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WO2015176240A1 - Dispositif de puissance et aéronef - Google Patents

Dispositif de puissance et aéronef Download PDF

Info

Publication number
WO2015176240A1
WO2015176240A1 PCT/CN2014/077964 CN2014077964W WO2015176240A1 WO 2015176240 A1 WO2015176240 A1 WO 2015176240A1 CN 2014077964 W CN2014077964 W CN 2014077964W WO 2015176240 A1 WO2015176240 A1 WO 2015176240A1
Authority
WO
WIPO (PCT)
Prior art keywords
fastening portion
hub
motor
propeller
cover
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/CN2014/077964
Other languages
English (en)
Chinese (zh)
Inventor
陶冶
邓涛
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.)
SZ DJI Technology Co Ltd
Original Assignee
SZ DJI Technology Co Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by SZ DJI Technology Co Ltd filed Critical SZ DJI Technology Co Ltd
Priority to PCT/CN2014/077964 priority Critical patent/WO2015176240A1/fr
Priority to CN201480002509.8A priority patent/CN104684805B/zh
Publication of WO2015176240A1 publication Critical patent/WO2015176240A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

Classifications

    • 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
    • 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 flight technology, and in particular, to a power device and an aircraft.
  • a rotorcraft is a flying device that uses a motor to drive a propeller to generate power to achieve space flight.
  • Portable rotorcraft includes UAVs (Unmanned Aerial Vehicles) that are controlled by ground remote control, etc. These aircrafts are widely used because of their relatively low cost and the ability to provide lightweight, flexible low-altitude, low-speed flight. To a variety of civilian areas, especially in various fields of geographic mapping, aerial photography and so on.
  • the power device of the existing rotorcraft generally includes: a motor driver connected to the flight controller, a motor that drives the propeller to rotate, and a propeller, and the propeller is fixed between the motor and the propeller through a hole between the motor shaft and the propeller.
  • the motor shaft is fixed by screwing between the shaft of the propeller and the hole of the propeller, or a protrusion is arranged on the rotating shaft of the motor, and a W slot is arranged in the hole of the propeller, and the propeller is fixed by the cooperation between the protrusion and the W slot.
  • the motor is fixed by screwing between the shaft of the propeller and the hole of the propeller, or a protrusion is arranged on the rotating shaft of the motor, and a W slot is arranged in the hole of the propeller, and the propeller is fixed by the cooperation between the protrusion and the W slot.
  • the assembly and disassembly generally require the use of tools, making the assembly and disassembly of the propeller inconvenient. While the fixing by the projections and the recesses is easy to assemble and disassemble, the cooperation of the projections and the grooves is easy to loosen, which is disadvantageous for the flight of the aircraft.
  • the technical problem to be solved by the embodiments of the present invention is to provide a power device and an aircraft, which can effectively ensure that the propeller is fixed on the motor and is easy to assemble and disassemble.
  • An embodiment of the present invention provides a power device, including: a propeller and a motor, the propeller includes a blade and a hub, the motor includes a stator assembly, a rotor assembly, and a rotating shaft, and the rotor assembly includes a sleeve body and a cover body. among them:
  • the hub is provided with a central hole, a first fastening portion, and the cover body is provided with a second fastening portion; between the first fastening portion of the hub and the second fastening portion of the cover A snap fit, and the rotating shaft cooperates with a center hole of the hub to fix the propeller to the motor.
  • first buckle portion of the hub and the second buckle portion of the cover body are buckled Fit.
  • the rotating shaft and the central hole of the hub are an interference fit.
  • the first locking portion includes a fastening member, and the fastening member is fixed on the inner wall of the receiving cavity; the first fastening portion is disposed on the inner wall of the receiving cavity;
  • the bottom of the cover is connected to the sleeve, the second fastening portion is protruded from the upper surface of the cover, and the second fastening portion includes: a buckle with the first fastening portion a member - a snap fit projection and a resisting member for resisting the fastener of the first snap portion.
  • the bottom of the cover body is connected to the sleeve body, the second buckle portion is protruded from the upper surface of the cover body, and the second buckle portion includes a fastener;
  • the first latching portion is disposed on an inner wall of the receiving cavity, and the first latching portion includes:
  • the fastener of the second fastening portion is a snap-fit projection and a resisting member for resisting the fastener of the second fastening portion.
  • the cover body and the second fastening portion provided on the cover body are integrally formed.
  • the motor comprises a brushless motor.
  • an embodiment of the present invention further provides an aircraft, including: an aircraft body and a power device fixed to the aircraft body, wherein the power device includes: a propeller and a motor, the propeller including a blade and a paddle a hub, the motor includes a stator assembly, a rotor assembly, and a rotating shaft, the rotor assembly including a sleeve body and a cover body, wherein:
  • the hub is provided with a central hole, a first fastening portion, and the cover body is provided with a second fastening portion; between the first fastening portion of the hub and the second fastening portion of the cover A snap fit, and the rotating shaft cooperates with a center hole of the hub to fix the propeller to the motor.
  • first fastening portion of the hub and the second fastening portion of the cover are interference-fitted by the buckle.
  • the rotating shaft has an interference fit with a center hole of the hub.
  • the motor comprises a brushless motor.
  • the cooperation between the center hole of the hub and the motor shaft, and the first buckle portion opened in the hub and the second buckle portion formed on the cover of the motor are more convenient.
  • the assembly and disassembly of the motor and the propeller in the aircraft power unit are completed, and the concentricity and verticality of the motor and the propeller can be ensured to some extent.
  • FIG. 1 is a schematic structural view of a motor of a power unit according to an embodiment of the present invention
  • FIG. 2 is a schematic structural view of a power unit according to an embodiment of the present invention.
  • FIG. 3 is a schematic structural view of a portion of a propeller according to an embodiment of the present invention.
  • FIG. 4 is a schematic structural view of a part of a motor according to an embodiment of the present invention.
  • Figure 5 is a schematic view showing another structure of a portion of a propeller according to an embodiment of the present invention.
  • Figure 6 is a cross-sectional view taken along line VI-VI of Figure 5;
  • FIG. 7 is another schematic structural view of a part of a motor according to an embodiment of the present invention.
  • Figure 8 is a schematic cross-sectional view taken along line VIII-VIII of Figure 2.
  • the center hole of the propeller cooperates with the rotating shaft of the motor, and the first fastening portion of the propeller cooperates with the second fastening portion of the cover of the motor, and the two matching manners can be fixed by using an interference fit. Therefore, the assembly and disassembly work between the propeller and the motor can be better accomplished without tools, and the propeller can be better fixed to ensure flight safety.
  • FIG. 1 is a schematic structural view of a motor of a power unit according to an embodiment of the present invention
  • FIG. 2 is a schematic structural view of a power unit according to an embodiment of the present invention
  • FIG. 3 is a schematic view of a portion of a propeller according to an embodiment of the present invention
  • 4 is a schematic structural view of a part of a motor according to an embodiment of the present invention
  • FIG. 8 is a schematic cross-sectional view taken along line VIII-VIII of FIG.
  • the power unit according to the present invention includes: a propeller and a motor, wherein the propeller includes a blade 11 and a hub 12, the motor includes a stator assembly 1, a rotor assembly 2, and a rotating shaft 3, and the rotor assembly 2 includes a casing 21. Cover body 22.
  • the stator assembly 1 is located at one end of the sleeve body 21, and the sleeve The other end of the body 21 is fixedly coupled to the cover 22. It can be understood that the position between the stator assembly 1, the rotor assembly 2 and the rotating shaft 3 and the connection relationship thereof can be referred to the prior art.
  • the hub 12 is provided with a central hole 121 and a first fastening portion 122.
  • the cover 22 is provided with a second fastening portion 221;
  • the first fastening portion 122 is snap-fitted with the second fastening portion 221 of the cover 22, and the rotating shaft 3 is engaged with the central hole 121 of the hub 12 to fix the propeller to the
  • the power unit 2 is described so that the propeller is better fixed to the motor.
  • the first fastening portion 122 includes four fasteners.
  • the first fastening portion 122 may include one, two, three, and the like as needed. As long as it can cooperate with the corresponding second hooking portion 221, the entire propeller can be fixed to the motor.
  • the first fastening portion 122 and the second fastening portion 221 are interference fit after being rotated or the like, and the rotating shaft 3 and the central hole 121 of the hub 12 are also interference fit.
  • the rotating shaft 3 and the central hole 121 of the hub 12 Through the cooperation between the rotating shaft 3 and the central hole 121 of the hub 12, not only the effect of fixing the propeller on the rotor assembly 2 of the motor and the removal of the propeller from the motor can be achieved, but also the motor and the motor can be better ensured. Concentricity between the shafts.
  • the interference fit between the first fastening portion 122 and the second fastening portion 221 after rotation the effect of better fixing the propeller on the motor and facilitating the removal of the propeller from the motor is further ensured. It is also possible to better ensure the verticality of the propeller.
  • the hub 12 is provided with a receiving cavity 123
  • the central hole 121 is disposed at a center of the receiving cavity 123
  • the first fastening portion 122 includes at least two fasteners.
  • the fasteners 1221 are fixed on the inner wall of the receiving cavity 123.
  • each of the two fasteners 1221 can be disposed at a fixed interval.
  • the inner wall of the receiving cavity 123 can also be used to fix the fasteners 1221 to ensure that the first fastening portion 122 and the second fastening portion 221 are fastened to better secure the propeller to the motor.
  • the paddle and the hub may be integrally formed.
  • the center hole 121 is fixed in the receiving cavity 123 by four symmetrical fixing members.
  • the fixing member may include only one, two or three, etc., as long as the center hole 121 can be fixed in the receiving cavity 123. Just fine.
  • the second fastening portion 221 Protruding on the upper surface of the cover 22 includes: a protrusion 2211 that is snap-fitted with the fastener 1221 of the first fastening portion 122, and is configured to respectively resist the first fastening portion 122
  • the cover 22 and the second fastening portion 221 disposed on the cover 22 may be integrally formed.
  • the side surface of the cover 22 can be provided with a heat dissipation hole, which can effectively dissipate heat during the operation of the brushless single machine.
  • the cooperation between the center hole of the hub and the motor shaft, and the first buckle portion opened in the hub and the second buckle portion opened on the cover of the motor can be more effective.
  • the ground ensures that the propeller is fixed on the relevant components of the motor, and the assembly and disassembly between the motor and the propeller in the aircraft power device can be conveniently performed, and the concentricity and verticality of the motor and the propeller can be ensured to some extent.
  • FIG. 5 is a schematic structural view of another portion of a propeller according to an embodiment of the present invention
  • FIG. 6 is a cross-sectional view taken along line VI-VI of FIG. 5
  • FIG. 7 is another schematic structural view of a portion of the motor of the embodiment of the present invention. .
  • the power device includes: a propeller and a motor, wherein the propeller includes a blade 11 and a hub 12, and the motor includes a stator assembly 1, a rotor assembly 2, and a rotating shaft 3,
  • the rotor assembly 2 includes a sleeve body 21 and a cover body 22. The sleeve 21 and the cover 22 may be in a fixed connection.
  • the hub 12 is provided with a central hole 421 and a first fastening portion 422.
  • the cover 22 is provided with a second fastening portion 521;
  • the first fastening portion 422 is snap-fitted with the second fastening portion 521 of the cover 22, and the rotating shaft 3 is engaged with the central hole 421 of the hub 12 to fix the propeller in the On the device assembly 2 of the motor.
  • the rotating shaft 3 and the central hole 421 of the hub 12 can be interference-fitted, and the first fastening portion 422 and the second locking portion 521 are interference fit after being rotated or the like.
  • the rotating shaft 3 and the central hole 421 of the hub 12 not only the propeller and the fixed motor can be fixed on the motor.
  • the interference fit between the first fastening portion 422 and the second fastening portion 521 after rotation the effect of better fixing the propeller on the motor and facilitating the removal of the propeller from the motor is further ensured. It is also possible to better ensure the verticality of the propeller.
  • the bottom of the cover body 22 is connected to the sleeve body 21.
  • the second fastening portion 521 is protruded from the upper surface of the cover body 22.
  • the second fastening portion 521 includes At least two fasteners 5211; specifically, a fixed spacing size distribution between each of the two fasteners 5211.
  • the cover 22 and the second fastening portion 221 disposed on the cover 22 may be integrally formed.
  • the number of fasteners of the second fastening portion 521 may include only one, two or three or the like as needed, as long as the first fastening portion 422 can cooperate with the first fastening portion 422 to fix the propeller to the motor.
  • the hub 12 is provided with a receiving cavity 423.
  • the center hole 421 is disposed at a center of the receiving cavity 423, and the first fastening portion 422 is disposed at the receiving cavity 423.
  • the first fastening portion 422 includes: a protrusion 4221 that is engaged with the fastening member 5211 of the second fastening portion 521, and a fastener for resisting the second fastening portion 521 The resisting member 4222 of 5211.
  • the paddle and the hub may be integrally formed.
  • the side surface of the cover 22 can be provided with a heat dissipation hole, which can effectively dissipate heat during the operation of the brushless single machine.
  • the cooperation between the center hole of the hub and the motor shaft, and the first buckle portion opened in the hub and the second buckle portion opened on the cover of the motor can be more effective.
  • the ground ensures that the propeller is fixed on the relevant components of the motor, and the assembly and disassembly between the motor and the propeller in the aircraft power device can be conveniently performed, and the concentricity and verticality of the motor and the propeller can be ensured to some extent.
  • An embodiment of the present invention further provides an aircraft, the aircraft comprising: an aircraft body and a power device fixed to the aircraft body, wherein the power device comprises: a propeller and a motor,
  • the propeller includes a paddle, a hub, the motor includes a stator assembly, a rotor assembly, and a rotating shaft, and the rotor assembly includes a sleeve body and a cover body, wherein:
  • the hub is provided with a central hole, a first fastening portion, and the cover body is provided with a second fastening portion; between the first fastening portion of the hub and the second fastening portion of the cover A snap fit, and the shaft cooperates with a central bore of the hub to secure the propeller to an associated component of the motor to secure the propeller on the motor.
  • a first interference between the first fastening portion of the hub and the second fastening portion of the cover body is achieved by a snap fit.
  • the rotating shaft is in an interference fit with a center hole of the hub.
  • the hub is provided with a receiving cavity, the central hole is disposed at a center of the receiving cavity, and the first fastening portion includes at least two fasteners, and at least two fasteners are fixed to the receiving cavity On the inner wall; the paddle and the hub are integrally formed.
  • the bottom of the cover body is connected to the sleeve body, and the second fastening portion is protruded from the upper surface of the cover body, and includes: a buckle that is engaged with the first buckle portion a projection, and a resisting member for respectively resisting the fastener of the first fastening portion.
  • the cover body and the second fastening portion provided on the cover body are integrally formed.
  • a heat dissipation hole is defined in a side surface of the cover body.
  • the motor includes a brushless motor.
  • the cooperation between the center hole of the hub and the motor shaft, and the first buckle portion opened in the hub and the second buckle portion opened on the cover of the motor can be more effective.
  • the ground ensures that the propeller is fixed on the motor, and the assembly and disassembly of the motor and the propeller in the aircraft power unit can be conveniently performed, and the concentricity and verticality of the motor and the propeller can be ensured to a certain extent, thereby making the flight of the aircraft more convenient. stable.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)

Abstract

La présente invention concerne un dispositif de puissance et un aéronef. Ledit dispositif de puissance comprend une hélice et un moteur. Ladite hélice comprend des pales d'hélice (11) et un moyeu d'hélice (12). Ledit moteur comprend un élément de stator (1), un élément de rotor (2) et un arbre rotatif (3). Ledit élément de rotor (2) comprend un corps de manchon (21) et un corps de couvercle (22). Ledit corps de couvercle (22) est pourvu d'un trou central (121) et d'une seconde partie boucle (221). Ledit corps de couvercle (22) est pourvu d'une deuxième portion de boucle (221). Ladite première partie boucle du moyeu d'hélice et ladite seconde partie boucle du corps de couvercle sont mises en correspondance au moyen d'une boucle et ledit arbre rotatif est mis en correspondance avec ledit trou central du moyeu d'hélice pour fixer ladite hélice sur ledit moteur. Par la présente invention, le moteur et l'hélice dans un dispositif de puissance d'un aéronef sont plus commodes à assembler et à désassembler. Pendant ce temps, la concentricité et la verticalité du moteur et de l'hélice sont assurées dans une certaine mesure.
PCT/CN2014/077964 2014-05-21 2014-05-21 Dispositif de puissance et aéronef Ceased WO2015176240A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
PCT/CN2014/077964 WO2015176240A1 (fr) 2014-05-21 2014-05-21 Dispositif de puissance et aéronef
CN201480002509.8A CN104684805B (zh) 2014-05-21 2014-05-21 一种动力装置及飞行器

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/CN2014/077964 WO2015176240A1 (fr) 2014-05-21 2014-05-21 Dispositif de puissance et aéronef

Publications (1)

Publication Number Publication Date
WO2015176240A1 true WO2015176240A1 (fr) 2015-11-26

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/CN2014/077964 Ceased WO2015176240A1 (fr) 2014-05-21 2014-05-21 Dispositif de puissance et aéronef

Country Status (2)

Country Link
CN (1) CN104684805B (fr)
WO (1) WO2015176240A1 (fr)

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US10126745B2 (en) 2015-01-04 2018-11-13 Hangzhou Zero Zero Technology Co., Ltd. System and method for automated aerial system operation
US10358214B2 (en) 2015-01-04 2019-07-23 Hangzhou Zero Zro Technology Co., Ltd. Aerial vehicle and method of operation
US9836053B2 (en) 2015-01-04 2017-12-05 Zero Zero Robotics Inc. System and method for automated aerial system operation
CN105173072B (zh) * 2015-07-23 2018-01-23 广州飞米电子科技有限公司 动力装置和飞行器
CN106606877A (zh) * 2015-10-23 2017-05-03 李海活 一种桨毂结构及具有该桨毂结构的螺旋桨和电机
CN107108011B (zh) * 2016-01-29 2019-04-09 深圳市大疆创新科技有限公司 无人机及其机臂机构
CN105667777B (zh) * 2016-03-29 2018-06-22 普宙飞行器科技（深圳）有限公司 四向伸缩桨叶保护罩、动力系统以及无人飞行器
CN105836120B (zh) * 2016-03-29 2018-06-29 普宙飞行器科技（深圳）有限公司 两向伸缩桨叶保护罩、动力系统以及无人飞行器
US10435144B2 (en) 2016-04-24 2019-10-08 Hangzhou Zero Zero Technology Co., Ltd. Aerial system propulsion assembly and method of use
CN107776867B (zh) * 2016-08-31 2023-03-07 臻迪科技股份有限公司 一种无人机机臂装置
CN206171814U (zh) * 2016-10-24 2017-05-17 深圳市道通智能航空技术有限公司 一种无人机旋翼自锁结构及无人机
WO2018134677A1 (fr) 2017-01-23 2018-07-26 Hangzhou Zero Technology Co., Ltd Système à caméras multiples et procédé d'utilisation associé
CN106986017B (zh) * 2017-03-10 2023-11-10 歌尔科技有限公司 一种螺旋桨快速装拆结构及无人飞行器
TWI642859B (zh) * 2017-11-20 2018-12-01 光寶電子（廣州）有限公司 拆裝結構與無人機
CN108725774A (zh) * 2018-06-14 2018-11-02 深圳市飞米机器人科技有限公司 桨叶、螺旋桨、动力装置及多旋翼飞行器

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US4415133A (en) * 1981-05-15 1983-11-15 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Solar powered aircraft
CN101590910A (zh) * 2009-04-03 2009-12-02 南京信息工程大学 一种高速转体式直升机
CN202006023U (zh) * 2011-02-28 2011-10-12 广东奥飞动漫文化股份有限公司 可对战玩耍的遥控玩具直升机
CN202020920U (zh) * 2011-03-31 2011-11-02 蔡少山 一种新型遥控式玩具直升飞机
CN202358299U (zh) * 2011-11-04 2012-08-01 深圳市大疆创新科技有限公司 一种拆装式多旋翼飞行器
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CN104684805A (zh) 2015-06-03
CN104684805B (zh) 2016-08-31

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