CN210882606U - Unmanned plane - Google Patents

Abstract

An unmanned aerial vehicle, comprising: the device comprises a shell, a flight control mainboard, a battery, an electric regulation module and a power interface module; the flight control main board, the battery and the electric regulation module are arranged in the shell in a stacking mode from bottom to top; the electric regulation module and the power interface module are arranged on the same layer. The unmanned aerial vehicle of the utility model can make the unmanned aerial vehicle compact by laminating the flight control mainboard, the battery and the electric regulation module in the shell of the unmanned aerial vehicle from bottom to top, thereby being beneficial to realizing the miniaturization and the light weight of the unmanned aerial vehicle; moreover, with electricity accent module and power interface module with the layer setting, can shorten the power supply route of electricity accent module, help unmanned aerial vehicle's miniaturization and lightweight.

Description

Unmanned plane

Technical Field

The utility model relates to an unmanned aerial vehicle especially relates to a lightweight unmanned aerial vehicle.

Background

An unmanned aircraft is called an unmanned aerial vehicle for short, and is called a UAV (unmanned aerial vehicle) in English, and is an unmanned aircraft controlled by using remote control equipment and/or a built-in program. With the development of market demands, some unmanned aerial vehicles tend to develop in a large-scale direction, such as a freight unmanned aerial vehicle or a spraying unmanned aerial vehicle, and other unmanned aerial vehicles develop in a direction of miniaturization and light weight more and more so as to meet the requirements of users on convenience. Meanwhile, the unmanned aerial vehicle which is miniaturized and light-weighted, such as the unmanned aerial vehicle below 250g, can directly fly without being prepared in some areas, so that the trouble of using the unmanned aerial vehicle by a user can be reduced. However, when designing the unmanned aerial vehicle in a miniaturized manner, the unmanned aerial vehicle designer finds that some modules in the unmanned aerial vehicle need to meet certain constraint conditions. For example, a satellite positioning module (including but not limited to a GPS, a big dipper, and the like) needs to be uncovered above, an Inertial measurement unit (IMU unit for short) needs to be weighted to a certain weight and then to be damped, a cradle head needs to have a certain damping space, a lower view height module for measuring the height of an unmanned aerial vehicle needs to be free of shielding in a field of view (FOV) range below a fuselage, and a flight control main board and an electric tilt battery need to consider heat dissipation and the like. How to make the internal space layout of the unmanned aerial vehicle more compact on the premise of satisfying at least part of module constraints is one of the directions of efforts of designers.

SUMMERY OF THE UTILITY MODEL

In order to solve the above-mentioned or other potential problems that exist among the prior art, some embodiments of the utility model provide an unmanned aerial vehicle, it includes: the device comprises a shell, a flight control mainboard, a battery, an electric regulation module and a power interface module; the flight control main board, the battery and the electric regulation module are arranged in the shell in a stacking mode from bottom to top; the power interface module and the electric regulation module are arranged on the same layer.

The unmanned aerial vehicle further comprises a lower determined height module, and the lower determined height module is fixed on the bottom surface of the flight control main board.

The unmanned aerial vehicle as described above, wherein the unmanned aerial vehicle further comprises a cooling fin, the cooling fin is used for cooling the flight control main board, and the lower determined height module penetrates through the cooling fin to be fixed on the bottom surface of the flight control main board.

The drone as described above, wherein the fins are formed with a continuous corrugated structure.

The unmanned aerial vehicle further comprises a satellite positioning module and an IMU module, wherein the satellite positioning module, the IMU module and the electric tilt module are arranged on the same layer.

The unmanned aerial vehicle as described above, wherein the IMU module is located in front of the satellite positioning module, and the satellite positioning module is located in front of the electrical tilt module; the satellite positioning module and the IMU module are integrated on a first circuit board, and the satellite positioning module is also used as a counterweight module of the IMU module; and a shielding cover is arranged below the satellite positioning module.

The unmanned aerial vehicle as described above, wherein the electrical tilt module and the power interface module are integrated on a second circuit board; the rear end of the second circuit board is provided with a first electric connection part, and the battery is provided with a second electric connection part matched with the first electric connection part.

As above unmanned aerial vehicle, wherein, unmanned aerial vehicle still includes the cloud platform, the cloud platform is located the place ahead of battery, just the cloud platform with have between the battery and supply the clearance of cloud platform activity.

The unmanned aerial vehicle further comprises a front arm module and a rear arm module, wherein the front arm module is mounted at the front part of the shell, and the rear arm module is mounted at the rear part of the shell; the front arm module is further integrated with a support module extending downwards, and an antenna module of the unmanned aerial vehicle is arranged in the support module.

The unmanned aerial vehicle comprises a front arm module, a front propeller and a rear arm module, wherein the front arm module comprises a front arm and a front propeller, the front propeller is mounted on the front arm, and the front arm is of a hollow rod-shaped structure; the rear machine arm module comprises a rear machine arm and a rear propeller arranged on the rear machine arm, and the rear machine arm is of a hollow rod-shaped structure.

As above unmanned aerial vehicle, wherein, the casing still is provided with be used for fly control mainboard radiating first heat dissipation wind channel and be used for the radiating second heat dissipation wind channel of electricity accent module.

The unmanned aerial vehicle as described above, wherein the first cooling air duct and the second cooling air duct are arranged in a spaced and stacked manner.

The unmanned aerial vehicle as above, wherein, the casing includes relative upper cover and the bottom that sets up and is located center between upper cover and the bottom, the battery is received and is located in the battery compartment of center, it fixes to fly the accuse mainboard through the second fastener the bottom of center, electricity is transferred the module and is fixed through the third fastener the top of center.

As above unmanned aerial vehicle, wherein, the confession is seted up to the rear end of center the breach that the battery passed, the casing still includes to cover to be established the tail-hood at battery rear.

The drone of any preceding claim, wherein the bottom cover includes a floor and an upper sidewall extending upwardly from the floor;

the first heat dissipation air duct comprises a first air inlet formed in the bottom plate and a first air outlet formed in the upper side wall.

As above unmanned aerial vehicle, wherein, second heat dissipation wind channel includes the second air intake that the center set up and the second air outlet that the upper cover set up.

As above unmanned aerial vehicle, wherein, the preceding lateral wall of center is formed with back concave part, back concave part includes top surface and side, top surface and side all are provided with the opening, form with the cooperation the second air intake.

As above unmanned aerial vehicle, wherein, the center is equipped with and is used for the installation department of unmanned aerial vehicle's cloud platform, the cloud platform passes the second air intake with the installation department is connected.

According to the technical scheme of some embodiments of the utility model, the flight control mainboard, the battery and the electric regulation module are stacked in the shell from bottom to top, so that the unmanned aerial vehicle becomes compact, and the miniaturization and the light weight of the unmanned aerial vehicle are realized; moreover, with electricity accent module and power interface module with the layer setting be favorable to reducing the power supply route of electricity accent module to help unmanned aerial vehicle's miniaturization and lightweight.

In addition, a first heat dissipation air duct for dissipating heat for the flight control main board and a second air duct for dissipating heat for the electric regulation module are formed on the shell of the unmanned aerial vehicle, so that the heat dissipation efficiency of heating components in the shell can be improved, and active heat dissipation components such as fans and the like can be omitted; especially when flight control mainboard adds the fin of punching press formula and strengthens the heat dissipation, can make the unmanned aerial vehicle that obtains weight below 250 g.

In addition, through with IMU module and satellite positioning module integration on a circuit board, can regard as the counter weight of IMU module with satellite positioning module to need not to set up solitary counter weight for IMU module, be favorable to reducing unmanned aerial vehicle's volume and weight. Certainly, also be favorable to unmanned aerial vehicle's miniaturization and lightweight through integrated on a circuit board with power interface module and electricity accent module, can shorten the power supply distance of battery for electricity accent module moreover to reduce the connecting wire.

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

Drawings

The above and other objects, features and advantages of the embodiments of the present invention will become more readily understood from the following detailed description with reference to the accompanying drawings. Embodiments of the invention will be described, by way of example and not by way of limitation, in the accompanying drawings, in which:

fig. 1 is a schematic structural view of an unmanned aerial vehicle provided in an embodiment of the present invention with a bottom cover removed;

fig. 2 is a schematic structural view of the unmanned aerial vehicle according to the embodiment of the present invention after the battery is detached;

fig. 3 is a schematic diagram of the unmanned aerial vehicle provided in the embodiment of the present invention after the upper cover is disassembled;

fig. 4 is a schematic view of the unmanned aerial vehicle provided in the embodiment of the present invention after the bottom cover is disassembled;

fig. 5 is a schematic structural view of the unmanned aerial vehicle according to the embodiment of the present invention after the horn is disassembled;

fig. 6 is an exploded view of an unmanned aerial vehicle according to an embodiment of the present invention;

fig. 7 is a top view of a first circuit board according to an embodiment of the present invention;

fig. 8 is a bottom view of a first circuit board according to an embodiment of the present invention;

fig. 9a and 9b are schematic views of a first heat dissipation air duct;

fig. 10a and 10b are schematic views of a second heat dissipation air duct.

Reference numerals:

10-unmanned aerial vehicle; 100-a housing; 110-an upper cover; 1101-a top plate; 1103-lower sidewall; 1105-a second air outlet; 130-middle frame; 1301-a front side wall; 1302-left side wall; 1303-rear sidewall; 1304-right sidewall; 1305-a battery compartment; 1306-a second air inlet; 1307-posterior concavity; 1308-a gap; 150-a bottom cover; 1501-a bottom plate; 1503-upper side wall; 1505-first air intake; 1507-a first air outlet; 1509-an internal recess; 15091-front surface; 15093-rear surface; 170-tail cap; 200-a horn module; 210-a front horn module; 230-rear horn module; 250-a support module; 201-a horn; 2011-front cover; 2013-rear cover; 202-a mounting seat; 203-a propeller; 300-a holder; 400-a second circuit board; 401-an electric regulation module; 403-power interface module; 4031-a first electrical connection; 500-a first circuit board; 501-satellite positioning module; 503-IMU module; 505-a shield; 600-a battery; 6001-second electrical connection; 700-flight control mainboard; 800-a heat sink; 8001-pleated structure; 8003-dodge mouth; 900-lower view height module; 1000-mounting a bracket; 10001-a projection; 1100-a first shock-absorbing structure; 1200-bolt.

Detailed Description

Some embodiments of the present invention will be described in detail below with reference to the accompanying drawings. The embodiments described below and the features of the embodiments can be combined with each other without conflict.

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

In the present invention, unless otherwise expressly stated or limited, the terms "mounted," "connected," and "secured" are to be construed broadly, e.g., as meaning fixedly connected, detachably connected, or integrally formed; they may be directly connected or indirectly connected through intervening media, or they may be connected internally or in any other suitable relationship, unless expressly stated otherwise. 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 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.

After being developed from the beginning of the 20 th century, unmanned aerial vehicles are rapidly used for military purposes such as aerial bombing and investigation. With the gradual maturity of unmanned aerial vehicle technology, when 20 century was over, unmanned aerial vehicle has entered into the rapid development phase, and 21 century, unmanned aerial vehicle has then appeared from the maximization to the trend of miniaturization development, and the unmanned aerial vehicle that a batch model is more small and exquisite, the performance is more stable begins to appear. Simultaneously, this period has also promoted the birth of civilian unmanned aerial vehicle, has released four shaft unmanned vehicles in succession and can be used for the unmanned vehicles of auto heterodyne. However, although the existing drones have developed relatively small models compared with the first drones all over the world, the weight of these drones still exceeds the control weight of the aircraft in some areas, and needs to be strictly controlled by the air traffic control department, and must be registered in the air traffic control department in advance to be used normally, and even some areas also require the civil drones to report the flight time and flight route to the relevant departments before flying.

In view of this, the design and manufacturer of the unmanned aerial vehicle begin to spend a lot of time and manpower and material resources trying to reduce the weight of the existing unmanned aerial vehicle, but because the existing unmanned aerial vehicle needs to be equipped with a lot of flight control motherboards with greater processing power, such as satellite positioning module, pan-tilt camera module, electric tilt module, lower definition height module, etc., the basic needs of the user can be met, meanwhile, in order to ensure that the unmanned aerial vehicle has sufficient cruising power, the unmanned aerial vehicle also needs to carry a battery with sufficient capacity, and the larger the capacity of the battery, the larger the weight of the battery is, the larger the weight of the unmanned aerial vehicle is. In addition, the limitation of each module still need be considered when designing, for example, the height module of looking into needs to be located unmanned aerial vehicle's bottom and its field angle within range need not to shelter from down, and the satellite positioning module then need be located unmanned aerial vehicle's top usually, simultaneously, still need consider the heat dissipation problem of each module, these all undoubtedly provide very big examination for unmanned aerial vehicle's miniaturization, lightweight design.

The purpose of this embodiment is to provide a unmanned aerial vehicle that lightweight, miniaturization, have better heat dissipation, especially strive for to make a unmanned aerial vehicle that has higher radiating efficiency, and weight is below 250 g. The unmanned aerial vehicle of this embodiment includes the casing and flies accuse mainboard, battery and electricity to transfer the module, and flies accuse mainboard, battery and electricity to transfer the module from up range upon range of in this casing down. Through will fly to control mainboard and electricity accent module and arrange respectively in the below and the top of battery, made things convenient for the battery to be mainboard and electricity accent module power supply, the bigger flight control mainboard of unmanned aerial vehicle heat dissipation capacity and electricity accent module also can be separated by the battery moreover, avoid the heat that the two gived off to influence each other, are favorable to making the inside overall arrangement of casing become compact. In addition, because the flight control mainboard is located the lower part of casing, then set up in the casing below for the lower height module of looking at of measuring unmanned aerial vehicle height can the snap-on the flight control mainboard, should be looked down height module can include but not limited to vision sensor and ultrasonic sensor and combination. Because the module of deciding the height down can the snap-on be located the flight control mainboard of lower floor, has just also shortened the assembly route of the two, and then reduces the quantity of connecting wire for example, can further realize unmanned aerial vehicle's miniaturization and lightweight. In some examples, the power interface module and the electrical tilt module can be arranged on the same layer, so that the distance for supplying power to the electrical tilt module by the battery is shortened, and the power supply efficiency is improved. In some specific examples, power interface module and electricity accent module can be integrated on same circuit board to reduce the occupation of space, conveniently do benefit to unmanned aerial vehicle's miniaturization and lightweight.

The following description is provided in conjunction with the accompanying drawings so that those skilled in the art can better understand the technical solutions of the present embodiments.

Fig. 1 is a schematic structural view of the unmanned aerial vehicle provided in this embodiment with the bottom cover removed; fig. 2 is a schematic structural view of the unmanned aerial vehicle according to the embodiment after the battery is detached; fig. 3 is a schematic diagram of the unmanned aerial vehicle provided in this embodiment after the upper cover is disassembled; fig. 4 is the schematic diagram of unmanned aerial vehicle after with the bottom decompose that this embodiment provided. In the following description, the directions shown in fig. 1 are taken as reference directions, but should not be taken as a specific limitation to the scope of protection.

As shown in fig. 1 to 4, the unmanned aerial vehicle 10 of the present embodiment includes: the cradle head comprises a housing 100, four arm modules 200 mounted on the housing 100 and extending radially, and a cradle head 300 mounted at the front end of the housing 100, wherein an image sensing device such as a camera and a video camera can be mounted on the cradle head 300. Specifically, the casing 100 includes an upper cover 110 and a lower cover 150 disposed opposite to each other, and a middle frame 130 located between the upper cover 110 and the lower cover 150, and the upper cover 110, the middle frame 130, and the lower cover 150 enclose an accommodation space for installing components such as the flight control motherboard 700 and the battery 600. The four arm modules 200 are radially installed at the left and right sides of the middle frame 130, and the pan/tilt head 300 is installed at the front end of the middle frame 130.

As shown in fig. 3, the upper cover 110 may include a top plate 1101 and a lower sidewall 1103 extending downward from the top plate 1101, wherein the lower sidewall 1103 may be snap-connected with the middle frame 130. As shown in fig. 4, the bottom cover 150 may include a bottom plate 1501 and an upper sidewall 1503 extending upward from the bottom plate 1501, wherein the upper sidewall 1503 may be snap-coupled with the middle frame 130. It should be understood that in other examples, the upper cover 110 and the bottom cover 150 are not limited to the above-mentioned structures, and those skilled in the art can design the structures according to actual needs.

It should be noted that, in other examples, the housing 100 may also include an upper housing and a lower housing that are oppositely disposed and can be covered together, and the upper housing and the lower housing are covered together to form an accommodating space for installing components such as the flight control main board 700 and the battery 600. In addition, the present embodiment also does not limit that the horn module 200 must be mounted on the middle frame 130, and it may be mounted on the upper cover 110 or the bottom cover 150. Likewise, the cradle head 300 is not limited to be installed at the front end of the middle frame 130, and may be installed at any other suitable position of the middle frame 130, or may be installed at any suitable position of the upper cover 110 and the lower cover 150. In addition, the pan/tilt head 300 is not limited to a single-axis or multi-axis pan/tilt head in this embodiment, as long as it can mount an image sensing device.

Fig. 5 shows a schematic diagram of the unmanned aerial vehicle of the embodiment after the horn is disassembled. As shown in fig. 1 to 5, the horn module 200 includes a front horn module 210 disposed at the front of the case 100 and a rear horn module 230 disposed at the rear of the case 100. In the present embodiment, two front boom modules 210 and two rear boom modules 230 are provided, respectively, on the left and right sides of the middle frame 130. Of course, in other examples, the number of the horn modules 200 is not limited to four, and may be specifically set according to actual needs, for example, six or eight radial horn modules 200 may be disposed around the housing 100.

Specifically, preceding horn module 210 is including being the preceding horn of hollow rod-shaped structure and the preceding screw of installation on preceding horn, and the optional integration has support module 250 down that extends still on preceding horn module 210, can also set up antenna module in this support module 250 for communicate between unmanned aerial vehicle 10 and the remote control equipment. In other words, in some examples, the front arm module 210 may only integrate the downwardly extending support module 250, and the antenna module may not be disposed in the support module 250. In some examples, the support module 250 may be a hollow rod-shaped structure separately manufactured and then assembled with the front arm, for example, a screw structure may be provided on the support module 250 and the front arm to be engaged with each other, and the support module 250 and the front arm may be screwed to be fixed. In other examples, the support module 250 and the front horn may be integrally formed by a process such as injection molding.

The rear arm module 230 includes a rear arm having a hollow rod-shaped structure and a rear propeller mounted on the rear arm. Through setting preceding horn and back horn to hollow shaft-like structure, not only can alleviate unmanned aerial vehicle 10's whole weight, the screw is connected with the electricity of electricity modulation module 401 with back screw before also being convenient for. However, it should be understood that the present embodiment is not limited to the front and rear booms having hollow rod-shaped structures, and in other examples, at least one of the front and rear booms may be solid or made into a frame-type structure.

Specifically, the front arm and the rear arm are assembled together by a front cap 2011 and a rear cap 2013 to form a hollow rod-shaped structure. Wherein, similar trapezoidal structure as shown in fig. 3 can all be makeed into to protecgulum 2011 and hou 2013, and this trapezium structure cavity and one end have the opening to both can guarantee that preceding horn and back horn have sufficient structural strength when protecgulum 2011 and hou cover 2013 lid are in the same place, have less weight again, be favorable to unmanned aerial vehicle 10's lightweight. Of course, in order to assemble the front cover 2011 and the rear cover 2013 together, mutually-matched snap structures may be provided on the front cover 2011 and the rear cover 2013, or the front cover 2011 and the rear cover 2013 may be fixed by a fastener such as a bolt or a screw.

It will be appreciated that in other examples, the support module 250 may also be integrated with the rear horn module 230, or the downwardly extending support module 250 may also be integrated with both the front horn module 210 and the rear horn module 230.

For the sake of brevity, in the following, unless otherwise specified or contradicted, the front and rear booms are collectively referred to as the boom 201, and the front and rear propellers are collectively referred to as the propellers 203.

With continued reference to fig. 3, a mounting seat 202 is provided at an end of the front cover 2011 far from the housing 100, a motor for driving the propeller 203 to rotate is installed in the mounting seat 202, and the propeller 203 is installed on a motor shaft of the motor, so that the propeller 203 can be driven to rotate by the driving of the motor, so as to provide a lift force for the unmanned aerial vehicle 10. The electric connection wire between the motor and the electric tilt module 401 passes through a cavity enclosed by the front cover 2011 and the rear cover 2013 so as to realize communication connection and/or power supply connection of the two. The propellers 203 may be double propellers as shown in fig. 3, single propellers, or, in some examples, two layers of propellers may be provided above and below the horn 201 to further improve the lift of the drone 10.

Fig. 6 is an exploded view of the drone provided in this embodiment. As shown in fig. 6, a flight control main board 700, a battery 600, and an electric tilt module 401 are stacked in this order from the bottom up in the housing 100. Wherein, in some examples, the cradle head 300 is located in front of the battery 600, and illustratively, the battery 600 is located in the same layer as the cradle head 300, for example, a notch 1308 for the battery 600 to pass through may be provided at the rear of the middle frame 130 as shown in fig. 2 and fig. 6, so as to achieve the purpose of locating the battery 600 and the cradle head 300 in the same layer. It is easy to understand, because cloud platform 300 probably rotates for casing 100 at the during operation, so it needs to have certain movable gap, in this embodiment, can be through the length and width height of rational configuration battery 600, can have enough capacity in order to satisfy under the prerequisite that unmanned aerial vehicle 10 continues a journey for a long time at battery 600, can guarantee again to have sufficient clearance between battery 600 and the cloud platform 300 and supply cloud platform 300 during operation to move about, unmanned aerial vehicle 10 can also have compact structure to satisfy its miniaturization and lightweight demand.

The unmanned aerial vehicle 10 of this embodiment, through flying to control mainboard 700, battery 600 and electricity accuse module 401 have been arranged into three layer construction in the vertical direction, and it flies to control mainboard 700 and is located the below of battery 600, thereby more be close to down and look high module 900, effectively reduced down and looked high module 900 and fly to control mainboard 700's installation distance, and electricity accuse module 401 separates through battery 600 with flying to control mainboard 700 again, then the heat that gives off separately can not influence each other, be favorable to the radiating optimization of unmanned aerial vehicle 10.

With continued reference to fig. 4, a power interface module 403, a satellite positioning module 501, and an IMU module 503 are further disposed on the same layer of the electrical tilt module 401, but in other examples, these modules may have other layouts, for example, the power interface module 403 and the flight control motherboard 700 are integrated on a motherboard. In this embodiment, the satellite positioning module 501 and the IMU module 503 are integrated on the first circuit board 500, the electrical tilt module 401 and the power interface module 403 are integrated on the second circuit board 400, the first circuit board 500 and the second circuit board 400 are fixed on the top of the middle frame 130 by fasteners such as bolts 1200, rivets, etc., and the first circuit board 500 is disposed in front of the second circuit board 400, so that the electrical tilt module 401 and the power interface module 403 can be close to the battery 600 located in the middle layer, while also reducing the influence of heat generated by the battery 600 on the satellite positioning module 501 and the IMU module 503. Through integrating satellite positioning module 501 and IMU module 503 on a circuit board to with electricity accent module 401 and power interface module 403 integration on another circuit board, not only can improve unmanned aerial vehicle 10's assembly efficiency, also reduced the space and the weight that these modules occupy after integrated together moreover, be favorable to unmanned aerial vehicle 10's miniaturization and lightweight. Moreover, after integrating power interface module 403 and electricity transfer module 401 on a circuit board, can shorten battery 600 to electricity transfer module 401's power supply distance, in some examples, electricity transfer module 401 and drive screw 203 pivoted motor power supply and during communication connection, also can shorten battery 600 for the distance of motor power supply, be favorable to reducing the connecting wire and simplify the overall arrangement, realize unmanned aerial vehicle's miniaturization and lightweight.

In some examples, as shown in fig. 2 and 6, the rear end of the second circuit board 400 is provided with a first electrical connection portion 4031 extending rearward, and correspondingly, the rear portion of the battery 600 is provided with a second electrical connection portion 6001 matched with the first electrical connection portion 4031, for example, the first electrical connection portion 4031 and the second electrical connection portion 6001 are provided as a contact type first electrical connection portion, a contact type second electrical connection portion, or a pin type first electrical connection portion, or a pin type second electrical connection portion. It should be appreciated that in this example, the power interface module 403 integrated on the second circuit board 400 generally needs to be located behind the electrical tilt module 401 so that it can form the first electrical connection 4031 extending rearward. Through setting up first electric connection 4031 and second electric connection 6001, can improve the stability of electric contact, guarantee that the battery has good power supply performance.

With continued reference to fig. 2 and 6, in order to protect the battery 600, a tail cover 170 is further covered behind the battery 600, and the tail cover 170 may be rotatably connected to the upper cover 110, for example, or may be detachably connected to the upper cover 110, for example, by clipping. Specifically, the tail cap 170 may be hinged at the rear end of the upper cap 110 by a hinge shaft, or the tail cap 170 and the upper cap 110 may be provided with a snap structure to be fitted to each other, so that the tail cap 170 can be detachably mounted on the upper cap 110 to cover behind the battery 600. Of course, the tail cap 170 may be fixed to the upper cap 110 by bolts, rivets, or other methods. It should be understood that although in the present embodiment, the tail cover 170 is mounted on the upper cover 110, in other examples, the tail cover 170 may be mounted on the middle frame 130 or the bottom cover 150. As shown in fig. 2, in some examples, the first electrical connection 4031 is visible when the tail cap 170 is flipped open.

Fig. 7 is a top view of the first circuit board of the present embodiment, and fig. 8 is a bottom view of the first circuit board of the present embodiment. As shown in fig. 7 and 8, the IMU module 503 is located in front of the satellite positioning module 501, and a shielding cover 505 is disposed below the satellite positioning module 501 (for example, a GPS module or a beidou module) to prevent other components in the housing 100 from affecting the operation of the satellite positioning module 501, and the satellite positioning module 501 serves as a counterweight module of the IMU module 503, so that it is not necessary to provide an independent counterweight module for the IMU module 503, which is beneficial to the miniaturization and light weight of the unmanned aerial vehicle 10. In particular, the satellite positioning modules 501 are each configured with an antenna of suitable weight so that when the satellite positioning module 501 is integrated with the IMU module 503, the weight requirements of the IMU module 503 may be reduced. For example, the satellite positioning module may be a GPS module that may employ a ceramic antenna, thereby providing the GPS module with a significant weight such that the ceramic antenna of the GPS module may act as a counterweight to the IMU module 503 when the GPS module is integrated with the IMU module.

Specifically, referring to fig. 6 to 8, the first circuit board 500 may be fixed to the housing 100 through the mounting bracket 1000, for example, the first circuit board 500 is fixed to the middle frame 130 through the mounting bracket 1000, and a first shock absorbing structure 1100 is further disposed between the first circuit board 500 and the mounting bracket 1000, so that the shock of the housing 100 is buffered through the first shock absorbing structure 1100, and the normal operation of the IMU module 503 is prevented from being affected. The first shock absorbing structure 1100 may be any suitable structure such as rubber, a spring, or any other structure capable of absorbing shock.

With continued reference to fig. 6 to 8, the mounting bracket 1000 further forms a protrusion 10001 extending toward the electrical tilt module 401, and the protrusion 10001 is fixed to the electrical tilt module 401 by a fastener such as a bolt 1200, a rivet, or the like. For example, the mounting bracket 1000 may be composed of a rectangular-like portion and a triangular-like portion, which may be integrally formed by stamping, or may be integrally formed by molding, but may also be screwed, welded, or otherwise connected together. One vertex of the triangular portion is used as a protrusion 10001, which extends from the rectangular portion and extends in the direction of the electronic tilt module 401, bolt holes are disposed at three vertices of the triangular portion, and the bolt 1200 passes through the bolt 1200 hole and is fixed with the middle frame 130, so that the first circuit board 500 is located at the top of the middle frame 130. The first shock absorbing structure 1100 is disposed at four vertices of the rectangular portion, and the first circuit board 500 is connected to the mounting bracket 1000 through the first shock absorbing structure 1100.

It will be appreciated that although the present embodiment employs a mounting bracket 1000 that includes both rectangular-like portions and triangular-like portions, in other examples, other suitable shapes of mounting brackets 1000 may be employed, such as rectangular brackets or triangular brackets, although more complex frame-type structures may also be employed.

As shown in fig. 1, 3, 4, and 6, the middle frame 130 includes a front sidewall 1301 and a rear sidewall 1303 disposed opposite to each other, and a left sidewall 1302 and a right sidewall 1304 disposed between the front sidewall 1301 and the rear sidewall 1303. The front side wall 1301 is recessed backward to form a rear recess 1307, an opening is provided on the rear recess 1307, the opening can also be used as a second air inlet 1306, which will be described in detail later, a mounting portion for mounting the cradle head 300 is provided in the middle frame 130 at a position corresponding to the opening, and the cradle head 300 is connected with the mounting portion through the opening. In some examples, the pan/tilt head 300 can also be coupled to the mounting portion via a second shock absorbing structure. For example, the second shock absorbing structure may include a shock absorbing member, wherein the shock absorbing member is proximate to a connection location of the second shock absorbing structure to the mounting portion. Through setting up second shock-absorbing structure, can reduce the influence of fuselage vibration to cloud platform 300, guarantee to install the stability of the image sensing equipment on cloud platform 300, guarantee to shoot the quality, and simultaneously, second shock-absorbing structure wholly is the type of falling L, install in order to accomodate unmanned aerial vehicle 10 on unmanned aerial vehicle 10 at the safety cover of cloud platform 300 when, because the elastic action of damper, make under the effect of guard shield, second shock-absorbing structure can drive cloud platform 300 and support and keep on unmanned aerial vehicle 10's center 130, thereby can avoid cloud platform 300's drunkenness in the front and back direction, in order to protect cloud platform 300. The shock absorbing member may be made of any suitable material such as rubber, spring, or any other material capable of absorbing shock.

One horn 201 is mounted to the front and rear of the left side wall 1302, and one horn 201 is mounted to the front and rear of the right side wall 1304. Portions of the left sidewall 1302 and the right sidewall 1304 near the rear end enclose a battery compartment 1305 for receiving the battery 600 with the rear sidewall 1303. It is easily understood that in order to form this battery chamber 1305, a spacer may be provided in the middle frame 130, and when the battery 600 is mounted in the battery chamber 1305, whether the battery 600 is mounted in place or not may be confirmed by the contact of the front end of the battery 600 with the spacer. A notch 1308 is provided in the rear sidewall 1303, through which notch 1308 the battery 600 can be mounted into the battery chamber 1305 from outside the middle frame 130. The distance between the portions of the front and rear side walls 1301, 1303 near the front ends and the rear recess 1307 serves as the movement gap of the cradle head 300, that is, the length of the battery 600 is smaller than the length of the left and right side walls 1302, 1304.

As shown in fig. 6, an upper support frame and a lower support frame may be respectively disposed at the top end and the bottom end of the battery chamber 1305, the first circuit board 500 and the second circuit board 400 may be fixed to the upper support frame by a fastener such as a bolt 1200, and the flight control main board 700 may also be fixed to the lower support frame by a fastener such as a bolt 1200.

It should be appreciated that the middle frame 130 is not limited to be configured in the above-described configuration, and in other examples, the middle frame 130 may be configured in any other suitable configuration.

As shown in fig. 4 and 6, the lower height module 900 is fixed on the bottom surface of the flight control main board 700, so that the environmental parameters are detected by the lower height module 900, and the control of the unmanned aerial vehicle 10 is realized.

Referring to fig. 4 and 6, in the flight control main boardThe heat dissipation sheet 800 is arranged below the flight control main board 700 to dissipate heat, the heat dissipation sheet 800 can be fixed to the flight control main board 700 through a bolt 1200 or a screw or other suitable method, the heat dissipated by the flight control main board 700 exchanges heat with ambient air through the heat dissipation sheet 800 by arranging the heat dissipation sheet 800 below the flight control main board 700, and therefore the temperature of the flight control main board 700 is reduced, and the flight control main board 700 can work normally. Heat sink 800 may be formed using a die casting process to form heat sink 800 or using a stamping process to form heat sink 800. For example, illustrated in FIGS. 4 and 6 is a heat sink 800 formed by a stamping process, which is typically stamped from an aluminum alloy, such that the density of the heat sink 800 can be as high as 2.7g/cm³The thickness can be reduced to below 0.05mm compared with the density of 1.8g/cm³The aluminum-magnesium alloy is manufactured into the radiating fins 800 with the thickness of more than 0.8mm through a die-casting process, so that the size and the weight of the unmanned aerial vehicle 10 can be effectively reduced. In some cases, a thermal conductive silicone may be disposed between flight control motherboard 700 and heat sink 800 to improve the thermal conductivity. It should be understood that since the heat sink 800 is provided below the flight control main board 700, in order to fix the lower view height module 900 on the bottom surface of the flight control main board 700, the bypass port 8003 may be provided on the heat sink 800, so that the lower view height module 900 may be fixed to the bottom surface of the flight control main board 700 through the bypass port 8003.

In some examples, fins 800 may all be of a structure similar to a flat plate. In other examples, the front end of the heat sink 800 may be formed as a continuous corrugated structure 8001, and the rear end of the heat sink 800 may be formed as a substantially flat structure, as shown in fig. 4 and 6. In other examples, fins 800 may all be pleated structures 8001. By providing the heat sink 800 with a continuous corrugated structure, the heat dissipation area can be further increased, and the heat dissipation efficiency can be improved.

Of course, in other examples, the heat generating components (e.g., the flight control motherboard 700, the electronic tilt module 401, etc.) in the casing 100 may also be cooled by providing a heat sink (e.g., a fin-shaped heat sink) or a heat dissipation fan.

In other examples, the drone 10 may further include an air duct for dissipating heat from devices (including but not limited to the flight control motherboard 700, the electronic tilt module 401, the battery 600, and the like) in the housing 100, and the air duct may dissipate heat from the devices in the housing 100 alone, or may cooperate with the above-mentioned heat sink 800, the fin-shaped heat sink, or the fan to dissipate heat from the devices in the housing 100.

Referring to fig. 3, 4 and 6, in some specific examples, the unmanned aerial vehicle 10 is provided with a first heat dissipation air duct for dissipating heat of the flight control main board 700 and a second heat dissipation air duct for dissipating heat of the electric power conditioner. The first heat dissipation air duct and the second heat dissipation air duct may be stacked and spaced apart from each other, for example, in fig. 3, 4, and 6, the first heat dissipation air duct and the second heat dissipation air duct are stacked and disposed along a vertical direction, and the first heat dissipation air duct and the second heat dissipation air duct are spaced apart from each other by the flight control motherboard 700, or when the heat dissipation fins 800 are disposed below the flight control motherboard 700, the first heat dissipation air duct and the second heat dissipation air duct may also be spaced apart from each other by the heat dissipation fins 800, so that the two heat dissipation air ducts are prevented from being influenced by each other. It should be understood that the present example does not limit that the unmanned aerial vehicle 10 must be provided with the first cooling air duct and the second cooling air duct, for example, the first cooling air duct or the second cooling air duct may be separately provided.

In the present embodiment, the first heat dissipation air duct includes an air duct that allows air to enter from the bottom of the housing 100 and flow out from the side of the housing 100. For example, taking the unmanned aerial vehicle 10 shown in fig. 4 as an example, the bottom cover 150 includes a bottom plate 1501 and an upper side wall 1503 extending upward from the bottom plate 1501, a first air inlet 1505 is provided on the bottom plate 1501, and a first air outlet 1507 is provided on the upper side wall 1503, so that air can enter from the first air inlet 1505, then flow through the flight control main board 700 (when the heat sink 800 is provided below the flight control main board 700, flow through the heat sink 800) and perform heat exchange, and the air after heat exchange flows out from the first air outlet 1507 provided on the upper side wall 1503, thereby achieving the purpose of cooling the flight control main board 700.

In a specific design, as shown in fig. 4, the first air inlet 1505 extends along the width direction of the drone 10, and in some examples, a plurality of first air inlets 1505 may be provided, and the plurality of first air inlets 1505 may be arranged along the length direction of the drone 10, so as to increase the air inlet amount and thus the heat dissipation efficiency. The first air inlet 1505 includes a front surface 15091 and a rear surface 15093 that are oppositely disposed in a length direction of the drone 10, and a left side and a right side that are oppositely disposed in a width direction of the drone 10. In some examples, the front surface 15091, the rear surface 15093, the left side surface, and the right side surface of the first air inlet 1505 may be provided to extend toward the inside of the housing 100, for example, an inner recess 1509 recessed into the housing 100 may be formed on the bottom plate 1501 at the time of preparation, and the first air inlet 1505 may be provided in the inner recess 1509. To direct wind into the first wind intake 1505 to reduce wind resistance, in some specific examples, the rear surface 15093 of the first wind intake 1505 may also be arranged to be angled towards the rear of the drone 10.

The first air outlet 1507 may be disposed at any suitable position of the upper sidewall 1503, for example, the upper sidewall 1503 includes a left upper sidewall 1503 and a right upper sidewall 1503, and the first air outlet 1507 is disposed on each of the left upper sidewall 1503 and the right upper sidewall 1503. In this embodiment, first air outlet 1507 can extend along unmanned aerial vehicle 10's length direction to improve the air output, then improve the efficiency of taking a breath in the casing 100, improve the radiating effect. It is understood that when there are a plurality of the first outlet ports 1507, a portion of the first outlet ports 1507 may be disposed on the left upper sidewall 1503, and another portion of the first outlet ports 1507 may be disposed on the right upper sidewall 1503.

The second heat dissipation air duct includes an air duct that allows air to enter from the front end of the housing 100 and to flow out from the side near the electrical tilt module 401. For example, in the unmanned aerial vehicle 10 shown in fig. 3 and 4, the second air inlet 1306 is disposed on the middle frame 130, the second air outlet 1105 is disposed on the upper cover 110, and air enters from the second air inlet 1306, then flows through the electrical tilt surface, exchanges heat with the electrical tilt, and then flows out from the second air outlet 1105 near the electrical tilt surface, so as to cool the electrical tilt module 401 and ensure normal operation of the electrical tilt module. During preparation, a rear concave portion 1307 is formed on the front side wall 1301 of the middle frame 130, the rear concave portion 1307 includes a top surface and a side surface, an opening for installing the pan/tilt head 300 is disposed on the top surface, and the opening can also be used as the second air inlet 1306. Of course, in some examples, the second air inlet 1306 may be disposed at other locations on the front side wall 1301, for example, while providing openings on both the top and side surfaces of the rear recess 1307 to cooperatively form the second air outlet 1105. A second air outlet 1105 is provided on the lower side wall 1103 of the upper cover 110, and the second air outlet 1105 is provided close to the electric appliance. It is understood that when the lower sidewall 1103 includes the left lower sidewall 1103 and the right lower sidewall 1103, the second air outlet 1105 may be disposed on both the left lower sidewall 1103 and the right lower sidewall 1103, and the number of the second air outlets 1105 disposed on the left lower sidewall 1103 and the right lower sidewall 1103 may also be flexibly adjusted as required, similar to the first air outlet 1507. The second air outlet 1105 may extend along the length of the drone 10 as shown in fig. 1 to improve air exchange efficiency.

Fig. 9a and 9b illustrate a first heat dissipation air duct for heat dissipation of a flight control main board of an unmanned aerial vehicle, and fig. 10a and 10b illustrate a second heat dissipation air duct for heat dissipation of an electric tilt module of the unmanned aerial vehicle. The heat dissipation manner of the unmanned aerial vehicle 10 shown in fig. 3, 4, and 6 during flight is briefly described below with reference to fig. 9a to 10b, so as to better understand the purpose and effect of the first heat dissipation air duct and the second heat dissipation air duct provided in the present embodiment.

When unmanned aerial vehicle 10 starts, the air current of unmanned aerial vehicle 10 bottom can get into inside casing 100 from first air intake 1505 of bottom plate 1501, then contact the heat transfer with fin 800, then flow out casing 100 from the first air outlet 1507 that upper left side wall 1503 and upper right side wall 1503 set up, realize the cooling to flying control mainboard 700 to guarantee that it can normally work. Because unmanned aerial vehicle 10 is at the during operation, the screw 203 that sets up on horn 201 rotates and can produce ascending air current from the center to both sides in unmanned aerial vehicle 10's bottom, through setting up above-mentioned first air intake 1505 and first air outlet 1507, can be with this part of air current effectual guide in casing 100, realize the cooling to flight control mainboard 700.

From the past backward air current that flows in the place ahead of unmanned aerial vehicle 10, then can follow the second air intake 1306 that sets up on the preceding lateral wall 1301 of center 130 and get into in the casing 100, then with the electricity accent module 401 heat transfer after, from left lower lateral wall 1103 and the outflow casing 100 of right lower lateral wall 1103, realize the cooling to electricity accent module 401.

Based on the foregoing, through being the heat dissipation wind channel of flying to control mainboard 700 and the configuration of electricity accent module 401 alone, although the heat dissipation wind channel of this embodiment is natural convection wind channel, nevertheless because two heat dissipation wind channels are independent, therefore can satisfy flying to control mainboard 700 and the respective heat dissipation demand of electricity accent module 401 basically, thereby it forces convection heat dissipation to need not to set up radiator fan or air pump again, thereby just also can omit radiator fan or air pump in unmanned aerial vehicle's the casing, do benefit to the weight and the volume that reduce unmanned aerial vehicle, realize unmanned aerial vehicle's miniaturization and lightweight.

It can be understood, in some examples, because satellite positioning module 501, IMU module 503 both arrange the place ahead at electricity accent module 401, so the air current of second air intake 1306 flow direction second air outlet 1105 is when cooling down electricity accent module 401, also can cool down satellite positioning module 501 and IMU module 503, and because second air outlet 1105 sets up near electricity accent module 401, so it is located unmanned aerial vehicle 10's afterbody basically, consequently, the air current of flowing out from this position also can not produce too big influence to unmanned aerial vehicle 10's aerodynamic performance, also, can compromise unmanned aerial vehicle 10's flight efficiency and radiating efficiency.

Finally, although the advantages associated with this embodiment have been described in the context of these embodiments, other embodiments may also include such advantages, and not all embodiments describe in detail all advantages of the invention, and the advantages objectively brought about by the technical features in the embodiments should all be considered as advantages of the invention which differ from the prior art, all falling within the scope of the invention.

Claims (18)

1. An unmanned aerial vehicle, comprising: the device comprises a shell, a flight control mainboard, a battery, an electric regulation module and a power interface module;

the flight control main board, the battery and the electric regulation module are arranged in the shell in a stacking mode from bottom to top;

the power interface module and the electric regulation module are arranged on the same layer.

2. The drone of claim 1, further comprising a lower elevation module secured to a bottom surface of the flight control motherboard.

3. The drone of claim 2, further comprising a heat sink for dissipating heat from the flight control motherboard, and wherein the lower elevation module is secured to a bottom surface of the flight control motherboard through the heat sink.

4. A drone according to claim 3, characterised in that the fins are formed with a continuous corrugated structure.

5. The drone of claim 1, further comprising a satellite positioning module and an IMU module, the satellite positioning module, the IMU module and the electrical tilt module being disposed on a same layer.

6. The drone of claim 5, wherein the IMU module is located in front of the satellite positioning module, which is located in front of the electrical tilt module; the satellite positioning module and the IMU module are integrated on a first circuit board, and the satellite positioning module is also used as a counterweight module of the IMU module; and a shielding cover is arranged below the satellite positioning module.

7. The drone of claim 6, wherein the electrical tilt module and the power interface module are integrated on a second circuit board; the rear end of the second circuit board is provided with a first electric connection part, and the battery is provided with a second electric connection part matched with the first electric connection part.

8. The drone of any one of claims 1-7, further comprising a cradle head, the cradle head being positioned in front of the battery, and a gap between the cradle head and the battery for movement of the cradle head.

9. The drone of any one of claims 1-7, further comprising a front horn module mounted to a front portion of the housing and a rear horn module mounted to a rear portion of the housing; the front arm module is further integrated with a support module extending downwards, and an antenna module of the unmanned aerial vehicle is arranged in the support module.

10. The drone of claim 9, wherein the front horn module includes a front horn and a front propeller mounted on the front horn, the front horn being a hollow rod-like structure; the rear machine arm module comprises a rear machine arm and a rear propeller arranged on the rear machine arm, and the rear machine arm is of a hollow rod-shaped structure.

11. The unmanned aerial vehicle of any one of claims 1-7, wherein the housing is further provided with a first heat dissipation air duct for dissipating heat from the flight control main board and a second heat dissipation air duct for dissipating heat from the electronic tilt module.

12. The unmanned aerial vehicle of claim 11, wherein the first and second cooling air ducts are spaced apart and stacked.

13. The unmanned aerial vehicle of claim 12, wherein the housing includes an upper cover and a bottom cover disposed opposite to each other and a middle frame disposed between the upper cover and the bottom cover, the battery is received in a battery compartment of the middle frame, the flight control main board is fixed to the bottom of the middle frame by a second fastener, and the electric tuning module is fixed to the top of the middle frame by a third fastener.

14. The unmanned aerial vehicle of claim 13, wherein a notch is formed in the rear end of the middle frame for the battery to pass through, and the housing further comprises a tail cover covering the rear of the battery.

15. The drone of claim 13, wherein the bottom cover includes a floor and an upper sidewall extending upwardly from the floor;

the first heat dissipation air duct comprises a first air inlet formed in the bottom plate and a first air outlet formed in the upper side wall.

16. The unmanned aerial vehicle of claim 13, wherein the second heat dissipation air duct comprises a second air inlet provided in the center frame and a second air outlet provided in the upper cover.

17. The unmanned aerial vehicle of claim 16, wherein a front side wall of the center frame is formed with a rear recess, the rear recess including a top surface and a side surface, the top surface and the side surface each being provided with an opening to cooperatively form the second air intake.

18. The unmanned aerial vehicle of claim 17, wherein the center frame is provided with an installation part for installing a cradle head of the unmanned aerial vehicle, and the cradle head passes through the second air inlet and is connected with the installation part.

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