CN109319086B

CN109319086B - Unmanned aerial vehicle frame and unmanned aerial vehicle

Info

Publication number: CN109319086B
Application number: CN201710648955.1A
Authority: CN
Inventors: 肖锭锋; 何建兵; 徐智芹; 温海军
Original assignee: Guangzhou Xaircraft Technology Co Ltd
Current assignee: Guangzhou Xaircraft Technology Co Ltd
Priority date: 2017-08-01
Filing date: 2017-08-01
Publication date: 2024-05-28
Anticipated expiration: 2037-08-01
Also published as: CN109319086A

Abstract

The invention provides an unmanned aerial vehicle frame and an unmanned aerial vehicle, wherein the unmanned aerial vehicle frame comprises: the machine body bearing plate is used for installing the first element and the second element; the transfer bin body is arranged on the machine body bearing plate, a connecting cavity with an opening end is formed in the transfer bin body, a through hole is formed in the transfer bin body and is communicated with the connecting cavity, wherein the first element and the second element are positioned outside the transfer bin body, the through hole is used for allowing a connecting wire of the first element to pass through a connecting wire of the second element, and the connecting cavity is used for accommodating a connecting interface of the connecting wire of the first element and the connecting wire of the second element; and the transfer bin cover sealing cover is arranged at the opening end of the transfer bin body. By applying the technical scheme of the invention, the technical problem that the unmanned aerial vehicle is waterproof and has high protection difficulty due to unreasonable design of the unmanned aerial vehicle body structure in the prior art can be solved.

Description

Unmanned aerial vehicle frame and unmanned aerial vehicle

Technical Field

The invention belongs to the technical field of aircraft equipment, and particularly relates to an unmanned aerial vehicle frame and an unmanned aerial vehicle.

Background

The unmanned aerial vehicle is an unmanned aerial vehicle which is controlled by utilizing the cooperation of wireless remote control equipment and a control induction device of the unmanned aerial vehicle. Along with the development of unmanned aerial vehicle aircraft technique, because unmanned aerial vehicle aircraft has advantages such as flexible, unmanned flight, operation requirement are low, unmanned aerial vehicle aircraft has been widely used in working fields such as agricultural plant protection, photography by plane, electric power inspection, environmental monitoring, forest fire prevention and disaster inspection, has effectively overcome the not enough that manned aircraft carries out aerial operation.

When the unmanned aerial vehicle flies, the unmanned aerial vehicle is in outdoor open air, water drops can be collected on the body of the unmanned aerial vehicle when the unmanned aerial vehicle encounters rain and fog, and particularly, the unmanned aerial vehicle is applied to agricultural plant protection. However, in the unmanned aerial vehicle in the prior art, the design of the body structure is unreasonable, so that the circuit, the pipeline and the waterway layout connected to the body are unreasonable, and the waterproof and protective difficulties of the circuit interface of each circuit, the pipeline interface of each pipeline and the waterway interface of each waterway are high.

Disclosure of Invention

The invention aims to provide an unmanned aerial vehicle frame and an unmanned aerial vehicle, which are used for solving the technical problems of high waterproof and protection difficulty of the unmanned aerial vehicle caused by unreasonable design of a body structure of the unmanned aerial vehicle in the prior art.

In order to achieve the above purpose, the invention adopts the following technical scheme: there is provided a drone frame, comprising: the machine body bearing plate is used for installing the first element and the second element; the transfer bin body is hermetically arranged on the machine body bearing plate, a connecting cavity with an opening end is formed in the transfer bin body, a through hole is formed in the transfer bin body and is communicated with the connecting cavity, wherein the first element and the second element are positioned outside the transfer bin body, the through hole is used for allowing a connecting wire of the first element to pass through a connecting wire of the second element, and the connecting cavity is used for accommodating a connecting interface of the connecting wire of the first element and the connecting wire of the second element; and the transfer bin cover sealing cover is arranged at the opening end of the transfer bin body.

According to another aspect of the present invention, a drone is provided. This unmanned aerial vehicle includes: the first component, the second component and the frame are arranged on the frame bearing plate of the unmanned aerial vehicle frame.

Use this unmanned aerial vehicle frame to assemble unmanned aerial vehicle for be formed with the junction box of transfer storehouse body in the unmanned aerial vehicle frame after the assembly is accomplished, at this moment, the junction interface of the connecting wire of the circuit layout in the unmanned aerial vehicle is all accomodate in the junction box of transfer storehouse body, make the attach fitting of connecting wire design with stealthy mode of laying, make the unmanned aerial vehicle assemble and accomplish the back can not receive the junction interface messy influence of connecting wire, whole outward appearance appears more clean and tidy, pleasing to the eye, and protect the junction interface of connecting wire through the transfer storehouse body, the junction interface of eliminating the connecting wire receives external environment factor to influence and appear contacting failure, damage scheduling problem.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings that are needed in the embodiments or the description of the prior art will be briefly described below, it being obvious that the drawings in the following description are only some embodiments of the present invention, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.

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

Fig. 2 is a schematic diagram of a second assembly structure of a unmanned aerial vehicle frame according to an embodiment of the present invention;

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

Fig. 4 is a schematic structural diagram of a second carrier plate of the unmanned aerial vehicle frame according to an embodiment of the present invention;

fig. 5 is a schematic structural diagram of a first view angle of a transfer cabin of the unmanned aerial vehicle frame according to an embodiment of the present invention;

Fig. 6 is a schematic structural diagram of a second view angle of a transfer cabin of the unmanned aerial vehicle frame according to the embodiment of the present invention;

fig. 7 is a schematic structural diagram of a transfer cabin cover of the unmanned aerial vehicle rack according to the embodiment of the invention;

fig. 8 is a schematic diagram of an assembly structure of a horn, a connecting collar and a sealing collar of an unmanned aerial vehicle frame according to an embodiment of the present invention;

Fig. 9 is a schematic diagram of an exploded structure of a fixed connection seat and a fixed connection compression ring of an unmanned aerial vehicle frame according to an embodiment of the present invention;

fig. 10 is a schematic structural view of a mounting frame of a unmanned aerial vehicle frame according to an embodiment of the present invention;

Fig. 11 is a schematic structural view of a sealing hose of a unmanned aerial vehicle frame according to an embodiment of the present invention;

Fig. 12 is a schematic structural view of a sealing collar of a unmanned aerial vehicle frame according to an embodiment of the present invention;

fig. 13 is a schematic structural view of a sealing ring of a unmanned aerial vehicle frame according to an embodiment of the present invention;

Fig. 14 is a schematic structural view of a front leg of a unmanned aerial vehicle frame according to an embodiment of the present invention;

fig. 15 is a rear leg structure of a drone frame of an embodiment of the present invention;

fig. 16 is an exploded view of a stand of a unmanned aerial vehicle according to an embodiment of the present invention;

Fig. 17 is a schematic structural view of an assembled tripod of a unmanned aerial vehicle frame according to an embodiment of the present invention;

Fig. 18 is a structural view of the mounted state of the foot stand of the unmanned aerial vehicle rack of the embodiment of the present invention;

fig. 19 is an exploded view of a fastening assembly in a foot rest of a drone frame according to an embodiment of the present invention;

fig. 20 is a schematic structural view of a first view angle of the unmanned plane according to an embodiment of the present invention;

fig. 21 is a schematic structural diagram of a second view angle of the unmanned aerial vehicle according to an embodiment of the present invention.

Wherein, each reference sign in the figure:

10. A fuselage carrying plate; 11. a first bearing plate; 12. a second bearing plate; 111. a first mating hole; 121. a second mating hole; 20. a transfer bin body; 211. a connecting cavity; 212. mounting through holes; 22. a bottom wall; 221. a first through hole; 222. a second through hole; 30. a horn; 40. a transfer bin cover; 41. sealing grooves; 91. a fixed connection assembly; 911. fixing the connecting seat; 912. the compression ring is fixedly connected; 913. a connecting collar; 9131. a connecting lug; 9111. a limiting groove; 50. a mounting frame; 51. an assembly space; 52. a dividing rail; 511. a first assembly space; 512. a second fitting space; 513. a power supply connector installation space; 92. a pulling connection assembly; 201. a first sidewall; 202. a second sidewall; 203. a third sidewall; 60. a wire outlet slot shell; 93. sealing the connection assembly; 931. sealing the hose; 932. a sealing collar; 9321. sealing the connecting part; 933. sealing compression rings; 9331. a connecting groove; 9311. a connection protrusion; 213. a sidewall protrusion; 214. a sealing protrusion; 215. a first screw connection lug; 70. a power installation casing; 80. a foot rest; 110. a front leg; 130. a rear leg; 9312. sealing ring grooves; 9322. a second screw connecting lug; 93210. fitting the protrusion; 9332. a third screw connecting lug; 01. a frame; 02. a power device; 03. a spraying device; 04. a pumping device; 05. a liquid storage container; 06. a housing; 07. a power supply battery module; 08. an inductive antenna; 2031. inserting a through hole; 31. a threading hole; 1110. a first connection portion; 1120. a first detour portion; 1130. a front support part; 1140. a front grounding part; 1150. a reinforcing part; 1310. a second connecting portion; 1320. a second detour portion; 1330. a rear support portion; 1340. a rear ground part; 200. a buffering vibration damper; 120. a connecting leg; 11100. a first connection hole; 11400. a second connection hole; 13100. a third connection hole; 13400. a fourth connection hole; 300. a fastening assembly; 310. a connecting bolt; 320. a lock nut; 1210. a front end portion connecting hole; 1220. and a rear end portion connecting hole.

Detailed Description

In order to make the technical problems, technical schemes and beneficial effects to be solved more clear, the invention is further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the scope of the invention.

It will be understood that when an element is referred to as being "mounted" or "disposed" on another element, it can be directly on the other element or be indirectly on the other element. When an element is referred to as being "connected to" another element, it can be directly connected to the other element or be indirectly connected to the other element.

It is to be understood that the terms "length," "width," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like are merely for convenience in describing and simplifying the description based on the orientation or positional relationship shown in the drawings, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus are not to be construed as limiting the invention.

Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include one or more such feature. In the description of the present invention, the meaning of "a plurality" is two or more, unless explicitly defined otherwise.

As shown in fig. 1 to 8, the unmanned aerial vehicle frame of this embodiment includes a fuselage loading board 10, a transfer bin body 20 and a transfer bin cover 40, the fuselage loading board 10 is used for installing first component and second component, the transfer bin body 20 forms a connecting cavity 211 with an open end, a through hole is arranged on the transfer bin body 20, the through hole is communicated with the connecting cavity 211, the transfer bin body 20 is connected on the fuselage loading board 10 in a sealing way, the transfer bin cover 40 is arranged at the open end of the transfer bin body 20 in a sealing way, wherein the first component and the second component are located outside the transfer bin body 20, the through hole is used for the connecting wire of the first component and the connecting wire of the second component to pass through, and the connecting cavity 211 is used for accommodating the connecting interface of the connecting wire of the first component and the connecting wire of the second component.

The unmanned aerial vehicle is assembled by using the unmanned aerial vehicle frame, so that the connecting cavity 211 of the transfer bin body 20 is formed in the unmanned aerial vehicle frame after the unmanned aerial vehicle frame is assembled, at the moment, the connection interfaces of connecting wires in the unmanned aerial vehicle are all contained in the connecting cavity 211 of the transfer bin body 20, which can be physical wire layout, such as a pipe line, or electric wire layout, the application is illustrated by taking the electric wire layout as an example, so that the connection joints of the connecting wires are designed in an invisible layout mode, the unmanned aerial vehicle can not be affected by disorder of the connection interfaces of the connecting wires after the unmanned aerial vehicle is assembled, the whole appearance is tidier and attractive, the connection interfaces of the connecting wires are protected through the transfer bin body 20, and the problems that the connection interfaces of the connecting wires are affected by external environment factors, are bad in contact, damaged and the like are eliminated. Furthermore, the first and second members are located outside the transfer bin body 20, so that the volume of the transfer bin body 20 can be reduced.

The unmanned aerial vehicle frame of this embodiment includes a plurality of horn 30, each horn 30 has relative first end and second end, each horn 30 has the cavity that link up first end and second end, the first end connection tip fixed connection of each horn 30 is on fuselage loading board 10, transfer storehouse body 20 includes around the first lateral wall 201 of connecting the chamber, the through-hole of transfer storehouse body 20 is including locating the installation through-hole 212 on the first lateral wall 201, the first end sealing connection of horn 30 is on first lateral wall 201, a plurality of horns 30 and a plurality of installation through-holes 212 one-to-one, namely the cavity and the installation through-hole 212 of installation through-hole 212 intercommunication horn 30, the second end of horn 30 is used for installing the second component, cavity and installation through-hole 212 are used for the connecting wire of second component to pass, and the connecting wire interface of second component is located the connecting the chamber 211. Through the hollow cavity that uses the connection chamber 211 and combine horn 30, so make not only install the connection interface of the connecting wire of first component, second component on fuselage loading board 10 accomodate in the connection intracavity, and make the connecting wire of the second component of installing on the tip of horn 30 wear to establish through the hollow cavity and extend, then accomodate the connection interface of second component in the connection intracavity, thereby still further realize unmanned aerial vehicle assembly back circuit layout's stealthy effect of accomodating, make unmanned aerial vehicle frame whole appear clean and tidy, pleasing to the eye.

In this embodiment, a sealing protrusion 214 is circumferentially provided on an end of the open end of the transfer chamber body 20, and a sealing groove 41 is circumferentially provided on the transfer chamber cover 40, the sealing protrusion 214 being sealingly engaged in the sealing groove 41. In the assembly process, the sealing of the open end of the connection cavity 211 is achieved by aligning the sealing groove 41 on the transfer cover 40 with the sealing protrusion 214 such that the sealing protrusion 214 is inserted and extended into the sealing groove 41 and then fixedly connecting the transfer cover 40 with the body carrier plate 10 by using the screw, that is, the transfer cover 40 is detachably connected to the transfer body 20.

As shown in fig. 1 to 4, the fuselage carrier plate 10 in the present embodiment includes a first carrier plate 11 and a second carrier plate 12, the first carrier plate 11 and the second carrier plate 12 are disposed opposite to each other, and the transfer cabin 20 is located between the first carrier plate 11 and the second carrier plate 12. The first bearing plate 11 and the second bearing plate 12 are used for supporting the transfer cabin body 20 and the plurality of horn 30 together, so that the mechanical strength of the unmanned aerial vehicle frame is improved, the transfer cabin body 20 and the horn 30 are connected between the first bearing plate 11 and the second bearing plate 12, a sealed connecting cavity 211 of the transfer cabin body 20 is formed, a large exposed installation space is formed, the exposed installation space formed between the first bearing plate 11 and the second bearing plate 12 is effectively utilized, and other corresponding parts required to be applied to in the unmanned aerial vehicle assembly process can be installed in the exposed installation space, so that the space utilization rate of the unmanned aerial vehicle frame is improved (in practice, the waterproof and protection requirements of assembly parts installed in the exposed installation spaces are not high, and the assembly parts can be easily waterproof and protected). In addition, the first loading board 11 is provided with a first mating hole 111, the second loading board 12 is provided with a second mating hole 121, the open end of the connecting cavity 211 is opposite to the first mating hole 111, the transferring bin body 20 covers the second mating hole 121, wherein the transferring bin body 20 further includes a bottom wall 22, the first side wall 201 extends vertically from the bottom wall 22 and extends out, the through hole of the transferring bin body 20 further includes a first through hole 221 and a second through hole 222 formed in the bottom wall 22, at this time, the second mating hole 121 is communicated with the connecting cavity 211 through the first through hole 221 and the second through hole 222, and the open end of the connecting cavity 211 is opposite to the first mating hole 111. In this embodiment, the first element includes an electric adjuster located outside the transferring bin 20, the first through hole 221 is used for passing through a connecting wire of the electric adjuster, the second element includes a motor installed at the second end of the horn 30, and the connecting wire of the motor passes through the corresponding installation through hole 212 and the hollow cavity of the horn 30, so that the interface of the electric adjuster and the connecting wire of the motor are located in the connecting cavity 211 of the transferring bin 20.

The transfer bin 20 of the embodiment further includes a second side wall 202, where the second side wall 202 is connected to the first side wall 201. The transfer bin 20 may include four first sidewalls 201, or include six first sidewalls 201, or include eight first sidewalls 201, or the like, and correspondingly, the number of the arms 30 is four, six, or eight. Preferably, the transfer bin 20 of the present embodiment includes four first side walls 201, the number of the arms 30 is four, and the four first side walls 201 are on average located at two sides of the second side wall 202, the through hole of the transfer bin 20 further includes a communication hole formed on the second side wall 202, that is, the outlet slot shell 60 formed on the second side wall 202, and the slot space of the outlet slot shell 60 is communicated with the connection cavity 211. When the unmanned aerial vehicle frame is assembled and applied to the unmanned aerial vehicle complete machine assembly, a worker wears out the connecting wire of the flight controller from the wire outlet slot shell 60, and is electrically connected between the flight controller and the electric control, at the moment, a connecting interface between the connecting wire of the flight controller and the connecting wire of the electric control is positioned in the connecting cavity 211 of the transfer bin body 20, and is arranged in the wire outlet slot shell 60 by applying the waterproof gasket, so that reliable and good sealing of the connecting wire wearing-out communication hole is realized.

In this embodiment, the first element includes a liquid storage container located outside the transfer bin 20, and the transfer bin 20 further includes a third side wall 203, the third side wall 203 is connected to the first side wall 201, the third side wall 203 is opposite to the second side wall 202, the four first side walls 201 are located on two sides of the third side wall 203 at the same time, the through hole of the transfer bin 20 further includes an insertion through hole 2031 located on the third side wall 203, the insertion through hole 2031 is used for allowing a connection line of the liquid storage container to pass through, and the second element of this embodiment further includes a nozzle (i.e. a spraying device 03) mounted at the second end of the horn 30, and the connection line of the spraying device 03 passes through the hollow cavity of the horn 30 and the mounting through hole 212, so that both the connection line interface of the liquid storage container and the connection line interface of the spraying device 03 are located in the connection cavity 211 of the transfer bin 20.

Referring to fig. 1,2 and 10, the unmanned aerial vehicle rack further includes a mounting frame 50, where the mounting frame 50 can be applied to mounting the power supply storage battery module 07, and for a plant protection unmanned aerial vehicle applied to plant protection operation, that is, the plant protection operation unmanned aerial vehicle applied by the present invention, the mounting frame 50 is not only applied to mounting the power supply storage battery module 07, but also applied to mounting the liquid storage container 05 storing liquid medicine in the plant protection spraying process. In this embodiment, the first side of the installation frame 50 is fixedly connected to the second carrying board 12, the installation frame 50 is located between two arms 30, and the installation frame 50 is fixedly connected to two adjacent arms 30 through the traction connection assembly 92, meanwhile, the first side of the installation frame 50 is also fixedly connected to the third side wall 203 of the transfer bin 20, and the second side of the installation frame 50 extends horizontally.

Specifically, as shown in fig. 10, the mounting frame 50 of the present embodiment is formed with an assembly space 51, the assembly space 51 is partitioned into a first assembly space 511 and a second assembly space 512 by a partition cross bar 52, the second assembly space 512 is away from the fuselage carrier plate 10, at this time, the second assembly space 512 in the mounting frame 50 is used for mounting and connecting the power supply battery module 07, and a power supply connector mounting space 513 is opened on a side wall of the second assembly space 512 away from the fuselage carrier plate 10, a power supply connector (not shown) is placed in the power supply connector mounting space 513, and the power supply connector is electrically connected with the flight controller by a connection wire, and the connection wire between the power supply connector and the flight controller is routed along the frame edge of the mounting frame, preferably an accommodating groove is opened on the frame edge, and the connection guide is accommodated in the accommodating groove of the frame edge. In this embodiment, the first assembling space 511 is used for assembling the liquid container 05. In addition, for the unmanned aerial vehicle applied to aerial photography, equipment such as an aerial camera and the like can be installed and connected in the first assembly space 511, or for the unmanned aerial vehicle applied to plant protection operation, the first assembly space 511 is used for installing and connecting the liquid storage container 05. The projections of the centers of circles of the end portions of the plurality of horn 30 far from the fuselage carrying plate 10 are located within the area of the first assembly space 511, that is, the projections of all the center of gravity positions are always located within the area of the first assembly space 511, no matter the center of gravity position of the unmanned aerial vehicle frame just assembled or the center of gravity position of the unmanned aerial vehicle complete machine which has been assembled, in fact, the offset change between all the center of gravity positions is always performed within the preset range for ensuring the stable flight.

As shown in fig. 14 and 15, the provided foot rest 80 includes a front leg 110 and a rear leg 130, wherein the front leg 110 includes a front support portion 1130 and a first detour portion 1120, the front support portion 1130 is connected with the first detour portion 1120, and a first turning corner is formed at a connection portion of the front support portion 1130 and the first detour portion 1120, one end of the front support portion 1130, which is far away from the first detour portion 1120, is used for being supported on a support surface, one end of the first detour portion 1120, which is far away from the front support portion 1130, is used for being connected with the fuselage carrier plate 10, and an opening of the first turning corner is directed toward the rear leg 130.

The foot rest 80 is used for helping the unmanned aerial vehicle to realize normal take-off operation and landing operation, in particular to the unmanned aerial vehicle in the landing process, the unmanned aerial vehicle is subjected to the reverse impact of the foot rest 80 by the support surface at the moment of landing on the support surface, and if the impact force transmission can not be effectively reduced, the precision spare and accessory parts of the unmanned aerial vehicle can be damaged. The front supporting leg 110 of the foot stand 80 adopts the first turning corner formed between the front supporting portion 1130 and the first roundabout portion 1120, so that the front supporting leg 110 has good elastic capability to resist impact, and can convert the reverse impact force of a supporting surface into the elastic potential energy of the front supporting leg 110, thus the reverse impact force received by the unmanned aerial vehicle in the landing process is effectively reduced, and meanwhile, the strength requirement of the unmanned aerial vehicle on the foot stand 80 in the use process can be met.

In the process of actually installing and assembling the unmanned aerial vehicle, the two front supporting legs and the two rear supporting legs of the foot stand 80 can be in the same structural form, for example, the front supporting legs 110 are all selected for installation to form the foot stand 80; the front support leg 110 can be selected for installation only at the front end of the unmanned aerial vehicle, and the rear support leg 130 can be selected for installation in other support leg forms capable of meeting the landing and taking-off requirements in the prior art; alternatively, the front leg 110 is selected as the rear leg 130 from the two rear legs of the unmanned aerial vehicle, and the front leg 110 is selected from the legs of the other prior art which can meet the landing requirements.

In the following description of the present application, the front leg 110 and the rear leg 130 are mounted in different configurations to form the stand 80, so as to describe the structural design of the stand 80 of the present application.

As shown in fig. 15, the rear leg 130 includes a rear supporting portion 1330 and a second detour portion 1320, the rear supporting portion 1330 is connected to the second detour portion 1320, and a second turning point is formed at a connection of the rear supporting portion 1330 and the second detour portion 1320, one end of the rear supporting portion 1330 remote from the second detour portion 1320 is used for supporting a supporting surface, one end of the second detour portion 1320 remote from the rear supporting portion 1330 is used for being connected to a mounting frame, and an opening of the second turning point faces the front leg 110, further, the supporting surface is used as a reference surface, and a height distance of an inflection point of the second turning point with respect to the supporting surface is smaller than a height distance of an inflection point of the first turning point with respect to the supporting surface. As with the front leg 110, the second turning corner is formed between the rear supporting portion 1330 and the second detour portion 1320 of the rear leg 130, so that the rear leg 130 has good elastic deformation capability, and is resistant to the impact force generated by the supporting surface, and can convert the reverse impact force of the supporting surface into the elastic potential energy of the rear leg 130, so that the reverse impact force of the unmanned aerial vehicle in the landing process is effectively reduced, and meanwhile, the strength requirement of the stand 80 for the unmanned aerial vehicle in the use process can be met.

Since the reverse impact force generated by the foot stand 80 is firstly applied to one end of the front leg 110 supported on the supporting surface and one end of the rear leg 130 supported on the supporting surface during the landing of the unmanned aerial vehicle, the reverse impact force instantaneously acts to cause severe deformation of the front support portion 1130 and the rear support portion 1330, and then the impact force is transferred to the fuselage carrying plate 10 and the mounting frame along the front leg 110 and the rear leg 130, in order to enable the front leg 110 and the rear leg 130 to sequentially reduce the direction from the fuselage carrying plate 10 to the supporting surface of the first roundabout portion 1120 and the front support portion 1130 of the front leg 110 and sequentially reduce the direction from the mounting frame to the supporting surface of the second roundabout portion 1320 and the rear support portion 1330 of the rear leg 130, so that the portion of the front support portion 1130 and the rear support portion 1330 closer to the supporting surface has stronger bending deformation capability and the breaking capability of the impact force is relieved by elastic deformation of the front support portion itself when receiving the instantaneous impact force.

The front leg 110 of the present invention further includes a first connection portion 1110 and a front ground portion 1140, and the rear leg 130 further includes a second connection portion 1310 and a rear ground portion 1340. The first end of the first connection portion 1110 is connected to the first detour portion 1120, the second end of the first connection portion 1110 extends horizontally, the first connection portion 1110 is connected to the bottom of the body carrier 10, as shown in fig. 14, the front leg 110 is connected to the bottom of the body carrier 10 by fastening with screws through the first connection hole 11100 formed in the first connection portion 1110, and the first connection portion 1110 is connected to the bottom surface of the body carrier 10 in a horizontal contact manner. A first end of the front ground 1140 is coupled to the front support 1130 for supporting on a support surface, and a second end of the front ground 1140 extends horizontally toward the rear leg 130. The first end of the second connection part 1310 is connected to the second detour part 1320, the second end of the second connection part 1310 extends in the vertical direction, the second connection part 1310 is connected to the side of the mounting frame, as shown in fig. 15, the rear leg 130 is connected to the side wall of the rear end of the body loading plate 10 by a screw through the third connection hole 13100 formed in the second connection part 1310, that is, the contact surface between the second connection part 1310 and the side wall of the body loading plate 10 is a surface extending in the vertical direction. A first end of the rear ground 1340 is connected to the rear support 1330 for supporting on a support surface, and a second end of the rear ground 1340 extends horizontally toward the front leg 110.

In order to further improve the supporting strength of the front leg 110 and the rear leg 130, as shown in fig. 14, the front leg 110 further includes a reinforcing portion 1150, the reinforcing portion 1150 is provided on the first turn portion 1120, the reinforcing portion 1150 extends to the front supporting portion 1130 along the first turn, and the reinforcing portion 1150 also extends to the first connection portion 1110, so that the mechanical strength of the front leg 110 is effectively enhanced, as shown in fig. 15, the cross-sectional profile shape of the second turn portion 1320 perpendicular to the central axis thereof is triangular, and the second turn portion 1320 is provided with a hollow cavity filled with a supporting filler, thereby reducing the manufacturing material consumption of the rear leg 130, and simultaneously, the supporting filler can be applied to support the rear supporting portion 1330 during the manufacturing process without collapsing and deforming the rear supporting portion 1330 having the hollow cavity. Of course, the post-support 1330 in the form of a solid post may be provided, or the hollow cavity of the post-support 1330 may be directly left hollow without any support filler.

In the process of landing of the unmanned aerial vehicle in actual operation, since the first connection portion 1110, the first detour portion 1120, and the portion of the front support portion 1130 adjacent to the first detour portion 1120 are each designed to have enhanced mechanical strength by the reinforcing portion 1150, when the unmanned aerial vehicle drops to the supporting surface and instantaneously receives the impact force of the supporting surface, the force is concentrated on the portion of the front support portion 1130 where the strength of the reinforcing portion 1150 is not enhanced. Therefore, when the impact force is instantaneously excessive, the elastic deformation of the front support portion 1130 of the front leg 110 is exceeded, at this time, the portion of the front support portion 1130 not reinforced by the reinforcing portion 1150 for hiding will break, and the breaking position is reasonably designed, so that the breaking position is furthest from the position of the fuselage carrier plate 10, and the damage degree to the unmanned aerial vehicle is minimal. For the rear leg 130, the rear support 1330 having a smaller strength is also the weakest point with respect to the load, and when the instantaneous impact force exceeds the load capacity, the rear support 1330 is broken first to counteract the impact force.

Because the strength distribution design of the front leg 110 is reasonably optimized in the present invention, that is, the first connection portion 1110, the first detour portion 1120, the front support portion 1130, the front grounding portion 1140 and the reinforcement portion 1150 are sequentially arranged in a shrinking manner, by combining the reinforcement portion 1150 with the optimized strength distribution design, it is ensured that each stress fracture is located between the first detour portion 1120 and the front grounding portion 1140 so as to be away from the fuselage carrier 10. Likewise, the strength distribution design of the rear leg 130 is reasonably optimized, that is, the second connection portion 1310, the second detour portion 1320, the rear support portion 1330 and the rear grounding portion 1340 are sequentially reduced, so that each time the rear leg 130 breaks, the location is located between the rear support portion 1330 and the rear grounding portion 1340, the stress breaking point is ensured to be far away from the fuselage carrier plate 10 and the mounting frame, and the damage degree to the fuselage carrier plate 10 and the mounting frame is minimized.

Since each leg of the foot rest 80 is disposed obliquely along the outer direction of the unmanned aerial vehicle after being mounted and fixed, in order to satisfy both the mechanical strength design of the front leg 110 and the aesthetic design of the front leg 110, as shown in fig. 14, the reinforcement portion 1150 is disposed at the outer sides of the first connection portion 1110, the front support portion 1130 and a portion of the first roundabout portion 1120 to form a hemming. In this way, the design of the side wrapping edges can make the front support leg 110 full and thick while enhancing the mechanical strength, and the external texture of the foot rest 80 is improved.

As shown in fig. 16 and 19, the stand 80 further includes a buffering vibration damper 200, the front grounding portion 1140 of the front leg 110 is connected with the buffering vibration damper 200 through a fastening assembly 300, and the rear grounding portion 1340 is connected with the buffering vibration damper 200 through the fastening assembly 300, so that in the landing process of the unmanned aerial vehicle, the impact force can be further reduced through the buffering vibration damper 200, and the impact force is reduced and transmitted to the direction of the fuselage carrying plate 10. The cushioning damper 200 is provided with a through-hole for inserting the grounding portion, and is provided with a receiving hole for receiving the connecting bolt 310. In the process of assembling and connecting the cushion damper 200 to the grounding portion of the corresponding leg, for example, the cushion damper 200 is connected to the front grounding portion 1140, the assembly worker inserts the front grounding portion 1140 into the through-insertion hole, and makes the second connection hole 11400 opened in the front grounding portion 1140 opposite to the receiving hole, then places the lock nut 320 under the front grounding portion 1140, and then connects the connection bolt 310 to the lock nut 320 after passing through the receiving hole and the second connection hole 11400, and the front grounding portion 1140 is pressed and locked to the wall of the through-insertion hole by the lock nut 320 to be connected and fixed. Similarly, the connecting bolt 310 is inserted through the receiving hole and the fourth connecting hole 13400 and then connected to the lock nut 320, and the lock nut 320 tightly locks the rear grounding portion 1340 to the wall of the through-hole for connection and fixation.

In the unmanned aerial vehicle landing process, when the foot rest 80 receives the instantaneous of impact, four landing legs of foot rest 80 all can take place to expand the deformation outward, when expanding the deformation volume excessively outward, then will lead to the junction of the first connecting portion 1110 of preceding landing leg 110 and the junction of the second connecting portion 1310 of back landing leg 130 to receive concentrated stress effect, just so lead to first connecting portion 1110 and second connecting portion 1310 also to belong to the easy fracture position. In order to prevent the foot stool 80 from being broken at the first and second connection portions 1110 and 1310 when the foot stool 80 is impacted, the foot stool 80 further includes a connection leg 120, a first end of the connection leg 120 is connected to the buffering vibration damper 200 on the front grounding portion 1140, and a second end of the connection leg 120 is connected to the buffering vibration damper 200 on the rear grounding portion 1340. As shown in fig. 16, a front end portion connecting hole 1210 is formed in the front end portion of the connecting leg 120, and a rear end portion connecting hole 1220 is formed in the rear end portion. In assembling the cushion damper 200 and the connection leg 120 of the front leg 110, the front end portion of the connection leg 120 is inserted into the through-insertion hole of the cushion damper 200, and the front end portion of the connection leg 120 is overlapped with the front grounding portion 1140, the second connection hole 11400 is opposite to the front end portion connection hole 1210, the lock nut 320 is located between the front end portion of the connection leg 120 and the wall of the through-insertion hole, and then the connection bolt 310 is connected to the lock nut 320, and the lock nut 320 presses the front grounding portion 1140 and the front end portion of the connection leg 120 against the wall of the through-insertion hole. Likewise, in the process of connecting the rear end portion of the connection leg 120 to the cushion damper 200 of the rear leg 130, the rear end portion of the connection leg 120 is inserted into the through-insertion hole of the cushion damper 200, and the rear end portion of the connection leg 120 is overlapped with the rear grounding portion 1340, the fourth connection hole 13400 is opposite to the rear end connection hole 1220, the lock nut 320 is located between the rear end portion of the connection leg 120 and the wall of the through-insertion hole, and then the connection bolt 310 is connected to the lock nut 320, the lock nut 320 presses the rear grounding portion 1340 and the rear end portion of the connection leg 120 against the wall of the through-insertion hole, and the assembled tripod 80 is shown with reference to fig. 17 and 18. During landing, the front leg 110 and the rear leg 130 are pulled by the connection leg 120, so that the tendency of the front leg 110 and the rear leg 130 to spread out is eliminated, and the first connection portion 1110 of the front leg 110 and the second connection portion 1310 of the rear leg 130 are ensured not to become breaking positions.

As shown in fig. 8 and 9, in the process of connecting the arms 30 with the fuselage carrier plate 10 and the transfer cabin body 20 to form the basic framework of the unmanned aerial vehicle frame, the connection ends of the arms 30 are connected with the fuselage carrier plate 10 through the fixed connection assemblies 91, the fixed connection assemblies 91 are located between the first carrier plate 11 and the second carrier plate 12, and in the actual assembly connection, two spaced fixed connection assemblies 91 are adopted at the connection end of each arm 30 to fix the arm 30 on the fuselage carrier plate 10. The fixed connection assembly 91 includes a fixed connection seat 911, a fixed connection compression ring 912, and a connection collar 913. The fixed connection seat 911 is fixedly connected to the second bearing plate 12, the fixed connection compression ring 912 is connected to the fixed connection seat 911, a clamping space is formed between the fixed connection compression ring 912 and the fixed connection seat 911, the horn 30 is assembled in the clamping space, the first bearing plate 11 is fixedly connected to the fixed connection compression ring 912, the connecting collar 913 is sleeved on the horn 30, the connecting collar 913 is provided with the connecting lugs 9131, particularly, the connecting collar 913 is symmetrically provided with the connecting lugs 9131 at 180 degrees, the limiting groove 9111 is formed in the inner side of the fixed connection seat 911, the connecting lugs 9131 extend into the limiting groove 9111, and the connecting collar 913 is clamped in the clamping space. The horn 30 is connected with the fixed connecting seat 911 and the fixed connecting compression ring 912 through the connecting collar 913, so that the horn 30 has certain shock absorption and buffering capacity relative to the fuselage bearing plate 10, and flexible assembly connection between the horn 30 and the fuselage bearing plate 10 is realized to a certain extent.

In other possible embodiments, the transfer chamber body 20 may be a cylindrical structure surrounded by side walls to form a circular cross-sectional profile shape.

Further, the two first sidewalls 201 far from the second sidewall 202 are curved sidewalls concave toward the inner side of the connecting cavity 211, such as arc-shaped sidewalls or turning curved sidewalls. Preferably, the two first side walls 201 are side walls formed by connecting two small straight walls through turns and concavely forming toward the connecting cavity 211 (i.e., turning curved side walls), and the mounting through holes 212 are provided on the small straight wall far from the third side wall 203 among the two small straight walls. Like this, the horn 30 that the installation through-hole 212 that sets up on these two little straight walls corresponds all is close to the symmetry central axis of unmanned aerial vehicle frame, and the contained angle between the horn 30 of connecting on these two little straight walls is less than the contained angle between the horn 30 of connecting on two first lateral walls 201 that are close to second lateral wall 202 to offset unmanned aerial vehicle frame or unmanned aerial vehicle's focus position is whole along the extending direction of installing frame 50, so that the assembly space of installing frame 50 is bigger, thereby satisfies unmanned aerial vehicle and can carry more article (or carry more liquid medicine) and fly.

The junction between two adjacent lateral walls all is equipped with first screw engaging lug 215, and transfer storehouse body 20 passes through corresponding first screw engaging lug 215 fixed connection on second loading board 12, then first loading board 11 passes through first loading board 11 through the screw and then the cooperation is connected on corresponding first screw engaging lug 215 in order to realize fixed connection.

In order to further achieve a stable tightness between the horn 30 and the first side wall 201, a sealing connection is thus provided between the first end of the horn 30 and the first side wall 201 by means of a sealing connection assembly 93. As shown in fig. 1, 11 to 13, the sealing connection assembly 93 includes a sealing hose 931, a sealing collar 932, and a sealing press ring 933. The sealing hose 931 may be a bellows, the first end of the sealing hose 931 is in sealing connection with the connection end portion of the horn 30, the second end of the sealing hose 931 is in sealing connection with the first side wall 201, the sealing collar 932 is in sealing connection with the first end of the horn 30, the sealing collar 932 extends out of the sealing connection portion 9321 at the end portion, the sealing connection portion 9321 is far away from the horn 30, the sealing connection portion 9321 is in sealing connection with the first end of the sealing hose 931 (specifically, a fitting protrusion 93210 is provided on a circumferential wall of the sealing connection portion 9321, and at the same time, a sealing ring groove 9312 is provided on an inner side wall of the first end of the sealing hose 931, when the sealing connection portion 9321 is inserted into the first end of the sealing hose 931, the fitting protrusion 93210 is fitted with the sealing ring groove 931 to form a sealing structure), a connecting groove 9331 is provided on an inner side of the sealing ring 933, a connecting protrusion 931 is provided on an outer side of the second end of the sealing hose 931, the connecting protrusion 9311 is stopped in the connecting groove 9331, the sealing ring 933 is connected to the first side wall 201 to press the second end of the sealing hose 931 against the first side wall 201, specifically, a plurality of sealing rings 9332 are fixedly connected to the first side wall by a plurality of fixing screws 32 each of the sealing ring 32. As shown in fig. 5 and 6, the first side wall 201 is provided with a side wall protrusion 213, the side wall protrusion 213 is disposed around the mounting through hole 212, the side wall protrusion 213 extends into the second end of the sealing hose 931, and the outer wall surface of the side wall protrusion 213 contacts with the inner wall surface of the sealing hose 931, so that the sealing between the sealing hose 931 and the first side wall 201 is more reliable and stable.

Meanwhile, the side wall of the sealing collar 932 is provided with a second screw connection lug 9322, and the second screw connection lug 9322 is matched and connected with the fixed connection seat 911 and the fixed connection pressing ring 912, so that the arm 30 is not only fixedly connected with the body bearing plate 10 through two spaced fixed connection components 91, but also fixedly connected with the body bearing plate 10 through the sealing collar 932, the fixed connection seat 911 and the fixed connection pressing ring 912.

According to another aspect of the present invention, as shown in fig. 14 and 15, there is provided a unmanned aerial vehicle, particularly a plant protection unmanned aerial vehicle applied to a plant protection operation. The unmanned aerial vehicle of this embodiment includes first component, the second component, unmanned aerial vehicle frame 01, wherein, unmanned aerial vehicle frame 01 includes fuselage loading board 10, transfer storehouse body 20 and transfer storehouse lid 40, transfer storehouse body 20 installs in fuselage loading board 10, transfer storehouse body 20 forms the link chamber 211 that has the open end, be equipped with the through-hole on the transfer storehouse body 20, the through-hole is linked together with link chamber 211, transfer storehouse lid 40 lid is located the transfer storehouse body 20 in order to seal the link chamber, be equipped with the connecting wire on the first component, be equipped with the connecting wire on the second component, first component and second component are installed in fuselage loading board 10 and are located the transfer storehouse body 20 outside, the connecting wire of first component and the connecting wire of second component pass the through-hole, the connection interface of the connecting wire of first component and second component is acceptd in the link chamber 211 of transfer storehouse body 20.

After the unmanned aerial vehicle is assembled and assembled, the unmanned aerial vehicle rack provided by the invention is used as a mounting connection frame platform of each part assembly part, so that the connection interfaces of connecting wires laid by wire lines in the unmanned aerial vehicle are all contained in the connection cavity 211 of the transfer bin body 20 in the unmanned aerial vehicle assembly and assembly process, the connection joints of the connecting wires are designed in an invisible layout mode, the connection interfaces of the connecting wires cannot be affected in disorder after the unmanned aerial vehicle is assembled and assembled, the whole appearance is tidier and attractive, the connection interfaces of the connecting wires are protected through the transfer bin body 20, and the problems that the connection interfaces of the connecting wires are affected by external environment factors, are bad in contact, damaged and the like are solved.

In the unmanned aerial vehicle of this embodiment, its unmanned aerial vehicle frame 01 still includes a plurality of horn 30, the horn has relative first end and second end, the horn 30 has the cavity that link up first end and second end, the first end fixed connection of each horn 30 is in fuselage loading board 10, the first end of each horn 30 and the corresponding through-hole one-to-one on the transfer storehouse body 20, the second end of each horn 30 is used for installing the second component, cavity and through-hole are used for supplying the connecting wire of second component to pass, and the connecting wire interface of second component is located the connection intracavity.

Specifically, the first component, the second component, and the connecting wire of second component all include first electric wire section, second electric wire section and third electric wire section in the cavity of horn 30 and the connecting chamber 211 of transfer storehouse body 20 of equipment assembly unmanned aerial vehicle in-process, the second end of first electric wire section is equipped with first connecting terminal, the second electric wire section is located the connecting chamber 211, the one end tip of second electric wire section is equipped with second connecting terminal, the first end electricity of third electric wire section is connected in first component, the second end of third electric wire section is equipped with the third connecting terminal, and the first end of first electric wire section is equipped with fourth connecting terminal, wherein first electric wire section wears to establish in the cavity of horn 30, place in the connecting chamber 211 after first connecting terminal and the coupling of second connecting terminal grafting, place in the connecting chamber 211 after second connecting terminal and fourth connecting terminal grafting coupling, like this, unmanned aerial vehicle's connected mode adopts portable, quick grafting coupling mode, maintenance personnel also can be installed and removed easily when maintaining the unmanned aerial vehicle, and maintenance personnel can conveniently install. In practice, the connecting wire may only include a first wire segment and a second wire segment, where a first end of the first wire segment is electrically connected to the first element, the second element, and the second element, a second end of the first wire segment is provided with a first connection terminal, and the second wire segment is located in the connection cavity 211, and an end of one end of the second wire segment is provided with a second connection terminal, and the first connection terminal is plug-coupled with the second connection terminal and then placed in the connection cavity 211, where the first wire segment is penetratingly provided in the hollow cavity.

When the aircraft control and other components to be assembled and connected to the fuselage carrier plate 10 are installed, the fuselage carrier plate 10 and the components mounted thereon are protected by the cover 06.

As shown in fig. 8, 14 and 15, the power device 02 is mounted on the end of the arm 30 far from the body bearing plate 10, and during the assembly, first, the power mounting sleeve 70 is fixedly sleeved on the end of the arm 30, the opening of the end of the arm 30 is sealed by the power mounting sleeve 70, and the power mounting sleeve 70 is provided with a penetrating socket for penetrating the connecting wire of the power device 02. The power unit 02 is then locked to the power mounting sleeve 70 using a bolt and nut fit.

Compared with the layout and installation of the wire line, in the embodiment, the unmanned aerial vehicle further comprises a spraying device 03, a pumping device 04 and a liquid storage container 05, the spraying device 03 is fixedly installed on the horn 30, the pumping device 04 is fixedly connected to the bottom surface of the body bearing plate 10 of the unmanned aerial vehicle frame, the liquid storage container 05 is detachably assembled on the unmanned aerial vehicle frame, the pumping device 04 is electrically connected with the flight control module, the spraying device 03 is connected with the pumping device 04 through a first conveying pipe, the first conveying pipe is arranged in the hollow cavity and the connecting cavity, the pumping device 04 is connected with the liquid storage container 05 through a second conveying pipe, specifically, a flowmeter is assembled and connected with the flight control module at any position of the connecting cavity 211 or the second bearing plate 12, and the flowmeter is arranged in a second conveying pipe between the pumping device 04 and the liquid storage container 05, so that the liquid capacity which is conveyed to the spraying device 03 through the pumping device 04 to spray can be known in real time.

Specifically, the first conveying pipe comprises a first pipe section, a second pipe section and a connecting joint, wherein an inserting through hole 2031 is formed in a third side wall 203 of the unmanned aerial vehicle frame, the connecting joint is arranged in the inserting through hole 2031 in a sealing mode, two ends of the first pipe section are respectively connected to a pumping device and a first end of the connecting joint, and two ends of the second pipe section are respectively connected to a second end of the connecting joint and a spraying device.

In the unmanned aerial vehicle of the present embodiment, the sensing antenna 08 (may be a communication sensing antenna, or a line sensing antenna, etc.) is fixedly mounted on the horn 30, wherein the horn 30 is provided with a threading hole 31, and a connecting wire electrically connected with the sensing antenna 08 and the connecting circuit board passes through the threading hole 31 in a sealing manner.

The foregoing description of the preferred embodiments of the invention is not intended to be limiting, but rather is intended to cover all modifications, equivalents, and alternatives falling within the spirit and principles of the invention.

Claims

1. An unmanned aerial vehicle frame, comprising:

a fuselage carrier plate (10), the fuselage carrier plate (10) being used for mounting a first element and a second element;

The transfer bin body (20), the transfer bin body (20) is installed in the fuselage loading plate (10), the transfer bin body (20) forms a connecting cavity (211) with an opening end, a through hole is formed in the transfer bin body (20), the through hole is communicated with the connecting cavity (211), the first element and the second element are located outside the transfer bin body (20), the through hole is used for allowing a connecting wire of the first element to pass through a connecting wire of the second element, and the connecting cavity (211) is used for accommodating a connecting interface of the connecting wire of the first element and the connecting wire of the second element;

The transfer bin cover (40) is arranged at the opening end of the transfer bin body (20) in a covering manner;

The machine body bearing plate (10) is provided with a machine arm (30) in an extending mode, the machine arm (30) is provided with a first end and a second end which are opposite, the machine arm (30) is provided with a hollow cavity penetrating through the first end and the second end, the middle rotating bin body (20) comprises a first side wall (201) surrounding a connecting cavity of the middle rotating bin body (20), a through hole of the middle rotating bin body (20) comprises a mounting through hole (212) arranged on the first side wall (201), the first end of the machine arm (30) is connected to the first side wall (201) of the middle rotating bin body (20), the mounting through hole (212) is communicated with the hollow cavity of the machine arm (30) and the connecting cavity (211) of the middle rotating bin body (20), and the second end of the machine arm (30) is used for mounting the second element, and the hollow cavity and the mounting through hole (212) are used for allowing a connecting wire of the second element to pass through;

The connection interface between the connection wire of the flight controller and the connection wire of the electric regulator is positioned in the connection cavity of the transfer bin body (20);

The unmanned aerial vehicle frame still includes the installing frame, installing frame fixed connection in fuselage loading board, the installing frame is formed with first assembly space and the second assembly space that is used for installing corresponding spare part.

2. The unmanned aerial vehicle frame according to claim 1, wherein the horn (30) has four or six or eight, respectively, and the first side wall has four or six or eight.

3. The unmanned aerial vehicle rack according to claim 2, wherein the first element comprises an electric regulator located outside the transfer bin body (20), the transfer bin body (20) further comprises a bottom wall (22), the first side wall (201) extends perpendicularly from the bottom wall (22), the through hole of the transfer bin body (20) further comprises a first through hole (221) formed in the bottom wall (22), the first through hole (221) is used for allowing a connecting wire of the electric regulator to pass out, the second element comprises a motor mounted at the second end of the horn (30), the connecting wire of the motor passes through the mounting through hole (212) and the hollow cavity of the horn (30), and a connecting interface of the connecting wire of the electric regulator and the connecting wire of the motor is located in the connecting cavity of the transfer bin body (20).

4. A drone frame according to claim 3, wherein the transfer bin (20) further comprises a second side wall (202), the second side wall (202) is connected to the first side wall (201), four or six or eight first side walls (201) are evenly distributed on two sides of the second side wall (202), and the through hole of the transfer bin (20) further comprises a communication hole arranged on the second side wall (202), wherein the communication hole is used for a connection line of a flight controller to pass out.

5. The unmanned aerial vehicle rack according to claim 4, wherein the first element comprises a liquid storage container located outside the transfer bin body (20), the transfer bin body (20) further comprises a third side wall (203), the third side wall (203) is connected to the first side wall (201), the third side wall (203) is opposite to the second side wall (202), four or six or eight of the first side walls (201) are located on two sides of the third side wall (203) on average, the through hole of the transfer bin body (20) further comprises an insertion through hole formed in the third side wall, the insertion through hole is used for allowing a connecting wire of the liquid storage container to pass out, the second element further comprises a nozzle mounted at the second end of the horn (30), a connecting wire of the nozzle passes through a hollow cavity of the horn (30) and the mounting through hole (212), and a connecting interface of the connecting wire of the container and the connecting wire of the nozzle is located in the connecting cavity of the transfer bin body (20).

6. The unmanned aerial vehicle frame according to claim 2, wherein the first end of the horn (30) is connected with the first side wall (201) of the transfer bin body (20) in a sealing manner through a sealing connection assembly (93), the sealing connection assembly (93) comprises a sealing hose (931), the first end of the sealing hose (931) is fixedly connected with the first end of the horn (30), and the second end of the sealing hose (931) is fixedly connected with the transfer bin body (20).

7. The unmanned aerial vehicle frame according to claim 6, wherein the sealing connection assembly (93) further comprises a sealing collar (932), the sealing collar (932) is in sealing connection with the connection end of the horn (30), a sealing connection portion (9321) extends out of the end of the sealing collar (932) far away from the horn (30), the sealing connection portion (9321) extends into the first end of the sealing hose (931), a matching protrusion (93210) is arranged on the circumferential wall of the sealing connection portion (9321), and a sealing ring groove (931) which is clamped with the matching protrusion (93210) is arranged on the inner side wall of the first end of the sealing hose (931).

8. The unmanned aerial vehicle frame according to claim 6, wherein the sealing connection assembly further comprises a sealing pressing ring (933) sleeved on the sealing hose (931), a connection protrusion (931) is arranged on the outer side of the second end of the sealing hose (931), and the sealing pressing ring (933) is fixedly connected to the first side wall (201) so as to press the connection protrusion (931) of the second end of the sealing hose (931) against the first side wall (201) in a sealing manner.

9. The unmanned aerial vehicle frame according to claim 8, wherein the inner side of the sealing collar (933) is provided with a connecting groove (9331), the connecting projection (9311) being stopped in the connecting groove (9331).

10. The unmanned aerial vehicle frame according to claim 8, wherein the first side wall (201) is provided with a side wall protrusion (213), the side wall protrusion (213) surrounds the mounting through hole (212), the side wall protrusion (213) extends into the second end of the sealing hose (931), and an outer wall surface of the side wall protrusion (213) is in contact with an inner wall surface of the sealing hose (931).

11. The unmanned aerial vehicle frame according to claim 5, wherein the end of the mounting frame is fixedly connected to a third side wall (203) of the transfer bin (20), the mounting frame being for mounting the liquid reservoir.

12. The unmanned aerial vehicle frame of claim 11, further comprising a foot rest (80), the foot rest (80) comprising a front leg (110) for connection to a front end of a fuselage carrying panel (10) and a rear leg (130) for connection to a rear end of the mounting frame, wherein the front leg (110) comprises a front support portion (1130) and a first turn (1120), the front support portion (1130) being connected to the first turn (1120) and forming a first turn at the junction of the two, an end of the front support portion (1130) remote from the first turn (1120) being adapted to be supported to a support surface, an end of the first turn (1120) remote from the front support portion (1130) being adapted to be connected to the fuselage carrying panel (10), and an opening of the first turn being directed towards the rear leg (130).

13. The unmanned aerial vehicle frame of claim 12, wherein the rear leg (130) comprises a rear support portion (1330) and a second detour portion (1320), the rear support portion (1330) being connected to the second detour portion (1320) and forming a second turn at the junction of the two, an end of the rear support portion (1330) remote from the second detour portion (1320) being adapted to be supported to the support surface, an end of the second detour portion (1320) remote from the rear support portion (1330) being adapted to be connected to the mounting frame, and the second turn opening towards the front leg (110).

14. The unmanned aerial vehicle frame according to claim 13, wherein the first detour (1120) and the front support (1130) are arranged in a decreasing order in the direction from the fuselage carrier plate (10) to the support surface, and the second detour (1320) and the rear support (1330) are arranged in a decreasing order in the direction from the mounting frame to the support surface.

15. The unmanned aerial vehicle frame of claim 14, wherein the front leg (110) further comprises a reinforcement (1150), the reinforcement (1150) is disposed on the first turn (1120), and the reinforcement (1150) extends along the first turn onto the front support (1130).

16. The unmanned aerial vehicle bay according to any one of claims 1 to 15, wherein the transfer bin cover (40) is detachably connected to the transfer bin body (20).

17. The unmanned aerial vehicle rack according to any one of claims 1 to 15, wherein the fuselage carrier plate (10) comprises a first carrier plate (11) and a second carrier plate (12), the first carrier plate (11) is arranged opposite to the second carrier plate (12), and the transfer bin body (20) is arranged between the first carrier plate (11) and the second carrier plate (12), a first mating hole (111) is arranged on the first carrier plate (11), and the opening end of the connecting cavity (211) is arranged opposite to the first mating hole (111).

18. The unmanned aerial vehicle bay according to any of claims 1 to 15, wherein at least a portion of the transfer cover (40) is made of a transparent material.

19. An unmanned aerial vehicle, comprising: a first element, a second element and a frame, the frame being a drone frame according to any one of claims 1 to 18, the first element and the second element being mounted on a fuselage carrier plate (10) of the drone frame.