CN218332472U

CN218332472U - Hood with automatic exhaust heat dissipation mechanism

Info

Publication number: CN218332472U
Application number: CN202222461410.9U
Authority: CN
Inventors: 周斌; 唐万任; 周涛
Original assignee: Dongguan Yongxieli Intelligent Technology Co ltd
Current assignee: Dongguan Yongxieli Intelligent Technology Co ltd
Priority date: 2022-09-17
Filing date: 2022-09-17
Publication date: 2023-01-17
Anticipated expiration: 2032-09-17

Abstract

The utility model discloses a hood with an automatic exhaust heat dissipation mechanism, which comprises a hood main body, wherein a cold water tank is arranged inside the hood main body, a circulating water pump is arranged inside the cold water tank, a circulating water pipe is arranged on the circulating water pump, and the circulating water pipe penetrates through the cold water tank and surrounds the inner wall of the hood main body; the utility model discloses aircraft bonnet with automatic exhaust heat dissipation mechanism, more louvres and bleeder vent have in the aircraft bonnet main part, discharge the heat through louvre and bleeder vent in the aircraft bonnet main part, and behind the switch on, circulating water pump begins work, it flows in the circulating water pipe fast to enable the inside liquid of cold water storage cistern, utilize heat-conduction and water heat absorption principle to absorb most heat, can avoid CPU and other electronic device, the circuit board burns out, avoid taking place the incident, the radiating effect is better, the radiating efficiency is higher, can the water-cooling heat dissipation with through the louvre, the bleeder vent dispels the heat.

Description

Hood with automatic exhaust heat dissipation mechanism

Technical Field

The utility model relates to an aircraft bonnet field, specific is aircraft bonnet with self-bleeding heat dissipation mechanism.

Background

The CPU and other parts of the computer generate heat in the high-speed running process, and the heat dissipation is a heat transfer process, so that the heat generated by the CPU is brought to other media, and the temperature of the CPU is controlled within a stable range. According to the environment of our life, the heat of CPU will be finally dispersed to the air, this process is exactly the computer heat dissipation, use the fan to dispel the heat to the CPU of computer at present usually, and discharge the heat through the louvre on the aircraft bonnet, but current aircraft bonnet because the louvre is small in quantity, and the heat dissipation ability is poor, the heat that produces in the computer working process only a small part is discharged from the louvre, most heat can't be discharged, lead to CPU and other electronic device, circuit board to burn out easily, the incident takes place easily, only dispel the heat through the louvre, the heat dissipation is too single, the radiating efficiency is too low.

SUMMERY OF THE UTILITY MODEL

To the weak point that exists among the above-mentioned technique, the utility model provides a aircraft bonnet with self-bleeding heat dissipation mechanism.

In order to achieve the above purpose, the utility model adopts the following technical scheme: aircraft bonnet with automatic heat dissipation mechanism exhausts, including the aircraft bonnet main part, the inside of aircraft bonnet main part is provided with the cold water storage cistern, the inside circulating water pump that is provided with of cold water storage cistern, the last circulating water pipe that installs of circulating water pump, circulating water pipe runs through the cold water storage cistern encircles on aircraft bonnet main part inner wall.

As further elaboration, be provided with a plurality of holding rings on the aircraft bonnet main part inner wall, the holding ring with detachable the connection between the circulating pipe.

As a further explanation, the opposite sides of the hood main body are both provided with heat dissipation panels, and a plurality of heat dissipation holes for heat dissipation are formed in the heat dissipation panels.

As a further elaboration, a plurality of interfaces are arranged in front of the hood main body and are uniformly arranged at intervals.

As a further explanation, the bottom of the hood main body is provided with four supporting legs, and the four supporting legs are all located on the same horizontal plane.

As a further explanation, an interface board and a plurality of air holes are also arranged on the back of the hood main body.

To sum up, the utility model discloses following beneficial effect has: the utility model discloses aircraft bonnet with automatic exhaust heat dissipation mechanism, more louvres and bleeder vent have in the aircraft bonnet main part, discharge the heat through louvre and bleeder vent in the aircraft bonnet main part, and behind the switch on, circulating water pump begins work, it flows in the circulating water pipe fast to enable the inside liquid of cold water storage cistern, utilize heat-conduction and water heat absorption principle to absorb most heat, can avoid CPU and other electronic device, the circuit board burns out, avoid taking place the incident, the radiating effect is better, the radiating efficiency is higher, can the water-cooling heat dissipation with through the louvre, the bleeder vent heat dissipation, can dispel the heat automatically.

Drawings

Fig. 1 is a perspective view of a hood with an automatic exhaust heat dissipation mechanism according to the present invention;

fig. 2 is a rear view of the hood with an automatic exhaust heat dissipation mechanism of the present invention;

fig. 3 is a schematic diagram of the internal structure of the hood with the automatic exhaust heat dissipation mechanism according to the present invention.

Reference numbers in the figures:

figure 1-bonnet body; 2-an interface; 3, switching; 4-a heat dissipation panel; 5-heat dissipation holes; 6-supporting feet; 7-air holes; 8-an interface board; 9-a circulating water pipe; 10-a positioning ring; 11-a cold water tank; 12-circulating water pump.

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.

As shown in fig. 1-3, the hood with an automatic exhaust and heat dissipation mechanism comprises a hood body 1, a cold water tank 11 is arranged inside the hood body 1, a circulating water pump 12 is arranged inside the cold water tank 11, a circulating water pipe 9 is installed on the circulating water pump 12, the circulating water pipe 9 penetrates through the cold water tank 11 and surrounds the inner wall of the hood body 1, one end of the circulating water pipe 9 is connected with the circulating water pump 12, the other end of the circulating water pipe 9 extends into the cold water tank 11, a plurality of positioning rings 10 are arranged on the inner wall of the hood body 1, the positioning rings 10 are detachably connected with the circulating water pipe 9, the circulating water pipe 9 can be stably attached to the inner wall of the hood body 1 by arranging the positioning rings 10, the circulating water pipe 9 is prevented from being separated, and heat dissipation panels 4 are arranged on two opposite sides of the hood body 1, the heat dissipation panel 4 is provided with a plurality of heat dissipation holes 5 for dissipating heat, the heat dissipation capacity of the hood main body 1 is improved by arranging more heat dissipation holes 5, the air circulation can be accelerated, the front of the hood main body 1 is provided with a plurality of interfaces 2, the interfaces 2 are uniformly arranged at intervals, the bottom of the hood main body 1 is provided with four supporting feet 6, the four supporting feet 6 are all positioned on the same horizontal plane, the back of the hood main body 1 is also provided with an interface board 8 and a plurality of air vents 7, the interface board 8 also comprises a power supply interface, a PS/2 interface, a serial interface, a parallel interface, an RJ-45 (network) interface, a USB interface, an audio interface and an IEEE1394 interface, in addition, the hood main body 1 is also internally provided with a computer hard disk system such as a power supply, a CPU, a memory, a hard disk, a CD-ROM and other input and output controllers, still be provided with switch 3 on the aircraft bonnet main part 1, and circulating water pump 12 passes through wire and switch 3, the power is connected, circulating water pump 12 can start through switch 3, still including water inlet and delivery port on the cold water storage cistern 11, can be through adding the coolant liquid to cold water storage cistern 11 toward the water inlet, cooling panel 4's inboard still is provided with radiator fan, and radiator fan is provided with two, two radiator fan are all through electric connection between switch 3 and the power, open the back with switch 3, can start circulating water pump 12 and radiator fan simultaneously, circulating water pump 12 extracts the coolant liquid and circulates in circulating pipe 9 and flows, dispel the heat with higher speed, and radiator fan discharges the heat of inside production from louvre 5.

The working principle is as follows: have more louvres 5 and bleeder vent 7 on the aircraft bonnet main part 1, louvre 5 and bleeder vent 7 through on the aircraft bonnet main part 1 are discharged the heat, and behind the switch on, circulating water pump 12 begins work, it flows in circulating water pipe 9 fast to enable the inside liquid of cold water storage cistern 11, utilize heat-conduction and water heat absorption principle to absorb most heat, can avoid CPU and other electronic device, the circuit board burns out, avoid taking place the incident, the radiating effect is better, the radiating efficiency is higher, can water-cooling heat dissipation and through the louvre, the bleeder vent heat dissipation, can dispel the heat automatically.

It is obvious to a person skilled in the art that the invention is not restricted to details of the above-described exemplary embodiments, but that it can be implemented in other specific forms without departing from the spirit or essential characteristics of the invention. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.

Furthermore, it should be understood that although the present specification describes embodiments, not every embodiment includes only a single embodiment, and such description is for clarity purposes only, and it is to be understood that all embodiments may be combined as appropriate by one of ordinary skill in the art to form other embodiments as will be apparent to those of skill in the art from the description herein.

Claims

1. The aircraft bonnet with automatic exhaust heat dissipation mechanism, its characterized in that: the water cooling device comprises a hood main body, wherein a cold water tank is arranged in the hood main body, a circulating water pump is arranged in the cold water tank, a circulating water pipe is installed on the circulating water pump, and the circulating water pipe penetrates through the cold water tank and surrounds the inner wall of the hood main body.

2. The hood with automatic exhaust heat dissipation mechanism according to claim 1, wherein: be provided with a plurality of holding rings on the aircraft bonnet main part inner wall, the holding ring with detachable the connection between the circulating pipe.

3. The hood with automatic exhaust heat dissipation mechanism according to claim 1, wherein: the relative both sides of aircraft bonnet main part all are provided with heat dissipation panel, the last a plurality of louvres that are used for the heat dissipation of having seted up of heat dissipation panel.

4. The hood with automatic exhaust heat dissipation mechanism according to claim 1, wherein: the front of the hood main body is provided with a plurality of connectors which are uniformly arranged at intervals.

5. The hood with automatic exhaust heat dissipation mechanism according to claim 1, wherein: the bottom of the hood main body is provided with four supporting legs, and the four supporting legs are all located on the same horizontal plane.

6. The hood with automatic exhaust heat dissipation mechanism according to claim 1, wherein: an interface board and a plurality of air holes are also arranged on the back of the hood main body.