Highly integrated airplane liquid cooling system

Abstract

The utility model discloses a highly integrated airplane liquid cooling system which comprises a self-pressurization liquid storage tank, an outlet of the self-pressurization liquid storage tank is connected with an inlet of a flow divider through a guide pipe, an outlet of the flow divider is connected with an inlet of an airplane antenna through a flow dividing guide pipe, and an outlet of the airplane antenna is connected with an inlet of a liquid collector through a guide pipe. An outlet of the liquid collector is connected with an inlet of the tail liquid cooling radiator through a guide pipe, an outlet of the tail liquid cooling radiator is connected with an inlet of the self-pressurization liquid storage tank through a guide pipe, airflow generated when an airplane flies penetrates through the tail liquid cooling radiator to be cooled, and gas enters the radiator shell through a gas inlet in the flying process of the airplane and enters the radiator shell through a gas outlet. According to the highly-integrated airplane liquid cooling system, the structure is simple, operation is easy and convenient, device control is more convenient, cooling can be achieved through the airflow when an airplane flies, special cooling energy is not needed, and a large amount of energy can be saved.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft liquid cooling, in particular to a highly integrated aircraft liquid cooling system. Background Technique

[0002] The liquid cooling system includes a tail liquid cooling device, an oil storage tank, a booster pump, etc. Among them, the tail liquid cooling device is installed at the tail part of a special aircraft, and within a specific temperature environment range, it provides the liquid supply flow rate and temperature required for heat dissipation for the tail antenna. However, the existing liquid cooling device has a complex structure and requires additional energy for cooling during cooling. Therefore, not only is the cooling effect poor, but also a large amount of energy is consumed. Content of the Utility Model

[0003] The technical problem to be solved by the utility model is to overcome the existing defects, and provide a highly integrated aircraft liquid cooling system, which has a simple structure and is easy to operate. It not only makes the control of the device more convenient, but also can be cooled by the airflow generated during aircraft flight, without the need for special cooling energy, which can save a large amount of energy and can effectively solve the problems in the background technique.

[0004] To achieve the above purpose, the utility model provides the following technical solution: a highly integrated aircraft liquid cooling system, including a self-pressurizing liquid storage tank. The outlet of the self-pressurizing liquid storage tank is connected to the inlet of a diverter through a conduit. The outlet of the diverter is connected to the inlet of an aircraft antenna through a diversion conduit. The outlet of the aircraft antenna is connected to the inlet of a liquid collector through a conduit. The outlet of the liquid collector is connected to the inlet of a tail liquid cooling radiator through a conduit. The outlet of the tail liquid cooling radiator is connected to the inlet of the self-pressurizing liquid storage tank through a conduit. The tail liquid cooling radiator is cooled by the airflow generated during aircraft flight.

[0005] Further, the self-pressurizing liquid storage tank includes an oil storage tank. A booster pump chamber is provided on the right end cover of the oil storage tank. A booster pump is installed inside the booster pump chamber. And a piston for compressing the oil inside it is provided inside the oil storage tank. And a pulling component for driving the piston to move is provided in the middle of the right end cover of the oil storage tank. An inlet and an outlet are provided on the right end cover of the oil storage tank. And a filter is provided on the outlet. And the inlet of the oil storage tank is connected to the outlet of the tail liquid cooling radiator through a conduit.

[0006] Further, the pulling component includes a pull rod for driving the piston to move. And a spring for pushing one end of the pull rod is provided on the oil storage tank. And a sealing piston is provided at one end of the pull rod located outside the oil storage tank. A sealing barrel is provided on one side of the oil storage tank. The sealing piston is slidably connected to the inside of the sealing barrel. The outside end of the pull rod located in the oil storage tank can be sealed by the sealing piston. And one end of the pull rod is pushed by the spring. The piston is driven to move by the pull rod. The oil cavity inside the oil storage tank is compressed by the piston, so as to self-pressurize the oil.

[0007] Furthermore, the tail liquid-cooled radiator includes a radiator housing. An S-shaped heat exchange tube is arranged inside the radiator housing, and oil can pass through the inside of the heat exchange tube. Conical air inlets and air outlets are respectively arranged on the front and rear sides of the radiator housing. During the cooling process, the tail liquid-cooled radiator is fixed on the aircraft. During the flight of the aircraft, air enters the inside of the radiator housing through the air inlet, and the air flow can cool the liquid inside the heat exchange tube to conduct cooling in this way.

[0008] Compared with the prior art, the beneficial effects of the present utility model are as follows: The outer end of the pull rod located outside the oil storage tank can be sealed by the sealing piston, and one end of the pull rod is pushed by the spring. The piston is pulled to move by the pull rod, and the oil cavity inside the oil storage tank is compressed by the piston to perform self-pressurization on the oil. During the cooling process, the tail liquid-cooled radiator is fixed on the aircraft. During the flight of the aircraft, air enters the inside of the radiator housing through the air inlet, and the air flow can cool the liquid inside the heat exchange tube to conduct cooling in this way. This highly integrated aircraft liquid-cooling system has a simple structure and is easy to operate. It not only makes the control of the device more convenient, but also can be cooled by the air flow during the flight of the aircraft, eliminating the need for a dedicated cooling energy source and saving a large amount of energy. BRIEF DESCRIPTION OF THE DRAWINGS

[0009] Figure 1 is a schematic structural diagram of the present utility model;

[0010] Figure 2 is a schematic structural diagram of the self-pressurizing liquid storage tank of the present utility model;

[0011] Figure 3 is a schematic cross-sectional structural diagram of the self-pressurizing liquid storage tank of the present utility model;

[0012] Figure 4 is a schematic cross-sectional structural diagram of the tail liquid-cooled radiator of the present utility model;

[0013] Figure 5 is a schematic internal structural diagram of the self-pressurizing liquid storage tank of the present utility model.

[0014] In the figure: 1 self-pressurizing liquid storage tank, 11 oil storage tank, 12 booster pump, 13 piston, 14 pulling assembly, 141 pull rod, 142 spring, 143 sealing piston, 144 sealing barrel, 15 filter, 2 diverter, 3 aircraft antenna, 4 liquid collector, 5 tail liquid-cooled radiator, 51 radiator housing, 52 heat exchange tube. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0015] The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0016] Please refer to Figures 1-5 , the present invention provides a technical solution: a highly integrated aircraft liquid cooling system, including a self-pressurizing liquid storage tank 1. The outlet of the self-pressurizing liquid storage tank 1 is connected to the inlet of a shunt 2 through a conduit. The outlet of the shunt 2 is connected to the inlet of an aircraft antenna 3 through a shunt conduit. The outlet of the aircraft antenna 3 is connected to the inlet of a liquid collector 4 through a conduit. The outlet of the liquid collector 4 is connected to the inlet of a tail liquid cooling radiator 5 through a conduit. The outlet of the tail liquid cooling radiator 5 is connected to the inlet of the self-pressurizing liquid storage tank 1 through a conduit. The tail liquid cooling radiator 5 is cooled by the airflow generated during aircraft flight. The self-pressurizing liquid storage tank 1 includes an oil storage tank 11. A pressurization pump chamber is provided on the right end cover of the oil storage tank 11. A pressurization pump 12 is installed inside the pressurization pump chamber. And a piston 13 for compressing the oil inside it is provided inside the oil storage tank 11. And a pulling assembly 14 for driving the piston 13 to move is provided in the middle of the right end cover of the oil storage tank 11. An inlet and an outlet are provided on the right end cover of the oil storage tank 11. And a filter 15 is provided on the outlet. And the inlet of the oil storage tank 11 is connected to the outlet of the tail liquid cooling radiator 5 through a conduit. The pulling assembly 14 includes a pull rod 141 for pulling the piston 13 to move. And a spring 142 for pushing one end of the pull rod 141 is provided on the oil storage tank 11. And a sealing piston 143 is provided at one end of the pull rod 141 located outside the oil storage tank 11. A sealing barrel 144 is provided on one side of the oil storage tank 11. The sealing piston 143 is slidably connected to the inside of the sealing barrel 144. The outside end of the pull rod 141 located in the oil storage tank 11 can be sealed by the sealing piston 143. And one end of the pull rod 141 is pushed by the spring 142. The piston 13 is pulled to move by the pull rod 141. The oil chamber inside the oil storage tank 11 is compressed by the piston 13, so as to self-pressurize the oil. The tail liquid cooling radiator 5 includes a radiator housing 51. An S-shaped heat exchange tube 52 is provided inside the radiator housing 51. And oil can pass through the inside of the heat exchange tube 52. And a conical air inlet and an air outlet are respectively provided on the front and back sides of the radiator housing 51. During the cooling process, the tail liquid cooling radiator 5 is fixed on the aircraft. During the flight of the aircraft, gas enters the inside of the radiator housing 51 through the air inlet. The airflow can cool the liquid inside the heat exchange tube 52, so as to carry out cooling. This highly integrated aircraft liquid cooling system has a simple structure and is easy to operate. It not only makes the control of the device more convenient, but also can be cooled by the airflow during aircraft flight, without the need for a dedicated cooling energy source, and can save a large amount of energy.

[0017] In use: The booster pump 12 can extract and boost the oil inside the oil storage tank 11. The sealing piston 143 can seal one end of the pull rod 141 located outside the oil storage tank 11. And one end of the pull rod 141 is pushed by the spring 142. The pull rod 141 pulls the piston 13 to move, and the piston 13 compresses the oil cavity inside the oil storage tank 11 to self-boost the oil, further boost the oil, so that the oil can be pumped into the aircraft antenna 3 for cooling and flow measurement. During the cooling process, the tail liquid-cooled radiator 5 is fixed on the aircraft. When the aircraft is flying, the gas enters the inside of the radiator housing 51 through the air inlet, and the air flow can cool the liquid inside the heat exchange tube 52 for cooling.

[0018] Although the embodiments of the present invention have been shown and described, those of ordinary skill in the art can understand that various changes, modifications, substitutions, and variations can be made to these embodiments without departing from the principle and spirit of the present invention.

Claims

1. A highly integrated aircraft liquid cooling system, comprising a self-pressurizing liquid storage tank (1), characterized in that: The outlet of the self-pressurizing liquid storage tank (1) is connected to the inlet of the diverter (2) through a conduit, the outlet of the diverter (2) is connected to the inlet of the aircraft antenna (3) through a diverter conduit, the outlet of the aircraft antenna (3) is connected to the inlet of the liquid collector (4) through a conduit, the outlet of the liquid collector (4) is connected to the inlet of the tail liquid cooling radiator (5) through a conduit, the outlet of the tail liquid cooling radiator (5) is connected to the inlet of the self-pressurizing liquid storage tank (1) through a conduit, and the tail liquid cooling radiator (5) is cooled by the airflow generated when the aircraft is flying.

2. A highly integrated aircraft liquid cooling system according to claim 1, characterized in that: The self-pressurizing liquid storage tank (1) comprises an oil storage tank (11), a booster pump chamber is arranged on the right end cover of the oil storage tank (11), a booster pump (12) is installed inside the booster pump chamber, a piston (13) is arranged inside the oil storage tank (11) for compressing the oil inside the oil storage tank (11), a pulling assembly (14) is arranged in the middle of the right end cover of the oil storage tank (11) for driving the piston (13) to move, a liquid inlet and a liquid outlet are arranged on the right end cover of the oil storage tank (11), a filter (15) is arranged on the liquid outlet, and the liquid inlet of the oil storage tank (11) is connected to the outlet of the tail liquid cooling radiator (5) through a conduit.

3. A highly integrated aircraft liquid cooling system according to claim 2, characterized in that: The pulling assembly (14) comprises a pulling rod (141) for pulling the piston (13) to move, and the oil storage tank (11) is provided with a spring (142) for pushing one end of the pulling rod (141), and a sealing piston (143) is provided at one end of the pulling rod (141) located outside the oil storage tank (11), and a sealing barrel (144) is provided on one side of the oil storage tank (11), and the sealing piston (143) is slidably connected to the inside of the sealing barrel (144).

4. The highly integrated aircraft liquid cooling system according to claim 1, characterized in that: The tail liquid cooling radiator (5) comprises a radiator shell (51), an S-shaped heat exchange tube (52) is arranged inside the radiator shell (51), and oil can pass through the inside of the heat exchange tube (52), and a conical air inlet and an air outlet are respectively arranged on the front and rear sides of the radiator shell (51).

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