WO2020103055A1 - Ensemble rotor et véhicule aérien sans pilote - Google Patents

Ensemble rotor et véhicule aérien sans pilote

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Publication number
WO2020103055A1
WO2020103055A1 PCT/CN2018/116793 CN2018116793W WO2020103055A1 WO 2020103055 A1 WO2020103055 A1 WO 2020103055A1 CN 2018116793 W CN2018116793 W CN 2018116793W WO 2020103055 A1 WO2020103055 A1 WO 2020103055A1
Authority
WO
WIPO (PCT)
Prior art keywords
motor
propeller
locking
locking portion
rotor assembly
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
PCT/CN2018/116793
Other languages
English (en)
Chinese (zh)
Inventor
杨健
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 CN201880039302.6A priority Critical patent/CN110891858B/zh
Priority to PCT/CN2018/116793 priority patent/WO2020103055A1/fr
Publication of WO2020103055A1 publication Critical patent/WO2020103055A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/10—Rotorcrafts
    • B64U10/13—Flying platforms
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/02—Hub construction
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/02—Hub construction
    • B64C11/04—Blade mountings
    • 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
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D35/00—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U30/00—Means for producing lift; Empennages; Arrangements thereof
    • B64U30/20—Rotors; Rotor supports
    • B64U30/29—Constructional aspects of rotors or rotor supports; Arrangements thereof
    • B64U30/291—Detachable rotors or rotor supports

Definitions

  • the present application relates to the field of flight technology, in particular to a rotor assembly and an unmanned aerial vehicle.
  • Multi-rotor unmanned aerial vehicles usually drive the propeller to generate power through the motor, so as to achieve space flight.
  • Portable multi-rotor unmanned aerial vehicles include some UAVs (Unmanned Aerial) that complete the flight through ground control and other control methods. These unmanned aerial vehicles can provide lightweight, flexible low-altitude and low speed due to their relatively low cost Flying has been widely used in various civil fields, especially in various geographic surveying, aerial photography and other fields.
  • the rotor assembly of a multi-rotor UAV generally includes a propeller and a motor that drives the propeller to rotate to provide rotational power.
  • the traditional connection between the motor and the propeller is screwed or snapped.
  • the motor on the multi-rotor unmanned aerial vehicle has two directions of clockwise rotation and counterclockwise rotation, two structural symmetries are required
  • the propellers are paired with a clockwise motor and a counterclockwise motor.
  • the users of unmanned aerial vehicles often need to disassemble and install the propeller, but many ordinary users cannot accurately distinguish between the propeller rotating clockwise and the propeller rotating counterclockwise. There will even be dangers such as bombers.
  • the present application provides a rotor assembly and an unmanned aerial vehicle that are easy to disassemble and have a foolproof function.
  • a rotor assembly for an unmanned aerial vehicle includes a main body and a plurality of arms fixedly connected to the main body.
  • the rotor assembly includes:
  • the first motor is installed at one end of the arm
  • the first propeller has a first locking portion for detachably connecting with the first motor
  • the second motor is installed at one end of the arm
  • the second propeller has a second locking portion for detachably connecting with the second motor
  • first locking portion is different from the second locking portion to prevent the first propeller from being installed on the second motor, or to prevent the second propeller from being installed on the first motor .
  • an unmanned aerial vehicle including:
  • the first motor is installed at one end of the arm
  • the first propeller has a first locking portion for detachably connecting with the first motor
  • the second motor is installed at one end of the arm
  • the second propeller has a second locking portion for detachably connecting with the second motor
  • first locking portion is different from the second locking portion to prevent the first propeller from being installed on the second motor, or to prevent the second propeller from being installed on the first motor .
  • the technical solution provided by the embodiments of the present application may include the following beneficial effects:
  • the present application designs a rotor assembly and an unmanned aerial vehicle.
  • the rotor assembly includes a first motor, a first propeller, a second motor, and a second propeller, wherein A propeller is provided with a first locking portion, and a second propeller is provided with a second locking portion which is different from the first locking portion.
  • first locking portion and / or the second locking portion be used to connect the first
  • the propeller is quickly installed on the first motor and / or the second propeller is quickly installed on the second motor, and it can also prevent the first propeller from being installed on the second motor or the second propeller from being installed on the first motor, thereby There will be no wrong propeller installation, to ensure that the UAV can work normally.
  • FIG. 1 is a schematic structural diagram of an unmanned aerial vehicle provided by an embodiment of the present application.
  • FIG. 2 is a top view of the UAV provided in FIG. 1;
  • FIG. 3 is a cross-sectional view of the UAV provided in FIG. 1;
  • Figure 3a is a partially enlarged view of Figure 3 at A;
  • Figure 3b is a partially enlarged view of Figure 3 at B;
  • FIG. 4 is a schematic structural view of the first propeller provided in FIG. 1;
  • FIG. 5 is a schematic structural diagram of the first motor provided in FIG. 1;
  • FIG. 6 is a schematic structural view of the elastic member provided in FIG. 1 mounted on the first motor;
  • FIG. 7 is a schematic structural view of the second propeller provided in FIG. 1;
  • FIG. 8 is a schematic structural diagram of the second motor provided in FIG. 1;
  • FIG. 9 is a schematic structural view of the elastic member provided in FIG. 1 installed in a second motor;
  • FIG. 10 is a schematic structural view of the first propeller provided in FIG. 1 mounted on a second motor
  • FIG. 11 is a schematic structural diagram of a first propeller provided by another embodiment of the present application.
  • FIG. 12 is a schematic structural diagram of a first motor provided by another embodiment of the present application.
  • FIG. 13 is a schematic structural diagram of a second propeller provided by another embodiment of the present application.
  • FIG. 14 is a schematic structural diagram of a second motor provided by another embodiment of the present application.
  • the first motor 31.
  • the first clamping part; 31a the third clamping part; 311, the first guide slot; 312, the first locking slot; 313, the first stopper; 32, the first rotor shell ; 33, the first shaft;
  • the first propeller 41.
  • the first locking portion 411.
  • the second motor 51.
  • the second clamping slot 51a.
  • the fourth clamping part 511.
  • the second locking slot 513.
  • Second propeller 60.
  • Second propeller 61.
  • Second locking portion 611.
  • the rotor assembly of the unmanned aerial vehicle of the present application generally includes a propeller and a motor that drives the propeller to provide rotation power. Since the motor on the multi-rotor unmanned aerial vehicle has clockwise rotation and counterclockwise rotation, the propeller mounted on the motor It also includes two symmetrical propellers, which are paired with a clockwise motor and a counterclockwise motor. In general, ordinary users cannot accurately distinguish between propellers rotating clockwise and propellers rotating counterclockwise. The problem of incorrectly installing the propellers often occurs, resulting in unmanned aerial vehicles not working properly, and even dangers such as bombers. Therefore, this application proposes a reasonable design, which can effectively solve the above problems.
  • an embodiment of the present application provides an unmanned aerial vehicle.
  • the unmanned aerial vehicle may include a main body 10, a plurality of arms 20 fixedly connected to the main body 10 and mounted on the arm 20.
  • Rotor assembly 100 includes a first motor 30, a first propeller 40 matching the number of the first motor 30, a second motor 50, and a second propeller 60 matching the number of the second motor 50.
  • the first motor 30 and the second motor 50 have different steering directions, and the structures of the first propeller 40 and the second propeller 60 are symmetrical to each other.
  • the number of the first motor 30, the first propeller 40, the second motor 50, and the second propeller 60 is not limited.
  • the first propeller 40 is provided with a first locking portion, and the first propeller 40 is detachably connected to the first motor 30 through the first locking portion, and the first motor 30 is installed on one of the arms 20
  • the second propeller 60 is provided with a second locking portion, through which the second propeller 60 is detachably connected to the second motor 50, and the second motor 50 is installed at one end of the other arm 20
  • the first locking portion is different from the second locking portion.
  • the arms 20 are distributed on the peripheral side of the main body 10 in a radial manner, and the number of the arms 20 is not limited.
  • the sum of the number of the first motor 30 and the second motor 50 matches the number of the arm 20.
  • the number of the arm 20 is four, which are two first arms 21 and two The two arms 22, the two first arms 21 and the two second arms 22 are spaced apart and arranged symmetrically on the peripheral side of the main body 10.
  • the two first motors 30 are respectively disposed on the ends of the two first arms 21 away from the main body 10
  • the two second motors 50 are respectively disposed on the ends of the two second arms 22 away from the main body 10.
  • a foolproof structure 45 is further provided on the first propeller 40.
  • the foolproof structure 45 can ensure the accurate docking between the first propeller 40 and the first motor 30 when the rotor assembly 100 is assembled.
  • the foolproof structure 45 can prevent the first propeller 40 and the second motor 50 from being reversed, so as to improve assembly accuracy and reliability, and thus ensure that the UAV can work normally.
  • the foolproof structure 45 may be any structure, such as a boss, a sheet-like structure, or a corner with rounded corners.
  • the position of the foolproof structure 45 is not limited.
  • the foolproof structure 45 is located above the first locking portion, which can not only facilitate the molding design of the first propeller 40, but also save the manufacturing cost of the rotor assembly 100.
  • the foolproof structure 45 has a column shape, such as a column shape, a square column shape, or other irregular column shapes.
  • the main body 10 is provided with a blocking member 70 on the side close to the second motor 50; when the first propeller 40 is assembled with the second motor 50 through the first locking portion, the blocking member 70 is connected to the end away from the arm 20
  • the foolproof structure 45 abuts to restrict the first propeller 40 from moving in the direction of the arm 20, so that the first propeller 40 cannot be locked on the second motor 50, thereby playing a foolproof role.
  • the foolproof structure 45 is provided with a gap 451, and the number and position of the gap 451 are not limited.
  • the number of gaps 451 is two
  • the two notches 451 are arranged symmetrically on both sides of the foolproof structure 45, and the notch 451 is adapted to the width of the resisting member 70.
  • the specific setting method of the foolproof structure 45 is not limited to the above listed cases, and this solution also protects other feasible setting methods, which are not listed here one by one.
  • the first locking portion includes a first locking portion 41, and a first locking groove portion 31 is provided on the first motor 30, and the first locking groove portion 31 Matches with the first latching portion 41;
  • the second locking portion includes a second latching portion 61, a second latching portion 51 is provided on the second motor 50, the second latching portion 51 and the second latching portion 61 Match.
  • the structure and the number of the first buckling portion 41 and the second buckling portion 61 are different, which is used for foolproofing, to prevent the first propeller 40 from being installed on the second motor 50 or the second propeller 60 from being installed on the first motor 30 on.
  • the shapes of the first locking portion 41 and the second locking portion 61 are different; or the height positions of the first locking portion 41 and the second locking portion 61 are different; or the first locking portion 41 and the second locking portion
  • the sizes of the parts 61 are different; or the number of the first snap parts 41 and the second snap parts 61 are different and so on.
  • the number of the second locking portions 61 is greater than the number of the first locking portions 41 to prevent the second propeller 60 from being installed on the first motor 30.
  • the number of the first locking portions 41 is two, the two first locking portions 41 are arranged on the first propeller 40 at intervals, and the number of the first locking groove portions 31 matches the number of the first locking portions 41 .
  • the number of the second locking portions 61 is four, and the four second locking portions 61 are arranged on the second propeller 60 in an annular array.
  • the number of the second locking groove portions 51 matches the number of the second locking portions 61 .
  • the present application does not limit the case where the number of second buckling portions 61 is smaller than the number of first buckling portions 41.
  • first propeller 40 When assembling, first install the first propeller 40 along the first catch portion 41 in the first catch portion 31 of the first motor 30, and then rotate the first propeller 40 so that the first catch portion 41 engages in the first A slot 31; similarly, first install the second propeller 60 along the second latch 61 in the second slot 51 of the second motor 50, and then rotate the second propeller 60 so that the first card
  • the buckle portion 41 is engaged in the second locking groove portion 51, so that the second propeller 60 is mounted on the second motor 50.
  • the first propeller 40 is assembled with the second motor 50, since the number of the first locking portions 41 is two and the number of the second locking grooves 51 is four, the first propeller 40 can pass the first The hook 41 is mounted on the second motor 50.
  • the first propeller 40 is provided with a foolproof structure 45, and the main body 10 is provided with a blocking member 70 on the side close to the second motor 50, thereby preventing the first propeller 40 from being installed on the second motor 50 or the second motor 50 cannot drive the first propeller 40 to rotate. If the second propeller 60 is assembled with the first motor 30, since the number of the second locking portion 61 is four, and the number of the first locking portion 31 is two, the second propeller 60 cannot be locked to the first motor 30 on.
  • the first hook portion 41 has a hook-shaped structure, which includes a first convex portion 411 and a first engaging portion 412.
  • the first convex portion 411 is convexly provided on the first propeller 40
  • the first engaging portion 412 is bent and extended from the first convex portion 411 at an end away from the first propeller 40.
  • the cross section of the first engaging portion 412 has a fan-shaped structure.
  • the first convex portion 411 is perpendicular to the first propeller 40
  • the first engaging portion 412 is perpendicular to the first convex portion 411.
  • a molding design of the buckle portion 41 does not require preset high-precision screw holes, and the operation is simple.
  • the structure of the second locking portion 61 is the same as the structure of the first locking portion 41 and includes a second convex portion 611 and a second engaging portion 612.
  • the second convex portion 611 protrudes from the second propeller 60, and the second engaging portion 612 bends and extends from the second convex portion 611 at the end away from the second propeller 60.
  • the second engaging portion 612 has a fan-shaped structure in cross section.
  • the second convex portion 611 is perpendicular to the second propeller 60
  • the second engaging portion 612 is perpendicular to the second convex portion 611, which not only facilitates the molding design of the second latch portion 61, but also does not need to be preset High-precision threaded holes, simple operation requirements.
  • the first propeller 40 includes a first hub 42 and a first blade 43, and the first blade 43 is connected to the first hub 42.
  • the second propeller 60 includes a second hub 62 and a second blade 63, and the second blade 63 is connected to the second hub 62.
  • the first buckle portion 41 is provided on the first propeller hub 42 and the second buckle portion 61 is provided on the second propeller hub 62, thereby facilitating the first buckle portion 41 and the first propeller hub
  • the 42 and the first blade 43 are integrally formed, and the second buckling portion 61, the second hub 62, and the second blade 63 are integrally formed, thereby saving a lot of processing costs.
  • two of the first locking portion 41, the first hub 42 or the first blade 43 may be integrally formed, and the second locking portion 61, the second hub 62 or the second blade 63 Two of them are integrally formed, and this application is not limited.
  • the first convex portion 411 is convex on the first hub 42
  • the second convex portion 611 is convex on the second hub 62.
  • both the inner and outer walls of the first convex portion 411 are arc-shaped, which facilitates the rotation of the first engaging portion 412 and engages with the first engaging groove portion 31.
  • Both the inner and outer walls of the second convex portion 611 have an arc shape, which facilitates the rotation of the second engaging portion 612 and engages with the second engaging groove portion 51.
  • the first motor 30 includes a first rotor shell 32 and a first rotating shaft 33.
  • the first rotating shaft 33 and the first rotor shell 32 rotate together when the first motor is in operation, and are located at the end of the first arm 21.
  • the second motor 50 includes a second rotor housing 52 and a second rotating shaft 53.
  • the second rotating shaft 53 and the second rotor housing 52 rotate together when the second motor is operating, and are located at the end of the second arm 22.
  • the first clamping groove portion 31 includes a first guide groove 311 and a first locking groove 312.
  • the first guide groove 311 is opened on the first motor 30.
  • the first locking groove 312 is formed at the end of the first guide groove 311, and its shape is adapted to the shape of the first engaging portion 412.
  • it also includes a first stop 313, the first locking groove 312 is perpendicular to the first guide groove 311, the first guide groove 311 is parallel to the first rotating shaft 33, and the first stop 313 is disposed in the first guide groove The connection between 311 and the first locking groove 312.
  • the second locking groove 51 includes a second guide groove 511 and a second locking groove 512, and the second guide groove 511 Opened on the second motor 50, a second locking groove 512 is formed at the end of the second guide groove 511, and its shape matches the shape of the second engaging portion 612.
  • it further includes a second stopper 513, the second locking groove 512 is perpendicular to the second guide groove 511, the second guide groove 511 is parallel to the second rotating shaft 53, and the second stopper 513 is disposed in the second guide groove The connection between 511 and the second locking groove 512.
  • the rotor assembly 100 further includes a plurality of elastic members 80.
  • the elastic member 80 is respectively installed on the first motor 30 and the second motor 50.
  • the elastic member 80 is a spring, and the two springs are respectively sleeved on the first rotating shaft 33 and the second rotating shaft 53.
  • a propeller hub 42 is provided with a first groove 441 whose outer dimension matches the outer diameter of the spring, and the first groove 441 is coaxial with the first transmission hole 44.
  • the second propeller hub 62 is provided with a second groove 641 whose outer dimension matches the outer diameter of the spring, and the second groove 641 is coaxial with the second transmission hole 64.
  • the first locking portion includes a third locking groove portion 41 a
  • the first motor 30 is provided with a third locking portion 31 a
  • the third latching portion 31a matches the third latching portion 41a.
  • the second locking portion includes a second locking portion 61, and a second locking groove portion 51 is provided on the second motor 50, the second locking groove portion 51 matches the second locking portion 61, wherein, due to the third locking groove
  • the shape of the portion 41a is different from the shape of the second hook portion 61, and thus has a foolproof effect.
  • the third buckling portion 31a, the second buckling portion 61, the third buckling portion 41a and the second buckling portion 51 can all adopt the above structure, and at the same time, the third buckling portion 31a can be connected to the second buckle The same number of parts 61 will not be repeated here.
  • the first locking portion includes a third locking groove portion 41a
  • the first motor 30 is provided with a third locking portion 31a
  • a third locking portion 31a is matched with the third latching portion 41a
  • the second locking portion includes a fourth latching portion 61a
  • the second motor 50 is provided with a fourth latching portion 51a
  • the fourth latching portion 51a and the fourth latching portion Match 61a are different, which is used for the foolproof effect, to prevent the first propeller 40 from being installed on the second motor 50 or the second propeller 60 from being installed on the first motor 30 on.
  • the third locking groove 41a and the fourth locking groove 61a have different shapes; or the third locking groove 41a and the fourth locking groove 61a have different depths; or the third locking groove 41a and the fourth locking groove 61a
  • the dimensions of 61a are different; or the numbers of the third locking groove portions 41a and the fourth locking groove portions 61a are different, etc., which are the same as the above principle and will not be repeated here.
  • an embodiment of the present application further provides a rotor assembly 100 for use in an unmanned aerial vehicle, wherein the unmanned aerial vehicle includes a main body 10 and a plurality of fixedly connected to the main body 10
  • the rotor assembly 100 includes a first propeller 40, a first motor 30 installed at the end of the arm 20, a second propeller 60, and a second motor 50 installed at the end of the arm 20.
  • the first propeller 40 is provided with the first lock portion as described above, and the second propeller 60 is provided with the second lock portion as described above; when the rotor assembly 100 is assembled, the first propeller 40 can be prevented from being installed on the second motor 50 or the first The two propellers 60 are installed on the first motor 30, which will not be repeated here.

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

Abstract

L'invention concerne un ensemble rotor et un véhicule aérien sans pilote. L'ensemble rotor comprend : une première hélice (40), un premier moteur (30), une deuxième hélice (60) et un deuxième moteur (50). La première hélice (40) est pourvue d'une première partie de connexion de verrou. La deuxième hélice (60) est pourvue d'une deuxième partie de connexion de verrou. La première partie de connexion de verrou est différente de la deuxième partie de connexion de verrou, de façon à empêcher le montage de la première hélice (40) au niveau du deuxième moteur (50) ou à empêcher le montage de la deuxième hélice (60) au niveau du premier moteur (30).
PCT/CN2018/116793 2018-11-21 2018-11-21 Ensemble rotor et véhicule aérien sans pilote Ceased WO2020103055A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
CN201880039302.6A CN110891858B (zh) 2018-11-21 2018-11-21 旋翼组件及无人飞行器
PCT/CN2018/116793 WO2020103055A1 (fr) 2018-11-21 2018-11-21 Ensemble rotor et véhicule aérien sans pilote

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/CN2018/116793 WO2020103055A1 (fr) 2018-11-21 2018-11-21 Ensemble rotor et véhicule aérien sans pilote

Publications (1)

Publication Number Publication Date
WO2020103055A1 true WO2020103055A1 (fr) 2020-05-28

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CN (1) CN110891858B (fr)
WO (1) WO2020103055A1 (fr)

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