CN108834430B

CN108834430B - Be applied to unmanned vehicles's motor structure, power component and unmanned vehicles

Info

Publication number: CN108834430B
Application number: CN201780015478.3A
Authority: CN
Inventors: 李忠洪; 陶志杰; 颜学力
Original assignee: SZ DJI Technology Co Ltd
Current assignee: SZ DJI Technology Co Ltd
Priority date: 2017-11-30
Filing date: 2017-11-30
Publication date: 2021-06-22
Anticipated expiration: 2037-11-30
Also published as: WO2019104646A1; CN108834430A

Abstract

A motor structure, a power assembly and an unmanned aerial vehicle applied to the unmanned aerial vehicle relate to the technical field of the unmanned aerial vehicle, the motor structure applied to the unmanned aerial vehicle comprises a stator (1), a rotor (2) and a bearing system (3) movably connected with the stator (1) and the rotor (2), and is characterized by further comprising buckle structures (4 and 5) for bearing axial load of the motor, wherein the buckle structures (4 and 5) and a base (11) of the stator (1) are fixed and clamp a rotating shaft (21) of the rotor (2); the bearing system (3) comprises at least one plain bearing (32) for taking up the axial load of the electrical machine; the axial stress balance of the motor is facilitated, and the axial movement of the rotating shaft (21) is prevented.

Description

Be applied to unmanned vehicles's motor structure, power component and unmanned vehicles

Technical Field

The technical scheme that this application is disclosed relates to unmanned vehicles technical field, especially relates to motor structure, power component and unmanned vehicles who is applied to unmanned vehicles.

Background

At present, the unmanned aerial vehicle can drive a rotor wing through a motor to provide lift force for flying.

In the process of researching the application, the inventor finds that the motor applied to the unmanned aerial vehicle in the prior art can only bear radial load, or the axial play of the rotating shaft of the motor is obvious.

Disclosure of Invention

The technical scheme disclosed by the application can at least solve the following technical problems: the motor applied to the unmanned aerial vehicle can only bear radial load, or the axial play of the rotating shaft of the motor is obvious.

One or more embodiments of the application disclose a motor structure applied to an unmanned aerial vehicle, which comprises a stator, a rotor, a bearing system movably connecting the stator and the rotor, and a buckle structure bearing the axial load of the motor, wherein the buckle structure is fixed with a base of the stator and clamps a rotating shaft of the rotor; the bearing system comprises at least one plain bearing for taking up the axial load of the electrical machine.

One or more embodiments of the present application disclose a power assembly applied to an unmanned aerial vehicle, including an electronic governor and a plurality of rotors, and a motor structure applied to an unmanned aerial vehicle, controlled by the electronic governor and driving the plurality of rotors to rotate, the motor structure applied to an unmanned aerial vehicle includes a stator, a rotor, and a bearing system movably connecting the stator and the rotor, and is characterized by further including a buckle structure bearing an axial load of the motor, the buckle structure being fixed with a base of the stator and clamping a rotating shaft of the rotor; the bearing system comprises at least one plain bearing for taking up the axial load of the electrical machine.

One or more embodiments of the present application disclose an unmanned aerial vehicle, including the fuselage, connect in the power component of installing on horn and the horn on the fuselage, power component includes electronic governor and a plurality of rotor and by electronic governor control and drive a plurality of the rotor pivoted is applied to unmanned aerial vehicle's motor structure, be applied to unmanned aerial vehicle's motor structure and include stator, rotor and swing joint the bearing system of stator and rotor, its characterized in that still includes the buckle structure who bears the axial load of motor, the buckle structure with the base of stator is fixed and the card is held the pivot of rotor; the bearing system comprises at least one plain bearing for taking up the axial load of the electrical machine.

Compared with the prior art, the technical scheme disclosed by the application mainly has the following beneficial effects:

the motor structure applied to the unmanned aerial vehicle comprises a stator, a rotor, a bearing system and a buckle structure, wherein the bearing system is movably connected with the stator and the rotor, the buckle structure is used for bearing the axial load of the motor, and the buckle structure is fixed with a base of the stator and clamps a rotating shaft of the rotor; the bearing system comprises at least one plain bearing for taking up the axial load of the electrical machine. The buckle structure can axially limit the rotating shaft and bear the axial load of the motor, so that the rotating shaft is prevented from moving in the axial direction. The sliding bearing of the bearing system bears most of the axial load of the motor, so that on one hand, the axial stress balance of the motor is favorably realized, and on the other hand, the axial movement of the rotating shaft is favorably prevented.

Drawings

FIG. 1 is an exploded view of a motor structure applied to an unmanned aerial vehicle in an embodiment of the present application;

fig. 2 is a schematic view illustrating an assembled structure of a fastening structure, a base and a rotating shaft according to an embodiment of the present disclosure;

FIG. 3 is a cross-sectional view of a motor structure applied to an UAV in an embodiment of the present application;

FIG. 4 is a cross-sectional view of a clip according to an embodiment of the present application;

FIG. 5 is an enlarged view of area I of FIG. 3;

FIG. 6 is a schematic view of a rotating shaft according to an embodiment of the present application;

FIG. 7 is a schematic cross-sectional view of a base in an embodiment of the present application;

fig. 8 is a partial sectional view of a motor structure applied to an unmanned aerial vehicle in another embodiment of the present application.

Description of the main reference numerals:

Detailed Description

To facilitate an understanding of the present application, the present application will now be described more fully with reference to the accompanying drawings. Preferred embodiments of the present application are shown in the drawings. This application may, however, be embodied in many different forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete.

Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs. The terminology used herein in the description of the present application is for the purpose of describing particular embodiments only and is not intended to be limiting of the application. The motor structure applied to the unmanned aerial vehicle, and the unmanned aerial vehicle, referred to in the detailed description are only preferred embodiments, and not all possible embodiments of the present application.

Referring to fig. 1, an exploded view of a motor structure applied to an unmanned aerial vehicle in an embodiment of the present application is shown. The motor structure applied to the unmanned aerial vehicle comprises a stator 1, a rotor 2 and a bearing system 3 movably connected with the stator 1 and the rotor 2. As illustrated in fig. 1, the motor structure applied to the unmanned aerial vehicle further includes a snap structure 4 for bearing an axial load of the motor, and the snap structure 4 is fixed to the base 11 of the stator 1 and retains the rotating shaft 21 of the rotor 2. The bearing system 3 comprises at least one plain bearing 32 for taking up the axial load of the electric machine.

The buckling structure 4 can axially limit the rotating shaft 21 and bear the axial load of the motor, so that the rotating shaft 21 is prevented from axially moving. The sliding bearing 32 of the bearing system 3 bears most of the axial load of the motor, which is beneficial to realizing the axial stress balance of the motor on one hand and preventing the rotating shaft 21 from moving in the axial direction on the other hand.

As illustrated in fig. 1, the base 11 is sheathed with a core 12 of the stator 1. An end cover 22 of the rotor 2 is connected with a rotating shaft 21 and a magnetic yoke 23, and a magnet 24 is arranged in the magnetic yoke 23. In an embodiment of the present application, the sliding bearing 32 may be an oil-impregnated bearing, a self-lubricating bearing, a liquid-lubricated bearing, or the like, which mainly bears an axial load.

Referring to fig. 1 to 7, fig. 2 is a schematic diagram illustrating an embodiment of the present disclosure after assembling the buckle structure 4 with the base 11 and the rotating shaft 21, fig. 3 is a cross-sectional view illustrating a motor structure applied to an unmanned aerial vehicle in an embodiment of the present disclosure, fig. 4 is a schematic cross-sectional view illustrating the buckle 41 in an embodiment of the present disclosure, fig. 5 is an enlarged view of a region i in fig. 3, fig. 6 is a schematic structural diagram illustrating the rotating shaft 21 in an embodiment of the present disclosure, and fig. 7 is a schematic cross-sectional view illustrating the base 11 in an embodiment of the present disclosure. The catch arrangement 4 comprises a first catch 41 and a second catch 42. As illustrated in fig. 2, the first catch 41 and the second catch 42 are spliced to form the catch structure 4. The first buckle 41 includes a fixing portion 411 and a retaining portion 412, the fixing portion 411 is fixed in the accommodating groove 112 of the base 11, and a portion of the retaining portion 412 is installed in the slot 211 of the rotating shaft 21.

The end cover 22 of the rotor 2 is provided with a connecting part 221 for connecting the rotating shaft 21, and the connecting part 221 abuts against the end surface of the bearing system 3 close to the bearing of the end cover 22, and the snap structure 4 and the connecting part 221 jointly define the axial gap of the rotating shaft 21. Since the snap structure 4 and the connecting portion 221 together define the axial gap of the rotating shaft 21, the axial play of the rotating shaft 21 will be further reduced.

The sliding bearing 32 is arranged at one end of the accommodating cavity 111 of the base 11 far away from the end cover 22 of the rotor 2, and the end part of the rotating shaft 21 extends beyond the end face of the sliding bearing 32.

The bearing system 3 further comprises at least one rotary bearing 31 for bearing the radial load of the motor, and the rotary bearing 31 is installed at one end of the accommodating cavity 111 close to the end cover 22. The end cover 22 is used for connecting the connecting portion 221 of the rotating shaft 21 to abut against the end surface of the slewing bearing 31.

As illustrated in fig. 2 to 4, the cross section of the fastening structure 4 is stepped, and the fixing portion 411 and the holding portion 412 are respectively fan-shaped. The inner ring 412a of the retaining part 412 is spaced from the surface of the slot 211, and the outer end surface 412b of the retaining part 412 far away from the base 11 abuts against the surface of the slot 211. As illustrated in fig. 5, a certain axial gap is left between the inner end surface 412c of the retaining portion 412 and the surface of the clamping groove 211, and the inner ring 412a of the retaining portion 412 is separated from the surface of the clamping groove 211 by the axial gap, which is beneficial to reducing the friction force between the retaining portion 412 and the clamping groove 211 and preventing the fastening structure 4 from excessively clamping the rotating shaft 21. The outer end surface 412b of the catch 412 abuts against the surface of the slot 211, so that the catch 412 can define an axial gap of the rotating shaft 21. Preferably, the second catch 42 is identical in construction to the first catch 41.

Preferably, the snap structure 4 is made of a friction and wear resistant material and is subjected to radial and axial deformation.

Referring to fig. 8, a partial cross-sectional view of a motor structure applied to an unmanned aerial vehicle in another embodiment of the present application is shown. Be applied to unmanned vehicles's motor structure's buckle structure 5 wholly is the ring form. The snap structure 5 comprises a first snap 51 and a second snap 52, and the first snap 51 and the second snap 52 are spliced to form the snap structure 5. The first buckle 51 is in a fan-ring shape as a whole. The fixing portion 511 and the holding portion 512 of the first buckle 51 are formed on the same plane. Preferably, the second buckle 52 is also in a fan-ring shape as a whole, and the fixing portion and the holding portion of the second buckle 52 are also formed on the same plane. It will be appreciated by those skilled in the art that other shapes of the snap structure are possible, and therefore, other modifications to the shape of the snap structure in accordance with the prior art and/or common general knowledge in the field are intended to fall within the scope of the present application.

An embodiment of this application discloses a power component for unmanned vehicles, including electronic governor and a plurality of rotor and by electronic governor control and drive is a plurality of the rotor pivoted is as above-mentioned any one be applied to unmanned vehicles's motor structure.

An embodiment of the application discloses unmanned vehicles, including the fuselage, connect in power component installed on horn and the horn on the fuselage, power component includes that above-mentioned arbitrary is applied to unmanned vehicles's motor structure.

Finally, it should be noted that: the above examples are only for illustrating the technical solutions of the present application, and are not limited thereto. Although the present application has been described in detail with reference to the foregoing embodiments, it will be understood by those skilled in the art that various changes in form and details may be made therein without departing from the spirit and scope of the invention. And such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions in the embodiments of the present application.

Claims

1. A motor structure applied to an unmanned aerial vehicle comprises a stator, a rotor and a bearing system movably connecting the stator and the rotor, and is characterized by further comprising a buckle structure bearing axial load of the motor, wherein the buckle structure is fixed with a base of the stator and clamps a rotating shaft of the rotor, the buckle structure comprises a fixing part and a clamping part, the outer end face, far away from the base, of the clamping part abuts against the surface of a clamping groove of the rotating shaft, and the inner ring of the clamping part is spaced from the surface of the clamping groove; the bearing system comprises at least one plain bearing for taking up the axial load of the electrical machine.

2. The motor structure applied to the unmanned aerial vehicle as claimed in claim 1, wherein the fixing portion is fixed in a receiving groove of the base, and a part of the retaining portion is fitted into a retaining groove of the rotating shaft.

3. The structure of claim 2, wherein the cross section of the buckle structure is stepped, and the fixing portion and the holding portion are respectively in a fan-ring shape.

4. The motor structure applied to the unmanned aerial vehicle as claimed in claim 2, wherein the buckle structure is annular as a whole, and the fixing portion and the holding portion are formed on the same plane.

5. The motor structure applied to the unmanned aerial vehicle as claimed in claim 1, wherein a connecting portion on an end cover of the rotor for connecting the rotating shaft abuts against an end face of the bearing system close to a bearing of the end cover, and the snap structure and the connecting portion jointly define an axial gap of the rotating shaft.

6. The motor structure applied to the unmanned aerial vehicle as claimed in claim 1, wherein the sliding bearing is disposed at an end of the housing cavity of the base, which is far away from the end cover of the rotor, and an end of the rotating shaft is beyond an end face of the sliding bearing.

7. The structure of claim 6, wherein the bearing system further comprises at least one rotary bearing for bearing the radial load of the motor, and the rotary bearing is installed at one end of the accommodating cavity close to the end cover.

8. The structure of the electric motor for unmanned aerial vehicle as claimed in claim 1, wherein the snap structure is made of friction-reducing and wear-resisting material and is subjected to radial and axial deformation.

9. The structure of claim 1, wherein the snap structure comprises a first snap and a second snap, and the first snap and the second snap are spliced to form the snap structure.

10. A power assembly applied to an unmanned aerial vehicle comprises an electronic speed regulator, a plurality of rotors and a motor structure applied to the unmanned aerial vehicle, wherein the motor structure applied to the unmanned aerial vehicle is controlled by the electronic speed regulator and drives the rotors to rotate and comprises a stator, a rotor and a bearing system movably connected with the stator and the rotor; the bearing system comprises at least one plain bearing for taking up the axial load of the electrical machine.

11. The power module for the unmanned aerial vehicle as claimed in claim 10, wherein the fixing portion is fixed in a receiving groove of the base, and a portion of the retaining portion is received in a retaining groove of the rotating shaft.

12. The power assembly for the unmanned aerial vehicle as claimed in claim 11, wherein the cross section of the buckle structure is stepped, and the fixing portion and the retaining portion are each in a shape of a fan ring.

13. The power assembly for the unmanned aerial vehicle as claimed in claim 11, wherein the buckle structure is annular as a whole, and the fixing portion and the retaining portion are formed on a same plane.

14. The power assembly applied to the unmanned aerial vehicle as claimed in claim 10, wherein a connecting portion on an end cover of the rotor for connecting the rotating shaft abuts against an end face of the bearing system close to a bearing of the end cover, and the snap structure and the connecting portion jointly define an axial gap of the rotating shaft.

15. The power assembly for the unmanned aerial vehicle as claimed in claim 10, wherein the sliding bearing is disposed at an end of the housing cavity of the base, which is far from the end cover of the rotor, and an end of the rotating shaft is beyond an end face of the sliding bearing.

16. The power assembly as claimed in claim 15, wherein the bearing system further comprises at least one rotary bearing for bearing the radial load of the motor, the rotary bearing being mounted in the housing chamber near one end of the end cap.

17. The power assembly for an unmanned aerial vehicle of claim 10, wherein the snap structure is made of a friction and wear resistant material and is subject to radial and axial deformation.

18. The power assembly for an unmanned aerial vehicle of claim 10, wherein the snap structure comprises a first snap and a second snap that are spliced to form the snap structure.

19. An unmanned aerial vehicle comprises a fuselage, a horn connected to the fuselage and a power assembly arranged on the horn, wherein the power assembly comprises an electronic speed regulator, a plurality of rotors and a motor structure which is controlled by the electronic speed regulator and drives the rotors to rotate and is applied to the unmanned aerial vehicle, the motor structure applied to the unmanned aerial vehicle comprises a stator, a rotor and a bearing system movably connected with the stator and the rotor, and the unmanned aerial vehicle is characterized by further comprising a buckle structure bearing axial load of the motor, the buckle structure is fixed with a base of the stator and clamps a rotating shaft of the rotor, the buckle structure comprises a fixing part and a clamping part, the outer end face, far away from the base, of the clamping part abuts against the surface of a clamping groove of the rotating shaft, and the inner ring of the clamping part is spaced from the surface of the clamping groove; the bearing system comprises at least one plain bearing for taking up the axial load of the electrical machine.

20. The UAV of claim 19 wherein the fixing portion is fixed in a receiving slot of the base, and a portion of the retaining portion is received in a slot of the shaft.

21. The UAV of claim 20 wherein the cross-section of the snap structure is stepped, and the fixing portion and the retaining portion are each in the shape of a fan ring.

22. The UAV of claim 20 wherein the snap structure is generally annular and the retainer and the catch are formed in the same plane.

23. The UAV of claim 19 wherein a connection on an end cap of the rotor for connecting the shaft abuts against an end face of the bearing system near a bearing of the end cap, the snap structure and the connection together defining an axial gap of the shaft.

24. The unmanned aerial vehicle of claim 19, wherein the sliding bearing is disposed at an end of the receiving cavity of the base distal from the end cap of the rotor, and an end of the shaft extends beyond an end face of the sliding bearing.

25. The UAV of claim 24 wherein the bearing system further comprises at least one slew bearing for radial loading of the motor, the slew bearing mounted in the pocket at an end proximate the end cap.

26. The UAV of claim 19 wherein the snap features are made of a friction and wear resistant material and are subject to radial and axial deformation.

27. The UAV of claim 19 wherein the snap feature comprises a first snap and a second snap that are joined to form the snap feature.