CN213443068U

CN213443068U - A unmanned aerial vehicle that is used for fuselage subassembly of unmanned aerial vehicle and has it

Info

Publication number: CN213443068U
Application number: CN202021994248.1U
Authority: CN
Inventors: 徐智芹; 何建兵; 肖锭锋
Original assignee: Guangzhou Xaircraft Technology Co Ltd
Current assignee: Guangzhou Xaircraft Technology Co Ltd
Priority date: 2020-09-11
Filing date: 2020-09-11
Publication date: 2021-06-15
Anticipated expiration: 2030-09-11

Abstract

The utility model discloses an unmanned aerial vehicle that is used for unmanned aerial vehicle's fuselage subassembly and has it, the fuselage subassembly includes: installing a frame; the connecting beam is fixedly connected with the mounting frame, the connecting beam is an integrally-formed part, and an antenna mounting seat is arranged on the connecting beam; the plurality of machine arms are arranged on the connecting beam at intervals. The utility model discloses a fuselage subassembly, reducible unmanned aerial vehicle make the structural distribution of fuselage subassembly more reasonable at the installation with the interference that dismantles the in-process and receive.

Description

A unmanned aerial vehicle that is used for fuselage subassembly of unmanned aerial vehicle and has it

Technical Field

The utility model belongs to the technical field of unmanned aerial vehicle's technique and specifically relates to an unmanned aerial vehicle that is used for unmanned aerial vehicle's fuselage subassembly and has it.

Background

In the unmanned aerial vehicle's of correlation technique fuselage subassembly, the position of antenna mount pad sets up unreasonablely, easily makes some parts in the unmanned aerial vehicle appear interfering with dismantling the in-process in the installation, even unmanned aerial vehicle receives the interference with dismantling the in-process in the installation, the structure of fuselage subassembly remains to be improved.

SUMMERY OF THE UTILITY MODEL

The utility model discloses aim at solving one of the technical problem that exists among the prior art at least. Therefore, an object of the utility model is to provide a fuselage subassembly for unmanned aerial vehicle, reducible unmanned aerial vehicle makes the structural distribution of fuselage subassembly more reasonable at the interference that the installation received with the dismantlement in-process.

The utility model also provides an unmanned aerial vehicle, including foretell fuselage subassembly.

According to the utility model discloses a fuselage subassembly for unmanned aerial vehicle, include: installing a frame; the connecting beam is fixedly connected with the mounting frame, the connecting beam is an integrally-formed part, and an antenna mounting seat is arranged on the connecting beam; the plurality of machine arms are arranged on the connecting beam at intervals.

According to the utility model discloses a fuselage subassembly for unmanned aerial vehicle through setting up the tie-beam, makes the tie-beam be integrated into one piece spare to can improve the production efficiency of tie-beam to a certain extent, improve the structural strength of tie-beam, can improve fuselage subassembly's assembly efficiency simultaneously effectively. Compared with the prior art, the connecting beam does not need to be assembled, so that the use of connecting pieces (such as screws) and the like can be effectively reduced, the weight of the connecting beam can be reduced to a certain degree, and the weight of the machine body assembly is reduced. Through set up the antenna mount pad on the tie-beam to be favorable to making antenna mount pad and installing frame spaced apart, thereby can avoid effectively taking place to interfere with unmanned aerial vehicle's battery or stock solution container etc. reduces the interference that receives in the unmanned aerial vehicle assembling process, the installation and the dismantlement operation of the battery of being convenient for and stock solution container. And then can improve the reliability of unmanned aerial vehicle structure, make the structural distribution of fuselage subassembly more reasonable.

According to some embodiments of the utility model, the antenna mount pad includes first mount pad and the second mount pad that the interval set up, first mount pad is suitable for the installation to be used for the location unmanned aerial vehicle's first antenna, the second mount pad is suitable for the installation to be used for receiving unmanned aerial vehicle's remote control instruction's second antenna.

In some embodiments of the present invention, the first mounting seat is located at an upper end of the connection beam, and/or the second mounting seat is located at a lower end of the connection beam.

In some embodiments of the present invention, the mounting opening of the first mounting seat is disposed upward, and/or the mounting opening of the second mounting seat is disposed downward.

In some embodiments of the present invention, the first mounting seat and the second mounting seat are disposed in a staggered manner in the vertical direction.

According to some embodiments of the utility model, the antenna mount pad with the installing frame is in the setting of misplacing in the fore-and-aft direction.

According to some embodiments of the utility model, the antenna mount pad is a plurality of, and is a plurality of the antenna mount pad distributes the left and right sides of tie-beam.

According to the utility model discloses a some embodiments, the tie-beam orientation is kept away from the direction of installing frame is sunken in order to inject the cooperation space, at least some of installing frame is located in the cooperation space, be equipped with the intercommunicating pore on the antenna mount pad, the intercommunicating pore with the cooperation space intercommunication.

According to some embodiments of the utility model, the tie-beam includes first roof beam body and two the second roof beam body, two the second roof beam body is located respectively the relative both ends of first roof beam body and with first roof beam body links to each other, first roof beam body with the installing frame cooperation is connected, the horn is two, two the horn is with two the second roof beam body one-to-one, every the horn with correspond the second roof beam body links to each other, be equipped with on the second roof beam body the antenna mount pad.

According to the utility model discloses unmanned aerial vehicle, include according to the utility model discloses the fuselage subassembly of above-mentioned embodiment.

According to the utility model discloses unmanned aerial vehicle is according to through setting up the utility model discloses the fuselage subassembly of above-mentioned embodiment. Thereby can improve the production efficiency of tie-beam to a certain extent, improve the structural strength of tie-beam, can improve unmanned aerial vehicle's assembly efficiency simultaneously effectively. Compared with the prior art, the connecting beam does not need to be assembled, so that the use of connecting pieces (such as screws) and the like can be effectively reduced, the weight of the connecting beam can be reduced to a certain degree, and the weight of the machine body assembly is reduced. Meanwhile, the interference of the unmanned aerial vehicle in the mounting and dismounting process can be reduced, and the battery and the liquid storage container can be conveniently mounted and dismounted. And then can improve the reliability of unmanned aerial vehicle structure, make unmanned aerial vehicle's structural distribution more reasonable.

Additional aspects and advantages of the invention will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of the invention.

Drawings

The above and/or additional aspects and advantages of the present invention will become apparent and readily appreciated from the following description of the embodiments, taken in conjunction with the accompanying drawings of which:

fig. 1 is a schematic diagram of an unmanned aerial vehicle according to some embodiments of the present invention;

fig. 2 is a schematic diagram of an unmanned aerial vehicle according to some embodiments of the present invention;

fig. 3 is a schematic diagram of an unmanned aerial vehicle according to some embodiments of the present invention;

FIG. 4 is an enlarged view of portion A of FIG. 3;

fig. 5 is a schematic diagram of an unmanned aerial vehicle according to some embodiments of the present invention;

fig. 6 is a schematic view of a connection beam according to some embodiments of the present invention;

fig. 7 is a schematic view of a connection beam according to some embodiments of the present invention;

fig. 8 is a schematic view of a connection beam according to some embodiments of the present invention;

fig. 9 is a schematic view of a connection beam according to some embodiments of the present invention;

fig. 10 is a schematic view of an installation frame according to some embodiments of the present invention;

fig. 11 is a schematic view of an installation frame according to some embodiments of the present invention;

fig. 12 is a schematic view of an installation frame according to some embodiments of the present invention;

fig. 13 is a schematic diagram of a partial structure of an unmanned aerial vehicle according to some embodiments of the present invention;

fig. 14 is a schematic view of a horn according to some embodiments of the present invention;

fig. 15 is a schematic view of a pivot according to some embodiments of the present invention;

fig. 16 is a schematic view of a mount according to some embodiments of the present invention;

fig. 17 is a schematic view of a latching assembly according to some embodiments of the present invention;

fig. 18 is a schematic view of a first lock member according to some embodiments of the present invention;

fig. 19 is a schematic view of a second lock fitting according to some embodiments of the present invention;

fig. 20 is a schematic view of a locking member according to some embodiments of the present invention;

fig. 21 is a schematic diagram of a partial structure of a drone according to some embodiments of the present invention;

figure 22 is a schematic view of a foot stool support leg according to some embodiments of the present invention;

fig. 23 is a schematic view of a second fitting according to some embodiments of the present invention;

fig. 24 is a schematic view of a first fixture according to some embodiments of the present invention;

fig. 25 is a schematic view of a second mount according to some embodiments of the invention;

fig. 26 is a schematic view of a reservoir according to some embodiments of the present invention;

fig. 27 is a schematic view of a reservoir according to some embodiments of the present invention;

fig. 28 is a schematic diagram of a first antenna according to some embodiments of the present invention;

fig. 29 is a schematic diagram of a second antenna according to some embodiments of the present invention;

fig. 30 is a schematic view of a power assembly according to some embodiments of the present invention;

FIG. 31 is a sectional view taken in the direction B-B in FIG. 30;

fig. 32 is a schematic view of a power assembly according to some embodiments of the present invention;

fig. 33 is a schematic view of a connection receptacle according to some embodiments of the present invention.

Reference numerals:

the unmanned aerial vehicle 100, the fuselage assembly 10,

the body 1 is provided with a plurality of connecting rods,

the connecting beam 11, the first beam body 111, the first matching groove 1110, the upper end wall 1111, the lower end wall 1112, the front end wall 1113, the first connecting portion 1114, the first connecting hole 11141, the stopping surface 1115, the stopping portion 1116, the connecting column 1117, the inserting and matching hole 11171, the wire passing hole 1118, the reinforcing hole 1119,

a pivot portion 112, a second mating groove 1120, an upper pivot wall 1121, a lower pivot wall 1122, a front pivot wall 1123, an antenna mounting base 1124, a first mounting base 11241; a second mounting base 11242;

a first rib 1125, a pivoting hole 1126, a reinforcing protrusion 1127,

the engaging portion 113, the third engaging groove 1130, the first limiting groove 1131, the limiting protrusion 1132, the second reinforcing rib 1133, the second beam 114,

mounting frame 12, mounting cavity 120, first mounting cavity 1201, second mounting cavity 1202,

a front end plate 121, a rear end plate 122, a side plate 123, a first side plate part 1231, a second mounting protrusion 12311, a second side plate part 1232, a transition part 1233, a positioning groove 1234, a positioning hole 1235,

the second connecting portion 124, the partition plate 125, the reinforcing plate 126, the battery guide module 127,

the reservoir guide module 128 is configured to guide the reservoir,

the number of the mounting frames 13 is such that,

the protection frame 14, the protection rod 141, the fixed seat 142,

the machine arm (2) is provided with a machine arm,

the pivot member 21, the engaging portion 211, the engaging hole 2110, the first outer wall 2111, the second outer wall 2112,

a second retaining groove 2113, a pivot protrusion 212, a mating hole 2122,

the arm lever (22) is provided with a lever,

the arm assembly 23, the mounting member 231, the mounting base plate 2311, the adapter 2312, the arm 232,

the arm-supporting bar 2321, the pivoting member 2322, the latch holder assembly 233, the first latch assembly 2331, the first circular ring portion 23311, the first pivot protrusion 23312, the pivot block 23313, the first latch portion 23314, the groove portion 23315, the second latch assembly 2332, the second circular ring portion 23321, the second pivot protrusion 23322, the second latch portion 23323,

a third limiting groove 23324, a locking member 2333, a mating boss 23331, a third pivot projection 23332,

connecting bar 23333, boss 23334, pivot bar 2334,

the landing gear 3 is provided with a landing gear,

the support leg assembly 301 is provided with,

a horse support leg 31, a front support leg 311, a first leg section 3111, a second leg section 3112, a support section 3113,

the length of the bottom leg 312, the rear leg 313,

the first fitting part 32 is provided with a first fitting part,

landing gear attachment assembly 33, first mount 331, second mount 332,

the second fitting piece 34, the connecting projection 341,

the power assembly (4) is provided with a power assembly,

a connecting seat 41, a sleeve part 411, a sleeve hole 4110, an extending part 412, a mounting part 413,

mounting assembly 42, mounting post 421, bearing 422, coupling assembly 423, fixed mount 424, rotating member 425,

a power unit 43, a power motor 431, a propeller assembly 432,

a driving device 44, a steering engine 441, a transmission shaft 442, a connecting rod assembly 443, a first connecting piece 4431,

the second adaptor 4432, the link 4433,

a liquid storage container 5, a liquid storage cavity 50, a liquid storage cavity 51, an upper box 511, a mounting groove 5111, a lower box 512,

the NFC reader-writer comprises a battery 6, an electronic control module 7, a communication module 71, a first antenna 711, a second antenna 712, a flight control module 72 and an NFC reader-writer 8.

Detailed Description

Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the drawings are exemplary only for the purpose of explaining the present invention, and should not be construed as limiting the present invention.

A fuselage assembly 10 for a drone 100 in accordance with an embodiment of the invention is described below with reference to fig. 1-33. Wherein, unmanned aerial vehicle 100 can be used for carrying out operations such as pesticide spraying or moisture sprinkling irrigation to crops in the agro-farming industry. Of course, the drone 100 may also be used in other fields such as spraying of fire-extinguishing fluid in forest fires, aerial photography, power routing inspection, environmental monitoring, forest fire prevention, and disaster patrol.

As shown in fig. 1-3, a fuselage assembly 10 for a drone 100 according to embodiments of the present invention includes: a mounting frame 12, a connecting beam 11 and a plurality of booms 2.

Specifically, as shown in fig. 1 to 3, the connection beam 11 is fixedly connected to the mounting frame 12, the connection beam 11 is an integrally formed member, the connection beam 11 is provided with the antenna mounting seat 1124, and the plurality of arms 2 are provided on the connection beam 11 at intervals. It should be noted that the mounting frame 12 may be used to mount the battery 6 and the liquid storage container 5 of the drone 100.

From this, in the fuselage assembly 10 of the unmanned aerial vehicle 100, the mounting frame 12 and the plurality of horn 2 can be provided on the connection beam 11. And tie-beam 11 is the structure setting of integrated into one piece, can improve the production efficiency of tie-beam 11 to a certain extent, improves the structural strength of tie-beam 11, can improve the assembly efficiency of fuselage subassembly 10 simultaneously effectively. Compared with the prior art, the connecting beam 11 does not need to be assembled, so that the use of connecting pieces and the like can be effectively reduced, the weight of the connecting beam 11 can be reduced to a certain degree, and the weight of the machine body assembly 10 is reduced.

As is known, the drone 100 has an antenna for locating the position of the drone 100, and also has an antenna for receiving remote control instructions issued by a user via the remote control device of the drone 100. Thus, the antenna mounting base 1124 may be used to mount both antennas, but may also mount other antennas for other purposes in the drone 100. Because tie-beam 11 and installing frame 12 fixed connection, and antenna mount 1124 establishes on tie-beam 11, thereby be favorable to making antenna mount 1124 and installing frame 12 spaced apart, thereby can know, when installation and dismantlement battery 6 and liquid storage container 5, the position setting of antenna mount 1124, can avoid effectively taking place to interfere with battery 6 or liquid storage container 5 etc., reduce unmanned aerial vehicle 100 at the installation and the interference of dismantling the in-process and receiving, be convenient for battery 6 and liquid storage container 5's installation and dismantlement operation. And then can improve the reliability of unmanned aerial vehicle 100 structure, make the structural distribution of fuselage subassembly 100 more reasonable.

According to the utility model discloses a fuselage subassembly 10 for unmanned aerial vehicle 100 through setting up tie-beam 11, makes tie-beam 11 be integrated into one piece spare to can improve the production efficiency of tie-beam 11 to a certain extent, improve the structural strength of tie-beam 11, can improve fuselage subassembly 10's assembly efficiency simultaneously effectively. In addition, compared with the prior art, the connecting beam 11 does not need to be assembled, so that the use of connecting pieces (such as screws) and the like can be effectively reduced, the weight of the connecting beam 11 can be reduced to a certain extent, and the weight of the machine body assembly 10 can be reduced. Through set up antenna mount 1124 on tie-beam 11 to be favorable to making antenna mount 1124 and installing frame 12 spaced apart, thereby can avoid effectively taking place to interfere with unmanned aerial vehicle 100's battery 6 or stock solution container 5 etc. reduce unmanned aerial vehicle 100 at the installation and the interference of dismantling the in-process and receiving, be convenient for the installation and the dismantlement operation of battery 6 and stock solution container 5. And then can improve the reliability of unmanned aerial vehicle 100 structure, make the structural distribution of fuselage subassembly 100 more reasonable.

As shown in fig. 1, 8 and 9, according to some embodiments of the present invention, the antenna mount 1124 includes a first mount 11241 and a second mount 11242 arranged at intervals, the first mount 11241 is adapted to mount a first antenna 711 for positioning the drone 100, and the second mount 11242 is adapted to mount a second antenna 712 for receiving remote control commands of the drone 100. It can be seen that the first antenna 711 and the second antenna 712 of the drone 100 may both be mounted on the antenna mount 1124 on the connecting beam 11. And the first mounting seat 11241 and the second mounting seat 11242 are arranged at intervals, so that signal interference between the first antenna 711 and the second antenna 712 can be avoided to a certain extent, mutual interference between the first antenna 711 and the second antenna 712 during installation and disassembly can be avoided to a certain extent, and the reliability of the structure of the unmanned aerial vehicle 100 is improved.

As shown in fig. 1, 2, 5 and 8, in some embodiments of the present invention, the first mounting seat 11241 is located at the upper end of the connection beam 11 and/or the second mounting seat 11242 is located at the lower end of the connection beam 11. It can be seen that, in the embodiment of the present invention, the first mounting seat 11241 may be located at the upper end of the connection beam 11, the second mounting seat 11242 may be located at the lower end of the connection beam 11, the first mounting seat 11241 may be located at the upper end of the connection beam 11, and the second mounting seat 11242 may be located at the lower end of the connection beam 11.

First antenna 711 is used for fixing a position unmanned aerial vehicle 100's position, mainly fixes a position through cooperating with the satellite to first mount pad 11241 is located the position setting of the upper end of tie-beam 11, can reduce effectively that other structures on unmanned aerial vehicle 100 are to the sheltering from of first antenna 711 in the upper and lower direction, improves the effect that first antenna 711 effectively fixes a position unmanned aerial vehicle 100. Positioning of the drone 100 is made more accurate. It is known that second antenna 712 is used for receiving the remote control command that unmanned aerial vehicle 100's remote control unit sent, and the user of operation remote control unit mainly is located unmanned aerial vehicle 100's below (namely on land), thereby second mount pad 11242 is located the position setting of the lower extreme of tie-beam 11, can reduce the sheltering from of other structures on unmanned aerial vehicle 100 to second antenna 712 in the up-and-down direction effectively, improve the speed that second antenna 712 receives remote control command, make the more omnidirectional receipt remote control command of second antenna 712, and then make unmanned aerial vehicle 100's controllability higher, unmanned aerial vehicle 100's running state changes more accurately, improve fuselage subassembly 10's reliability, improve unmanned aerial vehicle 100's reliability.

As shown in fig. 8 and 9, in some embodiments of the invention, the mounting port of the first mounting block 11241 is disposed upward and/or the mounting port of the second mounting block 11242 is disposed downward. Thus, in the embodiment of the present invention, the mounting hole of the first mounting seat 11241 may be disposed upward, the mounting hole of the second mounting seat 11242 may be disposed downward, the mounting hole of the first mounting seat 11241 may be disposed upward, and the mounting hole of the second mounting seat 11242 may be disposed downward.

The first antenna 711 is used for positioning the position of the unmanned aerial vehicle 100, and is mainly positioned by being matched with a satellite, so that the mounting port of the first mounting seat 11241 faces upwards, and after the first antenna 711 is mounted on the first mounting seat 11241, the first antenna 711 can vertically extend upwards, and therefore the effect of effectively positioning the unmanned aerial vehicle 100 by the first antenna 711 can be further improved. Positioning of the drone 100 is made more accurate. It is known that second antenna 712 is used for receiving the remote control command that unmanned aerial vehicle 100's remote control unit sent, and the user of operation remote control unit mainly is located unmanned aerial vehicle 100's below (namely on land), thereby second mount pad 11242's installing port sets up down, then after second antenna 712 installs to second mount pad 11242, can vertical downwardly extending, can further improve the speed that second antenna 712 received the remote control command from this, make the more omnidirectional receipt remote control command of second antenna 712, and then make unmanned aerial vehicle 100's controllability higher, unmanned aerial vehicle 100's running state changes more accurately, improve fuselage assembly 10's reliability, improve unmanned aerial vehicle 100's reliability.

As shown in fig. 1, 5, and 8-9, in some embodiments of the present invention, the first mounting seat 11241 and the second mounting seat 11242 are disposed in a vertically offset manner. Thereby, be favorable to guaranteeing the structural strength of tie-beam 11, avoid first antenna 711 and second antenna 712 at the installation simultaneously and dismantle in-process mutual interference, improve fuselage subassembly 10's reliability, improve unmanned aerial vehicle 100's reliability.

As shown in fig. 1, according to some embodiments of the present invention, the antenna mounting seat 1124 and the mounting frame 12 are disposed in a staggered manner in the front-rear direction. Thereby can further guarantee that antenna mount 1124 is spaced apart from installing frame 12, from this, when installation and dismantlement battery 6 and stock solution container 5, can avoid antenna mount 1124 and battery 6 or stock solution container 5 etc. to take place to interfere effectively, reduce unmanned aerial vehicle 100 at the installation and the interference that receives of dismantlement in-process, be convenient for the installation and the dismantlement operation of battery 6 and stock solution container 5. And then can improve the reliability of unmanned aerial vehicle 100 structure, make the structural distribution of fuselage subassembly 100 more reasonable.

According to some embodiments of the present invention, the antenna mounts 1124 are multiple, and the multiple antenna mounts 1124 are distributed on the left and right sides of the connection beam 11. Thereby making the structural distribution of the body assembly 10 more reasonable, and it can be understood that, when each antenna mount 1124 includes the first mount 11241 adapted to mount the first antenna 711 for positioning the drone 100 and the second mount 11242 adapted to mount the second antenna 712 for receiving the remote control command of the drone 100 of the above-described embodiment, since the plurality of antenna mounts 1124 are distributed on the left and right sides of the connection beam 11, it can be known that the plurality of first mounts 11241 are distributed on the left and right sides of the connection beam 11 and the plurality of second mounts 11242 are distributed on the left and right sides of the connection beam 11.

For example, as shown in fig. 1, 5, 8, and 9, the left and right sides of the connection beam 11 are respectively provided with a first mounting seat 11241 and a second mounting seat 11242, so that the first antenna 711 can be mounted on the left and right sides of the connection beam 11, the second antenna 712 can be mounted on the left and right sides of the connection beam 11, and the positions of the first antennas 711 and the second antennas 712 are set, so that the positioning effect of the unmanned aerial vehicle 100 can be improved, and the control accuracy of the unmanned aerial vehicle 100 can be improved. Moreover, it can be understood that the antennas for the same purpose are located on the left and right sides of the connecting beam 11, so that mutual signal interference can be avoided, the range of the transmittable signal and the receivable signal of the antenna of the unmanned aerial vehicle 100 can be expanded, and the reliability of the unmanned aerial vehicle 100 is improved.

According to the utility model discloses a some embodiments, the tie-beam 11 is sunken in order to inject the fitting space towards the direction of keeping away from installing frame 12, and at least a part of installing frame 12 is located the fitting space, is equipped with the intercommunicating pore on the antenna mount 1124, intercommunicating pore and fitting space intercommunication. Therefore, the structural arrangement of the connecting beam 11 can improve the reliability of the fixed connection of the mounting frame 12 of the connecting beam 11, and meanwhile, a certain space is formed between the connecting beam 11 and the mounting frame 12, so that the wiring is convenient. And the setting of intercommunicating pore on antenna mount 1124 can make the partly of installing the antenna on antenna mount 1124 stretch into the fitting space through the intercommunicating pore in, and then the antenna of being convenient for links to each other with unmanned aerial vehicle 100's flight control module 72.

As shown in fig. 1 and 8, according to some embodiments of the present invention, the connection beam 11 includes a first beam 111 and two second beams 114, the two second beams 114 are respectively located at two opposite ends of the first beam 111 and connected to the first beam 111, the first beam 111 is connected to the mounting frame 12 in a matching manner, the two booms 2 are two, the two booms 2 correspond to the two second beams 114 one-to-one, each boom 2 is connected to the corresponding second beam 114, and the second beam 114 is provided with an antenna mounting seat 1124. As can be seen, the connecting beam 11 is fixedly connected to the mounting frame 12 via the first beam 111, and is connected to the two arms 2 via the two second beams 114. Furthermore, the connecting beam 11 has a simple structure, and meanwhile, the connecting position of the connecting beam and the mounting frame 12 and the horn 2 is reasonably distributed, so that the horn 2 and the mounting frame 12 can be prevented from interfering when being connected and assembled with the connecting beam 11 to a certain extent, and the structural stability and reliability of the fuselage assembly 10 can be improved. And can know, because be equipped with antenna mount 1124 on the second roof beam body 114 to can guarantee effectively that the position of antenna mount 1124 sets up, can avoid to a certain extent taking place to interfere with battery 6 or stock solution container 5 etc. reduces the interference that unmanned aerial vehicle 100 received in the installation and dismantlement assembling process, the installation and the dismantlement operation of battery 6 and stock solution container 5 of being convenient for. And then can improve the reliability of unmanned aerial vehicle 100 structure, make the structural distribution of fuselage subassembly 10 more reasonable.

As shown in fig. 6, according to some embodiments of the present invention, a first reinforcing rib 1125 is disposed at the connection position of the second beam 114 and the first beam 111. Thereby can improve tie-beam 11's overall structure intensity, and then improve fuselage subassembly 10's reliability, improve unmanned aerial vehicle 100's reliability.

As shown in fig. 6, 7 and 10, according to some embodiments of the present invention, the first beam 111 is recessed toward a direction away from the mounting frame 12 to define a first fitting groove 1110, a first connecting portion 1114 is disposed on an inner wall of the first fitting groove 1110, a second connecting portion 124 is disposed on the mounting frame 12, and a portion of the mounting frame 12 is adapted to extend into the first fitting groove 1110 and is fittingly connected to the second connecting portion 124 through the first connecting portion 1114. Therefore, the installation frame 12 and the connection beam 11 can be fixedly connected through the first connection portion 1114 and the second connection portion 124, meanwhile, a part of the installation frame 12 extends into the structure of the first matching groove 1110, the installation frame 12 can be supported and positioned through the inner wall of the first matching groove 1110, the structural reliability of the fuselage assembly 10 can be further improved, and meanwhile, the first connection portion 1114 and the second connection portion 124 can be conveniently matched and connected by an operator.

As shown in fig. 6 and 7, in some embodiments of the present invention, the first connection portion 1114 is formed as a boss provided on an inner wall of the first fitting groove 1110, and a first connection hole 11141 is provided on the first connection portion 1114, the first connection hole 11141 penetrates through the first beam 111 in a thickness direction of the first beam 111, the second connection portion 124 is formed as a boss provided on the mounting frame 12, and a second connection hole is provided on the second connection portion 124, and the first connection hole 11141 and the second connection hole are fixedly connected by a connection member.

Therefore, the first connecting portion 1114 and the second connecting portion 124 have simple structures, simple and reliable matching connection modes and easy operation. The connecting piece can be a screw, so that the connecting piece is simple in structure, wide in source and low in cost. Meanwhile, it can be understood that, since the first connecting portion 1114 and the second connecting portion 124 are both formed as bosses, when the mounting frame 12 is connected with the connection beam 11 in a matching manner, the bosses formed by the first connecting portion 1114 and the bosses formed by the second connecting portion 124 need to be aligned, and the first connecting hole 11141 is opposite to the second connecting hole, so that the first connecting portion 1114 and the second connecting portion 124 can be fixedly connected through the connecting member. Therefore, the operator can align the first connecting portion 1114 and the second connecting portion 124 more accurately, and the efficiency of the matching connection between the installation frame 12 and the connecting beam 11 can be improved to a certain degree.

As shown in fig. 6, in some embodiments of the present invention, the inner wall of the first engaging groove 1110 is provided with a stopping portion 1116, at least a portion of an end surface of the stopping portion 1116 facing one side of the mounting frame 12 forms a stopping surface 1115, and at least a portion of the mounting frame 12 extending into the first engaging groove 1110 is adapted to stop against the stopping surface 1115 to make the first connecting portion 1114 and the second connecting portion 124 engage and connect. Therefore, the arrangement of the stopping portion 1116 can limit the mounting frame 12 to a certain extent, so that when at least a part of the mounting frame 12 extending into the first matching groove 1110 stops against the stopping surface 1115, the positions of the first connecting portion 1114 and the second connecting portion 124 are just opposite to each other, and the first connecting portion 1114 and the second connecting portion 124 are conveniently matched and connected, which is beneficial to improving the connecting and assembling efficiency of the mounting frame 12 and the connecting beam 11.

As shown in fig. 6, in some embodiments of the present invention, the stopping portions 1116 are plural and spaced apart, and each stopping portion 1116 extends along the circumferential direction of the inner wall of the first fitting groove 1110 to form a reinforcing rib structure. Therefore, the connection assembly efficiency of the installation frame 12 and the connecting beam 11 is improved, the structural strength of the connecting beam 11 can be improved, and the reliability of the machine body assembly 10 is improved.

As shown in fig. 6, 8 and 9, in some embodiments of the present invention, a wire passing hole 1118 penetrating through the first beam 111 is further disposed on the inner wall of the first fitting groove 1110, and the wire passing hole 1118 is far away from the mounting frame 12. Thereby be convenient for unmanned aerial vehicle 100's partial connecting wire penetrates first cooperation groove 1110 through crossing the line hole 1118 in, be favorable to avoiding unmanned aerial vehicle 100 to take place to scratch and break or scrape the connecting wire at the flight in-process with external things (for example branch) from this, and then can improve the fail safe nature that unmanned aerial vehicle 100 used, also can improve the outward appearance aesthetic property of fuselage subassembly 10 simultaneously, reduce fuselage subassembly 10's occupation space.

As shown in fig. 6, 8 and 9, according to some embodiments of the present invention, each of the second beams 114 includes a pivot portion 112 and a fitting portion 113 connected to each other, the pivot portion 112 is connected to the first beam 111, the pivot portion 112 is recessed toward a direction away from the mounting frame 12 to define a second fitting groove 1120, and one end of the horn 2 extends into the second fitting groove 1120 and is pivotally connected to the pivot portion 112. From this it can be known, horn 2 is pivotable for pin joint portion 112 to horn 2 is pivotable for tie-beam 11, and then when unmanned aerial vehicle 100 was idle, can fold horn 2, and then is favorable to reducing unmanned aerial vehicle 100's occupation space.

As shown in fig. 6, 7, 13 and 14, in some embodiments of the present invention, two opposite sidewalls of the second fitting groove 1120 are respectively provided with a pivot hole 1126, the pivot holes 1126 on different sidewalls are oppositely and coaxially disposed, each of the booms 2 includes a pivot member 21 and a boom rod 22, one end of the boom rod 22 is fixed on the pivot member 21, a portion of the pivot member 21 is located in the second fitting groove 1120, and a portion of the pivot member 21 located in the second fitting groove 1120 is provided with a fitting hole 2122, and the fitting holes 2122 are plural and are arranged one-to-one and coaxially with the pivot holes 1126 on the pivot portion 112. Therefore, when the boom 2 and the link beam 11 are coupled, a part of the pivot joint 21 needs to be inserted into the second coupling groove 1120 so that the plurality of coupling holes 2122 and the plurality of pivot holes 1126 are coaxially disposed in a one-to-one correspondence, and one adapter shaft can be sequentially inserted through the corresponding pivot hole 1126, coupling hole 2122, and pivot hole 1126, so as to pivotally couple the pivot joint 21 and the pivot joint 112, and further, the boom 2 and the link beam 11 can be pivotally coupled.

Specifically, as shown in fig. 6 and 7, the outer circumferential wall of the second fitting groove 1120 is provided with a reinforcing protrusion 1127, and the reinforcing protrusion 1127 is provided around the pivot hole 1126. Therefore, the reliability of the pivoting connection between the machine arm 2 and the connecting beam 11 can be improved, and the structural strength of the connecting beam 11 can be improved.

As shown in fig. 6, 8 and 9, in some embodiments of the present invention, the engaging portion 113 is recessed toward a direction away from the mounting frame 12 to define a third engaging groove 1130, the third engaging groove 1130 is communicated with the second engaging groove 1120, a portion of the pivot member 21 is located in the third engaging groove 1130, a first limiting groove 1131 recessed toward the third engaging groove 1130 is disposed on an outer peripheral wall of the third engaging groove 1130, and a limiting protrusion 1132 is disposed on a bottom wall of the first limiting groove 1131. As can be seen, the arm 2 is connected to the connecting beam 11 by the pivot 21. Meanwhile, the recessed direction of the first limiting groove 1131 is opposite to the recessed direction of the third matching groove 1130, and the arrangement of the limiting protrusion 1132 and the first limiting groove 1131 can also improve the structural strength of the second beam 114 to a certain extent.

As shown in fig. 8, in some embodiments of the present invention, a second reinforcement rib 1133 is disposed at the connection portion of the matching portion 113 and the pivoting portion 112. Thereby can improve the structural strength of second roof beam body 114, and then improve the overall structure intensity of tie-beam 11, improve the reliability of fuselage subassembly 10, improve unmanned aerial vehicle 100's reliability.

As shown in fig. 1 and 5, according to some embodiments of the present invention, the fuselage assembly 10 further includes two protection frames 14, and the two protection frames 14 are spaced apart from each other on the first beam 111 and located on a side of the first beam 111 away from the mounting frame 12. Components of the drone 100 that need to be protected can thus be arranged between two protection frames 14, for example the electronic control module 7 of the drone 100 can be arranged between the protection frames 14. And the two protection frames 14 can protect the electronic control module 7.

As shown in fig. 1, 6-9, in some embodiments of the present invention, a connection column 1117 is disposed on the first beam 111, an insertion hole 11171 is disposed on the connection column 1117, and a portion of the protection frame 14 is adapted to be inserted into the insertion hole 11171 to be connected to the first beam 111. Therefore, the matching mode of the protection frame 14 and the first beam body 111 is simple and easy to operate.

According to some embodiments of the present invention, the second beam 114 extends upwardly and rearwardly relative to the first beam 111. Therefore, since the extending direction of the first beam 111 is different from the extending direction of the second beam 114, the connecting beam 11 is integrally formed, so that the structural strength of the connecting beam 11 can be improved to some extent.

In some embodiments of the present invention, the second beam 114 extends upwardly at an angle of 10-35 with respect to the first beam 111. Optionally, the second beam 114 extends upwardly at an angle of 12 °, 19 °, 21 °, or 32 ° with respect to the first beam 111. It should be noted that, on a vertical plane parallel to the central axis of the first beam 111, an included angle between an orthographic projection of the central axis of the second beam 114 and the central axis of the first beam 111 is an angle that the second beam 114 extends upward relative to the first beam 111.

In some embodiments of the present invention, the second beam 114 extends rearward at an angle of 5 ° to 20 ° relative to the first beam 111. Optionally, the second beam 114 extends rearwardly at an angle of 9 °, 12 °, 14 °, or 16 ° relative to the first beam 111. It should be noted that an included angle between the central axis of the second beam 114 and an orthographic projection of the central axis of the first beam 111 on a horizontal plane is an angle that the second beam 114 extends backward relative to the first beam 111.

As shown in fig. 1-33, the unmanned aerial vehicle 100 according to the embodiment of the present invention includes the fuselage assembly 10 according to the above-mentioned embodiment of the present invention.

According to the utility model discloses unmanned aerial vehicle 100 is through setting up the basis the utility model discloses above-mentioned embodiment's fuselage subassembly 10. Thereby can improve the production efficiency of tie-beam 11 to a certain extent, improve the structural strength of tie-beam 11, can improve unmanned aerial vehicle 100's assembly efficiency simultaneously. And compare with prior art, tie-beam 11 need not to assemble, and then can reduce the use of connecting piece etc. effectively, and then also can reduce the weight of tie-beam 11 to a certain extent, makes unmanned aerial vehicle 100 lightweight. Meanwhile, the interference on the installation and disassembly processes of the unmanned aerial vehicle 100 can be reduced, and the battery 6 and the liquid storage container 5 can be conveniently installed and disassembled. And then can improve the reliability of unmanned aerial vehicle 100 structure, make unmanned aerial vehicle 100's structural distribution more reasonable.

The following describes the drone 100 according to a specific embodiment of the invention with reference to fig. 1-33. It is to be understood that the following description is exemplary only, and is intended to be illustrative of the present invention and is not to be construed as limiting the invention. Specifically, the drone 100 may be used in the agro-farming industry to perform operations such as pesticide spraying or water sprinkling irrigation on crops. Of course, this unmanned aerial vehicle 100 also can be used for spraying of fire extinguishing fluid in the forest fire, take photo by plane, other fields such as electric power inspection, environmental monitoring, forest fire prevention and disaster patrol.

Referring to fig. 1-33, a drone 100 according to an embodiment of the present invention includes: fuselage assembly 10, landing gear 3, power assembly 4, liquid storage container 5, battery 6 and electronic control module 7. The machine arms 2 are distributed on two sides of the machine body 1 and connected with the machine body 1. The body assembly 10 includes a body 1 and a horn 2. The landing gear 3 is fixed below the fuselage 1 to ensure the stability of the drone 100 in takeoff and landing. Power component 4 is fixed in the tip that fuselage 1 was kept away from to horn 2, and power component 4 provides lift for unmanned aerial vehicle 100 flight. Liquid storage container 5 carries and is used for the splendid attire to wait to spray or wait the article of transportation on fuselage 1, and battery 6 is fixed in on the fuselage 1, and power component 4 provides power for unmanned aerial vehicle 100, and electric control module 7 is fixed in on the fuselage 1 for control unmanned aerial vehicle 100's flight posture.

Referring to fig. 1 to 9, the fuselage 1 includes a connection beam 11 and a mounting frame 12 fixedly connected to the connection beam 11. The connection beam 11 includes a first beam 111 and two second beams 114 connected to two ends of the first beam 111, and each of the second beams 114 includes a pivot portion 112 and a matching portion 113 connected to each other.

Referring to fig. 6 and 7, the first beam body 111 includes an upper end wall 1111, a lower end wall 1112, and a front end wall 1113 connected between the upper end wall 1111 and the lower end wall 1112, wherein the front end wall 1113 is formed substantially in a structure having a circular arc shape in section. The upper end wall 1111, the lower end wall 1112 and the front end wall 1113 collectively enclose a first fitting groove 1110 opened rearward, so that the first beam body 111 is formed in a substantially U-shaped configuration in cross section. The first coupling portion 1114 and the stopping surface 1115 are formed on the inner wall of the first coupling groove 1110. The first connecting portion 1114 can extend along the upper end wall 1111, the lower end wall 1112 and the front end wall 1113, and the first connecting portion 1114 has a first connecting hole 11141 formed through the outer wall of the first beam 111.

Preferably, the inner wall of the first fitting groove 1110 is further formed with a stopping portion 1116, and the stopping portion 1116 may extend transversely and/or longitudinally along the inner walls of the upper end wall 1111, the lower end wall 1112 and the front end wall 1113 to form a reinforcing rib structure. The abutting surface 1115 may be formed on the abutting portion 1116 on the upper end wall 1111 and the lower end wall 1112, that is, at least a part of an end surface of the abutting portion 1116 facing the side of the mounting frame 12 forms the abutting surface 1115, and the abutting surface 1115 on the upper end wall 1111 and the abutting surface 1115 on the lower end wall 1112 are coplanar.

Furthermore, a connection column 1117 is formed on the outer peripheral surface of the upper end wall 1111, and the connection column 1117 is provided with an insertion hole 11171 with a forward opening. The front end wall 1113 is also provided with a wire through hole 1118.

Referring to fig. 6 to 9, the pivotal connection portions 112 include two, each of the pivotal connection portions 112 is also formed in a substantially U-shaped cross section, each of the pivotal connection portions 112 extends upward and rearward along the end surface of the first beam 111, wherein each of the pivotal connection portions 112 extends upward at an angle of 10 ° to 35 ° with respect to the first beam 111. Specifically, each pivot 112 extends upwardly at an angle of 12 °, 19 °, 21 °, or 32 ° with respect to the first beam 111. It should be noted that, on a vertical plane parallel to the central axis of the first beam 111, an included angle between an orthographic projection of the central axis of the second beam 114 and the central axis of the first beam 111 is an angle that the second beam 114 extends upward relative to the first beam 111. Wherein each pivot portion 112 extends rearwardly at an angle of 5-20 ° relative to the first beam 111. Specifically, each pivot 112 extends rearwardly at an angle of 9 °, 12 °, 14 °, or 16 ° relative to the first beam 111. It should be noted that an included angle between the central axis of the second beam 114 and an orthographic projection of the central axis of the first beam 111 on a horizontal plane is an angle that the second beam 114 extends backward relative to the first beam 111. A second engagement groove 1120 with a backward opening is formed in the pivot portion 112, and the second engagement groove 1120 is communicated with the first engagement groove 1110.

Specifically, each pivot portion 112 includes an upper pivot wall 1121, a lower pivot wall 1122, and a front pivot wall 1123 connected to the upper pivot wall 1121 and the lower pivot wall 1122. The upper pivoting wall 1121, the lower pivoting wall 1122, and the front pivoting wall 1123 extend along the ends of the upper end wall 1111, the lower end wall 1112, and the front end wall 1113, respectively, and first ribs 1125 are formed at the joints between the upper pivoting wall 1121 and the upper end wall 1111 and between the lower end wall 1112 and the lower pivoting wall 1122 to increase the connection strength between the pivoting wall 1121 and the upper end wall 1111 and between the lower end wall 1112 and the lower pivoting wall 1122. The upper pivoting wall 1121, the lower pivoting wall 1122 and the front pivoting wall 1123 enclose a second engaging groove 1120 with a rearward opening, and the upper pivoting wall 1121 and the lower pivoting wall 1122 are respectively provided with a pivoting hole 1126 coaxially disposed. The upper hinge wall 1121 and the lower hinge wall 1122 are also respectively provided with an antenna mounting seat 1124 extending vertically. The antenna mounting seat 1124 has a communication hole communicating with the second engagement groove 1120.

Further, as shown in fig. 9, an engaging portion 113 extends from an end of the pivot portion 112, and second ribs 1133 are respectively formed between an outer peripheral surface of the engaging portion 113 and the upper pivot wall 1121, the lower pivot wall 1122, and the front pivot wall 1123 of the pivot portion 112. The engaging portion 113 has an arc-shaped cross section, a third engaging groove 1130 having a rearward opening is formed in the engaging portion 113, and the third engaging groove 1130 has an arc shape and communicates with the second engaging groove 1120. The outer peripheral surface of the fitting portion 113 is further provided with a first limiting groove 1131, and a limiting protrusion 1132 is formed on the bottom wall of the first limiting groove 1131.

Referring to fig. 6 to 7 and 10 to 12, the mounting frame 12 is adapted to be coupled to the first beam body 111. Specifically, the mounting frame 12 includes a front end plate 121, a rear end plate 122, and two side plates 123 respectively connected to both ends of the front end plate 121 and the rear end plate 122. The front end plate 121 and the two side plates 123 are formed with second connecting portions 124, and the second connecting portions 124 are adapted to be connected with the first connecting portions 1114 to fixedly connect the mounting frame 12 with the first beam body 111. When the end surface of the front end plate 121 abuts against the abutting surface 1115 on the inner wall of the first mating groove 1110 during installation, each second connecting portion 124 is opposite to each first connecting portion 1114.

Referring to fig. 3, 10 to 12, the front end plate 121, the rear end plate 122 and the two side plates 123 together enclose a vertically penetrating mounting cavity 120. The liquid storage container 5 and the batteries 6 are suitable for penetrating into the mounting cavity 120 and are detachably connected with one or more of the front end plate 121, the rear end plate 122 and the two side plates 123. The two side plates 123 are formed as a first side plate portion 1231 and a second side plate portion 1232 which are connected in a bending manner, and the first side plate portion 1231 and the second side plate portion 1232 are connected by a transition portion 1233. Continuous reinforcing ribs are also formed on the side surfaces of the first side plate portion 1231, the second side plate portion 1232, and the transition portion 1233.

Further, the mounting frame 12 further includes a partition plate 125, and two ends of the partition plate 125 are respectively connected to the ends of the two second side plate portions 1232 close to the transition portion 1233. Isolation plate 125 divides mounting cavity 120 into first mounting cavity 1201 and second mounting cavity 1202. The battery 6 may be mounted in the first mounting space 1201, and the reservoir 5 may be mounted in the second mounting space 1202.

Further, referring to fig. 12, the first side plate 1231 is further provided with a positioning groove 1234, the sidewall of the first side plate 1231 is formed with a second mounting protrusion 12311, and the second mounting protrusion 12311 is provided with a positioning hole 1235. The second mounting protrusion 12311 is used to mount the landing gear 3.

Preferably, the mounting frame 12 further includes a reinforcing plate 126, the reinforcing plate 126 is disposed parallel to the front end plate 121, and both ends of the reinforcing plate 126 are connected to the first side plate 1231. The reinforcing plate 126 is adapted to be coupled with the reinforcing holes 1119 of the first beam 11 to reinforce the strength between the mounting frame 12 and the connecting beam 11.

Preferably, referring to fig. 3 and 10, a battery guide module 127 and a reservoir guide module 128 are further provided on the inner walls of the two side plates 123. When the battery 6 is mounted in the first mounting space 1201 and the reservoir 5 is mounted in the second mounting space 1202, the battery guide module 127 and the reservoir guide module 128 may guide, damp and fix the battery 6 and the reservoir 5.

Referring to fig. 1 to 5 and 13 to 14, the two horn arms 2 include two horn arms 2 rotatably connected to the two pivot portions 112 of the connecting beam 11, respectively. Wherein each horn 2 comprises a pivot 21, a horn rod 22 and an arm assembly 23.

Referring to fig. 14 and 15, the hinge 21 includes a socket 211 and two hinge protrusions 212 extending along the socket 211. The socket 211 includes a first outer wall 2111 and a second outer wall 2112, and the first outer wall 2111 and the second outer wall 2112 are located on the same circumference (coaxial line). The first outer wall 2111 and the second outer wall 2112 of the socket portion 211 together define a socket hole 2110, and the socket hole 2110 is adapted to be engaged with one end of the horn bar 22. The second outer wall 2112 is further provided with a second retaining groove 2113 in the peripheral wall. The two pivot convex portions 212 respectively extend along the radial direction of the sleeve portion 211, each pivot protrusion 212 is provided with one fitting hole 2122, so that two fitting holes 2122 are provided, and the two fitting holes 2122 are respectively in one-to-one correspondence with and coaxially arranged with the pivot holes 1126 on the pivot portion 112, thereby realizing the pivot connection between the arm 2 and the pivot portion 112.

One end of the arm lever 22 is fixed to the housing hole 2110, and the other end of the arm lever 22 is used for fixing the power module 4. In this embodiment, the horn bar 22 is made of an aluminum alloy tube wrapped with a carbon fiber material. Of course, the arm rod 22 may also be a plastic tube made of plastic or a carbon tube made of carbon fiber material.

Referring to fig. 13 and 16, arm assembly 23 includes a mounting member 231, an arm 232, and a latch assembly 233.

Specifically, the mounting member 231 includes a mounting substrate 2311 and an adaptor 2312 extending in a direction perpendicular to the mounting substrate 2311. The mounting member 231 is fixed to the transition portion 1233 by a mounting base plate 2311. The arm 232 includes an arm bar 2321 and a pivot member 2322 connected at both ends of the arm bar 2321. One end of the support arm 232 is pivotally connected to the adaptor 2312 of the mounting member 231 via the pivoting member 2322. The other end of the arm 232 is pivotally connected to the latching member 233 via a pivot member 2322.

Referring to fig. 17, the latching assembly 233 includes a first latch assembly 2331, a second latch assembly 2332, and a latch 2333.

Referring to fig. 13 and 18, the first locking member 2331 includes a first circular ring portion 23311 and two first pivot protrusions 23312 extending outward along an outer circumferential surface of the first circular ring portion 23311, a pivot block 23313 and a first locking portion 23314. The two first pivot protrusions 23312 are pivotally connected to the end of the arm 232 away from the mounting member 231 via a pivot member 2322. The first latch 23314 has a groove 23315 formed on a sidewall thereof.

Referring to fig. 17 to 19, the second lock assembly 2332 includes a second circular ring portion 23321 and two second pivot protrusions 23322 and second lock assembly 23323 extending outward along an outer circumferential surface of the second circular ring portion 23321. The inner peripheral surface of the second annular portion 23321 is further formed with a third stopper channel 23324. The two second pivot protrusions 23322 are pivotally connected to the pivot blocks 23313 such that the first circular ring portion 23311 and the second circular ring portion 23321 can be located on the same circumferential surface.

Referring to fig. 17 and 20, the locking member 2333 is connected to the second locking part 23323 by a pivot rod 2334, and the locking member 2333 includes a fitting boss 23331, a third pivot protrusion 23332 extending outwardly along a first end surface of the fitting boss 23331, and a connecting rod 23333 (which may be a separate part) extending along a second end surface of the fitting boss 23331. Further, a boss 23334 is formed on the second end face.

The deployment process of the horn 2 is described in detail below:

first, the arm 2 is rotated to fit the first outer wall 2111 of the pivot member 21 into the third fitting groove 1130 of the fitting portion 113. The matching portion 113 and the second outer wall 2112 are located on the same circumference, the matching portion 113 and the second outer wall 2112 enclose a complete cylinder, and meanwhile, the first limiting groove 1131 on the matching portion 113 and the second limiting groove 2113 on the peripheral wall of the second outer wall 2112 form a complete circular groove together.

Next, the arm 232 is rotated to fit the first ring portion 23311 of the first lock assembly 2331 and the second ring portion 23321 of the second lock assembly 2332 over the second retaining groove 2113 and the first retaining groove 1131, respectively. The limiting protrusion 1132 on the bottom wall of the first limiting groove 1131 is engaged with the third limiting groove 23324 on the inner peripheral surface of the second ring portion 23321, so as to prevent the second ring portion 23321 and the bottom wall of the first limiting groove 1131 from rotating.

Finally, the locking member 2333 locks the first circular ring portion 23311 of the first locking member 2331 and the second circular ring portion 23321 of the second locking member 2332 such that the first circular ring portion 23311 and the second circular ring portion 23321 are formed as one circular ring coaxially arranged with the cylinder surrounded by the fitting portion 113 and the second outer wall 2112. The first circle portion 23311 and the second circle portion 23321 form a lock to the second outer wall 2112 of the pivot 21 and the mating portion 113. Wherein the protrusion 23334 on the second end of the locking member 2333 and the recessed portion 23315 on the side wall of the first locking portion 23312 cooperate such that the first circle 23311 and the second circle 23321 compress the outer peripheral wall of the second outer wall 2112 of the pivot member 21.

Folding process of the horn 2: the folding process of the horn 2 is the reverse of the unfolding of the horn 2 and will not be described here.

Referring to fig. 21, the landing gear 3 includes two support leg assemblies 301, the two support leg assemblies 301 are mirror-symmetrical structures, and the two support leg assemblies 301 are installed under the body 1 in bilateral symmetry. Each support leg assembly 301 includes a foot prop support leg 31, a first mating member 32, a second mating member 34, and a landing gear attachment assembly 33. The undercarriage support legs 31 are connected below the fuselage 1 by a first fitting 32, a second fitting 34 and a landing gear attachment assembly 33.

Referring to fig. 22, the stand support leg 31 includes: a front leg 311, a bottom leg 312 and a rear leg 313, wherein the front leg 311 and the rear leg 313 are respectively connected to the front and rear ends of the bottom leg 312. Wherein the bottom leg 312 is tubular and extends in a front-to-back direction in a horizontal plane. The front leg 311 includes a first leg section 3111 connected to the bottom leg 312, a second leg section 3112 connected to the first leg section 3111 and a support section 3113 connected to the second leg section 3112. The support section 3113 is disposed parallel to the bottom leg 312.

Referring to fig. 12 and 21 to 23, the support section 3113 of the tripod support leg 31 is fitted into the positioning groove 1234 and connected to the second mounting projection 12311 by the connecting projection 341 provided on the second fitting piece 34.

The first fitting 32 connects the rear leg 313 to the rear end plate 122.

Referring to fig. 21, 24-25, the landing gear attachment assembly 33 includes a first mount 331, a second mount 332. A first mount 331 and a second mount 332 connect the second leg segment 3112 with the lower end wall 1112 of the first beam 111.

Referring to fig. 30 to 33, the power assembly 4 includes a connection base 41, a mounting assembly 42, a power unit 43, and a driving device 44.

The connecting seat 41 (divided into two pieces) includes an installation portion 413, a sleeve portion 411 extending along one end of the installation portion 413, and an extending portion 412 extending along an upper end face of the installation portion 413, a sleeve hole 4110 is opened inside the sleeve portion 411, and one end of the horn rod 22 far away from the body 1 is suitable for being fitted in the sleeve hole 4110.

The mounting assembly 42 includes a mounting post 421, a bearing 422, a coupling assembly 423, a fixed mount 424, and a rotating member 425. Wherein, two ends of the mounting column 421 are respectively fixed on the extension part 412 by the bearings 422 in a rotatable manner. The connecting assembly 423 and the fixing support 424 are connected and fixed to the mounting post 421. The rotating member 425 is coupled to the mounting post 421.

The power unit 43 includes two, and each power unit 43 includes a power motor 431 fixed to the fixed mount 424 and a propeller assembly 432 fixed to the power motor 431.

Referring to fig. 31 and 32, the driving device 44 includes a steering engine 441, a transmission device, a transmission shaft 442, and a link assembly 443, wherein the link assembly 443 includes a first adaptor 4431 connected with the rotation member 425, a second adaptor 4432 connected with the transmission shaft 442, and a link 4433 connected between the first adaptor 4431 and the second adaptor 4432. The first and

second adapters

4431 and 4432 are pivotally connected to the link 4433, respectively.

Referring to fig. 26 and 27, the reservoir 5 includes a container body 51 having a reservoir cavity 50, the reservoir cavity 50 being for holding a medical fluid; the container main body 51 includes an upper case 511 and a lower case 512 extending vertically downward from the bottom of the upper case 511, and the upper case 511 and the lower case 512 are integrally formed to form the liquid storage chamber 50. The upper case 511 and the lower case 512 form a "T" shape.

Referring to fig. 2 and 26, a mounting groove 5111 is provided on a front end surface of the upper case 511. Be suitable for the installation NFC module in the mounting groove 5111, still be provided with NFC read write line 8 on the up end of tie-beam 11.

Referring to fig. 1, the electronic control module 7 includes a communication module 71 and a flight control module 72. A communication module 71 and a flight control module 72 are attached to the fuselage 1. Specifically, the body 1 includes a mounting bracket 13. The mounting bracket 13 is connected to the first beam 111. A communication module 71 and a flight control module 72 are provided on the mount 13. The connecting line between the electronic control module 7 and the power assembly 4 can enter the first fitting groove 1110 through the line passing hole 1118 and then pass through the second fitting groove 1120 and the arm lever 22.

Preferably, the main body 1 further includes a protection frame 14, the protection frame 14 is disposed outside the mounting frame 13, the protection frame 14 includes two protection rods 141, and one end of each protection rod 141 is fixed to the insertion and matching hole 11171 of the connecting pole 1117. The other end of the guard bar 141 is fixed to the lower end wall 1112 through a fixing seat 142.

Referring to fig. 1, 28 and 29, the communication module 71 includes a first antenna 711 and a second antenna 712, and in this embodiment, the first antenna 711 and the second antenna 712 are respectively fixed on the antenna mounting seat 1124 of the upper pivoting wall 1121 and the lower pivoting wall 1122.

Other configurations and operations of the drone 100 according to embodiments of the present invention are known to those of ordinary skill in the art and will not be described in detail herein.

In the description herein, references to the description of the term "one embodiment," "some embodiments," "an illustrative embodiment," "an example," "a specific example," or "some examples" or the like mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the terms used above do not necessarily refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.

While embodiments of the present invention have been shown and described, it will be understood by those of ordinary skill in the art that: various changes, modifications, substitutions and alterations can be made to the embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the claims and their equivalents.

Claims

1. A fuselage assembly for a drone, comprising:

installing a frame;

the connecting beam is fixedly connected with the mounting frame, the connecting beam is an integrally-formed part, and an antenna mounting seat is arranged on the connecting beam;

the plurality of machine arms are arranged on the connecting beam at intervals.

2. The airframe assembly for a drone of claim 1, wherein the antenna mount includes first and second spaced apart mounts, the first mount adapted to mount a first antenna for positioning the drone, the second mount adapted to mount a second antenna for receiving remote control commands for the drone.

3. The airframe assembly for a drone of claim 2, wherein the first mounting seat is located at an upper end of the connecting beam, and/or the second mounting seat is located at a lower end of the connecting beam.

4. The airframe assembly for a drone according to claim 2, wherein the mounting port of the first mount is disposed upwardly, and/or the mounting port of the second mount is disposed downwardly.

5. The airframe assembly for unmanned aerial vehicle of claim 4, wherein the first mount pad and the second mount pad are offset in a vertical direction.

6. The airframe assembly for unmanned aerial vehicle of claim 1, wherein the antenna mount is offset from the mounting frame in a fore-and-aft direction.

7. The airframe assembly for unmanned aerial vehicle of claim 1, wherein the antenna mount is a plurality of, a plurality of the antenna mount distributes in the left and right sides of the tie-beam.

8. The fuselage assembly for an unmanned aerial vehicle of claim 1, wherein the tie-beam is recessed towards a direction away from the mounting frame to define a mating space, at least a portion of the mounting frame is located in the mating space, the antenna mount is provided with a communication hole, and the communication hole is communicated with the mating space.

9. The fuselage assembly for the unmanned aerial vehicle of any one of claims 1 to 8, wherein the connecting beam comprises a first beam body and two second beam bodies, the two second beam bodies are respectively located at two opposite ends of the first beam body and connected with the first beam body, the first beam body is connected with the mounting frame in a matching manner, the number of the horn is two, the horn corresponds to the two second beam bodies one to one, each horn is connected with the corresponding second beam body, and the antenna mounting seat is arranged on the second beam body.

10. A drone, characterized by comprising a fuselage assembly according to any one of claims 1 to 9.