CN215098315U

CN215098315U - Unmanned aerial vehicle for mounting microcomputer-mounted computer

Info

Publication number: CN215098315U
Application number: CN202120252443.5U
Authority: CN
Inventors: 熊勇良; 罗志勇; 叶涛; 吴强; 陈宁
Original assignee: Guangzhou Ufly Information Technology Co ltd
Current assignee: Guangzhou Ufly Information Technology Co ltd
Priority date: 2021-01-28
Filing date: 2021-01-28
Publication date: 2021-12-10
Anticipated expiration: 2031-01-28

Abstract

An unmanned aerial vehicle for hanging a microcomputer-mounted computer comprises a body, wherein a flying pipe box for loading the microcomputer-mounted computer is arranged at the bottom of the body, a holder is arranged at the bottom of the flying pipe box, the holder comprises a holder camera and a holder base for installing the holder camera, the holder base is detachably connected to the bottom of the flying pipe box through a plurality of damping balls, open grooves symmetrically arranged along the vertical direction are respectively arranged at two opposite sides of the body, a module battery is detachably inserted in the open grooves in a buckling mode respectively, the module battery comprises a battery shell and a battery pack arranged in the battery shell, thus, the microcomputer-mounted computer is loaded in the flying pipe box, the flying pipe box is arranged at the bottom of the body, two module batteries are arranged at two sides of the body in a symmetrical mode simultaneously, and the center of the bottom of the body can be used for placing the hardware with strict gravity center requirement of the microcomputer-mounted computer, the rationality of the overall structure layout is improved.

Description

Unmanned aerial vehicle for mounting microcomputer-mounted computer

Technical Field

The utility model belongs to the technical field of unmanned aerial vehicle, especially, relate to an unmanned aerial vehicle of miniature machine-mounted computer of carry.

Background

Unmanned aerial vehicles can be classified into military and civil applications according to the application field. For military use, unmanned aerial vehicles divide into reconnaissance aircraft and target drone. In the civil aspect, the unmanned aerial vehicle is applied to the fields of aerial photography, agriculture, plant protection, miniature self-timer, express transportation, disaster relief, wild animal observation, infectious disease monitoring, surveying and mapping, news reporting, electric power inspection, disaster relief, film and television shooting, romantic manufacturing and the like, and the application of the unmanned aerial vehicle is greatly expanded.

Along with unmanned aerial vehicle's development, the requirement to continuation of the journey is higher and higher more, and battery capacity, volume and quality are also do more and more thereupon, because traditional unmanned aerial vehicle adopts the monocell configuration mostly, simultaneously, flies to control etc. and establishes in the fuselage, consequently the influence of arranging of hardware is also bigger and bigger to centrobaric in unmanned aerial vehicle.

The large-capacity single cell described above has the following disadvantages:

1) when the specific weight of the battery is larger and larger relative to the weight of the whole machine, the gravity center of the whole machine is more and more difficult to configure; 2) if the battery is fixed at the position of the center of gravity, the whole hardware arrangement is damaged, and some hardware (such as flight control) with higher requirement on the center of gravity has to be shifted.

SUMMERY OF THE UTILITY MODEL

The utility model aims to solve the technical problem that because its battery ratio is bigger and bigger for the weight of complete machine to current unmanned aerial vehicle, to the more and more difficult problem of focus configuration of complete machine, provide an unmanned aerial vehicle of on-board computer of carry miniature machine.

The utility model provides an above-mentioned technical problem adopted technical scheme as follows:

the utility model provides an unmanned aerial vehicle of miniature machine year computer of carry, includes a fuselage, the fuselage bottom is equipped with one and is used for loading the pipe box that flies of miniature machine year computer, the bottom that flies the pipe box is equipped with a cloud platform, the cloud platform includes a cloud platform camera and is used for installing the cloud platform base of cloud platform camera, cloud platform base is connected through a plurality of shock attenuation ball detachably fly the bottom of managing the box, the relative both sides of fuselage are equipped with the open slot that sets up along vertical direction symmetry respectively, detachably buckle is inserted respectively in the open slot and is equipped with a module battery, module battery includes a battery housing and sets up group battery in the battery housing.

Further, the damping ball includes the damping ball body and locates respectively the first backstop portion and the second backstop portion of damping ball body both sides, first backstop portion and second backstop portion with form first installation screens and second installation screens between the damping ball body respectively, four corners whereabouts of flying pipe box bottom are equipped with a first fixed plate respectively, set up respectively on the first fixed plate with the first pilot hole of first installation screens adaptation, four corners whereabouts at cloud platform base top establish respectively with the second fixed plate that first fixed plate corresponds, set up on the second fixed plate with the second pilot hole of second installation screens adaptation.

Furthermore, an extending end extending along the direction departing from the damping ball body is arranged on the first stop part.

Further, the top that flies the pipe box is equipped with a plurality of first screw holes, the bottom of fuselage be equipped with the second screw hole that first screw hole corresponds, fly the pipe box with the fuselage passes through the cooperation detachably of screw, first screw hole and second screw hole and fixes together.

Furthermore, a plurality of heat dissipation holes are formed in the peripheral side wall of the flying pipe box.

Furthermore, the top of the flying pipe box is also provided with a wire through hole for wiring the microcomputer-mounted computer.

Furthermore, the top of the battery shell is also provided with a lug extending outwards, and the body is correspondingly provided with a step groove on the open groove.

Furthermore, a battery plug and a socket are correspondingly arranged on the lug of the battery shell and the stepped groove of the machine body.

Further, still include a plurality of with the articulated horn of connecting of fuselage, be equipped with rotor system on the horn respectively.

According to the above embodiment of the present invention, the unmanned aerial vehicle for mounting the microcomputer-based computer comprises a main body, a flying pipe box for mounting the microcomputer-based computer is arranged at the bottom of the main body, a cradle head is arranged at the bottom of the flying pipe box, the cradle head comprises a cradle head camera and a cradle head base for mounting the cradle head camera, the cradle head base is detachably connected to the bottom of the flying pipe box through a plurality of damping balls, open slots symmetrically arranged along the vertical direction are respectively arranged at two opposite sides of the main body, a module battery is detachably inserted in the open slots, the module battery comprises a battery housing and a battery pack arranged in the battery housing, thus, by loading the microcomputer-based computer in the flying pipe box, the flying pipe box is arranged at the bottom of the main body, and two module batteries are symmetrically arranged at two sides of the main body, so that the center of the bottom of the main body can be used for placing hardware with strict requirements on the gravity center of the microcomputer-based computer, the rationality of the overall structure layout is improved. In addition, the impact of strong wind airflow in the air on the tripod head can be reduced by utilizing the damping balls, so that the vibration or shaking degree of the tripod head can be reduced, and the image stability of the tripod head camera is improved.

Drawings

In order to more clearly illustrate the technical solution of the present invention, the drawings needed to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to these drawings without creative efforts.

Fig. 1 is an overall schematic view of a drone mounted with a microcomputer onboard computer according to an embodiment of the present invention.

Fig. 2 is an overall schematic view of a body of the drone on which the microcomputer is mounted according to an embodiment of the present invention.

Fig. 3 is an enlarged schematic view at a in fig. 1.

Fig. 4 is an enlarged schematic view at B in fig. 2.

Fig. 5 is a side view of a drone with a microcomputer onboard computer provided by an embodiment of the present invention.

Fig. 6 is an exploded view of a module battery and a body of the unmanned aerial vehicle mounted with a microcomputer on-board computer, according to an embodiment of the present invention.

Fig. 7 is a top view of a drone on which a microcomputer is mounted according to an embodiment of the present invention.

Fig. 8 is an enlarged schematic view at C in fig. 7.

Fig. 9 is a schematic structural diagram of a module battery of the drone on which the microcomputer is mounted according to an embodiment of the present invention.

Fig. 10 is an enlarged schematic view at D in fig. 9.

Fig. 11 is an overall schematic view of another angle of the module battery of the drone on which the microcomputer is mounted according to an embodiment of the present invention.

Fig. 12 is an enlarged schematic view at E in fig. 11.

Fig. 13 is a cross-sectional view of a module battery of a drone on which a microcomputer-based onboard computer is mounted according to an embodiment of the present invention.

Fig. 14 is a structural diagram of a flight tube box and a pan/tilt head of an unmanned aerial vehicle on which a microcomputer is mounted according to an embodiment of the present invention.

Fig. 15 is another structural diagram of a flight tube box and a pan/tilt head of the drone on which the microcomputer is mounted according to an embodiment of the present invention.

Fig. 16 is an enlarged schematic view at F in fig. 15.

Detailed Description

In order to make the technical problem, technical solution and advantageous effects solved by the present invention more clearly understood, the following description is given in conjunction with the accompanying drawings and embodiments to further explain the present invention in detail. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.

Referring to fig. 1 to 16 together, an embodiment of the present invention provides an unmanned aerial vehicle for mounting a microcomputer on-board computer, which includes a main body 1, a flying pipe box 3 for mounting the microcomputer on-board computer is disposed at the bottom of the main body 1, the microcomputer on-board computer is used for unmanned aerial vehicle flight control and communication with an intelligent terminal, a cradle head 4 is disposed at the bottom of the flying pipe box 3, the cradle head 4 includes a cradle head camera 41 and a cradle head base 42 for mounting the cradle head camera 41, the cradle head base 42 is detachably connected to the bottom of the flying pipe box 3 through a plurality of damping balls 5, open slots 11 symmetrically disposed along a vertical direction are respectively disposed at two opposite sides of the main body 1, a module battery 2 is detachably inserted into each open slot 11, the module battery 2 includes a battery case 21 and a battery pack (not labeled in the drawing) disposed in the battery case 21, like this, through loading microcomputer on-board computer in flying pipe box 3, and flying pipe box 3 establishes in 1 bottom of fuselage, install two module batteries 2 in 1 both sides of fuselage with the mode of symmetry simultaneously, make 1 bottom of fuselage center can place microcomputer-carried computer etc. to the stricter hardware of focus requirement, the rationality of overall structure overall arrangement has been improved, in addition, utilize the shock attenuation ball can alleviate the strong wind air current in the air to the influence of cloud platform, thereby can alleviate the degree that the cloud platform takes place vibrations or rocks, improve the image stability of cloud platform camera.

In this embodiment, the tops of two opposite side walls of the battery case 21 and the two opposite sides of the open slot 11 are respectively provided with a pressing buckle 22 capable of elastically stretching toward the inside of the battery case 21, the pressing buckle 22 includes a pressing portion 221, a buckling portion 222 spaced from the pressing portion 221, and a connecting portion 223 connecting the pressing portion 221 and the buckling portion 222, the tops of two opposite sides of the open slot 11 are respectively provided with a buckling slot 12 adapted to the buckling portion 223, so that when the module battery 2 needs to be assembled on the machine body 1, the pressing portion 221 of the pressing buckle 22 is pressed to elastically stretch the pressing buckle 22 toward the inside of the battery case 21, so that the module battery 2 is inserted into the open slot 11, and after the module battery 2 is inserted into the open slot 11, the pressing buckle 22 is stopped to be pressed, the pressing buckle 22 is restored to the initial state from the inside of the battery shell 21, and at the moment, the buckling part 223 of the pressing buckle 22 is buckled in the buckling groove 12, so that locking is achieved, therefore, a single module battery 2 with the same battery capacity is adopted for a large capacity, the total battery capacity is guaranteed to be unchanged, and the single module battery 2 can be more conveniently disassembled and assembled.

In this embodiment, as shown in fig. 1, 3, 14, 15 and 16, the damping ball 5 includes a damping ball body 51, and a first stopping portion 52 and a second stopping portion 53 respectively disposed on two sides of the damping ball body 51, a first mounting position (not shown) and a second mounting position (not shown) are respectively formed between the first stopping portion 52 and the second stopping portion 53 and the damping ball body 51, a first fixing plate 31 is respectively disposed at four corners of the bottom of the flying-tube box 3, first assembling holes (not shown) adapted to the first mounting position are respectively formed on the first fixing plate 31, second fixing plates 43 corresponding to the first fixing plate 31 are respectively disposed at four corners of the top of the pan-tilt base 42, second assembling holes (not shown) adapted to the second mounting position are formed on the second fixing plate 43, like this, cloud platform base 42 is connected through a plurality of shock attenuation balls 5 detachably fly the bottom of pipe box 3, simultaneously, utilizes shock attenuation ball 5 can alleviate the strong wind air current in the air to the influence of cloud platform 4 to can alleviate the degree that cloud platform 4 takes place vibrations or rocks, improve cloud platform camera 41's image stability.

In this embodiment, the first stopper portion 52 is provided with an extending end 54 extending in a direction away from the damping ball body 51, so that when the damping ball 5 is inserted and fixed to the first fixing plate 31 and the second fixing plate 43 through the extending end 54, the extending end 54 can provide a guiding and positioning function for the first stopper portion 52 and the second stopper portion 53 to be inserted into the first fitting hole and the second fitting hole, so that the first stopper portion 52 and the second stopper portion 53 can accurately and conveniently enter the first fitting hole and the second fitting hole, and the first fixing plate 31 and the second fixing plate 43 can be conveniently fixed in the first mounting position and the second mounting position between the first stopper portion 52 and the damping ball body 51 and between the second stopper portion 53 and the damping ball body 51.

In this embodiment, the sidewall of the flying-pipe box 3 is provided with a plurality of heat dissipation holes 32.

In this embodiment, the top of the flying-pipe box 3 is further provided with a wire through hole 33 for routing the microcomputer.

In this embodiment, as shown in fig. 9, 10, and 13, the battery case 21 is respectively provided with a mounting hole (not labeled) adapted to the pressing buckle 22, the pressing buckle 22 is assembled in the mounting hole, two clamping grooves 25 are respectively disposed at intervals at positions corresponding to the two mounting holes at the bottom of the top cover of the battery case 21, an expansion portion 224 slidably inserted into the two clamping grooves 25 and extending out of the two clamping grooves 25 is disposed on an inner side wall of the pressing portion 221, and two stoppers 225 for stopping the clamping grooves 25 are respectively disposed on two sides of one side of the expansion portion 224 away from the pressing portion 221; the pressing buckle 22 is further provided with a spring assembly (not shown), the spring assembly includes a first spring fixing post 226 disposed on the inner side wall of the connecting portion 223, a fixing seat 227 disposed at the bottom of the top cover of the battery case 21 and corresponding to the connecting portion 223, and a compression spring 228, one side of the fixing seat 227 corresponding to the connecting portion 223 is provided with a second spring fixing post 229 corresponding to the first spring fixing post 226, one end of the compression spring 228 is sleeved on the first spring fixing post 226, and the other end of the compression spring 228 is sleeved on the second spring fixing post 229.

In this embodiment, when it is necessary to mount the module battery 2 on the body 1, the pressing portion 221 is pressed, the telescopic part 224 is slidably inserted into the two holding grooves 25 and extends out of the two holding grooves 25, at the same time, the compression spring 228 is elastically compressed, so that the press button 22 is elastically extended and contracted toward the inside of the battery case 21, whereby the module battery 2 is inserted into the open groove 11, after the module battery 2 is inserted into the open groove 11, the pressing of the press button 22 is stopped, under the elastic restoring force of the compression spring 228, the pressing button 22 is elastically restored to the initial state from the inside of the battery case 21, the telescopic part 224 is slidably inserted into the two clamping grooves 25, and the stopper 225 is stopped on the clamping grooves 25, at this time, the buckling part 223 is buckled in the buckling groove 12, so as to realize locking; when the module battery 2 needs to be unloaded from the body 1, as long as the pressing portion 221 is pressed again, the expansion portion 224 is slidably disposed through the two clamping grooves 25 and extends out of the two clamping grooves 25, and meanwhile, the compression spring 228 is elastically pressed, so that the pressing buckle 22 elastically expands and contracts toward the inside of the battery housing 21, at this time, the buckling portion 223 separates from the buckling groove 12, so as to unlock, and then the module battery 2 is pulled out in the vertical direction, so that the unloading of the module battery 2 is completed.

In this embodiment, an escape notch 2241 for escaping from the compression spring 228 is opened in a middle position of the side of the expansion part 224 away from the pressing part 221 along the length direction thereof.

In this embodiment, as shown in fig. 4, 8, and 12, the positions of the two opposite sides of the open slot 11, which are adjacent to the bottom of the open slot 11, are respectively and correspondingly provided with a vertically arranged guide groove 13, the edges of the two opposite sides walls of the battery case 21, which correspond to the two opposite sides of the open slot 11, are respectively provided with a guide strip 23 adapted to the guide groove 13, the guide groove 13 and the guide strip 23 are additionally provided in this embodiment, on one hand, the installation of the module battery 2 can be faster performed, and on the other hand, the vertical matching action of the guide groove 13 and the guide strip 23 can reduce the horizontal shaking of the module battery 2.

In this embodiment, the two opposite sides of the open slot 11 are located below the fastening slot 12 and respectively provided with a first fixing block 14, and the two side walls of the battery case 21 corresponding to the two opposite sides of the open slot 11 are respectively provided with a second fixing block 24 which is matched with the first fixing block 14 and can be arranged on the first fixing block 14. The advantage of having add first fixed block 14 and second fixed block 24 in this embodiment lies in, can guarantee that module battery 2 is fixed more stably after putting the assembly vertically of module battery 2.

In this embodiment, the top of the battery housing 21 is further provided with a protrusion 25 extending outward, and the body 1 is correspondingly provided with a stepped groove 111 on the open groove 11.

In this embodiment, the protrusion 25 of the battery housing 21 and the stepped groove 111 of the body 1 are further provided with a battery plug 26 and a socket 112 correspondingly.

Furthermore, the aircraft further comprises a plurality of arms (not shown) hinged with the fuselage 1, and the arms are respectively provided with a rotor system (not shown).

The above description is only exemplary of the present invention and should not be taken as limiting the scope of the present invention, as any modifications, equivalents, improvements and the like made within the spirit and principles of the present invention are intended to be included within the scope of the present invention.

Claims

1. The utility model provides an unmanned aerial vehicle of miniature machine year computer of carry, a serial communication port, includes a fuselage, the fuselage bottom is equipped with one and is used for loading the pipe box that flies of miniature machine year computer, the bottom that flies the pipe box is equipped with a cloud platform, the cloud platform includes a cloud platform camera and is used for installing the cloud platform base of cloud platform camera, cloud platform base is connected through a plurality of shock attenuation ball detachably fly the bottom of pipe box, the relative both sides of fuselage are equipped with the open slot that sets up along vertical direction symmetry respectively, the detachably buckle is inserted respectively in the open slot and is equipped with a module battery, the module battery includes a battery case and sets up group battery in the battery case.

2. The micro airborne unmanned aerial vehicle of claim 1, wherein the shock absorption ball comprises a shock absorption ball body and a first stopping portion and a second stopping portion respectively disposed on two sides of the shock absorption ball body, a first installation position and a second installation position are respectively formed between the first stopping portion and the shock absorption ball body, a first fixing plate is respectively disposed at four corners of the bottom of the flying pipe box, first assembling holes adapted to the first installation position are respectively disposed on the first fixing plate, a second fixing plate corresponding to the first fixing plate is respectively disposed at four corners of the top of the holder base, and second assembling holes adapted to the second installation position are disposed on the second fixing plate.

3. An unmanned aerial vehicle for mounting a microcomputer-based computer on a vehicle as claimed in claim 2, wherein the first stop portion is provided with an extension end extending in a direction away from the damping ball body.

4. The unmanned aerial vehicle on which a microcomputer-based computer is mounted according to claim 1, wherein a plurality of first screw holes are formed in a top portion of the flying pipe box, a second screw hole corresponding to the first screw holes is formed in a bottom portion of the main body, and the flying pipe box and the main body are detachably fixed together through cooperation of screws, the first screw holes and the second screw holes.

5. An unmanned aerial vehicle carrying a microcomputer-based computer as claimed in claim 1, wherein the flight tube box is provided with a plurality of heat dissipation holes in its peripheral side wall.

6. The drone of claim 1, wherein the top of the flight tube box is further provided with a wire through hole for routing the microcomputer.

7. An unmanned aerial vehicle for mounting a microcomputer onboard computer as claimed in claim 1, wherein the battery housing is further provided with an outwardly extending projection at the top, and the body is correspondingly provided with a stepped groove on the open groove.

8. An unmanned aerial vehicle carrying a microcomputer onboard computer as claimed in claim 7, wherein the projections of the battery housing and the stepped grooves of the body are correspondingly provided with battery plugs and sockets.

9. An unmanned aerial vehicle having a microcomputer onboard a computer as claimed in claim 1, further comprising a plurality of arms hingedly connected to the fuselage, each arm having a rotor system thereon.