Heat dissipation system and control method thereof, high-altitude high-speed aircraft

Abstract

This invention discloses a heat dissipation system and its control method, as well as a high-altitude, high-speed aircraft. It belongs to the fields of thermal protection and heat pipe technology. The heat dissipation system includes a single-phase heat storage circuit, a heat pump heat dissipation circuit, and an auxiliary heat sink module. The single-phase heat storage circuit includes a connected heat-absorbing cold plate and a liquid storage tank. The heat-absorbing cold plate absorbs heat emitted by the heat-generating equipment, and the liquid storage tank absorbs and stores heat from the medium in the first pipeline. The evaporator of the heat pump heat dissipation circuit absorbs heat from the medium in the first pipeline, and the condenser of the heat pump heat dissipation circuit releases heat from the heat pump heat dissipation circuit. The auxiliary heat sink module includes a liquid storage tank, an evaporation chamber, and a nozzle located in the evaporation chamber and connected to the liquid storage tank. Part of the piping of the heat pump heat dissipation circuit is located within the evaporation chamber, and the nozzle is used to spray working fluid into the evaporation chamber. The purpose of this invention is to provide a heat dissipation system and its control method, as well as a high-altitude, high-speed aircraft, with good heat dissipation performance, suitable for heat dissipation of high-power equipment.

Description

Technical Field

[0001] This invention relates to the fields of thermal protection and heat pipe technology, and in particular to a heat dissipation system and its control method, and a high-altitude, high-speed aircraft. Background Technology

[0002] With the development of high-altitude, high-speed aircraft, these vehicles need to activate high-power equipment in a short period of time when performing missions, resulting in extremely high instantaneous heat dissipation requirements. For example, radar is a high-power device in high-altitude, high-speed aircraft, with extremely high power density when activated. The quality of heat dissipation technology will directly affect the working status, performance, and lifespan of such electronic equipment.

[0003] In existing technologies, the cooling methods for high-power equipment in high-altitude, high-speed aircraft are typically natural cooling or forced air cooling. Natural cooling utilizes heat conduction, natural convection, and radiation for heat dissipation, requiring no auxiliary equipment; only the design or selection of necessary heat sinks and some measures to enhance natural cooling are needed. Forced air cooling, compared to natural cooling, adds cooling fans to force convection cooling of the equipment. Forced air cooling is more advantageous for small to medium power electronic devices, but it cannot meet the heat dissipation requirements of high-power equipment.

[0004] Therefore, there is an urgent need for a heat dissipation system suitable for high-power equipment and high-altitude, high-speed aircraft. Summary of the Invention

[0005] The purpose of this invention is to provide a heat dissipation system and its control method, as well as a high-altitude, high-speed aircraft, which has a good heat dissipation effect and can be applied to the heat dissipation of high-power equipment.

[0006] Based on the above concept, the technical solution adopted by this invention is as follows:

[0007] The heat dissipation system includes:

[0008] A single-phase heat storage circuit includes a heat-absorbing cold plate and a liquid storage tank connected by a first pipeline. The heat-absorbing cold plate is used to absorb the heat emitted by the heat-generating equipment of a high-altitude, high-speed aircraft, and the liquid storage tank is used to absorb and store the heat of the medium in the first pipeline.

[0009] A heat pump heat dissipation circuit, wherein the evaporator of the heat pump heat dissipation circuit is used to absorb the heat of the medium in the first pipeline, and the condenser of the heat pump heat dissipation circuit is used to release the heat in the heat pump heat dissipation circuit.

[0010] An auxiliary heat sink module includes a liquid storage tank, an evaporation chamber, and a nozzle located in the evaporation chamber and connected to the liquid storage tank. A portion of the heat pump exhaust circuit is located within the evaporation chamber. The nozzle is used to inject working fluid into the evaporation chamber to absorb the heat from the portion of the heat pump exhaust circuit located within the evaporation chamber.

[0011] Optionally, the condensation assembly includes a fuel heat exchanger and a ram air heat exchanger. The fuel heat exchanger exchanges heat with the fuel circuit of the high-altitude, high-speed aircraft, and the ram air heat exchanger removes heat through the ram air introduced by the high-altitude, high-speed aircraft.

[0012] Optionally, the evaporator and the fuel heat exchanger are plate heat exchangers, the heat-absorbing cold plate is an aluminum alloy cold plate or a copper cold plate, and the stamped air heat exchanger is a tube-fin heat exchanger.

[0013] Optionally, the auxiliary heat sink module further includes an evaporation cold plate, which covers part of the pipeline of the heat pump exhaust circuit located in the evaporation chamber.

[0014] Optionally, the single-phase heat storage circuit further includes a heater, which is installed inside the liquid storage tank and used to heat the liquid in the liquid storage tank.

[0015] Optionally, the medium in the single-phase heat storage circuit is an aqueous solution of ethylene glycol with a mass concentration of 15-25%.

[0016] Optionally, the liquid in the storage tank is ammonia water with a concentration of 25-30%.

[0017] Optionally, the heat pump heat dissipation circuit further includes a compressor and an expansion valve, with the evaporator, the compressor, the condenser assembly, and the expansion valve arranged in sequence.

[0018] A control method for a heat dissipation system, used to control the aforementioned heat dissipation system, includes the following steps:

[0019] S1. Determine whether the heating device of the high-altitude, high-speed aircraft is activated. If yes, proceed to step S2; otherwise, proceed to step S3.

[0020] S2. Control both the single-phase heat storage circuit and the heat pump heat exhaust circuit to enter the first power mode, and execute step S4;

[0021] S3. Control the single-phase heat storage circuit and the heat pump heat exhaust circuit to start and enter the second power mode. The power of the second power mode is less than the power of the first power mode. After a preset time, execute step S1.

[0022] S4. When the liquid temperature in the storage tank reaches the upper temperature threshold, the auxiliary heat sink module is activated, so that the working fluid in the storage tank is atomized through the nozzle and sprayed into the evaporation chamber to absorb the heat of part of the pipeline of the heat pump exhaust circuit located in the evaporation chamber.

[0023] S5. When the liquid temperature in the storage tank drops to the lower limit threshold or the heating device stops working, the auxiliary heat sink module is turned off.

[0024] A high-altitude, high-speed aircraft includes a heat-generating device and the aforementioned heat dissipation system, wherein the heat-absorbing cold plate is used to absorb the heat emitted by the heat-generating device.

[0025] The heat dissipation system and control method proposed in this invention, as well as the high-altitude, high-speed aircraft, have at least the following beneficial effects:

[0026] The system directly absorbs the heat emitted by the high-altitude, high-speed aircraft's heat-generating equipment through a single-phase heat storage circuit, absorbs the heat in the single-phase heat storage circuit through a heat pump exhaust circuit, and absorbs the heat in the heat pump exhaust circuit through an auxiliary heat sink module. This allows the heat emitted by the heat-generating equipment to be absorbed by multiple circuits. Compared with natural cooling, the heat dissipation system has a higher heat dissipation capacity, which can meet the heat dissipation requirements of high-power equipment and ensure the normal operation of the heat-generating equipment. Attached Figure Description

[0027] Figure 1 This is a schematic diagram of the heat dissipation system provided in an embodiment of the present invention;

[0028] Figure 2 This is a control flowchart of the heat dissipation system provided in an embodiment of the present invention.

[0029] In the picture:

[0030] 1. Single-phase heat storage circuit; 11. First pipeline; 12. Heat-absorbing cold plate; 13. Liquid storage tank;

[0031] 2. Heat pump exhaust circuit; 21. Evaporator; 22. Condensation assembly; 221. Fuel oil heat exchanger; 222. Pressurized air heat exchanger; 23. Compressor; 24. Expansion valve;

[0032] 3. Auxiliary heat sink module; 31. Liquid storage tank; 32. Evaporation chamber; 33. Nozzle; 34. Evaporation cooling plate;

[0033] 10. Heating equipment;

[0034] 100. Fuel circuit; 200. Ram air. Detailed Implementation

[0035] To make the technical problems solved by the present invention, the technical solutions adopted, and the technical effects achieved clearer, the technical solutions of the present invention will be further described below in conjunction with the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are merely for explaining the present invention and are not intended to limit the present invention. Furthermore, it should be noted that, for ease of description, only the parts related to the present invention are shown in the accompanying drawings, not all of them.

[0036] In the description of this invention, unless otherwise explicitly specified and limited, the terms "connected," "linked," and "fixed" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0037] In this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, "above," "over," and "on top" of the second feature includes the first feature directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature includes the first feature directly below or diagonally below the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.

[0038] In the description of this embodiment, the terms "upper," "lower," "right," etc., refer to the orientation or positional relationship shown in the accompanying drawings. They are used only for ease of description and simplification of operation, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the present invention. In addition, the terms "first" and "second" are used only for distinction in description and have no special meaning.

[0039] Example 1

[0040] This embodiment provides a heat dissipation system with good heat dissipation effect, suitable for heat dissipation of high-power equipment. It should be noted that the heat dissipation system provided in this embodiment is suitable for heat dissipation of high-power equipment for short periods, exhibiting high heat dissipation efficiency and good heat dissipation effect.

[0041] like Figure 1 As shown, the heat dissipation system includes a single-phase heat storage circuit 1, a heat pump heat dissipation circuit 2, and an auxiliary heat sink module 3.

[0042] The single-phase heat storage circuit 1 is used to directly absorb the heat emitted by the heating equipment of the high-altitude, high-speed aircraft. Specifically, the single-phase heat storage circuit 1 includes a heat-absorbing cold plate 12 and a liquid storage tank 13 connected by a first pipeline 11. The heat-absorbing cold plate 12 is used to directly absorb the heat emitted by the heating equipment 10. In some embodiments, the heat-absorbing cold plate 12 is close to or in direct contact with the heating equipment 10 to better absorb the heat emitted by the heating equipment 10. A medium flows in the first pipeline 11, which absorbs the heat on the heat-absorbing cold plate 12 and then flows to the liquid storage tank 13. The liquid storage tank 13 is used to absorb and store the heat of the medium in the first pipeline 11. The heat absorbed by the liquid storage tank 13 is stored in the sensible heat of the liquid in the liquid storage tank 13. It should be noted that, as Figure 1 As shown, the single-phase heat storage circuit 1 is a loop, meaning that the outlet of the heat-absorbing cold plate 12 is connected to the inlet of the liquid storage tank 13 through the first pipe 11, and the outlet of the liquid storage tank 13 is connected to the inlet of the heat-absorbing cold plate 12 through the first pipe 11. It should also be noted that the liquid in the single-phase heat storage circuit 1 flows into the liquid storage tank 13 for heat absorption and storage, and the flow path is circulated by a pump in the circuit.

[0043] The aforementioned heat pump exhaust circuit 2 is used to absorb heat from the unidirectional heat storage circuit 1, that is, to indirectly absorb heat emitted by the heating device. Specifically, the evaporator 21 of the heat pump exhaust circuit 2 is used to absorb heat from the medium in the first pipe 11. In some embodiments, such as... Figure 1 As shown, after the medium in the first pipeline 1 absorbs heat in the heat-absorbing cold plate 12, it first passes through the evaporator 21 and then through the storage tank 13. The condenser assembly 22 of the heat pump exhaust circuit 2 is used to release the heat in the heat pump exhaust circuit 2. In some embodiments, the condenser assembly 22 can release heat to the cooling system of a high-altitude, high-speed aircraft; this embodiment does not limit this. It should be noted that most of the heat of the medium in the first pipeline 11 is absorbed by the storage tank 13, and a small portion is absorbed by the heat pump exhaust circuit 2.

[0044] The auxiliary heat sink module 3 is used to absorb heat from the heat pump exhaust circuit 2, that is, to indirectly absorb the heat emitted by the heating equipment. Specifically, the auxiliary heat sink module 3 includes a liquid storage tank 31, an evaporation chamber 32, and a nozzle 33 located in the evaporation chamber 32 and connected to the liquid storage tank 31. The liquid storage tank 31 is used to store the working fluid. The working fluid in the liquid storage tank 31 is sprayed into the evaporation chamber 32 through the nozzle 33 and evaporates to absorb heat. Part of the piping of the heat pump exhaust circuit 2 is located in the evaporation chamber 32. The nozzle 33 is used to spray the working fluid into the evaporation chamber 32 to absorb the heat of part of the piping of the heat pump exhaust circuit 2 located in the evaporation chamber 32. This allows the heat in the heat pump exhaust circuit 2 to be released not only through the condenser assembly 22, but also through the auxiliary heat sink module 3, improving the heat release effect. This results in a lower temperature of the medium in the evaporator 21 of the heat pump exhaust circuit 2, thereby improving the heat exchange efficiency in the evaporator 21. It should be noted that when the liquid temperature in the storage tank 13 reaches the upper temperature threshold, the auxiliary heat sink module 3 is activated to assist the heat pump exhaust circuit 2 in absorbing the heat emitted by the heating device 10, so as to prevent the storage tank 13 from overheating.

[0045] The heat dissipation system provided in this embodiment directly absorbs the heat emitted by the heat-generating device 10 of the high-altitude, high-speed aircraft through a single-phase heat storage circuit 1, absorbs the heat in the single-phase heat storage circuit 1 through a heat pump heat exhaust circuit 2, and absorbs the heat in the heat pump heat exhaust circuit 2 through an auxiliary heat sink module 3. This allows the heat emitted by the heat-generating device 10 to be absorbed by multiple circuits. Compared with natural cooling, the heat dissipation system has a higher heat dissipation capacity, which can meet the heat dissipation requirements of high-power equipment and ensure the normal use of the heat-generating device 10.

[0046] Furthermore, the single-phase heat storage circuit 1, the heat pump exhaust circuit 2, and the auxiliary heat sink module 3 are adjusted and coordinated with each other to improve the flexibility of the heat dissipation system for different heat dissipation conditions. The heat pump exhaust circuit 2 connects to multiple different heat sinks, realizing full utilization of available cold sources.

[0047] In addition, the heat dissipation system provided in this embodiment can also solve the problems of high heat flux density and instantaneous heat sink in short-term high-power heat dissipation, and has broad application prospects.

[0048] Optionally, please continue to see Figure 1The condenser assembly 22 includes a fuel heat exchanger 221 and a ram air heat exchanger 222. The fuel heat exchanger 221 exchanges heat with the fuel circuit 100 of the high-altitude, high-speed aircraft; that is, a portion of the heat in the heat pump exhaust circuit 2 is released into the fuel circuit 100 through the fuel heat exchanger 221. The fuel circuit 100 is the cold source in the high-altitude, high-speed aircraft and can absorb heat. The ram air heat exchanger 222 removes heat through the ram air 200 introduced by the high-altitude, high-speed aircraft; that is, another portion of the heat in the heat pump exhaust circuit 2 is released into the cooler ram air 200 through the ram air heat exchanger 222. Components such as the compressor in the high-altitude, high-speed aircraft can generate cooler ram air 200, which is blown onto the ram air heat exchanger 222, removing heat from it.

[0049] Optionally, in this embodiment, the evaporator 21 and the fuel oil heat exchanger 221 are plate heat exchangers to achieve better heat dissipation. The heat-absorbing cold plate 12 is an aluminum alloy cold plate or a copper cold plate to achieve better heat absorption. More specifically, the heat-absorbing cold plate 12 adopts a micro-channel aluminum alloy cold plate or a copper cold plate to improve its convective heat dissipation efficiency. The ram air heat exchanger 222 is a tube-fin heat exchanger, which has a better heat exchange effect in gas-liquid heat exchange.

[0050] Optionally, such as Figure 1 As shown, the auxiliary heat sink module 3 also includes an evaporator plate 34, which covers a portion of the piping of the heat pump exhaust circuit 2 located within the evaporation chamber 32. The nozzle 33 sprays the working fluid onto the evaporator plate 34, where it evaporates and absorbs heat, causing the temperature of the evaporator plate 34 to decrease and absorb heat from a portion of the piping of the heat pump exhaust circuit 2. In this embodiment, the auxiliary heat sink module 3 is located downstream of the condenser assembly 22, and the working fluid passing through the auxiliary heat sink module 3 directly enters the evaporator 21 for heat absorption. Optionally, the evaporator plate 34 is an aluminum alloy finned plate.

[0051] In this embodiment, the single-phase heat storage circuit 1 also includes a heater (not shown in the figure). The heater is installed inside the liquid storage tank 13 and is used to heat the liquid in the liquid storage tank 13 to prevent the liquid in the liquid storage tank 13 from freezing in a low-temperature working environment, thus solving the problem of equipment damage caused by freezing in the single-phase heat storage circuit 1. In this embodiment, when the temperature of the medium in the single-phase heat storage circuit 1 is below -5°C, the heater is started, and the pump driving the medium flowing in the first pipeline 11 is operated at low power; when the temperature of the medium in the single-phase heat storage circuit 1 rises to 0°C, the heater is stopped.

[0052] Optionally, the medium in the single-phase heat storage circuit 1 is an ethylene glycol aqueous solution with a mass concentration of 15-25%. Preferably, the concentration of the ethylene glycol aqueous solution is 20%, at which point the freezing point of the ethylene glycol aqueous solution is approximately -10°C. By using an ethylene glycol aqueous solution in the single-phase heat storage circuit 1, the freezing point is lowered, thereby reducing the probability of freezing.

[0053] In some embodiments, the liquid in the storage tank 31 is ammonia water with a concentration of 25-30%. Using ammonia water as an auxiliary heat sink makes the auxiliary heat sink module 3 simple and reliable, eliminates the need for anti-icing measures, has high latent heat, and a small carrying capacity. Furthermore, the auxiliary heat sink module utilizes liquid flash evaporation technology, effectively utilizing the latent heat of phase change of the liquid and improving heat dissipation capacity. Preferably, the concentration of ammonia water is 28%, and its freezing point is around -70°C, ensuring that it will not freeze during missions. Simultaneously, the saturation pressure of ammonia water is much higher than that of water, which can improve its evaporation efficiency and extend the operational altitude range of high-altitude, high-speed aircraft.

[0054] In this embodiment, the heat pump heat dissipation circuit 2 further includes a compressor 23 and an expansion valve 24. The evaporator 21, compressor 23, condenser assembly 22, and expansion valve 24 are arranged in sequence, and the expansion valve 24 is connected to the evaporator 21 through a pipeline to form a circuit. The working fluid in the heat pump heat dissipation circuit 2 is R134a.

[0055] This embodiment proposes a system that combines convection cooling and heat storage via a single-phase heat storage circuit 1, with heat discharged to the fuel circuit 100 and ram air 200 via a heat pump exhaust circuit 2, and flash vapor spray as an auxiliary heat sink module 3 when the heat sink is insufficient. This addresses the low cooling capacity of traditional natural cooling and forced air cooling solutions, as well as the inability of traditional single-phase liquid cooling to handle high heat flux density and instantaneous heat sink issues in short-term high-power heat dissipation.

[0056] Example 2

[0057] This embodiment provides a high-altitude, high-speed aircraft, including a heat-generating device 10 and the heat dissipation system described in Embodiment 1. The heat-absorbing cold plate 12 is located near or in contact with the heat-generating device 10 and is used to absorb the heat emitted by the heat-generating device 10.

[0058] Example 3

[0059] This embodiment provides a control method for a heat dissipation system, used to control the heat dissipation system in Embodiment 1, such as... Figure 2 As shown, the control method of the heat dissipation system includes the following steps:

[0060] S1. Determine whether the heating device 10 of the high-altitude, high-speed aircraft is activated. If yes, proceed to step S2; otherwise, proceed to step S3.

[0061] The heat-generating device 10 generates a large amount of heat after startup, which is a short-term high-power device requiring high-temperature cooling, thus necessitating stringent heat dissipation requirements. In this embodiment, step S1 can be executed by the controller within the high-altitude, high-speed aircraft.

[0062] S2. Control both the single-phase heat storage circuit 1 and the heat pump exhaust circuit 2 to enter the first power mode and execute step S4.

[0063] When the heating device 10 is started, both the single-phase heat storage circuit 1 and the heat pump exhaust circuit 2 are started and enter the first power mode. This first power mode can be understood as a higher power mode, that is, the power of both the single-phase heat storage circuit 1 and the heat pump exhaust circuit 2 is higher. Specifically, the power of the pump in the single-phase heat storage circuit 1 and the power of the pump in the heat pump exhaust circuit 2 are higher, which makes the flow rate of the medium in the pipeline faster.

[0064] The single-phase heat storage circuit 1 uses the heat-absorbing cold plate 12 to quickly remove the waste heat of the heating device 10. Part of it is transferred to the heat pump exhaust circuit 2 through the evaporator 21, and then released by the fuel heat exchanger 221 and the ram air heat exchanger 222 in the heat pump exhaust circuit 2. The majority of the rest is stored in the sensible heat of the working fluid in the liquid storage tank 13.

[0065] S3. Control the start of single-phase heat storage circuit 1 and heat pump exhaust circuit 2 and enter the second power mode. The power of the second power mode is less than the power of the first power mode. After a preset time, execute step S1.

[0066] When it is determined that the heat-generating equipment is not started, the heat dissipation requirement is low. At this time, the single-phase heat storage circuit 1 and the heat pump heat exhaust circuit 2 are started and enter the second power mode. The second power mode can be understood as a low power mode, that is, the single-phase heat storage circuit 1 and the heat pump heat exhaust circuit 2 operate at low power. The heat pump heat exhaust circuit 2 is used to reduce the temperature of the working fluid in the liquid storage tank 13 to a safe minimum temperature.

[0067] S4. When the liquid temperature in the storage tank 13 reaches the upper temperature threshold, the auxiliary heat sink module 3 is activated, so that the working fluid in the storage tank 31 is atomized through the nozzle 33 and sprayed into the evaporation chamber 32 to absorb the heat of part of the pipeline of the heat pump exhaust circuit 2 located in the evaporation chamber 32.

[0068] In step S4, when the liquid temperature in the storage tank 13 reaches the upper temperature threshold and the heating device 10 continues to work, the auxiliary heat sink module 3 is activated. Specifically, the control valve of the auxiliary heat sink module 3 is opened, so that the working fluid in the storage tank 31 is sprayed into the evaporation chamber 32 through the nozzle 33 and absorbs heat in the evaporation chamber 32. After the working fluid changes phase to vapor, it is discharged into the environment. In this process, the latent heat of phase change of the liquid working fluid is utilized, which greatly improves the heat exchange capacity and is suitable for the heat dissipation of high-power equipment for short periods of time, with a very good heat dissipation effect.

[0069] S5. When the liquid temperature in the storage tank 13 drops to the lower limit threshold or the heating device stops working, shut down the auxiliary heat sink module 3.

[0070] When the liquid temperature in the storage tank 13 drops to the lower limit threshold or the heating device stops working, it indicates that the heat dissipation requirement of the high-altitude high-speed aircraft is reduced. At this time, there is no need to introduce the auxiliary heat sink module 3 to ensure lower power consumption.

[0071] S6. After confirming that the heating equipment has stopped working, control both the single-phase heat storage circuit 1 and the heat pump exhaust circuit 2 to enter the second power mode.

[0072] It should be noted that after the liquid temperature in the storage tank 13 drops to the installation temperature and the heating equipment stops working, the single-phase heat storage circuit 1 and the heat pump exhaust circuit 2 are controlled to enter the second power mode until the working fluid temperature in the storage tank 13 drops to the preset temperature. The preset temperature is lower than the lower limit threshold.

[0073] The above embodiments merely illustrate the basic principles and characteristics of the present invention. The present invention is not limited to the above embodiments. Various changes and modifications can be made to the present invention without departing from its spirit and scope, and all such changes and modifications fall within the scope of the present invention as claimed. The scope of protection of the present invention is defined by the appended claims and their equivalents.

Claims

1. A heat dissipation system, characterized in that, include: A single-phase heat storage circuit (1) includes a heat-absorbing cold plate (12) and a liquid storage tank (13) connected through a first pipeline (11). The heat-absorbing cold plate (12) is used to absorb the heat emitted by the heat-generating equipment of the high-altitude high-speed aircraft, and the liquid storage tank (13) is used to absorb and store the heat of the medium in the first pipeline (11). The heat pump exhaust circuit (2) has an evaporator (21) for absorbing the heat of the medium in the first pipeline (11) and a condenser assembly (22) for releasing the heat in the heat pump exhaust circuit (2). The auxiliary heat sink module (3) includes a liquid storage tank (31), an evaporation chamber (32), and a nozzle (33) located in the evaporation chamber (32) and connected to the liquid storage tank (31). Part of the pipeline of the heat pump exhaust circuit (2) is located in the evaporation chamber (32). The nozzle (33) is used to spray working fluid into the evaporation chamber (32) to absorb the heat of part of the pipeline of the heat pump exhaust circuit (2) located in the evaporation chamber (32). The auxiliary heat sink module (3) also includes an evaporation cooling plate (34), which covers part of the pipeline of the heat pump exhaust circuit (2) located in the evaporation chamber (32); When the liquid temperature in the storage tank (13) reaches the upper temperature threshold, the auxiliary heat sink module (3) is activated to assist the heat pump exhaust circuit (2) in absorbing the heat emitted by the heating device (10); The nozzle (33) sprays the working fluid onto the evaporating plate (34) and evaporates on the evaporating plate (34), absorbing the heat on the evaporating plate (34), reducing the temperature of the evaporating plate (34), and absorbing part of the heat from the heat pump exhaust circuit (2); The auxiliary heat sink module (3) is located downstream of the condenser assembly (22).

2. The heat dissipation system according to claim 1, characterized in that, The condensation assembly (22) includes a fuel heat exchanger (221) and a ram air heat exchanger (222). The fuel heat exchanger (221) exchanges heat with the fuel circuit of the high-altitude high-speed aircraft, and the ram air heat exchanger (222) removes heat through the ram air introduced by the high-altitude high-speed aircraft.

3. The heat dissipation system according to claim 2, characterized in that, The evaporator (21) and the fuel oil heat exchanger (221) are plate heat exchangers, the heat-absorbing cold plate (12) is an aluminum alloy cold plate or a copper cold plate, and the stamped air heat exchanger (222) is a tube-fin heat exchanger.

4. The heat dissipation system according to claim 1, characterized in that, The single-phase heat storage circuit (1) also includes a heater, which is installed in the liquid storage tank (13) and is used to heat the liquid in the liquid storage tank (13).

5. The heat dissipation system according to any one of claims 1-4, characterized in that, The medium in the single-phase heat storage circuit (1) is an aqueous solution of ethylene glycol with a mass concentration of 15-25%.

6. The heat dissipation system according to any one of claims 1-4, characterized in that, The liquid in the storage tank (31) is ammonia water with a concentration of 25-30%.

7. The heat dissipation system according to any one of claims 1-4, characterized in that, The heat pump exhaust circuit (2) also includes a compressor (23) and an expansion valve (24), with the evaporator (21), the compressor (23), the condenser assembly (22) and the expansion valve (24) arranged in sequence.

8. A method for controlling a heat dissipation system, used to control the heat dissipation system according to any one of claims 1-7, characterized in that, Includes the following steps: S1. Determine whether the heating device of the high-altitude, high-speed aircraft is activated. If yes, proceed to step S2; otherwise, proceed to step S3. S2. Control both the single-phase heat storage circuit (1) and the heat pump heat exhaust circuit (2) to enter the first power mode, and execute step S4; S3. Control the single-phase heat storage circuit (1) and the heat pump heat exhaust circuit (2) to start and enter the second power mode. The power of the second power mode is less than the power of the first power mode. After a preset time, execute step S1. S4. When the liquid temperature in the storage tank (13) reaches the upper limit threshold, the auxiliary heat sink module (3) is activated, so that the working fluid in the storage tank (31) is atomized through the nozzle (33) and sprayed into the evaporation chamber (32) to absorb the heat of part of the pipeline of the heat pump exhaust circuit (2) located in the evaporation chamber (32). S5. When the liquid temperature in the storage tank (13) drops to the lower limit threshold or the heating device stops working, the auxiliary heat sink module (3) is turned off.

9. A high-altitude, high-speed aircraft, characterized in that: Includes a heat-generating device (10) and a heat dissipation system according to any one of claims 1-7, wherein the heat-absorbing cold plate (12) is used to absorb the heat emitted by the heat-generating device (10).

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