WO2017107128A1 - Structure à désaccouplement rapide, aéronef sans pilote comportant plusieurs hélices, composant et composant à hélices - Google Patents

Structure à désaccouplement rapide, aéronef sans pilote comportant plusieurs hélices, composant et composant à hélices 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
Application number
PCT/CN2015/098661
Other languages
English (en)
Chinese (zh)
Inventor
袁博
吴振凯
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 PCT/CN2015/098661 priority Critical patent/WO2017107128A1/fr
Priority to CN201580003654.2A priority patent/CN105939927B/zh
Publication of WO2017107128A1 publication Critical patent/WO2017107128A1/fr

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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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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Remote Sensing (AREA)
  • Toys (AREA)
  • Details Of Aerials (AREA)
  • Details Of Connecting Devices For Male And Female Coupling (AREA)

Abstract

Une structure à désaccouplement rapide (100) est utilisée pour raccorder amovible un composant à hélices (20) à une partie principale (10), et est caractérisée en ce que : lorsque la structure à désaccouplement rapide (100) raccorde le composant à hélices (20) à la partie principale (10), le composant à hélices (20) est raccordé électriquement à la partie principale (10) par l'intermédiaire de la structure à désaccouplement rapide (100) ; et une pluralité de composants à hélices (20) raccordés de manière correspondante à une pluralité de structures à désaccouplement rapide (100) sont interchangeables. L'invention concerne également un aéronef sans pilote (100, 300) possédant de multiples hélices, des composants et des composants à hélices.
PCT/CN2015/098661 2015-12-24 2015-12-24 Structure à désaccouplement rapide, aéronef sans pilote comportant plusieurs hélices, composant et composant à hélices WO2017107128A1 (fr)

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PCT/CN2015/098661 WO2017107128A1 (fr) 2015-12-24 2015-12-24 Structure à désaccouplement rapide, aéronef sans pilote comportant plusieurs hélices, composant et composant à hélices
CN201580003654.2A CN105939927B (zh) 2015-12-24 2015-12-24 多旋翼无人飞行器、组件及旋翼组件

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PCT/CN2015/098661 WO2017107128A1 (fr) 2015-12-24 2015-12-24 Structure à désaccouplement rapide, aéronef sans pilote comportant plusieurs hélices, composant et composant à hélices

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CN112810808A (zh) * 2021-02-10 2021-05-18 北京京东乾石科技有限公司 多旋翼无人机及其控制方法
CN113734414A (zh) * 2021-09-01 2021-12-03 深圳供电局有限公司 可拆卸无人机机臂装置

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CN108609165A (zh) * 2016-12-09 2018-10-02 北京京东尚科信息技术有限公司 无人机
CN206466160U (zh) * 2016-12-21 2017-09-05 深圳市道通智能航空技术有限公司 可拆卸机臂组件及飞行器
DE102017102172A1 (de) 2017-02-03 2018-08-09 Deutsches Zentrum für Luft- und Raumfahrt e.V. Verbindungsanordnung für einen modularen Multicopter und modularer Multicopter
CN107839876B (zh) * 2017-11-09 2020-12-01 山东科技大学 一种带有多套内嵌旋翼组合的细长型无人飞行器
CN110615097A (zh) * 2019-10-23 2019-12-27 深圳市道通智能航空技术有限公司 一种无人飞行器
CN113371185B (zh) * 2021-07-19 2023-08-08 江苏中天吉奥信息技术股份有限公司 一种地形航拍勘测方法及航拍飞行器
CN113665800A (zh) * 2021-07-26 2021-11-19 北京中天博地科技有限公司 一种基于私有云的免像控三维自动建模方法
CN113978710A (zh) * 2021-10-27 2022-01-28 广西电网有限责任公司电力科学研究院 一种动力模块化的多旋翼无人机

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CN113734414A (zh) * 2021-09-01 2021-12-03 深圳供电局有限公司 可拆卸无人机机臂装置

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