CN212556774U

CN212556774U - Unmanned aerial vehicle's horn device and have its unmanned aerial vehicle

Info

Publication number: CN212556774U
Application number: CN202021996341.6U
Authority: CN
Inventors: 何建兵
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: 2021-02-19
Anticipated expiration: 2030-09-11

Abstract

The utility model discloses an unmanned aerial vehicle's horn device and have its unmanned aerial vehicle, the horn device includes: the inner end of the horn body is connected with a body assembly of the unmanned aerial vehicle; the horn end socket, the horn end socket with the outer end of horn body links to each other, the horn end socket is equipped with the installation cavity, unmanned aerial vehicle's drive arrangement install in the installation cavity, unmanned aerial vehicle's power device rotationally install in the horn end socket just is located outside the installation cavity, just unmanned aerial vehicle's drive arrangement's part extends outside the installation cavity with the drive power device for the horn end socket rotates. According to the utility model discloses an unmanned aerial vehicle through installing drive arrangement in the installation cavity, can realize the reliable installation to drive arrangement, is favorable to making unmanned aerial vehicle's compact structure, optimizes unmanned aerial vehicle's structural layout, and the horn device's simple structure simultaneously, the processing degree of difficulty is lower.

Description

Unmanned aerial vehicle's horn device and have its unmanned aerial vehicle

Technical Field

The utility model belongs to the technical field of the unmanned air vehicle technique and specifically relates to an unmanned aerial vehicle's horn device and have its unmanned aerial vehicle is related to.

Background

Along with the development of unmanned aerial vehicle technique, people can utilize unmanned aerial vehicle to accomplish a lot of work, for example: the unmanned aerial vehicle in the correlation technique mostly adopts the form of four, six or eight even number rotors because the flight control algorithm and the motion form of the unmanned aerial vehicle system of the even number rotors are simpler usually, and the change of the lift force of the unmanned aerial vehicle is realized by adjusting the rotating speed of each rotor, thereby controlling the posture and the position of the unmanned aerial vehicle system. However, these drones in the related art are relatively large in size, the drive device is not reasonably installed, and the compactness of the overall structure is low.

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, the utility model provides an unmanned aerial vehicle's horn device can realize the reliable installation to drive arrangement, is favorable to making unmanned aerial vehicle's compact structure, optimizes the overall arrangement, and the simple structure of horn device simultaneously, the processing degree of difficulty is lower.

The utility model also provides an unmanned aerial vehicle with above-mentioned horn device.

According to the utility model discloses unmanned aerial vehicle's horn device, include: the inner end of the horn body is connected with a body assembly of the unmanned aerial vehicle; the horn end socket, the horn end socket with the outer end of horn body links to each other, the horn end socket is equipped with the installation cavity, unmanned aerial vehicle's drive arrangement install in the installation cavity, unmanned aerial vehicle's power device rotationally install in the horn end socket just is located outside the installation cavity, just unmanned aerial vehicle's drive arrangement's part extends outside the installation cavity with the drive power device for the horn end socket rotates.

According to the utility model discloses unmanned aerial vehicle's horn device through installing drive arrangement in the installation intracavity, can realize the reliable installation to drive arrangement, is favorable to making unmanned aerial vehicle's compact structure, optimizes unmanned aerial vehicle's structural layout, and the simple structure of horn device simultaneously, the processing degree of difficulty is lower, and horn body and horn end seat can machine shaping respectively to improve production efficiency, satisfy different actual requirements.

In some embodiments of the present invention, the horn end base includes a first section and a second section, the first section is sleeved on the outer end of the horn body, the second section is connected to the first section, the installation cavity is formed on the second section, the power device is rotatably installed on the second section, and the driving device drives the power device to wind the second section.

In some embodiments of the invention, the second section comprises: one end of the main body part is connected with the first section, and the outer side of the main body part is provided with a mounting hole communicated with the mounting cavity; the power device comprises a first extension part and a second extension part, wherein the central axis of the first extension part and the central axis of the second extension part are on the same straight line, the first extension part is connected to one end, far away from the first section, of the main body part, the second extension part is connected to the main body part and arranged at a distance from the first extension part in the length direction of the main body part, the power device is rotatably connected between the first extension part and the second extension part, and the driving device is installed in the installation cavity and is partially located below the first extension part and the second extension part.

In some embodiments of the present invention, the first extension is detachably connected to the main body.

According to the utility model discloses unmanned aerial vehicle, include: fuselage assembly, power device, drive arrangement and foretell horn device, power device includes power pack, power pack includes power motor and installs in power motor's screw, drive arrangement's part extends outside the installation cavity with the drive power motor winds the horn end seat rotates.

According to the utility model discloses unmanned aerial vehicle through setting up foretell horn device, can realize the reliable installation to drive arrangement, is favorable to making unmanned aerial vehicle's compact structure, optimizes unmanned aerial vehicle's structural configuration.

The utility model discloses an in some embodiments, drive arrangement includes steering wheel, transmission and link assembly, the steering wheel with transmission establishes the installation intracavity, the steering wheel with transmission's input links to each other, transmission's output with link assembly's one end links to each other, link assembly's the other end with power motor links to each other, steering wheel drive transmission's output rotates, so that link assembly drives power pack is relative the horn end seat rotates.

In some embodiments of the present invention, the connecting rod assembly comprises: one end of the first transfer piece is connected with the power motor; the second adapter is positioned below the first adapter, and one end of the second adapter is connected with the output end of the transmission device; and two ends of the connecting rod are respectively connected with the other end of the first adapter and the other end of the second adapter in a pivoting manner.

In some embodiments of the invention, the connecting rod has a first extreme position in which a side wall of the connecting rod facing the first adapter abuts the first adapter and a second extreme position in which the side wall of the connecting rod facing the first adapter abuts the first adapter; and at the second limit position, the side wall of the connecting rod, which faces the second adapter piece, is abutted against the second adapter piece.

In some embodiments of the present invention, the power device further comprises: the installation component, the installation component includes the erection column and connects the external member, the both ends of erection column all with the horn end socket rotationally links to each other, the both ends of connecting the external member respectively with motor power detachably links to each other, just connect the external member the middle part with the erection column cooperation is in order to incite somebody to action motor power is fixed to the erection column, the drive arrangement drive the erection column winds the axis of erection column rotates.

In some embodiments of the present invention, the mounting assembly further comprises: the power motor is installed to the fixing base, the two ends of the connecting sleeve are respectively connected with the fixing base in a detachable mode, and the middle of the connecting sleeve is matched with the installation column in an abutting mode.

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

Fig. 1 is a schematic structural diagram of an unmanned aerial vehicle according to an embodiment of the present invention;

fig. 2 is a schematic plan view of a partial structure of a horn end block, drive and power plant according to an embodiment of the present invention;

FIG. 3 is a schematic cross-sectional view taken at A-A in FIG. 2;

FIG. 4 is a schematic perspective view of FIG. 2;

fig. 5 is a schematic structural view of a first extension according to an embodiment of the present invention;

fig. 6 is a schematic structural view of a fixing base according to an embodiment of the present invention;

fig. 7 is a schematic structural view of a connection kit according to an embodiment of the present invention;

FIG. 8 is a perspective view of another angle of FIG. 4;

fig. 9 is a schematic structural view of a horn end mount according to an embodiment of the present invention;

fig. 10 is a schematic view of another angle of the drone according to an embodiment of the present invention;

fig. 11 is a schematic view of yet another angle of the drone according to an embodiment of the present invention;

FIG. 12 is an enlarged schematic view at B in FIG. 11;

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

fig. 14 is a schematic structural view of a connection beam of an unmanned aerial vehicle according to an embodiment of the present invention;

figure 15 is a front view of a connecting beam of an unmanned aerial vehicle according to an embodiment of the present invention;

fig. 16 is a schematic structural view of a connection beam of an unmanned aerial vehicle according to an embodiment of the present invention;

fig. 17 is a schematic structural diagram of a mounting frame of an unmanned aerial vehicle according to an embodiment of the present invention;

fig. 18 is a schematic structural view of another direction of the mounting frame of the unmanned aerial vehicle according to an embodiment of the present invention;

fig. 19 is a schematic structural view of a mounting frame of an unmanned aerial vehicle according to an embodiment of the present invention in yet another direction;

fig. 20 is a schematic structural view of a horn of an unmanned aerial vehicle according to an embodiment of the present invention;

fig. 21 is a schematic view of a partial structure of a horn of an unmanned aerial vehicle according to an embodiment of the present invention;

fig. 22 is a schematic structural view of a first pivot of an unmanned aerial vehicle according to an embodiment of the present invention;

fig. 23 is a schematic structural view of a first fixing member of an unmanned aerial vehicle according to an embodiment of the present invention;

fig. 24 is a schematic structural view of a locking assembly of an unmanned aerial vehicle according to an embodiment of the present invention;

figure 25 is a schematic structural view of a second locking accessory of the drone according to one embodiment of the present invention;

figure 26 is a schematic structural view of a first locking accessory of an unmanned aerial vehicle according to an embodiment of the present invention;

fig. 27 is a schematic structural view of a locking member of an unmanned aerial vehicle according to an embodiment of the present invention;

fig. 28 is a schematic structural view of yet another angle of the drone according to an embodiment of the present invention;

fig. 29 is a schematic structural view of a landing gear of an unmanned aerial vehicle according to an embodiment of the present invention;

fig. 30 is a schematic structural view of a first connector of an unmanned aerial vehicle according to an embodiment of the present invention;

fig. 31 is a schematic structural diagram of a first limiting member of an unmanned aerial vehicle according to an embodiment of the present invention;

fig. 32 is a schematic structural diagram of a second limiting element of the unmanned aerial vehicle according to an embodiment of the present invention;

fig. 33 is a schematic structural view of a liquid storage container of an unmanned aerial vehicle according to an embodiment of the present invention;

figure 34 is a cross-sectional view of a liquid storage container of an unmanned aerial vehicle according to an embodiment of the present invention;

fig. 35 is a schematic structural diagram of a first antenna of an unmanned aerial vehicle according to an embodiment of the present invention;

fig. 36 is a schematic structural diagram of a second antenna of the drone according to one embodiment of the present invention;

fig. 37 is a schematic structural view of a steering engine and transmission of an unmanned aerial vehicle according to an embodiment of the present invention;

fig. 38 is a schematic structural diagram of a mounting post of an unmanned aerial vehicle according to an embodiment of the present invention.

Reference numerals:

a drone 100;

a fuselage assembly 1; a connecting beam 11;

a connecting portion 111; a communicating chamber 1110; an upper end wall 1111; a lower end wall 1112; a front end wall 1113;

a connection boss 1114; a stop surface 1115; a second reinforcing rib 1116; a connecting post 1117; a wire passing hole 1118;

a pivot joint 112; a pivot chamber 1120; an upper pivot wall 1121; a lower pivot wall 1122;

a front pivot wall 1123; an antenna mount 1124;

a fitting portion 113; a mating cavity 1130; a first mating groove 1131; the mating protrusion 1132;

a mounting frame 12; a mounting chamber 120; a first mounting chamber 1201; a second mounting chamber 1202;

a front end plate 121; a rear end plate 122;

side plates 123; a first side panel portion 1231; a second mounting protrusion 12311;

a second side plate portion 1232; a transition portion 1233;

a first restraint slot 1234; a first connection hole 1235;

a first mounting projection 124; a separator 125; a reinforcing plate 126;

a battery guide module 127; reservoir guide module 128;

a mounting frame 13; a protective frame 14; a guard bar 141; a fixed body 142;

a horn device 2; a horn body 21;

a horn end mount 22; a first segment 221; a socket hole 2211;

a second segment 222; a main body portion 2221; mounting cavity 222 a; the mounting opening 222 b;

a first extension 2222; the first fitting hole 2222 a; a connection plate 22221; vertical plates 22222; a support portion 22223;

a second extension 2223; second fitting holes 22232;

a routing hole 2224;

a first pivot 23; a socket 231; holes 2310 are sleeved;

a first outer wall 2311; a second outer wall 2312; a second fitting groove 2313;

a pivot joint protrusion 232; an arm lever 24; an arm assembly 25; a first fixing member 251;

a mounting substrate 2511; an adapter 2512;

a support arm 252; a boom lever 2521; a second pivot 2322; a third pivot 2523;

a locking assembly 253; a first locking member 2531; a first annular portion 25311;

a first pivot protrusion 25312; a pivot block 25313; the first locking portion 25314; a groove portion 25315;

a second locking fitting 2532; a second annular portion 25321;

a second locking portion 25323; a mating groove 25334;

a locking member 2533; a mating boss 25331; a second pivot protrusion 25332;

a connecting bar 25333; a raised portion 25334; a pivot bar 2534;

a power plant 3; a power unit 31; a power motor 311; a propeller 312;

a mounting assembly 32; mounting posts 321; a connection kit 322; a fixed seat 323; a bearing member 324; a rotating member 325; a shock absorbing member 326; the fitting boss portion 3261;

a drive device 4;

a steering engine 41; the transmission 42; a drive shaft 421;

a connecting rod assembly 43; a first transition member 431; a second adapter 432; a connecting rod 433; a first connection lug 4331; a second engaging lug 4332; a third engaging lug 4333; a fourth engaging lug 4334; a pin 434; a mounting housing 44; a control circuit board 45;

a landing gear 5; a front leg 511; a third leg segment 5111; a second leg segment 5112; a first leg segment 5113;

a bottom leg 512; a rear leg 513; a third connecting member 52; a card slot 521;

the second connecting member 53; a first stopper 531; a third limiting groove 5311; a third connection hole 5312;

a second limiting member 532; a fourth limiting groove 5321; a fourth connection hole 5322;

a first connecting member 54; a second limiting groove 541; the second connection hole 542; a first reinforcing rib 543;

a liquid storage container 6; a reservoir chamber 60; a container main body 61; an upper case 611;

mounting grooves 6111; a lower case 612; a battery 7;

an electronic control module 8; a communication module 81; a first antenna 811; a second antenna 812; flight control module 82.

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 and intended to be used for explaining the present invention, and should not be construed as limiting the present invention.

The following disclosure provides many different embodiments, or examples, for implementing different features of the invention. In order to simplify the disclosure of the present invention, the components and arrangements of specific examples are described below. Of course, they are merely examples and are not intended to limit the present invention. Furthermore, the present invention may repeat reference numerals and/or letters in the various examples. This repetition is for the purpose of simplicity and clarity and does not in itself dictate a relationship between the various embodiments and/or configurations discussed. In addition, the present disclosure provides examples of various specific processes and materials, but one of ordinary skill in the art may recognize the applicability of other processes and/or the use of other materials.

The arm device 2 of the unmanned aerial vehicle 100 and the unmanned aerial vehicle 100 having the same according to the embodiment of the present invention are described below with reference to the drawings.

Referring to fig. 1, according to the utility model discloses an unmanned aerial vehicle 100's horn device 2 can include: a horn body 21 and a horn end mount 22.

Specifically, as shown in fig. 2 and fig. 3, the inner end of the horn body 21 is connected to the fuselage assembly 1 of the unmanned aerial vehicle 100, the horn end base 22 is connected to the outer end of the horn body 21, the horn end base 22 is provided with a mounting cavity 222a, the driving device 4 of the unmanned aerial vehicle 100 is installed in the mounting cavity 222a, the power device 3 of the unmanned aerial vehicle 100 is rotatably installed on the horn end base 22 and is located outside the mounting cavity 222a, and the part of the driving device 4 of the unmanned aerial vehicle 100 extends to the outside of the mounting cavity 222a to drive the power device 3 to rotate around the horn end base 22.

It should be noted that, among the correlation technique, drive arrangement hangs in the outside of horn device, and the utility model discloses in, through installing drive arrangement 4 in installation cavity 222a, can realize the reliable installation to drive arrangement 4, be favorable to making unmanned aerial vehicle 100's compact structure, optimize unmanned aerial vehicle 100's structural layout, horn device 2's simple structure simultaneously, the processing degree of difficulty is lower, and horn body 21 and horn end socket 22 can machine-shaping respectively, thereby improve production efficiency, satisfy different actual requirement, for example, can process the horn body 21 of different length as required, process the horn end socket 22 of different shapes as required simultaneously.

In some embodiments of the present invention, referring to fig. 1 and 3, the horn end base 22 includes a first section 221 and a second section 222, the first section 221 is sleeved on the outer end of the horn body 21, the second section 222 is connected to the first section 221, the mounting cavity 222a is disposed on the second section 222, the power device 3 is rotatably mounted on the second section 222, and the driving device 4 drives the power device 3 to rotate around the second section 222. For example, the first segment 221 is provided with a sleeve hole 2211, and the first segment 221 is sleeved on the outer end of the horn body 21 through the sleeve hole 2211. From this, through making horn end seat 22 include first section 211 and second section 222, be convenient for realize being connected between horn end seat 22 and the horn body 21, and when the outer end of horn body 21 was located to first section 221 cover, can also improve the structural strength of junction.

In some alternative embodiments of the present invention, as shown with reference to fig. 4 and 9, the second segment 222 includes: main part 2221, first extension 2222 and second extension 2223, main part 2221 one end is connected with first section 221, and the outside of main part 2221 is equipped with the installation mouth 222b that communicates with installation cavity 222a to partial structure (for example, steering wheel 41, transmission 42 described below) of drive arrangement 4 can be installed in installation cavity 222a through installation mouth 222b, is favorable to improving the installation effectiveness of drive arrangement 4.

Further, referring to fig. 3 and 4, the central axis of the first extension 2222 and the central axis of the second extension 2223 are on the same straight line, the first extension 2222 is connected to one end of the main body 2221 away from the first segment 221, the second extension 2223 is connected to the main body 2221 and is spaced apart from the first extension 2222 in the length direction of the main body 2221 (for example, as shown in fig. 4, the second extension 2223 is located between the first extension 2222 and the first segment 221), the power unit 3 is rotatably connected between the first extension 2222 and the second extension 2223, the driving unit 4 is mounted to the mounting cavity 222a, and a part of the driving unit 4 is located below the first extension 2222 and the second extension 2223.

It can be appreciated that the power unit 3 can rotate around the central axis of the first and

second extensions

2222 and 2223, so that by rotatably connecting the power unit 3 between the first and

second extensions

2222 and 2223, the power unit 3 can be reliably supported, which is beneficial for ensuring the reliability of the rotation of the power unit 3 around the arm end seat 22.

Further, as shown in fig. 4 and 5, the first extending portion 2222 is detachably connected to the main body portion 2221. Therefore, the first extending portion 2222 and the main body portion 2221 are made as separate pieces, which is beneficial to reducing the respective processing difficulty of the first extending portion 2222 and the main body portion 2221 and is convenient for maintenance. For example, the first extension portion 2222 and the main body portion 2221 are coupled by a threaded fastener.

In some optional embodiments of the present invention, referring to fig. 9, a wire hole 2224 is provided on the second section 222, one end of the electrical connection wire is connected to the power device 3, and the other end of the electrical connection wire extends into the second section 222 through the wire hole 2224 and is routed along the length direction of the inner cavity of the horn body 21 to be connected to the fuselage assembly 1, so as to achieve the electrical connection between the power device 3 and the fuselage assembly 1. It can be understood that, by routing the part of the electrical connection line in the horn body 21, the routing of the electrical connection line is convenient, which is beneficial to preventing the electrical connection line from being damaged by external objects, thereby being beneficial to ensuring the reliability of the operation of the power device 3. For example, as shown in fig. 9, there are two wire holes 2224, and two wire holes 2224 are spaced apart and disposed between the first section 2221 and the second extension 2223.

Referring to fig. 1, according to the utility model discloses unmanned aerial vehicle 100 can include: fuselage assembly 1, horn device 2, power device 3 and according to the utility model discloses above-mentioned embodiment's drive arrangement 4.

Referring to fig. 1, the power plant 3 includes a power unit 31, and the power unit 31 includes a power motor 311 and a propeller 312 mounted to the power motor 311. From this, when power device 3 during operation, power motor 311 can drive screw 312 and rotate to provide power for the flight of unmanned aerial vehicle 100.

Referring to fig. 2 and 3, the driving device 4 is installed in the installation cavity 222a, and a portion of the driving device 4 extends out of the installation cavity 222a to drive the power motor 311 to rotate around the horn end base 22. From this, through installing drive arrangement 4 in installation cavity 222a, can realize the reliable installation to drive arrangement 4, be favorable to making unmanned aerial vehicle 100's compact structure, optimize unmanned aerial vehicle 100's structural layout.

For example, in some examples, referring to fig. 1 and 3, a portion of the driving device 4 is located within the mounting cavity 222a, and the driving device 4 drives the power unit 31 to rotate relative to the horn device 2 about a predetermined axis L that is parallel to a central axis L1 of an outer end of the horn device 2 (e.g., the second section 222 of the horn end block 22 shown in fig. 3). From this, install drive arrangement 4 in installation cavity 222a can drive, the power pack 31 that is located the outer end of horn device 2 rotates around predetermineeing axis L, so that screw 312 rotates around predetermineeing axis L relative to horn device 2, thereby can change unmanned aerial vehicle 100's flight state, for example, change flight direction etc., therefore, can reduce the use quantity of horn device 2, for example need not set up 4 again, 6, more horn device 2 such as 8, change flight direction with the mode of the rotational speed of screw 312 on adjusting different horn device 2, but change flight direction through the mode that drive arrangement 4 rotated power pack 31, thereby make unmanned aerial vehicle 100 can only adopt two horn device 2, make unmanned aerial vehicle 100's structure simpler, the size is more small and exquisite, overall structure is compacter.

Note that, when the flight direction of the drone 100 is controlled by the drive device 4, for example, when the drone 100 flies in a vertical direction, the propeller 312 provides the drone 100 with a vertically upward lift, and the resultant force applied to the unmanned aerial vehicle 100 is in a vertical upward direction (it should be explained that the main force applied to the unmanned aerial vehicle 100 at this time may be a vertical upward lifting force and a gravity applied to the unmanned aerial vehicle 100 itself, and the lifting force is greater than the gravity), the propeller 312 can be driven by the driving device 4 to rotate around the preset axis L to incline to a certain angle relative to the arm device 2, at this time, the direction of the force provided by the propeller 312 is correspondingly changed, the direction of the resultant force applied to the unmanned aerial vehicle 100 is also correspondingly changed, for example, if the propeller 312 rotates forward, the resultant force tilts forward, and the drone 100 flies forward; similarly, the propellers 312 recline to rotate, then resultant force reclines, and the unmanned aerial vehicle 100 flies backward and so on, and in addition, through adjusting the rotational speed of the propellers 312 on two horn devices 2 respectively, the unmanned aerial vehicle 100 can also realize actions such as turning left and right, and no description is given here.

In addition, through setting up drive arrangement 4 in horn device 2 outer end and installing in installation cavity 222a, drive arrangement 4's installation is reliable, and is convenient, and can needn't occupy the space on the fuselage assembly 1, and simultaneously, because drive arrangement 4 can be close to power pack 31, therefore, make when drive arrangement 4 drive power pack 31 rotates around predetermineeing axis L relative horn device 2, the driving distance is shorter, thereby can improve drive arrangement 4's validity in work and operational reliability, and, drive arrangement 4 is convenient with being connected of power pack 31, thereby can improve unmanned aerial vehicle 100's packaging efficiency, and drive arrangement 4 drives power pack 31's reliability, thereby can improve drive arrangement 4's validity in work, and then can improve unmanned aerial vehicle 100's controllability.

In some embodiments of the present invention, as shown with reference to fig. 4 and 5, the driving device 4 may be located below the power device 3. Therefore, the driving device 4 can drive the power device 3 to rotate relative to the arm device 2 under the power device 3, so that the influence of the driving device 4 on the installation and the work of the power device 3 can be avoided, the influence of the power device 3 on the installation and the work of the driving device 4 is avoided, and the working reliability of the driving device 4 and the power device 3 and the reliability of the driving device 4 for driving the power unit 31 to rotate are ensured. However, the present invention is not limited to this, and the power unit 3 may be provided on a side portion of the drive unit 4, for example.

It should be noted that, when the driving device 4 is located below the power device 3, the driving device 4 may be located directly below the power device 3, or the driving device 4 may be located obliquely below the power device 3, and the driving device 4 may be located entirely below the power device 3, or may be partially located below the power device 3, as long as most of the driving device 4 is located below the power device 3, which is not described herein again.

In some embodiments of the present invention, referring to fig. 3 and 4, the driving device 4 includes a steering engine 41, a transmission device 42, and a connecting rod assembly 43, the steering engine 41 and the transmission device 42 are disposed in the mounting cavity 222a, the steering engine 41 is connected to an input end of the transmission device 42 (see fig. 37), an output end of the transmission device 42 is connected to one end of the connecting rod assembly 43, and the other end of the connecting rod assembly 43 is connected to the power motor 311, so that the connecting rod assembly 43 drives the power unit 31 to rotate relative to the arm end base 22.

It can be understood that the steering engine 41 located in the installation cavity 222a drives the output end of the transmission device 42 to rotate, so that the connecting rod assembly 43 drives the power motor 311 to rotate relative to the arm device 2 (for example, refer to fig. 3, the power motor 311 rotates around the preset axis L), the power motor 311 rotates and then drives the propeller 312 to rotate, and further changes the flight direction of the unmanned aerial vehicle 100, thereby, the steering engine 41 and the transmission device 42 are installed in the installation cavity 222a, on one hand, the steering engine 41, the transmission device 42 and the arm device 2 are reasonable in layout, the structure is compact, on the other hand, reliable installation of the steering engine 41 and the transmission device 42 can be realized, and the reliability of work of the steering engine 41 and the transmission device 42 can be improved.

In some optional embodiments of the present invention, referring to fig. 4, the link assembly 43 includes a first adapter 431, a second adapter 432 and a connecting rod 433, one end of the first adapter 431 is connected to the power motor 311, the second adapter 432 is located below the first adapter 431, one end of the second adapter 432 is connected to the output end of the transmission device 42, and two ends of the connecting rod 433 are pivotally connected to the other end of the first adapter 431 and the other end of the second adapter 432, respectively.

It can be understood that the steering engine 41 that is located the installation cavity 222a drives the output of transmission 42 and rotates, thereby it rotates to drive the relative horn device 2 of second adaptor 432, in order to drive the one end removal of connecting rod 433, the other end of connecting rod 433 drives first adaptor 431 and rotates, first adaptor 431 drives power motor 311 and rotates relative horn device 2, power motor 311 rotates and then drives screw 312 and rotate, and then change unmanned aerial vehicle 100's flight direction, therefore, can make link assembly 43's simple structure, the operation is reliable.

For example, referring to fig. 3 and 4, one end of the first adapter 431 is connected to the power motor 311 through a threaded fastener, a rotation center line of the first adapter 431 is aligned with the preset axis L, the second adapter 432 is located below the first adapter 431, the driving device 4 further includes a transmission shaft 421, and an output end of the transmission device 42 is connected to one end of the second adapter 432 through the transmission shaft 421.

In some embodiments of the present invention, referring to fig. 8, the connecting rod 433 has a first limit position in which a side wall of the connecting rod 433 facing the first adaptor 431 abuts the first adaptor 431; in the second limit position, a side wall of the connecting rod 433 facing the second adaptor 432 abuts against the second adaptor 432. Thus, by making the link 433 have the first limit position and the second limit position, the maximum rotation angle of the power unit 3 can be restricted, thereby ensuring reliability of rotation of the power unit 3 with respect to the arm unit 2.

For example, referring to fig. 8, the link 433 is formed in an arc shape and the link 433 protrudes outward toward a direction away from a line connecting rotational center lines of the first and

second adapters

431 and 432, one end of the link 433 has first and second coupling lugs 4331 and 4332 disposed at intervals in a thickness direction of the link 433, and the pin shaft 434 passes through the first and second coupling lugs 4331 and 43431 and 4332 in sequence such that one end of the link 433 is pivotably connected with the other end of the first adapter 431; the other end of the connecting rod 433 is provided with a third connecting lug 4333 and a fourth connecting lug 4334 which are arranged at intervals in the thickness direction of the connecting rod 433, and the pin shaft 434 sequentially passes through the third connecting lug 4333, the second adaptor 432 and the fourth connecting lug 4334 so that the other end of the connecting rod 433 is pivotally connected with the other end of the second adaptor 432.

In some embodiments of the present invention, referring to fig. 1 and 3, the horn end base 22 includes a first section 221 and a second section 222, the first section 221 is sleeved on the outer end of the horn body 21, one end of the second section 222 is connected to the first section 221, the mounting cavity 222a is disposed on the second section 222, the power device 3 is rotatably mounted on the second section 222, and the driving device 4 drives the power device 3 to rotate around the second section 222. For example, the first segment 221 is provided with a sleeve hole 2211, and the first segment 221 is sleeved on the outer end of the horn body 21 through the sleeve hole 2211. From this, the horn device 2's simple structure, the processing degree of difficulty is lower, and horn body 21 and horn end seat 22 can machine shaping respectively to improve production efficiency, satisfy different actual requirements, for example, can process the horn body 21 of different length as required, process the horn end seat 22 of different shapes as required simultaneously, in addition, when the outer end of horn body 21 was located to first section 221 cover, can also improve the structural strength of junction.

Further, referring to fig. 4 and 9, the second section 222 includes a main body portion 2221, a first extending portion 2222, and a second extending portion 2223, one end of the main body portion 2221 is connected to the first section 221, and an installation opening 222b communicated with the installation cavity 222a is formed in the outer side of the main body portion 2221, so that a part of the structure of the driving device 4 (for example, the steering engine 41 and the transmission device 42 described above) can be installed in the installation cavity 222a through the installation opening 222b, which is beneficial to improving the installation efficiency of the driving device 4.

Optionally, in some examples, as shown in fig. 3, the driving device 4 further includes a mounting shell 44, the mounting shell 44 covers the mounting opening 222b, the control circuit board 45 of the steering engine 41 is disposed in the mounting shell 44, and the outer end of the transmission shaft 421 penetrates through the mounting shell 44 to extend out of the mounting cavity 222a, so that by disposing the mounting shell 44 to cover the mounting opening 222b, the influence of an external object on the work of the steering engine 41 and the transmission device 42 can be reduced, the reliability of the work of the steering engine 41 and the transmission device 42 can be improved, and meanwhile, by disposing the control circuit board 45 of the steering engine 41 in the mounting shell 44, the driving device 4 can be compact in structure as a whole, and the reduction of space occupation can be facilitated.

From this, drive arrangement 4 can drive power motor 311 and rotate for first extension 2222 and second extension 2223, and power motor 311 drives the rotation of screw 312 for first extension 2222 and second extension 2223 in order to change unmanned aerial vehicle 100's flight direction, can understand, through rotationally connecting drive arrangement 4 between first extension 2222 and second extension 2223, can realize the reliable support to drive arrangement 4, is favorable to guaranteeing drive arrangement 4 around the pivoted reliability of horn device 2.

In some optional embodiments of the present invention, referring to fig. 3, the power device 3 further includes: the mounting assembly 32, the mounting assembly 32 includes a mounting post 321 and a connecting sleeve 322 (refer to fig. 7), two ends of the mounting post 321 are respectively rotatably connected to the first extending portion 2222 and the second extending portion 2223, two ends of the connecting sleeve 322 are respectively detachably connected to the power motor 311, a middle portion of the connecting sleeve 322 is matched with the mounting post 321 to fix the power motor 311 to the mounting post 321, and the driving device 4 drives the mounting post 321 to rotate relative to the boom device 2. As can be appreciated, by rotatably connecting the two ends of the mounting post 321 with the first extending portion 2222 and the second extending portion 2223 respectively, reliable supporting and positioning of the mounting post 321 can be realized, which is beneficial to ensure the reliability of the rotation of the driving device 4 around the horn device 2.

Alternatively, as shown in fig. 3, two ends of the mounting post 321 are rotatably connected to the first extending portion 2222 and the second extending portion 2223 through the bearing member 324, so that friction between the mounting post 321 and the first extending portion 2222 and the second extending portion 2223 is reduced, reliability of rotation of the mounting post 321 is improved, and reliable supporting and positioning of the mounting post 321 is facilitated.

For example, referring to fig. 5, the first extension portion 2222 includes a connecting plate 22221, a vertical plate 22222 and a support portion 22223, the connecting plate 22221 is connected to the main body portion 2221 by a threaded fastener, one end of the vertical plate 22222 is connected to the top of the connecting plate 22221 and the other end extends upward, one end of the support portion 22223 is connected to one side of the vertical plate 22222 away from the second extension portion 2223 and the other end extends in a direction away from the second extension portion 2223, a first fitting hole 2222a adapted to fit the bearing member 324 is further provided in the first extension portion 2222, the first fitting hole 2222a penetrates the vertical plate 22222 and the support portion 22223 in the extending direction of the support portion 22223, and a second fitting hole 22232 adapted to fit the bearing member 324 is provided in the second extension portion 2223.

In some specific embodiments of the present invention, as shown in fig. 3 and fig. 6, the mounting assembly 32 further includes a fixing seat 323, the power motor 311 is installed in the fixing seat 323, two ends of the connecting sleeve 322 are detachably connected to the fixing seat 323, and the middle of the connecting sleeve 322 is abutted to the mounting post 321. For example, referring to fig. 5, the motor is installed at the top of the fixing seat 323, two ends of the connecting sleeve 322 are detachably connected to the bottom of the fixing seat 323, respectively, and the middle of the connecting sleeve 322 is in abutting fit with the mounting post 321 so that the mounting post 321 is fixedly connected to the fixing seat 323. Therefore, the fixing seat 323 is beneficial to improving the reliability of connection between the power motor 311 and the mounting column 321, and the structure is simple and the installation is convenient.

Optionally, as shown in fig. 3 and 38, the mounting assembly 32 further includes a shock absorbing member 326, the shock absorbing member 326 is sleeved outside the mounting post 321 and located between the connection sleeve 322 and the fixing seat 323, so that the transmission of the vibration from the propeller 312 and the power motor 311 to the mounting post 321 can be reduced, and the reliability of the operation of the unmanned aerial vehicle 100 can be improved.

For example, the bumper 326 can be the flexible member such as rubber spare or silica gel spare, be equipped with a plurality of assembly bellying 3261 on the bumper 326, a plurality of assembly bellying 3261 are spaced apart in the circumference of bumper 326 and are set up, thereby after the assembly is accomplished, assembly bellying 3261 can produce great deformation in order to improve the joint strength between erection column 312, connection external member 322 and the fixing base 323, thereby guarantee the reliable reliability of rotating in order to improve unmanned aerial vehicle 100 work of fixing base 323.

In some alternative embodiments of the present invention, referring to fig. 38, the shock absorbing members 326 are plural, and the shock absorbing members 326 are spaced apart from each other in the length direction of the mounting post 321. Where a plurality refers to two or more, for example, the damping members 326 may be two, three, four, or five, etc. From this, be favorable to further reducing the vibrations transmission of screw 312 and power motor 311 to erection column 321, be favorable to improving the reliability of unmanned aerial vehicle 100 work.

In some embodiments of the present invention, referring to fig. 1, the unmanned aerial vehicle 100 includes two horn devices 2, two power devices 3 and two driving devices 4, and one power device 3 and one driving device 4 are respectively installed at the outer end of each horn device 2. From this, through setting up two horn devices 2, can reduce unmanned aerial vehicle 100's volume to reduce unmanned aerial vehicle 100's occupation space. In addition, when unmanned aerial vehicle 100 flies, can rotate the same or different inclination through controlling two drive arrangement 4 drives power pack 31 that is located two horn device 2 outer ends respectively to and adjust power pack 31's rotational speed, accomplish actions such as advancing, reversing, turn in order to realize unmanned aerial vehicle 100, the operation is comparatively simple.

An unmanned aerial vehicle 100 according to a specific embodiment of the present invention is described below with reference to fig. 1-36. 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. 1-36, an unmanned aerial vehicle 100 according to an embodiment of the present invention includes: the aircraft comprises an airframe assembly 1, an arm device 2, a power device 3, a driving device 4, a landing gear 5, a liquid storage container 6, a battery 7 and an electronic control module 8. The horn devices 2 are distributed on two sides of the fuselage assembly 1 and connected with the fuselage assembly 1. The landing gear 5 is fixed below the fuselage assembly 1 to ensure the stability of the drone 100 in takeoff and landing. Power device 3 is fixed in the tip that fuselage assembly 1 was kept away from to horn body 2, and power device 3 provides lift for unmanned aerial vehicle 100 flight. Liquid storage container 6 carries and is used for the splendid attire to wait to spray or wait the article of transportation on fuselage assembly 1, and battery 7 is fixed in on fuselage assembly 1, and power device 3 provides power for unmanned aerial vehicle 100, and electric control module 8 is fixed in on fuselage assembly 1 for control unmanned aerial vehicle 100's flight posture.

Referring to fig. 10 to 16, the fuselage assembly 1 includes a connecting beam 11 and a mounting frame 12 fixedly connected to the connecting beam 11. The connection beam 11 includes a connection portion 111 and two pivoting portions 112 connected to two ends of the connection portion 111.

Referring to fig. 13 and 14, the connection portion 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 cross section. The upper end wall 1111, the lower end wall 1112 and the front end wall 1113 collectively enclose a communication chamber 1110 opened rearward, so that the connecting portion 111 is formed in a substantially U-shaped cross-sectional configuration. The inner wall of the communication cavity 1110 is formed with a connection boss 1114 and a stop surface 1115. The connecting boss 1114 can extend along the upper end wall 1111, the lower end wall 1112 and the front end wall 1113, and a through hole penetrating through the outer wall of the connecting portion 111 is formed in the connecting boss 1114.

Preferably, the communication chamber 1110 further has a second rib 1116 formed on the inner wall thereof, and the second rib 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. The stopping surface 1115 may be formed on the second rib 1116 on the upper end wall 1111 and the lower end wall 1112, and the stopping surface 1115 on the upper end wall 1111 and the stopping 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 a through hole with a forward opening. The front end wall 1113 is also provided with a wire through hole 1118.

Referring to fig. 15 to 16, the pivotal connection portions 112 include two, each of the pivotal connection portions 112 is also formed in a substantially U-shaped cross section, and each of the pivotal connection portions 112 extends rearward and upward along the end surface of the connection portion 111.

Specifically, referring to fig. 14, the angle of the pivot portion 112 extending rearward relative to the connecting portion 111 is 5 to 20 degrees, and further, in a top view, the angle of the central axis (e.g., the central line B shown in fig. 14) of the pivot portion 112 extending rearward relative to the central axis (e.g., the central line a shown in fig. 14) of the connecting portion 111 is 5 to 20 degrees, preferably 9 degrees, 12 degrees, 14 degrees, and 16 degrees;

referring to fig. 15, the angle of the pivot portion 112 extending upward relative to the connecting portion 111 is 10 to 35 degrees, specifically, in the rear view direction, the included angle of the horizontal plane in which the central axis of the pivot portion 112 (the central axis B shown in fig. 15) and the central axis of the connecting portion 111 (the central axis a shown in fig. 15) are located is 10 to 35 degrees, and preferably 12 degrees, 19 degrees, 21 degrees, and 32 degrees. A hinge cavity 1120 with a backward opening is formed in the hinge portion 112, and the hinge cavity 1120 is communicated with the communication cavity 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 reinforcing ribs 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 hinge wall 1121, the lower hinge wall 1122 and the front hinge wall 1123 enclose a hinge cavity 1120 with a rearward opening, and the upper hinge wall 1121 and the lower hinge wall 1122 are respectively provided with coaxially disposed hinge holes. 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 defines a through hole communicating with the pivot cavity 1120.

Further, as shown in fig. 15, an engaging portion 113 extends from an end of the pivot portion 112, and reinforcing ribs are formed between an outer peripheral surface of the engaging portion 113 and each of the upper pivot wall 1121, the lower pivot wall 1122, and the front pivot wall 1123 of the pivot portion 112. The mating portion 113 has an arc-shaped cross section, a mating cavity 1130 with a backward opening is formed in the mating portion 113, and the mating cavity 1130 has an arc shape and is communicated with the pivot cavity 1120. The outer peripheral surface of the fitting portion 113 is further formed with a first fitting groove 1131, and a fitting protrusion 1132 is formed on the bottom wall of the first fitting groove 1131.

Referring to fig. 13 to 16, the mounting frame 12 is adapted to be coupled with the coupling portion 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 first mounting protrusions 124, and the first mounting protrusions 124 are adapted to be coupled with the coupling bosses 1114 to fixedly couple the mounting frame 12 with the coupling portions 111. When the end surface of the front end plate 121 abuts against the upper abutting surface 1115 of the inner wall of the communicating cavity 1110 during installation, each first installation bulge 124 is opposite to each connecting boss 1114.

In fig. 15 and 16, the front end plate 121, the rear end plate 122, and the two side plates 123 together enclose a vertically penetrating mounting chamber 120. The reservoir 6 and batteries 7 are adapted to be disposed through the mounting chamber 120 and removably connected to 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. The partition plate 125 divides the mounting chamber 120 into a first mounting chamber 1201 and a second mounting chamber 1202. The battery 7 may be mounted in the first mounting space 1201, and the reservoir 6 may be mounted in the second mounting space 1202.

Further, referring to fig. 17 to 19, a first limiting groove 1234 is further formed on the first side plate portion 1231, a second mounting protrusion 12311 is formed on a side wall of the first side plate portion 1231, and a first connecting hole 1235 is formed on the second mounting protrusion 12311. The second mounting protrusion 12311 serves to mount the landing gear 5.

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 coupling bosses 1114 to reinforce the strength between the mounting frame 12 and the coupling beam 11.

Preferably, referring to fig. 10 and 17, 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 7 is mounted in the first mounting space 1201 and the reservoir 6 is mounted in the second mounting space 1202, the battery guide module 127 and the reservoir guide module 128 can guide, damp and fix the battery 7 and the reservoir 6.

Referring to fig. 1, there are two horn devices 2, the two horn devices 2 are distributed on two sides of the fuselage assembly 1 and connected to the fuselage assembly 1, two ends of each horn device 2 in the length direction are respectively an inner end and an outer end, the inner end of each horn device 2 is installed on the fuselage assembly 1, the outer end of each horn device 2 is respectively installed with a power device 3 and a driving device 4

Specifically, referring to fig. 2 and 3, the horn device 2 includes a horn body 21 and a horn end base 22, the horn end base 22 is installed at the other end of the length direction of the horn body 21, the horn end base 22 includes a first section 221 and a second section 222, the first section 221 is sleeved outside the other end of the length direction of the horn body 21, one end of the second section 222 is connected to the first section 221, and the second section 222 serves as the outer end of the horn device 2.

Referring to fig. 3 and 4, the second section 222 includes a main body portion 2221, a first extending portion 2222 and a second extending portion 2223, the main body portion 2221 is provided with a mounting cavity 222a, the main body portion 2221 and the second extending portion 2223 are integrally formed, and the first extending portion 2222 is connected to the main body portion 2221 through a threaded fastener.

Specifically, referring to fig. 3 and 9, one end of the main body 2221 is connected to the first segment 221, a mounting opening 222b communicating with the mounting cavity 222a is formed in the outer side of the main body 2221, a central axis of the first extension 2222 and a central axis of the second extension 2223 are aligned on the same straight line, the first extension 2222 is connected to one end of the main body 2221, which is far from the first segment 221, the second extension 2223 is connected to the main body 2221 and is spaced from the first extension 2222 in the length direction of the main body 2221, and the power unit 3 is rotatably connected between the first extension 2222 and the second extension 2223.

Referring to fig. 3, the power device 3 includes a power unit 31 and a mounting assembly 32, the power unit 31 includes a power motor 311 and a propeller 312 mounted on the power motor 311, and the power device 3 provides a lift force for the unmanned aerial vehicle 100 to fly. The power unit 31 is rotatably coupled between the first and

second extensions

2222 and 2223 by the mounting assembly 32.

Referring to fig. 3, the mounting assembly 32 includes a mounting post 321, a connecting sleeve 322, a fixing seat 323, and a rotating member 325, two ends of the mounting post 321 are rotatably connected to the first extending portion 2222 and the second extending portion 2223 through a bearing member 324, respectively, the rotating member 325 is connected to an outer end of the mounting post 321, two ends of the connecting sleeve 322 are detachably connected to a bottom of the fixing seat 323, respectively, a middle portion of the connecting sleeve 322 is matched with the mounting post 321 to fix the fixing seat 323 to the mounting post 321, and the power motor 311 is disposed at a top portion of the fixing seat 323.

Referring to fig. 3 and 8, the driving device 4 includes a steering engine 41, a transmission device 42, and a link assembly 43, the steering engine 41 and the transmission device 42 are disposed in the installation cavity 222a, the steering engine 41 is connected to an input end of the transmission device 42, the link assembly 43 includes a first adaptor 431, a second adaptor 432, and a link 433, one end of the first adaptor 431 is connected to the installation column 321 through a rotating member 325, the second adaptor 432 is located below the first adaptor 431, one end of the second adaptor 432 is connected to an output end of the transmission device 42, and two ends of the link 433 are pivotally connected to the other end of the first adaptor 431 and the other end of the second adaptor 432, respectively.

It can be understood that steering engine 41 located in installation cavity 222a drives the output of transmission 42 to rotate, thereby drive second adaptor 432 and rotate relative to horn device 2, in order to drive the one end of connecting rod 433 and remove, the other end of connecting rod 433 drives first adaptor 431 and rotates, first adaptor 431 drives the installation axle and rotates relative to first extension 2222 and second extension 2223, erection column 321 drives fixing base 323 and rotates, in order to make motor 311 and screw 312 rotate around the rotation center line of installation axle (predetermine axis L promptly), and then change unmanned aerial vehicle 100's flight direction.

Referring to fig. 20 to 27, the two horn bodies 21 are rotatably connected to the two pivot portions 112 of the connecting beam 11 (see fig. 6). Wherein each horn body 21 includes a first pivot 23, a horn bar 24, and an arm assembly 25.

Referring to fig. 21 and 22, the first hinge member 23 includes a socket 231 and two hinge protrusions 232 extending along the socket 231. The socket 231 includes a first outer wall 2311 and a second outer wall 2312, and the first outer wall 2311 and the second outer wall 2312 are located on the same circumference (coaxial line). The first outer wall 2311 and the second outer wall 2312 of the receiving portion 231 together define a receiving hole 2310, and the receiving hole 2310 is adapted to be engaged with one end of the arm lever 24. The second outer wall 2312 is also provided with a second engaging groove 2313 on the peripheral wall. The two pivot protrusions 232 extend in the radial direction of the sleeve 231.

One end of the arm lever 24 is fixed to the fitting hole 2310 in a fitting manner, and the other end of the arm lever 24 is used for fixing the power unit 3. In this embodiment, the horn bar 24 is made of an aluminum alloy tube wrapped with a carbon fiber material. Of course, the arm bar 24 may also be a plastic tube made of plastic or a carbon tube made of carbon fiber.

Referring to fig. 21-23, arm assembly 25 includes a first mount 251, an arm 252, and a latch assembly 253.

Specifically, the first fixing member 251 includes a mounting substrate 2511 and an adaptor 2512 extending along the mounting substrate 2511. The first fixing member 251 is fixed to the transition portion 1233 via the mounting substrate 2511. The arm 252 includes an arm rod 2521 and a second pivot 2322 connected to two ends of the arm rod 2521. One end of the arm 252 is pivotally connected to the adaptor 2512 of the first fixing member 251 through the second pivoting member 2322, and the other end of the arm 252 is pivotally connected to the locking component 253 through the second pivoting member 2322.

Referring to fig. 24-27, the latching assembly 253 includes a first locking assembly 2531, a second locking assembly 2532, and a locking member 2533.

Referring to fig. 26, the first locking member 2531 includes a first ring portion 25311, two first pivot protrusions 25312 extending along an outer circumferential surface of the first ring portion 25311, a pivot block 25313 and a first locking portion 25314. The two pivoting protrusions 23312 are pivotally connected to an end of the arm 252 away from the first fixing member 251 through a third pivoting member 2523. A groove portion 25315 is formed on a side wall of the first locking portion 25314.

Referring to fig. 25, the second locking fitting 2532 includes a second annular portion 25321, and two second pivot protrusions 25332 and a second locking portion 25323 extending along an outer circumferential surface of the second annular portion 25321. The inner peripheral surface of the second annular portion 25321 is further formed with an engagement groove 25334. The two second pivot protrusions 25332 are pivotally connected to the pivot block 25313, such that the first circular ring portion 25311 and the second circular ring portion 25321 can be located on the same circumferential surface.

Referring to fig. 27, the locking member 2533 is connected to the second locking portion 25323 by a pivot rod 2534, and the locking member 2533 includes a mating protrusion 25331, a second pivot protrusion 25332 extending along a first end surface of the mating protrusion 25331, and a connecting rod 25333 (which may be separate parts) extending along a second end surface of the mating protrusion 25331. Further, a projecting portion 25334 is formed on the second end face.

The following describes in detail the deployment process of the horn body 21:

first, the arm body 21 is rotated to fit the second outer wall 2312 of the first pivot 23 into the fitting cavity 1130 of the fitting portion 113. The fitting portion 113 and the first outer wall 2311 are located on the same circumference, the fitting portion 113 and the first outer wall 2311 form a complete cylinder, and meanwhile, the first fitting groove 1131 on the fitting portion 113 and the second fitting groove 2313 on the peripheral wall of the second outer wall 2312 form a complete circular groove together.

Next, the rotation arm 252 fits the first ring portion 25311 of the first locking member 2531 and the second ring portion 25321 of the second locking member 2532 on the first fitting groove 1131 and the second fitting groove 2313. The engaging protrusion 1132 on the bottom wall of the first engaging groove 1131 engages with the engaging groove 23324 on the inner peripheral surface of the second annular portion 25321, so as to prevent the second annular portion 25321 and the bottom wall of the first engaging groove 1131 from rotating.

Finally, rotating the locking member 2533 locks the first ring portion 25311 of the first locking fitting 2531 and the second ring portion 25321 of the second locking fitting 2532, so that the first ring portion 25311 and the second ring portion 25321 are formed as one ring coaxially arranged with the cylinder surrounded by the fitting portion 113 and the first outer wall 2311. The first and second

circular portions

25311 and 25321 form a lock with the second outer wall 2312 of the first pivot 23 and the mating portion 113. Wherein the protrusion 25334 on the second end surface of the locking member 2533 and the groove 25315 on the side wall of the first locking portion 23312 cooperate to press the first annular portion 25311 and the second annular portion 25321 against the outer peripheral wall of the second outer wall 2312 of the first pivot member 23.

Folding process of the horn body 21: the folding process of the horn body 21 is opposite to the unfolding process of the horn body 21, and the description thereof is omitted.

Referring to fig. 11, the two landing gears 5 are mirror images, and the two landing gears 5 are installed below the fuselage assembly 1 in a left-right symmetrical manner. Each landing gear 5 comprises a front leg 511, a bottom leg 512 and a rear leg 513, a third link 52, a first link 54 and a second link 53. The landing gear 5 is connected below the fuselage assembly 1 by means of a third connection 31, a second connection 53 and a first connection 54.

Referring to fig. 28 and 29, the two landing gears 5 are mirror images of each other, and specifically, the two landing gears 5 are installed in a left-right symmetrical manner below the fuselage assembly 1. Each landing gear 5 comprises a front leg 511, a bottom leg 512 and a rear leg 513, a third link 52, a first link 54 and a second link 53. The landing gear 5 is connected below the fuselage assembly 1 by means of a third connection 31, a second connection 53 and a first connection 54.

Referring to fig. 29, front legs 511 and rear legs 513 are connected to front and rear ends of the bottom leg 512, respectively. Wherein the bottom leg 512 is tubular and extends in a front-to-back direction in a horizontal plane. The front leg 511 comprises a third leg segment 5111 connected to the bottom leg 512, a second leg segment 5112 connected to the third leg segment 5111, and a first leg segment 5113 connected to the second leg segment 5112. First leg segment 5113 is disposed parallel to bottom leg 512.

Referring to fig. 19 and 28, the first leg segment 5113 of the landing gear 5 is fitted into the first stopper groove 1234 and connected to the second mounting protrusion 12311 through a connecting protrusion provided on the first connecting member 54, specifically, a second connecting hole 542 is provided on the connecting protrusion, a first connecting hole 1235 is provided on the second mounting protrusion 12311, the first connecting hole 1235 and the second connecting hole 542 are connected by a fastener, and the third connecting member 52 connects the rear leg 513 to the rear end plate 122.

Referring to fig. 28, the landing gear second connecting member 53 includes a first limiting member 531 and a second limiting member 532, and the first limiting member 531 and the second limiting member 532 connect the second leg segment 5112 with the lower end wall 1112 of the connecting portion 111.

Referring to fig. 25 and 26, the liquid storage container 6 includes a container body 51 having a liquid storage cavity for containing the liquid medicine; the container body 51 includes an upper case 611 and a lower case 612 extending vertically from the bottom of the upper case, and the upper case 611 and the lower case 612 are integrally formed and jointly form the liquid storage cavity 60. The upper case 611 and the lower case 612 form a "T" shape.

Referring to fig. 26 and 33, an installation groove 6111 is provided on the front end surface of the upper case 611. Be suitable for the installation NFC module in the mounting groove 6111, still be provided with NFC read write line 9 on the up end of tie-beam 11.

Referring to fig. 1, electronic control module 8 includes a communication module 81 and a flight control module 82. A communication module 81 and a flight control module 82 are connected to the fuselage assembly 1. Specifically, the fuselage assembly 1 comprises a mounting frame 13. The mounting bracket 13 is connected to the connecting portion 111. A communication module 81 and a flight control module 82 are provided on the mount 13. The connecting line between the electronic control module 8 and the power device 3 can enter the communicating cavity 1110 through the line hole 1118 and then pass through the pivot cavity 1120 and the arm lever 24.

Preferably, the fuselage assembly 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 a through hole of the connecting column 1117. The other end of the guard bar 141 is fixed to the lower end wall 1112 by a fixing body 142.

Referring to fig. 27 and 28, the communication module 81 includes a first antenna 811 and a second antenna 812, and in this embodiment, the first antenna 811 and the second antenna 812 are respectively fixed on the antenna mounting seat 1124 of the upper pivoting wall 1121 and the lower pivoting wall 1122.

Referring to fig. 33 and 34, the reservoir 6 includes a container body 61 having a reservoir cavity 60, the reservoir cavity 60 being for holding a medical fluid; the container body 61 includes an upper case 611 and a lower case 612 extending vertically from the bottom of the upper case, and the upper case 611 and the lower case 612 are integrally formed and jointly form the liquid storage cavity 60. The upper case 611 and the lower case 612 form a "T" shape.

Referring to fig. 33, the front end surface of the upper case 611 is provided with a mounting groove 6111. Be suitable for the installation NFC module in the mounting groove 6111, still be provided with the NFC read write line on the up end of tie-beam 11.

Referring to fig. 11, the electronic control module 8 includes a communication module 81 and a flight control module 82. A communication module 81 and a flight control module 82 are connected to the fuselage assembly 1. Specifically, the fuselage assembly 1 comprises a mounting frame 13. The mounting bracket 13 is connected to the connecting portion 111. A communication module 81 and a flight control module 82 are provided on the mount 13. The connecting line between the electronic control module 8 and the power device 3 can enter the communicating cavity 1110 through the line hole 1118 and then pass through the pivot cavity 1120 and the arm lever 24.

Referring to fig. 11, 35 and 36, the communication module 81 includes a first antenna 811 and a second antenna 812, and in this embodiment, the first antenna 811 and the second antenna 812 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 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 of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", and the like, indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be construed as limiting the present invention.

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

In the present invention, unless otherwise expressly stated or limited, the terms "mounted," "connected," and "fixed" are to be construed broadly and may, for example, be fixedly connected, detachably connected, or integrally formed; the connection can be mechanical connection, electrical connection or communication; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meaning of the above terms in the present invention can be understood according to specific situations by those skilled in the art.

In the present application, unless expressly stated or limited otherwise, the first feature may be directly on or directly under the second feature or indirectly via intermediate members. Also, a first feature "on," "over," and "above" a second feature may be directly or diagonally above the second feature, or may simply indicate that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature may be directly under or obliquely under the first feature, or may simply mean that the first feature is at a lesser elevation than the second feature.

In the description herein, references to the description of the term "one embodiment," "some embodiments," "an example," "a specific example," or "some examples," etc., 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 invention. In this specification, the schematic representations of the terms used above are not necessarily intended to 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. Furthermore, various embodiments or examples and features of different embodiments or examples described in this specification can be combined and combined by one skilled in the art without contradiction.

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. An unmanned aerial vehicle's horn device, its characterized in that includes:

the inner end of the horn body is connected with a body assembly of the unmanned aerial vehicle;

the horn end socket, the horn end socket with the outer end of horn body links to each other, the horn end socket is equipped with the installation cavity, unmanned aerial vehicle's drive arrangement install in the installation cavity, unmanned aerial vehicle's power device rotationally install in the horn end socket just is located outside the installation cavity, just drive arrangement's part extends with the drive outside the installation cavity power device winds the horn end socket rotates.

2. The horn device of unmanned aerial vehicle of claim 1, characterized in that, the horn end socket includes first section and second section, the outer end of horn body is located to the first section cover, the second section with the first section links to each other, the installation cavity is established on the second section, power device rotationally install in the second section, drive arrangement drive power device rotates around the second section.

3. The horn apparatus of claim 2, wherein the second segment comprises:

one end of the main body part is connected with the first section, and the outer side of the main body part is provided with a mounting hole communicated with the mounting cavity;

the power device comprises a first extension part and a second extension part, wherein the central axis of the first extension part and the central axis of the second extension part are on the same straight line, the first extension part is connected to one end, far away from the first section, of the main body part, the second extension part is connected to the main body part and arranged at a distance from the first extension part in the length direction of the main body part, the power device is rotatably connected between the first extension part and the second extension part, and the driving device is installed in the installation cavity and is partially located below the first extension part and the second extension part.

4. The horn apparatus of claim 3, wherein the first extension is removably coupled to the main body portion.

5. An unmanned aerial vehicle, comprising: fuselage assembly, power plant, drive arrangement and according to any one of claims 1-4 the horn device, power plant includes power unit, power unit includes power motor and installs in the screw of power motor, drive arrangement's part extends outside the installation cavity in order to drive power motor rotates around the horn end socket.

6. The unmanned aerial vehicle of claim 5, wherein the driving device comprises a steering engine, a transmission device and a connecting rod assembly, the steering engine and the transmission device are arranged in the mounting cavity, the steering engine is connected with an input end of the transmission device, an output end of the transmission device is connected with one end of the connecting rod assembly, the other end of the connecting rod assembly is connected with the power motor, and the steering engine drives an output end of the transmission device to rotate, so that the connecting rod assembly drives the power unit to rotate around the arm end seat.

7. The drone of claim 6, wherein the linkage assembly includes:

one end of the first transfer piece is connected with the power motor;

the second adapter is positioned below the first adapter, and one end of the second adapter is connected with the output end of the transmission device;

and two ends of the connecting rod are respectively connected with the other end of the first adapter and the other end of the second adapter in a pivoting manner.

8. A drone according to claim 7, wherein the link has a first limit position in which a side wall of the link facing the first adaptor abuts the first adaptor and a second limit position; and at the second limit position, the side wall of the connecting rod, which faces the second adapter piece, is abutted against the second adapter piece.

9. The drone of claim 5, wherein the power device further comprises:

the installation component, the installation component includes the erection column and connects the external member, the both ends of erection column all with the horn end socket rotationally links to each other, the both ends of connecting the external member respectively with motor power detachably links to each other, just connect the external member the middle part with the erection column cooperation is in order to incite somebody to action motor power is fixed to the erection column, the drive arrangement drive the erection column winds the axis of erection column rotates.

10. The drone of claim 9, wherein the mounting assembly further comprises:

the power motor is installed to the fixing base, the both ends of connecting the external member respectively with fixing base detachably links to each other, just the middle part of connecting the external member with the cooperation of erection column butt.