CN213510836U

CN213510836U - Unmanned aerial vehicle engine water-cooling heat abstractor

Info

Publication number: CN213510836U
Application number: CN202022790816.2U
Authority: CN
Inventors: 应宁宁
Original assignee: Jiangxi Saijun Power Technology Co ltd
Current assignee: Jiangxi Saijun Power Technology Co ltd
Priority date: 2020-11-27
Filing date: 2020-11-27
Publication date: 2021-06-22
Anticipated expiration: 2030-11-27

Abstract

The utility model discloses an unmanned aerial vehicle engine water-cooling heat abstractor, which comprises an outer shell, the both ends of shell are all integrated into one piece and are provided with the mount pad, the shell is inside to encircle and is provided with the cooling tube, set gradually inlet and liquid outlet on the outer wall of shell one side, fixed mounting has the cooler bin on the outer wall of shell one side, the top of cooler bin is provided with the water pump, the first pipe of suction end fixedly connected with of water pump, the second pipe of output end fixedly connected with of water pump, the bottom of cooler bin is provided with the third pipe that communicates in its inside, fixed welding has the fin on the opposite side outer wall of shell; the utility model discloses can effectually continuously dispel the heat to the unmanned aerial vehicle engine, guarantee that the engine uses for a long time, reduce the production of potential safety hazard.

Description

Unmanned aerial vehicle engine water-cooling heat abstractor

Technical Field

The utility model relates to a cubical switchboard intelligent panel correlation equipment technical field specifically is an unmanned aerial vehicle engine water-cooling heat abstractor.

Background

At present, along with the progress of the scientific and technical level, the unmanned aerial vehicle is applied in more and more fields, and the unmanned aerial vehicle is mainly applied in the fields of agriculture and scientific research and can play more and more important roles in the life of people. Wherein the unmanned aerial vehicle engine is unmanned aerial vehicle's primary equipment, and the result of use of unmanned aerial vehicle is directly influenced to the quality of engine.

The engine is unmanned aerial vehicle's heart, and unmanned aerial vehicle is at the during operation, and the temperature of engine can be very high, if do not have fine heat abstractor, will lead to the unable long-time use of unmanned aerial vehicle, and engine temperature is too high can lead to the cooperation clearance to reduce between the mutual motion parts, hinders the normal motion of parts, causes the moving part card to die even when serious, produces the potential safety hazard, therefore we need propose an unmanned aerial vehicle engine water-cooling heat abstractor.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide an unmanned aerial vehicle engine water-cooling heat abstractor through the installation screw with shell fixed mounting on the engine, at the during operation, coolant liquid input inlet in the water pump extraction cooler bin, when the cooling tube through shell inside, the heat that the engine produced is taken away to the coolant liquid in the cooling tube, returns the cooler bin through the liquid outlet and forms the circulation heat dissipation to solve the problem that proposes in the above-mentioned background art.

In order to achieve the above object, the utility model provides a following technical scheme:

the utility model provides an unmanned aerial vehicle engine water-cooling heat abstractor, includes the shell, the equal integrated into one piece in both ends of shell is provided with the mount pad, the shell inside is surrounded and is provided with the cooling tube, inlet and liquid outlet have set gradually on the outer wall of shell one side, fixed mounting has the cooler bin on the outer wall of shell one side, the top of cooler bin is provided with the water pump, the first pipe of suction end fixedly connected with of water pump, the output end fixedly connected with second pipe of water pump, the bottom of cooler bin is provided with the third pipe that feeds through in its inside, fixed welding has the fin on the opposite side outer wall of shell.

Preferably, the mounting base is provided with four groups, the mounting base is provided with mounting holes, and mounting screws are fixedly mounted in the mounting holes.

Preferably, the cooling pipe is arranged in a threaded surrounding manner, a pipe groove matched with the cooling pipe is formed in the shell, and the cooling pipe is fixedly arranged in the pipe groove.

Preferably, one end of the cooling pipe is communicated with the liquid inlet, the other end of the cooling pipe is communicated with the liquid outlet, a fixing frame is arranged at the top of the cooling box, and the water pump is fixedly installed at the upper end of the fixing frame.

Preferably, one end of the first conduit penetrates through the cooling tank and extends to the inside of the cooling tank, one end of the second conduit is communicated with the liquid inlet, and one end of the third conduit is communicated with the liquid outlet.

Preferably, the fin is provided with four groups at least, four groups the fin is the equidistance array and sets up in the shell outer wall, the ventilation breach has been seted up to the one end of fin, the ventilation breach is provided with five groups at least, the fin sets up to the heat dissipation copper sheet.

Compared with the prior art, the beneficial effects of the utility model are that:

1. when the cooling device is used, the shell is fixedly sleeved on the engine through the mounting screws, the cooling liquid in the cooling box is extracted by the water pump and is input into the liquid inlet, when the cooling liquid passes through the cooling pipe in the shell, the cooling liquid in the cooling pipe takes away the heat generated by the engine, and the cooling liquid returns to the cooling box through the liquid outlet to form circulating heat dissipation, so that the continuous heat dissipation can be effectively carried out on the engine of the unmanned aerial vehicle, the long-time use of the engine is ensured, and the generation of potential safety hazards is reduced;

2. the multiple groups of heat dissipation copper sheets are arranged on one side wall of the shell in an equidistant array mode, so that auxiliary heat dissipation can be effectively carried out on the device, and in addition, the multiple groups of ventilation notches are formed in one end of each heat dissipation copper sheet, so that the cooling effect of the device can be further improved; the mounting mode that four groups of mounting seats and mounting holes are arranged at two ends of the shell enables the device to be simple in structure and convenient to mount and dismount.

Drawings

Fig. 1 is a schematic structural view of the present invention;

FIG. 2 is a schematic structural view of the pipe chase of the present invention;

FIG. 3 is a schematic structural view of the cooling tube of the present invention;

fig. 4 is a schematic structural view of the mounting base of the present invention;

fig. 5 is a schematic structural diagram of the heat sink of the present invention.

In the figure: 1. a housing; 2. a mounting seat; 3. a cooling tube; 4. a liquid inlet; 5. a liquid outlet; 6. a cooling tank; 7. a water pump; 8. a first conduit; 9. a second conduit; 10. a third conduit; 11. a heat sink; 12. mounting holes; 13. mounting screws; 14. a pipe groove; 15. a fixed mount; 16. a vent gap.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.

Referring to fig. 1-5, the present invention provides a technical solution:

an unmanned aerial vehicle engine water-cooling heat dissipation device comprises a shell 1, wherein both ends of the shell 1 are integrally provided with mounting seats 2, a cooling pipe 3 is arranged in the shell 1 in a surrounding manner, a liquid inlet 4 and a liquid outlet 5 are sequentially arranged on the outer wall of one side of the shell 1, a cooling box 6 is fixedly arranged on the outer wall of one side of the shell 1, a water pump 7 is arranged at the top of the cooling box 6, a suction end of the water pump 7 is fixedly connected with a first guide pipe 8, an output end of the water pump 7 is fixedly connected with a second guide pipe 9, a third guide pipe 10 communicated with the interior of the cooling box 6 is arranged at the bottom of the cooling box 6, the cooling pipe 3 is arranged in a threaded surrounding manner, a pipe groove 14 matched with the cooling pipe 3 is arranged in the shell 1, the cooling pipe 3 is fixedly arranged in the pipe groove 14, one end of the cooling pipe 3 is communicated with, the water pump 7 is fixedly arranged at the upper end of the fixed frame 15, one end of the first conduit 8 penetrates through the cooling box 6 and extends into the cooling box 6, one end of the second conduit 9 is communicated with the liquid inlet 4, and one end of the third conduit 10 is communicated with the liquid outlet 5; fix the cover joint on the engine through installation screw 13 with shell 1, coolant liquid input inlet 4 in the water pump 7 extraction cooler bin 6, when the cooling tube 3 through 1 inside of shell, the heat that the engine produced is taken away to the coolant liquid in the cooling tube 3, returns cooler bin 6 formation circulation heat dissipation through liquid outlet 5, can effectually last the heat dissipation to the unmanned aerial vehicle engine, guarantees that the engine uses for a long time, reduces the production of potential safety hazard.

The mounting base 2 is provided with four groups, a mounting hole 12 is formed in the mounting base 2, a mounting screw 13 is fixedly mounted in the mounting hole 12, radiating fins 11 are fixedly welded on the outer wall of the other side of the shell 1, at least four groups of radiating fins 11 are arranged, the four groups of radiating fins 11 are arranged on the outer wall of the shell 1 in an equidistant array mode, one end of each radiating fin 11 is provided with a ventilation notch 16, the ventilation notches 16 are at least five groups, and the radiating fins 11 are arranged into radiating copper sheets; the multiple groups of heat dissipation copper sheets are arranged on one side wall of the shell 1 in an equidistant array mode, auxiliary heat dissipation can be effectively carried out on the device, and in addition, the multiple groups of ventilation notches 16 are formed in one end of each heat dissipation copper sheet, so that the cooling effect of the device can be further improved; the mounting mode that four groups of mounting seats 2 and mounting holes 12 are arranged at two ends of the shell 1 enables the device to be simple in structure and convenient to mount and dismount.

The working principle is as follows: when the cooling device is used, the shell 1 is fixedly sleeved on an engine through the mounting screws 13, the water pump 7 extracts cooling liquid in the cooling tank 6 and inputs the cooling liquid into the liquid inlet 4, when the cooling liquid passes through the cooling pipe 3 in the shell 1, the cooling liquid in the cooling pipe 3 takes away heat generated by the engine and returns to the cooling tank 6 through the liquid outlet 5 to form circulating heat dissipation, so that the continuous heat dissipation can be effectively carried out on the engine of the unmanned aerial vehicle, the long-time use of the engine is ensured, and the generation of potential safety hazards is reduced; the multiple groups of heat dissipation copper sheets are arranged on one side wall of the shell 1 in an equidistant array mode, auxiliary heat dissipation can be effectively carried out on the device, and in addition, the multiple groups of ventilation notches 16 are formed in one end of each heat dissipation copper sheet, so that the cooling effect of the device can be further improved; the mounting mode that four groups of mounting seats 2 and mounting holes 12 are arranged at two ends of the shell 1 enables the device to be simple in structure and convenient to mount and dismount.

Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.

Claims

1. The utility model provides an unmanned aerial vehicle engine water-cooling heat abstractor, includes shell (1), its characterized in that: the equal integrated into one piece in both ends of shell (1) is provided with mount pad (2), shell (1) is inside to be encircleed and is provided with cooling tube (3), inlet (4) and liquid outlet (5) have set gradually on the outer wall of shell (1) one side, fixed mounting has cooler bin (6) on the outer wall of shell (1) one side, the top of cooler bin (6) is provided with water pump (7), the first pipe (8) of suction end fixedly connected with of water pump (7), the output fixedly connected with second pipe (9) of water pump (7), the bottom of cooler bin (6) is provided with the third pipe (10) that feeds through in its inside, fixed welding has fin (11) on the opposite side outer wall of shell (1).

2. The unmanned aerial vehicle engine water-cooling heat dissipation device of claim 1, wherein: the mounting seat (2) is provided with four groups, a mounting hole (12) is formed in the mounting seat (2), and a mounting screw (13) is fixedly mounted in the mounting hole (12).

3. The unmanned aerial vehicle engine water-cooling heat dissipation device of claim 1, wherein: the cooling pipe (3) is arranged in a threaded surrounding mode, a pipe groove (14) matched with the cooling pipe (3) is formed in the shell (1), and the cooling pipe (3) is fixedly installed inside the pipe groove (14).

4. The unmanned aerial vehicle engine water-cooling heat dissipation device of claim 1, wherein: one end of the cooling pipe (3) is communicated with the liquid inlet (4), the other end of the cooling pipe (3) is communicated with the liquid outlet (5), a fixing frame (15) is arranged at the top of the cooling box (6), and the water pump (7) is fixedly arranged at the upper end of the fixing frame (15).

5. The unmanned aerial vehicle engine water-cooling heat dissipation device of claim 1, wherein: one end of the first conduit (8) penetrates through the cooling box (6) and extends to the inside of the cooling box (6), one end of the second conduit (9) is communicated with the liquid inlet (4), and one end of the third conduit (10) is communicated with the liquid outlet (5).

6. The unmanned aerial vehicle engine water-cooling heat dissipation device of claim 1, wherein: the heat radiating fins (11) are at least provided with four groups, the four groups of heat radiating fins (11) are arranged on the outer wall of the shell (1) in an equidistant array mode, the ventilation notch (16) is formed in one end of each heat radiating fin (11), the ventilation notch (16) is at least provided with five groups, and the heat radiating fins (11) are arranged into heat radiating copper sheets.