Helicopter rotor system

Abstract

The utility model relates to the technical field of aircraft design, and provides a helicopter rotor system which comprises a rotor mechanism, a propeller blade, a propeller clamp assembly, a propeller clamp shaft assembly and a propeller hub central piece, one end of the propeller clamp assembly is connected with the propeller blade through a main propeller bolt, and the other end of the propeller clamp assembly is connected with one end of the propeller clamp shaft assembly. One ends of the propeller clamping shaft assemblies are connected with the propeller blades, the other ends of the propeller clamping shaft assemblies are connected with the propeller hub central piece, the propeller hub central piece is connected with the propeller clamping shaft assemblies, the main propeller bolts comprise the first main propeller bolt and the second main propeller bolt, the first main propeller bolt is arranged at the end close to the propeller blades, and the second main propeller bolt is arranged at the end close to the propeller hub central piece and is detachable and used for folding the propeller blades. According to the utility model, the second main paddle bolt is designed, so that the paddle can be folded in the transportation process, the space is reduced, the transportation is convenient, and the practicability is enhanced.

Description

TECHNICAL FIELD

[0001] The utility model relates to the technical field of aircraft design, especially relates to a helicopter rotor system. BACKGROUND

[0002] The domestic helicopter develops rapidly, is mainly used in the field such as plant protection, electric power inspection, geographical survey, logistics transportation at present. And the rotor system is the key to the flight of helicopter, and the control of rotor system includes four control modes of total moment, longitudinal, lateral and heading.

[0003] Most of the existing hub interiors adopt deep groove ball bearings, and the bearing bears axial force and radial force, but when the rotor rotates, the blade centrifugal force is large, the ball bearing will bear large axial load, which will cause the ball bearing to increase the wear of the ball and the inner and outer rings, the rotor system vibrates and the service life is reduced.

[0004] At present, the rotor system structure of oil-driven multi-rotor helicopter is complex, heavy, high in machining precision requirement and difficult to assemble. The existing rotor system is extremely inconvenient in the transportation process due to the blade length, and often needs to disassemble the blade, which is time-consuming and laborious. UTILITY MODEL CONTENTS

[0005] The utility model aims at at least one of the technical problems existing in the related art. To this end, the utility model provides a helicopter rotor system, the utility model is folded in the transportation process by the design second main paddle bolt, reduces space, convenient transportation, and enhances practicality.

[0006] The utility model provides a helicopter rotor system, including rotor mechanism, the rotor mechanism includes paddle, paddle clamp component, paddle clamp shaft component and hub central part, one end of paddle clamp component is connected with paddle through main paddle bolt, the other end of paddle clamp component is connected with one end of paddle clamp shaft component, the other end of paddle clamp shaft component is connected with hub central part, hub central part connects a plurality of paddle clamp shaft components,

[0007] The main paddle bolt includes first main paddle bolt and second main paddle bolt, and the first main paddle bolt is arranged at the end close to the paddle, and the second main paddle bolt is arranged at the end close to the hub central part, and the second main paddle bolt is detachable, and is used to fold the paddle.

[0008] Further, the paddle clamp component includes a paddle clamp and a paddle pad, one end of the paddle clamp is provided with a U-shaped opening, the paddle is arranged in the U-shaped opening, and the inner wall of the U-shaped opening is provided with a paddle pad, and the paddle pad is connected with the paddle by the first main paddle bolt and the second main paddle bolt.

[0009] Furthermore, the propeller clamp assembly further includes a propeller clamp plug cover, a propeller clamp end cover, a first cylindrical roller bearing, an inner shaft spacer, a thrust bearing, an inner shaft sleeve and a second cylindrical roller bearing;

[0010] The propeller clamp cover is arranged near the end of the second main propeller bolt, one side of the first cylindrical roller bearing abuts against the propeller clamp cover, the other side of the first cylindrical roller bearing abuts against the inner shaft sleeve, one end of the inner shaft spacer abuts against the inner shaft sleeve, and the other end abuts against the inner ring of the second cylindrical roller bearing, the outer ring of the second cylindrical roller bearing abuts against the propeller clamp end cover, the propeller clamp end cover is installed on the side near the propeller clamp shaft through threads, a thrust bearing is provided on the inner shaft sleeve, and the thrust bearing is positioned by a retaining ring;

[0011] The propeller clamp plug cover, the propeller clamp end cover, the first cylindrical roller bearing, the inner shaft spacer, the thrust bearing, the inner shaft sleeve and the second cylindrical roller bearing are all installed inside the propeller clamp.

[0012] Furthermore, the propeller clamp shaft assembly includes a propeller clamp shaft and a bearing, the inner shaft sleeve is installed on the propeller clamp shaft, the bearing is rotatably connected to the propeller hub central piece, a limiting base is provided at the root of the propeller clamp shaft, and the bearings are installed on both sides of the limiting base.

[0013] Furthermore, the hub central piece is provided with a limiting boss, the limiting base is provided with a limiting groove, and the limiting groove is adaptively connected to the limiting boss.

[0014] Furthermore, the propeller clamp assembly also includes a rocker arm, which is mounted on one end of the propeller clamp close to the hub center piece through bolts.

[0015] Furthermore, it also includes a control mechanism, which includes a rotor rod assembly, a swash plate assembly and a servo rod assembly. The rocker arm is connected to one end of the rotor rod assembly by a bolt, and the other end of the rotor rod assembly is connected to the movable plate of the swash plate assembly by a bolt. The fixed plate of the swash plate assembly is connected to the servo rod assembly by bolts, and the servo rod assembly is connected to the rocker arm servo.

[0016] Furthermore, it includes a front rotor subsystem and a rear rotor subsystem, the front rotor subsystem includes the rotor mechanism, the control mechanism and the front main reducer shaft, the rotor mechanism is fixed to the front main reducer shaft through a hub compression nut, and the control mechanism is fixed to the servo disc of the rocker servo through bolts;

[0017] The rear rotor subsystem includes a rotor mechanism, a control mechanism and a rear main reducer shaft. The rotor mechanism is fixed to the rear main reducer shaft through a hub compression nut, and the control mechanism is fixed to the servo disc of the rocker servo through bolts.

[0018] Furthermore, it also includes a control mechanism, which includes a rotor rod assembly, a swash plate assembly and a servo rod assembly. The rocker arm is connected to one end of the rotor rod assembly by a bolt, and the other end of the rotor rod assembly is connected to the movable plate of the swash plate assembly by a bolt. The fixed plate of the swash plate assembly is connected to the linear servo.

[0019] Furthermore, it includes a front rotor subsystem and a rear rotor subsystem, the front rotor subsystem includes the rotor mechanism, the control mechanism and the front main reducer shaft, the rotor mechanism is fixed to the front main reducer shaft through a hub compression nut, and the control mechanism is fixed to the servo disc of the linear servo through bolts;

[0020] The rear rotor subsystem includes a rotor mechanism, a control mechanism and a rear main reducer shaft. The rotor mechanism is fixed to the rear main reducer shaft through a hub compression nut, and the control mechanism is fixed to the servo disc of the linear servo through bolts.

[0021] The above one or more technical solutions in the embodiments of the present invention have at least one of the following technical effects:

[0022] The hub structure in the present invention can be expanded to a rotor hub structure with more than two hub arms and evenly distributed positions. It has strong reproducibility. The two rotor subsystems arranged front and back can be used for tandem helicopters, and the two rotor subsystems arranged up and down can be used for coaxial twin-rotor helicopters. A single rotor system combined with a tail rotor is also suitable for single-rotor helicopters.

[0023] The propeller clamp shaft and the hub center piece are rotatably connected, so that the vibration caused by the blades swinging up and down cannot be directly transmitted to the hub center piece, thereby increasing the stability of flight.

[0024] The propeller clamp is connected to the propeller blade. By designing the propeller blade pad and the second main propeller bolt, the propeller blade can be folded during transportation, which reduces space, facilitates transportation, and enhances practicality.

[0025] When the rotor rotates, the blades are subjected to centrifugal force. This forces the thrust bearing to bear axial force, leaving the cylindrical roller bearings exposed only to radial loads. This reduces wear and increases bearing life, making blade pitch control easier. Furthermore, the blade pitch control can be replaced by a linear servo instead of a rocker servo.

[0026] Additional aspects and advantages of the present invention will be given in part in the following description and will become apparent from the following description or learned through practice of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] In order to more clearly illustrate the technical solutions of the present invention or the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0028] Figure 1 The utility model provides a schematic diagram of the rotor mechanism structure of a helicopter rotor system.

[0029] Figure 2 The utility model is a schematic structural diagram of a blade clamp assembly of a helicopter rotor system.

[0030] Figure 3 The utility model is a schematic structural diagram of a blade clamp shaft assembly of a helicopter rotor system.

[0031] Figure 4 The utility model provides a schematic diagram of the connection of a rocker arm servo of a helicopter rotor system.

[0032] Figure 5 The utility model provides a linear servo connection diagram of a helicopter rotor system.

[0033] Figure 6 The utility model provides a schematic diagram of the connection of the hub central component of a helicopter rotor system.

[0034] Reference numerals:

[0035] 1. Propeller blade; 2. Propeller clamp assembly; 3. Hub centerpiece; 4. Propeller clamp shaft assembly; 5. Second main propeller bolt; 6. First main propeller bolt; 7. Propeller hub compression nut; 8. Rotor lever assembly; 9. Swashplate assembly; 10. Servo lever assembly; 11. Rocker servo; 12. Linear servo; 201. Propeller clamp; 202. Thrust bearing; 203. Inner shaft sleeve; 204. Retaining ring; 205. Inner shaft spacer Sleeve; 206, propeller clamp end cover; 207, rocker arm; 208, first cylindrical roller bearing; 209, second cylindrical roller bearing; 210, blade pad; 211, propeller clamp plugging cover; 212, end locking nut; 213, rubber damping cylinder; 214, sealing ring; 301, limiting boss; 302, propeller clamp shaft assembly mounting hole; 401, propeller clamp shaft; 402, bearing; 403, limiting groove. DETAILED DESCRIPTION

[0036] To make the purpose, technical solutions, and advantages of the present invention more clear, the technical solutions of the present invention will be clearly and completely described below. Obviously, the embodiments described are only some of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making any creative efforts are within the scope of protection of the present invention. The following embodiments are used to illustrate the present invention and are not intended to limit the scope of the present invention.

[0037] In the description of the embodiments of the present invention, the terms "first", "second" and "third" are used for descriptive purposes only and should not be understood as indicating or implying relative importance.

[0038] In the description of the embodiments of the present invention, it should be noted that, unless otherwise specified or limited, the terms "connected" and "connection" should be understood in a broad sense. For example, they can refer to fixed connections, detachable connections, or integral connections; mechanical connections, electrical connections; direct connections, or indirect connections through an intermediary. Those skilled in the art will understand the specific meanings of the above terms in the embodiments of the present invention based on specific circumstances.

[0039] In the description of this specification, the description with reference to the terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the embodiment of the utility model. In this specification, the schematic representation of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art can combine and combine different embodiments or examples described in this specification and the features of different embodiments or examples without contradiction.

[0040] The following combination Figures 1 to 6 The utility model describes a helicopter rotor system.

[0041] A helicopter rotor system includes a rotor mechanism, which includes a blade 1, a propeller clamp assembly 2, a propeller clamp shaft assembly 4, and a hub central component 3. One end of the propeller clamp assembly 2 is connected to the blade 1 through a main propeller bolt, and the other end of the propeller clamp assembly 2 is connected to one end of the propeller clamp shaft assembly 4. The other end of the propeller clamp shaft assembly 4 is connected to the hub central component 3. The hub central component 3 connects multiple propeller clamp shaft assemblies 4.

[0042] The main propeller bolts include a first main propeller bolt 6 and a second main propeller bolt 5. The first main propeller bolt 6 is arranged near the end of the blade 1, and the second main propeller bolt 5 is arranged near the end of the hub central part 3. The second main propeller bolt 5 is detachable for folding the blade 1.

[0043] In some embodiments of the present invention, by removing the second main propeller bolt 5, the blade 1 is rotated around the first main propeller bolt 6, and the blade is folded for easy transportation.

[0044] The propeller clamp assembly 2 includes a propeller clamp 201 and a blade pad 210. A U-shaped opening is provided at one end of the propeller clamp 201, and the blade 1 is arranged in the U-shaped opening. The inner wall of the U-shaped opening is provided with a blade pad 210. The blade pad 210 is connected to the blade 1 through the first main propeller bolt 6 and the second main propeller bolt 5.

[0045] The blade clamp assembly 2 further includes a blade clamp plug cover 211, a blade clamp end cover 206, a first cylindrical roller bearing 208, an inner shaft spacer 205, a thrust bearing 202, an inner shaft sleeve 203 and a second cylindrical roller bearing 209.

[0046] The propeller clamp cover 211 is arranged near the end of the second main propeller bolt 5, one side of the first cylindrical roller bearing 208 abuts against the propeller clamp cover 211, the other side of the first cylindrical roller bearing 208 abuts against the inner shaft sleeve 203, one end of the inner shaft spacer 205 abuts against the inner shaft sleeve 203, and the other end abuts against the inner ring of the second cylindrical roller bearing 209, the outer ring of the second cylindrical roller bearing 209 abuts against the propeller clamp end cover 206, and the propeller clamp end cover 206 is installed on the side near the propeller clamp shaft 401 through threads, and a thrust bearing 202 is provided on the inner shaft sleeve 203, and the thrust bearing 202 is positioned by a retaining ring 204.

[0047] The propeller clamp plug cover 211 , the propeller clamp end cover 206 , the first cylindrical roller bearing 208 , the inner shaft spacer 205 , the thrust bearing 202 , the inner shaft sleeve 203 and the second cylindrical roller bearing 209 are all installed inside the propeller clamp 201 .

[0048] In some embodiments of the present invention, the first cylindrical roller bearing 208, the inner shaft spacer 205, the thrust bearing 202, the inner shaft sleeve 203 and the second cylindrical roller bearing 209 are sealed inside the propeller clamp 201 by the propeller clamp blocking cover 211 and the propeller clamp end cover 206, and a sealing ring 214 is provided between the propeller clamp end cover 206 and the propeller clamp 201 to play a dust-proof and fixing role.

[0049] The first cylindrical roller bearing 208 is axially positioned by the inner shaft sleeve 203 and the end locking nut 212 .

[0050] The second cylindrical roller bearing 209 is axially positioned by the inner shaft spacer 205 and the retaining ring.

[0051] When the rotor rotates, the blade 1 is subjected to centrifugal force. At this time, the thrust bearing 202 is subjected to axial force, so that the first cylindrical roller bearing 208 and the second cylindrical roller bearing 209 are only subjected to radial load, which reduces wear and increases the service life of the bearings. The blade pitch change is easy to operate.

[0052] The propeller clamp assembly 2 further includes a rocker arm 207 , which is mounted on one end of the propeller clamp 201 close to the hub center piece 3 by means of bolts.

[0053] The propeller clamp shaft assembly 4 includes a propeller clamp shaft 401 and a bearing 402. The inner shaft sleeve 203 is installed on the propeller clamp shaft 401. The bearing 402 is rotatably connected to the hub central part 3. A limiting base is provided at the root of the propeller clamp shaft 401, and the bearings 402 are installed on both sides of the limiting base.

[0054] The hub central piece 3 is provided with a limiting boss 301 , and the limiting base is provided with a limiting groove 403 , which is adaptively connected to the limiting boss 301 .

[0055] In some embodiments of the present invention, a propeller clamp shaft assembly mounting hole 302 is provided on the propeller hub central piece 3, and multiple propeller clamp shaft assemblies are installed through the propeller clamp shaft assembly mounting hole 302, so that the rotor system of the present invention can expand multiple propeller hub support arms.

[0056] In some embodiments of the present invention, the propeller clamp shaft assemblies 4 are evenly distributed next to the hub central piece 3. Through bolt connection, the propeller clamp shaft 401 can rotate up and down around the bearing 402 to offset the force of the blades 1 swinging up and down when the rotor system rotates. The hub central piece 3 is provided with a limiting boss 301 to prevent the blades 1 from swinging up and down excessively.

[0057] In one embodiment of the present utility model, the operating mechanism includes a rotor rod assembly 8, a swash plate assembly 9 and a servo rod assembly 10, the rocker arm 207 is connected to one end of the rotor rod assembly 8 by bolts, the other end of the rotor rod assembly 8 is connected to the movable plate of the swash plate assembly 9 by bolts, the fixed plate of the swash plate assembly 9 is connected to the servo rod assembly 10 by bolts, and the servo rod assembly 10 is connected to the rocker arm servo 11.

[0058] The front rotor subsystem includes a rotor mechanism, a control mechanism and a front main reducer shaft. The rotor mechanism is fixed to the front main reducer shaft through a hub compression nut 7, and the control mechanism is fixed to the servo disc of the rocker servo through bolts.

[0059] The rear rotor subsystem includes a rotor mechanism, a control mechanism and a rear main reducer shaft. The rotor mechanism is fixed to the rear main reducer shaft through a hub compression nut 7, and the control mechanism is fixed to the servo disc of the rocker servo through bolts.

[0060] In another embodiment of the present invention, the operating mechanism includes a rotor rod assembly 8, a swash plate assembly 9 and a servo rod assembly 10. The rocker arm 207 is connected to one end of the rotor rod assembly 8 by a bolt, and the other end of the rotor rod assembly 8 is connected to the movable plate of the swash plate assembly 9 by a bolt. The fixed plate of the swash plate assembly 9 is connected to the linear servo 12.

[0061] The front rotor subsystem includes a rotor mechanism, a control mechanism and a front main reducer shaft. The rotor mechanism is fixed to the front main reducer shaft through a hub compression nut 7, and the control mechanism is fixed to the servo disc of the linear servo by bolts.

[0062] The rear rotor subsystem includes a rotor mechanism, a control mechanism and a rear main reducer shaft. The rotor mechanism is fixed to the rear main reducer shaft through a hub compression nut 7, and the control mechanism is fixed to the servo disc of the linear servo by bolts.

[0063] In some specific embodiments of the present invention, when the rotor rotates, the blade 1 is subjected to centrifugal force, which is transmitted to the propeller clamp 201 through the first main propeller bolt 6, and further transmitted to the thrust bearing 202, the inner shaft sleeve 203, the inner ring of the first cylindrical roller bearing 208, and the end locking nut 212 through the retaining ring 204. Finally, the centrifugal force of the blade 1 is transmitted to the propeller clamp shaft 401 through a threaded connection, and the propeller clamp shaft 401 is transmitted to the hub central part 3 through the connecting bolts.

[0064] When the rotor rotates, the blade 1 is also subjected to a shimmying load. A rubber damping cylinder 213 is installed between the second main propeller bolt 5 and the blade pad 210 to absorb and attenuate the vibration energy.

[0065] When the rotor rotates, in order to achieve controllable flight, the attack angle of blade 1 needs to be controllable, that is, blade 1 needs to rotate around the blade clamp axis 401. Two cylindrical roller bearings are designed. At this time, the cylindrical roller bearings are only subjected to radial force.

[0066] The rocker servo 11 pushes the servo rod assembly 10 to make the swash plate assembly 9 move up and down, that is, the rotor rod assembly 8 moves up and down together, so that the angle of attack of the blade 1 changes, that is, adjusting the collective pitch, changing the lift, and controlling the rise and fall; or the swash plate assembly 9 tilts so that the angle of attack of the blade 1 changes periodically after one rotation, that is, cyclic pitch change, to achieve roll and yaw.

[0067] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the various embodiments of the present invention.

Claims

1. A helicopter rotor system, characterized in that: The rotor mechanism includes a blade, a propeller clamp assembly, a propeller clamp shaft assembly, and a hub center piece. One end of the propeller clamp assembly is connected to the blade through a main propeller bolt, the other end of the propeller clamp assembly is connected to one end of the propeller clamp shaft assembly, the other end of the propeller clamp shaft assembly is connected to the hub center piece, and the hub center piece is connected to multiple propeller clamp shaft assemblies. The main propeller bolt includes a first main propeller bolt and a second main propeller bolt. The first main propeller bolt is arranged near the blade end, and the second main propeller bolt is arranged near the hub center piece end. The second main propeller bolt is detachable to fold the blade.

2. A helicopter rotor system according to claim 1, characterized in that: The propeller clamp assembly includes a propeller clamp and a blade pad. A U-shaped opening is provided at one end of the propeller clamp, and the blade is arranged in the U-shaped opening. A blade pad is provided on the inner wall of the U-shaped opening, and the blade pad is connected to the blade through the first main propeller bolt and the second main propeller bolt.

3. A helicopter rotor system according to claim 2, characterized in that: The propeller clamp assembly further includes a propeller clamp plug cover, a propeller clamp end cover, a first cylindrical roller bearing, an inner shaft spacer, a thrust bearing, an inner shaft sleeve, and a second cylindrical roller bearing; The propeller clamp cover is arranged near the end of the second main propeller bolt, one side of the first cylindrical roller bearing abuts against the propeller clamp cover, the other side of the first cylindrical roller bearing abuts against the inner shaft sleeve, one end of the inner shaft spacer abuts against the inner shaft sleeve, and the other end abuts against the inner ring of the second cylindrical roller bearing, the outer ring of the second cylindrical roller bearing abuts against the propeller clamp end cover, the propeller clamp end cover is installed on the side near the propeller clamp shaft through threads, a thrust bearing is provided on the inner shaft sleeve, and the thrust bearing is positioned by a retaining ring; The propeller clamp plug cover, the propeller clamp end cover, the first cylindrical roller bearing, the inner shaft spacer, the thrust bearing, the inner shaft sleeve and the second cylindrical roller bearing are all installed inside the propeller clamp.

4. A helicopter rotor system according to claim 3, characterized in that: The propeller clamp shaft assembly includes a propeller clamp shaft and a bearing, the inner shaft sleeve is installed on the propeller clamp shaft, the bearing is rotatably connected to the propeller hub central piece, a limiting base is provided at the root of the propeller clamp shaft, and the bearings are installed on both sides of the limiting base.

5. A helicopter rotor system according to claim 4, characterized in that: The hub central piece is provided with a limiting boss, and the limiting base is provided with a limiting groove, and the limiting groove is adaptively connected to the limiting boss.

6. A helicopter rotor system according to claim 2, characterized in that: The propeller clamp assembly further includes a rocker arm, which is mounted on one end of the propeller clamp close to the propeller hub central piece through bolts.

7. A helicopter rotor system according to claim 6, characterized in that: It also includes a control mechanism, which includes a rotor rod assembly, a swash plate assembly and a servo rod assembly. The rocker arm is connected to one end of the rotor rod assembly by a bolt, and the other end of the rotor rod assembly is connected to the movable plate of the swash plate assembly by a bolt. The fixed plate of the swash plate assembly is connected to the servo rod assembly by bolts, and the servo rod assembly is connected to the rocker arm servo.

8. A helicopter rotor system according to claim 7, characterized in that: It includes a front rotor subsystem and a rear rotor subsystem, wherein the front rotor subsystem includes the rotor mechanism, the control mechanism and the front main reducer shaft, the rotor mechanism is fixed to the front main reducer shaft through a hub compression nut, and the control mechanism is fixed to the servo disc of the rocker servo through bolts; The rear rotor subsystem includes a rotor mechanism, a control mechanism and a rear main reducer shaft. The rotor mechanism is fixed to the rear main reducer shaft through a hub compression nut, and the control mechanism is fixed to the servo disc of the rocker servo through bolts.

9. The helicopter rotor system according to claim 6, characterized in that: It also includes a control mechanism, which includes a rotor rod assembly, a swash plate assembly and a servo rod assembly. The rocker arm is connected to one end of the rotor rod assembly by a bolt, and the other end of the rotor rod assembly is connected to the movable plate of the swash plate assembly by a bolt. The fixed plate of the swash plate assembly is connected to the linear servo.

10. A helicopter rotor system according to claim 9, characterized in that: It includes a front rotor subsystem and a rear rotor subsystem, wherein the front rotor subsystem includes the rotor mechanism, the control mechanism and the front main reducer shaft, the rotor mechanism is fixed to the front main reducer shaft via a hub compression nut, and the control mechanism is fixed to the servo disc of the linear servo via bolts; The rear rotor subsystem includes a rotor mechanism, a control mechanism and a rear main reducer shaft. The rotor mechanism is fixed to the rear main reducer shaft through a hub compression nut, and the control mechanism is fixed to the servo disc of the linear servo through bolts.

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