WO2017049607A1 - 旋翼组件及具有旋翼组件的无人飞行器 - Google Patents

旋翼组件及具有旋翼组件的无人飞行器 Download PDF

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Publication number
WO2017049607A1
WO2017049607A1 PCT/CN2015/090771 CN2015090771W WO2017049607A1 WO 2017049607 A1 WO2017049607 A1 WO 2017049607A1 CN 2015090771 W CN2015090771 W CN 2015090771W WO 2017049607 A1 WO2017049607 A1 WO 2017049607A1
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WO
WIPO (PCT)
Prior art keywords
propeller
rotor
locking
elastic
locking member
Prior art date
Application number
PCT/CN2015/090771
Other languages
English (en)
French (fr)
Inventor
耶方明
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 JP2018515669A priority Critical patent/JP6553291B2/ja
Priority to CN201910236601.5A priority patent/CN110294117B/zh
Priority to EP15904483.3A priority patent/EP3354567B1/en
Priority to CN201580066433.XA priority patent/CN107108027B/zh
Priority to PCT/CN2015/090771 priority patent/WO2017049607A1/zh
Publication of WO2017049607A1 publication Critical patent/WO2017049607A1/zh
Priority to US15/934,239 priority patent/US10988242B2/en
Priority to US17/236,423 priority patent/US20210403151A1/en

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/32—Rotors
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • 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
    • B64C11/08—Blade mountings for non-adjustable blades
    • B64C11/10—Blade mountings for non-adjustable blades rigid
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/006—Safety devices
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/04—Helicopters
    • B64C27/08—Helicopters with two or more rotors
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C39/00—Aircraft not otherwise provided for
    • B64C39/02—Aircraft not otherwise provided for characterised by special use
    • B64C39/024—Aircraft not otherwise provided for characterised by special use of the remote controlled vehicle type, i.e. RPV
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D35/00—Transmitting power from power plant to propellers or rotors; Arrangements of transmissions
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D35/00—Transmitting power from power plant to propellers or rotors; Arrangements of transmissions
    • B64D35/02—Transmitting power from power plant to propellers or rotors; Arrangements of transmissions characterised by the type of power plant
    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/10—Rotorcrafts
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/10—Rotorcrafts
    • B64U10/13—Flying platforms
    • B64U10/14—Flying platforms with four distinct rotor axes, e.g. quadcopters
    • 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

Definitions

  • the present invention relates to the field of unmanned aerial vehicles, and more particularly to a rotor assembly and an unmanned aerial vehicle having the same.
  • the rotor assembly As a propulsion structure for a rotary-wing UAV, the rotor assembly is very demanding in quality, not only to provide suitable propulsion at higher speeds, but also to ensure safety at high speeds without causing unmanned aerial vehicles. Damage to itself and/or damage to other objects by the UAV.
  • the rotor assembly generally includes a motor and a propeller.
  • the propeller is fixedly coupled to the motor shaft, and the motor shaft rotates the propeller to generate a propulsive force when rotating.
  • the connection between the existing propeller and the motor is often complicated, and the propeller and the motor cannot be quickly disassembled, which makes the disassembly and assembly difficult and inconvenient to use; the existing motor and the propeller detachable rotor assembly may cause the propeller
  • the wear is more serious, and the long-term use makes the damage or even the risk of shooting the propeller, which has potential safety hazards.
  • a rotor assembly includes a motor, a propeller, and a connection assembly that connects the propeller to the motor.
  • the electric machine includes a stator and a rotor rotatable relative to the stator.
  • the connecting assembly includes a locking member disposed between the propeller and the rotor and rotatable relative to the rotor and the propeller, the locking member passing the propeller by rotation relative to the propeller Locked on the motor.
  • the locking member includes a locking buckle
  • the propeller is formed with a first locking block that cooperates with the locking buckle.
  • the locking buckle is connected with the first locking block.
  • one end of the buckle connected to the first locking block is formed with a second locking block adapted to the first locking block, and the first locking member passes the second locking piece A locking block engages the first locking block to lock the propeller.
  • first locking block and the second locking mutual coupling surface are inclined surfaces inclined by a predetermined angle with respect to the rotation axis of the propeller, and the surface is further away from the side of the rotation axis Keep away from the motor.
  • a first alignment mark is formed on a side surface of the propeller facing away from the motor, and a second alignment mark is formed on the lock, when the locking member locks the propeller into position, The first alignment mark and the second alignment mark are located on the same diameter of the propeller.
  • the propeller includes a paddle and a blade fixedly coupled to the paddle, and the first locking block is disposed on the paddle.
  • the number of the blades is two and fixed to both sides of the paddle in the same diametrical direction of the paddle, and the first locking block is located between the blades and close to the blade A paddle is left between the blade and the other blade for the lock to pass.
  • the rotor includes a rotating shaft and a connecting portion fixedly connected to the rotating shaft, and the locking member is rotatably disposed between the propeller and the connecting portion.
  • the connecting assembly includes a limiting member coupled to the propeller and rotatably defining the locking member on the connecting portion.
  • the limiting member includes a limiting flange and a mounting boss connected to the limiting flange, the limiting flange is fixed on the connecting portion and restricts the locking member to rotate along the propeller
  • the shaft is rotated
  • the mounting boss is coupled to the propeller and is capable of restricting relative rotation between the limiting members about the rotation axis.
  • the limiting flange and the protruding direction of the mounting stud are perpendicular to each other.
  • the connecting assembly includes an elastic member disposed between the locking member and the motor, and the elastic member is fixed to the rotor and elastically abuts against the locking.
  • the locking member includes a connecting portion, and the connecting portion is formed with a protruding portion facing the motor, and the elastic member is formed with an elastic convex portion protruding toward the propeller, the elastic convex portion a portion elastically abuts against the protruding portion, wherein the locking portion is rotatable relative to the propeller and the rotor, and the protruding portion is movable along the elastic convex portion to the elastic convex portion Different sides.
  • both the convex portion and the both sides of the elastic convex portion are smooth curved surfaces.
  • the connecting portion is annular, and a pressing piece is formed on an inner side surface thereof, and the protruding portion is formed on the pressing piece.
  • the elastic member includes a connecting portion and an elastic abutting piece, and the connecting portion is fixed to the rotor, and the elastic abutting piece protrudes toward the locking member with respect to a surface of the connecting portion.
  • the elastic convex portion is formed by bending the elastic abutting piece.
  • An unmanned aerial vehicle comprising at least one rotor assembly.
  • the rotor assembly includes a motor, a propeller, and a connection assembly that connects the propeller to the motor.
  • the electric machine includes a stator and a rotor rotatable relative to the stator.
  • the connecting assembly includes a locking member disposed between the propeller and the rotor and rotatable relative to the rotor and the propeller, the locking member passing the propeller by rotation relative to the propeller Locked on the motor.
  • the locking member includes a locking buckle
  • the propeller is formed with a first locking block that cooperates with the locking buckle.
  • the locking buckle is connected with the first locking block.
  • one end of the buckle connected to the first locking block is formed with a second locking block adapted to the first locking block, and the first locking member passes the second locking piece A locking block engages the first locking block to lock the propeller.
  • first locking block and the second locking mutual coupling surface are inclined surfaces inclined by a predetermined angle with respect to the rotation axis of the propeller, and the surface is further away from the side of the rotation axis Keep away from the motor.
  • a first alignment mark is formed on a side surface of the propeller facing away from the motor, and a second alignment mark is formed on the lock, when the locking member locks the propeller into position, The first alignment mark and the second alignment mark are located on the same diameter of the propeller.
  • the propeller includes a paddle and a blade fixedly coupled to the paddle, and the first locking block is disposed on the paddle.
  • the number of the blades is two and fixed to both sides of the paddle in the same diametrical direction of the paddle, and the first locking block is located between the blades and close to the blade A paddle is left between the blade and the other blade for the lock to pass.
  • the rotor includes a rotating shaft and a connecting portion fixedly connected to the rotating shaft, and the locking member is rotatably disposed between the propeller and the connecting portion.
  • the connecting assembly includes a limiting member coupled to the propeller and rotatably defining the locking member on the connecting portion.
  • the limiting member includes a limiting flange and a mounting boss connected to the limiting flange, the limiting flange is fixed on the connecting portion and restricts the locking member to rotate along the propeller
  • the shaft is rotated
  • the mounting boss is coupled to the propeller and is capable of restricting relative rotation between the limiting members about the rotation axis.
  • the limiting flange and the protruding direction of the mounting stud are perpendicular to each other.
  • the connecting assembly includes an elastic member disposed between the locking member and the motor, and the elastic member is fixed to the rotor and elastically abuts against the locking.
  • the locking member includes a connecting portion, and the connecting portion is formed with a protruding portion facing the motor, and the elastic member is formed with an elastic convex portion protruding toward the propeller, the elastic convex portion a portion elastically abuts against the protruding portion, wherein the locking portion is rotatable relative to the propeller and the rotor, and the protruding portion is movable along the elastic convex portion to the elastic convex portion Different sides.
  • both the convex portion and the both sides of the elastic convex portion are smooth curved surfaces.
  • the connecting portion is annular, and a pressing piece is formed on an inner side surface thereof, and the protruding portion is formed on the pressing piece.
  • the elastic member includes a connecting portion and an elastic abutting piece, and the connecting portion is fixed to the rotor, and the elastic abutting piece protrudes toward the locking member with respect to a surface of the connecting portion.
  • the elastic convex portion is formed by bending the elastic abutting piece.
  • the UAV further includes a fuselage and an arm connected to the machine by the arm, and the rotor assembly is distributed around the fuselage by the arm.
  • the arm includes a main arm and an arm, one end of the main arm is connected to the fuselage, and the other end is connected to the arm, and the rotor assembly is located at an end of the arm.
  • the number of the rotor assemblies is four, and the four rotor assemblies are distributed in a rectangular area around the fuselage, and the adjacent rotor assemblies have different directions of rotation during operation.
  • An unmanned aerial vehicle comprising at least one rotor assembly.
  • the rotor assembly includes a motor, a propeller, and a connection assembly that connects the propeller to the motor.
  • the electric machine includes a stator and a rotor rotatable relative to the stator.
  • the connecting assembly includes a locking member disposed between the propeller and the rotor and rotatable relative to the rotor and the propeller, the locking member passing the propeller by rotation relative to the propeller Locked on the motor. When the locking member locks the propeller, the steering of the propeller is the same as the rotation of the propeller when the propeller is in operation.
  • the locking member includes a locking buckle
  • the propeller is formed with a first locking block that cooperates with the locking buckle.
  • the locking buckle is connected with the first locking block.
  • one end of the buckle connected to the first locking block is formed with a second locking block adapted to the first locking block, and the first locking member passes the second locking piece A locking block engages the first locking block to lock the propeller.
  • first locking block and the second locking mutual coupling surface are inclined surfaces inclined by a predetermined angle with respect to the rotation axis of the propeller, and the surface is further away from the side of the rotation axis Keep away from the motor.
  • a first alignment mark is formed on a side surface of the propeller facing away from the motor, and a second alignment mark is formed on the lock, when the locking member locks the propeller into position, The first alignment mark and the second alignment mark are located on the same diameter of the propeller.
  • the propeller includes a paddle and a blade fixedly coupled to the paddle, and the first locking block is disposed on the paddle.
  • the number of the blades is two and fixed to both sides of the paddle in the same diametrical direction of the paddle, and the first locking block is located between the blades and close to the blade A paddle is left between the blade and the other blade for the lock to pass.
  • the rotor includes a rotating shaft and a connecting portion fixedly connected to the rotating shaft, and the locking member is rotatably disposed between the propeller and the connecting portion.
  • the connecting assembly includes a limiting member coupled to the propeller and rotatably defining the locking member on the connecting portion.
  • the limiting member includes a limiting flange and a mounting boss connected to the limiting flange, the limiting flange is fixed on the connecting portion and restricts the locking member to rotate along the propeller
  • the shaft is rotated
  • the mounting boss is coupled to the propeller and is capable of restricting relative rotation between the limiting members about the rotation axis.
  • the limiting flange and the protruding direction of the mounting stud are perpendicular to each other.
  • the connecting assembly includes an elastic member disposed between the locking member and the motor, and the elastic member is fixed to the rotor and elastically abuts against the locking.
  • the locking member includes a connecting portion, and the connecting portion is formed with a protruding portion facing the motor, and the elastic member is formed with an elastic convex portion protruding toward the propeller, the elastic convex portion a portion elastically abuts against the protruding portion, wherein the locking portion is rotatable relative to the propeller and the rotor, and the protruding portion is movable along the elastic convex portion to the elastic convex portion Different sides.
  • both the convex portion and the both sides of the elastic convex portion are smooth curved surfaces.
  • the connecting portion is annular, and a pressing piece is formed on an inner side surface thereof, and the protruding portion is formed on the pressing piece.
  • the elastic member includes a connecting portion and an elastic abutting piece, and the connecting portion is fixed to the rotor, and the elastic abutting piece protrudes toward the locking member with respect to a surface of the connecting portion.
  • the elastic convex portion is formed by bending the elastic abutting piece.
  • the UAV further includes a fuselage and an arm connected to the machine by the arm, and the rotor assembly is distributed around the fuselage by the arm.
  • the arm includes a main arm and an arm, one end of the main arm is connected to the fuselage, and the other end is connected to the arm, and the rotor assembly is located at an end of the arm.
  • the number of the rotor assemblies is four, and the four rotor assemblies are distributed in a rectangular area around the fuselage, and the adjacent rotor assemblies have different directions of rotation during operation.
  • the rotor assembly and the UAV are locked by a locking member that is rotatable relative to the rotor and the propeller, so that the rotating structure of the propeller is separated from the locking structure, so The locking member does not transmit torque to the propeller while locking the propeller, and can effectively wear the propeller and ensure the safety of the rotor assembly.
  • the above method of locking and unlocking the propeller is relatively simple and quick, and is convenient to use.
  • FIG. 1 is a perspective view of an unmanned aerial vehicle according to an embodiment of the present invention.
  • FIG. 2 is an exploded view of one of the revolving rotor assemblies of the UAV of FIG. 1.
  • FIG. 3 is a bottom plan view of the propeller of the rotor assembly of FIG. 2.
  • FIG. 4 is a perspective view of the rotor assembly of FIG. 2 assembled with the propeller in an unlocked state.
  • Figure 5 is a perspective cross-sectional view showing a portion of the structure of the rotor assembly of Figure 4;
  • Figure 6 is a perspective view of the rotor assembly of Figure 4 in a locked state.
  • Figure 7 is a perspective cross-sectional view showing a portion of the structure of the rotor assembly of Figure 6.
  • FIG. 8 is a perspective view of another revolving rotor assembly of the UAV of FIG. 1 with the propeller in a locked state.
  • Unmanned aerial vehicle 100 body 10 shell 11 Containing space 101 Arm 20 Main arm twenty one Arm twenty two Rotor assembly 30 Motor 31 stator 311 Rotor 312 Rotating shaft 312a Connection 312b Connection surface 312c side 312d Connection hole 312e propeller 32 Paddle handle 321 First registration mark 321a First locking block 321b First mating surface 321c Mounting holes 321d Paddle 322 Connection component 33 Limiter 331 Limit flange 331a Mounting stud 331b Through hole 331c Locking piece 332 Lock 332a Connection 332b Second locking block 332c Second mating surface 332d Second alignment mark 332e Resisting film 332f Protrusion 332g Elastic part 333 Connection 333a Elastic abutment piece 333b Shaft hole 333c Through hole 333d Convex 333e Shooting equipment 200 Yuntai 300
  • an unmanned aerial vehicle 100 is a rotary wing unmanned aerial vehicle capable of flying and hovering in the air to perform specific tasks, such as flight, tracking, monitoring, exploration, Search and rescue, sowing, spraying pesticides, fire fighting, aerial photography, etc.
  • the unmanned aerial vehicle 100 can be equipped with predetermined functional modules, such as sensors, photographing devices, medicine boxes, etc., to achieve specific functions.
  • the unmanned aerial vehicle 100 is equipped with a photographing device 200, so that the unmanned aerial vehicle 100 realizes an aerial photographing function, and the photographing device 200 is connected to the unmanned aerial vehicle 100 through a pan/tilt head 300,
  • the pan/tilt 300 can adjust the photographing direction and/or the tilt angle of the photographing apparatus 200 and can provide a shock absorbing function for the photographing apparatus 200.
  • the UAV 100 of the embodiments of the present invention includes a fuselage 10, a boom 20, and a rotor assembly 30.
  • the arm 20 is coupled to the body 10, and the rotor assembly 30 is distributed around the body 10 by the arm 20.
  • the UAV 100 is a quadrotor UAV, so the number of the rotor assemblies 30 is four, and the four rotor assemblies 30 are distributed in a rectangular area around the body 10. And each of the rotor assemblies 30 is located at one vertex of the rectangle.
  • the adjacent rotor assemblies 30 have different rotational directions during operation, and the opposite rotational directions of the rotor assemblies 30 are the same.
  • the rotation direction of the pair of opposing rotor assemblies 30 is counterclockwise (direction A), and the rotation of the pair of opposite rotor assemblies 30 is clockwise (direction B).
  • the number of the rotor assemblies 30 may be appropriately changed according to different requirements.
  • the number of the rotor assemblies 30 may be two, three, six, eight, sixteen, etc., or even The number of rotor assemblies 30 can be only one.
  • the airframe 10 is a carrier of the unmanned aerial vehicle 100, and the components, such as a sensor, a circuit board, a processor, a communication module, and a battery, can be carried on or in the body 10.
  • the body 10 includes a casing 11 in which a housing space 101 for housing the components is formed.
  • the outer casing 11 is streamlined to reduce air resistance during flight.
  • the outer casing 11 can have other shapes, such as polygonal, circular, elliptical, and the like. It can be understood that the outer casing 11 can also be omitted, and the fuselage 10 is formed only by the bracket overlapping.
  • the arm 20 is used to support the rotor assembly 30 and distribute the rotor assembly 30 around the fuselage 10 in a predetermined pattern.
  • the number of the arms 20 is two, and each of the arms 20 supports two of the rotor assemblies 30.
  • Each of the arms 20 includes a main arm 21 and an arm 22, one end of which is connected to the body 10, and the other end is connected to the arm 22, the main arm 21 and the branch
  • the arms 22 are connected to each other in a "T" shape.
  • Two of the rotor assemblies 30 corresponding to each of the arms 20 are respectively disposed at opposite ends of the corresponding arms 22.
  • the number of the arms 20 is the same as the number of the rotor assemblies 30, that is, each of the arms 20 supports one of the rotor assemblies 30. At this time, the arms 22 may be omitted.
  • the rotor assembly 30 is directly disposed at the end of the main arm 21.
  • the arm 20 can be omitted.
  • the rotor assembly 30 can be directly disposed on the body 10.
  • the arm 20 may also be a support arm extending from the body 10, and a plurality of the support arms extend from the periphery of the body 10 and the body 10 Fixed connection or integral molding.
  • the number of support arms is the same as the number of the rotor assemblies 30, i.e., each of the support arms supports one of the rotor assemblies 30.
  • the rotor assembly 30 includes a motor 31, a propeller 32, and a connection assembly 33.
  • the connection assembly motor 31 and the propeller 32 can be detachably coupled to each other by the connection assembly 33.
  • the motor 31 includes a stator 311 and a rotor 312 rotatable relative to the stator 311.
  • the rotor 312 can be fixedly coupled to the arm 20.
  • the rotor 312 includes a rotating shaft 312a and a connecting portion 312b fixedly coupled to the rotating shaft 312a.
  • the central axis of the rotating shaft 312a coincides with the rotational axis of the rotor 312.
  • the connecting portion 312b is located around the rotating shaft 312a.
  • the connecting portion 312b includes a connecting surface 312c facing the propeller 32 and a side surface 312d on the circumferential side of the connecting surface 312c.
  • the central position of the connecting surface 312c is fixedly coupled to the rotating shaft 312a.
  • a plurality of connecting holes 312e are defined in the connecting surface 312c.
  • the connecting holes 312e are threaded holes, and the number of the connecting holes 312e is four.
  • the number of the connecting holes 312e can be other suitable changes according to different requirements, for example, two, three, five, six and the like.
  • the rotating shaft 312a protrudes from the connecting surface 312c toward the propeller 32 by a predetermined distance.
  • the rotating shaft 312a has a plurality of portions of different diameters.
  • the motor 31 may be any suitable type of motor such as a brushless motor or a brushed motor.
  • the propeller 32 includes a paddle 321 and a paddle 322 that is fixedly coupled to the paddle 321 .
  • the paddle 322 is counterclockwise rotated toward the blade, i.e., the paddle 322 can provide propulsion for the UAV 100 in a counterclockwise direction.
  • the number of the blades 322 is two and fixed to both sides of the paddle 321 in the same diameter direction of the paddle 321 .
  • the paddle 321 is substantially cylindrical, the top surface of the paddle 321 is formed with a first alignment mark 321a, and the side of the paddle 321 is formed with a first locking block 321b.
  • the first alignment identifier 321a is a circular hole. It can be understood that the first alignment identifier 321a may also be other forms of identifiers. For example, the first alignment identifier 321a may be a triangle. A hole, a square hole, an elliptical hole, a graphic symbol attached to the paddle 321 and the like.
  • the number of the first locking blocks 321b is two, and the first locking blocks 321b are respectively located on two sides of the paddle, and the paddles are located between the paddles 322.
  • the first locking block 321b protrudes from the side of the paddle 321 and extends a certain length along the circumferential direction of the paddle 321 .
  • the first locking block 321b is disposed adjacent to the propeller 32 and is directed toward the blade 322.
  • the length of the first locking block 321b along the circumferential direction of the paddle 321 is smaller than that of the paddle 322.
  • the circumferential length of the side of the paddle 321 is such that there is a certain amount of space between the first locking block 321b and the propeller 32 that is rotated toward the blade 322 that faces away.
  • a first mating surface 321c is formed on a side of the first locking block 321b facing away from the motor 31, and the first mating surface 321c is a slope inclined at an angle with respect to an axis of rotation of the propeller 32, such that the The side of the first mating face 321c away from the rotational axis of the propeller 32 is closer to the tip end of the paddle 321 .
  • the paddle 321 is provided with a mounting hole 321d on a side surface of the motor 31.
  • the mounting hole 321d has a substantially cross section in a waist shape. It can be understood that the cross section of the mounting hole 321d may also be elliptical, polygonal or the like.
  • the connecting component 33 includes a limiting member 331, a locking member 332 and an elastic member 333.
  • the locking member 332 is located between the limiting member 331 and the elastic member 333
  • the elastic member 333 is located between the locking member 332 and the motor 31 .
  • the limiting member 331 includes a limiting flange 331a and a mounting boss 331b connected to the limiting flange 331a.
  • the limiting flange 331a and the mounting protrusion 331b protrude.
  • the direction is roughly vertical.
  • the limiting flange 331a has a substantially square plate shape. In other embodiments, the limiting flange 331a can be other suitable shapes.
  • a plurality of through holes 331c are defined in the limiting flange 331a, and the through holes 331c correspond to at least a part of the connecting holes 312e. In the present embodiment, the number of the through holes 331c is two, and thus the through holes 331c correspond to two of the connection holes 312e.
  • the shape of the mounting boss 331b is matched with the shape of the mounting hole 321d. After the mounting boss 331b is engaged with the mounting hole 321d, the propeller 32 cannot be opposite to the limiting member. 331 turns. A side surface of the mounting boss 331b facing the motor 31 is concavely formed with a recessed structure (not shown) adapted to the rotating shaft 312a.
  • the locking member 332 includes a latch 332a corresponding to the first locking block 321b and a connecting portion 332b connected to the latch 332a.
  • the latch 332a protrudes toward one side of the connecting portion 332b and is formed with a second locking block 332c adapted to the first locking block 321b, the second locking block 332c facing the center
  • the rotation axis of the motor 31 protrudes, and the second locking block 332c is formed with a second mating surface 332d that cooperates with the first mating surface 321c toward one side of the motor 31.
  • the inclination direction and inclination of the second mating surface 332d with respect to the rotation axis of the propeller 32 are the same as the inclination direction and inclination of the first mating surface 321c with respect to the optional center of the propeller 32, respectively.
  • the height of the second mating surface 332d relative to the surface of the connecting portion 332b is substantially equal to the height of the first locking block 321b along the rotation axis of the propeller 32.
  • the second mating surface 332d The height with respect to the surface of the connecting portion 332b is slightly higher than the height of the first locking block 321b along the rotation axis of the propeller 32.
  • a second alignment mark 332e corresponding to the first alignment mark 321a is formed on an end surface of the latch 332a away from the connecting portion 332b.
  • the second aligning identifier 332e is a circular hole. It can be understood that the second aligning identifier 332e may also be another type of identifier. For example, the second aligning identifier 332e may be a triangle. A hole, a square hole, an elliptical hole, a graphic symbol attached to the lock 332a, and the like. In addition, the second alignment identifier 332e may be the same as or different from the first alignment identifier 321a.
  • the connecting portion 332b is substantially annular, and a pressing piece 332f is formed on an inner side surface of the connecting portion 332b.
  • the number of the pressing pieces 332f is two. In other embodiments, the number of the pressing pieces 332f may be other suitable changes.
  • a protruding portion 332g (see FIGS. 5 and 7) is formed on one surface of the pressing piece 332f toward the motor 31, and both side surfaces of the protruding portion 332g are smooth curved surfaces.
  • the protruding portion 332g may also be directly formed on a side surface of the connecting portion 332b facing the motor 31, and thus the pressing piece 332f may be omitted.
  • the elastic member 333 is substantially in the form of a sheet and includes a connecting portion 333a and an elastic abutting piece 333b corresponding to the pressing piece 332f.
  • the connecting portion 333a defines a shaft hole 333c and a through hole 333d corresponding to at least a portion of the connecting hole 312e.
  • the number of the through holes 333d is two, and thus the through holes 333d correspond to two of the connection holes 312e.
  • the elastic abutting piece 333b protrudes toward the locking member 332 with respect to the surface of the connecting portion 333a, and the substantially central position of the elastic abutting piece 333b is bent to form a convex shape toward the locking member 332.
  • the convex portion 333e has a smooth curved surface on both sides of the convex portion 333e.
  • the elastic abutting piece 333b is integrally formed with the connecting portion 333a.
  • the elastic member 333 , the locking member 332 and the limiting member 331 are sequentially stacked on the connecting surface 312 c of the motor 31 , and the limiting member is assembled.
  • the through holes 331c of the 331 are respectively aligned with the corresponding through holes 333d of the elastic member 333 and the connecting hole 312e, and the rotating shaft 312a sequentially passes through the shaft hole 333c of the elastic member 333, the locking
  • the piece 332 is inserted into the recess of the limiting member 331.
  • the limiting member 331 and the elastic member 333 are fixed on the connecting surface 312c.
  • the limiting member 331 and the elastic member 333 are fixed to the connecting surface 312c by bolts 334.
  • the bolt 334 is screwed through the corresponding through hole 331c and the through hole 333d and the corresponding connecting hole 312e.
  • the locking member 332 is restrained between the limiting member 331 and the connecting surface 312c, and the locking member 332 is rotatable relative to the limiting member 331 and the rotor 312 around the rotating shaft 312a.
  • the rotation axis rotates.
  • the locking member 332 can elastically resist the elastic member 333 during the rotation.
  • the propeller 32 is connected to the limiting member 331.
  • the mounting post 331b is inserted into the mounting hole 321d of the propeller 32.
  • the first locking block 321b of the locking 332a is corresponding to the first locking block 321b.
  • the space between the propeller 32 and the blade 322 facing away from the propeller 32 extends along the rotational axis of the propeller 32 toward the tip end of the propeller 32.
  • the propeller 32 of the rotor assembly 30 after the above assembly is in an unlocked state.
  • the locking member 332 only needs to be rotated relative to the propeller 32 along the direction of rotation of the rotor assembly 30.
  • the second locking block 332c of the latch 332a and the first locking block 321b are engaged with each other. Specifically, the first mating surface 321c and the second mating surface 332d are aligned with each other and attached.
  • the first mating surface 321c and the second mating surface 332d are inclined with respect to the rotation axis of the propeller 32, and the tilting direction and the inclination are respectively the same, so that a better locking effect can be ensured;
  • the locking member 332 is elastically resisted by the elastic member 333.
  • the protruding portion 332g of the locking member 332 is located at the elastic member 333.
  • the convex portion 332g slides along the convex portion 333e and presses the convex portion 333e to deform the motor 31, the propeller 32
  • the protruding portion 332g slides to the other of the convex portion 333e Side. Since both the surfaces of the protruding portion 332g and the convex portion 333e are smooth curved surfaces, the smoothness of sliding of the locking member 332 can be ensured, and the sliding can be made to have a better hand feeling;
  • the convex portion 333e can apply a certain elastic force to the locking member 332, thereby making the locking member difficult to deliver, ensuring the locking effect.
  • whether the propeller 32 is locked in position according to the relative positions of the first alignment mark 321a and the second alignment mark 332e may be determined to prevent the locking from being considered.
  • the rotation is not enough to release.
  • the propeller 32 is locked in place.
  • FIG. 8 a perspective view of one or more of the clockwise revolving rotor assemblies 30 of the UAV 100 is shown.
  • the structure of the clockwise revolving rotor assembly 30 is substantially identical to the aforementioned counterclockwise revolving rotor assembly 30.
  • the first locking block 321b is disposed adjacent to the blade 322 that is directed clockwise, and the locking member 332 is rotationally locked relative to the propeller 32 to lock the propeller 32 in the clockwise direction.
  • the rotor assembly and the UAV are locked by a locking member that is rotatable relative to the rotor and the propeller such that the rotating structure of the propeller is separated from the locking structure, so the locking member is locked
  • the rotation of the propeller does not transmit torque to the propeller, which can effectively wear the propeller and ensure the safety of the rotor assembly.
  • the above method of locking and unlocking the propeller is relatively simple and quick, and is convenient to use.

Abstract

一种旋翼组件（30），包括电机（31）、螺旋桨（32）以及将所述螺旋桨（32）连接于所述电机（31）的连接组件（33）。所述电机（31）包括定子（311）以及能够相对于所述定子（311）转动的转子（312）。所述连接组件（33）包括设置于所述螺旋桨（32）与所述转子（312）之间且能够相对于所述转子（312）及所述螺旋桨（32）转动的锁紧件（332），所述锁紧件（332）通过相对于所述螺旋桨（32）的转动将所述螺旋桨（32）锁定于所述电机（31）上。本发明还涉及一种具有所述旋翼组件（30）的无人飞行器。

Description

旋翼组件及具有旋翼组件的无人飞行器 技术领域
本发明涉及无人飞行器领域，尤其涉及一种旋翼组件及具有该旋翼组件的无人飞行器。
背景技术
旋翼组件作为旋翼式无人飞行器的推进结构，其品质要求非常苛刻，不仅要能够在较高的转速下提供合适的推进力，而且又要保证高速旋转时的安全性，不会造成无人飞行器本身的损坏及/或无人飞行器对其他物体的损坏。
旋翼组件一般包括电机及螺旋桨，螺旋桨固定连接于所述电机转轴上，电机转轴在转动时带动所述螺旋桨转动以产生推进力。然而，现有的螺旋桨与电机之间的连接往往较为复杂，螺旋桨与电机之间也不能快速拆卸，造成拆装的困难及使用的不便；现有电机与螺旋桨可拆卸的旋翼组件会导致螺旋桨的磨损较为严重，长期使用使损坏甚至是射桨的风险，存在安全隐患。
发明内容
有鉴于此，有必要提供一种组装简单且能够保证使用安全的旋翼组件及具有所述旋翼组件的无人飞行器。
一种旋翼组件，包括电机、螺旋桨以及将所述螺旋桨连接于所述电机的连接组件。所述电机包括定子以及能够相对于所述定子转动的转子。所述连接组件包括设置于所述螺旋桨与所述转子之间且能够相对于所述转子及所述螺旋桨转动的锁紧件，所述锁紧件通过相对于所述螺旋桨的转动将所述螺旋桨锁定于所述电机上。
进一步地，所述锁紧件包括锁扣，所述螺旋桨上形成有与所述锁扣相配合的第一锁紧块，螺旋桨锁定时，所述锁扣与所述第一锁紧块相连接。
进一步地，所述锁扣与所述第一锁紧块相连的一端形成有与所述第一锁紧块相适配的第二锁紧块，所述第一锁紧件通过所述第二锁紧块与所述第一锁紧块相卡合锁定所述螺旋桨。
进一步地，所述第一锁紧块与所述第二锁紧相互结合表面为相对于所述螺旋桨的旋转轴心倾斜预定角度的斜面，所述表面远离所述旋转轴心的一侧更为远离所述电机。
进一步地，所述螺旋桨背离所述电机的一侧表面上形成有第一对位标识，所述锁扣上形成有第二对位标识，当所述锁紧件将所述螺旋桨锁定到位时，所述第一对位标识及所述第二对位标识位于所述螺旋桨的同一直径上。
进一步地，所述螺旋桨包括桨柄以及与桨柄固定连接的桨叶，所述第一锁紧块设置于所述桨柄上。
进一步地，所述桨叶的数量为两个且沿所述桨柄的同一直径方向固定于所述桨柄的两侧，所述第一锁紧块位于所述桨叶之间，且靠近其中一个桨叶并与另一个桨叶之间留有供锁扣通过的空余。
进一步地，所述转子包括转轴以及与所述转轴固定相连的连接部，所述锁紧件能够转动地设置与所述螺旋桨与所述连接部之间。
进一步地，所述连接组件包括限位件，所述限位件与所述螺旋桨相连并将所述锁紧件能够转动地限定于所述连接部上。
进一步地，所述限位件包括限位凸缘以及与所述限位凸缘相连的安装凸柱，所述限位凸缘固定于连接部上并限制所述锁紧件沿所述螺旋桨旋转轴心转动，所述安装凸柱与所述螺旋桨相连并且能够限制所述于所述限位件之间绕所述旋转轴心的相对转动。
进一步地，所述限位凸缘以及所述安装凸柱的凸出方向相互垂直。
进一步地，所述连接组件包括设置于所述锁紧件与所述电机之间的弹性件，所述弹性件固定于所述转子上并与所述锁紧弹性抵接。
进一步地，所述锁紧件包括连接部，所述连接部上形成有朝向所述电机的凸出部，所述弹性件上形成有朝向所述螺旋桨凸出的弹性凸部，所述弹性凸部弹性抵接于所述凸出部上，在所述锁紧件相对于所述螺旋桨及所述转子旋转使，所述凸出部能够沿所述弹性凸部运动至所述弹性凸部的不同侧。
进一步地，所述凸出部以及所述弹性凸部的两侧表面均为平滑的曲面。
进一步地，所述连接部为环形，其内侧面上凸出形成有抵压片，所述凸出部形成于所述抵压片上。
进一步地，所述弹性件包括连接部以及弹性抵接片，所述连接部固定于所述转子上，所述弹性抵接片相对于所述连接部的表面朝向所述锁紧件凸伸，所述弹性凸部为所述弹性抵接片弯折形成。
一种无人飞行器，包括至少一个旋翼组件。所述旋翼组件包括电机、螺旋桨以及将所述螺旋桨连接于所述电机的连接组件。所述电机包括定子以及能够相对于所述定子转动的转子。所述连接组件包括设置于所述螺旋桨与所述转子之间且能够相对于所述转子及所述螺旋桨转动的锁紧件，所述锁紧件通过相对于所述螺旋桨的转动将所述螺旋桨锁定于所述电机上。
进一步地，所述锁紧件包括锁扣，所述螺旋桨上形成有与所述锁扣相配合的第一锁紧块，螺旋桨锁定时，所述锁扣与所述第一锁紧块相连接。
进一步地，所述锁扣与所述第一锁紧块相连的一端形成有与所述第一锁紧块相适配的第二锁紧块，所述第一锁紧件通过所述第二锁紧块与所述第一锁紧块相卡合锁定所述螺旋桨。
进一步地，所述第一锁紧块与所述第二锁紧相互结合表面为相对于所述螺旋桨的旋转轴心倾斜预定角度的斜面，所述表面远离所述旋转轴心的一侧更为远离所述电机。
进一步地，所述螺旋桨背离所述电机的一侧表面上形成有第一对位标识，所述锁扣上形成有第二对位标识，当所述锁紧件将所述螺旋桨锁定到位时，所述第一对位标识及所述第二对位标识位于所述螺旋桨的同一直径上。
进一步地，所述螺旋桨包括桨柄以及与桨柄固定连接的桨叶，所述第一锁紧块设置于所述桨柄上。
进一步地，所述桨叶的数量为两个且沿所述桨柄的同一直径方向固定于所述桨柄的两侧，所述第一锁紧块位于所述桨叶之间，且靠近其中一个桨叶并与另一个桨叶之间留有供锁扣通过的空余。
进一步地，所述转子包括转轴以及与所述转轴固定相连的连接部，所述锁紧件能够转动地设置与所述螺旋桨与所述连接部之间。
进一步地，所述连接组件包括限位件，所述限位件与所述螺旋桨相连并将所述锁紧件能够转动地限定于所述连接部上。
进一步地，所述限位件包括限位凸缘以及与所述限位凸缘相连的安装凸柱，所述限位凸缘固定于连接部上并限制所述锁紧件沿所述螺旋桨旋转轴心转动，所述安装凸柱与所述螺旋桨相连并且能够限制所述于所述限位件之间绕所述旋转轴心的相对转动。
进一步地，所述限位凸缘以及所述安装凸柱的凸出方向相互垂直。
进一步地，所述连接组件包括设置于所述锁紧件与所述电机之间的弹性件，所述弹性件固定于所述转子上并与所述锁紧弹性抵接。
进一步地，所述锁紧件包括连接部，所述连接部上形成有朝向所述电机的凸出部，所述弹性件上形成有朝向所述螺旋桨凸出的弹性凸部，所述弹性凸部弹性抵接于所述凸出部上，在所述锁紧件相对于所述螺旋桨及所述转子旋转使，所述凸出部能够沿所述弹性凸部运动至所述弹性凸部的不同侧。
进一步地，所述凸出部以及所述弹性凸部的两侧表面均为平滑的曲面。
进一步地，所述连接部为环形，其内侧面上凸出形成有抵压片，所述凸出部形成于所述抵压片上。
进一步地，所述弹性件包括连接部以及弹性抵接片，所述连接部固定于所述转子上，所述弹性抵接片相对于所述连接部的表面朝向所述锁紧件凸伸，所述弹性凸部为所述弹性抵接片弯折形成。
进一步地，所述无人飞行器还包括机身以及机臂以所述机臂连接于所述机，所述旋翼组件通过所述机臂分布于所述机身周围。
进一步地，所述机臂包括一个主臂以及一个支臂，所述主臂的一端连接所述机身，另一端连接所述支臂，所述旋翼组件位于所述支臂的末端。
进一步地，所述旋翼组件的数量为四个，四个所述旋翼组件分布于所述机身周围的矩形区域内，相邻的所述旋翼组件在工作时的旋向不同。
一种无人飞行器，包括至少一个旋翼组件。所述旋翼组件包括电机、螺旋桨以及将所述螺旋桨连接于所述电机的连接组件。所述电机包括定子以及能够相对于所述定子转动的转子。所述连接组件包括设置于所述螺旋桨与所述转子之间且能够相对于所述转子及所述螺旋桨转动的锁紧件，所述锁紧件通过相对于所述螺旋桨的转动将所述螺旋桨锁定于所述电机上。所述锁紧件锁紧所述螺旋桨时相对螺旋桨的转向与所述螺旋桨工作时的旋向相同。
进一步地，所述锁紧件包括锁扣，所述螺旋桨上形成有与所述锁扣相配合的第一锁紧块，螺旋桨锁定时，所述锁扣与所述第一锁紧块相连接。
进一步地，所述锁扣与所述第一锁紧块相连的一端形成有与所述第一锁紧块相适配的第二锁紧块，所述第一锁紧件通过所述第二锁紧块与所述第一锁紧块相卡合锁定所述螺旋桨。
进一步地，所述第一锁紧块与所述第二锁紧相互结合表面为相对于所述螺旋桨的旋转轴心倾斜预定角度的斜面，所述表面远离所述旋转轴心的一侧更为远离所述电机。
进一步地，所述螺旋桨背离所述电机的一侧表面上形成有第一对位标识，所述锁扣上形成有第二对位标识，当所述锁紧件将所述螺旋桨锁定到位时，所述第一对位标识及所述第二对位标识位于所述螺旋桨的同一直径上。
进一步地，所述螺旋桨包括桨柄以及与桨柄固定连接的桨叶，所述第一锁紧块设置于所述桨柄上。
进一步地，所述桨叶的数量为两个且沿所述桨柄的同一直径方向固定于所述桨柄的两侧，所述第一锁紧块位于所述桨叶之间，且靠近其中一个桨叶并与另一个桨叶之间留有供锁扣通过的空余。
进一步地，所述转子包括转轴以及与所述转轴固定相连的连接部，所述锁紧件能够转动地设置与所述螺旋桨与所述连接部之间。
进一步地，所述连接组件包括限位件，所述限位件与所述螺旋桨相连并将所述锁紧件能够转动地限定于所述连接部上。
进一步地，所述限位件包括限位凸缘以及与所述限位凸缘相连的安装凸柱，所述限位凸缘固定于连接部上并限制所述锁紧件沿所述螺旋桨旋转轴心转动，所述安装凸柱与所述螺旋桨相连并且能够限制所述于所述限位件之间绕所述旋转轴心的相对转动。
进一步地，所述限位凸缘以及所述安装凸柱的凸出方向相互垂直。
进一步地，所述连接组件包括设置于所述锁紧件与所述电机之间的弹性件，所述弹性件固定于所述转子上并与所述锁紧弹性抵接。
进一步地，所述锁紧件包括连接部，所述连接部上形成有朝向所述电机的凸出部，所述弹性件上形成有朝向所述螺旋桨凸出的弹性凸部，所述弹性凸部弹性抵接于所述凸出部上，在所述锁紧件相对于所述螺旋桨及所述转子旋转使，所述凸出部能够沿所述弹性凸部运动至所述弹性凸部的不同侧。
进一步地，所述凸出部以及所述弹性凸部的两侧表面均为平滑的曲面。
进一步地，所述连接部为环形，其内侧面上凸出形成有抵压片，所述凸出部形成于所述抵压片上。
进一步地，所述弹性件包括连接部以及弹性抵接片，所述连接部固定于所述转子上，所述弹性抵接片相对于所述连接部的表面朝向所述锁紧件凸伸，所述弹性凸部为所述弹性抵接片弯折形成。
进一步地，所述无人飞行器还包括机身以及机臂以所述机臂连接于所述机，所述旋翼组件通过所述机臂分布于所述机身周围。
进一步地，所述机臂包括一个主臂以及一个支臂，所述主臂的一端连接所述机身，另一端连接所述支臂，所述旋翼组件位于所述支臂的末端。
进一步地，所述旋翼组件的数量为四个，四个所述旋翼组件分布于所述机身周围的矩形区域内，相邻的所述旋翼组件在工作时的旋向不同。
相对于现有技术，所述的旋翼组件及无人飞行器通过能够相对于所述转子及所述螺旋桨转动的锁紧件进行锁紧，使得所述螺旋桨的转动结构与锁紧结构分开，因此所述锁紧件在锁紧所述螺旋桨的同时不会将扭矩传递给所述螺旋桨，能够有效将对螺旋桨的磨损，保证旋翼组件的使用安全。此外，上述对螺旋桨进行锁定以及解除锁定的方式较为简单快捷，使用方便。
 附图说明
图1是本发明一实施方式的无人飞行器的立体图。
图2是图1的无人飞行器的其中一个旋向的旋翼组件的分解图。
图3是图2的旋翼组件的螺旋桨的仰视图。
图4是图2的旋翼组件组装完成后的立体图，其中螺旋桨处于未锁定状态。
图5是图4的旋翼组件的部分结构的立体剖视图。
图6是图4的旋翼组件处于锁定状态的立体图。
图7是图6的旋翼组件沿的部分结构的立体剖视图。
图8是图1的无人飞行器的另一个旋向的旋翼组件的立体图，其中螺旋桨处于锁定状态。
主要元件符号说明
无人飞行器 100
机身 10
外壳 11
收容空间 101
机臂 20
主臂 21
支臂 22
旋翼组件 30
电机 31
定子 311
转子 312
转轴 312a
连接部 312b
连接面 312c
侧面 312d
连接孔 312e
螺旋桨 32
桨柄 321
第一对位标识 321a
第一锁紧块 321b
第一配合面 321c
安装孔 321d
桨叶 322
连接组件 33
限位件 331
限位凸缘 331a
安装凸柱 331b
通孔 331c
锁紧件 332
锁扣 332a
连接部 332b
第二锁紧块 332c
第二配合面 332d
第二对位标识 332e
抵压片 332f
凸出部 332g
弹性件 333
连接部 333a
弹性抵接片 333b
轴孔 333c
通孔 333d
凸部 333e
拍摄设备 200
云台 300
如下具体实施方式将结合上述附图进一步说明本发明。
具体实施方式
请参阅图1，本发明实施方式的无人飞行器100为旋翼式无人飞行器，所述无人飞行器100能够在空中飞行、悬停以执行特定的任务，例如，飞行、追踪、监视、勘探、搜救、播种、喷洒农药、灭火、航拍等。所述无人飞行器100上可以搭载预定的功能模块，例如，传感器、拍摄设备、药箱等，以实现特定的功能。本实施方式中，所述无人飞行器100上搭载有拍摄设备200，使得所述无人飞行器100实现航拍功能，所述拍摄设备200通过云台300连接于所述无人飞行器100上，所述云台300可以调节所述拍摄设备200的拍摄方向及/或俯仰角度并且能够为所述拍摄设备200的提供减震功能。
本发明实施方式所述的无人飞行器100包括机身10、机臂20以及旋翼组件30。所述机臂20连接于所述机身10，所述旋翼组件30通过所述机臂20分布于所述机身10周围。本实施方式中，所述无人飞行器100为四旋翼无人飞行器，因此所述旋翼组件30的数量为四个，四个所述旋翼组件30分布于所述机身10周围的矩形区域内，且每一个所述旋翼组件30位于所述矩形一个顶点上。依据空气动力学的原理，为避免所述旋翼组件30在转动时产生扰流，相邻的所述旋翼组件30在工作时的旋向不同，相对的所述旋翼组件30的旋向相同。本实施方式中，其中一对相对的旋翼组件30的旋向为逆时针方向（A方向），另外一对相对的旋翼组件30的旋向为顺时针方向（B方向）。
当然，依据不同的需求，所述旋翼组件30的数量作合适的变化，例如所述旋翼组件30的数量可以为两个、三个、六个、八个、十六个等，甚至，所述旋翼组件30的数量可以仅为一个。
所述机身10为所述无人飞行器100的承载件，所述机身10上或者内部可以承载传感器、电路板、处理器、通信模块及电池等元件。本实施方式中，所述机身10包括外壳11，所述外壳11内部形成有收容上述元件的收容空间101。所述外壳11呈流线型，可以减小飞行时的空气阻力。在其他的实施方式，所述外壳11可以为其他形状，例如多边形、圆形、椭圆形等。可以理解，所述外壳11也可以省略，而只以支架搭接形成所述机身10。
所述机臂20用于支撑所述旋翼组件30并使所述旋翼组件30以预定样式分布于所述机身10周围。本实施方式中，所述机臂20的数量为两个，每一个机臂20支撑两个所述旋翼组件30。每一个所述机臂20包括一个主臂21以及一个支臂22，所述主臂21的一端连接所述机身10，另一端连接所述支臂22，所述主臂21以及所述支臂22相互呈“T”形连接。每一个所述机臂20所对应的两个所述旋翼组件30分别设置于对应的所述支臂22的两端。
在其他的实施方式中，所述机臂20的数量与所述旋翼组件30的数量相同，即每一个所述机臂20支撑一个所述旋翼组件30，此时，所述支臂22可以省略，而直接将所述旋翼组件30设置于所述主臂21的末端。
在另一其他实施方式中，所述机臂20可以省略，此时，所述旋翼组件30可以直接设置于所述机身10上。
在另一其他实施方式中，所述机臂20也可以为从所述机身10上延伸出的支撑臂，多个所述支撑臂从所述机身10周边延伸且与所述机身10固定连接或一体成型。所述支撑臂的数量与所述旋翼组件30的数量相同，即每一个所述支撑臂支撑一个所述旋翼组件30。
请参阅图2，为所述无人飞行器100的其中一个逆时针旋向的旋翼组件30的分解图。所述旋翼组件30包括电机31、螺旋桨32及连接组件33。所述连接组件电机31以及所述螺旋桨32能够通过所述连接组件33相互可拆卸地连接。
所述电机31包括定子311以及可相对于所述定子311转动的转子312。所述转子312能够与所述机臂20固定连接。所述转子312包括转轴312a以及与所述转轴312a固定相连的连接部312b。所述转轴312a的中心轴与所述转子312的旋转轴线相重合。所述连接部312b位于所述转轴312a的周围。所述连接部312b包括一个朝向所述螺旋桨32的连接面312c以及位于所述连接面312c周侧的侧面312d。所述连接面312c的中心位置固定连接所述转轴312a。所述连接面312c上开设有多个连接孔312e。本实施方式中，所述连接孔312e为螺纹孔，且所述连接孔312e的数量为四个。当然，所述连接孔312e的数量可以依据不同的需求可作其他合适的变化，例如，两个、三个、五个以及六个等。
所述转轴312a自所述连接面312c朝向所述螺旋桨32伸出预定距离。本实施方式中，所述转轴312a具有多个不同直径的部分。
本实施方式中，所述电机31可以为无刷电机、有刷电机等任意合适类型的电机。
所述螺旋桨32包括桨柄321以及与桨柄321固定连接的桨叶322。所述桨叶322为逆时针旋向桨叶，即，所述桨叶322逆时针方向可以为所述无人飞行器100提供推进力。本实施方式中，所述桨叶322的数量为两个且沿所述桨柄321的同一直径方向固定于所述桨柄321的两侧。
所述桨柄321大致呈圆柱状，所述桨柄321的顶面形成有第一对位标识321a，所述桨柄321的侧面形成有第一锁紧块321b。本实施方式中，所述第一对位标识321a为圆形孔，可以理解，所述第一对位标识321a也可以为其他形式的标识，例如，所述第一对位标识321a可以为三角形孔、方形孔、椭圆形孔、贴于所述桨柄321上图形符号等等。本实施方式中，所述第一锁紧块321b的数量为两个，所述第一锁紧块321b分别位于所述桨柄两侧，且均位于所述桨叶322之间的所述桨柄321的侧面上。所述第一锁紧块321b凸出于所述桨柄321的侧面并沿所述桨柄321的周向延伸一定长度。所述第一锁紧块321b靠近所述螺旋桨32旋向所指向的桨叶322设置，所述第一锁紧块321b沿所述桨柄321的周向的长度小于处于所述桨叶322之间的所述桨柄321的侧面的周向长度，使得所述第一锁紧块321b与所述螺旋桨32旋向所背向的桨叶322之间有一定空余。所述第一锁紧块321b背离所述电机31的一侧形成有第一配合面321c，所述第一配合面321c为相对于所述螺旋桨32的旋转轴线倾斜一定角度的斜面，使得所述第一配合面321c远离所述螺旋桨32的旋转轴线的一侧更为靠近所述桨柄321的顶端。
请同时参阅图3，所述桨柄321朝向所述电机31的一侧表面上开设有安装孔321d。本实施方式中，所述安装孔321d的横截面大致呈腰形。可以理解，所述安装孔321d的横截面也可以为椭圆形、多边形等其他形状。
所述连接组件33包括限位件331、锁紧件332以及弹性件333。所述锁紧件332位于所述限位件331与所述弹性件333之间，所述弹性件333位于所述锁紧件332与所述电机31之间。
所述限位件331包括限位凸缘331a以及与所述限位凸缘331a相连的安装凸柱331b，本实施方式中，所述限位凸缘331a以及所述安装凸柱331b的凸出方向大致垂直。所述限位凸缘331a大致呈方形板状。在其他的实施方式中，所述限位凸缘331a可以为其他合适的形状。所述限位凸缘331a上开设多个通孔331c，所述通孔331c与至少部分所述连接孔312e相对应。本实施方式中，所述通孔331c的数量为两个，因此所述通孔331c与所述连接孔312e的中的两个相对应。所述安装凸柱331b的形状与所述安装孔321d的形状相适配，所述安装凸柱331b的与所述安装孔321d相配合后，所述螺旋桨32不能够相对于所述限位件331转动。所述安装凸柱331b的朝向所述电机31的一侧表面内凹形成与所述转轴312a相适配的凹陷结构（图未示）。
所述锁紧件332包括对应于所述第一锁紧块321b的锁扣332a以及与所述锁扣332a相连的连接部332b。所述锁扣332a向所述连接部332b的一侧凸伸并且末端形成有与所述第一锁紧块321b相适配的第二锁紧块332c，所述第二锁紧块332c朝向所述电机31的旋转轴线突出，所述第二锁紧块332c朝向所述电机31的一侧形成有与所述第一配合面321c相配合的第二配合面332d。所述第二配合面332d相对于所述螺旋桨32的旋转轴线的倾斜方向与倾斜度分别与所述第一配合面321c相对于所述螺旋桨32的选装中心的倾斜方向与倾斜度相同。所述第二配合面332d相对于所述连接部332b的表面的高度与所述第一锁紧块321b沿所述螺旋桨32的旋转轴线的高度大致相当，优选地，所述第二配合面332d相对于所述连接部332b的表面的高度略高于所述第一锁紧块321b沿所述螺旋桨32的旋转轴线的高度。
所述锁扣332a远离所述连接部332b的一端表面形成有一个对应所述第一对位标识321a的第二对位标识332e。本实施方式中，所述第二对位标识332e为圆形孔，可以理解，所述第二对位标识332e也可以为其他形式的标识，例如，所述第二对位标识332e可以为三角形孔、方形孔、椭圆形孔、贴于所述锁扣332a上图形符号等等。此外，所述第二对位标识332e可以与所述第一对位标识321a相同或者不同。
所述连接部332b大致呈环状，所述连接部332b的内侧面上凸出形成有抵压片332f。本实施方式中，所述抵压片332f的数量为两个。其他的实施方式中，所述抵压片332f的数量可以作其他合适的变化。所述抵压片332f朝向所述电机31的一侧表面形成有凸出部332g（请参阅图5及图7），所述凸出部332g的两侧表面为平滑的曲面。
可以理解，所述凸出部332g也可以直接形成于所述连接部332b朝向所述电机31的一侧表面上，因而所述抵压片332f可以省略。
所述弹性件333大致为片状，包括连接部333a以及与所述抵压片332f相对应的弹性抵接片333b。所述连接部333a开设有轴孔333c以及至少部分所述连接孔312e相对应的通孔333d。本实施方式中，所述通孔333d的数量为两个，因此所述通孔333d与所述连接孔312e中的两个相对应。所述弹性抵接片333b相对于所述连接部333a的表面朝向所述锁紧件332凸伸，所述弹性抵接片333b的大致中部位置弯折形成朝向所述锁紧件332凸出的凸部333e，所述凸部333e两侧的表面为平滑的曲面。且本实施方式中，所述弹性抵接片333b与所述连接部333a为一体成型。
请参阅图2至图7，组装时，所述弹性件333、所述锁紧件332以及所述限位件331依序叠置于所述电机31的连接面312c上，所述限位件331的通孔331c分别与对应的所述弹性件333的通孔333d以及所述连接孔312e对准，所述转轴312a依次穿过所述弹性件333的所述轴孔333c、所述锁紧件332并插入所述限位件331的凹陷内。所述限位件331以及所述弹性件333固定于所述连接面312c上，本实施方式中，所述限位件331以及所述弹性件333通过螺栓334固定于所述连接面312c上，所述螺栓334穿过对应的所述通孔331c及通孔333d与对应的所述连接孔312e相螺接。所述锁紧件332被限制在所述限位件331与所述连接面312c之间，所述锁紧件332能够相对于所述限位件331以及所述转子312绕所述转轴312a的旋转轴心转动。所述锁紧件332转动过程中能够与所述弹性件333弹性抵持。所述螺旋桨32连接于所述限位件331上，所述安装凸柱331b插入所述螺旋桨32的安装孔321d内，所述锁扣332a的自对应的所述第一锁紧块321b与所述螺旋桨32旋向所背向的桨叶322之间的空余沿所述螺旋桨32的旋转轴心朝所述螺旋桨32的顶端延伸。
以上组装完成后的旋翼组件30的螺旋桨32位于未锁定状态，如欲锁定所述螺旋桨32，只需将所述锁紧件332沿所述旋翼组件30的旋向相对于所述螺旋桨32转动，使所述锁扣332a的第二锁紧块332c与所述第一锁紧块321b相互卡合，具体地，使所述第一配合面321c与所述第二配合面332d相互对准并贴合，由于所述第一配合面321c与第二配合面332d相对于所述螺旋桨32的旋转轴线倾斜且倾斜方向与倾斜度分别相同，因此能够保更好的锁定效果；在所述锁紧件332转动的过程中，所述锁紧件332与弹性件333弹性抵持，具体地，在所述螺旋桨32未锁定时，所述锁紧件332的凸出部332g位于所述弹性件333的凸部333e的一侧，在所述锁紧件332转动的过程中，所述凸出部332g沿所述凸部333e滑动并压迫所述凸部333e向所述电机31变形，所述螺旋桨32被锁定后，所述凸出部332g滑动至所述凸部333e的另外一侧。由于所述凸出部332g以及所述凸部333e的两侧表面均为平滑的曲面，因此可以保证所述锁紧件332的滑动的平顺性，且能够使滑动具有更好的手感；而且，在所述螺旋桨32被锁定后，所述凸部333e能够对所述锁紧件332施以一定弹性作用力，因此使得所述锁紧件不易送件，确保了锁紧的效果。
在锁紧所述螺旋桨32的过程中，可以依据所述第一对位标识321a以及所述第二对位标识332e的相对位置判断所述螺旋桨32是否锁紧到位，以防止所述锁紧以为旋转不到为而松脱。本实施方式中，当所述第一对位标识321a以及所述第二对位标识332e位于所述螺旋桨32的同一直径上时，所述螺旋桨32即锁紧到位。
请参阅图8，所示为为所述无人飞行器100的其中一个顺时针旋向的旋翼组件30的立体图。所述顺时针旋向的旋翼组件30的结构与前述的逆时针旋向的旋翼组件30基本相同。所述第一锁紧块321b靠近顺时针旋向所指向的所述桨叶322设置，所述锁紧件332沿所述顺时针旋向相对于所述螺旋桨32转动锁定所述螺旋桨32。
所述的旋翼组件及无人飞行器通过能够相对于所述转子及所述螺旋桨转动的锁紧件进行锁紧，使得所述螺旋桨的转动结构与锁紧结构分开，因此所述锁紧件在锁紧所述螺旋桨的同时不会将扭矩传递给所述螺旋桨，能够有效将对螺旋桨的磨损，保证旋翼组件的使用安全。此外，上述对螺旋桨进行锁定以及解除锁定的方式较为简单快捷，使用方便。
另外，采用将所述锁紧件相对于所述转子及螺旋桨沿所述旋翼组件的旋向旋转紧固，能够达成螺旋桨旋转时自紧的效果，进而确保锁紧的可靠性。
可以理解的是，本领域技术人员还可在本发明精神内做其它变化等用在本发明的设计，只要其不偏离本发明的技术效果均可。这些依据本发明精神所做的变化，都应包含在本发明所要求保护的范围之内。

Claims (54)

  1. 一种旋翼组件，包括电机、螺旋桨以及将所述螺旋桨连接于所述电机的连接组件，所述电机包括定子以及能够相对于所述定子转动的转子，其特征在于：所述连接组件包括设置于所述螺旋桨与所述转子之间且能够相对于所述转子及所述螺旋桨转动的锁紧件，所述锁紧件通过相对于所述螺旋桨的转动将所述螺旋桨锁定于所述电机上。
  2. 如权利要求1所述的旋翼组件，其特征在于：所述锁紧件包括锁扣，所述螺旋桨上形成有与所述锁扣相配合的第一锁紧块，螺旋桨锁定时，所述锁扣与所述第一锁紧块相连接。
  3. 如权利要求2所述的旋翼组件，其特征在于：所述锁扣与所述第一锁紧块相连的一端形成有与所述第一锁紧块相适配的第二锁紧块，所述第一锁紧件通过所述第二锁紧块与所述第一锁紧块相卡合锁定所述螺旋桨。
  4. 如权利要求3所述的旋翼组件，其特征在于：所述第一锁紧块与所述第二锁紧相互结合表面为相对于所述螺旋桨的旋转轴心倾斜预定角度的斜面，所述表面远离所述旋转轴心的一侧更为远离所述电机。
  5. 如权利要求2所述的旋翼组件，其特征在于：所述螺旋桨背离所述电机的一侧表面上形成有第一对位标识，所述锁扣上形成有第二对位标识，当所述锁紧件将所述螺旋桨锁定到位时，所述第一对位标识及所述第二对位标识位于所述螺旋桨的同一直径上。
  6. 如权利要求2所述的旋翼组件，其特征在于：所述螺旋桨包括桨柄以及与桨柄固定连接的桨叶，所述第一锁紧块设置于所述桨柄上。
  7. 如权利要求2所述的旋翼组件，其特征在于：所述桨叶的数量为两个且沿所述桨柄的同一直径方向固定于所述桨柄的两侧，所述第一锁紧块位于所述桨叶之间，且靠近其中一个桨叶并与另一个桨叶之间留有供锁扣通过的空余。
  8. 如权利要求1所述的旋翼组件，其特征在于：所述转子包括转轴以及与所述转轴固定相连的连接部，所述锁紧件能够转动地设置与所述螺旋桨与所述连接部之间。
  9. 如权利要求8所述的旋翼组件，其特征在于：所述连接组件包括限位件，所述限位件与所述螺旋桨相连并将所述锁紧件能够转动地限定于所述连接部上。
  10. 如权利要求9所述的旋翼组件，其特征在于：所述限位件包括限位凸缘以及与所述限位凸缘相连的安装凸柱，所述限位凸缘固定于连接部上并限制所述锁紧件沿所述螺旋桨旋转轴心转动，所述安装凸柱与所述螺旋桨相连并且能够限制所述于所述限位件之间绕所述旋转轴心的相对转动。
  11. 如权利要求10所述的旋翼组件，其特征在于：所述限位凸缘以及所述安装凸柱的凸出方向相互垂直。
  12. 如权利要求2所述的旋翼组件，其特征在于：所述连接组件包括设置于所述锁紧件与所述电机之间的弹性件，所述弹性件固定于所述转子上并与所述锁紧弹性抵接。
  13. 如权利要求12所述的旋翼组件，其特征在于：所述锁紧件包括连接部，所述连接部上形成有朝向所述电机的凸出部，所述弹性件上形成有朝向所述螺旋桨凸出的弹性凸部，所述弹性凸部弹性抵接于所述凸出部上，在所述锁紧件相对于所述螺旋桨及所述转子旋转使，所述凸出部能够沿所述弹性凸部运动至所述弹性凸部的不同侧。
  14. 如权利要求13所述的旋翼组件，其特征在于：所述凸出部以及所述弹性凸部的两侧表面均为平滑的曲面。
  15. 如权利要求13所述的旋翼组件，其特征在于：所述连接部为环形，其内侧面上凸出形成有抵压片，所述凸出部形成于所述抵压片上。
  16. 如权利要求13所述的旋翼组件，其特征在于：所述弹性件包括连接部以及弹性抵接片，所述连接部固定于所述转子上，所述弹性抵接片相对于所述连接部的表面朝向所述锁紧件凸伸，所述弹性凸部为所述弹性抵接片弯折形成。
  17. 一种无人飞行器，包括至少一个旋翼组件，所述旋翼组件包括电机、螺旋桨以及将所述螺旋桨连接于所述电机的连接组件，所述电机包括定子以及能够相对于所述定子转动的转子，其特征在于：所述连接组件包括设置于所述螺旋桨与所述转子之间且能够相对于所述转子及所述螺旋桨转动的锁紧件，所述锁紧件通过相对于所述螺旋桨的转动将所述螺旋桨锁定于所述电机上。
  18. 如权利要求17所述的无人飞行器，其特征在于：所述锁紧件包括锁扣，所述螺旋桨上形成有与所述锁扣相配合的第一锁紧块，螺旋桨锁定时，所述锁扣与所述第一锁紧块相连接。
  19. 如权利要求18所述的无人飞行器，其特征在于：所述锁扣与所述第一锁紧块相连的一端形成有与所述第一锁紧块相适配的第二锁紧块，所述第一锁紧件通过所述第二锁紧块与所述第一锁紧块相卡合锁定所述螺旋桨。
  20. 如权利要求19所述的无人飞行器，其特征在于：所述第一锁紧块与所述第二锁紧相互结合表面为相对于所述螺旋桨的旋转轴心倾斜预定角度的斜面，所述表面远离所述旋转轴心的一侧更为远离所述电机。
  21. 如权利要求18所述的无人飞行器，其特征在于：所述螺旋桨背离所述电机的一侧表面上形成有第一对位标识，所述锁扣上形成有第二对位标识，当所述锁紧件将所述螺旋桨锁定到位时，所述第一对位标识及所述第二对位标识位于所述螺旋桨的同一直径上。
  22. 如权利要求18所述的无人飞行器，其特征在于：所述螺旋桨包括桨柄以及与桨柄固定连接的桨叶，所述第一锁紧块设置于所述桨柄上。
  23. 如权利要求18所述的无人飞行器，其特征在于：所述桨叶的数量为两个且沿所述桨柄的同一直径方向固定于所述桨柄的两侧，所述第一锁紧块位于所述桨叶之间，且靠近其中一个桨叶并与另一个桨叶之间留有供锁扣通过的空余。
  24. 如权利要求17所述的无人飞行器，其特征在于：所述转子包括转轴以及与所述转轴固定相连的连接部，所述锁紧件能够转动地设置与所述螺旋桨与所述连接部之间。
  25. 如权利要求24所述的无人飞行器，其特征在于：所述连接组件包括限位件，所述限位件与所述螺旋桨相连并将所述锁紧件能够转动地限定于所述连接部上。
  26. 如权利要求25所述的无人飞行器，其特征在于：所述限位件包括限位凸缘以及与所述限位凸缘相连的安装凸柱，所述限位凸缘固定于连接部上并限制所述锁紧件沿所述螺旋桨旋转轴心转动，所述安装凸柱与所述螺旋桨相连并且能够限制所述于所述限位件之间绕所述旋转轴心的相对转动。
  27. 如权利要求26所述的无人飞行器，其特征在于：所述限位凸缘以及所述安装凸柱的凸出方向相互垂直。
  28. 如权利要求18所述的无人飞行器，其特征在于：所述连接组件包括设置于所述锁紧件与所述电机之间的弹性件，所述弹性件固定于所述转子上并与所述锁紧弹性抵接。
  29. 如权利要求28所述的无人飞行器，其特征在于：所述锁紧件包括连接部，所述连接部上形成有朝向所述电机的凸出部，所述弹性件上形成有朝向所述螺旋桨凸出的弹性凸部，所述弹性凸部弹性抵接于所述凸出部上，在所述锁紧件相对于所述螺旋桨及所述转子旋转使，所述凸出部能够沿所述弹性凸部运动至所述弹性凸部的不同侧。
  30. 如权利要求29所述的无人飞行器，其特征在于：所述凸出部以及所述弹性凸部的两侧表面均为平滑的曲面。
  31. 如权利要求29所述的无人飞行器，其特征在于：所述连接部为环形，其内侧面上凸出形成有抵压片，所述凸出部形成于所述抵压片上。
  32. 如权利要求29所述的无人飞行器，其特征在于：所述弹性件包括连接部以及弹性抵接片，所述连接部固定于所述转子上，所述弹性抵接片相对于所述连接部的表面朝向所述锁紧件凸伸，所述弹性凸部为所述弹性抵接片弯折形成。
  33. 如权利要求17所述的无人飞行器，其特征在于：还包括机身以及机臂以所述机臂连接于所述机，所述旋翼组件通过所述机臂分布于所述机身周围。
  34. 如权利要求33所述的无人飞行器，其特征在于：所述机臂包括一个主臂以及一个支臂，所述主臂的一端连接所述机身，另一端连接所述支臂，所述旋翼组件位于所述支臂的末端。
  35. 如权利要求17所述的无人飞行器，其特征在于：所述旋翼组件的数量为四个，四个所述旋翼组件分布于所述机身周围的矩形区域内，相邻的所述旋翼组件在工作时的旋向不同。
  36. 一种无人飞行器，包括至少一个旋翼组件，所述旋翼组件包括电机、螺旋桨以及将所述螺旋桨连接于所述电机的连接组件，所述电机包括定子以及能够相对于所述定子转动的转子，其特征在于：所述连接组件包括设置于所述螺旋桨与所述转子之间且能够相对于所述转子及所述螺旋桨转动的锁紧件，所述锁紧件通过相对于所述螺旋桨的转动将所述螺旋桨锁定于所述电机上，所述锁紧件锁紧所述螺旋桨时相对螺旋桨的转向与所述螺旋桨工作时的旋向相同。
  37. 如权利要求36所述的无人飞行器，其特征在于：所述锁紧件包括锁扣，所述螺旋桨上形成有与所述锁扣相配合的第一锁紧块，螺旋桨锁定时，所述锁扣与所述第一锁紧块相连接。
  38. 如权利要求37所述的无人飞行器，其特征在于：所述锁扣与所述第一锁紧块相连的一端形成有与所述第一锁紧块相适配的第二锁紧块，所述第一锁紧件通过所述第二锁紧块与所述第一锁紧块相卡合锁定所述螺旋桨。
  39. 如权利要求38所述的无人飞行器，其特征在于：所述第一锁紧块与所述第二锁紧相互结合表面为相对于所述螺旋桨的旋转轴心倾斜预定角度的斜面，所述表面远离所述旋转轴心的一侧更为远离所述电机。
  40. 如权利要求37所述的无人飞行器，其特征在于：所述螺旋桨背离所述电机的一侧表面上形成有第一对位标识，所述锁扣上形成有第二对位标识，当所述锁紧件将所述螺旋桨锁定到位时，所述第一对位标识及所述第二对位标识位于所述螺旋桨的同一直径上。
  41. 如权利要求37所述的无人飞行器，其特征在于：所述螺旋桨包括桨柄以及与桨柄固定连接的桨叶，所述第一锁紧块设置于所述桨柄上。
  42. 如权利要求37所述的无人飞行器，其特征在于：所述桨叶的数量为两个且沿所述桨柄的同一直径方向固定于所述桨柄的两侧，所述第一锁紧块位于所述桨叶之间，且靠近其中一个桨叶并与另一个桨叶之间留有供锁扣通过的空余。
  43. 如权利要求36所述的无人飞行器，其特征在于：所述转子包括转轴以及与所述转轴固定相连的连接部，所述锁紧件能够动地设置与所述螺旋桨与所述连接部之间。
  44. 如权利要求43所述的无人飞行器，其特征在于：所述连接组件包括限位件，所述限位件与所述螺旋桨相连并将所述锁紧件能够转动地限定于所述连接部上。
  45. 如权利要求44所述的无人飞行器，其特征在于：所述限位件包括限位凸缘以及与所述限位凸缘相连的安装凸柱，所述限位凸缘固定于连接部上并限制所述锁紧件沿所述螺旋桨旋转轴心转动，所述安装凸柱与所述螺旋桨相连并且能够限制所述于所述限位件之间绕所述旋转轴心的相对转动。
  46. 如权利要求45所述的无人飞行器，其特征在于：所述限位凸缘以及所述安装凸柱的凸出方向相互垂直。
  47. 如权利要求37所述的无人飞行器，其特征在于：所述连接组件包括设置于所述锁紧件与所述电机之间的弹性件，所述弹性件固定于所述转子上并与所述锁紧弹性抵接。
  48. 如权利要求47所述的无人飞行器，其特征在于：所述锁紧件包括连接部，所述连接部上形成有朝向所述电机的凸出部，所述弹性件上形成有朝向所述螺旋桨凸出的弹性凸部，所述弹性凸部弹性抵接于所述凸出部上，在所述锁紧件相对于所述螺旋桨及所述转子旋转使，所述凸出部能够沿所述弹性凸部运动至所述弹性凸部的不同侧。
  49. 如权利要求48所述的无人飞行器，其特征在于：所述凸出部以及所述弹性凸部的两侧表面均为平滑的曲面。
  50. 如权利要求48所述的无人飞行器，其特征在于：所述连接部为环形，其内侧面上凸出形成有抵压片，所述凸出部形成于所述抵压片上。
  51. 如权利要求48所述的无人飞行器，其特征在于：所述弹性件包括连接部以及弹性抵接片，所述连接部固定于所述转子上，所述弹性抵接片相对于所述连接部的表面朝向所述锁紧件凸伸，所述弹性凸部为所述弹性抵接片弯折形成。
  52. 如权利要求36所述的无人飞行器，其特征在于：还包括机身以及机臂以所述机臂连接于所述机，所述旋翼组件通过所述机臂分布于所述机身周围。
  53. 如权利要求52所述的无人飞行器，其特征在于：所述机臂包括一个主臂以及一个支臂，所述主臂的一端连接所述机身，另一端连接所述支臂，所述旋翼组件位于所述支臂的末端。
  54. 如权利要求36所述的无人飞行器，其特征在于：所述旋翼组件的数量为四个，四个所述旋翼组件分布于所述机身周围的矩形区域内，相邻的所述旋翼组件在工作时的旋向不同。
PCT/CN2015/090771 2015-09-25 2015-09-25 旋翼组件及具有旋翼组件的无人飞行器 WO2017049607A1 (zh)

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