WO2022236820A1 - 螺旋桨、动力装置、动力系统及无人飞行器 - Google Patents

螺旋桨、动力装置、动力系统及无人飞行器 Download PDF

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Publication number
WO2022236820A1
WO2022236820A1 PCT/CN2021/093883 CN2021093883W WO2022236820A1 WO 2022236820 A1 WO2022236820 A1 WO 2022236820A1 CN 2021093883 W CN2021093883 W CN 2021093883W WO 2022236820 A1 WO2022236820 A1 WO 2022236820A1
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WIPO (PCT)
Prior art keywords
propeller
upper cover
fixed
power device
drive motor
Prior art date
Application number
PCT/CN2021/093883
Other languages
English (en)
French (fr)
Inventor
李齐
陈鹏
蒋再龙
Original Assignee
深圳市大疆创新科技有限公司
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 深圳市大疆创新科技有限公司 filed Critical 深圳市大疆创新科技有限公司
Priority to CN202180081868.7A priority Critical patent/CN116710358A/zh
Priority to PCT/CN2021/093883 priority patent/WO2022236820A1/zh
Publication of WO2022236820A1 publication Critical patent/WO2022236820A1/zh

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    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64UUNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U30/00Means for producing lift; Empennages; Arrangements thereof
    • B64U30/20Rotors; Rotor supports
    • B64U30/29Constructional aspects of rotors or rotor supports; Arrangements thereof
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C27/00Rotorcraft; Rotors peculiar thereto
    • B64C27/04Helicopters
    • B64C27/12Rotor drives
    • B64C27/14Direct drive between power plant and rotor hub

Definitions

  • the present application relates to the technical field of unmanned aerial vehicles, in particular to a propeller, a power device, a power system and an unmanned aerial vehicle.
  • Drones are mainly used for aerial photography, follow-up photography and other scenarios, with high safety and operability.
  • the portability of drones has always been the focus of attention in the industry.
  • the present application provides a propeller, a power device, a power system and an unmanned aerial vehicle.
  • a power device for connecting with a propeller including a drive motor for connecting with the propeller, and the drive motor is used for driving the propeller to rotate;
  • the drive motor includes a rotating part and an upper cover, the upper cover is a single-layer structure, directly connected to the rotor of the drive motor, and the rotor of the drive motor and the upper cover are made of different materials;
  • the upper cover is used for fixed connection with the propeller, so that the rotor of the drive motor is fixedly connected with the propeller, and when the rotor of the drive motor rotates, the propeller is driven to rotate.
  • a propeller for connecting with a power device including a propeller hub for connecting with the power device;
  • the propeller hub is provided with a fixing part, and the fixing part includes a buckle part, and the buckle part is provided with a groove part for buckling with the power device, and the groove part includes a bottom wall and a The side walls on both sides of the bottom wall; when the propeller is connected to a power device, the groove part is used to clamp the assembly part of the power device, so that the propeller is fixedly connected to the power device;
  • the fixing part includes an extension part, the extension part extends from the hub to a direction away from the hub, and the buckle part is connected to an end part of the extension part away from the hub;
  • the extension part is used to partially extend into the power device, and the buckle part is used to engage with the power device.
  • a power system including a propeller and a power device connected to the propeller, the propeller includes a hub for connecting with the power device, and the power device includes a propeller for driving a driving motor for the rotation of the propeller hub;
  • the drive motor includes a rotating part and an upper cover, the upper cover is a single-layer structure, directly connected to the rotor of the drive motor, and the rotor of the drive motor and the upper cover are made of different materials;
  • the propeller is fixedly connected with the upper cover, so that the propeller is fixedly connected with the rotor of the drive motor, and when the rotor of the drive motor rotates, the propeller is driven to rotate.
  • an unmanned aerial vehicle including: a fuselage and the power system according to the third aspect, the power device of the power system is installed on the fuselage.
  • the application sets the upper cover as a single-layer structure, which is directly connected with the rotor of the driving motor, and does not require additional paddle seats to load the upper cover on the driving motor, reducing the number of parts , to achieve the effect of reducing the weight of the power unit, and can also save the axial space of the power unit, which is beneficial to reducing the size of the drone.
  • the rotor and the upper cover of the drive motor are made of different materials, and the upper cover can be made of lighter materials, which can further reduce the weight of the power device.
  • FIG. 1 is a three-dimensional schematic diagram of a power system in an embodiment of the present application.
  • Fig. 2 is an exploded schematic diagram of a power system in an embodiment of the present application.
  • Fig. 3 is a perspective schematic diagram of the power system in an embodiment of the present application after the blades are removed.
  • Fig. 4 is a schematic perspective view of another perspective of the power system in an embodiment of the present application after removing the blades.
  • Fig. 5 is an exploded schematic view of the power system in an embodiment of the present application after the blades are removed.
  • Fig. 6 is a schematic perspective view of an upper cover of a power device of a power system in another embodiment of the present application.
  • Fig. 7 is a schematic perspective view from another perspective of the upper cover of the power device of the power system in another embodiment of the present application.
  • Fig. 8 is a schematic perspective view of the power system without the blades in another embodiment of the present application.
  • Fig. 9 is a perspective view of another perspective view of the power system without the blades in another embodiment of the present application.
  • Fig. 10 is a schematic cross-sectional view of the power system without the blades in another embodiment of the present application.
  • Fig. 11 is a schematic diagram of the connection between the upper cover and the collar of the power device of the power system in an embodiment of the present application.
  • Fig. 12 is a schematic cross-sectional view of the upper cover of the power device of the power system in an embodiment of the present application.
  • FIG. 13 is a schematic cross-sectional view of the upper cover and collar of the power device of the power system in an embodiment of the present application.
  • Fig. 14 is a schematic cross-sectional view of the upper cover and collar of the power device of the power system in another embodiment of the present application.
  • FIG. 15 is a partially enlarged schematic view of FIG. 14 .
  • Fig. 16 is a schematic diagram of the connection between the upper cover and the elastic member of the power device of the power system in another embodiment of the present application.
  • Fig. 17 is a schematic cross-sectional view of the upper cover and the elastic component of the power device of the power system in another embodiment of the present application.
  • 18 and 19 are schematic diagrams of the fool-proof structure of the upper cover and the propeller hub of the power device of the power system in an embodiment of the present application.
  • An embodiment of the present application provides a power system, including a power device 1 and a propeller 2 connected to the power device 1 .
  • the power device 1 includes a driving motor 70 for connecting with the propeller 2, and the driving motor is used for driving the propeller to rotate.
  • the propeller 2 includes a hub 10 for connecting with the power device 1 and at least one blade 60 mounted on the hub 10 .
  • the drive motor 70 includes a rotating part and an upper cover 20, the upper cover 20 is a single-layer structure, directly connected with the rotor of the drive motor 70, and the rotor of the drive motor 70 and the upper cover 20 respectively adopt Made of different materials.
  • the upper cover 20 is used to be fixedly connected with the propeller, so that the rotor of the drive motor 70 is fixedly connected with the propeller, and when the rotor of the drive motor rotates, the propeller is driven to rotate.
  • the rotor of the driving motor 70 may be an outer rotor or an inner rotor. In this embodiment, the rotor of the drive motor 70 is an outer rotor.
  • the upper cover 20 is set as a single-layer structure, which is directly connected with the rotor of the driving motor 70, and no additional structures such as paddle seats are required to load the upper cover 20 on the driving motor 70, thereby reducing the number of parts and reducing power.
  • the effect of the weight of the device 1 can also save the axial (vertical direction shown in FIG. 1 ) space of the power device 1, which is conducive to reducing the size of the drone.
  • the rotor and the upper cover of the drive motor 70 are made of different materials, for example, the mass density of the material used for the yoke of the rotor is greater than that of the material used for the upper cover 20, which can further reduce the weight of the power unit.
  • the yoke of the rotor is made of copper
  • the material of the upper cover 20 is made of light aluminum alloy.
  • the upper cover 20 is provided with an assembly hole 21 or a fixing portion for snap-fitting with the propeller 2
  • the propeller 2 is provided with a corresponding fixing portion or an assembly hole 21
  • the assembly hole 21 is provided with
  • the upper cover 20 is provided with an assembly hole 21, and the propeller hub 10 of the propeller 2 is provided with a fixing portion 11, and the assembly hole 21 is provided with an assembly portion for snap-fitting with the fixing portion 11 of the propeller 2 .
  • the fixing part 11 and the assembling part can be connected in various ways, which will be described in detail below.
  • the propeller hub 10 and the upper cover 20 are fixed by the snap fit between the fixing part 11 and the assembling part, avoiding the use of propeller seats and screws to connect the propeller hub 10 and the upper cover 20, which can reduce the number of parts and simplify the assembly process. The cost is reduced, and the effect of reducing the weight of the power unit is achieved.
  • a first through hole 26 is formed in the middle of the upper cover 20 , and the driving motor 70 includes a motor shaft 71 , and the motor shaft 71 extends into the first through hole 26 and is drivingly connected with the propeller hub 10 .
  • the propeller hub 10 of the propeller 2 is provided with a mounting portion 27 for installing the blade 60, the propeller hub 10 may include a first propeller clip 16, an intermediate connector 17 and a second propeller clip 18, the fixing portion 11 is arranged on the second propeller clip 18 The bottom of a paddle clip 16, the intermediate connector 17 is connected to the top of the first paddle clip 16, and the installation part 27 is formed between the second paddle clip 18 and the first paddle clip 16 .
  • the number of paddle blades 60 is two, and the intermediate connecting piece 17 is connected in the middle of the first paddle clip 16 and the second paddle clip 18, forming a mounting pad on both sides of the intermediate connecting piece 17. part 27, each mounting part 27 is clamped with a paddle 60.
  • the driving motor 70 may include a casing, and the upper cover 20 includes a covering portion, and the covering portion is disposed on the casing. A plurality of ribs 28 are arranged at intervals on the bottom of the upper cover 20 to facilitate the connection between the upper cover 20 and the drive housing.
  • the fitting part includes a protrusion 22 protruding from the inner side wall of the fitting hole 21 into the fitting hole 21, and the protrusion 22 is used for It is clamped with the fixed part 11 of the propeller 2 .
  • the protrusion 22 is formed by the assembly hole 21 protruding toward the middle of the upper cover 20 .
  • the fixing part 11 of the propeller hub 10 of the propeller 2 includes a buckle part 13, and the buckle part 13 is provided with a groove part 14 for buckling with the protrusion 22 of the assembly part of the power plant 1, and the groove part 14
  • the portion 14 includes a bottom wall 141 and side walls 142 located on both sides of the bottom wall 141 .
  • the fixing part 11 may also include an extension part 12, the extension part 12 is extended from the hub 10 to a direction away from the hub 10 (shown as extending downward in FIG. 5 ), which can also be understood as , the extension part 12 is extended from the hub 10 to a direction away from the hub 10, the buckle part 13 is connected to the end of the extension part 12 away from the hub 10, the extension The part 12 is used for partially protruding into the power device, and the buckle part 13 is used for locking with the power device.
  • the extension part 12 When the fixing part 11 is connected with the assembling part, the extension part 12 partly extends into the assembling hole 21, and the groove part 14 of the buckling part 13 engages with the protrusion 22 in the assembling hole 21, so that the propeller hub 10 is fixed with loam cake 20.
  • the extension part 12 of the fixing part 11 passes through the assembly hole 21 downwards and then is screwed in along a preset direction to move the groove part 14 of the buckle part 13 To the position corresponding to the protruding block 22 , and then move upwards so that the groove portion 14 and the protruding block 22 are engaged with each other, so that the fixing portion 11 is engaged with the assembly portion.
  • the groove portion 14 includes a bottom wall 141 and side walls 142 located on two sides of the bottom wall 141 .
  • the assembling part includes a protrusion 22 snap fit with the groove part 14 .
  • the protrusion 22 snaps into the groove portion 14 , so as to realize the connection between the propeller hub 10 and the upper cover 20 .
  • the protrusion 22 is snapped into the groove portion 14, the two sides of the protrusion 22 abut against the side walls 142 on both sides of the bottom wall 141 respectively, and the protrusion 22 is far away from the assembly.
  • the gap 143 is greater than the thickness of the side wall 142 .
  • the number of the assembling holes 21 can be set in multiples, and they are uniformly arranged on the upper cover 20 along the circumference, and each assembling hole 21 is provided with the assembling part.
  • the propeller hub 10 is provided with fixing portions 11 corresponding to the number and positions of the assembly holes 21 , and are uniformly arranged on the propeller hub 10 along the circumference. Each fixing portion 11 is clamped and fixed with the corresponding assembly hole 21 , and fixes the propeller hub 10 and the upper cover 20 in all directions along the circumference of 360°.
  • the fitting part includes a slot 23 and a boss 24 , and the slot 23 is located between the side wall of the fitting hole 21 and the boss 24 between, the clamping groove 23 is used for clamping with the fixed part 11 of the propeller 2, and the side wall of the boss 24 and the mounting hole 21 is used for connecting the clamping groove 23 with the paddle of the propeller 2.
  • the hub 10 abuts against the fixing portion 11 when snapped into place.
  • the power device 1 may further include an elastic member 30 disposed on the upper cover 20, and the elastic member 30 is used for When the upper cover 20 is fixed with the fixing part 11 of the propeller 2, it resists the propeller 2, so as to push the propeller hub 10 away from the upper cover 20, and cooperate with the fixing part 11 and the buckle part 13 to engage with each other.
  • the power of the propeller hub 10 and the loam cake 20 are fixed more firmly.
  • Fixing the elastic component 30 on the upper cover 20 is used to fix the propeller hub 10 and the upper cover 20, which is convenient for automatic assembly and has better manufacturability. It can also avoid the use of screws to connect the propeller hub 10 and the upper cover 20 , avoiding reliability risks caused by loose screws.
  • the power device 1 may further include a collar 50 fixed to the upper cover 20 , one end of the elastic member 30 is fixed to the collar 50 , and the elastic member 30 is fixed to the upper cover 20 through the collar 50 .
  • the elastic member 30 may adopt a spring.
  • An end surface of the upper cover 20 is provided with a receiving groove 40 , and an end portion of the elastic member 30 is accommodated in the receiving groove 40 .
  • the collar 50 is sleeved on the outside of the elastic member 30 and fixed in the receiving groove 40, and the end of the elastic member 30 is fixed in the receiving groove 40, as shown in FIG. 11 , so that the elastic The component 30 is fixed on the upper cover 20 .
  • the elastic member 30 may include a body portion 31 and a connection end 32 connected to the body portion 31, the connection end 32 is accommodated in the receiving groove 40, and the connection end 32 The size is larger than the size of the body part 31 .
  • the inner diameter of the collar 50 is smaller than the size of the connecting end 32 and larger than the size of the body part 31 , and the collar 50 is sleeved on the outside of the body part 31 and fixed in the receiving groove 40 , the connecting end 32 is fixed in the receiving groove 40, thereby fixing the elastic member 30 in the receiving groove 40, that is, the connecting end 32 of the elastic member 30 is covered with a collar, and the elastic member 30 is fixed in the receiving groove 40. In the slot 40.
  • the collar 50 can be fixed to the upper cover 20 in various ways. To prevent the collar from falling off the motor cover.
  • the collar 50 and the receiving groove 40 can be fixed by glue.
  • the collar 50 and the receiving groove 40 can be fixed by an interference fit.
  • the side wall of the receiving groove 40 may be provided with a stepped hole 41, and the side of the collar 50 is provided with a The raised portion 51 is engaged with the stepped hole 41 , that is, the bottom of the collar 50 is engaged with the receiving groove 40 through an undercut structure. Referring to Fig. 16 and Fig.
  • the end of the elastic component 30 and the receiving groove 40 are directly riveted and fixed, and the collar 50 can be omitted to fix the elastic component 30 and the upper cover 20 .
  • the ends of the elastic component 30 are riveted and fixed to the upper cover 20 through a plurality of riveting parts 42 , so as to fix the elastic component 30 in the receiving groove 40 .
  • Multiple riveting parts 42 may be provided and evenly arranged along the circumferential direction of the elastic component 30 to ensure that the elastic component 30 is firmly connected to the upper cover 20 .
  • the end of the elastic component 30 can also be directly welded to the receiving groove 40 , and the collar 50 can also be omitted to fix the elastic component 30 to the upper cover 20 .
  • the motor upper cover 20 and the propeller hub 10 need to be differentiated for foolproofing.
  • patterns of different colors or different characters can be printed on the upper cover 20 and the propeller hub 10 to distinguish them.
  • the collars of the forward propeller and the collars of the reverse propeller may also be distinguished by different colors.
  • the structure and size of the upper cover and the propeller hub can also be distinguished.
  • the propellers include a first propeller (such as a forward propeller) and a second propeller (such as a reverse propeller), and the drive motor includes a first drive motor (such as a forward motor) and a second drive motor (such as a reverse motor) .
  • a first propeller is mountable to the first drive motor and not mountable to the second drive motor.
  • the second propeller can be mounted to the second drive motor and cannot be mounted to the first drive motor, thereby playing a foolproof effect.
  • the first propeller is, for example, a forward propeller
  • the second propeller is, for example, a reverse propeller
  • the first driving motor is, for example, a forward motor
  • the second driving motor is, for example, a reverse motor
  • the first propeller is a forward propeller
  • the second propeller is a reverse propeller
  • the first driving motor is a forward motor
  • the second driving motor is a reverse motor for example.
  • the forward propeller and the forward motor rotate clockwise
  • the reverse propeller and the reverse motor rotate counterclockwise.
  • the side of the assembly hole is provided with a fool-proof hole communicating with the assembly hole.
  • the fool-proof hole is configured to fit the propeller.
  • the fool-proof holes are not suitable for the propellers, so as to prevent the power unit from being equipped with propellers of different rotation directions.
  • the size of the fool-proof hole of the upper cover adapted to the forward propeller and the size of the fool-proof hole of the upper cover adapted to the reverse propeller can be set to different sizes, and the forward propeller and the upper cover of the adapted reverse propeller
  • the fool-proof hole of the upper cover is not compatible with the forward propeller, so as to prevent the forward propeller from being assembled with the upper cover.
  • the fool-proof hole of the upper cover is not compatible with the reverse propeller, so as to prevent the reverse propeller from being assembled with the upper cover, thereby playing the role of distinguishing fool-proof. Through the above settings, it plays the role of size foolproof.
  • the fool-proof holes abut against the propellers to prevent the power unit from being equipped with propellers of different rotation directions.
  • the size of the fool-proof hole of the upper cover of the forward propeller and the size of the fixed portion of the forward propeller and the fool-proof hole of the upper cover of the reverse propeller and the fixed portion of the reverse propeller can be set as For different sizes, when the forward propeller is assembled with the upper cover adapted to the reverse propeller, the fool-proof hole of the upper cover abuts against the fixing part of the forward propeller to prevent the forward propeller from being assembled with the upper cover.
  • the distance between the end of the fixed portion of the forward propeller and the center of the hub is different from the distance between the end of the fixed portion of the reverse propeller and the center of the hub.
  • the distance between the assembly hole of the forward motor and the central axis of the forward motor is different from the distance between the assembly hole of the reverse motor and the central axis of the reverse motor, so that the size of the forward propeller and the fixed part of the forward motor is the same as that of the reverse propeller.
  • the size of the fixed part of the reverse motor is configured into different sizes, so as to achieve the effect of size foolproof.
  • the inner end of the fixing part 11 includes a protruding part 19 extending toward the center of the hub, which can change the distance between the end of the fixing part and the center of the hub.
  • the distance between the end of the fixed part of the forward propeller and the center of the propeller hub can be different from the distance between the end of the fixed part of the reverse propeller and the center of the propeller hub.
  • the size of the screw is different from the size of the assembly hole of the reverse propeller, it can better prevent the wrong installation of the propeller.
  • the protrusion 19 can abut against the surface of the upper cover to prevent the propeller from being installed in the wrong motor upper cover.
  • the side of the assembly hole 21 is provided with a fool-proof hole 25 communicating with the assembly hole 21, and the side of the buckle part 13 of the fixing part 11 is along the propeller
  • the anti-fooling part 15 matched with the anti-fooling hole 25 can be protruded in the screwing-in direction.
  • the extension direction of the fool-proof part of the forward propeller and the fool-proof part of the reverse propeller are set to different directions, and the direction of the fool-proof hole of the upper cover of the forward motor and the fool-proof hole of the reverse propeller are set to different directions, so that The anti-fooling part of the forward propeller can only abut against the anti-fooling hole 25 in the corresponding direction only after being assembled to the correct assembly hole of the forward motor.
  • the anti-fooling part of the reverse propeller can only be assembled to the correct assembly hole of the reversing motor before it can abut against the anti-fooling hole in the corresponding direction, so as to achieve the effect of structural anti-fooling.
  • a fool-proof part protrudes from the side of the buckle part toward the center of the propeller hub.
  • the upper cover of the power unit is adapted.
  • the foolproof part is not suitable for the upper cover of the power device, so as to prevent the propeller from being installed on a power device with a different rotation direction.
  • the fool-proof portion abuts against the upper cover of the power device to prevent the propeller from being installed on a power device with a different rotation direction.
  • the embodiment of the present application also provides an unmanned aerial vehicle, including: a fuselage and a power system. It should be noted that the descriptions about the power system in the above embodiments and implementations are also applicable to the unmanned aerial vehicle of this embodiment.
  • the power unit of the power system is installed on the fuselage.
  • the unmanned aerial vehicle adopts the above-mentioned power system.
  • the upper cover is set as a single-layer structure, which is directly connected to the rotor of the driving motor, and no additional structures such as propeller seats are required to load the upper cover on the driving motor, reducing parts.
  • the number can achieve the effect of reducing the weight of the unmanned aerial vehicle, and can also save the axial space of the power unit, which is beneficial to reducing the size of the unmanned aerial vehicle.
  • the rotor and the upper cover of the driving motor are made of different materials, for example, the mass density of the material used for the yoke of the rotor is greater than that of the material used for the upper cover, which can further reduce the weight of the unmanned aerial vehicle.
  • pan/tilt handle provided by the embodiment of the present application and the pan/tilt with it have been introduced in detail.
  • specific examples are used to illustrate the principle and implementation of the present application.
  • the description of the above embodiment is only used to help understanding The method of this application and its core idea; at the same time, for those of ordinary skill in the art, according to the idea of this application, there will be changes in the specific implementation and scope of application.
  • the content of this specification should not understood as a limitation of the application.

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  • Aviation & Aerospace Engineering (AREA)
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Abstract

提供一种螺旋桨、动力装置、动力系统及多旋翼无人飞行器。动力装置包括用于与螺旋桨(2)连接以驱动螺旋桨(2)旋转的驱动电机(70)。驱动电机(70)包括转动部和上盖(20),上盖(20)为单层结构,其与驱动电机(70)的转子直接连接,且驱动电机的转子和上盖(20)分别采用不同的材料制成。上盖(20)用于与螺旋桨(2)固定连接,以使驱动电机(70)的转子与螺旋桨(2)固定连接,当驱动电机(70)的转子转动时,驱动螺旋桨(2)转动。将上盖(20)设置为单层结构,且与驱动电机(70)的转子直接连接,不需要额外设置桨座将上盖(20)装载在驱动电机(70),减少了零件的数量,达到减轻动力装置重量的效果,利于缩小无人机的尺寸。并且,上盖(20)可采用不同于转子的质量较轻的材料,可进一步减轻动力装置的重量。

Description

螺旋桨、动力装置、动力系统及无人飞行器 技术领域
本申请涉及无人机技术领域,尤其涉及一种螺旋桨、动力装置、动力系统及无人飞行器。
背景技术
随着人们生活品质的逐步提高,消费级无人机被越来越多用户青睐,无人机主要用于航拍、跟拍等场景,具有较高的安全性和操作性。无人机的便携性一直是业内关注的重点。
发明内容
本申请提供一种螺旋桨、动力装置、动力系统及无人飞行器。
具体地,本申请是通过如下技术方案实现的:
根据本申请的第一方面,提供一种动力装置,其用于与一螺旋桨连接,包括用于与所述螺旋桨连接的驱动电机,所述驱动电机用于驱动所述螺旋桨旋转;
所述驱动电机包括转动部和上盖,所述上盖为单层结构,与所述驱动电机的转子直接连接,且所述驱动电机的转子和所述上盖分别采用不同的材料制成;
所述上盖用于与所述螺旋桨固定连接,以使所述驱动电机的转子与所述螺旋桨固定连接,当所述驱动电机的转子转动时,驱动所述螺旋桨转动。
根据本申请的第二方面,提供一种螺旋桨,其用于与一动力装置连接,包括用于与所述动力装置连接的桨毂;
所述桨毂设有固定部,所述固定部包括卡扣部,所述卡扣部设有用于与所述动力装置卡接的凹槽部,所述凹槽部包括底壁和位于所述底壁两侧的侧壁;当所述螺旋桨与一动力装置连接时,所述凹槽部用于卡持所述动力装置的装配部,以使所述螺旋桨与所述动力装置固定连接;
所述固定部包括延伸部,所述延伸部自所述桨毂向远离所述桨毂的方向延伸设置,所述卡扣部连接于所述延伸部远离所述桨毂的端部;
所述延伸部用于部分伸入所述动力装置,所述卡扣部用于与所述动力装置卡接。
根据本申请的第三方面,提供一种动力系统,包括螺旋桨和与所述螺旋桨连接的动力装置,所述螺旋桨包括用于与所述动力装置连接的桨毂,所述动力装置包括用于驱动所述桨毂旋转的驱动电机;
所述驱动电机包括转动部和上盖,所述上盖为单层结构,与所述驱动电机的转子直接连接,且所述驱动电机的转子和所述上盖分别采用不同的材料制成;
所述螺旋桨与所述上盖固定连接,以使所述螺旋桨与所述驱动电机的转子固定连接,当所述驱动电机的转子转动时,驱动所述螺旋桨转动。
根据本申请的第四方面,提供一种无人飞行器,包括:机身和如第三方面所述的动力系统,所述动力系统的动力装置安装于所述机身。
由以上本申请实施例提供的技术方案可见,本申请将上盖设置为单层结构,与驱动电机的转子直接连接,不需要额外设置桨座将上盖装载在驱动电机,减少了零件的数量,达到减轻动力装置重量的效果,还可节省动力装置的轴向空间,利于缩小无人机的尺寸。并且,驱动电机的转子和上盖分别采用不同的材料制成,上盖可采用质量较轻的材料,可进一步减轻动力装置的重量。
附图说明
为了更清楚地说明本申请实施例中的技术方案,下面将对实施例描述中所需要使用的附图作简单地介绍,显而易见地,下面描述中的附图仅仅是本申请的一些实施例,对于本领域普通技术人员来讲,在不付出创造性劳动性的前提下,还可以根据这些附图获得其他的附图。
图1是本申请一实施例中的动力系统的立体示意图。
图2是本申请一实施例中的动力系统的分解示意图。
图3是本申请一实施例中的动力系统去除桨叶后的立体示意图。
图4是本申请一实施例中的动力系统去除桨叶后的另一视角的立体示意图。
图5是本申请一实施例中的动力系统去除桨叶后的爆炸示意图。
图6是本申请另一实施例中的动力系统的动力装置的上盖的立体示意图。
图7是本申请另一实施例中的动力系统的动力装置的上盖的另一视角的立体示意图。
图8是本申请另一实施例中的动力系统去除桨叶后的立体示意图。
图9是本申请另一实施例中的动力系统去除桨叶后的另一视角的立体示意图。
图10是本申请另一实施例中的动力系统去除桨叶后剖面示意图。
图11是本申请一实施例中的动力系统的动力装置的上盖与卡圈的连接示意图。
图12是本申请一实施例中的动力系统的动力装置的上盖的剖面示意图。
图13是本申请一实施例中的动力系统的动力装置的上盖与卡圈的剖面示意图。
图14是本申请另一实施例中的动力系统的动力装置的上盖与卡圈的剖面示意图。
图15是图14中的局部放大示意图。
图16是本申请另一实施例中的动力系统的动力装置的上盖与弹性部件的连接示意图。
图17是本申请另一实施例中的动力系统的动力装置的上盖与弹性部件的剖面示意图。
图18和图19是本申请一实施例中的动力系统的动力装置的上盖与桨毂的防呆结构的示意图。
具体实施方式
下面将结合本申请实施例中的附图,对本申请实施例中的技术方案进行清楚、完整地描述,显然,所描述的实施例仅仅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。
下面结合附图,对本申请的螺旋桨、动力装置、动力系统及无人飞行器进行详细说明。在不冲突的情况下,下述的实施例及实施方式中的特征可以相互组合。
本申请实施例提供一种动力系统,包括动力装置1和与动力装置1连接的螺旋桨2。动力装置1包括用于与所述螺旋桨2连接的驱动电机70,所述驱动电机用于驱动所述螺旋桨旋转。螺旋桨2包括用于与所述动力装置1连接的桨毂10和安装于桨毂10的至少一个桨叶60。
所述驱动电机70包括转动部和上盖20,所述上盖20为单层结构,与所述驱动电机70的转子直接连接,且所述驱动电机70的转子和所述上盖20分别采用不同的材料制成。所述上盖20用于与所述螺旋桨固定连接,以使所述驱动电机70的转子与所述螺旋桨固定连接,当所述驱动电机的转子转动时,驱动所述螺旋桨转动。需要说明的是,驱动电机70的转子可以是外转子,也可以是内转子。在本实施例中,驱动电机70的转子是外转子。
通过上述设置,将上盖20设置为单层结构,与驱动电机70的转子直接连接,不需要额外设置桨座等结构将上盖20装载在驱动电机70,减少了零件的数量,达到减轻动力装置1重量的效果,还可节省动力装置1的轴向(图1中所示为竖直方向)空间,利于缩小无人机的尺寸。并且,驱动电机70的转子和上盖分别采用不同的材料制成,例如转子的磁轭所用的材料的质量密度大于所述上盖20所用的材料的质量密度,可进一步减轻减轻动力装置的重量。在本实施例中,转子的磁轭采用铜,上盖20的材料采用质量较轻的铝合金。
目前市面所用的无人机,通常利用螺纹连接将螺旋桨与动力装置的电机直接连接,通过螺纹配合传递扭矩和拉力。但这种固定方式螺纹连接存在可靠性风险,螺丝松动后螺旋桨易从飞机上脱出,而且装拆难度较高,不便于桨的收纳和更换。
在一些可选的实施例中,所述上盖20设有用于与所述螺旋桨2卡接配合的装配孔21或固定部,螺旋桨2设有对应的固定部或装配孔21,装配孔21设有用于与固定部卡接配合的装配部,通过装配部与固定部卡接配合,实现螺旋桨2与上盖20的快拆连接,便于无人机的装拆和便携收纳。在本实施例中,上盖20设有装配孔21,螺旋桨2的桨毂10设有固定部11,所述装配孔21设有用于与所述螺旋桨2的固定部11卡接配合的装配部。固定部11和装配部可以通过多种方式连接,容下详述。通过固定部11与装配部卡接配合,将桨毂10与上盖20固定,避免采用桨座和螺丝的方式将桨毂10与上盖20连接,可以减少零件的数量,简化了组装工艺,降低了成本,达到减轻动力装置重量的效果。
上盖20中部设有第一通孔26,所述驱动电机70包括电机轴71,所述电机轴71伸入所述第一通孔26与所述桨毂10驱动连接。螺旋桨2的桨毂10设有用于安装桨叶60的安装部27,桨毂10可以包括第一桨夹16、中间连接件17以及第二桨夹18,所述固定部11设置于所述第一桨夹16的底部,所述中间连接件17连接于所述第一桨夹16的顶部,所述第二桨夹18与所述第一桨夹16之间夹设形成所述安装部27。在图中所示的例子中,桨叶60的数量为两个,中间连接件17连接在第一桨夹16和第二桨夹18的中间,在中间连接件17的两侧分别形成一个安装部27,每个安装部27内夹装一个桨叶60。驱动电机70可以包括外壳,所述上盖20包括盖合部,所述盖合部盖设于所述外壳。上盖20的底部间隔设置有多个筋条28,便于上盖20与驱动外壳连接。
参见图3至图5所示,在一实施例中,所述装配部包括从所述装配孔21的内侧壁向所述装配孔21内凸伸的凸块22,所述凸块22用于与所述螺旋桨2的固定部11卡接。可选地,凸块22由装配孔21朝向所述上盖20的中间凸起形成。
螺旋桨2的桨毂10的固定部11包括卡扣部13,所述卡扣部13设有用于与所述动力装置1的装配部的凸块22卡接的凹槽部14,所述凹槽部14包括底壁141和位于所述底壁141两侧的侧壁142。当所述螺旋桨2与动力装置1连接时,所述凹槽部14卡持所述凸块22,将固定部11与装配部卡接配合,以使所述螺旋桨2与所述动力装置1固定连接。
所述固定部11还可以包括延伸部12,所述延伸部12自所述桨毂10向远离所述桨毂10的方向延伸设置(图5中所示为向下延伸),也可以理解为,所述延伸部12自所述桨毂10向远离所述桨毂10的方向延伸设置,所述卡扣部13连接于所述延伸部12远离所述桨毂10的端部,所述延伸部12用于部分伸入所述动力装置,所述卡 扣部13用于与所述动力装置卡接。固定部11与装配部连接时,所述延伸部12部分伸入所述装配孔21,所述卡扣部13的凹槽部14与装配孔21内的凸块22卡接,从而将桨毂10与上盖20固定。所述螺旋桨2的桨毂10与所述上盖20固定时,固定部11的延伸部12向下穿过装配孔21后沿预设方向旋入,将卡扣部13的凹槽部14移动到与凸块22对应的位置,再向上移动使凹槽部14和凸块22相互卡接,以使得所述固定部11与所述装配部卡接。
所述凹槽部14包括底壁141和位于所述底壁141两侧的侧壁142。所述装配部包括与所述凹槽部14卡接配合的凸块22。所述螺旋桨2与所述上盖20固定时,所述凸块22卡接于所述凹槽部14内,从而实现桨毂10与上盖20的连接。所述凸块22卡接于所述凹槽部14时,所述凸块22的两侧与位于所述底壁141两侧的侧壁142分别抵接,所述凸块22远离所述装配孔21一侧与所述上盖20存在一个间隙143,以容置所述底壁141一侧的侧壁142。其中,所述间隙143大于所述侧壁142的厚度。凹槽部14与凸块22卡接后,凹槽部14的一侧侧壁142卡接在装配孔21的侧壁和凸块22之间,达到更好的固定作用。
所述装配孔21的数量可以设置多个,沿圆周均匀设置于所述上盖20,每个装配孔21均设置所述装配部。对应地,桨毂10设置与装配孔21数量及位置均对应的固定部11,沿圆周均匀设置于所述桨毂10。每个固定部11与对应的装配孔21卡接固定,沿圆周360°全方向将桨毂10与上盖20固定。
参见图6至图10所示,在另一实施例中,所述装配部包括卡槽23和凸台24,所述卡槽23位于所述装配孔21的侧壁与所述凸台24之间,所述卡槽23用于与所述螺旋桨2的固定部11卡接,所述凸台24及所述装配孔21的侧壁用于在所述卡槽23与所述螺旋桨2的桨毂10卡接时与所述固定部11抵接。
所述螺旋桨2的桨毂10与所述上盖20固定时,固定部11的延伸部12向下穿过装配孔21后沿预设方向旋入,将卡扣部13移动到与卡槽23对应的位置,再向上移动使卡扣部13使之与卡槽23相互卡接,所述卡扣部13的底面卡接于所述卡槽23,所述卡扣部13的两侧侧部分别与所述凸台24及所述装配孔21的侧壁相抵接,如图9所示,从而将桨毂10与上盖20相互固定。
参见图2、图5、图11至图13所示,在一些可选的实施例中,动力装置1还可以包括设置于所述上盖20的弹性部件30,所述弹性部件30用于在所述上盖20与所述螺旋桨2的固定部11相固定时抵持所述螺旋桨2,从而将桨毂10向远离上盖20的方向推,配合固定部11与卡扣部13相互卡接的力,将桨毂10与上盖20固定的更牢固。将弹性部件30固定在上盖20用于固定桨毂10和上盖20,便于实现自动化组装,工艺性更好。还可以避免采用螺丝的方式将桨毂10和上盖20连接,避免了因螺丝松动带来的可靠性风险。
进一步地,动力装置1还可以包括卡圈50,固定于所述上盖20,所述弹性部件30的一端与所述卡圈50固定,通过卡圈50将弹性部件30固定在上盖20。可选地,弹性部件30可以采用弹簧。
所述上盖20的端面设有收容槽40,所述弹性部件30的端部收容设置于所述收容槽40内。所述卡圈50套接于弹性部件30的外部并固定于所述收容槽40内,将所述弹性部件30的端部固定于所述收容槽40内,如图11所示,从而将弹性部件30固定在上盖20。
如图5所示,所述弹性部件30可以包括本体部31和与所述本体部31连接的连接端32,所述连接端32收容设置于所述收容槽40内,所述连接端32的尺寸大于所述本体部31的尺寸。
所述卡圈50的内径尺寸小于所述连接端32的尺寸、大于所述本体部31的尺寸,所述卡圈50套接于所述本体部31的外部并固定于所述收容槽40内,将所述连接端32固定于所述收容槽40内,从而将弹性部件30固定在收容槽40内,也即用卡圈罩住弹性部件30的连接端32,将弹性部件30固定在收容槽40内。
为防止卡圈50从上盖20脱落,卡圈50可以采用多种方式与上盖20固定。为防止卡圈从电机上盖脱落。在一实施例中,所述卡圈50与所述收容槽40可以通过胶体固定。在另一实施例中,所述卡圈50与所述收容槽40可采用过盈配合方式固定。参见图14和图15所示,在另一实施例中,所述收容槽40的侧壁可以设有台阶孔41,所述卡圈50的侧部设有与所述台阶孔41相适配的凸起部51,所述凸起部51卡接于所述台阶孔41,也即卡圈50的底部通过倒扣结构与收容槽40卡接固定。参见图16和图17所示,在另一实施例中,所述弹性部件30的端部与所述收容槽40直接铆压固定,可省去卡圈50将弹性部件30与上盖20固定。可选地,所述弹性部件30的端部通过多个铆压件42与上盖20铆压固定,从而将弹性部件30固定在收容槽40内。铆压件42可以设置多个,沿弹性部件30的周向均匀布置,以保证弹性部件30与上盖20连接牢固。在另一实施例中,所述弹性部件30的端部也可以与所述收容槽40直接焊接固定,同样可省去卡圈50将弹性部件30与上盖20固定。
由于无人机的螺旋桨通常分为正向螺旋桨和反向螺旋桨两种旋转方向,需要区别安装,因此电机上盖20和桨毂10需要做防呆区分。在一实施例中,可以在上盖20和桨毂10上印刷不同颜色的图案或不同文字做区分。在另一实施例中,也可以将正向螺旋桨的卡圈和反向螺旋桨的卡圈做成不同颜色进行区分。
在一些可选的实施例中,也可以对上盖和桨毂从结构和尺寸上做区分。所述螺旋桨包括第一螺旋桨(例如正向螺旋桨)和第二螺旋桨(例如反向螺旋桨),所述驱动电机包括第一驱动电机(例如正向电机)和第二驱动电机(例如反向电机)。第一螺旋桨能够安装至所述第一驱动电机且不能安装至所述第二驱动电机。所述第二螺旋 桨能够安装至所述第二驱动电机且不能安装至所述第一驱动电机,从而起到防呆作用。其中,第一螺旋桨例如为正向螺旋桨,第二螺旋桨例如为反向螺旋桨,第一驱动电机例如为正向电机,第二驱动电机例如为反向电机。下文中以第一螺旋桨为正向螺旋桨、第二螺旋桨为反向螺旋桨、第一驱动电机为正向电机、第二驱动电机为反向电机为例进行说明。本发明实施例中,在飞机飞行过程中,正向螺旋桨和正向电机向顺时针旋转,反向螺旋桨和反向电机向逆时针旋转。
所述装配孔的侧部设有与所述装配孔相连通的防呆孔,当所述动力装置装配对应旋转方向的螺旋桨时,所述防呆孔被配置为与所述螺旋桨适配。当所述动力装置装配不同旋转方向的螺旋桨时,所述防呆孔与所述螺旋桨不适配,以阻止所述动力装置装配不同旋转方向的螺旋桨。可以理解的,适配正向螺旋桨的上盖的防呆孔的尺寸与适配反向螺旋桨的上盖的防呆孔的尺寸可以设置为不同尺寸,正向螺旋桨与适配反向螺旋桨的上盖装配时,该上盖的防呆孔与正向螺旋桨不适配,以阻止正向螺旋桨与该上盖装配。反向螺旋桨与适配正向螺旋桨的上盖装配时,该上盖的防呆孔与反向螺旋桨不适配,以阻止反向螺旋桨与该上盖装配,从而起到区分防呆的作用。通过上述设置,起到尺寸防呆的作用。
当所述动力装置装配不同旋转方向的螺旋桨时,所述防呆孔与所述螺旋桨抵接,以阻止所述动力装置装配不同旋转方向的螺旋桨。可以理解的,适配正向螺旋桨的上盖的防呆孔的尺寸及正向螺旋桨的固定部的尺寸与适配反向螺旋桨的上盖的防呆孔及反向螺旋桨的固定部可以设置为不同尺寸,正向螺旋桨与适配反向螺旋桨的上盖装配时,该上盖的防呆孔与正向螺旋桨的固定部抵接,以阻止正向螺旋桨与该上盖装配。反向螺旋桨与适配正向螺旋桨的上盖装配时,该上盖的防呆孔与反向螺旋桨的固定部抵接,以阻止反向螺旋桨与该上盖装配,从而起到区分防呆的作用。通过上述设置,起到尺寸防呆的作用。
可选地,正向螺旋桨的固定部的端部和桨毂的中心的距离与所述反向螺旋桨的固定部的端部和桨毂的中心的距离不同。正向电机的装配孔和正向电机的中心轴线的距离与反向电机的装配孔和反向电机的中心轴线的距离不同,从而达到正向螺旋桨及正向电机的固定部的尺寸与反向螺旋桨及反向电机的固定部的尺寸被配置成不同的尺寸,达到尺寸防呆的效果。
当正向螺旋桨与反向电机固定时,正向螺旋桨的固定部的外侧端部与反向电机的上盖抵接,以阻止所述正向螺旋桨的固定部伸入反向电机的装配孔。当反向螺旋桨与正向电机固定时,反向螺旋桨的固定部的内侧端部与正向电机的上盖抵接,以阻止反向螺旋桨的固定部伸入正向电机的装配孔。或者,当反向螺旋桨与正向电机固定时,反向螺旋桨的固定部的外侧端部与正向电机的上盖抵接,以阻止所述反向螺旋桨的固定部伸入正向电机的装配孔。当正向螺旋桨与反向电机固定时,正向螺旋桨的固定部的内侧端部与反向电机的上盖抵接,以阻止正向螺旋桨的固定部伸入反向电机的装配 孔
参见图10所示,所述固定部11的内侧端部包括朝向所述桨毂中心延伸的凸出部19,可以改变固定部的端部和桨毂的中心的距离距离。通过上述设置,可以使正向螺旋桨的固定部的端部和桨毂的中心的距离与所述反向螺旋桨的固定部的端部和桨毂的中心的距离不同,在正向电机的装配孔的尺寸与反向螺旋桨的装配孔的尺寸不同的前提下,可以更好的防止螺旋桨错装的情况发生。螺旋桨装入错误的电机的上盖的装配孔,该凸出部19能够与上盖的表面抵接,以阻止螺旋桨装入错误的电机上盖。
参见图18和图19所示,在一实施例中,装配孔21的侧部设有与所述装配孔21相连通的防呆孔25,固定部11的卡扣部13的侧部沿螺旋桨的旋入方向可以凸设有与防呆孔25相适配的防呆部15。螺旋桨与相匹配的上盖固定时,所述延伸部12穿过所述装配孔21,所述卡扣部13与所述装配部卡接,所述防呆部15收容于所述防呆孔25内,可以起到防呆作用。将正向螺旋桨的防呆部和反向螺旋桨的防呆部的延伸方向设置为不同方向,正向电机的上盖的防呆孔和反向螺旋桨的防呆孔的方向设置为不同方向,从而使正向螺旋桨的防呆部只能装配到正确的正向电机的装配孔后才能与对应方向的防呆孔25相抵接。反向螺旋桨的防呆部只能装配到正确的反向电机的装配孔后才能与对应方向的防呆孔相抵接,实现结构防呆的效果。
可以理解的,所述卡扣部的侧部朝向所述桨毂的中心方向凸设有防呆部,当螺旋桨安装至对应旋转方向的动力装置时,所述防呆部被配置为与对应的动力装置的上盖适配。当螺旋桨安装至不同旋转方向的动力装置时,所述防呆部与该动力装置的上盖不适配,以阻止所述螺旋桨安装至不同旋转方向的动力装置上。进一步地,当所述螺旋桨安装至不同旋转方向的动力装置时,所述防呆部与该动力装置的上盖抵接,以阻止所述螺旋桨安装至不同旋转方向的动力装置上。
本申请实施例还提供一种无人飞行器,包括:机身和动力系统,需要说明的是,上述实施例和实施方式中关于动力系统的描述,同样适用于本实施例的无人飞行器。所述动力系统的动力装置安装于所述机身。
通过上述设置,无人飞行器采用上述动力系统,一方面将上盖设置为单层结构,与驱动电机的转子直接连接,不需要额外设置桨座等结构将上盖装载在驱动电机,减少了零件的数量,达到减轻无人飞行器重量的效果,还可节省动力装置的轴向空间,利于缩小无人机的尺寸。并且,驱动电机的转子和上盖分别采用不同的材料制成,例如转子的磁轭所用的材料的质量密度大于所述上盖所用的材料的质量密度,可进一步减轻减轻无人飞行器的重量。
需要说明的是,在本文中,诸如第一和第二等之类的关系术语仅仅用来将一个实体或者操作与另一个实体或操作区分开来,而不一定要求或者暗示这些实体或操作之间存在任何这种实际的关系或者顺序。术语“包括”、“包含”或者其任何其他变体意 在涵盖非排他性的包含,从而使得包括一系列要素的过程、方法、物品或者设备不仅包括那些要素,而且还包括没有明确列出的其他要素,或者是还包括为这种过程、方法、物品或者设备所固有的要素。在没有更多限制的情况下,由语句“包括一个……”限定的要素,并不排除在包括所述要素的过程、方法、物品或者设备中还存在另外的相同要素。
以上对本申请实施例所提供的云台手柄和具有其的云台进行了详细介绍,本文中应用了具体个例对本申请的原理及实施方式进行了阐述,以上实施例的说明只是用于帮助理解本申请的方法及其核心思想;同时,对于本领域的一般技术人员,依据本申请的思想,在具体实施方式及应用范围上均会有改变之处,综上所述,本说明书内容不应理解为对本申请的限制。

Claims (72)

  1. 一种动力装置,其用于与一螺旋桨连接,其特征在于,包括用于与所述螺旋桨连接的驱动电机,所述驱动电机用于驱动所述螺旋桨旋转;
    所述驱动电机包括转动部和上盖,所述上盖为单层结构,与所述驱动电机的转子直接连接,且所述驱动电机的转子和所述上盖分别采用不同的材料制成;
    所述上盖用于与所述螺旋桨固定连接,以使所述驱动电机的转子与所述螺旋桨固定连接,当所述驱动电机的转子转动时,驱动所述螺旋桨转动。
  2. 根据权利要求1所述的动力装置,其特征在于,所述上盖设有用于与所述螺旋桨卡接配合的装配孔或固定部。
  3. 根据权利要求2所述的动力装置,其特征在于,所述上盖设有装配孔,所述装配孔设有用于与所述螺旋桨卡接配合的装配部,所述装配部包括从所述装配孔的内侧壁向所述装配孔内凸伸的凸块,所述凸块用于与所述螺旋桨卡接。
  4. 根据权利要求3所述的动力装置,其特征在于,所述装配部包括从所述装配孔的内壁向所述装配孔内凸伸的卡槽和凸台,所述卡槽位于所述装配孔的侧壁与所述凸台之间,所述卡槽用于与所述螺旋桨卡接,所述凸台及所述装配孔的侧壁用于在所述卡槽与所述螺旋桨卡接时与所述螺旋桨抵接。
  5. 根据权利要求2所述的动力装置,其特征在于,所述装配孔的侧部设有与所述装配孔相连通的防呆孔,当所述动力装置装配对应旋转方向的螺旋桨时,所述防呆孔被配置为与所述螺旋桨适配;当所述动力装置装配不同旋转方向的螺旋桨时,所述防呆孔与所述螺旋桨不适配,以阻止所述动力装置装配不同旋转方向的螺旋桨。
  6. 根据权利要求5所述的动力装置,其特征在于,当所述动力装置装配不同旋转方向的螺旋桨时,所述防呆孔与所述螺旋桨抵接,以阻止所述动力装置装配不同旋转方向的螺旋桨。
  7. 根据权利要求5所述的动力装置,其特征在于,所述装配孔的数量为多个,沿圆周均匀设置于所述上盖。
  8. 根据权利要求1所述的动力装置,其特征在于,还包括设置于所述上盖的弹性部件,所述弹性部件用于在所述上盖与所述螺旋桨相固定时抵持所述螺旋桨。
  9. 根据权利要求8所述的动力装置,其特征在于,还包括卡圈,固定于所述上盖,所述弹性部件的一端与所述卡圈固定。
  10. 根据权利要求9所述的动力装置,其特征在于,所述上盖的端面设有收容槽,所述弹性部件的端部收容设置于所述收容槽内;所述卡圈套接于弹性部件的外部并固定于所述收容槽内,以将所述弹性部件的端部固定于所述收容槽内。
  11. 根据权利要求10所述的动力装置,其特征在于,所述弹性部件包括本体部和与所述本体部连接的连接端,所述连接端收容设置于所述收容槽内,所述连接端的尺寸大于所述本体部的尺寸;
    所述卡圈的内径尺寸小于所述连接端的尺寸、大于所述本体部的尺寸,所述卡圈 套接于所述本体部的外部并固定于所述收容槽内,以将所述连接端固定于所述收容槽内。
  12. 根据权利要求10所述的动力装置,其特征在于,所述卡圈与所述收容槽通过胶体固定。
  13. 根据权利要求10所述的动力装置,其特征在于,所述卡圈与所述收容槽过盈配合。
  14. 根据权利要求10所述的动力装置,其特征在于,所述收容槽的侧壁设有台阶孔,所述卡圈的侧部设有与所述台阶孔相适配的凸起部,所述凸起部卡接于所述台阶孔。
  15. 根据权利要求10所述的动力装置,其特征在于,所述弹性部件的端部与所述收容槽铆压固定。
  16. 根据权利要求10所述的动力装置,其特征在于,所述弹性部件的端部与所述收容槽焊接固定。
  17. 根据权利要求1所述的动力装置,其特征在于,所述驱动电机包括外壳,所述上盖包括盖合部,所述盖合部盖设于所述外壳。
  18. 根据权利要求1所述的动力装置,其特征在于,转子的磁轭所用的材料的质量密度大于所述上盖所用的材料的质量密度。
  19. 一种螺旋桨,其用于与一动力装置连接,其特征在于,包括用于与所述动力装置连接的桨毂;
    所述桨毂设有固定部,所述固定部包括卡扣部,所述卡扣部设有用于与所述动力装置卡接的凹槽部,所述凹槽部包括底壁和位于所述底壁两侧的侧壁;当所述螺旋桨与一动力装置连接时,所述凹槽部用于卡持所述动力装置的装配部,以使所述螺旋桨与所述动力装置固定连接;
    所述固定部包括延伸部,所述延伸部自所述桨毂向远离所述桨毂的方向延伸设置,所述卡扣部连接于所述延伸部远离所述桨毂的端部;
    所述延伸部用于部分伸入所述动力装置,所述卡扣部用于与所述动力装置卡接。
  20. 根据权利要求19所述的螺旋桨,其特征在于,所述凹槽部形成于所述卡扣部靠近所述延伸部的一侧表面。
  21. 根据权利要求19所述的螺旋桨,其特征在于,所述卡扣部的侧部朝向所述桨毂的中心方向凸设有防呆部,当所述螺旋桨安装至对应旋转方向的动力装置时,所述防呆部被配置为与所述动力装置适配;当所述螺旋桨安装至不同旋转方向的动力装置时,所述防呆部与所述动力装置不适配,以阻止所述螺旋桨安装至不同旋转方向的动力装置上。
  22. 根据权利要求21所述的螺旋桨,其特征在于,当所述螺旋桨安装至不同旋转方向的动力装置时,所述防呆部与所述动力装置的上盖抵接,以阻止所述安装至不同旋转方向的动力装置上。
  23. 根据权利要求21所述的螺旋桨,其特征在于,所述螺旋桨包括第一螺旋桨和第二螺旋桨,所述第一螺旋桨的固定部的端部和所述桨毂的中心的距离与所述第二螺旋桨的固定部的端部和所述桨毂的中心的距离不同。
  24. 根据权利要求23所述的螺旋桨,其特征在于,当所述第一螺旋桨与不对应的动力装置固定时,所述第一螺旋桨的固定部的外侧端部与不对应的动力装置的上盖抵接,以阻止所述第一螺旋桨的固定部装入不对应的动力装置的上盖;
    当所述第二螺旋桨与不对应的动力装置固定时,所述第二螺旋桨的固定部的内侧端部与不对应的动力装置的上盖抵接,以阻止所述第二螺旋桨的固定部装入不对应的动力装置的上盖。
  25. 根据权利要求19所述的螺旋桨,其特征在于,所述固定部的内侧端部包括朝向所述桨毂中心延伸的凸出部。
  26. 根据权利要求19所述的螺旋桨,其特征在于,所述固定部的数量为多个,沿圆周均匀设置于所述桨毂。
  27. 一种动力系统,其特征在于,包括螺旋桨和与所述螺旋桨连接的动力装置,所述螺旋桨包括用于与所述动力装置连接的桨毂,所述动力装置包括用于驱动所述桨毂旋转的驱动电机;
    所述驱动电机包括转动部和上盖,所述上盖为单层结构,与所述驱动电机的转子直接连接,且所述驱动电机的转子和所述上盖分别采用不同的材料制成;
    所述螺旋桨与所述上盖固定连接,以使所述螺旋桨与所述驱动电机的转子固定连接,当所述驱动电机的转子转动时,驱动所述螺旋桨转动。
  28. 根据权利要求27所述的动力系统,其特征在于,所述螺旋桨设有固定部,所述上盖设有装配孔,所述装配孔设有与所述固定部固定配合的装配部。
  29. 根据权利要求28所述的动力系统,其特征在于,所述固定部包括延伸部和卡扣部,所述延伸部自所述桨毂向远离所述桨毂的方向延伸设置,所述卡扣部连接于所述延伸部远离所述桨毂的端部;
    所述螺旋桨与所述上盖固定时,所述延伸部穿过所述装配孔,并沿预设方向旋入,以使得所述卡扣部与所述装配部卡接。
  30. 根据权利要求29所述的动力系统,其特征在于,所述固定部包括自所述卡扣部靠近所述延伸部的一侧表面形成的凹槽部,所述凹槽部包括底壁和位于所述底壁两侧的侧壁;所述装配部包括与所述凹槽部卡接配合的凸块;所述螺旋桨与所述上盖固定时,所述凸块卡接于所述凹槽部内。
  31. 根据权利要求30所述的动力系统,其特征在于,所述凸块卡接于所述凹槽部时,所述凸块的两侧与所述位于所述底壁两侧的侧壁分别抵接,所述凸块远离所述装配孔一侧与所述上盖存在一个间隙,以容置所述底壁一侧的侧壁;其中,所述间隙大于所述侧壁的厚度。
  32. 根据权利要求29所述的动力系统,其特征在于,所述装配部包括从所述装配 孔的内壁向所述装配孔内凸伸的卡槽和凸台,所述卡槽位于所述装配孔的侧壁与所述凸台之间;
    所述螺旋桨与所述上盖固定时,所述卡扣部卡接于所述卡槽,所述卡扣部的两侧侧部分别与所述凸台及所述装配孔的侧壁相抵接。
  33. 根据权利要求29所述的动力系统,其特征在于,所述上盖设有装配孔,所述装配孔设有所述装配部,所述装配孔的侧部设有与所述装配孔相连通的防呆孔,所述卡扣部的侧部沿所述螺旋桨的旋入方向凸设有与所述防呆孔相适配的防呆部;
    所述螺旋桨与所述上盖固定时,所述延伸部穿过所述装配孔,所述卡扣部与所述装配部卡接,所述防呆部收容于所述防呆孔内。
  34. 根据权利要求33所述的动力系统,其特征在于,所述螺旋桨包括第一螺旋桨和第二螺旋桨,所述驱动电机包括第一驱动电机和第二驱动电机;第一螺旋桨能够安装至所述第一驱动电机且不能安装至所述第二驱动电机;所述第二螺旋桨能够安装至所述第二驱动电机且不能安装至所述第一驱动电机。
  35. 根据权利要求34所述的动力系统,其特征在于,所述第一螺旋桨的固定部的端部和所述桨毂的中心的距离与所述第二螺旋桨的固定部的端部和所述桨毂的中心的距离不同;所述第一驱动电机的装配孔和所述第一驱动电机的中心轴线的距离与所述第二驱动电机的所述装配孔和所述第二驱动电机的中心轴线的距离不同。
  36. 根据权利要求35所述的动力系统,其特征在于,当所述第一螺旋桨与所述第二驱动电机固定时,所述固定部的外侧端部与所述上盖抵接,以阻止所述第一螺旋桨的固定部伸入所述第二驱动电机的装配孔;
    当所述第二螺旋桨与所述第一驱动电机固定时,所述固定部的内侧端部与所述上盖抵接,以阻止所述第二螺旋桨的固定部伸入所述第一驱动电机的装配孔。
  37. 根据权利要求28所述的动力系统,其特征在于,所述固定部的内侧端部包括朝向所述桨毂中心延伸的凸出部。
  38. 根据权利要求29所述的动力系统,其特征在于,所述装配孔的数量为多个,沿圆周均匀设置于所述上盖;所述卡扣部的数量为多个,沿圆周均匀设置于所述桨毂。
  39. 根据权利要求27所述的动力系统,其特征在于,还包括设置于所述上盖的弹性部件,所述弹性部件用于在所述上盖与所述螺旋桨相固定时抵持所述螺旋桨。
  40. 根据权利要求39所述的动力系统,其特征在于,还包括卡圈,固定于所述上盖,所述弹性部件的一端与所述卡圈固定。
  41. 根据权利要求40所述的动力系统,其特征在于,所述上盖的端面设有收容槽,所述弹性部件的端部收容设置于所述收容槽内;所述卡圈套接于弹性部件的外部并固定于所述收容槽内,以将所述弹性部件的端部固定于所述收容槽内。
  42. 根据权利要求41所述的动力系统,其特征在于,所述弹性部件包括本体部和与所述本体部连接的连接端,所述连接端收容设置于所述收容槽内,所述连接端的尺寸大于所述本体部的尺寸;
    所述卡圈的内径尺寸小于所述连接端的尺寸、大于所述本体部的尺寸,所述卡圈套接于所述本体部的外部并固定于所述收容槽内,以将所述连接端固定于所述收容槽内。
  43. 根据权利要求41所述的动力系统,其特征在于,所述卡圈与所述收容槽通过胶体固定。
  44. 根据权利要求41所述的动力系统,其特征在于,所述卡圈与所述收容槽过盈配合。
  45. 根据权利要求41所述的动力系统,其特征在于,所述收容槽的侧壁设有台阶孔,所述卡圈的侧部设有与所述台阶孔相适配的凸起部,所述凸起部卡接于所述台阶孔。
  46. 根据权利要求41所述的动力系统,其特征在于,所述弹性部件的端部与所述收容槽铆压固定。
  47. 根据权利要求41所述的动力系统,其特征在于,所述弹性部件的端部与所述收容槽焊接固定。
  48. 根据权利要求27所述的动力系统,其特征在于,所述驱动电机包括外壳,所述上盖包括盖合部,所述盖合部盖设于所述外壳。
  49. 根据权利要求27所述的动力系统,其特征在于,转子的磁轭所用的材料的质量密度大于所述上盖所用的材料的质量密度。
  50. 一种无人飞行器,其特征在于,包括:机身和动力系统,所述动力系统包括螺旋桨和与所述螺旋桨连接的动力装置,所述动力装置安装于所述机身;
    其中,所述螺旋桨包括用于与所述动力装置连接的桨毂,所述动力装置包括用于驱动所述桨毂旋转的驱动电机;
    所述驱动电机包括转动部和上盖,所述上盖为单层结构,与所述驱动电机的转子直接连接,且所述驱动电机的转子和所述上盖分别采用不同的材料制成;
    所述螺旋桨与所述上盖固定连接,以使所述螺旋桨与所述驱动电机的转子固定连接,当所述驱动电机的转子转动时,驱动所述螺旋桨转动。
  51. 根据权利要求50所述的无人飞行器,其特征在于,所述螺旋桨设有固定部,所述上盖设有装配孔,所述装配孔设有与所述固定部固定配合的装配部。
  52. 根据权利要求51所述的无人飞行器,其特征在于,所述固定部包括延伸部和卡扣部,所述延伸部自所述桨毂向远离所述桨毂的方向延伸设置,所述卡扣部连接于所述延伸部远离所述桨毂的端部;
    所述螺旋桨与所述上盖固定时,所述延伸部穿过所述装配孔,并沿预设方向旋入,以使得所述卡扣部与所述装配部卡接。
  53. 根据权利要求52所述的无人飞行器,其特征在于,所述固定部包括自所述卡扣部靠近所述延伸部的一侧表面形成的凹槽部,所述凹槽部包括底壁和位于所述底壁两侧的侧壁;所述装配部包括与所述凹槽部卡接配合的凸块;所述螺旋桨与所述上盖 固定时,所述凸块卡接于所述凹槽部内。
  54. 根据权利要求53所述的无人飞行器,其特征在于,所述凸块卡接于所述凹槽部时,所述凸块的两侧与所述位于所述底壁两侧的侧壁分别抵接,所述凸块远离所述装配孔一侧与所述上盖存在一个间隙,以容置所述底壁一侧的侧壁;其中,所述间隙大于所述侧壁的厚度。
  55. 根据权利要求52所述的无人飞行器,其特征在于,所述装配部包括从所述装配孔的内壁向所述装配孔内凸伸的卡槽和凸台,所述卡槽位于所述装配孔的侧壁与所述凸台之间;
    所述螺旋桨与所述上盖固定时,所述卡扣部卡接于所述卡槽,所述卡扣部的两侧侧部分别与所述凸台及所述装配孔的侧壁相抵接。
  56. 根据权利要求52所述的无人飞行器,其特征在于,所述上盖设有装配孔,所述装配孔设有所述装配部,所述装配孔的侧部设有与所述装配孔相连通的防呆孔,所述卡扣部的侧部沿所述螺旋桨的旋入方向凸设有与所述防呆孔相适配的防呆部;
    所述螺旋桨与所述上盖固定时,所述延伸部穿过所述装配孔,所述卡扣部与所述装配部卡接,所述防呆部收容于所述防呆孔内。
  57. 根据权利要求56所述的无人飞行器,其特征在于,所述螺旋桨包括第一螺旋桨和第二螺旋桨,所述驱动电机包括第一驱动电机和第二驱动电机;第一螺旋桨能够安装至所述第一驱动电机且不能安装至所述第二驱动电机;所述第二螺旋桨能够安装至所述第二驱动电机且不能安装至所述第一驱动电机。
  58. 根据权利要求57所述的无人飞行器,其特征在于,所述第一螺旋桨的固定部的端部和所述桨毂的中心的距离与所述第二螺旋桨的固定部的端部和所述桨毂的中心的距离不同;所述第一驱动电机的装配孔和所述第一驱动电机的中心轴线的距离与所述第二驱动电机的所述装配孔和所述第二驱动电机的中心轴线的距离不同。
  59. 根据权利要求58所述的无人飞行器,其特征在于,当所述第一螺旋桨与所述第二驱动电机固定时,所述固定部的外侧端部与所述上盖抵接,以阻止所述第一螺旋桨的固定部伸入所述第二驱动电机的装配孔;
    当所述第二螺旋桨与所述第一驱动电机固定时,所述固定部的内侧端部与所述上盖抵接,以阻止所述第二螺旋桨的固定部伸入所述第一驱动电机的装配孔。
  60. 根据权利要求51所述的无人飞行器,其特征在于,所述固定部的内侧端部包括朝向所述桨毂中心延伸的凸出部。
  61. 根据权利要求52所述的无人飞行器,其特征在于,所述装配孔的数量为多个,沿圆周均匀设置于所述上盖;所述卡扣部的数量为多个,沿圆周均匀设置于所述桨毂。
  62. 根据权利要求50所述的无人飞行器,其特征在于,还包括设置于所述上盖的弹性部件,所述弹性部件用于在所述上盖与所述螺旋桨相固定时抵持所述螺旋桨。
  63. 根据权利要求62所述的无人飞行器,其特征在于,还包括卡圈,固定于所述上盖,所述弹性部件的一端与所述卡圈固定。
  64. 根据权利要求63所述的无人飞行器,其特征在于,所述上盖的端面设有收容槽,所述弹性部件的端部收容设置于所述收容槽内;所述卡圈套接于弹性部件的外部并固定于所述收容槽内,以将所述弹性部件的端部固定于所述收容槽内。
  65. 根据权利要求64所述的无人飞行器,其特征在于,所述弹性部件包括本体部和与所述本体部连接的连接端,所述连接端收容设置于所述收容槽内,所述连接端的尺寸大于所述本体部的尺寸;
    所述卡圈的内径尺寸小于所述连接端的尺寸、大于所述本体部的尺寸,所述卡圈套接于所述本体部的外部并固定于所述收容槽内,以将所述连接端固定于所述收容槽内。
  66. 根据权利要求64所述的无人飞行器,其特征在于,所述卡圈与所述收容槽通过胶体固定。
  67. 根据权利要求64所述的无人飞行器,其特征在于,所述卡圈与所述收容槽过盈配合。
  68. 根据权利要求64所述的无人飞行器,其特征在于,所述收容槽的侧壁设有台阶孔,所述卡圈的侧部设有与所述台阶孔相适配的凸起部,所述凸起部卡接于所述台阶孔。
  69. 根据权利要求64所述的无人飞行器,其特征在于,所述弹性部件的端部与所述收容槽铆压固定。
  70. 根据权利要求64所述的无人飞行器,其特征在于,所述弹性部件的端部与所述收容槽焊接固定。
  71. 根据权利要求50所述的无人飞行器,其特征在于,所述驱动电机包括外壳,所述上盖包括盖合部,所述盖合部盖设于所述外壳。
  72. 根据权利要求50所述的无人飞行器,其特征在于,转子的磁轭所用的材料的质量密度大于所述上盖所用的材料的质量密度。
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