WO2017107128A1 - 快拆结构、多旋翼无人飞行器、组件及旋翼组件 - Google Patents

快拆结构、多旋翼无人飞行器、组件及旋翼组件 Download PDF

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Publication number
WO2017107128A1
WO2017107128A1 PCT/CN2015/098661 CN2015098661W WO2017107128A1 WO 2017107128 A1 WO2017107128 A1 WO 2017107128A1 CN 2015098661 W CN2015098661 W CN 2015098661W WO 2017107128 A1 WO2017107128 A1 WO 2017107128A1
Authority
WO
WIPO (PCT)
Prior art keywords
rotor
connector
assembly
fuselage
quick release
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/CN2015/098661
Other languages
English (en)
French (fr)
Inventor
袁博
吴振凯
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 CN201580003654.2A priority Critical patent/CN105939927B/zh
Priority to PCT/CN2015/098661 priority patent/WO2017107128A1/zh
Publication of WO2017107128A1 publication Critical patent/WO2017107128A1/zh
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/02—Gyroplanes
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
    • B64C1/061—Frames
    • B64C1/063—Folding or collapsing to reduce overall dimensions, e.g. foldable tail booms
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/30—Parts of fuselage relatively movable to reduce overall dimensions of aircraft
    • 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
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/10—Rotorcrafts

Definitions

  • the invention relates to a quick release structure, a multi-rotor unmanned aerial vehicle, a component and a rotor assembly.
  • the multi-rotor UAV includes an arm and a fuselage connected to the arm.
  • the connection between the arm of the existing multi-rotor UAV and the fuselage is mostly fixed, and a few adopt a quick release structure to rotate the multi-rotor.
  • the left and right arms of the UAV are connected to the fuselage.
  • the left and right arms and the fuselage are connected by the quick release structure, the left and right arms cannot be used interchangeably, so that the left and right arms that are quickly removed must be distinguished during storage and transportation to avoid installation errors, and it is not convenient to be on the scene when the fault occurs. service.
  • a multi-rotor unmanned aerial vehicle includes a fuselage, a rotor assembly, and a detachable quick release structure that connects the rotor assembly to the fuselage.
  • the quick release structure mechanically connects the rotor assembly to the airframe
  • the rotor assembly is electrically connected to the fuselage through the quick release structure; and the plurality of quick release structures correspondingly connect the plurality of the rotor assemblies to the machine
  • the connection positions of the body can be interchanged.
  • the quick release structure includes a joint and a mating portion detachably connected to the joint.
  • the rotor assembly When the rotor assembly is coupled to the fuselage, the rotor assembly is electrically connected to the fuselage through the joint and the mating portion.
  • one of the joint and the mating portion is disposed on the fuselage and electrically connected to the fuselage, and the other is disposed on the rotor assembly and electrically connected to the rotor assembly.
  • the joint includes a sleeve structure, and the sleeve structure is provided with a groove for receiving the fitting portion.
  • the shape and size of the groove are adapted to the shape and size of the fitting portion.
  • the joint further includes a lead assembly electrically connected to the body or the rotor assembly, the pin assembly being fixed on a bottom surface of the groove.
  • the pin component includes three pins, and the three pins are used for respectively electrically connecting the three-phase wires of the three-phase power supply.
  • the pin is made of a conductive material, and each of the pins is not electrically connected to each other.
  • the mating portion is provided with three connecting holes, and the three connecting holes are respectively used for electrically connecting three-phase lines of the three-phase power source.
  • the positions of the three pins are respectively corresponding to the positions of the three connection holes, and the three pins respectively penetrate the three connection holes, and the connector is electrically connected to the mating portion.
  • the number of the pin components is one or two.
  • the quick release structure further includes a connection structure, and the connection structure is connected to the joint or the joint portion.
  • the connecting structure comprises a fixing plate, and the quick release structure is connected to the rotor assembly through the fixing plate, and the joint or the fitting portion is fixed on the fixing plate.
  • the connecting structure includes a bolt passing through the fixing plate, and the quick release structure is connected to the body through the bolt.
  • the connecting structure includes a fixing portion and a detachable connecting member connected to the fixing portion, the fixing portion is coupled to the body, and the connecting member connects the rotor assembly to the fixing portion, the engaging member Resisting or disengaging from the fixing portion, the detachable structure is in a locked state or a detachable state.
  • the joint is disposed on the fixing portion, the body or the engaging member; the engaging portion is disposed on the engaging member or the fixing portion and the body.
  • the rotor assembly includes an arm coupled to the quick release structure, a motor fixedly coupled to the arm, and a propeller coupled to the motor, the motor for driving the propeller to rotate, thereby the multi-rotor unmanned aerial vehicle Provide flight power.
  • the arm includes a connecting arm and a supporting arm, one end of the connecting arm is fixedly connected to the supporting arm, and the other end is connected to the quick release structure; two ends of the supporting arm are respectively fixedly connected to the motor.
  • the number of the connecting arms is two, and the two connecting arms are fixed to the supporting arm at intervals.
  • One end of each connecting arm is fixedly connected to the supporting arm, and the other end is connected to the quick release structure.
  • a quick release structure for detachably attaching a rotor assembly to a fuselage.
  • the quick release structure connects the rotor assembly to the fuselage, the rotor assembly is electrically connected to the fuselage through the quick release structure; and the plurality of quick release structures correspondingly connect the plurality of the rotor assemblies to the fuselage
  • the connection locations are interchangeable.
  • the quick release structure includes a joint and a mating portion detachably connected to the joint.
  • the rotor assembly When the rotor assembly is coupled to the fuselage, the rotor assembly is electrically connected to the fuselage through the joint and the mating portion.
  • one of the joint and the mating portion is disposed on the fuselage and electrically connected to the fuselage, and the other is disposed on the rotor assembly and electrically connected to the rotor assembly.
  • the joint includes a sleeve structure, and the sleeve structure is provided with a groove for receiving the fitting portion.
  • the shape and size of the groove are adapted to the shape and size of the fitting portion.
  • the joint further includes a lead assembly electrically connected to the body or the rotor assembly, the pin assembly being fixed on a bottom surface of the groove.
  • the pin component includes three pins, and the three pins are used for respectively electrically connecting the three-phase wires of the three-phase power supply.
  • the pin is made of a conductive material, and each of the pins is not electrically connected to each other.
  • the mating portion is provided with three connecting holes, and the three connecting holes are respectively used for electrically connecting three-phase lines of the three-phase power source.
  • the positions of the three pins are respectively corresponding to the positions of the three connection holes, and the three pins respectively penetrate the three connection holes to electrically connect the connector with the mating portion.
  • the number of the pin components is one or two.
  • the quick release structure further includes a connection structure, and the connection structure is connected to the joint or the joint portion.
  • the connecting structure comprises a fixing plate, and the quick release structure is connected to the rotor assembly through the fixing plate, and the joint or the fitting portion is fixed on the fixing plate.
  • the connecting structure includes a bolt passing through the fixing plate, and the quick release structure is connected to the body through the bolt.
  • the connecting structure includes a fixing portion and a detachable connecting member connected to the fixing portion, the fixing portion is coupled to the body, and the connecting member connects the rotor assembly to the fixing portion, the engaging member Resisting or disengaging from the fixing portion, the detachable structure is in a locked state or a detachable state.
  • the joint is disposed on the fixing portion, the body or the engaging member; the corresponding engaging portion is disposed on the engaging member or the fixing portion and the body.
  • a multi-rotor unmanned aerial vehicle comprising:
  • each of the quick release structures includes a rotor connector and a fuselage connector detachably coupled to the rotor connector, the rotor connector being fixed to the rotor a component, the fuselage connector is fixed to the body;
  • the rotor connector is mechanically and electrically coupled to the fuselage connector; and when the rotor assembly is mounted to the fuselage through the fuselage connector and the rotor connector, the fuselage connector is coupled to the rotor Electrical connection.
  • the fuse link can still be engaged with the fuselage connector such that the rotor assembly is mounted to the fuselage at the predetermined angle.
  • the preset angle is 180 degrees, so that the rotor assembly is installed upside down.
  • each of the rotor assemblies includes a boom and a plurality of power units mounted on the arm.
  • each of the power units includes a propeller and a motor that drives the rotation of the propeller.
  • the shape of the arm includes at least one of the following: T type, V type, U type, Y type, and X type.
  • the arm includes a plurality of connecting ends, one of which is for connecting the rotor connector, and the other connecting end is for mounting the power device.
  • the arm is a hollow structure, and the wire is electrically connected to the rotor connector through the inside of the arm.
  • the rotor connector includes a mechanical connection portion and a mechanical connection portion
  • the body connector includes a mechanical mating portion for coupling with the mechanical connection portion, and an electrical mating portion for coupling with the electrical connection portion .
  • the rotor connector and the fuselage connector are both conductive members such that the rotor connector and the body connector are mechanically coupled while being mechanically coupled.
  • the rotor connector is provided with at least one of the following: an insert, an insertion slot, an insertion hole, a snap member, a fastening member, a snap groove, a snap hole, a threaded connector, a threaded hole, and a sleeve.
  • the body connector is provided with at least one of the following: an insert, an insertion slot, an insertion hole, a snap member, a fastening component, an engaging groove, a snap hole, a threaded connector, a threaded hole, a sleeve .
  • the multi-rotor UAV is a quadrotor unmanned aerial vehicle, a six-rotor unmanned aerial vehicle, an eight-rotor unmanned aerial vehicle or a ten-rotor unmanned aerial vehicle.
  • An assembly for assembling a multi-rotor unmanned aerial vehicle comprising:
  • each of the rotor assemblies being provided with a rotor connector for detachable connection with the fuselage connector; the rotor connector and the fuselage connector being mechanically coupled and electrically coupled;
  • the rotor assembly when the rotor assembly is assembled with the fuselage, the rotor assembly is mounted to the fuselage through the fuselage connector and the rotor connector, and the fuselage connector is electrically connected to the rotor connector.
  • one of the rotor assemblies of the rotor assembly can be mated with another fuselage connector corresponding to the rotor assembly such that the connection positions of the two rotor assemblies with the fuselage are interchangeable.
  • the two rotor assemblies have the same structure.
  • the rotor link after the rotor link is rotated by a predetermined angle about the axial direction of the rotor assembly, it can still cooperate with the fuselage connecting member, so that the rotor assembly is mounted at the preset angle to be mounted on the fuselage.
  • the preset angle is 180 degrees, so that the rotor assembly is installed upside down.
  • each of the rotor assemblies includes a boom and a plurality of power units mounted on the arm.
  • the power unit includes a propeller and a motor that drives the rotation of the propeller.
  • the shape of the arm includes at least one of the following: a T shape, a V shape, a U shape, a Y shape, and an X shape.
  • the arm includes a plurality of connecting ends, one of which is for connecting the rotor connector, and the other connecting end is for mounting the power device.
  • the arm is a hollow structure, and the wire is electrically connected to the rotor connector through the inside of the arm.
  • the rotor connector includes a mechanical connection portion and a mechanical connection portion
  • the body connector includes a mechanical mating portion for coupling with the mechanical connection portion, and an electrical mating portion for coupling with the electrical connection portion .
  • the rotor connector and the fuselage connector are both conductive members such that the rotor connector and the body connector are mechanically coupled while being mechanically coupled.
  • the rotor connector is provided with at least one of the following: an insert, an insertion slot, an insertion hole, a snap member, a fastening member, a snap groove, a snap hole, a threaded connector, a threaded hole, and a sleeve.
  • the body connector is provided with at least one of the following: an insert, an insertion slot, an insertion hole, a snap member, a fastening component, an engaging groove, a snap hole, a threaded connector, a threaded hole, a sleeve .
  • a rotor assembly for an unmanned aerial vehicle comprising:
  • An arm for detachably connecting with an unmanned aircraft body is provided with a fuselage connector;
  • a power assembly for providing flight power to the unmanned aerial vehicle, the power assembly being mounted on the arm;
  • a rotor connector fixed to the connecting end of the arm and the fuselage
  • the rotor connector is mechanically and electrically coupled to the fuselage connector; and when the rotor assembly is mounted to the fuselage through the fuselage connector and the rotor connector, the fuselage connector is coupled to the rotor Electrical connection.
  • the rotor link after the rotor link is rotated by a predetermined angle about the axial direction of the rotor assembly, it can still cooperate with the fuselage connecting member, so that the rotor assembly is mounted at the preset angle to be mounted on the fuselage.
  • the preset angle is 180 degrees, so that the rotor assembly is installed upside down.
  • the shape of the arm includes at least one of the following: a T shape, a V shape, a U shape, a Y shape, and an X shape.
  • the arm is a hollow structure, and the wire is electrically connected to the rotor connector through the inside of the arm.
  • the rotor connector includes a mechanical connection portion and a mechanical connection portion
  • the body connector includes a mechanical mating portion for coupling with the mechanical connection portion, and an electrical mating portion for coupling with the electrical connection portion .
  • the rotor connector and the fuselage connector are both conductive members such that the rotor connector and the body connector are mechanically coupled while being mechanically coupled.
  • the rotor connector is provided with at least one of the following: an insert, an insertion slot, an insertion hole, a snap member, a fastening member, a snap groove, a snap hole, a threaded connector, a threaded hole, and a sleeve.
  • the body connector is provided with at least one of the following: an insert, an insertion slot, an insertion hole, a snap member, a fastening component, an engaging groove, a snap hole, a threaded connector, a threaded hole, a sleeve .
  • the quick release structure of the present invention is capable of detachably connecting the rotor assembly to the air body.
  • the rotor assembly When the quick release structure connects the rotor assembly to the airframe, the rotor assembly is electrically connected to the fuselage through the quick release structure; A plurality of the quick-release structures are interchangeably connected to a plurality of the rotor assemblies.
  • the rotor assembly is detachably coupled to the fuselage, and a plurality of the quick release structures are interchangeably connected between the plurality of the rotor assemblies, such that a plurality of the rotor assemblies detached from the fuselage are stored and transported No need to distinguish, easy to store and transport.
  • the multi-rotor UAV fails, such as the failure of the rotor assembly, the failed rotor assembly can be quickly replaced with a spare rotor assembly or the failed component of the rotor assembly can be quickly replaced for on-site maintenance.
  • FIG. 1 is an exploded perspective view of a multi-rotor unmanned aerial vehicle according to an embodiment of the present invention.
  • Figure 2 is a partial enlarged view of the multi-rotor UAV of Figure 1.
  • FIG. 3 is an exploded perspective view of a multi-rotor unmanned aerial vehicle according to another embodiment of the present invention.
  • Multi-rotor unmanned aerial vehicle 100,300 body 10 Matching department 11 Connection hole 111 Threaded hole 12 Rotor assembly 20 Arm twenty one Connecting arm 211 Support arm 212 Motor twenty two propeller twenty three Quick release structure 200 Connector 30 Connection structure 301 Fixed plate 31 Fixed surface 311 Screw hole 32 bolt 33 Sleeve structure 34 Groove 35 Pin component 36
  • Embodiments of the present invention provide a multi-rotor unmanned aerial vehicle.
  • the multi-rotor unmanned aerial vehicle includes a fuselage, a plurality of rotor assemblies, and a plurality of quick release structures.
  • the plurality of rotor assemblies are used to provide flight power.
  • the plurality of quick release structures are used to connect the rotor assembly to the fuselage.
  • Each of the quick release structures includes a rotor connector and a fuselage connector detachably coupled to the rotor connector, the rotor connector being secured to the rotor assembly, the fuse connector being secured to the fuselage.
  • the rotor connector is mechanically coupled and/or electrically coupled to the fuselage connector.
  • the rotor link is engageable with the fuselage connector at a plurality of angular positions. Specifically, after each of the rotor links is rotated by a predetermined angle about the axial direction of the rotor assembly, the fuse link can still be engaged with the fuselage connector such that the rotor assembly is mounted to the fuselage at the predetermined angle.
  • the preset angle is 180 degrees such that the rotor assembly is mounted upside down.
  • the rotor link of one of the rotor assemblies is engageable with at least two fuselage connectors such that at least two of the rotor assemblies are interchangeable.
  • Embodiments of the present invention also provide an assembly for assembling a multi-rotor UAV that includes a fuselage, and a plurality of rotor assemblies.
  • the fuselage is provided with a fuselage connector.
  • the plurality of rotor assemblies are for providing flight power; each of the rotor assemblies is provided with a rotor connection for detachable connection with the fuselage connection; the rotor connection and the fuselage connection are mechanically coupled or/and electrically coupling.
  • the rotor connector is mechanically coupled and electrically coupled to the fuselage connector.
  • the rotor assembly is assembled with the fuselage, the rotor assembly is mounted to the fuselage through the fuselage connector and the rotor connector, and the fuselage connector is electrically coupled to the rotor connector.
  • one of the rotor assemblies of the rotor assembly is engageable with another fuselage connector corresponding to the rotor assembly such that the connection locations of the two rotor assemblies with the fuselage are interchangeable.
  • the two rotor assemblies are identical or different in construction.
  • Embodiments of the present invention also provide a rotor assembly for an unmanned aerial vehicle that includes an arm, a power assembly, and a rotor link.
  • the arm is for detachable connection to the body of the UAV.
  • the fuselage is provided with a fuselage connector.
  • the power assembly is for providing flight power to the unmanned aerial vehicle, and the power assembly is mounted on the arm.
  • the rotor connector is fixed to the connecting end of the arm and the body. Wherein, the rotor connector and the fuselage connector are mechanically coupled or/and electrically coupled.
  • the rotor connector is mechanically coupled and electrically coupled to the fuselage connector.
  • the fuselage connector is electrically coupled to the rotor connector.
  • a multi-rotor unmanned aerial vehicle 100 includes a fuselage 10 , a rotor assembly 20 , and a quick release structure 200 .
  • the rotor assembly 20 is detachably coupled to the fuselage 10 by the quick release structure 200.
  • the quick release structure 200 has a multi-position mounting manner or a multi-angle mounting manner. Specifically, in the illustrated embodiment, a plurality of the quick release structures 200 are interchangeably connected to the plurality of the rotor assemblies 20 at the connection position of the body 10.
  • the rotor assembly 20 When the rotor assembly 20 is coupled to the fuselage 10 through the quick release structure 200, the rotor assembly 20 is electrically and/or mechanically coupled to the fuselage 10 through the quick release structure 200.
  • the rotor assembly 20 is provided with a rotor connector
  • the body 10 is provided with an organic body connector.
  • the rotor assembly 20 and the body are 10 through the rotor connector and the fuselage connector simultaneously form an electrical connection and a mechanical connection.
  • the fuselage connector is electrically coupled to the rotor connector.
  • the rotor connector includes a mechanical connection and an electrical connection
  • the fuse connector includes a mechanical mating portion coupled to the mechanical connection and an electrical mating portion for coupling with the electrical connection.
  • the rotor connector and the fuselage connector may both be electrically conductive such that the rotor connector is electrically coupled to the fuselage connector while being mechanically coupled.
  • the rotor connector is provided with at least one of the following: an insert, an insertion slot, an insertion hole, a snap member, a fastening member, an engaging groove, and a card. Hole, threaded connection, threaded hole, fitting.
  • the fuselage connector can be correspondingly provided with at least one of the following: an insert, an insertion slot, an insertion hole, a snap member, a fastening component, Engagement groove, snap hole, threaded connection, threaded hole, sleeve.
  • the body connector includes a mating portion 11 disposed on the body 10.
  • the mating portion 11 defines a plurality of connecting holes 111.
  • the central axes of the plurality of connecting holes 111 are substantially parallel.
  • a plurality of the connection holes 111 are electrically connected to the body connector.
  • the number of the connecting holes 111 is six, and the six connecting holes 111 are respectively arranged along two parallel straight lines, and each of the three connecting holes 111 is arranged along one of the two parallel straight lines. And corresponding to the three-phase line connecting the three-phase power supply respectively; it can be understood that in other embodiments, the six connection holes 111 may be in other arrangements.
  • the fitting portion 11 is fixed to an outer side surface of the body 10.
  • the number of the engaging portions 11 is two, and the two engaging portions 11 are disposed opposite to the body 10. It can be understood that in other embodiments, the number of the engaging portions 11 can be according to actual needs. change.
  • the body 10 is further provided with a power source (not shown), and the body connector is electrically connected to the power source through a wire.
  • the body connector further includes a threaded hole 12 provided in the body 10.
  • the number of the threaded holes 12 is four, and each of the two threaded holes 12 is located on two sides of the two engaging portions 11; it can be understood that in other embodiments, the number of the threaded holes 12 can be Increase or decrease according to actual needs.
  • the rotor assembly 20 is detachably coupled to the fuselage 10 by the quick release structure 200.
  • the rotor assembly 20 includes a boom 21 and a power unit disposed on the arm 21.
  • each of the arms 21 is provided with a plurality of power devices, and the plurality of power devices have the same or opposite rotational directions of operation.
  • the arm 21 is of a hollow structure, and a wire is electrically connected to the rotor connector through the inside of the arm 21.
  • the shape of the arm 21 can be designed according to actual needs.
  • the shape of the arm 21 includes at least one of the following types: T type, V type, U type, Y type, and X type.
  • the arm 21 includes a plurality of connecting ends, one of which is for connecting the rotor connector, and the other connecting end is for mounting the power unit.
  • the arm 21 is T-shaped; specifically, the arm 21 includes a connecting arm 211 and a supporting arm 212 fixedly coupled to the connecting arm 211.
  • One end of the connecting arm 211 is connected to the supporting arm 212, and the other end is connected to the rotor connecting member.
  • Two ends of the support arm 212 are fixedly connected to the motor 22 respectively.
  • the length direction of the connecting arm 211 is perpendicular to the longitudinal direction of the support arm 212.
  • the rotor connector is disposed on the arm 21, and the rotor connector is electrically connected to the motor 22 by a wire.
  • the number of the rotor assemblies 20 is two, and the two rotor assemblies 20 are disposed opposite each other.
  • the power unit can include a motor, an engine, and the like.
  • the power unit includes a motor 22 and a propeller 23 that drives the propeller 23 to rotate.
  • the motor 22 is fixed to the arm 21, and the propeller 23 is coupled to the motor 22 for driving the propeller 23 to rotate to provide flight power to the multi-rotor UAV 100.
  • the multi-rotor unmanned aerial vehicle 100 may be a quadrotor unmanned aerial vehicle, a six-rotor unmanned aerial vehicle, an eight-rotor unmanned aerial vehicle or a ten-rotor unmanned aerial vehicle.
  • the multi-rotor UAV 100 is a quadrotor UAV.
  • the arm 21 of each of the rotor assemblies 20 includes two connecting arms 211 that are spaced apart from the support arms 212.
  • the rotor connector includes a joint 30 and a connection structure 301 that is coupled to the connection structure 301.
  • each connecting arm 211 is connected to the connecting structure 301 and the joint 30; a pin assembly 36 is fixed on the bottom surface of the recess 35 of each of the joints 30, and the three pins of the lead assembly 36 are respectively connected A three-phase line of the motor 22.
  • the corresponding body 10 is provided with four engaging portions 11, each of which cooperates with a corresponding one of the joints 30.
  • the number of the connection holes 111 formed in each of the fitting portions 11 is three.
  • the rotor connector further includes a fixing plate 31 provided on the joint 30.
  • the fixing plate 31 includes a fixing surface 311 facing the body 10, and the joint 30 is fixed to the fixing surface 311.
  • a screw hole 32 is formed in the fixing plate 31, and the screw hole 32 extends through the fixing plate 31.
  • the number of the screw holes 32 is two, and the two screw holes 32 are located on both sides of the joint 30. It can be understood that in other embodiments, the number of the screw holes 32 can be changed according to actual needs.
  • the joint 30 cooperates with the engaging portion 11 to electrically connect the rotor assembly 20 with the body 10.
  • the joint 30 includes a sleeve structure 34 fixed to the fixing surface 311.
  • the sleeve structure 34 is provided with a groove 35.
  • the shape and size of the groove 35 are adapted to the shape and size of the fitting portion 11.
  • a pin assembly 36 is fixed to the bottom surface of the recess 35, and the pin assembly 36 is electrically connected to the rotor connector.
  • the lead assembly 36 includes three pins made of a conductive material and not electrically connected to each other, and the three pins are respectively connected to the corresponding three-phase lines of the motor 22. Specifically, in the embodiment shown in FIGS.
  • the number of the lead components 36 of the connector 30 is two, and the two pins of the two lead components 36 are respectively connected to the corresponding two of the two motors 22
  • the pins of the pin assembly 36 corresponding to the two motors 22 are axially symmetrically distributed; the positions of the six pins correspond to the positions of the six connection holes 111 of the mating portion 11.
  • the joint 30 and the engaging portion 11 are interchangeable, that is, the engaging portion 11 is fixed on the fixing surface 311, and the joint 30 is fixed on the body 10.
  • the number of the quick release structures 200 is two, and the two rotor assemblies 20 are respectively coupled to the body 10 through the two quick release structures 200.
  • Two of the joints 30 are respectively fixed to the fixing faces 311 of the two fixing plates 31.
  • the two fixing plates 31 respectively fix one end of the connecting arms 211 of the arms 21 of the two rotor assemblies 20.
  • Two of the mating portions 11 are respectively disposed on the two opposite outer side surfaces of the body 10.
  • the four bolts 33 are respectively inserted into the four screw holes 12 through the four screw holes 32.
  • the two sleeve structures 34 are respectively sleeved on the engaging portion 11, and the engaging portion 11 is received in the groove 35.
  • the pins of the four sets of the lead assemblies 36 are respectively inserted into the connecting holes 111 of the mating portions 11 to connect the rotor assembly 20 to the body 10, the corresponding motor 22, the rotor connecting member, the lead
  • the leg assembly 36, the connecting hole 111 and the body connector form an electrical connection.
  • the two rotor assemblies 20 of the multi-rotor UAV 100 are interchangeable, that is, when the quick release structure 200 is disengaged from the fuselage 10, the rotor assembly 20 is detached from the fuselage 10; when reassembled
  • the two rotor assemblies 20 need not be distinguished, and the two rotor assemblies 20 can cooperate with any one of the two mating portions 11 through the joint 30 and the connecting structure 301 of the quick-release structure 200 connected thereto to make the rotor
  • the assembly 20 is coupled to the body 10 and is electrically coupled to the body 10.
  • the two rotor assemblies 20 of the multi-rotor UAV 100 are interchangeable such that the two rotor assemblies 20 detached from the fuselage 10 do not need to be distinguished when stored and transported.
  • the multi-rotor UAV 100 fails, such as a failure of the rotor assembly, the failed rotor assembly can be quickly replaced with a spare rotor assembly or the failed component of the rotor assembly can be quickly replaced for on-site maintenance.
  • the connecting structure 301 can be replaced by other structures, such as a detachable structure, the detachable structure includes a fixing portion and a detachable connecting member connected to the fixing portion, the fixing portion is connected to The body 10 is connected to the fixing portion by the locking member 20, and the engaging member is abutted or disengaged from the fixing portion, so that the detachable structure is in a locked state or a detachable state.
  • the joint 30 can be disposed on the fixing portion, the body 10 or the engaging member, and the corresponding engaging portion 11 is disposed on the engaging member or the fixing portion and the body.
  • the quick release structure is capable of detachably connecting the rotor assembly to the air body.
  • the quick release structure connects the rotor assembly to the air body, the rotor assembly is electrically connected to the air body through the quick release structure;
  • the quick release structure is interchangeable between a plurality of the rotor assemblies connected to each other.
  • the rotor assembly is detachably coupled to the fuselage, and a plurality of the quick release structures are interchangeably connected between the plurality of the rotor assemblies, such that a plurality of the rotor assemblies detached from the fuselage are stored and transported No need to distinguish, easy to store and transport.
  • the multi-rotor UAV fails, such as the failure of the rotor assembly, the failed rotor assembly can be quickly replaced with a spare rotor assembly or the failed component of the rotor assembly can be quickly replaced for on-site maintenance.

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Abstract

一种快拆结构（100），其用于将旋翼组件（20）可拆卸的连接于机身（10），其特征在于：该快拆结构（100）将该旋翼组件（20）连接于该机身（10）时，该旋翼组件（20）通过该快拆结构（100）与该机身（10）形成电性连接；多个该快拆结构（100）对应连接的多个该旋翼组件（20）之间能够互换。本发明还涉及多旋翼无人飞行器（100、300）、组件及旋翼组件。

Description

快拆结构、多旋翼无人飞行器、组件及旋翼组件 技术领域
本发明涉及一种快拆结构、多旋翼无人飞行器、组件及旋翼组件。
背景技术
多旋翼无人飞行器包括机臂及与该机臂相连接的机身，现有的多旋翼无人飞行器的机臂与机身之间的连接大都采用固定连接，少数采用快拆结构将多旋翼无人飞行器的左右机臂连接到机身。采用快拆结构连接左右机臂和机身时，左右机臂不能互换使用，导致被快拆下来的左右机臂于储存及运输时必须被区分以避免安装错误，且出现故障时不便于现场维修。
发明内容
有鉴于此，有必要提供一种能够使多旋翼无人飞行器便于维修与运输的快拆结构。
还有必要提供一种采用该快拆结构的多旋翼无人飞行器、用于组装成多旋翼无人飞行器的组件、以及旋翼组件。
一种多旋翼无人飞行器，其包括机身、旋翼组件及可拆卸的将该旋翼组件连接于该机身的快拆结构。该快拆结构将该旋翼组件机械连接于该机身时，该旋翼组件通过该快拆结构与该机身形成电性连接；多个该快拆结构对应连接的多个该旋翼组件于该机身的连接位置能够互换。
进一步的，该快拆结构包括接头及与该接头可分离连接的配合部，该旋翼组件连接于该机身时，该旋翼组件通过该接头及该配合部电性连接该机身。
进一步的，该接头及该配合部其中的一个设置在该机身上且与该机身电性连接，另一个设置在该旋翼组件上且与该旋翼组件电性连接。
进一步的，该接头包括套筒结构，该套筒结构开设有凹槽，该凹槽用于收容该配合部。
进一步的，该凹槽的形状及尺寸与该配合部的形状及尺寸相适配。
进一步的，该接头还包括与该机身或者该旋翼组件电性连接的引脚组件，该引脚组件固定在该凹槽的底面上。
进一步的，该引脚组件包括三个引脚，三个该引脚用于分别电性连接三相电源的三相线。
进一步的，该引脚是由导电材料制成的，且各个该引脚之间互不导通。
进一步的，该配合部开设有三个连接孔，三个该连接孔用于分别电性连接三相电源的三相线。
进一步的，三个该引脚的位置分别与三个该连接孔的位置相对应，三个该引脚分别穿入三个该连接孔，该接头与该配合部形成电性连接。
进一步的，该引脚组件的数量为一个或者两个。
进一步的，该快拆结构还包括连接结构，该连接结构与该接头或者该配合部相连接。
进一步的，该连接结构包括固定板，该快拆结构通过该固定板连接于该旋翼组件，该接头或者该配合部固定在该固定板上。
进一步的，该连接结构包括穿过该固定板的螺栓，该快拆结构通过该螺栓连接于该机身。
进一步的，该连接结构包括固定部及能够拆卸的连接于该固定部的卡接件，该固定部连接于该机身，该卡接件将该旋翼组件连接于该固定部，该卡接件与该固定部相抵持或者相脱离，使该可拆卸结构处于锁定状态或者能够拆卸状态。
进一步的，该接头设置在该固定部、该机身或者该卡接件上；该配合部设置在该卡接件或者该固定部、该机身上。
进一步的，该旋翼组件包括连接于该快拆结构的机臂、固定连接于该机臂的电机及连接于该电机的螺旋桨，该电机用于驱动该螺旋桨转动，从而为该多旋翼无人飞行器提供飞行动力。
进一步的，该机臂包括连接臂及支撑臂，该连接臂的一端固定连接该支撑臂，另一端连接于该快拆结构；该支撑臂的两端分别固定连接一个该电机。
进一步的，该连接臂的数量为两个，两个该连接臂间隔固定在该支撑臂上，每个该连接臂的一端固定连接该支撑臂，另一端连接一个该快拆结构。
一种快拆结构，其用于将旋翼组件可拆卸的连接于机身。该快拆结构将该旋翼组件连接于该机身时，该旋翼组件通过该快拆结构与该机身形成电性连接；多个该快拆结构对应连接的多个该旋翼组件于该机身的连接位置能够互换。
进一步的，该快拆结构包括接头及与该接头可分离连接的配合部，该旋翼组件连接于该机身时，该旋翼组件通过该接头及该配合部电性连接该机身。
进一步的，该接头及该配合部其中的一个设置在该机身上且与该机身电性连接，另一个设置在该旋翼组件上且与该旋翼组件电性连接。
进一步的，该接头包括套筒结构，该套筒结构开设有凹槽，该凹槽用于收容该配合部。
进一步的，该凹槽的形状及尺寸与该配合部的形状及尺寸相适配。
进一步的，该接头还包括与该机身或者该旋翼组件电性连接的引脚组件，该引脚组件固定在该凹槽的底面上。
进一步的，该引脚组件包括三个引脚，三个该引脚用于分别电性连接三相电源的三相线。
进一步的，该引脚是由导电材料制成的，且各个该引脚之间互不导通。
进一步的，该配合部开设有三个连接孔，三个该连接孔用于分别电性连接三相电源的三相线。
进一步的，三个该引脚的位置分别与三个该连接孔的位置相对应，三个该引脚分别穿入三个该连接孔，使该接头与该配合部形成电性连接。
进一步的，该引脚组件的数量为一个或者两个。
进一步的，该快拆结构还包括连接结构，该连接结构与该接头或者该配合部相连接。
进一步的，该连接结构包括固定板，该快拆结构通过该固定板连接于该旋翼组件，该接头或者该配合部固定在该固定板上。
进一步的，该连接结构包括穿过该固定板的螺栓，该快拆结构通过该螺栓连接于该机身。
进一步的，该连接结构包括固定部及能够拆卸的连接于该固定部的卡接件，该固定部连接于该机身，该卡接件将该旋翼组件连接于该固定部，该卡接件与该固定部相抵持或者相脱离，使该可拆卸结构处于锁定状态或者能够拆卸状态。
进一步的，该接头设置在该固定部、该机身或者该卡接件上；对应的该配合部设置在该卡接件或者该固定部、该机身上。
一种多旋翼无人飞行器，其包括：
机身；
多个旋翼组件，用于提供飞行动力；以及
多个快拆结构，用于连接该旋翼组件与该机身；每个该快拆结构包括旋翼连接件及与该旋翼连接件可拆卸连接的机身连接件，该旋翼连接件固定在该旋翼组件，该机身连接件固定在该机身；
其中，该旋翼连接件与该机身连接件能够机械耦合及电耦合；当该旋翼组件通过该机身连接件及该旋翼连接件安装在该机身时，该机身连接件与该旋翼连接件电性连接。
进一步的，每个该旋翼连接件绕该旋翼组件的轴向转动预设角度后，仍然能够与该机身连接件相配合，使得该旋翼组件转动该预设角度安装在该机身。
进一步的，该预设角度为180度，使得该旋翼组件倒置安装。
进一步的，每个该旋翼组件包括机臂及安装在该机臂上的多个动力装置。
进一步的，每个该动力装置包括螺旋桨及驱动该螺旋桨转动的电机。
进一步的，该多个动力装置的电机的工作旋转方向相同。
进一步的，该多个动力装置的电机的工作旋转方向相反。
进一步的，该机臂的形状包括如下至少一种：T型，V型，U型，Y型，X型。
进一步的，该机臂包括多个连接端，其中一个连接端用于连接该旋翼连接件，其余连接端用于安装该动力装置。
进一步的，该机臂为中空结构，导线穿过该机臂内部与该旋翼连接件电连接。
进一步的，该旋翼连接件包括机械连接部及电连接部，该机身连接件包括用于与该机械连接部相耦合的机械配合部、以及用于与该电连接部相耦合的电配合部。
进一步的，该旋翼连接件与该机身连接件均为导电件，使得该旋翼连接件与该机身连接件在机械耦合的同时，也电耦合。
进一步的，该旋翼连接件设有如下至少一种：插入件，插入槽，插入孔，卡接件，扣合件，卡合槽，卡合孔，螺纹连接件，螺纹孔，套合件。
进一步的，该机身连接件设有如下至少一种：插入件，插入槽，插入孔，卡扣件，扣合件，卡合槽，卡合孔，螺纹连接件，螺纹孔，套合件。
进一步的，该多旋翼无人飞行器为四旋翼无人飞行器、六旋翼无人飞行器、八旋翼无人飞行器或十旋翼无人飞行器。
一种用于组装成多旋翼无人飞行器的组件，其包括：
机身，该机身设有机身连接件；以及
多个旋翼组件，用于提供飞行动力；每个该旋翼组件设有用于与该机身连接件可拆卸连接的旋翼连接件；该旋翼连接件与该机身连接件能够机械耦合及电耦合；
其中，当该旋翼组件与该机身组装时，该旋翼组件通过该机身连接件及该旋翼连接件相配合而安装在该机身，该机身连接件与该旋翼连接件电性连接。
进一步的，其中一个该旋翼组件的旋翼连接件能够与另外一个该旋翼组件对应的机身连接件相配合，使得两个该旋翼组件与该机身的连接位置能够互换。
进一步的，两个该旋翼组件的结构相同。
进一步的，两个该旋翼组件的结构不相同。
进一步的，该旋翼连接件绕该旋翼组件的轴向转动预设角度后，仍然能够与该机身连接件相配合，使得该旋翼组件转动该预设角度安装在该机身。
进一步的，该预设角度为180度，使得该旋翼组件倒置安装。
进一步的，每个该旋翼组件包括机臂及安装在该机臂上的多个动力装置。
进一步的，该动力装置包括螺旋桨及驱动该螺旋桨转动的电机。
进一步的，该多个动力装置的电机的工作旋转方向相同。
进一步的，该多个动力装置的电机的工作旋转方向相反。
进一步的，该机臂的形状包括如下至少一种：T形，V形，U形，Y形，X形。
进一步的，该机臂包括多个连接端，其中一个连接端用于连接该旋翼连接件，其余连接端用于安装该动力装置。
进一步的，该机臂为中空结构，导线穿过该机臂内部与该旋翼连接件电连接。
进一步的，该旋翼连接件包括机械连接部及电连接部，该机身连接件包括用于与该机械连接部相耦合的机械配合部、以及用于与该电连接部相耦合的电配合部。
进一步的，该旋翼连接件与该机身连接件均为导电件，使得该旋翼连接件与该机身连接件在机械耦合的同时，也电耦合。
进一步的，该旋翼连接件设有如下至少一种：插入件，插入槽，插入孔，卡接件，扣合件，卡合槽，卡合孔，螺纹连接件，螺纹孔，套合件。
进一步的，该机身连接件设有如下至少一种：插入件，插入槽，插入孔，卡扣件，扣合件，卡合槽，卡合孔，螺纹连接件，螺纹孔，套合件。
一种无人飞行器的旋翼组件，其包括：
机臂，用于与无人飞行器的机身可拆卸连接；该机身设有机身连接件；
动力组件，用于给该无人飞行器提供飞行动力，该动力组件安装在该机臂上；以及
旋翼连接件，固定在该机臂与该机身的连接端；
其中，该旋翼连接件与该机身连接件能够机械耦合及电耦合；当该旋翼组件通过该机身连接件及该旋翼连接件安装在该机身时，该机身连接件与该旋翼连接件电性连接。
进一步的，该旋翼连接件绕该旋翼组件的轴向转动预设角度后，仍然能够与该机身连接件相配合，使得该旋翼组件转动该预设角度安装在该机身。
进一步的，该预设角度为180度，使得该旋翼组件倒置安装。
进一步的，该机臂的形状包括如下至少一种：T形，V形，U形，Y形，X形。
进一步的，该机臂为中空结构，导线穿过该机臂内部与该旋翼连接件电连接。
进一步的，该旋翼连接件包括机械连接部及电连接部，该机身连接件包括用于与该机械连接部相耦合的机械配合部、以及用于与该电连接部相耦合的电配合部。
进一步的，该旋翼连接件与该机身连接件均为导电件，使得该旋翼连接件与该机身连接件在机械耦合的同时，也电耦合。
进一步的，该旋翼连接件设有如下至少一种：插入件，插入槽，插入孔，卡接件，扣合件，卡合槽，卡合孔，螺纹连接件，螺纹孔，套合件。
进一步的，该机身连接件设有如下至少一种：插入件，插入槽，插入孔，卡扣件，扣合件，卡合槽，卡合孔，螺纹连接件，螺纹孔，套合件。
本发明的快拆结构能够将旋翼组件可拆卸的连接于机身，该快拆结构将该旋翼组件连接于该机身时，该旋翼组件通过该快拆结构与该机身形成电性连接；多个该快拆结构对应连接的多个该旋翼组件之间能够互换。该旋翼组件可拆卸的连接该机身，且多个该快拆结构对应连接的多个该旋翼组件之间能够互换，使得自该机身拆卸下来的多个该旋翼组件在储存及运输时无需区分，便于储存及运输。此外，当该多旋翼无人飞行器出现故障时，如旋翼组件出现故障，可以快速的将出现故障的旋翼组件更换为备用的旋翼组件或者快速更换旋翼组件中出现故障的部件，便于现场维修。
 附图说明
图1是本发明一实施例提供的多旋翼无人飞行器的分解示意图。
图2是图1中的多旋翼无人飞行器的局部放大图。
图3是本发明另一实施例提供的多旋翼无人飞行器的分解示意图。
主要元件符号说明
多旋翼无人飞行器 100,300
机身 10
配合部 11
连接孔 111
螺纹孔 12
旋翼组件 20
机臂 21
连接臂 211
支撑臂 212
电机 22
螺旋桨 23
快拆结构 200
接头 30
连接结构 301
固定板 31
固定面 311
螺孔 32
螺栓 33
套筒结构 34
凹槽 35
引脚组件 36
如下具体实施例将结合上述附图进一步说明本发明。
具体实施方式
下面结合附图，对本发明的一些实施例作详细说明。在不冲突的情况下，下述的实施例及实施例中的特征可以相互组合。
本发明的实施例提供一种多旋翼无人飞行器。该多旋翼无人飞行器包括机身、多个旋翼组件以及多个快拆结构。
该多个旋翼组件用于提供飞行动力。该多个快拆结构用于连接该旋翼组件与该机身。每个该快拆结构包括旋翼连接件及与该旋翼连接件可拆卸连接的机身连接件，该旋翼连接件固定在该旋翼组件，该机身连接件固定在该机身。
其中在一些实施例中，该旋翼连接件与该机身连接件能够机械耦合或/及电耦合。
在其中一些实施例中，该旋翼连接件能够在多个角度位置与该机身连接件相配合。具体地，每个该旋翼连接件绕该旋翼组件的轴向转动预设角度后，仍然能够与该机身连接件相配合，使得该旋翼组件转动该预设角度安装在该机身。例如，该预设角度为180度，使得该旋翼组件倒置安装。
在其中一些实施例中，其中一个旋翼组件的旋翼连接件能够与至少两个机身连接件相配合，使得其中至少两个旋翼组件互换安装位置。
本发明的实施例还提供一种用于组装成多旋翼无人飞行器的组件，其包括机身、以及多个旋翼组件。
该机身设有机身连接件。该多个旋翼组件用于提供飞行动力；每个该旋翼组件设有用于与该机身连接件可拆卸连接的旋翼连接件；该旋翼连接件与该机身连接件能够机械耦合或/及电耦合。
在其中一些实施例中，该旋翼连接件与该机身连接件同时机械耦合及电耦合。例如，当该旋翼组件与该机身组装时，该旋翼组件通过该机身连接件及该旋翼连接件相配合而安装在该机身，该机身连接件与该旋翼连接件电性连接。
在其中一些实施例中，其中一个该旋翼组件的旋翼连接件能够与另外一个该旋翼组件对应的机身连接件相配合，使得两个该旋翼组件与该机身的连接位置能够互换。两个该旋翼组件的结构相同或者不相同。
本发明的实施例还提供一种无人飞行器的旋翼组件，其包括机臂、动力组件、以及旋翼连接件。
该机臂用于与无人飞行器的机身可拆卸连接。该机身设有机身连接件。该动力组件用于给该无人飞行器提供飞行动力，该动力组件安装在该机臂上。该旋翼连接件固定在该机臂与该机身的连接端。其中，该旋翼连接件与该机身连接件能够机械耦合或/及电耦合。
在其中一些实施例中，该旋翼连接件与该机身连接件同时机械耦合及电耦合。例如，当该旋翼组件通过该机身连接件及该旋翼连接件安装在该机身时，该机身连接件与该旋翼连接件电性连接。
请参阅图1及图2，本发明一实施例提供的多旋翼无人飞行器100，其包括机身10、旋翼组件20及快拆结构200。该旋翼组件20通过该快拆结构200可拆卸的连接于该机身10。
该快拆结构200具有多位置安装方式或多角度安装方式。具体在图示的实施例中，多个该快拆结构200对应连接的多个该旋翼组件20于该机身10的连接位置能够互换。
该旋翼组件20通过该快拆结构200连接于该机身10时，该旋翼组件20通过该快拆结构200与该机身10形成电性连接或/及机械连接。具体在图示的实施例中，该旋翼组件20设置有旋翼连接件，该机身10设置有机身连接件，该旋翼组件20连接到该机身10时，该旋翼组件20及该机身10通过该旋翼连接件及该机身连接件同时形成电性连接及机械连接。例如，当该旋翼组件20通过该机身连接件及该旋翼连接件安装在该机身10时，该机身连接件与该旋翼连接件电性连接。
该旋翼连接件与该机身连接件的配合方式可以根据不同需求来设计，例如，在其中一个实施例中，该旋翼连接件包括机械连接部及电连接部，该机身连接件包括用于与该机械连接部相耦合的机械配合部、以及用于与该电连接部相耦合的电配合部。在其他实施例中，该旋翼连接件与该机身连接件可以均为导电件，使得该旋翼连接件与该机身连接件在机械耦合的同时，也电耦合。
该旋翼连接件的具体结构也可以根据不同需求来设计，例如，该旋翼连接件设有如下至少一种：插入件，插入槽，插入孔，卡接件，扣合件，卡合槽，卡合孔，螺纹连接件，螺纹孔，套合件。
该机身连接件的具体结构也可以根据不同需求来设计，例如，该机身连接件可以相应的设有如下至少一种：插入件，插入槽，插入孔，卡扣件，扣合件，卡合槽，卡合孔，螺纹连接件，螺纹孔，套合件。
具体在图示的实施例中，该机身连接件包括设于该机身10的配合部11，该配合部11开设有数个连接孔111，数个该连接孔111的中心轴基本平行。数个该连接孔111与该机身连接件电性连接。本实施例中，该连接孔111的数量为六个，六个该连接孔111分别沿两条平行的直线间隔设置，每三个该连接孔111沿该两条平行的直线中的一条间隔设置，且分别对应连接三相电源的三相线；可以理解，在其他实施例中，六个该连接孔111可以为其他排列方式。该配合部11固定在该机身10的一外侧表面上。本实施例中，该配合部11的数量为两个，两个该配合部11相对于该机身10相背设置；可以理解，在其他实施例中，该配合部11的数量可以根据实际需要改变。该机身10上还设有电源（图未示），该机身连接件通过导线与该电源电性连接。
进一步的，该机身连接件还包括设于该机身10的螺纹孔12。本实施例中，该螺纹孔12的数量为四个，每两个该螺纹孔12分别位于两个该配合部11的两侧；可以理解，在其他实施例中，该螺纹孔12的数量可以根据实际需要增加或者减少。
该旋翼组件20通过该快拆结构200能够拆卸的连接于该机身10。该旋翼组件20包括机臂21、以及设于该机臂21上的动力装置。具体在图示的实施例中，每个该机臂21上设有多个动力装置，该多个动力装置的工作旋转方向相同或者相反。该机臂21为中空结构，导线穿过该机臂21内部与该旋翼连接件电连接。
该机臂21的形状可以根据实际需要来设计，例如，该机臂21的形状包括如下至少一种：T型，V型，U型，Y型，X型。该机臂21包括多个连接端，其中一个连接端用于连接该旋翼连接件，其余连接端用于安装该动力装置。具体在图示的实施例中，该机臂21为T型；具体地，该机臂21包括连接臂211及固定连接于该连接臂211的支撑臂212。该连接臂211的一端连接该支撑臂212，另一端连接该旋翼连接件。该支撑臂212的两端分别固定连接一个该电机22。本实施例中，该连接臂211的长度方向与该支撑臂212的长度方向相垂直。该旋翼连接件设置在该机臂21上，该旋翼连接件通过导线与该电机22电性连接。本实施例中，该旋翼组件20的数量为两个，两个该旋翼组件20相背设置。
该动力装置可以包括电机、发动机等。具体在图示的实施例中，该动力装置包括电机22及螺旋桨23，该电机22驱动螺旋桨23转动。该电机22固定在该机臂21上，该螺旋桨23连接于该电机22，该电机22用于驱动该螺旋桨23转动，从而为该多旋翼无人飞行器100提供飞行动力。
该多旋翼无人飞行器100可以为四旋翼无人飞行器、六旋翼无人飞行器、八旋翼无人飞行器或十旋翼无人飞行器等。具体在图3所示的实施例中，该多旋翼无人飞行器100为四旋翼无人飞行器。每个该旋翼组件20的机臂21包括两个连接臂211，该两个连接臂211间隔的连接在支撑臂212上。该旋翼连接件包括接头30及连接结构301，该接头30与该连接结构301相连接。每个该连接臂211的一端连接该连接结构301及该接头30；每个该接头30的凹槽35的底面上固定一个引脚组件36，该引脚组件36的三个引脚分别对应连接一个该电机22的三相线。对应的该机身10上设置有四个配合部11，每个该配合部11与对应的一个该接头30相配合。每个该配合部11开设的连接孔111的数量为三个。
该旋翼连接件还包括设于该接头30的固定板31，该固定板31包括朝向该机身10的固定面311，该接头30固定在该固定面311上。该固定板31上开设有螺孔32，该螺孔32贯穿该固定板31。本实施例中，该螺孔32的数量为两个，两个该螺孔32位于该接头30的两侧；可以理解，在其他实施例中，该螺孔32的数量可以根据实际需要改变。
该接头30与该配合部11相配合，使该旋翼组件20与该机身10形成电性连接。该接头30包括固定在该固定面311上的套筒结构34，该套筒结构34开设有凹槽35，该凹槽35的形状及尺寸与该配合部11的形状及尺寸相适配。该凹槽35的底面上固定有引脚组件36，该引脚组件36与该旋翼连接件电性连接。该引脚组件36包括由导电材料制成的且互不导通的三个引脚，该三个引脚分别连接对应的该电机22的三相线。具体在图1及2所示的实施例中，该接头30的引脚组件36的数量为两个，两个该引脚组件36的六个引脚分别连接对应的两个该电机22的三相线，两个该电机22对应的该引脚组件36的引脚呈轴对称分布；六个该引脚的位置与该配合部11的六个连接孔111的位置相对应。
可以理解，在其他实施例中，该接头30及该配合部11可以互换，即该配合部11固定在该固定面311上，该接头30固定在该机身10上。
具体在图1及2所示的实施例中，该快拆结构200的数量为两个，两个该旋翼组件20分别通过两个该快拆结构200连接于该机身10。两个该接头30分别固定在两个该固定板31的固定面311上，两个该固定板31分别固定连接两个该旋翼组件20的机臂21的连接臂211的一端。两个该配合部11分别设置在该机身10的两个相背的外侧表面上。四个螺栓33分别穿过四个该螺孔32旋入四个该螺纹孔12内，两个该套筒结构34分别套在该配合部11上，该配合部11收容于该凹槽35。四组该引脚组件36的引脚分别穿入两个该配合部11的连接孔111内，使该旋翼组件20连接于该机身10，对应的该电机22、该旋翼连接件、该引脚组件36、该连接孔111及该机身连接件形成电性连接。
该多旋翼无人飞行器100的两个该旋翼组件20可以互换，即当该快拆结构200与该机身10脱离时，该旋翼组件20从该机身10上拆卸下来；当重新组装时，两个该旋翼组件20无需区分，两个该旋翼组件20均可以通过其连接的快拆结构200的接头30及连接结构301与两个该配合部11中的任意一个相配合以使该旋翼组件20连接到该机身10上，该旋翼组件20与机身10电性连接。该多旋翼无人飞行器100的两个该旋翼组件20可以互换，使得自该机身10拆卸下来的两个该旋翼组件20在储存及运输时无需区分。此外，当该多旋翼无人飞行器100出现故障时，如旋翼组件出现故障，可以快速的将出现故障的旋翼组件更换为备用的旋翼组件或者快速更换旋翼组件中出现故障的部件，便于现场维修。
可以理解，在其他实施例中，该连接结构301可以采用其他结构替代，如可拆卸结构，该可拆卸结构包括固定部及能够拆卸的连接于该固定部的卡接件，该固定部连接于该机身10，该卡接件将该旋翼组件20连接于该固定部，该卡接件与该固定部相抵持或者相脱离，使该可拆卸结构处于锁定状态或者能够拆卸状态。其中，该接头30可以设置在该固定部、该机身10或者该卡接件上，对应的该配合部11设置在该卡接件或者该固定部、该机身上。
上述快拆结构能够将旋翼组件能够拆卸的连接于机身，该快拆结构将该旋翼组件连接于该机身时，该旋翼组件通过该快拆结构与该机身形成电性连接；多个该快拆结构对应连接的多个该旋翼组件之间能够互换。该旋翼组件可拆卸的连接该机身，且多个该快拆结构对应连接的多个该旋翼组件之间能够互换，使得自该机身拆卸下来的多个该旋翼组件在储存及运输时无需区分，便于储存及运输。此外，当该多旋翼无人飞行器出现故障时，如旋翼组件出现故障，可以快速的将出现故障的旋翼组件更换为备用的旋翼组件或者快速更换旋翼组件中出现故障的部件，便于现场维修。
另外，本技术领域的普通技术人员应当认识到，以上的实施例仅是用来说明本发明而并非用作为对本发明限定，只要在本发明实质精神范围之内，对以上实施例所作的适当改变和变化都落在本发明要求保护的范围之内。

Claims (76)

  1. 一种多旋翼无人飞行器，其包括机身、旋翼组件及可拆卸的将该旋翼组件连接于该机身的快拆结构，其特征在于：该快拆结构将该旋翼组件机械连接于该机身时，该旋翼组件通过该快拆结构与该机身形成电性连接；多个该快拆结构对应连接的多个该旋翼组件于该机身的连接位置能够互换。
  2. 如权利要求1所述的多旋翼无人飞行器，其特征在于：该快拆结构包括接头及与该接头可分离连接的配合部，该旋翼组件连接于该机身时，该旋翼组件通过该接头及该配合部电性连接该机身。
  3. 如权利要求2所述的多旋翼无人飞行器，其特征在于：该接头及该配合部其中的一个设置在该机身上且与该机身电性连接，另一个设置在该旋翼组件上且与该旋翼组件电性连接。
  4. 如权利要求2所述的多旋翼无人飞行器，其特征在于：该接头包括套筒结构，该套筒结构开设有凹槽，该凹槽用于收容该配合部。
  5. 如权利要求4所述的多旋翼无人飞行器，其特征在于：该凹槽的形状及尺寸与该配合部的形状及尺寸相适配。
  6. 如权利要求4所述的多旋翼无人飞行器，其特征在于：该接头还包括与该机身或者该旋翼组件电性连接的引脚组件，该引脚组件固定在该凹槽的底面上。
  7. 如权利要求6所述的多旋翼无人飞行器，其特征在于：该引脚组件包括三个引脚，三个该引脚用于分别电性连接三相电源的三相线。
  8. 如权利要求7所述的多旋翼无人飞行器，其特征在于：该引脚是由导电材料制成的，且各个该引脚之间互不导通。
  9. 如权利要求7所述的多旋翼无人飞行器，其特征在于：该配合部开设有三个连接孔，三个该连接孔用于分别电性连接三相电源的三相线。
  10. 如权利要求9所述的多旋翼无人飞行器，其特征在于：三个该引脚的位置分别与三个该连接孔的位置相对应，三个该引脚分别穿入三个该连接孔，该接头与该配合部形成电性连接。
  11. 如权利要求7所述的多旋翼无人飞行器，其特征在于：该引脚组件的数量为一个或者两个。
  12. 如权利要求2所述的多旋翼无人飞行器，其特征在于：该快拆结构还包括连接结构，该连接结构与该接头或者该配合部相连接。
  13. 如权利要求12所述的多旋翼无人飞行器，其特征在于：该连接结构包括固定板，该快拆结构通过该固定板连接于该旋翼组件，该接头或者该配合部固定在该固定板上。
  14. 如权利要求13所述的多旋翼无人飞行器，其特征在于：该连接结构包括穿过该固定板的螺栓，该快拆结构通过该螺栓连接于该机身。
  15. 如权利要求12所述的多旋翼无人飞行器，其特征在于：该连接结构包括固定部及能够拆卸的连接于该固定部的卡接件，该固定部连接于该机身，该卡接件将该旋翼组件连接于该固定部，该卡接件与该固定部相抵持或者相脱离，使该可拆卸结构处于锁定状态或者能够拆卸状态。
  16. 如权利要求15所述的多旋翼无人飞行器，其特征在于：该接头设置在该固定部、该机身或者该卡接件上；该配合部设置在该卡接件或者该固定部、该机身上。
  17. 如权利要求1所述的多旋翼无人飞行器，其特征在于：该旋翼组件包括连接于该快拆结构的机臂、固定连接于该机臂的电机及连接于该电机的螺旋桨，该电机用于驱动该螺旋桨转动，从而为该多旋翼无人飞行器提供飞行动力。
  18. 如权利要求17所述的多旋翼无人飞行器，其特征在于：该机臂包括连接臂及支撑臂，该连接臂的一端固定连接该支撑臂，另一端连接于该快拆结构；该支撑臂的两端分别固定连接一个该电机。
  19. 如权利要求18所述的多旋翼无人飞行器，其特征在于：该连接臂的数量为两个，两个该连接臂间隔固定在该支撑臂上，每个该连接臂的一端固定连接该支撑臂，另一端连接一个该快拆结构。
  20. 一种快拆结构，其用于将旋翼组件可拆卸的连接于机身，其特征在于：该快拆结构将该旋翼组件连接于该机身时，该旋翼组件通过该快拆结构与该机身形成电性连接；多个该快拆结构对应连接的多个该旋翼组件于该机身的连接位置能够互换。
  21. 如权利要求20所述的快拆结构，其特征在于：该快拆结构包括接头及与该接头可分离连接的配合部，该旋翼组件连接于该机身时，该旋翼组件通过该接头及该配合部电性连接该机身。
  22. 如权利要求21所述的快拆结构，其特征在于：该接头及该配合部其中的一个设置在该机身上且与该机身电性连接，另一个设置在该旋翼组件上且与该旋翼组件电性连接。
  23. 如权利要求21所述的快拆结构，其特征在于：该接头包括套筒结构，该套筒结构开设有凹槽，该凹槽用于收容该配合部。
  24. 如权利要求23所述的快拆结构，其特征在于：该凹槽的形状及尺寸与该配合部的形状及尺寸相适配。
  25. 如权利要求23所述的快拆结构，其特征在于：该接头还包括与该机身或者该旋翼组件电性连接的引脚组件，该引脚组件固定在该凹槽的底面上。
  26. 如权利要求25所述的快拆结构，其特征在于：该引脚组件包括三个引脚，三个该引脚用于分别电性连接三相电源的三相线。
  27. 如权利要求26所述的快拆结构，其特征在于：该引脚是由导电材料制成的，且各个该引脚之间互不导通。
  28. 如权利要求26所述的快拆结构，其特征在于：该配合部开设有三个连接孔，三个该连接孔用于分别电性连接三相电源的三相线。
  29. 如权利要求28所述的快拆结构，其特征在于：三个该引脚的位置分别与三个该连接孔的位置相对应，三个该引脚分别穿入三个该连接孔，使该接头与该配合部形成电性连接。
  30. 如权利要求25所述的快拆结构，其特征在于：该引脚组件的数量为一个或者两个。
  31. 如权利要求21所述的快拆结构，其特征在于：该快拆结构还包括连接结构，该连接结构与该接头或者该配合部相连接。
  32. 如权利要求31所述的快拆结构，其特征在于：该连接结构包括固定板，该快拆结构通过该固定板连接于该旋翼组件，该接头或者该配合部固定在该固定板上。
  33. 如权利要求32所述的快拆结构，其特征在于：该连接结构包括穿过该固定板的螺栓，该快拆结构通过该螺栓连接于该机身。
  34. 如权利要求31所述的快拆结构，其特征在于：该连接结构包括固定部及能够拆卸的连接于该固定部的卡接件，该固定部连接于该机身，该卡接件将该旋翼组件连接于该固定部，该卡接件与该固定部相抵持或者相脱离，使该可拆卸结构处于锁定状态或者能够拆卸状态。
  35. 如权利要求34所述的快拆结构，其特征在于：该接头设置在该固定部、该机身或者该卡接件上；对应的该配合部设置在该卡接件或者该固定部、该机身上。
  36. 一种多旋翼无人飞行器，其包括：
    机身；
    多个旋翼组件，用于提供飞行动力；以及
    多个快拆结构，用于连接该旋翼组件与该机身；每个该快拆结构包括旋翼连接件及与该旋翼连接件可拆卸连接的机身连接件，该旋翼连接件固定在该旋翼组件，该机身连接件固定在该机身；
    其中，该旋翼连接件与该机身连接件能够机械耦合及电耦合；当该旋翼组件通过该机身连接件及该旋翼连接件安装在该机身时，该机身连接件与该旋翼连接件电性连接。
  37. 如权利要求36所述的多旋翼无人飞行器，其特征在于：每个该旋翼连接件绕该旋翼组件的轴向转动预设角度后，仍然能够与该机身连接件相配合，使得该旋翼组件转动该预设角度安装在该机身。
  38. 如权利要求37所述的多旋翼无人飞行器，其特征在于：该预设角度为180度，使得该旋翼组件倒置安装。
  39. 如权利要求36所述的多旋翼无人飞行器，其特征在于：每个该旋翼组件包括机臂及安装在该机臂上的多个动力装置。
  40. 如权利要求39所述的多旋翼无人飞行器，其特征在于：每个该动力装置包括螺旋桨及驱动该螺旋桨转动的电机。
  41. 如权利要求39所述的多旋翼无人飞行器，其特征在于：该每个机臂上的多个动力装置的电机的工作旋转方向相同。
  42. 如权利要求39所述的多旋翼无人飞行器，其特征在于：该每个机臂上的多个动力装置的电机的工作旋转方向相反。
  43. 如权利要求39所述的多旋翼无人飞行器，其特征在于：该机臂的形状包括如下至少一种：T型，V型，U型，Y型，X型。
  44. 如权利要求39所述的多旋翼无人飞行器，其特征在于：该机臂包括多个连接端，其中一个连接端用于连接该旋翼连接件，其余连接端用于安装该动力装置。
  45. 如权利要求39所述的多旋翼无人飞行器，其特征在于：该机臂为中空结构，导线穿过该机臂内部与该旋翼连接件电连接。
  46. 如权利要求36所述的多旋翼无人飞行器，其特征在于：该旋翼连接件包括机械连接部及电连接部，该机身连接件包括用于与该机械连接部相耦合的机械配合部、以及用于与该电连接部相耦合的电配合部。
  47. 如权利要求36所述的多旋翼无人飞行器，其特征在于：该旋翼连接件与该机身连接件均为导电件，使得该旋翼连接件与该机身连接件在机械耦合的同时，也电耦合。
  48. 如权利要求36所述的多旋翼无人飞行器，其特征在于：该旋翼连接件设有如下至少一种：插入件，插入槽，插入孔，卡接件，扣合件，卡合槽，卡合孔，螺纹连接件，螺纹孔，套合件。
  49. 如权利要求36所述的多旋翼无人飞行器，其特征在于：该机身连接件设有如下至少一种：插入件，插入槽，插入孔，卡扣件，扣合件，卡合槽，卡合孔，螺纹连接件，螺纹孔，套合件。
  50. 如权利要求36所述的多旋翼无人飞行器，其特征在于：该多旋翼无人飞行器为四旋翼无人飞行器、六旋翼无人飞行器、八旋翼无人飞行器或十旋翼无人飞行器。
  51. 一种用于组装成多旋翼无人飞行器的组件，其包括：
    机身，该机身设有机身连接件；以及
    多个旋翼组件，该多个旋翼组件用于提供飞行动力；每个该旋翼组件设有用于与该机身连接件可拆卸连接的旋翼连接件；该旋翼连接件与该机身连接件能够机械耦合及电耦合；
    其中，当该旋翼组件与该机身组装时，该旋翼组件通过该机身连接件及该旋翼连接件相配合而安装在该机身，该机身连接件与该旋翼连接件电性连接。
  52. 如权利要求51所述的组件，其特征在于：其中一个该旋翼组件的旋翼连接件能够与另外一个该旋翼组件对应的机身连接件相配合，使得两个该旋翼组件与该机身的连接位置能够互换。
  53. 如权利要求52所述的组件，其特征在于：两个该旋翼组件的结构相同。
  54. 如权利要求52所述的组件，其特征在于：两个该旋翼组件的结构不相同。
  55. 如权利要求51所述的组件，其特征在于：该旋翼连接件绕该旋翼组件的轴向转动预设角度后，仍然能够与该机身连接件相配合，使得该旋翼组件转动该预设角度安装在该机身。
  56. 如权利要求55所述的组件，其特征在于：该预设角度为180度，使得该旋翼组件倒置安装。
  57. 如权利要求51所述的组件，其特征在于：每个该旋翼组件包括机臂及安装在该机臂上的多个动力装置。
  58. 如权利要求57所述的组件，其特征在于：该动力装置包括螺旋桨及驱动该螺旋桨转动的电机。
  59. 如权利要求57所述的组件，其特征在于：该多个动力装置的电机的工作旋转方向相同。
  60. 如权利要求57所述的组件，其特征在于：该多个动力装置的电机的工作旋转方向相反。
  61. 如权利要求57所述的组件，其特征在于：该机臂的形状包括如下至少一种：T形，V形，U形，Y形，X形。
  62. 如权利要求57所述的组件，其特征在于：该机臂包括多个连接端，其中一个连接端用于连接该旋翼连接件，其余连接端用于安装该动力装置。
  63. 如权利要求57所述的组件，其特征在于：该机臂为中空结构，导线穿过该机臂内部与该旋翼连接件电连接。
  64. 如权利要求51所述的组件，其特征在于：该旋翼连接件包括机械连接部及电连接部，该机身连接件包括用于与该机械连接部相耦合的机械配合部、以及用于与该电连接部相耦合的电配合部。
  65. 如权利要求51所述的组件，其特征在于：该旋翼连接件与该机身连接件均为导电件，使得该旋翼连接件与该机身连接件在机械耦合的同时，也电耦合。
  66. 如权利要求51所述的组件，其特征在于：该旋翼连接件设有如下至少一种：插入件，插入槽，插入孔，卡接件，扣合件，卡合槽，卡合孔，螺纹连接件，螺纹孔，套合件。
  67. 如权利要求51所述的组件，其特征在于：该机身连接件设有如下至少一种：插入件，插入槽，插入孔，卡扣件，扣合件，卡合槽，卡合孔，螺纹连接件，螺纹孔，套合件。
  68. 一种无人飞行器的旋翼组件，其包括：
    机臂，用于与无人飞行器的机身可拆卸连接；该机身设有机身连接件；
    动力组件，用于给该无人飞行器提供飞行动力，该动力组件安装在该机臂上；以及
    旋翼连接件，固定在该机臂与该机身的连接端；
    其中，该旋翼连接件与该机身连接件能够机械耦合及电耦合；当该旋翼组件通过该机身连接件及该旋翼连接件安装在该机身时，该机身连接件与该旋翼连接件电性连接。
  69. 如权利要求68所述的旋翼组件，其特征在于：该旋翼连接件绕该旋翼组件的轴向转动预设角度后，仍然能够与该机身连接件相配合，使得该旋翼组件转动该预设角度安装在该机身。
  70. 如权利要求69所述的旋翼组件，其特征在于：该预设角度为180度，使得该旋翼组件倒置安装。
  71. 如权利要求68所述的旋翼组件，其特征在于：该机臂的形状包括如下至少一种：T形，V形，U形，Y形，X形。
  72. 如权利要求68所述的旋翼组件，其特征在于：该机臂为中空结构，导线穿过该机臂内部与该旋翼连接件电连接。
  73. 如权利要求68所述的旋翼组件，其特征在于：该旋翼连接件包括机械连接部及电连接部，该机身连接件包括用于与该机械连接部相耦合的机械配合部、以及用于与该电连接部相耦合的电配合部。
  74. 如权利要求68所述的旋翼组件，其特征在于：该旋翼连接件与该机身连接件均为导电件，使得该旋翼连接件与该机身连接件在机械耦合的同时，也电耦合。
  75. 如权利要求68所述的旋翼组件，其特征在于：该旋翼连接件设有如下至少一种：插入件，插入槽，插入孔，卡接件，扣合件，卡合槽，卡合孔，螺纹连接件，螺纹孔，套合件。
  76. 如权利要求68所述的旋翼组件，其特征在于：该机身连接件设有如下至少一种：插入件，插入槽，插入孔，卡扣件，扣合件，卡合槽，卡合孔，螺纹连接件，螺纹孔，套合件。
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