WO2017107128A1

WO2017107128A1 - Quick release structure, unmanned aerial vehicle having multiple propellers, component and propeller component

Info

Publication number: WO2017107128A1
Application number: PCT/CN2015/098661
Authority: WO
Inventors: 袁博; 吴振凯
Original assignee: 深圳市大疆创新科技有限公司
Priority date: 2015-12-24
Filing date: 2015-12-24
Publication date: 2017-06-29
Also published as: CN105939927A; CN105939927B

Abstract

A quick release structure (100) is used to detachably connect a propeller component (20) to a main part (10), and is characterized in that: when the quick release structure (100) connects the propeller component (20) to the main part (10), the propeller component (20) is electrically connected to the main part (10) via the quick release structure (100); and a plurality of the propeller component (20) correspondingly connected to a plurality of the quick release structures (100) are interchangeable. The invention further involves an unmanned aerial vehicle (100, 300) having multiple propellers, component and propeller component.

Description

Quick release structure, multi-rotor UAV, component and rotor assembly

Technical field

The invention relates to a quick release structure, a multi-rotor unmanned aerial vehicle, a component and a rotor assembly.

Background technique

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. When 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.

Summary of the invention

In view of this, it is necessary to provide a quick release structure that enables the multi-rotor UAV to be easily repaired and transported.

It is also necessary to provide a multi-rotor UAV employing the quick release structure, an assembly for assembling a multi-rotor UAV, and a rotor assembly.

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. When 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.

Further, the quick release structure includes a joint and a mating portion detachably connected to the joint. 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.

Further, 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.

Further, the joint includes a sleeve structure, and the sleeve structure is provided with a groove for receiving the fitting portion.

Further, the shape and size of the groove are adapted to the shape and size of the fitting portion.

Further, 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.

Further, 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.

Further, the pin is made of a conductive material, and each of the pins is not electrically connected to each other.

Further, 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.

Further, 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.

Further, the number of the pin components is one or two.

Further, the quick release structure further includes a connection structure, and the connection structure is connected to the joint or the joint portion.

Further, 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.

Further, the connecting structure includes a bolt passing through the fixing plate, and the quick release structure is connected to the body through the bolt.

Further, 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.

Further, 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.

Further, 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.

Further, 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.

Further, 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.

Further, 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.

Further, the number of the pin components is one or two.

Further, 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:

body;

a plurality of rotor assemblies for providing flight power;

a plurality of quick release structures for connecting the rotor assembly and 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 fixed to the rotor a component, the fuselage connector is fixed to the body;

Wherein 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.

Further, 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.

Further, the preset angle is 180 degrees, so that the rotor assembly is installed upside down.

Further, each of the rotor assemblies includes a boom and a plurality of power units mounted on the arm.

Further, each of the power units includes a propeller and a motor that drives the rotation of the propeller.

Further, the working directions of the motors of the plurality of power units are the same.

Further, the working rotation directions of the motors of the plurality of power devices are opposite.

Further, the shape of the arm includes at least one of the following: T type, V type, U type, Y type, and X type.

Further, 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.

Further, the arm is a hollow structure, and the wire is electrically connected to the rotor connector through the inside of the arm.

Further, 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 .

Further, 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.

Further, 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.

Further, 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 .

Further, 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:

a fuselage having a fuselage connector;

a plurality of rotor assemblies for providing flight power; 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;

Wherein, 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.

Further, 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.

Further, the two rotor assemblies have the same structure.

Further, the structure of the two rotor assemblies is different.

Further, 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.

Further, the power unit includes a propeller and a motor that drives the rotation of the propeller.

Further, 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.

A rotor assembly for an unmanned aerial vehicle, comprising:

An arm for detachably connecting with an unmanned aircraft body; the 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; and

a rotor connector fixed to the connecting end of the arm and the fuselage;

The quick release structure of the present invention is capable of detachably connecting the rotor assembly to the air body. 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. In addition, when 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.

DRAWINGS

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.

Main component symbol description

多旋翼无人飞行器Multi-rotor unmanned aerial vehicle	100,300100,300
机身 body	1010
配合部 Matching department	1111
连接孔 Connection hole	111111
螺纹孔Threaded hole	1212
旋翼组件 Rotor assembly	2020
机臂Arm	21twenty one
连接臂 Connecting arm	211211
支撑臂 Support arm	212212
电机Motor	22twenty two
螺旋桨propeller	23twenty three
快拆结构 Quick release structure	200200
接头 Connector	3030
连接结构 Connection structure	301301
固定板 Fixed plate	3131
固定面 Fixed surface	311311
螺孔 Screw hole	3232
螺栓 bolt	3333
套筒结构 Sleeve structure	3434
凹槽 Groove	3535
引脚组件 Pin component	3636

The invention will be further illustrated by the following detailed description in conjunction with the accompanying drawings.

detailed description

Some embodiments of the present invention are described in detail below with reference to the accompanying drawings. The features of the embodiments and examples described below can be combined with each other without conflict.

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.

In some embodiments, the rotor connector is mechanically coupled and/or electrically coupled to the fuselage connector.

In some of these embodiments, 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. For example, the preset angle is 180 degrees such that the rotor assembly is mounted upside down.

In some of these embodiments, 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.

In some of these embodiments, the rotor connector is mechanically coupled and electrically coupled to the fuselage connector. For example, 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 coupled to the rotor connector.

In some of these embodiments, 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.

In some of these embodiments, the rotor connector is mechanically coupled and electrically coupled to the fuselage connector. For example, when the rotor assembly is mounted to the fuselage through the fuselage connector and the rotor connector, the fuselage connector is electrically coupled to the rotor connector.

Referring to FIG. 1 and FIG. 2 , a multi-rotor unmanned aerial vehicle 100 according to an embodiment of the present invention 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.

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. Specifically, in the illustrated embodiment, the rotor assembly 20 is provided with a rotor connector, and the body 10 is provided with an organic body connector. When the rotor assembly 20 is coupled to the body 10, 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. For example, when the rotor assembly 20 is mounted to the fuselage 10 through the fuselage connector and the rotor connector, the fuselage connector is electrically coupled to the rotor connector.

The manner in which the rotor connector is coupled to the fuselage connector can be designed according to different requirements. For example, in one embodiment, 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. In other embodiments, 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 specific structure of the rotor connector can also be designed according to different requirements. For example, 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 specific structure of the fuselage connector can also be designed according to different requirements. For example, 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.

Specifically, in the illustrated embodiment, 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. In this embodiment, 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. In this embodiment, 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.

Further, the body connector further includes a threaded hole 12 provided in the body 10. In this embodiment, 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. Specifically, in the illustrated embodiment, 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. For example, 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. Specifically, in the illustrated embodiment, 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. In this embodiment, 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. In this embodiment, 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. Specifically in the illustrated embodiment, 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. Specifically in the embodiment illustrated in FIG. 3, 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. One end of 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. In this embodiment, 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. 1 and 2, 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 In the phase line, 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.

It can be understood that in other embodiments, 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.

Specifically, in the embodiment shown in FIGS. 1 and 2, 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. In addition, when 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.

It can be understood that in other embodiments, 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. When 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. In addition, when 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.

In addition, those skilled in the art should understand that the above embodiments are only used to illustrate the invention and are not intended to limit the invention, as long as it is within the scope of the spirit of the invention, the appropriate changes to the above embodiments. And variations are within the scope of the claimed invention.

Claims

A multi-rotor unmanned aerial vehicle comprising a fuselage, a rotor assembly and a detachable quick release structure connecting the rotor assembly to the fuselage, wherein the quick release structure mechanically connects the rotor assembly to the aircraft 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 the plurality of the rotor assemblies at the connection position of the fuselage.
The multi-rotor unmanned aerial vehicle of claim 1 wherein the quick release structure includes a joint and a mating portion detachably coupled to the joint, the rotor assembly passing through the joint when the rotor assembly is coupled to the fuselage And the mating portion is electrically connected to the body.
The multi-rotor unmanned aerial vehicle according to claim 2, wherein one of the joint and the engaging portion is disposed on the fuselage and electrically connected to the fuselage, and the other is disposed on the rotor assembly. Electrically coupled to the rotor assembly.
A multi-rotor unmanned aerial vehicle according to claim 2, wherein the joint comprises a sleeve structure, and the sleeve structure is provided with a groove for receiving the fitting portion.
A multi-rotor unmanned aerial vehicle according to claim 4, wherein the shape and size of the recess are adapted to the shape and size of the mating portion.
The multi-rotor UAV according to claim 4, wherein the joint further comprises a lead assembly electrically connected to the body or the rotor assembly, the pin assembly being fixed to a bottom surface of the recess.
The multi-rotor UAV according to claim 6, wherein the lead assembly comprises three pins, and the three pins are used for respectively electrically connecting the three-phase lines of the three-phase power supply.
The multi-rotor unmanned aerial vehicle of claim 7 wherein the pins are made of a conductive material and each of the pins is non-conducting.
The multi-rotor unmanned aerial vehicle according to claim 7, wherein the engaging portion is provided with three connecting holes, and the three connecting holes are respectively used for electrically connecting the three-phase wires of the three-phase power source.
The multi-rotor UAV according to claim 9, wherein the positions of the three pins are respectively corresponding to the positions of the three connecting holes, and the three pins respectively penetrate the three connecting holes. The joint is electrically connected to the mating portion.
The multi-rotor unmanned aerial vehicle of claim 7 wherein the number of the pin assemblies is one or two.
The multi-rotor unmanned aerial vehicle of claim 2, wherein the quick release structure further comprises a connection structure, the connection structure being coupled to the joint or the mating portion.
The multi-rotor unmanned aerial vehicle according to claim 12, wherein the connecting structure comprises a fixing plate, 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 .
A multi-rotor unmanned aerial vehicle according to claim 13 wherein the attachment structure includes a bolt extending through the retaining plate, the quick release structure being coupled to the fuselage by the bolt.
The multi-rotor UAV according to claim 12, wherein the connecting structure comprises a fixing portion and a detachable connecting member connected to the fixing portion, the fixing portion is coupled to the body, the engaging member The rotor assembly is coupled to the fixing portion, and the engaging member abuts or disengages from the fixing portion, so that the detachable structure is in a locked state or a detachable state.
The multi-rotor unmanned aerial vehicle according to claim 15, wherein the joint is disposed on the fixing portion, the body or the engaging member; the engaging portion is disposed at the engaging member or the fixing portion, On the fuselage.
The multi-rotor unmanned aerial vehicle of claim 1 , wherein the rotor assembly comprises a arm coupled to the quick release structure, a motor fixedly coupled to the arm, and a propeller coupled to the motor, the motor The propeller is driven to rotate to provide flight power to the multi-rotor unmanned aerial vehicle.
The multi-rotor unmanned aerial vehicle according to claim 17, wherein the arm comprises 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; the supporting arm The two ends of the motor are fixedly connected to each other.
The multi-rotor unmanned aerial vehicle according to claim 18, wherein the number of the connecting arms is two, and the two connecting arms are fixed to the supporting arm at intervals, and one end of each connecting arm is fixedly connected to the supporting arm. The other end of the arm is connected to the quick release structure.
A quick release structure for detachably connecting a rotor assembly to a fuselage, characterized in that: when the quick release structure connects the rotor assembly to the fuselage, the rotor assembly passes the quick release structure and the machine The body forms an electrical connection; a plurality of the quick release structures are interchangeably connected to the plurality of the rotor assemblies at the connection position of the fuselage.
The quick release structure according to claim 20, wherein the quick release structure comprises a joint and a joint portion detachably connected to the joint, and when the rotor assembly is coupled to the fuselage, the rotor assembly passes through the joint and the joint The mating portion is electrically connected to the body.
The quick release structure according to claim 21, wherein one of the joint and the fitting portion is disposed on the fuselage and electrically connected to the fuselage, and the other is disposed on the rotor assembly and The rotor assembly is electrically connected.
The quick release structure according to claim 21, wherein the joint comprises a sleeve structure, and the sleeve structure is provided with a groove for receiving the fitting portion.
The quick release structure according to claim 23, wherein the shape and size of the groove are adapted to the shape and size of the fitting portion.
The quick release structure according to claim 23, wherein the joint further comprises a lead assembly electrically connected to the body or the rotor assembly, the pin assembly being fixed to a bottom surface of the recess.
The quick release structure according to claim 25, wherein the lead component comprises three pins, and the three pins are used for respectively electrically connecting the three-phase wires of the three-phase power supply.
The quick release structure according to claim 26, wherein the pin is made of a conductive material and each of the pins is non-conductive to each other.
The quick release structure according to claim 26, wherein the engaging portion is provided with three connecting holes, and the three connecting holes are respectively used for electrically connecting the three-phase wires of the three-phase power source.
The quick release structure according to claim 28, wherein 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, so that the The joint is electrically connected to the mating portion.
A quick release structure according to claim 25, wherein the number of the lead assemblies is one or two.
The quick release structure according to claim 21, wherein the quick release structure further comprises a connection structure, the connection structure being connected to the joint or the fitting portion.
The quick release structure according to claim 31, wherein 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.
A quick release structure according to claim 32, wherein the connecting structure includes a bolt passing through the fixing plate, and the quick release structure is coupled to the body by the bolt.
The quick release structure according to claim 31, wherein the connecting structure comprises a fixing portion and a detachable connecting member connected to the fixing portion, the fixing portion is coupled to the body, and the engaging member The rotor assembly is coupled to the fixing portion, and the latching member abuts or disengages from the fixing portion, so that the detachable structure is in a locked state or a detachable state.
The quick release structure according to claim 34, wherein the joint is disposed on the fixing portion, the body or the engaging member; and the corresponding engaging portion is disposed on the engaging member or the fixing portion, On the fuselage.
A multi-rotor unmanned aerial vehicle comprising:

body;

a plurality of rotor assemblies for providing flight power;

a plurality of quick release structures for connecting the rotor assembly and 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 fixed to the rotor a component, the fuselage connector is fixed to the body;

Wherein 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.
A multi-rotor unmanned aerial vehicle according to claim 36, wherein each of said rotor links is still rotatable about a predetermined angle about an axial direction of said rotor assembly, and is still engageable with said fuselage connecting member such that said rotor The assembly rotates the preset angle to mount the body.
A multi-rotor unmanned aerial vehicle according to claim 37, wherein the predetermined angle is 180 degrees such that the rotor assembly is mounted upside down.
A multi-rotor unmanned aerial vehicle according to claim 36, wherein each of said rotor assemblies includes a boom and a plurality of power units mounted on the arm.
A multi-rotor unmanned aerial vehicle according to claim 39, wherein each of said power units includes a propeller and a motor that drives the rotation of the propeller.
A multi-rotor unmanned aerial vehicle according to claim 39, wherein the motors of the plurality of power units on each of the arms are operated in the same direction of rotation.
A multi-rotor unmanned aerial vehicle according to claim 39, wherein the motors of the plurality of power units on each of the arms are operated in opposite directions of rotation.
The multi-rotor unmanned aerial vehicle according to claim 39, wherein the shape of the arm comprises at least one of the following: T-shaped, V-shaped, U-shaped, Y-shaped, and X-shaped.
A multi-rotor unmanned aerial vehicle according to claim 39, wherein the arm includes a plurality of connecting ends, one of which is for connecting the rotor link, and the other of which is for mounting the power unit.
A multi-rotor unmanned aerial vehicle according to claim 39, wherein the arm is of a hollow structure, and the wire is electrically connected to the rotor link through the inside of the arm.
A multi-rotor UAV according to claim 36, wherein the rotor connector includes a mechanical connection and an electrical connection, the body connector including a mechanical mating portion for coupling with the mechanical connection, And an electrical mating portion for coupling to the electrical connection.
A multi-rotor unmanned aerial vehicle according to claim 36, wherein the rotor connecting member and the body connecting member are both conductive members, so that the rotor connecting member and the body connecting member are mechanically coupled, Electrical coupling.
The multi-rotor UAV according to claim 36, wherein 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 multi-rotor unmanned aerial vehicle according to claim 36, wherein 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 member, and an engaging groove. Engagement hole, threaded connection, threaded hole, fitting.
A multi-rotor UAV according to claim 36, wherein 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:

a fuselage having a fuselage connector;

a plurality of rotor assemblies for providing flight power; 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 Coupling and electrical coupling;

Wherein, 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.
The assembly of claim 51 wherein one of the rotor assemblies of the rotor assembly is engageable with another fuselage connector corresponding to the rotor assembly such that the two rotor assemblies are coupled to the body The locations are interchangeable.
The assembly of claim 52 wherein the two rotor assemblies are identical in construction.
The assembly of claim 52 wherein the two rotor assemblies are structurally different.
The assembly of claim 51 wherein the rotor link is still rotatable about a predetermined angle about the axial direction of the rotor assembly and is still engageable with the body connector such that the rotor assembly rotates the predetermined angle Installed in the fuselage.
The assembly of claim 55 wherein the predetermined angle is 180 degrees such that the rotor assembly is mounted upside down.
The assembly of claim 51 wherein each of said rotor assemblies includes a boom and a plurality of power units mounted to the arm.
The assembly of claim 57 wherein the power unit includes a propeller and a motor that drives the rotation of the propeller.
The assembly of claim 57 wherein the motors of the plurality of power units operate in the same direction of rotation.
The assembly of claim 57 wherein the motors of the plurality of power units operate in opposite directions of rotation.
The assembly of claim 57 wherein the shape of the arm comprises at least one of the following: a T shape, a V shape, a U shape, a Y shape, and an X shape.
The assembly of claim 57 wherein the arm includes a plurality of connectors, one of which is for connecting the rotor connector and the other of which is for mounting the power unit.
The assembly of claim 57 wherein the arm is a hollow structure and the wires are electrically connected to the rotor connector through the interior of the arm.
The assembly of claim 51 wherein the rotor link includes a mechanical connection and an electrical connection, the body connection including a mechanical mating portion for coupling with the mechanical connection, and for The electrical connection portion is coupled to the electrical mating portion.
The assembly of claim 51 wherein the rotor connector and the body connector are electrically conductive members such that the rotor connector is mechanically coupled to the body connector while being mechanically coupled.
The assembly according to claim 51, wherein the rotor connector is provided with at least one of the following: an insert, an insertion slot, an insertion hole, a snap member, a snap member, an engaging groove, a snap hole, and a thread. Connecting parts, threaded holes, fittings.
The assembly according to claim 51, wherein 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 member, an engaging groove, and an engaging hole. Threaded joints, threaded holes, fittings.
A rotor assembly for an unmanned aerial vehicle, comprising:

An arm for detachably connecting with an unmanned aircraft body; the 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; and

a rotor connector fixed to the connecting end of the arm and the fuselage;

Wherein 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.
A rotor assembly according to claim 68, wherein the rotor link is still rotatable about a predetermined angle about the axial direction of the rotor assembly, and is still engageable with the body connector such that the rotor assembly rotates the preset The angle is mounted on the fuselage.
The rotor assembly of claim 69 wherein the predetermined angle is 180 degrees such that the rotor assembly is mounted upside down.
A rotor assembly according to claim 68, wherein the shape of the arm comprises at least one of the following: a T shape, a V shape, a U shape, a Y shape, and an X shape.
The rotor assembly of claim 68 wherein the arm is a hollow structure and the wire is electrically connected to the rotor connector through the interior of the arm.
A rotor assembly according to claim 68, wherein the rotor link includes a mechanical connection and an electrical connection, the body connection including a mechanical mating portion for coupling with the mechanical connection, and An electrical mating portion coupled to the electrical connection.
The rotor assembly of claim 68 wherein the rotor link and the fuselage connector are electrically conductive members such that the rotor connector is mechanically coupled to the body connector while being mechanically coupled.
The rotor assembly according to claim 68, wherein 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 an engaging hole. Threaded joints, threaded holes, fittings.
The rotor assembly according to claim 68, wherein 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 member, an engaging groove, and an engaging hole. , threaded connection, threaded hole, fitting.