WO2022205020A1

WO2022205020A1 - Unmanned aerial vehicle

Info

Publication number: WO2022205020A1
Application number: PCT/CN2021/084200
Authority: WO
Inventors: 郭盛家; 吴琼伟; 左川露; 黄星; 陈天翊
Original assignee: 深圳市大疆创新科技有限公司
Priority date: 2021-03-30
Filing date: 2021-03-30
Publication date: 2022-10-06

Abstract

An unmanned aerial vehicle, comprising: a body (100) and a first circuit board assembly (200). An air guide channel (110) and a water guide groove (120) are provided on the body; at least a portion of the water guide groove communicates with the air guide channel; the first circuit board assembly is disposed on the body; and at least a portion of the first circuit board assembly is located within the air guide channel and is spaced apart from the water guide groove. The airflow flow rate within the air guide channel is relatively high, and surface heat of the first circuit board assembly can be quickly taken away, avoiding the malfunction or damage of the first circuit board assembly due to excessively high temperatures, and ensuring the working stability of the first circuit board assembly.

Description

unmanned aerial vehicle

technical field

The present application relates to the technical field of aircraft, and in particular, to an unmanned aerial vehicle.

Background technique

With the increase of the functions of the UAV, more electronic components need to be added on the circuit board. However, the electronic components on the circuit board assembly will generate a lot of heat during operation. If the heat cannot be dissipated in time, it will cause the electronic components Damaged due to excessive temperature.

During the flight of the unmanned aerial vehicle, if the electronic components are damaged, it will cause the unmanned aerial vehicle to be unable to perform the corresponding functions, and even cause the unmanned aerial vehicle to fall. Therefore, how to effectively dissipate heat from the electronic components on the circuit board has become an urgent need. solved problem.

Application content

The present application aims to solve at least one of the technical problems existing in the prior art or related technologies.

To this end, the present application proposes an unmanned aerial vehicle.

In view of this, the present application proposes an unmanned aerial vehicle, comprising: a fuselage and a first circuit board assembly, the fuselage is provided with an air guide channel and a water guide groove, at least part of the water guide groove is connected to the air guide channel; the first circuit board assembly , which is arranged on the fuselage, and at least part of the first circuit board assembly is located in the air guide channel and is spaced apart from the water guide groove.

The fuselage is provided with an air guide channel. During the flight of the UAV, the airflow can enter the air guide channel, and at least part of the first circuit board assembly is located in the air guide channel. During the flight of the UAV, the first circuit board The components will generate more heat, and some circuit board components located in the air guide channel can exchange heat with the airflow in the air guide channel, so that the heat on the surface of the first circuit board A circuit board assembly performs the function of cooling. During the flight of the unmanned aerial vehicle, the air flow in the air guide channel is relatively fast, which can quickly take away the surface heat of the first circuit board assembly and avoid the occurrence of abnormal function or damage of the first circuit board assembly due to excessive temperature. The working stability of the first circuit board assembly is ensured, thereby helping to improve the flight stability and safety of the unmanned aerial vehicle.

There is also a water guide groove in the fuselage, which is connected to the wind guide channel. During the flight of the UAV, if it encounters rainy weather, rainwater will enter the wind guide channel, and the rainwater entering the wind guide channel can flow into the guide channel. In the water tank, the water guide groove can guide the rainwater, so that the rainwater can be discharged from the fuselage, so as to avoid the accumulation of rainwater in the fuselage for a long time and cause corrosion or even damage to the internal parts of the fuselage. The first circuit board assembly and the water guide groove are spaced apart, and the water guide groove can guide the rainwater to prevent the rainwater from flowing to the first circuit board assembly, thereby avoiding the damage of the first circuit board assembly caused by the rainwater, and further reducing the damage of the first circuit board assembly. This ensures that the air guide channel can not only dissipate heat to the first circuit board assembly, but also makes it difficult for rainwater entering the fuselage to contact the first circuit board assembly, which is beneficial to improve the competitiveness of the product.

Additional aspects and advantages of the present application will become apparent in the description section below, or learned by practice of the present application.

Description of drawings

The above and/or additional aspects and advantages of the present application will become apparent and readily understood from the following description of embodiments in conjunction with the accompanying drawings, wherein:

1 shows a schematic structural diagram of an unmanned aerial vehicle according to an embodiment of the present application;

FIG. 2 shows a schematic structural diagram of an unmanned aerial vehicle according to another embodiment of the present application;

3 shows a schematic structural diagram of an unmanned aerial vehicle according to yet another embodiment of the present application;

4 shows a schematic structural diagram of an unmanned aerial vehicle according to yet another embodiment of the present application;

5 shows a schematic structural diagram of an unmanned aerial vehicle according to yet another embodiment of the present application;

6 shows a schematic structural diagram of an unmanned aerial vehicle according to yet another embodiment of the present application;

Figure 7 shows an enlarged view at A in Figure 6;

FIG. 8 shows a schematic structural diagram of an unmanned aerial vehicle according to yet another embodiment of the present application;

Fig. 9 shows the enlarged view at B in Fig. 8;

10 shows a schematic structural diagram of an unmanned aerial vehicle according to yet another embodiment of the present application;

11 shows a schematic structural diagram of an unmanned aerial vehicle according to yet another embodiment of the present application;

12 shows a schematic structural diagram of an unmanned aerial vehicle according to yet another embodiment of the present application;

13 shows a schematic structural diagram of an unmanned aerial vehicle according to yet another embodiment of the present application;

Figure 14 shows an exploded view of an unmanned aerial vehicle according to yet another embodiment of the present application;

FIG. 15 shows a schematic structural diagram of a second housing according to an embodiment of the present application;

FIG. 16 shows a schematic structural diagram of a second casing and a battery according to an embodiment of the present application;

FIG. 17 shows a schematic structural diagram of a second casing and a battery according to another embodiment of the present application;

18 shows a schematic structural diagram of an unmanned aerial vehicle according to yet another embodiment of the present application;

FIG. 19 shows a schematic structural diagram of an unmanned aerial vehicle according to yet another embodiment of the present application;

FIG. 20 shows a schematic structural diagram of an unmanned aerial vehicle according to yet another embodiment of the present application;

FIG. 21 shows a schematic structural diagram of a battery according to an embodiment of the present application;

Fig. 22 shows a schematic structural diagram of a first detection member and a protective elastic sheet according to an embodiment of the present application;

Fig. 23 shows a schematic structural diagram of a first detection member and a protective elastic sheet according to another embodiment of the present application;

Fig. 24 shows a schematic structural diagram of a first detection member and a protective elastic sheet according to yet another embodiment of the present application;

Fig. 25 shows a schematic structural diagram of a first detection member and a protective elastic sheet according to yet another embodiment of the present application;

FIG. 26 shows a schematic structural diagram of a pop-up assembly according to an embodiment of the present application;

Fig. 27 shows a schematic structural diagram of a pop-up assembly according to another embodiment of the present application;

Figure 28 shows an exploded view according to yet another embodiment of the present application;

Fig. 29 shows a schematic structural diagram of a pop-up assembly according to yet another embodiment of the present application;

FIG. 30 shows a schematic structural diagram of a pop-up assembly according to yet another embodiment of the present application;

FIG. 31 shows a schematic structural diagram of a first camera assembly and a first mounting bracket according to an embodiment of the present application;

FIG. 32 shows a schematic structural diagram of a first camera assembly and a first mounting bracket according to another embodiment of the present application;

Among them, the corresponding relationship between the reference numerals and the component names in Fig. 1 to Fig. 32 is:

100 body, 110 air guide channel, 111 air inlet, 112 first air outlet, 113 second air outlet, 114 first sub-air duct, 115 second sub-air duct, 116 groove, 120 water guide groove, 130 First housing, 140 second housing, 141 air guide grille, 142 opening, 150 third housing, 170 first camera assembly, 180 second camera assembly, 191 first mounting bracket, 200 first circuit board assembly , 210 positioning components, 220 gyroscope components, 230 core board components, 240 heat sinks, 300 water baffles, 400 fans, 500 second circuit board components, 510 ESC components, 520 storage components, 530 lidar components, 540 Fill light assembly, 600 battery, 610 battery shell, 620 buckle assembly, 621 push part, 622 buckle part, 623 second detection part, 630 drive part, 640 guide groove, 700 flow guide, 810 first detection Pieces, 820 protective shrapnel, 830 frame, 840 elastic components, 841 push pieces, 842 second elastic pieces, 900 wing components, 1000 pan/tilt components.

Detailed ways

In order to more clearly understand the above objects, features and advantages of the present application, the present application will be further described in detail below with reference to the accompanying drawings and specific embodiments. It should be noted that the embodiments of the present application and the features in the embodiments may be combined with each other in the case of no conflict.

Many specific details are set forth in the following description to facilitate a full understanding of the present application. However, the present application can also be implemented in other ways different from those described herein. Therefore, the protection scope of the present application is not limited by the specific details disclosed below. Example limitations.

Unmanned aerial vehicles according to some embodiments of the present application are described below with reference to FIGS. 1 to 32 .

The embodiment of the present application proposes an unmanned aerial vehicle, as shown in FIG. 1 and FIG. 2 , comprising: a fuselage 100 and a first circuit board assembly 200 , the fuselage 100 is provided with an air guide channel 110 and a water guide groove 120 , at least Part of the water guiding channel 120 communicates with the air guiding channel 110 ; the first circuit board assembly 200 is disposed on the body 100 , and at least part of the first circuit board assembly 200 is located in the air guiding channel 110 and is spaced apart from the water guiding channel 120 .

During the flight of the unmanned aerial vehicle, the airflow can enter the air guide channel 110, and at least part of the first circuit board assembly 200 is located in the air guide channel 110. During the flight of the unmanned aerial vehicle, the first circuit board assembly 200 will generate relatively The part located in the air guide channel 110 can exchange heat with the air flow in the air guide channel 110, so that the heat on the surface of the first circuit board assembly 200 can be carried away by the air flow, so as to play a role in the first circuit board assembly. 200 for cooling effect. During the flight of the unmanned aerial vehicle, the air flow in the air guide channel 110 is relatively fast, which can quickly take away the surface heat of the first circuit board assembly 200, so as to avoid the abnormal function or damage of the first circuit board assembly 200 due to excessive temperature. When the situation occurs, the working stability of the first circuit board assembly 200 is ensured, thereby helping to improve the flight stability and safety of the unmanned aerial vehicle.

The fuselage 100 is also provided with a water guide trough 120. The water guide trough 120 communicates with the wind guide channel 110. During the flight of the unmanned aerial vehicle, if it encounters rainy weather, rainwater will enter the wind guide channel 110 and enter the wind guide channel 110. The rainwater inside can flow into the water guide groove 120 , and the water guide groove 120 can guide the rainwater, so that the rainwater can be discharged out of the fuselage 100 , so as to avoid the accumulation of rainwater in the fuselage 100 for a long time and cause corrosion or even damage to the internal components of the fuselage 100 . The first circuit board assembly 200 and the water guide groove 120 are spaced apart, and the water guide groove 120 can guide rainwater to prevent the rainwater from flowing to the first circuit board assembly 200, thereby preventing the rainwater from causing damage to the first circuit board assembly 200, and further reducing the first circuit board assembly 200. The damage rate of the circuit board assembly 200 ensures that the air guide channel 110 can not only dissipate heat to the first circuit board assembly 200 but also prevent the rainwater entering the body 100 from contacting the first circuit board assembly 200, which is beneficial to improve the competitiveness of the product.

1 , 2 , 3 , 4 and 5 , in a possible embodiment, the fuselage 100 further includes: an air inlet 111 , a first air outlet 112 and a second air outlet 113 , the air inlet 111 is arranged at the head end of the fuselage 100, and the air inlet 111 is connected to the air guide channel 110; the first air outlet 112 is arranged on the top of the fuselage 100, and the first air outlet 112 is connected to the air guide channel 110 and the water guide groove. 120 ; the second air outlet 113 is provided on the side of the fuselage 100 , and the second air outlet 113 communicates with the air guide channel 110 and the water guide groove 120 .

In this embodiment, the fuselage 100 further includes an air inlet 111 , a first air outlet 112 and a second air outlet 113 . The fuselage 100 of the unmanned aerial vehicle has a head end and a tail end. During the flight of the unmanned aerial vehicle Generally, the head end of the fuselage 100 is the windward end, and the air inlet 111 is arranged at the head end of the fuselage 100, so that the air flow can quickly enter the air guide channel 110, thereby increasing the airflow velocity in the air guide channel 110, and the airflow can be The heat of the first circuit board assembly 200 is quickly taken away, the accumulation of high-temperature airflow in the air guide channel 110 is avoided, the heat dissipation of the first circuit board assembly 200 can be quickly performed, and the heat dissipation effect of the first circuit board assembly 200 is improved.

The top and the side of the fuselage 100 are respectively provided with a first air outlet 112 and a second air outlet 113. The first air outlet 112 and the second air outlet 113 are both connected to the air guide channel 110. The number of air flow can improve the discharge speed of the air flow, and the air flow in the air guide channel 110 can be quickly discharged. In the case of increasing the number of air outlets, since the top of the fuselage 100 is provided with the first air outlet 112 , rainwater will also enter the air guide passage 110 from the first air outlet 112 . The water guide channel 120 is connected to the second air outlet 113, so the rainwater entering the air guide channel 110 through the first air outlet 112 will flow into the water guide groove 120, and the water in the water guide groove 120 can pass through the second air outlet. 113 is discharged, and the water guiding groove 120 guides the rainwater to prevent rainwater from accumulating in the fuselage 100 for a long time. Since the rainwater in the water guide trough 120 can be discharged through the second air outlet 113, both the air guide channel 110 and the water guide groove 120 share the second air outlet 113, and the second air outlet 113 can both discharge air and water, and does not require Disposing a drain port for the water guide trough 120 alone simplifies the structure of the fuselage 100 and reduces the processing difficulty of the unmanned aerial vehicle.

In addition, the unmanned aerial vehicle may fly forward or reverse during flight, that is, the fore end of the fuselage 100 can be used as the windward end or the rear end of the fuselage 100 can be used as the windward end, but in most cases, the fuselage 100 The head end is mainly the windward end, so in this embodiment, the air inlet 111 is set at the head end of the fuselage 100. In other embodiments, the air inlet 111 can also be set at the rear end of the fuselage 100, or the The head end and the tail end of the body 100 are provided with air inlets 111 .

In a possible embodiment, compared to the air inlet 111 , the water guide trough 120 is close to the first air outlet 112 and the second air outlet 113 .

In this embodiment, the position of the water guiding groove 120 in the air guiding channel 110 is specifically defined. Compared with the air inlet 111 , the water guiding groove 120 is closer to the first air outlet 112 and the second air outlet 113 , that is, the water guiding groove. The distance between 120 and the first air outlet 112 and the second air outlet 113 is reduced, so the rainwater entering the air guide channel 110 through the first air outlet 112 only needs to flow a small distance to enter the water guide groove 120 The rainwater flowing out of the water guide channel 120 can flow out of the air guide channel 110 within a small distance. The rainwater can be discharged within a short distance in the air guide channel 110 , thereby reducing the retention time of the rainwater in the air guide channel 110 , the contact time of the rainwater with the components in the fuselage 100 is short, and the rainwater is not easy to affect the fuselage 100 . The internal components cause corrosion or even damage, reduce the damage rate of the unmanned aerial vehicle, and improve the stability and safety of the unmanned aerial vehicle.

The water guide trough 120 can be arranged below the first drain outlet or diagonally below, so that the rainwater can flow directly into the water guide groove 120 through the first air outlet 112 , and it is not necessary to set up a separate setting in the fuselage 100 to pour water into the water guide groove. The water channel structure in 120 simplifies the structure of the fuselage 100, thereby further reducing the processing difficulty of the unmanned aerial vehicle.

In a possible embodiment, the water guide groove 120 is set to extend along the first direction, and along the first direction, the length of the water guide groove 120 is greater than the length of the first air outlet 112 .

In this embodiment, the dimensional relationship between the water guiding groove 120 and the first air outlet 112 is defined, and the water guiding groove 120 is set to extend along the first direction. In the first direction, the length of the water guiding groove 120 is greater than that of the first air outlet. The length of 112 can be understood as the passage from the first air outlet 112 to the water guide groove 120 is flared, and the rainwater entering the air guide channel through the first air inlet 111 can be quickly discharged through the water guide groove 120. It is not easy to accumulate in the aqueduct 120 , so as to prevent a large amount of rainwater from accumulating in the aqueduct 120 and causing the rainwater to overflow the aqueduct 120 , which can not only prevent the rainwater from contacting the components in the fuselage 100 for a long time by quickly draining the rainwater, but also avoid the The rainwater overflows the water guiding groove 120 and contacts the first circuit board assembly 200, which further reduces the damage rate of the unmanned aerial vehicle and improves the reliability of the product.

2, 3 and 5, in a possible embodiment, the air guide channel 110 includes: a first sub-air channel 114, and the air inlet 111 and the first air outlet 112 communicate with the first sub-air channel 114; the second sub-air duct 115, the air inlet 111 is connected to the second sub-air duct 115, and the air outlet end of the second sub-air duct 115 faces the second air outlet 113.

In this embodiment, the air guide channel 110 includes a first sub-air channel 114 and a second sub-air channel 115 , the first sub-air channel 114 communicates with the air inlet 111 and the first air outlet 112 , and the second sub-air channel 115 communicates with each other. The air inlet 111 and the second air outlet 113, the airflow entering the fuselage 100 through the air inlet 111 can be discharged through the two air ducts, that is, the first sub-air duct 114 and the second sub-air duct 115 respectively guide the airflow, By increasing the number of sub-air ducts, the airflow can be divided, so that the airflow can be quickly discharged from the body 100 , thereby improving the heat dissipation speed of the first circuit board assembly 200 .

Specifically, the water guide groove 120 is located in the first sub-air duct 114 , and the rainwater entering the fuselage 100 through the first air outlet 112 enters the water guide groove 120 through the first sub-air duct 114 . The airflow in the duct 115 is discharged together through the second air outlet 113 .

2, 6 and 7, in a possible embodiment, the unmanned aerial vehicle further includes a water baffle 300, and the water baffle 300 is arranged in the water guide groove 120 and located in the first sub-air duct 114; Wherein, a water blocking plate 300 is provided on the side of the water guiding groove 120 away from the first air outlet 112 .

In this embodiment, the water baffle 300 is located in the first sub-air duct 114 , and the water baffle 300 separates the first circuit board assembly 200 from the water guide groove 120 to prevent the rainwater in the water guide groove 120 from interacting with the first circuit board assembly 200 contacts, thereby preventing the first circuit board assembly 200 from being short-circuited or damaged by rainwater corrosion. A water blocking plate 300 is provided on the side of the water guiding groove 120 away from the first air outlet 112 , so the water blocking plate 300 blocks rainwater from flowing into the water guiding groove 120 . The water guide groove 120 enters through the side opening of the water guide groove 120. The upper opening of the water guide groove 120 is to connect the first sub-air duct 114 with the water guide groove 120, so as to prevent part of the rainwater from entering the first sub-air duct 114 without flowing into it. In the water guide trough 120, the top and side walls of the water guide trough 120 are both open structures, which can ensure that the rainwater flows into the water guide trough 120 stably, so that the unmanned aerial vehicle can effectively guide the rainwater entering the interior, and improve the functional stability of the product. sex.

The water baffle 300 can be the side wall of the water guide trough 120 or the water baffle 300 can be arranged on the side wall of the water guide trough 120, and a gap is set between the water baffle 300 and the top of the fuselage 100, so as to prevent the water baffle 300 from blocking the first part. The air flow in the sub-air duct 114 can increase or decrease the height of the water baffle 300 according to the size of the product to ensure that the water baffle 300 can effectively block rainwater and prevent the rainwater from contacting the first circuit board assembly 200 .

In a possible embodiment, the water blocking board 300 includes: a water blocking board body and a hydrophobic coating, and the hydrophobic coating is provided on the surface of the water blocking board body.

In this embodiment, a hydrophobic coating is provided on the surface of the water baffle body, and the hydrophobic coating is hydrophobic, that is, water is not easy to stay on the surface of the hydrophobic coating. The rainwater flows out of the water guide trough 120, and the rainwater is not easy to accumulate in the water guide groove 120, thereby reducing the residence time of the rainwater in the body 100, which can effectively prevent the body 100 from being wet for a long time and cause corrosion or damage to the internal components of the body 100. Damage rate of unmanned aerial vehicles. Moreover, since the rainwater is not easy to accumulate in the water guide groove 120 , it can avoid the occurrence of the rainwater passing over the water guide groove 120 due to the vibration of the fuselage 100 when the unmanned aerial vehicle encounters unstable airflow, and further prevent the rainwater from contacting the first circuit board assembly 200 . , to improve product safety and reliability.

In a possible embodiment, the water guiding tank 120 includes: a water guiding tank body and a hydrophilic coating, and the hydrophilic coating is provided on the water guiding tank body.

In this embodiment, a hydrophilic coating is provided on the surface of the water guide body, and the hydrophilic coating can guide the rainwater, that is, the hydrophilic coating can guide the rainwater toward the direction close to the second drainage port, so that the rainwater can be quickly The water guide 120 is drained to prevent rainwater from accumulating in the water guide 120 for a long time, reducing the contact time between the rainwater and the internal parts of the fuselage 100 , and preventing the rainwater from causing corrosion or damage to the internal parts of the fuselage 100 .

As shown in FIG. 7 , in a possible embodiment, the height of the bottom wall of the water guide groove 120 decreases toward the direction close to the second air outlet 113 .

In this embodiment, the height change of the bottom wall of the water guide groove 120 is specifically limited. In the direction close to the second air outlet 113, the height of the bottom wall of the water guide groove 120 decreases, and the rainwater will extend under the action of gravity. The gradually lowered bottom wall of the groove flows toward the second air outlet 113, and the water guide groove 120 has a good drainage effect on the rainwater. The residence time in the water guide trough 120 is short, and since the height of the bottom wall of the water guide trough 120 changes gradually, the bottom wall of the water guide trough 120 is slanted, which can prevent rainwater from remaining in the water guide trough 120 and avoid long rainwater. The time is accumulated in the body 100 and the internal components of the body 100 are damaged.

8 and 9, in a possible embodiment, the unmanned aerial vehicle further includes: a groove 116, which is arranged on the bottom wall of the water guide groove 120, and the groove 116 is located in the water guide groove 120 close to the second exhaust air one side of the mouth 113.

In this embodiment, a groove 116 is provided on the side of the water guiding groove 120 close to the second air outlet 113, and the rainwater flowing through the water guiding groove 120 can flow into the groove 116, and the groove 116 can collect rainwater, and then The rainwater is discharged. If a lot of rainwater enters the fuselage 100, a large amount of rainwater will accumulate in the water guide groove 120. When the second air outlet 113 cannot discharge a large amount of rainwater, it may cause the rainwater to pass over the water blocking plate 300 and The contact with the first circuit board assembly 200 occurs. In order to avoid the above situation, the rainwater is collected by arranging the grooves 116, and a large amount of rainwater can be collected in the grooves 116. The grooves 116 play a role in buffering the rainwater. The rainwater that can be discharged in time is accumulated in the groove 116, and a large amount of rainwater is not easy to accumulate in the water guide groove 120, and the rainwater is not easy to cross the water retaining plate 300, which further improves the reliability of the drainage process of the unmanned aerial vehicle and reduces the failure rate of the unmanned aerial vehicle. Conducive to enhance the competitiveness of products.

As shown in FIG. 9 , in a possible embodiment, the groove 116 is located between the air outlet end of the second sub-air duct 115 and the second air outlet 113 .

In this embodiment, since the second sub-channel is also connected to the second air outlet 113 , in order to prevent the rainwater in the water guide trough 120 from flowing back into the second sub-air channel 115 , the groove 116 is arranged in the second sub-air channel 115 When the rainwater flows out of the water guide trough 120 between the air outlet end and the second air outlet 113, the rainwater in the water guide groove 120 will fall into the groove 116 and is not easy to enter the second sub-air duct 115, even if it enters the fuselage 100 The amount of rainwater inside is large and cannot be quickly discharged, and the rainwater will also accumulate in the groove 116, which effectively prevents the rainwater from being diverted into the second sub-air duct 115, thereby preventing the rainwater from contacting the devices in the second sub-air duct 115. Improve the reliability of UAVs.

4 , 10 and 11 , in a possible embodiment, the fuselage 100 includes: a first casing 130 and a second casing 140 , and the second casing 140 is detachably connected to the first casing 140 . The housing 130 , the space formed between the first housing 130 and the second housing 140 is provided with an air guide channel 110 .

In this embodiment, the first casing 130 and the second casing 140 are specifically defined as detachable structures, and the first casing 130 can be disassembled from the second casing 140 , that is, the body 100 is a split structure, and the During the installation process of the unmanned aerial vehicle, the electronic device can be installed in the second casing 140 first, and then the first casing 130 can be installed in the second casing 140, which is convenient for the installation process. Moreover, in the maintenance process of the UAV, the first casing 130 can be disassembled from the second casing 140, which can facilitate the maintenance of the first circuit board assembly 200 in the fuselage 100, and the second casing can be easily maintained. The interior of the body 140 is cleaned, which improves the convenience of the maintenance process.

Specifically, the first shell 130 and the second shell 140 may be provided with snap assemblies 620 that can cooperate with each other, so that the snap assemblies 620 on the first shell 130 can be snapped into the second shell 140 Snap assembly 620. Mounting holes may also be provided on the first housing 130 and the second housing 140 , and the first housing 130 is locked to the second housing 140 through locking members, such as bolts, passing through the mounting holes.

In a possible embodiment, the air inlet 111 is provided in the first housing 130 and/or the second housing 140; the first air outlet 112 is provided in the first housing 130 and/or the second housing 140; The second air outlet 113 is provided in the first casing 130 and/or the second casing 140 .

In this embodiment, the air inlet 111 is arranged at the head end of the fuselage 100. Since the space formed between the first casing 130 and the second casing 140 is provided with an air guide channel 110, the air inlet 111 is arranged at the first The housing 130 and/or the second housing 140 can be communicated with the air guide passage 110, and the air inlets 111 can be one, two or more, which can be increased or The number of air inlets 111 is reduced to ensure that the air intake can effectively dissipate heat from the first circuit board assembly 200 . Similarly, according to the structure of the fuselage 100, the arrangement positions of the first air outlet 112 and the second air outlet 113 can be reasonably arranged, and the first air outlet 112 can be arranged in the first housing 130 and/or the second air outlet 112. On the housing 140, the second air outlet 113 can also be provided on the first housing 130 and/or the second housing 140, and the number of the first air outlet 112 and the second air outlet 113 can be determined according to the exhaust air Demand increases or decreases accordingly.

In this embodiment, there are two air inlets 111 , one air inlet 111 is provided in the first housing 130 , and the other air inlet 111 is provided in the second housing 140 , which is located behind the pan/tilt assembly 1000 . The first air outlet 112 is provided on the top of the second housing 140 , and the second air outlet 113 is provided on the side of the first housing 130 .

3 and 12, in a possible embodiment, the fuselage 100 includes a guide grille 141, the guide grille 141 is provided in the second housing 140, and the guide grille 141 connects the first row The tuyere 112 is divided into at least two sub-air vents.

In this embodiment, a guide grill 141 is specifically defined at the first air outlet 112 , and the guide grill 141 can guide the airflow, so that the airflow can be stably discharged from the air guide channel 110 along the guide grill 141 . , so as to avoid turbulent flow of the air flow at the first air outlet 112 and affect the discharge speed of the air flow, and improve the discharge stability of the air flow.

Moreover, since the first air outlet 112 is arranged on the top of the fuselage 100, there may be sundries falling into the interior of the fuselage 100 from the first air outlet 112 on the top of the fuselage 100, A guide grille 141 is set at 112, and the guide grille 141 divides the first air outlet 112 into a plurality of sub-air outlets. The sundries enter the interior of the fuselage 100 and block the air guide channel 110 , thereby reducing the failure rate of the unmanned aerial vehicle and reducing the maintenance workload of the staff on the unmanned aerial vehicle.

The air guide grille 141 can reduce the flow cross-sectional area of the first air outlet 112, so the air guide grille 141 can also reduce the amount of rainwater entering the fuselage 100, which not only reduces the inflow of water but does not easily affect the exhaust, The amount of rainwater entering the fuselage 100 is small, so as to prevent the rainwater from damaging the components in the fuselage 100 .

With reference to FIG. 2 , FIG. 6 and FIG. 8 , in a possible embodiment, the unmanned aerial vehicle further includes a fan 400 , the fan 400 is arranged on the fuselage 100 , and the fan 400 is located in the air guide channel 110 .

In this embodiment, a fan 400 is defined in the air guide channel 110. The fan 400 can speed up the air flow rate in the air guide channel 110. When the air flow passes through the first circuit board assembly 200 quickly, the air flow can quickly take away the first circuit board assembly 200. The heat on a circuit board assembly 200 improves the heat dissipation speed of the first circuit board assembly 200, and prevents the first circuit board assembly 200 from being damaged due to excessive temperature. Moreover, the air flow driven by the fan 400 can also prevent the high-temperature gas from staying in the air guide channel 110 for a long time, so that the high-temperature gas can be quickly discharged from the fuselage 100, thereby keeping the gas temperature in the air guide channel 110 low, so that the airflow can be A circuit board assembly 200 efficiently exchanges heat.

With reference to FIG. 2 , FIG. 6 and FIG. 13 , in a possible embodiment, the unmanned aerial vehicle further includes a heat sink 240 , the heat sink 240 is provided on the first circuit board assembly 200 , and the heat sink 240 is located in the air guide channel 110 Inside.

In this embodiment, the heat sink 240 has good thermal conductivity. The heat sink 240 is arranged on the first circuit board assembly 200 and the heat sink 240 is placed in the air guide channel 110. The heat sink 240 can quickly displace the first circuit The heat of the board assembly 200 is exported to the air guide channel 110 , so as to speed up the heat dissipation speed of the first circuit board assembly 200 and improve the working stability of the first circuit board assembly 200 .

The heat sink 240 may cover part of the surface of the first circuit board assembly 200 in the air guide channel 110 , or the heat sink 240 may cover the entire surface of the first circuit board assembly 200 in the air guide channel 110 . The heat sink 240 may be a separate component fixed to the first circuit board assembly 200 , and the heat sink 240 may also be a part of the first circuit board assembly 200 .

In a possible embodiment, the fan 400 includes: an air intake end and an air exhaust end, the air intake end is connected to the air inlet 111 ; the air exhaust end faces the heat sink 240 .

In this embodiment, the airflow entering the air guide channel 110 enters into the fan 400 through the air inlet end of the fan 400, and the blades in the fan 400 drive the airflow, so that the airflow passes through the exhaust end of the fan 400 and blows the guide again. In the air channel 110 , since the exhaust end of the fan 400 faces the heat sink 240 , the airflow discharged through the exhaust end of the fan 400 will be directly blown to the heat sink 240 , and the air flow rate on the surface of the heat sink 240 is relatively fast, so that the air flow can be quickly carried by the heat sink 240 . The surface heat of the heat sink 240 is removed to speed up the heat dissipation speed of the heat sink 240, thereby accelerating the heat dissipation speed of the first circuit board assembly 200, ensuring that the temperature of the first circuit board assembly 200 is not easy to be too high, and improving the first circuit board assembly 200. functional stability and reduce the failure rate of unmanned aerial vehicles.

3, 13 and 14, in a possible embodiment, the unmanned aerial vehicle further includes: a second circuit board assembly 500 and a battery 600, the second circuit board assembly 500 is provided on the fuselage 100, The two circuit board assemblies 500 are in contact with the body 100 ; the body 100 is provided with an opening 142 , and the battery 600 is inserted into the opening 142 .

In this embodiment, it is specifically defined that the unmanned aerial vehicle further includes the second circuit board assembly 500. By increasing the functions of the unmanned aerial vehicle, the number of electronic devices on the circuit board will also increase accordingly, so the surface area of the circuit board assembly will also increase. If the air guide channel 110 is large, the air guide channel 110 may not be able to effectively dissipate heat for the circuit board assembly with a large surface area. Therefore, in this embodiment, at least part of the first circuit board assembly 200 is arranged in the air guide channel 110 for heat dissipation, and the other circuit board assembly, That is, the second circuit board assembly 500 is in contact with the body 100 , so that the second circuit board assembly 500 and the body 100 perform heat exchange.

Specifically, during the flight of the UAV, the surface of the fuselage 100 moves relative to the airflow, which can be understood as the surface of the fuselage 100 has an airflow with a faster flow rate, and the airflow with a faster flow velocity can exchange heat with the fuselage 100. The second circuit board assembly 500 can exchange heat with the body 100 , so the body 100 can export the heat of the second circuit board assembly 500 to the outside of the body 100 to realize the heat dissipation function of the second circuit board assembly 500 . The first circuit board assembly 200 conducts heat exchange with the airflow in the air guide channel 110, and the second circuit board assembly 500 conducts heat exchange with the body 100, so that each circuit board assembly can efficiently dissipate heat and avoid some circuit board assemblies due to If the temperature is too high and damage occurs, the working stability of the first circuit board assembly 200 and the second circuit board assembly 500 is improved, and the failure rate of the unmanned aerial vehicle is reduced.

In this embodiment, the second circuit board assembly 500 includes: an ESC assembly 510 , a storage assembly 520 , a lidar assembly 530 and a fill light assembly 540 .

The battery 600 can supply power to the first circuit board assembly 200, the second circuit board assembly 500, and the devices that need power supply in the body 100. The first circuit board assembly 200 and the second circuit board assembly 500 are located on both sides of the battery 600. Only one side of the second circuit board assembly 500 is provided with the battery 600, that is, only one side of the second circuit board assembly 500 is provided with a shield, so the second circuit board assembly 500 can have a larger contact area with the body 100, thereby speeding up the second circuit board assembly 500. The heat dissipation speed of the circuit board assembly 500 can ensure the heat dissipation speed of the first circuit board assembly 200 and the second circuit board assembly 500 by reasonably setting the installation positions of the first circuit board assembly 200 , the second circuit board assembly 500 and the battery 600 . , and can increase the space utilization rate inside the fuselage 100, which is beneficial to reduce the volume of the unmanned aerial vehicle.

In a possible embodiment, the opening 142 is provided at the rear of the fuselage 100 .

In this embodiment, the setting position of the opening 142 is specifically defined, and the opening 142 is arranged at the rear of the fuselage 100 , so the battery 600 is installed inside the fuselage 100 through the rear of the fuselage 100 . In this way, the first circuit board assembly 200 and the second circuit board assembly 500 can both extend along the length direction of the body 100, so the lengths of the first circuit board assembly 200 and the second circuit board assembly 500 are longer, which can improve the first circuit board assembly 200 and the second circuit board assembly 500. The heat dissipation surface area of the board assembly 500 accelerates the heat dissipation speed of the first circuit board assembly 200 and the second circuit board assembly 500 . The battery 600 will not be located in the extending direction of the first circuit board assembly 200 and the second circuit board assembly 500, that is, the battery 600 will not interfere with the installation positions of the first circuit board assembly 200 and the second circuit board assembly 500, which improves the machine. The space utilization rate inside the body 100 is reduced, and the volume of the unmanned aerial vehicle is reduced on the basis of ensuring the heat dissipation speed of the first circuit board assembly 200 and the second circuit board assembly 500 .

FIG. 15 shows a schematic diagram of the body 100 without the battery 600 inserted, FIG. 16 is a schematic diagram of the battery 600 inserted into the body 100 , and FIGS. Schematic.

As shown in FIG. 13 , in a possible embodiment, the first circuit board assembly 200 is located above the battery 600 , and the second circuit board assembly 500 is located below the battery 600 .

In this embodiment, the positions of the first circuit board assembly 200 and the second circuit board assembly 500 relative to the battery 600 are specifically defined, and the first circuit board assembly 200 and the second circuit board assembly 500 are respectively located above and below the battery 600 , the length direction of the first circuit board assembly 200 can be consistent with the length direction of the body 100, and the width direction of the first circuit board assembly 200 can be consistent with the length direction of the body 100, so that the first circuit board assembly 200 can have a larger The surface of the air guide is located in the air guide channel 110 . Similarly, the length direction of the second circuit board assembly 500 may be consistent with the length direction of the body 100, the width direction of the second circuit board assembly 500 may be consistent with the width direction of the body 100, and the second circuit board assembly 500 may be compatible with the body 100. The body 100 has a larger contact area, which improves the heat dissipation speed of the first circuit board assembly 200 and the second circuit board assembly 500 and improves the functional stability of the first circuit board assembly 200 and the second circuit board assembly 500 .

4 and 11, in a possible embodiment, the fuselage 100 further includes a third casing 150, the third casing 150 is detachably connected to the second casing 140, and the second casing 140 Located between the first casing 130 and the third casing 150 , the second circuit board assembly 500 abuts against the third casing 150 .

In this embodiment, since the second circuit board assembly 500 abuts against the third casing 150, the second circuit board assembly 500 is located between the second casing 140 and the third casing 150, and the third casing 150 can be disassembled Because of the second casing 140, the third casing 150 can be disassembled from the second casing 140 during the maintenance process of the UAV, which can facilitate the maintenance of the second circuit board assembly 500 in the fuselage 100, and The interiors of the second housing 140 and the third housing 150 can be cleaned to improve the convenience of the maintenance process.

Specifically, the second casing 140 and the third casing 150 may be provided with snap assemblies 620 that can cooperate with each other, so that the snap assemblies 620 on the third casing 150 can be snap-fitted to the second casing 140 Snap assembly 620. Mounting holes may also be provided on the third housing 150 and the second housing 140 , and the third housing 150 is locked to the second housing 140 through locking members, such as bolts, passing through the mounting holes.

The second circuit board assembly 500 can be fixed on the second casing 140 or the third casing 150 to prevent the second circuit board assembly 500 from shaking in the body 100 , and the second circuit board assembly 500 is not easily connected with the components in the body 100 . The bump reduces the damage rate of the second circuit board assembly 500 .

In a possible embodiment, the third housing 150 includes: a body and a thermally conductive adhesive, the thermally conductive adhesive is provided on the body, and the thermally conductive adhesive is provided between the second circuit board assembly 500 and the body.

In this embodiment, the thermally conductive adhesive is disposed on the surface of the body, and the thermally conductive adhesive has good thermal conductivity, and the thermally conductive adhesive can efficiently conduct the heat of the second circuit board assembly 500 to the body, thereby improving the heat dissipation efficiency of the second circuit board assembly 500 . The thermally conductive adhesive is also viscous, so the thermally conductive adhesive can fix the second circuit board assembly 500 to the body. By setting the thermally conductive adhesive, the second circuit board assembly 500 is fixed and the heat dissipation of the second circuit board assembly 500 can be accelerated. speed.

The thermally conductive adhesive can mount the second circuit board assembly 500 on the body, and it is not necessary to provide the snap-fit assembly 620 and the mounting hole between the second circuit board assembly 500 and the third housing 150 , which simplifies the second circuit board assembly 500 and the third The structure of the casing 150 reduces the processing workload of the second circuit board assembly 500 and the third casing 150, thereby reducing the production and processing cost of the unmanned aerial vehicle.

In a possible embodiment, the third casing 150 is a metal casing.

In this embodiment, the manufacturing material of the third casing 150 is specifically limited to be metal, and the metal has good thermal conductivity, and the metal casing can efficiently conduct the heat of the second circuit board assembly 500 to the outside of the casing 100, thereby improving the performance of the metal casing. Heat dissipation efficiency to the second circuit board assembly 500 .

As shown in FIG. 13 , in a possible embodiment, the unmanned aerial vehicle further includes a deflector 700 , the deflector 700 is provided on the third casing 150 , and a deflector 700 and the third casing 150 are arranged between the deflector 700 . There are diversion channels.

In this embodiment, it is specifically defined that a guide channel is provided on one side of the third housing 150 , and a guide member 700 is installed on one side of the third housing 150 , so that the gap between the guide member 700 and the third housing 150 is A diversion channel is formed. By setting the diversion channel, the gas flow rate on the surface of the third shell 150 can be accelerated. When the air flow passes through the third shell 150 quickly, the air flow can quickly take away the surface heat of the third shell 150, thereby improving the resistance to air flow. The heat dissipation speed of the second circuit board assembly 500 prevents the second circuit board assembly 500 from being damaged due to excessive temperature, reduces the damage rate of the second circuit board assembly 500 , and improves the functional stability of the second circuit board assembly 500 .

In a possible embodiment, the air guide 700 includes: a connecting part and a guide part, the connecting part is connected to the side wall of the third casing 150; the guide part is provided on the connecting part, the guide part and the third casing A guide channel is provided between the bodies 150 .

In this embodiment, the shape of the flow guide is specifically defined, a flow guide channel is formed between the connecting portion, the flow guide portion and the third housing 150, and the connecting portion is connected to the side wall of the third housing 150, so the flow guide member 700 does not need to be in contact with the bottom wall of the third housing 150 , and the second circuit board assembly 500 needs to abut against the bottom wall of the third housing 150 , and the air guide 700 will not block the bottom wall of the third housing 150 , so the third casing 150 can efficiently dissipate heat with the airflow, thereby improving the heat dissipation speed of the second circuit board assembly 500 .

As shown in FIG. 21 , in a possible embodiment, the battery 600 includes: a battery casing 610 and a buckle assembly 620 ; the buckle assembly 620 is provided in the battery casing 610 , and the opening 142 is provided with a buckle assembly 620 . Limiting part.

In this embodiment, during the installation process of the battery 600, the battery 600 is inserted into the opening 142, and when the battery 600 is moved to the installation position, the snap assembly 620 on the battery housing 610 is in contact with the limiting portion in the opening 142. In cooperation, the limiting portion limits the buckle assembly 620 , so that the battery 600 is not easily separated from the opening 142 , and the installation stability of the battery 600 is improved. When the battery 600 needs to be disassembled, the limiting portion and the buckle assembly 620 are disengaged, so that the battery 600 can be taken out from the opening 142 to facilitate charging or replacement of the battery 600 .

In other embodiments, a limiting portion may also be provided on the battery housing 610 , and the snap assembly 620 may be provided on the body 100 . statement.

As shown in FIG. 21 , in a possible embodiment, the buckle assembly 620 includes: a push portion 621 , a first elastic member and a buckle portion 622 . Part of the battery housing 610 is exposed to the opening 142 , and the push portion 621 is provided with On the part of the battery case 610 exposed to the opening 142 ; the head end of the first elastic member is connected to the battery case 610 , the tail end of the first elastic member is connected to the pressing portion 621 , and the first elastic member can move away from the battery case 610 . Push the push portion 621; the buckle portion 622 is connected to the push portion 621, and the push portion 621 can be inserted into the limiting portion.

In this embodiment, the push portion 621 is connected to the buckle portion 622 , so the push portion 621 can drive the buckle portion 622 to move. In contrast, when the battery 600 moves into the opening 142, the buckle portion 622 extends into the battery casing 610, and the pressing portion 621 also extends into the battery casing 610. At this time, the first elastic member is elastically deformed. When the battery 600 moves to the In the installation position, the first elastic member can push the push portion 621, so that the push portion 621 extends out of the battery case 610, so that the push portion 621 drives the buckle portion 622 to extend out of the battery case 610, and the buckle portion 622 can be connected with the battery case 610. The matching of the limiting parts makes it difficult for the battery 600 to escape from the opening 142 , thereby improving the installation stability of the battery 600 . By arranging the first elastic member to push the push portion 621, when the battery 600 moves to the installation position, the user does not need to pull the push portion 621, the first elastic member automatically pushes the push portion 621 to extend out of the battery housing 610, improving the user Ease of use of the snap assembly 620 .

When the battery 600 is installed to the installation position, part of the battery case 610 is exposed outside the body 100 , and the pressing part 621 is disposed on the part of the battery case 610 exposed outside the body 100 , that is, the body 100 will not be pressed against the body 100 . The part 621 is blocked, and the user can easily press the pressing part 621 .

When the battery 600 needs to be disassembled, the user can press the push portion 621, and the push portion 621 drives the buckle portion 622 to separate from the limiting portion, and the limiting portion no longer limits the battery 600, and the user can take out the battery 600, thereby facilitating charging and replacement of the battery 600.

In a possible embodiment, the unmanned aerial vehicle further includes: a first guide surface, disposed on the limiting portion, and the latch portion 622 can abut against the first guide surface and slide along the first guide surface, so that the latch portion 622 can slide along the first guide surface. 622 goes over the limit portion and is snapped into the limit portion; and/or a second guide surface is provided on the snap portion 622, and the first guide surface can abut against the limit portion and slide relative to the limit portion, so that the snap portion 622 goes over the limit part and snaps into the limit part.

In this embodiment, the limiting portion is provided with a first guide surface. During the installation of the battery 600 , the buckle portion 622 abuts against the limiting portion and can slide along the first guide surface on the surface of the limiting portion, so that the buckle portion 622 can slide along the first guide surface on the surface of the limiting portion. The portion 622 can go over the limiting portion, and the limiting portion can restrict the movement of the buckle portion 622 in the direction of moving out of the body 100 . By arranging the first guide surface on the limiting portion, the locking portion 622 can automatically pass over the limiting portion, and the user does not need to press the pressing portion 621 , which improves the convenience in the process of assembling the battery 600 . Similarly, a second guide surface may also be provided on the buckle portion 622 , and the second guide surface on the buckle portion 622 can slide relative to the limit portion, so that the buckle portion 622 can automatically go over the limit portion.

A guide surface may be provided on the limiting portion or the locking portion 622 , or a guide surface may be provided on the limiting portion and the locking portion 622 at the same time.

21 , 22 , 23 , 24 and 25 , in a possible embodiment, the unmanned aerial vehicle further includes: a first detection part 810 and a second detection part 623 , and the first detection part 810 The second detection piece 623 is arranged on the buckle assembly 620. When the first detection piece 810 detects the second detection piece 623, the battery 600 moves to the installation position.

In this embodiment, a first detection member 810 and a second detection member 623 are respectively provided on the inner wall of the opening 142 and the buckle assembly 620. The first detection member 810 can detect whether the battery 600 is moved to the installation position. During the installation of the battery 600, if the first detection part 810 does not detect the second detection part 623, it means that the battery 600 has not moved to the installation position, and it is necessary to continue to push the battery 600 into the fuselage 100. If the first detection part 810 detects When the second detection part 623 is reached, it means that the battery 600 has been moved to the installation position, that is, the battery 600 is installed in place. The user actively judges whether the battery 600 is installed in place, which improves the convenience of the assembly process of the battery 600 .

When the first detection member 810 detects the second detection member 623, it means that the battery 600 is installed in place. At this time, the limit part and the buckle part 622 cooperate to prevent the battery 600 from being separated from the body 100. Moreover, the battery 600 can be installed when the battery 600 is installed in place. , and then control the battery 600 to supply power to the first circuit board assembly 200 and the second circuit board assembly 500, so as to improve the stability of the power supply process.

When the first detection member 810 detects the second detection member 623, it may issue a prompt, such as a voice prompt and/or an indicator light prompt, etc., so as to facilitate the user to know whether the battery 600 is installed in place.

The first detection member 810 and the second detection member 623 may be a position sensor, a laser sensor, an infrared sensor, or the like.

With reference to FIGS. 22 to 25 , in a possible embodiment, the UAV further includes: a protective elastic piece 820 , the protective elastic piece 820 is arranged on the inner wall of the opening 142 , and the protective elastic piece 820 is located on the first detection part 810 and the second between the detection pieces 623 .

In this embodiment, it is specifically defined that a protective elastic sheet 820 is provided on the inner wall of the opening 142 to protect the first detection member 810. When the battery 600 is pushed into the body 100, the second detection member 623 is in contact with the protective elastic sheet. After 820, the protective elastic piece 820 can be pushed, and the protective elastic piece 820 elastically deforms and contacts the first detection piece 810. At this time, it is understood that the first detection piece 810 detects the second detection piece 623, that is, the battery 600 is installed to the installation position. After the battery 600 is disassembled, the protection elasticity is restored to the original state, and the protection elastic piece 820 is no longer in contact with the first detection member 810 , so as to avoid false detection of the first detection member 810 .

The first detection member 810 is protected by providing the protective elastic sheet 820 to prevent the battery 600 from colliding with the first detection member 810 during the installation process to prevent the first detection member 810 from being damaged, and to avoid other components after the battery 600 is disassembled. Entering into the opening 142 causes damage to the first detection member 810 , reduces the damage rate of the first detection member 810 , and can improve the user's experience of using the unmanned aerial vehicle.

15 , 26 , 27 , 28 , 29 and 30 , in a possible embodiment, the unmanned aerial vehicle further includes: an ejection assembly, the ejection assembly is arranged on the inner wall of the opening 142 , and the ejection assembly Can be used to push at least a portion of the battery 600 out of the opening 142 .

In this embodiment, the ejection assembly can push the battery 600 , so that the user can take out the battery 600 from the opening 142 . Specifically, the user presses the push portion 621 so that the push portion 621 drives the buckle portion 622 to separate from the limiting portion, and the limiting portion no longer limits the battery 600 . At this time, the pop-up assembly can remove the battery 600 By pushing, at least part of the battery 600 automatically extends out of the opening 142 , and the user does not need to forcefully pull the battery 600 out of the opening 142 , which improves the convenience for the user to take out the battery 600 .

Specifically, the ejection assembly can push some of the batteries 600 out of the opening 142 , and can also push all the batteries 600 out of the opening 142 . In this embodiment, the ejection assembly pushes some of the batteries 600 out of the opening 142 to prevent the batteries 600 from being completely separated from the body 100 . When the battery 600 is dropped, after part of the battery 600 is moved out of the opening 142 , the user can easily take out the battery 600 to ensure safety during the process of removing the battery 600 .

With reference to FIGS. 26 to 30 , in a possible embodiment, the pop-up assembly includes: a frame body 830 and an elastic assembly 840 ; the frame body 830 is arranged on the inner wall of the opening 142 ; the elastic assembly 840 is arranged on the frame body 830 , When the battery 600 is installed in the opening 142 , the battery 600 can deform the elastic component 840 , and when the buckle component 620 is separated from the limiting portion, the elastic component 840 can push at least part of the battery 600 to move out of the opening 142 .

In this embodiment, the frame body 830 is provided with an elastic component 840 . When the battery 600 is moved into the opening 142 , the battery 600 can push the elastic component 840 , so that the elastic component 840 is elastically deformed. When the snap portion 622 is separated from the limiting portion, the elastic force of the elastic component 840 can act on the battery 600 , so that the elastic component 840 pushes the battery 600 to push at least part of the battery 600 out of the opening 142 , so that the user can take out the battery 600 .

By changing the elastic force of the elastic component 840, the elastic component 840 can be changed to push the battery 600 to prevent the battery 600 from being completely pushed out of the opening 142 due to excessive elastic force of the elastic component 840, thereby improving the safety of the battery 600 disassembly process.

26 to 30, in a possible embodiment, the elastic component 840 includes: a push member 841 and a second elastic member 842, the push member 841 can slide in the frame body 830, and the frame body 830 is provided with A through hole for a part of the pushing member 841 to extend; the head end of the second elastic member 842 is connected to the frame body 830 , and the tail end of the second elastic member 842 is connected to the pushing member 841 .

In this embodiment, the second elastic member 842 can push the pushing member 841 , so that the pushing member 841 can push the battery 600 to move out of the opening 142 . Specifically, when the battery 600 is moved into the opening 142, the battery 600 pushes the pushing member 841, so that the pushing member 841 compresses the second elastic member 842, and the second elastic member 842 is elastically deformed. When the part is separated, the second elastic member 842 pushes the push member 841 , and the push member 841 pushes the battery 600 to extend out of the opening 142 .

The pusher 841 can slide in the frame body 830, and the frame body 830 can guide the pusher 841, so that the pusher 841 can move stably in the direction of withdrawing the battery 600 from the opening 142, so as to prevent the pusher 841 from being deflected, and improve the accuracy of the pusher 841. Stability of battery 600 disassembly process.

Two ends of the second elastic member 842 are respectively connected to the frame body 830 and the push member 841 , the second elastic member 842 is not easily separated from the frame body 830 , and the push member 841 is not easily separated from the second elastic member 842 , improving the structure of the second elastic member 842 stability.

In other embodiments, a limit structure can also be provided on the pusher 841, and the limit structure can abut against the frame body 830, so as to limit the pusher 841 from being separated from the frame body 830.

As shown in FIG. 21 , in a possible embodiment, the battery 600 further includes: a driving part 630 , the driving part 630 is provided in the battery casing 610 , and when the battery 600 is installed in the opening 142 , the driving part 630 can push the pusher 841, so that the second elastic member 842 is deformed.

In this embodiment, a driving part 630 is provided on the battery casing 610, and the driving part 630 can cooperate with the pushing member 841, that is, the driving part 630 can push the pushing member 841, and the pushing member 841 can also push the driving part 630. By arranging the driving part 630 , the cooperation stability of the battery casing 610 and the pusher 841 can be improved, and the stability of the disassembly and assembly process of the battery 600 can be improved.

In a possible embodiment, the first detection member 810 is connected to the buckle portion 622 , and when the battery 600 is installed in the installation position, the second detection member 623 is closer to the push portion 621 than the ejection assembly.

In this embodiment, the first detection member 810 is connected to the push portion 621, so the push portion 621 can drive the first detection member 810 to move. When the battery 600 is installed in the installation position, the second detection member 623 and the buckle portion The distance between the second detection piece 622 and the ejection assembly is smaller than the distance between the second detection piece 623 and the ejection assembly, that is, the distance between the second detection piece 623 and the buckle portion 622 is smaller, so the distance between the first detection piece 810 and the buckle portion 622 is also smaller. The extension length of the buckle assembly 620 is made short, and when the user presses the pressing part 621, the buckle assembly 620 is not easily broken, the damage rate of the buckle assembly 620 is reduced, and the reliability of the buckle assembly 620 is ensured. It is beneficial to improve the user's experience of using the unmanned aerial vehicle.

As shown in FIG. 21, in a possible embodiment, the unmanned aerial vehicle further includes: a guide rail and a guide groove 640, the guide rail is provided on one of the opening 142 and the battery housing 610; the guide groove 640 is provided on the opening 142 and the battery On the other of the housings 610 , the guide rails can slide in the guide grooves 640 .

In this embodiment, the guide grooves 640 can guide the guide rails, so that the battery 600 can be stably extended into or out of the opening 142 in one direction, so as to prevent the battery 600 from being installed in a wrong position, and can also prevent the battery 600 from being installed in a wrong position. The internal parts of the body 100 are damaged, and the stability of the disassembly and assembly process of the battery 600 is improved.

In order to further improve the convenience of the installation process, the guide groove 640 is provided in the battery housing 610 , and the guide rail is provided in the opening 142 . There may be two or more guide grooves 640 . When there are two guide grooves 640 , the two guide grooves 640 are respectively disposed on two side walls facing away from each other in the battery housing 610 , and two guide rails are correspondingly disposed in the opening 142 .

Moreover, connectors are provided on the battery 600 and in the body 100 , and the guide grooves 640 guide the guide rails to ensure that the battery 600 is assembled in place and the connectors are connected reliably.

As shown in FIG. 13 , in a possible embodiment, the first circuit board assembly 200 includes: a positioning assembly 210 and a gyroscope assembly 220 . Compared with the rear end of the fuselage 100 , the positioning assembly 210 and the gyroscopic assembly 220 Approaching the head end of the fuselage 100 .

In this embodiment, it is defined that the first circuit board assembly 200 is provided with a positioning assembly 210 and a gyroscope assembly 220. The positioning assembly 210 has a positioning function so that the user can know the location of the UAV, and the gyroscopic assembly 220 can provide The positioning component 210 and the gyro component 220 can ensure the stability of the unmanned aerial vehicle during the flight of the unmanned aerial vehicle according to the turning angle and heading indication of the unmanned aerial vehicle.

Since the unmanned aerial vehicle usually uses the head end of the fuselage 100 as the windward end, the positioning assembly 210 and the gyro assembly 220 are arranged at the head end of the fuselage 100 to obtain flight instructions accurately and timely, ensuring that the unmanned aerial vehicle is flying during the flight. stability.

As shown in FIG. 13 , in a possible embodiment, the first circuit board assembly 200 further includes: a core board assembly 230 , along the vertical line direction, the positioning assembly 210 and the distance between the gyroscope assembly 220 and the core board assembly 230 Greater than or equal to 10mm.

In this embodiment, the core board assembly 230 may integrate a CPU, a storage device, pins, etc. In order to avoid mutual interference between the electronic devices on the core board assembly 230 and the positioning assembly 210 and the gyroscope assembly 220, the The functional device and the working stability of the positioning assembly 210 and the gyroscope assembly 220 improve the reliability of the unmanned aerial vehicle during flight.

In addition, the CPU will generate a lot of heat during operation. In order to avoid damage to the positioning assembly 210 and the gyroscope assembly 220 caused by the excessively high surface temperature of the CPU, the distance between the positioning assembly 210 and the gyroscope assembly 220 and the core board assembly 230 is limited to be greater than or It is equal to 10mm, which reduces the damage rate of the positioning assembly 210, the gyroscope assembly 220 and the core board assembly 230.

1, 31 and 32, in a possible embodiment, the UAV further includes: a first camera assembly 170 and a second camera assembly 180, the head end of the fuselage 100, the The rear end and the top of the body 100 are provided with a first camera assembly 170 ; the second camera assembly 180 is provided at the bottom of the body 100 .

In this embodiment, the unmanned aerial vehicle has a first camera assembly 170 and a second camera assembly 180 , the first camera assembly 170 can obtain the front, rear, and top views of the fuselage 100 , and the second camera assembly 180 can obtain the fuselage 100 For the lower field of view, by increasing the number of camera components, the UAV has no blind spot or a small blind spot, which improves the barrier capability of the UAV, realizes the omnidirectional obstacle avoidance function of the whole machine, and improves the UAV during flight. safety.

Specifically, the first camera assembly 170 disposed at the head end of the fuselage 100 may be located at the included angle between the head end of the fuselage 100 and the side of the fuselage 100, and the first camera assembly 170 disposed at the rear end of the fuselage 100 may be located at At the angle between the rear end of the fuselage 100 and the side wall of the fuselage 100, the first camera assembly 170 can also obtain the field of view located on the side of the fuselage 100, reducing the blind spot of the unmanned aerial vehicle, and further improving the visibility during flight. safety.

1, 31 and 32, in a possible embodiment, the unmanned aerial vehicle further includes: a first mounting frame 191 and a second mounting frame, the first mounting frame 191 is provided on the fuselage 100, A camera assembly 170 is installed on the first mounting frame 191 ; the second installation frame is installed on the body 100 , and the second camera assembly 180 is installed on the second installation frame.

In this embodiment, there may be two or more first camera assemblies 170 , and the first camera assemblies 170 are installed on the first mounting bracket 191 together, that is, two or more first camera assemblies 170 are integrated into the first installation The first mounting frame 191 can be installed on the fuselage 100, thus realizing the installation of the first camera assembly 170, without the need to install each first camera assembly 170 on the fuselage 100 separately, thereby improving the unmanned Convenience of the aircraft assembly process.

Similarly, there may be two or more second camera assemblies 180 , and the second camera assemblies 180 are centrally installed on the second mounting bracket, which can also improve the convenience of the UAV assembly process.

In a possible embodiment, the unmanned aerial vehicle further includes: a first positioning column, a first shock-absorbing pad, a second positioning column and a second shock-absorbing pad, the first positioning column being provided on the first mounting frame 191; the first positioning column A shock-absorbing pad is sleeved on the first positioning column, the first camera assembly 170 is provided with a first positioning groove, and the first positioning groove is sleeved on the first shock-absorbing pad; the second positioning column is installed on the second mounting frame; Two shock-absorbing pads are sleeved on the second positioning post, the second camera assembly 180 is provided with a second positioning groove, and the second positioning groove is sleeved on the second shock-absorbing pad.

In this embodiment, during the assembly process of the unmanned aerial vehicle, the first shock absorbing pad is sleeved on the first positioning column, and then the first positioning column and the first positioning groove on the first camera assembly 170 are assembled. , the first positioning column plays a role in positioning and limiting the first camera assembly 170, and assembling the first positioning groove to the first fixed position realizes the function of the first camera assembly 170 being installed in place, without the need for staff to adjust the first camera assembly 170. The installation position of the camera assembly 170 improves the convenience of the installation process, and the first positioning column can also limit the first camera assembly 170 to prevent the first camera assembly 170 from shaking relative to the first mounting frame 191 and improve the first camera assembly. 170 installation stability. The first shock-absorbing pad has the function of shock absorption. When the unmanned aerial vehicle vibrates during flight, the first shock-absorbing pad damps the first camera assembly 170, which can prevent the first camera assembly 170 from colliding with the first mounting frame 191. The damage rate of the first camera assembly 170 is reduced, and the reliability of the first camera assembly 170 is improved.

Similarly, the second shock-absorbing pad is sleeved on the second positioning column, and then the second positioning column is assembled with the second positioning groove on the second camera assembly 180, and the second positioning column plays a role in the second camera assembly 180. Positioning and limiting action.

The first shock-absorbing pad and the second shock-absorbing pad can be deformed, so the installation positions of the first camera assembly 170 and the second camera assembly 180 can be fine-tuned to ensure that the installation positions of the first camera assembly 170 and the second camera assembly 180 meet the accuracy requirements .

As shown in FIG. 1 , in a possible embodiment, the UAV further includes: a wing assembly 900 , and the wing assembly 900 is arranged on the fuselage 100 ; the wing assembly 900 includes: a carbon fiber arm shell.

In this embodiment, it is specifically defined that the arm shell is supported by carbon fiber material, and the arm shell made of carbon limit material is lighter in weight, which reduces the weight of the whole unmanned aerial vehicle and improves the stability of the unmanned aerial vehicle during flight. , reduce energy consumption, thereby improving the endurance of unmanned aerial vehicles.

Moreover, due to the high hardness and strength of the arm shell supported by the carbon fiber material, the arm shell is relatively hard and not easy to be damaged. It is not necessary to increase the thickness of the arm shell to increase the strength of the arm shell. In this case, the cross-sectional area of the wing assembly 900 is also smaller, which can reduce the wind resistance of the wing assembly 900, reduce energy consumption, and increase the endurance of the unmanned aerial vehicle.

The arm shell is made of carbon fiber material, and the total mass can be reduced by more than 10 grams compared to the unmanned aerial vehicle in the prior art.

In a possible embodiment, guide surfaces are provided between adjacent wall surfaces of the housing of the machine arm.

In this embodiment, the shape of the arm shell is specifically defined, and a guide surface is arranged between adjacent walls of the arm shell to reduce the wind resistance of the arm shell and further increase the endurance of the unmanned aerial vehicle.

Specifically, the arm casing can adopt a streamlined design, which reduces the resistance of the arm casing by 70% compared to the UAV in the prior art in a common mode, which greatly increases the endurance.

In this application, the term "plurality" refers to two or more, unless expressly defined otherwise. The terms "installed", "connected", "connected", "fixed" and other terms should be understood in a broad sense. For example, "connected" can be a fixed connection, a detachable connection, or an integral connection; "connected" can be It is directly connected or indirectly connected through an intermediary. For those of ordinary skill in the art, the specific meanings of the above terms in this application can be understood according to specific situations.

In the description of this specification, the description of the terms "one embodiment", "some embodiments", "specific embodiment", etc. means that a particular feature, structure, material or characteristic described in connection with the embodiment or example is included in this application at least one embodiment or example of . In this specification, schematic representations of the above terms do not necessarily refer to the same embodiment or instance. Furthermore, the particular features, structures, materials or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.

The above descriptions are only preferred embodiments of the present application, and are not intended to limit the present application. For those skilled in the art, the present application may have various modifications and changes. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of this application shall be included within the protection scope of this application.

Claims

An unmanned aerial vehicle comprising:

a fuselage, the fuselage is provided with an air guide channel and a water guide groove, and at least part of the water guide groove is connected to the air guide channel;

The first circuit board assembly is arranged on the body, and at least part of the first circuit board assembly is located in the air guide channel and is spaced apart from the water guide groove.
The unmanned aerial vehicle of claim 1, wherein the fuselage further comprises:

an air inlet, the air inlet is arranged at the head end of the fuselage, and the air inlet communicates with the air guide channel;

a first air outlet, located on the top of the fuselage, and the first air outlet communicates with the air guide channel and the water guide groove;

The second air outlet is arranged on the side of the fuselage, and the second air outlet communicates with the air guide channel and the water guide groove.
The unmanned aerial vehicle of claim 2, wherein,

Compared with the air inlet, the water guide groove is close to the first air outlet and the second air outlet.
The unmanned aerial vehicle of claim 2, wherein the wind guide channel comprises:

a first sub-air duct, the air inlet and the first air outlet are connected to the first sub-air duct;

In the second sub-air duct, the air inlet is connected to the second sub-air duct, and the air outlet end of the second sub-air duct faces the second air outlet.
The unmanned aerial vehicle of claim 4, wherein the unmanned aerial vehicle further comprises:

a water baffle, arranged in the water guide groove and in the first sub-air duct;

Wherein, the water blocking plate is provided on the side of the water guiding groove away from the first air outlet.
The unmanned aerial vehicle of claim 5, wherein the water baffle comprises:

The body of the water baffle;

The hydrophobic coating is arranged on the surface of the water baffle body.
The unmanned aerial vehicle of claim 1, wherein the water guide comprises:

water guide body;

The hydrophilic coating is arranged on the water guiding tank body.
The unmanned aerial vehicle of claim 2, wherein,

In the direction approaching the second air outlet, the height of the bottom wall of the water guide groove decreases.
The unmanned aerial vehicle of claim 4, wherein the unmanned aerial vehicle further comprises:

The groove is arranged on the bottom wall of the water guide groove, and the groove is located on the side of the water guide groove close to the second air outlet.
The unmanned aerial vehicle of claim 9, wherein,

The groove is located between the air outlet end of the second sub-air duct and the second air outlet.
The unmanned aerial vehicle of claim 2, wherein the fuselage comprises:

the first shell;

The second casing is detachably connected to the first casing, and the air guide channel is provided in the space formed between the first casing and the second casing.
The unmanned aerial vehicle of claim 11, wherein,

the air inlet is arranged on the first casing and/or the second casing;

the first air outlet is provided in the first casing and/or the second casing;

The second air outlet is provided in the first casing and/or the second casing.
The unmanned aerial vehicle of claim 11, wherein the fuselage comprises:

The air guide grille is arranged on the second casing, and the air guide grille divides the first air outlet into at least two sub-air outlets.
The unmanned aerial vehicle of claim 2, wherein the unmanned aerial vehicle further comprises:

The fan is arranged on the fuselage, and the fan is located in the air guide channel.
The unmanned aerial vehicle of claim 14, wherein the unmanned aerial vehicle further comprises:

The heat sink is arranged on the first circuit board assembly, and the heat sink is located in the air guide channel.
The unmanned aerial vehicle of claim 15, wherein the fan comprises:

an air inlet end, the air inlet end communicates with the air inlet;

an air exhaust end, the air exhaust end faces the heat sink.
The unmanned aerial vehicle of claim 12, wherein the unmanned aerial vehicle further comprises:

The second circuit board assembly is arranged on the body, and the second circuit board assembly is in contact with the body;

The battery is provided with an opening on the body, the battery is inserted into the opening, and the first circuit board assembly and the second circuit board assembly are located on both sides of the battery.
The unmanned aerial vehicle of claim 17, wherein,

The opening is provided at the tail of the fuselage.
The unmanned aerial vehicle of claim 17, wherein,

The first circuit board assembly is located above the battery, and the second circuit board assembly is located below the battery.
The unmanned aerial vehicle of claim 17, wherein the fuselage further comprises:

a third case, detachably connected to the second case, the second case being located between the first case and the third case, the second circuit board assembly and the The third shell is offset.
The unmanned aerial vehicle of claim 20, wherein the third housing comprises:

ontology;

The thermally conductive adhesive is arranged on the main body, and the thermally conductive adhesive is arranged between the second circuit board assembly and the main body.
The unmanned aerial vehicle of claim 20, wherein,

The third casing is a metal casing.
The unmanned aerial vehicle of claim 20, wherein the unmanned aerial vehicle further comprises:

A flow guide is arranged on the third housing, and a flow guide channel is arranged between the flow guide and the third housing.
The unmanned aerial vehicle of claim 23, wherein the deflector comprises:

a connecting part, connected to the side wall of the third housing;

The flow guide portion is provided on the connection portion, and the flow guide channel is provided between the flow guide portion and the third housing.
The unmanned aerial vehicle of any one of claims 1 to 24, wherein the battery comprises:

battery case;

The buckle assembly is arranged on the battery casing, and the opening is provided with a limit part matched with the buckle assembly.
The unmanned aerial vehicle of claim 25, wherein the snap assembly comprises:

Pushing part, part of the battery casing is exposed at the opening, and the pushing part is provided on the part of the battery casing exposed at the opening;

A first elastic member, the head end of the first elastic member is connected to the battery case, the tail end of the elastic member is connected to the pressing portion, and the first elastic member can be moved away from the battery case. push the push portion in a direction;

The snap portion is connected to the push portion, and the push portion can be snap-fitted to the limit portion.
The unmanned aerial vehicle of claim 26, wherein the unmanned aerial vehicle further comprises:

A first guide surface is set on the limiting portion, and the snap portion can abut against the first guide surface and slide along the first guide surface, so that the snap portion goes over the limiting portion and snap-fit into the limiting portion; and/or

A second guide surface is provided on the buckling portion. The first guide surface can abut against the limiting portion and slide relative to the limiting portion, so that the buckling portion goes over the limiting portion and The clip is embedded in the limiting portion.
The unmanned aerial vehicle of claim 26, wherein the unmanned aerial vehicle further comprises:

a first detection piece, arranged on the inner wall of the opening;

A second detection piece is arranged on the buckle assembly, and when the first detection piece detects the second detection piece, the battery moves to the installation position.
The unmanned aerial vehicle of claim 28, wherein the unmanned aerial vehicle further comprises:

The protective elastic sheet is arranged on the inner wall of the opening, and the protective elastic sheet is located between the first detection piece and the second detection piece.
The unmanned aerial vehicle of claim 28, wherein the unmanned aerial vehicle further comprises:

An ejection assembly is provided on the inner wall of the opening, and the ejection assembly can be used to push at least part of the battery to move out of the opening.
The unmanned aerial vehicle of claim 30, wherein the ejection assembly comprises:

a frame body; arranged on the inner wall of the opening;

The elastic component is arranged on the frame body. When the battery is installed in the opening, the battery can deform the elastic component. When the buckle component is separated from the limiting portion, the elastic component is The elastic component can push at least part of the battery to move out of the opening.
The unmanned aerial vehicle of claim 31, wherein the resilient assembly comprises:

a pusher, the pusher can slide in the frame body, and the frame body is provided with a through hole for a part of the pusher to extend;

A second elastic member, the head end of the second elastic member is connected to the frame body, and the tail end of the second elastic member is connected to the push member.
The unmanned aerial vehicle of claim 32, wherein the battery further comprises:

The driving part is provided in the battery casing, and when the battery is installed in the opening, the driving part can push the pushing member to deform the second elastic member.
The unmanned aerial vehicle of claim 30, wherein,

the first detection piece is connected to the buckle portion;

When the battery is installed in the installation position, the first detection member is closer to the buckle portion than the ejection assembly.
The unmanned aerial vehicle of claim 25, wherein the unmanned aerial vehicle further comprises:

a guide rail, provided on one of the opening and the battery casing;

A guide groove is provided on the other of the opening and the battery case, and the guide rail can slide in the guide groove.
The unmanned aerial vehicle of any one of claims 1 to 24, wherein the first circuit board assembly comprises:

The positioning assembly and the gyroscope assembly 220 are closer to the head end of the fuselage than the tail end of the fuselage.
The unmanned aerial vehicle of claim 36, wherein the first circuit board assembly further comprises:

For the core board assembly, along the vertical line direction, the distance between the positioning assembly and the gyroscope assembly 220 and the core board assembly is greater than or equal to 10 mm.
The unmanned aerial vehicle of any one of claims 1 to 24, wherein the unmanned aerial vehicle further comprises:

a first camera assembly, the first camera assembly is provided at the head end of the fuselage, the tail end of the fuselage and the top end of the fuselage;

The second camera assembly is arranged at the bottom end of the fuselage.
The unmanned aerial vehicle of claim 38, wherein the unmanned aerial vehicle further comprises:

a first mounting frame, which is arranged on the body, and the first camera assembly is arranged on the first mounting frame;

A second mounting bracket is arranged on the body, and the second camera assembly is arranged on the second mounting bracket.
The unmanned aerial vehicle of claim 39, wherein the unmanned aerial vehicle further comprises:

a first positioning column, which is arranged on the first mounting frame;

a first shock-absorbing pad is sleeved on the first positioning post, the first camera assembly is provided with a first positioning groove, and the first positioning groove is sleeved on the first shock-absorbing pad;

a second positioning column, arranged on the second mounting frame;

A second shock-absorbing pad is sleeved on the second positioning post, the second camera assembly is provided with a second positioning groove, and the second positioning groove is sleeved on the second shock-absorbing pad.
The unmanned aerial vehicle of any one of claims 1 to 24, wherein the unmanned aerial vehicle further comprises:

a wing assembly located on the fuselage;

The wing assembly includes: a carbon fiber arm shell.
The unmanned aerial vehicle of claim 41, wherein:

A guide surface is provided between the adjacent wall surfaces of the casing of the machine arm.