Helicopter propeller hub, rotor wing system and helicopter

Abstract

The invention discloses a propeller hub for a helicopter, a rotor system and the helicopter, and relates to the technical field of aircrafts, the propeller hub comprises a variable pitch hinge mounting seat, an inner propeller hub center body, an elastic device and at least three force transmission devices, and the inner propeller hub center body is arranged in an inner cavity of the variable pitch hinge mounting seat; the elastic device is connected with the inner propeller hub center body and the variable pitch hinge mounting seat; each force transmission device is movably connected with the inner propeller hub center body, each force transmission device is connected with the inner side wall of the variable-pitch hinge mounting seat, and the variable-pitch hinge mounting seat can rotate relative to the force transmission devices so as to generate tilting rotation relative to the radial plane of the rotor shaft; when the rotor shaft rotates, the rotor shaft can drive the inner propeller hub center body, the force transmission devices and the pitch-variable hinge mounting base to rotate. And when the variable-pitch hinge mounting seat tilts relative to the radial plane of the rotor shaft, the elastic device can be compressed or stretched, and the variable-pitch hinge mounting seat can be reset under the action of restoring force of the elastic device. Flight flexibility and stability can be ensured, and the flight quality of the helicopter is effectively improved.

Description

Technical Field

[0001] This invention relates to the field of aircraft technology, and in particular to a rotor blade, rotor system and helicopter. Background Technology

[0002] Helicopters are capable of vertical takeoff and landing, hovering, and flying in any direction, possessing excellent hovering capabilities and maneuverability, making them widely used in various fields such as military, civilian, and emergency rescue. Among them, tiltrotor aircraft, as a type of aircraft that combines the characteristics of fixed-wing aircraft and helicopters, rely on their rotor system as the core for mode switching: the rotor's pitch control is executed via a variable pitch hinge, which precisely transmits control commands from the automatic swashplate to each blade; the automatic swashplate, as the core control mechanism, through the coordinated action of its stationary and moving rings, converts the pilot's collective pitch and cyclic pitch control inputs into synchronous blade deflection, thereby controlling the aircraft's lift and attitude. Traditional helicopters' fully articulated rotor hubs or star-shaped flexible rotor hubs, due to their complex structure, large weight, and high drag, cannot meet the urgent requirements of rotor systems for compactness, lightweight design, and high transonic performance. Meanwhile, the fully articulated rotor hub, using flapping and tessellation hinges as mechanical joints, inevitably has minute manufacturing and wear gaps, making it prone to instability phenomena such as "ground resonance" and "air resonance." The alternating loads of the fully articulated rotor hub are transmitted through these mechanical joints, leading to high stress concentration in these areas. During drastic changes in flight conditions, the hinge gaps and nonlinearities of the fully articulated rotor hub can cause abrupt or hysteretic changes in the dynamic response of the rotor system, easily inducing oscillations. The rotor system still faces ongoing challenges in vibration control, load optimization, and mode transition smoothness, requiring further innovation and optimization. Summary of the Invention

[0003] The purpose of this invention is to provide a rotor, rotor system and helicopter for helicopters to solve the problems existing in the prior art, and to ensure flight flexibility and stability, and effectively improve the flight quality of helicopters.

[0004] To achieve the above objectives, the present invention provides the following solution: This invention provides a helicopter rotor, comprising a pitch hinge mounting base, an inner rotor center body, an elastic device, and at least three force transmission devices, wherein: The variable pitch hinge mounting base is used to connect to the variable pitch hinge assembly; The inner rotor center body is disposed within the inner cavity of the variable pitch hinge mounting base; the inner rotor center body is used to connect with the rotor shaft; The elastic device is connected to both the inner paddle center body and the variable pitch hinge mounting base; One end of each of the force transmission devices is movably connected to the inner rotor center body, and the other end of each of the force transmission devices is movably connected to the inner sidewall of the variable pitch hinge mounting base. The variable pitch hinge mounting base can rotate relative to the force transmission device under the action of an external force, so that the variable pitch hinge mounting base tilts relative to the radial plane of the rotor shaft. When the rotor shaft rotates, it can drive the inner rotor center body, each of the force transmission devices, and the variable pitch hinge mounting base to rotate. When the variable pitch hinge mounting base tilts relative to the radial plane of the rotor shaft, it can compress or stretch the elastic device. The variable pitch hinge mounting base can be reset under the restoring force of the elastic device.

[0005] In one embodiment, the variable pitch hinge mounting base includes an outer paddle center body and at least two paddle arms connected to the outer paddle center body, each paddle arm being connected to one of the variable pitch hinge assemblies; the inner paddle center body is disposed within the inner cavity of the outer paddle center body; a plurality of grooves are provided on the inner sidewall of the outer paddle center body, and one end of each force transmission device away from the inner paddle center body is disposed within one of the grooves, and the end of each force transmission device away from the inner paddle center body can be slidably connected and / or rolledly connected with the inner sidewall of the corresponding groove.

[0006] In one embodiment, each of the force transmission devices includes a journal and a bearing assembly. One end of each journal is fixedly connected to the inner paddle center body, and the other end of each journal is connected to the corresponding bearing assembly. The outer side wall of each bearing assembly is in rolling connection with the inner side wall of the corresponding groove. The end face of each bearing assembly away from the inner paddle center body can contact the inner bottom wall of the groove and generate relative sliding.

[0007] In one embodiment, each of the grooves extends along a direction parallel to the centerline of the inner paddle core, and the two inner sidewalls of each groove are partially spherical, with the middle portion of each of the two inner sidewalls recessed away from the bearing assembly.

[0008] In one embodiment, the variable pitch hinge mounting base further includes two cover plates, which are respectively fixedly connected to both ends of the outer paddle center body; the elastic device includes multiple elastic components, and at least one elastic component is provided between each cover plate and the inner paddle center body.

[0009] The present invention also provides a rotor system, including a pitch hinge assembly, an automatic swashplate, a rotor shaft, blades, and a helicopter rotor. There are at least two pitch hinge assemblies and one-to-one corresponding blades. Each pitch hinge assembly is connected to a pitch hinge mounting base, each blade is connected to one pitch hinge assembly, each pitch hinge assembly is connected to the automatic swashplate, each automatic swashplate is connected to the rotor shaft, and the inner rotor center body is connected to the rotor shaft.

[0010] In one embodiment, each of the pitch hinge assemblies includes a pitch hinge housing and a bearing assembly 2, and each of the pitch hinge housings is rotatably connected to a paddle arm of the pitch hinge mounting base via the corresponding bearing assembly 2.

[0011] In one embodiment, the automatic swashplate includes a moving ring, a stationary ring, a spherical support, a ball-holding cover plate, and at least two tie rods. The moving ring is connected to the rotor shaft and can rotate with the rotor shaft. One end of each tie rod is movably connected to the moving ring, and the other end of each tie rod is movably connected to the pitch-changing hinge assembly. The stationary ring is located at the end of the moving ring away from the pitch-changing hinge assembly and is rotatably connected to the moving ring. A ball-holding cover plate is fixedly connected to each of the upper and lower ends of the moving ring, and the inner sidewall of the ball-holding cover plate matches and contacts the spherical outer wall of the spherical support.

[0012] In one embodiment, the automatic tilter further includes an anti-torsion arm and a clamp. The anti-torsion arm includes a connecting arm one and a connecting arm two. The moving ring, the connecting arm one, the connecting arm two, and the clamp are hinged in sequence. The clamp is detachably fixedly connected to the rotor shaft.

[0013] The present invention also provides a helicopter equipped with the aforementioned helicopter rotor.

[0014] The present invention achieves the following technical effects compared to the prior art: This invention provides a helicopter rotor, rotor system, and helicopter, including a variable pitch hinge mount, an inner rotor center body, an elastic device, and at least three force transmission devices. The inner rotor center body is disposed within the inner cavity of the variable pitch hinge mount. The elastic device is connected to both the inner rotor center body and the variable pitch hinge mount. One end of each force transmission device is movably connected to the inner rotor center body, and the other end of each force transmission device is movably connected to the inner sidewall of the variable pitch hinge mount. The variable pitch hinge mount can rotate relative to the force transmission devices under the action of an external force, causing the variable pitch hinge mount to tilt relative to the radial plane of the rotor shaft. When the rotor shaft rotates, it can drive the inner rotor center body, each force transmission device, and the variable pitch hinge mount to rotate. When the variable pitch hinge mount tilts relative to the radial plane of the rotor shaft, it can compress or stretch the elastic device, and the variable pitch hinge mount can reset under the restoring force of the elastic device.

[0015] The rotor shaft drives the power transmission device to rotate around the rotor shaft axis via the inner rotor hub. This power transmission device then drives the pitch hinge mount to rotate, which in turn drives the blades to rotate around the rotor shaft axis via the pitch hinge assembly, generating lift. When the blades perform periodic pitch changes, the blades, through the pitch hinge assembly, cause the pitch hinge mount to tilt relative to the inner rotor hub. The alternating torque and centrifugal force of all blades are self-balanced at the rotor hub center, effectively preventing the transmission of alternating torque to the rotor shaft. This significantly reduces the generation of adverse vibrations, providing strong protection for flight safety and effectively improving the helicopter's flight characteristics. An elastic device is used to reset the pitch hinge mount, ensuring accurate control of the rotor hub and guaranteeing flight flexibility and stability. Without this elastic device, the helicopter would lose accurate control of the rotor hub during maneuvers, posing a risk of loss of control. Attached Figure Description

[0016] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0017] Figure 1 This is a schematic diagram of the rotor system provided in Example 2; Figure 2 This is a schematic diagram of the structure of the helicopter rotor provided in Example 1; Figure 3 A cross-sectional view of the variable pitch hinge assembly provided in Embodiment 2; Figure 4 A schematic diagram of the structure of the automatic tilter provided in Embodiment 2; Figure 5 A cross-sectional view of the helicopter rotor provided in Example 1; Figure 6 This is a partial structural schematic diagram of the rotor system provided in Example 1; In the diagram: 1. Helicopter rotor; 11. Outer rotor center body; 12. Inner rotor center body; 13. Bearing assembly one; 14. Elastic component; 15. Support component; 16. Cover plate; 111. Rotor arm; 112. Groove; 121. Journal; 2. Pitch-changing hinge assembly; 21. Pitch-changing rocker arm; 22. Bearing assembly two; 23. Pitch-changing nut; 24. Locking plate; 25. Pitch-changing hinge housing; 26. Locking nut; 3. Automatic tilter; 31. Tie rod; 32. Moving ring; 33. Stationary ring; 34. Clamp; 35. Anti-torsion arm; 36. Spherical support; 37. Ball-holding cover plate; 4. Rotor shaft; 5. Blades. Detailed Implementation

[0018] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0019] It should be noted that in the description of this invention, the terms "upper," "lower," "left," "right," "inner," "outer," "front," "rear," "center," "longitudinal," "transverse," "length," "width," "thickness," "vertical," "horizontal," "top," "bottom," "clockwise," and "counterclockwise," etc., indicating directional or positional relationships, are based on the directional or positional relationships shown in the accompanying drawings. These are merely for ease of description and do not indicate or imply that the device or element must have a specific orientation, or be constructed and operated in a specific orientation; therefore, they should not be construed as limitations on this invention. Furthermore, the terms "first," "second," "third," and "fourth" are used for descriptive purposes only and should not be construed as indicating or implying relative importance. Additionally, it should be noted that in the description of this invention, unless otherwise explicitly specified and limited, the terms "set," "connected," and "linked" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; a mechanical connection or an electrical connection; a direct connection or an indirect connection through an intermediate medium; or a connection within two elements. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0020] The purpose of this invention is to provide a rotor, rotor system and helicopter for helicopters to solve the problems existing in the prior art, and to ensure flight flexibility and stability, and effectively improve the flight quality of helicopters.

[0021] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0022] Example 1 like Figures 1-6 As shown, this embodiment provides a helicopter rotor 1, including a variable pitch hinge mounting base, an inner rotor center body 12, an elastic device, and at least three force transmission devices, wherein: The pitch hinge mounting base is used to connect to the pitch hinge assembly 2; The inner rotor center body 12 is located inside the cavity of the variable pitch hinge mounting base; the inner rotor center body 12 is used to connect with the rotor shaft 4; The elastic device is connected to both the inner paddle center body 12 and the pitch hinge mounting base; One end of each force transmission device is movably connected to the inner rotor center body 12, and the other end of each force transmission device is movably connected to the inner side wall of the pitch hinge mounting base. The pitch hinge mounting base can rotate relative to the force transmission device under the action of external force, so that the pitch hinge mounting base tilts relative to the radial plane of the rotor shaft 4. When the rotor shaft 4 rotates, it can drive the inner rotor center body 12, each force transmission device and the pitch hinge mounting base to rotate. When the pitch hinge mounting base tilts relative to the radial plane of the rotor shaft 4, it can compress or stretch the elastic device. The pitch hinge mounting base can be reset under the restoring force of the elastic device.

[0023] The rotor shaft 4 drives the power transmission device to rotate around the axis of the rotor shaft 4 via the inner rotor hub 12. The power transmission device drives the pitch hinge mount to rotate, and the pitch hinge mount drives the blades 5 to rotate around the axis of the rotor shaft 4 via the pitch hinge assembly 2, generating lift. When the blades 5 perform periodic pitch changes, the blades 5 drive the pitch hinge mount to tilt relative to the inner rotor hub 12 via the pitch hinge assembly 2, causing the alternating torque and centrifugal force of all blades 5 to self-balance at the center of the rotor hub. This effectively prevents the transmission of alternating torque to the rotor shaft 4, thereby greatly reducing the generation of adverse vibrations and providing strong protection for flight safety, effectively improving the flight quality of the helicopter. The elastic device is used to reset the pitch hinge mount, ensuring accurate control of the rotor hub and ensuring flight flexibility and stability. Without the elastic device, the helicopter would lose accurate control of the rotor hub during maneuvers, posing a risk of loss of control.

[0024] In one embodiment, the variable pitch hinge mounting base includes an outer paddle center body 11 and at least two paddle arms 111 fixedly connected to the outer paddle center body 11. Each paddle arm 111 is used to connect to a variable pitch hinge assembly 2. An inner paddle center body 12 is disposed in the inner cavity of the outer paddle center body 11. A plurality of grooves 112 are provided on the inner sidewall of the outer paddle center body 11. One end of each force transmission device away from the inner paddle center body 12 is disposed in a groove 112. The end of each force transmission device away from the inner paddle center body 12 can be slidably connected and / or rolledly connected with the inner sidewall of the corresponding groove 112.

[0025] In one embodiment, each groove 112 extends in a direction parallel to the centerline of the inner paddle center body 12, and the two inner sidewalls of each groove 112 are partially spherical, with the middle of the two inner sidewalls of each groove 112 recessed in a direction away from the bearing assembly 13.

[0026] In one embodiment, a plurality of rotor arms 111 are evenly distributed along the circumference of the inner rotor center body 12 on the outer side wall of the outer rotor center body 11, which is annular. The rotor shaft 4 is connected to the inner rotor center body 12 via splines to transmit torque to the rotor hub.

[0027] In one embodiment, each force transmission device includes a journal 121 and a bearing assembly 13. One end of each journal 121 is fixedly connected to the inner paddle center body 12, and the other end of each journal 121 is fixedly connected to the corresponding bearing assembly 13. The outer side wall of each bearing assembly 13 is in rolling connection with the inner side wall of the corresponding groove 112. The end face of each bearing assembly 13 away from the inner paddle center body 12 can contact the inner bottom wall of the groove 112 and generate relative sliding.

[0028] In one embodiment, the variable pitch hinge mounting base further includes two cover plates 16, which are fixedly connected to both ends of the outer paddle center body 11 respectively; the elastic device includes a plurality of elastic components 14, and at least one elastic component 14 is provided between each cover plate 16 and the inner paddle center body 12.

[0029] In one embodiment, a support member 15 is also included. Both the support member 15 and the elastic member 14 are conical or substantially conical. The large end face of each elastic member 14 is fixedly connected to each cover plate 16. The small end face of the elastic member 14 and the large end face of the support member 15 are vulcanized and integrally formed. The small end of the support member 15 is fixedly connected to the inner core body 12.

[0030] In one embodiment, there are three force transmission devices, three grooves 112, and three propeller arms 111. The three force transmission devices are arranged at equal intervals along the circumference of the inner propeller center body 12, the three grooves 112 are arranged at equal intervals along the inner ring of the outer propeller center body 11, and the three propeller arms 111 are arranged at equal intervals along the outer ring of the outer propeller center body 11. Since the force transmission devices are distributed at 120°, it is ensured that at least two force transmission devices transmit force simultaneously when the propeller blade 5 rotates, reducing the impact and vibration during the torque transmission process.

[0031] In one embodiment, the cover plate 16 is bolted to the outer rotor hub center body 11. The elastic component 14 is a rubber elastic component. The bearing assembly 13 is a ball bearing with a cylindrical inner ring that is fixedly connected to the journal 121 of the rotor hub center body 12. The inner ring contains several balls and a cage, while the outer ring is arc-shaped and can make line contact with the side of the groove 112 for rolling. The bearing assembly 13 ensures precise transmission of the main shaft torque and also ensures coordination and synchronization between various moving parts, improving the overall performance of the rotor system.

[0032] Example 2 This embodiment provides a rotor system, including a pitch hinge assembly 2, an automatic swashplate 3, a rotor shaft 4, blades 5, and a helicopter rotor 1 as described in Embodiment 1. There are at least two pitch hinge assemblies 2 and blades 5, and they correspond one-to-one. Each pitch hinge assembly 2 is connected to a pitch hinge mounting base, each blade 5 is connected to one pitch hinge assembly 2, each pitch hinge assembly 2 is connected to an automatic swashplate 3, each automatic swashplate 3 is connected to the rotor shaft 4, and the inner rotor center body 12 is connected to the rotor shaft 4.

[0033] In one embodiment, each pitch hinge assembly 2 includes a pitch hinge housing 25 and a bearing assembly 22. Each pitch hinge housing 25 is rotatably connected to a paddle arm 111 of the pitch hinge mounting base via a corresponding bearing assembly 22.

[0034] In one embodiment, the automatic swashplate 3 includes a moving ring 32, a stationary ring 33, a spherical support 36, a ball-holding cover 37, and at least two tie rods 31. The moving ring 32 is connected to the rotor shaft 4 and can rotate with the rotor shaft 4. One end of each tie rod 31 is movably connected to the moving ring 32, preferably hinged. The other end of each tie rod 31 is movably connected to the pitch-changing hinge assembly 2, preferably hinged. The stationary ring 33 is located at the end of the moving ring 32 away from the pitch-changing hinge assembly 2, and is rotatably connected to the moving ring 32. A ball-holding cover 37 is fixedly connected to each of the upper and lower ends of the moving ring 32. The inner sidewall of the ball-holding cover 37 matches and contacts the spherical outer wall of the spherical support 36. The moving ring 32 and the stationary ring 33 are preferably rotatably connected by bearings, and the moving ring 32 and the stationary ring 33 can rotate relative to each other. The moving ring 32 can rotate with the rotor shaft 4. The stationary ring 33 can change its height and tilt (tilt relative to the radial plane of the rotor shaft 4) under the action of the collective pitch control stick. The spherical support 36 and the ball cover plate 37 are in spherical fit, which can limit the relative tilt between the moving ring 32 and the stationary ring 33, thereby changing the tilt state of the moving ring 32. The tie rod 31 connected to the moving ring 32 will be periodically pushed up and pulled down on this inclined plane as the moving ring 32 rotates (one cycle is completed for each revolution), thereby enabling the blade 5 to perform periodic pitch changes, such as longitudinal and lateral periodic pitch changes, to perform various attitude movements.

[0035] In one embodiment, the spherical support 36 is coaxially fitted and slidably connected to the rotor shaft 4. Its up-and-down movement can change the moving ring 32, the tie rod 31, and the pitch-changing hinge assembly 2, thereby enabling the blade 5 to achieve the function of collective pitch change.

[0036] In one embodiment, each pitch hinge assembly 2 further includes a pitch rocker arm 21 connected to the pitch hinge housing 25, and the pitch rocker arm 21 is hinged to the corresponding pull rod 31.

[0037] In one embodiment, bearing assembly 22 includes two deep groove ball bearings.

[0038] In one embodiment, each pitch hinge assembly 2 further includes a pitch nut 23, a locking plate 24, and a locking nut 26. Both ends of the deep groove ball bearing are provided with shoulders. The side of the bearing assembly 22 furthest from the outer propeller center body 11 is locked by the locking nut 26 (specifically, the locking nut 26 is threaded to the propeller arm 111). The deep groove ball bearing is limited along its axial direction by the shoulders and the locking nut 26. After the pitch hinge housing 25 is fitted onto the root of the propeller arm 111, the pitch nut 23 is tightened onto the end of the pitch hinge housing 25 near the root of the propeller arm 111, thus fixing the pitch hinge housing 25 to the root of the propeller arm 111. The locking plate 24 is disposed between the pitch hinge housing 25 and the pitch nut 23 to prevent relative rotation between the pitch hinge housing 25 and the pitch nut 23 after installation. Two deep groove ball bearings are mounted on the blade arm 111 of the outer blade center body 11, capable of simultaneously bearing radial and axial loads. Specifically, the centrifugal force generated by the blade 5 is transmitted to the pitch hinge housing 25, and then from the pitch hinge housing 25 through the pitch nut 23 and the deep groove ball bearings between the pitch nut 23 and the locking nut 26 to the locking nut 26. From the locking nut 26, the force is transmitted to the blade arm 111 of the outer blade center body 11, and then to the blade hub center. The centrifugal force of the three blades 5 is balanced at the blade hub center. The two deep groove ball bearings through which the blades 5 pass transmit the flapping / swaying force and torque from the pitch hinge housing 25 to the blade arm 111, and the bending moment of the three blades 5 is balanced on the outer blade center body 11.

[0039] In one embodiment, the variable pitch hinge housing 25 is connected to the blade 5 by a locking bolt, thereby realizing the variable pitch movement of the blade 5.

[0040] In one embodiment, the automatic swashplate 3 further includes an anti-torsion arm 35 and a clamp 34. The anti-torsion arm 35 includes a first connecting arm and a second connecting arm. The moving ring 32, the first connecting arm, the second connecting arm, and the clamp 34 are sequentially hinged together. The clamp 34 is detachably fixed to the rotor shaft 4. The moving ring 32 is fixed to the rotor shaft 4 by the anti-torsion arm 35 and the clamp 34, preventing it from rotating relative to the rotor shaft 4.

[0041] In one embodiment, the rotor shaft 4 is provided with two shoulders for restricting the axial movement of the clamp 34 along the rotor shaft 4. Specifically, the two shoulders are respectively provided at both ends of the clamp 34.

[0042] The helicopter rotor 1 of this embodiment is simpler than traditional structures, enabling flapping and oscillating functions. It reduces the need for traditional flapping and oscillating hinge structures, resulting in a compact structure and a smaller rotor hub size. The bearing assembly 13 is radially arranged along the inner rotor center body, preferably at a 120° angle. Its lever arm acting on the inner raceway is the distance from the rotor hub center to the contact point with the inner raceway, resulting in a large effective lever arm length and high torque transmission. The bearing assembly 13 is made of high-strength alloy steel and heat-treated, possessing high hardness and wear resistance, capable of withstanding the enormous bending and shearing forces brought about by high torque. The inner rotor center body 12 allows for a large operating angle (typically up to 25°), exhibiting excellent deflection capability. This embodiment is suitable for use on small tiltrotor aircraft.

[0043] Example 3 This embodiment provides a helicopter equipped with the helicopter rotor 1 as described in Embodiment 1.

[0044] In one embodiment, the helicopter includes a fuselage and the rotor system of Example 2.

[0045] In one embodiment, the helicopter is a tiltrotor aircraft.

[0046] Specific examples have been used to illustrate the principles and implementation methods of this invention. The descriptions of the above embodiments are only for the purpose of helping to understand the method and core ideas of this invention. Furthermore, those skilled in the art will recognize that, based on the ideas of this invention, there will be changes in the specific implementation methods and application scope. Therefore, the content of this specification should not be construed as a limitation of this invention.

Claims

1. A rotor blade for a helicopter, characterized by: The variable-pitch hinge mounting base is used for connecting with a variable-pitch hinge assembly. The inner mast hub center body is arranged in the inner cavity of the variable-pitch hinge mounting base. The elastic device is connected with the inner mast hub center body and the variable-pitch hinge mounting base. One end of each of the force transmission devices is movably connected with the inner mast hub center body, and the other end of each of the force transmission devices is movably connected with the inner side wall of the variable-pitch hinge mounting base. The variable-pitch hinge mounting base comprises an outer mast hub center body and at least two mast arm connected to the outer mast hub center body.

2. A hub for a helicopter according to claim 1, characterized in that: Each of the mast arm is used for connecting with one of the variable-pitch hinge assembly.

3. A hub for a helicopter according to claim 2, characterized in that: The inner side wall of the outer mast hub center body is provided with a plurality of grooves.

4. A hub for a helicopter according to claim 3, characterized in that: Each of the force transmission devices is movably connected with the inner side wall of the corresponding groove and / or rollingly connected with the inner side wall of the corresponding groove.

5. The helicopter blade of claim 2, wherein: Each of the force transmission devices comprises a journal and a bearing assembly.

6. A rotor system characterized by: Each of the journal is fixedly connected with the inner mast hub center body at one end and connected with the corresponding bearing assembly at the other end. Each of the bearing assembly is rollingly connected with the inner side wall of the corresponding groove. Each of the groove extends along a direction parallel to the center line of the inner mast hub center body. Each of the groove has two inner side walls which are partially spherical. The variable-pitch hinge mounting base further comprises two cover plates. Each of the cover plate is fixedly connected with the two ends of the outer mast hub center body. The elastic device comprises a plurality of elastic components. The variable-pitch hinge assembly and the paddle are at least two and one-to-one corresponding. Each of the variable-pitch hinge assembly is connected with the variable-pitch hinge mounting base. Each of the paddle is connected with one of the variable-pitch hinge assembly. Each of the variable-pitch hinge assembly is connected with the automatic tilt. Each of the automatic tilt is connected with the rotor shaft. The inner mast hub center body is connected with the rotor shaft.

7. The rotor system of claim 6, wherein: Each of the variable-pitch hinge assemblies comprises two variable-pitch hinge housings and two bearing assemblies, and each of the variable-pitch hinge housings is rotatably connected to one of the paddle arms of the variable-pitch hinge mounting base through the corresponding bearing assembly.

8. The rotor system of claim 6, wherein: The automatic tilting device comprises a movable ring, a fixed ring, a spherical support, a ball holding cover plate and at least two pull rods, the movable ring is connected with the rotor shaft and can rotate with the rotor shaft, one end of each of the pull rods is movably connected with the movable ring, the other end of each of the pull rods is movably connected with the variable-pitch hinge assembly, the fixed ring is arranged at the end of the movable ring away from the variable-pitch hinge assembly, the fixed ring is rotatably connected with the movable ring, the upper and lower ends of the movable ring are each fixedly connected with one of the ball holding cover plates, and the inner side wall of the ball holding cover plate is matched with and contacts the spherical outer wall of the spherical support.

9. The rotor system of claim 8, wherein: The automatic tilting device further comprises an anti-twist arm and a clamp, the anti-twist arm comprises a first connecting arm and a second connecting arm, the movable ring, the first connecting arm, the second connecting arm and the clamp are sequentially hinged, and the clamp is detachably fixedly connected with the rotor shaft.

10. A helicopter characterized by: The helicopter is provided with the paddle of any one of claims 1-5. Each of the variable-pitch hinge assemblies comprises two variable-pitch hinge housings and two bearing assemblies, and each of the variable-pitch hinge housings is rotatably connected to one of the paddle arms of the variable-pitch hinge mounting base through the corresponding bearing assembly.

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