WO2021196138A1

WO2021196138A1 - Heat dissipation device for cabin of unmanned aerial vehicle

Info

Publication number: WO2021196138A1
Application number: PCT/CN2020/083043
Authority: WO
Inventors: 杨思强
Original assignee: 南京达索航空科技有限公司
Priority date: 2020-03-31
Filing date: 2020-04-02
Publication date: 2021-10-07
Also published as: CN211969749U

Abstract

A heat dissipation device for the cabin of an unmanned aerial vehicle, the device comprising: a cabin inner cylinder (20), a cabin outer cylinder (10), a first heat dissipation sheet (13), a first heat preservation sheet (14), a second heat dissipation sheet (22) and a second heat preservation sheet (23). Following the relative rotation of the cabin inner cylinder and the cabin outer cylinder, when the first heat dissipation sheet and the second heat dissipation sheet overlap, heat in the cabin inner cylinder is rapidly conducted and dissipated by means of the first heat dissipation sheet and the second heat dissipation sheet, thereby promoting heat dissipation. When the first heat dissipation sheet and the second heat dissipation sheet are staggeredly distributed, the first heat preservation sheet and the second heat preservation sheet carry out heat preservation at the interior of the cabin inner cylinder, thereby reducing the speed at which heat is dissipated. The described heat dissipation device for the cabin of an unmanned aerial vehicle can increase the speed at which heat is dissipated at the interior of the engine cabin, while also having a heat preservation function, thus enabling the unmanned aerial vehicle to suit flight requirements in different environments.

Description

Radiating device for unmanned aerial vehicle cabin

Technical field

The utility model belongs to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle cabin heat dissipation device.

Background technique

Unmanned aircraft is abbreviated as unmanned aerial vehicle, which is an unmanned aircraft operated by radio remote control equipment and self-provided program control devices. As a new concept equipment, UAV has the advantages of flexibility, rapid response, unmanned flight and easy operation. It is widely used in meteorology, exploration, photography and other fields.

During the flight of the UAV, the integrated circuit components inside the cabin will generate a lot of heat. If this heat cannot be dissipated in time, it will easily cause the circuit board to overheat and affect the flight stability of the UAV. Therefore, it is necessary to install a heat dissipation device in the drone cabin to promote the rapid dissipation of heat.

However, drones sometimes need to fly in harsh working environments such as high temperatures. The low temperature in these areas will cause unstable power supply and insufficient flight power of the drone, which can easily cause the drone to ground and fall. risk.

technical problem

A heat dissipation device for an unmanned aircraft cabin is provided to solve the above-mentioned problems existing in the prior art.

Technical solutions

In order to achieve the above objectives, the present invention provides the following technical solutions:

A heat dissipating device for a cabin of an unmanned aerial vehicle, comprising: a cabin outer tube fixed on the drone and an inner cabin tube inserted in the cabin outer tube, the top of the cabin outer tube is closed, and the side outer wall of the cabin outer tube is close to One end of the bottom is provided with a fixing part for fixing the heat dissipation device, a plurality of arc-shaped first radiating fins and first heat insulation fins are attached to the side inner wall of the outer cylinder of the engine room; the top of the inner cylinder of the engine room is closed, and the engine room The inner cylinder is fixed with a support plate for fixing the integrated circuit board, the bottom of the engine room inner cylinder is screwed with a bottom plate, and the side outer wall of the engine room inner cylinder is attached with a plurality of second radiating fins and second insulation fins; The outer cylinder of the engine room and the inner cylinder of the engine room are rotatably connected.

In a further embodiment, the first heat radiating fin, the first heat insulation fin, the second heat radiating fin, and the second heat insulation fin are all arc-shaped structures and the arc surface angles are equal; the first heat dissipation fin and the second heat insulation fin The fins are arranged at intervals, and the second heat dissipation fins and the second heat insulation fins are arranged at intervals; the inner diameter of the first heat dissipation fin or the first heat insulation fin is equal to the outer diameter of the second heat dissipation fin or the second heat insulation fin; The relative rotation of the content, the heat sink has two states: heat dissipation and heat preservation; when the heat sink is in the heat dissipation state, the first heat sink overlaps the second heat sink, and the heat in the cabin inner cylinder passes through the first heat sink and the second heat sink When the heat dissipation device is in the heat preservation state, the first heat sink and the second heat sink are in a staggered distribution. At this time, the first heat insulation fin and the second heat insulation fin are arranged at intervals to block the heat in the inner cylinder of the engine room. Reduce the speed of heat dissipation. Through this setting, the drone's cabin can have the dual functions of heat dissipation and heat preservation, adapting to flight requirements in different environments.

In a further embodiment, the first heat sink and the second heat sink are made of thermally conductive silicone sheets, which have excellent thermal conductivity and can ensure the heat dissipation effect of the heat sink.

In a further embodiment, the first insulation sheet and the second insulation sheet are made of polystyrene board, and the polystyrene board has a certain insulation performance, which can make the heat dissipation device have a certain insulation performance, so that the drone can adapt to Flying in an alpine environment.

In a further embodiment, a fan is fixed on the top inner wall of the inner cylinder of the nacelle, and a number of heat dissipation holes are opened on the bottom plate along the vertical direction. Dissipate to the outside of the heat dissipation device through the heat dissipation holes, and the cold air outside the heat dissipation device enters the interior of the inner cylinder of the nacelle through the heat dissipation holes, thereby realizing rapid heat dissipation of the heat dissipation device.

In a further embodiment, the heat dissipation hole includes a first through hole near the middle of the bottom plate and a second through hole near the edge of the bottom plate, and the diameter of the top end of the first through hole is larger than the diameter of the bottom end of the first through hole; The diameter of the top end of the second through hole is smaller than the diameter of the bottom end of the second through hole; through this arrangement, the convection of air between the inner cylinder of the nacelle and the outside of the heat dissipation device is promoted, and the heat dissipation effect of the heat dissipation device is improved.

In a further embodiment, the side inner wall of the outer cylinder of the engine room is provided with a first annular groove at one end close to the bottom, and the end of the side outer wall of the inner cylinder of the engine room near the bottom is provided with a second annular groove. The groove and the second annular groove are arranged oppositely, and a number of balls are arranged in the first and second annular grooves; through this arrangement, the relative rotation of the nacelle inner tube and the nacelle outer tube is promoted, and the nacelle inner tube and the nacelle outer tube are reduced Friction and wear during relative rotation.

Beneficial effect

The cooling device for the cabin of the unmanned aerial vehicle provided by the utility model includes: an inner tube of the cabin, an outer tube of the cabin, a first radiating fin, a first insulation fin, a second radiating fin, and a second insulation fin. The inner tube of the nacelle and the outer tube of the nacelle can be relatively rotated, so that the first radiating fin and the second radiating fin are in different distribution states. When the first radiating fin and the second radiating fin overlap, the heat in the inner tube of the nacelle is radiated through the first heat sink. The fins and the second radiating fins quickly conduct and dissipate to promote heat dissipation; when the first and second radiating fins are staggered, the first and second insulation fins heat the inside of the cabin inner tube and reduce the heat dissipation speed . Compared with the prior art, the heat dissipation device for the nacelle of the drone provided by the utility model can increase the heat dissipation speed in the engine nacelle, while also taking into account the heat preservation function, so that the drone can adapt to flight requirements in different environments.

Description of the drawings

Fig. 1 is a schematic diagram of the structure of the heat dissipation device for the nacelle of the unmanned aerial vehicle of the present invention.

Figure 2 is a cross-sectional view of the heat dissipation device of the present invention.

Fig. 3 is a partial view of the utility model at A in Fig. 2.

Fig. 4 is a distribution diagram of the first heat dissipation fin, the first heat insulation fin, the second heat dissipation fin and the second heat insulation fin when the heat dissipation device of the present invention is in a heat dissipation state.

Fig. 5 is a distribution diagram of the first heat dissipation fin, the first heat preservation fin, the second heat dissipation fin and the second heat preservation fin when the heat dissipation device of the present invention is in a heat preservation state.

Figure 6 is a cross-sectional view of the structure of the bottom plate of the present invention.

1 to 6 are marked as: engine room outer tube 10, fixed portion 11, first annular groove 12, first radiating fin 13, first insulation sheet 14, engine room inner tube 20, second annular groove 21, The second heat sink 22, the second heat insulation sheet 23, the bottom plate 30, the heat dissipation hole 31, the first through hole 311, the second through hole 312, the support plate 40, the balls 50, and the fan 60.

Embodiments of the present invention

In the following description, a lot of specific details are given in order to provide a more thorough understanding of the present invention. However, it is obvious to those skilled in the art that the present invention can be implemented without one or more of these details. In other examples, in order to avoid confusion with the present invention, some technical features known in the art are not described.

Researchers have found that UAVs are extremely widely used. During the flight of the UAV, the integrated circuit components inside the cabin generate a lot of heat. If it is not discharged in time, the circuit board will easily overheat and affect the flight stability of the UAV. At the same time, drones sometimes need to adapt to the flying environment in high-cold areas, where the temperature is low, which can easily cause the power supply of the drone to be unstable, cause the drone to have insufficient flight power, and even cause the drone to ground. Falling conditions. Therefore, how to improve the heat dissipation device to ensure the heat dissipation effect while having the heat preservation function has become a problem that needs to be solved urgently.

In order to solve the above-mentioned problems, the present invention provides an unmanned aerial vehicle cabin heat dissipation device, as shown in FIG. 1 and FIG.

Specifically, in conjunction with Figures and 3, the nacelle outer tube 10 has a cylindrical structure, the top of the nacelle outer tube 10 is closed, and the side outer wall of the nacelle outer tube 10 is provided with a plurality of fixing parts 11 at one end near the bottom. The fixing portion 11 in this embodiment includes a connecting lug, and a connecting through hole is opened on the connecting lug. The outer cylinder 10 of the nacelle is fixed to the unmanned aerial vehicle by setting screws or bolts in the connecting through hole. The nacelle inner tube 20 also has a cylindrical structure. The top of the nacelle inner tube 20 is closed. The bottom inner wall of the nacelle inner tube 20 is provided with internal threads. The bottom of the nacelle inner tube 20 is screwed with a circular bottom plate 30. The side of the bottom plate 30 An external thread is provided, and the external thread is adapted to the internal thread on the bottom of the inner cylinder 20 of the nacelle. The inner cylinder 20 and the bottom plate 30 of the nacelle surround to form a closed containment cavity (not marked in the figure). The containment chamber is provided with a support plate 40, which is fixedly connected to the side inner wall of the nacelle, and the integrated circuit of the drone is installed With the support plate 40 on it. The nacelle inner tube 20 and the nacelle outer tube 10 are relatively rotatable. One end of the side inner wall of the nacelle outer tube 10 close to the bottom is along the first annular groove 12 in the circumferential direction; A second annular groove 21 is opened in the direction. The first annular groove 12 and the second annular groove 21 are arranged oppositely. A number of balls 50 are arranged in the first annular groove 12 and the second annular groove 21. When the barrel 10 rotates, the ball 50 rolls in the first annular groove 12 and the second annular groove 21, thereby reducing the friction and wear between the nacelle inner tube 20 and the nacelle outer tube 10.

With reference to FIGS. 4 and 5, a plurality of arc-shaped first heat dissipation fins 13 and first heat insulation fins 14 are attached to the side inner wall of the outer cylinder 10 of the nacelle. At the same time, a plurality of arc-shaped second heat dissipation fins 22 and second heat insulation fins 23 are attached to the side outer wall of the inner cylinder 20 of the nacelle. Wherein, the arc angles of the first heat dissipation fin 13, the first heat insulation fin 14, the second heat dissipation fin 22, and the second heat insulation fin 23 are all equal, which are all 30°. At the same time, the lengths of the first heat dissipation fin 13, the first heat insulation fin 14, the second heat dissipation fin 22, and the second heat insulation fin 23 in the vertical direction are also equal. The number of the first heat dissipation fins 13 and the first heat insulation fins 14 is equal, and both are six; The numbers of the second heat sink 22 and the second heat insulation piece 23 are also equal, both being six; the second heat sink 22 and the second heat insulation piece 23 are arranged at intervals to cover the lateral outer wall of the inner cylinder 20 of the nacelle. The inner diameter of the first heat dissipation fin 13 or the first heat insulation fin 14 is equal to the outer diameter of the second heat dissipation fin 22 or the second heat insulation fin 23. With the relative rotation of the nacelle outer tube 10 and the nacelle inner tube 20, the heat dissipation device has two states of heat dissipation and heat preservation. When the first heat sink 13 and the second heat sink 22 overlap, the first heat sink 13 and the second heat sink 22 form a connected thermal bridge. Due to the high thermal conductivity of the first heat sink 13 and the second heat sink 22, the cabin The heat of the content is quickly conducted and dissipated through the second heat sink 22 and the first heat sink 13, so as to realize rapid heat dissipation. At this time, the heat sink is in a heat dissipation state. When the first heat sink 13 and the second heat sink 22 are staggered, the first heat insulating fins 14 and the second heat insulating fins 23 are also staggered, and the thermal bridge formed by the first heat sink 13 and the second heat sink 22 is interrupted. An insulation layer formed by a thermal insulation sheet 14 and a second thermal insulation sheet 23 blocks the heat in the inner cylinder 20 of the nacelle, reduces the heat dissipation speed, and keeps the heat dissipation device in a thermal insulation state. Through such a setting, the cabin of the drone can quickly dissipate heat and also have the function of heat preservation, so that the drone can adapt to different flight loops. The first heat sink 13 and the second heat sink 22 in this embodiment are made of JRF-PM800 thermally conductive silicone sheet, and its thermal conductivity can reach 8.0W/(MK), with excellent thermal conductivity, and can ensure heat dissipation The device quickly dissipates heat. The thermal insulation sheet in this embodiment is made of polystyrene board (also known as polystyrene board), its thermal conductivity is not more than 0.041W/(MK), and has a certain thermal insulation performance, so that the heat dissipation device has a thermal insulation function. Adapt the drone to the alpine environment.

The heat in the nacelle inner tube 20 through heat conduction essentially belongs to a passive heat dissipation method, and the heat is dissipated through conduction and radiation. The heat in the inner cylinder 20 of the nacelle first needs to be transferred through the air and then transmitted and dissipated through the second heat sink 22 and the first heat sink 13. This heat dissipation process requires multiple heat transfer media, so a certain heat transfer time is required. Therefore, there is room for improvement in the heat dissipation device proposed by the present invention. In order to further improve the heat dissipation performance of the heat dissipation device, a fan 60 is fixed on the top inner wall of the inner cylinder 20 of the nacelle; at the same time, a number of heat dissipation holes 31 are opened on the bottom plate 30 along the vertical direction. . The continuous rotation of the fan 60 promotes the convection of the hot air in the inner cylinder 20 of the engine room and the hot air outside, and promotes heat exchange, so that the hot air is emitted through the heat dissipation holes 31, and the cold air enters the engine room inner cylinder through the heat dissipation holes 31. In the interior of 20, through this active heat dissipation method, the rapid heat dissipation of the heat dissipation device is realized.

In order to promote the convection of the hot air in the inner cylinder 20 of the nacelle and the cold air outside the heat sink, in conjunction with FIG. 2 and FIG. 6, in a further embodiment, the heat dissipation hole 31 includes a first through hole 311 near the middle of the bottom plate 30 and The second through hole 312 at the edge of the bottom plate 30. The diameter of the top end of the first through hole 311 is larger than the diameter of the bottom end of the first through hole 311. Under the action of the fan 60, the hot air in the inner cylinder 20 of the nacelle can easily flow out from the first through hole 311, and the outside cold air It is difficult to enter the interior of the nacelle inner tube 20 from the first through hole 311. The diameter of the top end of the second through hole 312 is smaller than the diameter of the bottom end of the second through hole 312. The outside cold air easily enters the interior of the nacelle inner tube 20 through the second through hole 312, while the hot air in the nacelle inner tube 20 is difficult to pass through the second through hole 312. The two through holes 312 are discharged. As a result, cold air enters the nacelle inner tube 20 from the second through hole 312 near the side, and the hot air in the nacelle inner tube 20 is discharged from the first through hole 311 near the middle, thereby forming a stable air circulation loop and improving the cabin. The convection of the air inside and outside the cylinder 20 improves the heat dissipation effect of the heat dissipation device.

The preferred embodiments of the present utility model are described in detail above with reference to the accompanying drawings. However, the present utility model is not limited to the specific details in the above-mentioned embodiments. Within the scope of the technical concept of the present utility model, various technical solutions of the present utility model can be made. These equivalent transformations all belong to the protection scope of the present invention.

Claims

A heat dissipating device for a cabin of an unmanned aerial vehicle, characterized by comprising: an outer cabin of the cabin fixed on the unmanned aerial vehicle and an inner cabin of the cabin inserted in the outer cabin of the cabin, the top of the outer cabin of the cabin is closed, and the outer cabin of the cabin One end of the side outer wall near the bottom is provided with a fixing part for fixing the heat dissipation device, the side inner wall of the outer cylinder of the engine room is attached with a plurality of arc-shaped first radiating fins and first heat insulation fins; the top of the inner cylinder of the engine room is closed A support plate for fixing the integrated circuit board is fixed in the inner cylinder of the nacelle, a bottom plate is screwed on the bottom of the inner cylinder of the nacelle, and a plurality of second radiating fins and second Insulation sheet; the outer cylinder of the engine room and the inner cylinder of the engine room are rotatably connected.
The heat dissipation device according to claim 1, wherein the first heat sink, the first heat insulation fin, the second heat dissipation fin, and the second heat insulation fin are all arc-shaped structures and the arc-shaped surface angles are equal; A heat dissipation fin and a second heat insulation fin are arranged at intervals, and the second heat dissipation fin and the second heat insulation fin are arranged at intervals; the inner diameter of the first heat dissipation fin or the first heat insulation fin is equal to the outer diameter of the second heat dissipation fin or the second heat insulation fin; With the relative rotation of the outer cylinder of the cabin and the contents of the cabin, the heat dissipation device has two states of heat dissipation and heat preservation; when the heat dissipation device is in the heat dissipation state, the first heat sink and the second heat dissipation fin overlap; when the heat dissipation device is in the heat preservation state, the first heat sink and the second heat sink overlap; A heat sink and a second heat sink are distributed in a staggered manner.
The heat dissipation device according to claim 1, wherein the first heat sink and the second heat sink are made of thermally conductive silica gel sheets.
The heat dissipation device according to claim 1, wherein the first heat insulation sheet and the second heat insulation sheet are made of polystyrene board.
The heat dissipation device according to claim 1, wherein a fan is fixed on the top inner wall of the inner cylinder of the nacelle, and a plurality of heat dissipation holes are opened in the vertical direction on the bottom plate.
The heat dissipation device according to claim 5, wherein the heat dissipation hole comprises a first through hole near the middle of the bottom plate and a second through hole near the edge of the bottom plate, and the top diameter of the first through hole is larger than that of the first through hole. The diameter of the bottom end of the hole; the diameter of the top end of the second through hole is smaller than the diameter of the bottom end of the second through hole.
The heat dissipation device according to claim 1, wherein a first annular groove is formed on an end of the side inner wall of the outer cylinder of the engine room near the bottom, and a second ring groove is formed on the end of the lateral outer wall of the inner cylinder of the engine room near the bottom. A groove, the first annular groove and the second annular groove are arranged oppositely, and a plurality of balls are arranged in the first annular groove and the second annular groove.