CN213073460U

CN213073460U - Unmanned aerial vehicle

Info

Publication number: CN213073460U
Application number: CN202022165409.2U
Authority: CN
Inventors: 伍振兴; 张雅文; 才志伟; 顾令东; 黎裕熙
Original assignee: SZ DJI Technology Co Ltd
Current assignee: SZ DJI Technology Co Ltd
Priority date: 2020-09-27
Filing date: 2020-09-27
Publication date: 2021-04-27
Anticipated expiration: 2030-09-27
Also published as: WO2022062194A1; CN114514802A

Abstract

The utility model discloses an unmanned aerial vehicle, including the fuselage, assemble in the electricity modulation board of fuselage and be used for doing the radiating radiator of electricity modulation board, the fuselage is including constituting accommodation space's casing, the upper surface and/or the side of casing are equipped with the opening, the opening with accommodation space intercommunication, the electricity modulation board is located in the accommodation space, the radiator install in the opening just expose in the fuselage. The utility model discloses cooperate the radiator in the electricity transfer board to expose the radiator and set up in the upper surface and/or the side of casing, through each flight gesture of coupling unmanned vehicles, the incoming flow when the flight is good in the matching can take away the heat on the electricity modulation board, thereby reaches radiating purpose.

Description

Unmanned aerial vehicle

Technical Field

The utility model relates to an unmanned vehicles.

Background

With the development of electronic technology, the integration degree of the circuit board is higher and higher, the size of the circuit board is smaller and smaller, and the heat flux density of the circuit board is higher and higher. When the circuit boards are applied to miniaturized products (such as unmanned aerial vehicles), the narrow space structure in the products is not beneficial to heat dissipation of the circuit boards. The temperature is a key factor influencing the reliability of the circuit board, and the heating power of the electric adjusting plate is high when the unmanned aerial vehicle violently flies. As the temperature increases, the failure rate of the circuit board increases in geometric multiple. Therefore, how to quickly and effectively dissipate heat from the circuit board is an important factor for determining the reliability of the product.

SUMMERY OF THE UTILITY MODEL

In view of this, the utility model provides an unmanned vehicles can effectively dispel the heat for the electricity modulation board.

An embodiment of the utility model provides an unmanned vehicles, including fuselage, assembly in the electricity modulation board of fuselage and be used for doing the radiating radiator of electricity modulation board, the fuselage is including constituting accommodation space's casing, the upper surface and/or the side of casing are equipped with the opening, the opening with accommodation space intercommunication, the electricity modulation board is located in the accommodation space, the radiator install in the opening just expose in the fuselage.

The utility model discloses unmanned vehicles's further improvement lies in, the opening set up in the anterior side of casing perhaps the afterbody side of casing.

The utility model discloses unmanned vehicles's further improvement lies in, the opening set up in the anterior top of casing perhaps the afterbody upper surface of casing.

The utility model discloses unmanned vehicles' further improvement lies in, unmanned vehicles still includes the horn that is connected to the fuselage and assembles in the rotor subassembly of horn, rotor subassembly includes the screw and drives the motor that the screw rotated;

the opening is formed in the upper surface of the tail of the machine body, and the radiator is located above the tail of the machine body and at least partially located below the propeller.

The utility model discloses unmanned vehicles' further improvement lies in, the opening with the radiator is located the afterbody top of fuselage, the casing includes the front shell of assembling above the fuselage front portion, the front shell includes the drainage surface that is used for leading the air current to the radiator, the drainage surface sets up in the upper surface of front shell is close to the one end of radiator; wherein, in the direction of the front portion towards the afterbody of fuselage, the bearing surface height that the drainage face is relative unmanned vehicles stood reduces.

The utility model discloses unmanned vehicles's further improvement lies in, the radiator include the heating panel and set up in a plurality of heat radiation fins on the heating panel, it is a plurality of heat radiation fins are located the surface of fuselage.

The utility model discloses unmanned vehicles' further improvement lies in, a plurality of heat radiation fins include a plurality of first fins, a plurality of second fins, a plurality of third fins and a plurality of fourth fins; the first fins are arranged in parallel in the direction from the front part of the machine body to the tail part, the second fins are arranged in parallel and are positioned on one sides of the first fins, the third fins are arranged in parallel and are positioned on the other sides of the first fins, one end, far away from the front part of the machine body, of each second fin bends and extends in the direction far away from the corresponding first fin, one end, far away from the front part of the machine body, of each third fin bends and extends in the direction far away from the corresponding first fin, and the fourth fins are arranged in parallel and are arranged on the second fins and the third fins in the plurality of ends, far away from the front part of the machine body.

The unmanned aerial vehicle of the utility model is further improved in that the casing further comprises a decorative shell assembled at the tail part of the vehicle body, and the decorative shell comprises a hollow part; the decorative shell covers the edge of the heat dissipation plate, and the plurality of heat dissipation fins protrude out of the decorative shell from the hollow portion.

The utility model discloses unmanned vehicles's further improvement lies in, unmanned vehicles still including assemble in decorate the shell with sealing member between the heating panel.

The utility model discloses unmanned vehicles's further improvement lies in, unmanned vehicles is still including setting up the electricity transfer board with heat conduction pad between the radiator, the heat conduction pad with the electricity transfer board the heat conduction contact of radiator.

The embodiment of the utility model provides a technical scheme can include following beneficial effect: the utility model discloses cooperate the radiator in the electricity transfer board to expose the radiator and set up in the upper surface and/or the side of casing, through each flight gesture of coupling unmanned vehicles, the incoming flow when the flight is good in the matching can take away the heat on the electricity modulation board, thereby reaches radiating purpose.

Drawings

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

FIG. 2 is a partially exploded schematic view of an unmanned aerial vehicle illustrating an exemplary embodiment of the present invention;

fig. 3 is a top view of an unmanned aerial vehicle, shown in an exemplary embodiment of the present invention;

fig. 4 is a schematic view of an unmanned aerial vehicle in a forward flight state according to an exemplary embodiment of the present invention;

FIG. 5 is an unmanned aerial vehicle illustrating an exemplary embodiment of the invention;

FIG. 6 is an unmanned aerial vehicle illustrating an exemplary embodiment of the invention;

fig. 7 is an unmanned aerial vehicle according to an exemplary embodiment of the present invention.

Detailed Description

The present invention will be described in detail below with reference to specific embodiments shown in the drawings. However, these embodiments are not intended to limit the present invention, and structural, methodical, or functional changes that may be made by one of ordinary skill in the art based on these embodiments are all included in the scope of the present invention.

The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. As used in this specification and the appended claims, the singular forms "a", "an", and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise. It should also be understood that the term "and/or" as used herein refers to and encompasses any and all possible combinations of one or more of the associated listed items.

In the following, some embodiments of the present invention will be described in detail with reference to the accompanying drawings, and features in the following examples and embodiments may be combined with each other without conflict.

Referring to fig. 1 and 2, an unmanned aerial vehicle 100 according to an embodiment of the present invention includes a body 10, an electrical tuning plate 21 assembled to the body 10, and a heat sink 22 for dissipating heat from the electrical tuning plate 21. The electrical panel 21 is provided with a plurality of electronic components for controlling flight, photographing, line detection, signal transmission, and the like of the unmanned aerial vehicle 100. The heat sink 22 is used for performing heat dissipation processing on a plurality of electronic components on the electronic circuit board 21.

In this embodiment, the main body 10 includes a casing 11 forming an accommodating space, an opening 111 is disposed on an upper surface and/or a side surface of the casing 11, the opening 111 is communicated with the accommodating space, the electrical tuning board 21 is located in the accommodating space, and the heat sink 22 is mounted on the opening 111 and exposed from the main body 10. In this embodiment, the heat sink 22 is fitted to the electrical adjustment plate 21, the heat sink 22 is exposed, and the incoming flow of the unmanned aerial vehicle 100 during flight is matched by coupling the flight attitudes, so that heat on the electrical adjustment plate 21 is taken away, thereby achieving the purpose of heat dissipation.

The utility model discloses an unmanned vehicles 100 is for passing through machine or consumption type unmanned aerial vehicle. The requirement of the miniaturized traversing machine on speed and maneuverability is high, and the heating value of the electric adjusting plate 21 is high, especially when the unmanned aerial vehicle 100 is in violent flight. At present, a fan which is only depending on a core board of the body 10 cannot meet the heat dissipation requirement of a chip on the electric adjusting board 21. If the electrical tuning board 21 is placed inside the fuselage 10, a larger-sized fan and heavier heat sink are required to dissipate heat from the electrical tuning board 21, which may increase the cost, weight, and volume of the unmanned aerial vehicle 100, which cannot be realized under the current space and weight constraints. And the utility model discloses in, through cooperating radiator 22 in electric tuning board 21 to expose radiator 22 and set up, under the same heat-sinking capability, can save the space of a fan in the fuselage 10, force the convection scheme than the fan, weight is lighter, and the continuation of the journey is longer, and the cost is also lower.

The opening 111 may be provided on the upper surface of the housing 11, or may be provided on a side surface of the housing 11. Further, the opening 111 may be provided on both the upper surface of the housing 11 and the side surface of the housing 11. Correspondingly, the electrical tuning board 21 is disposed at the position of the opening 111, and the heat sink 22 is mounted in the opening 111 and exposed from the main body 10.

In an embodiment where the opening 111 is provided at a side of the cabinet 11, the opening 111 may be provided at a front side of the cabinet 11 or a rear side of the cabinet 11. The two openings 111 may be disposed on two opposite sides of the housing 11, so as to increase the overall contact area and further achieve the purpose of heat dissipation.

In the embodiment where the opening 111 is provided on the upper surface of the cabinet 11, the opening 111 is provided above the front of the cabinet 11 or on the upper surface of the rear of the cabinet 11, and the electrical tuning board 21 and the heat sink 22 are correspondingly installed at the opening 111. Different settings of the position of the opening 111 all meet the requirement of incoming flow of the coupled unmanned aerial vehicle 100 during matching flight of various flight attitudes, so that the purpose of heat dissipation of the electric adjusting plate 21 is achieved.

In some embodiments, the opening 111 and the heat sink 22 are located above the aft portion of the fuselage 10. Correspondingly, in order to guide the airflow to the heat sink 22, the housing 11 includes a front shell 112 mounted above the front portion of the body 10, the front shell 112 includes a flow guiding surface 1121 for guiding the airflow to the heat sink 22, and the flow guiding surface 1121 is disposed at an end of the upper surface of the front shell 112 close to the heat sink 22. Wherein, in the direction from the front to the tail of the fuselage 10, the height of the drainage surface 1121 relative to the bearing surface on which the unmanned aerial vehicle 100 rests is reduced. The drainage surface 1121 may be an inclined surface or an arc surface.

When the unmanned aerial vehicle 100 flies forward, the head of the unmanned aerial vehicle 100 is inclined downwards by a preset angle to enable the radiating fins of the electric adjusting plate 21 to face the wind and perfectly radiate heat in the direction of the flying incoming flow. The higher the power consumption of the front flight is, the larger the flight inclination angle is, the faster the flight speed is, the windward area of the electric adjusting plate 21 is increased, and the increase of the heat dissipation capacity is perfectly matched with the increase of the power consumption.

Unmanned aerial vehicle 100 also includes a horn 30 coupled to fuselage 10 and a rotor assembly 40 mounted to horn 30. Rotor assembly 40 includes a rotor 41 and a motor 42 that drives rotor 41 in rotation. The opening 111 is disposed on the upper surface of the tail of the fuselage 10, and the heat sink 22 is located above the tail of the fuselage 10 and at least partially below the propeller 41. When the unmanned aerial vehicle 100 is in flight or hovering condition, the external flow field caused by the propeller 41 blows directly to the heat dissipation plate 221 from top to bottom, so that heat on the power conditioning plate 21 is carried away through the heat dissipation plate 221. In the present embodiment, the unmanned aerial vehicle 100 includes a plurality of horn 30 and screw assemblies assembled corresponding to the horn 30, for example: two-rotor aircraft, four-rotor aircraft, etc.

The utility model discloses an unmanned vehicles 100 is still including setting up the heat conduction pad 24 between electricity transfer board 21 and radiator 22, and heat conduction pad 24 and electricity transfer board 21, radiator 22 heat conduction contact can accelerate the heat transfer between electricity transfer board 21 and the radiator 22 through the setting of heat conduction pad 24.

As shown in fig. 1 to fig. 3, the heat sink 22 includes a heat dissipation plate 221 and a plurality of heat dissipation fins 222 disposed on the heat dissipation plate 221, the plurality of heat dissipation fins 222 are disposed on the surface of the main body 10, and the heat dissipation on the heat dissipation plate 221 can be accelerated by the disposition of the heat dissipation fins 222.

The plurality of heat dissipation fins 222 includes a plurality of first fins 2221, a plurality of second fins 2222, a plurality of third fins 2223, and a plurality of fourth fins 2224. The different shapes of the heat dissipation fins 222 are designed to meet the heat dissipation requirements at various flight attitudes. In this embodiment, in a direction from the front portion to the rear portion of the main body 10, the plurality of first fins 2221 are arranged in parallel, the plurality of second fins 2222 are arranged in parallel and located on one side of the plurality of first fins 2221, the plurality of third fins 2223 are arranged in parallel and located on the other side of the plurality of first fins 2221, one end of the second fins 2222 away from the front portion of the main body 10 is bent and extended in a direction away from the first fins 2221, one end of the third fins 2223 away from the front portion of the main body 10 is bent and extended in a direction away from the first fins 2221, and the fourth fins 2224 are arranged in parallel at one ends of the plurality of second fins 2222 and the plurality of third fins 2223 away from the front portion of the main body 10. The second fins 2222 and the third fins 2223 are bent, so that the airflow can be guided to different directions, and the heat dissipation requirements of the unmanned aerial vehicle 100 under working conditions such as violent ascent and violent pan brushing can be met.

As shown in fig. 4 and 5 in combination with fig. 2, when the unmanned aerial vehicle 100 flies forward, the inclination angle of the unmanned aerial vehicle 100 allows the heat sink 22 to face the wind and perfectly dissipate heat in response to the incoming flow of the flight. The higher the power consumption of the front flight, the larger the flight inclination angle and the higher the flight speed, the larger the power consumption of the electric adjusting plate 21, the larger the windward area of the radiator 22 and the perfect matching between the increase of the heat dissipation capacity and the increase of the power consumption of the electric adjusting plate 21.

As shown in fig. 6 in conjunction with fig. 2, the ascending incoming flow can also allow wind to travel over the fins 222 of the heat sink 22 when the unmanned aerial vehicle 100 violently ascends. The larger the heat productivity of the electric adjusting plate 21 is, the faster the rising speed is, the larger the corresponding rising incoming flow is, the matching between the increase of the heat dissipation capacity and the increase of the power consumption can be realized, and the overtemperature of the device on the electric adjusting plate 21 can be avoided.

As shown in fig. 7 in conjunction with fig. 2, when the UAV 100 violently brushes the pan, the lateral inclination of the UAV 100 also allows wind to pass between the fins 222 of the heat sink 22, thereby carrying away heat from the electrical panel 21.

As shown in fig. 6 in conjunction with fig. 2, in the hovering condition of the unmanned aerial vehicle 100, the external flow field induced by the propeller 41 directly blows from top to bottom to the heat dissipation fins 222 of the heat sink 22, and carries away heat on the tuning board 21.

Referring again to fig. 1 and 2, the housing 11 further includes a decorative cover 113 mounted to the rear of the body 10, and the decorative cover 113 includes a hollow portion 1131. The decorative shell 113 covers the edge of the heat sink 221, and the plurality of heat dissipating fins 222 protrude from the hollow portion 1131 to the decorative shell 113. In this embodiment, the hollow portion 1131 of the decoration shell 113 is U-shaped, the opening 111 of the decoration shell 113 faces the front shell 112, and after the decoration shell 113 is assembled to the body 10, the hollow shell is connected to the front shell 112.

Further, the unmanned aerial vehicle 100 further includes a sealing member 23 fitted between the decorative case 113 and the heat dissipation plate 221. By fitting this seal 23, the heat sink 221 and the fuselage 10 are hermetically connected, so that the heat sink 221 is exposed and the waterproof property of the fuselage 10 of the unmanned aerial vehicle 100 is ensured.

The utility model discloses cooperate the radiator in the electricity transfer board to expose the radiator and set up in the upper surface and/or the side of casing, through each flight gesture of coupling unmanned vehicles, the incoming flow when the flight is good in the matching can take away the heat on the electricity modulation board, thereby reaches radiating purpose. Compared with the scheme of the existing heat dissipation design, the space of one fan in the machine body can be saved under the same heat dissipation capacity, and compared with the scheme of forced convection of the fan, the fan-type heat dissipation fan has the advantages of lighter weight, longer endurance and lower cost.

Other embodiments of the invention will be apparent to those skilled in the art from consideration of the specification and practice of the invention disclosed herein. This application is intended to cover any variations, uses, or adaptations of the invention following, in general, the principles of the invention and including such departures from the present disclosure as come within known or customary practice within the art to which the invention pertains. It is intended that the specification and examples be considered as exemplary only, with a true scope and spirit of the invention being indicated by the following claims.

It will be understood that the invention is not limited to the precise arrangements described above and shown in the drawings and that various modifications and changes may be made without departing from the scope thereof. The scope of the present invention is limited only by the appended claims.

Claims

1. The utility model provides an unmanned vehicles (100), its characterized in that, including fuselage (10), assemble in the electricity transfer board (21) of fuselage (10) and be used for doing the radiating radiator (22) of electricity transfer board (21), fuselage (10) are including casing (11) that constitute accommodation space, the upper surface and/or the side of casing (11) are equipped with opening (111), opening (111) with accommodation space intercommunication, electricity transfer board (21) are located in the accommodation space, radiator (22) install in opening (111) and expose in fuselage (10).

2. The unmanned aerial vehicle (100) of claim 1, wherein the opening (111) is provided at a front side of the cabinet (11) or a rear side of the cabinet (11).

3. The unmanned aerial vehicle (100) of claim 1, wherein the opening (111) is disposed above a front portion of the cabinet (11) or an aft upper surface of the cabinet (11).

4. The unmanned aerial vehicle (100) of claim 3, wherein the unmanned aerial vehicle (100) further comprises a horn (30) coupled to the fuselage (10) and a rotor assembly (40) mounted to the horn (30), the rotor assembly (40) comprising a propeller (41) and a motor (42) for driving the propeller (41) in rotation;

the opening (111) is formed in the upper surface of the tail of the machine body (10), and the radiator (22) is located above the tail of the machine body (10) and at least partially located below the propeller (41).

5. The UAV (100) according to claim 3, wherein the opening (111) and the radiator (22) are located above the rear of the fuselage (10), the chassis (11) comprises a front shell (112) fitted above the front of the fuselage (10), the front shell (112) comprises a flow-guiding surface (1121) for guiding the airflow towards the radiator (22), the flow-guiding surface (1121) being arranged at the upper surface of the front shell (112) near one end of the radiator (22); wherein, in the direction from the front part to the tail part of the fuselage (10), the height of the diversion surface (1121) relative to the bearing surface on which the unmanned aerial vehicle (100) rests is reduced.

6. The UAV (100) of claim 1, wherein the heat sink (22) comprises a heat spreader plate (221) and a plurality of heat fins (222) disposed on the heat spreader plate (221), the plurality of heat fins (222) being located on a surface of the fuselage (10).

7. The UAV (100) of claim 6 wherein the plurality of cooling fins (222) comprises a plurality of first fins (2221), a plurality of second fins (2222), a plurality of third fins (2223), and a plurality of fourth fins (2224); the plurality of first fins (2221) are arranged in parallel in the direction from the front part to the tail part of the machine body (10), the plurality of second fins (2222) are arranged in parallel and are positioned on one side of the plurality of first fins (2221), the plurality of third fins (2223) are arranged in parallel and are positioned on the other side of the plurality of first fins (2221), one end, far away from the front part of the machine body (10), of the second fins (2222) is bent and extended in the direction far away from the first fins (2221), one end, far away from the front part of the machine body (10), of the third fins (2223) is bent and extended in the direction far away from the first fins (2221), and the fourth fins (2224) are arranged in parallel at one ends, far away from the front part of the machine body (10), of the plurality of second fins 2222 and the plurality of third fins (2223).

8. The UAV (100) according to claim 6, wherein the housing (11) further comprises a decorative shell (113) fitted to the rear of the fuselage (10), the decorative shell (113) comprising a hollowed-out portion (1131); the decorative shell (113) covers the edge of the heat dissipation plate (221), and the plurality of heat dissipation fins (222) protrude out of the decorative shell (113) from the hollow portion (1131).

9. The unmanned aerial vehicle (100) of claim 8, wherein the unmanned aerial vehicle (100) further comprises a seal (23) fitted between the trim cover (113) and the heat sink plate (221).

10. The unmanned aerial vehicle (100) of claim 1, wherein the unmanned aerial vehicle (100) further comprises a thermal pad (24) disposed between the electrical tuning board (21) and the heat sink (22), the thermal pad (24) being in thermally conductive contact with the electrical tuning board (21) and the heat sink (22).