WO2018153136A1 - 电机及电机固定结构 - Google Patents

电机及电机固定结构 Download PDF

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Publication number
WO2018153136A1
WO2018153136A1 PCT/CN2017/113793 CN2017113793W WO2018153136A1 WO 2018153136 A1 WO2018153136 A1 WO 2018153136A1 CN 2017113793 W CN2017113793 W CN 2017113793W WO 2018153136 A1 WO2018153136 A1 WO 2018153136A1
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WO
WIPO (PCT)
Prior art keywords
motor
conductive terminal
conductive
aircraft
fixing structure
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Application number
PCT/CN2017/113793
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English (en)
French (fr)
Inventor
孙维
罗东东
苏文兵
陈毅东
Original Assignee
深圳市道通智能航空技术有限公司
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Application filed by 深圳市道通智能航空技术有限公司 filed Critical 深圳市道通智能航空技术有限公司
Publication of WO2018153136A1 publication Critical patent/WO2018153136A1/zh
Priority to US16/567,188 priority Critical patent/US11309768B2/en

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    • 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
    • H02K5/22—Auxiliary parts of casings not covered by groups H02K5/06-H02K5/20, e.g. shaped to form connection boxes or terminal boxes
    • H02K5/225—Terminal boxes or connection arrangements
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
    • B64F5/40—Maintaining or repairing aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/10—Rotorcrafts
    • B64U10/13—Flying platforms
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U30/00—Means for producing lift; Empennages; Arrangements thereof
    • B64U30/20—Rotors; Rotor supports
    • B64U30/29—Constructional aspects of rotors or rotor supports; Arrangements thereof
    • B64U30/291—Detachable rotors or rotor supports
    • 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
    • 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
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto

Definitions

  • the present application relates to the field of aircraft, and in particular to a motor and motor fixing structure.
  • Multi-axis aircraft also known as rotorcraft, is equipped with multiple propellers, which are controlled by multiple propellers to control flight. It is widely used in aerial photography, detection, search and rescue, resource exploration, agriculture, etc., with small size and weight. Light, low cost, flexible operation and high security.
  • the multi-axis aircraft has a plurality of arms, and the motor that powers the propeller on the multi-axis aircraft is generally mounted on the arm through the motor base, and the ESC for controlling the motor is installed in the fuselage of the aircraft.
  • the motor base is fixedly mounted on the arm by a plurality of screws, the motor leads pass through the inside of the arm, and the motor leads are soldered to the ESC in the arm.
  • the control of the motor by the flight control is realized by the electrical conduction between the ESC and the flight controller on the multi-axis aircraft fuselage.
  • the technical problem to be solved by the present application is to overcome the power of the prior art multi-axis aircraft.
  • the machine operates complex technical defects during the disassembly process.
  • the present application provides a motor having a first conductive terminal disposed thereon, and a lead of the motor is electrically connected to the external device through the first conductive terminal.
  • the motor is provided with a protruding plug portion, and the first conductive terminal is disposed on the plug portion.
  • the motor includes a motor base and a motor body coupled to the motor base, and the plug portion is disposed on the motor base.
  • the motor further includes a connecting member
  • the motor base is provided with a through hole penetrating the motor base
  • the motor is connected to the external device through a connecting member passing through the through hole.
  • the first conductive terminal is a conductive contact, a conductive pin or a conductive socket.
  • a motor fixing structure including an aircraft arm and a motor detachably coupled to the aircraft arm, and the motor is provided with the motor
  • the lead wire is electrically connected to the first conductive terminal
  • the aircraft arm is provided with a second conductive terminal electrically connected to the aircraft control unit, and the first conductive terminal is electrically connected to the second conductive terminal.
  • the motor is provided with a protruding plug portion, the first conductive terminal is disposed on the plug portion, and the aircraft arm is disposed to receive the plug a slot of the portion, the second conductive terminal being disposed in the slot.
  • the motor includes a motor base and a motor body coupled to the motor base, and the plug portion is disposed on the motor base.
  • the motor fixing structure further includes a connecting member for detachably connecting the motor to the aircraft arm, and the motor base is provided with a through hole penetrating the motor seat.
  • a mounting hole is disposed on the aircraft arm, the connecting member passes through the through hole and the mounting hole, and the motor is detachably coupled to the aircraft arm through the connecting member.
  • the connecting member is a screw or a positioning pin.
  • the first conductive terminal and the second conductive terminal are both conductive contacts; or the first conductive terminal is a conductive pin, and the second conductive terminal is a conductive pin; Or the first conductive terminal is a conductive socket, and the second conductive terminal is a conductive pin.
  • the motor can be electrically connected to the control unit inside the aircraft through the first conductive terminal Sexual connection simplifies the way of connection, so that when the motor fails, the electrical connection of the first conductive terminal and the second conductive terminal can be disconnected to realize quick disassembly of the motor without any auxiliary tools, which simplifies the motor.
  • the disassembly and assembly operation improves the efficiency of motor replacement.
  • FIG. 1 is a schematic structural view of a motor according to an embodiment of the present application.
  • FIG. 2 is a structural split view of a motor fixing structure according to an embodiment of the present application.
  • Figure 3 is a front elevational view of the aircraft arm of the motor mounting structure of Figure 2;
  • connecting should be understood broadly, unless otherwise explicitly defined and defined, for example, it may be a fixed connection or a detachable connection; it may be a mechanical connection, It can be an electrical connection.
  • connecting should be understood broadly, unless otherwise explicitly defined and defined, for example, it may be a fixed connection or a detachable connection; it may be a mechanical connection, It can be an electrical connection.
  • the motor and motor fixing structure provided by the embodiments of the present application can be applied to various motor-driven movable objects, including but not limited to unmanned aerial vehicles (UAVs), ships, and robots.
  • UAVs unmanned aerial vehicles
  • the structure of the UAV includes a center housing, a boom, and a power system.
  • the arm is integrally or fixedly connected to the center housing, and the power system is mounted on the arm.
  • Typical power systems include electronic governors, motors, and propellers.
  • the motor is mounted on the arm, and the rotating shaft of the motor is coupled to the propeller. Propeller in the electricity
  • the force that causes the UAV to move such as the lift or thrust that causes the UAV to move, is generated under the drive of the machine.
  • the motor is detachably mounted to the arm of the UAV, and the motor and the aircraft arm together constitute a motor fixing structure.
  • the motor and motor fixing structure provided by the embodiment of the present application will be specifically described below with reference to the accompanying drawings.
  • FIG. 1 is a schematic structural diagram of a motor 100 according to an embodiment of the present application.
  • the motor 100 includes a motor base 1 and a motor body 2 that is disposed on the motor base 1 and detachably coupled to the motor base 1. It can be understood that the motor base 1 and the motor body 2 can also be integrally formed.
  • the motor base 1 is provided with a protruding insertion portion 12 and a through hole 13 penetrating the motor holder 1.
  • the first conductive terminal 11 is disposed on the plug portion 12, and the lead of the motor body 2 is electrically connected to the external device through the first conductive terminal 11.
  • the first conductive terminal 11 can be disposed at any suitable position.
  • the motor 100 is provided with a first conductive terminal 11 electrically connected to the lead of the motor body 2 on the motor base 1 so that the motor 100 can be electrically connected to the external device through the first conductive terminal 11 , thereby simplifying the connection manner. Therefore, when the motor 100 fails, the electrical connection of the first conductive terminal 11 and the external device can be disconnected, so that the motor 100 can be quickly disassembled without any auxiliary tools, which simplifies the operation of disassembling the motor and improves the motor. Replace the efficiency.
  • the motor securing structure is adapted to be mounted to a variety of motor driven movable objects to power a movable object.
  • the motor securing structure is applied to an unmanned aerial vehicle that includes an aircraft arm 200 and a motor 100 that is detachably coupled to the aircraft arm 200.
  • the motor 100 includes a motor base 1 and a motor body 2 that is disposed on the motor base 1 and detachably coupled to the motor base 1. It can be understood that the motor base 1 and the motor body 2 can also be integrally formed.
  • the motor base 1 is provided with a protruding plug portion 12 And a through hole 13 penetrating the motor holder 1, and the first conductive terminal 11 electrically connected to the lead of the motor body 2 is provided on the plug portion 12.
  • the aircraft arm 200 is provided with a mounting hole 203 and a slot 202 for receiving the plug portion 12.
  • the slot 202 is provided with a second conductive terminal 201 electrically connected to the control unit of the aircraft.
  • the plug portion 12 is inserted into the slot 202 such that the first conductive terminal 11 and the second conductive terminal 201 are in electrical contact, thereby completing the control of the motor 100 and the interior of the aircraft.
  • the electrical connection of the unit The insertion of the plug portion 12 on the motor base 1 and the corresponding provision of the slot 202 of the aircraft arm 200 have the advantage of more accurate positioning during disassembly and assembly.
  • the control unit can be ESC and/or flight control.
  • the lead wires of the motor 100 do not have to be electrically connected to the control unit through the aircraft arm 200, but are electrically connected through the first conductive terminal 11 and the second conductive terminal 201.
  • the motor 100 fails, it is only necessary to disconnect the first
  • the electrical connection between the one conductive terminal 11 and the second conductive terminal 201 may be. Therefore, this structure realizes quick disassembly of the motor 100 without any auxiliary tools, simplifies the operation of disassembly and assembly of the motor, and improves the efficiency of motor replacement.
  • the first conductive terminal 11 and the second conductive terminal 201 are respectively conductive contacts.
  • the first conductive terminal 11 is a conductive pin
  • the second conductive terminal 201 is a conductive socket adapted to the conductive pin.
  • the first conductive terminal 11 is a conductive socket
  • the second conductive terminal 201 is a conductive pin adapted to the conductive socket.
  • the first conductive terminal 11 and the second conductive terminal 201 can also adopt other similar terminal structures, and details are not described herein again, as long as the detachable electrical connection structure is used to fall within the scope of protection of the embodiment.
  • the motor fixing structure further includes a connecting member 3 for detachably connecting the motor 100 with the aircraft arm 200.
  • the connecting member 3 passes through the motor block 1 The hole 13 and the mounting hole 203 on the aircraft arm 200 thereby detachably connect the motor 100 to the aircraft arm 200.
  • the connecting member 3 is slightly positioned, and in other embodiments, it may be a screw.
  • the detachable connection between the motor 100 and the aircraft arm 200 can also be a threaded connection, a sliding connection, or a snap-fit connection that snaps together.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Power Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Manufacturing & Machinery (AREA)
  • Transportation (AREA)
  • Remote Sensing (AREA)
  • Motor Or Generator Frames (AREA)

Abstract

一种电机（100）及电机（100）固定结构，其中电机（100）设置有第一导电端子（11），电机（100）的引线通过第一导电端子（11）与外接设备电性连接，简化了连接的方式，从而当电机（100）发生故障时，只需断开第一导电端子（11）和外接设备的电性连接即可实现对电机（100）的快速拆卸，无需任何辅助工具，简化了电机（100）拆装的操作，提高了电机（100）更换效率。

Description

电机及电机固定结构
本申请要求于2017年2月27日提交中国专利局、申请号为201720182246.4、申请名称为“电机及电机固定结构”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
本申请涉及飞行器领域，具体涉及一种电机及电机固定结构。
背景技术
多轴飞行器，又称旋翼飞行器，其设有多个螺旋桨，通过多个电机控制多个螺旋桨来实现飞行，广泛用于航拍、检测、搜救、资源勘查、农业等各个领域，具有体积小、重量轻、费用低、操作灵活和安全性高等特点。多轴飞行器拥有多个机臂，多轴飞行器上给螺旋桨提供动力的电机一般通过电机座安装在机臂上，用于控制电机的电调板安装在飞行器的机身中。
现有技术的多轴飞行器，其电机座通过多根螺丝固定安装在机臂上，电机引线从机臂内部穿过，并将电机引线焊接到机臂内的电调板上。通过电调板与多轴飞行器机身上的飞控之间的电性导通，来实现飞控对电机的控制。当电机出现故障需要更换或拆卸维修时，由于电机引线是从机臂内部穿过焊接到在电调板上的，因此电机的拆装操作甚为不便。综上，如何实现多轴飞行器上的电机的快速拆装成为了现如今亟待解决的问题。
发明内容
为此，本申请要解决的技术问题在于克服现有技术的多轴飞行器的电 机在拆装的过程中操作复杂的技术缺陷。
为此本申请提供了一种电机，所述电机上设置有第一导电端子，所述电机的引线通过所述第一导电端子与外接设备电性连接。
根据本申请的一实施例，所述电机设有凸出的插接部，所述第一导电端子设置在所述插接部上。
根据本申请的一实施例，所述电机包括电机座和与所述电机座连接的电机本体，所述插接部设于所述电机座上。
根据本申请的一实施例，该电机还包括连接件，所述电机座上设有贯穿所述电机座的通孔，所述电机通过穿过所述通孔的连接件与外接设备连接。
根据本申请的一实施例，所述第一导电端子为导电触点、导电插针或导电插孔。
本申请解决其技术问题采用的另一技术方案为：构造一种电机固定结构，其包括飞行器机臂和与所述飞行器机臂可拆卸连接的电机，所述电机上设有与所述电机的引线电连接的第一导电端子，所述飞行器机臂上设有与飞行器控制单元电连接的第二导电端子，所述第一导电端子与第二导电端子电连接。
根据本申请的一实施例，所述电机上设有凸出的插接部，所述第一导电端子设于所述插接部上，所述飞行器机臂上设有用于***述插接部的插槽，所述第二导电端子设于所述插槽内。
根据本申请的一实施例，所述电机包括电机座和与所述电机座连接的电机本体，所述插接部设于所述电机座上。
根据本申请的一实施例，所述电机固定结构还包括用于将所述电机与所述飞行器机臂可拆卸连接的连接件，所述电机座上设有一贯穿所述电机座的通孔，所述飞行器机臂上设置有一安装孔，所述连接件穿过所述通孔和安装孔，所述电机通过所述连接件可拆卸地连接在所述飞行器机臂上。
根据本申请的一实施例，所述连接件为螺钉或者定位销。
根据本申请的一实施例，所述第一导电端子与所述第二导电端子均为导电触点；或者所述第一导电端子为导电插针，所述第二导电端子为导电插孔；或者所述第一导电端子为导电插孔，所述第二导电端子为导电插针。
本申请提供的电机及飞行器具有如下优点：
通过在电机和飞行器机臂上分别设置与电机的引线电连接的第一导电端子和与飞行器的控制单元电连接的第二导电端子，使得电机能够通过第一导电端子与飞行器内部的控制单元电性连接，简化了连接的方式，从而当电机发生故障时，只需断开第一导电端子和第二导电端子的电性连接即可实现对电机的快速拆卸，无需任何辅助工具，简化了电机拆装的操作，提高了电机更换效率。
附图说明
为了更清楚地说明本申请具体实施方式的技术方案，下面根据本申请的具体实施例并结合附图，对申请作进一步详细说明。
图1为本申请一实施例提供的电机的结构示意图；
图2为本申请一实施例提供的电机固定结构的结构拆分图；
图3为图2所示的电机固定结构中飞行器机臂的主视图。
图中各附图标记说明如下。
100-电机；1-电机座；11-第一导电端子；12-插接部；13-通孔；2-电机本体；3-连接件；200-飞行器机臂；201-第二导电端子；202-插槽；203-安装孔。
具体实施方式
下面将结合附图对本申请的技术方案进行清楚、完整地描述，显然，所描述的实施例是本申请一部分实施例，而不是全部的实施例。基于本申请中的实施例，本领域普通技术人员在没有做出创造性劳动前提下所获得的所有其他实施例，都属于本申请保护的范围。
在本申请的描述中，需要说明的是，术语“上”、“内”、“外”等指示的方位或位置关系为基于附图所示的方位或位置关系，仅是为了便于描述本申请和简化描述，而不是指示或暗示所指的装置或元件必须具有特定的方位、以特定的方位构造和操作，因此不能理解为对本申请的限制。此外，术语“第一”、“第二”仅用于描述目的，而不能理解为指示或暗示相对重要性。
在本申请的描述中，需要说明的是，除非另有明确的规定和限定，术语“连接”应做广义理解，例如，可以是固定连接，也可以是可拆卸连接；可以是机械连接，也可以是电连接。对于本领域的普通技术人员而言，可以具体情况理解上述术语在本申请中的具体含义。
此外，下面所描述的本申请不同实施方式中所涉及的技术特征只要彼此之间未构成冲突就可以相互结合。
本申请实施例提供的电机及电机固定结构可以应用到各种电机驱动的可移动物体上，包括但不限于无人飞行器(unmanned aerial vehicle，UAV)，轮船，机器人。现以无人飞行器为例进行说明。无人飞行器的结构包括中心壳体、机臂、和动力***。机臂与中心壳体一体连接或者固定连接，动力***安装于机臂上。典型的动力***包括电子调速器、电机和螺旋桨。具体地，电机安装在机臂上，电机的转动轴连接螺旋桨。螺旋桨在所述电 机的驱动下产生使得所述无人飞行器移动的力，例如，使得无人飞行器移动的升力或者推力。
该在本申请实施例中，由电机可拆卸地安装至无人飞行器的机臂，由电机和飞行器机臂共同组成电机固定结构。以下将结合附图具体描述本申请实施例提供的电机和电机固定结构。
图1是本申请提实施例提供的电机100的结构示意图。该电机100包括电机座1和设于电机座1上并与电机座1可拆卸连接的电机本体2。可以理解的，电机座1和电机本体2也可以一体成型。电机座1上设有凸出的插接部12以及贯通电机座1的通孔13。插接部12上设置有第一导电端子11，电机本体2的引线通过第一导电端子11与外接设备电性连接。当电机座1与电机本体2一体成型时，第一导电端子11可设置在任意合适的位置。
上述电机100，通过在电机座1上设置与电机本体2的引线电连接的第一导电端子11，以使得电机100能够通过第一导电端子11与外接设备电性连接，简化了连接的方式，从而当电机100发生故障时，只需断开第一导电端子11和外接设备的电性连接即可实现对电机100的快速拆卸，无需任何辅助工具，简化了电机拆装的操作，提高了电机更换效率。
图2是本申请一实施例提供的电机固定结构的结构拆分图。该电机固定结构适于安装到各种电机驱动的可移动物体上，以为可移动物体提供动力。在本实施例中，该电机固定结构应用于无人飞行器，其包括飞行器机臂200和与飞行器机臂200可拆卸连接的电机100。该电机100包括电机座1和设于电机座1上并与电机座1可拆卸连接的电机本体2。可以理解的，电机座1和电机本体2也可以一体成型。电机座1上设有凸出的插接部12 和贯通电机座1的通孔13，插接部12上设有与电机本体2的引线电连接的第一导电端子11。
如图3所示，飞行器机臂200上设有安装孔203和用于收容插接部12的插槽202，插槽202内设有与飞行器的控制单元电连接的第二导电端子201。当电机100被安装在飞行器机臂200上时，插接部12插设于插槽202中，使得第一导电端子11和第二导电端子201电性接触，从而完成电机100与飞行器内部的控制单元的电连接。在电机座1上设置插接部12以及在飞行器机臂200相应设置插槽202具有拆装过程中定位更加准确的优点。此处，控制单元可以为电调和/或飞控。
综上，电机100的引线不必穿过飞行器机臂200与控制单元电连接，而是通过第一导电端子11和第二导电端子201实现电连接，当电机100发生故障时，只需断开第一导电端子11和第二导电端子201的电连接即可。因此，这种结构实现了对电机100的快速拆卸，无需任何辅助工具，简化了电机拆装的操作，提高了电机更换效率。
本优选实施例中，第一导电端子11和第二导电端子201分别为导电触点。作为变形的实施方式，第一导电端子11为导电插针，第二导电端子201为与导电插针相适配的导电插孔。或者第一导电端子11为导电插孔，第二导电端子201为与导电插孔相适配的导电插针。当然第一导电端子11和第二导电端子201还可以采用别的类似的端子结构，具体不再加以赘述，只要采用可拆卸的电性连接结构均落入到本实施例保护的范围。
此外，如图2所示，该电机固定结构还包括连接件3，连接件3用于将电机100与飞行器机臂200可拆卸地连接。连接件3穿过电机座1上的通 孔13和飞行器机臂200上的安装孔203从而将电机100可拆卸地连接在飞行器机臂200上。在本实施例中，连接件3为定位稍，在其他实施例中也可以是螺钉。在其他可能的实施例中，电机100与飞行器机臂200之间的可拆卸连接还可以为螺纹连接、滑动连接或者是相互扣合在一起的卡扣连接。
可以理解的，不论是上述的电机还是电机固定结构都可以被应用到现有的飞行器中。
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 (11)

  1. 一种电机(100)，其特征在于，所述电机(100)上设置有第一导电端子(11)，所述电机(100)的引线通过所述第一导电端子(11)与外接设备电性连接。
  2. 根据权利要求1所述的电机(100)，其特征在于，所述电机(100)设有凸出的插接部(12)，所述第一导电端子(11)设置在所述插接部(12)上。
  3. 根据权利要求2所述的电机(100)，其特征在于，所述电机(100)包括电机座(1)和与所述电机座(1)连接的电机本体(2)，所述插接部(12)设于所述电机座(1)上。
  4. 根据权利要求3所述的电机(100)，其特征在于，该电机(100)还包括连接件(3)，所述电机座(1)上设有贯穿所述电机座(1)的通孔(13)，所述电机(100)通过穿过所述通孔(13)的连接件(3)与外接设备连接。
  5. 根据权利要求1-4任一项所述的电机(100)，其特征在于，所述第一导电端子(11)为导电触点、导电插针或导电插孔。
  6. 一种电机固定结构，其特征在于，其包括飞行器机臂(200)和与所述飞行器机臂(200)可拆卸连接的电机(100)，所述电机(100)上设有与所述电机(100)的引线电连接的第一导电端子(11)，所述飞行器机臂(200)上设有与飞行器的控制单元电连接的第二导电端子(201)，所述第一导电端子(11)与第二导电端子(201)电连接。
  7. 根据权利要求6所述的电机固定结构，其特征在于，所述电机(100)上设有凸出的插接部(12)，所述第一导电端子(11)设于所述插接部(12)上，所述飞行器机臂(200)上设有用于***述插接部(12)的插槽(202)，所述第二导电端子(201)设于所述插槽(202)内。
  8. 根据权利要求7所述的电机固定结构，其特征在于，所述电机(100)包括电机座(1)和与所述电机座(1)连接的电机本体(2)，所述插接部(12)设于所述电机座(1)上。
  9. 根据权利要求8所述的电机固定结构，其特征在于，该电机固定结构还包括用于将所述电机(100)与所述飞行器机臂(200)可拆卸连接的连接件(3)，所述电机座(1)上设有贯穿所述电机座(1)的通孔(13)，所述飞行器机臂(200)上设置有安装孔(203)，所述连接件(3)穿过所述通孔(13)和安装孔(203)，所述电机(100)通过所述连接件(3)可拆卸地连接在所述飞行器机臂(200)上。
  10. 根据权利要求9所述的电机固定结构，其特征在于，所述连接件(3)为螺钉或者定位销。
  11. 根据权利要求6-10任一项所述的电机固定结构，其特征在于，所述第一导电端子(11)与所述第二导电端子(201)均为导电触点；或者
    所述第一导电端子(11)为导电插针，所述第二导电端子(201)为导电插孔；或者
    所述第一导电端子(11)为导电插孔，所述第二导电端子(201)为导电插针。
PCT/CN2017/113793 2017-02-27 2017-11-30 电机及电机固定结构 WO2018153136A1 (zh)

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