of the first retainer ring 2212 and the angular bearing outer mounting portion 2111.

Specifically, the second retainer ring 2222 is disposed in a second clamping groove 2152 at a proximal end inside the paddle clip housing 21; the second oil seal 2232 is axially installed at the distal end of the second clamping groove 2152, radially installed between the outer circumference of the cylindrical roller bearing inner installation portion 235 and the cylindrical roller bearing outer installation portion 2114.

As shown in fig. 5, an oil injection structure is disposed on the wall of the paddle holder housing cylinder 211, and the oil injection structure includes a first oil injection hole 213 and a second oil injection hole 214.

The oiling structure is used for connecting an oiling unit 24, and the oiling unit 24 is used for injecting the lubricating grease into the torque conversion transmission assembly 22 in the paddle clamp shell 21, so that the torque conversion transmission assembly 22 can flexibly rotate. Preferably, the grease is an aviation grease.

The oil filling unit 24 includes a first oil filling plug 241 and a second oil filling plug 242. A first oil filling hole 213 is connected to the first oil filling plug 241, and a second oil filling hole 214 is connected to the second oil filling plug 242.

As shown in fig. 2 and 6, preferably, the axis of the first oil hole 213 is radially disposed on the proximal wall surface of the limiting table 2112 of the blade holder housing, and is communicated with the oil passing hole 21121 of the limiting table; so that the grease injected from the first grease plug 241 can lubricate the thrust cylindrical bearing unit and the angular bearing 224 at the same time.

As shown in fig. 2 and 6, preferably, the axis of the second oil plug 242 is radially disposed at the junction of the outer cylindrical roller bearing mounting portion 2114 and the outer cylindrical thrust bearing mounting portion 2113 and located on the outer cylindrical thrust bearing mounting portion 2113 side; so that the grease injected from the second grease plug 242 can lubricate the thrust cylindrical bearing unit and the cylindrical roller bearing 226 at the same time.

As shown in fig. 1 and 2, the proximal end face of the support flange 238 of the roll hinge support 23 is connected to the roll bar assembly 25 by the support flange connection location 2381.

The control system drives the variable-pitch pull rod assembly 25 and the variable-pitch hinge support piece 23 to rotate together with the central axis of the paddle clamp shell 21 as the center, so that the variable-pitch movement of the paddle unit 3 under the control of the control system is realized, the purpose of adjusting the magnitude and the direction of the lifting force generated by the paddle unit 3 is achieved, and the purpose of controlling the helicopter to realize various flight attitudes is achieved. Specifically, the pitch link assembly 25 includes a rotor swing arm 251 and a pitch link unit 252; the rotor swing arm 251 is hinged to the pitch link unit 252.

Preferably, the rotor arm 251 of the present embodiment 1 is connected to the proximal end of the pitch hinge support 23, and the pitch link unit 252 is connected to the steering system.

As shown in fig. 8, the rotor swing arm 251 includes a rotor swing arm mounting base 2511 and a rotor swing arm connection arm 2512, and the rotor swing arm mounting base 2511 articulates the rotor swing arm connection arm 2512.

The rotor swing arm mounting table 2511 is a ring table structure, and a plurality of rotor swing arm mounting parts 25111 are uniformly distributed on the circumference of the rotor swing arm mounting table 2511; the rotor swing arm mounting portion 25111 is structured to correspond to the support flange connection location 2381, preferably a via structure. The fastener passes through the rotor swing arm mounting part 25111 and is in threaded connection with the screw hole of the support member flange connection position 2381, and the pitch change pull rod assembly 25 is fixedly connected to the proximal end surface of the pitch change hinge support member 23, so that the control system drives the pitch change hinge support member 23 to rotate by taking the central axis of the blade clamp shell 21 as the center through the pitch change pull rod assembly 25, and the pitch change movement of the blade unit 3 is realized.

As shown in fig. 8, the rotor arm connecting arm 2512 has an arm structure with respect to the rotor arm mounting base 2511, and a rotor arm connecting portion 25121 is provided at a distal end of an arm of the rotor arm connecting arm 2512; the center of the rotor swing arm connection 25121 is far from the central axis of the rotor swing arm mounting table 2511; the pitch link assembly 25 is connected to the power take off of the steering system via the rotor swing arm connection 25121.

The variable-pitch pull rod assembly 25 of this embodiment 1 is connected to the inner cavity of the paddle clamp housing 21, so that not only can the external devices of the unmanned aerial vehicle be reduced, but also the pneumatic waste resistance of the operating system can be effectively reduced.

Example 2

Embodiment 2 discloses a helicopter rotor.

The technical solution of this embodiment 2 will be described with reference to fig. 1, 2, 11 and 12.

As shown in fig. 1 and 2, the helicopter rotor according to embodiment 2 includes 2 hubs; wherein at least 1 hub is the hingeless pitch hub of embodiment 1 of the present invention.

As shown in fig. 11, the helicopter rotor according to embodiment 2 further includes a blade unit 3 and a rotor hub connection unit 4.

Specifically, four blade units 3 are uniformly distributed and connected on the periphery of each hingeless pitch-variable hub; each blade unit 3 is fixedly connected to the hingeless pitch hub by one of the rotor hub connection units 4. The blade unit 3 rotates with the rotation of the pitch hinge support 23.

Preferably, the helicopter rotor according to embodiment 2 comprises two coaxially arranged hingeless pitch hubs, in particular an upper rotor section 100 and a lower rotor section 200. The helicopter body is coaxially connected to the upper rotor section 100 and the lower rotor section 200, and the upper rotor section 100 and the lower rotor section 200 are identical and each include the hingeless pitch hub of embodiment 1.

The rotor hub connection unit 4 of this embodiment 2 includes an anti-rotation pin 41 and a blade lock nut 42.

As shown in fig. 12, the blade unit 3 of the present embodiment includes a blade mounting portion 31 and a blade airfoil portion 32. The blade mounting portion 31 is provided at the proximal end of the blade unit 3 and the blade airfoil portion 32 is provided at the distal end of the blade unit 3.

As shown in fig. 12, the blade mounting portion 31 is provided with a blade locking portion 311, a blade locking support portion 312, a blade transition portion 313, and a blade anti-slip pin connection portion 314 in this order from the proximal end to the distal end.

In the installation state, the blade locking part 311 is located outside the end surface of the proximal end of the variable-pitch hinge support 23, specifically located outside the end surface of the flange installation position 2382 of the support and located in the inner cavity of the hub central housing 1; the blade lock support 312 and the blade transition 313 are located inside the pitch hinge support 23; the blade anti-slip pin connection 314 is provided on the blade transition 313.

As shown in fig. 2, the blade mounting portion 31 is further provided with a blade damping cavity 315 having a cavity structure at the blade locking support portion 312 and the blade transition portion 313; the function of the blade damping chamber 315 is:

(1) The weight of the paddle units 3 is reduced, the effective weight of the helicopter is reduced, and the pneumatic efficiency of the helicopter is improved.

(2) The structure of the rotor wing of the helicopter is optimized, so that the wall thickness of the whole structure of the blade mounting part 31 tends to be consistent, the structural stress in the manufacturing process of the blade unit 3 can be reduced, the abrupt change of torque transmission stress can be overcome, and the service life of the rotor wing of the helicopter is prolonged.

In embodiment 2, preferably, the blade locking portion 311 and the blade locking support portion 312 have a stepped pillow block structure; the blade locking support part 312 is positioned on the inner wall surface of the support piece inner cavity positioning part 2313; the blade locking part 311 is provided with a bolt structure, the blade locking part 311 extends out of the support member flange mounting position 2382, the blade locking nut 42 is in threaded connection with the blade locking part 311, so that the blade unit 3 is axially positioned and connected to the proximal end of the variable-pitch hinge support member 23, and is specifically connected to the end face of the support member flange mounting position 2382.

Preferably, the outer wall surface of the blade locking support portion 311 is in transitional connection with the inner wall surface of the support member inner cavity positioning portion 2313.

The blade transition portion 312 has a cone structure, and the taper of the blade transition portion 312 is consistent with the taper of the support member inner cavity cone portion 2311.

Preferably, the outer wall surface of the blade transition portion 312 is in transition connection with the inner wall surface of the support member inner cavity cone portion 2311.

This transitional connection between the blade mounting 31 and the pitch hinge support 23, after being axially positioned by the blade lock nut 42, further structurally ensures that the blade unit 3 is stable in position in the radial direction relative to the pitch hinge support 23, ensuring that the blade unit 3 can rotate synchronously with the pitch hinge support 23.

According to the invention, the blade unit 3 is tightly pressed by the blade locking nut 42 at the near end in the installation process, and the supporting position of the blade unit 3 is arranged between the blade installation part 31 and the conical surface of the variable-pitch hinge support piece 23, so that the requirement of rotor installation on special tools is avoided, and the installation efficiency is effectively improved. At the connection of the blade mounting part 31 and the blade airfoil part 32, also at the starting position of the blade airfoil part 32, the blade anti-slip pin connection part 314 is provided relatively perpendicular to the main structure of the blade airfoil part 32. The blade anti-slip pin connection 314 corresponds in position to an anti-slip pin passage 237 radially provided at the distal end of the variable-pitch hinge support 23 for the passage of the anti-slip pin 41.

During the installation of the blade unit 3, the blade installation portion 31 passes through the inside of the variable-pitch hinge support 23, rotates the blade unit 3, and the blade transition portion 312 and the conical surface of the support member inner cavity conical portion 2311 are gradually matched and combined in a progressive manner until the support member inner cavity conical portion 2311 of the variable-pitch hinge support 23 and the blade anti-slip pin connection portion 314 on the blade unit 3 are aligned, and installs the anti-slip pin 41.

In the process of installing the anti-rotation pin 41, the balancing weight 27 is simultaneously allocated and installed.

The anti-rotation pin 41 passes through the anti-slip pin passing part 237 on the support piece barrel tail 239 and the blade anti-slip pin connecting part 314 on the blade unit 3 at the same time, so that the circumferential position of the blade unit 3 can be limited, and the blade airfoil part 32 at the far end is effectively limited to perform circumferential waving.

As shown in fig. 2 and 1, compared to the conventional double pin method for connecting the hingeless hub to the blade, the blade mounting portion 31 of the present embodiment 2 can achieve the following technical effects:

(1) The blade mounting portion 31 of this embodiment 2 passes through the inside of the hingeless pitch hub, so that the helicopter hub of this embodiment 2 is compact.

(2) Compared with the prior art, the blade mounting portion 31 of the embodiment 2 is fixed at a position close to the rotation center of the hingeless pitch hub, so that the starting position of the blade airfoil portion 32 is as close to the rotation center of the rotor as possible, thereby improving the aerodynamic efficiency and reducing the aerodynamic resistance.

At the end of the installation of the blade unit 3, the blade lock nut 42 is also tightened again. The torque applied by the blade lock nut 42 can further compress the conical surfaces of the blade unit 3 and the variable-pitch hinge support 23, so that the structural consistency and the integral linkage of the blade unit 3 and the variable-pitch hinge support 23 can be further enhanced.

Preferably, in embodiment 2, after the blade lock nut 42 finally locks the blade unit 3 again to the proximal end of the variable-pitch hinge support 23, axial positioning reinforcement is performed on the blade lock nut 42, that is, axial positioning bolts are driven into the outer peripheral portion of the end face of the blade lock nut 42, so that the blade lock nut 42 and the variable-pitch hinge support 23 are additionally and fixedly connected in an axial direction. The additional axial connection can prevent the pitch-changing process of the blade unit 3 from loosening.

According to the technical scheme of the embodiment 2, the pneumatic efficiency of the helicopter can be greatly improved, and the pneumatic resistance of the helicopter is reduced.

Example 3

Embodiment 3 discloses a helicopter.

The helicopter includes a helicopter body and a rotor. A control system is arranged on the helicopter body.

This example 3 sets up: the control system is located in the inner cavity of the hub central housing 1, and the rotor is the helicopter rotor according to embodiment 2 of the present invention.

The control system is positioned in the inner cavity of the hub central housing 1 and is connected with the pitch link assembly 25.

Specifically, the control system is connected to the distance-changing rod unit 252 of the distance-changing rod assembly 25, and the control system can drive one end of the distance-changing rod unit 252 to perform an up-and-down displacement motion; the other end of the pitch link unit 252 is hinged to one end of the rotor swing arm 251 of the pitch link assembly 25; the pitch link unit 252 drives the rotor swing arm 251 and the pitch hinge support 23 fixedly connected to the other end of the rotor swing arm 251 to rotate around the axis of the pitch hinge support 23, so as to drive the blade unit 3 connected to the pitch hinge support 23 to perform a pitch movement.

The present invention is not limited to the above-mentioned embodiments, and any changes or substitutions that can be easily understood by those skilled in the art within the technical scope of the present invention are intended to be included in the scope of the present invention.

Claims

1. A hingeless pitch change hub, comprising a hub central housing (1) and a plurality of hub pitch change members (2);

the plurality of hub variable-pitch components (2) are uniformly distributed on the outer periphery side of the hub central shell (1); each hub variable-pitch component (2) is provided with a variable-pitch hinge support (23) which can be connected with a blade unit in a penetrating way;

the pitch changing component (2) of the propeller hub further comprises a propeller clamp shell (21), a torque changing transmission assembly (22) and a pitch changing pull rod assembly (25);

the variable-pitch hinge support (23) is rotatably arranged inside the paddle clamp shell (21), and the variable-pitch transmission assembly (22) is limited and arranged between the paddle clamp shell (21) and the variable-pitch hinge support (23);

one end of the variable-pitch pull rod assembly (25) is connected with the proximal end of the variable-pitch hinge support (23) and is positioned inside the hub central shell (1).

2. A hingeless pitch hub according to claim 1, wherein the proximal end of the blade unit (3) is connected through inside the pitch hinge support (23); a support piece inner cavity positioning part (2313), a support piece inner cavity transition part (2312) and a support piece inner cavity cone part (2311) are sequentially arranged in the variable-pitch hinge support piece (23) along the axial direction; the buttress lumen taper (2311) is a tapered cavity having a distal diameter greater than a proximal diameter.

3. The hingeless pitch hub of claim 1, wherein the blade holder housing (21) comprises a blade holder housing cylinder (211); the inside of the paddle clamp shell cylinder (211) is sequentially provided with a cylindrical roller bearing outer mounting part (2114), a thrust cylindrical bearing outer mounting part (2113), a paddle clamp shell limiting table (2112) and an angular bearing outer mounting part (2111) along the axial direction.

4. A hingeless pitch hub according to claim 3, wherein the outer part of the pitch-controlled hinge support (23) is provided with an inner cylindrical roller bearing mounting part (235), an inner thrust cylindrical bearing mounting part (234), an inner angular bearing mounting part (233), a support axial positioning groove (232), an axial positioning block positioning annular table (236) and a support barrel tail (239) in axial sequence; an axial positioning block annular table locking part (2361) is radially arranged on the axial positioning block positioning annular table (236).

5. The hingeless pitch hub according to claim 1, wherein the torque converter transmission assembly (22) comprises a torque transmission unit; the torque transmission unit comprises a cylindrical roller bearing (226), a thrust cylindrical bearing unit and an angular bearing (224) which are sequentially arranged along the axial direction; the thrust cylindrical bearing unit includes 2 thrust cylindrical bearings (225) disposed axially in succession.

6. The hingeless pitch hub of claim 5, wherein a second stop ring (2213) is disposed between the cylindrical roller bearing (226) and the thrust cylindrical bearing unit, and a first stop ring (2212) is disposed at a distal end face of the angular bearing (224); an axial positioning unit is arranged at the distal end surface of the first baffle ring (2212); the axial positioning unit comprises at least 2 axial positioning blocks (2211).

7. The hingeless pitch hub of claim 6, wherein the axial positioning block (2211) is provided with an axial positioning table (22111), a positioning locking portion (22112), an anti-rotation limiting groove (22113) and an axial adjustment mounting portion (22115); an axial position adjustment member is connected to the axial adjustment mounting portion (22115).

8. The hingeless pitch hub according to claim 7, wherein the axial positioning table (22111) is disposed at a proximal end of the axial positioning block (2211); the anti-rotation limiting groove (22113) is axially and penetratingly arranged in the middle of the inner ring of the axial positioning block (2211); the axial positioning block (2211) is provided with a positioning locking part (22112).

9. Helicopter rotor, characterized in that it comprises at least 1 of said hingeless pitch hubs according to any of claims 1-8, further comprising a blade unit (3) and a rotor hub connection unit (4);

The rotor hub connection unit (4) comprises an anti-rotation pin (41) and a blade lock nut (42);

the blade unit (3) comprises a blade mount (31) and a blade airfoil (32); the blade mounting part (31) is arranged in the variable-pitch hinge support (23) in a penetrating manner and is connected to the proximal end of the variable-pitch hinge support (23) through the blade locking nut (42); the anti-rotation pin (41) is arranged at the joint of the blade mounting part (31) and the blade airfoil part (32) and is used for radially limiting the blade unit (3) on the variable-pitch hinge support (23).

10. A helicopter comprising the helicopter rotor of claim 9, further comprising a helicopter fuselage; the helicopter body is provided with a control system;

the control system is connected with the variable-pitch pull rod assembly (25); the control system can drive the blade unit (3) to do variable-pitch motion through the variable-pitch pull rod assembly (25) and the variable-pitch hinge support piece (23).