CN117360826A - Unmanned aerial vehicle power device and unmanned aerial vehicle of integrated motor - Google Patents

Unmanned aerial vehicle power device and unmanned aerial vehicle of integrated motor Download PDF

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Publication number
CN117360826A
CN117360826A CN202311407471.XA CN202311407471A CN117360826A CN 117360826 A CN117360826 A CN 117360826A CN 202311407471 A CN202311407471 A CN 202311407471A CN 117360826 A CN117360826 A CN 117360826A
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CN
China
Prior art keywords
rotor
unmanned aerial
aerial vehicle
motor
stator
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
CN202311407471.XA
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Chinese (zh)
Inventor
罗东东
夏书岳
范欣林
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Shenzhen Lianhe Airplane Technology Co ltd
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Shenzhen Lianhe Airplane Technology Co ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Shenzhen Lianhe Airplane Technology Co ltd filed Critical Shenzhen Lianhe Airplane Technology Co ltd
Priority to CN202311407471.XA priority Critical patent/CN117360826A/en
Publication of CN117360826A publication Critical patent/CN117360826A/en
Pending legal-status Critical Current

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Classifications

    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02K—DYNAMO-ELECTRIC MACHINES
    • H02K7/00—Arrangements for handling mechanical energy structurally associated with dynamo-electric machines, e.g. structural association with mechanical driving motors or auxiliary dynamo-electric machines
    • H02K7/14—Structural association with mechanical loads, e.g. with hand-held machine tools or fans
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • B64U50/10—Propulsion
    • B64U50/13—Propulsion using external fans or propellers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • B64U50/10—Propulsion
    • B64U50/19—Propulsion using electrically powered motors
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Power Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)

Abstract

The invention relates to an unmanned aerial vehicle power device integrated with a motor and an unmanned aerial vehicle, belongs to the technical field of unmanned aerial vehicle driving devices, and solves the problems of complex structure, tedious installation and poor flying performance of the unmanned aerial vehicle. The unmanned aerial vehicle power device comprises a load rotor assembly, a stator assembly and a transmission unit; the load rotor assembly includes an integrated bladed hub, a rotor yoke, and a motor shaft; the blade of the integrated blade hub and the hub shell are integrally formed; the hub shell is provided with a shaft hole and a rotor magnet mounting ring table; the motor shaft is connected to the hub shell; a rotor magnetic yoke mounting groove is formed between the rotor magnet mounting ring table and the inner side wall surface of the hub shell; the rotor magnetic yoke is in limit connection in the rotor magnetic yoke mounting groove and connected to the inner side wall surface of the hub shell; the rotor yoke and the motor shaft are integrally formed on the hub shell. The unmanned aerial vehicle platform body has a light integrated structure, so that the manufacturing and mounting cost is effectively reduced, the power consumption of a motor can be reduced, and the flight efficacy of the unmanned aerial vehicle can be improved.

Description

Unmanned aerial vehicle power device and unmanned aerial vehicle of integrated motor
Technical Field
The invention relates to the technical field of unmanned aerial vehicle driving devices, in particular to an unmanned aerial vehicle power device integrated with a motor and an unmanned aerial vehicle.
Background
At present, unmanned aerial vehicle designs show modularization trend, generally include unmanned aerial vehicle platform organism module (rotor system, driving system), task load module and signal transmission control module etc.. The power system of the unmanned aerial vehicle is integrated with sub-modules such as a blade, a motor, an electric regulator and the like; the motor is widely applied to a permanent magnet synchronous motor, and the permanent magnet synchronous motor has the advantages of high driving efficiency, rapid speed change and high control precision.
In the prior art, the permanent magnet synchronous motor is widely applied to the fields of robots, mechanical arms, automation equipment, unmanned aerial vehicles, cloud platforms and the like. However, the requirements of the field on the motor are often that the structure is compact, the volume is small, the output torque is large, the output power is small, and the power consumption of the motor is high due to the fact that the volume and the weight of the motor are large when the continuous output torque of the existing motor is ensured. Therefore, in the design of a power system including the unmanned aerial vehicle field, the technical problems of the size of the motor, the optimization of the magnetic circuit of the motor, the wiring process of the motor and the like need to be fully considered so as to balance the output torque, the volume and the weight of the motor.
In particular, special attention is required in the design process of the unmanned aerial vehicle power system: the unmanned plane is used as an aircraft, and has high requirements on the weight and the movement flexibility of the whole structure; accordingly, unmanned aerial vehicle platform systems, particularly rotor systems and power systems, are required to be as compact as possible, lightweight, and have reasonable installation space to be able to meet the low power consumption and high torque output required for unmanned aerial vehicle flight performance, while meeting the rapid response requirements of simple installation process.
Therefore, how to design the unmanned aerial vehicle platform body module in a lightweight manner, simplify the production and installation process of the unmanned aerial vehicle platform body module, so as to reduce power transmission errors, optimize the unmanned aerial vehicle flight performance and the quick response performance, and become a problem to be solved by those skilled in the art.
Disclosure of Invention
In view of the above analysis, the invention aims to provide an unmanned aerial vehicle power device integrated with a motor and an unmanned aerial vehicle, so as to solve the technical problems of more modules, complex structure, tedious installation and poor flying performance and quick response of the existing unmanned aerial vehicle.
The specific technical scheme is as follows:
an unmanned aerial vehicle power device integrating a motor comprises a load rotor assembly and a stator assembly; the load rotor assembly includes an integrated bladed hub, a rotor yoke, and a motor shaft; the integrated bladed hub comprises a blade and a hub shell; the plurality of blades are circumferentially and uniformly distributed on the outer peripheral side of the hub shell and integrally formed with the hub shell; the hub shell is a rotary shell with an upper bottom shell; the inner side surface of the upper bottom shell of the hub shell is concentrically provided with a shaft hole, and the inner side surface of the upper bottom shell of the hub shell is concentrically provided with a rotor magnet mounting ring table; a rotor magnetic yoke mounting groove is formed between the rotor magnet mounting ring table and the inner side wall surface of the hub shell; the rotor magnetic yoke is limited in the rotor magnetic yoke mounting groove and connected to the inner side wall surface of the hub shell; the motor shaft is in limit connection with the shaft hole; the rotor yoke and the motor shaft are integrally formed on the hub shell.
Further, the motor also comprises a rotor magnet; magnet mounting notches are uniformly distributed on the circumference of the lower end of the rotor magnet mounting ring table, the lower end parts of the rotor magnets are respectively inserted into the magnet mounting notches, and the outer wall surfaces of the rotor magnets are adhered to the inner wall surfaces of the rotor magnet yokes.
Further, a rotor magnet limit part is arranged on the inner side wall surface of the rotor magnet yoke; the rotor magnetic yoke magnet limiting parts are circumferentially and uniformly distributed on the inner wall surface of the rotor magnetic yoke; the rotor magnetic yoke magnet limiting part is designed in a structural matching way with the rotor magnet.
Further, each of the rotor magnets is bonded to a part of an inner wall surface of the rotor yoke/the rotor yoke magnet limit portion.
Further, the motor shaft comprises a motor shaft mounting part, a motor shaft step part and a motor shaft transmission connecting part which are sequentially arranged; the tail end of the motor shaft transmission connecting part is provided with a motor shaft snap spring groove (134).
Further, knurling or centipedes are arranged on the inner wall surface of the motor shaft mounting part and/or the shaft hole; the motor shaft is integrally formed on the inner wall surface of the shaft hole through the motor shaft mounting part.
Further, the stator assembly comprises a stator base and a wound stator core unit; the stator seat comprises a stator seat connecting part and a stator seat mounting ring column.
Further, the wound stator core unit includes a stator core; the stator core comprises a stator core shaft core part formed integrally; the inner wall surface of the core part of the stator core shaft is provided with a stator core shaft core glue groove part; the outer peripheral surface of the upper part of the stator seat mounting ring column is provided with a stator seat mounting ring column outer glue groove part.
Further, the outer glue groove part of the stator seat mounting ring column and the axial center glue groove part of the stator core are provided with knurling or li and/or ring groove structures in a matching way.
An unmanned aerial vehicle comprises an unmanned aerial vehicle power device of the integrated motor and an unmanned aerial vehicle body; the unmanned aerial vehicle power device of integrated motor is connected on the unmanned aerial vehicle body.
Compared with the prior art, the invention has at least the following beneficial effects:
1. according to the motor, hub and propeller integrated design of the unmanned aerial vehicle power device integrated with the motor, the unmanned aerial vehicle is compact in structure, and the unmanned aerial vehicle is light in weight.
2. According to the unmanned aerial vehicle power device integrated with the motor, the motor and the propeller structure are optimized, so that the assembly, installation and disassembly procedures of the motor and the propeller are reduced.
3. The unmanned aerial vehicle power device integrating the motor realizes that the motor shaft and the rotor magnet yoke are integrally formed on the hub shell, thereby reducing the investment of motor production equipment and manufacturing tools, being beneficial to reducing production procedures, improving production efficiency and reducing motor cost.
Additional features and advantages of the invention will be set forth in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. The objectives and other advantages of the invention may be realized and attained by the structure particularly pointed out in the written description and drawings.
Drawings
The drawings are only for purposes of illustrating the embodiments and are not to be construed as limiting the invention, and like reference numerals refer to like parts throughout the several views.
Fig. 1 is a schematic diagram of the overall structure of an integrated motor unmanned aerial vehicle power device according to an embodiment of the present invention;
FIG. 2 is a cross-sectional view taken along A-A of FIG. 1;
FIG. 3 is an exploded view of FIG. 1;
FIG. 4 is a schematic diagram of a load rotor assembly according to an embodiment of the present invention;
FIG. 5 is a schematic view of an integrated bladed hub according to an embodiment of the present invention;
FIG. 6 is a schematic diagram of a rotor yoke according to an embodiment of the present invention;
FIG. 7 is a schematic diagram of a rotor yoke according to an embodiment of the present invention;
FIG. 8 is a schematic view of a motor shaft structure according to an embodiment of the present invention;
FIG. 9 is a schematic view of a stator assembly according to an embodiment of the present invention;
FIG. 10 is a schematic view of a stator base according to an embodiment of the present invention;
fig. 11 is a schematic diagram of a variable structure stator base structure according to an embodiment of the present invention (i.e., a stator base structure according to another technical solution in the embodiment);
fig. 12 is an exploded view of a part of the structure of a gear transmission unit according to an embodiment of the present invention.
Reference numerals:
1. a load rotor assembly; 11. an integrated paddle hub; 111. a paddle; 112. a hub shell; 1121. a rotor yoke mounting groove; 1122. a rotor magnet mounting ring table; 11221. a magnet mounting slot; 1123. a shaft hole; 1124. a heat radiation hole; 1125. the rotor magnetic yoke is provided with a rubber groove part; 12. a rotor yoke; 121. a rotor magnetic yoke glue groove part; 122. a rotor yoke magnet limit part; 13. a motor shaft; 131. a motor shaft mounting portion; 132. a motor shaft step portion; 133. a motor shaft transmission connection part; 134. a motor shaft snap spring groove; 135. an external gear pillow block; 14. a rotor magnet; 2. a stator assembly; 21. a stator base; 211. a stator seat connecting part; 2111. a stator seat connecting position; 212. the stator seat is provided with a ring column; 2121. the stator seat is provided with an annular column inner table; 21211. internal tooth pillow block of stator base; 2122. a first drive mounting location; 2123. a second drive mounting location; 2124. the stator seat is provided with an outer rubber groove part of the ring column; 22. a wound stator core unit; 221. an iron core yoke; 222. a stator core; 2221. a stator core shaft core part; 2222. stator teeth; 2223. stator tooth slots; 223. a winding; 3. a transmission unit; 31. a first transmission body; 32. a second transmission body; 3-1, a planetary gear; 4. a transmission body limiting unit; 41. a gasket; 42. and (5) clamping springs.
Detailed Description
The technical scheme of the invention is specifically described below with reference to the accompanying drawings. Wherein the showings are for the purpose of illustrating the principles of the invention and together with the description of the embodiments thereof are not intended to limit the scope of the invention.
The present embodiment sets: the stator seat 21 is located at the lower side of the upper bottom shell of the hub shell 112, and the upper and lower directions are defined at the upper side.
Example 1
An unmanned aerial vehicle power device integrating a motor.
In the prior art, the unmanned aerial vehicle platform body has the following technical defects:
1. the screw and the motor are all of split type modularization constitution, and the module is required to be installed and fastened, so that the screw and the motor have complex structure and large weight, and the material cost and the time cost of installation are consumed.
2. The head cover and the magnetic yoke of the permanent magnet synchronous motor need to be mounted in a pressing mode, equipment such as a pressing jig is usually needed, the mounting process is complex, the mounting cost is high, and the cost of the motor is directly increased.
3. The screw is installed on permanent magnet synchronous motor's skull upper portion generally, and compact and lightweight design can not be accomplished to motor and screw, directly influences unmanned aerial vehicle's flight performance optimization.
To overcome the above technical drawbacks, an unmanned aerial vehicle power device with an integrated motor of embodiment 1 is designed.
The following describes the technical scheme of the unmanned power device of the integrated motor of embodiment 1 with reference to fig. 1 to 12: as shown in fig. 1, 2 and 3, the motor-integrated unmanned aerial vehicle power device of this embodiment 1 includes a load rotor assembly 1, a stator assembly 2 and a transmission unit 3; the stator assembly 2 is inserted into the load rotor assembly 1; the transmission unit 3 is arranged between the load rotor assembly 1 and the stator assembly 2 in a limiting mode.
As shown in fig. 4, the load rotor assembly 1 comprises an integrated bladed hub 11, a rotor yoke 12, a motor shaft 13 and a rotor magnet 14.
As shown in fig. 2 and 5, the integrated bladed hub 11 comprises a blade 111 and a hub shell 112.
Preferably, a plurality of the blades 111 are circumferentially and uniformly distributed on the outer circumferential side of the hub shell 112 in an integrated manner; the design optimizes the structure of the motor and the propeller, and reduces the assembly, installation and disassembly procedures of the motor and the propeller.
As shown in fig. 5, in particular, the hub shell 112 is a swivel shell; an axle hole 1123 is concentrically arranged on the inner side surface of the shell bottom of the hub shell 112, and a rotor magnet mounting ring table 1122 is concentrically arranged on the inner side surface of the upper bottom shell of the hub shell 112; a rotor yoke mounting groove 1121 is formed between the rotor magnet mounting ring 1122 and the inner side wall surface of the hub shell 112.
A magnet mounting notch 11221 is provided at the lower end of the rotor magnet mounting ring 1122, and the circumferential width direction structure of the notch is identical to the structure of the rotor magnet 14. The lower end parts of the rotor magnets 14 are inserted into the magnet mounting slots 11221, and each rotor magnet 14 obtains stable limit in the circumferential direction.
As shown in fig. 5, preferably, a rotor yoke mounting groove 1125 is provided on the inner wall surface of the hub shell 112. Further preferably, the rotor yoke mounting adhesive groove 1125 is knurled or otherwise shaped and/or configured as a ring groove (only the ring groove is shown).
Preferably, the inner wall surface of the shaft hole 1123 is provided with knurling or li.
Preferably, a plurality of through heat dissipation holes 1124 are uniformly distributed between the shaft hole 1123 on the inner side of the upper bottom shell of the hub shell 112 and the rotor magnet mounting ring 1122, so as to dissipate heat generated by the stator assembly 2, which can effectively solve the problem of high heat influence performance of the motor in embodiment 1.
As shown in fig. 6, one of the rotor yokes 12 has a cylindrical ring structure; the outer wall surface of the rotor yoke 12 is provided with a rotor yoke glue groove part 121, and the inner wall surface is a smooth inner cylindrical surface.
As shown in fig. 7, the rotor yoke 12 may further be provided with a plurality of rotor yoke magnet limiting portions 122 circumferentially and uniformly distributed on an inner wall surface thereof; the rotor yoke magnet limiting part 122 is a sedimentation structure of the inner wall surface of the rotor yoke 12, and is used for limiting and connecting the rotor magnet 14; the rotor yoke magnet limiting portion 122 is configured to be structurally matched with the rotor magnet 14, and is disposed corresponding to the magnet mounting notch 11221.
The rotor magnet 14 may be a tile-shaped structure, and a plurality of the rotor magnets 14 are separately arranged; the rotor magnet 14 may be annular. The tile-shaped split rotor magnets 14 are made of sintered neodymium-iron-boron, the circular rotor magnets 14 are made of bonded neodymium-iron-boron or sintered neodymium-iron-boron, and when the circular rotor magnets 14 are made of bonded neodymium-iron-boron, the circular rotor magnets and the rotor magnet yokes 12 can be integrally injection molded.
Preferably, the rotor magnet 14 of embodiment 1 has a tile-shaped structure, and the material is sintered neodymium iron boron.
As shown in fig. 6 or 7, the rotor yoke glue groove 121 preferably has a knurled or li-groove structure (only the groove structure is shown) that matches the structure of the rotor yoke mounting glue groove 1125.
Preferably, the rotor yoke 12 is retained in the rotor yoke mounting groove 1121 and is coupled to the inner sidewall surface of the hub shell 112.
Further preferably, the rotor yoke 12 is integrally formed on the hub shell 112.
The outer wall surface of the rotor yoke 12 and the inner wall surface of the hub shell 112 are provided with mutually matched knurling or li and/or ring groove structures, so that the integration degree of the rotor yoke 12 and the hub shell 112 after the integrated forming process can be enhanced, and the safe operation of the whole motor is facilitated.
Further preferably, during the installation, an adhesive layer is provided on each of the outer wall surface of the rotor magnet 14 and the inner wall surface part of the rotor yoke 12/the rotor yoke magnet limiting part 122, and the rotor magnet 14 is adhered to the inner wall surface of the rotor yoke 12; specifically, in embodiment 1, the rotor magnet 14 is fixedly attached to the rotor yoke 12 by being bonded to the inner wall surface part of the rotor yoke 12 and the rotor yoke magnet stopper 122.
The rotor magnet 14 is bonded with the rotor yoke 12, so that the structural integration degree of the load rotor assembly 1 is further improved; the structure integrated design not only can reduce the investment of motor production equipment and jig of the upper bottom shell inner side device of the hub shell 112, reduce production procedures, improve production efficiency and reduce motor cost, but also can enable the unmanned aerial vehicle power device integrated with the motor to be simple and compact in structure and realize the lightweight design of the unmanned aerial vehicle.
As shown in fig. 8, the motor shaft 13 has a stepped shaft structure; a motor shaft mounting part 131, a motor shaft step part 132 and a motor shaft transmission connecting part 133 in sequence; a motor shaft snap spring groove 134 is arranged at the tail end of the motor shaft transmission connecting part 133.
Preferably, the motor shaft mounting portion 131 is integrally formed on the inner wall of the shaft hole 1123 with knurling or li.
The integral molding may be any integral molding manufacturing process including over molding, die casting molding, etc., or a combination of a plurality of the manufacturing processes.
Preferably, in embodiment 1, the motor shaft 13 and the rotor yoke 12 are manufactured first, and then the hub shell 112 is manufactured by injection molding. In the injection molding process of the hub shell 112, the motor shaft 13 and the rotor yoke 12 are integrally molded by a molding and/or die casting process using the motor shaft 13 and the rotor yoke 12 as embedded parts.
Further preferably, the motor shaft 13 and the rotor yoke 12 are integrally formed with the hub shell 112. This is advantageous for integration of the manufacturing process, and can reduce the manufacturing process flow and the manufacturing cost.
The parts of the load rotor assembly 1 of this embodiment 1 are formed into an integrated integral structure by performing an integral molding process. The load rotor assembly 1 with integrated structure is beneficial to the stable operation of the unmanned aerial vehicle motor. A transmission body limiting unit 4 is arranged at the motor shaft snap spring groove 134. The transmission unit 3 is disposed between the motor shaft stepped portion 132 and the transmission body limiting unit 4.
As shown in fig. 2 and 3, in particular, the transmission body limiting unit 4 includes a spacer 41 and a clip spring 42. The inner diameter of the gasket 41 is not smaller than the diameter of the motor shaft transmission connecting part 133, and the clamp spring 42 is arranged in the motor shaft clamp spring groove 134 and limits the gasket 41 on the motor shaft transmission connecting part 133.
As shown in fig. 9, the stator assembly 2 includes a stator base 21 and a wound stator core unit 22.
As shown in fig. 10, the stator base 21 includes a stator base connection portion 211 and a stator base mounting ring post 212.
Specifically, the stator base connection portion 211 is a plate structure, and a plurality of stator base connection positions 2111 are provided on the stator base connection portion 211; the motor-integrated unmanned aerial vehicle power device of this embodiment 1 is connected to the aircraft body by fasteners penetrating the stator seat connection sites 2111 on the stator seat 21.
Specifically, the stator base mounting ring post 212 is disposed on one end surface of the stator base 21, and a central hole of the stator base mounting ring post 212 penetrates through the plate structure of the stator base connecting portion 211.
A stator mount ring post inner table 2121 is provided in the center hole of the stator mount ring post 212. The lower end face of the stator seat mounting ring post inner table 2121 is a first transmission mounting position 2122, and the upper end face of the stator seat mounting ring post inner table 2121 is a second transmission mounting position 2123.
A mounting ring post pillow block is provided on the outer periphery of the stator base mounting ring post 212, wherein the pillow block is used for limiting the axial position of the wound stator core unit 22. Preferably, the end surface of the mounting ring post pillow block is used for limiting the axial position of the winding stator core unit 22; the stator base mounting ring post 212 is provided with a stator base mounting ring post external glue groove 2124 on the outer peripheral surface thereof, which is used for being glued to the wound stator core unit 22 through viscous glue substances.
Preferably, the outer rubber groove 2124 of the stator mounting ring post has a knurled or li-shaped and/or ring groove structure.
As shown in fig. 3 and 9, the wound stator core unit 22 includes a core yoke 221, a stator core 222, and windings 223.
Specifically, the stator core 222 includes an integrally formed stator core shaft core 2221 and stator teeth 2222. The stator core 222 is sleeved on the upper periphery of the stator base mounting ring post 212 by the stator core shaft core 2221, and the axial position of the stator core 222 is limited by the outer Zhou Zhoutai structure of the stator base mounting ring post 212.
As shown in fig. 3, a plurality of stator teeth 2222 are radially and circumferentially distributed on the outer circumference of the stator core portion 2221 from the axial shaft hole to the outside, and a stator tooth notch 2223 is formed between two adjacent stator teeth 2222.
As shown in fig. 9, the winding 223 is sleeved on the root of the stator tooth 2222.
Preferably, an inner wall surface of the stator core shaft portion 2221 is provided with a stator core shaft center glue groove portion that is matched with the stator seat mounting ring column glue groove portion 2124.
Preferably, the axial center rubber groove part of the stator core is in a knurling or li and/or ring groove structure.
In particular to embodiment 1, the stator tooth slot 2223 is 12 slots, and the rotor magnet 14 is 14 poles; wherein each of the N and S poles is half, and the N and S poles are alternately arranged on the inner wall surface of the rotor yoke 12 and mounted on the magnet mounting slot 11221.
The transmission unit 3 is used for movably connecting the stator assembly 2 and the load rotor assembly 1.
As shown in fig. 2 and 3, the transmission unit 3 of the present embodiment 1 includes a first transmission body 31 and a second transmission body 32. The first transmission body 31 and the second transmission body 32 are both connected with a fixed part and a rotary motion part by adopting bearings.
The upper end of the inner ring of the first transmission body 31 is limited on the lower surface of the motor shaft step portion 132, and the lower end of the outer ring of the first transmission body 31 is limited on the second transmission mounting position 2123.
The lower end of the inner ring of the second transmission body 32 is limited on the upper surface of the spacer 41, and the upper end of the outer ring of the second transmission body 32 is limited on the first transmission mounting position 2122.
The stator assembly 2 generates induced electromotive force after being electrified, a rotating magnetic field is formed between the stator teeth 2222 and the rotor magnet 14 which are oppositely arranged, so that the rotor assembly 1 generates electromagnetic torque, the rotor assembly 1 can generate rotating motion relative to the stator assembly 2 and the machine body connected with the stator assembly through the movable connection of the transmission unit 3, and the blades 111 generate power required by the aircraft including lifting force.
The first transmission body 31 and the second transmission body 32 are limited between the outer wall surface of the motor shaft 13 and the inner wall surface of the central hole of the stator base mounting ring post 212, and are located at two ends of the stator base mounting ring post inner table 2121, so as to form a structure for ensuring stable transmission of electromagnetic torque, and can ensure stable rotation of the rotor assembly 1 with the blades 111.
The motor-integrated unmanned aerial vehicle power device with the two bearings of the transmission unit 3 is suitable for unmanned aerial vehicles with smaller volumes, and is particularly suitable for unmanned aerial vehicles with tiny volumes.
As shown in fig. 11 and 12, the transmission unit of the present invention may also be a gear transmission unit. The gear transmission unit consists of a variable structure motor shaft and a variable structure stator seat which are matched with a gear box with a speed change function.
The motor shaft of the variable structure shown in fig. 12 is provided with motor shaft engaging external teeth on the motor shaft 13.
Specifically, an external gear pillow block 135 is disposed on the outer wall surface of the motor shaft transmission connection portion 133, and the motor shaft engaging external gear is disposed on the outer peripheral side wall of the external gear pillow block 135.
As shown in fig. 11, the variable structure stator base is a stator base inner gear boss 21211 provided on the stator base mounting ring post 212.
As shown in fig. 12, specifically, the stator base inner wall surface of the stator base mounting ring post inner table 2121 is provided with the stator base inner gear boss 21211, and the outer peripheral side wall of the stator base inner gear boss 21211 is provided with a stator base engagement inner gear portion.
In the installation state, the axial positions of the stator seat meshing inner tooth part and the motor shaft meshing outer tooth part correspond, and the gear meshing parameters are consistent.
Specifically, the gear transmission unit with a speed change function includes a plurality of planetary gears 3-1. The plurality of planetary gears 3-1 are circumferentially and uniformly arranged between the outer gear boss 135 and the stator base inner gear boss 21211, and are engaged with the stator base engagement inner gear portion at the outer periphery and the motor shaft engagement outer gear portion at the inner periphery. The gear engagement parameters of the planetary gear 3-1 are consistent with those of the stator base engagement inner tooth part and the motor shaft engagement outer tooth part.
By sizing the planetary gear 3-1, the stator seat meshing inner teeth and the motor shaft meshing outer teeth, different rotational speeds of the load rotor assembly at the same power input can be achieved.
Further specifically, planetary gear fixing end cover units are fixedly connected to two end faces of the stator seat mounting ring post inner table 2121 respectively, each planetary gear fixing end cover unit comprises a ring-shaped upper end cover and a ring-shaped lower end cover, planetary gear core shaft holes are uniformly distributed in the circumference of each upper end cover and the circumference of each lower end cover, and the number of the planetary gear core shaft holes is matched with that of the planetary gears 3-1; and bearing end cover limiting tables are arranged on opposite sides of the upper end cover and the lower end cover at the positions of the star gear core shaft holes.
The spindle at two ends of the planetary gear 3-1 is provided with planetary gear stepped shafts, each planetary gear 3-1 is respectively and limitedly connected with two planetary gear transmission bearings through the pillow block end face of the planetary gear stepped shaft and the corresponding bearing end cover limiting table on the upper end cover/the lower end cover, and the gear transmission unit is movably connected with the stator seat mounting ring column 212 through the planetary gear transmission bearings.
Such an integrated motor unmanned aerial vehicle power device with a gear transmission unit of the present invention is suitable for small or medium sized size unmanned aerial vehicles.
Example 2
An unmanned aerial vehicle.
The unmanned aerial vehicle of embodiment 2 of the present invention includes an unmanned aerial vehicle body and the unmanned aerial vehicle power device of the integrated motor of embodiment 1 of the present invention. The unmanned aerial vehicle power device of integrated motor passes through stator seat connecting portion 211 on the stator seat 21, with the fastener connection on the unmanned aerial vehicle fuselage.
The present invention is not limited to the above-mentioned embodiments, and any changes or substitutions that can be easily understood by those skilled in the art within the technical scope of the present invention are intended to be included in the scope of the present invention.

Claims (10)

1. An unmanned power device integrated with a motor is characterized by comprising a load rotor assembly (1) and a stator assembly (2);
the load rotor assembly (1) comprises an integrated bladed hub (11), a rotor yoke (12) and a motor shaft (13);
the integrated bladed hub (11) comprises a blade (111) and a hub shell (112); the blades (111) are circumferentially and uniformly distributed on the outer peripheral side of the hub shell (112) and are integrally formed with the hub shell (112);
the hub shell (112) is a rotary shell with an upper bottom shell; an axle hole (1123) is concentrically arranged on the inner side surface of the upper bottom shell of the hub shell (112), and a rotor magnet mounting ring table (1122) is concentrically arranged on the inner side surface of the upper bottom shell of the hub shell (112);
a rotor yoke mounting groove (1121) is formed between the rotor magnet mounting ring table (1122) and the inner side wall surface of the hub shell (112);
the rotor magnet yoke (12) is limited in the rotor magnet yoke mounting groove (1121) and is connected to the inner side wall surface of the hub shell (112);
the motor shaft (13) is in limit connection with the shaft hole (1123);
the rotor yoke (12) and the motor shaft (13) are integrally formed on the hub shell (112).
2. The unmanned power device of the integrated motor of claim 1, further comprising a rotor magnet (14); magnet mounting notches (11221) are uniformly distributed on the circumference of the lower end of the rotor magnet mounting annular table (1122), the lower end parts of the rotor magnets (14) are respectively inserted into the magnet mounting notches (11221), and the outer wall surfaces of the rotor magnets (14) are adhered to the inner wall surfaces of the rotor magnet yokes (12).
3. The unmanned aerial vehicle power device of the integrated motor according to claim 2, wherein the rotor yoke (12) is provided with a rotor yoke magnet limit part (122) on an inner side wall surface; the rotor magnetic yoke magnet limiting parts (122) are circumferentially and uniformly distributed on the inner wall surface of the rotor magnetic yoke (12); the rotor yoke magnet limiting part (122) is designed in a structure matching with the rotor magnet (14).
4. A motor-integrated unmanned power unit according to claim 2 or 3, wherein each of the rotor magnets (14) is bonded to an inner wall surface portion of the rotor yoke (12)/the rotor yoke magnet stopper portion (122).
5. The unmanned aerial vehicle power device of claim 4, wherein the motor shaft (13) comprises a motor shaft mounting portion (131), a motor shaft stepped portion (132) and a motor shaft transmission connecting portion (133) which are sequentially provided; the tail end of the motor shaft transmission connecting part (133) is provided with a motor shaft snap spring groove (134).
6. The unmanned aerial vehicle power device of claim 5, wherein the motor shaft mounting portion (131) and/or the inner wall surface of the shaft hole (1123) is provided with knurling or li; the motor shaft (13) is integrally formed on the inner wall surface of the shaft hole (1123) through the motor shaft mounting portion (131).
7. The unmanned power device of an integrated motor according to claim 6, wherein the stator assembly (2) comprises a stator base (21) and a wound stator core unit (22); the stator base (21) comprises a stator base connecting part (211) and a stator base mounting ring column (212).
8. The unmanned power device of the integrated motor of claim 7, wherein the wound stator core unit (22) comprises a stator core (222); the stator core (222) includes an integrally formed stator core shaft core (2221); an inner wall surface of the stator core shaft core part (2221) is provided with a stator core shaft core glue groove part; the outer peripheral surface of the upper part of the stator seat mounting ring column (212) is provided with a stator seat mounting ring column outer rubber groove part (2124).
9. The unmanned aerial vehicle power device of claim 8, wherein the stator base mounting ring post outer glue groove (2124) and the stator core axle center glue groove are provided with knurling or li-shi and/or ring groove structures in a matching manner.
10. A drone comprising the integrated motor drone of any one of claims 1-9, further comprising a drone fuselage; the unmanned aerial vehicle power device of integrated motor is connected on the unmanned aerial vehicle body.
CN202311407471.XA 2023-10-27 2023-10-27 Unmanned aerial vehicle power device and unmanned aerial vehicle of integrated motor Pending CN117360826A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202311407471.XA CN117360826A (en) 2023-10-27 2023-10-27 Unmanned aerial vehicle power device and unmanned aerial vehicle of integrated motor

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202311407471.XA CN117360826A (en) 2023-10-27 2023-10-27 Unmanned aerial vehicle power device and unmanned aerial vehicle of integrated motor

Publications (1)

Publication Number Publication Date
CN117360826A true CN117360826A (en) 2024-01-09

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Application Number Title Priority Date Filing Date
CN202311407471.XA Pending CN117360826A (en) 2023-10-27 2023-10-27 Unmanned aerial vehicle power device and unmanned aerial vehicle of integrated motor

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CN (1) CN117360826A (en)

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