CN216887195U

CN216887195U - Install rapid cooling device on high-speed aircraft top layer

Info

Publication number: CN216887195U
Application number: CN202220596942.0U
Authority: CN
Inventors: 姚舜祯; 刘海龙
Original assignee: Beijing Axicomb New Material Co ltd
Current assignee: Beijing Axicomb New Material Co ltd
Priority date: 2022-03-18
Filing date: 2022-03-18
Publication date: 2022-07-05
Anticipated expiration: 2032-03-18

Abstract

The utility model relates to a rapid cooling device arranged on the surface layer of a high-speed aircraft, which comprises a Venturi pump arranged on the surface layer of the high-speed aircraft, wherein one end of the Venturi pump is a large opening, the other end of the Venturi pump is a small opening, and the large opening end of the Venturi pump faces the tip end of the high-speed aircraft; a suction pipe is arranged in the middle of the Venturi pump and is connected with a solid water storage; and a one-way valve is arranged between the suction pipe and the solid water storage device. According to the utility model, the Venturi pump is arranged on the surface layer of the high-speed aircraft, so that the technical problems of reducing weight of the high-speed aircraft, saving cabin space of the high-speed aircraft, cooling the outer surface of the high-speed aircraft, preventing ablation of the outer surface of the high-speed aircraft and the like are effectively solved.

Description

Install rapid cooling device on high-speed aircraft top layer

Technical Field

The utility model relates to cooling of a high-speed aircraft, in particular to a rapid cooling device arranged on the surface layer of the high-speed aircraft.

Background

The prior hypersonic air defense missile at home and abroad has the flight speed Mach number reaching or exceeding 20, and the missile flies in the atmosphere at hypersonic speed (Ma is more than 5), and meets extremely serious pneumatic heating environment. Various structural heat-proof technical measures are provided for solving the problem of thermal barrier, and the technical measures are suitable for various pneumatic heating environments.

In order to cool the outer surface of a high-speed aircraft flying at high speed in the atmosphere, the outer surface ablation material and the device of the high-speed aircraft are explored. The outer surface of the high-speed aircraft is cooled by a solid water method, so that the problem of high heat cooling caused by the friction between the outer surface of the high-speed aircraft and the atmosphere in the atmosphere is solved. The utilization of solid water for cooling the outer surface of a high-speed aircraft has been reported in China and has a great prospect in the field of cooling the outer surface of the high-speed aircraft. Aiming at the provided condition requirements of the appearance, the aerodynamic heat and the like of the aircraft, a method for rapidly transmitting and dissipating the heat on the surface of the structural shell is researched and realized by adopting a solid water passive cooling technology, the scheme design of a fluid and thermal control system is carried out by combining constraint conditions such as the structural size, the structural quality and the like, the simulation analysis is carried out on the fluid and the heat of the design scheme through CFD simulation software, the fluid distribution is optimized, the thermal control scheme is optimized, the thermal resistance and the thermal resistance chain are reduced, and the thermal protection effect that the principle structure sample piece meets the project requirements is finally realized. However, the inherent techniques generally require water tanks, liquid supply pumps, battery packs and the like, which limit further applications in cooling high-speed aircrafts.

The heat protection technology of the current aircraft outer shell is continuously improved, but the heat protection problem of the aircraft flying at ultrahigh speed in the atmosphere for a long time still appears to be weak. As a novel thermal control scheme, the phase-change energy storage thermal control technology has high energy storage density, can absorb the working heat of the shell through the phase-change process of the internal phase-change material, can deal with larger heat flux density, has relatively simple structure and small volume ratio, and does not need additional mechanical or electronic devices. At present, the phase change energy storage thermal control technology has a small amount of application in the chip thermal control field of aviation, aerospace and the like, but the application is rarely reported in the aspect of the thermal protection technology of an aircraft shell, so that the utility model develops a solid water active cooling technology and researches the temperature control mechanism and feasibility of the solid water active cooling technology in the aspect of the thermal protection of the aircraft shell.

SUMMERY OF THE UTILITY MODEL

According to the utility model, the Venturi pump is arranged on the surface layer of the high-speed aircraft, and active cooling is carried out by using solid water, so that the technical problems of reducing weight of the high-speed aircraft, saving cabin space of the high-speed aircraft, cooling the outer surface of the high-speed aircraft, preventing ablation of the outer surface of the high-speed aircraft and the like are effectively solved.

The rapid cooling device is installed on the surface layer of the high-speed aircraft and comprises a Venturi pump installed on the surface layer of the high-speed aircraft; one end of the Venturi pump is a large opening, the other end of the Venturi pump is a small opening, and the large opening end of the Venturi pump faces the tip end of the high-speed aircraft; a suction pipe is arranged in the middle of the Venturi pump and is connected with a solid water storage; and a one-way valve is arranged between the suction pipe and the solid water storage.

According to the rapid cooling device provided by the utility model, the adopted Venturi pump can spray water to the outer surface of the high-speed aircraft to rapidly cool the outer surface of the high-speed aircraft. The structure is simple, the reliability is high, more loads can be loaded by saving the cabin space of the high-speed aircraft, and the weight of the high-speed aircraft is reduced without carrying a motor and a battery aiming at the cooling device on the outer surface of the high-speed aircraft; the problem that the chip is corroded due to electrolyte leakage is not considered; in addition, in the cooling process, the throwing ratio water column is more uniform, and the problem of nonuniform cooling of the outer surface of the high-speed aircraft cooled by the solid water column is solved.

In addition, the traditional ablation materials such as phenolic aldehyde and epoxy resin pollute the environment in the ablation process, and the rapid cooling device utilizes solid water to cool the high-speed aircraft, thereby effectively solving the problem of environmental pollution.

Wherein the venturi pump is mounted in a vertical direction in line with the air flow.

Wherein, the suction pipe is arranged at the middle upper part of the vertical direction of the Venturi pump.

Wherein the small opening end of the Venturi pump is a downward-hanging tail nozzle.

In the process of flying the missile in the air, the vacuum pressure applied to the one-way valve is increased along with the increase of the speed of the missile due to the difference of the upper caliber and the lower caliber of the pump outside the skin, and when the pressure is increased to a certain degree, the water pressure jacks the one-way valve, so that the temperature of the skin of the missile is reduced. And when the missile is not launched, the one-way valve can play a role in preventing the solid water storage from leaking.

Wherein, the number of the Venturi pumps is a plurality of, and the Venturi pumps are uniformly arranged on the surface layer of the high-speed aircraft.

In practical application, the number of the express cooling devices can be adjusted according to the condition of the high-speed aircraft.

Wherein the high-speed aircraft includes but is not limited to an early warning machine or a precision guidance remote air-ground missile.

Drawings

FIG. 1 is a schematic structural view of a high-speed aircraft equipped with a rapid cooling device;

FIG. 2 is a schematic diagram of a venturi pump;

in the figure: 1. a high speed aircraft; 2. a venturi pump; 3. the large opening end of the Venturi pump; 4. a straw; 5. a one-way valve; 6. small opening end of the venturi pump.

Detailed Description

The following examples are intended to illustrate the utility model but are not intended to limit the scope of the utility model.

Examples

The embodiment provides a rapid cooling device installed on the surface layer of a high-speed aircraft, such as the structural schematic diagram of the high-speed aircraft installed with the rapid cooling device shown in fig. 1.

The express cooling device comprises a Venturi pump 2 arranged on the surface layer of a high-speed aircraft 1, wherein one end of the Venturi pump 2 is a large opening (a large opening end 3 of the Venturi pump), and the other end of the Venturi pump 2 is a small opening (a small opening end 6 of the Venturi pump); the large opening end 3 of the Venturi pump faces the tip of the high-speed aircraft; the Venturi pump is of a vertical strip structure, and the vertical direction of the Venturi pump is consistent with that of the high-speed aircraft. The tip of the high-speed aircraft is forward.

Wherein, a suction pipe 4 is arranged in the middle of the Venturi pump 2 and is connected with the solid water storage; a check valve 5 is arranged between the suction pipe 4 and the solid water storage, as shown in fig. 2.

Wherein the suction pipe 4 is arranged at the middle upper part of the Venturi pump 2 in the vertical direction.

Wherein the venturi pump 2 is installed in a vertical direction in line with the air flow.

Wherein, the number of the Venturi pumps 2 is a plurality, and the Venturi pumps are uniformly arranged on the surface layer of the high-speed aircraft.

The small mouth end of the venturi pump 2 is a downward-hanging jet nozzle.

In practical application, the outer surface of the high-speed aircraft 1 can have air flow on the surface during the flight, and the air can flow from one end of the outer tip part of the high-speed aircraft 1 to the body part of the rear high-speed aircraft. The outer surface of the high-speed aircraft 1 is decorated with the Venturi pump 2, and air flows from the end with a large opening of the Venturi pump (the large opening end 3 of the Venturi pump) to the end with a small opening (the small opening end 6 of the Venturi pump). The air then forms a pressure difference δ P-1-P2 across the venturi pump 2. Water is sucked up from a solid water storage of the high-speed aircraft due to the air pressure difference; wherein, a one-way valve 5 is added in the connected suction pipe 4 to prevent water from flowing back to the solid water storage in the cabin of the high-speed aircraft, and simultaneously the flow rate of the solid water in the suction pipe 4 can be controlled; water in solid form is ejected behind the venturi pump 2 to cool the outer surface of the high speed aircraft 1. The water sprayed on the outer surface of the high-speed aircraft is more uniformly sprayed on the outer surface by forming a drooping tail nozzle at the rear part of the Venturi pump 2 (the small opening end 6 of the Venturi pump).

In addition, because the flying speed of the high-speed aircraft is high, a large amount of air is used for carrying water drops to spray on the outer surface of the high-speed aircraft, so that the water drops can be sprayed more uniformly. When the flying speed of the high-speed aircraft is fast enough, the outer surface of the high-speed aircraft can form a water vapor ring of water drops to wrap the outer surface of the high-speed aircraft, so that the outer surface of the high-speed aircraft is fully cooled.

Although the utility model has been described in detail hereinabove by way of general description, specific embodiments and experiments, it will be apparent to those skilled in the art that many modifications and improvements can be made thereto based on the utility model. Accordingly, such modifications and improvements are intended to be within the scope of the utility model as claimed.

Claims

1. A rapid cooling device arranged on the surface layer of a high-speed aircraft is characterized by comprising a Venturi pump (2) arranged on the surface layer of the high-speed aircraft, wherein one end of the Venturi pump (2) is a large opening, the other end of the Venturi pump is a small opening, and the large opening end (3) of the Venturi pump faces the tip end of the high-speed aircraft; a suction pipe (4) is arranged in the middle of the Venturi pump (2) and is connected with a solid water storage; a one-way valve (5) is arranged between the suction pipe (4) and the solid water storage.

2. A rapid cooling device according to claim 1, characterised in that the venturi pump (2) is mounted in a vertical direction coinciding with the air flow.

3. The rapid cooling device according to claim 1, wherein the number of the Venturi pumps (2) is multiple, and the Venturi pumps are uniformly installed on the surface layer of the high-speed aircraft.

4. A rapid cooling device according to claim 1, characterised in that the suction pipe (4) is arranged in the vertically upper middle part of the venturi pump (2).

5. A rapid cooling device according to claim 1, characterised in that the small end of the venturi pump (2) is a downwardly depending jet.

6. The rapid cooling device according to any one of claims 1 to 5, wherein the high-speed aircraft is an early warning machine or a precisely guided remote air-ground missile.