CN112455648A

CN112455648A - Unmanned aerial vehicle

Info

Publication number: CN112455648A
Application number: CN201910857086.2A
Authority: CN
Inventors: 接柏皓; 崔少华
Original assignee: Suzhou Zhendi Intelligent Technology Co Ltd
Current assignee: Suzhou Zhendi Intelligent Technology Co Ltd
Priority date: 2019-09-09
Filing date: 2019-09-09
Publication date: 2021-03-09

Abstract

The invention relates to the technical field of unmanned aerial vehicles, and discloses an unmanned aerial vehicle, which comprises a vehicle body and a plurality of vehicle arm assemblies arranged on the vehicle body; each horn component comprises a horn, a propeller arranged on the horn and a driving device for driving the propeller to rotate; the machine arm is provided with a connecting end, the machine body is provided with a machine body interface matched with the connecting end, and the connecting end is arranged in the machine body interface in a pluggable manner; along the plug direction, the link is equipped with the first plug of being connected with drive arrangement, is equipped with the first interface with first plug complex on the inner wall of fuselage interface, and when the link inserted the fuselage interface, first plug was connected with first interface electricity. In the above embodiment, the pluggable connected mode of horn and fuselage has made things convenient for depositing and shifting of unmanned aerial vehicle.

Description

Unmanned aerial vehicle

Technical Field

The invention relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle.

Background

In recent years, the unmanned aerial vehicle technology in China is rapidly developed, and the application of the unmanned aerial vehicle is more and more extensive. For example, in agriculture, the unmanned aerial vehicle can carry out spraying operation, or can carry out accurate control on agricultural production through carrying sensor to field crop growth information detection, soil moisture nutrition condition analysis, and the unmanned aerial vehicle can accomplish the task that the mankind is difficult to accomplish.

Among the prior art, unmanned aerial vehicle's fuselage and horn are mostly a body structure, are used for driving screw pivoted drive device on the horn to pass through the circuit and directly be connected with power and flight controller on the fuselage, but, unmanned aerial vehicle wholly occupies when not using space great to inconvenient depositing and shifting, the horn also takes place to collide with and lead to damaging with around object easily.

Disclosure of Invention

The invention provides an unmanned aerial vehicle, which is used for solving the problems that the whole unmanned aerial vehicle in the prior art occupies a large space and is inconvenient to store and transfer.

The embodiment of the invention provides an unmanned aerial vehicle, which comprises a body and a plurality of horn assemblies arranged on the body; wherein:

each horn assembly comprises a horn, a propeller arranged on the horn and a driving device for driving the propeller to rotate;

the machine arm is provided with a connecting end, the machine body is provided with a machine body interface matched with the connecting end, and the connecting end is arranged in the machine body interface in a pluggable manner;

along the plug direction, the link be equipped with the first plug that drive arrangement connects, be equipped with on the inner wall of fuselage interface with first plug complex first interface, work as the link inserts during the fuselage interface, first plug with first interface electricity is connected.

In the embodiment, the horn is arranged on the machine body in a pluggable manner, and when the horn is not used, the horn can be pulled out to separate the horn from the machine body, so that the whole occupied area is reduced, and the storage or transfer is facilitated; when the propeller needs to be used, the machine arm is inserted into the machine body, and the first plug is electrically connected with the first interface, so that the driving equipment drives the propeller to rotate.

Optionally, the unmanned aerial vehicle further comprises a flight controller arranged on the fuselage;

the first interface is connected with the flight controller.

Optionally, the body comprises a body main body and a shell arranged on the body main body, and the body main body is detachably and fixedly connected with the shell;

the machine body interface comprises a notch positioned on the machine body main body, and the first interface is arranged on the inner wall of the notch; when the shell is fixed on the machine body, the shell compresses the connecting end.

Optionally, the first interface is located on the bottom wall of the gap facing the housing, and the first plug is inserted into the first interface along a direction perpendicular to the horn.

Optionally, at least one side wall of the notch is provided with a first protrusion along the plugging direction, and the corresponding side wall of the connecting end is provided with a first clamping groove matched with the first protrusion;

or, the gap is provided with a first clamping groove on at least one side wall along the plugging direction, and the connecting end is provided with a first bulge matched with the first clamping groove on the corresponding side wall.

Optionally, one side of the shell, which compresses the connecting end, is provided with a second protrusion, and a second clamping groove matched with the second protrusion is formed in the corresponding side wall of the connecting end;

or, the shell compresses tightly the one side of link is equipped with the second draw-in groove, the link be equipped with on the lateral wall that corresponds with second draw-in groove complex second is protruding.

Optionally, an antenna is arranged on the body and used for communication connection between the unmanned aerial vehicle and the outside.

Optionally, along the plug direction, the link is equipped with the second plug that is used for connecting the antenna, be equipped with on the inner wall of fuselage interface with second plug complex second interface.

Optionally, at least one of the arms is provided with an antenna, and the antenna is connected to the communication module on the body through a corresponding second plug and a second interface.

Optionally, at least one of the horn and the body is provided with an antenna, and the antenna on the horn is connected to the antenna on the body through a corresponding second plug and a second interface.

Optionally, be equipped with the antenna on fuselage and at least one horn respectively, and to the horn that is provided with the antenna, along the plug direction, the link be equipped with the second plug of antenna connection, be equipped with on the inner wall of fuselage interface with second plug complex second interface. The antenna on the body and the antenna on the horn may interact.

Optionally, the portable electronic device further comprises a waterproof shell, the waterproof shell covers the surface of the body, the waterproof shell is provided with a connecting hole matched with the connecting end, and the connecting end penetrates through the connecting hole and then is inserted into the body.

For preventing the rainwater from getting into inside the waterproof case from the gap between connecting hole and the horn, connecting hole department is equipped with the sealing ring, the sealing ring is formed by elastic material preparation, just the internal diameter size of sealing ring is less than the external diameter size of link. When the connecting end of the horn passes through the sealing ring, the sealing ring is elastically deformed and tightly attached to the surface of the connecting end, so that rainwater is prevented from entering the interior of the horn from a gap.

This unmanned aerial vehicle is still including setting up cloud platform on the fuselage acquires the image for making things convenient for the cloud platform, waterproof housing include with the cloud platform corresponds the transparent part that sets up.

Optionally, the fuselage body comprises a frame comprising at least a first substructure and a second substructure connected at an angle.

Optionally, the rack further includes a third substructure, and the second substructure is connected to the third substructure at an angle;

first substructure, second substructure and third substructure connect gradually, first substructure with the second substructure encloses to become to be located the first accommodation space of first substructure below, the second substructure with the third substructure encloses to become to be located the second accommodation space of third substructure top, just first accommodation space with the second accommodation space is located respectively the both sides of second substructure.

Optionally, the mobile phone further comprises a cradle head and a battery assembly, wherein a battery jar is arranged on one side of the third substructure, which faces the second accommodating space, and the battery assembly is arranged in the battery jar;

the holder is fixed on the first substructure and is located in the first accommodating space.

Optionally, a fan is disposed on the second substructure, an airflow passage communicated with the fan and a heating element disposed along the airflow passage are disposed in the third substructure, an air outlet communicated with the airflow passage is disposed on a surface of the third substructure, and air sucked by the fan flows along the airflow passage and is discharged from the air outlet.

Optionally, the air conditioner further comprises a waterproof housing arranged on the surface of the body, a heat dissipation part is arranged at a position of the waterproof housing corresponding to the air outlet, an airflow loop is formed in a gap between the body and the waterproof housing, and airflow flowing out of the air outlet and the heat dissipation part are subjected to heat exchange and then are sucked into the interior of the airflow loop through the fan.

Optionally, the robot further comprises auxiliary equipment, the auxiliary equipment is provided with an end part matched with the machine body interface, and when the machine body is pulled out from the machine arm, the end part on the auxiliary equipment can be arranged in the machine body interface in a pluggable mode.

Each horn comprises a horn body and a connecting body arranged on the horn body, and the connecting end is positioned on the connecting body;

the plurality of horn assemblies are pairwise grouped to form at least one pair of horn assemblies, and in each pair of horn assemblies, two horn bodies share one connecting body.

Furthermore, in each pair of horn assemblies, at least one horn body is rotatably connected with the connecting body, and when the horn body rotatably connected with the connecting body rotates relative to the connecting body, the two horn bodies are closed or opened.

The embodiment of the invention also provides an unmanned aerial vehicle, which comprises a body, a machine arm component arranged on the body and a frame;

the frame includes at least a first substructure and a second substructure connected at an angle.

In the above embodiment, the components on the unmanned aerial vehicle may be disposed on these substructures, or disposed in the accommodation space enclosed by these substructures, so that the fuselage may be more compact, and the volume of the fuselage may be reduced.

the first substructure, the second substructure and the third substructure are connected in sequence, the first substructure and the second substructure enclose to be located a first accommodation space below the first substructure, the second substructure and the third substructure enclose to be located a second accommodation space above the third substructure, and the first accommodation space and the second accommodation space are respectively located on two sides of the second substructure.

Optionally, the first accommodating space and the second accommodating space are respectively provided with components on the unmanned aerial vehicle according to the size of the space.

Optionally, still include cloud platform and battery pack, wherein:

a battery groove is formed in one side, facing the second accommodating space, of the third substructure, and the battery assembly is arranged in the battery groove;

Drawings

Fig. 1 is a schematic view of an overall structure of an unmanned aerial vehicle according to an embodiment of the present invention;

fig. 2 is a schematic structural diagram of a fuselage of the unmanned aerial vehicle provided in the embodiment of the present invention;

fig. 3 is a schematic structural diagram of a frame of an unmanned aerial vehicle according to an embodiment of the present invention;

fig. 4 is a schematic view of a top view structure of a horn of the unmanned aerial vehicle provided in the embodiment of the present invention;

fig. 5 is a schematic view of a bottom view of a boom of the unmanned aerial vehicle according to the embodiment of the present invention;

fig. 6 is a schematic structural diagram of a waterproof housing of an unmanned aerial vehicle according to an embodiment of the present invention.

Reference numerals:

10-fuselage

11-fuselage body

110-notch 111-frame

1111-first substructure 1112-second substructure

1113-third substructure

12-shell

20-arm assembly 21-arm 22-propeller

210-connecting end 211-horn body 212-connecting body

211 a-first arm body 211 b-second arm body

30-Battery Assembly 40-cradle head

50 a-first plug 50 b-first interface

50 c-second plug 50 d-second interface

60 a-first projection 60 b-first slot

70-Fan

80-Water-proof case

81-Heat sink 82-attachment hole

Detailed Description

In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be described in further detail with reference to the accompanying drawings, and it is apparent that the described embodiments are only a part of the embodiments of the present invention, not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

The embodiment of the invention provides an unmanned aerial vehicle, wherein a horn is connected to a body in a pluggable manner, so that the horn can be pulled out of the body in the storage and transfer processes, and the space occupied by the whole unmanned aerial vehicle is reduced.

Specifically, the unmanned aerial vehicle comprises a vehicle body and a plurality of vehicle arm assemblies arranged on the vehicle body; wherein,

each horn component comprises a horn, a propeller arranged on the horn and a driving device for driving the propeller to rotate;

along the plug direction, the link is equipped with the first plug of being connected with drive arrangement, be equipped with on the inner wall of fuselage interface with first plug complex first interface, when the link inserts the fuselage interface, first plug is connected with first interface electricity.

In the embodiment, the horn is arranged on the body in a pluggable manner, and after the unmanned aerial vehicle finishes working, the horn can be pulled out to separate the horn from the body, so that the overall occupied space is reduced, and the unmanned aerial vehicle is convenient to store or transfer; when need use unmanned aerial vehicle to develop the during operation, insert the horn and locate on the fuselage, first plug is connected with first interface electricity this moment to drive equipment drive screw rotates, and the adjustment running state.

In order to more clearly understand the structure of the unmanned aerial vehicle provided by the embodiment of the present invention, a detailed description is given with reference to the accompanying drawings.

Referring to fig. 1, 4 and 5 together, the unmanned aerial vehicle includes a fuselage 10 and a plurality of horn assemblies 20 disposed on the fuselage 10, wherein each horn assembly 20 includes a horn 21, a propeller 22 disposed on the horn 21, and a driving device for driving the propeller 22 to rotate; be equipped with link 210 on horn 21, be equipped with on the fuselage 10 with link 210 complex fuselage interface, but link 210 pluggable sets up in the fuselage interface, along the plug direction, link 210 is equipped with the first plug 50a of being connected with drive arrangement, is equipped with on the inner wall of fuselage interface with first plug 50a complex first interface 50b, when link 210 inserts the fuselage interface, first plug 50a is connected with first interface 50b electricity. After the unmanned aerial vehicle finishes working, the horn 21 can be pulled out, so that the horn 21 is separated from the body 10, and the space occupied by the whole unmanned aerial vehicle is reduced, and the unmanned aerial vehicle is convenient to store or transfer; when the unmanned aerial vehicle is required to be used for carrying out work, the horn 21 is inserted into the body 10, and the first plug 50a is electrically connected with the first interface 50 b. Specifically, the unmanned aerial vehicle further includes a flight controller disposed on the fuselage 10, the first interface 50b is connected to the flight controller, when the horn 21 is inserted into the fuselage 10, the driving device is connected to the flight controller, the flight controller is configured to send a control instruction to the driving device, and the driving device drives the propeller 22 to rotate according to the corresponding control instruction. In addition, the unmanned aerial vehicle further comprises a battery assembly 30 arranged on the body 10, the first interface 50b is connected with the battery assembly 30, and when the horn 21 is inserted into the body 10, the battery assembly 30 can supply power for the driving device.

In addition, the device also comprises auxiliary equipment, wherein the auxiliary equipment is provided with an end part matched with the machine body interface, and when the machine arm 21 is pulled out of the machine body 10, the end part on the auxiliary equipment can be arranged in the machine body interface in a pluggable mode. The auxiliary equipment comprises a support, a power supply and the like, for example, after the horn 21 is pulled out of the machine body 10, the end part of the support is inserted into a machine body interface in the machine body 10, and the support plays a role in supporting the machine body 10, at the moment, shooting can be carried out through a camera arranged on the machine body 10, and thus multifunctional utilization is realized; alternatively, an external power source may be plugged into an interface within the body interface so that the battery assembly 30 may be recharged. Therefore, the body interface on the body 10 not only can fix the arm 21, but also can be connected with some external devices, integrates multiple functions, and has higher practicability.

In order to enable the unmanned aerial vehicle to be in communication connection with the outside, an antenna is arranged on the body 10 and connected with the communication module; alternatively, the antenna may be provided on the horn 21 to compress the volume of the body. In the latter arrangement, for each horn 21 and the body interface matched with the connection end 210 on the horn 21, along the plugging direction, the connection end 210 is provided with a second plug 50c for connecting an antenna, the inner wall of the body interface is provided with a second interface 50d matched with the second plug 50c, the second interface 50d is connected with the communication module on the body 21, and when the horn 21 is inserted into the body 10, the second plug 50c is electrically connected with the second interface 50 d. Specifically, an antenna is disposed on at least one of the booms 21, that is, an antenna may be disposed on one of the booms 21, or an antenna may be disposed on one or more of the booms 21, and the antenna is connected to a communication module on the body 21 through a corresponding second plug 50c and a second interface 50d, and the communication module is connected to the flight controller. The antennas can also be arranged on at least one of the arms 21 and the body 10, the antennas on the arms 21 are connected with the antennas on the body 10 through the corresponding second plugs 50c and the second interfaces 50d, the antennas on the arms 21 and the body 10 can be switched according to the distance of the flight distance and the requirement of data transmission when in use, and the antennas on the body 10 can still meet the function of user data transmission when the arms 21 are pulled out of the body 10.

In the specific arrangement, in each horn assembly 20, the horns 21 may be independently and detachably arranged on the fuselage 10, or two horns 21 may also be a group, share one connecting end 210, and be inserted into the same fuselage interface, in the latter form, specifically, each horn 21 includes a horn body 211 and a connecting body 212 arranged on the horn body 211, and the connecting end 210 is located on the connecting body 212; the plurality of horn assemblies 20 form at least one pair of horn assemblies 20 in pairs, in each pair of horn assemblies 20, two horn bodies 211 share one connecting body 212 and share one pair of plugs and interfaces, and the driving device on each horn 21 is connected with the battery assembly 30 and the flight controller through the shared pair of plugs and interfaces, so that the number of the interfaces and the body on the body 10 is reduced, the size of the unmanned aerial vehicle body 10 is reduced, and the structure is simpler. Further, in each pair of the horn assemblies 20, at least one horn body 211 is rotatably connected to the connecting body 212, and when the horn body 211 rotatably connected to the connecting body 212 rotates relative to the connecting body, the two horn bodies 211 are closed or opened; wherein, both the two arm bodies 211 can rotate relative to the connecting body 212, or, one of the arm bodies 211 is fixedly connected with the connecting body 212, and the other arm body 211 is rotatably connected with the connecting body 212, as shown in fig. 4 and 5, the pair of arm assemblies 20 adopts the latter form, the two arm bodies 211 are respectively a first arm body 211a and a second arm body 211b, the first arm body 211a is fixedly connected with the connecting body 212, and the second arm body 211b is rotatably connected with the connecting body 212, after the unmanned aerial vehicle finishes working, the second arm body 211b is rotated to a side close to the first arm body 211a until an included angle between the second arm body 211b and the first arm body 211a is zero, at this time, the connecting body is pulled out, because the second arm body 211b is closed with the first arm body 211a, the space occupied by the pair of arm assemblies 20 is compressed, the storage and the transfer are convenient; when the arm is used, the second arm body 211b is rotated in the opposite direction until the second arm body 211b and the first arm body 211a are opened to a set angle.

The whole body 10 is curved to reduce air resistance, as shown in fig. 2, the body 10 includes a body 11 and a housing 12 disposed on the body 11, the body 11 and the housing 12 are detachably connected, for example, by fastening screws, fastening slots, etc.; the body interface includes a notch 110 on the body 11, and the first interface 50b is disposed on the inner wall of the notch 110; inserting the connecting end 210 of the horn 21 into the notch 110, pressing the housing 12 against the connecting end 210, and finally fixing the housing 12 on the body 11, and fixing the horn 21 inserted in the notch 110 by pressing the body 10 against the housing 12, in other words, when fixing the housing 12 on the body 11, the notch 110 on the body 11 and the side of the housing 12 pressing against the connecting end 210 form the body interface. Specifically, the connecting end 210 may be inserted into the gap 110 along the direction of the horn 21, or may be inserted into the gap 110 along the direction perpendicular to the horn 21, in the latter form, as shown in fig. 2, the first interface 50b is disposed on the bottom wall of the gap 110 facing the housing 12. In addition, in order to enhance the stability, at least one side wall of the notch 110 is provided with a first protrusion 60a along the plugging direction, and the corresponding side wall of the connecting end 210 is provided with a first slot 60b matched with the first protrusion 60 a; or, at least one side wall of the notch 110 is provided with a first engaging groove along the inserting/pulling direction, and the connecting end 210 is provided with a first protrusion on the corresponding side wall for engaging with the first engaging groove. The first engaging groove 60b is a dovetail groove, and when the connecting end 210 is inserted into the notch 110, the first protrusion 60a slides into the first engaging groove 60b, thereby enhancing the connection between the horn 21 and the body 10. In addition to the matching between the protrusion and the slot between the notch 110 and the connection end 210, a similar structure may be provided between the housing 12 and the connection end 210, specifically, a second protrusion is provided on one side of the housing 12 for pressing the connection end 210, and a second slot matched with the second protrusion is provided on the corresponding side wall of the connection end 210; or, the one side that casing 12 compressed tightly link 210 is equipped with the second draw-in groove, link 210 be equipped with on the lateral wall that corresponds with second draw-in groove complex second protruding, when fixing casing 12 on fuselage main part 11, the second is protruding to be injectd in the second draw-in groove to play the fixed action to horn 21, avoid horn 21 shake in the flight. Referring to fig. 2, 4 and 5, the first interface 50b is disposed on the bottom wall of the notch 110 facing the housing 12, the first plug 50a on the connection end 210 is inserted into the first interface 50b in a direction perpendicular to the horn 21 or perpendicular to the bottom wall of the notch 110, the three side walls of the notch 110 are respectively provided with a first protrusion 60a along the inserting and pulling direction, one surface of the housing 12 for pressing the connection end 210 is provided with a second protrusion, and the connection end 210 of the horn 21 is provided with a first card slot 60b matched with the first protrusion 60a and a second card slot matched with the second protrusion on the corresponding side wall.

Fuselage main part 11 includes frame 111 and sets up the shell on frame 111, and frame 111 includes at least first substructure and the second substructure that connects with certain angle, and the last part of unmanned aerial vehicle can set up on these substructures, or sets up in the accommodation space who is enclosed by these substructures. In a specific embodiment, the rack comprises a first substructure and a second substructure, the first substructure and the second substructure are fixedly connected, and an included angle between the first substructure and the second substructure is a right angle, and the first substructure and the second substructure enclose an accommodating space for accommodating the electronic component. In another specific embodiment, as shown in fig. 3, the device further includes a third sub-structure 1113, the second sub-structure 1112 is connected to the third sub-structure 1113 at an angle, the first sub-structure 1111, the second sub-structure 1112 and the third sub-structure 1113 are connected in sequence, the first sub-structure 1111 and the second sub-structure 1112 enclose a first accommodating space located below the first sub-structure 1111, the second sub-structure 1112 and the third sub-structure 1113 form a second accommodating space located above the third sub-structure 1113, and the first accommodating space and the second accommodating space are respectively located at two sides of the second sub-structure 1112, so that the first sub-structure 1111, the second sub-structure 1112 and the third sub-structure 1113 form a rack similar to a zigzag shape. In the first accommodation space with be provided with the part on the unmanned aerial vehicle respectively according to the space size in the second accommodation space, wherein, unmanned aerial vehicle includes battery pack 30 and cloud platform, third substructure 1113 is equipped with the battery jar towards one side of second accommodation space, battery pack 30 sets up in the battery jar, cloud platform 40 is fixed on first substructure 1111, and be located first accommodation space, in addition, can be with the GPS module on the unmanned aerial vehicle, IMU module etc. set up in first substructure 1111, and with control circuit, sensor etc. set up in third substructure 1113, thus, the volume of fuselage 10 has been compressed to the zigzag frame, also make overall structure compacter. With continued reference to fig. 3, the angle between the first sub-structure 1111 and the second sub-structure 1112 is a right angle, the angle between the second sub-structure 1112 and the third sub-structure 1113 is a right angle, and the first sub-structure 1111 and the second sub-structure 1112, and the second sub-structure 1112 and the third sub-structure 1113 may be connected at other angles, which will not be described in detail herein.

In order to facilitate heat dissipation of the heating element inside the main body 10, the second substructure 1112 is provided with the fan 70, the third substructure 1113 is provided with an airflow passage communicated with the fan 70 and the heating element arranged along the airflow passage, the housing of the third substructure 1113 is provided with an air outlet communicated with the airflow passage, air sucked by the fan 70 flows along the airflow passage and is exhausted from the air outlet, and during the flowing process of the air along the airflow passage, the air exchanges heat with the heating element and takes away most of heat, so that the temperature of the heating element is reduced. When the waterproof casing 80 is disposed on the surface of the body 10, as shown in fig. 6, in order to avoid that the temperature inside the body 10 is too high and affects the normal operation of the electronic components, the waterproof casing 80 is disposed with a heat dissipation member 81 at a position corresponding to the air outlet, an airflow loop is formed in the gap between the body 10 and the waterproof casing 80, and the airflow flowing out from the air outlet is heat-exchanged with the heat dissipation member 81 and then sucked into the interior along the airflow loop by the fan 70 again to form a circulation. Specifically, the heat dissipation member 81 is a metal heat dissipation fin, and rainwater, cold air, and the like in the external environment exchange heat with the metal heat dissipation fin to continuously absorb heat of the metal heat dissipation fin, so as to cool the metal heat dissipation fin, that is, heat generated by the heating element in the body 10 is sequentially transferred to the external environment through the internal airflow and the metal heat dissipation fin.

As shown in fig. 6, the waterproof case 80 is provided with a connection hole 82 which is matched with a connection end 210 of the horn 21, and the connection end 210 is inserted into the body 10 after passing through the connection hole 82. Waterproof housing 80 keeps apart fuselage 10 and external environment, prevents inside the rainwater from soaking fuselage 10 to guaranteed the normal work of unmanned aerial vehicle in sleet weather. Further, the waterproof housing 80 is provided with a sealing ring at the connection hole 82, the sealing ring is made of an elastic material, and the inner diameter of the sealing ring is smaller than the outer diameter of the connection end 210. When the connection end 210 of the horn 21 passes through the sealing ring, the sealing ring is elastically deformed and closely attached to the surface of the connection end 210, thereby preventing rainwater from entering the inside from a gap. In addition, in order to facilitate the pan/tilt head 40 to acquire images, the waterproof housing 80 includes a transparent portion disposed corresponding to the pan/tilt head 40.

The embodiment of the invention also provides an unmanned aerial vehicle, as shown in fig. 1, the unmanned aerial vehicle comprises a body 10, a horn assembly 20 arranged on the body 10, and a frame, wherein the frame at least comprises a first substructure and a second substructure which are connected at a certain angle. The last part of unmanned aerial vehicle can set up on these substructures, or set up in the accommodation space who is enclosed by these substructures to can make the fuselage compacter, compressed the volume of fuselage.

In a specific embodiment, the rack comprises a first substructure and a second substructure, the first substructure and the second substructure are fixedly connected, and an included angle between the first substructure and the second substructure is a right angle, and the first substructure and the second substructure enclose an accommodating space for accommodating the electronic component. In another specific embodiment, as shown in fig. 3, the device further includes a third sub-structure 1113, the second sub-structure 1112 is connected to the third sub-structure 1113 at an angle, the first sub-structure 1111, the second sub-structure 1112 and the third sub-structure 1113 are connected in sequence, the first sub-structure 1111 and the second sub-structure 1112 enclose a first accommodating space located below the first sub-structure 1111, the second sub-structure 1112 and the third sub-structure 1113 form a second accommodating space located above the third sub-structure 1113, and the first accommodating space and the second accommodating space are respectively located at two sides of the second sub-structure 1112, so that the first sub-structure 1111, the second sub-structure 1112 and the third sub-structure 1113 form a rack similar to a zigzag shape.

In the first accommodation space with be provided with the part on the unmanned aerial vehicle respectively according to the space size in the second accommodation space, wherein, unmanned aerial vehicle includes battery pack 30 and cloud platform, third substructure 1113 is equipped with the battery jar towards one side of second accommodation space, battery pack 30 sets up in the battery jar, cloud platform 40 is fixed on first substructure 1111, and be located first accommodation space, in addition, can be with the GPS module on the unmanned aerial vehicle, IMU module etc. set up in first substructure 1111, and with control circuit, sensor etc. set up in third substructure 1113, thus, the volume of fuselage 10 has been compressed to the zigzag frame, also make overall structure compacter. With continued reference to fig. 3, the angle between the first sub-structure 1111 and the second sub-structure 1112 is a right angle, the angle between the second sub-structure 1112 and the third sub-structure 1113 is a right angle, and the first sub-structure 1111 and the second sub-structure 1112, and the second sub-structure 1112 and the third sub-structure 1113 may be connected at other angles, which will not be described in detail herein.

As can be seen from the above description, the unmanned aerial vehicle provided by the embodiment of the invention facilitates the storage and transfer of the unmanned aerial vehicle by the pluggable connection mode of the horn and the body, and the body interface on the body can also be connected with auxiliary equipment such as a bracket and the like, so that the practicability is enhanced; in addition, a waterproof shell can be arranged outside the machine body to adapt to weather such as rain, snow and the like.

It will be apparent to those skilled in the art that various changes and modifications may be made in the present invention without departing from the spirit and scope of the invention. Thus, if such modifications and variations of the present invention fall within the scope of the claims of the present invention and their equivalents, the present invention is also intended to include such modifications and variations.

Claims

1. An unmanned aerial vehicle is characterized by comprising a body and a plurality of horn assemblies arranged on the body;

2. The drone of claim 1, further comprising a flight controller disposed on the fuselage;

the first interface is connected with the flight controller.

3. The unmanned aerial vehicle of claim 1, wherein the fuselage comprises a fuselage body and a housing disposed on the fuselage body, the fuselage body being removably connected with the housing;

4. The unmanned aerial vehicle of claim 3, wherein the first interface is disposed on a bottom wall of the gap facing the housing, and the first plug is inserted into the first interface in a direction perpendicular to the horn.

5. An unmanned aerial vehicle as claimed in claim 3, wherein the gap has at least one side wall provided with a first protrusion along the plugging direction, and the connecting end is provided with a first slot on the corresponding side wall, the first slot being matched with the first protrusion;

6. The unmanned aerial vehicle of claim 3, wherein one side of the shell used for pressing the connecting end is provided with a second protrusion, and the connecting end is provided with a second clamping groove matched with the second protrusion on the corresponding side wall;

7. An unmanned aerial vehicle as claimed in claim 1, wherein the fuselage is provided with an antenna for communication connection between the unmanned aerial vehicle and the outside.

8. An unmanned aerial vehicle as claimed in claim 1, wherein along the plug direction, the link is provided with a second plug for connecting the antenna, and the inner wall of the fuselage interface is provided with a second interface matched with the second plug.

9. An unmanned aerial vehicle as claimed in claim 8, wherein at least one of the horn is provided with an antenna, and the antenna is connected with the communication module on the fuselage through a corresponding second plug and a second interface.

10. An unmanned aerial vehicle as claimed in claim 8, wherein at least one of the horn and the fuselage is provided with an antenna, and the antenna on the horn and the antenna on the fuselage are connected through a corresponding second plug and a second interface.

11. The unmanned aerial vehicle of claim 1, further comprising a waterproof housing, wherein the waterproof housing covers a surface of the fuselage, and the waterproof housing is provided with a connecting hole matched with the connecting end, and the connecting end passes through the connecting hole and then is inserted into the fuselage.

12. An unmanned aerial vehicle as claimed in claim 11, wherein a sealing ring is provided at the connecting hole, the sealing ring is made of elastic material, and an inner diameter of the sealing ring is smaller than an outer diameter of the connecting end.

13. An unmanned aerial vehicle as defined in claim 11, further comprising a pan/tilt head disposed on the fuselage, the waterproof housing including a transparent portion disposed in correspondence with the pan/tilt head.

14. The drone of claim 3, wherein the fuselage body includes a frame including at least a first substructure and a second substructure connected at an angle.

15. The drone of claim 14, wherein the chassis further includes a third substructure, and the second substructure is connected at an angle to the third substructure;

16. The drone of claim 15, further comprising a cradle head and a battery assembly, wherein,

17. An unmanned aerial vehicle as claimed in claim 15, wherein a fan is provided on the second substructure, an airflow passage communicating with the fan and a heating element provided along the airflow passage are provided in the third substructure, and an air outlet communicating with the airflow passage is provided on a housing of the third substructure, and air sucked by the fan flows along the airflow passage and is discharged from the air outlet.

18. The drone of claim 17, further comprising a waterproof housing disposed on a surface of the fuselage, a gap between the waterproof housing and the fuselage forming an airflow loop;

and a heat radiating part is arranged at a position of the waterproof shell corresponding to the air outlet, and the air flow flowing out of the air outlet is subjected to heat exchange with the heat radiating part and then is sucked into the interior of the waterproof shell along the air flow loop again.

19. The unmanned aerial vehicle of claim 1, further comprising an auxiliary device having an end that mates with the fuselage interface, the end on the auxiliary device being pluggable into the fuselage interface when the horn is unplugged from the fuselage.

20. An unmanned aerial vehicle as claimed in any one of claims 1 to 19, wherein each horn comprises a horn body and a connecting body provided on the horn body, the connecting end being located on the connecting body;

21. The drone of claim 20, wherein at least one horn body of each pair of horn assemblies is pivotally connected to the connector, and wherein the two horn bodies close or open when the horn body pivotally connected to the connector is rotated relative to the connector.

22. An unmanned aerial vehicle is characterized by comprising a body, a machine arm assembly and a frame, wherein the machine arm assembly is arranged on the body;

the frame comprises at least a first substructure and a second substructure connected at an angle.

23. The drone of claim 22, wherein the chassis further includes a third substructure, and the second substructure is connected at an angle to the third substructure;

24. The drone of claim 23, wherein the first and second accommodation spaces are respectively provided with components on the drone according to a size of the space.

25. The drone of claim 24, further comprising a cradle head and a battery assembly, wherein,