Rotor system of unmanned aerial vehicle and unmanned aerial vehicle

Abstract

The utility model relates to the field of unmanned aerial vehicles, in particular to a rotor wing system of an unmanned aerial vehicle and the unmanned aerial vehicle thereof.The rotor wing system of the unmanned aerial vehicle comprises a main shaft, the main shaft is rotationally connected with a plurality of rotor wing assemblies, the main shaft is further sleeved with an inclinator assembly, and a first connecting rod structure is hinged to the inclinator assembly; the inclinator assembly is hinged to the rotor wing assembly through a first connecting rod structure, a connecting piece is further hinged to the outer wall of the inclinator assembly, a second connecting rod structure is fixedly connected to the lower portion of the connecting piece, and the connecting piece is connected with a steering engine through the second connecting rod structure; the attack angle of the rotor wing is directly adjusted through the first connecting rod structure and the second connecting rod structure, and therefore the higher response speed, the higher control precision and the better energy utilization efficiency are achieved. In addition, the attack angle adjustment does not need to change the rotating speed of the rotor wings, so that the problem of flight inertia caused by rotating speed change is avoided, and the unmanned aerial vehicle has better dynamic stability when executing complex flight actions.

Description

TECHNICAL FIELD

[0001] The utility model relates to unmanned plane technical field, especially a rotor system of unmanned plane and unmanned plane thereof. BACKGROUND

[0002] With the popularization of unmanned plane in the scene of delivery, patrol, agricultural spraying, the unmanned plane equipped with large size rotor gradually becomes the market mainstream because of its characteristics of carrying heavier goods and flying more stably. This kind of unmanned plane usually changes the lift by adjusting the motor speed of multiple rotors, for example, to make the unmanned plane fly to the left, the speed of the left rotor is reduced, and the speed of the right rotor is increased, and the turning or moving is realized through the lift difference. However, this control mode depending on motor speed regulation has a key problem: the motor speed cannot be adjusted to the ideal speed instantaneously, resulting in slow flight control reaction and low precision. SUMMARY

[0003] The utility model aims at: aiming at the problem of the prior art that the large size rotor of unmanned plane is adjusted by motor, the adjustment of motor speed needs time, and the ideal speed cannot be adjusted instantaneously, resulting in low flight control precision of unmanned plane and slow counter pressure, provide a rotor system of unmanned plane and unmanned plane thereof.

[0004] In order to realize the above-mentioned purpose, the utility model adopts the technical scheme that:

[0005] A rotor system of unmanned plane, comprising a main shaft, a plurality of rotor assemblies are rotatably connected on the main shaft;

[0006] A tilting device assembly is further sleeved on the main shaft, the tilting device assembly moves along the main shaft axis direction, a first connecting rod structure is hinged on the tilting device assembly, and the tilting device assembly is hinged with the rotor assembly through the first connecting rod structure;

[0007] The first connecting rod structure is used for driving the rotor assembly to rotate;

[0008] A connecting piece is further hinged on the outer wall of the tilting device assembly, and the connecting piece is used to drive the tilting device assembly to move along the main shaft axis direction;

[0009] One end of the connecting piece is hinged with the tilting device assembly, the other end is hinged with a limiting piece, and the limiting piece is used to limit the horizontal movement of the connecting piece;

[0010] A second connecting rod structure is fixedly connected below the connecting piece, the second connecting rod structure is used to drive the connecting piece to work, and the connecting piece is connected with a rudder motor through the second connecting rod structure, and the rudder motor is used to drive the second connecting rod structure to work.

[0011] The application drives the second connecting rod structure to displace through the output end of the rudder, drives the connecting piece to move through the second connecting rod structure, drives the tilt disc assembly to rotate through the end of the connecting piece hinged with the tilt disc assembly, drives the first connecting rod structure to displace through the lifting movement of the tilt disc assembly, and drives the rotor assembly to rotate through the first connecting rod structure, so that the attack angle is changed.

[0012] The utility model discloses a rotor system of unmanned plane, the first connecting rod structure is hinged with the tilt ware assembly one end and rotor assembly the other end through the first connecting rod structure, so that when the tilt ware assembly moves along the axial direction of the main shaft, can drive the first connecting rod structure to move, thereby control each rotor assembly rotates, thereby change the attack angle of rotor assembly, still be equipped with second connecting rod structure, the first connecting rod structure is connected with the output end of rudder one end and is equipped with connecting piece the other end, the connecting piece is hinged with the outer wall of tilt ware assembly, so that when rudder works, synchronously drive second connecting rod structure to work, drive connecting piece through connecting rod structure, so that connecting piece promotes tilt ware assembly and moves up and down, and the connecting piece is also hinged with the limiting piece, so that the movement of connecting piece is the overturning movement, when second connecting rod structure promotes connecting piece, the hinged restriction of connecting piece and wing appears horizontal movement through connecting piece, and the hinged of connecting piece and tilt ware assembly makes connecting piece overturn, and tilt ware assembly can still move up and down, thereby drive first connecting rod structure realizes the attack angle regulation of rotor assembly, compared with the method that the traditional attack angle regulation of rotor assembly is adjusted through the motor, the application directly adjusts the attack angle of rotor through first connecting rod structure and second connecting rod structure, so that the response speed is faster, the control precision is higher and the energy utilization efficiency is better.

[0013] As a preferred scheme of the utility model, the tilt ware assembly comprises a tilt driven disc, the tilt driven disc is connected with a tilt disc at the bottom, the tilt driven disc moves synchronously with the tilt disc, and the tilt driven disc comprises symmetrically arranged first hinged parts, each first hinged part is hinged with the pull rod structure, and the pull rod structure is used for driving the rotor assembly to rotate.

[0014] The swashplate assembly is slidable by driving the second linkage structure via a servo motor, which makes the swashplate driven disk move synchronously with the swashplate. This allows the rotor assembly's angle of attack to be quickly adjusted via the first linkage structure. Compared to the traditional method of relying on a motor to adjust the speed, the response speed is faster and the flight control is more precise. The swashplate assembly adopts a design where the swashplate driven disk moves synchronously with the swashplate, making the motion transmission more stable and avoiding the energy loss or response lag that may be caused by a separate transmission structure, thus improving the overall mechanical reliability and durability.

[0015] As a preferred embodiment of the present invention, the first linkage structure includes a first pull rod, one end of which is hinged to the first hinge portion and the other end of which is hinged to a first rocker arm, and the end of the first rocker arm away from the first pull rod is hinged to the rotor assembly.

[0016] By using a two-stage linkage structure, the servo motor can effectively reduce friction and transmission loss when transmitting power through the linkage system, thereby improving the system's motion efficiency and ensuring smoother and more stable angle adjustment of the rotor assembly.

[0017] As a preferred embodiment of this utility model, the main shaft is provided with a rotating shaft at one end near the rotor assembly, and the main shaft is connected to the rotor assembly through the rotating shaft.

[0018] A rotating shaft is used to connect the main shaft and the rotor assembly, so that the subsequent first rocker arm can drive the rotor assembly to rotate.

[0019] As a preferred embodiment of the present invention, the rotor assembly includes a rotor clamp, which is rotatably connected to the rotating shaft, and a rotor is hinged to the end of the rotor clamp away from the rotating shaft.

[0020] As a preferred embodiment of the present invention, the connector includes an opening, the inner wall of which is hinged to the outer wall of the tilting disk, and the connector further includes a second hinge portion, which is hinged to the limiting member.

[0021] The opening design allows the connector to reliably cover and hinge to the outer wall of the swashplate, providing additional support and guidance as the swashplate slides along the main shaft, reducing lateral sway and improving the system's motion stability.

[0022] As a preferred embodiment of the present invention, the second linkage structure includes a second pull rod, one end of which is fixedly connected to the side of the connector away from the rotor assembly, and the other end is hinged to a second rocker arm, the end of which is away from the second pull rod and connected to the output end of the servo motor.

[0023] In a second aspect, a UAV includes a rotor system of the UAV as described above, and further includes a wing, wherein the rotor system of the UAV is connected to the wing.

[0024] The utility model discloses an unmanned plane, the rotor system of the wing of the unmanned plane can be controlled to drive the connecting piece to overturn motion through the rudder engine to the second connecting rod structure, and the tilting device assembly is driven to lift motion along the main shaft through the overturn motion of the connecting piece, when the tilting device main shaft lifts motion, synchronously drive the first connecting rod structure to displace, and the first connecting rod structure adjusts the angle of attack of rotor assembly, the unmanned plane makes the operation of whole unmanned plane more stable through the rotor system.

[0025] As a preferred scheme of the utility model, the limiting piece is fixedly connected with the wing.

[0026] The movement path of the connecting piece is limited by the limiting piece.

[0027] As a preferred scheme of the utility model, one end of the limiting piece is fixedly connected with the wing, and the other end is hingedly connected with the second hinged part.

[0028] As a preferred scheme of the utility model, the unmanned plane further includes a fuselage, the wing is connected with the fuselage, and the wing is provided with four wing tips and is symmetrically arranged on both sides of the fuselage.

[0029] As a preferred scheme of the utility model, the wing end is provided with a mounting bracket, and the mounting bracket is used for mounting the rudder engine.

[0030] The mounting bracket is arranged, so that the position of the rudder engine does not change during work, thereby better controlling the second connecting rod structure.

[0031] As a preferred scheme of the utility model, a motor is arranged in the mounting bracket, and the motor is connected with the main shaft.

[0032] The motor is connected with the main shaft, so that the rotor assembly of the unmanned plane can work.

[0033] As a preferred scheme of the utility model, a driving device is arranged in the fuselage.

[0034] In summary, due to the adoption of the above technical scheme, the utility model has the beneficial effects that:

[0035] 1. This utility model relates to a rotor system for an unmanned aerial vehicle (UAV). The invention includes a first linkage structure, with one end hinged to a swashplate assembly and the other end hinged to a rotor assembly. When the swashplate assembly moves along the axis of the main shaft, it drives the first linkage structure, thereby controlling the rotation of each rotor assembly and changing the angle of attack of the rotor assemblies. A second linkage structure is also included, with one end connected to the output end of a servo motor and the other end connected to a connector. This connector is hinged to the outer wall of the swashplate assembly, so that when the servo motor operates, it synchronously drives the second linkage structure. The linkage structure drives the connector, thus enabling the rotor assembly to rotate. The connector pushes the swashplate assembly for vertical movement. This connector is also hinged to a limiting member, allowing its movement to be a flipping motion. When the second linkage pushes the connector, the hinge between the connector and the wing restricts its horizontal movement. However, the hinge between the connector and the swashplate assembly allows the swashplate assembly to continue vertical movement even when the connector flips, thereby driving the first linkage to adjust the rotor assembly's angle of attack. Compared to the traditional method of controlling lift by adjusting rotor speed via a motor, this application directly adjusts the rotor angle of attack through the first and second linkage structures, achieving faster response, higher control precision, and better energy efficiency. Furthermore, since angle of attack adjustment does not require changing rotor speed, it avoids flight inertia problems caused by speed changes, resulting in better dynamic stability for the UAV when performing complex flight maneuvers.

[0036] 2. This utility model is a drone. The rotor system on the wings of the drone can be controlled by a servo motor to drive the connecting parts to rotate. The rotation of the connecting parts drives the swashplate assembly to move up and down along the main axis. When the swashplate main axis moves up and down, it simultaneously drives the first connecting part to move, and the first connecting part adjusts the angle of attack of the rotor assembly. By equipping the drone with this rotor system, the operation of the entire drone is more stable. Attached Figure Description

[0037] Figure 1 This is a schematic diagram of the rotor system of the UAV of this utility model;

[0038] Figure 2 This is a schematic diagram of the connection between the servo motor and the second linkage structure and the connecting parts of this utility model;

[0039] Figure 3 This is a schematic diagram showing the connection between the tilting driven disk, the first connecting rod structure, and the rotor clip of this utility model.

[0040] Figure 4 This is a schematic diagram of the tilter assembly and connector of this utility model;

[0041] Figure 5 is a structural schematic view of the connecting piece of the utility model;

[0042] Figure 6 is a structural schematic view of the second connecting rod structure of the utility model;

[0043] Figure 7 is a display view of the unmanned aerial vehicle of the utility model;

[0044] Figure 8 is a structural schematic view of the rotor assembly of the utility model;

[0045] Figure 9 is a structural schematic view of the tilt driven disc of the utility model;

[0046] Figure 10 is a posture display view of the unmanned aerial vehicle in the embodiment 3 of the utility model when flying;

[0047] Figure 11 is a posture schematic view of the unmanned aerial vehicle in the embodiment 3 of the utility model when taking off;

[0048] Figure 12 is a chord line schematic view of the wing in the embodiment 3 of the utility model.

[0049] Icon: 1-main shaft;2-rotary shaft;3-rotor assembly;31-rotor clamp;32-rotor;4-tilt assembly;41-tilt driven disc;411-first hinged part;42-tilt disc;5-connecting piece;51-opening part;52-second hinged part;6-first connecting rod structure;61-first pull rod;62-first rocker arm;7-second connecting rod structure;71-second pull rod;72-second rocker arm;8-steering machine;9-wing;91-chord line;10-mounting frame;11-fuselage;12-limiting piece. DETAILED DESCRIPTION

[0050] The utility model will be further described in detail in combination with specific embodiments. But this should not be understood as the range of the above-mentioned subject matter of the utility model is limited to the following embodiments, and all the technologies realized based on the content of the utility model belong to the range of the utility model.

[0051] In the description of the embodiments of the present application, the terms of orientation or position relationship such as "upper", "lower", "left", "right", "center", "inner", "outer" and the like are based on the orientation or position relationship when the product / device / apparatus of the present application is normally used. These terms of orientation or position relationship are only for the convenience of describing the present application or simplifying the description of the embodiments, and for the convenience of the skilled person to quickly understand the scheme, and do not indicate or imply that a specific device / component / element must have a specific orientation or be constructed and operated in a specific position relationship, and therefore cannot be understood as a limitation on the present application.

[0052] In addition, the terms "horizontal", "vertical", "suspension", "parallel" and the like do not mean that the corresponding device / component / element must be absolutely horizontal or vertical or suspended or parallel, but can be slightly inclined or deviated. For example, "horizontal" only means that its direction is more horizontal relative to "vertical", and does not mean that the structure must be completely horizontal, but can be slightly inclined. Alternatively, it can be simplified to understand that the corresponding device / component / element is arranged in the direction of "horizontal", "vertical", "suspension", "parallel" and the like, and can have an error / deviation of ±10% relative to the corresponding direction, more preferably an error / deviation of ±8%, more preferably an error / deviation of ±6%, more preferably an error / deviation of ±5%, and more preferably an error / deviation of ±4%. As long as the corresponding device / component / element is within the error / deviation range, it can still achieve its role in the scheme of the present application.

[0053] In addition, the terms "first", "second", "third" and the like in the description of the embodiments of the present application are only used to distinguish the same or similar components, and should not be understood as emphasizing or implying the relative importance of the specific components.

[0054] In addition, in the description of the embodiments of the present application, "several", "a plurality of", "several" represent at least 2. It can be 2, 3, 4, 5, 6, 7, 8, 9, etc. in any case, and even more than 9.

[0055] In addition, in the description of the technical scheme of the present application, unless otherwise specified / limited / limited, the terms "set", "install", "connect", "connect", "set", "lay", "arrange" should be understood broadly, for example, it can be fixedly connected, or it can be detachably connected, or integrally connected, which can be welding, riveting, bolting, screwing and other commonly used connection means in the art. The connection can be mechanical connection, electrical connection or communication connection; it can be directly connected, or indirectly connected through an intermediate medium, or the communication between two elements.

[0056] Example 1

[0057] like Figure 1 , Figure 2 , Figure 3 , Figure 4 and Figure 6 The rotor system of a drone shown includes a main shaft 1 rotatably connected to a rotor assembly 3. A swashplate assembly 4 is sleeved on the main shaft 1. The swashplate assembly 4 can move up and down along the axial direction of the main shaft 1. The swashplate assembly 4 is connected to the rotor assembly 3 through a first linkage structure 6. The first linkage structure 6 drives the rotor assembly 3 to rotate synchronously with the movement of the swashplate assembly 4, thereby changing the angle of attack of the rotor assembly 3. A connector 5 is hinged to the outer wall of the swashplate assembly 4. One end of the connector 5 is hinged to the swashplate assembly 4, and the other end is hinged to a limiting member 12. The limiting member 12 is used to restrict the horizontal movement of the connector 5.

[0058] A second linkage structure 7 is fixedly connected below the connector 5. One end of the second linkage structure 7 is fixedly connected to the connector 5, and the other end is connected to the output end of the servo motor 8. When the output end of the servo motor 8 is working, it can drive the second linkage structure 7 to work. The second linkage structure 7 pushes the connector 5 to move upward. Since one end of the connector 5 is hinged to the swashplate assembly 4 and the other end is hinged to the limit member 12, the swashplate assembly 4 is rotated around the hinge point between itself and the limit member 12 after being subjected to the force of the second linkage structure 7. The end of the connector 5 that is hinged to the swashplate assembly 4 is raised, thereby driving the swashplate assembly 4 to rise along the axis of the main shaft 1, which in turn drives the first linkage structure 6 to move. The first linkage structure 6 drives the rotor assembly 3 to rotate, thereby changing the angle of attack.

[0059] Furthermore, the first linkage structure 6 includes a first pull rod 61 hinged to the swashplate assembly 4. The end of the first pull rod 61 away from the swashplate assembly 4 is hinged to a first rocker arm 62, which is connected to the rotor assembly 3. In this way, when the swashplate assembly 4 rises, it drives the first pull rod 61 to move. Since the first pull rod 61 is hinged to the first rocker arm 62, when the first pull rod 61 moves, it drives the first rocker arm 62 to move, and the first rocker arm 62 drives the rotor assembly 3 to rotate.

[0060] Further, the second linkage structure 7 comprises a second pull rod 71 connected with the connecting piece 5, and the second pull rod 71 is provided with a second rocker arm 72 at one end away from the connecting piece 5, and the second rocker arm 72 is connected with the output end of the steering engine 8 at one end away from the second pull rod 71, when the steering engine 8 works, the output end of the steering engine 8 drives the second rocker arm 72 to move, and the second rocker arm 72 drives the second pull rod 71 to move, and since the second pull rod 71 is fixedly connected with the connecting piece 5, when the second pull rod 71 moves, the connecting piece 5 can be pushed to overturn, and since the connecting piece 5 is hingedly connected with the tilting device assembly 4, when the connecting piece 5 overturns, the tilting device assembly 4 is lifted together.

[0061] In one or more embodiments, the tilting device assembly 4 comprises a tilting driven disc 41, and the tilting driven disc 41 is connected with a tilting disc 42 at the bottom, the tilting driven disc 41 moves synchronously with the tilting disc 42, and the tilting driven disc 41 comprises symmetrically arranged first hinge parts 411, each of which is hingedly connected with the first pull rod 61, and the second linkage structure 7 is driven by the steering engine 8 to drive the tilting device assembly 4 to slide, so that the tilting driven disc 41 moves synchronously with the tilting disc 42, thereby quickly adjusting the attack angle of the rotor assembly 3 through the first pull rod 61 and the first rocker arm 62, and compared with the conventional mode of adjusting the rotating speed of the motor, the response speed is faster, and the flight control is more accurate; the design that the tilting driven disc 41 moves synchronously with the tilting disc 42 is adopted for the tilting device assembly 4, so that the motion transmission is more stable, the energy loss or response lag caused by the separate transmission structure is avoided, and the overall mechanical reliability and durability are improved, as shown in Figure 3 、 Figure 4 and Figure 12 .

[0062] In one or more embodiments, the main shaft 1 is provided with a rotating shaft 2 at one end close to the rotor assembly 3, and the main shaft 1 is connected with the rotor assembly 3 through the rotating shaft 2, the rotor assembly 3 comprises a rotor clamp 31, the rotor clamp 31 is rotationally connected with the rotating shaft 2, and the rotor clamp 31 is hingedly connected with a rotor 32 at one end away from the rotating shaft 2, as shown in Figure 2 and Figure 8 .

[0063] In one or more embodiments, the connecting piece 5 comprises an opening part 51, and the inner wall of the opening part 51 is hingedly connected with the outer wall of the tilting disc 42, and the connecting piece 5 further comprises a second hinge part 52, and the second hinge part 52 is hingedly connected with the wing 9.

[0064] Embodiment 2

[0065] In the second aspect, an unmanned aerial vehicle comprises a rotor system of the unmanned aerial vehicle of embodiment 1, and further comprises a wing 9, and the rotor system of the unmanned aerial vehicle is connected with the wing 9.

[0066] Further, the wing 9 is provided with a limiting piece 12 at one end of the connecting piece 5, the wing 9 is hinged with the second hinge part 52 through the limiting piece 12, the connecting piece 5 can reliably cover and hinge the outer wall of the tilt plate 42 through the design of the opening part 51, additional support and guiding effect is provided when the tilt plate 42 slides along the main shaft 1, transverse shaking is reduced, and the motion stability of the system is improved, as shown in Figure 1 、 Figure 2 With Figure 5 as shown.

[0067] Embodiment 3

[0068] This embodiment is an improvement on the wing in embodiment 2.

[0069] Specifically, the unmanned aerial vehicle further comprises a fuselage 11, the wing 9 is connected with the fuselage 11, and the chord line 91 of the wing 9 forms an included angle a with the fuselage 11, the included angle a being 30-60 degrees.

[0070] Further, the wing 9 is provided with four wings and is symmetrically arranged on both sides of the fuselage 11, each wing 9 is arranged in parallel with each other, and the chord line 91 of the wing 9 is parallel to the axis of the main shaft 1, by arranging the wing 9 of the unmanned aerial vehicle on the fuselage 11 in an inclined manner, and the chord line 91 of the wing 9 forms an included angle a with the fuselage 11, and the included angle a is 30-60 degrees, and the chord line 91 of the wing 9 is parallel to the axis of the main shaft 1, so that the unmanned aerial vehicle can first adjust the take-off posture to the posture that the chord line 91 of the wing 9 is perpendicular to the ground when taking off, at this time, the axis of the main shaft 1 is also perpendicular to the ground, and because the chord line 91 of the wing 9 is perpendicular to the ground, the wing 9 is also perpendicular to the ground, so that the resistance during take-off can be reduced, and after the unmanned aerial vehicle is in a flight posture, the chord line 91 of each wing 9 can be adjusted to be parallel to the ground, so as to increase the contact area between the wing 9 and the airflow, thereby improving the lift and reducing the energy consumption, as shown in Figure 10 and Figure 11 (Black arrows in the figure point to the moving direction of the unmanned aerial vehicle).

[0071] In one or more embodiments, the cross section of the wing 9 is airfoil-shaped, as shown in Figure 12 .

[0072] The above merely describes the preferred embodiments of the present application and is not intended to limit the present application, and any modification, equivalent replacement and improvement made within the spirit and principle of the present application shall be included in the protection scope of the present application.

Claims

1. A rotor system for an unmanned aerial vehicle (UAV), characterized in that, Includes a main shaft (1), on which a plurality of rotor assemblies (3) are rotatably connected; A swashplate assembly (4) is also fitted on the main shaft (1). The swashplate assembly (4) moves along the axis of the main shaft (1). A first connecting rod structure (6) is hinged on the swashplate assembly (4). The swashplate assembly (4) is hinged to the rotor assembly (3) through the first connecting rod structure (6). The first connecting rod structure (6) is used to drive the rotor assembly (3) to rotate; The outer wall of the tilter assembly (4) is also hinged with a connector (5), which is used to drive the tilter assembly (4) to move along the axis of the main shaft (1); One end of the connector (5) is hinged to the tilter assembly (4), and the other end is hinged to a limiting member (12). The limiting member (12) is used to restrict the horizontal movement of the connector (5). A second link structure (7) is fixedly connected below the connector (5). The second link structure (7) is used to drive the connector (5) to work. The connector (5) is connected to a servo motor (8) through the second link structure (7). The servo motor (8) is used to drive the second link structure (7) to work.

2. The rotor system of a UAV according to claim 1, characterized in that, The tilter assembly (4) includes a tilt follower disk (41), the bottom of which is connected to a tilt disk (42). The tilt follower disk (41) includes symmetrically arranged first hinge portions (411), each of which is hinged to a first link structure (6).

3. The rotor system of a UAV according to claim 2, characterized in that, The first linkage structure (6) includes a first pull rod (61), one end of which is hinged to the first hinge part (411), and the other end is hinged to a first rocker arm (62). The end of the first rocker arm (62) away from the first pull rod (61) is hinged to the rotor assembly (3).

4. The rotor system of a UAV according to claim 3, characterized in that, The main shaft (1) has a rotating shaft (2) at one end near the rotor assembly (3), and the main shaft (1) is connected to the rotor assembly (3) through the rotating shaft (2).

5. The rotor system of a UAV according to claim 4, characterized in that, The rotor assembly (3) includes a rotor clip (31), which is rotatably connected to the rotating shaft (2), and a rotor (32) is hinged to one end of the rotor clip (31) away from the rotating shaft (2).

6. The rotor system of a UAV according to claim 5, characterized in that, The connector (5) includes an opening (51), the inner wall of which is hinged to the outer wall of the tilting disk (42), and the connector (5) also includes a second hinge (52), which is hinged to the limiting member (12).

7. The rotor system of a UAV according to claim 6, characterized in that, The second linkage structure (7) includes a second pull rod (71), one end of which is fixedly connected to the side of the connector (5) away from the rotor assembly (3), and the other end is hinged to a second rocker arm (72), the end of which is away from the second pull rod (71) and connected to the output end of the servo motor (8).

8. A drone, characterized in that, The rotor system of the unmanned aerial vehicle (UAV) as described in any one of claims 1-7 further includes a wing (9), the rotor system of the UAV being connected to the wing (9).

9. A drone according to claim 8, characterized in that, The limiting member (12) is fixedly connected to the wing (9).

10. A drone according to claim 8, characterized in that, The drone also includes a fuselage (11), and the wings (9) are connected to the fuselage (11). The wings (9) are four in number and symmetrically arranged on both sides of the fuselage (11).

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