WO2018090987A1 - 动力组件及飞行器 - Google Patents

动力组件及飞行器 Download PDF

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Publication number
WO2018090987A1
WO2018090987A1 PCT/CN2017/111720 CN2017111720W WO2018090987A1 WO 2018090987 A1 WO2018090987 A1 WO 2018090987A1 CN 2017111720 W CN2017111720 W CN 2017111720W WO 2018090987 A1 WO2018090987 A1 WO 2018090987A1
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WO
WIPO (PCT)
Prior art keywords
base
power assembly
motor
hole
engaging portion
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/CN2017/111720
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English (en)
French (fr)
Inventor
胡亮军
邱龙学
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
Original Assignee
Autel Robotics 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 Autel Robotics Co Ltd filed Critical Autel Robotics Co Ltd
Publication of WO2018090987A1 publication Critical patent/WO2018090987A1/zh
Priority to US16/193,271 priority Critical patent/US10759526B2/en
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
    • F16D1/00—Couplings for rigidly connecting two coaxial shafts or other movable machine elements
    • F16D1/10—Quick-acting couplings in which the parts are connected by simply bringing them together axially
    • F16D1/108—Quick-acting couplings in which the parts are connected by simply bringing them together axially having retaining means rotating with the coupling and acting by interengaging parts, i.e. positive coupling
    • F16D1/112—Quick-acting couplings in which the parts are connected by simply bringing them together axially having retaining means rotating with the coupling and acting by interengaging parts, i.e. positive coupling the interengaging parts comprising torque-transmitting surfaces, e.g. bayonet joints
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/04—Helicopters
    • B64C27/12—Rotor drives
    • B64C27/14—Direct drive between power plant and rotor hub
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/001—Vibration damping devices
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/32—Rotors
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
    • F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
    • F16F15/10—Suppression of vibrations in rotating systems by making use of members moving with the system
    • F16F15/12—Suppression of vibrations in rotating systems by making use of members moving with the system using elastic members or friction-damping members, e.g. between a rotating shaft and a gyratory mass mounted thereon
    • F16F15/121—Suppression of vibrations in rotating systems by making use of members moving with the system using elastic members or friction-damping members, e.g. between a rotating shaft and a gyratory mass mounted thereon using springs as elastic members, e.g. metallic springs
    • F16F15/124—Elastomeric springs
    • F16F15/126—Elastomeric springs consisting of at least one annular element surrounding the axis of rotation
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/001—Vibration damping devices
    • B64C2027/003—Vibration damping devices mounted on rotor hub, e.g. a rotary force generator
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C2211/00—Modular constructions of airplanes or helicopters
    • 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
    • B64U10/14—Flying platforms with four distinct rotor axes, e.g. quadcopters
    • 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 invention relates to the field of aircraft technology, and in particular, to a power component and an aircraft.
  • Existing aircraft typically include a body, an arm coupled to the body, and a power assembly disposed on the arm.
  • the power assembly includes a motor and a propeller coupled to the shaft of the motor.
  • the propeller generally includes a seat body coupled to the rotating shaft of the motor and a propeller coupled to the seat body.
  • the shaft rotates under the action of the motor to drive the blade to rotate.
  • the seat and the shaft are generally threaded.
  • the present invention provides a power unit, a propeller, and an aircraft that are firm and easy to disassemble after assembly.
  • an embodiment of the present invention provides a power component, including:
  • a motor comprising a base body and a motor shaft coupled to the base body;
  • a fixing base is sleeved on the motor shaft and connected to the base body, and the fixing seat is provided with a first engaging portion;
  • a propeller comprising a base and a blade extending from the base, the base being provided with a second engaging portion that is engaged with the first engaging portion, the base being sleeved on the rotating shaft, and passing through the shaft A snap fit of the first latching portion and the second latching portion is coupled to the mount.
  • the fixing base has a top surface away from the base of the motor and an annular body connected to the top surface and enclosing the receiving space with the top surface, the top surface being open a through hole through which the second engaging portion passes, the first engaging portion being disposed on the top surface facing the The surface of the containment space.
  • a plurality of first bumps are disposed along the circumferential surface of the top surface facing the surface of the receiving space, and any two adjacent first bumps are fixed.
  • the second engaging portion is a stopper provided at the base.
  • the base includes a base and a connecting shaft connected to the base, and the second engaging portion is disposed on the connecting shaft.
  • the through hole includes a circular portion through which the connecting shaft passes and an extending portion communicating with the circular portion, the shape of the extending portion and the second engaging portion The shape is the same.
  • the stopper is disposed at a bottom of the base, and the stopper includes a vertical portion connected to a bottom of the base and a blocking portion extending from the vertical portion .
  • the through hole includes a first through hole having the same shape as the stopper and a second through hole communicating with the first through hole, the second through hole being curved .
  • the power assembly further includes an elastic member sleeved on the rotating shaft of the motor, the one end of the elastic member abutting the base toward the bottom surface of the base body, and the other end is opposite to the motor The base is abutted.
  • the power assembly further includes a retaining ring sleeved on the rotating shaft of the motor and located above the elastic member, and one side of the retaining ring abuts the base portion, and the other side Abutting against one end of the elastic member.
  • Another technical solution adopted by the present invention to solve the technical problem is to construct an aircraft comprising a fuselage, an arm connected to the fuselage, and a power assembly as described above provided on the arm.
  • the utility model has the beneficial effects that the propeller is detachably connected to the motor through the cooperation of the first engaging portion and the second engaging portion, which can effectively prevent the propeller from being loosened from the motor under vibration or acceleration, and is disassembled and assembled. Convenient and easy to carry.
  • FIG. 1 is a schematic structural view of an aircraft according to an embodiment of the present invention.
  • FIG. 2 is a schematic structural view of a motor in an embodiment of the present invention.
  • FIG. 4 is a schematic structural view of a retaining ring according to an embodiment of the present invention.
  • Figure 5 is a schematic structural view of one embodiment of the fixing base of the present invention.
  • FIG. 6 is a schematic structural view of another perspective view of the fixing base shown in FIG. 5;
  • Figure 7 is a schematic view showing the structure of one embodiment of the propeller of the present invention.
  • Figure 8 is a schematic view showing the structure of the connecting shaft in the propeller shown in Figure 7;
  • Figure 9 is a bottom view of the connecting shaft shown in Figure 8.
  • Figure 10 is a schematic structural view of another embodiment of the propeller of the present invention.
  • Figure 11 is a schematic structural view of another embodiment of the fixing base of the present invention.
  • FIG. 12 is a schematic structural view of the fixing seat shown in FIG. 11 from another perspective.
  • the aircraft 10 includes a fuselage 11, an arm 12 connected to the body 11, a power assembly 100 disposed at one end of the arm 12, a platform 15 connected to the body 11, and a pan/tilt 13 connected imaging device 14.
  • the number of the arms 12 is four, that is, the aircraft is a quadrotor. In other possible embodiments, the number of the arms 12 may also be 3, 6, 8, 10, and the like.
  • the pan/tilt 15 is used to reduce or even eliminate the vibration transmitted by the power unit 100 to the image device 14, In order to ensure that the imaging device 14 can capture a stable and clear image or video.
  • the imaging device 14 may be a binocular camera, a monocular camera, an infrared imaging device, an ultraviolet imaging device, a camcorder, or the like.
  • the image device 14 may be mounted directly on the aircraft 10 or may be mounted on the aircraft 10 via a platform 15 as shown in this embodiment.
  • the platform 15 allows the imaging device 14 to rotate relative to the aircraft 10 about at least one axis.
  • the power assembly 100 includes a motor 60 disposed at one end of the arm 12, a propeller 20 coupled to the motor 60, and a mount 30.
  • the motor 60 includes a base 63 and a motor shaft connected to the base 63.
  • the motor shaft includes a rotating shaft 61 and a connecting member 62.
  • the diameter of the connecting member 62 is larger than the diameter of the rotating shaft 61.
  • the fixing base 30 is sleeved on the motor shaft and connected to the base 63 of the motor.
  • the fixing base 30 has a top surface 37 away from the base 63 and an annular body 38 which is enclosed with the top surface 37 to form a receiving space 32.
  • the fixing base 30 is provided.
  • four threaded holes 36 are formed in the circumferential direction of the top surface 37, and the fixing base 30 is fixedly coupled to the base 63 of the motor 60 by four screws passing through the threaded holes 36.
  • the power assembly 100 further includes an elastic member 50 sleeved on the motor shaft and a retaining ring 40 sleeved on the motor shaft.
  • the retaining ring 40 is located at the elastic member 50.
  • the elastic member 50 is a reducing spring, and one end having a smaller inner diameter is held on the lower surface of the retaining ring 40, and the other end is supported on the base 63.
  • a through hole 41 similar to a rectangle is opened in the center of the retaining ring 40, and two arcuate notches 42 are also formed in the circumferential direction of the retaining ring 42.
  • first bumps 33 are disposed along the circumferential surface of the top surface 37 of the fixing base 30 toward the surface of the receiving space 32, and any two adjacent ones are first.
  • a fixing groove 35 is formed between the bumps 33.
  • the first engaging portion is a fixing groove 35.
  • the fixing base 30 is further provided with a second protrusion 34 connected to the annular body 38.
  • the second protrusion 34 is disposed along the circumferential direction of the annular body 38 and protrudes from the bottom surface of the annular body 38. And in an arc shape, the second bump 34 is embedded in the notch 42 of the retaining ring 40 in the assembled state.
  • the second projection 34 abuts against the annular inner wall surface 64 (shown in FIG. 2) of the base 63 of the motor to provide a positioning function that facilitates assembly of the mount 30 to the body 63.
  • the propeller 20 includes a base 21, a paddle 22 extending from the base 21, and a second catching portion coupled to the base 21.
  • the second latching portion is a stop 23.
  • the paddle 22 and the base 21 may be integrally formed, and the paddle 22 may be connected to the base 21 by other fixed connections.
  • the base portion 21 includes a base 211 and a connecting shaft 212 connected to the base 211.
  • the stopper 23 is disposed on the connecting shaft 212 and faces away from the central axis of the connecting shaft 212 along the bottom surface of the connecting shaft 212. The direction extends.
  • FIG. 9 is a bottom view of the base 21.
  • a connecting hole (not shown) is formed in the connecting shaft 212 of the base 21 for socketing the motor shaft.
  • the connecting hole further includes a first circular hole 2121 and a second circular hole 2122, the first circular hole 2121 is in communication with the second circular hole 2122, and the diameter of the first circular hole 2121 is larger than the second The diameter of the circular hole 2122 forms a transition surface between the first circular hole 2121 and the second circular hole 2122.
  • the first circular hole 2121 is for receiving the connecting member 62, and the second circular hole 2122 is for receiving the rotating shaft 61.
  • the upper end of the connecting member 62 of the motor shaft abuts against the transition surface of the first circular hole 2121 and the second circular hole 2122. At this time, the connecting shaft 212 cannot continue to move downward, thereby preventing the connecting shaft 212 from being crushed.
  • the role of the elastic member 50 or the retaining ring 40 is formed in the connecting shaft 212 of the base 21 for socketing
  • the top surface 37 of the fixing base 30 also has a through hole 31 for the second latching portion, that is, the stopper 23.
  • the through hole 31 includes a circular portion 31A through which the connecting shaft 212 passes and an extending portion 31B communicating with the circular portion 31A, wherein the shape of the extending portion 31A is the same as the shape of the stopper 23.
  • the stopper 23 on the connecting shaft 212 is aligned with the extending portion 31B of the through hole 31, and the through hole 31 is inserted so that the connecting shaft 212 and the stopper 23 are located in the accommodating space 32, at which time the elastic member 50 is compressed.
  • the state in which the connecting shaft 212 is rotated causes the stopper 23 to be caught in the fixing groove 35.
  • the side of the retaining ring 40 abuts against the bottom surface of the connecting shaft 212 and the stopper 23, and the other The side abuts against the elastic member 50, at which time the stopper 23 is tightly pressed in the fixing groove 35, thereby completing the assembly of the propeller 20 and the motor 60.
  • the function of the retaining ring 40 is: 1.
  • the topping force is evenly distributed; 2.
  • the elastic member 50 is shielded from the structure, so that the inside structure is not visible from the appearance surface, and the modification is performed.
  • the connecting shaft 212 is pressed downward to disengage the stopper 23 from the fixing groove 35, at which time the elastic member 50 is further compressed, and the connecting shaft 212 is rotated to a position where the stopper 23 is aligned with the extending portion 31B of the through hole 31. Pull out the connecting shaft 212 to complete the disassembly.
  • the propeller 20 of the present invention utilizes the snap fit of the stopper 23 and the fixing groove 35 and the motor 60 is fixed.
  • the tightening action of the elastic member 50 and the retaining ring 40 on the stopper 23 further consolidates the connection between the propeller 20 and the motor 60, and can effectively prevent the propeller 20 from being loosened from the motor 60 under vibration or acceleration. It is easy to assemble and disassemble and easy to carry.
  • the propeller 20 includes a base portion 21, a blade 22 extending from the base portion 21, and a stopper 23 provided on the bottom surface of the base portion 21.
  • the bottom surface of the base portion 21 is further provided with a receiving hole for receiving the rotating shaft of the motor.
  • the stop 23 includes a vertical portion and a barrier that is generally perpendicular to the vertical portion, i.e., the stop 23 is generally L-shaped.
  • the bottom surface of the base portion 21 is provided with two stoppers 23, and the two stoppers 23 are symmetrically disposed with respect to the central axis of the base portion 21.
  • the fixing base 30 includes a through hole 31, a receiving space 32, a first projection 33, a second projection 34, a fixing groove 35, a screw hole 36, and a shaft hole 37.
  • the shaft hole 37 is disposed at a center of an upper end of the fixing base 30.
  • the through hole 31 is disposed at two sides of the shaft hole 37, and each of the through holes 31 includes a shape matching a blocking portion of the stopper 23.
  • the first through hole and the second through hole 31B communicating with the first through hole 31A, wherein the second through hole 31B is curved.
  • the two through holes 31 are disposed symmetrically with respect to the shaft hole 37.
  • the stopper 23 passes through the through hole 31 and is inserted into the fixing base 30.
  • the fixing base 30 has a cylindrical shape, and the lower surface of the fixing base 30 is recessed to form a receiving space 32, and the receiving space 32 communicates with the through hole 31.
  • the bottom of the receiving space 32 extends downwardly to form a first bump 33 and a second bump 34, and the first bump 33 and the second bump 34 are both, the first bump A fixing groove 35 is formed between the 33 and the second bump 34.
  • the first bumps 33, the fixing grooves 35, the second bumps 34, and the through holes 31 are sequentially distributed along a circular trajectory of the accommodating space 32.
  • the height of the first protrusion 33 protruding from the bottom of the receiving space 32 is greater than the height of the second protrusion 34.
  • the stopper 23 is embedded in the fixing groove 35, and both sides are caught by the sidewalls of the first protrusion 33 and the second protrusion 34, thereby preventing the stopper 23 from being opposite to the fixing seat 30.
  • a rotation occurs.
  • Four through holes 36 are provided around the through hole 31, and the bolts are fixed to the base 63 of the motor 60 through the screw holes 36.
  • the elastic member 50 is sleeved on the motor shaft 61, and the elastic member 50 and the motor shaft 61 pass through the shaft hole 37 together, and one end of the elastic member 50 abuts the motor 60.
  • the base 63 has the other end for holding the lower end end surface of the base portion 31 such that the stopper 23 is embedded in the fixing groove 35 and cannot be moved downward to be disengaged from the fixing groove 35, thereby making the propeller 20
  • the fixing groove 35 and the elastic member 50 act together to be firmly fixed.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Acoustics & Sound (AREA)
  • Motor Or Generator Frames (AREA)
  • Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
  • Snaps, Bayonet Connections, Set Pins, And Snap Rings (AREA)

Abstract

一种动力组件及具有动力组件的飞行器，包括：电机（60）、固定座（30）和螺旋桨（20）。其中，固定座（30）套设于电机转轴（61）上并固定于电机的基体（63）上，固定座（30）设有第一卡接部。螺旋桨（20）包括基部（21）和自基部延伸的桨叶（22），基部（21）设有与第一卡接部卡接的第二卡接部。通过第一卡接部和第二卡接部的配合将螺旋桨（20）可拆卸地与电机（60）相连，能够有效防止螺旋桨（20）在振动或者有加速度的情况下与电机松脱，且拆装方便，便于携带。

Description

动力组件及飞行器 【技术领域】
本发明涉及飞行器技术领域，尤其涉及一种动力组件及飞行器。
【背景技术】
现有的飞行器通常包括机体、与机体相连的机臂以及设于机臂上的动力组件。动力组件包括电机和与电机的转轴相连的螺旋桨。螺旋桨一般包括与电机的转轴相连的座体和与座体相连的螺旋桨。该转轴在电机的作用下旋转从而带动桨叶旋转。目前，座体与转轴一般采用螺纹连接。
当座体与转轴采用螺纹连接时，由于座体的旋紧方向与桨叶在工作过程中的转动方向相同，桨叶在启动和工作过程中和转轴连接良好，但是在桨叶突然降速或者加速度变化较大的情况下，在加速度的作用下，座体与转轴易发生松脱。此外，在振动幅度较大的情况下，螺旋桨与电机转轴也容易发生松脱，导致射桨。且在螺旋桨发生碰撞后，螺旋桨需要工具才可以拧下。
【发明内容】
鉴于上述问题，本发明提供一种组装后牢固且便于拆卸的动力装置、螺旋桨以及飞行器。
为了达到上述目的，本发明实施例提供一种动力组件，包括：
电机，包括基体和与所述基体相连的电机转轴；
固定座，套设于所述电机转轴并与所述基体相连，所述固定座设有第一卡接部；
螺旋桨，包括基部和自所述基部延伸的桨叶，所述基部设有与所述第一卡接部卡接的第二卡接部，所述基部套设于所述转轴，并通过所述第一卡接部与所述第二卡接部的卡接配合与所述固定座相连。
在本发明的一实施例中，所述固定座具有远离所述电机的基体的顶面和与所述顶面相连并与所述顶面围成收容空间的环形主体，所述顶面开设有供所述第二卡接部通过的通孔，所述第一卡接部设于所述顶面朝向所述 收容空间的表面。
在本发明的一实施例中，沿所述顶面朝向所述收容空间的表面的周向间隔设置设有多个第一凸块，任意相邻两个所述第一凸块之间形成固定槽，所述第一卡接部为所述固定槽。
在本发明的一实施例中，所述第二卡接部为设于所述基部的挡块。
在本发明的一实施例中，所述基部包括基座和与所述基座相连的连接轴，所述第二卡接部设于所述连接轴。
在本发明的一实施例中，所述通孔包括供所述连接轴通过的圆形部和与所述圆形部连通的延伸部，所述延伸部的形状与所述第二卡接部的形状相同。
在本发明的一实施例中，所述挡块设于所述基部的底部，所述挡块包括与所述基部的底部相连的竖直部以及自所述竖直部弯折延伸的阻挡部。
在本发明的一实施例中，所述通孔包括与所述挡块形状相同的第一通孔和与所述第一通孔连通的第二通孔，所述第二通孔呈弧形。
在本发明的一实施例中，所述动力组件还包括套设于所述电机转轴的弹性部件，所述弹性部件一端与所述基部朝向所述基体的底面抵接，另一端与所述电机的基体抵接。
在本发明的一实施例中，所述动力组件还包括套设于所述电机转轴的挡圈并位于所述弹性部件的上方，所述挡圈一侧与所述基部抵接，另一侧与所述弹性部件的一端抵接。
本发明解决其技术问题采用的另一技术方案为：构造一种飞行器，包括机身、与所述机身相连的机臂以及设于所述机臂的如上述所述的动力组件。
本发明的有益效果是：通过第一卡接部和第二卡接部的配合将螺旋桨可拆卸地与电机相连，能够有效防止螺旋桨在振动或者有加速度的情况下与电机松脱，且拆装方便，便于携带。
【附图说明】
图1为本发明实施例中一种飞行器的结构示意图；
图2为本发明实施例中电机的结构示意图；
图3为本发明实施例中电机与固定座的分解图；
图4为本发明实施例中挡圈的结构示意图；
图5为本发明的固定座其中一实施例的结构示意图；
图6为图5所示固定座另一视角的结构示意图；
图7为本发明的螺旋桨其中一实施例的结构示意图；
图8为图7所示螺旋桨中连接轴的结构示意图；
图9为图8所示连接轴的仰视图；
图10为本发明的螺旋桨另一实施例的结构示意图；
图11为本发明的固定座另一实施例的结构示意图；
图12为图11所示的固定座另一视角的结构示意图。
【具体实施方式】
为了便于理解本发明，下面结合附图和具体实施方式，对本发明进行更详细的说明。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”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发明的技术领域的技术人员通常理解的含义相同。本说明书中在本发明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，不是用于限制本发明。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。
如图1-图3所示，飞行器10包括机身11、与机身11相连的机臂12、设置在机臂12一端的动力组件100、与机身11相连的云台15以及与云台13相连的影像设备14。
在本实施例中，机臂12的数量为4，即该飞行器为四旋翼飞行器，在其他可能的实施例中，机臂12的数量也可以为3、6、8、10等。
云台15用于减轻甚至消除动力组件100传递给影像设备14的振动， 以保证影像设备14能够拍摄出稳定清晰的图像或视频。
影像设备14可以是双目摄像头、单目摄像头、红外线影像设备、紫外线影像设备、摄录机等类似的设备。影像设备14可以直接搭载在飞行器10上，也可以通过如本实施例所示的云台15搭载在飞行器10上，云台15允许影像设备14相对于飞行器10绕至少一个轴转动。
动力组件100包括设置在机臂12一端的电机60、与电机60相连的螺旋桨20和固定座30。
电机60包括基体63和与基体63相连的电机转轴，电机转轴包括转轴61和连接件62，连接件62的直径大于转轴61的直径。
如图3所示，固定座30套设于电机转轴并与电机的基体63相连。在本发明的一实施例中，如图5和图6所示，固定座30具有远离基体63的顶面37和与顶面37共同围成收容空间32的环形主体38，固定座30上设有第一卡接部。在本发明的一实施例中，沿顶面37的周向贯通有4个螺纹孔36，固定座30通过4个穿过螺纹孔36的螺钉与电机60的基体63固定连接。
如图3和图4所示，在本发明的一实施例中，动力组件100还包括套设于电机转轴的弹性部件50以及套设于电机转轴的挡圈40，挡圈40位于弹性部件50的上方。在本发明的一实施例中，弹性部件50为变径弹簧，内径较小的一端顶持在所述挡圈40的下表面，另一端顶持在基体63上。挡圈40中央开设有类似于矩形的通孔41，在挡圈42的周向还开设有两个弧形的缺口42。
如图6所示，在本发明的一实施例中，沿固定座30的顶面37朝向收容空间32的表面的周向间隔设置有4个第一凸块33，任意相邻两个第一凸块33之间形成固定槽35。在本发明的一实施例中，第一卡接部为固定槽35。
在本发明的一实施例中，固定座30还设有与环形主体38相连的第二凸块34，该第二凸块34沿环形主体38的周向设置且凸出于环形主体38的底面并呈弧形，第二凸块34在装配状态下，嵌入挡圈40的缺口42内。该第二凸块34与电机的基体63的环形内壁面64(如图2所示)抵接从而起到定位的作用，该结构使得固定座30与机体63的装配更加容易。
如图7-图9所示，在本发明的一实施例中，螺旋桨20包括基部21、自基部21延伸的桨叶22以及与基部21相连的第二卡接部。在本发明的一实施例中，第二卡接部为挡块23。桨叶22与基部21可以一体成型，桨叶22也可以通过其他固定连接的方式与基部21相连。在本发明的一实施例中，基部21包括基座211和与基座211相连的连接轴212，挡块23设置在连接轴212上，并沿连接轴212的底面向远离连接轴212中心轴的方向延伸。
图9为基部21的仰视图。基部21的连接轴212内开设有连接孔(图未标示)，用于套接电机转轴。所述连接孔又包括第一圆孔2121和第二圆孔2122，所述第一圆孔2121与所述第二圆孔2122连通，且所述第一圆孔2121的直径大于所述第二圆孔2122的直径，第一圆孔2121与第二圆孔2122之间形成过渡面。所述第一圆孔2121用于收容连接件62，所述第二圆孔2122用于收容转轴61。在装配状态下，电机转轴的连接件62的上端与第一圆孔2121和第二圆孔2122的过渡面抵接，此时连接轴212无法继续向下移动，起到防止连接轴212压坏弹性部件50或挡圈40的作用。
如图5所示，固定座30的顶面37还贯通有供第二卡接部即挡块23通孔31。在本发明的一实施例中，通孔31包括供连接轴212通过的圆形部31A和与圆形部31A连通的延伸部31B，其中，延伸部31A的形状与挡块23的形状相同。
在装配时，将连接轴212上的挡块23对准通孔31的延伸部31B，并插入通孔31使得连接轴212及挡块23位于收容空间32内，此时弹性部件50处于被压缩的状态，转动连接轴212使得挡块23卡入固定槽35内，在弹性部件50的弹性回复力的作用下，挡圈40一侧与连接轴212的底面以及挡块23抵接，另一侧与弹性部件50抵接，此时，挡块23被紧紧压在固定槽35内，从而完成螺旋桨20与电机60的装配。在本发明的实施例中，挡圈40的作用为：1、平均分配顶持力；2、遮避所述弹性部件50，让人从外观面看不到里面的结构，起修饰作用。
在拆卸时，向下按压连接轴212，使挡块23脱离固定槽35，此时弹性部件50被进一步压缩，将连接轴212转动至挡块23与通孔31的延伸部31B对准的位置，拉出连接轴212即可完成拆卸。
本发明的螺旋桨20利用挡块23与固定槽35的卡接配合与电机60固 定，并通过弹性部件50和挡圈40对挡块23的压紧作用进一步巩固螺旋桨20与电机60之间的连接，能够有效防止螺旋桨20在振动或者有加速度的情况下与电机60松脱，且拆装方便，便于携带。如图10所示，螺旋桨20包括基部21、自基部21延伸的桨叶22和以及设置于基部21底面的挡块23。基部21的底面还开设有用于收容电机转轴的收容孔。在本发明的实施例中，挡块23包括竖直部和与所述竖直部大体垂直的阻挡部，即，挡块23大体呈L形。基部21的底面设有两个挡块23，且两个挡块23相对于基部21的中心轴呈对称设置。
如图11和12所示，固定座30包括通孔31、收容空间32、第一凸块33、第二凸块34、固定槽35、螺纹孔36和轴孔37。所述轴孔37设置于所述固定座30上端的中央处，所述通孔31设置于所述轴孔37的两侧，每一个通孔31均包括与挡块23的阻挡部形状相匹配的第一通孔和与第一通孔31A连通的第二通孔31B，其中，第二通孔31B呈弧形。两个通孔31相对于轴孔37呈中心对称设置。
所述挡块23穿过所述通孔31，插入所述固定座30中。具体的，在本实施例中，所述固定座30呈圆柱状，所述固定座30的下表面向内凹陷形成收容空间32，所述收容空间32与所述通孔31连通。所述收容空间32的底部分别向下延伸形成第一凸块33和第二凸块34，所述第一凸块33和所述第二凸块34均有两个，所述第一凸块33和第二凸块34之间形成固定槽35。第一凸块33、固定槽35、第二凸块34和通孔31沿所述收容空间32的圆形轨迹依次分布。所述第一凸块33凸出于所述收容空间32底部的高度大于所述第二凸块34的高度。所述挡块23嵌入所述固定槽35中，并且两侧被所述第一凸块33和第二凸块34的侧壁卡住，进而防止所述挡块23相对于所述固定座30发生转动。所述通孔31周围设有四个螺纹孔36，螺栓穿过所述螺纹孔36将所述固定座30固定于电机60的基体63上。所述弹性部件50套设于所述电机转轴61上，并且所述弹性部件50和所述电机转轴61共同穿过所述轴孔37，所述弹性部件50的一端抵持所述电机60的基体63，另一端用于顶持所述基部31的下端端面，使得所述挡块23嵌入所述固定槽35中，无法向下移动以脱离出所述固定槽35，从而使所述螺旋桨20在所述固定槽35和弹性部件50共同作用下，被牢固的固定住。
以上所述仅为本发明的实施方式，并非因此限制本发明的专利范围，凡是利用本发明说明书及附图内容所作的等效结构或等效流程变换，或直接或间接运用在其他相关的技术领域，均同理包括在本发明的专利保护范围内。

Claims (11)

  1. 一种动力组件，其特征在于，包括：
    电机，包括基体和与所述基体相连的电机转轴；
    固定座，套设于所述电机转轴并与所述基体相连，所述固定座设有第一卡接部；
    螺旋桨，包括基部和自所述基部延伸的桨叶，所述基部设有与所述第一卡接部卡接的第二卡接部，所述基部套设于所述转轴，并通过所述第一卡接部与所述第二卡接部的卡接配合与所述固定座相连。
  2. 根据权利要求1所述的动力组件，其特征在于，所述固定座具有远离所述电机的基体的顶面和与所述顶面相连并与所述顶面围成收容空间的环形主体，所述顶面开设有供所述第二卡接部通过的通孔，所述第一卡接部设于所述顶面朝向所述收容空间的表面。
  3. 根据权利要求2所述的动力组件，其特征在于，沿所述顶面朝向所述收容空间的表面的周向间隔设置设有多个第一凸块，任意相邻两个所述第一凸块之间形成固定槽，所述第一卡接部为所述固定槽。
  4. 根据权利要求1-3任一项所述的动力组件，其特征在于，所述第二卡接部为设于所述基部的挡块。
  5. 根据权利要求1-4所述的动力组件，其特征在于，所述基部包括基座和与所述基座相连的连接轴，所述第二卡接部设于所述连接轴。
  6. 根据权利要求5所述的动力组件，其特征在于，所述通孔包括供所述连接轴通过的圆形部和与所述圆形部连通的延伸部，所述延伸部的形状与所述第二卡接部的形状相同。
  7. 根据权利要求4所述的动力组件，其特征在于，所述挡块设于所述 基部的底部，所述挡块包括与所述基部的底部相连的竖直部以及自所述竖直部弯折延伸的阻挡部。
  8. 根据权利要求7所述的动力组件，其特征在于，所述通孔包括与所述阻挡部的形状相匹配的第一通孔和与所述第一通孔连通的第二通孔，所述第二通孔呈弧形。
  9. 根据权利要求2-8任一项所述的动力组件，其特征在于，所述动力组件还包括套设于所述电机转轴的弹性部件，所述弹性部件一端与所述基部朝向所述基体的底面抵接，另一端与所述电机的基体抵接。
  10. 根据权利要求9所述的动力组件，其特征在于，所述动力组件还包括套设于所述电机转轴的挡圈并位于所述弹性部件的上方，所述挡圈一侧与所述基部抵接，另一侧与所述弹性部件的一端抵接。
  11. 一种飞行器，其特征在于，包括机身、与所述机身相连的机臂以及设于所述机臂的如权利要求1-10任一项所述的动力组件。
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