WO2019010993A1 - 一种定子座、电机及飞行器 - Google Patents

一种定子座、电机及飞行器 Download PDF

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Publication number
WO2019010993A1
WO2019010993A1 PCT/CN2018/078931 CN2018078931W WO2019010993A1 WO 2019010993 A1 WO2019010993 A1 WO 2019010993A1 CN 2018078931 W CN2018078931 W CN 2018078931W WO 2019010993 A1 WO2019010993 A1 WO 2019010993A1
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WIPO (PCT)
Prior art keywords
bearing
stator
bearing cavity
cavity
motor
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.)
Ceased
Application number
PCT/CN2018/078931
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English (en)
French (fr)
Inventor
罗东东
苏文兵
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Autel Robotics Co Ltd
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Autel Robotics Co Ltd
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Filing date
Publication date
Application filed by Autel Robotics Co Ltd filed Critical Autel Robotics Co Ltd
Publication of WO2019010993A1 publication Critical patent/WO2019010993A1/zh
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02K—DYNAMO-ELECTRIC MACHINES
    • H02K5/00—Casings; Enclosures; Supports
    • H02K5/04—Casings or enclosures characterised by the shape, form or construction thereof
    • H02K5/16—Means for supporting bearings, e.g. insulating supports or means for fitting bearings in the bearing-shields
    • 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

Definitions

  • the present application relates to the field of aircraft technology, and in particular to a stator base, a motor having the stator base, and an aircraft having the same.
  • the height of the stator core of the motor is generally less than 30 mm. Such a structure may cause the performance of the motor to fail to meet the dynamic performance requirements of the aircraft. Increasing the height of the stator core requires a corresponding increase in the height of the stator seat, which complicates the manufacture of the stator base.
  • the coaxiality of the rotating shaft of the motor and the bearing cannot be ensured during the assembly of the motor. On the one hand, it causes difficulty in mass production of the motor, and on the other hand, it causes the use of the motor.
  • the bearing is constantly subject to wear and tear during the process, reducing the life of the motor.
  • the embodiment of the present application provides a stator base that can satisfy the dynamic performance requirements of the aircraft, has a simple manufacturing process, and has a long service life, and a motor and an aircraft having the stator base.
  • the embodiment of the present application provides the following technical solutions:
  • a stator seat includes: a fixing seat and a bearing sleeve, the bearing sleeve is fixed to the fixing seat, the bearing sleeve includes at least two bearing cavities, and the at least two bearing cavities are connected to each other, wherein two The bearing cavities are respectively disposed at opposite ends of the bearing sleeve.
  • the bearing sleeve includes at least three bearing cavities, respectively: a first bearing cavity, a second bearing cavity, ..., an Nth bearing cavity, wherein N is a natural number, and N> 2; the first bearing cavity and the Nth bearing cavity are respectively located at opposite ends of the bearing sleeve, and the bearing housings other than the first bearing cavity and the Nth bearing cavity are located Between the first bearing cavity and the Nth bearing cavity.
  • the outer diameters of the at least three bearing cavities are equal.
  • an outer diameter of the first bearing cavity is larger than an outer diameter of a bearing cavity other than the N-th bearing cavity, and an outer diameter of the N-th bearing cavity is larger than the first bearing cavity The outer diameter of the other bearing cavity.
  • the fixing seat and the bearing sleeve are integrally fixedly connected in a T-shaped structure.
  • the fixing base includes a base and a side wall extending from an outer edge of the base, and a receiving groove is formed between the base and the side wall.
  • the embodiment of the present application further provides the following technical solutions:
  • An electric motor comprising: a stator, a rotor, a bearing, and a stator seat as described above; the rotor is rotatably sleeved on an outer circumference of the stator, the stator is mounted on the stator seat, and the bearing is received in the stator The at least two bearing cavities of the bearing sleeve.
  • the stator includes a core, an insulation, and a coil.
  • the insulating portion is disposed on the iron core, the coil is wound around the iron core, the insulating portion isolates the iron core and the coil, and the bearing sleeve is inserted into a cavity of the iron core .
  • the stator has a height of 34 mm to 41 mm and the stator has an outer diameter of 34 mm to 42 mm.
  • the height of the stator is 35 mm, the outer diameter of the stator is 40.6 mm; or the height of the stator is 40 mm, and the outer diameter of the stator is 35.1 mm; or The height is 40 mm and the outer diameter of the stator is 40.6 mm.
  • the core includes a plurality of teeth that are wound around each of the teeth by a single or multiple enamel wires.
  • the coil is composed of 12 strands of enameled wire with a number of turns of 10 turns, and the enameled wire has a peeled wire diameter of 0.26 mm; or the coil is composed of 8 strands of enamelled wire, The number of turns is 9 turns, and the peeling diameter of the enameled wire is 0.26 mm; or the coil is made up of 12 strands of enameled wire, the number of turns is 9 turns, and the enameled wire is peeled.
  • the wire diameter is 0.26 mm.
  • the rotor includes a housing, a magnet, an outer cover, and a rotating shaft.
  • the outer casing is rotatably sleeved on the outer circumference of the iron core, the magnet is disposed on an inner wall of the outer casing, and is evenly distributed along a circumferential direction of the outer casing; the outer cover and the outer casing are away from the stator seat One end is connected, and the rotating shaft extends through the outer cover and is installed in the bearing.
  • an air gap is provided between the stator and the rotor of the motor, the air gap value is between 0.3 mm and 1 mm, and includes 0.3 mm and 1 mm.
  • an aircraft including: the motor as described above.
  • the aircraft further includes: a fuselage, a powerplant, a main wing, a short wing, and a tail.
  • the main wing is fixedly mounted to the fuselage.
  • the short wing is fixedly mounted to the main wing.
  • the power unit is mounted to the short wing, and the power unit includes the motor and a propeller mounted to the motor.
  • the tail fin is fixedly mounted behind the fuselage.
  • the bearing sleeve of the embodiment of the present application includes at least two bearing cavities, so that the height of the bearing sleeve can adapt to the variation of the height of the stator core of the motor, so that the height of the iron core can meet the performance requirements of the motor, and The flight performance of the aircraft has been improved.
  • the bearing sleeve comprises at least two bearing cavities, and when the parts of the motor are assembled, the precise positioning of the rotating shaft can be realized, the coaxiality of the bearing and the rotating shaft can be effectively ensured, and on the one hand, the mass production of the stator base is facilitated, and On the one hand, ensuring the coaxial arrangement of the bearing and the rotating shaft can reduce the shaking during the running of the motor, reduce the wear of the rotating shaft on the bearing, improve the smoothness of the running of the motor, and prolong the service life of the motor.
  • FIG. 1 is a schematic perspective structural view of a stator base according to an embodiment of the present application.
  • Figure 2 is a cross-sectional view of the stator base shown in Figure 1;
  • FIG. 3 is an exploded view of a motor according to an embodiment of the present application.
  • FIG. 5 is a schematic structural diagram of an aircraft provided by an embodiment of the present application.
  • a stator base 100 includes a fixing base 10 and a bearing sleeve 20 connected to the fixing base 10 .
  • the fixing base 10 and the bearing sleeve 20 form a substantially T-shaped integral structure for reducing assembly tolerances and ensuring concentricity.
  • the mount 10 and the bearing sleeve 20 can be provided in a unitary configuration by any suitable means, such as one-piece casting, welding or other suitable means.
  • the stator mount 100 can be formed from an aluminum alloy, steel or other suitable material.
  • the fixing base 10 and the bearing sleeve 20 may also be separable. After the fixing base 10 and the bearing sleeve 20 are respectively prepared, the bearing sleeve 20 is mounted on the bearing sleeve 20 On the fixed seat 10.
  • the mount 10 includes a base 102 and a side wall 104 that extends from an outer edge of the base 102.
  • the base 102 is substantially circular, and the side wall 104 is substantially annular.
  • a receiving groove 106 is defined between the base 102 and the side wall 104. It can be understood that in some other embodiments, the shape of the base 102 and the side walls 104 can be set to other shapes according to actual needs.
  • the bearing sleeve 20 is substantially a hollow cylinder, one end of which is connected to the middle of the base 102.
  • the bearing sleeve 20 includes at least two bearing cavities, respectively a first bearing cavity 21, ..., and an Nth bearing cavity 2N, wherein N is a natural number, and N>1, wherein 2N is the Nth bearing cavity
  • the numbering of the body, which is the continuation of the first bearing cavity 21, does not mean that the number of bearing cavities is a multiple of two.
  • the at least two bearing cavities communicate with each other and through the bearing sleeve 20.
  • the first bearing cavity 21 and the Nth bearing cavity 2N are respectively located at opposite ends of the bearing sleeve 20.
  • the rotating shaft of the motor when the rotating shaft of the motor is too high, if only one bearing is used to position the rotating shaft, the rotating shaft is likely to generate a large inclination rate, thereby reducing the coaxiality of the rotating shaft and the bearing, thereby affecting the rotating shaft and the bearing. And the degree of assembly between the bearing chambers and the operation of the motor.
  • the bearing sleeve 20 includes at least two bearing cavities for accommodating the bearings, and thus, when assembling the parts of the motor, the rotating shaft of the motor can be positioned by at least two bearings, and at least When the two bearings position the rotating shaft of the motor, the tilting rate of the rotating shaft of the motor can be gradually corrected to achieve accurate positioning of the rotating shaft, thereby effectively ensuring the coaxiality of the bearing and the rotating shaft and further ensuring the concentricity thereof.
  • the assembly tolerance between the rotating shaft, the bearing and the bearing cavity can be further reduced, thereby facilitating mass production of the stator seat; It can also reduce the shaking of the rotating shaft during the running of the motor, thereby improving the smoothness of the motor running and reducing the wear of the rotating shaft on the bearing, thereby prolonging the service life of the motor.
  • the first bearing cavity 21, ..., and the Nth bearing cavity 2N may be integrally fixed by integral casting, welding or other suitable means, and the first bearing cavity may also be detachably 21, ..., and the Nth bearing cavity 2N are connected together, such as clamps, threads or other suitable means. It is also possible to increase the number of bearing cavities by welding or assembly or other suitable means according to the actual situation, or to reduce the number of bearing cavities by disassembly or other means to meet the performance requirements of different aircraft.
  • the outer diameters of the first bearing cavity 21, ..., and the Nth bearing cavity 2N may be equal or unequal.
  • the bearing sleeve 20 includes at least three bearing cavities, respectively: a first bearing cavity 21, a second bearing cavity 22, ..., an Nth bearing cavity 2N, wherein N is a natural number And N>2.
  • the first bearing cavity 21 and the Nth bearing cavity 2N are respectively located at opposite ends of the bearing sleeve 20, and other bearing cavities are located between the first bearing cavity 21 and the Nth bearing cavity 2N.
  • the outer diameters of the first bearing cavity 21, the second bearing cavity 22, ..., and the Nth bearing cavity 2N may all be equal or unequal.
  • the outer diameter of the first bearing cavity 21 is larger than the Nth bearing cavity
  • the outer diameter of the bearing cavity other than 2N, the outer diameter of the Nth bearing cavity 2N is larger than the outer diameter of the bearing cavity other than the first bearing cavity 21, such a structure can make the manufacturing process of the stator block 100 Simple; and the outer diameters of the first bearing cavity 21 and the Nth bearing cavity 2N at the opposite end positions are larger than the outer diameter of the bearing cavity at the position between the two, and the closer to the bearing cavity in the middle of the bearing sleeve 20 The smaller the path.
  • the outer diameter of the first bearing cavity 21 is larger than the outer diameter of the second bearing cavity 22; the outer diameter of the second bearing cavity 22 is larger than the outer diameter of the third bearing cavity 23; The outer diameter of the bearing cavity 24 is larger than the outer diameter of the third bearing cavity 23; the outer diameter of the fifth bearing cavity 25 is larger than the outer diameter of the fourth bearing cavity 24.
  • the structure of the bearing sleeve 20 can better ensure the accuracy, simplify the manufacturing process, and improve the processing efficiency.
  • the outer diameter of the first bearing cavity 21 and the outer diameter of the Nth bearing cavity 2N may be equal or unequal, that is, the first The outer diameter of a bearing cavity 21 may be equal to the outer diameter of the Nth bearing cavity 2N, or may be larger than the outer diameter of the Nth bearing cavity 2N, or may be smaller than the outer diameter of the Nth bearing cavity 2N.
  • the diameter, specifically, the relative relationship between the first bearing cavity 21 and the outer diameter of the Nth bearing cavity 2N can be set according to different industrial needs.
  • the bearing sleeve 20 includes at least three bearing cavities, respectively a first bearing cavity 21, a second bearing cavity 22, ..., an Nth bearing cavity 2N, where N is a natural number, And N>2.
  • the first bearing cavity 21 and the Nth bearing cavity 2N are respectively located at opposite ends of the bearing sleeve 20, and the other bearing cavities are located between the first bearing cavity 21 and the Nth bearing cavity 2N.
  • the outer diameter of the first bearing cavity 21 is larger than the Nth bearing cavity
  • the outer diameter of the bearing cavity other than 2N, the outer diameter of the Nth bearing cavity 2N is larger than the outer diameter of the bearing cavity other than the first bearing cavity 21, such a structure can make the manufacturing process of the stator block 100
  • the relative relationship between the outer diameters of the bearing housings 21 and the other bearing cavities other than the Nth bearing cavity 2N may be free of any constraint. Further, the relative relationship between the outer diameters of the first bearing cavity 21 and the Nth bearing cavity 2N may be free from any constraint.
  • the stator base 100 provided by the embodiment of the present application is suitable for a motor, and is particularly suitable for a motor that provides flight power for an aircraft, such as a motor of a drone.
  • the bearing sleeve 20 of the stator base 100 adopts at least two bearing cavities, and can adapt to changes in the height of the stator core of the motor. For example, it can be applied to an iron core with a height of 30 mm or more, so that the core height can satisfy the performance of the power motor. Requirements, as well as an increase in the flight performance of the aircraft.
  • the bearing sleeve comprises at least two bearing cavities, and when the parts of the motor are assembled, the precise positioning of the rotating shaft can be realized, the coaxiality of the bearing and the rotating shaft can be effectively ensured, and on the one hand, the mass production of the stator base is facilitated, and On the one hand, ensuring the coaxial arrangement of the bearing and the rotating shaft can reduce the shaking during the running of the motor, reduce the wear of the rotating shaft on the bearing, improve the smoothness of the running of the motor, and prolong the service life of the motor.
  • FIG. 3 and FIG. 4 is a motor 200 according to an embodiment of the present application.
  • the motor 200 includes a stator 210 , a rotor 220 , a bearing 230 , and a stator base 100 of the above embodiment.
  • the stator 210 is mounted on the stator base 100.
  • the bearing 230 is received in the bearing sleeve 20 of the stator base 100.
  • the rotor 220 is sleeved on the outer circumference of the stator 210 and can be wound around the stator 210. Rotate.
  • the motor 200 may further include a washer 240 and a retaining ring 250.
  • the washer 240 can be replaced with a screw; the collar 250 can be replaced with a bushing.
  • the stator base 100 is for fixedly mounting the motor 200 on an aircraft.
  • Bearings 230 are received in the bearing sleeve 20, that is, each bearing cavity in the bearing 230 receives a bearing 230 correspondingly.
  • the stator 210 is received in the receiving groove 106 of the stator base 100 and adjacent to the inner wall of the side wall 104, but there is a gap between the inner wall of the side wall 104 and a predetermined distance.
  • the stator 210 includes a core 2101, an insulating portion 2102, and a coil 2103.
  • the insulating portion 2102 is applied to the iron core 2101, and the coil 2103 is wound around the iron core 2101.
  • the insulating portion 2102 isolates the iron core 2101 and the coil 2103.
  • the height of the stator 210 is at least 30 mm, and the outer diameter of the stator 210 is at least 22 mm. In a preferred embodiment, the height of the stator 210 is 34 mm to 41 mm, and the outer diameter of the stator 210 is 34 mm to 42 mm.
  • the height and outer diameter of the stator 210 may be set to appropriate values by adjusting the number of bearing cavities as desired by the motor 200, for example, to meet the performance requirements of the motor 200, the stator 210
  • the height is set to 40 mm, the outer diameter of the stator 210 is set to 40.6 mm; or the height of the stator 210 is set to 35 mm, the outer diameter of the stator 210 is set to 40.6 mm; or the height of the stator 210 is set to 40 mm, and the outer diameter of the stator 210 is set. It is 35.1mm.
  • the iron core 2101 may be formed by stacking materials (such as steel, nickel, iron, etc.) that are easily magnetized. In some embodiments, in order to reduce the weight of the motor 200, the iron core 2101 may be stacked by steel sheets. The thickness or average thickness of the steel sheet can be set to 0.2 mm to 0.5 mm.
  • the iron core 2101 includes a plurality of teeth. The number of teeth can be set to any suitable number according to the requirements of the motor 200, such as 9, 12, 18, 24, and the like.
  • the insulating portion 2102 is for isolating the iron core 2101 and the coil 2103 to prevent the motor 200 from being short-circuited.
  • the insulating portion 2102 may be formed of any material having insulating properties, such as plastic or digital powder.
  • the insulating portion 2102 in order to achieve the insulating effect, is formed of a digital powder coated on the surface of the body.
  • the average thickness thereof is at least 0.15 mm, for example, the insulating portion 2102 has an average thickness of 0.20 mm.
  • the coil 2103 is wound around the iron core 2101, and the coil 2103 includes at least one turn.
  • the coil 2103 may be wound around each of the teeth by a single or a plurality of enamelled wires (e.g., enamelled copper wires or enamelled aluminum wires).
  • the number of turns of the coil 2103 can be set to 8 ⁇ , 9 ⁇ , 10 ⁇ , 11 ⁇ , etc., for example, the coil 2103 is formed by 12 strands of enameled wire and having a number of turns of 10 turns.
  • the enameled wire has a peeled wire diameter of 0.26 mm; or the coil 2103 is composed of 8 strands of enameled wire, the number of turns is 9 turns, and the enameled wire has a peeled wire diameter of 0.26 mm;
  • the coil 2103 is composed of 12 strands of enameled wire, the number of turns is 9 turns, and the peeling diameter of the enameled wire is 0.26 mm.
  • the rotor 220 includes a housing 2201, a magnet 2202, an outer cover 2203, and a rotating shaft 2204.
  • the outer casing 2201 is disposed outside the stator 210. Specifically, the outer casing 2201 is rotatably sleeved on the outer circumference of the iron core 2101 and rotatable around the iron core 2101.
  • the magnet 2202 is disposed in the outer casing 2201. Specifically, the magnet 2202 is disposed on an inner wall of the outer casing 2201 and uniformly distributed along a circumferential direction of the outer casing 2201.
  • the outer casing 2201 is substantially a hollow cylinder and can be made of a highly efficient magnetic conductive material such as 10# steel or 20# steel.
  • the casing 2201 The distance between the bottom and the wing is between 0.4mm and 1mm.
  • the distance between the bottom of the outer casing 2201 and the wing is set to 0.6 mm.
  • the magnet 2202 includes a plurality of magnetic elements, which may be curved, rectangular or any other suitable shape.
  • the material of the magnetic element may be ferrite, neodymium iron boron or other suitable magnetic material, and the thickness or average thickness may be 0.8 mm, 0.9 mm, 1 mm, 1.1 mm, 1.2 mm, 1.3 mm, or the like.
  • the material of the magnetic element in order to satisfy the performance requirements of the motor 200, the material of the magnetic element may be selected from NdFeB, and the average thickness thereof is set to 1.8 mm.
  • the number of magnetic elements of the magnet 2202 can be set according to the performance requirements of the motor 200, for example, the number of magnetic elements is set to 12, 14, 16, or the like.
  • the height or average height of the magnets 2202 is at least 30 mm, for example, the height or average height of the magnets 2202 is set to 35 mm.
  • the outer cover 2203 is connected to an end of the outer casing 2201 away from the stator base 100.
  • the outer cover 2203 is provided with a shaft hole at the center thereof, the rotating shaft 2204 penetrates the shaft hole, and the rotating shaft 2204 and the The outer cover 2203 is fastened.
  • One end of the rotating shaft 2204 passes through the bearing 230, the washer 240 and the retaining ring 250, and the other end is connected to the propeller of the aircraft to prevent the propeller from rotating.
  • the rotating shaft 2204 in order to increase the fastening of the rotating shaft 2204 and the outer cover 2203 to increase the mechanical strength of the motor 200, the rotating shaft 2204 is at a fastening connection with the outer cover 2203 (ie A rough surface or flat position may be provided at the shaft hole.
  • the rough surface may be knurled and its length is less than or equal to the length of the shaft hole to prevent the rough surface or flat position from affecting the installation of the propeller or interfering with the bearing 230. .
  • an air gap is provided between the stator 210 and the rotor 220 of the motor 200, and the air gap value is between 0.3 mm and 1 mm, and includes 0.3 mm and 1 mm.
  • the motor 200 provided in this embodiment is applicable to any field of electromechanical integration, and is particularly suitable for an aircraft such as a drone.
  • the bearing sleeve 20 of the stator base 100 includes a plurality of bearing cavities that can accommodate changes in the height of the stator 210.
  • the height of the stator 210 can be at least 30 mm, so that the motor 200 can meet the performance requirements of the flight power. .
  • an aircraft 300 is provided according to an embodiment of the present application.
  • the aircraft 300 includes a fuselage 310 , a power unit 320 , a main wing 330 , a short wing 340 , and a tail wing 350 .
  • the main wing 330 is fixedly mounted on the body 310
  • the short wing 340 is fixedly mounted on the main wing 330
  • the power device 320 is mounted on the short wing 340
  • the tail wing 350 is fixedly mounted.
  • the body 310 includes various functional module circuit boards.
  • the aircraft 300 may further include: a pan/tilt head, a landing gear, and a tilting mechanism.
  • the pan/tilt is installed at the bottom of the body 310, and the pan/tilt can be equipped with a high-definition digital camera or other device to meet the specific needs of the user.
  • the aircraft 300 may include at least two short wings 340, and each of the short wings 340 is provided with two power devices 320, that is, the aircraft 300 may include at least four power devices 320.
  • the axes of rotation of the at least two power units 320 are arranged in parallel.
  • the mounting orientation of the power unit 320 is not specifically limited.
  • the power unit 320 includes a propeller 3201 and the motor 200 of the above embodiment.
  • the propeller 3201 is mounted on the motor 200, and the motor 200 is coupled to the short wing 340.
  • the propeller 3201 is driven to rotate in a specific direction (ie, the direction of rotation of the motor 200: clockwise or counterclockwise) to provide lift to the aircraft 300 to drive the aircraft 300. flight.

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

Abstract

一种定子座（100）、电机（200）及飞行器（300），定子座包括：固定座（10）和轴承套（20），轴承套固定于固定座，轴承套包括至少两个轴承腔体（21、22、……、2N），至少两个轴承腔体相互连通，其中两个轴承腔体（21、2N）分别设置于轴承套的两相对端。由于轴承套包括至少两个轴承腔体，使得轴承套的高度可以适应电机的定子铁芯（2101）高度的变化，使得铁芯高度能满足电机的性能要求，以及使得飞行器的飞行性能有所提升，并且在装配电机的零件时，可实现转动轴（2204）的精确定位，有效保证轴承（230）与转动轴的同轴度，从而有利于实现定子座的批量生产，也降低了转动轴对轴承的磨损，提高电机运行的平稳性，延长了电机的使用寿命。

Description

一种定子座、电机及飞行器
本申请要求于2017年07月11日提交中国专利局、申请号为201720837253.3、申请名称为“一种定子座、电机及飞行器”的中国专利申请的优先权，其全部内容通过引用结合在本申请中。
技术领域
本申请涉及飞行器技术领域，特别是涉及一种定子座，具有该定子座的电机，以及具有该电机的飞行器。
背景技术
无人机在灾情调查和救援、空中监控、输电线路巡检、航拍、航测以及军事领域有着广泛的应用前景。随着无人机行业的迅猛发展，飞行器的种类越来越多，功能需求也越来越多，导致飞行器对动力性能要求也增大。目前，电机定子铁芯高度一般在30mm以下，这样的结构会导致电机的性能无法满足飞行器动力性能要求。而增加定子铁芯高度，需相应地增加定子座的高度，这样会使得定子座的制造变得复杂。另外，由于电机加工工艺上的缺陷，在进行电机的装配时，无法保证电机的转动轴与轴承的同轴度，一方面会给电机的批量生产造成困难，另一方面会造成在电机的使用过程中轴承不断受到磨损的问题，减小了电机的使用寿命。
发明内容
为了解决上述技术问题，本申请实施例提供一种能满足飞行器动力性能要求、制造工艺简单且使用寿命长的定子座，以及具有此定子座的电机和飞行器。
为解决上述技术问题，本申请实施例提供以下技术方案：
一种定子座，包括：固定座和轴承套，所述轴承套固定于所述固定座，所述轴承套包括至少两个轴承腔体，所述至少两个轴承腔体相互连通，其中两个所述轴承腔体分别设置于所述轴承套的两相对端。
在一些实施例中，所述轴承套包括至少三个轴承腔体，分别为：第一轴承腔体、第二轴承腔体、……、第N轴承腔体，其中N为自然数，并且N>2；所述第一轴承腔体和第N轴承腔体分别位于所述轴承套的两相对端，所述第一轴承腔体和所述第N轴承腔体以外的其它轴承腔体位于所述第一轴承腔体和所述第N轴承腔体之间。
在一些实施例中，所述至少三个轴承腔体的外径均相等。
在一些实施例中，所述第一轴承腔体的外径大于第N轴承腔体以外的其它轴承腔体的外径，所述第N轴承腔体的外径大于第一轴承腔体以外的其它轴承腔体的外径。
在一些实施例中，所述固定座与所述轴承套为一体式固定连接，呈T型结构。
在一些实施例中，所述固定座包括底座和侧壁，所述侧壁从所述底座的外边缘延伸而出，所述底座和所述侧壁之间形成收容槽。
为解决上述技术问题，本申请实施例还提供以下技术方案：
一种电机，包括：定子、转子、轴承以及如上所述的定子座；所述转子可转动地套设于所述定子外周，所述定子安装于所述定子座，所述轴承收容于所述轴承套的所述至少两个轴承腔体。
在一些实施例中，所述定子包括：铁芯、绝缘部和线圈。所述绝缘部设置于所述铁芯上，所述线圈绕设于所述铁芯，所述绝缘部隔绝所述铁芯和所述线圈，所述轴承套插入所述铁芯的内腔中。
在一些实施例中，所述定子的高度为34mm至41mm，所述定子的外径为34mm至42mm。
在一些实施例中，所述定子的高度为35mm，所述定子的外径为40.6mm；或者，所述定子的高度为40mm，所述定子的外径为35.1mm；或者，所述定子的高度为40mm，所述定子的外径为40.6mm。
在一些实施例中，所述铁芯包括多个齿，所述线圈由单根或多根漆包导 线围绕所述的每个齿绕设而成。
在一些实施例中，所述线圈由12股漆包导线，匝数为10匝绕设而成，漆包导线的去皮线径为0.26mm；或者，所述线圈由8股漆包导线，匝数为9匝绕设而成，漆包导线的去皮线径为0.26mm；或者，所述线圈由12股漆包导线，匝数为9匝绕设而成，漆包导线的去皮线径为0.26mm。
在一些实施例中，所述转子包括：外壳、磁体、外盖及转动轴。所述外壳可转动地套设于所述铁芯外周，所述磁体设置于所述外壳的内壁，并沿所述外壳的周向均匀分布；所述外盖与所述外壳远离所述定子座的一端相连，所述转动轴贯穿所述外盖，并安装于所述轴承内。
在一些实施例中，所述电机的定子与转子间设有气隙，其气隙值在0.3mm-1mm之间，并包括0.3mm和1mm。
为解决上述技术问题，本申请实施例还提供以下技术方案：一种飞行器，包括：如上所述的电机。
在一些实施例中，所述飞行器还包括：机身、动力装置、主翼、短翼以及尾翼。所述主翼固定安装于所述机身。所述短翼固定安装于所述主翼。所述动力装置安装于所述短翼，所述动力装置包括：所述电机和安装于所述电机的螺旋桨。所述尾翼固定安装于所述机身后方。
与现有技术相比较，本申请实施例的轴承套包括至少两个轴承腔体，使得轴承套的高度可以适应电机的定子铁芯高度的变化，使得铁芯高度能满足电机的性能要求，以及使得飞行器的飞行性能有所提升。并且，轴承套包括至少两个轴承腔体，在装配电机的零件时，可实现转动轴的精确定位，有效保证轴承与转动轴的同轴度，一方面有利于实现定子座的批量生产，另一方面，保证轴承和转动轴的同轴设置，可减小在电机运转过程中的晃动，降低转动轴对轴承的磨损，提高电机运行的平稳性，延长了电机的使用寿命。
附图说明
一个或多个实施例通过与之对应的附图中的图片进行示例性说明，这些示例性说明并不构成对实施例的限定，附图中具有相同参考数字标号的元件表示为类似的元件，除非有特别申明，附图中的图不构成比例限制。
图1为本申请实施例提供的定子座的立体结构示意图；
图2为图1所示的定子座的剖视图；
图3为本申请实施例提供的电机的分解图；
图4为本申请实施例提供的电机的装配图；
图5为本申请实施例提供的飞行器的结构示意图。
具体实施方式
为了便于理解本申请，下面结合附图和具体实施方式，对本申请进行更详细的说明。需要说明的是，当元件被表述“固定于”另一个元件，它可以直接在另一个元件上、或者其间可以存在一个或多个居中的元件。当一个元件被表述“连接”另一个元件，它可以是直接连接到另一个元件、或者其间可以存在一个或多个居中的元件。本说明书所使用的术语“垂直的”、“水平的”、“左”、“右”、“内”、“外”以及类似的表述只是为了说明的目的。
除非另有定义，本说明书所使用的所有的技术和科学术语与属于本申请的技术领域的技术人员通常理解的含义相同。在本申请的说明书中所使用的术语只是为了描述具体的实施方式的目的，不是用于限制本申请。本说明书所使用的术语“和/或”包括一个或多个相关的所列项目的任意的和所有的组合。
请参阅图1与图2，为本申请实施例提供的一种定子座100，包括固定座10和与固定座10连接的轴承套20。所述固定座10与所述轴承套20形成大致为T型的一体式结构，用于减小装配公差，保证同心度。所述固定座10与所述轴承套20可以通过任何合适的方式设置成一体式结构，如一体式铸造、焊接或者其它合适的方式。所述定子座100可以由铝合金、钢材或其它合适材料加工形成。
可以理解的是，在一些其它实施例中，所述固定座10与所述轴承套20也可以是可分离的，固定座10与轴承套20分别制得后，将所述轴承套20安 装于固定座10上。
所述固定座10包括底座102和侧壁104，侧壁104从底座102的外边缘延伸而出。所述底座102大致为圆形，所述侧壁104大致为环形结构，所述底座102和侧壁104之间形成一收容槽106。可以理解的是，在一些其它实施例中，所述底座102和侧壁104的形状可根据实际需要设置为其它形状。
所述轴承套20大致为中空圆柱体，其一端连接所述底座102的中部。所述轴承套20包括至少两个轴承腔体，分别为第一轴承腔体21、……、及第N轴承腔体2N，其中N为自然数，并且N>1，其中2N为第N轴承腔体的编号，为延续第一轴承腔体21而来，并不表示轴承腔体个数为2的倍数。所述至少两个轴承腔体相互连通，贯穿所述轴承套20。所述第一轴承腔体21和第N轴承腔体2N分别位于所述轴承套20的两相对端。一般地，当电机的转动轴过高时，若只采用一个轴承对转动轴进行定位，转动轴容易产生较大的倾斜率，从而降低转动轴与轴承的同轴度，进而影响转动轴、轴承以及轴承腔体之间的装配度以及电机的运转。在本申请实施例中，所述轴承套20包括至少两个用于收容轴承的轴承腔体，因而，在装配电机的零件时，可以通过至少两个轴承定位电机的转动轴，而当采用至少两个轴承定位电机的转动轴时，可以逐步矫正电机的转动轴的倾斜率以实现对转动轴的精确定位，从而有效保证轴承与转动轴的同轴度以及进一步保证其同心度。进一步地，当轴承与转动轴的同轴度较高时，一方面，能够进一步减小转动轴、轴承以及轴承腔体之间的装配公差，从而有利于实现定子座的批量生产；另一方面，也可以减少转动轴在电机运转过程中的晃动，从而提高电机运行的平稳性以及降低转动轴对轴承的磨损，进而延长电机的使用寿命。
在一些实施例中，可根据不同的工业需要，调整N的值。例如，当轴承腔体为4个时，即N＝4，电机定子铁芯高度为35mm，此时不能满足特定的飞行器性能要求，则可通过加多轴承腔体，使得N＝5或者更大，使得电机定子铁芯高度增加，满足飞行器的性能要求。
所述第一轴承腔体21、……、及第N轴承腔体2N可通过一体式铸造、焊接或者其它合适的方式固定为一体，还可通过可拆卸的方式将所述第一轴承腔体21、……、及第N轴承腔体2N连接在一起，如卡箍、螺纹或者其它合适方式。还可以根据实际情况，通过焊接或组装或其它合适的方式来增加 轴承腔体的数量，或通过拆卸或其它方式来减少轴承腔体的数量，以满足不同飞行器的性能要求。
所述第一轴承腔体21、……、及第N轴承腔体2N的外径可以都是相等的，也可以是不相等的。
在一些实施例中，所述轴承套20包括至少三个轴承腔体，分别为：第一轴承腔体21、第二轴承腔体22、……、第N轴承腔体2N，其中N为自然数，并且N>2。所述第一轴承腔体21和第N轴承腔体2N分别位于所述轴承套20的两相对端，其它轴承腔体位于所述第一轴承腔体21和第N轴承腔体2N之间。所述第一轴承腔体21、第二轴承腔体22、……、及第N轴承腔体2N的外径可以都是相等的，也可以是不相等的。若所述第一轴承腔体21、第二轴承腔体22、……、第N轴承腔体2N的外径不相等时，所述第一轴承腔体21的外径大于第N轴承腔体2N以外的其它轴承腔体的外径，所述第N轴承腔体2N的外径大于第一轴承腔体21以外的其它轴承腔体的外径，这样的结构可使得定子座100的制造工艺简单；并且，相对两端位置的第一轴承腔体21和第N轴承腔体2N的外径比两者之间位置的轴承腔体外径大，越靠近轴承套20中间的轴承腔体的外径越小。例如，当N＝5时，第一轴承腔体21的外径大于第二轴承腔体22的外径；第二轴承腔体22的外径大于第三轴承腔体23的外径；第四轴承腔体24的外径大于第三轴承腔体23的外径；第五轴承腔体25的外径大于第四轴承腔体24的外径。这样的轴承套20的结构可以更好的保证精度，简化制造工艺，提高加工效率。
可以理解的是，在一些其它实施例中，所述第一轴承腔体21的外径与所述第N轴承腔体2N的外径可以是相等，也可以是不相等的，即所述第一轴承腔体21的外径可以等于所述第N轴承腔体2N的外径，也可以大于所述第N轴承腔体2N的外径，还可以小于所述第N轴承腔体2N的外径，具体地，可根据不同的工业需要，设置所述第一轴承腔体21与所述第N轴承腔体2N的外径的相对关系。
在一些实施例中，所述轴承套20包括至少三个轴承腔体，分别为第一轴承腔体21、第二轴承腔体22、……、第N轴承腔体2N，其中N为自然数，并且N>2。所述第一轴承腔体21和第N轴承腔体2N分别位于所述轴承套20的两相对端，其它轴承腔体位于所述第一轴承腔体21和第N轴承腔体2N之 间。若所述第一轴承腔体21、第二轴承腔体22、……、第N轴承腔体2N的外径不相等时，所述第一轴承腔体21的外径大于第N轴承腔体2N以外的其它轴承腔体的外径，所述第N轴承腔体2N的外径大于第一轴承腔体21以外的其它轴承腔体的外径，这样的结构可使得定子座100的制造工艺简单；而所述第一轴承腔体21和第N轴承腔体2N以外的其它轴承腔体的外径的相对关系可以无任何约束。并且，所述第一轴承腔体21和第N轴承腔体2N的外径的相对关系也可以无任何约束。
本申请实施例提供的定子座100，适用于电机，尤其适用为飞行器提供飞行动力的电机，如：无人机的电机。所述定子座100的轴承套20采用至少两个轴承腔体，可以适应电机的定子铁芯高度的变化，例如可以适用于高度30mm以上的铁芯，使得其铁芯高度能满足动力电机的性能要求，以及使得飞行器的飞行性能有所提升。并且，轴承套包括至少两个轴承腔体，在装配电机的零件时，可实现转动轴的精确定位，有效保证轴承与转动轴的同轴度，一方面有利于实现定子座的批量生产，另一方面，保证轴承和转动轴的同轴设置，可减小在电机运转过程中的晃动，降低转动轴对轴承的磨损，提高电机运行的平稳性，延长了电机的使用寿命。
请参阅图3和图4，为本申请实施例提供的一种电机200，所述电机200包括：定子210、转子220、轴承230以及上述实施例的定子座100。所述定子210安装于所述定子座100，所述轴承230收容于所述定子座100的轴承套20内，所述转子220套设于所述定子210外周，并可绕所述定子210进行旋转。
所述电机200还可以包括：垫圈240和挡圈250。在一些其它实施例中，所述垫圈240可替换为螺丝；所述挡圈250可替换为轴套。
所述定子座100用于将所述电机200固定安装于飞行器上。所述轴承套20内收容有轴承230，即轴承230中的每个轴承腔体相应收容一个轴承230。
所述定子210收容于所述定子座100的收容槽106内，并靠近所述侧壁104的内壁，但与侧壁104的内壁之间存在预设距离的间隙。所述定子210包括：铁芯2101、绝缘部2102和线圈2103。所述绝缘部2102涂覆于所述铁芯2101，所述线圈2103绕设于铁芯2101，所述绝缘部2102隔绝铁芯2101和线圈2103。在所述定子210安装于所述定子座100时，所述轴承套20插入所述 铁芯2101的内腔中。所述轴承套20的高度与定子210的高度需匹配。
其中，所述定子210的高度至少为30mm，并且，所述定子210的外径至少为22mm。在优选实施方式中，定子210的高度为34mm至41mm，定子210的外径为34mm至42mm。在一些实施例中，可以根据电机200的需要，通过调节轴承腔体的个数将所述定子210的高度和外径设置成合适的值，例如，为了满足电机200性能的需要，将定子210的高度设置为40mm，定子210的外径设置为40.6mm；或者定子210的高度设置为35mm，定子210的外径设置为40.6mm；或者定子210的高度设置为40mm，定子210的外径设置为35.1mm。
所述铁芯2101可由容易被磁化的材料(如：钢、镍、铁等)堆叠而成，在一些实施例中，为了降低电机200的重量，所述铁芯2101可由钢片堆叠而成，钢片的厚度或平均厚度可设置为0.2mm-0.5mm。所述铁芯2101包括多个齿，根据电机200的需求，其齿的数量可以设置成任意合适的个数，如：9个、12个、18个、24个等。
所述绝缘部2102用于隔绝所述铁芯2101和线圈2103，以防止所述电机200出现短路现象。绝缘部2102可以由任意具有绝缘特性的材料形成，如：塑胶或者数码粉等，在本实施例中，为了在达到绝缘的效果，绝缘部2102由涂覆在本体的表面上的数码粉形成，其平均厚度至少为0.15mm，例如所述绝缘部2102的平均厚度为0.20mm。
所述线圈2103绕设于所述铁芯2101上，所述线圈2103至少包含有一匝。为了提高所述电机200的效率，所述线圈2103可以由单根或多根漆包导线(如，漆包铜线或漆包铝线)围绕所述的每个齿绕设而成。根据电机200的需求，线圈2103的匝数可以设置为8匝、9匝、10匝、11匝等，例如，所述线圈2103由12股漆包导线，匝数为10匝绕设而成，漆包导线的去皮线径为0.26mm；或者，所述线圈2103由8股漆包导线，匝数为9匝绕设而成，漆包导线的去皮线径为0.26mm；或者，所述线圈2103由12股漆包导线，匝数为9匝绕设而成，漆包导线的去皮线径为0.26mm。
所述转子220包括：外壳2201、磁体2202、外盖2203以及转动轴2204。其中，所述外壳2201设于所述定子210外，具体地，所述外壳2201可转动地套设于所述铁芯2101外周，并可绕所述铁芯2101转动。所述磁体2202设 置于所述外壳2201内，具体地，所述磁体2202设于外壳2201的内壁，并沿所述外壳2201的周向均匀分布。
其中，所述外壳2201大致为中空圆柱体，可由如10#钢、20#钢等高效导磁材料制成。在实际应用中，即当将所述电机200安装于飞行器的机翼上时，为了防止出现电机200干涉现象，预防电机200卡死而导致电机200死机，降低飞行器的安全性，所述外壳2201的底部与机翼的距离在0.4mm到1mm之间。例如，将所述外壳2201的底部与机翼的距离设置为0.6mm。
所述磁体2202包括多个磁性元件，磁性元件的形状可以是弧形、长方形或其它任意合适的形状。所述磁性元件的材料可以为铁氧体、钕铁硼或其它合适的磁性材料，厚度或平均厚度可以是0.8mm、0.9mm、1mm、1.1mm、1.2mm、1.3mm等。在一些实施例中，为了在满足电机200的性能要求的条件下，磁性元件的材料可选用钕铁硼，设置其平均厚度为1.8mm。所述磁体2202的磁性元件的数量可以根据电机200的性能要求设置，例如将磁性元件的数量设置为12个、14个、16个等。例如，为了满足电机200的需求，设置为有14个磁性元件固定于所述外壳2201的内壁。所述磁体2202的高度或平均高度至少为30mm，例如，将所述磁体2202的高度或平均高度设置为35mm。
所述外盖2203与所述外壳2201远离所述定子座100的一端相连，所述外盖2203的中心设置有轴孔，所述转动轴2204贯穿轴孔，并且，所述转动轴2204与所述外盖2203紧固连接。所述转动轴2204的一端穿过轴承230，垫圈240和挡圈250，另一端可与飞行器的螺旋桨止转连接，以带动螺旋桨转动。
在一些实施例中，为了增加所述转动轴2204与所述外盖2203的紧固性从而增加电机200的机械强度，所述转动轴2204在与所述外盖2203的紧固连接处(即轴孔处)可设置一段粗糙的表面或扁位，该粗糙的表面可以是滚花，其长度小于或等于轴孔的长度，以避免该粗糙表面或者扁位影响螺旋桨的安装或者与轴承230干涉。
在本申请实施例中，所述电机200的定子210与转子220间设有气隙，其气隙值在0.3mm-1mm之间，并且包括0.3mm和1mm。
本实施例提供的电机200适用于任意机电一体化的应用领域，尤其适用于飞行器，如：无人机。所述定子座100的轴承套20包括多个轴承腔体，可 适应所述定子210的高度变化，例如，所述定子210的高度至少可以为30mm，从而使得电机200能满足飞行动力的性能要求。
请参阅图5，为本申请实施例提供的一种飞行器300，所述飞行器300包括：机身310、动力装置320、主翼330、短翼340和尾翼350。其中，所述主翼330固定安装于所述机身310上，所述短翼340固定安装于所述主翼330上，所述动力装置320安装于所述短翼340上，所述尾翼350固定安装于所述机身310后方。在本申请实施例中，所述机身310内含有各种功能模块电路板。
在本申请实施例中，所述飞行器300还可以包括：云台、起落架和倾转机构。其中所述云台安装于所述机身310的底部，所述云台可以搭载高清数码相机或其它设备以满足用户的特定的需求。
其中，所述飞行器300可以包括至少2个短翼340，每个短翼340上设有2个动力装置320，即所述飞行器300可以包括至少4个动力装置320。为了保证所述飞行器300飞行的稳定性，所述至少2个动力装置320的转动轴平行设置。在本申请实施例中，对所述动力装置320的安装方位不作具体限定。
所述动力装置320包括：螺旋桨3201和上述实施例的电机200。其中，所述螺旋桨3201安装在所述电机200上，所述电机200与所述短翼340相连接。当所述电机200运转时，带动所述螺旋桨3201沿着特定的方向(即电机200的转动方向：顺时针方向或者逆时针方向)转动，从而为所述飞行器300提供升力，带动所述飞行器300飞行。
最后应说明的是：以上实施例仅用以说明本申请的技术方案，而非对其限制；在本申请的思路下，以上实施例或者不同实施例中的技术特征之间也可以进行组合，步骤可以以任意顺序实现，并存在如上所述的本申请的不同方面的许多其它变化，为了简明，它们没有在细节中提供；尽管参照前述实施例对本申请进行了详细的说明，本领域的普通技术人员应当理解：其依然可以对前述各实施例所记载的技术方案进行修改，或者对其中部分技术特征进行等同替换；而这些修改或者替换，并不使相应技术方案的本质脱离本申请各实施例技术方案的范围。

Claims (16)

  1. 一种定子座(100)，其特征在于，包括：
    固定座(10)；
    轴承套(20)，所述轴承套(20)固定于所述固定座(10)，所述轴承套(20)包括至少两个轴承腔体，所述至少两个轴承腔体相互连通，其中两个所述轴承腔体分别设置于所述轴承套(20)的两相对端。
  2. 根据权利要求1所述的定子座(100)，其特征在于，所述轴承套(20)包括至少三个轴承腔体，分别为：第一轴承腔体(21)、第二轴承腔体(22)、……、第N轴承腔体(2N)，其中N为自然数，并且N>2；所述第一轴承腔体(21)和第N轴承腔体(2N)分别位于所述轴承套(20)的两相对端，所述第一轴承腔体(21)和所述第N轴承腔体(2N)以外的其它轴承腔体位于所述第一轴承腔体(21)和所述第N轴承腔体(2N)之间。
  3. 根据权利要求2所述的定子座(100)，其特征在于，所述至少三个轴承腔体的外径均相等。
  4. 根据权利要求2所述的定子座(100)，其特征在于，所述第一轴承腔体(21)的外径大于第N轴承腔体(2N)以外的其它轴承腔体的外径，所述第N轴承腔体(2N)的外径大于第一轴承腔体(21)以外的其它轴承腔体的外径。
  5. 根据权利要求1至4任一项所述的定子座(100)，其特征在于，所述固定座(10)与所述轴承套(20)为一体式固定连接，呈T型结构。
  6. 根据权利要求1至5任一项所述的定子座(100)，其特征在于，所述固定座(10)包括底座(102)和侧壁(104)，所述侧壁(104)从所述底座(102)的外边缘延伸而出，所述底座(102)和所述侧壁(104)之间形成收容槽(106)。
  7. 一种电机(200)，其特征在于，包括：定子(210)、转子(220)、轴承(230)以及如权利要求1至6中任一项所述的定子座(100)；
    所述转子(220)可转动地套设于所述定子(210)外周，所述定子(210)安装于所述定子座(100)，所述轴承(230)收容于所述轴承套(20)的所述至少两个轴承腔体。
  8. 根据权利要求7所述的电机(200)，其特征在于，所述定子(210)包括：铁芯(2101)、绝缘部(2102)和线圈(2103)；
    所述绝缘部(2102)设置于所述铁芯(2101)上，所述线圈(2103)绕设于所述铁芯(2101)，所述绝缘部(2102)隔绝所述铁芯(2101)和所述线圈(2103)，所述轴承套(20)插入所述铁芯(2101)的内腔中。
  9. 根据权利要求8所述的电机(200)，其特征在于，所述定子(210)的高度为34mm至41mm，所述定子(210)的外径为34mm至42mm。
  10. 根据权利要求9所述的电机(200)，其特征在于，所述定子(210)的高度为35mm，所述定子(210)的外径为40.6mm；
    或者，所述定子(210)的高度为40mm，所述定子(210)的外径为35.1mm；
    或者，所述定子(210)的高度为40mm，所述定子(210)的外径为40.6mm。
  11. 根据权利要求8至10中任一项所述的电机(200)，其特征在于，所述铁芯(2101)包括多个齿，所述线圈(2103)由单根或多根漆包导线围绕所述的每个齿绕设而成。
  12. 根据权利要求8至10中任一项所述的电机(200)，其特征在于，所述线圈(2103)由12股漆包导线，匝数为10匝绕设而成，漆包导线的去皮线径为0.26mm；
    或者，所述线圈(2103)由8股漆包导线，匝数为9匝绕设而成，漆包导线的去皮线径为0.26mm；
    或者，所述线圈(2103)由12股漆包导线，匝数为9匝绕设而成，漆包 导线的去皮线径为0.26mm。
  13. 根据权利要求8至12中任一项所述的电机(200)，其特征在于，所述转子(220)包括：外壳(2201)、磁体(2202)、外盖(2203)及转动轴(2204)；
    所述外壳(2201)可转动地套设于所述铁芯(2101)外周，所述磁体(2202)设置于所述外壳(2201)的内壁，并沿所述外壳(2201)的周向均匀分布；所述外盖(2203)与所述外壳(2201)远离所述定子座(100)的一端相连，所述转动轴(2204)贯穿所述外盖(2203)，并安装于所述轴承(230)内。
  14. 根据权利要求7至13中任一项所述的电机(200)，其特征在于，所述电机(200)的定子(210)与转子(220)间设有气隙，其气隙值在0.3mm-1mm之间，并包括0.3mm和1mm。
  15. 一种飞行器(300)，其特征在于，包括：如权利要求7至14中任一项所述的电机(200)。
  16. 根据权利要求15所述的飞行器(300)，其特征在于，还包括：
    机身(310)；
    动力装置(320)；
    主翼(330)，其固定安装于所述机身(310)；
    短翼(340)，其固定安装于所述主翼(330)；所述动力装置(320)安装于所述短翼(340)，所述动力装置(320)包括：所述电机(200)和安装于所述电机(200)的螺旋桨(3201)；以及
    尾翼(350)，其固定安装于所述机身(310)后方。
PCT/CN2018/078931 2017-07-11 2018-03-14 一种定子座、电机及飞行器 Ceased WO2019010993A1 (zh)

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