Wide-temperature-range strong pre-cooling system, aircraft and air inlet pre-cooling control method

Abstract

The invention discloses a wide-temperature-range strong pre-cooling system, an aircraft and an air inlet pre-cooling control method, and the wide-temperature-range strong pre-cooling system comprises a cooling unit; the cooling unit comprises a capillary tube bundle, and cooling water is pre-stored in the capillary tube bundle to form a pulsating heat tube; the liquid metal supply unit can be communicated with the cooling unit; the gas path unit can be communicated with the cooling unit; the water spraying unit can be communicated with the cooling unit; the air inlet cooling device meets the stamping air inlet cooling requirement of a wide speed range.

Description

Technical Field

[0001] The present invention relates to the field of mechanical automation technology, and in particular to a wide-temperature range strong pre-cooling system, an aircraft, and an intake air pre-cooling control method. Background Art

[0002] The high-speed development of aircraft has extremely important military and civilian value. Aviation turbine engines, characterized by horizontal takeoff and landing, reusability, and high specific impulse, are the mainstream aviation engine solution. However, the aerodynamic heating effect typically limits the flight limit of modern advanced aviation turbine engines to Mach 2.5. To further increase the flight speed of turbines, one of the main solutions is to use a heat exchanger structure to cool the ram air intake. This reduces the temperature of the turbine inlet airflow, offsetting the increase in intake air temperature caused by the aerodynamic heating effect during high-speed flight, and allowing the turbine to fly at higher speeds.

[0003] The working fluid uses liquids with strong heat absorption capacity and high density over a wide temperature range, primarily liquid metals such as sodium-potassium alloys, gallium-indium alloys, mercury, lithium, and lead-bismuth alloys. While excellent at high temperatures (>500K), cooling efficiency decreases at low temperatures (300-500K) due to the small temperature difference. If this technical solution is used alone, the heat exchange system will inevitably have significant redundancy in the high-temperature range.

[0004] The existing technology has poor adaptability to a wide speed range of ram air cooling. Summary of the Invention

[0005] The purpose of the present invention is to provide a wide temperature range strong pre-cooling system, aircraft and intake air pre-cooling control method to address the deficiencies in the prior art, which can adapt to the ram air intake cooling requirements in a wide speed range.

[0006] The present invention provides a wide temperature range strong pre-cooling system, comprising:

[0007] Cooling unit; the cooling unit includes a capillary tube bundle, in which cooling water is pre-stored to form a pulsating heat pipe;

[0008] a liquid metal supply unit capable of communicating with the cooling unit;

[0009] an air path unit capable of communicating with the cooling unit and a water spray unit capable of communicating with the cooling unit;

[0010] The wide temperature range strong pre-cooling system has at least the following three cooling states:

[0011] In the first cooling state, the cooling water in the cooling unit forms a continuous pulsating flow in the capillary bundle for cooling; in the second cooling state, the air path unit and the water spray unit are both connected to the cooling unit to spray the water in the cooling unit to the area to be dissipated heat; in the third cooling state, the liquid metal supply unit is connected to the cooling unit after the internal moisture is discharged, and the liquid metal circulates between the cooling unit and the liquid metal supply unit for cooling.

[0012] In the wide temperature range strong pre-cooling system as described above, optionally, the cold end of the capillary tube bundle is located in the fuel tank, and the hot end of the capillary tube bundle is located at a location where heat is to be dissipated; and the inner diameter of the capillary tubes on the capillary tube bundle is 0.8-2 mm.

[0013] In the wide temperature range strong pre-cooling system as described above, optionally, the gas circuit unit includes a first control valve and an air bleed pipe; one end of the air bleed pipe is connected to the capillary tube bundle through the first control valve, and the other end of the air bleed pipe is connected to a high-pressure gas source;

[0014] The water spray unit includes a second control valve and a spray head, and the spray head is connected to the capillary tube bundle through the second control valve;

[0015] In the second cooling state, the air bleed pipe, the capillary tube bundle, and the water spray unit are connected to form a passage so that water in the cooling unit is discharged through the water spray unit.

[0016] The wide temperature range strong pre-cooling system as described above, wherein, optionally, the liquid metal supply unit includes a liquid metal storage tank, a liquid metal pump, a liquid metal pipeline and a third control valve;

[0017] The liquid metal storage tank and the liquid metal pump are connected in series to the liquid metal pipeline, and the two ends of the liquid metal pipeline are respectively connected to the capillary tube bundle through the two third control valves; so that the liquid metal storage tank, the liquid metal pump and the capillary tube bundle constitute a liquid metal circuit.

[0018] In the wide temperature range strong pre-cooling system as described above, optionally, the liquid metal is a gallium indium tin alloy.

[0019] As described above, the wide temperature range strong pre-cooling system, wherein, optionally, the wide temperature range strong pre-cooling system is used to be in a first cooling state before the temperature of the area to be dissipated reaches the set temperature for the first time; when the temperature of the area to be dissipated reaches the set temperature for the first time, it is adjusted to a second cooling state; and after the second cooling state ends, it is adjusted to a third cooling state.

[0020] In the wide temperature range strong pre-cooling system as described above, optionally, the cooling water is deionized water, and at room temperature, the liquid filling rate of the capillary bundle is 50% to 70%.

[0021] According to another aspect of the present invention, an aircraft is further provided, comprising the wide temperature range strong pre-cooling system as described above, wherein the cold end of the capillary tube bundle is located in the fuel tank of the aircraft;

[0022] The air path unit is connected to the compressed air chamber of the engine of the aircraft.

[0023] According to another aspect of the present invention, an intake air precooling control method is also proposed, which includes the following steps:

[0024] S1, before the switching condition is first met, a pulsating heat pipe with deionized water as the medium is used to dissipate heat from the engine intake duct;

[0025] S2, when the switching condition is first met, using high-pressure gas to spray the deionized water in the pulsating heat pipe into the air inlet duct;

[0026] S3, after the deionized water in the pulsating heat pipe is discharged, liquid metal is circulated and pumped into the pulsating heat pipe to dissipate heat through the circulation of the liquid metal.

[0027] In the intake air pre-cooling control method as described above, preferably, the switching condition is that the intake air temperature is not less than 500K or the flight speed is not less than Mach 2.6.

[0028] Compared with the prior art, the present invention has a variety of different cooling methods, namely, in the first cooling state, the air is cooled by using a pulsating heat pipe; in the second cooling state, the air is cooled by spraying cooling water into the air flow; in the third cooling state, the heat is dissipated by circulating liquid metal. The three cooling states share the capillary bundle, and the same set of heat exchange structure is used to solve the problem that the prior art cannot take into account both low-temperature high-efficiency phase change heat transfer and high-temperature liquid metal strong convection cooling. The present invention also has the following effects: (1) Seamless coverage of a wide temperature range: 300-900K full-speed heat transfer has a high heat transfer density; at the same time, the two modes of pre-cooling technology, such as pulsating heat pipes and liquid metal active control, share a set of heat exchange systems, there is no design redundancy, and the size and weight can be greatly reduced. (2) High-efficiency heat-mass synergy: By using engine bleed air and local materials, the pulsating heat pipe evaporation temperature can be accurately controlled by dynamic pressure regulation, and water vapor can be sprayed into the mainstream to assist in cooling during the conversion. There is no material redundancy, and the overall energy efficiency is improved. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Figure 1 It is an axonometric view of the overall structure of the present invention;

[0030] Figure 2 2. It is a structural schematic diagram of the wide temperature range strong pre-cooling system proposed by the present invention in the first cooling state;

[0031] Figure 3 2 is a schematic structural diagram of the wide temperature range strong pre-cooling system proposed by the present invention in the third cooling state;

[0032] Figure 4 It is a flowchart of the steps of the method proposed by the present invention.

[0033] Description of reference numerals:

[0034] 1-cooling unit, 2-liquid metal supply unit, 3-gas circuit unit, 4-water spray unit;

[0035] 11 - capillary bundles;

[0036] 21 - liquid metal storage tank, 22 - liquid metal pump, 23 - liquid metal pipeline, 24 - third control valve;

[0037] 31 - first control valve, 32 - air bleed pipe;

[0038] 41 - second control valve, 42 - nozzle. DETAILED DESCRIPTION

[0039] The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and are not to be construed as limiting the present invention.

[0040] In response to the problems raised in the background technology, the present disclosure proposes the following embodiments to solve them.

[0041] Example 1

[0042] Please refer to Figures 1 to 3 This embodiment proposes a wide temperature range strong pre-cooling system, which includes: a cooling unit 1, a liquid metal supply unit 2, an air circuit unit 3 and a water spray unit 4.

[0043] The cooling unit 1 comprises a capillary tube bundle 11, which is pre-filled with cooling water to form a pulsating heat pipe. A pulsating heat pipe (PHP) is a highly efficient heat transfer device based on the principles of two-phase flow and self-oscillation. Its basic structure is a capillary loop, typically consisting of a serpentine or closed loop of slender, curved capillaries. The interior is partially filled with a working fluid, forming a "liquid-gas plug" structure with alternating liquid slugs and bubbles. At the hot end, when heated, localized working fluid evaporates, causing bubbles to expand, resulting in increased pressure and pushing adjacent liquid slugs toward the cooling end. At the cold end, after heat is released, the bubbles contract or condense into liquid, locally reducing pressure and causing the liquid slugs to flow in the opposite direction, forming self-oscillations. The alternating pressure difference between the heating and cooling ends triggers a continuous pulsating flow of the working fluid within the capillary tube. As the working fluid absorbs heat and evaporates in the evaporation section and releases heat and condenses in the condensation section, heat transfer efficiency is significantly improved through latent heat transfer. The oscillation of the liquid slugs and the compression and expansion of the bubbles further enhance heat transfer, creating a "heat-driven pump" effect. It is possible to explore applications in strong pre-cooling environments. The application temperature range of pulsating heat pipes mainly depends on the selection of working fluids, structural design, and environmental conditions. Since the phase change characteristics of the working fluid directly determine its operating temperature, by replacing the working fluid and optimizing the design, the pulsating heat pipe can adapt to a variety of environments from ultra-low temperature to high temperature. Among them, water has extremely high latent heat of phase change. The PHP of water working fluid uses the latent heat of phase change (2257kJ / kg) to achieve efficient heat transfer in the low temperature range below 500K, and transmits high heat flux density in a small space. However, when it exceeds 500K, it is easy to cause problems such as hydrogen embrittlement corrosion.

[0044] The liquid metal supply unit 2 is connected to the cooling unit 1, and the liquid metal supply unit 2 and the cooling unit 1 are controlled by a valve so that the cooling unit 1 can be cooled alone using the principle of a pulsating heat pipe. If necessary, a loop can be formed between the liquid metal supply unit 2 and the cooling unit 1.

[0045] The gas circuit unit 3 is connected to the cooling unit 1 via a valve, which controls whether the gas circuit unit 3 and the cooling unit 1 are connected. When the gas circuit unit 3 and the cooling unit 1 are connected, gas can be injected into the cooling unit 1 through the gas circuit unit 3. The water spray unit 4 is connected to the cooling unit 1. Specifically, the water spray unit 4 can be connected to the cooling unit 1 via a valve and cooperate with the gas circuit unit 3. When high-pressure gas is introduced into the cooling unit 1 through the gas circuit unit 3, the cooling water in the cooling unit 1 is sprayed out after passing through the water spray unit 4.

[0046] The wide temperature range strong pre-cooling system has at least the following three cooling states:

[0047] In the first cooling state, the cooling water in the cooling unit 1 forms a continuous pulsating flow in the capillary bundle 11 for cooling; in the second cooling state, the air path unit 3 and the water spray unit 4 are both connected to the cooling unit 1; so as to spray the water in the cooling unit 1 to the area to be dissipated heat; in the third cooling state, the liquid metal supply unit 2 is connected to the cooling unit 1 after the internal moisture is discharged, and the liquid metal circulates between the cooling unit 1 and the liquid metal supply unit 2 for cooling.

[0048] In practical applications, the wide temperature range strong pre-cooling system proposed in the present disclosure can be applied to aircraft engines. Taking its use on aircraft engines on aircraft as an example, before the flight takes off, deionized water is injected into the cooling unit 1 as the working fluid in the first cooling state. Liquid metal is added to the liquid metal supply unit 2. When the aircraft takes off, the wide temperature range strong pre-cooling system is controlled in the first cooling state; the intake air is cooled by a pulsating heat pipe; after the flight speed of the aircraft reaches Mach 2.6 for the first time, or the intake air temperature reaches 500K for the first time, the wide temperature range strong pre-cooling system is switched to the second cooling state, and the high-pressure gas on the aircraft is used to discharge the cooling water in the cooling unit 1. The discharged cooling water can be directly sprayed into the air inlet duct to mix with the intake air flow, so as to cool the intake air flow by absorbing heat due to evaporation of water. After the cooling water in the cooling unit 1 is discharged, the valve between the gas path unit 3 and the cooling unit 1, as well as the valve between the water spray unit 4 and the cooling unit 1 are closed, and the liquid metal supply unit 2 and the cooling unit 1 are connected to form a circulating liquid metal circuit through the liquid metal supply unit 2 and the cooling unit 1.

[0049] In practice, to ensure balanced cooling efficiency in both the first and third cooling states, the inner diameter of the capillary tubes in capillary tube bundle 11 is 0.8-2 mm. To maintain the cold end in the first cooling state and to cool the liquid metal during its circulation in the third cooling state, the cold end of capillary tube bundle 11 is located within the aircraft's fuel tank, while the hot end of capillary tube bundle 11 is located where heat is to be dissipated.

[0050] In a specific implementation, the air circuit unit 3 includes a first control valve 31 and an air bleed pipe 32; one end of the air bleed pipe 32 is connected to the capillary tube bundle 11 through the first control valve 31, and the other end of the air bleed pipe 32 is connected to a high-pressure gas source; the function of the air circuit unit 3 is to introduce high-pressure gas to discharge water in the cooling unit 1 when needed.

[0051] The water spray unit 4 includes a second control valve 41 and a nozzle 42, which is connected to the capillary tube bundle 11 via the second control valve 41. When high-pressure gas is introduced into the cooling unit 1 via the gas circuit unit 3, the cooling water within the cooling unit 1 is discharged. In practice, a redundant sealing ring (made of a ceramic-metal composite material) is installed at the liquid spray port of the nozzle 42. This ring, which can withstand temperatures of 900K and a pressure differential of 50 bar, prevents liquid metal from overflowing while venting the gas.

[0052] A graphene-boron nitride composite coating is coated on the inner wall of the capillary bundle 11 and the inner wall of the liquid metal flow channel on the liquid metal supply unit 2 to prevent cross contamination caused by water / liquid metal residue.

[0053] In the second cooling state, the air bleed pipe 32, the capillary tube bundle 11, and the water spray unit 4 are connected to form a passage, so that the water in the cooling unit 1 is discharged through the water spray unit 4. In a specific implementation, the air inlet end of the air bleed pipe 32 is connected to the compressed air chamber of the engine to facilitate the introduction of high-pressure gas.

[0054] To achieve cooling in the third cooling state, the liquid metal supply unit 2 includes a liquid metal storage tank 21, a liquid metal pump 22, a liquid metal pipeline 23, and a third control valve 24. Specifically, liquid metal is pre-stored in the liquid metal storage tank 21. The liquid metal storage tank 21 and the liquid metal pump 22 are connected in series to the liquid metal pipeline 23, and the two ends of the liquid metal pipeline 23 are connected to the capillary tube bundle 11 via two third control valves 24, so that the liquid metal storage tank 21, the liquid metal pump 22, and the capillary tube bundle 11 form a liquid metal circuit. In the third cooling state, driven by the liquid metal pump 22, the liquid metal enters the capillary tube bundle 11 from the liquid metal storage tank 21. When the liquid metal is at the hot end of the capillary tube bundle 11, it absorbs heat and cools the surrounding environment. When the liquid metal is at the cold end, it exchanges heat with the surrounding environment, releasing heat, and then returns to the liquid metal storage tank 21. In a specific implementation, the capillary tube bundle 11 may be formed by repeatedly bending a capillary tube.

[0055] In a specific implementation, the liquid metal is a gallium indium tin alloy. 68 In 22 Sn 10 , its melting point is -19℃, and the flow rate can be adjusted according to actual needs.

[0056] In a specific implementation, the wide-temperature range, strong pre-cooling system is configured to operate in a first cooling state before the temperature of the heat dissipation area first reaches the set temperature; then adjust to a second cooling state when the temperature of the heat dissipation area first reaches the set temperature; and finally adjust to a third cooling state after the second cooling state ends. The heat dissipation area, for example, could be the engine's air intake. The intake air temperature can be measured directly by a temperature sensor or obtained from a mapping between the aircraft's flight speed and the intake air temperature.

[0057] In a specific implementation, the cooling water is deionized water. At room temperature, the liquid filling rate of the capillary tube bundle 11 is 50% to 70%. This facilitates the use of the cooling water within the capillary tube bundle 11 as the working fluid of the pulsating heat pipe in the first cooling state. In the first cooling state, when the temperature of the location to be cooled reaches 373K, the first control valve 31 is controlled to open, increasing the pressure within the cooling unit 1 and raising the boiling point of the cooling water within the cooling unit 1, thus expanding the usable range of the first cooling state to 500K.

[0058] It should be noted that for capillary tubes connected end to end, in the third cooling state, the third control valve 24 can be set as a three-way valve to ensure that only one section of the capillary tube string is connected in series with the liquid metal supply unit. The length of the capillary tube connected in series with the liquid metal supply unit is determined by the positions of the two third control valves 24. In some implementations, the capillary tube can be connected in series with the liquid metal supply unit as two parallel sections.

[0059] It should be noted that the high-pressure gas source refers to a gas pressure source having a pressure greater than the internal pressure of the capillary tube bundle 11 .

[0060] Example 2

[0061] This embodiment is a specific application of embodiment 1, and the similarities are not repeated here. Only the differences are described below.

[0062] This embodiment provides an aircraft, which includes the wide temperature range strong pre-cooling system described in Example 1, wherein the cold end of the capillary tube bundle 11 is located in the fuel tank of the aircraft. The air circuit unit 3 is connected to the compressed air chamber of the aircraft engine.

[0063] Deionized water is pre-injected before takeoff, with a filling rate of 50% to 70%. In the first cooling state, deionized water is used as the working medium of the pulsating heat pipe, and liquid metal is injected into the liquid metal storage tank 21.

[0064] From takeoff until the first flight speed reaches Mach 2.6, the wide-temperature-range, intense pre-cooling system operates in its first cooling state, utilizing the pulsating heat pipe principle to cool the intake air. When the temperature at the engine air inlet approaches 373K, the pressure within the capillary bundle 11 is increased. Specifically, this is accomplished by introducing high-pressure gas through the bleed pipe 32 to raise the boiling point of the deionized water. This allows the evaporation temperature of the water in the pulsating heat pipe to match the intake air temperature, extending its operating range to 500K.

[0065] When the aircraft's flight speed reaches Mach 2.6 for the first time, the air path unit 3 and the cooling unit are connected, and the water spray unit 4 is turned on to enter the second cooling state; water is sprayed into the engine flow channel within a few seconds, using the latent heat of vaporization to assist in cooling.

[0066] At the end of the second cooling state, the liquid metal pump 22 is started to inject liquid metal, such as Ga-In-Sn alloy, at a flow rate of 100 L / min. The forced convection heat transfer coefficient reaches 8000 W / (m 2 · K); in specific implementation, the liquid metal pump 22 may be turned on when the second cooling state is about to end, as long as the second control valve 41 is closed before the liquid metal filling is completed.

[0067] In the third cooling state, the liquid metal pump is regulated so that the liquid metal flow rate increases as the temperature of the location to be cooled increases. The cooling process in this state is the same as that described in Example 1 and will not be repeated here.

[0068] Example 3

[0069] This embodiment is the control method of embodiment 1 or embodiment 2, and the similarities are not repeated here, and only the differences are described below.

[0070] Please refer to Figure 4 This embodiment proposes an intake air precooling control method, which includes the following steps:

[0071] S1, before the switching condition is first met, a pulsating heat pipe with deionized water as the medium is used to dissipate heat from the engine intake duct; in specific implementation, the switching condition can be that the aircraft's flight speed reaches 2.6 Mach for the first time, or that the aircraft's intake temperature reaches 500K for the first time.

[0072] In this step, when using a pulsating heat pipe to dissipate heat from the engine intake, when the temperature at the location where heat dissipation is required reaches 373K, high-pressure gas is introduced into the pulsating heat pipe to raise the boiling point of the deionized water in the pulsating heat pipe, thereby increasing the applicability of the pulsating heat pipe.

[0073] S2: When the switching condition is first met, high-pressure gas is used to spray the deionized water in the pulsating heat pipe into the intake duct. At this time, the second cooling state is entered, and water is sprayed into the engine flow channel within a few seconds, using the latent heat of vaporization (2000kJ / kg) to assist in cooling.

[0074] S3: After the deionized water in the pulsating heat pipe is drained, liquid metal is pumped into the pulsating heat pipe to dissipate heat through the circulating flow of the liquid metal. In practice, the liquid metal pump can be activated when the deionized water has been sprayed, or when it has not yet been sprayed, as long as the liquid metal does not spray out of the nozzle. After entering the third cooling state, the liquid metal pump is regulated so that the liquid metal flow rate increases as the heat source temperature rises.

[0075] In summary, the cooling method of the present invention can cover the pre-cooling temperature range of 300-900K.

[0076] The basic principles of the present disclosure have been described above in conjunction with specific embodiments. However, it should be noted that the advantages, strengths, and effects mentioned in this disclosure are merely illustrative and not restrictive, and should not be construed as necessarily possessed by each embodiment of the present disclosure. Furthermore, the specific details disclosed above are provided for illustrative purposes and to facilitate understanding, rather than as limitations. These details do not limit the present disclosure to necessarily being implemented using these specific details.

[0077] The block diagrams of the devices, devices, equipment, and systems involved in this disclosure are merely illustrative examples and are not intended to require or imply that they must be connected, arranged, or configured in the manner shown in the block diagrams. As will be appreciated by those skilled in the art, these devices, devices, equipment, and systems can be connected, arranged, or configured in any manner. Words such as "include," "comprise," "have," and the like are open-ended words, meaning "including but not limited to," and can be used interchangeably therewith. The words "or" and "and" used herein refer to the words "and / or" and can be used interchangeably therewith, unless the context clearly indicates otherwise. The word "such as" used herein refers to the phrase "such as but not limited to," and can be used interchangeably therewith.

[0078] Additionally, as used herein, "or" used in a list of items beginning with "at least one" indicates a separate list, so that, for example, a list of "at least one of A, B, or C" means A or B or C, or AB or AC or BC, or ABC (i.e., A and B and C). Furthermore, the word "exemplary" does not mean that the example described is preferred or better than other examples.

[0079] It should also be noted that in the system and method of the present disclosure, each component or each step can be decomposed and / or recombined. Such decomposition and / or recombination should be regarded as equivalent solutions of the present disclosure.

[0080] Various changes, substitutions, and modifications may be made to the technology described herein without departing from the teachings defined by the appended claims. Moreover, the scope of the claims of this disclosure is not limited to the specific aspects of the processes, machines, manufactures, compositions of things, means, methods, and actions described above. Currently existing or later developed processes, machines, manufactures, compositions of things, means, methods, or actions that perform substantially the same function or achieve substantially the same results as the corresponding aspects described herein may be utilized. Accordingly, the appended claims include within their scope such processes, machines, manufactures, compositions of things, means, methods, or actions.

[0081] The above description of the disclosed aspects is provided to enable any person skilled in the art to make or use the present disclosure. Various modifications to these aspects will be readily apparent to those skilled in the art, and the general principles defined herein may be applied to other aspects without departing from the scope of the present disclosure. Therefore, the present disclosure is not intended to be limited to the aspects shown herein, but rather to be accorded the widest scope consistent with the principles and novel features disclosed herein.

[0082] The above description has been provided for the purpose of illustration and description. In addition, this description is not intended to limit the embodiments of the present disclosure to the forms disclosed herein. Although a number of example aspects and embodiments have been discussed above, those skilled in the art will recognize certain variations, modifications, alterations, additions, and sub-combinations thereof.

Claims

1. A wide temperature range strong pre-cooling system, characterized by: include: A cooling unit (1); the cooling unit (1) comprises a capillary tube bundle (11), wherein cooling water is pre-stored in the capillary tube bundle (11) to form a pulsating heat pipe; a liquid metal supply unit (2) capable of communicating with the cooling unit (1); an air path unit (3) capable of communicating with the cooling unit (1) and a water spray unit (4) capable of communicating with the cooling unit (1); The wide temperature range strong pre-cooling system has at least the following three cooling states: In the first cooling state, the cooling water in the cooling unit (1) forms a continuous pulsating flow in the capillary tube bundle (11) for cooling; in the second cooling state, the gas path unit (3) and the water spray unit (4) are both connected to the cooling unit (1) so as to spray the water in the cooling unit (1) to the area to be cooled; in the third cooling state, the liquid metal supply unit (2) is connected to the cooling unit (1) after the internal water is discharged, and the liquid metal circulates between the cooling unit (1) and the liquid metal supply unit (2) for cooling.

2. The wide temperature range strong pre-cooling system according to claim 1, characterized in that: The cold end of the capillary tube bundle (11) is located in the fuel tank, and the hot end of the capillary tube bundle (11) is located at a location to be cooled. The inner diameter of the capillary tubes on the capillary tube bundle (11) is 0.8-2 mm.

3. The wide temperature range strong pre-cooling system according to claim 2, characterized in that: The air path unit (3) comprises a first control valve (31) and an air bleed pipe (32); one end of the air bleed pipe (32) is connected to the capillary tube bundle (11) via the first control valve (31), and the other end of the air bleed pipe (32) is connected to a high-pressure gas source; The water spray unit (4) comprises a second control valve (41) and a spray head (42), and the spray head (42) is connected to the capillary tube bundle (11) through the second control valve (41); In the second cooling state, the air duct (32), the capillary tube bundle (11) and the water spray unit (4) are connected to form a passage so that the water in the cooling unit (1) is discharged from the water spray unit (4).

4. The wide temperature range strong pre-cooling system according to claim 3, characterized in that: The liquid metal supply unit (2) comprises a liquid metal storage tank (21), a liquid metal pump (22), a liquid metal pipeline (23) and a third control valve (24); The liquid metal storage tank (21) and the liquid metal pump (22) are connected in series to the liquid metal pipeline (23), and the two ends of the liquid metal pipeline (23) are connected to the capillary tube bundle (11) through the two third control valves (24) respectively; so that the liquid metal storage tank (21), the liquid metal pump (22) and the capillary tube bundle (11) constitute a liquid metal circuit.

5. The wide temperature range strong pre-cooling system according to any one of claims 1 to 4, characterized in that: The liquid metal is a gallium-indium-tin alloy.

6. The wide temperature range strong pre-cooling system according to any one of claims 1 to 4, characterized in that: The wide temperature range strong pre-cooling system is used to be in a first cooling state before the temperature of the area to be dissipated reaches the set temperature for the first time; when the temperature of the area to be dissipated reaches the set temperature for the first time, it is adjusted to a second cooling state; and after the second cooling state ends, it is adjusted to a third cooling state.

7. The wide temperature range strong pre-cooling system according to any one of claims 1 to 4, characterized in that: The cooling water is deionized water. At room temperature, the liquid filling rate of the capillary bundle (11) is 50% to 70%.

8. An aircraft, characterized in that: The invention comprises the wide temperature range strong pre-cooling system according to any one of claims 1 to 7, wherein the cold end of the capillary tube bundle (11) is located in the fuel tank of the aircraft; The air circuit unit (3) is connected to the compressed air chamber of the engine of the aircraft.

9. An intake air precooling control method, characterized in that: The following steps are involved: S1, before the switching condition is first met, a pulsating heat pipe with deionized water as the medium is used to dissipate heat from the engine intake duct; S2, when the switching condition is first met, using high-pressure gas to spray the deionized water in the pulsating heat pipe into the air inlet duct; S3, after the deionized water in the pulsating heat pipe is discharged, liquid metal is circulated and pumped into the pulsating heat pipe to dissipate heat through the circulation of the liquid metal.

10. The intake air precooling control method according to claim 9, characterized in that: The switching condition is that the intake temperature is not less than 500K or the flight speed is not less than Mach 2.6.

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