Rotor device and aircraft

Abstract

This invention discloses a rotor device and an aircraft. The rotor device includes a hub assembly, a rotor shaft assembly, and a flapping hinge assembly. The hub assembly includes a hub body and two blades, which are respectively mounted at both ends along the axial direction of the hub body and have a fixed distance between them. A through hole in the radial direction is formed in the middle of the hub body. The rotor shaft assembly includes a main shaft and a shaft fixing member. The main shaft passes through the through hole, and the shaft fixing member covers the end of the main shaft that extends out of the through hole. The flapping hinge assembly includes a flapping shaft and a locking member. The flapping shaft passes sequentially through the hub body, the shaft fixing member, and the main shaft along an axial direction perpendicular to the rotor main shaft and is locked to the locking member, so that the hub body can flap and swing relative to the main shaft. The rotor device of this invention has a simple structure, is easy to assemble, and has low cost.

Description

Technical Field

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

[0002] Most existing small multi-rotor aircraft use a rigid hub connection method because they are small in size, light in weight and have low aerodynamic load. That is, the blades and motors are directly fixed to each other by bolts. However, this connection method is not suitable for medium and large aircraft. The vibration and fatigue generated during the flight of medium and large manned aircraft have high strength requirements for blades, hubs and even motors, which can easily cause fatigue damage at the blade root and shorten the blade service life.

[0003] The seesaw rotor, with its hinged blades and main shaft, can exhibit periodic flapping during flight, unloading most of the bending moment and reducing fatigue and vibration of the blades, hub, and electrodes, thus making it suitable for medium and large-sized aircraft. However, existing seesaw rotors are problematic because medium and large-sized aircraft are large, structurally complex, and have higher flight requirements. This necessitates adjustments to the rotor's angle and spacing, resulting in a complex installation structure, high cost, and inconvenient assembly. Summary of the Invention

[0004] The main objective of this invention is to propose a rotor device that provides a rotor structure for medium and large-sized aircraft that is simple in structure, easy to assemble, and can reduce fatigue during flapping.

[0005] To achieve the above objectives, the rotor device proposed in this invention includes:

[0006] A propeller hub assembly, comprising a propeller hub body and two propeller blades, the two propeller blades being respectively mounted at both ends of the propeller hub body along the axial direction and having a fixed spacing, and a through hole in the radial direction being provided in the middle of the propeller hub body.

[0007] A rotor shaft assembly, comprising a main shaft and a shaft retainer, wherein the main shaft passes through the through hole, and the shaft retainer covers the end of the main shaft extending out of the through hole; and

[0008] A flapping hinge assembly includes a flapping shaft and a locking fastener. The flapping shaft is sequentially inserted through the rotor hub body, the shaft fixing member, and the main shaft along an axis perpendicular to the rotor main shaft, and is locked to the locking fastener so that the rotor hub body can flap and swing relative to the main shaft.

[0009] Optionally, the rotor hub body has two opposing connecting ears protruding from the opening edge of the through hole, each connecting ear having a first hinge hole, the end of the main shaft having a second hinge hole, the shaft fixing member having a fixing groove, and a third hinge hole being formed on the opposite side walls of the fixing groove, the groove wall of the fixing groove being fitted to the outer peripheral wall of the main shaft, the outer peripheral side of the shaft fixing member abutting against the connecting ears, and the swing shaft gap passing through the first hinge hole, the third hinge hole, and the second hinge hole.

[0010] Optionally, the propeller hub assembly further includes two bushings, one end of each bushing passing through a first hinge hole, and the other end being clamped between the shaft fixing member and the connecting lug, with the swing shaft clearance passing through the bushing;

[0011] And / or, the waving hinge assembly further includes a sleeve, the sleeve being fitted with the waving shaft with a gap, and having an interference fit with the hole walls of the two second hinge holes and the hole wall of the third hinge hole.

[0012] Optionally, the waving shaft is a bolt, and the locking fastener is a slotted nut;

[0013] The swing hinge assembly also includes a stop member. The bolt has a stop hole at its tail end. The stop member passes through the stop hole and abuts against the slotted nut.

[0014] And / or, a washer is provided between the fixed end of the bolt and the connecting lug, and a washer is provided between the slotted nut and the other connecting lug.

[0015] Optionally, the main shaft is cylindrical, the outer periphery of the shaft fixing member is cubic, and the opening shape of the fixing groove is at least partially arc-shaped;

[0016] And / or, the outer side of the main shaft is provided with two opposing abutment grooves, the second hinge hole penetrates the bottom of the two abutment grooves, the bottom of the abutment groove is a plane, and it fits against the inner wall of the shaft fixing member.

[0017] Optionally, the rotor device further includes a buffer sleeve, which is sleeved on the main shaft. One end of the buffer sleeve abuts against the end face of the shaft fixing member, and the other end abuts against a retaining ring at the end of the main shaft away from the shaft fixing member.

[0018] And / or, the end face of the shaft fixing member opposite to the main shaft has a lifting part.

[0019] Optionally, the propeller hub body includes a detachably connected upper propeller hub and a lower propeller hub. The upper propeller hub and the lower propeller hub enclose and form two oppositely arranged mounting grooves. One end of each propeller blade is installed in one of the mounting grooves. The upper propeller hub has a first through hole, and the lower propeller hub has a second through hole. The first through hole and the second through hole together form the through hole. The upper propeller hub and the lower propeller hub are connected to press and fix the two propeller blades in the mounting grooves.

[0020] Optionally, the upper rotor hub has a plurality of spaced first connecting holes, and the lower rotor hub has a plurality of spaced second connecting holes. A connector is sequentially inserted through the second connecting hole and the first connecting hole to thread the upper rotor hub and the lower rotor hub.

[0021] And / or, the propeller hub assembly further includes a positioning pin, the upper propeller hub and the lower propeller hub are respectively provided with positioning holes, the positioning holes of the upper propeller hub and the positioning holes of the lower propeller hub are respectively provided, and the two ends of the positioning pin are respectively inserted into the two positioning holes to position the upper propeller hub and the lower propeller hub.

[0022] Optionally, the wall of the mounting groove is formed with a first stepped surface facing the bottom of the mounting groove, and one end of each blade is provided with a mounting portion. A second stepped surface is formed between the mounting portion and the end of the blade, and the first stepped surface abuts against the second stepped surface.

[0023] The present invention also proposes an aircraft comprising a fuselage and a rotor assembly as described above, connected to the fuselage.

[0024] The rotor device of this invention includes a rotor hub assembly, a rotor shaft assembly, and a flapping hinge assembly. Two blades are directly mounted and fixed to the rotor hub body to form a fixed pitch structure, eliminating the need for additional structures to adjust the pitch. This simple structure effectively reduces the overall weight. Furthermore, the rotor shaft assembly includes a main shaft and a shaft fixing component. The shaft fixing component covers the end of the main shaft. The flapping hinge passes through the rotor hub body and then through the shaft fixing component to the main shaft. This not only achieves radial and axial positioning and force transmission of the rotor hub assembly but also allows the rotor hub assembly to flap and swing relative to the main shaft around the flapping hinge axis. This unloads most of the bending moment, reducing fatigue and vibration of the blades and rotor hub body, and improving the service life of the rotor device. This structure uses only a shaft fixing component and a flapping shaft to achieve the hinge connection between the main shaft and the propeller hub body. The structure is simple. When the main shaft rotates, it transmits torque and tension through the shaft fixing component, so that the propeller hub assembly can rotate stably. It can also simplify the machining process of the outer peripheral surface of the main shaft, such as spline structure, thus simplifying the through hole structure of the propeller hub body. It has low manufacturing cost, is easy to maintain, and effectively saves costs. Attached Figure Description

[0025] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art 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 the structures shown in these drawings without creative effort.

[0026] Figure 1 This is a schematic diagram of the structure of an embodiment of the rotor device of the present invention;

[0027] Figure 2 for Figure 1 The front view of the rotor assembly shown;

[0028] Figure 3 for Figure 1 Exploded view of the rotor assembly shown;

[0029] Figure 4 for Figure 1 A cross-sectional view of the rotor assembly shown;

[0030] Figure 5 for Figure 4 Enlarged view of point A in the middle;

[0031] Figure 6 for Figure 1 Exploded view of the rotor hub assembly in the rotor device;

[0032] Figure 7 for Figure 1 A cross-sectional view of the rotor assembly from another perspective;

[0033] Figure 8 for Figure 7 Enlarged view of point B in the middle.

[0034] Explanation of icon numbers:

[0035] label name label name 100 Rotor unit 20 Rotor shaft assembly 10 propeller hub assembly 21 spindle 11 propeller hub body 211 Second hinge hole 111 Through hole 212 abutment groove 112 Connecting Ear 22 Shaft fixing component 1121 First hinge hole 221 Fixed groove 113 Upper propeller hub 222 Third hinge hole 1131 First connecting hole 223 hoisting department 114 Lower rotor hub 30 Waving hinge assembly 1141 Second connecting hole 31 Swing axis 1142 positioning holes 311 Stop hole 115 Mounting slot 32 Locking firmware 116 First step surface 33 sleeve 12 paddle blades 34 Stopping parts 121 Installation Department 35 gasket 122 Second step surface 40 Buffer sleeve 13 bushing 600 motor body 14 Positioning pin

[0036] The realization of the objective, functional features and advantages of the present invention will be further explained in conjunction with the embodiments and with reference to the accompanying drawings. Detailed Implementation

[0037] 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 a part of the embodiments of the present invention, and not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of the present invention.

[0038] It should be noted that if the embodiments of the present invention involve directional indicators (such as up, down, left, right, front, back, etc.), the directional indicators are only used to explain the relative positional relationship and movement of the components in a certain specific posture (as shown in the figure). If the specific posture changes, the directional indicators will also change accordingly.

[0039] Furthermore, if the embodiments of this invention involve descriptions such as "first" or "second," these descriptions are for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Therefore, a feature defined with "first" or "second" may explicitly or implicitly include at least one of those features. Additionally, the technical solutions of the various embodiments can be combined with each other, but this must be based on the ability of those skilled in the art to implement them. If the combination of technical solutions is contradictory or impossible to implement, it should be considered that such a combination of technical solutions does not exist and is not within the scope of protection claimed by this invention.

[0040] Because existing small aircraft have a rigid, fixed connection between the rotor hub and the main shaft, the ends of the hub and blades are prone to fatigue damage. In existing unmanned aerial vehicles (UAVs) with seesaw-type rotor structures, the small shaft size means that directly opening holes would significantly reduce strength. Therefore, the rotor shaft often incorporates a spline structure to achieve torque transmission with the hub. However, this structure requires high precision machining of both the outer spline structure and the mating inner spline, leading to high manufacturing costs. Furthermore, the rotor hub structure is typically a variable-pitch structure, making it more complex and requiring more mating components, further increasing costs and assembly difficulties. Similarly, helicopter rotors with variable-pitch functions require numerous matching structures, resulting in more components and a more complex structure. Therefore, this invention proposes a rotor device to solve at least one of the problems in the prior art, obtaining a simple, fixed-pitch, and easily assembled seesaw-type rotor structure.

[0041] Please refer to the reference. Figures 1 to 8 In one embodiment of the present invention, the rotor device 100 includes:

[0042] The propeller hub assembly 10 includes a propeller hub body 11 and two propeller blades 12. The two propeller blades 12 are respectively installed at both ends of the propeller hub body 11 along the axial direction and have a fixed distance. A through hole 111 along the radial direction is opened in the middle of the propeller hub body 11.

[0043] A rotor shaft assembly 20, comprising a main shaft 21 and a shaft fixing member 22, wherein the main shaft 21 passes through the through hole 111, and the shaft fixing member 22 covers the end of the main shaft 21 that extends out of the through hole 111; and

[0044] The flapping hinge assembly 30 includes a flapping shaft 31 and a locking fastener 32. The flapping shaft 31 is sequentially inserted through the rotor hub body 11, the shaft fixing member 22 and the main shaft 21 along an axis perpendicular to the rotor main shaft 21, and is locked to the locking fastener 32 so that the rotor hub body 11 can flap and swing relative to the main shaft 21.

[0045] In this embodiment, the rotor hub assembly 10 includes a rotor hub body 11 and rotor blades 12. The installation method of the rotor hub body 11 and rotor blades 12 is not limited here. For example, the rotor blades 12 can be directly clamped by a rotor hub clamp, or the rotor blades 12 can be directly threaded together, or the rotor blades 12 can be fixed by a groove, etc. The connection method can be detachable, so as to facilitate the replacement of rotor blades 12. The shape of rotor blades 12 can be curved, that is, propeller blades 12, which can have a better blade surface curve according to wind tunnel experiments, so as to achieve better drag reduction and speed increase effect. When rotor blades 12 are installed on rotor hub body 11, the distance between the ends of the two rotor blades 12 has been determined, so that there is a fixed gap between them, the structure is simple, and it is easy to disassemble and assemble.

[0046] A through hole 111 is provided in the middle of the rotor hub body 11 for the main shaft 21 to pass through. To facilitate the flapping and swinging of the rotor hub body 11, the through hole 111 and the main shaft 21 are clearance-fitted, or the opening size of the through hole 111 is larger than the cross-sectional size of the main shaft 21. Optionally, the opening shape of the through hole 111 is adapted to the outer peripheral shape of the main shaft 21, thereby facilitating assembly and enabling flapping and swinging. The main shaft 21 is generally the drive shaft of the motor, which rotates at high speed when the motor starts, thereby driving the rotor hub body 11 and the blades 12 to rotate and provide the lift required for flight. The main shaft 21 can be a solid shaft or a hollow shaft. Here, it is a hollow shaft, which can further reduce the weight of the rotor shaft assembly 20, save costs, and improve flight performance. The cross-section of the spindle 21 is generally circular. The shaft fixing part 22 is placed on the end of the spindle 21, and its cross-sectional shape is not limited. It can be circular, square or other shapes, as long as it is fixed with the spindle 21 by interference fit.

[0047] The flapping shaft 31 is a structure through which the propeller hub body 11, the shaft fixing member 22, and the main shaft 21 pass. It can be a bolt, screw, etc., and acts as a rotating joint for the propeller blade 12 to flap, thereby realizing the flapping action. The propeller hub body 11 is fixed by the cooperation between the locking member 32 and the flapping shaft 31, and the flapping action is realized by the clearance fit between the flapping shaft 31 and the above three components.

[0048] The rotor device 100 of the present invention includes a rotor hub assembly 10, a rotor shaft assembly 20, and a flapping hinge assembly 30. Two blades 12 are directly mounted and fixed through the rotor hub body 11 to form a fixed pitch structure. There is no need to add other structures to adjust the pitch. The structure is simple and effectively reduces the overall weight. Furthermore, the rotor shaft assembly 20 includes a main shaft 21 and a shaft fixing member 22. The shaft fixing member 22 is covered at the end of the main shaft 21. The flapping shaft 31 passes through the rotor hub body 11 and then passes through the main shaft 21 through the shaft fixing member 22. This not only realizes the radial and axial positioning and force transmission of the rotor hub assembly 10, but also allows the forward blade 12 to have a higher relative airflow velocity than the backward blade 12 when the main shaft 21 rotates. This results in uneven starting load on the blade 12, causing the blade 12 to flap and swing relative to the main shaft 21 with the flapping shaft 31 as the axis. This can unload most of the bending moment, thereby reducing the fatigue and vibration of the blade 12 and rotor hub body 11 and improving the service life of the rotor device 100. This structure only requires a shaft fixing member 22 and a flapping shaft 31 to achieve the hinge connection between the main shaft 21 and the hub body 11. There is no need to fix the shaft fixing member 22 separately, which makes the structure simple. When the main shaft 21 rotates, it transmits torque and tension through the shaft fixing member 22, so that the hub assembly 10 can rotate stably. It can also simplify the machining process of the outer peripheral surface of the main shaft 21, such as spline structure. This simplifies the through hole 111 structure of the hub body 11, resulting in low manufacturing cost, convenient maintenance, and effective cost savings.

[0049] Please refer to Figure 3 Optionally, the rotor hub body 11 has two opposing connecting ears 112 protruding from the opening edge of the through hole 111. Each connecting ear 112 has a first hinge hole 1121. The end of the main shaft 21 has a second hinge hole 211. The shaft fixing member 22 forms a fixing groove 221 and has a third hinge hole 222 on the opposite side walls of the fixing groove 221. The groove wall of the fixing groove 221 is fitted to the outer peripheral wall of the main shaft 21. The outer peripheral side of the shaft fixing member 22 abuts against the connecting ear 112. The swing shaft 31 passes through the first hinge hole 1121, the third hinge hole 222 and the second hinge hole 211.

[0050] In this embodiment, the connecting lug 112 is located at the center of the rotor hub body 11 along its axial direction and protrudes from the surface of the rotor hub body 11. This allows the rotor hub body 11 to be limited by the end of the main shaft 21 passing through the through hole 111 during the swinging motion, effectively controlling its swinging angle and improving stability and flight performance. The center lines of the first hinge hole 1121, the second hinge hole 211, and the third hinge hole 222 are on the same straight line, facilitating the assembly of the swinging shaft 31 and ensuring the stability of the swinging direction of the rotor hub body 11.

[0051] Here, the fixing groove 221 is fitted to the outer peripheral wall of the main shaft 21, which makes the fit between the peripheral fixing member and the main shaft 21 more stable and improves the installation stability of the shaft fixing member 22. At the same time, the outer peripheral side of the shaft fixing member 22 abuts against the inner wall surface of the connecting lug 112, which can provide a certain guiding effect for the flapping of the propeller hub body 11 and ensure the flapping effect.

[0052] Please continue to refer to Figure 3 Optionally, the propeller hub assembly 10 further includes two bushings 13, one end of each bushing 13 is inserted through a first hinge hole 1121, and the other end is clamped between the shaft fixing member 22 and the connecting lug 112, and the swing shaft 31 is inserted through the bushing 13.

[0053] And / or, the swing hinge assembly 30 further includes a sleeve 33, which is fitted onto the swing shaft 31 with a gap and is interference-fitted with the hole walls of the two second hinge holes 211 and the hole wall of the third hinge hole 222.

[0054] In this embodiment, to alleviate the direct wear between the swing shaft 31 and the propeller hub body 11, a bushing 13 is installed inside a first hinge hole 1121 of the propeller hub body 11. The bushing 13 can be made of an elastic or flexible material, such as rubber or silicone pads. Its cross-section is approximately T-shaped, with one end passing through the first hinge hole 1121 and having an interference fit with it for fixation. This allows the swing shaft 31 to pass through the bushing 13 without direct contact with the propeller hub body 11, effectively reducing friction, extending the service life of the swing shaft 31, and reducing noise generation. Here, the swing shaft 31 and the inner wall of the bushing 13 have a clearance fit, thus ensuring the function of the rotating pair. Meanwhile, the other end of the bushing 13 is clamped between the shaft fixing member 22 and the connecting lug 112. Here, the shaft fixing member 22 and the bushing 13 are in clearance fit when clamped, that is, a certain rotational safety clearance is maintained between the two, which can reduce the friction between the bushing 13 and the shaft fixing member 22 and ensure the swing characteristics. Optionally, in other embodiments, the bushing 13 can also be cylindrical and only pass through the first hinge hole 1121 to separate the swing shaft 31 and the propeller hub body 11.

[0055] With or without bushing 13, the swing hinge assembly 30 also includes a sleeve 33, which passes through the second hinge hole 211 and the third hinge hole 222, and is interference-fitted with both to ensure its axial position. The sleeve 33 can be made of metal or ceramic, such as steel pipe, effectively reducing wear between the swing shaft 31 and the main shaft 21 and the shaft fixing member 22, and improving performance. Here, the swing shaft 31 and the inner wall of the sleeve 33 are clearance-fitted, further ensuring the function of their rotating pair. Optionally, the two end faces of the sleeve 33 are flush with the outer periphery of the shaft fixing member 22, or can be recessed into the third hinge hole 222, thereby avoiding contact with the end face of the bushing 13 and improving swing characteristics.

[0056] Please combine Figure 7 and Figure 8 Optionally, the waving shaft 31 is a bolt, and the locking fastener 32 is a slotted nut;

[0057] The swing hinge assembly 30 also includes a stop member. The bolt has a stop hole at its tail end. The stop member passes through the stop hole and abuts against the slotted nut.

[0058] And / or, a washer 35 is sandwiched between the fixed end of the bolt and the connecting lug 112, and a washer 35 is sandwiched between the slotted nut and another connecting lug 112.

[0059] In this embodiment, for ease of assembly, the flapping shaft 31 is a bolt, with one end as the fixed end and the other end as the tail end, which can be secured solely by the locking fastener 32. To further ensure locking stability, a stop is provided, such as a cotter pin or a screw, with a stop hole at the tail end. When the slotted nut is secured to the bolt tail end, the stop is inserted into the stop hole and abuts against the slot of the slotted nut, thereby effectively preventing the slotted nut from loosening. This allows the structure to withstand centrifugal force from the hub assembly 10, as well as loads in the flapping and oscillating directions, thus improving the overall structural stability.

[0060] Based on the presence or absence of the aforementioned stop, a washer 35 is placed between the fixed end of the bolt and the connecting lug 112, and a washer 35 is placed between the slotted nut and the connecting lug 112, thereby improving the stability of the locking.

[0061] Optionally, the main shaft 21 is cylindrical, the outer periphery of the shaft fixing member 22 is cubic, and the opening shape of the fixing groove 221 is at least partially arc-shaped.

[0062] Alternatively, the outer side of the main shaft 21 is provided with two opposing abutment grooves 212, and the second hinge hole 211 passes through the bottom of the two abutment grooves 212. The bottom of the abutment groove 212 is a plane and fits against the inner wall of the shaft fixing member 22.

[0063] In this embodiment, the main shaft 21 is cylindrical, with a simple structure and easy processing. To fit the main shaft 21, the opening shape of the fixing groove 221 is at least partially arc-shaped. For example, the opening of the fixing groove 221 is circular, or a combination of arc and straight shapes; this is not limited here. The outer periphery of the shaft fixing member 22 is cubic, which facilitates its fit with the two oppositely arranged planar connecting ears 112, improving the guiding effect during swinging and waving, and ensuring waving characteristics.

[0064] Optionally, in order to prevent circumferential displacement and sliding between the spindle 21 and the shaft fixing member 22, an abutment groove 212 is provided on the outer side of the spindle 21. The bottom surface of the abutment groove 212 is flat, so that the inner wall surface of the shaft fixing member 22 also has a flat section, which can be fully fitted and abutted with it, improving the convenience of assembly, preventing it from sliding relative to the spindle 21, and ensuring structural stability.

[0065] Please refer to Figure 4 and Figure 5 Optionally, referring to the figure, the rotor device 100 also includes a buffer sleeve 40, which is sleeved on the main shaft 21. One end of the buffer sleeve 40 abuts against the end face of the shaft fixing member 22, and the other end abuts against a retaining ring at the end of the main shaft 21 away from the shaft fixing member 22.

[0066] And / or, the end face of the shaft fixing member 22 facing away from the main shaft 21 has a lifting part 223.

[0067] In this embodiment, the rotor device 100 also includes a buffer sleeve 40. The buffer sleeve 40 can be made of rubber or silicone, possessing a certain degree of flexibility or elasticity. Sleeveted around the periphery of the main shaft 21, it reduces the distance between the through hole 111 and the main shaft 21, thereby preventing the rotor hub assembly 10 from swinging at excessive angles. Furthermore, based on its material properties, it reduces collisions between the rotor hub assembly 10 and the main shaft 21 at low speeds or when stationary, thus protecting the main shaft 21 and extending the service life of the rotor device 100. Simultaneously, the upper end of the buffer sleeve 40 abuts against the end face of the shaft fixing member 22, and the lower end abuts against the retaining ring of the main shaft 21, providing axial restraint and improving axial stability. The buffer sleeve 40 and the main shaft 21 are interference-fitted, allowing them to rotate together.

[0068] Based on the presence or absence of the buffer sleeve 40, the end face of the shaft fixing member 22 facing away from the main shaft 21 forms a lifting part 223. The lifting part 223 is a ring structure, which facilitates the lifting of the rotor device 100, thereby enabling wind tunnel experiments and providing convenience for the design of improving the flapping characteristics. In other embodiments, the lifting part 223 may also be a hook or other structure.

[0069] Optionally, the rotor hub body 11 includes an upper rotor hub 113 and a lower rotor hub 114 that are detachably connected. The upper rotor hub 113 and the lower rotor hub 114 enclose and form two oppositely arranged mounting grooves 115. One end of each rotor blade 12 is installed in one of the mounting grooves 115. The upper rotor hub 113 has a first through hole, and the lower rotor hub 114 has a second through hole. The first through hole and the second through hole together form the through hole 111. The upper rotor hub 113 and the lower rotor hub 114 are connected to press and fix the two rotor blades 12 in the mounting grooves 115.

[0070] In this embodiment, to simplify the structure, the rotor hub body 11 is divided into a detachably connected upper rotor hub 113 and a lower rotor hub 114. The two hubs can be joined together to form a circular opening mounting groove 115. By assembling the upper rotor hub 113 and the lower rotor hub 114, the rotor blade 12 can be installed and fixed, further simplifying the assembly steps and improving efficiency. The detachable connection here can be a threaded connection, a combination of snap-fit ​​and threaded connection, or a plug-in connection, etc., and is not limited here.

[0071] Please refer to Figure 6 Optionally, the upper rotor hub 113 is provided with a plurality of spaced first connecting holes 1131, and the lower rotor hub 114 is provided with a plurality of spaced second connecting holes 1141. A connector is sequentially passed through the second connecting hole 1141 and the first connecting hole 1131 to thread the upper rotor hub 113 and the lower rotor hub 114.

[0072] And / or, the propeller hub assembly 10 further includes a positioning pin 14, wherein the upper propeller hub 113 and the lower propeller hub 114 are respectively provided with positioning holes 1142, the positioning holes 1142 of the upper propeller hub 113 and the positioning holes 1142 of the lower propeller hub 114 are correspondingly provided, and the two ends of the positioning pin 14 are respectively inserted into the two positioning holes 1142 to position the upper propeller hub 113 and the lower propeller hub 114.

[0073] In this embodiment, the upper rotor hub 113 and the lower rotor hub 114 are connected by a thread, thereby ensuring the stability of the connection structure. Optionally, multiple first connecting holes 1131 are provided and arranged at intervals along the axial direction of the upper rotor hub 113. The second connecting holes 1141 are provided in a one-to-one correspondence with the first connecting holes 1131. The bolts here can be used with slotted nuts and stop members are provided to improve the stability of the connection and at the same time provide a good fixing effect on the blade 12.

[0074] Optionally, to improve installation convenience, positioning holes 1142 are provided on the opposite end faces of the upper rotor hub 113 and the lower rotor hub 114. Positioning pins 14 are installed in these positioning holes 1142 to achieve relative positioning of the two components, preventing misalignment and improving the coaxiality of the rotor blades 12. This ensures uniform clamping force when fixing the root of the rotor blades 12 and extends the service life of the rotor hub assembly 10. The use of positioning pins 14 facilitates assembly and reduces the processing cost of the rotor hub body 11.

[0075] Please refer to Figure 6 Optionally, the groove wall of the mounting groove 115 is formed with a first stepped surface 116, the stepped surface facing the bottom of the mounting groove 115, and a mounting part 121 protruding from one end of each blade 12. A second stepped surface 122 is formed between the mounting part 121 and the end of the blade 12, and the first stepped surface 116 abuts against the second stepped surface 122.

[0076] In this embodiment, to prevent the blade 12 from detaching from the mounting groove 115, a first stepped surface 116 is formed on the groove wall of the mounting groove 115. Correspondingly, the blade 12 also has a second stepped surface 122. During installation, the mounting part 121 is inserted into the mounting groove 115, and the first stepped surface 116 abuts against the second stepped surface 122, thereby axially limiting the blade 12 and preventing loosening, effectively ensuring structural stability. Optionally, the first stepped surface 116 and the second stepped surface 122 are inclined relative to the bottom of the mounting groove 115, thereby facilitating the assembly of the blade 12.

[0077] The present invention also proposes an aircraft (not shown), which includes a fuselage and a rotor device 100 as described above, connected to the fuselage. Since the rotor device 100 of the aircraft adopts all the technical solutions of all the foregoing embodiments, it at least has the beneficial effects brought about by the technical solutions of the foregoing embodiments, and will not be described in detail here.

[0078] The aircraft can be a helicopter or a flying car, etc.

[0079] The above description is merely a preferred embodiment of the present invention and does not limit the patent scope of the present invention. Any equivalent structural transformations made using the contents of the present invention's specification and drawings under the inventive concept of the present invention, or direct / indirect applications in other related technical fields, are included within the patent protection scope of the present invention.

Claims

1. A rotor device, characterized in that, The rotor assembly includes: The propeller hub assembly includes a propeller hub body and two blades. The two blades are respectively installed at both ends of the propeller hub body along the axial direction and have a fixed distance. A through hole in the radial direction is opened in the middle of the propeller hub body. A rotor shaft assembly, comprising a main shaft and a shaft retainer, wherein the main shaft passes through the through hole, and the shaft retainer covers the end of the main shaft extending out of the through hole; and A flapping hinge assembly includes a flapping shaft and a locking fastener. The flapping shaft is sequentially inserted through the propeller hub body, the shaft fixing member, and the main shaft along an axis perpendicular to the main shaft, and is locked to the locking fastener so that the propeller hub body can flap and swing relative to the main shaft. The rotor hub body has two opposing connecting ears protruding from the opening edge of the through hole. Each connecting ear has a first hinge hole. The end of the main shaft has a second hinge hole. The shaft fixing member has a fixing groove and a third hinge hole is opened on the two side walls opposite to the fixing groove. The groove wall of the fixing groove is fitted to the outer peripheral wall of the main shaft. The outer peripheral side of the shaft fixing member abuts against the inner wall surface of the connecting ear. The swing shaft gap passes through the first hinge hole, the third hinge hole, and the second hinge hole.

2. The rotor device as described in claim 1, characterized in that, The propeller hub assembly also includes two bushings, one end of each bushing is inserted through a first hinge hole, and the other end is clamped between the shaft fixing member and the connecting lug, and the swing shaft clearance is inserted inside the bushing; And / or, the waving hinge assembly further includes a sleeve, the sleeve being fitted with the waving shaft with a gap, and having an interference fit with the hole walls of the two second hinge holes and the hole wall of the third hinge hole.

3. The rotor device as described in claim 1, characterized in that, The waving shaft is a bolt, and the locking fastener is a slotted nut; The swing hinge assembly also includes a stop member. The bolt has a stop hole at its tail end. The stop member passes through the stop hole and abuts against the slotted nut. And / or, a washer is provided between the fixed end of the bolt and the connecting lug, and a washer is provided between the slotted nut and the other connecting lug.

4. The rotor device according to any one of claims 1 to 3, characterized in that, The main shaft is cylindrical, the outer periphery of the shaft fixing member is cubic, and the opening shape of the fixing groove is at least partially arc-shaped. And / or, the outer side of the main shaft is provided with two opposing abutment grooves, the second hinge hole penetrates the bottom of the two abutment grooves, the bottom of the abutment groove is a plane, and it fits against the inner wall of the shaft fixing member.

5. The rotor device according to any one of claims 1 to 3, characterized in that, The rotor device also includes a buffer sleeve, which is sleeved on the main shaft. One end of the buffer sleeve abuts against the end face of the shaft fixing member, and the other end abuts against a retaining ring at the end of the main shaft away from the shaft fixing member. And / or, the end face of the shaft fixing member opposite to the main shaft has a lifting part.

6. The rotor device according to any one of claims 1 to 3, characterized in that, The propeller hub body includes a detachably connected upper propeller hub and a lower propeller hub. The upper propeller hub and the lower propeller hub are arranged to form two opposite mounting grooves. One end of each propeller blade is installed in one of the mounting grooves. The upper propeller hub has a first through hole and the lower propeller hub has a second through hole. The first through hole and the second through hole together form the through hole. The upper propeller hub and the lower propeller hub are connected to press and fix the two propeller blades in the mounting grooves.

7. The rotor device as claimed in claim 6, characterized in that, The upper rotor hub has a plurality of spaced first connecting holes, and the lower rotor hub has a plurality of spaced second connecting holes. A connector is sequentially inserted through the second connecting hole and the first connecting hole to thread the upper rotor hub and the lower rotor hub. And / or, the propeller hub assembly further includes a positioning pin, the upper propeller hub and the lower propeller hub are respectively provided with positioning holes, the positioning holes of the upper propeller hub and the positioning holes of the lower propeller hub are respectively provided, and the two ends of the positioning pin are respectively inserted into the two positioning holes to position the upper propeller hub and the lower propeller hub.

8. The rotor device as claimed in claim 6, characterized in that, The wall of the mounting groove has a first stepped surface facing the bottom of the mounting groove. Each blade has a mounting portion protruding from one end. A second stepped surface is formed between the mounting portion and the end of the blade. The first stepped surface abuts against the second stepped surface.

9. An aircraft, characterized in that, The aircraft includes an airframe and a rotor assembly connected to the airframe as described in any one of claims 1 to 8.

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