阅读说明：本技术 旋翼组件及无人飞行器 (Rotor subassembly and unmanned vehicles ) 是由 杨健 于 2018-11-21 设计创作，主要内容包括：本申请公开了一种旋翼组件及无人飞行器,包括第一螺旋桨(40)、第一电机(30)、第二螺旋桨(60)及第二电机(50),第一螺旋桨(40)设有第一锁接部,第二螺旋桨(60)设有第二锁接部,第一锁接部与第二锁接部不同,以防止第一螺旋桨(40)安装在第二电机(50)上或防止第二螺旋桨(60)安装在第一电机(30)上。(The application discloses rotor subassembly and unmanned vehicles, including first screw (40), first motor (30), second screw (60) and second motor (50), first screw (40) are equipped with first locking portion, and second screw (60) are equipped with second locking portion, and first locking portion is different with second locking portion to prevent that first screw (40) from installing on second motor (50) or prevent that second screw (60) from installing on first motor (30).)

1. A rotor assembly for an unmanned aerial vehicle, the unmanned aerial vehicle including a body and a plurality of with body fixed connection's horn, characterized in that the rotor assembly includes:

the first motor is arranged at one end of the machine arm;

the first propeller is provided with a first locking part and is used for being detachably connected with the first motor;

the second motor is arranged at one end of the machine arm;

the second propeller is provided with a second locking part and is detachably connected with the second motor;

wherein the first locking portion is different from the second locking portion to prevent the first propeller from being mounted on the second motor or to prevent the second propeller from being mounted on the first motor.

2. A rotor assembly according to claim 1, wherein a fool-proof structure is provided on the first rotor for preventing the first rotor from being mounted on the second motor.

3. A rotor assembly according to claim 2, wherein the fool-proofing structure is located above the first locking portion.

4. A rotor assembly according to claim 3, wherein the fool-proofing structure is cylindrical for resisting a stop of the main body of the unmanned aerial vehicle to prevent the first propeller from being mounted on the second motor.

5. A rotor assembly according to claim 4, wherein the fool-proofing structure has a notch for cooperating with the stop to prevent the second motor from driving the first rotor to rotate.

6. A rotor assembly according to any one of claims 1-5, wherein the first locking portion comprises a first latch portion, the first motor is provided with a first latch portion that mates with the first latch portion, and the first latch portion is latched with the first latch portion; or

The second locking part comprises a second clamping groove part, a second clamping part matched with the second clamping groove part is arranged on the second motor, and the second clamping part is clamped with the second clamping groove part.

7. The rotor assembly according to claim 6, wherein the second locking portion includes a second locking portion, and the second motor is provided with a second locking groove portion matching with the second locking portion, and the second locking groove portion is locked with the second locking portion and the second locking groove portion.

8. A rotor assembly according to claim 7, wherein the first catch portion is shaped differently than the second catch portion; or the number of the first buckling parts is different from that of the second buckling parts.

9. A rotor assembly according to claim 8, wherein the number of second catches is greater than the number of first catches to prevent the second propeller from being mounted on the first motor.

10. A rotor assembly according to claim 9,

the first propeller comprises a first propeller hub and a first blade connected to the first propeller hub, and the first buckling part is arranged on the first propeller hub.

The second propeller comprises a second propeller hub and a second blade connected to the second propeller hub, and the second buckling part is arranged on the second propeller hub.

11. A rotor assembly according to claim 10, wherein the first catch comprises:

the first convex part is convexly arranged on the first propeller hub;

the first clamping part is bent and extended from one end, far away from the first propeller hub, of the first convex part, and the cross section of the first clamping part is of a fan-shaped structure;

the first convex part is perpendicular to the first hub, and the first clamping part is perpendicular to the first convex part.

12. A rotor assembly according to claim 11, wherein the second catch portion is of the same construction as the first catch portion.

13. A rotor assembly according to claim 6, wherein the first slot portion comprises:

the first guide groove is formed in the first motor;

the first locking groove is formed at the tail end of the first guide groove, the shape of the first locking groove is matched with that of the first clamping part, and the first clamping part is clamped with the first locking groove;

the first locking groove is perpendicular to the first guide groove, the first guide groove is parallel to a driving shaft of the first motor, and a first stop block is arranged at the joint of the first guide groove and the first locking groove and used for fixing the first clamping portion.

14. A rotor assembly according to claim 13, wherein the second slot portion has the same structure as the first slot portion.

15. A rotor assembly according to any one of claims 7-14, further comprising:

and the elastic pieces are respectively arranged on the first motor and the second motor and are respectively matched with the first locking part and the second locking part.

16. A rotor assembly according to claim 15,

the first motor comprises a first rotating shaft and a first rotor shell, the first rotor shell rotates together with the first motor when the first motor works, and the elastic piece is arranged on the first rotating shaft.

The second motor comprises a second rotating shaft and a second rotor shell, the second rotating shaft and the second rotor shell rotate together when the second motor works, and the elastic piece is arranged on the first rotating shaft.

17. A rotor assembly according to claim 6, wherein the first locking portion includes a first slot portion, the first motor is provided with a first locking portion matching with the first slot portion, and the first locking portion is locked with the first slot portion.

18. An unmanned aerial vehicle, comprising:

a main body;

a plurality of arms fixedly connected with the main body;

the first motor is arranged at one end of the machine arm;

the first propeller is provided with a first locking part and is used for being detachably connected with the first motor;

the second motor is arranged at one end of the machine arm;

the second propeller is provided with a second locking part and is detachably connected with the second motor;

wherein the first locking portion is different from the second locking portion to prevent the first propeller from being mounted on the second motor or to prevent the second propeller from being mounted on the first motor.

19. The UAV of claim 18 wherein the first propeller is provided with a fool-proof structure for preventing the first propeller from being mounted on the second motor.

20. The UAV of claim 19 wherein the fool-proof structure is located above the first lock.

21. The UAV of claim 20 wherein the fool-proof structure is cylindrical, and the body has an abutment on a side thereof adjacent to the second motor, the abutment cooperating with the fool-proof structure to prevent the first propeller from being mounted on the second motor.

22. The UAV of claim 21 wherein the fool-proof structure has a notch for engaging the stop to prevent the second motor from driving the first propeller.

23. The unmanned aerial vehicle of any one of claims 18-22, wherein the first locking portion comprises a first latch portion, the first motor is provided with a first latch portion matching the first latch portion, and the first latch portion is latched with the first latch portion; or

The second locking part comprises a second clamping groove part, a second clamping part matched with the second clamping groove part is arranged on the second motor, and the second clamping part is clamped with the second clamping groove part.

24. The unmanned aerial vehicle of claim 23, wherein the second locking portion comprises a second locking portion, the second motor is provided with a second slot portion matched with the second locking portion, and the second slot portion is locked with the second locking portion and the second slot portion.

25. The UAV of claim 24 wherein the first and second snap-fit portions are shaped differently; or the number of the first buckling parts is different from that of the second buckling parts.

26. The UAV of claim 25 wherein the number of second detents is greater than the number of first detents to prevent the second propeller from being mounted on the first motor.

27. A rotor assembly according to claim 26,

the first propeller comprises a first propeller hub and a first blade connected to the first propeller hub, and the first buckling part is arranged on the first propeller hub.

The second propeller comprises a second propeller hub and a second blade connected to the second propeller hub, and the second buckling part is arranged on the second propeller hub.

28. The UAV of claim 27 wherein the first clasp comprises:

the first convex part is convexly arranged on the first propeller;

the first clamping part is bent and extended from one end, far away from the first propeller, of the first convex part, and the cross section of the first clamping part is of a fan-shaped structure;

the first convex part is perpendicular to the first propeller, and the first clamping part is perpendicular to the first convex part.

29. The UAV of claim 28 wherein the second latch portion is identical in structure to the first latch portion.

30. The UAV of claim 23 wherein the first slot portion comprises:

the first guide groove is formed in the first motor;

the first locking groove is formed at the tail end of the first guide groove, the shape of the first locking groove is matched with that of the first clamping part, and the first clamping part is clamped with the first locking groove;

the first locking groove is perpendicular to the first guide groove, the first guide groove is parallel to a driving shaft of the first motor, and a first stop block is arranged at the joint of the first guide groove and the first locking groove and used for fixing the first clamping portion.

31. The UAV of claim 30 wherein the second slot portion is structurally identical to the first slot portion.

32. The unmanned aerial vehicle of any of claims 24-31, wherein the rotor assembly further comprises:

and the elastic pieces are respectively arranged on the first motor and the second motor and are respectively matched with the first locking part and the second locking part to respectively fix the first propeller and the second propeller.

33. The UAV according to claim 32,

the first motor comprises a first driving shaft and a first rotor shell, the first rotating shaft and the first rotor shell rotate together when the first motor works, and the elastic piece is arranged on the first rotating shaft.

The second motor comprises a second rotating shaft and a second rotor shell, the second rotating shaft and the second rotor shell rotate together when the second motor works, and the elastic piece is arranged on the second rotating shaft.

34. The unmanned aerial vehicle of claim 23, wherein the first locking portion comprises a first slot portion, the first motor is provided with a first buckling portion matched with the first slot portion, and the first buckling portion is buckled with the first slot portion.

Technical Field

The application relates to the technical field of flight, especially, relate to a rotor subassembly and unmanned vehicles.

Background

The multi-rotor unmanned aerial vehicle generally drives a propeller to rotate through a motor to generate power, so that space flight is realized. The portable multi-rotor unmanned aerial Vehicle comprises UAVs (unmanned aerial vehicles) and the like which complete flight by ground remote control and other control modes, and the unmanned aerial Vehicle is relatively low in cost, can provide light, flexible and low-altitude and low-speed flight, and is widely applied to various civil fields, particularly various fields such as geographical mapping and aerial photography.

The rotor assemblies of multi-rotor unmanned aerial vehicles typically include propellers and motors that rotate the propellers to provide rotational power. Traditional connected mode between motor and the screw adopts thread tightening or buckle connection fixed etc. however, because the motor on the unmanned vehicles of many rotors has clockwise rotation and anticlockwise rotation two kinds of directions, consequently need have the screw of two kinds of structure symmetries respectively with clockwise rotation's motor and anticlockwise rotation's motor pair and use. And the use user of unmanned vehicles often need to dismantle and install the screw, but many ordinary users can't accurately distinguish clockwise rotation's screw and anticlockwise rotation's screw, often can appear the wrong problem of adorning the screw, leads to unmanned vehicles unable normal work, can appear danger such as exploding even.

Disclosure of Invention

In view of this, this application provides a rotor subassembly and unmanned vehicles that easily dismantles and have prevent slow-witted function.

According to a first aspect of embodiments of the present application, there is provided a rotor assembly for an unmanned aerial vehicle, the unmanned aerial vehicle including a main body and a plurality of arms fixedly connected to the main body, the rotor assembly comprising:

the first motor is arranged at one end of the machine arm;

the first propeller is provided with a first locking part and is used for being detachably connected with the first motor;

the second motor is arranged at one end of the machine arm;

the second propeller is provided with a second locking part and is detachably connected with the second motor;

wherein the first locking portion is different from the second locking portion to prevent the first propeller from being mounted on the second motor or to prevent the second propeller from being mounted on the first motor.

According to a second aspect of embodiments of the present application, there is provided an unmanned aerial vehicle including:

a main body;

a plurality of arms fixedly connected with the main body;

the first motor is arranged at one end of the machine arm;

the first propeller is provided with a first locking part and is used for being detachably connected with the first motor;

the second motor is arranged at one end of the machine arm;

the second propeller is provided with a second locking part and is detachably connected with the second motor;

wherein the first locking portion is different from the second locking portion to prevent the first propeller from being mounted on the second motor or to prevent the second propeller from being mounted on the first motor.

The technical scheme provided by the embodiment of the application can have the following beneficial effects: the application designs a rotor subassembly and unmanned vehicles, this rotor subassembly includes first motor, first screw, second motor and second screw, wherein, be equipped with first locking portion on the first screw, the second screw is equipped with the second locking portion different with first locking portion, not only can be through first locking portion and/or second locking portion, install first screw on first motor fast and/or install the second screw on the second motor fast, and also can prevent that first screw from installing on the second motor or the second screw is installed on first motor, thereby the wrong problem of screw dress can not appear, ensure that unmanned vehicles can normally work.

It is to be understood that both the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the application.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the description of the embodiments are briefly introduced below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.

FIG. 1 is a schematic structural diagram of an unmanned aerial vehicle provided by an embodiment of the present application;

FIG. 2 is a top view of the unmanned aerial vehicle provided in FIG. 1;

FIG. 3 is a cross-sectional view of the UAV provided in FIG. 1;

FIG. 3a is an enlarged view of a portion of FIG. 3 at A;

FIG. 3B is an enlarged view of a portion of FIG. 3 at B;

FIG. 4 is a schematic view of the first propeller provided in FIG. 1;

FIG. 5 is a schematic view of the first electric machine provided in FIG. 1;

fig. 6 is a schematic view of the structure provided in fig. 1 in which the elastic member is mounted on the first motor;

FIG. 7 is a schematic view of the second propeller provided in FIG. 1;

FIG. 8 is a schematic diagram of the structure of the second electric machine provided in FIG. 1;

FIG. 9 is a schematic view of the elastic member provided in FIG. 1 mounted on a second motor;

FIG. 10 is a schematic view of the structure of FIG. 1 in which the first propeller is mounted on the second motor

FIG. 11 is a schematic view of a first propeller according to yet another embodiment of the present application;

fig. 12 is a schematic structural diagram of a first electric machine according to yet another embodiment of the present application;

FIG. 13 is a schematic view of a second propeller according to yet another embodiment of the present application;

fig. 14 is a schematic structural diagram of a second motor according to yet another embodiment of the present application.

Description of reference numerals:

100. a rotor assembly;

10. a main body;

20. a horn; 21. a first arm; 22. a second arm;

30. a first motor; 31. a first slot part; 31a, a third buckling part; 311. a first guide groove; 312. a first locking groove; 313. a first stopper; 32. a first rotor shell; 33. a first rotating shaft;

40. a first propeller; 41. a first fastening part; 411. a first convex portion; 412. a first engaging portion; 41a, a third slot part; 42. a first hub; 43. a first blade; 44. a first transmission hole; 441. a first groove; 45. a fool-proof structure; 451. a notch;

50. a second motor; 51. a second slot portion; 51a and a fourth buckling part; 511. a second guide groove; 512. a second locking groove; 513. a second stopper; 52. a second rotor case; 53. a second rotating shaft;

60. a second propeller; 61. a second fastening part; 611. a second convex portion; 612. a second engaging portion; 61a, a fourth bayonet portion; 62. a second hub; 63. a second blade; 64. a second drive aperture; 641. a second groove;

70. a stop member;

80. an elastic member.

Detailed Description

The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are some, but not all, embodiments of the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.

Some embodiments of the present application will be described in detail below with reference to the accompanying drawings. The embodiments described below and the features of the embodiments can be combined with each other without conflict.

The utility model provides an unmanned vehicles's rotor subassembly generally includes the screw and drives the motor that the screw rotates in order to provide rotary power, because the motor on the unmanned vehicles of many rotors has clockwise rotation and two kinds of directions of anticlockwise rotation, installs the screw on the motor and also includes the screw of two kinds of structural symmetry, pairs the use with clockwise rotation's motor and anticlockwise rotation's motor respectively. In general, a common user cannot accurately distinguish a clockwise rotating propeller from a counterclockwise rotating propeller, and often the problem of mistakenly assembling the propellers occurs, so that the unmanned aerial vehicle cannot normally work, and even danger such as explosion can occur. Therefore, the application provides a reasonable design, which can effectively solve the problems.

As shown in fig. 1 to 9, an embodiment of the present application provides an unmanned aerial vehicle that may include a body 10, a plurality of horn 20 fixedly connected to the body 10, and a rotor assembly 100 mounted on the horn 20. Rotor assembly 100 includes a first motor 30, a number of first propellers 40 matching first motor 30, a second motor 50, and a number of second propellers 60 matching second motor 50. The first motor 30 and the second motor 50 are different in rotation direction, and the first propeller 40 and the second propeller 60 are symmetrical to each other in structure. There is no limitation on the number of the first motor 30, the first propeller 40, the second motor 50, and the second propeller 60.

In this embodiment, the first propeller 40 is provided with a first locking portion, the first propeller 40 is detachably connected with the first motor 30 through the first locking portion, and the first motor 30 is installed on one end of one of the arms 20; the second propeller 60 is provided with a second locking portion, the second propeller 60 is detachably connected to the second motor 50 through the second locking portion, the second motor 50 is installed at one end of the other arm 20, and the first locking portion is different from the second locking portion in order to prevent the first propeller 40 from being installed at the second motor 50 or the second propeller 60 from being installed at the first motor 30.

Specifically, as shown in fig. 2, the horn 20 is dispersedly disposed on the circumferential side of the body 10 in a radial form, and the number of the horn 20 is not limited. The sum of the number of the first motors 30 and the number of the second motors 50 matches the number of the horn 20, in this embodiment, the number of the horns 20 is four, and there are two first horns 21 and two second horns 22, respectively, and the two first horns 21 and the two second horns 22 are arranged at intervals and are arranged on the peripheral side of the main body 10 in a cross-symmetry manner. The two first motors 30 are respectively disposed on ends of the two first arms 21 far away from the main body 10, and the two second motors 50 are respectively disposed on ends of the two second arms 22 far away from the main body 10.

As shown in fig. 1 to 4, as a further improved technical solution, a fool-proof structure 45 is further provided on the first propeller 40. In one aspect, fool-proofing structure 45 may ensure an accurate interface between first rotor 40 and first motor 30 when rotor assembly 100 is assembled. On the other hand, the fool-proof structure 45 can prevent the first propeller 40 and the second motor 50 from being reversely mounted, so as to improve the assembly accuracy and reliability, and further ensure that the unmanned aerial vehicle can normally work.

Specifically, as shown in fig. 1 and 4, the fool-proof structure 45 may be any structure, for example, a boss, a sheet structure, or a corner is designed by fillet processing, and the position of the fool-proof structure 45 is not limited, in this embodiment, the fool-proof structure 45 is located above the first locking portion, which not only facilitates the molding design of the first propeller 40, but also saves the manufacturing cost of the rotor assembly 100.

As shown in fig. 1, 10-11, in an alternative embodiment, the fool-proof structure 45 is in a column shape, such as a cylinder, a square column or other irregular column shape. Wherein, a stop member 70 is disposed on one side of the main body 10 close to the second motor 50; when the first propeller 40 is assembled with the second motor 50 through the first locking portion, the end of the abutting member 70 far away from the horn 20 abuts against the fool-proof structure 45 to limit the first propeller 40 from advancing toward the horn 20, so that the first propeller 40 cannot be locked on the second motor 50, thereby playing the fool-proof role.

As shown in fig. 4 and 10, in another alternative embodiment, the fool-proof structure 45 is provided with two notches 451, the number and the positions of the notches 451 are not limited, in this embodiment, the two notches 451 are symmetrically disposed on two sides of the fool-proof structure 45, and the notches 451 are adapted to the width of the stopper 70. When the first propeller 40 is assembled with the second motor 50 through the first locking portion, if the first propeller 40 can be directly locked on the second motor 50 through the first locking portion, but the gap 451 is matched with the blocking member 70, the first propeller 40 cannot rotate, that is, the second motor 50 cannot drive the first propeller 40 to rotate, and the unmanned aerial vehicle cannot normally operate. It can be understood that if the first locking portion needs to be rotated to be locked on the second motor 50, the first propeller 40 cannot be attached to the second motor 50, i.e., the unmanned aerial vehicle cannot operate normally. Of course, the specific arrangement of the fool-proof structure 45 is not limited to the above-mentioned example, and other feasible arrangements are also protected by the present solution, which are not listed here.

As shown in fig. 4 to 8, in an alternative embodiment, the first locking portion includes a first latching portion 41, the first motor 30 is provided with a first latching portion 31, and the first latching portion 31 matches with the first latching portion 41; the second locking portion includes a second locking portion 61, the second motor 50 is provided with a second locking slot portion 51, and the second locking slot portion 51 matches with the second locking portion 61. The first locking portion 41 and the second locking portion 61 have different structures or numbers, and are used for preventing the fool-proof function, so that the first propeller 40 is prevented from being mounted on the second motor 50 or the second propeller 60 is prevented from being mounted on the first motor 30. For example, the first engaging portion 41 and the second engaging portion 61 have different shapes; or the first buckling part 41 and the second buckling part 61 are different in height; or the first buckling part 41 and the second buckling part 61 are different in size; or the number of the first buckling parts 41 is different from that of the second buckling parts 61, and the like.

In an alternative embodiment, the number of the second catching portions 61 is greater than the number of the first catching portions 41 to prevent the second propeller 60 from being mounted on the first motor 30. For example, the number of the first locking portions 41 is two, two first locking portions 41 are arranged on the first propeller 40 at intervals, and the number of the first locking groove portions 31 matches the number of the first locking portions 41. The number of the second fastening parts 61 is four, the four second fastening parts 61 are arranged on the second propeller 60 in an annular array, and the number of the second fastening parts 51 is matched with that of the second fastening parts 61. Of course, the present application does not limit the case where the number of the second locking portions 61 is smaller than the number of the first locking portions 41.

During assembly, the first propeller 40 is firstly installed in the first slot part 31 of the first motor 30 along the first buckling part 41, and then the first propeller 40 is rotated to enable the first buckling part 41 to be buckled in the first slot part 31; similarly, the second propeller 60 is first mounted in the second slot 51 of the second motor 50 along the second locking portion 61, and then the second propeller 60 is rotated so that the first locking portion 41 is locked in the second slot 51, thereby mounting the second propeller 60 on the second motor 50. In contrast, if the first propeller 40 is assembled with the second motor 50, since the number of the first catching portions 41 is two and the number of the second catching groove portions 51 is four, the first propeller 40 can be mounted on the second motor 50 through the first catching portions 41. However, the fool-proof structure 45 is disposed on the first propeller 40, and the main body 10 is disposed with the stopper 70 on a side close to the second motor 50, so that the first propeller 40 can be prevented from being mounted on the second motor 50 or the second motor 50 can not drive the first propeller 40 to rotate. If the second screw 60 is assembled with the first motor 30, the second screw 60 cannot be locked on the first motor 30 because the number of the second locking portions 61 is four and the number of the first locking groove portions 31 is two.

Specifically, as shown in fig. 4, the first locking portion 41 has a substantially hook-shaped structure, and includes a first protrusion 411 and a first engaging portion 412. The first protrusion 411 is disposed on the first propeller 40 in a protruding manner, and the first engaging portion 412 is bent and extended from the first protrusion 411 at an end away from the first propeller 40. The cross section of the first engaging portion 412 is a fan-shaped structure, in this embodiment, the first protrusion 411 is perpendicular to the first propeller 40, and the first engaging portion 412 is perpendicular to the first protrusion 411, which not only facilitates the molding design of the first engaging portion 41, but also does not require a threaded hole with high precision, and is easy to operate.

As shown in fig. 7, the second locking portion 61 has the same structure as the first locking portion 41, and includes a second convex portion 611 and a second engaging portion 612. The second protrusion 611 is disposed on the second propeller 60 in a protruding manner, and the second engaging portion 612 is bent and extended from the second protrusion 611 at an end away from the second propeller 60. The second engaging portion 612 has a fan-shaped cross section. In the present embodiment, the second protrusion 611 is perpendicular to the second propeller 60, and the second engaging portion 612 is perpendicular to the second protrusion 611, which not only facilitates the molding design of the second locking portion 61, but also does not require a high-precision threaded hole, and the operation requirement is simple.

In an alternative embodiment, as shown in fig. 4 and 7, the first propeller 40 includes a first hub 42 and a first blade 43, the first blade 43 being attached to the first hub 42. The second propeller 60 includes a second hub 62 and a second blade 63, the second blade 63 being attached to the second hub 62. In the present embodiment, the first fastening portion 41 is disposed on the first hub 42, and the second fastening portion 61 is disposed on the second hub 62, so that the first fastening portion 41, the first hub 42 and the first blade 43 can be conveniently formed integrally, and the second fastening portion 61, the second hub 62 and the second blade 63 can be conveniently formed integrally, thereby saving a large amount of processing cost. Of course, two of the first latch portion 41, the first hub 42, or the first blade 43 may be integrally formed, and two of the second latch portion 61, the second hub 62, or the second blade 63 may be integrally formed, which is not limited in the present application.

As shown in fig. 4 and 7, the first protrusion 411 is provided to protrude from the first hub 42, and the second protrusion 611 is provided to protrude from the second hub 62. In this embodiment, the inner and outer walls of the first protrusion 411 are arc-shaped, so that the first engaging portion 412 can rotate and engage with the first engaging groove 31. The inner and outer walls of the second protrusion 611 are arc-shaped, so that the second engaging portion 612 can rotate and engage with the second groove 51.

As shown in fig. 1 to 2, 5, and 8, the first motor 30 includes a first rotor case 32 and a first rotation shaft 33. The first rotating shaft 33 and the first rotor case 32 rotate together when the first motor operates, and are located at an end of the first arm 21. The second motor 50 includes a second rotor case 52 and a second rotation shaft 53, and the second rotation shaft 53 and the second rotor case 52 rotate together when the second motor operates and are located at an end of the second horn 22.

As shown in fig. 5, the first bayonet groove portion 31 includes a first guide groove 311 and a first locking groove 312, and the first guide groove 311 is opened on the first motor 30. Specifically, the first locking groove 312 is formed at the end of the first guide groove 311, and has a shape that matches the shape of the first engaging portion 412. In this embodiment, a first stopper 313 is further included, the first locking groove 312 is perpendicular to the first guide groove 311, the first guide groove 311 is parallel to the first rotation shaft 33, and the first stopper 313 is disposed at the junction of the first guide groove 311 and the first locking groove 312.

As shown in fig. 4 to 5, when the first propeller 40 and the first motor 30 are assembled, the first engaging portion 412 is first placed in the first guide slot 311, and then the first propeller 40 is rotated around the first rotating shaft 33, so that the first engaging portion 412 passes through the first stopper 313 and is engaged with the first locking slot 312, wherein the first stopper 313 is used for fixing the first engaging portion 412 on the first locking slot 312 and preventing the first engaging portion 412 from slipping out of the first locking slot 312.

As shown in fig. 8, the second engagement portion 51 has the same structure as the first engagement portion 31, the second engagement portion 51 includes a second guide groove 511 and a second locking groove 512, the second guide groove 511 is formed on the second motor 50, and the second locking groove 512 is formed at the end of the second guide groove 511 and has a shape matching the shape of the second engagement portion 612. In this embodiment, a second stopper 513 is further included, the second locking groove 512 is perpendicular to the second guiding groove 511, the second guiding groove 511 is parallel to the second rotating shaft 53, and the second stopper 513 is disposed at the junction of the second guiding groove 511 and the second locking groove 512.

As shown in fig. 7 to 8, when the second propeller 60 is assembled with the second motor 50, the second engaging portion 612 is first placed in the second guide slot 511, and then the second propeller 60 is rotated around the second rotating shaft 53, so that the second engaging portion 612 passes through the second stopper 513 and is engaged with the second locking slot 512, wherein the second stopper 513 is used for fixing the second engaging portion 612 on the second locking slot 512 and preventing the second engaging portion 612 from slipping out of the second locking slot 512.

As shown in fig. 3 to 8, in the present embodiment, the first propeller 40 is further provided with a first transmission hole 44, the first transmission hole 44 is provided at the center of the first hub 42, and the first protrusion 411 is provided outside the first transmission hole 44. When the first propeller 40 is assembled with the first motor 30, the first rotating shaft 33 is mounted on the first transmission hole 44. The second propeller 60 is further provided with a second transmission hole 64, the second transmission hole 64 is provided at the center of the second hub 62, a second protrusion 611 is provided outside the second transmission hole 64, and the second rotary shaft 53 is mounted on the second transmission hole 64 when the second propeller 60 is assembled with the second motor 50.

As shown in fig. 3-9, in an alternative embodiment, rotor assembly 100 further includes a plurality of resilient members 80. In the present embodiment, the elastic member 80 is a spring, the two springs are respectively sleeved on the first rotating shaft 33 and the second rotating shaft 53, the first hub 42 is provided with a first groove 441, the outer dimension of the first groove 441 is matched with the outer diameter of the spring, and the first groove 441 is coaxial with the first transmission hole 44. The second hub 62 is provided with a second groove 641, the outer dimension of the second groove 641 is matched with the outer diameter of the spring, and the second groove 641 is coaxial with the second transmission hole 64.

As shown in fig. 3 to 9, when the first propeller 40 is assembled with the first motor 30, after the first engaging portion 412 is placed in the first guide groove 311, one end of the elastic member 80 abuts against the end surface of the first motor 30, the other end of the elastic member 80 abuts against the bottom of the first groove 441, and the first propeller 40 is rotated in the direction of the first lock groove 312 while pressing the first propeller 40 downward. When the first engaging portion 412 rotates to a position below the first locking groove 312, the first propeller 40 is released, and the first propeller 40 moves upward by the elastic force of the elastic member 80 and is engaged with the first locking groove 312.

When detaching, the first propeller 40 is pressed downward such that the first engaging portion 412 is positioned below the first locking groove 312, the first engaging portion 412 is released from the connection with the first stopper 313, and the first propeller 40 is rotated in the direction of the first guide groove 311. When the first engaging portion 412 is positioned in the first guide groove 311, the first propeller 40 is released, and the first propeller 40 can be taken out from the first motor 30.

Similarly, the assembling and disassembling processes of the second propeller 60 and the second motor 50 are the same as the above principle, and are not described again.

As shown in fig. 7 to 8, 11 and 12, in a further alternative embodiment, the first locking portion includes a third slot portion 41a, a third latching portion 31a is provided on the first motor 30, and the third latching portion 31a matches with the third slot portion 41 a. The second locking portion includes a second locking portion 61, the second motor 50 is provided with a second locking slot portion 51, the second locking slot portion 51 is matched with the second locking portion 61, wherein the shape of the third locking slot portion 41a is different from the shape of the second locking portion 61, so that the fool-proof effect is achieved. It can be understood that the third latching portion 31a, the second latching portion 61, the third latching portion 41a and the second latching portion 51 can all adopt the above structure, and the third latching portion 31a can have the same number as the second latching portion 61, which is not described herein again.

As shown in fig. 11 to 14, in a further alternative embodiment, the first locking portion includes a third slot portion 41a, a third buckling portion 31a is provided on the first motor 30, and the third buckling portion 31a matches with the third slot portion 41 a; the second locking portion includes a fourth latching portion 61a, the second motor 50 is provided with a fourth latching portion 51a, and the fourth latching portion 51a matches with the fourth latching portion 61 a. The third slot portion 41a and the fourth slot portion 61a have different structures or numbers, and are used for foolproof function, so as to prevent the first propeller 40 from being mounted on the second motor 50 or the second propeller 60 from being mounted on the first motor 30. For example, the third and fourth bayonet portions 41a, 61a are of different shapes; or the third and fourth bayonet portions 41a, 61a are of different depths; or the third and fourth bayonet portions 41a, 61a are of different sizes; or the number of the third slot portion 41a is different from that of the fourth slot portion 61a, and so on, which are the same as the above principle, and are not described herein again.

Referring to fig. 1 to 14, an embodiment of the present application further provides a rotor assembly 100, where the rotor assembly 100 is used for an unmanned aerial vehicle, where the unmanned aerial vehicle includes a main body 10 and a plurality of booms 20 fixedly connected to the main body 10, the rotor assembly 100 includes a first propeller 40, a first motor 30 mounted at an end of the booms 20, a second propeller 60, and a second motor 50 mounted at an end of the booms 20, in this embodiment, the first propeller 40 is provided with a first locking portion as described above, and the second propeller 60 is provided with a second locking portion as described above; when rotor assembly 100 is assembled, first propeller 40 is prevented from being mounted on second motor 50 or second propeller 60 is prevented from being mounted on first motor 30, and will not be described in detail herein.

While the invention has been described with reference to specific embodiments, the scope of the invention is not limited thereto, and those skilled in the art can easily conceive various equivalent modifications or substitutions within the technical scope of the invention. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.